N916FD
Registered owner: FEDERAL EXPRESS CORP, TN (owner ≠ operator)
Operators of this aircraft
Who operated this tail, and how firmly we know it.
No operator established for this aircraft.
Accident & incident history
No NTSB accidents or incidents on file for this aircraft.
Maintenance disclosures
LEFT WING OTBD L/E SLAT # 4 I/B LOWER SURFACE REAR EDGE HAS (2) GOUGES APPLIED PERMANENT REPAIR AT L/WING O/B L/E SLAT # 4 I/B LOWER SKIN IAW SRM 57-43-02- 2R, REP 1, TABLE 201, FIG 201, SHEET 6 AND SRM 51-70-10-2R, REP 4
R1 DOOR EXTERIOR SLIDE LIGHT INOP. RELAMPED R1 DOOR EXTERIOR SLIDE LIGHT IAW AMM 33-51-06-2 OPS CHKD SERVICEABLE.
ENTRY DOOR IS NOT GIVING PROPER INDICATIONS UPON CLOSING. SLIDE LIGHT IS NOT COMING ON AND THE DOOR ARMING LEVER HAS RESISTANCE WHEN MOVING. WHEN TRYING TO DISARM THE DOOR, SLIDE ARMING LEVER WILL NOT GO COMPLETELY INTO THE GREEN SAFE BAND. MAY BE A GIRT BAR ISSUE. WE ARE CONSIDERING THE DOOR/SLIDE AS ARMED. RELEASED FOR SERVICE PER MEL : 52-11-01-A. CLEANED AND INSPECTED GIRT BAR AND FLOOR FITTING IAW AMM 25-66-10-2. SLIDE ARMED CORRECTLY, ALL TEST PASSED. A/C OK FOR SERVICE.
DURING SERVICE CHECK, FOUND COURIER PBE VACUUM BAG SEAL BROKEN. RELEASED FOR SERVICE PER MEL : 35-20-01 CATEGORY : D EXPIRATION : 08SEP24 "MEL 35-20-01: COURIER COMPARTMENT PBE UNIT REMOVED. REMOVED FROM ACFT UNSERVICEABLE PBE FROM COURIER AREA POSITION. INSTALLED NEW PBE ON COURIER AREA POSITION IAW AMM 35-31-01-4-99.
DOOR 1R DISARMED BUT SLIDE LIGHT REMAINED ILLUMINATED. AMM: 25-66-00-5 PERFORMED ADJUSTMENT/TEST I.A.W. AMM 25-66-00-5. DOOR 1R FOLLOWS OK FOR SERVICE.
ON APPROACH ILS 29 AUTOPILOT CAPTURED GLIDE SLOPE 1 DOT HIGH, RESULTING IN HIGH PITCH OVER, NOSE DOWN MOVEMENT. SHORTLY AFTER GLIDE SLOPE CAPTURE THE ASA SHOWED LAND2/NO LAND 3 AND LT AUTOPILOT CMD NOT ILLUMINATED. AUTOPILOTS WERE DISCONNECTED, CONTROLS WERE HEAVY IN ROLL AND PITCH AXIS. INSPECTED AND EXAMINED AILERON AND AILERON TRIM CONTROL SYS MECHANISMS AND LATERAL CONTROL FEEL MECHANISM FOR PRESENCE OF UNWANTED OBJECTS OR OBJECTS THST TOUCH IAW AMM 27 11 00 0 OK , INSPECTED ELEVATOR CONTROL SYS MECHANISM & ELEVATOR FEEL MECH SYS .OK . PERFORMED AILERON CONTROL SYS OPS TEST IAW AMM 27 11 00 5. OK. PERFORMED AILERON & ELEVATOR CONTROL SYS OS TEST IAW AMM 27 11 00 5 & 27 31 00 5 . ALL OKAY.
AIRCRAFT HAS HEAVY CONTROL FEEL IN ROLL AXIS. ROD BETWEEN LATERAL CONTROL FEEL, CENTERING AND TRIM MECHANISM AND LATERAL CONTROL OVERRIDE MECHANISM FOUND WITH BEARING SEAL OUT REFERENCE IPC 27-11-14-02 ITEM 55. ROD R&R'D PER AMM 27-11-14-2 AND AMM 27-11-16- 4.
LE SLAT DISAGREE UPON SELECTION OF FLAPS 1 ON APPROACH. QRH COMPLETED. PAN-PAN DECLARED. EMERGENCY DECLARED ROTARY ACTUATORS FOR TORQUE LIMITER TRIP INDICATION NO TRIP FOUND. FLAT/SLAT BITE AND ERASE PROC ACCOMPLISHED. FSEU BITE AND LE SLATS OPS CHECK ACCOMPLISHED NO FAULTS. C/O 5 CYCLES OF SLATS OPS CHECK IAW FIM 27-81 TASK 803 W/ NO REMARKS. NO EICAS NOR STATUS MSG.
SELECTING FLAPS 1 GOT LE SLAT DISAGREE WITH LEADING EDGE LIGHT. RAN QRH AND AND LIGHT STAYED ON. DECLARED EMERGENCY. BITE TEST FOR FSEU EXISTING FAULT CHECKED WAS NO FAULT. FLAP & SLAT OPS SEVERAL TIMES WITH HYD. & ELECTRICAL. OPS NORMAL, NO FAULT. SLAT PDU CHECKED FOR OVERLOAD. FOUND ALL OK. ALL SLAT ROTARY ACTUATORS CHECKED, FOUND SLAT NR 3 & 4 ACTUATORS OVERLOAD INDICATOR TRIPPED, RESET. FLAP & SLAT OPS AGAIN, ALL INDICTIONS NORMAL. ROTARY ACTUATORS NR.3 & 4 CHECKED AGAIN, FOUND ALL OK. RESOLVER INPUT CHECKED BETWEEN LT SLAT LT & RR SLAT & ALL OK. CHECKED SLAT TRACKS, OK, NOT DRY.
LIGHTS INOP IN GALLEY FASTEN SEAT BELT SIGN. IAWAMM 33-24-00-2 REPLACE THE LAMPS IN THE FASTEN SEAT BELT SIGN IAW AMM 33-24-00-2, OPS OK.
RIGHT FORWARD ENTRY DOOR SLIDE LIGHT STAYS ILLUMINATED AFTER DOOR IS DISARMED. ACCOMPLISHED FIM 52-11-00, OPS TEST ON GND PERFORMED ON SLIDE ARM/DISARM INDICATION AND OPERATION IAW AMM 52-71-00-5 ALL SATISFACTORY, NO MALFUNCTIONS.
RIGHT SIDE SERVICE DOOR FAILED TO DISARM. DOOR 1R - CHECKED GIRT BAR FOR SMOOTH ENGAGE/DISENGAGE ACTION X 20 TIMES AND OPERATION OF DOOR WARNING LIGHT IAW AMM 52-11-00-862-077 VERIFED NO DEBRIS HINDERS GIRT BAR ENGAGEMENT/DISENGAGEMENT INTO FLOOR CLEATS. A/C OK TO CONTINUE
RH WING #2 ENGINE DRAG FITTING HOLE #9 HAS CRACK AND CORROSION INDICATIONS NOTED. ACCOMPLISHED REPAIR ON RH WING #2 ENGINE DRAG FITTING HOLE #9 IAW EA F-5730-T0370276 P1, WINGS-PLATES AND SKINS- RH WING, UPPER SKIN AT PYLON DRAG FITTING, REJECTABLE CRACK/CORROSION INDICATIONS, MAJOR REPAIR.
RH WING #2 ENGINE DRAG FITTING HOLE #18 HAS REJECTABLE INDICATIONS DUE TO CORROSION. ACCOMPLISHED REPAIR ON #2 ENGINE DRAG FITTING HOLE #18 IAW EA F-5730-T0370276 P1, WINGS-PLATES AND SKINS-RH WING, UPPER SKIN AT PYLON DRAG FITTING, REJECTABLE CRACK/CORROSION INDICATIONS, MAJOR REPAIR.
RH WING #2 ENGINE DRAG FITTING HOLE #2 HAS CRACK AND CORROSION INDICATIONS NOTED. ACCOMPLISHED #2 ENGINE DRAG FITTING HOLE #2 REPAIR IAW EA F-5730-T0370276 P1, WINGS- PLATES AND SKINS- RH WING, UPPER SKIN AT PYLON DRAG FITTING, REJECTABLE CRACK/CORROSION INDICATIONS, MAJOR REPAIR.
RH WING #2 ENGINE DRAG FITTING HOLE #12 HAS REJECTABLE INDICATIONS DUE TO CORROSION. ACCOMPLISHED REPAIR ON #2 ENGINE DRAG FITTING HOLE #12 IAW EA F-5730-T0370276 P1, WINGS-PLATES AND SKINS- RH WING, UPPER SKIN AT PYLON DRAG FITTING, REJECTABLE CRACK/CORROSION INDICATIONS, MAJOR REPAIR.
RH WING #2 ENGINE DRAG FITTING HOLE #17 HAS REJECTABLE INDICATIONS DUE TO CORROSION ACCOMPLISHED REPAIR ON RH WING #2 ENGINE DRAG FITTING HOLE #17 IAW EA F-5730-T0370276 P1, WINGS-PLATES AND SKINS-RH WING, UPPER SKIN AT PYLON DRAG FITTING, REJECTABLE CRACK/CORROSION INDICATIONS, MAJOR REPAIR.
RH WING #2 ENGINE DRAG FITTING HOLE #4 HAS REJECTABLE INDICATIONS DUE TO CORROSION ACCOMPLISHED #2 ENGINE DRAG FITTING HOLE #4 IAW EA F-5730-T0370276 P1, WINGS-PLATES AND SKINS-RH WING, UPPER SKIN AT DRAG FITTING, REJECTABLE CRACK/CORROSION INDICATIONS, MAJOR REPAIR.
RH WING #2 ENGINE DRAG FITTING HOLE #8 HAS REJECTABLE INDICATIONS DUE TO CORROSION ACCOMPLISHED #2 ENGINE DRAG FITTING HOLE #8 REPAIR IAW E.A. F-5730-T0370276 P1, WINGS- PLATES AND SKINS-RH WING, UPPER SKIN AT DRAG FITTING REJECTABLE CRACK/CORROSION INDICATIONS, MAJOR REPAIR
#1 ENGINE DRAG FITTING, HOLE #5 HAS REJECTABLE INDICATIONS DUE TO CORROSION COMPLIED WITH EA# T F-5730-0370300 P1, WINGS-PLATES AND SKINS-L/H WING, UPPER SKIN AT PYLON DRAG FITTING REJECTABLE CRACK/CORROSION INDICATIONS ON HOLE #5 REPAIR, MAJOR REPAIR
MAIN CABIN SEAT TRACK F/S 1370 RBL 48 SEAT TRACK INBD FLANGE BOTTOM SIDE EXFOLIATION CORROSION. REPAIRED SEAT TRACK IAW SRM 53-00-52-2R, MAJOR REPAIR
#1 ENGINE DRAG FITTING, HOLE #15 HAS REJECTABLE INDICATIONS DUE TO CORROSION. COMPLIED WITH EA# T F-5730-0370300 P1 WINGS-PLATES AND SKINS-L/H WING, UPPER SKINS AT PYLON DRAG FITTING REJECTABLE CRACK/CORROSION INDICATIONS ON HOLE #15 REPAIR, MAJOR REPAIR
#1 ENGINE DRAG FITTING, HOLE #13 HAS REJECTABLE INDICATIONS DUE TO CORROSION COMPLIED WITH EA# T F-5730-0370300 P1, WINGS-PLATES AND SKINS-L/H WING, UPPER SKIN AT PYLON DRAG FITTING REJECTABLE CRACK/CORROSION INDICATIONS ON HOLE #13 REPAIR, MAJOR REPAIR
#1 ENGINE DRAG FITTING, HOLE #12 HAS REJECTABLE INDICATIONS DUE TO CORROSION. COMPLIED WITH EA# T F-5730-0370300 P1, WINGS-PLATES AND SKINS-L/H WING, UPPER SKIN AT PYLON DRAG FITTING REJECTALE CRACK/CORROSION INDICATIONS ON HOLE #12 REPAIR, MAJOR REPAIR.
#1 ENGINE DRAG FITTING, HOLE #10 HAS REJECTABLE INDICATIONS DUE TO CORROSION. COMPLIED WITH EA# T F-5730-0370300 P1, WINGS-PLATES AND SKINS-L/H WING, UPPER SKIN AT PYLON DRAG FITTING-REJECTABLE CRACK/CORROSION INDICATIONS ON HOLE #10 REPAIR, MAJOR REPAIR.
