N767NC

Part: SUPPORT FITTING — DAMAGED · airframe 81,968 hrs · 81,233 cycles

COMPLY WITH ERA 510021-14AD, REV ORIG REF AMDS CARDS 5740-01114-01A AND -01B. COMPLIED WITH ERA 510021-14AD, REV ORIG ON RT AND LT MLG RETRACT CYLINDER SUPPORT FITTING BORES.

Part: SKIN — CRACKED (FUSELAGE) · airframe 81,794 hrs · 81,049 cycles

FOUND ONE CRACK .281" LONG NOTED AT FWD CARGO DOOR FRAME FWD LOWER CORNER FUSELAGE SKIN. REPAIRED IAW DWG SR09530117 AND RESTORED ACCESS IAW AMM 25-52-01-201, PAGE 3. ACCOMPLISHED PERMANENT REPAIR IAW DWG SR09530117.

Part: SKIN — CORRODED (FUSELAGE) · airframe 81,794 hrs · 81,049 cycles

AFT CARGO DOOR JAMB LOWER CENTER OF OPENING APPROX FS 1088 ACFT SKIN BULGING AND CORROSION FALLS FROM SET SCREW HOLE AND SKIN IS TAPPED (064-15) AD RELATED. R & R LOWER PAN SECTION ON AFT CARGO DOORJAMB LOWER AREA IAW SRM 53-05, FIG 44. R & R SEAL DEPRESOR AFT CARGO DOORJAMB IAW SRM 53-05, FIG 44.

Part: SKIN — CRACKED (FUSELAGE) · airframe 81,794 hrs · 81,049 cycles

DURING L-CHECK, AT THE FWD CARGO DOOR JAMB AFT EDGE, THE SEAL DEPRESSOR AND FUSELAGE SKIN WERE FOUND CRACKED. WORK IAW ER/A 508945-14 AS FOLLOWS: SECTION II - WITHIN EVERY 8,000 CYCLES AFTER SECTION I ASSOCIATED ER/A 13-508945 ADDED. ACCOMPLISHED PERMENANT REPAIR ON FWD CARGO DOOR CUT-OUT AFT IAW ER/A 508945-14 REV ORIGINAL. INSTALLED ID TAG IAW PS 900-5-1 NR 4.

Part: TEE FITTING — CRACKED (BS 1100) · airframe 81,794 hrs · 81,049 cycles

AFT CARGO DOOR INTERCOSTAL TEE FITTING ABOVE DOOR CUTOUT IS CRACKED AT BS 1100 L18R. R & R TEE FITTING AT AFT CARGO DOOR INTERCOSTAL ABOVE DOOR CUT-OUT IAW SRM 51-30-5 AND DC-9-A-20-16-00-401-926A.

Part: BATTERY PACK — INOPERATIVE (EMERGENCY LIGHT) · airframe 80,983 hrs · 80,136 cycles

DURING LINE CHECK, MAINTENANCE FOUND THE FIRST THREE EMERGENCY OVERHEAD LIGHTS TO BE INOPERATIVE. MAINTENANCE REPLACED THE BATTERY PACK AND THE LIGHTS RETURNED TO AN OPERATIONAL CONDITION.

Part: BATTERY PACK — DISCHARGED (CABIN) · airframe 2,880 hrs · 2,561 cycles

DURING LINE CHECK, FOUND EMERGENCY EGRESS AISLE LIGHTING INOP, ROWS 5 THROUGH 9. REPLACED BATTERY PACK AT ROW 7 POWER SUPPLY.

Part: CHANNEL — CRACKED (FUSELAGE) · airframe 79,698 hrs · 78,806 cycles

CRACKED J CHANNEL ON APB - CRACKED. PERFORMING INSP OF APB LOWER T SECTION PER 5310-01203-01, FOUND J CHANNEL STIFFENER CRACKED AT STA 25L ON APB JUST ABOVE T ATTACH LOCATION. CAN BE SEEN THRU ACCESS HOLE. REMOVED CRACKED J FRAME. DRILLED NEW J, INST J PER BOEING SRM 51-30 INST 6EA 3/16 HI-LOCS AND BOLTS FOR CABLE FEED THRU ON BULKHEAD. REMOF873942. INSP REPAIR OK TO CLOSE QC2048. CLOSED AFT CARGO COMPARTMENT AFT WALL.

Part: CONNECTOR — DISCONNECTED (CABIN) · airframe 2,290 hrs · 1,984 cycles

DURING SERVICE CHECK, MAINTENANCE FOUND EMERGENCY ESCAPE PATH LIGHTING INOPERATIVE AT ROW 14, RIGHT SIDE. MAINTENANCE RECONNECTED WIRE CONNECTOR AT ROW 14, RIGHT SIDE. OPERATIONAL CHECK WAS GOOD. AIRCRAFT OK FOR SERVICE.

Part: SKIN — DENTED (FUSELAGE) · airframe 79,161 hrs · 78,310 cycles

DURING MAINTENANCE VISIT AT STA-SA, A DENT WAS FOUND ON THE FUSELAGE SKIN AT STA 144 BETWEEN L18L AND L19L. THE DENT WAS SUBSEQUENTLY REPAIRED PER ER/A 491556-14 SECTION I. PERFORM SECTION II INSPECTION PER ER/A 491556-14 AS FOLLOWS: INITIAL INSPECTION - WITHIN 8,000 CYCLES REPEAT INSPECTION - EVERY 8,000 CYCLES.

Part: INTERCOSTAL — WORN (BS 617) · airframe 79,161 hrs · 78,310 cycles

MAIN CABIN AT STA 617 LT SIDE, UPPER SURFACE OF INTERCOSTAL IS WORN IN SEVERAL SPOTS, AT FLOOR SUPPORT. 60-005. REMOVED 2" ANGLE AND INTERCOSTAL AT STA 617 LT SIDE IAW SRM 51-30-2 PG 1 INSTALLED REPLACEMENT INTERCOSTAL "L" ANGLE AND ATTACHED "Z" ANGLE TO FLOOR STRUCTURE MAIN CABIN IAW SRM 51-30-2 PG1 OUT OF SEQUENCE ORIGINAL MAT THICKNESS IS 0.063. MAT LOSS IS 0-028". FABRICATED NEW L-ANGLE, PN 1276248 IAW DWG NO PL5910760 AND SRM 51-10-4 PG1. ALODINED AND PRIMED NEW ANGLE IAW SRM 51-10-3, PARA 14 & 21, COMPLETED.

