N903DE

Part: CONNECTOR — DAMAGED (TAILCONE HANDLE) · airframe 71,517 hrs · 52,831 cycles

TAILCONE UNSAFE ILLUMINATED INTERMITTENTLY ON PUSH BACK. R/R EXT. HANDLE SWITCH CONNECTOR (P1-779). SYS OPS NORMAL AT THIS TIME REF MD88 AMM 52-70. (LP5586780)

Part: LINE — LEAKING (HYD SYSTEM) · airframe 71,498 hrs · 52,813 cycles

AFTER STARTING THE APU & TURNING PACKS ON FOR HEAT THE AFT MIDDLE CABIN STARTED TO FILL W/SMOKE & FUMES. FOUND APU INLET CONTAMINATED WITH HYDRAULIC FLUID DUE TO LEAK FROM RT T/R ACCUMULATOR SUPPLY LINE. SECURED LINE CLEANED AREA AND LEAK CKD. NO OTHER LEAKS FOUND. C/W WORK CARD 2120-2367 USING STEP (14) PER MCC, C/W W/CARD 4950-2215 ALT. DUCT BURN FOR SKYDROL. REPLACED WATER COALESCER BAG PER W/C 2170-4139. NO SMOKE NO FUMES NO SMELL. NO GO ODI 2172 C/W.

Part: BATTERY PACK — INOPERATIVE (EMERGENCY LIGHTS) · airframe 71,058 hrs · 52,389 cycles

CABIN AND BOTH FWD ENTRANCES EMERGENCY LIGHTS AT L2-175, L2-152 AND L2-155 INOP. REPLACED BATTERIES IN POWER SUPPLY PACK AT B5-23 PER MD88 AMM 33-53. OPS CHKS GOOD, A/C OK FOR SVC. (LP6216345)

Part: CONTROL MODULE — MALFUNCTIONED (FIRE WARNING) · airframe 69,770 hrs · 51,239 cycles

MID CARGO COMPARTMENT FIRE WARNING. LT ILLUM ON PANEL. EXTINGUISHED WITHIN 5 - 7 SECONDS WITH NO ACTIONS FROM CHECKLIST. GOOD SYSTEM AFTERWARD. COULD NOT DUPLICATE FAULT. REMOVED AND REPLACED CARGO DET-FIREX 3-BAY PANEL MODULE P/N ON/OFF 474007 S/N ON 0101 S/N OFF 1198. (LP5835402)

Part: UNKNOWN — ODOR (CABIN) · airframe 69,616 hrs · 51,102 cycles

AFTER ENG START PILOT IN CABIN 12C NOTICED OILY SMELL THROUGHT FLIGHT UNTIL ENG SHUTDOWN. NO SMELL IN COCKPIT. SUSPECT RT PACK OR RT ENG. RMVD BORO PLUGS FROM #1 AND #2 ENGS FOR INSP OF 6TH AND 13TH STAGE COMP. RMVD SADDLE DUCT CAPS FROM BOTH 8TH AND 13STAGE ON BOTH ENGS. MD88 MM 72-00. BOROSCOPED HPC 6/7/13 AND BOTH SADDLE DUCTS. NO EVIDENCE OF OIL FOUND ON BOTH NR 1 AND 2 ENGINES. RE INSTALLED NR 1 AND 2 ENG 6TH STAGE AND 13 STAGE BORO PLUGS PER M/M 72-00, RE INST SADDLE DUCT CLAMPS. RMVD RT A/C PACK FLOW CONT VALVES AND ACM Y DUCTS. NO EVIDENCE OF OIL CONTAMINATION, RE INSTALLED Y DUCTS AND FLOW CONT VALVES BOTH SIDES. NEEDS LK CK AND OPS CKS LT AND RT A/C PACK SYS. C/W ODI PREVENTION REF NO GO ODI PREVENTION PROGRAM ATA 2172 AND W/C'S 2120-2367, 2170-4139, AND 7100-2619. A/C SMELLS NORMAL ALL CHECKS NORMAL REF MD88 AMM 2125. (LP5015006)

Part: NUT — DEFECTIVE (LIGHT TERMINAL) · airframe 69,373 hrs · 50,898 cycles

SPARKS AND SMOKE CAME FROM WING LANDING LIGHT SWITCH DURING EXTENSION. R/R LT AND RT LANDING LIGHT SWITCHES PER MD88 AMM 33-41. DURING REPLACEMENT THOROUGHLY INSP WIRES AND TERM IN ADJACENT AREAS FOR BURN MARKS AND DEGRADATION. NO SIGNS OF TROUBLE. AFTER REPLACEMENT, PROBLEM STILL REMAINED. AFTER REMOVING LT SWITCH FOUND BURN MARKS ON B1 TERM OF LIGHT SWITCH. SWITCH TERM MAKING CONTACT WITH TRIM NUT. REPLACED TRIM NUT AND SCREW WITH APPROPRIATE SIZED HARDWARE. SWITCH NO LONGER MAKING CONTACT. ALL SWITCHES CHECK GOOD. OK FOR SVC. (LP4893064)

Part: FLEX LINE — LEAKING (FIRE EXTINGUISHE) · airframe 69,263 hrs · 50,811 cycles

WHILE WORKING CARD FIRE EXT. DEPLOYMENT LINE ROUTING AND LEAK CHECK, FOUND #1 BOTTLE LH ENG SUPPLY FLEX LINE LEAKING. R/R SUPPLY FLEX LINE PER MD88 AMM 26-20-04 LEAK CK GOOD. (LP5350797)

Part: ENGINE — FAILED (LEFT) · airframe 69,263 hrs · 50,811 cycles

SHIP 9003 - IFSD/ATB - DUE TO LEFT ENGINE FAILURE ON CLIMB-OUT. MAINTENANCE REPORTED TURBINE DAMAGE AND THE NUMBER 1 ENGINE WAS REPLACED. (LP5350786).

Part: ENGINE — OVERTEMP (LEFT) · airframe 69,263 hrs · 50,811 cycles

REF LOG 5350786 NBR 1 FIRE BOTTLE DISCHARGED DUE TO LEFT ENGINE FAILURE AND OVERTEMP. RMVD AND RPLCD NBR 1 FIRE BOTTLE PER MD88MM 26-20. CKS NML. A/C OK FOR SRVC. (LP5350788)

Part: FRAME — CRACKED (FUSELAGE) · airframe 69,236 hrs · 50,791 cycles

CRACKED FRAME STA Y 1463 CANT BELOW VENTRAL STAIRWAY ACTUATOR CYLINDER AT AFT ACC COMPARTMENT. CRACK FRAME STA Y 1463 WAS REPAIRED PER SRM 53-03 FIG 43.

Part: FRAME — WORN (BS 1388) · airframe 69,236 hrs · 50,791 cycles

INITIAL INSPECTION: WORN WEB ON CANTED FRAME STA 1388 REF LONG 3L AT AFT ACC COMPARTMENT. WEAR ON WEB CANTED FRAME STA 1388 REF LONG 3L WAS REPAIRED PER ER/A 573504-14 REV ORIG. (LP0851952)

Part: SMOKE DETECTOR — FALSE ACTIVATION (RT AFT LAVATORY) · airframe 68,641 hrs · 50,267 cycles

RIGHT AFT LAVATORY SMOKE DETECTOR ACTIVATED. INSPECTED THE AFT CABIN AND AFT LAVATORIES FOR SMOKE. NO SMOKE OR EVIDENCE OF SMOKE FOUND. REPLACED RT AFT LAVATORY SMOKE DETECTOR IAW AMM 26-13. CHECKED GOOD.

Part: ENGINE — MAKING METAL (LEFT) · airframe 68,180 hrs · 49,896 cycles

IN-FLIGHT SHUTDOWN AND DIVERSION TO GSP. THE FLIGHT CREW REPORTED THAT AT FL320 A SLIGHT ODOR AND VIBRATION OCCURRED; BOTH WENT AWAY THEN THE LEFT ENGINE OIL FILTER CLOG INDICATION ILLUMINATED AND THE VIBRATION RETURNED. THE ENGINE SHUT DOWN WHILE THE FLIGHT CREW WAS PERFORMING THE QRH PROCEDURES FOR OIL FILTER CLOG MESSAGE. MAINTENANCE FOUND METAL ON THE CHIP DETECTOR AND IN THE OIL FILTER. THE NUMBER 1 ENGINE WAS REPLACED AND THE AIRCRAFT WAS RETURNED TO SERVICE.