#1 ENGINE DRAG FITTING, HOLE #8 HAS REJECTABLE INDICATIONS DUE TO CORROSION COMPLIED WITH EA# T F-5730-0370300 P1, WINGS-PLATES AND SKINS-L/H WING, UPPER SKIN AT PYLON DRAG FITTING REJECTABLE CRACK/CORROSION INDICATIONS ON HOLE #8 REPAIR, MAJOR REPAIR
#1 ENGINE DRAG FITTING, HOLE #4 HAS A CRACK INDICATION. COMPLIED WITH EA T F-5730-T0370300 P1, WINGS-PLATES AND SKINS-L/W WING, UPPER SKIN AT PYLON DRAG FITTING REJECTABLE CRACK/CORROSION INDICATION HOLE #4 REPAIR, MAJOR REPAIR
#1 ENGINE DRAG FITTING, HOLE #3 HAS A CRACK INDICATION COMPLIED WITH EA# T F-5730-T0370300 P1, WINGS-PLATES AND SKINS-L/H WING, UPPER SKIN AT PYLON DRAG FITTING REJECTABLE CRACK/CORROSION INDICATIONS HOLE #3 REPAIR, MAJOR REPAIR
AFT CARGO CMPARTMENT MAIN CABIN FLOOR BEAM LOWER CHORD, FLOOR BEAM STRAP CORRODED BETWEEN F/S 1400-1420. REPAIRED FLOOR BEAM STRAP @ FS 1380-1440 IAW SRM 53-00-51-2R, MAJOR REPAIR
MAIN CABIN FLOOR PANEL 232MBF IS DAMAGED FABRICATED ZONE 230 FLOOR BOARD 232MBF ON VTMAE TRAVELER # T22/1632965 IAW DWG SRZ- 25-005 REVISION R, MAJOR REPAIR: ORIG SUB DATE: 9/6/2022
FLOOR PANEL 231MQF HAS IMPACT DAMAGED AS MARKED FABRICATED ZONE 230 FLOOR BOARD 231MQF ON VTMAE TRAVELER # T22/1632472 IAW DWG SRZ-25-005 REVISION R, MAJOR REPAIR. ORIG SUB DATE: 9/6/2022
FLOOR PANEL 232MJF HAS MULTIPLE IMPACT DAMAGE AND WEAR MARKS FABRICATED ZONE 230 FLOOR BOARD 232MJF ON VTMAE TRAVELER # T22/1632426 IAW DWG SRZ- 25-005 REVISION R, MAJOR REPAIR: ORIG SUB DATE: 9/6/2022
FLOOR PANEL 231MJF HAS MULTIPLE IMPACT DAMAGE AND WEAR MARKS FABRICATED ZONE 230 FOOR BOARD 231MJF ON VTMAE TRAVELER # T22/1632471 IAW DWG SRZ- 25-005 REVISION R, MAJOR REPAIR: ORIG SUB DATE: 9/6/2022
FLOOR PANEL 231MEF HAS MULTIPLE IMPACT DAMAGE AND WEAR MARKS FABRICATED ZONE 230 FLOOR BOARD 231MEF ON VTMAE TRAVELER # T22/1632449 IAW DWG SRZ- 25-005 REVISION R, MAJOR REPAIR: ORIG SUB DATE: 9/6/2022
FLOOR PANEL 232MAF HAS MULTIPLE IMPACT DAMAGE AND WEAR MARKS FABRICATED ZONE 230 FLOOR BOARD 232MAF ON VTMAE TRAVELER #T22/1632417 IAW DWG SRZ- 25-005 REVISON R, MAJOR REPAIR. ORIG SUB DATE: 9/6/2022
FLOOR PANEL 231MAF HAS MULTIPLE IMPACT DAMAGE AND WEAR MARKS FABRICATED ZONE 230 FLOOR BOARD 231MAF ON VTMAE TRAVELER # T22/1632425 IAW DWG SRZ- 25-005 REVISION R, MAJOR REPAIR. ORIG SUB DATE: 9/6/2022
FLOOR PANEL 232MBF HAS IMPACT DAMAGED AS MARKED FABRICATED ZONE 230 FLOOR BOARD 232MBF ON VTMAE TRAVELER # T22/1632420 IAW DWG SRZ- 25-005 REVISION R, MAJOR REPAIR. ORIG SUB DATE: 9/6/2022
FLOOR PANEL 231MBF HAS MULTIPLE IMPACT DAMAGE AND WEAR MARKS FABRICATED ZONE 230 FLOOR BOARD 231MBF ON VTMAE TRAVELER # T22/1632443 IAW DWG SRZ- 25-005 REVISION R, MAJOR REPAIR: ORIG SUB DATE: 9/6/2022
FLOOR PANEL 231MFF HAS MULTIPLE IMPACT DAMAGE AND WEAR MARKS FABRICATED FLOOR BOARD 231MFF ON VTMAE TRAVELER # T22/1632450 IAW DWG SRZ-25-005 REVISION R, MAJOR REPAIR. ORIG SUB DATE: 9/6/2022
AFT CARGO DOOR AFT LOWER CORNER BENT AND SECTIONS MISSING REPAIRED AFT CARGO DOOR LOWER AFT CORNER IAW SRM 52-30-01-2R CARGO DOOR EXTERNAL SKIN REPAIR 4, MAJOR REPAIR.
COURIER AREA FLOOR BOARD 222MEF IS DELAMINATED FABRICATED COURIER AREA FLOOR BOARD 222MEF ON TRAVELER T22/1631880 IAW DWG SRZ-25- 005 REV R, MAJOR REPAIR
FLOOR BOARD 222MDF IS DELAMINATED FABRICATED COURIER AREA FLOOR BOARD 222MDF FROM TRAVELER T22/1631882 IAW DWG SRZ- 25-005 REV. R "MAJOR REPAIR"
COURIER AREA FLOOR BOARD 221BF IS DELAMINATED FABRICATED COURIER AREA FLOOR BOARD 221BF FROM TRAVELER T22/1631832 IAW DWG SRZ- 25-005 REV R, MAJOR REPAIR.
MDIS 916 29-02 5134 29JUN22 CDG OPEN U ON SHORT FINAL 27R CDG GOT LH HYD EICAS MESSAGE. SHORTHLY AFTER TOUCHDOWN GOT LH HYD SYSTEM PRESS EICAS MESSAGE AND NO TILLER AUTHORITY. USE DIFFERENTIAL BRAKING TO VACATE THE RUNWAY. LH HYD QTY WAS 0.07USG. AFTER SHUTDOWN HYD QTY DOWN TO 0.0 USG. NO HYD OVERHEAT.EMERGENCY DECLARED.VERBALY REPORTED BY CREW MEMBER 5072525.WRENCH INOP. REMOVED AND REPLACED STEERING HOSE HYD ASSY IAW AMM 20-10-10-4, REF IPC 32-34-51-15 ITEM 317. REFILLED LH HYD SYS IAW AMM 12-12-01-3, RAN APU PER RH TO PRESSURISE LH SYS, LEACK CHECK OK. 30JUN22 01:22..HJK.. - CONF CALL HELD WITH EMEA MOC, HANS-MDO AND DAVE-MGR. ALL GOOD WITH REPLACEMENT OF LINE AS FIX, A/C BEING RETURNED TO SERVICE
MDIS 916 52-10 4624 21JAN22 AMS FACT U DOOR 1 LEFT EXTERIOR HANDLE LATCH SPRING BROKEN. ENT BY:5192511 RPT BY:5192511 SHGN 21JAN22 07:25 AMS U REQUIRED PART SPRING PARTNO 69B13054-1 CPN 521285. IDENTIFIED PARTS SPRING MPN: 69B13054-1 CPN: 5215285 QTY: 1 FACT 21JAN22 11:24 AMS U REMOVED AND REPLACD SPRING IAW AMM SUBTASK 52-11-13-822-022 REV 129.0 PARTNO 69B13054-1 FAA FORM 8130-3 TRACKING NO 05714748. OPS CHECK GOOD.
COMPLY WITH WORK IN PROCCESS EA #F-5310-T0365897 WORK ACCOMPLISHED PER FEDEX EA #F-5310-T0365897
DURING PREFLIGHT FOUND EMERGENCY LIGHT GUARDED SWITCH CARD BROKEN INOPERABLE. IDENTIFIED PARTS SWITCH GUARD MPN: 402-112 CPN: 3313437 QTY: 1 PART 22JAN21 05:20 CDG U ORDER PART MPN: 402-112 CPN: 3313437 QTY: 1 MSN: 2044766 OIL 22JAN21 05:51 CGN U NO RESTRICTION, REF : F-3350-T0359321 F-3350-T0359321 PART 1 HAS TO BE COMPLIED NOW. PART 2 HAVE TO BE DONE IN 4 CYCLE ACCOMPLISHED EA F-3350-T0359321 PART 1 AS REQUIRED. A/C OK FOR FLIGHT. C/7257126 OILS 22JAN21 CGN U OIL REFERENCE: F-3350-T0359321 TERMINATING ACTION REQUIRED. INSTALLED THE NEW EMERGENCY LIGHT SWITCH GUARD BY THE ACCOMPLISHMENT OF THE E.A:F-3350-T0359321 PT2. OK TO CONTINUE.
L1 DOOR ''SLIDE'' LIGHT INOPERABLE WHEN THE DOOR IS CLOSED AND THE SLIDE IS ARMED. FOLLOWING FIM 25-66-00-FT 802, REBULB PERFORMED, IAW WDM 25-66-11. TEST OK.
DOOR 1R EXTERIOR EMERGENCY LIGHT INOPERABLE. BULB REPLACED ACC AMM 33-51-06-2-1 REV 126.7. OPERATIONS TEST SATISFACTORY.
LT OUTBOARD AFT FLAP LOWER SURFACE REPAIR AT 102 INCHES FROM INBOARD EDGE AND 10 INCHES FROM THE AFT EDGE REPAIR, REQUIRES EVALUATION TO DETERMINE IF IT WAS ACCOMPLISHED IN ACCORDANCE WITH APPROVED DATA. EVALUATED REPAIR IAW EO F-5100-7-5001 A6 PT1. STRUCTURES-REPAIR CATALOG-B757-200 REPAIR IDENTIFICATION & TRACKING REQUIREMENTS 14 CFR 121.707. NO REPAIR RECORDS AVAILABLE. FOUND NOT TO COMPLY WITH SRM. CORRECTIVE ACTION: REPLACED REPAIR, IAW SRM 57-53-01-2R REPAIR 1 FIG 201 TRACKING ON EA F-5750-T0358538. WINGS-FLIGHT SURFACES-LT OUTBOARD AFT FLAP LOWER SURFACE COMPOSITE REPAIR 102" FROM INBOARD, 10" FROM TRAILING EDGE RSC TRACKING. THIS IS A CATEGORY A. MAJOR REPAIR.
FUSELAGE SKIN REPAIR WAS REPLACED BS 727-743 S21R-S22R SRM 53-00-01-2R REPAIR 16 FIG 201. ON WO 61602 SNRM N00005 18 AUG 2014. NEW SDR RAISED DUE WRONG SDR ATTACHED TO RECORDS EVALUATED REPAIR, IAW EO F-5100-7-5001 A6 PT1. STRUCTURES-REPAIR CATALOG-B757-200 REPAIR IDENTIFICATION & TRACKING REQUIREMENTS 14 CFR 121.707. FOUND TO COMPLY WITH SRM 53-00-01-2R REPAIR 16 FIG 201. CATEGORY B REPAIR. MCMRT WO 61602 SNRM N00005. NEW SDR RAISED DUE WRONG SDR ATTACHED TO PREVIOUS RECORDS.
LT INBOARD MAIN FLAP UPPER SURFACE HAS SMALL PUNCTURE HOLE. REPAIRED DAMAGES, IAW SRM 51-70-07-0G AND FEDEX EA F-5730-T0358461 "WING-FLIGHT SURFACES-LT INBOARD MAIN FLAP COMPOSITE REPAIR-RSC TRACKING."
CABIN FLOOR BEAM INTERCOSTALS ABOVE FWD CARGO AFT BULKHEAD STACHNIONS AT BSTA 845 LBL & RBL 16.05 HAVE ELONGATED HOLES WHERE STACHION PINS LOCATE. REPLACED INTERCOSTALS, QTY 2, BS 839-BS 860, LBL 16 & RBL 16, IAW EA F-5340-T0358516. FUSELAGE-ATTACH FITTINGS-ALTERNATIVE FINISH AND EXTRUSION DURING FABRICATION OF INTERCOSTAL BS 839 TO BS 860, RBL AND LBL 16.
RT VERTICAL STABILIZER PANEL 175N2001 IS DAMAGED. DAMAGE IS 13.5" FROM L EDGE OF PANEL AND 15" FROM BOTTOM OF PANEL PLEASE EVA. REPAIRED SMALL PUNCTURE ON THE OUTER SKIN OF RT VERTICAL STAB PANEL P/N=175N2001, IAW SRM 55-30-01-2R REPAIR 5 AND SRM 51-70-10-2R REPAIR 4.
MAIN CARGO DECK FLOOR BEAM UPPER SURFACE EVIDENCE OF CORROSION AT BS 1100 RBL 24 TO RBL 44 , NUMEROUS LOCATIONS CORROSION REMOVED IAW SRM53-10-02-REV 125 AND FOUND TO BE OUT OF LIMITS IAW SRM 53-00-51-1A DETAIL III REV.125 CARRIED OUT REPAIR IAW EAF-5321-T0343108 PART(1) TITLE "FUSELAGE- FLOOR - MAIN DECK FLOOR BEAM UPPER CHORD-BS1100-CORRODED."
PDIS 916 52-00 2660 11MAR20 CDG FACT U LEFT ENTRY DOOR DIFFICULTY TO CLOSE. PERFORMED LEFT ENTRY DOOR LUBRICATION AS PER AMM 12-21-18-3. OPS CHECK OK. DOOR NO MORE DIFFICULT TO OPEN OR CLOSE.A/C OK FOR SERVICE.
DURING SERVICE CHECK FOUND RT EXTERIOR EMERGENCY LIGHT INOP. SERVICED RIGHT EMERGENCY SLIDE LIGHT WITH NEW BULB P/N 767 AS PER MM 33-51-06-2-1. ALL TEST PASSED, MEL CLOSED.
CREW WRITE UP. WITH BOTH PACKS ON WITH ENGINES RUNNING, THE COCKPIT IS VERY LOUD ON THE GROUND AND IN THE AIR. THE EXCESSIVE NOISE SEEMS TO COME FROM AIR FLOW FROM THE PACK. THIS IS A REPEAT WRITE UP FOR MANY YEARS. FLIGHT DECK NOISE LEVEL MEASUREMENT CHECK CARRIED OUT IAW AMM 21-00-00-6 RESULT 75DBS. CARRIED OUT TROUBLESHOOTING OF FLIGHT DECK NOISE IAW AMM 21-00- 00-6. RECIRCULATION AIR CHECK VALVE SATIS, RECIRCULATION FAN FILTER SATIS, CONDITIONED AIR BYPASS VALVE SATIS, BOTH PACKS VERIFIED IN LOW FLOW WITH BOTH ENGINES AT IDLE WITH APU BLEED OFF AND RECIRCULATION FAN ON. FOUND NO ORIFICE REDUCER PLATE INSTALLED AT EITHER BS 585 OR BS 883. FABRICATED ORIFICE PLATE IAW VT MOBILE AEROSPACE ENGINEERING INC DRAWING NUMBER 11812440. SEE ERS 18-04689 FOR ENGINEERING CORRESPONDENCE. INSTALLED ORIFICE PLATE AT BS 585 IAW AMM 21-20-01-4. CARRIED OUT ORIFICE INSTALLATION TEST IAW AMM 21-20-01-4. CARRIED FLIGHT DECK NOISE LEVEL MEASUREMENT CHECK IAW AMM 21-00-00-6 RESULT 67DBS. P/N 11812440-0450-0230
PDIS 916 36-11 2170 07SEP19 CPH OPEN U LOGPAGES:2531648 R ENG BLEED OFF EICAS MSG JUST BEFORE V1. COMPELED WITH QHR PROCEDURE. SHGN 07SEP19 20:50 CPH U PROCEEDING WITH T/S IAW FIM 36-10/816. R&RED PRSOV ON RT ENGINE, OPERATION IS NORMAL ALL OK.
RECEIVED "GEAR DISAGREE" EICAS WHEN THE GEAR WAS RAISED. THE EICAS REMAINED ON FOR APPROXIMATLEY 4 SEC. ALL OTHER INDICATIONS WERE NORMAL. PSEU BITE PERFORMED NO FAULT FOUND ALSO HISTORY FAULT NO FOUND. IAW FIM 32-09 REF. WRI 32-30/2016 FOR FINDING AND REPLACEMENT OF LEFT MAIN GEAR DOOR ACTUATOR. AFTER TOWING A/C TO ANOTHER POSITION A/C JACKED IAW. AMM 07-11-01-2 AND CONTINUED T/S PER FIM 32-30 TASK 814. NO FAULTS FOUND. LEFT HYDRAULIC SYSTEM PRESSURISED WITH GROUND HYDRAULIC CART IAW. AMM 29-11-00-2 AND PERFORMED GEAR SWING IAW. AMM 32-32-00-5 FOR MAIN GEAR AND AMM 32-34-00-5 FOR NOSE GEAR. CYCLED GEAR 3 TIMES AND ALL TEST PASSED AND NO FAULTS OR EICAS MESSAGES APPEARED. A/C PUT BACK TO NORMAL CONDITION AND REACTIVATED FLIGHT MODE IAW AMM 32-09-02/201. A/C OK FOR SERVICE.
