N794AJ

Part: UNKNOWN — UNKNOWN (UNKNOWN)

DAMAGE TO FLOOR STRUCTURE F/S 1148 BL RIGHT 45 WL 208. REPAIR OF DAMAGE FLOOR STRUCTURE AT F/S1148 BL RIGHT 45 WL 208. FABRICATE REPLACEMENT PARTS AND INSTALL PER SRM.

Part: BATTERY — DISCHARGED (SMOKE DETECTOR) · airframe 62,774 hrs · 48,170 cycles

CREW RECEIVED A LOWER AFT CARGO FIRE WARNING AT FL360 ON ARRIVAL INTO EFD. CREW IMMEDIATELY INITIATED THE EMERGENCY PROCEDURE AND BEGAN AN EMERGENCY DECENT AND DIVERTED TO CWF, WHICH WAS JUST SOUTH OF POSITION. THE FIRE CREW SWEPT AIRCRAFT UPON LANDING AND NO EVIDENCE OF FIRE WAS FOUND. LOWER CARGO DETECTION SYSTEM WAS TESTED AND FOUND THAT ONE DETECTOR HAD LOW BATTERY WHICH WAS REPLACED. SUBSEQUINT TESTING OF SYSTEM FOUND NO ADDITIONAL FAULTS AND SYSTEM TESTS PASSED.

Part: DUCT — CRACKED (ZONE 400) · airframe 62,562 hrs · 48,035 cycles

ON CLIMB APPROXIMATELY 1500' #3 ENGINE HAD FIRE WARNING. ACCOMPLISHED CHECKLIST. LIGHT EXTINGUISHED DID NOT FIRE BOTTLE. RETURNED TO KFLL. ON VISUAL INSPECTION OF ENGINE IT WAS FOUND THAT THE BLEED AIR DUCT HAD RUPTURED/CRACKED.

Part: STIFFENER — CRACKED (LT WING)

L/H WING FRONT SPAR VERTICAL STIFFENER CRACKED AT W/STA 255L. TO REPLACE A CRACKED VERTICAL STIFFENER ON THE LEFT WING FRONT SPAR WEB AT W/STA 254. REPLACE VERTICAL STIFFENER PER EA 20-2021-008. OBTAIN DTA WITHIN 12 MONTHS.

Part: SKIN — CORRODED (LT ELEVATOR TE)

CORROSION ON L/H ELEVATOR OUTBOARD TRAILING EDGE. TO REPAIR CORRODED ELEVATOR SKIN AT THE TRAILING EDGE IN THE STATIC WICKS AREA. PERFORM REPAIR OF ELEVATOR TRAILING EDGE PER STS ENGINEERING AUTHORIZATION 80-2021-016 AND 80-2021-015. OBTAIN DTA WITHIN 12 MONTHS.

Part: WEB — DAMAGED (LT AILERON) · airframe 62,415 hrs · 47,951 cycles

DAMAGE WEB AT L/H AILERON TAB HINGE ASSEMBLY. TO PREFORM SPLICE ON A DAMAGED WEB SUPPORTING THE L/H OUTBOARD AILERON TRIM ROD HINGE ASSEMBLY.REMOVE AILERON TRIM ROD HINGE ASSEMBLY. REPAIRE DAMAGE WEB PER B727 SRM 51-40-02 TYPICAL WEB REPAIR. INSTALL AILERON TRIM HINGE ASSEMBLY.

Part: SKIN — DELAMINATED (LT AILERON)

DELAM ON LH AILERON COMPOSITE TRAILING EDGE. TO REPAIR DELAMINATION ON AILERON TRAILING EDGE. REPAIR AILERON TRAILING EDGE PER B727 SRM 51-40-20 GENERAL REPAIR - ALUMINUM HONEYCOMB REPAIRS - 250 DEGREE FAHRENHEIT (121 DEGREE CELSIUS) CURE.

Part: STRINGER — CORRODED (FUSELAGE)

CORRODED FUSELAGE STRINGER AT F/STA 443, STRINGER 11R. TO REPAIR A CORRODED FUSELAGE STRINGER AT F/STA 443, 11 RIGHT. CUT OUT DAMAGED AREA AND PERFORM REPAIR PER DC-6A&B OVERHAUL MANUAL FIGURE 12-2.

