N905DL

Part: SWITCH — INTERMITTENT (TAILCONE) · airframe 84,106 hrs · 64,503 cycles

INTERMITTENT TAILCONE UNSAFE MESSAGE ON GROUND. DEFERRED PER MEL 53-00-01B. RELEASED TAIL CONE MECHANISM FOR MTC REF MD88 AMM 53-53. T/S PER MD88 WDM 53-73. FOUND INTERNAL HANDLE TAILCONE SWITCH INTERMITTENT. R/R SWITCH REF MD88 AMM 52-70. OPS CHECK GOOD. C/W RII INSTALL SWITCH + TAILCONE + SLIDE PER 53-53. RESECURED TAILCONE MECHANISM AND SLIDE AFTER MTC ACCOMPLISHED, REF MD88 AMM 53-53. MEL + PLACARD REMOVED NO (M) PROCEDURES. (LP6630196)

Part: SWITCH — CORRODED (TAILCONE) · airframe 84,089 hrs · 64,488 cycles

TAILCONE UNSAFE LIGHT ILLUMINATED AT GATE WHILE PARKED IN HEAVY RAIN. INSPECTED TAILCONE RELEASE MECHANISM AND VERIFIED LOCKPINS ARE INPLACE, LOCKING CABLE IS PROPERLY SECURED. TAILCONE UNSAFE LIGHT IS CLEARED. DUE TO HISTORY, DEFERRED SAME IAW MEL 53-00- 01B. MC NOTIFIED. (M) PROC C/W. PLAC INSTALLED. T/S TAILCONE WARNING PER MD88 AMM 52-70 AND MD88 WDM 53-73. INSPECTED INNER TAILCONE SWITCH AND EXT. TAILCONE SWITCH CANNON PLUG FOUND EXT.SWITCH SWITCH CORROSION.CLEANED CANNON PLUG AND R /R EXT.SWITCH .OPS CK NO FAULT NOTED.PLACARD REMOVED.NBO 'M' PROCEDURE.OK FOR SVC.(LP6630190)

Part: TERMINAL — BROKEN (GROUND STUD) · airframe 84,034 hrs · 64,427 cycles

TAIL CONE UNSAFE OAP. T/S PER MD88 WDM 52-73-11. FOUND BROKEN GROUND RING TERMINAL AT GROUND STUD 616. REPAIRED TERMINAL PER SWPM CH. 20. OPS CK GOOD. (LP6630148)

Part: BATTERY PACK — DISCHARGED (COCKPIT) · airframe 83,765 hrs · 64,161 cycles

COCKPIT EMER LIGHTS STA 140 NOT ILLUMINATE WHEN DOING EMER LIGHT CHECK. REPLACED B5-23 BATTERY PACK PER AMM 33-50-00 FIG 1. SYSTEMS CHECK NORMAL. (LP4634454)

Part: SKIN — CRACKED (FUSELAGE) · corrosion level 2 · airframe 82,541 hrs · 63,078 cycles

HIDDEN DAMAGE: CORROSION AND CRACK ON SKIN, ALSO SUNKEN AND BROKEN FASTENERS AT SETTLEMENT SURFACE AREA (FUSELAGE STRUCTURE) OF LOWER TCAS ANTENNA. (CORROSION LEVEL 2). REPAIRED PER ER/A 575558-14 REV ORIGINAL (SECTION I) PERMANENET REPAIR AND ETI-88-19-015 REV 3.

Part: LONGERON — CORRODED (FUSELAGE) · corrosion level 2 · airframe 82,541 hrs · 63,078 cycles

HIDDEN DAMAGE: AFTER PERFORMED CUT OUT ON EXTERNAL SKIN, CORROSION WAS FOUND ON LONGERON 30 BTW STA Y =237-256 AT FWD CARGO COMPARTMENT IN REF NRC 00347. (CORROSION LEVEL 2). LONGERON REPAIRED PER ER/A 575585-14 REV ORIGINAL.

Part: RUDDER — DAMAGED · airframe 82,537 hrs · 63,076 cycles

AWR: DUE TO SEVERAL PAINT FLAKES ON BOTH SIDES OF RUDDER SURFACES, PERFORM REMOVE/INSTALL RUDDER ASSY ON REFERENCE OF NRC00054. SUMMARY OF THE NRC# 00056 RUDDER ASSY AND CONTROL TAB WAS REMOVED AND INSTALLED PER MD88 AMM 27-20-01-401 AND MD88 AMM 27-20-02 AND DUE TO RUDDER WAS PAINTED ON NRC 00054 BALANCE CHECK WAS PERFORMED PER DC-9/MD-80 SRM 55-40-1 PARAGRAPH 21 TO 24. HAVING A MOMENT +487.8IN/LBS. TEST WAS PERFORMED PER MD88 AMM 27-01-05-201 AND PER MD88 AMM 22-01-03-201. (LP0944989)

Part: PAN — CRACKED (R1 DOOR) · airframe 82,537 hrs · 63,076 cycles

INITIAL INSPECTION: CRACKED PAN AND STRAP (FWD EDGE) BTW BEAM 3-4 AT FWD SERVICE DOOR (R1). PAN AND STRAP (FWD EDGE) BTW BEAM NBR 3 AND 4 AT FWD SERVICE DOOR WERE REPAIRED PER ERA 575421-14 REV. ORIGINAL AND ETI-88-19-012 REV. 4. (LP0944450)

Part: SKIN — CRACKED (FUSELAGE) · airframe 82,537 hrs · 63,076 cycles

CRACK WAS FOUND 0.250" OF LENGTH ON FUSELAGE SKIN STA Y=160 BTW LONGS 3L & 4L. FUSELAGE SKIN WAS REPAIRED PER SRM 53-04-3 FIG 8 (SHEET 5).

Part: SKIN — CRACKED (FUSELAGE) · airframe 82,537 hrs · 63,076 cycles

CRACK WAS FOUND 0.250" OF LENGTH ON FUSELAGE SKIN STA Y=160 BTW LONGS 3L & 4L. FUSELAGE SKIN STA Y=160 BTW LONGS 3L & 4L WAS REPAIRED PER SRM 53-04-3 FIG 5 (SHEET 3).

Part: BEAM — CORRODED (FUSELAGE) · corrosion level 2 · airframe 82,537 hrs · 63,076 cycles

CORROSION ON DOOR JAMB LOWER BEAM AND PREVIOUS REPAIR DOUBLER BTW Y=1155-1212 AT AFT CARGO COMPARTMENT (C3). (CORROSION LEVEL 2) DOOR JAMB LOWER BEAM AND PREVIOUS REPAIR DOUBLER BTW Y=1155-1212 AT AFT CARGO COMPARTMENT WAS REPAIRED PER SRM 53-05 FIG 123 A.

Part: DOOR FRAME — CRACKED (EMERGENCY EXIT) · airframe 82,537 hrs · 63,076 cycles

CRACK ON UPPER AREA OF THE DOOR JAMB AT RH FWD EMERGENCY EXIT DOOR. CRACK OF 0.750" LENGTH ON UPPER AREA OF THE DOOR JAMB AT RH FWD EMERGENCY EXIT DOOR WAS REPAIRED PER DC9/MD80 SRM 53-05 FIG 32. (LP0938242)

Part: DOOR FRAME — CORRODED (BS 1212-1218) · corrosion level 2 · airframe 82,537 hrs · 63,076 cycles

INITIAL INSPECTION: CORROSION ON DOOR JAMB WEB BTW STA 1212 TO 1218 L28R AT AFT CARGO COMPARTMENT. DOOR JAMB WEB BTW STA 1212 TO 1218 L28R AT AFT CARGO COMPARTMENT WAS REPAIRED PER DC9/MD80 SRM 53-01 FIG. 4. (LP0937071)

Part: SKIN — CRACKED (BS 422) · airframe 82,537 hrs · 63,076 cycles

FIVE CRACKS WERE FOUND ON LOWER AFT CORNER EXTERNAL SKIN AT FORWARD CARGO DOOR JAMB STA Y= 422. ON LOWER AFT CORNER EXTERNAL SKIN AT FORWARD CARGO DOOR JAMB STA Y= 422 WAS REPAIRED PER ER/A 575330-14AD REV.ORIGINAL (SECTION I PERMANENT REPAIR) AND ETI-88-19-011 REV.1.(LP0937207)

Part: INTERCOSTAL — CORRODED (BS 1212-1231) · corrosion level 2 · airframe 82,537 hrs · 63,076 cycles

CORROSION TYPE EXFOLIATION ON INTERCOSTAL BTW L29L STA 1212 TO 1231 AT AFT CARGO COMPARTMENT (C3). DUE TO THE EXCESSIVE DAMAGE (CORROSION LEVEL 2) INTERCOSTAL ON STA 1212 TO 1231 WAS REPLACED PER DWG : 5936071 REV: W AND DC-9/MD80 SRM 51-30-2 AND 51-30-5. (LP0935487)

Part: BEAM — CRACKED (L1 DOOR) · airframe 82,537 hrs · 63,076 cycles

INITIAL INSPECTION: CRACKED BEAM NBR 8 (AFT EDGE) AT FWD PASSENGER DOOR (L1). BEAM NBR 8 (CRACK OF 1.063") WAS REPAIRED PER DC9/MD80 SRM 52-05 PAR. 75 FIG 95 SHEET 3. (LP0934558)

Part: CHANNEL — CORRODED (BS 1117-1155) · corrosion level 2 · airframe 82,537 hrs · 63,076 cycles

