N947DL

Part: NOSE COWL — DELAMINATED (NR 2 ENGINE) · airframe 74,683 hrs · 55,752 cycles

NR 2 ENG NOSE COWL HAS DELAMINATED AT 12 O'CLOCK POSITION, CARBON FIBER PEELING AWAY. REMOVED AND REPLACED NR 2 ENG NOSE COWL PER AMM 71-10-01.

Part: SMOKE DETECTOR — MALFUNCTIONED (LAVATORY) · airframe 74,664 hrs · 55,734 cycles

FIRST CLASS LAVATORY SMOKE DETECTOR ACTIVATED AT THE GATE. NO SMOKE OR ODORS NOTED. R & R THE SMOKE DETECTOR. OPS NORMAL.

Part: SUPPORT FITTING — DAMAGED (RT MLG) · airframe 74,500 hrs · 55,593 cycles

RT MLG RETRACT MECHANISM SUPPORT FITTING BUSHINGS DAMAGED AND PIN WORN. REPLACED RT MLG RETRACT MECHANISM SUPPORT FITTING PER AMM 57-40-02.

Part: LOCK — MISSING (SEAT 24E) · airframe 72,967 hrs · 54,407 cycles

INSPECTED ALL SEATS IN THE VICINITY OF OVERWING EXIT IAW AMM 25-23-00-201. FOUND SEAT 24E MISSING CLIP ON RECLINE ACTUATOR ALLOWING SEAT TO BLOCK EXIT DOOR. REINSTALLED ACTUATOR LOCKING CLIP. SEAT NOW LOCKED IN UPRIGHT POSITION. ALL OTHER SEATS IN THE EXIT ROWS CHECKED NORMAL. OK FOR SERVICE.

Part: WARNING SYSTEM — FALSE ACTIVATION (COCKPIT) · airframe 72,241 hrs · 53,805 cycles

DIV TO BHM DUE TO NO 2 ENGINE OIL STRAINER CLOGGED MESSAGE CAUSING ENGINE TO REMAIN AT IDLE. ENGINE WAS NOT SHUT DOWN. CONTRACT MAINTENANCE REMOVED FILTER AND CONFIRMED CLEAN. REMOVED FILTER AND FOUND CLEAN. REPLACED FILTER AND FORWARDED INDICATION TO MEL 79-00-05.

Part: DOOR FRAME — CRACKED (EMERGENCY EXIT) · airframe 71,948 hrs · 53,581 cycles

OVERWING EMERGENCY EXIT DOOR CRACKED ON THE DOOR FRAME. THE DOOR FRAME WAS REPAIRED IAW SRM 53-05, PAR 42, FIG. 32.

Part: SKIN — DENTED (BS 645-646) · airframe 71,948 hrs · 53,581 cycles

DENT ON EXTERNAL FUSELAGE SKIN BETWEEN BS 646 - 645, LONGERONS 29L - 29R. THE SKIN WAS REPAIRED IAW ETI-88-17-147, REV 6, AND ER/A 558091-14, REV ORIGINAL.

Part: VANE — WORN (RT WING TE FLAP) · airframe 71,948 hrs · 53,581 cycles

WEAR ON REPAIR DOUBLER OF MIDDLE GUIDE VANE UPPER SURFACE AT RT WING OTBD FLAP. THE GUIDE VANE WAS REPAIRED IAW SRM. 57-03 D, PAR 11.

Part: SKIN — CRACKED (LT WING) · airframe 71,948 hrs · 53,581 cycles

LEFT WING CRACKED TE SKIN HEATER BLANKET. SKIN REPAIRED IAW ER/A 494597-14AD MA, REV A.

Part: DOOR FRAME — CRACKED (RT NLG DOOR) · airframe 71,948 hrs · 53,581 cycles

CRACKED RT NLG DOOR FRAME Y=46. PREVIOUS REPAIR DOUBLER ON RT DOOR FRAME WAS REPLACED IAW SRM 53-05, FIG 110.

Part: DOOR FRAME — CRACKED (NLG) · airframe 71,948 hrs · 53,581 cycles

CRACKED LT NLG DOOR FRAME LBL 46. REPAIRED IAW SRM 53-05, FIG 110.

Part: SKIN — WORN (FUSELAGE) · airframe 71,948 hrs · 53,581 cycles

WORN OUT DOUBLER AND HOUSING OF HOLD OPEN HOOK AT FWD PASSENGER ENTRY DOOR. DOUBLER WAS REPLACED IAW SRM 52-05 FIG 20A. HOUSING WAS BLENDED OUT AND MEASURED IAW SRM 52-01 PAR 3 FIG 1 AND (UT) WAS ACCOMPLISHED ON HOUSING IAW NDT SPM 04-00-07 PAR. 5 FIG.3 (SHEET 1 AND 2).

Part: INTERCOSTAL — CRACKED (PAX DOOR) · airframe 71,948 hrs · 53,581 cycles

CRACKED INTERCOSTAL BETWEEN BEAMS 4 AND 5 BS 175 AT FWD PASSENGER ENTRY DOOR. THE INTERCOSTAL WAS REPLACED IAW SRM 51-30-1, AND SRM 51-30-2.

Part: DOUBLER — WORN (CARGO DOOR) · airframe 71,948 hrs · 53,581 cycles

WORN EXTERNAL PREVIOUS REPAIR DOUBLER AT FWD CARGO DOOR AFT LOWER CORNER. REPLACED IAW ER/A 486624-14MA, REV ORIGINAL.

Part: BEAM — CRACKED (PAX DOOR) · airframe 71,948 hrs · 53,581 cycles

CRACKED FWD END OF BEAM NR 2 AT FWD PASSENGER DOOR. THE BEAM WAS REPAIRED IAW SRM 52-05, REPAIR 69, FIGURE 84.

Part: FILTER — CLOGGED (ENGINE OIL) · airframe 71,801 hrs · 53,485 cycles

.WHILE DESCENDING THROUGH 8,000 FEET, RECEIVED A RT ENGINE OIL STRAINER CLOG LIGHT. PERFORMED QRH, OPERATED RT ENGINE UNTIL LANDING. REPLACED THE ENGINE OIL FILTER IAW AMM 79-20. INSPECTION OF FILTER REVEALS CARBON. ODI PREVENTION PARA 3 STEPS A-F.

Part: TRANSDUCER — FAILED (ANTI-SKID SYS) · airframe 71,042 hrs · 52,950 cycles

LEFT INBD ANTI-SKID ON OAP WHEN GEAR EXTENDED. EMERGENCY WAS DECLARED. REPLACED ANTI-SKID TRANSDUCER.

Part: BATTERY PACK — INOPERATIVE (CABIN) · airframe 68,483 hrs · 51,072 cycles

MAINTENANCE FOUND THAT EMERGENCY LIGHTS WOULD NOT ILLUMINATE USING THE F/A TEST SWITCH. BATTERY PACK B5-49 WAS REPLACED AND THE LIGHTS TESTED OK.

Part: LIGHT — INOPERATIVE (CABIN) · airframe 67,421 hrs · 50,353 cycles

DURING LINE CHECK, MAINTENANCE FOUND THAT THE EMERGENCY LIGHTING AT SEAT 21D IN THE CABIN WAS INOPERATIVE. MAINTENANCE REPLACED THE LIGHT ASSEMBLY AND PERFORMED A SATISFACTORY FUNCTIONAL CHECK OF IT.

Part: SKIN — DAMAGED (BS 503-598) · airframe 66,739 hrs · 49,876 cycles

WINDOW BELT AT RT FS 503 - 598 DAMAGED. REPLACED SKIN IAW DWG 5932737-501 AND ER/A 516230-14, REV A.