MAIN CARGO DECK FLOOR BEAM UPPER CHORD CORRODED BS1040 TO BS 1080 LBL 24.5 CORROSION REMOVED IAW SRM 51-10-02 REV 125 AND FOUND TO BE OUTSIDE LIMITS IAW SRM 53-00-51-1A DETAIL III REV 125 NOMINAL THICKNESS OF UPPER CHORD = 0.090" MAX ALLOWABLE BLEND = 10% = 0.009" ACTUAL MAX BLEND DEPTH = 0.060" FLOOR BEAM UPPER CHORD REPLACED IAW BOEING DWG #144N8017,111N5201 AND SRM 51- 40-02 REV 125 BS 1040 T0 BS 1080 LBL 24.5.
MAIN CARGO DECK FLOORBEAM UPPER CHORD CORRODED BS 1040-BS 1080 RBL 26. CORROSION REMOVED IAW SRM 51-10-02 REV 125 AND FOUND TO BE OUT OF LIMITS IAW SRM53-00-51-1A DETAIL III REV 125. NOMINAL THICKNESS OF UPPER CHORD 0.090" MAX ALLOWABLE BLEND=10%=0.009 ACTUAL MAX BLEND DEPTH= 0.024". FLOORBEAM UPPER CHORD REPLACED IAW DWG 144N8017, 111N5201 AND SRM 51-40-02 REV 125 BETWEEN BS1040 TO BS 1080.
MAIN CARGO DECK FLOOR BEAM UPPER CHORD CORRODED BS 1040-BS1080 LBL 45.5 CORROSION REMOVED IAW SRM 51-10-02 REV 125 AND FOUND TO BE OUTSIDE LIMITS IAW SRM 53-00-51-1A DETAIL III REV 125 NOMINAL THICKNESS OF UPPER CHORD = 0.090", MAX ALLOWABLE BLEND = 10% 0.009" ACTUAL MAX BLEND DEPTH = .043". FLOOR BEAM UPPER CHORD REPLACED IAW BOEING DWG # 144N8017, 111N5201 AND SRM 51- 40-02 REV 125. BS 1040 TO BS 1080 LBL 45.5
INTERCOSTAL DAMAGED BSTA 1055, RBL0-RBL26. REPAIRED DAMAGED INTERCOSTAL IAW SRM 51-70-12-REV 125 AND EAF-5340-T0343588 PART(1).
MAIN DECK FLOOR BEAM EVIDENCE OF CORROSION ON UPPER SURFACE BS376 BETWEEN LBL47 AND LBL55 AT FASTERNER HOLES CORROSION REMOVED IAW SRM 51-10-02 AND FOUND TO BE OUT OF LIMIT IAW SRM 53-00-511A NOTE B DETAIL II ORIGINAL THICKNESS 0.125" ,DEPTH OF BLEND=0.029", MAX ALLOWABLE=0.012" , AREA REPAIRED IAW FEDEX E.A.#:F-5321-T0342941 PART (1)
MAIN DECK SEAT TRACK, EVIDENCE OF CORROSION ON UPPER SURFACE BS 344 TO BS 376 LBL 6.75. CORROSION REMOVED IAW SRM 51-10-02 REV 125 AND FOUND TO BE OUTSIDE ALLOWABLE LIMITS IAW SRM 53-00-52-1A FIG 101 DETAIL VIII REV 125. NOMINAL THICKNESS OF FLANGE =0.085", DEPTH REMOVED 0.020" MAX ALLOWABLE 0.017 BLEND MUST NOT BE LESS THAN 20X AWAY FROM AN EXISTING FASTENER, BLEND IS AT A FASTENER LOCATION. SEAT TRACK REPLACED IAW DWG 3504.
SLAT TAI COVER PANEL 524AL HAS SIGNS OF LOWER SURFACE CORROSION. FABRICATED AND INSTALLED NEW SKIN PANEL IAW DWG 114N4079 REV B AND GMM 7-0-1001, AND EA F-5750-TO343532 PART 1.
EVIDENCE OF CORROSION ON UPPER SURFACE OF FLOORBEAM AT BS 364 RBL 46 TO RBL 56 AT NUMEROUS LOCATIONS MAIN CARGO DECK. REMOVED CORROSION ON UPPER SURFACE OF FLOORBEAM AT BS 364 RBL 46 TO RBL 56 IAW SRM 51-10-02 REV 125 MEASURED AND EVALUATED BLENDED AREAS IAW SRM 53-00-51-1A DETAIL III REV 125 AND FOUND AREA TO OUT OF LIMITS. REPAIRED IAW SRM 53-00-52-2R-8 REPAIR 8 AND EA F 5310-TO343269.
R/H VERTREAL STAB HAS SUSPECT PANEL DAMAGE ON LOWER R/H SIDE FWD OF BSTA 1729. REPAIRED IAW SRM 55-30-01-2R
ANGLE RETAINER BRACKET BS 1715.5 RBL 11.5 CORRODED. EVALUATE AND RECTIFY, REPLACED BRACKET IAW SRM 51-40-02 REV 125.
UPON REMOVAL OF WEB AT BS 336 LBL 24 SUPPORT BRACKETS FOUND TO BE CORRODED UNDER WEB. SUPPORT BRACKETS REPLACED IAW SRM 51-40-02 AND DWG 141N5170 REV C.
HARD POINT MOUNT CORRODED BETWEEN BS 323 AND 344, LBL 24. THE MOUNT FITTING WAS REPLACED IAW SRM 51-40-02, REV 125.
CORROSION ON FLOORBEAM TOP CAP UPPER SURFACE AT BS 1640 RBL 30 TO 40. CORROSION REMOVED IAW SRM 51-10-02 REV 125 AND FOUND TO BE OUT OF LIMITS IAW SRM 53-00-51-1A ALLOWABLE DAMAGE FIG 101 DETAIL III REV 125. MEASUREMENTS RECORDED. ORIGINAL MATERIAL THICKNESS = 0.125" MAX ALLOWABLE DEPTH OF CLEAN UP = 10% 0.0125" MAX DEPTH OF CLEAN UP = 0.087". REPAIR CARRIED OUT IAW EA F-5310-TO343359 P1 FLOORBEAM TOP CAP BSTA 1640, RBL 25-40 CORRODED AND SRM 53-00-51-2R REPAIR 8.
CORROSION ON WEB BENEATH CABLE FAIRLEAD BS 336 LBL 24. CORROSION REMOVED IAW SRM 51-10-02 AND FOUND TO BE OUT OF LIMITS IAW SRM 53-00-04-1A DETAIL II REV 125. REPLACED WEB IAW DRAWING 141N5170 REV C AND SRM 51-40-02 REV 125.
ANGLE RETAINER BRACKET BS.1715.5 LBL 11.2 CORRODED BRACKET REPLACED AT BS 1715.5 LBL 11.2 IAW SRM 51-40-02 REV 125
RT WING REAR SPA WIGGLE PLATE CRACKED AT WSTA 344 REPLACED WIGGLE PLATE AT WSTA 344 IAW SRM 51-40-02 REV 125.
LAV SERVICE PANEL 119AL STRENGHTENING RIB IS CORRODED REPLACED CORRODED LAV SERVICE PANEL RIB IAW SRM 51-40-02 REV 125.
EVIDENCE OF CORROSION ON DOOR 1L LOWER GATE EXTERIOR SURFACE AT FORWARD AND AFT LOCATIONS ADJACENT TO SEAL REATAINER REMOVE CORROSION AND CHECK LIMITS IAW SRM REMOVED CORROSION AND MEASURED AND EVALAUTED BLENDS IAW SRM 52-10-02-1A FIG 101 DETAIL XII REV 125 AND FOUND TO BE OUT OF LIMITS. A MINIMUM OF 0.050" IS PERMITTED LOCALLY AND AN AVERAGE OF 0.090" IS PERMITTED ALONG THE SURFACE AVERAGE. EXTENSIVE CORROSION FOUND AND MEASURED TO BE LESS THAN 0.060" AVERAGE. REPLACED LOWER GATE IAW SRM 51-40-02 REV 125 AND IPC 52-11-01-12 FIG 12 SHEET 7.
LT WING, NR 1 & NR 2 FLAP TRACKS LOOSE AT AFT ATTACH POINTS. REPLACED NR 1 & NR 2 FLAP TRACK, AFT ATTACH BOLTS IAW AMM 27-51-15.
RT WING, NR 7 & NR 8 FLAP TRACKS LOOSE AT AFT ATTACH POINTS. REPLACED NR 7 & NR 8 FLAP TRACK, AFT ATTACH BOLTS IAW AMM 27-51-15
CORROSION ON SEAT TRACK UPPER FLANGES BS 1080-1180 LBL 24.75 AT SEVERAL LOCATIONS. REMOVED CORROSION ON SEAT TRACK AT BS 1080-1180 LBL 24.75 IAW SRM 51-10-02 REV 125. MEASURED AND EVALUATED BLENDS IAW SRM 53-00-1A DETAIL VII AND VIII REV 125 AND FOUND TO BE OUT OF LIMITS. REPLACED CORRODED SEAT TRACK LOCATED BS 1075-1180 LBL 24.75 IAW SRM 51-40-02 REV 125 AND IAW DWG 144N5001.
MAIN CARGO DECK SEAT TRACK CORRODED ON UPPER FLANGE BS 1080-1180 LBL 45.5. REMOVED CORROSION IAW SRM 51-10-02 REV 125 , MEASURED AND EVALUATED BLENDS IAW SRM 53-00-52-1A DETAIL VII AND VIII REV 125. FOUND TO BE OUT OF LIMITS. SEAT TRACK REPLACED IAW SRM 51-40-02 AND DRAWING 144N5001.
CORROSION ON SEAT TRACK UPPER FLANGES BS 1080-1180 RBL 45.5 MAIN CARGO DECK. REMOVED CORROSION IAW SRM 51-10-02 REV 125. MEASURED AND EVALUATED BLENDS IAW SRM 53-00-52-1A DETAIL VII AND VIII REV 125 AND FOUND TO BE OUT OF LIMITS AT SEVERAL LOCATIONS. NOMINAL THICKNESS=0.085" MAX ALLOWABLE BLEND (20%)=0.017" MAX DEPTH OF BLEND=0.060". DRILLED UP AND INSTALLED NEW SEAT TRACK IAW SRM 51-40-02 REV 125 AND DRAWING 144N5001 SHEET 3 REV A.
MAIN CARGO DECK FLOORBEAM UPPER TEE HAD EVIDENCE OF CORROSION AT BS 1100, RBL 48 - 56. THE CORROSION WAS REMOVED IAW SRM 53-10--02, REV 125, AND FOUND TO BE OUT OF LIMITS IAW SRM 53-00-51-1A, DETAIL III, REV 125. REPAIRED IAW EA F-5321-343108.
DOOR R2 PREVIOUS REPAIR FOUND TO BE CRACKED AFTER REPEAT INSPECTION AT UPPER HINGE CUTOUT CARRIED OUT REPAIR TO DOOR 2R EXISTING REPAIR DOUBLER IAW.FEDEX EA# F-5210- T0343194 PART(1) TITLE" DOORS-PASSANGER/CREW- DOOR 2R UPPER HINGE CUT-OUT REPAIR-ANGLE CRACKED" AND SRM 52-10-02-2R REPAIR 1 REV 125 AND SRM 51-40-02 REV 125. THIS IS A CATEGORY B REPAIR ,INSPECTION THRESHOLD 50,000 TOTAL DOOR FLIGHT CYCLES OR 5,800 FGHT CYCLES AFTER REPAIR INSTALLATION IF THE DOOR FLIGHT CYCLES ARE NOT KNOWN. INSPECTION METHOD :HIGH FREQUENCY EDDY CURRENT.INTERVAL 5,800 DOOR FLIGHT CYCLES FLIGHT CYCLES AT TIME OF REPAIR=27177 FLIGHT HOURS AT TIME OF REPAIR= 71433
MAIN CARGO DECK FLOORBEAM UPPER SURFACE EVIDENCE OF CORROSION AT BS 1100 RBL 24 TO RBL 44, NUMEROUS LOCATIONS CORROSION. REMOVED IAW SRM 53-10-02 REV 125 AND FOUND TO BE OUT OF LIMITS IAW SRM 53-00-51-1A DETAIL III REV 125. CARRIED OUT REPAIR IAW EA F-5321-T0343108 PART(1).
MAIN CARGO DECK SEAT TRACK EVIDENCE OF CORROSION ON LOWER SURFACE FLANGE AT BS 1057 RBL 44 REMOVED CORROSION ON STUB BEAM UPPER CHORD IAW SRM 51-10-02 REV 125 AND FOUND TO BE OUT OF LIMITS IAW SRM 53-00-51-1A DETAIL III REV 125. FLOOR BEAM UPPER CHORD REPLACED IAW BOEING DRAWINGS 144N8017 143N5470 AND 111N5201 AND SRM 51-40-02 REV 125
MAIN CARGO DECK FLOORBEAM UPPER SURFACE EVIDENCE OF CORROSION AT BS 1200 RBL 49 AND 59 AND RBL 26 TO RBL 44. CORROSION REMOVED IAW SRM 51-10-02 REV 125 MEASURED AND EVALUATED BLENDS IAW SRM 53-00-51-1A DETAIL III REV 125 AND FOUND BLENDS TO BE OUT OF LIMITS AT SEVERAL LOCATIONS. NOMINAL THICKNESS OF UPPER CHORD = 0.130" MAX BLEND ALLOWED = 0.013" MAX DEPTH OF BLEND = 0.033". REPAIR CARRIED OUT IAW SRM 53-00-51-2R REPAIR 8.
MAIN CARGO DECK SEAT TRACK EVIDENCE OF CORROSION ON UPPER SURFACE AT NUMBEROUS LOCATIONS BS 1180 TO BS 1200 AT RBL 44 CORROSION REMOVED IAW SRM 51-10-02 REV 125 AT BS 1180 TO BS 1200 AND FOUND TO BE OUTSIDE LIMITS IAW SRM 53-00-52-1A DETAIL VII REV 125. SEAT TRACK SECTION BS 1180 TO BS 1280 RBL 44 REPLACED IAW BOEING DRAWING # 46N5130 REV A AND SRM 51-40-02 REV 125 .