Part: BATTERY PACK — DISCHARGED (CABIN) · airframe 68,072 hrs · 49,807 cycles

EMERGENCY CEILING LIGHTS AT ROW 17-20 INOP. REPLACED BATTERY PACK AT B5-102 REF AMM 33-53. OPS CHECK GOOD.

Part: BATTERY PACK — INOPERATIVE (EMERGENCY LIGHTS) · airframe 66,805 hrs · 48,803 cycles

LEFT AND RIGHT AFT OVERWING EXIT DOOR EMERGENCY LIGHTS INOPERATIVE. CONFIRMED A BAD BATTERY PACK. REPLACED IAW AMM 33-53. CHECKED GOOD.

Part: BATTERY PACK — DISCHARGED (CABIN) · airframe 66,777 hrs · 48,779 cycles

DURING SERVICE CK FOUND ROW 25 UPPER OVERWING EMERGENCY LIGHTS AND ADJACENT CEILING LIGHTS INOP. REPLACED BATTERY PACK AND OPERATION CHECKS NORMALLY.

Part: SIGN — INOPERATIVE (EMERGENCY LIGHTS) · airframe 66,606 hrs · 48,637 cycles

AFT OVERWING UPPER EMERGENCY EXIT SIGNS NOT ILLUMINATED.

Part: CONNECTOR — DAMAGED (CABIN) · airframe 66,387 hrs · 48,448 cycles

SEAT 17D-E EMER PATH LIGHT INOP. R&R DAMAGED PLUG AND CONNECTORS PER AMM 2050. OPS CK GOOD.

Part: BATTERY PACK — DISCHARGED (CABIN) · airframe 66,252 hrs · 48,326 cycles

EMERGENCY EXIT LIGHTS INOP OVER THE OVER WING EXIT DOOR, AFT DOORS. DURING T/S FOUND EMERGENCY LIGHT BATTERY PACK B5-105 IN POOR CONDITION. RPLD PER WDM 33-51-12. OPS CK NML. OK FOR SVC.

Part: BATTERY PACK — INOPERATIVE (EMERGENCY LIGHTS) · airframe 66,252 hrs · 48,326 cycles

EMERGENCY EXIT LIGHTS INOPERATIVE OVER THE FWD OVERWING EXIT DOOR. REPLACED THE BATTERY PACK. CHECKED NORMAL. REPLACED IAW WDM 33-51-12. OK FOR SERVICE.

Part: PANEL — DELAMINATED (LT WING SPOILER) · airframe 64,606 hrs · 47,077 cycles

INBD PORTION OF LT WING GROUND SPOILER DELAMINATING. REMOVED, REPAIRED, AND INSTALLED THE PANEL IAW DWG 5936824.

Part: UNKNOWN — ODOR (CABIN) · airframe 64,238 hrs · 46,794 cycles

STRONG ODOR OF RUBBER & OIL IN MID CABIN AFTER TAKEOFF. ODOR CYCLES ON AND OFF THROUGHOUT CLIMBOUT. TROUBLESHOT AND NO DEFECTS NOTED. COMPLIED WITH PNEU SYS DUCT BURN OUT PER CARD 7100-2619. NO DEFECTS NOTED. (LP9306868)

Part: ACCESS PANEL — CORRODED (LT WING) · corrosion level 2 · airframe 64,210 hrs · 46,772 cycles

CORROSION ON SETTLEMENT AREA OF SECOND ACCESS NR 1303C AND 1307C AT LT WING. CORROSION ON SETTLEMENT AREA OF SECONDARY ACCESS NR 1307C WAS REPAIRED PER ER/A 551683-14AD REV. ORIGINAL AND CORROSION ON SETTLEMENT AREA OF SECONDARY ACCESS NR 1303C WAS REPAIRED PER ER/A 551743-14AD REV.

Part: FRAME — CRACKED (BS 733) · airframe 64,210 hrs · 46,772 cycles

CRACKED FRAME BS 733, LONGERONS 28 - 29L. THE FRAME WAS REPAIRED IAW SRM 51-70-11 REPAIR 1.

Part: FRAME — CHAFED (BS 1401) · airframe 64,210 hrs · 46,772 cycles

CHAFING BTW HYD CILYNDER LINE AND FRAME BS 1401, LONGERON 21R. THE FRAME WAS REPAIRED IAW SRM 53-03-D FIGURE 4

Part: FRAME — CRACKED (BS 1510) · airframe 64,210 hrs · 46,772 cycles

A CRACK ON FRAME BS 1510. THE FRAME WAS REPAIRED PER ER/A 497316-14MA REV. ORIGINAL AND SRM 51-30-5 AND 51-30-2.

Part: WEB — CORRODED (BS 430) · corrosion level 2 · airframe 64,210 hrs · 46,772 cycles

CORROSION ON WEB BETWEEN LONGERON 26R AND BS 430. REPAIRED IAW ETI- 88-16-433 REV, 1 AND ER/A 551740-14 REV: ORIGINAL.

Part: PAN — CRACKED (CARGO DOOR) · airframe 64,210 hrs · 46,772 cycles

CRACKS ON OUTER AND INNER PAN BELOW STOP FITTING NR 5 AT MID CARGO DOOR. THE PAN WAS REPAIRED IAW ERA 551717-14 REV ORIGINAL.

Part: SKIN — CORRODED (FUSELAGE) · corrosion level 2 · airframe 64,210 hrs · 46,772 cycles

CORROSION AROUND AFT LAVATORY SERVICE ACCESS CUTOUT. AFT LAVATORY SERVICE ACCESS CUTOUT WAS REPAIRED PER ER/A 551691-14 REV ORIGINAL AND ETI-88-16-401 REV 2.

Part: RUB STRIP — CORRODED (FUSELAGE) · corrosion level 2 · airframe 64,210 hrs · 46,772 cycles

CORROSION ON RT FUSELAGE SKIN SETTLEMENT AREA OF RUBSTRIPS OF STA Y:1080 BTW LONGS 30 TO 29R. CORROSION WAS REMOVED ON RT FUSELAGE SKIN SETTLEMENT AREA OF RUBSTRIPS OF STA Y:1080 BTW LONGS 30 TO 29R PER SRM 51-10-3 PAR 26. ORIGINAL THICKNESS IS 0.160 AND REMAINING THICKNESS IS 0.114, THEREFORE ITS OUT LIMITS PER SRM 53-04 PAR 57. AREA OUT LIMITS WAS REPAIRED AND PERFORM VISUAL INSPECTION, INITIAL 8000 CYCLES, REPETITIVE 8000 CYCLES PER SRM 53-04 PAR 57 FIG 57 PAG 397.

Part: TRACK — CORRODED (FUSELAGE) · corrosion level 2 · airframe 64,210 hrs · 46,772 cycles

CORROSION ON LT TRACK BTW STA Y= 1007 TO Y= 1320 BTW LONG 28LH TO 27 LT. NEW TIE TRACK SECTION BTW STA Y=1003 TO 1231 AND STA Y= 1231 TO 1322 WAS REPLACED PER SRM 51-30-1.

Part: SKIN — CORRODED (LT WING) · corrosion level 2 · airframe 64,210 hrs · 46,772 cycles

CORROSION ON INTERNAL FASTENER HOLES (9) LWR ACCESS DOOR CUTOUT BTW XRS=189 TO 214, STR 12 AND 15 AT LT WING. THE REPAIR WAS PERFORMED PER ER/A 550361-14AD REV ORIG AND ETI- 88-16-389 REV 1.

Part: SKIN — CORRODED (RT WING) · corrosion level 2 · airframe 64,210 hrs · 46,772 cycles

CORROSION ON INTERNAL HOLES (8) LWR ACCESS DOOR CUTOUT BTW XRS=189 TO 214, STRINGER 12 AND 15 AT RT WING. REPAIR WAS PERFORMED PER ER/A 550361-14AD REV ORIG.

Part: FLOOR PANEL — DAMAGED (COCKPIT) · corrosion level 2 · airframe 64,210 hrs · 46,772 cycles

CORROSION AND CRACK ON COCKPIT FLOOR PANEL 120D. THE CORROSION WAS REMOVED IAW SRM 51-10-3 PAR. 26.

Part: FRAME — DAMAGED (AFT BULKHEAD) · airframe 64,210 hrs · 46,772 cycles

AFT PRESSURE BULKHEAD LOWER FRAME SPLICES BETWEEN LONGERONS 26 - 27L AND 26 - 27R. THE BULKHEAD WAS REPAIRED PER ER/A 551681-14 REV. ORIGINAL AND ETI-88-16-387 REV. ORIGINAL.

