N943DL

Part: BATTERY PACK — INOPERATIVE (EMERGENCY LIGHTS) · airframe 73,549 hrs · 54,767 cycles

EMERGENCY LIGHTS INOPERATIVE AT THE AFT OVERWING EXITS. TROUBLESHOT IAW WDM 33-51-13. REMOVED AND REPLACED THE BATTERY PACKS. OPS CHECKED GOOD.

Part: SKIN — CRACKED (FUSELAGE) · airframe 73,541 hrs · 54,761 cycles

CRACKED SKIN, STRINGER 15L.

Part: SKIN — CRACKED (BELLY) · airframe 73,521 hrs · 54,745 cycles

WORKING PRI 557381-14AD, THE LOWER AFT SKIN FOUND CRACKED. REPAIRED IAW ERA 557381-14AD.

Part: BATTERY PACK — INOPERATIVE (EMERGENCY LIGHTS) · airframe 73,388 hrs · 54,622 cycles

OVERHEAD EMERGENCY LIGHTS INOPERATIVE ABOVE FIRST CLASS AND ECONOMY. REPLACED THE BATTERIES ABOVE ROWS 4 AND 12 IAW AMM 33-53, CHECKED GOOD.

Part: BATTERY PACK — DISLODGED (EMERGENCY LIGHT) · airframe 71,502 hrs · 53,198 cycles

EMERGENCY LIGHTS AT ROWS 10-14 INOPERATIVE. FOUND BATTERIES DISLOGED FROM POWER PACK. REINSTALLED PER AMM 33-53. CHECKED OK.

Part: WIRE — PULLED (EMERGENCY LIGHT) · airframe 71,502 hrs · 53,198 cycles

EMERGENCY LIGHT INOPERATIVE AT SEAT 24R. FOUND BOTH WIRES PULLED WITH MOLEX PLUX MISSING. INSTALLED PINS, SOCKETS. AND RECEPTICALS PER SWPM CH20. CHECKED OK.

Part: INLET — CONTAMINATED (APU) · airframe 71,192 hrs · 52,966 cycles

SHIP 943 EXPERIENCED FUMES AND WHITE SMOKE BOTH IN CABIN AND COCKPIT SHORTLY AFTER LIFTOFF. EMERGENCY DECLARED AND RETURNED TO DEPARTURE. FOUND APU INLET CONTAMINATED WITH APU ENGINE OIL. APU REPLACED. ENGINE BLEED DUCTS BORESCOPED WITH NO OIL FOUND. LT AND RT PACKS INSPECTED WITH NO OIL RESIDUE FOUND. AIRCRAFT RETURNED TO SERVICE.

Part: DOUBLER — CRACKED (FUSELAGE) · airframe 70,922 hrs · 52,751 cycles

TAIL INTERIOR, SKIN SPLICE DOUBLER HAS 1/2" LONG CRACK AT BS 1429.5, 11" LT OF CTR, IN CROWN AREA. REPAIRED PER FINAL ERA 550970-14 REV ORIGINAL.

Part: SKIN — CRACKED (FUSELAGE) · airframe 70,922 hrs · 52,751 cycles

DURING OPEN HOLE INSPECTION OF PRI 550970-14 STEP 5, HAD CRACK INDICATION AT ONE HOLE UNDER THE EXTERNAL SKATE IN FUSELAGE SKIN. REPAIRED PER FINAL ERA 550970-14 REV ORIGINAL.

Part: STRUCTURE — CRACKED (FUSELAGE) · airframe 70,922 hrs · 52,751 cycles

ERA 550970-14 SECTION I ISSUED FOR CRACK DAMAGE AND BUSHING REPAIR AT STA 1429 BETWEEN L2L AND L3L. ACCOMPLISH SECTION II EVERY C CHECK FOLLOWING SECTION I.

Part: RELEASE SYSTEM — WORN (TAILCONE) · airframe 70,922 hrs · 52,751 cycles

TAILCONE RELEASE CAM BASE IS WORN. REMOVED AND INSTALLED TAIL CONE RELEASE CAM BASE REF AMM 53-53-02. TESTED AND ADJUSTED PER AMM 53-53-02.

Part: CABLE — WORN (TAILCONE) · airframe 70,922 hrs · 52,751 cycles

TAILCONE INT CABLE WORN. REPLACED CABLE REF AMM 53-53-00.

Part: SKIN — DENTED (BS 275) · airframe 70,922 hrs · 52,751 cycles

DENT AT FRAME BS 275 , 2" ABOVE LONGERON #9, APROX .5" X .75", .018" BELOW SURFACE SKIN. REPAIRED IAW SRM 53-04-02

Part: SKIN — DENTED (FUSELAGE) · airframe 70,922 hrs · 52,751 cycles

DENT AT STA 416, LONGERON 7, APPROX 1.5" X 1.25", .031" BELOW SKIN. REPAIRED PER ERA 551073-14 REV ORIGINAL.

Part: SKIN — DENTED (FUSELAGE) · airframe 70,922 hrs · 52,751 cycles

DENT AT STA 370, LONGERON NR 8, APPROXIMATELY 1.25" X .375", .017" BELOW SKIN SURFACE. REPAIR IAW ER/A 551073-14, REV ORIG.

Part: SKIN — DENTED (BS 475) · airframe 70,922 hrs · 52,751 cycles

DENT AT BS 475, LONGERON #7, APROX .75" X .- 5", .025" BELOW SKIN SURFACE. REPAIRED PER ERA 551073-14 REV. A.