INITIAL INSPECTION: CORROSION ON RH "Z" CHANNEL BTW STA 1117 TO 1155 AT AFT CARGO COMPARTMENT (C3). Z CHANNEL RH BTW STA 1117 TO 1155 AT AFT CARGO COMPARTMENT WAS REPLACED PER DC9/MD80 SRM 53-24-0 FIG. 11A AND SRM 51-30-01. (LP0934104)

Part: BEAM — CRACKED (L1 DOOR) · airframe 82,537 hrs · 63,076 cycles

INITIAL INSPECTION: CRACKED BEAM NBR 1 AND 2 (FWD EDGE) AT FWD PASSENGER DOOR (L1). BEAM NBR 1 (CRACK 0.750") AND BEAM NBR 2 (CRACK 0.781") ON FWD EDGE AT FWD PASSENGER DOOR WERE REPAIRED PER DC9/MD80 SRM 52-05, PAR. 68, FIG. 82 AND PAR. 69, FIG. 84. (LP0934224)

Part: DOUBLER — CORRODED (BS 579-593) · corrosion level 2 · airframe 82,537 hrs · 63,076 cycles

INITIAL INSPECTION: CORROSION ON REPAIR DOUBLER SPLICE BTW L30 TO LL29R AND STA 593 TO 579 AT MID CARGO COMPARTMENT. DOUBLER SPLICE BTW L30 TO LL29R AND STA 593 TO 579 AT MID CARGO COMPARTMENT WAS REPLACED PER DC9 / MD80 SRM 53-14-2 FIG.3. (LP0933052)

Part: DOOR — CORRODED (APU BAY) · airframe 82,537 hrs · 63,076 cycles

INITIAL INSPECTION:CORROSION ON RH DOOR AT APU.(EHV). RH ACCESS DOOR AT APU P/N: 5914694-95 S/N: UNKNOWN WAS REPLACE PER SERVICEABLE RH ACCESS DOOR AT APU P/N: 5914694-95 S/N: DL26. THEN FUNCIONAL TEST WAS PERFORMED AT PRESSURE RELIEF DOOR LATCHES. TEST OK PER MD88 AMM 52-45-00-201. (LP0931809)

Part: WINDOW SILL — CRACKED (COCKPIT) · airframe 82,141 hrs · 62,729 cycles

WINDOW SILL BETWEEN CAPTAIN WINDOW AND CENTER WINDOW IS CRACKED. REMOVED AND REPLACED WINDOW SILL BETWEEN CAPTAINS AND CENTER WINDSHIELD IAW SRM 51-30-1, 51-30-5 AND DWG 5912350 REV DV.

Part: WIRE — BROKEN (CABIN) · airframe 81,935 hrs · 62,543 cycles

ON SVC CK FOUND AFT EXIT DOOR EMERGENCY EXIT DOOR IDENTIFIER INOP. T/S REPLACED LIGHT ASSY -NO HELP FOUND BROKEN WIRE BEHIND SINK CABINET REPAIRED SAME, WDM 33-51. (LP4140023)

Part: SMOKE DETECTOR — FAILED (LAVATORY) · airframe 81,893 hrs · 62,503 cycles

LAVATORY SMOKE DETECTOR WILL NOT TURN OFF LOCATIONS:201. REPLACED LAV SMOKE DETECTOR. ATF/C LAV. OPS CKD OK. (LP0758906)

Part: SMOKE DETECTOR — FAULTY (LAVATORY) · airframe 81,759 hrs · 62,385 cycles

FWD LAV SMOKE DETECTOR ALERTING CONTINUOUSLY. R&R FWD LAV SMOKE DETECTOR.

Part: FLOOR PANEL — DAMAGED (CABIN) · airframe 81,280 hrs · 61,975 cycles

FLOOR PANEL WAS WEAK AND CONCAVED BETWEEN SEATS 1B AND 1C. REMOVED AND REPLACED THE FLOOR PANEL IAW AMM 53-20-01/201.

Part: CONNECTOR — LOOSE (CABIN) · airframe 81,242 hrs · 61,946 cycles

18DE EMERGENCY EXIT LIGHT INOP. RELAMP NO HELP(440303) FOUND CONNECTOR LOOSE AT ROW 18DE. SECURED CONNECTOR. CHECKS GOOD.

Part: PIN — MISSING (R1 DOOR SLIDE) · airframe 81,063 hrs · 61,815 cycles

FOUND THE R1 SLIDE ENGAGEMENT PIN MISSING. R & R THE R1 DOOR SLIDE IAW AMM 2561-4964.

Part: WIRE HARNESS — BROKEN (EMERGENCY LIGHTS) · airframe 81,013 hrs · 61,772 cycles

SEAT 30DE EMERGENCY LIGHT INOPERATIVE. FOUND THE WIRE HARNESS BROKEN UNDER THE SEAT. R & R THE WIRE HARNESS IAW AMM 33-53. OPS CHECKED GOOD.

Part: FILLER — CRACKED (CATWALK) · airframe 80,973 hrs · 61,743 cycles

FOUND RIGHT AFT FILLER ASSY ON CATWALK WITH 2 CRACKS. REMOVED AND REPLACED FILLER ASSY P/N 5937691-2 CKS GOOD.

Part: CONNECTOR — DAMAGED (WINDOW HEAT) · airframe 80,619 hrs · 61,461 cycles

FLASH FROM WIRING ON F/OS WINDOW WIRING. FOUND THE WINDOW HEAT CONNECTORS BROKEN AND FRAYED. REPLACED ALL THREE CONNECTORS WITH NEW IAW SWPM 20. OK FOR SERVICE.

Part: WIRE HARNESS — DEFECTIVE (CABIN) · airframe 80,045 hrs · 61,027 cycles

FOUND SEAT 34ED WHITE ESCAPE PATH LIGHT INOP. R&R HARNESS FROM LIGHT ASSY TO WALL CONNECTION PER SWPM CH 20.

Part: BULB — INOPERATIVE (EMERGENCY LIGHT) · airframe 79,885 hrs · 60,914 cycles

SEAT 18D EMERGENCY LIGHT INOP. REPLACED BOLBE AND LIGHT ASSY NO HELP. FOUND EMERGENCY LIGHT DISCONNECTED. RECONNECTED LIGHT. OPS CK GOOD. (LP3019173)

Part: FIRE WARNING — FALSE ACTIVATION (AFT CARGO BAY) · airframe 78,992 hrs · 60,161 cycles

RECEIVED AFT CARGO FIRE INDICATION AFTER LANDING. COMPLIED WITH QRH. INDICATION CEASED. REMOVED AND REPLACED NR 1 FIRE BOTTLE AND REPLACED AFT CARTRIDGE IAW AMM 26-22.

Part: CABLE — BROKEN (VENTRAL STAIR) · airframe 78,849 hrs · 60,050 cycles

CABLE ON VENTRAL STAIR CATWALK BROKEN.

Part: SKIN — CRACKED (FUSELAGE) · airframe 77,671 hrs · 59,179 cycles

ACFT SKIN SPLICE PLATE HAS .50 INCH LONG CRACK APPROXIMATELY 13 INCHES RT OF LONGERON 1. THE OTBD END OF THE CRACK WAS LOCATED WITH HFEC, THE INBD END EXTENDS UNDER VERTICAL STAB RT ATTACH ANGLE MOUNT DOUBLER. REPAIRED IAW PRI 554287-14 REV 0 AND COMPLIED WITH ER/A 554287-14 REV A.

Part: FRAME — CRACKED (NOT REPORTED) · airframe 77,671 hrs · 59,179 cycles

FRAME WEB HAS A 1.75 INCH LONG CRACK NEAR THE 8 CLOCK POSITION. REPAIRED REF ERA 554434-14 REV ORIG.

Part: BATTERY PACK — INOPERATIVE (EMERGENCY LIGHTS) · airframe 76,513 hrs · 58,319 cycles

LT AND RT FD OVERWING EXIT IDENTIFIER LIGHTS INOPERATIVE. REPLACED BATTERIES AT B5013 AND OPS CHECKED GOOD IAW AMM 33-53.

Part: WIRE — BROKEN (CABIN) · airframe 76,438 hrs · 58,270 cycles

EMERGENCY LIGHT OUT AT ROW 15, BROKEN WIRE BY SIDE WALL AT PIN. REPAIRED, NEW PIN INSTALLED. OPS CHECKS GOOD.

Part: DUCT — BLOWN (ANTI ICE) · airframe 76,189 hrs · 58,104 cycles

RETURNED TO DEPARTURE DUE TO RT ENGINE FIRE WARNING DURING CLIMB. ENGINE WAS NOT SHUTDOWN. MAINTENANCE FOUND REAR RT ANTI-ICE DUCT BLOWN. ALSO FOUND UPPER COWL DAMAGED. REPLACED RT REAR ANTI-ICE TUBE. UPPER COWL REPLACED ON LP 8019864. LEAK/ENGINE RUNS NORMAL. AIRCRAFT RTS.

Part: WIRE HARNESS — FAILED (EMERGENCY LIGHT) · airframe 75,522 hrs · 57,649 cycles

FLIGHT CREW ON FLT 2482, FOUND THE EMERGENCY LIGHT AT SEAT ROW 30 INOPERATIVE. MAINTENANCE FOUND AND REPAIRED A BAD JUNCTION BETWEEN THE ACFT AND SEAT.