Part: SEAT TRACK — CORRODED (BS 1007-1155) · corrosion level 2 · airframe 64,210 hrs · 46,772 cycles

CORROSION FOUND ON THE RT SEAT TRACK BETWEEN BS 1007 - 1155, LONGERON 27 - 28R. THE SEAT TRACK WAS REPLACED IAW SRM 51-30-1.

Part: SKIN — CORRODED (BS 1080) · corrosion level 2 · airframe 64,210 hrs · 46,772 cycles

CORROSION FOUND ON RT FUSELAGE SKIN SETTLEMENT AREA OF RUBSTRIPS BS 1080 BETWEEN LONGERONS 29 - 30R. THE CORROSION WAS REMOVED IAW SRM 51-10-3 PAR 26.

Part: SEAT TRACK — CORRODED (BS 1212-1320) · corrosion level 2 · airframe 64,210 hrs · 46,772 cycles

CORROSION ON RT SEAT TRACK BETWEEN BS 1212 - 1320, LONGERONS 27 - 28R. THE SEAT TRACK WAS REPLACED IAW SRM 51-30-1, 51-10-4, 51-10-3 PAR 14-21.

Part: FLOOR PANEL — DAMAGED (COCKPIT) · corrosion level 2 · airframe 64,210 hrs · 46,772 cycles

CORROSION AND A CRACK ON COCKPIT FLOOR PANEL 120B. THE CORROSION WAS REMOVED IAW SRM 51-10-3 PAR. 26.

Part: DOUBLER — CORRODED (FUSELAGE) · corrosion level 2 · airframe 64,210 hrs · 46,772 cycles

CORROSION ON REPAIR DOUBLER ON FRAME CHANNEL STA STA Y= 1271 BTW LONG 23 LT TO 26 LT ALSO BTW LONG 29 RT TO 28 LT. REPAIR WAS REPLACED PER SRM 53-03D FIG2A.

Part: DOUBLER — CORRODED (FUSELAGE) · corrosion level 2 · airframe 64,210 hrs · 46,772 cycles

CORROSION ON EXTERNAL RADIO ALTIMETER ANTENNA CUTOUT BTW STA Y=712 AND Y=731. DOUBLER WAS REPLACED PER DGW 5911412 REV DV AND SRM 51-30-2 AND 51-30-5.

Part: FITTING — CORRODED (FUSELAGE) · corrosion level 2 · airframe 64,210 hrs · 46,772 cycles

CORROSION ON FRAME CLIP AT STA Y=1287 BTW LONG 30 AND 29L. FRAME CLIP WAS REPAIRED PER SRM 53-03D FIG 3.

Part: FRAME — CRACKED (FUSELAGE) · airframe 64,210 hrs · 46,772 cycles

CRACKED FRAME STA Y = 1346 AND BTW X=11 TO X=-11. FRAME AT STA Y=1346 AND BTW X=11 TO X=-11 APPROX WAS REPAIRED PER ER/A 094719-14MA REV A.

Part: STRINGER — CRACKED (RT WING) · airframe 64,210 hrs · 46,772 cycles

CRACK WAS FOUND ON STRINGER 11 STA XRS=168 AT RT WING. CRACKED STRINGER 11 AT STA XRS=-168 AT RT WING WAS REPAIRED IN REFERENCE TO CARD 5712-01030-04 AND IN ACCORDANCE WITH SERVICE REWORK DRAWING SR09570100.

Part: STRINGER — CRACKED (LT WING) · airframe 64,210 hrs · 46,772 cycles

CRACK WAS FOUND ON STRINGER 11 STA XRS=168 AT LT WING. CRACKED STRINGER 11 AT STA XRS=168 AT LT WING WAS REPAIRED IN REFERENCE TO CARD 5712-01030-03 AND IN ACCORDANCE WITH SERVICE REWORK DRAWING SR09570100.

Part: FRAME — WORN (FUSELAGE) · airframe 64,210 hrs · 46,772 cycles

WEAR ON FRAME STA Y = 1346 X= 10 APPROX AT AFT ACC COMPARTMENT. FRAME AT STA Y = 1346 X= 10 APPROX AT AFT ACC COMPARTMENT WAS REPAIRED PER ER/A 094719-14MA REV A.

Part: FRAME — CRACKED (FUSELAGE) · airframe 64,210 hrs · 46,772 cycles

CRACKED CHANNEL STA Y = 1510 CANT 8 POSITION AT AFT ACC COMPARTMENT. FRAME WAS REPLACED PER DWG 9911843-5 REV AC AND SRM 51-30-2.

Part: ACCESS DOOR — CORRODED (WING) · corrosion level 2 · airframe 64,210 hrs · 46,772 cycles

CORROSION ON COUNTERSINK OF FUEL ACCESS PLATE NBR 1307C. ACCESS DOOR 1307C WAS REPLACED PER SRM 51-22-2A PAR 6 TABLE 1.

Part: DOOR — WORN (LT MLG) · airframe 64,210 hrs · 46,772 cycles

WEAR (5EA) ON STRUT DOOR LOWER SURFACE ON LT MLG. OUTBOARD DOOR ON MAIN LANDING GEAR WAS REPLACED PER CMM 32-17-06 AND ADJUSTED PER AMM 32-12-01.

Part: REPAIR — CORRODED (FUSELAGE) · corrosion level 2 · airframe 64,210 hrs · 46,772 cycles

CORROSION ON LOWER MID CARGO DOORJAMB PREVIOUS REPAIR AROUND BLIND NUTS BTW STA Y =636 TO 693. REPAIR DOUBLER WAS REPLACED PER SRM 53-05 FIG 123.

Part: FLOOR PANEL — CRACKED (FUSELAGE) · airframe 64,210 hrs · 46,772 cycles

CRACKED FLOOR PANEL 200D. FLOOR PANEL NR 200D WAS CHANGED INSERT PER AMM 53-20-01-201 AND CRACKED AREA ON 200D FLOOR WAS REPAIRED PER AMM 25-00-00 PAR 3.

Part: CUSP WEB — CRACKED (FUSELAGE) · airframe 64,210 hrs · 46,772 cycles

CRACKED LT CUSP WEB BTW STA Y=804-807 AND X=54 TO 60. WEB WAS REPLACED PER SRM 51-30-2 AND 51-30-5.

Part: CUSP WEB — CRACKED (BS 898) · airframe 64,210 hrs · 46,772 cycles

BS 898 A CRACK ON CUSP WEB. THE CUSP WEB WAS REPAIRED IAW SRM 53-05-131A-2.

Part: CUSP WEB — CORRODED (FUSELAGE) · corrosion level 2 · airframe 64,210 hrs · 46,772 cycles

CORROSION ON LT CUSP WEB FROM X= 54 TO X= 60 BTW STA Y= 807 TO Y= 945. STA Y=834 TO 837 WAS FOUND OUT OF LIMITS AND REPAIRED WITH NRC 01147 AND STA Y=898 WAS FOUND OUT OF LIMITS AND REPAIRED WITH NRC 01154.

Part: WEB — CORRODED (BS 370-435) · corrosion level 2 · airframe 64,210 hrs · 46,772 cycles

CORROSION ON WEB LONGERONS 24 AND 26R, BS 370 - 362 AND BS 427 - 435. FOUND OUT OF LIMITS PER ER/A 511165-14MA REV D.

Part: DOUBLER — CRACKED (BS 1474) · airframe 64,210 hrs · 46,772 cycles

CRACK ON PRODUCTION DOUBLER IN ELEVATOR ACCUMULATOR ACCESS DOOR FRAME AT BS 1474. DOUBLER WAS REPLACED IAW SRM 51-30-5, 51-30-2 AND DWG 5917686-7 REV AA.

Part: CUSP WEB — CORRODED (BS 237-313) · corrosion level 2 · airframe 64,210 hrs · 46,772 cycles

CORROSION ON RT CUSP WEB X -60 TO X -44 UPPER AN LOWER BS 237 - 313. THE CUSP WEB WAS REPLACED AND REPAIRED IAW 51-30-1, 51-30-2, 51-30-5 AND ER/A 551706-14 REV. ORIGINAL AND ETI-88-16-413 REV. ORIGINAL.

Part: LONGERON — CORRODED (BS 1282-1304) · corrosion level 2 · airframe 64,210 hrs · 46,772 cycles

CORROSION ON LONGERON 22L BETWEEN BS 1282 AND 1304. THE LONGERON WAS REPAIRED IAW SRM 53-02 FIG 18.

