N923DL

Part: WIRE — LOOSE · airframe 72,344 hrs · 55,292 cycles

FLIGHT CREW REPORTED SMOKE IN THE COCKPIT ON APPROACH; DONNED O2 MASKS. SMOKE WAS COMING FROM UNDERNEATH THE CAPTAINS TAXI LIGHT CONTROL PANEL. AN EMERGENCY WAS DECLARED. MAINTENANCE FOUND A LOOSE TERMINAL WIRE AT THE LANDING LIGHT/GROUND FLOOD LIGHT SWITCH PANEL. THE TERMINAL WAS RE-SECURED AND THE ACFT HAS RETURNED TO SERVICE.

Part: BATTERY PACK — INOPERATIVE (EMERGENCY LIGHTS) · airframe 70,322 hrs · 53,843 cycles

DURING LINE CHECK, MAINTENANCE FOUND THAT THE EMERGENCY LIGHTS AT ROWS 2-10 OF THE CABIN WERE INOPERATIVE. MAINTENANCE REPLACED THE BATTERY PACKS FOR THE NOTED LIGHTED AREAS AND THE OPS CHECKED GOOD.

Part: SKIN — CRACKED (BS 680) · corrosion level 2 · airframe 70,069 hrs · 53,665 cycles

CORROSION AND CRACKED BELLY SKIN AT BS 680, STRINGERS 29 - 30L, REPAIRED THE SKIN IAW ERA 537463-14, REV ORIG.

Part: WEB — CORRODED (DOOR FRAME) · corrosion level 2 · airframe 68,880 hrs · 52,874 cycles

C-1 DOOR AFT CUTOUT WEB CORRODED APPROXIMATELY STA 27-434, LONGERONS L-27 AND L-25. BURNISHED AREA C-1 DOOR CUT-OUT WEB STA 427 TO 434, LONGERON L-27 TO L-25 AND ALODINED AREA. C/W UT OF AREA WITH ORIG 0.040 REM MAT 0.030 IAW NDTM P. 4 CA 04-00-07 A 9710. EVALUATED AREA ORIG MAT 0.040, REM MAT 0.030, LOSS MAT 0.010 FOUND TO BE OUT OF LIMITS. FABRICATED DOUBLER PN 2024T3, 0.040, P/O ST-0000-3441, DIM 7.6 X 7.25 CUT OUT DAMAGE DIM 3.2 X 7.25 LOCATED & DRILLED DOUBLER HOLES. ALODINED & PRIMERED DOUBLER & AREA C-1 DOOR AFT CUTOUT WEB STA 427 L27R-L25R. INSTALLED DOUBLER ALL IAW SRM 53-01, 53-14-2, 51-10-4 & 51-10-3.

Part: PULLEY BRACKET — WORN (TAILCONE RELEASE) · airframe 68,880 hrs · 52,874 cycles

LEFT PULLEY BRACKET, TAIL CONE RELEASE CABLE, GUARD PIN HOLE WORN. R & R PULLEYS BRACKET FOR TAIL CONE RELEASE CABLE AT LOWER LEFT IAW SRM 51-30-02 AND SRM 51-30-01.

Part: FRAME — CRACKED (L1 DOOR) · airframe 68,880 hrs · 52,874 cycles

DOOR FRAME CRACKED INSIDE L-1 DOOR AT UPPER AFT CORNER. REMOVED L-1 DOOR IAW AMM 52-11-00-401, STEP 1A-2A5. INSTALLED SERVICEABLE L1 DOOR IAW AMM 52-11-00-501. PERFORMED SATISFACTORY RIG & LEAK/PRESSURE CHECK IAW AMM 52-11-00.

Part: SKIN — DAMAGED (BS 239) · airframe 68,886 hrs · 52,880 cycles

SKIN FOUND DENT AND SCRATCH AT BS 239 BELOW STRINGER 17L. REPAIRED IAW ERA 531743-14, REV A SEC III.

Part: WIRE — BROKEN (EMERGENCY LIGHT) · airframe 67,641 hrs · 51,974 cycles

DURING LINE CHECK, MAINTENANCE FOUND THAT THE EMERGENCY LIGHTS AT ROW 6DEF WAS INOPERATIVE. MAINTENANCE FOUND WIRES BROKEN AT THE LIGHT RECEPTACLE. REPLACED THE LIGHT ASSEMBLY AND THE SYSTEM RETURNED TO NORMAL.

Part: SKIN — CORRODED (BS 617-636) · corrosion level 2 · airframe 69,188 hrs · 53,066 cycles

SIGNS OF CORROSION FOUND ON FUSELAGE LOWER SKIN AND INTERNAL C2 DOOR SURROUND DOUBLER. DAMAGE LOCATED AT STA 617-636 AND BETWEEN LONGERONS 29L AND 29R. DAMAGE CUT OUT AND REPAIRED IAW SECTION I OF ER/A 525291-14.

Part: SKIN — CORRODED (FUSELAGE) · corrosion level 2 · airframe 69,188 hrs · 53,066 cycles

CORROSION FOUND ON SKIN AT TCAS ANTENNA LOCATION. PERMANENT REPAIR ACCOMPLISHED IAW ER/A 525060-14.

Part: LIGHT — INOPERATIVE (COCKPIT/CABIN) · airframe 66,818 hrs · 51,381 cycles

DURING LINE CHECK, MAINTENANCE FOUND THAT THE OVERHEAD EMERGENCY LIGHT IN COCKPIT AND AT DOORS L1 & L2 WERE INOPERATIVE. MAINTENANCE REPLACED THE LIGHT ASSEMBLIES, REPLACED BULBS, AND PERFORMED A SATISFACTORY FUNCTIONAL CHECK OF IT.

Part: WIRE — SHORTED (EMERGENCY LIGHTS) · airframe 66,250 hrs · 51,009 cycles

DURING LINE CHECK, MAINTENANCE FOUND THAT THE EMERGENCY LIGHT IN AFT CABIN. MAINTENANCE FOUND A SHORT IN THE WIRES IN THE TAIL AND REPAIRED WIRES.

Part: SPRING — MISSING (TEE) · airframe 65,785 hrs · 50,661 cycles

MX DISCOVERED THAT THE TEE PIN SPRINGS WERE MISSING AND REQUIRED REPLACEMENT.

Part: BULKHEAD — CRACKED (TAILCONE) · airframe 65,785 hrs · 50,661 cycles

MX DISCOVERED THAT THE EMERGENCY ESCAPE PATH TAILCONE RELEASE ALIGNMENT PIN BULKHEAD SKIN WAS CRACKED. THIS IS CONSIDERED A DEFECT IN THE EMERGENCY ESCAPE SYS AND COULD HAVE AN ADVERSE AFFECT ON THE EVACUATION ROUTE IF IT PREVENTED PROPER DEPLOYMENT OF THE TAILCONE. THIS NOT IN COMPLIANCE WITH 14 CFR PART 121.703. THE PIN AND DAMAGE WAS R & R IAW ER/A 483847-14MA. THE RII WAS SATISFACTORY.

Part: PIN — WORN (TAILCONE RELEASE) · airframe 65,785 hrs · 50,661 cycles

MX DISCOVERED THAT THE RELEASE LATCH "TEE PIN" FOR THE TAILCONE WAS WORN OUT OF ALLOWABLE LIMITS. THE T-PINS WERE REPLACED AND THE SYS WAS RIGGED TO SPECIFICATIONS. THE FUNCTIONAL CHECK WAS COMPLETED SATISFACTORILY.

Part: RELEASE CABLE — FRAYED (TAILCONE) · airframe 65,785 hrs · 50,661 cycles

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

Part: ARM — OUT OF RIG (TAILCONE RELEASE) · airframe 65,785 hrs · 50,661 cycles

MX DISCOVERED THAT THE TAILCONE RELEASE ARM WAS OUT OF ALLOWABLE RIG LIMITS. THE AFT TAILCONE RELEASE ARM WAS ADJUSTED TO GET PIN CLEARANCE FROM THE DOOR STOP AND THE SYSTEM WAS RIGGED BACK INTO SPECIFICATIONS. THE RII STEPS WERE COMPLETED.

Part: RELEASE CABLE — BROKEN (TAILCONE) · airframe 65,785 hrs · 50,661 cycles

MX DISCOVERED THAT THE EMERGENCY ESCAPE PATH TAILCONE RELEASE CABLE WAS BROKEN. THIS IS CONSIDERED A DEFECT IN THE EMERGENCY ESCAPE SYS AND COULD HAVE AN ADVERSE AFFECT ON THE EVACUATION ROUTE IF IT PREVENTED PROPER DEPLOYMENT OF THE TAILCONE. THIS NOT IN COMPLIANCE WITH 14 CFR, PART 121.703. THE CABLE END WAS REPLACED.

