N940DL

Part: CIRCUIT CARD — DAMAGED · airframe 72,376 hrs · 53,781 cycles

ON LANDING APPROACH FLIGHT ATTENDANT CALL ON LND ROLL OUT + REPORTED ELECTRICAL SMOKE SMELL- PASSENGER ALSO REPORT THIS DURING DEPLANING. ODOR WAS AROUND 2L DOOR AREA. FOUND CONDENSATION DRIPPING ON LED LIGHT ASSY AND CIRCUIT CARD AT L2-674. REPLACED CIRCUIT CARD. SECURED DUCT BOOTS ABOUVE FLIGHT ATTENDANT SEAT TO PREVENT CONDENSATION FROM DRIPPING. SYSYEM CHECKS GOOD.

Part: FRAME — CRACKED (BS 1437) · airframe 72,200 hrs · 53,651 cycles

BS 1437 LONGERON 2L FRAME LOWER CAP CRACKED. REPAIRED IAW ERA 551781-14 REV ORIG.

Part: DUCT — CRACKED (CABIN AIR) · airframe 72,194 hrs · 53,648 cycles

AT FL250 THE "FLOW" LIGHT ILLUMINATED WITH CABIN ALTITUDE RISING. CREW DESCENDED TO 10,000 FEET. CORRECTIVE ACTION: MAINTENANCE FOUND RIGHT SPIDER DUCT CRACKED.

Part: CONTROLLER — FAULTY (CABIN TEMP) · airframe 71,940 hrs · 53,445 cycles

AT FL360, CABIN TEMP WAS REPORTED TOO COLD. RIGHT PACK TEMP CONTROL VALVE WOULD NOT MOVE TO FULL HOT IN AUTO. WORKS OK IN MANUAL. LEFT PACK WOULD NOT GO PAST 3/4 HOT IN AUTO OR MANUAL. CYCLED AIR SUPPLY ON THE LT PACK. RESULT WAS LT PACK FAIL. SINGLE PACK OPERATION AT FL360 RESULTED IN RT PACK FAIL. CABIN OXYGEN MASKS DEPLOYED. DURING DESCENT, RECOVERED BOTH PACKS. REPLACED CABIN TEMP CONTROLLER IAW AMM 21-61. PERFORMED LT AND RT PACK HEALTH CHECKS IAW WORK CARDS 2120-2277 AND 2120-2758. NO DEFECTS NOTED. PERFORMED HULL LEAKAGE DECAY CHECK IAW AMM 21-00-00/501. REPLACED O2 GENERATORS AS NECESSARY ON LP 8936547.

Part: CONNECTOR — UNSECURE (CABIN) · airframe 71,379 hrs · 53,040 cycles

30DE EMERGENCY LIGHT INOPERATIVE. RESECURED PLUG ASSY, OPS CK NORMAL AT THIS TIME.

Part: RADOME — DAMAGED · airframe 70,099 hrs · 52,158 cycles

AT 10,000 ACFT TOOK LIGHTNING STRIKE, SUSPECT RT SIDE RADOME. REPAIRED MULTIPLE LIGHTNING STRIKES RT SIDE FUSELAGE BS 36 THRU BS 408 IAW SRM 53-04.

Part: ANGLE — DAMAGED (AFT BULKHEAD) · airframe 69,599 hrs · 51,787 cycles

DURING INSPECTION OF AFT PRESSURE BULKHEAD LOWER TEE CHORD AFT FLANGE THE 3 DRAIN HOLES WERE FOUND WITH A .3750" DIAMETER. INSPECTION OF THE DRAIN HOLES DOES NOT SHOWN SIGNS OF CRACKS. AFT PRESSURE BULKHEAD LOWER TEE CHORD AFT FLANGE WAS REPLACED IAW ER/A 539895-14, REV ORG, ASSOCIATED AA 5310-01449. ADDED FOR AC 0940. ASSOCIATED ER/A 88-539895 ADDED FOR AC 0940.

Part: FRAME — CRACKED (BS 389) · airframe 69,594 hrs · 51,785 cycles

CRACKED FRAME BS 389 BETWEEN LONGERONS 29 RT AND 28 RT AT FWD CARGO COMPARTMENT. FRAME WAS REPAIRED IAW ER/A 539883-14, REV ORIGINAL.

Part: LANYARD — BROKEN (R1 DOOR SLIDE) · airframe 69,594 hrs · 51,785 cycles

MAINTENANCE DISCOVERED THAT THE EMERGENCY ESCAPE SLIDE AT DOOR 1R HAD A BROKEN LANYARD. THE LANYARD WAS NOT CONNECTED BETWEEN THE GIRT-BAR AND THE SLIDE RELEASE. THIS WOULD PREVENT PROPER DEPLOYMENT OF THE ESCAPE SLIDE AND IS NOT IN COMPLIANCE WITH 14 CFR, PART 121.703. THE DOOR SLIDE LANYARD WAS REPLACED.

Part: ACCESS PANEL — DAMAGED (RT WING) · airframe 69,594 hrs · 51,785 cycles

ELONGATED HOLES ON RT WING ACCESS PANEL 1414C CUT OUT, BELOW RUBSTRIP. THE ACCESS PANEL WAS REPAIRED IAW SRM 51-22-2A, 51-30-2, AND 51-10-3 PAR 21 AND 14.

