N911DE

Part: CONNECTOR — DISCONNECTED (EMERGENCY LIGHTS) · airframe 64,724 hrs · 50,762 cycles

FOUND EMERGENCY LIGHTS OUT ON SEAT 35 DE AND 25 DE. RECONNECTED THE QUICK DISCONNECTS ON THE EMERGENCY LIGHTS FOR SEATS 25 AND 35 DE. OPS CHECK GOOD. (LP4893432)

Part: CABLE — TORN (TAILCONE) · airframe 64,591 hrs · 50,640 cycles

AWR IN REFERENCE AMDS 5350-4287 STEP 4 TORN ON TAILCONE KEVLAR CABLE WAS FOUND. KEVLAR CABLE WAS REPLACED PER MD-88 AMM 20-30-01 AND MD-88 AMM 20-10-17-201. (LP1012703)

Part: DOUBLER — CORRODED (FUSELAGE) · corrosion level 2 · airframe 64,591 hrs · 50,640 cycles

CORROSION ON PRODUCTION DOUBLER AT AFT LAVATORY PANEL. DUE TO CORROSION OUT OF LIMITS PRODUCTION DOUBLER AT AFT LAVATORY PANEL WAS REPAIRED AS A TIME LIMITED REPAIR PER ETI-88-19-027 REV. 3 AND ER/A 576847-14 REV. ORIG SECTION I. MAINTENANCE REQUIREMENTS WERE VERIFIED AND FOLLOWINGS ACTION ARE NEEDED: ACCOMPLISH SECTION II REPETITIVE INSPECTIONS WITHIN EVERY 3,000 CYCLES AFTER ACCOMPLISHMENT OF SECTION I: TIME-LIMITED REPAIR. ACCOMPLISH SECTION III PERMANENT REPAIR WITHIN 8,000 CYCLES AFTER ACCOMPLISHMENT OF SECTION I: TIME-LIMITED REPAIR. SEE LOG PAGE 1007276. (LP1012136)

Part: SKIN — DAMAGED (FUSELAGE) · airframe 64,591 hrs · 50,640 cycles

INITIAL INSPECTION: CREASE ON FUSELAGE SKIN BTW STA Y=1265 AND Y =1277 BTW LONG 27L AND 28R. FUSELAGE SKIN BTW STA Y=1265 AND Y=1277 BTW LONG 27L AND 28R WAS REPAIRED PER ER/A 576844-14 REV.: ORIG. SEC.: I AND ETI-88-19-030 REV: ORIG. ACCOMPLISH SECTION II REPETITIVE INSPECTIONS WITHIN EVERY 8,000 CYCLES FROM APPROVAL DATE (27-MAR-19) PER ER/A NO. 576844-14 REV. ORIG. SEC. II. FOLLOW UP UNDER LOG 1007252. (LP1008277)

Part: PAINT — DAMAGED (RUDDER TAB) · airframe 64,591 hrs · 50,640 cycles

INITIAL INSPECTION: MISSING AND DAMGE PAINT ON RUDDER CONTROL TAB. TAB WAS REMOVED/INSTALLED PER AMM 27-20-02-401. PAINTED PER P.S. 900-3-6-NO36 AND BALANCED PER SRM 55-40-01. (LP1006583)

Part: SKIN — DENTED (FUSELAGE) · airframe 64,591 hrs · 50,640 cycles

FUSELAGE SKIN STA Y=1250-1287 & L27L TO L28R DENTS & SCRATCHES. ACCOMPLISH ER/A 576844-14 SECTION II INSPECTION WITHIN EVERY 8000 CYCLES AFTER ACCOMPLISHMENT OF THE SECTION I REPAIR. (LP1007252)

Part: SKIN — DAMAGED (FUSELAGE) · airframe 64,591 hrs · 50,640 cycles

FUSELAGE SKIN AFT LAV SERVICE DOOR CUTOUT STA Y=1307-1322, L-22L SKIN & INTERNAL DOUBLER/ CORROSION. ACCOMPLISH ER/A 576847-14 SECTION II INSPECTION WITHIN EVERY 3000 CYCLES UNTIL SECTION III IS ACCOMPLISHED WITHIN 8000, ALL AFTER ACCOMPLISHMENT OF SECTION I. (LP1007276)

Part: COALESCER BAG — DIRTY (AC BAY) · airframe 64,159 hrs · 50,295 cycles

AFTER T/O AND GEAR RETRACTION STRONG SMELL FROM NOSE TIRES NOTICED IN FLT DECK AND MAIN CABIN. C/W ODI SMOKE /ODOR T/S WC 2120-2367 PERFORMED ALTERNATE DUCT BURNOUT PER WC4950-2215 AND COALESCE BAGS REPLACED PER WC2170-4139 COULD NOT DUPLICATE ODOR[428838] REF LOG PAGES 5320990,5320994,5320995 AND 5320996 ALSO C/W FULL BURN CARD. (LP5320992)

Part: WARNING SYSTEM — FALSE ACTIVATION (COCKPIT) · airframe 62,708 hrs · 49,078 cycles

DUE TO EMERGENCY DECLARED BECAUSE OF TOO LOW GEAR AURAL WARNING FOR GEAR WARNING DURING APPROACH. T/S THE EGPWS AND RADIO ALTIMETER SYSTEMS PER AMM 34-45 AND 34-42 RESPECTIVELY. CHECK ALL ANTENNA CONNECTIONS FOR CORROSION AND SECURITY.FINDINGS.

Part: SLIDE — TORN (SERVICE DOOR) · airframe 62,600 hrs · 48,979 cycles

SERVICE DOOR SLIDE NOTED TO BE TORN. REPLACED R1 SLIDE PACK.

Part: DOOR FRAME — DIRTY (AFT PAX DOOR) · airframe 62,421 hrs · 48,835 cycles

FORCE REQUIRED TO OPEN THE DOOR AND DROP THE TAILCONE. AFT PASSENGER DOOR OUT OF LIMITS IAW AMDS 88- 0553-8-0066, AMDS 5350-01077-0101 STEP 7. CLEANED DEBRIS FROM THE DOOR OPENING AND CABLES WERE LUBRICATED. CABLE ASSY RECHECKED, DOOR OPEN FORCE FOUND TO BE WITHIN LIMITS AT 17LBS IAW AMDS 88-0553-8-0066.

Part: BATTERY — DISCHARGED (CABIN) · airframe 61,818 hrs · 48,380 cycles

EMERGENCY CEILING LIGHTS IN TAIL INOP. BATTERIES WOULD NOT HOLD CHARGE. CHANGED 'D' CELL BATTERIES OPERATIONAL CHECK OF TAIL PATH CEILING LIGHTS GOOD IAW AMM 33-50. P/N AD-4002P.

Part: UNKNOWN — ODOR (CABIN) · airframe 60,931 hrs · 47,651 cycles

DIVERTED DUE TO A REPORTED SWEET BURNING ODOR FROM OVERHEAD BINS AT SEAT ROWS 12 TO 20. NO ODOR WAS PRESENT IN THE COCKPIT. MAINTENANCE INSPECTED THE AIRCRAFT INTERIOR, THE OVERHEAD LIGHT BALLAST AND THE AREA ABOVE THE PSUS. THE RECIRCULATION FAN AND THE BAG BINS WERE ALSO INSPECTED. NO ODORS WHERE NOTED. THE NO-GO ODI WC WAS COMPLIED WITH AND THE AIRCRAFT WAS RETURNED TO SERVICE.