Part: POWER SUPPLY — INOPERATIVE (EMERGENCY LIGHT) · airframe 65,738 hrs · 50,630 cycles

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

Part: CONNECTOR — LOOSE (EMERGENCY LIGHTS) · airframe 65,738 hrs · 50,630 cycles

DURING LINE CHECK, MX FOUND EMERGENCY LIGHTS AT ROW 18D IN CABIN INOPERATIVE. FOUND CONNECTOR LOOSE, CONNECTED IT, AND FUNCTIONALLY CHECKED SYSTEM.

Part: BATTERY — INOPERATIVE (EMERGENCY LIGHTS) · airframe 65,140 hrs · 50,224 cycles

DURING LINE CHECK, MX FOUND THAT BOTH THE FWD AND THE AFT OVERWING EMERGENCY EXIT SIGNS WERE INOPERATIVE. MX REPLACED THE BATTERIES IN BOTH BATTERY PACKS AND THE LIGHTS RETURNED TO AN OPS CONDITION.

Part: LONGERON SPLICE — CRACKED (FUSELAGE) · airframe 62,147 hrs · 48,107 cycles

LONGERON 29L SPLICE IS CRACKED AT STA 1193-1211. REMOVED SPLICE ON LONGERON 29L AT STA 1193-1211 IAW MD80 SRM 51-30-5 PG 12 AND 29. TP BE REPAIRED ON NRC 202495.

Part: FITTING — CHAFED (NR 2 PYLON) · airframe 62,147 hrs · 48,107 cycles

NR 2 PYLON AT NAC 201 I/B LOWER SIDE BULKHEAD FITTING EXTERIOR CHAFED. BLENDED DAMGAED AREA, FOUND TO BE OUT OF LIMITS. REPAIR TO BE ACCOMPLISHED PER PRI 501029-14 REV 0 & 1.

Part: FRAME — CRACKED (FUSELAGE) · airframe 62,147 hrs · 48,107 cycles

MAIN CABIN STA 1117 LONGERON 7L FRAME IS CRACKED. CUT OUT DAMAGED AREA IAW MD80 SRM 53-03D FIG 4. FABRICATED REPAIR PART 2 EA ANGLE REPAIR AND FILLER REPAIR IAW MD80 SRM 53-03D FIG 4 AND INSTALLED PER MD80 SRM 51-30-2 PARA 1 PG 1, MD80 SRM 51-30-5 PARA 1 PG 1 AND SRM 51-20-0 PARA 1 PG 1 AT SAA ON N/R CARD 196449.

Part: CUSP WEB — CORRODED (FUSELAGE) · airframe 62,147 hrs · 48,107 cycles

LT CUSP WEB AT STA 834 LBL 58 IN MAIN CABIN IS CORRODED. FOUND TO BE OUT OF LIMITS IAW MD80 SRM 53-01 PG 8 FIG 1. FABRICATED AND INSTALLED FILLER SPLICE DOUBLER AND RING DOUBLER PER MD80 SRM 51-30-2 PG 24 DURING HMV ON NRC 197383.

Part: FLOOR SUPPORT — CORRODED (FUSELAGE) · airframe 62,147 hrs · 48,107 cycles

CORROSION ON MAIN CABIN FLOOR SUPPORT ATTACH ANGLE STA 200 RBL 42. FOUND TO BE OUT OF LIMITS IAW MD80 SRM 53-01 PG 8 FIG 1. FABRICATED AND INSTALLED FLOOR SUPPORT ANGLE ON MAIN CABIN AT STA 200 RBL 42 IAW MD80 SRM 51-30-01 FIG 1 PGS 1, 2 AND 3 AT SAA DURING HMV ON.

Part: LONGERON — CRACKED (FUSELAGE) · airframe 62,147 hrs · 48,107 cycles

IN CABIN FUSELAGE LONGERON 3L IS CRACKED AT STA 160. BLENDED DAMAGE SECTION, FABRICATED AND INSTALLED LONGERON REPAIR AND SPLICE IAW DC9/MD80 SRM 53-02 DURING HMV.

Part: FLOOR SUPPORT — CORRODED (FUSELAGE) · airframe 62,147 hrs · 48,107 cycles

CORROSION ON MAIN CABIN FLOOR SUPPORT MOUNT TRACK STA 188 RBL 4. FOUND FLOOR SUPPORT STA 188 RBL 44 OUT OF LIMITS IAW MD80 SRM 53-01 FIG 1 SHEET 3 PG 8. FABRICATED AND INSTALLED FLOOR SUPPORT AT STA 188 RBL 44 IAW MD80 SRM 51-30-5 PG 12 AT DURING HMV ON.

Part: CUSP WEB — CORRODED (FUSELAGE) · airframe 62,147 hrs · 48,107 cycles

MAIN CABIN RT CUSP WEB HAS CORROSION FROM STA 503-525 INCLUDING THE PREVIOUS REPAIR DOUBLER AT STA 511. REMOVED CORROSION CUSP WEB AREA FROM STA 503-525. MATERIAL LOST FOUND TO BE OUT OF LIMITS IAW MD80 SRM 53-01 FIG 1 SHEET 3. CUT OUT DAMAGE AREA IAW DWG SG09530019. FABBED FILLER, DOUBLER AND RING DOUBLER IAW MD80 SRM 51-10-4 FIG 3 AND SG09530019 DRAWING AND CUSP BEAM SPLICE UPPER PER SRM 51-10-0 PG 2 AND 51-10-4 FIG 3A AND INSTALLED IAW MD80 SRM 51-30-5 PGS 1-14 51-30-2 PGD 24 AND 26B DURING HMV ON NRC 203713. (NRC 203713)

Part: FLOOR SUPPORT — GOUGED (FUSELAGE) · airframe 62,147 hrs · 48,107 cycles

MAIN CABIN FLOOR SUPPORT STRUCTURE IS GOUGED AT STA 826 LBL 17-RBL 17. FOUND TO BE OUT OF LIMITS IAW DC9/MD80 SRM 53-01 FIG 1 PG 8. FABRICATED AND INSTALLED FLOOR SUPPORT IAW DC9/MD80 SRM 51-30-5 PARAGRAPH 7 ON NRC 202315. (NRC 202315)

Part: SEAT TRACK — CORRODED (FUSELAGE) · airframe 62,147 hrs · 48,107 cycles

MAIN CABIN SEAT TRACK AT RBL 22 HAS CORROSION FROM SEAT TRACK PLUG AT STA 433-797. FOUND STA 498.5-499.5 AND STA 597-598 TO BE OUT OF LIMITS IAW MD80 SRM 51-10-01 FIG 26. INSTALLED NEW SECTION OF TRACK RBL 22 STA 493-609 AND 2 EA SPLICES AND REPAIR PLATES IAW MD80 SRM 53-05 FIG 4F AT SAA DURING HMV ON. (NRC 202328)

Part: SEAT TRACK — CORRODED (FUSELAGE) · airframe 62,147 hrs · 48,107 cycles

MAIN CABIN STA 1098-1088 BL22L SEAT TRACK HAS CORROSION. FOUND OUT OF LIMITS IAW MD80 SRM 53-05 FIG 4B 1 SECTION D-D SHEET 2 PG 28. REPAIR TO BE ACCOMPLISHED ON NRC 202469.

Part: SEAT TRACK — CORRODED (FUSELAGE) · airframe 62,147 hrs · 48,107 cycles

MAIN CABIN STA 454 TO 456 BL L22 SEAT TRACK HAS CORROSION. REMOVED CORROSION AT STA 454-456 L22 SEAT TRACK, FOUND TO BE OUT OF LIMITS.

Part: CUSP WEB — CORRODED (FUSELAGE) · airframe 62,147 hrs · 48,107 cycles

CTR CARGO STA 560-579 LONGERON 18R LOWER WEB CUSP SURFACE AREA HAS CORROSION. FOUND TO BE OUT OF LIMITS IAW MD80 SRM 53-01 FIG 1 PARA 3 PG 8, 2. CUT OUT DAMAGED AREA AND FABRICATED AND INSTALLED CUSP MEMBRANE ON LONGERON 18R BETWEEN STA 560-579 PER MD88 DRAWING SG09530019 AND SRM 51-30-2 PG 1 AT SAA ON N/R CARD 191671.

Part: CUSP WEB — CORRODED (FUSELAGE) · airframe 62,147 hrs · 48,107 cycles

MAIN CABIN RT CUSP WEB HAS CORROSION AT STA 287 AREA IS BLOWN OUT. FOUND CORROSION TO HAVE 100 PERCENT MATERIAL LOSSOUT OF LIMITS PER MD80 SRM 53-10-02 PG 12. REPAIR TO BE ACCOMPLISHED ON NRC 203707.

