N959DL

Part: RELEASE CABLE — FRAYED (TAILCONE) · airframe 72,149 hrs · 54,153 cycles

AFT TAILCONE RELEASE SYSTEM, UPPER LEFT CABLE IS FRAYED. REPLACED CABLE AND ADJUSTED PER AMM 53-53-00.

Part: ANGLE — CORRODED · corrosion level 2 · airframe 72,149 hrs · 54,153 cycles

CORROSION FOUND ON THE FLOOR ZEE ANGLE AT THE L1 DOOR FRAME, WHERE THE THRESHOLD ATTACHES. REMOVED AND REPLACED THE ZEE ANGLE IAW DWG 9936534.

Part: BATTERY PACK — INOPERATIVE (EMERGENCY LIGHTS) · airframe 72,066 hrs · 54,084 cycles

EMERGENCY LIGHTS INOPERATIVE, ROWS 31-38. REPLACED THE BATTERY PACK AT B5-212 IAW AMM 33-53-00.

Part: CABLE — TIGHT (PEDAL) · airframe 72,028 hrs · 54,057 cycles

APPROACHING GATE, HAD NO BRAKES ON CAPTAIN`S SIDE. NORMAL HYDRAULIC QUANTITY AND PRESSURE. LEFT ENGINE ONLY TAXI WITH AUXILIARY AND TRANSFER PUMPS ON. PERFORMED A BRAKE HYDRAULIC CONTROL SYSTEM TEST IAW AMM WITH NO TROUBLE FOUND. TAXIED AIRCRAFT AND APPLIED FULL BRAKES THREE TIMES WITH NO ISSUES. MCC LOG ISSUED TO INSPECTED CAPTAIN'S RUDDER PEDAL ADJUSTMENT MECHANISM. FOUND CABLE TENSION TOO TIGHT AND DETENT LUG NOT FULLY ENGAGING DETENT SLOTS. SUSPECT PEDALS COULD HAVE MOVED AWAY FORWARD DURING BRAKING. ADJUSTED THE CABLE TENSION IAW AMM. DETENT LUG NOW FULLY ENGAGES DETENT SLOTS IN ALL POSITIONS.

Part: SKIN — CRACKED (LAV SERVICE PNL) · corrosion level 2 · airframe 71,794 hrs · 53,872 cycles

AFT LAV SERVICE PANEL HAS CRACK SKIN AND CORROSION ON AFT LOWER CORNER. REPAIRED PER PRI 565769-14 REV 0 THRU REV 8. RECEIVED FINAL ERA 565769-14 REV ORIG. FINAL ERA 565769-14 AND PRI 565769-14 REV 0 THRU REV 8 MATCH. REF LOG 0431540 FOR TRACKING.

Part: LIGHT — INOPERATIVE (SEAT 12D) · airframe 71,133 hrs · 53,351 cycles

SEAT MOUNTED EMERGENCY LIGHT 12D INOPERATIVE. INSTALLED A NEW LENS AT SEAT 12D EMERGENCY LIGHT. LIGHT OPS NORMAL IAW AMM 33-50.

Part: DOOR — MISSING (APU BAY) · airframe 70,565 hrs · 52,877 cycles

ON WALAROUND FOUND LEFT APU ACCESS DOOR MISSING. NO DAMAGE NOTED ON ACFT INST LEFT APU ACCESS DOOR.

Part: FUSE — FAILED (EMERGENCY LIGHTS) · airframe 70,396 hrs · 52,744 cycles

EMERGENCY FLOOR LIGHTS IN FWD CABIN WILL NOT TURN ON. REPLACED FUSES ON THE BATTERY PACK. EMERGENCY FLOOR LIGHTS IN FWD CABIN WORK GOOD. OK FOR SERVICE.

Part: OXYGEN MASK — UNWANTED DEPLOY (CABIN) · airframe 70,326 hrs · 52,690 cycles

ON NORMAL LANDING ALL OXYGEN MASK DOORS OPENED. INSPECTED AND REPACKED THE OXYGEN MASKS, NO PINS FIRED, SECURED ALL OXYGEN MASK DOORS CLOSED IAW AMM 35-02. VERIFIED SWITCH GUARDED AND SAFETIED. PERFORMED ADJUSTMENT TEST ON ANAROID SWITCH IAW AMM 35-21-02-201. CHECKED RELAYS R2-314 AND R2-315. REMOVED AND REPLACED R2-315 RELAY IAW WDM 35-24-01. OPS CHECKED GOOD. OK FOR SERVICE.

Part: BATTERY — DISCHARGED (CABIN) · airframe 70,177 hrs · 52,573 cycles

CABIN ROWS 11-15 CEILING EMER LIGHTS INOP. REMOVED & REPLACED BALLAST BATTERIES. OPS CHECK GOOD.

Part: LAMP — INOPERATIVE (EMERGENCY LIGHT) · airframe 70,034 hrs · 52,459 cycles

EMERGENCY LIGHT AT SEAT 11 DEF INOPERATIVE. REPLACED THE LAMPS. OPS CHECKED GOOD.

Part: CONNECTOR — DISCONNECTED (EMERGENCY LIGHTS) · airframe 69,961 hrs · 52,401 cycles

PAX SEAT 2CD EMERGENCY LIGHT INOPERATIVE. FOUND THE WIRE HARNESS DISCONNECTED UNDER THE SEAT. SECURED THE CONNECTOR. OPS CHECKED GOOD IAW MM 33-50.

Part: ANNUNCIATOR — FAILED (COCKPIT) · airframe 69,606 hrs · 52,147 cycles

AFTER ARRIVAL AND BLOCK IN AT GATE, CREW REPORTED SMOKE FROM THE EOAP, MULTIPLE CIRCUIT BREAKERS TRIPPED, AND APU FIRE WARNING. APU WAS SHUTDOWN AND FIRE BOTTLES DISCHARGED. APU FIRE WARNING WAS FALSE INDICATION, SUSPECTED TO BE RELATED TO EOAP ISSUE. THE EOAP WAS REPLACED. REPLACED CARGO SMOKE DETECTOR CONTROL PANEL. REPLACED CARGO FIRE CONTROL MODULE. REPLACED BOTH FIRE EXTINGUISHER BOTTLES AND APU FIRE BOTTLE FLEX LINES DUE TO LEAKAGE.

Part: LAMP — INOPERATIVE (EMERGENCY LIGHT) · airframe 69,299 hrs · 51,926 cycles

SEAT ROW 1CD EMERGENCY LIGHTS INOPERATIVE. REPLACED THE LAMPS. OP'S CHECKED GOOD.

