DS9 Document EFTA01261592

el fr MAJOR REPAIR AND ALTERATION US Dess-rrnm of Tr systukn (Airframe, Powerplant, Propeller, or Appliance) Pram /Matron AthillnlitiliCOO cwa ne.2120402) Ey S414011I neves Tweet wear MA Um One INSTRUCTIONS: Mint or type See Tide 14 CFR Part 43 Append; B, AC 43.9-1 (or subsequent thereof) for as entries. §43.9. and revision instruceons and caposidon of Ws form. Ms report Is rewired by law µ9 U.S.C. §44701). Falun) to report can result in pen" for each such violation. (49U.S.C.§41001(a)) 1. Aircraft NadanalitY and Registrebon Mark N727KB Serial No. RK-260 Make Beech Model 400A Sancta 2. Owner Name (As shown on registraton certincate) PUMPJACK AVIATION LLC Address (As shown on registration certificate) banns 1511 W EPA 91 CA) Caoo. Stab [VICTIM NAME REDACTED] 026014203 Couruy USA 3. For FM Use Only 4. Type S. Unit Identification Repair Mention Unit Make Made( Serial No. O in AIRFRAME . both (As described fn non? I above) RX. 410 O O POWERPLANT O O PROPELLER O O APPLIANCE Type stsmeaclunar 6. Conformity Statement A. Agency's Name and Address B. Kind of Agency sere ShresiAter a Clones Moon 4 U. S. Ciellfirsiteci ~ado 1 Manufacturer we. Amino* ForrionCernacesso Mechanic C. Certificate No. orr SS Or KS Swoon 3437625 SI 0117 convi 115A ms s; nence Organize:al 0. !entry that the repair and/or alteration made to the unit(s idenefled at tarn 5 above and described on the ravens or attachments hereto have been made in accordance with the requirements of Pan 43 c4 the U.S. Federal Aviation Regulations and that the information furnished heroin es bye and correct to ere bast of my knowledge. per t4 CFR Part 43 K Extended range fuel 91 APP. B of horized Inctrvidual t -1q 4 020 7. Approval for Return to Simko Pursuant to the authority 9 ven persons specked below. the Unit identified in sera 5 wee inspected in the manner ;ascribed by the Administrator of me Federal Aviation Administration and is plApproved nitelectee BY FM FF. Standards Inspector Manufacturer Maintenance Organization Panora ApPreNed KY Canna" Department of Trooper FAA Designee Repair Station X Inspection AUtlailtrilial Other (SpeCd4 Certificate Cf Designation No.3437625 SigrultufWDEKEI of Authonzod Individual a ff C'S I ti - 20/30 FAA Form 337 (10/06) Page I SDNY_GM_02758010 SUBJECT TO PROTECTIVE ORDER PARAGRAPHS 7, 8, 9, 10, 15, and 17 EFTA_00244932 EFTA01261592 NOTICE Weight and balance or operating limitation changes shalt be entered in the appropriate aircraft Ward. An alteration must be COnwabble with all previous alterations to assure continued conformity MO the applicable airworthiness requirements. S. Descapdan of Work Accomplished (If more space is tallied. attach odoloons) 31100t3 Identify wen efroWt netiOneety end regiavellon mem end Wife *or* completed.) .4777101 •1420 Netionelty and Registration PAWS Dale Installed copilot windshield P/N: LA45AS31001-024, S/N: 10013 under STC no. ST018935WI. Weight and balance revision no factor. ClAddelonal Sheets An Attached FM Form 337 (10/06) Page 2 SDNY_GM_02758011 SUBJECT TO PROTECTIVE ORDER PARAGRAPHS 7, 8, 9, 10, 15, and 17 EFTA_00244933 EFTA01261593 0 MAJOR REPAIR AND ALTERATION u s Deaem mintof (Airframe, Powerplant, Propeller, or Appliance mmert moos *ewe Awnwaw Fano Amend CAM No 2i20.4020 r30,2C07 Meannic IRON Nods Fos FAA Me Only INSTRUCTIONS. Print or type all entries Soo FAR 43.9. FAR 43 Append.% B. and AC 43.9-1 (or subsequent Rowe therocif) for mabuctions and discos/Son of tie limn. This nowt is required by ern (49 U S C 1421) Faikrra ki. report can result In CM pearly not to exceed x1.000 far tab such Waco (Section 901 Federal Anton Act 1958) 1 . Aircraft Natonallty and Regisastion Mark N727KB WW1 No RK-260 Make Raytheon Aircraft Company Model 400A 1 See. 2. Owner Name (Ai Mown on registration corterain) Flight Options .LLC Moss, Awe) Anson t PKWY Ct, wt. OH no USA 3. For FAA Use OW 4. Type E. Unit itiontincatlon Repair Maralke Unit Make MOW sone Number CI El AIRFRAME PM described In ;tern I above) 0 0 POWERPLANT 0 0 PROPELLER El El APPLIANCE Taw mieuracam IL Conformity Statement A Agency's Name and Address B. KM of Arcot OH Ma 0 U.S. Ceraficated Mechanic 0 IMenufacturer 0 Foreign Ceraicated Mechanc C. Certificate No. 0 CsnAcale[ADDRESS REDACTED]aten CRS # VVC7R34SJ 0 Centime:0 MaIntonanCe OnoWitation o made to the uni(s) Idwitlfied In Nam 5 atcre• and deleted on the reline or attaChmentS hatid0 have been made n aCCOrdatiOn wet the niquiromeras d Part 43 of Me U.S. Facet* Adam Repulsions and IoM Urbana/ion furnished herein is true and coned to the best of my ImoMedpe. Extended rano fuel Wisea 14 CFR Pal 43 0 MostireiDete al AtOorIzed Irdni3ual Anton J. Koprivnik r 02/24/2020 7. Approval for Return ba Pursuant to the authority given persons maned below. the uM klenakid ii Rem 5 was Impacted in to manner presorted by the Admmotrator of ale Federal Aviation Adrnolinranal and is El rePROWO 0 REJECTED BY FM Fit Standards inspector Manutactutw Maintenance Orponitaton Parson Approwdl by Camden Department of Tranapon FM Oesagnee X Repot staton Meg SOW) Impecte Aultiorttabon Grant* or Desianatfon No CRS I VVC7R348.) Sgricurelosto Of Author/ad Irendual oy z zz ,/' An on J. Koprivnik 02/24/2020 A / FAA Fort 337 IOW SDNY_GIv10275801 2 SUBJECT TO PROTECTIVE ORDER PARAGRAPHS 7, 8, 9, 10, 15, and 17 EFTA_00244934 EFTA01261594 SDNY_GM_02758013 SUBJECT TO PROTECTIVE ORDER PARAGRAPHS 7, 8, 9, 10, 15, and 17 EFTA_00244935 EFTA01261595 NOTICE woof and balance or operating limitation changes shall b e entered in Me appropriate aircraft word. An alteration must be compatible with ail pievfous mentions to assure continued conformity with the applicable ainvorthiness requirements S. Description of Work Accomplished (if mote space Is required, attach additional sheets Identity with *cab nationably and registration mark and date work completed) N727KB Nationality and Registration Mark 02/24/2020 Data This 337 is to correct the original Dated 01/04/2013. Corrected block ti I, Registration number from N746TA to N787TA and fills in the serial number to Ft/C-260. All other data is correct. 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 6224189-002 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-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 Display Control Panel 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 SOD-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 (2) 822-0891-008 Flight Management Computer PWR-4000 (4) 622.9945-021 IAPS Power Card GPS-4000 822-0931-003 GPS Receiver Mounts 622-9430-002 EFD /MFD Mounts EFB Electronic Flight Bag Mounting EAdditional Sheets Are Attached Form 337 0046) SDNY_GM_02758014 SUBJECT TO PROTECTIVE ORDER PARAGRAPHS 7, 8, 9, 10, 15, and 17 EFTA_00244936 EFTA01261596 SDNY_GM_02758015 SUBJECT TO PROTECTIVE ORDER PARAGRAPHS 7, 8, 9, 10, 15, and 17 EFTA_00244937 EFTA01261597 NOTICE Weight end balance or operating limitation changes shag be entered In the appropriate aircraft record. A n alteration must be compatible with all previous alterations to assure continued conibmity with the applicable aimorthiness requirements S. Description of Work Accomplished (If more space is required, attach additional sheets Identify with aircraft nationality and ragisfrabon mark end date work completed) N727KB Nationality and Registration Ma* Page 2 of 3 Installed the Following Equipment along with Associated Hardware. 02/24/2020 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 fig IFIS) 6.5 60.83 ECU-3000 822-1200-998 File Server Unit (1st IFIS) 0.40 57.5 AFD-3010E 822-1753-416 Adaptive Flight Display 12.90 89.2 AFD-3010E 822.1753.416 Adaptive Flight Display 12.90 89.2 AFD-3010E 822-1753.416 Adaptive Flight Display 12.90 89.2 AFD-3010E 822-1753-416 Adaptive Flight Display 12.90 89.2 IMT-3010 822.1140401 AFD Mounting Rack 4.40 85.0 IMT-3010 822.1140-401 AFD Mounting Rack 4.40 85.0 IMT-3010 822-1140-401 AFD Mounting Rack 4.40 85.0 IMT-3010 822-1140-401 AFD Mounting Rack 4.40 85.0 10852301700 Fuel Quantity Conditioner 0.90 324 PC920-2A2000PH-2A1 Fuel Flow Conditioner 1.10 325 GPS-40005 822-2189-004 GPS 6.0 37 CI 429.200 GPS/XW Antenna 1.0 166.14 Amp Cluster N241100-002 DC Voltmeter 1.5 97.4 373.93.1501-1 Speed Switch x2 0.25 89.2 D8U-5010E 822-2215-202 Data ease 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 822-1290-003 AHS Mounting Rack 1.80 57.5 MMT-3010 822.1290-003 AHS Mounting Rack 1.80 57.5 CHP-3010 822-1280-002 Course Heading Panel 1.30 92.5 Options Configuration Module OCM-4103 822.1463.228 0.30 57.5 WAAS/I.PV OCM4100 822.1463.228 Options Configuration Module 0.30 57.5 WAAS/tPV El AddlilOnil Shuts Ni Attar:hart Form 337 (won SDNY_GM_02758016 SUBJECT TO PROTECTIVE ORDER PARAGRAPHS 7, 8, 9, 10, 15, and 17 EFTA 00244938 EFTA01261598 SDNY_GM_02758017 SUBJECT TO PROTECTIVE ORDER PARAGRAPHS 7, 8, 9, 10, 15, and 17 EFTA_00244939 EFTA01261599 NOTICE Weight and balance or operating Amitatlon changes shall be entered in the vampish, airtualt record. M alteration must be canoe:Age wait at previous alterations ro assure continued calamity with the applicable einvorthiness requirements. 8. Description of Work Accomplished Of more specs is required, attach additional sheets, identify with aircraft natbnally and registration ma* and date yak completed.) N727KB Nationmay and Registration mark Page 3 of 3 02/24/2020 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 AMC-3000A (2) 822.1378-001 Attitude Heading Computer 4.80 57.5 DCP-3030 (2) 822.1828-002 Display Control Panel 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 XM WR-1000 822-2031-002 XM Weather 41.0 LT-4001-010 Master Caution Panel 1.3 87.0 Rev. Panel 373-91.3203-1 Pilot Reversion Panel 0.2 88.0 Rev. Panel 373.91.3203.3 Co-pilot Reversion Panel 0.2 88.0 9-PEG [SSN REDACTED]-9 9-Pedestal Panel 1.8 92.89 345-6169 ELT Switch 0.2 88.0 Annunciator 2-F840233-I AUX BATT (1/2) Annunciator 0.05 88.0 Annunciator (2) 2-F840232-I Pull Up/ Terrain Annunciator 0.05 88.0 Annunciator 2-F840231-I TERR INHBT/ TERR Fall 0.05 88.0 In Accordance with SIC ST10959SC. See Attached Copy AFM Supplement, Nextant Aerospace Doc. No. [SSN REDACTED] Rev IR Dated 09/02/2011 or later FM 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 IAW 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. Aircraft Weighed see Report Dated 12/21/2012 K Additonal Sheets Are Attached town 337 hoes) SDNY_GM_02758018 SUBJECT TO PROTECTIVE ORDER PARAGRAPHS 7, 8, 9, 10, 15, and 17 EFTA 00244940 EFTA01261600 SDNY_GM_02758019 SUBJECT TO PROTECTIVE ORDER PARAGRAPHS 7, 8, 9, 10, 15, and 17 EFTA_00244941 EFTA01261601 0 MAJOR REPAIR AND ALTERATION Js : v.:m.3,n cl "rvdp:cisi.., (Airframe, Powerplant, Propeller, or Appliance) Nam! anon Adrileilaatlen Fan /wares ONO PO 2,10490 Metal (Yawn 'wiry Naas Fee MAIM 0.1. eNSTRUCTiCtiS: Pala w tyre all entnes See Tee 74 CFR 1.3.0. Pan 43 Appendix S. IS AC 13.91 (or subtentinni tensing' Pew!) be inStilietan and dillmalllon of Ws fern This report la required by law (49 U.S.C. §44701). Failure lo report can resutt in a civil penalty for OaCh such Vidalia,. (49 U.S.C. 946301(1)) Nationality and ReptilitIon Mark USA N727KS Serial No. RK-2S0 1. Micron Make Raytheon Aircraft Company uaaa Saes 4 Name (As shown on rep/groom contecale) Ad 2. Corner Co Nan MN. XT Leasing CO. LLC as 3. For FAA Use Only I The data identified herein complies with the applicable DALE E sinvoithiness requiremenu and ts approved for the above desenbed aircraft, subject to oonfomilty Inspection by a person DRENCKHAHN """aa an authorised in I4CFR 13.7 FAA Inspector MSP-FSDO•GLI5 4- WM & UMIldentlflealon Repair Minion Urn Make Model Serial No • RI AIRFRAME kern 1 (4.5 deserts : f in above) 0 0 POIM1ERPtANT 0 0 PROPELLER CI O APPLIANCE Tape wanutaawar 4. Confonwity 91altenteril I 0 Kind of Agency S. knorwrie U. Canes I Menufedurin Falign Canicard Mahe* C. Catibleale NO. / CankaMORaork Simon I cartileand Malnwenos OrganiaMlon KX5R005N I have been made in accordance lurnnhed Wain Is bee and coned ( ) Centime in awn el above antleemotied on ma reverse orattadtrnents hereto with the repukemenla of Pert 43 of Me U.S. Federal Analog, Regulannte and that the information to Me best of my knowledge. Extended range Net pee 14 CFR Pan 43 O APO a Signature/Dele orMed Intivkluil .5- /1-.2o ( f-^ 7. Approval for Return to Service l e Pursuard to the eugmnty Yuen persons spec-Fed below. Me unit Identified in nem 5 was impeded in Ma manner pretabged by Admenstralor of me Federal Aviation Acknostiaten and is 2 Appienied 0 Rejected SY FAA Mt Standards Inspector Manufacturer Maintenance COMnizabon Parkin AppeNed by tannin Demotion ce Troweat FAA Designee / Reba, Sleben Inspection Audit:enamel OthW (SPonF)7 Ceatificalo or Designation NO KX5R005N Sigratunut of Aulbeetzed tridrenualz , --e---g-7 .... ..--dezn S^I )- 2o /i.-- FAA Form 337 rrcm. SDNY_GM_02758020 SUBJECT TO PROTECTIVE ORDER PARAGRAPHS 7, 8, 9, 10, 15, and 17 EFTA_00244942 EFTA01261602 SDNY_GM_02758021 SUBJECT TO PROTECTIVE ORDER PARAGRAPHS 7, 8, 9, 10, 15, and 17 EFTA_00244943 EFTA01261603 NOTICE Weight end balance or operating Mutation changes Shea be entered in the appropnale aircraft record An alteration must be COmpebblit with el previous *Aerations to assure continued conlomety whir the applicable airworthiness requirements. IL DewSart of Work Accomplished (If ma were re reaaed each actitaned sheets leen* rani entre natfoneity end movie:Kra malt and date tarkCariplered) USA 14727 KI3 Nakielity and Realltretren Mark [ Date 1. Installed Gamin Automatic Dependant Surveillance-Broadcast (ADS-6) system referencing Elliott Aviation Technica Products Development Inc. drawings 121.3761-M0560.60 revision IR, and 121-4070-E0560-000 revision PA. A satisfactory ground test of the ADS-8 Out system was completed using a Aerofiek IFR-6000. checking for proper configuration and equipment performance requirements. The Installed ADS-B Out system has been shown to meet the equipment requirements of 14CFR 91.227. 2. The following LRU's are installed and interfaced referencing the previously approved equipment pairing of the GTX-3000 Mode '5' transponders and the GDL-88 Universal Access Transceiver by STC ST04214CH. a) Removed existing Rockwell Collins TOR-94D Mode "S" Transponders pin 622.9210-004. sin's 3MPD. and 6053 from right hand upper avionics shelf at sta 48. Installed two Gamin GTX-3000 Mode "S. Transponders (TSO-C112d), pin 011-01997-00, on right hand upper avionics shelf, s/n 20S008042 at sta. 49.7. and s/n 20S008050 at ste. 52.95. b) Installed a Garmin GDL-88 Universal Access Transceiver (TSO-C154c), p/n 010-00860-30. s/n 22U000700 on right hand upper avionics shelf at sta 46.95. The G0L-88 is connected to a GA-36 Antenna (TSO-C144), p/n 013-00244-00 s/n 14145 at sta. 128.7 through the GPS port and a UAT Antenna (TSO-C86c) p/n CI710.40.30. s/n 522354 at Ma. 35.1 for the FIS-B weather function. c) Installed a Garmin Flight Stream 110 (TSO-C157), p/n 010-01194-01. s/n 3G0000731 on the co-pilots manual holder at sta 136, interfaced to the GDL-88 UAT. The Flight Stream 110 provides FIS-B weather, ADS-B traffic, and GPS position data. 3. The FAA Approved Airplane Flight Manual Supplement for the Garmin Automatic Dependant Surveillance (ADS-B) Transponder installation ReporNumber FMS-4079-560 Revision IR, dated was placed in the Aircraft Flight Manual and must be available to the pilot at all times. 4. Structural work performed referencing the following: Elliott Aviation Technical Products Development Inc. drawing 121-3761-M0560-60 revision IR. Beechcraft Corporation Model 400/400A Maintenance Manual p/n 128-590001.9 Revision C29, Beechcraft Corporation Structural Repair Manual phi 128590001.17 Revision C16. and acceptable methods contained in AC43.13-1B. chapter 4, si.c.uon 4, and AC43.13-28, chapters 1,2,and 3. 5. The electrical interface of the Garmin Automatic Dependant Surveillance (ADS-8) Transponders was performed referencing Elliott Aviation Technical Products Development Inc. drawing 121-4070-E0560-000 revision PA. Wiring fabrication and interface performed in accordance with Beechcraft Corporation Beechjet 400/400A series wiring manual pin 128-590001-79 Revision 0, and acceptable practices contained in AC43.13.18, change 1, chapter 11. I 6. Weight and balance and equipment list have been revised to reflect this installation. 7. Instructions for Continued Airworthiness, Elliott Aviation Technical Products Development Inc Report ICA-4079-560 Revision IR , provided in aircraft records. END AOrlibcoad Sheets Are Attached FAA Form 337 imam SDNY_GM_02758022 SUBJECT TO PROTECTIVE ORDER PARAGRAPHS 7, 8, 9, 10, 15, and 17 EFTA_00244944 EFTA01261604 SDNY_GM_02758023 SUBJECT TO PROTECTIVE ORDER PARAGRAPHS 7, 8, 9, 10, 15, and 17 EFTA_00244945 EFTA01261605 l e 41; Elliott Aviation Technical Products Development, Inc. 6601 74m Ave Building A Milan. IL 61264 ELLKYIT AVIATION Instructions for Continued Airworthiness For Garmin ADS-8 System Installation Report No.: ICA-4079- Revision Dated 05/01121 1 01 60 IR 18 19 Instructions for Continued Airworthiness For Garmin ADS-B Out System Installation (Type Certificate A16SW) 0 Z018 ELUOTT AVIATION TECHNICAL PRODUCTS DEVELOPMENT. INC. Elliott Aviation Technical Products Development. Inc. reserves the copyright of all information and illustrations in this publication which is provided in confidence and which may not be used for any purpose other than for which it was onginally supplied. The pubica - may not be reproduced in part or in whole without the consent in writing of Elliott Aviation Technical Products Development. Inc II SDNY_GM_02758024 SUBJECT TO PROTECTIVE ORDER PARAGRAPHS 7, 8, 9, 10, 15, and 17 EFTA_00244946 EFTA01261606 SDNY_GM_02758025 SUBJECT TO PROTECTIVE ORDER PARAGRAPHS 7, 8, 9, 10, 15, and 17 EFTA_00244947 EFTA01261607 • Elliott Aviation Technical Products Development Inc. 6601 74" Ave Building A Milan, IL 61264 EWOTT AVIATION Instructions for Continued Airworthiness for Garin ADS•8 S tem Installation Report No.: ICA-4079-660 Revisi• : IR Dated 05/0112 8 2. 19 REVISIONS PAGE Rev Description Page (S) Date Approved By IR Initial Release ALL SDNY_GM_02758026 SUBJECT TO PROTECTIVE ORDER PARAGRAPHS 7, 8, 9, 10, 15, and 17 EFTA_00244948 EFTA01261608 SDNY_GM_02758027 SUBJECT TO PROTECTIVE ORDER PARAGRAPHS 7, 8, 9, 10, 15, and 17 EFTA_00244949 EFTA01261609 Elliott Aviation Technical Products Development. Inc. C7, 6601 74m Ave Building A Milan, IL 61264 ELLIOTT AVIATION Instructions for Continued Airworthiness For Garmin ADS-B System Installation Report No.: ICA-4079-560 Revision: IR Dated 05/01/2018 3 of 19 TABLE OF CONTENTS COVER PAGE 1 REVISIONS PAGE 2 TABLE OF CONTENTS 3 Chapter 1 Introduction 4 Chapter 2 Maintenance Instructions and Shedules 6 Chapter 3 Access 13 Chapter 4 Lifting and Shoring 14 Chapter 5 Loving and Weighing 14 Chapter 6 Towing and Taxing 14 Chapter 7 Parking and Mooing 14 Chapter 8 Placards and Markings 14 Chapter 9 Servicing 14 Chapter 10 Air worthiness Limitations 15 Appendix A Al SDNY_GM_02758028 SUBJECT TO PROTECTIVE ORDER PARAGRAPHS 7, 8, 9, 10, 15, and 17 EFTA_00244950 EFTA01261610 SDNY_GM_02758029 SUBJECT TO PROTECTIVE ORDER PARAGRAPHS 7, 8, 9, 10, 15, and 17 EFTA 00244951 EFTA01261611 t:t 7 Elliott Aviation Technical Products Development. Inc. C=J 6601 74" Ave Building A Milan. IL 61264 ELLIOTT AVIATION Instructions for Continued Airworthiness For Garmin ADS-B System Installation Report No.: ICA-4079- 60 Revision IR i Dated 05/01/2 18 4019 Chapter 1 INTRODUCTION 1.1 Scope/Purpose/Applicability/Distribution The Instructions for Continued Airworthiness (ICA) described herein are applicable only to RK-260 modified with Gamin ADS-8 System. These ICA describe the recommended and required maintenance procedures for the installation of Gamin ADS-8 System. The maintenance information provided by this document must be included in the operator's Aircraft Maintenance Manual and the operator's Aircraft Scheduled Maintenance Program. All documents listed in the required documents section must be maintained with this document. FM accepted revisions to this document will be distributed by mail to the applicable certifying authorities and operators of legally modified aircraft. 1.2 System Description The features of this modification include the removal of both Collins TDR-94D transponders and replacement win Garmin GTX 3000 transponders, reusing the existing aircraft wiring. This modification also includes a Garmin G 88 GPS / UAT and optional Flight Stream 110 Bluetooth FIS-B installation. A GPS and UAT-SBS antenna is installed. Annunciation is added for ADS-B status. New circuit breakers are installed in the copilot's circuit break r panel. New wiring is added to supply the GTX 3000 transponders with GPS position for the GUI. 88. The Flight Stream 110 (if installed) supports properly equipped FIS-8 capable Bluetooth devices 1.3 Required Data All requited data is located in Appendix A of this document. 1.4 Referenced Gamin documents: 1.5 Nomenclature Drawing Number Rev Date GTX 3000 Transponder Installation Manual 190-00926-01 L Oct 2015 GDL 84/88 TSO Installation Manual 190-01122-00 H Dec 2014 Flight Stream 110/210 TSO Installation Manual 190-01700-00 E Dec 2015 Systems Control: 1.5.1 The GTX 3000 transponders replace the Collins TDR-94D transponders. AN control is via the existing Colli s Pro Line 21 cockpit Control Display Units. No changes to operational control are imposed by this STC. 1.5.2 The GDL 88 is a GPS sensor and FIS-B UAT receiver. The Gni. 88 has no external control. 1.5.3 The Flight Stream 110 is a Bluetooth repeater for the GDL 88 FIS-B products and has no external control. 1.8 Document administration: 1.6.1 This document will be revised by Elliott Aviation Engineering when revisions to descriptive or approval da warrant. 1.6.2 When this document is revised, all pages will be revised to indicate the current level. Chapter 10 will have own revision status embedded. FM approved revisions to the document wiN be distributed by mail to the applicable certifying authorities and operations of legally modified aircraft. is SDNY_GM_02758030 SUBJECT TO PROTECTIVE ORDER PARAGRAPHS 7, 8, 9, 10, 15, and 17 EFTA_00244952 EFTA01261612 SDNY_GM_02758031 SUBJECT TO PROTECTIVE ORDER PARAGRAPHS 7, 8, 9, 10, 15, and 17 EFTA_00244953 EFTA01261613 Elliott Aviation Technical Products Development, Inc. G:7 6601 74m Ave Building A Milan, IL 61264 ELLIOTT AVIATION Instructions for Continued Airworthiness For Garmin ADS-B System Installation Report No: ICA-4079- 60 Revision IR 1 Dated 05/01/2 18 5o 19 1.7 Abbreviations and Definitions: 1090ES A transponder distinction. 1090 is the classic frequency of Secondary Surveillance Radar (SSR) transponders. The addition of 'E5 at the end signifies that the transponder is equipped with Extended Squitter used by the ADS-B aircraft segment. Note that this class of transponder supports Class 'A" airspace (altitudes above 18,000 feet) operations. Typically, no FIS•B or TIS-8 functionality is included, compared to UAT. AMM Aircraft Maintenance Manual DAH Design Approval Holder. The FAA term that includes STC holders such as Elliott Aviation. FIS-B Flight Information System broadcast. A radio frequency service that transmits weather and aeronautical products, either by satellite or ground based systems. Refer to FM Advisory Circular 20-149A for thorough explanation. Latency The total time between when the position is measured and when the position is transmitted by the aircraft. A 14 CFR §91.227 performance requirement for ADS-8 broadcast systems. The collection of specific equipment, interface and testing represented by this STC comprises an approved Latency OEM Original Equipment Manufacturer. SBS Surveillance and Broadcast Service. Provided by the FAA. Ground based transmission at a frequency of 978 MHz. SDA System Design Assurance. A 14 CFR §91.227 performance requirement for ADS-8 broadcast systems. The collection of specific equipment, interface and testing represented by this STC comprises an approved SDA. UAT Universal Access Transceiver. A new device that supports the ADS-8 aircraft segment at lower altitudes (below 18,000 feet) Allows smaller aircraft that operate below Class 'A' airspace a more 1.8 Precautions Typical precautions are to be taken when accessing. removing, replacmg, testing or inspecting these modificatio's. Specific precautions will be addressed in context throughout this document. 1.9 Units of measurement: Non- metric. English units including Inches, feet, etc SONY_GM_02758032 SUBJECT TO PROTECTIVE ORDER PARAGRAPHS 7, 8, 9, 10, 15, and 17 EFTA_00244954 EFTA01261614 SDNYGM02758033 SUBJECT TO PROTECTIVE ORDER PARAGRAPHS 7, 8, 9, 10, 15, and 17 EFTA_00244955 EFTA01261615 Elliott Aviation Technical Products Development, Inc 6601 74"' Ave Building A Milan. IL 61264 ELLIOTT AVIATION Instructions for Continued Airworthiness For Garmin ADS-B System Installation Chapter 2 MAINTENANCE INSTRUCTIONS AND SCHEDULES: 2.1 Mandatory Replacements: The GTX 3000 1090ES Transponder, GDL 88 GPS / UAT and optional Flight Stream 110 systems' electrical components and installation is "On Condition" as determined by routine surveillance and there is no mandatory replacement time for any aspect of this system. Refer to 400A OEM AMM, Wiring Procedures and Repair — Description and Operations - chapter 20. for comprehensive wiring harness surveillance concerns. See Chapter 10 Airworthiness Limitations for antenna installation inspections. 2.2 Recurring Maintenance: 2.2.1 Antenna Installations Antenna installations require special inspection requirements and shall be maintained using Chapter 10 o this document. Report No.: ICA-4079.580 Revision; IR Dated 05/01,2018 6 119 2.2.2 Bulkhead Feedthrough Installation The bulkhead feedthrough installation requires no special inspections requirements and shall be maintained using normal OEM maintenance manual procedures 2.2.3 Basic Mode S Transponder functions: The instalation of the GTX 3000 transponders must continue to meet the operational requirements of 14 CFR §§ 91.413, 91.215, and 91.217 and comply with the transponder system tests and inspections called out in 14 CFR § 43. appendix F. The Collins Pro Line 21 altitude reporting equipment connected to the Gamin ADS-B transponders must comply with all applicable 14 CFR §§ 91.217. 91.411, and part 43 appendix E test and inspection requirements. If the altimetry system is compliant with the Reduced Vertical Separation Minimum (RVSM standards, the requirements and tolerances stated in the approved RVSM maintenance program must be met. ADS-B installation does not alter these requirements. 2.2.4 ADS-8 functions: Compliance with aircraft equipage requirements imposed by the operational requirements of 14 CFR §§ 91.225 and 91.227 is achieved by these STC modifications. ADS-B Maintenance is "On Condition" as determined by routine surveillance during Mode S maintenance, by the flight crew as well the FAA Air Tr c Control system. 2.2.5 FIS43 functions: This modification has an optional installation that supports ground based SBS FIS-B reception. UAT/FIS-B Maintenance is "On Condition'. 2.3 Setup and Configuration in Service 2.3.1 Garmin GDL 88 2.3.1.1 Confrm Garmin GDL 88 line replaceable unit part number from the Elliott Aviation wiring diagra 121-3781-E0580-000 located in Appendix A. 2.3.1.2 Obtain Elliott Configuration Instructions located in Appendix A. Read Section 5 of Configuration Instructions before proceeding with reconfiguration of the GDL 88. Take special note of the specific instructions for laptop computer interface, software effectivity and maintenance record details. The GDL-88 will not function property until software setup and configuration is accomplished. SDNY_Givi_02758034 SUBJECT TO PROTECTIVE ORDER PARAGRAPHS 7, 8, 9, 10, 15, and 17 EFTA_00244956 EFTA01261616 SDNY_GM_02758035 SUBJECT TO PROTECTIVE ORDER PARAGRAPHS 7, 8, 9, 10, 15, and 17 EFTA 00244957 EFTA01261617 Cc--t2 Elliott Aviation Technical Products Development, Inc. 6601 74" Ave Building A Milan, IL 61264 ELLIOTT AVIATION Instructions for Continued Airworthiness For Garmin ADS-B System Installation Report No.: ICA-4079-660 Revision: IR Dated 0510112 718 7 or 19 PRECAUTION: -1 I Part number, configuration and electrical interface has been evaluated I and approved for ADS-B Latency and SDA requirements. Any deviations I will require additional approval. _I 2.3.1.3 While using the Elliott Configuration Instructions Section 5. access to the CDL 88 Diagnostics section is available. Real time GPS information is presented. 2.3.1.4 For setup and configuration, GPS reception must be confirmed using the diagnostic page. Use known GPS position to validate the GDL 88 diagnostic position readout such as the aircrafts navigation GPS. This information is presented on the Pro Line 21 cockpit control display unit un r the IDX pages. Sample page below show typical GDL 88 GPS data. 2.3.1.5 After GPS reception is verified aircraft maybe returned to service. 2.3.1.6 For troubleshooting an in-service system, GPS activity may be confirmed using this diagnostic I. page. Lack of GPS position may be due to disconnect antenna coax. faulty antenna or faulty GD 88. Neither the GDL 88 nor GPS antenna is field serviceable. If faulty, the CDL 88 line replaCeable unit may only be repaired by Garmin. Replace a faulty GPS antenna with new. Sample page: • 001.114411wall hal: 11.30 p. 0 . n _ as speoks CoonsfinaleS La Sams Una InIsmutios in *SWUM flea (3) OnonsfeS • ISOM a E: Pbt WO awat iCausi isinOOSAKU0. Os Vats au isle 3. MI 42I M 06.422 IPS mpoplinfann I masa. DWI Wean WC Ons I 110.1).121 moan MTh= I nail /Sat US, I .trasiCri4 MIMI AS lapin i WV.= al ARMCO. it4233/0/01 atiC vati EMIC aunt St:sitar° I it SOW^ Una* OPInICIMTIOPeCk I a l Upload Software moat We RN I la Teel gays . Miltilutkolt I Ma MO.40416free I Sara Cantor/Nab- 1.44.10Sfrallea— Ana CoollarOme, SDNY_GM_02758036 SUBJECT TO PROTECTIVE ORDER PARAGRAPHS 7, 8, 9, 10, 15, and 17 EFTA_00244958 EFTA01261618 SDNY_GM_02758037 SUBJECT TO PROTECTIVE ORDER PARAGRAPHS 7, 8, 9, 10, 15, and 17 EFTA_00244959 EFTA01261619 Elliott Aviation Technical Products Development, Inc. 6601 74m Ave Building A Milan. IL 61264 ELLIOTT AVIATION Instructions for Continued Airworthiness For Garmin ADS-B S stem Installation Report No.: ICA-4079-560 Revision IR Dated 05/01 18 8" 19 2.3.2 GTX 3000 Transponder 2.3.2.1 Confirm Garrnin GTX 3000 line replaceable unit part number from the Elliott Aviation wiring diagram 121.4079-E0560-000 located in Appendix A. 2.3.2.2 Obtain Elliott Configuration Instructions located in Appendix A. Read sections 2 and 4 of this document before proceeding with reconfiguring of the GTX 3000. Take special note of the requirements for laptop computer interface and software effectivity details. The CDC 3000 will not function properly until software setup and configuration is accomplished. - PRECAUTION: i Part number, configuration and electrical interface has been evaluated I I and approved for ADS-B Latency and SDA requirements. Any deviations i will require additional approval. 2.3.2.3 While using the Elliott Configuration Instructions, access to the GTX 3000 status is available. Real time information is presented. 2.3.2.4 For setup and configuration, the following items must be verified: • GPS Position • Magnetic • Weight on wheels is operating correctly. • ADS-B mode indicated. • 4096 code agrees with Pro Line 21 RTU ATC settings. • Flight ID agrees with Pro Line 21 RTU Alt settings.(note: Dynamic (pilot set) Flight ID t available on aircraft all.) • TCAS status correct for aircraft. Most aircraft will have TCAS installed. 2.3.2.5 GPS position is confirmed using the 'Info / ADS-B Out' page. Confirm GPS position from the GDL 88. Sample page follows to show typical GTX 3000 GPS source information. 2.3.2.6 Heading is confirmed using 'Info I EHS' page. Confirm heading from the Pro Line 21 system. Sample page follows to show typical GTX 3000 Heading source information. 2.3.2.7 WOW. ADS-B mode. 4096 Code, FligM ID, and TCAS status is confirmed using the 'Status' pave in the GTX 3000 configuration tool. Sample page follows to show typical GTX 3000 'Status* page information. 2.3.2.8 After these have been verified perform 14 CFR 43 App F I A-..I. 11 2.3.2.9 The aircraft may now be returned to service. SDNY GIvl02758038 SUBJECT TO PROTECTIVE ORDER PARAGRAPHS 7, 8, 9, 10, 15, and 17 EFTA_00244960 EFTA01261620 SDNY_GM_02758039 SUBJECT TO PROTECTIVE ORDER PARAGRAPHS 7, 8, 9, 10, 15, and 17 EFTA_00244961 EFTA01261621 Elliott Aviation Technical Products Development, Inc. 6601 74" Ave Building A Milan, IL 61264 ELLIOTT AVIATION Instructions for Continued Airworthiness for Garmin ADS-B System Installation GTX 3000 Configuration GPS Sample page: In Amon ••••• •Stmolo. 04 . 1.4-1.••• . ._+S•11041 Crammelmusamsamirm tammotsmaaantammeammilmai.- 01160.•••••••Ir. 1.001••••••••• • 411••••••••••••••C IPP•sHeimoneo roe. in...1...w Wl Pec•••••••••••••C Inwm.•••••• •• Somn•••••••••••C almmentwe - 1 soistis•-•rob..... . r... 'MO Do.. Is *nes run° r . a I /nee , P•11014a.celel .. enn" ,.:Z.N.I..* . ••ranyiza 4 ....za j i : ... is .. roma..." I I II.W.HPA I l : ssaas ".4". iity-ipn. la nitt ..,.re1~0.101••••• r ilevaaaelle-lelliall • Oa cam r anassai •14... 6 ... - - -. "--. 0•••=er i rtn.nni. Crorn•...... 'lett.. • ,LC___Po , I resins •.1. avow, r .0....3...0. oirm••••••VU ' /a ma. • iirealliessoNst. r. GTX 3000 Configuration Heading Sample page: I. NM Ii ..i.':.:... D...., Si. ....0. kw: __ _ W.L.-.:•,...;••=••••••••••••rup -1 1 / I • •••••asftern opa.bmr., r .allierib.PC = 1 WaradmiliWin •••taell••••••• '1 i I tImbr "— . J 1..4e lionsia•slamplMC- 71 . ..wry • eon Traramma aro.. isiona cos rof....... nuar.:4.••• lc wawa. r if.. r It Kan.. rith.:ribrii . I I r ""4" na. 1.1 • ern r Sara. r OsirMaISIS/ I "a" FIVa•Plem •Il'anitil•MOO•f• ma 011•14ll CIESIolli trIMMOSIT'rr e" rens ttttttttttttw Report No.: ICA-4079.560 Revision: IR Dated 05/01/2018 9 of 9 SDNY_GM_02758040 SUBJECT TO PROTECTIVE ORDER PARAGRAPHS 7, 8, 9, 10, 15, and 17 EFTA_00244962 EFTA01261622 SDNY_GM02758041 SUBJECT TO PROTECTIVE ORDER PARAGRAPHS 7, 8, 9, 10, 15, and 17 EFTA_00244963 EFTA01261623 Elliott Aviation Technical Products Development, Inc. 6601 74th Ave Building A Milan. IL 61264 ELIJOTT AVIATION Instructions for Continued Airworthiness For Garmin ADS-B System Installation Report No ICA-4079-560 Revision: IR Dated 05/0112018 10 of 19 GTX 3000 Configuration Status Sample Page Seen& 0.••••Setse. 000 eta tio40.“1 'red orreman •ersetiox 6.17412.-1 net oars; Poem: I r nt.tau roam ; GEM =III r sway runt= r D.:cram P Nana rucef r Ilia. a., r..aCu - ram r 'Cato r For.U.T..-;MgJe vans, swam I r UrRInfixaMM r J s • r vuortemitbai r ttaltentif-312=1Iial — 00.2.T CO lag •PosalidelP)—• Psepporitamis ftatecaripti-la P sena atiblIP•atlap sad.— r r r [repeated 3 times] IP 2.3.2.10 For troubleshooting an in-service system, GPS activity may be confirmed using this 'Info! ADS Out' page. Lack of GPS position may be due to G0L 88 issues such as disconnect antenna faulty antenna or faulty G0L 88. See 2.5 above. If the GIDL 88 is not suspect, suspect RS 232 interface, configuration or GTX 3000 transponder. The GTX 3000 is not field serviceable. If taut the GTX 3000 line replaceable unit may only be repaired by Garmin. 2.3.2.11 For troubleshooting an in-service system, heading activity may be confirmed using this "Info I E S' page. Lack of heading may be due to suspect 429 interface or configuration. The GTX 3000 heading source is the same as is used for the Flight Crew presentations The GTX 3000 is not fie d serviceable. If faulty, the GTX 3000 line replaceable unit may only be repaired by Garmin. 2.3.2.12 For troubleshooting an in-service system, the above may be confirmed using this 'Status' page: • Weight on wheels is operating correctly. (squat switch. wiring and config). • ADS-B mode indicated. (GDL 88, valid 429 data, wiring and config). • 4096 code agrees with Pro Line 21 CDU ATC settings. Access the Pro Line control display unit and exercise the squawk codes, the GTX 3000 should indicate correctly almost immediately. (wiring and config). • Flight ID agrees with Pro Line 21 CDU ATC settings. Select reversionary mode on the associated instrument panel to enable off-side control display unit GTX 3000 control. (CD . wiring and config). • TCAS status correct for aircraft Most aircraft will have TCAS installed. Confirm TCAS by visual observation of directional antennas and / or Pro Line control display unit TCAS pag . Confirm no faults if TCAS installed and the ADS-B system is interfaced properly. (wiring a config). 2.3.2.13 The GTX 3000 is not field serviceable. If faulty. the GTX 3000 line replaceable unit may only be repaired by Garmin. SDNY_GM_02758042 SUBJECT TO PROTECTIVE ORDER PARAGRAPHS 7, 8, 9, 10, 15, and 17 EFTA_00244964 EFTA01261624 SONYGM02758043 SUBJECT TO PROTECTIVE ORDER PARAGRAPHS 7, 8, 9, 10, 15, and 17 EFTA_00244965 EFTA01261625 • Elliott Aviation Technical Products Development, Inc. 6601 74th Ave Building A Milan, II. 61264 ELUOTT AVIATION Instructions for Continued Ainvorthiness For Garmin ADS-8 S ern Installation Report No.: ICA-4079- 0 Revision IR Dated 05/01 18 11 19 2.3.3 GTX 3000 "N" number Registration change. 2.3.3.1 Obtain Elliott Configuration Instructions located in Appendix A. Using sections 2 and 4 of the Configuration Instructions Access the 'Aircraft" tab on the GTX 3000 configuration tool. Modify e registration as needed and press enter to set the configuration. Shutdown the configuration tool and verify registration number change using WR 6000 or similar transponder test set. Sample page: GTX300 a 6k Berl irdo Aircraft I Airframe Walla 'Rtg!orta; yogurt log r &cart Configuration i Aircraft Registration 'r•; lAtA Airfai e Designate L VFR Code 3209. 2..: ,7 f 1-7C AVGQty KAOAddrea (hoc) I [Set ICA: Address from Reid:ration Courtly United States SDNY_GM_02759044 SUBJECT TO PROTECTIVE ORDER PARAGRAPHS 7, 8, 9, 10, 15, and 17 EFTA_00244966 EFTA01261626 SDNY_GM_02758045 SUBJECT TO PROTECTIVE ORDER PARAGRAPHS 7, 8, 9, 10, 15, and 17 EFTA 00244967 EFTA01261627 • Elliott Aviation Technical Products Development, Inc. 6601 74th Ave Budding A Milan, IL 61264 ELLIOTT AVIATION Instructions for Continued Airworthiness For Garmin ADS-B S ern Installation Report No.: ICA-4079-560 Revision IR Dated 05/0112018 12 •19 2.4 GTX 30001 GDL 881 Pro Line 21 Troubleshooting Reported Issue Steps Transponder reporting: Altitude Observe or determine Collins flight displays for air data indications. If present and correct. GTX 3000 suspect wiring or configuration. Transponder reporting: Heading Observe or determine Collins flight displays for heading indications. If present and correct. GTX 3000 suspect wiring or configuration. Transponder reporting: ADS-B - Air Observe or determine the ADS-B annunciator status. If ADS-8 annunciation OFF. suspect GTX 3000 in use. If ADS-B annunciation ON, suspect GDL 88 LRU. wiring or configuration. Transponder reporting: ADS-B - Surface Not seen by flight crew. report will come from ATC Ground. Same as above for ADS-B annunciation status. Transponder reporting: Mode C Observe or determine the Collins CDU annunciations. If alternate GTX 3000 can be controlled using Collins CDU. suspect the GTX 3000 LRU. TCAS Collins CDU: Navigate to ATC page and observe status. Access the Collins MFD status page. TCAS faults with ATC faults point to transponder malfunction. TCAS faults alone point to TCAS. r G Commercial Off The Shelf ADS-B receiver devices are suitable for GO NO GO confirmation that the TX 3000 transponders are transmitting GPS position. HOWEVER, on y approved calibrated test devices, such as the IFR 6000, may be used to confirm transponder output power and minimum trigger levels as well as diversity isolation. To conduct an in-depth as-Installed complete functional check including UAT, qualified test equipment such as IFR 6000 will be required. Refer to specific test set instructions for operation and testing. SDNY_GM_02758046 SUBJECT TO PROTECTIVE ORDER PARAGRAPHS 7, 8, 9, 10, 15, and 17 EFTA_00244968 EFTA01261628 SDNY_GM_02758047 SUBJECT TO PROTECTIVE ORDER PARAGRAPHS 7, 8, 9, 10, 15, and 17 EFTA_00244969 EFTA01261629 Elliott Aviation Technical Products Development, Inc. CZ-3 6601 74''' Ave Building A Milan, IL 61264 ELLIOTT AVIATION Instructions for Continued Airworthiness For Garrnin ADS-B System Installation Report No • ICA-4079-560 Revision IR Dated 05/01/2018 13 of 19 Chapter 3 ACCESS: 3.1 Overview: The information contained herein supplements the basic Maintenance Manuals only in those areas listed, when aircraft is modified in accordance with Elliott Aviation drawings and diagrams specified in Section 1.3 of this document. 3.1.1 GTX 3000s are located in the forward right avionics bay upper equipment shelf. A configuration module i also located inside the J3302 connectors. 3.1.2 GDL 88 is located in the forward left avionics bay lower equipment shelf. A configuration module is also located inside the J811 connector. 3.1.3 Fight Stream 110 (if installed) is located on the back of the Pilots chart holder cabinet. 3.1.4 ADS-B 1/2 annunciator is located in the cockpit panel 3.1.5 GA36 GPS Antenna is located on top of the aircraft fuselage above the cockpit headliner at FS 128.74 rig of center line 3.1.6 UAT Antenna is located on the belly of the aircraft fuselage below the left forward avionics bay at FS 35.1 3.1.7 Wiring follows existing aircraft wire routes in the nose and cockpit area. 3.2 Equipment and wiring access: No new access is required from the installation of this modification. Access to all equipment and wiring is gained using existing aircraft maintenance manual techniques. 3.2.1 GDL 88 and GTX 3000 rack mounted Line Replaceable Units (LRU): 3.2.1.1 No hand tools are required. The coax and wire harness connectors knurled and are intended to be removed and tightened by hand. Should assistance in the form of pliers be used, take care to n distort or over tighten. 3.2.1.2 Observe typical avionics systems precautions including: • Coax connectors. Do not bend or kink the coax, avoid bending the center pin, inspect for debris prior to reinstallation. • Wire harness connectors. Disengage associated circuit breakers first. Use care when handl ng connectors to ensure shield drain integrity, alternate locking screw tightening sequence and ensure proper alignment during re-installation. 3.2.1.3 Each LRU rack uses a lock down mechanism to secure the LRU in the rack. • To remove, pull while twisting counter clockwise until the LRU hook is clear. The LRU show now be free. • To install, align the LRU in the rack. Slide the LRU until the foot is firmly engaged in the rack LM the lockdovm mechanism over the LRU hook. Tighten firmly until secure. • Conduct necessary checkout procedures described elsewhere in this document. 3.2.1.4 Configuration Modules are located inside the J881 GDL 88 connector and inside each J3302 G X 3000 connector. Hand tools are required to gain access inside the backshell. Retain hardware after removal. To install secure retained hardware and Reconnect to applicable unit. Conduct necessary checkout procedure described elsewhere in this document. d SDNY_GM_02758048 SUBJECT TO PROTECTIVE ORDER PARAGRAPHS 7, 8, 9, 10, 15, and 17 EFTA_00244970 EFTA01261630 SDNY_GM_02758049 SUBJECT TO PROTECTIVE ORDER PARAGRAPHS 7, 8, 9, 10, 15, and 17 EFTA 00244971 EFTA01261631 Elliott Aviation Technical Products Development, Inc 6601 74" Ave Building A Milan, IL 61264 ELLIOTT AVIATION Instructions for Continued Airworthiness For Garman ADS-8 System Installation Report No.: ICA-4079-680 Revision: IR Dated 05/0112C 8 14 of 19 3.2.3 Flight Stream 110 (if installed) Line Replaceable Unit (LRU), GPS and UAT antennas: Hand tools are required. These components are secured with screws and nuts. To remove, remove this hardware and retain. Disconnect the electrical / coax connector. To install, secure with the retained hardware. Reconnect electrical /coax connector. 3.2.4 ADS-8 1/2 Annunciator: Hand tools are required. This component is secured with locking paws. To gain access to these locking paws gently pull the annunciator lens out. Screws located inside loosen the upper and lower screw. Once locking paw has been loosened pull annunciator body out of the annunciator housing and instrument pane To install insert annunciator body back through the instrument panel and annunciator housing. Tighten locking paws until annunciator body and housing are tight against the instrument panel, then press annunciator lens firmly into the annunciator body. Conduct necessary checkout procedures described elsewhere in this document. Chapter 4 LIFTING AND SHORING: Not applicable this modification. Chapter 5 LEVELING AND WEIGHING: Not applicable this modification Chapter 6 TOWING AND TAXIING: Not applicable this modification. Chapter 7 PARKING AND MOORING: Not applicable this modification Chapter 8 PLACARDS AND MARKINGS: Not applicable this modification. Chapter 9 SERVICING: Not applicable this modification SDNY_GliA_02758050 SUBJECT TO PROTECTIVE ORDER PARAGRAPHS 7, 8, 9, 10, 15, and 17 EFTA_00244972 EFTA01261632 SDNY_GM_02758051 SUBJECT TO PROTECTIVE ORDER PARAGRAPHS 7, 8, 9, 10, 15, and 17 EFTA_00244973 EFTA01261633 Elliott Aviation Technical Products Development, Inc. CZ, ifQC7 6601 7451Ave Building A Milan, IL 61264 ELLIOTT AVIATION Instructions for Continued Airworthiness For Garmin ADS-B S tern Installation Report No.: ICA-4079-560 Revision: IR Dated 05/0112018 15 of 19 Chapter 10 AIRWORTHINESS LIMITATIONS 10.1 FAA Approval of Airworthiness Limitations This chapter of this supplement must be attached to the Airplane Maintenance Manuals. The information contained herein supplements the basic Maintenance Manuals only in those areas listed, when the aircraft is modified in accordance with FM Form 337 for the installation of Garmin ADS-B System. For limitations and procedures not contained in this supplement, consult the basic Airplane Maintenance Manuals. The Airworthiness Limitations Section is FAA approved and specifies maintenance required and un 14CFR §§ 43.16 and 91.403, unless an alternative program has been FAA approved. FAA APPROVED: Principal Avionics Inspector Minneapolis — St. Paul FSDO FM Approved Date: SDNY_GM_02758052 SUBJECT TO PROTECTIVE ORDER PARAGRAPHS 7, 8, 9, 10, 15, and 17 EFTA_002 44974 EFTA01261634 SDNY_GM_02758053 SUBJECT TO PROTECTIVE ORDER PARAGRAPHS 7, 8, 9, 10, 15, and 17 EFTA_00244975 EFTA01261635 • Elliott Aviation Technical Products Development. Inc. 6601 74. Ave Budding A Milan. IL 61264 ELLIOTT AVIATION Instructions for Continued Airworthiness For Garmin ADS-8 System Installation Chapter 10 Revisions Status Report No.: ICA-4079-560 Revision: IR Dated 05/01/2016 16 of 19 Rev Description Page (S) Date FAA Approved By IR INITIAL RELEASE ALL FAA Approved Date: SDNY_GM_02758054 SUBJECT TO PROTECTIVE ORDER PARAGRAPHS 7, 8, 9, 10, 15, and 17 EFTA_00244976 EFTA01261636 SDNY_GM_02758055 SUBJECT TO PROTECTIVE ORDER PARAGRAPHS 7, 8, 9, 10, 15, and 17 EFTA_00244977 EFTA01261637 Elliott Aviation Technical Products Development, Inc. 6601 74m Ave Budding A Milan. IL 61264 ELLIOTT AVIATION Instructions for Continued Airworthiness For tannin ADS-B System Installation Report No.: ICA-4079-560 Revision: IR Dated 0510112018 17 of 19 10.1 GPS & UAT Antenna The area of the GPS and UAT Antenna installations must be inspected visually for damage, wear, and corrosion in accordance with Hawker/Beechcraft general inspection criteria in addition use eddy current inspection techniques in accordance with MIL-STC-271 using templates defined in section 10.3. Structural Element (Skin) Threshold (Flights) Recumng (Flights GPS Antenna. Connector Hole 9,058 9,058 GPS Antenna, Fastener Hole 4,146 4,146 UAT Antenna, Connector Hole 21,139 21,139 UAT Antenna Fastener Hole 7,572 7,572 10.2 Inspection Method The connector and fastener holes should be inspected using eddy current inspection techniques, according to the intervals outlined in tables below. POD curves from the NTIAC 'Nondestructive Evaluation Capabdities ate Book' for lap splice joint specimens that a 0.10' crack has a 90% probability of detection using eddy currfnt techniques. The threshold crack length for each location indicates that a crack, if present should be detectable at the time of the threshold inspection. Cracks longer than 0.10' must be repaired prior to the next flight. the inspection should indicate the following details; Modification Affected Aircraft System Structural Detail Inspection Notes GPS Antenna UAT Antenna Aircraft Skin Connector Hole Inspect edge of hole in skin. Doubler Fastener Holes Inspect fastener holes in skin. Cracks are most likely around fastener holes closest to the edges of the doubler. 10.3 Required Circle Templates Modification Rivets 0.201" 0.75 GPS Antenna UAT Antenna X [repeated 3 times] FAA Approved Date: SDNY_GM_02758056 SUBJECT TO PROTECTIVE ORDER PARAGRAPHS 7, 8, 9, 10, 15, and 17 EFTA_00244978 EFTA01261638 SDNY_GM_02758057 SUBJECT TO PROTECTIVE ORDER PARAGRAPHS 7, 8, 9, 10, 15, and 17 EFTA_00244979 EFTA01261639 Elliott Aviation Technical Products Development, Inc. 6601 74"' Ave Building A Milan, IL 61264 ELLIOTT AVIATION Instructions for Continued Airworthiness For Gamin ADS-B System Installation Report No.: ICA-4079.560 Revision: IIR Dated 0901/20 8 18 of 9 10A Eddy Current Templates EDDY CURRENT CIRCLE TEMPLATE (SELECTED R(VETS) 0 0.194' 0 0.225' 0 0.256' O 0.288' DlA DIA [repeated 3 times] O °-294. 