Part: HINGE FITTING — CORRODED (LT WING LE FLAP)

CORRODED HINGE FITTING FOR L/H WING #1 LEADING EDGE FLAP AT W/STA 283L. TO REMOVE AND REPLACE A CORRODED FITTING ON #1 LEADING EDGE FLAP (W/STA 283L). REMOVE CORRODED FITTING. MANUFACTURE NEW FITTING PER DRAWINGS NUMBER 65-16273 AND BAC 1508-128. INSTALL NEW FITTING PER B727 SRM 51-30-2.

Part: STRINGER CLIP — CORRODED (ZONE 100)

CORRODED CLIP AT STRINGER 17L, F/STA 1186 BULKHEAD. TO REPLACE A CORRODED CLIP AT FUESLAGE STRINGER 17L, F/STA 1186. REMOVE AND REPLACE CORRODED STRINGER CLIP.

Part: STRINGER CLIP — CORRODED (ZONE 100)

CORRODED CLIP AT STRINGER 19L, F/STA 1186 BULKHEAD. TO REPLACE A CORRODED CLIP AT FUSELAGE STRINGER 19L, F/STA 1186. REMOVE AND REPLACE CORRODED STRINGER CLIP.

Part: HINGE FITTING — CORRODED (LT WING LE FLAP)

OUTBOARD HINGE FITTING CORRODED FOR L/H WING #2 LEADING EDGE FLAP AT W/STA 269L. TO REMOVE AND REPLACE A CORRODED FITTING ON #2 LEADING EDGE FLAP (W/STA 269L). REMOVED CORRODED FITTING. MANUFACTURE NEW FITTING PER DRAWINGS NUMBER 65-16271 AND BAC1508-128. INSTALL NEW FITTING PER B727 SRM 51-30-2.

Part: STRINGER CLIP — CORRODED (ZONE 100)

CORRODED CLIP AT STRINGER 18L, F/STA 1186 BULKHEAD. TO REPLACE A CORRODED CLIP AT FUSELAGE STRINGER 18L, F/STA 1186. REMOVE AND REPLACE CORRODED STRINGER CLIP.

Part: SUPPORT BRACKET — CRACKED (LT SPOILER)

LEFT WING #3 FLIGHT SPOILER ACTUATOR SUPPORT BRACKETS CRACKED, INBRD AND OUTBRD. REPALACED LEFT WING #3 SPOILER ACTUATOR BRACKETS (BOTH). REMOVED AND REPLACE LEFT WING #3 SPOILER ACTUATOR BRACKETS P/N 65-24608-17 OUTBOARD BRACKET, AND P/N 65-24608-19 INBOARD BRACKET.

Part: SPAR — CORRODED (LT WING)

CORROSION ON AFT WING SPAR LOWER CHORD BETWEEN LBBL 19.2 AND WS 210L. CORROSION WAS FOUND ON THE AFT WING SPAR LOWER CHORD CENTER SECTION AND LT SECTION. SPLICES WILL BE PERFORMED AT LBBL 19.2 ON THE CENTER WING SECTION AND AT WS 210 ON THE LT WING SECTION. PERFORM AFT WING SPAR LOWER CHORDS SPLICES PER DRAWINGS AND EAC EO 1920. NOTE: FINAL APPROVAL OF THIS EO WILL BE PROVIDED ONCE PROVIDES FORM FAA 8110-3 AT THE REPAIR COMPLETION.

Part: MOUNT — CORRODED (NR 2 ENGINE)

REPLACEMENT OF CORODED #2 ENGINE MOUNT FITTING. TO REPLACE CORRODED AFT ENGINE MOUNT FITTING AND TEE CHORDS AT #2 ENGINE POSITION. REMOVE AND REPLACE #2 ENGINE SUPPORT FITTING P/N 65-18670-1, CHORDS P/N 65-31281-3, 65-31281-4, 65-22913-5, 65-22913-6, AND WEB OF #2 ENGINE MOUNT SUPPORT STRUCTURE.

Part: DOOR FRAME — CORRODED (MAIN CARGO DOOR)

MAIN CARGO DOOR JAMB INNER SKIN REPLACEMENT. TO REPLACE THE MAIN CARGO DOOR JAMB INNER SKIN (FORWARD LOWER SECTION AT F/STA 520) FOR CORROSION DAMAGE. REMOVE AND REPLACE CORRODED SECTIO OF DOOR JAMB PER B727 SRM 51-30-2.