Part: CUSP WEB — CORRODED (BS 1022-1041) · corrosion level 2 · airframe 64,210 hrs · 46,772 cycles

CORROSION ON LT CUSP WEB, X 54 TO X 60 BETWEEN BS 1022 - 1041. REPAIRED IAW SRM 53-05 FIG.131A-14, 51-10-3 PAR 14, 21 AND 38.

Part: CUSP WEB — CORRODED (BS 984-1022) · corrosion level 2 · airframe 64,210 hrs · 46,772 cycles

CORROSION ON RT CUSP WEB X -60 TO X -44 UPPER AND LOWER BETWEEN BS 984 - 1022. THE CUSP WEB WAS REPAIRED IAW SRM 53-05 FIG. 131A-4.

Part: CUSP WEB — CORRODED (BS 834-837) · corrosion level 2 · airframe 64,210 hrs · 46,772 cycles

CORROSION FOUND ON THE LT CUSP WEB FROM X 54 TO X 60, BS 834 - 837. THE CUSP WEB WAS REPAIRED IAW SRM 53-05 FIG. 131.

Part: FRAME — WORN (BS 1500) · airframe 64,210 hrs · 46,772 cycles

WEAR ON PREVIOUS REPAIR BS 1500 FRAME. REPAIRED IAW SRM 53-01 FIG 4 AND 51-30-2.

Part: CUSP WEB — CORRODED (BS 1193-1212) · corrosion level 2 · airframe 64,210 hrs · 46,772 cycles

CORROSION ON RT CUSP WEB REPAIR DOUBLER BETWEEN X - 60 TO X -44BS 1193 TO 1212. PREVIOUS REPAIR DOUBLER WAS REPLACED IAW SRM 53-05 FIG 131A-12.

Part: CUSP WEB — CRACKED (BS 845) · airframe 64,210 hrs · 46,772 cycles

CRACK ON RT CUSP WEB BS 845 AND X -60 AT PAX CABIN. THE CUSP WEB WAS REPAIRED IAW SRM 53-05 FIG 131A-1 AND 51-30-5.

Part: CUSP WEB — CORRODED (BS 1022-1098) · corrosion level 2 · airframe 64,210 hrs · 46,772 cycles

CORROSION ON THE RT CUSP WEB X -60 TO X -44 UPPER AND LOWER BETWEEN BS 1022 TO 1098. THE CUSP WEB WAS REPLACED IAW SRM 51-30-2 AND DWG 9930612 REV. CB.

Part: CUSP WEB — CORRODED (FUSELAGE) · corrosion level 2 · airframe 64,210 hrs · 46,772 cycles

CORROSION ON RT CUSP WEB X-60 TO X-44 UPPER AND LOWER BTW STA Y 807 TO 826. DAMAGE ON AREA WAS REPAIRED PER SRM 53-05 FIGURE 131A-4 SHEET 1 AND SRM 51-30-5.

Part: INTERCOSTAL — CRACKED (FUSELAGE) · airframe 64,210 hrs · 46,772 cycles

CRACK ON INTERCOSTAL X=0 BTW STA Y=1022-1041 AT CABIN FLOOR STRUCTURE. INTERCOSTAL WAS REPAIR PER SRM 53-01 FIG 2.

Part: CUSP WEB — CORRODED (FUSELAGE) · corrosion level 2 · airframe 64,210 hrs · 46,772 cycles

CORROSION ON LT CUSP WEB X= 54 TO X= 60 BTW Y= 598 TO Y =712 AT PAX CABIN. CUSP WEB WAS REPAIRED PER SRM 53-05 FIG 131A.

Part: CUSP WEB — CORRODED (BS 503-598) · corrosion level 2 · airframe 64,210 hrs · 46,772 cycles

CORROSION FOUND ON RT CUSP WEB X -60 TO X - 44 UPPER AND LOWER BTW BS 503 - 598. REPAIRED IAW SRM 53-05 FIG. 131A-6,51-10-3 PAR 14 AND 21.

Part: CUSP WEB — CORRODED (FUSELAGE) · corrosion level 2 · airframe 64,210 hrs · 46,772 cycles

CORROSION ON RT ANGLE CUSP LOWER SURFACE BTW STA Y=160-168, VIEW FROM E/E COMPARTMENT. ANGLE CUSP LOWER SURFACE BTW STA Y=160-168 WAS REPAIRED PER SRM 53-05 FIGURE 55.

Part: CUSP WEB — CRACKED (FUSELAGE) · airframe 64,210 hrs · 46,772 cycles

CRACKED RT CUSP WEB ON STA Y= 579 TO 598 AND X= -54 TO -60. CUSP WEB WAS REPAIRED PER SRM 53-05 FIG 131A-6.

Part: ACCESS DOOR — CORRODED (WING) · corrosion level 2 · airframe 64,210 hrs · 46,772 cycles

CORROSION ON SETTLEMENT AREA AND COUNTERSINK OF FUEL ACCESS PLATE NR 1409. ACCESS DOOR 1409C WAS REPLACED PER SRM 51-22-2A AND IPC 57-30-00.

Part: ACCESS DOOR — CORRODED (WING) · corrosion level 2 · airframe 64,210 hrs · 46,772 cycles

CORROSION ON SETTLEMENT AREA AND COUNTERSINK OF FUEL ACCESS PLATE NR 1303C. FUEL ACCESS DOOR 1303C WAS REPLACED.

Part: SKIN — WORN (L1 DOOR) · airframe 64,210 hrs · 46,772 cycles

WEAR ON L1 DOOR EXTERNAL SKIN LOWER EDGE BTW STA Y=160- Y=168. WEAR ON L1 DOOR EXTERNAL SKIN LOWER WAS REPAIRED PER SRM 52-05 FIG 37.

Part: SEAT TRACK — CORRODED (FUSELAGE) · corrosion level 2 · airframe 64,210 hrs · 46,772 cycles

CORROSION ON LT SEAT TRACK X=22 OF Y=880 AT PAX CABIN. SEAT TRACK WAS REPAIRED PER SRM 53-05 FIG 4A SHEET 1.

Part: ACCESS DOOR — CORRODED (WING) · corrosion level 2 · airframe 64,210 hrs · 46,772 cycles

CORROSION ON SETTLEMENT AREA AND COUNTERSINK OF FUEL ACCESS PLATE NR 1357C. FUEL ACCESS DOOR WAS REPLACED PER IPC 57-30-00 AND SRM 51-22-2A.

Part: SLEEVE — TORN (HYD PUMP) · airframe 64,210 hrs · 46,772 cycles

TORN SLEEVE ON CONDUIT AT AUXILIARY HYDRAULIC PUMP. SLEEVE IN CONDUIT AUX HYDRAULIC PUMP WAS INSTALLED IAW ER/A 467688-14MAAD REV. D.

Part: ACCESS PANEL — CORRODED (WING) · corrosion level 2 · airframe 64,210 hrs · 46,772 cycles

CORROSION ON SETTLEMENT AREA AND COUNTERSINK OF FUEL ACCESS PLATE NBR 1367C. ACCESS PANEL WAS REPLACED PER IPC 57-30-00 AND MAGNETIC DRIPLESS FUEL MEASURING STICK WAS INSTALLED PER AMM 28-40-02.

Part: FLOORBEAM — CORRODED (FUSELAGE) · corrosion level 2 · airframe 64,210 hrs · 46,772 cycles

CORROSION OUT OF LIMIT ON FLOORBEAM STA Y= 1322 X=-33 AT RIGHT AFT LAVATORY FLOOR STRUCTURE. FLOORBEAM WAS REPAIRED PER SRM 53-05 FIG 20A.

Part: INTERCOSTAL — CRACKED (FUSELAGE) · airframe 64,210 hrs · 46,772 cycles

CRACK ON INTERCOSTAL X=0 BTW STA Y=769-788, INTERCOSTAL X=3 BTW STA Y=1271-1288. ALSO ON INTERCOSTAL UPPER EDGE X=0 BTW STA Y=1287-1309 AT CABIN FLOOR STRUCTURE. INTERCOSTALS BTW STA 796-788 AND BTW STA 1287-1309 WERE REPLACED PER DWG 9936580 REV BT, BS, BW AND SRM 51-30-2 AND 51-30-5. INTERCOSTAL BTW STA 1271-1288 WAS REPAIRED PER SRM 53-01 FIGURE 2.