Part: BRACKET — WORN (TAILCON SLIDE) · airframe 66,739 hrs · 49,876 cycles

DURING INSPECTION, DISCOVERED THAT THE EMERGENCY ESCAPE SLIDE IN THE TAILCONE WAS NO LONGER IN AN ACCEPTABLE CONFIGURATION. THE HOLD DOWN BRACKETS SHOW HOLES FOR LOCKING WIRE TO BE WORN OUT. AN OUT OF POSITION, MISRIGGED, POOR CONDITION, OR ILL-ARRANGED SLIDE ASSEMBLY COULD PREVENT PROPER DEPLOYMENT OF THE ESCAPE SYSTEM AND IS NOT IN COMPLIANCE WITH 14 CFR, PART 121.703. THE TAILCONE SLIDE RETENTION CLIPS WERE REPLACED AND AN RII WAS COMPLETED SATISFACTORILY. LP 1939205.

Part: BOTTLE — EMPTY (ESCAPE SLIDE) · airframe 66,739 hrs · 49,876 cycles

MAINTENANCE DISCOVERED THAT THE EMERGENCY ESCAPE SLIDE INFLATION BOTTLE AT DOOR 1L WAS DEPLETED OF ITS CHARGE. THIS WOULD PREVENT PROPER DEPLOYMENT OF THE ESCAPE SLIDE AND IS NOT IN COMPLIANCE WITH 14 CFR PART 121.703. THE DOOR SLIDE INFLATION BOTTLE WAS REPLACED.

Part: SLIDE — DISLODGED (L1 DOOR) · airframe 66,133 hrs · 49,476 cycles

PILOT REPORTED SLIDE PACK FELL OUT OF 1L DOOR WHEN OPENED. MAINTENANCE REINSTALLED 1L SLIDE PACK.

Part: SLIDE — DISLODGED (L1 DOOR) · airframe 66,074 hrs · 49,446 cycles

L1 DOOR SLIDE FELL OFF. MAINTENANCE REINSTALLED DOOR SLIDE.

Part: LATCH — WORN (TAILCONE) · airframe 65,990 hrs · 49,378 cycles

RT UPPER TAILCONE LATCH ASSY LOOSE AND WORN AT SLIDER BLOCK. REPAIRED IAW AMM 53-53-02.

Part: LATCH — UNSECURE (TAILCONE) · airframe 65,990 hrs · 49,378 cycles

RIGHT LOWER TAILCONE LATCH ASSY ATTACH HARDWARE MISSING. R & R LOOSE RIVETS IAW SRM 51-30.

Part: LATCH — DAMAGED (TAILCONE) · airframe 65,990 hrs · 49,378 cycles

RIGHT LOWER TAILCONE LATCH ASSY ATTACH HARDWARE MISSING ON 1510 FRAME. REMOVED LATCH, REPLACED LOOSE AND MISSING FASTENERS IAW SRM 51-30-02, INSTALLED LATCH.

Part: BRACKET — WORN (TAILCONE) · airframe 65,990 hrs · 49,378 cycles

LT BRACKET WORN FOR KEVLAR CABLE SPRING ATTACH POINT ON TAILCONE. OBTAINED SHOP PART, MPN 9952641-5 AND DRILLED UP. TREATED AND PRIMED. NEED TO ASSEMBLE PARTS AND INSTALL. REF IPC 53-50. AND DWG 99552641. INSTALLED REF AMM 53-53-02.

Part: MOUNT BRACKET — WORN (TAILCONE) · airframe 65,990 hrs · 49,378 cycles

SUPPORT STRUCTURE AND MOUNT BRACKET ON ACFT FOR RT LOWER TAILCONE LATCH IS WORN AND LOOSE FASTENERS. R & R WORN LATCH, REPLACED LOOSE FASTENERS IAW SRM 51-30.

Part: TAIL CONE — NO TEST · airframe 65,990 hrs · 49,378 cycles

TAILCONE FAILED TO DROP WITH AFT CABIN DOOR RELEASE IAW AMDS 5350-01077-0101, STEP 3, REF L/P'S 1784037, 1783916,1783887 AND 1783832 FOR REPAIRS AND PERFORMED THE AMDS CARD 5350-01077-0101. TAILCONE FUNCTIONAL.

Part: WIRE — DAMAGED (EMERGENCY LIGHTS) · airframe 65,707 hrs · 49,193 cycles

DURING LINE CHECK, MAINTENANCE FOUND THAT THE EMERGENCY LIGHTS AT SEATS 12DE AND 20DE WERE INOPERATIVE. MAINTENANCE REPLACED THE WIRE HARNESS AT 12DE AND REPLACED THE PIGTAIL ASSEMBLY AT 20DE. THE SYSTEM RETURNED TO NORMAL OPERATION.

Part: WIRE HARNESS — INTERMITTENT (EMERGENCY LIGHTS) · airframe 65,280 hrs · 48,880 cycles

DURING CHECK, MAINTENANCE FOUND THAT SEAT 30D EMERGENCY PATH LIGHT WAS INTERMITTENT. MAINTENANCE REPLACED THE LIGHT HARNESS AND THE OPS CHECK WAS GOOD.

Part: BATTERY PACK — INOPERATIVE (EMERGENCY LIGHTS) · airframe 64,345 hrs · 48,204 cycles

DURING LINE CHECK, MAINTENANCE FOUND THE AFT CEILING OVERHEAD EXIT EMERGENCY LIGHTS WERE INOPERATIVE. MAINTENANCE REPLACED THE BATTERIES IN THE POWER SUPPLY AND THE LIGHTS RETURNED TO AN OPERATIONAL STATE.

Part: BATTERY PACK — INOPERATIVE (EMERGENCY LIGHTS) · airframe 63,962 hrs · 47,960 cycles

PILOTS FOUND THAT THE EMERGENCY LIGHTING IN THE COCKPIT WAS INOPERATIVE. MAINTENANCE REPLACED THE BATTERIES. OPS CHECKED GOOD.

Part: CONNECTOR — INOPERATIVE (EMERGENCY LIGHT) · airframe 63,865 hrs · 47,901 cycles

AFT AIR STAIR EMERGENCY LIGHTS ARE OUT AT THE AFT LIGHT ASSY. REINSTALLED CONNECTOR. OPS CHECKED GOOD.

Part: POWER SUPPLY — WEAK (EMERGENCY LIGHTS) · airframe 63,597 hrs · 47,714 cycles

DURING LINE CHECK, MAINTENANCE FOUND THAT THE EMERGENCY LIGHTS AT BOTH FORWARD OVERWING EXITS WERE TOO DIM TO PROVIDE ESCAPE GUIDANCE. MAINTENANCE REPLACED THE BATTERIES, POWER SUPPLY AND THE LIGHTS RETURNED TO AN OPERATIONAL CONDITION.

Part: POWER SUPPLY — INOPERATIVE (EMERGENCY LIGHTS) · airframe 62,631 hrs · 47,027 cycles

DURING LINE CHECK, MX FOUND THAT THE OVERHEAD EMERGENCY PATHWAY LIGHTING FOR THE CATWALK IN THE TAIL COMPARTMENT WAS INOPERATIVE. MX REPLACED THE POWER SUPPLY AND THE LIGHTS RETURNED TO AN OPERATIONAL CONDITION.

Part: SKIN — DAMAGED (BS 769-788) · airframe 62,210 hrs · 46,732 cycles

LIGHTNING STRIKE ON LT WINDOW BELT BS 769 AND 788 AT FWD LOWER CORNER. DUE TO DAMAGE IT IS OUT OF LIMITS AREA WAS REPAIRED IAW ER/A 514806-14, REV. ORIG.

