N928DL

Part: BATTERY PACK — DISCHARGED (EMERGENCY LIGHTS) · airframe 73,625 hrs · 55,405 cycles

EMERGENCY LIGHTS INOPERATIVE AT FORWARD GALLEY AND OVERHEAD AT ENTRY DOOR. INSTALLED A NEW BULB IN THE FWD GALLEY RED LIGHT AND CHARGED THE BATTERIES.

Part: BRACKET — BROKEN (TAILCONE LOCK) · airframe 73,625 hrs · 55,405 cycles

TAIL CONE CAM LOCK RECEPTACLE BRACKET BROKEN FOR ACCESS DOOR. FABRICATED A NEW BRACKET AND INSTALLED IAW DWG 5940163.

Part: HINGE FITTING — CRACKED (RT WING) · airframe 73,625 hrs · 55,405 cycles

RIGHT WING REAR SPAR LOWER CAP INBD HINGE FITTING AT XRS 164 SHOWS A CRACK INDICATION. REPAIRED IAW DRAWING J060271-510 AND ER/A 552142-14AD, REV. ORIG.

Part: SPAR CAP — CRACKED (RT WING) · airframe 73,625 hrs · 55,405 cycles

RIGHT WING WS 164 INTERNAL SPAR LOWER CAP HAS 1/8 INCH LONG CRACK RUNNING FROM UNDER RIB END FITTING TO RADIUS. REPAIRED IAW DRAWING J060271-510 AND ER/A 552142-14AD, REV. ORIG.

Part: FUSE — FAILED (EMERGENCY LIGHTS) · airframe 73,296 hrs · 55,149 cycles

13ED TO 30ED EMERGENCY LIGHTS INOPERATIVE. TROUBLESHOT IAW WDM 33-51-14. REPLACED FUSE IAW CMM 33-21. CHECKED GOOD.

Part: BATTERY PACK — DISCHARGED (CABIN) · airframe 73,197 hrs · 55,062 cycles

OVERWING EMERGENCY LIGHT INOPERATIVE. R & R B5-49 BATTERY PACK REF AMM 33-53. OPS CK GOOD.

Part: WIRE — DAMAGED (EMERGENCY LIGHT) · airframe 73,160 hrs · 55,032 cycles

EMERGENCY LIGHT 19CD. TERMINATED SPLICE AT 19CD IAW SWPM 20 AND EWIS. OPS CHECKED GOOD.

Part: ACTUATOR — FAILED (MLG) · airframe 72,960 hrs · 54,880 cycles

RETURNED TO DEPARTURE, DUE TO RIGHT MAIN LANDING GEAR UNSAFE INDICATION AFTER GEAR RETRACTION. RIGHT MAIN LANDING GEAR RETRACT ACTUATOR FOUND TO BE BYPASSING. REPLACED ACTUATOR PER AMM 32-32-02. COMPLIED WITH NO-GO ODI PREVENTION. CYCLED GEAR 15 TIMES. ALL OPS CHECKED NORMAL.

Part: CABLE — BROKEN (NLG STEERING) · airframe 70,267 hrs · 52,955 cycles

BREAK TENSION NOSE WHEEL STEERING CONTROL SYSTEM CABLES ARE BROKEN. REPAIRED IAW AMM 32-51-00.

Part: INLET — DIRTY (APU) · airframe 68,532 hrs · 51,753 cycles

CREW REPORTED LIGHT HAZE AND BURNING ODOR IN FORWARD CABIN WITH FIRST CLASS LAVATORY SMOKE DETECTOR SOUNDING DURING CLIMBOUT. CREW REDUCED POWER AND HAZE/ODOR DISSIPATED. PROBLEM RETURNED WITH POWER RE-APPLIED. THE ACFT WAS RETURNED TO DEPARTURE. MAINTENANCE INSPECTED BOTH ENGINE INLETS, EXHAUST, AND UNDER COWLING FOR OIL LEAKS, NONE FOUND. INSPECTED GEAR, FLAPS, SPOILERS, TAIL SECTION, THRUST REVERSER CONTROL VALVES FOR HYDRAULIC LEAKS, NONE FOUND. ACCOMPLISHED FULL DUCT BURN OUT. APU INLET BOX REMOVED, CLEANED, AND RE-INSTALLED.

Part: SKIN — CRACKED (BS 1380) · airframe 67,274 hrs · 50,837 cycles

TAIL EXTERIOR, SKIN CRACKED AT STA 1380, JUST ABOVE LONGERON 13L. INSTALLED DOUBLER IAW ER/A 524784-14, REV O, WORK ACCOMPLISHED ON PRI 524784-14 AND N/R 103.

Part: FRAME — CRACKED (BS 1429) · airframe 67,274 hrs · 50,837 cycles

LT VERTICAL BS 1429 FRAME WEB CRACKED FWD SIDE, BETWEEN L6 AND L7. REMOVED TAIL ANTI ICE DUCT IAW AMM 30-10-17. REPAIRED LT VERTICAL WEB FRAME STA 1437 WEB CRACK BETWEEN L-8 AND L-9 IAW ER/A 519146-14MA. INSTALLED TAIL ANTI ICE DUCT IAW AMM 30-10-17. NR 125 ASSOCIATED ER/A 14-519146 ADDED FOR AC 0928.

