REV LTR

REV LTR NEW A S CRAVIRIl iffares5gowa. LAYOUT SY 9, tow,* .V.0 'ft / f rl to t I i CHEMED SY 2 ICJ • I? GP LOR I a STRESS Cr R-Ilo• II 1 go/olint._ HAIL.PRCS MASS PREP MFG QUALM' PROJ DIOR hail rthl 2a. PGIT REV LTR G DRAWN BY LAYOUT BY CHECKED SY • OP LOR STRESS OP SAMUPRCS LASS PREP 4 P.O OLIALITY r PROP OMR PCTI —L. ' MODEL - GV S/N - 506 THIS DRAWING contrans NO PHOTO REPRO SHEETS Gulfstream® 8ROPRIETARY NOTICE TOP DRAWING - THIS DATA AND INFORMATION DISCLOSED HEREIN IS PROPIETARY DM A OF GULFSTREAM AEROSPACE REPAIR/MODIFICATION, GV SIN 506 CORPORATION. NEITHER THIS DA FA NOR THE DAT A CONTAINED HEREIN SHALL BE REPRODUCED. USED OR DISCLOSED TO OTHERS WITHOUT THE WRITIE.N CAGE CODE 59734 SIZE A DWG NO. SE50000506 REV. 9 AUTHORIZA1 ION OF GULFS IREAM AEROSPACE CORP. MAC T MAISER- I .SHEET I Of 10 EFTA01112846 Section 1 This drawing defines and authorizes specific repair/modification drawing(s) for the serial numbered aircraft below. This drawing will be revised ilwhen additional repair andior modification drawings are required. Dwg Number Rev Drawing Title Repair (Dash No.) SE55202I 09 SKIN FtPR-STA 782-828.5. STGR I 6R- 18R -1 A SE05 102901 B STD RPR-BUSHING INSTL. FUSELAGE SKIN -I B SF35105101 GV FLOORBD RPR-INSERT REMOVAL. & REPLACEMENT Gulfstreamit TOP DRAWING - REPAIR/MODIFICATION, GV S/N 506 pwci NO. SE50000506 REV B SHEET 2 OF 10 EFTA01112847 Section II This section identifies Gulfstrearn typc-dcsign data for which the 8 I I 0-3 form is net available foe O.C. Dept to support aircraft departure. Q.0 and shop personnel have verified the drawing effectivity is appropriate for use on the aircraft serial number identified in this drawings tide. This section also defines and authorizes amplierriemlor type-design data that is approved for use during rework of the aircraft serial number hlentifted in this drawing's tide. This section will be revised ilfwhen additional type-design data is required to support rework of this aircraft. Dwg Number Res' Drawing Title Repair (Dash No.) Gulfstream. TOP DRAWING - REPAIR/MODIFICATION, GV S/N 506 Diatia. SE50000506 REV B I SHEETS OP 10 EFTA01112848 This section defines and authorises specific deviations encountered ea aircraft serial number identified in this drawing's fide. These are deviations noted while this aircraft was undergoing service repair or modification at Gulfiereun Savannah Service Center. This section also addresses structural discrepancies on aircraft which ate not covered by existing repair drawings. Structural repair manual or other FAA approved sources. GuIfstnani Service Engineering has reviewed the discrepancies listed below for the aircraft serial number identified in this drawing's title. All items hated below have been reviewed and are deemed ainvorthy for continued normal operations. REV. A CS2.621tS4.11. Discrepancy: Aircraft sustained a lightning strike and numerous entsyfexit points have been noted. Overview of affected areas en Fasebge Skis Rai sides Overview affected areas bewste• FS 79.250 and FS 123.6117 GulfstreamS TOP DRAWING - REPAIR/MODIFICATION, GV S/N 506 DWG NO, SE50000506 REV.: B SHEETS OF 10 Section III cont. EFTA01112849 REV. A cont. CS262854.1.1.11 Preliminary Engineering Disposition: FOR AREAS: fl 1 LOWER HOLE ONLY. #5. 09. 