N931DL

Part: SKIN — SEPARATION (LT WING TE FLAP) · airframe 76,132 hrs · 57,539 cycles

LEFT WNIG T/E OTBD FLAP HAS A 7.250 INCH SEPERATION.

Part: ENGINE — FAILED (NR 2) · airframe 76,114 hrs · 57,525 cycles

DIVERTED DUE TO THE NR 2 ENGINE FAILED DURING CLIMB OUT. CREW DID SHUT ENGINE DOWN. MAINTENANCE FOUND METAL IN THE TAIL PIPE AND TURBINE DAMAGE. THE ENGINE WAS CHANGED.

Part: SKIN — DENTED (RT WING SLAT) · airframe 76,138 hrs · 57,544 cycles

RIGHT WING SLAT L/E DENTED. REMOVED AND REPLACED THE SLAT IAW 2900-4224-RH-0. REPAIRED IAW ERA 562988-14. REV A, SECTION III.

Part: STRAP — FRAYED (EVAC SLIDE) · airframe 75,055 hrs · 56,700 cycles

FWD SVC DOOR - DOOR SLIDE RELEASE LANYARD STRAP FRAYED LOOKING BACK FROM FRONT AT RELEASE CABLE. REPLACED SLIDE PER AMM 25-62-00, AND CARD 5200-0654.

Part: SLIDE — DAMAGED (L1 DOOR) · airframe 75,055 hrs · 56,700 cycles

L1 DOOR SLIDE PIN PULLED AND SLIDE UNRAVELED. REMOVED AND REPLACED THE L1 DOOR SLIDE IAW AMDS 2561-4964.

Part: SLIDE — DAMAGED (TAILCONE) · airframe 75,055 hrs · 56,700 cycles

TAILCONE SLIDE PACK UNRAVELED. REPLACED TAIL CONE SLIDE AND COMPLETED REQUIRED INSPECTIONS.

Part: SKIN PANEL — CRACKED (RT HORIZ STAB) · airframe 75,055 hrs · 56,700 cycles

DURING LFEC INSPECTION OF RT HORIZONTAL STAB UPPER AFT SKIN PANEL, OBSERVED 1/2" LONG CRACK INDICATION AT SPECIFIED LOCATION. REFERENCE ER/A 558877-14AD REV ORIG.

Part: TAB — DELAMINATED (RIGHT) · airframe 75,055 hrs · 56,700 cycles

RIGHT ANTI-FLOAT TAB HAS AREA OF DELAMINATION ON OB AREA OF DELAMINATION ON OTBD END UPPER AND LOWER SURFACE. REMOVED AND REPLACED ANTI-FLOAT TAB ON AMDS 2730-4382.

Part: FIRE LOOP — MALFUNCTIONED (FWD CARGO) · airframe 74,973 hrs · 56,641 cycles

FWD CARGO B LOOP FIRE WARNING STUCK ON. BREAKERS RESET. OPS CHECKED NORMAL. LOOPS "A" "B" "BOTH" ALL FUNCTION NORMAL. (LP# 3142068)

Part: WIRE — NOT REPORTED (CABIN) · airframe 74,940 hrs · 56,611 cycles

SEAT MOUNTED EMERGENCY LIGHT AT 30DE INOP. REPLACED PIG TAIL AT SEAT 30D PER AMM 33-52. CHECKS GOOD.

Part: LAMP — INOPERATIVE (EMERGENCY LIGHT) · airframe 74,922 hrs · 56,596 cycles

RT FWD OVERWING EXIT SIGN INOPERATIVE. REPLACED THE LAMPS IAW AMM 33-50. OPS CHECKED GOOD.

Part: WIRE HARNESS — DAMAGED (EMERGENCY LIGHTS) · airframe 74,789 hrs · 56,491 cycles

EMERGENCY LIGHT SEAT ROW 18DE INOPERATIVE. FOUND SEAT WIRE HARNESS DAMAGED. REPLACED THE WIRE HARNESS IAW AMM 33-50, OPS OK.

Part: WIRE — BROKEN (EMERGENCY LIGHT) · airframe 73,811 hrs · 55,762 cycles

WALL MOUNTED EMERGENCY LIGHT ON CATWALK INOPERATIVE. FOUND WIRES BROKEN. REPAIRED THE WIRING IAW SPWM CHAPTER 20 AND EWIS. OPS CHECKED GOOD.

Part: WIRE HARNESS — DAMAGED (EMERGENCY LIGHT) · airframe 73,811 hrs · 55,762 cycles

SEAT MOUNTED EMERGENCY LIGHT AT SEAT 20D INOPERATIVE. REPLACED THE PIGTAIL IAW SPWM CHAPTER 20 AND EWIS.

Part: SKIN — CRACKED (FUSELAGE) · airframe 72,889 hrs · 55,061 cycles

DURING WALKAROUND, A FOUND CRACK ON BELLY SKIN BY AFT EDGE OF MID CARGO DOOR. IAW ERA 550253-14 REVISION ORIGINAL.

Part: CSD — OVERSERVICED · airframe 71,859 hrs · 54,308 cycles

CREW NOTED THE LOSS OF ELECTRICAL POWER WHILE CLIMBING OUT. THE RT ENGINE GENERATOR TRIPPED OFF LINE AND WOULD NOT RESET AND THE APU GENERATOR WOULD NOT PICK UP POWER. THE FLIGHT WAS RETURNED. PERFORMED EMERGENCY LANDING AND ALTERNATE GEAR EXTEND. LEFT GENERATOR POWER SYS WAS INOPERATIVE AND ALREADY ON MEL PRIOR TO DEPARTURE. FOUND BOTH CSD'S OVERSERVICED. ELECTRICAL SYSTEM CHECK-OUTS PERFORMED WITH NTF NOTING LT GENERATOR MEL. REPLACED LT GENERATOR RELAY, ACFT CROSS-TIE RELAY AND EMERGENCY POWER SWITCH. REPLACED LT ENGINE CSD AND GENERATOR. ENGINE RUNS PERFORMED WITH WITH ALL CONFIGURATIONS CHECKED INCLUDING APU WITH NO FAULTS. FUNCTIONAL TEST FLIGHT.

Part: PIN — PULLED (L1 DOOR SLIDE) · airframe 71,655 hrs · 54,161 cycles

MAINTENANCE FOUND L1 DOOR SLIDE PARACHUTE PIN PULLED WHILE GETTING AN OK TO INSTALL. THE SLIDE PACK WAS REPLACED.

Part: SKIN — DAMAGED (RT WING AILERON) · airframe 71,655 hrs · 54,161 cycles

RT WING AILERON UPPER SURFACE NUMEROUS LOCATIONS WITH EXPOSED COMPOSITE. R & R RT AILERON REF AMDS WC 2710-4124-RT AND NR 176, AILERON CONTROL TAB REF AMDS WC 2710-4376-RT AND NR 333 AND AND AILERON TRIM TAB REF AMDS WC 2710-4627 -RT AND NR 335.

Part: SKIN — CRACKED (BS 1429) · airframe 71,655 hrs · 54,161 cycles

TAIL INTERIOR CROWN, SKIN SPLICE DOUBLER HAS CRACK WHICH ORIGINATES UNDER VERTICAL STABILIZER SPLICE PLATE, VISIBLE END HAS BEEN MARKED USING HFEC, 4" INBD OF L3L, BS 1429. REPAIRED IAW PRI 544011-14 AND REV AND COMPLIED WITH ERA 544011-14, REV ORIG.