Part: VALVE — FAULTY (RUDDER) · airframe 68,954 hrs · 51,685 cycles

DURING FLIGHT, CONTROL CHECK ON TAXI OUT, THE RIGHT RUDDER PEDAL WAS COMPLETELY JAMMED WITH NO MOVEMENT FROM EITHER SIDE. THE STEERING BYPASS & RELIEF VALVE WAS FOUND TO BE FAULTY AND WAS REPLACED. OPERATIONAL CHECKS WERE GOOD. (LP# 8829848)

Part: SWITCH — BURNED (LANDING LIGHT) · airframe 67,713 hrs · 50,725 cycles

ACFT PERFORMED AN AIR TURN BACK TO DEPARTURE AFTER DETECTING AN ACRID, BURNING ELECTRICAL ODOR IN THE COCKPIT. NO VISIBLE SMOKE IN COCKPIT, BUT ODOR WAS STILL PRESENT AFTER RETURNING TO THE GATE. MAINTENANCE FOUND THE LEFT WING LANDING LIGHT SWITCH S1-5 BURNED TO BE THE SOURCE OF THE ODOR. THE SWITCH WAS R & R IAW AMM. NO OTHER DISCREPANCIES NOTED, AND THE ACFT WAS RETURNED TO SERVICE.

Part: SKIN — DAMAGED (BS 229) · airframe 67,608 hrs · 50,645 cycles

DUE PRI 546901-14: FOUND 2 PULLED FASTENERS AT BS 229 BETWEEN 29RT AND 30RT. C/W PRI 546901-14, REV 0,1, 2, 3. C/W PRI 546901-14, REV 4, 8 MAY 16 AT 2230E. VERIFIED ERA 546901-14, REV ORIGINAL MATCHES PRI 546901-14, REV 0,1,2,3,4 8TH MAY 16 AT 2230E.

Part: SPLICE STRAP — CORRODED (FUSELAGE) · corrosion level 2 · airframe 68,905 hrs · 51,648 cycles

ER/A 546901-14 WAS ISSUED TO ADDRESS CORROSION TO THE SPLICE STRAP COMMON TO THE FUSELAGE BUTT SPLICE AT STA 229.

Part: WIRE — DAMAGED (EMERGENCY LIGHTS) · airframe 67,601 hrs · 50,640 cycles

MAINTENANCE FOUND THE EMERGENCY ESCAPE PATH LIGHTS INOPERATIVE FROM SEAT ROWS 31 TO 36. MAINTENANCE FOUND A WIRE DAMAGED AND SHORTING TO GROUND UNDER SEAT ROW 36 AND REPAIRED SAME. THE EMERGENCY LIGHTS CHECKED OK.

Part: CABLE — FRAYED (ESCAPE SLIDE) · airframe 67,389 hrs · 50,484 cycles

MSP MAINTENANCE FOUND THE KEVLAR CABLE FOR THE TAILCONE EMERGENCY ESCAPE SLIDE FRAYED. THE CABLE WAS REPLACED.

Part: WIRE — BROKEN (EMERGENCY LIGHTS) · airframe 67,389 hrs · 50,484 cycles

EXIT PATH EMERGENCY LIGHTS ROW 24-30 AND OVER WING EXIT LIGHTS INOPERATIVE. WIRE BROKEN AT SIDEWALL VENT ROW 28R. REPAIRED IAW WDM 33-51-14.

Part: WIRE HARNESS — FAILED (EMERGENCY LIGHTS) · airframe 66,900 hrs · 50,141 cycles

MAINTENANCE FOUND SEAT 10D EMERGENCY LIGHTING INOPERATIVE 30DEC. REPLACED THE HARNESS. CHECKED OK.

Part: POWER SUPPLY — INOPERATIVE (EMERGENCY LIGHTS) · airframe 66,195 hrs · 49,625 cycles

MAINTENANCE FOUND OVERWING EMERGENCY LIGHTS INOPERATIVE. MAINTENACE R & R OVERWING EMERGENCY LIGHT POWER SUPPLY. CHECKED OK.

Part: BATTERY PACK — INOPERATIVE (EMERGENCY LIGHTS) · airframe 65,782 hrs · 49,330 cycles

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

Part: SKIN — DENTED (BS 229) · airframe 65,575 hrs · 49,182 cycles

TWO DENTS BETWEEN STRINGERS 17 & 18L BS 229. CUT OUT THE DAMAGE IAW SRM 53-04-3, FIG 2, SHT 5. DRILLED A REPAIR DOUBLER IAW SRM 53-04-3, FIG 2, SHT 5. INSTALLED REPAIR DOUBLER IAW SRM 53-04-3, FIG 2

Part: WIRE — BROKEN (EMERGENCY LIGHTS) · airframe 65,049 hrs · 48,804 cycles

DURING LINE CHECK, MAINTENANCE FOUND THAT THE EMERGENCY PATHWAY LIGHTING AT SEAT 22E IN THE CABIN WAS INOPERATIVE. MAINTENANCE FOUND A WIRE BROKEN IN THE HARNESS. THE WIRE WAS REPAIRED AND THE SYSTEM RETURNED TO NORMAL OPERATION. LP 6998358.

Part: LIGHT — DAMAGED (CATWALK) · airframe 64,533 hrs · 48,462 cycles

MAINTENANCE FOUND TWO EMERGENCY LIGHT ASSEMBLIES ON CAT WALK DAMAGED. MAINTENANCE REPLACED BOTH EMERGENCY LIGHT ASSEMBLIES ON CAT WALK.

Part: CHARGER — INOPERATIVE (EMERGENCY LIGHTS) · airframe 63,765 hrs · 47,884 cycles

THE CREW FOUND THAT THE FLIGHT DECK EMERGENCY LIGHTS WERE INOPERATIVE. MAINTENANCE REPLACE THE BATTERY ON THE BATTERY PACK CHARGER AND OPS CHECKED GOOD.

Part: BATTERY PACK — INOPERATIVE (EMERGENCY LIGHTS) · airframe 63,650 hrs · 47,797 cycles

DURING LINE CHECK, MAINTENANCE FOUND THAT THE OVERHEAD EMERGENCY LIGHT IN THE FIRST CLASS SECTION WAS INOPERATIVE. MAINTENANCE REPLACED THE BATTERY PACKS FOR THE NOTED LIGHTED AREAS AND OPS CHECKED GOOD.

Part: LONGERON — DAMAGED (BS 1348) · airframe 62,318 hrs · 46,825 cycles

DURING NON ROUTINE CHECK, WEAR AND ELONGATED HOLE ON LONGERON 19R, BS 1348 AT AFT ACCESSORY COMPARTMENT. SECTION OF LONGERON REMOVED IAW SRM 53-02, FIG 18. NEW SECTION OF LONGERON AND SPLICE DRILLED IAW SRM 53-02, FIG 18. NEW SECTION WERE TREATED AND PAINTED IAW SRM 51-10-3, PAR 21 AND 14. NEW SECTION INSTALLED IAW SRM 51-10-3, PAR 21 AND 14.