010, Al, 111Z 013. & NI 4 USE HOLE CONTROL TOOLING TO PULL HOLE 100% IN THE DIRECTION REQUIRED TO CLEAN OUT THE BLENDED/DAMAGED AREAS. HOLE IS TO BE OPENED TO A CLEAN AND ROUND. I 61 -.I 66 DIA. THEN COUNTERSINK FOR AN NASI097AD5 RIVET, THE COUNTERSINK BEING CONCENTRIC TO THE NEW HOLE DIA. MAINTAIN MINIMUM 1.5 X DIAMETER EDGE DISTANCE ON OVERSIZED HOLES. IF OVERSIZED HOLE REMOVE ALL DAMAGE THEN INSTALL NAS1097ADS RIVETS IN SUBJECT HOLES WET WITH F5890 SEALANT OR EQUIVALENT PRODUCT PER MIL-S-8802 IF ANY OF THE BLENDEDIDAMAGED AREA DOES NOT CLEAN OUT, RESUBMIT INFORMATION WITH PICTURES FOR FURTHER DISPOSITIONING. FOR AREAS:Y I, #2. 03.S4. 06. 07, @ 08 PLEASE MARK THE EXACT RIVET LOCATION ON THE PROVIDED DRAWING AND RESUBMIT INFORMATION FOR FURTHER DISPOSITIONING. FOR THE HORIZONTAL TIPCAP. REMOVE STATIC WICK BASE AND INSPECT BASE EATING SURFACE AND THE ATTACHING SURFACE OF THE TIPCAP FOR DAMAGE. RESUBMIT RESULTS. CSZ62854.I.2 & ES262894.I_1 Discrepancy: ACC Customer has complied with the prelim disposition and provided details. Gulfstream* TOP DRAWING - REPAIRJMODIFICATION, GV S/N 506 pvic NO SE50000506 REV: B SHEET 5 OF 10 Section III cont. EFTA01112850 REV. A coat CS262854.1.2 & CS267354.1.3 Discrepancy cont.: Gulfstream® TOP DRAWING - REPAIR/MODIFICATION, GV S/N 506 =QS SE50000506 REV B SHEET 6 OF 10 Section III coot EFTA01112851 REV. A cont. C.749$4413 & CS262854.I.3 Discrepancy cont.: realt2244 1.2.1 Prolhnlaary Engiamtiog Disposition: FOR AREAS: 0 1, 42,03, 64. trk 07, & 48 PLEASE MEASURE THE FASTENER PITCH (CENTER-TO-CEVIER HOLE DISTANCE) TO THE ADJACENT FASTENER ABOVE AND TO THE ADJACENT FASTENER BELOW THE DISCREPANT HOLE. IF THERE IS AN ADJACENT FASTENER FORWARD OR AFT OF THE SUBJECT HOLE, PLEASE PROVIDE THE FASTENER PITCH FOR THOSE ALSO. MEASUREMENTS PROVIDED SHOULD BE TO .XX INCH MINIMUM DECIMAL PLACE ACCURACY. RESUBMIT RESULTS FOR FURTHER DISPOSITIONING. FOR AREAS: N 3 LOWER HOLE ONLY, 05, 89, MO. MI I, t/12. 813.8 814 THAT WERE DISPOSITONED PREVIOUSLY, IF THE HOLES HAVE NOT BEEN COUNTERSUNK. LIMIT COUNTERSINK TO .240 INCH DIA. AND AFTER INSTALLING THE NASI097ADS RIVET. SHAVE HEAD FLUSH. THE HORIZONTAL TIPCAP IS ACCEPTABLE AS IS FOR CONTINUED NORMAL OPERATION. TOUCH-UP FIN 213 3012 AND PAINT TO CUSTOMER REQUIREMENTS. C9-949244.1.3.1 Eaglateerlog Dbposkko• Sr AREAS 04,6, & 8: AT NOTED LOCATIONS INSTALL FRFFIE PLUGS PER SE05102901-I. KEEP FREEZE PLUG HOLES TO A MINIMUM SIZE TO CLEAN OUT DAMAGE WHILE SATISFYING ALL REPAIR DRAWING REQUIREMENTS. AREAS 4 AND 8 SHOULD HAVE A .453 DIA. HOLE WITH A .490,500 DIA. CSK. AREAS 6 SHOULD BE A .281 DIA. HOLE WITH A .320,330 DIA. CSK. Gulfstream ® TOP DRAWING - REPAIR/MODIFICATION, GV S/N 506 DWG NO. SE50000506 REV.: B I SHEET? OF 10 EFTA01112852 Section III cont. REV. A ant. CS2621154.133 Engineering Disposition for AREAS MI 3. tc 7: AT NOTED LOCATIONS INSTALL FREEZE PLUGS PER 5E05102901-I. KEEP FREEZE PLUG HOLES TO A MINIMUM SIZE TO CLEAN OUT DAMAGE WHILE SATISFYING ALL REPAIR DRAWING REQUIREMENTS. AREA 1 & AREA 3 UPPER LOCATION SHOULD HAVE A 312 DIA. HOLE WITH A .360,370 DIA. CSK. AREA 7 UPPER AND LOWER LOCATIONS SHOULD BE A .2131 DIA. HOLE WITH A .320-.330 DIA. CSK.. WHILE AREA 7 CENTER LOCATION SHOULD HAVE A A53 MA. HOLE WITH A .490,500 DIA CSK. CS262854.1.33 Esgiaortieg Dispestitloa for AREA NI AT NOTED LOCATION INSTALL A FREEZE PLUG PER 5E05102901.1. KEEP FREEZE PLUG HOLES TO A MINIMUM SIZE TO CLEAN OUT DAMAGE WHILE SATISFYING ALL REPAIR DRAWING REQUIREMENTS. AREA 2 SHOULD HAVE A .312 DIA. HOLE WITH A .360-370 DIA CSK. AfTetted 'AXIS= on FWD Skin (Ann #3) Gulfstream. TOP DRAWING - REPAIR/MODIFICATION, GV S/N 506 DWG NO. SE50000506 REV.: B SHEETS OF to EFTA01112853 Section