N934DL

Part: TRANSFORMER — DAMAGED (CABIN) · airframe 74,177 hrs · 55,915 cycles

FUME EVENT AT CRUISE. SMELLED ELECTRICAL BUT COULD NOT ISOLATE. WENT AWAY AFTER 5 MIN APPROX. MAYBE ASSOCIATED WITH ENG ANTI ICE. ON DESCENT RETURNED COMPLIED WITH QRH. SEEMED TO DISSIPATE AFTER RIGHT PACK/ AND RECIRC FAN/ GND SVC BUS C/B'S PULLED. ON GND FUME SMELL RETURNED. MAYBE ASSOCIATED WITH PACKS. T/S PER WORK CARD 2120-2367 ITEM 1&2. FOUND ISLE LIGHTING TRANSFORMER T1-1 DAMAGED. REPLACED PER AMM 20-50. OPS CK GOOD PER AMM 33-21. TOOK AIRCRAFT OUT FOR TAKE OFF POWER RUN VERIFIED NO ODOR. APU AND SURROUNDING AREA SHOW NO SIGNS OF CONTAMINATION. INSPECTED COALESCER BAGS AND REPLACED SAME. NO SIGNS OF CONTAMINATION. OK FOR SVC.

Part: SENSOR — FAILED (LT WING SLAT) · airframe 74,120 hrs · 55,865 cycles

SLAT DISAGREE WARNING LIGHT ILLUMINATED. COMPLIED WITH TAKEOFF WARNING TEST, NO FAULTS, CHECKED PSEU AND SIF COMPUTERS, ALL CHECK GOOD. DFDR REMOVED. LT WING SLAT C SENSOR FOUND FAILED. REPLACED SENSOR AND ADJUSTED OTHER SENSORS. REPLACED NR 2 STALL WARNING COMPUTER. COMPLETED HIGH ENERGY STOP INSPECTION DUE TO HIGH SPEED ABORTED TAKE-OFF. NO ADDITIONAL FINDINGS.

Part: BATTERY PACK — INOPERATIVE (EMERGENCY LIGHTS) · airframe 70,955 hrs · 53,473 cycles

THE FLIGHT CREW FOUND THAT THE EMERGENCY LIGHTS WOULD NOT ILLUMINATE WHEN TESTED. MAINTENANCE REPLACED EMERGENCY LIGHT BATTEY PACKS AND THE LIGHTS CHECKED OK.

Part: SKIN — DAMAGED (BS 750-769) · airframe 70,941 hrs · 53,461 cycles

LIGHTNING STRIKE ON WINDOW FRAME BETWEEN BS 750 TO 769 AND LONGERONS 12RT TO 13RT. REWORKED AREAS WERE MEASURED, UT WAS ACCOMPLISHED IAW NDT SPM 04-00-07, PAR 5, FIG 3, SHEET 1 AND 2. BLEND OUTS ON ZONE CRITICAL, THE ORIGINAL THICKNESS ON BLEND OUT 1 IS .086" AND REMAINING THICKNESS .083" THE ORIGINAL THICKNESS BLEND OUT, 2 IS .085" AND REMAINING THICKNESS .082", THE ORIGINAL THICKNESS BLEND OUT 3 IS .085" AND REMAINING THICKNESS .082" THE ORIGINAL THICKNESS ON BLEND OUT 5 IS .086" AND REMAINING THICKNESS .082", THEREFORE ALL AREAS ARE WITHIN OF LIMITS IAW ER/A 545081-14, REV ORIGINAL HFEC INSPECTION WITHIN EVERY 24 MONTHS AFTER SECTION I UNTIL SECTION III IS ACCOMPLISHED.

Part: SKIN — DAMAGED (BS 731-750) · airframe 70,941 hrs · 53,461 cycles

LIGHTNING STRIKES ON WINDOW FRAME BETWEEN BS 731 TO BS 750 AND LONGERONS 12 RT TO 13 RT. REWORKED AREAS WERE MEASURED (UT) WAS ACCOMPLISHED IAW NDT SPM 04-00-07, PARAGRAPH 5, FIG 3, SHEET 1 AND 2. BLEND OUT ON ZONE CRITICAL, 1 IS .090" AND REMAINING THICKNESS .085" THEREFORE AREA ARE WITHIN OF LIMITS IAW ERA 545080-14, REV A. HFEC INSPECTION WAS ACCOMPLISHED AND CRACKS WERE NOT FOUND IAW ER/A 545080-14, REV A.

Part: SKIN — DAMAGED (BS 647-693) · airframe 70,941 hrs · 53,461 cycles

LIGHTNING STRIKES, FOUR ON WINDOW FRAME BETWEEN BS 674 TO 693 AND LONGERONS 14TO 15R. MEASURE REWORKED AREAS, UT) WAS ACCOMPLISHED IAW DC/MD NDT SPM 04-00-07 PAR 5, FIG 3, SHEET 1 AND 2. BLEND OUT ON ZONE CRITICAL BLEND OUT, 2 THE ORIGINAL THICKNESS ES .120 AND REMAINING THICKNESS .115. THEREFORE AREA IS WITHIN LIMITS IAW ER/A 545077-14, REV ORIG. HFEC WAS ACCOMPLISHED AND CRACKS WERE NOT FOUND I.A.W ER/A 545077-14. REV ORG. PERFORM HFEC INSPECTION WITHIN EVERY 24 MONTHS AFTER SECTION I UNTIL ACCOMPLISHED OF SECTION III. PERFORM PERMANENT REPAIR ON OR BEFORE 84,500 TOTAL FLIGHT CYCLES, THIS INSPECTION WILL BE MONITORED UNDER LOG PAGE 2412695.

