N905DE

Part: CHANNEL — CRACKED (COWLING) · airframe 68,778 hrs · 50,421 cycles

CHANNEL CRACKED TWO PLACES AFT SIDE OF NOSE COWL AFT BULKHEAD 6 O'CLOCK POSITION. REPLACED NR 1 NOSE COWL REF AMM 71-10-01.

Part: SLIDE — UNSECURE (L1 DOOR) · airframe 68,736 hrs · 50,382 cycles

L1 DOOR SLIDE PIN PULLED AND SLIDE PACKAGE STARTED TO OPEN. R&R L1 DOOR SLIDE PER W/C 2561-01358-04A.

Part: LAMP — INOPERATIVE (EMERGENCY LIGHT) · airframe 68,062 hrs · 49,806 cycles

EMERGENCY LIGHTS WERE INOPERATIVE AT 1CD. REPLACED THE LAMP. OPS CHECKED GOOD.

Part: SLIDE — LOW PRESSURE (R1 DOOR) · airframe 67,491 hrs · 49,355 cycles

R1 DOOR SLIDE PRESSURE OUTSIDE OF GREEN RANGE. REPLACED THE SERVICE DOOR SLIDE IAW WORK CARD 2561-4964.

Part: LIGHT — INOPERATIVE (CABIN) · airframe 67,078 hrs · 49,027 cycles

L1 DOOR EMERG LIGHT INOP. RELAMPED IAW AMM 33-50.

Part: BATTERY PACK — INOPERATIVE (EMERGENCY LIGHTS) · airframe 66,156 hrs · 48,266 cycles

EMERGENCY LIGHTS ROWS 22-25 CELING INOPERATIVE. R & R THE BATTERIES IN B5104. OPS CHECKED GOOD.

Part: SENSOR — LOOSE (WINDSHIELD) · airframe 64,928 hrs · 47,336 cycles

DURING TAXI IN, FIRST OFFICER`S WINDSHIELD HAD A LARGE SPARK. WINDSHIELD HEAT IS NO LONGER FUNCTIONING. FOUND THE WINDOW ANTI-FOG SENSOR LOOSE AND IN CONTACT WITH MOUNT SPRING. SECURED AND TESTED IAW AMM 30-41-01. OK FOR SERVICE.

Part: BATTERY PACK — INOPERATIVE (EMERGENCY LIGHTS) · airframe 64,676 hrs · 47,172 cycles

COCKPIT EMERGENCY LIGHTS WERE INOPERATIVE. REPLACED THE BATTERY PACK AND TESTED IAW AMM 33-53. OPS CHECKED OK.

Part: LANYARD — DAMAGED (L1 DOOR SLIDE) · airframe 63,644 hrs · 46,357 cycles

DAMAGE IN L1 SLIDE RELEASE LANYARD CABLE. L1 RELEASE LANYARD CABLE WAS REPLACED IAW AMM 25-62-01.

Part: STRINGER — CRACKED (FUSELAGE) · airframe 63,644 hrs · 46,357 cycles

CRACK OF 0.750" WAS FOUND ON STRINGER 17R . REPAIRED PER ERA 547891-14AD REV. ORG. AND ERA 547892-14 REV. ORG. .

Part: FRAME — CRACKED (FUSELAGE) · airframe 63,644 hrs · 46,357 cycles

INITIAL INSPECTION CRACK ON FRAME OF CANT STA Y=1510 BETWEEN 12:00 TO 1:00 POSITION AT AFT ACCESSORIES COMPARTMENT. FRAME WAS REPLACED IAW SRM 51-30-2 AND DWG 9911843.

Part: FLOOR PANEL — DAMAGED (FUSELAGE) · airframe 63,644 hrs · 46,357 cycles

ELONGATED HOLES ON GENERATION FLOOR PANEL NR 826G, 389G AND 769G. DUE TO EXCESSIVE ELONGATED HOLE FLOOR PANEL 769G WAS REPAIRED IAW SRM 51-70-4, FIG 1, SH 2 FLOOR PANEL 826G HOLES WERE DRILLED TO NEXT OVERSIZED IAW SRM 51-10-4, FLOOR PANEL 389G WILL BE REPLACED FOR EXCESSIVE DAMAGE, NEW FLOOR PANEL WAS DRILLER AND ADJUSTED IAW SRM 51-10-4.

Part: ACCESS PANEL — CORRODED (NOT REPORTED) · corrosion level 2 · airframe 63,644 hrs · 46,357 cycles

CORROSION ON FUEL ACCESS PANEL 1331C. THE ACCESS PANEL WAS REPLACED IAW AMM 20-30-01.

Part: CARGO TRACK — CORRODED (BS 1145-1155) · corrosion level 2 · airframe 63,644 hrs · 46,357 cycles

CORROSION ON RIGHT CARGO TRACK BETWEEN BS 1145 - 1155. THE CARGO TRACK WAS REPLACED IAW DWG 5936663 REV "Y", SRM 51-10-1 AND 51-30-2.

Part: CARGO TRACK — CORRODED (BS 1145-1222) · corrosion level 2 · airframe 63,644 hrs · 46,357 cycles

CORROSION ON LEFT CARGO TRACK BETWEEN BS 1145 - 1222. THE CARGO TRACK WAS REPLACED IAW SRM 51-30-2, SRM 51-30-1 AND DWG 5936663 REV "Y".

Part: CARGO TRACK — CORRODED (BS 1221-1322) · corrosion level 2 · airframe 63,644 hrs · 46,357 cycles

CORROSION ON LEFT CARGO TRACK BS 1221 - 1322. CARGO TRACK WAS REPLACED IAW DWG 5936660 REV BZ.

Part: CARGO TRACK — CORRODED (BS 1261-1322) · corrosion level 2 · airframe 63,644 hrs · 46,357 cycles

CORROSION ON RIGHT CARGO TRACK FROM BS 1231 - 1322. THE CARGO TRACK WAS REPLACED IAW SRM 51-30-2, SRM 51-30-1. SRM, 51-10-4, SRM.51-10-3 PAR. 14-21 AND DWG 5936660 REV, BZ.

Part: ACCESS PANEL — CORRODED (LT WING) · corrosion level 2 · airframe 63,644 hrs · 46,357 cycles

CORROSION ON COUNTERSINK AND SETTLEMENT AREA ON FUEL ACCESS PANEL 1311C ON LT WING. THE ACCESS PANEL WAS REPLACED.

Part: LONGERON — CORRODED (BS 1287-1309) · corrosion level 2 · airframe 63,644 hrs · 46,357 cycles

CORROSION ON LONGERON 22L BETWEEN BS 1287 - 1309. THE LONGERON WAS FOUND OUT LIMITS AND REPAIRED IAW 53-02 FIG 18.

Part: DOUBLER — CORRODED (BS 636-645) · corrosion level 2 · airframe 63,644 hrs · 46,357 cycles

CORROSION ON INTERNAL DOUBLER AT INNER FUSELAGE MID CARGO BAY BETWEEN BS 636 - 645 LONGERON 29R AND 29L. THE DOUBLER WAS REPLACED IAW SRM 51-10-4, 51-10-3 PAR 14 AND 21, 51-30-2, 51-30-5 AND DWG. 5911412 REV. DU.

Part: PAN — CRACKED (CARGO DOOR) · airframe 63,644 hrs · 46,357 cycles

CRACKED FWD EDGE PAN ON FWD CARGO DOOR OVER BEAM NR 5. THE EDGE PAN WAS REPAIRED IAW SRM 53-05D FIG.