Part: SKIN — CRACKED (BS 373-374) · airframe 62,318 hrs · 46,825 cycles

NON ROUTINE CHECK, FUSELAGE SKIN WAS FOUND CRACKED BETWEEN BS 373 AND 374 LONGERONS 20 - 21R AT UPPER FWD DOOR FRAME. REPAIRED IAW ETI-88-14-003, REV 3 AND ER/A 521180-14 AD REV "A".

Part: NOT REPORTED — CRACKED (RT WING) · airframe 67,440 hrs · 50,526 cycles

AT HMV4 A RT RS CRACK AT XRS 164 WAS REPAIRED AND THE SPLICE AT XRS 111.5. REQUIRED A FASTENER DEVIATION AS AMOC TO AD 2011-17-11.

Part: FRAME — CRACKED (LT WING) · airframe 62,316 hrs · 46,824 cycles

CRACK ON LT WING MAIN FRAME AT LOWER STRINGER 11 XRS 168. DAMAGE REMOVED, REPAIR WAS ACCOMPLISHED IAW CARD 5712-01030-03.

Part: ANGLE — CORRODED (FUSELAGE) · airframe 68,898 hrs · 51,642 cycles

CORROSION ON RT CUSP ANGLE STW STA Y=190-206 AT PAX CABIN FLOOR STRUCTURE. CUSP ANGLE WAS REPAIRED IAW SRM 53-05, FIG 55 AND ER/A 521188-14MA.

Part: SPAR CAP — CRACKED (RT WING) · airframe 62,316 hrs · 46,824 cycles

CRACK WAS FOUND ON RT WING REAR LOWER SPAR CAP. REPAIRED IAW SR J060165, REV AD AND CARD 5710-01110-12.

Part: CUSP WEB — CORRODED (FUSELAGE) · airframe 68,898 hrs · 51,642 cycles

CORROSION ON RT FLOOR CUSP WEB BTW STA Y=218-220 X=44 TO X=-60 AT PAX CABIN. CUSP WEB BTW STA Y=218-220 X=-44 TO X=-60 WAS REPLACED FOR EXCESSIVE CORROSION.

Part: LONGERON — CORRODED (FUSELAGE) · corrosion level 2 · airframe 68,898 hrs · 51,642 cycles

CORROSION ON LONG 29L STA Y=1287 BELOW FRAME CLIP AT AFT CARGO COMPARTMENT. DAMAGED LONGERON WAS REMOVED, NEW LONGERON SECTION AND SPLICES WERE DRILLED, TREATED, PAINTED AND INSTALLED IAW ER/A 521207-14 REV A.

Part: ACCESS PANEL — CORRODED (RT WING) · airframe 68,898 hrs · 51,642 cycles

CORROSION ON RT MAIN FUEL TANK PLATE NR 1460C COUNTERSINK HOLES AND SETTLEMENT AREA. CORROSION WAS REMOVED, COUNTERSINK HOLES WERE MEASURED, MAX DIAMETER ALLOWABLE IS 0.532" AND MAX DIAMETER MEASURED IS 0.579 ON C3 ADJACENT HOLES THEREFORE OUT OF LIMITS IAW SRM 51-22-2A, FUEL ACCESS PLATE NBR 1460C WAS REPLACED.

Part: STRUCTURE — CORRODED (SERVICE ACCESS) · airframe 68,898 hrs · 51,642 cycles

CORROSION ON CUT OUT OF FWD LAVATORY SERVICE ACCESS. DAMAGE AREA WAS REPAIRED IAW ER/A 521182-14.

Part: HINGE FITTING — CORRODED (TE FLAP) · airframe 68,898 hrs · 51,642 cycles

CORROSION ON FLAP HINGE FITTING UPPER OUTBD STUD STA XRS=111. HINGE FITTING WAS REMOVED AND REPLACED.

Part: CARGO TRACK — CORRODED (BS 1155-1322) · corrosion level 2 · airframe 62,316 hrs · 46,824 cycles

CORROSION ON LT CARGO TRACK FROM BS 1155 - 1322. CORROSION REMOVED AND FOUND OUT LIMITS IAW SRM 53-05, FIG 4C AND 51-10-3 PARR 26. CARGO TRACK REPLACED IAW SRM 51-30-1.

Part: LONGERON — CRACKED (BS 1418) · airframe 62,316 hrs · 46,824 cycles

CRACKED LONGERON 2L BS 1418. LONGERON REMOVED IAW SRM 5130-2. NEW SECTION OF LONGERON AND SPLICE DRILLED AND TRIMMED SRM 53-02, FIG 18. NEW LONGERON AND SPLICE WERE INSTALED IAW SRM 53-07, FIG 18 AND 51-30-2 , 51-30-5.

Part: LONGERON — DAMAGED (BS 1418) · airframe 62,316 hrs · 46,824 cycles

ELONGATED HOLES ON LONGERON 1, BS 1418. LONGERON REMOVED IAW SRM 51-30-2, 51-305. NEW LONGERON SECTION DRILLED AND TRIMMED IAW SRM 51-10-4 0150. NEW LONGERON AND SPLICE INSTALLED IAW SRM 51-30-2 , 51-30-5.

Part: SKIN — DAMAGED (RUDDER) · airframe 62,316 hrs · 46,824 cycles

DAMAGE METALLIZED COATING ON RT/ LT SURFACE OF RUDDER. REPAIRED IAW SRM 51-70-1AD, PAR 23 AND OPN 1031, JIV 2000-8149-08 A/C 0959 CRWE 02 STEPS 1 TO 14.

Part: ACCESS PANEL — CORRODED (LT WING) · corrosion level 2 · airframe 62,316 hrs · 46,824 cycles

CORROSION OUT OF LIMITS ON COUNTERSINK AT LT MAIN FUEL TANK PLATE NR 1361C. REPAIRED SRM 51-22-2A, PAR 6 COND II.

Part: ACCESS PANEL — CORRODED (RT WING) · airframe 68,898 hrs · 51,642 cycles

RT MAIN FUEL TANK ACCESS PANEL 1466C, COUNTERSINK CORRODED, REPAIRED.

Part: ACCESS PANEL — CORRODED (LT WING) · airframe 68,898 hrs · 51,642 cycles

LT WING MAIN FUEL TANK ACCESS COVER 1365C COUNTERSINK CORRODED, REPAIRED.

Part: ACCESS PANEL — CORRODED (LT WING) · airframe 68,898 hrs · 51,642 cycles

LT WING MAIN FUEL TANK ACCESS COVER 1355C COUNTERSINKS CORRODED, REPAIRED.

Part: SKIN — CORRODED (FUSELAGE) · airframe 68,898 hrs · 51,642 cycles

FWD LAV SERVICE DOOR FUSELAGE CUTOUT, LATCH POINT CORRODED. CUTOUT, REPLACED.

Part: ACCESS PANEL — CORRODED (LT WING) · airframe 68,898 hrs · 51,642 cycles

LT MAIN FUEL TANK ACCESS COVER 1367C COUNTERSINKS CORRODED, REPAIRED.