Part: FLOORBEAM — CORRODED (FUSELAGE) · corrosion level 2 · airframe 64,210 hrs · 46,772 cycles

CORROSION ON FLOORBEAMS STA Y=1322 AND Y=1338 BTW X=- 17 TO X=-60 AND X=17 TO X=60 AT CABIN FLOOR STRUCTURE. STA Y= 1322 X=-33 REMAINING THICKNESS IS .071" THEREFORE IT IS OUT OF LIMITS PER SRM 53-05 FIG. ALL OTHER AREAS MENTIONED ARE WITHIN LIMITS.

Part: CUSP WEB — CORRODED (FUSELAGE) · corrosion level 2 · airframe 64,210 hrs · 46,772 cycles

CORROSION ON RT CUSP WEB X -60 TO X - 44 UPPER AND LOWER BTW STA Y 389 TO 503. WEB WAS REPLACED PER SRM 51-30-2 AND 51-30-5.

Part: CUSP WEB — CORRODED (FUSELAGE) · corrosion level 2 · airframe 64,210 hrs · 46,772 cycles

CORROSION ON LT CUSP WEB FROM X= 54 TO X= 60 BTW STA Y= 1212 TO Y= 1231 UPPER AND LOWER SURFACE AT PAX CABIN. LT CUSP WEB FROM X= 54 TO X= 60 BTW STA Y= 1212 TO Y= 1231 WAS REPAIRED PER SRM 53-05 FIG 131 A.

Part: LONGERON — CORRODED (FUSELAGE) · corrosion level 2 · airframe 64,210 hrs · 46,772 cycles

CORROSION ON LONGERON 23LH BTW STA Y=1283 TO Y=1290. LONGERON SECTION 23 LT BTW STA Y=1281 TO 1328 WAS REPAIRED PER SRM 53-02 FIG 18.

Part: CUSP WEB — CORRODED (FUSELAGE) · corrosion level 2 · airframe 64,210 hrs · 46,772 cycles

CORROSION ON LT CUSP WEB BTW STA Y=550-562 AND Y= 589-596 X=54-60. LT CUSP WEB BTW STA Y=550-562 AND Y=589-596 X=54-60 WAS REPAIRED PER SRM 53-05 FIG 131A-11, SRM 51-30-5, 51-10-3 PAR 21 AND 14.

Part: FLOOR PANEL — CRACKED · airframe 64,210 hrs · 46,772 cycles

CRACKS ON GENERATION FLOOR PANELS NR: 256A, 465A, 617A 693A, 927A, 1003A, 1079A. GENERATION FLOOR PANELS NR: 256A, 465A, 617A 693A, 927A, 1003A, 1079A WERE REPAIRED PER SRM 53-05 PAR 145 AND 51-70-1 PAR 10.

Part: DOUBLER — CORRODED (FUSELAGE) · corrosion level 2 · airframe 64,210 hrs · 46,772 cycles

CORROSION ON RT CUSP WEB REPAIR DOUBLER BTW STA X= - 60 TO X= - 44 ON STA Y=1098 TO Y=1117. REPAIR DOUBLER WAS REPLACED PER SRM 53-05 FIGURE 131A-7.

Part: FLOOR PANEL — DAMAGED (CABIN) · airframe 64,210 hrs · 46,772 cycles

FLOOR PANEL DAMAGED. THE FLOOR PANEL WAS REPLACED IAW AMM 53-20-01-201 PARAGRAPH 7B.

Part: CUSP WEB — PUNCTURED (FUSELAGE) · airframe 64,210 hrs · 46,772 cycles

PUNCTURED ON LT CUSP WEB X= 53 AND STA Y= 1062 AT PAX CABIN. PUNCTURED ON LT CUSP WEB X=53 AND Y=1062 WAS REPAIRED PER SRM 53-01 FIG 1 SHEET 2.

Part: CUSP WEB — CORRODED (FUSELAGE) · corrosion level 2 · airframe 64,210 hrs · 46,772 cycles

CORROSION ON LT CUSP WEB X= 54 TO X= 60 BTW Y=389 TO Y= 465 AT PAX CABIN. PREVIOUS DOUBLER WAS REPLACED PER SRM 53-05 FIG 131A-13.

Part: FRAME — CRACKED (BS 1450) · airframe 64,210 hrs · 46,772 cycles

CRACK ON FRAME ANGLE BS 1450 BETWEEN LONGERON 1 AND 3L & RT SIDE. THE FRAME ANGLE WAS REPLACED IAW DWG 9911860 REV. "L" AND SRM 51-30-5.

Part: SEAT TRACK — CORRODED (BS 270-273) · corrosion level 2 · airframe 64,210 hrs · 46,772 cycles

CORROSION ON RT SEAT TRACK AT X -22 BETWEEN BS 270-273. THE SEAT TRACK WAS REPAIRED IAW SRM 53-05 FIG. 4F, 51-10-3 PAR. 21, 14, 51-10-4 AND 51-30-1.

Part: INTERCOSTAL — CRACKED (BS 1355) · airframe 64,210 hrs · 46,772 cycles

CRACK ON PREVIOUS REPAIR DOUBLER OF INTERCOSTAL BA 1355, X -24. THE INTERCOSTAL WAS REPAIRED IAW SRM 53-01 FIG.2.

Part: CUSP WEB — CRACKED (BS 275) · airframe 64,210 hrs · 46,772 cycles

A CRACK WAS FOUND ON THE LT CUSP WEB BS 275, X 49. THE CUSP WEB WAS REPAIRED IAW SRM 53-05 FIG. 131A-15.

Part: FLOOR PANEL — DAMAGED (CABIN) · airframe 64,210 hrs · 46,772 cycles

FLOOR PANEL DAMAGED. REPLACED THE FLOOR PANEL IAW AMM 53-20-01-201 AND AMM 25-00-00-201.

Part: PAN — CRACKED (BS 886-905) · airframe 64,210 hrs · 46,772 cycles

CRACK FOUND ON THE RT WINDOW RING PAN FWD UPPER CORNER AND THE AFT LOWER CORNER BETWEEN BS 886 AND 905. THE RING PAN WAS REPAIRED IAW ER/A 333615-14MA REV. G.

Part: CUSP WEB — CRACKED (BS 218) · airframe 64,210 hrs · 46,772 cycles

CRACK ON LT CUSP WEB BS 218 X=45. CUSP WEB REPAIRED IAW SRM 53-05 FIG 131A-5.

Part: CUSP WEB — CRACKED (BS 303) · airframe 64,210 hrs · 46,772 cycles

CRACK ON LT CUSP WEB BS 303 AND X= 45. CUSP WEB WAS REPAIRED IAW SRM 53-05 FIG 131A-1.

Part: DOUBLER — WORN (FWD CARGO DOOR) · airframe 64,210 hrs · 46,772 cycles

AFT LOWER DOUBLER OF THE FWD CARGO DOOR FOUND WORN. THE DOUBLER WAS REPLACED IAW ERA 486624-14 MA REV ORIG.

Part: PAN — CRACKED (BS 845-864) · airframe 64,210 hrs · 46,772 cycles

CRACK ON LT WINDOW RING PAN LOWER FWD CORNER BS 845 AND 864. THE PAN WAS REPAIRED IAW ER/A 333615-14MA REV. G.

Part: PAN — CRACKED (BS 886-905) · airframe 64,210 hrs · 46,772 cycles

CRACK ON LOWER AFT CORNER ON LT WINDOW RING PAN BS 886 AND 905. THE PAN WAS REPAIRED IAW ER/A 333615-14MA REV. G.

Part: PAN — CRACKED (BS 845-864) · airframe 64,210 hrs · 46,772 cycles

CRACK ON RT WINDOW RING PAN UPPER FWD CORNER BS 845 AND 864. THE PAN WAS REPAIRED IAW ER/A 333615-14MA REV. G.

Part: PAN — CRACKED (BS 332-351) · airframe 64,210 hrs · 46,772 cycles

CRACK ON LT WINDOW RING PAN UPPER FWD CORNER BETWEEN BS 332 - 351. THE PAN WAS REPAIRED IAW ER/A 333615-14MA REV. G.

Part: VANE — CRACKED (RT WING TE FLAP) · airframe 64,210 hrs · 46,772 cycles

CRACKED RT WING INBD FLAP OUTBD GUIDE VANE AT UPPER SKIN INBD LWR CLEVIS HARDWARE ACCESS. THE VANE WAS REMOVED IAW AMM 27-51-03-201.

Part: SKIN — DENTED (RT ELEVATOR TAB) · airframe 64,210 hrs · 46,772 cycles

DENT ON UPPER SURFACE OF CONTROL TAB AT RT ELEVATOR BTW STA APPROX XHS 30 TO XHS 78. CONTROL TAB WAS REPLACED PER IPC 55-20-00-05.