Part: SKIN — DAMAGED (BS 1100) · airframe 70,941 hrs · 53,461 cycles

LIGHTING STRINKE ON LOWER WINDOW FRAME, BS 1100 RT SIDE. REWORKED AREAS WERE MEASURED, UT WAS ACCOMPLISHED IAW NDT SPM 04-00-07, PAR 5, FIG 3, SHEET 1 AND 2. BLEND OUT ON ZONE CRITICAL, 1 THE ORIGINAL THICKNESS IS .084" AND REMAINING THICKNESS .080", THE ORIGINAL THICKNESS ON BLEND OUT 3 IS .095" AND REMAINING THICKNESS .090", THEREFORE AREAS ARE WITHIN OF LIMITS IAW ER/A 545082-14, REV ORIGINAL HFEC INSPECTION WAS ACCOMPLISHED AND CRACKS WERE NOT FOUND IAW ER/A 545082-14, REV ORIGINAL. PERFORM HFEC INSPECTION WITHIN EVERY 24 MONTHS AFTER SECTION I UNTIL SECTION III IS ACCOMPLISHED.

Part: SKIN — DENTED (LT WING TE FLAP) · airframe 70,941 hrs · 53,461 cycles

SEVERAL DENTS ON LOWER SKIN, BELOW OF REPAIR DOUBLER OF LT WING OTBD FLAP INBD GUIDE VANE. LOWER SKIN OF LT WING OTBD FLAP INBD GUIDE VANE WAS REPAITED IAW SRM 57-03D, PAR II.

Part: DOOR — CRACKED (THRUST REVERSER) · airframe 70,941 hrs · 53,461 cycles

SEVERAL CRACK ON HOLES OF OUTER SKIN AT LT ENGINE THRUST REVERSE UPPER DOOR. SKIN AT LT ENGINE TRUST REVERSE UPPER DOOR WERE REPAIRED IAW AMM 78-30-07-801.

Part: STRAP — CORRODED (DOOR FRAME) · corrosion level 2 · airframe 70,941 hrs · 53,461 cycles

CORROSION ON REPAIR STRAP ON LOWER AT AFT CARGO COMPARTMENT DOOR JAMB BETWEEN BS 1155 TO BS 1212. STRAP WAS REPLACED IAW ER/A 457309-14, REV A AND SRM 53-05, FIG 123A.

Part: SKIN — CORRODED (FUSELAGE) · airframe 72,530 hrs · 54,690 cycles

CORROSION BTW FUSELAGE SKIN AND DOUBLER ON LOWER CORNER AT AFT LAVATORIES SERVICE PANEL CUT OUT. REMOVED CORROSION AREAS, MEASURE: ORIG, MATERIAL THICKNESS IS 0.063" REMAINING THICKNESS IS 0.055". REPAIRED PER ER/A.

Part: SKIN — DEFORMED · airframe 70,941 hrs · 53,461 cycles

DEFORMED FUSELAGE SKIN AND DOUBLERS ON LOWER AND FWD, AFT CORNERS AT AFT LAVATORY SERVICE PANEL CUTOUT. REPAIRED LOWER FWD CORNER IAW ERA 397822-14 MA, REV B.

Part: ACCESS PANEL — CORRODED (RT WING) · corrosion level 2 · airframe 70,941 hrs · 53,461 cycles

CORROSION ON SEATING AREA AND COUNTERSINK ON FUEL ACCESS PLATE 1409C AT RT WING. ACCESS PLATE REPLACED.

Part: CARGO TRACK — CORRODED (BS 1220-1320) · corrosion level 2 · airframe 70,941 hrs · 53,461 cycles

CORROSION ON LT CARGO TRACK BETWEEN BS 1220 - 1320. THE CARGO TRACK WAS REPLACED IAW SRM 51-10-4 AND 51-30-01 AND 51-30-5.

Part: FLOOR PANEL — CRACKED (COCKPIT) · airframe 70,941 hrs · 53,461 cycles

CRACK ON FLOOR PANEL BETWEEN CAPTAIN SEAT AND COLUMN AT LT COCKPIT. FLOOR PANEL WAS REPLACED IAW SRM 51-10-03, 51-10-04 ON 51-30-01.

Part: DOOR FRAME — CORRODED (CARGO BAY) · corrosion level 2 · airframe 70,941 hrs · 53,461 cycles

CORROSION ON LOWER DOOR JAMB BEAM AT MID CARGO COMPARTMENT. PREVIOUS REPAIR SPACER WAS REPLACED IAW SRM 53-05, FIG 123A AND ERA 504344-14, REV ORIGINAL.

Part: DOOR FRAME — CRACKED (EMERGENCY EXIT) · airframe 70,941 hrs · 53,461 cycles

CRACK ON UPPER CENTER DOOR JAMB AT LT FWD EMERGENCY EXIT. CRACK ON UPPER DOOR JAMB LT WAS REPAIRED IAW SRM 53-05, FIG 32.

Part: LONGERON — CORRODED (BS 1231-1240) · corrosion level 2 · airframe 70,941 hrs · 53,461 cycles

CORROSION ON LONGERON 28LT BETWEEN BS 1231 TO BS 1240 AT AFT CARGO COMPARTMENT. FASTENERS AND CORROSION WERE REMOVED, REWORKED AREA WITHIN LIMITS WAS TREATED AND PAINTED, FASTENERS WERE INSTALLED IAW SRM 51-10-3 PAR 26, 21/14, 51-30-2, 53-02 PAR 13, 51-10-1.