III cont. REV. A cont. CS262854.1.3.1: 1.3.2 & 1.3.3 Engineering lb.po.ition coot. Affected Rivet locations on Aft Skin (areas NI, ft2, N4, 06,11, N8) CS262354.13.4 Lightening Disposition for AREA //IS: AREA $15 IS ACCEPTABLE FOR CONTINUED NORMAL OPERATIONS. TOUCHUP FINISH AREA WITH #213, *3012 AND TOPCOAT TO MATCH SURROUNDING FINISH. Gulfstream, TOP DRAWING - REPAIRJMODIFICATION, GV S/N 506 DWG NO SE50000506 REV.: B SHEET 9 OF 10 EFTA01112854 GUITSTREAM V MAINTENANCE MANUAL UNSCHEDULED MAINTENANCE CHECKS - INSPECTION / CHECK 1. Lightning Strike — Inspection A. Preparation (1) References • Safe Ground Maintenance Procedure, 20-00.00, Maintenance Practices • Preflight - Inspection, 20-00-00, Inspection / Check • Aileron and Trim Control System - Operational Test. 27-10-00, Adjustment / Test • Aileron / Flight Spoiler Control System - Functional Test, 27.11-00, Adjustment / Test or Code 271103 • Rudder and Trim Control System - Operational Test. 27-20.00, Adjustment / Test or Code 272113 • Elevator Control System - Operational Test, 27-30-00, Adjustment Test or Code 273005 • Flap System - Operational Test, 27-50-00. Adjustment Test or Code 275003 • Ground Spoiler System - Functional Test, 27.62-00, Adjustment / Test or Code 276203 • Engine Lower Cowl Door - Open and Close Procedures, 71-10-00, Maintenance Practices • Engine Upper Cowl Door - Open and Close Procedures. 71-10-00. Maintenance Practices • Engine Scavenge Strainers - Detailed Inspection, 79.21.03, Inspection / Check or Code 792107 • Engine and Accessory Gearbox Magnetic Chip Detectors - Detailed Inspection, 79-21-04, Inspection / Check or Code 790011 (2) Aircraft Preparation (a) Prepare aircraft for safe ground maintenance. See Safe Ground Maintenance Procedure, 20-00-00, Maintenance Practices. (b) When a lightning strike is reported, four following items of information should be obtained from flight crew: • Did anyone actually see the strike and, if so, where was it • Was landing gear extended or retracted • Were flaps extended or retracted • Were spoilers extended or retracted Oa B. Inspection 1) Perform inspection of airframe as follows: WARNING: FAILURE TO DISSIPATE HYDRAULIC PRESSURE BEFORE INSTALLING OR REMOVING ALL LANDING GEAR AND LANDING GEAR DOOR SAFETY DEVICES SHALL CAUSE DAMAGE TO AIRCRAFT OR MAY RESULT IN SERIOUS INJURY OR DEATH. FAILURE TO ENSURE ALL PERSONNEL AND EQUIPMENT ARE CLEAR OF FLIGHT CONTROL SURFACES BEFORE OPERATING FLIGHT CONTROLS MAY RESULT IN SERIOUS INJURY OR DEATH. (a) Dissipate hydraulic system pressure by cycling flight controls and / or operating brake pedals several times. COPY Project (3N3Xer&POr Nbr.: 05-50-00 Page 601 June 30/11 Date: Z Ser Zai/ EFTA01112855 GUITSTRLAM V MAINTENANCE MANUAL WARNING: FAILURE TO INSTALL ALL LANDING GEAR AND LANDING GEAR DOOR SAFETY DEVICES BEFORE WORKING IN ANY WHEEL WELL MAY RESULT IN SERIOUS INJURY OR DEATH. (b) Install all landing gear and landing gear door safety devices. (c) If location of lightning strike entry point is known, perform the following: NOTE: On occasion, one rivet may have a lower resistance than others and may attract a low current. This can cause a rivet to melt away. Paint discoloration will also be evident. If such a condition covers an area of several fasteners, it will be necessary to check the heat treat condition of the material to determine if it has been locally affected. If this situation is encountered, contact Gulfstream Technical Operations for assistance. If discrepancies are found in this procedure, contact Gulfstream Technical Operations for disposition and assistance. Start at known location and verify a strike entry point. Start from strike entry point, look for a path of pinpoint bum marks and / or charred spots on paint surface structure and proceed along the path as far as possible and locate the exit point. 