N949DL

Part: WIRE HARNESS — DISCONNECTED (CABIN) · airframe 74,916 hrs · 56,188 cycles

EMERGENCY ESCAPE LIGHT AT SEAT 35D WAS INOPERATIVE. RE-CONNECTED SEAT HARNESS, CHECKS GOOD REF AMM 33-53.

Part: WIRE — LOOSE (EMERGENCY LIGHT) · airframe 74,792 hrs · 56,081 cycles

EMERGENCY LIGHTS ABOVE COCKPIT CEILING AND FWD F/A SEAT INOP. REPLACED BATTERY PACK AND BATTERY NO HELP 406124. FOUND WIRE L790C18 LOOSE AT LIGHT L1-160. SECURED SAME. EMERGENCY LTS CK NML MD 88 AMM 33-51. (LP4808133)

Part: SMOKE DETECTOR — FALSE ACTIVATION (FWD LAVATORY) · airframe 74,734 hrs · 56,030 cycles

FWD LAV SMOKE DETECTOR SOUNDED FOR SEVERAL MINUTES. RMVD AND REPLACED F/C LAV SMOKE DET. IAW MD88 AMM 26-13. (LP4808092)

Part: SMOKE DETECTOR — FALSE ACTIVATION (LAVATORY) · airframe 74,734 hrs · 56,030 cycles

ON TAXI - IN, FIRST CLASS LAV SMOKE DETECTOR ALARMED CONTINUOUSLY. REPLACED 1ST CLASS LAV SMOKE DETECTOR. OPS CK GOOD. (LP4808091)

Part: SKIN — CRACKED (FUSELAGE) · airframe 74,727 hrs · 56,024 cycles

AFT LAV PANEL DOOR CUTOUT CORRODED/CRACKED AT THE 6 OCLOCK POS. COMPLIED WITH ERA 572887-14 REV O. MONITORED ON LOGSHEET 0817105. (LP4808088)

Part: BATTERY — DISCHARGED (CABIN) · airframe 74,488 hrs · 55,792 cycles

EMERGENCY LIGHTS ON CEILING ARE INOPERATIVE THROUGHOUT THE MAIN CABIN. MAINTENANCE FOUND THAT THE BATTERIES AT OVERHEAD BIN 4D, E, 25D, E AND 29D, E WERE NOT CHARGED. THE BATTERIES IN THE POWER PACKS WERE REPLACED AND ALL EMERGENCY CEILING LIGHTS NOW WORK.

Part: SMOKE DETECTOR — FAULTY (L;AVATORY) · airframe 74,370 hrs · 55,682 cycles

FWD LAVATORY SMOKE DETECTOR WILL NOT TURN OFF. REPLACED DETECTOR. (LP0721172)

Part: FRAME — CRACKED (FUSELAGE) · airframe 74,112 hrs · 55,471 cycles

1.5 INCH CRACK RT SIDE CANTED FRAME. STOP-DRILLED 1.5" CRACK PER SRM 53-01. ACCOMPLISHED HFEC CRACK CONTAINED IAW SRM 53-01. FABRICATED DOUBLER PER SRM 53-01 FIG 2. ALODINED PER SRM 53-10-3. PRIMED PER PROCESS STANDARD MANUAL 900-3-6 NR 3. INSTALLED DOUBLER PER SRM 53-01. RESTORED FINISH PER PS 900-3.

Part: CONNECTOR — DAMAGED (EMERGENCY LIGHT) · airframe 73,829 hrs · 55,245 cycles

SEAT 3D EMERGENCY LIGHTS INOPERATIVE. REPAIRED THE CONNECTOR IAW STANDARD WIRING PRACTICE MANUAL. CHECKED GOOD. OK FOR SERVICE.

Part: SMOKE DETECTOR — DIRTY (LAVATORY) · airframe 73,785 hrs · 55,211 cycles

IN FLIGHT FA REPORTED THAT FWD LAV SMOKE DETECTOR BEEPED FOR ABOUT 20 SECONDS. NO SMOKE FUMES NOTED. FOUND COPIOUS AMOUNTS OF DUST & DEBRIS ON TOP OF SMOKE DETECTOR. REMOVED & REPLACED FWD LAV SMOKE DETECTOR. OK FOR SVC PER MD88 AMM 26-13.

Part: SMOKE DETECTOR — MALFUNCTIONED (LAVATORY) · airframe 73,512 hrs · 54,983 cycles

SMOKE DETECTOR IN FWD LAVATORY CONTINUALLY GOING OFF. NO SMOKE, FUMES OR FIRE. REPLACED THE FWD LAVATORY SMOKE DETECTOR IAW AMM 26-13, OPS CHECKED OK.

Part: CONNECTOR — DEFECTIVE (CABIN) · airframe 72,796 hrs · 54,421 cycles

DURING SVC CHECK FOUND EMERGENCY LIGHTS ON SEAT 3CD AND 22ED INOP. REPINNED CONNECTORS AND OPS CHECKED IAW MD88 AMM 33-53.

Part: BATTERY — UNKNOWN (SMOKE DETECTOR) · airframe 72,577 hrs · 54,263 cycles

FWD LAV SMOKE DETECTOR FALSE ALARM FOR APPROX. 5 MINUTES. R/R SMOKE DETECTOR BATTTERY CKS NML PER MD-88 26-17. (LP3861420)

Part: WEDGE — DAMAGED (LT WING TE FLAP) · airframe 71,916 hrs · 53,706 cycles

LEFT WING INBOARD TRAILING FLAP TRAILING EDGE HAS DAMAGE APROX 6 INCHES OUTBOARD OF FUSELAGE. COMPLIED WITH IAW ERA 56-1321-14, REV ORIGINAL, SECTION 2. REPLACED THE TRAILING EDGE WEDGE IAW DRAWING 5935966.

Part: STRUCTURE — CRACKED (VERTICAL STAB) · airframe 71,698 hrs · 53,527 cycles

THREE CRACK INDICATIONS WERE CONFIRMED AT STA ZFS=53.267, STA 57.267 AND STA ZFS=58.267 HOLES RT SIDE. AREA WAS REPAIRED PER ER/A 494480-14AD REV B SECTION III AND ETI-88-17-209 REV 3.

Part: SPAR — DAMAGED (VERTICAL STAB) · airframe 76,144 hrs · 57,230 cycles

VERTICAL STABILIZER RH SPAR CHORD ZFS 52 HOLE DAMAGE AMOC 17-162. ERA REV C IS CURRENT.

Part: ACCESS PANEL — CORRODED (NOT REPORTED) · corrosion level 2 · airframe 71,698 hrs · 53,527 cycles

CORROSION ON COUNTERSINKS AND SETTLEMENNT AREA AT FUEL ACCESS PLATE 1414C. THE ACCESS PANEL WAS REPLACED IAW SRM 51-22-2A COND. II.

Part: SKIN — CRACKED (BS 1309) · airframe 71,698 hrs · 53,527 cycles

CRACK ON EXTERNAL FUSELAGE SKIN BS 1309, LONGERONS 6R TO 7R. THE CRACK WAS .500 INCH. AREA WAS REPAIRED IAW ER/A 559535-14, REV ORIG, AND ETI -88-17-206, REV 2.

Part: TAB — DEBONDED (RT ELEVATOR) · airframe 71,698 hrs · 53,527 cycles

DISBONDED PREVIOUS REPAIR ON THE RT ELEVATOR GEAR TAB T/E. THE DAMAGED AREA WAS REPAIRED IAW SRM 51-70-2D, PAR 18, AND 55-04, PAR 3, FIG 2.

Part: SPACER — CORRODED (BS 1154-1211) · corrosion level 2 · airframe 71,698 hrs · 53,527 cycles

CORROSION ON PREVIOUS REPAIR SPACER AT LOWER DOOR FRAME BEAM BS 1154 - 1211. THE SPACER WAS REPLACED IAW SRM 53-05, FIG 123, AND 51-30-5.

Part: INTERCOSTAL — CRACKED (BS 184) · airframe 71,698 hrs · 53,527 cycles

CRACKED INTERCOSTAL BS 184 BETWEEN BEAMS 5 AND 6, AT THE L1 DOOR. THE INTERCOSTAL WAS REPLACED IAW SRM 51-10-2, 51-30-2 , 51-30-5, AND DWG 9955763, REV K.

Part: TAB — DELAMINATED (RT ELEVATOR) · airframe 71,698 hrs · 53,527 cycles

DENTS AND DELAMINATION ON UPPER SKIN OF THE RT ELEVATOR ANTI-FLOAT TAB. DENTS WERE FOUND TO BE IN LIMITS. THE DELAMINATION WAS REPAIRED IAW SRM 55-04, PAR 2, FIG 1.