Part: WIRE — BROKEN (EMERGENCY LIGHT) · airframe 60,380 hrs · 47,233 cycles

EMERGENCY LIGHTING INOPERATIVE AT 24DE. FOUND WIRE BROKEN ON HARNESS. REPAIRED THE WIRE HARNESS IAW SWPM 20. ALL LIGHTS OPS CHECKED GOOD IAW AMM 33-53.

Part: BATTERY PACK — INOPERATIVE (EMERGENCY LIGHTS) · airframe 60,380 hrs · 47,233 cycles

EMERGENCY CEILING LIGHTS INOPERATIVE BETWEEN ROWS 26 AND 30. REPLACED THE BATTERIES AT ROW 28. OPS CHECKED GOOD IAW AMM 33-53.

Part: WIRE — BROKEN (EMERGENCY LIGHT) · airframe 60,223 hrs · 47,113 cycles

DURING SERVICE CHECK, FOUND AFT CATWALK MIDDLE EMERGENCY LIGHT INOPERATIVE. WIRE BROKEN FROM CONNECTOR. INSTALLED NEW TERMINAL PIN IAW SWPM 20. OPS CHECKED OK. OK FOR SERVICE.

Part: CONNECTOR — BROKEN (EMERGENCY LIGHT) · airframe 60,223 hrs · 47,113 cycles

DURING SERVICE CHECK, FOUND SEAT 22 EMERGENCY LIGHT INOPERATIVE. FOUND CONNECTOR BROKEN. INSTALLED A NEW CONNECTOR IAW SWPM 20. OPS CHECKED OK. OK FOR SERVICE.

Part: COFFEEMAKER — MALFUNCTIONED (GALLEY) · airframe 60,188 hrs · 47,084 cycles

ON ENTERING THE ACFT, A STRONG ELECTRICAL BURNING ODOR. TROUBLESHOT IAW IAW 2120-2367. FOUND F/C FWD NR 1 COFFEEMAKER HEATING WITH SWITCH IN OFF POSITION CREATING A BURNING ODOR. R & R THE COFFEEMAKER AND TESTED IAW AMM 25-36. OPS OK. NO ODOR. OK FOR SERVICE.

Part: RELEASE CABLE — BROKEN (TAILCONE) · airframe 59,922 hrs · 46,897 cycles

AFT ACCESSORIES COMPARTMENT: BROKEN RELEASE TAILCONE CONTROL CABLE WIRES AT 10 HRS POSITION. RELEASE TAILCONE CONTROL CABLE AT 10 HRS POSITION WAS REPLACED AND ADJUSTED PER AMM 20-10-17-201 AND PER AMM 53-53-00-501.

Part: SKIN — CRACKED (EMERGENCY EXIT) · airframe 59,922 hrs · 46,897 cycles

DAMAGE TEE FITTING DURING PERFORMING OF AMDS CARD 5200-2503 STEP 2 (F), ONE CRACK WAS FOUND TO THE LT AFT EMERGENCY EXIT DOOR INNER SKIN. REPAIRED IAW ETI-88-17-075 REV 3 AND ERA 555630-14 REV ORIGINAL.

Part: OUTFLOW VALVE — CRACKED (CABIN PRESSURE) · airframe 59,922 hrs · 46,897 cycles

CRACK ON OUTFLOW VALVE BUTTERFLY. DAMAGED OUTFLOW BUTTERFLY VALVE WAS REMOVED IAW AMM 21-32-05 401.

Part: RIB — CRACKED (SLAT PANEL) · airframe 59,922 hrs · 46,897 cycles

LEFT WING HAD A CRACKED RIB ON SLAT PANEL NR 3 AT XOS 332. THE SLAT PANEL WAS REPLACED, INSTALLED AND ADJUSTED IAW AMM 27-80-01.

Part: FRAME — CRACKED (BS 1485) · airframe 59,922 hrs · 46,897 cycles

AFT ACCESORIES COMPARTMENT HAD A CRACKED FRAME BS 1485. THE FRAME WAS REPAIRED IAW SRM 53-03D, FIG 43.

Part: PAN — CRACKED (EMERGENCY EXIT) · airframe 59,922 hrs · 46,897 cycles

CRACK ON RT EMERGENCY EXIT DOOR FRAME PAN UPPER AREA BS 864 TO 880. DAMAGE AREA WAS REPAIRED IAW ETI-88-17-063 REV 5, ER/A 554155-14 REV. ORIG. AND SRM 53-05 FIG 32.

Part: RIB — CRACKED (LT WING) · airframe 59,922 hrs · 46,897 cycles

LEFT WING RIB CRACKED ON FIXED LEADING EDGE APROX XRS 295. THE RIB WAS REPLACED IAW SRM 51-30-2, 51-30-5.

Part: SHEAR TIE — CRACKED (BS 1380) · airframe 59,922 hrs · 46,897 cycles

AFT ACCESORIES COMPARTMENT HAD A CRACKED SHEAR TIE BS 1380 BETWEEN LONGERONS 17 & 18R. THE SHEAR TIE WAS REPLACED IAW SRM 53-14-4, 51-30-2, AND 51-30-5.

Part: ANGLE — CRACKED (L1 DOOR) · airframe 59,922 hrs · 46,897 cycles

L1 DOOR HAS A CRACKED ANGLE ON FWD INTERCOSTAL BETWEEN BEAMS 4 AND 5. THE ANGLE WAS REPLACED IAW SRM 51-30-2 AND DWG 9955763 REV. M.

Part: ACCESS PANEL — DAMAGED (NOT REPORTED) · airframe 59,922 hrs · 46,897 cycles

ELONGATED HOLES ON FUEL TANK ACCESS PANEL1365C. REPAIRED IAW SRM 51-22-2A PAR. 6.

Part: FLOOR SUPPORT — CORRODED (FUSELAGE) · corrosion level 2 · airframe 59,922 hrs · 46,897 cycles

CORROSION ON FLOOR SUPPORTS BTW STA Y=1145 AND Y= 1222 BTW LONG 28 RT AND 29 RT. DUE TO EXCESSIVE CORROSION UPPER FLOOR SUPPORT WAS REPLACED PER SRM 51-30-1, 51-30-2 AND 51-30-5. CORROSION ON LOWER FLOOR SUPPORT WAS ATTENDED WITH NRC 00976.

Part: FRAME — CRACKED (FUSELAGE) · airframe 59,922 hrs · 46,897 cycles

AFT ACCESSORIES COMPARTMENT, CRACKED FRAME ON STA Y=1485 CANT. DAMAGE AREA WAS REPAIRED PER ETI-88-17-065 REV 1 AND ER/A 555626-14 RE ORIG.

Part: FLOOR SUPPORT — CORRODED (FUSELAGE) · corrosion level 2 · airframe 59,922 hrs · 46,897 cycles

AFT CARGO COMPARTMENT, CORROSION ON FLOOR SUPPORT STA Y= 1117 BTW LONG 28LH AND 28 RT. FLOOR SUPPORT WAS REPLACED PER , SRM.51-30-5. (LP2900754)

Part: CARGO TRACK — CORRODED (CARGO BAY) · corrosion level 2 · airframe 59,922 hrs · 46,897 cycles

CORROSION ON LT TIE DOWN TRACK FROM STA Y=1117 TO STA Y=1122 IN AFT CARGO COMPARTMENT. TIE TRACK WAS REPLACED PER DRAWING 5936660 REV BZ AND SRM 51-30-1, 51-30-2 AND 51-30-5.