Part: LONGERON — CORRODED (FUSELAGE) · airframe 73,442 hrs · 55,499 cycles

AFT CARGO BILGE, L29L HAS SMALL SPOT OF CORROSION, BS1231. REPAIRED PER SRM.

Part: SHEAR TIE — CORRODED (BS 1218) · corrosion level 2 · airframe 71,655 hrs · 54,161 cycles

AFT CARGO BILGE, 2 SHEAR TIES HAVE CORROSION, BOTH SIDES OF L30C, BS 1218. BLENDED AND CHECKED LIMITS REF SRM 53-01, FIG 1.

Part: ATTACH BRACKET — CORRODED (AFT CARGO BAY) · corrosion level 2 · airframe 71,655 hrs · 54,161 cycles

AFT CARGO ENTRY LOWER ATTACH STRUCTURE CORRODED. REPAIRED IAW SRM 53-05, FIG 123 AND ER/A 499523-14MA.

Part: FRAME — CRACKED (BS 1463) · airframe 71,655 hrs · 54,161 cycles

TAIL INTERIOR, CANTED FRAME FWD WEB HAS .3750" LONG CRACK THAT ORIGINATES IN RIVET HOLE, END IS MARKED WITH HFEC, APPROXIMATELY 12" INBD OF L9L, BS 1463. NR FOR ADDITIONAL INFORMATION 001-0311:5300-2551/012 00113. REPAIRED IAW SRM 53-03, FIG 38C.

Part: WIRE HARNESS — DAMAGED (EMERGENCY LIGHTS) · airframe 69,223 hrs · 52,481 cycles

MAINTENANCE FOUND SEAT 26 EMERGENCY ESCAPE PATH LIGHT INOPERATIVE. SEAT 26 SEAT WIRING HARNESS WAS REPLACED. OPS CHECKED GOOD.

Part: SKIN — CORRODED · corrosion level 2 · airframe 73,393 hrs · 55,459 cycles

GENERAL SURFACE CORROSION ON FWD CABIN PRESSURE SAFETY VALVE FUSELAGE SKIN. PRESSURE VALVE COLLAR WAS REPLACED IAW DWG 591657555-5 REV.E. AND SRM 51-30-1 & 51-30-2 FWD CABIN PRESSURE SAFETY VALVE WAS REMOVED, INSTALLED, AND TESTED IAW AMM 21-32-07. (UT) WAS ACCOMPLISHED. ORIGINAL THICKNESS IS 0.050" IN AND MINIMUM REMAINING THICKNESS IS 0.09" IN THEREFORE COLLAR IS "OUT OF LIMITS" IAW SRM 53-01 FIG.1 AND NDT SPM 04-00-07 PARAGRAPH FIG.3 (SHEET 1 AND 2).

Part: TERMINAL — BROKEN (EMERGENCY LIGHTS) · airframe 68,201 hrs · 51,761 cycles

DURING CHECK, MAINTENANCE FOUND THE EMERGENCY LIGHTS WERE INOPERATIVE ON THE CAT WALK. MAINTENANCE FOUND A BROKEN TERMINAL END AND THEY REPLACED THE TERMINAL END AND THE OPS CHECK WAS GOOD.

Part: BATTERY PACK — INOPERATIVE (EMERGENCY LIGHTS) · airframe 67,863 hrs · 51,533 cycles

DURING LINE CHECK, MAINTENANCE FOUND THAT THE EMERGENCY LIGHTS IN THE VENTRAL STAIRWAY WERE INOPERATIVE. MAINTENANCE REPLACED THE BATTERY PACKS FOR THE NOTED LIGHTED AREAS AND THE OPERATIONAL CHECKED GOOD.

Part: CONNECTOR — LOOSE (EMERGENCY LIGHTS) · airframe 66,679 hrs · 50,691 cycles

DURING LINE CHECK, MAINTENANCE FOUND THAT THE EMERGENCY LIGHTS AT SEATS 2CD AND 4CD IN THE CABIN WAS INOPERATIVE . MAINTENANCE CORRECTED A LOOSE CONNECTION AT 2CD AND REPAIRED THE CONNECTOR AT 4CD, AND THE SYSTEM RETURNED TO NORMAL OPERATION.

Part: CABLE — OUT OF RIG (AIR STAIR) · airframe 65,008 hrs · 49,530 cycles

MX DISCOVERED THAT THE RETRACT CABLE FOR THE CATWALK IN TAIL SECTION, WAS NOT ABLE TO PROPERLY MAINTAIN CATWALK POSITIONING. CATWALK WILL NOT COME UP WHEN THE AIRSTAIRS GO DOWN. THE SYS WAS FORWARDED AND PLACARD PROCEDURES WERE COMPLIED WITH. ON 03JUL, THE CATWALK CABLE TENSION WAS FOUND TO BE LOW AND OUT OF LIMITS. THE CABLE WAS RIGGED BACK INTO PROPER TENSION SPECIFICATIONS AND THE ACFT WAS RETURNED TO SERVICE. (LP NR 9579664)

Part: CAM LOCK — LOOSE (CATWALK) · airframe 64,941 hrs · 49,495 cycles

THE CABIN F/A AND NUMEROUS PASSENGERS REPORTED A LOUD NOISE AT THE REAR STAIRWAY. THE CATWALK REMAINED STUCK IN THE UP POSITION-BLOCKING THE EES PATH- FROM THE LAST TIME THE STAIRS HAD BEEN EXTENDED AND WAS JOLTED OUT OF THAT STUCK POSITION DURING TAXI. MX FOUND A LOOSE CAMLOCK WHICH WAS RESTRICTING THE CATWALK FROM RETURNING TO THE "EXIT PATH" POSITION. THE CAMLOCK WAS SECURED AND A FUNCTIONAL CHECK PROVED THE CATWALK FUNCTIONED CORRECTLY.

Part: BUSHING — WORN (UNKNOWN) · airframe 64,798 hrs · 49,386 cycles

MX DISCOVERED THAT THE TEE PIN AND THE TEE PIN BUSHINGS WERE WORN BEYOND ALLOWABLE LIMITS AND REPLACED.

Part: BATTERY PACK — INOPERATIVE (EMERGENCY LIGHTS) · airframe 64,531 hrs · 49,189 cycles

DURING LINE CHECK, MX FOUND THAT THE EMERGENCY PATHWAY LIGHTING EXIT SIGN AT THE AFT OVERWING EXIT WAS INOPERATIVE. MX REPLACED THE BATTERY PACK AND THE LIGHTS RETURNED TO AN OPS CONDITION.

Part: BULKHEAD WEB — CRACKED (NLG WW) · airframe 64,448 hrs · 49,127 cycles

FOUND CRACK IN FWD WEB OF NOSE GEAR WHEEL WELL. REMOVED WEB. INSTALLED REPLACEMENT WEB IAW ERA 513701-14, REV ORIG.

