N526MC

Part: SKIN — DAMAGED (ZONE 200) · airframe 22,337 hrs · 97,742 cycles

BS 740 TO 999.9 AT S6L/R LAP JOINT SCRIBE LINE DAMAGED. REPAIRED IN ACCORDANCE WITH SERVICE REQUEST 1-750626371 APPROVED BY FAA FORM 8100-9 DATED 2 OCT 2008, DETAILS OF WORK KEPT IN EO-473B205 & EO-4753B113.

Part: SKIN — DAMAGED (ZONE 200) · airframe 97,742 hrs · 20,093 cycles

FUSELAGE STA 520 TO STA 740 AT S-23L/R LAP JOINT SCRIBE LINE DAMAGED. REPAIRED IN ACCORDANCE WITH SERVICE REQUEST 1-750634474 APPROVED BY FAA FORM 8100-9 DATED 2 OCT 2008, DETAILS OF WORK KEPT AT EO-4753B203 & EO-4753B114.

Part: SKIN — DAMAGED (ZONE 100) · airframe 97,742 hrs · 20,093 cycles

FUSELAGE SCRIBE LINE OVERLAPPED SKIN BETWEEN BS 520-560 AT S34R DAMAGED. REPAIRED IN ACCORDANCE WITH SERVICE REQUEST 1-751139526 APPROVED BY FAA FORM 8100-9 DATED 02 OCT 2008, DETAILS OF WORK KEPT IN EO-4753B204 & EO-4753B114.

Part: SKIN — DAMAGED (ZONE 200) · airframe 97,742 hrs · 20,093 cycles

FUSELAGE STA 520 TO STA 740 AT S-23L/R LAP JOINT SCRIBE LINE DAMAGED. REPAIRED IN ACCORDANCE WITH SERVICE REQUEST 1-750634474 APPROVED BY FAA FORM 8100-9 DATED 2 OCT 2008, DETAILS OF WORK KEPT AT EO-4753B203 & EO-4753B114.

Part: SKIN — DAMAGED (ZONE 200) · airframe 22,337 hrs · 97,742 cycles

BS 2181-2360 AT S12L/R LAP JOINT SCRIBE LINE DAMAGED. REPAIRED IN ACCORDANCE WITH SERVICE REQUEST 1-750626156 APPROVED BY FAA FORM 8100-9 DATED 30 SEP 2008, DETAILS OF WORK KEPT AT EO-4753B202 & EO-4753B114.

Part: SKIN — DAMAGED (ZONE 100) · airframe 97,742 hrs · 20,093 cycles

FUSELAGE STA 520 TO 740 AT STR 34L LAP JOINT SCRIBE LINE DAMAGE. REPAIRED IAW SERVICE REQUEST 1-963742727 APPROVED BY FAA FORM 8100-9 DATED 02 OCT 08 DETAILS OF WORK EO4753B206 & EO 4753B114.

Part: SKIN — DAMAGED (FUSELAGE) · airframe 97,742 hrs · 20,093 cycles

FUSELAGE SCRIBE LINE OVERLAPPED SKIN BETWEEN STA 670 TO 741 AT STR 34R DAMAGED. REPAIRED IAW BOEING SERVICE REQUEST 1-751139674 APPROVED BY FAA FORM 8100-9 DATED 26 SEP 2008. DETAILS OF WORK PERFORMED KEPT ON ATLAS ENGINEERING ORDER EO4753B207 AND EO4753B114.

Part: ENGINE — FAILED (NR 2) · airframe 96,493 hrs · 19,885 cycles

AT FL 32.0 HOURS AFTER TAKEOFF, NR 2 ENGINE STALLED AND ROLLED BACK. THROTTLE WAS PULLED TO IDLE AND STALLING QUIT. WHEN THE THROTTLE WAS PUSHED ABOVE 80 PERCENT N2 STALL AND VIBRATION REOCCURRED, EGT REMAINED IN LIMITS. REMOVED AND REPLACED NR 2 ENGINE PER 71-00-02.

Part: PANEL — DELAMINATED (TE FLAP) · airframe 96,469 hrs · 19,818 cycles

NR 1 KNEE CAP PANEL UNDER SURFACE DELAMINATED. REPAIRED PER EO NR 4757A431 AND SRM 51-40-14 AND 51-40-15.

Part: BOLT — SHEARED (TRUNNION) · airframe 96,469 hrs · 19,818 cycles

FORWARD UPPER TRUNNION NUT LOCKING PLATE BOLTS SHEARED AND TRUNNION NUT REQUIRES TORQUE CHECK SUSPECT MOVEMENT IN HOUSING. TRUNNION HOUSING REMOVED AND REPLACED IAW AMM 57-43-01/ 401 AND 32-11-19. ALL FIT CLEARANCES AND NDT OF PINS SATISFACTORY PER BSOPM 20-20-01. HOUSING ATTACHMENT BRACKETS NDT IAW D6-7170 PART 6 51-00-00, NO CRACKS EVIDENT. GEAR RETRACTION AND EXTENSION PERFORMED.

Part: SKIN — DELAMINATED (SPOILER) · airframe 96,469 hrs · 19,818 cycles

RIGHT WING NR 7 GROUND SPOILER HAS SIGNS OF DELAMINATION. REPAIRED IAW SRM 57-40-24 AND 51-40-20, AND EO NR 4757A429.

Part: FLAP — PERFORATED (LT TE FLAP) · airframe 96,469 hrs · 19,818 cycles

LEFT INBOARD FOREFLAP PERFORATED APPROX 12 INCH INBOARD FROM IT'S OUTBOARD EDGE APPROX WS 1178. REPAIR CARRIED OUT IAW EO NR 4757A432.

Part: ACCESS PANEL — CORRODED (RT WING TE FLAP) · airframe 96,469 hrs · 19,818 cycles

RIGHT WING TRAILING EDGE INBOARD MIDFLAP LOWER SURFACE ACCESS PANEL WBL 240.00 HAS SIGNS OF CORROSION. REMOVED AND REPAIRED CORROSION AT WBL 240.00 PER SRM 57-40-20.

Part: STRUCTURE — CRACKED (KRUEGER FLAP) · airframe 95,952 hrs · 19,704 cycles

NR 15 KRUEGER FLAP UPPER BACKUP STIFFENER REPAIRED DOUBLER CRACKED AT OUTBOARD HINGE SUPPORT AREA. REPLACED EXISTING REPAIR DOUBLER IAW SRM 51-10-01.

Part: STRINGER — CORRODED (ZONE 100) · airframe 95,952 hrs · 19,704 cycles

AFT CARGO COMPARTMENT LEFT SIDE STRINGER 51 CORROSION AT STATION 1540, LEVEL 1 CORROSION. AFT CARGO STRINGER CORROSION REPAIRED IAW SRM 51-10-01. APPLIED FINISH IAW 51-21-00.

Part: SKIN — SCRATCHED (ZONE 100) · airframe 95,952 hrs · 19,704 cycles

PERFORMED EO 4753B107 FOUND SCRIBE LINE DISCREPANCY. REPAIRED LAP JOINT PER ATLAS EO 4753B107 AND 4753B108.