Part: LAMP — INOPERATIVE (EMERGENCY LIGHT) · airframe 75,051 hrs · 57,334 cycles

DURING LINE CHECK, NOTED EMERGENCY LIGHTS IN AFT EQUIPMENT BAY WERE INOPERATIVE. REPLACED THE LAMP IAW AMM 33-53 AND OPS CHECKED GOOD.

Part: CONNECTOR — DETACHED (EMERGENCY LIGHTS) · airframe 73,467 hrs · 56,204 cycles

DURING LINE CHECK, MAINTENANCE FOUND THAT THE EMERGENCY LIGHTS AT THE FWD RT GALLEY SIDEWALL WAS INOPERATIVE. MAINTENANCE FOUND A CONNECTOR IN THE WIRE HARNESS AT THE FIRST ROW SEATS UNPLUGGED, RECONNECTED IT, AND FUNCTIONALLY CHECKED THE SYSTEM. LP 6721096.

Part: WIRE — LOOSE (EMERGENCY LIGHTS) · airframe 73,314 hrs · 56,102 cycles

DURING LINE CHECK, MAINTENANCE FOUND THAT THE EMERGENCY LIGHTING AT SEAT 26D IN THE CABIN WAS INOPERATIVE. MAINTENANCE CORRECTED A LOOSE CONNECTION AND THEN OPERATIONALLY CHECKED THE SYSTEM. LP 6721008

Part: LANYARD — DETACHED (L1 GIRT BAR) · airframe 72,808 hrs · 55,788 cycles

L1 DOOR GIRT BAR LANYARD CAME LOOSE. MAINTENANCE REINSTALLED GIRT BAR LANYARD.

Part: LOCK PIN — OUT OF ADJUST · airframe 72,534 hrs · 55,607 cycles

VENTRAL STAIR CAT WALK LOCK PIN IS OUT OF AJUSTMENT. ADJUSTED THE LOCK PIN IAW AMM 53-20-06. ACCOMPLISHED SATISFACTORY OPS CHECK IAW AMM 53-20-06.

Part: RELEASE CABLE — KINKED (TAILCONE) · airframe 72,527 hrs · 55,602 cycles

MAINTENANCE DISCOVERED THAT THE TAILCONE EMERGENCY RELEASE CABLE WAS KINKED BEYOND ALLOWABLE LIMITS. THE CABLE WAS REPLACED AND THE SYSTEM WAS RIGGED TO SPECIFICATIONS.

Part: CARGO TRACK — CORRODED (BS 1185-1220) · corrosion level 2 · airframe 72,527 hrs · 55,602 cycles

AFT CARGO TRACK LT SIDE HAS LIGHT CORROSION FROM BS 1185-1220 L27L. REMOVED THE CORROSION, FOUND 100 PERCENT MATERIAL LOSS IAW SRM 53-05. R & R THE CARGO TRACK IAW SRM 53-05, FIG 4G, SH 1.

Part: DOOR FRAME — CORRODED (BS 1174-1211) · corrosion level 2 · airframe 72,527 hrs · 55,602 cycles

AFT CARGO DOOR FRAME, FWD FACE AND LOWER FLANGE HAS CORROSION BETWEEN BS 1174-1211. REMOVED CORROSION IAW SRM 51-10-3 AND FOUND TO BE OUT OF LIMITS IAW SRM 53-05, FIG 123, SHT 2. LOCATED, DRILLED AND INSTALLED DOUBLER AND SPACER REPAIR PARTS IAW SRM 53-05, FIG 123.

Part: FORMER — CRACKED (BS 1401) · airframe 72,527 hrs · 55,602 cycles

AFT ACCESSORY BAY, LT SIDE AT BS 1401, LONGERON 14L HAS A CRACKED FORMER. REMOVED FORMER, FABRICATED NEW FORMER, LOCATED, AND INSTALLED IAW DWG 5913596, REV AL AND SRM 51-30-02, 51-30-05.

Part: FRAME — CORRODED (BS 1322) · corrosion level 2 · airframe 72,527 hrs · 55,602 cycles

AFT CARGO BS 1322 L30 CORRODED ON FRAME. THE FRAME IS OUT OF LIMITS IAW SRM 53-01. CUT OUT DAMAGE SECTION, FABRICATED, AND INSTALLED REPAIR IAW SRM 53-03, FIG 2A.

Part: FRAME — CRACKED (BS 1485) · airframe 72,527 hrs · 55,602 cycles

AFT ACCESSORY BAY CANTED FRAME BS 1485, LT SIDE LOWER WEB CRACKED. CUT OUT CRACKED SECTION OF WEB,. FABRICATED AND INSTALLED DOUBLER AND TRIPLER IAW SRM 53-03, FIG 48.

Part: STRUCTURE — CORRODED (BS 1231) · corrosion level 2 · airframe 72,527 hrs · 55,602 cycles

CORROSION IN AFT CARGO BILGE AREA, BS 1231 L29R-28R, FWD AND AFT OF FORMER. REMOVED THE CORROSION AND EVALUATED MAT AT STA 1231, FROM L-29R-28R ON FORMER. ORIG MATERIAL .080, REMAINING MATERIAL .050, MAT LOSS .030 AND FOUND TO BE OUT OF LIMIT IAW SRM 53-01, REPLACED FORMER IAW SRM 51-30-5.

Part: LONGERON — DAMAGED (BS 305) · airframe 72,527 hrs · 55,602 cycles

FOUND A DENTED AND BENT LONGERON AT FORWARD CARGO BAY BS 305, LONGERON L29R. REPAIRED THE LONGERON FLANGE IAW SRM 51-10-2. HFEC AREA IAW NDT SPM, PT 6 06-10-01. NO CRACKS NOTED, FABRICATED AND INSTALLED A REPAIR ANGLE IAW SRM 53-02, FIG 19.

Part: LONGERON — DAMAGED (BS 305) · airframe 72,527 hrs · 55,602 cycles

FOUND A DENTED AND BENT LONGERON AT BS 305, LONGERON 30L. REPAIRED IAW SRM 51-10-2. HFEC AREA IAW NDTSPM PT6 06-10-01, NO CRACKS NOTED, FABRICATED AND INSTALLED A REPAIR ANGLE IAW SRM 53-02, FIG 19.

Part: FRAME — CRACKED (BS 1287) · corrosion level 2 · airframe 72,527 hrs · 55,602 cycles

FRAME BS 1287 LONGERON 23L CRACKED AND CORRODED. A CUT OUT DAMAGED SECTION OF FRAME. FABRICATED REPAIR AND INSTALLED IAW SRM 53-03, FIG, 2 A.

Part: LONGERON SPLICE — CORRODED (BS 1420) · corrosion level 2 · airframe 72,527 hrs · 55,602 cycles

AFT ACCESSORY BAY LONGERON SPLICE 17R AT BS 1420 WAS CORRODED. REMOVED CORROSION AND FOUND TO BE OUT OF LIMITS IAW SRM 53-01 AND 51-10-03, PARA 26. REMOVED AND INSTALLED A NEW LONGEORN SPLICE IAW SRM 51-30-05 AND 51-10-4, PARA 2.

Part: STRUCTURE — CORRODED (BS 408-427) · corrosion level 2 · airframe 72,527 hrs · 55,602 cycles

FWD CARGO BAY BS 408-427, STR 29-30L HAS AREAS OF CORROSION. REMOVED CORROSION IAW SRM 51-10-3 AND FOUND OUT OF LIMITS IAW SRM 53-01, FIG 1, PAGE 3. CUT OUT DAMAGE AREA, FABRICATED AND INSTALLED REPAIR IAW SRM 53-02, FIG 18.

Part: DOOR FRAME — CRACKED (R1 DOORWAY) · airframe 72,527 hrs · 55,602 cycles

CRACK NOTED ON R1 DOOR, LOWER AFT DOOR FRAME CORNER. CUTOUT DAMAGED AREA, FABRICATED AND INSTALLED REPAIR IAW SRM 53-05, FIG 112.

Part: LONGERON — DAMAGED (BS 305) · airframe 72,527 hrs · 55,602 cycles

FOUND DENT AND BENT LONGERON AT FORWARD CARGO COMPARTMENT BS 305, LONGERON L28R. CUTOUT DAMAGED SECTION OF LONGERON IAW SRM 53-02, PAR 12 FIG 18. C/W HFEC INSP ON CUT OUT AND OPEN EXISTING HOLES IAW NDT SPM PART 6, 06-01-01 NO DEFECTS NOTED A NR 15270. LOCATED AND DRILLED LONGERON SECTION AND INSTALLED REPAIR PARTS ALL IAW SRM 53-02, PARA 12, FIG 18.

Part: SKIN — CORRODED (BS 1338) · airframe 72,527 hrs · 55,602 cycles

LT SIDE AFT FUSELAGE BS 1338, L22L, CORROSION ON EXTERIOR FUSELAGE SKIN. REPLACED SKIN BS 1202-1338, L18-26L IAW DWG 593021, REV EH.

Part: FRAME — CRACKED (BS 1437) · airframe 72,527 hrs · 55,602 cycles

AFT ACCESSORY BAY FRAME BS 1437, L2L CRACKED. REPLACED FRAME IAW SRM 51-30-2.

Part: LONGERON — CRACKED (BS 1437) · airframe 72,527 hrs · 55,602 cycles

AFT ACCESSORY BAY BS 1437, LONGERON 2R CRACKED. REPLACED IAW SRM 51-30-2.