0 Dw 0 (Mr DIA AD3 AIM 0.325' ow 0.425' ow ADS 0358" 0 0.388' DIA DlA 0.456' DIA 0 0.488• ADS EDDY CURRENT CIRCLE TEMPLATE (0201" DIAMETER HOLE) 0 0.301'DIA 0.401°014 0.501' DIA SDNY_GM_02758058 SUBJECT TO PROTECTIVE ORDER PARAGRAPHS 7, 8, 9, 10, 15, and 17 EFTA_002 44980 EFTA01261640 SDNY_GM_0275£0359 SUBJECT TO PROTECTIVE ORDER PARAGRAPHS 7, 8, 9, 10, 15, and 17 EFTA 00244981 EFTA01261641 Elliott Aviation Technical Products Development Inc. 6601 70 Ave Building A Milan, IL 61264 ELLIOTT AVIATION Instructions for Continued Airworthiness For Garmin ADS-8 System Installation Report No. ICA-4079-560 Revision: IR Dated 05/01/20; 8 19 of 9 EDDY CURRENT CIRCLE TEMPLATE (0.750" DIAMETER HOLE) r -- 0.1350'014 0.950' OR 1.050• DIA FAA Approved Date: SDNCGM_02758060 SUBJECT TO PROTECTIVE ORDER PARAGRAPHS 7, 8, 9, 10, 15, and 17 EFTA_00244982 EFTA01261642 SDNY_GM_02758061 SUBJECT TO PROTECTIVE ORDER PARAGRAPHS 7, 8, 9, 10, 15, and 17 EFTA 00244983 EFTA01261643 Elliott Aviation Technical Products Development. Inc. S 6601 74m Ave Building A Milan. IL 61264 ELLIOTT AVIATION Instructions for Continued Airworthiness For Gamin ADS-B System Installation APPENDIX A ATTACHMENTS Report No.: ICA•3761.5p0 Revision. A Dated 02/24/217 All documents listed in the table below must be attached to this document and maintained in accordance with Chapte one. ATTACHMENTS DOCUMENT NO. TITLE REV PAGES CFG-3761.560 Configuration Instructions for Gamin ADS-B Out System Installation IR 14 121-4079-E0560-000 GTX3000 Transponders and GDLB8 ADS-B System IR 6 121-3761-M0560-050 Wire Routing Installation IR 3 SDNY_GM_02758062 SUBJECT TO PROTECTIVE ORDER PARAGRAPHS 7, 8, 9, 10, 15, and 17 EFTA 00244984 EFTA01261644 SDNY_GM_02758063 SUBJECT TO PROTECTIVE ORDER PARAGRAPHS 7, 8, 9, 10, 15, and 17 EFTA 00244985 EFTA01261645 Elliott Aviation Technical Products Development, Inc. 6601 74" Ave Building A Milan, IL 61264 ELLIOTT AVIATION Instructions for Continued Airworthiness For Garmin ADS•B S tern Installation Report No.: ICA-4079- Revision: R Dated 05/01/20 8 1 of 9 Instructions for Continued Airworthiness For Garmin ADS-B Out System Installation (Type Certificate Al 6SW) OD 2018 ELLIOTT AVIATION TECHNICAL PRODUCTS DEVELOPMENT, INC. Elliott Aviabon Technical Products Development. Inc. reserves the copyright of ail information and illustrabons in this publication whit is provided in confidence and which may not be used for any purpose other than for vidikti it was originally supplied. The publication may not be reproduced in part or in whole without the consent in writing of Elliott Aviation Technical Products Development, Inc. SDNY_GM_02758064 SUBJECT TO PROTECTIVE ORDER PARAGRAPHS 7, 8, 9, 10, 15, and 17 EFTA_00244986 EFTA01261646 SDNY_GM_027513065 SUBJECT TO PROTECTIVE ORDER PARAGRAPHS 7, 8, 9, 10, 15, and 17 EFTA_00244987 EFTA01261647 Elliott Aviation Technical Products Development, Inc. 6601 74tl1 Ave Budding A Milan, IL 61264 ELLIOTT AVIATION Instructions for Continued Airworthiness For Garmin ADS-B S em Installation Report No.: ICA-4079- '0 Revision: R Dated 05/01120.8 2 of 9 REVISIONS PAGE Rev Description Page (S) Date Approved By IR Initial Release ALL SDNY_GM_02758066 SUBJECT TO PROTECTIVE ORDER PARAGRAPHS 7, 8, 9, 10, 15, and 17 EFTA_00244988 EFTA01261648 SDNY_GM_0275f0D67 SUBJECT TO PROTECTIVE ORDER PARAGRAPHS 7, 8, 9, 10, 15, and 17 EFTA_00244989 EFTA01261649 Elliott Aviation Technical Products Development. Inc. 6601 74° Ave Building A Milan, IL 61264 ELLIOTT AVIATION Instructions for Continued Airworthiness For Garmin ADS-B System Installation TABLE OF CONTENTS Report No.: ICA-4079.560 Revision: R Dated 05/01/20 8 3 of 9 COVER PAGE 1 REVISIONS PAGE 2 TABLE OF CONTENTS 3 Chapter 1 Introduction 4 Chapter 2 Maintenance Instructions and Shedules 6 Chapter 3 Access 13 Chapter 4 Lifting and Shoring 14 Chapter 5 Laving and Weighing 14 Chapter 6 Towing and Taxing 14 Chapter 7 Parking and Moring 14 Chapter 8 Placards and Markings 14 Chapter 9 Servicing 14 Chapter 10 Airworthiness Limitations 15 Appendix A Al SDNY_GM_02758068 SUBJECT TO PROTECTIVE ORDER PARAGRAPHS 7, 8, 9, 10, 15, and 17 EFTA 00244990 EFTA01261650 SDNY_GM_02758069 SUBJECT TO PROTECTIVE ORDER PARAGRAPHS 7, 8, 9, 10, 15, and 17 EFTA 00241991 EFTA01261651 • Elliott Aviation Technical Products Development. Inc. 6601 74°' Ave Building A Milan. IL 61264 AVIATION Instructions for Continued Airworthiness For Garmin ADS-B System Installation Report No.: ICA-4079-560 Revision: Dated 05/01/20 8 4 of 9 Chapter 1 INTRODUCTION 1.1 Scope/Purpose/Applicability/Distribution The Instructions for Continued Airworthiness (ICA) described herein are applicable only to RK-260 modified with Garmin ADS-B System. These ICA describe the recommended and required maintenance procedures for the installation of Garmin ADS-B System. The maintenance information provided by this document must be included in the operators Aircraft Maintenance Manual and the operator's Aircraft Scheduled Maintenance Program. All documents listed in the required documents section must be maintained with this document. FAA accepted revisions to this document will be distributed by mail to the applicable certifying authorities and operators of *gaily modified aircraft. 1.2 System Description The features of this modification include the removal of both Collins TDR-940 transponders and replacement with Gamin GTX 3000 transponders, reusing the existing aircraft wiring. This modification also includes a Garmin GDL 88 GPS / UAT and optional Flight Stream 110 Bluetooth FIS-B installation. A GPS and UAT-SBS antenna is installed. Annunciation is added for A0S-B status. New circuit breakers are installed in the copilot's circuit break panel. New wiring is added to supply the GTX 3000 transponders with GPS position for the GDL 88. The Flight Stream 110 (if installed) supports property equipped FIS-B capable Bluetooth devices 1.3 Required Data AS requited data is located in Appendix A of this document. 1.4 Referenced GarmIn documents: Nomenclature Drawing Number Rev Date GTX 3000 Transponder Installation Manual 190-00926-01 L Oct 2015 GDL 84/88 TSO Installation Manual 190-01122.00 H Dec 2014 Flight Stream 110/210 TSO Installation Manual 190-01700-00 E Dec 2015 1.5 Systems Control: 1.5.1 The GTX 3000 transponders replace the Collins TOR-94D transponders. All control is via the existing Colli Pro Line 21 cockpit Control Display Units. No changes to operational control are imposed by this STC. 1.5.2 The GDL 88 is a GPS sensor and FIS-B UAT receiver. The GDL 88 has no external control. 1.5.3 The Flight Stream 110 is a Bluetooth repeater for the GDL 88 FIS-B products and has no external control. 1.8 Document administration: 1.6.1 This document wIl be revised by Elliott Aviation Engineering when revisions to descriptive or approval dais warrant. 1.6.2 When this document is revised, all pages will be revised to indicate the current level. Chapter 10 will have own revision status embedded. FAA approved revisions to the document wilt be distributed by mail to the applicable certifying authorities and operations of legally modified aircraft. SDNY_GM_02758070 SUBJECT TO PROTECTIVE ORDER PARAGRAPHS 7, 8, 9, 10, 15, and 17 EFTA 00244992 EFTA01261652 SDNY_GM02758071 SUBJECT TO PROTECTIVE ORDER PARAGRAPHS 7, 8, 9, 10, 15, and 17 EFTA_00244993 EFTA01261653 Elliott Aviation Technical Products Development, Inc. C:C7 6601 74m Ave Building A Milan, IL 61264 ELLIOTT AVIATION Instructions for Continued Airworthiness For Garmin ADS-8 System Installation Report No.: ICA-4079-580 Revision: iFt Dated 05/01/2018 5 of 9 1.7 Abbreviations and Definitions: 1090ES A transponder distinction. 1090 is the classic frequency of Secondary Surveillance Radar (SSR) transponders. The addition of 'ES' at the end signifies that the transponder is equipped with Extended Squitter used by the ADS-B aircraft segment Note that this class of transponder suppo Class 'A' airspace (altitudes above 18.000 feet) operations. Typically, no FIS-B or TIS-8 functionality is included. compared to VAT. AMM Aircraft Maintenance Manual DAH Design Approval Holder. The FAA term that includes STC holders such as Elliott Aviation. FIS-B Flight Information System broadcast. A radio frequency service that transmits weather and aeronautical products, either by satellite or ground based systems. Refer to FM Advisory Circul. 20-149A for thorough explanation. Latency The total time between when the position is measured and when the position is transmitted by the aircraft. A 14 CFR §91.227 performance requirement for ADS -B broadcast systems. The collectio of specific equipment, interface and testing represented by this STC comprises an approved Latency OEM Original Equipment Manufacturer. SIBS Surveillance and Broadcast Service. Provided by the FM. Ground based transmission at a frequency of 978 MHz. SDA System Design Assurance. A 14 CFR §91.227 performance requirement for ADS-8 broadcast systems. The collection of specific equipment interface and testing represented by this STC comprises an approved SDA. UAT Universal Access Transceiver. A new device that supports the ADS-8 aircraft segment at lower altitudes (below 18,000 feet) Mows smaller aircraft that operate below Class 'A" airspace a more 1.8 Precautions Typical precautions are to be taken when accessing, removing, replacing, testing or inspecting these modifications. Specific precautions will be addressed in context throughout this document. 1.9 Units of measurement: Non- metric. English units including Inches. feet. etc.. SDNY_GM_02758072 SUBJECT TO PROTECTIVE ORDER PARAGRAPHS 7, 8, 9, 10, 15, and 17 EFTA_002 44994 EFTA01261654 SDNY_GM_02758073 SUBJECT TO PROTECTIVE ORDER PARAGRAPHS 7, 8, 9, 10, 15, and 17 EFTA_00244995 EFTA01261655 Elliott Aviation Technical Products Development, Inc. 6601 74^ Ave Building A Milan. IL 61264 ELLIOTT AVIATION Instructions for Continued Airworthiness For Gamin ADS-B S em Installation Report No.: ICA-4079-560 Revision: IR Dated 05/01/2018 6of1$ Chapter 2 MAINTENANCE INSTRUCTIONS AND SCHEDULES: 2.1 Mandatory Replacements: The GTX 3000 1090ES Transponder. GDL 88 GPS r UAT and optional Flight Stream 110 systems' electrical components and installation is "On Condition" as determined by routine surveillance and there is no mandatory replacement time for any aspect of this system. Refer to 400A OEM AMM, Wiring Procedures and Repair — Description and Operations - chapter 20, for comprehensive wiring harness surveillance concerns. See Chapter 10 Airworthiness Limitations for antenna installation Inspections. 2.2 Recurring Maintenance: 2.2.1 Antenna Installations Antenna installations require special inspection requirements and shall be maintained using Chapter 10 of this document. 2.2.2 Bulkhead Feedthrough Installation The bulkhead feedthrough installation requires no special inspections requirements and shall be maintain' using normal OEM maintenance manual procedures 2.2.3 Basic Mode S Transponder functions: The installation of the GTX 3000 transponders must continue to meet the operational requirements of 14 CFR §§ 91.413, 91.215, and 91.217 and comply with the transponder system tests and inspections called out in 14 CFR § 43, appendix F. The Collins Pro Line 21 altitude reporting equipment connected to the Garmin ADS-8 transponders must comply with all applicable 14 CFR §§ 91.217, 91.411, and part 43 appendix E test and inspection requirements. If the alhmetry system is compliant with the Reduced Vertical Separation Minimum (RVSM) standards. the requirements and tolerances stated in the approved RVSM maintenance program must be met. ADS-B installation does not after these requirements. 2.2.4 ADS-B functions: Compliance with aircraft equipage requirements imposed by the operational requirements of 14 CFR §§ 91.225 and 91.227 is achieved by these STC modifications. ADS-8 Maintenance is "On Condition" as determined by routine surveillance during Mode S maintenance, by the flight crew as well the FAA Air Tra Control system. 2.2.5 FIS-8 functions: This modification has an optional installation that supports ground based SBS FIS-B reception. UATIFIS-B Maintenance is "On Condition'. 2.3 Setup and Configuration in Service 2.3.1 Gannin GDL 88 2.3.1.1 Confirm Gannin GDL 88 line replaceable unit part number from the Elliott Aviation wiring diagram 121-3761-E0560-000 located in Appendix A. 2.3.1.2 Obtain Elliott Configuration Instructions located in Appendix A. Read Section 5 of Configuration Instructions before proceeding with reconfiguration of the GDL 88. Take special note of the spec' instructions for laptop computer interface. software effectivity and maintenance record details. The GDL-88 will not function properly until software setup and configuration Is accomplished. SDNY_GM_02758074 SUBJECT TO PROTECTIVE ORDER PARAGRAPHS 7, 8, 9, 10, 15, and 17 EFTA_00244996 EFTA01261656 SDNY_GM_02758075 SUBJECT TO PROTECTIVE ORDER PARAGRAPHS 7, 8, 9, 10, 15, and 17 EFTA 00244997 EFTA01261657 c1 Elliott Aviation Technical Products Development, Inc. /r i Report No.: ICA.4079- 7 6601 74" Ave Building A Revision: ir! Milan, IL 81264 ELLIOTT Dated 05/01/2014 AVIATION 7 of 1 Instructions for Continued Airworthiness For Garrnin ADS-B System Installation PRECAUTION: Part number, configuration and electrical interface has been evaluated and approved for ADS-8 Latency and SDA requirements. Any deviations will require additional approval. 2.3.1.3 White using the Elliott Configuration Instructions Section 5, access to the GDL 88 Diagnostics section is available. Real time GPS information is presented. 2.3.1.4 For setup and configuration. GPS reception must be confirmed using the diagnostic page. Use known GPS position to validate the GDL 88 diagnostic position readout such as the aircrafts navigation GPS. This information is presented on the Pro Line 21 cockpit control display unit unde the ICA pages. Sample page below show typical GDL 88 GPS data. 2.3.1.5 After GPS reception is verified aircraft maybe returned to service. 2.3.1.6 For troubleshooting an in-service system. GPS activity may be confirmed using this diagnostic page. Lack of GPS position may be due to disconnect antenna coax, faulty antenna or faulty GDL 88. Neither the GDL 88 nor GPS antenna is field serviceable. If faulty, the GDL 88 line replaceablE unit may only be repaired by Garmin. Replace a faulty GPS antenna with new. Sample page: • 00114/11 betel Tool tvia _es _el n_. Clagassde bleal."6•13 Sin Is una Itheamta eamilon I: :: Ns Vas MI Atlanta) sail) easilOGOS I: 7, Ms bled Micas lesSOISSOna rttrir m bat met 41.1 16-19/16-422 i -t iespiesdarea DIEM was. Wel Menet Ulna: suar.n1 Caallipratles Lac nor 32 ini SOS wet iira sill ISAR MOD wain ran=ge MCDC 00 Lionel 16-72215-412 mccotspg Bbl mcs rat* 411 trisa UPS•to a...ton re•C•4 •si up:n:150am ming tar* "I Tall Opens Meaciens sat Csiewa- I AstienStSYStrote I Loaf Colinas_ Ana Ornernsviasa. SDNv_GM_02758076 SUBJECT TO PROTECTIVE ORDER PARAGRAPHS 7, 8, 9, 10, 15, and 17 EFTA_00244998 EFTA01261658 SDNYGivl_02758077 SUBJECT TO PROTECTIVE ORDER PARAGRAPHS 7, 8, 9, 10, 15, and 17 EFTA_00244999 EFTA01261659 ca Elliott Aviation Technical Products Development, Inc. tr.7 6601 74th Ave Building A Wan, IL 61264 ELLIOTT AVIATION Instructions for Continued Airworthiness For Garmin ADS-B System Installation Report No.: ICA-4079-560 Revision: IR Dated 05/01/201 ti of 1 2.3.2 GTX 3000 Transponder 2.3.2.1 Confirm Garman GTX 3000 line replaceable unit part number from the Elliott Aviation wiring diagram 121.4079-E0560.000 located in Appendix A. 2.3.2.2 Obtain Elliott Configuration Instructions located in Appendix A. Read sections 2 and 4 of this document before proceeding with reconfiguring of the GTX 3000. Take special note of the requirements for laptop computer interface and software effectivity details. The GTX 3000 will not function property until software setup and configuration is accomplished. PRECAUTION: Part number, configuration and electrical interface has been evaluated I and approved for ADS-B Latency and SDA requirements. Any deviations will require additional approval. L_ 2.3.2.3 VVIUle using the Elliott Configuration Instructions, access to the GTX 3000 status is available. Real time information is presented. 2.3.2.4 For setup and configuration, the following items must be verified: • GPS Position • Magnetic • Weight on wheels is operating correctly. • ADS-B mode indicated. • 4096 code agrees with Pro Line 21 RTU ATC settings. • Flight ID agrees with Pm Line 21 RTU ATC settings.(note: Dynamic (pilot set) Flight ID n• available on aircraft all.) • TCAS status correct for aircraft. Most aircraft will have TCAS installed. 2.3.2.5 GPS position is confirmed using the 'Info /ADS-8 Our page. Confirm GPS position from the GD 88. Sample page follows to show typical GTX 3000 GPS source information. 2.3.2.6 Heading is confirmed using 'Info / EMS" page. Confirm heading from the Pro Line 21 system. Sample page follows to show typical GTX 3000 Heading source information. 2.3.2.7 WOW, ADS-8 mode. 4096 Code, Flight ID, and TCAS status is confirmed using the 'Status' page in the GTX 3000 configuration tool. Sample page follows to show typical GTX 3000 'Status' page information. 2.3.2.6 After these have been verified perform 14 CFR 43 App F ¶ A-J. 2.3.2.9 The aircraft may now be returned to servce SDNY_GM_02758078 SUBJECT TO PROTECTIVE ORDER PARAGRAPHS 7, 8, 9, 10, 15, and 17 EFTA 002450(X1 EFTA01261660 SDNY_GM_02758079 SUBJECT TO PROTECTIVE ORDER PARAGRAPHS 7, 8, 9, 10, 15, and 17 EFTA 00245001 EFTA01261661 Cl/ Elliott Aviation Technical Products Development, Inc. 6601 74m Ave Building A C2;11 Milan, IL 61264 ELLIOTT AVIATION Instructions for Continued Airworthiness For Garmin ADS-B S tern Installation Report No.: ICA-4079-5 Revision: R Dated 05/01/20 8 9 of 9 GTX 3000 Configuration GPS Sample page: 16; w,.r ~1' 1" Pei" ririara" — rerrrf— Im0~ • ' 4,11~~~ - CIO ~Yea yimmtimIm • r . III~~• ~BC • 119~~alm4fl". 4,1~•~0 0. 77r I - aals I 42.- . . -. .. . .. . . In ., . • war i•••••••sa /921112 o sal:, rasp .! r sew ran • •I' MI'S rso.„.;_ row. ;•••••...ss rs ass tt"..!!.Ki =2. now r"`""- 4-- ii...-...- i• i D?=C_' ---t. er- :::reas." • r scam oam ;reassess • e.... _____ /tuft.» ár.. ......a. fl atcars,. . I" MCC I g" Jr -. 'It."'" • I II raw: r: '''`' :::zr.--.1-..----• !ragas V so*, ar..r.v. . ,g GTX 3000 Configuration Heading Sample page: Sa• a‘la !la an an* .~.....r.tre~ . i tylr , rnassam . e ; —ass- .sasossasts— beral~177 ~ 11 ••••••••miern bessare "i r Soi~Pa' .i assesasaer. t2C: rue I fl an * irLioata~ roam. ii es. ita=0: Br tom I dues.' ... tram rats • rafts • ~aim restte noses. I/ mom _SI . j••• ..cassa. •--. Par.. :r grease» rec.. inr, ....4 !.......!ir.. ~v..% r ` n r `• inn "' r•. La.as r•ossosa mama 4» ; r ereateaun : a.. ... . ransom r sosama r is tasara ;,, r en I; ;II I.r...—. J ~Wil» • I Prime_ ‘ 1;:szeranno 'IP•issain. e• setwasam ~goon, r sands.. • •• I orse.-- i SDNY_GM_02758080 SUBJECT TO PROTECTIVE ORDER PARAGRAPHS 7, 8, 9, 10, 15, and 17 EFTA_00245002 EFTA01261662 SDNY_GM_02758081 SUBJECT TO PROTECTIVE ORDER PARAGRAPHS 7, 8, 9, 10, 15, and 17 EFTA_00245003 EFTA01261663 Elliott Aviation Technical Products Development. Inc. 6601 74^ Ave Building A Milan. IL 61264 ELLIOTT AVIATION Instructions for Continued Airworthiness For Garrnin ADS-B System Installation GTX 3000 Configuration Status Sample Page: !...whiwwwww.pre iisirembe • _ r 0 Mart • MDO omo 'IP smote !a r C:O4.-k•si Vast I 411.00.0.00 „ oraw, Pr' ;r x.,ru . • I r lifg.,fers) .15" awe_ =Al CHIN itt3PISLIEIY—•1 r r ILIAC] r r.-...cvurcutedg r w...snota r ism krtaaseaVa• r UtCuakitYaLthend P ÊM% IO slizelbaSis ilopoileop ! I- tat . I r r fn.Cabara r f- Farm • r r lit.katal Mina 1 I rv. r tic= rprni ac r For Inc 1k.' .2 Ca I r r tlartra Cada' ecal.4.4 1 r Mattel ille:@aa *irf O ammo eahilPe.b. Is ..vp Report No.: ICA-4079-560 Revision: R Dated 05/01/20 8 10 of 9 2.3.2.10 For troubleshooting an in-service system, GPS activity may be confirmed using this 'Info! ADS-B Out page. Lack of GPS position may be due to GDL 88 issues such as disconnect antenna coax, faulty antenna or faulty GDL 88. See 2.5 above. If the GDL 88 is not suspect, suspect RS 232 I interface, configuration or GTX 3000 transponder. The GTX 3000 is not field serviceable. If faulty the GTX 3000 line replaceable unit may only be repaired by Gamin. 2.3.2.11 For troubleshooting an in-service system, heading activity may be confirrned using this -Info! E " page. Lack of heading may be due to suspect 429 interface or configuration. The GTX 3000 II heading source is the same as is used for the Flight Crew presentations The GTX 3000 is not serviceable. If faulty, the GTX 3000 line replaceable unit may only be repaired by Gamin. 2.3.2.12 For troubleshooting an in-service system, the above may be confirmed using this 'Status' page: • Weight on wheels is operating correctly. (squat switch, wiring and config). • ADS-8 mode indicated. (GDL 88, valid 429 data. wiring and config). • 4096 code agrees with Pro Line 21 CDU ATC settings. Access the Pro Line control displa unit and exercise the squawk codes, the GTX 3000 should indicate correctly almost immediately. (wiring and config). • Flight ID agrees with Pro Line 21 CDU ATC settings. Select reversionary mode on the associated instrument panel to enable off-side control display unit GTX 3000 control. (CDU, wiring and config). • TCAS status correct for aircraft. Most aircraft will have TCAS installed. Confirm TCAS by visual observation of directional antennas and! or Pro line control display unit TCAS page Confirm no faults if TCAS installed and the ADS-B system is interfaced properly. (wiring a config). 2.3.2.13 The GTX 3000 is not field serviceable. If faulty, the GTX 3000 line replaceable unit may only be repaired by Gamin. SDNY_GM_02 758082 SUBJECT TO PROTECTIVE ORDER PARAGRAPHS 7, 8, 9, 10, 15, and 17 EFTA_002450O4 EFTA01261664 SDNY_GM_02758083 SUBJECT TO PROTECTIVE ORDER PARAGRAPHS 7, 8, 9, 10, 15, and 17 EFTA_00245005 EFTA01261665 . Elliott Aviation Technical Products Development. Inc. 6601 74"' Ave Building A Milan, 1L 61264 ELLIOTT Report No.: ICA-4079-50 Revision: IR Dated 05/01/20 8 11 of 9 AVIATION Instructions for Continued Airworthiness For Garmin ADS-B S tern Installation 2.3.3 GTX 3000 'N" number Registration change. 2.3.3.1 Obtain Elliott Configuration Instructions located in Appendix A. Using sections 2 and 4 of the Configuration Instructions Access the "Aircraft' tab on the GTX 3000 configuration tool. Modify e registration as needed and press enter to set the configuration. Shutdown the configuration tool and verify registration number change using IFR 6000 or similar transponder test set. Sample page: GTX3030 Install Info I Aircraft j Aidrame — Aircraft Configuration Failure Log__ Aircraft Registration 1= lATA Airline Designator L VTR Code tint, AFISQty 12 _Zs! I ICAO Address Oleo Set ICAO Address from Registration Country United States _2zi SDNY_GM_02758084 SUBJECT TO PROTECTIVE ORDER PARAGRAPHS 7, 8, 9, 10, 15, and 17 EFTA_00245006 EFTA01261666 SDNY_GM_02758085 SUBJECT TO PROTECTIVE ORDER PARAGRAPHS 7, 8, 9, 10, 15, and 17 EFTA 00245007 EFTA01261667 • Elliott Aviation Technical Products Development. Inc. 6601 74° Ave Building A Milan, IL 61264 EWOTT AVIATION Instructions for Continued Airworthiness For Gamin ADS-B System Installation 2.4 GTX 3000 / GDL 88 / Pro Line 21 Troubleshooting Report No.: ICA-4079-56,0 Revision: I Dated 051011201 12 oft Reported Issue Steps Transponder reporting: Attitude Observe or determine Collins flight displays for air data indications. If present and correct, GTX 3000 suspect wiring or configuration. Transponder reporting: Heading Observe or determine Collins flight displays for heading indications. If present and correct. GTX 3000 suspect wiring or configuration. Transponder reporting: ADS-B • Air Observe or determine the ADS-8 annunciator statue. If ADS-B annunciation OFF, suspect GTX 3000 in use. If ADS-B annunciation ON, suspect GDL 88 LRU, wiring or configuration. Transponder reporting: ADS-8 - Surface Not seen by flight crew, report will come from ATC Ground. Same as above for ADS-B annunciation status. Transponder reporting: Mode C Observe or determine the Collins CDU annunciations. If alternate GTX 3000 can be controlled using Collins CDU, suspect the GTX 3000 LRU. TCAS Collins CDU: Navigate to ATC page and observe status. Access the Collins MFD status page. TCAS faults wkh ATC faults point to transponder malfunction. TCAS faults alone point to TCAS. r Commercial Off The Shelf ADS-8 receiver devices are suitable for GO / NO GO confirmation that the GTX 3000 transponders are transmitting GPS position. HOWEVER, only approved calibrated test devices, such as the IFR 6000. may be used to confirm transponder output power and minimum trigger levels as well as diversity isolation. To conduct an in-depth as-installed complete functional check including UAT, qualified test equipment such as the IFR 6000 will be required. Refer to specific test set instructions for operation and testing. SDNY_GM_02758086 SUBJECT TO PROTECTIVE ORDER PARAGRAPHS 7, 8, 9, 10, 15, and 17 EFTA 00245008 EFTA01261668 SDNY_GM_0275f0D87 SUBJECT TO PROTECTIVE ORDER PARAGRAPHS 7, 8, 9, 10, 15, and 17 EFTA_00245009 EFTA01261669 Elliott Aviation Technical Products Development. Inc. C;;:7 6601 74I" Ave Building A Milan, IL 61264 ELLIOTT AVIATION Instructions for Continued Airworthiness For Garmin ADS-8 System Installation Chapter 3 ACCESS: Report No.: ICA-4079-560 Revision: IR Dated 05/01/2018 13 of 19 3.1 Overview: The information contained herein supplements the basic Maintenance Manuals only in those areas listed, when th aircraft is modified in accordance with Elliott Aviation drawings and diagrams specified in Section 1.3 of this document. 3.1.1 GTX 3000s are located in the forward right avionics bay upper equipment shelf. A configuration module is also located inside the J3302 connectors. 3.1.2 GDL 88 is located in the forward left avionics bay lower equipment shelf. A configuration module is also located inside the .1811 connector. 3.1.3 Flight Stream 110 (if installed) is located on the back of the Pilots chart holder cabinet. 3.1.4 ADS-8 1/2 annunciator is located in the cockpit panel 3.1.5 GA36 GPS Antenna is located on top of the aircraft fuselage above the cockpit headliner at FS 128.74 right of center line 3.1.6 UAT Antenna is located on the belly of the aircraft fuselage below the left forward avionics bay at FS 35.14 3.1.7 Wiring follows existing aircraft wire routes in the nose and cockpit area. 3.2 Equipment and wiring access: No new access is required from the installation of this modification. Access to all equipment and wiring is gained using existing aircraft maintenance manual techniques. 3.2.1 GM. 88 and GTX 3000 rack mounted Line Replaceable Units (LRU). 3.2.1.1 No hand tools are required. The coax and wire hamess connectors knurled and are intended to be removed and tightened by hand. Should assistance In the form of pliers be used, take care to not distort or over tighten. 3.2.1.2 Observe typical avionics systems precautions including: • Coax connectors. Do not bend or kink the coax, avoid bending the center pin, inspect for debris prior to reinstallation. • Wire harness connectors. Disengage associated circuit breakers first. Use care when handlin connectors to ensure shield drain integrity, alternate locking screw tightening sequence and ensure proper alignment during re-installation. 3.2.1.3 Each LRU rack uses a lock down mechanism to secure the LRU in the rack. • To remove, pull while twisting counter clockwise until the LRU hook is dear. The LRU shoul now be free. • To instal, align the LRU in the rack. Slide the LRU until the foot is firmly engaged in the rack. Lift the lockdown mechanism over the LRU hook. Tighten firmly until secure. • Conduct necessary checkout procedures described elsewhere in this document. 3.2.1.4 Configuration Modules are located inside the J881 GDL 88 connector and inside each .13302 GT 3000 connector. Hand tools are required to gain access inside the backshell. Retain hardware after removal. To install secure retained hardware and Reconnect to applicable unit. Conduct necessary checkout procedure described elsewhere in this document. SDNYGIvl02758088 SUBJECT TO PROTECTIVE ORDER PARAGRAPHS 7, 8, 9, 10, 15, and 17 EFTA_002.45010 EFTA01261670 SDNY_GM_02758089 SUBJECT TO PROTECTIVE ORDER PARAGRAPHS 7, 8, 9, 10, 15, and 17 EFTA_0024501 I EFTA01261671 Elliott Aviation Technical Products Development. Inc. r 6601 74°' Ave Building A Milan, IL 61264 ELLIOTT AVIATION Instructions for Continued Airworthiness For Garmin ADS-B System Installation Report No.: ICA-4079-560 Revision: IR Dated 05/0112018 14 of 19 3.2.3 Flight Stream 110 (if installed) Line Replaceable Unit (LRU). GPS and UAT antennas: Hand tools are required. These components are secured with screws and nuts. To remove, remove this hardware and retain. Disconnect the electrical / coax connector. To install, secure with the retained hardware. Reconnect electrical / coax connector. 3.2.4 ADS-B 1/2 Annunciator: Hand tools are required. This component is secured with locking paws. To gain access to these locking paws gently pull the annunciator lens out. Screws located inside loosen the upper and lower screw. Once locking paw has been loosened pull annunciator body out of the annunciator housing and instrument panel To install insert annunciator body back through the instrument panel and annunciator housing. Tighten locking paws until annunciator body and housing are tight against the instrument panel. then press annunciator lens firmly into the annunciator body. Conduct necessary checkout procedures described elsewhere in this document. Chapter 4 LIFTING AND SHORING: Not applicable this modification. Chapter 5 LEVELING AND WEIGHING: Not applicable this modification. Chapter 6 TOWING AND TAXIING: Not applicable this modcation. Chapter 7 PARKING AND MOORING: Not applicable this modification. Chapter 8 PLACARDS AND MARKINGS: Not applicable this modification. Chapter 9 SERVICING: Not applicable this modification. SDNY_GM_02758090 SUBJECT TO PROTECTIVE ORDER PARAGRAPHS 7, 8, 9, 10, 15, and 17 EPTA_002450 I 2 EFTA01261672 SDNY_GM_02758091 SUBJECT TO PROTECTIVE ORDER PARAGRAPHS 7, 8, 9, 10, 15, and 17 EFTA_00245013 EFTA01261673 Elliott Aviation Technical Products Development, Inc. LW 6601 741" Ave Building A Milan, IL 61264 ELLIOTT AVIATION Instructions for Continued Airworthiness For Garmin ADS-B S stem Installation Report No.: ICA-4079-56 Revision: I Dated 051011201 15 of 1 Chapter 10 AIRWORTHINESS LIMITATIONS 10.1 FAA Approval of Airworthiness Limitations This chapter of this supplement must be attached to the Airplane Maintenance Manuals. The information contained herein supplements the basic Maintenance Manuals only in those areas listed, when the aircraft is modified in accordance with FAA Form 337 for the installation of Garmin ADS-8 System. For limitations and procedures not contained in this supplement. consult the basic Airplane Maintenance Manuals. The Airworthiness Limitations Section is FM approved and specifies maintenance required and u 14CFR 99 43.16 and 91.403, unless an alternative program has been FAA approved. FAA APPROVED: Principal Avionics Inspector Minneapolis — St. Paul FSDO FAA Approved Date: SDNY_GM_02758092 SUBJECT TO PROTECTIVE ORDER PARAGRAPHS 7, 8, 9, 10, 15, and 17 EFTA 00245014 EFTA01261674 SDNY_GM_02758093 SUBJECT TO PROTECTIVE ORDER PARAGRAPHS 7, 8, 9, 10, 15, and 17 EFTA 00245015 EFTA01261675 • Elliott Aviation Technical Products Development. Inc. 6601 74° Ave Building A Wan, IL 61264 <Z1 ELLIOTT AVIATION Instructions for Continued Airworthiness For Garmin ACS-8 S stem Installation Report No.: ICA-4079-561 Revision: IR Dated 05/01/201 16 oft Chapter 10 Revisions Status Rev Description Page (6) Data FM Approved By IR INITIAL RELEASE ALL FAA Approved Date: SDNY_GM_02758094 SUBJECT TO PROTECTIVE ORDER PARAGRAPHS 7, 8, 9, 10, 15, and 17 EFTA 00245016 EFTA01261676 SDNY_GM_02758095 SUBJECT TO PROTECTIVE ORDER PARAGRAPHS 7, 8, 9, 10, 15, and 17 EFTA_00245017 EFTA01261677 • Elliott Aviation Technical Products Development, Inc. 6601 741" Ave Building A Milan, IL 61264 t:::2 t:qc ELLIOTT AVIATION Instructions for Continued Airworthiness For Garmin ADS-B System Installation Report No.: ICA-4079-560 Revision: IR Dated 05/01/2018 17 of 19 10.1 GPS & UAT Antenna The area of the GPS and UAT Antenna installations must be inspected visually for damage, wear, and corrosion in accordance with Hawker/Beecticraft general inspection criteria in addition use eddy current inspection techniques m accordance with MIL.STC-271 using templates defined in section 10.3. Structural Element (Skin) Threshold (Flights) Recurring (Flights GPS Antenna, Connector Hole 9,058 9.058 GPS Antenna, Fastener Hole 4,146 4,146 UAT Antenna, Connector Hole 21,139 21,139 UAT Antenna Fastener Hole 7,572 7,572 10.2 Inspection Method The connector and fastener holes should be inspected using eddy current inspection techniques, according to intervals outlined in tables below. POD curves from the NTIAC "Nondestructive Evaluation Capabilities Da Book" for lap splice joint specimens that a 0.10' crack has a 90% probability of detection using eddy curt techniques. The threshold crack length for each location indicates that a crack, if present should be detectable the time of the threshold inspection. Cracks longer than 0.10' must be repaired prior to the next flight T inspection should indicate the following details; Affected Aircraft System GPS Antenna UAT Antenna Structural Detail Connector Hole Doubler Fastener Holes 10.3 Required Circle Templates Modification Rivets 0.201" 0.75 GPS Antenna UAT Antenna X FAA Approved Date: Inspection Notes Inspect edge of hole in skin. Inspect fastener holes in skin. Cracks are most likely around fastener holes closest to the edges of the doubler. e e SDNY_GM_02758096 SUBJECT TO PROTECTIVE ORDER PARAGRAPHS 7, 8, 9, 10, 15, and 17 EFTA_00245018 EFTA01261678 SDNY_GM_02758097 SUBJECT TO PROTECTIVE ORDER PARAGRAPHS 7, 8, 9, 10, 15, and 17 EFTA_00245019 EFTA01261679 • Elliott Aviation Technical Products Development, Inc. 6601 74" Ave Building A Milan. IL 61264 AVIATION Instructions for Continued Airworthiness For Garmin ADS•B S tem Installation Report No.: ICA-4079- Revision: I Dated 05/01/201 18 of 1 10.4 Eddy Current Templates 0 0.194" DlA 0 °294. Dw 0 "94. ow AD3 EDDY CURRENT CIRCLE TEMPLATE (SELECTED RIVETS) O AD4 0.225' Dw Q 0256' DIA O 0288' DIA 0.32T 0.356- I 1 0.388' ow DIA 0.425* 0.456" 0.488' Ll ow DIA Dw ADS ADS EDDY CURRENT CIRCLE TEMPLATE (0.201" DIAMETER HOLE) 0.301' MA 0 0.401' Diek 0.501' DIA SDNY_GM_02758098 SUBJECT TO PROTECTIVE ORDER PARAGRAPHS 7, 8, 9, 10, 15, and 17 EFTA_00245020 EFTA01261680 SDNY_GM_027580.9 SUBJECT TO PROTECTIVE ORDER PARAGRAPHS 7, 8, 9, 10, 15, and 17 EFTA_00245021 EFTA01261681 Elliott Aviation Technical Products Development. Inc. C: r 6601 74U Ave Building A Milan, IL 61264 ELLIOTT AVIATION Instructions for Continued Airworthiness For Garmin ADS•B System Installation Report No.: ICA-4079-56 Revision: II Dated 05/011201 19 of 1 EDDY CURRENT CIRCLE TEMPLATE (0.750" DIAMETER HOLE) (Th.) 0.850' DR 0.950' OR 1O50' DIA FM Approved Date: SDNY_GM_02758100 SUBJECT TO PROTECTIVE ORDER PARAGRAPHS 7, 8, 9, 10, 15, and 17 EFTA_00245022 EFTA01261682 SDNY_GM_02758101 SUBJECT TO PROTECTIVE ORDER PARAGRAPHS 7, 8, 9, 10, 15, and 17 EFTA_00245023 EFTA01261683 • Elliott Aviation Technical Products Development. Inc. C:;:2 6601 74^ Ave Building A Milan, IL 61264 ELLIOTT AVIATION Instructions for Continued Airworthiness For Garmin ADS-B System Installabon APPENDIX A ATTACHMENTS Report No.: ICA-3761-563 Revision: A, Dated 02/24/201/ AI MI documents listed in the table below must be attached to this document and maintained in accordance with Chapter one. ATTACHMENTS DOCUMENT NO. TITLE REV PAGES CFG.3761.560 Configuration Instructions for Garmin ADS-B Out System Installation IR 14 121-4079-E0560-000 GTX3000 Transponders and GDL86 ADS-B System IR 6 121-3761-M0560-050 Wire Routing Installation IR 3 SDNY_GM_02758102 SUBJECT TO PROTECTIVE ORDER PARAGRAPHS 7, 8, 9, 10, 15, and 17 EFTA_00245024 EFTA01261684 SDNY_GM_02758103 SUBJECT TO PROTECTIVE ORDER PARAGRAPHS 7, 8, 9, 10, 15, and 17 EFTA_00245025 EFTA01261685 Elliott Aviation Technical Products Development, Inc. 6601 741" Ave Building A Milan, IL 61264 ELLIOTT AVIATION Flight Manual Supplement For Gamin ADS-8 System Installation Report No.. FMS4079.560 Revision: IR Page I of 5 FM Approved Aircraft Flight Manual Supplement For Garmin ADS-B Out System Installation In Beechcraft Corporation Model 400A (Beechjet) (Type Certificate A16SW) Registration: N727KB Serial Number: RK-260 This supplement must be attached to the Approved Airplane Flight Manual when the Garmin ADS-B Out System is installed in accordance with FM From 337 dated S- a- 201k . The information contained in this document supplements or supersedes the basic Airplane Flight Manual only for the areas listed. For Limitations, Procedures, and Performance not contained in this supplement, consult the basic Airplane Flight Manual DALE E CDOSYnnedbYDALE ,EIXENDOWel DRENCKHAUN ciats't".°113315g FAA Approved /u1SP-FSDo..ais fiD 2018 ELLIOTT AVIATION TECHNICAL PRODUCTS DEVELOPMENT, INC. Elliott Aviation Technical Products Development. Inc reserves the copyright of an information and illustrations in this publication which is prowled in confidence and which may not be used for any purpose other than for %each it was ongnally supplied. The pubkation may not be reproduced in pad or in whole mhout the consent in writing of Elliott Aviation Techncal Products Development. Inc FAA APPROVED DATE: SDNY_GM_02758104 SUBJECT TO PROTECTIVE ORDER PARAGRAPHS 7, 8, 9, 10, 15, and 17 EFTA_00245026 EFTA01261686 SDNY_GM_027513105 SUBJECT TO PROTECTIVE ORDER PARAGRAPHS 7, 8, 9, 10, 15, and 17 EFTA_00245027 EFTA01261687 Elliott Aviation Technical Products Development, Inc. 6601 7401 Ave Budding A Milan, IL 81264 ELUOTT Report No.: FMS-4079-560 Revision: IR Page 2 Of 5 AVIATION Flight Manual Supplement For Garmin ADS•8 System Installation REVISIONS PAGE Rev Description PM. PP Date Approved By IR Initial Release ALL FM APPROVED DATE: SDNY_GM_02758106 SUBJECT TO PROTECTIVE ORDER PARAGRAPHS 7, 8, 9, 10, 15, and 17 EFTA_00245028 EFTA01261688 SDNY_GM_02758107 SUBJECT TO PROTECTIVE ORDER PARAGRAPHS 7, 8, 9, 10, 15, and 17 EFTA_00245029 EFTA01261689 A :2 Elliott Aviation Technical Products Development, Inc. 6601 74m Ave Building A Milan. IL 61264 ELLIOTT AVIATION Flight Manual Supplement For Garmin ADS-8 System Installation Report No.: FMS-4079-560 Revision: IR Page 3 of 5 TABLE OF CONTENTS COVER PAGE 1 REVISIONS PAGE 2 TABLE OF CONTENTS 3 I General- 4 2 Limitations 5 3 Emergency 5 4 Abnormal' 5 5 Normal. 5 6 Performance. 5 7 Weight and Balance I Equipment List 6 FAA APPROVED DATE: SDNY_GM_02758108 SUBJECT TO PROTECTIVE ORDER PARAGRAPHS 7, 8, 9, 10, 15, and 17 EFTA_00245030 EFTA01261690 SDNY_GM_02758109 SUBJECT TO PROTECTIVE ORDER PARAGRAPHS 7, 8, 9, 10, 15, and 17 EFTA 0024503I EFTA01261691 Elliott Aviation Technical Products Development, Inc. 6601 74'" Ave Building A Milan, IL 61264 ELLIOTT AVIATION Flight Manual Supplement For Garmin ADS-8 System Installation Report No.' F MS-4079- 560 Revision: IR Page 4 of 5 1 General: The Garmin GTX 3000 Mode S Transponders meet FAA TSO C112d and are digitally interfaced into the Collins Pro Line 21 system. This includes existing Alr Data Systems (ADS) and control systems. There is no change to the Collins Pro Line 21 Control Display Unit (CDU) *ATC CONTROL' page operations or indications. There is no change to the existing transponder circuit breaker assignment, value, labeling or operation. The GTX 3000 Transponders also meet FM TSO C166b and therefore incorporate by design ADS-8 OUT 1090ES functionality. No separate control is required to enable ADS-B functionality The GTX 3000 Transponders are digitally interfaced to the Attitude Heading System (Ah1S) and TCAS (if installed) to support ADS-8 functionality. The Garmin GDL 88 CPS 1 UAT meets FM TSO C145c/B2 and is interfaced wth the GTX 3000 Transponders to serve as ADS-B required position source. No separate control is available and may only be disabled by pulling the circuit breaker. ADS-B GPS required position source failure is indicated by the amber ADSB 1 or ADSB 2 annunciators. The 'V and' annunciators lights illuminate based on the active transponder. ADS-B position monitoring is only available when the selected transponder is ON. ADS-B device failure is indicated by the ATC FAIL annunciation displayed on the ProLine 21 RTU. The GOL 88 GPS 1 UAT also meets FM TSO C154c which allows reception of FM TSO C157W1 ADS-S FIS-B Information for distribution to Portable Electronic Devices via a Germ'', Right Stream 110 Bluelooth FM TSO C157 transceiver. No separate control is available and may only be disabled by pulling the circuit breaker. The GDL 88 GPS I UAT and optional Flight Stream 110 Bluetooth units are protected by the following circuit breakers: CIB Name Amps Location Bus ADS-B GPS 1 Pilot CB Panel 28vdc Right Main Bus FIS-B BL TH 1/2 Pilot CB Panel 28vdc Right Main Bus The Installed ADS-B OUT system has been shown to meet the equipment requirements of 14 CFR 91.227. FM APPROVED DATE: SDNY_GM_ SUBJECT TO PROTECTIVE ORDER PARAGRAPHS 7, 8, 9, 10, 15,02758110 and 17 EFTA_00245032 EFTA01261692 SDNY_GM_02758111 SUBJECT TO PROTECTIVE ORDER PARAGRAPHS 7, 8, 9, 10, 15, and 17 EFTA_00245033 EFTA01261693 Elliott Aviation Technical Products Development, Inc 6601 le l Ave Budding A Milan, IL 61264 ELUOTT AVIATION Flight Manual Supplement For Gannin ADS-B System Installation Report No FMS-4079-560 Revision: IR Page 5 of 5 2 This STC does not constitute airworthiness approval for portable electronic devices whether used to display FIS-B information or any other aviation application. This STC approves FIS-B provisions which may be displayed on a Portable electronic device as avowed by regulation. An operational approval may be required. The GDL88 GPSIUAT is not approved as a navigation position source. 3 Emergency: No change to basic AFM 4 Abnormal: 4.1 ADS-8 position loss: In the event the ADSB 1 or ADSB 2 annunciator (amber) illuminates. notify ATC. 4.2 ADS-8 loss of function: In the event an ATC FAIL message on the RTU. select alternate transponder. 5 Normal: 5.1 Before Taxi —Select transponder ON (this enables ADS•B ground functions for ATC mandating) 5.2 Shutdown — After parking brake is set, select transponder to STBY. 5.3 If the optional Fight Stream it 0 is installed FIS-B information is intended to enhance pilot awareness of weather and airspace conditions. It does not replace positive two way communication when making safety critical weather or routing decisions. Use FIS-B weather and NAS status information as follows: a) To aid pilot awareness of hazardous meteorological conditions and awareness of the regulatory status of the airspace. b) Changes in hazardous meteorological conditions andfor airspace status the pilot should communicate with the ATC controller. FSS specialist, or operator dispatch for more information about the current meteorological conditions or regulatory airspace status. c) FIS-B information is meant to enhance flight planning only It lacks sufficient resolution and updating necessary for tactical maneuvenng. 6 Performance: No change to basic AFIA. 7 Weight and Balance I Equipment List: See basic Airplane Flight Manua! for current Weight and Balance FAA APPROVED DATE. SDNY_Gbl_ 12 SUBJECT TO PROTECTIVE ORDER PARAGRAPHS 7, 8, 9, 10, 15,027581 and 17 EFTA_00245034 EFTA01261694 SDNY_GM_02758113 SUBJECT TO PROTECTIVE ORDER PARAGRAPHS 7, 8, 9, 10, 15, and 17 EFTA_00245035 EFTA01261695 0 MAJOR REPAIR AND ALTERATION u S commin a (Airframe, Powerplant, Propeller, or Appliance) re,,,,..t.k eon. Approved Ole No 2110-0020 I in0C07 Electronic Tractom Motet For FAA Use Only moon minim AoTONISIINU011 INSTRUCTIONS Poe Or type all sites, See FAR 439, FAR 43 APP4094 B. and AC 43 941 (or subsequent tension Mem° for instrucleCns and dispotatIOn ol INS TOM. TM report is requited by law (49 U S C 1421). FOX, I report Can Iran poi penalty ro4 10 exceed 51.000 EX each such Motion (Seaton 901 Fatima Aviator. Act 1051) Re I. mit NabOrdely and Regrura0n Mat N787TA ROOM No. RK-260 Make Raytheon Aircraft Company 400A Model 400A Series Owner Name (As Thom) on nrpostrabon 4.40.6400 Flight Options .LLC Address (AS shown on regq4mcon corhiScate) Mans 26180 CUMS versant PKWY 2. oil 110Spaideitati stew ad re 44143-1453 Coat OA 3. ForFAA Um Only 4. Type S. Unit IdernInkatIon Repair Alletatco UM make Medal Renal Hunter O CI AIRFRAME (As defented In ISOM 1 aee.e) O O POWERPLANT O . PROPELLER O O APPUA/4CE eye menatount & Conformity Statement A Agency's Name and Mired 5 Kind of Agency Hr. Nextant Aerospace Mew [ADDRESS REDACTED] corm/ USA 0 US Certilluned Mechanic 0 IMentilaCturer O FOn/On Centacated Mechanic C. Certicele No. 0 CertIlltMed Repay Staten CRS # 25NR667B 0 Cereficaleal Maintenance Orgerrzefen a I army met the repair andfor ailcvatem matte 10 the mint.) identified item 6 above and detainee on tie reverse or attachments harem nave been made n accordance min the !muniments of p r143 ol teUSfederalikidamn Regulations and that Cie intermatoin luthelied Wen 4 Ina and correct ba the beet el m o ketrodedEre Ealendad ranee Ml per 14 CFR Pen 43 Ape e O SynahreiDale of Authorized A.Ockwell 01/04/2013 7. &PPM allot Return tO Unice mason to roamed/ efiel Gamma EnRiliedt*Tht the unt d0n14d m ROM 5 was mIfeCted in the manner inscribed by no kinnietrater oft's Federal/Walton Atennetrawin and 9 ®APPROVED U REJECTED BY FM FN Stundards ROPecier Manu/adrier I.4atneenanCe Orpenineeal Person Approved by canaden Dom/Mem of Transport FAA Demme* X Rorer Staboo inset:son Authteraben COX; (Specify, Ctintiarne or Deeigraben No CRS # 25NR6678 SignatweiDate 0.1 Authentic, Ind 41i. A.Ockwell * I 01/04/2013 FAA Form 33? (sloe) SDNY_GM_02758114 SUBJECT TO PROTECTIVE ORDER PARAGRAPHS 7, 8, 9, 10, 15, and 17 EFTA_00245036 EFTA01261696 SDNY_GM02758115 SUBJECT TO PROTECTIVE ORDER PARAGRAPHS 7, 8, 9, 10, 15, and 17 EFTA_00245037 EFTA01261697 NOTICE Weight and balance or operating lernriation changes shalt be entered in the appropriate aircraft record An alteration must be compatible with all promos alterations to assure continued conformity with the &upbeat° mourthiness requirements. 8. Description of Work Accomplished (groom space is required. attach &ethanol sheets identity math entre nehonaWy and registration mark end date wale completed) N787TA Nabonahty and Registration Mark 01/04/2013 Installed the following In-Flight Entertainment System in accordance with STC 0 ST03960AT and in accordance with Nextant Aerospace Master Drawing List 081002067. Revision E. Dated January 26 2011 The Emteq LED cabin lights provide high reliability low power consumption Indirect Cabin Lighting, Galley Task Lighting and Lavatory Vanity Lighting. Installed LED Passenger Safety Signs The cabin lights are interfaced to the existing cabin lighting power distribution and control switches. Installed Cabin LED Lighting System without the Venue System in accordance with DB1107014. Rev IR Dated January 26.2012 Installed LEO Passenger Safety Signs in accordance with Wiring Diagram DB 1108001 Rev IR January 26 2012 Scheduled Inspection and Maintenance. inspect System Installation Component including wire Bundles, Cables Racks and Connector Condition and security in conjunction with the B Check (every 400 hours after Initial 200 Hours -r inspection) tasks and "CI Check (every 1200 after initial 200 Hr -r Inspection) Per Hawker Beethiet 400A Maintenance Manual 5.20.02 requirements listed within Scheduled Inspection Section Rt(-1 and above ICA for LED Cabin Lighting System Ref to Nextant Aerospace Document No DB1108019 Rev IR Dated September 22 2011 or Later FAA Accepted Revisions Installed Iridium Sat Comm and Broadband Internet System with Almell Axxess II and ATG 4000 in Accordance with DB 1001013. Rev D ICA for Aimee System Ref to Nextant Aerospace Document No D81105003. Rev A dated September 22 2011 or later FAA 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 ATG4000 Installation Manual 013485 Revision B Dated November 2009 or later applicable revision Aircell Assess II WtAN AFM Supplement DB10,32072 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 the following Nextant Aerospace Drawings This is Located under the Seat Divan NX252-10007-03. NX252.10007.04. NX252-10007-05 NX252-10007-06 NX252-10007-12. NX252-10007-13. Rev IR Dated June 04 2012 Channel Hat Inverter Mount Rev IR Dated June 12. 2012. Any Inverter 115 VAC. WfHeatsink and Hat. Rev IR. Dated June 14 2012 Mount Plate ,Single Inverter. Under Divan Rev IR Dated. June 13. 2012. Assy, Inverter. Divan Mount Rev IR. Dated June t4 .2012 Assy Bracket Plate Mount Inverter Linder Divan Rev IR, Dated June 14 2012. Angle.1xl* Inverter Mount CA for Astronics 115 VAC Cabin Inverter Ref to Nextant Aerospace Report No 081108018 Rev IR Date 9/27)2011 or later FAA Accepted Revision. Aircraft Flight Supplement DB1109012 has been installed on the Aircraft See Current Weight and Balance Dated 12121/2012 End K Additional Sheets Are Attached FAA Form 337 8006) SDNY_GM_02758116 SUBJECT TO PROTECTIVE ORDER PARAGRAPHS 7, 8, 9, 10, 15, and 17 EFTA_00245038 EFTA01261698 I SDNYGM02758117 SUBJECT TO PROTECTIVE ORDER PARAGRAPHS 7, 8, 9, 10, 15, and 17 EFTA_00245039 EFTA01261699 Mottebalsigs of America Aleparbnent of ¶ransportntion — Arberal Ablation Abministration Supplemental Type Certificate /itch e).treeel ...47/14924/4 ST03960AT Nextant Aerospace LLC 3800 Southern Blvd. West Palm Beach, FL 33406 ~VA. 1.4/ trAitaye 4s 4/, /l/re tom)." r let14.reose fineljec/ a 44 ISientarliraoj wad erno.474.a 44,9/er on 4oefee/eiateenew •714•14 /X at ivere414Ivw niroe4rowen4 !Ile/ 2 5 Federal Aviation ett‘merlkard fle0;-.4--migni-... A I6SW S.4 .• Hawker Beechcraft Corporation Sett4/.. 400A gavot/tits .gasajw. Kioeirot. Installation of Rockwell Collins Venue In-Flight Entertainment(IFE), Aircell Axxess Cabin II Iridium Phone and High Speed Internet System with Wireless Local Area Network (WEAN) Astronics II5VAC 60HZ Cabin Inverter, and Emteq LED Cabin Lighting System in accordance with Nextant Aerospace LLC, Muter Drawing List DB1002067, Revision E, dated January 26, 2012, or later FAA approved revision. 2//evelshivai won nwohiva.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. emeakeek semi 44 Ceincamanjr agar oref4sea .44 4tanA,,,r inne..4(4,.....4. 0.14/...frt monied' /moo /' /k ea hfeneie m/ &am 4 44 . //arevonre)/~/er 144 zrovforwt:/&*/*At ..telvath/n/4".. gewk otiorAwlehe July 28,2012 (4.