Part: CUSP WEB — CRACKED (BS 845-864) · airframe 63,644 hrs · 46,357 cycles

A CRACK WAS FOUND ON LT CUSP WEB BETWEEN BS 845 - 864 AND X 44 TO X 60. THE CUSP WEB WAS REPAIRED IAW SRM 53-05 FIG 131A-10.

Part: STRINGER — CRACKED (FUSELAGE) · airframe 63,644 hrs · 46,357 cycles

CRACKED STR NR 20 LT STA Y, 1003 ABOVE TRAPEZOIDAL PANEL AT LT WHEEL WELL. STRINGER NR 20 WAS REPAIRED IAW SRM 53-02, FIG 22.

Part: SKIN — CRACKED (CARGO DOOR) · airframe 63,644 hrs · 46,357 cycles

CRACK ON OUTER SKIN BETWEEN BEAMS NR 1 TO 2 AND PROJECTION STA Y:658 OF AFT MID CARGO COMPARTMENT DOOR. SKIN WAS REPAIRED IAW ERA 486446-14MA, REV ORIGINAL.

Part: SKIN — CRACKED (FUSELAGE) · airframe 63,644 hrs · 46,357 cycles

CRACK OF 0.062" ON FUSELAGE SKIN AT THE UPPER FWD DOOR JAMB CORNER STA Y=375.5 BETWEEN LONG 19-20 RT OF THE FWD CARGO COMPARTMENT. FUSELAGE SKIN AT THE UPPER FWD DOOR JAMB CORNER STA Y= 375.5 BETWEEN LONGERON 19-20 RT OF THE FWD CARGO COMPARTMENT WAS REPAIRED IAW ER/A 547889-14AD, REV ORIGINAL, SECTION I AND SRM 53-05, FIG 105 IN REF ERA 547889-14AD, REV ORIGINAL DTE: REPAIR APPROVAL IS LIMITED TO 60,000 A/C TOTAL CYCLES ONLY, ADDITIONAL EA IS REQUIRED FOR CONTINUE SERVICE BEYOND THIS LIMITS, NOTE TO ENGINEER. THIRD STAGE APPROVAL IS REQUIRED PRIOR TO INSPECTION THRESHOLD IAW PROCEDURES ESTABLISHED IN FAA AC 12-93. LOG RELATED 2606557, REPETITIVE INSPECTIONS, TBD: PERFORM SECTION II TO THIS ERA 547889-14, AD REV ORIGINAL.

Part: LONGERON — CRACKED (FUSELAGE) · airframe 63,644 hrs · 46,357 cycles

INITIAL INSPECTION, CRACK ON LONG 3LT AND STA Y=1437 AT AFT ACCESSORIES COMPARTMENT. LONGERON WAS REPAIRED IAW SRM 53-02, FIG 18.

Part: LONGERON — CRACKED (FUSELAGE) · airframe 63,644 hrs · 46,357 cycles

INITIAL INSPECTION, CRACK ON LONG 4RT AND STA Y=1437 AT AFT ACCESSORIES COMPARTMENT. LONGERON WAS REPAIRED IAW SRM 53-02, FIG 18.

Part: FRAME — CRACKED (BS 1322) · airframe 63,644 hrs · 46,357 cycles

CRACK ON FRAME BS 1322 LONGERON 17R. THE FRAME WAS REPAIRED IAW ER 493697-14MA REV. B.

Part: ACCESS PANEL — CORRODED (RT WING) · corrosion level 2 · airframe 63,644 hrs · 46,357 cycles

CORROSION ON COUNTERSINK AND SETTLEMENT AREA OF FUEL ACCESS PANEL 1414C ON RT WING. THE ACCESS PANEL WAS REPLACED.

Part: DOOR FRAME — CRACKED (BS 919) · airframe 63,644 hrs · 46,357 cycles

CRACK ON EMERGENCY EXIT DOOR FRAME (UPPER AREA) BS 919 LT SIDE. THE DOOR FRAME WAS REPAIRED IAW SRM 53-05 FIG.32.

Part: ACCESS PANEL — CORRODED (NOT REPORTED) · corrosion level 2 · airframe 63,644 hrs · 46,357 cycles

CORROSION ON COUNTERSINKS AND SETTLEMENT AREA ON FUEL ACCESS PANEL 1335. ACCESS PANEL WAS REPLACED.

Part: BEAM — CRACKED (CARGO DOOR) · airframe 63,644 hrs · 46,357 cycles

CRACK ON BEAM NR 5 AND BS 427 OF FWD CARGO DOOR. THE BEAM WAS REPLACED IAW SRM 51-30-2 AND 51-30-5.

Part: ANGLE — CRACKED (EMERGENCY EXIT) · airframe 63,644 hrs · 46,357 cycles

CRACKED ANGLE ON DOOR STOP AT RT AFT OVERWING EMERGENCY EXIT. THE ANGLE WAS REPLACED IAW DWG 9957735 REV. G AND SRM 51-30-5 AND 51-30-2.

Part: FLOOR PANEL — DAMAGED (MAIN CABIN) · airframe 63,644 hrs · 46,357 cycles

DAMAGED FERRULS ON FLOOR PANEL. FLOOR PANEL REPAIRED IAW AMM 53-20-01-201 AND AMM 88 53-20-01-201.

Part: LONGERON — CRACKED (BS 1437) · airframe 63,644 hrs · 46,357 cycles

CRACK FOUND ON LONGERON 16L, BS 1437. THE LONGERON WAS REPLACED IAW SRM 53-14-4 FIG 4, SRM 51-30-5, AND SRM 51-30-2.

Part: CUSP WEB — CRACKED (BS 905-927) · airframe 63,644 hrs · 46,357 cycles

CRACK ON LEFT CUSP WEB BS 905 - 927, X 54 - 60. THE CUSP WEB WAS REPAIRED IAW SRM 53-05 FIG. 131A-14 51-30-2, 51-30-5, AND 51-10-3 PAR. 14,21 & 38.

Part: CUSP WEB — CORRODED (BS 1060-1079) · corrosion level 2 · airframe 63,644 hrs · 46,357 cycles

CORROSION ON RT CUSP WEB BS 1060 - 1079. CUSP WEB REPAIRED IAW SRM 53-05 FIG. 131A-14 AND SRM 51-30-5.

Part: CUSP WEB — CORRODED (BS 965-984) · airframe 63,644 hrs · 46,357 cycles

CORROSION ON LT CUSP WEB BETWEEN BS 965 - 984 AND X 54 - 60. THE CUSP WEB WAS REPAIRED IAW SRM 53-05 FIGURE 131A-2.

Part: ANGLE — CRACKED (PAX DOOR) · airframe 63,644 hrs · 46,357 cycles

CRACK ON ANGLE BEAM FWD AT FWD ENTRY DOOR. ANGLE WAS REPLACED IAW SRM 51-30-2, 51-30-5, AND DWG 9955752 REV M.

Part: CUSP WEB — CORRODED (BS 446-459) · airframe 63,644 hrs · 46,357 cycles

CORRODED PREVIOUS REPAIR DOUBLER ON LT CUSP WEB BETWEEN BS 446 - 459 , X 54 - 60. THE DOUBLER WAS REPLACED IAW SRM 53-05 FIGURE 131A-2.