Part: SKIN — CRACKED (FUSELAGE) · airframe 69,594 hrs · 51,785 cycles

A CRACK WAS FOUND ON THE INNER SKIN, BETWEEN BEAMS NR 6 AND 7 AT THE L1 DOOR. THE SKIN WAS REPAIRED IAW SRM 52-01, FIG 2.

Part: SKIN — CRACKED (BS 1474) · airframe 69,594 hrs · 51,785 cycles

CRACKS FOUND ON FUSELAGE SKIN AT BS 1474 BETWEEN LONGERONS 22 - 23R. REPAIRED IAW IAW SRM 53-01, FIG 2, SH 3.

Part: LONGERON — CRACKED (BS 160) · airframe 69,594 hrs · 51,785 cycles

A CRACK WAS FOUND ON LONGERON 3L, BS 160. THE LONGERON WAS REPAIRED IAW SRM 53-02, FIG 18.

Part: TEE FITTING — CRACKED (R1 DOOR FRAME) · airframe 69,594 hrs · 51,785 cycles

CRACK ON TEE FITTING AT AFT EDGE OF BEAM NR 4 FWD SERVICE DOOR, R-1. THE TEE FITTING WAS REPLACED IAW SRM 51-30-1 AND 51-30-5.

Part: DOOR FRAME — CORRODED (CARGO BAY) · corrosion level 2 · airframe 69,594 hrs · 51,785 cycles

CORROSION ON PREVIOUS REPAIR SPACER ON AFT LWR CARGO COMPARTMENT DOOR JAMB. PREVIOUS REPAIR SPACER WAS REPLACED IAW SRM 53-05, FIG 123, AND SRM 51-30-5.

Part: SEAT TRACK — CORRODED (BS 795) · corrosion level 2 · airframe 69,594 hrs · 51,785 cycles

CORROSION ON LT SEAT TRACK X 22 AND BS 795. THE SEAT TRACK WAS REPAIRED IAW SRM 53-05, FIG F4, 51-10-3, 51-30-2, 51-30-5 AND 51-30-1.

Part: DOUBLER — CORRODED (BS 584-590) · airframe 72,415 hrs · 53,816 cycles

CORROSION ON SPLICE REPAIR DOUBLER BETWEEN BS 584 - 590, LONGERONS 29 - 30R MID CARGO BAY. THE REPAIR SPLICE WAS REPLACED.

Part: DOUBLER — WORN (PAX DOOR) · airframe 69,594 hrs · 51,785 cycles

WEAR ON REPAIR DOUBLER BETWEEN BEAM 6 AND 7 OF PASSENGER DOOR. REPAIR DOUBLER WAS REPLACED IAW SRM 51-30-2.

Part: SEAT TRACK — CORRODED (BS 858) · corrosion level 2 · airframe 69,594 hrs · 51,785 cycles

CORROSION ON PREVIOUS REPAIR PLUG, ON RT SEAT TRACK BS X=-54, Y=858, CFS. PLUG WAS REPLACED IAW SRM 53-05, FIG 4A, SHEET 1.

Part: SEAT TRACK — CORRODED (BS 1259) · corrosion level 2 · airframe 69,594 hrs · 51,785 cycles

HAS CORROSION ON SEAT TRACK PLUG, X=-22 AT BS 1259 RT SIDE. PLUG WAS REPLACED IAW SRM 53-05, FIG 4A.

Part: SEAT TRACK — CORRODED (BS 641-859) · corrosion level 2 · airframe 69,594 hrs · 51,785 cycles

CORROSION FOUND ON SEAT TRACK PLUGS AT X=56, BS 641-859 LT SIDE, THE PLUGS WERE REPLACED IAW SRM 53-05, FIG 4A.

Part: INTERCOSTAL — UNKNOWN · airframe 68,022 hrs · 50,710 cycles

REMOVE AND REINSTALL INTERCOSTAL AT L11 BETWEEN STA 864-845 LT TO FOM. REMOVED AND REINSTALLED L-11 BETWEEN STA. 845 AND STA 864 IAW PRI 533343-14 A, REV O. AWAITING FINAL ERA 533343-14, REV ORIGINAL.

Part: WIRE HARNESS — DAMAGED (EMERGENCY LIGHTS) · airframe 67,681 hrs · 50,473 cycles

MAINTENANCE FOUND THE EMERGENCY LIGHTS AT SEAT 15C TO BE INOPERATIVE. MAINTENANCE REPLACED THE WIRE HARNESS AND THE OPS CHECKED GOOD.

Part: SKIN — GOUGED (BS 233) · airframe 67,026 hrs · 50,026 cycles

DENT WITH A V-SHAPED GOUGE ON A REPAIR DOUBLER, UPPER, AFT 4 CORNERS REPAIR DOUBLER. THE DAMAGE IS LOCATED AT BS 233 BETWEEN LONGERONS 17L AND 18L. THE GOUGE WAS BLENDED SMOOTH IAW SRM 53-04. THE DENT MEASURES 2.50, UP/DOWN X 2.00, FWD/AFT, AND IS A MAXIMUM OF 0.180" DEEP. REPAIRED IAW ER/A 528796-14.

Part: BATTERY PACK — INOPERATIVE (EMERGENCY LIGHTS) · airframe 66,899 hrs · 49,919 cycles

DURING LINE CHECK, MAINTENANCE FOUND THAT THE EMERGENCY EXIT SIGNS AT BOTH OF THE FORWARD OVERWING HATCHES WERE INOPERATIVE. MAINTENANCE REPLACED THE BATTERIES. OPS CHECK WAS GOOD.