Part: ACCESS PANEL — CORRODED (RT WING) · airframe 68,898 hrs · 51,642 cycles

RT MAIN FUEL TANK ACCESS COVER 1464C COUNTERSINKS CORRODED, REPAIRED.

Part: ACCESS PANEL — CORRODED (LT WING) · airframe 68,898 hrs · 51,642 cycles

LT MAIN FUEL TANK ACCESS COVER 1363C COUNTERSINKS CORRODED, REPAIRED.

Part: ACCESS PANEL — CORRODED (LT WING) · airframe 68,898 hrs · 51,642 cycles

LT WING MAIN FUEL TANK ACCESS PANEL 1307C COUNTERSINKS CORRODED, REPAIRED.

Part: ACCESS PANEL — CORRODED (WING) · airframe 68,898 hrs · 51,642 cycles

MAIN FUEL TANK PLATE NR 1357C COUNTERSINK CORROSION, OUT OF DIMENSION AFTER CLEANUP, TANK PLATE REPLACED.

Part: ACCESS PANEL — CORRODED (WING) · airframe 68,898 hrs · 51,642 cycles

MAIN FUEL TANK PLATE NR 1371C, CORROSION IN COUNTERSINKS, OUT OF DIMENSION AFTER CLEAN UP. TANK PLATE REPLACED.

Part: CUSP WEB — CORRODED (FUSELAGE) · airframe 68,898 hrs · 51,642 cycles

LT CUSP WEB CORRODED FROM X54-X60, BETWEEN STA 930-943, AT FLOOR STRUCTURE CABIN.

Part: ACCESS PANEL — CORRODED (WING) · airframe 68,898 hrs · 51,642 cycles

MAIN FUEL TANK ACCESS PLATE 1454C COUNTERSUNKS CORRODED, HOLE DIAMETER OUT OF LIMITS AFTER CLEANUP. REPLACED TANK PANEL.

Part: CUSP WEB — CORRODED (FUSELAGE) · airframe 68,898 hrs · 51,642 cycles

CORROSION RT CUSP WEB, BETWEEN X=-54 TO X=-60, Y= 1098 TO 1155 AT FLOOR CABIN STRUCTURE. WEB REPLACED.

Part: CUSP WEB — CORRODED (FUSELAGE) · airframe 68,898 hrs · 51,642 cycles

CORROSION ON RT CUSP WEB, BETWEEN X-54 TO X=-60, STA 1165-1169, 1174-1187, 1204-1212, 1217-1220, 1234-1244, AT FLOOR CABIN STRUCTURE. WEB REPLACED.

Part: SEAT TRACK — CORRODED (FUSELAGE) · airframe 68,898 hrs · 51,642 cycles

CORROSION ON RT SEAT TRACK, X=-22, STA 1034-1035, AREA REMOVED AND REPLACED.

Part: CUSP WEB — CRACKED (FUSELAGE) · airframe 68,898 hrs · 51,642 cycles

CORROSION LVL 2, CRACKED RT CUSP WEB, BETWEEN X=-54 TO X=-60, STA Y=1287-1309. CUSP WEB REPAIRED.

Part: ACCESS PANEL — CORRODED (WING) · corrosion level 2 · airframe 68,869 hrs · 51,617 cycles

MAIN FUEL TANK ACCESS PANEL 1311C CORRODED IN COUNTERSINK HOLES AND SETTLEMENT AREA. REPLACED THE ACCESS PANEL IAW 52-22-2A.

Part: LONGERON — CORRODED (BS 1418) · corrosion level 2 · airframe 68,869 hrs · 51,617 cycles

CORROSION ON LONGERON 24L, BS 1418 AT AFT ACCESSORY COMPARTMENT. THE LONGERON WAS REMOVED AND REPLACED IAW 51-30-5, 51-30-2, 51-10-4, 51-10-3. AND 53-02 FIG 18.

Part: ACCESS PANEL — CORRODED (RT WING) · corrosion level 2 · airframe 68,869 hrs · 51,617 cycles

CORROSION ON RIGHT WING FUEL TANK ACCESS PANEL NR 1456C ON COUNTERSINK HOLES AND SETTLEMENT AREA. THE ACCESS PANEL WAS REPLACED.

Part: SPLICE — CORRODED (BS 1338) · corrosion level 2 · airframe 68,869 hrs · 51,617 cycles

CORROSION ON LEFT FWD SPLICE OF AFT PRESSURE BULKHEAD LOWER TEE BS 1338 BETWEEN LONGERONS 26-27L. SPLICE WAS REMOVED IAW SRM 51-30-5 SPLICE WAS FABRICATED, IAW SRM 53-03 D FIG 37, NEW SPLICE WAS TREATED AND PAINTED IAW SRM 51-10-3 PAR 14,21 NEW SPLICE WAS INSTALLED IAW SRM 51-30-5 CIC WAS APPLIED IAW SRM 51-10-3 PAR 38.

Part: CUSP WEB — CORRODED (BS 612) · corrosion level 2 · airframe 68,830 hrs · 51,579 cycles

CORROSION ON LT CUSP WEB FROM X 54 TO X 60 BS 612. REPAIRED IAW SRM 53-05 FIG 131A-13 AND 51-20-2 AND 51-10-3 PAR 14-21 P.S. 900-5-1 NO0 04.

Part: CUSP WEB — CORRODED (CABIN) · corrosion level 2 · airframe 62,316 hrs · 46,824 cycles

CORROSION ON LEFT CUSP WEB. FABRICATED DOUBLER AND INSTALLED IAW SRM 51-10-3, PAR 14, 21, 26, 38.

Part: SKIN — CORRODED (BS 1282) · corrosion level 2 · airframe 68,830 hrs · 51,579 cycles

CORROSION ON OVERLAP SKIN BS 1282 AND LONGERON 26L. FINGER DOUBLER WAS FABRICATED, TREATED AND PAINTED IAW SRM 51-10-1 FIG 36 AND 51-10-3 PAR 14 AND 21. FINGER DOUBLER WAS INSTALLED IAW SRM 51-30-2.

Part: CUSP WEB — CORRODED (BS 1063-1095) · corrosion level 2 · airframe 68,830 hrs · 51,579 cycles

CORROSION ON RT CUSP WEB X -54 TO X -60, BS 1063 - 1064, 1092 - 1095, 1072 - 1075. REPAIRED IAW SRM 53-05 FIG. 131A-13.

Part: CUSP WEB — CORRODED (BS 826-842) · corrosion level 2 · airframe 62,316 hrs · 46,824 cycles

CORROSION ON LT CUSP WEB REPAIR DOUBLER, X=54-X=60 BETWEEN BS 826-842. DOUBLER REMOVED IAW SRM 51-30-5. DOUBLER FABRICATED IAW SRM 53-05, FIG 131A-6, AND INSTALLED IAW SRM 53-05, FIG 131A-6.