Part: FLOORBEAM — WORN (BS 636) · airframe 79,161 hrs · 78,310 cycles

MAIN CABIN AT STA 636 LT SIDE, UPPER SURFACE OF FLOORBEAM IS WORN IN SEVERAL SPOTS, AT FLOOR LEVEL 60-003. BLENDED OUT DAMAGE MAIN CABIN AT STA 636 LT SIDE LBL 14 IAW SRM 51-10-3 MATERIAL THICKNESS FOUND TO BE OUT OF LIMITS IAW SRM 53-01, FIG 1 (PG8). FABRICATED REPAIR ANGLE (1EA) WEAR STRIP (1EA) AND SHIM (1EA) IAW SRM 53-05 (PG 100). INSTALLED (1EA) ANGLE REPAIR (1EA) SHIM, (1EA) WEAR STRIP ATSTA 636 LT SIDE LBL 14 IAW SRM 53-05 (PG100) AND SRM 51-30 (PG 12), COMPLETED, INSPECTED.

Part: SKIN — CORRODED (FLOOR PANEL) · airframe 79,161 hrs · 78,310 cycles

CABIN FLOOR PANEL 33D, FWD END UPPER SKIN SCREW HOLES ARE CORRODED, PULLED THRU AND WORN. REMOVED FLOOR PANEL FROM MAIN CABIN IAW MM DC9-A-53-20-01-201-925A-A, REMOVED CORROSION FROM SCREW HOLES AT OTBD SIDE OUT OF LIMITS IAW SRM 51-10-3, PAGE 46, SRM 53-01, FIG 1, SHT 3, FABRICATED, LOCATED AND DRILLED. TREATED AND PRIMED AND INST NEW PANEL IAW SRM 51-10-4, PARA 2, SRM 51-30-2, PG 2, SRM 51-10-3, PARA 14-21.

Part: SKIN — DAMAGED (FLOOR PANEL) · airframe 79,161 hrs · 78,310 cycles

CABIN FLOOR PANEL 9D HAS PUNCTURE IN TOP SKIN. R & R PANEL 91D FLOOR CABIN AREA IAW SRM 53-05, FIG 2, PG 9 AND 11. NDT FOUND NO CRACKS AT REPAIR AREA IAW NDT SPM 06-10-01-001. FABRICATED REPAIR FILLER AND DOUBLER IAW SRM 51-10-3, PG 31, 32, 40, 41. INSTALLED FILLER AND DOUBLER ON CABIN FLOOR PANEL 91D IAW SRM 53-05, PG 10-11, FIG 2. COMPLETED INSP.

Part: FLOOR SKIN — CORRODED (BS 188-200) · airframe 79,161 hrs · 78,310 cycles

METAL SUB FLOOR AND EXISTING REPAIR HAS CORROSION STA 188 TO 200 BETWEEN BL-0 AND LBL 22. FABRICATED DOUBLER REPAIR IAW SRM 51-70-4, FIG 2. PG 5 & 9. TREATED & PRIMED IAW SRM 51-10-3, PG 31, PAR 14 & PG 40, PARA 21. INSTALLED 1EA INTERCOSTAL, 2EA T SUPPORT, 1EA SUPPORT FLOOR. 1EA HAT SUPPORT, 1EA DOUBLER REPAIR STA 188 TO 200 BETWEEN BL0 & LBL 22 IAW SRM 51-70-4, FIG 2, PG 1 & 4.

Part: SKIN — DENTED (FLOOR PANEL) · airframe 79,161 hrs · 78,310 cycles

CABIN FLOOR PANEL 85D HAS SHARP DENTS AND SCREWS PULLED THRU TOP SKIN. REPAIRED PUNCTURE AND CRACKED HAT CHANNELS IAW SRM 53-01, P7, FIG 1. OUT OF LIMITS IAW SRM 51-50-1, PG 1-2, ENDS OF HAT CHANNELS IAW SRM 51-10-2. NDT CHECK FOUND IAW NDT SPM 06-10-01.001. TREATED AND PRIMED AREA IAW SRM 51-10-3, PG 31, 32, 40, 41. DRILLED OUT PUNCTURE IAW SRM 51-10-4, PG 1. FILLED HOLE IN FLOOR PANEL WITH RIVET IAW SRM 53-01, PG7.

Part: SKIN — CORRODED (FLOOR PANEL) · airframe 79,161 hrs · 78,310 cycles

CABIN FLOOR PANEL 32D FWD END IS BENT UP, 1EA RIVET IS HAS CORROSION AROUND SCREW HOLES ON TOP SKIN. REMOVED CABIN FLOOR PANEL. REMOVED CRACKED SECTION AND REPAIRED CABIN FLOOR PANEL IAW 53-05, FIG 1, PG10. TREATED AND PRIMED BARE AREAS IAW SRM 51-10-3, ITEM 21, PG 40-42. INSTALLED CABIN PANEL 32D AT STA 312 IAW SRM 51-30-1, PG 1-4.

Part: FLOOR SUPPORT — CORRODED (BS 160-295) · airframe 79,161 hrs · 78,310 cycles

CABIN FLOOR SUPPORT ANGLE, STA 160 TO 295, BL-0 HAS CORROSION. REMOVED CORROSION IAW SRM 51-10-3, PAGE 46, PAR 26, OUT OF LIMITS IAW SRM 53-01, PG 8, REMOVED CABIN FLOOR SUPPORT ANGLE IAW SRM 51-30-5PG. FABRICATED CABIN FLOOR SUPPORT ANGLE IAW SRM 53-13-1. TREATED AND PRIMED IAW SRM 51-10-3, SRM 51-10-3. INSTALLED CABIN FLOOR SUPPORT ANGLE AT STA 160 TO STA 295 BL-0 IAW SRM 51-30-5, SRM 53-13-1.