Part: BATTERY PACK — INOPERATIVE (EMERGENCY LIGHTS) · airframe 66,446 hrs · 49,594 cycles

DURING LINE CHECK, MAINTENANCE FOUND THAT THE EMERGENCY EXIT SIGN FOR THE FWD RIGHT OVERWING HATCH WAS INOPERATIVE. MAINTENANCE REPLACED THE BATTERIES IN THE POWER SUPPLY AND THE LIGHTS RETURNED TO AN OPERATIONAL CONDITION.

Part: WIRE — BROKEN (EMERGENCY LIGHT) · airframe 65,620 hrs · 49,011 cycles

SEAT ROW 24ED, TWO RED EMERGENCY PATH LIGHTS INOPERATIVE. REPAIRED BROKEN WIRE IAW SWPM 20.

Part: CONNECTOR — DAMAGED (EMERGENCY LIGHTS) · airframe 65,620 hrs · 49,011 cycles

SEAT ROW 28ED WHITE EMERGENCY PATH LIGHT INOPERATIVE. REPLACED WIRE HARNESS CONNECTOR IAW SWPM 20 . OPS CHECKED GOOD.

Part: RELEASE CABLE — FRAYED (TAILCON) · airframe 64,910 hrs · 48,555 cycles

MAINTENANCE DISCOVERED THAT THE TAILCONE EMERGENCY RELEASE CABLE, JUST AFT OF TEE PIN, WAS FRAYED BEYOND ALLOWABLE LIMITS. CABLE WAS REPLACED AND THE SYSTEM WAS RIGGED TO SPECIFICATIONS.

Part: POWER SUPPLY — INOPERATIVE (EMERGENCY LIGHTS) · airframe 64,910 hrs · 48,555 cycles

DURING LINE CHECK, MAINTENANCE FOUND THAT THE EXTERIOR EMERGENCY LIGHTS WERE INOPERATIVE. MAINTENANCE REPLACED THE POWER SUPPLY AND THE LIGHTS RETURNED TO AN OPS CONDITION.

Part: CABLE — OUT OF ADJUST (TAILCONE RELEASE) · airframe 64,910 hrs · 48,555 cycles

DURING THE TAILCONE RELEASE SYSTEM FUNCTIONAL CHECK, MAINTENANCE FOUND THAT THERE WAS EXCESSIVE TENSION OF 25 LBS IN THE RELEASE CABLE SYSTEM. THE CABLE RELEASE MECHANISM WAS ADJUSTED AND THE SYSTEM WAS RIGGED TO PULL AT 19 LBS.

Part: SKIN — CRACKED (BS 1380) · airframe 64,910 hrs · 48,555 cycles

FUSELAGE SKIN CRACKED BS 1380, 3 INCHES ABOVE LONGERON 14R. REPAIRED SKIN CRACK IAW PRI 521072-14, REV ORIGINAL, RECEIVED FINAL ER/A 521072-14, REV ORIG 327360.

Part: SLIDE — MISRIGGED (TAILCONE) · airframe 64,910 hrs · 48,555 cycles

INSPECTION DISCOVERED THAT THE EMERGENCY ESCAPE SLIDE IN THE TAILCONE WAS NO LONGER IN AN ACCEPTABLE CONFIGURATION. A MISRIGGED, IMPROPERLY INSTALLED, NOT HOOKED SLIDE COVER WOULD PREVENT PROPER DEPLOYMENT OF THE ESCAPE SYS AND IS NOT IN COMPLIANCE WITH 14 CFR PART 121.703. THE TAILCONE SLIDE COVER WAS REINSTALLED CORRECTLY AND THE RII WAS COMPLETED SATISFACTORILY.

Part: RELEASE CABLE — FRAYED (TAILCONE) · airframe 64,910 hrs · 48,555 cycles

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

Part: LATCH — WORN (TAILCONE RELEASE) · airframe 64,910 hrs · 48,555 cycles

MAINTENANCE DISCOVERED THAT THE LT LOWER RELEASE LATCH SPADE FOR THE TAILCONE WAS WORN BEYOND ALLOWABLE LIMITS. THE LATCH SPADE WAS REPLACED AND THE SYSTEM WAS RIGGED TO SPECIFICATIONS. THE FUNCTIONAL CHECK WAS COMPLETED SATISFACTORILY.

Part: CAM — WORN (TAILCONE RELEASE) · airframe 64,904 hrs · 48,550 cycles

DURING CHECK, KEVLAR CABLE CAM AT THE TAIL CONE RELEASE MECHANISIM WAS WORN. REPLACED CAM BASE IAW AMM 53-53-02, PB 201.

Part: PIN — LOOSE (TAILCONE RELEASE) · airframe 64,904 hrs · 48,550 cycles

DURING CHECK, KEVLAR CAM PIN LOOSE ON THE TAILCONE RELEASE MECHANISIM. DISASSEMBLED & RETORQUED IAW AMM 53-53-02.

Part: LAMP — INOPERATIVE (EMERGENCY LIGHT) · airframe 64,737 hrs · 48,447 cycles

DURING LINE CHECK, FOUND THE FORWARD OVERWING DOOR EMERGENCY EXIT LIGHT INOPERATIVE. REPLACED LAMPS AND OPS CHECKED NORMAL.