Part: SPAR — DAMAGED (LT WING)

CENTER WING SPAR TEMPORARY REPAIR FOR FERRY FLIGHT. TEMPORARY REPAIR FOR DAMAGE TO CENTER WING AFT SPAR LOWER CAP FOR FERRY FLIGHT TO INSTALL PERMANENT REPAIR. 727-227 LEFT HAND WING REPAIR TEMPORARY. S/N 21243.

Part: SKIN — CORRODED (FUSELAGE)

FUESLEAGE SKIN REPLACEMENT BETWEEN F/STA 259.5 AND 360 STRINGER 19L AND 26L. TO REPLACE A CORRODED SKIN BETWEEN F/STA 259.5 AND 360, FROM STRINGER 20L AND 25L. REMOVE AND REPLACE CORRODED SKIN PER SRM.

Part: STRINGER — CORRODED (BS 950)

CORRODED FUSELAGE LONGERON #27R F/STA 950. TO REPAIR A CORRODED STRINGER. REMOVE CORROSION AND INSTALL REPAIR PER B727 SRM 51-40-4.

Part: BEAM — CORRODED (LT HORIZ STAB) · airframe 62,240 hrs

CORROSION ON LT HORIZONTAL STABILIZER UPPER TRAILING EDGE BEAM. TO REPAIR A CORRODED HORIZONTAL STABILIZER TRAILING EDGE BEAM. CUT DAMAGED BEAM AT STA 82.5 AND SPLICE IN NEW OUTBOARD SECTION PER SRM 55-10-6 FIGURE 1 HORIZONTAL STABILIZER T.E. BEAM REPAIR.

Part: BEAM — CORRODED (RT HORIZ STAB) · airframe 62,240 hrs

CORROSION ON RT HORIZONTAL STABILIZER LOWER TRAILING EDGE BEAM. TO REPAIR A CORRODED HORIZONTAL STABILIZER TRAILING EDGE BEAM. CUT DAMAGED BEAM AT STA 88.29 AND SPLICE IN NEW OUTBOARD SECTION PER SRM 55-10-6 FIGURE 1 HORIZONTAL STABILIZER T.E. BEAM REPAIR.

Part: BEAM — CORRODED (LT HORIZ STAB) · airframe 62,240 hrs

CORROSION ON LT HORIZONTAL STABILIZER LOWER TRAILING EDGE BEAM. TO REPAIR A CORRODED HORIZONTAL STABILIZER TRAILING EDGE BEAM. CUT DAMAGED BEAM AT STA 78.29 AND SPLICE IN NEW OUTBOARD SECTION PER SRM 55-10-6 FIGURE 1 HORIZONTAL STABILIZER T.E. BEAM REPAIR.

Part: BEAM — CORRODED (RT HORIZ STAB) · airframe 62,240 hrs

CORROSION ON RT HORIZONTAL STABILIZER UPPER TRAILING EDGE BEAM. TO REPAIR A CORRODED HORIZONTAL STABILIZER TRAILING EDGE BEAM. REMOVE AND REPLACE CORRODED BEAM WITH NEW PER SRM 51-30-2 FASTENER REMOVAL AND INSTALLATION.

Part: CROSSBEAM — CRACKED (FUSELAGE)

CRACK ON CROSS BEAM STA 856-850 @ LBL 45.50. TO REPAIR A CRACKED WEB ON A FLOOR CROSS BEAM. THE CRACK IS LOCATED BETWEEN F/SAT 850 AND 856 AT LBL 45.50. PERFORM REPAIR OF CRACKED WEB PER REPAIR DRAWING #E2499-001. DTA MUST BE OBTAINED WITHIN 12 MONTHS.

Part: SKIN — CORRODED (FUSELAGE)

CORROSION AT RT WING ILLUMINATION LIGHT. TO REPAIR A CORRODED SKIN BETWEEN F/STA 720B AND 720C AND LONGERON S-14R AND S-16R. REPAIR CORRODED SKIN PER SRM 53-30-3 FIGURE 22. SEE PAGE 2 FOR RE-INSPECTION REQUIREMENTS.