* March 22,2012 lF h oro:neenl.. lFesh treneariese: Melvin D. Tay Manager Atlanta Aircraft Certification Office My aaaaaa er it. certificate is pa/M401• 11, • II.. b ein mealetala el,•00. or iapalameme roe aisedatirm 1 years. se tone. tl• — •-41•Ital le occeriatke MCA rM 21.4`. SDNY_GM_02758118 SUBJECT TO PROTECTIVE ORDER PARAGRAPHS 7, 8, 9, 10, 15, and 17 EFTA_00245040 EFTA01261700 I SDNYGM1,102758119 SUBJECT TO PROTECTIVE ORDER PARAGRAPHS 7, 8, 9, 10, 15, and 17 EFTA 00245041 EFTA01261701 Builds Stain of Army int frlepartment of Zransporthtion - Acthern1 cAbintion ekioniniotration Supplemental. 'Type Cr-ertificate ((Continuation "Beet) Ykt•C;n6.61eST03960AT When the Rockwell Collins Venue system is installed Airplane Flight Manual Supplement, DBI 106015, 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, DB 1109012, Revision IR, dated March 22, 2012, or later FAA approved revision, is required. This system is intended to provide intemet connection and email services to the airplane's cabin using portable electronic devices (PEDs). Any other intended (unction 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. 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. DB I 108018, 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 &meg LED Cabin Lighting system is installed Instructions for Continued Airworthiness (ICA), Nextant Aerospace Document No. DBI108019, Rev IR, dated September 22, 2011, or later FAA accepted revisions must be made available to the operator at the time of installation. my 4444 Ion a Ws coatific•C• pp** Ole Or • rim 1I ten icena(q ga.ON, e, aersot0000t cot a. • FRA t I 11110.2-1110-ilf) ,a 2 of 2 MU This flltatINc. may ma trandernel oecereara win MR 21.42. SDNY_GM_02758120 SUBJECT TO PROTECTIVE ORDER PARAGRAPHS 7, 8, 9, 10, 15, and 17 EFTA 00245042 EFTA01261702 SDNYGM02758121 SUBJECT TO PROTECTIVE ORDER PARAGRAPHS 7, 8, 9, 10, 15, and 17 EFTA 00245043 EFTA01261703 Bala Aisles of Asmara larpartment of Zromsportation - Aaiun! Abiation cAbmististrution frapplentental ralgin (Certificate ((Continuation 'fleet) ...44;flitedy ST03960AT &tie/gig/4a The Certification Basis for this installation is per Type Certificate Data Sheet A I6SW original Certification Basis, Federal Aviation Regulation (FAR), Part 25 as amended by Amendment 25-I through 25-40 plus FAR 25.1335, 25.1351(d), 25.1353(cX5), and 25.1447 of Amendment 25-41; FAR 25.29, FAR 25.255, and FAR 25.1353(cX6) 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 25.175300(O 25.1757 25.1471 25.1529 [25-541 [25-1231 125.1231 125.1131 125-541 [-I Indicates amendment level Sy, OX ***** tea sr thin cortItten• rr poolsbablo by • lit. of at steatite PLOP*, or lorNiSosasett mrestobotb7I r•orS• en 00th. 0-2-1O0 Are 'J C3. PALM N. ttttt Nate at be trointorcal •CforolooCo WO /M I1.0. SDNY_GM_02758122 SUBJECT TO PROTECTIVE ORDER PARAGRAPHS 7, 8, 9, 10, 15, and 17 EFTA_00245044 EFTA01261704 SDNYGM027.123 SUBJECT TO PROTECTIVE ORDER PARAGRAPHS 7, 8, 9, 10, 15, and 17 EFTA_00245045 EFTA01261705 /ESKA DEPARTMENT OF TRANSPORTATION FEIXFIAL AVIATION maismAncei STANDARD AIRWORTHINESS CERTIFICATE • witim ure 30 ) IlMtrietstrt•O•PaXn I 1 AS:Wt SOW I OUTWIT .E0IllWat•••••0 RAYTHEON AIRCRAFT CO ••••E• IIIITRIA REAORA I RIT•260 TRANWORT I ANSOVKIKO we wow< TsNI mai* boalsaia 16/^.1.0 Pes• shaft SI. Steen,. SIAOS• awl meloP•01 imtlin•P•I•mflitliwtinimarlina •••••••Isis ono ••••tvessmana iptala••••••••IllarearSa m••••••••ingmtse• 0.....•••••••Osisisadosea. ANN. NONE • ell•em000•100•5 new pr ••••••0.0 b•••••••••••••affilnolainaci• ••••••• gamine ••••••• ••••••••• Paannel•••••11 an trat-.24:trazzre4-- SDNY_GM_02758124 T TO PROTECTIVE ORDER PARAGRAPHS 7, 8, 9, 10, 15, EFTA_00245046 EFTA01261706 SONY_GM_02758125 T TO PROTECTIVE ORDER PARAGRAPHS 7, 8, 9, 10, 15, EFTA_00245047 EFTA01261707 veto ..... sot ...tAct DEPARTMENT Of TRANSPCOTATICAITECERN. AVIATION ACAINGTRATIC*1 STANDARD AIRWORTHINESS CERTIFICATE P400•407, MP 1 linu.04, ...4.0.4.011. I 4.0.14 I Mew I emtoor. i "tovn",""vc RAYTHEON AIROULET CO "act' .7271C IIR-400A 0-260 TRANSPORT S A.T.Cirr 410 11044 Ia @AI 1m nes stk* mpg snmeSeVS.0041. 011. 1Slillat••••/........ 4 anal.. mint mann stnnaitio wane ognailivapilla aim few • •••••••••••••••••••ka• •••••••••••••• minspoin 1••• Ora. ••••••••440.en min. NONE ?AMA...OW.0MM laser weas Imo_ al ownliptillaw adisa Solindsona nano. .Yid amiale••••101 4. al • 010,./ 011•001, ••••••••••• NIES • Ma vn— astute& ho/.0 cuencrt ow mew: .74 pawn roccan N./Mom( Thor. ems* Igo...is M.. tow. !m.o. inn la otoscan SONY_GM02758126 r TO PROTECTIVE ORDER PARAGRAPHS 7, 8, 9, 10, 15, EFTA_00245048 12/II/I999 c*IT 110140:1 Tit.= DEREK B. J EFTA01261708 SONY:GM3 r TO PROTECTIVE ORDER PARAGRAPHS 7, 8, 9, 10, 15. EFTA_00245049 EFTA01261709 O MAJOR REPAIR AND ALTERATION or Tnracorialxn (Airframe, Powerplant, Propeller, or Appliance) Feat Avian Adisialtballon Ofeta 2120e020 Ito 110112011 farrow Nag mate For FAA la 0* INSTRUCTIONS: One% or type all entries. See Trile 14 CFR 543.9, Pad 43 Appends 9, and AC 43.9.1 (or subsequent revision thereof) for InstructiOnS and disposition of this lean. This report Is required by law (49 U.S.C. g44701). Failure to report can result in a civil penally for each with violation. (49 U.S.C. §46301(a)) 1. Aircraft Nationality and Registration Mark N727KG Sedal No. RK-260 mai°, . RAYTHEON AIRCRAFT COMPANY 'odel 400A Senes 2. owner Name (As shown on registration certificate) STONY POINT I LLC Address (As shown on registration cart/rate) mans I Vil PACK sorra a OH ASHEVILLE Side 0.04Thcacxoth DO 281013/19 Coney UNITED STATES 3. For FAA Use Only 4. Typo 6. Unit Identification Repak alteration tint Make Model Serial No. ID 0 AIRFRAME (As Oesenber 1 in Item 1 above) 0 O POYVERP1ANT O o PROPELLER O O APPLIANCE Type Manuredurer . 6. Conformity Statement A. Agency. Name and Address B. Kind el Agency twiw CCHSTANTAMATOM V. S. Cerurcated Manure i Mateciurer ,,,,,.. en =soon Hi Foregri Coti cued Meade C. Certificate No. car CrivaArdo gm OHIO x Celine/[ADDRESS REDACTED] cony UNIMOSTATES Cerlincaled mammon*, GAII•Hinton D. I certify that the repair andlor Moreton made to the unit(' 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 cored to the best of my dge. Extended range fuel per 14 CFR Part 43 D SigHitorefDEI horsed Intl I fr i 7. Approval for um to Service Pursuant to the authority given persons sp beow, the ,,It identified in Item 5 was inspected in the manner prescribed by the Administrator of the Federal Aviation Administration and Is ix1Approved faRelected BY FAA Fl. Standards Inspector Manufacturer Maintenance Organization Persona *moved by Canada DeposimeM of Transport FM Designee X Station Inspection Authoritaban her Ot (Serway) Certificate or Designation No. CRSNWC7R346J Signatu lib of Authorized Individual - //o)40 c Jr FAA Form 337(10/06) Page I SDNY_GM_02758128 SUBJECT TO PROTECTIVE ORDER PARAGRAPHS 7, 8, 9, 10, 15, and 17 EFTA_00245050 EFTA01261710 SDNY_GM_02758129 SUBJECT TO PROTECTIVE ORDER PARAGRAPHS 7, 8, 9, 10, 15, and 17 EFTA_00245051 EFTA01261711 NOTICE Weight and balance or operating limlation changes shalt be entered in the appropriate aircraft record. An alteration must be compatible with alt previous alterations to assure continued conformity with the applicable eirmythiness requirements. 8. [recedePon of Work Accomplished (If more space as fileilleark &WW1 Od0410ne shoats. Idinfty wah skarn nabboadly and regisrmoon mark and date won, COMAtindl k727146 1n23200 Plan*/ and Papistraton Mark Data INSTALLED BEECH 400/400A/400T SERIES CABIN INTERIOR NOISE REDUCTION SYSTEM IN ACCORDANCE WITH ENGINEERING DRAWING N23011100-501 APPROVED BY EDWARD KATS ON FAA FORM 8110-3 DATED MARCH I0, 2015. COMPLETED WEIGHT AND BALANCE OF AIRCRAFT INSTRUCTIONS FOR CONTINUED AIRWORTHINESS: INSPECT AIRCRAFT IN ACCORDANCE WITH MANUFACTURES SPECIFICATIONS, NO SPECIAL INSPECTION REQUIRED EDAddiflonaf Sheers Are Attached FM Form 337 (10/06) Page 2 SDNY_GM_02758130 SUBJECT TO PROTECTIVE ORDER PARAGRAPHS 7, 8, 9, 10, 15, and 17 EFTA 00245052 EFTA01261712 SDNY_GM_02758131 SUBJECT TO PROTECTIVE ORDER PARAGRAPHS 7, 8, 9, 10, 15, and 17 EFTA 00245053 EFTA01261713 DEPARTMENT OF TRANSPORTATION FEDERAL AVIATION ADMINISTRATION STATEMENT OF COMPLIANCE WITH AERWORTHINESS STANDARDS I DATE March 10. 2015 AIRCRAFT OR AIRCRAFT COMPONENT IDENTIFICATION 2. MAKE Beechcraft Corporation 3. MODEL NO. 400A 4. TYPEIA/44am. Rah Ilelicepter. se.) Airplane 5. NAME OF A ITT [CA N i Constant Aviation LIST OF DATA 6. IDENTIFICATION 7. TITLE N2301, Revision 0 Dated 06130/2014 D10095, Revision (4 Dated 09/05/2013 010081. Revision A Dated 09/05/2013 Master Data list Beech 400/400AMOOT Senes Cabin Interior Noise Reduction System Structural Substantiation Report for N23011103-501 Installation N23011100-501 Weight and Balance Analysis NOTES: 1. This approval indicates the data listed above demonstrates compliance only with the regulations specified by paragraph and subparagraph listed below as "Applicable Requirements". Compliance to the additional regulations not listed here may be required. This town does not constitute FAA approval of all the data necessary for the substantiation of compliance to the necessary requirements for the entire alteration 2. This approval Is applicable to Beechcraft 400A aircraft, SRI RIC•260, N727KG only 3. This approval covers structural aspects only 4. This approval covers engineering data only and is not an Installation approval End --- end— & PURPOSE OF DATA To show compliance with applicable Federal Airworthiness Regulations for the alteration performed on Beechcraft 400A aircraft, Sat RK-260, N727KG only. 9. APPLICABLE REQUIREMENTS (Lisispeaftcsettau) 14 CFR Part 26 §§ 25.23(b), Arndt 25-0; 25.29(b), Amdt 254; 25.301, Arndt 26-23; 25.303, Amdt 25-23; 26.305(a)(b), Amdt 2548; 25.307(a), Amdt 26-23; 25.561(aRbKc ), Amdt 25-23; 25.601, Arndt 25-0; 25.603, Arndt 25-38; 25.805, Amdt 254); 25.609, Arndt 25-0; 25.611, Arndt 26-23; 26.613, Arndt 25-0; 25419, Arndt 25-23; 25423, Amdt 25-0; 25425, Amdt 26-23 10. CERTIFICATION - Under authority vested by direction of Ile Adminiorntnr under 14 CFR Part 183, data listed above and attached sheets numbered established procedures and found to comply with applicable requirements 0 Recommend approval of these data I DAIS Therefore el Approve them data and in aennatanee wish conditions and limitations of appointment been examined in accordance with none have orthc Ainvonhiness Standards listed. II. SIGNATURES(S)OF DESIGNATED ENGINEERING REPRESENTATIVE(S) I?. DESIGNATION NUMBER(S) 13 CLASSIFICATION (Si Edward Kalsehweil 4-4 DERT-605279-NM Structures FAA Form 8110.3 (03/101 SUPERSEDES PREVIOUS EDITION SDNY_GM_02758132 SUBJECT TO PROTECTIVE ORDER PARAGRAPHS 7, 8, 9, 10, 15, and 17 EFTA_00245054 EFTA01261714 SDNY_GM_02758133 SUBJECT TO PROTECTIVE ORDER PARAGRAPHS 7, 8, 9, 10, 15, and 17 EFTA 00245055 EFTA01261715 0 MAJOR REPAIR AND ALTERATION u 3 oissammi oi tweeenern (Airframe, Powerplant, Propeller, or Appliance) menstruumen Awitinintine Fare 001TOM3 cos me 2120-0O20 Mr/Oil Ea.:Ironic Tracking Number For FAA Use Only INSTRUCTIONS: Print or type all entries. See Title 14 CFR §43.9, Pail 43 Appends B. and AC 43.9.1 (or subsequent revision Dieted) for 096yr:eons and disposition of this form. This report is required by law (49 U.S.C. 1421). Failure to report can result in a eve penalty for each such vialation. (49 U.S C. §46301(8)) I. Aircraft Nationality and Regisblitian Mark N727KG Sal No. RK-260 Make RAYTHEON AIRCRAFT COMPANY Model 400A Series 2.- Owner Name (As sham on regiatnelton certificate) STONY POINT 1 LLC Address (As Mown on reeistradon cetti6cafe) m1 W PACK SQ STE 304 Cm ASHEVILLE SW* NC Lp 28801-3419 carry I INITF D STATES 3. For FAA Use Only 4. ype S. UnN IdeMIScallon Repair PRefa40A Unt Make Modal Social Number El n AIRFRAME (As descnbed in Gem I above) 0 O P0WERPLANT 0 O PROPELLER O O APPLIANCE Type mandocium 6. Conformay Statement A. Agencys Name and Address B. Kind of Agency ran Constant Aviation 0 U.S. Carlacaled Mechanic 0 I Manufacturer mans [ADDRESS REDACTED] 0 Sonar Carlierate0 Mechanic C Genre-ale No. city Cleveland sva•Ohia El Cerlicated Repair Staten CRS WC7R346J co 44135 cr...rry USA 0 Cenfixated Maintenance Organization B. I cents that Me repair andfor aiteration made to the urit(s) Minified Is item 5 above and described on me reverse or attachments hereto have been made in accordance WPM the remirements of Part 4301 the U.S. Federal Aviation Regulations and that the intonabon furnished herein is true and correct to the best of my knowledge. Branded range fuel pm 14 CFR Part 43 0 App. B ..,....1-,71;7,0te SignabitvDete of AuMaired Individual Date: z..,. 17 cmt-Pra .7.R 4 r/4/ 1 S . -7 ..ApproyallorReturn to Service Pursuant to Be authority Pen Persons specified below the knit identified In item 5 was Irapected in the mariner posscrAied by Me Administrator of the Federal ANON Administration and is ®APPROVED 0 RENCIED BY O FAA fit Standards Inspector 0 maimed 0 Makibmanat Organlubm r, " Person Approved by Canadan Department of Transport O FAA Designee 0 Repair Stalks, 0 Inspecbon Aulhcrizalon Olher /Spark) Cerblicale or Designason No. CRS WC7R3461 Signature/0aq of Autherkerilndividual ._ ea Date: .2 el — /.,7 —/S-- FAA Form 337 (1001) SDNY_GM_02758134 SUBJECT TO PROTECTIVE ORDER PARAGRAPHS 7, 8, 9, 10, 15, and 17 EFTA_00245056 EFTA01261716 NOTICE Weight end balance or operating bmitation changes shall be entered in the ePPMPriafe aircraft record An alteration must be compatible with an previous alterations to assure continued conformity with the applicable airworthiness requirements. 8. Description of Work Accomplished (If mom space is required, attach additional sheets Identify with aircraft nationality and re0Strabon mark and date work completed) N7271W 03/12/2015 Nationality and Registration Mark Date Accomplished installation of a Standby Instrument in accordance with Nextan1Aerospace STC# ST10959SC per Master Drawing List STC Document (Report: [SSN REDACTED] Rev EF.13, 06119/2014) with approved deviations as follows. Equipment removed: Smith Industries Standbyaltimetes(Part.Numbes-1614AM10);Smith-IndustriesStandbyairspeed.Indicator(Part-Number476AS1)-and13— Standby Attitude Indicator (Part Number. 501.1412.03). Equipment instated: Mil-Continent M0302 Standby Instrument (Part Number: 6420302-5). Structural Deviations. 'IMO, MD-302 STBY Instrument Upgrade' Drawing (NX311-10010 Rev IR. 02/20/2015) and 'Let FWD Circuit Breaker Panel Fabrication* Engineering Order (CA-EO-0315-02 Rev IR. 03104/2015) approved by Paul Redding (DERT-410115-CE) on FAA Form 8110-3 dated: 03/04/2015. Performed satisfactory Ground Test Procedure in accordance with STC Document ([SSN REDACTED] Rev O,12/0912013). Provided Instructions for CoMiwed Airworttiriess STC Document ([SSN REDACTED] Rev 8. 11/18/2013). Provided Airplane Flight Manual Supplement STC Document ([SSN REDACTED] Rev IR, 12/16/2013). Aircraft Equipment List updated and Weight & Balance revised to reflect these changes. ND K Additianal Sheets Are Attached FAA Form 337 (loos} SDNY GM 02758135 SUBJECT TO PROTECTIVE ORDER PARAGRAPHS 7, 8, 9, 10, 15, and 17 EFTA_00245057 EFTA01261717 MAJOR REPAIR AND ALTERATION u s OtIPOW0,1 01 TIIIIVCABOC. (Airframe, Powerplant, Propeller, or Appliance) newel Annan Abilmonineri Form Ayerovol WO No 21100070 2/28/2011 EleelrenC Tracking Number ref FAA Uso Only INSTRUCTORS: Peril or typo as entries See Tin 14 CFR §43.9. Part 4 Appendix B. and AC 43.9.1 (cc subsequent revision thereat for heath:MS all &position of this loop This report is repaired by law U.S.C. 1421). Failure to Ina dull Sx (49 report can result penally each such viNation. (49 U.S C. §46301(a)) 1. Aircraft Nationality and Registrabon Mark N727KG Wei No. RK-260 Make RAYTHEON AIRCRAFT COMPANY Model 400A Series ormiir Name (As shown on mulserstionamtgatle) STONY POINT 1 LLC Address (As shown on registration certakate) Admen 1 W PACK SQ STE 305 cay ASHEVII I F swat& ao 2fLULL-34.19 cooky UNITED STATP5, 3. For FAA Use Only 4. Type S. Unit Identification Repair Alterman UM Make Model Serial NuMber 0 0 AIRFRAME (As Oeunbed In Rem f above) 0 • POWERPLANT 0 El PROPELLER 0 . APPLIANCE Type laraantes 6. Conformity Statement A Agency's Name and Address B. KM olAgency Name Constant Aviation 0 U.S. CerbS:ated Mechanic 0 Mal NatWest Adtress [ADDRESS REDACTED] 0 Foreign Cedificated Mechanic C • Cenecate No any Cleveland sun Ohio 0 temcated Repay Station CRS WC7R346J zo 44135 coArrillsA 0 Undated Maintenance Orgarization 0. leanly Moline repair an dlor alterabon made lo the rairt(s) klontiferd in ROMS/Wove and described on the reverse or attachments hereto hive been made vi (KONdenee ATOMS requirements of P fl 43 of the U.S. Federal Aviation Regulation and that the information furnished herein is true and cartel to the best of my knowledge Extended range fuel per 14 CFR Past 43 APO. 8 0 Signature/Date of Authonzed Ickfendial Date: ..> i " Ce sr ,(4.er P cA-11),:e Pz. -VP/71- 7. Approval for liptuM 10 Servkt Pursuant to the authority given persons specified below. the unit identified in item 5 was inipeeled b the manner prescribed by the AdMiniSliabX of the Federal Avia n AdrNmUtration and Is 0 APPROVED 0 REJECTED BY 0 FAA Fit scandals inspector 0 Mantslacluror 0 Maintenance organaation _ u PIMA ApprOved try Canadian Department*, Transport 0 FAA Designee til Repay Station 0 Inspection Atehorization Other (Specify) CertAcate or DesagnaecA No. CRS WC7R346J Signeiurepate et Au Incloduai - Date: g ....1 _45_ FAA Form 337 (1006) SDNY_GM_02758136 SUBJECT TO PROTECTIVE ORDER PARAGRAPHS 7, 8, 9, 10, 15, and 17 EFTA_00245058 EFTA01261718 NOTICE Weight and balance or operating limitation changes shall be entered in the appropriate aircraft record An alteration must be compatible with att previous alterations to assure continued conformity with the app....cable airworthiness requvements. 8. Description of Work Accomplished (If more space is required, attach additional sheets. Identify with aircraft nationality end registration mark and date work completed.) N727KG 03/12/2015 Nationality and Registration Mark Date Accomplished modification of Glareshield to incorporate LED Annunciators in accordance iinth Nexiant Aerospace STCJ 5710959SC per Master Drawing List STC Document (Report [SSN REDACTED] Rev EF.13, 06/19/2014). Performed satisfactory Ground Test Procedure in accordance with SIC Oommwmt ([SSN REDACTED] Rev A, 07/25(2013). No Change to Equoment List or Weight & Balance. END K Additional Sheets Are Attached FM Faint 337 (t041) SDNY_GM_02758137 SUBJECT TO PROTECTIVE ORDER PARAGRAPHS 7, 8, 9, 10, 15, and 17 EFTA_00245059 EFTA01261719 nextant aerospace Date: March 12, 2015 To: Constant Aviation,L1C From: Nextant Aerospace,LLC //REIMAGINED //REBUILT //REBORN Subject: Supplemental Type Certificate and Nextant Aerospace Sound Kit authorization for 400A serial number RK- 260 (N727KG) This letter serves to provide evidence that the listed Supplemental Type Certificate and Nextant Aerospace Sound Kit on a single installation basis by entities listed in this letter. This also approves Constant Aviation to purchase all articles needed to complete the installation and modifications documented in the master Drawing Lists. All change requests, invoices, and amendments to the purchase agreement must be approved be Nextant Aerospace. Nextant Aerospace Supplier quality provisions 1, 4, 5, 8 apply for this sub contracted maintenance event. Supplemental Type Certificate (s) 1. ST1059SC Proline 21 ) for installation of MD-302 System a. Master Drawing List: [SSN REDACTED] MDL (Master Drawing List) Proline 21 Rev EF.13 later approved by Nextant Aerospace 2. ST1059SC (Proline 21) for installation of Glareshield modification and installation a. Master Drawing List: 373.00-0001 MDL (Master Drawing List) Proline 21 Rev EF.13 later approved by Nextant Aerospace Nextant Aerospace Sound Kit 1. N23011100.501-1 a. Master Kiting listing N23011100-501KL dated 2014-01.17 b. FAA 8110-3 dated March 10, 2015 2. N23011100-501-2 a. Master Kiting listing N23011100-501KL dated 2014.01.17 b. FAA 8110.3 dated March 10, 2015 Retain a copy of this Authorization in your aircraft records. A copy of this authorization letter is to be retained in all aircraft records, as applicable. Agreement acceptance By: Aircraft Details Name: Registration Number : Company: Aircraft hours: Date: Aircraft Cycles: Note: A signed copy must be returned to Nextant Aerospace SDNY_GM_02758138 SUBJECT TO PROTECTIVE ORDER PARAGRAPHS 7, 8, 9, 10, 15, and 17 EFTA_00245060 EFTA01261720 SDNY_GM_02758139 SUBJECT TO PROTECTIVE ORDER PARAGRAPHS 7, 8, 9, 10, 15, and 17 EFTA_00245061 EFTA01261721 UnitrA ciltalt• of 'dnaOa Peptirtment of flirtinsportntion jehrral cglibintion pininiatration Supplemental tri. gpe Qlertifirate Areendet ST10959SC .972.; reggAzfeitaers're Nextant Aerospace LLC 26180 Curtiss-Wright Pkwy. Richmond Heights, 01144143 os-4,4v days 444 oft deur V; .../"Aanippmewia &wit do 4, oz.4.(vm ona'Avam, at abuyvv47.v.i nytui-en,nho ern", 25./44 Federal Aviation :,;(w4i4v.i (See Pages 1 and 4 for complete certification basis.) ea;wissoanefiii. Kre;ecovo.fiCoodn- A I 6SW ../4.6 Hawker Deechcraft Corp. . Rival 400A ftiOrriildhl rare guifens";e7r A Installation of Rockwell Collins Pro Line 21 Electronic Flight Instrument System (EFTS) with Rockwell Collins EMS-6100, Localizer Performance with Vertical Guidance (LPV) approach capability and Universal Avionics Systems Company (UASC) Terrain Awareness Warning System ('I'A WS) in accordance with Nextant Aerospace LLC Master Drawing List Doc. No. [SSN REDACTED] Revision W, dated March 29, 2012, or later FAA approved version. Seindokevoi anaivoreiskw: I) 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 fi t SD Engines FAA approved Airplane Flight Manual Supplement, Nextant Aerospace LLC Doc. No. [SSN REDACTED] Revision !R. dated 10/19/2009, or later FAA approved version, is required on board the modified aircraft. orreArsie any/ att .oryseeray .tode ere041M 40. 404: /ee entor, oeiagotworto en rem' mehnno-ordsevE **ended v wins' Oe a oelena•teibei aita w tanntv:te toteriZene (5, o/[4. .57odow 4,o:way .446flum;(4,86;1/4 xtseArgewavii June 26, 2008 givo./...04.9...w October 19.2009 ark esisteesi 944•00.17 ,4451 September 26, 2011; April 05, 2012 (Signora Steno L. Lardinois Manager. Sysserns and Flight Test Anna. Chicago Aircraft Certification Office (TOM ny NUrRlen of this r • bete is pan s a • by • llnee not ore ay el .000. or lnotlsanent ,Mt e6Nanp 1 rho • of tetra. /MA t , •110.2(10.0) Mt t et • PAOLO lone cora( CCCCC t nay 01 (••48fessitl CCCCC eloo• with MO al.O. SDNY_GM_02758140 SUBJECT TO PROTECTIVE ORDER PARAGRAPHS 7, 8, 9, 10, 15, and 17 EFTA_00245062 EFTA01261722 SDNY_GM_02758141 SUBJECT TO PROTECTIVE ORDER PARAGRAPHS 7, 8, 9, 10, 15, and 17 EFTA_00245063 EFTA01261723 Anita. *to in of America !cpartnirtif of Ernosportation - Arberal cAbintion eAbininiatration Supplemental 'Type Tertifirate ((Qontinutttion *pet) -.47/40210a STI 09595C "424,elawono. October 19.2009 Date Amended: September 26, 2011; April 05,2012 ..ZenelabeVIJ onagovaaGhtes//44444aega: 4) For aircraft equipped with Williams FJ44.3AP Engines, those engines must be installed under STC ST0237 LA. 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-t I? and RK- I 19 thru RK-139, Hawker Beechcraft Service Bulletin No. 34.3431. RK- 118, RK-I40 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. 373.00.0036 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. 1.4Woorthey. Siva : Based on 14 CFR §§21.115 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 A I 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 Al 6SW and §§ 14 CFR Pan 25 as shown on page 4 of 4 of this sTc. Any oltoloylon of tau Certif . /COCO JO DCAJOAOOJC. OF t ff.* Of aol *Acetate.; SI,O0O. or foorasordroot An o.coothoo l two. or bock. TPA IPOS 91)4.2.10....03 PAIL r or 4 Milt MID C fffff irate may 0r fffff forrod In dote:donee sal. FAA 11.4f. SDNY_GM_02758142 SUBJECT TO PROTECTIVE ORDER PARAGRAPHS 7, 8, 9, 10, 15, and 17 EFTA 00245064 EFTA01261724 SDNY_GM_02758143 SUBJECT TO PROTECTIVE ORDER PARAGRAPHS 7, 8, 9, 10, 15, and 17 EFTA 00245065 EFTA01261725 !Inittb Shan of Anita(/' Peportturnt of 7gru)Isportntion - Xrheral Ablation Abminiatration $npplemzrztal Type aertificatt (Qlontinuatian Sheet) girar/tameastx adobe: 19.2009 Dale Amulet,: Scptanbcr 26, 2011; April 05, 2012 Based on 14 CFR §§ 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 A I6SW and the following later regulations: Amdi.12.4.4) 25.771 (2,4) AmA.323.23) 23.301; 23.303; 25381; 25.607: 25 611, 25.773 (00)(2X6) Amdt[25-3111 25.1309 (oXbXcX3Xc)(2): 25.1322 Amcli.125-401 25.901 (b)11)(ik 25.1549 (.XbXo) Anok.123-41) 23.1321 (oX9XcX4). 23.1331;25.1333 Aract(25-42) Arndt 125461 Anok.(25-541 Arm8.125-72; Amdi.125-801 25.1501 25.603:23.603; 25.613: 25.1529 25.307: 25.571. 25.1307 25.1316 25.1329 00 (c)(4k 25.1151 (oX1X10. 25.1381:25.1521 (o)(ck 25.1513f0):25.1581; 25.1583(0 Amtli.123.86) Art44'125-901 Amdt125.91] Arod1.125-1021 A0,0.125-105) 25.305 25.1303 25.561 25.951 (oX8) 25.1585 fa) Am& (25-1011) Am& (25-1091 An14.(25-1131 Ardt125-122) Amdt(25-17.31 25.1323 (d) 25.1323 MOW 25.869 (BM; 23.1431 25.1317 (010)(c) 25.1353(0(1) Based on 14 CFR if 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: AnutiOrigInall 25.601.25.605, 25.609. 25.613.25.1301. 25.1357, 23.1381. 25.1323.23.1541. 13.1381 Anidt124.41 25.771(0 mock 125431 25101; 25301:25.305. 25.307, 25.561(c)c 23.607: 25.611.25.1307 A4,1323-381 25.603.25.1322. 25.1583(c) Am6.125-401 23.1583 fa) ton0.(25-411 Anolt125-421 Anodo125-46) Aro:8.125-543 Aradt[2.3.721 25.1309 (100)XoX6Xon) 25.1501 25.777(Xc) 25.1529 25.869(4)(1) 23.1351 MI) Anet.123-1021 Amth(23-113) Andt.125.123) 25.981(40) 25.143100 25.1333 (Xc) - END aay HC' lea Of MO certificate is pralmee0to ay • nag of set neat." 11.000. Or ilterieeeseAC roe **COSI", 3 roar,. or lota. .LA AVoi 4110-3-11‘0.40) NOR 4 Of 4 mall • • Yy a. trOAS le In aaatd. v, SDNY_GM_02758144 SUBJECT TO PROTECTIVE ORDER PARAGRAPHS 7, 8, 9, 10, 15, and 17 EFTA_00245066 EFTA01261726 SDNY_GM 02758145 SUBJECT TO PROTECTIVE ORDER PARAGRAPHS 7, 8, 9, 10, 15, and 17 EFTA_00245067 EFTA01261727 Nextant Aerospace LLC 355 Richmond Rd. Richmond Heights OH 44143 Master Drawing List Report No.: [SSN REDACTED] Revision EF.13 Document Number: [SSN REDACTED] Revision: EF.13 2/24/2015 Upgrade of Collins Proline 4 to Proline 21 Avionics System Hawker Beech 400A Aircraft FAA STC ST10959SC Approved By Date 6-19-2014 Page 1 of 17 SDNY_GM_02758146 SUBJECT TO PROTECTIVE ORDER PARAGRAPHS 7, 8, 9, 10, 15, and 17 EFTA 00245068 EFTA01261728 Nextant Aerospace LLC [ADDRESS REDACTED]143 Report No.: [SSN REDACTED] Revision EF.[ADDRESS REDACTED]awing List- Upgrade of Collins Proline 4 to 21 Avionics System in the Hawker Beech 400A Aircraft REVISIONS LEVEL DESCRIPTION APPROVED DATE IR Initial Release TT A Minor Changes 71 2125/09 8 Major Rewrite DLB 6129/09 C Minor Changes OLB 7/7/09 D Minor Changes OLB 9009 E Minor Changes OLB 9/18109 F Project Clean up O1$ 10/12/09 G Revised SSA/CCAIDCU Config documents. . OLB 10/16/09 H Project Clean up MB 11/24/[ADDRESS REDACTED]awing Revisions. Aircraft Serial Number Applicability added O18 917/10 J Addition of FJ44-3AP Engine Instrument display capability DLB 9/23/10 K Corrected FJ44-3AP drawing callouts MB 10/27/10 L . Revised Certification Plan [SSN REDACTED] Revised drawings: Table 1: [SSN REDACTED] Table 8A: 373.77-4100 [SSN REDACTED]-01 [SSN REDACTED] 373.77.4200-01 [SSN REDACTED] [SSN REDACTED] [SSN REDACTED] [SSN REDACTED] Added drawing [SSN REDACTED] to Table 8A DLB 11/5110 M Updated MDL to indicate new and revised documents and drawings for amendment SA7464CH-T. DUB 12/15/10 N Revised DCU Config [SSN REDACTED] Added CSU-4100 drawing [SSN REDACTED]. 0LB 1-24-2011 Page 2 of 17 SDNY_GM_02758147 SUBJECT TO PROTECTIVE ORDER PARAGRAPHS 7, 8, 9, 10, 15, and 17 EFTA_00245069 EFTA01261729 Nextant Aerospace LLC 355 Richmond Rd. Richmond Heights OH 44143 Report No.: [SSN REDACTED] Revision EF.13 Master Drawing I — Upgrade of Collins Proline 4 to 21 Avionics System in the Hawker Beech 400A Aircraft • REVISIONS (CONTINUED) LEVEL DESCRIPTION APPROVED DATE O Revised EIS GTP [SSN REDACTED] DLB 5:31-2011 -Revised DCU-Config 373,00 0026 Revised RVSM addendum [SSN REDACTED] Revised drawings: Table 1: 37342-0001 Table 8A: 373-774100 [SSN REDACTED]-01 373-774200 373-774200-01 [SSN REDACTED] [SSN REDACTED] [SSN REDACTED] [SSN REDACTED] P Revised El Analysis [SSN REDACTED] Revised ELA [SSN REDACTED] 7-26-2011 Revised SSA [SSN REDACTED] Revised drawings: Table 1: [SSN REDACTED] [SSN REDACTED]-01 373.34.2530 [SSN REDACTED]-01 [SSN REDACTED] [SSN REDACTED]-01 37334.2550 [SSN REDACTED]-01 Table 8A: 373.34-2515 [SSN REDACTED] [SSN REDACTED] 37334.2545 Added software and part number note to Q Table 8A. DLB 9-20-2011 Added Software documents to Supporting Data table. Minor Change submittal of drawings 373-77- 4001-01 and [PHONE REDACTED]-01. R Re-formatted MDL for aircraft effectivity. DLB 9-26-2011 Page 3 of 17 SDNCGM_02758148 SUBJECT TO PROTECTIVE ORDER PARAGRAPHS 7, 8, 9, 10, 15, and 17 EFTA_00245070 EFTA01261730 Nextant Aerospace LLC [ADDRESS REDACTED] Report No.: [SSN REDACTED] Revision EF.13 Master Drawing List — Upgrade of Collins Proline 4 to 21 Avionics System in the Hawker Beech 400A Aircraft REVISIONS (CONTINUED) LEVEL DESCRIPTION APPROVED DATE S Added STC Amendment Project SA7659CH-T documents and revisions 10-27-2011 T Revised documents: DLB 12-29-20t1 [SSN REDACTED] Cert'Plan 373.00.0040 Struct Anal 373-91.6000 TAWS Installation U Added Table 11. DLB 1.5.2012 V Revised Drawings: [SSN REDACTED] [SSN REDACTED]-01 [SSN REDACTED] 373-34.5102 [SSN REDACTED] Revised Reports: 373-0D-0034 [SSN REDACTED] [SSN REDACTED] [SSN REDACTED] 373.00.0043 Added Report: [SSN REDACTED] DLB 2-8-2012 W Revised Reports: [SSN REDACTED] 373.00.0044 DLB 3-29-2012 X Minor Drawing Changes DG 5/2/2012 Y Added [SSN REDACTED], [SSN REDACTED]. 373-22- 1200. [SSN REDACTED]-01, Minor drawing changes DG 7/5/2012 Z Minor Drawing Changes Amendment to add MD-302, T5835, Glareshield Annunciators. OLD 6120/2013 AA Removed TS835 EPS. OLD 7/1/2013 BB Revised MD302 and Glareshield Annun GTPs. DLB 7/30/2013 CC Removed MD-302 Standby Attitude Module. DLB 8/15/2013 DD Added MD-302 Standby Attitude Module. OLD 11/182013 EE Revised MD302 GTP [SSN REDACTED]. DLB 12/9/2013 Page 4 of 17 SDNY_GM_02758149 SUBJECT TO PROTECTIVE ORDER PARAGRAPHS 7, 8, 9, 10, 15, and 17 EFTA 00245071 EFTA01261731 Nextant Aerospace LLC 355 Richmond Rd. Richmond Heights OH 44143 Report No.: [SSN REDACTED] Revision EF.13 Master Drawing List - Upgrade of Collins Proline 4 to 21 Avionics System in the Hawker Beech 400A Aircraft EF Revised ICA [SSN REDACTED], RVSM Report 373-00.0029. Revised/added drawings marked at Issue EF. a..._ 6.19.14 EF.01 Chg [SSN REDACTED]-01 - WO APP, 373-34.5021 - WI) NO1 ADF 9/8/2014 EF.02 Chg [SSN REDACTED], 373.34-4510-01 - WD TCAS, 373-34- 4511 TCAS RELOCATION 9/9/2014 EF.03 Chg [SSN REDACTED] Production GIP. 9/17/2014 EF.04 Add NX311-10003, NX311-10003-01 - Nutplate Spacers. Instrument Panel 9/23/2014 EF.05 Chg WD #1 PFD chg GND to Float GND (ECR 1865) 9/26/2014 EF.06 CHG [SSN REDACTED] WI) #2 ADF (ECR 1907) 10/1/2014 EF.07 Chg [SSN REDACTED], [SSN REDACTED]-01 10/2/2014 EF.08 Chg [SSN REDACTED], [SSN REDACTED]-01 10/7/2014 EF.09 Chg NX316-10001-01, add NX110-10004, NX110-10005, moved NX315-10005 to table 12. 10/30/2014 EF.10 Chg NX110-10005 10/31/2014 EF.11 Chg 373.77.4200.01 1/15/2015 EF.12 Chg 373.34.7001 and 373.46.2001.01 1/27/2015 EF.13 Chg [SSN REDACTED], [SSN REDACTED]-01. [SSN REDACTED], 373-42- 1007-01 2/242015 The latest revis'on letter of this document will be shown in the upper right hand corner of each page below the document number. The entire document will be repaginated and re- released each me revisions are made. Page 5 of 17 SDNY_GM_02758150 SUBJECT TO PROTECTIVE ORDER PARAGRAPHS 7, 8, 9, 10, 15, and 17 EFTA 00245072 EFTA01261732 Nextant Aerospace LLC 355 Richmond Rd. Richmond Heights OH 44143 Report No.: [SSN REDACTED] Revision EF.13 Master Drawing List — Upgrade of Collins Proline 4 to 21 Avionics System in the Hawker Beech 400A Aircraft SUBSTANTIATION DATA Documents applicable to all aircraft: [SSN REDACTED] EF.13 Master Drawing List [SSN REDACTED] D.01 Instructions for Continued Airworthiness [SSN REDACTED] A Ground Test Plan, EMI Documents.applicable-to-Pratt&-Whitney-JT-150-engine equipped-aircraft- [SSN REDACTED] IR Electrical Load Analysis [SSN REDACTED] C Systems Ground Test Plan [SSN REDACTED] A Collins Proline 4 to 21 Function Hazard Assessment [SSN REDACTED] C Collins Profine 4 to 21 System Safety Assessment [SSN REDACTED] A Collins Proline 4 to 21 Common Cause Analysis [SSN REDACTED] IR Airplane Flight Manual Supplement [SSN REDACTED] B Flight Test Plan [SSN REDACTED] B Ground Test Plan, Engine Instrument System 373.00.0014 IR Engine Instrument Comparison Analysis [SSN REDACTED] B Collins Proline 21 DCU Configuration Report 373.00.0016 IR Structural Analysis - Upgrade of Collins Praline 4 to Proline 21 Avionics System [SSN REDACTED] IR Airspeed Analysis [SSN REDACTED] IR RVSM Substantiation Report [SSN REDACTED] E Project Specific Certification Plan 373.00.0020 IR DCU Structural Load Test Plan 373-93.7000.3-A A Structural Analysis - Transponder Antennas Installation 373.93.7000.7-A IR Structural Analysis - TCAS Antenna Installation 373.93-7000.9-A IR Structural Analysis - GPS/XM Antenna Installation [SSN REDACTED]-21-A IR Structural Analysis - Forward Pressure Bulkhead Feed Through Plate Installation Documents applicable to Williams FJ44-3AP engine equipped aircraft: [SSN REDACTED] A Electrical load Analysis- Williams FJ44-3AP Equipped [SSN REDACTED] A Airplane Flight Manual Supplement- Williams FJ44-3AP Equipped [SSN REDACTED] F Ground Test Plan, Engine Instrument System - Williams FJ44- 3AP Equipped [SSN REDACTED] a Engine Instrument Comparison Analysis- Williams FJ44-3AP Equipped [SSN REDACTED] C Engine Data Concentrator Configuration Report - Williams FJ44.3AP Equipped [SSN REDACTED] A System Safety Assessment Addendum — WiNiams FJ44.3AP Equipped [SSN REDACTED] D Certification Plan/Compliance Checklist Report — Amendment to add Williams FJ44-3AP Engine Instrument Display Option [SSN REDACTED] B Addendum to RVSM Substantiation Report 373.00.0018 373.00-0030 IR Structural Analysis — Addendum to 37100-0016 [SSN REDACTED] A Ground Test Plan, Glareshield Annunciators [SSN REDACTED] IR Instructions for Continued Airworthiness —Glareshield Annunciators Page 6 of 17 SDNYGM02758151 SUBJECT TO PROTECTIVE ORDER PARAGRAPHS 7, 8, 9, 10, 15, and 17 EFTA 00245073 EFTA01261733 Nextant Aerospace LLC 355 Richmond Rd. Richmond Heights OH 44103 Report No.: 373-00.0001 Revision EF.13 toaster Drawing List — Upgrade of Collins Proline 4 to 21 Avionics System in the Hawker Beech 400A Aircraft SUBSTANTIATION DATA (cont.) Aircraft with FMS-6100 LPV Installed [SSN REDACTED] [SSN REDACTED] IR [SSN REDACTED] A [SSN REDACTED] A IR [SSN REDACTED] Assessment, LPV [SSN REDACTED] IR GPS-40005 Change Impact Analysis Aircraft with Universal Avionics TAWS A Installed 373-00.0031 F Certification Plan, LPV/TAWS [SSN REDACTED] IR [SSN REDACTED] A [SSN REDACTED] A [SSN REDACTED] A [SSN REDACTED] A [SSN REDACTED] IR [SSN REDACTED] IR 373.00-0043 A 373.00-0044 A Aircraft with Upgraded GlareshIeld Annunciator [SSN REDACTED] PITOT TUBE REPLACEMENT [SSN REDACTED] IR Aircraft with MD-302 SAM Installed [SSN REDACTED] IR Aircraft with MD-302 Standby Instrument [SSN REDACTED] IR [SSN REDACTED] IR [SSN REDACTED] 373.00.0051 373.00.0060 [SSN REDACTED] [SSN REDACTED] 373.00.0057 Certification Plan, LPV/TAWS Airplane Flight Manual Supplement, LPV Flight Test Plan, LPV Ground Test Plan, LPV CollinsProline'21-Function Hazardand'System'Safety IR C IR IR B Airplane Flight Manual Supplement, TAWS Flight Test Plan, TAWS Ground Test Plan, TAWS Collins Proline 21 System Safety Assessment, TAWS Structural Analysis — TAWS Installation Instructions for Continued Airworthiness — TAWS Installation Electrical Load Analysis— TAWS Installation Configuration Matrix—TAWS Installation Collins Proline 21 Function Hazard Assessment, TAWS Panel Certification Plan Ground Test Plan, Pilot Tube Replacement Certification Plan Certification Plan Airplane Flight Manual Supplement. MD-302 Flight Test Plan, MD-302 Ground Test Plan. MD-302 Function Hazard Assessment, MD-302 System Safety Assessment, MD-302 Instructions for Continued Airworthiness — MD-302 Electrical Load Analysis—MD-302 Installation Page 7 of 17 SDNY_GM_02758152 SUBJECT TO PROTECTIVE ORDER PARAGRAPHS 7, 8, 9, 10, 15, and 17 EFTA 00245074 EFTA01261734 Nextant Aerospace LLC 355 Richmond Rd. Richmond Heights OH 44143 Report No.: [SSN REDACTED] Revision EF.13 Master Drawino List — Upgrade of Collins Proline 4 to 21 Avionics System in the Hawker Beech 400A Aircraft DESIGN DATA This project consists of a upgrading the existing Collins Proline 4 CRT Flight Displays to Proline 21 LCD Flight Displays. As part of this STC most of the existing remaining avionics wiring is removed and replaced with new wire. Those wiring diagrams are listed in Table 9. The remaining existing avionics interface remains as originally TC'd. the existing AHS-85E Attitude Heading Reference System (AHRS) can be upgraded to Collins AHS-3000A per Collins STC ST02173LA in conjunction with this STC. Reference Table 6 for wiring interface drawings to be used with the Proline 4 to 21 upgrade. The existing Collins RTA-444 Radar can be upgraded to Collins RTA-854 Turbulence Detection Radar per Collins STC ST01474VVI-D in conjunction with this STC. Reference Table 7 for wiring interface drawings to be used with the Proline 4 to 21 upgrade. The aircraft must have dual Collins AMS-5000 Avionics Management Systems installed prior to the incorporation of the Proline 4 to 21 STC. It can be upgraded per Collins STC ST00485WI-D in conjunction with this STC. The base STC Installation consists of removing the existing Collins Pro Line 4 Integrated Displays (7x7 CRTs) system and installing: • Three Pro Line 21 Rat Panel Liquid Crystal Displays (8X10 LCD) • Engine Instrument Display Integration (Pratt & Whitney JT15D-5 (See Table 1A)) • Fuel Quantity Display Integration • Upgrade of the existing Collins FMC5000 to the FMC6000 • Replacement of Master Warn/Master Caution Panel These systems will be installed IAW data listed in Table 1 STC Options include: • Fourth LCD panel as #2 MF0. This system will be installed IAW data listed in Table 5. • Collins TCAS II. This system will be installed LAW data listed in Table 2. • XM Satellite receiver. This system will be installed IAW data listed in Table 3. • Single or Dual IFIS-5000 Integrated Flight Information System (IFIS) This system will be installed IAW data listed in Table 4. • Williams FJ44-3AP Engine Instrument Display Integration. This system will be installed JAW data listed in Table 8. Engines must be installed under STC ST02371LA • Universal Avionics TAWS A. This system will be installed JAW data listed in Table 10. • FMS-6100 WAAS/LPV Approaches. This system will be installed PAW data listed in Table 11. • Glareshield Annunciators. This system will be installed IAW data listed in Table 12. • Midcontinent Instruments MD302. This system will be installed PAW data listed in Table 13. Page 8 of 17 SDNY_GM_02758153 SUBJECT TO PROTECTIVE ORDER PARAGRAPHS 7, 8, 9, 10, 15, and 17 EFTA_00245075 EFTA01261735 Nextant Aerospace LW [ADDRESS REDACTED] Report No.: [SSN REDACTED] Revision EF.[ADDRESS REDACTED]awing List - Upgrade of Collins Proline 4 to 21 Avionics System in the Hawker Beech 400A Aircraft Aircraft ADolicabilitv Do to minor factory wiring variances of aircraft serial number ranges the installer must observe the Aircraft Applicability column for determination of applicable drawings to use. The applicability breakdown is as follow: All RK-48 and Below RK-49 and Above All drawings are applicable to either JT15D or FJ44-3AP engine equipped aircraft excluding Table 1A (JT15D aircraft only) and Table 8 (FJ44-3AP aircraft only). For baseline installation the following drawings in Table 1 should be used with both JT15D and FJ44-3AP engine equipped aircraft: Table 1 Drawings Rev Issue Description Aircraft Applicability Wiring Diagrams 373-34.2001 W/D NO.1 CCP ALL [SSN REDACTED] K EF.05 W/D NO.1 PFD RK-48 AND BELOW 373.34.2510.01 J EF.05 W/D NO.1 PFD RK-49 AND ABOVE [SSN REDACTED] W/D NO.1 DCP RK-48 AND BELOW [SSN REDACTED]-01 W/D NO.1 DCP RK-49 AND ABOVE 373-34.2521 W/D NO.2 DCP ALL 37334.2530 W/D NO.1 MFD RK-48 AND BELOW 373.34.2530.01 W/D NO.1 MFD RK-49 AND ABOVE 373.34.2550 W/D NO.2 PFD RK-48 AND BELOW [SSN REDACTED]-01 WAD NO.2 PFD RK-49 AND ABOVE [SSN REDACTED] EF W/D AUX BATT TEST ALL EF SINGLE AUX BAT (PS- ALL [SSN REDACTED] A 835) WIRING DIAGRAM [SSN REDACTED] W/D CKT BKR PNL RK-48 AND BELOW 373-245000.01 W/D CKT BKR PNL RK-49 AND ABOVE [SSN REDACTED] W/D FUEL FLOW CONV RK-48 AND BELOW 373.73.5001.01 EF W/D FUEL FLOW RK-49 AND ABOVE CONV 373.28.6001 W/D FUEL QTY CONV RK-48 AND BELOW [SSN REDACTED]-01 EF W/D FUEL OTY CONV RK-49 AND ABOVE 373.33.1206 EF W/D MC/MW INTERFACE ALL 373.34.3004 EF REVERSION ALL [SSN REDACTED] W/D CHP ALL [SSN REDACTED] W/D NOSE RJB MOD RK-48 AND BELOW [SSN REDACTED]-01 W/D NOSE RJB MOD RK-49 AND ABOVE 373-91.0000 WIRE ROUTING DIAGRAM ALL 33.11.02-01 IR COCKPIT LIGHTING ECO RK-48 AND BELOW Drawings Rev Issue Description Aircraft Applicability 373-24.3100 W/D VOLT AMMETER EXT RK-48 AND BELOW [SSN REDACTED].01 A EF W/D VOLT AMMETER RK-49 AND ABOVE Page 9 of 17 SDNY_GM_02758154 SUBJECT TO PROTECTIVE ORDER PARAGRAPHS 7, 8, 9, 10, 15, and 17 EFTA_00245076 EFTA01261736 Nextant Aerospace LLC 355 Richmond Rd. Richmond Heights OH 44143 Report No.: [SSN REDACTED] Revision EF.13 Master Drawing List - Upgrade of Collins Proline 4 to 21 Avionics System in the Hawker Beech 400A Aircraft EXT [SSN REDACTED] H EF W/D SWITCH PANELS ALL DB1008007 O Z STBY GYRO LIGHTING MOD RK-049 AND ABOVE Structural Drawings [SSN REDACTED] G Z SW PNL ASSY ALL 373.91.3213 G Z SW PNL FAB ALL 373-91.4110 L EF - SHELF FAB ALL 373-91.4100 M EF SHELF ASSY ALL 373.91.4000 K EF SHELF INSTL ALL 373.92-4110 G Z INST PNL FAB ALL 373.92-4100 C INST PNL ASSY ALL 373.92.4110.3 H EF ANGLE, INST PNL ALL 373-92.4110-5 H EF ANGLE, INST PNL ALL 373.92.4110-7 H EF ANGLE, INST PNL ALL 373.92.4110-8 B EF PNL. INST, FO STD RK-49 AND ABOVE. OPTIONAL 373-924110-10 8 EF PNL, INST, XTi-DOM RK-49 AND ABOVE. OPTIONAL 373.92.4110.14 A EF PNL, INST. XTi-INT RK-49 AND ABOVE, OPTIONAL 373.92.4110-21 J EF ANGLE, INST PNL ALL 373-924110-23 H EF RACK, TJ BLOCK ALL NX311-10003 A EF.04 ASSY, NUTPLATE SPACER RK-1 THRU RK-999 NX311-10003.01 A EF.04 PLATE, NUTPLATE SPACER RK-1 THRU RK-999 NX311-10004 A EF MOD, AFD-3010 ALL [SSN REDACTED] F INST PNL INSTL ALL [SSN REDACTED] C SPEED SWITCH ASSY ALL [SSN REDACTED] D SPEED SWITCH FAB ALL 373.93.1511.9 IR IASNS SWITCH OVERLAY ALL 373.94.2110 IR OVHD PNL MOD FAB ALL [SSN REDACTED] A OVHD PNL MOD ASSY & INSTL ALL [SSN REDACTED] D EF PEDESTAL EXT FAB ALL [SSN REDACTED] C EF PEDESTAL EXT ASSY ALL [SSN REDACTED] D EF PEDESTAL EXT INSTL ALL FWD PEDESTAL ALL [SSN REDACTED] IR MODIFICATION ALTERNATE ALL [SSN REDACTED] B EF GPS/STBY BATT SHELF INSTL ALTERNATE ALL [SSN REDACTED] A EF GPS/STBY BATT SHELF ASSY EF PLATE, PILOTS MIC ALL NX230-10001-03 JACK PNL NX311-10002.01 B EF WEDGE. INST PNL ALL EO 024-11 IR PITOT PROBE ALL. OPTIONAL. Page 10 of 17 SDNY_GM_02758155 SUBJECT TO PROTECTIVE ORDER PARAGRAPHS 7, 8, 9, 10, 15, and 17 EFTA_00245077 EFTA01261737 Nextant Aerospace LLC 355 Richmond Rd. Richmond Heights OH 44143 Report No.: [SSN REDACTED] Revision EF.13 Master Drawing List - Upgrade of Collins Proline 4 to 21 Avionics System in the Hawker Beech 400A Aircraft [SSN REDACTED] STANDBY BATTERY ALL IR EF CIRCUIT BREAKER INSTALLATION Table 1A should be used with both JT15D engine equipped aircraft: "fable IA Drawings applicable to Pratt & Whitney JT15D engine equipped aircraft only: Aircraft Applicability RK-48 AND BELOW RK-49 AND ABOVE RK-48 AND BELOW RK-49 AND ABOVE RK-48 AND BELOW RK-49 AND ABOVE RK-48 AND BELOW RK-49 AND ABOVE ALL Drawings Rev Issue Description [SSN REDACTED] [SSN REDACTED]-01 [SSN REDACTED] [SSN REDACTED]-01 [SSN REDACTED] 373.77-4003.01 [SSN REDACTED] 373.77-4004.01 [SSN REDACTED] [SSN REDACTED] B F A E B E IR IR W/O NO.1 DCU W/D NO.1 DCU W/D NO.2 OCU W/D NO.2 OCU W/D NO.1 EDC WAD NO.1 EDC W/D NO.2 EDC W/D NO.2 EDC CSU-4100 STRAPPING OIL PRESS. TRANS. INSTL ALL Page 11 of 17 SDNY_GM_02758156 SUBJECT TO PROTECTIVE ORDER PARAGRAPHS 7, 8, 9, 10, 15, and 17 EFTA 00245078 EFTA01261738 Nextant Aerospace LLC 355 Richmond Rd. Richmond Heights OH 44143 Report No.: [SSN REDACTED] Revision EF.13 Master Drawino List — Upgrade of Collins Proline 4 to 21 Avionics System in the Hawker Beech 400A Aircraft For any installation including optional installation TCAS II the following drawings in Table 2 should be used in addition to the drawings included in the base installation and any other optional installations: Table 2 Drawings Wiring Diagrams Rev Description Aircraft applicability [SSN REDACTED] F EF.02 WID TCAS RK-48 AND BELOW 37334-4510.01 B EF.02 W/D1CAS RK-49 AND ABOVE [SSN REDACTED] EF W/D TCAS INT (TTR-920 ALL OR TTR-4000) [SSN REDACTED] E W/D NO.1 TOR RK-48 AND BELOW [SSN REDACTED]-01 B W/D NO.1 TOR RK-49 AND ABOVE [SSN REDACTED] E W/D NO.2 TDR ALL Structural Drawings [SSN REDACTED] IR EF.02 TCAS INSTURELOCATE ALL [SSN REDACTED] 2 ANTENNA FAB ALL [SSN REDACTED] ANTENNA INSTL ALL For any installation including optional installation XM satellite receiver the following drawings in Table 3 should be used in addition to the drawings included in the base installation and any other optional installations: Drawings Wiring Diagrams [SSN REDACTED] Structural Drawings [SSN REDACTED] [SSN REDACTED] Table 3 Rev Description G EF.12 W/D XM SAT REC • ANTENNA FAB E 2 ANTENNA INSTL Aircraft applicability ALL [repeated 3 times] For any installation including optional installation Single or Dual IFIS-5000 the following drawings in Table 4 should be used in addition to the drawings included in the base installation and any other optional installations: Drawings Wiring Diagrams [SSN REDACTED] 373.46-2001.01 [SSN REDACTED] [SSN REDACTED]-01 Table 4 Rev Description EF.12 E WID NO.1 FSU W/0 NO.1 FSU W/D NO.2 FSU W/D NO.2 FSU Aircraft applicability RK-48 AND BELOW RK-49 AND AFTER RK-48 AND BELOW RK-49 AND ABOVE For any installation including optional installation of #2 MFD the following drawings in Table 5 should be used in addition to the drawings included in the base installation and any other optional installations: Drawings Wiring Diagrams [SSN REDACTED] [SSN REDACTED]-01 373-34.2002 E Rev J E Table 5 Description • W/D 2MFD • W/D 2MFD W/D NO.2 CCP Aircraft applicability RK-48 AND BELOW RK-49 AND ABOVE ALL Page 12 of 17 SDNY_GM_02758157 SUBJECT TO PROTECTIVE ORDER PARAGRAPHS 7, 8, 9, 10, 15, and 17 EFTA_00245079 EFTA01261739 Nextant Aerospace LLC 355 Richmond Rd. Richmond Heights OH 44143 Report No.: [SSN REDACTED] Revision EF.13 Master Orawino List- Upgrade of Collins Prolific 4 to 21 Avionics System in the Hawker Beech 400A Aircraft For any installation upgrading the existing AHS-85E Attitude Heading Reference System (AHRS) to Collins AHS-3000A per Collins STC ST02173LA in conjunction with this SIC the following drawings in Table 6 should be used in addition to the drawings included in the base installation and any other optional installations: Table 6 Issue Aircraft Drawings Rev Description applicability Wiring Diagrams [SSN REDACTED] W/D NO.1 AHC RK-48 AND BELOW 373.34.2003.01 B W/D NO.1 AHC RK-49 AND ABOVE 373.34.2004 W/D NO.2 AHC RK-48 AND BELOW [SSN REDACTED]-01 B W/D NO.2 AHC RK-49 AND ABOVE For any installation upgrading the existing Collins RTA-444 Radar to Collins RTA-854 Turbulence Detection Radar per Collins STC ST01474WI-D in conjunction with this STC the following drawings in Table 7 should be used in addition to the drawings included in the base installation and any other optional installations: Drawings Wiring Diagrams 37334.4801 Rev C Issue Table 7 Description W/D WX RADAR Aircraft applicability ALL For any aircraft equipped with Williams FJ44-3AP Engines installed under STC ST02371LA the following drawings in Table 8 should be used. Table 8 drawings should be used in addition to the drawings included in the Table 1 and any other optional installations: NOTE: The below design data in Table 8 is approved for use with Collins Proline 21 AFD.3010(E) MR 8.2 software only. This software is defined as AFD-3010 part number 822-1084-416 and AFD-3010E part number 822.1753-416 only. The below design data in Table 8 is approved for use with Collins Proline 21 DCU-3001C V7.0 software only. This software is defined as DCU-3001C part number 822.2362-003. The below design data in Table 8 is approved for use with Collins Prolino 21 IOC-4100 MR V8.0 software only. This software is defined as IOC-4100 part number 822.1362-511. Table 8 Drawings Rev Issue Description Aircraft applicability Wiring Diagrams [SSN REDACTED] F W/D LH FADEC INT. AND NO. 1 RK-48 AND BELOW EF DCU [SSN REDACTED]-01 K W/D LH FADEC INT. AND NO. 1 RK-49 AND ABOVE EF DCU [SSN REDACTED] E W/D RH FADEC INT. AND NO.2 DCU RK-48 AND BELOW [SSN REDACTED]-01 L EF.11 W/D RH FADEC INT. AND NO. 2 DCU RK-49 AND ABOVE [SSN REDACTED] F W/D NO.1 PFD TO FADEC INTERFACE ALL [SSN REDACTED] F W/D NO.1 MFD TO FADEC INTERFACE ALL Page 13 of 17 SDNY_GM_02758158 SUBJECT TO PROTECTIVE ORDER PARAGRAPHS 7, 8, 9, 10, 15, and 17 EFTA 00245080 EFTA01261740 Nextant Aerospace LLC 355 Richmond Rd. Richmond Heights OH 44143 Report No.: 373-00-00O1 Revision EF.13 Master Drawing List — Upgrade of Collins Proline 4 to 21 Avionics System in the Hawker Beech 400A Aircraft Table 8 (Continued) Drawings Rev Issue Description Aircraft applicability Wiring Diagrams [SSN REDACTED] W/D NO.2 PFD TO FADEC INTERFACE ALL 373-42 0001 A CSU.4100 STRAPPING ALL 373.34.2545 F Z WiD NO.2 MFD TO FADEC INTERFACE ALL As an option the remaining existing avionics wiring replacement may be done IAW the drawings listed below in Table 9. Table 9 Drawings Rev Issue Description Aircraft applicability Wiring Diagrams [SSN REDACTED] O W/D NO.1 MSP ALL [SSN REDACTED] D W/D NO.2 MSP ALL 373.22.1200 E W/D APP RK-048 AND BELOW [SSN REDACTED]-01 ID EF.01 W/D APP RK-049 AND ABOVE [SSN REDACTED] O EF W/D SPEED SWITCH ALL [SSN REDACTED] F EF W/D NO.1 VHF ALL [SSN REDACTED] E EF W/D NO.2 VHF ALL 373.23.5001 I EF.08 W/D AUD RK-48 AND BELOW [SSN REDACTED]-01 H EF.08 W/D AUD RK-49 AND ABOVE 373.23.6000 D Z W/D ELT ALL 373.25.1301 D W/D NO 1 CLOCK RK-48 AND BELOW [SSN REDACTED]-01 B W/D NO 1 CLOCK RK-49 AND ABOVE [SSN REDACTED] E Z W/D NO 2 CLOCK RK-48 AND BELOW [SSN REDACTED]-01 C Z W/D NO 2 CLOCK RK-49 AND ABOVE 373.34.1111 G EF W/D NO.1 ADC RK-48 AND BELOW 373.34-1111-01 E EF W/D NO.1 ADC RK-49 AND ABOVE [SSN REDACTED] E EF W/D NO.2 ADC RK-48 AND BELOW 373.34-1112-01 E EF W/D NO.2 ADC RK-49 AND ABOVE 373-34.3001 E W/D NO.1 VIR ALL [SSN REDACTED] E W/D NO.2 VIR ALL [SSN REDACTED] F EF W/D RADIO ALT ALL [SSN REDACTED] G EF W/D TAWS 8000 RK-48 AND BELOW [SSN REDACTED]-01 G EF W/D TAWS 8000 RK-49 AND ABOVE 373.34-4501 D W/D NO.1 DME ALL 373.34-4502 D W/D NO.2 DME ALL [SSN REDACTED] H EF W/D NO.1 GPS RK-48 AND BELOW [SSN REDACTED] H EF W/D NO.2 GPS ALL 373-34.5021 E EF.01 W/D NO.1 ADF ALL 373-34.5022 E EF 06 W/D NO.2 ADF ALL [SSN REDACTED] E Y W/D NO.1 RTU RK-48 AND BELOW [SSN REDACTED] E EF W/D DATA BASE ALL Page 14 of 17 SDNY_GM_02758159 SUBJECT TO PROTECTIVE ORDER PARAGRAPHS 7, 8, 9, 10, 15, and 17 EFTA 00245081 EFTA01261741 Nextant Aerospace LLC 3.55 Richmond Rd. Richmond Heights OH 44143 Report No.: [SSN REDACTED] Revision EF.13 Master Drawino List — Upgrade of Collins Proline 4 to 21 Avionics System in the Hawker Beech 400A Aircraft Table 9 (Continued) Drawings Rev Issue Description Aircraft applicability Wiring Diagrams [SSN REDACTED].01 E EF W/D NO.1 RTU RK-49 AND ABOVE 373-39.1202 D W/D NO.2 RTU RK-48 AND BELOW 373-39.1202.01 E EF W/D NO.2 RTU RK-49 AND ABOVE 73-394GQ1 D W/D DAU P&W JT15D aircraft only. RK-48 AND BELOW [SSN REDACTED].01 A W/D DAU P&W JT15D aircraft only. RK-49 AND ABOVE [SSN REDACTED] F EF W/D IAPS LPI ALL [SSN REDACTED] G EF.13 W/D IAPS LP2 RK-48 AND BELOW 373-42.1002-01 G EF.13 W/D IAPS LP2 RK-49 AND ABOVE 373.42.1003 0 W/D IAPS LP3 ALL [SSN REDACTED] F W/D IAPS LP4 ALL [SSN REDACTED] E WID IAPS RP1 ALL [SSN REDACTED] G EF.13 W/D IAPS RP2 RK-48 AND BELOW [SSN REDACTED]-01 D EF.13 W/D IAPS RP2 RK-49 AND ABOVE [SSN REDACTED] D W/D IAPS RP3 RK-48 AND BELOW [SSN REDACTED]-01 W/D IAPS RP3 RK-49 AND ABOVE [SSN REDACTED] F W/D IAPS RP4 ALL 373-34.6001 G EF W/D NO.1 CDU ALL [SSN REDACTED] H EF W/D NO.2 CDU ALL For installation Universal Avionics TAWS A in conjunction with this STC the following drawings in Table 10 should be used in addition to the drawings included in the base installation and any other optional installations: Drawings Wiring Diagrams [SSN REDACTED] 373-91.3446 Structural Drawings 373-91.6000 Rev O IR A Table 10 Issue Description Aircraft applicability EF W/D Universal TAWS . ALL TAWS Wire Routing Diagram ALL TAWS Installation For FMS-6100 WAAS/LPV Approach capability in conjunction with this STC the following drawings in Table 11 should be used in addition to the drawings included in the base instaNation and any other optional installations: Drawings Wiring Diagrams [SSN REDACTED] [SSN REDACTED] Table 11 Rev Issue Description Z No. 1 FMS-6100 WAAS LPV Upgrade B Z No. 2 FMS-6100 WAAS LPV Upgrade Aircraft applicability ALL ALL Page 15 of 17 SDNY_GM_02758160 SUBJECT TO PROTECTIVE ORDER PARAGRAPHS 7, 8, 9, 10, 15, and 17 EFTA_00245082 EFTA01261742 Nextant Aerospace LW 355 Richmond Rd. Richmond Heights OH 44143 Report No.: [SSN REDACTED] Revision EF.13 Master Drawino List — Upgrade of Collins Proline 4 to 21 Avionics System in the Hawker Beech 400A Aircraft For Installation new Glareshield Annunciators In conjunction with this STC the following drawings In Table 12 should be used in addition to the drawings included in the base installation and any other optional installations: Drawings Rev Issue Table 12 Description Aircraft applicability Wiring Diagrams CC Glareshield Annunciators Wiring ALL [SSN REDACTED] Diagram Structural Drawings NX110-10004 A EF.09 Glareshield Reg. No Placard ALL NX110-10005 G EF.10 Engine Fire Placard ALL NX316-10001 C EF.09 Assy, Glareshield, New Design ALL N (D) NX316-10001-01 C EF.09 Glareshield. (ND) ALL NX316-10001-02 B Z Glareshield Main Support ALL NX316-10001-03 IR Z Strap, Glareshield. Upper ALL NX316-10001-04 IR Z Strap, Glareshield. (ND), Lower ALL NX316-10001.05 IR Z Shim, New Glareshield, Top Side Arm, LH ALL NX316-10001.06 IR Z Shim, Glareshield, ND, Lower ALL Shim, New Glareshield, Top Side ALL NX316-10001-07 IR Z Arm, RH NX315-10005 IR EF Placard. Eng Fire Bell Switch ALL For installation Midcontinent Instruments MD-302 in conjunction with this STC the following drawings in Table 13 should be used in addition to the drawings included in the base installation and any other optional installations: Table 13 Drawings Rev Issue Description Aircraft applicability Wiring Diagrams [SSN REDACTED] C OD MD302 Standby Instrument Wiring Diagram ALL Structural Drawings NX312-1211009 A DD MD302 Installation with PitotlStatic Lines Retrofit ALL Page 16 of 17 SDNY_GM_02758161 SUBJECT TO PROTECTIVE ORDER PARAGRAPHS 7, 8, 9, 10, 15, and 17 EFTA_00245083 EFTA01261743 Nextant Aerospace LLC 355 Richmond Rd. Richmond Heights OH 44143 Report No.: [SSN REDACTED] Revision EF.13 Master Drawino List— Upgrade of Collins Proline 4 to 21 Avionics System in the Hawker Beech 400A Aircraft Supporting Data Aircraft Drawings Rev Issue Description applicability Wiring Diagrams [SSN REDACTED] A WO Fuel Quantity Cal Box ALL 373.28.6002 IR WM Fuel Quantity Test Box ALL Software Accomplishment Summary Aro- FJ44-3AP 815-2680-011 A 3010(E) Equipped Aircraft Only Software Configuration Index FJ44-3AP 815-2684-024 A AFO-3010(E) Equipped Aircraft Only Software Accomplishment Summary IOC- FJ44-3AP 832-5125-511 4100 Equipped Aircraft Only Software Configuration Index FJ44-3AP B18-6437-511 IOO-4100 Equipped Aircraft Only Software Accomplishment Summary DCU- FJ44-3AP 963-4655-003 3001C Equipped Aircraft Only Software Configuration Index FJ44-3AP 963-4657-003 DCU-3001C Equipped Aircraft Only PT-[SSN REDACTED] C EF.03 PRODUCTION, GROUND TEST PROCEDURE (PROLINE 21 UPGRADE) ALL PT-[SSN REDACTED] B EF PRODUCTION, GROUND TEST PROCEDURE (EIS) ALL Page 17 of 17 SDNY_GM_02758162 SUBJECT TO PROTECTIVE ORDER PARAGRAPHS 7, 8, 9, 10, 15, and 17 E 00245084 EFTA01261744 SDNY_GM_02758163 SUBJECT TO PROTECTIVE ORDER PARAGRAPHS 7, 8, 9, 10, 15, and 17 EFTA 00245085 EFTA01261745 U.S OEPAFITNENT OF TRANSPORTATION FEDERAL AVIATION AOUINISTRATION STATEMENT OF COMPLIANCE WITH AIRWORTHINESS STANDARDS 1. DATE March 4. 