Part: BATTERY PACK — INOPERATIVE (EMERGENCY LIGHTS) · airframe 64,358 hrs · 48,169 cycles

DURING LINE CHECK, MX FOUND THAT THE OVERHEAD EMERGENCY PATHWAY LIGHTING AT ROWS 02-14, 20-24, AND THE OVERWING EXIT SIGN AT ROW 25 WERE ALL INOPERATIVE. MX REPLACED THE BATTERIES IN THE POWER SUPPLY AND THE LIGHTS RETURNED TO AN OPERATIONAL CONDITION.

Part: POWER SUPPLY — INOPERATIVE (EMERGENCY LIGHT) · airframe 63,164 hrs · 47,326 cycles

DURING LINE CHECK, MX FOUND THAT THE OVERWING EMERGENCY EXIT SIGNS AT ROW 24 WERE INOPERATIVE. MX REPLACED THE BATTERIES IN THE POWER SUPPLY AND THE LIGHTS RETURNED TO AN OPS CONDITION.

Part: BATTERY PACK — FAILED (EMERGENCY LIGHT) · airframe 62,648 hrs · 46,956 cycles

DURING LINE CHECK, MX FOUND THAT THE EMERGENCY PATHWAY LIGHTING IN THE COCKPIT HAD FAILED. MX REPLACED BOTH BATTERY PACKS AND THE LIGHTS RETURNED TO AN OPS CONDITION.

Part: CABLE — MISROUTED (TAILCONE) · airframe 61,247 hrs · 45,940 cycles

AT ROTATION, THE CREW NOTED A "TAILCONE UNSAFE" MESSAGE ON THE OVERHEAD ANNUNCIATOR PANEL. ON LANDING, MAINTENANCE DISCOVERED THAT THE TAILCONE INTERNAL RELEASE HANDLE WAS OUT OF POSITION AT THE INTERNAL SWITCH. CABLE WAS REPOSITIONED TO THE CORRECT ROUTING PER THE MAINTENANCE MANUAL. ALL TAILCONE POSITION INDICATIONS NOW CHECK NORMAL AND THE AIRCRAFT HAS RETURNED TO SERVICE.

Part: SKIN — DAMAGED (CENTER WING BOX) · airframe 61,232 hrs · 45,929 cycles

DURING HMV, ELONGATED HOLES WERE FOUND ON CTR WING TANK UPPER AND LOWER SURFACE IN STA Y=938, X=22, AND Z=13 AT WING BOX AREA. HOLES WERE ENLARGED, BUSHINGS INSTALLED AND DOUBLER INSTALLED REF ERA 503291-14 REV ORIG.

Part: DOOR FRAME — CRACKED (FUSELAGE) · airframe 1 hrs · 1 cycles

DURING HMV A CRACK WAS FOUND ON FORWARD UPPER CORNER OF FWD SERVICE DOOR JAMB AT STA Y=175 BTW LONGERON 11 AND 12R. DAMAGE WAS CUT OUT AND DOUBLER INSTALLED IAW SR09530172 REV G.

Part: SKIN — CORRODED (BS 788-791) · airframe 1 hrs · 1 cycles

CORROSION ON FUSELAGE SKIN BELOW RUB STRIP FROM STA Y=791, 788 BTW LONG 28 RT TO 29 RT. REPAIR PER SRM 53-04 FIG 57.

Part: DOOR FRAME — CORRODED (BS 376-382) · airframe 1 hrs · 1 cycles

CORROSION ON SPLICE OF FWD CARGO COMPARTMENT DOOR FRAME FROM STA Y=376-382 AND 417-423. REPAIRED PER ERA 503263- 14 REV A.

Part: TUNNEL WALL — CORRODED (BS 1290 L23-24L) · airframe 1 hrs · 1 cycles

CORROSION ON LONGERON 23 LT AND 24 LT STA Y=1290 AT AFT CARGO COMPARTMENT LT TUNNEL. REPAIRED PER SRM 53-02 FIG 18.

Part: DOOR FRAME — SCRATCHED (R1 DOOR) · airframe 1 hrs · 1 cycles

SEVERAL SCRATCHES ON R1 DOOR JAMB INTERNAL PANEL APPROXIMATELY STA Y=170 BTW LONG 18RH-19 RT. REPAIRED PER SRM 53-05 FIG 55.

Part: SKIN — CORRODED (FUSELAGE) · airframe 61,232 hrs · 45,929 cycles

CORROSION ON FUSELAGE SKIN BELOW RUB STRIP FROM STA Y=791,788 BETWEEN LONGERON 28 RT TO 29 RT. DOUBLER REPAIR ACCOMPLISHED IAW DC9/MD80 SRM 53-04 FIG 57.

Part: LONGERON — CORRODED (FUSELAGE) · airframe 61,232 hrs · 45,929 cycles

CORROSION ON LONG 23 LT AND 24 LT STA Y=1290 AT AFT CARGO COMPARTMENT LT TUNNEL. LONG 23 LT WAS REPLACED IAW DC9/MD80 SRM 53-02 FIG 18.