Part: FLOORBEAM — CORRODED (FUSELAGE)

CORROSION ON O/B END STA 880 FLOORBEAM LOWER CHORD @ RBL 68. CORROSION ON OUTBOARD END OF STA 880 FLOORBEAM LOWER CHORD AT RBL 68. CUT OUT AND REMOVE DAMAGE, REPAIR PER SRM 53-10-08 FIGURE 8. RE-INSPECTION REQUIREMENTS: HFEC REQUIRED. INITIAL: 55,000 CYCLES AFTER REPAIR INSTALLATION RECURRENT: 18,000 CYCLES.

Part: CONTROLLER — FAILED (CABIN PRESSURE) · airframe 61,866 hrs · 47,633 cycles

AIRCRAFT DEPRESSURIZED IN THE MIDDLE OF A PARABOLA. DESCENT WAS INITIATED AT FIRST INDICATION OF DEPRESSURIZATION. MAXIMUM ALTITUDE REACHED WAS FLIGHT LEVEL 310. FOUND THAT THE CABIN PRESS CONTROLLER HAD FAILED.

Part: WIRE HARNESS — BROKEN (ZONE 400) · airframe 61,830 hrs · 47,606 cycles

DURING CRUISE FLIGHT NR 3 ENG FIRE INDICATION. PROCEDURE & CHECKLIST INITIATED. BOTH ENG FIRE BOTTLE DEPLOYED. FIRE INDICATION REMAINED ON. ALL ENG PARAMETERS NORMAL EXCEPT ENG OIL TEMP AT RED LINE. ENG FIRE INDICATION REMAINED ON UP TO SECURING AIRPLANE & POWER REMOVED.

Part: WARNING LIGHT — ILLUMINATED (COCKPIT) · airframe 61,707 hrs · 47,530 cycles

DURING CLIMB OUT, LOWER AFT BODY OVERHEAT LIGHT ILLUMINATED. ACCOMPLISHED CHECKLIST & RETURNED TO KTIX.

Part: ENGINE — POWER LOSS (NR 2) · airframe 61,406 hrs · 47,358 cycles

DURING CLIMBOUT THE NR 2 ENGINE LOSS POWER.

Part: HYDRAULIC LINE — RUPTURED (HYDRAULIC SYS) · airframe 61,258 hrs · 47,272 cycles

CLIMBING THROUGH 12000FT B-SYSTEM 2 PUMP LOW PRESS LIGHT FLICKERED FOLLOWED BY A-SYSTEM FLUID DECREASING TO 2.5 GALLONS AND B-SYSTEM FLUID DECREASING TO 0. APPROPRIATE CHECKLIST INITIATED AND RETURNED TO BASE WITHOUT INCIDENT. AN EMERGENCY WAS NOT DECLARED. MAINTENANCE REPLACED THE RUPTURED B-SYSTEM NR 2 HYDRAULIC PUMP PRESSURE LINE, SERVICED THE HYDRAULIC SYSTEMS AND PERFORMED AN OPERATIONAL AND LEAK CHECK.

Part: REGULATOR VALVE — LEAKING (HYDRAULIC SYS) · airframe 61,223 hrs · 47,251 cycles

DURING PARABOLA NUMBER 2 STRONG SMELL IN FLIGHT DECK AND CABIN AFTER NUMBER 5. COULD NOT IDENTIFY AND RETURNED TO BASE. MAINTENANCE FOUND THE SMELL TO BE SKYDROL FROM THE HYDRAULIC RESERVOIR PRESSURE REGULATOR LEAKING INTO THE PRESSURIZING LINE. THE LINES WERE FLUSHED AND THE REGULATOR WAS REPLACED.

Part: COMPRESSOR — FAILED (NR 1 ENGINE)

DURING CLIMB BETWEEN 180 TO 210 FLIGHT LEVEL NR 1 ENG COMPRESSOR STALL FOLLOWED BY OIL TEMP RISE. AFTER SECOND COMPRESSOR STALL NR 1 ENG OIL PRESS LIGHT ILLUMINATED. ENG WAS SHUT DOWN PER AOM. NR 1 ENG OPERATED APPROX 9 MINUTES OIL PRESS ABOUT 20 PSI. POST FLIGHT INSPECTION REVEALED NO INLET OR EXHAUST DAMAGE. THE NR 1 AND NR2 COMPRESSORS WOULD NOT ROTATE. THE ACFT WAS RELEASED FOR A TWO ENG FERRY TO KMIA. (S)