Part: SKIN — DENTED (BS 416) · airframe 70,922 hrs · 52,751 cycles

DENT AT BS 416, LONGERON 7, APROX 1.5" X 1.25", .031" BELOW SKIN SURFACE. REPAIRED PER ERA 551073-14 REV. ORIGINAL.

Part: SKIN — DENTED (FUSELAGE) · airframe 70,922 hrs · 52,751 cycles

DENT AT STA 475, LONGERON 7, APPROX .75" X .- 5", .025" BELOW SKIN SURFACE. REPAIRED PER ERA 551073-14 REV ORIGINAL.

Part: SKIN — DENTED (FUSELAGE) · airframe 70,922 hrs · 52,751 cycles

DENT AT FRAME STA 294, 3.5" ABOVE LONGERON NR 9, APPROXIMATELY 1.25" X 1.0", .033" BELOW SURFACE SKIN. INSTALLED REPAIR PARTS IAW ERA 551073-14, REV ORIGINAL.

Part: SKIN — DENTED (BS 370) · airframe 70,922 hrs · 52,751 cycles

DENT AT BS 370, LONGERON 8, APROX 1.25' X .375", .017" BELOW SKIN SURFACE. REPAIR PER ER/A 551073-14 REV ORIG.

Part: SKIN — DENTED (BS 570) · airframe 70,922 hrs · 52,751 cycles

DENT AT BS 570, LONGERON 7, APROX 1.25" X .75", .029" BELOW SKIN SURFACE. REPAIRED PER ER/A 551073-14 REV. ORIGINAL.

Part: SKIN — DENTED (FUSELAGE) · airframe 70,922 hrs · 52,751 cycles

DENT AT FRAME STA 275 , 2" ABOVE LONGERON NR 9, APPROXIMATELY .5" X .75", .018" BELOW SURFACE SKIN. REPAIRED IAW SRM 53-04-02 REF ER/A 551073-14, REV ORIGINAL.

Part: SKIN — DENTED (BS 294) · airframe 70,922 hrs · 52,751 cycles

DENT AT FRAME BS 294, 3.5" ABOVE LONGERON #9, APROX 1.25" X 1.0", .033" BELOW SURFACE SKIN. INSTALLED REPAIR PARTS IAW ERA 551073-14 REV ORIGINAL.

Part: SKIN — DENTED (FUSELAGE) · airframe 70,922 hrs · 52,751 cycles

DENT AT STA 570, LONGERON 7, APPROX 1.25" X .75", .029" BELOW SKIN SURFACE. REPAIRED PER ER/A 551073-14 REV ORIGINAL.

Part: SKIN — DENTED (FUSELAGE) · airframe 70,922 hrs · 52,751 cycles

DENT AT STA 601, 3.5" ABOVE LONGERON NR 7, APPROXIMATELY 1.125 X 075", .015 BELOW SKIN SURFACE. REPAIR COMPLETED IAW PRI 551073-14, REV 0, AND ER/A 551073-14, REV ORIGINAL.

Part: SKIN — DENTED (FUSELAGE) · airframe 70,922 hrs · 52,751 cycles

DENT AT STA 416, LONGERON- NR 7, APROX 1.5" X 1.25", .031" BELOW SKIN SURFACE. REPAIRED IAW PRI 551073-14, REV 0 AND ERA 551073-14, REV ORIGINAL.

Part: SKIN — DENTED (FUSELAGE) · airframe 70,922 hrs · 52,751 cycles

DENT AT STA 662, LONGERON NR 6, APPROXIMATELY 1.5" X 1.25", .018 BELOW SKIN SURFACE. REPAIRED IAW PRI 551073-14, REV 0 AND ERA 551073-14, REV ORIGINAL.

Part: SKIN — DENTED (FUSELAGE) · airframe 70,922 hrs · 52,751 cycles

DENT AT STA 570, LONGERON NR 7, APPROXIMATELY 1.25" X .75", .029" BELOW SKIN SURFACE. REPAIR IAW PRI 551073-14, REV 0 AND ERA 551073-14, REV ORIGINAL.

Part: SKIN — DENTED (FUSELAGE) · airframe 70,922 hrs · 52,751 cycles

DENT AT STA 475, LONGERON NR 7, APPROXIMATELY .75" X .-5", .025" BELOW SKIN SURFACE. REPAIRED IAW PRI 551073-14 REV 0 AND ERA 551073-14, REV ORIGINAL.

Part: SKIN — DENTED (FUSELAGE) · airframe 70,922 hrs · 52,751 cycles

DENT AT FRAME STA 636, 1.75" BELOW LONGERON NR 6, APPROXIMATELY 1.0" X 1.125", .019 BELOW SKIN SURFACE. REPAIRED IAW PRI 551073-14 REV 0 AND ERA 551073-14, REV ORIGINAL.

Part: FRAME — CRACKED (FUSELAGE) · airframe 70,922 hrs · 52,751 cycles

DURING OPPORTUNITY INSPECTION, FOUND FRAME CRACKED AT STA 1437, L1. REPAIRED FRAME BY DAMAGE CUTOUT AND INSTALLING REPAIR ANGLE IAW PRI 551051-14, REV 0 AND REV 1.

Part: FRAME — CRACKED (FUSELAGE) · airframe 70,922 hrs · 52,751 cycles

TAIL INTERIOR, CANTED FRAME RT WEB INBD EDGE HAS 1" CRACK AT OVERHEAD HORIZONTAL STIFFENER, CBS 1485. NR FOR ADDITIONAL INFORMATION 001-0392:5300-2551/027, 00161 CMOR; REPAIRED. REF; SRM 53-03, FIG 49.