Part: SEAT TRACK — CORRODED (FUSELAGE) · airframe 62,147 hrs · 48,107 cycles

MAIN CABIN STA 640 TO 797 BL 22L SEA TRACK HAS CORROSION. REMOVED CORROSION, AREA BETWEEN STA722 TO 796 OUT OF LIMITS, CUT OUT DAMAGED AREA OF SEAT TRACK, INSTALLED NEW SEAT TRACK SECTION AND SPLICE IAW DC9/MD80 SRM 53-05 DURING HMV.

Part: FLOOR PANEL — CORRODED (CABIN) · airframe 62,147 hrs · 48,107 cycles

CABIN FLOOR PANEL 160G HAS CORROSION AT NUMEROUS LOCATION ON UPPER SURFACE AND ASSOC MOUNTING CLIPS 2EA HAVE CORROSION AT FASTENER HOLES. BLENDED OUT CORROSION ON CABIN FLOOR PNL 160G AND FOUND TO BE OUT OF LIMITS IAW DC9/MD80 SRM 53-01. BLENDED OUT CORROSION 2EA FLOOR SUPPORT FITTINGS. FOUND TO BE OUT OF LIMITS IAW DC9/MD80 SRM 53-01. FABBED FLOOR PNL AND DOUBLER IAW DC9/MD80 SRM 53-25-0 PG 5&7. INSTALLED DOUBLER ON FLOOR PNL 160G IAW DC9/MD80 SRM 51-30-2.1. REMOVED AND REPLACED 2EA FITTING AT CABIN FLOOR PNL IAW DC9/MD80 SRM 51-30-2 PG 24. AT SAA DURING PSV.

Part: SEAT TRACK — CORRODED (FUSELAGE) · airframe 62,147 hrs · 48,107 cycles

MAIN CABIN SEAT TRACK AT RBL 55 HAS CORROSION FROM STA 306 TO STA 799. REMOVED CORROSION FOUND TO BE OUT OF LIMITS, REMOVED DAMAGE AT 3 EA AREAS, FABRICATED AND INSTALLED 3 PLUGS AND CHANNELS IAW DC9/MD80 SRM 51-30-1 DURING HMV AT ST AEROSPACE SAN ANTONIO.

Part: FLOOR PANEL — CORRODED (CABIN) · airframe 62,147 hrs · 48,107 cycles

CABIN FLOOR PANEL 1174 HAS CORROSION ON 3 EA LOWER SURFACE AREAS WHERE MOUNT SHIMS ARE MISSING AND CENTER SUPPORT CHANNEL IS CRACKED AT ENDS AND HAS 3 EA PUNCTURES. CORROSION FOUND TO BE OUT OF LIMITS, FABRICATED FLOOR PANEL AND CENTER SUPPORT CHANNEL AND INSTALLED IAW DC9/MD80 SRM 51-30 DURING HMV.

Part: SEAT TRACK — CORRODED (FUSELAGE) · airframe 62,147 hrs · 48,107 cycles

MAIN CABIN STA 422 TO 797 BL 55 SEAT TRACK HAS CORROSION. REMOVED CORROSION, FOUND TO BE OUT OF LIMITS IN 3 AREAS, REMOVED DAMAGED AREAS, INSTALLED PLUGS AND NUT CHANNELS IAW DC9/MD80 SRM 53-05 FIG 4A FROM STA 423-426, 437-441 AND 498 TO 501 DURING HMV.

Part: LONGERON — CORRODED (FUSELAGE) · airframe 62,147 hrs · 48,107 cycles

AFT CARGO LT TUNNEL AREA AT STA 1199 LONGERON 22L HAS CORROSION ON LOWER SIDE AT SPLICE FITTING. FOUND OUT OF LIMITS. CUT OUT CORRODED SECTION PER MD80 SRM 53-02 PG 50 FIG 18 SHEET 1. FABRICATED LONGERON REPAIR AND SPLICE AT STA 1199 STR 22L AND INSTALLED PER MD80 SRM 53-02 PG 50-51 FIG 18 AT SAA ON N/R CARD 197301.

Part: CUSP WEB — CORRODED (FUSELAGE) · airframe 62,147 hrs · 48,107 cycles

MAIN CABIN RT SIDE CUSP WEB STA 606 TO 610 HAS CORROSION. REMOVED CORROSION, OUT OF LIMITS, REMOVED DAMAGE, FABRICATED FILLER AND DOUBLERS AND INSTALLED IAW REPAIR DRAWING G 09530019 DURING HMV.

Part: FITTING — CRACKED (LT WING) · airframe 62,147 hrs · 48,107 cycles

LT WING FIXED L/E RIB ANGLE CLIP IS CRACKED AT STA XOS 352. HFEC INSPECTION PER NDTSPM 06-10-01-001 VERIFIED CRACK EXIST AT DISCREPANT AREA. REPAIR TO BE PERFORMED ON NRC 191904.

Part: FLOOR SUPPORT — CORRODED (FUSELAGE) · airframe 62,147 hrs · 48,107 cycles

CORROSION ON MAIN CABIN FLOOR SUPPORT TRACK STA 1140 TO STA 1145 LBL 3. FLOOR SUPPORT TRACK FOUND TO BE OUT OF LIMITS, REPLACED ON OPN 0101 DURING HMV.

Part: CUSP WEB — CORRODED (FUSELAGE) · airframe 62,147 hrs · 48,107 cycles

MAIN CABIN RT CUSP WEB HAS CORROSION FROM STA 655 TO 693. REMOVED CORROSION FROM RT CUSP WEB, OUT OF LIMITS, FABRICATED AND INSTALLED NEW SECTION OF WEB IAW DC9/MD80 SRM 51-10-3 DURING HMV.

Part: SKIN — DENTED (FUSELAGE) · airframe 62,147 hrs · 48,107 cycles

DENT ON FUSELAGE SKIN AT STA 275 BETWEEN L 29R AND L30 AREA OF WATER DRAIN FITTING. FOUND 4 EA DENTS IN AREA WITH 2 DENTS OUT OF LIMITS DUE TO CREASE, ACCOMPLISHED ERA 499679-14 REV V ORIG DURING HMV.

Part: CUSP WEB — CRACKED (FUSELAGE) · airframe 62,147 hrs · 48,107 cycles

MAIN CABIN RT CUSP WEB REPAIR HAS 2EA CRACKS BETWEEN STA 218 & 237. REMOVED SEAT TRACK STA 218-256, REMOVED SPLICE AND CUSP WEB AT STA 218 & 237. LOCATED AND DRILLED NEW P/N 9930538U67. OK TO REINSTALL SEAT TRACK.

Part: SKIN — DENTED (BS 275 L29L) · airframe 62,147 hrs · 48,107 cycles

DENT ON FUSELAGE SKIN AT BS 275 L29L. DENT OUT OF LIMITS IAW 53-04-1 PG 28 PARA 5A.

Part: CUSP WEB — CORRODED (FUSELAGE) · airframe 62,147 hrs · 48,107 cycles

MAIN CABIN RT CUSP WEB HAS CORROSION FROM STA 262 TO 269. FOUND AREA TO HAVE 100 PERCENT MATERIAL LOSS, REMOVED DAMAGED SECTION FABRICATED DOUBLER SPLICE AND FILLER AND INSTALLED IAW DC9/MD80 SRM 51-30 AND DWG G09530019 DURING HMV.

Part: SKIN — CORRODED (FUSELAGE) · airframe 62,147 hrs · 48,107 cycles

FUSELAGE SKIN BULGED OUT AT STA 217 BETWEEN L29 R AND L30 AROUND FWD JACK PAD FITTING. REMOVED JACK PAD AND DOUBLER, FOUND INNER DOUBLER CRACKED AND CORRODED.

Part: CUSP WEB — CORRODED (FUSELAGE) · airframe 62,147 hrs · 48,107 cycles

MAIN CABIN STA 1238 LT CUSP WEB IS CORRODED RBL 58. BLENDED CORROSION AT STA 1238 CUSP WEB RBL 58, FOUND TO BE OUT OF LIMITS.

Part: ATTACH FITTING — CORRODED (GIRT BAR) · airframe 62,147 hrs · 48,107 cycles

IN MAIN CABIN GIRT BAR ATTACH FITTINGS ARE CORRODED STA 1143 AND STA 1167. REMOVED CORROSION, FOUND TO BE OUT OF LIMITS. REPLACED GIRT BAR FITTINGS, FABRICATED AND INSTALLED GIRT BAR BRACKETS IAW SRM 51-30-5 DURING HMV.

Part: CUSP WEB — CORRODED (FUSELAGE) · airframe 62,147 hrs · 48,107 cycles

MAIN CABIN LEFT CUSP WEB CORRODED STA 1287-1307 LBL 46-60. REMOVED FASTENERS FOR ACCESS, REMOVED CORROSION FOUND TO BE OUT OF LIMITS.