Part: CUSP WEB — CORRODED (BS 1003-1020) · corrosion level 2 · airframe 63,644 hrs · 46,357 cycles

CORROSION ON RT CUSP WEB BS 1003 - 1020. THE CUSP WEB WAS REPAIRED IAW SRM 51-30-2, 53-05 FIG. 131A-14 , 51-10-3 PAR. 21,14 AND 51-30-5 CABIN.

Part: CUSP WEB — CORRODED (BS 984-1022) · airframe 63,644 hrs · 46,357 cycles

CORRODED REPAIR DOUBLERS ON LT CUSP WEB BETWEEN BS 984 - 1003, AND BS 1003 - 1022, X 54 - 60. REPAIR REPLACED IAW SRM 53-05 FIG. 131A-4, 131A-6, 51-10-3 PAR. 14,21,38, 51-30-2 AND 51-30-5.

Part: RIB — CRACKED (RT WING) · airframe 63,644 hrs · 46,357 cycles

CRACK ON RIB XOS 455 ON RT WING FIXED LE STRUCTURE. THE RIB WAS REPAIRED IAW SRM 57-06B D FIG. 12 SHEET 4.

Part: CUSP WEB — CORRODED (BS 1041-1050) · corrosion level 2 · airframe 63,644 hrs · 46,357 cycles

CORROSION ON RT CUSP WEB BS 1041 - 1050. THE CUSP WEB WAS REPAIRED IAW SRM 53-05 FIG. 131A-13.

Part: CUSP WEB — CORRODED (BS 934-946) · corrosion level 2 · airframe 63,644 hrs · 46,357 cycles

CORROSION ON PREVIOUS REPAIR DOUBLER ON LT CUSP WEB BS 934 - 946, X 54-60. REPAIRED IAW SRM 53-05 FIG 131. AND 51-30-2.

Part: LONGERON — CRACKED (BS 1437) · airframe 63,644 hrs · 46,357 cycles

CRACK ON LONGERON 3R BS 1437. THE LONGERON WAS REPAIRED IAW SRM 53-02 FIG.18.

Part: CUSP WEB — CORRODED (BS 560-579) · airframe 63,644 hrs · 46,357 cycles

CORROSION ON CUSP WEB BETWEEN BS 560 - 579, X 54 - 60. THE CUSP WEB WAS REPAIRED IAW SRM 51-30-2, SRM 51-10-3 PAR. 38, 26, 21 & 14, NDT SPM 04-00-07 PAR 5 FIG.3 SHEET 1-2, SRM 53-05 PAR 166, SRM 53-05 FIG. 131A-14, AND SRM 51-30-5.

Part: DOUBLER — CORRODED (BS 446-465) · corrosion level 2 · airframe 63,644 hrs · 46,357 cycles

CORROSION ON REPAIR DOUBLER BS 446 - 465 AND X -44 TO -60. AREA WAS REPAIRED IAW SRM 53-05 FIG.131A-11, 51-10-3, 51-30-1, 51-30-2 & 51-30-5.

Part: CUSP WEB — CRACKED (FUSELAGE) · airframe 63,644 hrs · 46,357 cycles

CRACK ON LT CUSP WEB OF STA Y642 BETWEEN STA X54 TO X60 AT PAX CABIN. REPAIRED IAW SRM 53-05 FIG 131A-14, 51-30-2, 51-10-3 PAR 21,14, 51-30-5 AND 51-10-3.

Part: TAB — DELAMINATED (RT ELEVATOR) · airframe 63,644 hrs · 46,357 cycles

DELAMINATED RT CONTROL TAB AT RT ELEVATOR. REPLACED WITH SERVICEABLE CONTROL TAB.

Part: FRAME — CORRODED (BS 1309) · corrosion level 2 · airframe 64,188 hrs · 46,799 cycles

CORROSION ON FRAME PREVIOUS REPAIR BS 1309 BETWEEM LONGERONS 28 AND 29L. THE REPAIR WAS REPLACED IAW SRM 53-03D FIG 2A.

Part: CUSP WEB — CORRODED (BS 522-544) · corrosion level 2 · airframe 64,188 hrs · 46,799 cycles

CORROSION ON REPAIR DOUBLER ON RT CUSP WEB BETWEEN BS 522 AND 544. THE REPAIR DOUBLER WAS REPLACED IAW SRM 53-05 FIG 131A-7, SRM 51-30-5, SRM 51-10-3.

Part: CUSP WEB — CORRODED (FUSELAGE) · corrosion level 2 · airframe 64,188 hrs · 46,799 cycles

CORROSION ON CUSP WEB BTW STA Y=592 TO Y=517 AND STA X=54 TO 60 AT PAX CABIN. CORROSION FINDING WAS ATTENDED PER SRM 53-05 FIG 131-A, 51-30-2, 51-30-5, 51-10-3 PAR 14,21 AND 38.

Part: CUSP WEB — CORRODED (BS 489-493) · corrosion level 2 · airframe 64,188 hrs · 46,799 cycles

CORROSION ON RT CUSP WEB BETWEEN BS 489 AND 493. THE CUSP WEB WAS REPAIRED IAW SRM 53-05 FIG 131A, 51-30-2, 51-10-3 PAR 14,21 AND 38.

Part: LONGERON — CRACKED (BS 1418) · airframe 63,644 hrs · 46,357 cycles

CRACK ON LONGERON 2L, BS 1418. LONGERON WAS REPLACED IAW SRM 51-30-5.

Part: DOUBLER — CORRODED (BS 1221-1231) · corrosion level 2 · airframe 63,644 hrs · 46,357 cycles

CORROSION ON PREVIOUS REPAIR DOUBLER OF LT CUSP WEB BS 1221 - 1231, X 54 - 60. THE DOUBLER WAS REPAIRED IAW 53-05 FIG 131A-2.

Part: ACCESS PANEL — PUNCTURED (LT WING) · airframe 63,644 hrs · 46,357 cycles

PUNCTURE ON SECONDARY ACCESS PANEL 1303C ON LT WING. THE ACCESS PANEL WAS REPAIRED IAW ER/A 530866-14 AD MA REV ORIGINAL.

Part: CUSP WEB — CORRODED (BS 1220-1231) · corrosion level 2 · airframe 63,644 hrs · 46,357 cycles

CORROSION ON CUSP WEB FROM BS 1220 - 1231, X -54 AND X -60. CUSP WEB REPAIRED IAW 53-05 FIG 131A-1.

Part: CUSP WEB — CORRODED (BS 1168-1174) · corrosion level 2 · airframe 63,644 hrs · 46,357 cycles

CORROSION ON CUSP WEB FROM BS 1168 TO 1174 BETWEEN X -54 AND -60. REPAIRED IAW SRM 53-05 FIG 131A-1.

Part: CUSP WEB — CORRODED (BS 579-598) · corrosion level 2 · airframe 63,644 hrs · 46,357 cycles

CORROSION ON LT CUSP WEB BETWEEN BS 579 - 598, X 54-60. REPAIRED IAW SRM 53-05 FIG 131A-14.

Part: CUSP WEB — CORRODED (BS 655-674) · corrosion level 2 · airframe 63,644 hrs · 46,357 cycles

CORROSION ON CUSP WEB FROM BS 655 - 674 BETWEEN X -54 TO X -60. CUSP WEB WAS REPAIRED IAW SRM 53-05 FIG 131A-5.