Part: TAB — DELAMINATED (RT ELEVATOR) · airframe 71,698 hrs · 53,527 cycles

DENTS AND DELAMINATION ON UPPER SKIN OF THE RT ELEVATOR ANTI-FLOAT TAB. DENTS WERE FOUND TO BE IN LIMITS. DELAMINATION WAS REPAIRED IAW SRM 55-04, PAR 2, FIG 1.

Part: BEAM — CRACKED (L1 DOOR) · airframe 71,698 hrs · 53,527 cycles

CRACKED BEAM NR 6 BS 177 AT THE L1 DOOR. THE BEAM WAS REPAIRED IAW ER/A 498178-14MA, REV ORIGINAL.

Part: FITTING — CRACKED (SERVICE DOOR) · airframe 71,698 hrs · 53,527 cycles

CRACKED CLIP ON BEAM NR 1 STA Y=164 AT FWD GALLEY SERVICE DOOR R1. CLIP WAS REPLACED PER DWG 9911579 REV L.

Part: REPAIR — CORRODED (FUSELAGE) · corrosion level 2 · airframe 71,698 hrs · 53,527 cycles

CORROSION ON PREVIOUS REPAIR SPACER AT LOWER DOOR JAMB BEAM STA Y=636 TO Y=693 5300-2358. REPAIR WAS ACCOMPLISHED PER SRM 53-05, FIG 123.

Part: LONGERON SPLICE — CORRODED (FUSELAGE) · corrosion level 2 · airframe 71,698 hrs · 53,527 cycles

CORROSION SPLICE ON LONG 28R BILGE AREA STA Y=225 TO 240 AT FWD CARGO COMPARTMENT. SPLICE WAS REPLACED PER SRM 53-14-2 FIG 1, SRM 51-10-4 AND SRM 51-30-5.

Part: DOOR FRAME — CORRODED (BS 1154-1211) · corrosion level 2 · airframe 71,698 hrs · 53,527 cycles

CORROSION ON LOWER DOOR FRAME BEAM BS 1154 TO 1211. CORROSION WAS REMOVED IAW SRM 51-10-3, PAR 26, 21, AND 14.

Part: WIRE — SPARKS (WINDOW) · airframe 70,842 hrs · 52,836 cycles

CAPTAIN`S CLEARVIEW WINDOW WIRES SPARKED ON TAXI IN. TERMINATED THE WIRES IAW SWPM 20-20. CHECKED GOOD.

Part: BATTERY PACK — INOPERATIVE (EMERGENCY LIGHTS) · airframe 70,781 hrs · 52,790 cycles

FWD EMERGENCY LIGHTS INOPERATIVE. REMOVED AND REPLACED THE BATTERY PACK. OPS CHECKED OK IAW AMM 33-51.

Part: CONNECTOR — UNSECURE (EMERGENCY LIGHTS) · airframe 70,155 hrs · 52,353 cycles

EMERGENCY LIGHTS INOPERATIVE ROWS 17-23. SECURED THE CONNECTOR BETWEEN 17 - 18E. CHECKED OK IAW WDM 33-51.

Part: LIGHT — INOPERATIVE (EXTERIOR) · airframe 69,903 hrs · 52,151 cycles

EXTERIOR EMERGENCY ILLUMINATION SYSTEM. RIGHT EXTERIOR EMERGENCY LIGHT INOP. RELAMPED EXT EMERGENCY LIGHT AND ASSOCIATED HARDWARE PER AMM 33-50. OPS NORMAL, OK FOR SVC.

Part: WIRE — BROKEN (EMERGENCY LIGHT) · airframe 69,762 hrs · 52,038 cycles

ROW 17 SEAT MOUNTED EMERGENCY LIGHT INOPERATIVE. INSPECTED PLUG AT SEAT FOR EMERGENCY LIGHTING, FOUND WIRE BROKEN. REPAIR THE WIRE, CHECKED GOOD.

Part: POWER SUPPLY — INOPERATIVE (EMERGENCY LIGHTS) · airframe 69,592 hrs · 51,883 cycles

FWD EMERGENCY EXIT OVERWING LIGHT INOPERATIVE. REMOVED & REPLACED THE POWER SUPPLY UNIT IAW AMM 33-53. OPS CHECKED OK.

Part: SLIDE — LEAKING (TAILCONE) · airframe 69,370 hrs · 51,693 cycles

DURING ROUTINE TAILCONE AND SLIDE DEPLOYMENT AFT EMERG SLIDE, SN 693 DEVELOPED A LEAK AT LOWER SEAM AND DID NOT STAY INFLATED FOR 10 MINS. WORK CONTROL CARD 88-0525-8-0408 MFG DATE 08/1984. SLIDE REPLACED AND REQUIRED INSPECTION ACCOMPLISHED.

Part: CONNECTOR — DISCONNECTED (EMERGENCY LIGHTS) · airframe 69,228 hrs · 51,582 cycles

EMERGENCY LIGHTS INOPERATIVE ROW 17-23. CONNECTED THE CONNECTOR AT 17ABC. OPS CHECKED NORMAL IAW WDM 33-51.

Part: BATTERY PACK — INOPERATIVE (EMERGENCY LIGHTS) · airframe 68,675 hrs · 51,187 cycles

THE CREW OF FLIGHT 1417 FOUND THE EMERGENCY ESCAPE PATH LIGHTING INOPERATIVE BETWEEN ROWS 17 AND 23. MAINTENANCE REPLACED THE BATTERY PACK ABOVE SEAT 23DE AND THE LIGHTS CHECKED OK.

Part: WIRE — LOOSE (EMERGENCY LIGHT) · airframe 67,585 hrs · 50,434 cycles

THE CREW FOUND THE EMERGENCY LIGHTS INOPERATIVE BETWEEN SEAT ROWS 17 AND 23. MAINTENACE TROUBLESHOT AND FOUND AND RESECURED A LOOSE CONNECTION AT SEAT ROW 17DE.

Part: CONNECTOR — UNSECURE (EMERGENCY LIGHTS) · airframe 67,551 hrs · 50,409 cycles

MAINTENANCE FOUND EMERGENCY LIGHTS INOPERATIVE BETWEEN ROWS 17 AND 23. A LOOSE CONNECTOR WAS SECURED AT ROW 16DEF AND LIGHTS CHECKED NORMAL.

Part: BATTERY PACK — INOPERATIVE (EMERGENCY LIGHTS) · airframe 67,357 hrs · 50,267 cycles

DURING LINE CHECK, MAINTENANCE FOUND THAT THE OVERHEAD EMERGENCY LIGHTING FROM ROW 17 TO 25 WERE INOPERATIVE. MAINTENANCE RESET THE BATTERY PACK AND THE LIGHTS RETURNED TO AN OPS CONDITION.

Part: BATTERY PACK — INOPERATIVE (EMERGENCY LIGHTS) · airframe 66,842 hrs · 49,865 cycles

MAINTENANCE FOUND CABIN SEAT MOUNTED EMERGENCY LIGHTS INOPERATIVE FROM ROWS 17-24DE. THE BATTERIES WERE REPLACED.

Part: BATTERY PACK — INOPERATIVE (EMERGENCY LIGHTS) · airframe 66,734 hrs · 49,800 cycles

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

Part: WIRE — DAMAGED (EMERGENCY LIGHTS) · airframe 66,527 hrs · 49,664 cycles

DURING LINE CHECK, MAINTENANCE FOUND THAT THE EMERGENCY LIGHTING AT SEAT 3 CD WAS INOPERATIVE. MAINTENANCE FOUND WIRES BROKEN IN THE HARNESS. THE WIRE HARNESS WAS REPAIRED AND THE SYSTEM RETURNED TO NORMAL OPERATION.

Part: CLAMP — OUT OF ADJUST (TAILCONE RELEASE) · airframe 66,508 hrs · 49,653 cycles

CHECK FAILED STEP 21 OF THE TAILCONE RELEASE SYSTEM OPS CHECK. THE EXTERIOR RELEASE CABLE WAS OUT OF ALLOWABLE LIMITS AT THE CLAMP TO THE INTERNAL RELEASE CABLE. THE CLAMP ON THE CABLE WAS ADJUSTED AND THE SYSTEM WAS RIGGED BACK INTO SPECIFICATIONS. THE RII STEPS WERE COMPLETED AND THE FOLLOW-UP CHECK WAS SUCCESSFUL.