Part: SKIN — DENTED (RT WING TE FLAP) · airframe 64,210 hrs · 46,772 cycles

TWO DENTS ON UPPER SKIN OF RT MID VANE AT OUTBOARD FLAP. THE VANE WAS REPAIRED IAW SRM 57-03D PAR 11.

Part: VANE — DELAMINATED (RT WING TE FLAP) · airframe 62,493 hrs · 45,492 cycles

RT OTBD FLAP CENTER VANE HAS DELAMINATION ON T/E. REPLACED ON NR 19. R & R RT OTBD FLAP CENTER FLAP VANE IAW AMM 27-51-03.

Part: SKIN — DAMAGED (RUDDER) · airframe 62,495 hrs · 45,493 cycles

CONDUCTIVE COATING ON SEVERAL AREAS OF THE RUDDER ARE CHIPPED AWAY AND OUT OF AMM LIMITS FOR SANDING AND REPAINTING AND WILL REQUIRE A NEW RUDDER. R & R RUDDER IAW AMM 27-20 AND WC 2720-4421. OK FOR SERVICE.

Part: STRUCTURE — CRACKED (TAILCONE) · airframe 62,467 hrs · 45,477 cycles

MAINTENANCE FOUND 4 CRACKS EMINATING FROM THE 5:00 POSITION TAILCONE ALIGNMENT PIN HOLE. A REPAIR WAS INSTALLED IAW ER/A 497316-14MA, REV ORIG.

Part: SKIN — CRACKED (RT WING) · airframe 62,467 hrs · 45,477 cycles

UPPER RT WING T/E PANEL CRACKED FWD OF GROUND SPOILER OTBD END. REMOVED AND REPAIRED IAW SRM 51-90-0, PAR 8I. REINSTALLED IAW DWG 5936824.

Part: FRAME — CRACKED (BS 1485) · airframe 62,467 hrs · 45,477 cycles

TAIL INTERIOR, LT CANTED FRAME WEB HAS .5" LONG CRACK AT FASTENER, BS 1485, 10 O`CLOCK POSITION, 1" BELOW HORIZONTAL STIFFENER.INSTALLED LT VENT BOX ASSY. ALL WORK PERFORMED AND COMPLETED IAW SRM 53-03, FIG. 48.

Part: FRAME — CRACKED (BS 1510) · airframe 62,467 hrs · 45,477 cycles

TAIL INTERIOR, AFT CANTED FRAME BS 1510 HAS .5" CRACK AT TAIL CONE ALIGNMENT PIN, 8 O`CLOCK. REPAIRED IAW ERA497316-14MA, REV ORIGINAL.

Part: PIN — DISENGAGED (L1 DOOR SLIDE) · airframe 62,199 hrs · 45,302 cycles

MAINTENANCE FOUND L-1 DOOR SLIDE PARACHUTE PIN DISENGAGED. THE L-1 DOOR SLIDE WAS REPLACED.

Part: BATTERY PACK — INOPERATIVE (EMERGENCY LIGHTS) · airframe 61,448 hrs · 44,740 cycles

DURING LINE CHECK, MAINTENANCE FOUND THAT THE OVERHEAD EMERGENCY LIGHTING IN THE GALLEY WAS INOPERATIVE. MAINTENANCE REPLACED THE BATTERIES. OPS CHECKED GOOD.

Part: DUCT — CONTAMINATED · airframe 61,001 hrs · 44,446 cycles

CREW REPORTED SMOKE, ODOR IN AFT CABIN ON DESCENT WITH AFT RIGHT LAVATORY SMOKE DETECTOR ALERTING MOMENTARILY. MAINTENANCE BOROSCOPED BOTH ENGINES LOOKING FOR SIGNS OF OIL RESIDUE, NONE FOUND. REQUEST MAINTENANCE REPLACED THE RECIRCULATION FAN AND FILTER. EVIDENCE OF OIL WAS FOUND IN BOTH PACK DUCTS, SO BOTH PACKS WERE PUT ON MEL. SHIP WAS FERRIED AND MAINTENANCE COMPLIED WITH ALL MCC REQUESTED TASKS ON N/R CARDS 1-15. RAN ENGINES AT TAKEOFF POWER WITH PACKS SET TO HOT AND ACFT PRESSURIZED. NO SMOKE OR ODOR PRESENT.

Part: UNKNOWN — SMOKE (CABIN) · airframe 61,001 hrs · 44,446 cycles

DURING DECENT FOR LANDING, THE CABIN CREW REPORTED VISIBLE SMOKE IN CABIN. MAINTENANCE REPLACED THE APU AFTER THE BLEED DUCT WAS FOUND DRY. EXTENDED THE DUCT BURNOUT.

Part: APU — ODOR (CABIN) · airframe 60,992 hrs · 44,440 cycles

CREW PERFORMED AN ATB AT FL130 DUE TO THE F/A REPORT OF HAZE IN AFT CABIN. ACCOMPANIED BY THE AFT LAVATORY SMOKE DETECTORS SOUNDING. MAINTENANCE INSPECTED ENGINES AND APU FOR OIL LEAKS. NONE FOUND. PERFORMED DUCT BURNOUT PROCEDURE TWICE. NO FURTHER FUMES OR SMOKE PRESENT. ACFT HAS RETURNED TO SERVICE.

Part: ENGINE — FAILED (NR 1) · airframe 58,737 hrs · 42,808 cycles

THE NR 1 ENGINE FAILED DURING TAKEOFF. FLIGHT RETURNED TO DEPARTURE. PILOTS HEARD A THUD, NOTICED LT ENGINE ROLLED BACK AND SHUTDOWN, AND THE EGT INCREASED. THE QRH WAS COMPLIED WITH AND THE FUEL WAS SHUTOFF. MAINTENANCE FOUND METAL IN TAIL PIPE AND TURBINE DAMAGE. THE NR 1 ENGINE WAS REPLACED.

Part: SKIN — CRACKED (BS 1380) · airframe 57,202 hrs · 41,762 cycles

DURING CHECK, NOTED A SKIN CRACKED AT BS 1380, RT SIDE ABOVE PYLON. REPAIRED IAW 521154-14, SECTION 1.

Part: SKIN — DAMAGED (VERTICAL STAB) · airframe 57,202 hrs · 41,762 cycles

SCHEDULED VERTICAL STABILIZER L/E SKIN DAMAGED. REPAIRED IAW AMDS WC REF AD 2011-15-01.

Part: CABLE — FRAYED (TAILCONE RELEASE) · airframe 57,202 hrs · 41,762 cycles

DURING CHECK, NOTED TAIL CONE LATCH TWO LEVER CABLES LT AND RT SIDE WERE FRAYED. REPLACED LT AND RT SIDE LATCH CABLES IAW AMM 53-53-00.

Part: STRUCTURE — CORRODED (BS 1271) · corrosion level 2 · airframe 57,202 hrs · 41,762 cycles

DURING CHECK, CORROSION IN AFT CARGO AT BS 1271, AFT SIDE L28L-29R. REPAIRED IAW SRM 53-03D, FIGURE 2A.

Part: FRAME — CRACKED (FUSELAGE) · airframe 57,202 hrs · 41,762 cycles

DURING CHECK, NOTED CRACKED FRAME AT 4 O'CLOCK POSITION BY TAILCONE GUIDE PIN RECEPTICLE. REPAIRED IAW ER/A 497316-14MA.

Part: COTTER PIN — MISSING (TAILCONE) · airframe 57,202 hrs · 41,762 cycles

AFTER MAINTENANCE, ZONE FINAL INSPECTION NOTED THE TAIL CONE RELEASE TEE PIN CENTER SLIDING BOLT HAD NO COTTER PIN INSTALLED. SAFETIED T-PIN BOLT IAW AMM 53-53-00.

Part: CLAMP — LOOSE (RELEASE CABLE) · airframe 57,202 hrs · 41,762 cycles

DURING CHECK, NOTED THE RELEASE CABLE CONDUIT CLAMPS ARE LOOSE, AT BOTTOM OF TAILCONE ATTACH FRAME. TIGHTENED CLAMPS IAW AMM 53-53-00.

Part: PAN — CRACKED (EMERGENCY EXIT) · airframe 57,202 hrs · 41,762 cycles

DURING CHECK, NOTED RT FWD OVERWING EMERGENCY EXIT DOOR PAN IS CRACKED FWD OF LATCH LUG, IN RADIUS. HEAT TREATED DOUBLERS WERE INSTALLED IAW SRM 53-05, FIG 32.