Part: HINGE FITTING — CORRODED (RT MLG DOOR) · airframe 62,147 hrs · 48,107 cycles

RT MLG DOOR FWD UPPER HINGE HAS A CRACK. HFEC INSP IAW NDTSPM 06-10-01.001 VERIFIED CRACK EXISTS ON HINGE. REMOVED RT MLG DOOR HINGE FITTING IAW MD80 SRM 51-30-1 AND 51-30-5. AFTER REMOVAL OF HINGE FITTING FOUND SMALL PITTING CORROSION AND CHAFE DAMAGE ON MOUNTING SURFACES. TO BE COMPLETED ON NR 196417.

Part: CUSP WEB — CORRODED (FUSELAGE) · airframe 62,147 hrs · 48,107 cycles

MAIN CABIN LEFT CUSP WEB IS CORRODED STA 1231-1250 LBL 47-61. REMOVED 6 RIVETS FOR ACCESS, BLENDED CORROSION FOUND TO BE OUT OF LIMITS. REMOVED DAMAGE AREA FABRICATED AND INSTALLED FILLER AND REPAIR IAW DC9/MD88 SRM 53-0 5 DURING HMV.

Part: CUSP WEB — CORRODED (FUSELAGE) · airframe 62,147 hrs · 48,107 cycles

IN MAIN CABIN LT CUSP WEB HAS CORROSION STA 845-886 LBL 59/ BLENDED CORROSION, 100 PERCENT MATERIAL LOSS, REMOVED DAMAGED AREA FABRICATED REPAIR PARTS AND FILLER, INSTALLED PER DC9/MD80 SRM 51-30-02 DURING HMV.

Part: LONGERON — CORRODED (FUSELAGE) · airframe 62,147 hrs · 48,107 cycles

AFT CARGO LONGERON 28R HAS CORROSION AT STA 1287 UNDER TRANSVERSE FRAME. BLENDED AREA, MATERIAL LOSS 100 PERCENT. REMOVED DAMAGED AREA, FABRICATED AND INSTALLED REPAIR SECTION AND SPLICES IAW DC9/MD80 SRM 53-02 DURING HMV.

Part: DOUBLER — CORRODED (FS 1256-1266) · airframe 62,147 hrs · 48,107 cycles

AFT CARGO BILGE AREA, SKIN DOUBLER FROM FS 1256-1266 AT CENTER LONGERON HAS CORROSION ON SURFACE AND EDGES ARE WARPED AND BULGED. REMOVED ALL FASTENERS COMMON TO EXISTING SKIN REPAIR FS1256-1266 AT L30 IAW MD80 SRM 51-30-5 PG 29. REMOVED EXTERNAL DOUBLER.

Part: CUSP WEB — CORRODED (FUSELAGE) · airframe 62,147 hrs · 48,107 cycles

IN MAIN CABIN LEFT CUSP WEB IS CORRODED STA 655-674 LBL 60. REMOVED CORROSION, DAMAGE FOUND TO BE OUT OF LIMITS, REMOVED DAMAGED SECTION OF CUSP WEB, FABRICATED FILLER AND DOUBLERS AND INSTALLED IAW DC9/MD80 SRM 51-30-2 DURING HMV.

Part: LONGERON — CORRODED (FUSELAGE) · airframe 62,147 hrs · 48,107 cycles

AFT CARGO LONGERON 29R HAS 2 EA LOCATIONS WITH CORROSION AT FASTENERS FROM FS 1322 TO 1309. BLENDED CORROSION, OUT OF LIMITS, FABRICATED REPAIR SPLICE AND INSTALLED IAW DC9/MD80 SRM 53-02 DURING HMV.

Part: CUSP WEB — CORRODED (FUSELAGE) · airframe 62,147 hrs · 48,107 cycles

IN MAIN CABIN LEFT CUSP WEB IS CORRODED STA 674 LBL 59. REMOVED CORROSION. FOUND TO BE OUT OF LIMITS IAW MD80 SRM 53-01 FIG 1 SHEET 3. FABRICATED AND INSTALLED REPAIR DOUBLER, FILLER AND RING DOUBLERS IAW MD80 SRM 53-05 AND DRAWING SE09530019 DURING HMV ON NRC 197365.

Part: CUSP WEB — CORRODED (FUSELAGE) · airframe 62,147 hrs · 48,107 cycles

MAIN CABIN LEFT CUSP WEB IS CORRODED STA 617-636 LBL 60. FOUND TO BE OUT OF LIMITS UNDER NUT PLATE BRACKET.

Part: CUSP WEB — CORRODED (FUSELAGE) · airframe 62,147 hrs · 48,107 cycles

MAIN CABIN LEFT CUSP WEB IS CORRODED LBL 60 STA 598-671. REMOVED CORROSION ON CUSP WEB, FOUND TO BE OUT OF LIMITS. FABRICATED AND INSTALLED FILLER, DOUBLER AND RING DOUBLER PER MD80 SRM 53-05 AND DRAWING SG09530019 DURING HMV ON NRC 197370.

Part: CUSP WEB — CORRODED (FUSELAGE) · airframe 62,147 hrs · 48,107 cycles

CTR CARGO FROM STA 617 TO STA 598 AT LONGERON 18R LOWER WEB CUSP AREA HAS SURFACE CORROSION. REMOVED CORROSION FROM LOWER AND UPPER SURFACE OF CUSP WEB, FOUND TO BE OUT OF LIMITS.

Part: FITTING — CORRODED (FUSELAGE) · airframe 62,147 hrs · 48,107 cycles

FWD CARGO LOWER BILGE FRAME TIE HAS CORROSION AT STA 427 AND L-30. REMOVED CORROSION, FOUND TO BE OUT OF LIMITS, REMOVED DAMAGED TIE SECTION, FABRICATED NEW SECTION AND REPAIR SPLICE AND INSTALLED IAW DC9/MD80 SRM 53-14-2 DURING HMV.

Part: SPACER — CORRODED (CARGO BAY) · airframe 62,147 hrs · 48,107 cycles

CTR CARGO DOOR JAMB LWR SECTION SILL SURFACE CORROSION. REMOVED SURFACE CORROSION FOUND OUT OF LIMITS IAW DC9/MD80 SRM 53-01-FIG 1. REMOVED DAMAGED SPACER AT CTR CARGO DOOR JAMB LWR SECTION. FABBED SPACER IAW DC9/MD80 SRM 53-05 FIG 123. TREATED AND PRIMED AREA SPACER IAW DC9/MD80 SRM 51-10-3 PG 31. TO BE COMPLETED ON NR 191667.

Part: LONGERON SPLICE — CORRODED (FUSELAGE) · airframe 62,147 hrs · 48,107 cycles

CTR CARGO STA 579 LONGERON 28L TIE IN SPLICE ON LONGERON, CORROSION ON SURFACE. REMOVED CORROSION, FOUND TO BE OUT OF LIMITS, FABRICATED AND INSTALLED REPLACEMENT FILLER IAW DC9/MD80 SRM 51-30-5 DURING HMV.

Part: STOP FITTING — DAMAGED (FUSELAGE) · airframe 62,147 hrs · 48,107 cycles

FWD CARGO DOOR FWD JAMB NR 5 STOP FITTING HAS AN A ELONGATED HOLE. REMOVED NR 5 JAMB FITTING FOUND HOLE ELONGATED AWAITING ENGINEERING. TO BE COMPLETED ON NR 196857 (NRC 196857).

Part: LONGERON — CORRODED (FUSELAGE) · airframe 62,147 hrs · 48,107 cycles

FWD CARGO LONGERON 19R AND LONGER SPLICE AND 2 EA SPLICE FITTINGS HAVE CORROSION FROM STA 294-326. CORROSION OUT OF LIMTS, REMOVED LONGERON SEGMENT, AND SPLICE FITTINGS, FABRICATED AND INSTALLED LONGERON AND FITTINGS IAW DC9/MD80 STM 53-02 DURING HMV.

Part: FRAME — CRACKED (FUSELAGE) · airframe 62,147 hrs · 48,107 cycles

AFT ACCESSORY COMPARTMENT RT SIDE AT STA 1380, FWD SIDE OF FRAME CRACK IN RADIUS OF SUPPORT STRUCTURE FOR UPPER AFT PYLON MOUNT (NRC 198073).

Part: SKIN — CRACKED (LE SLAT) · airframe 62,147 hrs · 48,107 cycles

LT WING NR 3 SLAT INNER SKIN HAS A CRACK AT STA XOS 348 AT FASTENER HOLE (NRC 191898).

Part: FORMER — CRACKED (RT WING) · airframe 62,147 hrs · 48,107 cycles

RT WING L/E COMPT XOS 461 FORMER IS CRACKED AT FASTENER HOLE (NRC 191413).