3 Replace any burned or charred static wick(s) as required. NOTE: Static discharge wicks are the most likely exit path. If lightning strike entry point location is unknown, perform the following: of/Ai From ground level, no greater than arms length distance, start forward of main entrance door and proceed clockwise around aircraft. NOTE: Follow the sequence detailed in Preflight - Inspection. 20.00.00, Inspection / Check. N/A 2 Visually inspect all extremities of aircraft including radome, wing tips / winglets, fuselage tail cone for pinpoint bum marks and / or charred spots. NiA 3 Visually inspect all projections such as antennas, angle of attack probes. pilot static probes and total air temperature probes for pinpoint bum marks and f or charred spots. N/A4 Visually inspect upper fuselage, vertical stabilizer and horizontal stabilizer for pinpoint burn marks and / or charred spots on structure and control surfaces including static wicks. 04(e) Was the landing gear extended? If Yes, inspect the following: A/M1 Visually inspect main and nose landing gear structural attachment locations (fuselage and gear) for indication of electrical current passing through landing gear (burn marks or charred spots). a If more than 2 square inches of paint discoloration is seen, disassemble and inspect all moveable joints between the discharge point(s) and airframe structure. l) Where indication is present, replace all bearings located between fixed airframe structure and the exit point on the landing gear. 042 Visually inspect for melted grease nipples. 05-50-00 Page 602 June 30/11 EFTA01112856 GULISTREAM V MAINTENANCE MANUAL a If a melted grease nipple is found, disassemble the joint, check surface condition, clear all grease passages, replace nipple and reservice with grease. Accomplish replacement within 50 flying hours. AM 3 Visually inspect brackets holding electrical components for indication of electrical current passage. a If burn marks and I or charred spots are found on electrical component brackets, perform a functional check of electrical component. 4..//4 4 Visually inspect brackets holding hydraulic components for indication of electrical current passage. a If burn marks or charred spots are found on hydraulic component brackets, it is possible the contained hydraulic fluid was subjected to excessive heat build-up. The amount of heat absorbed depends on how much surrounding metal is available to form a heat sink. If that possibility exists, drain, flush and reservice affected hydraulic system. g/Af) If flaps and / or spoilers were extended, inspect the following: N/A 1 Visually inspect ailerons, flaps and spoilers for indication of electrical current passage. a If burn marks or charred spots are found on any surfaces, visually inspect all connections between parent surface and affected surfaces including bonding jumpers, hinges, bearings and lateral control system including ailerons, flight spoiler and ground spoiler actuators and attachments. b For wing mounted surfaces, visually inspect their controls along wing rear beam. c If there is indication that a high current passed through an aileron, flap or spoiler bearing, disassemble bearing for an inspection of bearing surface and grease / lubricant. Replace sealed bearings that are affected by a high current. ( 2 Visually inspect elevators and elevator trim tabs for indication of electrical current passage. a If burn marks or charred spots are found on elevator surfaces, visually inspect all connections including bearing hinges and bonding jumpers back down to fuselage. 