Part: FLOORBEAM — CORRODED (BS 1338) · corrosion level 2 · airframe 72,527 hrs · 55,602 cycles

CORROSION ON FLOORBEAM BS 1338 RBL 20-40. REMOVED CORROSION IAW NDT SPM PART 4, 04-00-07. FOUND TO BE OUT OF LIMITS IAW SRM 53-01. REPAIRED IAW ERA 397783-14MA.

Part: ATTACH ANGLE — CORRODED (RT WING TE FLAP) · airframe 77,268 hrs · 58,878 cycles

CORROSION ON ATTACH ANGLE, INSIDE RT WING OTBD FLAP, INBD HINGE, INSIDE INSPECTION ACCESS OPENING. FOUND OUT OF LIMITS. FABRICATED AND INSTALLED REPAIR DOUBLER.

Part: SEAT TRACK — CORRODED (BS 788-1041) · corrosion level 2 · airframe 72,527 hrs · 55,602 cycles

SEAT TRACK, LBL 54, BS 788-1041 CORRODED. R & R THE SEAT TRACK IAW AMM 53-40-01.

Part: SEAT TRACK — CORRODED (BS 936-1088) · corrosion level 2 · airframe 72,527 hrs · 55,602 cycles

SEAT TRACK BS 936-1088 FOUND TO BE CORRODED AT LBL 22. REMOVED THE SEAT TRACK, LOCATED AND DRILLED A NEW SEAT TRACK AND INSTALLED IAW AMM 53-40-01 AND SRM 51-10-04, PARA 9.

Part: SUPPORT ANGLE — CORRODED (CARGO DOOR) · airframe 77,268 hrs · 58,878 cycles

MID CARGO DOOR INTERNAL STRUCTURE CORRODED AT BOTTOM OF DOOR, STRUCTURE SUPPORT LENGTH OF DOOR. REMOVED AND REPLACED STRUCTURAL SUPPORT ANGLE ON MID CARGO DOOR INTERNAL STRUCTURE BOTTOM SIDE.

Part: SEAT TRACK — DAMAGED (BS 1030-1309) · corrosion level 2 · airframe 72,527 hrs · 55,602 cycles

MAIN CABIN SEAT TRACK BS 1030-1309, RBL 58, HAS SURFACE SCRATCHES, AND CORROSION. REMOVED THE CORROSION AND FOUND TO BE OUT OF LIMIT. R & R THE SEAT TRACK IAW SRM- 51-10-3, 53-05, 51-10-4, AMM 53-40-01.

Part: SUPPORT ANGLE — CORRODED (CARGO DOOR) · airframe 77,268 hrs · 58,878 cycles

CORROSION FOUND IN MID CARGO DOOR INTERNAL STRUCTURE ANGLE SUPPORT FWD TO AFT OF IS EXFOLIATED. REMOVED AND REPLACED THE ANGLE SUPPORT .

Part: SEAT TRACK — CORRODED (BS 788-1041) · corrosion level 2 · airframe 72,527 hrs · 55,602 cycles

SEAT TRACK RBL 54, BS 788-1041 CORRODED. REMOVED AND REPLACED THE SEAT TRACK IAW AMM 53-40-01 AND SRM 51-10-4, PARA 2.

Part: CUSP WEB — CRACKED (BS 1002-1022) · airframe 72,527 hrs · 55,602 cycles

FOUND CRACK & HOLE AT CUST WEB LOWER SURFACE FROM BS 1002 - 1022 LONGERON 18L. REMOVED AND REPLACED THE CUSP WEB IAW PARA 2, 51-30-02,51-30-01 & 51-30-05.

Part: CUSP WEB — CORRODED (BS 1212) · airframe 77,268 hrs · 58,878 cycles

CORROSION FOUND ON THE CUSP WEB LOWER SURFACE BS 1212 LONGERON 18L. THE CUSP WEB WAS FOUND TO BE OUT OF LIMITS 100% MATERIAL LOSS. DOUBLER AND FILLER FABRICATED AND INSTALLED.

Part: SHEAR TIE — CORRODED · airframe 77,268 hrs · 58,878 cycles

CORROSION ON SHEAR TIE. FOUND TO BE BEYOND LIMITS. CUT OUT THE DAMAGED SECTION LONGERONS 29L. FABRICATED A REPAIR AND INSTALLED.

Part: CUSP WEB — CRACKED (BS 1103) · airframe 72,527 hrs · 55,602 cycles

RT CUSP WEB BS 1103 IS CRACKED. CUT OUT DAMAGE AREA. FABRICATED REPAIR DOUBLER, REPAIR FILLER, AND INSTALLED REPAIR IAW SRM 53-05, FIG 131A-5 AND FAS ER NR 2-37153-801A, REV A.

Part: CUSP WEB — CORRODED (BS 1060-1079) · airframe 77,268 hrs · 58,878 cycles

RIGHT CUSP WEB BETWEEN BS 1060-1079 IS CORRODED. CUTOUT THE DAMAGE, FABRICATED A REPAIR AND INSTALLED.

Part: CUSP WEB — CORRODED (BS 1065) · airframe 77,268 hrs · 58,878 cycles

CORROSION ON LT CUSP WEB AT BS 1065. CUT OUT DAMAGE, FABRICATED A REPAIR AND INSTALLED.

Part: CUSP WEB — CORRODED (BS 1084) · airframe 77,268 hrs · 58,878 cycles

CORROSION ON RT CUSP WEB AT BS 1084. CUTOUT THE DAMAGE, FABRICATED A REPAIR AND INSTALLED.

Part: FLOOR SKIN — CRACKED (BS 160) · airframe 72,527 hrs · 55,602 cycles

COCKPIT FLOOR WEB APPROXIMATELY BS 160, RBL 14 IS CRACKED. COCKPIT FLOOR WEB STA 160, RBL14 CUTOUT DAMAGE, FABRICATED REPAIR DOUBLER, ALODINED AND PRIMED, AND INSTALLED REPAIR DOUBLER IAW SRM 53-01, FIG. 4.

Part: PAN — CRACKED (CABIN WINDOW) · airframe 72,527 hrs · 55,602 cycles

L/T SIDE MAIN CABIN WINDOW PAN BETWEEN BS 541-560 TABS SHOWED EVIDENCE OF CRACKS. REPAIRED LT WINDOW PAN IAW ER/A 333615-14MA, REV G.

Part: PAN — CRACKED (CABIN WINDOW) · airframe 72,527 hrs · 55,602 cycles

L/T SIDE MAIN CABIN WINDOW PAN BETWEEN BS 560-579 BOTH UPPER AND LOWER TABS SHOWED EVIDENCE OF CRACKS. REPAIRED PAN IAW ER/A 333615-14MA, REV G .

Part: PAN — CRACKED (CABIN WINDOW) · airframe 72,527 hrs · 55,602 cycles

RIGHT SIDE MAIN CABIN WINDOW PAN BETWEEN BS 655-674, UPPER TAB SHOWED EVIDENCE OF A CRACK. REPAIRED IAW ER/A 333615-14MA REV G.

Part: SKIN — CRACKED · airframe 72,527 hrs · 55,602 cycles

LT SIDE, AFT NLG DOOR CUT-OUT, AFT HINGE CUT-OUT IS CRACKED ON FUSELAGE SKIN. CRACK TERMINATED ON END THE HINGE CUT OUT SKIN. FABRICATED REPAIR DOUBLER AND INSTALLED IAW SRM 53-05, FIG 158. AND SRM 51-30-02.

Part: LONGERON — CORRODED · corrosion level 2 · airframe 72,527 hrs · 55,602 cycles

CORROSION ON LONGERON 30L INSIDE MID OVERHEAD BIN JUST INSIDE OF DOOR LOWER FRAME. FABRICATED REPAIR DOUBLER AND FILLER IAW ER/A 504719-14, REV ORIG. AND INSTALLED IAW ER/A 504719-14, REV ORIG.

Part: RELEASE CABLE — WORN (TAILCONE) · airframe 72,527 hrs · 55,602 cycles

MAINTENANCE DISCOVERED THAT THE KEVLAR SLEEVE OVER THE RELEASE CABLE FOR THE TAILCONE WAS WORN OUT OF ALLOWABLE LIMITS. THE CABLE WAS REPLACED AND THE SYSTEM WAS RIGGED TO SPECIFICATIONS. THE FUNCTIONAL CHECK WAS COMPLETED SATISFACTORILY.

Part: SKIN — CRACKED (NLG DOOR) · airframe 72,527 hrs · 55,602 cycles

RT SIDE AFT NLG DOOR, POSSIBLE CRACK ON EXISTING DOUBLER REPAIR, AFT HINGE. REMOVED EXISTING DOUBLER REPAIR AND FABRICATED NEW REPAIR DOUBLER IAW SRM 53-05, FIG 158, INSTALLED ID TAG IAW DELTA PSM.900-5-1, NR 04. REMOVED EXISTING DOUBLER REPAIR AND FABRICATED NEW REPAIR DOUBLER IAW SRM 53-05, FTG 158, INSTALLED ID TAG IAW DELTA PSM 900-5-1, NR 04.

Part: BATTERY PACK — INOPERATIVE (EMERGENCY LIGHTS) · airframe 71,761 hrs · 55,028 cycles

DURING LINE CHECK, MAINTENANCE FOUND THAT THE OVERHEAD EMERGENCY LIGHTS AT ROWS 11-14 IN CABIN WERE INOPERATIVE. MX REPLACED THE BATTERIES IN THE POWER SUPPLY AND THE LIGHTS RETURNED TO AN OPERATIONAL CONDITION.