Part: SKIN — DAMAGED (FUSELAGE) · airframe 66,049 hrs · 49,999 cycles

CARGO DOOR SURROUND DOUBLER DAMAGED. REMOVED DOOR DOUBLER. REPAIR INSTALLED ON NR 18 IAW ER/A 518711-14.

Part: SKIN — DAMAGED (BS 712-740) · airframe 66,049 hrs · 49,999 cycles

FUSELAGE SKIN DAMAGE FS 712 - 740 BETWEEN L23-26R. DAMAGE REMOVED IAW SRM 53-04, FIG12C 660169. PERFORMED HFEC ON CUT-OUT AREAS IAW NDT MAN PT 6 CH 6-10-01.001. NO CRACKS NOTED. REPAIR INSTALLED IAW SRM 53-04, FIG 12C.

Part: SKIN — DAMAGED (FUSELAGE) · airframe 66,049 hrs · 49,999 cycles

FUSELAGE SKIN DAMAGED AFT OF NR 2 CARGO DOOR, DAMAGE REMOVED AND REPAIRED IAW SRM 53-04, FIG 12C.

Part: FRAME — DAMAGED (BS 712) · airframe 66,049 hrs · 49,999 cycles

FORMER AT FS 712 BETWEEN LONGERONS 21R-25R DAMAGED. REMOVED DAMAGES FRAME SECTION. INSTALLED NEW FRAME SECTIONS IAW SRM 53-04, FIG 12C. C/W PRI 518883-14, REV O.

Part: DOUBLER — DENTED (BS 730) · airframe 66,049 hrs · 49,999 cycles

INTERNAL DOUBLER DENTED AT FS 730 BETWEEN L29R AND L28R. DAMAGE R & R IAW PRI 518871-14 REV 1 ON N/R 12.

Part: DOUBLER — DENTED (BS 728) · airframe 66,049 hrs · 49,999 cycles

INTERNAL DOUBLER DENTED FS 728 BETWEEN L28R AND L27R. DAMAGE R & R IAW PRI 518871-14, REV 1 ON N/R 12.

Part: DOUBLER — CRACKED (BS 725) · airframe 66,049 hrs · 49,999 cycles

INTERNAL DOUBLER CRACKED AND DENTED FS 725 AT L29R. HFEC VERIFIED CRACK AND MARKED ENDS. DAMAGE REMOVED AND REPAIRED IAW PRI 518871-14, REV 1 ON N/R 12.

Part: POWER SUPPLY — INOPERATIVE (EMERGENCY LIGHT) · airframe 64,467 hrs · 48,882 cycles

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

Part: POWER SUPPLY — INOPERATIVE (EMERGENCY LIGHT) · airframe 64,264 hrs · 48,728 cycles

DURING LINE CHECK, MX FOUND THAT BOTH OF THE AFT OVERWING OVERHEAD EMERGENCY EXIT SIGNS WERE INOPERATIVE. MX REPLACED THE POWER SUPPLY AND THE LIGHTS RETURNED TO AN OPERATIONAL CONDITION.

Part: POWER SUPPLY — INOPERATIVE (EMERGENCY LIGHTS) · airframe 64,222 hrs · 48,694 cycles

DURING LINE CHECK, MX FOUND THAT THE EMERGENCY EXIT SIGN LIGHTS OVER THE LT AND RT SIDES OF ROW 25 IN THE CABIN WERE INOPERATIVE. MX REPLACED THE POWER SUPPLY AND THE LIGHTS RETURNED TO AN OPERATIONAL CONDITION.

Part: SLIDE — DETACHED (R1 DOOR) · airframe 62,170 hrs · 47,232 cycles

FLIGHT CREW FOUND DOOR 1R SLIDE NOT ATTACHED PROPERLY. MAINTENANCE SECURED SLIDE. AIRCRAFT OKAY FOR SERVICE.

Part: BATTERY — DISCHARGED (CABIN) · airframe 62,058 hrs · 47,156 cycles

DURING LINE CHECK, MAINTENANCE FOUND THAT THE TWO OVERHEAD EMERGENCY ESCAPE LIGHTING IN THE MOST AFT SECTION OF THE CABIN WERE INOPERATIVE. MAINTENANCE REPLACED THE BATTERIES AND THE OPERATIONAL CHECK WAS GOOD.

Part: DOOR FRAME — CORRODED (CARGO BAY) · airframe 61,526 hrs · 46,821 cycles

SUPPLEMENT TO N/R T0226803. NEW BEAM, INTERCOSTALS STRAPS AND FLOOR SUPPORTS WERE INSTALLED IAW DC9/MD80 SRM 51-30-2 AND51-30-5 AND DOUGLAS DWG 5976038 REV A.

Part: DOUBLER — DAMAGED (FUSELAGE) · airframe 61,530 hrs · 46,823 cycles

HIDDEN DAMAGE; ELONGATED HOLES ON INNER PRODUCTION DOUBLER OF FUSELAGE SKIN AT STA Y=237 BTW LONGERONS 18LT AND 19LT. REPAIR ACCOMPLISHED ON N/R (TO 226870).