Part: FINGER DOUBLER — CORRODED (BS 1231-1271) · corrosion level 2 · airframe 59,922 hrs · 46,897 cycles

AFT CARGO BAY HAS CORROSION ON A FINGER DOUBLER BETWEEN LONGERONS 28L AND 28R, BS 1231 - 1271. THE FINGER DOUBLERS WERE REPLACED IAW SRM 53-04-3, FIG. 12.

Part: DOUBLER — CORRODED (DOOR FRAME) · corrosion level 2 · airframe 59,922 hrs · 46,897 cycles

AFT CARGO BAY CORROSION ON PREVIOUS REPAIR DOUBLER OF LOWER DOOR FRAME BEAM. THE REPAIR WAS REPLACED IAW SRM 53-05, FIG 123, ETI-88-17-048 REV. ORIGINAL AND ERA 554139-14 REV. ORIGINAL.

Part: WEB — CRACKED (BS 1437) · airframe 59,922 hrs · 46,897 cycles

AFT ACCESORIES COMPARTMENT HAS A CRACKED WEB BS 1437, LONGERIN 8 - 9L. THE WEB WAS REPAIRED IAW ETI-88-17-058 REV 1, AND ER/A 554147-14 REV. ORIG.

Part: INTERCOSTAL — CRACKED (RT MLG WW) · airframe 59,922 hrs · 46,897 cycles

RIGHT MLG WHEEL WELL HAS A CRACKED INTERCOSTAL BELOW THE HYD HAND PUMP. THE INTERCOSTAL WAS REPAIRED IAW SRM 53-01, FIG 2.

Part: SKIN — CRACKED (LT WING) · airframe 59,922 hrs · 46,897 cycles

LEFT WING CRACKED ON LOWER SKIN BUTE DOOR, XCW 104. THE BUTE DOOR WAS REPAIRED IAW SRM 51-70-4, FIG 1, 51-30-2 AND 51-30-1.

Part: FLOOR PANEL — CORRODED (COCKPIT) · corrosion level 2 · airframe 59,922 hrs · 46,897 cycles

METALLIC FLOOR PANEL UNDER FIRST OFICCER SEAT CORRODED. A NEW FLOOR PANEL WAS DRILLED IAW SRM 51-10-4 AND A NEW FLOOR PANEL WAS INSTALLED.

Part: ACCESS PANEL — CORRODED (NOT REPORTED) · corrosion level 2 · airframe 59,922 hrs · 46,897 cycles

CORROSION ON FUEL TANK ACCESS PANELS 1410C AND 1303C. THE ACCESS PANELS WERE REPLACED.

Part: ACCESS PANEL — CORRODED (RT WING) · corrosion level 2 · airframe 59,922 hrs · 46,897 cycles

CORROSION ON FUEL TANK ACCESS NR 1414C RT. FUEL TANK ACCESS NR 1414C WAS REPLACED PER SRM 51-22-2A PAR 6.

Part: WEB — CRACKED (BS 1463) · airframe 59,922 hrs · 46,897 cycles

CRACKED WEB BS 1463, LONGERONS 7 - 8L. THE WEB SECTION WAS REPLACED IAW SRM 53-14-4 FIG 3, AND 51-30-5.

Part: WEB — CORRODED (SERVICE DOOR) · airframe 59,922 hrs · 46,897 cycles

ELONGATED HOLE ON WEB ON AFT SERVICE DOOR INNER STRUCTURE. REPAIRED IAW ETI-88-17-060 REV 1 AND ERA 554151-14 REV ORIG.

Part: FLOOR PANEL — CRACKED (NOT REPORTED) · airframe 59,922 hrs · 46,897 cycles

CRACK ON FLOOR PANEL. THE FLOOR PANEL WAS REPAIRED IAW AMM 25-00-00-801 AND SRM 53-01 FIG. 2.

Part: CUSP WEB — CORRODED (BS 1117-1174) · corrosion level 2 · airframe 59,922 hrs · 46,897 cycles

CORROSION ON RT CUSP WEB FROM BS 1117 - 1174, RBL 44 - 60. THE CUSP WEB WAS REPLACED IAW SRM 51-30-2, AND 51-30-5.

Part: CUSP WEB — CORRODED (FUSELAGE) · corrosion level 2 · airframe 59,922 hrs · 46,897 cycles

CORROSION ON RT CUSP WEB FROM STA Y=712 TO STA Y=769 AND BTW X=-44 TO X=-60 UPPER AND LOWER SURFACE. CUSP WEB WAS REPLACED PER SRM 53-05 FIG 131A AND ER/A 554156-14 REV ORIG.

Part: CUSP WEB — CORRODED (FUSELAGE) · airframe 59,922 hrs · 46,897 cycles

CORROSION ON RT CUSP WEB FROM STA Y=663 TO STA Y=665U AND BTW X=-54 TO X=-60 PER AND LOWER SURFACE. DAMAGE AREA WAS REPAIRED SRM 53-05 FIG 131 A.

Part: CUSP WEB — CORRODED (FUSELAGE) · corrosion level 2 · airframe 59,922 hrs · 46,897 cycles

PAX CABIN, CORROSION OUT OF LIMITS ON CUSP WEB FROM STA Y=826 TO STA Y=905, BTW X=-60 TO X=-44. CUSP WEB OF STA Y=826 TO Y=846 AND Y=846 TO Y=905 WAS REPAIRED AND FABRICATED PER SRM 53-05 FIG 131.

Part: CUSP WEB — CORRODED (FUSELAGE) · corrosion level 2 · airframe 59,922 hrs · 46,897 cycles

CORROSION ON LT CUSP WEB FROM STA Y=598 TO STA Y=712 BTW X=44 TO X=60 UPPER AND LOWER SURFACE. CUSP WEB WAS REPLACED PER SRM 53-05 FIG 131A AND ER/A 554156-14 REV ORIG.

Part: SKIN — CRACKED (VERTICAL STAB) · airframe 59,922 hrs · 46,897 cycles

VERTICAL STABILIZER, CRACKS (3EA'S) ON VERTICAL STABILIZER DORSAL FIN LEADING EDGE ACCESS PANEL CUTOUT 6301A. DAMAGE AREA WAS REPAIRED PER SRM 55-05 FIGURE 3 SHEET 1. PERFORM DECAL CONDITION VISUAL INSPECTION EVERY "C" CHECK PER TOPP 30-10-70 PAR I PG 14.

Part: SKIN — CRACKED (FUSELAGE) · airframe 59,922 hrs · 46,897 cycles

CRACKED FUSELAGE SKIN STA Y=1361 LONG 14 RT. SKIN STA Y=1361 LONG 14R WAS REPAIRED PER ETI-88-17-041 REV 3 AND ERA 554129-14 REV ORIG.

Part: SKIN — CORRODED (HORIZ STAB) · corrosion level 2 · airframe 59,922 hrs · 46,897 cycles

HIDDEN DAMAGE CORROSION ON LT BARREL NUT HOLE NR 7 STA XH 27. CORROSION ON LT BARREL NUT HOLE NR 7 WAS ATTENDED PER ERA NR 554142-14 REV. ORIGINAL.

Part: FLOOR PANEL — CRACKED (FUSELAGE) · airframe 59,922 hrs · 46,897 cycles

CRACK ON CHANNEL OF FLOOR PANELS NR 541A, 465A AND 389G. FLOOR PANELS NR 541A. 465A AND 389G WERE REPAIRED PER SRM 53-05 FIG 131 PAR 145.