Part: BATTERY PACK — INOPERATIVE (EMERGENCY LIGHT) · airframe 71,761 hrs · 55,028 cycles

DURING LINE CHECK, MAINTENANCE FOUND THAT THE EMERGENCY PATHWAY LIGHTING AT SEAT 33 IN THE CABIN WAS INOPERATIVE. MAINTENANCE REPLACED THE BATTERY PACK FOR THE NOTED LIGHTED AREA AND OPS CHECKED GOOD.

Part: BATTERY PACK — INOPERATIVE (EMERGENCY LIGHTS) · airframe 70,870 hrs · 54,437 cycles

DURING LINE CHECK, MAINTENANCE FOUND THAT THE EMERGENCY LIGHTING IN THE COCKPIT WAS INOPERATIVE. MAINTENANCE REPLACED THE BATTERY PACKS FOR THE NOTED LIGHTED AREAS AND THE OPS CHECK WAS GOOD.

Part: WIRE HARNESS — BROKEN (EMERGENCY LIGHTS) · airframe 70,249 hrs · 54,041 cycles

DURING LINE CHECK, MAINTENANCE FOUND THAT THE EMERGENCY LIGHTS AT ROW 16DE INOPERATIVE. MAINTENANCE FOUND THAT THE WIRE HARNESS WAS BROKEN, REPLACED WIRE HARNESS, AND FUNCTIONALLY CHECKED THE SYSTEM.

Part: SKIN — CRACKED (BS 1437) · airframe 69,516 hrs · 53,525 cycles

SKIN CRACKED AT FASTENER HOLE BELOW LONGERON 2R BS 1437. REPAIRED IAW ER/A 517463-14 REV ORIG.

Part: FRAME — CRACKED (BS 1463) · airframe 69,516 hrs · 53,525 cycles

FRAME WEB CRACKED AT STA 1463 BETWEEN 10 AND 11:00 POSITION FROM FASTENER ON LOWER CHORD -M-. BAR CODE: HK2TS7, MIRS WO NB: 10905-84, NR CARD SERIAL: 174, JOB NR: 00000. DISSASSEMBLED BRACKET AND CUTOUT SPIDER WEB CRACK PATTERN TO CONTAIN DAMAGE. AFT WEB DAMAGE CONTAINED. REMOVED CRACKED SECTION -39 WEB (361750) VERIFY DAMAGE CONTAINED HFEC INSP DAMAGE CONTAINMENT-OK IAW NDT SPM 06-10-01-001. REPAIR FABRICATION OF FILLER, DOUBLER, & SHIMS AND INSTALLED REPAIR IAW ER/A 517570-14 REV. O.

Part: CABLE — OUT OF RIG (TAILCONE RELEASE) · airframe 69,516 hrs · 53,525 cycles

DURING THE TAILCONE RELEASE SYSTEM FUNCTIONAL CHECK, MX FOUND THAT THERE WAS EXCESSIVE TENSION IN THE RELEASE CABLE SYSTEM. THE CABLE T-PIN CLIPS WERE RE-ADJUSTED AND THE SYSTEM WAS RE-RIGGED. THE RII STEPS WERE COMPLETED AND THE FOLLOW-UP CHECK WAS SUCCESSFUL.

Part: LATCH — WORN (TAILCONE RELEASE) · airframe 69,516 hrs · 53,525 cycles

DURING A CHECK OF TAILCONE RELEASE SYSTEM, MX FOUND THAT THE UPPER RT SIDE CABLE BLOCK FOR THE TAILCONE LATCH WAS WORN BEYOND ALLOWABLE LIMITS. MX REPLACED THE UPPER SLIDING BLOCKS FOR THE RT SIDE ONLY. THE TAILCONE WAS RIG CHECKED AFTER INSTALLATION AND FOUND OPS.

Part: ARM — WORN (TAILCONE RELEASE) · airframe 69,516 hrs · 53,525 cycles

MX DISCOVERED THAT THE RT UPPER RELEASE LATCH LEVER FOR THE TAILCONE WAS WORN BEYOND ALLOWABLE LIMITS. THE LATCH LEVER ARM WAS REPLACED AND THE SYS WAS RIGGED TO SPECIFICATIONS. THE FUNCTIONAL CHECK WAS COMPLETED SATISFACTORILY.

Part: SKIN — CRACKED (BS 1418) · airframe 69,509 hrs · 53,518 cycles

SKIN CRACKED AT BS 1418, RT SIDE UNDER VERTICAL STAB L/E. REPAIRED SKIN CRACK IAW ER/A 517531-14AD SECTION I, REVISION ORIGINAL.

Part: STRUCTURE — DAMAGED (VERTICAL STAB) · airframe 69,509 hrs · 53,518 cycles

THE 4, 5 & 6 FASTENER ABOVE VFS 52.267 ELONGATED. DISTORTED VERTICAL STAB REAMED HOLES, HFEC INSPECTED, REPAIRED IAW ER/A 517473-14AD REVISION ORIGINAL.

Part: STRUCTURE — CRACKED (VERTICAL STAB) · airframe 69,509 hrs · 53,518 cycles

FWD FLANGE VERTICAL STABILIZER CRACKED. FIRST FASTENER ABOVE VFS 52-267 SPLICE SHOWS CRACK INIDCATION RT SIDE. REMOVED L/E, ACCOMPLISHED INSPECTION, REPAIR ACCOMPLISHED IAW ER/A 517473-14AD, REV ORIGINAL.

Part: NOZZLE — FAILED (ACM) · airframe 69,357 hrs · 53,405 cycles

DIVERTED FLIGHT AFTER SMOKE AND A BURNING ODORS WERE NOTED IN THE CABIN AND COCKPIT. LT PACK TURBINE NOZZLE AND PNEUMATIC PRESSURE REGULATOR BAD AND REPLACED. PERFORMED DUCT BURNOUT. OPS CHECKED OK AND NO FURTHER SMOKE OR FUMES WERE NOTED.

Part: BATTERY PACK — INOPERATIVE (EMERGENCY LIGHT) · airframe 69,210 hrs · 53,306 cycles

DURING LINE CHECK, MX FOUND THAT THE EMERGENCY LIGHTING IN THE COCKPIT WAS INOPERATIVE. MX INSTALLED A NEW BATTERY PACK AND THE LIGHTS RETURNED TO AN OPS CONDITION.

Part: POWER SUPPLY — INOPERATIVE (EMERGENCY LIGHT) · airframe 67,843 hrs · 52,380 cycles

DURING LINE CHECK, MX FOUND THAT BOTH THE LT AND RT OVERWING EMERGENCY EXIT SIGNS WERE INOPERATIVE. MX REPLACED THE FORWARD LEFT POWER SUPPLY AND THE LIGHTS RETURNED TO AN OPS CONDITION.

Part: BATTERY PACK — INOPERATIVE (EMERGENCY LIGHT) · airframe 67,614 hrs · 52,207 cycles

DURING EMERGENCY LIGHT TEST, OVER WING LIGHT WERE INOPERATIVE, REPLACED BATTERY PACK AND TESTED OK.

Part: WIRE HARNESS — DAMAGED (EMERGENCY LIGHTS) · airframe 66,405 hrs · 51,322 cycles

DURING LINE CHECK, MAINTENANCE FOUND THAT THE EMERGENCY PATHWAY LIGHTING AT ROW 23DE IN THE CABIN WAS INOPERATIVE. MAINTENANCE REPLACED THE SEAT WIRE HARNESS AT 23DE AND FUNCTIONALLY CHECKED THE SYSTEM.

Part: FLOORBEAM — CORRODED (FUSELAGE) · airframe 65,853 hrs · 50,984 cycles

AFT CABIN STA 1338 LBL 30 TO LBL 42 FLOOR BIN WITH CORROSION. REMOVED CORROSION, FOUND TO BE OUT OF LIMITS, REMOVED DAMAGED AREA OF FLOORBEAM, FABRICATED FLOORBEAM REPAIR AND INSTALLED IAW DC9/MD80 SRM 53-05 DURING MAINTENANCE VISIT.

Part: TRACK — CORRODED (FUSELAGE) · airframe 65,853 hrs · 50,984 cycles

MAIN ENTRY AREA STA 165 RBL 7 TRACK WITH CORROSION. REMOVED CORROSION, FOUND TO BE OUT OF LIMITS, REMOVED, FABRICATED AND INSTALLED TRACK AT MAIN ENTRY AREA DURING CPCP MAINTENANCE VISIT.

Part: SUPPORT — CORRODED (FUSELAGE) · airframe 65,853 hrs · 50,984 cycles

CORROSION ON SUPPORT LOCATED AT STA 256-2 AND LBL 35. REMOVED CORROSION, FOUND TO BE OUT OF LIMITS, REMOVED SUPPORT, FABRICATED AND INSTALLED NEW SUPPORT IAW DC9/MD80 SRM 51-30 DURING MAINTENANCE VISIT.

Part: FINGER DOUBLER — CORRODED (FUSELAGE) · airframe 65,853 hrs · 50,984 cycles

CORROSION INSIDE BILGE MID CARGO COMPARTMENT AT STA 579 TO 598 BETWEEN R29 AND R28. REMOVED FASTENERS, REMOVED CORROSION, FOUND TO BE OUT OF LIMITS, REMOVED DAMAGED FINGER DOUBLER, FABRICATED AND INSTALLED IAW DC9/MD80 SRM 51-10-2 DURING MAINTENANCE VISIT AT ST AEROSPACE SAN ANTONIO.