Part: SKIN — DAMAGED (FUSELAGE) · airframe 61,530 hrs · 46,823 cycles

HIDDEN DAMGE; ELONGATED HOLES ON EXTERNAL FUSELAGE SKIN FROM STA Y=229 TO Y=250 BTW LONGERONS 18LT AND 19LT. REPAIR WAS ACCOMPLISHED ON N/R (TO 226865).

Part: DOUBLER — DAMAGED (FUSELAGE) · airframe 61,526 hrs · 46,821 cycles

ELONGATED HOLES ON PREVIOUS REPAIR DOUBLER FROM STA Y=229 TO Y=250 AND LONGERON 18LT. DOUBLER REPAIR WAS ACCOMPLISHED IAW IAW ERA 334241-14 REV B.

Part: SKIN — DENTED (FUSELAGE) · airframe 61,530 hrs · 46,823 cycles

HIDDEN DAMAGE; DENT ON EXTERNAL FUSELAGE SKIN STA Y=231 AND LONGERON 19L. REPAIR ACCOMPLISHED ON N/R (T0 226875).

Part: SKIN — CRACKED (FUSELAGE) · airframe 61,526 hrs · 46,821 cycles

DURING HMV A CRACK WAS FOUND ON FUSELAGE SKIN AT STA Y=1418 BTW LONGERON 1 AND 2RT WITH 0.562" LENGTH. CRACK AREA ON FUSELAGE WAS CUT OUT AND FILLER, DOUBLER INSTALLED IAW ERA 497385-14 REV ORIG.

Part: BEAM — DAMAGED (FUSELAGE) · airframe 61,526 hrs · 46,821 cycles

ELONGATED HOLE ON AFT DOORJAMB BEAM STA Y=427 BTW LONG 24RT-25RT AT C1. REPAIRED PER ERA 497374-14 REV B.

Part: SKIN — DAMAGED (FUSELAGE) · airframe 61,526 hrs · 46,821 cycles

DURING HMV ELONGATED HOLES WAS FOUND ON FUSELAGE SKIN FROM STA Y=1418 TO 1422 BTW LONGERON 1 AND 2RT. CUT OUT DAMAGE AREA OF FUSELAGE SKIN AND INSTALLED FILLER, DOUBLER IAW ERA 497385-14 REV ORIG.

Part: FAIRING — WORN (VERTICAL STAB) · airframe 1 hrs · 1 cycles

DURING HMV WEAR WAS FOUND ON OUTER OF VERTICAL STABILIZER TIP FAIRING BETWEEN STA YV=200 AND 220 AT RT AND LT SIDE. BLEND OUT DAMAGE RT SIDE WITHIN LIMITS REF MD88 SRM 55-01 FIG 1 THE LT SIDE WAS REPAIRED IAW ERA 451447-14 REV A.

Part: CUSP WEB — CORRODED (FUSELAGE) · airframe 61,526 hrs · 46,821 cycles

SUPPLEMENT N/R T0225448. NEW SECTION OFF CUSP ANGLE WAS INSTALLED IAW DC9/MD80 SRM 53-05 FIG 25. (TO 225448) (NO ORIG MRR ENTRY FOR "SUPP INFO" TO ATTACH TO)

Part: FILLER — CORRODED (FUSELAGE) · airframe 61,526 hrs · 46,821 cycles

DURING HMV CORROSION WAS FOUND ON PREVIOUS REPAIR FILLER STA Y=1190=1194 BTW LONGERON 30 TO 29LT C3. FILLER WAS REPLACED IAW MD88 SRM 53-04D FIG 12B.

Part: PAN — CRACKED (C3 DOOR) · airframe 61,526 hrs · 46,821 cycles

DURING HMV A CRACK WAS FOUND ON C3 DOOR PAN AT FWD EDGE AND NR 4 BEAM INTERSECTION (UNDER DOOR STOP FITTING POSITION). DOOR PAN WAS STOP DRILLED AND DOUBLER WAS INSTALLED IAW MD88 SRM 52-05 FIG 50.

Part: FRAME — CRACKED (FUSELAGE) · airframe 61,526 hrs · 46,821 cycles

DURING HMV A CRACK WAS FOUND ON FRAME AT STAY=1451 AND LONGERON 1. CRACK ON FRAME WAS BLENDED OUT AND INSTALL FILLER, DOUBLER IAW MD88 SRM 53-03D FIG 4.

Part: FINGER DOUBLER — DAMAGED (FUSELAGE) · airframe 61,526 hrs · 46,821 cycles

DURING HMV NEED TO RE-EVALUATE OF REPAIR PARTS AT PREVIOUS FUSELAGE SKIN REPAIR ON STA Y=1316-1322 BTW LONGERON 18RT-21RT. REPLACED FINGER DOUBLER IAW MD88 SRM 53-04D FIG 12B.

Part: SKIN — CRACKED (FUSELAGE) · airframe 61,526 hrs · 46,821 cycles

DURING HMV CRACKS WERE FOUND ON FUSELAGE SKIN AT STA Y=373.750 OF 0.046" LENGTH,Y=374.750 OF 0.046" LENGTH, Y=375.250 OF 0.031" LENGTH AND Y=376.0 OF 0.093" LENGTH OF THE FWD CARGO DOOR JAMB UPPER CORNER. DAMAGED SKIN WAS CUT OUT AND DOUBLERS INSTALLED IAW MD88 SRM 53-05 FIG 105.