Part: SKIN — SCRATCHED (ZONE 100) · airframe 95,952 hrs · 19,704 cycles

PERFORMED EO 4753B100 FOUND SCRIBE LINE DISCREPANCY. REPAIRED LAP JOINT BS 520-1000 LEFT AND RIGHT SEE NON ROUTINE CARD 9022 AND 9030. BUTT JOINT BS 1961 S46L-S12R PER NON ROUTINE CARD 7455. ALL OTHER SCRIBE LINE DEFECTS COVERED BY ATLAS EO4753B112, 4753B113, 4753B116.

Part: SKIN — SCRATCHED (ZONE 200) · airframe 95,952 hrs · 19,704 cycles

SURROUNDING M/D L-3 DOOR CUTOUT AFT LOWER DOUBLER EDGE FUSELAGE SKIN FOUND SCRIBE LINE. BLENDED PER BOEING LETTER NR 1-749452899-5 AND EO4753B109.

Part: SPAR — CORRODED (RT WING) · airframe 95,952 hrs · 19,704 cycles

WS 410 - WS 470 FRONT SPAR CORROSION EVIDENT ON RIGHT WING. BLENDED OUT CORROSION IAW SRM 51-10-01. REPROTECTED PER 51-10-02.

Part: FLOORBEAM — CRACKED (ZONE 100) · airframe 95,952 hrs · 19,704 cycles

AFT CARGO COMPARTMENT STA 1700 RBL 55 FLOORBEAM CHORD ANCHOR NUT AREA FOUND MINOR CORROSION. LEVEL 1, BLENDED OUT CORROSION IAW SRM 51-10-01 0.049" 1" WIDE 2" LONG. REPROTECTED PER 51-10-02. APPLIED CORROSION INHIBITOR COMPOUND.

Part: STRINGER — CORRODED (ZONE 100) · airframe 95,952 hrs · 19,704 cycles

AFT CARGO COMPARTMENT STA 1890 STRINGER 46 CORRODED. REMOVED CORROSION PER SRM 51-10-01. REPROTECTED PER 51-10-02.

Part: STRINGER — CORRODED (ZONE 100) · airframe 95,952 hrs · 19,704 cycles

AFT CARGO COMPARTMENT STA 1500 STRINGER 43 CORRODED. REMOVED CORROSION PER SRM 51-10-01. REPROTECTED PER 51-10-02.

Part: SPAR — CORRODED (RT WING) · airframe 95,952 hrs · 19,704 cycles

W/S 780 UPPER SKIN MIDSPAR CORROSION EVIDENT. LEVEL 1 RIGHT WING, BLENDED OUT CORROSION IAW SRM 51-10-01. REPROTECTED PER 51-10-02.

Part: DOOR FRAME — CRACKED (BS 1686-1687) · airframe 95,952 hrs · 19,704 cycles

MAIN DECK NR 4R DOOR AFT SIDE EDGE FRAME LOWER POSITION FOUND CRACKED. REPAIRED CRACK PER SRM 52-10-02.

Part: STRINGER — CORRODED (ZONE 100) · airframe 95,952 hrs · 19,704 cycles

AFT CARGO COMPARTMENT STRINGER 51 CORROSION WITH MARKING AT STATION 1800, LEVEL 1 CORROSION. AFT CARGO STRINGER CORROSION REPAIRED IAW 53-10-03.

Part: STRINGER — CRACKED (BS 2240) · airframe 95,952 hrs · 19,704 cycles

AFT AND BULK CARGO COMPARTMENTS STA 2240 LEFT SIDE STRINGER 50 FOUND CRACKED. STRINGER REPAIRED PER 53-10-03.

Part: RIB — CRACKED (NR 12 K FLAP) · airframe 95,952 hrs · 19,704 cycles

NR 12 KRUGER FLAP INNER FACE UPPER BACKUP STIFFENER O/B END CRACKED. REPAIRED PER BOEING MESSAGE NR 1-748489952-4.

Part: STRINGER CLIP — CORRODED (ZONE 100) · airframe 95,952 hrs · 19,704 cycles

AFT CARGO COMPARTMENT STRINGER 44 LEFT CLIP CORROSION AT STATION 1680, LEVEL 1 CORROSION. REPLACED CLIP PER SRM 51-10-01.

Part: SKIN — SCRATCHED (ZONE 100) · airframe 95,952 hrs · 19,704 cycles

PERFORMED EO 4753B107 FOUND SCRIBE LINE DISCREPANCY. REPAIRED LAP JOINT PAR ATLAS EO 4753B107 AND 4753B108.

Part: SKIN — SCRATCHED (ZONE 100) · airframe 95,952 hrs · 19,704 cycles

PERFORMED EO 4753B100 FOUND SCRIBE LINE DISCREPANCY. REPAIRED LAP JOINT PER ATLAS EO 4753B106.

Part: SKIN — CORRODED (TE FLAP) · airframe 95,952 hrs · 19,704 cycles

LEFT OUTBOARD AFT FLAP UPPER SKIN HAS MINOR SURFACE CORROSION FOUND AFT OF OUTBOARD OF NR 2 SPINDLE. BLENDED OUT CORROSION IAW SRM 51-10-01. REPROTECTED PER 51-10-02.

Part: RIB — CRACKED (NR 11 K FLAP) · airframe 95,952 hrs · 19,704 cycles

NR 11 KRUGER FLAP INNER FACE UPPER BACKUP STIFFENER I/B END CRACKED. REPAIRED PER BOEING MESSAGE NR 1-748489952-4.

Part: STRINGER — CORRODED (ZONE 100) · airframe 95,952 hrs · 19,704 cycles

AFT CARGO COMPARTMENT STRINGER 49 CORROSION AT STATION 1600, LEVEL 1 CORROSION. AFT CARGO STRINGER CORROSION REPAIRED IAW SRM 51-10-01. APPLIED FINISH IAW 51-21-00.

Part: BRACE — WORN (ZONE 400) · airframe 95,952 hrs · 19,704 cycles

NR 1 DIAGONAL BRACE FORWARD PORTION LOWER SURFACE PRIMER DISCOLORED. REPLACED DIAGONAL BRACE PER MM 54-10-03.

Part: BRACE — WORN · airframe 95,952 hrs · 19,704 cycles

NR 4 DIAGONAL BRACE FORWARD PORTION LOWER SURFACE PRIMER DISCOLORED. REPLACED DIAGONAL BRACE PER MM 54-10-03.

Part: INU — FAILED (NR 1) · airframe 95,931 hrs · 19,697 cycles

AIR TURN BACK, AFTER TAKEOFF THE CAPT'S ADI AND THE NR 1 INS FAILED. PLACING THE PLATFORM SWITCH TO POSITION 3 MADE NO DIFFERENCE. SWAPPED NR 1 AND NR 3 INU DUE TO NR 1 FAILED. OPS CHECKED GOOD ON NR 1 PLACED NR 3 ON DMI.

Part: PANEL — CRACKED (ZONE 500) · airframe 95,740 hrs · 19,657 cycles

LT WING UPPER SURFACE LEADING EDGE TO FRONT SPAR PANEL (BEHIND NR 9 LEADING EDGE FLAP WS 862) HAS 2 INCH CRACK. PANEL REPAIRED IAW SRM 51-40-9 AND 51-40-12.