Part: SKIN — DAMAGED (BS 390 L28-29R) · airframe 79,161 hrs · 78,310 cycles

LOWER FUSELAGE STA Y390, BETWEEN LONGERON 28RT AND LONGERON 29R SKIN WITH DENT. COLD FORMER SKIN BACK TO ORIGINAL CONTOUR AT LOWER FUSELAGE FABED AND INST INTERNAL REPAIR DOUBLER IAW SRM 53-04, FIG 38 VIEW G NDT CHECK NO CRACKS IAW NDT SPM 06-10-01.001 MEASURED SKIN DENT D=.60", X=.016". FOUND TO BE WITHIN LIMITS IAW SRM 53-04, FIG 38 COND 1B OUT OF LIMITS DUE TO PROXIMITY OF FRAME IAW SRM 53-04, FIG 38 COND 1A.

Part: SEAT TRACK — CORRODED (BS 200-280) · airframe 79,161 hrs · 78,310 cycles

SEAT TRACK STA 200 TO 280, RBL 22 HAS CORROSION. REMOVED CORROSION IAW SRM 51-10-3 ORIGINAL MATERIAL THICKNESS IS .090" MAT LOSS RANGE FROM .040"-.060" IN SEVERAL AREAS, OUT OF LIMITS. REMOVED SEAT TRACK IAW SRM 51-30-5 FABED SEAT TRACK FROM PN 09-5300-3-1513 BATCH 0000879227 IAW SRM 53-05, PG 19, INSTALLED SEAT TRACK IAW SRM 51-30-1.

Part: SKIN — DAMAGED (FLOOR PANEL) · airframe 79,161 hrs · 78,310 cycles

CABIN FLOOR PANEL 840 HAS SHARP DENT AND PULLED SCREW THRU TOP SKIN. INSTALLED REPAIR WASHERS PANEL DAMAGED SCREW HOLE IAW SRM 51-30-1 PAGE 5. OTHER DAMAGE ON FLOOR PANEL, OUT OF LIMITS IAW SRM 53-04 FIG38. CUT OUT DAMAGE IAW SRM 53-05 PG 10 FIG 1, FABRICATED FILLER AND DOUBLER IAW SRM 53-05 PG10 FIG 1, TREATED AND PRIMED FILLER AND DOUBLER IAW SRM 51-10-3, PAGE 31-32, SHT 40, INSTALLED FILLER AND DOUBLER IAW SRM 53-05.

Part: BRACKET — CRACKED (SERVICE DOORWAY) · airframe 79,161 hrs · 78,310 cycles

FWD SERVICE DOOR BEAM NR2 AT AFT FRAME BRACKET CRACKED. VERIFIED CRACK ON BRACKET IAW NDT SPM 06-10-01.001. R & R BRACKET AT FWD SERVICE DOOR BEAM NR2 AT AFT FRAME IAW SRM 51-30-5, PARA 7B, SRM 51-30-2, PARA 8, SRM 51-30-7, PARA 6. COMPLETED AND INSPECTED.

Part: FLOORBEAM — CORRODED (BS 200 BL0-20) · airframe 79,161 hrs · 78,310 cycles

CABIN FLOORBEAM ANGLE STA 200 BL-0 TO RBL 20 HAS CORROSION. REMOVED CORROSION IAW SRM 51-10-3, PG 46, OUT OF LIMITS IAW SRM 53-01, PG 8, FIG 1, SHT3. REMOVED CABIN FLOOR SUPPORT ANGLE IAW SRM 51-30-5, PG 29, 30, ITEM 8, FIG 16. FABRICATED CABIN FLOOR SUPPORT ANGLE IAW SRM 53-13-1. TREATED & PRIMED CABIN FLOORBEAM ANGLE IAW SRM 51-10-3 AND SRM 51-10-3. INSTALLED CABIN FLOORBEAM ANGLE IAW SRM 51-30-5.

Part: FLOORBEAM — CORRODED (BS 160) · airframe 81,794 hrs · 81,049 cycles

FLOORBEAM BS 160 BETWEEN BL-0 AND LBL 22 HAS CORROSION. REMOVED CORROSION CABIN FLOORBEAM. REMOVED FLOORBEAM IAW SRM 51-30-5PG 29. FABRICATED FLOORBEAM. INSTALLED NEW FLOORBEAM IAW SRM 51-30-5 PG 12.

Part: ANGLE — CORRODED (FUSELAGE) · airframe 79,161 hrs · 78,310 cycles

FWD CARGO DOOR CUTOUT FWD FRAME L-ANGLE BELOW LOWEST STOP FITTING IS CORRODED. REMOVED CORROSION IAW SRM 51-10-3 PARA 26 FOUND TO BE OUT OF LIMITS IAW SRM 53-01, FABBED REPAIR ANGLES WITH SHT 2024-T3 .040" BATCH 0001900675, INSTALLED REPAIR ANGLES (2) -19,-21 IAW SRM 51-30-5 PARA 7B.

Part: CHANNEL — DAMAGED (FLOOR PANEL) · airframe 79,161 hrs · 78,310 cycles

PASSENGER CABIN FLOORBOARD 60-B-50 HAT CHANNEL HAS DAMAGE. ENDS OF ALL 5 HAT CHANNELS DAMAGED & SEVERAL CRACKS IN WEB PART OF PANEL. OUT OF LIMITS PER DC9 SRM 53-05. FABBED FLOOR PANEL ASSY REF DC9 SRM 53-23-0 PG 7 FIG 4 & DWG 9923613, TREATED HAT CHANNELS & WEB PNL REF DC9 SRM 51-10-3 PG 40-42, PRIMED HAT CHANNELS AND WEB PNL REF DC9 SRM 51-10-3 PG 31-32, ASSEMBLED FLOOR REF DWG 9913613 AND SRM 51-30-2 PG 1-14.