Part: SKIN — CORRODED (BS 370-389) · corrosion level 2 · airframe 61,526 hrs · 46,821 cycles

DURING HMV CORROSION WAS FOUND ON SKIN BS 370-389 BETWEEN LONGERONS 28-30L IN FWD CARGO COMPARTMENT. REPAIRED IAW SRM 53-04D FIG 12B.

Part: CUSP WEB — CORRODED (BS 1117-1198) · airframe 61,526 hrs · 46,821 cycles

DURING HMV, CORROSION WAS FOUND ON RT CUSP WEB. REPAIRED IAW SRM 53-20-02D.

Part: ANGLE — CORRODED (BS 148-160) · airframe 61,526 hrs · 46,821 cycles

DURING HMV, CORROSION WAS FOUND ON CUSP WEB ANGLE FROM BS 148-160 X=-52--60. CUSP WEB WAS REPAIRED IAW ERA 497030-15 REV ORIG.

Part: SKIN — DAMAGED (WINDOW BELT) · airframe 61,526 hrs · 46,821 cycles

DURING HNV, LIGHTNING STRIKE WAS FOUND ON LEFT WINDOW BELT FRAME LOWER EDGE STA 275-712 LOWER AFT EDGE. REPAIRED IAW ERA.

Part: CUSP WEB — CORRODED (BS 1193-1250) · airframe 61,526 hrs · 46,821 cycles

DURING HMV, CORROSION WAS FOUND ON RT CUSP WEB BTW X-54--60 BS 1193-1250. THE CUSP WEB WAS REPLACED IAW SRM 53-20-02D.

Part: ANGLE — CORRODED (BS 197) · airframe 61,526 hrs · 46,821 cycles

DURING HMV CORROSION WAS FOUND ON CUSP WEB ANGLE STA Y=197 BTW X=-54--60. ANGLE WAS REPAIRED IAW ERA 497030-14 REV ORIGINAL AND DWG 9910078 REV JC.

Part: SKIN — CORRODED (FUSELAGE) · airframe 61,526 hrs · 46,821 cycles

DURING HMV CORROSION WAS FOUND ON DOUBLER REPAIR BELOW SCUFF PLATE OF L1 DOOR STATION 80-200. REPAIRED IAW SRM 53-04 FIG 12C.

Part: SKIN — CORRODED (FUSELAGE) · airframe 61,526 hrs · 46,821 cycles

DURING HMV CORROSION WAS FOUND ON OUTER FUSELAGE SKIN AT SETTLEMENT AREA OF FILLET PANELS RUB STRIPS SAT Y=727 BETWEEN L 21LT AND 22LT,STA Y=750-807 BETWEEN L 26LT TO 30,STA Y=788-807,Y=845,Y=940-1003 BETWEEN L 16LT AND 18LT FUSELAGE SKIN WAS REPAIRED IAW MD88 SRM 53-04D FIG 53 AND BLENDED AREA WAS WITHIN LIMITS.

Part: SKIN — CORRODED (FUSELAGE) · airframe 61,526 hrs · 46,821 cycles

DURING HMV CORROSION WAS FOUND ON OUTER FUSELAGE SKIN AT SETTLEMENT AREA OF FILLET PANELS RUB STRIPS STA Y=940-1003 AND L 18LT AND STA Y=1079-1130 BETWEEN L 26LT AND 30. FUSELAGE SKIN WAS REPAIRED IAW MD88 SRM 53-04D FIG 53 BLENDED AREA WAS WITHIN LIMITS.

Part: SKIN — CORRODED (FUSELAGE) · airframe 61,526 hrs · 46,821 cycles

DURING HMV CORROSION WAS FOUND ON EXTERNAL SKIN AT RUBSTRIP SETTLEMENT AREAS FROM STA Y=864-867, Y=891-965,Y=991-1041 AT LONGERON 18RT FUSELAGE SKIN WAS REPAIRED IAW MD88 SRM 53-04D FIG 53. AREA BLENDED WAS WITHIN LIMITS PER SAME SRM.

Part: TAB — DELAMINATED (ELEVATOR) · airframe 61,526 hrs · 46,821 cycles

DELAMINATED L ELEVATOR CONTROL TAB WAS REPAIRED IAW MD88 SRM 55-04 PARA 3A.

Part: PLATE — CORRODED (VERTICAL STAB) · airframe 61,526 hrs · 46,821 cycles

DURING HMV AFTER REMOVAL REPAIR BUSHINGS ON INBD AND OUTBD PLATES OF VERTICAL STABILIZER CORROSION WAS FOUND IN BORES REF SRM 55-02 FIG 28 FOR REPAIR. REWORKED DAMAGED PLATES BORE AND INSTALLED BUSHINGS IAW ERA 497032-14 REV.

Part: SKIN — CORRODED (BS 737-831) · airframe 61,526 hrs · 46,821 cycles

DURING HMV CORROSION WAS FOUND ON EXTERNAL FUSELAGE SKIN AT RUBSTRIP SETTLEMENT AREA FROM BS 737-831 BETWEEN LONGERON 21R - 30R. FOUND WITHIN LIMITS IAW SRM 53-04D FIG 53 SHEET 8-9.