Part: STRUCTURE — CRACKED (BS 1485) · airframe 66,479 hrs · 49,633 cycles

TAIL BS 1485 WEB AND ANGLE CRACKED IN THREE PLACES, RT SIDE FWD OF RUDDER TRIM ACTUATOR. REPAIRED IAW ERA 537139-14, REVISION ORIGINAL.

Part: BUSHING — WORN · airframe 66,479 hrs · 49,633 cycles

TEE PIN BUSHING WORN. REPLACED BUSHING IAW AMM 53-53-00.

Part: FRAME — CRACKED (BS 1510) · airframe 66,479 hrs · 49,633 cycles

BS 1510 FRAME CRACKED AT THE 3:30 ALIGNMENT PIN. INSTALLED REPAIR IAW ER/A497316-14MA. REINSTALLED BULB SEAL AND CABLE BRACKET. INSTALLED REPAIR IAW ER/A4973 16-14MA. REV ORIG.

Part: FRAME — CRACKED (BS 886) · airframe 66,479 hrs · 49,633 cycles

MAIN OVERWING FRAME BS 886 RT SIDE IS CRACKED, CONFIRMED WITH EDDY REWORKED OVERWING FRAME AT BS 886. ACCOMPLISHED HFEC INSPECTION OF REWORKED AREA IAW NDTSPM 06-10-01.001, NO CRACKS NOTED.

Part: LIGHT — BROKEN (SEAT 16D) · airframe 66,456 hrs · 49,620 cycles

DURING LINE CHECK, MAINTENANCE FOUND THAT THE EMERGENCY LIGHTING AT SEAT 16D IN THE CABIN WAS BROKEN. MAINTENANCE REPLACED THE PIGTAIL AT THE LIGHT AND THE SYSTEM RETURNED TO NORMAL OPERATION.

Part: BATTERY PACK — INOPERATIVE (EMERGENCY LIGHT) · airframe 65,277 hrs · 48,813 cycles

DURING LINE CHECK, MAINTENANCE FOUND THAT THE OVERHEAD EMERGENCY LIGHT AT SEAT 34 WAS INOPERATIVE. MAINTENANCE REPLACED THE BATTERIES. OPS CHECKED GOOD.

Part: WIRE HARNESS — DAMAGED (EMERGENCY LIGHTS) · airframe 65,172 hrs · 48,745 cycles

DURING LINE CHECK, MAINTENANCE FOUND THAT THE EMERGENCY LIGHT AT SEAT 18DE WAS INOPERATIVE. MAINTENANCE REPLACED THE WIRE HARNESS AND FUNCTIONALLY CHECKED THE SYSTEM.

Part: BATTERY PACK — INOPERATIVE (EMERGENCY LIGHTS) · airframe 64,872 hrs · 48,520 cycles

DURING LINE CHECK, MAINTENANCE FOUND THAT THE EMERGENCY LIGHT AT SEAT 25A IN THE CABIN WAS INOPERATIVE. MAINTENANCE REPLACED THE BATTERIES. OPS CHECK WAS GOOD.

Part: CHIP DETECTOR — LEAKING (APU) · airframe 64,036 hrs · 47,869 cycles

DIVERTED AIRCRAFT DUE TO REPORTS OF SMOKE IN THE CABIN AND AFT LAVATORY SMOKE DETECTORS SOUNDING. FOLLOWED QRH, SECURED THE RECIRCULATION FAN & THE LEFT PACK, AND THE SMOKE DISSIPATED. MAINTENANCE FOUND THE APU DRAIN CHIP DETECTOR LEAKING OIL, WHICH CONTAMINATED THE APU. DUCT BURNOUT PROCEDURES WERE ACCOMPLISHED. OPEN

Part: BATTERY PACK — INOPERATIVE (EMERGENCY LIGHTS) · airframe 64,032 hrs · 47,866 cycles

DURING LINE CHECK, MAINTENANCE FOUND THAT THE EMERGENCY EXIT SIGNS AT BOTH OF THE OVERWING HATCHES WERE INOPERATIVE. MAINTENANCE REPLACED THE BATTERIES IN THE POWER SUPPLY AND THE LIGHTS RETURNED TO AN OPERATIONAL CONDITION.

Part: CONNECTOR — BROKEN (EMERGENCY LIGHTS) · airframe 62,094 hrs · 46,566 cycles

DURING CHECK, MX FOUND THAT THE EMERGENCY PATHWAY LIGHTING AT ROW 24D IN THE CABIN WAS INOPERATIVE. MX FOUND A BROKEN WIRE CONNECTOR UNDER THE SEAT, REPLACED IT, AND FUNCTIONALLY CHECKED THE SYSTEM.

Part: FRAME — CRACKED (BS 1510) · airframe 61,981 hrs · 46,488 cycles

CRACK ON FRAME BS 1510 CANT BETWEEN 7HRS AND 8HRS POSITION IN AFT ACCESSORY COMPARTMENT . FRAME WAS REMOVED IAW SRM 51-30-2 AND NEW FRAME WAS INSTALLED IAW SRM 51-30-2.

Part: CHANNEL — CRACKED (CARGO BAY) · airframe 61,981 hrs · 46,488 cycles

SEVERAL CRACKS ON FASTENERS HOLES AREA UPPER CHANNEL, OF AFT CARGO COMPARTMENT DOOR BARRIER. CRACKS ON CHANNEL WERE REMOVED IAW ER/A 383099-14 MA AND SRM 53-01, FIG 04. DOUBLERS REPAIR WERE FABRICATED, TREATED, PAINTED, AND INSTALLED IAW ER/A 383099-14 MA AND SRM 51-30-2.

Part: SKIN — CRACKED (BS 1418) · airframe 61,992 hrs · 46,495 cycles

CRACK ON INNER FUSELAGE SKIN AT BS 1418, BETWEEN LONGERONS 1 - 2R IN AFT ACCESSORY COMPARTMENT, CRACK REMOVED, DOUBLERS AND FILLERS WERE FABRICATED AND INSTALLED IAW ER/A 494602-19 AD REV "C". ASSOCIATED ER/A 00-494602.

Part: DOME NUT — CORRODED (BS 266-296) · airframe 61,981 hrs · 46,488 cycles

RUSTED DOME NUTS ON INNER FUSELAGE SKIN STA 266 AND 296. PROJECTION LONG 1 (FCS) (MRB 53-139-02). ANTENNA TCAS PLATE INTERCOSTALS LONG SECTION WERE REMOVED. NEW LONGERON WAS DRILLED INSTALLED. INSTALLED ALL COMPONETS PREVIOSLY REMOVED IAW SRM 51-30-5, 51-30-2, 51-10-4 , 53-02, FIG 18 AND 51-10-3. RII COMPLETED.

Part: RELEASE CABLE — FRAYED (TAILCONE) · airframe 61,981 hrs · 46,488 cycles

MX DISCOVERED THAT THE TAILCONE EMERGENCY RELEASE CABLE WAS FRAYED BEYOND ALLOWABLE LIMITS. THE CABLE WAS REPLACED AND THE SYS WAS RIGGED TO SPECIFICATIONS. THE RII STEPS WERE COMPLETED.

Part: SKIN — DAMAGED (BS 1098) · airframe 61,981 hrs · 46,488 cycles

CORROSION ON FUSELAGE SKIN FILLET PANEL RUBSTRIP AREA BS 1098 LONGERONS 28 & 29R. SKIN REPAIRED IAW SRM 53-04, FIG 57.

Part: SKIN — CORRODED (BS 1086-1122) · airframe 61,981 hrs · 46,488 cycles

CORROSION ON FUSELAGE SKIN BENEATH FILLET PANEL RUBSTRIPS STA Y=1086-1122 , BETWEEN LONGERON 26 TO 30R IN REF 497, ZONE 50, T0 291579. FASTENER WERE REMOVED, CORROSION WAS REMOVED, AREA WAS MEASURED NOMINAL THICKNESS, AREA WERE TREATED AND PAINTED, AREA OUT OF LIMITS.

Part: SKIN — CORRODED (BS 1082-1112) · airframe 61,981 hrs · 46,488 cycles

CORROSION ON FUSELAGE SKIN BENEATH FILLET PANEL RUBSTRIPS STA Y=1082-1093; Y=1105-1112 BETWEEN LONGERON 27 TO 30L IN REF 498, ZONE 50. FASTENERS WERE REMOVED, CORROSION WAS REMOVED, AREA WAS MEASURED NOMINAL THICKNESS ON FUSELAGE SKIN, AREA WAS TREATED AND PAINTED.