Part: WIRE HARNESS — INOPERATIVE (EMERGENCY LIGHTS) · airframe 55,968 hrs · 40,910 cycles

DURING LINE CHECK, MX FOUND THAT THE EMERGENCY PATHWAY LIGHTING IN ROWS 15 AND 18 OF THE CABIN WERE INOPERATIVE. MX REPLACED THE WIRE HARNESS AND FUNCTIONALLY CHECKED THE SYS.

Part: BATTERY PACK — INOPERATIVE (EMERGENCY LIGHT) · airframe 55,701 hrs · 40,736 cycles

DURING LINE MX CHECK, THE EMERGENCY EXIT LIGHTS IN THE TAIL CONE WERE FOUND TO BE INOPERATIVE. BOTH AFT BATTERY PACKS WERE REPLACED IAW AMM 33-53-00 AND THE SYS OPS CHECKED GOOD.

Part: BATTERY PACK — INOPERATIVE (EMERGENCY LIGHTS) · airframe 55,069 hrs · 40,285 cycles

SEVERAL OVERHEAD EMERGENCY LIGHTS INOPERATIVE. R & R BATTERIES IN BATTERY PACKS 1C, 2ED, 33ED AND RT AFT LAV. OPS CHECKS GOOD.

Part: ENGINE — FAILED (LEFT) · airframe 54,307 hrs · 39,717 cycles

FLIGHT RETURNED TO DEPARTURE DUE TO LT ENGINE INDICATIONS. TURNED OFF ANTI-ICE, FELT SHUDDER, HEARD BANG AND THEN NOTED LT ENGINE EPR DROP AND EGT RISE AND THEN STABILIZE. MX FOUND TURBINE DAMAGE, METAL IN TAIL PIPE. ALSO PIECE OF TURBINE BLADE PUNCTURED CASE BUT WAS CONTAINED IN ENGINE COWLING. MX REPORTED THAT NO METAL WAS FOUND IN THE ENGINE COWLING. ENGINE WAS NOT SHUTDOWN. ENGINE WAS CHANGED.

Part: SPAR CAP — CRACKED (VERTICAL STAB) · airframe 53,735 hrs · 39,298 cycles

VERTICAL STAB LEFT FRONT SPAR CAP CRACKED . COMPLIED WITH ERA 485915-14 AD REV A CODE 55-31.

Part: DOUBLER — CRACKED (BS 1463 L18R) · airframe 53,735 hrs · 39,298 cycles

INSPECTION FOUND THE OUTER CAP DOUBLER ANGLE OF THE BS 1463 CANTED BULKHEAD, CRACKED IN ITS BEND RADIUS JUST BELOW THE AFT END OF THE L18R END FITTING. CRACK IS APPROXIMATELY 1.0 INCH LONG RUNNING BEHIND EXISTING FASTENERS. ACCOMPLISHED ON NRC NR 155 AND ERA 505369-14 REV O.

Part: PAN — CORRODED (CARGO DOOR FRAME) · corrosion level 2 · airframe 53,735 hrs · 39,298 cycles

FWD CARGO DOOR LOWER FRAME PAN CORROSION STA 370- 427. CORROSION WAS FOUND TO BE OUT OF LIMITS, SPLICED IN NEW LOWER PAN SECTION PER THE SRM 53-05 AND DWG J060228.

Part: WIRE HARNESS — DAMAGED (CABIN) · airframe 53,467 hrs · 39,129 cycles

DURING SERVICE CHECK, MAINTENANCE FOUND EMERGENCY LIGHT AT SEAT 26ED INOPERATIVE. REMOVED AND REPLACED DAMAGED HARNESS. OPERATION CHECKS GOOD.

Part: STRUCTURE — CORRODED (HORIZ STAB) · airframe 52,947 hrs · 38,768 cycles

DUE ERA 485928-14 REV ORIG CODE 55-11...ACTL 2153..MD88 STABILIZERS/HORIZONTAL - L/R OUTER CONSTANT SECTION UPPER CENTER PLATES/BARREL NUT HOLES/CORROSION REPAIR. C/W ERA 485928-14 REV A ON NON-ROUTINE NUMBER 1. REMOVED LT AND RT OUTBOARD LEADING EDGES AND STAB TIPS PER MD88 ERA_485928-14 STEP 1. REPAIRED PER ERA 485928-14 REV A.

Part: CONNECTOR — UNSECURE (CABIN) · airframe 51,238 hrs · 37,577 cycles

MAINTENANCE FOUND EMERGENCY PATHWAY LIGHT INOPERATIVE AT ROW1C. MEL 33-00-24 APPLIED. RE-SECURED CONNECTOR AND NOW OPERATION CHECKS GOOD. MEL REMOVED.

Part: SPAR — DAMAGED (VERTICAL STAB) · airframe 49,647 hrs · 36,548 cycles

ELONGATED HOLE ON VERTICAL STAB LT FRONT SPAR CHORD FLANGE ZFS=66.500. REPAIR PER ERA 485915-14 REV ORG. (DLM88102899)

Part: SKIN — DAMAGED (VERTICAL STAB) · airframe 49,647 hrs · 36,548 cycles

ELONGATED SCREW HOLE ON LOWER AFT SECTION OF VERTICAL STAB REMOVABLE LEADING EDGE AT STA ZFS = 54 RIGHT SIDE. REPAIRED PER ERA 485923-14 REV ORG. (DLM88102889)

Part: SKIN PANEL — CORRODED (HORIZ STAB) · corrosion level 2 · airframe 49,647 hrs · 36,548 cycles

PITTING CORROSION ON BARREL NUT ACCESS HOLES 3 PLACES OF LT HORZ STAB UPPER SKIN MIDDLE PANEL AT STA 8.2. REPAIR PER ERA 485928-14 ORIG REV. (DLM88102871)

Part: DOOR FRAME — CORRODED (FUSELAGE) · corrosion level 2 · airframe 49,647 hrs · 36,548 cycles

EXFOLIATION CORROSION ON LWR DOOR JAMB BETWEEN STA X=17 TO -17 AT AFT ENTRY DOOR JAMB STA 1350. REPAIRED PER ERA 485913 REV ORG. (DLM88102874)

Part: SKIN PANEL — CORRODED (HORIZ STAB) · corrosion level 2 · airframe 49,647 hrs · 36,548 cycles

PITTING CORROSION ON BARREL NUTS ACCESS HOLE 3 PLACES OF RT HORZ STAB UPPER SKIN MIDDLE PANEL AT STA XH=8.2. REPAIRED PER ERA 485928-14 REV ORIG. (DLM88102873)

Part: SKIN PANEL — CORRODED (HORIZ STAB) · corrosion level 2 · airframe 49,647 hrs · 36,548 cycles

PITTING CORROSION ON BARREL NUTS ACCESS HOLES 2 PLACES OF RT HORZ STAB UPPER SKIN FWD PANEL AT STA XH=28.2. REPAIRED PER ERA 485927-14 REV ORIG. (DLM88102872)

Part: SKIN — DAMAGED (VERTICAL STAB) · airframe 49,647 hrs · 36,548 cycles

ELONGATED SCREW HOLES ON LOWER AFT SECTION OF VERTICAL STAB REMOVABLE LEADING EDGE LEFT SIDE REPAIR PER ERA 485924-14 REV ORG. (DLM88102902)

Part: DOOR FRAME — CORRODED (FUSELAGE) · corrosion level 2 · airframe 49,647 hrs · 36,548 cycles

C3 CARGO DOOR SURROUND LOWER JAMB BEAM CORROSION. REPAIRED PER ERA 482650-14. (DLM88102878)

Part: LIGHT — INOPERATIVE (CABIN) · airframe 49,188 hrs · 36,230 cycles

MAINTENANCE FOUND THE EMERGENCY EXIT LIGHT AT SEAT 1C TO BE INOPERATIVE. MAINTENANCE REPLACED THE LIGHT ASSEMBLY. AN OPERATIONAL CHECK WAS PERFORMED AND THE AIRCRAFT WAS RETURNED TO SERVICE (2010-D0838) (DLM88101856).

Part: WIRE HARNESS — DAMAGED (CABIN) · airframe 49,085 hrs · 36,163 cycles

DURING LINE CHECK MAINTENANCE FOUND EMERGENCY LIGHT AT ROW 1C INOPERATIVE. MAINTENANCE FOUND WIRES PULLED OF PINS AND REPLACED THE LIGHT HARNESS. OPERATIONAL CHECK OF LIGHT NOW CHECK GOOD.