Part: SKIN PANEL — CRACKED (HORIZ STAB) · airframe 65,853 hrs · 50,984 cycles

MAJOR REPAIR, UPPER AFT SKIN PANEL ON THE RT SIDE OF THE HORIZONTAL STABILIZER WAS PREVIOUSLY FOUND CRACKED DURING INSPECTION BY EA 09-460214-12AD, MAINTENANCE TO PERFORM A BONDED DOUBLER TO THIS AIRCRAFT TO PROVE OUT THE METHOD AND GAIN AMOC APPROVAL TO AD 2007-10-04. ER/A 499760-14AD PROVIDES INSTRUCTIONS TO ACCOMPLISH.

Part: FRAME — CORRODED (FUSELAGE) · airframe 65,853 hrs · 50,984 cycles

CORROSION ON FRAME LOCATED AT STA 1309 BETWEEN LONGERON 28L AND 28R. REMOVED CORROSION, FOUND TO BE OUT OF LIMITS, REMOVED DAMAGE, FABRICATED REPAIR SECTION AND ANGLES, INSTALLED REPAIR IAW DC9/MD80 SRM 53-03 DURING CPCP MAINTENANCE VISIT AT ST AEROSPACE SAN ANTONIO.

Part: STRUCTURE — CRACKED (HORIZ STAB) · airframe 65,853 hrs · 50,984 cycles

ACCOMPLISH ERA 499760-14AD FOR CRACKED HORIZONTAL STABILIZER. COMPLIED WITH ERA 499760-14AD REVISION 0 DURING MAINTENANCE VISIT.

Part: SKIN — GOUGED (FUSELAGE) · airframe 65,853 hrs · 50,984 cycles

LT AFT EXTERNAL LAVATORY SERVICE PANEL CHAFING 2 PLACES AND GOUGED TOWARD AFT. GOUGE FOUND TO BE OUT OF LIMITS, ACCOMPLISHED ERA 49973-14 REV 1 DURING CPCP MAINTENANCE VISIT.

Part: BATTERY PACK — DISCHARGED (COCKPIT) · airframe 65,388 hrs · 50,678 cycles

MAINTENANCE FOUND THAT THE EMERGENCY LIGHTING IN THE COCKPITWAS INOPERATIVE, ALTHOUGH THE CABIN EEPLS WORKED NORMALLY. MAINTENANCE REPLACED THE BATTERY PACK AND THE LIGHTS RETURNED TO AN OPERATIONAL CONDITION.

Part: LIGHT — DAMAGED (CABIN) · airframe 63,457 hrs · 49,351 cycles

DURING LINE CHECK MAINTENANCE FOUND EMERGENCY LIGHT ASSEMBLY AT SEAT 2C DAMAGED. MAINTENANCE REPLACED LIGHT ASSEMBLY AT 2C. OPERATION OF LIGHT CHECKS OK.

Part: WIRE — DAMAGED (EMERGENCY LIGHTS) · airframe 63,188 hrs · 49,182 cycles

DURING LINE CHECK, MX FOUND NR1 & NR2 LOWER ESCAPE PATH LIGHTS ABOVE CATWALK IN TAIL COMPARTMENT INOPERATIVE. MX RETERMINATED BOTH LIGHTS SWPM 20. OPS OF LIGHTS NOW CHECKS OK.

Part: SKIN — CRACKED (HORIZ STAB) · airframe 61,417 hrs · 47,970 cycles

FAILED OPERATION 8959AD. PERFORMED TEMPORARY REPAIR PER DWG SR09550028-NOTE 42. HFEC RE-INSPECT PWR DWG EVERY 500 CYCLES. MTC PERFORMED ON LOG PAGES J293326002 AND J293326005.

Part: TERMINAL — LOOSE (EMERGENCY LIGHTS) · airframe 61,319 hrs · 47,900 cycles

DURING MAINTENANCE CHECK FOUND ALL EMERGENCY LIGHTS AFT OF ROW 31 INOP. MAINTENANCE FOUND TERMINALS LOOSE AT AFT BUS BAR S3-388. SECURED WITH NEW HARDWARE. OPERATIONAL CHECK OF LIGHTS IS NOW GOOD.

Part: WIRE HARNESS — FAULTY (CABIN) · airframe 61,266 hrs · 47,861 cycles

DURING A LAYOVER CHECK, MAINTENANCE FOUND THE FLOOR EMERGENCY LIGHTS AT 17DE TO BE INOPERATIVE. MAINTENANCE REPLACED THE WIRE HARNESS AT 17DE. AN OPERATIONAL CHECK WAS NORMAL AND THE AIRCRAFT WAS RETURNED TO SERVICE.

Part: BATTERY PACK — INOPERATIVE (EMERGENCY LIGHTS) · airframe 61,112 hrs · 47,760 cycles

MX FOUND THE EMERGENCY LIGHTS ABOVE THE L1 AND R1 FLIGHT DECK DOORS TO BE INOPERATIVE. MX REPLACED THE BATTERIES, ONE OF WHICH WAS AT ZERO VOLTS. AN OPS CHECK WAS GOOD AND THE ACFT WAS RETURNED TO SERVICE.

Part: BATTERY PACK — INOPERATIVE (EMERGENCY LIGHTS) · airframe 61,064 hrs · 47,729 cycles

EMERGENCY LIGHTS INOPERATIVE AT SEATS 31 - 38. REPLACED BATTERY PACK. LIGHTS CHECK NORMAL.

Part: BATTERY PACK — INOPERATIVE (EMERGENCY LIGHTS) · airframe 61,033 hrs · 47,717 cycles

EMERGENCY PATH LIGHT ON CEILING AT DOOR 2L WAS INOPERATIVE. MAINT REPLACED THE BATTERY POWER SUPPLY AT ROE 35DE OVERHEAD BIN. OPERATION OF LIGHTS NOW CHECKS GOOD.

Part: BATTERY PACK — INOPERATIVE (EMERGENCY LIGHT) · airframe 60,945 hrs · 47,668 cycles

CEILING EMERGENCY LIGHTS OUT FROM ROW 17 TO 30. REPLACED BATTERIES FOR POWER SUPPLIES AT B5-104 STA 902 AND B5-106 STA 1057 ROW 17 TO 22 STILL INOP ROW 22 TO 30 CK GOOD /981218. REPLACED EMERGENCY BATTERIES AT POWER SUPPLY B5-102 STA 671. ALL EMERGENCY LIGHTS ON, NOW NORMAL. OK FOR SERVICE.

Part: BRACKET — CRACKED (LT OWING DOOR) · airframe 58,922 hrs · 46,346 cycles

DURING MAINTENANCE FOUND CRACKED LOWER AFT FITTING AT LT AFT OVERWING EXIT DOOR. FITTING BRACKET WAS REPLACED IAW SRM'S 51-30-2, 51-10-4 AND 51-10-3.

Part: SKIN — DAMAGED (FUSELAGE) · airframe 58,922 hrs · 46,346 cycles

THIS NR IS ISSUED DUE TO REWORKED AREA OUT OF LIMITS PER NR T0129257 AR STA Y=646. DAMAGE REPAIRED IAW SRM 53-05 FIG 123.

Part: HEATER — MISINSTALLED (WING ANTI ICE) · airframe 58,922 hrs · 46,346 cycles

REMOVE AND REPLACE RT WING ANTI-ICE HEATER BLANKET DUE TO 3 VOIDS GREATER THAN 144 INCHES. HEATER BLANKET WAS REPLACED IAW SRM 51-20-0, EA 09-070683-03AD REV L, AND AMM 30-80-02-501.

Part: SUPPORT — DEFORMED (LT MLG) · airframe 58,922 hrs · 46,346 cycles

DEFORMED BEARING BORE ON LT MLG SUPPORT. BORE REWORKED IAW EA 09-093855-03 AD 0104.

Part: SUPPORT — CORRODED (LT MLG) · airframe 58,922 hrs · 46,346 cycles

PITTING CORROSION ON INNER SURFACE OF BUSHING BORE LT MLG SUPPORT. PITTING CORROSION REPAIRED IAW ERA 473515-14.

Part: SKIN — CRACKED (BS 1437) · airframe 58,922 hrs · 46,346 cycles

CRACK .075 INCH ON AFT FUSELAGE SKIN AT STA 1437 BTW LONG 2 RT AND 3 RT REF NR T0129081. CRACK REPAIRED IAW SRM 53-04D FIG 27.

Part: SKIN — MISREPAIRED (FUSELAGE) · airframe 58,922 hrs · 46,346 cycles

INADEQUATE INSTALLATION OF FASTENERS ON TEMPORARY PREVIOUS REPAIR OF FUSELAGE SKIN AT LEFT NOSE TUNNEL FROM STA Y=41 TO 47. DISCREPANCY REPAIRED IAW ERA 456678-14 REV C.

Part: TAB — DAMAGED (RUDDER) · airframe 58,922 hrs · 46,346 cycles

DAMAGED METALIZED OF RUDDER CONTROL TAB ROD FAIRING. THIS NR WAS ACCOMPLISHED IAW OPN 1031 CARDS 1640 TO 1648 AND SRM 51-70-1AD PARA 23.

Part: SIGN — UNKNOWN (EMERGENCY LIGHTS) · airframe 58,922 hrs · 46,346 cycles

EXIT SIGN LIGHT VALVE REQUIRED OUT OF LIMITS. EXIT SIGN LIGHTS WERE REPLACED IAW AMM 11-00-01-201.

