EFTA00011669

el, -- MAJOR REPAIR AND ALTERATION US Department Of Tm114104/111011 (Airframe, Powerplant, Propeller, or Appliance) FOsteral Aviation Adednitrallen OM No.21200020 Exp. 541/2011 Ettoternie TM:alp Wetter Ems. For FAA Use °My INSTRUCTIONS: Pita or type all entries. See Title 14 PROT436 §43.9. Part 43 Appendix B, and AC 43.9-1 (or subsequent revision thereof) for instructIons and disposition of tNs form. This report Is required by law (49 PROT437. §44701). Failure to report can result Ina mil penally for each such violation. (49 PROT438. §46301(a)) 1. Aircraft Nationality and Registration Mark UNITED STATES / N188TS Serial No. RK-244 'make RAYTHEON AIRCRAFT COMPANY Model 400A Series 2. owner Name (As shown on registration certificate) THORAIR LLC Address As shown on registration certificate) Address 04. [VICTIM NAME REDACTED] re 44871-2218 cam/ UNITED STATES 3. For FAA Use Only 4. Type 5. Unit Identification Repair Alteration Untt Make Model Serial No. ril I I [VICTIM NAME REDACTED] (As described in Item I above) RK.244 K POWERPLANT K n [VICTIM NAME REDACTED] Type Manufacturer I Conformity Statement A. Agency's Name and Address B. Kind of Agency in Coastal'. Aviation LLC U. S. Genic/mad Mechanic I Idanufaclurer Meese Foreign Cerbhcated Ilechanic C. Certificate No. cis CLEVELAND sys OH 7 Conticaled Repair Station ai 44143 c.,,,,,,,, USA Certificated Maintenance organization CRS#WC7R346J D. I certify That the repair and/or alteration made to the una(s have been made In accordance with the requirements of furnished herein is true and Identified Part In Item 5 above and described on the 43 of the U.S. Federal Aviation Regulations reverse or attachments hereto and That the Information Extended range fuel per 14 PROT439 Part 43 App. B 10/04/2019 umTotemic. Pursuant to the authority g Administrator of the Federal i, rsons spec ' • .. , t e un Administreti• ' and is n leg I In Item 5 Approved vial nspected in the manner prescribed by the Rejected BY - Manufacturer Maintenance Organization - Persons Approved by Canadian Department of Transom' ____j FM RI Standards Inspector FM Designee MI Repair Station pectIon Authorization Other (Specify) Certificate or Desi nation No. CRS# WC7R346J Signature/Da f Author ed Individual 10/04/2019 FAA Form 337 (10/06) Page I PROT0 NOTICE Weight and balance or operating limitation changes shall be entered In the appropriate aircraft record. M alteration must be compatible with all previous alterations to assure continued conformity with the applicable airworthiness requirements. S. Description of Work Accomplished (Il more space is moulted. attach additional sheets. Identify mitt steal? nationally end registratIon m** end date work completed) UNITED STATESIMOSTS mov2019 Nationality and RegistraMn Mark Date Engine Inlet Rivet Repair Installed blind rivets in place of the damaged solid rivets on the lip of the right hand engine inlet forebody assembly part number 541000-004, serial number R0010, In accordance with nextant aerospace engineering order NT-EO-1118-31 rev IR dated 11/29/2018 with FM form 8110-3 dated 11/30/2018. Instructions for Continued Airworthiness: Follow the maintenance inspection practices in the aircraft maintenance manual. Inspection intervals shall remain as indicated in the aircraft maintenance manual or operators approved inspection program as appropriate. Weight and Balance unaffected. Reference Constant Aviation work order CCM-3160 END ­ditional Sheets Arc Attached Pagc 2 PROT1 U.S. DEPARTMENT OF TRANSPORTAllON FEDERAL AVIATION ADMINISTRATION STATEMENT OF COMPLIANCE WITH AIRWORTHINESS STANDARDS 1. DATE November 30, 2018 AIRCRAFT OR AIRCRAFT COMPONENT IDENTIFICATION 2. MANE Textron Aviation 3. MODEL NO. N541000-004 4. TYPE Mkorst &*e. Propeller, ea) Forebody Assy S. NAME OF APPLICANT Nextant Aerospace LLC Cleveland, Ohio LIST OF DATA SLREIffla NT-EO-1118-31 Rev. IR November 29, 2018 Engine Inlet Rivet Repair. Notes: 1) The structural aspects only of the above listed data are approved herein. This approval Is only for the engineering data. It Indicates the data listed above demonstrates compliance only vAth the regulations specified by paragraph and subparagraph listed below as 'Applicable Requirements." 2) This form constitutes FAA approval of all the engineering data necessary for substantiation of compliance to necessary requirements for the entire repair. e. PURPOSE OF DATA: Engineering data to support repair procedure for Textron 400A Forebody May PIN N541000-004, SRN R0010 under Nextant Aerospace Work Order No.10585.1.1. 9. APPLICABLE REQUIREMENTS (UM speckle sections) PROT440 Title 14 Part 25.301(25-23), 25.303(25-23], 25.305(a)(bUcX25-23), 25.307(a125-231, 25.801[25-00), 25.603(aXbXc)(25-38), 25.605(a){25-00), 25.807(25-23), 25.809(eXbX25-00], 25.811(25-2n 25.813(aXbXcX25-00], 25.619[25-23]. and 25.625(a)(0XcX25-231. re. CERTFICATION - Under minority Pen 193. dots nand above and on 'Bathed appacsoie requirements of the AInvortnIness K Recommend wired bydrecelon of the AdrranIstralor end In accordance with conditions and Ilmitallons of appcdnMsent under 14 PROT441 sheds numbered _BA, have been emartned in accordance with established procedures all found es coos* et Standards Listed approval of these data these data I (We) Therefore FrA. Approve it SIGNATURE(S) OF DESIGNATED ENGINEERING RE PRESENTAttVE(S) 12. DESIGNATION NUMBERS(S) I3. CLASSIFICATION(S) pre:7 4 Z.--; DERT-410115-CE Structures FAA Form 8110.3 (03-10) SUPERSEOES PREVIOUS EDITION File Number. H18777-01 Page 1 of 1 PROT2 PROT3 e i (6, US Departalerd 0/ Trenelarlation Federal Aviation taimiwarzion Olaf NO. 2120-0920 SM Ent I QM O Ekciront Trackhg Haw For FAA thia Oral INSTRUCTIONS: Print or type all entries. See Tide 14 PROT442 §43.9 Part 43 Appendix B. and AC 43.9-1 (or subsequent revision thereof) for Instructions and disposition of this form. This report is required by law (49 PROT443. §44701). Failure to report can result In a cNa penalty ler each such Notation. (49 PROT444. §46301(a)) 1. Aircraft Nationakty and Registration Mark UNITED STATES / N188TS Serial No. RK-244 Make Model 400A Series a Owner Name (As shown on registration certa1cato THORAIR LLC Address As shown on registration certificate) At:keen an SANDUSKY ham 011I0 za 44871-2218 cosier UNITED STATES 3. For FAA Uso Only 4. Type ill. Unit identrestIon Repair Alteration UM Make Model Serial No. WI [j AIRFRAME RATIMONAMCIMFTCOSIMY RK-244 K K POVVERPIANT PROPELLER I I APPLIANCE 11Y01 Manufacturer 6. Conformity Statement A. Agencys Name and Address B. Hind Of Agency sew Constant Aviation LLC U. S. CerWketed Mechanic 1 Manufacturer Newt I Portion Certificated Mechanic a, CLEVELAND suds OH Ceblitaied Re r PM/ Station CRS#WC7R346J zis 44143 c,,,,....., USA Certificated Maintenance Organization D. I certify that the repair and/or alteration made to the unit(s identified in Item 5 above and described on the reverse or attachments hereto have been made In accordance with the requirements of Part 43 of the U.S. Federal Aviation Regulations and that the Mfonnallon Wished herein is true and Extended per 14 APP. range fuel PROT445 Part 43 B K 10/04/2019 turn-Vs-Service Pursue Administrator I to the authority g nri of the Federal a ion Administrati end Is I in item 5 Approved Inspected In the manner prescribed by the Relected t..--- - FAA Fit. Standards Inspector Manufacturer Maintenance Organlzabon Department 01 Transport BY FAA Designee M Repair Station i spection Authorization Certificate or Designation No. CRS# WC7R346J Signature/Da AW d IndNidual 10/04/2019 FAA Form 337(10/06) Page I PROT4 NOTICE Weight and balance or operating limitation changes shall be entered ✓n the appropriate aircraft record. M alteration must be compatible with ail previous alienations to assure continued conformity with the applicable airworthiness requirements. 8. Description of Work Accomplished (f mote space Is reputed. attach additional sheets ;den* Mih sitar* nationality and regisfratton math and date soak completed) UNITED STATES! NIESTS IW04/2019 Nationality end Registration Mark Date Engine Inlet Rivet Repair Installed blind rivets in place of the damaged solid rivets on the lip of the right hand engine inlet forebody assembly part number 541000-004, serial number R0010, in accordance with nextant aerospace engineering order NT-ED-1118-31 rev IR dated 11/29/2018 with FM form 8110-3 dated 11/30/2018. Instructions for Continued Airworthiness: Follow the maintenance inspection practices in the aircraft maintenance manual. Inspection intervals shall remain as indicated in the aircraft maintenance manual or operators approved inspection program as appropriate. Weight and Balance unaffected. Reference Constant Aviation work order CCM-3160 END- FlAdditional Sheets Are Attached Page 2 PROT5 U.S. DEPARTMENT OF TRANSPORTATION 1. DATE November 30, 2018 2. MAKE S. MODEL NO. N541000-004 4. TYPE (Aber* Engine, People, art) Forebody Assy & NAME OF APPLICANT LIST OF DATA & PENTIF(GM.PN 7. TITLE NT-EO-1118-31 Rev. IR November 29, 2018 - Engine Inlet Rivet Repair. Notes: 1) The structural approval is demonstrates subparagraph 2) This form constitutes substantiation data are approved herein. This the data listed above specified by paragraph and engineering data necessary for for the entire repair. - END aspects only of the above Ilsted only for the engineering data. It Indicates compliance only with the regulations listed below as 'Applicable Requirements." FAA approval of all the of compliance to necessary requirements a. PURPOSE OF DATA: Engineering data to support repair procedure for Textron 400A Forebody May PIN N541000-004, S/N R0010 under Nextant Aerospace Work Order No.10565.1.1. 9. APPLICABLE REOUREMENTS (LMIIPodfic MadanN PROT446 nee 14 Pad 25.301[25-23], 25.303(25.23], 25.305(a)(b)(cX25-23), 25.307(aX25-23), 25.801[25-00), 25.603(aXb)(c)[25-38], 25.605(a)(25-00), 25.807[25-23), 25.609(a)(bX25-001, 25.811[25-23), 25.613(eXbXcX25-00), 25.619[25-23), and 25.625(aXbXcX25-23). 10. CERTIFICATION - WON surely veiled byAvalon of the Adeninistrstor end I n azeardance WM conekns end IrkatIons of appolnonent under I 4 PROT447 Pert 163. data bled above and cn attached thetas numbered N/A have been exalted In accordance wilh colablahed procedurea and found to complyv/4h aPIANON requarrmega of the AINronnIness Standards Listed p Recommend approval of these data El Approve Omni dale I I. SIGNATURES) OF DESIGNATED ENGINEERNO REPRESENTAT1VE(SI 12. DESIGNATION NU)eERS(S) 13. CLASSFICATION(S) ptridia ..----C.o. DENT-410115-CE Structures FM Form 8110-3 (03.10) SUPERSEDES PREVIOUS EDITION Flle Number H18777-01 Page 1 of 1 PROT6 S PROT7 nextant aerospace //gerMAGINED immer //Rang» I EO Ik NT-EO•1118-31 I Tine: Engine Intet Rivet Repelt ENGINEERING ORDER ARTICLE DESCRIPTION Locklithaageke Teatret Aviden 400A Alrenol Soorial Naait) See Rerrans onnette nier Mam Die purpose of Ibis EO is to am for te ins:asem "kid Sits gmt CR32124-XX)of »vroor-iet° lengt in pace of te damaged sol» rivet (PIN: MS20426AD5-XX)on tie enge Int» forebody neemt*: The repair wil be accennistied on It» RH engen ijkt forelndy assembly (PIN: N541000-004. Sin. Ft0010) REGULATORY Aa ~d Pa MorinhaN Aa tasa /t~ clualcabeSMOZIFUFAI *pen/ b ~d to San, ~IS a I44JOR - anion, D YES ISINO MMO 01160RO LU D YES NO ~We InhAeOreal O YES giro Pmbn OS Peperibiba • YES Ca NO Das tble EO signilkently aflect wenk beaam otiodural strengt eircraft perbmara peperplant opreten, light dandaddicre. or ober aineortiiness goalies? MAJOR ' b YES /APK* OIO Cm tb EO be accompliihod by accepled paden a dementary operator» MINOR D YES I - II Pompen done, oe& Ibis EO special* affect inwort elt»? ' ~gr St MINOR !Duo assks. tE3 1/MOR O MNOR Ei STC (Ne ST02371LA) ~ISW Ballifo Clep D YES 0 NO MA ~COO NINA E3 YES 1:1 NO GENERAL Crimen UWAticivnnta repro 1: Oemaged Rivel Locatief, en RN Engte Wal eig, Motel Stan) remenitenyeas O YES 0 NO Resafidaterom Het PM: N541000-004 SIN: R0010 Wtr. 10565.1.1 (Original WO. IR wit approval) 13003 (IR.1 WO) OberrytAex Proclise Specificeer:n: CA;1015 REVISION ~WIN OM CfACRPTION ECII k REV4E0 Iff IR I 1129018 kik" Proposal MA R Avahalumov IRA 1071/2019 Updated b gemme sper& engerd ringt trem ceesenellen. dur Is Snot and 81104 at R stands WA P. Avabalumov ACIION DAM PrepreedEly 10/1/2019 ander' By 10/1/2019 Approved By ikowdbyPinUsa vinv• 1011/2019 >019.10.02 Wil.» mto Form No. NT.E0-01 I Ree A Page 1013 This Document h Unzontroted Onc• Ptt:lied PROT8 PROT9 ITEM //fatMAGMED //U/da! //REBORN EO a: NT.EO1118-31 DISTRUCTIONS Title: Engine Inlet Rivet Repair ENGINEERING ORDER 1 PROCEDURES 1 Visually rasped the engine inlet hp and barrel for any other damaged, missing a loose bsteners. • If no addennal discrepancies are detected, calla° with repair as °dined below. - If additional descepamies me rant canted Nettie Aerospace la depositors CiEs•C« 00 2 3 Visualy inspect No engine roan es defined in Sib Task 724140420-801of hi Mann Inlombonel LivE WtINTENANCE MANUAL- FJ443AP 111030402 (blest re' • If no additional cracrepanOes are detected. conatie with repair u coined below. • If Mai:anal durepancies me noted. corded Nettant Aerospace for deposition. NVE C.A.C. OSS e 41/ 2 Cs4.c, 0.' Locale damaged rivets as shown in Figure 1 end carefully and completely dal al the remaining hateier material. making sure not to damage, ably, a oversize the fastener hole. 4 Prepare the holed the missing bsteners for instillation of Caiegyailax Riven RN CR3212-5.XX in feu of nominal solid rivets MS20426AD540C • Prepare ham by aging and reaming to the required rivet Sae, as required, per ClwayMaa clocunent CA.1015 • Determine be correct gdp Sangth for to fasteners to be used. cabana Cherybax document CA-1015. • Using the manufacturers reornmended installation ton install Ne reel fasteners per ChemyMax dowdiest CA.1015. • Inspect the conedeted rivet set lo verify te lodeng coiled has been inserted and the stem has hazed flush with the rivet head. Refer to Chemyttix anseent CA-1015 Ix Inspection ad verification. -END LAKTATIONS None INSTRUCTIONS FOR CONTINUING AIRWORTHINESS (ICA's) Follow the maintenance inspection practices in Ne aircraft rnslaenevce manual. Inspection intervals shall roman as indicated vita eircrin't marilenanco manual or waralas approved inspection program as appropnan COMPLIANCE AH.:RNI M0DEI ~AT ~TPA,» t/uS8 13 San crIstAtall A RSA WC7R346J AlxaAfleB1W NIMILA lc 2•Vel DATE 10/27 Form No. NT.E0-01 I Rev A Page 2 ol 3 This Document is Unconuolled Once Printed PROT10 PROT11 ry //REINiAGiNED //RESULT //MORN EO /: NT-E0:11111-31 I Title: Engine Inlet Rivet Repair ENGINEERING ORDER Figure 1: Damaged Rivet Location on RH Engine Inlet Up (Typical Shown) Page 3 ol 3 Form No. NT•EOA1 I Rev A This Document Is Uncontrolled Once Printed PROT12 S PROT13 0 US DepeVret of Tranwortefon Wend Avliclon Adearileintlein DNB ,40- 2120'0020 Exp. Pamela Elearerie Trackog Witco For FAA Use Only INSTRUCTIONS: Print or type all entries. See Title 14 PROT448 §43.9, Part 43 Appendix B, and AC 43.9-1 (or subsequent revision thereof) for instructions and disposition oft* form. This report is required by law (49 PROT449. §44701). Failure to report can result in a civil penalty lor each such violation. (49 PROT450. §48301(a)) 1. Aircraft UNITED STATES / N188TS Serial No. RK-244 Make Model 400A Series 2. Owner THORAIR LLC Address (As shown on registration certiecate) Address coy SANDUSKY SYS OH 2p 44871 Cathy UNITED STATES 3. For FAA Uso Only 4. Type 6. Unit identification Repair Alteration Unk Make Model Serial No. I-1 m, AIRFRAME MYPEOP.A0CRAFT COMM" (As described in Men; 1 above) MOEN POWERPLANT PROPELLER APPLIANCE Type Menet/were.. Now CONSTANT AVIATION U. & Caollkated Mechanic I Manufacturer Adana Foreign CatilloNed Mechank Ott CLEVELAND sew OR i CalLated Certificated Repair Stallion CRS# WC7R346J 10 44143 Candy UNITED STATES Maintenance Organ/wk., D. I certify that the repair andior alteration made to the unks Identified in Item 5 above and deathbed on the reverse or attachments hereto have been made in accordance with the requirements of Part 43 of the U.S. Federal Aviation Regulations and that the Information furnished herein Is true and correct to the best of m knovA i • i i per 14 PROT451 Part 43 Am. B Sign 10/7/2019 7. A • proval for Return to Service Pursuant to the authority paten persons specified below. the Lilt Wenn, In item 6 va tinspected Administrator of the Federal Aviation Administration and la I Approved In the mama prescribed by the Rigel:led BY --"' FAA Fit. Standards Inspector - Manufacturer - - Maintenance OrgaNzatlon Depaitrnen1 of Transport FM Designee I Repair Station Inspection Authorization Certificate or Designation No. C RS# WC7R346J Signature) . e uthori ed Individual ,,i 10/7/2019 Page 1 PROT14 NOTICE Weight end balance or operating Nmitallon changes shell be entered in the appropriate aircraft record. An alteration must be compatible with all previous alterations to assure continued conformity with the applicable airworthiness requirements. S. Description of Work Accomplished al more space is requirec( attach additional sheets. Mandy *eh thrash nationally and registration mark and date oak completed) mire, STATES /N1887/3 107/2019 Date INSTALLATION OF ADS-B OUT ON PART 25 AIRCRAFT Complied with installation of BHE & Associates, LTD. STC# ST11216DS Installation of Automatic Dependent Surveillance-Broadcast Out on Part 25 Aircraft IAW BHE & Associates,LTD. Master Data List (MDL) number [SSN REDACTED] Rev.G. Dated 8/29/2019. Reference BHE & Associates, LTD. Aircraft Flight Manual Supplement (AFMS) Installation of ADS-B Out on Part 25 Aircraft. Report number [SSN REDACTED] Rev.C. Dated 5/4/2019. Reference BHE & Associates, LTD. Electrical Load Analysis (ELA) Installation of ADS-B Out on Part 25 Aircraft. Report number [SSN REDACTED] Rev.B. Dated 10/9/2018. Reference BHE & Associates, LTD. Instructions for Continued Airworthiness (ICA) Installation of ADS-B Out on Part 25 Aircraft. Report number [SSN REDACTED] Rev.D. Dated 3/19/2019. Weight and Balance: Reference calculated weight and balance dated 10/7/2019. Equipment List: Updated. Reference Work Order: CCM-R3160. END riAdditional Sheets Ne Attached Page 2 PROT15 vs/miaow (gamma etpartmeat IT'ramprtation Feetativiationiftfothistratlim Supplemental! )re Cergficate .9Ifiumbir ST1 1 216DS MU traffic-au laud to: BHE & Associates, Ltd. San Antonio, TX 78216 tert,fes doe for dap is the type asign fi r dejedfruandert aid Me limaationsaftatcotdiftims denybtr as Jpenfreanron meets de airavuotheartythetwas iltaft25 ?Pi/federal Aviation Regulations. Original Product - Type Ceniticate Number: See attached approved model list (AML) Make: See attached AML Model: See attached AML Description orlype Design Change: Installation of automatic dependent surveillance-broadcast (ADS-8) out on Part 25 aircraft, in accordance with Master Data List [SSN REDACTED], Revision IR, dated June 29, 2018 or later FM approved revision. For Instructions for Continued Airworthiness and Airplane Flight Manual Supplement reference the attached AML. Limitations and Conditions: 1. The installer must determine whether this design change is compatible with previously approved modifications. 2. If the holder agrees to permit another person to use this certificate to alter a product, the holder must give the other person written evidence of that permission. 3. See attached AML for additional limitations and conditions. 'flu a/41fmk. amide supporting eta wild is the 6ashforappronisiende fit nittsuntwifere4 saspellatid; and inrokeefor a termination ate is oderwite ene6/10flay t6efiminu aide Fralreigratioll dIteladdrinu Date of Application: February 9. 2018 Date of Issuance: June 29. 2018 Date Reissued: Date Amended: roy Oben fiticitaial 3(9watt/re 9itk VT ORB Aviation Project ODA Administrator ODA-831473-SW Any alteration ot this cert.ficale is constable by a fine of not exCeedngS1.000. or imprisonment not exceeding 3 years. or bolt. Dies certificate may be transferred or made evade to third persons by licensing agreements en accordance with le PROT452 21.47. Possession of this Supplemental Type Cerbncale (STC) document by persons otter pen the STC heeler does not commute rights to the design data nor to alter an aireaft aircraft engine, or propeller. The STCs supporting documentation (drawings. instructions, speofications, flight manual supplements. CC ) is the ptcperty of the STC holder. An SIC hotter who aeon a person to use the SIC to ate( an airaaft. airaaft engine, or propeller moat Mande that person Mm mitten permission acceptable tome FAA (Ref le PROT453 21 120) FAA Form 8110-2 (5114) Page i of 2 PROT16 SledStates ofilmen?a Department triansportation ediraf2viationAtfmtnistratthrt Supplemental 75 pe Certificate 1NSTRUCITONS The transfer endorsement below may be used to notify the appropriate FAA Aircraft Certification Office of the transfer of this Supplemental Type Certificate. The FAA will reissue the certificate in the name of the transferee and forward it to him. Transfer Endorsement Transfer the ownership of Supplemental Type Certificate Number: ST11216DS To (Name and address of transferee) From (Name and address of grantor) Extent of Authority (if licensing agreement): One etransfer Signature ?grantor My alteration of this certificate is punishable by a fine of not exceerfing 51.000. or imprisonment not exceeding 3 years. or both. This certificate may be transferred or made available to third persons by licensing agreements in accordance with 14 PROT454 21.47. Possession *falls Supplemental Type Certificate (STC) document by persons other than the SIC holder does not constitute rights to the design data nor to alter an aircraft. aircraft engine. or propeller. The Sits supporting documemadon (drevangs. instructions, specifications, flIgM manual supplements, etc.) is the property of the SIC holder. ,M STC holder who allows a parson to use the STC to alter an aircraft. aircraft engine. or propeller must provide That person with written permission acceptable to the FAA. (Ref. 14 PROT455 21.120). FAA Form 8110-2 (5/14) Page 2 of 2 PROT17 DocuSign Envelope ID: CFB828B5-6FE8-4C80-A4E3-5461F9B20045 INSTRUCTIONS FOR CONTINUED AIRWORTHINESS FOR THE INSTALLATION OF ADS-B OUT ON PART 25 AIRCRAFT REPORT No. [SSN REDACTED] Revision D Date: 03/19/2019 NOTICE: The contents of this document are proprietary to BHE & Associates, Ltd. and shall not be disclosed, disseminated, copied, or used except for purposes expressly authorized in writing by BHE & Associates, Ltd. BHE & Associates, Ltd. San Antonio, TX 78216 USA CAGE: N/A Rerd By VLDRB, FSCM 47M27, Shl 1 of 39, 2019/Marl19 PROT18 DocuSign Envelope ID: CFB628B5-6FES-4C8D-A4E3-5461F9B2D045 NOTICES AND SIGNATURES Notices: Note: Paragraphs and/or figure numbers followed by" I" indicate a change by latest revision. Approval Signatures: REPORT No. [SSN REDACTED], Rev: D Page 2 of 36 Rem By VT-DRS. FSCM 471027, Sht 2 01 39. 2019/Mer/19 PROT19 DocuSign Envelope ID: CFB628B5-6FE8-4C8D-A4E3-5461F9820045 Record of Revisions Revision Number" ri Ion -l7 - ..-:.4 of change 106 Dats.- NIOtOY0 IR Initial Release 5/9/18 A 6/27/18 Page 8, Section 1.1 revised transponder and GPS part numbers. Page 10, Section 2 remove' light Hours' from Table 4 B Page 4, Revised list of aircraft models in Introduction Pages 9, 24-25, 28-29, Revised aircraft models in Tables 3, 7, and 9. Pages 8 and 28, clarified wording for installation. 11/6/18 C Revised Table 3 on page 9 Revised Table 4 on page 10 Revised Table 5 on page 26 Revised Table 6 on pages 27 & 28 Revised section 6.1.9 on page 31 Revised figures on pages 13 & 20, Added figures on pages 14, 17 & 18 1/18/19 D Added STC number on page 4. Added figure on page 24. Revised form in Appendix C. 3(lcitict BHE & Associates. Ltd. Page 3 of 36 Rerd By VT-DRB, FSCM 471,0127, Sht 3 of 39, 2019/Mar/19 PROT20 DocuSign Envelope ID: CFB62885-6FEB-4C8D-A4E3-5461F9B2D045 INTRODUCTION These Instructions for Continued Airworthiness (ICA) document have been developed using the guidelines in Appendix "H" of 14 PROT456 Part 25 as required by §FAR 21.50 and §25.1529. This document is designed to provide avionics and aircraft technicians with sufficient information to inspect, troubleshoot, adjust, repair, test, remove, and install ADS-B on the following Part 25 Aircraft. Bombardier Inc. - CL-600-1A11, CL-600-2Al2, CL-600-2B16 (Challengers) Gulfstream Aerospace -1125 Westwind Astra, Astra SPX, Gulfstream 100, G150 Gulfstream - G-1159, G-1159A, G-1159B, G-IV, GV Gulfstream - 200 Sabreliner - NA-265-65, NA-265-70, NA-265-80 Textron Aviation Inc. - 500. 550, S550, 560 (Citation) Textron Aviation - 400, 400A (Beechjet) Textron Aviation - 650 Textron Aviation - HS.125 Series 700A, HS.125 Series 700B, BAe.125 Series 800A, BAe.125 Series 8006, Hawker 800XP, Hawker 750, Hawker 850XP, Hawker 900XP Learjet - 60 (STC Aircraft) Dassault Aviation - Falcon 10, Mystere-Falcon 50, Mystere-Falcon 20-05/D5fE5/F5, Mystere-Falcon 200, Mystere-Falcon 900 Table 1: Equipment Type Description New CPN Qty DO-260B ADS-B Out TOR-94 Transponder 622-9352-502 0, 1 or 2* TDR-94D Transponder 622.9210-502 0, 1 or 2* GPS1203C GPS Receiver 84327-50-XXXX 0 or 1 CI 429-200 GPS Antenna CI 429-200 0 or 1 GPS-40005 GPS Receiver 822-2189- 004/005/006/007/010/011/100 0, 1 or 2 *Either TOR-94 or TDR-94D will be installed. The above equipment is installed in accordance with FM Supplemental Type Certificate No. ST11216DS . See the List of Applicable Publications (LOAP) in Appendix A of this document. The publications listed in the LOAP constitute the required information essential for continued airworthiness for the aircraft. The documents contained in the LOAP are a necessary part of this ICA and the latest revision should be available to maintenance personnel when performing maintenance. The STC holder will continue to monitor changes to the ICA that were the basis of the supplementary ICA and provide revised supplemental ICA as necessary. The information in this document supplements or supersedes the original manufacturer's maintenance manual only in those areas listed. For limitations, procedures and other information not contained in this document, refer to the aircraft manufacturer's maintenance manuals, illustrated parts manuals and wiring diagrams or the vendor manuals as listed in the LOAP. Page 4 of 36 Reid By VT-DRB, FSCM 47MZ7, Shl 4 of 39. 2019/Mar/19 PROT21 Docu&an Envelope ID: CFB628B5-6FE841C8D-A4E3-5461F9B20045 RECORD OF REVISIONS For continuous use of this document, this document must be maintained in current revision status. Each time the STC holder finds it necessary to revise this document; a revision will be distributed to all users of the STC. Revisions will be supplied to the customer by: a) E-mail with an attached PDF file, or b) Compact Disc (CD) via mail Changes to this document will be incorporated by an updated revision to the complete document. All pages will indicate the "new" revision level. Upon receipt of the new revision, the previous revision should be discarded and replaced with the updated, current, revision. Changes to this document will be listed in the revision block on page 3. It is the responsibility of the person(s) performing maintenance on the installed system to ensure that this document is current prior to performing this maintenance. The current revision number may be verified by contacting the STC holder, BHE & Associates. Report any discrepancies to the installation of this STC using the form in Appendix C of this document. Once filled out the form must be sent to both the ODA and the STC holder. Their addresses are as follows: ODA VT-DRB Aviation Consultants San Antonio, Texas 78216 STC Holder BHE & Associates Ltd. San Antonio, Texas 78216 Page 5 of 36 Rani By VT-ORB. FSCM 47M27. Sht 5 of 39, 2019/Marf19 PROT22 DocuSign Envelope ID: CFB62885.6FE84C8Da4E3•5461F982D045 TABLE OF CONTENTS INTRODUCTION 4 RECORD OF REVISIONS 5 1 SYSTEM DESCRIPTION 8 1.1 GENERAL 2 AIRWORTHINESS LIMITATIONS 10 2.1 Inspection Intervals 10 2.2 Inspection Program 22 2.3 Inspection Method 22 2.4 Eddy Current Inspection 28 3 MAINTENANCE PRACTICES 29 3.1 Removal/Installation 29 3.2 Access Location 29 4 POWER DISTRIBUTION 30 4.1 Circuit Breakers by Bus 30 5 SYSTEM TROUBLESHOOTING 31 6 INSPECTION REQUIREMENTS 31 6.1 Scheduled Inspections and Maintenance Checks 31 6.2 Wiring 34 Appendix A - List of Applicable Publications Al Appendix B - Special Tools and Equipment B1 Appendix C - Discrepancy Reporting Form Cl Page 6 of 36 Red Ely VT-DRB, FS0.4 47k4Z7, sat 6 of 39. 2019,MartI9 PROT23 DocuSign Envelope ID: CFEt628B5.6FE8-4C8D-A4E3-5461F9B20045 LIST OF FIGURES AND TABLES Table 1: Equipment 4 Table 2 Equipment List 8 Table 3 Equipment by Aircraft 9 Table 4 Inspection Intervals 10 Table 5 Manual List 28 Table 6 Access Panel Location 29 Table 7 Equipment Installation Locations by Aircraft 29 Table 8 New and Upgraded Equipment 30 Table 9 Maintenance Manual by Aircraft 33 BHE 8 Associates, Ltd. Page 7 of 36 Red By VT•ORB. FSCM 47MZ7. Sht 7 of 39. 2019/Mar/19 PROT24 DocuSign Envelope ID: CFB62895-6FES4C8D-ACE3-5461F9820045 1 SYSTEM DESCRIPTION 1.1 GENERAL This STC will include installations and/or updates to equipment to allow for Automatic dependent surveillance - broadcast Out (ADS-B Out). ADS-B periodically broadcasts information about each aircraft, such as identification, current position, altitude, and velocity, through an onboard transmitter. The equipment list in Table 2 below details the equipment required for this installation. The TDR-94/94D Transponder(s) will be upgraded to part number 622-9352-502 (94) or 622- 9210-502 (94D), if not previously installed. The TDR-94/94D Transponder is an all solid-state, crystal-controlled receiver/transmitter. The transponder(s) will get the GPS information from either a newly installed Freeflight GPS1203C GPS receiver and dedicated GPS antenna; or, a GPS-4000S GPS receiver. Depending on the aircraft configuration, the GPS-4000/A/S may be previously installed. If the previously installed GPS- 4000/A/S is not a part number 822-2189-004/005/006/007/010/011/100 it will have to be upgraded to one of these part numbers. (Reference Tables shown on drawing [SSN REDACTED] for applicable GPS installation based on aircraft model) Wiring is added dependent on the installed or replaced GPS receiver(s), Transponder(s), and annunciator installed. (Reference Tables shown on drawing [SSN REDACTED] for applicable installations based on aircraft model and subsequent Wire Routing drawing [SSN REDACTED]).See section 6.1.9 for details on inspection. An optional ADS-B Out annunciator can be installed to alert the pilot that the ADS-B function of the active transponder is not properly functioning. The ADS-B Out annunciator is required for all standalone GPS installations. Standalone means the GPS only provides data to the transponders. All 1203C installations and 4000S installations that only connect to the transponders are standalone. It can be installed as an option for installations where the 4000S is used for both ADS-B and FMS navigation. ((Reference Tables shown on drawing [SSN REDACTED] for applicable ADS-B Out Annunciator installation based on aircraft model) Table 2 E ul ment List Type Description New CPN 1 Qty DO-260B ADS-B Out TDR-94 Transponder 622-9352-502 0, 1 or 2* TDR-94D Transponder 622-9210-502 0, 1 or 2* GPS1203C GPS Receiver 84327-50-XXXX 0 or 1 CI 429-200 GPS Antenna CI 429-200 0 or 1 GPS-4000S GPS Receiver 822.2189- 004/005/006/007/010/011/100 0, 1 or 2 •Either TDR-94 or TDR-94D will be installed. Page 8 of 36 Red By VT-ORB. FSCM 471027, Snl 8 of 39. 2019/MartI9 PROT25 DocuSign Envelope ID: CFB626B5-6FE8-4C80.A4E3-5461F9B2D045 Table 3 below lists the equipment being installed by aircraft. The aircraft will leave with updated TDR- 94s or 94Ds depending on the what transponder was already existing. Table 3 Equipment by Aircraft Aircraft Transponder Installed/Retained/Replaced GPS Installed/Replaced Antenna Installed I Learjet 60 TDR-94s or 94Ds GPS-1203C or GPS- 40005 CI 429-200 Gulfstream Aerospace 1125 Westwind Astra, Astra SPX, Gulfstream 100, G150 GPS-4000S N/A Gulfstream G-1159, G-1159B, G-IV, GV 4000S CI 429-200 Gulfstream G-1159A GPS-40005 N/A Gulfstream 200 GPS-4000S N/A Textron Aviation 500 40005 CI 429-200 Textron Aviation 550, 5550, 560 4000S CI 429-200 Textron Aviation 400 4000S CI 429-200 400A GPS-4000S N/A Textron Aviation 650 40005 CI 429-200 Bombardier CL-600- 1A11 CL-600-2Al2, CL- 600-2616 40005 CI 429-200 Sabreliner NA-265- 65, NA-265-70, NA-265- 80 GPS-40005 N/A HS.125 700A, BAe.125 800A/800B, Hawker 800XP 40005 CI 429.200 1-15.125 700B, Hawker 750/850XP/900XP GPS-4000S N/A Dassault Aviation Falcon 10, Mystere- Falcon 50, Mystere- Falcon 20- C5/D5/ES/FS, Mystere-Falcon 200, Mystere-Falcon 900 GPS-40005 N/A Page 9 of 36 Reid By VT-ORB, FSCM 47M27. SM 9 of 39. ₹019/Marl19 PROT26 DowSign Envelope ID: CF862885-6FE8-4CSD-A4E3-5461F9S2D04S 2 AIRWORTHINESS LIMITATIONS The Airworthiness Limitations section is FAA approved and specifies maintenance required under 14 PROT457 §§43.16 and 91.403 of the Federal Aviation Regulations unless an alternative program has been FAA approved. 2.1 Inspection Intervals The following items require high Frequency Eddie Current inspections including 2.0 inch detailed visual inspection around periphery of the installation. Inspections as listed in the table below. Table 4Inspection Intervals Inspection requirements are for AML fuselage modification Inspection In ervals (Flight Cycles) Detectable Crack Length (in.) Threshold Recurring Fwd bulkhead penetrations 4,000 4,000 0.200 GPS Antenna Installation 6,700 6,350 0.200 GPS Antenna Installation (See Note 1) 5,650 5,400 0.200 Note1: These intervals are applicable to the Textron Aviation Cessna 650 and all the Gulfstream Models The following images specify antenna installation and bulkhead feedthrough installation locations. Page 10 of 36 Rerd By VT-DRB, FSCM 47MZ7, Sht 10 of 39. 2019iMar/19 PROT27 DowSign Envelope ID: CFB62885-6FEB-4C8D-A4E3-5461F9B2D045 BOMBARDIER INC. CL-600-1A11 (CL-600), -2Al2 (CL-601), -2B16 (CL-601-3A VARIANT, CL-601 -3R VARIANT, CL-604 VARIANT) ACCEFTAKE LOCATION TS IS FS 310.00 MOO 03 21°4° Fs mos n 295.00 32140 FS is 25000 I FS 13600 21130.22"D OO FS 193.00 Fs 19900 FS 364.03 FS Fs 343.00 379.00 FS 394 00 FS TS 424 449.95 473.15 rs Fs It 499.00 MAO 539.00 IS FS FS 441.50 494.00 513.00 s' br H00000 Page 11 of 36 Red By VT-ORB. FSCM 47M27, Shl l l of 39: 2019/Ma019 PROT28 DocuSign Envelope ID: CFB62885-6FE8-4C8D-A4E3-5461F9B2D045 TEXTRON AVIATION 400 ACCEPTABLE LOCATION F'S FS .46 FS [repeated 3 times] 17224 196 FS PS Fs PS 124.61 141.14 159.25 II FS 203.35 221.46 240.75 260.04 FS [repeated 5 times] 1:6534 13767 1220 6214 .35 212.40 231.42 25039 269.69 71.65 niD I PRESS BLPHD FS 20.2e FS FS 60.91 99.02 FS FS 6996 108.07 'Pi iirki Page 12 of 36 Red By VT-DRB. FSCM 47MZ7, Snt 12 of 39. 2019/Mar/19 PROT29 DocuSign Envelope ID: CFB628B5-6FE8-4C8D-A4E3-5461F9B20045 TEXTRON AVIATION INC. 550, S550, 560 FS 59 00 FS 134.00 94.00 FWD 117.00 PRESS BOOM i FS FS 151 .00 179.02 FS 165.00 FS 225.23 23 (560) FS 223.40 FS 216.10 (560 ONLY) Page 13 of 36 Reel By VT-ORB, FSCM 47MZ7, Sht 13 of 39. 2019/Matil9 PROT30 DoneSign Envelope ID: CF8628B5-6FE8-4C8D-A4E3-5461F962D045 TEXTRON AVIATION INC. 650 FS 58 00 FS 94.00 FWD PRESS BLKHD FS FS 172.00 202.00 FS FS 157.00 187.00 FS FS 261.00 288.76 FS I 245 00 272.00 I Page 14 of 36 Red By VT-DRB, FSCM 47M27. SM 14 of 39. 2019iMari19 PROT31 DocuSgn Envelope ID: CF862885-6FE8-4C8D-A4E3-5481F9820045 TEXTRON AVIATION HS.125 SERIES 700A, BAe.125 SERIES 800A 8c 800B, HAWKER 800XP 163.3 3013 220.0 }I I I J~p7III13 171 07 M11O-1 MO FII 201.0 202.3 Ft r-T T 1 1'0IOIOI 000) - n. Page 15 of 36 Rory By VT-ORB. FSCM 47MZ7. Sill 15 of 39. 2019/Mar/i9 PROT32 59.23 7523 r5 61.23 47.23 F3 33.3 F2 I I DocuSign Envelope ID: CFB628B5-6FE8-4CEID-A4E3-5461F9B2D045 LEARJET 60 110.99 124.39 151.19 170,59 201.79 222.1 FS Fl 137.79 110 F12 F14.4 99.57 164.59 184.99 1210.19 F11 f13 F 5 Fe 197.50 I 1941 1 1 1 I I I [repeated 8 times] 1 I I I 70.59 Fl IA 336.61 F23 216.. 274.59 302.59 323.59 I 355.16 IS F200 F21A I . F25 3 234.19 25059 2M29 lel 4663 F17 F19 F21 F22 F24 I 0 orr0 1 IL MI ' Page 16 of 36 Red By VT-DRB. FSCM 47MZ7, Sill 16 of 39, 2019/Marf19 PROT33 DowSign Envelope ID: CFB62885-6FE8-4O3D-A4E3-5461F982DO45 GULFSTREAN/ G-1159, G-1 1598, G-IV FS FS 145.0 .0 193.0 FS FS '33.0 181.0 FS 63.0 FV4) PRESS BLKHD IAII- 100 I I . I. I N I [repeated 5 times] ...1 I 1 1 I H .1 I \ I- I-1 I 1 LEI Page 17 of 36 Ro(d By VT-DRS, FSCM 47M27. Ste 17 of 39. 2019/Mar/19 PROT34 DocuSign Envelope ID: CF862885-6FE8-4C8D-A4E3-5461F9020045 GULFSTREAN/ GV FS [repeated 4 times] 157.' 181.0 205.0 229.0 145.0 193.0 217.0 241.0 FS [repeated 4 times] WL 100 C ES 63.0 FWD PRESS BUCK) vzi I [repeated 4 times] 1 I [repeated 4 times] n 1 I I i- I I I I -L p_ I I .1_I J 1 I I\ Page 18 of 36 Rerd By 1/7-DRB, FSCM 47M27. Shl 18 of 39. 2019/Mar/19 PROT35 DocuSign Envelope ID: CFB628B5-6FEB4C8D-A4E3-5461F9B2D045 1 (WL 0.0) I' 000 I I 0 0 I I III - SS 0 M III III I I I I II I I /1 I I I II t i // I I I I -.L 7 ALTERNATE LOCATION LOOKING AFT AT FWD SIDE OF FORWARD PRESSURE BULKHEAD (TEXTRON AVIATION 400) II Page 19 of 36 Red By VTORB, FSCM 47M27, Sht 19 of 39. 2019rMar/19 PROT36 DocuSign Envelope ID: CFB62885-6FEB-4C8D-A4E3-5461F9B2D045 I \-- TT IF I. I Il l i I ,II. -- -LL-,__LI LOOKING AFT AFT AT FWD SIDE OF FORWARD PRESSURE BULKHEAD (TEXTRON AVIATION INC. 500, 550, S550, 560) REPORT No. 584.00-0047, Rev: D Page 20 of 36 Reid By VT-DRB, FSCM 47MZ7, Sht 20 of 39, 2019/Mar/19 PROT37 ; '' locq 1 • 'I 4. 44 * ID: o•r:: I:I IB+11:4:11-4- {s :oo I ( ---t DocuSign Envelope ID: CFB629BS-6FEB4C80-A4E3-6461F9132D045 CW1 747F (ALTERNATE LOCAnOIN WOMAN MOW rc-: -X+ 7:i m -it r t-t,- 4* i Vc It ilit a ±:ii- :r 44 1 4 1 1 + r /'+/ t: I LI I ° 4L+" .r*: 1 O Pl ICIM I:1 1 ! I:l stt i ,42 HI i In: Etifa : 4 -141?1 1-#11:4 I II:I I Iiiiii il I iiiii+pool: 1+4 ,:l:; O: 0.1 ifr: III. II IA\ rs, • Lk' i 14+ 1 1 :+: V' +"\ , fr, I ,41 i i..., _EL LOOKING AFT AT FRO SCE OF FORWARD PRESSURE Bult01110 (LEARJET 60) I- I 1,1 II I I I 1+7 REPORT No. 564.00-0047, Rev: D BHE & Associates. Ltd. Page 21 of 36 Refd By VT-DRB. FSCh147M27. Sht 21 of 39, 2019/Mar/19 PROT38 DoeuSIgn Envelope ID: CFB62885-6FE84C8D-A4E3•5461F982D045 2.2 Inspection Program Perform additional fuselage modification inspections. 2.3 Inspection Method Inspect fuselage skin in the modification area, doubler fastener holes area, using high frequency eddy current inspection techniques, according to the intervals outlined in table 4. The detectable crack length for eddy current inspection techniques is 0.200'. For the fastener holes, the inspector should look for cracks on the surface of the skin and doubler around the fastener holes. REPORT No. [SSN REDACTED], Rev: Page 22 of 36 Rerd By VT-ORB. FSCM 47M27. Sht 22 of 39. 2019/Mar/19 PROT39 DocuSIgn Envelope ID: CF862885-6FES-4C813-A4E3-54619982D045 INSPECTION AREA & METHOD FWD BULKHEAD PENETRATIONS typical Instal14tic, shown, Innsspectitiont:y#: tcvaltlienettatto i tau ada Ealtaijiar" !lc ..41:insiirat";:z4TTEraillirs.-:417.4e-tir4LW-re--412 Page 23 of 36 Red By VT.ORB. FSCM 47M27, SM 23 of 39. 2019/Mar/19 PROT40 Doc Sign Envelope ID: CF8628854IFE9-4C8D-A4E3-5481F9B2D045 .INSPECTION AREA & METHOD FWD BULKHEAD PENETRATIONS I r-ftn2Critr e f.. wags*/ Page 24 of 36 Red By VTdMB, FSCM 47M27. SM 24 of 39. 2019/M8r/19 PROT41 DocuSign Envelope ID; CFS62885-6FE8-4C80-ACE3-5461F9B2D045 INSPECTION AREA & METHOD GPS Antenna Typical Instk 0%; ,Ipes.49.*4; :Applicable to all ditenzia g a • AI EAT ;Xl fira s REPORT No. [SSN REDACTED], Rev: I) Page 25 of 36 Red By VT DRB. FSCM 47M27, Slit 25 o139, 2019/Mar/19 PROT42 DocuSign Envelope ID: CFB62865-6FE8-4C8D-A4E3-5461F9B2O045 LNSPECTION AREA & METHOD GPS ANTENNA Typiciiliris'tallati ii slio ii Inspections 'are applicable to all.azItepnainstallations REPORT No. 584.00-0047, Rev: D Page 26 of 36 Reid By VT-ORB, ESCM 47A127. Sht 26 of 39. 2019/Mar/19 PROT43 DocuS'gn Envelope ID: CFB628B5 6FE8.4C8D-A4E3-5461F9B2D045 DISPECTION AREA & METHOD GPS ANTENNA Typical lastallation shot% Intztectiotw ate applicable to all antenna '4=' !ta ins j SAW& ,4,1". REPORT No. [SSN REDACTED], Rev: O SHE & Associates, Ltd. Page 27 of 36 Red By VT-ORB, FSCM 47MZ7, Sht 27 of 39, 2019/Meff19 PROT44 DocuSign Envelope ID: CFB828B5-6FE8-4C8D-A4E3-5461F9B2D045 2.4 Eddy Current Inspection For eddy current inspection requirements and procedures, refer to the referenced documents in the table below for the different aircraft types. The following documents describe the various procedures and requirements for HF eddy current inspection including personnel, instrumentation, equipment setup and standardization, probes, special tools and equipment eddy current standards, and eddy current test procedures required by the Cessna Aircraft Company. The defects identified by this method are incipient fatigue or corrosion stress cracks in bores, machining radii, shoulders and countersunk holes, and in the actual skin. The direction of propagation defects are perpendicular to in-flight stresses in the case of fatigue stress cracks, or perpendicular to internal stresses for stress corrosion cracks. This method also detects minor corrosion-induced surface damage. Table 5 Manual List Aircraft Manual Document Number Learjet 60 Non-Destructive Inspection Manual NDI-2 (Chapter 3) Textron (Citation) 500, 550, S550, 560 Series 500 Non-Destructive Testing Manual 5056ND (Part 6, Chapter 20) 650 Model 650 Non-Destructive Testing Manual 65ND (Part 6, Chapter 20) Textron (Beechjet) 400, 400A Model 4001400A/400XP Maintenance Manual 128-590001-9C29 (Chapter 20-80-03) Textron (Beechcraft) HS.125 700A, Bae.125 800A, Bae.125 8006, Hawker 800XP 125 Series 1-800, Hawker 750, 800, 800XP, 850XP, and 900XP Non-Destructive Testing Manual N/A (General Techniques Part 8) Challengers Structural Repair Manual N/A (Chapter 51) Gulfstream G-1159, G-1159B, G- IV, GV Structural Repair Manual N/A (Chapter 51) IIIIIIIIII____ FAA APPROVED: Project ODA Administrator VT DRB Aviation Consultants A Division of VT San Antonio Aerospace, Inc. I IIII"ISan Antonio, TX 78216 Date Page 28 of 36 Rerd By VT-DRB. FSCM 47MZ7. Sht 28 of 39. 2019/Mar/19 PROT45 DocuSIgn Envelope ID: CF862885-6FE8-4C8Da4E3-5461F982D045 3 MAINTENANCE PRACTICES 3.1 Removal/Installation The following installation manuals contain complete, detailed instruction for the installation and removal of equipment. Installation locations for the equipment vary by aircraft, reference tables 6, 7 and 9 for more details on equipment locations and respective maintenance manuals. • Equipment Installation Manual for the FreeFlight System Model 1203C GPS/SBAS Sensor, document 86764, Installation Section • Collins GPS-4000( ) Global Positioning System Installation Manual, document 523-0780545, Installation Section. TDR-94/94D ATC/Mode-S Transponder System (-5)O(), document 523-0821492, Installation Section 3.2 Access Location Refer to the Aircraft Maintenance Manuals listed in table 9 for additional details. Table 6 Access Panel Location Location of Access Access Panels Nose Avionics Bay Forward Nose Access Panels (Right & Left) Cabin EE Racks N/A Instrument Panel & Pedestal N/A Tail Avionics Bay Tail Access Panel Table 7 Equipment Installation Locations by Aircraft Aircraft Transponder Location GPS Location Learjet 60 Nose Nose (GPS-4000S) Cabin (1203C) Gulfstream Aerospace 1125 Westwind Astra, Astra SPX, Gulfstream 100, 0150 Nose Nose Gulfstream 200 Nose Nose Gulfstream G-1159, G- 1159A, G-1159B, G-IV RH EE Rack, Cabin RH EE Rack, Cabin Gulfstream GV LH & RH EE Rack, Cabin LH & RH EE Rack, Cabin Textron Aviation 500, 550, S550,560 Nose Nose Page 29 of 36 Rerd By VT-DRB, FSCM 47M27, Sht 29 of 39, 2019iMar/19 PROT46 DocuSign Envelope ID: CFB62885-6FE8-CC8D-A4E3-6461F9B2D045 Aircraft Transponder Location GPS Location Textron Aviation 400/400A Nose Nose Textron Aviation 650 Aft Cabin Nose (GPS-4000S) Cabin (1203C) Bombardier CL-600-1A11 CL-600-2Al2, CL-600-2B16 Under Floor, Cabin Under Floor, Cabin Sabreliner NA-265-65, NA-265-70, NA-265-80 Nose Alternate: FWD EE Shelf Nose Alternate: FWD EE Shelf Textron Aviation HS.125 700A/700B, BAe.125 800A/800B, Hawker 750/800X131850X131900XP Nose Alternate: AFT EE Shelf Under Floor, Cabin Alternate: AFT EE Shelf Dassault Aviation Falcon 10, Mystere-Falcon 20- 05/D5/E5/F5, Mystere- Falcon 200, Mystere-Falcon 900 Nose Nose Dassault Aviation Mystere- Falcon 50 Nose Nose Alternate: Aft Avionics Shelf 4 POWER DISTRIBUTION 4.1 Circuit Breakers by Bus There are multiple options for the installation, the table below shows the possible equipment part numbers that may have changed with this update and the associated electrical load. The following equipment part numbers may have changed with this update. Table 8 New and Upgraded Equipment Equipment/System Model/Part Number ' d Amp Max Loa s in TDR-94 622-9352-502 1.79 TDR-94D 622-9210-502 1.79 GPS RECEIVER GPS1203C 84327-50-XXXX 0.179 GPS RECEIVER GPS-40005 822-2189- 004/005/006/007/010/011/100 0.56 Page 30 of 36 Rerd By VT-DRB, FSCM 47M27, Set 30 of 39, 2019fMar/19 PROT47 DccuSign Envelope ID: CFB62885-6FE8-4C80-A4E34461F9B2D045 5 SYSTEM TROUBLESHOOTING For troubleshooting information, refer to the following; Equipment Circuit Breaker Document GPS1203c ADS-B GPS Equipment Installation Manual for the FreeFlight System Model 1203C GPS/SBAS Sensor GPS 4000S ADS-B GPS Collins GPS-40005 Global Positioning System Installation Manual, document 523-0780545, Maintenance Section TDR-94D TDR TDR-94/94D ATC/Mode-S Transponder System (-5XX), Document Number 523-0821492, Maintenance Section 6 INSPECTION REQUIREMENTS 6.1 Scheduled Inspections and Maintenance Checks This section of the document contains information regarding Time Limits - Inspection and Maintenance Checks, Overhaul and Replacement Items and Inspection Requirements. 6.1.1 Time Limits - Inspection and Maintenance Checks Note: Recommended inspection/maintenance intervals do not guarantee that the item will function properly between inspection/maintenance checks. The inspection intervals are based on average usage and environmental conditions. Aircraft operated under extreme conditions, (extreme hot, extreme cold, high humidity, salty air, etc.) may require more frequent maintenance than the intervals specified in this document. The aircraft operator may perform more frequent inspection/maintenance checks based on his usage. 6.1.2 Visual Inspections The equipment necessary for conducting a visual inspection usually consists of a strong flashlight, a mirror with a ball joint, and a 2.5x - 4x magnifying glasses. A 10x magnifying glass is recommended for positive identification of suspected cracks. 6.1.3 Corrosion Treatment Before attempting a close, visual inspection of any selected part or structural area, it should be checked for signs of corrosion. Any corrosion found should be tested to discover its extent and severity. Heavy or severe corrosion requires immediate corrective action. If mild corrosion is present, it should be carefully, but completely, removed before continuing with preparations for the visual inspection. 6.1.4 Structural Failure Determination. The first step in a visual inspection should be an examination of the area for deformed or missing fasteners. These should be identified for subsequent replacement. A close examination for cracks in the surfaces of structural members should then be made with the aid of a flashlight. The majorities of cracks start at, and progress from, points of concentrated stress such as sharp corner cutouts and fastener holes. Cracks may also occur in sheet metal bend radii and similar places that were subjected to severe forming operations during manufacture. Page 31 of 36 Red By VT•DRB. FSCM 471427, Stu 31 of 39, 2019/Mar/19 PROT48 DocuSign Envelope ID: CFB628B5-6FE8-4C8Da4E3.5461F9B20045 6.1.5 Cleaning of Structural Parts All parts of areas from which mild corrosion has been removed should be thoroughly cleaned using an approved solvent. (Metal conditioner should not be applied at this time as it may interfere with subsequent dye penetrant inspection.) 6.1.6 Cleaning Other Areas All other areas to be inspected should also be cleaned of any deposits that might hinder the discovery of existing surface flaws. The protective finish need not be removed. The cleaning should be performed using any approved solvent. For cleaning high heat-treat steel parts, or areas in which a high heat steel part is installed, use only the approved solvents. 6.1.7 Crack Detection Technique When looking for surface cracks, the inspector should point his flashlight towards himself and hold it at an angle of 5° - 45° to the surface. (See Figure 6) The extent of the crack may be traced by directing the beam at right angles to the crack. Never direct the light beam at such an angle that the reflected beam shines directly into the eyes. The proper procedure is to keep the eyes above the reflected beam. FLASHLIGHT INCIDENT - LIGHT BEAM 5° TO 45° EYE ABOVE REFLECTED LIGHT BEAM REFLECTED LIGHT BEAM FAYING SURFACES CRACK OPEN TO SURFACE Figure 6 - Inspection for Cracks 6.1.8 Verification of cracks A lOx magnifying glass may be used to confirm the existence or extent of a suspected crack. Page 32 of 36 RON By VT-ORB. FSCM 47M27. Sht 32 or 39: 2019/Mar119 PROT49 DocuSign Envelope ID: CFB62855.6FE8.4C8D-A4E3-5461F982D045 6.1.9 Visual Wiring Inspection Perform visual inspections of the wiring. These visual inspections should be performed as part of the existing applicable inspection cycles, not to exceed 1200 hours. (Reference Tables shown on drawing [SSN REDACTED] for applicable installations based on aircraft model and subsequent Wire Routing drawing [SSN REDACTED]) Refer to the pertinent Maintenance Document listed below: Table 9 Maintenance Manual by Aircraft Aircraft, - TCDS Model Learjet 60 60 P/N MM-103 Bombardier Inc CL-600- 1A11 CL-600-1A11 PSP 601-2 Bombardier Inc CL- 6002Al2, CL-6002616 CL-600-2B12, CL-600- 2616 CL 604 AMM Dassault Aviation Falcon 10 Falcon 10 Dassault Falcon 10 Dassault Aviation Mystere-Falcon 20- C5/D5/E5/F5, Mystere Falcon 200 Mystere Falcon 20- C5/D5/E5/F5 Dassault Fan Jet Falcon Dassault Aviation Mystere-Falcon 50 Mystere Falcon 50 Dassault Falcon 50/50EX Dassault Aviation Mystere-Falcon 900 Mystere Falcon 900 Dassault Falcon 900 Galaxy/Gulfstream G100/SPX G100/Astra SPX P/N G100-1001-11-1 Galaxy/Gulfstream 1125 Astra 1125 Astra P/N 25W-1001-11-1 Galaxy/Gulfstream 200, Gulfstream G150 Gulfstream 200, G150 Gulfstream G-1159, G- 11596 G-1159, G-1159B Gulfstream II Gulfstream G-1159A G-1159A Gulfstream III Gulfstream G-IV G-IV Gulfstream IV Aircraft Gulfstream GV GV Gulfstream V Aircraft 500/550/S550 500/550/S550 Model 500 Maintenance Manual Page 33 of 36 Bern By VT-DRB, FSCM 47MZ7, Slit 33 of 39, 2019/Mar/19 PROT50 DowSign Envelope ID: CFB62885-6FES-4C8D.A4E3-5461F982D045 560 560 Model 560 Maintenance Manual 650 650 Model 650 Maintenance Manual Textron (Beechjet) 400, 400A 400/400A P/N 128-590001-9C HS.125 700A, 700B 700A, 700,B AFMS-125-700 BAe 125 800A, 800B 800A, 800B AFMS-800 750 750 AFMS-800XP 800XP 800XP AFMS-800XP 850XP 850XP AFMS-800XP 900XP 900XP AFMS-800XP Sabreliner Aviation NA-265-70, NA-265-80 NA-265-70, NA-265-80 P/N SE 0405 MM Sabreliner Aviation NA-265-65 NA-265-65 P/N SE 0303 MM A "visual inspection" is defined as the process of using the eye, alone or in conjunction with various aids, as the sensing mechanism from which judgments may be made about the condition of a unit to be inspected. This level of inspection is made from within touching distance unless otherwise specified. A mirror may be necessary to enhance visual access to all exposed surfaces in the inspection area. This level of inspection is made under normally available lighting conditions such as daylight, hangar lighting, flashlight, or droplight. A visual inspection may require the removal or opening of access panels or doors. Stands, ladders, or platforms may be required to gain proximity to the area being checked. The inspection criteria provided below is intended as general guidance. Conduct special inspection as deemed appropriate by each operator based on aircraft experience. Any discrepancies found should be repaired. 6.2 Wiring The inspection criteria provided below is intended as general guidance. Special inspection should be conducted as deemed appropriate by each operator. My discrepancies found should be repaired. a. Wire/Wire Bundle - Inspect for: Aluminum drill shavings, lint or dust on or inside wire bundles. Aluminum shavings can, with vibration or other motion, cut through wire insulation and provide a conductive path between wires in a bundle or to adjacent grounded structure. Lint and dust can accumulate on wire bundles and may, if subjected to overheated wires, ignite or possibly feed an electrical fire. Page 34 of 36 Rerd By VT-DRB. FSCM 47MZ7. Sht 34 o139. 