Part: THRESHOLD — CORRODED (FUSELAGE) · corrosion level 2 · airframe 48,898 hrs · 36,019 cycles

AFT CARGO DOOR THRESHOLD CORRODED REPAIRED IAW ERA 482650-14ON NR 99. (DLM88101412)

Part: SKIN — CORRODED (HORIZ STAB) · airframe 47,016 hrs · 34,726 cycles

REPLACED RT HORIZONTAL STABILIZER UPPER AFT SKIN PER EA 09-460214-12AD REV D AND ERA 461387-14AD.

Part: ENGINE — SHUTDOWN (LEFT) · airframe 42,634 hrs · 31,879 cycles

AT FL320, THE LEFT ENGINE SHUT DOWN. THE N2/HYD PRESSURE/OIL PRESSURE WENT TO -0-. THE ENGINE WINDMILLED FOR 25 MINS WITH -0- OIL PRESSURE. REMOVED AND REPLACED NR 1 ENGINE PER TRAS 9T102.

Part: NONE — NONE · airframe 41,599 hrs · 31,151 cycles

DURING SCHEDULED INSPECTION OF THE OVERWING HEATER BLANKET AN ADDITIONAL VOID WAS REPORTED IN THE BONDLINE BETWEEN THE HEATER BLANKET AND THE WING UPPER SKIN. ENGINEERING EVALUATION DETERMINED THE VOID WAS NOT NEW. THE DIFFERENCE FROM PRIOR INSPECTION WAS BECAUSE OF THE ACCURACY OF THE NDI METHOD. THE VOID WAS STILL WITHIN MANUAL LIMITS. DISPOSITIONED PER ER/A 09-093771-14AD.

Part: SKIN — CRACKED (HORIZONTAL STAB) · airframe 41,205 hrs · 30,865 cycles

DURING ACCOMPLISHMENT OF EA 09-460214-12 OPN 0101, THE TRIM OUT IN THE HORIZONTAL STAB UPPER INBOARD SKIN PANEL EXTENDED PAST THE BARREL NUT PAD UP. THE TRIM OUT AND SPOTFACE INTO THE PAD UP WAS SUBMITTED TO BOEING FOR APPROVAL, AND WAS APPROVED AS A TEMPORARY REPAIR PER THE TYPICAL STAB UPPER SKIN INSPECTIONS. THIS WAS DOCUMENTED AND INCLUDED IN ERA 461387-14.

Part: AXLE — DAMAGED (NLG) · airframe 34,086 hrs · 25,983 cycles

CREW REPORTED NOSE SCRAPPING SOUND FROM NOSE GEAR AFTER 90 DEGREE TURN ON RAMP. ON NOSE GEAR FOUND LEFT WHEEL BOTH INNER AND OUTER BEARINGS DAMAGED AND ROLLERS MISSING. LEFT AXLE REQUIRES REPLACING.

Part: BATTERY — DISCHARGED (FLASHLIGHT) · airframe 34,034 hrs · 25,943 cycles

MID CABIN FLIGHT ATTENDANT FLASHLIGHT RED LIGHT NOT BLINKING. REPLACED LIGHT ASSY.

Part: REGULATOR — INOPERATIVE (RT A/C PACK) · airframe 33,861 hrs · 25,818 cycles

ON CLIMBOUT SAT RIGHT PACK FAILED. COOL OFF AND RESET, PROCEDURE DID NOT REGAIN PACK INITIALLY. PACK REGAINED APPROX 10 MINUTES LATER. ON CLIMBOUT SAT BOTH AUTO 1 AND AUTO 2 CONTROLLERS FAILED AFTER RT PACK FAILED. RAN BOTH ENGINES TO TAKEOFF POWER. FOUND RIGHT ENGINE AUG VALVE NOT WORKING CORRECTLY. REPLACED ANTICIPATOR.

Part: FAN — ODOR (RECIRCULATION) · airframe 32,472 hrs · 24,933 cycles

AIR TURNBACK. AFTER T/O, CLIMB 8000 FT NOTICED SMOKE IN COCKPIT. RETURNED TO PHL. DURING DEBRIEF F/AS REPORTED SLIGHT SMOKE ODOR IN CABIN, ALSO NO SMOKE DETECTORS SOUNDING IN LAVS. PERFORMED TROUBLESHOOTING PER TROUBLESHOOTING TREE OPN 5088. FOUND LIKELY SOURCE WAS RECIRCULATION FAN. CONTINUED WITH TROUBLESHOOTING THROUGH TAKEOFF POWER ENGINE RUN. NO OTHER SOURCES OF SMOKE, FUMES OR VAPORS FOUND. REPLACED AIR CONDITIONING MOISTURE BAGS FOR PRECAUTIONARY. FWD RECIRCULATION FAN AND PLACARDED PER MEL 21-00-43. PULLED AND COLLARED RECIRC FAN CONT CB J7.

Part: APU — LEAKING (APU BAY) · airframe 25,794 hrs · 20,113 cycles

SMOKE ALARM GOING OFF IN AFT LAV HAZE OBSERVED BY FLT ATTENDENT - REPLACED APU FOR OIL LEAK - PERFORMED DUCT BURNOUT

Part: OVEN — FIRE (CABIN) · airframe 23,636 hrs · 18,559 cycles

F/A REPORTED A FIRE IN FWD GALLEY OVEN DURING OVEN OPERATION. FLAME CONTINUED AFTER POWER REMOVED FROM GALLEY. F/A EXTINGUISHED WITH HALON BOTTLE AND CREW DIVERTED FLIGHT TO KTYS. CONTRACT WITH MTC CONFIRMED THAT FIRE WAS ISOLATED TO SHORTED OVEN HEATER ELEMENT WHICH HAD IGNITED FOOD IN OVEN. NO DAMAGE OUTSIDE OVEN OR GALLEY AREA AND NO INJURIES. MTC PULLED OVEN CONTROL CB AND PLARDED PER MEL 25-00-12.

Part: ENGINE — FAILED (NR 1)

NR 1 ENGINE FLAMED OUT PASSING 5,000 FT ON DEPARTURE, N2 WENT TO ZERO. REPLACED ENGINE.

Part: LINE — FAILED (NR 2 ENGINE)

LOST RIGHT HYDRAULIC QUANTITY AND PRESSURE ON CLIMBOUT FROM KJAX. REPLACED ENGINE DRIVEN HYDRAULIC PUMP PRESSURE LINE THROUGH PYLON. SERVICED RIGHT HYD SYSTEM. LEAK CHECK GOOD. REPLACED NR 2 ENG CASE DRAIN AND PRESSURE FILTERS. NO METAL FOUND. OPN AND LEAK GOOD.

Part: GENERATOR — SHORTED (NR 1 ENGINE)

NR 1 ENG GENERATOR DROPPED OFF LINE, CREW RTO BELOW 85 MPH. REPLACED ENGINE GENERATOR.

Part: APU — FAILED (APU COMPT)

IN CRZ AT FL330, SMOKE IN CABIN WHEN AIRFOIL A/I TURNED ON. SMOKE DISSIPATED WHEN A/I TURNED OFF. FOUND APU TO BE LEAKING OIL AND DISTRIBUTED INTO PNEUMATIC SYSTEM, RENDERED APU INOP. RAN ENGINES TO TAKEOFF POWER, ALL OK. REPLACED APU.

Part: LINER — DAMAGED (NR 2 ENGINE)

DURING G/A AND SUBSEQUENT LANDING F/A REPORTED SMOKE SMELL AND STRANGE NOISE FROM RT ENGINE. FOUND DAMAGED LINER AT 7 O'CLOCK POS IN NR 2. BORESCOPED ENGINE.

Part: BATTERY PACK — MALFUNCTIONED (CABIN)

EMERGENCY EVACUATION LIGHTS OUT IN FWD PART OF COACH AND ALL OF FIRST CLASS CABIN. RERACKED B5-100 BATTERY PACK, OPN NML.

Part: ANGLE — CRACKED (KEEL BEAM)

FOUND DURING C-2 LETTER CHECK, RT AFT MLG FRAME SUPPORT ANGLE CRACKED .5 INCH AT KEEL BEAM. REPAIRED PER SRM 53-05 FIG 101.

Part: SKIN — CRACKED (C 1 DOOR)

FOUND ON C2 LETTER CHECK, C-1 DOOR EXTERIOR HANDLE CUTOUT. REPAIRED PER SRM 52-05 FIG 30.