Part: LONGERON — CORRODED (BS 1287-1309) · airframe 62,210 hrs · 46,732 cycles

CORROSION ON LONGERON 24L BETWEEN BS 1287-1309 IN AFT CARGO COMPARTMENT. CORROSION WAS REMOVED IAW SRM 51-10-3, PAR 26. AREA FOUND OUT OF LIMITS. LONGERON REPLACED BETWEEN BS 1279 TO 1301 IAW SRM 53-02, FIG 18.

Part: WINDOW FRAME — CRACKED (BS 541-560) · airframe 62,210 hrs · 46,732 cycles

CRACK ON THE FWD LOWER CORNER AT CABIN WINDOW CUTOUT BETWEEN BS 541 - 560 RT SIDE. REPAIR WAS ACCOMPLISHED IAW AMR 09531242, REV 1, AND ER/A 516230-14, REV ORIG.

Part: BULKHEAD — DAMAGED (BS 1338) · airframe 62,210 hrs · 46,732 cycles

DAMAGE ON AFT PRESSURE BULKHEAD TEE CAP BS 1338 BETWEEN LONGERONS 25 TO 30 LT. DUE TO DAMAGE ON AREAS THAT ARE NOT ALLOWED IAW SRM 53-05, FIG 115, TEE CAP REPLACED, NEW TEE CAP INSTALLED IAW SRM 51-10-4, 51-10-3 PAR 26 AND 14 AND SRM 51-30-1, 51-30-2, AND 51-30-5.

Part: SKIN — CRACKED (BS 1418) · airframe 62,210 hrs · 46,732 cycles

CRACKED FUSELAGE SKIN BS 1418 BETWEEN LONG 2-3L. REPAIR WAS ACCOMPLISHED IAW ER/A 516238-14AD, REV ORIGINAL.

Part: LONGERON — CRACKED (BS 1437) · airframe 62,210 hrs · 46,732 cycles

CRACKED LONGERON 13LT BS 1437. DAMAGE SECTION WAS REMOVED, NEW LONGERON AND SPLICE INSTALLED IAW SRM 53-02, FIG 18.

Part: LONGERON — CRACKED (BS 1418 L2R) · airframe 62,210 hrs · 46,732 cycles

CRACKED LONGERON 2RT ON BS 1418. DAMAGE SECTION OF LONGERON REMOVED, NEW LONGERON INSTALLED IAW SRM 53-02, FIG 18 51-10-3.

Part: DOOR FRAME — CORRODED (BS 1174) · airframe 62,210 hrs · 46,732 cycles

CORROSION ON LOWER DOOR FRAME BS 1174. REPAIR PARTS WAS FABRICATED, TREATED, PAINTED, AND INSTALLED IAW SRM 51-10-3, PAR 21 AND 14 53-05, FIG 123.

Part: LONGERON — DAMAGED (BS 1418) · airframe 62,210 hrs · 46,732 cycles

MISDRILLED LONGERON 1RT BS 1418. DAMAGE LONGERON WAS REMOVED NEW LONGERON AND SPLICE WERE INSTALLED IAW SRM 53-02, FIG 18, SRM 51-10-3 PAR 21/14.

Part: DOUBLER — CORRODED (BS 1311-1321) · corrosion level 2 · airframe 62,210 hrs · 46,732 cycles

CORROSION ON INNER PRODUCTION DOUBLER, BS 1311-1316 BETWEEN L21-22L, BS 1319-1321 BETWEEN L21-22L AND BS 1313-1314 BETWEEN L22-23L AT AFT CARGO COMPARTMENT LT UTILITY TUNNEL. DUE TO EXCESSSIVE DAMAGE AREAS WERE REPAIRED IAW ER/A 516225-14 REV ORIG (UT) WAS ACCOMPLISHED. AREAS OUT OF LIMITS IAW SRM 53-01, FIG 1.

Part: SKIN — DAMAGED (BS 617-636) · airframe 62,210 hrs · 46,732 cycles

LIGHTNING STRIKE ON RT WINDOW BELT FRAME BETWEEN BS 617-636 AT AFT UPPER CORNER. DAMAGE OUT OF LIMITS. REPAIRED IAW AMR 09531244, REV 1 AND ER/A 516219-14, REV ORIG.

Part: SKIN — DAMAGED (RUDDER) · airframe 62,210 hrs · 46,732 cycles

DAMAGED METALLIZED ON BOTH SURFACES OF RUDDER. RUDDER REPAIRED IAW 51-70-1A, PAR 27.

Part: CUSP WEB — CORRODED (BS 1083) · corrosion level 2 · airframe 62,210 hrs · 46,732 cycles

CRACKED ON LEFT CUSP WEB, BS 1083 BETWEEN X=54-60 AT FLOOR CABIN STRUCTURE. REMOVED PARTS IAW SRM 51-30-2 AND 51-30-5 REPAIR PARTS WERE INSTALLED IAW SRM 53-05, FIG 131. REPAIR WAS IDENTIFIED IAW PS 900-5-1 NR 04 FASTENERS WERE INSTALLED IAW SRM 51-30-2 AND 51-30-5, CORROSION LEVEL: 2.

Part: LONGERON — CRACKED (BS 1287 L12L) · airframe 62,210 hrs · 46,732 cycles

CRACKED LONGERON 12L BS 1287. DAMAGE SECTION OF LONGERON WAS REMOVED AND NEW SECTION OF LONGERON WAS INSTALLED IAW SRM 53-02, FIG 18, SRM 51-10-3, 51-10-4, 51-30-2, AND 51-30-5.

Part: CUSP WEB — CORRODED (FUSELAGE) · corrosion level 2 · airframe 62,210 hrs · 46,732 cycles

CORROSION ON RT CUSP WEB PREVIOUS REPAIR DOUBLER, X=-54 TO X=-60 BETWEEN STA Y=1198 TO 1202 PAX CABIN. REF 190, ZONE 58 (T0 284266). CORROSION ON PREVIOUS REPAIR DOUBLER WAS REMOVED, NEW REPAIR DOUBLER WAS FABRICATED AND INSTALLED IAW SRM 51-10-3 PAR 14, 21, 38, AND 51-30-5.

Part: LONGERON — CRACKED (BS 160 L3L) · airframe 62,210 hrs · 46,732 cycles

CRACKED LONGERON 3L BS 160 AT PAX CABIN. CRACKED LONGERON WAS TRIMED OUT AND NEW LONGERON AND SPLICE WERE INSTALLED IAW SRM 53-02, FIG 18 AND SRM 51-30-2, 51-30-5. RII COMPLETED FOIM 200802821, AM 761273 DELTA ID.

Part: SEAT TRACK — CORRODED (CABIN) · corrosion level 2 · airframe 62,210 hrs · 46,732 cycles

CORROSION ON LEFT SEAT TRACK X=22 BETWEEN STA Y=1286 TO1295 PAX CABIN. DAMAGE AREA WAS CUTOUT AND NEW INSTALLED AND IDENTIFIED AREA AND APPLIED CIC. IAW SRM 51-10-3, PAR 14, 21, 26, 38, 51-30-1 PS-900-5-1 NR 04.

Part: LONGERON — CRACKED (BS 1437) · airframe 62,210 hrs · 46,732 cycles

CRACKED LONGERON 12L ON BS 1437. DAMAGE LONGERON WAS REMOVED, NEW LONGERON SECTION WAS INSTALLED IAW SRM 53-02, FIG 18, 51-10-3 PAR 21/14.