MAIN CARGO DECK SEAT TRACK EVIDENCE OF CORROSION ON UPPER SURFACE AT NUMEROUS LOCATIONS BS 1180 TO BS 1200 LBL 24.5 REMOVED CORROSION ON SEAT TRACK AT BS1180-1200 LBL24 IAW SRM 51-10-02 REV.125 MEASURED AND EVALUATED BLENDS IAW SRM 53-00-52-1A DETAIL VII & VIII REV 125 AND FOUND TO BE OUT OF LIMITS AT SEVERAL LOCATIONS. NOMINAL THICKNESS=0.085" MAX ALLOWABLE BLEND (20%)=0.017" MAX DEPTH OF BLEND = 0.060" REPAIRED CORRODED SEAT TRACK AT BS 1180-1200 LBL.24.5 IAW SRM 53-00-52-2R OPTION 2 ,REPAIR 3 REV 125
MAIN CARGO DECK SEAT TRACK EVIDENCE OF CORROSION ON UPPER SURFACE AT NUMEROUS LOCATIONS BS 1180 TO BS 1200 LBL 24.5 CORROSION REMOVED IAW SRM 51-10-02 REV 125 AND FOUND TO BE OUT OF LIMITS AT SEVERAL LOCATIONS IAW SRM 53-00-52-1A DETAIL VII AND VIII REV 125. REPAIR CARRIED OUT IAW SRM 53-00-52-2R REPAIR 3 OPTION 2.
MAIN CARGO DECK SEAT TRACK EVIDENCE OF CORROSION ON UPPER SURFACE BS 953 TO BS 968 AND BS 1160 LBL 58.5 SEAT TRACK CORROSION BETWEEN BS 953-968 LBL 58.5 FOUND TO BE OUT OF LIMITS IAW SRM 53-00-52-1A DETAIL VII AND VIII REV.125.REPAIRED SEAT TRACK IAW SRM 52-00-52-2R REPAIR 3 OPTION 2 FIG.201 REV 125 AND FEDEX E.A.#:F -5321-T0343502 PART(1)
MAIN CARGO DECK SEAT TRACK EVIDENCE OF CORROSION ON UPPER SURFACE AT NUMEROUS LOCATIONS BS 1015 TO BS 1075 RBL 26 CORROSION REMOVED IAW SRM 51-10-02 REV 125 AND FOUND TO BE OUTSIDE LIMITS IAW SRM 53-00-51-1A DETAIL III REV 125 NOMINAL THICKNESS OF UPPER CHORD = 0.090" MAX ALLOWABLE BLEND = 10% = 0.009" ACTUAL MAX BLEND DEPTH = 0.024" FLOOR BEAM UPPER CHORDS REPLACED IAW BOEING DWG #144N8017,111N5201, 143N570 AND SRM 51-40-02 REV 125 BS 900 T0 BS 1080 RBL 26
MAIN CARGO DECK SEAT TRACK EVIDENCE OF CORROSION ON UPPER SURFACE AT NUMEROUS LOCATIONS BS915 TO BS 1080 LBL 24.5 CORROSION REMOVED IAW SRM 51-10-02 REV 125 AND FOUND TO BE OUTSIDE LIMITS IAW SRM 53-00-51-1A DETAIL III REV 125, NOMINAL THICKNESS OF UPPER CHORD = 0.090" MAX ALLOWABLE BLEND = 10% 0.009" ACTUAL MAX BLEND DEPTH = 0.060". FLOOR BEAM UPPER CHORDS REPLACED IAW BOEING DWG #111N5201, 144N8017, 143N5470 AND SRM 51-40-02 REV 125. BS 900 TO BS 1080 LBL 24.5
MAIN CARGO DECK CREASE BEAM EVIDENCE OF CORROSION ON UPPER SURFACE AT NUMEROUS LOCATIONS BS 1040 TO BS 1180 RBL 64 REMOVED CORROSION ON CREASE BEAM AT BS 1040-1180, RBL 64 IAW SRM 51-10-02 REV 125. MEASURED AND EVALUATED BLENDS IAW SRM 53-40-13-1A DETAIL VII REV.125 AND FOUND TO BE OUT OF LIMITS.NOMINAL THICKNESS=0.071" ,MAX ALLOVABLE BLEND (10%)=0.007" MAX DEPTH OF BLEND=0.030". FABRICATED AND INSTALLED NEW CREASE BEAM IAW.FEDEX GMM.7-0-1001 REV .151 AND BOEING DRAWING #144N5214 REV.INITIAL AND SRM 51-40-02 REV.125
MAIN CARGO DECK FLOORBEAM UPPER SURFACE EVIDENCE OF CORROSION AT BS 1200 LBL 3 TO LBL 20 AND LBL 30 TO LBL 40 NUMEROUS LOCATIONS. CORROSION REMOVED IAW SRM 51-10-02 REV 125 AND FOUND TO BE OUTSIDE LIMITS IAW SRM 53-00-51-1A DETAIL III REV 125 AT LBL 8. REPAIR CARRIED OUT IAW SRM 53-00-51-2R REPAIR 8.
MAIN CARGO DECK CREASE BEAM EVIDENCE OF CORROSION ON UPPER SURFACE BS1040 TO BS 1180 LBL 64 NUMEROUS LOCATIONS. CORROSION REMOVED AND FOUND TO BE OUTSIDE OF LIMITS IAW SRM 53-40-13-1A DETAIL VII, REV 125. REPLACED INBOARD CHORD IAW SRM 51-40-02 & BOEING DRAWING 144N5214
MAIN CARGO DECK SEAT TRACK EVIDENCE OF CORROSION ON SEAT TRACK UPPER SURFACE BS 1180 TO BS 1200 LBL 44 NUMEROUS LOCATIONS. REMOVED CORROSION ON SEAT TRACK AT BS 1180-1200 LBL44 IAW SRM 51-10-02 REV 125, AND MEASURED AND EVALUATED BLENDS IAW SRM 53-00-52-1A DETAIL VII & VIII REV 125, FOUND TO BE OUT OF LIMITS. NOMINAL THICKNESS = 0.085" MAX ALLOWABLE BLEND (20%)=0.017", MAX DEPTH OF BLEND =0.070" FABRICATED SEAT TRACK AND SPLICE AND INSTALLED IAW SRM 53-00-52-2R OPTION 2, REV 125.
MAIN CARGO DECK SEAT TRACK EVIDENCE OF CORROSION ON UPPER SURFACE AT NUMEROUS LOCATIONS BS 1075 TO BS 1180- RBL 26 CORROSION REMOVED IAW SRM 51-10-02 REV 125.BLENDS MEASURED AND EVALUATED IAW SRM 53-00-52-1A DETAIL VII AND DETAIL VIII REV 125 AND FOUND TO BE OUT OF LIMITS AT SEVERAL LOCATIONS. REPLACED SEAT TRACK IAW SRM 51-40-02 REV 125 AND BOEING DRAWING 144N5001
MAIN CARGO DECK CREASE BEAM EVIDENCE OF CORROSION ON UPPER SURFACE BS 900 TO BS 1040 LBL 64 NUMEROUS LOCATIONS. CORROSION REMOVED AND FOUND TO BE OUTSIDE LIMITS IAW 53-40-13-1A DETAIL VII REV 125. INBOARD CHORD TO BE REPLACED IAW SRM AND DRAWING144N5152.
MAIN CARGO DECK CREASE BEAM EVIDENCE OF CORROSION ON UPPER SURFACE AT NUMEROUS LOCATIONS BS900 TO BS 1040 RBL 64 CORROSION REMOVED AND FOUND TO BE OUTSIDE OF LIMITS IAW SRM 53-40-13-1A DETAIL VII. CREASE IBEAM INBOARD CHORD TO BE REPLACED IAW SRM.51-40-02 REV 125 AND BOEING DWG# 144N5152
EVIDENCE OF CORROSION ON SEAT TRACK UPPER SURFACE INBOARD AND OUTBOARD FLANGES BS 900 TO BS 1080 AT RBL 45.5 NUMEROUS LOCATIONS. CORROSION REMOVED IAW SRM 51-10-02 REV 125 AND FOUND TO BE OUTSIDE LIMITS IAW SRM 53-00-51-1A DETAIL III REV 125, NOMINAL THICKNESS OF UPPER CHORD = 0.090" MAX ALLOWABLE BLEND = 10% 0.009" ACTUAL MAX BLEND = 0.076". FLOORBEAM UPPER CHORD REPLACED IAW DWG 111N5201, 143N5470, 144N8017 AND SRM 51-40-02 REV 125 BS 900 T0 BS 1080 RBL 45.5.
L/H WING REAR SPAR EVIDENCE OF CORROSION ON RIB WSTA 817 CARRIED OUT REPAIR TO L/H WING REAR SPARE T/E RIB AT WS.817 IAW FEDEX E.A. # F-5740- T0343045 PART (1) TITLE "WINGS-ATTACH FITTINGS - TRAILING EDGE RIB AT WS 817 - L/H WING CORROSION. THIS IS A MINOR REPAIR.
MAIN CARGO DECK SEAT TRACK EVIDENCE OF CORROSION ON UPPER SURFACE BS 915 TO BS 1080 LBL 45.5 CORROSION REMOVED IAW SRM 51-10-02 REV 125 BS 900 TO BS 1040 LBL 45.5 AND BS 1040 TO BS 1080 LBL45.5 BOTH SECTIONS FOUND TO BE OUTSIDE LIMITS IAW SRM 53-00-51-1A DETAIL III REV 125.. FLOOR BEAM UPPER CHORDS REPLACED IAW BOEING DRAWINGS # 111N5201 ,143N5470 ,144N8017 AND SRM 51-40-02 REV 125.
EVIDENCE OF CORROSION ON INBOARD FLAP TRACK SUPPORT STRUCTURE FITTING IN RT MLG WHEEL WELL AFT BULKHEAD BS 1180. CORROSION REMOVED IAW SRM 51-10-02 REV 125. REPAIR CARRIED OUT IAW EA F-5340-TO343107.
MAIN DECK, EVIDENCE OF CORROSION ON THE UPPER SURFACE OF THE FLOOR SUPPORT AT BS 340 LBL 34. CORROSION REMOVED IAW SRM 51-10-02, REV 125, AND FOUND TO BE OUT OF LIMITS IAW 53-00- 04-1A ALLOWABLE DAMAGE 1, FIG 101, DETAIL III, REV 125. THE FLOOR SUPPORT WAS REPLACED IAW SRM 51-40-02, REV 125.
MAIN CARGO DECK, EVIDENCE OF CORROSION ON LOWER SURFACE OF FLOORBEAM UPPER CHORD AT BS1660 LBL 53.5. CORROSION REMOVED IAW SRM 51-10-02 AND FOUND TO BE OUTSIDE LIMITS IAW SRM 53-00-51-1A FIG 101 DETAIL III REV 125. REPAIR CARRIED OUT IAW 53-00-51-2R REPAIR 8.
MAIN CARGO DECK SEAT TRACK HAS EVIDENCE OF CORROSION ON UPPER SURFACE AT BS1636 LBL 47. REMOVED CORROSION AND FOUND TO BE OUT OF LIMIT IAW SRM 53-00-52-1A ALLOWABLE DAMAGE 1, CARRIED OUT REPAIR IAW SRM 53-00-52-22 REPAIR 3, OPTION 2 REV 125, THIS IS A MAJOR REPAIR.
LH OVERWING FILL PORT FOUND TO HAVE SKIN CORROSION REMOVED CORROSION ON L/H VERWING FILL PORT SKIN AND FOUND TOBE OUT OF LIMITS IAW SRM 57-20-01-1A FIG 102 DET I REV 125MEASUREMENTS :ALLOWABLE MIN.REMANING THIKNESS=0.240" ACTUAL THICKNESS =0.200" ALLOWABLE BLEND WIDTH=0.8" ACTUAL BLEND WIDTH=1.3".CARRIED OUT REPAIR IAW FEDEX E.A.# F-5730-T0343023 TITLE:WINGS -PLATES AND SKINS- CORROSION OVERWING FILL PORT L/H WING AND IAW.SRM57-20-01-2R REPAIR 7 REV 125.
RH OVERWING FILL PORT FOUND TO HAVE SKIN CORROSION CARRIED OUT REPAIR TO R/H WING UPPER SKIN AT FILL PORT IAW FEDEX E.A.#: F-5730- T0343044 PART (1) TITLE:" WINGS - PLATES AND SKINS - CORROSION OVERWING FILL PORT R/H WING" AND SRM 57-20-01-2R REPAIR #7 REV.125
R/H WING EVIDENCE OF CORROSION ON REAR SPAR TRAILING EDLE RIB WSTA 817 CARRIED OUT REPAIR TO R/H WING REAR SPAR T/E RIB IAW.FEDEX E.A. # :F5740-T0343046 PART (1) TITLE "WINGS-ATTACH FITTINGS- TRAILING EDGE RIB AT W/S 817-R/H WING-CORROSION THIS IS A MINOR REPAIR.
RT IN/BD MAIN FLAP IN/BD PROGRAMMING TRACK RIB CRACKED. REPAIRED IAW EA F-5750-T0343141 P1. THIS IS A MAJOR REPAIR.
EVIDENCE OF CORROSION ON UPPER SURFACE OF MAIN DECK FLOOR INTERCOSTAL BS 344 TO BS 364 BL 0. CORROSION REMOVED IAW SRM 51-10-02 REV 125 AND FOUND TO BE OUT OF LIMITS IAW SRM 53-00-51-1A REV 125. REPLACED INTERCOSTAL IAW SRM 51-40-02 AND DWG 141N5191 REV A.
MAIN DECK FLOORBEAM EVIDENCE OF CORROSION ON UPPER SURFACE OF FLOORBEAM AT BS 324 RBL 42 TO RBL 58 NUMEROUS LOCATIONS. CORROSION REMOVED AND FOUND TO BE OUTSIDE LIMITS IAW SRM 53-00-51-1A DETAIL III. REPAIR CARRIED OUT IAW SRM 53-10-08-2R REPAIR 1. NOTE THIS IS A CATEGORY B REPAIR.
MAIN CARGO DECK EVIDENCE OF CORROSION ON ANCHOR NUTS AND ANCHOR NUT STRIPS ON LOWER SURFACE OF FLOORBEAM AT BS1680 AT LOCATIONS BETWEEN LBL4 AND LBL 47.5. CORROSION REMOVED AND FOUND TO BE OUTSIDE LIMITS AT BS 1680 LBL 32.5. REPAIR CARRIED OUT IAW SRM 53-60-51-2R REPAIR 3.
FLOOR PANEL 241MCF CRACKED/DENTED. REPAIRED FLOOR PANEL 241 MCF IAW SRM 53-00-50-2R MATERIALS: FIBREGLASS: BMS 9-3 TY.H B/N: 21263471 RESIN: BMS 8-201 TY.4 B/N: 0181564800.
FLOOR PANEL MWF251 CRACKED. REPAIRED FLOOR PANEL 251 MWF IAW SRM 53-00-50-2R MATERIALS: FIBREGLASS: BMS 9-3 TY.H B/N: 21263471 RESIN: BMS 8-201 TY.4 B/N: 0181564800 INSERT P/N:SL618-3A B/N: 0161126.