Part: FLOOR PANEL — CRACKED (FUSELAGE) · corrosion level 2 · airframe 59,922 hrs · 46,897 cycles

CORROSION AND CRACKED FLOOR PANEL 120D. FLOOR PANEL 120D WAS REPLACED PER AMM 20-30-01.

Part: PAN — CORRODED (FUSELAGE) · corrosion level 2 · airframe 59,922 hrs · 46,897 cycles

FWD CARGO COMPARTMENT, CORROSION ON LOWER PAN OF DOORJAMB FROM STA Y=373 TO Y=424. JAMB WAS REPAIRED PER SRM 53-05 FIG 44A.

Part: VANE — PUNCTURED (RT WING TE FLAP) · airframe 59,922 hrs · 46,897 cycles

RIGHT WING PUNCTURED ON PREVIUS REPAIR ON INBD FLAP INBD VANE. REPAIRED IAW SRM 57-03D PARAGRAPH 11 FIGURE 11.

Part: ACCESS PANEL — CORRODED (WING) · corrosion level 2 · airframe 59,922 hrs · 46,897 cycles

CORROSION COUNTERSINK HOLES AND SETTLEMENT AREA OF FUEL ACCESS PLATES NR 1335C AND 1311C. ACCESS PLATES NR 1335C AND 1311C WERE REPLACED PER SRM 51-22-2A PAR 6 CONDITION III.

Part: SKIN — WORN (BS 275-294) · airframe 59,922 hrs · 46,897 cycles

WEARS ON UPPER EDGE OF RT WINDOW BELT BETWEEN BS 275 AND 294. REPAIRED IAW ETI-88-17-056 REV.1 AND ER/A 554134-14 REV. ORIG.

Part: FLOOR PANEL — CORRODED (CABIN) · corrosion level 2 · airframe 59,922 hrs · 46,897 cycles

CORROSION ON FLOOR PANEL IN FRONT FWD SERVICE DOOR. A NEW FLOOR PANEL WAS FABRICATED IAW DWG 9957828 REV Y, AND SRM 51-30-2.

Part: LONGERON — CRACKED (FUSELAGE) · airframe 59,922 hrs · 46,897 cycles

AFT ACCESSORY COMPARTMENT: CRACKED LONG 5R ON STA Y=1437. LONGERON WAS REPAIRED PER SRM 53-02 FIG 18.

Part: DOOR FRAME — NOT REPORTED (FUSELAGE) · airframe 59,922 hrs · 46,897 cycles

DISCREPANT AREA WAS FOUND, FOR NDT INSPECTION AT LOWER AFT (FS Y= 416 TO FS Y= 427) DOOR JAMB CORNER OF FWD CARGO DOOR. REF ER/A 333230-14 REV. A.

Part: FLOOR SUPPORT — CORRODED (FUSELAGE) · corrosion level 2 · airframe 59,922 hrs · 46,897 cycles

AFT WET AREA: CORROSION ON FLOOR SUPPORTS X-20 AND X20 BTW STA 1309 TO 1338. FLOOR SUPPORTS WERE REPLACED PER SRM 51-30-1 AND 51-10-4.

Part: SKIN — CRACKED (RT WING) · airframe 59,922 hrs · 46,897 cycles

DURING NDT INSPECTION A CRACK WAS FOUND XRS= 160 TO 168 RIGHT SIDE LOWER WING SKIN REAR SPAR. REPAIRED IAW ER/A 554148-14AD REVISION ORIGINAL.

Part: FLOOR PANEL — WORN (NOT REPORTED) · airframe 59,922 hrs · 46,897 cycles

WEAR ON FLOOR PANEL 886C CHANNEL. REPLACED IAW DWG 9936639 REV. P.

Part: CUSP WEB — CORRODED (BS 1083-1085) · corrosion level 2 · airframe 59,922 hrs · 46,897 cycles

CORROSION OUT OF LIMITS ON RT CUSP WEB FROM BS 1083 TO 1085, RBL 44 TO 60 UPPER AND LOWER SURFACE. THE CUSP WEB WAS REPAIRED IAW SRM 53-05 FIG. 131A-13.

Part: CUSP WEB — CRACKED (BS 1206-1210) · airframe 59,922 hrs · 46,897 cycles

CRACKED CUSP WEB BETWEEN BS 1206 - 1210 LBL 54 - 60. THE DAMAGED AREA WAS REPAIRED IAW 53-05, FIG 131-A.

Part: CUSP WEB — CRACKED (BS 1287-1308) · airframe 59,922 hrs · 46,897 cycles

CRACKED ON RT CUSP WEB FROM BS 1287 - 1308 AND RBL 44 - 60. DAMAGE AREA WAS REPAIRED IAW SRM 53-05 FIG 131A.

Part: FLOOR SUPPORT — CRACKED (BS 1287-1307) · airframe 59,922 hrs · 46,897 cycles

CRACKS FOUND ON THE FLOOR SUPPORT BETWEEN BS 1287 - 1307 BL 0. THE FLOOR SUPPORT WAS REPLACED IAW SRM 51-30-2 AND 51-30-5.

Part: DOUBLER — WORN (RT WING) · airframe 59,922 hrs · 46,897 cycles

RIGHT WING, WEAR ON REPAIR DOUBLER AT FIXED LEADING EDGE AT XCW=121 . DOUBLER REPAIR WAS REPLACED IAW SRM 51-30-2,51-30-5 AND 57-06B PAR. 27 FIG.29 SHEET 2.

Part: SKIN — CRACKED (LE SLAT) · airframe 59,922 hrs · 46,897 cycles

LEFT WING, CRACKED SKIN ON LT SLAT PANEL NR 2 AT STA XOS=240. REPAIRED PER SRM 57-01 FIG 3 (SHEET 2).

Part: BEAM — CRACKED (L1 DOOR) · airframe 59,922 hrs · 46,897 cycles

L1 DOOR, CRACKED BEAM NR 8 AFT END. BEAM NR 8 WAS REPAIRED PER SRM 52-05 PAR 83 FIG 111.

Part: FITTING — CRACKED (CARGO DOOR) · airframe 59,922 hrs · 46,897 cycles

CRACK ON CLIP UPPER FWD CORNER BEAM 6 AT AFT CARGO DOOR C3. CLIP WAS REPLACED PER SRM 51-30-5 AND DWG 3934011 REV D.

Part: FLOOR SUPPORT — CORRODED (BS 160-200) · corrosion level 2 · airframe 59,922 hrs · 46,897 cycles

FWD WET AREA HAS CORROSION THAT IS OUT OF LIMITS ON FLOOR SUPORT, BS 160 - 200, LBL 54. THE FLOOR SUPPORT WAS REPLACED IAW SRM 51-30-2, 51-30-5, AND 51-10-3, PAR 21, AND 14.

Part: FLOOR SUPPORT — CRACKED (FUSELAGE) · airframe 59,922 hrs · 46,897 cycles

FWD WET AREA, CRACK ON FLOOR SUPPORT STA Y=237 BTW X=44LH TO X=RH44. SUPPORT WAS REPLACED PER SRM 53-14-2 FIG 4A.

Part: DOOR FRAME — CORRODED (APU DOOR) · corrosion level 2 · airframe 59,922 hrs · 46,897 cycles

CORROSION ON APU RIGHT DOOR FRAME. DAMAGE AREA WAS REPAIRED IAW SRM 52-05 FIG.10.

Part: SEAT TRACK — OUT OF LIMITS (BS 1065-1067) · corrosion level 2 · airframe 59,922 hrs · 46,897 cycles

SEAT TRACK RBL 22, BS 1065 - 1067 OUT OF LIMITS. THE SEAT TRACK WAS REPAIRED IAW SRM 53-04 FIG 4A.