Part: SKIN — DENTED (FUSELAGE) · airframe 79,161 hrs · 78,310 cycles

LOWER FUSELAGE STA Y1104, BETWEEN LONG 28R AND LONG 30 SKIN WITH DENT. COLD FORMED SKIN BACK TO ORIGINAL CONTOUR IAW SRM 53-04 FIG 38, HFEC SURFACE INSP PER NDTSPM 06-10-01.001, NO CRACKS, FABBED INTERNAL REPAIR DOUBLER 2EA FROM 2024-T3 0.032" IAW SRM 53-33-0 PG 13 FIG 3 & 53-04, TREATED AND PRIMED IAW SRM 51-10-3 PG 31 PER 14 & PG 40 PAR 21, INSTALLED REPAIR DOUBLER IAW SRM 53-04 FIG 38 PAGE 218Z.

Part: FLOOR PANEL — CRACKED (CABIN) · airframe 79,161 hrs · 78,310 cycles

CABIN FLOOR PNL 95D HAS CRACK AND DENT IN TOP SKIN. FABBED FLOOR PANEL 95D USING MATERIAL SHT 7075-T6 .025" BATCH 0001520995 IAW DC9 SRM 53-23-0 PG 9 AND SRM 51-10-4 PG 1, TREATED AND PRIMED IAW DC9 SRM 51-10-3 PG 40-42 AND SRM 51-10-3 PG 31-32, INSTALLED TOP SKIN IAW DC9 SRM 51-10-4 PG 1-12.

Part: SKIN — DENTED (FUSELAGE) · airframe 79,161 hrs · 78,310 cycles

LOWER FUSELAGE STA Y390 BETWEEN LONGERON 29R AND 30, EXTERNAL SKIN WITH DENT. COLD FORMED SKIN BACK TO ORIGINAL CONTOUR AT LOWER FUSELAGE STA 390 BETWEEN LONG 29R AND 30, FABBED AND INSTALLED INTERNAL REPAIR DOUBLER IAW SRM 53-04 FIG 38 VIEW G AND NDT CHECKED NO CRACKS NOTED PER NDTSPM 06-10-01.001, MATERIAL USED FOR REPAIR DOUBLER IS .032" 2024-T3 BATCH 0001500932.

Part: FLOORBOARD — CORRODED (CABIN) · airframe 79,161 hrs · 78,310 cycles

PASSENGER CABIN FLOORBOARD 79-50 HAS CORROSION. REMOVED CORROSION IAW SRM 51-10-3 P 46 STEP 26, FOUND TO BE OUT OF LIMITS PER SRM 53-05 PAGE 12, FABRICATED NEW PANEL 79-50 SHEET 7075T6-0.25" BATCH 0001520995 IAW SRM 51-23-0 AND 51-10-4, TREATED AND PRIMED, FABRICATED PANEL IAW SRM 51-10-3 PG 31-40-41.

Part: SUPPORT — CORRODED (FUSELAGE) · airframe 79,161 hrs · 78,310 cycles

PASSENGER CABIN FWD GALLEY DRAIN PAN SUPPORT STRUCTURE IS CORRODED. OUT OF LIMIT IAW DC9 SRM 51-10-3, CUT OUT DAMAGE AREA OF FLOOR WEB STA 160 RBL 52 IAW SRM 51-70-4. FABRICATED REPAIR DOUBLER IAW SRM 51-70-4, 51-10-3, INST REPAIR DOUBLER IAW SRM 51-70-4, FABRICATED OTBD SUPPORT STRUCTURE FLOOR, IAW SRM 53-13-1 AND SRM 51-10-3. INST SUPPORTS IAW SRM 51-30-1. INSTL DRAIN PAN IAW SRM 51-30-1.

Part: FLOORBOARD — CORRODED (CABIN) · airframe 79,161 hrs · 78,310 cycles

PASSENGER CABIN FLOORBOARD NR 21 HAS CORROSION AND IS CRACKED. REMOVED AND REPLACED PASSENGER CABIN FLOORBOARD PANEL 21, (SKIN WEB PANEL REPLACED) IAW DC9 SRM 53-20-0 PAGE 4H AND SRM 53 -05 PAGE 10.

Part: FLOOR PANEL — DAMAGED (FUSELAGE) · airframe 79,161 hrs · 78,310 cycles

FLOOR PANEL 49D HAS CRACK AT RIVET AND SCREWS ARE PULLED THRU TOP SKIN. REMOVED FLOOR PANEL 49D IAW DC-9 SRM 51-30-1, REMOVED CORR ON SCREW HOLES IAW SRM 51-10-3 PG 26-46, REMOVED HAT CHANNELS FOR REPAIR IAW SRM 51-30-2 AND SRM 53-05 PG 10, NDT INSP NO CRACKS FABBED FAIRING AND REPAIR DOUBLER IAW DC9 SRM 51-30-2 PAGE 30-31. INSTALLED FILLER AND DOUBLER IAW DC9 SRM 51-30-2 PAGE 25. INSTALLED FLOOR PANEL 49D IAW SRM 51-30-1 PAGES 1-8.

Part: FLOOR SUPPORT — CRACKED (STA 200 LBL 25) · airframe 79,161 hrs · 78,310 cycles

CABIN FLOOR SUPPORT ANGLE FOUND TO BE CRACKED AT STA 200, LBL 25. REMOVED IAW SRM 51-30-5, PG 1-3, FIG 1, MAT. ID 2652479 EXTRUSION, IAW SRM 53-13-1, PG 25, 26, FIG 11, LOCATED AND DRILLED EXTRUSION IAW SRM 51-10-4, PG 1, PARA 2. TREATED AND PRIMED IAW 51-10-3, PARA 14, 21, AND INST AW SRM 51-30-5, PARA 7, STA 200, LBL 25.

Part: FLOOR PANEL — DENTED (CABIN) · airframe 79,161 hrs · 78,310 cycles

CABIN FLOOR PNL 96D HAS SEVERAL SHARP DENTS IN TOP SKIN. REMOVED HAT CHANNELS FROM CABIN FLOOR PANEL, TOP SKIN BS 1003 TO 1068 IAW SRM 51-30-2 PAG 24-26. RECEIVED NEW TOP SKIN 66" X 21" 7075-T6 PER SRM 53-23-0 FIG 6 PNL TYPE C. FABBED NEW SKIN PER DWG 5930352 AND 9919601, TREATED AND PRIMED IAW SRM 51-10-3 PG 31-32, PG 24-26.