FLOOR PANEL 241MCF IS CRACKED AND DENTED.
3 DENTS ON TOP OF EMPENNAGE JUST TO THE LEFT OF RUDDER . REQUIRE EVALUATION REPAIRED IAW SRM 53-80-01 FIG 1 R2 SH1 & 51-70-10-2R REPAIR 4
AFT CARGO DOOR CRACK IN SEAL DEPRESSOR AT AFT UPPER CUTOUT. SEAL DEPRESSOR FOUND TO BE OUT OF LIMITS IAW SRM 52-30-02-1A. REPLACED SEAL DEPRESSOR IAW SRM 51-40-02.
DURING PREFLIGHT FOUND LT 1 EMERGENCY EXIT LIGHT BATTERY OFF LOAD. LT 1 EMERGENCY BATTERY PACK REPACED PER AMM 33-51-07-2. TEST SATIS.
DURING DEPARTURE, ON GEAR RETRACTION. THE DOORS LIGHT REMAINED ILLUMINATED. COMPLIED WITH QRH & LIGHT WENT OUT. OPERATED GEAR DOORS WITH GROUND MAINTENANCE PANEL, DOORS OPEN NORMALLY. DURING CLOSING OPERATION, RT MAIN GEAR DOOR DOESN'T CLOSED. R & R THE RT MAIN GEAR TRUCK POSITIONER SHUTTLE VALVE IAW AMM 32-32-17-4. R & R THE GEAR DOOR, OPERATED GEAR SEQUENCE VALVE IAW AMM 32-32-05-4. R & R THE DOWNLOCK. OPERATED THE DOOR SEQUENCE VALVE IAW MM 32-32-07-4-0. R & R THE LOCK RELEASE INSTL MLG DOOR ACTUATOR ASSY. R & R INTERLOCK RELEASE ACTUATOR IAW AMM 32-35-06-4 R & R DOWNLOCK, OPERATED DOOR SEQUENCE VALVE IAW AMM 32-32-07-4. TESTED MAIN AND NOSE LDG SYSTEM 7 TIMES IAW AMM 32-32-05-4, AND 32-3
AFTER TAKEOFF AND GEAR RETRACTION, THE GEAR DOOR LIGHT STAYED ON. CYCLED GEAR, AND THE LIGHT EXTINGUISHED. REMOVED AND REPLACED MAIN GEAR UPLOCK OPERATED SEQUENCE VALVE IAW AMM 32-32-09-4. TWO HYRAULIC LINES ARE INOPERATIVE AND REPLACED. R & R THE MAIN GEAR SAFETY VALVE IAW 32-35-05-4, REPLACED THE FLEX HOSES ON THE RT MAIN GEAR UPLOCK OPERATED SEQUENCE VALVE IAW AMM 20-10-10-8 AND PERFORMED HYD SYSTEM BLEEDING AND CONTINUED TEST IAW AMM 32-32-09-4, AND AMM 32-35-05-4. NO LEAKS FOUND AND ALL TESTS ARE OK. COMPLIED WITH MAIN LDG RETRACTION/EXTENSION TESTED IAW AMM 32-32-00-5, ALL TESTED OK .
AFTER TAKEOFF, WHEN THE LANDING GEAR WAS RETRACTED, THE GEAR DOOR LIGHT STAYED ON WITH A GEAR DOORS EICAS MESSAGE. RECYCLED GEAR, AND THE INDICATIONS REMAINED. PERFORMED TROUBLESHOOTING IAW FIM 32-09 FAULT TREE 804, PSEU BITE PROCEDURE .NO FAULTS FOUND. REMOVED AND REPLACED THE RT MAIN LANDING GEAR DOOR ACTUATOR IAW AMM 32-32-12-4. OPS CHECKED GOOD.
L1 DOOR WILL NOT ARM. FOUND A SCREW ON FWD GIRT BAR END FITTING LOOSE. REALIGNED FITTING. TIGHTENED SCREW IAW AMM 52-11-25. OPERATED L1 DOOR ARMING MECHANISM MULTIPLE TIMES. OKAY FOR SERVICE.
HIGH SPEED REJECT FOR MAIN CARGO DOOR LIGHT AND SUBSEQUENT TAKE OFF CONFIGURATION EICAS AND HORN, MAX SPEED 110 KTS. FOUND ACTUATOR ARM BOLTS LOOSE ON FWD PRESSURE DOOR LOCK SWITCH. ADJUSTED THE SWITCH IAW AMM 52-72-00-5. PERFORMED MCD WARNING TEST IAW AMM 52-72-00-5. ALL TEST PASSED SEVERAL TIMES. OK FOR SERVICE.
DURING ENG START, THE LEFT ENGINE EGT REACHED 689 DEGREES USING RICH. ABORTED ENGINE START. FOLLOWED QRH.
DURING ENGINE START, THE RT ENGINE EGT REACHED 668 DEGREES USING RICH. ABORTED THE ENGINE START. FOLLOWED QRH. PERFORMED VISUAL INSPECTION OF L.P. TURBINE AND THE INTERNAL PART OF THE EXHAUST COLLECTOR IAW AMM 78-11-04/601 AND NO DAMAGE FOUND. ACFT OK FOR SERVICE.
DURING ENGINE START, LEFT ENGINE EGT REACHED 689 DEGREES USING RICH. ABORTED THE ENGINE START. FOLLOWED QRH. PERFORMED BOROSCOPE INSPECTION, HP, IP, AND LP TURBINES, AND COMBUSTION SECTION IAW AMM 72-00-00/601. NO LIMITING DEFECTS FOUND. AIRCRAFT OK FOR SERVICE RAN BOTH ENGINES AT IDLE IAW JRH FOR 5 MINUTES AND FOUND ALL PARAMETERS NORMAL. DURING STARTING SEQUENCE, PEAK EGT WAS APPROXIMATELY 350 DEG C ON BOTH ENGINES. PERFORMED TEST NR 13 AT TAKEOFF POWER IAW MM 71-00-00/501 AND FOUND ALL NR 1 ENGINE PARAMETERS IN GOOD RANGE. ACFT OK TO CONTINUE.
ARMING LEVER ON L1 DOOR STIFF AND HARD TO OPERATE. SYSTEM TEST OF THE L1 DOOR GIRT BAR MECHANISM C/OUT IAW AMM 52-11-25 REV117.0. TESTED GOOD.
PUNCTURE ON LT OTBD AFT FLAP LOWER SKIN AT APPROX 79 INCHES FROM OTBD EDGE OF FLAP, AND 4.5 INCHES FROM TRAILING EDGE. PERMANENT REPAIR CARRIED OUT IAW EA F-570-T0328366 WRI 57509181 WO 00066976.
VERTICAL SCRATCHES ON EXTERNAL SURFACE OF THE FUSELAGE SKIN AT BS 1395 - 1404.5, JUST BELOW STRINGER 4R. TWO SCRATCHES AT BS 1396 AND THREE AT BS 1404. REPAIRED IAW EA F-5330-T0328332 PART 1.
DELAMINATION FOUND ON SLAT NR 7 T/E WEDGE. REPAIRED IAW EA F-5750-T0328276 P1.
DELAMINATION FOUND ON SLAT NR 6 T/E WEDGE. REPAIRED IAW EA F-5750-T0328628 A P2.
NR 2 PYLON STIFFENER ATTACH BOLT SHEARED AT THE INBD SIDE PPS 185. TWO LOCK FASTENERS FOUND LOOSE. REPAIRED IAW EA F-5450-T0328352.
NR 2 PYLON STIFFENER ATTACH BOLT SHEARED AT INBD SIDE PPS 185. FOUND TWO LOCK FASTENERS LOOSE. REPAIRED IAW EA F-5450-T0328352.
NR 2 PYLON STIFFENER ATTACH BOLT SHEARED AT INB SIDE PPS 185. TWO LOCK FASTENERS FOUND LOOSE. REPAIRED IAW EA F-5450-T0328352.
CORROSION ON RT WING UPPER SKIN AT REAR SPAR WBL 103. CARRIED OUT EA F-5730-T0328363.
CORROSION ON LT WING UPPER SKIN AT REAR SPAR APPROX WBL 100. REPAIR CARRIED OUT IAW EA F-5730-T0328310
EXTERNAL POWER RECEPTACLE PAN, BS 418-430, STRINGERS 27-28R CRACKED. REPAIRED IAW EA F-5320-T0328191 REV NO POS P1.
SLIDE LIGHT, RT CREW DOOR INOPERATIVE. OPERATIONS CHECK ARM & DISARM, FEW TIMES LIGHT COMES ON EVERY TIME, ACFT OK FOR SERVICE IAW AMM 25-66-00-5. OPERATIONS CHECK ARM & DISARM FEW TIMES LIGHT COMES ON EVERY TIME. ACFT OK FOR SERVICE IAW AMM 25-66-00-5.
WHEN FLAPS 1 SELECTED, LE SLAT ASYMMETRY. COMPLIED WITH QRH, LANDING UNEVENTFUL. R & R NR 5 SLAT OTBD DRIVE ROTARY ACTUATOR IAW AMM 27-81-81-4. PERFORMED SEVERAL SLAT MOVEMENTS. ALL TEST PASSED. ACFT OK FOR SERVICE.
LEFT ENG BREAD BAND VIBRATION INDICATOR ENTERED & REMAINED IN AMBER BAND. CREW CONDUCTED COMPULSORY LT ENG SHUTDOWN IAW QRH. CREW REPORTED THAT THEY DIDN'T FEEL ANY VIBRATION. EICAS MX MSGS LT ENG BB VIB & LT ENG VIB BITE PRESENT, SUSPECTED INDICATION. R & R RED LT ENG AVM ACCELEROMETER IAW AMM 77-31-01-4. R & R RED LT ENG AVM SIGNAL CONDITIONER IAW MM 77-31-03-4. NEED TO PERFORM HIGH POWER RUN. PERFORMED AVM SYS OPERATIONAL TEST IAW AMM 77-31-00-5-0 AT 70 PERCENT N1. PERFORMED LT ENG VIBRATION SURVEY TEST 6 IAW AMM 71-00-00-5-3.
DOOR 1R EMER ESCAPE SLIDE ARMING MECHANISM IS NOT ARMING PROPERLY. HAD TO CYCLE DOOR FOLLOWED BY 4 ATTEMPTS POSITIONING THE ARMING HANDLE TO ARM BEFORE A SUCCESSFUL ARMING WAS ACHIEVED, REPEAT. PERFORMED R1 DOOR GIRT BAR MECHANISM ADJUSTMENT & TEST IAW AMM 52-11-25-5. UNDER INSPECTION FOUND DEBRIS IN GIRT BAR MECHANISM. CLEANED & GREASED GIRT BAR MECHANISM IAW AMM 12-21-18-3. PERFORMED SYS TEST OF GIRT BAR MECHANISM IAW AM 52-11-25-5, CHECKED GOOD.
ON RIGHT ENTRY DOOR, THE SLIDE LIGHT DOES NOT ILLUMINATE WHEN THE DOOR IS ARMED. RELAMPED IAW SMP, PERFORMED GIRT BAR PROXIMITY SWITCHES & MX PRACTICES IAW MM 25-66-11-02. OK FOR SERVICE.
UPON BLOCK IN FOUND R1 DOOR HAD SLIDE LIGHT NOT ILLUMINATED WHEN DOOR IS DISARMED. TROUBLESHOOTING PERFORMED IAW FIM 25-66 FAULT TREE 802. TARGETS CLEANED, SLIDE GIRT BAR TARGETS ADJUSTED IAW AMM 25-66-11-2. SLIDE ARM LIGHT OPERATION TESTED OK.
SLIDE LIGHT NOT ILLUMINATED WITH RT CREW ENTRY DOOR ARMED UPON LANDING. ADJUSTMENT TEST ON PROXIMITY SWITCH ON GIRT BAR RT DOOR.
SLIDE LIGHT NOT ILLUMINATED WITH RT CREW ENTRY DOOR ARMED UPON LANDING. ADJUSTMENT TEST ON PROXIMITY SWITCH ON GIRT BAR RT DOOR IAW AMM 25-66-11-2. TESTED SATISFACTORY.
DURING SERVICE CHECK, FOUND NEAR THE FWD LOWER EDGE OF 1L DOOR AN EMERGENCY LIGHT PLATE MISSING. CONNECTED WIRES TO EXIT LIGHT COMPLIED WITH EA F-3350-T0314504 P1.
R1 ENTRY DOOR DIFFICULT TO ARM. PERFORMED LUBRICATION OF FLOOR FITTINGS & BAR LOCKS IAW MM 25-66-01-644-055. INSPECTION CHECK PERFORMED IAW MM 25-66-10-202-039. ACFT OK FOR SERVICE.
UNCOMMAND RT RUDDER ON CLIMB OUT 11.3K FOR 1-3 SECONDS. AUTOPILOT STAYED CONNECTED. NO STATUS OR ADV MSG OR OVERHEAD LIGHT ON WITH HYD POWER ON. PERFORMED TROUBLE SHOOTING. TROUBLE SHOOTING FOUND ON RT RUDDER RATIO CHANGER MODULE, MODULE FAULT, FAULT BALL SET YELLOW. PERFORMED RESET OF FAULT BALL, PERFORMED BITE PROCEDURE OF RUDDER RATIO CHANGER MODULE & BITE PROCEDURE OF BOTH SAM ALL OK NO FAULT BALLS SET. DVI OF PINK13 CONNECTOR D705A SHOWS PIN BENT & PUSHED IN. PINK13 OF CONNECTOR D705A RE ENGAGED. CHECKED CONNECTORS OF RT SAM OK. CHECKED CIRCUIT BETWEEN RT SAM PINK13 & RT RRCM PIN D9 0 2 OHM OK. REINSTALLED RT SAM RT RRCM & ACM 2R. SCM 2R WAS REMOVED DUE TO ACCESS. ALL REQUIRED INSTALLATION TESTS PERFORMED, ALL OK. PERFORMED MCDP TEST 30 & 40 BOTH OK.
DURING SERVICE CHECK FOUND FWD EMER LIGHTS TEST SWITCH, ABOVE L1 DOOR, WILL NOT TEST. R & R IAW CHAPTER 20 SMP & WDM 33-51-12. DURING INSTALLATION FOUND BAD TERMINAL ON WIRE W3532-0035-22. TERMINAL REQUIRES REPLACEMENT. TEMPORARILY SLAVED WIRE TO SWITCH & PERFORMED EMER LIGHTS TEST IAW AMM 33-51-00-5. TEST SATISFACTORY. AWAITING NEW TERMINAL TO FINISH INSTALLATION. INSTALLED TERMINAL ON WIRE W3532-0035-22 IAW SWPM 20-30-15 AND WDM 33-51-12. PERFORMED EMER LIGHTS TEST IAW AMM 33-51-00-5. TEST SATISFACTORY. ACFT OK TO CONTINUE SERVICE.