Part: PLATE — SCRATCHED (VERTICAL STAB) · airframe 61,232 hrs · 45,929 cycles

SCRATCHES ON INBD PLATES LOCATED ZRS=178 AND XH=5.5 AT VERTICAL STABILIZER. HOLES ON INBD PLATES WERE REAMED IAW SRM 55-02 PAR 24 B1. REPAIR BUSHINGS FABRICATED IAW SRM 55-02 PAR24C.

Part: SKIN — CRACKED (FUSELAGE) · airframe 61,232 hrs · 45,929 cycles

A CRACK OF 0.656 ON LT FUSE SKIN AT STA Y=1417 BTW LONG 1-2 LT, CRACK OF 0.281 ON LT INTERNAL ANGLE AT STA Y=1424 BTW LONG 1-2 CRACK OF 0.281 ON LT INTERNAL ANGLE STA 1424 BTW LONG 1-2. DOUBLER REPAIR ACCOMPLISHED IAW ERA 502201-14AD ORIG.

Part: DOOR FRAME — CORRODED (CARGO BAY) · airframe 61,232 hrs · 45,929 cycles

CORROSION ON CARGO COMPARTMENT DOOR FRAME BS 376-382 AND 417-423 C1. REPAIR DOUBLERS WERE INSTALLED IAW ERA 503262-14 REV A.

Part: SKIN — DELAMINATED (RUDDER) · airframe 61,232 hrs · 45,929 cycles

DELAMINATED RT SIDE UPPER EDGE OF RUDDER. RT SIDE UPPER EDGE OF RUDDER WAS REPAIRED IAW SRM 51-70-1A PAR 23.

Part: SKIN — CORRODED (BS 1098) · airframe 61,232 hrs · 45,929 cycles

CORROSION ON FUSE SKIN BELOW RUB STRIP STA Y=1098. REPAIR DOUBLER INSTALLED IAW DC9/MD80 SRM 53-04 FIG 57.

Part: SKIN — DAMAGED (FUSELAGE) · airframe 61,232 hrs · 45,929 cycles

LIGHTNING STRIKE ON LT WINDOW BELT FRAMES LOWER FORWARD EDGE 788 TO 807. DOUBLER REPAIR WAS ACCOMPLISHED IAW ERA 503271-14 REV ORIG.

Part: WIRE — PULLED (CABIN) · airframe 61,090 hrs · 45,820 cycles

DURING LINE CHECK, MAINTENANCE FOUND THAT THE EMERGENCY PATHWAY LIGHTING IN ROWS 18-23 OF THE CABIN WERE INOPERATIVE. MAINTENANCE FOUND A WIRE PULLED FROM THE CONNECTOR AT SEAT 18E, RE-TERMINATED THE WIRE, AND FUNCTIONALLY CHECKED THE SYSTEM.

Part: BATTERY PACK — DISCHARGED (COCKPIT) · airframe 61,030 hrs · 45,781 cycles

DURING LINE CHECK, MAINTENANCE FOUND THAT THE EMERGENCY LIGHTING IN THE COCKPIT WAS INOPERATIVE. MAINTENANCE REPLACED THE BATTERY PACK AND THE LIGHTS RETURNED TO AN OPERATIONAL CONDITION.

Part: LOCK PIN — LACK OF LUBE (TAILCONE) · airframe 59,906 hrs · 44,965 cycles

DURING TAIL CONE FUNCTIONAL CHECK RELEASE SYSTEM, BULKHEAD DOOR CONTROL ARM FAILED TO DEPLOY. MAINTENANCE REMOVED AIRSTAIR FORWARD CEILING PANELS AND DOOR FRAME COVERS FOR ACCESS. LOCK PINS WERE LUBRICATED PER AMM 53-53. PERFORMED OPN 6908AD. OPERATION TEST NOW TEST GOOD QC 1503. CLOSED AIRSTAIRS UPPER AND FORWARD CEILING PANELS AND DOOR FRAME COVERS.

Part: LIGHT — INOPERATIVE (CABIN) · airframe 58,427 hrs · 43,969 cycles

DURING LINE CHECK MX, FOUND EMERGENCY LIGHTS AT 1 DC AND 4 DC INOPERATIVE. MX REPLACED LIGHT ASSY AT 1DC, RELAMPED AND, REPLACED LENS ASSY AT 4DC. BOTH LIGHTS NOW OPERATED OK.

Part: BATTERY — DISCHARGED (CABIN) · airframe 58,224 hrs · 43,858 cycles

DURING LINE CHECK MX FOUND EMERGENCY EXIT SIGN LIGHTS AT BOTH LT AND RT AFT OVERWING DOOR INOPERATIVE. MX REPLACED BATTERIES IN POWER SUPPLY. OPS OF LIGHTS NOW CHECKS GOOD.

Part: CONNECTOR — DAMAGED (EMERGENCY LIGHTS) · airframe 57,071 hrs · 43,071 cycles

MX FOUND THE ESCAPE PATH LIGHT AT SEAT 16D TO BE INOPERATIVE. MX REPLACED THE SEAT CONNECTOR. AN OPS CHECK WAS PERFORMED AND THE ACFT WAS RETURNED TO SERVICE.

Part: UNKNOWN — ODOR (CABIN) · airframe 49,163 hrs · 37,927 cycles

ODOR OF SMOKE, RUBBERY, DURING TAXI OUT. INSPECTED TAIL COMPARTMENT, AND APU COMPARTMENT, NO PROBLEMS FOUND, RAN APU AIRALL NORMAL.