2019/Mar/19 PROT51 DocuSign Envelope ID: CFB62885-6FE8-4C80-A4E3-5461F982D045 Wire insulation that has become brittle. Wire may be more susceptible to cracking. Damaged insulation and/or exposed conductor material of wires. Cracked, chafed and cut insulation can provide a conductive path between wires in a bundle or to adjacent grounded structure. Pinched wires can occur at wire clamps, connector backshell clamps, excessively tight cable ties, etc. Inappropriatefimproper wiring repairs such as the use of duct tape, electrical tape, poor crimp splices, etc. Wire insulation damage due to fluid leaks (i.e. fuel, hydraulic fluid, etc.) Separation of electrical wires from hydraulic, fuel and oxygen lines. Ensure a minimum of 0.5-inch separation and any wiring routed within 2.0 inches must be clamped to provide separation. Small bend radii of wire. Wiring subjected to excessively tight bend radii may sustain damage to the wire insulation. Sagging wire bundles. Ensure bundles are not allowed to droop onto structure, components, cables, hoses, other bundles, etc. Wire attached to the outside of a wire bundle using plastic ties instead of being installed under existing wire clamps. Can cause chafed and cut wire insulation. Unsupported wires running into conduit or wire supported in such a way as to pull the wire against the side of the conduit entrance instead of into the center. Can cause chafed and cut wire insulation. Proximity to high temperature equipment. Wiring shall be kept separate from high temperature equipment, such as resistors, exhaust stacks, heating ducts and deicers, to prevent wire insulation deterioration. Wires with different insulation types should not be routed together, where possible. Certain wire insulations may be easily abraded by other types of wire insulation. b. Wire Harness Clamps - Inspect for: Condition. Ensure any protective material on the wire clamp (i.e. rubber, plastic, etc.) is in serviceable and functional condition. Clamps should be secured to structure and wire bundle should be snug in clamp. Ensure clamps are not installed over splices. c. Connectors - Inspect for: Condition. Make sure connectors are free of corrosion, moisture, dust and metal shavings. Check for wom environmental seals, loose contact tension, proper contact locking, missing seal plugs, missing dummy contacts, etc. Drip loops should be maintained when connectors are below the level of the hamess and tight bends at connectors should be avoided or corrected. d. Backshells - Inspect for: Condition: Wires may break at connector backshells due to excessive flexing, lack of strain relief or improper buildup. Loss of backshell bonding may also occur due to these and other factors. Page 35 of 36 Rerd By VT-DRB, FSCM 47M27, Slit 35 o139, 2019/Mar/19 PROT52 DoeuSign Envelope ID: CFB628B5-6FE8-4C8D-A4E3-6461F9B2D045 e. Electrical Conduits and Sleeving - Inspect for: Susceptibility to water/moisture entrance: Conduits should not be susceptible to the entrance of moisture. If moisture going into conduits and sleeving is unavoidable, provisions should be made in the lower portions of the conduit to drain any moisture and prevent accumulation. Condition: Damage to sleeving and conduits, if not corrected, will often lead to wire damage. Make sure components are free from corrosion, moisture, dust, and metal shavings. Check that conduit is secured to structure. f. Terminations - Inspect for: Condition: Terminal lugs and splices are susceptible to mechanical damage, corrosion, heat damage and chemical contamination. The buildup and nut torque on wire lugs is critical to their performance. Grounding Points - Inspect for: Condition: Grounding points should be checked for security (i.e. tightness) condition of termination, cleanliness and corrosion. Any grounding points that have corroded or have lost their protective coating should be repaired and checked for proper resistance. CAUTION Use care when disturbing or removing wire harness/bundles to minimize the possibility of wire insulation damage or cracking. Care must be especially used in areas with severe moisture problems. During any repair, modification, or installation work in close proximity to wire bundles, mounts, connectors and systems, ensure that these areas are protected from and/or cleaned of metal shavings and debris. Page 36 of 36 Reid By VT-DRB. FSCM 47A427. Sht 36 of 39. 2019/Maril 9 PROT53 DocuSign Envelope ID: CFB62885-6FE8-4C8D-PAE3-5461F9B2D045 Appendix A - List of Applicable Publications NOTE: The latest released revision of the publications listed in the LOAF' constitutes the required information essential for continued airworthiness for the aircraft. Document Title Document Number Airplane Flight Manual Supplement [SSN REDACTED] Master Data List (includes wiring diagrams, equipment installations and ground test) [SSN REDACTED] TDR-94/94D ATC/Mode-S Transponder System (-5XX) Install Manual 523-0821492 GPS-4000( ) Global Positioning System Installation Manual 523-0780545 Equipment Installation Manual for the FreeFlight System Model 1203C GPS/SBAS Sensor 86764 Page Al of Al Red By VT-ORB. FSCM 47M27. Sht 37 of 3s. 2019/Mad19 PROT54 DocuSign ErnieMpe ID: CFB62885-8FE8-4C8D-A4E3-S461F9B2D045 Appendix B - Special Tools and Equipment Transponders - Aeroflex IFR-6000 or equivalent test set. GPS - JCAir 429 or equivalent 429 Bus Reader GPS - Oscilloscope Page 61 of B1 Rerd By VT-DRB. FSCM 47MZ7, Sht 38 of 39. 2019/Marrt 9 PROT55 DocuSign Envelope ID: CF8928856FE8-4C8D-A4E3.5461F9B20045 Appendix C - Discrepancy Reporting Form This form to be used by aircraft owner operators and modification centers to report discrepancies with modifications and repairs approved by the ODA. DATE DISCREPANCY DISCOVERED: Self explanatory. DISCREPANCY: Describe the discrepancy In detail. RECOMMENDED CORRECTIVE ACTION: Describe what actions you recommend taking to correct the discrepancy. REPORTED BY: Self explanatory. COMPANY NAME: PERSON TO CONTACT: PHONE NUMBER: TITLE: Signature: Self explanatory. Date: Self explanatory. Please submit the completed form to the following contact: mim ilikiODA Unit San Antonio, TX 78216 Phone: Email: Page C1 of C1 Reid By VT-DRS, FSCM 47M27, Sht 39 of 39. 2019/Marf19 PROT56 PROT57 0 US Cerviertem of Transprecen Acenhesealoa 061B Na 21200020 5v: 5/30201e Slecircnie Trackeo itenbee For FM Use day INSTRUCTIONS: Print or type all entries. See Tele 14 PROT458 §43.9. Part 43 Appendix 13, and AC 43.9-1 (or subsequent revision thereof) for instructions and disposition of this form. This report is required by law (49 PROT459. §44701). FaNure to report can result in a civil penalty for each such violation. (49 PROT460. §46301(a)) 1. Aircraft USA/N493LX Senal No. RK-244 Make Raytheon Aircraft Company Model 400A Senes 2. owner Flight Options Address (As shown on registration certificate) Address Cry Richmond Helpers State OH 20 44143.1453 Court,/ USA 4. Type Repair Alteration Unit Make Model Serial No. O x AIRFRAME minneeiriir (As described in Item 1 above) xx.h. 0 POINERPU*17 IMI ni PROPELLER E El APPLIANCE Type Manufacturer B. Conformity Statement Nam Neeani Aerospace U. S. Certacated mechanic I mammon, Maine Foreign Certificated Mechanic Ce Cleveland sum OH x CerbeCeled Repair Station CRS# 25NR667B AI 44I43-1453 CoottY use D. I certify that the repair and/or alteration made to the unit(s) identified in tern 5 above and described on the reverse or attachments hereto have been made in accordance with the requirements of Part 43 of the U.S. Federal Aviation Regulations and that the information furnished herein is tree and correct to the best of my knowledge. Aer 14 PROT461 Part 43 App. B Signature/Date of Authorized lndivi /2-1 -..110/- 7. Approval fo - / - -.1 /Y Pursuant to the authority g'ven persons specified below, the unit Identified in item 5 was 'nspected in the manner prescribed by the Administrator of the Federal Aviation Administration and is FlApproved fi Rejected FAA Flt. Standards Inspector Manufacturer PerSOM Approved by Canadian Department of Transport BY FAA Designee X Repair Station Certificate or Designation No. CRS# 25NR667B Signature/Date of Authorized 7 -17-7/.7 V- o /- zei/ PROT58 NOTICE Weight and balance or operating limitation changes shall be entered in the appropriate aircraft record An alteration must be compatible with all previous alterations to assure continued conformity with the applicable airworthiness requirements (if more Spaced required. attach additional sheets Identity kWh aircraft nationality and registration mark and date wan( comma fed ) N493&X 12/2912013 Dale This 337 is amended 01APR2019 to correct a Typo in block 8. Installed New Pitot Probes in accordance with STC ST10959SC. Nextant Master Drawing List Document [SSN REDACTED] Rev CC EO24-11. Removed Pitot Probes Part Number PHi 100-MU-R-1 Removed Pitot Probes Part Number PH1100-MU-L-1 Installed Pitot Probes Part Number PH1100-MUR-EN Serial Number 1975803 Installed Pitot Probes Part Number PH1100-MUL-EN Serial Number 1728401 Leak Check carried ouit Beechcraft Aircraft Maintenance Manual Chapter 34-12-00-201 ICA Continue with Normal Hawker Beech Maintenance Practices for this area. END MAdditiOnal Sheets Are Attached AA Form 337 (10/06) Paec 2 PROT59 DEPARTMENTOFTRANSPORTATION-FEDERALAVIATIONADMMISTRAMON STANDARD AIRWORTHINESS CERTIFICATE I NATICNALRY AND 2 MANUFACTUFtER AND MODEL 3 AIRCRAF7 SERIAL 4 C.ATEGORY REGISTRATON MARKS Raytheon Aircraft NUMMER N188TS Company 400A RK-244 Wansport AUTIORITY AND BASIS FOR ISSUANCE Tim ~hem mikse Is MAO 'usunn 41 PROT462. I M704 and tet tra is ol te Med mumx. Im ~I nebb kanel has teen Ameneel and bm& b con» 4) he I. møta Sekt MOS wen In Si *nåml erd tes Sin Ikno b ~n rimniner4 Min mokaNs memMmenve anti Mit areteliness ca as moMnI ty Ames t ts Con ca MAIMIOnn fid bonn, emem M mad Menn &menn -None- I TERMS AND CONOITIONS Inmm soner suemenel summint motet ora IsminIca dis b «bunne estitethof by I. FM, dIe annellinem ~tale e &KM N losa as te munmmak penmee nallamict and ~Sms are parmaIncondate w1 Pon2I.43, and tiden NOS Avatm Rimelann. As irs~ sd M an. N#4Iffld b elt Unnd Maks. )ATE OF ISSUANCE R3/06/2014 GL-25 44,111~.~01. 3 pts orket 14SCERIIRCATE RUST SE DISPLAYER NITE MIOIM1 IR ACC0R0ANCE WRII APPLICISE KREML AMT> REGIAATOIS. A Fonn 1100.2 (04-11) Supersedes Previous EMMA DESIGNATION NUMSER FeoPn fttRAvi- PROT60 PROT61 UNITED STATES OF AMERICA DEPARTMENT OF TRANSPORTATION-FEDERAI. AVIATION ADMINISTRATION STANDARD AIRWORTHINESS CERTIFICATE I NATIONALITY AND REG;STRATION MARKS 188TS 2 MANUFACTURER AND MODEL Company 400A 3 AIRCRAFT SERIAL NUMBER RK-244 5 AUTHORITY AND BASIS FOR ISSUANCE This aivotess cedifute is issued pursual to 49 PROT463.§441d4 and cues that, as of te dale of issuance, the knit to vkh issued has been lispected and found la cohfomi to the type certificate therefor, to be in conk for safe operation, and has been shoo lo meet the (quires alba appliote (mottos:Pie and detaised airworthiness oode as provided by Wavle) lhe Convention on loleminhal Cid Ando, except as holed bait bagel: -None- FS-'?SO 4 CATEGORY Iransport 6 TERMS AND CONDITIONS UtSSOOnef seehdered, suspended, reveled, Of a lEnitatioo date is otherwise eslabished te FAK, this iirivofiess cetficale is effective as long as the maillenance, prevehlative mairdenarte, and alleradols are performed in accordance wit Pat 21, 43, and 91 of the Federal Aviation Regulations, as appropriate, and the ate is relisleted ih to Utd States. DATE OF ISSUANCE DESIGNATION NUMBER R3/06/2014 GL-25 Arty allergen, reprodudon, Of misuse of Oils rdicale may be puhishab'e by a fine rId weeding 11,660 mririsonment hot exceerfn9 3 elfS aboth. THIS CERTIFICATE MUST BE DISPLAYED IN THE AIRCRAFT IN ACCORDANCE VIITH APPI(CA8LE FEDERAL AVIATION REGULATIONS. FAA Form 81002 (04.11) Supersedes Previous Edition PROT62 PROT63 U S Department or Transportation Administration October 9, 2018 Aircraft Registration Branch AFS-750 To whom it may concern: During review of AFS-750 records it was found that a discrepancy existed of the Airworthiness Certificate for N188TS, Make: Raytheon Aircraft Company, Model: 400A, Serial Number RK-244, it was noted that the Airworthiness Certificate registration number did not show the required Nationality letter "N". During inspection of the aircraft it was found that the original Airworthiness Certificate did in fact have the required Nationality letter. Made a copy of the original Airworthiness Certificate and forwarded to AFS-750. If you have any questions in this matter, please contact me at FAA PMI CLE FSDO PROT64 I PROT65 US Department of Trarecolaeco Federal Minion AenenIstratIon nefiee 2120-0020 Erg 531/N18 Electnooe Trecbro Nine INSTRUCTIONS: Pnnt or type an entries. See Title 14 PROT464 §43.9. Pan 43 Appendix B, and AC 43.9-1 (or subsequent revision thereof) for Instructions and disposition of this foam. This report is required by law (49 PROT465. §44701). Failure to report can result in a civil penalty for each such violation. (49 PROT466. 146301(a)) 1. Aircraft USA / N188TS Serial No. RK-244 make Model 400A Series 2. Owner THORAIR LLC Address (As shown on registration certrficate) swan C.,/ SANDUSKY State OHIO Zp 44171-221$ Catrily UNITM STATES 3. For FM Use Only 4 Type 6. Unit Identification Unit Make Model Serial No. Repel Alteration RAMC°. MOW Call1en AIRFRAME POWERPLANT X 7 [7 PROPELLER ri❑ APPLIANCE Type Manufacturer [ADDRESS REDACTED]atement Ilsere Heston: Arnow* U. S. Certificated Mechanic J Manufacturer woes, :WO 0." s "eert Pa in., r cc, ciewiene sub ollb i Cerlillaterl Repast StabOrt CRS# WC7R346J ye 44143 careen. united Stain Certificated Maintenance OrganizatiOn D. I certify that the repair and/of alteratIon have been made in accordance furnished herein is true and correct EXtended range fuel made to the unit(s identified in item 5 above and described on the reverse or attachments hereto with the requirements of Pan 43 of the U.S. Federal Aviation Regulations and that the information to the best of my knowledge. per 14 PROT467 Part 43 App. B 0/06/2017 . crrova atom to ce Pursuant to the authority given persons specified below, the unit Idenrel Administrator of the Federal Aviation Administration and 's I in Item5 1/22sinspeed Approved ct in the manner prescribed by the Rejected ,--. - .0 FM Flt. Standards Inspector Manufacturer Maintenance Org nization Department Of Transport BY ~I C FAA Designee I Repair Station Certificate Designation or No. CRS# WC7R346J4 10/06/2017 age PROT66 NOTICE Weight and balance or operating limitation changes shall be entered in the appropriate aircraft record. An alteration must be compatible with all previous alterations to assure continued conformity with the applicable airworthiness requirements. (If more space is required, attach additional sheets. Identify with aircraft nationality and registration mark and date sat completed) N18878 10/06/[ADDRESS REDACTED]C# ST02371LA Winglet Option Installation Installed Nextant Aerospace Winglets IAW Nextant Aerospace STC# ST2371LA amended date 3/10/2017, Master Data List# MDL-NXT-001 Rev J, dated 2/14/2017, and minor deviations IAW EO# NT-EO-0817-09 Rev A and NT-EO-1017-09 Rev IR. Removed Equipment Item Left Wingtip Assembly Left Strobe/Position Light Assembly Wing Tip Lens Right Wingtp Assembly Right Strobe/Position Light Assembly Wing Tip Lens Tail Strobe Light Tail Position Light Strobe Power Supply Installed Equipment Item Left Winglet Assembly Right Winglet Assembly Left Winglet Light Assembly Right Winglet Light Assembly Tail Strobe Cover Plate Tail Position Cover Plate Part Number 45A10552-001 45A88750-22 8888-170000-01 45A10552-002 45A88750-22 8888-170000-02 4588315-121 45A88754-11 01-790080-00 Part Number NEXT-SA15250LA57-10001 NEXT-SA15250LA57-10002 87-03916-001 87-03917-001 NX0047-3340-0101-001 NX0047-3340-0102-001 Serial Number 00575 Serial Number S-N EXT-0001 S-NEXT-0001 00214 00216 ICA Follow the maintenance inspection practices in the Nextant Aerospace Instructions for Continued Airworthiness Document No. NX0047-ICA0-0101 Rev. A, dated 6/20/2016 or later FAA approved revisions. AFMS FAA Approved Airplane Flight Manual Supplement Document No. NX0047-AFMS-0101 Rev. IR, dated 3/10-2017 or later FAA approved revisions have been added to the Airplane Flight Manual Weight and Balance Reference Weight and Balance Report dated 10/06/2017 END FlAdditional Sheets Are Attached Page 2 PROT67 1aIrt 3tatrrir.i peparbnent of troantsporittiou - "cigirdcrul (Affirztion iiitiotruttrur $uppinnental Qltrtificute Xenzhe ST02371LA g,444420,eiwawil, Nextant Aeros a LLC Richmond Heights, Ohio 44143 A../4404firiti4.04,2,0 (;" aro devOrnA.• A4e4g:toennaltilseeitodel4 deneraiennei ernaectanisreensi dereVeer od ifrowajeasestiowissnee6 eserotoeisreisam reyessiewswhO 19aeke 25* oyet4 Faival...4exmaw. ...94,64.4kni. *Certification basis is set forth on TCDS A I6SW and continuation sheets 3 and 4. araf tellvickae 4 / seb g.....stfrjeassrelicsondao.• Al6SW agaa• Beechcraft Corporation AlCedef 400A Sava-ohiv),AF,Trog'.ivr. Veer Alteration of a Beechcraft Corporation 400A airplane, to replace Pratt Whitney JT15D-5 series engines with Williams International F.144-3AP engines (TCDS E3GL) with Full Authority Digital Engine Control (FADEC) and associated systems (Config. A) and (tor) the installation of Nextarrt Winglets (Config. B), in accordance with Nextant Aerospace Master Drawing List No.: MDL-NXT-001, Revision Ilt dated 8/22/2011, or later FAA approved revisions and the appropriate FAA approved Airplane Flight Manual Supplement(s) for the applicable installed configuration(s): NXT I -AFMS, Rev IR, dated September 1.5, 2011 or later FAA approved revisions Confic. B: NX0047-AFMS-0101, Rev III, dated March 10, 2017 or later FAA approved revisions 51207Vi(711:104/ ffed.g.;:seaarand. The installation thould not be incorporated in any aircraft unless it is determined that the interrelationship between this installation and any previously approved configuration will not introduce any adverse effect upon the airworthiness of that aircraft. The approval of this modification applies to the above-noted airplane models only. If the holder agrees to permit another person to use this certificate to alter the product, the holder shall give 'Mrs other person written evidence of that permission. (CONTINUED on page 3) .97Z ageterAra• mall* idryneronar dun weenie lg. k'tt)A. yieroaneenenoin e jot de.o4t-te Juvrevanse.tmonendtar aosts.4/^ a lawsresirays dole w theitsgm.YE eViii4e4.44 EgenadheErrhso (AA Alwree.olyx;thew...4,197,a44Theen. 244 0rffstieraim Ode Vei.l.gredrner.• March 24, 2008 September 27, 2011 arehnseaSeesei. .7173.14141. • March 10, 2017 .4osestehiss. ore.44.4a5sse:sedmisie Manager, Propulsion Branch Los Angelus Aircraft Certification Office Arty aarnation of this costifrata is punishato 6y a fans of not EVANfily) 51.004 or islphsromar rot goodthe I Yoga w both Mt Porn t, te.f (10.40) Pegs a of Rifts' eatific.... trip, k miffing( in acrordaricsteitfi filt22.47. PROT68 PROT69 ait/bat/tin Putterien ,Drparhnritt of Zgrzruspnrtritinit - gtheral Akan-firm Ahministratinit $upplrnwntal `Tut Certificate (Crutinuatitm Akeet) Are/dr ST02371LA ..ganeltruleet7J ernea;raitas 7traetiuteeelY Nextant Aerospace, LLC, "Installation of Rockwell Collins Pro Line 21," Amended STC ST10959SC, dated September 26, 2011 or later FAA approved revisions is required as part of this alteration. The new Vmca and Vmcg values are 94 KIAS and 93 KIAS respectively. The new engine minimum rated thrust is 3,031 lb at sea level, flat rated to an ambient temperature of 77°F. Approved engine fuels are: Grade Specification Jet A ASTM-D 1655 Jet A-1 ASTM-D 1655 FAA accepted revisions of the Nextant Aerospace, LLC Instructions for Continued Airworthiness document must be made available to the operator with the installation of the STC configuration(s). o Config. NXT1-ICA, Revision IR, or later FAA accepted revisions. o Config. B: NX0047-ICAO-0101, Revision A, or later FAA accepted revisions. g.../OrpoM Sera, The certification basis for this modification is as follows: The original certification basis for the Hawker Beechcraft Model 400A airplanes identified on TCDS AI6SW, Revision 26, dated March 17, 2010: Pan 25 of the Federal Aviation Regulations effective February 1, 1965. as amended by 25-1 through 25-40, plus §§ 25.1335, 25.1351(d), 25.1353(c)(5), and 25.1447 of Amendment 25-41: §§ 25.29, 25.255, and 25.1353(c)(6) of Amendment 25-42; and §§ 25.361(b) and 25.1329(h) of Amendment 25-46. Part 36 of the Federal Aviation Regulations effective December 1, 1969, as amended by 36-1 through 36.17; SFAR 27 effective February 1. 1974. as amended by 27-1 through 27.5; and Special Conditions No. 25-ANM-32 dated February 22, 1990 (High Altitude Operation at 45,000 feet), and Special Conditions No. 25-ANM-33 dated June 18, 1990 (Lightning and Radio Frequency Energy Protection). (See NOTE 12) Equivalent Safety Items (I) Out-of-trim characteristics FAR 25.255 (2) Pilot compartment view FAR 25.773(b)(2) (3) Passenger compartment door FAR 25.813(e) (4) Emergency cut marking FAR 25.811(d)(1) and 25.811(d)(2) Application for amended Type Certificate dated February 18, 1988. Jtry alteration of this certiftatte is punishable fy a fine of not akseefing $1,000, or imprisonment not woofing 3 years, or tot& ma tom •110-20.0-6•11 Page > of 4 his certificate may be transfermf in aa-ordance vita ffR 121.47. PROT70 PROT71 Alltittb "Mtn 2.nterics cpartunnt of Transportation - AchrraI cAfitatinn cAlintinistratbn $uppinnental `Crypt Griffin:dr (aradinuation *int) ifielenhie ST02371LA Regulation at a later amendments for components and areas affected by the change (Ref. FAA approved Compliance Check List): Subpart A - General: §§ 25.2(25-99) Subpart B - Flight: §§ 25.207(25-121), 25.255(25-42) Subpart C - Structure: §§ 25.571 (25-96) Subpart D - Design and Construction: §§ 25.603(25-46), 25.605(25-46), 25.611(25-123), 25.613(25-112), 25.625(25-72),25.832(25-72), 25.863(2546), 25.869(25-123), Subpart E - Powerplant: §§ 25.901(25-46), 25.903(25-100), 25.951(25-73), 25.961(25-57), 25.981(25-125), 25.994(25-57), 25.997(25-57), 25.1013(25-72), 25.1019(25-57), 25.1021(25.57), 25.1043(25-42), 25.1045(25-57), 25.1091(25-100), 25.1093(25-72), 25.1103(25-46), 25.1141(25-115), 25.1143(25-57), 25.1163(25-57), 25.1165(25-72), 25.1181(25-115), 25.1183(25-101), 25.1185(25-94), 25.1189(25-57), 25.1195(25-46), 25.1203(25-123), 25.1207(25-46). Subpart F - Equipment: §§ 25.1301(25-123), 25.1305(25-115), 25.1307(25-72), 25.1309(25-123), 25.1316(25-80), 25.1317(25-122), 25.1321(25-41), 25.1331(25-41), 25.1351(25-72), 25.1353(25-123), 25.1357(25-123), 25.1381(25-72), 25.1431(25-113),25.1438(25.41), Subpart G - Operating Limitations and Information: 4§ 25.1501(25.42), 25.1521(25-72), 25.1527(25-105), 25.1529(25-54), 25.1543(25-72), 25.49(25-40), 25.1551(25-72), 25.1557(25-72), 25.1581(25-72), 25.1583(25-105). Subpart H - Electrical Wiring interconnection Systems (EWIS): §§ 25.1701(25-123), 25.1703(25-123), 25.1705(25-123), 25.1707(25-123), 25.1709(25-123), 25.1711(25-123), 25.1713(25-123), 25.1715(25-123), 25.1717(25-123), 25.1719(25-123), 25.1721(25-123), 25.1723(25-123), 25.1725(25-123), 25.1727(25-123), 25.1729(25-123), 25.1731(25-123), 25.1733(25-123). 14 PROT468 Part 34(34-3): 34.11 14 PROT469 Part 36 ( 36-28): 36.1-36.7, 36.101--36.105, 36.1501, 36.1581. The following Nextant Aerospace Continued Airworthiness Supplements are applicable to airplanes modified in accordance with this SIC: • Master Minimum Equipment List document No. MMEL Rev. 8, dated 02/21/2011 or later FAA approved revisions. • EWIS (Electrical Wiring Interconnection Systems) Inspection Procedure/Report No. NXTI-EA-007 Rev A dated 8/24/11 or later FAA approved revisions. fisty etonstion of this cortificatoispanishafr ty a fins of not mutant; $1,004 or impironment not meeting 3 years, or 6oth. ran tar. •110-2 (10-641 Hoe 4 of ?Fu certificate wiry ht trittufard in ocronforwe with Tilt21.47. PROT72 PROT73 e2b G1 U.S Detwomert ce (Airframe, Powerplant, Propeller, or Appliance Trongorubon Foam, Aviation AdoONstnelon Form Po tressed OW No 2120.0020 11/30,/2007 Electronic Tracking Number INSTRUCTIONS: Print or type all entries. See FAR 43.9. FAR 43 Appendix B. and AC 43.9-1 (Or subsequent revision thereof) for instructions and disposition of this form. This report is required by law (49 PROT470. 1421). Failure to report can result in a civil penalty not to exceed 51.000 for each such violation (Section 901 Federal Aviation Act 1958) 1. Aircraft N493LX Serial No. RK 244 Make Model 400A Series 2. owner Name (As Mew,, On registration Certificate) Flight Options .LLC Address city Richmond Heiahts stow OH To 44143-1453 Country aL li 4. ype Repair Alt ration Unit Make Model Serial Number K 0 AIRFRAME (As arescnbed in Item I above) 0 K POWERPLANT 0 K PROPELLER O K APPLIANCE Type Millilelig Of 8. Conformity Statement B Kind of Agency Nama Constant Aviation Address Cry Cleveland stow. OH zip 44143-1453 country USA O U.S. Certificated Mechanic O I PAartufaCturtot O Foreign Certificated Mechanic C. Certificate 140. a Certificated Repair Station CRS # WC7R346J O Certificated Maintenance Organization D. I certify that the repair and/or alteration made to the unit(s) kilentilled in item 5 above and described on the reverse a attadvnents hereto have been made in accordance with the requirements of Part 43 of the U.S. Federal Aviation Regulations and that the information furnShed herein is true and correct to the best of my knowledge. per 14 PROT471 Part 43 K App. 8 Signature/Date of Authorized Inc% • 09/Sep/2017 7. Approval for Return to Service Pursuant to the authority given persons specified below, the un Aciminlyttele: el the Federal Aviation Administration and iS t identified a in item APPROVED 5 was IN inspected in the manner prescnbed by the REJECTED BY FAA FR Standards Inspector Manufacturer Person Approved by Canadian FM Designee X Repair Station Certificate or WC7R346J Signature/Date of Authorized Indwilua 09/Sep/2017 FAA Form 337 (10-06) PROT74 NOTICE Weight and balance or operating limitation changes shall be entered in the appropriate aircraft record. An alteration must be compatible with all previous alterations to assure continued conformity with the applicable airworthiness requirements. S. Description of Work Accomplished (If more space is required, attach additional sheets. !dentin/ with aircraft nationality and registration mark and date work completed.) N493LX 12/Sep/2017 Date This is a revised FAA 337 to correct the Serial Numbers of the Engines that were installed by Nextant Aerospace CRS # 25NR667B on FAA 337 Dated 05/30/2013 Nextant Aerospace Completed STC # ST02371LA Removed Pratt and Whitney 1115D-5 Series Engines. Installed the Williams International F144-3AP Engines with Full FADEC and Associated Systems in accordance with Nextant Aerospace MDL -NXT-001 Rev IR Dated 08/22/2011 or later FAA approved revisions, and FAA Approved AFM Supplement NXT-1-AFMS Rev IR dated 9/15/2011 of later FAA Approved revisions. Installed Left Engine Part Number. 111000-202 Serial No. 252767 Installed Right Engine Part Number 111000-202 Serial No. 252768 ICA AFM Supplement was installed on Aircraft. Nextant Aerospace Instructions for Continued Airworthiness Document NXT-ICA Rev IR or later FAA accepted revisions are included in the Aircraft Maintenance Records. Carried out Engine Ground Runs and System 0PS checks IAW Ground Test Plan [SSN REDACTED] Rev F. End Additional Sheets Are Attached FAA Form 337 (10.06) PROT75 DEPARTMENT OF TRANSPORTATION -FEDERAL AVIATION ADMINISTRATION • STANDARD AIRWORTHINESS CERTIFICATE 1 NATIONALITY AND REGISTRATION MARKS 188TS 2 MANUFACTURER AND MODEL Company 400A This aiNionhiness certificate is issued pigswill ro a9 U.S,C.§ 44104 and ciffeas tat as of h dale of issuance, lbe a'rrctal to-Old issued has been inspected and loth Ia conform la the biao l2ftfolIO MeV, to be IP cordon for sale petal, nod has been shown lo meet Ila requirements of die applicable orrhensine and dallied airworthiness code as provided by Annul Odle ConverEon on International CHil Nation, min as noted herein, Exceptions: NUMBER RK -244 4 CATEGORY Transport -None- Untasssoonersurt¢ndered,suspended,sevoked,oraIek Non date isotheneise eslablIshed by Ilia FAn:Bils ainiiiness Ls effective as loll as Ibe maintanance, [WPM MAIRIOPRO, and detains are performed in accolanoe Mt Parts 21, 43, and Biddle Fedtial Aviation Reohlons, as appropriale, and the airclAis ROM IP the Ad Stales. ' 83/06/2014 DESIGNATION NUMBER GL-25 Any allemlion, reproduction, or misuse alibis cediNcele maybe punishable by a he nal Bank) RN) ar IMOSIONPIPOIReed4 3 years or bd. THIS CERTIFICATE MUST BED SPLAYED IN THE AIRCRAFT IN ACCORDANCE WITH APPLICABLE FEDERAL AYIAi10N REGULATIONS, FM Form 8100.2 (04.11) Supersedes Previous Edition PROT76 4 4 PROT77 DEPARTMENT -FEDERAL AVIATION ADMINISTRATION STANDARD AIRWORTHINESS CERTIFICATE 1 NATIONALITY AND REGISTRATION MARKS N49311 2 MANUFACTURER AND MODEL Company 400A NUMBER RK -244 4 CATEGORY Transport This ainvotiness Rite is issued ptusuardlo le U,S.C. §,14iGit and cerUdes tali as of Ihe dole of issuance, the aircraft 0 which issued has been inspected and teund 0 coin to 0e type cetterate 086,0 he in condition foi sale operation, Ed hos been shown 0 meth tecui:emeols of the applicable comprottenSiVe and delailed aimodiness cede as proxided by Annex ft to Ihe Convention Internaennal Civil Aden, except as noted herein. Exceptions: *None* keg SeqrSUR ntlemtl,suspended,revoked,ora terminationdateisolheraiseeslebfshedbytheFAA,thleakwodhinessceAiticale is effectiN asking sthamaintenance,preventativemaiNenance,am fl2 it Pot 21,43, Bed 91 of the Federal Aeileen Re dalions,a5 *ale, and to airCril DESIGNATION NUMBER 03/06/2014 DART833943g Any allelloo, reprodudoo, a misuse of INS ceititale may he punishable by a fine not exceeding $1,069 or imposoemeel rot exceeding 3 pars or both, THIS CERTIFICATE MUST BE DISPLAYED IN THE AIRCRAFT IN ACCORDANCE WITH APPLICABLE FEDERAL AVIATION REGULATIONS. FAA Form 8100.2 041) Supersedes Previous Edition PROT78 I PROT79 4/10/2014 Flight Standards District Office Great Northern Tech Bldg. II North Olmstead, Ohio 44070 Cleveland Flight Standards District Office: ThorAir LLC. would like to request a new airworthiness certificate for Serial number RK-244, Raytheon Aircraft Company 400A. The reason for requiring an airworthiness certificate change is a new registration number is being placed on the aircraft. Included with this letter is AC Forum 8050-64 issue date Apr 03, 2014 showing the change in registration number from N493LX to N18815. Signature of Owner: Title of Owner: President of ThorSpoft, Inc., ThorAir, LLC. It's Member PROT80 PROT81 FAA FORM 8130-6, APPLICATION FOR U.S. AIRWORTHINESS CERTIFICATE Form Approved O.M.D. No.2'20-0018 Es notion Date 02/28/2013 0 APPLICATION FOR LI' S 0461€70171 U.S. AIRWORTHINESS ol "r4Hponalion Federal AMARA CERTIFICATE Ameniurstion INSTRUCTIONS- PIN ea IYPe. Done 464 in shaded meat these we for FAA use only &AP °nye; only to en eunspize0 FAA REOOSON4live. II eddma,el space is (waned. use eaectunent Fn special Opt panne, complete Sect ens I1 VI. end Vii es appecable a i 1. REGISTRATION MARX N493O( 2. AIRCRAFT BUILDERS NAME nAm Raytheon Aircraft Co 3 AIRCRAFT MODEL DESIGNATION 400A 4 YR. MFR. 1999 FM CCOiNG 5. AIRCRAFT SERIAL NO, RK-244 6. ENGINE BUILDER'S NAME (MAW Williams International 7 ENGINE MODEL DESIGNATION FJ44-3AP 8. POWER CP pew s 9 es 2 PROPELLER [ULCERS NAME Fa/ N/A 10. PROPELLER MODEL DESIGNATION It AIRCRAFT IS I( ac eropk*F41 N/A IMPORT R 1 N d APPLICATION IS HEREBY MADE FOR Om mks ma/ I A I STANDARD AIRMRTHINESS CERTIFICATE essen...") I Im•-• I I00-00 I Iw000.0 Ill m-0-00, I Ice...n.1 I• 9. 03. I tom,- a SPECIAL AIRWCRTHIMESS CERTIFICATE Mom era HRH 7 PRIMARY 9 UGHT-SPORT Rom aHo I I AIITMIT• I I PamN'PIFIRTIFR I I W074-STR-Conirtd I I G&W I I Lighter then At 2 LIMITED 5 PROyiSIONAL 1 CLASS I Awsue. emu 2 CUSS,' 1 AGR/CULTURE AN PEST CONTROL 2 AERIAL SURVEY 3 AERIAL ADVERTISING 3 RESTRICTED Asa* Ammon, A Ms amend, 4 FOREST memo NassAmcM 5 PATROLLING 6 MATTER CONTROL 0 OTHER 6moel 1 RESEARCH AND DEVELOPMENT 2 AMATEUR BUILT 3 EMOTION 4 AIR RACING 5 CREW TRAINING 6 MARHET SURVEY 0 TO SHOW COMPLIANCE WITH THE PROT472 7 OPERATING MoMMYCS*9.41FIT BUILT AIRCRAFT EXPERIMENTAL a Esisiing Myatt wilICIA en limning., pleura a do mimosa $1011 4 antra smem(s) re a amoesi s BA OPERATiNG 86 a °Ining POMEIV U614E-SPORT lIC IION U9N-SINH 4gelP600. ."I sry tax1/31Oxial11011486, Mary finsotHress airmailietaaa a 21 I90 9 UNMANNED 9A REVAK,. ma DEVELOPMENT IOC' I CREW TRAINING AIRCRAFT 98 MARKET SURVEY I FERRY FLIGHT KR REPAIRS. ALTERATOG. PAAINTEWMCE OR STORAGE SPECIAL FLIGHT PERMIT wow. 2 EVACUATE FROM AREA OF IMPENDING DANGER 13 epreNen re eneA/Csa Irer corwAre Nam so 4. we 44•44.4.4.. en 44.44 440 3 OPERATION IN EXCESS Cf MAxaTUR4 CERTIFICATED TAKEOFF MIGHT 4 DELIVERING OR EXPCRDNG I 6 I • I PRODUCTION FLIGHT TESTING 6 CUSTOMER DEMONSTRATION FLIGHTS cl a MULTIPLE AIRWORTHINESS CERTIFICATE p.m. ABOVE 1,1•16:MOOMMOM fl ees 'Gaffed, MOND* i Pi in 5 X d A. REGISTERED OMER Ma Mom M confooled oat intate, IF DEALER. CIIECK HERE I NAME ThorAir LW MS. Sandusky. OH 44871 B. AIRCRAFT CERTIFIGATICR BASIS Him ammo ems we awasse• me ga MOMM3) i AIRCRAFT SPEOFICATKFI OR TYPE CERTIFICATE DATA SHEET Ira Ne am 44.44.',1 A16SW Rev 28 1 AIRWORTHINESS DIRECTIVES omen et emkm A Ma a• Hamm Toe moot*, ..44.4.4.4 0 Me IMMO Wainer WMIONP in. *M Ss AP ow • / DM Mm•Mitak.) Bi Weekly 2014 2/10/2014 - 02/23/2014 ARCRAFT LISTING /camp normrts$ WA SUPPLEMENTAL TYPE CERTIFICATE 6/4 me es nth 47c Accepome) See Attached Sheet C AIRCRAFT OPERATION AND MAINTENANCE RECORDS CHECK IF RECORDS IN CCSIPUANCENAni 14 PROT473 Ma 92417 TOT AL AIRFRAME HOURS 8616.1 TTAF 3 EXPERIMENTAL OM.Y crorFANH to.. mw, 4n [strew, AAA/ a4` 40 WA D. CERTIFICATON • I hereby <wily MAIM?* accordines mils TM 49 01the WHO Stale. aiwarTness cwVcate Amsted 14filitered arner (or his 4WD 8 MO Put deaf! m tam. that me anon Cole 44101 Is are [pica es FERMI Aselben RepAMICess. end the Ihe eircreA Is nomoto In 16 FORM ANOKA ASWIliSrea en el DATE OF APPLICATION 03/06/2014 NAME AND TIRE 'Fin tn..) Anton Koprivnik Agent &GNAT N. INSPECTION AGENCY VERIFICATION A THE AIRCRAFT DESCRIBED ABOVE HAS SEEN INSPECTED AND FOUND MRAORTHY BY: 044.40•44. mos ovIr 24 Cam/ V. I 2 14 PROT474 Mel 121 CERTIFICATE HOLDER Pre CooMMI0 Mal 3 CERTIRCATED MECHANIC Mfrs 04.1400"421 6 CERTIFICATED REPAIR ARON IOW amen NO) 5 AIRCRAFT MANUFACTURER MA* nine es fray DATE TILE SIGNATURE V. FM REPRESENTAITVE MIN/CATION Ossamtc sepszes,4 sea e.4414.44 THE CERTIFICATE REQUESTED A I TIM :+m the rave 61404X4 ii1Seetion 1 or W meets moan for 4 AMEMSMETIT OR MODIFICATION OFCURRENT AIRWORTHINESS CERTIFICATE B. Inspemon the spec* figt4 pemil Lwow Seam MI Tros con04100 Dy I FAA INSPECTCR FAA DESIGNEE DATE 03/06/2014 MIOGIFS00 CFFICE GL-25 4 FAA INSPECT SIGNATURE DART833943 MP FM Form 8130-8 (4/11) NI PteirCUI Editions Superioded pt t it s, 9 V C. 1.--• MAR 1 0 2014 CLE- PROT82 §I IF; 2 A. IAANUFACTURER NAME ADDRESS B. PROOUCTON BASIS (OMCk Opplable Rehl PRODUCTION CERTIFICATE (GMT ACAS OPMFMAt Noted TYPE CERTIFICATE OTHER: C. GinQUANTITY OFCERTIFICATES REQUIRED FOR OPERATING NEEOS NAME AND TITLE (MINNOW) SIGNATURE VII. SPECIAL FLIGHT PERMIT PURPOSES OTHER TIAN PRODUCTION FLIGHT TEST A. OESCRIPTON OF AIRCRAFT REGISTERED OAT ER ADDRESS BURGER (Mgee) MODEL SERIAL NJM BE R REGISTRATION NARK 8 OESCRIPTION OF FuGHT CUSTOMER DEMONSTRATION FUGHTS O fl ee ' *plait) FROM TO VIA OEPARTURE DATE DURATION C CREW REQUIRED TO OPERAT E DE AIRCRAFT AND ITS EQUIPMENT 1 1 PILOT I 1 COP LOT I I FUGNTENGiNEER I I OTHER (Spay) D THE AIRCRAFT CCU NOT MEET THE APPLICABLE NRWORTNNESS REQUIREMENTS AS FOU.ONS: E TIE FOLLONNG RES I R CTIOW ARE CONSIDERED NECESSARY FOR SA.E OPERATION. (Use ran E Hammy) F CERTIFCATIOI Ant" cm* Minim um roosono0 owmr (or Na KAM) of d out Seated Mom tot to *ar is registered Min tre Foleng Maga. Adorn unman in accorcance win DM 49 ol ligo Urand Salm Can 4001 olzo and migicabig Fail Mean Rogotallont AM MK Os Scut hog tom Monger) end is Nete Ice Om fltaN Onamect DATE NAME ANOMIE (PAN HIM/ SIGNATURE R ta a brg as ...IZ;: ec i , i s; 4 gi 1 A Operatng Lentaactm are Matkings In COnVerma WEIN PROT475 WOOF, Ott As AppIcatle 0. Satomat <I Concenitg. FAA Ferro BI304 Meath when reptsmx0 It RAO Airmeiness CelAcalica ke mom Mae (Mach when resiroN a CononI CP6M A Lm1444414 llarated C. Gala. Drafting& Prows^ alt (AMacit step tequentn i I. PreVous Afrovetrinela Certificate immg in Mcorglarm VAR IF PROT476 Swam 21.191 (0 CAR FOMM teutenno i 0 Curve Wotan ana Basra Mormon AvtAitei in Mar E FM F Alie AI Ito DAM ratK41. Fpm 337 (MmA men (man i J. Cycle' Meatiness CAMARA Issued In Mordants WO 14 PROT477 Anoka 21.183 (d) (dopy sow/ F ins itzpeceon ROCONOS in MVO Records K. Us(+l4p01 ArgraElliolincal of Corpora FM Form 813615 MOO when rewind) FAA Form 8130-141111 Ai Provous Eddidif Superseded adman Formai -PDF Page 2 x2 AP. PROT83 DEPARTMENT -FEDERAL AVIATION ADMINIST STANDARD AIRWORTHINESS CERTIFICATE 1 NATIONALITY AND REGISTRATION MARKS N493LX 2 MANUFACTURER AND MODEL Company 400A NUMBER RK-244 4 CATEGORY Transport This *Pitiless codhala is WI pool lo 49 PROT478, 04164 and cedes del, as plata dalo ol Imam IP *tall to which issued has boa Odd and found lo oordorm loth lypa ceicole thlor, to 66 11109dliOri for sale operadoa, and has teen shown to meet the requirempls alto app!icahlo comprehensive and 'Maki airworthiness coda as pro* by Amax Blob Condo on Intomolipal C4 Nation, mantas rich hail Exceplions: *NONE* lints sow mended, sap*, 'evoked, klerroirellori dale is otherwise Petted b le FAA, this ahodies Whale is Palmas lop as h mitenco, praventalio mite/a, widiPa4s21,43,and SI of at Red Ade R MORS, as a ro ' le, and the a DESIGNATION NUMBER 03 06 2014 DART833943GL Any alvaOon, reproduction, or misuse of INs Cirliall) may ho piste% by a foie riot ova* 51,656 imprisonmord °pooling 3youscrbolt THIS CERTIFICATE MUST BE DISPLAYED IN THE AIRCRAFT IN ACCORDANCE WITH APPLICABLE fE0ERAl AVIATION REGULATIONS, FAA Form 81004 0411) Supersedes Previous Edition PROT84 I i PROT85 DEPARTMENT OF TRANSPORTATION • FEDERAL AVIATION ADMINISTRATION SPECIAL AIRWORTHINESS CERTIFICATE A CATEGORY/DESIGNATION ERrirtienta 1 PURPOSE Market S:4rvq,' / Q w MANU- FACTURER NAME /4,,(( N/A q ,Y ADDRESS/di/id/WA. ("% C FLIGHT FROM r /7 AVI,VeV'', \\\ TO iii ' ' WAY' ' U N- 493LX i; t SERIAL NO. RK-244 BUILDER RaytheonOki , raTt 'Cd.4, MO* 400A E DATE OF ISSUANCEFe ',0".5/401'41' /O,.MRY Aug/ 04 /2014 OPERATING LIMITA S'Oe '\k -.: :5110:10,0 PART OF THIS CERTIFICATE DESIGNATION OR OFFICE NO. DART833943GL Any alteration, reproduction or misuse of this certificate may be punishable by a fine not exceeding $1,000 or imprisonment not exceeding 3 pars, or both. THIS CERTIFICATE MUST BE DISPLAYED IN THE AIRCRAFT IN ACCORDANCE WITH APPLICABLE TITLE 14, CODE OF FEDERAL REGULATIONS (PROT479). FAA FORM 8130.7 (071041 SEE REVERSE SIDE NSN; 0052.00.6934000 PROT86 A A This airworthiness certificate is issued under the authority of Public Law 104, 49 United Slates Code" (PROT480) 44704 and Title 14 Code of Federal Regulations (PROT481), aB The ainuorthiness ceifificale authorizes the manufacturer named on the reverse side to conduct production flight tests, and only production flight tests, of aircraft registered in his name, No person may conduct production flight tests under this certificate: (1) Carrying persons or propel/ for compensation or hire: and/or (2) Crying persons not essential to the purpose of the flight C airworthiness cethficate aulhonZes the flight specified on the reverse side for the purpose shown in Block A, D ceilificate ceitilies Mal as of the dale of issuance, the aircraft to which issued has been inspected and found to meet the requirements of the applicable PROT482, The aircraft does not meet the requirements of the applicable comprehensive and detailed airworthiness code as provided by Annex 8 to the Convention On international Civil Aviation, No person may operate the aircraft described On the reverse side: (1) except in accordance with the applicable PROT483 and in accordance with conditions and limitations which may be prescribed by the Administrator as part of this certificate; (2) over any foreign country without the special permission of that country, E Unless sooner surrendered, suspended, or revoked, this airworthiness certificate is effective for the duration and under the conditions prescribed in 14 PROT484, Part 21, Section 21,181 or 21,217. PROT87 ThorAire March 3, 2014 ThorAir, LLC. Sandusky, Oh Re: RK 244 - Agent Authorization To whom it may concern: This letter is to confirm that ThorAir, (IC, authorizes Nextant Aerospace, LLC, as ThorAir's agent for a Beechjet 400A, bearing serial number RK-244 and FAA Registration number N493LX, which is owned by ThorAir, LLC., and operated by ThorSport, Inc., for any and all authorized FAA actions needed. Sincerely, Thor ' By: M.% \ "ZY`WtS \A\AQO\U Notary's Official Signature Sworn and subscribed to me this day,3 of nx V1 2014 ThorAir • • Sandusky Ohio 44870 ThorAfr PROT88 PROT89 RK-244 STC list (03/05/2014) Reference 8130-6: Application for Standard Airworthiness Certificate Transport Category, dated March 6, 2014 Reference section III owners certification ST02371LA: Replacement of Pratt & Whitney JT15D-5 series engine with Williams International FJ44-3AP engine (TCDS E3GL) with Full Authority Digital Engine Control (FADEC) and associated systems. ST10959SC: Installation of Rockwell Collins Pro Line 21 Electronic Flight Instrument System (EFIS) with Rockwell Collins FMS-6100, Localizer Performance with Vertical Guidance (LPV) approach capability and Universal Avionics System Company (UASC) Terrain Awareness Warning System (TAWS) ST03960AT: Installation of Aircell Axxess Cabin II Iridium Phone and High Speed Internet System with Wireless Local Area Network (WEAN), Astronics 115VAC 60Hz Cabin Inverter and Bonner LED Cabin Lighting System. ST01572WI: Installation of four (4) model 400A OEM seats, one (1) three-place divan, one (1) aft toilet, one (1) set of aft pocket door dividers, one (1) set of forward pocket door dividers and LED lighting. STC01794LA: Installation of Hawker 97650W0370 or 9750W0370-8 battery ST000812SE: Group airplane approval for Reduced Vertical Separation Minimum - (RVSM) PROT90 PROT91 PROT92 PROT93 *iiCa4117A SAC ?ROMA \O SER\ AL # MOOV_V PROT94 PROT95 PROT96 PROT97 FAA FORM 8130-6, APPLICATION FOR U.S. AIRWORTHINESS CERTIFICATE Form Approved O.m.g. No. 2120.0018 itai ion Dale 0228/2013 T2 I 0 1 3 U S Department aTranspenal Federal A AdmInIstr ion U.S. AIRWORTHINESS laton CERTIFICATE on Ill INSTRUCTIONS - Print or type. Do not wille in shaded meat Mese re for FAA it use only. Submit original only to an authorized FM Representative. If acklronal 0/ -1 space is required. use rtectuneM For special tight permits complete Sections 3 -i II. 1/1 and VII as applicable. 22 ilr. Q 1. REGISTRATION MARK N493LX 2. AIRCRAFT BUILOEI3'S NAME (owl 3. AIRCRAFT MODEL DESIGNATION 400A 4. YR. MFR. 1999 N FAA COOING a u a I S 5. AIRCRAFT SERIAL NO. RK-244 B B. ENGINE BUILDER'S NAME mew Williams International 7. ENGINE MODEL DESIGNATION FJ44-3AP _p B. NUMBER OF ENGINES 9. PROPELLER BUILOEF7S NAME mar ID. PROPELLER MODEL DESIGNATION I AIRCRAFT IS fawn 2 ejohness) 2 N/A N/A IMPORT APPLICATION IS HEREBY MADE FOR Itasca wiplagge WM/ I A I ei STANDARD AIRWORTHINESS CERTIFICATE metre crecold I has, I I win,' I I awc I/Imams-Yr I I ....... I I.4,00. I Iona, 0 SPECIAL AIRWORTHINESS CERTIFICATE (Crectiarreeem ram 7 PRIMARY 9 LIGHT-SPORT emisam I 1 AlMene I I Poser-Peradlule I I Weistit•ShisCentel I I GM.' I I LOW den At 2 LIMITED 5 PROVISIONAL I CLASS I Aeon On) 2 CLASS II r G I AGRICULTURE AND PEST CONTROL 2 AERIAL SURVEY 3 AERIAL ADVERTISING t 3 RESTRICTED mama apeastrarl am ametothe 4 FOREST mem anstmerd 5 PATROLLING e WEATHER CONTROL g 0 OTHER (soeat) I RESEARCH AND DEVELOPMENT 2 AMATEUR BUILT 3 EXHIBITION 3 4 AIR RACING 5 CREW TRAINING a MARKET SURVEY a 0 TO SHOW COMPLIANCE WITH THE PROT485 7 OPERATING Porgy Conn) KIT BUILT AIRCRAFT 2 ' EXPERIMENTAL BA Existing aircraft MithOlA WI aiworminess centate & do not meal 5 I03.1 2 r 4 Ordesti (mare mal to OF MOWN° OPERATING Be °wary LIM-Sport Kiiitaft sr U ai LIGHT-SPORT ornicl WSW, ' PnAlAutt, Issued spacial 99M-sporl Meow ainvonhiness canters under 5 VAC 9 UNMANE D 9A RESEARCH MID DEVELOPMENT [ 9C I I CREW TRAINING AIRCRAFT 90 MARKET SURVEY I FERRY FLIGHT FOR REPAIRS. ALTERATIONS. MANTENANCE OR STORAGE SPECIAL FLIGHT PERMIT promo 2 EVACUATE FROM AREA OF IIMENONG GANGER B opnAbno No pantheon IMO 00TOIMI Memo a w in mama m mart. sew 3 OPERATION IN EXCESS OF MAXIMUM CERTIFICATED TAKE-OFF WEIGHT 4 DELIVERING OR EXPORTING 15 I I PRODUCTION FLIGHT TESTING e CUSTOMER DEMONSTRATION FLIGHTS CI, a MULTIPLE AIRWORTHINESS CERTIFICATE fa.* MOVE %Skied Opirailoisne•Starclair iv •Linfte 41 4:10600A01 A REGISTERED OWNER mu rem an ememir arms remserse) IF DEALER, CHECK HERE I NAME Flight Options LLC Richmond Heights .OH 44143 Z 8 AIRCRAFT CERTIFICATION BASIS (ChM, •APraa, WOCA. Onie0. 1. 0 dent *I OJOS* 0 P 0 A16SW AIRCRAFT SPECIFICATION OR TYPE CERTIFICATE DATA SHEET ICA• ma and mummer Rev 28 AIRWORTHINESS DIRECTIVES 403/4,0 4 *a aapikwidei 404 we cowpwata awg•womerter eft rail ADSUPPLEMENT mile* I n as assay sewn MOO IWO 0 OPON410/9 Bi Weekly 2013-25 12/02/2013 - 12/15/2013 P AIRCRAFT LISTING roraeraeamemOU NM i SUPPLEMENTAL TYPE CERTIFICATE (LIS member-SA SIC bitsponffic See attached sheet C. AIRCRAFT OPERATION AND MAINTENANCE RECORDS i 1 /c.00t:memtion CHECK F RECORDS IN WI 91 TH A i PROT486 sec 17 TOTAL AIRFRAME HOURS TTAF 8581A3 3 EXPERIMENTAL ONLY (Emu have sae arm MI chime Sited a wend) 2.81 D. CERTIFICATION • I hereby centy Nal am imordaroa with Tele 49 el the UMW Sires altworthWess crater. reapeslot Ms regtslarloviner(or Ns gentle! tie eirnalt deserted stove. that We amend Ca* 44101 ABS end swabs Federal Avietion Rogulatice, and that the repaired with Me Federal Aviation AtInintralam Iti Orereft has teen illSPOCIOd and is Arwonhy and OSP* for the 12/29/2013 Agent SIG A THE AIRCRAFT DESCRIBED ABOVE HAS BEEN INSPECTED AND FOUND AIRWORTHY BY: Komar ma mammy Nall per it I1310.4oles/ I 3 se r W 2g 2 14 PROT487 put 121 CERTIFICATE HOLOER tom cement ram 3 CERTIFICATED MECHANIC (61.0494:41• No) e CERTIFICATED RE PAR $TATi N (OW CeMcate PM) t tul C 3 A CC 5 AIRCRAFT MANUFACTURER ter • • reran MN j V DATE TITLE SIGNATURE at (Ora AU *roam WC* awe A aVII) I THE CERTIFICATE REQUESTED P A I Tad that ma maul described described n Seam I or VII more regurernents for 4 AMENDMENT OR MODIFICATION OF CURRENT AIRWORTHINESS CERTIFICATE 'S z 2 B. Impechan toter:mist No porta under Section VII was conducted by FAA INSPECTOR FM DESIGNEE Zi W g CERTIFICATE HOLDER UNDER 14 PROT488 pales 14 PROT489 Wit 121 OR 135 1a PROT490 11 145 nYr a iF, 9u s DATE 12/29/2013 MIDOIF SOO OFFICE CLE-25 FAA Form B1306(4111) Al Previous &Mons PROT98 PROT99 A. MANUFACTURER IR SGG NAME ADDRESS B. PRODUCTION BASIS (Chick appitsbis Mm) PRODUCTION CERTIFICATE (Give proxkottim Akar° number) TYPE CERTIFICATE OTHER ft C GNE QUANTITY OF CERTIFICATES REQUIRED f OR OPERATING NEEDS NAME AND TITLE (Prini of RPM SIGNATURE A DESCRIPTION OF AIRCRAFT REGISTERED OWNER ADDRESS BUILDER (Make) MODEL SERIAL NUMBER REGISTRATION MARK B. DESCRIPTION OF FIGHT CUSTOMER DEMONSTRATION FLIGHTS 0 (Check 11 morat4) FROM TO VIA DEPARTURE OATE DURATION C. CREW REQUIRED TO OPERATE THE AIRCRAFT AND ITS EOUIPME NT I PILOT I I CO-PILOT I I FLIGHT ENGINEER I I OTHER (Specify) D THE AIRCRAFT DOES NOT MEET THE APPLICABLE AIRWORTHINESS REQUIREMENTS AS FOLLOWS. E. THE FOLLOWING RESTRICTIONS ARE CONSIDERED NECESSARY FOR SAFE OPERATION eltadmmni dnecessory) F. CERTIFICATION - I Namby =try Meilen the recoteted =nor for his ageed)of Me aircraft described them: that the aiwah is mcistered math the Federal Atielign Adniftisvation in smorcteme mt. Tills 49 of the LISS Sates Code 44101 gun and applicable Federal Mallon Regattas. end that IM aircraft hes Wen =peeled end s safe for the NOV desated DATE NAME AND TITLE (NW Of RPM SIGNATURE A. Operating Limitations and MaikessnOmnpharce Wan 14 PROT491 Section 919. f4 APPlicable G. Steinman( of Colonnity. FAA Form 8130-9 (Mach when mugs* B. Cat Opening LerMations Attached 14 Foreign Almmtniness Gerthcaban for Import Airat (Attach when spired) C. bete Drarwma Phoiographa etc (Alfa, whin 0.9a0NO I D. Caren) Segni and BNence Wormalion Available In Aircraft I I. Previous Arworehmen Cantata Issued in Accordance With 14 PROT492 Section 21.191 (a) CAR (Onginet MaCNKO I I E Major Rest and Maralion. FAA Form 337 (Minh when inured) F. This inspecbon Recorded n Aumaft Records J Current Airworthiness Cenfcate Issued n Accordance Wen 14 PROT493 Seelien 21.181 (a) (Copy egeeMNO K Ufett-Spcs AraM Stmement of Compiarce. FAA Fran 8130-1S (AEW, when =NYS) FM Form 81304 (4111) Ap Previous Edabm Superseded Demonic Forms -PDF Page 2 Of 2 PROT100 PROT101 DEPARTMENT OF TRANSPORTATION-FEDERAL AVIATION ADMINISTRATION 1 NATIONALITY AND REGISTRATION MARKS N493LX 2 MANUFACTURER AND MODEL Company 400A NUMBER RK-244 4 CATEGORY Transport This airworthiness certificate is issued pursuant to 49 PROT494. § 44704 and certifies that, as of the date of issuance, ircraft to which issued has been inspected and found to conform to the type certificate therefor, to be in condon for safe o 'on, and has been shown to meet the requirements of the applicable comprehensive and detailed airworthiness code as sided by Annex 8 to the Convention on International Civil Aviation, except as noted herein. Exceptions: *None* Unless sooner surrendered, sus is effective as long a 91 of the Federal A DATE OF ISSUANC 12/29/2013 /d, revoked, or a termination date is otherwise established by the FAA, this ainvottiness certificate rts 21, 43, and DART833943GL Any alteration, reproduction, or misuse of this certificate may be punishable by a fine not exceeding $1,000 or imprisonment not exceeding 3 years or both. THIS CERTIFICATE MUST BE DISPLAYED IN THE AIRCRAFT IN ACCORDANCE WITH APPLICABLE FEDERAL AVIATION REGULATIONS. PROT102 S PROT103 DEPARTMENT OF TRANSPORTATION • FEDERAL AVIATION ADMINISTRATION SPECIAL AIRWORTHINESS CERTIFICATE A CATEGORY/DESIGNATION EXPERIMENTAL I' - PURPOSE RESEADIAJELOPOKX i 0B MANU. NAME //b, A .,:`, il4,,1,/ - ADDRESS III OWAI)Vd1 FLIGHT FROM N j AY i,kiA / - 1`, TO il r`4, I , D N• 493L4 11;1 t ', , StRIALNO. RK- 244 BUILDER RaythemAihrifikpany 1.4 MODEL 4C0A E DATE OF ISSUANCE K..8) '&31 1 /0 .€XPIRY Jan 12.2014 OPERATING LIMITATIO,i' At,' 08';20B,igE PART OF THIS CERTIFICATE "D'ESIGNATION OR OFFICE NO. DART833943a Any alteratio •production or misuse of this cetficale may be punishable by a fine not exceeding $1,000 or imprison • 1 not exceeding 3 years, or both, THIS CERTIFICATE MUST BE DISPLAYED IN THE AIRCRAFT IN A9 i 'DANCE WITH APPLICABLE TITLE 14, CODE OF FEDERAL REGULATIONS (PROT495). FAA FORM 8130.7 (07(041 SEE REVERSE SIDE NSW. 005240.6914000 PROT104 A certificate is issued under the authority of Public Law 104.6, 49 United States Code (PROT496) 44704 and Title 14 Code of Federal Regulations (PROT497). B The airworthiness certificate authorizes the manufacturer named on the reverse side to conduct production flight tests, and only production flight tests, of aircraft registered in his name, No person may conduct production :light tests under this certificate: (1) Carrying persons or properly for compensation or hire: and/or (2) Crying persons not essential to the purpose of the flight. certificate authorizes the flight specified on the reverse side for the purpose shown in Block A. certificate ceitifies that as of the date of issuance, the aircraft to which issued has been inspected and found to meet the requirements of the applicable PROT498, The aircraft does not meet the requirements of the applicable comprehensive code as provided by Annex 9 to the Convention On international Civil Aviation. No person may operate the aircraft described on the reverse side (1) except in accordance with the applicable PROT499 and in accordance with conditions and limitations which may be prescribed by the Administrator as part of this certificate; (2) over any foreign county without the special permission of that country. E Unless sooner surrendered, suspended, or revoked, this airworthiness certificate is effective for the duration and under the conditions prescribed in 14 PROT500, Part 21, Section 21.181 or 21.217. PROT105 RK 244 STC list (12-26-2013) Reference 8130-6: Application for Standard Airworthiness Certificate Transport Category, dated December 26, 2013 Reference section ill owners certification ST02371LA: Replacement of Pratt & Whitney JT15D-5 series engine with Williams International FJ44-3AP engine (TCDS E3GL) with Full Authority Digital Engine Control (FADEC) and associated systems. ST10959SC: Installation of Rockwell Collins Pro Line 21 Electronic Flight Instrument System (EFIS) with Rockwell Collins FMS-6100, Localizer Performance with Vertical Guidance (LPV) approach capability and Universal Avionics System Company (UASC) Terrain Awareness Warning System (TAWS) ST03960AT: Installation of Aircell Axxess Cabin II Iridium Phone and High Speed Internet System with Wireless Local Area Network (WLAN), Astronics 115VAC 60Hz Cabin Inverter and Bonner LED Cabin Lighting System. ST01572WI: Installation of four (4) model 400A OEM seats, one (1) three-place divan, one (1) aft toilet, one (1) set of aft pocket door dividers, one (1) set of forward pocket door dividers and LED lighting. STC01794LA: Installation of Hawker 97650W0370 or 9750W0370-8 battery ST000812SE: Group airplane approval for Reduced Vertical Separation Minimum - (RVSM) PROT106 PROT107 Cleveland. Ohio 44143 December 26, 2013 Nextant Aeros ace, LLC Cleveland, Ohio 44143 Attention: Re: RK-244 - Agent Authorization To whom it may concern: aLti Options This letter is to confirm that Flight Options, LLC ("FO") authorizes Nextant Aerospace, LLC, as FO's agent, for a Beechjet 400A, bearing serial number RK-244 and FM Registration Number N493LX (also identified as a "Nextant 400XT"), which is owned by FO, for any and all authorized FAA actions in regards to: Airworthiness Classification Experimental X Airworthiness Classification Standard Sincerely, Flight Options, LLC By: Ma_ Vice President, Administration & Contracts Notary's Officio" &Ina-Cure Siam ana subscx tbez1 4-o Pt -141 do. 2 G, ckC bef-,e.,nt•er O4 2_01 3 bl PROT108 PROT109 PROT110 I PROT111 0 US Mammon a Riff', Apotral ovs Ne 2l mono itt3orzoci7 Electronic Trackin Number 9 Trarapanalkin (Airframe, Powerplant,Propeller, or Appliance) Fedni Aviation AchninIstratreri INSTRUCTIONS: Pant or type all entries. See FAR 43.9. FAR 43 Appendix 8. and AC 429-1 (or subsequent revision thereof) for instructors and disposition of this form. This report is required by law (49 PROT501. 