Part: FLOOR SUPPORT — CORRODED (FUSELAGE) · airframe 79,161 hrs · 78,310 cycles

CABIN FLOOR SUPPORT ANGLE STA 200 BETWEEN RBL-24 AND RBL-44 HAS CORROSION. BLENDED CORROSION PER DC9 SRM 51-10-3 PG 46, MATERIAL ORIGINAL .070", MATERIAL LOST .015" FOUND TO BE OUT OF LIMITS PER SRM 51-30-5 PG 29, FABBED & DRILLED SUPPORT ANGLE P/N 5265247 9, TREATED AND PRIMED PER SRM 51-10-3 PG 40 & PG 31 PAR 14. INSTALLED SUPPORT ANGLE PER DC9 SRM 51-30-5.

Part: FLOOR PANEL — DENTED (CABIN) · airframe 79,161 hrs · 78,310 cycles

CABIN FLOOR PNL 50D HAS SCREWS PULLED THRU AND DENT. REMOVED MAIN CABIN FLOOR PNL 50D PER DC9 SRM 51-30-6 PARG 5, CUT OUT DAMAGE PER DC9 53-05 PG 9-12 FABBED DOUBLER AND FILLER USING MAT. 7075-T6 .032" BATCH 0001691306 AND 7075-T6 .025" BATCH 0001570995 SRM 53-05 FIG 1 PG 10. INSTALLED DOUBLER AND FILLER PER DC9 SRM 51-30-2 PAGE 24-28, AND INSTALLED REPAIR WASHER ON FLOOR PANEL. INSTALLED MAIN CABIN FLOOR PANEL 50D PER DC-9 51-30-6 PAGE 5.

Part: FLOOR SUPPORT — CORRODED (FUSELAGE) · airframe 79,161 hrs · 78,310 cycles

CABIN FLOOR SUPPORT STA 160 TO 200, RBL-44 HAS CORROSION. REMOVED CORROSION IAW SRM 51-10-3 PG 46, FOUND TO BE OUT OF LIMITS IAW SRM 53-01 PG 8 FIG 1, REMOVED CABIN FLOOR SUPPORT STA 160 TO 200 RBL-44 IAW SRM 51-30-5 PG 29-30. FABBED CABIN FLOOR SUPPORT IAW SRM 53-13-1 PG 26 FIG 11 SHT 2. TREATED AND PRIMED CABIN FLOOR SUPPORT IAW DC9 SRM 51-10-3, INSTALLED IAW DC9 SRM 51-30-5 PG 12 PAR 7.

Part: FLOORBOARD — CRACKED (CABIN) · airframe 79,161 hrs · 78,310 cycles

PASSENGER CABIN FLOORBOARD 103-50 CORNER IS CRACKED REMOVED DAMAGE IAW SRM 53-05 PG 9-10, FABRICATED REPAIR DOUBLER AND FILLER IAW SRM 53-05. TREATED AND PRIMED DOUBLER AND FILLER INSTALLED REPAIR DOUBLER AND FILLER ON PASS CABIN FLOORBOARD 103-50 IAW SRM 53-05 PG 9-10. NDT INSP NO CRACKS NOTED.

Part: SKIN — DENTED (FUSELAGE) · airframe 79,161 hrs · 78,310 cycles

LOWER FUSELAGE STA Y370, BETWEEN LONG 29R AND LONG 30, EXTERIOR SKIN WITH DENT. MEASURED SKIN OUT OF LIMITS IAW SRM 53-04 FIG 38 PAGE 217. COLD FORMER SKIN BACK TO ORIGINAL CONTOUR AT DENTED AREA IAW SRM 53-04 FIG 38. HFEC SURFACE INSP PER NDT SPM 06-10-01.001 NO CRACKS NOTED. FABBED, TREATED, PRIMED & INSTALLED REPAIR DOUBLER IAW DC9 SRM 53-04 FIG 38 VIEW V PAGES 218. INSTALLED REPAIR ID TAG ON REPAIR AREA IAW PS 900-5-1 NO 04.

Part: DOUBLER — CRACKED (FUSELAGE) · airframe 79,161 hrs · 78,310 cycles

BETWEEN LONGERONS 15R & 16R AT STA 1117 BRACKET-DOUBLER IS CRACKED. REMOVED BRACKET-DOUBLER DAMAGE AND FASTENERS ON STA 1117 BETWEEN LONGERON 15R AND 16R IAW SRM 53-03 PAGE 1. FABBED REPAIR PARTS 1 DOUBLER, 2EA SPLICE WITH SHEET 2014-T6 .050" BATCH 0001654113 IAW SRM 53-13-3 FIG 1 PG 5 INSTALLED REPAIR PARTS DOUBLER AND SPLICES IAW DC-9 SRM 53-03 PAGE 2 FIG 44 AT STA 1117 BETWEEN LONGERONS 15R AND 16R.

Part: SKIN — DENTED (FUSELAGE) · airframe 79,161 hrs · 78,310 cycles

LOWER FUSELAGE BS Y343 BETWEEN LONG 18R AND 19R EXTERNAL SKIN WITH DENT. REMOVED DAMAGED AREA AT LOWER FUSELAGE STA Y343 BETWEEN LONG 18R AND 19R, DIAMETER CUT OUT .550", FABRICATED AND INSTALLED INTERNAL REPAIR FINGER DOUBLER AND EXTERNAL REPAIR DOUBLER, INTERNAL REPAIR DOUBLER, FILLER ANDSKIN PLUG IAW DC9 SRM 53-04 FIG 38 VIEW V AND SRM 51-30-5. INSTALLED ID TAG.