Part: PANEL — DELAMINATED (ZONE 500) · airframe 95,740 hrs · 19,657 cycles

LEFT WING UPPER SURFACE PANEL NR 521 HAS EVIDENCE OF DELAMINATION ABOUT 3 INCHES LONG 6 INCHES FORWARD OF THE TRAILING EDGE AND 18 INCHES INBOARD OF THE OUTBOARD EDGE. ALSO AN AREA 3 INCHES LONG 21 INCHES AWAY FROM THE OUTBOARD EDGE AND 5 INCHES AFT OF THE LEADING EDGE. REPAIRED PANEL IAW SRM 51-40-12 AND XEO 57-121207. PERMANENT REPAIR TO BE ACCOMPLISHED AT NEXT C-CHECK.

Part: PANEL — GOUGED (ZONE 500) · airframe 95,740 hrs · 19,657 cycles

LEFT WING UPPER SURFACE PANEL NR 521 HAS A CIRCULAR SHAPED GOUGE ABOUT 12 INCHES OUTBOARD OF THE INBOARD EDGE ( 7.5 INCHES LONG BY 5.5 WIDE). INTERIM REPAIR ACCOMPLISHED IAW SRM 51-40-15 AND XEO 57-121207.

Part: PANEL — DELAMINATED (ZONE 500) · airframe 95,740 hrs · 19,657 cycles

LEFT HAND WING UPPER SURFACE PANEL NR 521 HAS EVIDENCE OF DELAMINATION 3 INCHES LONG, 2INCHES AWAY FROM OUTBOARD EDGE AND 5 INCHES FROM THE LEADING EDGE. REPAIRED PANEL IAW SRM 51-40-12 AT 250 DEGREES AND 26" HG VACUUM AND XEO 57-121207.

Part: PANEL — DELAMINATED (ZONE 500) · airframe 95,740 hrs · 19,657 cycles

LT WING UPPER SURFACE LEADING EDGE TO FRONT SPAR PANEL (BEHIND NR 8 LEADING EDGE FLAP WS 917) HAS EVIDENCE OF DELAMINATION. PANEL REPAIRED IAW SRM 51-40-9 AND 51-40-12.

Part: PANEL — DELAMINATED (LT WING) · airframe 95,740 hrs · 19,657 cycles

LT WING UPPER SURFACE LEADING EDGE TO FRONT SPAR PANEL (BEHIND NR 6 LEADING EDGE FLAP WS 1028) HAS EVIDENCE OF DELAMINATION. PANEL REPAIRED IAW SRM 51-40-9 AND 51-40-12.

Part: PANEL — DELAMINATED (ZONE 600) · airframe 95,054 hrs · 19,521 cycles

LT WING UPPER L/E FIXED PANEL AT WS 490.00 HAS AN AREA OF 2.0 INCH LONG BY 2.0 INCH WIDE OF DELAMINATION. PERMANENT REPAIR ACCOMPLISHED AS PER B747-200 SRM 51-40-09 FIG 18, SHEETS 1 THRU 5 AND SRM 51-40-12. ALSO, REFERENCE ATLAS AIR EO NR 4757A393.

Part: FRAME — CRACKED (NR 3 NACLLE) · airframe 95,054 hrs · 19,521 cycles

NR 3 ENGINE RT CORE COWL FORWARD FRAME HAS A HOLE AND CRACK. PERMANENT REPAIR ACCOMPLISHED AS PER B747-200 SRM 51-20-01 FIG 4 AND SRM 51-40-03 FIG 1. ALSO, REFERENCE ATLAS AIR XEO NR 71-092807.

Part: DOOR — DEBONDED (ZONE 600) · airframe 95,054 hrs · 19,521 cycles

RT WING GEAR INBOARD STRUT DOOR AFT EDGE, CENTER AREA HAS A 10.0 INCH LONG BY 4.0 INCH WIDE OF MATERIAL SEPARATING AT BS 1343.3. PERMANENT REPAIR ACCOMPLISHED AS PER B747-200 SRM 51-40-09 FIG 12, SHEETS 1 THRU 4 AND SRM 51-40-12. ALSO, REFERENCE ATLAS AIR EO NR 4752A125.

Part: PANEL — DELAMINATED (RT WING) · airframe 95,054 hrs · 19,521 cycles

RT WING UPPER L/E FIXED PANEL AT WS 317.32 HAS AN AREA OF 2.0 INCH LONG BY 2.0 INCH WIDE OF DELAMINATION. PERMANENT REPAIR ACCOMPLISHED AS PER B747-200 SRM 51-40-09 FIG 18, SHEETS 1 THRU 5 AND SRM 51-40-12. ALSO, REFERENCE ATLAS AIR EO NR 4757A393.

Part: FAIRING — DELAMINATED (RT WING TE FLAP) · airframe 95,054 hrs · 19,521 cycles

RT WING NR 5 FLAP TRACK FORWARD FIXED FAIRING AT WBL 235.20, OUTBOARD SIDE HAS AN AREA 12.0 INCH LONG BY 2.0 INCH WIDE OF DELAMINATION AND CRACK. PERMANENT REPAIR ACCOMPLISHED AS PER B747-200 SRM 51-40-09 FIG 6, SHEETS 1 THRU 4 AND SRM 51-40-12. ALSO, REFERENCE ATLAS AIR EO NR 4757A395.

Part: PUSHROD — SHEARED (TE FLAP) · airframe 94,734 hrs · 19,459 cycles

ON WALK AROUND FOUND NR 5 FLAP TRACK MOVABLE CANOE FAIRING AFT PUSH ROD SHEARED AND BENT AND FORWARD LINK SUPPORT BENT. INBOARD SIDE OF FAIRING SEAL RETAINER WAS DAMAGED AND A 20 INCH SECTION OF COMPOSITE SKIN UNDER THE RETAINER WAS CRACKED.ROD AND LINK WAS REMOVED AND REPLACED AS PER 747-200 MM 27-51-39 AND FAIRING WAS REMOVED FROM AIRCRAFT AS PER CDL 27-51-2, REFERENCE ATLAS DMI M07 242.

Part: SEAT TRACK — CRACKED (BS 1906) · airframe 94,356 hrs · 19,381 cycles

MAIN DECK SEAT TRACK AT BS1906, LBL 99 HAS CROWN LUGS CRACKED. PERMANENT REPAIR WAS ACCOMPLISHED AS PER 747-200 SRM 53-10-05 FIG 1A AND 747-200 SRM 51-10-08. ALSO, REF: ATLAS AIR XEO NR 53-071307.

Part: SKIN — CRACKED (NR 3 NACELLE) · airframe 94,356 hrs · 19,381 cycles

NR 3 ENGINE LT CORE COWL NR 437, AFT LOWER CORNER LONGERON STRUCTURE AND OUTER COWL SKIN HAS A CRACK AND LOOSE RIVETS. PERMANENT REPAIR ACCOMPLISHED AS PER 747 SRM 54-31-03 FIG 3 AND ATLAS EO4771A026 AND FAA 8110-3 FORM (REF: FIG. 1 AND 2) AND ATLAS AIR XEO NR 54-071307.