Part: DOUBLER — CRACKED (RT WING) · airframe 62,147 hrs · 48,107 cycles

RT WING LEADING EDGE COMPT XFS 397 DOUBLER ON FORMER IS CRACKED (NRC 191871).

Part: SKIN PANEL — DELAMINATED (RT WING) · airframe 62,147 hrs · 48,107 cycles

RT WING UPPER SURFACE T/E PNL IS CRACKED AND DELAMINATED XW 138 TO 118 (NRC 191414).

Part: RIB — CRACKED (RT WING) · airframe 62,147 hrs · 48,107 cycles

RT WING FIXED L/E RIB IS CRACKED AT UPPER FWD SPAR ATTACHMENT STA XRS 162 THRU 3 FASTENER HOLES. (NRC 191358)

Part: SKIN — CRACKED (LT WING) · airframe 62,147 hrs · 48,107 cycles

LT WING FIXED L/E SKIN IS CRACKED AT LOWER T/E AT STA XRS 250 (NRC 191363).

Part: SKIN — CRACKED (LT WING) · airframe 62,147 hrs · 48,107 cycles

LT WING FIXED L/E SKIN LOWER T/E IS CRACKED AT STA XRS 264 (NRC 191364).

Part: SKIN — CORRODED (FUSELAGE) · airframe 62,147 hrs · 48,107 cycles

UPON REMOVAL OF LONGERON 29L FROM STA 1212 TO STA 1338 FOUND ADDITIONAL CORROSION ON SKIN. BLENDED OUT CORROSION, FOUND TO BE OUT OF LIMITS, FABRICATED INTERNAL REPAIR DOUBLER AND INSTALLED IAW MD80 SRM 53-04-0. DURING HMV AT ST AEROSPACE SAN ANTONIO.

Part: SKIN — DENTED (FUSELAGE) · airframe 62,147 hrs · 48,107 cycles

DENT ON FUSELAGE SKIN OVER FRAME AT STA 256, 3" ABOVE LONGERON 18L. MEASURED DENT, FOUND TO BE OUT OF LIMITS.

Part: SKIN — DENTED (BS 218) · airframe 62,147 hrs · 48,107 cycles

DENT ON FUSELAGE SKIN OVER FRAME AT BS 218 BETWEEN L18-19L. DENT OUT OF LIMITS IAW SRM 53-04-1 FIG 8. REMOVED DENT IAW SRM 53-04 FIG 38 COND 4.

Part: SKIN — DENTED (FUSELAGE) · airframe 62,147 hrs · 48,107 cycles

GOUGE ON FUSELAGE SKIN EXTERNAL SURFACE, AT STA 204, 12" ABOVE L18L. MEASURED GOUGE, DAMAGE IS OUT OF LIMITS.

Part: SKIN — DENTED (FUSELAGE) · airframe 62,147 hrs · 48,107 cycles

DENT ON FUSELAGE SKIN OVER FRAME AT STA 256 BELOW LONGERON 17L. MEASURED DENT, FOUND TO BE OUT OF LIMITS.

Part: SKIN — DENTED (FUSELAGE) · airframe 62,147 hrs · 48,107 cycles

2 EA DENT ON FUSELAGE SKIN AT STA 254 AND 255 BETWEEN L17L AN L18L. MEASURED DENT, FOUND TO BE OUT OF LIMITS.

Part: SKIN — DENTED (FUSELAGE) · airframe 62,147 hrs · 48,107 cycles

DENT ON FUSELAGE SKIN AT STA 230, BETWEEN L18L AND L18L. MEASURED DENT, FOUND TO BE OUT OF LIMITS.

Part: WIRE — LOOSE (CATWALK) · airframe 61,895 hrs · 47,928 cycles

DURING LINE CHECK, MAINTENANCE FOUND AN EMERGENCY PATHWAY LIGHT FOR THE CATWALK IN THE TAIL COMPARTMENT WAS INOPERATIVE. MAINTENANCE FOUND A LOOSE WIRE AND SECURED IT. THE SYSTEM RETURNED TO NORMAL OPERATION.

Part: WIRE HARNESS — DEFECTIVE (CABIN) · airframe 61,124 hrs · 47,421 cycles

DURING LINE CHECK MAINTENANCE FOUND EMERGENCY LIGHT AT SEAT 15 D, E INOPERATIVE. MAINTENANCE REPLACED LIGHT HARNESS AT ROW 15 D, E. OPERATION OF LIGHT NOW CHECKS GOOD.

Part: POWER SUPPLY — INOPERATIVE (CABIN) · airframe 60,802 hrs · 47,186 cycles

DURING LINE CHECK MAINTENANCE FOUND EMERGENCY LIGHT POWER SUPPLY B5-27 INOPERATIVE. MAINTENANCE REPLACED POWER SUPPLY PER AMM 33-53.

Part: SKIN — CRACKED (BS 1473 L3R) · airframe 60,179 hrs · 46,734 cycles

A CRACK IN THE FUSELAGE SKIN WAS FOUND AT STA 1473, L3R. CRACK WAS REPAIRED IAW ER/A 491884-14.

Part: SILL — CORRODED (FUSELAGE) · airframe 60,179 hrs · 46,734 cycles

DURING PSV "N" CHECK IN MSP C-3 DOOR CUTOUT LOWER SILL LONGERON CORRODED ALONG ITS VERTICAL WEB. REPAIRED IAW ER/A 491895-14.

Part: SKIN — GOUGED (BS 1305) · airframe 60,179 hrs · 46,734 cycles

WHILE IN MSP FOR PSV N-CHECK FOUND FUSELAGE SKIN DENTED AND GOUGED AND STA 1305, L18R-L19R. REPAIRED IAW ER/A 492041-14.

Part: PANEL — LOOSE (VERTICAL STAB) · airframe 60,179 hrs · 46,734 cycles

DURING PSV "N" CHECK IN MSP, FOUND LOOSE FASTENERS IN VERT STAB L/E PANEL AT ZRS52.267. REPAIRED IAW ER/A 455844-14.

Part: SKIN — CRACKED (VERTICAL STAB) · airframe 60,179 hrs · 46,734 cycles

VERTICAL STAB LT DORSAL SIDE SKIN WAS FOUND CRACKED AT THE LOWER AFT CORNER OF THE RAM AIR INLET ACCESS DOOR CUTOUT. REPAIRED IAW ER/A 491888-14.

Part: DOUBLER — DAMAGED (FUSELAGE) · airframe 60,179 hrs · 46,734 cycles

RT FUSELGE SKIN INNER SKIN DOUBLER STA 1451 REPAIRED IAW ERA 491926-14.

Part: DOUBLER — DAMAGED (FUSELAGE) · airframe 60,179 hrs · 46,734 cycles

FUSELAGE LT INNER SKIN SPLICE DOUBLER STATION 1451 REPAIRED IAW ERA 491925-14.

Part: FUSE — BLOWN (BATTERY PACK) · airframe 59,929 hrs · 46,579 cycles

DURING LINE CHECK MAINTENANCE FOUND EMERGENCY LIGHTS FROM ROW 34 TO AFT OF AIRCRAFT INOPERATIVE. MAINTENANCE REPLACED THE FUSES IN THE AFT BATTERY PACK. OPERATION OF LIGHTS NOW CHECKS GOOD.

Part: LIGHT — INOPERATIVE (CABIN) · airframe 58,313 hrs · 45,486 cycles

MAINTENANCE FOUND THE EMERGENCY ESCAPE PATH LIGHT AT SEAT 18D TO BE INOPERATIVE. MAINTENANCE REPLACED THE EMERGENCY PATH LIGHT ASSEMBLY. AN OPERATIONAL CHECK WAS PERFORMED AND THE AIRCRAFT WAS RETURNED TO SERVICE (2010-DO844) (DLM88101914).

Part: WIRE HARNESS — DAMAGED (EMERGENCY LIGHTS) · airframe 57,433 hrs · 44,893 cycles

SEAT 11DE EMERGENCY PATH LIGHT INOPERATIVE. REPLACED 11DE WIRE HARNESS AND LIGHT RETURNED TO NORMAL OPERATION.

Part: COWL DOOR — DAMAGED (COWLING) · airframe 53,292 hrs · 42,199 cycles

REPAIR MARK UPPER COWL DOOR ASSEMBLY. LEFT SIDE REPAIRED IAW EA 09-056907-12 ME05.

Part: OIL COOLER — UNKNOWN (NR 1 ENGINE) · airframe 52,083 hrs · 41,453 cycles

NR 1 ENG GEN/CSD OIL TEMP RUNNING IN YELLOW BAND IN CLIMB AND UPON REACHING RED BAND AT TOP OF CLIMB DISCONNECTED CSD. APU GEN ALREADY ON MCO- DIVERTED TO IAD. REMOVED AND REPLACED LEFT CSD AND GENERATOR PER AMM 426246 ENGINE DISCONNECT AND RECONNECTED CSD LOADED A/C WITH ELECT REMOVED AND REPLACED LEFT ENG CSD OIL COOLER REF MM 71139.