Part: SEAT TRACK — WORN (BS 200-247) · airframe 59,922 hrs · 46,897 cycles

WEAR ON SEAT TRACK RBL 44, BS 200 - 247. THE SEAT TRACK WAS REPAIRED IAW SRM 53-05, FIG 4F.

Part: CUSP WEB — CORRODED (BS 905-927) · airframe 59,922 hrs · 46,897 cycles

CRACKED ON RT CUSP WEB FROM BS 905 - 927, RBL 44 - 60. REPAIRED IAW SRM 53-05 FIG. 131 A-1.

Part: CUSP WEB — CORRODED (BS 633-640) · corrosion level 2 · airframe 59,922 hrs · 46,897 cycles

CORROSION ON RT CUSP WEB, BS 633 - 640, RBL 54 - 60 UPPER AND LOWER SURFACE. REPAIRED IAW SRM 53-05 FIG 131 A-11.

Part: FLOOR SUPPORT — CORRODED (BS 200) · corrosion level 2 · airframe 59,922 hrs · 46,897 cycles

CORROSION WAS FOUND ON THE FLOOR SUPPORT BS 200 LBL 54. REMOVED AND REPLACED THE FLOOR SUPPORT IAW SRM 51-30-5, DWG 9910078 REV JC, AND SRM 51-10-2.

Part: PAN — CRACKED (L1 DOOR) · airframe 59,922 hrs · 46,897 cycles

L1 DOOR PAN CRACKED BETWEEN TOP AND BEAM NR 1. THE PAN WAS REPAIRED IAW SRM 52-05 PAR 14 FIG 18A.

Part: LONGERON — CRACKED (BS 1418) · airframe 59,922 hrs · 46,897 cycles

AFT ACCESORIES COMPARTMENT, CRACKED LONGERON 2L, BS 1418. THE LONGERON WAS REPAIRED IAW SRM 53-02 FIG 18.

Part: SPACER — CORRODED (CARGO DOOR FRAME) · corrosion level 2 · airframe 59,922 hrs · 46,897 cycles

CORROSION ON PREVIOUS REPAIR DOUBLER OF LOWER DOOR FRAME BEAM. SPACER WAS REPLACED IAW SRM 53-05 FIG. 123.

Part: LONGERON — CRACKED (BS 1418) · airframe 59,922 hrs · 46,897 cycles

AFT ACCESORIES COMPARTMENT HAD A CRACKED LONGERON 2R, BS 1418. THE LONGERON WAS REPAIRED IAW SRM 53-02 FIG 18.

Part: VANE — CORRODED (RT WING TE FLAP) · corrosion level 2 · airframe 59,922 hrs · 46,897 cycles

RIGHT WING CORRODED ON LOWER SURFACE INBD SIDE AT RT OTBD FLAP OTBD VANE. THE VANE WAS REPLACED .

Part: PAN — CRACKED (LT OVERWING EXIT) · airframe 59,922 hrs · 46,897 cycles

CRACK ON UPPER PAN AT THE LT FWD OVERWING EMERGENCY EXIT DOOR. THE PAN WAS REPAIRED IAW SRM 52-05 FIG. 51.

Part: CUSP WEB — CORRODED (FUSELAGE) · corrosion level 2 · airframe 59,922 hrs · 46,897 cycles

PAX CABIN, CORROSION ON LT CUSP WEB FROM STA Y=586 TO STA Y=591 BTW X=54 TO X=60 UPPER AND LOWER SURFACE. AREA WAS PROTECT PER SRM 51-00-12 PAR 3 AND WAS ATTENDED AND REPAIRED PER SRM 53-05 FIG 131 A-13.

Part: CUSP WEB — CORRODED (FUSELAGE) · corrosion level 2 · airframe 59,922 hrs · 46,897 cycles

CORROSION ON DOUBLER REPAIR OF LT CUSP WEB BTW STA Y=826 TO 845 AND X=60 TO 54. CUSP WEB WAS REPAIRED PER SRM 53-05 FIG 131A-2.

Part: LONGERON — CRACKED (BS 541) · airframe 59,922 hrs · 46,897 cycles

CRACKED LONGERON 4R BS 541. THE LONGERON WAS REPAIRED IAW SRM 53-02 FIG. 18.

Part: SPAR — CORRODED (LT PYLON) · corrosion level 2 · airframe 59,922 hrs · 46,897 cycles

LT PYLON, CORROSION ON UPPER FRONT SPAR BORE AT FWD ENGINE MOUNT YOKE ON STA Y=1307. CORROSION ON UPPER BORE WAS REPAIRED PER SRM 54-04D PAR 14 F.

Part: WEB — CORRODED (BS 148) · corrosion level 2 · airframe 59,922 hrs · 46,897 cycles

CORROSION ON WEB BS 148.5 X.9. THE WEB WAS REPAIRED IAW SRM 51-70-4, FIG 1.

Part: FRAME — CRACKED (BS 1231) · airframe 59,922 hrs · 46,897 cycles

CRACKED FRAME ANGLES BS 1231 BETWEEN LONGERONS 4 AND 7L. THE FRAME ANGLES WERE REPLACED IAW SRM 53-14-3, AND 51-30-2.

Part: ANGLE — CRACKED (R1 DOOR) · airframe 59,922 hrs · 46,897 cycles

R1 DOOR HAD A CRACKED FWD, LOWER ANGLE ON BEAM NR 1. THE ANGLE WAS REPLACED IAW SRM 51-30-5, AND DWG 9911579 REV L.

Part: INTERCOSTAL — CRACKED (L1 DOOR) · airframe 59,922 hrs · 46,897 cycles

L1 DOOR CRACKED ANGLE ON FWD INTERCOSTAL BETWEENS BEAMS NR 4 AND 5. THE INTERCOSTAL WAS REPLACED IAW SRM 51-30-2.

Part: CUSP WEB — CORRODED (BS 620-623) · corrosion level 2 · airframe 59,922 hrs · 46,897 cycles

CORROSION ON RIGHT CUSP WEB, BS 620 - 623 AND BETWEEN RBL 54 - 60 UPPER AND LOWER SURFACE. FOUND TO BE OUT OF LIMITS AND REPAIRED IAW SRM 51-70-4, FIGURE 2 AND INSTALLED IAW SRM 51-30-5.

Part: CABLE — DAMAGED (RT MLG WW) · airframe 59,922 hrs · 46,897 cycles

RIGHT MLG WHEEL WELL HAD DAMAGED LACING OF HYD ELECTRIC MOTOR DRIVEN AUXILIARY PUMP FEED CABLE. THE LACING WAS REPLACED IAW ER/A 767688-14,MAAD, REVISION D AND SWPM 20-10-01.

Part: PAN — CRACKED · airframe 59,922 hrs · 46,897 cycles

CRACK ON LT WINDOW RING PAN AFT/LOWER CORNER BS 598. PAN WAS REPAIRED IAW SRM 53-05, PAR 139, FIG 122, ER/A 487747-14MA REV. A, AND ER/A 493648-14MA REV. A.

Part: PAN — CRACKED (BS 1041) · airframe 59,922 hrs · 46,897 cycles

CRACK ON LT WINDOW RING PAN AFT/UPPER CORNER BS 1041. RING PAN WAS REPAIRED IAW SRM 53-05 PAR. 139 FIG. 122, ER/A 487747-14MA REV. A AND ER/A 493648-14MA REV. A.