Part: CUSP WEB — CORRODED (BS 716) · corrosion level 2 · airframe 68,830 hrs · 51,579 cycles

CORROSION ON RT CUSP WEB BS 716 BTW X -54 TO X -60. REPAIR FABRICATED, TREATED, PAINTED, AND INSTALLED IAW SRM 51-10-3, PAR. 21 AND 14, 53-05 FIG. 131A-14 AND 51-30-5.

Part: CUSP WEB — CORRODED (BS 465-484) · corrosion level 2 · airframe 62,316 hrs · 46,824 cycles

CORROSION ON REPAIR DOUBLER OF CUSP WEB BETWEEN X=-54-X=-60, BS 465-484. REPAIR DOUBLER WAS REMOVED IAW SRM 51-30-2. DOUBLER AND TRIPLER FABRICATED IAW SRM 53-05, FIG 131A-6. INSTALLED IAW SRM 51-30-2.

Part: WIRE — BROKEN (EMERGENCY LIGHTS) · airframe 60,999 hrs · 45,863 cycles

THE PILOT DISCOVERED THAT THE EMERGENCY PATHWAY LIGHTING AT ROW 24DE IN THE CABIN WAS INOPERATIVE. MX FOUND A BROKEN WIRE UNDER THE SEAT, REPAIRED THE WIRE, AND THE SYS RETURNED TO NORMAL OPERATION.

Part: SKIN — CRACKED (BS 1418) · airframe 60,950 hrs · 45,829 cycles

CRACKED SKIN AT BS 1418 TOP CENTER BELOW RAM AIR INLET. VIEWED FROM INSIDE LWR REMOVABLE PANEL. REPAIRED IAW ER/A 516329-14AD, REV ORIG.

Part: SKIN — CRACKED (BS 1410) · airframe 60,950 hrs · 45,829 cycles

INTERNAL SKIN DOUBLER CRACKED AT BS 1410 LONGERON 2L. TAIL INTERIOR. REMOVED OLD INTERNAL SKIN DOUBLER AND BACK DRILLED NEW DOUBLER. INSTALLATION OF DOUBLER WAS ACCOMPLISHED ON ER/A 516331-14AD, REV O.

Part: SKIN — CRACKED (BS 1410) · airframe 60,950 hrs · 45,829 cycles

SKIN CRACKED AT BS 1410 TWO INCHES INBD OF LONGERON 2L AT TAIL INTERIOR. HFEC NDT SPM 06-10-01.001 MARKED ENDS OF CRACKS. REPAIR INSTALLED IAW ER/A 516331-14AD.

Part: LONGERON SPLICE — CRACKED (BS 1418) · airframe 60,950 hrs · 45,829 cycles

AFT SECTION OF LONGERON CRACKED AT SPLICE AT LONERON 2R BS 1418, REMOVED DAMAGED LONGERON, INSTALLED NEW SECTION OF LONGERON REF SRM 53-10-00.

Part: TEAR STRAP — CRACKED (FUSELAGE) · airframe 60,950 hrs · 45,829 cycles

CRACKED TEAR STRAP RT AFT SIDE OF REMOVABLE PANEL. JUST FWD OF RAM AIR INLET. REMOVED TEAR STRAP AFT RT SIDE. INSTALLED TEAR STRAP (GUSSET) IAW SRO 9530162.

Part: LATCH — WORN (TAILCONE RELEASE) · airframe 60,999 hrs · 45,863 cycles

DURING A CHECK OF TAILCONE RELEASE SYS, MX FOUND THE RT SIDE SLIDING BLOCK FOR THE TAILCONE LATCH WAS WORN BEYOND ALLOWABLE LIMITS. MX REPLACED THE SLIDING BLOCK, RERIGGED THE TAILCONE, AND FOUND OPERATIONAL. THE RII COMPLETED FOLLOWING MX.

Part: STIFFENER — CRACKED (BS 1418) · airframe 60,950 hrs · 45,829 cycles

STIFFENER CRACKED AFT OF FRAME 1418 AT L2. HFEC CONTINUED CRACK IAW NDT MANUAL 06-10-01. INSTALLED STIFFNER IAW PRI 516400-14. INSPECTED REPAIR INSTALLATION IAW PRI. WORK ACCOMPLISHED IAW ER/A 516400-14, REV ORIGINAL.

Part: FRAME — CRACKED (BS 905) · airframe 60,950 hrs · 45,829 cycles

OVERWING FRAME CRACKED RT SIDE AT BS 905, OTBD OF FLOOR. REMOVED CRACKED FRAME BS 905, RT SIDE FROM JUST BELOW L18R TO ABOUT 7 INCHES ABOVE L10R. LOCATED NEW FRAME AND INSTALLED.

Part: SKIN — CRACKED (BS 1361 L14R) · airframe 620,951 hrs · 46,678 cycles

MAINTENANCE NOTED A FUSELAGE SKIN CRACK AT BS 1361 AND L14R. REPAIR IAW 516213-14.

Part: SLIDE — MISINSTALLED (TAILCONE) · airframe 60,950 hrs · 45,829 cycles

INSPECTION DISCOVERED THAT THE EMERGENCY ESCAPE SLIDE IN THE TAILCONE HAD AN IMPROPERLY INSTALLED COVER. THIS WOULD PREVENT PROPER DEPLOYMENT OF THE ESCAPE SLIDE AND IS NOT IN COMPLIANCE WITH 14 CFR PART 121.703. THE TAILCONE SLIDE, COVER, AND LANYARDS WERE RE-INSTALLED CORRECTLY.

Part: SIGN — BROKEN (EMERGENCY LIGHTS) · airframe 60,872 hrs · 45,772 cycles

DURING LINE CHECK, MX FOUND THAT THE EMERGENCY PATHWAY LIGHTING EXIT IDENTIFIER AT THE OVERWING EXIT ROW 24 WAS BROKEN. MX REPLACED THE EXIT IDENTIFIER AND PERFORMED A SATISFACTORY FUNCTIONAL CHECK OF IT.

Part: CONNECTOR — LOOSE (EMERGENCY LIGHTS) · airframe 59,246 hrs · 44,619 cycles

DURING LINE CHECK, MX FOUND THAT THE EXTERIOR EMERGENCY LIGHT WAS INOPERATIVE SUCH THAT IT WAS ON IN THE ARM SWITCH POSITION. MX FOUND A LOOSE CONNECTOR ON THE BATTERY PACK, RE-SEATED THE CONNECTOR, AND THE SYSTEM RETURNED TO NORMAL OPERATION. (LP 9088466)

Part: BATTERY PACK — INOPERATIVE (EMERGENCY LIGHTS) · airframe 58,118 hrs · 43,879 cycles

DURING LINE CHECK, MAINTENANCE FOUND THAT THE EMERGENCY EXIT SIGNS ABOVE BOTH OF THE FWD OVERWING HATCHES WERE INOPERATIVE. MAINTENANCE REPLACED THE BATTERY PACK AND THE LIGHTS RETURNED TO AN OPERATIONAL CONDITION.