Part: SKIN — CORRODED (BS 729-786) · airframe 61,981 hrs · 46,488 cycles

CORROSION ON FUSELAGE SKIN BENEATH FILLET PANEL RUBSTRIPS STA Y=729-739 ,Y=782-786, BETWEEN LONGERON 21 TO 30L IN REF 499, ZONE 50 (T0 291577). FASTENERS WERE REMOVED , CORROSION WERE REMOVED, AREA WAS MEASURED NOMINAL THICKNESS ON FUSELAGE SKIN, AREA WAS TREATED AND PAINTED.

Part: SKIN — CORRODED (BS 729-783) · airframe 61,981 hrs · 46,488 cycles

CORROSION ON FUSELAGE SKIN BENEATH FILLET PANEL RUBSTRIPS STA Y=729-731, Y=752-783, BETWEEN LONG 22RT TO 30 (FS) IN REF 500 ZONE 50 (T0 291576). FASTENERS WERE REMOVED, CORROSION WAS REMOVED.

Part: ACCESS PANEL — CORRODED (WING) · corrosion level 2 · airframe 61,981 hrs · 46,488 cycles

DURING HEAVY MX, CORROSION WAS FOUND IN THE COUNTERSINK HOLES OF FUEL TANK ACCESS PANEL 1478C. PANEL AS REPAIRED IAW SRM 51-22-2A, PAR 6.

Part: ACCESS PANEL — CORRODED (WING) · corrosion level 2 · airframe 61,981 hrs · 46,488 cycles

DURING HEAVY MX VISIT, CORROSION WAS FOUND IN THE COUNTERSINK HOLES OF FUEL TANK ACCESS PANEL 1464C. PANEL AS REPAIRED IAW SRM 51-22-2A, PAR 6.

Part: SEAT TRACK — CORRODED (BS 1084-1088) · corrosion level 2 · airframe 61,981 hrs · 46,488 cycles

CORROSION FOUND ON THE LT SEAT TRACK X-22 AT STA Y=1084 - 1088 IN THE PASSENGER CABIN FLOOR STRUCTURE. SEAT TRACK R & R IAW SRM 51-30-1 & -5.

Part: ACCESS PANEL — CORRODED (WING) · corrosion level 2 · airframe 61,981 hrs · 46,488 cycles

DURING HEAVY MX VISIT, CORROSION WAS FOUND IN THE COUNTERSINK HOLES OF FUEL TANK ACCESS PANEL 1373C. PANEL AS REPAIRED IAW SRM 51-22-2A, PAR 6.

Part: ACCESS PANEL — CORRODED (WING) · corrosion level 2 · airframe 61,981 hrs · 46,488 cycles

DURING HEAVY MX, CORROSION WAS FOUND IN THE COUNTERSINK HOLES OF FUEL TANK ACCESS PANEL 1470C. PANEL AS REPAIRED IAW SRM 51-22-2A, PAR 6.

Part: CARGO TRACK — CORRODED (BS 1022-1135) · corrosion level 2 · airframe 61,981 hrs · 46,488 cycles

CORROSION FOUND DURING SCHEDULED INSPECTION ON THE RT CARGO TRACK BETWEEN BS 1022-1135, REPAIRED IAW SRM 53-24-0D, FIG 11 AND INSTALLED IAW SRM 51-10-4 & 51-10-3, PAR 14, 21, 38.

Part: ACCESS PANEL — CORRODED (WING) · corrosion level 2 · airframe 61,981 hrs · 46,488 cycles

DURING HEAVY MX, CORROSION WAS FOUND IN THE COUNTERSINK HOLES OF FUEL TANK ACCESS PANEL 1456C. PANEL AS REPAIRED IAW SRM 51-22-2A, PAR 6.

Part: ACCESS PANEL — CORRODED (WING) · corrosion level 2 · airframe 61,981 hrs · 46,488 cycles

DURING HEAVY MX VISIT, CORROSION WAS FOUND IN THE COUNTERSINK HOLES OF FUEL TANK ACCESS PANEL 1436C. PANEL AS REPAIRED IAW SRM 51-22-2A, PAR 6.

Part: SKIN — CORRODED (BS 806) · corrosion level 2 · airframe 61,981 hrs · 46,488 cycles

CORROSION ON FUSELAGE SKIN UNDER WING TO FUSELAGE FILLET FAIRING BS 806 BETWEEN LONGERONS 28 TO 30R. REPAIRED IAW SRM 53-04, FIG 57.

Part: BRACKET — CRACKED (BS 937) · airframe 61,981 hrs · 46,488 cycles

CRACKED BRACKET ON FWD DOOR FRAME BS 937, X=24 AT LT MLG WHEEL WELL. BRACKET REPLACED IAW ER/A 09076074-03. BRACKET WAS REMOVED AND NEW BRACKET WAS INSTALLED IAW SRM 51-30-2, 51-30-5.

Part: SKIN — CORRODED (BS 1098) · airframe 61,981 hrs · 46,488 cycles

CORROSION ON FUSELAGE SKIN FILLET PANEL RUBSTRIP AREA BS 1098 BETWEEN LONGERONS 28 & 29R. SKIN REPAIRED IAW SRM 53-04, FIG 57.

Part: ANGLE — CORRODED (BS 200) · corrosion level 2 · airframe 61,981 hrs · 46,488 cycles

CORROSION ON CUSP ANGLE BS 200 AND X=-58. FOR EXCESIVE DAMAGE, CUSP ANGLE WAS REPAIRED; ITEMS FLOOR SUPPORT, WEBS, STOPS FITTINGS, SPAR, & SEAT TRACK -44 WERE REMOVED FOR ACCESS. DAMAGE SECTION ON CUSP ANGLE WAS CUT OUT, NEW SECTION ANGLE WAS DRILLED & ADJUSTED, FOR GAIN ACCESS REMOVAL DAMAGE SECTION CUSP ANGLE, DOOR JAMB STA 160 TO 200 WAS CUT OUT, REPAIR DOUBLERS FOR CUP ANGLE & DOOR JAMB WAS FABRICATED AND INSTALLED WITH REPAIR DOUBLERS, DOOR JAMB WITH REPAIR DOUBLERS WERE INSTALLED, ITEMS FOR GAIN ACCESS WERE INSTALLED, AND THIS REPAIR FOR SRM WAS APPLY ER/A 517488-14, REV ORIG AND SRM 53-05, FIG 55. RII COMPLETED.

Part: SKIN — DAMAGED (RUDDER) · airframe 61,981 hrs · 46,488 cycles

METALLIZED COVER ON RUDDER DAMAGED AND WAS REPAIRED IAW SRM 57-70-1 AD PAR. 23.

Part: LONGERON — CRACKED (BS 905 L4L) · airframe 61,981 hrs · 46,488 cycles

CRACK ON LONGERON 4 LT AT STA 905 AT PAX CABIN ( FCS). LONGERON CRACKED WAS REMOVED NEW LONGERON AND SPLICE WERE DRILLED AND ADJUSTED AREA AND REPAIR PARTS WERE TREATED AND PAINTED AND REPAIR PARTS, LONGERON AND SPLICE, WERE INSTALLED IAW SRM 53-02, FIG 18.

Part: LONGERON — CRACKED (BS 1380 L8L) · airframe 61,981 hrs · 46,488 cycles

CRACK ON LONGERON 8 LT AT STA Y=1380 IN AFT ACCESSORY COMPARTMENT. LONGERON CRACKED WAS REMOVED, NEW LONGERON AND SPLICE WERE DRILLED AND ADJUSTED AREA AND REPAIR PARTS WERE TREATED AND PAINTED AND REPAIR PARTS. LONGERON AND SPLICE WERE INSTALLED IAW SRM 53-02, FIG 18.

Part: LONGERON — CRACKED (BS 1380 L11L) · airframe 61,981 hrs · 46,488 cycles

CRACK ON LONGERON 11L BS 1380 IN AFT ACCESSORY COMPARTMENT. LONGERON CRACKED WAS REMOVED NEW LONGERON AND SPLICE WERE DRILLED AND ADJUSTED AREA AND REPAIR PARTS WERE TREATED AND PAINTED AND REPAIR PARTS, LONGERON AND SPLICE, WERE INSTALLED IAW IAW SRM 53-02, FIG 18.

Part: CUSP WEB — CORRODED (BS 988) · corrosion level 2 · airframe 61,981 hrs · 46,488 cycles

CORROSION FOUND ON LT CUSP WEB AT BS 988 AND X=60 IN THE PASSENGER CABIN FLOOR STRUCTURE. REPAIRED IAW SRM 53-05, FIG 231A-5 AND 53-05, FIG 131A-5.