2015 AIRCRAFT OR AIRCRAFT COMPONENT IDENTIFICATION 2. FLAKE Beechcraft Corporation 3 MODEL NO. 400A 4. TYPE (AAVAIR. Engine. Pgairer. NC) Aircraft 5 NAME OF APPLICANT Constant Aviation LIST OF DATA 6 IDFNTFICATION 7 TIRE CA-E0-0315-02 Rev. IR March 4. 2015 NX311-10010 Rev. IR February 20. 2015 LH FWD Circuit Breaker Panel Fabrication. Install. MD-302 STBY Instrument Upgrade. END Notes: 1) The structural aspects only of the above listed data are approved herein. This approval is only for the engineering data. N indicates the data listed above demonstrates compliance only with the regulations specified by paragraph and subparagraph listed 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. S. PURPOSE OF DATA: Engineering data in support of major alteration to Beechcraft 400A, SIN RK-260. co APPuCABLE REOUIREMENTS (List 4;604 amino's) CFR 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 authorey Pan 153. data Nilel stone end On spots* novo ensue a the Alivaltinea K Recommend num by damn a ir* Aernnetraior end in aocadanco will cannibals aid linillidions or ap/Xentn•N uncle% 14 CFR need SIIIRLI nurnbilte0 S&. MO Me tornand n aCCOonanCe wit 100:41111401 prOCOOtaroe Nor lout 10 comply win Stesidardi LIS160. approval of these data these data I (We) Therefore k: Approve II. SIGNATURE(S) OF DESIGNATED ENGINEERING REPRESENTATIVES) 12. DESIGNATION NUMEERSIS1 IS CLASS7FICATIONIS/ oire.-.0" Paul Hedding DERT-410115-CE Structures FAA Form 8110-3 (03-10) SUPERSEDES PRE1nOuS Eornot. Fs! Niareer. NiSMOdi Page loll SDNY_GM_02758164 SUBJECT TO PROTECTIVE ORDER PARAGRAPHS 7, 8, 9, 10, 15, and 17 EFTA 00245086 EFTA01261746 SDNY_GM_02758165 SUBJECT TO PROTECTIVE ORDER PARAGRAPHS 7, 8, 9, 10, 15, and 17 EFTA 00245087 EFTA01261747 AIR SERVICES ENGINEERING ORDER CA-EO-0315-02 REVIR Model- Nextant 400XT P/N: N/A Title: LH FWD Circuit Breaker Panel Fabrication • Drawing(s) N995801 Tail-Serial Numbe Number(s):N727KG - RK-260 DESCRIPTION The purpose of this Engineering Order is to add proper labeling for the circuit breaker panel on the Avionics Bus. Current circuit breaker panel is not properly labeled. I Remove Circuit Breaker plug at location shown on page 2. 2. Create Blue circle around location called out on page 2. 3. Label Circuit Breaker Panel With ADVISORY PNL above the location. Follow drawing N995801 for text sizing and color. APPROVALS CREATED BY: A Howard DATE: 03/04/2015 VED BY: P APRO p Buzz DATE: 03/04/2015 CHECKED BY: C. Blackwell DATE: 03/04/2015 FM APPROVAL REQUIRED? YES 0 NO O Change:MAJOR 0 MINOR O Page 1 of 2 This document Is electronkally controlled, once printed It is uncontrolled [email protected] • [PHONE REDACTED] • www.airservicesusa.com Composites • Accessories • NDT • Engineering SDNY_GM_02758166 SUBJECT TO PROTECTIVE ORDER PARAGRAPHS 7, 8, 9, 10, 15, and 17 EFTA 00245088 EFTA01261748 SDNY_GM_02758167 SUBJECT TO PROTECTIVE ORDER PARAGRAPHS 7, 8, 9, 10, 15, and 17 EFTA 00245089 EFTA01261749 CO n 0 T m C 0 cAi 0 -4 9° I-1 CA P N to CL) 0605n00vi.n 0 3 0 • OO0 z 12. • rn 10 3 3 a) 3 10 1110.TOSI1S831AJeSJIIXMMM Aricjit ar • .. 44 a I • I • I • 4-, 1 • It 1 -• • . g lb." rr...• MO , IR ° I M O i ll" tit area tau vs 'Niro WU wan si)„ rdg cle so Ns ti i‘l 1/4... ‘. .) .OOOOOOOO ..--O--.); 1 0 am rams ... r - Vral I ea a ale lire a an a ref i t"' IOU 2 . 5.10 Wen 1 AT r140 Teen e. tale. Ian In) Illy LIM` cgs I 'I' FEN ,ett•— €2*,&" Le Imo S3:NOIAo CDC)00® ® ® au le Win fon, 0=3 OW Sf1 001 sae aZO 1:C Ina On IS Wu 00111 311.1 Ale SAWA —4-- NI 0:Cre. Nlyy I Al• kranarf COW MU MA 1.141 LVEI 10,0 dr, OOO • W XI • an n I 003 in f OOOOOO ra I n I Ca I Cu r s 11.911 1:174 • t3 13rti 9113 MU and ( Kt 110 1Q . ' t 4:0 na4 Nal' CI tru 4 Na 1NO3 on 3Ai t/ ISNI 9N3 cid EFTA01261750 SDNY_GM_02758169 SUBJECT TO PROTECTIVE ORDER PARAGRAPHS 7, 8, 9, 10, 15, and 17 EFTA 00245091 EFTA01261751 Nextant Aerospace LLC 355 Richmond Rd. Richmond Heights OH 44143 Report No.: 373.00-0055 Revision B Instructions For Continued Airworthiness Midcontinent Instruments MD-302 Standby Attitude Module (SAM) Hawker/Beechcraft 400A Aircraft These instructions must be attached to the approved Airplane Maintenance Manual when a Midcontinent Instruments MD-302 Standby Attitude Module is installed in accordance with SIC ST10959SC. The information contained herein supplements or supersedes the basic Airplane Maintenance Manual only in those areas listed herein. For limitations, procedures, and performance information not contained in this supplement, consult the basic Airplane Maintenance Manual. Accepted By Nextant Aerospace Date 1-18-2013 I of 20 SDNY_GM_02758170 SUBJECT TO PROTECTIVE ORDER PARAGRAPHS 7, 8, 9, 10, 15, and 17 EFTA_00245092 EFTA01261752 Nextant Aerospace LLC 355 Richmond Rd. Richmond Heights OH 44143 LOG OF REVISIONS Report No.: 373.00-0055 Revision B REV PACES DESCRIPTION ACCEPTED BY DATE IR All Initial Release Nextant Aerospace 3.25.13 A 4.5 Deleted MD302 Internal Battery Nextant Aerospace 7-1-13 B All Removed additional reference to MD-302 Internal battery. Removed remote barn-set function and Mach readout test as they are no longer available. Nextant Aerospace 11-18-13 2 of 20 SDNY_GM_02758171 SUBJECT TO PROTECTIVE ORDER PARAGRAPHS 7, 8, 9, 10, 15, and 17 EFTA 00245093 EFTA01261753 Nextant Aerospace LLC 355 Richmond Rd. Richmond Heights OH 44143 Report No.: [SSN REDACTED] Revision B TABLE OF CONTENTS 1.0 Introduction 4 2.0 System Description 4 3.0 Control/Special Procedures 4 40 Servicing 5.0 Maintenance 5 6.0 Troubleshooting 6 7.0 Removal and Replacement 10 8.0 Diagrams 11 9.0 Special Inspections 12 10.0 Protective Treatments 12 11.0 Fasteners 12 12.0 Special Tools 12 13.0 Commuter 12 14.0 Overhaul 12 15.0 Airworthiness Limitations 12 16.0 Revisions 12 Appendix A, Applicable Drawings Appendix B, MD-302 Ground Test 3 of 20 SDNY_GM_02758172 SUBJECT TO PROTECTIVE ORDER PARAGRAPHS 7, 8, 9, 10, 15, and 17 EFTA 00245094 EFTA01261754 Mutant Aerospace LLC 355 Richmond Rd. Richmond Heights OH 44143 1.0 Introduction Report No.: [SSN REDACTED] Revision B This document is applicable to the Beech 400A Airplanes, modified by the installation of the Midcontinent Instruments MD-302 Standby Attitude Module (SAM) in accordance with this STC. This document complies with the requirements of 14 CFR Pan 25.1529, ICA. These Maintenance Requirements and Instructions for Continuous Airworthiness (ICA) pertain to the installation of MD-302 Standby Attitude Module (SAM). Modification of an aircraft by this Supplemental Type Certificate obligates the aircraft operator to include the maintenance information provided by this document in the operator's Aircraft Maintenance Manual and the operator's Aircraft Scheduled Maintenance Program. 2.0 System Description The model MD302 series Standby Attitude Module is a self-contained situational awareness instrument that provides aircraft attitude, altitude, airspeed and slip indication. The MD-302 will replace the three existing clectro-mcchanical 2" Standby Attitude, Altimeter, and Airspeed. The MD302 design is built around a solid-state electronic sensor array for high reliability. The dual, high- resolution LCD display uses smooth graphics, daylight•readable brightness, and a configurable lighting response curve to ensure optimal visibility in all conditions. The MD302 will be supplied emergency backup power by a dedicated existing Standby Emergency Battery. With this backup the MD-302 system meets the operational requirements for aircraft with all electronic instruments. SYSTEM COMPONENTS The system consists of the following components: MD-302 Standby Attitude Module (SAM) Existing Standby Battery ARM/ON Annunciator Switch MD-302 IS protected by the following circuit breaker: C/B Name Amps Location STBY ATT MD 2 LH FWD CB Panel BUS Standby Bat Bus 3.0 Control/Special Procedures Normal operating procedures are identified in the MD-302 Standby Attitude Module (SAM) Installation and Operating Manual, publication number 9017782 Section 3. 4.0 Servicing — There is no required servicing of systems installed under this STC. 4 of 20 SDNY_GM_02758173 SUBJECT TO PROTECTIVE ORDER PARAGRAPHS 7, 8, 9, 10, 15, and 17 EFTA 00245095 EFTA01261755 Nextant Aerospace LLC 355 Richmond Rd. Richmond Heights OH 44143 5.0 Maintenance Report No.: 373.00-0055 Revision B Maintenance should be referred to person or facility certificated to perform the work being accomplished. The following manuals contain complete detailed maintenance instructions and should be consulted for all maintenance activities not covered within this ICA: MD-302 Standby Attitude Module (SAM) Installation and Operating Manual, publication number 9017782 A. Scheduled Inspections and-Maintenance Wire/Cable/Racks/Connectors Inspect system installation components including wires bundles, cables, racks, and connector condition and security in conjunction with "B" Check (Every 400 hours after initial 200 hour "I" inspection) tasks and "C" check (Every 1200 hours after initial 200 hour "I" inspection) per Hawker Beechjet 8400 Maintenance Manual 5.20.02 requirements as listed within Scheduled Inspections Section RK-I and above. PRESSURE SYSTEM AND ALTIMETER VERIFICATION Per federal regulation 14 CFR 91.41I, it is required that each static pressure system and each altimeter have been tested and inspected within the last twenty-four (24) calendar months. MD-302 Configuration The configuration module contains the system configuration as certified under this STC. If the configuration module fails or the configuration is lost the new configuration module must be reconfigured per Nextant Aerospace Ground Test located in Appendix B. 6.0 Troubleshooting Maintenance and troubleshooting should be referred to person or facility certificated to perform the work being accomplished. When troubleshooting the system, reference: Appendix A, Electrical Drawing List. MD-302 Standby Attitude Module (SAM) Installation and Operating Manual, publication number 9017782, Section 5. 5 of 20 SDNY_GM_02758174 SUBJECT TO PROTECTIVE ORDER PARAGRAPHS 7, 8, 9, 10, 15, and 17 EFTA 00245096 EFTA01261756 Nextant Aerospace LLC 355 Richmond Rd. Richmond Heights OH 44143 Report No.: [SSN REDACTED] Revision B The following Figures and ace riated descriptions represent warnings or errors and describe the typical reasons and appropriate response action. FIGURE 6.1 The attitude display has failed due to exceedance of internal rate sensors, loss of airspeed or other various reasons. This will typically self-correct. However, if it does not, immediately have the unit serviced. FIGURE 6.2 The altimeter instrument has failed, possibly due to exceedance of the pressure sensor range. This may self- correct, but if the error persists, immediately have the unit serviced. FIGURE 6.3 The airspeed instrument has failed, possibly due to exceedance of the pressure sensor range. This may self- correct, but if the error persists, immediately have the unit serviced. 6 of 20 SDNY_GM_02758175 SUBJECT TO PROTECTIVE ORDER PARAGRAPHS 7, 8, 9, 10, 15, and 17 EFTA_00245097 EFTA01261757 Nextant Aerospace LLC 355 Richmond Rd. Richmond Heights OH 04143 Report No.: [SSN REDACTED] Revision B FIGURE 6.4 The airspeed and altimeter display have both failed due to exceedance of their respective sensor ranges. This may self-correct, but if the error persists, service unit immediately. FIGURE 6.5 This message is displayed when power is removed at low airspeed (typical ground condition). The pilot has 60 seconds to confirm to remain on, otherwise the unit will automatically power off to conserve battery. 11111011tWA/0/1 IMP SDI/131 ilC0104 FIGURE 6.6 The configuration module has failed or is not installed properly. Internal settings will be used. If the configuration module is installed, it should be serviced immediately. "NINO camsemsas I uocsitastio !meanie 1 wars, conwoes FIGURE 6.7 Internal failure. Service unit immediately. 7 of 20 SDNY_GM_02758176 SUBJECT TO PROTECTIVE ORDER PARAGRAPHS 7, 8, 9, 10, 15, and 17 EFTA 00245098 EFTA01261758 Nestant Aerospace LUC 355 Richmond Rd. Richmond Heights OH 44143 FIGURE 6.8 Internal failure. Service unit immediately. FIGURE 6 9 Report No.: [SSN REDACTED] Revision B Internal (unit) and external settings (configuration module) failure. It is unlikely that both settings would be lost. Try to reconfigure the unit. Service unit if this error persists. FIGURE 6.10 Internal (unit) settings were found to be invalid. The configuration module settings will be copied to internal memory. Service unit if this error persists. FIGURE 6.11 External settings (configuration module) were found to be invalid. The internal settings will be copied to the configuration module memory. Service unit if this error persists. FIGURE 6.12 Internal (unit) and external (configuration module) settings were found to be different. This is typically the result of replacing a unit in an existing installation. The external settings will be copied to replace the settings in internal memory. *I I eldIall100141 1 h rotintIllIXOCt own Of Dann t41.1.01,1106A1 8 of 20 SDNY_GM_02758177 SUBJECT TO PROTECTIVE ORDER PARAGRAPHS 7, 8, 9, 10, 15, and 17 EFTA_00245099 EFTA01261759 Nextant Aerospace LLC 355 Richmond Rd. Richmond Heights OH 44143 Report No.: [SSN REDACTED] Revision II FIGURE 6.13 In configuration mode, this may be the result of lost settings both internally and externally. Try to configure the unit. Seek service if error persists. I •,-; I 1 411:441CO•LOn.31 SUSI* OP We .41.61WILL IC Hi 0 HI. ianet• wa NG /IMAgt FIGURE 6.14 In configuration mode, this may be the result of lost settings and a failure to initialize memory. Try to restart and configure the unit. Seek service if error persists. FIGURE 6.15 Internal (unit) and external (configuration module) settings were found to be different. This is typically the result of replacing a unit in an existing installation. In configuration mode, this choice allows selection of which settings to use. All other discrete inputs and suspected wiring faults should be isolated using basic troubleshooting procedures and the wiring diagrams identified in Appendix A. 9 of 20 SDNY_GM_02758178 SUBJECT TO PROTECTIVE ORDER PARAGRAPHS 7, 8, 9, 10, 15, and 17 EFTA_00245 I 00 EFTA01261760 Nextant Aerospace LLC 355 Richmond Rd. Richmond Heights OH 44143 Report No.: [SSN REDACTED] Revision B 7.0 Removal and Replacement NOTE: Properly protect aircraft electrical connectors if unit is to be removed for extended period of time. MD-302 (Center Instrument Panel) Removal of MD-302: a. Remove Electrical Power from Aircraft.. 12._lientoYe 4 mountingscrews_fromMD-302 c. Slide out unit from panel and disconnect electrical connector and pitot static lines. Installation of MD-302. a. Secure electrical connector and pitot static lines. b. Install MD-302 with four mounting screws. c. Apply aircraft power and verify MD-302 powers up and no flags in view. Perform ftinction and pitot static system leak tests per Appendix B Section II. MD-302 Configuration Module (MD-302 Sub-D Connector) NOTE: The Configuration Module PC Board Assembly contains sensitive electronics that can be damaged by electrostatic discharge (ESD). Appropriate precautions should be applied prior to handling this component. Removal of MD-302 Configuration Module: a. Remove Electrical Power from Aircraft.. b. Remove MD-302 as above. c. Remove top cover of MD-302 Sub-D connector. d. Using appropriate pin removal tool remove the 4 configuration module PC Board pins from the connector and remove module. Installation of MD-302 Configuration Module: (Refer to Figure 7-I on next page) a. Insert the pins of the Configuration Module PC Board Assembly (Item 3) into their corresponding locations as noted below using an appropriate pin insertion tool. b. The wires coming from the Configuration Module PC Board Assembly are marked as follows on the circuit board: WI, TP2, TP3, TP4. c. With the D-Sub oriented up (pin locations 1-5 on top), orient the Configuration Module PC Board Assembly with the electronic parts facing UP prior to pin insertion. d. Install each pin into the rear of the D-Sub connector as follows: • TPI = config return = pin IS • TP2 = config data = pin 14 • TP3 = config clock = pin 10 • TP4 = config power = pin 5 c. Install the D-Sub Backshell Spring (Item 5) as shown. f. Place the D-Sub Slide Lock (Item 6) over the D-Sub connector. g. Install the D-Sub connector with Slide Lock and cable harness attached into the Backshell (Item 9) and secure with (2) screws (Item 8). Verify that the Backshell Spring is between the Slide Lock and Backshell. Move the Slide Lock back and forth to verify free movement. 10 of 20 SDNY_GM_02758179 SUBJECT TO PROTECTIVE ORDER PARAGRAPHS 7, 8, 9, 10, 15, and 17 EFTA 00245101 EFTA01261761 Nextant Aerospace LLC 355 Richmond Rd. Richmond Heights OH 44143 Report No.: [SSN REDACTED] Revision B h. Route the aircraft wire harness bundle (excluding shield braids) between the two halves of the Cable Strain Relief Clamp (Item 7). The Clamp should be placed over the chafe protection installed in Step 2 (if used). i. Loosely connect the two halves of the Cable Strain Relief Clamp with (2) screws (Item 8). j. Place the Cable Strain Relief Clamp in the Backshell as shown. k. Bend the wires of the Configuration Module PC Board Assembly 180 degrees so that the PC Board has components facing down as s ho Bel careful not to p ace excess strain on the solder connections between the wires and the PC Board. I. Capture the Configuration Module PC Board Assembly into the Backshell by placing the Backshell Cover (Item 2) on top of the Backshell. m. Secure the Backshell Cover onto the Backshell using (2) Screws (Item 9). n. The completed assembly should look as shown. Verify that the Slide Lock operates freely and that no wires are pinched, nicked, or otherwise damaged. d. Reinstall MD-302 per the above procedure. e. Apply aircraft power and verify MD-302 powers up and no flags in view. Perform Configuration, Function Test, and pitot static system leak test per Appendix B. Figure 7-1 Configuration Module Assembly ••.• a. ••••• ...ow awes... s • nn "we Inx• wawa no. • • tae....... • • ow .....• a now.••••••• moos . • q.t.,. ... ra. c • • P.n. •Imsor toe lost••••••• 04. • inner••••a• oe.••••••••••.*•• r • • swede.. •••••••.samr..••••••••••• 'wain* 8.0 Diagrams The applicable drawings required to perform certain aspects of this ICA are contained in the aircraft drawing package provided to end user and listed in Appendix A. 11 of 20 SDNY_GM_02758180 SUBJECT TO PROTECTIVE ORDER PARAGRAPHS 7, 8, 9, 10, 15, and 17 EFTA_00245 102 EFTA01261762 Nextant Aerospace LLC 355 Richmond Rd. Richmond Heights OH 44143 9.0 Special Inspections — None 10.0 Protective Treatments — Not Applicable 11.0 Fasteners —Not Applicable 12.0 Special Tools— None 13.0 Commuter —Not Applicable Report No.: [SSN REDACTED] Revision B 14.0 Overhaul — Not Applicable 15.0 Airworthiness Limitations 15.1 The Airworthiness Limitations section is FAA approved and specifies maintenance required under §§43.16 and 91.403 of the Federal Aviation Regulations unless an alternative program has been FAA approved. No additional airworthiness limitations arc added to the aircraft maintenance procedures with this installation. 16.0 Revisions Should a revision be required, a letter will be submitted to the Aircraft Certification Office with a copy of the revised ICA. Once a revision is accepted, a copy of the revised ICA will be issued for subsequent installations. Revisions will be sent to operators of previously altered aircraft via US Mail based on STC Authorization Letter address. It is up to the aircraft operator to advise Nextant Aerospace of address changes or change of aircraft ownership. Nextant Aerospace Main Offices 26180 Curtiss-Wright Pkwy. Richmond Heights OH 44143 USA Phone 216.261.9000 Email: [email protected] WA& a of 20 SDNY_GM_02758181 SUBJECT TO PROTECTIVE ORDER PARAGRAPHS 7, 8, 9, 10, 15, and 17 EFTA_00245 103 EFTA01261763 Nextant Aerospace LLC 355 Richmond Rd. Richmond Heights OH 44143 APPENDIX A APPLICABLE WIRING DIAGRAMS Report No.: [SSN REDACTED] Revision B Drawing Number Titlo [SSN REDACTED] MD302 Standby Instrument Wiring Diagram 13 of 20 SDNY_GM_02758182 SUBJECT TO PROTECTIVE ORDER PARAGRAPHS 7, 8, 9, 10, 15, and 17 EFTA_00245104 EFTA01261764 Nextant Aerospace LLC 355 Richmond Rd. Richmond Heights OH 44143 Report No.: [SSN REDACTED] Revision B APPENDIX B Ground Test Procedure Midcontinent Instruments-MD.302-Standby-Attitude Module-- - TABLE OF CONTENTS Page 1. System Configuration 17 II. Ground Tests 18 14 of 20 SDNY_GM_02758183 SUBJECT TO PROTECTIVE ORDER PARAGRAPHS 7, 8, 9, 10, 15, and 17 EFTA_00245 I 05 EFTA01261765 Neatant Aerospace LLC 355 Richmond Rd. Richmond Heights OH 44143 I. SYSTEM CONFIGURATION Report No.: [SSN REDACTED] Revision B Configure the MD-302 in accordance with MD-302 Standby Attitude Module (SAM) Installation and Operating Manual, publication number 9017782, Section 4. System configuration shall be as follows: DISPLAY CONFIGURATION Roll Display Fixed Scale Airspeed Units Knots Display Orientation Vertical Left _DIMblING_CONFIGURATION_ Dimming Control EXT 5V Dimming Curve See Section 4.3.2 of above manual. Set as required to match existinfi flight displays. AIRCRAFT CONFIGURATION Panel Tilt I I degrees Range MMO .78M Range Markings None ARINC Speed High Speed 15 of 20 SDNY_GM_02758184 SUBJECT TO PROTECTIVE ORDER PARAGRAPHS 7, 8, 9, 10, 15, and 17 EFTA_00245 I 06 EFTA01261766 Nestant Aerospace LLC 355 Richmond Rd. Richmond Heights OH 44143 II. GROUND TEST Test Equipment Required Pitot Static test equipmentCal Date Initial Power-On Report No.: [SSN REDACTED] Revision B a. Assure that all avionics systems circuit breakers are set. b. Provide ground power to the aircraft and power all aircraft busses. c. Assure that all avionics arc activated and exhibit no failures or abnormalities. d. Verify flags pull from view on MD-302 after initialization is completed (Initialization lime may take several minutes). PASS/FAIL Liehtine And Accessibility a. While varying the center instrument panel lighting controls, verify lighting of the MD-302 is functioning. PASS/FALL 16 of 20 SDNY_GM_02758185 SUBJECT TO PROTECTIVE ORDER PARAGRAPHS 7, 8, 9, 10, 15, and 17 EFTA_00245 I 07 EFTA01261767 Neatens Aerospace LLC 355 Richmond Rd. Richmond Heights OH 40143 MD-302 Emereencv Battery Power Test Report No.: [SSN REDACTED] Revision B I. With normal 28 vdc electrical power to the airplane select the Standby Battery switch to ARM. Select cockpit annunciators BRT/DIM switch to BRT. Verify that STBY PWR and ARM annunciators illuminate. Confirm that the MD-302 is powered and with no flags in view. 2. Select aircraft BATTERY switch to OFF. Observe that emergency electrical power activates and that STBY PWR and ON annunciators illuminate. Verify the MD-302 is powered with no flags in view. 3. Select Standby Power Arm Switch to the OFF position (button released). Switch STBY PWR, ARM , and ON annunciators should be extinguished. 4. Apply normal 28 VDC electrical power to airplane, select the Standby Battery switch to ARM, and verify MD-302 is powered with no flags in view.. Pass Fail MD-302 Static Test I. Compare the MD-302 display with that of primary flight displays. a. Attitude will be * 0.5°. b. Airspeed indication will be minimum setting as configured. c. Altitude will indicate field elevation within ± 20 feet. (Ensure proper taro setting) Pass Fail 17 of 20 SDNY_GM_02758186 SUBJECT TO PROTECTIVE ORDER PARAGRAPHS 7, 8, 9, 10, 15, and 17 EFTA_00245 I 08 EFTA01261768 Nextant Aerospace LLC 355 Richmond Rd. Richmond Heights OH 44143 MD-302 Air Data Tests System Leak Test Report No.: [SSN REDACTED] Revision S I. Connect Pitot/Static test set to both Pitot/Static Systems. 2. Evacuate the static pressure system until a pressure differential equivalent to the maximum cabin pressure differential for which the airplane is type certificated is achieved (14,000 feet). Without additional pumping for a period oft minute, the loss of indicated altitude must not exceed 2 percent of the equivalent altitude of the maximum cabin differential pressure (280 feet). Pass Fail NOTE: The following accuracy tests are only required as part of the 24 month I4CRF 91.411 certification. Altitude Accuracy Connect Pitot/Static test set to both Pilot/Static Systems. Using following table verify accuracy of MD•302 Altimeter display. Note: The MD•302 does not contain a static error correction curve. At certain altitudes significant altitude differences from the primary aircraft displays and the MD•302 may occur. NOTE: All Tolerances arc + or -. Measurements in feet. Altitude Tester MD-302 Tolerance -1000 20 0 20 500 20 1000 20 1500 25 2000 30 3000 30 4000 35 6000 40 8000 60 10000 80 12000 90 14000 100 16000 110 18000 120 20000 130 22000 140 25000 155 30000 180 35000 205 40000 230 45000 255 50000 280 Continued next page 18 of 20 SDNY_GM_02758187 SUBJECT TO PROTECTIVE ORDER PARAGRAPHS 7, 8, 9, 10, 15, and 17 EFTA 00245109 EFTA01261769 Neatens Aerospace LLC 355 Richmond Rd. Richmond Heights OH 44143 Report No.: [SSN REDACTED] Revision B NOTE: Tests on this page and next page need to be conducted concurrently to assure hysteresis is within tolerance. Altitude Accuracy (Continued) Altitude Tester MD-302 Tolerance 45000 280 40011L. 230_ 35000 205 30000 180 25000 155 22000 140 20000 130 18000 120 16000 110 14000 100 12000 90 10000 80 8000 60 6000 40 4000 35 3000 30 _ 2000 30 1500 25 1000 20 500 20 0 20 -1000 20 NOTE: Assure all altitude readings are within tolerance. PASS Fail 19 of 20 SDNY_GM_02758188 SUBJECT TO PROTECTIVE ORDER PARAGRAPHS 7, 8, 9, 10, 15, and 17 EFTA_00245110 EFTA01261770 Sextant Aerospace LLC 355 Richmond Rd. Richmond Heights OH 44143 Airspeed/Mach Accuracy Set altitude at 5,000 ft. Set Speed as shown in chart and record data for items listed. SPEED Tester MD-302 50kts 75kts 100Icts I25kts I50kts I 75kts 200kts 225kts 250kts 275kts 300kts 325kts 350kts NOTE: Speeds must be within +/- 4 kts of test value Set altitude a 30,000 R. Report No.: [SSN REDACTED] Revision B ENO OF. REALM' I 20 of 20 SDNY_GM_02758189 SUBJECT TO PROTECTIVE ORDER PARAGRAPHS 7, 8, 9, 10, 15, and 17 EFTA_0024511I EFTA01261771 Nextant Aerospace LIS 355 Richmond Rd. Richmond Heights OH 44143 Document No.: [SSN REDACTED] Revision IR Hawker Beechaaft 400A FAA APPROVED AIRPLANE FLIGHT MANUAL SUPPLEMENT HAWKER BEECHCRAFT 400A Midcontinent Instruments MD-302 Standby Attitude Module (SAM) This Supplement must be attached to the Approved Airplane Flight Manual when the Midcontinent Instruments MD•302 Standby Attitude Module (SAM) is installed in accordance with STC ST10959SC and Nextant Aerospace Master Document List [SSN REDACTED]. The information contained herein supplements the information of the basic Airplane Flight Manual. For Limitations, Procedures and Performance information not contained in this Supplement, consult the basic Airplane Flight Manual. FAA APPROVED 113,-1) 4:°1 Steven L. Lardinois, Manager Systems and Flight Test Branch, ACE-117C Chicago Aircraft Certification Office 2300 E. Devon Ave. Des Plaines, IL 60018 FAA Central Region Date: DEC 16 2013 Title Page SDNY_GM_02758190 SUBJECT TO PROTECTIVE ORDER PARAGRAPHS 7, 8, 9, 10, 15, and 17 EFTA_00245 I 12 EFTA01261772 Nextant Aerospace LLC 355 Richmond Rd. Richmond Heights OH 44143 LOG OF REVISIONS Document No.: [SSN REDACTED] Revision IR Hawker Beechcraft 400A REV PAGES DESCRIPTIONS FAA APPROVED IR ALL Initial Release 5:. N. tia.....0 lov A“e-ii7c _Stevent Lardinoisaanager Systems and Flight Test Branch, ACE-117C Chicago Aircraft Certification Office 2300 E. Devon Ave. Des Plaines. IL 60018 FAA Central Region Date: DEC 16 2013 Page i SDNY_GM_02758191 SUBJECT TO PROTECTIVE ORDER PARAGRAPHS 7, 8, 9, 10, 15, and 17 EFTA_00245I 13 EFTA01261773 Nextant Aerospace LLC 355 Richmond Rd. Richmond Heights OH 44143 TABLE OF CONTENTS Document No.: [SSN REDACTED] Revision IR Hawker Beechcraft 400A SECTION DESCRIPTION PAGE 1 GENERAL 1 2 LIMITATIONS 1 3 EMERGENCY PROCEDURES 1 3A ABNORMAL PROCEDURES 2 4 NORMAL PROCEDURES 3 5 PERFORMANCE 7 6 WEIGHT AND BALANCE/EQUIPMENT 7 7 SUPPLEMENTS 7 FAA Approved Date: DEC 16 2013 Page ii SDNY_GM_02758192 SUBJECT TO PROTECTIVE ORDER PARAGRAPHS 7, 8, 9, 10, 15, and 17 EFTA 00245114 EFTA01261774 Nextant Aerospace LLC 355 Richmond Rd. Richmond Heights OH 44143 Document No.: 373.00-0048 Revision IR Hawker Beechcraft 400A SECTION 1 - GENERAL SYSTEM DESCRIPTION. The model MD302 series Standby Attitude Module is a self-contained situational awareness instrument that provides aircraft attitude, attitude, airspeed and slip indication. The MD302 design is built around a solid-state electronic sensor array for high reliability. The dual, high-resolution LCD display uses smooth graphics, daylight-readable brightness, and a configurable lighting response curve to ensure optimal visibility in all conditions. The MD302 will be supplied emergency backup power by a dedicated existing Standby Emergency Battery. With this backup the MD-302 system will meet the operational requirements for aircraft with all electronic instruments. SYSTEM COMPONENTS The system consists of the following components: MD-302 Standby Attitude Module (SAM) Existing Standby Battery ARM/ON Annunciator Switch MD-302 IS protected by the following circuit breaker: C/B Name Amps Location BUS STBY ATT IND 2 LH AFT CB Panel Standby Bat Bus SECTION 2 - OPERATING LIMITATIONS NO CHANGE TO AFM SECTION 3 - EMERGENCY PROCEDURES The MD302 is designed to operate reliably and provide the critical situational awareness needed even if the aircraft power systems fail. When this occurs, the unit provides emergency operation by continuing to perform seamlessly and uninterrupted in Flight Mode. When primary aircraft power to the unit is lost in flight, the unit will immediately begin operating on standby battery power. This is indicated by the STANDBY POWER ON annunciator illuminated. FAA Approved Date: DEC 16 2013 Pagel SDNY_GM_02758193 SUBJECT TO PROTECTIVE ORDER PARAGRAPHS 7, 8, 9, 10, 15, and 17 EFTA_00245 I 15 EFTA01261775 Nextant Aerospace LLC 355 Richmond Rd. Richmond Heights OH 44143 SECTION 3A - ABNORMAL PROCEDURES Document No.: 373.00.0048 Revision IR Hawker Beechcraft 400A The following indication may be shown during system failure: The attitude display has failed. Use remaining aircraft systems for navigation. The altimeter instrument has failed. Use remaining aircraft systems for altitude. The airspeed instrument has failed. Use remaining aircraft systems for airspeed. I 3 70t FM Approved Date: DEC 16 2013 Page 2 SDNY_GM_02758194 SUBJECT TO PROTECTIVE ORDER PARAGRAPHS 7, 8, 9, 10, 15, and 17 EFTA_00245 I 16 EFTA01261776 Nextant Aerospace LLC 355 Richmond Rd. Richmond Heights OH 44143 Document No.: 373.00.0048 Revision IR Hawker Beechcraft 400A SECTION 4- NORMAL PROCEDURES Pre-Flight Select Standby Power On using Standby Power ARM/ON switch. Perform Standby Power test per Airplane Fight Manual (AFM) Section 4. After power up verify MD-302 enters Flight Mode as shown below. Operation In Pre-flight Mode, power is applied to the unit and the Introduction Screen appears during startup. During Pre-flight Mode, the Introduction Screen will be displayed while the unit conducts an initial Power-up Built-in Test (P8IT) of the system to validate operational readiness. This includes, among others, an internal test to verify software and memory, and confirmation that the internal settings and identification of the unit match the Configuration Module installed in the aircraft cable harness. The Introduction Screen will be displayed for approximately five seconds and will transition to Flight Mode when complete. AllMidContinent' 'Er inivont. y..Y.ONRS SAKI MD302 SNV VERSION 1.0.1 RUN TAIE (NRs) 1704 MU/EIGHT MODE INTRODUCTION SCREEN In Flight Mode, the unit operates normally by displaying four major functions: Attitude, Altitude, Airspeed, and Slip Information FAA Approved Date: DEC 16 2013 Page 3 SDNY_GM_02758195 SUBJECT TO PROTECTIVE ORDER PARAGRAPHS 7, 8, 9, 10, 15, and 17 EFTA 00245117 EFTA01261777 Nextant Aerospace LLC 355 Richmond Rd. Richmond Heights OH 44143 Attitude Document No.: [SSN REDACTED] Revision IR Hawker Beechcraft 400A The Attitude Indicator consists of seven parts: Horizon Line, Sky (blue), Ground (brown), Symbolic Airplane, Roll Scale, Pitch Scale and Slip Indicator. The Roll Scale is depicted as an arc of graduations representing bank angles of 0° (triangle), 10°, 20°, 30°, 45° (small triangle) and 60°. The unit is operable and usable in a continuous and unlimited roll range of 360°+. The Roll Pointer is the triangle just below the Roll Scale and represents the aircraft in relation to its bank angle. It is configured to operate conversely to the Roll Scale behavior. That is, a fixed Roll Scale produces a rotating Roll Pointer. The Pitch Scale is depicted as a series of graduations representing pitch angles every 5°, with every 10° graduation being wider and numbered. The unit is operable and usable in a continuous and unlimited pitch range of 360°+. A series of chevrons (A) will appear overlaid on the Pitch Scale at attitudes greater than ± 45'. This is to indicate to the pilot the direction of the horizon for quick reference when in unusual pitch attitude. The chevrons always point toward the horizon line. FAA Approved Date: DEC 16 2013 ATTITUDE OPIAATIOTT m° asap desonsbatos W pick nine Sr WI TAM 144 °Y.,°.. pelf. I•— /SUIT% Is,•. Page 4 SDNY_GM_02758196 SUBJECT TO PROTECTIVE ORDER PARAGRAPHS 7, 8, 9, 10, 15, and 17 EFTA_00245I 18 EFTA01261778 Nextant Aerospace LLC 355 Richmond Rd. Richmond Heights OH 44143 Document No.: [SSN REDACTED] Revision IR Hawker BeechCraft 400A The Slip Indicator portion of the display will always appear at the bottom of the Attitude Display. The Slip Indicator is represented by a shaded translucent background with two white lines around center and a white ball. When the ball is maintained between the vertical lines during banking maneuvers, the turn is considered "coordinated' without slip. The Slip Indicator's background becomes semi-transparent if the Roll Scale or Roll Pointer pass behind the indicator. All other elements remain visible. Altitude The Altimeter consists of four pads: Altitude Window, Altitude Tape, Barometric Setting Window and optional Altitude Trend Bar. The Altitude Window displays the current, barometric corrected altitude. The digits of the display are in increments of ten and the window is expanded over this portion of the number to display a minimum spread of twenty units. The numbers will 'roll' or scroll to assist in quick reference to the increasing or decreasing nature of the aircraft's attitude. The hundreds, thousands and ten-thousands digits appear to the left of the tens digits with the thousands and ten-thousand digits slightly larger than the others. The Altitude Pointer (triangle) to the right of the window points to the associated position on the Altitude Tape of the current altitude. Attitude units of measure appear below the Altitude Window and can be changed during Flight Mode using the Options Menu. The pilot may select feet or meters. The Altitude Tape is a vertical scale along the right margin of the display. The current altitude is always in the middle of the tape and indicated by the Altitude Pointer on the right side of the Altitude Window. The tape has numeric indications every one-hundred units with minor graduations every fifty units and sub- graduations every twenty-five units. The tape will 'roll' or scroll to assist in quick reference to the increasing or decreasing nature of the aircraft's altitude. Pailude Temd lab. Wirt. Aidiod• TO/afkais • - 120 BARO r29 92 950C - —nn I— 75 2 0 i 0 2 [ 93,i oc W FEET i_. - -90 NTS 9200- - 80 All/ludo AWN* WO. of Wenn VAnteel1/44.• The Barometric Window shows the currently set barometric pressure. It is identified by the abbreviation BARO and is located at the top center of the Airspeed/Attitude Display. Setting the current barometric pressure compensates the altitude for the appropriate environmental conditions. FAA Approved Date: DEC 16 2013 Page 5 SDNY_GM_02758197 SUBJECT TO PROTECTIVE ORDER PARAGRAPHS 7, 8, 9, 10, 15, and 17 EFTA_002,15 I 19 EFTA01261779 Nextant Aerospace LLC 355 Richmond Rd. Richmond Heights OH 44143 Document No.: 373.00-0048 Revision IR Hawker Beechcraft 400A The barometric selling can be adjusted by turning the Control Knob while in Flight Mode. When adjusting the barometric pressure, the window will increase in size and the digits will turn green. When finished setting the pressure, the window will return to its original size and color. Barometric pressure units can be selected during Flight Mode using the Options Menu. The Altitude Trend Bar is located along the right margin of the Altitude Display. This feature is optional and can be turned ON or OFF using the Options Menu. The Altitude Trend Bar is magenta.in.color-andoriginates-atthe currentaltitude.onthe-Altitude-Tape -always-from-the middle of the display, directly across from the Altitude Pointer. The height of the Trend Bar, above or below the current altitude, indicates the altitude of the aircraft on the Altitude Tape if the current vertical speed or 'altitude trend' is maintained over a period of six seconds. For example, as seen in Image 7, the current altitude is approximately 2,420 feet. The Trend Bar is at approximately 2,470 feet, indicating that the aircraft's altitude will be 2,470 feet in six seconds if the current vertical speed or climb is maintained constant. The length of the Trend Bar will increase with increased dive or climb rates and approach zero or disappear entirely as the vertical speed reaches zero in level flight. Airspeed The Airspeed Indicator Display consists of three parts: Airspeed Window, Airspeed Tape and Airspeed Limitations or Range Markings. The Airspeed Window displays the current Indicated Airspeed (IAS). The digits of the display are enlarged for visibility and increment by one unit. The units will 'roll' or scroll to assist in quick reference as to the increasing or decreasing nature of the aircraft's airspeed. The Airspeed Pointer (triangle) to the left of the window points to the associated position on the Airspeed Tape of the current airspeed. The Airspeed Tape is a vertical scale along the left margin of the display. The current airspeed is always in the middle of the tape and indicated by the Airspeed Pointer on the left side of the Airspeed Window. The Airspeed Tape has numeric indications every ten or twenty units depending on the unit of measure selected. Minor graduations appear every five or ten units, respectively. The Airspeed Tape will 'roll' or scroll to assist in quick reference as to the increasing or decreasing nature of the aircraft's airspeed. A traditional barber pole will be displayed if the aircraft nears Vmo value. FM Approved Date: DEC 16 2013 C 320 itti 22.1 260": 4 : :114) (7., _ lAnn , 2 7°7 2 20i ff. 260 I_p cut I 1': I( M 230 280 . 0 n " - Page 6 SDNY_GM_02758198 SUBJECT TO PROTECTIVE ORDER PARAGRAPHS 7, 8, 9, 10, 15, and 17 EFTA_00245 I 20 EFTA01261780 Nextant Aerospace LLC 355 Richmond Rd. Richmond Heights OH 44143 Document No.: [SSN REDACTED] Revision IR Hawker Beechcraft 400A Brightness Control SAM is configured to adjust its brightness based on the aircraft's manual lighting bus control This installation uses the center panel dim control in the cockpit overhead. Thetpilotor crew membercantemporarily-overridetheturrentbrightnest and-manually — increase or decrease brightness. To adjust brightness, briefly press the Control Knob. The brightness bar will appear overlaid on the Attitude Display and turning the Control Knob will increase or decrease the current setting. While the unit remains powered, the manual adjustment witl remain saved and any change in the lighting bus or photocell sensor will increase or decrease the brightness from the newly set manual adjustment point. When the unit is powered OFF, the manual adjustment will be reset and default to the lighting response curve programmed into memory per the settings in the Configuration Mode setup by the installer. SECTION 6 - PERFORMANCE NO CHANGE TO AFM SECTION 6 - WEIGHT AND BALANCEIEQUIPMENT NO CHANGE TO AFM SECTION 7 - SUPPLEMENTS NO CHANGE TO AFM FAA Approved Date: DEC 16 2013 Page 7 SDNY_GM_02758199 SUBJECT TO PROTECTIVE ORDER PARAGRAPHS 7, 8, 9, 10, 15, and 17 EFTA_00245 I 21 EFTA01261781 UNITED STATES OF AMERICA DEPARTMENT OF TRANSPORTATION-FEDERAL AVIATION ADMINISTRATION STANDARD AIRWORTHINESS CERTIFICATE NATIONALITY ARO 2 MANUFACTURER ANO MODEL 3 AIRCRAFT SERIAL 1 CATEGORY REG* TRATION MARRS RAYTHEON AIRCRAFT CO NUMBER N721CC BE-400A RR-260 TRANSPORT 5 AUTNORRY AND BASIS FOR !SWARM TIN inortsiss art* Semi passim NUS C 4004 mod oohs( d dee isasaRe Sat bine IN lo boo *obi MFRS b cote bin Wanks het. b b614 miles b Si end* Wes ban Sew b Noteserti RDA &RIM, onial* aid NOS ifroseNas cc* Al Bata /du RN Care OloyelrICid M411b1.6a1 n NH ANN ERIS NONE 6 TERMS MO CONDITIONS Wks Axes Nirdwet Refl. %WAN es s lonehgta ONI AhresnatINS Ns FAA to siKelinies owlkoN haw as lug as to ouSini "raft SARA at rots Nopecmg ENFOrce *Pot 21 {7,M elm ha MYNA ARUN" a alas RNA hail le Wad juw DATE OF ISSUANCE R 12/11/1999 OESPSNATION ?AMER PA-P500-68 kr, ifbeillOOWOUtek0, Mal cites csesSals airy tepelelatilthe N te4tMeidel FLMb co Mel tel omega MSS bit INSCERTEICATE RUSIN OVUM N THE NRCRAFT DI ACCERCONCE MTN AFRICABLE REGULATOR FM kom 8100-2 !OFT I I &Wm., Plate SDNY_GM_02758200 SUBJECT TO PROTECTIVE ORDER PARAGRAPHS 7, 8, 9, 10, 15, and 17 EFTA_00245 I 22 EFTA01261782 SDNY_GM_02758201 SUBJECT TO PROTECTIVE ORDER PARAGRAPHS 7, 8, 9, 10, 15, and 17 EFTA_00245123 EFTA01261783 DEPARTMENT 06 TRANSSS,Warar2VIATION AISMINIPRATION OANelkP •ffittrilINESSCERTJA914VE 3 be kt 2ela r set,7.AA,..;„ft co. S sul NU s oflueSposuseporetocrso sy.ononso of .0516 M ow Sila**0•1001.1Sana the Ills .eel Pet C6ItbYll, bt. oh trawl. litelm.. I de k. . ..e.r.cn brut m" 0;.,...3.viel IN., ‘W tel.4 oi the itoscottocomixento se lad Otiora atwohroAtis owe as ..46. too oiltAirn-imooton tattsiscat Ow stiat nape arnoitelosSn • 4146-1.066 Trahsport 6 161,74',6 17,514) • ri ucalStertra4 - Ej dna: censtrya,n74.36c.. "..4"4 4 7.90., `t re"""". "? ....,:p.:1 1W . T. 1" : ".2 .1;: c64 ; Ad i,,,r "*"° .:* arsw 6:o gt6r. t.5,erei,r.tarem0SI1IL 7hrtif0.46-oriS , 4c,2- kat 13S"rs '" ; "617Si2b . 6•0.. Ares9;43 IYA. 1N A a:19 *ter: lir rig ta1 • :1: _J r/ 44 tit eilkoldit0 . • - SDNY_GM_02758202 SUBJECT TO PROTECTIVE ORDER PARAGRAPHS 7, 8, 9, 10, 15, and 17 EFTA_00245124 EFTA01261784 SDNY_GM_02758203 SUBJECT TO PROTECTIVE ORDER PARAGRAPHS 7, 8, 9, 10, 15, and 17 EFTA 00245125 EFTA01261785 REPLACEMENT AIRWORTHINESS CERTIFICATE REQUEST FAR ORDER 8130.26, Paragraph 215 1. wi4.4..,„i" Cr boNit iLL. requesto replacement NO pose ph. Ainvorthkicsa Certificate for Aircraft 117/ct, izg•-ua ReptIsalan (NI ?but *aid Rosati RR gnu yes A (MYR The nightal certificate is: last • • 'Mutilated X:_"N" anther nine on* .6.. kba-M-eg J2-29- 2°'y • SDNY_GM_02758204 SUBJECT TO PROTECTIVE ORDER PARAGRAPHS 7, 8, 9, 10, 15, and 17 EFTA 00245126 EFTA01261786 SDNY_GM02758205 SUBJECT TO PROTECTIVE ORDER PARAGRAPHS 7, 8, 9, 10, 15, and 17 EFTA 00245127 EFTA01261787 0 MAJOR REPAIR AND ALTERATION SOmannom as (Airframe, Powerplant, Propeller, or Appliance) tramponmas Rani Amman man mumon Fens k Noetone Core 2 i200020 I inde2COT Electronic Tracking Number FOr FAA U54 Only INSTRUCTIONS: Pnnt or typo as entries See FAR 43.9. FAR 43 Appendix 8. and AC 419-1 (or subsequent revision meted) lor instructions and dospOSIbo of this Nem. This report is required by law (49 U.S.C. 1421) Falure to report can result in dig way not Irt exceed St.000 for each such Notabch (Secton 901 Federal Aviation Act 1958) 1. Aircraft Nationality and Registration Mark N787TA Serial No. RK-260 Make Beechcraft Model 400A Seats 2. Owner Name (As shown on registration certificate) Flight Options LLC Address (As shown on registration cerb.6caSe) Address: 26180 Curtiss Wright Pkwy City: Richmond Hts sum Oh Zit): 44143 Cony USA 3. For FAA We Only 4. Type S. Unit Identification Repair Nara", Um Make Model Serial Number CI 0 AIRFRAME (A3 WU/Media Om I above) 0 O POWERPLANT 0 • PROPELLER • O APPLIANCE bee hinlearss S. Conformity Statement A. Adeney'S Name and Address 8 Kind of Army .40r* Nextant Aerospace Mama [ADDRESS REDACTED] car Cleveland sow OH 2.