Part: SKIN — CRACKED (FUSELAGE) · airframe 79,161 hrs · 78,310 cycles

CRACKED SKIN AT FS 1123 BETWEEN STRINGERS 14, 15R. HFEC SURFACE INSPECTED IAW DC9 NDTSPM 06-10-01.001, VERIFIED CRACK MARKED ENDS APPROX 1.5" LONG, CUT OUT SKIN 1.5" LONG FABRICATED DOUBLER, FILLERS REPAIR, MAT'L DMS 1592, .032, TREATED, PRIMED, INSTALLED IAW SRM 53-04, FIG 46, PG 281-279, AND SRM 51-10-3, PG 31.

Part: SKIN — DAMAGED (BS 229-211) · airframe 79,161 hrs · 78,310 cycles

FUSELAGE SKIN, EXTERNAL DOUBLER REPAIR AT STA 229 TO STA 211, L18L AND L20L FOUND TO BE WITHIN PROXIMITY DISTANCE TO ADJACENT EXT DOUBLER REPAIR, REMOVED EXISTING REPAIR IAW SRM 51-30-8, PG 4, STEP 13. FABED DOUBLER, FILLER, INTERNAL FINGER DOUBLERS IAW SRM 53-04. REPAIR DOUBLER, FILLER, AND INTERNAL FINGER DOUBLERS IAW SRM 53-04, PERFORMED OPS CHECK, NO LEAK NOTED IAW DC9-A-21-20-00 -501-927A-A, PG 1+2.

Part: SKIN — DAMAGED (BS 1108 L5R) · airframe 79,161 hrs · 78,310 cycles

WEAR ON EXTERNAL DOUBLER REPAIR AT FUSELAGE SKIN BS 1108, L5R. REMOVED EXISTING EXTERNAL DOUBLER IAW SRM 51-30-2, PG 1EA. REPAIR DOUBLER, SRM 53-04, FIG 3A AND SRM 51-10-4, PARA 2. TRIMMED OUT PYLON L/E INBD EDGE IAW SRM 53-04, FIG 3A, AND SRM 54-02. TREATED AND PRIMED 1 EA REPAIR DOUBLER IAW SRM 53-04, FIG 3A INSTALLED 1 EA REPAIR DOUBLER IAW SRM 53-04, FIG 3A AND SRM 51-30-2, FIG 2.

Part: SKIN — DENTED (BS 222-249) · airframe 79,161 hrs · 78,310 cycles

DENT ON FUSELAGE SKIN EXTERNAL DOUBLER REPAIR BS 222 TO BS 249, BETWEEN L16L AND L18L. REMOVED REPAIR DOUBLERS AND ANGLE SUPPORT FITTING, 2 EA IAW 51-30-8, PG 4 STEP 13. CUTOUT THE SKIN AREA FROM STA 224-STA 257 L17L AND L18L IAW SRM 53-04,. HFEC CUTOUT, SURFACE AND OPEN HOLES FABRICATED REPAIR IAW SRM 53-04. INSTALLED REPAIR IAW SRM 51-30-2, AND SRM 51-30-5.

Part: SKIN — DAMAGED (BS 1116-1136) · airframe 79,161 hrs · 78,310 cycles

FUSELAGE SKIN DOUBLER REPAIR STA 1116 TO STA 1136, BETWEEN LONGERON 16R AND LONGERON 17R, FOUND TO BE WITHIN PROX DISTANCE TO ADJACENT EXTERNAL DOUBLER REPAIR AT STA 1108, LONG 15R, VERTICAL AND HORIZONTAL DISTANCE APPROX 4.5 INCHES. NO ACTION REQUIRED. REPAIR DOUBLER AT STA 1136, BETWEEN L-16R AND L-17R FOUND TO BE IAW SRM 53-04, FIG 54.

Part: SEAT TRACK — CRACKED (BS 712 RBL 22) · airframe 79,161 hrs · 78,310 cycles

FOUND CRACK IN SEAT TRACK AT RBL 22 AT STA 712. REMOVED SEAT TRACK FROM STA 683.5 TO 721.5, RBL 22 IAW SRM 53-05,. FABED REPAIR SPLICE PLATES AND REPLACEMENT SEAT TRACK SECTION, IAW SRM 53-05, PG 30, FIG 4D. INSTALLED SEAT TRACK AT RBL 22R, STA 683.5 TO 721.5 AND INSTALLED PRODUCTION SPLICE PLATES FROM STA 674 TO 693 IAW SRM 53-05, FIG 4D, PG 13, PARA 4A, SECTION B-B.

Part: FITTING — CRACKED (BULKHEAD) · airframe 79,161 hrs · 78,310 cycles

AFT SIDE OF BULKHEAD STA 69, RBL 15 TO WHEEL WELL PRESSURE PANEL VERTICAL FITTING CRACKED IN RADIUS AND LWR ATTACH BOLT HOLE TO EDGE OF FITTING, VIEWED THRU ACCESS 4201A FWD OF RUDDER PEDALS REMOVED IAW SRM 51-30-5, PG 29, FABRICATED NOSE GEAR BEAM ATTACH FITTING REF TRAVELER NR87331020001, AND INST IAW SRM 51-30-5, PG 12.

Part: CUSP WEB — MISREPAIRED (FUSELAGE) · airframe 79,161 hrs · 78,310 cycles

MAIN CABIN, BETWEEN STA Y753 AND STA Y775, CUSP MEMBRANE WITH INAPPROPRIATE REPAIR. REMOVED CUSP MEMBRANE MAIN CABIN BETWEEN STA Y753 AND 794, -X59, IAW SRM 51-30-2, PG 24, FABRICATED IAW SRM 51-13-3, PG 26, FIG 11, ITEM 10, TREATED, PRIMED IAW SRM 51-10-3, PG 32, AND INSTALLED IAW SRM 51-30-2.

Part: LONGERON — CRACKED (FUSELAGE) · airframe 79,161 hrs · 78,310 cycles

LONGERON UNDER RT MAIN STATIC PORT IS CRACKED. FABRICATED REPAIR ANGLE IAW SRP DC9-A-53-10-04-801-663A-A, INSTALLED REPAIR ANGLE IAW SRP DC9-A-53-10-04-801-663A-A, REPAIR PARTS INST ON RT MAIN STATIC PORT LONGERON FWD CARGO IAW SRP DC9-A-53-10-04-801-663A-A, IDENTIFIED REPAIR ON RT MAIN STATIC PORT IAW PS 900-5-1, NR 4, AT LONGERON 25, BETWEEN STA. 522 AND STA 541, RT SIDE.