Part: FRAME — DAMAGED (FUSELAGE) · airframe 70,922 hrs · 52,751 cycles

ER/A 551051-14 ISSUED TO ACCOMPLISH REPAIR TO FS 1451. FOLLOW ON ACTION IS REQUIRED. ACCOMPLISH SECTION II REPEAT INSPECTIONS EVERY 3,000 FLIGHT CYCLES FOLLOWING ACCOMPLISHMENT OF SECTION I IAW SRM 51-00-10, TABLE 2, THE DAMAGED FRAME IS NOT FCBS, THEREFORE, NO REPEAT INSPECTIONS ARE REQUIRED.

Part: FRAME — CRACKED (FUSELAGE) · airframe 70,922 hrs · 52,751 cycles

TAIL INTERIOR, CANTED FRAME LT WEB INBD EDGE HAS 3" CRACK AT OVERHEAD HORIZONTAL STIFFENER, CBS 1485. REPAIRED IAW SRM 53-03, FIG 48.

Part: BEAM — CORRODED · corrosion level 2 · airframe 70,922 hrs · 52,751 cycles

MID CARGO BAY DOOR OPENING LOWER EDGE LONGERON 28R BEAM OUTER SURFACE VERTICAL LEG HAS SURFACE CORROSION AROUND FASTENER HOLES. REPAIRED IAW SRM 53-05 FIG 123.

Part: WIRE — SHORTED (RUDDER) · airframe 69,236 hrs · 51,549 cycles

FLIGHT RETURNED TO DEPARTURE DUE TO SEVERAL LARGE UNCOMMANDED YAW - RUDDER INPUTS REPORTED WHILE CLIMBING THROUGH 16K FT. THE AUTOPILOT DISENGAGED AND THE DFGC SYSTEM CIRCUIT BREAKER C18 OPENED AND WOULD NOT RESET. BOTH MCP AND AUTOTHROTTLE FUNCTIONS WERE LOST. SPURIOUS YAW INPUTS CONTINUED UNTIL THE YAW DAMP SWITCH WAS TURNED OFF AND THEN THE UNCOMMANDED YAW INPUTS CEASED. T/S IAW WDM AND INSPECTED RUDDER POSITION CIRCUIT. FOUND WIRE 20610X22RD WAS SHORTED TO ACFT GROUND. WAS ABLE TO DUPLICATE PILOT WRITE-UP. REPAIRED WIRE IAW SWPM CH 20. RAN RTS CHECKED GO. THE ACFT HAS RETURNED TO SERVICE.

Part: SUPPORT FITTING — SHEARED (TAILCONE) · airframe 69,180 hrs · 51,517 cycles

MAINTENANCE FOUND TAILCONE UPPER LATCH SUPPORT FITTING SHEARED OFF. THE TAILCONE WAS REPLACED.

Part: FRAME — CRACKED (TAILCONE) · airframe 69,180 hrs · 51,517 cycles

TAILCONE FRAME CRACKED AT RT UPPER LATCH FITTING. REPLACED TAIL CONE ASSY., INSTALLATION & OPS CHECKS GOOD, AMDS CARD 2561-4001.

Part: LAP JOINT — CORRODED (BS 588) · corrosion level 2 · airframe 69,165 hrs · 51,510 cycles

REMOVED MID CARGO BIN PANEL FOUND CORROSION AT LAP SPLICE BS 588, STR 26L. DAMAGE CONFINED TO FINGER DOUBLER ONLY. CW REPAIR INSTRUCTIONS 542580-14.

Part: BATTERY PACK — INOPERATIVE (EMERGENCY LIGHTS) · airframe 68,578 hrs · 51,063 cycles

DURING LINE CHECK, MAINTENANCE FOUND THAT THE EMERGENCY LIGHTING IN THE CABIN WAS INOPERATIVE. MAINTENANCE REPLACED THE BATTERIES AT 5DE AND 35DE. OPS CHECK WAS GOOD.

Part: LIGHT — INOPERATIVE (SEAT 24D) · airframe 66,191 hrs · 49,428 cycles

DURING LINE CHECK, MAINTENANCE FOUND THAT THE EMERGENCY LIGHT AT SEAT 24D WAS DAMAGED. MAINTENANCE REPLACED THE LIGHT ASSEMBLY AND PERFORMED A SATISFACTORY FUNCTIONAL CHECK.

Part: WIRE HARNESS — DAMAGED (EMERGENCY LIGHT) · airframe 65,891 hrs · 49,178 cycles

DURING LINE CHECK, MAINTENANCE FOUND THAT THE EMERGENCY LIGHT AT SEAT 11DE WAS INOPERATIVE. MAINTENANCE REPLACED THE WIRE HARNESS AND THE SYSTEM RETURNED TO NORMAL OPERATION.

Part: BEARING — FAILED (NR 1 ENGINE) · airframe 64,989 hrs · 48,478 cycles

FLIGHT CREW EXECUTED AN AIR RETURN, FOLLOWING THE NR 1 ENGINE "OIL STRAINER CLOG" WARNING LIGHT ILLUMINATING. SEQUENCE OF EVENTS INCLUDE THE CLOG MESSAGE AT 1000 FT, COMPLYING WITH THE QRH AND THE MESSAGE REMAINING AT IDLE, SO THE CREW THEN INITIATED THE RETURN AND DECLARED AN EMERGENCY. MAINTENANCE FOUND METAL ON CHIP DETECTOR AND IN OIL FILTER. LAB RESULTS SHOW METAL COMING FROM THE MAIN BEARING AREAS. ENGINE HAS BEEN REPLACED.