* 44143 Cony. USA O u.S. Ca:Skated Mechanic O Manufacturer O Foreign Cetacale4 Mechanic C. Cenocate No. 52 crocus Row( Noon CRS # 25NR667B O Certificated Maintenance Organization 0. Ionise trim the repair analOr alterffign made to the tmit(s) odenttfecl in item 5 above and deathbed on the reverse Or attachments hereto nave been made in accordance nit the requirements of Pad 43 of the U S. Federal Ahabon Regulations and that the information furniShed herein iS IM and correction tat dm knOMedpe Extended ranee fuel per 14 CFR Part 43 APP 8 0 Signature/Oale a Authorized Indinduat 11 1 1061/2012 7. Approval for Return to Service Pursuant to Me &Monty given pinata specified below. the un I Men tied in item 5 was knower:lathe manner prescribed by the Admentiator of Ine Federal Avalon AdrrstindfabOn and IS 0 APPROtrto El REJECTED BY FM Ft Standards Inspector manufacturer Maintenance Organization PerSOnfii)reoved try Canadian Department of Transport FM Designee X Repair Saloon InspecsonAulhorrtabon Oast (satisfy) Cenrecaie or Oestmeon No. CRS # 25NR667B Signature/Woof Aerometer Individual 10/9/2012 -dieuda, FAA Form 337 ('0.06) SDNY_GM_02758206 SUBJECT TO PROTECTIVE ORDER PARAGRAPHS 7, 8, 9, 10, 15, and 17 EFTA_00245 I 28 EFTA01261788 SDNY_GM_02758207 SUBJECT TO PROTECTIVE ORDER PARAGRAPHS 7, 8, 9, 10, 15, and 17 EFTA_00245 I 29 EFTA01261789 NOTICE Weight and balance or operating limitation changes shalt 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. 8. Description of Work Accomplished Of mote space is required, attach additional sheets Identify with aircraft nationality and registration mark and dale work completed) N787TA Nationality and Registration Mark 10/9/2012 Date Carried out Repair to the Left Pylon Bell Frame Crack. Repaired Clip P/N 45A96063-7 Crack Damage at Flight Station 329.92 in accordance with US Technical Document EO6217 Rev A, Approved by DERT-605367-NM Darrell A. Meyer. The Clip P/N 45A96063-7 is .063" thick and is made of AL Alloy 202443 CLAD. See Attached FM Form 8110-3 Signed by Robert M. Halvorson DERT-605221-NM Dated 10/19/12 Nextant Aerospace EO 108-11 Rev E dated 10/19/12 and US Technical Document U-1-1229 Rev K dated 10/17/12.for Structural Substantiation. Instructions for Continued Airworthiness. Follow normal maintenance practices for the left and right engine pylon clip repair as called out in the AMM for the Beechjet 400/400A. Weight and balance change is negligible. End K Additional Sheets Are Attached FAA Form 337 00-06) SDNY_GM_02758208 SUBJECT TO PROTECTIVE ORDER PARAGRAPHS 7, 8, 9, 10, 15, and 17 EFTA 00245130 EFTA01261790 SDNY_GM_02758209 SUBJECT TO PROTECTIVE ORDER PARAGRAPHS 7, 8, 9, 10, 15, and 17 EFTA_00245131 EFTA01261791 DEPARTMENT OF TRANSPORTATION FEDERAL AVIATION ADkUNISTRAMON STATEMENT OF COMPLIANCE WITH AIRWORTHINESS STANDARDS I. DATE October 19. 2012 AIRCRAFT OR AIRCRAFT COMPONENT IDENTIFICATION 2. MAKE Hawker Beechcraft 3. MODEL NO. 400A (see note 3) 4. TYPE (Altplow. Rack lielloopter. eat) Airplane • S. NAME OF APPLICANT Nextant Aerospace (see note 4) LIST OF DATA 6. IDENTIFICATION 7. TITLE Nextant Aerospace Document: Repair - LH/RH Engine Pylon Clip Structural Substantiation al Engine Pylon Clip (P/N 45A96063-7) Crack Damage Repair NOTES: 1. Detail design and Structural approval only. 2. This approval is for the engineering design data only. II indicates the data listed above demonstrates compliance only with the regulations specified by paragraph and subparagraph listed below as 'Applicable Requirements. This form does not constitute FM approval of all the engineering data necessary for substantiation of compliance to necessary requirements for the entire repair. This approval is for the engineering design and substantiation data. It is not an installation approval. 3. Model: Hawker Beechcraft 400A as defined per TCDS No. AISSW. 4. Applicant: Nextant Aerospace, 26180 Curtin Wright Pkwy. Cleveland, OH 44143 U.S. LLC 25NR667B. 5. Applicable to the following aircraft SM & RAN: RK-137 N400M, RK-230 N722NK, RK-123 N410FL, RK-225 N4151.X, RK-248 N226WC, RK-289 N440LX, RK-093 N493CW, RK-310 N451LX, RK-252 N790TA, RK-195 N718TA, RK-239 NOSH._ RK-284 N439LX. RK-334 N442FL, RK-368 hM27FL, RK-327 N4541X, RK-146 N748TA, RK-280 N787TA, RK-413 N482I.X, RK-397 14473FL, RK-365 N459Ut, RK-387 N4781.X, RK-189 N715TA, RK-264 N428LX, RK-244 N492LX. RK-180 N709TA. End end end EO No. 108-11 Rev. E Dated 10/19/12 US Technical Document: U1-1229 Rev. K Dated 17 Oct 12 —end end 8. PURPOSE OF DATA To show compliance with applicable regulations in support of a Major Repair on Hawker Beechcraft Model 400A as listed in Note 5. 9. APPLICABLE REQUIREMENTS (Lin sprafic sections) 14 CFR Part 25: 25.301 Arndt. 25-23, 25.303 Amdt. 25-23. 25.305(a)(b) Amdt. 25-88, 25.307(a) Amdt. 25-72, 25.601 Amdt. 25-0. 25.603 Arndt. 25-46. 25.605 Arndt. 25-46. 25.609 Amdt. 25-0. 25.611 Arndt 2543. 25.613(a)(b) Arndt. 25-112. ICI CERTIFICATION - Under authority vested by direction of the Administrator and in accordance with conditions and limitations of appointment under 14 CFR Pan 183. data listed above and attached sheets numbered none have been examined in accordance with established proceduns and found to comply with applicable requirement of the Airworthiness Standards listed. Recommend approval of these data I (We) Therefore Approve these data II. SIONATURES(S) OF DESIGNATED ENGINEERING REPRESENTATIVEO) 12. DESIGNATION NUMBER(S) 13. CLASSIFICATION (5) Robert M. Halvorson 4e4Z--- DERT-605221-NM Structures FAA Form 8110-3 (03/10) SUPERSEDES PREVIOUS EDITION SDNY_GM_02758210 SUBJECT TO PROTECTIVE ORDER PARAGRAPHS 7, 8, 9, 10, 15, and 17 EFTA_00245132 EFTA01261792 SDNY_GM_027513211 SUBJECT TO PROTECTIVE ORDER PARAGRAPHS 7, 8, 9, 10, 15, and 17 EFTA_00245 I 33 EFTA01261793 nextant aerospace ENGINEERING ORDER EO NO. 108 REV. E MODEL: BEECH 400A RN: 45A96063-7 TITLE: Repair - LH/RH Engine Pylon Clip DRAWING NO. n/a REV: - Serial Number(s): RK-137, RK-230, RK-123, RK-225, RK- 248, RK-289, RK-093, RK-310, RK-252, RK-195, RK-239, RK-284, RK-334, RK-368, RK-327, RK-146, RK-260, RK-413, RK-397, RK-365, RK-387, RK-189, RK-264, RK-244, RK-180 DESCRIPTION ORDER DESCRIPTION: Repair, LH/RH Sell Frames: Follow U.S. Technical EC) 6217 for repair instrculions, document is attached (REF ECR 951) Note: Item 1 in repair bib of materials, section 2.1 of U.S. Technical EO 621710 be fabricated from .040* thick 2024-T3 CLAD AL PER AMS-QQ-A-250/5 (REF ECR 760) APPROVALS CREATED BY: Keogh /Imelda DATE: 10180012 APPROVED BY: DATE: CHECKED BY: Kevin Hirnalrlaht DATE: 101812012 FAA APPROVAL REQUIRED? YES 0 NO O Change: MAJOR MINOR 0 O G ERING PRODUCTION QUA A CUSTOMER I AGENCY AO DATE: 4 49/ere--0 DATE' DATE: _Aga 91/4 -r DATE: Form No. NXT-4261 Rev IR Reference Doc: SOP 4.1 Once Printed This Form is Uncontrolled SDNY_GM_02758212 SUBJECT TO PROTECTIVE ORDER PARAGRAPHS 7, 8, 9, 10, 15, and 17 EFTA_00245 I 34 EFTA01261794 SDNY_GM_02758213 SUBJECT TO PROTECTIVE ORDER PARAGRAPHS 7, 8, 9, 10, 15, and 17 EFTA 00245135 EFTA01261795 nextant aerospace ENGINEERING CHANGE REQUEST ECR NO. 951 MODEL Beech 400A TIRE: Repair — LWRH Engine Pylon Cap Revision PIN: 45A98083-7 DRAWING NO. REV: INMATE() BY: Kevin HirnelrigN REASON: Allan not in egeolhily range need EO repair DEPT: Engineering DATE: 10/8/2012 CHANGE DESCRIPTION REQUESTED CHANGE QFSCRIPROt : Revise E0 108D TO REV E to Include ehealyeyror SIN RK-260.14K-413. RK-397,RK-365, RX-187. RK•1119. RK-284, RK•244. RK-180 ECR DISPOSITION ECR: ACCEPT 0 REJECT O BY: Kevin Hirrielighl DATE: 10/8/2012 REASON FOR REJECRON: APPROVALS J FAA APPROVAL REQUIRED? YES 0 NO O Change: MAJOR MINOR O ENGINEERING PRODUCTION QUALITY ASSURANCE SUPPLY CHAIN DATE: [repeated 4 times] Form No. NXT-425/ Rev A Reference SOP 4.1 Once Printed this Form is Uncontrolled SDNY_GM_02758214 SUBJECT TO PROTECTIVE ORDER PARAGRAPHS 7, 8, 9, 10, 15, and 17 EFTA 00245136 EFTA01261796 SDNY_GM_02758215 SUBJECT TO PROTECTIVE ORDER PARAGRAPHS 7, 8, 9, 10, 15, and 17 EFTA_00245 I 37 EFTA01261797 U.S. TECHNICAL ENGINEERING REPORT DOC. NO.: E06217 REVISION: C PAGE: 1 of 10 TITLE: Repair — LH/RH Engine Pylon Clip (P/N 45A96063-7) Crack Damage Nextant Aerospace — Beechjet 400A APPLICATION BY DATE NEXT ASSEMBLY AIRPLANE ENGINEER F. Valerio 20 July 11 N/A 400A APPROVED M. Perez 22 July 11 EFFECTIVITY: See Section 1.2 Revisions REVISION SYMBOL DESCRIPTION DATE APPROVAL NC iNITUU. RELEASE 22July 11 Darrel Meyer A (Rated Figure 3. Section 3.0. and Bak added Rose 4. Ref UST WO 16231 08 Aug I1 Darrel Mayer B Ftevlsed EC, per customer request for Ground Stud relocation. Added Figure S. 16 Sep 11 Darrel Meyer C Revised E0 per customer request to add Waal RN-285. Ref UST WO 06297 13 Oct 11 Darrel Meyer List of Active Pastes Rev C [repeated 10 times] PG 1 2 3 4 $ 6 7 8 9 10 Rev PO NOTICE This document contains- U S. Technical "(UST) proportery information and is subject to mum upon request It is fronsinined for the sole purpose of aiding the trantaaico of business between UST and Re recipient. All information. day designs. and drawings contained Mein are proprietary to and the property of LIST, ref may no be rtrodead or °vied. nor appeopristed 10 uses in any way detrimental to the inkrrsu of LIST, including disclosure to outside panic,. directly or indirectly, without specific written comma of LIST SDNY_GM_02758216 SUBJECT TO PROTECTIVE ORDER PARAGRAPHS 7, 8, 9, 10, 15, and 17 EFTA 00245135 EFTA01261798 SDNY_GM_02758217 SUBJECT TO PROTECTIVE ORDER PARAGRAPHS 7, 8, 9, 10, 15, and 17 EFTA_00245139 EFTA01261799 U.S. TECHNICAL AMaghn holutts. Stakes POttrA9liCcuillestos ENGINEERING REPORT DOC. NO.: E06217 REVISION: C PAGE: 2 of 10 TABLE OF CONTENTS SECTION SUBJECT PAGE TITLE PAGE 1 REVISION HISTORY 1 TABLE OF CONTENTS 2 1.0 GENERAL 3 1.1 SCOPE 3 1.2 EFFECTIVITY 3 1.3 APPLICABILITY 3 1.4 REFERENCES 3 1.5 SAFETY PRECAUTIONS 3 1.6 FUNCTIONAL TEST INFORMATION 3 1.7 WEIGHT & BALANCE REPORT 3 1.8 STRUCTURAL SUBSTANTIATION REPORT 3 1.9 ELECTRICAL LOAD DATA 3 2.0 DAMAGE & DAMAGE REPAIR 5 2.1 REPAIR BILL OF MATERIALS 9 3.0 REPAIR INSTRUCTIONS 9 4.0 INSTRUCTIONS FOR CONTINUED AIRWORTHINESS 10 ATM EMS? SDNY_GM_02758218 SUBJECT TO PROTECTIVE ORDER PARAGRAPHS 7, 8, 9, 10, 15, and 17 Erl'A_00245140 EFTA01261800 SDNY GM 02758219 SUBJECT TO PROTECTIVE ORDER PARAGRAPHS 7, 8, 9, 10, 15, and 17 EFTA_00245141 EFTA01261801 U.S. TECHNICAL retdurts.SOYCO. f.gim•:y 6 Cut:talk. ENGINEERING REPORT DOC. NO.: EO6217 REVISION: C PAGE: 3 010 1.0 GENERAL 1.1 Scope This document describes the procedure for repair of LH/RH Engine Pylon Clip Crack damage. The Clip P/N 45A96063-7 is .063" thick and is made of Al Alloy 2024-T3 CLAD. 1.2 Effectivity Hawker Beechcraft 400A MSN (Registration #) RK-279 (N436FL) and RK-295 (N898TA). 1.3 Applicability Damaged area shown in photo pictures in Section 2. 1.4 References Beechjet 400A Structural Repair Manual. 1.5 Safety Precautions Follow safety practices in Beechjet 400A Structural Repair Manual. 1.6 functional Test Information N/A 1.7 Weight and Balance Report N/A 1.8 Structural Substantiation Report US Technical Document No. U1-1229. 1.9 Electrical Load Data N/A FO E402 SDNY_GM_02758220 SUBJECT TO PROTECTIVE ORDER PARAGRAPHS 7, 8, 9, 10, 15, and 17 EFTA 00245142 EFTA01261802 SDNY_GM_02758221 SUBJECT TO PROTECTIVE ORDER PARAGRAPHS 7, 8, 9, 10, 15, and 17 EFTA_00245 I 43 EFTA01261803 ENGINEERING REPORT DOC. NO.: E06217 REVISION: C PAGE: 4 of 10 2.0 DAMAGE & DAMAGE REPAIR Area of Damage Locations: Clip PIN: 45A96063-7 DETAIL Figural— Damage Locations (SRM 53-10-631 Fan EA, S2 03$7234A SIDNY_GM_02 758222 SUBJECT TO PROTECTIVE ORDER PARAGRAPHS 7, 8, 9, 10, 15, and 17 EFTA_00245144 EFTA01261804 SDNY_GM_02758223 SUBJECT TO PROTECTIVE ORDER PARAGRAPHS 7, 8, 9, 10, 15, and 17 EFTA_00245 I 45 EFTA01261805 ENGINEERING REPORT DOC. NO.: EO6217 REVISION: C PAGE: Sof10 2.0 DAMAGE & DAMAGE REPAIR — (Continued), Figure 2 — Photo of LH Clio P/N: 45A96063-7 Crack Damage (RH Oppositel Increase damage cut out to eliminate edgedistance issue to Bound stud. Clear''/." greater perimeter of contact surface for both Angle Doubler and Doubler mating surfaces. AIM EA-IS: Doubler perimeter SDNY_GM_02758224 SUBJECT TO PROTECTIVE ORDER PARAGRAPHS 7, 8, 9, 10, 15, and 17 EFTA_00245 146 EFTA01261806 I SDNY_GM_02758225 SUBJECT TO PROTECTIVE ORDER PARAGRAPHS 7, 8, 9, 10, 15, and 17 EFTA 00245147 EFTA01261807 ENGINEERING REPORT DOC. NO.: E06217 REVISION: C PAGE: 6 of 10 2.0 DAMAGE & DAMAGE REPAIR — (Continuedi REPAIR DOUBLER, ITEM 2. MS20470AD6 FLUSH RIVETS EXTRA FRAME CUTOUT TO ALLOW FOR EXISTING FASTENER LOCATION. (ENG 42 RH ONLY) (e:AIS I ING SNAP FASTENER) EXISTING FASTENER LOCATION 0.129/.132 INSTALL MS20470AO4 OR CR3213-4 RIVET TYP ADDED FASTENER LOCATION DRILL TO .161- / .164' DIA. INSTALL ITEM 3 RIVET. (EXISTING STANDOFF SCREW HOLE) (GROUND STUD FASTENER HOLE ORINGINAL LOCATION) 0.6 BOND AREA - FRAME CUTOUT (45A96063-7 BRACKET) EXISTING FASTENER LOCATION DRILL 70 0.161/.164 INSTALL MS20470,405 RIVET OR HL1EIPB-5 HI-LOX PIN OF SUITABLE LENGTH WITH HL70-5 HI-LOK COLLAR TYP REPAIR ANGLE DOUBLER, ITEM 1. R .25 TYP. STA 329.92 FRAME - EXISTING UNMODIFIED FASTENER TYP Fiore 3 - Sketch of RH Clio Repair OM O000site Fr* E4132 UP L RH OUTBD SDNY_GM_02758226 SUBJECT TO PROTECTIVE ORDER PARAGRAPHS 7, 8, 9, 10, 15, and 17 EFTA_00245 II 48 EFTA01261808 SDNY_GM_02758227 SUBJECT TO PROTECTIVE ORDER PARAGRAPHS 7, 8, 9, 10, 15, and 17 EFTA_00245149 EFTA01261809 U.S.IECHNICAL Artatica Prtducn.Smket, f mirethy Sfmtrmw. ENGINEERING REPORT 2.0 DAMAGE & DAMAGE REPAIR - (ContInuedi Figure 4 — Photo of RH Clio Final Repair (LH O000shel lam 14.153 DOC. NO.: EO6217 REVISION: C PAGE: 7 0110 SDNY_GM_02758228 SUBJECT TO PROTECTIVE ORDER PARAGRAPHS 7, 8, 9, 10, 15, and 17 EFTA_00245 ISO EFTA01261810 SDNY_GM_02758229 SUBJECT TO PROTECTIVE ORDER PARAGRAPHS 7, 8, 9, 10, 15, and 17 EFTA 00245151 EFTA01261811 ENGINEERING REPORT DOC. NO.: EO8217 REVISION: C PAGE: 8 of 10 2.0 DAMAGE & DAMAGE REPAIR — (Continued). Figure 5 — Photo of Ground Stud Relocation New Ground Stud Location Fan EMU SDNY_GM_02758230 SUBJECT TO PROTECTIVE ORDER PARAGRAPHS 7, 8, 9, 10, 15, and 17 EFTA_00245 152 EFTA01261812 SDNY_GM_02758231 SUBJECT TO PROTECTIVE ORDER PARAGRAPHS 7, 8, 9, 10, 15, and 17 EFTA_00245 I 53 EFTA01261813 U.S. Avbiiim TECHNICAL PreluttOrMtet stria:mei ENGINEERING REPORT DOC. NO.: E06217 REVISION: C irl isitiim PAGE: 9 of 10 2.1 *Note locations. Repair Bill of Materia s Table 1: Repair Parts List Item No. Qty Assy Description Specifications Remarks / Notes 1 2 LH/RH Engine Pylon Clip Angle Doubler 040' THICK See Figures 1 thru 3 [2024-T3tLAD AL PER AMS-QQ-A-250/5 2 2 Doubler .040' THICK 2024-13 CLAD AL PER AMSQQ-A-25015 3 AR Rivet • MS20470AD5 or CR3213-5-5 AR Chem Film MIL-C-5541, 4 CLASS 3 5 AR PolyamIde Epoxy Primer MIL-PRE-23377 TYPE 1. CLASS C 6 AR Adhesive HYSOL EA 9309.3NA 7 2 RH Engine Pylon Clip Flush Rivet MS20426AD6 See Figure3 Permissible to use oversize HL18PB-5 or HL18PB-6-4 and collar HI-Lok fasteners at limited access 3.0 MECH. INSP. REPAIR INSTRUCTIONS: 3.1 CAREFULLY CUT THE DAMAGED AREA FROM THE LH/RH STA 329.92 FRAME AS NEEDED TO REMOVE CRACK DAMAGE. ENSURE ADEQUATE CLEARANCE IS MAINTAINED TO ACCOMMODATE BUTTS OF RIVETS INSTALLED BY THIS FIELD REPAIR (AS SHOWN IN FIGURES 2 & 3). TAKE CARE NOT TO DAMAGE UNDERLYING STRUCTURE. 3.2 CAREFULLY HAND FORM DAMAGED AREA OF FRAME TO ORIGINAL CONTOUR AS REQUIRED. REFORM 45A96063-7 CLIP AS REQUIRED. 3.3 CHECK. USING A SUITABLE NOT TECHNIQUE (e.g. FLUORESCENT PENETRANT OR EDDY CURRENT), TO ENSURE NO CRACKS EXIST AND ALL DAMAGE HAS BEEN REMOVED. REPORT ANY ADVERSE FINDINGS TO RAC FOR ASSESSMENT BEFORE CONTINUING 17TH THIS REPAIR. 3.4 FABRICATE RFPAIR I-OW(1ER AND REPAIR ANGLE DOUBLER FROM .040 ALUMINUM SHEET PER A MINIMUM 20 EDGE SHOWN IN FIGURES 2 & 3. THE STA 329.92 FRAME. ANGLE DOUBLER TO -T42 THICK AMS-Q DISTANCE AND BEND CONDITION I:1 2024-T3 1,14L.eice1/4.44 49L-4e: CLAD A-250/5. size AS REQUIRED MAINTAINING TO ALL PICKED UP FASTENERS AS FORMED TO NEST OVER IMO FLANGE OF RADIUS .06 MIN. HEAT TREAT REPAIR PER AMS2770 AFTER FORMING COMPLETE. Fern E4 33 SDNY_GM_02758232 SUBJECT TO PROTECTIVE ORDER PARAGRAPHS 7, 8, 9, 10, 15, and 17 EFTA 00245154 EFTA01261814 SDNY_GM_02758233 SUBJECT TO PROTECTIVE ORDER PARAGRAPHS 7, 8, 9, 10, 15, and 17 EFTA_00245 I 55 EFTA01261815 U.S. TECHNICAL **buy, Picea Semcn ENGINEERING REPORT DOC. NO.: E06217 REVISION: C rflowisaogrikow, PAGE: 10 of 10 3.0 REPAIR INSTRUCTIONS: MontInuedl MECH. INSP. 3'5 CAREFULLY REMOVE ALL EXISTING FASTENERS PICKED UP BY THE REPAIR DOUBLER PER THE MODEL 400/400A SRM, 51.40-00. 3.6 DRILL ALL FASTENER HOLES AS SHOWN IN FIGURES 2 8 3 IN ACCORDANCE WITH THE MODEL 400/400A SRM, 51.41-00 (SOLID RIVETS), 51.43-01 (BLIND RIVETS). MAINTAIN MIN 20 EDGE DISTANCE AT ALL FASTENER LOCATIONS AND 4D60 SPACING AT ALL ADDED FASTENER LOCATIONS. DRILL REPAIR DOUBLER TO MATCH LOCATION AND SIZE OF EXISTING STANDOFF SCREW HOLES. DRILL GROUND STUD HOLE AT NEW LOCATIONS DEPICTED IN FIGURE 5. DEBURR ALL SHARP EDGES. 3'7 PREPARE AND BOND THE REPAIR DOUBLER IN PLACE USING HYSOL EA 9309.3NA ADHESIVE IN ACCORDANCE WITH THE ADHESIVE MANUFACTURER'S INSTRUCTIONS. ALLOW ADHESIVE TO FILL GAP CAUSED BY LAP OF INBD FRAME FLANGES. 38 INSTALL ALL FASTENERS AS SHOWN IN FIGURES 2 AND 3 PER THE MODEL. 400/400A SRM, 51-40-00 (SOLID RIVETS), 51.43-01 (BLIND RIVETS). NOTE THE UPPER FASTENER SECURING THE 45A96063-7 CLIP WILL BE INSTALLED THROUGH THE REPAIR DOUBLER AND CLIP ONLY. 3*9 PROTECT ALL BARE ALUMINUM WITH CHEM FILM PER MIL-C-5541, CLASS 3 AND ONE COAT OF MIL-PRE-23377 TYPE 1, CLASS C POLYAMIDE EPDXY PRIMER. ENSURE A 0.6 AREA AROUND THE GROUND STUD HOLE REMAINS FREE OF PRIMER AS SHOWN IN FIGURE 2. 3.10 REINSTALL ALL OTHER REMOVED HARDWARE WITH EXISTING TYPE AND SIZE FASTENERS OF SUITABLE GRIP LENGTH. 4.0 INSTRUCTIONS FOR CONTINUED AIRWORTHINESS FOLLOW NORMAL MAINTENANCE PRACTICES FOR THE LH/RH ENGINE PYLON CLIP REPAIR AS CALLED OUT IN THE AMM FOR BEECHJET 4001400A. NOTES 1. WEIGHT AND BALANCE CHANGE NEGLIGIBLE. 2. ALL DIMENSIONS ARE IN INCHES UNLESS OTHERWISE SPECIFIED. 3. EMBODIMENT OF THIS FIELD REPAIR MUST BE RECORDED IN THE AIRCRAFT LOG BOOK STATING THIS FIELD REPAIR NUMBER AND REVISION. -, nal, SDNY_GM_02758234 SUBJECT TO PROTECTIVE ORDER PARAGRAPHS 7, 8, 9, 10, 15, and 17 EFTA 00245156 EFTA01261816 SDNY GM 02758235 SUBJECT TO PROTECTIVE ORDER PARAGRAPHS 7, 8, 9, 10, 15, and 17 EFTA 00245157 EFTA01261817 C O MAJOR REPAIR AND ALTERATION LIS ownew a (Airframe, Powerplant, Propeller, or Appliance) wwwwien Wont mew Fan Vowed On alp 2,204020 wrancor Electronic Tracking Number For FAA Use Only INSTRUCTION& Pint or type M entries. Sn FAR 419, FAR 43Aporentfa B. and AC 43.9.1 (or subsequent revision Men/07) for inarsraana and disposaion of en Wm. This report is required by Ism (49 U.S.C. 1421). Finn to report an result in a ors penalty not to exceed 51.000 foe each such women (Section 901 Federal Mahn Act 1958) 1. Aircraft NotonaRY and Registration Mark N787TA Serial No. RK-260 Make Raytheon Aircraft Company 400A SAWN 400A Sees 2. Owner Name (As shone on mgetrat ten Write(*) Flight Options .LLC AddreSS (As Shawn On regisfrabon centime) Address 26180 Curtiss Wright PKWY cry Richmond Heights Dar OH to 44143.1453 cons USA 3. For FAA Use 0017 4. Typo 5. UM Identification Repair Merano Unit Make Model Sena Number 0 0 AIRFRAME (As CleaCtiaeol in Rein I Nate) ID O POWERPLANT 0 O PROPELLER O O APPLIANCE Tams I. Conformity Statement A. Agency, Kline and Adana B. IWO otAgenO7 Nerve Nertant Aerospace Adams [ADDRESS REDACTED] conay USA O ua. CeMubed Inithanic O Manufacturer O FOretbri Cecinas:I Mechanic C Certacate No ID osmoses Repair Station CRS # 25NR667B O Certificated Maintenance oroanuation D I tenth that the repair ardror alteration made to the uniks) /Penned in 5 above and described on the reverse a anamunents hereto have been made in accordance with the equirements of Pan 43 of the U.S Federal Aviation Regulations and that the oft:maw lurnened herein is We and torten te the best el my knowledge. Extended range rum per 14 CFR Part 43 App .B 0 SenstworDite A.Ockwell of Autrolzedna L .. 01/08/2013 7. Approval for Return to Service Pursuant to the anion Elam person weaned been. the um Admnistrator or Pre Federal Aviation Admintarron and is xlen Cr Ind in item 5 was inspected elm manner presaged by Me APPROVED 0 REJECTED BY FM Di Standards Inspector Manufacturer Mainlenance Organuabon Person Approved by Canadian Depart mem of Transport FAA Designee X Repair Station Inspection AulhOritabOn Otter (Spey) Certircat or Demonatan No CRS ft 25NR6678 sgnalurweale or meccad tneAdi A .Ockwell 01/08/2013 mat FAA Form 337 °ober SDNY_GM_02758236 SUBJECT TO PROTECTIVE ORDER PARAGRAPHS 7, 8, 9, 10, 15, and 17 EFTA 00245158 EFTA01261818 SDNY_GM_02758237 SUBJECT TO PROTECTIVE ORDER PARAGRAPHS 7, 8, 9, 10, 15, and 17 EFTA_00245 I 59 EFTA01261819 NOTICE weight and balance or operating limitalion Changes shalt be entered in the appropriate antral, record. An alteration must be compatible with alt previous alterations to assure continued conformity with the appbcable airworthiness requirements 8. Description of Work Accomplished (II more space is required. attach additional sheets identify with aircraft nationality and registration mark and date trot* COMpleted) N787TA Nationally and Negotiation Mark Installed Bose Headset Mount Panel Connector ( LEMO) 6 Pin 01/08/2013 Date Modify Pilots and Co-pilots microphone jack panels per Nextant Aerospace Drawing NX230-10001 & NX230-10001-02. Wire connected per Nextant Aerospace Drawing NX230.10001.01. Install circuit breakers in LH AFT Circuit Breaker panel as marked on Nextant Aerospace Drawing N995803 for part Number N995803-4. This was FAA Approved by Dan Buzz DER-T-230019-CE on a FAA 8110.3 dated 01/08/2013 Using Nextant Aerospace Engineering Document 1037 Dated 12/17/2012 ICA Continue with Normal Maintenance Manual Inspection Requirements for this area End K Additional Sheets Are Attached FAA Form 337 00081 SDNY_GM_02758238 SUBJECT TO PROTECTIVE ORDER PARAGRAPHS 7, 8, 9, 10, 15, and 17 EFTA_00245 I 60 EFTA01261820 SDNY_GM_02758239 SUBJECT TO PROTECTIVE ORDER PARAGRAPHS 7, 8, 9, 10, 15, and 17 EFTA 00245161 EFTA01261821 U.S. DEPARTMENT OF TRANSPORTATION FEDERAL AVIATION ADMINISTRATION STATEMENT OF COMPLIANCE WITH AIRWORTHINESS STANDARDS 1. DATE 12/19/2012 AIRCRAFT OR AIRCRAFT COMPONENT IDENTIFICATION 2. MAKE Hawker Beecticraft 3. MODEL NO. 400A SIN RK-260 Only 4. TYPE (Aoan.% ROOM. PleaCOONe ere) Airplane 5. NAPA OF APPLICANT Nertant Aerospace LW LIST OF DATA 6. IDENTIFICATKHI 7. TITLE Nestent Aerospace Dooarnent EO 1037 dated 12/1772012 Engineenng Order Install Bose Headsel Panel Mount Connedor (LEMO) 6 Pin END This approval is for the electrical systems aspects only. Note: The above data does not meet the criteria of FM Part [ADDRESS REDACTED]atement Number ANM-01-04. System Wiring Policy for Certfication of Pan 25 Airplanes. Additional approvals may be required. This approval is for engineering design data only and it not an installation approval. It intimates the data listed above demonstrates compliance only with the regulations specified by paragraph and subparagraph listed below as *APPLICABLE REQUIREMENTS.' (Compliance with addniona I regulations not listed here may be required). This form does not constitute FAA approval of an the engineering design data necessary for substantiation of compliance to necessary requirements for the entire alteration' e. PURPOSE OF DATA; Support maid flotation to aircraft Hastier Boadicea 400A RK-260 Only. 9. APPLICAElat REQUIREMENTS/Lel speedo stairs) 14 CFR 25.1301(a)(b)(c)(ORIGI.25.1307(c)(25-23). 25.1357(eXc)(ORIGL 25.1431(aXe(ORIG), 25.1541IORICI Note: Compliance hes been found to the amendment levels indicated on Hawker Beecncraft TCDS Revision 26 Part 25 Amendment 25-I through 25-00 to the above aPP.Cable requirements. 10. CERTIFICATION • Under aulhonty vested by direction of the Administrator and in accordance with °mullions and &neatens of appohtment undo. 14 CFR Part 163 of aro Federal Aviation Regulations. date ;sled above and on eiteched than numbered bea have been °waned In accordance wen established prOCedUree and found to comply with appecabie reaueemontS of no Ainvortriness Standards listed. I (We) Therefore approve these data. I t. S*RATUREty. F r 31014A ENGINEERING REPRESENTATIVE(S) 12. OESKINARCIN NUMBERS(5) IT. CLASSIFICATION(S) Danis 1. Bum - 4"4?' DEBT-230019-CE Systems and Equipment FM Form 5110-3 (03/10) SUPERSEDES PREv1QUS EDITION GPO 901.613 SDIV_GM_02258240 SUBJECT TO PROTECTIVE ORDER PARAGRAPHS 7, 8, 9, 10, 15, and 17 EFTA_00245162 EFTA01261822 SDNY_GM02758241 SUBJECT TO PROTECTIVE ORDER PARAGRAPHS 7, 8, 9, 10, 15, and 17 EFTA 00245163 EFTA01261823 le MAJOR REPAIR AND ALTERATION us oreenneuer (Airframe, Powerplant, Propeller, or Appliance) Tareaniesi Finionl MARNA Aeithidelnase rim, Artmve O me No. 21200=0 1 Ir302007 s Electionic Trio:song Number For FM Use Only INSTRUCTIONS: Pike or type all enMes. See FAR 43.9. FAR 43 Appends B. and AC 43 9.1 ;or subsequ nt revision Meteor) for moo:Sons and dispomen <4814 form. This report a required by law (49 ll S C 1421) Fa4441 report can resat in a civil penalty ratio exceed SIAM for each aide vision (Secton 901 Federal Avalon Act 1958) 1. Aircraft Nationality and ecru!~ Mark N787TA Segel No. RK-260 Make Raytheon Aircraft Company 400A Model 400A Series 2. Owner Name (As Mown on reeisrfauon certificate) Flight Options .LLC Mimes (As Stavin On 'Sinew avracate) Mem 7 6180 CI irtivA Wright PKWY c.iy Richmond Heights sm. OH zo 44143-1453 °brio aL il 3. For FAA Use Only 4. Type 5. Unit lantificarban Repair Memban tint Make Model Serer Number 0 0 AIRFRAME (AS OnCrt0e0 in Item I SONO 0 o POWERPLANT 0 O PROPELLER O CI APPLIANCE Type lAirif =kw a. Conformity Statement A_ Agency's Name and Address 8. And or Agency Ham Nextant Aerospace mews [ADDRESS REDACTED] CA Cleveland avv. OH rip 44143-1453 Canty USA 0 U.S Cogitated Mechanic 0 IMIIMeacturer 0 Foreign Contented 1.40010,11C . C. Certelcale ter. ea Certificated Repair Stabon CRS * 25NR667B o certificated MairilenanCe OrgarillOil o. i tete that the repair and/or altereliOn made to the Wills) identified in item 5 above and described on the reverse or ellachmems herald have been made h accordance ugh the requirements °IP n not the in Federal Aviation Regulations and that the Wormabon Wished herein store and correct to the OW of my knowledge. Extended range AS par la CFR Reno • Me 8 SignaturetOate or Authonzrae 44 1 (5 A.Ockwell 01/08/2013 7. APPrOval for Return to Senile* Plirluantto me authority given persons pecilied below, the unit identified AcMcistrator or the Federal Aviation AdMiniSnatAn and is in earn APPROVEO 5 was In inspected in the manner presorted by the REJECTED BY FM Flt Standards Inspector Manufacturer Maintenance Orgenizaten Perntin APPrOved by Canarlan Deparbnent or Transport FM Designee X Repair Saban lose/roam Aulhetila•nn Other (Sretity) CerlitiCale Of De-Knaue R # 2 r, No CS 5NR6678 S Authorized enate:M:41e or IndMd A.Ockwell ape.Q(..( 01/08/2013 FAA Form 337 0 0-00 SDNY_GM_02758242 SUBJECT TO PROTECTIVE ORDER PARAGRAPHS 7, 8, 9, 10, 15, and 17 EFTA 00245164 EFTA01261824 SDNY_GM_027513243 SUBJECT TO PROTECTIVE ORDER PARAGRAPHS 7, 8, 9, 10, 15, and 17 EFTA_00245 I 65 EFTA01261825 NOTICE Weight and balance or operating limitation changes shall be entered in the appropriate aircraft record. An alteration must be compatible with all proviouS alteration to assure continued conformity with the *potable einvOrthiness requirements. 8. Description of Work Accomplished (If more space is required, attach additional sheets. Identify with aircraft nationality and registrabon mark and date work completed) N787TA Nationality and Registration Mark 01108(2013 Date This is a deviation from Nextant Aerospace Document E0-1037 installation of Bose Headset Panel Mount Connector install circuit breakers for Bose Headset per drawing NX230-10001-01 Rev A and mark AFT Circuit breaker panel (N995803) per marked up overlay drawing N995803-4 Test headset connections using following procedure A.) Optional Equipment: 1. Handheld VHF radio 2. COM•120 or equivalent VHF Comm test set. B.) Close the following CB's. PIT AUDIO, COPLT AUDIO, AURAL WARN, COMM N01, COMM NO 2, RTU 1, RTU 2, 1MFD, 1MFD HEATER, 2MFD, MFD HEATER, IPFD, WED HEATER, 2PFD, 2PFD HEATER, PROCU HT N01, FMS 1, FCS 1, PROCU HT NO2, FMS 2, FCS 2, 1 FSU PRI, 1 FSU BAT, AUX BATT 1 (ON AUX BATT 1 MOUNT) PLT BOSE AND CO-PLT BOSE circuit breakers. C.) Connect External Power unit. 0.1 Plug in 80SE headset into pilots lEMO jack. E.) Turn on aircraft power. Test Pilots BOSE: Test may be accomplished using either the interphone system with speakers or one of the Optional items listed as Optional Equipment (Section A 1-2) Note that if the handheld radio method or the test set method Is used, rt is necessary to follow all local radio discipline guidelines for authorized operators using established procedures prior to keying up and transmitting on any active operational channel. For Interphone testing, 1.) Set pilots and co-pilots audio panel to interphone. Turn on cabin speakers. 2.) Speak into mic and verify audio is present. 3.) Speak into opposite side cabin mic and verify audio is heard. Test Co-Pilots BOSE: 4.) Repeat steps 1- 3 for co-pilots side. Perform the following (steps 5-8) regardless of headphone jack test method: 5.) Set STOP ARM SW to ARM position. Jumper WOW to simulate aircraft in air. Pull LH BUS TIE C8 and LOAD BUS TIE CB. Verify pilots audio is Mop. Set aircraft power switch to Emergency position. 6.) Verify that the Co-Pilots headset Is still operational. 7.) Pull all Aux Batt and standby battery CO's. Co-pilot audio should be Inoperative. 8.) Reset all CO's and return WOW switch to normal configuration. 9.) TEST COMPLETE 0 Additional Sheets Are Attached FAA 337 Form (10.06) SDNY_GM_02758244 SUBJECT TO PROTECTIVE ORDER PARAGRAPHS 7, 8, 9, 10, 15, and 17 EFTA 00245166 EFTA01261826 SDNY_GM_02758245 SUBJECT TO PROTECTIVE ORDER PARAGRAPHS 7, 8, 9, 10, 15, and 17 EFTA 00245167 EFTA01261827 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 cordon,* with the applicable airworthiness requirements. 8. Description of Work Accomplished Of more space is required. attach additional sheets. Identify with aircraft nationaffly and registration mark and date work completed.) N787TA Nationality and Registration Mark To test using handheld radio or test set. 01/08/2013 Date 1.) Tune handheld radio or test set to suitable local VHF radio test frequency. (a suitable channel will be within the range 118.000MHz to 136.975MHz) 2.) Tune OH RTU to frequency of handheld radio or tester. 2.) Set pilots and co-pilots audio panel to receive #1 VHF. 3.) Generate tone from test set or transmit voice from handheld radio. Audio should be heard on headset. 4.) set tester to receiver mode. Key microphone and speak Into headset. Audio should be heard on test set or handheld radio. S.) Repeat steps 3 - 4 above to test co-pilots headphone jack. 6.) Perform steps 5.9 from Interphone testing procedure above. This was Approved by Dan Buzz DER-T -230019-CE on a FAA 8110-3 Dated 01/08/2013 using Nextant Aerospace Document E01140 Dated 01/03/2013 and Nextant Aerospace Drawing NX230-10001-01 Rev A Dated 01/07/2013 End K Additional Sheets Are Attached FAA 337 Form (10436) SDNY_GM_02758246 SUBJECT TO PROTECTIVE ORDER PARAGRAPHS 7, 8, 9, 10, 15, and 17 EFTA 00245168 EFTA01261828 SDNY_GM_02758247 SUBJECT TO PROTECTIVE ORDER PARAGRAPHS 7, 8, 9, 10, 15, and 17 EFTA_00245 I 69 EFTA01261829 U.S. DEPARTMENT OF TRANSPORTATION FEDERAL AVIATION ADMINISTRATION STATEMENT OF COMPLIANCE WITH AIRWORTHINESS STANDARDS 1. DATE 1-8-2013 AIRCRAFT OR AIRCRAFT COMPONENT IDENTIFICATION 2 MAKE Hater BealsCrell 3. MODEL NO. 400A SIN RK-260 Only 4. TYPE (4erpiana Rasp. Hereoprec a) Airplane 5. NAME OF APPLICANT Nextan1 Amapa* LLC UST OF DATA 6 IDENTIFICATION 7. TITLE !Sealant Aerospace Document E0 1140 dated 113/2013 Haan: Aerospace Drawing N8230-10001.01 Rev. A dated 1/72013 Engineering Order Deviation to (0-[ADDRESS REDACTED]awing WM Bose Lent Connector (6 Pin) END This approval Is for the elecincal systems aspects only. Note: The above data does not meet the criteria of FAA Pan [ADDRESS REDACTED]atement Number ANM-01.04; System Wiring Policy for Certiecation of Part 25 Airplanes. Additional approvals may be required. 'This approval is for engineering design data only and is not an installation approval. It indicates the data ;died above demonstrates comptance only with the regulations specified by paragraph end subparagraph listed below as 'APPLICABLE REQUIREMENTS" (Compliance with additional regulations not listed here may be !equine)). This form does not constitute FAA approval of all the engineering design data necessary for substantiation of compliance to necessary requirements for the entire alteration' e. PURPOSE OF DATA Support major alteration to aircraft Haar Steelton 400A RK-260 Only. 9. APPLICABLE REOUIREMENTS Relsoecticseceerta 14 CFR 25. I30100(b)(c)ORIC), 25.1301(0Pd-231, 25.1 357(a)(c8ORIG), 25.1431(3)(0)(0121GL 25.15411/WIG) Note: Compliance has been found to the amendment evels indicated on Hawker Beechcraft TCOS Revision 26 Part 25 Amendment 25-1 through 254010 the above applicable requirements. 10. CERTIFICATION - Under autheety vested by dicta of the Aginised.tralos and in accoidanos mut oancalons and Irniteikos of appointment under 14 CFR Pan 163 of the Federal Aviation Regulations. data had above and on earthed sheets numbered bib have been examined In accadance wah established procedures and found to comply with applicable minx...nye. of the ArrortIvress Standard. twee 1 (We) Therefore approve these data. II. SIGNATURE( ES1SNATE ENO TERNCREPRESENTATIVELO 12. OESGNAllON NUMIIEFtS(S) 13. CLASSIFICATION(S) .- Da ML DERT.230019-CE Systems end Slut:more orm 6110.3 (Oahe) SUPERSEDES PREVIOUS EDITION CP0901413 SDNY_GM_02 758248 SUBJECT TO PROTECTIVE ORDER PARAGRAPHS 7, 8, 9, 10, 15, and 17 EFTA_00245170 EFTA01261830 SDNY_GM_02758249 SUBJECT TO PROTECTIVE ORDER PARAGRAPHS 7, 8, 9, 10, 15, and 17 EFTA_00245171 EFTA01261831 7 I 6 I 5 4, 4 I 3 1-4,6 Na 'ARCS URAles CO-PLT BOSE show as red band RN L040 O Mr rift O EmERGETCT O LW LOAD O BLACK OP NO CO. n• NON-ESSENTIAL Zio-ar• 166"65 7 rcgray 0000 BM IS UV goy. —.,•••• p00000000 Mall C irte•-"gt PLT BOSE show as blue band remove text and show no band FADEC PNL COLOR/VERBAGE (WITHOUT SHADES, WITH BOSE) a I 7 I 6 I 5 4 ••• I"6 6 .71 . 446 LW WI CI 1 1 11 3 TOM SDNY_GM_02758250 SUBJECT TO PROTECTIVE ORDER PARAGRAPHS 7, 8, 9, 10, 15, and 17 EFTA_00245 I 72 EFTA01261832 SDNY_GM_02758251 SUBJECT TO PROTECTIVE ORDER PARAGRAPHS 7, 8, 9, 10, 15, and 17 EFTA_00245 I 73 EFTA01261833 0 MAJOR REPAIR AND ALTERATION u9 tornathril rr (Airframe, Powerplant,Propeller, or Appliance) no awn' AVallOrl AtleinIstatOn Fenn neennee cm no atooNo wormer thecoonic Tracking Number For FM Use Only INSTRUCTIONS: Print or Ithas all envies. See FAR 43.9. FAR 43 Appetite( B. and AC 43 thi (or subsequent revision 0100200 for manctions and disposition of this form. Tras report is :pewee by law (49 U.S.C. 1421). Fetus to report can Mee in a deal penalty AO( lo exceed 51,000 Weeds such violation (Sefton 901 Federal Avarice) Act 1958) I. Aircraft Nationality and Registration Mark N787TA Seas No. RK-260 Make Raytheon Aircraft Company 400A MOON 400A Stiles 2. Owner Name (As ShOWI1 on regranition militate) Flight Options .LLC Address (As shown on rethUratrOn corattifth MOMS. 26180 Curtiss Wrioht PKWY cot Richmond Heights swe OH Lo 441 4 3 . 14M DU*, !1 3. For FAA Use Only V. Type S. Unit Identification Repair Alteration Unit Make Model Serial Ns.mtcr O I21 AIRFRAME (As described in Rem I above) . • PONIERPLANT O O PROPELLER O O I APPLIANCE Type MettvJaef I. Canteen-lit( Statement A Agency's Name and Atkins; B. Kbd &Agency Nave Nextant Aerospace O U.S. Cenolicated Mechanic O IManufactuna mane [ADDRESS REDACTED] O Foreign Cerarcatea Mechanic C. Certificate No. Fe, Cleveland Slab OH 0 Certificated Repair Station ze 44143-1453 cooing USA O Certificated Maintenance Organirabon CRS 4 25NR667B a I only that the regal, and/or Merton made to the unit(s) witness in gem sante and oesossed en the 'menace MaChments hereto have been made A accordance v«th the 'millennia of P rt 43 of tie U.S. Federal Avation Regulations and that the infcvmatin furnished herein Is true and correct to the best of my knowledge. Extended range fuel par 14 CFR Part 43 none O SignaturelOale of Aulhorladivia% 24: I A.Ockwell • k,.. \ 01/08/2013 7. Approval for Return to Service Pursuant I the authority given persons specified below. the unit icienMed in item AdmiliStrernt of Me Federal Aviaton At:Minim:3ton and is 0 APPROVED 5 was In inspected in the manner prescribed by the REJECTED FM Fit Standards Inspector Manufacturer Maintenance Organization Pc-son Appnwed by Canadian Detente.' of Transport BY FM Designee X Repay Sefton insmaica Authalzation other Mean Certificate or Oesignabon o. C R S et 25NR667B SignatureMate of Authorized A.Ockwell ../ a l at )LikCk 01/08/2013 FAA Form 337 (10-06) SDNY_GM_02758252 SUBJECT TO PROTECTIVE ORDER PARAGRAPHS 7, 8, 9, 10, 15, and 17 EFTA_00245174 EFTA01261834 SDNY_GM_02758253 SUBJECT TO PROTECTIVE ORDER PARAGRAPHS 7, 8, 9, 10, 15, and 17 EFTA_00245 I 75 EFTA01261835 NOTICE Weight and balance c operating limitation changes shaft be entered ill the appropriate a:ceraft record An alteration must to compatible with ail previous alterations to assure continued confemzely with the applreable airworthiness requirements. 8. Description of Work Accomplished (Union, space is required, attach additional sheets. identify with aircraft nalionatity and refastration mark and date work completed) N787TA Nations/4y and Registration Mark 1/08/2013 Date Replaced Dayton Granger Static Wick 16305 with Dayton Grainger Part Number 74001 This was FAA Approved on an 8110-3 by Dan Buzz DER-T 230019-CE on Jan 08 2012 Using Neztant Aerospace Engineering Order 1123 Dated 12/26/2012. ICA Changes to weight and Balance are negligible Continue with Normal Hawker Beech 400A Inspection requirements End 0 Additional Sheets Are Attached FAA Form 337 00431/1 SDNY_GM_02758254 SUBJECT TO PROTECTIVE ORDER PARAGRAPHS 7, 8, 9, 10, 15, and 17 EFTA_00245 I 76 EFTA01261836 SDNY_GM_02758255 SUBJECT TO PROTECTIVE ORDER PARAGRAPHS 7, 8, 9, 10, 15, and 17 EFTA_00245 I 77 EFTA01261837 U.S. DEPARTMENT OF TRANSPORTATION FEDERAL AVIATION ADMINISTRATION STATEMENT OF COMPLIANCE WITH AIRWORTHINESS STANDARDS 1. DATE 1.8-2013 AIRCRAFT OR AIRCRAFT COMPONENT IDENTIFICATION 2. WAKE Hawker Ereethcraft 3. MODEL NO. 400A SIN RK.260 Only 4. TYPE (ROW* Redo. Nettopfer. at) Airplane S. NAME OF APPLICANT Nextant Aerospace LI.0 LIST OF DATA 8. IDENTIFICATION 7. TITLE Nextant Aerospace Document EO 1123 dated 12/26/2012 Engineering Order Replace DIG 16305 Static Wick with 740001 END This approval is for the electrical systems aspects only. 'This approval Is for engineering design data only and is not an installation approval. It indicates the data listed above demonstrates compliance only wilts the regulations Specked by paragraph and subparagraph listed below as 'APPLICABLE REQUIREMENTS' (Compliance with additional regulations not listed here may be required). This form does not constitute FAA approval of all the engineering design data necessary for substantiation of compliance to necessary requirements for the entire alteration.' a. PURPOSE OF DATA Support major alteration to aircraft Hawker Beechcraft 400A RK-260 Only. 9. APPUCABLE REQUIREMENTS got speedy secret's) 14 CFR 25.13010X<HORIGI Note: Compliance has been found to the amendment levels indicated on Heater Beechcraft TCOS Revision 26 Pad 25 Amendment 25-1 through 25-40 to the above applicable requirements. 10. CERTIFICATION - Under authority vested by erection of the Administrator and in accordance with condaions and Iknaations of appointment under 14 CFR Part 183 of the redifinAViatiOn RegtAati0119. data listed above end on attached sheets nbotered WA have been esernined in accordance with established procedures and found to comply with applicable requirements of the Airworthiness Standards listed. I (We) Therefore approve those data. II SiGNATURE S F SIG D ENGINEERING REPRESENTATNE(S) 12. DESIGNATION NUMBERS(S) 13. CIASSIFICAIION(S) (Wier L. Ouse L5" CERT-2300I9-CE Systems and Equipment 0 (03 0) SUPFASEDESPREVI Id GPO 901 OM SDNY_GM_027582S6 SUBJECT TO PROTECTIVE ORDER PARAGRAPHS 7, 8, 9, 10, 15, and 17 EFTA_00245178 EFTA01261838 SDNY_GM_02758257 SUBJECT TO PROTECTIVE ORDER PARAGRAPHS 7, 8, 9, 10, 15, and 17 EFTA 00245179 EFTA01261839 • 0 MAJOR REPAIR AND ALTERATION S Creenn co (Airframe, Powerplant, Propeller, or Appliance) if in, #3••••• F•O•rat •••••• shmeseseen ram Amaral wash 2120.0020 02007 Electra* Tracking Number For FAA Use Only INSTRUCTIONS. Print Or type ell entries. Sew FAR 43 ft, FAR 43 Appendix ES arid AC 43.9-1 for subsequent resittion thereo° for instructions and discosillai or INS form. This report Is red** by law (49 U S.C. 1421). Failure to report can result in a civil penalty not to exceed 91.000 for each such violation (Section 901 Federal Aviation Act 1958) 1. Aircraft Mationatity and Registration Mark N787TA Serial No. RK-260 Make Raytheon Aircraft Company 400A Steel 400A Setts 2. Owner Name (As shoe, on registration certificate) night Options. LLC Address (As shown on regetfatiOn Cethealt) earn 26180 Curtiss Wright PKWY Co, Richmond Heights sin OH ro 44143-1453 caster USA 3. for FAA Use Only 4. ype S. Unit Identification Repair Metall* Unit Make Mend Serial Number o ig AIRFRAME (As desistedkr Item I above) 0 O POWERPLANT 0 O PROPELLER 0 IN APPLIANCE Tow Manufseeser IL Conformity Stabtment A Agency's Name and MTh. B. thnd of Agency Nome Nextanl Aerospace Address 355 Richmond Road Car Cleveland Stet OH re 44143-1453 wary USA 0 U.S. Certificated Mechanic 0 I Manulactteer C Foreign Certificated Mechanic C. Certificate No. e Certificated Rep* Slahon CRS # 25NR667B 0 Certificated Maintenance Organization D. I Gently that the repair andfor alteration made to the uni(s) identified in tem 5 above and described on She reverse or attachments hereto have been made In accordance with the requirements ol Pan 43 of the U S. Federal Aviation Regutallons and that De infotmalien furrished herein is true and correct to the best of my knoniedge. Exterseed Mega fur per ta CFR Part 43 APP. B 0 SDnalurarDale of A e -411 A.Ockwell zed i / 01/04/2013 7. Approval for Return to Service Pursuant to the authority given persons specifed bekm, the unit Men AdrninistratOr Of the, Federal Aviation AdminiShation and is 0 Med Innen' ti was Yowled in Use manner prescribed hythe APPROVE° 0 REJECTED BY FAA Flt Standards Inspector Maintenance Organization Person Approved by Canadian Manufacturer Department of Transport FAA DeSicree X Repair Station inspirit* Aulhorizahon Other (Speedy) Certificate or DeSenaliOn NO. CRS tt 25NR6678 SignaturerDate of Authirlial inthrinZ , A.Ockwell 01/04/2013 FAA Form 337 (t006) SDNY_GM_02758258 SUBJECT TO PROTECTIVE ORDER PARAGRAPHS 7, 8, 9, 10, 15, and 17 EFTA_00245 I 80 EFTA01261840 SDNY_GM_02758259 SUBJECT TO PROTECTIVE ORDER PARAGRAPHS 7, 8, 9, 10, 15, and 17 EFTA_0024518 I EFTA01261841 NOTICE Weight and balance or operating &Melina changes shall be entered in the appopriate aircraft record. An afteration must be compatible with alt previous alterations to assure continued conformity with the applicable airworthiness requirements. 8. Description of Work Accomplished (If mom space Is required, attach additional sheets. Identity with aircraft nationally and registration mark and date work completed.) N787TA Nationally and Registration Mark Title: Ice Detector Master Caution / Master Warning Light on Constantly Re-Installed the previously removed components ( Ref 5/8 30-2600, Rev 2) 01/04/2013 Date 1.) Isolation Relay K255 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 E0 corrections on E0 page 2 See FAA Form 8110-3 signed by Daniel Buzz DERT - 230019-CE. Dated 8-13-2012 and Nextant Aerospace Engineering Order E0 130.12 Rev D. Dated 7-18-2012 ICA Weight and Balance Changes are Negligible Continue to Use Existing Beechjet 400/400AMaintenance Manuals Inspection Procedure for this Area END El Additional Sheets Are Attached FAA Form 337 Mal SDNY_GM_02758260 SUBJECT TO PROTECTIVE ORDER PARAGRAPHS 7, 8, 9, 10, 15, and 17 EFTA 00245182 EFTA01261842 SDNYGM02758261 SUBJECT TO PROTECTIVE ORDER PARAGRAPHS 7, 8, 9, 10, 15, and 17 EFTA 00245183 EFTA01261843 U.S. DEPARTMENT OF TRANSPORTATION FEDERAL AVIATION ADMINISTRATION STATEMENT OF COMPLIANCE WITH AIRWORTHINESS STANDARDS 1. DATE 8-13-2012 AIRCRAFT OR AIRCRAFT COMPONENT IDENTIFICATION 2 MAKE Hawker thseencraft 3. MODEL NO. 400A SIN Ft1G260 Only 4. TYPE (Akprent Radio. lfeht0Cet. at) Alfplane 5. NAME OF APPLICANT Nolant Aerospace LLC UST OF DATA O. CENTIFCATION T. TRIE Neaten( AerC49812 Document 130-12 dated 7-18-12 Rev. 0 Engineering Order Ice Detector htCAINI Light On Constantly END This approval is for the electficat systems aspects only. 8. PURPOSE OF DATA Support Male( alienation to aircraft Hawker Reechcraft 400A RK-260 Only. 9. APPLICABLE REQUIREMENTS psi sPeotTesecobrol 14 CFR 25.1301(a) R3iig1 Note: Compliance has been found to the amendment levels indicated on Hawker Beecbcraft 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 Imitations of eppoiNmenl undo' 14 CFR Parl 183 of the Federal Aviation Regulations. data listed above and on attached sheets numbeltd INS have been examined In accordance Kith established procedures and found to comply with applicable requkements of the Ainvortheness Standards hated. I (We) Therefore approve these data. 11. SIGNATURE( • S1GNATEDENCANEERING REPRESENTATNE(S) 12. DESIGNATION NUMBERS(S) ter. CIASSIFICATION(SI - Daniel L. Buzz DERT-230019-CE Systems and Equipment arm 81104 (03110) SUPERSEDES PREVIOUS EDITION OPOS01413 SDNY_OM_02758262 SUBJECT TO PROTECTIVE ORDER PARAGRAPHS 7, 8, 9, 10, 15, and 17 EFTA_00245184 EFTA01261844 SDNY_GM02758263 SUBJECT TO PROTECTIVE ORDER PARAGRAPHS 7, 8, 9, 10, 15, and 17 EFTA_00245 I 85 EFTA01261845 e l , MAJOR REPAIR AND ALTERATION u.S omarwerr or (Airframe, Powerplant, Propeller, or Appliance) eamemation Foss Admen Amonhinosin Fain Approves Om No. zia34020 iv307037 EftdrOrOC Tracking Number For FAA Use Only INSTRUCTIONS. Print or type all envies. See FAR 43.9. FAR 43 Apperclix 4). and AC 43151 (or subsequent revision thereof) fel InUnctienfr and dispcierlicei d this lone. This repel is required by law (49 U.S.C. 1421). Failure to report can result in a civil penally net to exceed $1.000 ler sad i such vitiation (Section 901 Federal Aviatrix, Act 1956) 1. Aircraft Nadariatty and RegiStralice Mark N787TA Serial No. RK-260 Make Raytheon Aircraft Company 400A Model 400A Series 2. Owner Name (As Shown an registration cwMcare) Flight Options .LLC Address (As shemn on registration cerrifice4e) milieu 26180 Curtiss Wright PKWY Ley Richmond Heights Sum OH zu 44143-1453 catty USA 3. For FAA Use Only 4. Tree S. Unit Identification Repair Menace Unit Make Model Serial Number 0 0 AIRFRAME (As desaibec 1 in !rem 1 above) 0 O POWEFtPlANT 0 El PROPELLER O El APPLIANCE Type Merulidunir 6. Conformity Statement A. Agency's Nam. and Address B K rid of Agency None Nextant Aerospace Maass [ADDRESS REDACTED] en, Cleveland swim OH zip 44143-1453 cowry USA 0 U.S. CerliReated Mechanic O 'Manufacturer O Foreion Certificated Mechanic C. Cervical. No. 0 Certificated Repair Station CRS # 25NR6675 0 Certificated Maimenarce Organization D. I cone/ that the repair andfor adoration male lo ate unit(S) Identified In gem 5 above and described on the reverse or attachments herelo have been made in accordance am IM requirements of Past 43 ti the U.S. Federal Aviation Regidatons and that the information fumIsted herein is live and correct to the best of my knowledge. Edended range fuel per 14 CFR Part 43 APP. S O Signatureftlate of Authorized A.Ockwell . _ • 0.-- 01/04/2013 7. Approval ler Return to Service Pursuant to the authority given persons seemed bedew. the Untlidenefecl in item 5 was inspetted in the matte. prescribed by the Administrator of the Federal Adabon AdministrabOn and a ®APPROVED 0 REJECIEO BY FM FR Standards irSpeCtOf Mani/Winer Maintenance Omandalion Person Approved by Canadian Department of Transpxl FM Designee X steses mason inspection Automation OCIO. (Spock(Y) Certificateor Designation No. CRS # 2SNR6878 SignaftweVale c4 Authorized Ind' A.Ockwell 01/04/2013 ii FAA Form 337 °ono SDNY_GM_02758264 SUBJECT TO PROTECTIVE ORDER PARAGRAPHS 7, 8, 9, 10, 15, and 17 EFTA_00245186 EFTA01261846 SDNY_GM_02758265 SUBJECT TO PROTECTIVE ORDER PARAGRAPHS 7, 8, 9, 10, 15, and 17 EFTA_00245 I 87 EFTA01261847 • NOTICE Weight and balance a operating limitation changes shalt be entered in the appropriate aircraft record. An alteration must be compatible with alt previous aRerations to assure continued calamity with the applicable ainvorthiliess requirements. 8. Description of Work Accomplished (((more space is required, attach additional sheets Wady with aimed' noticeably and registration meth and date work completed) N787TA Nationakty and Registration Mark Incorporated the following Cockpit Glareshield Repair Procedure. 