Part: SKIN — SCRATCHED (FUSELAGE) · airframe 61,526 hrs · 46,821 cycles

DURING HMV SCRATCHES ON OUTER FUSELAGE SKIN AT SETTLEMENT AREA OF FILLET PANELS RUB STRIPS STA Y=1117 TO 1130 BETWEEN LONGERON 20LT AND 26LT AND STA Y=946 TO 1003 PROJECTION TO LONGERON 18LT REF MD88 SRM 53-04 FIG 53 FOR REPAIR.

Part: FITTING — CORRODED (FUSELAGE) · airframe 60,937 hrs · 46,391 cycles

DURING PSV IN MSP FOUND LONGERON FITTING AT STA 1334 L29L CORRODED. FITTING REPLACED PER SRM 53-01.

Part: SWITCH — LEAKING (APU) · airframe 60,741 hrs · 46,263 cycles

DURING CLIMB THERE WAS A PACK ODOR, PACKS FULL COLD. FLIGHT ATTENDANTS REPORTED SMOKE DETECTORS IN LAVATORY SOUNDING. FLIGHT CREW WENT TO MANUAL ON PACKS AND SELECTED A WARMER SETTING. SMELL AND ALARMS CEASED IN ABOUT 2-3 MINUTES. OK REST OF FLIGHT. MAINTENANCE FOUND APU OIL LEAK AT LOP SWITCH. MAINTENANCE REPAIRED SAME. APU LEAK CHECK GOOD. APU INLET AREAS CLEANED AND PACK BURNOUT/OPN 5089 PERFORMED. MAINTENANCE ALSO REPLACED BOTH WATER SEPARATOR BAGS.

Part: WIRE — BROKEN (CABIN) · airframe 60,353 hrs · 46,013 cycles

CREW WROTE UP AT SEAT ROW 27DE FOUND WIRE BUNDLE FOR EMERGENCY LIGHTS EXPOSED AND ONE WIRE BROKEN. MAINTENANCE REPAIRED WIRE AND EMERGENCY LIGHTS NOW CHECK OK.

Part: CHARGER — INOPERATIVE (CABIN) · airframe 60,254 hrs · 45,945 cycles

ONCE POWER WAS REMOVED FROM THE AIRCRAFT THE EXTERNAL EMERGENCY LIGHT WOULD NOT EXTINGUISH. MAINTENANCE CYCLED POWER AND NO HELP. BATTERY CHARGER B5-49 WAS FOUND INOPERATIVE. CHARGER WAS REPLACED PER M/M 33-53. OPERATION OF LIGHTS NOW CHECKS OK.

Part: WIRE HARNESS — DAMAGED (EMERGENCY LIGHT) · airframe 59,620 hrs · 45,507 cycles

DURING LINE CHECK, MX FOUND EMERGENCY EXIT LIGHT AT 1CD INOPERATIVE. MX RE-TERMINATED THE WIRE HARNESS. OPERATION OF LIGHT NOW CHECKS OK.

Part: LANYARD — DISCONNECTED (EVAC SLIDE) · airframe 59,385 hrs · 45,355 cycles

CREW WROTE UP ON INBOUND FLIGHT THAT L2 DOOR SLIDE LANYARD WAS NOT CONNECTED TO SLIDE. MAINTENANCE RECONNECTED LANYARD IN COMPLIANCE WITH MD88 AMM 25-62-00-201. SLIDE BOTTLE PRESSURE CHECKS GOOD. (2010-D1360) (DLM88103190)

Part: THRESHOLD — CORRODED (CARGO BAY) · corrosion level 2 · airframe 59,070 hrs · 45,134 cycles

THRESHOLD CORRODED. CORROSION ON C-2 CARGO COMPARTMENT THRESHOLD. REPAIRED IAW SRM 53-05, FIG 123.

Part: DOOR FRAME — CORRODED (BS 1154-1211) · corrosion level 2 · airframe 58,856 hrs · 44,965 cycles

FOUND DURING OPN 57422 INSP OF CARGO DOOR JAMBS, CORROSION AT C-3 DOOR JAMB LOWER CUT-OUT, STA 1154 TO 1211. FABRICATED NEW STRAP IAW SRM 53-05, FIG 103. INSTALLED NEW STRAP IAW SRM 53-05, FIG 123.

Part: SKIN — CORRODED (BS 256-292) · corrosion level 2 · airframe 58,856 hrs · 44,965 cycles

FOUND 3 AREAS OF CORROSION, 1 AT APPROX STA 256 AND STR 29L ONE AT APPROX STA 256 AND STR 30 AND ONE AT STA 292 AND STR 30. REPLACED AFFECTED SKIN FROM FACTORY SPLICE TO STA 303 IAW ERA 484936-14 REV ORIG PERMANENT REPAIR.

Part: SPAR — DAMAGED (VERTICAL STAB) · airframe 58,856 hrs · 44,965 cycles

DURING FASTENER REMOVAL FOR ACCOMPLISHMENT OF EA 09-482741-14MA, OPN 8901 HAD ELONGATED HOLE ON VERTICAL STABILIZER LT FRONT SPAR CHORD COMMON TO CHORD AND OVERLYING SKIN PERFORMED TIME LIMITED REPAIR IAW ERA 484939-14 REV ORIG REPAIR LIMITED TO 24 MONTHS UNLESS OTHERWISE APPROVED.