Part: BATTERY — INOPERATIVE (EMERGENCY LIGHT) · airframe 63,929 hrs · 48,757 cycles

DURING LINE CHECK, MX FOUND THAT THE OVERHEAD EMERGENCY PATHWAY LIGHTING IN THE COCKPIT WAS INOPERATIVE. MX REPLACED THE BATTERIES IN THE POWER SUPPLY AND THE LIGHTS RETURNED TO AN OPERATIONAL CONDITION.

Part: SKIN — DAMAGED (BS 946-965) · airframe 62,177 hrs · 47,517 cycles

DURING HMV LIGHTNING STRIKES WERE FOUND ON LT WINDOW BELT AT FWD/LWR CORNERS BTW STA Y=946-965. AREA WAS BLENDED AND DOUBLER INSTALLED IAW ERA 503252-14 REV ORIG.

Part: SKIN — CRACKED (BS 1418 L1-2R) · airframe 62,177 hrs · 47,517 cycles

SKIN CRACKED AT BS 1418 L1-2R, REMOVE DAMAGE AREA AND INSTALLED FILLER AND DOUBLER IAW ER/A5010910-14 REV ORIG.

Part: SKIN — DAMAGED (BS 560-579) · airframe 62,177 hrs · 47,517 cycles

DURING HMV LIGHTNING STRIKES WERE FOUND ON LT WINDOW BELT AT AFT UPPER CORNER BTW STA Y=560-579. AREA WAS BLENDED OUT IAW ERA 503255-14 REV ORIG.

Part: SKIN — DAMAGED (BS 1067-1070) · airframe 62,177 hrs · 47,517 cycles

DURING HMV LIGHTNING STRIKES WERE FOUND ON LT WINDOW BELT AT LOWER FWD CORNER STA Y=1067 AND LOWER AFT CORNER STA Y=1070. AREA BLENDED OUT IAW ERA 502205-14 REV ORIG.

Part: SKIN — DAMAGED (BS 750-769) · airframe 62,177 hrs · 47,517 cycles

DURING HMV LIGHTNING STRIKES WERE FOUND ON LT WINDOW BELT AT FWD AND AFT EDGES BTW STA Y=750-769. AREA WAS BLENDED AND DOUBLER INSTALLED IAW ER/A 503251-14 REV ORIG.

Part: FRAME — DAMAGED (BS 1250-1271) · airframe 62,177 hrs · 47,517 cycles

DURING HMV, NICKS WERE FOUND ON RT WINDOW BELT FRAME AT AFT/UPPER CORNER BTW STA Y=1250-1271. NICKS WERE BLENDED OUT IAW ERA 503255-14 REV ORIG.

Part: SKIN — DAMAGED (BS 984-1003) · airframe 62,177 hrs · 47,517 cycles

DURING HMV, LIGHTNING STRIKES WERE FOUND ON LT WINDOW BELT AT LWR AND UPPER EDGE BTW STA Y=984-1003. AREA WAS BLENDED OUT IAW ERA 503255-14 REV ORIG.

Part: SKIN — DAMAGED (BS 503-522) · airframe 62,177 hrs · 47,517 cycles

DURING HMV, LIGHTNING STRIKES WERE FOUND ON RT WINDOW BELT AT AFT LWR CORNER BTW STA Y=503-522. AREAS WERE BLENDED OUT IAW ERA 503255-14 REV ORIG.

Part: SKIN — DAMAGED (BS 370-389) · airframe 62,177 hrs · 47,517 cycles

DURING HMV, LIGHTNING STRIKES WERE FOUND ON RT WINDOW BELT AT FWD UPPER CORNER BTW STA Y=370-389. AREA WAS BLENDED OUT IAW ERA 503255 REV ORIG.

Part: SKIN — DAMAGED (BS 1212-1231) · airframe 62,177 hrs · 47,517 cycles

DURING HMV, LIGHTNING STRIKE FOUND ON LT WINDOW BELT AT FWD LWR CORNER BTW STA Y=1212-1231. AREA WAS BLENDED OUT AND DOUBLER INSTALLED IAW ERA 503254-14 REV ORIG.

Part: SKIN — DAMAGED (BS 1098-1117) · airframe 62,177 hrs · 47,517 cycles

DURING HMV, LIGHTNING STRIKE FOUND ON R WINDOW BELT FRAME AT LWR CORNER EDGE BTW STA Y=1098-1117. WINDOW BELT WAS REPAIRED IAW ER/A 503247-14 REV ORIG.

Part: SKIN — DAMAGED (BS 1079-1098) · airframe 62,177 hrs · 47,517 cycles

DURING HMV, SCRATCHES WERE FOUND ON RT WINDOW BELT AT FWD/LWR CORNERS BTW STA Y=1079-1098. SCRATCHES WERE BLENDED OUT IAW ERA503255-14 REV ORIG.

Part: SKIN — DAMAGED (BS 1231-1250) · airframe 62,177 hrs · 47,517 cycles

DURING HMV, LIGHTNING STRIKES WERE FOUND ON LT WINDOW BELT AT AFT/LWR CORNER BTW STA Y=1231-1250. AREA WAS BLENDED OUT IAW ERA 503255-14 REV ORIG.

Part: DOOR FRAME — CORRODED (CARGO DOORWAY) · airframe 62,177 hrs · 47,517 cycles

DURING HMV, CORROSION WAS FOUND ON LWR DOORJAMB BEAM BTW STA Y=1154 AND 1211 REPAIRED IAW SRM 53-05 FIG 123.

Part: SKIN — DAMAGED (BS 1079-1098) · airframe 62,177 hrs · 47,517 cycles

DURING HMV, LIGHTNING STRIKES WERE FOUND ON LT WINDOW BELT AT FWD UPPER CORNER BTW STA Y=1079-1098. AREA WAS BLENDED AND DOUBLER INSTALLED IAW ERA 503253-14 REV ORIG.

Part: SKIN — DAMAGED (BS 408-427) · airframe 62,177 hrs · 47,517 cycles

DURING HMV, LIGHTNING STRIKES WERE FOUND ON RT WINDOW BELT AT FWD UPPER CORNER BTW STA Y=408-427. BLENDED WINDOW BELT IAW ERA 503255-14 REV ORIG.

Part: SKIN — DAMAGED (BS 617-636) · airframe 62,177 hrs · 47,517 cycles

DURING HMV, LIGHTNING STRIKE WAS FOUND ON RT WINDOW BELT FRAMES AT AFT LOWER CORNER BTW STA Y=617, 636 WINDOW BELT FRAME WAS BLENDED OUT AND DOUBLER WAS INSTALLED IAW ER/A 503245-14 REV ORIG.

Part: SKIN — DAMAGED (BS 693-712) · airframe 62,177 hrs · 47,517 cycles

DURING HMV, LIGHTNING STRIKES WERE FOUND ON LT WINDOW BELT AT AFT LWR CORNERS BTW STA Y=693-712. WINDOW BELT WAS BLENDED OUT AND DOULER INSTALLED IAW ER/A 503250-14 REV ORIG.

Part: SKIN — DAMAGED (BS 636-655) · airframe 62,177 hrs · 47,517 cycles

DURING HMV, LIGHTNING STRIKES WERE FOUND ON RT WINDOW BELT AT FWD LWR CORNER BTW STA Y=636-655. WINDOW BELT WAS BLENDED OUT AND DOUBLER INSTALLED IAW ER/A 503245-14 REV ORIG.