1421). Faiture to report can result in a civil penalty not to exceed 51.000 for each such violation (Section 901 Federal Aviation Act 1955) 1. Aircraft N493LX Serial No RK-244 Make Model 400A Soles 2. Owner Address Cry Richmond Heights state. OH Zip 44143-1453 co.ty USA 4. Typo Repair Alteration Unit Make Model Senal Number 0 ►1 AIRFRAME (As descnbect in gem 1 above) III a P0WERPLANT K a PROPELLER K O APPLIANCE Type lilanyfanser 8 Knd of Agency Nerve Nextant Aerospace Address City Cleveland stn. OH Zip 44143-1453 cony USA O u.S. Certificated Mechanic O 'Manufacturer O Foreign Centticated Mechanic 0 Certificated Repair Station CRS # 25NR667B D. I candy that the repair smiler alteration made to the unit(s) Identiaed in item 5 above and described on the reverse or attachments hereto have been made n accordance with the requiements of Part 43 of the U.S. Federal Aviation Regulations and that the information furnished herein is true and correct to the best of ray knowledge. per 14 PROT502 Part 43 Apo. Et 11 05/30/2013 Pursuant to the authority given persons speared ['Sow, the unit identified in item 5 was inspected in the manner prescribed by the Administrator of the Federal Aviation Administration and is El APPROVED K REJECTED BY FAA Fit Standards Inspector Manufacturer [Person Approved by Canadian FAA Designee Inspection Au •rization i other (SPearY) Certificate or CRS it 25NR667B 05/30/2013 FAA Form 337 (1006) PROT112 PROT113 NOTICE Weight and balance or operating limitation changes shall be entered in the appropriate aircraft record. An alteration must be compatible with all previous alterations fo assure continued conformity with the applicable airworthiness requirements (If more space is required, attach additional sheets. !den* with aircraft nationality and registration mark and date work completed) N493LX 05/30/2013 Date Part I of 3 The Following Equipment was removed along with Associated Hardware. EFD-871 622-9345-203 Electronic Flight Display EFD-871 622.9345.203 Electronic Flight Display MFD-871 622-9434-213 Multi Function Display ICU-85 622-6189-002 Internal Compensation Unit ICU-85 622-6189-002 Internal Compensation Unit AHC-SSE 622-9336-400 Attitude/Heading Computer AHC-85E 622-9336-400 Attitude/Heading Computer SDU-6408 622-9735-001 Sensor Display Unit SDU-6408 622-9735-001 Sensor Display Unit DCP-5000 822-1028-011 Display Control Panel DCP-5000 822.1028.011 ARP-851 622-9500-011 Altitude Reference Panel ARP-851 622-9500.011 Altitude Reference Panel AAP-851 822.0328.011 Altitude Awareness Panel AAP-851 822-0328-011 Altitude Awareness Panel CHP-850 622-7397-002 Course Heading Panel DBU-4100 822-0014-002 Data Base Unit DAU-650 622-9344-101 Data Acquisition Unit SDD-640A 622-9347-001 Sensor Display Driver IOC-4000 ( 4) 622-9814-514 Card Assembly MDC-4000 622-9818-751 Maintenance Computer CSU-4000 (2) 822.0049-002 Configuration Strapping Unit FMC-5000 (4) 822-0891-008 Flight Management Computer PWR-4000 (4) 622-9945-021 !APS Power Card GPS•4000 822-0931-003 GPS Receiver Mounts 622-9430-002 EFD /MFD Mounts EFB Electronic Flight Bag Mounting El Additional Sheets Are Attached Form 337 (10-06) PROT114 PROT115 NOTICE Weight and balance or operating limitation changes shall be entered in the appropriate aircraft record. An alteration must be compatible with all previous alterations to assure continued conformity with the applicable airworthiness requirements. (If more space is required, attach additional sheets. Identify with aircraft nationality and registration mark and date work completed.) N493LX 5/30/2013 Page 2 of 3 Installed the Following Equipment along with Associated Hardware. Date Model Part Number Description Weight Arm CCP-3000 822-1746-002 Cursor Control Panel 2.60 90.0 CCP-3000 822-1746-002 Cursor Control Panel 2.60 90.0 DCU-3001C 822-2362.003 Data Concentrator Unit 5.0 325 DCU-3001C 822-2362-003 Data Concentrator Unit 5.0 325 ECU-3000 822-1200-209 External Compensation Unit 0.40 57.5 ECU-3000 822.1200-209 External Compensation Unit 0.40 57.5 FSU-5010 822-1543.101 File Server Unit (1" ins) 6.5 60.83 ECU-3000 822-1200.998 File Server Unit (1st IRS) 0.40 57.5 AFD-3010E 822-1753.416 Adaptive Flight Display 12.90 89.2 AFD-3010E 822-1753.416 12.90 89.2 AF0-3010E 822-1753-416 12.90 89.2 AFD-3010E 822-1753-416 12.90 89.2 IMT-3010 822-1140.401 AFD Mounting Rack 4.40 85.0 IMT-3010 822-1140-401 4.40 85.0 IMT-3010 822-1140-401 4.40 85.0 IMT-3010 822-1140-401 4.40 85.0 10852801Y00 Fuel Quantity Conditioner 0.90 324 PC920-2A2000PH-2A1 Fuel Flow Conditioner 1.10 325 GPS-40005 822-2189-004 GPS Receiver 6.0 37 Cl 429-410 GPS Antenna 1.0 166.14 Amp Cluster N241100-002 DC Voltmeter 1.5 97.4 [SSN REDACTED]-1 Speed Switch (2) 0.25 89.2 DBU-5010E 822-3000-202 Data Base Unit 1.60 134.5 PS-835D 501-1228.004 Power Supply 12.5 52.9 MMT-5000 822-1811-003 File Server Unit Rack 0.30 57.5 MMT-3010 (2) 822-1290-003 AHS Mounting Rack 1.80 57.5 XM WR-1000 822-2031-002 XM Weather 1.5 41.0 CHP-3010 822-1280.003 Course Heading Panel 1.30 92.5 Options Configuration Module. OCM-4100 822-1463-228 0.30 57.5 WAAS/LPV Options Configuration Module. OCM-4100 822-1463.228 WAASAPV 0.30 57.5 Form 337 (10.06) PROT116 PROT117 NOTICE Weight and balance or operating limitation changes shell be entered in the appropriate aircraft record. An alteration must be compatible with all previous alterations to assure continued conformity with the applicable airworthiness requirements. (If more space is required, attach additional sheets. Identify with aircraft nationality and registration mark and date work completed.) N493LX 05/30/2013 Page 3 of 3 Date Model Part Number Description Weight Arm CSU-4100 (2) 822-1364-002 Configuration Strapping Unit 1.60 55.7 MDC-3110 822-1987.006 Maintenance Data Computer 0.80 55.7 FMC-6000 (2) 822-0868-123 Flight Management Computer 1.90 55.7 ADC-850D (2) 822-0389-468 Air Data Computer 5.30 60.83 AHC-3000A (2) 822-1378-001 Attitude Heading Computer 4.80 57.5 DCP-3030 (2) 822-1828-002 1.90 89.96 PWR-4000 (4) 622-9945-022 IAPS Power Card 1.3 55.0 IOC-4100 (4) 822-1362-511 Input/output Concentrator 0.8 55.0 LT-4001-010 Master Caution Panel 1.3 87.0 Rev. Panel [SSN REDACTED].1 Pilot Reversion Panel 0.2 88.0 Rev. Panel [SSN REDACTED]-3 Co-pilot Reversion Panel 0.2 88.0 9-PED [SSN REDACTED].9 9-Pedestal Panel 1.8 92.89 345-6196 ELT Switch 0.2 88.0 Annunciator Led-42-12-8B-E0Y47 AUX BATT (1/2) Annunciator 0.05 88.0 Annunciator (2) Led-40-18-88-E0Y4S Pull Up/ Terrain Annunciator 0.05 88.0 Annunciator 2-F840231 Terrain Inhibit/ Terrain Fail 0.05 88.0 In Accordance with SIC ST10959SC. See Attached Copy AFM Supplement, Nextant Aerospace Doc. No. 373.00.0023 Rev IR Dated 09/02/2011 or later FAA approved revision, installed on Aircraft. Equipment Pilot Guides are Installed in the Aircraft as Portable Document Format (.pdf) via supplied I-Pad. NOTE: Portable electronic devices used to store required aircraft records required by Part 91.9 are considered Electronic Flight Bags (EFB) per FAA Advisory Circular AC 120-768 par 4-g. Commercial operators are required to obtain authorization for their use from their managing Flight Standards District Office. Instructions for Continued Airworthiness (ICA) Ref Nextant Aerospace Document [SSN REDACTED].Rev C or Later are included in the Aircraft Maintenance Records Carried out System Ground Test Plan PAW Master Drawing List (MDL) 373.00.004 Rev C. Carried out Hawker Beechcraft Service Bulletin 34-3431 Reduced Vertical Separation Minimum (RVSM) Airframe Inspection / Modification. Performed FAR 91.411Inspection per Part 43 appendix "E" Pitot Static & FAR 91.413 Inspection per Part 43 appendix "F" Transponder System checks. K Additional Sheets Are Attached Form 337 (10.06) PROT118 PROT119 *atm of 4\ nterica department of eafrartsportation Ifeberal (Ablation glibministration $upplerttental Type Certificate .121, an.1.456%4 ACIalate ST10959SC Nextant Aeros ace LLC Richmond Heights, OH 44143 arA4A 44,a; donjs414,A 4ye diainfr44 /40avnneediclavle /.4 dovialani azulawelaivo rRJ rataSewitereen nwv/4i airnaam trytabetneaht marl 25 944 Federal Aviation Jigewana.J. (See Pages 3 and 4 for complete certification basis.) eini'sezeilierka• 4,eg;n4jetatin./YimaGe Al 6SW ../44. Hawker Beechcraft Corp. ,.#r61. 400A gieW.)7/w tyriffifs 91474 KZ/7r Installation of Rockwell Collins Pro Line 21 Electronic Flight Instrument System (EMS) with Rockwell Collins FMS-6100, Localizer Performance with Vertical Guidance (LPV) approach capability and Universal Avionics Systems Company (UASC) Terrain Awareness Warning System (TAWS) in accordance with Nextant Aerospace LLC Master Drawing List Doc. No. 373.00.0001 Revision W, dated March 29, 2012, or later FAA approved version. Sintelalsiinss andriaisiast: 1) The installer must determine whether this design change is compatible with previously approved modifications. 2) If the holder agrees to permit another person to use this certificate to alter a product, the holder must give that person written evidence of that permission. . 3) For aircraft equipped with Pratt & Whitney al 5D Engines FAA approved Airplane Flight Manual Supplement, Nextant Aerospace LLC Doc. No. 373-00.0008 Revision IR, dated 10/19/2009, or later FAA approved version, is required on board the modified aircraft. cete94'eare and 4 invites? a/a 0444' Ai a Au) wiaatvs,.....4.4 S'ent t...41..vtentseired wt.itar.a.'ei vvend re a keetaisaloin cotto tweserwe:m ma < 4. 4A .4144,4x4,47 4v r724 .9;eArat lenearaectleM gia.4./yrrearairen June 26, 2008 g4.4. elt;vacar..t October 19.2009 glao freV.1.31/..1 afflealb2(' September 26, 2011; April 05, 2012 Manager, Systems and Flight Test Branch Chicago Aircraft Cenitication Office (Tirle) Any .notation or (big JS poroshata., OY . floe of not ovcoodino .1.J.O. or Joprison.0.1 .0C •mcoOdinq 1 year., or Opt.. Fmk rot.. 4110-2110.641 PAGE I of 4 P&G'S This NY be trans:oared Ja accorderce .Jco fa 21.42. PROT120 PROT121 jfintieb Stales of ,Aintrita !el:ointment of 2granisportation ebernt Ablation ,2\ botinisfration Supplemental `Type Tertifirate (Cartiinuation $ijeet) Aa,724/e ST I 0959SC Pak o>44.saonoo• October 19, 2009 Date Amended: September 26, 2011; April 05, 2012 gleadeal OesetWAISAYIJ 7ISVialeAr k 4) For aircraft equipped with Williams FJ44-3AP Engines, those engines must be installed under STC ST0237ILA. 5) For aircraft equipped with Williams FJ44-3AP Engines FAA approved Airplane Flight Manual Supplement, Nextant Aerospace LLC Doc. No. 373.00.0023 Revision IR, dated September 2, 2011, or later FAA approved version, is required on board the modified aircraft. 6) Aircraft must have previously qualified for Operations in Reduced Vertical Airspace via: RK-I thru RK-I 17 and RK-I 19 thru RK-I39, Hawker Beechcraft Service Bulletin No. 34-3431. RK-118, RIC-140 thru RK-224, Hawker Beechcraft Service Bulletin Nos. 34-3228 and 34-3431. RK-225 thru RK-299, Hawker Beechcraft Service Bulletin No. 34-3431. RK-300 and after as original equipped from Hawker Beechcraft. 7) For aircraft equipped with Universal Avionics Systems Corporation (UASC) TAWS FAA approved Airplane Flight Manual Supplement, Nextant Aerospace LLC Doc. No. [SSN REDACTED] Revision IR, approved March 28, 2012, or later FAA approved version, is required on board the modified aircraft. 8) For aircraft with Collins Proline 21 FMS-6100 LPV Approach enabled FAA approved Airplane Flight Manual Supplement, Nextant Aerospace LLC Doc. No. [SSN REDACTED] Revision IR, approved March 28,2012, or later FAA approved version, is required on board the modified aircraft. tifeaeAaten Suit: Based on 14 PROT503 §p 1.115 and 21.101, and the FAA policy for significant changes in FAA Order 8110.48, the certification basis for the Hawker Beechcraft 400A aircraft is as follows: a. The type certification basis for the Hawker Beechcraft 400A aircraft is shown on TCDS Al 6SW for parts not changed or not affected by this change. b. The certification basis for the parts changed or affected by this change since the reference date of application, September 29, 2009, is based on TCDS A I6SW and §§ 14 PROT504 Part 25 as shown on page 4 of 4 of this STC. Any alser [son of chis cerCIfjcace is pvnishable 0y 4 Zito or hot eeeoedin0 01.000. or inpeJsohosoc not extooding J years. or both. FAA ram IIIO-0.1110-PII PACE 3 of 4 PAGES This ces(iIi4Ate *my be Cron ***** SO' An sccordance .lth FAA L.U. PROT122 I PROT123 !lulled *alto of /mtrica pepartment of Eransportatiott - geberal jAbiation cAbministration Supplemental Igp Tertificate ((Continuation Ace° Paie4 rAvacteres October 19. 2009 Date Amended: September 26, 2011; April 05, 2012 Based on 14 PROT505 §§ 21.115 and 21.101, and the FAA policy for significant changes in FAA Order 8110.48, the certification basis for the baseline Installation of Rockwell Collins Pro Line 21 Electronic Flight Instrument System (EFIS) with Rockwell Collins FMS-6100 modification was determined to be TCDS A I6SW and the following later regulations: Amdt.[24-4) 25.771 (Le) Amdt(25.23) 25.301; 25.303: 25.581; 25.607: 25.611. 25.773 (a)(1)(1)(d) Amdt.(25.38J 25.1309 (eXtiXe)(cXeNn: 25.1322 Amdi.)25-401 25.901 (b)(1Xi); 25.1549 (1)(bXe) Amdt.I25-41) 25.1321 (aX6)(e)(e): 25.1131;25.1333 Amdt.[25-421 Amdt.125-46) Amdt.(25.54) Amdl.(25.72J Amdt.125.801 25.1501 25.603; 25.605: 25.613; 25.1529 25.307;25.571, 25.1307 25.1316 25.1329(N (OK): 25.1351 (a)(1)(d): 25.1381; 25.1521 (a)(c); 25.1543(6); 25.1581: 25.1563 (a) Am& (25-86) Andt[25.90J Amdt.12541) Amdl.125-1021 Amdt.(25-105) 25.305 25.1303 25.561 25.981 (a)(b) 25.1585(a) Amdt.(25.108J Arndt 125-1091 Amdi.(25-1 131 Amdt (25-122) Amdl.(25.123J 25.1325 (d) 25.1323 (aX060 25.869 ('X4):25.1431 25.1317 (a)(bXe) 25.1353 (aXc) Based on 14 PROT506 §§ 21 115 and 21.101, and the FAA policy for significant changes in FAA Order 8110.48, the certification basis for the Collins Proline 21 FMS-6100 with LPV Approach enabled and UASC TAWS was determined to be TCDS A I6SW and the following later regulations: Amdt (Original) 25.601, 25.605, 25.609, 25.613. 25.1301, 25.1357, 25.1381. 25.1525, 25.1541, 15.1581 Amdt.(24-4) 25.771 (a) Amdt.(2S-23) 25.301; 25.303; 25.305, 25.307, 25.561(c); 25.607; 25.611, 25.1307 Amdi.(25.38) 25.603, 25.1322, 25.1583(e) Amdl [25.40) 25.1585 (a) Amdt.(25•41) Amdt.(25-42) Amdt.(25-46) Amdt(25.54) Amdt.(25-72) 25.1309 (a)(b)(c)(6)(eXg) 25.1501 25.777(a0(c) 25.1529 25.869(a)(1) 25.1351 (a)(1) Amdt.(25-102) Amdt.[25-1 13) Amdt.[25.123] 25.98 1(a)(b) 25.1431(a) 25.1153 (aXe) - END - A y elu at on of C J* cort• Mktg is pimp& 'DM by s fine at not *Ambling $1.000, or Jowlsoewnt tun •xcentiao 3 yens, or Ugh. !AA 400.4 $110.1-1110.0!1 IPla 4 of 0 MASS This c•rt4 ('care 'Ay be transferred in ACCOt011AC• with FAA 21.4/. PROT124 PROT125 0 u.SOccrartment or Tcansporodon ROHR Aviation A/mnions:in Form Approved OMB No. 21200720 itranwr INSTRUCTIONS: Pnnt or type all entries. See FAR 43.9, FAR 43 Appendix B. and AC 43.91 (or subsequent revision thereof) for instructions and disposition of this form. This report is required by law (49 PROT507. 1421). Failure to report can result in a civil penalty not 10 exceed 51.000 1. Alrcraft N493LX Serial No. RK 244 Make Model 400A Series 2. Owner Name (As shown on registration cemecate) mo ss ra city slew OH zip 44143-1453 canny USA 4. Type Repair Alteration Unit Make Model Serial Number El El AIRFRAME (As descnbed in Item I ahove) K O POWERPLANT 0 K PROPELLER 0 K APPLIANCE Typo manitock_tor G. Conformity Statement name AROMA city Cleveland slaw. OH Zip 44143-1453 campy USA O1 Manufacturer C. Certificate No C Certificated Repair Station CRS # 25NR667B O Certificated Maintenance organization O. I certify that the repair and/or alteration made to the unit(s) identified in tern 5 above and described on the reverse or attachments hereto have been made in accordance with the requirements of Part 43 of the U.S. Federal Aviation Regulations and that the information furnished herein is true and correct to the best of my knowledge. per 10 PROT508 Part 43 App. B 0 Signature/Date of Authorized Individ 05/30/2013 Pursuant to the authority given persons speofied below, the unit identified in item 5 was inspected in the manner prescribed by the El APPROVED El REJECTED BY FAA Flt standards inspector Manufacturer I Person Approved by Canadian FAA Designee Inspection Autftrization Other Specify) Certificate or CRS # 25NR667B Signature/Date of Authorized Individual 05/30/2013 PROT126 PROT127 NOTICE Weight and balance or operating limitation changes shall be entered in the appropriate aircraft record. An alteration must be compatible with all previous alterations to assure continued conformity with the applicable airworthiness requirements. (If more space is required, attach additional sheets. Identify with aircraft nationality and registration mark and date work completed.) N493LX Nationality and Registration Mack Nextant Aerospace Completed STC tt ST02371LA Removed Pratt and Whitney JT15D-5 Series Engines . 05/30/2013 Date Installed the Williams International FJ44-3AP Engines with Full FADEC and Associated Systems in accordance with Nextant Aerospace MDL -NXT-001 Rev IR Dated 08/22/2011 or later FAA approved revisions, and FAA Approved AFM Supplement NXT-1-AFMS Rev IR dated 9/15/2011 of later FAA Approved revisions. Installed Left Engine Part Number. 111000-202 Serial No. 252757 Installed Right Engine Part Number 111000-202 Serial No. 252758 ICA AFM Supplement was installed on Aircraft. Nextant Aerospace Instructions for Continued Airworthiness Document NXT-ICA Rev IR or later FAA accepted revisions are included in the Aircraft Maintenance Records. Carried out Engine Ground Runs and System OPS checks IAW Ground Test Plan [SSN REDACTED] Rev F. End FAA Form 337 (ro.os) PROT128 PROT129 }lidkit Alnico erAciericii Pepin. Intent of ZIrmispectrdinit - jliederid cAbintion i*ittriiriotration $upplemental Tuve Certifiaxte ACeenz4/, ST02371LA Yt, rfiriVcale 'Akira Nextant Ados ace LLC cre3/4 ) /Lair liar a. /4 Ow devrAfr alfriSearndastenal dowlakiw cerrelconait4J. erreArei reet9freheemorniter4 riecemitarthew rwatimervai tegnarl 25 * teen ..greverea47.4iw -94,144*."0. *Certification basis is set forth on TCDS A l6SW and continuation sheets 3 and 4. ifgviriteaordra' *to WreiViartrivi'rcero.• A 1 GSW Hawker Beechcraft 400A Nvo*afeiis ifira Our Meir Replacement of Pratt &, Whitney 5D-5 series engine with Williams International FJ44-3AP engine (TCDS E3GL) with Full Authority Digital Engine Control (FADEC) and associated systems, in accordance with Nextant Aerospace Master Drawing List No.: MDL-NXT-001, Revision 1R dated 8/22/2011, or later FAA approved revisions and FAA Approved Airplane Flight Manual Supplement, NXTI-AFMS, Rev IR, dated September 15, 2011 or later FAA approved revisions. Nextant Aerospace, LLC Instructions for Continued Airworthiness document NXT1-ICA, Revision IR, or later FAA accepted revisions must be provided with this STC. ..Weetheaivto rriorteewrieliw.i: The installation should not be incorporated in any aircraft unless it is determined that the interrelationship between this installation and any previously approved configuration will not introduce any adverse effect upon the airworthiness of that aircraft. The approval of this modification applies to the above-noted airplane models only. If the holder agrees to permit another person to use this certificate to alter the product, the holder shall give the other person written evidence of that permission. (CONTINUED on page 3) gai ereVetakt ecoriall.irwrevar ata ele.it;aA onewoorararre-evnertia At Oat/the JItneerteleredJaOrneed retwevie.v. a. knieririzaiva Abe Ai careciari evireteddevel. ./Mteire:OrrIcv, eyeafei Rielerrat6thierleiva ..egedieritealredicva fkia,/eryacre4;v:. March 24, 2008 ame/kwavien.. September 27, 2011 14. raterneleil.- &itroit Manager, Propulsion Branch Los Angeles Aircraft Certification Office (Time) Any alteration of this atiffrate it panisfiable by a fine of no: excetelloyi $1,004 or iiniultonment not taccediv 3 years, or Gotta YM rem 0110.2(10.4i) Pegs r of 4 Vic certificate nay de trainfeired moat:met n1(0)1(.4.21.47 PROT130 PROT131 INSTRUCTIONS: The transfer endorsement below may be used to notify the appropriate FAA Regional Office of the transfer of this Supplemental Type Certificate. The FAA will reissue the certificate in the name of the transferee and forward it to him. TRANSFER ENDORSEMENT Transfer the ownership of the Supplemental Type Certificate Number to Paine of transferee) Oteritrss of transfer) tecum(vr an! itrrei) (ail Sr•14 da Zip rile) from (name ofgrantor)(Pr(nt or we), (fiffiress of grantot) OrlimbentnIscrert) tic% Seal an d Zip roe) Extent of Authority (if licensing agreement): Date of Transfer: Signature of grantor an MO Pagc2 or 4 PROT132 PROT133 puttee Plates WI Anterior .Bcpairtnient of Zikantepartation - lfebernt Abintiou Pt bmirtistrtttiorr $upplartentai Zgin Tertifirate (ffinutinuntion $11291) Afeeenie/< ST02371LA -2reintrakiinr analifoncerdeanix (conitnan(1 Nextant Aerospace, LLC, "Installation of Rockwell Collins Pro Line 21," Amended STC ST10959SC, dated September 26, 2011 or later FAA approved revisions is required as part of this alteration. The new Vince and Vmcg values arc 94 KIAS and 93 K1AS respectively. The new engine minimum rated thrust is 3,031 lb at sea level, flat rated to an ambient temperature of 77°F. Approved engine fuels are: Grade Specification Jet A ASTM-D 1655 Jet A-1 ASTM-D 1655 Wee49catkew,....fiani The certification basis for this modification is as follows: The original certification basis for the Hawker Beecheraft Model 400A airplanes identified on TCDS AI6SW, Revision 26, dated March 17, 2010: Part 25 of the Federal Aviation Regulations effective February 1, 1965, as amended by 25.1 through 25.40, plus §§ 25.1335, 25.135I(d), 25.1353(c)(5), and 25.1447 of Amendment 25.41; §§ 25.29, 25.255, and 25.1353(0(6) of Amendment 25.42; and §§ 25.361(b) and 25.132900 of Amendment 25.46. Part 36 of the Federal Aviation Regulations effective December 1, 1969, as amended by 36-1 through 36-17; SPAR 27 effective February 1, 1974, as amended by 27-I through 27-5: and Special Conditions No. 25-ANM-32 dated February 22, 1990 (High Altitude Operation at 45,000 feet), and Special Conditions No. 25-ANM-33 dated June 18, 1990 (Lightning and Radio Frequency Energy Protection). (See NOTE 12) Equivalent Safety Items: (I) Out.of-trim characteristics § 25.255 (2) Pilot compartment view § 25.773(b)(2) (3) Passenger compartment door § 25.813(c) (4) Emergency exit marking §§25.811(d)(1) and 25.811(d)(2) Application for amended Type Certificate dated February 18, 1988. Regulation at a later amendments for components and areas affected by the change (Ref. FAA approved Compliance Check List): Subpart A - General: 25.2(25.99) Subpart 11 - Flight: 25.207(25-121), 25.255(25.42) Subpart C Structure: 25.571 (25-96) pay dimwit of the attfwan is pialisha64 by a fine of not cowling $1,000, or neprinament not aim% 3 pan, or boa PM Pons 0310.2110-6I) sego ) of 4 ?hit certificate nay ds traurfirra f in anonfann with TRIL21.47. PROT134 PROT135 palish Stoles 01 A tunics Peparfutent of Zrattoporintion - jliehertti cAbintiott Jtlbritittistrrttirm $upplartental Zglat Tertifiatte (clantinuation $beet) ./rande.# ST02371LA WeriaAniaimegade:s iconloaraesed Subpart D - Design and Construction: 25.603(25-46), 25.605(25-46), 25.611(25-123), 25.613(25-112), 25.625(25-72), 25.832(25-72), 25.863(25-46), 25.869(25.123), Subpart E - Powernlant: 25.901(25.46), 25.903(25-100), 25.951(25-73), 25.961(25-57), 25.981(25-125), 25.994(25-57), 25.997(25-57), 25.1013(25-72), 25.1019(25-57), 25.1021(25.57), 25.1043(25.42), 25.1045(25-57), 25.1091(25400), 25.1093(25-72, 25.1103(25.46), 25.1141(25-115), 25.1143(25-57), 25.1163(25-57), 25.1165(25-72), 25.1181(25-115), 25.1183(25-101), 25.1185(25-94), 25.1189(25-57), 25.1195(25.46), 25.1203(25-123), 25.1207(25.46). Subpart F - Equipment: 25.1301(25-123), 25.1305(25-115), 25.1307(25-72), 25.1309(25-123), 25.1316(25-80), 25.1317(25-122), 25.1321(25-41), 25.1331(25-41), 25.1351(25-72), 25.1353(25-123), 25.1357(25-123), 25.1381(25-72), 25.1431(25-113), 25.1438(25-41), Subpart G - Operating Limitations and Information: 25.1501(25.42), 25.1521(25-72), 25.1527(25- 105), 25.1529(25-54), 25.1543(25-72), 25.1549(25-40), 25.1551(25-72), 25.1557(25-72), 25.1581(25-72), 25.1583(25-105). Subpart H- Electrical Wiring interconnection Systems (EWIS): 25.1701(25-123), 25.1703(25-123), 25.1705(25-123), 25.1707(25-123), 25.1709(25-123), 25.1711(25-123), 25.1713(25-123), 25.1715(25423), 25.1717(25-123), 25.1719(25-123), 25.1721(25-123), 25.1723(25423), 25.1725(25-123), 25.1727(25-123), 25.1729(25-123), 25.1731(25-123), 25.1733(25-123). 14 PROT509 Part 34 (34-3): 34.11 14 PROT510 Part 36 (36-28): 36.1-36.7, 36.101--36105, 36.1501, 36.1581. The following Nextant Aerospace Continued Airworthiness Supplements are applicable to airplanes modified in accordance with this STC: • Master Minimum Equipment List document No. MMEL Rev. 8, dated 02/21/2011 or later FAA approved revisions. • EWIS (Electrical Wiring Interconnection Systems) Inspection Procedure/Report No. NXTI-EA-007 Rcv A dated 8/24/11 or later FAA approved revisions. -END- Any iteration of this artyieate is punishable by a fine of not evettfing ii,00cs or implisonntent not mere% 3 years, or both PM Pons 1110-2(10-40 Pogo 4 at 4 This syndicate may be transtetriin acrodance nib TAR,21.47. PROT136 PROT137 0 u S oessani or Tissoananon Paws minion ministration Font amens 0m8 No 2t204:020 it nor2037 For FAA Um Only INSTRUCTIONS: Print or type all entries. See FAR 43.9, FAR 43 Appendix B. and AC 43 9.1 (or subsequent revision thereof) for instructions and dispositio of this form This report is required by law (49 V.S.C. 1421). Failure to report can result in a civil penalty not to exceed 51.000 for each such 'elation (Section 901 Federal Aviation Ad 1958) 1. Aircraft N493LX Serial No. RK 244 Make Model 400A Senes 2. Owner Name (As ShOwn on tegistrabOn certificate) Metes, City Richmond Heinfits swe.OH zip 44143-1453 coulee USA 4. Type S. Unit Identification Repair PAeratiOn Unit Make Mood Serial Number El El AIRFRAME O POWERPLANT ID O PROPELLER O O APPLIANCE Typo Manufacturer B K no of Agency Nara moms cry Cleveland slate OH zo 44143-1453 Country USA 0 U.S. Certificated Mechanic 0 Manufacturer 0 El Certificated Repair Station CRS # 25NR667B 0 D. I certify that Ihe repair and/or allerabon made to the unit(s) identified in item 5 above and described on the reverse or attachments hereto have been made In accordance with the requirements of Part 43 of the U S Federal Aviation Regalabons and that the information furnished herein is true and correct to the best of my knowledge - Per 14 PROT511 Part 43 App. B MI 2/29/2013 7. Approval for Return t lett Pursuant to the authority given persons specified below, the unit identified in item 5 was inspected in the manner prescribed by the APPROVED El REJECTED FAA Flt Standards Inspector Manufacturer i Person ApprOved by Canadian BY Certificate Designation CRS or # 25NR667B FAA Designee No. Other (SPecif0 /29/2013 FAA Form 337 (teat) PROT138 PROT139 NOTICE Weight and balance or operating limitation changes shall be entered in the appropriate aircraft record. An alteration must be compatible with all previous alterations to assure continued conformity with the applicable airworthiness requirements. (If more space is required, attach additional sheets. Identify with aircraft nationality and registration mark and date work completed N493LX Nationality and Registration Math 12/29/2013 Date Installed the following In-Flight Entertainment System in accordance with STC # ST03960AT and in accordance with Nextant Aerospace Master Drawing List DB1002067. Revision F.05 Dated: October 9, 2013. Installed Bonner Cabin LED Lighting System without the Venue System in accordance with NX330-1304002. Rev B Dated October 17, 2013. Ref. drawing for parts list. ICA Requirements. Ref FAA Order 8100.17 Page 7-5 and 7-6 Use FM publications such as AC 43.13.1, Acceptable Methods, Techniques, and Practices - Aircraft Inspection and Repair. and AC 43.13-2, Acceptable Methods, Techniques, and Practices - Aircraft Alterations; part 43 appendix D; or other applicable aviation standards. Installed Iridium Sat Comm (Cockpit Phone only) and Broadband Internet System with Aircell Axxess II and ATG 4000 in Accordance with DB 1001013. Rev E ICA for Aircell System Ref to Nextant Aerospace Document No DB1105003. Rev A dated September 22 2011 or later FM Accepted Revisions The following manuals contain complete detailed maintenance instructions and should be consulted for all maintenance activities not covered within this ICA: Aircell Axxess II Installation Manual 012004 Revision E, dated March 2010 or later applicable revision Aircell ATG-4000 Installation Manual D13485 Revision B Dated November 2009 or later applicable revision Aircell Axxess II WLAN AFM Supplement DB1002072 Rev IR dated March 22 2012 for the has been Installed in the AFM Installed the Astronics DC-AC 115 VAC Power Supply in Accordance with DB1002067 Rev F.04 Dated 10/9/2013 This is Located under the Seat Divan ICA for Astronics 115 VAC Cabin Inverter Ref to Nextant Aerospace Report No DB1108018 Rev IR Date 9/22/2011 or later FAA Accepted Revision. Aircraft Flight Supplement DB1109012 has been installed on the Aircraft See Current Weight and Balance Dated: December 29, 2013 End FAA Form 337 (io.os) PROT140 PROT141 Vniteb 'take of ;America gleporiment of ligrattoportation geberal cMialion cabrninistration $upplementat Type Tertificate Actinetede4 ST03960AT .71;5 fernAvA' 44"a West Palm Beach, FL 33406 reehAm ten/ee rieenfe 4, Or /me eAlikes/9- dravethyyreetafe/ end at, etw'rerhiw4 Awe/ erna>;v7J acyrise se4 VerseAtif "wen ineet zee felivideiVtinkl esyntinview/3 r/ !Arne 25 Vier Federal Aviation .92,1"42vawa. Sfironetrity4n1- • , ;fie KvOrrelo •AC0,6- AI 6SW ..4160A Hawker Beechcraft Corporation Sea: 400A fiskle.s0/eisss el .gs>ir iiSlsises War.' Installation of Rockwell Collins Venue In-Flight Entertainment(1FE), Aircell Axxess Cabin II Iridium Phone and High Speed Internet System with Wireless Local Area Network (W LAN) Astronics 115VAC 60HZ Cabin Inverter, and Emteq LED Cabin Lighting System in accordance with Nextant Aerospace LLC, Master Drawing List DB1002067, Revision E, dated January 26, 2012, or later FAA approved revision. ,9ramArhiv., 4welfenaiv,J.• This approval should not be extended to other aircraft of this model on which other previously approved modifications are incorporated, unless it is determine by the installer that the interrelationship between this change and any other previously approved modifications will produce no adverse effect upon the airworthiness of that airplane. If the holder agrees to permit another person to use this certificate to alter the product, the holder shall give the other person written evidence of that permission. ..We3 ovietrain twee 'Or ay/Are/49 44/et avtii nt; etzyteretet.Ateeentteas 4. *Or/ foyhl Jitemfeeireet. Jeninena e n rime re re beziniiseekvs etr* hl reeete,:le estireifiVergy /4 .4 1,4,,,:viderv/re r//6 ....XsArset fleas/4w 0.4 July 28, 2012 -eget rAwerewee March 22, 2012 fate re/:waved: ewe sowitiveAv6.- Atlanta Aircraft Certification Office My sitoraclon of this corcilicsfe is ounissablo Dye lino of hoc osensitno 12,000, or Imprisonment not exceeoing J ye***, or moth. VAL fwm 8110-2(10-fel MGt I of 1 YMCAS This cora/leaf* se/ N csonstfrzoii In se,ezdan.• mach PAR 21.4.. PROT142 PROT143 VolItb *tato of America pepartnunt of transportation - Xeherni Pkbintion ptbministrntion $upptententnl Zype Certificate (Tantinuation $beet) tfriteregett ST03960AT When the Rockwell Collins Venue system is installed Airplane Flight Manual Supplement, DB1106015, Revision A, dated March 22, 2012, or later FAA approved revision, is required. When the Aircell Axxess II system is installed Airplane Flight Manual Supplement, DB1002072, Revision IR, dated March 22, 2012, or later FAA approved revision, is required. When the Astronics Cabin Inverter system is installed Airplane Flight Manual Supplement, DB1109012, Revision IR, dated March 22, 2012, or later FAA approved revision, is required. This system is intended to provide internet connection and email services to the airplane's cabin using portable electronic devices (PEDs). Any other intended function of this equipment will require a re- examination of the certification basis. When the Rockwell Collins Venue system is installed Instructions for Continued Airworthiness (ICA), Nextant Aerospace Document No. DB1002068, Rev IR, dated September 22, 2011, or later FAA accepted revisions must be made available to the operator at the time of installation. When the Aircell Axxess II system is installed Instructions for Continued Airworthiness (ICA), Nextant Aerospace Document No. DBII05003, Rev A, dated September 22, 2011, or later FAA accepted revisions must be made available to the operator at the time of installation. When the Astronics Cabin Inverter system is installed Instructions for Continued Airworthiness (ICA), Nextant Aerospace Document No. DB I 108018, Rev IR, dated September 22, 2011, or later FAA accepted When the Emteq LED Cabin Lighting system is installed Instructions for Continued Airworthiness (ICA), Nextant Aerospace Document No. DB1108019, Rev IR, dated September 22, 2011, or later FAA accepted Any alteration of this ooze ion* purdahs)) • by • flea at net trend nq 11,000, or ltprlsonwent not arcabffir4 l years, or both. MA it 1110-2-1(10-49) PAGE 2 or 3 PAGES This entificat• way b transforrect in •ccoraanc• with PAR 22.17. PROT144 PROT145 Alates of ,America peoartment of grzinsportation - geberat Ablation Administration $upplemental `Type Tertificate (Tantirtuation Sheet) A rtaidede ST03960AT enr/Veleedava The Certification Basis for this installation is per Type Certificate Data Sheet Al6SW original Certification Basis, Federal Aviation Regulation (FAR), Part 25 as amended by Amendment 25-1 through 25.40 plus FAR 25.1335, 25.1351(d), 25.1353(c)(5), and 25.1447 of Amendment 25-41; FAR 25.29, FAR 25.255, and FAR 25.1353(e)(6) of Amendment 25-42; and FAR 25.361(b) and 25.1329(h) of Amendment 25-46. In addition the following specified rules amendment levels were used for this installation. 25.571 25.1353(aXc) 25.1357 25.1431 25.1529 [25.541 [25.123] [25-1231 [25-113] [25-541 (1 Indicates amendmen level Any alt aaaaa on or this corellicett is punishable by • Tins of not enabling 53,000, Or laprisonnent not intending 1 years, or both. FAA EOM 0110-2-2(20-01 AWL 3 of 3 PAGES This certificate nay be transfersest in accordance with FAR 11.4r. PROT146 MS PROT147 0 u s orsemieni al hasp:dam F000.11 AARIOA AdwANtratlen ram Append ore tie 21204020 11/30,2t03 Elect/oat Trackirg Number INSTRUCTIONS: RIM of type all entries. See FAR 43.9, FAR 43 Appendix B. and AC 43.9.1 (or subsequent revision thereof) for Instructions and disposition of this form. This report is required by law (40 PROT512. 1424 Failure to report can result Mach& penalty not to exceed 61800 I. Aircraft NationaRy and Registration Mark N493LX Serial No. RK244 Make Model 400A Series 2. Owner Flight Options, LLC Address (As shown on registration cerfifiCate) cityHichmOnd Heights sue:Ohio 4944143-1453 ciairoa.8 4. Type 6. Unit IdeMlfic alien Repel/ Alteration Und Make Model Serial Number El el AIRFRAME (As describer:1ln ken l above) 0 ii POWERPLANT 0 El PROPELLER O D APPLIANCE rye. Nara ...over B. KIM of Agency Na Avi _ i n Aa&es cityCleveland swoOhio CI U.S. Certificated Mechanic 0 IManufacturer 0 0 CRS#WC7R34OJ zo44135 courevOnited States CI Certificated Maintenance Organization D. I certify that the repak andiOI alteration made to the unit(s) Identified in item 5 above and described on the rover c or Mtn:laments hereto have been made In accordance with the requirements of Pen 43 of the U.S. Federal Aviation Regulations and that the information furnished heroin Is true and correct to the best of my knowledge. per 14 PROT513 Part 43 App. 8 ill Date: December 30, 2013 Service Pursuant to the authority given persons spooned below, the unit Idea tn item 6 W3S inspected In the manner presorted by the Administrator of the Federal Aviation Administration end is El APPROVED II REJECTED BY FM Fa Standards Inspector Manufacturer IAMMenance Organization FM Designee other moon CerOlicate or CRSHWC7R346J Onlonolion No. SignauxerDate el Date: December 30 , 2013 FAA Form 337 node PROT148 PROT149 NOTICE Weight and balance or operating limitation changes shall be entered in the appropriate aircraft reCOM. An alteration must be compatible will, all previous alterations to assure continued conlomety with the applicable airworthiness requirements. (If more space is required, attach additional sheets. identify with eircrak nationality and registration mark and dale work completed) N493LX 12/30/2013 Dale ACCOMPLISHED INTERIOR REFURBISHMENT/MODIFICATION AND 3 PLACE DIVAN INSTALLATION THE FOLLOWING AIRCRAFT INTERIOR ITEMS HAVE BEEN REFURBISHED: RepalMed, recovered control columns with Mane Bed( Leather Accordance with BeedVel 400A AMM 20-70.00-701. 25.0040-001 Removed and Replaced Glare shield and Eyebrow panel material with Matte Sack Leather In Accordance with Becch)et 400A AMM 20-60-00.201. Removed and Replaced Cockpit Sidewal malarial MU Mane Black Leather In Accordance with Beet:lel 400A AMM 20.80-00.201. Removed and replaced Pitc1 Seal Pad Number TA W II00PM000I Serial Number 82. Foam and recovered with Garen Sheepskin Oak and Excel Cappucdno Leather. Removed and replaced Co-Pilot Seat Part Number TABH100CM00.01 Serial Number 248, Foam and recovered w.thCarrell Sheepskin Oak and Excell Cappuccino Leather. Removed and Replaced Loll Hand #4 Passenger Seal Pad Number 2524.014(-530A) Serial Number 990719.4 Foam and recovered with Townsend Leather (Heritage Brown) Removed and replaced Right Hand #5 Passenger Seal Part Number 2524.014(-530B) Serial Number 990426-7 Foam and recovered with Townsend Leatherpleriinge Brown) Removed arid Replaced Left Hand 03 Passenger Seal Pan Number 2524.014(5306)Sedal Number 03061845 Foam and recovered with Townsend Leather Removed and replaced Right Hand S7 Passenger Seat Pan Number 2524-014(530A) Serial Number 030708.2 Foam and recovered with Townsend Leather DIE FOLLOWING MANUALS AND APPROVED DATA HAVE OLEN UTILIZED FOR OASIS OF REFURBISHMENT. Skendla Flammability Test S254978 as approved by FM t)EIT Jane Mersa* (DERY 832780-CE) on FM form 8110-3 dated 4/23/2013 Flame Out Elam/1180'4y Test 4351 as approved by FM DER Herb Reed II (DERT-230293.CE) on FM Form 8110-3 dated 12/23/2013. Skandla Flammability Test Report IP 22081 Rev A as approved by FM DER and Faberslein( DERY-832780-CE) on FM Form 8110-3 dated 05/02/2013. Three Place Divan installation: Installed (3) ptace divan part Number 32.03913(MOVOT123.K02 S/N 003702 In Accordance Men Aviation Fabricators SIC/ STOI572W1 and Skandia Rammila test report 5254978 per Jane Bibeisleln FM DER (DERV-832780-CE) dated 4/23.2013 THE FOLLOWING INTERIOR ITEMS HAVE BEEN MODIFIED: UR Golly Assy, RM Galley May, Divan Amy. LM Galley Assy and install per Deka G drawing DGD-GW1.101 Rev 0, DGD-CAOI -101 E0 E- t. LfH Galley Install DGO-CA01-501 Rev EO A-1. DGOCAot-501 Rev IR as approved on FAA formal 10-3 pm FAA DER Donald Geese* (DERT-750135-SW) dated March 25 2013. RA4 Galley Assy and Install per Della G drawings DGD-CA02-101 Rev B. OGLICA02-501 Rev IR as approved on FM /OM 8110-3 by FM DER Donald Geese* (DERT-750135-SW) dated March 25. 2013 Divan Assy per Delta G drawings OCID-CA09-101 Rev C and DGD-CA09-101 E0 0-1 as approved on FM form 8110.3 per FM DER Donald Giuospk (DERT 750135-SW) dated March 25. 2013, Month Kit Sfdewa0 esay &arena 2553-0038 RCN C. Bonner sldeledge any *away 25324)032 Rev C Bonner Ka Foldout Table assy drawings 2553.0041 Rev C and 2553-0040 Rev EL Bonner XTI finer Kit Ina drawing 2553-0037 Rev C as approved on FAA form 8110.3 per Stephen Formes DERT-230238-CE dated Dec 20, 2013. INSTRUCTIONS FOR CONTINUEDAIRWORTHINESS. THE REMOVAL OF THE INTERIOR IS ON THE CONDITION OF FAILURE. THERE ARE NO ADDITIONAL INSPECTIONS REQUIRED. CONTINUE TO INSPECT JAW MANUFACTURERS MBA, SRIL OR CMM AS APPLICABLE AIRCRAFT EQUIPMENT LIST AND WEIGHT AND BALANCE WERE UPDATED BY THE CUSTOMER -END--- O Additional Sheets Are Attached FAA Form 337 (1008) PROT[ADDRESS REDACTED]ATEMENT OF COMPLIANCE WITH THE FEDERAL AVIATION REGULATIONS DATE Dec 26, 2013 MAKE Beeehcraft Corporation MODEL 400A TYPE (Airplane. Radio. Helicopter, eta) AIRPLANE NAME O APPLICANT NEXTANT Aerospace Cleveland OH. LIST OF DATA IDENTIFICAITON TITLE REPORT: BEECHJET 400A INTERIOR STRUCTURAL SUBSTANTIATION BEECHJET 400A XTI LINER KIT INSTL. Beechjet 400A, Aircraft Serial No. RK-244 Certification Bases for this aircraft modification is per Type Certificate Number A I GSW Revision 28 dated April 12,2013 RKG3282 Rev. IR, 8-28-2013 2553-0037 Rev C, dated 8-30-2013 PURPOSE OF DATA DESCRIBE AND SHOW VERIFICATIONS FOR NEXTANT INTERIOR INSTALLATION ON BEECHJET 400A, AIRCRAFT SERIAL NO. RK-244 APPLICABLE REQUIREMENTS ( List spec* sections) 14 PROT514 Part 25 §.301, 303, 305, 307a), 365, 561, 571,601, 603, 605, 609, 613 CERTIFICATION - Under authority of appointment under Pan 183 of have been vested by direction of the Administrator and in accordance with conditions the Federal Aviation Regulations, data listed above and on attached sheets examined in accordance with established procedures and found to comply Regulations. Approve these data and limitations numbered with applicable requirements of the Federal Aviation I 01413 Therefore O Recommend 0 SIGNATURE(S) OF DESIGNATED ENGINEERING REPRESENTATIVE(S) DESIGNATION NUMBER(S) CLASSIFICATION(S) DERT-230238-CE STRUCTURES AND DAMAGE TOLERANCE FAA Form 8110-3 OO0) SUPERSEDES PREVIOUS EDITOR CPO 961.613 PROT152 PROT153 le NS Droorintro of Trampoutto Fees Aviation Administraton FamAprons:1 OMB No. 2120-0020 11/30/8:07 INSTRUCTIONS: Prialor type all entries. See FAR 43.9. FAR 43 Appendix 8. and AC 43.9-1 (or subsequent revision (recto') for instructions and disposition of this form. This report is required Dy taw (49 PROT515. 1421). Failure to report can result in a civil penalty not to exceed 91,000 1. Aircraft Nationality and Registration Ma* N493LX Serial No. RK 244 Make Model 400A Series 2. Owner 00°t°'° coy sets OH re 44143-145 cater USA 4. Type 5. U it Identification Repair Minden Unit Make Model Serial Number I gii AIRFRAME o POVVERPIANT 0 PROPELLER n ii APPLIANCE ;pit MonufrOuree B. Knd of Agency Norte Andrea City Cleveland see. OH Ze 44143-1453 country USA Cl /Manufacturer SI Certificated Repair Station CRS # 25NR667B D. I certify that the repair have been made in accordance furnished herein is true per 10 PROT516 Part 43 App. B anclior and MI alteration made to the unit(s) identi ed in item 5 above and described on the reverse or attachments hereto with the requirements of Part 43 of the U.S. Federal Aviation Regulations and that the Information correct to the best of my knowledge. 12/29/2013 prove or'eum o Pursuant to the authority given persons specified below, the unit idenUSed r j in dem 5 was inspected in the manner presort ed by the APPROVED K REJECTED Inspector Manufacturer Maintenance Or oepanment of Transposed BY FAA Designee Certificate or 2129/2013 CRS # 25NR667B PROT154 PROT155 NOTICE Weight and balance or operating limitation changes shall be entered in the appropriate aircraft record. An alteration must be compatible with all previous alterations fo assure continued conformity with the applicable airworthiness requirements. (If more space is required, attach additional sheets. Identify with aircraft nationality and registration mark and date work completed.) N493LX 12/29/2013 Date Installed the following In-Flight Entertainment System in accordance with STC # ST03960AT and in accordance with Nextant Aerospace Master Drawing List D81002067. Revision F.05 Dated: October 9, 2013. Installed Bonner Cabin LED Lighting System without the Venue System in accordance with NX330-1304002. Rev B Dated October 17, 2013. Ref. drawing for parts list. ICA Requirements. Ref FM Order 8100.17 Page 7-5 and 7-6 Use FM publications such as AC 43.13-1, Acceptable Methods, Techniques, and Practices - Aircraft Inspection and Repair, and AC 43.13-2, Acceptable Methods, Techniques, and Practices - Aircraft Alterations; part 43 appendix 0; or other applicable aviation standards. Installed Iridium Sat Comm (Cockpit Phone only) and Broadband Internet System with Aircell Axxess II and ATG 4000 in Accordance with DB 1001013. Rev E ICA for Aircell System Ref to Nextant Aerospace Document No DB1105003. Rev A dated September 22 2011 or later FM Accepted Revisions The following manuals contain complete detailed maintenance instructions and should be consulted for all maintenance activities not covered within this ICA: Aircell Axxess It Installation Manual D12004 Revision E, dated March 2010 or later applicable revision Aircell ATG-4000 Installation Manual D13485 Revision B Dated November 2009 or later applicable revision Aircell Axxess II WLAN AFM Supplement D61002072 Rev IR dated March 22 2012 for the has been Installed in the AFM Installed the Astronics DC-AC 115 VAC Power Supply in Accordance with DB1002067 Rev F.04 Dated 10/9/2013 This is Located under the Seat Divan ICA for Astronics 115 VAC Cabin Inverter Ref to Nextant Aerospace Report No DB1108018 Rev IR Date 9/22/2011 or later FM Accepted Revision. Aircraft Flight Supplement DB1109012 has been installed on the Aircraft See Current Weight and Balance Dated: December 29, 2013 End FAA Form 337 (10-06) PROT156 PROT157 Vniteb *oho of L•ttrica !epartment of Zranzportation geberal crtbiation Abministratian $uppietrtental Mgpe Certificate 0 1.4) tree/nia• Ammo/4 Afarland ST03960AT 3800 Southern Blvd. West Palm Beach, FL 33406 ere/Au ea* nefeente la dr fir s eieureArze anvivivertnee/ Arhi /.4^ elnerAtteeveht eseVite arrAr rlJ 4fierVetareprea meet* hie tretoevareaJ erree:rementi ri e 044'25 Ver Federal Aviation ifoyereekaMJ. Cseritenreivat A6:Matee t 6sw SAC Hawker Beechcraft Corporation sea. 400A cZetierffr/Ova r/Fp://r Fyn cellar Installation of Rockwell Collins Venue In-Flight Entertainment(IFE), AffCel I Axxess Cabin II Iridium Phone and High Speed Internet System with Wireless Local Area Network (W LAN) Astronics I I 5VAC 60HZ Cabin InVerter, and Emteq LED Cabin Lighting System in accordance with Nextant Aerospace LLC, Master Drawing List DB1002067, Revision E, dated January 26, 2012, or later FAA approved revision. 2::rnzahma nwawaivr.i.• This approval should not be extended to other aircraft of this model on which other previously approved modifications are incorporated, unless it is determine by the installer that the interrelationship between this change and any other previously approved modifications will produce no adverse effect upon the airworthiness of that airplane. If the holder agrees to permit another person to use this certificate to alter the product, the holder shall give the other person written evidence of that permission. terhAYEAT envne.g. ,sewterfaye reitik erAhie evrerreveAt4entzereas a.. *Irv/ tea/e, Jetterseiregi Jatonexted AN:rine/re to 4vrtifiver/eivA o&* rJ et4reelm eV/Ma:an • ery de r/66. .rnOnse,/tedrireivs ,./UneiltifeakivA. Over etwAve44-4. July 28, 2012 Ode rAuftern re March 22, 2012 Ode erAsJoreott.- 0404* at/tenni- Manager Atlanta Aircraft Certification Office Any Alcoration of tbla CerellIcare Is poninablt by a Ilo et net exceeding 13,000. or imprisonment nee stcnOlzq J )sirs, or Sorb. TAS. Iran MG - 1 of 2 PAGta This costa:Scare sky 000 n o ferrod In acCergen,e wIcA IAR 14.4,. PROT158 PROT159 3.ilnilebStafeo of America !epartment of granepartation - Ofeberal Abiatiart Abministration Supplemental. 'Tut Tertifirate ( cintinuation *feet) A1/402,60ST03960AT When the Rockwell Collins Venue system is installed Airplane Flight Manual Supplement, DB1106015, Revision A, dated March 22, 2012, or later FAA approved revision, is required. When the A ircell Axxess II system is installed Airplane Flight Manual Supplement, DB1002072, Revision IR, dated March 22, 2012, or later FAA approved revision, is required. When the Astronics Cabin Inverter system is installed Airplane Flight Manual Supplement, DB1109012, Revision IR, dated March 22, 2012, or later FAA approved revision, is required. This system is intended to provide Internet connection and email services to the airplane's cabin using portable electronic devices (PEDs). Any other intended function of this equipment will require a re- examination of the certification basis. When the Rockwell Collins Venue system is installed Instructions for Continued Airworthiness (ICA), Nextant Aerospace Document No. DB1002068, Rev III, dated September 22, 2011, or later FAA accepted When the Aircell Axxess II system is installed Instructions for Continued Airworthiness (ICA), Nextant Aerospace Document No. DB1105003, Rev A, dated September 22, 2011, or later FAA accepted revisions must be made available to the operator at the time of installation. When the Astronics Cabin Inverter system is installed Instructions for Continued Airworthiness (ICA), Nextant Aerospace Document No. DB1108018, Rev lit, dated September 22, 2011, or later FAA accepted When the Emteq LED Cabin Lighting system is installed instructions for Continued Airworthiness (ICA), Nextant Aerospace Document No. DB1108019, Rev iR, dated September 22, 2011, or later FAA accepted My alteration of this coiCitiCOM is ponishible by a rine of not •XMMISM r1.000. or SePrisorrtent not exceeding l press, or both. tilt row 1110-2-1110-0i Mt 2 of 3 outs This certificatebey be transferred In ICCOrdlnef rich FM 2l.47. PROT160 PROT161 giliien Atated of ?merlon pepartment of ' :transpartation - Offeberal cAbiation cataninistration Supplemental Type Certificate (Continuation Ant) A/14022,4 4ST03960AT % ,4:1oteleiva .954re,i4.• The Certification Basis for this installation is per Type Certificate Data Sheet Al 6SW original Certification Basis, Federal Aviation Regulation (FAR), Part 25 as amended by Amendment 25-1 through 25-40 plus FAR 25.1335, 25.1351(d), 25.1353(c)(5), and 25.1447 of Amendment 25-41; FAR. 25.29, FAR 25.255, and FAR 25.1353(c)(6) of Amendment 2542; and FAR 25.361(b) and 25.1329(h) of Amendment 25-46. In addition the following specified rules amendment levels were used for this installation. 25.571 25.1353(We) 25.1357 25.1431 25.1529 125-541 [25-1231 [25-1231 [25-1131 125.541 [..] Indicates amendmcn level END - Any alteration of this certificate is punishable by a fins of not exceeding 41.000, or Itearlsonnant not exceeding A years, or both. FAA Fon. 0110-Z-1110-6U ME 3 of 3 PAGES This Certificate may ae transferred in teceordence with FAR 22.17. PROT162 PROT163 Nextant Aeros ace LLC est Palm Beach FL 33406 Master Drawing List Report No: DB1002067 Revision F.05 Document Number: DB1002067 Revision: F.0510/1812013 In-Flight Entertainment HAWKER BEECHCRAFT 400A Aircraft FAA STC ST03960AT Approved By Date 1-4-2013 Page 1 of 7 PROT164 PROT165 O u.5 Onsarymor or rrompxv,43n Fedni Aviation Adralniftrittlen Fttri ',waved OMB No 2120.0020 11/1C/2007 Etecironic Tracking Number INSTRUCTIONS: Print or type all entries. See FAR 43.9, FAR 43 Appendix B. and AC 43.91 (or subsequent revision thereof) (Or instructions and disposition of this form. This report is required by law (49 U.S C. 1421). Failure to report can result in a civil penally not to exceed 51,000 1. Aircraft N493LX Serial No. RK 244 Make Model 400A Ser,es 2. owner Name (As shown on registrabon cera ate) Address (As shown on registration centhcate) Add"" c ty Richmond Heigbts slaw. OH 7.,9 44143-1453 county USA 4. Type Repair Alteration lint Make Model Serial Number 0 :I AIRFRAME . (As descnbed in (tern 1 above) K O POWERPLANT Ell K PROPELLER ID APPLIANCE Type manatee( 8 Kind of Agency tin Address Coy Cleveland sum OH zip 44143-1453 duality USA O U.S. certificated Mechanic O Manufacturer C. Cendicate No. 0 CRS # 25NR6678 0. I certify that the repair and/or alteration made to the unit(s) identified in item 5 above and described on the reverse or attachments hereto have been made in accordance with the requirements of Part 43 or the U.S. Federal Aviation Regulations and that the information furnished herein is true and correct to the best o(m knowled•0 per 14 PROT517 Pan 43 APP. B 1:3 12/29/2013 7. Approval for Return to rvtce Pursuant to the authOnly given persons specified below, the unit identified in item 5 was inspected in the manner prescribed by the El APPROVED K REJECTED Inspector Manufacturer Department of TranSperl BY Certificate Designation CRS or # 25NR6678 FAA Designee No Otner (Specify) "iv 12129/2013 PROT166 PROT167 NOTICE Weight and balance or operating limitation changes shall be entered in the appropriate aircraft record. An alteration must be compatible with all previous alterations to assure continued conformity with the applicable airworthiness requirements. (If more space is required, attach additional sheets. Identify with aircraft nationality and registration mark and date work completed.) N493LX Upper Aft Baggage Panel od 12/29/2013 Date Modified Baggage Ceiling Panel to Accommodate the Engine FADEC wire harness. 1. Fabricated two panel pieces, N251103-001 and N251103.002. 2. Installed N251103-001 to existing baggage compartment structure 128.440095.1 using two screws and install N251103-002 as shown with a trim to fit honeycomb piece fabricated from interiors using potted inserts. 3. Attached honeycomb baggage panel to N251103-001 in upper aft baggage area using three 4055-21 Camloc quarter- turn fasteners and 214.16D receptacles. Secured N251203-002 to existing upper aft baggage panel with two Camloc 40S5-21 quarter - turn fasteners and 214-16D receptacles. See attached FAA Form 8110-3 Signed by DERT-410115-CE on February 12, 2013 using Nextant Aerospace Engineering Order EO 029. Rev E Dated February 8. 