Part: CUSP WEB — CORRODED (BS 579-598) · corrosion level 2 · airframe 63,644 hrs · 46,357 cycles

CORROSION ON CUSP WEB BS 579 - 598 BETWEEN X -54 & -60. CUSP WEB REPAIRED IAW SRM 53-05 FIG 131A-14.

Part: CUSP WEB — CORRODED (BS 541-560) · corrosion level 2 · airframe 63,644 hrs · 46,357 cycles

CORROSION ON LEFT CUSP WEB BETWEEN BS 541 TO 560 X 54-60. DUE TO EXCESSIVE CORROSION AREA WAS REPAIRED IAW SRM 53-05 FIGURE 131A-6.

Part: FLOOR PANEL — DAMAGED (PAX CABIN) · airframe 63,644 hrs · 46,357 cycles

DAMAGED FLOOR PANEL. THE FLOOR PANEL WAS FABRICATED AMM 53-20-01-201.

Part: PAN — CRACKED (BS 788-965) · airframe 63,644 hrs · 46,357 cycles

CRACK ON RING PAN LOWER FWD BETWEEN BS 965 - 946 AND 788 - 806. RING PAN WAS REPAIRED IAW SRM 53-05 FIG 122 AND ERA?S 493648-14MA REV A. AND 487747-14MA REV A.

Part: PAN — CRACKED (BS 541-560) · airframe 63,644 hrs · 46,357 cycles

CRACK ON FWD UPPER CORNER OF RING PAN BETWEEN BS 541- 560. RING PAN REPAIRED SRM 53-05 FIG 122 AND ER'AS 493648-14MA REV A AND 487747-14MA REV A.

Part: PAN — CRACKED (BS 598-603) · airframe 63,644 hrs · 46,357 cycles

CRACK ON FWD UPPER CORNER OF RING PAN BETWEEN BS 598-603. RING PAN REPAIRED IAW SRM 53-05 FIG 122 AND ERA 487747-14MA REV A AND 493648-14MA REV A.

Part: PAN — CRACKED (BS 805-826) · airframe 63,644 hrs · 46,357 cycles

CRACK ON AFT LOWER CORNER OF RING PAN BETWEEN BS 826-805. RING PAN REPAIRED IAW SRM 53-05 FIG 122 AND ER/A 487747-14MA REV A AND 493648-14MA REV A.

Part: PAN — CRACKED (BS 1231-1250) · airframe 63,644 hrs · 46,357 cycles

CRACK ON RING PAN LOWER FWD BETWEEN BS 1250 - 1231. RING PAN REPAIRED IAW SRM 53-05 FIG 122 AND ER/A 487747-14 MA REV A AND 593648-14 MA REV A.

Part: PAN — CRACKED (BS 769-788) · airframe 63,644 hrs · 46,357 cycles

CRACK ON FWD UPPER AND AFT LWR CORNER OF RING PAN BETWEEN BS 769-788 . RING PAN WAS REPAIRED IAW SRM 53-05 FIG. 122 AND ER/A 487747-14MA REV. A AND 493648-14 MA REV. A.

Part: PAN — CRACKED (BS 712-731) · airframe 63,644 hrs · 46,357 cycles

CRACK ON FWD UPPER CORNER OF RING PAN BETWEEN BS 731-712. RING PAN WAS REPAIRED IAW SRM 53-05 FIG 122 AND ERAS 487747-14 MA REV. A AND 493648-14 MA REV. A.

Part: PAN — CRACKED (636-864) · airframe 63,644 hrs · 46,357 cycles

CRACK ON FWD LWR CORNER OF RING PANS BETWEEN BS 845 - 864, 805 - 788, 788 - 679 AND 655 - 636. RING PAN REPAIRED IAW SRM 53-05 FIG 122 AND ERAS 487747-14MA REV. A AND 493648-14MA REV. A.

Part: PAN — CRACKED (BS 655-674) · airframe 63,644 hrs · 46,357 cycles

CRACK ON AFT UPPER CORNER OF RING PAN BETWEEN BS 655-674. RING PAN WAS REPAIRED IAW SRM 53-05 FIG 122 AND ERAS 493648-14 MA REV A. AND 487747-14MA REV A.

Part: PAN — CRACKED (BS 1022-1041) · airframe 63,644 hrs · 46,357 cycles

CRACK ON FWD UPPER CORNER OF RING PAN BETWEEN BS 1022 - 1041. RING PAN REPAIRED IAW SRM 53-05 FIG 122 AND ERAS 493648-14MA REV A. AND 487747-14MA REV A.

Part: PAN — CRACKED (BS 712-1079) · airframe 63,644 hrs · 46,357 cycles

CRACK ON FWD UPPER CORNER OF RING PAN BETWEEN BS 712 - 731 , 1022 - 1007 AND 1079 - 1060. RING PAN REPAIRED IAW SRM 53-05 FIG.122 AND ER/AS 493648-14MA REV. A AND 487747-14MA REV. A.

Part: PAN — CRACKED (BS 1174-1180) · airframe 63,644 hrs · 46,357 cycles

CRACK ON FWD LWR CORNER OF RING PAN BETWEEN BS 1174-1180. RING PAN REPAIRED IAW SRM 53-05 FIG 122 AND ERAS 493648-14MA REV A. AND 487747-14MA REV A.

Part: PAN — CRACKED (BS 465-469) · airframe 63,644 hrs · 46,357 cycles

CRACK ON FWD UPPER CORNER OF RING PAN BETWEEN BS 465-469. RING PAN WAS REPAIRED IAW SRM 53-05 FIG.122 AND ERAS 493648-14MA REV. A AND 487747-14MA REV.A.

Part: PAN — CRACKED (BS 347-351) · airframe 63,644 hrs · 46,357 cycles

CRACK ON AFT LWR CORNER OF RING PAN BS 351-347. RING PAN REPAIRED IAW SRM 53-05 FIG. 122 AND ER/A 487747-14MA REV. A AND 493648-14MA REV. A.

Part: PAN — CRACKED (BS 597-750) · airframe 63,644 hrs · 46,357 cycles

CRACK ON RING PAN LOWER AFT BETWEEN BS 679 - 750 AND 617 - 597. RING PAN WERE REPAIRED IAW SRM 53-05 FIG. 122 AND ER/A 487747-14MA REV. A AND 493648-14MA REV. A.

Part: SKIN — CORRODED (FUSELAGE) · corrosion level 2 · airframe 63,644 hrs · 46,357 cycles

INITIAL: EXFOLIATION CORROSION ON INTERNAL FUSELAGE SKIN BETWEEN STA Y= 230 TO 237 AND LONG 25 RT TO 26 RT AT FWD CARGO COMPARTMENT. FINGER DOUBLER WAS CUT FOR EXCESSIVE DAMAGE AND NEW DOUBLER WAS FABRICATED IAW SRM 53-04, FIG 12D AND SKIN CORROSION WAS REMOVED IAW SRM 51-10-3, PAR 26, 21, 14.

Part: CONNECTOR — DAMAGED (EMERGENCY LIGHTS) · airframe 63,159 hrs · 45,992 cycles

MAINTENANCE FOUND THE EMERGENCY LIGHT INOPERATIVE AT SEAT 24D. THE CONNECTOR WAS REPAIRED BY INSTALLING A NEW PIN ON A WIRE AND THE LIGHT CHECKED OK.

Part: TAB — DAMAGED (RUDDER) · airframe 62,706 hrs · 45,651 cycles

RUDDER TAB SPLIT AT T/E. R & R RUDDER TAB IAW AMM 27-20.