Part: SKIN — DAMAGED (BS 1174-1193) · airframe 62,177 hrs · 47,517 cycles

DURING HMV, LIGHTNING STRIKES WERE FOUND ON RT WINDOW BELT AT FWD LWR CORNER BTW STA Y=1174-1193. WINDOW BELT WAS BLENDED OUT AND DOUBLER INSTALLED IAW ER/A 503248-14 REV ORIG.

Part: SKIN — DAMAGED (BS 731-750) · airframe 62,177 hrs · 47,517 cycles

DURING HMV, LIGHTNING STRIKES WERE FOUND ON WINDOW BELT AT FWD LWR CORNER BTW STA Y=750-731. WINDOW BELT WAS BLENDED OUT AND DOUBLER WAS INSTALLED IAW ER/A 503246-14 REV ORIG.

Part: SKIN — CORRODED (BS 1121-1124) · airframe 62,177 hrs · 47,517 cycles

DURING HMV, CORROSION WAS FOUND ON FUSELAGE SKIN UNDER WING TO FUSELAGE FILLET FAIRING STA Y=1121-1124 BTW LONGS 26LH-27LH. CORROSION WAS BLENDED OUT AND DOUBLER INSTALLED IAW MD-88SRM 53-04 PARA 57.

Part: SKIN — DAMAGED (BS 655-674) · airframe 62,177 hrs · 47,517 cycles

DURING HMV, LIGHTNING STRIKE WAS FOUND ON LT WINDOW BELT AT AFT/LOW CORNERS BTW STA Y=655-674. WINDOW BELT WAS BLENDED AND DOUBLER INSTALLED IAW ER/A 503249-14 REV ORIG.

Part: SKIN — CORRODED (BS 769 L27-28L) · airframe 62,177 hrs · 47,517 cycles

DURING HMV CORROSION WAS FOUND ON FUSELAGE SKIN UNDER WING TO FUSELAGE FILLET FAIRING STA Y=769 BETWEEN LONGERON 27 LT AND 28 LT FUSELAGE SKIN WAS BLENDED OUT AND REPAIR DOUBLER INSTALLED REF SRM 53-04 PARA 57.

Part: SKIN — DAMAGED (VERTICAL STAB) · airframe 62,177 hrs · 47,517 cycles

DURING HMV, ELONGATED HOLES WERE FOUND ON VERTICAL STABILIZER LEADING EDGE SKIN STA ZFS=55.813. ELONGATED HOLES IN SHIN WERE REAMED AND BUSHINGS INSTALLED REF EA 09-470871-12AD REV G ME08.

Part: SKIN — CORRODED (HORIZONTAL STAB) · airframe 62,177 hrs · 47,517 cycles

DURING HMV, CORROSION WAS FOUND ON RT HORIZONTAL STAB CTR SECTION UPPER BARREL NUT HOLES STA XH=7 (5 PLACES). CORROSION WAS REMOVED FROM BARREL NUT HOLES, REAMED AND BUSHINGS INSTALLED REF ER/A 502181-14 REV ORIG.

Part: SKIN — CORRODED (HORIZONTAL STAB) · airframe 62,177 hrs · 47,517 cycles

DURING HMV, CORROSION WAS FOUND ON BARREL NUT HOLES NR 21 AND 22 RT HORIZONTAL STAB UPPER SKIN STA XH=27 CORROSION WAS REMOVED FROM BARREL NUT HOLES. REAMED AND BUSHING INSTALLED REF ER/A 502181-14 REV ORIG.

Part: SKIN — CORRODED (HORIZONTAL STAB) · airframe 62,177 hrs · 47,517 cycles

DURING HMV CORROSION WAS FOUND ON LT HORIZONTAL STABILIZER CTR SECTION UPPER BARREL NUT HOLES (4 PLACES) STA XH=7. CORROSION WAS REMOVED FROM BARREL NUT HOLES, REAMED AND BUSHINGS INSTALLED REF ER/A 502181-14 REV ORIG.

Part: SKIN — CRACKED (FUSELAGE) · airframe 62,177 hrs · 47,517 cycles

DURING HMV, CRACKS WERE FOUND ON FUSELAGE SKIN STA Y=1437 BTW LONGERON 2 AND 4LT. MAINTENANCE BLENDED OUT THE DAMAGED AREA AND INSTALLED A REPAIR DOUBLER.

Part: BEAM — CRACKED (SERVICE DOOR) · airframe 62,177 hrs · 47,517 cycles

CRACK ON AFT SECTION OF BEAM NR 1 AT FWD SERVICE DOOR. WAS INSTALLED IAW SRM 52-05-0 FIG 40 & SRM 51-10-4.

Part: PAN — CRACKED (MID CARGO DOOR) · airframe 62,177 hrs · 47,517 cycles

MID CARGO DOOR PAN GOUGED. DOUBLER REPAIR INSTALLED IAW SRM 52-05D FIG 50.IG 50.

Part: CUSP WEB — CORRODED (BS 388-433) · airframe 62,177 hrs · 47,517 cycles

CORR ON RT CUSP WEB STA Y=388-408,408-417 AND 427-433 X=-54 TO X=-60. NEW WEB INSTALLED IAW DRD 53-20-02D PAR 802.

Part: SKIN — CRACKED (FUSELAGE) · airframe 62,177 hrs · 47,517 cycles

CRACKS UPPER CORNER OF FWD CARGO DOOR CUTOUT. DOUBLER REPAIR ACCOMPLISHED IAW ER/A 502190-14AD REV ORIG.

Part: WIRE HARNESS — FAULTY (CABIN) · airframe 61,803 hrs · 47,272 cycles

DURING LINE CHECK, MAINTENANCE FOUND THAT THE EMERGENCY EXIT SIGN AT THE WING EXIT HATCH IN ROW 13DE WAS INOPERATIVE. MAINTENANCE REPLACED THE WIRE HARNESS AND FUNCTIONALLY CHECKED THE SYSTEM.

Part: CABLE — MISINSTALLED (TAILCONE) · airframe 61,746 hrs · 47,230 cycles

TAIL CONE SLIDE INSTALLATION FAILED ROUTINE INSPECTION IN CVG. THE HARNESS CABLE WAS FOUND TO BE INCORRECTLY INSTALLED AT THE LEFT ATTACH POINTS. MAINTENANCE DID CORRECT THE INSTALLATION PER ERA 493276-14. RE-INSPECTED AND APPROVED.

Part: SKIN — DAMAGED (FUSELAGE) · airframe 61,345 hrs · 46,977 cycles

FUSELAGE SKIN FS 340 L-6R LIGHTNING STRIKE. REPAIRED IAW ERA 498140-14.

Part: STRINGER SPLICE — CORRODED (FUSELAGE) · airframe 59,390 hrs · 45,577 cycles

STRINGER SPLICE CORRODED AT STA 484. REPLACED STRINGER SPLICE PART NR 3924814-503 PER DWG 3924814.

Part: WIRE — BROKEN (EMERGENCY LIGHT) · airframe 59,238 hrs · 45,467 cycles

DURING LINE CHECK MX, FOUND EMERGENCY PATH LIGHT AT 38DE INOPERATIVE. MX REPAIRED BROKEN WIRE IAW AMM. OPS OF LIGHT NOW CHECKS OK.