Part: LONGERON — CRACKED (BS 160 L2L) · airframe 62,210 hrs · 46,732 cycles

CRACKED LONGERON 2L BS 160 AT PAX CABIN. CRACKED LONGERON WAS TRIMED OUT AND NEW LONGERON SPLICE WERE INSTALLED IAW SRM 53-02, FIG 18, SRM 51-30-2, 51-30-5.

Part: WEB — CORRODED (BS 826-845) · corrosion level 2 · airframe 62,210 hrs · 46,732 cycles

CORROSION ON PREVIOUS REPAIR DOUBLER STA Y=826-845, BETWEEN X=54-60. WEB WAS REMOVED AND NEW WEB WAS INSTALLED IAW SRM 51-10-4, 51-30-2, 51-30-5. (LP #0941206)

Part: LONGERON — CRACKED (BS 1287) · airframe 62,210 hrs · 46,732 cycles

CRACKED LONGERON 12L AT BS 1287. DAMAGE SECTION OF LONGERON WAS REMOVED AND NEW SECTION INSTALLED IAW SRM 53-02, FIG 18, SRM 51-10-3, 51-10-4, 51-30-2, AND 51-30-5.

Part: LONGERON — CRACKED (BS 750) · airframe 62,210 hrs · 46,732 cycles

CRACK ON LONGERON 1 BS 750. REPLACED IAW SRM 53-02, FIG 18 AND 51-30-2, 51-31-5.

Part: LONGERON — DAMAGED (BS 308) · airframe 62,210 hrs · 46,732 cycles

MISDRILLED LONGERON 2L BS 308 AT PAX CABIN. DAMAGE SECTION WAS REMOVED FROM BS 282 - 320 IAW SRM 51-30-2 AND 51-30-5. NEW LONGERON AND SPLICES WERE INSTALLED IAW SRM 53-02- FIG18, 51-10-3 PAR 14 AND 21, 51-30-2.

Part: LONGERON — CRACKED (BS 1193) · airframe 62,210 hrs · 46,732 cycles

CRACKED LONGERON 9R AT INTERSECTION WITH FRAME BS 1193 PAX CABIN. DAMAGE SECTION LONGERON WAS REMOVED, NEW SECTION LONGERON AND SPLICE WERE INSTALLED AND IDENTIFIED IAW SRM NR51-30-2, NR51-30-5, NR51-10-4, NR 53-02-FIG 18, NR PS 900-5-1 NR 4.

Part: LONGERON — CRACKED (BS 160) · airframe 62,210 hrs · 46,732 cycles

CRACKED LONGERON NR 4L BS 160 AT PAX CABIN. LONGERON REPLACED IAW SRM 53-02 FIG 18 AND 51-30-2, 51-30-5.

Part: LONGERON — DAMAGED (BS 375) · airframe 62,210 hrs · 46,732 cycles

IMPROPER HOLE ON LONGERON 4L BS 375 AT PAX CABIN. LONGERON DAMAGE WAS CUT OUT, NEW LONGERON SECTION WAS FABRICATED AND INSTALLED IAW SRM 53-02, FIG 18 AND SRM 51-10-3 PAR 14, 21.

Part: LONGERON — CRACKED (BS 1212) · airframe 62,210 hrs · 46,732 cycles

CRACKED LONGERON 9L AT INTERSECTION WITH FRAME, BS 1212 PAX CABIN. SECTION LONGERON FROM BS 1203-1222 WAS REMOVED IAW SRM 53-02 AND PRODUCTION SPLICE WAS REMOVED IAW SRM 51-30-5 AND 51-30-2 NEW LONGERON AND SPLICE WERE TRIMMONT AND INSTALLED IAW SRM 53-02 AND 51-30-5 AND 51-30-2 RII COMPLETED.

Part: SKIN — CORRODED (BS 864-886) · corrosion level 2 · airframe 62,210 hrs · 46,732 cycles

CORROSION ON PREVIOUS REPAIR DOUBLER BETWEEN BS 864 TO 886 X=54-60. REPAIR DOUBLERS WERE REPLACED IAW SRM 53-05, FIG 131A, WAS REMOVED AND WAS INSTALLED.

Part: FUSE — FAILED (EMERGENCY LIGHTS) · airframe 62,168 hrs · 46,708 cycles

DURING LINE CHECK, MX FOUND THAT THE FLOOR TRACK EMERGENCY PATHWAY LIGHTING IN ROWS 31 AND AFT IN THE CABIN WERE INOPERATIVE. MX REPLACED A FAILED FUSE IN THE POWER SUPPLY. OPS CHECK WAS GOOD.

Part: POWER SUPPLY — INOPERATIVE (EMERGENCY LIGHTS) · airframe 61,980 hrs · 46,565 cycles

DURING LINE CHECK, MX FOUND THAT THE EMERGENCY PATHWAY LIGHTING IN THE AFT ROWS OF THE CABIN WERE INOPERATIVE. MX REPLACED THE POWER SUPPLY AND THE LIGHTS RETURNED TO AN OPS CONDITION.

Part: BATTERY PACK — INOPERATIVE (EMERGENCY LIGHT) · airframe 61,940 hrs · 46,534 cycles

DURING LINE CHECK, MX FOUND THAT THE EMERGENCY PATHWAY LIGHTING IN ROWS 31-36 OF THE CABIN WERE INOPERATIVE. MX REPLACED THE BATTERIES AND CHARGER ASSY. OPS CHECK WAS GOOD.

Part: BATTERY PACK — INOPERATIVE (EMERGENCY LIGHT) · airframe 61,906 hrs · 46,505 cycles

DURING LINE CHECK, MX FOUND THAT THE EMERGENCY PATHWAY LIGHTING IN ROWS 31-36 OF THE CABIN WERE INOPERATIVE. MX REPLACED THE BATTERIES IN THE POWER SUPPLY AND THE LIGHTS RETURNED TO AN OPS CONDITION.

Part: LIGHT — INOPERATIVE (CABIN) · airframe 61,857 hrs · 46,473 cycles

DURING LINE CHECK, MX FOUND THAT THE EMERGENCY PATHWAY LIGHTING IN ROWS 31-36 OF THE CABIN WERE INOPERATIVE. MX REPLACED THE FUSE AND THE BATTERY PACK. ALSO, INSPECTED THE WIRE HARNESS AND THEN FUNCTIONALLY CHECKED THE SYS.

Part: CONNECTOR — LOOSE (EMERGENCY LIGHT) · airframe 61,152 hrs · 46,015 cycles

DURING LINE CHECK, MX FOUND THAT THE EMERGENCY PATHWAY LIGHTING IN THE VENTRAL STAIRWAY WERE INOPERATIVE. MX FOUND A LOOSE CONNECTOR, RESECURED THE CONNECTOR AND THE SYS RETURNED TO NORMAL OPERATION.

Part: BATTERY PACK — DISCHARGED (EMERGENCY LIGHTS) · airframe 60,117 hrs · 45,284 cycles

DURING LINE CHECK, MAINTENANCE FOUND THAT THE EMERGENCY PATHWAY LIGHTING FOR THE FORWARD OVERWING EXITS IN THE CABIN WERE TOO DIM TO PROVIDE ESCAPE GUIDANCE. MAINTENANCE REPLACED THE BATTERIES IN THE BATTERY PACK AND THE LIGHTS RETURNED TO AN OPERATIONAL CONDITION.