2013 ICA Weight change is Negligible. Continue with Beechjet 400/400A Maintenance Manual Inspection Procedures for this Area End PROT168 PROT169 1. DATE February 12, 2013 2 MAKE Corporation 3. MODEL NO. 400A 4. TYPE (Aircraft Engine. Propeller, etc ) Aircraft 5. NAME OF APPLICANT Richmond Heights, Ohio LIST OF DATA 8 IDENTIFICATION 7 TITLE EO 029 Rev. E February 8, 2013 Upper Aft Baggage Panel Mod. Notes: 1) The structural aspects approval is only for the demonstrates compliance subparagraph listed below 2) This form constitutes FAA substantiation of compliance END-----------data are approved herein. This the data listed above specified by paragraph and engineering data necessary for for the entire alteration. only of the above listed engineering data. It indicates only with the regulations as "Applicable Requirements." approval of all the to necessary requirements e. PURPOSE OF DATA: Engineering data in support of major alteration to Hawker Beechcraft 400A, SIN RK-244. 9. APPLICABLE REQUIREMENTS (List SpeCiat sections) PROT518 Title 14 Part 25.301[25-23], 25.303[25-23], 25.305(a)(b)(c)[25-23), 25.307(a)[25-23], 25.562(c)[25-23), 25.601[25.00], 25.603(a)(b)(c)[25-38), 25.605(a)[25-00), 25.607[25-23], 25.609(a)(b)[25-00], 25.611[25-23], 25.613(a)(b)(c)(25-00), 25.619[25-23], 25.625(a)(b)(c)[25-23), and 25.789[25-32]. 10. CERTIFICATION - Under authority Part 183. data listed above and on applicable requirements of the Airworthiness K Recommend vested by direction of the Administrator and attached sheets numbered NIA_ have been examined in accordance with conditions and limitations of appointment under 14 PROT519 In accordance with established procedures and found to comply with Standards Listed. these data a Approve DESIGNATED ENGINEERING REPRESENTATIVE(S) 13. CLASSIFICATION(S) in DERT-410115-CE Structures FAA Form 8110-3 (03-10) SUPERSEDES PREVIOUS EDITION FsIe Number. H13107-O6 Page 1 of 1 PROT170 PROT171 U.S Onedrrentol Transponason darndinrstion Form Apprcacd OMB no 2120-0O20 limoacor INSTRUCTIONS: Pont or type an entries. See FAR 43.9, FAR 43 Appendix B. and AC 43.9.1 (or subsequent revision thereof) for instructions and disposition of this form. This report is required by law (49 PROT520. 1421). Failure to report can result in a cave penalty not to exceed 61,000 1. Aircraft Nationality and Regstration Mark N493LX Serial No. RK 244 Make Model 400A Series 2. Owner Name (As shown on registration cerbticate) Address (As shown on r ;strewn cerbtkate Armen car Richmond Heieht§ State OH to 94143-1453 county OA 4. Type S. Unit Identification Repair Alteration Unit Make Model Serial Number K 0 AIRFRAME (As described in item I above) El O POWERPLANT K O PROPELLER K 0 APPLIANCE Typo Mandacttser B Kind of Agency Name Address City Cleveland Suite. OH zp 44143-1453 county USA El U.S. Certificated Mechanic a Manufacturer Cl Foreign Certificated MechaniC 0 CRS # 25N R667B ID Certificated Maintenance Organization D. I Certify that the repair andror alteration made to the und(s) identified in item 5 above and described on the reverse or attachments hereto have been made in accordance with the requirements of Pad 43 of the U.S. Federal Aviation Regulations and that the information per 14 PROT521 Part 43 APP. CI 0 12/29/2013 7. Approval for Return to S ice ii..2 in item 5 was inspected in the manner prescnbed by the APPROVED 0 REJECTED inspector Manufacturer BY Certificate Designation CRS or # 25NR6678 FM Designee NO. 12/29/2013 FAA Form 337 (1ODO) PROT172 PROT173 NOTICE Weight and balance or operating limitation changes shall be entered in the appropriate aircraft record. An alteration must be compatible with all previous alterations to assure continued conformity with the applicable airworthiness requirements. (If more space is required, attach additional sheets. Identify with aircraft nationality and registration mark and dale work completed.) N493LX 12/29/2013 Date Installed New Pitot Probes in accordance with STC ST10159SC. Nextant Aerospace Master Drawing List Document 373-00.0001 Rev CC EO24-11 Removed Pitot Probes Part Number PH1100-MU-R-1 Removed Pitot Probes Part Number PH1100-MU-L-1 Installed Pitot Probes Part Number PH1100-MUR-EN Serial Number 1975803 Installed Pitot Probe Part Number PH1100-MUL-EN Serial Number 1728401 Leak Check carried out IAW Beechcraft Aircraft Maintenance Manual Chapter 34-12.00-201. ICA Continue with Normal Hawker Beech Maintenance Practices for this Area End FAA Form 337 pace) PROT174 PROT175 0 v s owinnint ot (Air(rame, Powerplant, Propeller, or Appliance) Transatmen Administration Form /owned 06,18 N. 2i204020 ii3Or2 C07 INSTRUCTIONS Print or type all entries. See FAR 43 9, FAR 43 Appendix B. and AC 43.9.1 (or subsequ nt revision there* fOr InStruetiOnS and disposition of this form. This report is required by law (49 PROT522. 1421) Failure to report can result in a civil penally not O exceed $1,000 I. Aircraft N493LX Serial No. RK 244 Make Model 400A Series 2. Owner AdCMCS2 City sta. OH zc 44143-1453 comity Na 4. Type Repair Alteration Unit Make Model Senal Number ili K AIRFRAME (As desciibed in item 1 above) 0 O POWERPLANT O PROPELLER K O APPLIANCE Type Man& Dela, Name Address City Cleveland sup.. OH zip 44143-1453 Cutory USA ID U.S. Certificated Mechanic 0 I Manufacturer 0 0 CRS # 25NR6676 El Ceti/leafed Maintenance Organization O. I certify that the repair and/or alteration made to the unit(s) identified in item 5 above and described on the 'Over e or attachments hereto have been made in accordance with the requirements of Part 43 of the U.S. Federal Aviation Regulations and trat the information per 14 PROT523 Part 43 App. B 0 12/29/2013 7. Approval for Return t 'ervice 0 in item 5 was inspected in the manner prescn bed by the APPROVED 0 REJECTED BY Inspector Manufacturer FM Designee X Repair Station Certificate or Design lion No. 12129/2013 CRS # 25NR6676 PROT176 PROT177 NOTICE Weight and balance or operating limitation changes shall be entered in the appropriate aircraft record. An alteration must be compatible with all previous alterations to assure continued conformity with the applicable airworthiness requirements. (If more space is required, attach additional sheets. Identify with aircraft nationality and registration mark and dale work completed) N493LX Provisions for 19107 in Cockpit Sidewall at FS122.735 12/29/2013 Date Added Mount provisions for J9107 in bracket assy. 45A88588-3 at Flight Station 122.735 provided in Structure Repair Manual Document 53-20.05-001. Use receptacle MS3470W18. See attached FAA Form 8110-3 Signed By DERT-410115-CE Dated December 28, 2012 using Nextant Aerospace Engineering Order 115-12 Rev C, Dated November 27, 2012 for details. ICA Weight change is Negligible. Continue with Beechjet 400/400A Maintenance Manual Inspection Procedures. End FAA Form 337 (to-067 PROT178 PROT179 1. DATE December 28, 2012 2. MAKE Corporation 3. MODEL NO. 400A 4. TYPE (Aircraft. Engine, Propeller, etc.) Aircraft LIST OF DATA 0 IDENTIFICATION 7 DILE EO 115-12 Rev. C November 27, 2012 Mount Provisions for J9107. Notes: 1) The structural aspects only of the above listed data are approved herein. This approval is only for the engineering data. It indicates the data listed above demonstrates compliance only with the regulations specified by paragraph and subparagraph listed ' below as "Applicable Requirements." 2) This form constitutes FM approval of all the engineering data necessary for substantiation of compliance to necessary requirements for the entire alteration. s. PURPOSE OF DATA: Engineering data in support of major alteration to Hawker Beechcraft 400A, S/N RK-244. 9. APPLICABLE REQUIREMENTS (List specific sections) PROT524 Title 14 Part 25.301[25-23], 25.303[25-23), 25.305(a)(b)(c)[25-23), 25.307(a)125-231, 25.601[25.00), 25.603(a)(b)(c)[25-38], 25.605(a)(25-00), 25.607(25-23], 25.609(a)(b)[25-00], 25.611[25-23], 25.613(a)(b)(c)[25- 00), 25.619(25-23), and 25.625(a)(b)(c)[25-23]. 10. CERTIFICATION - Under authority vested by drectica of the Administrator and in accordance with conditions and limitations of appointment under 14 PROT525 Pad 183, data listed above and on attached sheets numbered N/A have been examined in accordance with established procedures and (cord to comply with applicable requirements of the Airworthiness Standards Listed. 0 Recommend approval of these data I (we) Therefore El ApprOvatheSe data it. SIGNATURE(S) OF DESIGNATED ENGINEERING REPRESENTATIVEIS) 13. CLASSiFICATiONIS) DERT-410115-CE Structures File Number. H12740.03 Page 1 01 PROT180 PROT181 0 u s ceprvurenter Tiensevuoce Fodonl Aviation Anniniornion Form APPrOvatl OMB No. 212043020 11 nolcor Elect(WIC Tracking Number INSTRUCTIONS: Print or lype all entries. See FAR 43.9, FAR 43 Appendix 8, and AC 43 9.1 (or subsequent revision thereof) for instructions and disposition of this loan. This report is required by law (49 PROT526. 1421). Failure to report can result in a civil penalty not to exceed 31000 1. Aircraft N493LX Serial No. RK 244 Make Model 400A Series 2. Owner Address (As shown on re istration certificate Addf05f City site. OH zp 44143-1453 Cony USA 4. Type 6. Unit Identification Repair Alteration Unit Make Model Serial Number 0 0 AIRFRAME (As described in pem 1 above) li O POWERPLANT 0 Ill PROPELLER El O APPLIANCE Typt Manigactortv A Agency's Name and Address B. K nd of Agency wens Address Cali Cleveland sin. OH zip 44143-1453 cairn USA 0 U.S. Certificated Mechanic a IManufacturer 0 C. Cenificate No. 0 Certificated Repair Station CRS # 25NR667B 0 Certificated Maintenance Organization D. I certify that the repair and/or alteration made to the wigs) identified in item 5 above and described on Ihe reverse or attachments hereto have been made in accordance vith the requirements of Part 43 of the U.S. Federal Aviation Regulations and that the information per 14 PROT527 Part 43 K App. 8 12/29/2013 Pursuant to the authority given persons pecifed below, the unit Administrator of the Federal Aviation Administration and Is identified CI. in item 5 was inspected In the manner prescribed by the APPROVED K REJECTED Inspector Manufacturer BY FAA Designee Oder (Specify) Certificate or CRS # 25NR6676 12/29/2013 PROT182 PROT183 NOTICE Weight and balance or operating limitation changes shall be entered in the appropriate aircraft record. An alteration must be compatible with all previous alterations to assure continued conformity with the applicable airworthiness requirements. (If more space is required, attach additional sheets. lden ify with aircraft nationality and registration ma* and date work completed.) N493LX Title: Ice Detector Master Caution / Master Warning Light on Constantly Re-Installed the previously removed components ( Ref S/B 30-2600, Rev 2) 12/29/2013 Date 1.) Isolation Relay 1(255 P/N: 50-380048-1 2.) Diode CR654, P/N: 132408-22 3.) Ground stud GS151A P/N: M535206-246 (Stud may be marked GS152) As shown in chapter 30-01-01-01 of AMM. 4.) Wire number corrections on wiring diagram 30-01-01-01 Page 1 correct drawing errors on original drawing. Inspect, verify and correct wiring per EO corrections on EO page 2 See attached FAA Form 8110-3 signed by Daniel Buzz DERT-230019-CE. Dated 8/13/2012 using Nextant Aerospace Engineering Order EO 0130 Rev D. Dated 7/18/2012 ICA Weight and Balance Changes are Negligible Continue to Use Existing Beechjet 400/400A Maintenance Manuals Inspection Procedure for this Area END FAA Form 337 (r0-06) PROT184 I PROT185 STATEMENT OF COMPLIANCE WITH AIRWORTHINESS STANDARDS . 1. DATE 8.13.2012 2. MAKE - liwker Eleechcraft 3. MOOEL NO. 400A S/N RK-244 Only 4. TYPE (Airplane. Radio. Heecopter. etc) Airplane S. NAME OF APPLICANT LIST OF DATA B. IDENTIFICATION 7. TITLE Document 130-12 dated 7-18-12 Rev. D Engineering Order Ice Detector MCiVIW Light On Constantly aspects only. This approval is for the electrical systems B. PURPOSE OF DATA Support major alteration to a Ire aft Hawker Eleechcraft 400A RK-244 Only. 9. APPLICABLE REQUIREMENTS (flu SPeriCC stations) 14 PROT528 25.1301(a) (Dire] Note: Comphance has been found to the amendment levels indicated on Hawker Beechczaft TCOS Revision 26 Part 25 Amendment 25.1 through 25-40 to the above applicable requirements. 10. CERTIFICATION - Linder aulh why vested by direction of Ilia Administrator and in accordance vMhconditions and limitations of appointment under 14 PROT529 Pat1183 of the Federal Aviation Regulations. data listed above and on attached sheets numbered &a have bawl examined in accordance with established procedures and round to comply with applicable requirements of the Airworthiness Standards listed. I (We) Therefore approve these date. It. SIUNATUR 4GNATE E I E RI REPRESENTATNE(S) 13. CLASSIRCATILMIS) Systems and Equipment CERT-230019-CE ..'AA Form 81104 (03710) SUPERSEDES PREVIOUS EDITION GPO 901.813 PROT186 PROT187 u.S oreartivent or TIIIMPC41•11}1 reaveritration Form Approved ORS No. N20-0020 timOr2tW INSTRUCTIONS: Print or type all entries. See FAR 43.9. FAR 43 Appendix B. and AC 43.9-1 (or subsequent revision thereof) for instructions and disposition Of this form. This report is required by law (49 PROT530. 1421). Failure to report can result in a civil penalty not 10 exceed 51.000 for eaCh such icilabon (Section 901 Federal Aviation Act 1958) I. Aircraft N493LX Serial No. RK 244 Make Model 400A Series 2. owner Name (As shown on regishation oendicafe) A6Sress City Richmond Heiaht state. OH zip 44143-1453 country USA 4. Typo Repair Mention Unit Make Model Serial Number h.e. K AIRFRAME (As descnbed in (ern t above) K O POWERPLANT 0 O PROPELLER 0 APPLIANCE Typo Man./acts,: G. Conformity Stat moat Nanie Meese city Cleveland State OH zo 44143-1453 Courtry USA 0 Manufacturer ISI Certificated Repair Station CRS # 25NR6678 CI Certificated Maintenance Organization D. I certify that the repair anchor alteration made to the unit(s) Identified in item 5 above and described on the reverse or attachments hereto have been made in accordance with the requirements of Part 43 of the U.S. Federal Aviation Regulations and that the information per 14 PROT531 Part 43 App. II 0 12/29/2013 prove or tum l': crir ce Pursuant to the authority given persons specified below, the unit Identified Admi ist,ator of the Federal Aviation Administration and is 0 in item APPROVED 5 was 0 inspected in the manner prescribed by the REJECTED FM Fit Standards Inspector Manufacturer BY Certificate Designation CRS or # 25NR667B FM Designee No. X Repair Station inspection Authorize% on Other Specify) 12/29/2013 FAA Form 337 00-00 PROT188 PROT189 NOTICE Weight and balance or operating limitation changes shall be entered in the appropriate aircraft record. An alteration must be compatible with all previous alterations to assure continued conformity with the applicable airworthiness requirements. (If more space is required, attach additional sheets. Identify with aircraft nationality and registration mark and date work completed.) N493LX Antenna Repair Patch 12/29/2013 Date After removing the forward lower "L" Band Antenna, Instead of removing the Antenna doubler and filling the connector hole with a coin patch and installing nut plate plugs P/N. DB1105020-189-25, the antenna repair doubler P/N. DB104042.001 was installed on the existing antenna doubler and two coin repair patches P/n. DB1104042-002 were installed, one on top of the other to allow for a flush skin repair. The existing nut plate holes were filled with 4 screws P/N. AN525-10R7. See Attached FAA Form 8110-3 signed by DERT-410115-CE dated August 15, 2012 using Nextant Aerospace Engineering Order 139-12 Rev C Dated August 03,1111Mails. ICA Weight and Balance change is Negligible. Continue with Beechjet 400/400A Maintenance Manual Inspection Procedures. End FAA Form 337 po-orn PROT190 PROT191 1. DATE August 15, 2012 2. MAKE Corporation 3. MODEL NO. 400A 4. TYPE (Aircraft. Engine. Propeller, etc) Aircraft LIST OF DATA 7 TITLE EO 139-12 Rev. C August 3, 2012 Antenna Repair Patch (L-Band Antenna Moved). Notes: compliance only with the regulations specified by paragraph and subparagraph listed below as "Applicable Requirements.' 2) This form does not constitute FAA approval of all the engineering data necessary for substantiation of compliance to necessary requirements for the entire alteration. The electrical requirements are not included in this approval and require separate approval. B. PURPOSE OF DATA: Engineering data in support of FAA STC ST03960AT. PROT532 Title 14 Part 25.301[25-23], 25.303[25-23], 25.305(a)(b)(c)[25-23), 25.307(a)[25-231, 25.365(a)(b)(c)(d)(f)(g)[25-00], 25.562(c)(25-23], 25.601[25-00], 25.603(a)(b)(c)[25.38), 25.605(a)(25-00), 25.607[25-23], 25.609(a)(b)125-00), 25.611[25-23], 25.613(a)(b)(c)[25-00), 25.619[25-23], 25.625(a)(b)(c)[25-23), and 25.789[25-32). Pan 183. data listed above and on applicable requirements of the Airworthiness K Recommend El Approve vested by direction of the Administrator and attached sheets numbered N/A have been examined in accordance with cor.011ons and limitations of appointment under 14 PROT533 in accordance with established procedures and found to comply with Standards Listed. these data II. SIGNATURE(S) OF DESIGNATED ENGINEERING REPRESENTATNE(S) 13. CLASSIFICATIONS) DERT-410115-CE Structures FAA Form 8110.3 (03-10) SUPERSEDES PREVIOUS EDITION Fite Number. H12418.02 Page 1 of 1 PROT192 PROT193 le vs oriparinem or Tamperiewn Fulmer Aviation noeniseetion ram AProved OMB No. 21204020 11/302007 INSTRUCTIONS: Print or type all entries. See FAR 43.9. FAR 43 Apperdx B. and AC 43.9-1 (or subsequent revision thereof) for instructions and disposition of this form. This report is required by law (40 PROT534. 1421). Failure tO report can result in a cinf penalty net to exceed 81.000 1. Aircraft N493LX Serial No. RK 244 Make Model 400A Series 2. Owner Name (As shown on reels:tattoo certificate) Address (As shown on tegisfration certificate) neoresi City sure. OH zo 44143-1453 cumin USA 4. Type Repair Alteration Unit Make Model Serial Number K E4 AIRFRAME (Asdescribed in MOM I Mon) K D PONIERPLANT O PROPELLER El APPLIANCE Type meoracmar 8. Kind of Agency Rae Address City Cleveland slaw OH zip 44143-1453 Country USA O U.S. Cenincated Mechanic CI IManufacturer O C. Coruscate No. 0 CRS # 25NR667B 0. i certify that the repair and/or alteration made to the unit(S) Identified in Kern 5 above and described on the reverse or attachments hereto have been made in accordance with the requirements of Part 43 of the U.S. Federal Aviation Regulations and that the information per 14 PROT535 Part 43 APP. B 0 12/29/2013 Pursuant to the authority given persons pecified below. The unit identified Administrator of the Federal Aviation Admnistration and is 111 in Item 5 was inspected in the manner prescribed by the APPROVED 0 REJECTED FAA Fit Standards Inspector Manufacturer i Person Approved by Canadian BY FM Designee CedifiCete or 12/29/2013 CRS # 25NR667B FAA Form 331 (10-os) er' PROT194 PROT195 NOTICE Weight and balance or operating limitation changes shall be entered in the appropriate aircraft record. An alteration must be compatible with all previous alterations to assure continued conformity with the applicable airworthiness requirements. (If more space is required, attach additional sheets. Identify with aircraft nationality and registration mark and date work completed.) N493LX Title: Pedestal cover extension Modification 12/29/2013 Date After STC modification of pedestal per [SSN REDACTED]_B, existing pedestal close out tray needs to be extended to cover appropriate areas. Modification of the close out tray is required. Modify the pedestal close out tray per drawing NX25 - 10002. See attached FAA Form 8110-3 signed by DERT - 410115-CE. Dated 11/8/2013 using Nextant Aerospace Engineering Order EO 1018 Rev F. Dated 10/9/2013 ICA Weight and Balance Changes are Negligible Continue to Use Existing Beechjet 400/400AMaintenance Manuals Inspection Procedure for this Area END PROT196 PROT197 1. DATE November 8, 2013 2. MAKE Corporation 3. MODEL NO. 400A 4. TYPE (Aimsft. Engine, Properler, eft) Aircraft 5. NAME Of APPLICANT LIST OF DATA 7 TIP E EO 1018 Rev. F October 9, 2013 - Pedestal Cover Extension Modification. - Notes: below as 'Applicable Requirements? 2) This form constitutes FM approval of all the engineering data necessary for substantiation of compliance to necessary requirements for the entire alteration. B. PURPOSE OF DATA: Engineering data in support of major alteration to Hawker Beechcraft 400A, SIN RK-244. 9. APPLICABLE REQUIREMENTS (List specilic sections) PROT536 Title 14 Part 25.301(25.23), 25.303[25-23), 25.305(a)(b)(c)(25-23], 25.307(a)[25-23), 25.562(c)(25-23), 25.601(25-00], 25.603(a)(b)(c)[25-38], 25.605(a)[25-00), 25.607(25-23), 25.609(a)(b)[25-00), 25.611[25-23], 25.613(a)(b)(c)(25-00), 25.619(25.23), 25.625(a)(b)(c)125-23), and 25.789[25-32). Part 183, data listed above and on applicable requirements of the ArnvonhMess K Recommend vested by direction of the Administrate( and attached sheets numbered Nth have teen examined In accordance with conditions and lirnotati5ns of appointment under 14 PROT537 in accordance with established procedures and found to comply with Standards Listed. these data 0 Approve 11. SIGNATURE(S) OF DESIGNATED ENGINEERING REPRESENTATIVE(S) DERT-410115-CE Structures File Number H13817.04 Page 1 of 1 PROT198 I PROT199 0 Deparment of TrarreonatIon Ayarwal Aviation Aahaduration Form Approved OMB No. 2120-0020 lino/mg INSTRUCTIONS: Print or type all entries. See FAR 43.9. FAR 43 Appendix B. and AC 43.9-1 (or subsequent revision thereof) for instructions and disposition of this loon. This report is required by law (49 U. S.C. 1421). Failure to report can result in a civil penalty not to exceed 51,000 for each such violation (Section 901 Federal Aviation Act 1959) 1. Aircraft N493LX Serial No. RK 244 Make Model 400A Series 2. Owner Name (As shown on rogiSfrafion certificate) Adere6s cry site OH tip 44143.1453 coowy USA 4. Typo Repair Alteration Unit Make Model Serial Number 0 0 AIRFRAME (As described in Nem 1 above) Ill IE POWERPLANT 0 PROPELLER K O APPLIANCE Type manufacturer' Nana Patron cry Cleveland State. OH tip 44143-1453 Country USA CI u.s. Certificated Mechanic O I Manufacturer O B CRS # 25NR667B O D. I certify that the repair and/Or alteration made to the unit(s) identified in item 5 above and described on tne reverse or attachments hereto have been made in accordance with the requirements of Part 43 of the U.S. Federal Aviation Regulations and that the information per 14 PROT538 Part 43 APP. B El 12/29/2013 Ell in item 5 was Inspected In the manner presalbecl by the APPROVED K REJECTED FAA Flt Inspector Standards Manufacturer BY Certificate Designation CRS or # 25NR667B FM Designee No. InsPeCtiOn Authorization 12/29/2013 PROT200 PROT201 NOTICE Weight and balance or operating limitation changes shall be entered in the appropriate aircraft record. An alteration must be compatible with all previous alterations to assure continued conformity with the applicable airworthiness requirements. (If more space is required, attach additional sheets. Identify with aircraft nationality and registration mark and date work completed.) N49311 DEACTIVATE CLOCKS 12/29/2013 Date For Pilots Clock Deactivation: I.) Removed PLT CLOCK circuit breakers from LH FWD CB Panel. Spliced feed wires together. Cap and Stowed Load side wires. 2.) At Radio Junction Box: a.) disconnected wire W78-I9 from 393IJ25 PIN R & S. b.) Spliced wire W78-19 from pin R with 3931322 wire W71-3 (20) pin D•. For Co-Pilots Clock Deactivation: 4.) Removed COPLT CLOCK circuit breakers from LH FWD CB Panel. Spliced feed wires together. Cap and Stowed Load side wires. 5.) At Radio Junction Box: a.) disconnected wire W78.45 from 39311B1 3931R3 pin 3. b.) cap and stowed wire. c.) Installed jumper from pin 3 to 3931.122 pin F* (splice with wire W71-4 (20)) 6.) Tested all WOW interface circuits at #1 & #2 DCU, #1 & #2 DCP,01 & #2 PFD,ti I & #2 MFD, DAU, #1 &#2 ADC, #1 & #2 GPS, #1 & #2 FSU, #1 & #2 TDR. 7.) Changed power wiring for ELT from #2 Clock to #2 Audio panel. Disconnected wire from inline fuse ELTFI feed side and connected to Audio power input 2350P4 pin 8 (spliced with wire W965.019 (20)). Tested ELT. This removal was electrically approved by FAA DERT-230019-CE using a FAA 8110-3 Dated November 15, 2013 Using Nextant Engineering order 1165 Rev B Dated 11/13/2013 End FAA Form 337 (1005) PROT202 PROT203 V.S. DEPARTMENT OF TRANSPORTATION 1. DATE 11.15-2013 2. MAKE - Hawker Beechcraft . \ 3. MODEL NO. 400A SIN RK-244 Only 4. TYPE (Airplane, Radio. Helicopter, etc.) Airplane LIST OF DATA G. IDENTIFICATION 7. TITLE Document EO 1165 dated 11.13.13 Rev. B - Engineering Order Deactivate Clocks END This approval is for the electrical systems aspects onty. 8. PURPOSE OF DATA Support major alteration to aircraft Hawker Beechcraft 400A RK-244 Only. 14 PROT539 25.1301(a) pig' Note: Compliance has been found to the amendment levels indicated on Hawker Beechcraft 400A TCDS Revision 26 Part 25 Amendment 25- 1 through 25-40 to the above applicable requirements. 10. CERTIFICATION - Under authority vested by direction of the Administrator and in accordance with conditions and limitations of appointment under 14 PROT540 Pan 183 of the Federal Aviation Regulations. data listed above and on attached sheets numbered WA have been examined In accordance with established procedures and found to comply with applicable requirements of the Airworthiness Standards listed. I (We) Therefore approve these data. 11. SIGNATURES I N ING REPRESENTATNE(S) DERT-230019-CE Systems and Equipment 1-AA Form 8110-3 (03/10) SUPERSEDES PREVIOUS EDITION GPO 90t413 PROT204 PROT205 C Trans •piinment el T portaarn Administration Form Appnarod om8 No.21204020 I 1r30,2C07 INSTRUCTIONS: Print or type 31 entries. See FAR 43.9. FAR 43 Appendix B. and AC 43.9-1 (or subsequent revision thereof) for instructions and disposition of this form. This report is required by law (49 U.S C. 1421). Failure to report can result In a civil penalty not to exceed $1,030 1. Aircraft N493LX Serial No. RK 244 Make Model 400A Bones 2. Owner Address (As shown on regtsfration certificate) AnSress Gila sin OH zip 44143-14U Camay USA 3. Far FAA Use Only 4. Type Repair Alteration Unit Make Model Serial Number 0 AIRFRAME 0 O POWERPLANT o K PROPELLER U APPLIANCE TWO Mania:Leer 6. Conformity Slat mont B. K nd of Agency Wits Melon City Cleveland Stati OH co 44143-1453 cowry USA 0 u.S. CerbliCaMd Mechanic 0 I Manufacturer 0 Foreign Ceetbealed Mechanic C. Certificate NO. 0 CRS # 25NR667B 0 Certificated Maintenance Organization D. !certify that the repair and/Or alteration made to the rings) identified in item 5 above and described on the reverse or attachments hereto have been made in accordance with the requirements of Part 43 of the U.S. Federal Aviation Regulations and that the information furniihed herein is true and correct to the best of my knowledge. per 14 PROT541 Part 43 K APP. B 12/29/2013 Pursuant to the authonly given persons specified below, the unit identified El in item 5 was inspected in the manner prescribed by the APPROVED 0 REJECTED av FM Fit Standards Inspector Manufacturer FAA Designee inspection Authorization Cenificace Or Designation No 2/29/2013 CRS # 25NR667B PROT206 PROT207 NOTICE Weight and balance or operating limitation changes shall be entered in the appropriate aircraft record. An alteration must be compatible with all previous alterations to assure continued conformity with the applicable airworthiness requirements. (It more space is required, attach additional sheets. Identify with aircraft nationality and registration mark and date work completed.) N493LX TITLE: Aircraft Windshield Sealing Process Deviation: 12/29/2013 Allow Deviation from AMM 56-10-00-201 for the sealing of the aircraft windshield process. Date Temporary fasteners are not necessary during the sealing of the windshield. Original & typical bolts for installation may be used during the process, to keep retainers and shims in place during the entire sealing & installation of the windshield. After proper sealing time had elapsed, torqued bolts for installation of windshield per AMM. See attached FM Form 8110-3 Signed By DERT-410115-CE Dated June 12, 2013 using Nextant Aerospace Engineering Order 1257, Rev. A, Dated May 21, 2013 for details. ICA Weight change is Negligible. Continue with Beechjet 400/400A Maintenance Manual Inspection Procedures. End FAA Form 337 (10-08) PROT208 PROT209 1. DATE June 12, 2013 2. MAKE Corporation 3. MODEL NO. 400A 4. TYPE (Aircraft Engine. Propene( eta) Aircraft LIST OF DATA 6 IDFNTIRCATION 7 TITLE EC 1257 Rev. A May 21, 2013 Aircraft Windshield Sealing Process Deviation. Notes: below as 'Applicable Requirements." 2) This form constitutes FAA approval of all the engineering data necessary for substantiation of compliance to necessary requirements for the entire repair. 8. PURPOSE OF DATA: Engineering data in support of major repair to Hawker Beechcraft 400A, SIN RK-244. PROT542 Title 14 Part 25.301[25-23), 25.303[25-23), 25.305(a)(b)(c)(25-23], 25.307(a)[25-23], 25.601[25-00), 25.603(a)(b)(c)(25-38], 25.605(a)(25-00), 25.607(25-23], 25.609(a)(b)[25-00), 25.611[25-23), 25.613(a)(b)(c)(25- 00], 25.619[25-231, and 25.625(a)(b)(c)125-231. Part 183: data listed above and on applicable requirements of the Ainvorthiness K Recommend vested by direction of the Administrator and in accordance with condelices and limitations of appointment under 14 PROT543 attached sheets numbered _Ha_ have been examined in accordance with established procedures and found to comply with standards Listed. these data i015 Approve II. SIGNATURES) OF DESIGNATED ENGINEERING REPRESENTATIVES) 13. CIASSIFICATION(S) DERT-410115-CE Structures File Number. H13367-01 Page 1 oft PROT210 PROT211 e u.s oepavvent or Truirexitatien Folond AvlatIon Adonlnistration FormApprond OMB No. 2i2043020 iti3OIXOT INSTRUCTIONS: Print or type all entries. See FAR 43.9. FAR 43 Appendix 9. and AC 43.94 (or subsequent revision thereof) for instructions and disposition of this form. This report is required by law (49 V $ C. 1421). Failure to report can result in a Civil penalty not to exceed $1,000 t. Aircraft Nationally and Registration Mark N493LX Serial No. RI< 244 Make Model 400A Series t Owner *guess Ci:y Mete OH zp 44143-1453 CoJtry USA 4. Typo 5. U It Identification Repair Alteration Unit Make Model Serial Number El AIRFRAME (As descnbed in Item I above) MI El POWERPLANT l: PROPELLER 0 El APPLIANCE Typo manure:firer A. Agency's Name and AddreSS It Kmd of Agency mete mons City Cleveland state. OH zo 44143.1453 cmintry USA O I Manufacturer 0 CRS # 25NR667B 0. I certify that the repair andror ateraten made to the twigs) identified in item 5 above and described on the reverse or attachments hereto have been made in accordance with the requirements of Pad 43 of the U.S. Federal Aviation Regulations and that the information per 14 PROT544 Part 43 App. B 0 2/29/2013 7. Approval for Return (Service Pursuant to the authority given pe sons specified below. the unit identified in item 5 was inspected in the manner prescribed by the AdMiNStrator of the Federal Aviation Administration and is 121 APPROVED K REJECTED Inspector Manufacturer BY Certificate Designation CRS or # 25NR667B FAA Designee No. • /2013 FAA Form 337 no-06) PROT212 PROT213 NOTICE Weight and balance or operating limitation changes shall be entered in the appropriate aircraft record. An alteration must be compatible with all previous alterations to assure continued conformity with the applicable airworthiness requirements. (If more space is required, attach additional sheets. Identify with aircraft nationality and registratkin mark and date work completed.) N493LX 12/29/2013 Date Requested for use of new processes & materials for the removal and installation of Main & Side Windscreen, deviation from HBC AMM When performing the removal and installation of the windscreen and/or cockpit side windows, the following deviations from the HBC AMM are allowed & recommended: 1. During the removal & installation of the main windscreen, reference FO-AMMS document, chapter 56-10-01 for the main windscreen installation using AVDEC materials. This document correctly defines the processes and materials to be used for the removal and installation of the main windscreen. 2. During the removal and installation of the cockpit side windows, reference Flight Options FO-AMMS Document, chapter 56-10-10 & 56-10-11 for the replacement of the side window inner rubber gasket. This document correctly defines the processes and materials to be used for the replacement of the cockpit side windows inner rubber gasket. NOTE: TG8498 & HT3935-7 may not be used on exterior surfaces unless sealant is to be painted after curing for protection against UV light. PERMISSIBLE TO PAINT OUTER WINDSHIELD RETAINER WITH Chevron White JET GLO, CM0570513 (Sherwin-Williams) This Alteration was FAA Approved by FM DERT-410115-CE using an FM Form 8110-3 dated December 28, 2013. Using Nextant Aerospace Engineering Order 1303 Rev B Dated November 13, 2013 ICA Continue with Normal Hawker Beech Maintenance manual Inspection Requirements for this Area End PROT214 PROT215 1. DATE December 28, 2013 2. MAKE Corporation 3. MODEL NO. 400A 4. TYPE (Aircraft. Engine. Propeller, etc.) Aircraft LIST OF DATA 7 TITLE EO 1303 Rev. B November 13, 2013 Process & Material Deviation for the Removal and Installation of the Main & Side Windscreens. Notes: 1) The structural aspects only of the above listed data are approved herein. This approval is only for the engineering data. It indicates the data listed above demonstrates compliance only with the regulations specified by paragraph and subparagraph listed below as "Applicable Requirements? 2) This form constitutes FAA approval of all the engineering data necessary for substantiation of compliance to necessary requirements for the entire alteration. B. PURPOSE OF DATA. Engineering data in support of major alteration to Hawker Beechcraft 400A, S/N RK-244. 9. APPLICABLE REQUIREMENTS (Ust specific sections) PROT545 Title 14 Part 25.301[25-23], 25.303[25-23], 25.305(a)(b)(c)[25-23], 25.307(a)125-231, 25.562(c)[25-231, 25.601[25-00], 25.603(a)(b)(c)[25-38], 25.605(a)[25-00], 25.607[25-23], 25.609(a)(b)[25-00], 25.611[25-23), 25.613(a)(b)(c)[25-00], 25.619[25-23], 25.625(a)(b)(c)(25-23], and 25.789[25-32]. 10. CERTIFICATION - Under authority vested by direction of the Administrator and in accordance with conditions and limitations of appointment under 14 PROT546 Part 183. data listed above and on attached sheets numbered N/A , have been examined in accordance with established procedures and found to comply with applicable requirements of the Airworthiness Standards Listed. 0 Recommend approval of these data 0 Approve these data 11. SIGNATURE $ OF DESIGNATED ENGINEERING REPRESENTATn/E(S) DERT-410115-CE Structures FAA Form 8110-3 (03.10) SUPERSEDES PREVIOUS EDITION Fie Number H13949.01 Page tof PROT216 PROT217 0 u.s cworwienice TranNonsoan Fetal Aviation Aomiresuation Fool Approved 04/43 No. 21200020 1 traOrau37 INSTRUCTIONS: Print or types. entries. Sec FAR 43.9. FAR 43 Appendix B. and AC 43.91 (or subsequent revision thereof) for instructions and disposition or this form. This report is required by law (49 PROT547. 1421). Fa • i'e to report can result in a OM penally not to exceed S1.000 ror each such violation (Section 901 Federal Aviation Act 1956) 1. Aircraft N493LX Serial No. RK 244 Make Mcdel 400A Series 2. Owner Address (As shown on regisfra bon certificate) Address Crly Slate OH zip 44143-1453 cowry USA 4. Type Repair Alteration Unit Make Model Serial Number AIRFRAME (As descnbed in Item I above) Ill 0 POWERPLANT El K PROPELLER K 0 APPLIANCE Tyco M-sgVactwer e. Kind of Agency Name Address City Cleveland Stale. OH Zip 44143-1453 count USA O U.S. Certificated Mechanit O Manufacturer O Foreign Cenneated Mechanic CB Certificated Repair Station CRS it 25NR667B D. I certify that the repair and/or aileratlon made to the unit(s) identified in item 5 above and described on the reverse or attachments hereto have been made in accordance with the requirements of P rt 43 of the U.S. Federal Aviation Regulations and that the information furnished herein is true and correct to the best of my know: dge. per 14 PROT548 Part 43 K 12/29/2013 App. S Pursuant to the authonty given persons specified below, the unit Identified in item 5 was inspected in the manner prescnbed by the 9 APPROVED 0 REJECTED inspector Manufacturer Departing/Mot Transport BY FM Designee Other tSpeci6r) Certificate or 12/29/2013 CRS # 25NR667B PROT218 PROT219 NOTICE Weight and balance or operating limitation changes shell be entered in the appropriate aircraft record. An alteration must be compatible with all previous alterations to assure continued conformity with the applicable airworthiness requirements. (If more space is required, attach additional sheets. Identify with aircraft nationality and registration mark and date work completed.) N493LX Title : Replace MD-302 with Round Style Standby Gauges 12/29/2013 Date Aircraft with MD302 digit SAM instruments must be reverted back to using round standby gauges until issues are resolved. Modified Instrument Panel ([SSN REDACTED]-14) to allow the installation of the original round standby gauges per drawing NX311-10007-03 Rev A Fabricated round indictor subpanel per drawing NX311-10007-01 Rev B Installed instruments into subpanel and install subpanel into main instrument panel per drawing NX311-10007. See Attached 8110-3 DERT 410115-CE dated November 8, 2013 per Nextant Aerospace EO 1543 Rev D dated October 23, 2013 End FAA Form 337 110.06) PROT220 PROT221 t. DATE November 8, 2013 2. MAKE Corporation 3. MODEL NO. 400A 4. TYPE (Aircraft. Engine. Propeller. efc) Aircraft LIST OF DATA 6 IDENTIFICATION 7 MI E EO 1543 Rev. D October 23, 2013 Replace MD-302 With Round Style Gauges. END-- Notes: below as "Applicable Requirements." 2) This form does not constitute FM approval of all the engineering data necessary for substantiation of compliance to necessary requirements for the entire alteration. The electrical requirements are not included in this approval and require separate approval. a. PURPOSE OF DATA: Engineering data in support of major alteration to Hawker Beechcraft 400A, SIN RK-244. PROT549 Title 14 Part 25.301[25-23), 25.303[25-23], 25.305(a)(b)(c)[25-23], 25.307(a)[25-23], 25.562(c)[25-23], 25.601[25-00), 25.603(a)(b)(c)[25-38], 25.605(a)[25-00), 25.607(25-23], 25.609(a)(b)[25-00], 25.611[25-23], 25.613(a)(b)(c)[25.00], 25.619[25-23], 25.625(a)(b)(c)[25-23], and 25.789[25-32). IC. CERTIFICATION - Under authority Part 183, data listed above and on applicable requirements of the Airworthiness 0 Recommend vested by direction of the Administrator and in accordance with conditions and limitations of appointment under 14 PROT550 attached sheets numbered N!A have been examined in accordance wth estatished procedures and found to comply with Standards Listed. these data )4 Approve i 1. SIGNATURE S OF DESIGNATED ENGINEERING REPRESENTATIVE(S) DERT-410115-CE Structures FAA Form 8110.3 (03-10) SUPERSEDES PREVIOUS EDITION File Number. I413818-01 Paget off PROT222 PROT223 0 U.SOnertrrient of rimironifion Foam Aviation ArtninIstration Fan Marano ENO 2120-ccdo waocco7 I Electronic Tricking Number INSTRUCTIONS: Print or typo ail entries. See FAR 419, FAR 43 Appenox B. and AC 43 9.I (or subseccent ression thereof)or instructions and disposition of this form. This report is required by law (49 PROT551. 1421). Failure to report can result in a civil penalty not to exceed 51.000 for each such violation (Section 901 Federal Aviation Act 1954) 1. Aircraft N493LX Serial No. RK 244 Make Model 400A Series 2. Owner Aram" city Stale. OH 7.0 44143-1453 cvisdry USA 4. Type Repair Alteration Unit Make Model Serial Number 1111 AIRFRAME POWERPLANT PROPELLER II APPLIANCE Typo Vardatheor A. Asiencys Name and Address 8. Kind of Agency Name Address Cry Cleveland Sara. OH iv 44143-1453 Ccuray USA CI U.S. Certificated Mechanic O (Manufacturer 0 CRS # 25N R667B O Certificated MaiMenance Organization D. I certify that the repair arilror alteration made to the unri(S) identified in item 5 above and described on the reverse or attachments hereto have been made in accordance with the requirements of Part 43 of the U.S. Federal Aviation Regulations and that the information per 14 PROT552 Part 43 App. 8 INI 12/29/2013 Pursuant to the authOrity given persons pecilled below. the unit identified in item 5 was inspected in the manner prescribed by the Administrator of the Federal Aviation Administration and is 0 APPROVED K REJECTED 1 Inspector Manufacturer i Person Approved by Canadian DeparUnent of Transport BY FAA Designee Certificate or Designation No 12/29/2013 CRS # 25NR667B FAA Form 337 it 0-06) PROT224 PROT225 NOTICE Weight and balance or operating limitation changes shall be entered in the appropfiate aircraft record. An alteration must be compatible with all previous alterations to assure continued conformity with the applicable airworthiness requirements. (If more space is required, attach additional sheets. Identify with aircraft nationality and registration mark and date work completed.) N493LX Spoiler Linkage Closeout Modification 12/29/2013 Date Modified the Cockpit Floor Close out Panels Part Number: LH 45A30839-7 (Pilots) and Part Number: RH 45A30839-7 ( Co-Pilots) . Installed Nextant Aerospace Closeout Panel Part Number NX532- 1004-1 between these Panels to allow room for the New Throttle Quadrant to fit under the Center Pedestal This Alteration was FAA Approved by FAA DERT-410114-CE using a FAA 8110-3 Dated December 28, 2013 using Nextant Aerospace Engineering Order 1563 Rev. B Dated December 24, 2013 ICA Continue with Normal Hawker Beech Maintenance Manual Inspection Requirements for this Area End FAA Form 337 (lam PROT226 I PROT227 1. DATE December 28, 2013 2. MAKE Corporation 1. MODEL NO. 400A 4. TYPE (Aircraft Engine, Pnopetter. etc.) Aircraft LIST OF DATA 7 TITLE EO 1563 Rev. B December 24, 2013 Spoileron Linkage Closeout Modification. Notes: below as 'Applicable Requirements." 2) This constitutes FAA approval of all the engineering data necessary for substantiation of compliance to necessary requirements for the entire alteration. 8. PURPOSE OF DATA: Engineering data in support of major alteration to Hawker Beechcraft 400A, SIN RK-244. PROT553 Title 14 Part 25.301[25-23], 25.303[25.23), 25.305(a)(b)(c)(25-23J, 25.307(a)(25-23], 25.601[25-00], 25.603(a)(b)(c)[25-381, 25.605(a)(25.00), 25.607[25-231, 25.609(a)(b)[25-00], 25.611(25-23), 25.613(a)(b)(c)[25- 00], 25.619[25-231, and 25.625(a)(b)(c)(25-231. 10. CERTIFICATION • Under authority vested by drection of the Administrator and in accordance with conitions and irmitations of appointment under 14 PROT554 Part 183, data listed above and on attached sheets numbered N/A have been examined in accordance with established procedures and found to comply with applicable requirements of the Airworthiness Standards Listed. K Recommend approval of these data 0 Approve these data 11. SIGNATURE OF DESIGNATED ENGINEERING REPRESENTATIVES) 13. CLASSIFICAT/ON(S) DERT-410115-CE Structures FAA Form 8110-3 (03.10) SUPERSEDES PREVIOUS EDITION Fite Number. H13950-0I Pageioll PROT228 I PROT229 le u S Deeinmem re soopooion Administration IC"' Itte.Orl AO OW No 2120-0020 11/3C/2007 Electronic Tracking' Number INSTRUCTIONS: Print or type a'l entnes See FAR 43.9. FAR 43 Appendix 8. and AC 43.9.1 (or subsequent revision thereof) for instructions and disposition of this form. This report is required by law (49 PROT555. 1421). Failure to report can result In a civil penalty not to exceed 51.000 for each such vitiation (Section 901 Federal Aviation Act 1958) 1. Aircraft N493LX Sena' No. RK 244 Make Model 400A Series 2. Owner Address (As ShOwn on registration certificate) Addre ss City sow. OH tip 441431453 couroy USA 4. Type Repair Alteration Unit Make Model Serial Number CI AIRFRAME K O POWERPLANT O K PROPELLER O O APPLIANCE TIP° Manufactory Nome Address City Cleveland sole OH 21p 44143-1453 cony USA O U.S. Cenificaled Mechanic O Manufacturer II9 Certificated Repair Station CRS # 25NR6676 O Cedaficated Maintenance Organization D. I certify that the repair and/or alteration made to the und(s) identified in dem 5 above and described on the reverse or attachments hereto have been made in accordance with the requirements of Pail 43 of the U.S. Federal Aviation Regulations and that the information per 14 PROT556 Part 43 K 12/29/2013 App. 8 0 in item 5 was iispected in the manner prescribed by the APPROVED O REJECTED Inspector Manufacturer BY Certificate Designation CRS or # 25NR6676 FAA Designee No. 12/29/2013 FAA Form 337 (0046) PROT230 PROT231 NOTICE Weight end balance or operating limitation changes shall be entered in the appropriate aircraft record. An alteration must be compatible with all previous alterations fo assure continued confomety with the applicable airworthiness requirements. (If more space is required, attach additional sheets. Identify with aircraft nationality and registration mark and date work completed.) N493LX Nextant Aerospace Carried out a Repair to the Horizontal Stabilizer Ribs 12/29/2013 Using Nextant Aerospace Kit Part Number NXK-128-6200 Rev B. Dated July16. 2012. The following Ribs were replaced. NXR-45A21112-007 NXR-45A21113-007 NXR-45A21101-021 NXR-45A21116-007 NXR-45A21117-007 Rib - H Stab Cant STA 13.779. Rib - H Stab Cant STA 29.921. Rib - H Stab Cant STA 46.063. Rib - H Stab Cant STA 62.205 Rib - H Stab Cant STA 78.346 The following Ribs were not Replaced as there was not Damaged. NXR128-620020-001 NXR128-620020-002 Date This Kit was FAA Approved by DER-T 410115-CE Structures on an FAA 8110-3. Dated June 12, 2013. Using Nextant Aerospace Engineering Drawing NXR-128-6200 Rev B Dated July 16.2012 END PROT232 PROT233 1. DATE June 12, 2013 2. MAKE Corporation 3. MODEL NO. 400A 4. TYPE (Aircraft, Engine, Propeller, etc) Aircraft Nextant Aeiospace LLC Richmond Heights. Ohio LIST OF DATA 6 IDENTIFICATION 7 TfTLE NXR-128-6200 Rev. B July 16, 2012 NXR-45A21112-007 Rev. C July 13, 2012 NXR-45A21113-007 Rev. B July 13, 2012 NXR-45A21114.007 Rev. B July 13. 2012 NXR-45A21115-007 Rev. C July 13, 2012 NXR-45A21101.021 Rev. A July 19. 2012 NXR-45A21116-007 Rev. B July 13, 2012 NXR-45A21117-007 Rev. B July 13, 2012 Kit - Horizontal Stabilizer Rib Replacement Installation Instructions. Rib - H Stab Cant STA 13.779. Rib - H Stab Cant STA 29.921. Rib - H Stab Cant STA 46.063. Rib - H Stab Cant STA 46.063. Rib Assy - H Stab Cant STA 46.063. Rib - H Stab Cant STA 62.205. Rib - H Stab Cant STA 78.346. e. PURPOSE OF DATA: Engineering data to support repair procedure for Horizontal Stabilizer P/N 45A21002-0121 on Hawker Beechcraft 400A, S/N RK-244. PROT557 Title 14 Part 25.301[25-23], 25.303[25-23), 25.305(a)(b)(c)(25-23), 25.307(a)(25-23), 25.601[25-00], 25.603(a)(b)(c)125-381, 25.605(a)(25-00), 25.607(25-23], 25.609(a)(b)(25-00), 25.611(25-23), 25.613(a)(b)(c)(25- 00), 25.619[25-23], and 25.625(a)(b)(c)(25-23]. 10. CERTIFICATION • Under authority vested by direction of the Administrator and in accordance with conditions and tirnitatians of appointment under 14 PROT558 Part 183, data listed above and on attached sheets numbered .,..2_ have been examined in accordance with established procedures and found to comply mm applicable requirements of the seaworthiness Standards Listed. O Recommend approval of these data 0 Approve these data 1 I. SIGNATURE S OF DESIGNATED ENGINEERING REPRESENTATIVE(S) DERT-410115-CE Structures File Number H13370-01 Page 1 of 2 PROT234 PROT235 1. DATE June 12, 2013 2. MAKE Corporation 3. MODEL NO 400A 4. TYPE (Aircraft Engine, Propetter. etc.) Aircraft Nextant Aerospace LW LIST OF DATA 7 TIT' E Notes: 1) The structural aspects only of the above listed data is only for the engineering data. It indicates the data compliance only with the regulations specified by below as 'Applicable Requirements' 2) This form constitutes FM approval of all the engineering substantiation of compliance to necessary requirements herein. This approval demonstrates and subparagraph listed necessary for entire repair. are approved listed above paragraph data for the 8. PURPOSE OF DATA: Engineering data to support repair procedure for Horizontal Stabilizer P/N 45A21002-0121 on Hawker Beechcraft 400A, S/N RK-244. 0. APPLICABLE REQUIREMENTS (List spectic sections) PROT559 Title 14 Part 25.301(25-23], 25.303[25-23), 25.305(a)(b)(c)[25-23), 25.307(a)[25.23], 25.601[25-00], 25.603(a)(b)(c)[25-38), 25.605(a)(25.00], 25.607[25-23], 25.609(O1:0[25-00], 25.611(25-23), 25.613(a)(b)(c)[25- 00], 25.619[25-23], and 25.625(a)(b)(c)[25-23). 10. CERTIFICATION • Under authority Part 163. data listed above and on applicable requirements of the Airworthiness vested by direction of the Administrator and in accordance with conditions and 5mitations of appointment under 14 PROT560 attached sheets numbered ...7,_ have been examined in accordance wdh established procedures and found to comply mlh Standards Usted. these data Recommend i, Approve It. SIGNATURES OF DESIGNATED ENGINEERING REPRESENTATIVE(S) 12. DESIGNATION NUMBERSIS) 13 CLASSIFICATION(S) DERT-410115-CE Structures FAA Form 8110.3 (03-10) SUPERSEDES PREVIOUS EDITION File Number 1113370.01 Page 2 of 2 PROT236 I PROT237 0 he ovolownot Form APProved 11M0f2007 Timmy/woo Federal Ai/1HW Adrairdallntkia INSTRUCTIONS: Print or type all entries. See FAR 43.9 FAR 43 Appendix B, and AC 43.9.1 (or subsequent revision thereof) for instructions and disposition of this form. This report is required by law (49 PROT561. 1421). Failure to report can result In a civil penalty not to exceed 31,000 for each such 10latiOn (Salon 901 Federal Aviation Act 1958) N493LX Serial No. RK244 1. Aircraft Make Model 400A Series 2. Owner Name (As shown on registration cerfrfiCate) Flight Options, LLC Address As shown on registration certificate cayRichmond Heights swoOhio zo44143-1453 ecitritryUSA 4. Type Repar Alteration Unit Make Model Serial Number 1 AIRFRAME POWERPLANT O PROPELLER K 0 APPLIANCE Trim Menulectirer IL Conformity Statement B. K rid of Agency rwooConstant Aviation Add. cisCleveland swoOhio O U.S. Certificated Mechanic O I Manufacturer El Certificated Repair Station CRS#WC7R346J [ADDRESS REDACTED]ates D. I certify that the repair and/or alteration made to the wit(s) identified in item 5 above and described on the reverse or attachments hereto have been made in accordance with the requirements of Part 43 of the U.S. Federal Anabon Regulations and that the information furnished herein is true and correct to the best of m per 14 PROT562 Part 43 K Date: December 30, 2013 App. 8 to Service Pursuant to the authority given pe sons specified below, the unit identi irl ed in item S was Inspected in the manner prescribed by the APPROVED K REJECTED FM Fit Standards Inspector Manufacturer Maintenance Orgarizatica BY FM Designee X Repair Staten Certificate or CRS#WC7R346J Signature/Date • Date: December 30 , 2013 FAA Form 337 (lo-os) PROT238 NOTICE Weight and balance or operating limitation changes shall be entered in the appropriate aircraft record. An alteration must be compatible with all previous alterations to assure continued conformity with the applicable airworthiness requirements. (If more space is required, attach additional sheets. Identify with aircraft nationality and registration mark and date work completed.) N493LX 12130/2013 Date ACCOMPLISHED INTERIOR REFURBISHMENT/MODIFICATION AND 3 PLACE DIVAN INSTALLATION THE FOLLOWING AIRCRAFT INTERIOR ITEMS HAVE BEEN REFURBISHED: Repainted, recovered control Ocrumns with Matte Black Leather Accordance with Beechjet 400A AMM 20-70-00.701, 25-00430-001 Removed and Replaced Glare sHeld and Eyebrow panel material with Matte Black Leathern Accordance with Beechjet 400A AMM 20.60.00.201 Removed and Replaced Cor-kpl Sidewise material with Matte Black Leather in Accordance with Beechjet 400A AMM 20-60-00-201. Removed and replaced Pilot Seat Pan Number TABHIOOPM0001 Serial Number 62, Foam and recovered with Garrett Sheepskin Oak and Excel' Cappuccino Leather. Removed and replaced Co-Pilot Seat Part Number TABH100CM00-01 Serial Number 248. Foam and recovered with Garrett Sheepskin Oak and Excel' Cappuccino Leather. Removed and Replaced Lett Hard /Xs Passenger Seat Part Number 2524-014(-530A) Serial Number 990719.4 Foam and recovered with Townsend Leather Removed and replaced Right Hand #5 Passenger Seat Pan Number 2524.014(4308) Serial Number 990426-7 Foam and recovered with Townsend LeaMer(Hertlage Brown) Removed and Replaced Left Hand 88 Passenger Seat Part Number 2524-014(530B)Serial Number 030818-6 Foam and recovered with Townsend Leather Removed and replaced Right Hand *7 Passenger Seat Pal Number 2524-014(530A) Serial Number 030708-2 Foam and recovered with Townsend Loather (lenlage Brown) THE FOLLOWING MANUALS AND APPROVED DATA HAVE BEEN UTILIZED FOR BASIS OF REFURBISHMENT: Skandia Flammability Test S254978 as approved by FAA DER Jane Biberstein (DERV 832780-CE) on FM form 8110-3 dated 412312013. Flame Out Flammability Test 4311 as approved by FM DER Herb Reed II (GERT-230293-CE) on FM Form 8110-3 dated 12/23/2013. Skandia Flammabitly Test Report TP 22681 Rev A as approved by FM DER Jane Biberstein( DERV-832780-CE) on FM Form 8110-3 dated 05/02/2013. Three Place Divan installation: Installed (3) place divan part Number 32-0396(A6OPT)7123.K02 S/N 003702 In Accordance with Aviation Fabricators STCIST01572VVI and Skandia FlammiNity test report 5254976 per Jane Biberstein FM DER (DERY-832780-CE) dated 4/23-2013 THE FOLLOWING INTERIOR ITEMS HAVE BEEN MODIFIED: LM Gaily Assy. FUH Galley Assy, Divan Assy. LIM Galley Assy and Install per Delta G drawing OGO-CA01-101 Rev 0, DGD-CA01-101 E0 E-1, UH Galley Install DGD.CA01-501 Rev EO A-1, DGD-CA01-501 Rev IR as approved on FM form 8110-3 per FM DER Donald Mimeo (DERT-750t35-SW) dated March 25 2013. RM Galley Assy and Install per Delta G drawings DGD-CA02.101 Rev 8, DGD-CA02-501 Rev IR as approved on FM form 8110-3 by FM DER Donald Gillespie (DERT-750135SW) dated March 25. 