Part: HYDRAULIC SYSTEM — UNKNOWN (LEFT) · airframe 51,111 hrs · 40,819 cycles

L HYD PRESS DROP TO ZERO QTY 19 FROM 12 BLED AIR FROM LT HYD RES TO CORRECT LEVEL RAN ALL HYD, OPERATED SYSTEMS. NO LEAKS OR PRESS DROPS QTY STAYED NORMAL CKS OK.

Part: PSEU — UNKNOWN (MLG) · airframe 47,997 hrs · 38,713 cycles

LANDING GEAR WARNING SOUNDED WITH GEAR DOWN AND LOCKED AND THREE GREEN. WARNING HORN COULD NOT BE SILENCED. REPLACED PSEU PER AMM AND CENTRAL AURAL WARNING COMPUTER AFT JACKING A/C AND FAILURE TO DUPLICATE. BOTH REQUIRE CHECKOUT RAN AUTO-SELF TEST OF PSEU PER AMM. CHECKS GOOD WITH NO FAULTS. C/W ADJ/TEST OF CENTRAL AURAL WARNING UNIT PER AMM. ALL MODES CHECK GOOD. SWUNG GEAR NUMEROUS TIMES AT VARIOUS L FLAP SETTINGS. UNABLE TO DUPLICATE LANDING GEAR WARNING INDICATION. SYSTEM CHECKS GOOD. OK FOR SVC.

Part: CUSP WEB — CORRODED (FUSELAGE) · corrosion level 2 · airframe 47,714 hrs · 38,523 cycles

CORROSION ON R-1 DOOR CUSP AT FS 200 FLOOR LEVEL. REMOVED AND REPLACED CUSP ANGLE PN 9910078U13 AND FABRICATED AND INSTALLED WEB REPAIR ANGLE 6.90 IN X 2.90 IN X 7.90 IN FROM 7075-0 .071 IN HEAT TREATED TO TPS-1003 AND 4.00 IN X 7.00 IN X 1.90 IN X 7.90 IN FROM 7075-0 .100 HEAT TREATED TO TPS-1003 AND ANGLE 1.15 IN X 1.60 IN X 8.20 IN FROM 2024-T3 .071 AND WEB REPAIR 14.5 IN X 9.7 IN FROM 7075-T6 .025 IAW DC-9/MD-80 SRM 53-05D FIG 55 AND 51-70-4 FIG 2.

Part: DOOR FRAME — CORRODED (FUSELAGE) · corrosion level 2 · airframe 47,714 hrs · 38,523 cycles

CORROSION R-1 DOOR JAMB LOWER AT FS 198 BELOW AFT CORNER PLATE. FABRICATED AND INSTALLED WEB REPAIR DOUBLER 15 IN X 21.6 IN FROM 7075-T6 .025 IAW DC-9/MD-80 SRM 51-10-3D AND 51-70-4 FIG 4.

Part: SKIN — CORRODED (ELEVATOR TAB) · corrosion level 2 · airframe 47,714 hrs · 38,523 cycles

CORROSION RT ELEVATOR ANTI-FLOAT TAB LOWER SURFACE. REPLACED TAB P/N 5930497-502 IAW DC-9/MD-80 SRM 55-01.

Part: DOUBLER — CORRODED (FUSELAGE) · corrosion level 2 · airframe 47,714 hrs · 38,523 cycles

CORROSION ON INNER SKIN DOUBLER FS 755 BETWEEN S-30 AND S-29L. CUT OUT CORRODED AREA. FABRICATED AND INSTALLED DOUBLER 60.0 IN X 10.5 IN FROM 7075-T6 .032 IAW MD-80 SRM 53-34-0 FIG 2, 51-30-5 AND 51-10-3D.

Part: SKIN — CRACKED (FUSELAGE) · airframe 47,714 hrs · 38,523 cycles

CRACK IN FUSELAGE SKIN FS 1380 S-13R. CUT OUT CRACK AREA. FABRICATED AND INSTALLED DOUBLER 7-3/4 IN X 12-1/4 IN FROM 2024-T3 .063 IAW MD-88 SRM 53-04D FIG 12B AND 51-10-2D.

Part: SKIN — CRACKED (FUSELAGE) · airframe 47,714 hrs · 38,523 cycles

INCOMING DISCREPANCY TEMPORARY REPAIR FOR CRACKS ON FUSELAGE SKIN FS 1380 S-13L. FABRICATED AND INSTALLED A PERMANENT REPAIR DOUBLER 12" BY 11.50" FROM 20240T3 .020 IAW DC-9/MD-80 SRM 53-04D FIG 12B.

Part: CUSP WEB — CORRODED (BS 1193-1212) · corrosion level 2 · airframe 47,714 hrs · 38,573 cycles

CORROSION ON RT CUSP WEB BETWEEN FS 1193 TO FS 1212. FABRICATED AND INSTALLED REPAIR DOUBLER 16.5" BY 13.2" 7075-T62 .025 IAW DC-9/MD-80 51-10-3D, 51-70-4 FIG 2, 51-30-1 AND 53-01 FIG 4.

Part: CUSP WEB — CRACKED (FUSELAGE) · corrosion level 2 · airframe 47,714 hrs · 38,523 cycles

CORROSION RT CUSP WEB BETWEEN 1232 TO 1250 AND CRACK AT LIGHTNING HOLE. BLENDED CORROSION, ROUTED OUT CRACK. HFEC IAW NDTSPM 06-01-01.001 TRIM OUT. FABRICATED AND INSTALLED REPAIR DOUBLER 3.10 IN X 4.55 IN IAW DC-9/MD-80 SRM 53-01 FIG 4 AND 51-10-3D.

Part: MEMBRANE — CORRODED (FUSELAGE) · corrosion level 2 · airframe 47,714 hrs · 38,523 cycles

CORROSION ON L2 DOOR SUB-FLOOR FS 1136 TO 1174. REMOVED CORROSION. FABRICATED AND INSTALLED REPAIR DOUBLER 8" BY 6" FROM 7075-T6 .071, FILLER AND SHIM IAW DC-9/MD-80 SRM 51-70-4, AND 53-30-5.

Part: CUSP WEB — CORRODED (BS 636-655) · corrosion level 2 · airframe 47,714 hrs · 38,523 cycles

CORROSION ON RT CUSP WEB FROM FS 636 TO FS 655 UPPER SIDE OF PAX CABIN. FABRICATED AND INSTALLED REPAIR DOUBLER 16" BY 13" FROM 7075-T6 .032 IAW DC-9/MD-80 51-10-3D AND 51-70-4 FIG 2.

Part: SKIN — CRACKED (FUSELAGE) · airframe 47,714 hrs · 38,523 cycles

CRACK INDICATIONS FWD SERVICE DOOR FWD UPPER CORNER FS 169.5, 4.5" BELOW L-11, FS 170, 5" BELOW L-11, FS 173, 2.5" BELOW L-11. CUT OUT CRACKED AREA OF FWD NR 1 DOOR SUPER CORNER IAW MD-80 SRM 51-10-1. FABRICATED AND INSTALLED REPAIR DOUBLER 24" X 19" FROM 2024-T3 .063, 21" X 15" FROM 2024-T3 .090 AND FILLER 5.1" BY 2.3" FROM 2024-T3 .050" IAW DC-9/MD-80 SRM 53-05D FIG 112, AND 51-10-3D.

Part: CUSP WEB — CORRODED (FUSELAGE) · corrosion level 2 · airframe 47,714 hrs · 38,523 cycles

CORROSION RT CUSP WEB FROM FS 965 TO 984 AROUND FASTENERS. FABRICATED AND INSTALLED REPAIR DOUBLER 12.5 X 3 INCHES FROM 7075-T6 .025 CLAD IAW MD-80 53-01 FIG 4, 51-10-3D, 51-30-5.

Part: CUSP WEB — CORRODED (BS 827-847) · corrosion level 2 · airframe 47,714 hrs · 38,523 cycles

CORROSION ON RT CUSP WEB FROM FS 827 TO FS 847 AROUND FASTENERS. FABRICATED AND INSTALLED REPAIR DOUBLER 12-7/8" BY 3-3/16" FROM 7075-T6 .032 IAW DC-9/MD-80 SRM 53-01 FIG 4 AND 51-10-3D.

Part: HOUSING — CORRODED (RUDDER) · corrosion level 2 · airframe 47,714 hrs · 38,523 cycles

CORROSION ON RUDDER CONTROL BEARING HOUSING. REMOVED AND REPLACED RUDDER BEARING HOUSING P/N 3913121 IAW DC-9/MD-80 SRM 51-30-05.