Part: DETECTION SYS — FALSE INDICATION (NR 3 STRUT)

FLIGHT 819 DEPARTED FROM MIA, WHILE IN CRUISE AT THE ASSIGNED ALTITUDE (ONE HOUR OUT ) THE CREW REPORTED THE NUMBER 3 STRUT OVERHEAT LIGHT ILLUMINATED, THE CREW PERFORMED THE ABNORMAL PROCEDURES, THE NUMBER 3 STRUT OVERHEAT LIGHT WENT OUT. THE AIRCRAFT RETURNED TO MIA AND LANDED WITHOUT ANY FURTHER INCIDENT. MAINTENANCE PERFORMED AN INSPECTION AND TEST OF THE NUMBER 3 STRUT OVERHEAT SYSTEM IAW THE B-727 MM CH 26-11-00 AND 71-00, NO DISCREPANCIES WERE NOTED. THE AIRCRAFT WAS RETURNED TO CARGO SERVICE AND DISPATCHED WITHOUT FURTHER INCIDENT.

Part: ACTUATOR — BYPASSING (MLG DOOR)

FLIGHT 8413 DEPARTED MIA WHILE IN THE CLIMB THE CREW REPORTED THE LEFT HAND MAIN LANDING GEAR DOOR WARNING LIGHT CAME ON AFTER THE LANDING GEAR SELECTOR HANDLE WAS MOVED FROM THE GEAR UP POSITION TO THE OFF POSITION. THE AIRCRAFT RETURNED BACK TO MIA AND LANDED WITHOUT FURTHER INCIDENT. AFTER TROUBLESHOOTING THE PROBLEM, MAINTENANCE FOUND THE LEFT HAND MAIN LANDING GEAR DOOR ACTUATOR BYPASSING. THE ACTUATOR WAS REMOVED AND REPLACED IAW B-727 MM CH 32-32-81, A LEAK CHECK AND A FUNCTIONAL CHECK WAS ACCOMPLISHED AND FOUND GOOD IAW B-727 MM CH 32-32-81. AFTER THE REPAIRS WERE COMPLETED THE AIRCRAFT WAS RETURNED TO SERVICE.

Part: PCU — MALFUNCTIONED (ELEVATOR) · airframe 57,868 hrs · 45,317 cycles

ON TAXI OUT CONTROL YOKE JAMMED WILL NOT MOVE FWD. AC RETURNED TO RAMP. AIRCRAFT WAS FERRIED BACK TO MIAMI. NO DEFECTS REPORTED ON FLIGHT. REMOVED FLOOR PANEL, INSPECTED CONTROL CABLES EBL, EAL, EBR, EAR & PULLEYS BS 540, 740, 870, 950 & 1050 NO DEFECTS. OPEN PANELS ON TOP OF VERTICAL STAB TO GAIN ACCESS FOR INSPECTION OF CABLES AND PULLEYS, NO DEFECTS. OPEN LH & RH PANEL TO ELEVATOR PCU'S FOUND COLLAR MISSING FROM THRU BOLTS AT RH PCU TAB ROD REACTION LINK, REMOVED & REPLACED ELEVATOR PCU. INSPECTED LH & RH ELEVATOR TAB CONTROL ROD FOR CORRECT INSTALLATION PER BOEING ISAR 97-06-2735-10. CASTELLATED NUTS & COTTER PINS INSTALLED IAW SPM 20-50-01/2 & IPC 27-30-00-31. TEST FLT PERFORMED WITH NO DEFECTS.