Part: WIRE HARNESS — DAMAGED (EMERGENCY LIGHTS) · airframe 68,606 hrs · 51,813 cycles

DURING LINE CHECK, MAINTENANCE FOUND THAT THE EMERGENCY PATHWAY LIGHTING AT SEAT 20D IN THE CABIN WAS INOPERATIVE. MAINTENANCE FOUND THE SEAT HARNESS DAMAGED. THE WIRE HARNESS WAS REPLACED AND THE SYSTEM RETURNED TO NORMAL OPERATION.

Part: WIRE — BROKEN (EMERGENCY LIGHTS) · airframe 68,583 hrs · 51,795 cycles

DURING LINE CHECK, MAINTENANCE FOUND THAT THE EMERGENCY LIGHTING AT SEAT 24D IN THE CABIN WAS INOPERATIVE. MAINTENANCE FOUND A BROKEN WIRE IN THE CONNECTOR. THE CONNECTOR WAS REPAIRED AND THE SYSTEM RETURNED TO NORMAL OPERATION. LP 6466124

Part: CONNECTOR — DAMAGED (EMERGENCY LIGHT) · airframe 67,925 hrs · 51,345 cycles

DURING LINE CHECK, MAINTENANCE FOUND THAT THE EMERGENCY LIGHTS AT SEAT 34DE WAS INOPERATIVE. MAINTENANCE FOUND WIRES BROKEN AT THE CONNECTOR PIN. THE CONNECTOR WAS PINNED AND THE SYSTEM RETURNED TO NORMAL OPERATION.

Part: LATCH — LOOSE (TAILCONE RELEASE) · airframe 66,533 hrs · 50,354 cycles

MAINTENANCE DISCOVERED THAT THE TAILCONE UPPER RT RELEASE LATCH WAS VERY LOOSE. THE TAILCONE RELEASE LATCH ASSY AND CLAMP WERE BOTH REPLACED AND THEN RIGGED TO SPECIFICATIONS. THE RII STEPS WERE COMPLETED.

Part: LATCH — OUT OF LIMITS (TAILCONE RELEASE) · airframe 66,533 hrs · 50,354 cycles

MAINTENANCE DISCOVERED THAT THE TAILCONE UPPER LEFT RELEASE LATCH WAS OUT OF ALLOWABLE RIG LIMITS. THE TAILCONE RELEASE LATCH ASSY WAS REPLACED AND THEN RIGGED TO SPECIFICATIONS. THE RII STEPS WERE COMPLETED.

Part: DOOR FRAME — CRACKED (BS 886) · airframe 66,533 hrs · 50,354 cycles

RIGHT OVERWING FRAME INSPECTION, BS 886, FOUND CRACKED. REPAIRED IAW AMDS 5310-01415-0202.

Part: LANYARD — UNSECURE (GIRT BAR) · airframe 65,475 hrs · 49,613 cycles

CREW REPORTED THE R1 DOOR GIRT BAR LANYARD WAS NOT CONNECTED PROPERLY. REINSTALLED & SECURED R1 DOOR GIRT BAR LANYARD LATCH AS REQUIRED. OPS CHECKED GOOD IAW AMM 25-62.

Part: WIRE — CHAFED (EMERGENCY LIGHTS) · airframe 65,385 hrs · 49,545 cycles

DURING LINE CHECK, MAINTENANCE FOUND THAT THE EMERGENCY LIGHTS IN AFT CABIN WERE INOPERATIVE. MAINTENANCE FOUND A WIRE CHAFING, REPAIRED WIRE INSULATION, AND REPLACED THE BATTERY PACKS. OPS CHECKED NORMAL.

Part: BATTERY PACK — INOPERATIVE (EMERGENCY LIGHT) · airframe 64,980 hrs · 49,264 cycles

DURING LINE CHECK, THE AFT OVERWING EMERGENCY EXIT OVERHEAD LIGHTS WERE INOPERATIVE. REPLACED BATTERY PACK AND POWER SUPPLY IAW AMM 33-51. OPS CHECK GOOD.

Part: BATTERY PACK — INOPERATIVE (EMERGENCY LIGHT) · airframe 64,980 hrs · 49,264 cycles

DURING ROUTINE LINE CHECK, THE CEILING EMERGENCY LIGHTS FROM ROW 22-36 WERE FOUND TO BE INOPERATIVE. REPLACED THE CABIN EMERGENCY LIGHT BATTERIES AMM 33-53 AND OPS CHECKED GOOD.

Part: BATTERY PACK — INOPERATIVE (EMERGENCY LIGHTS) · airframe 64,980 hrs · 49,264 cycles

DURING SERVICE CHECK, FOUND LIGHTS INOPERATIVE AT ROW 25 AT BOTH AFT EMERGENCY EXIT DOORS. REPLACED BATTERY PACK ABOVE ROW 25 D/E IAW AMM 33-53-00. OPS CHECKS GOOD.

Part: BATTERY PACK — INOPERATIVE (EMERGENCY LIGHTS) · airframe 64,942 hrs · 49,234 cycles

DURING LINE CHECK, MX FOUND THAT THE OVERHEAD EMERGENCY PATHWAY LIGHTING IN THE COCKPIT AND IN THE GALLEY WERE INOPERATIVE. MX REPLACED BATTERY PACKS. OPS CHECKED GOOD.