2013, Divan Any per Delta G draynngs DGD-CA09.101 Rev C and OGOGA09-101 E0 D-1 as approved on FM form 6110-3 per FM DER Donald Gillespie (DERT 750135-SW) dated March 25, 2013, Bonner Kit Sideway assy drawing 2553-0036 Rev C, Bonner Sideledge assy drawing 2532-0002 Rev C, Bonner Kit Foldout Table assy «manes 2553.0041 Rev C and 2553-0040 Rev B. Bonner XTI liner Kit knit drawing 2553.0037 Rev C as approved on FM form 8110-3 per Stephen Forness DERT-230238-CE dated Dec 26. 2013. INSTRUCTIONS FOR CONTINUED AIRWORTHINESS: THE REMOVAL OF THE INTERIOR IS ON THE CONDITION OF FAILURE. THERE ME NO ADDITIONAL INSPECTIONS REQUIRED. CONTINUE TO INSPECT lAW MANUFACTURERS ANN, SRM, OR CMM AS APPLICABLE AIRCRAFT EQUIPMENT LIST AND WEIGHT AND BALANCE WERE UPDATED BY THE CUSTOMER END - El Additional Sheets Are Attached PROT239 STATEMENT OF COMPLIANCE Willi THE FEDERAL AVIATION REGULATIONS DATE Dec 26, 2013 MAKE Beechcrall Corporation MODEL 400A TYPE (Airplane. Radio. Helicopter. etc.) AIRPLANE NAME OF APPLICANT NEXTANT Aerospace Cleveland OH. LIST OF DATA IDENTIFICAITON TITLE REPORT: BEECHJET 400A INTERIOR STRUCTURAL SUBSTANTIATION BEECHJET 400A XTI LINER KIT INSTL. Beechjet 400A, Aircraft Serial No. R K-244 Certification Bases for this aircraft modification is per Type Certificate Number Al 6SW Revision 28 dated April 12,2013 RKG3282 Rev. IR, 8-28-2013 2553-0037 Rev C, dated 8.30.2013 PURPOSE OF DATA DESCRIBE AND SHOW VERIFICATIONS FOR NEXTANT INTERIOR INSTALLATION ON BEECRIET 400A, AIRCRAFT SERIAL NO. RK-244 APPLICABLE REQUIREMENTS ( Ust specific sections) 14 PROT563 Part 25 §.301, 303, 305, 307a), 365, 561, 571, 601, 603, 605, 609.613 CERTIFICATION - Under authority of appointment under Part 183 of have been vested by direction of the Administrator and in accordance with conditions the Federal Aviation Regulations, data listed above and on attached sheets examined in accordance with established procedures and found to comply Regulations. Approve these data and limitations numbered with applicable requirements of the Federal Aviation l(11AB Therefore Recommend H SIGNATURE(S) Or DI s IGNATED ENGINEERING REPRESENTATIVE(S) DESIGNATION NUMBER(S) CLASSIFICATION(S) DERT-230238-CE STRUCR/RES AND DAMAGE TOLERANCE FAA Form 8110-3 (I I.70j surrasmrs PREVIOUS EDITION GPO 901 • 61) PROT240 PROT241 products engineering services, inc. STRUCTURAL ANALYSIS REPORT Forward Calley Cabinet Modifications - Beechcraft Model 400A, RK-244 & RK-305 Document No: 313-ST-001 Revision IR PREPARED BY: Date: December 24, 2013 APPROVED BY: APPROVED BY: Manager - Design Engineering President THIS DOCUMENT CONTAINS INFORMATION OF A PROPRIETARY NATURE AND SHALL NOT BE TRANSMITTED, REVEALED, OR DISCLOSED TO ANYONE WITHOUT THE EXPRESS WRITTEN PERMISSION OF LEE PRODUCTS ENGINEERING SERVICES, INC. ADDITIONALLY, USE OF THE INFORMATION IS PROHIBITED EXCEPT WHEN EXPRESSLY AUTHORIZED BY LEE PRODUCTS ENGINEERING SERVICES, INC. PROT242 Lee Products Engineering Services, Inc. 313-ST-001 REV. IR PAGE ii REVISION RECORD Revision Date Description Approval IR 12/24/13 Initial Release See Cover Sheet PROT243 313-ST-001 REV. IR PAGE iii 1. INTRODUCTION 1 2. REFERENCES 2 2.1 CONSTANT AVIATION DRAWINGS 2 2.2 APPLICABLE SUPPLIER DRAWINGS (AVIATION FABRICATORS) 2 2.3 APPLICABLE LPESI REPORTS 2 2.4 APPLICABLE GOVERNMENT DOCUMENTS 2 3. CERTIFICATION BASIS 2 4. DESCRIPTION 3 4.1 GENERAL 3 4.2 RH FORWARD GALLEY ASSY & INSTL 3 4.3 RH FORWARD DIVAN MODIFICATION 4 4.4 LH FORWARD GALLEY ASSY & INSTL 5 4.5 LH AFT LAVATORY EXTENSION 7 5. STRUCTURAL SUBSTANTIATION 7 5.1 LH FORWARD GALLEY ASSY & INSTL 7 6. CONCLUSION 8 APPENDIX A A.1 PROT244 313-ST-001 REV. IR PAGE 1 1. INTRODUCTION The purpose of this report is to demonstrate the structural substantiation to applicable 14 PROT564 Part 25 regulations as they relate to the installation and modification of various interior cabinets on Beechcraft Model 400A, S/N's RK- 244 and RK-305, for a FAA Form 337 major alteration, performed by Constant Aviation at their Cleveland, OH facility. The installations consist of the replacement of new RH and LH forward galleys, and modification to the existing closet frame, an extension of the aft lavatory, and a modification to the side-facing divan with the manufacturer's approval. Everything except the new LH forward galley has been accomplished on a previous modification as documented in LPESI Report 222-ST-001. Therefore, only the new galley will be discussed and analyzed in this report. The floorplan for the two (2) Beechcraft Model 400A aircraft is as shown below. s• VA P• way nom to. I IIVX ISM II CO Figure 1-1 - Floorplan RIO PROT245 313-ST-001 REV. IR PAGE 2 2. REFERENCES 2.1 Constant Aviation Drawings ,v Drawing Np. Rev. Title NXT0213-01 IR LH Galley Assembly NXT0213-02 IR LH Galley Installation NXT0213-05 IR Weight Placard Installation NXT0313-01 IR RH Galley Assembly NXT0313-02 IR RH Galley Installation NXT0313-03 IR Divan Assembly NXT0313-07 IR 4" Lay Ext 2.2 Applicable Supplier Drawings (Aviation Fabricators) Drawipg ri9. Rev. . Titla. D-10666 A 3 Place Divan Installation (STC ST01572WI) 2.3 Applicable LPESI Reports Drawing itch . iNvi Titlp 222-ST-001 B Miscellaneous Cabinet Modifications - Beechcraft Model 400A 2.4 Applicable Government Documents Document. ,,:,.R64,:. i, Titi#, . .i: ‹ , 14 PROT565 Part 25 See Sect. 3 Airworthiness Standards: Transport Category Airplanes ANM-115-09-017 1/28/10 Interaction of Interior Structures, Including Seats 3. CERTIFICATION BASIS The Beechcraft Model 400A certification basis is defined Type Certificate Data Sheet (TCDS) A16SW, Rev. 28, the Certification Basis is 14 PROT566 Part 25 dated February 1, 1965, including Amendments 25-1 through 25-40. The individual 14 PROT567 Part 25 subparagraphs that will be discussed herein are: 25.301(a)(b)(c) Loads (Amdt. 25-23) 25.303 Factors of Safety (Amdt. 25-23) 25.305(a)(b) Strength and Deformation (25-23) 25.307(a) Proof of Structure (Amdt. 25-23) PROT246 313-ST-001 REV. IR PAGE 3 25.341(c) 25.561(a)(b)(c) 25.601 25.603(a)(b) 25.605 25.607(a)(b) 25.609(a)(b) 25.613(a-e) 25.625(a)(b)(c) 25.787(a)(b) 25.789 4. DESCRIPTION Gust Loads (No Amdt.) Emergency Landing Loads - General (Amdt 25-23) Design and Construction - General (No Amdt.) Materials and Workmanship (Amdt. 25-38) Fabrication Methods (No Amdt.) Fasteners (Amdt. 25-23) Protection of Structure (No Amdt.) Materials Strength Properties ... (No Amdt.) Fitting Factors (Amdt. 25-23) Stowage Compartments (Amdt. 25-38) Retention of Items of Mass ... (Amdt. 25-32) 4.1 General The modification of the Model 400A aircraft consists of replacing the existing RH and LH forward cabinets with new assemblies, modifying the RH forward 3- place side-facing divan by refurbing the divan, and modifying the existing LH aft lavatory cabinet by extending its cabinet structure to close out the area around it. All but the new LH galley are previously installed and certified on previous 400A aircraft, and analyzed in LPESI Report 222-ST-001. 4.2 RH Forward Galley Assy & Instl The NXT0313-01 RH forward galley assembly (installed per NXT0313-02) is the same as that previously installed on other Model 400A aircraft. An illustration of the galley in Figure 4-1. PROT247 313-ST-001 REV. IR PAGE 4 Figure 4-1 - RH Forward GalleyAssy (Contact Pad on Upper Area Not Shown) The galley is manufactured from strong lightweight 0.50-inch thick ATR-FP- 501F2 Nomex/fiberglass composite panels from AAR Composites, and fabricated using ATR panel pin construction. The RH forward galley is installed between the existing RH forward structural partition (which separates the flight deck with the cabin) forward of it and the 3-place side-facing divan immediately aft of it. The lower wider section of the cabinet also encloses the aircraft's air conditioning evaporator mounted separately to the floor structure underneath. 4.3 RH Forward Divan Modification The NXT0313-03 3-place side-facing divan assembly consists of new drawer and fascia door panels onto the existing structural divan frame (Aviation Fabricators D-10666 STC'd Installation Kit - STC ST01572WI). It has also been installed in previous Model 400A aircraft, and analyzed in LPESI Report 222-ST-001. An illustration of the divan assembly is provided in Figure 4-2. PROT248 313-5T-001 REV. IR PAGE 5 Figure 4-2 - RH Forward Divan Mod The divan closeout panels are manufactured from strong lightweight 0.50- inch thick ATR-FP-501F2 Nomex/fiberglass composite panels from AAR Composites, and fabricated using ATR panel pin construction. The STC'd divan frame installation consists of a structural frame (bottom only - no seat backs, cushions form the divan backs), restraint systems consisting of lap belts and shoulder harnesses for all three (3) seated positions, and a D-106699 floorboard modification installation underneath the divan. The frame installed in eight (8) places into the existing cabinet "Brownline" seat track extrusions (inboard and outboard). 4.4 LH Forward Galley Assy & instl The NXT0213-01 LH forward galley assembly is a traditional aircraft galley and is located between the flight deck and the entry door, directly aft of the existing LH forward structural partition (bulkhead). The new galley replaces an existing galley of similar design and the same size. In fact, this new galley assembly is the same as previously installed in other Model 400A aircraft, and analyzed in LPESI Report 222-ST-001, except for a minor change to the upper forward portion of the cabinet. As can be seen in a comparison of the galley illustrations below and Fig. 4-3 of 222-ST- 001, the change consists of eliminating the small recessed condiment tray drawer and extending (down) the existing compartment to compensate. The galley is manufactured from strong lightweight 0.50-inch thick ATR-FP- 501F2 Nomex/fiberglass composite panels from AAR Composites, and fabricated using ATR panel pin construction. An illustration of the LH forward galley is provided in Figure 4-3. PROT249 I 313-ST-001 REV. IR PAGE 6 Figure 4-3 - LH Forward Galley Assy The LH forward galley is installed per NXT0213-02 and is installed utilizing the same existing installation attachments - five (5) screw/insert attachments into the existing partition and four (4) floor attachments (2 into the existing seat track and 2 into existing floorboard mounts, and is the same as the previous NXT0313-05 installation analyzed in LPESI Report 222-ST-001. The empty cabinet weights 86.15 pounds (less than the 90.61 pound galley analyzed in LPESI Report 222-ST-001) and the total placarded content weight (Ref. NXT0213-05) of 141.0 pounds (only 1.0 pound more than the 222-ST-001 analyzed galley). Therefore, the total installation weight of the NXT0213-02 galley is 3.46 pounds lighter than that analyzed in LPESI Report 222-ST-001, and is therefore structurally substantiated by comparison. PROT250 313-ST-001 REV. IR PAGE 7 4.5 LH Aft Lavatory Extension The NXT0313-07 LH aft lavatory modification consists of augmenting the toilet cabinet with new panels and compartments between the existing cabinet and the RH aft partition. An illustration of the modification to the aft lavatory is shown in Figure 4-4 (new components in gray). , --7.-z it:Z-7XL It tl FWD Mgr Figure 4-4 - LH Aft Lavatory Extension This is the same as previously analyzed in LPESI Report 222-ST-001. 5. STRUCTURAL SUBSTANTIATION The structural analysis will be generated using traditional means based on conservative assumptions. In determining the Margin of Safety (MS), the resulting analytical result will be subtracted from 1.0 so that any MS greater than 0.0 is considered a positive margin. Also, MS's greater than 3.0 will be listed as "+Ample". 5.1 LH Forward Galley Assy & Instl The critical loadings for the LH forward galley are the 9.0g forward and 3.5g side load conditions. However, since the new galley weighs 3.5 pounds less than the previously analyzed galley, is of similar shape and design, includes that same installed equipment, and utilizing the same aircraft attachment points, the new galley assembly and installation is therefore structural substantiated by comparison. PROT251 313-ST-001 REV. IR PAGE 8 The largest placarded drawer is the top, center drawer in the lower section of the galley, which is placarded for 45.0 pounds. The drawer is restrained by a standard Actron paddle latch, P/N A23511-1S. The applied load to the latch is (the drawer itself + hardware is 5.0 pounds): Applied Load = (5.0 lbs + 45.0 Ibs) x 3.5g x 1.15ff = 201.3 pounds The minimum load rating for the A23511 paddle latch by its manufacturer is 225.0 pounds. The resulting margin of safety is: M.S. = 225.0 lbs / 201.3 Ibs) - 1.0 = +0.12 6. CONCLUSION Based on the above structural analysis, the new cabinets and modification and their installations, listed in Sect. 2.1, into the aircraft have been shown to be compliant with the applicable 14 PROT568 Part 25 regulations, as defined in Sect. 3 with positive margins of safety. PROT252 D C B A 4 3 2 ba Weed, Oaten(' • OWSOITSOCOOn osoOpyry /it Oaten Pa met) Oftmermo wan covelannla Imailtatoe, gat •Oneirtil 4211041.4vOltarano wan, Su, Si MO Sal fl tt O. OMIT .00.1.C. A f at RR lWeiaw ,O4T m2041,149 4' IV RN Ople u A vitt hit° n. sorrow of uomm O male. Px,vows now as to WRAC! OP Oa I* 0 ,11.0401000 ft wnall Mitt /0 Lai O• sceerAMINITSINSOOVAN.,4114CaiK 61 taibic ramighwa Mat Oat la NIL •••0.CCIRO dthi %Welt% s Si PMTS. trilats3 Marl' 00.? • OD rSO .OtanSeli .0.0•04 on elin.ot flange. ...Gia✓ Nat 04.1.1 COMO worts nt man Ontala STOMP 1.73 B.. ito s1 I - .9381101 - ]A 1.50 A 2'3511 004 Oda ITN O 0001:04•009 Ott @deaf* 0-12 100. ten a OLCS.ORTIP .301 SAM POT laXONOL5 A23511 .3 $ BASIC PART 511.0905R A 2951$ 39040. .00 X 94 th• .20 ROT nal A nsie lams aose ad A ISM son Nuo 0.40 not WOWS .4••• DASH Na A oat noos Beata 1 .44 45' 41* .5 45- .7 .13 NONE • 9 .75 45' Oa BOLT IIATCRIAL LETTER 9 41904.599. NO e ewe enemewei =1- =0, I %S Henn:- ate C I *23510 seed() It 4.4•.TolIGHANAVICA Rom) ••••••• MOTO3 UST 091/4TEALIt 1.1100. WA, AST - .CATION 10.11. - W S a n e l s PS. of Oat if 00 SOY OCAS •Orr rem an-cosh. Inman a-weans to SNOOP .00, eleC• MIS are 4••••• t Iwo. HIM palm. 2 tam LATCH :78;;: ft 7 : 1::are k ASS'Y. A23 511 SMOGS 4 3 1 A V XIIN3ddV PROT253 U. S. DEPARTMENT OF TRANSPORTATION - t.DA it 4/23/2013 STATEMENT Of COMPLIANCE WITH AIRWORTHINESS STANDARDS 2.MAKE Raytheon S.MODEL NO. 400A 4.TyPE(4SPIAFt. Engintt Propeler. eta) Airplane 5.NAME OF APPLICANT Constant Aviation-CLM LIST OF DATA 6.IDENTIFICATION 7,TITLE Design Data 5254976 Rev NC Skandia, Inc. Flammability. Bunsen Burner Testing Test Specimen P/N's Cont. 25 (represents main entry 27 (represents upper med 28 (represents lower med, 29 (represents pax seat back 30 (represents'seat shrouds) 31 (represents entry Steps, 33 (represents cntrt coltimn 34 (repreientsckpt defog 35 (represents table shrouds) 36 (represents dado and aircelltloSeout) 39 (represents crew seats) Notes: 1) Work accomplished under 2) Flammability tettimitnessing 3) IAW Skandia. Flammability.Streamfine Test Results door trim) surround) lower.Med surround, lh aft blkhd) shrouds, arms, crash pad) cockpit ped step) boots, rudder boots) vent closeout) Skandia Inc. WO # /54976-13, Ref Document ID 9365(). only, does not constitute installation approval of materials. Testing Test Plan 21306, Rev IR, Dated 11/03/11 Page 2 8,PURPOSE OF DATA Demonstration of Compliance with material flammability regtilrenients for S/NRK;244 Q.APPLICAEILE REQUIREMENTS (Llsl specific sections) 14 PROT569 .Pert 25:853(a) Arndt 25-116 Appendix F Patti (a)(1)(6 14 PROT570 Pert 25.853 (a)Amdt 25,116 ApPenflixF Part I (p)(1) (ii) 14 PROT571 Part 25.855 (d).8met 25-118 Appendix F Part I (6) Amdt 25-111 10.CERTIFICATION. under authority vested by direction of the of appointment under 14 PROT572 Part 183, data listed above and examined In accordance with established protedures and found Standards listed.. 0 Recommend approval of these data E.w.: Approve these data Administrator snd in accordance withrOnditione and 5i-ribbons on attached sheets numbered I - -1 - have been to comply with appliCable requirement's of the AinmorthlRess 11.SIGNATURE(S) OF DESIGNATED ENGINEERING REPRESENTATIVE %DESIGNATION NUMBER(S) 13.CLASSIFICATION(S) DERV-832780-CE' Structural Special FAA - Form 8110-3 COMO-SUPERSEDES PREVIOUS. EDITION PROT254 I i PROT255 FEDERAL AVIATION ADMNISTRATION 1. DATE March 25, 2013 2. MAKE Beechjet 3. MOOD- NO. 400A 4. TYPE ~ant Rathq tiolicopfix etc) AIRPLANE UST OF DATA B. IDENTIFICATION 7 ITTI F Document No. DGD-CA08-501 REV: IR Dated: 6/13/12 DGD-CA09.101 REV; C Dated: 1/25113 OGD-CA09-101 EO: D-1 Dated: 2/28/13 DGD-CA13-101 REV: IR Dated: 2/28/13 DGD-CA14-101 REV: IR Dated: 1/31/13 ARMREST RH INSTL DIVAN ASSY DIVAN ASSY CARD TABLE ASSY LAV CLOSET FRAME End of Data NOTES: MOD is for Beechjet model 400A (Nextant 400XT variant) SIN RK-244 only. is for the structural design aspects only on the above listed date and an Installation approval. only for regulations specified in the "Applicable Requirements" block. with additional regulations not listed herein may be required. This form FAA approval of all engineering design data for the entire Additional 8110-3 approvals may be necessary for Damage Tolerance, Mechanical Systeme, Electrical, Weight & Balance, as well as other basis, refer to TC data sheet No. Al 6SW Approvals are provided separately. 1. This approval 2. This approval does not constitute 3. Approval is Compliance alteration. Flammability, disciplines. 4. For certification 5. Structural 8. PURPOSE OF DATA To provide type data fo FAA approval of structure in support of a return to service on S/N RK•244. This approval is for design data only on a major alteration and is not an Installation approval. 14 PROT573 Part 25.601 Amdt 25-0, 25.603(a)(b), Amdt 25-38, 25.605 Amdt 25-0, 25.609 Amdt 25-0, 25.611, Amdt 25-23, 25.613 (1)(b)(c) Amdt 25-0, 25.619 Amdt 25-23, 25.625 Amdt 25-23, 25.785 (s)(6)(rXdXeX1) Amdt 25-32, 25.789 Amdt 25.32 Pad 183, data Mod above and with applicable requirements of the K Recommend vested by Erection of on attached sheets numbered Aknorthiness Standards approval of teem Mese data the Administrator N/A have and In acc0rdenCe with conditions and limitations of appointment urger 14 PROT574 been examined In accordance with established procedures and found to comply Listed. data 0 Approve !IlaPRESENTATIVE(S) 12. DESIGNATION NUIABERDIS) 13. Ct scSIFICATION(S) DERT-750135-SW STRUCTURAL FM Form 8110-3 (03n o)SuPERSEDES PREVIOUS EDITION PROT256 PROT257 13DLG-CON-0325E 1. DATE March 25, 2013 2. MAKE Beechjet 3. MODEL NO. 4OOA 4. TYPE (AI/plane, Rs:No, HeScepter, at' AIRPLANE LIST OF DATA 0 IDENTIFICATION 7 TITI F Document No. DGD-CA01-SS-07 REV: IR Dated: 3/6/13 SUBSTANTIATION ANALYSIS ---------- End of Data NOTES: of the Intenor on an Hawker Boochcratt 400A Aircraft Is for Beechiet model 40DA (Nextant 400XT variant) SIN RK-244 only. Is for the structural design aspects only on the above listed data and an installation approval. only for regulations specified In the "Applicable Requirements" block. with additional regulations not listed herein may be required. This form FAA approval of all engineering design data for the entire Additional 8110.3 approvals may be necessary for Damage Tolerance, Mechanical Systems, Electrical, Weight & Balance, as well as other basis, refer to TC data sheet No. A18SW 1. This approval 2. This approval 3. Approval is Compliance alteration. Flammability, disciplines. 4. For certification B. PURPOSE OF DATA Structural substantiation In support of FAA Form 337 for aircraft SIN RK-244. This approval is for design data only on a major alteration and is not an Installation approval. 9. APPLICABLE REQUIREMENTS Wit speck sections) 14 PROT575 Pert 25.30I(Amdt. 25-23), .303IAmdt. 25-23),...30S(s)(b)LAmdt. ES-23)..307lAmdt 25-231,.34t (Arndt. 25-0), .361 'Arndt. 25-231, .6011Amdt.25-01, .603(eXb)lArndt.25-381,.605lAmdt.23-01,.609[Arndt.23-0],.611fAmdt.25-231,.613(eXbXc)lAmdl.2S-Ob.625 'Arndt. 25- 23], .785(O(bXc)(d)(e)(BlAmdt. 25-32), .78700iAmdt 25-32),.789lAmdt. 25,32] Part 183, data listed above and with aPPlicable requkemertS Ot the vested by direction on attached sheets numbered Any:tininess Standards approval of these these dee of the Administrator NA have and In accordance with conditions end Inflations of appointment under 14 PROT576 been examined in accordance with established procedures and found to comply Listed. date Recommend g.i Approve !I'M, ENTATIvE(S) 12. DESIGNATIoN NUmBERS(S) 13. CLASSIFICATIONS1 DERT-75O135-SW STRUCTURAL FAA Form 8110-3 (mate SUPERSEDES PREVIOUS EDITION PROT258 PROT259 13DLG-CON-0325B V.S. DEPARTMENT OF TRANSPORTATION FEDERAL AVIATION ADIANISTRATION 1. DATE March 25, 2013 2. MAKE Beechjet 3. MODEL NO. 400A 4. TYPE (Aaptano. Radio, Itkopter. ac) AIRPLANE UST OF DATA 6 IDFNTIFICATION 7 TITLE Document No. DGD-CA02.1O1 REV: B Dated: 1(25/13 DGD-CA02-501 REV: IR Dated: 6/13/12 DGD-CA13-501 REV: IR Dated: 12/21/12 DGD-CA13-501 £0: A-1 Dated: 2/28/12 DGD-CA04.1O1 REV: IR Dated: 6/13/12 RH GALLEY ASSY RH GALLEY INSTL CARD TABLE INSTL CARD TABLE INSTL SIDE LEDGE ASSY End of Data NOTES: is for Beechjet model 400A (Nextant 400XT variant) S/N RK-244 only. is for the structural design aspects only on the above fisted data and an Installation approval. only for regulations specified In the "Applicable Requirements" block. with additional regulations not listed herein may be required. This form FAA approval of all engineering design data for the entire Additional 81104 approvals may be necessary for Damage Tolerance, Mechanical Systems, Electrical, Weight & Balance, as well as other basis, refer to TC data sheet No. A165W Approvals are provided separately. 1. This approval 2. This approval 3. Approval le Compliance alteration. Flammability, disciplines. 4. For certification S. Structural 8. PURPOSE OF DATA To provide type data fo FM approval of structure in support of a return to service on S/N RK-244. This approval Is for design data only on a major alteration and is not an Installation approval. 9. AP PLICAI3LE REQUIREMENTS (List spec& sections) 14 PROT577 Part 25.601 Arndt 25-0, 25.603(004, Amdt 25-38, 25.605 Amdt 25-0, 25.609 Arndt 254, 25.6111 Amdt 25.23, 25.613 (a)(b)(c) Amdt 25-0, 25.619 Amdt 25-23, 25.625 Amdt 25-23, 25.785 (a)(bXcXdXeXf) Amdt 25-32,25.789 Amdt 2542 Part 183. date listed Stove and on with applicable requirements of the vested by direction of attached sheets numbered Nninwthiness Standards approval of those these data the Administraior N/A htwo and in ecoontanee vilth condbons and limitations of appointment under 14 PROT578 been examined in accordance with established procedures and found to comply Listed, data U Recommend I (we) Therefore tlif Approve 12. DESIGNATION NUMBERS(S} 13. CLASSIF1CATION(S) !IMISPRESENTATNE(S) DERT-750135-SW STRUCTURAL FM Form 8110-3 (03!10) SUPERSEDES PREVIOUS EDITION PROT260 PROT261 13DLG-CON-0325A U.S. DEPAarruENT OF TRANSPORTATION 1. DATE March 25.2013 2. MAKE Beechjet 3. MODEL NO. 400A 4. TYPE (Afro/amt. R.d Hata( et. oft) AIRPLANE & NAME OF APPLICANT LIST OF DATA 6 TIFNTIFiCATKIN 7 TiTLE Document No. OGD-CA01-101 REV: D Dated: 3/5/13 000-CA01.101 EO: E-1 Dated: 3/6/13 DGD-CA01-501 REV: IR Dated: 6/13/12 CGD-CA01-501 EO: A-1 Dated: 1/29/13 DOD-CA01-501 EO: A-2 Dated: 3/5/13 LH GALLEY ASSY LH GALLEY ASSY LH GALLEY INSTL End of Data NOTES: Is for Beechjet model 400A (Nextant 400XT variant) S/N RK-244 only. is for the structural design aspects only on the above listed data and an Installation approval. onlyfor regulations specified in the "Applicable Requirements" block. with additional regulations not listed herein may be required. This form FAA approval of ail engineering design data for the entire Additional 8110-3 approvals may be necessary for Damage Tolerance, Mechanical Systems, Electrical, Weight & Balance, as well as other basis, refer to TC data sheet No. A16SW Approvals are provided separately. 1. This approval 2. This approval 3. Approval is Compliance alteration. Flammability, disciplines. 4. For certification S. Structural 8. PURPOSE OF DATA To provide type data for FAA approval of structure in support of a return to service on S/N RK-244. This approval Is for design data only on a major alteration and is not an installation approval. 9. APPLICABLE REQUIREMENTS (LIN NAOS marina) 14 PROT579 Part 25.601 Arndt 25-0, 25.603(06), Amdt 25-38, 25.605 Amdt 25-0, 25.609 Amdt 25-0,25.611, Arndt 25-23, 25.613 (a)(bXe) Amdt 25-0, 25.619 Amdt 25-23, 25.625 Arndt 25-23, 25.785 (a)(b)(e)(dXeXf) Amdt 25-32, 25.789 Amdt 25-32 10. CERTIFICATION - Under authenly vested by direction of Pan 183. data 'sled above and on attached sheets numbensd with applicable requiroments of the Airworthiness Standards K Recommend approval al these CE3Approv. these data the Administrator WA have end h accordance with comfit:Ins and Imitations of appointment under 14 PROT580 been examined In accordance with astatoshed procedures and found to tarn* Listed. data 1 U RE OF DESIGNAT D ENGiNEERING REPRESENTATNE(S) 12. DESIGNATION NuMBERS(S) 13. CLASSIFICATION(SI CERT-750135-SW STRUCTURAL FAA Form 81104 (03/10) SUPERSEDES PREVIOUS EDITION PROT262 PROT263 Aviation Fabricators n e Clinton, Missouri 64735 Report # AF-475FTP August 09, 2010 Rev (A) Functional Test Procedure for STC # ST01572W1 Hawker Beechcraft Cabin Configuration Applicable Aircraft Model: Hawker Beechcraft 400, 400A PROT264 Aviation Fabricators. Inc. Clinton, Missou►i 64735 Revision Log AF-475FTP ' 08-0940 Rev (A) Page 2 of 4 Date Rev Pages Description Approved by 08-09-10 A 1 -Added model 400A G.R. Lowe III -Changed data list # to AF-475MDL PROT265 Aviation Fabricators Inc. Clinton, MO. 64735 For Interior Cabin Configurations Document No.: AF-528 Revision "IR" Revision Date: 11121111 Applicable to: Hawker Beechcraft model 400A Modified by FAA STC ST01572WI The information in the Instructions (or Continued Airworthiness is FM accepted material and complies with 14 PROT581 25.1529, Instructions for Continued Airworthiness. It supersedes or adds to that provided in the Maintenance Manual for the Hawker Beechcraft 400A Aircraft, only where covered in the items contained herein. For limitations and procedures not contained in the Supplement, consult the Component Maintenance Manual, or other approved airplane data. Page 1 of 16 PROT266 aRIFABAt AVIATION FABRICATORS Fax Nov 7, 2012 571 * 00-3 70a CERTIFICATE OF CONFORMANCE This certifies that Aviation Fabricators, Divan, 3 Place with stowage provisions, Beechjet, part number, 32-0396(A60P)T1≥3.K-02, serial number, 003702, was manufactured in, or determined to be in conformity to anc with approved design data and is in a condition for safe operation for installation on aircraft. Vice-President Aviation Fabricators • Central Airmotive PROT267 ) REVISION PAGE Document Title: Instructions for Continued Airworthiness Prepared By: Todd Ponue Reviewed By: Jeffrey R. Lowe Updates to the ICA will be made by Aviation Fabricators Inc. Updates will be listed in the log of revisions and the effective pages will be listed below. Log of Revisions REV. NO. EFFECTED PAGE(S) DESCRIPTION DATE APPROVED BY IR All Initial Release 11/21/11 JRL Per the requirement of Appendix H of 14 PROT582 Part 25 paragraph 1-125.1 (c), the changes made to the ICA by the applicant will be distributed via mail by means of paper copy Page 2 of 15 PROT268 1101011 ICA Document No.: AF-528 Revision (IR) Dale: November 21, 2011 DESCRIPTION PAGE REVISION PAGE 2 3 ABBREVIATIONS AND DEFINITIONS 4 1.0 INTRODUCTION 5 2.0 INSPECTION REQUIREMENTS AND OVERHAUL SCHEDULE 9 3.0 DIMENSION AND ACCESS. 11 4.0 LIFTING AND SHORING 11 5.0 LEVELING AND WEIGHING 11 6.0 TOWING AND TAXIING 11 7.0 PARKING AND MOORING 11 8.0 PLACARDS AND MARKINGS 12 9.0 SERVICE INFORMATION 13 10.0 AIRWORTHINESS LIMITATIONS 15 11.0 TROUBLESHOOTING INFORMATION 15 Page 3 of 16 PROT269 1 REVISION PAGE Document Title: Instructions for Continued Airworthiness Prepared By: Reviewed By: Updates to the ICA will be made by Aviation Fabricators Inc. Updates will be listed in the log of revisions and the effective pages will be listed below. Log of Revisions REV. NO. EFFECTED PAGE(S) DESCRIPTION DATE APPROVED BY IR All Initial Release 11/21/11 JRL Per the requirement of Appendix H of 14 PROT583 Part 25 paragraph H25.1 (c), the changes ) made to the ICA by the applicant will be distributed via mail by means of paper copy Page 2 of 15 PROT270 I c. Revision (IR) n on, Date: November 21, 2011 DESCRIPTION PAGE REVISION PAGE 2 3 ABBREVIATIONS AND DEFINITIONS 4 1.0 INTRODUCTION 5 2.0 INSPECTION REQUIREMENTS AND OVERHAUL SCHEDULE 9 3.0 DIMENSION AND ACCESS' 11 4.0 LIFTING AND SHORING 11 5.0 LEVELING AND WEIGHING 11 6.0 TOWING AND TAXIING 11 7.0 PARKING AND MOORING 11 8.0 PLACARDS AND MARKINGS 12 9.0 SERVICE INFORMATION 13 10.0 AIRWORTHINESS LIMITATIONS 15 11.0 TROUBLESHOOTING INFORMATION 15 Page 3 of 16 PROT271 n on, MO. 64735 ABBREVIATIONS AND DEFINITIONS Revision (IR) Abbreviations Definitions AML FAA Approved Model List (AML) Detailed Inspection (DET) An intensive examination of a specific Item, installation or assembly to detect damage, failure or irregularity. Available lighting is normally supplemented with a direct source of good lighting at an Intensity deemed appropriate. Inspection aids such as mirrors, magnifying tenses, etc. may be necessary. Surface cleaning and elaborate access procedures may be required. FAA Federal Aviation Administration FAA MIDO FAA Manufacturing Inspection District Office General Visual Inspection (GVI) A visual examination of an interior or exterior area, installation or assembly to detect obvious damage, failure or irregularity. This level of Inspection Is made from within touching distance unless otherwise specified. A mirror may be necessary to enhance visual access to all exposed surfaces in the Inspection area. This level of inspection is made under normally available lighting conditions such as daylight, hangar lighting, flashlight or droplight and may require removal or opening of access panels or doors. Stands, ladders or platforms may be required to gain proximity to the area being checked. ICA Instructions for Continued Airworthiness Special Detailed Inspection (SDI) An Intensive examination of a specific Item, Installation , or assembly to detect damage, failure or irregularity. The examination is likely to make extensive use of specialized Inspection Techniques and/or equipment. Intricate cleaning and substantial access or disassembly procedure may be required. STC Supplemental Type Certificate Page 4 of 15 PROT272 1.0 INTRODUCTION Revision (IR) The purpose of this Maintenance Manual Supplement and Instructions for Continued Airworthiness (ICA) is to provide the maintenance technician with the information necessary to ensure the continued airworthiness of the Aviation Fabricators cabin configuration, per installation number 400-3, when installed in the aircraft passenger cabin in accordance with Aviation Fabricators design data included on Master Data List AF-475MDL and per Supplement Type Certificate (STC) No. ST01572WI. Modifications to an aircraft obligates the operator to include the maintenance Information provided by this document into the operators aircraft Maintenance Manual and operator's aircraft scheduled maintenance program. This document defines supplementary maintenance operations and frequencies recommended by Aviation Fabricators Inc., to ensure the aircraft's airworthiness. The information contained herein addresses the requirements specified in 14 PROT584 25.1529, Instructions for Continues Airworthiness and supplements the basic Airplane Maintenance Manual only in those areas listed as pertains to the installation of divan assemblies, as installed per the Aviation Fabricator Master Data List AF-475MDL. For limitations and procedures not contained in this supplement, consult the basic Airplane Maintenance Manual. DATA All information to support the continued airworthiness of this modification is contained in: STC ST01572WI. Master Data List: AF-475MDL. Installation: 3 Place Divan (Ref. Installation number 400-3), Installation Instructions D-10666 for P/N 32-0396K-X Parts: P/N 32-0396K-X, 3 Place Divan Installation The new divan assembly (with restraint system) is a self contained complete assembly that mounts to the existing seat track, using standard fittings, in accordance with FAA approved floor plans. The (restraint system) seat belts are attached to the seat track with typical tie down fittings and the inertia reel shoulder harness is bolted to the divan frame on the outboard side using standard aircraft hardware. Design Change Control All data and changes to the parts and assemblies will be tracked per Master Data List AF- 475MDL Rev C or later FM approved revision. Applicable Aircraft Beechjet 400A Page 6 of 16 PROT273 Tinton, MO. 64735 ABBREVIATIONS AND DEFINITIONS Revision (IR) Abbreviations Definitions AML FM Approved Model List (AML) Detailed Inspection (DET) An intensive examination of a specific Item, installation or assembly to detect damage, failure or irregularity. Available lighting is normally supplemented with a direct source of good lighting at an intensity deemed appropriate. Inspection aids such as mirrors, magnifying lenses, etc. may be necessary. Surface cleaning and elaborate access procedures may be required. FM FAA MIDO FM Manufacturing inspection District Office General Visual Inspection (GVI) A visual examination of an interior or exterior area, installation or assembly to detect obvious damage, failure or irregularity. This level of inspection Is made from within touching distance unless otherwise specified. A mirror may be necessary to enhance visual access to all exposed surfaces in the inspection area. This level of Inspection is made under normally available lighting conditions such as daylight, hangar lighting, flashlight or droplight and may require removal or opening of access panels or doors. Stands, ladders or platforms may be required to gain proximity to the area being checked. ICA Instructions for Continued Airworthiness Special Detailed Inspection (SDI) An Intensive examination of a specific item, Installation , or assembly to detect damage, failure or irregularity. The examination is likely to make extensive use of specialized Inspection Techniques and/or equipment. Intricate cleaning and substantial access or disassembly procedure may be required. STC Supplemental Type Certificate Page 4 of 15 PROT274 Revision (IR) Clinton, MO. 1.0 INTRODUCTION The purpose of this Maintenance Manual Supplement and Instructions for Continued Airworthiness (ICA) is to provide the maintenance technician with the information necessary to ensure the continued airworthiness of the Aviation Fabricators cabin configuration, per installation number 400-3, when installed in the aircraft passenger cabin in accordance with Aviation Fabricators design data included on Master Data List AF-475MDL and per Supplement Type Certificate (STC) No. ST01572WI. Modifications to an aircraft obligates the operator to include the maintenance Information provided by this document into the operators aircraft Maintenance Manual and operator's aircraft scheduled maintenance program. This document defines supplementary maintenance operations and frequencies recommended by Aviation Fabricators Inc., to ensure the aircraft's airworthiness. The information contained herein addresses the requirements specified in 14 PROT585 25.1529, Instructions for Continues Airworthiness and supplements the basic Airplane Maintenance Manual only in those areas listed as pertains to the installation of divan assemblies, as installed per the Aviation Fabricator Master Data List AF-475MDL. For limitations and procedures not contained in this supplement, consult the basic Airplane Maintenance Manual. DATA All information to support the continued airworthiness of this modification is contained in: STC ST01572WI. Master Data List: AF-475MDL. Installation: 3 Place Divan (Ref. installation number 400-3), Installation Instructions D-10666 for P/N 32-0396K-X Parts: P/N 32-0396K-X, 3 Place Divan Installation The new divan assembly (with restraint system) is a self contained complete assembly that mounts to the existing seat track, using standard fittings, in accordance with FAA approved floor plans. The (restraint system) seat belts are attached to the seat track with typical tie down fittings and the inertia reel shoulder harness Is bolted to the divan frame on the outboard side using standard aircraft hardware. Design Change Control All data and changes to the parts and assemblies will be tracked per Master Data List AF- 475MOL Rev C or later FAA approved revision. Applicable Aircraft Beechjet 400A Page 5 of 15 PROT275 3 Place Divan P/N 32-0396K-X (Top not shown for clarity) KOT p I falliew nO MOUM If I / II N ...IVA YAW &W intOTIA40 W>C0.101 RR infa INN rani letWOCOITIAMT LOCMOIOISKWIWitatil I nil FOOT ATTACHMENT TO DIVPN rat no A...nova PIX4 NS1nail MINI 'In WC.101/21t Wit* 01 FOOTA1TACWASIT TO TRACK ISO WAIN,11, Figure 1.0A Revision (IR) "War" FOOT AlTPCaCENT ...0 CKWIll WWII" WI Page 6 of 15 PROT276 Inertia Reel Attachment Seat Belt Attachment Figure 1.0C 11.111.11 DIVAN FRAME NUT WASHER INERTIA REEL Figure 1.0B SEAT BELT TIE DOWN FITTING SEAT TRACK REF Revision (IR) BOLT Page 7 of 15 PROT277 3 Place Divan P/N 32-0396K-X (Top not shown for clarity) FOOTATTACHMENT TO DIVAN °err 1.0=Erall FOOT ATTPCHMENr TOTRICK main AUCOrilt TOMMIADAMOICCI >RCS Figure 1.0A Revision (IR) FOOT ATTPV0MTMCKWn4 GAP Page 6 of 15 PROT278 1 1 1 101 11 Inton, . 473 Inertia Reel Attachment Figure 1.0B Seat Belt Attachment Figure 1.0C Revision (IR) Page 7 of 15 PROT279 SEAT BOTTOM ASSEMBLY NALL n on, MO. 84735 auguiousssguiLieugeme Figure 1.0D Revision (IR) Page 8 of 15 PROT280 A ti r r Revision (IR) nton, MO. 64735 2.0 INSPECTION REQUIREMENTS AND OVERHAUL SCHEDULE 1. To comply with14 PROT586 25.1529, continue the new divan assembly (with restraint system) on the same inspection and maintenance schedule used per the Hawker Beechcraft Maintenance Manual for cabin section inspections. a. The new cabin configuration components require no service other than inspection at normal inspection interval of 200 hours. b. The safety belts require no service other than inspection at normal inspection interval of every 200 hours. c. Perform a detailed visual inspection of each passenger seat bottom and back cushions and covering of all cabin interior components to detect apparent or obvious defects or irregularities. On the cushion assembly, check for cracks and punctures within a 4" diameter circle. The cushion assembly can have no more than three defects found within the 4" diameter circle. If a cushion develops a "lump", check to see if there are no more than two lumps within a 4" diameter circle. Any damage to the cushions outside of the described limits will require them to be replaced. Visually inspect the covering assemblies for holes, punctures, and tears. If the damage to the covering is holes smaller than 1/2 " in diameter or a cut at a maximum of 2" in length then the covering is satisfactory. The sewing of the cover assemblies is not to exceed 1" tearing. Any damage to the covering assemblies outside of the described limits will require them to be replaced. d. Visually inspect the divan and seat assembly tubes and diaphragm for cracks and deformation. Damaged conditions could be detected as a crack at the edge of the tube or along the length of the tubes or as a crack, tear or cut found on the seat bottom or back diaphragm. Visually inspect all hardware for excessive wear before and after installation. Replace the seat back and bottom diaphragm if two cracks or deformations are found with a 4" diameter circle. If a tear or cut is found with a maximum of 6", replace the diaphragm. There shall be no broken tubes. There shall be no sharp corners, edges, or protrusions that may Injure passengers. Replace the tubes if they are bent in such a way that they are more than 2" off center. Replace the seat tubes if crack length is found to be .125" or greater. Replace the tube if a dent is found running longer than 3". Replace the seat tubes if deformation is greater than .25" the overall thickness of the tube diameter. Cracked or broken fasteners or fittings are to be replaced with new immediately. Page 9 of 15 PROT281 SEAT BOTTOM ASSEMBLY Clinton, MO. 64736 CUSHION ASSEMBLY REFFRFN0F Figure 1.0D Revision (IR) Page 8 of 16 PROT282 A a r Revision (IR) nton, MO. 4736 2.0 INSPECTION REQUIREMENTS AND OVERHAUL SCHEDULE 1. To comply with14 PROT587 25.1529, continue the new divan assembly (with restraint system) on the same inspection and maintenance schedule used per the Hawker Beechcraft Maintenance Manual for cabin section inspections. a. The new cabin configuration components require no service other than inspection at normal inspection interval of 200 hours. b. The safety belts require no service other than inspection at normal inspection interval of every 200 hours. c. Perform a detailed visual inspection of each passenger seat bottom and back cushions and covering of all cabin interior components to detect apparent or obvious defects or irregularities. On the cushion assembly, check for cracks and punctures within a 4" diameter circle. The cushion assembly can have no more than three defects found within the 4" diameter circle. If a cushion develops a "lump", check to see if there are no more than two lumps within a 4" diameter circle. Any damage to the cushions outside of the described limits will require them to be replaced. Visually inspect the covering assemblies for holes, punctures, and tears. If the damage to the covering is holes smaller than '/Z' in diameter or a cut at a maximum of 2" in length then the covering is satisfactory. The sewing of the cover assemblies is not to exceed 1" tearing. Any damage to the covering assemblies outside of the described limits will require them to be replaced. d. Visually inspect the divan and seat assembly tubes and diaphragm for cracks and deformation. Damaged conditions could be detected as a crack at the edge of the tube or along the length of the tubes or as a crack, tear or cut found on the seat bottom or back diaphragm. Visually inspect all hardware for excessive wear before and after installation. Replace the seat back and bottom diaphragm if two cracks or deformations are found with a 4" diameter circle. If a tear or cut is found with a maximum of 6", replace the diaphragm. There shall be no broken tubes. There shall be no sharp corners, edges, or protrusions that may Injure passengers. Replace the tubes if they are bent in such a way that they are more than 2" off center. Replace the seat tubes if crack length is found to be .125" or greater. Replace the tube if a dent Is found running longer than 3". Replace the seat tubes if deformation is greater than .25" the overall thickness of the tube diameter. Cracked or broken fasteners or fittings are to be replaced with new immediately. Page 9 of 16 PROT283 Revision (IR) For repair or replacement of damaged or broken parts or assemblies contact Aviation Fabricators Inc. 2. Inspection Time Limit for the cabin configuration installations: 200 +1- hour inspection for the new cabin configuration components Task Code Schedule Date Mech Insp AFI-100 a. Inspect for damage to upholstery. AFI-101 b. Inspect safety belts for wear, cuts, fraying, damage, and deterioration. AFI-102 c. Inspect safety belt attachment fittings for wear and damage AFI-103 d. Inspect foot fittings for damage, security, and function. AFI-104 e. Inspect seat frame for damage, and corrosion. AFI-105 f. Inspect overall seat for fit and function. A. The new divan assembly and restraint system are on the same inspection and maintenance schedule used per the Hawker Beechcraft Maintenance Manual for passenger seats. Page 10 of 15 PROT284 3.0 DIMENSION AND ACCESS: Revision (IR) The installation of this cabin configuration does not change the dimensions of the aircraft or alter the access to any existing aircraft system. 4.0 LIFTING AND SHORING No change. 5.0 LEVELING AND WEIGHING Divan Maximum Allowable Seat Weight 80 lbs w/ Seat Bottom Upholstery Base Weight of Divan Assembly w/ Restraint System = 50 lbs (includes empty drawer weight) 6.0 TOWING AND TAXIING No change. 7.0 PARKING AND MOORING No change. Page 11 of 16 PROT285 non, MO. 64735 Revision (IR} For repair or replacement of damaged or broken parts or assemblies contact Aviation Fabricators Inc. 2. Inspection Time Limit for the cabin configuration installations: 200 +1- hour inspection for the new cabin configuration components Task Code Schedule Date Mech Insp AFI-100 a. Inspect for damage to upholstery. AFI-101 b. Inspect safety belts for wear, cuts, fraying, damage, and deterioration. AFI-102 c. Inspect safety belt attachment fittings for wear and damage AFI-103 d. Inspect foot fittings for damage, security, and function. AFI-104 e. Inspect seat frame for damage, and corrosion. AR-105 f. Inspect overall seat for fit and function. A. The new divan assembly and restraint system are on the same inspection and maintenance schedule used per the Hawker Beechcraft Maintenance Manual for passenger seats. Page 10 of 16 PROT286 3.0 DIMENSION AND ACCESS: Revision (IR) The installation of this cabin configuration does not change the dimensions of the aircraft or alter the access to any existing aircraft system. 4.0 LIFTING AND SHORING No change. 5.0 LEVELING AND WEIGHING Divan Maximum Allowable Seat Weight 80 lbs w/ Seat Bottom Upholstery Base Weight of Divan Assembly w/ Restraint System = 50 lbs (includes empty drawer weight) 6.0 TOWING AND TAXIING No change. 7.0 PARKING AND MOORING No change. Page 11 of 16 PROT287 Revision (IR) Clinton, O. 84735 8.0 PLACARDS AND MARKINGS Three (3) placards are required in conjunction with this modification: 1. The divan installation requires placard part numbers 15-0288 and 32-0377-20 to be installed in plain view of the seat occupants on the forward divider. LIFE VEST LOCATED IN UNDER SEAT COMPARTMENT PIN 1S•0288 FASTEN SEATBELTANO SMOULDER HARNESS FOR TAXI. TAKEOFF AND LANDING P/N 32-0377-20 Figure 8.0A 2. A placard stating "to install harness over seat occupant's fwd shoulder" is sewn on to restraint system part numbers 3088-7-061-2396 and should be legible and easily viewed by the seat occupant. Figure 8.0B Page 12 of 16 PROT288 9.0 SERVICE INFORMATION Typical Passenger Seating Service Instructions: A. Upholstery Cleaning: Service Instructions Revision (IR) 1. Remove seat back and seat bottom cushion assemblies from the interior seating components. 2. Clean the cushions in accordance with instructions issued by the company responsible for the upholstery covering so that knowledge of the upholstery material's fire retardant properties are known and will not be compromised. 3. Clean and inspect restraint system for damage, fraying, cuts or seam deterioration. 4. Inspect all attachment fittings and replace if necessary. 5. Inspect overall interior component for fit and function. Typical Maintenance Instructions: Divan Assembly The divans are self contained complete assemblies that mount to the existing aircraft cabin seat track using standard fittings in accordance with approved floor plans. Refer to Figure 1.0A. Divan Installation Installation of the divan requires aligned the feet on the existing seat track and -attaching the divan legs using standard hardware. Refer to Installation Instruction drawing D-10666 for complete installation details and hardware part numbers. Divan Removal Removal of the divan requires loosening the attaching hardware and lifting the divan from its location on the seat track. The feet will be slid forward or aft to the end of the seat track or a gap in the track for their removal. Cushions Seat back and seat bottom cushion assemblies are removed by simply pulling the cushion inboard away from the Velcro on the sidewall or up away from the Velcro on the pan of the divan assembly, respectively. All covering and upholstery materials must comply with 14 PROT588 25.853 as stated on the Finish Materials Listing AF-476. The cushion design and layout were determined & manufactured by the seat installer to match the design of the cabin interior in the aircraft. Refer to Figure 1.0D for Cushion Assembly Reference for basic assemblies. Page 13 of 16 PROT289 8.0 PLACARDS AND MARKINGS Revision (IR) Three (3) placards are required in conjunction with this modification: 1. The divan installation requires placard part numbers 15-0288 and 32-0377-20 to be installed in plain view of the seat occupants on the forward divider. 35.6 UFE VEST LOCATED IN UNDER SEAT COMPARTMENT PIN 15.0288 FASTEN SEATBELT AND SHOULDER HARNESS FOR TAXI TAKEOFF AND LANDING Figure 8.0A PIN 32-0377-20 2. A placard stating "to install harness over seat occupant's fwd shoulder is sewn on to restraint system part numbers 3088-7-061-2396 and should be legible and easily viewed by the seat occupant. Figure 8.0B illitaill KIrILIZI nnmrunuu • fOISLROWINIllf Page 12 of 16 PROT290 Clinton, MO. 84735 9.0 SERVICE INFORMATION Typical Passenger Seating Service Instructions: A. Upholstery Cleaning: Service Instructions Revision (IR) 1. Remove seat back and seat bottom cushion assemblies from the interior seating components. 2. Clean the cushions in accordance with instructions issued by the company responsible for the upholstery covering so that knowledge of the upholstery material's fire retardant properties are known and will not be compromised. 3. Clean and inspect restraint system for damage, fraying, cuts or seam deterioration. 4. Inspect all attachment fittings and replace if necessary. 5. Inspect overall interior component for fit and function. Typical Maintenance Instructions: Divan Assembly The divans are self contained complete assemblies that mount to the existing aircraft cabin seat track using standard fittings in accordance with approved floor plans. Refer to Figure 1.0A. Divan Installation Installation of the divan requires aligned the feet on the existing seat track and -attaching the divan legs using standard hardware. Refer to Installation Instruction drawing O-10666 for complete installation details and hardware part numbers. Divan Removal Removal of the divan requires loosening the attaching hardware and lifting the divan from its location on the seat track. The feet will be slid forward or aft to the end of the seat track or a gap in the track for their removal. Cushions Seat back and seat bottom cushion assemblies are removed by simply pulling the cushion inboard away from the Velcro on the sidewall or up away from the Velcro on the pan of the divan assembly, respectively. All covering and upholstery materials must comply with 14 PROT589 25.853 as stated on the Finish Materials Listing AF-476. The cushion design and layout were determined & manufactured by the seat installer to match the design of the cabin interior in the aircraft. Refer to Figure 1.0D for Cushion Assembly Reference for basic assemblies. Page 13 of 16 PROT291 Clinton, M0. 647 Revision (IR) Inertia Reel Inertia reel removal is accomplished by loosening attaching hardware and removing from the divan frame bracket. Refer to Installation Instruction drawing D-10666 for complete installation details and hardware part numbers. Refer to Figure 1.08. Seat Belt Seat belt and removal is accomplished by loosening attaching hardware and removing from the existing aircraft seat track. Refer to Installation Instruction drawing D-10666 for complete installation details and hardware part numbers. Refer to Figure 1.0C. B. RECOMMENDED OVERHAUL PERIODS No additional overhaul time limitations and requirements apply to the Aviation Fabricators' interior cabin configuration. Page 14 of 15 PROT292 10.0 AIRWORTHINESS LIMITATIONS Revision (IR) The Airworthiness Limitations section is FAA approved and specifies maintenance required under Sec. 43.16 and 91.403 of the Federal Aviation Regulations unless an alternative program has been FM approved. There are no new (or additional) Airworthiness Limitations associated with this equipment and /or installation. 11.0 TROUBLESHOOTING INFORMATION Refer to the existing Aircraft Maintenance Manual for troubleshooting the 3 place divan installation that is required beyond the information found on the installation drawing D-10666. For replacement pads or repair of damage parts: Contact Aviation Fabricators at Troubleshooting this installation should only be accomplished by FM approved repair stations with the appropriate ratings or appropriately rated operator/individuals, with required test equipment and service data. Page 16 of 15 PROT293 Clinton, MO. 64736 Revision (IR) Inertia Reel Inertia reel removal is accomplished by loosening attaching hardware and removing from the divan frame bracket. Refer to Installation Instruction drawing D-10666 for complete installation details and hardware part numbers. Refer to Figure 1.0B. Seat Belt Seat belt and removal is accomplished by loosening attaching hardware and removing from the existing aircraft seat track. Refer to Installation Instruction drawing D-10666 for complete installation details and hardware part numbers. Refer to Figure 1.0C. B. RECOMMENDED OVERHAUL PERIODS No additional overhaul time limitations and requirements apply to the Aviation Fabricators' interior cabin configuration. Page 14 of 15 PROT294 10.0 AIRWORTHINESS LIMITATIONS Revision (IR) Dale: November 21, 2011 The Airworthiness Limitations section is FM approved and specifies maintenance required under Sec. 43.16 and 91.403 of the Federal Aviation Regulations unless an alternative program has been FAA approved. There are no new (or additional) Airworthiness Limitations associated with this equipment and /or installation. 