Part: CHIP DETECTOR — MISSING (NR 2 ENGINE)

EN ROUTE TO MEXICO, THE NR 2 OIL QUANTITY DECREASED TO ZERO FOLLOWED BY A DROP IN OIL PRESSURE. PRECAUTIONARY SHUT DOWN NR 2 ENGINE. AIRCRAFT DIVERTED BACK TO MMMD AND LANDED WITHOUT FURTHER INCIDENT. MAINTENANCE INSPECTED NR 2 ENGINE AND FOUND NR 4 BEARING CHIP METAL DETECTOR OFF. RE-INSTALLED CHIP DETECTOR PLUG LEAK CHECK GOOD IAW MM 72-00 AND PWA SERVICE BULLETIN 39-08. ENGINE SERVICED PER MM 12-13-1. AIRCRAFT RETURNED BACK TO SERVICE. (M)

Part: ENGINE — MALFUNCTIONED (NR 3)

FLT 813 - KMIA-TBPB - AFTER DEPARTURE FORM KMIA, NR 3 OIL PRESSURE INDICATED ABOVE ARC LINE, AND THEN OIL TEMP BEGAN CLIMBING AND WENT ABOVE ARC LINE. SHUT OFF NR 3 ENGINE AS PER PROCEDURES. AIRCRAFT DIVERTED BACK TO KMIA AND LANDED WITHOUT FURTHER INCIDENT. MAINTENANCE FOUND NR 3 ENGINE OIL OVER SERVICED. DRAINED OIL SYSTEM AND REMOVED OIL FILTER. INSPECTED FILTER AND FOUND NO CONTAMINATION. REPLENISHED OIL TANK WITH 19 QTS PER MM 12-13-1 AND 79-00 PAGE 301. RAN ENGINE AT TAKEOFF POWER FOR FIVE MINUTES. OIL TEMP STAYED 85 DEGREES OIL PRESSURE AT 55 PSI. ALSO, RAN ENGINE AT DIFFERENT POWER SETTINGS OIL PARAMETERS WITHIN LIMITS. CHECKED OPERATIONAL OF FUEL HEAT VALVE AT 1.4 EPR. VALVE OPERATION NORMAL

Part: FUEL CONTROL — CONTAMINATED (NR 1 ENGINE)

AFTER DEPARTURE FROM KMIA, NR 1 ENGINE RPM BEGAN TO INCREASE AND DECREASE DURING CLIMB OUT. AIRCRAFT DIVERTED BACK TO KMIA AND LANDED WITHOUT FURTHER INCIDENT. MAITNENANCE INSPECTED NR 1 ENGINE INLET AND EXHAUST IAW CHAPTER 71-00. NO DAMAGE FOUND, INSPECTED FCU AND FOUND WATER IN MOISTURE TRAP. MAINTENANCE CLEANED AND LUBE BELOW IAW MM CHAPTER 73-21-01. PERFORMED RUN UP IAW MM CHAPTER 71-00, OPS CHECK GOOD. AIRCRAFT RETURNED BACK SERVICE. (M)

Part: BLADE — DAMAGED (COMPRESSOR)

IN FLIGHT NR 3 ENGINE COMPRESSOR STALLED TWICE AND HAD HIGH EGT INDICATION. ENGINE NR 3 WAS SHUTDOWN IN FLIGHT AND FLIGHT CONTINUED TO KMIA WITHOUT FURTHER INCIDENT. MIA MAINTENANCE INSPECTED ENGINE NR 3 AND FOUND THE C-9 THROUGH C-13 BLADES DAMAGED. ENGNE WAS REMOVED AND REPLACED IAW AMJ FORMS B-48 AND B-49. MAINTENANCE PERFORMED LEAK CHECKS AND OPERATIONAL CHECKS NORMAL IAW AMJ FORM B-41. AIRCRAFT WAS RETURND TO SERVICE. (M)

Part: OIL CAP — LOOSE (NR 2 ENGINE)

FLT 835 - KMIA/UVF - CAPTAIN REPORTED, NR 2 ENGINE OIL QUANTITY INDICATED 1.5 WHILE INFLIGHT. LOW OIL QUANTITY LIGHT DID NOT ILLUMINATE. AIRCRAFT DIVERTED TO SJU AND LANDED WITHOUT FURTHER INCIDENT. MAINTENANCE FOUND NR 2 ENGINE OIL CAP NOT SECURED. ENGINE OIL WAS SERVICED. OIL CAP REPLACED AND SECURED WITH SAFETY WIRE IAW MM 12-13-01. AIRCRAFT RETURNED BACK SERVICE. (M)

Part: FITTING — WORN (LT & RT WING)

LEFT AND RIGHT WING - FITTINGS WITH WEAR. LOCATED AT WBL 297.3 OUTBOARD ACTUATOR SCREW FAIRING.