EVIDENCE OF SEVERAL LIGHTNING STRIKES ON FWD RT NLG DOOR 714. NLG DOOR REPAIRED IAW SRM 52-80-02 & 51-70-03 PARA 5 REV 112.
NR 2 SLAT LOWER COVE ANGLE CORRODED BETWEEN AUXILIARY TRACK ATTACHMENTS. REPAIRED IAW 57-43-18 REV 30.
NUMBER 3 SLAT SHOWS SIGNS OF CORROSION ON LOWER AFT CHORD & UPPER SKIN. REPAIRED IAW EA F-5750-T0310894.
EVIDENCE OF SEVERAL LIGHTNING STRIKES ON LT NOSE GEAR DOOR 713. LIGHTNING STRIKES REPAIRED IAW SRM 52-80-02 REPAIR 4 & 51-70-03 PARA 5M REV 112.
APU DOOR SKIN DAMAGED ADJACENT TO DOOR 1 LATCH, NUMBERED 1 - 5 FWD TO AFT. REPAIR CUT OUT IAW EA F-5240-T0310700 REV PT 1.
APU DOOR SKIN DAMAGED ADJACENT TO THE DOOR LATCH 3 NUMBERED 1 - 5 FWD TO AFT. REPAIR CUT OUT IAW EA F-5240-T0310700 REV PT1 SATIS.
APU DOOR SKIN DAMAGED TO THE DOOR LATCH 5, NUMBERED 1 -5 FWD TO AFT. REPAIR CUT OUT IAW F-5240-T0310700 REV PT1.
IMPACT DAMAGE ON SHEAR PLATE AT MCD THRESHOLD BS 560. SHEAR PLATE REPLACED.
APU DOOR SKIN DAMAGED ADJACENT TO THE DOOR LATCH 2, NUMBERED 1 - 5 FWD TO AFT. REPAIR CUT OUT IAW EA F-5240-T0310700 REV PT 1 SATIS.
NUMBER 1 SLAT HAS QTY 4 DENTS IN THE TE WEDGE TOP SKIN. REPAIRED IAW SRM 51-70-10 & 57-43-02.
NUMBER 5 SLAT HAS QTY 7 DENTS IN THE TE WEDGE TOP SKIN REPAIRED IAW SRM 57-43-02 & 51-70-10.
UPPER FUSELAGE BS 1320 - 1350 STRINGER 4R. SCRIBE GOUGE MARKS EVIDENT ON FUSELAGE SKIN BELOW LAP JOINT REPAIRED IAW SRM 53-00-01, SB757-53A0092 & EA F-5300-T0310858.
UPPER FUSELAGE BS 1390 - 1410 STRINGER 4R. SCRIBE & GOUGE MARKS EVIDENT ON FUSELAGE SKIN BELOW LAP JOINT. REPAIRED IAW SRM 53-00-01 & SB 757-53A0092.
MULTIPLE LIGHTNING STRIKES ON LOWER SKIN PANEL FROM FWD PRESS BULKHEAD BS 200 TO FWD AVIONICS BAY DOOR. REPAIR CARRIED OUT IAW EA F-5300-T0310667.
SEVERAL LIGHTNING STRIKES FOUND ON FWD AVIONICS BAY DOOR SKIN 113AL. REPAIRED IAW EA F5240-T0310668.
LEFT THS TIP BONDING POINT BRACKET FOR LT ELEVATOR FOUND IN POOR CONDITION. REPAIR CARRIED OUT TO LT THA TIP UPPER BEAM IAW EA F-5500-T0310741.
DURING AGEING INSPECTION, REPAIR INSPECTED IAW EO-5100-7-5001 PT 1. REPAIR AT CREASE BEAM STATION 1190 STRINGER 17L FOUND NOT TO CONFORM TO SRM 51-70-12 FIG 1. OUTER ANGLE FOUND NOT BE INCORRECT GAUGE & MID ANGLE FOUND TO HAVE MECHANICAL DAMAGE MID & OUTER ANGLE REPLACED AT OPEN FASTENER HOLE LOCATIONS 1/64 OVERSIZE FASTENERS INSTALLED IAW SRM 51-70-02 FIG 1 TABLE 1.
NUMBER 5 SLAT CORROSION ON INBD CLOSURE ANGLE REPAIRED IAW EA F-5750-T0310708.
NUMBER 6 SLAT INBD CLOSURE ANGLE CORRODED. REPAIRED IAW EA F-5750-T0310704.
LEFT INBD MAIN FLAP TE HONEYCOMB TOP SKIN PUNCTURE REPAIR IAW SRM 57-53-01 & SRM 51-70-07.
DVI OF THE ENG 2 PYLON MOUNT BULKHEAD FITTING REVEALS NICK DAMAGE EVIDENT TO THE LOWER FLANGE OTBD SIDE AFT EDGE. REPAIRED IAW SRM 51-10-02 & EA F-5440-T0310190.
SLAT NR 5 ON AFT FACE SPAN WISE CHORD CORRODED. SPAN WISE CHORD PN 114N3011-1 REPLACED.
LEFT OTBD FLAP CORROSION ON INTERNAL FRONT SPAR LOWER ANGLE CORROSION REMOVED IAW EA F-5750-T0310561.
RIGHT OTBD MAIN FLAP CORROSION ON FWD SPAR INTERNAL LOWER FLANGE. REPAIR IAW EA F-5750-T0310699.
RIGHT WING OTBD FLAP STRESS PANEL NUTPLATE CORROSION IN SEVERAL PLACES. CORROSION REPAIRED IAW EA F-5750-T0310492.
SLAT NR 1 CORROSION ON NOSE SKIN LOWER SURFACE SLAT. REPAIRED IAW EA F-5750-TO310402.
SLAT NR 7 CORROSION ON AFT LOWER CHORD. REPAIRED IAW CMM 57-43-28.
DURING AGEING INSPECTION EF-5100-7-5001PT1 FOUND DENT STILL APPARENT BELOW DOUBLER REPAIR IAW EA F-5330-117347. EXISTING DOUBLER REPAIR REMOVED & SKIN DENT DRESSED OUT IAW 5300. NEW DOUBLER FABRICATED & INSTALLED REPAIR AREA NOW CONFORMS TO EA F-5330-117347
MCD SEAT TRACK AT BS 580 LBL 45.50 UPPER FLANGE IS CRACKED & FASTENER PULLED.
MCD MODIFICATION FLOORBEAM COUPLER SPLICE FITTING AT BS 580 LBL 45.50 UPPER FLANGE CRACKED.
NDT REPORT DELAMINATION OF LT ELEVATOR LOWER SKIN LE APPROX 1.5 IN X 0.5 IN. INVESTIGATION CARRIED OUT ON SUITABLE REPAIRS IAW SRM 55-20-01 REPAIR 1 FIG 201 TABLE 2 350 CURE REPAIR NOT AVAILABLE AT THIS LOCATION , ELEVATOR REPLACED.
AFTER CLOSING LT ENTRY DOOR, THE ESCAPE SLIDE GIRT BAR ENGAGEMENT LIGHT DID NOT ILLUMINATE. FOUND GIRT BAR OUT OF PLACE IN LT ENTRY DOOR. GIRT BAR INSTALLED, CHECKED FOR OPERATION & FOUND OK IAW AMM 25-60.
ESCAPE SLIDE ARMED LIGHT OVER L1 IS BURNED OUT. RELEASED FOR SERVICE IAW MEL 25-66-05-A ESCAPE SLIDE GIRT BAR ENGAGEMENT LIGHTS INOPERATIVE. ENGAGEMENT OF SLIDE L1 HAS BEEN VISUALLY VERIFIED. AC OK FOR SERVICE BSL R BULBS CHECKED OK. FOUND BULB SUPPORT SEPARATED FROM THE BASE. BASE FOLD INSIDE THE PANEL, WILL NEED TO OPEN THE PANEL TO CHECK IF IT'S POSSIBLE TO REASSEMBLE. HAVE TO CHECK IF THE UPDATED PART IS THE FULL ASSEMBLY. R & R THE SOCKET IAW AMM 25-66-11-2 FOUND LIGHT WORKING INTERMITTENTLY, STILL NEEDS MORE TROUBLESHOOTING. CLEANED GIRT BAR PROXIMITY SWITCHES, PERFORMED ADJ TEST IAW MM 25-66-11-2, OPERATIONS CHECKED OK.
RIGHT AILERON OTBD PCA INPUT ROD NUT MISSING. INSTALLED NUT IAW AMM 27-11-20.
DENT ON LOWER FUSELAGE BS 1681-1696 BETWEEN S27-29L. FOUND OUT OF LIMITS IAW SRM 53-00-01, FIG 101. TRIMMED OUT DAMAGE AREA IAW SRM 51-10-02 & EA F-5330-T0301824, REV PS PT 1, REPAIRED IAW EA F-5330-T0301824, REV PS PT 1.
DURING SVC, FOUND LT SLIDE EMERGENCY LIGHT INOPERATIVE. BULB REPLACED IAW AMM 33-51-06-2-1 REV 103.2. OP TESTED GOOD IAW AMM 33-51-00-0, REV 103.2.
IN CLIMB, PASSING FL 300 AT CLIMB POWER EICAS MSG "LT ENGINE OVERHEAT" COMPLIED WITH QRH. ENGINE WAS AT IDLE WITH LIGHT REMAINING ON. IN PROCESS OF ABOUT TO SHUTDOWN ENGINE LIGHT EXTINGUISHED. LT ENGINE REMAINED AT IDLE UNTIL TAXI-IN AND SHUTDOWN. LEFT ENGINE HP2 OUTLET DUCT ASSY AND THE HP6 DUCT ASSY WAS REPLACED AS PER AMM 36-11-01-4-1. OPS CHECK OF THE AIR SUPPLY DISTRIBUTION SYSTEM WAS PERFORMED AS PER AMM 36-11-00-5 WITH ALL OPS NORMAL. ENGINE RUN WAS CONDUCTED, ALL INDICATIONS NORMAL.
RT DOOR EXTERNAL EMERGENCY LIGHT INOPERATIVE. BULB REPLACED IAW AMM 33-51-06-2-1. LIGHT TESTED SATISFACTORY.
AFTER PUSH BACK COMPLETE LT FWD ENTRY DOOR EICAS ILLUMINATED. RELEASED FOR SERVICE IAW MEL: 52-71-01
UPON ARRIVAL TO ACFT, FOUND THE L1 DOOR BLOWN. THE L1 EMERGENCY SLIDE HANGING OUT. R & R L1 DOOR ESCAPE SLIDE. REF AMM 25-66-01-4. ACFT OK FOR SERVICE.
UPON REMOVAL OF APU INLET STRAP, FOUND SKIN CORRODED STA 1780, STR 5-6 RIGHT. REMOVED SKIN SECTION IAW SRM 51-40-2. LOCATED, DRILLED, AND DEBURRED NEW SKIN IAW SRM 51-40-5. INSTALLED NEW SKIN IAW SRM 51-40-2, REV 103.
DURING FLIGHT, RECEIVED A "L ENG BLEED OFF" EICAS. SUSPECT PRSOV AND SENSOR.
UPON ARRIVAL OF ACFT, CREW INADVERTINLY DEPLOYED L1 DOOR ASSIST BOTTLE AND L1 DOOR EVACTUATION SLIDE BY MISTAKE. REPLACED L1 DOOR ESCAPE SLIDE IN REF AMM 25-66-01-4. ALSO INSTALLED NEW GIRT BAR PROXIMITY SWITCH MAGNET IAW AMM 25-66-11-2. OPS CHECK OK AT THIS TIME. DOOR SLIDE ARMS AND DISARMS NORMALLY WITH ASSOCIATED ARM LIGHT ABOVE DOOR. INSTALLED NEW DOOR SLIDE COVER PN 416N2100-700D IAW AMM 25-66-01-4. DOOR SLIDE COVER WAS LOANED TO US FROM ORDER NR 312815.
ON CLIMBOUT PASSING 30000 FT, RECEIVED LT ENG OVERHEAT, PULLED THRUST LEVER BACK AND WARNING EXTINGUISHED. INSPECTED ENG FOR EVIDENCE OF DUCT LEAKS. FOUND FOIL WRAP MISSING FROM IP DUCT IN STRUT. DUCT CLAMP WAS NOT TIGHT. TIGHTENED CLAMP NEEDS ENG RUN. CLAMP AND SEAL ORDERED AS A PRECAUTION. REPLACED SEAL AND CLAMP ON FLEXIBLE JOINT OF HP 2 PORT JUST ABOVE ENG STRUT FIRE WALL. RE-FOILED CLAMP AND ENGINE RUN TO TO POWER FOR 5 MIN.S WITH, NO EVIDENCE OF AIR LEAKS. OK FOR SERVICE. REF : SERVICE LETTER 757-SL-36-11-A.
DURING CLIMB PASSING FL180, EICAS MESSAGE DISPLAYS L ENG OVHT ALL OTHER ENG INDICATIONS WERE NORMAL. RETARDED L THROTTLE AND TURNED OFF L BLEED AIR. AFTER APPROXIMATELY 2 MIN THE EICAS MESSAGE WENT AWAY. DECLARED EMERGENCY AND LANDED WITH L ENG AT IDLE. COMPLIED WITH QRH. REPLACED HP2 DUCT ASSY AS PER MM36-11-01-4. ALL WORK COMPLETED BY IASA MX.
DURING CLIMB PASSING FL180 EICAS MESSAGE DISPLAYS L ENG OVHT ALL OTHER ENG INDICATIONS WERE NORMAL. RETARDED L THROTTLE AND TURNED OFF L BLEED AIR. AFTER APPROXIMATELY 2 MIN THE EICAS MESSAGE WENT AWAY. DECLARED EMERGENCY AND LANDED WITH L ENG AT IDLE. COMPLIED WITH QRH. REPLACED HP2 DUCT ASSY AS PER MM36-11-01-4.
CORROSION FOUND ON FLOORBEAM AT STA 365, RBL 3 TO RBL 51. EVALUATE AND RECTIFY. REPAIR CARRIED OUT ON FLOORBEAM UPPER CHORD AT STATION 365 BETWEEN RBL 3 AND RBL 51 IN ACCORDANCE WITH B 757-200 SRM 53-00-51 FIGURE 201 REPAIR 1, REVISION 93. REPAIR IS CLASSIFIED AS MAJOR AS PER GMM 6-02-100 CRITERIA.
UNDOCUMENTED BLEND REPAIR FOUND ON THE AFT SIDE OF THE LT WING REAR SPAR WEB AT RSS 183. EVALUATE AND RECTIFY. LEFT WING REAR SPAR WEB CORROSION BLEND REPAIR CARRIED OUT IAW EA F-5710-118827 DATED MAY 24 2008. REPAIR IS CLASSIFIED AS MAJOR PER GMM 6-02-100.