11.0 TROUBLESHOOTING INFORMATION Refer to the existing Aircraft Maintenance Manual for troubleshooting the 3 place divan installation that is required beyond the information found on the installation drawing D-10666. For replacement parts or repair of damage parts: Contact Aviation Fabricators at Troubleshooting this installation should only be accomplished by FAA approved repair stations with the appropriate ratings or appropriately rated operator/individuals, with required test equipment and service data. Page 15 of 15 PROT295 U. S. DEPARTMENT OF TRANSPORTATION 1.DATE $/02/2013 2.MAKE Raytheon 3.MODEL NO. 400A 4.TYPE(AiVane• Engine. PrOplber. etc) Airplane 5.NAME OF APPLICANT Constant Aviation-CLM LIST OF DATA 6,IDENTIFICATION 2.TITLE TP 22681 Rev A Dated 05/02/2013 Skandia, Inc. Flammability Oil Burner Testing and Vertical Notes: 1) Work accomplished under 2) Flammability test witnessing materials. Test Report Burner Testing Skandia Inc. WO # 254987-13, Ref Document ID 93685. only, does not constitute installation approval of the 8.PURPOSE OF DATA Demonstration of compliance with material flammability requirements for S/N RK-244 9.APPLICABLE REQUIREMENTS (Ust specific sections) 14 PROT590 Part 25.853 (a) Amdt 25.116 Appendix F Part I (a)(1)(ii) 14 PROT591 Part 25.853 (c) Amendment 25-116 Appendix F Part II 10.CERTIFICATION - Under authority vested by direction of the of appointment under 14 PROT592 Part 183, data listed above and on examined in accordance with established procedures and found Standards listed. O I ( ) Therefore Recommend approval of these data `?.{ECApprove these data Administrator attached to comply and in accordance with conditions and limitations sheets numbered have been with applicable requirements of the Ainvorthiness 11.SIGNATURE(S) OF DESIGNATED ENGINEERING REPRESENTATIVE 12.DESIGNATION NUMBER(S) 13.CLASSIFICATION(S) I ERY-83278O-CE Structural Special FAA Forni 8110-3 (03/10) SUPERSEDES PREVIOUS EDITION PROT296 - PROT297 FAA FORM 8130-6, APPLICATION FOR U.S. AIRWORTHINESS CERTIFICATE Form Approved O.M.B. No.2120-0018 Expiration Dam 02/28/2013 a U.S Deparonen U.S. AIRWORTHINESS bTrenStaaratten Federal !Mallon CERTIFICATE ANnuNarstion INSTRUCTIONS • Print or type. Do net wraci n shaded cent then are for FM use only &lam* colonel only Man aL4hOrited FM Remesentalive If additional space a reparad, For Pahl Sections use indented Wool permits ccmplete IL W. and VII as coolIcable. I. AIRCRAFT DESCRIPTION I. REGISTRATION NARK N493LX 1 ARCRAF I OuiLOER'S NAME Pam/ 3. AIRCRAFT MODEL DESIGNATION 400A 4. YR MFR. 1999 FM CODING 5. A.RCRAFT SERIAL NO. RK-244 6. ENGINE SULZER'S NAME (5 Williams International 7. ENGINE MODEL DESIGNATION FJ44-3AP B. HOMER OF ENGINES 2 9 PROPELLER BURGERS NAME Plate N/A 10. PROPELLER WO a DESIGNATION It AIRCRAFT IS nentia emmicaan N/A I IMPORT es 0 D cc ta G a ra AN es 0 APPUCAT ION IS HEREBY MADE FOR **a eforese.4...) I A I STA/COMO AIRWORTHINESS CERTiFICATE (woo sematm/ I I 'Knit I I mol l I maeoll I I ^AA"' I I ce's's" . I I Nato' I I ob'm B I SPEOAL AI IMORTFINESS CERTIFICATE cora swoon io•NI 7 PRIMARY 9 LIGHT-SPORT « - t,-, I Inman, I fr oar-Paractsa I_ I Weigi-Stetanved I I Oder !keret Wan Air 2 UNITED MORMON/M. 1 CLASS I 5 Mama dessa 2 CLASS rl 1 AGRICULTURE MO PEST CONTROL 2 AERIAL SURVEY 3 AERIAL ADVERTISING 3 RESTRICTED rens etesam(Al III 44 COI4WWII 4 FOREST fat tlie• tO4S/649 5 PATRIXUNS 0 HEATHER CONTROL 0 OTHER (Socorrt 1 if RESEARCH AANCCEVELOPME DEVELOPMENT 2 AMATEUR BUILT 3 EXHIBITION 4 AIR RACING 5 CREW TRAINING 6 MARKET SURVEY 0 TO SNOW CCMPUANCE W(I14 THE PROT593 7 OPERATING "Mg Coney KIT MALT AIRCRAFT I M Eating Mart Hamm an eineortetess certficals 0 do real ma 1103.1 EXPERIMENTAL pate of eget) rowa:Lac a OPERATING 68 OWING UOI-Sport KR-bult LIGHT-SPORT SC OPerlen9 lighl-spcm pravfousle 'sued spa* Ilalt-Mierl Caletexy eirtvorthatass 21.190 colficalti tea m121.190 9 UNMANNED 9A RESEARCH NC DEVELOPMENT I K I I CREW TRAINING AIRCRAFT 98 MARKET SURVEY I FERRY FUG HT FOR REPAIRS. ALTERATIONS. MAINTENANCE. OR STORAGE FLIGHT PERMIT FROM AREA OF IMPENDING SPECIAL !MOW. 2 EVACUATE DAN3ER 8 0440.001 b be P:04444084 namaereis S•ex. VI a• vw es 4wecrat el town. lag 3 OPERATIONIN EXCESS OF MAXIMUM CERTIFICATED TAKECCF HEIGHT 4 CEUVEMNG OR EXPORTING 16 I I PRODUCTION FIGHT TESTING 6 CUSTOMER DEMONSTRATOR RAMS CI 6 MULTIPLE mRACRTHMESS CERTIFICATE gem MOstainmaid Oessorrarramesser astma, a melema/ i ft E at ii 1 li A REGETERED OWNER IF DEALER. CHECK HERE--ss I ma sin COIRCIAtt/Intia feifelnii NAME F igh Options LLC Richmond Heights .OH 44143 8 AIRCRAFT CERTIFICATION OASIS tOmm aeons. macs ramemec. ems. a$ evanesce AIRCRAFT SPECIFICATION OR TYPE CERTIFICATE DATA sasEET crass se and /imam no/ N/A AIRWORTHINESS ORECTIVES ensecti444amaessam es am mei mee melee es 4004, a no wAD SOOWEAMMT ~YAP nes ilsesety same n fl eas al 4•044444 Bi Weekly 2013-22 10/21/2013 - 11/03/2013 AIRCRAFT LISTWG (Caaeme e.1003 N/A SUPPLEMENTAL TYPE CERTIFICATE AM ranks &lath SIC Acarnembel N/A C. AIRCRAFT OPERATION AND WuNTENANCE RECORDS I CHECK IF RECORDS IN COMPU c ANCE MATH 417 art, lat91. TOTAL AIRFRAME HOURS TTAF 8578.62 3 EXPERIMENTAL ONLY myna., /*was" pi ati. saw <e nrage) 14.82 0. CERTIFICATION slant, e•My Malian aceardwo6 `IS TIO• 49 al MA Urges Man alretalhaess canifiona racemrsIed. we mastered caws (or Ns gen° of Ma Mutt dsunbad Raw DIM We Wash CRCs 41101 1St RN WRNS Feel* Aviation Recatatons. SCout the is rageletinld Yana* Federal Ablation AcireNstralcet In DATE OF APPUCATON 1 /18/2013 illibila Agent H ill i A THE NRCRAFT CESCRO3E0 ABOVE HAS BEEN INSPECTED ANI)FOUNO SCOW/ BY: Crew we NeartstaY 2 14 PROT594 pwl 121 CERTIFICATE MADERO" cantariel 3 I CERTIFICATED MECHANIC gos Cameos on 6 CERTIFICATED REPAIR STATION (C.• Cfnea• Ab ) 5 AIRCRAFT MANLIFACTURER patesere rem/ DATE TITLE SIGNATURE V. FAA REPRESENTATIVE CERTIFICATION tow ALL aeons • Mom M.,4 ova) ,s THE CERTIFICATE REQUESTED A. I And Mat re Sand demoted in San I cc VII mow raparemerts rim 4 /JAEsfwENT CR IAOCCICATICN OF CURRENT MRIACRTHINESS CERTif iCATE avower., for a special not pooh weer Section VII .as conned Dr FM INSPECTOR FM DESIGNEE CERTIFICATE HOLDER UNCER 14 PROT595 65 14 CF 121 OR 135 14 II DATE 11/16/2013 meCOFSDO OFFICE CLE-25 FAA Form 81304 (4J 11) AI P 'anus Editions Stpetseded Electronic Format -PO F RECtIvED QD co a 0 L. a PJ 0 DEC 1 a 2013 CLE - 01.22 PROT298 PROT299 au i 9. 8 t )1 9 C A. MAMJFACTURER NAME *OGRESS PRODUCTION SASS (C.hecR makes (MN PRODUCTION CERTS1CATE (Caro induCann can/tka nprnaO TYPE CERTIFICATE OTHER C. GM QUANTITY OF CERTIFICATES REQUIRED FOR OFERATIM3 NEEDS NAME ANC% TILE (AM or WM SIGNATURE H k VIA 2 1 O I 2 i E. Z I g g A DESCRIPTION OF AIRCRAFT REGISTERED OANER ADDRESS EIULCIER NON MODEL SERIAL NUMBER REGSTRATION MARK E. DESCRIPTION OF FLIGHT CuS7CatFR DEMONSTRATION FLIGHTS C) act I I ar~e) FROM 70 DEPARTURE DATE DURATION C. CREW REQUIRED TO OPERATE THE AIRCRAFT AHD ITS EOUPMENT I I PILOT I I COPILOT I ll FUGHT ENGINEER I I O71-IER(Sact/H D. THE AIRCRAFT DOES NOT MEET THE APPUCABLE NRWORTHNESS REQUIREMENTS AS FOLLOWS: THE FOLLOWING RESTRICTK)NS ARE CONSIDERED NECESSARY FOR SAFE OPERATION-. (Use onacnrneni a necessary) F. CERTIFICATION • i hereby unly ow $ an roe nagmenal wince Mr his gat 44 the ~all ~abed Moat OW 1119 Wain li tasleffee mil Me Federal Ayaldin ~eleance, In acmrclance rain Tale 49 of me Unted Swiss Code 44101 mag erd applKetae Federal Anegan Resat" and mat roe awal has can ins:main arc s saM by Me MN detwited. DATE tom4E AM) TITLE (Peal a lyta) SIGNATURE VII. AIRWORTHINESS 0CCUMENTATION I FAAltaGNEE us* or*) ir A OPelead Written. nO Mallngs In Cotriplancie Ma 14 CPR anion 919. AeNtolatile G. Seamen ol Conaway. FAA Form 81309 (Mach .tenrequWo It Foreign Anvorthiness Centation Tor Irian Mend (Meta when recl~) a ^Mane Maclied C. DMA Ortharga ~cgs" em. One& when ~era i I. PnaMme ~eau Cartkam issued a Abadan. WM le cat agago 21.191 (a) cm conrai attach:di l D. Carat ~IF« aid Enna Wormann Mama in Mcrae E Marx RONK imil Mermen FM Form337 (Meal when ragweed) 1 J. Cunard Pirercaemes Graeae leased in Aacrilence WM la caR sock", 21.191 (a) tconschm F. Trn inseam« Recorder, n Aircraft Records K. ØØ Alma awns% ol Ccerørecte. FAA Form 60015 (Mach when MON« FM Form 91304 VIII 1 ) All Previous Eagle SuNKII40400 Electronic Format -PDF Poii• 2 2 PROT300 PROT301 DEPARTMENT . FEDERAL AVIATION ADMINISTRATION SPECIAL AIRWORTHINESS CERTIFICATE A CATEGORYIDESIGNATION EVERIEITA. PURPOSE RESEW & COMMENT ,,,:A' B MANU- FACTURER NAME /f/VA.J;-,(-1--1;11\ ADDRESS 8d,Nti(Al \'4, ' c FLIGHT FROM II/AVM* AI`A TO III '11,0 I r,) \ E' ',.!,! n u N. 4.91I X III '')-,; v,-- - --n--) L NO. SERIAL R-241 BUILDER Raytheon Ater4facip* IA MODEL OA E DATE OF ISSUANCE tiorO\ \ Ili /0 ;E:X,FAY Jan 12. 2014 OPERATING LIMITKONNIPIi1820134t PART OF THIS CERTIFICATE li ' DESIGNATION OR OFFICE NO. DART833943GL Any alteration, reproduction or misuse of this certificate may be punishable by a fine not exceeding $1,000 or imprisonment not exceeding 3 years, or both. THIS CERTIFICATE MUST BE DISPLAYED IN THE AIRCRAFT IN ACCORDANCE WITH APPLICABLE TITLE 14, CODE OF FEDERAL REGULATIONS (PROT596). FAA FORM 5130.7 (MN} SEE REVERSE SIDE NSN. 0052.004914000 PROT302 A A certificate is issued under the authority of Public Law 104.6, 49 United Stales Code (PROT597) 44704 and Title 14 Code of Federal Regulations (PROT598). 0 w The airworthiness certificate authorizes the manufacturer named on the reverse side 0 conduct production flight !et, and only production flight tests, of aircraft registered in his name. No person may conduct production flight tests under this certificate: (1) Caging persons or property for compensation or hire: and/or 0 Carrying persons not essential to the purpose of the flight r v certificate authorizes the flight specified.on the reverse side for the purpose shown in Block A, D certificate certifies that as of the date of issuance, the aircraft to which issued has been inspected and found to meet the requirements °title applicable PROT599. The aircraft does not meet the requirements of the applicable comprehensive code as provided by Annex 6 to the Convention On International CivilAvialion. No person may operate the aircraft described on the reverse side: (1) except in accordance with the applicable PROT600 and in accordance with conditions and limitations which may be prescribed by the Administrator as part of this certificate; (2) over any foreign country without the special permission of that country. E Unless sooner surrendered, suspended, or revoked, this airworthiness certificate is effective for the duration and under the conditions prescribed in 14 PROT601, Part 21, Section 21,161 or 21.217. PROT303 DEPARTMENT OF TRANSPORTATION . FEDERAL AVIATION ADMINISTRATION SPECIAL AIRWORTHINESS CERTIFICATE A CATEGORY/DESIGNATION ' EXPERIMENTAL PURPOSE Research and Development B MANU• FACTURER NAME NIA ADDRESS NIA p C FLIGHT FROM ON:A TO 0\ D N• 493LX 4\\ SERIAL NO, RK2 44 BUILDER Raytheon Aircraft Company MODEL 400A DATE OF ISSUANC MAY12012013 EXPIRY Nom Ri2013 OPERATING U ATIONS DATE 1 1. ARE PART OF THIS CERT E DESIGNATIO OR OFFICE NO, DARF-400148•CE Any alteration, reproduction o misuse of this certi ie may be punishable by a fine not exceeding $1,000 or imprisonment not exceeding 3 years, or both, THIS CERTIFICATE MUST BE DISPLAYED IN THE AIRCRAFT IN ACCORDANCE WITH APPLICABLE TITLE 14, CODE OF FEDERAL REGULATIONS (PROT602), FAA Form 813P 04120111 Nous Edition 01104 May be Used until Depleted SEE REVERSE SIDE NSN: 00524493400 PROT304 c A n certificate is issued under the authority of Public Law 104.6, 49 United Slates Code (PROT603) 44704 and Title 14 Code of Federal Regulations (PROT604). B The airworthiness certificate authorizes the manufacturer named on the reverse side to conduct production fight tests, and only production flight tests, of aircraft registered in his name, No person may conduct production flight tests under this certificate (1) Carrying persons or property for compensation or hire: andlor (2) Carrying persons not essential to the purpose of the flight. ft v certificate authorizes the flight specified on the reverse side for the purpose shown in Block A. D certificate codifies that as of the date of issuance, the aircraft to which issued has been inspected and found to meet the requirements of the applicable PROT605. The aircraft does not meet the requirements of the applicable comprehensive code as provided by Annex 8 to the Convention On International Civil Aviation, No person may operate the aircraft described on the reverse side (1) except in accordance with the applicable PROT606 and in accordance with conditions and limitations which may be prescribed by the FM as part of this certificate; (2) over any foreign country without the special permission of that country. E Unless sooner surrendered, suspended, or revoked, this airworthiness certificate is effective for the duration and under the condnions prescribed in 14 PROT607, Pad 21, Section 21.181 or 21.211. PROT305 U.S.Oepartment of Transportation Administration REG. NO. N4931X EXPERIMENTAL OPERATING LIMITATIONS For Research and Development (R&D) MAKE: MODEL 400A WM 0404140MO Ohio 44070 SERIAL NO: RK - 244 THESE OPERATING LIMITATIONS SHALL BE ACCESSIBLE TO THE PILOT 1. No person may operate this aircraft unless the FAA Form 8130-7, Special Airworthiness Certificate. is displayed at the cabin or cockpit entrance and visible to passengers or flight crew members. 2. No person may operate this aircraft for other than the purpose of Research and Development to accomplish the flight operation outlined in the applicant's program letter Dated November 13.2013, which describes compliance withl4 PROT608 21.193 (d) and made available to the pilot in command of the aircraft In addition, this aircraft shall be operated in accordance with applicable.air traffic and general operating rules of 14 PROT609 part 91,and all additional limitalionsherein prescribed under the provisions of 14 PROT610 91.319 (i). 3. R&D flights must be conducted IAW Nextant Aerospace's Program Letter Dated November 13. 2013, within the geographical area described In the program letter. R&D Rights will be conducted In North America 4. Except for takeoffs and landings, this arcraft must not be operated over densely populated areas or in congested airways. 5. This aircraft must not be operated unless it is maintained and Inspected in accordance with the appropriate military technicalpublIcations and/a manufacturer's recommendation. The owner/operator must select, establish, identify, and use an inspection program set forth in 14 PROT611 91.409 (e), (f),(g), and (h). This inspection program must be recorded in the aircraft maintenance records. 6. The Pilot In Command of this aircraft must hold an appropriate category/Gass rating. If required for the type of aircraft to be flown, the Pilot In Command also must hold either an appropriate type rating or a Letter of Authorization issued by an FM Flight Standards Operations Inspector. 7. This aircraft may be operated under VFR, day and/or night. 8. The Aircraft may be operated under IFR, and must be properly equipped for instrument flight in accordance with 14 PROT612 91.205. 9. No person may operate this aircraft for carrying persons or property for compensation or hire. 10. No person may be carried in this aircraft during flight unless that person is essential to the purpose of the flight. 11. The Pilot In Command of this aircraft must advise each passenger of the experimentalnature of this arcraft, And explain that It does not meet the certification requirements of a standard certified aircraft. 12. This Aircraft must contain the Beech Model 400A Flight Manual with Nextant 400XT AFM Section Insert, Placards, markings, etc. (or other operating instructions developed for an STC modification), as required by14 PROT613 91.9. 13. This Aircraft is Prohibited from Aerobatic Flight , that is an Intentional Maneuver involving an Abrupt change in the Aircrafts attitude, an abnormal attitude, or abnormal acceleration not necessary for normal flight, unless part of show compliance flight testing 14. This aircraft shall not be used for glider towing, banner towing, or intentionalparachute jumping. Page 102 PROT306 PROT307 Administration 15. No person shall operate this aircraft unless within the preceding 12 Calendar months it has had a condition inspection performed in accordance with 14 PROT614 Part 43, appendix D,or other FAA approved programs, and was found to be in a condition for safe Operation. This inspection will be recorded in the aircraft maintenance records. 18. FAA•certificated Repair Stations and FM - Certified mechanics with appropriate ratings, as authorized by 14 PROT615 43.3 may perform inspections required by these limitations. 17. Inspections shall be recorded in the aircraft maintenance records showing the following or a similarly worded statement: "I certify that this aircraft has been inspected on (insert date) in accordance with the scope and detail of 14 PROT616 part 43, appendix D,or other FAA approved programs and found to be In a condition for safe operation." The entry will Include the aircraft's totaltime-in-service, and the name, signature, certificate number, and type of certificate held by the person performing the inspection. 18. If the aircraft, engine, or propeller operating limitations are exceeded, an appropriate entry will be made In the aircraft records. 19. This aircraft must not be operated unless it is maintained and inspected in accordance with the requirements of 14 PROT617 Part 43. 20. This aircraft must display the word `EXPERIMENTAL" In accordance with 14 PROT618 45.23(b). 21. The Pilot In Command of this aircraft must notify air traffic control of the experimental nature of this aircraft when operating into or out of airports with operating control bra The Pilot In Command must plan routing that will avoid densely populated areas and congested airways when operating VER. 22. This aircraft does not meet the requirements of the applicable, comprehensive, and detailed AInvorthIness code as provided by Annex 8 of the International Convention of Civil Aviation. The Owner/Operator of this aircraft must obtain written permission from another country's Civil Airworthiness Authority (CAA) prior to operating this aircraft in or over that country. That written permission must be carried aboard the aircraft together with the U.S. airworthiness certificate and, upon request, be made available to an FAA inspector or the CAA in the country of operation. 23. Aicraft instruments and equipment installed and used under 14 PROT619 91205 must be inspected and maintained in accordance with the requirements of 14 PROT620 parts 43 and 91. Any maintenance or inspection of this equipment must be recorded in the Aircraft Maintenance records. 24. Application must be made to the geographically responsible FSDO or MO for any revision to these operating limitations. 25. 14 PROT621 47.45 requires that the FM Aircraft Registry must be notified within 30 days of any change it the aircraft registrant's address. Such notification Is to be made by submitting Aeronautical Center Form 8050-1, Aircraft Registration Application, to AFS•750 in Oklahoma City, OK. 26. Condition Inspections must be performed in Accordance with 14 PROT622 Part 43 Appendix D at least every 100 Hrs Flight Hours. This Inspection must be performed by an FM Certified Mechanic with the Appropriate Ratings as deemed in 14 PROT623. 43.3 27. The Special Airworthiness Certificate and Operation Limitations will eerie on. Jan 12.2014 Designated Airworthiness Representative DART833943GL Issued at Cuyahoga Airport Date Issued: November18 2013 Page 2 c42 PROT308 PROT309 Quality Assurance Department To: Flight Standards District Office North Olmsted, Ohio 44070 From: Date: November 13, 2013 Chief Inspector Subject: FAA Program letter for Beech let 400A, Serial number RK-244, Registration Number N493LX. Ref: FAA order 8130.2G 1. Registered Owner: Flight Options LLC. Address: 2. Aircraft Description: Twin Engine Light let a. Registration: N493LX b. Aircraft Builder Raytheon Aircraft Co c. Year mfg.: 1999 d. Aircraft Serial Number: RK-244 e. Aircraft Model Designation: Beech Jet 400A 3. The program purpose for the aircraft will be used To complete the flight performance profile in Research & Development Category in support of FAA Project SA 152501A-7 (Replacement of Wingtips) 4. Program Duration a. List the estimated flight hours required for program: 20 Hrs b. Number of flights: 20 c. Number of days: 60 S. Describe the areas over which the flights to be conducted and address of base operation: The base of operation is Cuyahoga County Airport, 355 Richmond, Cleveland, Ohio. Flights will be conducted in North America. 6. Describe the aircraft configuration: This Aircraft is a standard Beech let 400A with new Williams F144-3AP engines and upgraded avionics with full authority digital engine controls (FADEC) a. Maintenance Program 1. Hawker Beechcraft Maintenance Manual Chapter 5 Rev C22 or later with the exception of the .1115D Engines. 2. Williams International recommended FJ44 3A Maintenance manual (FADEC maintenance is covered in 71.00.00 of this manual) 3. Maintenance Requirements for the Throttle Quadrant is addressed in the Instructions for Continued Airworthiness on the FJ44-3AP STC. 202 A Tel Work Cell '4'Spt& PROT310 PROT311 Cleveland. Ohio 44143 November 13, 2013 Nextant Aerospace, LLC Cleveland, Ohio 44143 Attention: Re: RK-244 - Agent Authorization To whom it may concern: aLitOptions This letter is to confirm that Flight Options, LLC (TO") authorizes Nextant Aerospace, LLC, as FO's agent, for a Beechjet 400A, bearing serial number RK-244 and FAA Registration Number N493LX (also identified as a "Nextant 400XT'), which is owned by FO, for any and all authorized FAA actions in regards to: X Airworthiness Classification Experimental Airworthiness Classification Standard Sincerely, Flight Options, LLC By: Vice President, Administration & Contracts PROT312 :I•1A1 1: PROT313 FAA FORM 1030-6, APPLICATION FOR U.S. AIRWORTHINESS CERTIFICATE Fpm Approved O.M.O. No. 2120-0018 Expiration Date 02/28/2013 a U.S. Cepartmem U.S. AIRWORTHINESS a Transponaton CERTIFICATE Adirealsrratioe INSTRUCTIONS • Prim or Iwo Do nol rote in shaded arms; Mese are for FAA molly. Sutom cripnal otmr a en eufacrized FM Repfeientatne. If edclOomil Space is motive& use ailachnent. For special IIHM permits complete Sections H. A. and Alas applicable e t 0 * r • gi I REGISTRATION MARK N493LX 2. AIRCRAFT MOLDERS NAME mum 3. AIRCRAFT MOOELDESGNATION 400A 4. YR MFR. 1999 FM COOING 5 AIRCRAFT SERIAL NO. RK244 S ENGINE BUILDER'S NAME Ago.) Williams International 7. ENGINE MODEL OESIGNATION FJ44.3AP 8. NUMBER OF ENGINES 2 9 PROPELLER BUILDERS NAME MAN N/A ID PROPELLER MOO EL DESIGNATION II. AIRCRAFT IS farm moomsam N/A IMPORT gi burr g g et u a APPUCATION IS HEREBY MACE FOR. Momoorrim on) I A l STANDARD NROORTIMIESS CERTIFICATE roses *wpm Hama Honor, I I I I roarrem I [morn. Hamm. I lona 8 re SPECIAL MFMORTICESS CERTINCATE Moo refierme Arm/ 7 PRIAMM 9 UGHT-SPCRT limas Caw I IN/Hanel I loompParadue I I WeIgHtellarotrc4 I 1 Cider I I Utter Mari M 2 UNITED 1 LASS C 2 5 PROVISIONAL Room oleo CLASS II 1 AGRICULTURE AND PEST CONTROL 2 AEFOAL SURVEY 3 AERIM.A0VERMING 3 RESTRICTED Mcrae to 44 <40:1•000) 4 FOREST 0$0.4 ten."4"; 5 PATROLLING 6 HEATHER CONTROL 0 OTHER (40/4240 I I RESEARCH AND CEVELCPMENT 2 AMATEUR BUILT 3 EXHH/TION 4 AIR RACING S CREW BINNING 6 MARKET SURVEY 0 TO SHOW COMPLIANCE VAN THE PROT624 7 OPERATING Morro Crown KIT MKT AIRCRAFT I OA EMOTE aMmill*Mota an armorinns cortfale II 00 nol noel 6103.1 4 EXPERIMENTμ nmcompramoN rem romum e OPERATIC 58 OPROUBUDIGpoil Kt-tun UGHT4PC111 ec OPTION 1911-sped HICAPIT *PAP WOO 5911-spat allegory almannona cerMeate untie 621.190 9 UMMNMED 9A RESEARCH AND DEVELOPMENT ICI I CREW TRAINING AIRCRAFT 96 MARKET SURVEY I FERRY FLIGHT FOR REP...MS.ALTERATION& MAINTENANCE CR STORAGE SPEOAL FLIGHT PERMIT mops 2 EVACUATE FROM AREA OF IMPENDING DANGER 8 wersoo re re mower oaf ammo mom me. oval motes* inform HIN 3 OPERATION IN EXCESS OF MAXJMUM CERTIFICATED TAKEOFF WEIGHT 4 DEUVERING OR EXPORTING I 5 I I PROCUCTIONCL4HT TESTING 6 CUSTOMER CEMONSTRATIONFUGHTS CI 6 MULTIPLE AIRWORTHINESS CERTIFICATE KAM MOM Moron Oiwatim on lanOwe a bile•raniffitaal i § is i A REGISTEREDCOTNER Hs was , mita a rose nommor IF DEALER. CHECK HERE o I NM* F ight Options.LLC Flight Options LLC , Richmond Heights .OH 44143 B AIRCRAFT CERTIFICATION 8ABG rtmempoommuar mamma Sr, n **gat AIRCRAFT SPECIFICATION CR TYPE CERTIFICATE DATA SHEET rom rie ma A•VOiLl ion N/A 1 ACVORTMNESS ORECTIVES (Owl delloWeormOs ii• erreraloomeerwmormeree AD Si,. -Van. 'VW miss If or mmymno ordinee as itooleeerf W O o Bi-Weeky 2013-09, 04/22/2013 - 05/05/2013 NRCRAFT LISTING (G.........e.nw N/A SUPPLEMENTAL TYPE CERTIFICATE ON east el nen Sit N/A C. NRCRAFT OPERATION MID MAINTENANCE RECORDS CAECK IF RECORDS IN COMPLIANCE WIN 14 PROT625 maion 91.417 TOTAL AIRFRAME CURS 8563.80 3 EXPERIAMMTAL ONLY oa gmmeem sa f me resima im moray Pommel D. accordant* MoKorinests DATE A CERTIRCATION - Mersey wiry Minim Me regtsond maw (of Pis mere) of fl ame deemed atom out me a cart is roomers wfl um Femme miafion Auffirientlen In am Title 49 of to vow Stain Coo:lan), rt)aa and swears Feciend Amato Regutataro and mat lie wenn has Wen is eimilby WV* aP* cenlftele OF APPLICATION 05/13/2013 THE AIRCRAFT OESCREIEDMIOVE u i 5 qe a 2 III PROT626 1 CERTIFICATE HOLDEROm I a l 'CERTIFICATED MECRANICIG•• Gesture no, I 0 I I CERTIFICATED REPAIR STATION min comm. 5 AIRCRAFT MANUFACTURER (ava nava weary DATE I WILE I SIGNATURE (I A I A," 5 OFFICE fl u rt ttatax Awns taco HMO A Mee) 14 THE CERTIFICATE REQUESTED A. I lino Mal ins Wine dilated In Salon Ice VII meets refoiterrors to MIENINENT OR MODIFICATION OF CURRENT NRW3RTHWESS CERTIFICATE B. IrdPr-Sen Tor a Medial WY pWT1 Lwow Sprain VII was conducted by. FM INSPECTOR FM DESIGNEE DATE /1400/40 MICOSSOO ct-91T 4 FAA Fern 81304 (4/11) Al Preview Etna Superseded Msdronic Tama -POF Page 1 o12 PROT314 r PROT315 VI. PRODUCTION FLIGHT TESTING A. MANUFACTURER NAME ADDRESS Et PRODUCTION BASIS (CAM M0MS* amp PRODUCTION CERTIFICATE 1Gw Skis cetelicettinai) TYPE CERTIFICATE OTHER C. GIVE OLLANNTY OF CERTIFICATES REWIRED FOR OPERATING NEEDS DATE OF APPLICATOR I NAME ANO TITLE (PAM MK*) SIGNATURE VLL SPECIAL. ruGHT PERMIT PURPOSES OTHER THAN PRODUCTION WONT TEST A DESCRIPTION OF MRCRAFT REGISTERED OWNER ADDRESS BUIDER (444/g) MODEL SERIAL NUMBER REGISTRATION MARK B. DESCRIPTION OF RIGHT CUSTOMER DEMONSTRATION FLIGHTS CI COMM arpiest, FROM TO VIA OEPARTURE DATE DURATION G CREW REWIRED TO OPERATE THE MRCRAFT AND ITS EOUIPMENT I I PILOT I i COPILOT I I FLIGHT ENGINEER I I oTHERmixtoM O. THE AIRCRAFT DOES NOT MEET THE APPLICABLE ARWORTHWESS REOUREMENTS AS FOLLOWS: E TIE FOU.OWNO RESTRICTIONS ARE CONSIDERED NECESSARY FOR SAFE OPERATOR Ma artaconenr.r moues) F. CERTIFICATION • 1 nints own& ita I inn ronmerse comer (or PM onov) ol to ICS emoted sten TM et glen A Is recitietedweh re Feces& Aeatt:c AOrtmusilon In KConlarball MI. TIN 49 d Me UMW gabs Cods 44101 AM Old Opplane F.dfl ANSI Regal** anent Os eaten ras omen (Assam AN o d. b. so fir easerisol DATE NAME AND TITLE (HMI Or Wee SIGNATURE a 3 4.4 ..4 g 3_ E tf ll At i z V cam Unallons end Morkims In Complisnes W0114 PROT627 Seclion 919. m Apro EL Stammers of CoMonons, FAA Fpm 8,30.9 (Attach twee i 'Quince )t Forolr Akoortinom Owilkslon fix loom Nana man Atm' rogue') Y El Curia Camel° Lieritef ens Aliened c oga. Dr. &Arcs. 12744O3rXim. etc lath rinuiroal X I Ewa* Mvoltenrs 14 PROT628 SICEcti hi. 3 a) semen Ai Accordsnas Win CAR (EloGolM (mown 1 D. Omen: weiM re4 BOOM Ink/motion Awilatle in Aktran E. Majot Eepal and Minton. FAA Form 337 (ARM Men IMMO IV J Carp' ANAIEhnenCe. MSIved in AtEcedanCe Wm Id PROT629 Swim 2 S .I. Fit (of 1 (Cary Onto* ic F. Ms iromraon Ftscanol In Moan Recant N. UV-Sport Alrcret SUOMMI ciCarolarcoo. FM Form 813013 Mach Men nequeed) FAA Form 61304 (4111) MI Pnwians Edllioni gnomons(' Eiscimoic Formal -POF Page 2 of 2 PROT316 PROT317 DEPARTMENT • FEDERAL AVIATION ADMINISTRATION SPECIAL AIRWORTHINESS CERTIFICATE A CATEGORY/DESIGNATION EXPERIMENTAL PURPOSE a MK. FACTURER NAME NIA ADDRESS NIA st C FLIGHT FROM et TO D N. 4931,X SERIAL NO. RK244 BUILDER Raytheon Company MODEL OA E Any imprisonment IN ACCORDANCE DATE OF ISSUANCE mAymoi3 EXPIRY NOV11612013 OPERATING LIMITATIONS DATE ARE PART OF THIS CERTIFICATE DESIGNATION OR OFFICE NO. DARF-400148•CE alteration, reproduction or misuse of this cerii cafe may be perishable by a fine not exceeding $1,000 or not exceeding 3 years, or both. THIS CERTIFICATE MUST BE DISPLAYED IN THE AIRCRAFT WITH APPLICABLE TITLE 14, CODE OF FEDERAL REGULATIONS {PROT630), FAA Form 8130.1 (4412011) Previous Edition 01104 May be Used old Depleted SEE REVERSE SIDE NSM 0052.00.693.4000 PROT318 A PI certificate is issued under the authoriry of Public Law 104.5, 49 United Slates Code (PROT631) 44184 and Tile 14 Code of Federal Regulations (PROT632). D w The airworthiness certificate authorizes the manufacturer named on the reverse side to conduct production fight tests, and only production light tests, of aircraft registered in his name. No person may conduct production flight tests under this certificate (1) Carrying persons or property for compensation or hire: andfor (2) Carrying persons not essential to the purpose of the night. r v certificate authorizes the light specified on the reverse side for the purpose shown in Block A, D certificate certifies that as of the dale of issuance, the aircraft to which issued has been inspected and found to meet the requirements of the applicable PROT633. The aircraft does not meet the requirements of the applicable comprehensive code as provided by Annex 8 to the Convention On International Civil Aviation. No person may operate the aircraft described on the reverse side (1) except in accordance with the applicable PROT634 and in accordance with condons and limitations which may be prescribed by the FM as pad of this certificate; (2) over any foreign country without the special permission of that country, in c Unless sooner surrendered, suspended, of revoked, this airworthiness certificate is effective for the duration and under the conditions prescribed in 14 PROT635, Part 21, Section 21.181 or 21.217. PROT319 mato STATES OF AMERICA 1 NATIONALITY NC 2 MANUFACTURER AND MODEL 4 CATEGORY REGISTRATION MARKS Raytheon Aircraft Co. NUMBER N493LX 400A RK-244 Transport This eawonhasess cenAcate is issued pagan to the Federal Avtation Ad of 19SI) and cents, the, es a the date of deemd& the simnel to shish weed Ms been inspected and found to conleem to the type corshcato Monitor, to be In condbon to safe operation and has been enhan to rneel the re:we-rents of the applicable comprehensive and detailed einvonNness code as prove:kid by Anneal° the Convention on Intemallenal CM AWtbn• except as noted lea Escepbons: None TEWASANO CONDITIONS Unless sooner stnendered. suspended. teroked. at a terrnInahcn data N othanvise establoshect by the Adadnistrelor. this einirenhiness Cette:000 b elleCIMI BO Bee es the maintenance. preventatse men•Mend. and alterations are Paired In adadane *RI Fans 2I. 43. and 91 of Me Fathom, A registered Yl Sr UMW States. R 10/01/1999 AEA -FSCO -23 My Menlo% repoduceon. a Meese of Ithoelitcate may be paetheble Menne not exceeding SIAM et lepreonmeini not 11$014.910 3 semisweet. THIS CERTIFICATE MUST BE DISPLAYED M THE SAGAMI IN ACCORDANCE tMTH AMICABLE FEDERAL AVIATION REGULATIONS. FAA Farm 4100-2 (108) PROT320 - PROT321 Cleveland, Gala 44143 May 8.2013 VIA HAND DELIVERY Nextant Aerospace, LLC Cleveland, Ohio 44143 Attention: Re: RK-244 - Agent Authorization Ladies and Gentlemen: eit Options This letter is to confirm that Flight Options. LLC ("Flight Options") authorizes Nextant Aerospace, LLC, as Flight Options' agent, for a Beechjet 400A, bearing serial number RK-244 and FAA Registration Number N493LX, which is owned by Flight Options, for any and all authorized FAA actions. Sincerely. FLIGHT OPTIONS LLC Vice President of Whole Aircraft Acquisitions and Sales STATE OF OHIO tty Camm. ExpteS APIS a 2016 511-41.3 PROT322 PROT323 U.S. Department Administration EXPERIMENTAL OPERATING LIMITATIONS PURPOSE MAKE Company MODEL 400A REGISTRATION N493LX SERIAL NUMBER RK244 I ) No person may operate this aircraft unless FAA Form 8130-7 is displayed at the cabin or cockpit entrance and is visible to passengers or flightcrew members. 2) No person may operate this aircraft for other than the purpose of RESEARCH AND DEVELOPMENT to accomplish the flight operation outlined in the program letter, dated May 13, 2013, which describes compliance with 14 PROT636 §21.193(d) and has been made available to the pilot-in-command of the aircraft. In addition, this aircraft must be operated in accordance with applicable air traffic and general operating rules of 14 PROT637 Part 91, and all additional limitations herein prescribed under the provisions of 14 PROT638 § 9I.319(i). 3) All flights must be conducted within the 48 contiguous United States of America, except for takeoffs and landings, this aircraft must not be operated over densely populated areas or in congested airways except when otherwise directed by Air Traffic Control or in an emergency situation. 4) N/A 5) N/A 6) N/A 7) This aircraft must not be operated unless it is inspected and maintained in accordance with appropriate military technical publications and/or manufacturer's recommendations. The owner/operator must select, establish, identify, and use an inspection program as set forth in 14 PROT639 §91.409(e), (0, (g) and (h). This inspection program must be recorded in the aircraft maintenance records. 8) The Pilot in Command of this aircraft must hold an appropriate category/class rating. If required for the type of aircraft to be flown, the Pilot in Command must also hold either an appropriate type rating or a letter of authorization issued by an FAA Flight Standards Operations Inspector. 9) N/A 10) N/A II) This aircraft may be operated under IFR, and must be properly equipped for instrument flight in accordance with 14 PROT640 § 91.205. All test maneuvers must be conducted during day Visual Meteorological Conditions (VFR). 12) No person may operate this aircraft for carrying persons or property for compensation or hire. 13) No person may be carried in this aircraft during flight unless that person is essential to the purpose of the flight. 14) N/A 15) The pilot in command of this aircraft must advise each passenger of the experimental nature of this aircraft, and explain that it does not meet the certification requirements of a standard certificated aircraft. 16) This aircraft must contain the placards, markings, etc., (or other operating instructions developed for an STC modification) as required by 14 PROT641 §91.9. Total Pages: 3 PROT324 PROT325 EXPERIMENTAL OPERATING LIMITATIONS PURPOSE MAKE Company MODEL 400A REGISTRATION N493LX SERIAL NUMBER RK244 Page 2 of 3 17) This aircraft is prohibited from aerobatic flight; that is, an intentional maneuver involving an abrupt change in the aircraft's attitude, an abnormal attitude, or abnormal acceleration not nectssary for normal flight. I 8) This aircraft may conduct acrobatic flight in accordance with 14 PROT642 § 91.303. Aerobatics must not be attempted until sufficient flight experience has been gained to establish that the aircraft is satisfactorily controllable and in compliance with 14 PROT643 § 91.319(b). Acrobatic maneuvers intended to be performed must be satisfactorily accomplished and recorded in the aircraft records during the flight test period. I 9) N/A 20) This aircraft must not be used for glider towing, banner towing, or intentional parachute jumping. 21) No person must operate this aircraft unless within the preceding 12 calendar months it has had a condition inspection performed in accordance with the scope and detail of 14 PROT644 part 43 appendix D, or other FAA- approved programs and was found to be in a condition for safe operation. This inspection will be recorded in the aircraft maintenance records. 22) FAA-certificated repair stations and FAA-certificated mechanics with appropriate ratings as authorized by 14 PROT645 §43.3 may perform inspections required by these operating limitations. 23) Inspections must be recorded in the aircraft maintenance records showing the following or a similarly worded statement: "I certify that this aircraft has been inspected on (insert date) in accordance with the scope and detail of 14 PROT646 part 43, appendix D, or other FAA-approved programs, and was found to be in a condition for safe operation." The entry will include the aircraft total time-in-service, and the name, signature, certificate number and type of certificate held by the person performing the inspection. 24) If aircraft, engine, or propeller operating limitations are exceeded, an appropriate entry will be made in the aircraft records. 25) This aircraft must not be operated unless it is maintained and inspected in accordance with the requirements of 14 PROT647 Part 43. 26) This aircraft must display the word EXPERIMENTAL in accordance with 14 PROT648 §45.23(b). 27) The pilot-in-command of this aircraft must notify Air Traffic Control of the experimental nature of this aircraft when operating into or out of airports with operating control towers. The pilot in command must plan routing that will avoid densely populated areas and congested airways when operating VFR. 28) This aircraft does not meet the requirements of the applicable, comprehensive and detailed airworthiness code as provided by Annex 8 to the Convention on International Civil Aviation (ICAO). The owner/operator of this aircraft must obtain written permission from another country's Civil Airworthiness Authority (CAA) prior to operating this aircraft in or over that country. That written permission must be carried aboard the aircraft together with the U. S. airworthiness certificate, and upon request, be made available to an FAA inspector or the CAA in the country of operation. 29) Aircraft instruments and equipment installed and used under 14 PROT649 §91.205 must be inspected and maintained in accordance with the requirement!: of parts 14 PROT650 parts 43 and 91. Any maintenance or inspection of this equipment must be recorded in the aircraft maintenance records. 30) Application must be made to the geographically responsible MIDO (Cleveland, OH MIDO) for any revision to these operating limitations. 31) 14 PROT651 § 47.45 requires that the FAA Aircraft Registry must be notified within 30 days of any change in the aircraft registrant's address. Such notification is to be made by submitting Aeronautical Center Form 8050-I to AFS-750 in Oklahoma City, Oklahoma. 32) Condition inspections must be performed in accordance with 14 PROT652 part 43, appendix D at least every 100 flight hours. The inspections must he performed by an FAA-certificated mechanic with appropriate ratings as definntl in 14 r.pp x dl PROT326 PROT327 EXPERIMENTAL OPERATING LIMITATIONS PURPOSE MAKE Corn . any MODEL 400A REGISTRATION N493LX SERIAL NUMBER RK244 Page 3 of 3 33) Familiarization flights must be conducted only over sparsely populated areas. If aerobatics are involved, the applicant must inform the local FAA office and additional limitations may be imposed as necessary. III. DARF-400148-CE May 20.2013 igna u e PROT328 PROT329 Quality Assurance Department To: Flight Standards District Office North Olmsted, Ohio 44070 From: Date: May 13, 2013 Director of Quality Assurance Subject: FAA Program letter for Beech Jet 400A, Serial number RK244, Registration Number N493LX Ref: FAA order 8130.2G 1. Registered Owner: Flight Options RC . Address: 2. Aircraft Description: Twin Engine Light Jet a. Registration: N493LX b. Aircraft Builder Raytheon Aircraft Co c. Year mfg.: 1999 d. Aircraft Serial Number: RK244 e. Aircraft Model Designation: Beech let 400A 3. The program purpose for the aircraft will be used To complete the flight performance profile in Research & Development Category in support of FAA Project SA 15250LA-T (Replacement of Wingtips) 4. Program Duration a. List the estimated flight hours required for program: 300 Hrs b. Number of flights: 100 c. Number of days: 180 S. Describe the areas over which the flights to be conducted and address of base operation: The base of operation is Cuyahoga County Airport, 355 Richmond, Cleveland, Ohio. Flights will be conducted in North America. 6. Describe the aircraft configuration: This Aircraft is a standard Beech Jet 400A with new Williams F144-3AP engines and upgraded avionics with full authority digital engine controls (FADEC) a. Maintenance Program 1. Hawker Beechcraft Maintenance Manual Chapter S Rev C22 or later with the exception of the 1T150 Engines. 2. Williams International recommended F144 3A Maintenance manual (FADEC maintenance is covered in 71-00-00 of this manual) 3. Maintenance Requirements for the Throttle Quadrant is addressed in the instructions for Continued Airworthiness on the F144-3AP STC. enior Inspector PROT330 PROT331 LOG BOOK ENTRY from Designated Airworthiness Representative (DAR) REGISTRATION NUMBER AIRCRAFT MAKE/MODEL SERIAL No. TT/TSN LANDINGS/CYCLES N493LX 400A RK244 8563.8 7115 I find that the aircraft meets the requirements for the certification requested and have issued a Special Airworthiness Certificate dated May 20, 2013 for the purpose of Research and Development. Limitations dated May 20. 2013 and issued with this certificate must be complied with. The aircraft must be maintained in accordance with manufacturers requirements unless another FAA approved maintenance program is utilized. Issuance of this certificate does not eliminate or replace any required maintenance requirements. The Special Airworthiness Certificate has been issued as required to support Research and Development flight-testing as defined in th app icant's program letter. The Standard Airworthiness Certificate dated R 19p111999 has been superseded. 4/5/ 20 2.013 Date PROT332 PROT333 le u 5 Oesenrnont or Trantpeeltavan lAcINal Aviation Achninilanakai Foon Soo/own OW) No 2120-0O20 itsodusi INSTRUCTIONS: Print or type all entries. See FAR 43.9. FAR 43 Appendix B, and AC 43.91 (or subsequent revision thereof) for instructions and disposition of this form. This report is required by law (49 PROT653. 1421). Failure to report can result in a civil penalty nor to exceed 51.000 1. Aircraft NatiOnality and Registration Mark N493LX Serial No RK-244 Make model 400A Series 2. Owner Name (As Shown on registration certificate) Flight Options .11O Ancireas cry Richmond Heiohts slew OH z,,, 44143-14 Country USA 4. Type S. Unit Identification Repair Alteration Unit Make Model Serial Number 0 El AIRFRAME (AS described in Item I above) CI O POVVERPLANT K O PROPELLER O O APPLIANCE Type tasrvisaune A. AgenCYS Name and Address Et Kind of Agency Nanny I Armrest Cq Cleveland sure. OH zu 44143.1453 Country USA O U.S. Cenelicated Mechanic O Manufacturer O Foreign Certificated Mechant 0 CRS # 25NR667B O Certificated maintenance Organization D. I certify that the repair and/or alteration made to the unit(s) Identified in item 5 above and descnoed on the reverse or attachments hereto have been made in accordance with the requirements of Part 43 of the U.S. Federal Aviation Regulations and that the information per 14 PROT654 Part 43 APP. B 0 05/30/2013 Pursuant to the authority given persons specified below, the unit identified es in item 5 was inspected in me manner prescribed by the APPROVED 0 REJECTED BY Inspector Manufacturer I Person Apart/wed by Canadian FM Designee Other Specify) Certificate or CRS # 25NR667B 05/30/2013 PROT334 lb PROT335 NOTICE Weight and balance or operating limitation changes shall be entered in the appropriate aircraft record. An alteration must be compatible with all previous alterations to assure continued conformity with the applicable airworthiness requirements. (If more space is required, attach additional sheets. Identify with aircraft nationality and registration math and date work completed.) N493LX Nationality and Registration mark Part I of 3 The Following Equipment was removed along with Associated Hardware. 05/30/2013 EFD-871 622.9345-203 Electronic Flight Display EFD-871 622.9345.203 Electronic Flight Display MFD-871 622.9434.213 Multi Function Display ICU-85 622-6189-002 Internal Compensation Unit ICU-85 622-6189-002 Internal Compensation Unit AHC-85E 622.9336-400 Attitude/Heading Computer AHC-85E 622-9336-400 Attitude/Heading Computer SDU-640B 622-9735-001 Sensor Display Unit SDU-640B 622.9735-001 Sensor Display Unit DCP-5000 822-1028.011 DCP-5000 822-1028.011 ARP-851 622.9500-011 Altitude Reference Panel ARP-851 622.9500-011 Altitude Reference Panel AAP-851 822-0328-011 Altitude Awareness Panel AAP-851 822.0328.011 Altitude Awareness Panel CHP-850 622-7397-002 Course Heading Panel DBU-4100 822-0014-002 Data Base Unit DAU-650 622-9344.101 Data Acquisition Unit SDD-640A 622-9347-001 Sensor Display Driver IOC-4000 ( 4) 622-9814-514 Card Assembly MDC-4000 622-9818-751 Maintenance Computer CSU-4000 (2) 822-0049-002 Configuration Strapping Unit FMC-5000 (4) 822-0891-008 Flight Management Computer PWR-4000 (4) 622.9945.021 lAPS Power Card GPS-4000 822-0931-003 GPS Receiver Mounts 622-9430-002 EFD /MFD Mounts EFB Electronic Flight Bag Mounting 0 Additional Sheets Are Attached Date Form 337 (10.C6) PROT336 PROT337 NOTICE Weight and balance or operating limitation changes shall be entered in the appropriate aircraft record. An alteration must be compatible with all previous alterations to assure continued conformity with the applicable airworthiness requirements. (If more space is required, attach additional sheets. Identify with aircraft nationality end registration mark and date work completed.) N493LX 5/30/201 Page 2 of 3 Installed the Following Equipment along with Associated Hardware. Date Model Part Number Description Weight Arm CCP-3000 822-1746.002 Cursor Control Panel 2.60 90.0 CCP-3000 822-1746-002 Cursor Control Panel 2.60 90.0 DCU-3001C 822-2362-003 Data Concentrator Unit 5.0 325 DCU-3001C 822-2362.003 Data Concentrator Unit 5.0 325 ECU-3000 822-1200-209 External Compensation Unit 0.40 57.5 ECU-3000 822-1200.209 External Compensation Unit 0.40 57.5 FSU-5010 822.1543.101 File Server Unit (1° IFIS) 6.5 60.83 ECU-3000 822-1200.998 File Server Unit (1st IFIS) 0.40 57.5 AFD-3010E 822-1753.416 12.90 89.2 AFD-3010E 822-1753.416 12.90 89.2 AFD-3010E 822.1753-416 12.90 89.2 AFD-3010E 822.1753-416 12.90 89.2 IMT-3010 822-1140-401 4.40 85.0 INIT-3010 822-1140-401 4.40 85.0 IMT-3010 822-1140-401 4.40 85.0 IMT-3010 822-1140-401 4.40 85.0 10852801Y00 Fuel Quantity Conditioner 0.90 324 PC920-2A2000PH-2A1 Fuel Flow Conditioner 1.10 325 GPS-4000S 822-2189-004 GPS Receiver 6.0 37 CI 429-410 GPS Antenna 1.0 166.14 Amp Cluster N241100-002 DC Voltmeter 1.5 97.4 [SSN REDACTED]-1 Speed Switch (2) 0.25 89.2 DBU-5010E 822-3000-202 Data Base Unit 1.60 134.5 PS-8350 501-1228-004 Power Supply 12.5 52.9 MMT-5000 822-1811-003 File Server Unit Rack 0.30 57.5 MMT-3010 (2) 822-1290-003 AHS Mounting Rack 1.80 57.5 XM WR-1000 822-2031-002 XM Weather 1.5 41.0 CHP-3010 822-1280-003 Course Heading Panel 1.30 92.5 Options Configuration Module. OCM-4100 822-1463.228 WAAS/LPV 0.30 57.5 Options Configuration Module. OCM-4100 822-1463-228 0.30 57.5 WAAS/LPV El Additional Sheets Are Attached Form 337 (10.06) PROT338 S PROT339 NOTICE Weight and balance or operating limitation changes shall be entered in the appropriate aircraft record. An alteration must be compatible with all previous alterations to assure continued conformity with the applicable airworthiness requirements. (II more space is required, attach additional sheets. Identity with aircraft nationality and registration mark and date work completed.) N493LX 05/30/2013 Page 3 of 3 Date Model Part Number Description Weight Arm CSU-4100 (2) 822.1364.002 Configuration Strapping Unit 1.60 55.7 MDC-3110 822.1987.006 Maintenance Data Computer 0.80 55.7 FMC-6000 (2) 822.0868.123 Flight Management Computer 1.90 55.7 ADC-850D (2) 822.0389.468 Air Data Computer 5.30 60.83 AHC-3000A (2) 822-1378.001 Attitude Heading Computer 4.80 57.5 DCP-3030 (2) 822-1828-002 1.90 89.96 PWR-4000 (4) 622-9945-022 IAPS Power Card 1.3 55.0 IOC-4100(4) 822-1362-511 Input/output Concentrator 0.8 55.0 LT-4001.010 Master Caution Panel 1.3 87.0 Rev. Panel [SSN REDACTED]-1 Pilot Reversion Panel 0.2 88.0 Rev. Panel [SSN REDACTED]-3 Co-pilot Reversion Panel 0.2 88.0 9-PED [SSN REDACTED]-9 9-Pedestal Panel 1.8 92.89 345.6196 ELT Switch 0.2 88.0 Annunciator led-42-12-BB-E0Y47 AUX BATT (1/2) Annunciator 0.05 88.0 Annunciator (2) Led-40-18-BB-E0Y45 Pull Up/ Terrain Annunciator 0.05 88.0 Annunciator 24840231 Terrain Inhibit/ Terrain Fail 0.05 88.0 In Accordance with STC ST109595C. See Attached Copy MM Supplement, Nextant Aerospace Doc. No. 373.00-0023 Rev IR Dated 09/02/2011 or later FAA approved revision, installed on Aircraft. Equipment Pilot Guides are Installed in the Aircraft as Portable Document Format (.pdf) via supplied I-Pad. NOTE: Portable electronic devices used to store required aircraft records required by Part 91.9 are considered Electronic Flight Bags (EFB) per FAA Advisory Circular AC 120-768 par 4-g. Commercial operators are required to obtain authorization for their use from their managing Flight Standards District Office. Instructions for Continued Airworthiness (ICA) Ref Nextant Aerospace Document [SSN REDACTED].Rev C or Later are included in the Aircraft Maintenance Records Carried out System Ground Test Plan PAW Master Drawing List (MDL) 373.00.004 Rev C. Carried out Hawker Beechcraft Service Bulletin 34-3431 Reduced Vertical Separation Minimum (RVSM) Airframe Inspection / Modification. Performed FAR 91.411Inspection per Part 43 appendix "E" Pitot Static & FAR 91.413 Inspection per Part 43 appendix "F" Transponder System checks. Form 337 0046) PROT340 PROT341 11,1Ra "lain of Jkinerira Pepartment of Zranspotintion getter:II (Ablation cAbministrution $uppientental 'ape Certificate arletecalei 44.444.4relk• ../fianZies ST I 0959SC Nextant Aeros ace LLC Richmond Heights, Of! 44143 &WOW 44114 ereir 6 414 *WO eie441/444AretiliWIfiedaletede 44 da.M74/4AVO emaneavaaesoa 44-9,4erai 044-454e4arnev• .444ev'O 4wr i"e"-..044. "wan...4 *end 25 ./4,4 Federal Aviation Avast (See Prima 3 and 4 for complete certification basis.) oniadailsc;n4;474,44;ney, Al 6SW ./E0.4. Hawker Beechcraft Corp. ..sgedi 4O0A givertythao rano ntiosYlier Installation of Rockwell Collins Pro Line 21 Electronic Flight Instrument System (EFTS) with Rockwell Collins FMS-6100, Localizer Performance with Vertical Guidance (LPV) approach capability and Universal Avionics Systems Company (UASC) Terrain Awareness Warning System (TAWS) in accordance with Nextant Aerospace LLC Master Drawing List Doc. No. [SSN REDACTED] Revision W, dated March 29, 2012, or later FAA approved version. 24.n.r.gaivm ebuilf;v344.;viu : 1) The installer must determine whether this design change is compatible with previously approved modifications. 2) If the holder agrees to permit another person to use this certificate to alter a product, the holder must give that person written evidence of that permission. . 3) For aircraft equipped with Pratt & Whitney JTISD Engines FAA approved Airplane Flight Manual Supplement, Nextant Aerospace LLC Doc. No. [SSN REDACTED] Revision IR, dated 10/19/2009, or later FAA approved version, is required on board the modified aircraft. erehAe".44 cad a- ar da, 4, AA tryserisslawnetha rim ryl revie AvaLeiArroaoreei why...need envsione tv a kaniaer.44va dale resenr4ht 44144444441454 43rR .4444;s41,44.7494 la; Alevre 4.444.444,4 ./11.404sim4.14n4.4.4a Para eAreeesetm • June 26, 2008 gaze r/e....';w&-.4 October 19, 2009 Paleets...4.10eni: 512/P OrnelleAl : September 26, 2011; April 05,2012 anger, ys ems all g Chicago Aircraft Certification Office (lisle) Any *1 CCCCC Jon of this eertitlwce Jr pleas n0 a1,ON. Or S00 041K AOt Oxe010anp l yllerS. of both. TM Parw 1110.1110.0/1 O is coral lats. n4y aft trans need In neerderee win IM 1.4 . PROT342 0 0 PROT343 ilnifebikafee Of America Pepartment of Zrunsportzation - 1:cberal cAbiation crthntiliistrittion Supplemental `Type Qlertificate (Continuation $lieet) te/ rande, ST I 0959SC rAswenen• October 19.2009 Date Amended; September 26, 2011; April 05.2012 Monlerlavio andrinsetaavki nevrawedi: 4) For aircraft equipped with Williams FJ44-3AP Engines, those engines must be installed under SIC ST0237ILA. 5) For aircraft equipped with Williams FJ44-3AP Engines FAA approved Airplane Flight Manual Supplement, Nextant Aerospace LLC Doc. No. [SSN REDACTED] Revision IR, dated September 2, 2011, or later FAA approved version, is required on board the modified aircraft. 6) Aircraft must have previously qualified for Operations in Reduced Vertical Airspace via: RK- I thru RK- I 17 and RK-I 19 thru RK-I39, Hawker Beechcraft Service Bulletin No. 34.3431. RK-I 18, RK-140 thru RK-224, Hawker Bccchcraft Service Bulletin Nos. 34-3228 and 34-3431. RK-225 thru RK-299, Hawker Beechcraft Service Bulletin No. 34-3431. RK-300 and after as original equipped from Hawker Beechcraft. 