Part: WIRE — LOOSE (EMERGENCY LIGHT) · airframe 58,468 hrs · 44,693 cycles

MAINTENANCE FOUND THE EMERGENCY PATH LIGHT AT SEAT 25C TO BE INOPERATIVE. MAINTENANCE FOUND A LOOSE WIRE AND RE-SECURED IT. AN OPS CHECK WAS PERFORMED AND THE AIRCRAFT WAS RETURNED TO SERVICE.

Part: LIGHT — INOPERATIVE (CABIN) · airframe 58,461 hrs · 44,687 cycles

MAINTENANCE FOUND THE EMERGENCY PATH LIGHT AT SEAT 21 TO BE INOPERATIVE. MAINTENANCE REPLACED THE LIGHT ASSEMBLY. AN OPS CHECK WAS PERFORMED AND THE AIRCRAFT WAS RETURNED TO SERVICE.

Part: LIGHT — INOPERATIVE (SEAT 11D) · airframe 57,847 hrs · 44,269 cycles

THE EMERGENCY LIGHT AT SEAT 11D WAS FOUND TO BE INOPERATIVE. MX REPLACED THE LIGHT ASSY. AN OPS CHECK WAS NORMAL AND THE ACFT WAS RETURNED TO SERVICE.

Part: LOCK — LOOSE (CABLE TURNBUCKLE) · airframe 57,394 hrs · 43,966 cycles

GEAR HANDLE WOULD NOT RAISE. QRH PROCEDURES COMPLETED. STILL UNABLE TO RAISE GEAR. GEAR HANDLE RELEASE BUTTON WAS FULLY RECESSED AIRBORNE AND WOULD NOT FUNCTION. JACKED AC. INSPECTED GEAR HANDLE AND ANTI RETRACTION LATCH. FOUND ANTI RETRACTION CABLE TURNBUCKLE LOCKS LOOSE. RE-RIGGED ANTI RETRACTION CABLE AND INSTALLED TURNBUCKLE CLIPS REF MM 32-31-01. PERFORMED SEVERAL GEAR SWINGS WITH NO PROBLEMS NOTED. COMPRESSED STRUT AND ANTI RETRACTION BUTTON FUNCTIONS NORMAL. EXTENDED AND RESERVICED STRUT. DOWN JACKED ACFT

Part: FRAME — CRACKED (FUSELAGE) · airframe 57,388 hrs · 43,962 cycles

FUSELAGE MAIN FRAME OVERWING CRACKED. REPAIRED IAW EA 09-460094-12, ME03.

Part: SKIN — DENTED (RT WING TE FLAP) · airframe 55,794 hrs · 42,884 cycles

MX FOUND THE DENT OUTSIDE OF ALLOWABLE LIMITS ON RT WING TE FLAP. REPAIR IAW ER/A 475220-14.

Part: HYDRAULIC SYSTEM — UNKNOWN (LEFT) · airframe 53,370 hrs · 41,265 cycles

LEFT HYD SYSTEM FAILED IN FLIGHT. LEFT HYD PRESS WENT TO ZERO WITH INCREASING QTY. QTY BEFORE EVENT 11, AFTER 19. ALTITUDE FL330 AUX PUMP OFF WHEN SPEEDBRAKE APPLIED. RAN ELECTRIC PUMPS, BLEED ALL AIR AND FOAM. RAN ENGINES, BLED ALL AIR AND FOAM AGAIN. SERVICED LEFT AND RIGHT SYSTEMS TO FULL PER M/M. SYSTEM HAS GOOD PRESSURE.

Part: SENSOR — WEAK (LT MLG) · airframe 52,584 hrs · 40,746 cycles

GEAR DOOR OPEN LIGHT ILLUM IN CRUISE. LIGHT EXTINGUISHED ONCE ON DESCENT STARTED. FOUND LT MAIN GEAR DOOR SENSOR OUT OF LIMITS NDS SENSOR P/N 279202670. REPLACED D1-30 PER MM DOOR INDICATIONS NORMAL SWU GEAR INDICATIONS NORMAL.

Part: POWER SUPPLY — INOPERATIVE (EMERGENCY LIGHTS) · airframe 51,210 hrs · 39,856 cycles

ON L/O, FOUND ROWS 27DE AND AFT E-PATH LIGHTS INOP. REPLACED POWER SUPPLY. OPS NML, S/N ON 11284, S/N OFF 3796, P/N 333701650.

Part: ODOR — DETECTED (COCKPIT) · airframe 42,050 hrs · 33,649 cycles

ON SHORT FINAL WITH ENG AND AIRFOIL A/I ON, THERE WAS A BURNING ODOR IN AFT CABIN AND F/O SIDE AFT LAV SMOKE DETECTOR WAS SOUNDING. ODOR CLEARED WHEN AIRFOIL A/I WAS TURNED OFF. CHECKED A/C FOR ENGINE AND HYDRAULIC LEAKS. NONE NOTED. PERFORMED OPN 5089 PNEU SYSTEM DUCT BURNOUT. CHECKS GOOD. ALSO PERFORMED OPN 5088 PNEU DIST CABIN SMOKE/ODOR TROUBLESHOOTING.