Part: SKIN — CRACKED (BS 1437) · airframe 58,922 hrs · 46,346 cycles

CRACKS ON FUSELAGE SKIN STA Y=1437 LONG 2RT TO 4 LT. CRACKS REPAIRED IAW SRM 53-04 FIG 27.

Part: ANGLE — CORRODED (FUSELAGE) · airframe 58,922 hrs · 46,346 cycles

EXFOLIATION CORROSION ON WEB ANGLE STA Y=168 AND Y=200 X=60 AT FWD CABIN STRUCTURE W1. CORROSION DAMAGE REPAIRED IAW SRM 53-05 FIG 55.

Part: PANEL — CRACKED (VERTICAL STAB) · airframe 58,922 hrs · 46,346 cycles

CRACK OF 1.000 INCH ON VERTICAL STAB OVER LT PANEL LOWER SECTION OF REMOVABLE L/E. CRACK WAS REPAIRED IAW ERA 473514-14 REV ORIG.

Part: SKIN — DAMAGED (RUDDER) · airframe 58,922 hrs · 46,346 cycles

DAMAGED METALIZED FINISH ON RUDDER SURFACE. THIS NR WAS ACCOMPLISHED IAW OPN 1031 CARDS 1766-1774 AND SRM 51-70-1AD PARA 23A.

Part: LANYARD — BROKEN (L2 DOOR SLIDE) · airframe 58,922 hrs · 46,346 cycles

BROKEN STRANDS ON EVACUATION SLIDE AUTOMATIC FIRING LANYARD CABLE AT L2 DOOR. L2 DOOR EVACUATION SLIDE WAS REPLACED IAW OPN 3875 CARD 607 AND AMM 25-62-00.

Part: DOUBLER — WORN (L1 DOOR HOLD CUT) · airframe 58,922 hrs · 46,346 cycles

WEAR ON DOUBLER AT L1 DOOR HOLD OPEN CUT. DOUBLER REMOVED AND REPLACED IAW ERA 378453-14 REV A.

Part: SKIN — DAMAGED (BS 260-280) · airframe 58,922 hrs · 46,346 cycles

DUE AT HMV ERA 089062-14 REV C CODE 9-53-31-20 PERMANENT REPAIR. ERA C/W AT HMV ON AEROMEXICO NR T0128252.

Part: SKIN — DENTED (BS 211-219) · airframe 58,922 hrs · 46,346 cycles

DENTS ON FUSELAGE SKIN STA Y=219, 217, 211 BTW LONGS 17 AND 18 LT. DAMAGED SKIN REPLACED IAW SRM 53-04 FIG 12B.

Part: SKIN — DAMAGED (BS 1176-1181) · airframe 58,922 hrs · 46,346 cycles

WAVINESS ON FUSELAGE SKIN BTW STA Y=1176 TO 1181 AND LONG 17 AND 18 RT. SKIN WAS REPLACED IAW SRM 53-04D FIG 12C.

Part: PAN — DAMAGED (CARGO DOOR) · airframe 54,011 hrs · 43,063 cycles

SPARE CARGO DOOR. SDR REQUIRED FOR SRM 52-05D FIG 050. CRACK ON INNER PAN UNDER NR 3 STOP ON FORWARD SIDE OF DOOR. INSTALLED DOUBLER PER SRM 52-05 D FIG 50.

Part: STRUCTURE — BIRD STRIKE (FUSELAGE) · airframe 52,326 hrs · 41,972 cycles

THE RADOME, FUSELAGE SKIN FROM FS 37 TO 65.75, FS 37 BULKHEAD, AND OTHER FRAMES WERE DAMAGED BY A BIRD STRIKE. THE DAMAGED PARTS WERE REPLACED WITH NEW PARTS AND THE DAMAGED FUSELAGE SKIN WAS CUT OUT AND A NEW SKIN SECTION WAS SPLICED IN.

Part: SKIN — DAMAGED (FS 769-788) · airframe 50,997 hrs · 41,052 cycles

LIGHTNING STRUCK THE FUSELAGE SKIN AT THE WINDOW BELT BETWEEN FS 769-788. DAMAGED SKIN WAS BLENDED AND INSPECTED TO ENSURE DAMAGED MATERIAL WAS REMOVED.

Part: COFFEEMAKER — BURNED (AFT GALLEY) · airframe 50,897 hrs · 40,979 cycles

A/C ARRIVED WITH AN INBOUND STATING 'AFTER LANDING FLIGHT ATTENDANTS REPORTED ACRID SMELL IN AFT CABIN. SMELL DISSIPATED QUICKLY. ALL COCKPIT INDICATIONS APPEARED NORMAL. ANTI ICE WAS ON AND AIRFOIL WAS OFF'. AFTER C/W OPN 5088, MX FOUND COFFEE POTS HOT AND BURNT COFFEE IN BOTTOM OF POTS. A/C APU INTAKE IS CLEAN. AFT CARGO IS CLEAN. 48 SECTION CLEAN AND NO SMOKE DETECTED.

Part: SWITCH — FAILED (COCKPIT) · airframe 50,443 hrs · 40,640 cycles

UPON LANDING HEARD POP AND SAW SMALL AMOUNT OF SMOKE UNDER GLARESHIELD BENEATH NOSE LTS SWITCH. SMOKE/VAPOR DISSIPATE WITHIN SECONDS. ODOR ASSOCIATED. FOUND WIRES FOR BACKGROUND LIGHTING ON LANDING. PANEL CONNECTOR LOOSE AND ARCING. INSTALLED NEW LOCKWASHERS AND SECURED TERMINALS, ALL CHECKS GOOD.

Part: LINK — DEFECTIVE (NLG DOOR) · airframe 48,391 hrs · 39,156 cycles

AFTER GEAR RETRACTION LOUD NOISE AND VIBRATION IN COCKPIT. REPLACED RIGHT NOSE GEAR DOOR LINK.

Part: RELAY — FAILED (EMERGENCY LIGHT) · airframe 47,400 hrs · 38,472 cycles

A/C DID NOT PASS EMERGENCY POWER TEST. REPLACED BATTERY CHARGER AND TRANSFER RELAY.

Part: BULKHEAD — DAMAGED (FUSELAGE) · airframe 44,138 hrs · 36,219 cycles

THE BEARINGS IN THE THRUST REVERSER VALVE ACTUATING MECHANISM DETERIORATED ALLOWING THE P-DOME INSULATION BLANKET GUARD TO WEAR INTO THE P-DOME SKIN. ADDITIONALY, A SCREW ON THE VALVE CAM FOLLOWER CRANK ASSY WORE THROUGH THE P-DOME SKIN AND FWD DOUBLER. THE DAMMAGE IS AT Z=-23 AND RBL 35 ON THE STA 1338 P-DOME BULKHEAD. TWO DOUBLERS WERE INSTALLED ON THE FWD SIDE OF THE P-DOME PER ER/A 420372-14 TO REPAIR THE DAMAGE.

Part: SKIN — DAMAGED (FUSELAGE) · airframe 44,138 hrs · 36,219 cycles

DURING HMV-3, FOUND ADDITIONAL DAMAGE AT L-1 DOOR HOLD-OPEN HOOK CUTOUT. INCREASED CUTOUT IN FUSELAGE SKIN TO 3.75 IN. (FWD-AFT) BY 2.90 IN. (UP-DOWN) MAX. INSTALLED REPAIR DOUBLERS PER ER/A 378453-14 REV. A.

Part: ACTUATOR — LEAKING (LT MLG) · airframe 41,938 hrs · 34,677 cycles

AFTER GEAR RETRACTION ON T/O LEFT MAIN GEAR RED LIGHT REMAINED ON. POM ABNORMAL PROCEDURES FOLLOWED UNTIL GEAR DOWN WITH 3 GREEN LIGHTS. GEAR WAS LEFT DOWN AND RETURNED TO ATL. FOUND LT GEAR RETRACT ACTUATOR LEAKING. REMOVED AND REPLACED SAME. OP CHECKS GOOD.

Part: SWITCH — FAILED (COCKPIT) · airframe 41,523 hrs · 34,381 cycles

ALL THREE LANDING GEAR LIGHTS REMAINED ILLUM. RED WITH GEAR HANDLE UP, NORMAL INDICATION WITH GEAR HANDLE DOWN. GEAR CAME UP WITH GEAR HANDLE UP. REPLACED S1-89 (LEVER SWITCH) AND ACTUATOR PER M/M.

Part: LANYARD — BROKEN (EVAC SLIDE) · airframe 41,098 hrs · 34,055 cycles

L2 DOOR SLIDE LANYARD BROKEN. INSTALLED NEW LANYARD.

Part: BATTERY — DISCHARGED (CABIN) · airframe 39,667 hrs · 33,048 cycles

UPPER EMERGENCY FLASHLIGHT AT L1 DOOR HAS DEAD BATTERY. REPLACED BATTERY, OPS NORMAL.

Part: ENGINE — FAILED (NR 1) · airframe 39,564 hrs · 32,979 cycles

DURING CLIMB THROUGH FL300, ENGINE STALLED AND FLAMED-OUT UPON INITIAL POWER REDUCTION. THE ENGINE WAS BOROSCOPED ON 05/12/01 FOR ANOTHER STALL AT ALTITUDE. REPLACED ENGINE.

Part: ENGINE — FAILED (NR 1) · airframe 39,564 hrs · 32,979 cycles

DURING FLIGHT WHILE LEVELING AT FL310 NR 1 ENGINE CAUSED LOUD BOOM AND BEGAN ROLLING BACK. ENGINE WAS SHUT DOWN AND AIRCRAFT RETURNED TO ATL. REPLACED ENGINE.