Part: LATCH — WORN (TAILCONE) · airframe 63,348 hrs · 48,053 cycles

UPPER LT AND RT TAILCONE RETENTION LATCHES WORN. REPLACED UPPER LT TAILCONE LATCH ASSY WITH PN 3913351 IAW AMM 53-53. BLENDED WORN PARTS W/IN LIMITS IAW DWG 4920459-3. INSTALLED LATCH RIGGING ACCOMPLISHED ON CARD 53-50-01077-0101. INSTALLATION IAW IPC 53-50-00-25A. RII COMPLETED.

Part: FRAME — CRACKED (BS 1510) · airframe 63,348 hrs · 48,053 cycles

BS 1510 FRAME IS CRACKED AT 4:30 POS AT TAIL CONE ALINGMENT PIN--CRACKED EMPENNAGE (HFEC-M-). NR 128: REPAIRED IAW ERA 511420-14, REV ORIGINAL BY FRAME SECTION REPLACEMENT. WORK ACCOMPLISHED ON PRI 511420-14 REV O COINCIDES WITH FINAL ER/A 511420-14, REV ORIGINAL.

Part: SKIN — CRACKED (BS 1380) · airframe 63,348 hrs · 48,053 cycles

FUSELAGE SKIN CRACKED IN 5 EA AREAS 12" ABOVE PYLON STA 1380- CRACKED EMPENNAGE(HFEC -M-). REPAIRED IAW ER/A 511418-14, REV ORIGINAL. WORK ACCOMPLISHED ON PRI 511418-14 REV O AND REV 1.

Part: SKIN — DAMAGED (BS 1510) · airframe 63,348 hrs · 48,053 cycles

LIGHTNING STRIKE ON EXTERIOR SKIN 5:00 AND 5:30 POSITION AT BS 1510 JUST FWD OF TAIL CONE. REMOVED FASTENERS AND REMOVED PAINT AROUND DAMAGED AREA. FOUND DAMAGE TO BE OUT OF LIMITS IAW SRM 53-04-1. TRIMMED OUT DAMAGE MAINTAINING ED AND .50" RADIUS IAW SRM 53-01. REPAIRED DAMAGED AREA AT BS 1510 IAW ER/A 511450-14.

Part: SKIN — CRACKED (BS 1447) · airframe 63,348 hrs · 48,053 cycles

CROWN SKIN CRACKED AT BS 1447 BETWEEN S2-3L. CUT OUT CRACK WITH ONE INCH HOLE SAW. PERFORMED HFEC OF CUT OUT IAW NDT SPM 06-10-001. NO DEFECTS NOTED.

Part: BATTERY PACK — INOPERATIVE (EMERGENCY LIGHT) · airframe 62,947 hrs · 47,791 cycles

DURING LINE CHECK, MX FOUND THAT THE LT OVERWING EMERGENCY EXIT SIGN WAS INOPERATIVE. MX REPLACED THE BATTERY PACK IN THE POWER SUPPLY AND THE LIGHTS RETURNED TO AN OPS CONDITION.

Part: LONGERON — CRACKED (BS 1307 L8R) · airframe 61,898 hrs · 47,037 cycles

DURING HMV, A CRACK WAS FOUND ON LONGERON 8 RT ON STA Y=1307 AT PAX CABIN. DAMAGE AREA WAS CUT OUT AND NEW SECTION SPLICED IN IAW SRM 53-02 FIG 18.

Part: BEAM — CORRODED (CARGO DOORWAY) · airframe 61,898 hrs · 47,037 cycles

DURING HMV, CORROSION WAS FOUND ON MID CARGO COMPARTMENT LOWER DOOR FRAME BEAM, BS Y=655 AND Y=674, AROUND SETSCREW HOLES. DAMAGE AREA WAS CUT OUT AND PLUGS INSTALLED IAW ER/A 504344-14 REV ORIG.

Part: SKIN — CORRODED (BS 763-826) · airframe 61,898 hrs · 47,037 cycles

DURING HMV, CORROSION WAS FOUND ON FUSELAGE SKIN UNDER FILLET PANEL FAIRING RUBSTRIPS BETWEEN STA Y=763-826 AND LONGERON 25 RT-30. FUSELAGE SKIN BLENDED OUT. INSTALLED DOUBLER REPAIR IAW SRM 53-04 PARA 57.

Part: BEAM — CORRODED (CARGO DOORWAY) · airframe 61,898 hrs · 47,037 cycles

DURING HMV, CORROSION WAS FOUND ON MID CARGO COMPARTMENT LOWER BEAM STA Y=636-693. BLENDED AREA AND INSTALLED DOUBLER IAW SRM 53-05 FIG 123.

Part: FRAME — CRACKED (BS 864) · airframe 61,897 hrs · 47,036 cycles

DURING HMV, A CRACK WAS FOUND ON FUSELAGE FRAME OVERWING OF THE STA Y=864 AND X=55 AT THE CABIN FLOOR STRUCTURE. FRAME WAS REPLACED IAW DWG SR09530282 REV C.

Part: LONGERON — CRACKED (BS 1437 L4L) · airframe 61,897 hrs · 47,036 cycles

DURING HMV, A CRACK WAS FOUND ON LONGERON 4 LT AT INTERSECTION WITH FRAME BS 1437. REMOVED LONGERON FROM BS 1432 TO 1448 AND SLICED IN NEW LONGERON IAW SRM 53-02 FIG 18.

Part: SKIN — CRACKED (BS 374) · airframe 61,897 hrs · 47,036 cycles

DURING HMV, CRACKS WERE FOUND LENGTH OF 0.109 INCH AND 0.125 INCH IN FUSELAGE SKIN FWD CARGO COMPARTMENT DOOR FWD UPPER CORNER AT BS 374 CLOSE TO DOOR FRAME EDGE. DAMAGE AREA WAS CUT OUT AND DOUBLERS FILLER INSTALLED IAW ERA 504233-14AD REV ORIG.