01/04/2013 Date Removed the Cockpit Glareshield and installed the following parts to reinforce the Glareshield. REO051-11-06, NXRP45A88736.103, NXRP45A88736-102. Reinstalled the repaired Glareshield IAW HBC 400A Maintenance Manual 31-10-00-201. See Attached FAA Form 8110-3 signed by DERT-410115-CE Paul Hedding Dated December 05, 2012 using Nextant Aerospace Engineering Order EO118-12. Rev C. Dated January 30, 2012. ICA Weight change is Negligible. Continue with Beechjet 400/400A Maintenance Manual Inspection Procedures End Additional Sheets Are Attached FAA Form 337 twat SDNY_GM_02758266 SUBJECT TO PROTECTIVE ORDER PARAGRAPHS 7, 8, 9, 10, 15, and 17 EFTA 00245188 EFTA01261848 SDNY_GM_02758267 SUBJECT TO PROTECTIVE ORDER PARAGRAPHS 7, 8, 9, 10, 15, and 17 EFTA 00245189 EFTA01261849 V.S. DEPARTMENT OF TRANSPORTATION FEDERAL AVIATION ACOANISTRATICN STATEMENT OF COMPLIANCE WITH AIRWORTHINESS STANDARDS 1. DATE December 5, 2012 AIRCRAFT OR AIRCRAFT COMPONENT IDENTIFICATION 2. MAKE Hawker Beechcraft Corporation 3. MODEL NO. 400A P. TYPE (Mtn& Engine. Propellor. tee) Aircraft SNARE OF APPUCANT Nextant Aerospace LLC Richmond Heights, Ohio LIST OF DATA A OFNIWICATEN 7 TITLE EO 118-12 Rev. C January 30, 2012 Repair Glaresheild Procedure. ' — 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 fisted below as 'Applicable Requirements! 2) This form constitutes FM approval of all the engineering data necessary for substantiation of compliance to necessary requirements for Me entire alteration. a PURPOSE OF DATA Engineering data in support of major alteration to Hawker Beechcraft 400A, S/N RK-260. 9 APPLICABLE REQUIREMENTS (List 'flab sections) CFR 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[25.23], and 25.625(a)(b)(c)(25-23]. 10 CERTIFICATION • under aultanty vested by cerecito of the MITIMIIIII0C and in exerdencs win OMEN% end simian at appointment under 14 CFR Past ID. seethed atom and on attached sheets numbered N/A hose been mermlned In act0rdarge wIll estifeshed procedures and found b wryly wen oversee% recesitetnentsol the ASeccIleness Sividards tatted. 0 Recommend approval Online data I (WO Thefefere 0 Approve ono data II. SIGNATUREIS1OF DESIGNATED ENOMEERING REPRESENTATIVEIS) 12. DESIGNATION NialaBERSIS) I3- CLASSIFICATION(5) osts,..e.“4,7_. Paul Hedding DERT-410115-CE Structures FM Form 6110-3 103-10) SUPERSEDES PREVIOUS EDITION Fie Number IMISISOS Paige 1 eft SDNY_GM_02758268 SUBJECT TO PROTECTIVE ORDER PARAGRAPHS 7, 8, 9, 10, 15, and 17 EFTA 00245190 EFTA01261850 SDNY GM 02758269 SUBJECT TO PROTECTIVE ORDER PARAGRAPHS 7, 8, 9, 10, 15, and 17 EFTA_00245191 EFTA01261851 0 MAJOR REPAIR AND ALTERATION ultereaserre or (Airframe, Powerplant, Propeller, or Appliance) Tenspaunen tearer Aolookm Adaithouvaer. ram rowans 01.3 No 21700M os192407 Somme TWIN) Number Foe FAA Use Only INSTRUCTIONS: Print or type all enbies. See FAR 43.9. FAR 43 Appendix 6, and AC 43.91 (or subsequent reveren theme) roe 1400:11Orn as *apostle.) ef Ws Icon. TN, report is required bylaw (49 U.S C. 1421). FORM 10 WWI Can mall in a cud penally not lo exceed 11.000 for each such Ncration (Section Sot Federal Avialbn Ad 1954) 1. Aircraft Nationality and Registratkei Mark N71)7TA Serial No. RK-260 Make Raytheon Aircraft Company 400A Model 400A Series 2. Owner Name (As shown on registration tee &NV Flight Options .LLC Address (43 shown on ntonuranon derldaElp Address 26180 Curtiss Mich, PKWY ay Richmond Height5 met OH zy, 46143-1451 County oe, 3. For FAA Use Only 4. Type 5. Unit klentfficallon Repair Menace Us Make Model Serial Number III 74 AIRFRAME Ma descnbed in hem t above) • O POWERPLANT • O PROPELLER • CI APPLIANCE Toe Menurecrurto 6. Conformity Statement A Agency; Name and Address B. KM of Agency Nn Neulan! Aerospace Address [ADDRESS REDACTED] cony USA 0 U.S. Cerldcated Mechanic 0 IManufacturer 0 Fereign Certificated Mechanic C Generate NO ® CerlAcated Repair Station CRS # 25NR667B 0 Cerlificated Maintenance Organdation D. I unify INN the repair andlor alteration made to the uni(s) idemaiod in tem 5 stove and described on Me reverse or attachments hereto have been made in acCordante vie the requirements of Pail 43 ot the U.S. Federal Aviation Regulations and that the information Nrnished heroin is true and correct to the best of my knowledge. Extended range fuel pet 14 CFR Pan 43 App. ll 0 Signature/DM. Of AultiOrlied A.Ockwell ..Ci- 01/04/2013 7. Approval for Return to Service Pursuant to the authority given persons specified be:ow, the inn ;den hied in item S was inspected In the manner preseMed by the Administrator of Lae Federal Aviation Adniintstraban and is ®APPROVED 0 REJECTED BY FM F1 Standards Inspector Manuracurer Mainlename Organize:3w Person Approved by Canadian Department of Transport FAA Desiree X Rear Stabon InspeakinAulhonzation Olher Space?) Certificate or Designation No. CRS N 25NR6e713 Sign !ureic/ale of Authorized Indi A.Ockwell 01/04/2013 FAA form 337 NOM SDNY_GM_02758270 SUBJECT TO PROTECTIVE ORDER PARAGRAPHS 7, 8, 9, 10, 15, and 17 EFTA 00245192 EFTA01261852 SDNY_GM_027513271 SUBJECT TO PROTECTIVE ORDER PARAGRAPHS 7, 8, 9, 10, 15, and 17 EFTA 00245193 EFTA01261853 NOTICE Weight and balance or operating NIMI8li011 changes shall be entered in the appropriate aircraft record An alteration must be corrpalible with se previous alterations to assure continued conformity with the applicable airworthiness requirements. 8. Description of Work Accomplished (if more space is required. attach additional sheets. Identity with aircraft nationality end registration mark and date wadi completed.) 01/04/2013 I N787TA Nationality and Registration Mark Provisions for 19107 in Cockpit Sidewall at F5122.735 Date Added mount provisions for 19107 in bracket assy. 45488588-3 at Flight Station 122.735 provided in Structure Repair Manual Document 53-20-05-001. Use receptacle PAS3470W18. See attached FAA Form 8110-3 Signed By OERT-410115-CE Paul Hedding. Dated May 14, 2012 using Nextant Aerospace Engineering Order 115-12 Rev B, Dated April 04. 2012 for details. KA Weight change is Negligible. Continue with Beechjet 400/400A Maintenance Manual Inspection Procedures. End ZAdditional Sheets Are Attached FAA Form 337 (lea) SDNY_GM_02758272 SUBJECT TO PROTECTIVE ORDER PARAGRAPHS 7, 8, 9, 10, 15, and 17 EFTA_00245 I 94 EFTA01261854 SDNY GM 02758273 SUBJECT TO PROTECTIVE ORDER PARAGRAPHS 7, 8, 9, 10, 15, and 17 EFTA_00245 I 95 EFTA01261855 V.S. DEPARTMENT Of TRANSPORTATION FEDERAL AVIATION AOMMSTRATKIN STATEMENT OF COMPLIANCE WITH AIRWORTHINESS STANDARDS 1. GATE May 14, 2012 AIRCRAFT OR AIRCRAFT COMPONENT IDENTIFICATION 2. MAKE Hawker Beechcraft Corporation 0. MODEL NO. 400A 4. TYPE (Aircraft &Ora. N0W*: Bb) Aircraft S. NAVE OF APPLICANT Nextant Aerospace LLC Richmond Heights, Ohio LIST OF DATA B CFNTFICATION 7 TITLE EO 115-12 Rev. B April 4, 2012 Mount Provisions for J9107. END- Notes: 1) The structural aspects only of the above listed data we 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 reqUrements for the entire alteration. s. PURPOSE OF DATA Engineering data in support of major alteration to Hawker Beechcraft 400A, SIN RK-260. 9. APPLICABLE REQUIREMENTS (Usi ssecatIc sections) CFR Title 14 Pad 25.301(25-23), 25.303(25-23), 25.305(a)(b)(c)(25-23), 25.307(x)(25-23), 25.601(25.00), 25.603(a)(b)(c)125-38). 25.6o50H25-001, 25.607(25-23), 25.609(a)(b05-00), 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 litiewiria waled by direction SIM Administrator and in accorearva ?Mils ccorialont and limations of impciaonent ulcer 14 CFR Pan too data AMC mem end on attathad then numbered S&. nave been mainined h accordance with established Frocedures tad bond to comply with applicable requirements ol th•AirstrINnesit standards LIMO 0 ReCommeod approvM of these data I 8W Therekto al Approva those data II. $18NATURE(S) OF DESIGNATED ENGINEERING REPRESENTATNE(S) IT. DESIGNATION NIJMBERMS1 IT. CLASSIFICATION(5) Pre.24.9 Paul Hedding DERT-410115-CE Structures FAA EOM, 81103 (0110) SUPERSEDES PREVIOUS EDRION Fla Number: H12259-25 Page I Ml SDNY_GM_02758274 SUBJECT TO PROTECTIVE ORDER PARAGRAPHS 7, 8, 9, 10, 15, and 17 EFTA_00245 I 96 EFTA01261856 SDNY_GM_02758275 SUBJECT TO PROTECTIVE ORDER PARAGRAPHS 7, 8, 9, 10, 15, and 17 EFTA_00245 I 97 EFTA01261857 0 MAJOR REPAIR AND ALTERATION u.S Ommeemer (Airframe, Powerplant, Propeller, or Appliance) Tempo-en roma ammo iumeninmen rum rimmed over no ernes 1 irdiadom EleMoNc Tracking tine For FAA Use Only INSTRUCTIONS: Print or type all AAA. See FAR 43.9, FAR 49 Appendx B. and AC 4341 (or subsequert revision thereof) for instructions and diSpollmn Of tNS norm. This report is remind try km (49 U.S.C. 1421). Forum to report can result A a civil penalty not to erceed91.000 Fix each such Wagon (Sedan 901 Federal Aviation Ad 1959) I. Aircraft Nalionikty and Reghtralion Mark N787TA Sena' No. RK-260 Make Raytheon Aircraft Company 400A Model 400A series t. 0vmer Name (As shown on registration certdcad Flight Options .LLC Address (As shown on registration Ferrate') A6311$:. 26180 Curtiss Wright PKWY coy Richmond Heights slow. OH zo 44343-1451 Comm QM 1. For FAA Use Only 4. Type 5. Unit Identification Repair Alteration Unit Make Model Serial Number' 0 [23 AIRFRAME (As described in bent 1 above) 0 a POWERPLANT o O PROPELLER El El APPLIANCE Tam siuntiracur S. Conformity Statement A Agency's Name and Address B. IMAMAgency tax. Nextant Aerospace mous [ADDRESS REDACTED] cows USA O u.S. Cenidcafed Mechanic O IManutadurer O Faragn Certificated Mechanic C. Coruscate No. Ca Certificated Repay Slaps CRS * 25NR667B O Ceruncate4MarilenaneOrgsnizalkri D. I certify that the repair enclitic alteration made to the und(s) *Wined in den 5 Move an:tete:awe on the reverse or atiachmentS hereto have been made in accordance 'AEI the reouirements of P n 43 of Me U.S. Federal Aviaton Regulations and that the Montalto(' Nrnished herein Is We and correct to the best of my knoMedge. Extended range fuel per 14 CFR Part 43 APP. B • Signalmen/ale of Authorized Intivid A.Ockwell (.t— 01/04/2013 7. Approval for Return to Urines Pursuant to the NAM:My given persons speoted below. In. unit Mien Fred in item 5 was ',spasm° in the manner prescribed by the ADMINSTTRIO( dee Federal ARabOrl ATIMINOTECCR and Is CAI APPROVED 0 REJECTED BY FAA Fit Standards Inspector IMIWIDCILITED Maintenance Organ: Mon Person Approved by Canadian Depanmen1 of MIAOW FAA Desire° X Repair Station inspection Aulhorlistion Other (SAMOA CertAcete or CletignaCon No. CRS a 25NR6878 Sign wreDate of Authorized nrclvidu A Ockwell . 01/04/2013 FAA Form 337 /10-0th SDNY_Glvl_02758276 SUBJECT TO PROTECTIVE ORDER PARAGRAPHS 7, 8, 9, 10, 15, and 17 EFTA_00245198 EFTA01261858 SDNYGM02758277 SUBJECT TO PROTECTIVE ORDER PARAGRAPHS 7, 8, 9, 10, 15, and 17 EFTA_00245 I 99 EFTA01261859 NOTICE Weight and balance or operating limitation changes shall be entered in the appropriate aircraft record. An alteration must be compatible with all previous afferabons to assure Continued conformity with the appCcable airworthiness requirements. 8. Description of Work Accomplished 11I more space is required, attach additional sheets. Identify with aircraft nationality and registration mark and date work compkted.) NTSTTA Nationality and Registration Mark Installed Alternative Fuel Cap Screws in U14 and R/H Fuel Cap Removed the NAS517-3-3 Screws and Installed MS34694 —050 01/04/2013 Oats This was FAA Approved by Robin Harrison DERT-605234-NM on FAA 8110-3 Dated 06 December 2012 using Western Aerospace Engineering Order 083-11. Rev C Dated Nov 09.2011 ICA Weight and Balance changes are negligible Continue with Normal Hawker Beechjet400A Maintenance Manual Inspection Requirements for this Area End . Additional Sheets Are Attached FAA Form 337 (10-06) SDNY_GM_02758278 SUBJECT TO PROTECTIVE ORDER PARAGRAPHS 7, 8, 9, 10, 15, and 17 EFTA_00245200 EFTA01261860 SDNY_GM_027513279 SUBJECT TO PROTECTIVE ORDER PARAGRAPHS 7, 8, 9, 10, 15, and 17 EFTA_00245201 EFTA01261861 U S DEPAPI WENT OF TRANSPORTATION FEDERAL AVIATION ADOMPSTRATION STATEMENT OF COMPLIANCE WITH AIRWORTHINESS STANDARDS I. DATE 06 December 2012 AIRCRAFT OR AIRCRAFT COMPONENT IDENTIFICATION 2. MAKE. Hawker Beechcraft 3. MODEL NO. 400A (see note 3) 4. TYPE Wreak Engine. Ptoceete, etc) Airplane A 5. NAME OF APP SCANT Nextanl Aerospace (see note 4) LIST OF DATA I. DENTIFICATION 7. ITrLE Nextant Aerospace Alternate Fuel Cap Screws. QS/GUMMI: E0 NO. 083-11 Rev. C Date: 09 Nov. 2011 -end Notes: 1. Detail Design and Structural Approval only. 2. This approval indicates the data listed above demonstrates compliance only with the regulations specified by paragraphs and subparagraphs listed below as 'Applicable Requirements? Compliance to adational regulations not listed here may be required. This form DOES NOT constitute FM approval of all the data necessary for substantiation of compliance to necessary requirements for the entire alteration/repair. This approval is only for the engineering design andlor substantiation data. It is not an installation approval. 3. Model: Hawker Beechcraft 400A (Raytheon Beethjet), identified by FM TCDS No. A16SW. 4. Applicant: Nextant Aerospace, 28180 Curtiss Wright Pkwy. Cleveland, OH 44143 U.S. LLC 25NR6678. 5. Applicable aircraft: RK-001 thru RK-999. except RK-279, 108, 028, 274. 295. 230, 292, 123, 225. 137, 248, 289, 310, 252, 195, 239, 284, 368, 334, 327, 146, 260 and 413. s. PURPOSE OF DATA To show compliance with applicable regulations in support of a Major Repair/Alteration FAA Form 337 Approval for Alternate Fuel Cap Screws, Repair for Nextant Aerospace • Hawker Beechcratt 400A Model Aircraft SIN identified by Serial No's listed in Note 5. above. t APPUCASLE REOUIREMENTS Arriassawssesonsi 14 CFR, PART25 paragraphs: 25.305(a)(b) Arndt. 25-86; 25.307(a) Arndt. 25-72; 25.601 Amdt. 25.0; 25.6036006(c) Arndt. 25.46; 25.605(a) Arndt. 25-46; and 25.609(a) Amdl. 25-0. 10. CERTIFICATION 103. dale aall0re t (Wt - Undm avinorlly 'SRO abets Ind on attached romiternents of Me AMedhlneSS Therefore 0 Recommend vested toy <Peden or Me AdrMlafraler and In accordance sheds nuMmed no have bean examinedIn weN corollons Inc Ilrndarlons of appoloyntel tinder 14 CFR Pan accordance old+ eslatihrted procedures and Mond to empty *Kb Siandards forted. approval of these data these data Approve 11. SIGry.c/f/ (S) OF DEVON Ell ENGINEERNO REPRESENTATIvE(S) 12DESIGNATION NUMBER(S) II CLASSIFICATIONS) DERT-605234 i I -NM Structures , R in Harrison FM FORM is TO3 I0)10) SUPERSEDES PREVIOUS EDITION SDNY_GM_02758280 SUBJECT TO PROTECTIVE ORDER PARAGRAPHS 7, 8, 9, 10, 15, and 17 EFTA_00245202 EFTA01261862 SDNY_GA0102758281 SUBJECT TO PROTECTIVE ORDER PARAGRAPHS 7, 8, 9, 10, 15, and 17 EFTA_00245203 EFTA01261863 0 MAJOR REPAIR AND ALTERATION u s 401111rOM Of (Airframe, Powerplant,Propeller, or Appliance) TorsprOort rose Atrellen AcrroolsbalrOn Fon Appro.:I OMB No. 2i200020 lux:air Electra* Traddng Number For FAA US4 OnlY INSTRUCTIONS: Printer type as entries. See FAR 43.9, FAR 43 Await 8, and AC 43.9-1 (or subsequent revision Mewl) tor instructions and dePosiezin of this kern. This MOM dr required by law (40 U.S.C. 1421). Faire to repel fan result in a civil penalty not to exceed 31000 to each Arm *56m (Section 001 Federal Aviation Mt 1950) J.Aircraft Nationality and Registration Mark N787TA Serial No. RK-260 Make Raytheon Aircraft Company 400A Model 400A Series 2. Owner name (As Shown on mgistrehise terldIcefe) Flight Options .LLC Address (As shown an s kim den14000) moms 26180 Curtiss Wright PKWY Cey Richmond Heights surto. OH as 4± 1143-1453 cony aL i 3. For FAA Use Only 4. ype S. Unit Identification Repair Memoon Unit Make Model Serial Number 0 El AIRFRAME (As deSeibed in tem l above) El a POWERPLANT 0 O PROPELLER 0 El APPLIANCE Typo itirufaciirer 6. Conformity Statement A. Agency's Name and Address 0 Knd of Agency Herne Rodent Aerospace Add'sts 26180 Curtiss Wright Parkway Cily Richmond Heights Why OH no 44143-1453 carol, USA O US. conecafed mechanic O1 manouccater O Forego Certificated Mechant C. Geniis. No. 0 Certificated Repair Staoon CRS # 25NR667B 0 Certificated Maintenance Organization a I certify thal the repair ancifor einem motto to the unit(s) cleared In dem 5 *Ogre and described on the reVerSOOr attachments hereto have been mode in accordance rem the requirements of Part 43 of the U S. Federal Aviation Requisite's and tnat Me information furnished herein is true and correct to the best of my knowledge Extended ended range fuel per t 4 CFR Part 43 6 O ! of Au Sgnaturo/Date lhonzed KCVO LL A.Ockwell 1P 01/04/2013 7. Approval for Return to Sendai Pursuant to the *Malty given persons weevil below. the unit identified Administrate( of the Federal Aviation Administration and is lire M deco 5 was inspected in the manner prescribed by the APPR4vE0 0 REJECTED BY FM Fl Standards Inspocla Manufacturer Maintenance Organization Palen Approved by Canedian Department ol Transport FAA Designee X Renew Salim Inspection Authorization other (Space) °Mambo or Designation No. CRS X 25NR6878 Signature/Date of Authorized insiduzak A.Ockwell 01104/2013 FAA Form 337 (1006) SONT_GlX_02758282 SUBJECT TO PROTECTIVE ORDER PARAGRAPHS 7, 8, 9, 10, 15, and 17 EFTA_00245204 EFTA01261864 SDNY_GM_02758283 SUBJECT TO PROTECTIVE ORDER PARAGRAPHS 7, 8, 9, 10, 15, and 17 EFTA 00245205 EFTA01261865 NOTICE Weight and balance or operating limitation changes shall be entered in the appropriate aircraft record An alteration must be compatible with an previous alterations to assure continued conformity with the applicable airworthiness requirements. B. Description of Work Accomplished Of more space is required, enact additional sheets. Identify with aircraft nationality and registration mark and date work completed.) N787TA Nationality and Registration Mark Modify Existing GPS/ XM Antenna mounting Doubler plate (P/N 11892.6) Modified Doubler view of drawing RRK279EO052-11-2. 01/04/2013 Date Modification will be comprised of enlarging the aft portion of existing 2" center hole by drilling 0.625" hole spaced per drawing. Radius blends intersecting edge to 2" hole per drawing. This was FAA approved by Paul Hedding DERT-410115-CE on 8110-3 Dated December 05, 2012 using Nextant EO 052-11 Rev B Dated November 13, 2012 ICA Weight and Balance change is negligible. Continue with Beechjet 400/400A Normal Maintenance Manual Inspections for this Area End E3 Additional Sheets Are attached FAA Form 337 (mai SDNY_GM_02758284 SUBJECT TO PROTECTIVE ORDER PARAGRAPHS 7, 8, 9, 10, 15, and 17 EFTA_00245206 EFTA01261866 SDNY_GM_02758285 SUBJECT TO PROTECTIVE ORDER PARAGRAPHS 7, 8, 9, 10, 15, and 17 EFTA_00245207 EFTA01261867 U.S DEPARTMENT OF TRANSPORTATION FEDERAL AVIATION ADIANISTRAMN STATEMENT OF COMPLIANCE WITH AIRWORTHINESS STANDARDS 1. DATE December 5. 2012 AIRCRAFT OR AIRCRAFT COMPONENT IDENTIFICATION 2. MAX! Hawker Beecheraft Corporation S. MODEL NO. 400A 4. TYPE (Maya. Engme. Prope(W etc) Aircraft S NAME OF APPLICANT Nextant Aerospace LLC Richmond Heights, Ohio LIST OF DATA 8 expriFiCATION 7 TITLF EO 052-11 Rev. 8 November 13, 2012 -- — GPS / XM Antenna Doubler Engineering Order. — -- ENO Notes: 1) The structural aspects only of the above fisted 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 fisted 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. a. PURPOSE OF DATA: Engineering data in support of major alteration to Hawker Beechcraft 400A, S/N RK-260. 9. APPLCABLE REOUNTEMENTS Ells scenes wen) CFR Title 14 Part 25.301[25-23). 25.303[25-23), 25.305(a)(b)(c)[25.23), 25.307(a)(25.23], 25.365(a)(b)(c)(d)(f)(g)(25.00]. 25.562(c)(25-23], 25.601(25-00], 25.603(a)(b)(c)[25-36), 25.605(a)(25-On 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[25-321 10. CERTIFICATKIN - Under authceily Parl 183. data Wed above trod on rgyarabe Mesitornonls of the Almonhinens 0 Recommend vested by direction of the AdmentIrraor and In meadow wet condone and Imilailons of appoelleent wider 14 CFR attuned sneers numbered .X6,. have been *rhea In accordant. MP ealaretteed eroadunas and Wed to comply with Standards listed. approval of Mese data Mese data I (We) Therefore 04 Approve II. SIGNARIRE(S)OF DESIGNATED ENGPMERING REERESENTAIIVE(S) 12. DESIGNATION NoLMERS(S) 13. CLASSWICATION(S) ..0.0:5,' 4.,.... Paul Madding DERT-410115-CE Structures FM Form 61104 ((3-10) SUPERSEDES PREVIOUS EDITION Fla Number 111267(504 Paste 1 M1 SDNY_GM_02758286 SUBJECT TO PROTECTIVE ORDER PARAGRAPHS 7, 8, 9, 10, 15, and 17 EFTA_00245208 EFTA01261868 SDNYGM02758287 SUBJECT TO PROTECTIVE ORDER PARAGRAPHS 7, 8, 9, 10, 15, and 17 EFTA_00245209 EFTA01261869 0 MAJOR REPAIR AND ALTERATION mho rinveted 04/13 Nor 21204:020 i oXv2DT ElactfOniCTraCking Number u s oweemed (Airframe, Powerplant, Propeller, or Appliance) Truntrensicn For FAA Use Only fide.. Mimi., ArirnInalrallon INSTRUCTIONS- Print or type all entries. See FAR 43.9. FAR 43 Appendix B. and AC 439.1 (or subsequent revisor, thereon for halfway* and osposition or this tow This cepa o reqdred by law (49 U.S.C. 1421). Filters to repot can made in penally rot to exceed 51.000 for each such ficralica (Section 901 Federal Aviation Act 1993) Wilonakty and Regisimoth Mark N787TA Serial No. RK-260 1. Aircraft Make Raytheon Aircraft Company 400A Model 400A Seems Name (43 show on regIsfragon and/caw Address (As shown on nagishrelion awascare) mann 26180 Curtiss Wright PKWY 2. Owner Flight Options .I. I.0 c,o Richmond Heights surer OH zp 44143-1453 Canto OA 3. For FAA Use Only 4. Typo 5. Unit identification Repair Alteration Unit Make Model Serial Number • L AIRFRAME Ms desenbed in Item I above) D O POWERPLANT D O PROPELLER 0 IN APPLIANCE Thee merMeaucer 6. Conformity Statement k kgOncy'S Name and Address B. It nd of Agency Kane Nextant Aerospace Anon [ADDRESS REDACTED] cows USA O U $ Cent/rated Meehan/0 0 Maninfixer O Foreign cemcatee mechanic C. Cerbrcato No 0 Certificated Repair Station CRS # 25NR6676 O Certificated lAaintrifianCe Organization 13. laitythat the repair aerator atieretion made to the unil(s) identified in item 5 above and described on the reverse or &moments hereto have been meek, aeon:Wee eulti the requirements of Part 43 cd the U.S. Federal Aviation Regulation and that the information bmithed herein iS into and coned IS me best 01 my lutowledge Extended range fuel per 14 CFR Pan 43 APP. 9 0 Siartalure/Da A.Ockwell fe Of AuthOrized IrclivicI ,Lc 01/04/2012 7. Approval /Of Rattan to ServIce Pwsuant to the aulteanty given persons peofiad below. the un I identified in item Atenintstralor 01 the Federal AviettonAdroniseation and is El aPPROWO 5 was inspected in me manner prescribed by the il REJECTED • BY FM Fft Standards Inspector klanufdelliref MainteninC0 Organ:mica Depa rtment Posen APPreved by Carodon of Transport FM Designee X ROOM Station InspectionAuthodzagon Other ESCROW oink*, Or oelignstico sie CRS # 25NR6678 SignaturefDate of AtOnOrizetlIndi A.Ockwell 1,( ,,e 01/04/2012 a. FAA Form 337 1104ced SDNYGfil02758288 SUBJECT TO PROTECTIVE ORDER PARAGRAPHS 7, 8, 9, 10, 15, and 17 EFTA_00245210 EFTA01261870 SDNY_GM_02758289 SUBJECT TO PROTECTIVE ORDER PARAGRAPHS 7, 8, 9, 10, 15, and 17 EFTA_0024521 I EFTA01261871 NOTICE weight and balance or operating frnitation changes shall be entered in the SPOWeanala Aetna retold. An alteration must be compatible with alt previous alterations to assure continued conformity with the applicable airworthiness requirements 8. Description of Work Accomplished Of more space is required, attach addrtional sheets. Identify mth aircraft nationality and registration matt and date work completed.) N787TA Nationality and Registration Mark 01/042012 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. Attach honeycomb baggage panel to N251103-001 in upper aft baggage area using three 40S5-21 Camloc quarter- turn fasteners and 214-160 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 Paul Hedding on November 28 2012 using Nextant Aerospace Engineering Order EO 029. Rev C Dated November 15.2012. ICA Weight change is Negligible. Continue with Beechjet 400/400A Maintenance Manual Inspection Procedures. End 0 Additional Sheets Are MSG'S FAA Form 337 MAN SDNY_GM_02758290 SUBJECT TO PROTECTIVE ORDER PARAGRAPHS 7, 8, 9, 10, 15, and 17 EFTA_00245212 EFTA01261872 SDNY_GM_02758291 SUBJECT TO PROTECTIVE ORDER PARAGRAPHS 7, 8, 9, 10, 15, and 17 EFTA 00245213 EFTA01261873 U.S DEPARTMENT OF TRANSPORTATION FEDERAL AVIATION ADMINISTRATION STATEMENT OF COMPLIANCE WITH AIRWORTHINESS STANDARDS I. DATE November 28, 2012 AIRCRAFT OR AIRCRAFT COMPONENT IDENTIFICATION 2 MAKE Hawker Beechcraft Corporation 3. MODEL NO. 400A 4. TYPE (AnYerf. Engem. Prouder. N e ) Aircraft S. NAME OF APPLICANT Nextant Aerospace LLC Richmond Heights. Ohio UST OF DATA 6 IDFNTIFICATION 7 TM F EO 029 Rev. C November 15. 2012 Upper AR Baggage Panel Mod. 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. 6. PURPOSE OF OAT* Engineering data in support of major alteration to Hawker Beechcraft 400A, SIN RK-260. 9. APPLICABLE REOUREMENTS (UM specIlt MeTons) CFR Title 14 Part 25.301[25-23]. 25.303[25-231, 25.305(a)(b)(c)(25-23), 25.307(a)(25-231, 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)[25-001, 25.619(25.23], 25.625(a)(b)(c)[25-23), and 25.789[25-321 10. CERTIFCATION - Under astray vested by drecnon at the Admrisever and in recterms WM ccertions end imlanms at appertment under 14 CFR Psi 18.3. data rated above and co attached sneer numbered NIA hove been examined In secardere air ettableherd mord ems and found 10 amply '.e applicable requeemers at iheArrortnem Standards Listed. K Recommend approval of these data I (We) Therekte 0 Approve thane data II SZNATUREISI OF DESIGNATED ENCANEERNG REPRESENTATIVE(S) 12 CESCIVATIDN NUMBERS($) 11 CLASSECATIONES) .al~ Paul Hedding DERT-410115-CE Structures FM Form 81104 (03-10) SUPERSEDES PREVIOUS EDMON Fee Number. 1112861-05 Pan Id SDNY_GM_02758292 SUBJECT TO PROTECTIVE ORDER PARAGRAPHS 7, 8, 9, 10, 15, and 17 EFTA ()02452(4 EFTA01261874 SDNY GM_02758293 SUBJECT TO PROTECTIVE ORDER PARAGRAPHS 7, 8, 9, 10, 15, and 17 EFTA_00245215 EFTA01261875 0 MAJOR REPAIR AND ALTERATION V513eoreeR 0 (Airframe, Powerplant, Propeller, or Appliance) TraMEMMo. FedymIkAllti011 Aoft.IMMIthila RAM Apgead OW No 2.200320 to300:07 ENclroric Tracking Norntier FOE FAA the Only INSTRUCTIONS: Print or type af °nines. See FM egg FM et Adding( B. and AC 43.9-1 (or subSepuent revistOn theme° (04 MaTfueliCha and diSposillco 44 this form. This report is required Of law (49 U.S.C. 1421). Fare to report can result Wady* pin* not to Mead St.000 Kir each such OLPAOR (Section ROI Federal nation Act 19513) 1. Ai rcraft tiabonater and DPERSDREOR Ma N787TA Serial No. RK-260 Make Raytheon Aircraft Company 400A Medal 400A soon 2. Owner NEMO (As Shensi On legiSf Mien Cerelfeele) Flight Options .LLC AddreSS (As shown an reg.l.frefien Martin) Adams 26180 Curtiss Wright PKWY oily Richmond Heighte sow OH zo 44143.1453 coney OA 3. For FAA Us* Only 4, Type S. Unit Identification Rep& Allirelien /Mil Make Model Send Number El lEl AIRFRAME (A.SCIOSCIIIMKI tri I fen, I above) 0 E POWERPLANT 0 ci PROPELLER E II APPLIANCE Two 14m/Ilse, 6. Conformity Statement A. Agency, Name and Address & Kind oftener Name Nextant Aerospace Mem [ADDRESS REDACTED].1453 Curvy USA 0 U.S. CerldCated Mechanic 01 Menu/educe( 0 Foreign catficate mechanic C cerificato NO 0 Cerlficated Repayswoon CRS # 25NR667B 0 Controvert Maintenance Organdallon 0. I Way Mal the repair MAO alteration made to tne un4(s) identified in item 5 stove and described on the reverse or atiactinaentri hereki have been made in occordarICO with the requanneres of Pan 43 0 the U S. Federal Aviatbn Repot:None and mat the intimation furnished herein is true and correct to the tat of my knOv1.090. &landed range Mt per 14 CFR Pan 43 APP. El O SIgratseerriate Of Authatied MO A.Ockwell a 01/0412013 T. Approval for Return to Senile, Pursuant to the authonty given persons peofrol below, the unit identified in deco e was Inspected in the manner prescribed by Me AtIrnnistia.or of the Federal Avow Adnthisiusliect and is tzi APPROVED 0 REJECTED 8Y FM Flt Standards IDSpectOr manufacturer Mahlenance OrgariZBECO Parson Approved by CanacAsn Department a Transport FM Designee X Repair Stollen InspeChOn Autfortzatton osier (Speed?) CerneCate or CretainatiOn NO. CRS # 25NR667B Signature/DM el Authorized dna A.Ockwell CtitIL 01104/2013 FAA Form 337 (t0-06) SDNYGivi02758294 SUBJECT TO PROTECTIVE ORDER PARAGRAPHS 7, 8, 9, 10, 15, and 17 EFTA_002452 I 6 EFTA01261876 SDNY_GM_02758295 SUBJECT TO PROTECTIVE ORDER PARAGRAPHS 7, 8, 9, 10, 15, and 17 EFTA_002452 17 EFTA01261877 NOTICE Weight and balance or operating limitation changes shalt be entered in the appropriate aircraft record. An alteration must be compatible with all previous alterations fo assure continued conformity with the applicable seaworthiness requirements. 8. Description of Work Accomplished (If more space is required, attach additional sheets. Identify with aircraft nationalay and registration mark end date work completed) N787TA Nationality and Registration Mark 01(04/2013 Date The Aircraft comes from the Factory equipped with Aero Instruments PH1100-MU-L-1 (R-1) chromium plated Pitot Tubes. This is to replace them with ISO approved Tubes PH1100-MU-L-EN (R-EN) The Electrical Aspects of this was approved by Mr. Dan Buzz FAA DERT-230019-CE Systems and Equipment on an FAA 8110-3 Dated 11/7/2012 .Using Nextant Aerospace Engineering Order 024-11 Rev Original Dated 04/11/2011 The Mechanical Aspect was Approved by Paul Hedding FAA DERT-410115-CE Mechanical Systems on a FAA 8110-3 Dated Nov 09.2012 Using Nextant Aerospace Engineering Order 024-11 Rev Original Dated 4/11/2011 ICA. Continue with Normal Hawker Beech Maintenance Manual Inspections for this Area There are no Changes to the Weight and Balance End (S) Additional Sheets Are Attached FAA Form 337 (1096) SDNY_GM_02758296 SUBJECT TO PROTECTIVE ORDER PARAGRAPHS 7, 8, 9, 10, 15, and 17 EFTA_00245218 EFTA01261878 SDNY_GM_02758297 SUBJECT TO PROTECTIVE ORDER PARAGRAPHS 7, 8, 9, 10, 15, and 17 EFTA 00245219 EFTA01261879 U S. OEPARTMENT OF TRANSPORTATION FEDERAL AVIATION ADIONISTRATiON STATEMENT OF COMPLIANCE WITH AIRWORTHINESS STANDARDS 1. DATE November 9, 2012 AIRCRAFT OR AIRCRAFT COMPONENT IDENTIFICATION t. MAKE Hawker Beechcraft Corporation 3. 1•30EL NO 400A 4. TYPE I /and. Engine. PIANO'''. a ) Aircraft 5. NAME OF APPLICANT Nextant Aerospace Cleveland. Ohio LIST OF DATA 6 IDANTIFTATION 7 MP Engineering Order 024-11 Rev. Original April 11.2011 Pitot Probe. Notes: 1) The Mechanical Systems 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 does not constitute FAA approval of all the engineering data necessary for substantiation of compliance to necessary requirements for the entire alteration. The electrical regulations are not covered by this approval and require separate approval. 5. PURPOSE OF DATA In support of a major alteration to Beech 400A SIN RK-260 aircraft. 9. APPLICABLE REOURENENTS (LIM spools WON) CFR Title 14 Part 25.601(25.00], 25.603(a)(b)(25-381, 25.605126-00). 25.607(a)(b)(c)125-23), and 26.1325(b)(c)(25-121. 10. CERTFICATK)N • Under memory Pan MI data brad above aid en applicable requirements Mee AtrocrINnets 0 Recommend vested by Median or the Administrator and in ascordance MO condoms and Ineadcas of appointment undo, 14 CAR trod sheets numbered MA_ have been examined I, aCC0rdana with atobtslwrel Oreg.:lune end found to complyMA Standards WWI. approval or these data Mesa data I (we) Therefore : 4 Approve it. SIGNATURES) OF DESIGNATED ENGINEERING REPRESENTATNEM) 12. DESIGNATION NUMBERS(S) 13. CAASSIMCATION(S) .011...%"-A"..._> Paul Hedding DERT-410115-CE Mechanical Systems FAA FORM 8110.3 (03.10) SUPERSEDES PREmOtIS EDITION FM Number NItele-0i SDNY_GM_02758298 SUBJECT TO PROTECTIVE ORDER PARAGRAPHS 7, 8, 9, 10, 15, and 17 EFTA_00245220 EFTA01261880 SDNY_GM02758299 SUBJECT TO PROTECTIVE ORDER PARAGRAPHS 7, 8, 9, 10, 15, and 17 EFTA_00245221 EFTA01261881 U.S. DEPARTMENT OF TRANSPORTATION FEDERAL AVIATION ADMINISTRATION STATEMENT OF COMPLIANCE WITH AIRWORTHINESS STANDARDS 1. DATE 11/7/2012 AIRCRAFT OR AIRCRAFT COMPONENT IDENTIFICATION 2. MAKE HavAer Seethe:aft 3. MODEL NO. 400A SIN RK-260 Only 4. TYPE (Airplane. Radio. Hattopter. Se) Airplane S NAME OF APPLICANT Nexlanl Aerospace L LC UST OF DATA S. IDENTFICATION 7. TITLE Nextant Aerospace Document 024.11 dated 411l 111 Rev. Original Engineering Oder Pilot Probe END -- This approval is for the electrical systems aspects only. O. PURPOSE Of DATA Support major atetation to aircraft Hawker BeecIscraft 400A RX-200 Only. 9. APPLICABLE REQUIREMENTS Ws/ secede seesaw 14 CFR 25.1301(egO (Orig) Note: Con panoe has been found to the amendment levels indicated on Hawker Seochcrall TCDS Revision 20 Part 25 Amendment 25.1 through 25-40 to the above applicable tequircrrents. 10. CERTIFICATION • Wider aiahodly vested by retectko Male Administrator and in accordance Mitt condtiOnS and linilattOns of appointment under 14 CFR Pad 163 of the Federal Ainalron Regulations. data listed above and co azacned steels numbered WA rum been examined in occordanco with estabilmed procedures and found to complymei applicable reel:Yemenis of me Adwonhanoss Standards baled. I (We) Therefore approve these data. II. MOHAN MS) ESIGNA 0 ENGINEERING REPRESENTATNE($) 12 DESIGNATION NUMBERS(S) 13. CUsS3iFICATiON(S) Daniel L. Burt <4 DERT-230019-CE Systems and Eraipment oms 8110.3 (03/10) SUPERSEDES PREY/OUR EDMON GPO 631653 SDNY_GM_02758300 SUBJECT TO PROTECTIVE ORDER PARAGRAPHS 7, 8, 9, 10, 15, and 17 EFTA_00245222 EFTA01261882 SDNYGM02758301 SUBJECT TO PROTECTIVE ORDER PARAGRAPHS 7, 8, 9, 10, 15, and 17 EFTA_00245223 EFTA01261883 0 MAJOR REPAIR AND ALTERATION u s ovonned (Airframe, Powerplant,Propeller, or Appliance) tampanaton reeenonvetion AtIntleisteition Fenrgeoved owe No. mann iirdacO7 Electronic Tracking Number For FAA Use Only INSTRUCTIONS: Prim or type all entrlµ. See FAR 43.9. FAR 43 AppendIS B. and AC 43.41 (or subsequent revision this (or instructors and dispose:on of this loan. This leer is required by law (49 U.S.C. 1421). Fa ure 10 report can result in aerie wally not to exceed 5 1.030 for each such /darn (Section 901 Federal Aviation Act 1906) 1. Aircraft Nannality and Registration mars N787TA Serial No. RK-260 Make Raytheon Aircraft Company 400A Model 400A Series 2. Owner Name (As 'new , on reagrason carnal./ Flight Options .LLC Address (As shown on registration cad kale) Address 76180 Curtiss Wright PKWY OtY Richmond Height" saws OH zip 44143-1453 caws, USA 3. For FAA Use Only 4. Type S. Unit Identification Repair Alteration Unit Make Model Serial Number • 0 AIRFRAME (As described in Item 1 above) Ill • POWERPLANT El In PROPELLER i:l is APPLIANCE Type dantrocuree 6. Conformity Statement A. Agency's Name and Address B. Kind of Agency Noma Nexlant Aerospace Adonis [ADDRESS REDACTED] caws" USA 0 U.S. Certdcaled Mechanic Cl Manufacturer 0 Fortran Canalcaleg Methane C. Cartricate No. 0 Cridcaled Repair Staten CRS # 25NR6678 0 Cerelicated Main:emerge Organdason D. I Certify that the repair and/or allergen made to the untie) Identified n tern S above and desenbed on the reverse or attachments hereto hare been made in accordance with the requirements or Pan 43 of De U.S. Federal Aviation Regfiglicen and that the inferno:in Wished march is true and correct to the best of my knerneedee Extended range fuel per 14 CFR Part 43 APP. 0 0 Signature/Dan of Authoring A.Ockwell \L 01/04/2013 7. Approval for Return to Service Pinball le the Dona* given persons ;rotted beton, the unit AdmiNstrator of the Federal Aviation Administration and is 1MI Weaned in item 5 was inspected in the manner evescrbed by the APPROVED 0 REJEGIED BY FM Ftt Standards Inspector ma/undue( - Maintenance Or Person Approved by Canadian Department of Teenier FAA Douro° X Recta Station Inspection Authorizatiori i Other (Spec fy) Conks* or Designer Na CRS /125NR6678 SignaturerDate of Authorized Indite/dual A.Ockwell 01/04/2013 FAA Form 337 00.00 SDNY_GM_02 758302 SUBJECT TO PROTECTIVE ORDER PARAGRAPHS 7, 8, 9, 10, 15, and 17 EFTA_00245224 EFTA01261884 A , SDNYGM02758303 SUBJECT TO PROTECTIVE ORDER PARAGRAPHS 7, 8, 9, 10, 15, and 17 EFTA_00245225 EFTA01261885 NOTICE Weight and balance or Oporahng limitation changes shsa be colored m the appmpaale aircraft record. An alteraton must be compatible with all previous alterations to assure continued conformity with the applicable airworthiness requirements. 8. Description of Work Accomplished (;r more space is required. attach additional sheers. Identify with aircraft nationality and registration /near and date work completed.) N787TA Nationality and Registration Mark 01/04/2013 Date Installed the following In-Flight Entertainment System in accordance with STC # ST03960AT and in accordance with Nextant Aerospace Master Drawing List DB1002067. Revision E. Dated January 26 2012. The Emteq LED cabin lights provide high reliability low power consumption Indirect Cabin Lighting, Galley Task Lighting and Lavatory Vanity Lighting. Installed LED Passenger Safety Signs The cabin lights are interfaced to the existing cabin lighting power distribution and control switches. Installed Cabin LED Lighting System without the Venue System in accordance with 061107014. Rev IR Dated January 26.2012. Installed LED Passenger Safety Signs in accordance with Wiring Diagram DB 1108001 Rev IR January 26 2012 Scheduled Inspection and Maintenance. Inspect System Installation Component including wire Bundles, Cables Racks and Connector Condition and security in conjunction with the B Check (every 400 hours after Initial 200 Hours "I" inspection) tasks and "C" Check (every 1200 after initial 200 Hr -r Inspection) Per Hawker Beechjet 400A Maintenance Manual 5.20.02 requirements listed within Scheduled Inspection Section RK-1 and above ICA for LED Cabin Lighting System Ref to Nextant Aerospace Document No DB1108019 Rev IR Dated September 22 2011 or later FAA Accepted Revisions Installed Iridium Sat Comm and Broadband Internet System with Aircell Axxess II and ATG 4000 in Accordance with DB 1001013. Rev D ICA for Aircell System Ref to Nextant Aerospace Document No DB1105003. Rev A dated September 22 2011 or later FAA 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 013485 Revision 6 Dated November 2009 or later applicable revision Aircell Axxess II WLAN AFM Supplement 081002072 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 the following Nextant Aerospace Drawings This is Located under the Seat Divan NX252-10007-03. NX252-10007-04. NX252-10007-05 NX252-10007-06 NX252-10007-12. NX252-10007-13. Rev IR Dated June 04 2012 Channel Hat Inverter Mount Rev IR Dated June 12, 2012. Assy Inverter 115 VAC. Wft-leatsink and Hat. Rev IR. Dated June 14 2012 Mount Plate ,Single Inverter. Under Divan Rev IR Dated. June 13. 2012. Assy, Inverter, Divan Mount Rev IR. Dated June 14 .2012 Assy ,Bracket Plate Mount Inverter ,Under Divan Rev IR, Dated June 14 2012. Angle.txr inverter Mount ICA for Astronics 115 VAC Cabin Inverter Ref to Nextant Aerospace Report No 081108018 Rev IR Date 9/22/2011 or later FAA Accepted Revision. Aircraft Flight Supplement 081109012 has been installed on the Aircraft See Current Weight and Balance Dated 12/21/2012 End K Additional Sheets Are Attached FAA Form 317 tIOCel SDNYGM02758304 SUBJECT TO PROTECTIVE ORDER PARAGRAPHS 7, 8, 9, 10, 15, and 17 EFTA_00245226 EFTA01261886 SDNYGM02758305 SUBJECT TO PROTECTIVE ORDER PARAGRAPHS 7, 8, 9, 10, 15, and 17 EFTA_00245227 EFTA01261887 Uniteb 'thin of Pontrica lilepartment of litransportation —jeberal Ablation Abininistration $upplernental Type gertificate Ma ter/Ilia* t5erted/e Nextant Aerospace LLC 3800 Southern Blvd. West Palm Beach, FL 33406 ST03960AT reellriv 44/44 rotor et• /4- /Ave air, Ae /41Xtroviterettiet/ teat° /We Sifte/teee eta tenant deer/eft tte reeSitaneeeto tter/t metterettvete orretertmetie r/ra425 a Federal Aviation .:faretlemwd. (C.liamaren't .4 ;•••• Mv9•3"4* r)nirrf c Al 6SW Hawker Beechcraft Corporation sew: 400A ge.i rip/es /Wyo. .47.04tv Installation of Rockwell Collins Venue In-Flight Entertainment(IFE), Aircell Axxess Cabin II Iridium Phone and High Speed Internet System with Wireless Local Area Network (W LAN) Astronics I t SVAC 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. wo.cifoosaiv..4.- 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. .97/3 ere/Airk and/ it twevitir da/et ett,1 IC,Na weereetteardfitmvereia rir 00r/era/r% Jeerer/awe/ Jnsneadvi nerd:vire it /rtmtireehett Wide edeetetie 4v/rteaded* de • Adotte/Wirr/er e//eft grederettt Lee:v/4w ./t/tvtive:Vetr/tivt 247 . le r/trarbe /ten July 28,2012 Om- Almoner March 22, 2012 2r /e ere:tweet fa. ile entevided.. Melvin D. Tay Manager Atlanta Aircraft Certification Office Ali SIC ##### on 0f Ws CfltI 'CAC* JO OSIUS,o Is Oy ell no of sot anuMlp OZ IW ii0-01, OlAt I of This COISISICS10 OS, De SS...tgrrid I W SDNY_GM_02758306 SUBJECT TO PROTECTIVE ORDER PARAGRAPHS 7, 8, 9, 10, 15, and 17 EFTA_00245228 EFTA01261888 SDNY_GM_02758307 SUBJECT TO PROTECTIVE ORDER PARAGRAPHS 7, 8, 9, 10, 15, and 17 EFTA_00245229 EFTA01261889 Nada 'inks of Pautrica !apartment of Transportation - Noborul cAbiation eAbininistration $upplementat Type (Certificate Mantinuation Sheet) ./1/eieddese 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, 0131109012, Revision IR, dated March 22, 2012, or later FAA approved revision, is required. This system is intended to provide intemet 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. DBI002068, 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. DBI 105003, 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 IR, dated September 22, 2011, or later FAA accepted revisions must be made available to the operator at the time of installation. 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 revisions must be made available to the operator at the time of installation. My •Icentson el aim cortIticoto it sysionaei• ty • On Of net ortmOinoll.000, or reps se FM raw 4110-34 (10-0) PAGE 2 of ) PAWS This meanest* soy b tramtortro to accoreme• vita IM II.47. SDNY_GM_02758308 SUBJECT TO PROTECTIVE ORDER PARAGRAPHS 7, 8, 9, 10, 15, and 17 EFTA_00245230 EFTA01261890 SDNY_GM_02758309 SUBJECT TO PROTECTIVE ORDER PARAGRAPHS 7, 8, 9, 10, 15, and 17 EFTA 00245231 EFTA01261891 liMilsb Alen of Ponteita lepartnteitt of transportation - geberal Ablation cAbmittistration Supplemental Type Certificate (€tnntinutttion *fleet) ../i/teotoPeee ST03960AT MVOea/Ma ..,9aJtD.• 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(eX5), and 25.1447 of Amendment 25-41; FAR 25 29, FAR 25.255, and FAR 25.1353(c)(6) of Amendment 25-42; and FAR 25.361(6) and 25.I329(h) of Amendment 25-46. In addition the following specified rules amendment levels were used for this installation. 25.571 [25-54] 25.135300(c) [25-1231 1-1 Indicates amendmen level 25.1357 125-1231 25.1431 125-1131 25.1529 125441 y • ton[ IM • by ri• $1,no, . In t $110-2-1110-49) PAU 3 01 3 144t4 This cortiticato may be frantnne An accordance with nit 21.47. SDNY_GM_02758310 SUBJECT TO PROTECTIVE ORDER PARAGRAPHS 7, 8, 9, 10, 15, and 17 EFTA_00245232 EFTA01261892 SDNYGM02758311 SUBJECT TO PROTECTIVE ORDER PARAGRAPHS 7, 8, 9, 10, 15, and 17 EFTA_00245233 EFTA01261893 MAJOR REPAIR AND ALTERATION u.S Desminsve 0. (Airframe Powerplant, Propeller, or Appliance) TrarsPadll01 Paden. Aviation admerromsan sormssonnssi Owe No. 21204020 I ir30r2407 Electronic Tracking Number For CAA Use Only INSTRUCTIONS: Print or type all entries See FAR 43.9. FAR 43Appendix B. and AC 43 0.1 (or subsequent revision thereof) fOr InSeualan and disposition of INS form. This radon is required by law (49 U.B.C. 1421). Failure to report can result m cM1 penally not to mooed $1,000 for eacri such rotation (Section 901 Federal Avisinn Act 1056) 1. Aircraft Nationally and Regisbation Mark N787TA Serial No. RK-260 Make Raytheon Aircraft Company 400A mom 400A Senn 2. Owner Name (As shown on resatration froiticsto Flight Options .L.LC Address (As shown On fecAbarkin certolce/0 Admen 26180 Curtiss Wright PKWY Coy Richmond Heights sta. OH zc 44143.1453 car USA 3. Far FAA Use Only 4. Type 6. Unit IdentlIkWon Repair ANeraten Unit Make MDON Serial Number 0 e AIRFRAME (AS cleSated on item f above) 0 • POWERPLANT 0 El PROPELLER O • APPLIANCE Type lisnutenuiw S. Conformity Statement A AMMO NAM and Address S. KM of Agency Nov Nextant Aerospace O U.S. Certificated Meehan O I Mande:luny 66 [ADDRESS REDACTED] O Foreign CenAcated Mother* C. Certificate No. City Cleveland State. OH e Certificated Repair Station CRS # 25NR667B Zip 44143-1453 cow., USA O Certificated Maintenance Organization D. I ung). Mal Me repair andMir alteralkel made le the unit(s) i tithed in item 5 above and described on the reverse or atladimenla hereto have been made in accordance with the req./dements of P it 430f 1M U S. Federal Aviation Regulataons and that Me information furnished herein is true and correct to the best of my kncoviectge Extended range fuel Fer 148CFR Ran 43 App. 0 Signature:Date of Aulliceized I i i A.Ockweli 1/04/2013 7. Approval foe Return to Service Pursuam to the authority glean persons swilled below, me um iden Administrator of the Federal Aviation Administration and is 0 Wed in item S was impeded in the manner prescribed by the APPROVED 0 REJECTED BY FAA Fa Standards Inspector Department Manufacturer Maintenance Organzabon Person Approved by Canadian of Transport FAA Designee X Repair Staten inspection Atnnonzation Other Soto*/ Certificate or MoRSiinson No. C 25NR6678 signatwerosis or Authorized Irma id A.Ockwell 01/04/2013 FM Form 337 0040 SDNY_GM_02758312 SUBJECT TO PROTECTIVE ORDER PARAGRAPHS 7, 8, 9, 10, 15, and 17 EFTA_00245234 EFTA01261894 SDNY GM 02758313 SUBJECT TO PROTECTIVE ORDER PARAGRAPHS 7, 8, 9, 10, 15, and 17 EFTA_00245235 EFTA01261895 NOTICE Weight end balance or operating limitation changes shag be entered in the appropfiate aircraft record. An alteration must be compatible with all previous alterations to assure continued conformity with the applicable einvorthiness requirements. 8. Description of Work Accomplished (If more space is required, attach additional sheets. Identify with aircraft nationality and registration mark and date work completed.) N787TA Nationality and Registration Mark Nextant Aerospace Carried out a Repair to the Horizontal Stabilizer Ribs 01/04/2013 Using Nextant Aerospace Kit Part Number NXK-128-6200 Rev B. Dated July16. 2012. The following Ribs were replaced. NXR-45A21112-007 Rib — H Stab Cant STA 13.779. NXR-45A21113-007 Rib — H Stab Cant STA 29.921. NXR-45A21101.021 Rib — H Stab Cant STA 46.063. NXR-45A21116-007 Rib — H Stab Cant STA 62.205 NXR-45A21117-007 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 Paul Hedding DER-T 410115-CE Structures on an FAA 8110-3. Dated December 5.2012. Using Nextant Aerospace Engineering Drawing NXR-128-6200 Rev B Dated July 16. 2012 ICA Ref to Current weight and Balance dated 12/06/2012 Continue with Normal Hawker Beech 400A Maintenance Practices for this Area End 0 Additional Sheets Are Attached FAA Form 337 00-06) SDNY_GM_02758314 SUBJECT TO PROTECTIVE ORDER PARAGRAPHS 7, 8, 9, 10, 15, and 17 EFTA_00245236 EFTA01261896 SDNY_GM_02758315 SUBJECT TO PROTECTIVE ORDER PARAGRAPHS 7, 8, 9, 10, 15, and 17 EFTA_00245237 EFTA01261897 U.S. DEPARTMENT CF TRANSPORTATION FEDERAL AVIATION ADMINISTFLATKIN STATEMENT OF COMPLIANCE WITH AIRWORTHINESS STANDARDS I. DATE December 5, 2012 AIRCRAFT OR AIRCRAFT COMPONENT IDENTIFICATION 2. MAKE Hawker Beechcraft Corporation 3. MOCEL NO. Horizontal Stabilizer P/N 45A21001-635 4 TYPE (EMIllt &SAL AIMS/. erc) Component S. NAME OF APPLICANT Nextant Aerospace LLC Richmond Heights, Ohio LIST OF DATA A OFNTIFICAT/ON 7 TITLE NXR-128-6200 Rev. 8 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. 8 July 13. 2012 NXR-45A21117-007 Rev..B July13, 2012 Kit - Horizontal Stabilizer Rib Replacement Installation Instructions. Rib — H Stab Cant STA 13.779. Rib — H Stab Cant STA 29121. 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 Cf DATA: Engineering data in support of major repair to Hawker Beechcraft Horizontal Stabilizer P/N 45A21001-635, SIN RK-260. 9. APPLICABLE REQUIREMENTS (Usl spec& sections) CFR Title 14 Part 25.301(25-23), 25.303[25-23), 25.305(a)(b)(c)(25-23], 25.307(a)(25-231 25.601(25.00], 25.603(a)(b)(c)(25-38), 25.805(a)(25-00]. 25.607(25.23), 25.609(a)(b)(25-001 25.611125-23], 25.613(a)(b)(c)(25- 00). 25.619[25-23], and 25.625(a)(b)(c)125-23). 10 CERTIFCATION - Under solIWIN veiled by dIrecten a the AdmnIsuroor and h accordance win conditions artl anmenom el appefinlent under I4 CFR Pan 153. dMa IlMed Wove arid on MlWWd Meets Malted ,2._ have been memhed h accordance well 101111.1110:1 crooneses and bind to cOmPlY tat aPPOC•01.1 requirements of MeArsonninesa Slandarelf LMed. 0 Recommend approval or Maio data I (Wo) Therefore CD Approve these data II. SI0NATUREIS) OF CESIGNATEDENGINEERING REPRESENTATIVE(S) 12 DESIGNATION NUMBERSIS) It CLASSIFICATION(5) °.4'-- Paul Redding DERT-410115-CE Structures FAA Form $110-3 (03-101 SUPERSEDES PREVIOUS EDITION Fib tenter. 1412677•03 Pape I il l SDNY_GM_02758316 SUBJECT TO PROTECTIVE ORDER PARAGRAPHS 7, 8, 9, 10, 15, and 17 EFTA_00245238 EFTA01261898 SDNY GM 02758317 SUBJECT TO PROTECTIVE ORDER PARAGRAPHS 7, 8, 9, 10, 15, and 17 EFTA 00245239 EFTA01261899 V.S. DEPARTMENT OF TRANSPORTATION FEDERAL AVIATION ADMINISTRATION STATEMENT OF COMPLIANCE WITH AIRWORTHINESS STANDARDS 1. DATE December 5, 2012 AIRCRAFT OR AIRCRAFT COMPONENT IDENTIFICATION 2 MAKE Hawker Beechcraft Corporation 3. MODEL NO Horizontal Stabilizer PIN 45A21001-635 4. TYPE Walt Ear.. Propeller, arc.) Component S. NAME OF APPLICANT Nextant Aerospace LLC Richmond Heights. Ohio UST OF DATA a ORNDFICATIDN 7 TITLIF END— 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 repair. a PURPOSE OF DATA: Engineering data in support of major repair to Hawker Beechcraft Horizontal Stabilizer P/N 45A21001.635, SR4 RK-260. D. APPLICABLE REQUIREMENTS (Ust mealc Sod/0115) CFR Title 14 Part 25.301[25-23). 25.303(25.23), 25.305(a)(b)(c)(25.23J, 25.307(a)[25-23L 25.601[25-00J. 25.603(a)(b)(c)[25.38), 25.605(a)(25-00). 