Part: DOOR — DELAMINATED (FAIRING) · airframe 94,356 hrs · 19,381 cycles

NR 1 ENGINE RT STRUT TRAILING EDGE FAIRING DOOR, PANEL NR 454AR, FORWARD LOWER CORNER HAS AN AREA OF 7.0 INCH BY 10.0 INCH AREA OF DELAMINATION. ACCOMPLISHED PERMANENT REPAIR AS PER 747-200 SRM 51-40-06 FIG 4, SHEET 1 AND 747-200 SRM 51-40-20. ALSO, REF: ATLAS AIR XEO NR 54-071207.

Part: FAIRING — PUNCTURED (WING TO BODY) · airframe 94,356 hrs · 19,381 cycles

LOWER BODY FAIRING PANELS 194C AND 194B HAVE A PUNCTURED HOLE. PANEL 194B AREA OF PUNCTURE IS 2.750 BY .750 INCHES AND 194C IS 1.250 BY .750 INCHES. PERMANENT REPAIR WAS ACCOMPLISHED AS PER 747-200 SRM 51-40-09 FIG 11 AND 747-200 SRM 51-40-12. ALSO, REF: ATLAS AIR XEO NR 53-071107.

Part: PANEL — DELAMINATED (RT WING) · airframe 94,356 hrs · 19,381 cycles

RT WING FUELING BAY ACCESS PANEL NR 621BB, INNER SKIN HAS 2 EACH AREAS OF DELAMINATION. PERMANENT REPAIR WAS ACCOMPLISHED AS PER 747-200 SRM 51-40-09 FIG 18, SHEET 1, 3, AND 5, TABLE 1, PREPEG 250* F CURE. ALSO, REFERENCE ATLAS AIR XEO NR 57-071207.

Part: PUSHROD — BROKEN (TE FLAPS) · airframe 93,980 hrs · 19,300 cycles

ON W/A, FOUND RT INBOARD TRAILING EDGE FLAP PUSH-ROD ASSY BROKEN. REMOVED AND REPLACED INBOARD TRAILING EDGE FLAP PUSH-ROD ASSY IAW MM 27-51-39. SYSTEM OPERATIONS CHECKED OK.

Part: PANEL — CRACKED (BS 260-280) · airframe 93,725 hrs · 19,249 cycles

CRACK INDICATION ON RT SIDE PANEL BETWEEN STA 260 AND 280 AT WL 150. CRACK LOCATION IS STA 272 WL 150, BELOW RIVET RUNNING AFT 15 MM IN LENGTH. REPAIRED CARRIED OUT IAW SRM 53-10-04 FIG 116.

Part: PANEL — CRACKED (BS 1241-1250) · airframe 94,846 hrs · 17,103 cycles

MAIN DECK STATION 1241 TO 1250 LBL 75 TO 97 CLOSEOUT PANEL NEAR TRIM AIR DUCT FOUND CRACKED. MAIN DECK STATION 1241 TO 1250 LBL CLOSEOUT PANEL REPLACED AS PER SB 747-53-2329 PART 4.

Part: DUCT — DAMAGED (NR 1 ENGINE) · airframe 93,058 hrs · 19,113 cycles

NUMBER ONE POSITION ENGINE SERIAL NUMBER 517598 WAS FOUND WITH A 4 INCH BLOWN HOLE ON 8TH STAGE "Y" DUCT. DUCT WAS REMOVED AND REPLACED AS PER 747 MM 75-25-00.

Part: CONTROL PANEL — INOPERATIVE (ILS) · airframe 92,488 hrs · 18,986 cycles

ILS SYSTEM INOP AT BOTH CAPT AND F/O, F/O HAS FLAGS BUT NO IDENT. CAPT HAS NO FLAG AND NO IDENT. REMOVED AND REPLACED ILS CONTROL PANEL. GROUND TESTED ILS SYSTEM PER MM 34-31-14. SYSTEM TEST NORMAL.

Part: SKIN — CRACKED (RT WING) · airframe 92,366 hrs · 18,963 cycles

RT WING UPPER L/E PANEL HAS 2 EACH AREAS WITH COMPOSITE CRACKS AT WBL 480, WBL 480 FORWARD CRACK IS 8.0 INCHES LONG. REPAIR AREA IS 3.0 INCH BY 12.0 INCH, WBL 480 AFT CRACK IS 6.0 INCHES LONG. REPAIR AREA IS 7.0 INCH BY 12.0 INCH. PERMANENT REPAIR WAS ACCOMPLISHED AS PER B747 SRM 51-40-09 FIG 18 AND 747 SRM 51-40-12. ALSO, REFERENCE ATLAS EO 4757A333.

Part: SKIN — CRACKED (LT WING) · airframe 92,366 hrs · 18,963 cycles

LT WING UPPER L/E PANEL AT WBL 450 SURFACE HAS AREA OF COMPOSITE CRACK. ACCOMPLISHED PERMANENT REPAIR OF AREA OF CRACK AS PER B747 SRM 51-40-09 FIG 18 AND 747 SRM 51-40-12. CRACK LENGTH IS 2.0 INCHES LONG AND REPAIR AREA IS 4.0 INCH BY 7.0 INCH. ALSO, REFERENCE ATLAS EO 4757A333.

Part: BRACKET — CRACKED (NLG) · airframe 92,355 hrs · 18,959 cycles

RED GEAR DOOR LIGHT AND RED GEAR LIGHT ON AFTER RETRACTION. ANNUNCIATOR PANEL PRIM + ALT GEAR LIGHTS OUT. PRIM + ALT NOSE DOOR LIGHTS ILLUMINATED. PER ALT, OPS GEAR EXTENDED AND RETRACTED. NOSE GEAR DOOR DID CLOSE, BUT REQUIRED LONGER THAN NORMAL TIME. TROUBLE SHOOTING REVEALED STRUT PRESSURE/EXTENSION LOW AND NLG TORSION LINK CLOSURE BRACKET BROKEN. NLG, OLEO SEALS REPLACED AND CLOSURE BRACKET, REMOVED AND REPLACED WITH SERVICEABLE UNIT. NLG RETRACTION TEST CARRIED OUT, ALL OPS NORMAL. LHT WORK ORDER LFN 12/06 AND GROUND LOG BOOK AA12729 TO AA12751 FOR FURTHER DETAIL.

Part: DUCT — CRACKED (NR 3 ENGINE) · airframe 91,240 hrs · 18,714 cycles

AIR TURNBACK, NR 3 ENGINE IN FLIGHT FIRE. BOTH NACELLE TEMPS 8.5. NR 3 ENGINE FIRE HANDLE PULLED. NR 3 ENGINE EGT 924 DEG WITH REDUCED POWER, T/O OF 104.3 POWER REMAINED AT 103.0 FOR 6 TO 7 MINUTES. REMOVED AND REPLACED NR 3 ENGINE EDP, RETURN PRESSURE AND CASE DRAIN FILTER. PERFORMED ENGINE RUN-UP. OPS CHECK SATISFACTORY PER MM 29-11-05. FOUND 1-EACH PNEUMATIC DUCTING RUPTURE BELOW OVER PRESSURE S/O VALVE. REPLACED DUCT ASSY. PERFORMED ENGINE RUN-UP, OPS CK SATISFACTORY AS PER MM 78-34-00.

Part: SKIN — CRACKED (NR 4 PYLON) · airframe 91,042 hrs · 18,675 cycles

FOUND 1 CRACK ON NR 4 PYLON PRECOOLER EXHAUST SKIN CUTOUT. REPORT CRACK, REMOVED PER SRM 51-10-01. REPAIR CARRIED OUT PER BOEING SERVICE ID NR 1-198251549-11.