Part: STRUCTURE — MISSING (RUDDER) · airframe 62,706 hrs · 45,651 cycles

FLAME SPRAY MISSING FROM CRITICAL ZONES ON RUDDER IAW SRM 55-03, PAGES 91 AND 92. R & R RUDDER IAW AMM 27-20.

Part: SKIN — CORRODED (FUSELAGE) · airframe 64,215 hrs · 46,819 cycles

FUSELAGE SKIN CORRODED AND SHEARED RIVETS AT FWD LOWER CORNER OF AFT LAVATORY SERVICE PANEL. REPAIED IAW ER/A.

Part: SKIN — CRACKED (BS 1361) · airframe 62,221 hrs · 45,319 cycles

ACFT SKIN HAS .5" LONG CRACK THRU FASTENER HOLE IN LAP SEAM AT BS 1361, L14R. REPAIRED IAW ER/A 542121-14, REV ORIGINAL.

Part: SKIN — CRACKED (BS 1361) · airframe 62,219 hrs · 45,317 cycles

CRACK FUSELAGE SKIN ON L14R AT BS 1361. REPAIRED IAW ER/A 542121-14.

Part: SUPPORT FITTING — CRACKED (LT WING) · airframe 62,219 hrs · 45,317 cycles

GROUND SPOILER ACTUATOR SUPPORT FITTING CRACKED AT FWD INBD END, LT WING. R & R GROUND SPOILER SUPPORT DRIVE FITTING REF DWG SR09570010, REV H.

Part: SKIN — CRACKED (BS 1361) · airframe 62,219 hrs · 45,317 cycles

FUSELAGE SKIN CRACK AT BS 1361 ON L14R. FOLLOW ON ACTION IS REQUIRED. THIS IS A MAJOR REPAIR. ACCOMPLISH SECTION II NTE 12 MONTHS FROM ACCOMPLISHMENT OF SECTION I REPAIR.

Part: SLIDE — DAMAGED (L1 DOOR) · airframe 60,039 hrs · 43,810 cycles

MAINTENANCE FOUND THE L1 DOOR SLIDE DAMAGED. MAINTENANCE REPLACED THE L1 DOOR SLIDE.

Part: LINE — LEAKING (APU OIL) · airframe 58,085 hrs · 42,415 cycles

THE CREW DIVERTED DUE TO WHITE HAZE FILLING THE CABIN AFTER TAKEOFF. BOTH AFT LAVATORY SMOKE DETECTORS WERE SOUNDING. MAINTENANCE FOUND THE APU LEAKING OIL AT THE TURBINE BEARING HOUSING PRESSURE/SCAVENGE OIL TUBE ASSY. THE APU WAS REPLACED AND A DUCT BURNOUT WAS PERFORMED, HOWEVER THE OIL SMELL CONTINUED WITH THE NR 1 ENGINE OPERATING EITHER PACK. FURTHER INVESTIGATION FOUND THE NR 1 ENGINE INLET BULLET FULL OF OIL. THE OIL FEED TUBE AND THE TACH GENERATOR COVER O-RINGS WERE ALL REPLACED. NO FURTHER SMOKE OR ODOR DURING HIGH POWER RUN.

Part: CONTROLLER — MALFUNCTIONED (CABIN PRESSURE) · airframe 57,660 hrs · 42,134 cycles

THE CREW EXECUTED AN EMERGENCY DESCENT DUE TO LOSS OF CABIN PRESSURIZATION. MASKS DID NOT DEPLOY. MAINTENANCE REPLACED THE CABIN OUTFLOW DRIVE ASSY IAW AMM 21-32. THE NR 2 CABIN PRESSURE CONTROLLER WAS REPLACED IAW AMM 21-32. THE FORWARD LT CABIN PRESSURE SAFETY VALVE WAS REPLACED IAW AMM 21-32 BECAUSE IT WAS FOUND OPEN DURING THE CABIN PRESSURIZATION CHECKS.

Part: SPAR — CRACKED (WING) · airframe 57,383 hrs · 41,947 cycles

WING REAR SPAR CRACKING AT XRS 164.

Part: WIRE HARNESS — DAMAGED (EMERGENCY LIGHT) · airframe 56,637 hrs · 41,415 cycles

DURING LINE CHECK, MX FOUND THAT THE EMERGENCY PATHWAY LIGHTING IN ROWS 13 AND 21DE OF THE CABIN WERE INOPERATIVE. MX REPLACED THE WIRE HARNESS AND FUNCTIONALLY CHECKED THE SYSTEM.

Part: BATTERY PACK — INOPERATIVE (EMERGENCY LIGHT) · airframe 56,637 hrs · 41,415 cycles

DURING LINE CHECK, MX FOUND THAT THE EMERGENCY PATHWAY LIGHTING IN THE COCKPIT AND THE L1 DOOR EXIT SIGN HAD FAILED. MX REPLACED THE BATTERIES IN THE POWER SUPPLY AND THE LIGHTS RETURNED TO AN OPERATIONAL CONDITION.

Part: WIRE — DAMAGED (EMERGENCY LIGHT) · airframe 56,337 hrs · 41,195 cycles

DURING ROUTINE LINE CHECK, EMERGENCY LIGHT AT SEAT 14E FOUND TO BE INOPERATIVE. SEAT WIRING WAS REPAIRED IAW AMM 20 AND OPERATION CHECKED GOOD.

Part: WIRE — DAMAGED (EMERGENCY LIGHTS) · airframe 56,337 hrs · 41,195 cycles

DURING ROUTINE LINE CHECK, THE EMERGENCY LIGHT AT SEAT 21E WAS FOUND TO BE INOPERATIVE. THE SEAT WIRING WAS REPAIRED IAW AMM 20 AND OPERATION CHECKED GOOD.

Part: CONNECTOR — DAMAGED (EMERGENCY LIGHTS) · airframe 55,546 hrs · 40,649 cycles

DURING LINE CHECK, MX FOUND THAT THE EMERGENCY PATHWAY LIGHTING AT ROW 13DE INOPERATIVE. MX FOUND A PIN PULLED OFF IN THE CONNECTOR, REPLACED PIN AND THE SYS RETURNED TO NORMAL OPERATION.

Part: BATTERY PACK — INOPERATIVE (EMEGENCY LIGHT) · airframe 55,237 hrs · 40,454 cycles

DURING SERVICE CHECK, EMERGENCY LIGHTS IN TAIL COMPARTMENT INOPERATIVE. R & R BATTERIES IN TAIL COMPARTMENT POWER SUPPLY. OPERATION CHECKS GOOD.

Part: WIRE — BROKEN (EMERGENCY LIGHT) · airframe 55,134 hrs · 40,380 cycles

DURING SERVICE CHECK, FOUND AISLE EMERGENCY LIGHTING INOPERATIVE ROWS 17 AND 29. FOUND WIRES BORKEN, REPAIRED SPLICES IAW SWPM. OPS CHECKS GOOD.

Part: CONNECTOR — LOOSE (EMERGENCY LIGHT) · airframe 55,051 hrs · 40,325 cycles

DURING SERVICE CHECK, EMERGENCY LIGHTS OUT AT SEATS 16C AND 21C. RESECURED CONNECTOR AT SEATS 16C AND 21C. OPERATION CHECKS OK.