25.607[25.23), 25.609(01/H25-04 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 fl .o.ty vents Dr dkeclIOn el tie AMMIstrala and ki INCOMMOI YAM Cernatired anti fmtaleed of eppaintmeel under II CFR PM 103. data reed above end on MOMS Ihmla numbered _2_ have been carranoa 11 saw:Ines WEI ealatiMed proadaree end found 10 Comply Min apSabte mammon% of IM AINOOIMIWI4 Simard, UMW. 0 Recommend approval of Vat data I (We) Therefore 0 Appron these data II. SIGNATURE(S)OF DESIGNATED ENGINEERING REPRESENTATNE(S) 12. DESIGNATION NUMBERS(S) 13. GLASSFICATION(S) te... "9. Paul Hedding DERT-410115-CE Structures FAA Form 8110-3 (03-10) SUPERSEDES PREVIOUS EDITION Fee Nurriam111267743 Page 2 ci 2 SDNY_GM_02758318 SUBJECT TO PROTECTIVE ORDER PARAGRAPHS 7, 8, 9, 10, 15, and 17 EFTA_00245240 EFTA01261900 SDNY_GM_02758319 SUBJECT TO PROTECTIVE ORDER PARAGRAPHS 7, 8, 9, 10, 15, and 17 EFTA 00245241 EFTA01261901 0 MAJOR REPAIR AND ALTERATION ersowariveniai (Airframe, Powerplant,Propeller, or Appliance) Temennen moue mune mmaittmern Fern Acrwed am to. 21200020 it/X.2007 Elecgonic Tracang Number For FAA Use Only INSTRUCTIONS: Print or type all engirt,. See FAR 43.9. FAR 43 Appendix B. and AC 43.9-I (or subSequeM revision eared) for inst.' urnons and disposition of this form. This report is required by law (49 U S.C. 1421). roma to report can resut In a reel penalty not to exteed S1.000 for each such earn (Salton 901 Federal Aviation Act 1958) I. Aircraft Nalionakty and Registrean Mark N787TA Serial No. RK-260 Make Raytheon Aircraft Company 400A MOON 400A Series Owner Name (As Memo on registration cernacate) Flight Options .LLC Adams (As shown on registration bereecale) mow 261130 Curtiss Wright PKWY 2. Ctty Richmond Hetoht% eta& OR zo 0143-1453 Carey USA 3. For FAA Use Only 4. Type S. Unit identification Repair Atletation Una Make Model sew Number 0 e AIRFRAME (As Oesenbe I In Nem I above) 0 ci POWERPLANT li O PROPELLER O O APPLIANCE Type klanieedwer 6. Conformity Statement A. Agency's Name and Address 8. Kind of Agency teliMI. Nextant Aerospace Ames [ADDRESS REDACTED] Cerny USA O U.S. Cereetaies Mechanic O IManufacturer O Foreign CertifiCated Mechanic C. Certificate No. 0 Cenidadied Repadr Station CRS # 25NR667B O Certdcaled Maintenance Organizer:4i 0. I away that me repair and/or alteration made to the unit(s) 'denuded in deco 5 above and descntel on the reverse a eiteetweene hereto have teen made in accordance with the requirements of Part 43 of the V.S. Federal Aviation Regulatons and that the infernatan furnished herein a tee and correct to the best of my knowledge &tended range fuel pe 14 CFR Pert 43 App 8 0 Signature/Date of Autho A.Ockweil 01/04/2013 6-- 7. Approval for Return to Service Pursuant to the authority given pe sons specified below. the unit iclen lied in item 5 was nspected In the manner prescribed by the Adn'inisValor of the Federal Aviaton Administration and is Eg APPROvEO 0 REJECTED BY FAA FII Standards Inspector Manufacturer Maintenance Organitaren Person Approved by Canadian Department 017taneral FAA Designee X Repair Stat.= limpet:bon Authorization Otter (Specify) Celeste or Desarntion No. CRS /2 25NR6678 Sign turerDale of Authorized In A.Ockwell \ (4 01/04/2013 FAA Form 337 pea) SDNY_GM_02758320 SUBJECT TO PROTECTIVE ORDER PARAGRAPHS 7, 8, 9, 10, 15, and 17 EFTA 00245242 EFTA01261902 SDNY_GM_02758321 SUBJECT TO PROTECTIVE ORDER PARAGRAPHS 7, 8, 9, 10, 15, and 17 EFTA_00245243 EFTA01261903 NOTICE Weight and balance °roweling Marabou changes shall be entered in (ho appropriate aircraft record. An alteration must be compatible web all previous aReratioas fo assure continued confonnay with the septet* akvaxlienesS1104101710ift 8. Description of Work Accomplished (If more space is required, attach additional sheets. Identity with aircraft nationality and registration mark and dale work completed.) N787TA Nationality and Registration Mark Nextant Aerospace Install Flight Display Systems Moving Map System. 011 04/2013 Date Install CB panel P/N: NX253-10003-01 and Overlay P/N: NX253-10003-02 using two (2) each brackets, P/N: DB1104014. Install FD200-7/8 Unit in lower Galley and Drawing NX253-1004-01 wire per drawing NX252-10001-01.( Ref: Flight Display System MAN-FD200CPU-7/8 ) Install FD102CV unit on L/H side of Galley. Ref: MAN-FD102CV Configure and Test per Flight Display System Document MAN-FD200CPU-7/8 Chapter 4 This Installation was FAA Approved on an 8110-3 by Dan Buzz DERT-230019-CE. On Dec 27.2012 using Nextant Aerospace Engineering Order 1121 Dated 12/22/2012 Rev IR ICA The FD200CPU-7/8 is a Moving Map Designed not to require regular General Maintenance. Ref to Weight and Balance Dated 12/21/2012. End (2] Additional Sheets Are Attached FAA Form 337 (man SDNY_GM_02758322 SUBJECT TO PROTECTIVE ORDER PARAGRAPHS 7, 8, 9, 10, 15, and 17 EFTA_00245244 EFTA01261904 SDNY_GM_02758323 SUBJECT TO PROTECTIVE ORDER PARAGRAPHS 7, 8, 9, 10, 15, and 17 EFTA_00245245 EFTA01261905 U.S. DEPARTMENT OF TRANSPORTATION FEDERAL AVIATION ADMINISTRATION STATEMENT OF COMPLIANCE WITH AIRWORTHINESS STANDARDS 1. DATE 12/27/2012 AIRCRAFT OR AIRCRAFT COMPONENT IDENTIFICATION 2. MAKE NeWker Beef:hash 3. MODEL NO. 400A Slat RK-260 Only 14. TYPE (Ahpfsne. IWO, 14O4,0At0e, ens) Akplan• S. MAIM or APPLICANT Rodent Aerospace LLC UST OF DATA 0.10ENT1FICATK01 7. TITLE Nextant Aerospace Document EO 1121 dated 12/22/2012 Rev. IR Engineering Order Install Moving Map System ENO This approval Is for the electrical systems aspects only. Note: The above data does not meet the criteria of FM Pad [ADDRESS REDACTED]atement Number ARM-0144; System Wring Policy for Ce Monter of Part 25 Airplanes. Additional approvals may be required. 'TNS approval is for engineering design data only and Is not en installation approval. It indicates the dela listed above demonstrates compliance only vett, the regulations specified by paragraph and subparagraph fisted beton as "APPLICABLE REQUIREMENTS.' (Compliance xith addCanal regulativs not listed hero may be required). This form does net constilige FM approval of e0 the engineering design data necessary for substantiation of compliance to necessary requiremenli for the entire MerNion' 8. PURPOSE Of DATA Support major allateftort to airaaft Hawker' Beachaeft 400A R11•260 Only. O. APPUCABLE REOUREMENTS (List spool/caw/end 14 CFR 25.1301(e)(101c)(0RiGs. 25.1307(c)(25.23). 25.1357(a)(c)(ORiG), 25.1431(a)(0gORIGh 253541014G) Note: Compliance has been found to the amendment levels indicated on Henrik& Beechcraft ICOR Revision 20 Part 25 Amendment 254 through 2540 to the above applicable requirements. 10. CERTIFICATION - Under authonty vested by direction of the Admindlra4or and in aceordanCo wit conditions and leniatione of sopoinuncnt under 14 CFR Pan 103 of are Federal Aviation Regulations, data I Sled above and on areas shoes numbend n have been examined in accordance nth eel Aliened protiedures and romml le comply rind applcabie requirements of the AirwcithMess Standards listed I (We) Therefore approve these data. t I. SIGNATURE(S)• F 0 S1GNA1 ENGINEERea3 REPRESENTAINE(S) 12. OFSIGNATON NUMBERS(S) 13, 0LASSIFICATION(S) Owed L Duct • z4 0ERT•230019•SE Systems and Equipment EDITION GPO 101413 SDNY_GM_02758324 SUBJECT TO PROTECTIVE ORDER PARAGRAPHS 7, 8, 9, 10, 15, and 17 EFTA_00245246 EFTA01261906 SDNY_GM_02758325 SUBJECT TO PROTECTIVE ORDER PARAGRAPHS 7, 8, 9, 10, 15, and 17 EFIA_00245247 EFTA01261907 0 MAJOR REPAIR AND ALTERATION u s Onanwew of (Airframe, Powerplant, Propeller, or Appliance) Terecosecin FOOOtal Ablation Admirthif Wen Form Approve °M0 No 21204320 I I trYX07 Eledronic Inciting Number For FAA Use Only INSTRUCTIONS: PAM or 49e as Verde See FAR 439. FAR 43Appecdx 8, and AC 43.9-1 (a subsequent revision there08 for inSMICOS and chip:Aden ofthis form. This report is required by In (49 U.S.C. 1421). Failure weapon can Mull in a WI penalty not lo exceed 51.000 ix each such iceelics (Section 901 Federal Aviation Act 1959) 1. Aircraft Nationality and Registrationifedt N787TA Serial No. RK-260 Make Raytheon Aircraft Company 400A PASS 400A Sides Ornw Name (As shown on registration cogitate) Flight Options .LLC Address (As shown on registration certificate) Movie 26180 Curtiss Wright PKWY 2. or, Richmond Heights us OH Zp 44143-1453 canes USA 3. For FAA Use Onty 4 ype 5. Unit Identification Repair Nitration Unit Make Model Serial Number 0 cl AIRFRAME (AS descn&cd nil /tam r oboe) 0 O POWERRANT ID O PROPELLER El . APPLIANCE Type varoroces & Conformity Statement A. Agency, Name and Address 8. Kind of Agency fee Nexlant Aerospace 0 U.S. CortiricaNa MeChanie 0 I Manufacturer Adams [ADDRESS REDACTED] 0 Foreign C08144400 Mecham C. Cerentata No cay Cleveland soot OH co Coruscated Repair Staton at. 44143-1453 coo-oy USA 0 Cortinceedmaintemecooroanicaoon CRS # 25NR6676 D. I certify that the repair anchor alteration made o the unil(s) wowed in Rem 5 above and described on Me reverse or alladvnenis heieo have been made in accordance with the recturernents of Pan 43 of the U.S. Federal Aviation Regriabons and that the Vdormatinn furnished herein is true and correct lo the best Of my knOveledge. Extended range fuel 43 Pa pa 14 CFFt Part p App. 8 E l SionstureiOale of A.Ockwell 01/04/2013 T. Approval for Return to Sento Pursuant to vie authOnty given persons pearled below, the un /identified in item 5 was inspecled in the manner prescribed by the AdrniniStralOr 01 the Fe...walk/lawn Adminisitatton and is i'll APPROVED 0 REJECTED 13Y FM Fit Standards inspector Manufacturer Matnienents Omardzahon Person Approved by Canadian DeperinveM of Transport FM Designee X Repair Staten Inteection AUMOrite9On 011'el (SPeofy) Camticae of Diesignato . s No CRS N 25NR667B SpriaturciDate of Authorized A.Ockwell 01/04/2013 FAA Form 337 (10-00 SDNY_GM_02758326 SUBJECT TO PROTECTIVE ORDER PARAGRAPHS 7, 8, 9, 10, 15, and 17 EFTA_00245248 EFTA01261908 SDNY_GM_02758327 SUBJECT TO PROTECTIVE ORDER PARAGRAPHS 7, 8, 9, 10, 15, and 17 EFTA_00245249 EFTA01261909 NOTICE Weight and balance or operating linetation 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 ainVOrthinOSS requirements. 8. DescripUon of Work Accomplished (It more spat* is requited attach additional sheets. Identify with aircraft nationality and registration mark and date work completed.) N7B7TA Nationality and Regis/ration Mark Nextant Aerospace Completed STC # ST02371LA: 01/04/2013 Cale Replacement of the Pratt and Whitney JT15D-5 Series Engines with 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. 252745 Installed Right Engine Part Number 111000-202 Serial No. 252746 ICA AFM Supplement was installed on Aircraft. Nextant Aerospace Instructions for Continued Airworthiness Document NXT-ICA Rev IR or later FM 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. See Weight and Balance Dated 12/22/2012 End 0 Additional Sheets Are Attached FAA Form 337 note) SDNY_GM_02758328 SUBJECT TO PROTECTIVE ORDER PARAGRAPHS 7, 8, 9, 10, 15, and 17 EFTA 00245250 EFTA01261910 SDNY_GM_02758329 SUBJECT TO PROTECTIVE ORDER PARAGRAPHS 7, 8, 9, 10, 15, and 17 EFTA 00245251 EFTA01261911 2.i..iftbschd..(9f Department d f transportation - alrebcritl cAbintinit 'that'll' attrition Supplemental Type Certificate .94trent•leara..weelk ./raeneces, ST02371LA Nextant Aerospace, LLC 26180 Curtiss Wright Parkway Richmond Heights, Ohio 44143 CW01. Ante 044170 1:1, 0910 fint/Vir'neViatIV;VelPSICh/Ved, rtritIa4inta arroirtwedZen.A dres/crol'Al CV9tatIVI/IIMIel atirpeearal mawthwana.4 aieeriel 25• v °74 irreArneAciakiv. Saaithivm. *Certification basis is set froth on TCDS Al 6SW and continuation sheets 3 and 4. ifc@aurealgrailei ..fifinWeriaandlcrent‘.. A 16SW -I" Hawker Beecheraft 400A OwerMm aiejw. nwsw Replacement of Pratt & Whitney JTI5D-5 series engine with Williams International FJ44.3AP engine (TCDS E3GL) with Full Authority Digital Engine Control (FADEC) and associated systems, in accordance with Nexiant Aerospace Master Drawing List No.: MDL-NXT-00I, Revision IR 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 NXTI-ICA, Revision IR, or later FAA accepted revisions must be provided with this STC. efallen1/4141,10, 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) rergearnadi 4n4O4 wygeavhir (la te444:0 rcragtAte trifirceriarfrin 4iin a. firs' (mat nweerrtrienni stritutnalvi ettanier a Imwtherhiva teak lJ elitreevat aikridtetereiE r n ago‘40/valar ?en FreinralAntracrerrSthrWrateiva 9,,,,,,0,ydazam March 24, 2008 9174.yreimmea. September 27, 2011 sfro ezenrstded. eineitatrIn. (51timure) dC.-) Manager, Propulsion Branch Los Angeles Aircraft Certification Office (Title) Pay iittmation tf this ratfTwatt u pm:tithe.% Sy a fiat of not girding 14004 or imprisonment net eroding .1 pa; or both. FM ham 4110.211.0.0) rya i Of • lEis artificals may& IMILIfilltri lel WO/4M tiia ItAitn47. SDNY_GM_02758330 SUBJECT TO PROTECTIVE ORDER PARAGRAPHS 7, 8, 9, 10, 15, and 17 EFTA 00245252 EFTA01261912 SDNY_GM_02758331 SUBJECT TO PROTECTIVE ORDER PARAGRAPHS 7, 8, 9, 10, 15, and 17 EFTA_00245253 EFTA01261913 INSTRUCTIONS: The transfer adornment below may be used to notify the appropriate FAA Regional Office of the transit! of this Surrogate-nu i 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 (Wan of trait/re) Organ of transfer) Orinferensers) tin Pan .nziptok) from 6Yarse ofgrantor)print or type) COlirors ofgrantor) FIAndireortfirtl) (Fitx skate tatiptok) Extent of Authority (if licensing agreement): Date of Transfer: Signature of grantor (In ink) File 2 of 4 SDNY_GM_02758332 SUBJECT TO PROTECTIVE ORDER PARAGRAPHS 7, 8, 9, 10, 15, and 17 EFTA_00245254 EFTA01261914 SDNYGM_02758333 SUBJECT TO PROTECTIVE ORDER PARAGRAPHS 7, 8, 9, 10, 15, and 17 EFTA_00245255 EFTA01261915 'Julien Althea jkmericn !rpm:intent of girrn noportat lion - Athena kftintion Abminialration Supplemental `Type Tertifirate (alontinuation *feet) ./reeeniev, ST02371LA 2h:data/at orneonaei&v. amalateW • 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 arc 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 ertoicahip. lath The certification basis for this modification is as follows: The original certification basis for the Hawker Becchcra ft Model 400A airplanes identified on TCDS AI6SW, Revision 26, dated March 17, 2010: Part 25 of the Federal Aviation Regulations effective Febmary I, 1965, as amended by 25-I through 25-40, plus §§ 25.1335, 25.1351(d), 25.1353(4(5), and 25.1447 of Amendment 25.41; §§ 25.29, 25.255, and 25.1353(cX6) of Amendment 2542; and §§ 25.361(6) 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 affective February I, 1974, as amended by 27.1 through 27-5; and Special Conditions No. 25-AN61-32 dated February 22, 1990 (High Altitude Operation at 45,000 feel), and Special Conditions No. 25-AN M-33 dated June 18, 1990 (Lightning and Radio Frequency Energy Protection). (Sec NOTE 12) Equivalent Safely Rant (I) Out-of-trim characteristic, § 25.255 (2) Pilot compartment view § 25:773(b)(2) (3) Passenger compartment door § 25.813(e) (4) Emergency exit marking §§25.811(dXl) and 25.81 l(dX2) Application for amended Type Ceitificate dated Febtuary IS, 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 13— Flight: 25.207(25-121), 25.255(25.42) Subpart C — Structure: 25.571 (25-96) Any diction of this certificate ir purauLar sfy a fire of not ceding O,004 or ingnnonnott me codling 3 pan, or Sink nu term 1119.1110.01 i*In a or 4 %is merles', amy Se (maltaseVI allOWOOKI lath .330(2317. SDNY_GM_02758334 SUBJECT TO PROTECTIVE ORDER PARAGRAPHS 7, 8, 9, 10, 15, and 17 EFTA_00245256 EFTA01261916 SDNY_GM_02758335 SUBJECT TO PROTECTIVE ORDER PARAGRAPHS 7, 8, 9, 10, 15, and 17 EFTA_00245257 EFTA01261917 Xnittb Slake COf iAnwrica Peparhuent of Crtmosporhttion ebern1 Ablation ,Sthministrution Supplemental Zgpe dertifirate (Olontinuation Ate° freedniesST02371LA irenVieeakiniessitrateramr, • 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 —Powerplant: 25.901(25.46), 25303(25400), 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-n, 25.1103(2546), 25.1141(25-115), 25.1143(25-57), 25.1163(25-57), 25.1165(25-72), 25.1181(25-115), 25.1183(25-109, 25.1185(25-94), 25.1189(25-57), 25.1195(25-46), 25.1203(25-123), 25.1207(25-46). Subpart F —Ent:lament: 25.1301(25-123), 25.1305(25-115), 25.1307(25-72), 25.1309(25423), 25.1316(25-80), 25.1317(25422) 25.1321(2541), 25.1331(25-41), 25.1351(25-72), 25.1353(25423), 25.1357(25-123), 25.1381(25-72), 25.1431(25413), 25.1438(25-41), Subpart G — OperatingLimitations 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-n), 25.1557(25-72), 25.1581(25-72), 25.1583(25-105). Subpart H -Electrical Whine Interconnection Systems (EWIS): 7.5.1701(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(25423), 25.1725(25423), 25.1727(25-123), 25.1729(25-123), 25.1731(25-123), 25.1733(25-123). 14 CFR Part 34 (34-3): 34.11 14 CFR Part 36 (36-281: 36.1-36.7, 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 Proccdurr-/Report No. NXT1-EA-007 Rcv A dated 8/24/11 or later FAA approved revisions. -END- Any Iteration of M4 twilfleau it punidadli gy a fr et of not waling 51,m or impnionmont not ageing years, or 6ot1 PM to.w 41141•300-64) •.r 4 at 4 ttrifitat may 6* twain -m(6 rectonfowe nit hcAt21.47. SDNYGM_02758336 SUBJECT TO PROTECTIVE ORDER PARAGRAPHS 7, 8, 9, 10, 15, and 17 EFTA_00245258 EFTA01261918 SDNY_GM_02758337 SUBJECT TO PROTECTIVE ORDER PARAGRAPHS 7, 8, 9, 10, 15, and 17 EFTA_00245259 EFTA01261919 eV MAJOR REPAIR AND ALTERATION u S down. a (Airframe, Powerplant, Propeller, or Appliance) vii, onaw mess mane. Arinirriernern Fr...ingrate ONO No 21200O20 i want? Eaxecnic Tracking Number For FAA Use Onty INSTRUCTIONS. Print or type all entries. See FM 43.t FAR 43 Appeedx B, and AC 43.th I (or subsequent revision thereof) for infinite/MS and disposaro of this form Ths won I required by tow (49 U.S.C. 1421). Faso Oa report can nit in a cmi penalty fret to steeled $1,000 for each such notation (Section 901 FeitierN Aviation Ad 1958) I. Aircraft Nalionelity and Regisvatron Mark N787TA Serial NO. RK-260 Make Hawker Beeeheraft Corporation M00M 400A Series 2 Owner Name (As shown on nmsbabon CeMeeete) Flight Options, LLC &Press (AS shown on registration cemna/e) acrev.26180 Curtiss Wright PKWY cviCleveland sw•Ohio zo44143-1453 caiAviUSA 3. For FAA Use Only 4. Type 6. Unit identification Repair Mention Unit Make Modal Seem Naive, O ID AIRFRAME (AS cleienbecl m Rem 1 above) 0 O POWERPLANT O D PROPELLER O O APPLIANCE Pepe swinacina 6. Conformity Statement A AgenCy a Name and Address B. Kind 0 Atom" unConslant Aviation 0 U.S. Certificated mechanic O Manufacturer Aesess.[ADDRESS REDACTED] 0 Foreign Ceiviscalee Wallowa C. Certificate No. catCleveland sw•Ohio 89 Catocatee Reper Station CRSINVC7R346J hp44135 coa,United State 0 Collacated ManWriance Organzatien 0. Ice-My that the repot antor alteration made lo the wits) idendied in items above and dewibed on se ravine or attachments hemp have been made in accordance we, the requirements of Part 43 it the U.S. Federal Aviaban Regulators and that the information furnished herein itt true end maw to the best or my Ealended range NM per 14 CFR Pan 43 App.I3 O Signature/001e of A ---7 ..(72e" /0244/ 20 / Fo'• 1. Aria • la la Return to Service Pursuant to ere authority given persons specified • .IN ' led in item 5 was inspected In Me manner prescl0ed by tee Administrator of the Federal Aviation AdollinerrabOn and is IS APPROVED O REJECTED BY FM Fe Standards inspector 1Aanufactow Maintenance Organization Person APProniti by Canadian Depanmenl 01 Transport FM Designee X Repair Static., Inspection Autionceben Other (SPecify) avowstar Designalitn No. CRStiWC7R346J Signature/Date of Aurinnzed Mt:MOM (it I A . (0 DEL te-?__ FAA Form 337 pooh SDNY_GM_02758338 SUBJECT TO PROTECTIVE ORDER PARAGRAPHS 7, 8, 9, 10, 15, and 17 EFTA_00245260 EFTA01261920 SDNY_GM_02758339 SUBJECT TO PROTECTIVE ORDER PARAGRAPHS 7, 8, 9, 10, 15, and 17 EFTA 00245261 EFTA01261921 NOTICE Weight and balance or operating limitation changes shaft oe entered in the appropriate aircraft record. An alteration must be compatible with a previous alterations to assure continued conformity with the applicable airworthiness requirements 8. Description of Work Accomplished (If more space is required, attach additional sheets Identity with aircraft nationality and registration mark and date work completed) N787TA 27DEC12 Nationality and Regstration Mark ACCOMPLISHED INTERIOR MODIFICATION AND 3 PLACE DIVAN INSTALLATION Date THE FOLLOWING AIRCRAFT INTERIOR ITEMS HAVE BEEN MODIFIED. PILOT SEAT PART NUMBER TAB/0001140001 SERIAL NUMBER 59. CO-PILOT SEAT PART NUMBER TABH100CM0001 SERIAL NUMBER 56. RIGHT HAND PASSENGER SEAT *1 PART NUMBER 2524 014.5308 SERIAL NUMBER 991215-20, RIGHT HAND PASSENGER SEAT 82 PART NUMBER 2524.014-530B SERIAL NUMBER 991215-23. LEFT HAND PASSENGER SEAT 81 PART NUMBER 2524 014-5300 SERIAL NUMBER 991215-3, LEFT HAND PASSENGER SEAT 82 PART NUMBER 2524.014.5308 SERIAL NUMBER 000925. LAV SEAT CUSHIONS. CONSOLE ASSEMBLY (DADOS). ALL BAGGAGE PANEL MATERIAL. CARPET, AIR STAIR MATERIAL, LEFT HAND GALLEY, RIGHT HAND GALLEY, LEFT HAND AND RIGHT HAND CARD TABLE. LEFT HAND AND RIGHT NAND SIDE LEDGE, RIGHT NAND ARMREST, DIVAN ASSEMBLY. HEADLINER MATERIAL. WINDOW LINE MATERIAL. LOWER SIDE WALL MATERIAL. UPPER AND LOWER ENTRY DOOR MATERIAL. AFT LAV BULKHEAD MATERIAL. AFT BULKHEAD MIRROR. CONTROL COLUMN YOKES MATERIAL GLARE SHIELD MATERIAL DIVAN SEAT CUSHIONS. CABINETRY. CONTROL YOKE BOOTS MATERIAL AND RUDDER PEDAL BOOTS MATERIAL. THE FOLLOWING MANUALS AND APPROVED DATA HAVE BEEN UTILIZED FOR BASIS OF MODIFICATION: o MOWER BEECHCRAFT AMM AND SEIM. NEXTANT MR E0 029-11 EXTERIOR BAGGAGE MODIFICATION AS APPROVED ON FM FORM 8110-3 BY DERT 410115-CE. PAUL HEDDING DATED 28NOV12.. DELTA G DESIGN DRAWINGS. LEFT HAND GALLEY ASSEMBLY DGD-CA01.101 REV B DATED 2&SEP12, LEFT HAND GALLEY INSTALLATION DGD-CAOI-501 REV IR DATED 31JUN12, RIGHT HAND GALLEY INSTALLATION DG/1-CA02-501 REV IR DATED 13JUN12. SIDE LEDGE INSTALLATION 0nI3-r.A04-501 REV IR DATED 13JUN12, RIGHT HAND GALLEY ASSEMBLY DGD-CA02.101 REV. A DATED 08AUG12, CABIN HEADLINER DGD-CA013-101 EO. A-4 DATED IODECIZ CABIN HEADLINER DGD-CA08-101 REV IR. DATED 13JUN12, WINDOW LINER DGOCA07-101 EO A-4 DATED 100EC12, WINDOW LINER OGOCA07-101 REV IR DATED 13JUN12, LAVATORY CABINET DGD-CA10-101 REV IR. DATED 120EC12, LAVATORY HEADLINER DGO-CA11-101 REV IR. DATED 17DEC12, SIDE LEDGE ASSEMBLY DGD-CA04-101 REV IR DATED 3JUN12, SIDE LEDGE ASSEMBLY DGD-CA04-101 EO: AS DATED 20DEC12. AS APPROVED BY DER DONALD GILLESPIE (DERT-750135-SW) ON FM FORM 8110-3 DATED 19DECI2, CARD TABLE INSTALLATION DOD-CA13-501 REV IR DATED 21DEC12. STRUCTURAL SUBSTANTIATION CIGO- CA01-SS-05 REV IR AS APPROVED BY DER DONALD GILLESPIE (DERT-750135-SW) ON FM FORM 8110-3 DATED 21DEC12. ACES FLAMMABILITY SUBSTANTIATION REPORT A121812-01FSR REV. IR AS APPROVED BY DER KEVIN CAMPBELL (DERT-230220-CE) ON FM FORM 8110-3 DATED 1813EC12, ACES FULIAMABILRY SUBSTANTIATION REPORT A102612-01FSR REV. IR AS APPROVED BY DER KEVIN CAMPBELL (CERT-230220-CE) ON FM FORM 8110.3 DATED 21300712, ACES FLAMMABILITY TEST PLAN M120312-01FP REV A AS APPROVED BY DER KEVIN CAMPBELL (DERT- 230220-CE) ON FM FORM 8110-3 DATED 170EC12, ACES FLAMMABILITY TEST RESULTS REPORT M122112-02FR REV IR AS APPROVED BY DER KEVIN CAMPBELL (DERT230220-CE) ON FM FORM 8110.3 DATED 21DEC12. THREE (3) PLACE DIVAN INSTALLATION: INSTALLED THREE (3) PLACE DIVAN PART NUMBER' 32-0398(A8OP)T123.k.02. SERIAL NUMBER: 003851 IN ACCORDANCE WITH AVIATION FABRICATORS INC. STC 8 STO1 572WI. COMPLETE UNIT PIN 400-3. INSTRUCTIONS FOR CONTINUED AIRWORTHINESS: THE REMOVAL OF THE INTERIOR IS ON THE CONDITION OF FAILURE. THERE ARE NO ADDITIONAL INSPECTIONS REQUIRED CONTINUE TO INSPECT IAW MANUFACTURERS AMM. SRM, OR CMM AS APPLICABLE AIRCRAFT EQUIPMENT LIST AND WEIGHT AND BALANCE WERE UPDATED BY THE CUSTOMER 0 Additional Sheets Are Attached FAA Form 337 (loose+ SDNYGIvl02758340 SUBJECT TO PROTECTIVE ORDER PARAGRAPHS 7, 8, 9, 10, 15, and 17 EFTA_00245262 EFTA01261922 SDNY_GM_02758341 SUBJECT TO PROTECTIVE ORDER PARAGRAPHS 7, 8, 9, 10, 15, and 17 EFTA 00245263 EFTA01261923 12DLG-CON-1219D (IS OSPARTMENT OF TRANSPORTATION FEDERAL PATIATiONAOISISTRATION STATEMENT OF COMPLIANCE WITH AIRWORTHINESS STANDARDS I. DATE December 19. 2012 luFtCRAFT OR AiRCRAFT COMPONENT IDEN1111CAT1ON t. MAC Seechjet 3. MODEL NO 400A 4 TYPE Redo. ?tamper s tea OF APPUCAHT Constant Aviation Cleveland, Ohio (Morn. ex ) AIRPLANE UST OF DATA 8 IDENTYWAigN 7 TMF Document No. 0OO-CA10-101 REV: IR Dated: 12/12112 OGD-CA11-101 REV: IR Dated: 12/17/12 LAVATORY CABINET LAVATORY HEADLINER NOTES: MOD. LH MOD, LH Is for Beechfet model 400A iNestant 400XT variant) Sift RK-260 only. is for the structural design aspects only on the above bated 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 intro 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. At 6SW Approvals are provided separately. 1. This approval 2. This approval does not constitute 3. Approval is Compliance does not constitute alteration. Flammability, disciplines. 4. For certification 5. Structural 8. PURPOSE Or DATA To provide type data fo FAA approval of structure in support of a return to service on SIN RK-260. This approval Is for design data only on a major alteration and is not an installation approval. a APPUCAOLE REOUIREMENTS ftn: admit secilcast 14 CFR Part 25.601 AmM 25-0. 15.603(sKti), Aedt 25-38, 25.685 'list 254, 25405 Aredt 254. 25.611, Amdt 25-23, 25.613 (6)41”(c) A rade 25-0, 25619 Arndt 25-23,25.615 Amet 25-23, 2.5.785 (sX6)(001X<K0 Arndt 1542, 25.759 Arndt 15-31 10 CERTIFICATION . Under away Pan Tea data listed stove and on Wet spplorebar reouTernarta Melo 0 Rocommend /few) !hombre 0 wren vested by dtrealon at and teed nuobefird Aintrottlinna Standard. approval *lea IP* Admalabalor 141.4 have and on atarralance wth ceedilons and arnItallons ol appoIntrnefa under 14 CFR been earened In accordant, MU, oatabashed procedures and found to coney UMW. dab thew date II _SIONATURE(S)OF OESIGNAIE0 IMEENING REPRESENTATNE(S) 12 OESICMAOON NUMBER S I] CLASSIFICATIONS) t L ips OERT-750135-SW STRUCTURAL • G FAA Form 8110-3 moo) SVPViStOtS PHEWUS EDITION SDNY_GM_02 758342 SUBJECT TO PROTECTIVE ORDER PARAGRAPHS 7, 8, 9, 10, 15, and 17 EFTA_00245264 EFTA01261924 SDNY_GM_02758343 SUBJECT TO PROTECTIVE ORDER PARAGRAPHS 7, 8, 9, 10, 15, and 17 EFTA_00245265 EFTA01261925 12DLG-CON-1219C V 5 DEPARTMENT OF TRANSPORTATION FEDERAL AvATIONAceleitSTRATON STATEMENT OF COMPLIANCE WITH AIRWORTHINESS STANDARDS F pATE December 19, 2012 AIRCRAFT OR AIRCRAFT COMPONENT 1I€N11FICATWN t. MucE Beechiet 3 MOOEr. NO 400A 4 TYPE WPM AIRPLANE RAS a NAME Of APPLICANT Constant Aviation Cleveland, Ohio irellOcin 44C) UST OF DATA 6 i0ENTiFICATON 1.1$€ Document No. DOD-CAW-101 REV: IR Dated: 6f13/12 DOD-CA06-101 E0:4-4 Dated: 12/10/12 DGD-CA07401 REV: IR Dated: 6/13/12 OGO-CA07-101 ED:A-4 Dated: 12/10/12 CABIN HEADLINER CABIN HEADLINER WINDOW LINER MOD WINDOW LINER MOD MOD MOD Is for Beech)et model 400A (Nextant 400XT varlantl SIN RK.200 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 81103 approvals may be necessary for Damage Tolerance, Mechanical Systems, Eloctrkal. Weight & Balance, as well as other basis, rotor to TC data sheet No. Al 6SW Approvals are provided separately. NOTES: 1. This approval 2. This approval does not constitute 3. Approval is Compliance does not constitute alteration. Flammability, disciplines. 4. For certification 5. Structural 5 PURPOSE Of DATA To provide type data for FAA approval of structure in support of a return to service on S/N RK-260. This approval is for design data only on a major alteration and Is not an installation approval 0. APPLCABLE REOuNDOENTS set nate moose le CFR Part 23.60I Aside 25-0, 25.603(a)(14, Amdt 2.536, 25605 Meet 25-0, 25.609 Arndt 25-0. 25411, Arndt 2523.25.613 (a)(bNc) Arndt 25425.619 Arndt 2S-23.25425 Asa 15-23. 25.785 (a)(b)(e)(dife)(0 Arndt 25-32. 25.7/t9 A mei 3532 ID. CERTIFICATION - trader trararey wend by cdrecial or lie Admired/eta and in liCCOrdars00 wth corvsrooro and lineations or appointment end. 14 CFR Part 183. data Med atom and on tiered sera numtend N/A have teen examined In accordance *de catalpas/wed procedures and found 10 comet? *eh Wale** riKailltments or the Almontinen Slandered Laded 0 Retain/none approval at lege* deb I (We) There/ore 0 **Prow Thole den I ATuROS) Of 0 EroNATE0 ENING RETWESENTATTVHSi 12. DESIGNATION isOINERRS) II tASSiF1CAT S) n N 1 4.71 DERT-750135-SW STRUCTURAL Donald Gilllee le FAA Form 8110-3 irdel 0; SUPERSEDES PREVIOUS EDITION SDNY_GM_02758344 SUBJECT TO PROTECTIVE ORDER PARAGRAPHS 7, 8, 9, 10, 15, and 17 EFTA_00245266 EFTA01261926 SDNY_GM_02758345 SUBJECT TO PROTECTIVE ORDER PARAGRAPHS 7, 8, 9, 10, 15, and 17 EFTA_00245267 EFTA01261927 12DLG-CON-1219A U S DEPARTMENT OF TRANSPORTATION FEDERAL AVIATION Ate4INISTRATION STATEMENT OF COMPLIANCE WITH AIRWORTHINESS STANDARDS I DATE December 19. 2012 AIRCRAFT OR AIRCRAFT COMPONENT IDENTIFICATION 2 MAKE Beedijet 3 MOOEL NO 400A 4 TYPE pUrplaita Rata nalcopfar. at) AIRPLANE 5 MALE Of APPLICANT Constant Aviation Cleveland, Ohio UST OF DATA IOENIIICAI 11 7 TITS Document No. DOD-CAM-101 REV: B Dated: 9/28112 DGD-CA01-501 REV: IR Dated: 6113/12 00D-CA02-101 REV: A Dated: 1908112 DG0-CA02-501 REV: IR Dated: 6/13/12 LII GALLEY ASSY LH GALLEY INSTL RH GALLEY ASSY RH GALLEY INSTL End of Data --is for Beechjet model 400A (Nextant 400XT variant) SIN RK-260 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, E locbical, Weight & Balance, ae well as other basis, refer to TC data sheet No. A16SW Approvals are provided separately. MOTES: 1. This approval 2. This approval does not constitute 3. Approval is Compliance does not constitirte alteration. Flammability, disciplines. 4. For certification 5. Structural I PURPOSE OF DATA To provide type data to FAA approval of structure in support of a return to service on S/N RK-260. This approval is for design data only on a major alteration and Is not an Installation approval. 9 APPLICABLE REQUIREMENTS (OW spodnc [awn/ 14 CFR Pin 25.601 Arndt 25-0, 25.603(.(b), Aside 25-38,25.605 Arndt 2,1.-0. 25.609 Aside 25-0, 25.611. Arndt 25-23.25.6t3 (4X6)(c)Amdt 25-0,25.619 Arndt 25-23,25.615 Arndt 25-23, 25.785 (e)(1))(rXrilfrXf) A aid' 25-32, 25,7119 Attach 25-32 10. CERTIFICATION Under authority vested by bile03011 of ine Adngrattrek. end et atecntanme nee/ amount aryl SMabons of appartmont We 14 CFR Pad 183. data Meted above sod on headed sheet. numbered WA hen been examined In accomlancer wet cdabthed precedulte and lourEl to campy vam aorrwarse resumer/sad the A NrcethInons Standard. Listed 0 FMCOMMend approval at &as date I (V00) Therefor. 0 A0Olva this* 404 to SIGNATURES) OF OEeIOFtA PICANESIING REPRESENTAT 12. DESIGNATION MAAWRS(S) I3 CIASSIFCAMOKSI l, 91--aSiete t / DERT-750135-SW STRUCTURAL Donald Giller sa— FAA Form 111104 (out 0; SUPERSEDES PREVIOUS EIXTION SDNY_Gtvl_02758346 SUBJECT TO PROTECTIVE ORDER PARAGRAPHS 7, 8, 9, 10, 15, and 17 EFTA_0O245268 EFTA01261928 SDNY_GM_02758347 SUBJECT TO PROTECTIVE ORDER PARAGRAPHS 7, 8, 9, 10, 15, and 17 EFTA_00245269 EFTA01261929 12OLG-CON-1219B U.S. OEPARIVENT OF TRANSPORTATION FEDERAL AVIATION ACAMOSTRAncti STATEMENT OF COMPUANCE WITH AIRWORTHINESS STANDARDS 1. DAM December 19, 2012 AIRCRAFT OR AIRCRAFT COMPONENT ID NTWICAMON 2 MAKE Beechjet 3 MODEL NO 400A RFS Notcopfer. 5 NAME OF APPUCANT Constant Aviation Cleveland, Ohio 4. TYPE (airplane, etc/ AIRPLANE LIST OF DATA II IDENDFICA • 7 fiRE Document No. EIGD-CA04-101 REV: IR Dated 6/13/12 DOD-CAN-101 EOA-4 Dated 12)11/12 OGD-CA04.501 REV. IR Dated 6/13/12 SIDE LEDGE ASSY SIOE LEDGE ASSY SIDE LEDGE INSTL NOTES is for Boochjet model 400A (lextant 4001Cf variant) SIN RK-260 only. Is for the structural design aspects only on the above listed data and an installation approval. only for regulations specified In the "Applicable RequIremenb" block. with additional regulations not listed herein may be required. Thia form FAA approval of all engineering design data for the entire Additional 8110-3 approvals may bo necessary for Damage Tolerance. Mechanical Systems, Electrical. Weight a Balance, as well as other basis, refer to TC data shoot No. AI6SW Approvals are provided separately 1. This approval 2. This approval does not constitute 3. Approval is Compliance does not constitute alteration. Flammability, disciplines. 4. For certification 5. Structural $ PURPOSE OF OA t A To provide type data to FAA approval of structure in support of a return to service on S/N RK-260. This approval Is for design data only on a major attention and Is not an installation approval. a APPLCABLE REOPMEMENTS (LW meat NOM* 14 CFR Pan 25.601 Amdt 25-0, 25.603(a)(11), Aped( 25-3a 25.605 emit 25-0, 25.605 Assdt 25-0, 25.61 I, Arndt 25-23, 25.613 faXbKr)Amcli 25-0, 25.619 Amdt 25-23,25.625 Asa 25-23,25.785 (a)(bXON)leXI) Am& 25,32,25.739 Aedt 25-32 10. CERTIFICATION • UnSer 4.441100ty WSW by dreithon cd the Actmrelemor and in accordance with cord:Ochs and Orr Satan of ap000nlmonl um:feria CFR Pail 183. date' led above and an McNiff (boots mentoisd N/A h4v0 boon examined b accordance with esudasnod pr000ciunis and found la carnal ••,10 aniatie roaulternents of Me Aiwa 'ones, Sof 'bents UAW 0 Recommend approval of thee* dilla I (We) Thertiellt el Approve these date II SiGNATURE(S) OF OESiGwi 0 ENGINEERING REPRESEIITATIVEM it DESIGNATION NUMBERS(S) is MASSWICATION(S1 5,L.,s4Q . . DERT-750135-SW STRUCTURAL Donald GI e Att .t d le FM Form 9110-3 (OLIO) SUPERSEDES PREVIOUS EDITION SDNY_GM_02758348 SUBJECT TO PROTECTIVE ORDER PARAGRAPHS 7, 8, 9, 10, 15, and 17 EFTA_00245270 EFTA01261930 SDNY_GM_02758349 SUBJECT TO PROTECTIVE ORDER PARAGRAPHS 7, 8, 9, 10, 15, and 17 EFTA 00245271 EFTA01261931 (660) 885.8317 (660) 885-3743 Fax vommavf abeam email: saleseaviabeom AUTHORIZATION OF STC USE: DATE: 12-17-12 TO: Nextant Aerospace LLC 26180 Curtiss Wright Parkway Cleveland, OH 44143 AVIATION FABRICATORS Reference your order number: 003793 . Authorization is hereby given for one time usage of Supplemental Type Certificate Number SA001572W1 install Aviation Fabricators' Beecheratl 3 Place Divan w/ Tabs P/N 32-0396(A6011T123.K-02 SIN 003651 . This kit is approved for installation on Beechcra ft , 400A (airman make) (aircraft I model) RK-260 (raw Number of airman) Aviation Fabricators 805 North Fourth Street Clinton, Missouri, 64735 og e Inspector (Note: ibis emu be original tyro on colored AvOsIon Fabriudors knechead) Aviation Fahrkators • Central Airmotive 805 North Fourth Street. Clinton, Missouri 64735 SDNY_GM_02758350 SUBJECT TO PROTECTIVE ORDER PARAGRAPHS 7, 8, 9, 10, 15, and 17 EFTA_00245272 EFTA01261932 SDNY_GM_02758351 SUBJECT TO PROTECTIVE ORDER PARAGRAPHS 7, 8, 9, 10, 15, and 17 EFTA_00245273 EFTA01261933 LI S. DEPARTMENT OF TRANSPORTATION FEDERAL AVIATION ADMINISTRATION STATEMENT OF COMPLIANCE WITH AIRWORTHINESS STANDARDS 1. DATE October 9, 2012 AIRCRAFT OR AMCRAFT COMPONENT IDENTIFICATION 2. LUKE Hawker Beechcraft Corporation 3. MODEL NO. 400A Beechjet 4. TYPE (Aka** Enders, Proposer. Mt.) Aircraft 5. NAME OF APPLICANT Constant Aviation, LLC LIST OF DATA e. IDENTIFICATION T. TITLE Report: A100912-01FP REV IR END FLAMMABILITY TEST PLAN - YOKE COLUMNS - HAWKER BEECHCRAFT CORPORATION MODEL 400A BEECHJET SN RK-327 Note: 1. Approval of test results is required. END PURPOSE OF DATA Document the flammability test requirements for the installation of new coverings to the yoke columns on Hawker Beechcraft Corporation Model 400A Beechjet SN RK-327. Test plan approval only, in support of a major alteration. 8. APPLICABLE REQUIREMENTS (List specific sections) 14CFR Part 25.853(a) at Amendment 25.116 10. CERTIFICATION inter millionty Pan UM. Seta fisted store and on attached Milt wens. repeal...ants cr ON AmoorMiness misled by drection al Ow Pdminisinsice and in accordance sMt numbered None harm boon examined Mtn conditions end insane cieepoinknera under 14 CFR in neordence vier estatethed procedures and bend to comply Standards Wed. approval of these data data U Recommend 1 eAle) Therefore 0 Approve these 11 SIGNATURE(5) OF DESIGNATED ENGINEERING REPRESENTATIVE(5) 12. DESIGNATION NUMBERS(S) 13. CLASSIFICATION(S) Aviabon Contemn° a Engineer SoluZne. K.C. Campbell - DEBT-230220-CE Structures FAR 23 & 25 FAA Form 8110-3(03110) SUPERSEDES PREVIOUS EDITION SDNY_GM_02758352 SUBJECT TO PROTECTIVE ORDER PARAGRAPHS 7, 8, 9, 10, 15, and 17 EFTA_00245274 EFTA01261934 SDNY_GM_02758353 SUBJECT TO PROTECTIVE ORDER PARAGRAPHS 7, 8, 9, 10, 15, and 17 EFTA_[ADDRESS REDACTED]ATEMENT OF COMPLIANCE U S. DEPARTMENT OF TRANSPORTAT ON FEDERAL AVIATION ADM NGTRATON WITH AIRWORTHINESS STANDARDS i DATE October 10. 2012 AIRCRAFT OR AIRCRAFT COMPONENT IDENTIFICATION 2. MAKE Hawker Seethe/aft Corporation 3. MODEL NO. 400A Beechjet 4 TYPE (AMTPE EnSithei Pi01/6eW e(c) Aircraft 5 NW OF APPLICANT Constant Aviation. LLC LIST OF DATA llIDENTIFICATICD 7 TITLE Report: A101012-01FR REV IR u . END FLAMMABILITY TEST HAWKER BEECHCRAFT Notes: 1 The flammability listed above subparagraph 2. This form does RESULTS - YOKE COLUMNS- CORPORATION MODEL 400A BEECHJET SN RK-327 aspects only of the above listed data are approved herein. It indicates the data demonstrates compliance only with the regulations specified by paragraph and listed below as 'Applicable Requirements.' not constitute FM approval of all the engineering data necessary for of compliance to necessary requirements for the entire alteratiordrepair. With additional regulations may be required. =nu: END substanbation Compliance PURPOSE OF DATA Document Hawker Beechcraft Corporation the flammability test results for the installation of new coverings to the yoke columns on Model 400A Beechjet SN RK-327 in support of a major alteration. 8. APPLICABLE RECSAFtEMENTS 14CFR Part 25.853(a) at Amendment DIM specific sections) 25-116 10. CERDFCATI0N -Under sumonty PIP 183. data listed above and on enIKIWKI wall applicable requiranonla d the Aewalthiness K Recommend I ( we) Thorofare 12 Approve these tested by chrechon d the Adminshatof and in accordance shoeis numbered None have been examined wth oonloares and limitations tg in acoatdenoe with established procedures appoffianeni under 14 CFR and bond to co Standards lisled approval of these data data P/1 11. SIGNATURE'S) OF OESIGNATED ENGINEERING REPRESENTATIVE(S) 12. DESIGNATION NUMBERS(S) II CLASSIFICATIONIM Aviation Consuming & Engineer:0ns, K.C.Campbell Jpc. - &iga( 0ERT-230220-CE Structures FAR 23 & 25 FAA Form 6110-3(03/10)SUPERSEDES PREVIOUS EDITION SDNY_GM_02758354 SUBJECT TO PROTECTIVE ORDER PARAGRAPHS 7, 8, 9, 10, 15, and 17 EFTA_00245276 EFTA01261936 SDNY_GM_02758355 SUBJECT TO PROTECTIVE ORDER PARAGRAPHS 7, 8, 9, 10, 15, and 17 EFTA_00245277 EFTA01261937 U.S. DEPARTMENT OF TRANSPORTATION FEDERAL AVIATION ADMINISTRATOR STATEMENT OF COMPLIANCE WITH AIRWORTHINESS STANDARDS t. DATE December 17, 2012 AIRCRAFT OR AIRCRAFT COMPONENT IDENTIFICATION 2. MAKE Hawker Beechcraft Corporation 3. MOOEL NO. 400A Beechjet 4. TYPE (Aitraft, Engine. Propels,. etc) Aircraft 5. NAME OF APPLICANT Constant Aviation, LLC UST OF DATA 6 IDENTIFICATION 7. TITLE Report: Al20312-01FP REV A g===. END FLAMMABILITY AND FIREBLOCK TEST PLAN - INTERIOR REFURBISHMENT - HAWKER BEECHCRAFT CORPORATION MODEL 400A BEECHJET SN RK-260 Note: 1. Approval of test results is required. a END nix= ====siss=======sasam=== scr.========a ______us= PURPOSE OF DATA Document the flammability and fireblock test requirements for the interior refurbishment on Hawker Beechcraft Corporation Model 400A Beechjet SN RK-260. Test plan approval only, in support of a major alteration. a. APPLICABLE REQUIREMENTS (List specific sections) 14CFR Parts 25.853(a)(c) al Amendment 25-116 10 CERTIFICATION .under WINN* Pail 183. dam Wed Move and on attached 'nth weak tepirermrits of the Airworthiness Cl Recommend I PAW metres 83 Approve then tined by section of vie Admileltalce and in scootance sheets numbered Nate have been examined MITI coaddoas and limeitions of apporment inlet 14 CFR in acconiance '.4th 'wampum mocedures and found 10 Wray Standards listed approval of these data data II. SIGNATURE(S) OF DESIGNATED ENGINEERING REPRESENTATIVE(S) 12. DESIGNATION NUMBERS(S) IT. CLASSITCATIOMM Aviation Consuking & E - nip Bolutioc ; fc. K.C. Campbell DERT-230220-CE Structures FAR 23 & 25 FAA Form 81104 03110) SUPERSEDES PREVIOUS EDITION SIDNY_GM_02750356 SUBJECT TO PROTECTIVE ORDER PARAGRAPHS 7, 8, 9, 10, 15, and 17 EFTA 00245278 EFTA01261938 .__I SDNY_GM 02758357 SUBJECT TO PROTECTIVE ORDER PARAGRAPHS 7, 8, 9, 10, 15, and 17 EFTA_00245279 EFTA01261939 12DLG-CON-1221B U S DEPARTMENT OF TRANSPORTATION FEDERAL AVIATOR ADIMIMISTRATICM STATEMENT OF COMPLIANCE WITH AIRWORTHINESS STANDARDS I. DATE December 21, 2012 AIRCRAFT OR AIRCRAFT COMPONENT IDENTIFICATION 2 MAKE Beechjet 3. MODEL NO 400A 4 TYPE (Want AIRPLANE R . 5 MMIE OF APPLICANT Constant Aviation Cleveland, Ohlo Himoacter. aft) LIST OF DATA a inCJITIFICATION 7 TIDE Downer* No. DGO-CA01-SS-05 REV: IR Dated: 12/21/12 SUBSTANTIATION ANALYSIS NOTES: OF THE INTERIOR ON AN HAWKER BEECHCRAFT 400A AIRCRAFT Is for Beechjet model 400A (Nextant 400XT variant) SIN RK-260 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 heroin 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. AISSW 1. This approval 2. This approval does not constitute 3. Approval is Compliance does not constitute alteration. Flammability, disciplines. 4. For certification II PURPOSE OF DATA Structural substantiation in support of FAA Form 337 for aircraft S/N RK-260. This approval is for design data only on a major alteration and is not an installation approval. S. APPLICABLE REQUIREMENTS U.S spedac sedan) 14 CFR Part 25.301lAmdt.25-23l, .303lAmilL 25-231, .305(aKINIA fedi- 25-23h .307Radt 25-231, ..341latath. 2.5-01,3611Asdt. 25-23I, .60liAtodt. 25-0h .6030KbilAnadt. 25-3Sh.6051Amdt 2-5-01,.609lAmdt.25-0I,.61 liAtedt. 25-231, -613(aXb)(e)IAaadl 2S-01..625 IA red t. 25. 23I,•73filaXIIX4XdX4)(filAmdt.25-32I..787(aKAmdt 25-321.7IMIAmdt. 25-321 10 CERTIFICATION - Under eiAnOray vested by dliecbon of the Adieldeltailor and in sCCordan00 wIth COndiliOnt and anaiadat5 el App6ntivrant undo( 14 CFR Pad 183. data listed above and en attached cheats numbered WA have been examined in ecoadance wan estabashed premiums and found to comply 'AIR OPP/iced, requaementa of the AlronnOness Stardards LIsled. K Recommend approve of these data I (NMe) Therefor IS) Approve these data I I i TURE(S) OF DESCNA ENGINEEPSIG REPRESENTATIVES) 12. DESIGNATOR NUMBERSIS) '3 CLASSIFICADONSSI ri. I bient-4 OERT-750135-SW STRUCTURAL Id Gilles SDNY_GM_02758358 SUBJECT TO PROTECTIVE ORDER PARAGRAPHS 7, 8, 9, 10, 15, and 17 EFTA_00245280 EFTA01261940 J SDNY_GM_02758359 SUBJECT TO PROTECTIVE ORDER PARAGRAPHS 7, 8, 9, 10, 15, and 17 EFTA_00245281 EFTA01261941 U.S. DEPARTMENT OF TRANSPORTATION FEDERAL AVIATION ADMINISTRATION STATEMENT OF COMPLIANCE WITH AIRWORTHINESS STANDARDS 1. DATE December 21, 2012 AIRCRAFTORAIRCRAFTCOMPONENT IDENTIFICATION 2. MAKE Hawker Beechcraft Corporation a. ri00e. NO. 400A Beechjet 4 TYPE OUR:raft &vim Preplan et) Aircraft S. NAME OF APPOCANT Constant Aviation, LLC . UST OF DATA 6 IDENTIFICATION 7. TITLE Report: A122112-02FR Rev IR END FLAMMABILITY AND FIREBLOCK TEST RESULTS - INTERIOR REFURBISHMENT - HAWKER BEECHCRAFT CORPORATION MODEL 400A BEECHJET SN RK-260 Notes: 1. The flammability aspects only of the above listed data are approved herein. 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 does not constitute FM approval of all the engineering data necessary for substantiation of compliance to necessary requirements for the entire alteratioNrepair. Compliance with additional regulations may be required. ===i11 = = =n n. = END 31:1¢===.7t==.72111: elf )matt Mt= PURPOSE OF DATA Document the flammability and fireblock test results for interior refurbishment on Hawker Beechcraft Corporation Model 400A Beechjet RK-260 in support of a major alteration. 8. APPLICABLE REQUIREMENTS (Ust Weak 640440 14CFR Parts 25.853(a)(c) at Amendment 25-116 to. CERTIFICATION. rider authority Pan 181 data listed repro and on attached wen appleade requirements of Me Ainsonibeets El Recommend vested by direction of the Administrator end in aixordance sheets numbered None_ nave been ataininect MT Mattes and Imitations of appointment under 14 CFR In aosceciance war estateened procedures and found to comply Standards Wed. approval of then data data I PAM Therefore el Approve these II. SIGNATURE(S) OF DESIGNATED ENGINEERING AEPRESENTATIvE(S) 12. DESIGNATION NUMBERS(S) i 3 CLASSIFKATION(S) Aviation Consulting & E ring So iqns. IMP. ( K C. Campbell DERT-230220CE &mans FAR 23 8 25 FAA Form 8110-3(07110) SUPERSEDES PREVIOUS EDMON SDNY_GM_02758360 SUBJECT TO PROTECTIVE ORDER PARAGRAPHS 7, 8, 9, 10, 15, and 17 EFTA_00245282 EFTA01261942 SDNY_GM_02758361 SUBJECT TO PROTECTIVE ORDER PARAGRAPHS 7, 8, 9, 10, 15, and 17 EFTA 00245283 EFTA01261943 U.S. DEPARTMENT OF TRANSPORTATION FEDERAL AVIATION ADMINISTRATION STATEMENT OF COMPLIANCE WITH AIRWORTHINESS STANDARDS I. DATE November 27, 2012 AIRCRAFT OR AIRCRAFT COMPONENT IDENTIFICATION 2 MAKE Hawker Beechcraft Corporation 3. MODEL NO 400A 4 TYPE (Aircraft. Enpna Aoperim NO Aircraft S. NAME OF APPLICANT Natant Aerospace LLC Cleveland. Ohio, LIST OF DATA a IDFNTIFICATSIN 7 TITO E EC 1018 Rev. A December 26, 2012 Pedestal Cover Extension Mod. 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 "Appticabie Requirements' 2) This form constitutes FAA approval of all the engineering data necessary for substantiation of compliance to necessary requirements for the entire aeration. B. PURPOSE OF DATA Engineering data in support of major alteration to Hawker Beechcraft 400A. SIN RK-260. I. APPLICABLE REOUIREMENTS (List specific seams) CFR 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)(bXc)(25-00), 25.619(25-23), 25.625(a)(b)(c)(25-23). and 25.789(25-32). 10 CERTIFICATION • Under evinanty Pan 103. an Wad Move and an appicala Meurainents ri/ its Air...Winans 0 Recommend I (We) TheledOre 0 Approve aimed by muse, el du aaa040 /NMI hung:dead SI _ Mandan:Is Utast Adereasidnx and in ecomilenos van conditions and Iniketions cd appoinment under 14 CFR hays Wm entirramd in imotalermia sale sstetasned peccedures and found to cony* tvrei data approval of these these data II SIGNATURE(S) OF DESIGNATED ENGINEERING REPRESENTATIVE(S) 12 DESIGNATION NUMBERS(S) ¶3 CLASSIFEATION(S) :4-'' '4%-- Paul Hedding DERT-410115-CE Structures FAA Form 8110-3 (03-10) SUPERSEDES PREVIOUS somou File HUMS' 102734-01 Pagel N l SDNY_GM_02758362 SUBJECT TO PROTECTIVE ORDER PARAGRAPHS 7, 8, 9, 10, 15, and 17 EFTA_00245284 EFTA01261944 SDNY_GM_02758363 SUBJECT TO PROTECTIVE ORDER PARAGRAPHS 7, 8, 9, 10, 15, and 17 EFTA 00245285 EFTA01261945 MAJOR REPAIR AND ALTERATION (Airframe, Powerplant, Propeller, or Appliance) Fara OCceaved Oettliee 21200520 linOrXO7 _ Electronic Tracers Number or IAA Use Ent, INSTRUCTIONS: Pnnt or type all entries. See Title 14 CFR §43.9. Part 43 Appendix B. and AC 43.9-1 (or subsequent revision thereof) for indructiOns and disposition of this form This report is required by law (49 U.S.0 §44701). Failure to report can result in a civil penalty for each such violation. (49 U.S.C. 546301(a)). 1. Aircraft Nationality and Registration Mark N787TA Serial No. RK-260 Make Raytheon Aircraft Company Model 400A Saes 2. owner Name (As shown on registration certificate) Flight Options LLC Address (AS shOwn on registration certificate) 26180 Curtiss Wright Pkwy Richmond Heights. Ohio 44143-1453 3. For FM Use Only 4. Type 5. Unit IdentlikatIOn Repair Alleraion Unit Make Model Serial No. ., AIRFRAME — (As clesathed in Item 1 above) POWERPLANT PROPELLER APPLIANCE Type Manufacturer 6. Conformity Statement A Agencys Name and Address B. Keo of Agency Flying Colours Corp. R.R. #5, Peterborough Airport Peterborough, Ontario K9J 6X6 CANADA U.S. Certificated Mechanic I Manufacturer i Foreign Certificated Mechanic C Certificate No. Certificated Repair Station Canadian AMO 45-05 Certificated Maintenance Organization D I certify that the tepee and/or alteration made to the unit(S) identified in dem 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 5 true and correct to the test of my knowledge. Extended range fuel per 14 CFR Part 43 App. B (If yes, place 1 copy On board) Signature i Date of Authorized Individual FCC 45, December 13, 2012 ACA 5.. Tim Pickett 7. Approval for Return to Service Pu suant to the authority given persons speoted bans the unit identif eel in item 5 was inspected in the manner prescnbed by the Administrator of the Federal Aviation Administration and is V APPROVED _ REJECTED B V FM FR Standards Inspector Manufacturer Maintenance Organization V Persons Approved by Canadian Department of Transportation FM Designee Repair Station Inspection Authorization Other (Specify) Certificate or Designation No. Canadian AMO 45-08 Signature / Date of Authorized Individual i 1 1/4\ FCC I LSO Is-sr December 13. 2012 ACA 2 Tim Pickett I OA tam 337 BOOR SDNY_OM_02759364 SUBJECT TO PROTECTIVE ORDER PARAGRAPHS 7, 8, 9, 10, 15, and 17 EFTA_00245286 EFTA01261946 NOTICE Weight and balance or operating limitation changes shall be entered in the appropnate a ircrafl record. An alteration must be compatible with all previous alterations to assure continued conformity with the applicable airworthiness requirements 8. Description of Work Accomplished (If more space is required, attach additional sheets. Identify with aircraft nationality and registration mark and date work completed.) N787TA Nahonany and stassurairon Stark December 13.2012 Date USE OF JETGLO PAINT ON WINDSHIELD / WINDOW RETAINERS 1) U.S. Technical Engineering Order EO 6546.001 'Protective Material Substitution • Use of JetGlo Paint on Outer Windshield and Side Window Retainer applied. 2) This alteration is approved under FM Form 8110-3 issued by Robert M. Halvorson, DERT•605221•NM, dated October 12, 2012. 3) There are no additional continuing airworthiness inspections required as a result of this work. The inspection criteria and frequency of these areas is covered in the existing Eleechjel 400A inspection program. 4) This installation has no effect on aircraft weight and balance. 