SURFACE CORROSION FOUND ON PYLON NUMBER TWO LEFT SIDE INNER SKIN FORWARD OF ACCESS PANEL 443LL, PPS 126 TO PPS 181. EVALUATE AND RECTIFY. REPLACED LEFT SIDE INNER SKIN FORWARD OF ACCESS PANEL 443LL OF PYLON NUMBER TWO IN ACCORDANCE WITH BOEING DRAWING 311N5046, BOEING DRAWING 311N5002 AND B757-200 SRM 51-10-02 REV 93. REPAIR CLASSIFIED AS MAJOR AS PER FEDEX GMM 6-02-100 CRITERIA.
SURFACE CORROSION FOUND ON PYLON NUMBER ONE LEFT SIDE INNER SKIN AFT OF ACCESS PANEL 433CL. EVALUATE AND RECTIFY. REPLACED LEFT SIDE INNER SKIN AFT OF ACCESS PANEL 433CL OF PYLON NUMBER ONE IN ACCORDANCE WITH BOEING DRAWING 311N5046, BOEING DRAWING 311N5002, AND B757-200 SRM 51-10-02 REV 93. REPAIR CLASSIFIED AS MAJOR PER FEDEX GMM 6-02-100 CRITERIA.
PYLON NUMBER ONE RIGHT SIDE SKIN CUTOUT AT ACCESS PANEL 433GR FOUND CORROSION, FROM PPS 100 TO PPS 120. EVALUATE AND RECTIFY. REPLACED PYLON NUMBER ONE SKIN CUTOUT PANEL 433GR IN ACCORDANCE WITH BOEING DRAWING 311N5002 AND SRM 51-10-02 REV 93.
PYLON NUMBER TWO RIGHT SIDE STRUT SKIN CUTOUT AT ACCESS PANEL 443AR FOUND CORROSION, FROM PPS100 TO PPS126. EVALUATE AND RECTIFY. REPLACED PYLON NUMBER TWO STRUT SKIN CUTOUT PANEL 443AR IN ACCORDANCE WITH BOEING DRAWING 311N5002 ID0014, SRM 51-10-02 REV 93. REPAIR CLASSIFIED AS MAJOR PER FEDEX GMM 6-2-100 CRITERIA.
SURFACE CORROSION ON PYLON NUMBER TWO LEFT SIDE PANEL INNER SKIN FORWARD OF ACCESS PANEL 443HL, PPS 124 TO PPS 200. EVALUATE AND RECTIFY. PYLON NUMBER TWO LEFT SIDE SKIN PANEL LOCATED FORWARD OF ACCESS PANEL 443HL REPLACED IN ACCORDANCE WITH BOEING DRAWING 311N5046 SHEET 2, 311N5002 AND B757-200 SRM 51-10-02 REVISION 93. REPAIR CLASSIFIED AS MAJOR AS PEF FEDEX GMM 6-2-100.
CORROSION ON PYLON NUMBER ONE LT INNER STRUT SKIN NEAR ACCESS PANEL 433BL CUTOUT, PPS 124.76. EVALUATE AND RECTIFY. REPLACED PYLON NUMBER ONE LT INNER STRUT SKIN NEAR ACCESS PANEL 433BL CUTOUT IN ACCORDANCE WITH BOEING DRAWING 311N5002 ID 0013 REVISION E, 311N5046 ID 00002 REVISION A AND B757-200 SRM 51-10-02 REVISION 93. REPAIR CLASSIFIED AS MAJOR PER FEDEX GMM 6-2-100.
CORROSION FOUND ON PYLON NUMBER ONE INNER STRUT SKIN NEAR ACCESS PANEL 433JR CUTOUT, PPS 162.8. EVALUATE AND RECTIFY. PYLON NUMBER ONE RIGHT SIDE PANEL SKIN NEAR ACCESS PANEL 433JR CUTOUT REPLACED IN ACCORDANCE WITH BOEING DRAWING 311N5002 ID 0014 REVISION E, 311N5046 ID0002 REVISION A AND B757-200 SRM 51-10-02 REVISION 93. REPAIR CLASSIFIED AS MAJOR PER FEDEX GMM 6-2-100.
PYLON NUMBER TWO LEFT FORWARD STRUT SKIN CUT OUT AT ACCESS PANEL 443GL FOUND CORROSION, FROM PPS 100 TO PPS 126. EVALUATE AND RECTIFY. REPLACED PYLON NUMBER TWO STRUT SKIN CUT OUT PANEL 443GL IN ACCORDANCE WITH BOEING DRAWING 311N5002 AND SRM 51-10-02 REVISION 93. REPAIR CLASSIFIED AS MAJOR AS PER FEDEX GMM 6-2-100 CRITERIA.
PYLON NUMBER TWO INNER SKIN OF ACCESS PANEL 443BR FOUND WITH SURFACE CORROSION, FROM PPS 126 TO PPS 151. EVALUATE AND RECTIFY. PYLON NUMBER TWO INNER SKIN OF ACCESS PANEL 443BR, REPAIRED BY AERO MECHANICAL INDUSTRIES INC. (AMII) IN ACCORDANCE WITH EA NR F-5450-118721. PYLON STRUT SKIN SIDE PANEL ASSEMBLY INSTALLED IN ACCORDANCE WITH BOEING DRAWING NUMBER 311N5046 SHEET 2, BOEING DRAWING NUMBER 311N5002 AND BOEING B757-200 SRM 51-10-02 REVISION 93. REPAIR CLASSIFIED AS MAJOR AS PER FEDEX GMM 6-2-100.
PYLON NUMBER TWO UPPER AFT WING TO STRUT FAIRING SUPPORT BRACKET CRACKED, ADJACENT TO PPS 174.3. EVALUATE AND RECTIFY. REPLACED PYLON NUMBER TWO UPPER AFT WING TO STRUT FAIRING SUPPORT BRACKET IN ACCORDANCE WITH EA NR F-5450-118812 AND B757-200 SRM 51-00-02 REVISION 93. REPAIR CLASSIFIED AS MINOR AS PER FEDEX GMM 6-2-100.
DENT FOUND ON LOWER FUSELAGE FRAME AT STA 480 BETWEEN STRINGER S-26L AND S-27L. EVALUATE AND REPAIR AS REQUIRED. REPAIR CARRIED OUT AS PER EA 757-5332-00-F0087 IN THE PTF MOD CARD NR 118250068DSSR02. REPAIR CLASSIFIED AS MAJOR AS PER FEDEX GMM 6-2-100 CRITERIA.
CORROSION ON L2 DOOR AFT FRAME WEB SURFACE BELOW HANDLE. TO REMOVE CORROSION AS PER SRM. REPAIR ON L2 DOOR AFT FRAME WEB SURFACE BELOW HANDLE WAS CARRIED OUT AS PER FEDEX EA NR F-5210-117342. REPAIR CLASSIFIED AS MINOR PER GMM 6-2-100 CRITERIA.
SCRIBE MARK DEPTH OF 0.0053 INCH, LENGTH OF 1.0 INCH FOUND ON BUTT JOINT AT STA 1620, 10 INCHES ABOVE STRINGER 14L. EVALUATE AND RECTIFY. REPAIRED BUTT JOINT AT STATION 1620 IN ACCORDANCE WITH FEDEX ENGINEERING AUTHORIZATION F-5310-117340. REPAIR CLASSIFIED AS MINOR GMM 6-2-100 CRITERIA.
PYLON NUMBER ONE RIGHT FORWARD SKIN FOUND DENT. EVALUATE AND RECTIFY. REPLACED PYLON NUMBER ONE RIGHT FORWARD SKIN IN ACCORDANCE WITH B757- 200, SRM 51-10-02 AND BOEING DRAWING NUMBER 311N5002. REPAIR CLASSIFIED AS MAJOR AS PER FEDEX GMM 6-2-100 CRITERIA.
CRACK ON INNER PERFORATED SKIN OF OUTER DUCT ASSEMBLY AT THREE O'CLOCK SIDE STRUT LOCATION. TO EVALUATE AND RECTIFY. REPAIR CRACK ON INNER PERFORATED SKIN OF OUTER DUCT ASSEMBLY AT THREE O'CLOCK SIDE STRUT LOCATION. A NEW REPAIR DOUBLER WAS FABRICATED AND INSTALLED IN ACCORDANCE WITH THE TECHNICAL VARIANCE (ROLLS ROYCE) APPROVAL EASA DOA NR EASA 215.035. REPAIR CLASSIFIED AS MAJOR AS PER GMM 6-02-100 CRITERIA.
PYLON NR 1 SKIN CUTOUT AT ACCESS PANEL 433AL FOUND CORROSION. TO EVALUATE AND RECTIFY, REPLACED SKIN CUTOUT OF ACCESS PANEL IAW SRM 51-10-02 AND DRAWING 311N5002. REPAIRED CLASSIFIED AS MAJOR PER GMM 6-2-100 CRITERIA.
CORROSION FOUND ON R4 DOOR SCUFF PLATE SUPPORT BRACKET AT STA 1656, STA 1678, RBL 66. INSTALLED NEW SUPPORT BRACKET AT STA 1656, STA 1678 RBL 66 IN ACCORDANCE WITH B757 SRM 51-40-02 REV 93. REPAIRED CLASSIFIED AS MINOR PER FEDEX GMM 6-02-100.
CORROSION ON CREASE BEAM INBOARD CHORD AT BS 1280, S-17R. REPLACED THE CORRODED CREASE BEAM INBOARD CHORD, BS 1280, S-17R IN ACCORDANCE WITH FEDEX ENGINEERING AUTHORIZATION NR F-5310-117339 DATED JANUARY 25, 2008. REPAIR CLASSIFIED AS MINOR AS PER GMM 6-2-100.
CORROSION ON SEAT TRACK AT STA 1266, STA 1280, RBL 24. SEAT TRACK AT STA 1266 TO STA 1280, RBL 24 REPLACED NEW TRACK AS PER B757-200 SRM 51-10-02 REV 93. REPAIR CLASSIFIED AS MINOR PER GMM 6-2-100 CRITERIA.
EXISTING REPAIR, SKIN EXTERNAL DOUBLER, STA 1681, STRINGER S-15L TO EVALUATE EXISTING REPAIR. EXISTING REPAIR FOUND NOT IAW SRM APPLICABILITY. SKIN EXTERNAL DOUBLER REPLACED. R & R DOUBLER IAW EA F-5330-117347. REPAIR A CATEGORY B REPAIR AS DEFINED IN SRM 51-00-06, REQUIRING SUPPLEMENTAL INSPECTION IN ADDITION TO THOSE ALREADY SPECIFIED IN THE MPD. SUPPLEMENTAL INSPECTION ARE TO BEGIN WHEN THE AIRFRAME ACCUMULATES 34,500 FLIGHT CYCLES WITH REPEAT INSPECTIONS EVERY 3,000 FLT CYCLES. THE SKIN PANEL IS TO BE INSPECTED USING LFEC (PER B757 NDT 53-00-06, PART 6) ALONG THE PERIPHERAL FASTENER ROWS THROUGH THE EXTERNAL DOUBLER. REPAIR IS CLASSIFIED MAJOR AS PER GMM 6-2-100 CRITERIA.
EXISTING REPAIR FOUND IN AFT CARGO FLOORBOARD STRINGER L10.45, STA 1320-1340, TO EVALUATE EXISTING REPAIR. EXISTING REPAIR FOUND NOT IAW B757-200 SRM 51-70-11 FIG 1 DETAIL I, II. AFT CARGO FLOORBOARD STRINGER REPLACED IAW B757-200 SRM 51-10-02 REV 93. REPAIR IS CLASSIFIED AS MINOR PER GMM 6-2-100 CRITERIA.
EXISTING REPAIR FOUND IN AFT CARGO FLOORBOARD STRINGER L16.10, STA 1320-1340, TO EVALUATE EXISTING REPAIR. EXISTING REPAIR FOUND NOT IAW B757-200 SRM 51-70-11 FIG 1 DETAIL I, II. AFT CARGO FLOORBOARD STRINGER REPLACED IAW B757-200 SRM 51-10-02 REV 93. REPAIR IS CLASSIFIED AS MINOR PER GMM 6-2-100 CRITERIA.
EXISTING REPAIR FOUND IN AFT CARGO FLOORBOARD STRINGER L7.55, STA 1320-1340, TO EVALUATE EXISTING REPAIR. EXISTING REPAIR FOUND NOT IAW B757-200 SRM 51-70-11 FIG 1 DETAIL I, II. AFT CARGO FLOORBOARD STRINGER REPLACED IAW B757-200 SRM 51-10-02 REV 93. REPAIR IS CLASSIFIED AS MINOR PER GMM 6-2-100 CRITERIA.
EXISTING REPAIR FOUND IN AFT CARGO FLOORBOARD STRINGER L16.10, STA 1300 TO EVALUATE EXISTING REPAIR. EXISTING REPAIR FOUND NOT IAW B757-200 SRM 51-70-11 FIG 1, DETAIL I, II. AFT CARGO FLOORBOARD STRINGER REPLACED IAW B757-200, SRM 51-10-02 REV 93. REPAIR IS CLASSIFIED AS MINOR PER GMM 6-02-100 CRITERIA.
EXISTING REPAIR FOUND IN AFT CARGO FLOORBOARD STRINGER L10.45, STA 1280-1300, TO EVALUATE EXISTING REPAIR. EXISTING REPAIR FOUND NOT IAW B757-200 SRM 51-70-11, FIG 1 DETAIL I, II. AFT CARGO FLOORBOARD STRINGER L10.45 REPLACED IAW B757-200 SRM 51-10-02 REV 93. REPAIR IS CLASSIFIED AS MINOR PER GMM 6-02-100 CRITERIA.
EXISTING REPAIR FOUND IN AFT CARGO FLOORBOARD STRINGER L7.55, STA 1280-1300, TO EVALUATE EXISTING REPAIR. EXISTING REPAIR FOUND NOT IAW B757-200 SRM 51-70-11 FIG 1, DETAIL I, II. AFT CARGO FLOORBOARD STRINGER L7.55, REPLACED IAW B757-200 SRM 51-10-02 REV 93. REPAIR IS CLASSIFIED AS MINOR PER GMM 6-2-100 CRITERIA.
EXISTING REPAIR FOUND IN AFT CARGO FLOORBOARD STRINGER R7.55, STA 1320-1340. TO EVALUATE EXISTING REPAIR. EXISTING REPAIR FOUND NOT IAW B757-200 SRM 51-70-11 FIG 1 DETAIL I, II REV.93. AFT CARGO FLOORBOARD STRINGER AT R7.55, FROM STA 1200 TO STA 1343.5, REPLACED IAW B757-200 SRM 51-10-02 REV 93.
RT WING INBD SLAT NR 6 HAS HEAVY CORROSION JUST BELOW PANEL 612GB. REPLACED OUTBOARD LOWER ANGLE IAW SRM 51-10-02 REV 93. REPAIR IS CLASSIFIED AS MAJOR PER GMM 6-2-100 CRITERIA.