Part: LONGERON — CRACKED (BS 1437 L12L) · airframe 61,897 hrs · 47,036 cycles

DURING HMV, A CRACKED LONGERON WAS FOUND LONGERON 12 LT AT INTERSECTION WITH FRAME 1437. LONGERON WAS REMOVED FROM BS 1437 TO 1448 AND SPLICED IN NEW LONGERON IAW SRM 53-02 FIG 18.

Part: SKIN — CRACKED (BS 175.75) · airframe 61,897 hrs · 47,036 cycles

DURING HMV, A CRACK WAS FOUND IN FWD SERVICE DOOR CUTOUT FUSELAGE SKIN FWD UPPER CORNER AT BS 175.75, CLOSE TO DOOR JAMB EDGE WITH THE LENGTH OF 0.055 INCH. DAMAGE AREA WAS CUT OUT AND REPAIRED DOUBLERS FILLER. INSTALLED IAW SRM 53-05 FIG 112.

Part: LONGERON — CRACKED (BS 541 L4R) · airframe 61,897 hrs · 47,036 cycles

DURING HMV, A CRACK WAS FOUND ON LONGERON 4 RT BS 541 OF INTERNAL FUSELAGE STRUCTURE. LONGERON WAS REPAIRED IAW SRM 53-02 FIG 18.

Part: LONGERON — CRACKED (BS 275 L17L) · airframe 61,897 hrs · 47,036 cycles

DURING HMV A CRACK WAS FOUND ON LONGERON 17 LT ON STA Y=275 AT PAX CABIN. LONGERON WAS REPAIRED IAW SRM 53-02 FIG 18.

Part: LONGERON — CRACKED (BS 389 L17R) · airframe 61,897 hrs · 47,036 cycles

DURING HMV A CRACKED LONGERON 17 RT ON FRAME STA Y=389 AT PAX CABIN. LONGERON WAS REPAIRED IAW SRM 53-02 FIG 18.

Part: SKIN — DAMAGED (RUDDER) · airframe 61,897 hrs · 47,036 cycles

DAMAGED METALIZED COATING ON RUDDER SURFACES. RUDDER SURFACE WERE REPAIRED IAW SRM 51-70-1AD PARAGRAPH 23A.

Part: LIGHT — INOPERATIVE (ROW 3CD) · airframe 59,277 hrs · 45,166 cycles

DURING LINE CHECK, MX FOUND EMERGENCY PATHWAY LIGHTAT ROW 3CD INOPERATIVE. MX REPLACED ASSOCIATED LIGHT ASSY. OPS CHECKS GOOD.

Part: FIXTURE — MELTED (GALLEY LIGHT) · airframe 59,214 hrs · 45,116 cycles

A STRONG ODOR WAS DETECTED COMING FROM THE FIRST CLASS GALLEY STORAGE AREA. FLIGHT CREW DECLARED AN EMERGENCY AND DIVERTED. MX FOUND A FWD GALLEY STORAGE LIGHT FIXTURE SOCKET MELTED AND CHARRED. THE FIXTURE WAS REMOVED, WIRES WERE STOWED, AND THE CIRCUIT BREAKER WAS DEACTIVATED. DEFERRED AND PLACARD.

Part: ENGINE — FLAMED OUT (NR 1) · airframe 57,091 hrs · 43,748 cycles

DURING TOP OF DESCENT AT FL320, THE FLIGHT CREW NOTICED THAT THE NR 1 ENGINE HAD FLAMED OUT. FLIGHT CREW DECLARED AN EMERGENCY, CONTINUED DESCENT, AND WAS ABLE TO RESTART THE NR 1 ENGINE AT FL220. THE FLIGHT LANDED WITHOUT FURTHER INCIDENT AND TAXIED TO THE GATE. MX COMPLIED WITH THE TROUBLESHOOTING PROCEDURES FOR AN ENGINE FLAMEOUT, AN ENGINE BOROSCOPE, REPLACED OIL FILTER, FUEL FILTER, AND THE FUEL CONTROL.

Part: ENGINE — FLAMED OUT (NR 1) · airframe 57,091 hrs · 43,748 cycles

DURING TOP OF DESCENT AT FL320, THE FLIGHT CREW NOTICED THAT THE NR 1 ENGINE HAD FLAMED OUT. FLIGHT CREW DECLARED AN EMERGENCY, CONTINUED DESCENT, AND WAS ABLE TO RESTART THE NR 1 ENGINE AT FL220. THE FLIGHT LANDED WITHOUT FURTHER INCIDENT AND TAXIED TO THE GATE. MX COMPLIED WITH THE TROUBLESHOOTING PROCEDURES FOR AN ENGINE FLAMEOUT, AN ENGINE BOROSCOPE, REPLACED OIL FILTER, FUEL FILTER, AND THE FUEL CONTROL. (DLM88101444) (2010-D0654)

Part: FUEL CONTROL — INOPERATIVE (NR 1 ENGINE) · airframe 57,091 hrs · 43,748 cycles

LEVEL AT CRUISE ALTITUDE OF FL 340 DESCENDED TO FL 320 UPON LEVELING ENGINE ROLLBACK AND SHUTDOWN. ENGINE WAS RESTARTED APPROX 15 MIN AFTER SHUTDOWN AT 22000 FT. C/W FLAMEOUT T/S. REPLACED FUEL FILTER. C/W LOW IDLE N2 T/S. NEEDS BOROSCOPE. REPLACED MAIN ENGINE OIL FILTER AND INSP CHIP DETECTOR. BOROSCOPE C/W. REPLACED NR 1 ENGINE FUEL CONTROL. OPS CK GOOD. (DLM88101444)