Part: PAN — CRACKED (DOOR FRAME) · airframe 53,632 hrs · 39,316 cycles

FWD ACCESSORY COMPARTMENT DOOR PAN CRACKED AT AFT EDGE. FABRICATED REPAIR DOUBLER AND INSTALLED PER ER/A 505157-14 REV 0.

Part: SPAR CAP — CRACKED (RT WING) · airframe 53,632 hrs · 39,316 cycles

RT WING REAR SPAR LOWER CAP CRACKED.

Part: SUPPORT FITTING — CORRODED (AFT CARGO DOOR) · corrosion level 2 · airframe 53,632 hrs · 39,316 cycles

CORROSION ON SUPPORT FITTING AT BS 1212 FOR AFT CARGO DOOR BEAM. REMOVED AND REPLACED FITTING.

Part: STRAP — CORRODED (DOOR FRAME) · corrosion level 2 · airframe 53,632 hrs · 39,316 cycles

AFT CARGO DOOR FRAME WEB STRAP AT BS 1174 CORRODED OUT OF LIMITS. FABRICATED NEW STRAP PER DWG 5936442 AND INSTALLED.

Part: TEE FITTING — CORRODED (BS 1155 L28R) · corrosion level 2 · airframe 53,632 hrs · 39,316 cycles

CORROSION ON TEE FITTING AT BS 1155 L28R AFT CARGO BEAM. REMOVED AND REPLACED TEE FITTING.

Part: TEE FITTING — CORRODED (BS 1155 L29R) · corrosion level 2 · airframe 53,632 hrs · 39,316 cycles

CORROSION ON TEE FITTING AT STA 1155 L-29R. REMOVED AND REPLACED TEE FITTING.

Part: SUPPORT FITTING — CORRODED (BS 1155) · corrosion level 2 · airframe 53,632 hrs · 39,316 cycles

CORROSION ON SUPPORT FITTING TO AFT CARGO DOOR BEAM AT BS 1155. CORROSION OUT OF LIMITS REMOVED AND REPLACED SUPPORT.

Part: BEAM — CORRODED (DOOR SILL) · corrosion level 2 · airframe 53,632 hrs · 39,316 cycles

AFT CARGO DOOR SILL BEAM CORROSION. CORROSION OUT OF LIMITS. REMOVED AND REPLACED DOOR BEAM.

Part: LIGHT — INOPERATIVE (CATWALK) · airframe 53,006 hrs · 38,860 cycles

DURING SERVICE CHECK, MAINTENANCE FOUND 3 EMERGENCY LIGHTS INOPERATIVE AFTWARD OF CATWALK. MAINTENANCE REMOVED AND REPLACED BATTERIES IN B5-28 PER AMM. OPERATION CHECKS GOOD.

Part: CONNECTOR — DAMAGED (CABIN) · airframe 51,184 hrs · 37,612 cycles

DURING LINE CHECK, MAINTENANCE FOUND CONNECTOR FOR ROW 26DE EMERGENCY PATHWAY LIGHT DAMAGED. MAINTENANCE RE-PINNED CONNECTOR. OPERATION CHECKS GOOD.

Part: WIRE — BROKEN (CABIN) · airframe 50,528 hrs · 37,193 cycles

DURING LINE CHECK, MAINTENANCE FOUND EMERGENCY PATHWAY LIGHTING INOPERATIVE AT ROW 27DE. MAINTENANCE FOUND AND REPAIRED BROKEN WIRE. OPERATION CHECKS GOOD. AIRCRAFT OKAY FOR SERVICE.

Part: SIGN — INOPERATIVE (CABIN) · airframe 49,395 hrs · 36,466 cycles

DURING LINE CHECK MAINTENANCE FOUND THE AFT EMERGENCY EXIT SIGN INOPERATIVE. MAINTENANCE REPLACED THE LIGHT ASSEMBLY AND THE SYSTEM NOW CHECKS OPERATIONAL. (2010-D1239) (DLM88102841).

Part: WIRE — DAMAGED (CABIN) · airframe 49,383 hrs · 36,454 cycles

DURING LINE CHECK, MAINTENANCE FOUND EMERGENCY LIGHT AT 1CD INOPERATIVE. MAINTENANCE REPAIRED DAMAGED WIRE. OPERATION OF LIGHT NOW CHECKS OK. (2010-D1236) (DLM88102766)

Part: OIL SYSTEM — OVERTEMP (NR 1 ENGINE) · airframe 49,203 hrs · 36,322 cycles

DURING CLIMB, THE NR1 ENGINE OIL TEMPERATURE FLUCTUATED BETWEEN 130 AND 180 DEGREES. FLIGHT CREW SHUTDOWN THE NR1 ENGINE IAW QRH AND DIVERTED THE ACFT, SAFELY LANDING. MX REPLACED THE NR1 ENGINE.

Part: SPAR CAP — CRACKED (RT WING) · airframe 48,940 hrs · 36,148 cycles

REF EA 09-471576-12, REV ORIG ME05 HIDDEN DAMAGE: CRACK OF APROX 3.312 INCH ON THE RT WING LOWER SPAR CAP AT STA XRS=108 REF NRC T0178869 AND T0179341. SLOT CUT CRACK IAW AMR 0907304 REV 3, FAB NEW SPLICES IAW AMR0957304, REV 3 REPAIR INSTRUCTIONS 23 AND 24. TREATED/PAINTED REPAIR PARTS IAW SRM 51-10-3 IAW 14/21. NEW PARTS WHERE IN STALLED IAW DWG J060165/AMR 0957304, REV 4 AMR 0957304, REV7/FINAL ERA 183920-14 REV ORIGINAL.

Part: PAN — CRACKED (CARGO DOOR) · airframe 48,940 hrs · 36,148 cycles

CRACK ON PAN BELOW AFT STOP NR 3 AT C1 DOOR REF T0178310. CRACK WAS STOPED DRILLED IAW SRM 52-05, FG 50 AND 51. DOUBLER WAS FABRICATED IAW SRM 52-05, FIG 50 AND TREATED/PAINTED IAW 51-10-3. EDDY CURRENT INSP OF STOP DRILL FOUND NO CRACK AFTER STOP DRILL. REPAIR WAS INSTALLED IAW SRM52-05, FIG 50.

Part: SPAR CAP — DAMAGED (RT WING) · airframe 48,940 hrs · 36,148 cycles

REF EA 09-471576-12, REV ORIGINAL ME05 OPN NR0 502 REPAIR (5) CRACKS OF 812, .0.750, 0.125, 1.00 LENGTH ON THE WING REAR SPAR LOWER CAP AFT VERTICAL LEG AT INBD ATTACH POINT_OF THE RT WING FLAP HINGE FITTING XRS=164. GAINED ACCESS IAW AMR 0957304 REV 2 AND DWG J 060105 REV U, SRM51-30-2, SRM 51-30-5. CRACKS WHERE REMOVED IAW AMR 0957304REV2 AND NEW PARTS WHERE MADE IAW AMR 0957302 REV 2. REPAIR PARTS WHERE TREATED AND PAINTED IAW SRM 51-10-4. REPAIR PARTS WHERE INSTALLED IAW 51-30-5. REPAIR WAS ACCOMPLISHED IAW AMR 0957304, REV 4 AND FINAL ERA 983920-14, REV ORIGINAL.

Part: SUPPORT FITTING — CORRODED (LT MLG) · corrosion level 2 · airframe 48,940 hrs · 36,148 cycles

PITTING CORROSION ON LT MLG SUPPORT FITTING BUSHING BORE AT WALL AND AFT FACE. CORROSION BLENDED OUT IAW EA 09-093855-03, AD REV B, ME01, OPN 0103 AND FOUND WITHIN LIMITS IAW DWG 5935812. BUSHING BORE TREATED IAW SRM 51-10-3.