Part: FLOOR SUPPORT — CORRODED (FUSELAGE) · airframe 57,930 hrs · 43,796 cycles

MAIN CABIN STA 200 LBL 16 TO RBL 44 HAS CORROSION. FABRICATED MAIN CABIN FLOOR SUPPORT IN REF TO DC-9/ MD-80 SRM 53-14-1 PG 29 49 AND DC9/MD80 SRM 51-10-4 PG 1. INSTALLED FLOOR SUPPORT ANGLE STA 200 LBL 16 TO RBL 44 IAW MD80 SRM 51-30-20 PG 29-30 AND SRM 51-30-5 PG 12. AT SAA/SAT DURING HMV ON N/R 184846 W/O 88822390001.

Part: MEMBRANE — DAMAGED (FUSELAGE) · airframe 57,930 hrs · 43,796 cycles

MAIN CABIN SUB FLOOR MEMBRANE HAS CORROSION AND IS CRACKED AT FASTENERS HOLE AT B STA 218 APPROX AND LBL 44 AS MARKED. FABRICATED REPAIR DOUBLER AND FILLER PER SRM MD 80 51-70-4 FIG 2. INSTALLED REPAIR DOUBLER AND FILLER PER SRM MD 51-70-4 FIG 2. AT SAA/SAT DURING HMV ON N/R 183111 W/O 88822290001.

Part: WEB — CORRODED (FUSELAGE) · airframe 57,930 hrs · 43,796 cycles

FWD CABIN FLOOR WEB CORRODED AND CRACKED STA 200 RBL 6. FAB REPAIR DOUBLER IAW DC9 SRM 53-01 PG 25 FIG 4 AND INSTALLED IAW DC9 SRM 51-30-2 PG 1.

Part: FLOOR SUPPORT — CORRODED (FUSELAGE) · airframe 57,930 hrs · 43,796 cycles

MAIN CABIN SUPPORT STA 200 FROM LBL 16 TO RBL 22 HAS CORROSION. REMOVED AND REPLACED FLOOR SUPPORT IAW DC90 SRM 51-30-5 PG 12.

Part: FLOOR SUPPORT — CORRODED (FUSELAGE) · airframe 57,930 hrs · 43,796 cycles

CABIN FLOOR SUPPORT CORROSION STA 180 LBL 38. INSTALLED FLOOR SUPPORT ANGLE IAW DC9 SRM 51-30-5 PG 12.

Part: FLOOR SUPPORT — CORRODED (FUSELAGE) · airframe 57,930 hrs · 43,796 cycles

MAIN CABIN FLOOR SUPPORT LBL 55 STA 190-200 CORROSION. FAB SUPPORT LBL 55 STA 190-200 IAW DC9 / MD 80 SRM 53-14-1 PG 29 AND INSTALLED PER IAW DC9 SRM 51-30-5 PG 12.

Part: FLOOR SUPPORT — CORRODED (FUSELAGE) · airframe 57,930 hrs · 43,796 cycles

MAIN CABIN FLOOR SUPPORT AT LBL 44 FROM STA 160 TO 200 CORRODED. FABRICATED FLOOR SUPPORT ANGLE IAW DC9/MD80 SRM 53-14-1 FIG 11 SHEET 1-2 PG 27-29. INSTALLED FLOOR SUPPORT ANGLE AT LBL 44 STA 160-200 IAW DC9/MD80 SRM 51-50-5 PG 12. AT SAA/SAT DURING HMV ON N/R 184843 W/O 88822420001.

Part: FLOOR SUPPORT — CORRODED (FUSELAGE) · airframe 57,930 hrs · 43,796 cycles

FLOOR SUPPORT PANEL AT LBL 7 AND RBL 7 STA 168 TO 200 ARE CORRODED. INSTALLED 2 EA REPLACED SUPPORT ANGLES IAW MD80 SRM 51-30-5 PG 12 PAR 7.

Part: MEMBRANE — CORRODED (FUSELAGE) · airframe 57,930 hrs · 43,796 cycles

MAIN CABIN SUB FLOOR MEMBRANE HAS CORROSION AND CRACKED STA 218 LBL 44. INSTALLED REPAIR DOUBLER AND FILLER PER MD80 SRM 521-70-4 FIG 2.

Part: TRACK — CORRODED (FUSELAGE) · airframe 57,930 hrs · 43,796 cycles

FWD LT CLOSET AT TRACKS EXFOLIATED. REMOVED TRACKS. OK TO LOCATE DRILL FROM P/N 50021 BATCH 0001171620 PER SRM 53-24-0 FIG 4 LBL 44.

Part: SEAT TRACK — CORRODED (FUSELAGE) · airframe 57,930 hrs · 43,796 cycles

FWD LT CLOSET SEAT TRACK EXFOILATED. FABRICATED SEAT TRACK SECTION PEER MD80 SRM 53-05 FIG 4F. INSTALLED SEAT TRACK SECTION STA 218-230 LBL 22 PER SRM MD80 53-05 FIG 4F. AT SAA/SAT DURING HMV ON N/R 190582 W/O 88822060001.

Part: LIGHT — INOPERATIVE (CABIN) · airframe 57,769 hrs · 43,690 cycles

DURING SERVICE CHECK MAINTENANCE FOUND EMERGENCY LIGHT AT ROW 1 CD INOPERATIVE. MAINTENANCE REPLACED LIGHT ASSEMBLY AT SEAT ROW 1CD. OPERATION OF LIGHTS NOW CHECK OK PER AMM 33-53-01.

Part: GENERATOR — FAILED (NR 1 ENGINE) · airframe 57,525 hrs · 43,520 cycles

AFTER LANDING IN ATL WHILE WAITING FOR GATE, LEFT GENERATOR OFF AND A/C CROSS TIE ILLUMINATED. WHILE COMPLETING QRH PROCEDURES LEFT ENGINE FIRE LIGHT ILLUMINATED AIRCRAFT BEHIND SHIP 947 REPORTED SMOKE. CREW ACCOMPLISHED ENGINE FIRE PROCEDURES INCLUDING FIRING BOTH FIRE BOTTLES. MAINTENANCE FOUND UNCONTAINED GENERATOR FAILURE AND EVIDENCEOF FIRE. NUMBER 1 ENGINE CHANGE.

Part: BATTERY PACK — INOPERATIVE (EMERGENCY LIGHTS) · airframe 56,942 hrs · 43,088 cycles

DURING LINE CHECK, MX FOUND OVERWING EMERGENCY EXIT LIGHTS INOPERATIVE (ROWS 24DE AND 25ABC). MX REPLACED BATTERIES. OPS CHECKS GOOD.

Part: SPAR — DAMAGED (VERTICAL STAB) · airframe 55,970 hrs · 42,466 cycles

VERTICAL STABILIZER FRONT SPAR RT CHORD ZFS=52, OVERSIZED HOLES REPAIRED IAW ERA 487648-14 REV A.

Part: SEAL — FAILED (OIL CAP) · airframe 55,529 hrs · 42,187 cycles

FLIGHT CREW DIVERTED ACFT DUE TO SMOKE IN THE CABIN. MX FOUND APU OIL CAP SEAL IN POOR CONDITION WITH OIL ON THE GROUND. MX R & R OIL CAP SEAL AND ACCOMPLISHED OPERATION 5089 DUCT BURN-OUT.

Part: UNKNOWN — ODOR (COCKPIT) · airframe 52,914 hrs · 40,399 cycles

STRONG SMOKE (ELECTRICAL) SMELL OCCURRED IN COCKPIT AND FIRST CLASS WHEN POWER PUSHED UP TO TAXI AFTER ENGINE START. T/S PER M/M 05-50-01-101 INSPECTED FWD AND AFT E/E COMPT I RLY R2-51. INSP BEHIND COCKPIT OVERHEAD PANEL AND RLYS AND C/BS BEHIND FWD FLT ATTENDANT SEAT. CKD APU INLET NO CONTAMINATION CKD C/BS IN OVERHEAD IN F/C CKD OPN OF PACKS USING ENG AND APU OK, RAN ENGS ALL OPN OK. NO SMOKE OR ELECTRICAL SMELL.