Part: BRACKET — DAMAGED (MLG) · airframe 64,272 hrs · 47,994 cycles

CREW DECLARED AN EMERGENCY DUE TO GEAR DOOR OPEN LIGHT REMAINING ILLUMINATED AFTER GEAR EXTENSION. EXECUTED A GO-AROUND AND PERFORMED ALTERNATE GEAR EXTEND PROCEDURES IAW THE QRH. FOUND A MISSING BOLT, ECCENTRIC, AND SHEARED BRACKET THAT HOLDS THE TARGET. ALL MISSING, OR DAMAGED, REPLACED AND THE GEAR OPERATION CHECKED GOOD.

Part: WIRE — DAMAGED (EMERGENCY LIGHT) · airframe 63,712 hrs · 47,596 cycles

SEAT MOUNTED ESCAPE PATH LIGHT INOP AT 34D. REPAIRED WIRE IAW 20 AND SYS OPS CHECKS OK; OK FOR SERVICE.

Part: COVER — DAMAGED (SLAT TRACK) · airframe 62,256 hrs · 46,509 cycles

LOWER L/E SLAT TRACK COVERS FOR TRACKS 4, 12, 9 ,14, 13 & 15, HAS SHAVED EDGES AS NOTED. LW-L/E-TRKS-4,12,9,14,13 & 15. BLENDED OUT DAMAGED AREAS ON 6EA TRACK COVERS 4,9,13,14 AND 15 FOUND WITHIN LIMITS AND 12 TRACK COVER FOUND OUT OF LIMITS. TRACK 12 COVER FABRICATED AND INSTALLED IAW SRM 57-01, SRM 55-10-3, SRM 51-30-2 AND EA 57-06BD.

Part: FRAME — CRACKED (FUSELAGE) · airframe 62,256 hrs · 46,509 cycles

AFT VAULT DOOR FRAME HAS CRACK PROPAGATING BEYOND STOP DRILL. CRACK IS 0.5 IN LONG LOCATED ON UPPER RT CORNER, 5 IN RT OF CENTER LINE. REPLACED UPPER FRAME AT AFT VAULT DOOR IAW SRM 51-30-2 AND 51-30-5.

Part: SKIN — CRACKED (BS 1418) · airframe 62,256 hrs · 46,509 cycles

FOUND ON VERTICAL STABILIZER THROUGH ACCESS PANEL 6310B RT SIDE BS 1418, BETWEEN BL0 AND STRINGER 1R-2R; SKIN CRACKED. ACCOMPLISHED REPAIR AT FUSELAGE SKIN BS 1418 BETWEEN LONGERON 2L & L2R IAW ER/A 501344-14 REV "O" FINAL & SRM 53-04, FIG 40, SHEET 2.

Part: BULKHEAD — CRACKED (FUSLEAGE) · airframe 62,256 hrs · 46,509 cycles

FUSE FWD BULKHEAD WEB CRACKED. ( . 776 " ) BS 37, BL. 29 LH. WITH CUSP LINE, DOT 045. CUT OUT DAMAGE AREA, DIMENSION: 2.1250" X 1.0" AT FUS BULKHEAD STA 37, LBL 29. REMOVED, FABRICATED, AND INSTALLED REPAIR PARTS: REPLACEMENT SPLICE/ REPAIR & FILLER, IAW ER/A:483847-14 MA REV "O", FIG 1. IDENTIFIED REPAIR IAW PS 900-5-1-N 4. AT FUS FWD BULKHEAD WEB ANGLE STA 37, LBL 29 WITH CUSP LINE. PERFORMED HFEC IAW BNDT SPM 06-10-01-001, HEAT TREATED SPLICE REPAIR PS 900-4-2. TREATED, PRIMED & TOP COATED IAW SRM 51-10-3. JOB COMPLETED. ASSOCIATED ER/A 00-483847 ADDED FOR AC 0943.

Part: SKIN — CORRODED (BS 1041-1136) · airframe 62,256 hrs · 46,509 cycles

FUSELAGE LT SIDE WING TO BODY FAIRING RUB STRIPS FROM STA 1041 TO STA 1136 UPPER AND LOWER ARE DISBONDING IN SEVERAL AREAS WITH MANY DRILLED OUT FASTENERS AND CORROSION AROUND FASTENER HOLES. REMOVED RUB STRIPS, DRILLED OUT FASTENERS, AND CORROSION AT SKIN UPPER AND LOWER UNDER RUB STRIP FROM STA 1041 TO 1136 IAW SRM 51-10-3. ORIG MAT UPPER SKIN REMAINED WITHIN LIMITS. LWR SKIN MATERIAL REMOVED 38 PERCENT, FOUND OUT OF LIMITS. REWORKED DIM 4" X 3" IAW SRM 53-04-1, REPAIRED AND IDENTIFIED SKIN AT STA 1117, LONG 27L IAW DWG 5609530014, REV:A AND IAW DELTA P 900-500-1N-4. JOB COMPLETED.

Part: STRUCTURE — CORRODED (FUSELAGE) · airframe 62,256 hrs · 46,509 cycles

BS 1401 TO CANTED FRAME 1463, INNER SKIN AND SOME ANGLES WITH CORROSION AND SEVERAL AREAS WITH BARE METAL BETWEEN BL 17, 5 AND BL 28 LT, REMOVED CORROSION ON ANGLE AT BS 1429, BL 17 AND REPLACED INTERCOSTAL FROM BS 1401-1429, BL 17.5 TREATED AND PRIMED AND TOP COATED BARE METAL ON SKIN AND ANGLE BETWEEN BL 117.5 AND BL 28L FROM BS 1401 TO CANTED FROM BS 1463 IAW SRM 51-30-2, 51-30-1, 53-14-4, 53-01, 51-30-1.