Part: FRAME — GOUGED (FUSELAGE) · airframe 91,042 hrs · 18,675 cycles

FOUND STA 2460 FRAME INNER CHORD AT APPROX LBL 33 FOUND BADLY GOUGED ABOUT 1/4 DEEP. REPAIR CARRIED OUT PER BOEING TELEX 1-196011744-1 AND 1-196011744-2AND FAA FROM 8100-9.

Part: SKIN — CRACKED (NR 2 PYLON) · airframe 91,042 hrs · 18,675 cycles

FOUND 2 CRACKS ON NR 2 PYLON PRECOOLER EXHAUST SKIN CUTOUT. REMOVED, REPORTED CRACK AND CARRIED OUT REPAIR PER BOEING RESPONSE MSG NR 1-198251446-7.

Part: SKIN — CRACKED (NR 2 PYLON) · airframe 91,042 hrs · 18,675 cycles

FOUND NR 2 PYLON ACCESS PANEL 463AR CUT-OUT CRACK. REPAIR C/OUT ON NR2 PYLON ACCESS DOOR CUT-OUT 463AR PER BOEING RESPONSE MSG 1-200482351-2. CRACKED FASTENER HOLE AT NAC STA 284 REAMED THROUGH SKIN AND STRAP PER BOEING MSG 1-200482351-7. NIL CRACK FOUND AFTER HOLE REAMED. FREEZE PLUG HOLE PER SRM 51-10-08.

Part: SKIN — CRACKED (NR 1 PYLON) · airframe 91,042 hrs · 18,675 cycles

FOUND 2 CRACKS ON NR 1 PYLON PRECOOLER EXHAUST SKIN CUTOUT. T-CHORD ON CUTOUT FOUND CRACK. REPORTED CRACKS, REMOVED PER BOEING RESPONSE MSG =1-200634469-2 AND 1-200634469-5. REPAIR CARRIED OUT ON NR 1 PYLON PRECOOLER CUTOUT PER BOEING RESPONSE MSG = 1-200634469-5.

Part: SKIN — BULGED (CENTER TANK) · airframe 91,042 hrs · 18,675 cycles

CENTER TANK TOP SKIN AT STA 1238 LBL 38.8 - 48.0 AREA FOUND SIGN OF SKIN BULGING. AFTER CLEAN- UP BLENDED AREA IS BETWEEN LBL 57 & LBL 65 AT STA 1241.TO CARRIED OUT OPEN HOLE HFEC PER BOEING MSG 1-200482565-1. CORROSION REMOVAL CARRIED OUT IAW SRM 51-10-01. SURFACE RE-PROTECTED IAW SRM 51-10-02 & FAA FORM 8100-9.

Part: FITTING — DAMAGED (NR 4 PYLON) · airframe 91,042 hrs · 18,675 cycles

NR 4 WING SIDE DSB FITTING OUTBD BEARING HOLE BORED TO 2.2768". (FINAL HOLE 0 FOR 3RD, OVERSIZE 2.2745" - 2.2755"). C/O SLEEVE REPAIR ON NR 4 DSB FITTING AS PER BOEING REPLY MESSAGE NR 1-202125094-7. C/O MAGNETIC PARTICLE INSPECTION ON MACHINED SURFACE AS PER BOEING SOPM 20-20-01.

Part: SILL — CORRODED (FUSELAGE) · airframe 91,042 hrs · 18,675 cycles

AFT CARGO LOWER DOOR SILL EXTERNAL SURFACE UNDER LATCH PRIM SUPPORT FITTING (AFT MOST/#16) AT STA 1914 FOUND CORROSION. DEFECT FOUND AFTER FITTING REMOVED. REPAIR CARRIED OUT PER BOEING TELEX 1-197304721 AND FAA FORM 8100-9.

Part: SKIN — CORRODED (RT WING) · airframe 91,042 hrs · 18,675 cycles

UPON REMOVAL OF TAPER LOCK FASTENER AT WS1084 FOUND WING INNERSPAR LOWER SKIN PADDED AREA WITH CORROSION BETWEEN FSSI 1111-1114. REMOVED CORROSION AND CARRIED OUT REPAIR ON RIGHT WING ILES 1116.0 LOWER SKIN PADDED AREA PER BOEING RESPONSE MSG NR 1-201142367-5.

Part: ENGINE — FAILED (NR 4) · airframe 90,885 hrs · 18,706 cycles

NORMAL TAKEOFF THRUST SET N1 100.1/OAT AND 03.*C WITH AUTOTHROTTLES ON AT 1500. AGL JUST AFTER CLIMB, THRUST SET TO 102.5, NR 4 ENGINE EXPERIENCED A MASSIVE COMPRESSOR STALL AT 2800, MSL. IMMEDIATELY REDUCED THRUST TO NR 4 ENGINE. STALL CEASED AT THAT TIME. IT WAS NOTED THAT NR 4 EGT WAS RAPIDLY CLIMBING IN THE CAUTION RANGE BUT RECOVERED WHEN THRUST WAS REDUCED TO IDLE. KEPT NR 4 ENGINE AT IDLE RPM AND RETURNED TO AIR FIELD. REMOVED AND REPLACED NR 4 ENGINE PER W/O 01-AA-45. OPS CHECK OK PERFORMED TEST ON NR 4 AND CHECK OK.

Part: SEAT TRACK — BROKEN (BS 1900-1920) · airframe 90,665 hrs · 18,594 cycles

MAIN DECK AT APPROX STA 1900 LEFT SIDE SEAT TRACK HAS TWO BROKEN LUGS AT SIDE CARGO DOOR. REPLACED SEAT TRACK PER SRM 53-10-05 AND EO 4753A753.

Part: DUCT — BLOWN (NR 4 NACELLE) · airframe 96,671 hrs · 18,594 cycles

RTO: DURING T/O ROLL, FIRE DET LIGHT CAME ON WITH HIGH NR 4 EGT AND BOTH NR 4 ENGINE NACELLE TEMPS WERE APPROX 7.0 T/O ABORTED AT 80KTS. BRAKE O/H LIGHT CAME ON LW/RF. REMOVED AND REPLACED DAMAGE 14TH STAGE DUCT LT SIDE, LEAK CK OK REF MM 75-25-00. ACCOMPLISHED HIGH ENERGY STOP INSPECTION AS PER MM 05-51-10. NO DEFECTS NOTED. BRAKES OK FOR SVC. ACCOMPLISHED HIGH ENERGY STOP INSPECTION PER PER MM 5-51-10 PG 202 SECTION C. NO DEFECTS NOTED. REMOVED AND REPLACED NR 4 ENGINE HIGH STAGE VALVE AS PER MM 36-11-05. OPS CHECKED OK.