Part: SPAR — CRACKED (WING) · airframe 51,293 hrs · 39,339 cycles

FOUND CRACK IN REAR SPAR LOWER CHORD AT O/B FLAP, I/B HINGE. CUT OUT DAMAGED SECTION OF CHORD AND SPLICED IN NEW SECTION. REPAIRED IAW ER/A 471595-14.

Part: STINGER — CORRODED (FUSELAGE) · airframe 50,319 hrs · 38,628 cycles

UPON REMOVAL OF DOME NUT PLATE, FOUND EXFOLIATING CORROSION IN CHANNEL OF S-20R STA 758. REPLACED DAMAGED SECTION OF STRINGER IAW SRM 53-00-03.

Part: LINK — BROKEN (RT NLG DOOR) · airframe 48,055 hrs · 37,177 cycles

AFTER GEAR RETRACTION, EXCESSIVE VIBRATION IN NOSE WHEEL AREA. EXTENDED GEAR AND DECLARED EMERGENCY. VIBRATION CONTINUED AFTER GEAR EXTENSION. FOUND RT NOSE GEAR DOOR LINK BROKEN. REMOVED AND REPLACED RT FWD DOOR LINK PER MM. NOSE GEAR AND DOORS OPERATE NORMAL.

Part: SKIN — CRACKED (BS 1380 L14R) · airframe 47,606 hrs · 36,881 cycles

CRACKED FUSELAGE SKIN AROUND FASTENERS AT STA 1380 LONG 14 RT. REPAIRED PER SRM 53-04D FIG 18 ON N/R T0059314 HMV/GDL.

Part: CUSP WEB — CRACKED (BS 1200) · airframe 47,606 hrs · 36,881 cycles

CRACK ON RT CUSP WEB AT STA =1200. REPAIRED PER SRM 51-70-4 FIG 2. ON N/R T0058357 HMV/GDL.

Part: VANE — DENTED (RT WING TE FLAP) · airframe 47,606 hrs · 36,881 cycles

DAMAGE PREVIOUS REPAIR AND DENTS ON RT WING OUTBD FLAP INBD GUIDE VANE. REPAIRED PER SRM 57-03D PARA 8A FIG 9A.

Part: DOOR FRAME — CORRODED (CARGO DOORWAY) · airframe 47,606 hrs · 36,881 cycles

GALVANIC CORROSION ON FWD CARGO COMPARTMENT DOOR JAMB LOWER BEAM TASK 51-53300. REPAIRED PER SRM 53-05D FIG 804D SHEET 1 ON N/R TOO58462 HMV/GDL.

Part: LONGERON — CRACKED (BS 200 L8R) · airframe 47,606 hrs · 36,881 cycles

CRACK ON LONGERON 8RH STA Y=200. REPAIRED PER SRM 53-02 FIG 18 ON NR T0058590.

Part: LONGERON — CRACKED (BS 1437 L16L) · airframe 47,606 hrs · 36,881 cycles

CRACK ON LONGERON 16 LT STA 1437 IN AFT ACCESORY COMP. REPAIRED PER DRW S910228 ITEM 47 ON HR T0058497.

Part: DOOR FRAME — CRACKED (OVERWING DOOR) · airframe 47,606 hrs · 36,881 cycles

CRACKED AFT DOOR JAMB FRAME ON LT AFT OVERWING DOOR. REPAIRED PER SRM 52-05D FIG 51 ON N/R T0058927 HMV/GDL.

Part: FITTING — CRACKED (DOOR FRAME) · airframe 47,606 hrs · 36,881 cycles

CRACKS ON FWD AND AFT DOOR JAMB CLIPS AT LF FWD OVERWING DOOR. REPLACED CLIPS PER DWG 9957735 ON N/R T0058929 HMV/GDL.

Part: TAB — DENTED (RT ELEVATOR) · airframe 47,606 hrs · 36,881 cycles

DENT AND LIGHTNING STRIKE ON RT ELEVATOR ANTI-FLOAT TAB. REPAIRED PER DRD 55-04D PARA 2D FIG 1 ON N/R T0059182 HMV/GDL.

Part: LONGERON — CRACKED (FUSELAGE) · airframe 47,606 hrs · 36,881 cycles

CRACKED LONGERON 6RH AT STA. Y=927. REPAIRED PER SRM 53-02 FIG 18 ON N/R T0058771 HMV/GDL.

Part: SKIN — CORRODED (BS 244-246) · airframe 47,606 hrs · 36,881 cycles

SURFACE CORROSION ON INNER FUSELUGE SKIN BETWEEN STA 244 AND LONGERONS 29-30 LT. REPAIRED PER DWG 5936434 ON N/R T0059277 HMV/GDL.

Part: FRAME — CRACKED (BS 1416 L6L) · airframe 47,606 hrs · 36,881 cycles

CRACK ON FRAME ANGLE AT STA 1416 CANT LONGERON 6 LT. REPAIRED PER DRAWING 9977858 ITEM 160 ON NR T0058491.

Part: LONGERON — CRACKED (BS 1437 L4L) · airframe 47,606 hrs · 36,881 cycles

CRACK ON LONGERON 4 LH STA 1473. REPAIRED PER SRM 53-02 FIG 18 ON NR T0058494.

Part: RIB — CRACKED (LT WING) · airframe 47,606 hrs · 36,881 cycles

CRACKED RIB ON LT WING OUTBD REMOVABLE TRAILING EDGE. REPAIRED PER SRM 57-01 FIG 3 ON N/R T0058787 HMV/GDL.

Part: LONGERON — CRACKED (FUSELAGE) · airframe 47,606 hrs · 36,881 cycles

CRACK ON LONGERON 4 RH STA Y=522 AND Y=541. REPAIRED PER SRM 53-02 FIG 18 ON NR T0058606.

Part: CUSP WEB — CORRODED (FUSELAGE) · airframe 47,606 hrs · 36,881 cycles

CORROSION ON LEFT CUSP WEB AT STA Y=878, TASK 58-53313. REPAIRED PER ERA 398191MA ON N/R T0058322.

Part: SKIN — DENTED (BS 1193) · airframe 47,606 hrs · 36,881 cycles

TWO SKIN DENTS AT FS 1193 BETWEEN L-29L AND L-30. REPAIRED WITH AN INTERNAL FINGER DOUBLER AND EXTERNAL SKIN DOUBLER. DTA RESTRICTION OF 8000 CYCLE INSPECTION INTERVALS APPLIES TO THIS REPAIR.

Part: CUSP WEB — CORRODED (BS 984-1003) · airframe 47,606 hrs · 36,881 cycles

CORROSION ON LEFT CUSP WEB BETWEEN STA Y=984 AND Y=1003, TASK 58-53313. REPAIRED PER ERA 398191-14MA ON N/R T0058324 HMV/GDL.

Part: LONGERON — CRACKED (BS 1437 L3R) · airframe 47,606 hrs · 36,881 cycles

CRACK ON LONGERON 3RH STA1437. REPAIRED PER SRM 53-02 FIG 18 ON NR T0058495

Part: RIB — CRACKED (RT WING) · airframe 47,606 hrs · 36,881 cycles

CRACKED RT WING OUTBD REMOVABLE TRAILING EDGE RIB. REPAIRED PER SRM 57-01 FIG 3 ON N/R T0058792 HMV/GDL.