Part: LOCK NUT — CORRODED (HORIZONTAL STAB) · corrosion level 2 · airframe 61,981 hrs · 46,488 cycles

CORROSION FOUND ON THE LT & RT AFT ATTACH LUGS OF THE HORIZONTAL STABILIZER ON THE LOCK NUTS. THE LOCK NUTS WERE REPLACED IAW AMM 55-10-00-201 AND THE REQUIRED INSPECTION WAS COMPLETED.

Part: FLOOR SUPPORT — CORRODED (BS 1171) · corrosion level 2 · airframe 61,981 hrs · 46,488 cycles

CORROSION WAS FOUND ON THE LAVATORY FLOOR SUPPORT STRUCTURE AT STA 1171 AND X=58. FLOOR SUPPORT STRUCTURE REPAIRED IAW SRM.

Part: BEAM — CORRODED (CARGO DOOR) · corrosion level 2 · airframe 61,981 hrs · 46,488 cycles

CORROSION FOUND ON A PREVIOUS REPAIR DOUBLER ON THE LOWER BEAM OF THE AFT CARGO COMPARTMENT DOOR JAMB, FROM STA 1168 TO 1180 AND BETWEEN 1190 TO 1210 AT LONG 28R. REPAIRED IAW SRM 53-05, FIG 123.

Part: STRUCTURE — WORN (BS 1510) · airframe 61,981 hrs · 46,488 cycles

WEAR WAS NOTED ON THE CAM BASE OF THE TAIL CONE RELEASE SYS AT BS 1510. THE CAM BASE WAS REPLACED IAW AMM 53-53-02-201 AND THE REQUIRED INSPECTION WAS COMPLETED.

Part: CUSP WEB — CORRODED (BS 487-497) · corrosion level 2 · airframe 61,981 hrs · 46,488 cycles

CORROSION WAS FOUND ON THE RT CUSP WEB UPPER & LOWER SURFACES BETWEEN BS 487 & 497. REPAIRED IAW SRM 53-05, FIG 131 A-6.

Part: BRACKET — CORRODED (RUDDER BELLCRANK) · airframe 61,981 hrs · 46,488 cycles

DURING SCHEDULED HEAVY MAINTENANCE, CORROSION WAS FOUND ON THE RUDDER BELLCRANK AND BRACKET. THE RUDDER BELLCRANK AND BRACKET WERE REPLACED IAW AMM 27-20-06.

Part: FLOOR SUPPORT — CORRODED (BS 255) · corrosion level 2 · airframe 61,981 hrs · 46,488 cycles

CORROSION WAS FOUND ON THE LAVATORY FLOOR SUPPORT STRUCTURE AT BS 255 BETWEEN X=22 & X=44. FLOOR SUPPORT STRUCTURE WAS REPAIRED IAW SRM 51-30-05 & 51-10-3 PAR 14/21.

Part: RETAINER — CORRODED (SERVICE DOOR) · corrosion level 2 · airframe 61,981 hrs · 46,488 cycles

DURING SCHEDULED HEAVY MAINTENANCE, CORROSION WAS FOUND ON THE FWD SERVICE DOOR SEAL RETAINER LOWER SECTION. CORROSION ON STRAP WAS REMOVED IAW SRM 51-10-3 PAR 26 AND THE STRAP WAS TREATED AND PAINTED IAW SRM 51-10-3 PAR 14 AND 21 , THE STRAP WAS INSTALLED IAW SRM 51-30-1.

Part: LONGERON — CRACKED (BS 160) · airframe 61,981 hrs · 46,488 cycles

CRACKED LONGERON 3L BS 160 AT PAX CABIN. CRACKED LONGERON REMOVED. REPLACED WITH A NEW SECTION IAW 53-02, FIG 18.

Part: LONGERON — CRACKED (BS 160) · airframe 61,981 hrs · 46,488 cycles

CRACKED LONGERON 2L BS 160 AT PAX CABIN. CRACKED LONGERON REPLACED FOR A NEW IAW SRM 53-14, SRM 51-30-2, & SRM 51-30-05.

Part: CAMSHAFT — CORRODED (TAILCONE RELEASE) · airframe 61,981 hrs · 46,488 cycles

MX DISCOVERED THAT THE EMERGENCY ESCAPE PATH TAILCONE RELEASE CABLE CAM SHAFT HAD CORRODED HARDWARE. THE NUTS WERE REPLACED AND THE SYSTEM WAS ADJUSTED.

Part: SKIN — CRACKED (BS 1418) · airframe 61,992 hrs · 46,495 cycles

CRACK ON INNER FUSELAGE SKIN AT BS 1418 BETWEEN LONGERONS 1 - 2R IN AFT ACCESSORY COMPARTMENT, CRACK REMOVED, DOUBLERS AND FILLERS WERE FABRICATED AND INSTALLED IAW ER/A 494602-19AD, REV "C".

Part: TAB — CORRODED (RT ELEVATOR) · corrosion level 2 · airframe 61,981 hrs · 46,488 cycles

CORROSION FOUND ON THE RT ELEVATOR CONTROL TAB L/E. THE RT ELEVATOR CONTROL TAB WAS REPLACED AND THE REQUIRED INSPECTION WAS COMPLETED.

Part: BATTERY PACK — INOPERATIVE (EMERGENCY LIGHT) · airframe 61,520 hrs · 46,144 cycles

DURING LINE CHECK, MX FOUND THAT THE FLOOR MOUNTED EMERGENCY PATHWAY LIGHTING AT ROWS 17-22 OF THE CABIN, WERE INOPERATIVE. MX REPLACED THE BATTERIES AT ROW 17 AND THE LIGHTS RETURNED TO AN OPS CONDITION.

Part: WIRE — BROKEN (EMERGENCY LIGHT) · airframe 61,435 hrs · 46,075 cycles

DURING LINE CHECK, MX FOUND THAT THE EMERGENCY PATHWAY LIGHTING AT ROWS 18E-23E IN THE CABIN WERE INOPERATIVE. MX FOUND A BROKEN WIRE AT 18E AND REPAIRED IT. THE SYS RETURNED TO NORMAL OPERATION.

Part: WIRE — LOOSE (EMERGENCY LIGHT) · airframe 61,260 hrs · 45,942 cycles

DURING LINE CHECK, MX FOUND THAT THE EMERGENCY PATHWAY LIGHTING IN ROWS 17-23 OF THE CABIN WERE INOPERATIVE. MX FOUND A LOOSE WIRE IN THE CONNECTOR, RESECURED IT, AND THE SYS RETURNED TO NORMAL OPERATION.

Part: FLOOR PANEL — DAMAGED (BS 1250-1271) · airframe 60,453 hrs · 45,383 cycles

AFT CARGO FLOOR PANEL PEELED BETWEEN BS 1250 AND 1271. FABRICATED DOUBLER IAW SRM 53-01, FIG 4. NO DEFECTS NOTED. TREATED AND PRIMED REPAIR PART. INSTALLED DOUBLER IAW SRM 53-01, FIG 4.

Part: TEE FITTING — DAMAGED (BS 1338) · airframe 60,453 hrs · 45,383 cycles

TEE FITTING CRACKED AND BUCKLED AT BS 1338 AT JACK PAD AREA. CRACKED ON BELLY FWD OF APU COMPARTMENT. REMOVED ALL DAMAGED PARTS, ACCOMPLISHED OPPORTUNITY INSPECTION OF SURROUNDING STRUCTURE. NO ADDITIONAL DAMAGE FOUND. APPLIED SEALANT AND CORBAN TO THE REPAIR AREA. SEALED AREA IAW DWG 5910252 AND APPLIED CORBAN. C/W PRI ER/A 509741-14, REV 2. REIDENTIFIED REPAIR AS PERMANENT IAW STEP 16 OF FINAL ER/A 509741-14, REV ORIGINAL.

Part: CAP — LEAKING (APU OIL) · airframe 59,835 hrs · 44,928 cycles

CABIN CREW REPORTED AN OILY ODOR WITH FAINT SMOKE IN THE CABIN SHORTLY AFTER TAKEOFF. EVENTUALLY IT ALL DISSIPATED, BUT THEN IT REOCCURRED WHEN THE APU WAS STARTED AT THE ARRIVAL GATE. MAINTENANCE FOUND THAT THE APU OIL CAP WAS LEAKING. THE OIL CAP WAS REPLACED, THE APU INLET CLEANED, A DUCT BURNOUT WAS PERFORMED, AND THE COALESCER BAGS WERE REPLACED. THE AIRCRAFT HAS RETURNED TO SERVICE.

Part: BATTERY PACK — INOPERATIVE (EMERGENCY LIGHTS) · airframe 59,272 hrs · 44,530 cycles

DURING LINE CHECK, MAINTENANCE FOUND THAT THE OVERHEAD EMERGENCY PATHWAY LIGHTING IN ROWS 11-15 OF THE CABIN WERE INOPERATIVE. MAINTENANCE REPLACED THE BATTERIES IN THE POWER SUPPLY AND THE LIGHTS RETURNED TO AN OPERATIONAL CONDITION.