Part: WIRE — DAMAGED (CABIN) · airframe 57,892 hrs · 44,528 cycles

MAINTENANCE FOUND THE EMERGENCY ESCAPE PATH LIGHT AT SEAT 3C TO BE INOPERATIVE. MAINTENANCE RE-TERMINATED THE WIRE AT SEAT 3C. AN OPERATIONAL CHECK WAS PERFORMED AND THE AIRCRAFT WAS RETURNED TO SERVICE (2010-D0836)(DLM88101852).

Part: SKIN — DAMAGED (VERTICAL STAB) · airframe 57,566 hrs · 44,302 cycles

VERT STAB L/E SKIN UPPER REM PNL LWR EDGE REPAIRED IAW ERA 482723-14.

Part: FRAME — CRACKED (FUSELAGE) · airframe 56,903 hrs · 43,872 cycles

REPAIR OF CRACKS PER INSP OF FUSELAGE OVERWING FRAMES IAW EA 09-460094-12, ME03.

Part: GCU — FAULTED (GENERATOR) · airframe 56,479 hrs · 43,635 cycles

RT ENG GEN FAULT ON T/O ROLL AT 40KIAS. REPLACED RT GCU IAW MM. RAN RT ENG WITH GEN LOADED SEVERAL TIMES. OPS CK NML. VOLTS AND FREQS NML. MCO/PLAC RMVD.

Part: SUPPORT FITTING — UNKNOWN (DOOR) · airframe 53,605 hrs · 41,763 cycles

AFT BB DOOR STOP SPPT FITTING REPLACED IAW EA 09-451701-12, ME11.

Part: SEAL — DAMAGED (WASTE DRAIN) · airframe 52,520 hrs · 41,030 cycles

FWD & AFT WASTE DRAIN VALVE SEAL REPAIRED IAW ERA 468214-14.

Part: TURBINE — FAILED (NR 2 ENGINE) · airframe 51,892 hrs · 40,600 cycles

IN FLT RETURN RT ENG FAILURE DURING CLIMB-OUT NORMAL PWR T/O WITH ENG A/I ON. ALL INDICATIONS NORMAL. AT 1300' AGL BUMP NOISE LIKE A COMP STALL. PERFORM INITIAL ACTION ITEMS AND STARTED RETURN TO AIRPORT. PLANNED TO RUN ENG AT IDLE BUT APPROX 2-3 MIN ENG STARTED TO VIBRATE. CONT ENG FAILURE CKLIST AND SECURED RT ENG NORMAL LANDING. REMOVED AND REPLACED RT ENG PER TRANSMITTAL 9T102.

Part: PULLEY — OBSTRUCTED (LT RUDDER PEDAL) · airframe 49,249 hrs · 38,843 cycles

DURING FLIGHT CONTROL CHECK, LEFT RUDDER PEDAL WAS STUCK. RIGHT PEDAL DEFLECTION NORMAL. NOSE WHEEL STEERING NORMAL. ALL HYD PRESS GOOD. PEDAL CAME FREE WITH A LOUD SNAP INSIDE RUDDER HOUSING ON CAPTS SIDE. NOW CHECKS NORMAL OPEN NOSE GEAR DOORS AND NOSE GEAR COMPARTMENT FOR INSPECTION OF RUDDER PEDAL. ALSO, REMOVED INSULATION WALL FOR INSPECTION 713249 FOUND AND REMOVED DEBRIS FROM BOTH LOCKOUT CAM/ROD ASSY AND PULLEY. CK CABLES PULLEYS ETC. NO OTHER DISCREPANCIES

Part: SKIN — CORRODED (FUSELAGE) · corrosion level 2 · airframe 47,848 hrs · 37,891 cycles

CORROSION ON SKIN AFT LAV SERVICE COMPT. REPAIRED BY BLENDING, MECHANICALLY REMOVING CORROSION, FABRICATED AND INSTALLED INTERNAL REPAIR DOUBLER 13.75 X 13.175 X 7.73. FROM 6AL-4V .032 IAW DC-9/MD-80 SRM 53-01 FIG 1AND 51-10-3, AND DELTA ERA 098896-14 REV B AND 397822-14MA REV ORIGINAL.

Part: ANGLE — CORRODED (FUSELAGE) · corrosion level 2

S/O NR 291017, N/R 27938 CORROSION AFT CARGO (Z) ANGLE AT LOWER DOOR OPENING FS 1155 TO FS 1212. REMOVED CORROSION, FOUND OUT OF LIMITS. FABRICATED AND INSTALLED (Z) ANGLE REPAIR 45.7 INCHES X 2.0 INCHES FROM 7075-T6 CLAD .071INCHES IAW SRM 51-30-05, 53-05D FIG. 63 AND DWG NR 5936038 CHG. E ADV.

Part: PAN — CRACKED (FUSELAGE) · corrosion level 2 · airframe 47,848 hrs · 37,891 cycles

S/O 291017 N/R 28606 AND 28610, CORROSION AND CRACKS ON OUTER DOOR PAN ON C-3 DOOR.BLENDED AND CUT OUT CRACKED AREA. FABRICATED AND INSTALLED 2 EA. REPAIR DOUBLERS 16 INCHES LONG FROM 64L-4V .063 AND REPAIR ANGLE 6.0 INCHES X 1.8 INCHES X .81 INCH FROM 2024-T3 .063 INCH AND 3 EA. PAN REPAIRS 18.25 INCH X 2 INCHES, 9.25 INCHES X 2 INCHES AND 12.5 INCHES X 2.3 INCHES FROM 6AL-4V .063 REPAIR DOCUMENT 52-05D AND SRM 51-30-5.

Part: SKIN — DAMAGED (FUSELAGE)

CREASE IN FUSELAGE SKIN FS 218 BETWEEN L-18L AND L-19L. CUT OUT CREASED AREA OF SKIN AT LONGERON 18L AND 19L. FABRICATED AND INSTALLED REPAIR DOUBLER 34.0625 X 9.40 INCHES FROM 2024-T3 .063 AND P/N S2912900-5U5000 IAW MD-88 SRM 53-04D FIG 25 AND 51-30-0.

Part: DOOR FRAME — CORRODED (FUSELAGE) · corrosion level 2

AFT ENTRANCE DOOR LOWER CUTOUT FWD FACE CORRODED (ADJACENT TO FLOOR SUPPORT RBL 20 TO LBL 20 WL 208. CUT OUT 2 EA CORRODED SECTIONS OF DOOR CUTOUT. FABRICATED AND INSTALLED DOOR JAMB REPAIR 3 X 4.75 X 1 X 2 INCHES FROM 2024-T3 AND 2 EA FILLERS 4.7 X 1.6 INCHES AND 1.3 X 2.3 INCHES FROM 2024-T3 .050 CLAD IAW DC-9/MD-80 SRM 53-05 FIG 34.

Part: SEAT TRACK — CORRODED (FUSELAGE) · corrosion level 2

S/O 291017, NR 27796 CORROSION/WEAR MARK IN SEVERAL AREAS AT CABIN LT IB SEAT TRACK AND UPPER FLANGE FASTENER HOLES FROM FS 1174 - 1309. REMOVED AND REPLACED SECTION OF SEAT TRACK P/N 53-0997-004 FROM FS 1260 - 1309 AND SPLICE P/N ACA7413-505 IAW SRM 53-05 FIG. 4F, 51-10-3D PG. 17, 19, 24, 25, 28, 53-24-0 FIG. 6A, 51-10-1 FIG. 26.