Part: SKIN — DAMAGED (TE FLAP) · airframe 47,606 hrs · 36,881 cycles

RT INBD FLAP LOWER SKIN WAS SPLICED BETWEEN XIFO 47.5 AND XIFO 99.5. THIS 43" SPLICE WAS A HOT BONDED REPAIR PER MD88 SRM 51-70-2 PAR. 18.B. THIS REPAIR WAS DUE TO A TIME-LIMITED SRM REPAIR TO THE SKIN.

Part: FITTING — CORRODED (CARGO DOOR FRAME) · airframe 47,606 hrs · 36,881 cycles

GALVANIC CORROSION ON AFT CARGO COMPARTMENT DOOR JAMB LOWER BEAM. TASK 51-53300. REMOVED AND REPLACED IAW DWG 5936038 ON N/R T0058464 HMV/GDL.

Part: FITTING — CRACKED (DOOR FRAME) · airframe 47,606 hrs · 36,881 cycles

CRACK ON AFT UPPER DOOR JAMB AT RT FWD OVERWING DOOR. CLIP REPLACED PER DWG 9957735 ON N/R T0058935 HMV/GDL.

Part: SKIN — DENTED (BS 215) · airframe 47,606 hrs · 36,881 cycles

A DENT AND A CREASE WAS REPAIRED WITH A DOUBLER. THE DOUBLER WAS INSTALLED AT FS 215 BETWEEN L-29R AND L-30. THIS REPAIR IS NEAR THE JACK POINT SUPPORT AND THE ATC TRANSPONDER ANTENNA FINGER DOUBLER. DTA REQUIRES A INSPECTION EVERY 8000 CYCLES.

Part: CUSP WEB — CORRODED (FUSELAGE) · airframe 47,606 hrs · 36,881 cycles

CORROSION ON CUSP WEB IN PASSENGER CABIN AT STA Y-589. REPAIRED PER EA 398191-14MA ON N/R T0058363 HMV/GDL.

Part: CUSP WEB — CORRODED (BS 513) · airframe 47,606 hrs · 36,881 cycles

CORROSION ON CUSP WEB IN PASSENGER CABIN AT STA Y=513 TASK 58-53313. REPAIRED PER ERA 398191-14MA ON NR T0058366 HMV/GDL.

Part: CUSP WEB — CORRODED (FUSELAGE) · airframe 47,606 hrs · 36,881 cycles

CORROSOIN ON CUSP WEB IN PASSENGER CABIN BETWEEN STA Y=1071-1098 TASK 58-53313. REPAIRED PER ERA 398191-14MA ON N/R T0058367 HMV/GDL.

Part: CUSP WEB — CORRODED (FUSELAGE) · airframe 47,606 hrs · 36,881 cycles

CRACKED LT CUSP WEB AT STA Y=1186. REPAIRED PER ERA 398191-14MA ON N/R T0058897 HMV/GDL.

Part: CUSP WEB — CRACKED (FUSELAGE) · airframe 47,606 hrs · 36,881 cycles

CRACKED RT CUSP WEB AT STA. Y=560. REPAIRED PER ERA 398191-14MA ON N/R T0059229 HMV/GDL.

Part: ENGINE — ACTIVATED (NR 2) · airframe 45,276 hrs · 35,345 cycles

RT ENGINE SLOW TO ACCELERATE. PERFORMED ENGINE ACCELERATION CHECK PER M/M. BOTH ENGINE ACCELERATE WELL WITHIN LIMITS. ENGINE PARAMETERS GOOD.

Part: LINE — CRACKED (HYD SYSTEM) · airframe 43,585 hrs · 34,159 cycles

LEFT HYD SYS PRESSURE AND QUANTITY DROPPED TO ZERO IN FLIGHT. REPLACED HYD SUPPLY LINE TO NUMBER 1 ENGINE HYD PUMP.

Part: OVEN — SMOKE (F/C GALLEY) · airframe 41,752 hrs · 32,821 cycles

F/C OVEN SMOKES EXCESSIVELY WHEN TURNED ON. REPLACED OVEN IN F/C GALLEY. OPS CHECK OK.

Part: TRANSCEIVER — DEFECTIVE (WX RADAR SYS) · airframe 40,012 hrs · 31,622 cycles

AFTER TAKEOFF WEATHER RADAR FAILED. REPLACED RADAR INDICATOR, NO HELP. REPLACED RADAR TRANSCEIVER AND CLEANED COOLING FAN SCREEN. NOW TESTS GOOD.

Part: SWITCH — UNSERVICEABLE (NLG) · airframe 37,776 hrs · 30,129 cycles

ON APPROACH WHEN GEAR HANDLE LOWERED, HAD ONLY TWO MAIN GEAR GREEN LIGHTS - NO NOSE GEAR LIGHT RED OR GREEN. FOLLOWED CHECKLIST WITH GOOD NLG PIN .2500 INCH AND MAINT CONCURANCE SHOWED GOOD GEAR. NOSE GEAR LIGHT REMAINED OFF ENTIRE TAXI UNTIL POWER SWAPPED OVER AT GATE. REMOVED AND REPLACED PROX BOX. NO HELP - REINSTALLED ORIGINAL. REPLACED NOSE GEAR INTERLOCK SWITCH. COMPLETED GEAR SWING. CHECKS OK.

Part: SMOKE DETECTOR — MALFUNCTIONED (LAVATORY) · airframe 37,280 hrs · 29,791 cycles

AFT LEFT LAV SMOKE DETECTOR CHIRPING. REPLACED SAME.

Part: PROBE — FAILED (TAT) · airframe 36,752 hrs · 29,398 cycles

IN FLT CREW REPORTED AUTOPILOT PROBLEM, HAD BOTH DFGCS NOT RESPONDING TO ANY FLT GUIDANCE PANEL IMPUTS AND MSG OF FAIL 26 ON FMAS. THEN REPORTED A LITTLE BURNING ODOR AND DECIDED TO DIVERT TO BHM. REPLACED TOTAL AIR TEMP PROBE. PERFORMED DUCT BURNOUT FOR ODOR.

Part: CABLE — BROKEN (LT GEAR WELL) · airframe 35,483 hrs · 28,477 cycles

DURING APPROACH THE LEFT FLAP INDICATION STUCK AT 0 DEGREES DURING FLAP EXTENSION. A/C ROLLED AND AUTO PILOT DISC A/C FLAP HANDLE RECYCLED AND FLAPS CAME DOWN NORMALLY HOWEVER A/C REQUIRED 2 UNITS OF RIGHT AILERON TRIM FOR REMAINDER OF APPROACH. C/A - INSPECTED AND FOUND FLAP BUS CABLE 34A BROKEN. REMOVEDAND REPLACED FLAP BUS CABLES 34A AND 34B PER OPN 2000 RIGGEDPER M/M OPS CKS GOOD

Part: HYDRAULIC SYSTEM — LEAKING (RT MLG WW) · airframe 34,847 hrs · 28,029 cycles

CREW REPORTED ON FINAL APPROACH WITH PACKS IN FULL COLD GOT SMOKE IN THE CABIN. FOUND HYDRAULIC LEAK IN RIGHT WHEEL WELL. FLUID HAD TRANSITIONED TO APU INLET CONTAMINATING A/C SYSTEM. COMPLIED WITH OPERATIONS 5088 AND 5089 DUCT BURN OUT PROCEDURE. CLEANED INLET.