Part: SUPPORT FITTING — DAMAGED (LT MLG) · airframe 48,940 hrs · 36,148 cycles

SCRATCHES ON LT MLG SUPPORT FITTING BEARING BORE. DAMAGE REMOVED IAW EA 09-093855-03AD, REV B, ME01, OPN 0103 AND BORE WAS FOUND TO BE IN LIMITS. BEARING BORE WAS TREATED IAW SRM 51-10-3 PAR 34.

Part: SUPPORT FITTING — DAMAGED (RT MLG) · airframe 48,940 hrs · 36,148 cycles

SCRATCHES ON RT MLG SUPPORT FITTING BEARING BORE. DAMAGE BLENDED OUT IAW EA 09-093855-03AD REV B, ME02 OPN 0203AND FOUND WITHIN LIMITS. BEARING BORE TREATED IAW SRM 51-10-3.

Part: BEAM — CORRODED (BS 636-693) · corrosion level 2 · airframe 48,940 hrs · 36,148 cycles

EXFOLIATION CORROSION ON THE MID CARGO COMPARMENT DOOR JAMB LOWER BEAM STA Y=636-693(C2). CORROSION WAS REMOVED IAW SRM 51-10-3 AND FOUND TO BE OUT OF LIMITS IAW SRM 53-05, FIG 123. FABERICATED NEW PARTS IAW SRM 53-05-123. TREATED AND PAINTED IAW SRM 51-10-3, PAR 14 AND 21. INSTALLED NEW PARTS IAW 53-05, FIG 123.

Part: BEAM — CORRODED (BS 1168-1198) · airframe 48,940 hrs · 36,148 cycles

EXFOLIATION CORROSION ON AFT COMPARTMENT DOOR JAMB LOWER BEAM REPAIR DOUBLER STA Y=1168-1198 (C3). REMOVED DOUBLER IAW SRM 51-30-5. FAB NEW DOULBER IAW SRM 53-05, FIG 123. INSTALLED NEW DOUBLER IAW SRM 51-30-5 AND 53-05 FIG 123.

Part: DOOR FRAME — CORRODED (CARGO BAY) · corrosion level 2 · airframe 48,940 hrs · 36,148 cycles

EXFOLIATION CORROSION ON LOWER DOORJAMB PAN OF C1. DOORJAMB WAS REPLACED IAW SRM'S 51-10-3 PAR 26, 53-05D FIG 804D, AND ERA 483910.

Part: WIRE — DISCONNECTED (EMERGENCY LIGHT) · airframe 48,523 hrs · 35,848 cycles

MX FOUND SEAT 2C AND 4C EMERGENCY LIGHTS INOP. RELAMPED SEAT 4C AND FOUND WIRE PULLED OUT OF LIGHT 2C. REPINNED WIRE INTO LIGHT SOCKET OF 2C. OPS CHECK OF LIGHTS NOW CHECK GOOD.

Part: SKIN — CRACKED (HORIZ STAB) · airframe 46,545 hrs · 34,535 cycles

CRACK IN STAB UPPER AFT RT SKIN. REPAIRED SKIN IN ACCORDANCE WITH ERA 460409-14AD.

Part: STRUT — UNDERSERVICED (NLG) · airframe 41,744 hrs · 31,406 cycles

AT GEAR RETRACTION, THERE WAS AN ABNORMAL CLUNK FOLLOWED BY A NOSE GEAR RED UNSAFE LIGHT. NO EVIDENCE OF NLG CONTACT IN NOSE W/W, JACKED AC RAN NLG DISCONNECTED FWD DOORS SHOOK ALL GEAR WIRING NO UNSAFE INDICATION. CHECKED NLG STRUT SVC, FOUND SVC LOW SERVICED NLG STRUT PER MM. RECONNECTED FWD DOORS OPERATED NLG, OPS NORMAL CHECKED SENSORS PROX BOX CKS GOOD.

Part: ENGINE — UNKNOWN (NR 2) · airframe 41,321 hrs · 31,140 cycles

NR 2 ENGINE ROLLED BACK ON LEVEL OUT AT 4000 FT ON APPROACH. OIL PRESS WENT TO ZERO. ENGINE WAS MANUALLY SHUT DOWN. REPLACED NR 2 ENG OIL FILTER, NO METAL FOUND CHECKED CHIP DETECTOR NO METAL FOUND NEEDS LEAK CK REMOVED FUEL CONTROL P M/M. REPLACED FUEL PUMP AND FUEL CONTROL PER M/M NEEDS OPS CHECK. OP CHECKS GOOD PER M/M.

Part: SKIN — CRACKED (HORIZ STAB) · airframe 40,415 hrs · 30,538 cycles

HORIZONTAL STABILIZER/RT/UPPER AFT SKIN PANEL, CRACK REPAIR. THE UPPER AFT SKIN PANEL OF THE RT HORIZONTAL STABILIZER WAS FOUND WITH A .25" CRACK NEAR THE INBD AFT EDGE OF THE PANEL. THE CRACK WAS STOP DRILLED ON THE FWD END AND ROUTED OUT TO THE AFT EDGE OF THE PANEL ON A TIME LIMITED BASIS. THE PERMANENT REPAIR REQUIRES REPLACEMENT OF THE SKIN PANEL. THE REPAIR WAS ACCOMPLISHED PER ER/A 460409-14.

Part: OUTFLOW VALVE — STUCK (CABIN PRESSURE) · airframe 34,175 hrs · 26,252 cycles

LOSS OF PRESSURIZATION AT FL 280. EMERGENCY DESCENT TO 10,000 FT. CABIN ALTITUDE GOT UP TO A MAX OF 11,000 FT. OUTFLOW VLV APPEARED FULL CLOSED WITH FLOW LIGHT ON AT CONTROLLER. CABIN CONTINUED TO CLIMB. BOTH PACKS OPERATING NORMAL. REMOVED INSULATION FROM OUTFLOW VALVE AND SECURED PROPERLY.

Part: EXTINGUISHER — LEAKING (CABIN) · airframe 33,480 hrs · 25,753 cycles

AFT WATER FIRE EXTINGUISHER LEAKING. REPLACED SAME.

Part: ACTUATOR — FAILED (NLG) · airframe 30,043 hrs · 23,426 cycles

AFTER GEAR RETRACTION, NOTICED LOUD VIBRATION. CYCLED LANDING GEAR, VIBRATION CONTINUED, WORSE AT HIGHER AIRSPEED. FOUND RIGHT NOSE GEAR DOOR OPEN. INSPECTED AREA, NO DAMAGE FOUND. REPLACED RIGHT NOSE GEAR DOOR ACTUATOR PER M/M. CHECKS OK.

Part: WIRE — DAMAGED (AFT AIRSTAIR) · airframe 29,944 hrs · 23,362 cycles

AFT CABIN EMERGENCY LIGHTS INOP. REPAIRED WIRING AT AFT AIRSTAIR FWD LIGHT.

Part: BLEED VALVE — MALFUNCTIONED (NR 2 ENGINE) · airframe 29,470 hrs · 23,039 cycles

ON TAKEOFF POWER APPLICATION NR 2 ENGINE FAILED TO COME OUT OF IDLE POWER. REPLACED START BLEED CONTROL VALVE PER MM.