443 Visually inspect horizontal stabilizer pivot area, horizontal stabilizer actuator and its attachment for evidence of burn marks or charred spots. AlfikAl If there is no sign of damage or deterioration from a high current, perform a functional test of each of the following systems: • Aileron and Trim Control System - Operational Test, 27-10-00, Adjustment / Test • Aileron / Flight Spoiler Control System - Functional Test, 27-11-00, Adjustment / Test or Code 271103 • Rudder and Trim Control System • Operational Test, 27-20-00, Adjustment / Test or Code 272113 • Elevator Control System - Operational Test, 27-30-00, Adjustment / Test or Code 273005 05-50-00 Page 603 June 30/11 EFTA01112857 GULFS REAM MAINTENANCE MANUAL • Flap System - Operational Test. 27-50-00, Adjustment / Test or Code 275003 • Ground Spoiler System - Functional Test, 27-62-00, Adjustment I Test or Code 276203 (2) Visually inspect all structural joints between point where current entered airframe and exit point. Perform inspection of engines as follows: a) Position maintenance platform(s) by engine as required. (b) Ensure that the engine has been shut down for at least 5 minutes. (c) Open upper and lower cowl doors. See Engine Lower Cowl Door - Open and Close Procedures, 71-10-00, Maintenance Practices and Engine Upper Cowl Door - Open and Close Procedures, 71.10.00, Maintenance Practices. (d) Perform external Visual Inspection of the engine for damage. (e) If there are signs of damage or arcing, inspect the following oil system components: Examine the scavenge oil strainers (see Engine Scavenge Strainers - Detailed Inspection, 79-21-03, Inspection I Check or Code 792107): • Accessory gearbox • Front bearing chamber • Rear bearing chamber OM 2 Examine magnetic chip detectors after 25 ±10 hours. See Engine and Accessory Gearbox Magnetic Chip Detectors - Detailed Inspection, 79.21-04, Inspection I Check or Code 790011. /V/4f) If no metal particles are found in Step 1.B.(3Xe)2 proceed as follows. 1 Perform Step 1.11(3)(02 again after 50 :O0. 75 t10 and 100 +10 flight hours. NOTE: If no metal particles are found after 100±10 flight hours, return engine to normal operations. AL) Examine fan blades for arc burns (lightning strikes). NOTE: A sign of arc bum is a circular or semicircular area on the blade surface. 7 area will have a change of color (dark blue oxide), there can also be signs pitting, melting or cracking. C. Follow On • (1) Inspect for presence of foreign objects. (2) Record all maintenance actions in accordance with current governing authority. 