Part: SKIN — DENTED (TE FLAP) · airframe 47,220 hrs · 36,733 cycles

THE LT INBOARD FLAP SKIN DENTED. THE DAMAGED SKIN WAS CUT OUT AND A NEW SECTION OF SKIN WAS SPLICED IN PLACE.

Part: DOOR FRAME — CORRODED (FUSELAGE) · airframe 47,218 hrs · 36,732 cycles

AFT CARGO COMPARTMENT DOOR LOWER JAMB REPAIR - SEVERAL POINTS OF CORROSION AT AFT CARGO DOOR LOWER JAMB BETWEEN STA 1155 AND 1180. A PERMANENT REPAIR WAS PERFORMED IAW SRM 53-05, FIG 63.

Part: SKIN — CRACKED (FUSELAGE) · airframe 47,218 hrs · 36,732 cycles

FUSELAGE SKIN REPAIR BETWEEN STA 160-200 AND LONGERONS 20-22L - FIVE CRACKS WERE FOUND ON FUSELAGE SKIN BETWEEN STA 189-193 OVER LONGERON 22L. FUSELAGE SKIN WAS REPAIRED IAW BOEING SERVICE REWORK DRAWING SR-09530219-7001 AND IAW EA 09-069085-12AD, REV D.

Part: SKIN — DENTED (LT ELEVATOR) · airframe 47,218 hrs · 36,732 cycles

LT LOWER ELEVATOR SKIN REPAIR AT STA XFS=57.5 - DENT OUT OF LIMITS. PERMANENT REPAIR INSTALLED PER SRM 55-03, FIG 13A.

Part: SKIN PANEL — DENTED (RUDDER) · airframe 47,218 hrs · 36,732 cycles

RUDDER LEADING EDGE RT PANEL REPAIR AT STA ZR=108 - DENT OUT OF LIMITS. PERMANENT REPAIR INSTALLED IAW SRM 51-70-1A.

Part: FRAME — CRACKED (FUSELAGE) · airframe 47,218 hrs · 36,732 cycles

STA 1446 UPPER CANTED FRAME REPAIR - THREE CRACKS AT STA 1446 CANTED FRAME. PERMANENT REPAIR WAS PERFORMED IAW SRM 53-03 FIG 30 AS ORDERED BY EA 09-062073-12 REV C, OPN 0103.

Part: SKIN — DAMAGED (FUSELAGE) · airframe 47,218 hrs · 36,732 cycles

FUSELAGE SKIN REPAIR BETWEEN STA 1155 AND STA 1174 BETWEEN LONGERONS 23L-25L - TEMPORARY REPAIR INSTALLED. PERMANENT REPAIR INSTALLED IAW SRM 53-04, FIG 12B VIEW C.

Part: LONGERON — CRACKED (FUSELAGE) · airframe 47,218 hrs · 36,732 cycles

NOSE LONGERONS 22L THROUGH 26L MODIFICATION (AD 98-24-33) - CRACK FOUND ON LONGERON 25L AT STA 160 WHICH WAS CORRECTED PER SRM 53-02, FIG 18. AS PER DELTA EA 09-069225-12AD, REV C, OPN 0104. ALL FUSELAGE LONGERON FRAME JOINTS FROM STA 160-200 AND LONGERONS 22LH TO 26LH WERE REINFORCED WITH DOUBLERS AND CLIPS AS SHOWN IN EA 09-069225-12AD, REV C, OPN 0105.

Part: BULKHEAD — CORRODED (FUSELAGE) · airframe 47,218 hrs · 36,732 cycles

DURING CURRENT VISIT, LOWER TEE CHORD OF PRESSURE BULKHEAD WAS FOUND WITH CORROSION DAMAGE. TEE REPLACED PER EA 09-086680-12, HOWEVER REPLACEMENT CHORD HAD SHORT EDGE MARGIN CONDITIONS AT SEVERAL LOCATIONS. BOEING REPAIR STRAP INSTALLED PER 458447-14

Part: CONNECTOR — SHORTED (NR 2 ENGINE) · airframe 46,682 hrs · 36,348 cycles

ON DEPARTURE FROM ATL, CREW HAD RIGHT ENGINE FIRE WARNING SOUND. RIGHT ENGINE B FIRE LOOP WAS ALREADY ON MCO. CREW PULLED FIRE HANDLE AND DISCHARGED BOTH FIRE BOTTLES. FLIGHT RETURNED TO ATL AND LANDED WITHOUT FURTHER INCIDENT. ATL MTC FOUND THE CONNECTOR SHORTED FOR THE A LOOP AND THE B LOOP BAD. REPAIRED THE CONNECTOR AND REPLACED THE LOOP, ALL INDICATIONS NOW NORMAL.

Part: O-RING — LEAKING (RT MLG WW) · airframe 43,935 hrs · 34,395 cycles

RIGHT HYD SYSTEM ENG DRIVEN PUMP INOP W/AUX PUMP OFF QTY 6. WHEN AUX PUMP ON QTY 3. WHEN ATTEMPTING TO PRESSURIZE SYS FOR GEAR EXTENSION PRESS WAS AT ZERO AND QTY WAS AT 3. REPLACED O-RING ON RIGHT SPOILER PRESSURE REDUCING VALVE. ALSO REPLACED AUX PUMP AND RIGHT EDP.