Part: COVER — DAMAGED (L2 DOOR) · airframe 32,324 hrs · 26,159 cycles

L2 SERVICE DOOR EXIT SIGN WILL NOT STAY ON. FOUND EXIT SIGN COVER DAMAGED REPLACED COVER OK FOR SERVICE

Part: INTAKE DUCT — CONTAMINATED (APU) · airframe 31,428 hrs · 25,487 cycles

INTERMITTENT SMOKE ODOR IN PAX CABIN DURING CRUISE AND DESCENT NEAR MID CABIN AND AFT CABIN - FOUND SMALL AMOUNT OF OIL IN APU INLET - CLEANED SAME - PERFORMED DUCT BURNOUT

Part: SEAL — CUT (RT MLG WW) · airframe 31,097 hrs · 25,251 cycles

RT HYD SYSTEM FAIL, ALTERNATE GEAR EXTEND, AIRCRAFT TOWED TO THE GATE. REPLACED O-RING SEAL AT RT BRAKE PRESS MANIFOLD. LEAK AND OPERATIONAL CHKS OK.

Part: COALESCER BAG — CONTAMINATED (ACM) · airframe 30,681 hrs · 24,952 cycles

AT T/O PUNGENT ODOR REPORTED BY F/A IN REAR CABIN ALONG WITH LAV SMOKE DETECTOR GOING OFF. A/C ATB. PERFORMED DUCT BURNOUT PROCEDURE. CHECKS OK ON POWER RUN.

Part: TRIM TAB — SEIZED (RUDDER)

PRIMARY TRIM INTERMITTENTLY FAILS. REPLACED PRIMARY TRIM ACTUATOR, ALL CKS NORMAL.

Part: HEATER — FAILED (RT FUSELAGE)

SMOKE IN CABIN AT FL230 60KMI OUT OF CVG - RT SIDE OF A/C AT SEAT 11E. FOUND EVIDENCE OF INSULATION FIRE DUE TO FAULT WITH ALT STATIC PORT HEATER OR ASSOCIATED WIRING.

Part: APU — INOPERATIVE (AUX)

AT 24,000 FT ON CLIMBOUT, A SLIGHT HAZE APPEARED IN THE CABIN AND BOTH AFT SMOKE DETECTORS WENT OFF. APU HAD BEEN OFF FOR 10-15 MINS. LEVELED OFF AND RETURNED TO ATL. PERFORMED DUCT BURNOUT. REPLACED COALESCERS, CLEANED APU INLET.

Part: COALESCER BAG — ICED UP (CABIN)

ON CLIMBOUT, BOTH SMOKE DETECTORS IN AFT LAVS WENT OFF AND SMELL OF HOT AIR ODOR IN CABIN. CABIN SUPPLY TEMP 65 DEGS, BOTH ENG HAD A/I ON. HP OFF, NO HELP. A/I OFF AND TEMP RTN TO NORMAL. REPLACED COALESCER BAGS DUE ICING.

Part: SEAL — OUT OF POSITION (2L DOOR)

ON CLIMBOUT, FLOW LIGHT ILLUMINATED. PRESS VALVE INDICATED FULL CLOSED AND PACKS IN AUTO WITH PRESS 30 PSI EACH. UNABLE TO CONTROL PRESS AND CABIN ALT. CONDUCTED FLT BELOW 10,000 FT, VALVE DID MODULATE ONCE LEVELED OFF. F/A ADVISED DOOR SEALS AT 2L HAD STRONG AIRFLOW ON DESCENT. FOUND SEAL AT 2L OUT OF TRACK. REINSTALLED SAME, PRESS A/C WITH PACK AND OPS NORMAL.

Part: OIL SYST — LEAKING (APU)

WHEN WING ANTI-ICE WAS TURNED ON CABIN TEMP, IT GOT VERY HOT WITH AN ACCOMPANYING SMELL, ALSO SMOKE (LIGHT) THROUGHOUT CABIN WHICH ACTIVATED SMOKE ALARM IN REAR LAV. FOUND APU LEAKING OIL INTO APU. CORRECTED LEAK, PERFORMED BURNOUT.

Part: PACK — FAILED (TAIL)

AT FL 370 LT PACK WENT TO ZERO, TEMP STUCK FULL COLD. LOST CABIN PRESS IN DESCEND. RT PACK HELD ONCE BELOW FL200, PRESS A/C TO 4 PSID. FOUND LT ACM FROZEN, DEFERRED LT PACK TO MCO/PLAC PER MEL 21-00-01A. REPLACED ACM.

Part: BATTERY CHARGER — FAILED (E/E COMP)

AFTER BLOCKING IN AND TRANSFERRING TO EXT PWR, CREW NOTICED BURNING SMELL AND BATTERY CHARGER C/B POPPED. REPLACING BATTERY CHARGER.

Part: STRUT — REQD SERVICE (NLG)

UNSAFE NOSE GEAR AFTER T/O. FOUND NOSE STRUT FLAT. SERVICED, JACKED, CYCLED AND LEAK CHECKED GEAR.

Part: OIL PRESS SW — STICKING (NR 1 ENGINE)

AT FL 180, THE LEFT OIL STRAINER CLOGGING MSG. ON THE O.A.P. ILLUMINATED THEN WENT OFF. THEN, 10 SECONDS LATER, THE LIGHT REILLUMINATED. PER P.O.M., ENGINE STRUT DOWN AND RETURNED TO ATL. CORRECTIVE: CHECKED CHIP DETECTOR. CHECKS GOOD. CHECKED MAIN OIL FILTER, CHECKS GOOD. REPLACED OIL FILTER, LEAK CHECKS GOOD. REPLACED OIL DIFFERENTAL PRESSURE SWITCH PER M/M, CHECKS GOOD. RAN ENG PER P.F.H.B. CHECKS OKAY. NO MRR. REJECTED GT 595.

Part: FRAME — CRACKED (BS 1418)

THE UPPER FLANGE OF THE FUSELAGE FRAME AT FS 1418 AND LONGERON 2L WAS FOUND WITH TWO CRACKS. THE FIRST CRACK IS LOCATED IN THE FRAME RADIUS AND THE SECOND ON THE HORIZONTAL FLANGE PARALLEL TO THE FIRST CRACK. THE DAMAGE WAS TRIMMED OUT AND FILLED PER DAL EO 9-63538-3.

Part: SKIN — DENTED (BS 365-371)

THE FUSELAGE SKIN AT FS 365 TO 371 AND BETWEEN L-19R AND 21R WAS PREVIOUSLY DENTED AND TIME-LIMITED REPAIRED. THE REPAIR WAS REMOVED AND A PERMANENT REPAIR WAS INSTALLED PER DL ERA 273591-14.

Part: SKIN — DENT (BS 237)

THE FUSELAGE SKIN IS DENTED AFT OF FS 237, 5 INCHES ABOVE THE L-18L CUSP. THE DENT IS APPROX .125 INCH DEEP, 4 INCHES LONG, 2.5 INCHES WIDE. THE DAMAGE WAS CUT OUT AND A FILLER AND DOUBLER WAS INSTALLED PER DL ERA 273568-14.

Part: SKIN — DENTED (FS 237)

THE FUSELAGE SKIN WAS FOUND TO BE BADLY DENTED AROUND FS 237 AND BETWEEN 18L AND 20L. THE DENT WAS CUT OUT AND A FILLER AND DOUBLER WAS INSTALLED PER DL ERA 273565.

Part: SUB FLOOR — CRACKED (BS 1300)

LT SUBFLOOR IS CRACKED AT FS 1300. REMOVED OLD SUBFLOOR AT FS 1300, DRILLED UP NEW SUBFLOOR, INSTALLED SUBFLOOR PER SRM 53-05 PG 380.

Part: SKIN — DENTED (RT TE FLAP)

FOUND DURING F-2 LETTER CHECK - DENT FOUND ON UNDERSIDE OF I/B FLAP MEASURING APPROX .50 INCH DIA. REPAIRED PER SRM 57-03, FIG 7.