Part: SPAR — DAMAGED (VERTICAL STAB) · airframe 56,867 hrs · 42,912 cycles

DURING PSV VISIT IN MSP AN ELONGATED HOLE WAS FOUND ON THE LT SIDE OF THE VERTIAL STAB FRONT SPAR CHORD. THE SUBJECT HOLE WAS OPENED TO (0.218"). THE HOLE WAS OPENED IN THE SPAR CHORD TO ALLOW FOR 0.030" WALL MIN. ON REPAIR BUSHING. SEE FIG.1 DETAIL/LOCATION. BUSHING WAS INSTALLED AND A REPAIR STRAP WAS INSTALLED PER DRAFT SG0955005-7003 REPAIR.REPAIRS WERE COMPLETED PER ERA 494479-14, NR 226.

Part: SPAR — DAMAGED (VERTICAL STAB) · airframe 56,867 hrs · 42,912 cycles

DURING PSV VISIT IN MSP 6 DAMAGED HOLES WERE FOUND ON THE RT SIDE OF THE VERTICAL STAB FRONT SPAR CHORD. THE SUBJECT HOLES WERE OPENED TO NR 1-(0.218") NR 4-(0.218") NR 5-(0.218") NR -6(0.218") NR 7-(0.234") RESPECTIVELY. THE HOLES ARE OPENED IN THE SPAR CHORD TO ALLOW FOR 0.030 WALL MIN. ON EA. BUSHING. BUSHINGS ARE INSTALLED AT EACH LOCATION AND A REPAIR STRAP WAS INSTALLED PER DRAFT SG0955005-7003 REPAIR. DURING THE REPAIR THE FORTH HOLE BELOW NR 1 WAS DAMAGED AND REQUIRED OVERRSIZE TO .246 TO OBTAIN CLEAN HOLE. NOTE THAT ALL HOLES WERE OUT OF ROUND AND NO CRACKS WERE FOUND DURING INITIAL INSP ERA-494480-14.

Part: SKIN — CRACKED (FUSELAGE) · airframe 56,867 hrs · 42,912 cycles

DURING PSV VISIT IN MSP, A SKIN CRACK WAS FOUND AT FS 1418 AT L-2L APPROXIMATELY 2 INCHES IN LENGTH. THERE IS AN EXISTING REPAIR JUST FWD OF THE REPAIR AREA THAT THE NEW INTERNAL REPAIR DOUBLER WILL BUTT AGAINST, PREVIOUSLY INSTALLED PER SRM-53-04 FIG 23. THE SKIN IS MF 0.05" 2024-T3 CLAD. ERA 494602-14 REV O. ETOPS CATEGORY 'F': ANY OTHER EVENT DETRIMENTAL TO ETOPS

Part: SEAT TRACK — CORRODED (FUSELAGE) · airframe 1 hrs · 1 cycles

SEAT TRACK LBL 22 AND STA 1155 THRU 1240 CORROSION ON LUGS AND DOWN IN TRACK. REMOVED SEAT TRACK SECTION AND SPLICED PER MD88 SRM 53-01 AND SRM 53-05.

Part: SKIN — CRACKED (FUSELAGE) · airframe 56,867 hrs · 42,912 cycles

JULY 14 THIS AIRCRAFT WAS IN PSV IN MSP DEPT 260. DURING INSPECTION OF THE VERTICAL STAB A CRACK WAS VERIFIED AT STA 1401 L-2L. CRACK WAS REPAIRED PER ERA,494602-14_NON ROUTINE 108. ETOPS CATEGORY 'F': ANY OTHER EVENT DETRIMENTAL TO ETOPS

Part: FITTING — DAMAGED (FUSELAGE) · airframe 56,867 hrs · 42,912 cycles

REMOVED FASTENERS FOR FOR ACCESS AT L-28R & REMOVED SECTION OF SHEAR CLIP, SHEAR CLIP OUT OF LIMITS, MFG,D NEW CLIP OUT OF 7075T6 .071 CORROSION CONTAINED, INSTALLED SHEAR CLIP AT L-28R AND 1 RIVET AT L-28L. RESTORED PROTECTIVE FINISH. REPAIR COMPLETE PER SRM 53-01 FIG 1 NR 166. ETOPS CATEGORY 'F': ANY OTHER EVENT DETRIMENTAL TO ETOPS.

Part: BATTERY PACK — DISCHARGED (CABIN) · airframe 56,748 hrs · 42,824 cycles

DURING SERVICE CHECK MAINTENANCE FOUND EMERGENCY LIGHTS FROM ROW 17-23 INOPERATIVE. MAINTENANCE REPLACED POWER PACK FOR INOPERATIVE ROWS. OPERATION OF LIGHTS NOW CHECKS OK. BATTERY PACK WAS LAST REPLACED ON 06-04-11 FOR SAME FAULT.

Part: WIRE — BROKEN (CABIN) · airframe 56,595 hrs · 42,727 cycles

DURING LINE CHECK MAINTENANCE FOUND EMERGENCY EXIT LIGHTS AT ROW 17-23 INOPERATIVE. MAINTENANCE RE-SPLICED A BROKEN WIRE AT ROW 17 PER 20-50-01. OPERATION OF LIGHTS NOW CHECKS GOOD.

Part: BATTERY — ACTIVATED (CABIN) · airframe 56,595 hrs · 42,727 cycles

DURING LINE CHECK MAINTENANCE FOUND 1ST CLASS CEILING EMERGENCY EXIT LIGHT INOPERATIVE. MAINTENANCE REPLACED BATTERIES IN FIRST CLASS CEILING EMERGENCY EXIT POWER SUPPLY. OPERATION OF LIGHTS NOW CHECKS OK.

Part: BATTERY — DISCHARGED (CABIN) · airframe 56,595 hrs · 42,727 cycles

DURING LINE CHECK MAINTENANCE FOUND EMERGENCY LIGHTS IN ROWS 17-23. MAINTENANCE REPLACED BATTERIES IN BATTERY PACK AT ROW 17. OPERATION OF LIGHTS NOW CHECKS OK.

Part: LIGHT — CONTAMINATED (R1 GALLEY) · airframe 56,112 hrs · 42,388 cycles

DURING CRUISE FLIGHT ATTENDANT NOTICED THE R1 GALLEY LIGHT WAS MELTING SURROUNDING MATERIAL CAUSING NOXIOUS SMELL. THE CIRCUIT BREAKER FOR R1 GALLEY LIGHT UNDER F207 WAS PULLED AND COLLARED. MAINTENANCE INSPECTED AND FOUND LIGHT ASSEMBLY AND WIRES WERE BURNT DUE TO HOLE IN COMPARTMENT ABOVE 207 CAUSING FLUID CONTAMINATION. CORRECTIVE ACTION WILL REQUIRE COMPOSITE REPAIR OR NEW GALLEY AND LIGHT ASSEMBLY. ITEM IS TO REMAIN ON MEL.

Part: BATTERY PACK — INOPERATIVE (EMERGENCY LIGHTS) · airframe 55,416 hrs · 41,925 cycles

DURING LINE CHECK MX, FOUND LT AND RT OVERWING EXIT LIGHT INOPERATIVE. MX REPLACED BATTERY PACK IAW REF 33-53-00. OPS OF LIGHTS CHECKS OK.

Part: BATTERY PACK — INOPERATIVE (EMERGENCY LIGHTS) · airframe 54,549 hrs · 41,333 cycles

MX FOUND THE EMERGENCY FLOOR LIGHTS BETWEEN ROWS 17-23 TO BE INOPERATIVE. MX CHECKED BOTH EMERGENCY BATTERY PACKS AND FUSES, ALL CHECKED OK. MX RE-SECURED WIRING BETWEEN ROWS 16 AND 17. AN OPS CHECK WAS PERFORMED AND THE ACFT WAS RETURNED TO SERVICE.

Part: BATTERY — DISCHARGED (CABIN) · airframe 54,528 hrs · 41,322 cycles

MAINTENANCE FOUND THE EMERGENCY LIGHTS AT SEATS 17-23 TO BE INOPERATIVE. MAINTENANCE REPLACED THE BATTERIES AT B5-102. AN OPERATIONAL CHECK WAS PERFORMED AND THE AIRCRAFT WAS RETURNED TO SERVICE (2010-D0966) (DLM88102086).