Part: FIRE LOOP — CHAFED (NR 4 ENGINE)

FLT EI 9867 - ON TAKEOFF ROLL, NR 4 ENGINE FIRE WARNING LIGHT AND BELL CAME ON. MAX BRAKES APPLIED AT 95 KTS. TAKEOFF ABORTED. INSPECTED NR 4 ENGINE, NO PRIMER DISCOLORATION OR ANY SIGN OF HEAT DAMAGE. PERFOMED NR 4 ENGINE PNEUMATIC LEAK CHECK, NORMAL PER 71-00-00. PERFORMED HIGH ENERGY STOP HEAT DAMAGE CONDITION INSPECTION. ALL NORMAL PER AMM 5-51-10. CHECKED NR 4 ENGINE FIRE DETECTION SYSTEM A AND B. REPAIRED INSULATION CHAFFED WIRING B-LOOP AT 12 AND 3 O'CLOCK POSITION PER 26-11-52. PERFORMED ENGINE HIGH POWER RUN UP CHECK, ALL NORMAL. REF LOG PAGES 542971, 542972 AND 542973. (M)

Part: CONTROL PANEL — FAILED (ILS)

AIRCRAFT DIVERTED DUE TO (ILS LOC AND GS NOT RECEIVABLE) ON BOTH CAPTAIN AND FO HSI, ALL FLAGS VISIBLE ON BOTH SIDES INDICATING COMPLETE FAILURE OF THE ILS NAV CONTROL PANEL. REPLACED ILS CONTROL PANEL IAW MM 34-31-01 PERFORMED OPS CHECK ON ILS SYSTEM OK IAW MM34-31-00 FOUND WORKING SATISFACTORY. (K)

Part: STRUCTURE — MISSING (NR 4 ENGINE)

POST FLIGHT INSPECTION, FLT EK4979, 07/DEC/2004. DURING INSPECTION, FOUND NR 4 ENGINE AFT CENTER BODY CRACKED OFF. MISSING, LAST 20 INCHES FROM T/E. REMOVED AND REPLACED NR 4 ENGINE AFT CTR BODY IAW MM 78-11-02. INSPECTED AREA AFT OF NR 4 ENGINE FLAPS, WING AND TAIL SECTION. NO DAMAGE FOUND.

Part: PDU — FAILED (L/E SLAT)

DURING CLIMB-OUT, NR 3 LEADING EDGE FLAP WOULD NOT RETRACT. REMOVED AND REPLACED NR 3 LE PDU. OPS CHECK OK IAW MM 27-81-03. PDU OFF PN 126344-17-1, SN 22337, TOTAL MAINT DELAY, 3 HRS, 17 MIN. NOTE: NO FUEL WAS DUMPED.

Part: WIRE — DAMAGED (BLEED SYSTEM)

DURING CLIMB AT FL15.0, NR 4 ENG NACELLE 'B' IND WENT OT 6.0. 'A' IND 3.1. THRUST LEVEL 110.0, N1 & EGT NORMAL ON ALL ENGS. 'B' IND RETURNED TO 3.5 AT FL25.0 WITH CLIMB POWER SET. NR 4 ENG 'A' & 'B' INDS WENT TO 8,0 & EGT ON NR 4 ENG WENT TO 940 & NR 4 THRUST LEVER RETARDED & FHB PROCEDURES COMPLIED WITH. NR 2 BLEED AIR VALVE CLOSED HI STAGE LIGHT REMAINED ON & 'A' & 'B' INDS RETURNED TO 3.0. FOUND RT CORE LOOP CONNECTOR WIRING DAMAGED. R & R CONNECTOR. REPAIRED SERVERAL WIRES AT DIFFERENT LOCATIONS ON ENG ACCY PER MM. FOUND OVER PRESSURE VALVE LEAKING DURING LEAK CHECKS. R & R OVER PRESS VALVE ACC MM. LEAK CHECK SATISFACTORY. CHKD ALL DUCTS ON ENG & NO DEFECTS FOUND. R & R OVER PRESSURE VALVE ACC P

Part: SEAT TRACK — DAMAGED (FUSELAGE)

MAIN DECK SEAT TRACK CROWN DAMAGE 3 INCHES AT STATION 1802. DAMAGED SECTION OF SEAT TRACK WAS REPLACED IAW SRM 51-10-05. (M)

Part: WARNING SWITCH — OUT OF ADJUST (CARGO DOOR)

CARGO DOOR LIGHT ANNUNCIATOR LIGHT CAME ON IN FLIGHT AS WELL AS FORWARD CARGO LIGHT ON F/E PANEL. FHB PROCEDURE CARRIED OUT. ADJUSTED DOOR WARNING SWITCH. OPERATED DOOR SEVERAL TIMES, DOOR LIGHTS NORMAL, ALL OFF WHEN DOOR CLOSED MM 52-34-00/501. AIRCRAFT WAS DIVERTED TO DXB/IST. (M)

Part: FIRE LOOP — CHAFED (NR 2 ENGINE)

AT APPROXIMATELY 10,000 FT, NR 2 ENIGNE 'A' LOOP WAS INDICATING 7 UNITS, 'B' LOOP INDICATING 2.5. COMPLETED FHB 3.26.10 PROCEDURES NACELLE TEMPERATURE INDICATION ABNORMAL. RETARDED THROTTLE NO CHANGE, 30 SECON LATER 'A' LOOP INDICATES 9 PLUS, 'B' LOOP FLUCTUATES BETWEEN 2.5 AND 7.5. ENGINE FAILURE SHUTDOWN CHECKLIST ACCOMPLISHED. NR 2 ENGINE 'B' LOOP FOUND CHAFFING WIRES. REPAIRED WIRES AS PER SWPM 20-20-00 AND OPERATION CHECK SATISFACTORY AS PER MM 26-01-00. (M)

Part: THROTTLE — STUCK (NR 3 ENGINE)

NR 3 ENGINE THROTTLE STUCK AT POSITION IT WAS IN AT CRUISE POWER. IT FINALLY CAME LOOSE AT 10,000 FT. SHUT DOWN ENGINE AT 10,000 FT AND RESTARTED BETWEEN 10,000 FT AND 4,000 FT. OPERATED OK AFTER START. INSPECTED NR 3 ENGINE FOR WINDMILLING PER MM 72-00-00 PATE 682, NO DEFECTS NOTED. INLET AND EXHAUST INSPECTED AND THROTTLE FEEDBACK CABLE CLEANED CLEANED PER MM 72-00-00. ENGINE RUN COMPLIED WITH PER MM 73-00-00, NO DEFECTS NOTED. OK FOR CONTINUED SERVICE. (M)

Part: CONTROLLER — MALFUNCTIONED (CABIN PRESSURE)

DURING CRUISE FL370, PACKS NR 1 & 2 OPERATING, NR 1 PACK AIRFLOW APPROX 20 PSI & NR 2 PACK AIRFLOW 33 PSI, CABIN BEGAN TO CLIMB RAPIDLY. RATE LIMIT LIGHT ON. CABIN SHOWED A MOMENTARY DESCENT THEN BEGAN TO CLIMB RAPIDLY. SELECTED MANUAL PRESSURE. CABIN CONTINUED TO CLIMB RAPIDLY & ALTITUDE WARNING HORN ON. THIRD PACK WAS TURNED ON & OUTFLOW VALVES IMMEDIATELY SELECTED TO CLOSE. CABIN CONTINUED TO CLIMB. EMERGENCY DESCENT INITIATED. AFTER RECTIFICATION OF APU, ALL 3 PACKS CHECKED OK FOR NORMAL OPS AS PER AMM 5-51-08. EXCESSIVE CABIN PRESSURE LEAK CHECK CARRIED OUT WITH GOOD RESULTS. CHECKED UP TO 4 PSI AT 500 V/S. PRESSURE BLKHDS ETC CHECKED NO DEFECTS OR LEAKS AS PER 5-51-08. A/C SERVICEABLE. (M)

Part: LINE — CRACKED (HYD SYSTEM)

AIR TURN BACK, NR 1 HYDRAULIC SYSTEM LEAKING. QUANTITY STOPPED AT 2 GALLONS AFTER PLACING EDP SWITCH TO DEPRESS. ADP WORKED NORMAL AFTER 20 MINUTES IN CONTINUOUS ADP PRESSURE DROPPED TO ZERO. FOUND LINE CRACKED AT CLAMP IN SAILBOAT AREA. REMOVED AND REPLACED HYDRAULIC LINE IAW MM. CASE DRAIN FILTERS CHANGED AND SYSTEM OPERATED AND LEAK CHECKED IAW MM.