Part: PROXIMITY SWITCH — INOPERATIVE (LT MLG) · airframe 37,355 hrs · 31,347 cycles

AFTER TAKEOFF IN DEN, ON GEAR RETRACTION, LEFT MLG UNSAFE LIGHT REMAINED ON. GEAR HANDLE UP, GEAR DOOR LIGHT OUT. CYCLED GEAR AS PER POM, LEFT MAIN GEAR UNSAFE REMAINED ON. GEAR RETRACTION WAS EXTREMELY LOUD WITH A LOT OF VIBRATION. REPLACED LEFT MAIN GEAR UPLOCK PROXIMITY SWITCH. SWUNG GEAR SEVERAL TIMES, ALL INDICATIONS NORMAL.

Part: WIRE — BROKEN (ROW 1)

ON PREFLIGHT CHECK, FOUND FIRST CLASS EMERGENCY LIGHTS NOT WORKING. FOUND WIRE BROKEN IN SEAT TRACK AT ROW 1 C, D. REPAIRED WIRE. REPLACED POWER SUPPLY AND BATTERY PACK.

Part: ACTUATOR — FAILED (LT MLG)

LT MAIN LANDING GEAR UNSAFE INDICATION WITH GEAR HANDLE UP. CYCLED GEAR DOWN, INDICATION OK. UP UNSAFE AGAIN. GEAR DOOR LIGHT OUT TILL FL270 THEN INTERMITTENT. ALSO, AUTOSPOILER FAIL MSG ON EOAP. DIVERTED TO DFW. REPLACED LEFT MAIN LANDING GEAR ACT, SWUNG GEAR. OPERATION NORMAL AND ALL INDICATION NORMAL.

Part: OIL SYST — LEAK (APU COMPT)

AFTER T/O, THE RIGHT AFT LAVATORY SMOKE DETECTOR WENT OFF. FLIGHT ATTENDANT REPORTED BURNING SMELL. RETURNED TO JFK. APU OIL LEAK. DUCT BURNOUT AND SOCK CHANGED.

Part: BEARING — FAILED (APU)

DURING CLIMBOUT, AFT LAV SMOKE DETECTOR SOUNDED AND SMOKE AND ODOR DETECTED BY FLT. ATTENDENTS. AIRCRAFT RETURNED TO YUL. CONTRACT MTC FOUND OIL LEAKING FROM APU INLET, SUBMITTER SUSPECTS BEARING FAILURE. MTC IN PROCESS OF CLEANING APU COMPARTMENT CHANGING WATER SEPARATOR BAGS AND DUCT BURNOUT.

Part: APU — LEAKING (AFT FUSELAGE)

AFTER TAKEOFF, THE FLIGHT ATTENDANTS REPORTED THE AFT LAVATORY SMOKE DETECTOR GOING OFF AND REPORTED SMOKE IN THE AFT CABIN. RETURNED TO GATE. FOUND APU LEAKING OIL INTO INLET, DEFERRED.

Part: ENGINE — FAILED (NR 1)

DURING FLT, NR 1 ENG COMPRESSOR STALLED AND ROLLED BACK. THIS WAS PROCEEDED BY A SINGLE CHUG AT APPROX FL 140 AND 280 KTS IN THE CLIMB. ENG SHUTDOWN IN FLT AND RETURNED TO BASE. REPLACED ENGINE.

Part: AIR DISTRIBUTION — ODOR (CABIN)

ON FINAL APPROACH, AN ACRID BURNING SMELL WAS DETECTED IN CBN/ CKPT. BOTH AFT SMOKE DETS WENT OFF. NO VISIBLE CONTAMINATION NOTED. PERFORMED DUCT BURNOUT PROCEDURES PER MM. INSP AREA FOR LKS AND SMELL/ NO PROBS NOTED. COALESCER BAGS PREV RPLD.

Part: FRAME — CRACKED (BS 1418)

DURING ACCOMPLISHMENT OF EO 9-63538-3, THE FRAME WAS FOUND TO BE CRACKED AT STR 2L AND 2R IN EXCESS OF 3 WHICH IS THE MAX ALLOWED BY THE MODIFICATION. THE CRACK WAS LOCATED AT STA 1418. THE FRAME WILL BE REPAIRED WITH A FACTORY STYLE SPLICE.

Part: LONGERON — CORRODED (BS 1300)

CORROSION WAS FOUND AROUND SEVERAL DRAIN HOLES ON LONGERONS 27L, 28L, AND 29L NEAR FS 1300. THE CORROSION RESULTED IN A LEAK IN THE GALLEY DRAIN TUBE. THE HOLES WERE OVERSIZED TO A MAX DIAMETER OF .5.

Part: STRINGER — CORROSION (BS 1315-1338)

CORROSION WAS FOUND ON STR 29L AT APPROX FS 1315 AND EXTENDING TO THE AFT END OF THE PART FS 1338. THE STRINGER WAS CUT AT STA 1315 AND THE SECTION WAS REMOVED. SPLICED INA NEW SECTION OF STRINGER PER ERA 330658-14.

Part: SKIN — DAMAGED (BS 200-208)

DAMAGE TO THE CROWN AREA SKIN RESULTED FROM SUDDEN CONTACT WITH AN OVERHEAD WORK PLATFORM. DAMAGE LOCATION IS FS 200 TO 208, AT S- 6 TO 7R. REMOVAL OF THE DAMAGE RESULTED IN A 7.5 FWD/AFT X 6 UP/ DOWN CUTOUT IN THE FUSELAGE SKIN. INSTALLED EXTERNAL SKIN DOUBLER PER ERA 330680-14.

Part: SKIN — DAMAGED (BS 238)

DAMAGE TO THE CROWN AREA SKIN RESULTED FROM SUDDEN CONTACT WITH AN OVERHEAD WORK PLATFORM. THE DAMAGE IS LOCATED AT STA 238, STR 6 TO 9. REMOVAL OF THE DAMAGE RESULTED IN A 4.5 FWD/AFT X 14.875 UP/DOWN CUTOUT IN THE FUSELAGE SKIN. AN EXTERNAL DOUBLER WAS INSTALLED TO REPAIR THIS DAMAGE.

Part: SPOILER — WORN (LT WING)

THE LT I/B AND O/B FLIGHT SPOILER CENTER HINGE ASSEMBLIES WERE BOTH WORN ON THE OUTBOARD FACE OF THE I/B LUG. THE BUSHINGS WERE REMOVED AND THE LUGS WERE SPOTFACED AS WELL AS LOCALLY BLENDED TO REMOVE DAMAGE. THE I/B HINGE FITTING WAS SPOTFACED .75 DEEP ON THE O/B FACE OF THE I/B LUG AND THE HOLE WAS OPENED UP TO .830. ON THE O/B HINGE, THE O/B FACE OF THE I/B LUG WAS SPOTFACED 0.080 DEEP, BUT THE HOLE WAS NOT ENLARGED.

Part: HINGE FITTING — CORROSION (LT SPOILER)

THE LT I/B AND O/B FLIGHT SPOILER CENTER HINGE FITTINGS WERE FOUND TO HAVE CORROSION LOCATED IN THE BORE THAT ACCEPTS THE ASBY 10-18 BEARING. THE HOLES HAVE BEEN OVERSIZED AND A BUSHING INSTALLED TO RETURN THE BORE TO THE ORIGINAL BP DIA. THE HOLE IN THE I/B HINGE FITTING WAS OVERSIZED TO 1.263 AND THE OUTER FITTING OVERSIZED TO 1.258. REPAIRED PER ERA 330667-14.

Part: SKIN — DENTED (BS 218)

THE FUSELAGE SKIN WAS FOUND TO HAVE A DENT AT FS 218 AT STR 17.4L. THE DENT WAS CUT OUT WITH THE DIMENSIONS OF .75 UP/DOWN AND 2.75 FWD/AFT. THIS DENT WAS REPAIRED PER SRM 53-04, FIG 12B, CLASS 1 WITH AN ADJUSTED DOUBLER SHAPE.

Part: LIGHT LENS — LIGHTNING STRIKE (RT WING)

AIRCRAFT INCURRED LIGHTNING STRIKE ON APPROACH AND SMOKE WAS SMELLED IN CABIN AND COCKPIT. THE SMOKE OCCURED 5 TO 8 MIN AFTER STRIKE AND DISSIPATED AFTER 10 MIN. INSPECTED AIRCRAFT PER M/M 05-53-00 PG 601. FOUND RT AFT TAIL LIGHT LENS SHATTERED AND NO OTHER DAMAGE NOTED. REPLACED LENS, RAN PACKS AND NO ODORS OR SMOKE.

Part: SKIN — CRACKED (LT NLG DOOR)

FUSELAGE SKIN CRACKED LT NLG DOOR AFT HINGE CUTOUT. FOUND DURING C-2 LTR CK TPAMM. REPAIRED PER SRM 53-05 FIG 62.

Part: ANGLE — CRACKED (RT WW)

MLG W/W AFT O/B STRIKER ANGLE CRACKED. FOUND AT C-2 LTR CK. REPAIRED PER SRM 53-05 FIG 81A.5.

Part: PAN — CRACKED (C 1 DOOR)

C-1 DOOR AFT PAN CRACKED 1 INCH, FOUND AT C-2 LTR CK. REPAIRED PER SRM 52-05 FIG 26A.