7) For aircraft equipped with Universal Avionics Systems Corporation (UASC) TAWS FAA approved Airplane Flight Manual Supplement, Nextant Aerospace LLC Doc. No. [SSN REDACTED] Revision IR, approved March 28, 2012, or later FAA approved version, is required on board the modified aircraft. 8) For aircraft with Collins Proline 21 FMS-6100 LPV Approach enabled FAA approved Airplane Flight Manual Supplement, Nextant Aerospace LLC Doc. No. 373.00-0032 Revision IR, approved March 28,2012, or later FAA approved version, is required on board the modified aircraft. Based on 14 PROT655 §§2 1 .1 15 and 21.101, and the FAA policy for significant changes in FAA Order 8110.48, the certification basis for the Hawker Beechcraft 400A aircraft is as follows: a. The type certification basis for the Hawker Beechcraft 400A aircraft is shown on TCDS Al6SW for parts not changed or not affected by this change. b. The certification basis for the parts changed or affected by this change since the reference date of application, September 29, 2009, is based on TCDS A I6SW and §§ 14 PROT656 Part 25 as shown on page 4 of 4 of this STC. Any ale &&&&& on of rerun Cleo is Duo aneela by a Gn0 of not *needing Si.000. Or inparsonmene Trot OACOOd.no 1 yo00. Or bOth. "a Man 4110.14(10431 PAU 3 of 4 eAGLI This certificate way be cransfyi red f., accordance Win FAA 11.0. PROT344 PROT345 Janda Slake of America Department of Zgransportntion - federal Abiation Atiministration $uppiettuntal 'Type aertificatt (a:Continuation $hnt) gkr4, ViAkanot October 19, 2009 Date Amended: September 26, 2011; April 05. 2012 Based on 14 PROT657 §§ 21.115 and 21.101, and the FAA policy for significant changes in FAA Order 8110.48, the certification basis for the baseline Installation of Rockwell Collins Pro Line 21 Electronic Flight Instrument System (EFTS) with Rockwell Collins FMS-6100 modification was determined to be TCDS Al6SW and the following later regulations: Amda 124-4] 25.771 (a.e) MOORS-23) 25.301; 25.303; 25.581; 25.607; 25.611, 25.773 (aX1X2Xd) Amdt(25-310 25.1309 00(bXeXdflg); 25.1322 Amck.(25-40] 25.901 (b)0X0; 25.1549 (4X6X0 Amd1.125-411 25.1321 (a0(b)(c)(c); 25.1331; 25.1333 Mndt.(25-42) Amd1425-46] Ai/Mt(2544) Amdi.125-721 Am0112540) 25.1501 25.603; 25.605; 25.613; 25.1529 25.307; 25.571. 25.1307 25.1316 25.1329(h) NO; 23.1351 MOM 25.1381; 25.1521 (.Xc); 25.1543 (b); 25.1581; 25.1583 (a) Amdt425.861 Amd1425.901 Amdtl25.91) Amett25-102) Amdt[25.105J 25.305 25.1303 25.561 25.981 (a(6) 25.1585 (o) Amdt425.108) Amdl.(25.109] Amdc.(25-113) Amdi425-1221 Amc11425-1231 25.1325 00 25.1323 (a)(1)(g) 25.869 (aX4); 25.1431 25.1317 (aX6)(e) 25.1353 (aXM Based on 14 PROT658 §§ 21 115 and 21.101, and the FAA policy for significant changes in FAA Order 8110.48, the certification basis for the Collins Proline 21 FMS-6100 with LPV Approach enabled and UASC TAWS was determined to be TCDS Al6SW and the following later regulations: AmattOriginali 25.601. 25.605. 25.609. 25.613.25.1301, 25.1357. 25.1381. 25.1525, 25.1541, 1S.1581 Amdr[24-41 25.771 (a) Amd1.(25-23) 25.301; 25.303; 25.305. 25.307, 25.561(c); 25.607; 25.611. 25.1307 Amdt.(25.381 25.603. 25.1322, 25.1583(O Amdl.(25.401 25.1585 (a) Ainc1i125-411 Aindi.(25-421 Amdt125-46) Amdl.(25-541 Amdt.(25-72) 25.1309 (a)(b)(401)(aXa) 25.1501 25.777(a)(c) 25.1529 25469(a)(1) 25.1351 (a)(1) Amdr(25-102) Amdt.P5-113i A=0(25-1231 25.981(aXb) 25.14310) 25.1353 (aXe) - END - Any &&&&&& On of t • COrtifiene II poniSOSO by • fPM 0f not ontoolling SI.000, or I pti SASS not •44•003n9 3 Hero. or both. FAA Mom 4110.2.1110.401 PS 4 Of 4 SOS Thin cortirIsto My M trensferrod in accordence .ith DA 21.17. PROT346 PROT347 0 U.S OOPWITIAI Of trenwraln-m Naomi Aviation AtIrnialcustron Form Approved omen° 2120-0O20 11/30,2007 INSTRUCTIONS: Print or type alt entries. See FAR 43.9 FAR 43 Appendix B. and AC 43.9-1 (or subsequent revision thereof) for instructions and disposition Of this fOrm. This report is required by law (49 PROT659. 1421). Failure to report can result in a civil penalty not to exceed $1,000 1. Aircraft Nabonality and Registration Mark N493LX Serial No. RK 244 Make Model 400A Series 2. Owner Address CT). slaw. OH zip 4414 -14 Country 4. Type Repair Alteration Unit Make Model Serial Number 0 el AIRFRAME (As described in hem t above) 0 POWERPLANT 0 O PROPELLER 0 APPLIANCE Type stmeeaurer rim. Adores, City Cleveland sta. OH zip 44143-1453 Cotrey USA O IManufacturer 0 CRS # 25NR667B D. I certify that the repair and/or Migration made to the unit(s) identified in item S above and described on the rever e or attachments hereto have been made in accordance with the requirements of P rt 43 of the U.S. Federal Aviation Regulations and that the information per 14 PROT660 Part 43 App. 6 El Signature/Date of Authorized Individ 05/30/2013 Pursuant to the authonty given persons specified below. the unit identified in item 5 was inspected in the manner prescribed by the A P P R O V E D 0 REJECTED BY FM Fit Standards Inspector Manufacturer FAA Designee i Certificate or Designator NO CRS # 25NR667B Signature/Date of Authorized Individu. 05/30/2013 FAA Form 337 0-061 PROT348 PROT349 NOTICE Weight and balance or operating limitation changes shall be entered in the appropriate aircraft record. An alteration must be compatible with all previous alterations to assure continued conformity with the applicable ainvorthtness requirements. (11 more space is required, attach additional sheets. Identify with aircraft nationality and registration mark and date work completed.) N493LX Nextant Aerospace Completed STC # ST02371LA Removed Pratt and Whitney JT15D-5 Series Engines . 05/30/2013 Date Installed the Williams International FJ44-3AP Engines with Full FADEC and Associated Systems in accordance with Nextant Aerospace MDL -NXT-001 Rev IR Dated 08/22/2011 or later FAA approved revisions, and FAA Approved AFM Supplement NXT-1-AFMS Rev IR dated 9/15/2011 of later FAA Approved revisions. Installed Left Engine Part Number. 111000-202 Serial No. 252757 Installed Right Engine Part Number 111000-202 Serial No. 252758 ICA AFM Supplement was installed on Aircraft. Nextant Aerospace Instructions for Continued Airworthiness Document NXT-ICA Rev IR or later FAA accepted revisions are included in the Aircraft Maintenance Records. Carried out Engine Ground Runs and System OPS checks SAW Ground Test Plan 373.00-0024 Rev F. End PROT350 l PROT351 }loath Slake 01,P1merico Pepiirtmettt of "Mri iapnr ha lion - Athena cAb in tint' cainiiiiiistration $uppinnental Tut antificate -4400 fi ST02371LA 97L YlerrAWne.weee'n' Nextant Aeros ace, LLC er4eed /414 tArel /4 jfr o eirtifra/Se e'h/ Fara' /4 Atekheem andeanr44im& erre/fre rrevvtv//temon med.' /4 aewer/41;orvat terthwtevno•°Mad 25* oth -9,7viprzteathiv: -93efideravv. *Certification basis is set forth on Tan A I6SW and continuation sheets 3 and 4. .6:10.4.4101flotet Wee/r/ea/n./Kmres,".. Al 6SW Hawker 13eechcraft 400A Stverfer4kn gam Ylis t refe.wyn. Replacement of Pratt & Whitney JT15D-5 series engine with Williams International F144.3AP engine (TCDS E3GL) with Full Authority Digital Engine Control (FADEC) and associated systems, in accordance with Nextant Aerospace Master Drawing List No.: MDL-NXT-001, Revision IR dated 8/22/2011, or later FAA approved revisions and FAA Approved Airplane Flight Manual Supplement, NXTI-AFMS, Rev IR, dated September IS, 2011 or later FAA approved revisions. Nextant Aerospace, LLC Instructions for Continued Airworthiness document NXT1-ICA, Revision IR, or later FAA accepted revisions must be provided with this STC. Smitrom, anatvraimo.. The installation should not be incorporated in any aircraft unless it is determined that the interrelationship between this installation and any previously approved configuration will not introduce any adverse effect upon the airworthiness of that aircraft. The approval of this modification applies to the above-noted airplane models only. If the holder agrees to permit another person to use this certificate to alter the product, the holder shall give the other person written evidence of that permission. (CONTINUED on page 3) Sot ewhiecalo emal/h arvyralearts riala reufrofis /4 irmajfice twravertraketemaria as elecl teethe Ornrenalreaffireonselerierweverviev a 4werrihthive dale' As ederrot;to evireadeal, ,Arketiteow/c, eyeen Fetrieredfitvideen dgriorriredretheva givenc4flactwiew, 51k4seAunonen.- March 24, 2008 September 27, 2011 .02/4 mti.senvi• ebvemaremi.- frithierriev. (Signature) Manager, Propulsion Branch Los Angeles Aircraft Certification Office (Title) Any eremites? of Mu certificate it punishable by a fine of not tweeting 31,004 or imprisonment not weeding 3 years, or froth. FAA ran 0110-200•441 Pete 1 at 4 .7 du eratferace may Sc transfenvi arronfaure ',nth fillt,27.47. PROT352 PROT353 INSTRUCTIONS: The transfer endorsement below may be used to notify the appropriate FAA Regional Office of the transfer of this Supplemental Type Certificate. The FAA will reissue the certificate in the name of the transferee and forward it to him. TRANSFER ENDORSEMENT Transfer the ownership of the Supplemental Type Certificate Number to (frame of transferee) attains of transfer) Oliallite and lora) (CYcz Shut, and Liptak) from (Name of gran tor)(Trint or type)_ (Address of grantor) Pato kr /al I aft) (plat Pete, end Zip rah) Extent of Authority (if licensing agreement): Date of Transfer: Signature of grantor an ink) Past 2 of 4 PROT354 PROT355 puilrb Auden (Of cAnterirn Prinirltitent of Vint ttoportn tion - gebertil cabintioat cAbmittiotra Non $upplatuntal Ewe Tertificate (Cfontinuation $liget) Afeeenie/< ST02371LA ..Waterrthirm3 ammo/la:ono. loomammeil Nextant Aerospace, LLC, "Installation of Rockwell Collins Pro Line 21," Amended STC ST10959SC, dated September 26, 2011 or later FAA approved revisions is required as part of this alteration. The new Vmca and Vmeg values arc 94 KIAS and 93 K1AS respectively. The new engine minimum rated thrust is 3,031 lb at sea level, flat rated to an ambient temperature of 77°F. Approved engine fuels are: Grade Specification Jet A ASTM-D 1655 Jet A-I ASTM-D 165.5 rerlejeeethewSewth The certification basis for this modification is as follows: The original certification basis for the Hawker Beechcraft Model 400A airplanes identified on TCDS Al6SW, Revision 26, dated March 17, 2010: Part 25 of the Federal Aviation Regulations effective Febmary I, 1965, as amended by 25.1 through 25-40, plus §§ 25.1335, 25.1351(d), 25. I353(cX5), and 25.1447 of Amendment 25.41; §§ 25.29, 25.255, and 25.1353(eX6) of Amendment 25.42; and §§ 25.361(b) and 25.1329(h) of Amendment 25-46. Part 36 of the Federal Aviation Regulations effective December 1, 1969, as amended by 36-1 through 36-17; SPAR 27 effective Febmary 1, 1974, as amended by 27.1 through 27-5; and Special Conditions No. 25-ANM-32 dated Febmary 22, 1990 (High Altitude Operation at 45,000 feet), and Special Conditions No. 25-ANM-33 dated June 18, 1990 (Lightning and Radio Frequency Energy Protection). (Sec NOTE 12) Equivalent Safety Items: (1) Out-of-trim characteristics § 25.255 (2) Pilot compartment view § 25.773033(2) (3) Passenger compartment door § 25.813(e) (4) Emergency exit marking §§ 25.811(d)(1) and 25.811(d)(2) Application for amended Type Certificate dated February 18, 1988. Regulation at a later amendments for components and areas affected by the change (Ref. FAA approved Compliance Check List): Subpart A - General : 25.2(25.99) Subpart B - Flight: 25.207(25-121), 25.255(25.42) Subpart C - Structure: 25.571 (25-96) piny dictation of tfiu marmite is ponisfrabb by a fine of not crow% 31,004 or imprisonment not eventing 3 rue or 6oth. FM roes M20-2110-411 Pete t of a 'MO eategete may fre tmeilerrel tit °creamy with f:P4t21.47. PROT356 PROT357 Nuittb "hilts Of America Pepartment of transportation - geberni ciliation cAbmittistrntion "Sup-plartental Type Certificate (gartfinurdion $ipet) Afeednlei, ST02371LA free4eathen Sera /conk:tam, Subpart D - Design and Construction: 25.603(25.46), 25.605(25-46), 25.611(25-123), 25.613(25-112), 25.625(25-72), 25.832(25-72), 25.863(25.46), 25.869(25.123), Subvert E - Powernlant: 25.901(25.46), 25.903(25-100), 25.951(25.73), 25.961(25-57), 25.981(25-125), 25.994(25-57), 25.997(25-57), 25.1013(25-72), 25.1019(25-57), 25.1021(25.57), 25.1043(25-42), 25.1045(25-57), 25.1091(25-100), 25.1093(25-72, 25.1103(25.46), 25.1141(25-115), 25.1143(25-57), 25.1163(25-57), 25.1165(25-72), 25.1181(25-115), 25.1183(25-101), 25.1185(25-94), 25.1189(25-57), 25.1195(25.46), 25.1203(25-123), 25.1207(25-46). Subvert/ - Equivalent& 25.1301(25-123), 25.1305(25-115), 25.1307(25-72), 25.1309(25-123), 25.1316(25-80), 25.1317(25-122), 25.1321(25.41), 25.1331(25-41), 25.1351(25-72), 25.1353(25-123), 25.1357(25-123), 25.1381(25-72), 25.1431(25-113), 25.1438(25-41), Subpart G - Operating Limitations and Information: 25.1501(25.42), 25.1521(25-72), 25.1527(25- 105), 25.1529(25-54), 25.1543(25-72), 25.1549(25-40), 25.1551(25-72), 25.1557(25-72), 25.1581(25-n), 25.1583(25-105). Subpart H - Electrical Wiring interconnection Systems (EWIS): 25.1701(25-123), 25.1703(25-123), 25.1705(25-123), 25.1707(25-123), 25.1709(25-123), 25.1711(25-123), 25.1713(25-123), 25.1715(25-123), 25.1717(25-123), 25.1719(25-123), 25.1721(25-123), 25.1723(25-123), 25.1725(25-123), 25.1727(25-123), 25.1729(25-123), 25.1731(25-123), 25.1733(25-123). 14 PROT661 Part 34 (34-3): 34.11 14 PROT662 Part 36 (36-28): 36.I--36.7, 36.101-36.105, 36.1501, 36.1581. The following Noxtant Aerospace Continued Airworthiness Supplements are applicable to airplanes modified in accordance with this STC: • Master Minimum Equipment List document No. MMEL Rev. 8, dated 02/21/2011 or later FAA approved revisions. • EWIS (Electrical Wiring Interconnection Systems) Inspection Procedure/Report No. NXTI-EA-007 Rev A dated 8/24/11 or later FAA approved revisions. -END- Any titivation of this entifstote is pintisita64 ky a fine of no ttrutatto $3.000, or imprisonment not to-ceding 3 years, or 6otk ma Foxe 6110.2420.481 Part • 04 4 ihiscertifiSote may 6: tmofertain areortanee with Tfilt,21.47. PROT358 PROT359 420 US Dispartinent at nainert1140 Want Aviation Administration Form Approved OM No 21200020 11/302301 Electorsic Tracking Natter INSTRUCTIONS: Print or type all entries. See Title 14 PROT663 §43.9, Part 43 Appendix B, and AC 43.9-1 (or subsequent revision thereof) for instructions and disposition of this form. This report Is required by law (49 U S.C. §44701). Failure to report can result in a civil penalty for each such violation. (49 PROT664. §46301(a)) 1. Aircraft USA, N493LX Serial No. RK-244 Make RAYTHEON AIRCRAFT COMPANY ICAO AIRCRAFT ADDRESS CODE:51416115 Model 400A Series Not Applicable 2. Owner At:Cross City RICHMONO HEIGHTS State OHIO Le 44143.1453 4. Type 6. Unit Identification Repair Alteration Unit Make Model Serial No. K ril AIRFRAME (As described In Item I above) 0 K POWERPLANT 0 IN PROPELLER 0 K APPLIANCE Type Manufacturer Hem. me U. S. Certificated Mechanic Manufacturer Adams City Blichantica Style NY Cedificated Repair Station DJFA206D rip 13101 USA x D. I certify that the repair and/or alteration made to the unit s) identified in item 5 above and described on the reverse or attachments hereto have been made In accordance with the requirements of Part 43 of the U.S. Federal Aviation Regulations and that the information per 14 PROT665 Part 43 K APP. (3 Signature/Date of rove or 0 0Service Pursue t to the authority given persons specified below, the unit Identified Administrator of the Federal Aviation Administration and Is L in item 5 was inspected in the manner prescribed by the Approved D Rejected BY FAA Fit. Standards Inspector Manufacturer X FAA Designee Repair Station Other (Specify Certificate or Designation No. DJFA 206D Signature/Date of Autho FAA Form 337 rio-os) PROT360 PROT361 NOTICE Weight and balance or operating limitation changes shall be entered in the appropriate aircraft record. An alteration must be compatible with all previous alterations to assure continued conformity with the applicable airworthiness requirements. S. Description of Work Accomplished (If more space is required, attach additional sheets Identify with aircraft nationality and registration math and date work completed.) USA N493LX 4/3/2012 Date Removed EFB Mount Assembly that was previously installed under Engineering Order M25-10/05-011. The aircraft weight and balance has been updated. INSTRUCTIONS FOR CONTINUED AIRWORTHINESS: None AA Form 337 no-as END PROT362 PROT363 1 NATIONAUTY AND 2 MANUFACTURER AND MODEL 3 AIRCRAFT SERtAL 4 CATEGORY Raytheon Aircraft Co. N493LX 400A RK -244 Transport REGISTRATION MARKS NUMBER 5 AUTHORITY AND BASS FOR ISSUANCE Thy almorthIrtess terra la Issued pursuant to Coi Federal /widen Act of1 958 end coreDea that. as of Ihe dabs of tuuance. the Omit to ittah Issued has been Inspected end toad to =don to Ou type corticate Nervfot, to Debt:I:neon for sate operettas end has been ahem to meet the 13(grernents of the appkable comprehensive end detailed atm.:stings' code seen: toed by Marox no the Convandon on ~aeon& tDMI Avtatkai. except es noted herein. ecoepeons: None 5 TERMS MD CONDMONS Unless *toner riumerared, stoponded. mob& or e torrnhattri date Is °View» oatab i by ITO Attnertseator, this idnecelhbeta Cereksto ta effectNe es Iona as the mal pre-rental:ye rnatitamance, and alterallona are performed In accordance oil Parts 21. 43. end 91 of the Foam: Airtet)on Redutothra te. and the a-YtTelbrotl-ktared h Pe Ulled Stem. DATE OP ISSUANCE R 10/01/1999 AEA -FSDO -23 My ~an norcducart. or raw of Cia cerCt•uu may he swittable Dye Pie sol escorstsp 11,000 a bralkeresnt nut n¢eedh+p3 ras or tat THIS CERTIFICATE aftt8T 88 DISPtAYED N THE AIRCRAFT P4 ACCORDANCE WITH APFUCABLE FEDERAL AYIATION REGULATIONS. FAA Form 81004 (3-08) PROT364 II 4 PROT365 ENGINEERING ORDER Aircraft Type Aircraft Number Serial Number Station Engineering Order Number M25-10/05-011 Revision Numbe Original Date 10-19-2005 Page 1 of: 1 E NG I NE ER I NG ORDE R T I TL E Electronic Flight Bag Mount Installation - Beechjet 400 Fleet Effectivity: Description: Accompanying Documents:. Aircraft serial numbers RK-123 and after To install a fabricated mount assembly near the co-pilots map light rheostat to hold the electronic flight bag computer Work Compliance Instructions Form. DER approved Engineering Directive EDW01-5. FAA forms 337 and 8110-3, For the effective aircraft to obtain a paperless cockpit environment Reason: Prepared By Keith Gawsyszawski Quality Assurance Robert Beaumont Approved By Todd Hattaway Regulat • ry Compliance Date 10-19.2005 Date ;eta Date Major Repair K Minor Repair FAA Approval (E) Yes K No Weight & Balance Affected (E) Yes K No Weight 4 lb increase Arm 108 Parts Required Yes, FG3500-400N, EFB mount assembly, 4 each AN3-5A bolts, 4 each NAS1149F0363P washers, 1 each -[ADDRESS REDACTED]awings Required Yes, 1175TA, rev A. 5245D, rev B, 5244FC, rev B (included in the Engineering Directive) Publications Affected Equipment List Update K yes 18) No RVSM Status Affected None K Yes No AD List Affected K yes No Estimated Cost $176.00 Estimated Labor Hours 4.0 hours Distribution Remarks I References Z000000 Maintenance Planning Maintenance Quality Assurance Operations Procurement Aircraft Manufacturer The planning department shall add this EO to a scheduled work order whenever an effective aircraft is located at one of the Raytheon dedicated maintenance facilities and adequate down time permits. Priority Code (check all that apply) K Urgent IZ Mandatory K Attrition FO-09 GMIVI Revision 1 0912005 PROT366 PROT367 .i sirr iZadrizia WORK COMPLIANCE INSTRUCTIONS Page: Aircraft Number: Station: Work Order # Effectivity 1 of 2 RK-123 and after 0 Enginee ing Order Number: M25-10/05-011 OR 0 Fleet Campaign Directive Number: T I T L E Electronic Flight Bag (EFB) Mount Installation Procedures For Flight Options, LLC., Beechjet 400A's Item Work Description Mechanic Inspected 01 Document the maintenance action on a Flight Options maintenance transaction report form FO-501 with the following statement in the discrepancy side: 'Accomplishment of Flight Options EO M25-10/05-011 Installation of the Electronic Flight Bag, FG3500 mount assembly is due' 07 Remove electrical power from aircraft and disconnect main aircraft battery. 03 Loosen the upper glare shield and right side cover (which contains the reading fight and air-cell phone assemblies) by removing the mounting screws and separating the Velcro strips. 04 Remove the three screws and 90 degree cover panel form the aft edge of the right side cover panel and discard. cr 05 With the glare shield and right side cover disconnected, locate the pre- existing fastener holes located on the shelf just below the copilots windshield and temporarily install the Electronic Flight Bag (EFB) mount assembly using the four AN3-5A bolls and NAS1149F0363P plain washers (included In the kit) to the pre-existing fastener holes. Snug but do not tighten bolts at this time. a rtt 06 Adjust the position of the EFB mount assembly to provide sufficient clearance between the existing ashtray and the EFB mount thumbscrew. - 07 When proper clearance Is achieved in step five. (thumbscrew does not touch the ashtray when rotated), tighten mounting bolts to 22 to 28 inch pounds (AMM Chap 20). 08 Reinstall the right side panel. Trim the aft edge of the panel as necessary to provide clearance between the panel and the 1175TA bracket, as identified in engineering Directive EDW01-5, figure 2, on page 3. Trim leather covering as necessary and secure with adhesive (contact cement or equivalent). e 09 hn. Verify condition of Velcro on the upper glareshield and right side panel for proper security. Secure as necessary. 10 Install the EFB computer (Fujitsu) into the holder bracket. ".. ?am 11 With the EFB mount installed, loosen the thumbscrew knob on the mount assembly % to one full turn maximum (do not allow the lioldlt arm to separate from the mechanical stop pin In the drawing number 1175 mount bracket). 12 With the EFB mount assembly arm loose; verify the co-pilots control column and wheel does not come in contact with the EFB mount assembly using the following procedure: Perform this task by moving the control column full travel forward and aft and rotating the control wheel full left and right while also rotating the EFB mount assembly in all possible configurations. Verify that the EFB mount assembly does not make contact with any part of the control yoke and wheel. If contact does not occur, proceed to step 17 and N/A and initial blocks 13 through 16. Form Completed By: Date: Log Page: F0-10 GMM Revision 1 0912005 PROT368 PROT369 .. ---... nrcria WORK COMPLIANCE INSTRUCTIONS Page. Aircraft Number. Station: Work Order # Effectivity 2 of 2 RK-123 and after El Engineering Order Number: M25-10/05-011 OR 0 Fleet Campaign Directive Number: T I TLE Electronic Flight Bag (EFB) Mount Installation Procedures For Flight Options, LLC., Beechjet 400A's Item Work Description Mechanic Inspected 13 If contact occurs, remove the mount assembly 'Hold-It' arm, identified in figure 2 of engineering directive EDW01-5, page 3, by completely removing the thumbscrew. Take note not to lose the wedge shaped bushing located in the eye of the 'Hold-It' ann which supplies the locking feature of the mount assembly. 14 Locate the small Allen type set screws and adjust as necessary to move the arm towards the more vertical position. Make''/. turn adjustments at a time. 15 Reinstall the 'Hold-Ir arm assembly, taking note to install the wedge bushing with the tapered end first into the eye of the arm assembly and tighten the thumbscrew. Caution: Make sure the mechanical stop pin located on the drawing number 1175 mount bracket fits within the machined slot on the inside part of the eye portion of the "Hold-It' arm assembly. 16 Repeat steps 10 through 14 until proper clearance between the control yoke and the EFB is achieved. 17 After the final adjustments are made to the Allen type set adjustment screws, apply a small amount of Loctite 242 to the screw threads to secure from loosening. 18 Resecure the upper glareshleld to the right side panel by reinstalling the mounting screws and resecurinq the Velcro strips. 4 i- 19 Attach the power plug to the EFB computer. .4 20 Install the fabricated '-11' placard as stated in the engineering directive EDW01.5, page 2, to the right cockpit side wan panel just below the side window. 21 Reconnect the main aircraft battery. Secure as necessary. 22 Complete the corrective action side of the Flight Options aircraft maintenance transaction form FO-501 with the fonowing statement: 'Complied with Flight Options EO M25-10/05-011. installation of the Electronic Flight Bag assembly FG3500-400N in accordance with DER approved Engineering Directive EDW01-5, see FM form 8110-3 dated 8- 12-05 and Flight Options Work Compliance InsDuchene. ri." ;As,• 23 Complete the accompanying Engineering Directive checklist on page 2 and the previously FM field approved form 337 by completing blocks 6 and 7 in its entirety. When completed, forward one copy of the 337 and the complete Engineering Directive package and Form 8110-3 to the 'Duality Assurance Department in Binghamton. New York and one copy of the FM form 337 and 8110-3 to the local Flight Standards District Office via US mail within two business days after completion of the installation. - END - 7414 t, . ili'C.: t Form Completed By: Date: Log Page: FO-10 OMM Revision 1 09/2005 PROT370 PROT371 0 US Ciepailmant al WardpOrtalion Fodor& Aviation Administratinn rovoti Form Aw OMB No. 2120-C020 I U30/2007 E isaron'c 'finking Number or FAA Us* Only INSTRUCTIONS: Print a type di entries See Title 14 PROT666 §43.9, Part 43 Appendix B. and AC 43.9-1 (or subsequent revision thereof) for instructions and disposition of this form. This report is required by law (49 U S.C. §44701). Failure to report can result in a civil penalty for each such violation. (49 PROT667. §46301(a)) 1. Aircraft N493LX Serial No. RK-244 Make HAWKER BEECHCRAFT CORP Model BEECHJET Series 400A 2. Owner Name (As shawl on registration certificate) SHMITKA AIR INC SOUTHEASTERN MILLS INC IT AL AddreSS (As shown on registration certificate) Marta Oty Fddwriond itakifits Sale OH rip 14142.1453 County USA 4. Type Repair Alteration Unit Make Model Serial No. Er. O AIRFRAME 0 POWERPLANT ill III PROPELLER Ill K APPLIANCE Type Manufacturer Mn kkaki O00ons. U.0 U. S. Certificated Mechanic I Manufacturer Aden, 27 Umr 0utr•Stito II Foreign Certificated mermanc Cky Mara Stow NY DJFA206D rip 13104 Corny USA PC Cenificaled maintenance Organization D. I certify that the repair and/or alteration made to the unit s) identified in item 5 above and described on the reverse or attachments hereto have been made in accordance with the requirements of Part 43 of the U.S. Federal Aviation Regulations and that the information per 14 PROT668 Part 43 App. B 7. Approva or Return to Service Pursuant to the authority given persons specified below, the unit identified in dem 5 was inspected in the manner prescribed by the Approved EiRejected BY FAA Fit. Standards Inspector Manufacturer X FAA Designee Repair Station FLIGHT OPTIONS 135 AIR CARRIER CERTIFICATE Certificate or Designation No. DJFA 206D FAA Form 337 poem PROT372 NOTICE Weight and balance or operating limitation changes shall be entered in the appropriate aircraft record. An alteration must be compatible with all previous alterations to assure continued conformity with the applicable airworthiness requirements. B. Description of Work Accomplished (If more space is required, attach additional sheets. Identify with aircraft nationality and registration mark end date work completed.) USA N493LX SN-244 4/11/2011 Date REPAIRED LEFT FUSELAGE SKIN ABOVE PYLON IAW US TECHNICAL EO6110 227227. 8110-3 DATED MARCH 27, 2011. (WORK ORDER # 227277 SQ-208) WEIGHT AND BALANCE NEGLIGIBLE INSTRUCTIONS FOR CONTINUED AIRWORTHINESS: FOLLOW NORMAL MAINTENANCE PRACTICES FOR THE LT AFT FUSELAGE SKIN ASSEMBLY REPAIR AS CALLED OUT IN THE BEECHJET 400A MAINTENANCE MANUAL [REDACTED]UXXXXX)OOOO([REDACTED])O([REDACTED]JOOOOO([REDACTED]YJCXXXXXX PROT373 0 US OlOattnienl or litany:anew Administration Fenn Approved OW) No. 2120-CO2O itiPlarit7 Searle Tracking Number Fee FAA Unlit* INSTRUCTIONS: Print or bre all fl ies. See Title 14 PROT669 §43.9. Part 43 Appendix B. and AC 43.9-1 (or subsequent revision thereof) for instructions and disposition of this form. This report is required by law (49 PROT670. §44701). Failure to report can result in a civil penalty for each such violation. (49 PROT671. §46301(a)) N493LX Serial No. RK-244 Make HAWKER BEECHCRAFT CORP Model BEECHJET Series 400A 2. Owner SHMITKA AIR INC SOUTHEASTERN MILLS INC ET Al Mani City Itrearnand Heights Stale OH Zip 4042.1453 County USA - 4. Type - - Repair Alteration Unit Make Model Serial No. B e O AIRFRAME 0 O POWERPLANT 0 0 PROPELLER 0 O APPLIANCE Type Manufacturer A Agency's Name and Address Notre Fitoctivent tic U. S. Certificated mechanic I Manufacturer Address 27 SWOOP. Subs Foreign Certificated mechanic City Einonsonn SW* NY - DJFA206D Vp 13104 Corny USA D. I certify that the repair and/or alteration made to the unit s) Identified In item 5 above and deserted on the reverse or attachments hereto have been made in accordance with the requirements of Part 43 of the U.S. Federal Aviation Regulatio s and that the information per 14 PROT672 Part 43 App. B it 7. Appro for Return to Service Pursuant to the authority given persons specified below, the unit identified in item 5 was inspected in the manner prescribed by the KApproved :7 :Rejected BY Inspector Manufacturer X FAA Designee Repair Station FLIGHT OPTIONS 135 AIR CARRIER CERTIFICATE FAA Form 337 riootR PROT374 NOTICE Weight and balance or operating limitation changes shall be entered in the appropriate aircraft record. An alteration must be compatible with all previous alterations to assure continued conformity with the applicable airworthiness requirements. (If more space is required, attach additional sheets. Identify with aircraft nationality end registration mark and da e work completed.) USA N493LX SN-244 3/8/2011 Date REPAIRED LEFT ELEVATOR IAW US TECHNICAL EO5770 226648. 8110-3 DATED APRIL 19 2010 (WORK ORDER # 227277 SQ-97) WEIGHT AND BALANCE NEGLIGIBLE INSTRUCTIONS FOR CONTINUED AIRWORTHINESS: FOLLOW NORMAL MAINTENANCE PRACTICES FOR THE ELEVATOR AS CALLED OUT IN THE BEECHJET 400A MAINTENANCE MANUAL [REDACTED])0000000([REDACTED]W)000000([REDACTED]WXX PROT375 el US Coco lfr as-lent ct TransP0nEOP Fedora, Aviation Administration Form Approved ore No. 2129.0320 I 1/30r2037 Flectonic Tracking Nome For FAA Use CMly INSTRUCTIONS: Print °inn: all Writs. See Title 14 PROT673 §43.9, Part 43 Appendix B. and AC 43.9-1 (or subsequent revision thereof) for instructions and disposition of this form. This report is required by law (49 U S.C. §44701). Failure to report can result in a civil penalty for each such violation. (49 PROT674. §46301(a)) 1. Aircraft N493LX Serial No. RK-244 Make HAWKER BEECHCRAFT CORP Model BEECHJET Series 400A 2. Owner SHMITKA AIR INC ET-AL SOUTHEASTERN MILLS INC C/0 FLIGHT OPTIONS LW ASCENT I I LW PRIME TIMEASSOCIATES LIC Addma ca Renmore Hoehn Shoo ON Zip 44142.1451 Country USA 4. Type Repair Alteration Unit Make Model Serial No Er AIRFRAME K POWERPLANT 0 PROPELLER El O APPLIANCE Type Manufacturer Name Flirt (Mims. LLC U. S. Certificated Mechanic I Manufacturer Addams 27 Link Din Suite a city a no/WNW Sur NV Certificated Repli' Station DJFA206D Zas 13604 Cony uta X D. I certify that the repair and/or alteration made to the unit s) Identified in item 5 above and described on the reverse or attachments hereto have been made in accordance with the requirements of Pan 43 of the U.S. Federal Aviation Regulations and that the information per 14 PROT675 Part 43 App. B Signature/Date of Authorized IndiVidual /49 "'' I 9 -.26 /e) . pprova r eturn to Service Pursuant to the authority given persons specified below, the unit identif . in item 5 was inspected in the manner prescribed by the Approved - LRejected BY Inspector Manufacturer X Department Transport FAA Designee Repair Station FLIGHT OPTIONS 135 AIR CARRIER CERTIFICATE Certificate or Designation No. DJFA 2O6D Si nature/Date of Authorized Individual FAA Form 337(,008) PROT376 NOTICE Weight and balance or operating limitation changes shall be entered in the appropriate aircraft record. An alteration must be compatible with all previous alterations to assure continued conformity with the applicable airworthiness requirements. (If more space is required, attach additional sheets. Identify with aircraft nationality and registration mark and date work completed.) USA N493LX SN-244 10/19/2010 Date SUBSTITUTED FASTENERS IN H-STAB LOWER SKIN PER EO5938 2272771FAD FROM US TECHNICAL 8110-3 DATED 10/18/2010 WEIGHT AND BALANCE NEGLIGIBLE INSTRUCTIONS FOR CONTINUED AIRWORTHINESS: NORMAL MAINTENANCE PRACTICES FOR THE HORIZONTAL STABILIZER ASSEMBLY AS CALLED OUT IN THE BEECHJET 400A MAINTENANCE MANUAL [REDACTED]W[REDACTED] PROT377 0 US Department otTrwnocnaton Administration form Approved ORD No. 21204020 2/20/2011 ElettfOtt Tracking lOwnber For FAA Ustionly INSTRUCTIONS: Print or type all entries. See Title 14 PROT676 §43.9. Part 43 Appendix B. and AC 43.9-1 (or subsequent revision thereof) for Instructions and disposition of this form. This report Is required by law (49 PROT677. §44701). Failure to report can result in a chill penalty for each such violation. (49 PROT678. §48301(a)) 1. Aircraft USA N493LX Serial No. RK - 244 Make Model BEECHJET Series 400A 2 Owner AIR GHISLAINE INC SOUTHEASTERN MILLS INC ASCENT II LLC Address As shown on : • istration certificate) Address Co RICHMOND HEIGHTS stale OHIO PAP 44143-1453 Canto USA 4. Type Repair Alteration Unit Make Model Serial No. III ig AIRFRAME (As descnoed in Item 1 above) O POWERPLANT In In PROPELLER D Et APPLIANCE Type manufacturer A Agency's Name and Address Nam Fl IGHT OPTIONS I I C U. S Certificated Mechanic I Manufacturer mew 27 LINK DRIVE SUITE B tab' niNSHAPiATON ewe NY Certificated Repair Sleben DJFA 206 D rs. 13904 Cowry USA D. I certify that the repair andlor alteration made to the unit(s) Identified in item 5 above and described on the reverse or attachments hereto have been made in accordance with the requirements of Part 43 of the U.S. Federal Aviation Regulations and that the Information furnished herein is true and correct to the best of my knov.ledge. Signature/Date of Authorized Individual per 14 PROT679 Part 43 App. B et 0 Pursuant to the authority g ten persons specified below, the unit Identified E in item 5 was nspected in the manner prescribed by the Approved D Rejected BY Inspector Manufacturer 1 I Department 0 Transport FAA Designee Repair Station Certi icate or Designation No DJFA 206 D Signature/Date of Authorized Individual a-7-)/0 orm 377 .10 55; PROT378 PROT379 NOTICE Weight and balance or operating limitation changes shall be entered in the appropriate aircraft record. An alteration must be compatible with ail previous alterations to assure continued conformity with the applicable airworthiness requirements. al more space is required, attach additional sheets. Identify with aircraft nationality and registration mark and date work completed.) USA N493LX FEB 04 2010 Oate ACCOMPLISHED INSTALLATION OF MAIN LANDING GEAR HEAT SHIELD COVER KIT 128-1002-0001 SERIAL NUMBER 137 AS DESCRIBED IN ENGINEERING ORDER EO M32-10/08.023. ALL WORK ACCOMPLISHED I/ANV HBC MAIN LANDING GEAR HEAT SHIELD COVER KIT 128-1002-0001 SERIAL NUMBER 137 AND ENGINEERING ORDER M32-10/08-023 REV. A DATED 11-13-08. WEIGHT AND BALANCE NEGLIGIBLE. INSTRUCTIONS FOR CONTINUED AIRWORTHINESS: INSPECT THE HEAT SHIELD BLANKETS AND COVERS IIIVW FLIGHT OPTIONS INSPECTION PROGRAM OR THE MANUFACTURES INSPECTION PROGRAM AS APPROPRIATE. END D Additional Sheets Are Attached FAA Form 337 mum PROT380 PROT381 («TED STATES OF AMERICA 1 NATIONALITYAND REGISTRATION MAWS 111:4931:: 2 MANUFACTURER AND MCGEE .ty, !"`1':-47 -:err.: '7'. Co. ga; 3 ~CRAFT SERIAL NUMBER 4 CATEGORY Tgre-rnert 6 AUTNORRY MID BASIS FOR ISSUANCE Thlo brontroas retkable hand pinuudbEls fornrrironAd of 1968 old corm est r of be fa of 199Ancr MINN90 broth hard hoe Os Imp~ anl MUM Enna:tom lo Ty bee torkslo ~doh b to In carbon for SO ~Or hoe alin area b mul81. niquIrsenb WIN opplerbo comprobonota and Ward otroptroo4 cor r pro0040 by Ara • b iho Oserflon on Irdonoronal cm AS «CS as ~el barb Escloptiort Hon? 8 TERMS AND CONDITIONS Unkba agnet aunendaried. aulpengeO, molted. Or a twolnation dab O WfrMls inee•••• by the Admlniatrator. INY alreenfleona or!~ aaata4r long at 034 ~Manna maintenance, and snore am pertonned n accorbanba Win Pans 21. 43. and 91 of Po Fodor Aviation Reauttgona, ond M olfcrtalrmrlorocl b M United SUS GATE OF ISSUANCE 10/01/199? FM RE DUE Any Sen. ogeOduCtlan. Or gang he 401~» may ba puNYlYN by • Ina not nogg% 11.000 r Saber ant eg ~gang 3 yearn r toet. THIS CERTIFICATE MUST BE °GRATED N THE ~RIFT IN Arymanobt WITH APPLICABLE FEDERAL AVIATION REGULATIONS MA Fans 81004 (308) uml ED STATES OF ~RICA DEPART MENT OF TRANSPORTATION - FEDERAL AVIATION ADMINISTRATION I. IMTIDNALITYNIp OBECOSTRATION MARRS 2 144NUFACTUREA AMR MODEL 3 AmicstArr SCRIM. CATEGoar N79STA 400A RK-244 TRANSPORT `5 to' AUTHORITY AND OASIS FOR ISSUANCE orronrnerartralo earl Purina& to Ina Fang& AnatOn Act ot ItiSS IMO Cowles g Maciata Col alumna& Wm area fa *fin ogre hag son .rtypeaod and hawk] IQ contotre to Me NO* 4:011.1•414 urofoc lo Is In conenon 10f se OINC•140^ and has Ow Won a root IM tIlOv.~1,13 Of ins sortie cornAssAansoye an0 0415380 sonhos coco worry by 41•1•11110 ow Corson on Ingenabonal Crra AnanOn. agog r •04•0 Pina ~MOM NCNE 6 Trim 5n0 CONORGNS onto moons .1NO 4I•3 01 • usmånaton 0411.4 Olhers.•• egubt.shee by Its Aenianraglet 11u• 0 oink. as kw, do the mentenanCe• 13•••rontam• mantanarc• ono imenorni all 0•00•1141d an ~nip ••••••••••• görg70,71bani cen.scate I.CCOrSDAC•wel•••fll 1 43 analll ot ma agatwarAnabon oproonT goo/psis and In* Won fl196~1.11f138UMN0 Sue FAA -AESEN ATI ; If DESIGNATION ~ABER K-10/01/99 ACE - FSDC)--07 Ally anambOniagettuchOn. 0t m ,pro or ban. DNS CERTIFICA onATION REGULATIONS cal. may be Prohare tor hooncormara SUM ~soarer not exciorr93 MUST BE DISPLAYED IN THE AIRCRAFT IN ACCORDANCE WITH APPLICABLE FEDERAL 4. Form 81C-2 (ago o U.S 0.100311X19 889438 PROT382 PROT383 SIAM OF MJERICA EISSANTNENT OF THANSPORTATIOK-FEDETIAL AVIATION ADMINISTRATION I NATIONALITY NED SEGSPRATION Maki t mAKTFACRIRCA »zo mODEL. 3 AnIt.AArt Spun. 1RASER I CATEGORY 11793TA 400A RK-244 TRANSPORT --:. S. ALJTWORITO MAD BASIS ton eatiOCE fM Yn10MNee I GAMIN I Slue Durward To Sa FealotalAYOrer Ap 01 Igi4 ar0 ~Ma riatelliitiflaYo M LIAlstile A stall s ortach GISMO NA tart Inspects, wry lourd by oysters to ma iypb ~La ~tot to a s condiron be NIS 0pefie0n and its boon Sown 10 mops tro ricistatrass W us ityspIsltie cosign/1es~ arel Oculderal ontitnrstall Slob as oroROPO by ~MI Scotto Corwenvon an Ifeanmeponai CM1 ARMS^ tre0Opl ad 'gen ~sin Exonaorts: NONE T EONS AND CONISTioNS Una some: Awrimiend, suwandest rtvekat CI s ternnallan S. Y onletren• altaplOtteO py OIa AdnlnCtnwl. Ste akworah sett Perireitr A fl ats K tenp.n 1M sorsimonsa pesetzlittatt insratranCa. ISO nerehCan re PRONNOO eI accordant* ...SP/JR21.4. t °Ss Fasterantia SST 'Oats as ASOropeate. Rid Se NSW: tY/Cryslonld ARIUS*. SWIM DATE OF LSSIMNde R-10 01/99 ACE-PSI:0-07 Any elltrAbOrt, riPrOdUCIA2/1.O/ mika may to NS Y • SO NA osstrAro SI .000. et+nwneonmemnol excipoiling 3 Pin, Os ADS THIS CEATINCesTE tAVST PE DISPLAYED IN, THE AC/CRAFT IN ACCORDANCE WITH APPLICABLE FEDERAL W1ATION REOyIATIONS. VE -2414~:44, t: ." - * V.B. o.no:tine 889058 • PROT384 z PROT385 C C-A.A-Xdaa rt- cri-10 e a a Federal Aviadon Administration Forth Approved Office Identification "Mk Ch-C4 ' PS00 -23 INSTRUCTIONS: Print or type all entries. See FAR 43.9, FAR 43 Appendix B, and AC 43.9-1 (or subsequent revision thereof) for instructions and disposition of this form. This report is required by law (49 U S.C. 1421). Failure to report can result in a civil penalty not to exceed $1,000 for each such violation (Section 901 Federal Aviation Act of 1958). 1. Aircraft Make Beechcraft Model 400A Serial No. RK-244 N793TA 2. owner NORTH CHANNEL LLC ET-AL C Fll h ns LLC Richmond Heights H 43-1494 3. For FM Use Only THE TECHNICAL DATA IDENTIFIED HEREIN HAS BEEN FOUND TO COMPLY WITH APPLICAB ftWORTHINESS REQUIREMENTS AND IS HEREBY APPROVED FOR USE ONLY ON THE A @IB A RCRATT, SUBJECT TO litINSPECTION1Y-A-PERSON-IN-14-PROT680 PART-43:7:-- APPROVING INSPECTOR 3 0 JUN 2004 War OA FcTICI 91 4. Unit Identifies 6. Type Unit Make Model Serial No. Repair Alteration AIRFRAME X (As described in item 1 above) POWERPLANT PROPELLER APPLIANCE Type Manufacturer A. x U.S. Certificated Mechanic /O .2 it252 VS' 7 7 earjaHauji - icturt rz ts, 0" 44143 ond Manufacturer D. I certify that the repair and/or alteration made to the unit(s) identified in item 4 above and described on the reverse or attachments hereto have been made in accordance with the requirements of Pan 43 of the U.S. Federal Aviation Regulations and that the information furnished herein is true and correct to the best of my knowledge. Date /2- - 02 .:9--017 Signature of Authorized Individual tz_____-- 7. Approval for Return To Service Pursuant to the authority given persons specified below the unit identified in item 4 was inspected in the manner prescribed by the Administrator of the Federal Aviation Administration and is X APPROVED 0 REJECTED BY FM Flt. Standards Inspector Manufacturer FM Designee Repair Station Person Approved by Transport Canada Airworthiness Group i i O da , t Alkei to ll il flee Date of Approval or Rejection I,2 98- O11 Certificate or CA2006is Sig FM Fenn MT MA% PROT386 NOTICE Weight and balance or operating limitation changes shall be entered in the appropriate aircraft record. An alteration must be compatible with all previous alterations to assure continued conformity with the applicable airworthiness requirements. (If more space is required, attach additional sheets. Identify with aircraft nationality and registration mark and date work completed ) Installed the following equipment In Beechcraft 400A SIN RK-244: Equipment Install Manual Pilot's Guide TAWS 8000 (Class B) 009-18001.001 Current Revision N/A 009-18000-001 Current Revision Installed Goodrich Avionics Systems Landmark TAWS8000 system (TSO-C151a Class B) using Flight Options LLC electrical drawing 400-3446-20-01 and applicable manufacturers installation manuals listed above. This installation includes the optional Terrain Display function. FAA Approved Flight Manual SupplernenialoliA4i0iii6ist,oe,thrOci (Cid rithccaft when the Class B TAWS 8000 system is in use: The TAWS 8000 system has been previously approved for multiple Beechjet aircraft under STC ST01881CH-D, with the Terrain Display function enabled. This installation has been inspected and found to conform to the operational and technical characteristics of STC ST01881CH-13 with minor deviations in location of switching relays and wiring interface points as depicted on Flight 0plionSiLLC drawing 400-3446-20-01. Similarity to STC ST01881CH-D is the basis for this request for field approval. Using the respective manufacturer's instructions for post-installation ground tests. performed operational checks on all systems. The systems performed to manufacturer's specifications and no interference to existing aircraft systems was noted. In addition to specific instructions contained in the manufacturer's installation manual(s) noted above, all physical mounting considerations were made with reference to AC 43.I3.2A. Chapter I. Chapter 2. Chapter 3, and Chapter II as they apply to this installation. Regarding attachment to additional structure all alterations were inspected to comply with the aircraft manufacturer's structural repair and alteration specifications. In addition to specific instructions contained in the manufacturer's installation manual(s) noted above, wire bundles were fabricated using MIL-SPEC, Teful wire, that meets the acceptability requirements of AC43.13-1B, Chapter I I, Section 7, Paragraph 11-85 (a) and/or (b). paragraph 11.88. and paragraph 11.89. All wiring was masked in accordance with AC43.B-18, Chapter I I, Section 16, Pam. 11.206. 11.207, 11.208 (a) and/or (b) and 11.210 (a) and (b). Individual wires were formed into bundles by lacing and tying using the techniques described in AC43.I3-1B, Chapter II, Section 12, paragraph 11.158 (a) and (b). Cables were routed and secured in the aircraft using AC43.13-18. Chapter I I, Section 8, Para.11-96. (a) through (gg) as a guide. An electrical load analysis was performed per AC43 13-1B Chapter II Section 3 Paragraph 36. The maximum probable continuous electrical load does not exceed 80% of the generator(s) output capacity. All compasses aboard this aircraft were checked for accuracy on completion of this installation. The aircraft equipment list and weight and balance were updated instructions for continued aliworifftness (ICA) for thls aircraft alteration and Interfacing components are as follows; (1) Introththtion to the aircraft altered is explained above. (2) Description of the major alteration is explained above. - (3) - Demotion Information is described In Um doeurrientallstod above for each particular.product (4) servicing, (8) Diagram, and icciii platy. (9) iir Ssrasiess ements, (10) Application of protective treatment') (11) Data, (12) LIM of Special Tools (14) Recommended Overhaul Periods. and (15) Airworthiness limitation section are not applicable. (5) Maintenance, (6) troubleshooting Information (7) Removal and Replacement, and (13) for commuter category alrenift of the products listed, will be IAW the appropriate and current manufacturers Installation manuals. (16) Revision wilt be in accordance with the manufacturers' maintenance manuals and submitted to the local FSDO. Antennas and other parts and materials Installed such as wiring, circuit breakers, switches, annunciators, clamps, doublers, shelves, and racks will be Inspected In conjunction with the Raytheon Sectchjet 400A Phase C Inspection program, for condition, *acuity of attachment evidence of damage, and normal operation IAW FAR 25.1529 and/or applicable manufacturers service instructions n Additional Sheets Are Attached 'U.S GPO 1994-568-012/00019 PROT387 JAN 03 2005. 0 , us Dem-wont FM.* Avision Mimi*Aram Form Approved .11-2- 4 C-74 - FS Da - 2 3 INSTRUCTIONS: Print or type all entries. See FAR 43.9, FAR 43 Appendix 8, and AC 43.9-1 (or subsequent revision thereof) for instructions and disposition of this form. This report is required by law (49 PROT681. 1421). Failure to report can result in a civil penalty not to exceed $1,000 for each such violation (Section 901 Federal Aviation Act of 1958). 1. Aircraft Make Beechcraft Model 400A Serial No. RK-244 N793TA 2. Owner NORTH CHANNEL LLC ET-AL CIO Flight ions LLC Richmond Heights OH 44143-1494 4. Unit Identification 5. Type Unit Make Model Serial No. Repair Alteration AIRFRAME described in item X (As t above) POWERPLANT PROPELLER APPLIANCE Type Manufacturer S. Conformity Statement Lynn H. Huyen c mon a g b 43-14114 X U.S. Certificated Mechanic A8P 278825845 Manufacturer D. I certify that the repair and/or alteration made to the uniqs identified in item 4 above and described on the reverse or attachments hereto have been made in accordance with the requirements of Part 43 of the U.S. Federal Aviation Regulations and that the information furnished herein is true and correct to the best of my knowledge. Date /*, -.2 .2- - 0 9/ Signature of Authorized Individual 7. Approval for Return To Service Pursuant Administrator BY to the authority g yen persons specified below the unit identified in item 4 was inspected in the manner prescribed by the of the Federal Aviation Administration and is I213 APPROVED 0 REJECTED FM Rt. Standards Inspector Manufacturer Other ( i I ee FM Designee Repair Station Person Appro by Transport Canada invort ness Grou Date of Approval Rejection Certificate or S FOAfilan SA NMI PROT388 NOTICE Weight and balance or operating limitation changes shall be entered in the appropriate aircraft record. An alteration must be compatible with all previous alterations to assure continued conformity with the applicable airworthiness requirements. (If more space is required, attach additional sheets. Identify with aircraft nationality and registration mark and date work completed.) Removed existing MK-VI GPWS system in conjunction with installation of new TAWS (EGPWS) system reference FM form 337 dated 12-22-O4. Aircraft weight and balance and equipment list data have been revised. END 0 *U.S.GPO:1994-568-012/00019 PROT389 0 US Copan:nen 0 Ffiderol Mutton Aclairattation Form Approved Office 0 t5'.--- 7/31.'-- INSTRUCTIONS: Print or type all entries. See FAR 43.9. FAR 43 Appendix B. and AC 43.9-1 (or subsequent revision thereof) for instructions and disposition of this form. This repod is required by law (49 PROT682. 1421). Failure to report can result in a civil penalty not to exceed 24.000 for each such violation (Section 901 Federal Aviation Act of 1958). 1. Aircraft Make BEECHJET Model 400A Serial No. RK244 N793TA 2. Owner FLIGHTOPTIONS Address As shown on istration certificate) I NO H S.. OHIO 44143 3. For FAA Use On y 6. Type Unit Make Model Serial No. Repair Alteration AIRFRAME descnbed in "ern 1 x (As POWERPLANT PROPELLER APPLIANCE Type Manufacturer 6. Con ormity Statement MPLETIONS INC. LEVELANCL HI 4143 R4GR031Y X Certificated Repair Station Manufacturer D. I certify that the repair andior alteration made to the units identified in item 4 above and described on the reverse or attachments hereto have been made in accordance with the requirements of Part 43 of the U.S. Federal Aviation Regulations and that the information furnished herein is true and correct to the best of my knowledge. Date 12-10-2004 f A rized Indiv' ual for Return To Se ce 7. Approval Pursuant Administrator BY to the authority given persons specified•below the unit identified in item 4 was inspected in the manner prescribed by the of the Federal Aviation Administration and is l2; APPROVED O REJECTED FAA FIL Standards Manufacturer RECEIVED FAA Designee Person Approved by Transport Date of Approval 12-10-2004 or Rejection Certificate or R4GRO31Y Signature of Authorized Individual DEC 16 2004 ell r atite-f AA Filar, 317 o,N PROT390 NOTICE Weight and balance or operating limitation changes shall be entered in the appropriate aircraft record. An alteration must be compatible with all previous alterations to assure continued conformity with the applicable airworthiness requirements. (If more space is required, attach additional sheets. Identify with aircraft nationality and registration mark and date work completed.) AIRCRAFT: BEECHJET 400A N793TA RK-244 FABRICATED AND INSTALLED THE FOLLOWING USING APPROVED DER DRAWINGS SEE FAA FORM 8110-3 DATED 12-08-2004 1) Ft/H Galley 2) a) Assembly drawing #36G-200A006 b) Installation drawing #36G-200F006 There are no additional inspections required for continued airworthiness other than those prescribed by the aircraft manufacturer during regular inspections. END 0 •11.S.GP(11994-568-012/00019 PROT391 0 Form Approved us c.vikvvnevii a Administration _I Q OffArAliFS no INSTRUCTIONS: Print or type all entries. See FAR 43.9, FAR 43 Appendix B, and AC 43.9-1 (or subsequent 1 2 3 thereof) for instructions and disposition of this form. This report is required by law (49 PROT683. 1421). Failure to report can result . it penalty not to exceed $1,000 for each such violation (Section 901 Federal Aviation Act of 1958). 1. Aircraft Make RAYTHEON Model 400A Serial No. RK-244 USA N793TA 2 Owner SAMAIR INC ET-AL WICHITA, KS 67207 THE TECHN CAL DATA REQUIREMENTS AND TO CONFOR ITY INSPECTION -2-S103 IDENTIFIED HEREIN HAS BEEN FOUND TO COMPLY WITH APPLICABL NYORTHtNESS IS HEREBY APPROVED FOR USE ONLY ON TH BY A PERSON IN 14 PROT684 PART 43.7. APPROVING INSPECTOR BJECT DATE K.°1 AEA FSDO 23 4. Unit Identificall ype Unit Make Model Serial No. Repair Alteration AIRFRAME item (As described in 1 above) X POWERPLANT PROPELLER APPLIANCE Type Manufacturer STEPHEN J. MAIDEN C/O FLIGHT OPTIONS LLC RICHMOND HEIGHTS, OH 44143 X A 297605039 Manufacturer D. I certify that the repair and/or alteration made to the unit(s identified in item 4 above and described on the reverse or attachments hereto have been made in accordance with the requi ements of Part 43 of the U.S. Federal Aviation Regulations and Mat the information furnished herein is true and correct to the best of m knowledge. Date JUNE 10, 2003 7. Approval for Ret n To ice Pursuant to the authority given persons specified below the unit identified in m 4 was inspected in the manner prescribed by the Administrator of the Federal Aviation Administration and is jn APPROVED 0 REJECTED Inspector Manufacturer Other (Specify) OPTIONS FLIGHT SUPPORT, INC., dibia FLIGHT OPTIONS BY FAA Designee Repair Station JUNE 10, 2003 Certificate or DJFA206D KEITH GAWSYSZAWSKI FM Form 31? mig PROT392 NOTICE Weight and balance or operating limitation changes shall be entered in the appropriate aircraft record. An alteration must be compatiblewitlzall previous alterations to assure continued conformity with the applicable ainvorthiness requirements. 8 Description'9trork Accomplished (If more space is required, attach additional sheets. Identify with aircraft nationality and registration mark and date work completed.) INSTALLED ROCKWELL COLLINS, INC., SUPPLEMENTAL TYPE CERTIFICATE #ST00881WI-D, MODIFICATION OF COLLINS TCAS II SYSTEM INSTALLATION WITH COLLINS TTR-920 CHANGE 6.04a RECEIVER TRANSMITTER TO A COLLINS TCAS II SYSTEM INSTALLATION WITH COLLINS TTR-920 CHANGE 7 TCAS II RECEIVER TRANSMITTER IN ACCORDANCE WITH COLLINS INSTALLATION INSTRUCTIONS AS LISTED ON AML tt ST00881WI-D. AIRCRAFT FLIGHT MANUAL SUPPLEMENT INSERTED INTO AIRCRAFT FLIGHT MANUAL. NO CHANGE TO WEIGHT AND BALANCE. O Additional Sheets Are Attached *U.S.GPO:1994-568-012/CO019 PROT393 1 3 JUN 2003 O US Department rd Falderal Aviation Administration Form Approved :31-f stiCAgrESIX) can result 23111 penalty not INSTRUCTIONS: Print or type all entries. See FAR 43.9. FAR 43 Appendix instructions and disposition of this form. This report is required by law (49 PROT685. to exceed $1 ,000 for each such violation (Section 901 Federal Aviation Act of B. and AC 43.9-1 (or 1421). Failure to report 1958). 