DEEP DENT PROTRUDED OUTWARD AT LT FWD EXT FUSELAGE ON STA 335, S-23L. EXTERNAL REPAIR CARRIED OUT ON LT FUSELAGE AT STA 335, S-23L IAW B757-200 SRM 53-00-01 REV 93 FIG 201 REPAIR 3. REPAIR IS CLASSIFIED AS MAJOR PER GMM 6-2-100 CRITERIA.
EXISTING REPAIR FOUND IN AFT CARGO FLOORBOARD STRINGER L2.90 FROM STA 1320 TO 1340 TO EVALUATE EXISTING REPAIR. EXISTING REPAIR FOUND NOT IAW B757 SRM 51-70-11 FIG 1 DETAIL I, II STRINGER L2.90 FROM STA 1320 TO STA 1340. REPLACED IAW B757 SRM 51-10-02 REV 93. REPAIR IS CLASSIFIED AS MINOR PER GMM 6-2-100 CRITERIA.
AFT CARGO FS 1400-1420 R.1610 HAS CORROSION ON FLOOR NUT PLATE STRIPS 3 PLACES, MARKED. CORROSION REMOVED FROM AFT CARGO FLOOR NUT PLATE STRIPS FROM STA 1400 TO STA 1420 IAW B757 SRM 51-10-02 REV 93. DEFECT FOUND EXCEED ALLOWABLE LIMIT PER B757 SRM 53-00-53 REV 93, DAMAGE 1 FIG 101 DETAIL V. STRINGER R16.10 FROM STA 1400 TO STA 1420 REPLACED IAW B757 SRM 51-10-02 REV 93. REPAIR IS CLASSIFIED AS MINOR PER GMM 6-2-100 CRITERIA.
FOUND CORROSION ON INTERCOSTAL FROM STA 1300 TO STA 1320, RBL 21. REPLACED IAW SRM 51-10-02 REV.93 PER EAR P337-24137-C0045. REPAIR IS CLASSIFIED AS MAJOR PER GMM 6-2-100.
CORROSION FOUND ON FLOORBOARD U-CHANNEL FROM STA 1700 TO STA 1718, BL 0. SUPPORT REPLACED IAW SRM 51-10-02 REV.93 AS PER EAR P337-24137-C0013. REPAIR IS CLASSIFIED AS MAJOR PER GMM 6-2-100.
CORROSION FOUND ON CLIP AT STA 1520, S-15R. CLIP REPLACED IAW B757 SRM 51-10-02 REV 93 AND STA ENG EAR NR P337-24137-C0012. REPAIR IS CLASSIFIED AS MINOR PER GMM 6-2-100 CRITERIA.
CORROSION FOUND ON ATTACH FITTING AT STA 1540, S-15R. CLIP REPLACED IAW B757 SRM 51-10-02 REV 93 AS PER STA ENG EAR P337-24137-C0016. REPAIR IS CLASSIFIED AS MINOR PER GMM 6-2-100 CRITERIA.
CORROSION ON FLOORBEAM AT STA 1280, RBL6, RBL10, RBL14. CORROSION FOUND EXCEED LIMITS IN SRM 53-00-51 FIG 101. REPAIR CARRIED OUT IAW SRM 53-00-51, REPAIR 3, FIG. 201. REPAIR CLASSIFIED AS MAJOR PER GMM 6-2-100.
EXISTING REPAIR FOUND IN AFT CARGO FLOORBOARD STRINGER L16.10, STA 1460-1480, TO EVALUATE EXISTING REPAIR. EXISTING REPAIR FOUND NOT IAW B757 SRM 51-70-11 FIG 1 DETAIL I, II. STRINGER L16.10 FROM STA 1460 TO STA 1480 REPLACED IAW B757 SRM 51-10-02 REV 93. REPAIR IS CLASSIFIED AS MINOR PER GMM 6-2-100 CRITERIA.
EXISTING REPAIR FOUND IN AFT CARGO FLOORBOARD STRINGER R10.45, STA 1320-1340, TO EVALUATE EXISTING REPAIR. EXISTING REPAIR FOUND NOT IAW B757-200 SRM 51-70-11 FIG 1 DETAIL I, II. AFT CARGO FLOORBOARD STRINGER R.10.45 REPLACED IAW B757-200 SRM 51-10-02 REV 93. REPAIR IS CLASSIFIED AS MINOR PER GMM 6-2-100 CRITERIA.
EXISTING REPAIR FOUND IN AFT CARGO FLOORBOARD STRINGER L2.90, STA 1400-1420. TO EVALUATE EXISTING REPAIR. TO EVALUATE EXISTING REPAIR. EXISTING REPAIR FOUND NOT IAW SRM 51-70-11 FIG 1 DETAIL I, II. AFT CARGO FLOORBOARD STRINGER L2.90, REPLACED IAW SRM 51-10-02 REV.93. REPAIR IS CLASSIFIED AS MINOR PER GMM 6-2-100 CRITERIA.
EXISTING REPAIR FOUND IN AFT CARGO FLOORBOARD STRINGER R10.45, STA 1420-1440 TO EVALUATE EXISTING REPAIR. EXISTING REPAIR FOUND NOT IAW B757-200 SRM 51-70-11 FIG 1, DETAIL I, II. AFT CARGO FLOORBOARD STRINGER R10.45 REPLACED IAW B757-200 SRM 51-10-02 REV 93. REPAIR IS CLASSIFIED AS MINOR PER GMM 6-2-100 CRITERIA.
EXISTING REPAIR FOUND IN AFT CARGO FLOOR BOARD STRUCTURE L7.55, STA 1460-1480, TO EVALUATE EXISTING REPAIR. EXISTING REPAIR FOUND NOT IAW B757-200 SRM 51-70-11 FIG 1 DETAIL I, II REV 83 STRINGER L7.55, STA 1460-1480. REPLACED IAW B757-200, SRM 51-10-02 REV 93. REPAIR IS CLASSIFIED AS MINOR PER GMM 6-2-100 CRITERIA.
EXISTING REPAIR FOUND AT CARGO FLOORBOARD STRINGER R16.10, STA 1320-1340. TO EVALUATE EXISTING REPAIR. EXISTING REPAIR FOUND NOT IAW B757 SRM 51-70-11 FIG 1 DETAIL I, II STRINGER R16.10. REPLACED IAW B757 SRM 51-10-02 REV 93. REPAIR IS CLASSIFIED AS MINOR PER GMM 6-2-100 CRITERIA.
EXISTING REPAIR FOUND IN AFT CARGO FLOOR BOARD STRINGER R7.55, STA 1260-1280. TO EVALUATE EXISTING REPAIR. EXISTING REPAIR FOUND NOT IAW B757 SRM 51-70-11 FIG 1 DETAIL I, II STRINGER R7.55. REPLACED IAW B757 SRM 51-10-02 REV 93. REPAIR IS CLASSIFIED AS MINOR PER GMM 6-2-100 CRITERIA.
EXISTING REPAIR FOUND IN AFT CARGO FLOORBOARD STRINGER L10.45, STA 1460-1480, TO EVALUATE EXISTING REPAIR. EXISTING REPAIR FOUND NOT IAW B757 SRM 51-70-11 FIG 1, DETAIL I, II STRINGER L10.45. REPLACED IAW B757 SRM 51-10-02 REV 93. REPAIR IS CLASSIFIED AS MINOR PER GMM 6-2-100 CRITERIA.
EXISTING REPAIR FOUND IN AFT CARGO FLOORBOARD STRINGER R2.90, STA 1460-1480. TO EVALUATE EXISTING REPAIR. EXISTING REPAIR FOUND NOT IAW B757 SRM 51-70-11 FIG 1 DETAIL I, II, STRINGER R.290 FROM STA 1460 TO STA 1480 REPLACED IAW B757 SRM 51-10-02 REV 93. REPAIR IS CLASSIFIED AS MINOR PER GMM 6-2-100 CRITERIA.
EXISTING REPAIR FOUND IN AFT CARGO FLOORBOARD STRINGER R.755, STA 1460-1480. TO EVALUATE EXISTING REPAIR. EXISTING REPAIR FOUND NOT IAW B757 SRM 51-70-11 FIG 1, DETAIL I, II. STRINGER R 7.55 FROM STA 1460 TO STA 1480 REPLACED IAW B757 SRM 51-10-02 REV 93. REPAIR IS CLASSIFIED AS MINOR PER GMM 8-2-100 CRITIERIA.
EXISTING REPAIR FOUND IN AFT CARGO FLOORBOARD SUPPORT L7.55, STA 1500-1520. TO EVALUATE EXISTING REPAIR. EXISTING REPAIR FOUND NOT IAW SRM 51070-11 FIG 1 DETAIL I, II. STRINGER L7.55 FROM STA 1500 TO STA 1520 REPLACED IAW B757 SRM 51-10-02 REV 93. REPAIR IS CLASSIFIED AS MINOR PER GMM 6-2-100 CRITERIA.
EXISTING REPAIR FOUND IN AFT CARGO FLOORBOARD STRINGER L2.90 STA 1540-1560, TO EVALUATE EXISTING REPAIR. EXISTING REPAIR FOUND NOT CARRIED OUT IAW B757 SRM 51-70-11 FIG 1 DETAIL I, II. STRINGER L2.90 FROM STA 1540-1560 REPLACED IAW B757-200 SRM 51-10-02 REV 93. REPAIR IS CLASSIFIED AS MINOR PER GMM 6-2-100 CRITERIA.
EXISTING REPAIR FOUND IN AFT CARGO FLOOR BOARD SUPPORT R11.40, STA 1500-1520 TO EVALUATE EXISTING REPAIR. EXISTING REPAIR FOUND NOT IAW SRM 51-70-11 FIG1 DETAIL I, II STRINGER R11.40 FROM STA 1500 TO STA 1520 REPLACED IAW B757 SRM 51-10-02 REV 93. REPAIR IS CLASSIFIED AS MINOR PER GMM 6-2-100 CRITERIA.
EXISTING REPAIR FOUND IN AFT CARGO FLOORBOARD STRINGER R2.90 INTERSECTION AT STA 1240 TO EVALUATE EXISTING REPAIR. EXISTING REPAIR FOUND NOT IAW B757-200 SRM 51-70-11 FIG 1, DETAIL I, II. AFT CARGO FLOORBOARD STRINGER REPLACED IAW B757-200, SRM 51-10-02 REV 93. REPAIR IS CLASSIFIED AS MINOR PER GMM 6-02-100.
EXISTING REPAIR FOUND ON RI DOOR SILL BETWEEN STA 365 AND STA 395 FOUND WITH ELONGATED HOLES AND CORROSION. REMOVED EXISTING REPAIR AND REPLACED IAW SRIM 51-10-02 REV. 93. REPAIR IS CLASSIFIED AS MAJOR PER GMM 6-2-100 CRITERIA.
SLAT NR 7 TRAILING EDGE WEDGE EXTERNAL DOUBLER, REF: ENTRY NR R15 IN 4X-BY EXTERNAL DAMAGE RECORD SHEET. THE TEMPORARY REPAIR DOUBLER AT SLAT NR 7 TRAILING EDGE WEDGE OUTER SURFACE SKIN REMOVED. COMPLIED WITH ATTACHMENT B OF EO F-5100-7-5001 P1. REPAIR DOUBLER, FABRICATED AND INSTALLED IN ACCORDANCE WITH B757-200 SRM 51-70-10 REPAIR 4, FIG 201 (SHEET 1 OF 5) REV 93. THE NEW 6.5 INCH BY 10 INCH REPAIR DOUBLER IS CLASSIFIED AS MAJOR REPAIR PER GMM 6-2-100 CRITERIA. THIS IS A PERMANENT REPAIR AND NO FOLLOW UP ACTION IS REQUIRED.
EXISTING REPAIR, SLAT NR 6 TRAILING EDGE WEDGE EXTERNAL DOUBLER (REF: 4X-BY EXTERNAL DAMAGE RECORD SHEET ENTRY NR R4) TO EVALUATE EXISTING REPAIR. ACCOMPLISHED EVALUATION IAW ATTACHMENT B OF EO F-5100-7-5001 P1. EXISTING REPAIR DOUBLER AT NR 6 SLAT IS AN INTERIM REPAIR. REPLACED DOUBLER IAW B757-200 SRM 51-70-10, REPAIR 4, FIG 201 SHT 1 OF 5 REV 93. THE NEW 7" BY 9" REPAIR DOUBLER IS CLASSIFIED AS A MAJOR REPAIR PER GMM 6-2-100 CRITERIA. THIS IS A PERMANENT REPAIR. NO FOLLOW-UP ACTION REQUIRED.
CORROSION AROUND SCREW HOLE ON STA 365, RBL3, RBL7, RBL11, RB15, RBL19, RBL23, RBL27, RBL31, RBL35, RBL39, RBL43, RBL47, RBL51. CORROSION FOUND EXCEED SRM LIMITS. FLOORBEAM REPAIR CARRIED OUT IAW SRM 53-00-51 REV. 93, FIG. 201, REPAIR 1. REPAIR IS CLASSIFIED AS MAJOR PER GMM 6-2-100 CRITERIA.
CORROSION ON FLOORBEAM AT STA 377.7, LBL3, LBL6, LBL10 AND LBL12. FOUND EXCEED LIMITS IN SRM 53-00-51. REPAIR CARRIED OUT IAW SRM 53-00-51 FIG 201 REPAIR 1 REV. 93. REPAIR IS CLASSIFIED AS MAJOR PER GMM 6-2-100 CRITERIA.
CORROSION ON FLOORBEAM AT STA 344, LBL4, LBL2, BL0, RBL 2 AND RBL 4. REPAIR CARRIED OUT IAW SRM 53-00-51 FIG.201 REPAIR 1. REPAIR IS CLASSIFIED AS MAJOR PER GMM 6-2-100 CRITERIA.
CORROSION ON INBOARD STRUCTURE AT STA 1280, S17L. REPLACED IAW DWG NR 146N5590. REPAIR IS CLASSIFIED AS MAJOR PER GMM 6-2-100 CRITERIA.
CORROSION ON FLOORBEAM AT STA 1640, LBL9 AND RBL14. REPAIR CARRIED OUT IAW SRM 53-00-51 FIG 201 REPAIR 1 AS PER EAR P337-24137-C0017.
CORROSION ALONG RT CREASE BEAM INBOARD CHORD LT ANGLE AT STA 660-686, S-17R. REPLACED AS PER EA F-5310-117337. REPAIR IS CLASSIFIED MAJOR PER GMM 6-2-100 CRITERIA.
CORROSION FOUND ON LT CREASE BEAM OUTBD CHORD AT STA 1190, S17. REPAIR CARRIED OUT PER EAR P337-24137-C0014 AND EAR P337-24137-C0093 REV.A. REPAIR IS CLASSIFIED AS MAJOR PER GMM 6-2-100 CRITERIA.