Part: SKIN — LIGHTNING STRIKE (FUSELAGE) · airframe 47,848 hrs · 37,891 cycles

S/O 291017 N/R NR 28450 EXTERNAL FUSELAGE HAS SEVERAL LIGHTNING STRIKES FROM FS 150 TO FS 186 L-3L TO L-5L. BLENDED IAW SRM 53-04D FIG. 38. NDT VERIFIED THICKNESS IAW STME 797-95 (2001). FABRICATED AND INSTALLED REPAIR DOUBLER 9 INCHES X 6 INCHES FROM 2024-T3 .050 INCHES AND 7.5 INCHES X 7.2500 INCHES FROM 2024-T3 .025 IAW 53-04 FIG. 38, 51-10-3D AND 51-30-2.

Part: CUSP WEB — CORRODED (FUSELAGE) · corrosion level 2

CORROSION ON LT CUSP WEB FS 503 TO 522. CUT OUT CORRODED AREA OF WEB. FABRICATED AND INSTALLED WEB REPAIR 12.5 X 3.25 INCHES FROM P/N 53-1060-006 IAW MD-80 SRM 53-01 FIG 1 AND FIG 4, 51-30-5, AND 51-10-3D.

Part: CUSP WEB — CORRODED (FUSELAGE) · corrosion level 2

CORROSION ON LT CUSP WEB FS 522 TO 541. CUT OUT CORRODED AREA OF WEB. FABRICATED AND INSTALLED WEB REPAIR 10.5 X 10.875 INCHES FROM 7075-T6 .032 IAW MD-80 SRM 53-01 FIG 1 AND FIG 4, 51-30-2, AND 51-10-3D.

Part: SKIN — LIGHTNING STRIKE (BS 215)

EXTERNAL FUSELAGE HAS LIGHTNING STRIKES FS 215 L-2R. CUT OUT LIGHTNING STRIKE AFFECTED AREA. FABRICATED AND INSTALLED REPAIR INTERNAL DOUBLER 8.5 X 6.875 INCHES FROM 2024-T3 .025 AND DOUBLER 4.875 X 7.5 INCHES FROM 2024-T3 .063 IAW MD-80 SRM 53-04D PG 218 FIG 38 SHEET 35, 51-10-3D, 51-30-2 AND 51-30-0 PG 1.

Part: DOUBLER — CORRODED (BS 755) · corrosion level 2

CORROSION AT MID CARGO COMPARTMENT FS 755 L-29L TO L-29R. FOUND INNER DOUBLER 100 PERCENT MATERIAL LOSS. FABRICATED AND INSTALLED DOUBLER 5.5 X 1 INCH FROM 7075-T6 .032 IAW MD-80 SRM 51-30-5, 53-01 DRD 51-010, SRM 51-10-3D AND DPS 900-2 NR 5.

Part: CUSP WEB — CORRODED (BS 617-636) · corrosion level 2

CORROSION RT CUSP WEB FS 617 TO FS 636. FABRICATED AND INSTALLED DOUBLER REPAIR 35.25 X 4.25 INCHES FROM 7075-T6 .032 IAW DC-9/MD-80 SRM 53-01D FIG 4 AND 51-70-4 FIG 2.

Part: CUSP WEB — CORRODED (FUSELAGE) · corrosion level 2

CORROSION ON CUSP WEB FS 389 TO FS 408. CUT OUT CORRODED WEB. CUT TO FIT AND INSTALLED REPAIR DOUBLER P/N 531060008 IAW MD-88 SRM 53-01 PG 19, 51-30-1, 51-30-5 AND DELTA ERA 398191-MA DATED 9-18-02.

Part: CUSP WEB — CORRODED (BS 1152-1155) · corrosion level 2

CORROSION ON L-2 DOOR CUSP WEB. BLENDED CORROSION. FABRICATED AND INSTALLED DOUBLER REPAIR 5.6 X 6.7 INCHES FROM 7075-T6 .071 IAW DELTA ERA 398191-14MA ISSUED 9-18-02.

Part: WEB — CORRODED (BS 1157-1160) · corrosion level 2

CORROSION ON LT WEB PANEL ADJACENT TO L-2 DOOR. CUT OUT CORRODED SECTION OF PANEL. FABRICATED AND INSTALLED REPAIR DOUBLER 8.0 X 9.0 X 10.0 INCHES FROM 7075-T6 .071 IAW MD-80 SRM 53-01 FIG 1, 51-30-5, AND 51-10-3D.

Part: CUSP WEB — CORRODED (BS 636-655) · corrosion level 2

CORROSION ON LT CUSP WEB FS 636 TO 655. CUT OUT CORRODED AREA OF WEB. FABRICATED AND INSTALLED WEB REPAIR 18 X 3 INCHES FROM 87075-T6 .032 IAW MD-80 SRM 53-01 FIG 1, 51-30-1 AND 51-10-3D.

Part: SEAT TRACK — CORRODED (BS 1079-1309) · corrosion level 2

CORROSION WEAR MARK ON SEVERAL AREAS AT CABIN LT CENTER SEAT TRACK AND UPPER FLANGE FASTENER HOLES FROM FS 1079 TO 1309. REMOVED CORROSION AND WEAR MARKS IAW DC-9/MD-80 SRM 51-10-3D. REMOVED OUT OF LIMITS SECTION OF SEAT TRACK FS 1088 TO FS 1200. INSTALLED REPLACEMENT TRACK P/N 53-0997-006 IAW MD-80 SRM 53-05D FIG 4 AND 51-30-5.

Part: FRAME — CORRODED (BS 1380) · corrosion level 2

CORROSION FS 1380 L-29 FWD/AFT SIDE OF FRAME. BLENDED CORROSION. FABRICATED AND INSTALLED DOUBLER REPAIRS 8.2 X 3 X 2.1 INCHES AND 8 X 2 X 1.1 INCHES FROM 7075-T6 .032 IAW MD-80 SRM 53-01 FIG 2, 51-30-5D.

Part: CUSP WEB — CORRODED (BS 693-712) · corrosion level 2

CORROSION LT CUSP WEB FS 693 TO FS 712. BLENDED CORROSION. RECEIVED AND INSTALLED DOUBLER REPAIR P/N 53-1060-006 IAW DC-9/MD-80 SRM 51-70-4, 51-10-3D, 51-30-2 AND DELTA ERA 413196-14MA ISSUED 5-15-03.

Part: CUSP WEB — CORRODED (BS 920-946) · corrosion level 2

CORROSION RT CUSP WEB FS 920 TO FS 946. CUT OUT CORRODED SECTION OF WEB. FABRICATED AND INSTALLED CUSP WEB REPAIR DOUBLER 4.70 X 4.30 INCHES FROM 7075-T6 .040 IAW DC-9/MD-80 SRM 53-01 FIG 4 SHT 4, 51-10-3D AND 51-30-5.