Part: LONGERON — CRACKED (FUSELAGE) · airframe 79,161 hrs · 78,310 cycles

LONGERON UNDER RT MAIN STATIC PORT IS CRACKED. FABRICATED REPAIR ANGLE IAW SRP DC9-A--53-10-04-801-663A-A, TRIM LONGERON, INSTALLED REPAIR ANGEL IAW SRP DC9-A-53-10-04-801-663A-A. REPAIR PARTS INSTALLED ON RT MAIN STATIC PORT LONGERON FWD CARGO IAW SRP DC9-A-53-10-04-801-663A-A, ALODINED -5 ANGLE.

Part: FRAME — CRACKED (STA 1266) · airframe 79,161 hrs · 78,310 cycles

TAIL CONE COMPARTMENT, STA 1266, CANTED 1212.376 LONGERON NR 9 WITH A CRACK. REMOVED SPLICE, STA 1252, 1EA PLATE, STA 1278, AND CUT OUT LONGERON SECTION. LOCATED, DRILLED, TREATED AND PRIMED AND INSTALLED LONGERON SECTION, SPLICE REPAIR, SPLICE, STA 1252, AND PLATE, STA 1278, IAW SRM 53-02, FIG 18, PG 49-52, SRM 53-13-4, PG 14, FIG 4, SRM 51-10-3 PG 31, SRM 51-30-2, PG 2, AND SRM 51-30-5, PG 12.

Part: STRINGER — CRACKED (BS 1258 S11L) · airframe 79,161 hrs · 78,310 cycles

TAIL CONE, AFT ACCESSORY COMPARTMENT STRINGER., STA 1258 AND LONGERON 11LT, WITH CRACK. REMOVED SPLICE STA 1252 IAW SRM 51-30-2, PG 1, SRM 51-30-5, CUT OUT LT 11 STR STA 1252 TO STA 1275, IAW SRM 53-02, PG 50. LOCATED AND DRILLED, TREATED, PRIMED, AND INST LONGERON SECTION IAW SRM 53-02, FIG 18, SRM 51-10-3, SRM 51-30-2, PG 2 AND SRM 51-30-5, PG12, SRM 53-13-4.

Part: BEAM — CRACKED (BS 712 RBL 55) · airframe 79,161 hrs · 78,310 cycles

CABIN FLOOR STUB BEAM WEB AND UPPER CHORD C-CHANNEL CRACKED STA 712, RBL55 RL064. R & R IAW SRM 51-30-02, PG 1-4, "C" CHANNEL PN 9915527, BATCH 0002030328. FABRICATED 1 EA FLOOR STUB BEAM WEB OUT OF 7075T6 .063, BATCH 0001939188, IAW SRM 53-15-3, PG 3, FIG 1, ITEM 6, AT STA 712, RBL 55.

Part: FLOOR PANEL — DENTED (CABIN) · airframe 79,161 hrs · 78,310 cycles

CABIN FLOOR PANEL 92D TOP SKIN DENTED/CRACKED AT FWD END 77-05. UPPER SKIN OUT OF LIMITS DUE TO CRACK FROM PANEL EDGE, TO FASTENER HOLE, IAW SRM 53-01, PG 1, DETAIL 4. REMOVED 2 EA HAT CHANNELS IAW SRM 53-05, PGS 9-10. FABED REPAIR SKIN WITH MATERIAL 7075-T6, .025 BATCH 0001520995, IAW SRM 53-05, PGS 10-12. TREATED AND PRIMED IAW SRM 51-10-3, PGS 40-42, 31-32, REINSTALLED HAT CHANNELS 2 EA, IAW SRM 51-30-2, PGS 1-7.

Part: DOUBLER — CRACKED (FUSELAGE) · airframe 79,161 hrs · 78,310 cycles

BETWEEN LONGERONS 15L - 16L AT STA 1117 BRACKET-DOUBLER IS CRACKED. REMOVED BRACKET-DOUBLER DAMAGE AND FASTENERS ON STA 1117 BETWEEN LONGERONS 15L, 16L IAW SRM 53-03, PG 211, FORMED REPAIR C, STEP 1, 2, FABRICATED REPAIR PARTS IAW SRM 53-13-3, FIG 1, PG 5. INSTALLED REPAIR PARTS (DOUBLER, SPLICE IAW SRM 53-03, PG 211, FIG 44 FORMER REPAIR C, STEP 12, 13, 14 ON STA 1117 BETWEEN LONGERONS 15L + 16L.

Part: FLOOR SKIN — DENTED (FLOOR PANEL 47D) · airframe 79,161 hrs · 78,310 cycles

CABIN FLOOR PNL 47D HAS PULLED SCREWS AND DENTS IN TOP SKIN. BLENDED DAMAGE, OUT OF LIMITS IAW SRM 53-01, PG 8. CUT OUT DAMAGE IAW SRM 53-05, PG 10. FABBED FILLER AND DOUBLER IAW SRM 53-05, PG 10, FIG 1. TREATED AND PRIMED FILLER AND DOUBLER IAW SRM 51-10-3. INSTALLED FILLER AND DOUBLER, 47D IAW SRM 53-05, INSTALLED REPAIR WASHERS ON IAW SRM 51-30-1, FOUND CRACK IN 2EA DENTS OUT OF LIMITS IAW SRM 53-01, PG 8, FIG 1.