Part: BEAM — CORRODED (FUSELAGE) · airframe 57,695 hrs · 43,566 cycles

AFT CARGO DOOR SILL LONGERON 28R LOWER FLANGE CORROSION AT STA 1231 AND 1250. REPAIRED PER ERA500867-14 REV ORIGINAL. (NRC 89)

Part: TAIL CONE — FAILED (FUSELAGE) · airframe 57,695 hrs · 43,566 cycles

THE TAIL CONE RELEASE FUNCTIONAL CHECK FAILED THE PULL TEST. AMOUNT THAT SCALE EXCEEDED ALLOWABLE LIMITS WAS NOT SPECIFIED. NO CORRECTIVE ACTION IDENTIFIED PER TO NEC 139. MRR 121257. (2012-D0233) LP #DL0004253.

Part: FAN — SEIZED (RECIRCULATION) · airframe 57,637 hrs · 43,519 cycles

DURING CLIMB GOT ELECTRICAL ODOR THROUGHOUT CABIN AND COCKPIT NO EVIDENCE OF SMOKE IN AIRCRAFT AND ODOR EVENTUALLY DECREASED. PERFORMED. FOUND RECIRC FAN MOTOR SEIZING ON CABIN RECIRCULATION FAN. REMOVED AND REPLACED SAME PER AMM. ADJUSTED AND TEST CHECKED GOOD. AIRCRAFT IS OKAY FOR SERVICE.

Part: SKIN — CRACKED (FUSELAGE) · airframe 55,977 hrs · 42,354 cycles

DURING PSV VISIT IN MSP 11JUN11, A CRACK WAS FOUND ON THE FUSELAGE SKIN AT APPROXIMATELY STA 1437 JUST ABOVE L3R. THE CRACK EMANATES FROM AN EXISTING LOWER MOST FASTENER HOLE ALONG STA 1437 SHEAR TIE. REPAIRED PER ERA 493325-14. CUT OUT DAMAGE 1.0" DIA AND SKIN REPAIR PER MD80 SRM 53-01 FIG 4 SHT 4. REPAIRED ON N/R 16.

Part: ATTACH ANGLE — CRACKED (FUSELAGE) · airframe 55,977 hrs · 42,354 cycles

DURING PSV IN MSP CRACKS WERE FOUND ON THE 5912141-86 FUSELAGE TO VERTICAL STABILIZER ATTACH ANGLE NEAR STA 1465. DAMAGE REPAIRED PER ERA 493329-14 REV ORIG. THIS DATE 6-8-2011. THIS ITEM WORKED ON N/R 20.

Part: SOCKET — MELTED (CABIN) · airframe 55,936 hrs · 42,325 cycles

AFTER PASSENGERS DEPARTED ACFT SMOKE OBSERVED IN THE CABIN AT ROW 18A. CAPT TURNED OFF ALL ELECTRICAL POWER AND SMOKE DISSIPATED. CAPT CALLED FOR FIRE DEPT TO COME TO AIRCRAFT. MAINTENANCE FOUND THE LEFT SIDE OVERHEAD LIGHT BULB AND SOCKET MELTED AT ROW 18A. MAINTENANCE REPLACED THE LIGHT BULB, SOCKET, AND BALLAST FOR THE AFFECTED LIGHT.

Part: CONNECTOR — NOT SEATED (AC BAY) · airframe 55,768 hrs · 42,214 cycles

DURING LINE CHECK, MAINTENANCE FOUND CATWALK FORWARD SIDEWALL EMERGENCY LIGHTS INOPERATIVE. MAINTENANCE RESEATED CONNECTORS. OPERATION CHECKS GOOD.

Part: WIRE — BROKEN (AC BAY) · airframe 55,768 hrs · 42,214 cycles

DURING LINE CHECK, MAINTENANCE FOUND CATWALK, MIDDLE SIDEWALL EMERGENCY LIGHTS, INOPERATIVE. MAINTENANCE TROUBLESHOT AND FOUND BROKEN WIRES, REPAIRED SAME PER SWPM. OPERATION CHECKS GOOD.

Part: SKIN — CRACKED (FUSELAGE) · airframe 55,699 hrs · 42,167 cycles

ON WALK-AROUND FOUND CRACK IN BELLY SKIN BELOW C-2 CARGO DOOR. REPAIRED IAW ERA 491928-14 ON N/R/C 1.

Part: CONNECTOR — DIRTY (CABIN) · airframe 54,020 hrs · 41,018 cycles

MAINTENANCE FOUND THE EMERGENCY ESCAPE PATH LIGHTS AT SEAT ROWS 1-12 TO BE INOPERATIVE. MAINTENANCE FOUND THE INPUT POWER SOURCE CONNECTOR NEAR SEAT 3C TO BE DIRTY. MAINTENANCE REPLACED THE CONNECTOR. AN OPERATIONAL CHECK WAS PERFORMED AND THE AIRCRAFT WAS RETURNED TO SERVICE (ODI 2010-D0943)(DLM88102030).

Part: WIRE HARNESS — DAMAGED (EMERGENCY LIGHTS) · airframe 53,660 hrs · 40,764 cycles

THE EMERGENCY FLOOR LIGHTS AT SEAT 10D WERE FOUND TO BE INOPERATIVE/ DAMAGED. MX REPLACED THE HARNESS. AN OPS CHECK WAS PERFORMED AND THE ACFT WAS RETURNED TO SERVICE. (DLM88101519)

Part: APU — UNSERVICEABLE (APU BAY) · airframe 52,036 hrs · 39,796 cycles

FOUND INLET GUIDE VANES COKED WITH OIL. INSPECTED APU INLET NO OIL EVIDENCE FOUND R/R APU PER MM, ALL OPS NORMAL. C/W OPN 5089 DUCT BURNOUT, C/W OPN 7967 COALESCER BAG R/R OK FOR SERVICE.

Part: STARTER — DAMAGED (NR 2 ENGINE) · airframe 51,226 hrs · 39,241 cycles

NR 2 ENG STARTER HOUSING CAME APART AND DAMAGED LOWER FWD COWL. A PIECE OF GEAR HIT THE COWL CAUSING A DENT ON THE INSIDE AND SOME FIBERS ON THE OUTSIDE TO SPLINTER OUT. GEAR DID NOT PASS THRU COWL. REPLACED NR 2 ENGINE STARTER, OPS CHECKS OK. REPLACED NR 2 ENGINE LWR FWD COWL.