Part: ENGINE — DAMAGED (NR 2) · airframe 54,288 hrs · 41,163 cycles

CLIMBING THROUGH 12000 RT ENGINE LOOP B ILLUMINATED FOLLOWED BY LOOP 1 AND FIRE HANDLE LIGHT FOR RT ENGINE. ENGINE WAS SHUT DOWN AND RTB SINGLE ENGINE EMERGENCY. INFLIGHT SHUTDOWN REPORT COMPLETED. FOUND 13TH STG DUCT TO EXIT CASE BLOWN. REPLACED NR 2 ENGINE PER TRANS 9T102AD.

Part: LIGHT — INOPERATIVE (SEAT 4C) · airframe 53,332 hrs · 40,493 cycles

DURING LAYOVER INSP FOUND EMERGENCY LIGHTING INOP AT SEAT 4C. R & R EMERGENCY LIGHT ASSY. CKS GOOD.

Part: RELAY — FAILED (ELECTRICAL) · airframe 49,880 hrs · 38,278 cycles

DUE TO LONG HISTORY OF BREAKERS POPPING AND SOME ELECTRICAL ODOR IN CABIN, WE LOOKED FOR AND FOUND CONNECTORS AND CURRENT LIMITERS ON THE T1,T2,AND T3 SIDE OF THE AC BUSS TIE RELAY WITH SEVERE HEAT DAMAGE. REPLACED AC BUSS TIE RELAY TWO FEEDER WIRES AND CURRENT LIMITERS ON THE T1,T2 AND T3 SIDE. POWER CHECKS GOOD IN ALL MODES.

Part: SCUFF PLATE — BROKEN (CARGO BAY) · airframe 47,649 hrs · 36,773 cycles

WEAR DEFORMED AND BROKEN SCUFF PLATE OF AFT CARGO BIN. REPLACED SCUFF PLATE PER DWG 5936070.

Part: SKIN — CRACKED (BS 1437 S2-5R) · airframe 47,649 hrs · 36,773 cycles

DURING HMV AT GDL, SKIN CRACKS WERE FOUND AT STA 1437 BETWEEN S-2R AND S-5R. THE CRACKS WERE REMOVED AND REPAIRED PER ER/A 464563-14.

Part: SKIN — DAMAGED (BS 598 S22R) · airframe 47,649 hrs · 36,773 cycles

LIGHTNING STRIKES AT L-22R FS 598 RESULTED IN TWO 1.25" DIAMETER HOLE CUTOUTS. AN INTERNAL TITANIUM FINGER DOUBLER WAS INSTALLED AS THE REPAIR.

Part: RIB — CRACKED (LWS 453) · airframe 47,649 hrs · 36,773 cycles

CRACK ON LT WING FIXED LEADING EDGE RIB STA XFS=453. REPLACED RIB PER DWG 9919329-9.

Part: RIB — CRACKED (LWS 446) · airframe 47,649 hrs · 36,773 cycles

CRACK ON LT WING FIXED LEADING EDGE RIB STA XFS=446. RIB REPLACED PER DWG 9919329-7.

Part: ANGLE — CRACKED (BS 1003) · airframe 47,649 hrs · 36,773 cycles

CRACK ON ANGLE AT STA Y=1003 BTWN X=7 AND X=-7 KEEL BEAM AREA. REPLACED ANGLE PER DWG 5936395 AND SRM 51-30-1/51-30-2/51-30-5.

Part: ATTACH FITTING — CORRODED (BS 1155) · airframe 47,649 hrs · 36,773 cycles

CORROSION ON STRUCTURE AT STA 1155 BTWN LONGERON 29 AND 28 RT. REPLACED CLIP PER DWG 9936073.

Part: ANGLE — WORN (FUSELAGE) · airframe 47,649 hrs · 36,773 cycles

WORN LT LWR ANGLE AT AFT ENTRY DOOR, REPLACED ANGLE PER DWG 9915565.

Part: ATTACH FITTING — BROKEN (BULKHEAD) · airframe 47,649 hrs · 36,773 cycles

BROKEN CLIP ON O/B END OF P-DOME LT NR 3 STIFFENER. REPLACED CLIP PER DOUGLAS DWG 9915558.

Part: FLOORBEAM — CRACKED (BS 650 S25-26R) · airframe 47,649 hrs · 36,773 cycles

CRACK ON FLOOR SUPPORT STA Y=650 BTWN LONGERON 25 RT AND 26 RT REPAIRED PER ERA 413029-14MA.

Part: SKIN — CORRODED (BS 712-731) · airframe 47,649 hrs · 36,773 cycles

CORROSION DAMAGED THE SKIN AND DOUBLER FROM FS 712 TO 731 BETWEEN L-29L AND L-28R. A PREVIOUS REPAIR, ER/A 363898-14,WAS ALSO IN THIS AREA. A MX SPLICED THE SKIN AND DOUBLER FROM FS 655 TO FS 759 AT THE C-2 DOOR.

Part: CUSP WEB — CORRODED (BS 984-1003) · airframe 47,649 hrs · 36,773 cycles

CORROSION ON RT CUSP WEB AT STA Y=984 TO Y=1003. REPLACED WEB PER DWG 9930612.

Part: SUPPORT — CORRODED (L2 DOOR SLIDE) · airframe 47,649 hrs · 36,773 cycles

CORROSION ON AFT SLIDE SUPPORT AT L2. REPLACED SUPPORT PER SRM DWG 9930612.

Part: SUPPORT — CORRODED (L2 DOOR SLIDE) · airframe 47,649 hrs · 36,773 cycles

CORROSION ON FWD SLIDE SUPPORT AT L2 DOOR. REPLACED SUPPORT PER SRM 51-30-50, 51-10-4.

Part: CUSP WEB — CORRODED (BS 508) · airframe 47,649 hrs · 36,773 cycles

CORROSION ON RT CUSP WEB AT STA Y=508, REPLACED SECTION OF WEB PER DWG 9930538.

Part: CUSP WEB — CORRODED (BS 1041-1022) · airframe 47,649 hrs · 36,773 cycles

CORROSION ON LT CUSP WEB BETWEEN STA Y=1041 TO Y=1022. REPLACED SECTION OF WEB PER DWG 9930612.

Part: SUPPORT — CORRODED (R1 DOOR SLIDE) · airframe 47,649 hrs · 36,773 cycles

CORROSION RT AFT SLIDE SUPPORT AT R1 DOOR. REPLACED SUPPORT PER SRM 51-30-1, 51-10-4.

Part: SUPPORT — CORRODED (R1 DOOR SLIDE) · airframe 47,649 hrs · 36,773 cycles

CORROSION ON FWD SLIDE SUPPORT AT R1, REPLACE SUPPORT PER SRM 51-30-1, 51-10-4.

Part: THRESHOLD — CORRODED (R1 DOOR) · airframe 47,649 hrs · 36,773 cycles

CORROSION ON WEB THRESHOLD AT R1. REPLACED THRESHOLD PER DWG 9957828.

Part: THRESHOLD — CORRODED (R1 DOOR) · airframe 47,649 hrs · 36,773 cycles

FOUND CORROSION ON PLATE THRESHOLD AT R1. REPLACED PLATE THRESHOLD PER DWG 9957828.

Part: WEB — CORRODED (BS 1140) · airframe 47,649 hrs · 36,773 cycles

CORROSION ON WEB AT STA Y=1140 AND X=54. REPAIR PER SRM 51-30-5.

Part: OVEN — SMOKE (GALLEY) · airframe 44,533 hrs · 34,630 cycles

CREW REPORT FROM F/A THAT HAD LIGHT HAZY SMOKE IN THE FWD AND MID CABIN BUT HEAVIEST IN FWD GALLEY AREA. BURNING NON-ELECTRICAL SMELL. FLT CREW COULD SMELL IN COCKPIT BUT NO VISIBLE SMOKE. C/W OP 5088. FOUND FC OVEN OVERHEATING AND CAUSING BURNING SMELL IN FC CABIN AND COCKPIT. REMOVED OVEN CANNON PLUG AND PULLED C/B. SEE ITEM 3 FOR OVEN MCO. REPLACED OVEN OPS NML MCO/PLACARD REMOVED.

Part: SKIN — GROUND DAMAGE (FUSELAGE) · airframe 44,337 hrs · 34,502 cycles

JETWAY CONTACTED FUSELAGE SKIN AT FS 133 - FS 148, SKIN GOUGED TO A DEPTH OF .015 INCHES. REPAIRED PER SRM 53-04 FIG 12B CLASS 1 PERMANENT REPAIR.