Part: CUSP WEB — CORRODED (BS 1250-1270) · corrosion level 2 · airframe 47,714 hrs · 38,523 cycles

CORROSION ON RT CUSP WEB FROM FS 1250 TO FS 1270 AROUND FASTENERS. INSTALLED REPAIR DOUBLER P/N D539201640 IAW DC-9/MD-80 SRM 53-01 FIG 4 AND 51-10-30.

Part: TAB — CORRODED (RT ELEVATOR) · corrosion level 2 · airframe 47,714 hrs · 38,573 cycles

CORROSION ON RT ELEVATOR ANTI-FLOAT TAB SKIN LOWER SURFACE. REPLACED RIGHT ELEVATOR ANTI-FLOAT TAB IAW DELTA AIRLINES MD-88 IPC 55-00-0013.

Part: SKIN — CRACKED (FUSELAGE) · airframe 47,714 hrs · 38,523 cycles

CRACK IN FUSELAGE SKIN FS 1437 S-2R. CUT OUT CRACK 2 IN X 2-1/2 IN. FABRICATED AND INSTALLED DOUBLER AND FILLER REPAIRS FROM 2024-T3 .071 AND 2024-T3 .063 IAW DC-9/MD-80 SRM 53-04D FIG 12B AND 51-10-2.

Part: SKIN — CRACKED (VERTICAL STAB) · airframe 47,714 hrs · 38,523 cycles

VERTICAL STAB LT SIDE HAS A CRACK IN L/E SKIN AT LT SIDE OF APU INLET, NEXT TO ACCESS COVER. STOP DRILLED CRACK IAW DC-9/MD-80 SRM 55-05 FIG 3. FABRICATED AND INSTALLED REPAIR DOUBLER 3-3/8" BY 3-1/2" FROM 2024-T3 .063 IAW DC-9/MD-80 SRM 51-10-3 AND 55-05 FIG 3.

Part: CUSP WEB — CORRODED (BS 598-620) · corrosion level 2

CORROSION ON RT CUSP WEB FROM FS 598 TO FS 620 IN PAX CABIN. REMOVED CORRODED AREA OF WEB FS 256. INSTALLED REPAIR DOUBLER P/N 53-1060-006 IAW DC-9/MD-80 51-30-2 AND 51-70-4.

Part: CUSP WEB — CORRODED (FUSELAGE) · corrosion level 2 · airframe 47,714 hrs · 38,523 cycles

CORROSION ON PAX CABIN LT CUSP WEB BETWEEN FS 636 TO FS 655. REMOVED CORROSION, FOUND EVIDENCE OF CRACK. TRIMMED OUT CRACK. FABRICATED AND INSTALLED REPAIR DOUBLER 4.6" BY 2" FROM 7075-T6 .032 IAW DC-9/MD-80 SRM 51-70-4 FIG 2, AND 51-10-3D.

Part: CUSP WEB — CORRODED (BS 256) · corrosion level 2

CORROSION ON RT CUSP WEB AT FS 256 AROUND CIRCUMFERENTIAL BOTTOM ATTACH AREA. REMOVED CORRODED AREA OF WEB FS 256. FABRICATED AND INSTALLED REPAIR DOUBLER 6.5" X 4.0" AND FILLER FROM CLAD 7075-T62 .020 AND .032 IAW DC-9/MD-80 51-10-3D, 51-70-4.

Part: LINE — FAILED (HYD SYSTEM) · airframe 45,179 hrs · 36,712 cycles

RIGHT HYDRAULIC PRESSURE WENT TO ZERO IN FLIGHT. QTY WENT TO 6, THEN 2, THEN 7. USED ALT GEAR EXTENSION. LANDED SAFELY. FOUND HYD PRESSURE LINE IN PYLON FAILED. REPLACED SAME.

Part: DOOR FRAME — CORRODED (C3 DOOR) · airframe 44,295 hrs · 36,085 cycles

CORROSION ON AFT LOWER WEB OF C3 CARGO BIN DOOR JAMB CLOSE TO STA Y= 1212 AEROMEXICO NRC T0024551. REPLACED WEB OF LOWER C3 CARGO BIN DOOR JAMB.

Part: BEAM — CORRODED (DOORWAY) · airframe 44,295 hrs · 36,085 cycles

CORROSION ON C2 CARGO BIN DOOR JAMB BEAM AEROMEXICO NRC T0024526. REPLACED CORRODED AREA OF C2 CARGO BIN DOOR JAMB BEAM.

Part: BEAM — CORRODED (CARGO DOORWAY) · airframe 44,288 hrs · 36,082 cycles

CORROSION ON C3 CARGO BIN DOOR JAMB BEAM NRC T0024527. REPLACED C3 CARGO BIN DOOR JAMB BEAM.

Part: FRAME — CRACKED (FUSELAGE) · airframe 44,288 hrs · 36,082 cycles

CRACK ON FORMER WEB AT X=0 OF AFT P-DOME FWD FACE STRUCTURE AEROMEXICO NRC T0024606. REPLACED FORMER WEB.

Part: BEAM — CRACKED (RT OVERWING) · airframe 44,288 hrs · 36,082 cycles

CRACK ON FWD ANGLE OF AFT RIGHT OVERWING EXIT DOOR BEAM NR 1 AEROMEXICO NRC T0024557. REPLACED FWD ANGLE OF RIGHT OVERWING EXIT DOOR BEAM NR 1.

Part: BEAM — CRACKED (L1 DOORWAY) · airframe 44,288 hrs · 36,082 cycles

CRACK ON AFT EDGE OF L1 DOOR BEAM NR 1 NRC T0024535. REPAIRED AFT EDGE OF L1 DOOR BEAM NR 1.

Part: RETAINER — CRACKED (WINDOW BELT) · airframe 44,288 hrs · 36,082 cycles

CRACK IN WINDOW BELT RETAINER BETWEEN STA Y= 886 AND Y=905 RT SIDE. REPAIRED WINDOW BELT RETAINER PER ERA 398163-14MA AEROMEXICO NRC T0024621.

Part: FITTING — CRACKED (FWD RT FUSELAGE) · airframe 44,288 hrs · 36,082 cycles

CRACK ON FWD AND AFT CLIP OF R1 DOOR BEAM NR 1. REPLACED CLIPS AEROMEXICO NRC T0024531. CRACK ON FWD EDGE OF R1 DOOR BEAM NR 1. REPLACED BEAM AEROMEXICO NRC T0024532. CRACK ON FWD EDGE OF R1 DOOR BEAM NR 4. REPLACED BEAM AEROMEXICO NRC T0024533. CRACK ON FWD FITTING OF R1 DOOR BEAM NR 1. REPLACED FITTING AEROMEXICO NRC T0024605.

Part: BEAM — CRACKED (L1 DOOR) · airframe 44,286 hrs · 36,081 cycles

CRACKED FWD EDGE OF BEAM NR 2 ON L1 DOOR AEROMEX NRC T0024035, CRACKED AFT EDGE OF BEAM NR 1 ON L1 DOOR AEROMEX NRC T0024034. REPAIRED FWD EDGE OF BEAM NR 2 IAW SRM 52-05D FIG 31. REPAIRED AFT EDGE OF BEAM NR 1 IAW SRM 52-05D FIG 31.

Part: CONNECTOR — BROKEN (CABIN) · airframe 43,591 hrs · 35,578 cycles

SEAT EMERGENCY LIGHT INOP AT 24D. REPAIRED BROKEN CONNECTOR AT SEAT TO SIDEWALL DISCONNECT.

Part: BATTERY PACK — DISCHARGED (CABIN) · airframe 43,546 hrs · 35,547 cycles

AFT EMERGENCY EXIT IDENTIFIER LIGHTS INOP. REPLACED BATTERY PACK, NOW CHECKS NORMAL.

Part: STRAINER — CLOGGED (NR 2 ENGINE) · airframe 40,997 hrs · 33,849 cycles

DURING DEPARTURE RT OIL STRAINER CLOGGED MSG CAME ON. FOLLOWED CHECK LIST RETARDED TO IDLE LIGHT REMAINED ON. CONTINUED TO OPERATE AT IDLE. .OIL TEMP REACHED 114 BEFORE THROTTLES WERE RETARDED TO IDLE. DURING TAXI IN EGT ON RT ENG WAS 423. COMPARED T0 330 ON LT ENG. REPLACED DELTA P SWITCH RAN ENG LK CKD GOOD OIL PRESS/TEMP GOOD AT ALL ENG SETTINGS. REPLACED OIL FILTER NO DEBRIS FOUND ON OIL FILTER OR MCD.OIL TEMP PLACARDS OK AS WELL AS EGT WITHIN LIMITS

Part: GENERATOR — MALFUNCTIONED (NR 1 ENGINE) · airframe 40,477 hrs · 33,465 cycles

AFTER TAKEOFF AT 1000 FT AGL LEFT ENG GENERATOR TRIPPED OFF AND GOT X-TIE LOCKOUT MESSAGE. RT ENG DID NOT PICK UP BUS. RESET LT GENERATOR AND REPOWERED BUS. APU WAS STARTED BUT NOT PUT ON LINE. LANDED WITH X-TIE LOCKOUT MESSAGE. RESET RELAY, SERVICED CSD, RAN ENGINE.