Part: SPLICE — BROKEN (1L DOOR) · airframe 39,501 hrs · 31,886 cycles

ON INSPECTION FOUND EMERGENCY EXIT LIGHT AT 1L DOOR INOP RELAMPED-NO HELP. FOUND WIRES DISCONNECTED BEHIND DOOR CLOSEOUT PANELS. REMOVED PANELS AND REPAIRED QUICK DISCONNECT CONNECTORS ON LIGHT ASSY. OPN OF LIGHT NORMAL. REPLACED REMOVED CLOSEOUT PANELS.

Part: CLAMP — LOOSE (#2 ENGINE) · airframe 38,046 hrs · 30,788 cycles

TAIL COMPT HIGH WARNING DURING CLIMBOUT CA FOUND RT CROSSBLEED VALVE CLAMP LEAKING TIGHTENED CLAMPLK CKS GOOD.

Part: CLAMP — LOOSE (A/C BAY) · airframe 37,965 hrs · 30,726 cycles

PASSING THROUGH 14000 FEET ON CLIMBOUT TAIL COMPARTMENT TEMP HIGH LIGHT CAME ON. HIGH PRESSURE BLEED TURNED OFF, NO HELP. RAN ABNORMAL CHECKLIST AND LIGHT WENT OUT AFTER TURNING OFF THE LEFT PACK. FOUND CLAMP LOOSE AND LEAKING DOWNSTREAM OF LEFT TEMP CONTROL VALVE. TIGHTENED SAME AND TIGHTENED OTHER CLAMPS IN AREA PRECAUTIONARY.

Part: SWITCH — FAILED (LT WING TANK) · airframe 33,994 hrs · 27,832 cycles

FUEL LEVEL LOW LIGHT ILLUMINATED PASSING 23,000 WINGS LEVEL AND REMAINED ON. *S/D* REPLACED LT TANK LOW LEVEL FLOAT SWITCH PER M/M 28-42-01, CKS GOOD.

Part: SKIN — DENTED (FUSELAGE) · airframe 32,490 hrs · 26,716 cycles

SKIN DENTS WERE FOUND AT FS 237 BETWEEN LONGERONS 18L AND 19L. THE DAMGAE WAS TRIMMED OUT AND REPAIRED WITH AN EXTERNAL DOUBLER PER ERA 334241-14 AT HMV.

Part: SKIN — DAMAGED (FUSELAGE) · airframe 32,490 hrs · 26,716 cycles

THE FUSELAGE SKIN AND INTERNAL DOUBLER WERE FOUND CREASED FROM FS 530 TO FS 541 BETWEEN L-20R AND L-20L. THE DAMAGE RESULTED IN A 2.75 X 12 CUTOUT IN THE FUSELAGE SKIN. ERA 334264-14 INSTALLS AN EXTERNAL DOUBLER AND REPLACES THE EXISTING INTERNAL SKIN DOUBLER. THE DAMAGE WAS FOUND AT HMV.

Part: WINDOW POST — LIGHTNING STRIKE (FUSELAGE) · airframe 32,490 hrs · 26,716 cycles

LIGHTNING DAMAGE TO THE OUTER SKIN WAS DISCOVERED ON THE LEFT HAND NR 7, 15, 21, 23 AND 25 WINDOW FRAMES. DAMAGE CLEAN-UP CONSISTED OF 6 SEPARATE BLENDS RANGING FROM .002- .006 IN DEPTH. ERA 368614-14 BLENDS AND TREATS THE DAMAGE AT ALL LOCATIONS AND INSTALLS A REPAIR AT WINDOWS NR 23 AND 25 PER SRO DRAWING 9530053 AND FIGURE 1 OF THE ERA. THE DAMAGE WAS ACTUALLY FOUND AT LETTER CHECK ON 10-28-1999 AND WAS ALLOWED TO REMAIN IN SERVICE AS A TIME LIMITED REPAIR UNTIL THE HMV OF MARCH OF 2000, WHEN THE PERMANENT REPAIR WAS INSTALLED.

Part: SKIN — DENTED (FUSELAGE) · airframe 32,490 hrs · 26,716 cycles

TWO DENTS WERE FOUND IN THE FUSELAGE SKIN. ONE DENT WAS LOCATED AT FS 218 AT L-18L AND THE OTHER WAS AT FS 240 BETWEEN L-17 LAND L-18L. THE DENTS WERE CUT OUT AND EXTERNAL REPAIRS INSTALLED PER ERA 334239-14 AT HMV.

Part: HANDLE — OUT OF RIG (MLG)

AFTER TAKEOFF, LANDING GEAR HANDLE WOULD NOT COME UP. ADJUSTED TURNBUCKLE ON GEAR HANDLE RELEASE CABLE. SERVICED STRUTS.

Part: COALESCER — DIRTY (CABIN)

SMOKE IN CABIN AFTER TAKEOFF. AFT LAV SMOKE DETECTOR ACTIVATED. CKD W/W'S FOR LEAKS, CKD HYD SVC BOTTLES, REPLACED AFT SMOKE DETECTORS, REPLACED WATER SEPARATOR BAGS. FOUND LT WATER SEPARATOR INLET OILY. REPLACED LT ACM, CLEANED APU INLET ASSY AND PLENUM. PERFORMED DUCT BURNOUT. RAN PACKS OFF APU PNEUMATICS AND PERFORMED HIGH POWER RUN. AFTER ENG RUN AND BURNOUT, REPLACED WATER SEPARATOR BAGS AGAIN, PRECAUTIONARY.