Part: CUSP WEB — CORRODED (BS 450-460) · corrosion level 2 · airframe 59,922 hrs · 46,897 cycles

CORROSION ON LEFT CUSP WEB FROM BS 450 TO 460 BETWEEN LBL 44 TO 60 UPPER AND LOWER SURFACES. THE CUSP WEB WAS REPAIRED IAW SRM 53-05 FIG. 131A-14.

Part: PAN — CRACKED (BS 1041-1060) · airframe 59,922 hrs · 46,897 cycles

CRACK ON LT WINDOW RING PAN FWD/LOWER CORNER BS 1041, 1060. THE RING PAN WAS REPAIRED IAW SRM 53-05 PAR 139, FIG. 122, ER/A 487747-14MA, REV. A, AND ER/A 493648-14MA REV. A.

Part: PAN — CRACKED (BS 905) · airframe 59,922 hrs · 46,897 cycles

CRACK ON LT WINDOW RING PAN AFT LOWER CORNER BS 905. REPAIRED IAW SRM 53-05, PAR 139, FIG 122, ER/A 487747-14MA, REV. A, AND ER/A 493648-14MA, REV. A.

Part: PAN — CRACKED (BS 886) · airframe 59,922 hrs · 46,897 cycles

CRACK ON RT WINDOW RING PAN FWD/UPPER CORNER BS 886. REPAIRED IAW SRM 53-05, PAR 139, FIG 122, ER/A 487747-14MA, REV.A, AND ER/A 493648-14MA, REV.A.

Part: PAN — CRACKED · airframe 59,922 hrs · 46,897 cycles

CRACK ON RT WINDOW RING PAN AFT UPPER CORNER. THE PAN WAS REPAIRED IAW SRM 53-05 PAR. 139 FIG. 122, ER/A NO. 487747-14MA REV. A, AND ER/A 493648-14MA REV. A.

Part: PAN — CRACKED (BS 845) · airframe 59,922 hrs · 46,897 cycles

CRACK ON RT WINDOW RING PAN FWD UPPER CORNER BS 845. REPAIRED IAW SRM 53-05, PAR 139, FIG 122, ER/A 487747-14MA, REV A, AND ER/A 493648-14, REV A.

Part: PAN — CRACKED (BS 946-1022) · airframe 59,922 hrs · 46,897 cycles

CRACK ON RT WINDOW RING PAN FWD/LOWER CORNER BS 946 - 1022. RING PAN REPAIRED IAW SRM 53-05, PAR 139, FIG 122, ER/A 487747-14 MA, REV A, AND ER/A 493648-14 MA, REV A.

Part: TAB — DAMAGED (RUDDER) · airframe 59,775 hrs · 46,789 cycles

RUDDER TAB FLAME SPRAY MISSING. FOUND DURING A/C STRIP AND PAINT. REPLACED RUDDER TAB.

Part: FRAME — CRACKED (TAILCONE) · airframe 59,387 hrs · 46,481 cycles

TAILCONE ATTACH FRAME CRACKED AT 3 OCLOCK AND 2 O`CLOCK POSITIONS. REMOVED DAMAGED FRAME SECTION AND STARTED INSTALLING NEW SECTION. INSTALLED NEW FRAME IAW DWG 5966769.

Part: CONTROL VALVE — MALFUNCTIONED (WATER SEPARATOR) · airframe 58,246 hrs · 45,628 cycles

DUE TO SMOKE IN THE COCKPIT. REPLACED RT WATER SEPARATOR TEMPERATURE CONTROL VALVE IAW AMM 21-20.

Part: LINE — LOOSE (HYD SYSTEM) · airframe 58,246 hrs · 45,628 cycles

NR 2 PYLON-HYDRAULIC LINE LOOSE AT PASS THRU INSIDE PYLON. REMOVED HYDRAULIC AND SENSE LINES AT FEED THROUGH, FOUND HOLE FOR PRESSURE LINE OUT OF ROUND. CLEANED SUBJECT LINE TO 1" DIA TRUE HOLE-326893. REINSTALLED HYDRAULIC AND SENSE LINES AT FEED THROUGH-913342. NEEDS LEAK CHECK.

Part: STRUCTURE — CORRODED · corrosion level 2 · airframe 57,103 hrs · 44,838 cycles

CORROSION SEVERAL PLACES LOWER SIDE OF CABIN SUB-FLOOR ABOVE C-3 DOOR. FOUND CORROSION WHILE INSPECTING TO GIVE OK TO APPLY CIC IN AREA. REPAIRED IAW SRM 53-05, FIG 131A-21.

Part: LANYARD — DAMAGED (R1 DOOR SLIDE) · airframe 57,003 hrs · 44,764 cycles

MAINTENANCE DISCOVERED THAT THE EMERGENCY ESCAPE SLIDE AT DOOR 1R HAD A NON-SERVICEABLE LANYARD. THIS COULD PREVENT PROPER DEPLOYMENT OF THE ESCAPE SLIDE AND IS NOT IN COMPLIANCE WITH 14 CFR PART 121.703. THE DOOR SLIDE GIRT BAR LANYARD WAS REPLACED.

Part: CONNECTOR — DAMAGED (EMERGENCY LIGHT) · airframe 55,861 hrs · 43,971 cycles

DURING LINE CHECK, MAINTENANCE FOUND THAT THE EMERGENCY LIGHTING AT SEAT 3D IN THE CABIN WAS INOPERATIVE. MAINTENANCE REINSTALLED A PULLED PIN IN THE CONNECTOR AND THE LIGHTS RETURNED TO AN OPERATIONAL CONDITION. LP 7068108.

Part: BATTERY PACK — INOPERATIVE (EMERGENCY LIGHT) · airframe 53,944 hrs · 42,593 cycles

DURING CHECK, MAINTENANCE FOUND THE LT AND RT OVERWING EXIT LIGHTS WERE INOPERATIVE. MAINTENANCE REPLACE THE BATTERY PACK AND THE LIGHTS WERE OPERATIONAL.

Part: LATCH — LOOSE (GIRT BAR) · airframe 53,266 hrs · 42,088 cycles

CREW DISCOVERED THAT THE R1 GALLEY DOOR GIRT BAR LATCHES WERE LOOSE. MAINTENANCE SECURED THE LATCHES.

Part: BLADE — DAMAGED (NR 1 ENGINE) · airframe 53,178 hrs · 42,022 cycles

CREW DIVERTED, DUE TO AN ENGINE STALL ON THE NR 1 ENGINE. MAINTENANCE FOUND 1 FAN BLADE DAMAGED BEYOND LIMITS AND SOME ACOUSTIC PANEL DAMAGE IN THE COLD STREAM. ENGINE WAS CHANGED.

Part: LANYARD — BROKEN (L1 DOOR SLIDE) · airframe 51,788 hrs · 41,062 cycles

AFTER ARRIVAL, PILOT REPORTED L1 DOOR ESCAPE SLIDE LANYARD WAS FOUND TO BE BROKEN. THE LANYARD WAS REPLACED.

Part: FAN — FAILED (CABIN) · airframe 51,677 hrs · 40,981 cycles

RETURNED TO DEPARTURE, AN ELECTRICAL ODOR CIRCULATING IN CABIN. MX FOUND RECIRCULATION FAN 3-PHASE CIRCUIT BREAKERS HAD TRIPPED. RECIRCULATION FAN WAS REPLACED AND THE OPS CHECK WAS GOOD. REPLACED THE RECIRCULATION FILTER AS A PRECAUTION. RAN PACKS WITH BOTH APU AND ENGINE AIR SUPPLY AND NO ODOR WAS IDENTIFIED. ACFT HAS RETURNED TO SERVICE.