Part: LINE — CHAFED (HYD SYSTEM) · airframe 42,036 hrs · 33,056 cycles

LT HYD QTY BEGAN TO DECREASE IN CLIMBOUT FOLLOWED BY DECREASE IN PRESSURE. AFTER FOLLOWING QRH LT SIDE WENT BACK UP FROM 2 TO 17 QUARTS, PRESS REMAINED AT ZERO, PUMPS TURNED BACK OFF. FOUND HYD LINE CHAFED IN AIR CONDITION COMPARTMENT BEHIND P-DOME, LEFT SIDE. REPLACED SAME, LEAK CHECK OK.

Part: O-RING — FAILED (RT HYD SYSTEM) · airframe 38,457 hrs · 30,515 cycles

RT HYD QTY DROPPED FROM 10 QTS TO 4 QTS IN FLT WHEN RT SYSTEM WAS TURNED OFF QTY ROSE TO 15 WHEN RT SYS TURNED ON FOR LANDING SYS QTY DROPPED TO 1 QTY PRESSURE REMAINED GOOD. LEAK FROM RIGHT SYSTEM PRESSURE FILTER MODULE REDUCER - REPLACED O-RING.

Part: ODOR — DETECTED (CABIN) · airframe 38,452 hrs · 30,511 cycles

FOLLOWING TAKEOFF IN ATLANTA AT 6000 FEET AGL FLIGHT ATTENDANT NOTICED STRONG ACRID ODOR OF SMOKE THROUGHOUT CABIN. PERFORMED DUCT BURNOUT PROCEDURE.

Part: ACTUATOR — FAILED (RT MLG) · airframe 35,082 hrs · 28,089 cycles

RT MAIN GEAR UNSAFE LIGHT REMAINS ON AFTER GEAR RETRACTION. PERFORMED POM PROCEDURES, LIGHT REMAINS ON. ALSO GOT AUTO-SPOILER FAIL MSG ON AFTER INITIAL GEAR RETRACTION, LANDING GEAR INDICATION. CHECK PROX SENSORS ALL OK. REPLACED RIGHT MAIN GEAR ACTUATOR ASSY, OPS CHECKS OK, NO LEAK DETECTED. REF M/M 32-32-02-2.

Part: WIRE — CHAFED (GALLEY) · airframe 32,237 hrs · 26,001 cycles

WIRE H760D8C FROM GALLEY 4 C PHASE C/B, CHAFED INTO ADEL CLAMP. THIS IS INSIDE THE GENERATOR BUS CIRCUIT BREAKER PANEL. REF UPPER EPC C/B PANEL. ELECTRIAL ARCHING OCCURRED. REPLACED C/B AND REPAIRED WIRE PER WDM CH 20.

Part: WARNING LIGHT — ILLUMINATED (NR 2 ENGINE) · airframe 31,223 hrs · 25,220 cycles

RT ENGINE OIL STRAINER CLOG LIGHT IN FLT. DID NOT EXTINGUISH. RT ENGINE SHUTDOWN PER POM, RETURNED TO ATL. REPLACED OIL FILTER AND OIL PRESSURE SWITCH AND EOAP.

Part: VALVE — MALFUNCTIONED (NR 2 ENGINE)

CLIMBING OUT OF COS, RIGHT ENGINE OIL TEMP EXCEEDED 135 DEGREES ALONG WITH RT FUEL HEAT VALVE OPEN MESSAGE. C/W POM PROCEDURE, NO HELP. AIR TURNBACK TO COS. ON FINAL APPROACH MSG WENT OUT AND TEMP RETURNED TO NORMAL. REPLACED FUEL HEAT VALVE.

Part: POWER SUPPLY — INOPERATIVE (CABIN)

AFT CABIN EMERGENCY TRACK LIGHTING INOP. REPLACED REAR PATH LIGHTING POWER SUPPLY, OPS CK NORMAL.

Part: LIGHT — CONTAMINATED (CABIN)

READING LIGHT 29E OVERHEATED, A LITTLE SMOKE COMING FROM THAT AREA OF OVHD AND EXCESSIVE HEAT AROUND LIGHT. FOUND BUBBLE GUM WRAPPER INSIDE LIGHT COVER HAD BEEN BURNING. REMOVED GUM WRAPPER, ALL OK.

Part: JAMB — CORRODED (C1 DOORWAY)

FUSELAGE C1 DOOR CUTOUT LOWER JAMB PAN, SPLICE REPAIR OF CORRODED JAMB PAN. THE LOWER JAMB PAN AT THE C1 DOOR CUTOUT LOWER SILL WAS FOUND CORRODED. A NEW SECTION OF PAN WAS SPLICED IN AT THE LOWER SILL PER ER/A 363864-14.

Part: AIR DISTRIBUTION — ODOR (LAVATORY)

DURING CLIMBOUT WITH ENG ANTI-ICE ON AFT FLT ATT SMELLED SMOKE, WITHIN SHORT TIME LAV SMOKE ALARM CAPT SIDE SOUNDED. LAV INSP NO SIGN OF SMOKE OR FIRE, WITHIN TWO MINS ALARM SILENCED. RAN PACKS WITH ENGINES. PERFORMED AUG VALVE CHECK, NO TROUBLE FOUND. F/A REPORTED ODOR BUT NO VISIBLE SMOKE

Part: COALESCER BAG — CONTAMINATED (CABIN)

ON T/O, ACRID SMELL IN A/C. PERFORMED DUCT BURNOUT, CHANGED WATER SEPARATOR BAGS, CHECKS OK.