1. Aircraft Make RAYTHEON Model 400A Serial No. RK-244 USA N793TA 2. Owner SAMAIR INC ET-AL WICHITA, KS 67207 3. For FAA Use On y 5. Type Unit Make Model Serial No. Repair Alteration AIRFRAME described in X (As item 1 above) POWERPLANT PROPELLER APPLIANCE Type Manufacturer Stephen J. Maiden C/O FLIGHT OPTIONS LLC RICHMOND HEIGHTS, OH 44143 X A297605039 Manufacturer ' ' D. I certify hereto information that the repair and/or have been made furnished herein 10 June, 03 alteration made to the unit(s) identified in item in accordance with the requ' is true arid correct to t 7. 4 above and described on the reverse or attachments Date Pursuant Administrator BY Date fu to the authority g ven persons specified below, the unit identified of the Federal Aviation Administration and is X) APPROVED in it 4 was inspected in the manner prescribed by the O REJECTED FAA Designee or Rejection to too Manufacturer Repair Station Certificate or DJFA206D Inspector AIR AGENCY CERTIFICATE Person Approved by Canada Airworthiness Transport Grow Other (Specify) FLIGHT OPTIONS LLC of Approval tad FM ?cal 33? IOW PROT394 NOTICE Weight and balance or operating limitation changes shall be entered in the appropriate aircraft record. An alteration must be compatible with all previous alterations to assure continued conformity with the applicable airworthiness requirements. a -9 rict i; 8. Destflpli of Work Aecomplished (If more spacriseequired, attach additional sheets. Identify with aircraft nationality and registration mark and date work completed.) INSTALLED ROCKWELL COLLINS, INC., SUPPLEMENTAL TYPE CERTIFICATE #ST00881WI-D, MODIFICATION OF COLLINS TCAS II SYSTEM INSTALLATION WITH COLLINS TTR-920 CHANGE 6.04a RECEIVER TRANSMITTER TO A COLLINS TCAS II SYSTEM INSTALLATION WITH COLLINS TTR-920 CHANGE 7 TCAS II RECEIVER TRANSMITTER IN ACCORDANCE WITH COLLINS INSTALLATION INSTRUCTIONS AS LISTED ON AML # ST00881WI-D. AIRCRAFT FLIGHT MANUAL SUPPLEMENT INSERTED INTO AIRCRAFT FLIGHT MANUAL. NO CHANGE TO WEIGHT AND BALANCE. END 0 *U.S.GPO:1994-568-012/00019 PROT395 r Satiltbinalto of Amnia Pepartment of transportation - Aebtral tAbintion Abministralints $upplemental Jgpe Tertifirate ../14;9a 0./e ST00881 IN I. D .ffa trinVeale. t;hoowlie Rockwell Collins, Inc. 400 Collins Road NE, MS 164.100 Cedar Rapids, IA 52498 rerlOns arc/46 refer res a, r/rwirrsirfc 46Arreverionoarekne en 46 Snarteivra orairavnAiievpo derOr a.; bynee.Aftherevr nonAs t neivreedionmaree:vwennia Val • erst.4:: • derpottr/tivar. niaseetliteduce Vienckdres 1:24"4.- •See attached FAA Approved Model List (AML) No. ST0088IWI-D for list of approved airplane models and applicable airworthiness regulations. Sive.soraiv. rtf4r: Modification of Collins TCAS 11 or TCAS 94 (TCAS II) system installation with Collins TTR-920 Change 6.04a Receiver Transmitter to a Collins TCAS II or TCAS 94 (TCAS II) system installation with Collins TTR-920 or Collins 17R-921 or Cellists TTR-4000 Change 7.0 TCAS 11 Receiver Transmitter and optional TPR-901 in accordance with Collins Installation Instructions as listed on AML No. ST0088IWID, Revision -, or later FAA approved revisions. 5Saoardshei ( 0 Approval of this change in type design applies to the above model aircraft only. (2) Compatibility of this design change with previously approved modifications must be determined by the installer. (3) A copy of this Certificate and FAA Approved Model List (AML) No. ST00881WI-D issued June 30, 2000, or later FAA approved revision, must be maintained as pan of the permanent records for the modified aircraft. (4) Prior installation and approval of a Collins TTR-920 Change 6.04a Receiver Transmitter is a prerequisite to this STC. (5) If the holder agrees to permit another person lo use this certificate to alter the product, the holder shall give the other person written evidence of that pennission. .974, sada. .isenvevt&to ar/er rey(ori U Lf. ho.h'l At, evreresiafattesentetU es 10e/ sena atenstAnet Jet.irina neater' Pe a AryesentieniVi Ate 0.l esCinvtvde nrferAitastafr ,,,Z1Lreereateer/re Vide !Rea- .1/4 ,-vtetwain . June 29, 2000 !Alt e/ti.i.tuageo June 30, 2000 firor:• trtwr«l. fere.o syno-sated. July 14, 2000, December I, 2000 11111111- Administrator, DAS-500864-CE My •iteronon of tai. tertifiCott le penialible by • tine of sot exteallO9 $1.000. Or Oar @Omen, aet OflteillIsfr J rears. Or boa. TOD Noy be into rrrrr to error et wf t0 PM 73.• . IAA r0t. $110-2110-44) Via I PROT396 1 PROT397 Avionics Cerblicalkan Center Rockwell Collins May 14, 2003 WO030737.DOC Fli ht O lions Cleveland, OH 44143 Tel: (216) 797-3500 Attention: Mr. Jody Kremsreiter/ Mr. Richard Fine (Collins on-site) Subject: STC ST00881WI-D Modification of Collins TCAS II System Installation with Collins TTR-920 Change 6.04a Receiver Transmitter and TPR-900 Mode S to a Collins TCAS II System Installation with Collins TTR-920, Collins TTR-921 or Collins TTR-4000 Change 7.0 TCAS II Receiver Transmitter and optional TPR-901 in Part 25 Aircraft Dear Mr. Kremsreiter: Enclosed is a compact disk with one copy each of the following FAA approved STC data: 1. STC ST00881WI-D Certificate, dated December 1, 2000. 2. FAA Approved Model List (AML) Number ST00881WI-D, amended April 15, 2003. 3. Drawing Index 992-4358-001. Revision M. 4. One copy of each drawing listed on Drawing Index 992-4358-001. 5. Airplane Flight Manual Supplement, ACC-00-105, Revision -. This letter is our authorization for Flight Options to use this STC as basis for the installation of our equipment in our at lanes based on the following model and serial numbers provided by Mr. of Rockwell Collins. PROT398 '1 PROT399 Flight Options STC ST00881WI-D May 14, 2003 Page 2 WO030737.DOC STC ST00881WI-D Model MSN MSN 400A RK006 RK248 RK016 RK252 RK022 RK257 RK027 RK260 RK030 RK264 RK031 RK265 RK045 RK268 RK062 RK271 RK093 RK273 RK146 RK274 RK161 RK276 RK168 RK279 RK178 RK282 RK180 RK284 RK186 RK289 RK189 RK292 RK195 RK295 RK198 RK297 RK201 RK301 RK202 RK305 RK209 RK307 RK222 RK310 RK230 RK317 RK234 RK324 RK237 RK327 RK239 RK328 RK244 RK334 RK245 Please return a record of any additional aircra performed using this STC. My fax number is data before we can authorize additional installations. (s) to me for installations Collins needs to receive this PROT400 % % a ..) PROT401 Flight Options STC ST00881WI-D May 14, 2003 Page 3 WO030737.DOC Flight Options is responsible for the regulatory approval of any deviations from STC ST00881WI-D. Instructions explaining how to access the data on the CD have been inserted inside the jewel case. Customer satisfaction is important to us, and we would appreciate your input. Please corn lete and return the enclosed questionnaire or email me at nd let us know how we can best serve you. We trust this data will fulfill your installation requirements. However, if you have any questions, please call me at Collins Avionics Certification Center /pah Enclosure PROT402 PROT403 ee US DoPan:mon 0 Federal /Melton Admkdstrallon Form Approved Arh ienn INSTRUCTIONS: Print or type all entries. See FAR 43.9, FAR 43 Appendix B, and AC 43.9-1 or subsequent revision for instructions and disposition of this form. This report is required by law (49 PROT686. 1421). Failure to report can result in a civil penalty not to exceed 31,000 for each such violation (Section 901 Federal Aviation Act of 1958). 1. Aircraft Make Beechjet Model 400A Serial No. RK- .214 4 USA N 793T/) 2. Owner Sitni AL.e TP C er-At_ coicitarf, KS (.7. 1 °2 The data identified herein complied with applicable airworthines - The above described aircraft subject to conformity inspected - --- --- ' This approval is ontifor this'aircraftmakerm Date Approving Inspector tr i m - 12002 6. Type Unit Make Model Serial No. Repair Alteration AIRFRAME described in item X (As 1 above) POWERPLANT 7 1 PROPELLER APPLIANCE Type Manufacturer Keith Gawsyszawski i i Richmond Hts., ON 44143 X AP 287603483 Manufacturer D. I certify that the repair and/or alteration made to the unit(s) identified in item 4 above hereto have been made in accordance with the requrements of Part 43 of the U.S. information furnished herein is true and correct to the best of my knowledge. and described on the reverse or attachments Federal Aviation Regulations and that the Date April 5, 2002 7. Approval for Return To Service Pursuant Administrator BY to the authority given persons specified below, the unit identified in item 4 was inspected in the manner prescribed by the of the Federal Aviation Administration and is 00 APPROVED U REJECTED FM Fit. Standards Inspector Manufacturer ,K., Inspection Authorization FAA Designee Repair Station 44 4,1 ?00?- Certificate or iv,-1.1374.93A3P1 PM Noto PROT404 NOTICE Weight and balance or operating limitation changes shall be entered in the appropriate aircraft record. An alteration must be compatible with all previous alterations to assure continued conformity with the applicable airworthiness requirements. (If more space is required, attach additional sheets. Identify with aircraft nationality and registration mark and date work completed.) 1. Removed existing Tail Navigation Light Assembly including the rubber shock mount. 2. Installed Whelen Engineering, Inc. Model 70805-01 Tail Position Light Assembly in accordance with part number 04-0112558-00 instruction sheet to include installation procedures and drawing number 70805. 3. The light assembly will be operationally tested under Flight Options Continuous Airworthiness Maintenance Program under Phases IC, 9C and I7C. 4. Weight and Balance change found negligible. END-- *U.S.GPO:1994-568-012/00019 PROT405 CO PO U.S. Department Federal Malkin Administration 'arm Approved Li W!? Mt- INSTRUCTIONS: Print or type all entries. See FAR 43.9, FAR 43 Appendix B, and AC 43.9-1 (or subsequent revision thereof) for instructions and disposition of this form. This report is required by law (49 PROT687. 1421). Failure to report can result in a civil penalty not to exceed S1,000 for each such violation (Section 901 Federal Aviation Act of 1958). I. Aircraft Make RAYTHEON AIRCRAFT Model 400A Serial No. RK-244 USA N793TA 2. Owner Name (As shown on registration certificate) KETTLER ROBERT, MICHELS PIPELINE CONSTRUCTION INC, SOUTHEASTERN MILLS INC, REI AIR LLC, ET-AL Address WICHITA KS 67207-1315 S. Type Unit Make Model Serial No. Repair Alteration AIRFRAME X POWERPLANT PROPELLER APPLIANCE TYPe Manufacturer 8. Kind of Agency RAYTHEON AIRCRAFT SERVICES SAN ANTONIO TEXAS 78216 us. Certificated Meclunie CRS-XA14605K LIMITED AIRFRAME X ertificated Station C Repro M anufacturer D. I certify that the repair and/or have been made in accordance furnished herein is true and correct Date 12-10-01 alteration made to the unit(s) with the requirements to the best of m identified of Part 43 of knowled the unit identified and is in item 4 the U.S. Federal in item above and described on the reverse or attachments hereto Aviation Regulations and that the information 4 was inspected 'n the manner prescribed by the 0 REJECTED BY Pursuant to the authority given persons specified below, Administrator of the Federal Aviation Administration Pi APPROVED FAA Fit- Standards Inspector Manufacturer FAA Designee x Repair Station • a Airworthiness Grou 12-10-01 Certificate or Desisnation No. CRS-XA14605K FAA Form 337 (12.81) PROT406 NOTICE Weight and balance or operating limitation changes shall be entered in the appropriate aircraft record. An alteration must be compatible with all previous alterations to assure continued conformity with the applicable airworthiness requirements. (If more space is required, attach additional sheets. !den* with aircraft nationality and registration mark and date work completed.) MAKE: RAYTHEON 400A S/N: RK-244 REG: N793TA DATE: 12-10-01 ALL SEVEN CABIN SEATS AND THE LAVATORY SEAT WERE FIREBLOCKED IN ACCORDANCE WITH FAR 25.853 (a) APPENDIX F PART I (a) (1) (ii) AND FAR 25.853 (c) APPENDIX F PART II AMENDMENT 25-83. THE FIREBLOCKING WAS ACCOMPLISHED IN ACCORDANCE WITH THE SKANDIA INC. TEST PLAN #8335 REV. IR DATED 12-04-01, REFERENCE THE FORM 8110-3 DATED 12-04-01 APPROVED BY DESIGNATED ENGINEERING REPRESENTATIVE, #DERY-410100-CE, STRUCTURAL SPECIAL. SEE THE FORM 8110-3 DATED 10-09-01 AS REFERENCE FOR THE FIREBLOCKING FLAMMABILITY TEST RESULTS OF THE SEATS THAT WAS PREVIOUSLY TESTED AND APPROVED ON THE SKANDIA INC. TEST PLAN #8118 REV. IR DATED 10-01-01 FOR P/N 8118-1 AND 8118-2 ONLY, APPROVED BY DESIGNATED ENGINEERING REPRESENTATIVE, #DERY-410100-CE, STRUCTURAL SPECIAL. END El Additional Sheets Are Attached * U.S. GOVERNMENT PRINTING OFFICE: 1992-769-012/60157 PROT407 0 I Department el Federal Aviation Transportation Administration Form Approved OMB No. 2120.0020 .9-7 9 a -, INSTRUCTIONS: Print or type all entries. See FAR 43.9, FAR 43 Appendix B, and AC 43.9-1 (or subsequent revision thereof) for instructions and disposition of this form. This report is required by law (49 PROT688. 1421). Failure to report can result in a civil penalty not to exceed $1,000 for each such vjolation (Section 901 Federal Aviation Act of I9581. I. Aircraft Make RAYTHEON AIRCRAFT Model 400A Serial No. RK-244 USA N793TA 2. Owner Name ICEITLER ROBERT, MICHELS PIPELINE CONSTRUCTION INC, SOUTHEASTERN MILLS INC, REI AIR. LLC, ET-AL Address WICHITA KS 67207-1315 S. Type Unit Make Model Serial No. Repair Alteration AIRFRAME X POWERPLANT PROPELLER APPLIANCE Type Manufacturer U.S. Certifkated Mechanic CRS-XA14605K - RADIO CLASS 1,11,III X Certificthated Repair Station Mara a:rum D. I certify that the repair and/or alteration made to the unit(s) have been made in accordance with the requirements furnished herein is true and correct to the best of m Date 12-10-01 identified in item 4 above and described on the reverse or attachments hereto of Part 43 of the U.S. Federal Aviation Regulations and that the information knowled e. BY Pursuant to the authority given persons specified below, the unit identified in item 4 was inspected in the manner prescribed by the l7 APPROVED 0 REJECTED FAA Fit Standards Inspector Manufacturer FAA Designee x Repair Station Pawn Approved by Transport 12-10-01 Certificate or CRS-XA14605K FAA Form 317 (12.88) PROT408 NOTICE Weight and balance or operating limitation changes shall be entered in the appropriate aircraft record An alteration must be compatible with all previous alterations to assure continued conformity with the applicable airworthiness requirements. (i f more space is required attach additional sheets. Men* with aircraft nationally and registration mark and date work completed) MAKE: RAYTHEON 400A SIN: RK-244 REG: N793TA DATE: 12-10-01 MODIFIED THE EXISTING RIGHT HAND FORWARD GALLEY/CLOSET CABINET IN ACCORDANCE WITH THE RAYTHEON AIRCRAFT SERVICES DWG. #528-2526-001 REV. A DATED 07-27-00, REFERENCE THE FORM 8110-3 DATED 12-07-01 APPROVED DESIGNATED ENGINEERING REPRESENTATIVE, #DERT-405126-CE, STRUCTURAL. THE MODIFICATION CONSISTED OF INSTALLING ELECTRICAL PROVISIONS FOR A MAPCO, CUP HOLDERS AND LIGHTING IN THE FORWARD SECTION OF THE BAGGAGE CABINET. THE ELECTRICAL WIRING FOR THE GALLEY/CLOSET CABINET WAS INSTALLED IN ACCORDANCE WITH THE RAYTHEON AIRCRAFT SERVICES DWG. #RAS-73-0112 REV. ER DATED 12-05-01, REFERENCE THE FORM 8110-3 DATED 12-07-01 APPROVED BY DESIGNATED ENGINEERING REPRESENTATIVE, #DERT-710137-SW, SYSTEMS AND EQUIPMENT. THE MODIFIED GALLEY/CLOSET CABINET HAS A NEW WEIGHT OF 84.5 Lbs. AND A MOMENT OF 12844.0. THE WEIGHT AND BALANCE FORM AND THE EQUIPMENT LIST HAVE BEEN REVISED AND BOTH FORMS HAVE BEEN INSERTED IN THE AIRCRAFT FLIGHT MANUAL. END Ei Additional Sheets Me Attached * U.S. GOVERNMENT PRINTING OFFICE: 1992-769-012/60157 PROT409 egp/ 1) MAJOR REPAIR ANDALTERATION US. Department AdmInistntIon Form Approved Office Idenfification .....Nca-207 p t. INSTRUCTIONS: Print or type all entries. See FAR 43.9, FAR 43 Appendix B, and AC 43.9-1 (or subsequent revision thereof) for instructions and disposition of this form. This report is required by law (49 PROT689. 1421). Failure to report can result in a civil penalty not to exceed 51,000 for each such *lotion (Section 901 Federal Aviation Act of 19581. 1. Aircraft Make RAYTHEON AIRCRAFT Model 400A Serial No. RK-244 USA N793TA 2. Owner Name KETTLER ROBERT, MICHELS PIPELINE CONSTRUCTION INC, SOUTHEASTERN MILLS INC, REI AIR LLC, ET-AL Address WICHITA KS 67207-1315 3. For FAA PROT690 Only S. Type Unit Make Model Serial No. Repair Alteration AIRFRAME X POWERPLANT PROPFI 1 Pla. APPLIANCE Wile Manufacturer 1115 PAUL WILKINS ROAD U.S Certificated Mechanic CRS-XAI4605K Foreign Catikated MeCtiallk X Certificated Repafr Station Mandsctunt D. I certify that the repair and/or alteration made to the unit( have been made in accordance with the requirements tbmished herein is true and correct to the best of m Date 12-10-01 ) identified in item 4 above and described on the reverse or attachments of Part 43 of the U.S. Federal Aviation Regulations and that the information hereto BY Date Pursuant to the authority given persons specified below, the unit identified in item la APPROVED 4 was inspected in the manner prescribed by the III REJECTED FAA Mt. Standards Inspector Manufacturer of Approval FAA Designee or Rejection 12-10-01 x Repair Station Certificate or Desinnation No. CRS-XA14605K FAA Form 337 (1243s) PROT410 NOTICE Weight and balance or operating limitation changes shall be entered in the appropriate aircraft record. An alteration must be ' compatible with all previous alterations to assure continued conformity with the applicable airworthiness requirements. #f more space it required. attach additional sheets. Identify with aircraft nationally and registration mark and date work completed) MAKE: RAYTHEON 400A S/N: RIC-244 REG: N793TA DATE: 12-10-01 FABRICATED AND INSTALLED A NEW THE LIFE VEST CONTAINER IN THE TOILET CABINET IN ACCORDANCE WITH THE RAYTHEON AIRCRAFT SERVICES DWG. #562-3832-001 REV. IR DATED 08-22-00, REFERENCE THE FORM 8110-3 DATED 12-07-01 APPROVED BY DESIGNATED ENGINEERING REPRESENTATIVE, #DERT-405126-CE, STRUCTURAL. THE LIFE VEST CONTAINER WAS FABRICATED USING AAR COMPOSITES FLAT NOMEX PANEL P/N ATR-FP-251F2, REFERENCE THE FORM 8110-3 DATED 07-01-99 APPROVED BY DESIGNATED ENGINEERING REPRESENTATIVE, #CHI-410, STRUCTURAL SPECIAL. THE MODIFICATION OF THE CONTAINER WAS FOR THE INSTALLATION OF A NEW EASTERN AERO MARINE LIFE VEST, P/N PO1074-113. THE WEIGHT CHANGE IS NEGLIGIBLE. THE EQUIPMENT LIST HAS BEEN REVISED TO REFLECT THE NEW LIFE VEST AND HAS BEEN INSERTED IN THE AIRCRAFT FLIGHT MANUAL. END El Additional Sheets Am Attached * U.S. GOVERNMENT PRINTING OFFICE: 1992-769-012/60157 PROT411 0 I us oepaiment errnhnscxxiatan Federal Million Form Approved e'z,-... "le c'ethisro oge; ' ftb INSTRUCTIONS: Print or type all entries. See FAR 43.9 Appendix B. and AC 43.9-1 (or subsequent revision thereof) for instructions and disposition of this form. This report is required by law (49 PROT691. 1421). Failure to report can result in a civil penalty not to exceed $1,000 for each such violation (Section 901 Federal Aviation Act of 1958). 1. Aircraft Make RAYTHEON Model 400A Serial No. RK-244 N793TA 2. Owner Name (As shown on registratkin certificate) AIRCAP LLC WICHITA, KS 67207-1315 3. For FAA Use On y THE DATA IDENTIFIED HEREIN COMPLIES WITH APPLICAB AIRWORTHINESS REQUIREMENTS AND IS APPROVED ONLY FOR THE ABOVE DESCRIBED AIRCRAFT SU d CT T C NFO TY INSPECTION BY A PERSON AUTHORIZED IN FAR 43.7 APR 0 4 2000 DATE DPA-FSDO 5. Type Unit Make Model Serial No. Repair Alteration AIRFRAME described in Item 1 X (As above) POWERPLANT PROPELLER APPLIANCE Type Manufacturer Elliott Aviation Moline, IL 61266-0100 U.S. Certified Mechanic CGHR812C Foreign Certified Mechanic X Certificatedted Repair Station Manufacturer D. I certify that the repair and/or alteration made to the unit(s) identified in item 4 above and described on the reverse or attachments hereto have been made in accordance with the requirements of Part 43 of the U.S. Federal Aviation Regulations and that the information Date 3/29/2000 7. Approv Pursuant to the authority given persons specified below, the unit dentified in item 4 was inspected in the manner prescribed by the 03 APPROVED 0 REJECTED FAA Fit. Standards Inspector Manufacturer BY FAA Designee Airworthiness Group Da e of Approval or Rejection ft 9/ 90D0 Certificate or CGHR812C Siaillilli Opp FAA Form 337 (1zes) PROT412 NOTICE Weight and balance or operating limitation changes shall be entered in the appropriate aircraft record. An alteration must be compatible with all previous alterations to assure continued conformity with the applicable airworthiness requirements. (if more space is required, attach additional sheets, Identify with aircraft nationality end registration mark and date work accomplished) 1. INSTALLED PENNY & GILES PASSENGER DIGITAL CABIN DISPLAY MODEL 2700. 2. THE CABIN DISPLAY WAS FLUSH MOUNTED IN THE FWD RH CLOSET/GALLEY CABINET AT 152.0 INCHES AFT OF DATUM FACING AFT. CONNECTED UNIT TO FACTORY PROVISION HARNESS LOCATED IN THE CABINET. THE UNIT WILL DISPLAY TEMPERATURE, TRUE AIRSPEED, ALTITUDE AND E.TA INFORMATION. THE DISPLAY IS FAA/PMA CERTIFIED. THE CABIN DISPLAY WAS INSTALLED IN ACCORDANCE WITH B&D INSTALLATION MANUAL P/N 2700-003-026 REV 0 DATED DECEMBER 19,1996. 3. PERFORMED EMI INTERFERENCE TEST IN ACCORDANCE WITH AC43.13-1B SECTION 8 PARAGRAPH 11-107 AND FAR 23.1309 AND 23.1431. 4. WEIGHT AND BALANCE DATA, EQUIPMENT LIST AND AIRFRAME LOGBOOKS WERE REVISED TO REFLECT THIS INSTALLATION. 5. FOR THE ABOVE INSTALLED SYSTEM NO ADDITIONAL MAINTENANCE IS REQUIRED BEYOND THE REQUIREMENTS OF 14 PROT692 PART 91 SUBPART E MAINTENANCE, PREVENTATIVE MAINTENANCE AND ALTERATIONS PER THE FOLLOWING INSTALLATION MANUAL• (1) B&D INSTALLATION MANUAL P/N 2700-003-026 REV 0 DATED DECEMBER 19,1996 5. INSTRUCTIONS FOR CONTINUED AIRWORTHINESS CHECKLIST (1) INTRODUCTION-REF THIS 337 FORM BLOCK 1 (2) DESCRIPTION-REF THIS 337 FORM BLOCK 8 (3) CONTROL OPERATION INFORMATION- REF THIS 337 FORM BLOCK 8 (4) SERVING INFORMATION-NOT APPLICABLE (5) MAINTENANCE INSTRUCTIONS-REF THIS 337 FORM BLOCK 8 (6) TROUBLESHOOTING INFORMATION-REF THIS 337 FORM BLOCK 8 (7) REMOVAL AND REPLACEMENT-REF THIS 337 FORM BLOCK 8 (8) DIAGRAMS- NOT APPLICABLE (9) SPECIAL INSPECTION REQUIREMENTS-NOT APPLICABLE (10) APPLICATION OF PROTECTIVE TREATMENTS-NOT APPLICABLE (11) DATA-NOT APPLICABLE (12) LIST OF SPECIAL TOOLS-NOT APPLICABLE (13) COMMUTER CATERGORY NC- ELECTRICAL LOAD ANALYSIS-NOT APPLICAPLE (14) NO ADDITIONAL OVERHAUL TIME LIMITATIONS (15) AIRWORTHINESS LIMITATIONS SECTION-NOT APPLICABLE (16) REVISION-IF A REVISION TO THIS ICA IS NECESSARY A LETTER WILL BE SUBMITTED TO THE LOCAL FSDO WITH A COPY OF THE REVISED FM FORM 337 AND REVISED ICA. END * U.S. G.P.O 1990-761-753 PROT413 APR 2 1 MI I US Department MAJOR REPAfR AND ALTERATION of TronsporisSan Fodor& Aviation AdmInistraUon Form Approved Atm Idettnyi lliefl- -F SDO INSTRUCTIONS: Print or type all entries. See FAR 43.9 Appendix B, and AC 43.9-1 (or subsequent revision thereof) for instructions and disposition of this form. This report is required by law (49 PROT693. 1421). Failure to report can result in a civil penalty not to exceed $1,000 for each such violation (Section 901 Federal Aviation Act of 1958). 1. Aircraft Make BEECH Model 400A Serial No. RK-244 N793TA 2. Owner AIRCAP LLC Address (A wn n strafion certificate) WITCHA KS 67207-1315 3. For FAA Use On y 5. Type Unit Make Model Serial No. Repair Alteration AIRFRAME As described in Item 1 above) X POWERPLANT PROPELLER APPLIANCE Type Manufacturer 6. Con ormity Statement Elliott Aviation Moline, IL 61266-0100 U.S. Certified Mechanic CGHR812C Foreign Certified Mechanic X Certificated Repair Station Manufacturer D. I certify that the repair and/or alteration made to the unit(s) Identified in item 4 above and described on the reverse or attachments hereto have been made in accordance with the requirements of Part 43 of the U.S. Federal Aviation Regulations and that the information Date 4/14/00 Si 7. Appro Pursuant Administrator BY to the authority given persons specified below, the unit identified in item 4 was inspected in the manner prescribed by the of the Federal Aviation Administration and Is IEJ APPROVED ID REJECTED FAA Ft Standards Inspector Manufacturer FAA Designee 4/14/00 Certificate or C G FAA Form 337 OM) PROT414 NOTICE Weight and balance or operating limitation changes shall be entered in the appropriate aircraft record. An alteration must be compatible with all previous alterations to assure continued conformity with the applicable airworthiness requirements. B. Description of Work Accomplished (If more space is required, attach additional sheets, Identify with aircraft nationality and registration mark and date worn accomplished.) 400A, RK-244, N793TA, 4/14100 Removed all the interior and the cabinetry items to facilitate a complete refurbishment of the interior per the customers request. Removed all the finishes and material's as required. Recovered the cabin headliner, the left and right hand window panels, the emergency exit panel and the cabin door upper panel with Douglas Interior products: Fabric, DEF 9135, PN 04, Ivory, DA. # 12777, REF # 402396-402545. See the bum test report WO #45065-00 and the form 8110-3, Both dated 03/03/00 and approved by D.E.R. #DERY 405020-CE, Structural special. Recovered the left and right hand drink ledge consoles with Rogers & n: Fabric, FRET #9103-05, Baroque, Treated at Skandia, REF treatment #SKEP41539. See the burn test report WO #46487- 00 and the FORM 8110-3, both dated 04-13-00 and approved by Judy Boggs, D.E.R. #DERV - 405020-CE structural special. Recovered both crew seats, seven cabin seats, the lavatory seat with leather Townsend leather. Leather, Classic pecan, Part #CL- 17, D/L #11428. See the bum test report WO# 44969-00 and the form 8110-3, both dated 03-01.00 and approved by Judy Boggs, D.E.R. 5020-CE structural special. The lower door panel , aft side of the left hand partitlan and both game table inserts with leather pecan, TF-17 D/L 11429.See bum test report Wo # 44969-00 dated 03/01/00 and approved by Judy Boggs DER # DERV 405020-CE. Recovered the aft right hand partition, the outboard side of the aft stub partition. the three panels of the aft baggage compartment and the Inside of the fwd closet/galley cabinet with aircraft interior products, fabric, grospoint #440, beige, lot #8817-8824, treated at Skandia, Ref. Treatment #SKFP15268, see the bum test report WO#35268 dated 06-24-99 and the form 8110.3 dated 07-16.99, both approved by D.E.R. #CHI-410, Structural special. Cut, fitted, surged and installed new carpet throughout the cockpit and cabin area using aircraft interior products, CTM Pattern N r. ultra suede 034. See the burn test report #AIP stock and the form 8110-3 both dated 3-03-00 and approved b D.E.R. #60-572, structures (interiors).. Removed the pilot and copilot crew seat restraint systems. Both restraint systems were sent out to Am Safe, Inc. for rework. Installed both crew seat restraint systems P/N 504246-401-2291 after work was accomplished by Am- Safe, Inc. Reference both 8130-3 Forms dated 04-07-00 from Am-Safe, Inc. Removed the lavatory seat and all cabin seat belt assemblies and inertia reels. Sent all out to Belt Makers, Inc. for rewebbing. Installed the rewebbed lavatory seat and all cabin seat belt assemblies and inertia reels, see the certification paperwork, WO #31888R. The galley/closet, upright storage cabinet, fwd and aft bulkheads, game tables, drink ledges and the vanity cabinet was covered with Carl F. Booth & Co. Waterfall Buginga Veneer., requirements. All seven cabin seats and the lavatory seat were fireblocili ew illardance with FAR 25.853 (a) appendix F part I (a) reference the burn test report #22702 dated 04-15-00 approved by D.E.R. #DERY405020-CE, for the flammability (1) (II) and FAR 25.85) (c) appendix F part II amendment 25-83. The fireblocking was accomplished in accordance with the Skandia, Inc. test plan #5880 Rev. new dated 04-13-00, , reference the form 8110-3 dated 04-13-00 approved by D.E.R. #DERY-405020-CE, structural special. Reference the FM Form 337 dated 0414-00. Complied with AD 7408-09 R2 Transport category that have one or more lavatories equipped with paper or linen waste receptacles by installing placards as required by this AD. AD 98-25-10R1 Aircraft Belts, Inc. Seat restraint system does not apply due to aircraft belts being AM-Safe inc. aircraft seat belts. The work performed on this aircraft has been inspected in accordance with the current maintenance rules of the Federal Aviation Regulations and for the work performed this aircraft is approved for return to service. Weigh and balance change negligible. END Q Additional Sheets Are Attached * U.S. G. P.O 1990-791-753 PROT415 Form Approved uSOeparonent of Transportatfon - Administration ) rouece- 00b-61 ofr INSTRUCTIONS: Print or type all entries. See FAR 43.9, FAR 43 Appendix B, and AC 43.9-1 (or subsequent revision thereof) for instructions and disposition of this form. This report is required by law (49 PROT694. 1421). Failure to report can result in a civil penalty not to exceed $1,000 for each violation (Section 901 of Federal Aviation Act of 1958). Make Raytheon Model 400A 1. Aircraft Serial No. RK-244 N428HR 2. Owner See Attached Copy dd vin on registration certificate) Wichita, KS 67201 S. Typo Und Make Model Serial No. Repair Alteration described in Item 1 AIRFRAME (As above) X POWERPLANT C) C..i •-•C C.") PROPELLER • .. et . . 8 - -I a - t APPLIANCE Type - "" 00 0crt Manufacturer Kenneth W. Chitty X U.S. Certificated Mechanic 454944057 101 S. Webb P.O. Box 2902 Certified Repair Station Witchita, Ks 67201-2902 Manufacturer D. I certify that the repair and/or alteration made to the unit(s Identified in item 4 above and described on the reverse or attachments hereto have been made In accordance with the requirements of Part 43 of the U.S. Federal Aviation Regulations and that the information furnished herein is true and correct to the best of my know edge. Date 03-06-00 Signature of A 7. Approval for Retu Pursuant o the authority given persons specified below, the unit identified in item 4 was inspected in the manner prescribed by the Administrator of the Federal Aviation Administration and is 031 APPROVED 0 REJECTED FAA Fit Standards Inspector Manufacturer X BY FAA Designee Repair Station Canada Airworthiness Grou • 03-06-00 Certificate or 454944057 Signature of FAA Form 337 (12-88) 1r/ cc rn PROT416 NOTICE Weight and balance or operating limitation changes shall be entered in the appropriate aircraft record. An alteration must be compatible with all previous alterations to assure continued conformity with the applicable airworthiness requirements. (If mom space is required, attach additional shoots. Identify with aircraft nationality and registration mark and date 1•.a& completed.) Installed Dog Harness P/N CS-H-1 in accordance with Aerodesign Engineering Report 1912-1 Rev.IR, 6-9-96, ( Faa Form 8110-3 dated 03-03-2000 is the Approved Data ) "Structual Substantiation, Restraint Harness for a Dog, installed into an Aircraft." This installation meets FAR 25.853b-2 Flammability requirements. This harness will be stored with the NC loose equipment and a copy of the Engineering report will be placed in the Flight Manual, instructions are in paragraph 3.0 No Weight & Balance change. END K Additional Sheets are Attached PROT417 UNITED STATES OF規钢獻 DEPARTMENT OF TRA料SPORTATION-FEDERAL AVIATION ADMINISTR盯ION NATO世AL耐AND REGISTRATION 'ARKS 2. 咽剮鄲TURER AND h ODEL 3.觫CRAFT SERIAL NU nER .CATEGORY 暇黷蠟珊蒸戀鱗p轄Y N79n; R和244 5. AUTHORITY AND BASIS FOR ISSUANCE This airworthiness ceft翱郎鯽ed puts ant to the Federal Aviation Act of 195 and certifies that, as of the date o f issuance, the . a rcraft to which issued has been inspected and found to confofm to the type cectitate therC拖r, to be in condition for safe ope昭(ion: and has been sl own to meet the requirements of the applicable compreheilsive and detaited aim°rthiness code as provided by Annex 8 to the Convention on International Civil Aviation, except as noted herein, Exceptions' Unless sooner surrendefed, suspended, revoked, or a termina∥on date is otherwise甾伍廿ished by the Admin trator, this 胖onihiness cerl'kale Ise什ective as long as the maintenance .preventat e maintenance, and alle藺o鷓are perlorrned in accordance with Parts21.43.. d91 of theFederalAviatio fifiequ • lions,as appropriate, and the aircraft is registered in the United States, DESIGNATION NUMBER 可 璁囔鋤囤7 Any alteration, reprodu ion, or misuse of this cerlilicate may be punishable by a line not exceeding Si, 0,o imprisonment not exceeding 3.... years, or both, THIS CERTIFICATE MUST BE DISPLAYED IN THE AIRCRAFT IN ACCORDANCE WITH APPLICABLE FEDERAL AVIATION REGULATIONS,I FAA Form 81昤2 眸) . *U.S,G.P.0:1 8 66S028 PROT418 1 0 f. $ ' PROT419 1 NATIONALITY AND ' REGISTRATION MARYS N4281IR 2 11711d.UNIAiiirRALFT COMPANY 4001 NUMBER RK-244 4 CATEGORY TRANSPOR This airwortiness certificate is issued pursuant tote Federal Aviation Act of 1958and certifies that, as of the date of issuance, the aircraft to which issued has been inspected and lound to conform to the type certificate therefor, to be in condition for safe operation, and has been shown to meet the requirements of the applicable comprehensive and detailed airworthiness code as provided by Annex 8 to the Convention on International Civil Aviation, except as noted herein. Exceptions: NONE Unless sooner surrendered, suspended, revoked, or a termination date is otherwise established by the Administrator, this airworthiness certificate is effective as long as the maintenance, preventative maintenance, and alterations are performed in accordance with Parts 21,43, and 91 of the FederalAvialion Regulations, as appropriate, and the aircraft is registered in the United Stales. 10-01-99 MIR CE-50115, Any alteralion, reproduction, or misuse of thiscerhlicate may be punishable by a fine not exceeding S1,000, or imprisonment notexceeding 3 years, or both, THIS CERTIFICATE MUST BE DISPLAYED IN THE AIRCRAFT IN ACCORDANCE WITH APPLICABLE FEDERAL AVIATION REGULATIONS. FAA Form 8100.2 (8.,s2) *U,S, GOVERNMENT PRINTING OFFICE:1R31 • 668.228 PROT420 PROT421 Or ?-11 fol US Department Went Aviation Administration 1-orm Approved Office identification SW FSDO 17 INSTRUCTIONS: Print or type all entries. See FAR 43.9, FAR 43 Appendix 8, and AC 43.9-1 (or subsequen revision thereof) for Instructions and disposition of this form. This report is required by law (49 PROT695. 1421). Failure to report can result in a civil penalty not to exceed $1,000 for each such violation (Section 901 Federal Aviation Act of1959). 1. Aircraft Make RAYTHEON Model 400A Serial No. RK-244 USA N428HR 2. Owner Address WICHITA, KANSAS 67201-0085 3. For FAA Uso Only 5. Typo Unit Make Model Serial No. Repair Alteration AIRFRAME X POWERPLANT PROPELLER APPLIANCE Type Manufacturer I-A, Agency's Name and Address 8. Kind of Agency U.S. Dedicated Mechanic CRS-XA14605K RADIO CUSS I,II,III X Certificated Repair Station Manufacturer D. I certify that the repair and/or alteration made to the und(s) have been made in accordance with the requirements Date 12-22-99 of Part identified in item 4 above and described on the reverse or attachments hereto 43 of the U.S. Federal Aviation Regulations and that the Information 7 BY in item 4 was inspected in the manner prescribed by the fP APPROVED 0 REJECTED FAA Rt. Standards Inspector Manufacturer FAA Designee X Repair Station Canada Airworthiness Gro • 12-22-99 Certificate or CRS-XA14605K FAA Form 337 (1248) PROT422 NOTICE Weight and balance or operating limitation changes shall be entered in the appropriate aircraft record. An alteration must be compatible with all previous alterations to assure continued conformity with the applicable airworthiness requirements. (If more space is required, attach additional sheets. Identtot with aircraft nationally and registration mark and date kettlecompleted.) MAKE: RAYTHEON 400A Wit RK-244 REG: N428HR DATE: 12-22-99 INSTALLED AN ALLIEDSIGNAL FLITEFONE VI AIRBORNE RADIOTELEPHONE SYSTEM CONSISTING OF THE FOLLOWING EQUIPMENT: MOD/MFG DESCRIPTION WEIGHT ARM RT-18D REC/TRANSMITTER WRACK 400-0125-2000 7.8 47.8 WH-I0 HANDSET 400-0123-112 1.5 106.3 WH-IO HANDSET W/CORD 400-0123-112 2.5 252.0 AT-462 ANTENNA 121-014378-01 0.5 365.1 THE ALLIEDSIGNAL FLITEFONE VI SYSTEM WAS INSTALLED IN ACCORDANCE WITH THE BEECH AIRCRAFT CORPORATION DWG. #128-340675, REV. ORIGINAL, DATED 11-13-95 AND THE CHANGE ORDER #G76866 DATED 10-11-96. THE ELECTRICAL WIRING FOR THIS INSTALLATION WAS INSTALLED IN ACCORDANCE WITH THE BEECH AIRCRAFT CORPORATION DWG. 128-340606 REV. A DATED 10-27-94. A FUNCTIONAL TEST OF THE EQUIPMENT HAS BEEN PERFORMED IN ACCORDANCE WITH FAR 25.1301, FAR 25.1309 AND CHECKED IN ACCORDANCE WITH FAR 25.1431 FOR OPERATING SATISFACTORILY AND DID NOT ADVERSELY AFFECT OTHER COMPONENTS INSTALLED IN THE AIRCRAFT. THE ALLIEDSIGNAL FLITEFONE VI OPERATORS MANUAL P/N: 006-08834.0000 AND THE INSTRUCTIONS FOR CONTINUED AIRWORTHINESS DOC. #FF VI-ICA-RK-244 DATED 12-22-99 HAVE BEEN INSERTED IN THE AIRCRAFT AS PART OF THE AIRCRAFT'S PERMANENT RECORDS. THE AIRCRAFT WEIGHT AND BALANCE FORM AND EQUIPMENT LIST HAVE BEEN REVISED TO REFLECT THIS MODIFICATION AND BOTH FORMS HAVE BEEN INSERTED IN THE AIRCRAFT FLIGHT MANUAL. END- * U.S. GOVERNMENT PRINTING OFFICE: 1992-769-012/60157 PROT423 ,SAN ANTONIO, TX. PAGE 1 OF 2 DOCUMENT NO. FF VI-ICA-RK-244 DATE: 12-22-99 FOR A BEECHCRAFT MODEL 400A WITH AN ALLIEDSIGNAL FLITEFONE VI AIRBORNE RADIOTELEPHONE SYSTEM I. INTRODUCTION: THIS MAJOR ALTERATION TO THIS AIRCRAFT OBLIGATES THE AIRCRAFT OPERATOR TO INCLUDE THE FOLLOWING MAINTENANCE INFORMATION PROVIDED BY THIS DOCUMENT IN THE OWNER/OPERATOR'S AIRCRAFT MAINTENANCE MANUAL AND THE OWNER/OPERATOR'S AIRCRAFT SCHEDULED MAINTENANCE PROGRAM. 2. DESCRIPTION: THE ALLIEDSIGNAL FLITEFONE VI AIRBORNE RADIOTELEPHONE SYSTEM CONSISTS OF A RECEIVER/TRANSMITTER INCLUDING ITS MOUNTING RACK, TWO HANDSETS INCLUDING MOUNTING RACKS, TWO RETRACT CORDS, AN ANTENNA, ASSOCIATED WIRING, AND ANY RELATED HARDWARE. THE BASIC RADIOTELEPHONE SYSTEM IS A MOBILE COMMUNICATION SYSTEM FOR AIRCRAFT. IT OPERATES IN A FREQUENCY RANGE BETWEEN 454.675 - 454.975 Mhz 13 CHANNELS TO RECEIVE AND 459.675 - 459.975 Mhz 13 CHANNELS TO TRANSMIT. 3. CONTROL, OPERATION INFORMATION: REFERENCE THE ALLIEDSIGNAL FLITEFONE VI INSTALLATION MANUAL, REV. E, REPORT 1362, BASIC ISSUE DATED SEP. 1/90 AND THE ALLIEDSIGNAL FLITEFONE VI OPERATOR'S MANUAL P/N 006-08834-0000. 4. SERVICING INFORMATION: THE ALLIEDSIGNAL FLITEFONE VI AIRBORNE RADIOTELEPHONE SYSTEM IS ON CONDITION AND THERE IS NO PERIODIC, PREVENTIVE, OR SCHEDULED MAINTENANCE REQUIRED FOR CONTINUED OPERATION OF THIS SYSTEM. 5. MAINTENANCE INSTRUCTIONS: THE SCHEDULED MAINTENANCE TASKS REQUIRED BY THIS MODIFICATION TO BE ADDED TO THE AIRCRAFT OWNER/OPERATORS APPROPRIATE AIRPLANE MAINTENANCE PROGRAM AS FOLLOWS: a. PERFORM, ON AT LEAST AN ANNUAL BASES, A PERIODIC INSPECTION OF THE EQUIPMENT RACK, EQUIPMENT MOUNTINGS, ASSOCIATED WIRING, CABLES, CONNECTORS, HARDWARE, ANTENNA AND RELATED AIRCRAFT STRUCTURE FOR INTEGRITY, SECURITY, WEAR, CHAFFING, AND ETC.. SPECIAL ATTENTION SHOULD BE GIVEN TO THE AIRCRAFT PRIMARY STRUCTURE WITH REGARDS TO FATIGUE AND STRESS CRACKING, CORROSION, AND ETC.. 6. TROUBLESHOOTING INFORMATION: REFERENCE THE ALLIEDSIGNAL FLITEFONE VI AIRBORNE RADIOTELEPHONE SYSTEM MAINTENANCE MANUAL P/N 150-1364-000 REV. E, DATED SEP. 90 OR LATER REVISION. 7. REMOVAL AND REPLACEMENT INFORMATION: REFERENCE THE ALLIEDSIGNAL FLITEFONE VI AIRBORNE RADIOTELEPHONE SYSTEM MAINTENANCE MANUAL P/N 150-1364-000 REV. E, DATED SEP. 90 OR LATER REVISION. SHOULD IT BECOME NECESSARY TO REMOVE THE FLITEFONE VI, SECURE THE ASSOCIATED CABLES AND WIRING, COLLAR THE APPLICABLE CIRCUIT BREAKERS, PLACARD THE AIRCRAFT THAT THE UNIT HAS BEEN REMOVED, REVISE THE WEIGHT & BALANCE AND THE EQUIPMENT LIST AND MAKE A LOGBOOK ENTRY THE UNIT HAS BEEN REMOVED FOR SERVICE, REFER TO 91.213 OF TITLE 14 OF THE CODE OF FEDERAL REGULATIONS AND/OR THE AIRCRAFT'S MEL. 8. DIAGRAMS: THERE ARE NO ACCESS PLATES THAT NEED TO BE REMOVED FOR INSPECTION. 9. SPECIAL INSPECTION REQUIREMENTS: SPECIAL INSPECTION REQUIREMENTS ARE NOT APPLICABLE 10. APPLICATION OF PROTECTIVE TREATMENTS: APPLICATION OF PROTECTIVE TREATMENTS ARE NOT APPLICABLE. 11. DATA: INSTALLATION REQUIREMENTS MAY BE FOUND WITHIN THE ACCEPTED INDUSTRY PRACTICES CONTAINED WITHIN AC 43.13-1B CHAPTERS 4, 6, 7, 11, AND 12, AND IN ACCORDANCE WITH AC 43.13-2A CHAPTERS 1, 2, 3, II, AND 13. PROT424 %a PROT425 "RAYTHEON AIRCRAFT SERVICES SAN ANTONIO, TX. 12. LIST OF SPECIAL TOOLS: SPECIAL TOOLS ARE NOT REQUIRED. PAGE 2 OF 2 DOCUMENT NO. FF VI-ICA-RK-244 DATE: 12-22-99 13. FOR COMMUTER CATEGORY AIRCRAFT: NOT APPLICABLE, THIS AIRCRAFT NOT COMMUTER CATEGORY AIRCRAFT a ELECTRICAL LOADS: THE RAYTHEON AIRCRAFT SERVICES ELECTRICAL LOAD ANALYSIS DOCUMENT REV. DATED AND THE RAYTHEON AIRCRAFT SERVICES EMI/RFI GROUND TEST PROCEDURES DOCUMENT N REV. DATED HAVE BEEN PLACED IN THE AIRCRAFT AS PART OF THE AIRCRAFT's PERMANENT RECORDS. b. METHODS OF BALANCING FLIGHT CONTROLS: N/A TO THIS INSTALLATION c. IDENTIFICATION OF PRIMARY AND SECONDARY STRUCTURES: N/A TO THIS INSTALLATION d. SPECIAL REPAIR METHODS APPLICABLE TO THE AIRPLANE: N/A TO THIS INSTALLATION 14. RECOMMENDED OVERHAUL PERIODS: THERE ARE NO ADDITIONAL OVERHAUL TIME LIMITATIONS. IS. AIRWORTHINESS LIMITATION SECTION: THERE ARE NO ADDITIONAL AIRWORTHINESS LIMITATIONS. 16. REVISION: THE INSTRUCTIONS FOR CONTINUED AIRWORTHINESS CHECKLIST (ICA) MAY BE REVISED BY SUBMITTING A LETTER TO THE LOCAL FSDO WITH A COPY OF THE REVISED FAA FORM 337 AND REVISED ICA. THE FAA INSPECTOR ACCEPTS THE CHANGE BY SIGNING BLOCK 3 AND INCLUDING THE FOLLOWING STATEMENT: "THE ATTACHED REVISED/NEW INSTRUCTIONS FOR CONTINUED AIRWORTHINESS (DATE ) FOR THE ABOVE AIRCRAFT OR COMPONENT MAJOR ALTERATION HAVE BEEN ACCEPTED BY THE FAA, SUPERSEDING THE INSTRUCTIONS FOR CONTINUED AIRWORTHINESS (DATE )." ONCE THE REVISION HAS BEEN ACCEPTED, A MAINTENANCE RECORD ENTRY WILL BE MADE, IDENTIFYING THE REVISION, ITS LOCATION AND DATE OF THE FORM 337. 17. ASSISTANCE: NOT APPLICABLE. 18. IMPLEMENTATION AND RECORD KEEPING: a. FOR MAJOR ALTERATIONS PERFORMED IN ACCORDANCE WITH FAA FIELD APPROVAL POLICY, THE OWNER/OPERATOR OPERATING UNDER PART 91 IS RESPONSIBLE FOR ENSURING THAT THE ICA IS MADE PART OF THE APPLICABLE SECTION 91.409 INSPECTION PROGRAM FOR THEIR AIRCRAFT. THIS IS ACCOMPLISHED WHEN A MAINTENANCE ENTRY IS MADE IN THE AIRCRAFT'S MAINTENANCE RECORD IN ACCORDANCE WITH SECTION 43.9. THIS ENTRY RECORDS THE MAJOR ALTERATION AND IDENTIFIES THE ORIGINAL ICA LOCATION (e.g., BLOCK 8 OF FAA FORM 337) ALONG WITH A INSPECTION/MAINTENANCE REQUIREMENTS. b. FOR MAJOR ALTERATIONS PERFORMED IN ACCORDANCE WITH A FIELD APPROVAL ON AIR CARRIER AIRCRAFT, THE AIR CARRIER OPERATOR IS RESPONSIBLE FOR ENSURING THAT THE ICA IS MADE PART OF THE APPLICABLE INSPECTION/MAINTENANCE PROGRAM FOR THEIR AIRCRAFT. IF A PROCEDURE IS NOT CURRENTLY INCLUDED IN THE OPERATOR'S MANUAL TO INCORPORATE ICA, THIS PROCESS WILL NEED TO BE APPROPRIATELY ADDRESSED (i.e. THE OPERATOR SUBMITS A REVISION TO ITS MAINTENANCE PROGRAM TO THE APPLICABLE CERTIFICATE-HOLDING DISTRICT OFFICE (CHDO). a FOR AIRCRAFT INSPECTED UNDER AN APPROVED AIRCRAFT INSPECTION PROGRAM (AAIP), THE OPERATOR WILL SUBMIT A CHANGE TO THE CHDO IN ACCORDANCE WITH SECTION 135.419B. d. FOR AIR CARRIER AIRCRAFT INSPECTED USING AN ANNUAL 100 HOUR INSPECTION PROGRAM, A REFERENCE TO NEW ICA WILL BE MADE IN THE AIRCRAFT'S MAINTENANCE RECORD IN ACCORDANCE WITH SECTION 43.9. THIS ENTRY RECORDS THE MAJOR ALTERATION AND IDENTIFIES THE ORIGINAL ICA LOCATION (e.g., ICA ARE LOCATED/ATTACHED TO BLOCK 8 OF FAA FORM 337). IN ADDITION, THE OPERATOR WILL REQUEST A REVISION TO THE OPERATOR'S OPERATIONS SPECIFICATIONS, ADDITIONAL MAINTENANCE REQUIREMENTS, WHICH INCORPORATES THE ICA INTO THE INSPECTION PROGRAM. PROT426 PROT427 ea KS. Deputnient of I/deb:oration federal Aviation Admmoration Form Approved 02pe tdentification gene bYV FSDO 17 INSTRUCTIONS: Print or type all entries. See FAR 43.9, FAR 43 Appendix B. and AC 43.9-1 (or subsequen revision thereof) for instructions and disposition of this form. This report is required by law (49 PROT696. 1421). Failure to report can result in a dvii penalty not to exceed 51000 for each such violation (Section 901 Federal Aviation Act of 1958). 1. Aircraft Make RAYTHEON Model 400A Serial No. RK-244 USA N428HR 2. Owner Address As shown on registration certificate) WICHITA, KANSAS 67201-0085 3. For FAA Uso Only 5. Type Unit Make Model Serial No. Repair Alteration AIRFRAME X POWERPLANT PROPELLER APPLIANCE Type Manufacturer RAYTHEON ALRCRAFT SERVICES RADIO CRS-XA14605K CLASS MUM X certificated Repairs tation Manufacturer D. I net* that the repair and/or alteration made to the unit(s) have been made in accordance with the requirements Date 12-22-99 of Part the is identified in item 4 above and described on the reverse or attachments 43 of the U.S. Federal Aviation Regulations and that the information hereto specified below, Administration and BY Pursuant to the authority given persons Administrator of the Federal Aviation unit identified in item 4 was inspected In the manner prescribed by the 0 APPROVED 0 REJECTED FAA Rt. Standards Inspector Manufacturer Other (SIKCifY) FM Designee x I Repair Station Person Approved Canada Airworthin by Transport - p • Date of Approval 12-22-99 or Rejection Certificate or CRS-XA14605K FAA Form 337 (I2-8e) PROT428 NOTICE Weight and balance or operating limitation changes shall be entered in the appropriate aircraft record. An alteration must be compatible with all pmvious alterations to assure continued conformity with the applicable airworthiness requirements. (It more space is required, attach additional sheets Identify with aircraft nationality and registration mark and date work completed.) NINCE: RAYTHEON 400A S/N: RK-244 REG: N428HR DATE: 12-22-99 INSTALLED A SUNDSTRAND MIC-VI GROUND PROXIMITY WARNING SYSTEM CONSISTING OF THE FOLLOWING EQUIPMENT: MOD/MFG DESCRIPTION P/N WEIGHT ARM MK-VI GPWS COMPUTER 965-0686-020 4.2 33.1 ADC-500 CONVERTER 500-8020 2.3 38.2 BRACKET & PLATE 0.5 36.1 WIRING & CONNECTOR 3.5 54.0 THE SUNDSTRAND MK-VI GPWS SYSTEM WAS INSTALLED IN ACCORDANCE WITH THE STC #SA3322SO ISSUED 09-18-92 AND REISSUED 10-04-95 AND THE HANGER ONE MASTER DRAWING LIST #11892-GPWS, REV. D DATED 03-22-93. THE ELECTRICAL WIRING WAS INSTALLED IN ACCORDANCE WITH THE RAYTHEON AIRCRAFT SERVICES DWG. #RAS-67-9917 REV. IR DATED 11-05-99, REFERENCE THE FORM 8110-3 DATED 11-23-99 APPROVED BY ROBERT M. HURLEY, DESIGNATED ENGINEERING REPRESENTATIVE #DERT-710137-SW, SYSTEMS AND EQUIPMENT. A FUNCTIONAL TEST OF THE EQUIPMENT HAS BEEN PERFORMED IN ACCORDANCE WITH FAR 25.1301, FAR 25.1309 AND CHECKED IN ACCORDANCE WITH FAR 25.1431 FOR OPERATING SATISFACTORILY AND DID NOT ADVERSELY AFFECT OTHER COMPONENTS INSTALLED IN THE AIRCRAFT. THE SUNDSTRAND MK-VI GPWS APPROVED FLIGHT MANUAL SUPPLEMENT, REV. B DATED 03-30-93 HAS BEEN INSERTED IN THE SUPPLEMENT SECTION OF THE AIRCRAFT FLIGHT MANUAL AND THE GPWS PILOT'S GUIDE P/N 060-4087-000 REV. A DATED 10-96 HAS BEEN INSERTED IN THE AIRCRAFT AS PART OF THE AIRCRAFTS PERMANENT RECORDS. THE AIRCRAFT WEIGHT AND BALANCE FORM AND THE EQUIPMENT LIST WERE REVISED TO REFLECT THIS MODIFICATION AND BOTH FORMS WERE INSERTED IN THE AIRCRAFT FLIGHT MANUAL. END - D Additional Sheets Are Attached * U.S. GOVERNMENT PRINTING OFFICE: '992-769-012,60157 PROT429 tad Ztatta Drxrim Beparanutt of transportation - fuleral 2thation Sadminisattion *upplemental tgpe Certificate c../Yetzinkit- al rcs, Inc. Fulton County Airport-Brown Eteld Atlanta, Georgia 30336 .gatiZadLa.7 .,.4w,a(4/i02.erirvA-fefe,i/owthns idoedmiXearnitalthn444;td.oniefedin;a SA3322SO .d.. A. ;a4,0friatadifenowoneater aaizaameraiemena-ari 25 a r ze.ama. iternsia e - peeareA.L.Snee...ate: "ea Al6SW Beech 400A -44 ale-a9/47/ 5-Sesrv 4 k 2r: Installation of a Sundstrand MK VI GPAYWn necordance with ranger One. Drawing List No. 11892-GPWS, Rev. B, dated September 17, 1992, or I/16;r FAA Approved revision. Seciiim-44andLrea:rnad: This approval should not be extended to other aircraft of this model on which other previously approved modifications are incorporated unless it is determined by the installer that the interrelationship between this change and any of those other previously approved modifications will produce no adverse effect upon the airworthiness of that aircraft. FAA Approved Airplane Flight Manual Supplement, dated September 18, I992, is a required part of this STC. ir ewasaxeitseesandiefry4eWores:rdir eataithukte,oPS'leitis-r.Wren ,a1,44esasrarre.esess,.e:tv.#4-4wesatias- S.2;:s4rai tars,z..1;:w COP2neiuIenx/Zon. August 5, 1992 September 18, 1992 October 4, 1995 Associate Manager, ACE-116A Atlanta Aircraft rertifititinn Offira (Title) Any alteration of this en:Orate is punishable by a fine of not exceeding ;1,000, or imprisonment not exceeding 3 years, or both. This route nay be transferred in accordance with FAR 21.17. CAA rota 6110-2 11 0-60) PROT430 4- PROT431 I II IV I L-I JJI~t-i1N_INV L_ .L - DWG. LIST NO. 11892- GPWS DATE 9/1/92 REV. D DATE 3/22/93 ET 1 OF 1 SYSTEM SUNDSTRAND MK- VI GPWS F. A. A. PROJECT NO. CE- 115A- 2970 . AIRCRAFT TYPE BEECHJET 400E STC SA 3 -3 2 2S0 DATED 9/18/92 DRAWING NO. REVISION SHTS PAGE EO/REMAR LTR DATE TITLE TRI- 92- 108 9 - 2- 92 STRUCTURAL SUBSTANIATION REPORT GPWS AFMS B 3/22/93 AIRPLANE FLIGHT MANUAL SUPPLEMENT S 060- 3942 6/92 INSTALLATION DESIGN GUIDE 11892- 2 A 3/22/93 INSTALLATION PROCEDURES 11892- 3 A 3 / 2 2/93 BLOCK DIAGRAM 1 1 11892- 4 D 3/22/93 WIRING DIAGRAMS 2 182 11892- 5 8 - 29- 92 PARTS LIST & GENERAL NOTES 11892- 6 8 - 29- 92 GPWS MOUNTING PLATE 11892- 7 8 - 31- 92 ADC-S[ADDRESS REDACTED]ATE 11 '- 8 8 - 29- 92 SUPPORT BRACKET 892-1 A 3/22/93 GROUND TEST PROCEDURES 060- 3956- 000 D 9/17/92 FLIGHT TEST PROCEDURES 500- 8000- RO 8/29/92 DESIGN SPECIFICATIONS ADC-S00 PROT432 • d a PROT433 U.S DEPARTMENT OF TRANSPORTATION STATEMENT OF COMPLIANCE WITH THE FEDERAL AVIATION REGULATIONS DATE 11)23/99 HAKE Beech MODEL NO. 400A TYPE Muria Rodeo. Idelmopstr. toc.I Airplane NAME OF APPLICANT Raytheon Aircraft Services LIST OF DATA - - IDENTIFICATION TITLE Raytheon Drawings RAS-67.9917 Rev IR Dated 11/05/99 Sundstrand Mk-VI Ground Pro>amrty Warning Sys Note: This approval is for the Electrical aspects of the engineering design data only, and is not installation approval. Approval for aircraft SIN RK-244 only. Approval for GPWS is for only the minor deviations to FAA STC SA3322SO. After modification is complete, perform EMURFI test In accordance with Raytneon report RAS-GF-9714, EMI/RF1 Test Procedure. PURPOSE OF DATA In support of a modification to install a GPWS in serial number RK-244. APPUCAS LE REOUIREMENTS(ArtspeoficcaA) FAR 25.1301 a,b,c FAR 25.1359 d FAR 25.1431 c CERTIFICATION - Under authority vested by direction of the of appointment under Pan 183 of the Federal Aviation Regulations, None have beat examined Administrator and in accordance with conditions and dam listed above and on attached sheets numbered in accordance with established procedures and found limitations to comply with applicable requirements of the Federal Aviation 70W Therdore K Rccommead Regulations. approval of That data these this ra Approve SIGNATURE(SI OF DESIGNATED ENGINEERING R AWES) DESIGNATION NUMBERS(E) CLASSIFICATIONS) DERT-710137-SW Systems & Equipment FAA Form 8110-3 (i1.70)9SEPMCESPRETICUS ENRON OFOreal 11- 23-99 13:SS RECEIVED FRO14:512 989-2998 P.03 PROT434 t PROT435 Form Approved O.M.B. No.21208018 0 LLSDeporimcre AIRWORTHINESS of tonsponalicn CERTIFICATE Federal Arlation Administration INSTRUCTIONS - Print or type. Do not write in shaded areas: these are for FM useonly. Submit original only to an authorized FM Representative. II additional spacers required. use an attachment For special fight penes compete Sectaans II and VI or VII as applicable I. AIRCRAFT DESCRIPTION 1REGISTRATION MARK N428HR 2AIRCRAFT BUILDERS NAILS (Make) 3. AIRCRAFT MODEL DESIGNATION 400A 4.YR. MFR 1999 FM CODING 7,s cc 1 0 5. AIRCRAFT SERIAL NO. RK-244 6. ENGINE BUILDERS NAME WNW Pratt & Whitney Canada 7. ENGINE MODEL DESIGNATION JT15I3-5 tif L S 8. NUMBER OF ENGINES 2 9. PROPELLER BUILDERS NAME (Mike) N/A 10. PROPELLER MODEL DESIGNATION N/A 11. AIRCRAFT LS (Check t I apptitable) (IMPORT II. CERTIFICATION REQUESTED APPLICATION IS HEREBY MADE FOR: (Check applicable awns ) A 1 X STANDARD AIRWORTHINESS CERTIFICATE (Indkate category) I Th)RMAI I I Inure t (ACROBATIC x (TRANSPORTI I GLIDER I BALLOON B SPECIAL AeftWOFITHINESS CERTIFICATE (Clerk Aapropda Ferns) 2 LIMITED 5 1 CLASS I PROVISIONAL (Mc:rate doss) 2 CLASS II 1 AGRICULTURE AND PEST CONTROL 2 AERIAL SURVEYING 3 AERIAL ADVERTISING 3 RESTRICTED (indicate opention(s) to be conducted) 4 FOREST (Wida(e conservation) 5 PATROLLING 6 WEATHER CONTROL 7 CARRIAGE OF CARGO 0 OTHER (Spear) EXPERIMENTAL flmacare operation(4) 1 RESEARCH AND DEVELOPMENT 2 AMATEUR BUILT 3 EXHIBITION 4 to be Conducted) 4 RACING 5 CREW TRAINING MKT. SURVEY 0 TO SHOW COMPLIANCE WITH FAR I FERRY FLIGHT FOR REPAIRS. ALTERATIONS. MAINTENANCE OR STORAGE 8 SPECIAL FLIGHT PERMIT ancricale 00rvattbn to be conducted. then 2 EVACUATE FROM AREA OF IMPENDING DANGER complete Section VI or Fil as side) 3 OPEAT)ON IN EXCESS OF MAXIMUM CERTIFICATED TAK