Part: DOUBLER — CORRODED (BS 594) · airframe 62,256 hrs · 46,509 cycles

MID CARGO BILGE STA 594 BETWEEN LONG 30 AND LONG 29R DOUBLER HAS CORROSION SPOTS BETWEEN DOME NUTS. REMOVED CORROSION AT MID CARGO BILGE STA 594 BETWEEN NG L30-29R DOUBLER AROUND AND BETWEEN DOME NUTS ORIG MAT OF DOUBLER .063 MAT REMOVED .033 REMAINING MAT .030 REWORKED AREA SIZE 1.0X4.0. FOUND OUT OF LIMITS IAW SRM 51-10-3, 53-001 FIG 1. FABRICATED AND REPLACED DOUBLER PN 5936434-35 AT MID CARGO BILGE STA 594 BETWEEN LONG 30-29R SRM 51-30-2, PG 1.

Part: SKIN — CRACKED (NR 3 SLAT) · airframe 62,256 hrs · 46,509 cycles

RT WING NR 3 SLAT HAS 2EA POSSIBLE CRACKS ON LOWER SKIN. VERIFIED 1EA CRACK ONLY AT RT WING NR 3 SLAT 21" FROM OTBD EDGE AND 5.0 FROM T/E CUT OUT DAMAGE ARA SIZE 2.0 X 1.7500 INSTALLED DOUBLER AND FILLER REPAIR IAW SRM 57-09D, FIG 10B. INSTALLED ID TAG FOR REPAIR IAW DELTA PS 900-5-1-NO. 04.

Part: FLOORBEAM — CORRODED (BS 787) · airframe 62,256 hrs · 46,509 cycles

MID CARGO BILGE BS 787, FLOORBEAM ANGLE FROM LONG 28L TO 28R HAS SURFACE CORROSION. CLEANED AREA IAW SRM 51-10-3. REMOVED CORROSION IAW SRM 51-10-3, FOUND CORROSION OUT OF LIMITS REF SRM 53-01, FIG 1. PAGE 8, REPLACED FLOORBEAM IAW SRM 51-30-2.

Part: CHANNEL — CORRODED (BS 218-239) · airframe 62,256 hrs · 46,509 cycles

FWD CARGO BS 218 TO 239, BETWEEN L27 - 28L CORROSION BETWEEN INTERCOASTAL AND U CHANNEL . REMOVED CORRODED AT U CHANNEL, FOUND OUT OF LIMITS, IAW SRM 53-01, FIG.1. REPLACED U CHANNEL IAW SRM 51-30-1.

Part: CUSP WEB — CORRODED (BS 1148) · airframe 62,256 hrs · 46,509 cycles

CABIN FLOOR RT CUSP WEB HAS HEAVY CORROSION SPOT AT FRAME FITTING, FS 1148. REPLACED CABIN FLOOR RT CUSP WEB BS 1098-1174. IAW SRM 51-10-3, SRM 51-30-02,L SRM 51-10-4 AND 51-30-5 AND 51-30-1.

Part: SEAT TRACK — CORRODED (BS 807-826) · airframe 62,256 hrs · 46,509 cycles

SEAT TRACK LBL 55 HAS CORROSION AND WEAR AREAS BS 807-826. BLENDED SEAT TRACK, FOUND OUT OF LIMITS AT STA 826, CUT OUT DAMAGE AREA, PERFORMED SEAT TRACK REPAIR IAW SRM 53-05, FIG 4F SHEETS CONFIGURATION SR09530085-7007.

Part: CUSP WEB — CORRODED (BS 560-579) · airframe 62,256 hrs · 46,509 cycles

RT CUSP WEB HAS HEAVY CORROSION SPOTS FROM FS 560-579 RBL 60". AFTER REMOVED CORROSION AT CABIN FLOOR RT CUSP WEB FROM BS 560 TO 579, RBL.60", FOUND AREA OUT LIMITS AND CRACKED. CUTOUT CORRODED AREA, FABRICATED DOUBLER, FILLER AND RING DOUBLER. INSTALLED FABRICATED PARTS, IAW SRM 51-30-2, 51-10-3, 53-14-2, 51-30-5, 53-05, CONF.7021 PG 908.

Part: CUSP WEB — CORRODED (BS 560-568) · airframe 62,256 hrs · 46,509 cycles

FOUND HEAVY CORROSION AT CABIN OTBD CUSP WEB BETWEEN FS 560-568. APPROX, RBL 60. REMOVED CORROSION IN AREA AND FOUND IT TO BE OUT OF LIMITS. CUT OUT AREA DAMAGE, FABRICATED FILLER, DOUBLER, AND RING DOUBLER AND INSTALLED IAW SRM 51-30-2, 51-30-1, 51-30-5 AND SRM 53-05 FIG. 131A-13 (SHEET 1-5).

Part: CUSP WEB — CRACKED (BS 825) · airframe 62,256 hrs · 46,509 cycles

LEFT CUSP WEB, BS 825 CRACKED. REPAIRED DAMAGED IAW SRM 53-05, CONFIGURATION 7001, FIG 131A-1.