Part: STRUCTURE — CORRODED (RT WING AILERON)

RIGHT WING OUTBOARD AILERON TRAILING EDGE (PN 652176634) (SN 226) UPPER, LOWER SKIN AND HONEYCOMB CORE, CORRODED.

Part: STRUCTURE — DELAMINATED (RT WING LE FLAP)

RIGHT WING OUTBOARD FORE FLAP (PN 65-21631-274) (SN BN386) UPPER SKIN AND HONEYCOMB CORE DELAMINATED SECTION.

Part: SKIN — CORRODED (RT WING)

RIGHT WING, LOWER SKIN - LOWER SURFACES CORRODED AT WS 637, BETWEEN STIFFENER NR 8 AND STIFFENER NR 9.

Part: FITTING — CORRODED (LT WING)

LEFT WING MAIN LANDING GEAR, REAR SPAR TRUNNION ATTACH FITTING CORRODED.

Part: RETAINER — CRACKED (CARGO DOOR)

AFT CARGO COMPARTMENT, NR 2 CARGO DOOR - FORWARD AND AFT LOWER CORNER (SEAL DEPRESSOR) CRACKED.

Part: DOOR FRAME — CRACKED (LT MLG)

LEFT MAIN LANDING GEAR, WING DOOR AFT FRAME CRACKED.

Part: BEAM — CORRODED (FUSELAGE)

BS 740 BULKHEAD, HORIZONTAL CHORD CORRODED, LOCATED AT WL 170 BETWEEN LBL 40 INCHES AND RBL 40 INCHES.

Part: STRUCTURE — CORRODED (SPOILERS)

RT WING, SPOILER NR 8 (PN 65-17348-74C) (SN 6114W) UPPER, LOWER SKIN AND HONEYCOMB CORE CORRODED.

Part: SKIN — DELAMINATED (LT WING TE FLAP)

LEFT WING OUTBOARD AFT FLAP (PN 65-21635-85) (SN BN486) UPPER AND LOWER SKIN DELAMINATED.

Part: FRAME — CORRODED (FUSELAGE)

AFT CARGO COMPONENT LOWER CHORD CORRODED AT BS 950 BULKHEAD, BETWEEN S-26L AND S28L.

Part: STIFFENER — CRACKED (FUSELAGE)

BS 1183 AFT PRESSURE BULKHEAD, STIFFENERS CRACKED, LOCATED AT WL 227 LEFT AND RIGHT SIDE.

Part: FLOORBEAM — CORRODED (MAIN CARGO CABIN)

MAIN CARGO CABIN BS 1130 LOWER CHORD CORRODED.

Part: STRUCTURE — CORRODED (RT WING TE FLAP)

RIGHT WING INBOARD AFT FLAP (PN 65-21634-80) (SN BN375) UPPER, LOWER SKIN AND HONEYCOMB CORE CORRODED.

Part: STRUCTURE — DELAMINATED (LT WING LE FLAP)

LEFT WING INBOARD FORE FLAP (PN 652130-188) (SN BN720) UPPER, LOWER SKIN AND HONEYCOMB CORE DELAMINATED SECTION.

Part: SKIN — CORRODED (FUSELAGE)

FUSELAGE SKIN CORRODED LOCATED FROM BS 920 TO BS 923, STR 18A LEFT LEVEL.

Part: ACCESS PANEL — DELAMINATED (FUSELAGE)

AIR CONDITION BAY ACCESS PANEL (PN 65-58513-12) INNER SKIN DELAMINATED.

Part: INSULATION — LOOSE (FIRE LOOP)

CAPTAIN REPORTED LOWER AFT BODY OVERHEAT LIGHT CAME ON AFTER DEPARTURE. AIRCRAFT RETURNED AND PERFORMED AN OVERWEIGHT LANDING WITHOUT FURTHER INCIDENT. MAINTENANCE RESET INSULATOR AT FIRE LOOP. OPS CHECK NORMAL IAW.

Part: FUEL PUMP — FAILED (NR 1 ENGINE)

DURING CRUISE NR 1 ENGINE FLAMED OUT AND WOULD NOT RESTART. AIRCRAFT LANDED AT DESTINATION AIRPORT. AFTER TROUBLESHOOTING FOUND ENGINE DRIVED FUEL PUMP DEFECTIVE. REPLACED PUMP, OPS CHECK OK.