Part: SKIN — DAMAGED (LT WING TE FLAP) · airframe 47,734 hrs · 36,847 cycles

DURING HMV ELONGATED HOLES WERE REPORTED ON UPPER SKIN OF LT OUTBOARD FLAP INBOARD SECTION. A NEW SKIN AND FINGER DOUBLER WERE FABRICATED AND INSTALLED IAW BOEING PRODUCTION DWG 9935954-15.

Part: VANE — WORN (LT WING) · airframe 47,734 hrs · 36,847 cycles

DURING HMV, FOUND WEAR ON THE SURFACE OF THE LT INBOARD FLAP INBOARD GUIDE VANE. A PERMANENT REPAIR WAS PERFORMED IAW MD-80 SRM 57-03D FIG 9A PARAGRAPH 8A.

Part: SKIN — CORRODED (BS 628 S29-30R) · airframe 47,734 hrs · 36,847 cycles

FUSELAGE SKIN REPAIR AT STA=628 BETWEEN LONGERONS 30 AND 29 RT. A REPAIR WAS PERFORMED IAW ER/A 457183-14 REV D.

Part: SKIN — DAMAGED (FUSELAGE) · airframe 47,734 hrs · 36,847 cycles

DURING HMV AN INADEQUATE REPAIR WAS FOUND ON UPPER FUSELAGE SKIN BETWEEN STA Y=461 AND Y=469 LONGERONS 6 AND 7 LT. A PERMANENT REPAIR WAS PERFORMED IAW MD-80 SRM 53-04 FIG 12B.

Part: CUSP WEB — CRACKED (FUSELAGE) · airframe 47,734 hrs · 36,847 cycles

CRACK ON RT CUSP WEB AT STA Y=222, NEW CUSP WEB WAS INSTALLED IAW DOUGLAS DWG 9930538.

Part: SKIN — CRACKED (FUSELAGE) · airframe 47,734 hrs · 36,847 cycles

DURING MC THREE CRACKS WITH .031", .031" AND .046" LENGTH WERE FOUND ON FUSELAGE SKIN AT STA Y=191 AND Y=197 NEXT TO LONGERON 22LH. A PERMANENT REPAIR WAS PERFORMED IAW EA 09-069085-12AD REV DME-02 IN COMPLIANCE WITH AD 98-17-06.

Part: DOUBLER — CRACKED (FUSELAGE) · airframe 47,734 hrs · 36,847 cycles

DURING HMV, A .45 INCH LONG CRACK WAS FOUND ON INTERNAL DOUBLER P/N 5936434-43 AT STA Y=579 BETWEEN LONGERONS 28 AND 29 LT A REPAIR WAS PERFORMED IAW ER/A 465656-14.

Part: SKIN — DENTED (FUSELAGE) · airframe 47,734 hrs · 36,847 cycles

DURING HMV, TWO DENTS WERE FOUND CLOSE TO AN EXISTING REPAIR AT STA Y=250 AND BETWEEN LONGERON 19 AND 20 LT. EXISTING REPAIR WAS REMOVED AND A PERMANENT REPAIR WAS PERFORMED IAW ER/A 095061-14 AND MD-80 SRM 53-04D FIG 12B VIEW AU.

Part: VANE — DELAMINATED (TE FLAP) · airframe 47,734 hrs · 36,847 cycles

DURING HMV, REPORTED A DELAMINATION ON UPPER SKIN OF INBOARD GUIDE VANE AT LEFT OUTBOARD FLAP. A PERMANENT REPAIR WAS PERFORMED IAW MD-80 SRM 57-03D PARAGRAPH 8A FIG 9A AND SRM 51-70-2D PARAGRAPH 6A, 6C, 10B, 10D AND 10E.

Part: SKIN — CORRODED (FUSELAGE) · airframe 47,734 hrs · 36,847 cycles

DURING HMV, CORROSION WAS FOUND AT STA Y=730 ON SKIN P/N 5936 066-5 BETWEEN LONGERON 30 AND 29 RT. A PERMANENT REPAIR WAS PERFORMED IAW ER/A 465648-14.

Part: SKIN — NICKED (RT TE FLAP) · airframe 47,734 hrs · 36,847 cycles

DURING HMV, SEVERAL NICKS WERE FOUND ON THE RT INBOARD FLAP LOWER SKIN P/N 9935942-6. A REPAIR WAS PERFORMED IAW ER/A 466344-14.

Part: SKIN — MISREPAIRED (FUSELAGE) · airframe 47,734 hrs · 36,847 cycles

DURING HMV AN INADEQUATE REPAIR WAS FOUND ON UPPER FUSELAGE SKIN BETWEEN STA Y=385 AND Y=393 LONGERON 8 AND 9 LT. A PERMANENT REPAIR WAS PERFORMED IAW SRM 53-04 FIG 12B.

Part: DOOR FRAME — CORRODED (CARGO BAY) · airframe 47,734 hrs · 36,847 cycles

DURING HMV, CORROSION WAS FOUND ON AFT CARGO COMPARTMENT DOOR JAMB DOUBLER AT STA Y=1154 P/N 5936433-5 BETWEEN LONGERONS 30 AND 29 RT. A REPAIR WAS PERFORMED IAW DWG AMR0953586 R2 DATED ON 15 JAN 08.

Part: SKIN — MISREPAIRED (FUSELAGE) · airframe 47,734 hrs · 36,847 cycles

DURING HMV, AN INADEQUATE REPAIR WAS FOUND ON UPPER FUSELAGE SKIN BETWEEN STA Y=499 AND Y=507 LONGERON 6 AND 7 LT. A PERMANENT REPAIR WAS PERFORMED IAW MD-80 SRM 53-04 FIG 12B.

Part: SKIN — ERODED (TE FLAPS) · airframe 47,734 hrs · 36,847 cycles

DURING HMV, EROSION WAS FOUND ON LOWER SKIN OF OUTBOARD GUIDE VANE OF RT INBOARD FLAP. A PERMANENT REPAIR WAS PERFORMED IAW MD-80 SRM 57-03D PARAGRAPH 8A FIG 9A.

Part: SKIN — DELAMINATED (TE FLAP) · airframe 47,734 hrs · 36,847 cycles

DURING HMV, IT WAS FOUND A DELAMINATION ON UPPER SKIN OF INBOARD GUIDE VANE AT RT OUTBOARD FLAP. A PERMANENT REPAIR WAS PERFORMED IAW MD-80 SRM 57-03D PARAGRAPH 8A FIGURE 9A AND SRM 51-70-2D PARAGRAPH 6A, 6C, 10B, 10D AND 10E

Part: LATCH — CORRODED (GIRT BAR) · airframe 47,734 hrs · 36,847 cycles

CORROSION ON GIRT BAR LATCH SUPPORT STA Y=1140 X=57 LT SIDE, NEW SUPPORT WAS INSTALLED IAW BOEING DWG 9930612.