Part: O-RING — LEAKING (RT MLG WW)

EN ROUTE, RIGHT HD QTY IND DECREASED TO 4 QTS. FOUND O-RING ON SPOILER REDUCER LEAKING. REPLACED SAME.

Part: ACTUATOR ARM — CRACKED (LT TE FLAP)

I/B FLAP ACTUATOR ARM CRACKED. REPLACED ARM.

Part: WEB — DAMAGED (LT MLG WW)

AT HMV, TEMPORARY REPAIR ON AFT O/B CORNER OF LT W/W. REMOVED TEMP REPAIR AND DYE CHECKED CRACK, 6.25 INCHES LONG. REMOVED VERT STIFFENER TO PICK UP 5TH HOLE FROM REPAIR ANGLE. FABR NEW REPAIR ANGLE AND SENT TO HEAT TREAT PER SRM 53-05 FIG 81A. RE-MEASURED CRACK FOUND TO BE UNDER 6 INCH IN LENGTH. INSTALLED DOUBLER.

Part: HORIZ BEAM — CRACKED (FWD SERV DOOR)

AT HMV, FWD SERVICE DOOR IS CRACKED ON HORIZONTAL BEAM BELOW HINGE ATTACH FITTING. REPAIRED PER SRM 52-05 FIG 25.

Part: SUPPORT — CRACKED (AFT FUSELAGE)

AT HMV, RT TAI AREA LOUVER 2 SUPPORTS CRACKED. REPAIRED PER SRM 53-05 PG 181, PG 183, PG 185.

Part: SEAT TRACK — CORRODED (BS 1089-1165)

AT HMV, SEAT TRACK CORRODED INBD AND OUTBD SECTIONS JUST FWD OF AFT SERVICE DOOR. REPAIRED PER SRM 53-05 FIG 4F.

Part: SEAT TRACK — CORRODED (CABIN)

AT HMV, SEAT TRACK ADJACENT TO AFT SERVICE DOOR AFT INBD SECTION CORRODED. REPAIRED PER SRM 53-05 FIG 4F.

Part: NOSE COWL — DENTED (NR 2 ENG)

AT HMV, NR 2 ENG NOSE COWL L/E DENTED AT 2 O'CLOCK POSITION. REPAIRED PER SRM 54-04 FIG 9.

Part: DOOR — WORN (MID CARGO COMPT)

AT HMV, MID CARGO DOOR HANDLE CUTOUT FLANGE IS WORN AND BENT. REPAIRED PER SRM 52-05 FIG 30 PG 159.

Part: LONGERON — CRACKED (BS 1418)

DURING OVERHAUL, FOUND LONGERON 2R CRACKED AFT OF FS 1418 FRAME. REPAIRED PER SRM 53-02 FIGURE 5.

Part: FLANGE — BENT (C3 DOOR)

DURING OVERHAUL, FOUND THE FLANGE AROUND THE C-3 DOOR HANDLE BENT. REPAIRED PER SRM 52-05 FIG 30.

Part: SUPPORT — CRACKED (TAIL VENT)

DURING HMV, FOUND LOUVER SUPPORTS CRACKED LT EXTERIOR THE 2 LOWER SUPPORTS WERE CRACKED AT FWD END. REPAIRED PER SRM 53-05 PG 181, 183, AND 185.

Part: SKIN — DENTED (BAGGAGE DOOR)

DURING OVERHAUL, FOUND C-1 B/B DOOR SKIN BENT AT DOOR HANDLE. REPAIRED PER SRM 52-05 FIG 30 PAGE 159.

Part: SUB FLOOR — CRACKED (RT AFT FUS)

DURING HMV, FOUND AFT RT SUBFLOOR CRACKED FWD OF PYLON BULKHEAD. REPLACED SUBFLOOR PER SRM 53-5 FIG 97.

Part: SKIN — LIGHTNING STRIKE (FS 450-655)

AT HMV, LIGHTNING STRIKES ON UPPER FUS SKIN HAS MULTIPLE LIGHTNING STRIKES ON IT FROM FS 450, 463, 484, 530, 579, AND 655 LT SIDE AT 1000 POS AND FS 655, 674, 750 LT SIDE AT 1100 POSITION. REPAIRED DAMAGE PER SRM 53-04 FIG 38 SH 6. REMOVED DAMAGED RIVET AT FS 655, REMOVED AND INSTALLED RIVETS AT STA 655, 674, 750 AND TREATED BURNISHED AREAS. ALL WORK DONE ACCORDING TO SRM 53-04 FIG 38.

Part: SKIN — GOUGED (FS 225)

DENT WITHIN LIMITS PER SRM 53-04 FIG 38. BLENDED GOUGE, FOUND TO BE OUT OF LIMITS PER SRM 53-04 FIG 38. TRIMED OUT DAMAGED AREA, BEGAN FABRICATING PARTS PER SRM 53-04 FIG 38, FINISHED FABRICATING PARTS PER SRM 53-04 FIG 38. INSTALLED DOUBLERS PER SRM 53-04 FIG 38.

Part: SKIN — DENTED (FS 225)

DURING HMV, FOUND SKIN DENTED GOUGED AT FS 225 LT SIDE AT 1000 POSITION. REPAIRED PER SRM 53-04 VIEW J FIG 38.