Part: CUSP WEB — CORRODED (FUSELAGE) · corrosion level 2

CORROSION ON LT CUSP WEB FS 446 TO FS 465. CUT OUT CORRODED WEB. FABRICATED AND INSTALLED REPAIR DOUBLER 2.5" 1.5" X 2" X 2" FROM 7075-T6 .020 AND P/N 53-1060-002 IAW MD-88 SRM 53-01 PG 19, 51-30-2 PG 1 AND PS 900-2-4-1 NR 2.

Part: CUSP WEB — CORRODED (FUSELAGE) · corrosion level 2

CORROSION ON LT CUSP WEB FS 408 TO FS 427. CUT OUT CORRODED WEB. FABRICATED AND INSTALLED REPAIR DOUBLER 7 X 3 INCHES FROM 7075-T6 .032 IAW MD-88 SRM 51-70-4 FIG 13-01 PG 19, 51-30-1, 51-30-5 AND DELTA ERA 413196-14MA DATED 5/15/03.

Part: CUSP WEB — CORRODED (BS 1060-1079) · corrosion level 2

CORROSION ON LT CUSP WEB FROM FS 1060 TO 1079. CUT OUT CORRODED SECTION OF WEB. DRILLED UP DOUBLER P/N 53-1060-008 AND INSTALLED IAW MD-80 SRM 51-10-3D, 51-30-2, AND 51-10-3D.

Part: CUSP WEB — CORRODED (FUSELAGE) · corrosion level 2

CORROSION RT CUSP WEB FS 426 TO FS 446. CUT OUT CORRODED SECTION OF WEB. FABRICATED AND INSTALLED WEB REPAIR 7.5 X 3 INCHES FROM 7075-T6 .032" IAW DC-9/MD-80 SRM 53-01 FIG 4 SHT 4, 51-10-3D PARA 23, 30, AND 51-30-5.

Part: SKIN — GOUGED (CARGO DOOR)

C-3 CARGO DOOR FWD INSIDE EDGE GOUGED. BLENDED GOUGES, ORIGINAL THICKNESS .050", .032" MATERIAL REMAINING, NDT VERIFIED OUT OF LIMITS. INSTALLED DELTA GENERIC 383 REPAIR DOUBLER IAW MD-80 SRM 52-33-0 FIG 1, 52-01 FIG 1, 51-30-5, 52-03D FIG 8.

Part: CUSP WEB — CORRODED (FUSELAGE) · corrosion level 2

CORROSION ON LT CUSP WEB FS 731 TO 750. FABRICATED AND INSTALLED WEB REPAIR FROM 7075-T6 .020" IAW MD-80 SRM 53-01 FIG 1, 51-30-5, AND 51-10-3D.

Part: CUSP WEB — CORRODED (BS 769-788) · corrosion level 2

CORROSION RT CUSP WEB FS 769 TO FS 788. FABRICATED AND INSTALLED CUSP WEB ANGLE 6.875 X 1 X 1.875 INCHES FROM 7075-T6 .080 IAW DC-9/MD-80 SRM 51-10-2, 51-70-5, 51-10-3D AND 51-30-5.

Part: CUSP WEB — CORRODED (BS 1098-1117) · corrosion level 2

CORROSION RT CUSP WEB FS 1098 TO FS 1117. CUT OUT CORRODED SECTION OF WEB. FABRICATED AND INSTALLED REPAIR DOUBLER 16.25 X 3.375 INCHES FROM 7075-T6 .032 IAW DC-9/MD-80 SRM 51-70-4 FIG 2, 51-70-4 FIG 2, AND 51-30-2 AND 51-30-4.

Part: CUSP WEB — CORRODED (BS 985-1000) · corrosion level 2

CORROSION RT CUSP WEB FS 985 TO FS 1000. CUT OUT CORRODED SECTION OF WEB. FABRICATED AND INSTALLED WEB REPAIR 3.25 X 3.50 X 5 X 3.50 INCHES FROM 7075-T6 .025 IAW DC-9/MD-80 SRM 53-01 FIG 4 SHT 4, 51-10-3D PARA 23, 30, AND 51-30-5.

Part: CUSP WEB — CORRODED (BS 980-1003) · corrosion level 2

CORROSION ON LT CUSP WEB FROM FS 980 TO 1003. CUT OUT CORRODED SECTION OF WEB. FABRICATED AND INSTALLED DOUBLER 14 X 3.125 INCHES FROM 7075-T6 .032 IAW MD-80 SRM 53-01 FIG 1 AND ERA 398191-14MA DATED 9/16/02.

Part: CUSP WEB — CORRODED (BS 115-1174) · corrosion level 2

CORROSION RT CUSP WEB FS 1155 TO FS 1174. CUT OUT CORRODED SECTION OF WEB. FABRICATED AND INSTALLED REPAIR DOUBLER 15.6 X 7.7 INCHES FROM 7075-T6 .032 IAW DC-9/MD-80 SRM 53-01 FIG 1, 51-70-4 FIG 2 AND 51-10-3D.

Part: CUSP WEB — CORRODED (BS 636-665) · corrosion level 2

CORROSION RT CUSP WEB FS 636 TO FS 665. FABRICATED AND INSTALLED CUSP WEB 10.4 X 2.6 INCHES FROM 7075-T6 .025 IAW DC-9/MD-80 SRM 53-01 FIG 4, 53-74-0D FIG 4, 51-30-2 PG 1&12 AND 51-10-3D PAGE 16.

Part: CUSP WEB — CORRODED (BS 665-684) · corrosion level 2

CORROSION RT CUSP WEB FS 665 TO FS 684. FABRICATED AND INSTALLED CUSP WEB 15 X 2.7 INCHES FROM 7075-T6 .025 IAW DC-9/MD-80 SRM 53-01 FIG 4, 53-74-0D FIG 4, 51-30-2 PG 1&12 AND 51-10-3D PAGE 16.

Part: TERMINAL BLOCK — ROTTED (LAVATORY LIGHTS) · airframe 47,848 hrs · 37,891 cycles

ORIG FAA FINDING, LAV LIGHT ASSY, TERMINAL BLOCKS HAVE DRY ROTTED CONNECTOR INSULATION THIS IS FOUND BY REMOVING THE VERTICAL LIGHT LENS AND THAT WILL EXPOSE THE TERMINAL STRIP OR BLOCK THE CONNECTOR ON THAT STRIP WILL HAVE A PLASTIC INSULATION COATING THAT WILL DISINTEGRATE UPON TOUCH. THIS COULD RESULT IN THE CONNECTORS TOUCHING OR SHORTING. REPAIRED WIRING PER AMM 20.

Part: SKIN — GOUGED (BS 556)

GOUGE ON LOWER FUSELAGE SKIN AT L-30 TO L-29R FS 556. GOUGE FOUND TO BE CRACKED. CUT OUT CRACKED AREA, FABRICATED AND INSTALLED DOUBLER 8 X 6.75 INCHES FROM 2024-T3 .050 AND FINGER DOUBLER 10 X 8.25 INCHES FROM 2024-T3 .025 IAW MD-80 SRM 53-04D FIG 38.

Part: SKIN — CRACKED (FUSELAGE)

S/O 291017 NR 26766 FUSELAGE SKIN HAS A CRACK AT FS 390 L-30 TO L-29R. CUT OUT CRACKED AREA, HFEC, NO CRACKS INDICATED, FABRICATED AND INSTALLED 8" X 7" SKIN REPAIR FROM 2024-T3 .050 AND FINGER DOUBLER 8-1/2" X 7-5/8" FROM 2024-T3 .025 IAW MD-88 SRM 53-04D, FIG 38.