Part: ENGINE — MALFUNCTIONED (NR 2) · airframe 40,335 hrs · 33,351 cycles

THE ENG ABOUT 8 TO 10 SECA FOR WARM UP, ON T/O ROLL ENG WOULD NOT ACCELERATE PAST IDLE. GAVE THE ENG 6 SECS WITH THROTTLES UP TO RESPOND. ABORTED T/O ROLL AROUND 80 KT. RT ENG, NR 2. PERFORMED CHECK OUT OF RT ENG PER PFHB. OPS CHECK NORMAL. OK FOR SERVICE.

Part: DUCT — CRACKED (AFT AIR COND BAY) · airframe 40,293 hrs · 33,322 cycles

AFTER T/O AIRCRAFT WOULD NOT PRESSURIZE. BOTH PACKS WERE ON FLOW LIGHT ILLUMINATED. FOUND RT HOT AIR MANIFOLD DUCT CRACKED - REPLACED SAME

Part: SOCKET — BURNED (CABIN) · airframe 37,190 hrs · 31,060 cycles

STRONG ODOR, POSSIBLY ELECTRICAL IN AREA OF CABIN OVERWING. FOUND LOWER SIDEWALL LIGHT SOCKET BURNED AT ROW 25 RIGHT. REPLACE SAME.

Part: CONTROL PANEL — OVERHEATED (E/E BAY) · airframe 36,399 hrs · 30,469 cycles

RT A/C BUS OFF MSG PRIOR TO TAKEOFF WITH ACCOMPANYING AHRS 2 BASIC LIGHT. SLIGHT ODOR OF ELECTRICAL FUMES AFTER ATTEMPT AT POWER TRANSFER AT GATE. REPLACED AC BUS CONTROL PANEL.

Part: RECEPTACLE — BURNED (CABIN) · airframe 36,136 hrs · 30,263 cycles

FLT ATTN CALL LIGHT WILL NOT RESET AT AFT POSITION. FOUND CANNON PLUG AT SEAT ROW 16DE BURNT. REPLACED CANNON PLUG FLT ATTN CALL LIGHT, SYS OPS CKS GOOD.

Part: DUCT — CONTAMINATED (ANTI ICE SYSTEM) · airframe 35,640 hrs · 29,879 cycles

FUMES FROM WING ANTI-ICE SYSTEM SET OFF SMOKE DETECTORS IN BOTH AFT LAVS - COULD NOT DUPLICATE - PERFORMED DUCT BURNOUT AS PRECAUTION

Part: SMOKE DETECTOR — ACTIVATED (AFT LAVS) · airframe 35,455 hrs · 29,745 cycles

AFTER T/O, THERE WAS A DEICING FLUID ODOR AND HAZE IN THE CABIN. BOTH AFT LAVS AND FWD LAV SMOKE DETECTOR ACTIVATED. HAZE AND ODOR DISSIPATED AND DIDN''T RETURN. PERFORMED DUCT BURNOUT PROCEDURE.

Part: BATTERY PACK — DISCHARGED (CABIN) · airframe 34,947 hrs · 29,358 cycles

EMERGENCY ESCAPE PATH LIGHTING FROM ROW31AFT IS INOP. MAINT. RPLCD BATTERY CHARGER AFT OVRHD POSITION. ALL ESCAPE PATH LIGHTS CK GOOD.

Part: ENGINE — FLAMED OUT (NR 2) · airframe 34,696 hrs · 29,170 cycles

NR 2 ENG FLAMEOUT ON T/O OUT OF CVG. REPLACED ENGINE.

Part: ENGINE — FLAMED OUT (NR 2) · airframe 34,696 hrs · 29,170 cycles

RT ENGINE FLAMED OUT AT 12000 FT ON CLIMBOUT, ALL OTHER ENGINE INSTUMENTS NORMAL ALL FUEL PUMPS WERE OPERATING. REPLACED NR 2 ENG.

Part: BATTERY PACK — FAILED (CARGO BAY) · airframe 33,331 hrs · 28,185 cycles

OVERWING EVECUATION LIGHTS WOULD NOT ILLUMINATE. REPLACED THE BATTERY PACK, OPS CHECKS GOOD.

Part: FLOW VALVE — FAILED (LT A/C PACK) · airframe 33,165 hrs · 28,064 cycles

AT FL350 STARTED LOOSING CABIN PRESSURE. DID RAPID DESCENT TO 10K. IT APPEARS LEFT PACK LOST. REPLACED LEFT FLOW CONTROL VALVE.

Part: SENSOR — OUT OF ADJUST (ACCESS COMPT DR)

ACCESS COMPT DOOR LIGHT ILLUMINATED IMMEDIATELY AFTER T/O. AIRCRAFT WOULDN'T PRESSURIZE. VISUAL INSPECTION CONFIRMED COMPT DOOR PROPERLY CLOSED. PRESSURIZED A/C TO 6.25 PSI DIFF, OPS NORMAL. DOOR WARNING SYS DEFERRED, ADJUSTED PROX SENSOR.

Part: APU — LEAKING (AFT FUSELAGE)

DISPATCH ADV A/C RETURNING TO YUL WITH SMOKE IN CABIN. CAPT REPORTED BURNING ODOR ONLY. GIRLS IN AFT CABIN REPORTED LAV SMOKE DETECTOR GOING OFF AND BURING ODOR. CAPT REPORTED HE WAS CLIMBING THRU 3,000 FT AND CLOUD COVER TURNED ON WING ANTI-ICE WHEN THEY NOTICED THE ODOR. HE CLIMBED TO 10,000 FT AND ODOR WAS GONE BUT DECIDED TO RETURN TO YUL. DURING DESCENT GOING THRU CLOUD COVER AT 1,000 FT LEVEL TURNED ON ANTI-ICE AGAIN AND NOTICED BURNING SMELL. AFTER LANDING NO ODOR NOTICED. AIR CANADA MECHANIC FOUND APU OIL AT MIN AND COMPARTMENT SPRAYED WITH OIL. FTL CREW PLACARD APU INOP.

Part: INDICATOR — FAILDED (RT MLG)

RT MLG GREEN DOWN AND LOCK LIGHT INOP. VERIFIED GEAR DOWN AND LOCKED. RELAMPED GEAR INDICATOR. GEAR INDICATION CKS NML NOW.

Part: BATTERY — DISCHARGED (CABIN)

CABIN EMERGENCY FLASHLIGHT BESIDE AFT SINGLE JUMPSEAT APPERARS TO BE LOSING CHARGE. REPLACED BATTERY AND BULB OP CKS NORM.

Part: AIR DISTR — ODOR (CABIN)

FLIGHT ATT REPORTS STRONG ELEC SMELL JUST PRIOR TO LANDING. RAN BOTH ENG TO T/O PWR PER PFHB NO SMOKE OR SMELL COULD NOT LOCATE ANY EVIDENCE OF ELECTRICAL FIRE OK FOR SVC.

Part: PRESSURE REG — MALFUNCTIONED (RIGHT)

ON FINAL APPROACH, GOT SMOKE AND HOT AIR SMELL IN CABIN. BOTH ENGINES AND AIRFOIL ANTI ICE WERE ON . AIR CONDITIONING INDICATIONS WERE NORMAL. C/A: PERFORMED AUG VALVE CHECK PER PFHB. AUG FAILED TEST. REPLACED. THERMOSTAT/ANCPTR/PILOT PRESS REGULATORS, NO HELP. FOUND AUG VALVE MODEL TG, REPLACED SAME. FOUND LEFT PACK PRESSURE REGULATOR BAD. REPLACED BOTH WATER SEPARATOR BAGS, PRECAUTIONARY.

Part: PUMP — FAILED (LT MLG WW)

AFTER T/O, SMOKE IN CABIN AND COCKPIT WITH SMOKE ALARMS ON FURTHER INSP FOUND HYD TRANSFER PUMP CASE DRAIN LINE HAD FILLED ITS OVERFLOW CONTAINER. WHICH IN TURN HAD BEEN RUNNING INTO THE APU INTAKE. REPLACED HYD TRANSFER PUMP, DUMPED AND CLEANED DRAIN CAN. APU WILL HAVE TO BE CLEANED TO PREVENT FURTHER CONTAMINATION OF AIR CONDITIONER SYSTEMS.