Part: CUSP WEB — CORRODED (BS 427-436) · airframe 62,256 hrs · 46,509 cycles

LEFT CUSP WEB AT BS 427 TO 436 HAS SURFACE CORROSION. REMOVED CORROSION AND FOUND OUT OF LIMITS IAW SRM 51-10-3 AND 53-01. INSTALLED REPAIR IAW SRM 53-05.

Part: WINDOW FRAME — CRACKED (BS 1041-1022) · airframe 62,256 hrs · 46,509 cycles

PASSENGER LT CABIN WINDOW FRAME LOWER FWD CORNER CRACKED BETWEEN STA-1041 AND 1022, REMOVED FASTENERS AND CUTOUT DAMAGED AREA. FABRICATED ANGLE REPAIR, SHIM, & INSTALLED ALL AT PASSENGER LT CABIN WINDOW FRAME LOWER CORNER BETWEEN STA 1041 TO 1022 IAW SRM 51-30-2, SRM 53-05, & SRM 51-10-2A. INSTALLED REPAIR ID ACCOMPLISHED STANDARD 900-5-1 NR 4, PAGE 1, 06-14-07.

Part: LIGHT — INOPERATIVE (CABIN) · airframe 62,121 hrs · 46,404 cycles

DURING LINE CHECK, MX FOUND THAT THE EMERGENCY PATHWAY LIGHTING AT ROW 11DEF IN THE CABIN WAS INOPERATIVE. MX REPLACED THE LIGHT ASSY AND FUNCTIONALLY CHECKED IT.

Part: BATTERY PACK — INOPERATIVE (EMERGENCY LIGHTS) · airframe 61,747 hrs · 46,122 cycles

DURING LINE CHECK, MX FOUND THAT BOTH OF THE OVERWING EMERGENCY EXIT SIGNS AT 24A & 24E WERE INOPERATIVE. MX REPLACED THE BATTERIES. OPS CHECK WAS GOOD.

Part: WIRE — BROKEN (EMERGENCY LIGHTS) · airframe 61,706 hrs · 46,084 cycles

DURING LINE CHECK, MX FOUND THAT THE EMERGENCY PATHWAY LIGHTING AT ROW 13DF IN THE CABIN WAS INOPERATIVE. MX FOUND A BROKEN WIRE AND RE-ATTACHED IT. THE SYSTEM RETURNED TO NORMAL OPERATION.

Part: BATTERY PACK — INOPERATIVE (EMERGENCY LIGHTS) · airframe 61,542 hrs · 45,961 cycles

DURING LINE CHECK, MX FOUND THAT THE EMERGENCY PATHWAY LIGHTING IN ROWS 4-13 OF THE CABIN WERE INOPERATIVE. MX REPLACED THE BATTERIES. OPS CHECKED GOOD.

Part: TRACK — CORRODED (FUSELAGE) · airframe 59,757 hrs · 44,751 cycles

FWD ENTRY AREA CORROSION STA 160 LBL 7. REMOVED CORROSION ON TRACK AND FOUND TO BE OUT OF LIMITS PER MD88 SRM 53-05 PG 24. REPLACED TRACK AT STA 160 LBL 7 IAW MD88 SRM 51-30-1.

Part: TRACK — CORRODED (FUSELAGE) · airframe 59,757 hrs · 44,751 cycles

FWD ENTRY DOOR AREA TRACK CORROSION STA 225 LBL 5. REMOVED CORROSION AND FOUND TO BE OUT OF LIMITS PER MD80 SRM 53-04. FABRICATED TRACK PER MD80 SRM 53-14-2 AND INSTALLED PER TRACK AT STA 225 LBL 5 IAW MD80 SRM 51-30-05.

Part: CONNECTOR — LOOSE (CABIN) · airframe 59,030 hrs · 44,252 cycles

DURING LINE CHECK MAINTENANCE FOUND AFT STAIRWAY FORWARD EMERGENCY LIGHT INOPERATIVE ON LEFT SIDE. MAINTENANCE SECURED LOOSE CONNECTOR AT LIGHT. OPERATION OF LIGHT NOW CHECKS OK.

Part: PANEL — DAMAGED (VERTICAL STAB) · airframe 58,625 hrs · 43,962 cycles

VERTICAL STABILIZER LEADING EDGE PANEL FASTENER HOLES WERE FOUND DAMAGED AND REPAIRED PER DC9/MD-80 SRM 53-03D FIG 30.

Part: LIGHT — INOPERATIVE (SEAT 31) · airframe 57,216 hrs · 43,052 cycles

DURING LINE CHECK MX FOUND EMERGENCY PATH LIGHTS BEHIND SEAT 31 INOPERATIVE MX TROUBLESHOT AND FOUND FAULTY EJECT HANDLE IDENTIFIER LIGHT. LIGHT WAS REPLACED AND NOW OPS OF LIGHTS CHECKS OK.

Part: LIGHT — INOPERATIVE (CABIN) · airframe 55,952 hrs · 42,201 cycles

MAINTENANCE FOUND THE EMERGENCY LIGHT AT SEAT 2D TO BE INOPERATIVE. MAINTENANCE REPLACED THE LIGHT ASSEMBLY. AN OPS CHECK WAS PERFORMED AND THE AIRCRAFT WAS RETURNED TO SERVICE.

Part: POWER SUPPLY — INOPERATIVE (EMERGENCY LIGHTS) · airframe 55,446 hrs · 41,874 cycles

MX FOUND THE EMERGENCY LIGHTS FROM THE AFT GALLEY AND AFT TO BE INOPERATIVE. MX REPLACED THE AFT POWER SUPPLY. AN OPS CHECK WAS PERFORMED AND THE ACFT WAS RETURNED TO SERVICE.