Part: FLASHLIGHT — UNSERVICEABLE (1L DOOR) · airframe 45,014 hrs · 35,877 cycles

FLASHLIGHT AT 1L DOOR INOP NOT FLASHING. REPLACED SAME.

Part: WATER HEATER — SHORTED (FWD LAVATORY) · airframe 44,263 hrs · 35,382 cycles

DURING DESCENT FWD LAV SMOKE DETECTOR WENT OFF. F/A NOTED A CHEMICAL SMELL WHEN THE DOOR WAS OPENED. REPLACED OVERHEATED WATER HEATER.

Part: MASK — MALFUNCTIONED (COCKPIT OXYGEN) · airframe 43,179 hrs · 34,618 cycles

CAPTS 02 MASK ALLOWS TO FLOW IN BUT NOT TO EXHALE. REPLACED MASK ASSY.

Part: BULB — BURNED OUT (LTGEAR IND) · airframe 40,881 hrs · 33,071 cycles

A/C DID FLY BY TO CONFIRM GEAR DOWN LOG BOOK WRITE UP WAS: BULB BURNED OUT IN LT MAIN GEAR INDICATOR. RELAMPED INDICATOR.

Part: ADC — FAILED (COCKPIT) · airframe 40,163 hrs · 32,568 cycles

CAPT LOST AIRSPEED INDICATOR AFTER AIRBORNE. FLT 1425 DIVERTED TO BOSTON FROM PVD. REPLACED NR 1 CADC PER MM. ALL CHECKS OK.

Part: BRAKE ASSY — BROKEN (NR 3) · airframe 39,041 hrs · 31,795 cycles

AFTER PUSHBACK A/C WOULD NOT TAXI. FOUND NR 3 BRAKE BROKEN & SEIZED. REPLACED NR 3 BRAKE AND WHEEL ASSY.

Part: BOLT — SHEARED (RIGHT GEAR) · airframe 36,336 hrs · 29,794 cycles

IRREG: GEAR DOOR OPEN AND RT GEAR UNSAFE LIGHT IN FLT CORR. ACT: FOUND LWR. BOLT FOR ACTUATOR LINK ASSY. SHEARED REPLD BOLT.

Part: ODOR — DETECTED (CABIN) · airframe 35,688 hrs · 29,327 cycles

AFTER TAKEOFF SMELLED ODOR IN CABIN. FIRST IN THE BACK THEN UP FRONT AND IN COCKPIT, PASSENGERS SAID IT SMELLED LIKE OIL. CREW THOUGHT IT SMELLED ELECTRICAL. PERFORMED DUCT BURNOUT.

Part: WIRE — BROKEN (CABIN) · airframe 35,686 hrs · 29,324 cycles

PAX SEAT 35 D/E EMERGENCY LIGHT INOP. FOUND BROKEN WIRE. REPLACED SEAT HARNESS EMERGENCY LIGHT, NOW NORMAL.

Part: SKIN — DAMAGED (FUSELAGE) · airframe 32,865 hrs · 27,245 cycles

EXISITNG DENT FOUND IN SKIN AT STA 320 AT LONGERON L-26R. REPAIRED IN ACCORDANCE WITH ER/A 334689-14.

Part: FAIRING — MISSING (LT WING) · airframe 32,258 hrs · 26,797 cycles

AILERON TRIM WILL NOT MOVE LEFT OR RIGHT IN CRUISE. WORKED IN CLIMB BUT JAMMED IN CRUISE WITH A/P OFF AND ON. FOUND LT AILERON TRAILING EDGE TRIM TAB ROD COVER FAIRING (UPPER PORTION) MISSING. REPLACED COVER. OPERATION NOW CHECKS NORMAL.

Part: FAN — SEIZED (AIR DISTRIBUTION)

UNIDENTIFIED FUMES IN CABIN. FOUND FUMES COMING FROM CEASED CABIN AIR RECIR FAN. PULLED AND COLLARED C/B'S, FWD RECIR FAN TO MCO AND PLAC PER MEL 21-00-43.

Part: INDICATOR — MALFUNCTIONED (LANDING GEAR)

NOSE WHEEL AND MAIN LANDING GEAR INDICATORS INDICATED UNSAFE UNTIL INDICATOR LIGHTS WERE PRESS. THIS CAUSED A GO-AROUND. REPLACED PROX BOX, JACKED A/C, RAN SEVERAL TIMES AND NO FAULTS. CHECKED PROX SWITCHES, ALL GEAR AND NO FAULTS. A/C CKS GOOD FOR SERVICE PER MM CHAP 31, 32.

Part: NAV DISPLAY — FAILED (COCKPIT)

CAPTS NAV DISPLAY FUZZY. SWITCHED TO EIFS BOTH ON 2, NO HELP. SWITCHED BACK TO NORMAL AND THE CAPTS PRI FLT DISPLAY SIZZLED AND WENT BLANK. USED COMPACT ON LOWER SCREEN BUT, STILL FUZZY. HAD ELEC SMELL AND SMOKE. PULLED C/B'S AND DIVERTED TO BUF. REPLACED CAPT PFD.

Part: BRACKET — BROKEN (LT LE FLAP)

LEFT 0 SLAT EXTEND CABLE PULLEY BRACKET BROKEN JUST OUT BOARD OF THE LT 0 SLAT DRIVE TRACK. THE BRACKET CAUSED DAMAGE TO A 16 WIRE BUNDLE JUST O/B OF THE LT 0 SLAT DRIVE TRACK. THE WIRES WERE SPLICED AND THE SLATS RETRACTED THE A/C WAS FERRED TO ATL ON FLIGHT 9935 FOR FUTHER REPAIR.

Part: TAIL CONE — DAMAGED (AFT FUSELAGE)

TAIL CONE DEPLOYED. REPAIRED TAIL CONE DAMAGE PER ERA 362367-14. REINSTALLED TAIL CONE ESCAPE SLIDE DID NOT DEPLOY BECAUSE PREV HYD LEAK SOAKED VELCRO HOLDDOWN FOR LANDYARD NOT ALLOWING FOLLOW-UP OF SAME TO PULL SLIDE CVR OFF SLIDE. CLEANED VELCRO AND RESECURED LANDYARD, PERFORMED TAIL CONE DROP TEST.

Part: WINDSHIELD — CRACKED (RT COCKPIT)

AT FLT LEVEL 310, F/O WINDSHIELD CRACKED. REPLACED F/O WINDSHIELD AND CONTROLLER.

Part: UPLOCK SENSOR — MALFUNCTIONED (NLG)

NOSE GEAR UNSAFE LIGHT ILLUMINATED AT CRUISE ALTITUDE AND REMAINED ILLUMINATED WHEN AUX AND TRANSFER PUMPS TURNED ON. REPLACED NOSE GEAR UPLOCK SENSOR, SWUNG NOSE GEAR AND PERFORMED BITE ON PROX BOX, ALL INDICATIONS NORMAL.

Part: FRAME — CRACKED (RT MLG WW)

FOUND DURING A-1 LETTER CHECK - RT FWD WHEELWELL FRAME CRACKED O/B SIDE. REPAIRED PER SRM 53-05, FIG 78A.