Part: ENGINE — FAILED (NR 1) · airframe 28,858 hrs · 22,605 cycles

AT ABOUT 600 FT AGL ON CLIMB 8R ATL THE LT ENGINE ROLLED BACK TO IDLE. TRIED TO PUSH POWER UP ON DOWNWIND AND IT WOULD NOT ACCELERATE PAST 38 PCT N1. ALL ENGINE INDICATIONS WERE NORMAL NO NOISE OR VIBRATION. NORMAL AMOUNT OF YAW FOR SITUATION. REPLACED NR 1 ENGINE PER TRANSMITTAL 9T102.

Part: STRUT — LOW (NLG) · airframe 27,776 hrs · 21,773 cycles

NOSE LANDING GEAR WOULD NOT RETRACT. RETURNED TO CLT. INSPECTED NOSE LANDING GEAR AND DOORS, NO DAMAGE OR FOREIGN OBJECTS FOUND. NOSE GEAR OLEO FLAT ON ARRIVAL. SERVICED STRUT PER OPN 4703, SWUNG NOSE LANDING GEAR PER MM 07-11-00-2. GEAR RETRACTION AND INDICATION NORMAL.

Part: COALESCER BAG — DIRTY (A/C BAY) · airframe 26,288 hrs · 20,693 cycles

SMOKE IN CABIN, PERFORMED DUCT BURNOUT. REPLACED COALESCER BAG.

Part: CHIP DETECTOR — LEAKING (APU) · airframe 25,892 hrs · 20,414 cycles

SHORTLY AFTER TAKEOFF, F/A REPORTED HAZE IN CABIN WITH ALL 3 SMOKE ALARMS GOING OFF. SMELLED LIKE BURNING SMELL. CAME OUT OF OVERHEAD DUCTING. RETURNED TO PHX. FOUND APU MAG CHIP DETECTOR LEAKING AND OIL INGESTED IN APU INTAKE. REPLACED CHIP DETECTOR AND PERFORMED DUCT BURN OUT PROCEDURE PER M/M 36-10-00-2.

Part: FCU — LEAKING (APU`) · airframe 23,627 hrs · 18,750 cycles

IN CRUISE STRONG KEROSENE SMELL. FOUND APU FCU LEAKING. REPLACED APU, PERFORMED DUCT BURNOUT.

Part: COALESCER BAG — CONTAMINATED (ACM BAY) · airframe 23,497 hrs · 18,646 cycles

AT V1 SPEED BOTH LT AND RT AIR CONDITIONING TEMP HIGH LIGHTS ILLUMINATE ON OAP. ON RETURN TO FIELD LIGHTS WENT OUT AND RE-ILLUMINATED ON DOWNWIND LEG. SMOKE AND FUMES WERE SMELLED IN CABIN AND COCKPIT. REPLACED WATER SEPARATOR BAGS. PERFORMED LT AND RT AUGMENTATION VALVES CHECK PER MD88 PREFLIGHT HANDBOOK. RAN BOTH ENG AT T/O PWR FOR 4 MIN. NO SMOKE PRESENT.

Part: APU — FAILED (AFT) · airframe 23,495 hrs · 18,644 cycles

ON TAXI OUT APU AUTO SHUT DOWN, GOT APU FAULT INDICATION AND BURNING SMELL THROUGHOUT AIRCRAFT. APU EXPERIENCED INTERNAL FAILURE, EXPANDED CASE, AND DAMAGED INLET DOOR AND SURROUNDING PANEL. REPLACED APU AND INLET DOOR PANEL ASSEMBLY. REPAIRED WIRES DAMAGED BY DOOR PANEL EXPANSION. PERFORMED DUCT BURNOUT PROCEDURES AND REPLACED COALESCER BAGS.

Part: OXYGEN MASK — DAMAGED (COCKPIT) · airframe 23,413 hrs · 18,590 cycles

QUICK DONNING CREW OXYGEN MASK ASSY HEAD HARNESS, BLEW INTERNAL HOSE UPON REMOVAL FROM STOWAGE CONTAINER. DELTA (P/N 59001066) (S/N 40401). REPLACED MASK HOSE ASSY.

Part: CONNECTOR — DISCONNECTED (ROW 29DE)

SEAT MOUNTED EMERGENCY ESCAPE PATH LIGHT AT 29 D/E INOP. RECONNECTED TERMINAL AT FLOOR LIGHT, CKS GOOD.

Part: SKIN — GOUGED (C3 DOORWAY)

TWO GOUGES FOUND ON THE SKIN AND UNDERLYING DOUBLER AT THE AFT EDGE OF THE C3 DOORWAY. REPAIRED PER ERA 332554-14.

Part: SKIN — DENTED (BS 237)

DURING INSP, THE FUSE SKIN WAS FOUND DENTED AT APPROX BS 237, L19L. REPAIRED PER ERA 332546-14.

Part: SKIN — DENTED (BS 351)

A DENT WAS FOUND ON THE FUSE SKIN AT APPROX FS 351 JUST ABOVE L20R. CUTOUT MEASURES APPROX 3.1 BY 3.6. REPAIRED PER ERA 332545-14.

Part: SKIN — DENTED (BS 235)

THE FUSELAGE SKIN WAS FOUND DENTED AT FS 235 AND L17L. RESULTING CUTOUT IS 9 BY 8.75. REPAIRED PER ERA 332547-14.

Part: SKIN — DENTED (BS 218)

THE FUSE SKIN WAS FOUND DENTED AT APPROX 218 JUST BELOW L18L. RESULTING CUTOUT WAS 2.1 BY 5.9. REPAIRED PER ERA 332548-14.

Part: FRAME — CRACKED (BS 1418)

FS 1418 FRAME CRACKED AT L2R. CRACK IS APPROX 2.0625 INCH LENGTH. REPAIRED PER ERA 332541-14.

Part: ENGINE — FAILED (NR 2 ENGINE)

ON T/O, THE NR 2 ENGINE COMPRESSOR STALLED AT APPROX 300 FT ALTITUDE. THE N1 SPEED WENT TO ZERO AND THE ENGINE WAS SHUT DOWN. FLT RETURNED TO BTR. OPERATIONS REPORTED TURBINE PARTS WERE FOUND ON THE RUNWAY NR 2 ENGINE CHANGE IS IN PROGRESS.

Part: STRUT — REQD SERVICED (NLG)

NOSE GEAR UNSAFE LIGHT ON WITH GEAR HANDLE UP, EXCESSIVE WIND NOISE FROM GEAR PROBLEM. RESERVICED NOSE GEAR, JACKED A/C, RAN GEAR 10 TIMES AND GEAR OPERATION NORMAL.

Part: STRUT — REQD SERVICE (NLG)

AFTER TAKEOFF, GEAR WOULD NOT RETRACT, USED REL, GOT MAINS UP, NOT NOSE GEAR, A/C STAYED IN GROUND MODE. RETURNED PHL. LANDED UNEVENTFULLY, NOSE GEAR STEERABLE. SERVICED NOSE STRUT PER MM 32 21 02. CYCLED NOSE GEAR, OPS NORMAL.

Part: ANGLE — CRACKED (WW KEEL BEAM)

KEEL BEAM AFT ANGLE (W/W AFT JAMB) CRACKED RT SIDE. FOUND DURING C-2 LTR CK TPAMM. REPAIRED PER SRM 53-05, FIG 101.