Part: SKIN — DAMAGED (BS 220) · airframe 51,036 hrs · 40,521 cycles

DUE TO FUSELAGE DENT AND GOUGE AT BS 220 BETWEEN LEFT LONGERON 17 AND 18, REPAIR IS REQUIRED IAW ER/A 516336-14, SECTION II. MX COMPLETED REPAIR IAW ER/A 516336-14, SECTION 2 AND THE REQUIRED INSPECTION WAS COMPLETED.

Part: SKIN — DAMAGED (BS 229) · airframe 51,036 hrs · 40,521 cycles

DURING NON ROUTINE CHECK, DAMAGE WAS NOTED ON THE ACFT LT SIDE 12" AFT OF STA 229 AND 7" ABOVE LONGERON 18. INSTALLED REPAIR IAW SRM 53-04-5, FIG 2 & FIG 5. REQUIRED INSPECTION COMPLETED.

Part: SKIN — DENTED (FUSELAGE) · airframe 51,036 hrs · 40,521 cycles

DURING ARRIVAL AT GATE, FOUND A DENT JUST BELOW AND AFT OF THE 1L PASSENGER DOOR. PERMANENT REPAIR ACCOMPLISHED IAW ER/A 516336-14, SECTION 2 AND SRM 53-04-5, FIG 2 AND FIG 5.

Part: UNKNOWN — ODOR (CABIN) · airframe 50,577 hrs · 40,162 cycles

FLIGHT CREW REPORTED A STRONG ELECTRICAL ODOR THROUGHOUT ACFT WITH ENGINE ANTI-ICE ON. ODOR LASTED 10 MINUTES. OCCURRED A SECOND TIME AT ALTITUDE. STRONG ELECTRICAL HEAT ODOR, NOT OIL. MX DID NOT FIND ANY TROUBLE AND COMPLETED THE PNEUMATIC SYS DUCT BURNOUT IAW AMDS CARD 7100-2619. ACFT IS OK FOR SERVICE.

Part: FLOOR PANEL — CRACKED (CARGO BAY) · airframe 49,698 hrs · 39,557 cycles

TWO INCH CRACK IN BIN 6 TRANSITION FLOOR PANEL. PERFORMED A TIME LIMITED REPAIR IAW DRD 53-24-0D F.801.

Part: SKIN — DAMAGED (FS 190 TO 590) · airframe 48,527 hrs · 38,710 cycles

FOUND LIGHTNING STRIKES ON BELLY OF AIRCRAFT, LEFT SIDE, FROM BEHIND NOSE WHEEL TO IN FRONT OF LANDING GEAR. REPAIRED PER SRM 53-04-01, PARAGRAPH 5

Part: CONNECTOR — DISCONNECTED (EMERGENCY LIGHT) · airframe 48,466 hrs · 38,663 cycles

DURING SERVICE CHECK, MAINTENANCE FOUND 11D/E EMERGENCY PATHWAY LIGHT INOPERATIVE. RECONNECTED UNDERSEAT CONNECTOR. OPS CHECKED NORMAL.

Part: LIGHT — INOPERATIVE (TAILCONE) · airframe 47,647 hrs · 38,127 cycles

DURING SERVICE CHECK, MAINTENANCE FOUND BOTH EMERGENCY LIGHTING TAIL CONE SECTION INOPERATIVE. MAINTENANCE RELAMPED BOTH EMERGENCY LIGHTS IN TAIL CONE SECTION. OPERATION CHECKS NORMAL.

Part: WEB — CRACKED (FUSELAGE) · airframe 46,924 hrs · 37,618 cycles

CRACK ON SUBFLOOR STATION 161 RBL 28. INSTALLED DOUBLER PER SRM 53-04 FIG 4.

Part: WINDOW FRAME — DAMAGED (FUSELAGE) · airframe 45,442 hrs · 36,567 cycles

TOOL MARKS ON WINDOW FRAME UPPER SECTION FROM STA Y=845 TO 864 AT FUSELAGE SKIN LEFT SIDE. REPAIRED PER ERA 490025-14.

Part: SKIN — CORRODED (FUSELAGE) · airframe 45,442 hrs · 36,567 cycles

CORROSION ON FUSELAGE SKIN AT RUB STRIPS SETTLEMENT AREA STA Y=773 LONGERON 28R. REPAIRED PER SRM 53-04D.

Part: SKIN — DAMAGED (RUDDER) · airframe 45,442 hrs · 36,567 cycles

DAMAGED METALIZED COAT ON RUDDER SURFACE. REPAIRED PER SRM 51-70-1AD.

Part: TAB — DELAMINATED (RUDDER) · airframe 45,442 hrs · 36,567 cycles

DELAMINATED RUDDER CONTROL TAB FAIRING. REPAIRED PER SRM 51-70-1AD AND SRM 51-70-1D.

Part: TAB — DENTED (ELEVATOR) · airframe 45,442 hrs · 36,567 cycles

DENT ON LOWER SURFACE I/B SIDE OF RT ELEVATOR GEARED TAB. REPAIRED PER SRM 554-04 PAR.3.A.

Part: LIGHT — BROKEN (CABIN) · airframe 44,138 hrs · 35,729 cycles

MX FOUND THE EMERGENCY LIGHT AT 4C TO BE BROKEN. MX REPLACED THE LIGHT ASSY AT 4C. AN OPS CHECK WAS PERFORMED AND THE ACFT WAS RETURNED TO SERVICE.

Part: POWER SUPPLY — INOPERATIVE (CABIN) · airframe 43,345 hrs · 35,178 cycles

EMERGENCY LIGHTS AT SEAT ROWS 31 THRU 38 INOP. CVG MAINTENANCE REPLACED POWER SUPPLY PER AMM. OPERATIONAL CHECK OF LIGHT NOW OK.

Part: DUCT — BLOWN (NR 1 ENGINE) · airframe 36,805 hrs · 28,959 cycles

DURING CLIMB THROUGH 6,500 MSL, FIRE DETECTOR LOOP OAP APPEARED FOLLOWED BY LEFT FIRE INDICATION. ALL INDICATIONS APPEARED NORMAL AND ENGINE WAS LEFT AT IDLE POWER PER THE QRH. NOTE ENG ANTI-ICE WAS ON. OPENED LT ENG COWL. FOUND DUCT JUST AFT OF ENG COWL ANTI-ICE VALVE WITH BROKEN COUPLING AND DUCT SEPARATED. REMOVED AND INSTALLED ANTI ICE DUCT NEED ENG RUN. RAN ENGINE. PERFORMED LEAK TEST ON NOSE COWL ANTI ICE DUCT NO LEAKS NOTED.

Part: RESERVOIR — LEAKING (RT HYD SYSTEM) · airframe 35,698 hrs · 27,569 cycles

AT FL160, RT HYD QTY WENT TO 2. PRESSURE WAS OK. FOUND RESERVOIR OVERFILL BOTTLE FULL. DISCONNECTED RT MAIN GEAR ACTUATOR AND CYLINDER NUMEROUS TIMES FOUND THIN FILM ON SHAFT PER TML. RECOMMENDED RT HYS RESV AND RT MLG ACTUATOR 448555. REMOVED AND REPLACED HYD RESVOIR IAW M/M. LEAK CHECK OK AND SERVICED. ALSO SEE ITEM07 FOR RT ACTUATOR FOR REFERENCE.