Part: SCHRADER VALVE — FAILED (NLG)

AFTER T/O, NOSE GEAR LIGHT REMAINED RED AND NOISE HEARD. GEAR DOOR LIGHT AND NLG PIN INDICATED NORMAL. WITH GEAR HANDLE DOWN ALL INDICATIONS NORMAL. FOUND NOSE STRUT BOTTOMED OUT. REMOVED AND INSPECTED SCHRADER VLV ON NOSE GEAR. FOUND PACKING IN POOR CONDITION. REPLACED VLV AND PACKING. SERVICED STRUT, JACKED A/C AND CYCLED GEAR. ALL INDICATIONS NORMAL.

Part: SKIN — DENTED (BS 582)

FUSELAGE SKIN FS 579-588, STRG 20L-21L : SKIN CUTOUT REPAIR FOR DENT. THE FUSELAGE SKIN BETWEEN FS 579 AND 588 AND BETWEEN STRINGERS20L AND 21L WAS BADLY DENTED BY IMPACT WITH GROUND EQUIPMENT. THE DAMAGED AREA OF SKIN WAS TRIMMED AWAY AND AN EXTERNAL ALUMINUM REPAIR DOUBLER WAS INSTALLED TO REPAIR THE DAMAGE. THE REPAIR WAS ACCOMPLISHED PER ER/A 365054-14, REV B.

Part: JAMB — CORRODED (C1 DOORWAY)

FUSELAGE DOOR SURROUND C1 DOOR, LOWER JAMB PAN, SPLICE REPAIR. THE LOWER JAMB PAN OF THE FWD CARGO DOOR OPENING WAS FOUND WITH EXTENSIVE CORROSION. THE CORRODED SECTION OF PAN WAS CUTOUT AND A NEW PIECE SPLICED IN PER THE GUIDLINES OF THE MD-88 SRM 53-05, FIG 44 AND AS DOCUMENTED IN ER/A 364000-14.

Part: SCHRADER VALVE — LEAKING (NLG STRUT)

UPON GEAR RETRACTION NOSE GEAR INDICATED UNSAFE. APPEARED GND PROX SWITCH NOT ACTUATED. LOWERED GEAR, ALL GEARS INDICATED GREEN. FOUND NLG STRUT FLAT DUE TO LEAKING SCHRADER VLV. REPLACED VLV, SVCD STRUT, NO LEAKS FOUND.

Part: LIGHT — FAILED (CABIN)

F/A OBSERVED AND SMELLED SPARKS COMING FROM AN EMERGENCY EXIT LIGHT AND SMELLED SMOKE. DIVERTED TO GSB. FOUND SMALL BURN ON LOWER AFT CORNER OF SIDEWALL PANEL. NOT AIRCRAFT RELATED. SUSPECT PASSENGER CARRY-ON DE-VICE.

Part: FILL LINE — LOOSE (AFT LAVATORY)

EMERGENCY DECLARED AT 8,000 FT, CLIMBING OUT OF ATL, DUE TO SMOKE SMELL REPORTED IN AFT CABIN. RETURNED TO ATL. MAINTENANCE FOUND EVIDENCE OF LAV FLUID COMING FROM FUSELAGE DRAINS. FOUND LAV FILL LINE LOOSE, TIGHTEND SAME. PERFORMED DUCT BURNOUT PER M/M. REPLACED COALESER BAGS, NO SMOKE SMELL NOTICED.

Part: LAMP — LOOSE (CABIN)

EMERGENCY LIGHTING STRIP 3RD RED LIGHT FROM FWD GALLEY WILL NOT LIGHT. RESECURED LAMP, OPS NORMAL.

Part: TURBINE — DAMAGED (NR 2 ENGINE)

CLIMBING THROUGH FL 240, FELT A STRONG JOLT AND LOUD BANG, THE RT ENGINE EPR AND N1 BEGAN TO DETERIORATE, BUT ALL ELSE WAS NORMAL. ENGINE SHUT-DOWN BEFORE LANDING. FOUND METAL IN T/P. CORRECTIVE-REPLACED NR 2 ENGINE AND T/R. REROUTED TO SHOP. SUPPLEMENT: (03-07-96). SHOP EXAMINATION SHOWED 3RD STAGE TURBINE INNER AIR-SEALING ANTI-ROTATION PIN (QTY-1) MISSING. PIN DAMAGED TURBINE BLADES, RESULTING IN TURBINE FAILURE.

Part: CONTROL PANEL — MALFUNCTIONED (AUTO THROTTLE)

DURING CLIMB PASSING APPROX 1,000 FT, AUTO THROTTLES WOULD NOT WORK, MODE CONTROL PANEL FROZE AND A/C HAD UNCOMMANDED ROLL/YAW. REPLACED DFGC CONTROL PANEL, RAN RTS ON DFGC 1 AND 2, BOTH SYSTEMS GO. CREW HAD RESET DFG SW-B CKT BRKR SYSTEM HAD RETURNED TO NORMAL.

Part: WINDSHIELD — SHATTERED (CENTER)

CENTER WINDSHIELD SHATTERED INFLT, DIVERTED TO ATL. REPLACED WINDSHIELD, OPERATION NORMAL.