Part: TEE CHORD — CRACKED · airframe 80,028 hrs · 16,287 cycles

Internal inspection of #4 pylon found aft horizontial flange of R/H Tee Chord cracked at NC 270 Bulkhead in area of upper link fitting. Crack is located at the end fastener hole.

Part: CLAMP — LOOSE (NR 4 ENGINE)

LIM/MIA - NR 4 ENGINE FIRE LIGHT CAME ON CLIMBING THROUGH 20.0. BOTH A/B LOOPS WERE AT 9.0. FIRE SWITCH PULLED. FIRE BOTTLE WAS NOT FIRED. HYDRAULIC PUMP NR 4 IN SUPPLY OFF POSITION OR 1 PLUS 30 MINUTES. PERFORMED NACELLE OVERTEMPERATURE INSPECTION ON NR 4 ENGINE. FOUND LOOSE CLAMP ON 8TH STAGE DUCT. SECURED AS REQUIRED. RAN NR 4 ENGINE. OPS CHECK NORMAL IAW 71-00-00. (M)

Part: FRAME — CRACKED (FUSELAGE)

DURING HFEC INSPECTIN PER D6-7170 PART 6, 51-00-00, INSPECTION FOUND BS 2231 FRAME CRACK INDICATION AT STRINGER 25L. CRACK CONFIRMED. CRACK AREA TRIMMED OUT. FILLERS AND STRAP DOUBLERS FABRICATED. INSTALLED PER SRM 51-30-02 AND STANDARD PRACTICES. REF SB 747-53A2450. (M)

Part: FRAME — CRACKED (FUSELAGE)

DURING INSPECTION, FOUND FRAME CRACKED STATION 800 STRINGER 17L ADJACENT TO 2L MED. STOP DRILL NOT REQUIRED DUE CRACK RAN OFF END OF FRAME. FABRICATED REPAIR STACK UP DOUBLERS. INSTALLED PER STANDARD SRM PRACTICES. REF SB 53-10-04 FIG 114. (M)

Part: SKIN — CRACKED (FUSELAGE)

DURING HFEC INSPECTION, FOUND UPPER FORWARD CORNER OF AFT LOWER LOBE CARGO COMPT CRACKED .87 INCHES AT BS 1815, STRINGER 27R. TRIMMED OUT CRACKED AREA. FABRICATED FILLER AND REPAIR STACK UP DOUBLERS PER SRM 53-30-03 FIG 60, TYPE II. INSTALLED PER SRM REPAIR SCHEME AS NOTED ABOVE. (M)

Part: ANGLE — CRACKED (FUSELAGE)

DURING ROUTINE INSPECTION, FOUND CEILING ZEE CHORD ANGLE CRACKED IN LEFT BODY GEAR WHEEL WELL AT BS 1438 AND LBL 107. TRIMMED AWAY DAMAGED AREA. FABRICATED FILLER AND REPAIR ANGLES. INSTALLED PER STANDARD SRM PRACTICES. (M)

Part: SKIN — CORRODED (FUSELAGE)

DURING INSPECTION, FOUND SKIN CORROSION AT 4L MED LOWER AFT CORNER CUT OUT. TRIMMED AWAY CORRODED AREA. FABRICATED FILLER AND REPAIR STACK UP DOUBLERS. INSTALLED FASTENERS PER STANDARD SRM 51-30-02 PRACTICES. (M)

Part: FRAME — DAMAGED (FUSELAGE)

DURING ROUTINE INSPECTION, FOUND UPPER CHORD WITH CRITICAL HOLE ELONGATED AT BS 1265L AT WL 197. STACK UP DOUBLERS REMOVED. AREA CHECKED, PREVIOUS CRACKS CONTAINED. ALL HOLES IN STACK UP DOUBLERS OVERSIZED. OVERSIZED FASTENERS INSTALLED PER STANDARD PRACTICES. REPAIR SUBJECT TO REPETETIVE INSPECTIONS. (M)

Part: FITTING — CRACKED (NR 1 PYLON)

DURING VISUAL INSPECTION OF NR 1 PYLON, SUPPORT FITTING (P/N 65B94161-1) AT NAC 222 WAS DISCOVERED LOOSE. FURTHER INSPECTION AND DISASSEMBLY REVEALED THE ATTACHING BOLTS ON THE UPPER AND LOWE LEFT SIDE ATTACH POINTS WRE WORN AND THE SUPPORT FITTING BUSHINGS ELONGATED. MAGNETIC PARTICLE INSPECTION (MPI) INDICATED A SMALL CRACK IN THE ID OF THE LOWER ATTACH LUG FITTING. HOLE OVERSIZED PER BOEING TELEX, BOTH HOLES RE-BUSHED AND RETURNED TO NOMINAL SIZE. SUPPORT FITTING WAS REINSTALLED USING NEW ATTACHING HARDWARE. IN ADDITION, A SECONDARY INSPECTION REVEALED MIGRATING SHIM MATERIAL IN ADJACENT STRUCTURE. MIGRATING SHIM MATERIAL REPAIRED PER SRM 51-10-10, FORM 8110-3 ISSUED FOR OVERSIZED HOLE. (M)

Part: FIRE LOOP — INOPERATIVE (NR 2 ENGINE)

FLT 6137 - AMS-DXB - NR 2 ENGINE FIRE WARNING FAULT LIGHT CAME ON DURING THE TAKEOFF ROLL, ''B'' LOOP INDICATED 8 UNITS. WHEN AIRCRAFT BLOCKED IN, NR 2 ENGINE ''B'' LOOP FIRE WARNING READ 8 UNITS. FOR TROUBLESHOOTING FIRE WARNING CARDS WERE SWAPPED, BUT NO HELP. REINSTALLED CARDS IN ORIGINAL POSITIONS. REMOVED ALL CONNECTORS ON ''B'' LOOP FIRE WARNING ELEMENTS, CLEANED AND REINSTALLED. NO CHANGE IN READING. ITEM DEFERRED AS DMI 00-020 AND PLACARDED NR 2 ENGINE ''B'' LOOP FIRE WARNING INOPERATIVE PER DDPG 26-1. ACCOMPLISHED HIGH ENERGY STOP INSPECTION, NO DISCREPANCIES OBSERVED. ON 2-14-00, KUL MAINTENANCE RESEATED A11 CONTROL CARD AND PERFORMED OPERATIONAL CHECK AND SYSTEM NOW OPERATES NORMALLY. (M)