2. Hail Damage to Aircraft / Engine — Inspection NOTE: This inspection can be utilized for hail damage to aircraft and / or engine sustained in-flight or on the ground. A. Preparation SPECIAL TOOLS AND TEST EQUIPMENT Maintenance Platform Standard (1) References 05-50-00 Page 604 June 30/11 EFTA01112858 We.3.1()(c_oos-- - (AO RR BR710-Al EMM 72-00-00-200-806 RevDate: Nov 15/06 Inspection of the Engine after lightning Strike Effectivity: BR710 INSPECTION/CHECK 06 TASK 72-00-00-200-806 Inspection of the Engine after Lightning Strike WARNING: BE CAREFUL WHEN YOU DO WORK ON THE ENGINE PARTS AFTER THE ENGINE IS SHUTDOWN. THE ENGINE PARTS CAN STAY HOT FOR ALMOST ONE HOUR. WARNING: DO NOT TOUCH HOT PARTS WITHOUT APPLICABLE GLOVES. HOT PARTS CAN CAUSE AN INJURY. IF YOU GET AN INJURY PUT IT IN COLD WATER FOR 10 MINUTES AND GET MEDICAL AID. 1. Job Set-Up Information A. Fixtures, Tools, Test and Support Equipment REFERENCE DESIGNATION No Specific Access Platform(s) No Specific Circuit Breaker Safety Clip(s) No Specific Inspection Lamp No Specific Inspection Mirror e. Referenced Information REFERENCE DESIGNATION 71-10-00, PB 201 TASK 71-10-00-010- 801 71-10-00, PB 201 TASK 71-10-00-410- 801 72-31-02, PB 601 TASK 72-31-02-200- 801 Open the Upper and Lower Cowls Close the Upper and Lower Cowls Inspection of the Compressor (Fan) Blades and the Annulus Fillers 79-00-00, PB 601 Inspection of the Oil System - General TASK 79-00-00-200- 801 04. Job Set-Up Printed: Oct 03/11 THIS PAGE MUST NOT BE RETAINED FOR REFERENCE EFTA01112859 RR BR710-A1 EMM 72-00-00-200-806 RevDate: Nov 15/06 Inspection of the Engine after Lightning Strike Effectivity: BR710 INSPECTION/CHECK 06 SUBTASK 72-00-00-860-013 (s. Aircraft configuration etitin, Make sure the aircraft is prepared for safe ground maintenance (Refer to the Aircraft Maintenance Manual (AMM)). £(/41(2) Prepare the engine for safe ground maintenance (a) Make sure that the engine has been shut down for at least 5 minutes. 4.--(b) Open, safety and tag the circuit breakers (Refer to the AMM). 3) Put the access platform(s) in position. SUBTASK 72-00-00-010-008 J1L(B. Open the Upper and Lower Cowl Doors (Refer to 71-10-00, PB 201/TASK 71-10-00-010-801). 3. Procedure SUBTASK 72-00-00-210-016 QA /14A. Visually examine the engine externally for damage. NOTE: If there are signs of damage or arcing, continue with SUBTASK 72-00-00-210-017. UBTASK 72-00-00-210-017 . Examine the oil system items that follow: ep44 (1) Examine the magnetic chip detectors after 25 (+/-10) flight hours (Refer to 79-00-00, PB 601/TASK 79-00-00-200-801). N/A (2) If no metal particles are found in step (1) (a) Do step (1) again after 50 (+/-10), 75 (+/-10) and 100 (+/-10) flight hours. (b) If no metal particles are found after 100 flight hours start normal operations again. Printed: Oct 03/11 THIS PAGE MUST NOT BE RETAINED FOR REFERENCE EFTA01112860 RR BR710-Al EMM 72-00-00-200-806 RevDate: Nov 15/06 Inspection of the Engine after Lightning Strike Effectivity: BR710 INSPECTION/CHECK 06 SUBTASK 72-00-00-210-019 014 30C1 toa . Examine the fan blades for arc burns (lightning strikes) (1) Examine the fan blades, (Refer to 72-31-02, PB 601/TASK 72-31- 02-200-801). JBS1. 20A000 NOTE: A sign of arc burn is a circular or semi-circular area on the blade surface. The area will have a change of color (dark blue oxide), there can also be signs of pitting, melting or cracking. 4 SUBTASK 72-00-00-869-002 D. Record the lightning strike in the engine log book. 4. Close-Up SUBTASK 72-00-00-160-005 A. Make sure that the work area is clean and clear of all tools and equipment. SUBTASK 72-00-00-410-010 B. Close the Upper and Lower Cowl Doors (Refer to 71-10-00, PB 201/TASK 71-10-00-410-801). SUBTASK 72-00-00-860-014 C. Aircraft configuration (1) Put the engine back to a condition for operation (a) Remove the access platform(s) from the work area. (b) Remove the safety clips and the tags and close the