Part: WINDOW FRAME — DAMAGED (FUSELAGE) · airframe 47,393 hrs · 37,425 cycles

DAMAGE IN CABIN WINDOW FRAMES - LIGHTNING STRIKE DAMAGE WAS FOUND IN THE CORNERS ON NR 60 AND 62 CABIN WINDOW FRAMES. PERMANENT REPAIRS INSTALLED PER ERA 385062-14 REV C. THE WINDOW BELT PANEL P/N 9958156-1 WAS REPLACED PER BOEING DRAWING 5930543-577.

Part: FITTING — WORN (LT MLG) · airframe 47,393 hrs · 37,425 cycles

REPAIR AT THE LT WING LANDING GEAR FITTING, WEAR DAMAGE OF BUSHING P/N 2937332-501 ON FITTING P/N 5935812-19 AT STA Y=974. FITTING BORE WAS REAMED AND OVERSIZED BUSHING WAS INSTALLED PER BOEING SERVICE REWORK DRAWING SR09570087 REV A. BORE WITHIN LIMITS PER AD2004-25-14 AMENDMENT 39-13902 DATED 20JAN05. REF ERA 457430-14AD.

Part: PANEL — CRACKED (RUDDER) · airframe 47,393 hrs · 37,425 cycles

A 25.8 INCH LONG CRACK ALONG THE UPPER EDGE OF THE LEFT SIDE. AFT RUDDER PANEL AT STA ZR 143.00. PERMANENT REPAIR INSTALLED PER SRM 51-70-01A, PARA 22 AND FIG 60 AND INCLUDING MINOR DEVIATIONS PER SPECIFIED IN AEROMEXICO'S REPAIR DRAWING AMR0955064 R01. APPROVED BY DELTA ERA 457176-14.

Part: DOOR FRAME — CORRODED (AFT CARGO DOOR) · airframe 47,393 hrs · 37,425 cycles

SEVERAL CORROSION POINTS IN THE AFT CARGO COMPARTMENT DOOR JAMB BEAM BETWEEN STA Y=1155.0 AND 1212.0. CORROSIONS BLENDED OUT. ACCOMPLISHED PERMANENT REPAIR FOLLOWING INSTRUCTIONS AND RECOMMENDATIONS CONTAINED IN THE MD-80 SRM 53-05D, FIG 63, INCLUDING MINOR DEVIATIONS SPECIFIED IN AEROMEXICO'S REPAIR DRAWING AMR0953548 KR02. APPROVED BY DELTA AND INCLUDED IN DELTA ER/A NR 457309-1.

Part: CUSP WEB — CRACKED (FUSELAGE) · airframe 47,393 hrs · 37,425 cycles

CRACK ON CUSP WEB - A CRACK WAS FOUND ON FUSELAGE CUSP WEB AT STA Y=245. REPAIRED IAW ERA 398191-14 MA, FIG 5, REV A.

Part: VANE — MISREPAIRED (RT WING TE FLAP) · airframe 47,393 hrs · 37,425 cycles

EXISTING EXTERNAL REPAIR DOUBLER OUT OF SRM ON L/E OF RT WING OUTBD FLAP, INBD VANE AT STA 153.00. REMOVED EXISTING REPAIR AND INSTALLED REPAIR IAW AEROMEXICO DRAWING AMR0957141 R03 AND REPAIR SKETCH SK-06-147/AQR. APPROVED BY DELTA ERA 457403-14, STA XV1=153.00.

Part: VANE — DELAMINATED (LT WING TE FLAP) · airframe 47,393 hrs · 37,425 cycles

DELAMINATION ON EXTERNAL SKIN AND INTERNAL DOUBLER OF LT WING OUTBD FLAP INBD VANE. AN AREA 1.25 IN BY 2.0 IN AT EXTERNAL UPPER SKIN AND AN AREA 0.75 IN BY 1.25 IN AT INTERNAL DOUBLER FLAP VANE INBD END AT STA XV=153.00. REPAIRED PER AEROMEXICO REPAIR DRAWING AMR0957141 R03 AND REPAIR SKETCH SK-06-143/AQR AND DELTA ERA 457402-14.

Part: SKIN — LIGHTNING STRIKE (WINDOW BELT) · airframe 47,382 hrs · 37,421 cycles

THE RIGHT SIDE WINDOW BELT FROM APPROXIMATELY STA 760 TO STA 810 WAS REPLACED PER ERA 385062-14 ON N/R T0036084 OF THE CURRENT HMV-3 CHECK.

Part: DOOR FRAME — CORRODED (FS 1155-1212) · airframe 47,382 hrs · 37,421 cycles

CORROSION FOUND ON AFT CARGO COMPARTMENT LOWER JAMB. CORROSION BLENDED AND REPAIRED.

Part: WINDOW FRAME — DAMAGED (FUSELAGE) · airframe 47,382 hrs · 37,421 cycles

CABIN WINDOW FRAME REPAIR, MULTIPLE INSTANCES OF LIGHTNING STRIKE DAMAGE. REPAIRED PER 369388-14.