Part: BULKHEAD — CRACKED (BS 1480)

WHILE ACCOMPLISHING SB 747-53A2390, HFEC INSPECTION OF BS 1480 HOLE NR 19 REVEALED A CRACK IN THE WEB PANEL ONLY. PER SB 747-53A2390 HOLE WAS OVERSIZED TO .5625 INCH WEB PANEL ONLY. INSTALLED FREEZE PLUG. FABRICATED SEPARATE BUSHING FOR THE WEB SPLICE PLATE, BULKHEAD AND OUTER CHORD SPLICE FITTING. (M)

Part: DOUBLER — CRACKED (R1 DOOR)

R1 DOOR HINGE CUTOUT DOUBLER CRACKED, PREVIOUSLY INSTALLED AT UPPER CUTOUT. REPLACED DOOR HINGE CUTOUT DOUBLER PER SB 747-52-2144. (M)

Part: FITTING — CRACKED (NR 6 SPOILER ACT)

DURING ROUTINE INSPECTION, FOUND NR 6 SUPPORT ACTUATOR SUPPORT FITTING CRACKED ON SPOILER SUPPORT BEAM. REPLACED SUPPORT FITTING PER SRM 51-30-02. (M)

Part: DOUBLER — CRACKED (R1 DOOR)

L1 DOOR HINGE CUTOUT DOUBLER, PREVIOUSLY INSTALLED, AT THE LOWER CUTOUT FOUND CRACKED. REPLACED DOUBLER ON DOOR HINGE CUTOUT PER SB 747-52-2144. (M)

Part: STRINGER — MISDRILLED (BS 1480)

DURING ACCOMPLISHMENT OF SB 747-53A2390 FIG 19, DETAIL L, OVERSIZING HOLES AT STRINGER 39 LEFT AND RIGHT SIDES FROM .25 INCH BY .375 INCH WOULD CAUSE UNACCEPATABLE EDGE DISTANCE. PER TELEX TLS-AMS-99-00033H, PERFORMED HFEC OPEN HOLE INSPECTION, OVERSIZED HOLE BY .0625 INCH AND INSTALLED BOLT BACB30NX10K BOLT. (M)

Part: FITTING — CRACKED (BS 1480)

DURING HFEC INSPECTION OF BS 1480, FOUND LEFT OUTERCHORD SPLICE FITTING CRACKED BETWEEN HOLES NR 14 AND NR 15. REPLACED SPLICE FITTING IAW SB 747-53A2390. (M)

Part: MAP LIGHT — SMOKING (LT COCKPIT)

FLT EK9880 - AMS/DXB - APPROXIMATELY 5 HOURS IN CRUISE, CAPTAIN NOTICED SMOKE COMING FROM AREA OF CAPTAINS MAP LIGHT ASSEMBLY. THIS WAS A MOMENTARY CONDITION. THE FLIGHT CONTINUED FOR ANOTHER 4 HOURS UNEVENTFULLY. DXB MAINTENANCE INSPECTED ALL WIRING BEHIND CAPTAINS MAP LIGHT ASSY AND NO BURNING FOUND. MAP LIGHT ASSY OPERATIONS NORMALLY. (M)

Part: INS — MALFUNCTIONED (COCKPIT)

FLT AZ9204 - MXP/JFK - ATB - ALL THREE INS SYSTEMS MALFUNCTIONED. ALL PREFLIGHT FUNCTIONS WERE NORMAL, INS ALIGNED AND LOADED PROPERLY. AFTER DEPARTURE FROM MXP, UPDATED NR 1 INS USING LSA (VOR) AND GVA FOR NR 2 INS, UPDATE PROPERLY OBTAINED. A SECOND UPDATE WAS ATTEMPTED AT LBL (VOR). ALL THREE (3) INS WARNING LIGHTS APPEARED AT THE SAME TIME AND ALL EXHIBITED THE SAME FAULT CODE. ATLAS AIR OPERATIONS CONTROL CENTER. JFK REQUESTED CREW TO RETURN TO MXP, DUMPED FUEL AND RETURNED TO MXP. INS NAVIGATION UNITS REPLACED. OPERATIONS CHECKS NORMAL. NO OTHER ABNORMALITIES OBSERVED. (M)

Part: PANEL — MISSING (RT WING)

DURING WALKAROUND, FOUND 6 INCH BY 12 INCH PIECE OF RIGHT WING FUSELAGE PANEL MISSING. NO OTHER ABNORMALITIES NOTED. REPLACED PANEL P/N 65B067212. (M)

Part: PDU — DEFECTIVE (RT TE FLAP)

FLT 1358 - ANC/LAX - ATB - AFTER TAKEOFF, DURING FLAP RETRACTION, RIGHT NR 1 LEADING EDGE FLAP WOULD NOT RETRACT. TRIED TO USE ALT SYSTEM BUT LE FLAP DRIVE C/B TRIPPED. RESET CIRCUIT BREAKER AND TRIED AGAIN BUT NOT HELP. DUMPED 6,000 KILOS OF FUEL AND RETURNED TO ANC. FOUND RIGHT NR 1 LE FLAP POWER DRIVE UNIT, P/N 126344-15-1 DEFECTIVE. REPLACED PDU AND OPERATION NOW NORMAL. (M)

Part: TURNBUCKLES — FAILED (NR 3 TR UNIT)

DURING LANDING WITH REVERSE ACTIVATED, NR 3 THRUST REVERSER LEVER SNAPPED FORWARD AND NR 3 ENGINE STAYED IN FULL REVERSER. UNABLE TO REDUCE TO IDLE REVERSE. ENGINE SHUT DOWN. FOUND THE TURNBUCKLES FOR PUSH PULL CONTROL CABLE AT T3A-4 AND T3B-4 HAD COME APART. TURNBUCKLES RECONNECTED AND FULL RIGGING CHECK ACCOMPLISHED IAW MM 76-11-00. ENGINE RUN UP AND THRUST REVERSER OPERATION NOW NORMAL. (M)

Part: COUPLING — FAILED (NR 4 ENGINE)

ATB, MIA/EZE - FLT 7425/16 - 'AFTER TAKEOFF AT 1800 FEET, NR 4 ENGINE EGT JUMPED UP ABOUT 50 DEGREES, IMMEDIATELY FOLLOWED BY A FIRE WARNING...FIRE WARNING CEASED AFTER FUEL SHUT OFF TO ENGINE. COMPLETED PROCEDURES'. FOUND CLAMP ON TUBE ASSY (AFT AIR SUPPLY) AT THRUST REVERSER PNEUMATIC CHECK VALVE FAILED CAUSING DUCT TO SEPARATE FROM VALVE AND BEND OUTBOARD. (REF CF6-50 IPC 75-00-03, DUCT NR 20, PN 9057M85G02, FAILED CLAMP, NR 15, PN 9130M367P340, ALSO FOUND BRACKET ASSY, NR 45, BENT, AND MOUNT BOLT FOR BRACKET BROKEN, NR 50, PN J644P15B). RT THRUST REVERSER FOUND WITH HEAVY DAMAGE BY PRE-COOLER RAM AIR INLET CAUSED BY DUCT SEPARATION. REPLACED ALL DEFECTIVE COMPONENTS. NR 4 ENG OPERATION NORMAL. (X)