Part: GENERATOR — FAILED (NR 2 ENGINE) · airframe 33,170 hrs · 25,407 cycles

NUMBER 2 ENGINE GENERATOR FAILED IN FLIGHT. REPLACED GENERATOR AND CSD.

Part: SKIN — GOUGED (FUSLAGE) · airframe 32,817 hrs · 25,173 cycles

FUSELAGE SKIN DENTED AND GOUGED AT STATION 646 AND LONGERON 30. REPAIRED IAW ERA 096160-14.

Part: SKIN — DAMAGED (FUSELAGE) · airframe 32,817 hrs · 25,173 cycles

FUSELAGE SKIN DAMAGED AT TWO LOCATIONS BETWEEN STATIONS 1250 AND 1287 AND LONGERONS 29L AND 30. REPAIRED I/A/W ERA 096383-14.

Part: PROXIMITY SENSOR — FAILED (E/E BAY DOOR) · airframe 32,002 hrs · 24,564 cycles

AT T/O AIRCRAFT WOULD NOT PRESSURIZE. TRIED BOTH MANUAL AND AUTO PRESS, NO HELP. LOUD NOISE HEARD THROUGHOUT A/C. ALL DOORS ON OAP SHOWED CLOSED. RESEATED E/E DOOR. REPLACED PROX SENSOR FOR DOOR.

Part: BULB — INOPERATIVE (EMERGENCY LIGHT) · airframe 29,723 hrs · 22,971 cycles

EMERGENCY LIGHT INOP AT 25E. RELAMPED, CHECKS NORMAL.

Part: PANEL — LEAKING (LEFT WING) · airframe 28,206 hrs · 21,936 cycles

FUEL LEAK LEFT WING INNER COVER SECOND PANEL FROM FUSELAGE. REPAIRED LEAK.

Part: SKIN — DENTED (FS 1287, L-30) · airframe 23,900 hrs · 18,780 cycles

FUSELAGE / SKIN / FS 1287 / L-30 : DENT CUTOUT REPAIR THE FUSELAGE SKIN WAS DENTED BY GROUND EQUIPMENT AT FS 1287 AND LONGERON 30. THE DAMAGED AREA OF SKIN WAS REMOVED WITH A 14" X 22.25" SKIN CUTOUT. THE CUTOUT WAS REPAIRED WITH AN EXTERNAL ALUMINUM DOUBLER PER ER/A 381018-14, REV B.

Part: SKIN — DENTED (FS 1250, L-29L) · airframe 23,900 hrs · 18,780 cycles

FUSELAGE / SKIN / FS 1250 / L-29L : DENT CUTOUT REPAIR THE FUSELAGE SKIN WAS DENTED BY GROUND EQUIPMENT AT FS 1250 AND LONGERON 29L. THE DENTED AREA WAS REMOVED WITH A 16.1" X 20.1" CUTOUT IN THE SKIN. THE CUTOUT WAS REPAIRED WITH AN EXTERNAL ALUMINUM DOUBLER INSTALLED PER ER/A 381017 -14, REV B.

Part: VALVE — CONTAMINATED (FUSELAGE)

CABIN COMPLETELY DEPRESSURIZES ON DESCENT THROUGH 4000 FT. NO LIGHTS ASSOCIATED. AUTO 1 SELECTED WITH CORRECT ALTIMETER AND FIELD ELEVATION. FOUND DEBRIS IN PRESSURE RELIEF VALVE. CLEARED SAME.

Part: SKIN — DAMAGED (BS 408)

C1 DOOR CUTOUT FOUND WITH THREE SEPARATE GOUGES TO THE LWR SKIN. DAMAGE IS DEEP ENOUGH TO REQUIRE SKIN DAMAGE TO BE CUTOUT. REPAIRED PER ERA 333230-14, REV A.

Part: SKIN — DENTED (BS 240)

DENT FOUND IN FUSELAGE SKIN AT APPROX FS 240 BETWEEN L18L AND L20L. DAMAGE CUTOUT IS APPROX 20 BY 13. REPAIRED PER ERA 333205-14, REV A.

Part: FRAME — CRACKED (BS 1418)

FS 1418 FRAME WAS CRACKED IN TYP LOCATIONS AT L2L AND L2R. REPAIRED PER ERA 333212-14.

Part: WIRE — SHORTED (CABIN)

EMERGENCY FLOOR TRACK LIGHTING INOP. FOUND BARE WIRES ON FLOOR. MADE APPROVED REPAIRS. ALSO, FOUND SHORTED SOCKET. REPLACED SAME.

Part: TIRE — FAILED (NR 1)

AFTER TOUCHDOWN AT APPROX 133 KTS CREW FELT A HARD SHUDDER AND A/C STARTED TO PULL TO LEFT. NO OTHER INDICATIONS IN THE COCKPIT OR ON THE ENGINES. NR 1 TIRE FAILED.

Part: SCHRADER VALVE — FAILED (NLG STRUT)

AFTER TAKEOFF, NOSE GEAR FAILED TO RETRACT. A/C RETURNED TO CVG. FOUND FLUID LEVEL OK AND LOW ON AIR. REPLACED SCHRADER VLV, RESERVICED FLUID AND AIR. A/C NOSE JACKED AND NOSE GEAR RETRACTED OK. TAXIED A/C. NOSE STRUT IS NOW HOLDING FLUID AND AIR. NO OTHER PROBLEMS NOTED.

Part: EPR LINE — LOOSE (NR 2 ENGINE)

ACFT HAD NML PWR FOR T/O WITH AUTO THROTTLES ENGAGED.BY 10K LT ENG EPR FELL .30 WITH ALL N1/N2/FF/EGT MATCHED. AUTO THROTTLES KICKED OFF. ACFT WOULD BARELY CLIMB WITH RT EPR AT MAX CLIMB PWR. AFTER LANDING, ALL PARAMETERS NML. RAN ENGS PER PFHB TO T/O PWR AND CLIMB PWR SETTINGS. BOTH ENG INDICATIONS MATCHED. FOUND NR 2 ENG EPR LINE LOOSE AT PT2 CLUSTER, NR 2 FAN CASE. RETORQUED SAME, RAN ENG, ALL PARAMETERS NORMAL.

Part: TIRE — FAILED (RT MLG)

ON T/O, NR 4 TIRE THREW CAP DAMAGING RT FLAP/ RT GEAR FLYING DOOR. RT ENG NOSE COWL AND NR 2 ENG 1ST STG FAN. NR 4 TIRE STILL HOLDING AIR (200 LBS), REPLACED NR 3 AND 4 MAIN WHEEL ASSYS. EVALUATING OTHER DAMAGE TO AFIX REPAIR.

Part: SPLICE — MISSING (CABIN)

ONE EACH EMERGENCY ESCAPE PATH LIGHT INOPERATIVE AFT OF GALLEY. ITEM WAS ON MCO 807665001. SPLICED IN BROKEN WIRE AT MODULE.

Part: TIRE — BLOWN (LT MLG)

AFTER TAKEOFF, RECEIVED LEFT MAIN GEAR UNSAFE LIGHT AND RETURNED FLL. FOUND NR 2 MAIN TIRE BLOWN, WITH WIRING TO SENSOR DAMAGED AND FLAP DAMAGED. REPLACED NR 1, NR 2 WHEELS AND REPAIRED WIRING. FERRIED TO ATL FOR REPAIRS.

Part: EEL FUSE — FAILED (CABIN)

DURING PREFLIGHT, FWD CABIN FLOOR TRACK EMERGENCY LIGHTS INOP. REPLACED FUSE IN BATTERY PACK, OPERATION NORMAL.