Part: SKIN — CRACKED (FUSELAGE) · airframe 47,203 hrs · 37,287 cycles

REPAIR OF FUSELAGE SKIN - FUSELAGE SKIN CRACK OF 0.125 IN AT STA Y=185 AND OTHER OF 0.094 AT STA Y=186 AT LONGERON 22 LT. REPAIRED IAW SERVICE REWORK DRAWING SR 09530219-7001 AND IAW EA 09-069085-12 AD OPN 0203.

Part: OIL SYSTEM — LEAKING (APU) · airframe 42,332 hrs · 33,829 cycles

FIRST FLIGHT ATB SMOKE IN CABIN WITH LAV DETECTORS SOUNDING FLIGHT CXLD. MTC WORKING OPN'S 5088 AND 5089 SMOKE T/S AND DUCT BURN OUT.

Part: CONTROL PANEL — FAULTY (ELECTRICAL SYS) · airframe 40,850 hrs · 32,786 cycles

RIGHT GENERATOR OFF LIGHT AT 8000 FT CLIMBING OUT OF CVG. RESET PER POM, NO JOY. REPLACED RT ENGINE GENERATOR CONTROL PANEL PER ELECTRICAL DISTRIBUTION PANEL FAULT LIGHT. RAN ENGINES, ALL GENERATORS CK OK.

Part: BATTERY PACK — DISCHARGED (CABIN) · airframe 40,557 hrs · 32,584 cycles

COCKPIT EMERGENCY LIGHT WILL NOT ILLUMINATE. REPLACED FWD BATTERY AND BATTERY PACK ASSY B5-23 PER M/M, CHECK'S OK.

Part: SENSOR — MALFUNCTIONED (NR 1 SLAT) · airframe 39,367 hrs · 31,760 cycles

UPON SLAT RETRACTION DISAGREEMENT LIGHT ILLUMINATED WITH FLAP HANDLE IN THE FULL UP POSITION.NO ASSYMETRY. FOUND C31 SENSOR PLUNGER AND SPRINGS WORN.REPLACED SAME. SYSTEM CKS OK

Part: HOSE — LEAKING (LT HYD SYS) · airframe 39,160 hrs · 31,614 cycles

ON CLIMBOUT LT HYD QTY AND PRESS DROPPED TO ZERO QTY BEGAN TO RISE ON ARRIVAL CVG, 4 QTS APPROACH 9 QTS ON SHUTDOWN PUMP OFF. REPLACING LINE P/N 299600044 LT ENG PRESS FLEX LINE.

Part: BATTERY — INOPERATIVE (EMERGENCY LIGHT) · airframe 39,129 hrs · 31,598 cycles

ON LAYOVER, FOUND F/C OVERHEAD AISLE EMERGENCY LIGHTS INOP. REMOVED AND REPLACED BATTERIES PER M/M, CHECKS NORMAL.

Part: LIGHT — INOPERATIVE (CABIN) · airframe 38,328 hrs · 31,010 cycles

FOUND EMERGENCY EXIT ROW LIGHTS ROWS 35-38 AND AFT AIRSTAIR DOOR LIGHTS INOPERATIVE. RELAMPED

Part: TUBE — LEAKING (LT THR REV CONT) · airframe 37,700 hrs · 30,565 cycles

ON CLIMB OUT HYD QTY ON LEFT SIDE ENGINE DROPS TO 3/4 QT FOLLOWED POM PROCEDURES AND SHUT OFF HYD PUMPS ON LEFT SIDE UNTI CONFIGURING FOR LANDING. CORR ACT. FOUND LINE LEAKING AT LEFT THRUST REVERSER MODULE. REPLACED LINE AND LEAK CHECKED. PERFORMED OPN 5089. CHECKS GOOD.

Part: OXYGEN MASK — FAILED (COCKPIT) · airframe 34,588 hrs · 28,241 cycles

RTG, CAPTS O2 MASK FAILED AND DEPLETED SYSTEM. REPLACED MASK AND SERVICED O2.

Part: DUCT — CRACKED (NR 2 ENGINE) · airframe 34,007 hrs · 27,813 cycles

WHILE CLIMBING THRU 11K FT NR 2 ENG FIREALOOP ILLUMINATED AT 13K FT NR 2 FIREBELL WARNING HANDLE ILLUMINATED. THROTTLE WAS RETARDED TO IDLE AND LIGHT EXTINGUISHED. UPON ENG INSP FOUND DUCT BETWEEN 13TH STAGE DUCT AND NOSE COWL ANTI ICE VALVE CRACKED. REPLACED DUCT AND PERFORMED ENG RUN PER PFHB. LEAK CHECKED GOOD.

Part: COALESCER BAG — CONTAMINATED (AFT) · airframe 33,024 hrs · 27,077 cycles

ON INITIAL CLIMB SMOKE IN CABIN AND COCKPIT FOR 5 MINUTES.SMELLED LIKE OIL BURNOFF. PERFORMED INSPECTION AND DUCT BURNOUT PER JIC AND M/M.

Part: APU — LEAKING (APU BAY)

WITH ENG A/I ON AND PNEUMATIC X-FFED CLOSED, GOT SMOKE AND FUMES IN CABIN. BOTH AFT LAV SMOKE DETECTORS WENT OFF. ENG A/I ON FOR APPROX 20 MINS. A/C WAS ON APPROACH WITH ENG PWR AT 1.3 EPR, ALT BELOW 10K FT. PERFORMED DUCT BURN-OUT PER MM. REPLACED WATER SEP BAGS. FOUND APU LEAKING OIL. PLACED ON MCO.