Part: DOWNLOCK SENSOR — MALFUNCTIONED (RT MLG) · airframe 52,206 hrs · 39,786 cycles

RIGHT MAIN GEAR UNSAFE LIGHT ALONG WITH LANDING GEAR AURAL WARNING. REPLACED RT DOWNLOCK PROX SENSOR-CONDUIT AND CONNECTOR PROX TEST NOW GOOD.

Part: SKIN — DAMAGED (FS 245) · airframe 48,017 hrs · 37,123 cycles

FUSELAGE SKIN DAMAGED AND UNDERLYING STRUCTURE MISDRILLED. SKIN CUT OUT AND DAMAGED HOLES OVERSIZED AND BUSHED. DAMAGE AT FS 229-250 ABOVE L-18L.

Part: TEE FITTING — WORN (FUSELAGE) · airframe 47,600 hrs · 36,852 cycles

AFT PRESSURE BULKHEAD TEE LOWER PORTION REPAIR AT STA 1338, LONGERON 28L-28R - WEAR. A PORTION OF THE LOWER PART OF BULKHEAD TEE WAS SECTIONED AND NEW SECTION INSTALLED PER EA 09-086680-12 REV E.

Part: FRAME — CORRODED (FUSELAGE) · airframe 47,600 hrs · 36,852 cycles

CORROSION ON FRAME AT STA 1380 BETWEEN LONGERON 28R-28L. CORROSION REMOVED AND NEW FRAME INSTALLED PER SRM 51-10-23 AND 51-10-30.

Part: BUSHING — CORRODED (VERTICAL STAB) · airframe 47,600 hrs · 36,852 cycles

CORROSION ON BUSHINGS OF VERTICAL STAB PIVOT POINT OUTBOARD AND INBOARD SIDE. NEW BUSHINGS FABRICATED AND INSTALLED PER SRM 55-02D PARA 24A (A), (B) AND (C).

Part: SKIN — MISREPAIRED (FUSELAGE) · airframe 47,591 hrs · 36,848 cycles

FUSELAGE SKIN REPAIR AT STA 1322 BETWEEN LONGERONS 25R TO 26R - NONAPPROVED PERMANENT REPAIR. PERMANENT REPAIR PERFORMED IAW AM REPAIR DRAWING NR AMR0953591 REV01 AND ERA 460142-14.

Part: SKIN — CRACKED (FUSELAGE) · airframe 47,591 hrs · 36,848 cycles

FUSELAGE SKIN REPAIR AT STA 1437 BETWEEN LONGERONS 1L-4L - SKIN CRACKED. PERMANENT REPAIR INSTALLED IAW AM REPAIR DRAWING NR AMR0953592 R01 AND ERA 460141-14.

Part: DOOR FRAME — CORRODED (FUSELAGE) · airframe 47,591 hrs · 36,848 cycles

STRUCTURAL REPAIR AT THE FWD CARGO DOOR JAMB - EXFOLIATION CORROSION. CORROSION REMOVED, PERMANENT REPAIR INSTALLED PER SRM 53-05D, FIG 804D.

Part: SKIN — CRACKED (FUSELAGE) · airframe 47,591 hrs · 36,848 cycles

FUSELAGE SKIN REPAIR AT ST 1437 BETWEEN LONGERONS 3R-4R - SKIN CRACKED. PERMANENT REPAIR INSTALLED PER SRM 53-04D, FIG 27.

Part: SKIN — CRACKED (FS 1437) · airframe 47,586 hrs · 36,845 cycles

DURING CURRENT VISIT, TWO CRACKS WERE REPORTED IN THE FUSELAGE SKIN AT FS 1437, BETWEEN L1 AND L-4L. THE CRACKS WERE 0.5" IN LENGTH. THE DAMAGE WAS CUTOUT AND A BOEING APPROVED REPAIRED INSTALLED PER 460141-14

Part: SKIN — MISREPAIRED (FS 1322) · airframe 47,586 hrs · 36,845 cycles

DURING THE CURRENT VISIT, AN UNIDENTIFIED REPAIR WAS REPORTED ON THE FUSELAGE SKIN AT FS 1322 BETWEEN L25R AND L26R. A BOEING APPROVED REPAIR WAS INSTALLED PER 460142-14.

Part: WIRE — BROKEN (CABIN) · airframe 45,784 hrs · 35,672 cycles

EMERGENCY PATH LIGHT INOP AT AISLE SEAT 15E. REPAIRED BROKEN WIRE.

Part: ENGINE — BIRD INGESTION (NR 1) · airframe 41,394 hrs · 32,500 cycles

ACRID SMELL IN COCKPIT AND CABIN SHORTLY AFTER TAKEOFF IN DCA. SMELL WORSENED ACCORDING TO FLT ATTENDANTS. DIVERTED TO IAD. FLT CREW DISCOVERED BIRD REMAINS ON STATOR BLADES OF LEFT ENGINE INTAKE ABOUT 6 ABOVE BULLET NOSE. NO APPARENT DAMAGE TO FN BLADES. SMELL HAD BEGUN TO DISSIPATE DURING DESCENT. PERFORMED BIRD STRIKE INSP. 05-51-08 NO DEFECTS NOTED. CLEAN STATOR VANE AND INSPECTED ENG, RAN ENGINE AND A/C PACKS, NO ODORS OR SMELLS PRESENT, ENGINE RUN NORMAL.