5) Details of work performed are maintained on file al Flying Colours under work order 125842. END No Additional Sheets Are Attached SDNY_GM_02758385 SUBJECT TO PROTECTIVE ORDER PARAGRAPHS 7, 8, 9, 10, 15, and 17 EFTA_00245287 EFTA01261947 SIA.JOR REPAIR AND ALTERATON Fong. /ached 048 mu. zilsCO20 (Airframe, PowitrptuR, Propeller, or Appliance) et Nauss asp zsgmrs Ps•••••••••• Ialwarefr. (A-4 -rt tr r - terRIXTIZea Pena pp el /nem *OW at PSI 0 Aipital I keis I IC Cal relet~n ors need) Wm/ oray eietdepasikn gnaw Ttetempal le mi ttilis VOIJAC lab Ranregettommaincia pear fotb eaptaltd.0O3 ' Wadi womeloixt Pleelent01 Heal aka Illr Ws EAwwnw MS Braila-Err I ioo.9 t Mame BOON. "RK- 2reo /Say et limpid° WA N-icrim t awe Nne(Ag awn M SIS0.07111S0 /9/4 611a549./Ne Xi*. c 7 --A‘ MSS (As ton aro" beta /Veins t: I F. s'iant 4.47 7 ae Igo Curia ...Ai 1:11-1,44W lathnona AlitMiln,01/ 1N, SI • Re Wallin OS 1 a Ilei SEMIS A TOP* tali Ible Mal 1 • Illna *Or Alerette >" < AlPritnii Is bon f Mau) foes eleecte/ POPMEPLANT mass • warm Tv* ttrosike • cosw.ltrImamwd A Pesaro ere /41••• I Ott d Pen C outleat pdperweirti -Atin4) Slog .:u.licsassistriffic final cams werant nOF ciip V& .24,10o <ally id M/I7 frooKNAN y bb Co:ASS Rapt Mom 2/VM/VaD Warm ON ilYitt a kgmhawit 10..delse Mewl 4 sae midemebel ante ergeme et bob Mt es Ow KEE inlet mob law MO US Felliat Mtn ApirMni Sidle Farm Ise mode t. nabs eV* wasieelll boa, Is lee irdaermitalebeeteferelesS 0112.• Die 7 /10 ---Corbs, et Wersion reltilliel --- a r I frogradlw Riga% Simla* Ina Iner~ Mom 4••• Impeed h env__ pmallyelbr4 nnaltion Iota gIonPIIIIr• •PaastIbibm 04•44m1• as Real lalkokInsturo b. PI MOCOMD pica • are ilwallielme np.e6:naseteeien abassigl PAR ! Mae yr humps taws . Clew Dias *teal MRS filla /O S ..,- Capeen n iglart i Xo tt Joeee ' steridatal-10 d eco tz_110 ,6-4 rnka rmatia I _ _ a efuld 5oo:n so-oi-A0N !nig/Gioia I REM-VW soy 1 4 2405 at -Gus !SN0Ild0 1N0Ild :Ag ;Ras SDNY_GM_02758368 SUBJECT TO PROTECTIVE ORDER PARAGRAPHS 7, 8, 9, 10, 15, and 17 EFTA_00245288 EFTA01261948 SDNY GM 02758367 SUBJECT TO PROTECTIVE ORDER PARAGRAPHS 7, 8, 9, 10, 15, and 17 EFTA_00245289 EFTA01261949 NOIICE WSW ind has witeandiotaiSs abseiptslai to oaken* be esepkit • steal nowt AA moth. areeilltainie dpateillindbimb ono cats/ critarstrie opplbsilb Sam• • S. Dellattles at Vitt Mileaked parmeapeas kropant St edeased arm mme INIIIIssly ow I itglelses sash a I debisalt ompelati gOvovei, afrAi emnrite 44D .4vir4ed,r4, jetvgi9IVAwr &4rrns' 47r 0WO In 57a 5775 11911LA .1 In/ Seca -4)494r 1.42-4,vr ANA 0'7,9zAtice I Earn' 10-744 la( DitreP .271 .9aege Recola I O a6oci :00:Cl SO-0I-A0N rathOnine nt !potato/9'e !SN0Ild0 1H0Ili :AS zuec SUBJECT TO PROTECTIVE ORDER PARAGRAPHS 7, 8, 9, 10, 15, and 17 EFTA 00245290 EFTA01261950 SDNY_GM_02758369 SUBJECT TO PROTECTIVE ORDER PARAGRAPHS 7, 8, 9, 10, 15, and 17 EFTA_00245291 EFTA01261951 _,. F - Form Approved . OMB No 2120-0020 MAJOR REPAIR AND ALTERATION Powerplant, Propeller, Appliance) For FM Use Only (Airframe, or /tigi eon P til-S -3 INSTRUCTIONS Print or type an entries See FAR 43 9, FAR 43 Appendix 8. and AC 43.9-1 (or subsequent thereof) for instructions and *position of this form This report is requited by law (49 U S C 1421) Failure to report can result in a clvil penalty not to exceed $1,000 for each such violation (Section 901 Federal Aviation Act of 1958) 1. Aircraft Make Raytheon Aircraft Company Model 400A Serial No. RK-260 Nationality and Registration Mark N787TA 2. Owner Name (As Sheen on registration certificate) Grand/Sakwa Transportation LLC Go Flight Options LLC Address (As shown on registration certificate) 26180 Curtiss-Wright Parkway Richmond Heights, OH 44143-1453 3. For FAA Use Only 4. Unit Identification 5. Type Urn: Make Model Serial No Repair MOr3tOrl AIRFRAME -- (As described in Item 1 above) ---- i POWERPLANT PROPELLER APPLIANCE Type Manufacturer 6. Conformity Statement A Agency's Name and Address B Kind of Agency C. Certificate No. Rapid Aircraft Repair, Inc. U.S. Certificated Mechanic R.R. #5, Peterborough Airport Foreign Certificated Mechanic AMO 73-92 Peterborough, Ontario v Certificated Repair Station - Canadian K9J 6X6 CANADA Manufacturer D. I certify that the repair and/or alteration made to the ya(s) ten made in accordance with the requirements of Part 43 of the U.S. Federal to the best of my knowledge. ified in item 4 above and deserted on the reverse or attachmentS Aviation Regulations and that the Information furnished hereto have been herein is true and correct t, al Date June 1, 2004 Signature of Authorized Individual n l ett 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 .1 APPROVED _ REJECTED BY FM Flt Standards Manufacturer Inspection Authorization Other (Specify) FM Designee Repair station v PenrsznaAtriprovAli by Transport Date of Approval or Rejection June 1, 2004 Certificate or Designation No. AMO 73-92 of Authorized Ind./Coal Tim Pickett FM Form 33? (2a1 U.S GPO' 11004463-171 SDNY_GM_02758370 SUBJECT TO PROTECTIVE ORDER PARAGRAPHS 7, 8, 9, 10, 15, and 17 EFTA_00245292 EFTA01261952 NOTICE Weght 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 w,th the applicable airworthiness requirements. S. Description of Work Accomplished (If more space is required. attach additional sheets. Identify with aircraft nationality and registration mark and date work completed.) GRAPHIC FILM 220 APPLICATION 1) Applied 3M Graphic Film 220 and 7-Year Metallic Series Film to exterior of aircraft per Flight Options Engineering Directive EDU91-1 Rev B dated 3/19/04 and EDU91-2 Rev A dated 3/19/04: and FAA 8110-3 form issued by William B. Cotney, Jr., DERT-510080-CE, dated March 19, 2004. 2) There are no additional continuing airworthiness inspections required as a result of this mod cation. Inspection aiteria and frequency for this item is contained in the existing Beechjet 400A airframe inspection program. 3) This modification has no effect on aircraft weight and balance. 4) Details of work performed are maintained on file at Rapid AircraftSepair under work order 042771. ""'END 1 Additional Sheets Are Attached SONY_GM_02758371 SUBJECT TO PROTECTIVE ORDER PARAGRAPHS 7, 8, 9, 10, 15, and 17 EFTA_002A5293 EFTA01261953 U.E. DEPARTMENT OF TRANSPORTATION FEDERAL MAANONADMINISTRATION STATEMENT OF COMPLIANCE WITH THE FEDERAL AVIATION REGULATIONS DATE March 19, 2004 AIRCRAFT OR AIRCRAFT COMPONENT IDENTIFICATION MAKE Raytheon Aircraft Co. MODEL NO. 400A TYPE fitltja.... Sadie. asigeepter, *Ie. Airplane NAME OF APPLICANT Flight Options, LLC Richmond Heights, OH 44143 LIST OF DATA IDENTIFICATION TITLE Right Options, LLC Dwg: EDU91.1 Rev B Dated: 3/19/04 Flight Options, LLC Dwg: EDU91.2 Rev: A Dated: 3/19/04 GRAPHIC FILM 220 APPLICATION 7-YEAR METALLIC SERIES FILM APPLICATION • END NOTES: Note: I) Approval for structural aspects of the above listed data only. 2) This approval is valid only for Raytheon Aircraft Co.400A S/N: RK-260 (N787TA) PURPOSE OF DATA To show compliance with the regulations listed below in suppnn of exterior graphic film application. This is design data approval only, not installation approval. APPLICABLE REQUIREMENTS (slat spealtic sec AAAAA t FAR 25.601, 25.603, and 25.605 CERTIFICATION - Under the authority vested by direction of the Administrator and in accordance with the conditions and limitations of appointment under Part '83 of the Federal Aviation Regulations. data listed above and on attached sheets numbered AS ABOVE have been ClaMillett in accordance with established procedures and found 10 comply with applicable requirements of the Federal Aviation Regulations. I (sficicrinwnatire 0 Recommend approval or these data El Approve these data SIGNATURES) OF DESIGNATED ENGINEERING REPRESENTAT (SI DESIGNATION NUMBERSIS) CLASSIFCAT/ON(S) DERT-510080-CE -STRUCTURES- William B. Color/. Jr. b hike .s .4 1- Ir ..70) SUPERSEDES PREVIOUS EDITION •3O91•Ese SDNY_GM_02758372 SUBJECT TO PROTECTIVE ORDER PARAGRAPHS 7, 8, 9, 10, 15, and 17 EFTA_00245294 EFTA01261954 I SDNY_GM_02758373 SUBJECT TO PROTECTIVE ORDER PARAGRAPHS 7, 8, 9, 10, 15, and 17 EFTA_00245295 EFTA01261955 APR 01 2004 I C E MAJOR REPAIR AND ALTERATION us OnwIrrem e (Airframe, Powerplant, Propeller, or Appliance) Federal...WM:in orii_ MISAMIsalion .00 Form Approved No. OMB 2120-0020 For FAA Us* Only Office Identification suArniAZEST)0 can result in nenalty not INSTRUCTIONS: Print or type all entries. See FAR 43.9. FAR 43 Appendix B. and AC 43.9-1 (or instructions and disposition of this form. This report is required by law (49 U S.C. 1421). Failure to report to exceed 51.000 for each such violation (Section 901 Federal Aviation Act of 1958). 1. Aircraft Make RAYTHEON Model 400A Serial No. RK-260 Nationality and Registration Mark USA N787TA 2 Owner . Name (As shown on registration certificate) KIRK AIR LLC ET-AL Address (As shown on registration certificate) CIO FLIGHT OPTIONS LLC 26180 CURTISS WRIGHT PARKWAY RICHMOND HEIGHTS OH 44143 . 3. For FAA Use Only 4. Unit Identification 5. Type Unit Make Model Sena! No. Repair Alteration AIRFRAME (A described in item 1 above) X POWERPLANT PROPELLER APPLIANCE Type Manufacturer 6. Conformity Statement A. Agency's Name arid Address 8. Kind of Agency C. Certificate No. JAY 'EMERSON DAVIS CIO FLIGHT OPTIONS LLC 26180 CURTISS WRIGHT PARKWAY RICHMOND HEIGHTS, OH 44143 X U.S. Certificated Mechanic AP 2788753 Foreign Certificated Mechanic Certificated Repair Station Manufacturer D. I certify that the repair and/or 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 rogue ements 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 March 29, 2004 Signature of Authorized ividual 914 7. Approval for Return To Service P Administrator BY rsuanl to the authority g von persons specified below the unit identified in item 4 was inspected in the manner prescribed by the of the Federa Aviation Administration and is IG APPROVED 0 REJECTED FAA Fli. Standards Manufacturer Inspection Authorization Other (SPecify) FLIGHT OPTIONS LLC, AIR FAA Designee Repair Station Person Approved by Transport Canada Airworthiness Group Date of Approval or Rejection Ma ch 29, 2004 Certificate or Designation No. DJFA206D Signature of Authoriz • - WI KEITH GAWSYSZAWSKI rMt 33/ SDNYGM02758374 SUBJECT TO PROTECTIVE ORDER PARAGRAPHS 7, 8, 9, 10, 15, and 17 EFTA_00245296 EFTA01261956 a 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. 8. Description id,Work Accomplished (If more shoes is required, attach additional sheets. Identify with aircraft nationality and registration mark and date work completed.) INSTALLED ROCKWELL COLLINS, INC., SUPPLEMENTAL TYPE CERTIFICATE 4.51-00881WI-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 V Additional Sheets Aro Attached 1.l.S.GPO:1994-568-012/00019 SDNY_GIA_02758375 SUBJECT TO PROTECTIVE ORDER PARAGRAPHS 7, 8, 9, 10, 15, and 17 EFTA_00245297 EFTA01261957 ilnittbAtatto of Atoosica Pepartnient of transportation -- Xtberal Abiation Abministraiion Supplemental Zupe Certificate .i'Veinghoe s-roossiWI-D .$74 ete15,44.... 4.4tedie Rockwell Collins, Inc. 400 Collins Road NE, MS 164.100 Cedar Rapids, IA 52498 ~444 dela, deer am £S. %,. .4444,4%. £6/...04..4voore4er.to•aat 44../.•.4/wo 4.4.1e.~.4/44.: 41.40... 4.. .floetteanowevo o 4 n i•ebVideln1J resrwt.4.44ust... rtiZeit• • rye:6C • •fterAtArvi.a. e;+d;tafdie.4e/ See Keneja-a44 • *See attached FAA Approved Model List (AML) ..4154.44 • No. ST0088IWI-D for list of approved airplane models and applicable airworthiness regulations. Sloc...06m 49.554.- Alutisv. Modification of Collins TCAS II or TCAS 94 (TCAS II) system installation with Collins 1TR-920 Change 6.04a Receiver Transmitter to a Collins TCAS II or TCAS 94 (TCAS II) system installation with Collins TTR-920 or Collins TTR•92 I or Collins TTR-4000 Change 7.0 TCAS II Receiver Transmitter and optional TPR-901 in accordance with Collins Installation Instructions as listed on AML No. ST0088IWI-D. Revision or later FAAopproved revisions. ovnittrnwid4;mki.. (I) 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 Cenificate and FAA Approved Model List (AML) No. ST0088IWLD issued lune 30, 2000, or later FAA approved revision, must be maintained as part of the pennanent records for the modified aircraft. (4) Prior installation and approval of a Collins 11R-920 Change 6.04a Receiver Transmitter is a prerequisite to this STC. (5) 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. a,d *wad: arpotvie*doteoAcid at a. 4.64Vesowee.ostialereovrov4 4 00.-./44.4/ adiefebtabebbe 44y.. 444v1 Amy ' r el/ dr./4C-tre4..vottee:444/ ice a. Acelsw..«)/~/ev• Vat .7niente../efeanive Twee ei ewatteaew lune 29, 2000 YAW& 4)4.1.14Araer June 30, 2000 July 14. 2000. December 1.2000 Administrator, DAS•500864CE 01 li tl• 444444 Cele Is pd....bible by • Sine al net tor ra.e0a. or toprIeersert 00t estredisp I nova. et Wu. IN wrtlrlbt. bey 4 vq•r•rr.d Is •Creedarce with P alit. SDNY_GA4_02758376 SUBJECT TO PROTECTIVE ORDER PARAGRAPHS 7, 8, 9, 10, 15, and 17 EFTA_00245298 EFTA01261958 SDNY_GM_02758377 SUBJECT TO PROTECTIVE ORDER PARAGRAPHS 7, 8, 9, 10, 15, and 17 EFTA 00245299 EFTA01261959 Aviorics Certificakin Center 405 Ccans Road NE Rockwell Collins May 14, 2003 WO030737.DOC Flight Options 26180 Curtiss-Wright Parkway 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 17R-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 your airplanes based on the following model and serial numbers provided by Mr. Richard Fine of Rockwell Collins. SDNY_GM_02758378 SUBJECT TO PROTECTIVE ORDER PARAGRAPHS 7, 8, 9, 10, 15, and 17 EFTA 00245300 EFTA01261960 SDNYGM02758379 SUBJECT TO PROTECTIVE ORDER PARAGRAPHS 7, 8, 9, 10, 15, and 17 EFTA 00245301 EFTA01261961 Flight Options STC ST00881WI-D May 14, 2003 Page 2 Model 400A WO030737.DOC STC 3T00881WI-D MSN MSN 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 aircraft serial number(s) to me for installations performed using this STC. My fax number is (319) 295-0337. Collins needs to receive this data before we can authorize additional installations. a SDNY_GM_0275B380 I SUBJECT TO PROTECTIVE ORDER PARAGRAPHS 7, 8, 9, 10, 15, and 17 EFTA_00245302 EFTA01261962 SDNYGM02758381 SUBJECT TO PROTECTIVE ORDER PARAGRAPHS 7, 8, 9, 10, 15, and 17 EFTA 00245303 EFTA01261963 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 satisfactiqn is important to_us, and_w.e_woultappreciate your input. Please complete and return the enclosed questionnaire or email me at dwiessenerockwellcollins.com and 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 (319) 295-0618. Douglas W. Jessen Collins Avionics Certification Center Mail Station 164-100 /pah Enclosure SDNY_GM_02758382 SUBJECT TO PROTECTIVE ORDER PARAGRAPHS 7, 8, 9, 10, 15, and 17 EFTA_00245304 EFTA01261964 SDNYGM02758383 SUBJECT TO PROTECTIVE ORDER PARAGRAPHS 7, 8, 9, 10, 15, and 17 EFTA_00245305 EFTA01261965 - • • MAJOR REPAIR AND ALTERATION (Airframe, Powerplant, Propeller, or Appliance) Form Approved OMB No. 2120-0020 For FM Use Only tiflcaW INSTRUCTIONS! P nt or type at entries. See FAR 43.9, FAR 43 Appende B. and AC 43.9-1 (or subsequent the for instructions and disposition of this font 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 (Sectron 901 Federal Aviation Ac of 19513). 1. Aircraft Make Raytheon Aircraft Company Model 400A Serial No. RK-260 Nationality and Registration Mark N787TA 2. Owner Name (As shown on registration certificate) Grand/Sakwa Transportation LLC cto Flight Options LLC Address (As shown on registration certificate) 26180 Curtiss-Wright Parkway Richmond Heights, OH 44143 3. For FM Use Only 4. Unit Identification 5. Type Unit Make Model Serial No Repair Ale ratio!, AIRFRAME described Item 1 V (As in above) POWERPLANT PROPELLER APPLIANCE Type Manufacturer 6. Conformity Statement A. Agency's Name nd Address B Kind of Agency C. Certificate No. Rapid Aircraft Repair, Inc. R.R. 45, Peterborough Airport Peterborough, Ontario K9J 6X6 CANADA u S. Certificated Mechanic AMO 73-92 Foreign Certificated Mechanic V Certificated Repair Station - Canadian Manufacturer D I certify that the repair and/or alteration made to the units) den ified in item 4 above and described on the reverse o attachments made in accordance with the requirements of Part 43 of the U.S. Federal Aviation Regulations and that the information furnished herein to the best of my knoMedge. / hereto have been is true and Cana Date May 28, 2004 Signature of Authorized Individual ere .„ ALowtoP Pickett 1. Approval for Return to Service Pursua t to the authority given persons specified below, the unit identified in item 4 was inspected in the manner prescnbed by the Administrator of the Federal Aviat on Administration and is / APPROVED _ REJECTED By FM Flt Standards Inspector Manufacturer Inspection Authoraation Other (Specify) FM Designee Repair Station s/ Person Approved by Transport Canada Airworthiness Group Date of Approval or Reject on May 28. 2004 Cert ific Dessgrate or aton No AMO 73-92 Signature of AuthOrtzed Individual ,1 4, n'm Pickett FAA Form 33702410 U S GPO 1989.0.563 71 SDNYGM_02758384 SUBJECT TO PROTECTIVE ORDER PARAGRAPHS 7, 8, 9, 10, 15, and 17 EFTA_00245306 EFTA01261966 _. • NOTICE Weight and balance or operating limitation changes shall be entered in the appropnate aircraft record An alteration must be compatible with all previous alterations to assure continued conformity with the applicable airworthiness requisments 8. Description of Work Accomplished (If more space is required. attach additional sheets. Identity with aircraft nationality and registration math and date worn completed ) REPAIR OF FUSELAGE CHAFF • • 1) Chaff mark in fuselage just aft of nose gear opening repaired by installation of doubler (202473 .040") per Raytheon Aircraft drawing SR-BJ-00015 and FM form 8110-3 issued by Larry G. Young, DERV-230322-CE, dated July 3, 2003. 2) There are no additional continuing airworthiness inspections required as a result of this repair. Inspection criteria and frequency for this item is contained in the existing Beechjet 400A inspection program. 3) This repair has no effect on aircraft weight and balance. 4) _ Detailsof work perfonnertAre maintained on file at Rapid kip:raft Repair under work order 04?772. "*" END ***** 1 Additional Sheets Are Attached SUBJECT TO PROTECTIVE ORDER PARAGRAPHS 7, 8, 9, 10, 15, and 17 EFTA_00245307 EFTA01261967 • US. DEPAIIIIIENT OF TRANSPORTATION FEDERAL AVIATION ACIONICTRAMI STATEMENT OF COMPLIANCE WITH THE FEDERAL. AVIATION rteGULArlotss MAKE Mac &echos?! AIRCRAFT OR 818c8ArTDOMPOtitra IOFIMIC-AVION Oaf July 3, 2003 MODEL NO. MU 300 TYpfi fcrials-A Pas. Morspu. err I '<Aide OF APPLICANT 400.400A Ahplano Ftayahema Aircraft Ccuoparly KIITOfOnC• a Of 840-2003.07-066 LISLOF DATA fortit if !DATION l TiY SR-B1-00013 Rev. Standard Itapair- Chafing. Aft Nose acts Duet on Fuselage SkIO". NOWA: I. Thia dart approval is is support of and coortlrutos approval of the data listed herein and is not valid for any other purpose or application. 2. This approval is for Structural details only. This approval It only for the ononeezing design data. 3. Operator should obtain final approval from thoir looal regulatory anthorlty. Purertabe or DATA To approve laid royale, APPLICABLE rtCQUIREareta3 aar Inca rectipw Id CFR Part 25.25, 2S.301, 25.303, 25.305, 23.307.23.601. 25403 sod 23.4501. CERTIFICATION - Unor anhothy rosin by Croaks% of the A dalairtralor and In Loan:Una with ocraildaat mad limitation of appolonint oadcr ran Irs oftAt Padarat aorLatha bisalarbas, dam Itatal neve 0,4-aa-a••••&.4-ab..4••••••••rand. hart bus nasialard la aCCONLOCI with ctlaftflaf pintdota ad fond to comply old appllotble tcooketaata af rb. Tra•ral MAW.. tegatadams. I Ma, Tbanfore Raaaaassal antral of dame ist• AD IP frit 11C40 dna BKINATURE(6) OF DESIGNATED PIGUIEFJUSO fiEPRESPIITAilvefS1 Law), O. Yount Of SICSLATION HUMBEliSfai DERV-210122-03 FAA Form 81104 asuman toirtam ctAssactrAnaals1 Structural GOO 001441 SDNY_GM_02758386 SUBJECT TO PROTECTIVE ORDER PARAGRAPHS 7, 8, 9, 10, 15, and 17 EFTA_OO2453O8 EFTA01261968 I SONYGM02758387 SUBJECT TO PROTECTIVE ORDER PARAGRAPHS 7, 8, 9, 10, 15, and 17 EFTA_00245309 EFTA01261969 0 MAJOR REPAIR AND ALTERATION US DeD0linsrl t1 (Airframe, Powerplant, Propeller, or Appliance) Federal AriMi00 AdsniNcalion Form Approved OMB No 2120-0020 For FAA Use Only orrice a cation XL INSTRUCTIONS: Print or type all entries. See FAR 43.9. FAR 43 Appendix 8, and AC 419-1 (or subsequen re instructions and disposition of this form. This report is required by law (49 V.S.C. 1421). Failure to report can result u2 3 penany not to exceed $1,000 for each such violation (Section 901 Federal Aviation Act of 1958). 1. Aircraft Make Beechcraft Model 4O0A Serial No. RK•260 Nationality and Registration Mark N787TA 2 owner . Name (As shown on registration certificate) Flight Options LLC Address (As shown on registration certificate) 26180 Curtiss-Wright Pkwy Richmond Heights OH 44143-1494 THE REOUIREMENTS TO DATE TECHNICAL UAMA IU NI inn AND IS HEREBY APPROVED CONFORMITY iNSPECTION BY A PERSON APPROVING .2 / 2 6 (04 AEA FSDO FOR USE IN 14 CFR 23 INSPECTOR ONLY ON TH PART 43.7. IRCRAFT, SUBJECT 4. Unit Idea it 5. Type Unit Make I Model I Serial No. Repair Alteration AIRFRAME described in item 1 above)— X (As POWERPLANT PROPELLER APPtIANCE Type Manufacturer 6. Con ormity Statement A. Agency's Name and Address B. Kind of Agency C. Certificate No. Lynn H. Huyen CIO Flight Options LLC 26180 Curtiss Wright Pkwy. Richmond HeigNs. OH 44143 x U.S. Certificated Mechanic MP 278825845 Foreign Certificated Mechanic Certificated Repair Station Manufacturer D. I certify that the repair andfor 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 requi ements 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 February 24, 2004 Signature o Authorized Individua l 7. Approval for Return To Service Pursuant Administrator BY to the authority given persons specified belowthi?mit identified in item 4 was inspected in the manner prescribed by the of the Federal Aviation Administration and is APPROVED O REJECTED FAA Fit. Standards Inspector Manufacturer )„( Inspection Authorization Other (Specify) FM Designee Repair Station Person Approved by Transport Canada A Mess Group Date of Approval or Rejection 02 -2.7--ay0 Certificate or Designation No. PJ-24/c61 Signatu Authorized In I IAA fam.131 SDNY_GM_027 58368 SUBJECT TO PROTECTIVE ORDER PARAGRAPHS 7, 8, 9, 10, 15, and 17 EFTA_0O24531O EFTA01261970 NOTICE Weight and balance or operating limitation changes shall be entered in the appropriate airaaft record. An alteration must be compatible with all previous alterations to assure continued conformity with the applicable airworthiness requirements. CIL/ C. —(.74.-1-! 8. Description of Work Accomplished (If more spat`' is required attach additional sheets. Identify With aircraft nationality and registration mark and date won( completed.) Installed the following equipment in Beechcraft 400A S/N RK-260: Equipment Install Manual Maintenance Manual Pilot's Guide TAWS 8000 (Class B) 009-18001-001 Rev D N/A 009.18000.001 Rev B Dated 20 March 2003 Dated II June 2002 Installed Goodrich Avionics Systems Landmark TAWS8000 system (iSO-C161a Class 8) using Flight Options LLC electrical drawing 400-3448-20-01 and applicable manufacturers Installation manuals listed above. INS instatation includes the optional Terrain Display function. • • — FAA'AppidO(dflighThAanUal-Supplerneni.400-3448-20 must.bcronbearckthitaticraft when.. the_gass S.TAWS8002,systemis Iduse. The TAWS 8000 SYSleM has been previously approved for multiple peecteel aircraft under SIC 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-D with minor deviations In location of switching relays and wiring inierfatepoints as depicted on Flight Options LLC drawing 400-344620-01. Similarity to STC ST01881CH-D is the basis for this request for field approval. Using the respective manufacturer's instructions for pout-installation ground tests. performed operational checks on all systems The systems nes-lamed to manufacturer's specilicatiorts and no interference to existing aircraft systems was noted. In addition to specific instructions remained in the manufacturer's installation manual(s) noted above, all physical mounting considerations were mode with reference ICI AC 43.13-2A. 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 instmetions contained in the manufacturer's installation manual(s) noted above, wire bundles were fabricated using MIL-SPEC, Teti wire, that meets the acceptability requirements of AC43.13.1 B, Chapter I I. Section 7. Paragraph 11.85 (a) and/or (b), paragraph 11.88. and paragraph 11.89. All wiring was marked in accordance with AC43.13.1 B, Chapter II. Section 16, Part 11-206. I 1.207, 11.208 (a) and/or Mond 11-210 (a) and (b). Individual wires were forimd into bundles by lacing and tying using the technique, described m AC43.13-I 8, Chapter 11, Section 12. paragraph I I -158 (a) and (b). Cables were routed and secured in the aircraft using AC43.13-1B. Chaplet 1 I, Section S. Para.11.96. (a) through (galas a guide. An electrical load analysts was pc rents- the electrical load does not exceed 75% of the rated generator capacity. All compasses aboard this aircraft were checked for accuracy on completion of this installation 'Me aircraft will be weighed on completion of the interior modifications and new data will he entered into the Flight Manual. The aircraft equipment list and weight and balance were updated INSTRUCTIONS FOR CONTINUED AIRWORTHINESS LAW HBAW 95-15 DATED 10-07.SII: Instructions for continued airworthiness (ICA) for this aircraft alteration and interfacing components are as follows; (1) Introduction to the aircraft altered is explained above. (2) Description of the major alteration is explained above. . (3) - Operation Information is des-crib/4 in the documents listed above for each panicular product. (4) 3tivielnit. (8) Diagrams one access elms. (9) Doecial Inspection naukerprida. (10) Application of Protective atatmenls. (11) Qp.lp, (12) List of Special Toots, Ile) Recommended Overhaul Periods. and (15) Airworthiness limitation section are not applicable. IS) Maintenance. (6) troubleshooting information. (7) Removal and Replacement, and (13) for commuter exactiory aircraft of the products listed, will be JAW the appropriate and current manufacturers installation manuals. (16) Revision will be in accordance with the manufacturers maintenance manuals and submitted to the local FSDO. Antennas and other parts and materials inStahed such as wiring, circuit breakers, switches. annunciators, clamps, doublers, shelves, and racks will be inspected in conjunction with the Raytheon B•ecturri 400A Phase C inspection program, for condition, security of attachment, evidence of damage. and normal operation tAW FAR 25.1529 and/Or applicable manufacturers service instructions O Additional Sheets Are Attached 'VS GPO:1944-568-012/00019 SDNY_GM_027 58389 SUBJECT TO PROTECTIVE ORDER PARAGRAPHS 7, 8, 9, 10, 15, and 17 EFTA_002453 I I EFTA01261971 0 MAJOR REPAIR AND ALTERATION ea useirnent or frareronimion. (Airframe, Powerplant, Propeller. or Appliance) Feelers, Awl•Wri Form Approved OMB No. 2120.0020 For FAA Use Only Oar identification I 7 77W14- 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 low (49 U.S.C. 1421); Failure to report can re ull in a civil penalty not to exceed 51.000 for each such violation (Section 901 Federal Av.abon Ad of 1958). . 1. Aircraft Make Raytheon Aircraft Company Model 400A Serial No. RK-260 Nationality and Registration Mark N787TA 2. Owner Name (As Shown on regisfration certificate) Bloomfield Investment, Moro LLC, Maka of Turgeland, East Penn Mnufactudng, Et-Al. Flight Options LLC Address (As shown on registration certificate) 26180 Curtiss Wright Parkway iI Richmond Heights OH 44143 3. For FAA Use Only 4. Unit Identification 5. Type Unit Make i Model Serial No. Repair Alteration AIRFRAME described in Ilern I above) X (As POWERPLANT PROPELLER APPLIANCE - Type Manufacturer 6. Conformity Statement A. Agency's Name and Address B. Find of Agency C. Certificate No. Pedro Vachler 1017 Big Torch Street West Palm Beach, Fl 33407 x U.S. Certified Mechanic ASP 582392447 Foreign Certified Mechanic Certificated Repair Station — Manufacturer O. 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 Pad 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 I I/07/03 Signature of zed Individual 7. App oval 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 El APPROVED ci REJECTED FAA Flt. Standards Inspector Manufacturer x Inspection Authorization Other ( ) FAA Designee Repair Station ' Person Approved by Transport Canada Ainvodhiness Group Date of Approval or Rejection I U07/03 Certificate or Designation 8 No. 4463004 IA Signature of Authorized Individual ---V.-e FAA Form 337 I' 2.04) SONY_GM02758390 SUBJECT TO PROTECTIVE ORDER PARAGRAPHS 7, 8, 9, 10, 15, and 17 EFTA_00245312 EFTA01261972 - 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 cone:wryly with the applicable airworthiness requirements. 8. Description of Work Accomplished (If more space is required, attach additional sheets. Identify with aircraft nationality and registration mark and date work accomplished.) N787TA , Beechjet 400A, S/N RK-260, TT 3247.1, 11/07/2003 Installed an Artex ELT-110-4 ELT, S/N 70130 with mount and remote switch in cockpit I/AAN Raytheon Aircraft DWG 128-340597, DWG 128-340582 and Beechjet 400A maintenance manual chapter 25.61.00-201using installation kit # 455-7004. Used existing Raytheon wiring provisions. Instructions for Continued Airworthiness are contained in the Beechjet 400 A maintenance manual. Revised the weight and balance I equipment list and inserted into the flight manual. END Additional Sheets Are Attached O U.S. G.P.O 1990.761-753 SDNY_GM_02758391 SUBJECT TO PROTECTIVE ORDER PARAGRAPHS 7, 8, 9, 10, 15, and 17 EFTA 00245313 EFTA01261973 .... O 4 MAJOR REPAIR AND ALTERATION • US Dtpartatted (Airframe, Powerplant, Propeller, or Appliance) °transportation federal Aviation Afoialstratlea Form Approved OMB No. 3120.0020 For FAA Use Only Office Identification 5 ts.// 7 j INSTRUCTIONS: Print or type all entries. See FAR 43.9, FAR 43 Appendix B, and AC 43.94 (or subseque t revision thereof) for instructions and dispositio of this form. This report is required by law (49 U.S.C. 1421). Failure to report can result in a ivil penalty not to exceed $1,000 for each such violation (Section 901 Federal Aviation Act of 19581. I. Aircraft Make RAYTHEON AIRCRAFT Model 400A Serial No. RK-260 Nationality and Registration Mark USA N787TA 2. Owner Name (As shown raw registration certificate) RAYTHEON TRAVEL AIR COMPANY, FLY AWAY LLC, BLOOMFIELD INVESTMENT COMPANY LLC, WILERO LLC. MAKA OF TURRTLELAND /SC., EAST PENN MANUFACTURING CO.NC. FC CORPORATE AIR TRAVEL INC. SAMOLOT U.C. ALCON INC. PILGRIM COVE AIR LLC, LEONARD M. RAND AND BARBARA E RAND, AIR OMISIAINE MC, NASSAU HOLDINGS INC, BERGEN INDUSTRIES INC. Address RI shown an registration certificate) 101 SOUTH WEBB ROAD WICHITA, KS 67207 3. For FAA Use Only 4. Unit Identification 5. Type Unit Make Model Serial No. Repair Alteration AIRFRAME (As described in Item I above) X POWERPLANT PROPPI I PR APPLIANCE Type Manufacturer 6. Conformity Statement A. Agency's Name and Address B. Kind of Agency C. Certircate No. RAYTHEON AIRCRAFT SERVICES 1115 PAUL WILKINS ROAD SAN ANTONIO TEXAS 78216 U.S. Catificatea Mechanic CRS-XA 14605K LIMITED AIRFRAME Foreipi Catificatt4 Mechanic X librated Repair Swim manCaufact urer 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 knowledge. Dale 02-25-02 Signatum of Authorized Individual MONTY CARROLL aceefr 7. Approval for Return to Service BY Pursuant to the authority given persons specified below, the unit identified Administrator of the Federal Aviation Administration and is in item 4 was inspected 'n the manner prescribed by the Ilij APPROVED 0 REJECTED FAA Flt. Standards Inspector Manufacturer Inspection Authorizstico Other (Specify) FAA Designee x Repair Station Person Approved by Tampon Canada Airworthiness Orono Dar of Approval or Rejection 02-25-02 Certificate or Designation No. CRS-XA14605K Signature of Authorized Individual MONTY CARROLL Alcttdcw-al FAA Form 337 (12-810 SDNY_GM_027513392 SUBJECT TO PROTECTIVE ORDER PARAGRAPHS 7, 8, 9, 10, 15, and 17 EFTA 00245314 EFTA01261974 NOTICE Weight and balance or operating limitation changes shall be entered in the appropriate aircraft record. An alteration must be compatible with all prevzous alterations to assure continued conformity with the applicable airworthiness requirements. 8. Description of Work Accomplished ef snore spats is required, attach additional their. Wen* with aircraft nationality and registration mark and data work completed.) MAKE: RAYTHEON 400A SIN: RK-260 REG: N787TA DATE: 02-25-02 ALL SEVEN CABIN SEATS AND THE LAVATORY SEAT WERE FIREBLOCICED 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 SICANDIA INC. TEST PLAN #8497 REV. A DATED 02-25-02 FOR P/N's 8497-1 AND 8497-2 ONLY, REFERENCE THE FORM 8110-3 DATED 02-25-02 APPROVED BY DONNA J. PARRISH, DESIGNATED ENGINEERING REPRESENTATIVE, #DERY-410100-CE, STRUCTURAL SPECIAL. END tEl Adrienne's' Sheets An Attached * U.S. GOVERNMENT PRINTING OFFICE: 1992-769.012/60757 SDNY_GM_02758393 SUBJECT TO PROTECTIVE ORDER PARAGRAPHS 7, 8, 9, 10, 15, and 17 EFTA 00245315 EFTA01261975 t ve MAJOR REPAIR AND ALTERATION - U.S. Demi:mug (Airframe, Powerplant, Propeller, or Appliance) of 'NM/a uto Mani Atiallas MmInIstrallon Earn Approved OMB No. 1120-0020 For FAA Use Only Office identification •5 e...rf 7 At_ INSTRUCTIONS: and disposition I. Aircraft Print or type all entries. See FAR 43.9, FAR 43 Appendix B, of this form. This report is required by law (49 U.S.C. 1421). Failure I Federal Av jgagsjukchs2Jamojagnma ti nQ imi fj2 Make RAYTHEON AIRCRAFT and AC 43.9.1 (or subsequent revision thereof) for instructions to report can result in a civil penalty not to exceed 81,000 Model 400A Serial No. RK-260 Nationality and Registration Mark USA N787TA i. Owner Name on regifinstion certificate) FLY AWAY LW, COMPANY LW, WILERO LLC, LLC., EAST PENN INC FC CORPORATE AIR TRAVEL. INC, PILGRIM COVE AIR LIZ. BARBARA E. RAND, AIR GITISLAINE INC, BERGEN INDUSTRIES INC. Address (As shown on registration certificate) 101 SOUTH WEBB ROAD WICHITA, ICS 67207 (As shown RAYTHEON TRAVEL AIRCOMPANY, BLOOMFIELD INVESTMENT MAKA OF TURRIIEIAND MANUFACTURING CO. INC. SAMOLOT LW, ALCON LEONARD M. RAND AND INC, NASSAU HOLDINGS 3. For FAA Use Only 4. Unit Identification S. Type Unit Make Model Serial No. Repair .. Alteration AIRFRAME (As described in Item I above) X POWERPLANT PROPELLER APPLIANCE 'cape Manufacturer 6. Conformity Statement A. Agency's Name and Address B. Kind of Agency C. CatiflosteNo. RAYTHEON AIRCRAFT SERVICES 1115 PAUL WILKINS ROAD SAN ANTONIO TEXAS 78216 US. Canificad Meclonie CRS-XA14605K LIMITED AIRFRAME RADIO CLASS 1,13,111 Foreign Caniasied Meanie X cemented Rreak Winn Manufactura D. I certify that the repair and/or alteration made to the unit( ) 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 02-25-02 Signature of Authorized Individual MONTY CARROLL 7. Approval for Return to Service BY Pursuant to the authority given persons specified below, the unit i Administrator of the Federal Aviation Administration and is entitled in item 4 was inspected in the manna prescribed by the 0 REJECTED g APPROVED FAA FR Standards Inspector Manufacturer Inspection Authorizatkc Other (Specify) FAA Designee x Repair Station Person Approved by Transport Canada Ainvorthinen Gray Date of Approval or Rejection 02-25-02 Certificate a D esismati CRSce No. en Signature of Authorized Individual zooei: „.. (4 MONTY CARROLL FAA Form 337 0240 SONY_GM_02758394 SUBJECT TO PROTECTIVE ORDER PARAGRAPHS 7, 8, 9, 10, 15, and 17 EFTA_00245316 EFTA01261976 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. 8. Description of Work Accomplished a / more space Inquired. attach additional shear. Identify with aircraft nationally and regbtration mark and date mark completed.) 1116EkBAMIESINSIA NLEIS:20 EgaLNL$__A l2ATES2r__5&2 1 7T : 2 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 02-22-02 APPROVED ICAMALA J. MEADER, 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-73-0203 REV. IR DATED 02-22-02, REFERENCE THE FORM 8110-3 DATED 02-22-02 APPROVED BY ROBERT M. HURLEY, DESIGNATED ENGINEERING REPRESENTATIVE, #DERT-710137-SW, SYSTEMS AND EQUIPMENT. THE WEIGHT AND BALANCE FORM AND THE EQUIPMENT LIST HAVE BEEN REVISED AND BOTH FORMS HAVE BEEN INSERTED IN THE AIRCRAFT FLIGHT MANUAL. El Additional Sheets Are Attached * U.S. GOVERNMENT PRINTING OFFICE: 1992-769-012/60157 SDNY_GM_02758395 SUBJECT TO PROTECTIVE ORDER PARAGRAPHS 7, 8, 9, 10, 15, and 17 EFTA 00245317 EFTA01261977 0 MAJOR REPAIR AND ALTERATION U.S.necanmen (Airframe, Powerplant, Propeller, or Appliance) of Trancpneo Federal Parlitiall AtirPIDISill a Form Approved OMB No.2120-0020 For FAA Use Only Office Identification ...,MI I7 AL.' INSTRUCTIONS: Print or type all entries. Sec 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 51,000 for each such violation (Section 901 Federal Aviation Act of 19581. I. Aircraft Make RAYTHEON AIRCRAFT Model 400A Serial No. RK-260 Nationality and Regismadai Mark USA N787TA Z. Owner 101 Name cenilleate) COMPANY, FLY AWAY tiC, COMPANY tiC, WILERO LLC, LEX-, EAST PENN INC. FC CORPORATE AIR TRAVEL, ENC. PILGRIM COVE AIR LIZ, BARBARA E. RAND, AIR GIBSLAINE INC, BERGEN INDUSTRIES INC. Address (As stoma on registration cent/kale) SOUTH WEBB ROAD WICHITA, KS 67207 (As shown on registration RAYTHEON TRAVEL AIR BLOOMFIELD INVESTMENT MAKA OF TVRRTLIRAND MANUFACTURING CO. INC. SAMOLOT LLC,ALCON LEONARD M. RAND AND INC, NASSAU HOLDINGS 3. For FAA Use Only 4. Unit Identification S. Type Unit Make Model Serial No. Repair Alteration AIRFRAME (As described in Item I above) X POWERPIANT PROPELLER APPLIANCE Type Manufacturer 6. Conformity Statement A. Agency's Name and Address B. Kind of Agency C. Certificate No. RAYTHEON AIRCRAFT SERVICES 1115 PAUL WILKINS ROAD SAN ANTONIO TEXAS 78216 U.S. Cenitxated Mechanic CRS-XA14605K LIMITED AIRFRAME Fcceign Catifgatcd Mechanic X Certificated Repair Sbnon sitinestwiti D. I certify that the repair and/or alteration made to the unit( ) 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 nue and correct to the best of my owledse. i f//// Date Signature of Authorized Individual 02-25-02 MONTY CARROLL 7. Approval for Return to Service BY Pursuant to the authority given persons specified below, the unit identified Administrator of the Federal Aviation Administration and is in item 4 was inspected in the manner prescribed by the El APPROVED 0 REJECTED FAA FIE Standards Inspector Lk Manufacturer Inspection Authorization Other (Specify) FAA Designee Repair Station Person Approved by Transport Canada Airworthiness Group Del of Approval or Rejection 02-25-02 Certificate or Nao D R S- CRS-XA14605K Signature of Authorized Individual g MONTY CARROLL „ „.....„4 .4, FAA Form 337 (124S) SDNY_Givl_02 758396 SUBJECT TO PROTECTIVE ORDER PARAGRAPHS 7, 8, 9, 10, 15, and 17 EFTA_00245318 EFTA01261978 NOTICE Neighs and balance or operating limitation changer 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 (Varese space Is required. attach add Itional sheets. Men* with aircraft nationally and registration mark and date work completed) MAKE RAYTHEON 400A C/N RK 260 RAC• N787TA 1a 02 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 02-22-02 APPROVED BY KAMALA J. MEADER, DESIGNATED ENGINEERING REPRESENTATIVE, HDERT-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 JUDY BOGGS, 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 P01074-113. 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 -- El Additional Sheets Are Attached * US. GOVERNMENT PRINTING OFFICE: 1992-769412/60157 SDNY_GM_02758.397 SUBJECT TO PROTECTIVE ORDER PARAGRAPHS 7, 8, 9, 10, 15, and 17 EFTA 00245319 EFTA01261979 . 0 MAJOR REPAIR AND ALTERATION OMB No. 2120.0020 US Departmot (Airframe, Powerplant, Propeller, or Appliance) I:canApproved of liariSparcann For FAA Use Only Federal Aviation , Administration PM am A U Identification 54 ..) 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 and penalty not to exceed 51,000 for each violation (Section 901 of Federal Aviation Act of 1968). Make Raytheon Model 400A 1. Aircraft Serial No. RK-260 Nationally and Registration Mark N787TA 2. Owner Name (As shown on registration certificate) See Attached Copy ( 2 Pages ) Address (As shown on registration certificate) 101 S. Webb Rd. Wichita, KS 67201 3. For FAA Use Only 4. Unit Identification 6. Type Unit Make Model Serial No. Repair Natation described in Item I AIRFRAME (As above) X POWERPLANT PROPELLER .6 rr. pz .--: CO ..0 APPLIANCE Type i r i op 22. Manufacturer -Ts .T.2 CO '-`• 0 Gi 6. Conformity Statement CZ1 A. Agency's Name and Address B. Kind of Agency C. Certificate No. tas Kenneth W. Chiny X U.S. Certificated Mechanic 454944057 tot S. Webb Foreign Certificated Mechanic P.O. Box 2902 Certified Repair Station WitehiLs 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 knowledge. Date 03-06-00 Signature of Authorized Individual .6-4,-,76 ezi g ar 7. Approval for Return To Service Pursuant o the authority given persons specified below, the unit identified in itom 4 was Inspected in the manner prescribed by the Administrator of the Federal Aviation Administration and Is ID APPROVED 0 REJECTED FAA FIL Standards Inspector Manufacturer X Inspection Authorization Other (Specify) BY FAA Designee Repair Station Person Approved by Transport Canada Airworthiness Group _ Date of Approval or Rejection 03-06-00 Certificate or Designation No. Signature of Authorized Individual 454944057 .....1 0...rzzie ide. 7 9:- : ) orm 337 (12-ere SDNY_GM_02768399 ti SUBJECT TO PROTECTIVE ORDER PARAGRAPHS 7, 8, 9, 10, 15, and 17 EFTA_00245 320 EFTA01261980 NOTICE compatible with all previous alterations to assure continued conlomtify with the applicable airworthiness requirements. Weight and balance or operating limitation changes shall be entered in the appropriate aircraft record. An alteration must be • 8. Description of Work Accomplished al more space is required, attach additional sheets. Identify with aircraft nationality and registration mark and date mark completed.) Installed Dog Harness PIN 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. O Additional Sheets are Attached SDNY_Glv1_02 758399 SUBJECT TO PROTECTIVE ORDER PARAGRAPHS 7, 8, 9, 10, 15, and 17 EFTA_0024532 I EFTA01261981 0 MAJOR REPAIR AND ALTERATION Il.S.Drputinent (Airframe, Powerplant, Propeller, or Appliance) of Inassertalen NOM finalise Molaittrom Form Approved OMB No. 2120-0020 For FAA Use Only Office Identification SW FSDO 17 eat - INSTRUCTIONS: Print or type all entries. See FAR 43.9. FAR 43 Appakix B. and AC 43.9-1 (or subsequen revision thereof) for instructions and disposition of this form. This report is required by taw (49 US.C. 1421). Failure to report can result in a civil penalty not to exceed 51000 for oath such violation (Section 901 Federal Aviation Act of 1958). 1- Aircraft Make RAYTHEON Model 400A Serial No. RK-260 Nationality and Registration Mark USA N787TA 1 Owner Name (As shown on registration certificate) RAYTHEON AIRCRAFT COMPANY Address (As Shawl on registration certificate) 9709 E CENTRAL AVE WICHITA, KANSAS 67206-2507 3. For FAA Use Only 4. Unit Identification 6. Type Unit Make Model Serial No. Repair Ateration AIRFRAME (As described in Item 1 above) X POWERPLANT PROPELLER APPUANCE Type Meer 8. Conformity Statement A. Adam's Name and Address S. Kind of Agency C. Gratecate No. RAYTHEON AIRCRAFT SERVICES 1115 PAUL WILIUNS ROAD ANTONIO TEXAS 78216 u.S. Certircated methane CRS-XA14605K LIMITED AIRFRAME RADIO CLASS 1,11,111 Fore:on Cerlirsadvel Medlar* X certificated Repo sheen SAN Mandassurer D. I certify that the repair and/or alteration made to the uni(s) identified In item 4 above and described on the reverse or attachments hereto have been made in accordance with the requileMOMS 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 01-28-00 Signature of Authorized Individual MONTY CARR0LL 1/ ( tee..e...r.r / rn Service 7. Approval for Retu to BY 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 El APPROVED 9 REJECTED FAA Ftt. Standards Inspector Manufacturer Inspection Authorization Other (Specify) FAA Designee x Repair Station Person Approved by Transport Canada Airworthiness Group Date of Approval or Refection 01-28-00 Certificate or on No. CRS-XA14605K Signature of Authorized Individua M0NTY CARROLL .flet c .e.e.417 orm 337 (1248) SDNY_GM_02758400 SUBJECT TO PROTECTIVE ORDER PARAGRAPHS 7, 8, 9, 10, 15, and 17 EFTA_00245322 EFTA01261982 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. 8. Description of Work Accomplished (It more space is mated. attach &Malone, sheets identify with aircraft nationaty end reglstradon mark end date work completed.) MAKE: RAYTHEON 400A SIN. RK-760 REG: N787TA DATE• 01-78.00 INSTALLED A SUNDSTRAND MK-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 33.10 ADC-500 CONVERTER 500-8020 2.25 38.17 BRACKET & PLATE 0.5 36.14 WIRING & CONNECTOR 3.5 54.0 THE SUNDSTRAND MK-VI GPWS SYSTEM WAS INSTALLED IN ACCORDANCE WITH THE STC NSA3322SO ISSUED 09-18.92 AND REISSUED 10-04-95 AND THE HANGER ONE MASTER DRAWING LIST N11892-GPWS, REV. 13 DATED 03-22-93. THE ELECTRICAL WIRING WAS INSTALLED IN ACCORDANCE WITH THE RAYTHEON AIRCRAFT SERVICES DWG. NRAS-67-9915 REV. IR DATED 09-29-99, REFERENCE THE FORM 8110-3 DATED 12-30-99 APPROVED BY ROBERT M. HURLEY, DESIGNATED ENGINEERING REPRESENTATIVE NDERT-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 PILOTS GUIDE PIN 060-4087-000 REV. A DATED 10.96 HAS BEEN INSERTED IN THE AIRCRAFT AS PART OF THE AIRCRAFT'S 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 ❑X Additional Sheets Are Attached * US. GOVERNMENT PRINTING OFFICE: 1992-769-012/60157 SDNY_GM_02758401 SUBJECT TO PROTECTIVE ORDER PARAGRAPHS 7, 8, 9, 10, 15, and 17 EFTA_00245323 EFTA01261983 Stara rr amnics Beparrment of tramportation—fidual 21.0iation ildministration ,*upplemental tgpe Certificate Ar eerni er, SA3322S0 Raytheon Aircraft Services, Inc. Sonneneastsaairecact4. 3992 Aviation Circle Fulton County Airport-Brown Feld Atlanta, Georgia 30336 .614.0,-..amAdatad.fittraArteeta nzensre0a-e 25 ..1.8,0 Federal Aviation Ajughatat& elreigeGasee--47 44%/KM4f.: a/c: viZ44' AI6SW Beech 400A Paeactitee.vatts-Vardiar , Installation of a Sundstrand MK VI GEWS:#6, accordance with Jaeger One. Drawing List No. 11892-GPWS, Rev. B, dated September 17, 1992, or 1,26.r FAA Approved revision. ...Ltaaani,witee.onanet,; This approval should not be extended to other aircraft of this model on which other previously approved modifications arc 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 MaM1711 Supplement, dated September 18, 1992, is a required part of this STC. S st..ennS0-aarseiciSeasfros141.7.4rea,Ao leesedvzseVenryweeetistiataarressacZesar sin- Strelnahertamuval.,:ualada,s, •a t PerYla's4^• • • August 5, 1992 September 18, 1992 1.4.4, / • October 4, 1995 1.4apect freS.A.-7 David P. est (strews) Associate Manager, ACE-116A Atlanta Aircraft rertifintinn ()fife.. (Tide) An, eatetation of this certificate is path/table by a fine of not weeding $1,000, or imprisonment not warding Span, of both. TIP certificate mry be traufesnd in oscontate with FAR 21.17. t•afota8110-2(10-411) SDNY_GM_02758402 SUBJECT TO PROTECTIVE ORDER PARAGRAPHS 7, 8, 9, 10, 15, and 17 EFTA_00245324 EFTA01261984 SDNY_GM_02758403 SUBJECT TO PROTECTIVE ORDER PARAGRAPHS 7, 8, 9, 10, 15, and 17 EFTA_00245325 EFTA01261985 DWG. LIST NO. 11892-GPWS DATE 9/1/92 REV• D DATE 3/22/93 f ST 1 OF I SYSTEM SUNDSTRAND MK-VI GPWS . AIRCRAFT TYPE BEECHJET 400A F.R.A. PROJECT NO.CE-11SA-2970 STC SI 3 3 2 230 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 Auwu4witmmrtimod.sopuotea 6 060-3942 6/92 INSTALLATION DESIGN GUIDE 11892-2 A 3/22/93 INSTALLATION PROCEDURES 11892-3 A 3/22/93 st.ocx molten", 1 1 11892-4 D 3/22/93 WIRING DIAGRAMS t 2 182 11892-5 8-29-92 PARTS LIST & GENERAL NOTES 11892-6 8-29-92 mvsmammmapum 11892-7 8-31-92 ADC-S00 WONTING PLATE 11 '-.8 8-29-92 =Pima mycmn 892-1 A 3/22/93 MWUND TEST PROCEDURES 060-3956-000 D 9/17/92 FLIGHT TEST PROCEDURES S00-8000-R0 8/29/92 DESIGN SPECIFICATIONS ADC-S00 ' . SDNY_GM_02758404 SUBJECT TO PROTECTIVE ORDER PARAGRAPHS 7, 8, 9, 10, 15, and 17 EFTA 00245326 EFTA01261986 SDNY_GM_02758405 SUBJECT TO PROTECTIVE ORDER PARAGRAPHS 7, 8, 9, 10, 15, and 17 EFTA_00245327 EFTA01261987 O US. DEPARTMENT OF TRANSPORTATION FEDERAL AVIATION ADMINPSTRATtoN STATEMENT OF COMPLIANCE WITH THE FEDERAL AVIATION REGULATIONS DATE 12/30/99 AIRCRAFT OR AIRCRAFT COMPONENT IDENTIFICATION MAKE Beech MODEL NO. 400A ilypE mi Raga Natrepnr. ta na eI Airplane AN NAME OF AP PUC T Raytheon Aircraft Services UST OF DATA WENTIFICATION rThE Raytheon Drawings RAS-67-9915 Rev IR Dated 09/29/99 Sundstrand Mk-VI Ground Proximity Warning Sys Note: This approval is for the Electrical aspects of the engineering design data only, and Is not installation approval. Approval for aircraft S/N RK-260 only. Approval for GPWS Is for only the minor deviations to FAA STC SA3322SO. After modification is complete, perform EMI/RFI test In accordance with Raytheon report RAS-GF-9714, EMI/RFI Test Procedure. PURPOSE OF DATA In support of a modification to install a GPWS in serial number RK-260. APPUCABLE REQUIREMENTS Sin.manfirnemnn FAR 25.1301 a,b,c FAR 25.1359 d FAR 25.1431 c CERTIFICATION • Under authority vested by direction of the Administrator and in accordance with conditions and limitations of appointment tmder Part 183 of the Federal Aviation Regulations, data listed above and on attached sheets numbered None have been exainilled in accordance witb Ertablulled procedures and test= to comply with applicable requirements of the Federal I On) Therefore Aviation El fl Regulations. Recommend approval &Maeda* Approved, et daa =WORM OP DESIGNATED ENGINEERING RF-PRESENTATMEM DEt:GNATIoN NumBERSI:11 CLASSIFICATION(S) 7 r s..-I.". '''Spit, DERT-710137-SW Systems & Equipment Robert M. Hu4y FM Form 8110-3 (1t-TI) SUPETmcnrs PREMOUS EDMoN GPO SOW11 SDNY_GlvI_02758,106 SUBJECT TO PROTECTIVE ORDER PARAGRAPHS 7, 8, 9, 10, 15, and 17 EFTA_00245328 EFTA01261988 SDNY_GM_02758407 SUBJECT TO PROTECTIVE ORDER PARAGRAPHS 7, 8, 9, 10, 15, and 17 EFTA 00245329 EFTA01261989