Part: DUCT — ODOR (CABIN AIR)

ON SHORT FINAL 600 AGL, F/A REPORT SMOKE IN CABIN. PERFORMED POM AND SMOKE CLEARED. SMOKE SMELLED LIKE BLEED AIR. SMOKE CLEARED AFTER A/C PACKS TURNED OFF. BOTH PACK OIL LEVEL CHECK OK. COALESCER BAGS, NO CONTAMINATION AND CLEAN. ENG BLEED DUCT CHECKED, NO CONTAMINATION. BOTH PACKS OPS WITH APU, NO FAULTS. DUCT BURN-OUT PROCEDURE C/W PACK OPERATING WITH ENG RUNNING NORMAL.

Part: COALESCER — DIRTY (RT PACK)

PACK SMOKE/SMELL ON TAKEOFF. TURNED BOTH PACKS OFF, SMELL DISSIPATED. LEFT PACK ON FOR REST OF FLT, NO SMELL. INSPECTED APU INLET DOORS, FOUND OILY RESIDUE INSIDE FWD DOOR. INSPECTED LT AND RT ACMS AND REPLACED COALESCER BAGS. RAN ENGINES WITH PACKS RUNNING, NO SMOKE OR ODOR PRESENT. FWD APU PNEUMATICS TO MCO ON SEPARATE LOG ITEM.

Part: OVEN — DIRTY (GALLEY)

AFT GALLEY OVENS HAD LIGHT SMOKE AND BURNING ODOR. TURNED OFF ALL OVENS. SMOKE AND ODOR WENT AWAY, DID NOT SMELL LIKE BURNING FOOD. FOUND TAPE ON OVEN INSERTS. REMOVED INSERTS AND CHECKED OVENS, NO SMOKE NOTED. OPS NML.

Part: TIRE — FAILED (RT MLG)

NUMEROUS COMPRESSOR STALLS ON RIGHT ENGINE AFTER LIFTOFF. NR 4 MAIN TIRE RECAP, SEPARATED FROM OUTBOARD PORTION OF TIRE AND CAUSED FOD DAMAGE TO NR 2 FAN, NOSE COWL AND LOWER COWL DOOR. FOUND EXTENSIVE DAMAGE TO FAN AND COMPRESSOR SECTION AND REQUIRED ENGINE CHANGE.

Part: CONNECTOR — LOOSE (CABIN)

EMERGENCY TRACK LIGHTS INOP FROM SEAT 4C TO SEAT 15D. RESEATED CONNECTOR ON POWER SUPPLY, CKS GOOD.

Part: SKIN — GOUGED (BS 235)

THE FUSELAGE SKIN AT STA 235 AND BETWEEN L18L AND L20L WAS GOUGED DUE TO CONTACT WITH A JETWAY. THE DAMAGE CONSISTS OF THREE GOUGES UP TO 0.030 MAX DEPTH. THIS DAMAGE WAS REPAIRED WITH A DOUBLER, PER ERA 362370-14.

Part: AIR DISTRIBUTION — ODOR (CABIN)

ON TAKEOFF ROLL, F/A IN AFT JUMP SEAT SMELLED AN ELECTRICAL OR HOT RUBBER ODOR. RAN NR 1 AND NR 2 ENGINES TO TAKEOFF POWER SEVERAL TIMES PER M/M, NO ODORS DETECTED.

Part: CONTROL UNIT — MALFUNCTIONED (AC BUS)

CRUISE AT FL 330, APU FAULT LIGHT AND APU OIL PRESSURE LIGHT ILLUMINATED AND APU SHUTDOWN AUTOMATICALLY. REPEAT EVENT. CHECKED APU FAULTS, NONE. CHECKED APU OIL, GOOD. RAN APU, OK FOR SERVICE. CROSSTIE LOCKOUT ON MCO AND PLA. REPLACED A/C BUS CONTROL UNIT. REMOVED MCO AND PLA ON CROSS TIE LOCKOUT.

Part: ENGINE — FAILED (NR 2)

NR 2 ENG HAD SEVERE VIBRATION IN CLIMB FROM FL31 TO 35. LOST OIL PRESS/RT HYD PRESS AND HAD FIRE WARNING. BOTH EXT BOTTLES USED AND ALT GEAR EXT MADE. ENG HAD DRAGGING FAN AND OIL IN TAIL PIPE. REPLACED ENGINE AND ROUTED TO SHOP. ****S/D**** ENGINE SHOP DISASSEMBLY FOUND N2 CENTER TUBE FRACTURED. ALSO FOUND T2 SHAFT TWISTED. OIL FIRE INDICATIONS FOUND IN ID OF N2 ROTOR. N2 REAR HUB PREVIOUSLY MODIFIED PER EO 49-63034-3.

Part: ENGINE — FAILED (NR 2)

STRONG ENGINE NR 2 VIBRATION FOLLOWED BY LOW HYD-E PRESS, FOLLOWED BY ENGINE FIRE WARNING NR 2. EMERGENCY GEAR EXT USED, ZERO HYD FLUID ON LANDING. NR 2 ENG WAS SHUTDOWN, BOTH FIRE BOTTLES USED. NR 2 ENGINE WAS REPLACED AND ROUTED TO SHOP.

Part: DOOR FRAME — WORN (CARGO DOOR)

C-1 DOOR PAN AND UNDERLYING INTERCOSTAL WORN FWD SIDE. FOUND DURING A-1 LTR CK TPAMM. REPAIRED PER MM 52-05 FIG 27.

Part: DOOR FRAME — CRACKED (LT MLG)

MLG FWD DOOR FRAME CRACKED 3.5 INCHES AT O/B RADIUS. FOUND DURING A-1 LTR CK TPAMM. REPAIRED PER SRM 53-05 FIG 78A.