Part: GENERATOR — FAILED (NR 2 ENGINE) · airframe 40,636 hrs · 31,950 cycles

ABORTED TAKEOFF AT 85 KNOTS DUE TO RIGHT GENERATOR FAIL. FOUND RT GEN GCU LOOSE IN RACK. RESECURED AND RAN ENGINE GEN, STILL WOULD NOT COME ON LINE AND CAUSED X-TIE LOCKOUT. SWAPPED APU AND RIGHT GEN GCUS PER MM 24-20-07-401. RIGHT GEN STILL INOP ON RUN. X-TIE MSG RESET AFTER RIGHT CSD DISCONNECTED. APU GEN POWERS RIGHT BUS OK. X-TIE SYS CHECKED OK PER MM 24-20-00-201 TEST H.

Part: SKIN — CRACKED (FUSELAGE) · airframe 37,787 hrs · 29,943 cycles

THE AFTERBODY FUSELAGE SKIN WAS FOUN WITH A CRACK AT FS 1418 JUST INBD OF THE VERTICAL STABILIZER TO FUSELAGE ATTACH ANGLE AT LONGERON 1R. THE CRACK WAS REMOVED WITH A 2.5 X 1 INCH CUTOUT AND REPAIRED WITH A TITANIUM REPAIR DOUBLER PER ER/A 384848-14, REV A.

Part: ENGINE — FAILED (NR 2) · airframe 36,452 hrs · 29,008 cycles

NR 2 ENGINE SHUTDOWN IN FLIGHT. RT OIL PRESSURE ZERO. AMBER LIGHT, QUANTITY, AND TEMP OK. GOT COMPRESSOR STALL, EGTTO 800. S/D ENGINE AND RETURNED TO CVG. RT OIL PERSSURE NEVER GOT OFF ZERO. REMOVED AND REPLACED NR 2 ENGINE. CHECKS GOOD PER PFHB

Part: ENGINE — MAKING METAL (NR 1) · airframe 33,740 hrs · 27,052 cycles

LEFT ENG OIL STRAINER CLOG MSG IN FLIGHT PROCEEDED BY VIBRATION IN AIRCRAFT. SHUTDOWN ENGINE PER POM. ALL ENGINE INDICATIONS WERE NORMAL FOR CLIMB POWER. FOUND METAL IN ENG OIL FILTER. REPLACED ENGINE.

Part: ENGINE — FAILED (NR 1) · airframe 33,740 hrs · 27,052 cycles

AT 10 - 15 MIN AFTER T/O AT 14,000 FT HAD AN AIRFRAME VIB. CLIMBED TO 20,000 FT AND THE OIL CLOG LIGHT CAME ON WITH HARD KNOCKING ON THE FLOORBOARD OF COCKPIT. PULLED POWER BACK BUT CLOG LIGHT STAYED ON. SHUTDOWN THE ENG, HAD POSITIVE OIL PRESSURE THROUGHOUT WINDMILL PROCESS. REPLACED ENGINE.

Part: FRAME — CRACKED (CABIN) · airframe 33,396 hrs · 26,802 cycles

CRACKS WERE FOUND IN THE FS 1446 FRAME ON BOTH THE LEFT AND RIGHT SIDES SIMILIAR TO THOSE NOTED IN S/B 53-227. THE FRAME WAS REPLACED. THE DAMAGE WAS NOTED PER INSPECTION AT HMV.

Part: HANDLE — FAILED (FLAP/SLAT) · airframe 32,236 hrs · 25,955 cycles

STALL INDICATION LIGHT ON OAP DURING CLIMBOUT. INFLIGHT RTN BOTH SYSTEMS TESTED PER POM. REPLACED FLAP HANDLE SWITCH

Part: BALLAST — INOPERATIVE (CABIN) · airframe 31,190 hrs · 25,156 cycles

FAINT ELECTRICAL ODOR IN REAR CABIN. FOUND 2 CEILING LIGHTS IN AREA OF SMELL INOP RT SIDE. SUSPECT BALLAST UNIT CAUSING SMELL. PULLED C/B ON RT SIDE CABIN OVERHEAD LIGHTS. NO FURTHER SMELL NOTED. REPLACED BALLAST.

Part: SKIN — DENTED (FS 237)

THE FUSELAGE SKIN IS DENTED AFT OF FS 237, 5 INCHES ABOVE THE L-18L CUSP. THE DENT IS APPROXIMATELY .125 INCH BY 3 INCH BY 2.5 INCH. A TIME LIMITED REPAIR WAS ORIGINALLY INSTALLED. THIS REVISION PROVIDES PERMANENT REPAIR INSTRUCTIONS TO THE REPAIR PER DL ERA 272073 REV B.

Part: SKIN — GOUGED (FS 636)

THE FUSELAGE SKIN WAS FOUND WITH EDGE DAMAGE FWD OF THE C2 DOOR. THE DAMAGE WAS TO THE OUTER SKIN ONLY AND AFTER CLEANUP MEASURED APPROX 2 INCH BY 5 INCH. THE PERMANENT REPAIR WILL BE ACCOMPLISHED PER MD88 SRM 53-05 FIG 80 CONFIG 7003.

Part: SKIN — CORRODED (FS 779-807)

CORROSION WAS FOUND UNDERNEATH THE FAIRING RUB STRIP BETWEEN FS 779 AND 807. THE CORROSION WAS REMOVED AND BLENDED OUT WITH THE MAXIMUM DEPTH OF DAMAGE .130 OCCURRING AT FS 807. REPAIRED PER DL ERA 273091 RC.

Part: STRINGER — CRACKED (BS 1425)

STRINGER L-2 CRACKED AT STA 1425. FOUND AT LETTER CHECK, REPAIRED PER SRM 53-02.