circuit breakers (Refer to the Aircraft Maintenance Manual (AMM)). (2) Put the aircraft back to a condition for operation (Refer to the AMM). Printed: Oct 03/11 THIS PAGE MUST NOT BE RETAINED FOR REFERENCE EFTA01112861 GV COMPUTERIZED MAINTENANCE PROGRAM CM Pnet. REGISTRATION N33XE SERIAL NO. 506 TITLE Ice Detector Probe (Right) - Operational Test 308004 Pavlof 1 PARENT CON/ OPERABCN LOGBOOK Airframe AUTHORITY Part 135 AIRMUWE HOURS 548}0 AIRFRAME CYCLES 1488 TASK TYPE FunctionaUOps Test ZONEFACCESS COMPLIANCE REMARKS REOUMENENTS REFERENCE PROCEDURE REFERENCE 3041-01 ESINATED HOURS 1.0 Sat NOM SERVCE NOES APE COLLECTED NO ANN MRCSS II< IMMOACTUREA TO WORM THE OMNTERANCE FRO MM AND TO INCREASE TM MAYOLITY Of THE AMMO T if .6 ASPORIANT NMI 11001/CIAIM NOME ACCUIMIN ST WeiCs CODES NO NMI CIKMONCOMS DAMN COMPLETING AmNNTEIONCE NOM CA FAX ALL 001"1111DINCO. CARDS TO OULFSIREAV COP GROUP AT SSITASSIGMON Tau I IOC ISNIOWIRS. OOP ocossoo i moososemoaorN SERIAL KAMER s vtrA w❑ PART NUMBER SAS 044.141111 MATERIAL COST LABOR HOURS: TECI CERTIFICATE) 7095 0 ODIAPONOCE DATE 06/06VA/ RARE / a RIVICATE I 14 —6 1 7`,-Fi. .. 'ft r‘1 DATE 6 itt-t. kit (-) WORK ORDER. EM3XE005-0407 :31VOldla130 EFTA01112862 I I I I I Gulfs ream GV COMPUTERIZED MAINTENANCE PROGRAM 308003 Page 1 of 2 ISSUED/REVISED: 06/30106 AREA 308003 Ice Detector Probe (Left) - Operational Test 308004 Ice Detector Probe (Right) - Operational Test A. reparation (1) Reference • Safe Ground Maintenance Procedure, 20-00-ao, maintenance Practices 2) Aircraft Preparation a) Prepare aircraft for safe ground maintenance. See Safe Ground Maintenance Procedure, 20.00.00, Maintenance Practices. (b) Ensure the following Circuit Breakers (CB) are depressed: CB NAME CB PANEL CB LOCATION COMBINED WOW Pilot C2 WARN LTS PWR #2 LEER A9 ANN LTS PWR #6 LEER B7 L ICE DET CONT LEER E3 L ICE DET LEER F3 WARN LTS PWR #1 REER A23 ANN LTS PWR #7 REER 824 R ICE DET CONT REER E14 R ICE DET REER F14 ) Apply electrical power to aircraft. (d) On DISPLAY SYSTEM CONTROL panel, select all switches to NORM. e) On System Monitor panel, select MAINT TEST switch to on. B. Prrocedure ) Pull L ICE DET circuit breaker. Verify the following CAS message is displayed: • L ICE DETECT FL (amber) ) Depress L ICE DET circuit breaker. Verify the following on CAS: • L ICE DETECT FL message is not displayed, then is displayed for 2 - 4 seconds and then is not displayed • L ICE DETECTED (amber) message is displayed for 1 second (approximately) and then is not displayed Pull R ICE DET circuit breaker. Verify the following CAS message is displayed: • R ICE DETECT FL (amber) Depress R ICE DET circuit breaker. Verify the following on CAS: • R ICE DETECT FL message is not displayed, then is displayed for 2 - 4 seconds and then is not displayed EFTA01112863 G Gulfstream V COMPUTERIZED MAINTENANCE PROGRAM I I 0 308003 Page 2 of 2 ISSUED/REVISED: 06/30/06 (CONTINUED) 308003 Ice Detector Probe (Left) - Operational Test 308004 Ice Detector Probe (Right) - Operational Test AREA • R ICE DETECTED (amber) message is displayed for 1 second (approximately) and then is not displayed How On 1) Pull L ICE DET and R ICE DET circuit breakers. On System Monitor panel, select MAINT TEST switch to OFF. 3) On DISPLAY SYSTEM CONTROL panel, select all switches to OFF. (4) Remove electrical power from aircraft. (5) Inspect for presence of foreign objects. (6) Record all maintenance actions in accordance with current governing authority. EFTA01112864