Part: UNKNOWN — UNKNOWN (UNKNOWN) · airframe 43,901 hrs · 34,208 cycles

DURING DESCENT WHEN SPEED BRAKE/ SPOILER HANDLE WAS MOVED AFT RT HYD SYS PRESS DROPPED TO 0 AND QTY EVENTUALLY INCREASED FROM 13 TO 18. LATER WHEN SLAT HANDLE MOVED TO EXTEND LEFT HYD PRESS DROPPED TO 0 AND LEFT QTY INSP AND REPLACED SYS PRESS RETURN CASE DRAIN FILTERS BOTH SIDE NO METAL FOUND. NDS LEAK CHECKED SERVICED BOTH HYD SYS AND BLED SYS. LEAK CHECKS OK, RAN ALL HYD SYSTEMS, PRESS INDICATIONS NORMAL.

Part: ACTUATOR — BROKEN (NLG) · airframe 41,789 hrs · 32,669 cycles

LOUD BANG WHEN GEAR RETRACTION ATTEMPTED. NLG WOULD NOT LOCK UP. GOT THREE GREENS WHEN HANDLE PLACED BACK TO DOWN. FOUND NLG RETRACT ACTUATOR BROKEN AND ROD END PULLED OUT OF ACTUATOR. ROD END HAD FALLEN BACK AND MOVEMENT OF GEAR CAUSED PENETRATION THROUGH WHEEL WELL BULKHEAD. REPLACED ACTUATOR AND REPAIRED DAMAGE

Part: UPLOCK — BROKEN (RIGHT MLG) · airframe 37,409 hrs · 29,658 cycles

GEAR DOOR OPEN LIGHT REMAINED ON AFTER GEAR EXTENSION. EXECUTED A GO AROUND AND COMPLIED WITH POM PROCEDURES TO UNEVENTFUL LANDING. FOUND MAIN LANDING GEAR LATCH FOLLOW UP MECHANISM ATTACH BOLT BROKEN REF IPC 32-30-00-12A ITEM 126. REPLACED BOLT AND CYCLED DOORS SEVERAL TIMES. GEAR DOOR OPERATION IS NOW NORMAL.

Part: BULKHEAD — DAMAGED (FUSELAGE) · airframe 35,724 hrs · 28,482 cycles

DURING HMV-2, TOOLING DAMAGE WAS FOUND ON THE VERTICAL FLANGE OF PN 5910130387 AFT PRESSURE BULKHEAD TEE CAP AT STA 1338 BETWEEN L-29L TO L-29R, AND ON PN 5910130285 PRESSURE BULHHEAD WEB. THE TEE CAP WAS SPICED PER MD80 SRM 53-03, FIG 37. THE WEB WAS REPAIRED PER MD80 SRM 53-05, FIG 116. A TITANIUM DOUBLER WAS USED TO REPAIR THE SKIN THAT WAS CUT OUT FOR ACCESS.

Part: HEATER — SHORTED (LAVATORY) · airframe 33,588 hrs · 26,919 cycles

SMOKE REPORTED ON APPROACH TO ATL IN AFT LT LAV. FOUND AFT LT LAV WATERLINE HEATER SHORTED CAUSING TEFLON TAPE TO MELT. REPLACED HEATER.

Part: SKIN — CORRODED (FUSELAGE) · airframe 33,454 hrs · 26,813 cycles

CORROSION DAMAGE FOUND IN FUSELAGE SKIN AT FS 636, L30. CORROSION WAS REMOVED AND REPAIRED PER ERA 412319-14.

Part: SEAL — BENT (T/E FLAP) · airframe 33,454 hrs · 26,813 cycles

THE LT WING LOWER SKIN WAS FOUND WORN AT APPROX XRS 108 AT THE WING REAR SPAR. DAMAGE CAUSED BY BENT FWD EDGE OF SEAL ANGLE (P/N 5856281-15) OF FLAP HINGE FAIRING. DAMAGE WAS BLENDED SMOOTH AND REWORKED PER ERA 412307-14, REV A.

Part: THERMOSTAT — FAILED (RT ENGINE) · airframe 31,370 hrs · 25,290 cycles

CREW DECLARED EMERGENCY - UNABLE TO MAINTAIN CABIN ALTITUDE WHEN CLIMBING FROM 35K TO 37K WITH FLOW LT ON AND 1200FPM CABIN RATE OF CLIMB- MAX CABIN ALTITUDE WAS 11K. NO MASKS DEPLOYED. AT 10K WITH OUTFLOW VALVE FULLY CLOSED CABIN ALT WAS 1K WITH 4.5PSID MAINTAINED. REPLACED RT AUG VALVE ANTICIPATOR THERMOSTAT

Part: COALESCER BAG — CONTAMINATED (AC BAY) · airframe 31,310 hrs · 25,239 cycles

IMMEDIATELY AFTER T/O, F/A CALLED TO REPORT FUMES IN CABIN, NO VISUAL INDICATIONS. RETURNED TO AIRPORT AFTER DECLARING EMERGENCY. FOUND OIL IN APU INLET. PERFORMED DUCT BURNOUT.

Part: SKIN — DENTED (FUSELAGE) · airframe 29,658 hrs · 24,010 cycles

THE FUSELAGE SKIN BETWEEN FS 294 & 313 AND BETWEEN STRINGERS 22L & 24L WAS BADLY DAMAGED BY GROUND EQUIPMENT. THE DAMAGED AREA OF SKIN WAS CUT OUT AND REPAIRED WITH AND EXTERNAL ALUMINUM DOUBLER PER ER/A 378025-14, REV B.

Part: ENGINE — HOT START (NR 2) · airframe 29,171 hrs · 23,665 cycles

ON STARTING THE RIGHT ENGINE, RECEIVED A HOT START INDICATION (612 EGT). AFTER FOLLOWING THE ABORTED START PROCEDURE CREW WAS INFORMED OF A TAILPIPE FIRE. COMPLETED THE TAILPIPE PROCEDURE AND RETURNED TO GATE. THE FIRE CREW PUT OUT THE TAILPIPE FIRE. PEAK TEMP 612 MOMENTARY. REPLACED ENGINE, REPLACING NR 2 ENGINE.

Part: ANGLE — CRACKED (BS 1474)

THE RT VERTICAL STABILIZER TO FUSELAGE ATTACH ANGLE WAS FOUND WITH A 1.5 CRACK ALONG THE I/B FASTENER ROW OF THE HORIZONTAL FLANGE OF THE ANGLE. THE CRACKED AREA OF FLANGE WAS CUT AWAY AND REPAIRED WITH A STEEL REPAIR ANGLE PER ER/A 368626-14, REV A.

Part: OVEN — SMOKING (GALLEY)

AFTER TAKEOFF, FWD GALLEY OVEN STARTED SMOKING, FLT ATT REPORTED SMOKE WAS WHITE. GALLEY TURNED OFF, CB PULLED AND SMOKE STOPPED.

Part: BALLAST — BURNED (CABIN)

JUST BEFORE PUSHBACK, THE SIDE WALL LIGHT, CAPT SIDE OF FIRST CLASS BURNED OUT, RELEASING A FAINT ELECTRICAL SMOKE SMELL. DISCONNECTED BALLAST AT 1 AB FWD TO MCO 25-00-12. INSPECTED AREA FOR DAMAGE, NONE FOUND.

Part: LIGHT BALLAST — SHORTED (CABIN)

BURNING SMELL AND SMOKE COMING FROM AREA OF ROW 26. OVERHEAD LIGHTS FLICKERING AT ROW 26 AT THE SAME TIME SMELL OCCURED. DEACTIVATED BALLAST FOR OVERHEAD AND SIDEWALL LIGHTS FOR ROW 26 E/D. SECURED CONNNECTORS FOR BALLASTS. FOUND BALLAST SHORTED. REPLACED BALLAST.

Part: ACTUATOR — FAILED (LT MLG DOOR)

ON GEAR RETRACTIONS RED LIGHT RT MAIN GEAR EXTENDED 3 GREEN BUT GEAR DOOR OPEN LT ON. FLIGHT RETURNED TO BOS. FOUND BROKEN TORQUE SHAFT. REPLACED RT GEAR DOOR AND DOOR ACTUATOR.

Part: RADAR — FAILED (EE COMPT)

DURING CLIMBOUT, HAD TWO AIR TURNBACKS DUE TO FAILURE OF WEATHER RADAR. REPLACED AHARS, TRSCVR AND ANTENNA. OPERATION NORMAL.

Part: ANGLE — CRACKED (AFT KEEL BEAM)

FOUND ON D-1 LETTER CHECK, CROSSOVER ANGLE CRACKED BOTH LT AND RT CORNERS AFT OF KEEL BEAM. REPAIRED PER SRM 53-05 FIG 101.