Part: SKIN — DAMAGED (RUDDER) · airframe 47,734 hrs · 36,847 cycles

DURING HMV, TWO METALIZED DAMAGES WERE FOUND BOTH RUDDER SURFACES AT THE LT SIDE IT WAS 87 INCHES LONG BY 34 INCHES WIDTH AT THE RT SIDE IT WAS 71 INCHES LONG AND 30 INCHES WIDTH. A PERMANENT REPAIR WAS PERFORMED IAW MD-80 SRM 51-70-1A D PARAGRAPH 23A.

Part: SKIN — DAMAGED (TE FLAP) · airframe 47,729 hrs · 36,845 cycles

THE RT WING INBD MAIN FLAP LOWER REMOVEABLE TRAILING EDGE SKIN WAS SPLICED TO REMOVE NICKS.

Part: SKIN — CRACKED (BS 579) · airframe 47,729 hrs · 36,845 cycles

FUSELAGE SKIN INTERNAL DOUBLER AT FS 579 BETWEEN LONGERONS 28L AND 29L HAD A 0.45" CRACK. THE CRACK WAS TRIMMED OUT, AND AN INTERNAL REPAIR DOUBLER WAS INSTALLED.

Part: DOUBLER — CORRODED (BS 1154) · airframe 47,729 hrs · 36,845 cycles

CORROSION AT FS 1154 BETWEEN L-29R AND L30R TO THE INTERNAL DOUBLER RESULTED IN A 2" BY .5" CUTOUT. THE OVERLYING SKIN WAS UNAFFECTED. MX INSTALLED A REPAIR DOUBLER WITH A STRUCTURAL SHIM EXTERNALLY PER 09-465651-14. REPAIR WAS APPROVED FOR STATIC STRENGTH WITH DTA TO FOLLOW AT A LATER DATE.

Part: SKIN — CORRODED (BS 731 L29-30R) · airframe 47,729 hrs · 36,845 cycles

CORROSION CUTOUT TO THE SKIN AND INTERNAL DOUBLER AT FS 731 AND LONGERON 29R AND 30. REPAIR WAS ACCOMPLISHED WITH AN EXTERNAL DOUBLER AND TRIPLER.

Part: SKIN — CRACKED (HORIZONTAL STABS) · airframe 45,584 hrs · 35,351 cycles

DURING LETTER CHECK, THE HORIZONTAL STABILZIER UPPER AFT SKIN PANEL WAS FOUND WITH A FOUR INCH CRACK AT THE INBOARD AFT EDGE (RHS). THE UPPER SKIN PANEL WAS REPLACED, REF 460111-14.

Part: ODOR — DETECTED (CABIN) · airframe 38,091 hrs · 30,047 cycles

PASSING THRU 10,000 MSL NOTICED ELECTRICAL ODOR, NO SMOKE OR HAZE NOTED. PERFORMED DUCT BURNOUT AND INSPECTED AIRCRAFT.

Part: HYDRAULIC LINE — LEAKING (NR 2 ENGINE) · airframe 37,016 hrs · 29,319 cycles

LOST RIGHT HYD SYSTEM IN FLIGHT. REPLACED RIGHT ENGINE PRESSURE FLEX LINE FOR LEAKING.

Part: POWER SUPPLY — INOPERATIVE (EMERGENCY LIGHT) · airframe 36,458 hrs · 28,910 cycles

ON LAYOVER, FOUND SEAT ROWS 25-30, EMERGENCY FLOOR PATH LIGHTS INOPERATIVE. REPLACED AFT FLOOR PATH LIGHTING POWER SUPPLY AND BATTERY PACK.

Part: POWER SUPPLY — INOPERATIVE (EMERGENCY LIGHT) · airframe 36,458 hrs · 28,910 cycles

ON LAYOVER CHECK FOUND RT FWD OVERWING EMERGENCY LIGHT INOPERATIVE. REPLACED BATTERIES AND POWER SUPPLY.

Part: PROXIMITY SENSOR — FAILED (NLG) · airframe 35,960 hrs · 28,568 cycles

NOSE GEAR UNSAFE ON T/O. NOSE GEAR EXTENDED NORMALLY UPON RETURN. REPLACED NOSE GEAR LOCK PROX SENSOR.

Part: CHARGER — CRACKED (FLASHLIGHT) · airframe 34,696 hrs · 27,693 cycles

FLASHLIGHT CRADLE AT FWD ENTRY DOOR BROKEN.

Part: CONTROL WHEEL — JAMMED (OUT FLOW VALVE)

UNABLE TO PRESSURIZE AIRCRAFT WHILE CLIMBING THROUGH 3000 TO 4000 FT AGL. AUTO 1 AND AUTO 2 FAIL LIGHTS CAME ON AND UNABLE TO CLOSE OUTFLOW VALVE MANUALLY WITH CONTROL WHEEL PAST THE 20 DEG MARK ON THE FLAP SCALE. FOUND SCREW JAMMING CONTROL WHEEL IN PEDESTAL. REMOVED SCREW.

Part: LINKAGE — BROKEN (LT TE FLAP)

LEFT INBOARD FLAP I/B ACTUATOR LINKAGE ARM AND WELD ASSY BROKE ON GEAR DOOR. REPLACED ARM AND WELD ASSY. INSPECTED W/W AND OPERATED FLAPS SEVERAL TIMESM, OPS CKS NORMAL.

Part: SEPARATOR BAG — DIRTY (CABIN)

DURING CLIMB SEVERAL MINUTES AFTER TURNING ON ENG ANTI-ICE, BURNING ODOR WAS DETECTED AND FLT ATT AND PAX REPORTED FAINT SMOKE IN CABIN. CHECKED APU LT AND RT HYD SYS AND LT AND RT PACKS FOR LEAKS, NONE FOUND. ACMS BOTH FULL OF OIL PREFORMED DUCT BURN OUT PER M/M 36-10-00 AND REPLACED BOTH WATER SEPARATOR BAGS, NO FUMES FROM LT OR RT PACKS WITH APU OR ENG ANTI-ICE ON OR OFF.

Part: BATTERY — DISCHARGED (AFT GALLEY)

EMERGENCY FLASHLIGHT AT AFT GALLEY INOP. NO MRR. REJECTED 12-12-95, GT 595.

Part: ANGLE — CRACKED (KEEL BEAM)

FOUND DURING F-1 LETTER CHECK, KEEL BEAM AFT ANGLE CRACKED, CROSSOVER AFT SIDE OF MLG WHEEL WELL. REPAIRED PER SRM 53-05 FIG 101.

Part: PACK — ODOR (CABIN)

AFTER TAKEOFF HAD STRONG BURNING ODOR IN MID CABIN AREA, RETURNED ATL. TROUBLESHOOTING DETERMINED CAUSE OF ODOR FROM OIL CONTAMINATION IN PACK. REPLACED WATER SEPARATOR BAGS AND PERFORMED DUCT BURNOUT. RETURNED TO SERVICE.