Part: FLOOR PANEL — DAMAGED (CABIN) · airframe 79,161 hrs · 78,310 cycles

CABIN FLOOR PNL 40D IS BENT UP AND SCREW HOLE IS WORN. FOUND CRACKS AT SCREW HOLE IN FLOOR PANEL. REMOVED DAMAGED AREA IAW SRM 51-70-2, PG 209. REQ NDT TO CHECK CUTOUT AREA FOR CRACK. NDT FOUND NO CRACKS IAW NDT IAW SRM 53-05, PG 10. TREATED AND PRIMED CUTOUT AREA AND REPAIR DOUBLER IAW SRM 51-10-3, PG 31, 32, 40, 41. INSTALLED REPAIR DOUBLER IAW DC9 SRM 51-30-2, PG 1 THRU 8, AND SRM 51-10-4, PG 1, AT CABIN FLOOR PANEL 40D.

Part: FITTING — CRACKED (FUSELAGE) · airframe 79,161 hrs · 78,310 cycles

STA 1151 BELOW LONGERON 14R THERE IS A CRACK IN THE DOUBLER. REMOVED SHEAR CLIP PER SRM 51-30-5 PAGE 29 FABBED SHEAR CLIP WITH SHT 2014-T0, 0.050 IAW SRM 53-13-3, PAGE 5. HEAT TREATED SHEAR CLIP TO 2014-T6 CONDITION, IN REF TO TRAVELER 87330820001. FABRICATED REPAIR SHEAR CLIP IAW SRM 53-03, PAGE 211, INSTALLED IAW SRM 53-03, PAGE 211, PAR 39, STEP C12, C13, C14, PAGE 213 FIG 44.

Part: SKIN — CORRODED (FLOOR PANEL) · airframe 79,161 hrs · 78,310 cycles

FLOOR PANEL, 36D FWD END UPPER SKIN IS TORN AND SCREW HOLES ARE WORN AND CORRODED. BLENDED CORROSION IN LIMITS, CUT OUT DAMAGED HOLES, FABRICATED DOUBLER AND FILLER. INSTALLED DOUBLER AND FILLER IAW SRM 51-10-3, SRM 51-30-1, SRM 53-23-0, SRM 53-05, SRM 51-10-03. INSTALLED FLOOR PANEL IAW AMM DC9-A-53-20-01-201-925A-A.

Part: SKIN — CRACKED (FLOOR PANEL) · airframe 79,161 hrs · 78,310 cycles

CABIN FLOOR PNL 92D HAS CRACKS IN TOP SKIN. REMOVED FLOOR PANEL IAW SRM 53-05, PG 4 AND 10. FABED UPPER SKIN IAW SRM 53-23-0, PG 9, FIG 4, SRM 51-10-4, FIG 3, FIG 7, SRM 51-10-2, PARA 4, FIG 9. INST FLOOR PANEL UPPER SKIN IAW SRM 51-30-2, FIG 3, AND SRM 53-23-0, PG 7, FIG 4, AND SRM 51-10-3, PG 31, 32, 40, 41.

Part: FLOOR PANEL — CORRODED (COCKPIT) · airframe 79,161 hrs · 78,310 cycles

COCKPIT FLOOR PANEL 15 AFT SIDE HAS CORROSION ON UPPER SURFACE, AT SEVERAL AREAS. REMOVED FLOOR PANEL 15 IAW SRM 51-10-3, PARA 26. FABRICATED FLOOR PANEL IAW SRM 51-10-4, PG 1-2, 20, INSTALLED COCKPIT FLOOR PANEL 15 IAW SRM 51-10-3, PARA 26 DAMAGE EXCEEDS ALLOWABLE LIMITS IAW SRM 53-01, FIG 1,SHEET 3.

Part: FLOOR PANEL — CRACKED (CABIN) · airframe 79,161 hrs · 78,310 cycles

CABIN FLOOR PANEL 93B FWD END HAS BROKEN RIVET AND SCREWS PULLED THRU TOP SKIN. REMOVED BROKEN RIVET FWD END AND FOUNDTO BE A CRACK. CUT OUT DAMAGED AREA IAW SRM 53-05, PG 10, FIG 1 FABRICATED REPAIR DOUBLER & FILLER, IAW SRM 51-10-3, PG 31, 40, AND 41. INST REPAIR DOUBLER AND FILLER IAW SRM 51-30-2, PG 24. COMP INSP AND RII COMPLETED.

Part: FLOORBOARD — DAMAGED (PAX CABIN) · airframe 79,161 hrs · 78,310 cycles

PASSENGER CABIN FLOORBOARD 71-50 CORNER IS DAMAGED. REMOVED DAMAGED AREA OF FLOORBOARD IAW SRM 53-05, PG 9, 10, MATERIAL ID SHT 7075-T6, BATCH 0001691309, FABED DOUBLER & FILLER, MATERIAL THICKNESS .032 CLAD IAW SRM 53-05, PG 10. TREATED AND PRIMED IAW INSTALLED DOUBLER & FILLER TO CABIN FLOORBOARD 71-50 IAW SRM 53-05, PG 10.

Part: FLOORBOARD — CRACKED (CABIN) · airframe 79,161 hrs · 78,310 cycles

PASSENGER CABIN FLOORBOARD NR 17 FIBERGLASS IS DAMAGED AND CRACKED. FABRICATED FLOOR PANEL ASSY NR 17 REF TRAVELER NR 87331210001, AND DWG NR 9923432. CORK TAPE TO BE ACCOMPLISHED ON WORK CARD NR 0590-40 20-8M, PG 7, PARA A/2. COMPLIED WITH ER/A 491545-14, REV ORIG.

Part: STRUCTURE — CORRODED (FUSELAGE) · airframe 79,161 hrs · 78,310 cycles

CABIN FLOOR STRUCTURE STA 160-165 BETWEEN LBL 8 AND LBL 16 HAS CORROSION. REMOVED CORROSION STA 160 TO 165, LBL 8 TO LBL 16 IAW DC9 SRM 53-10-3, PG 46 OUT OF LIMITS IAW DC9 SRM 53-01 PAGE 8, FIG 1. REMOVED EXFOLIATED PLATE IAW DC9 SRM 51-30-1. FABBED PLATE, REF TRAVELER 87330990001, SAA 9910078-279, ASSEMBLED PLATE AND BRACKET IAW DC9 SRM 51-30-2, PARA 1. INSTALLED ASSEMBLY PARTS IAW DC9 SRM 51-30-1, PAGE 1.

Part: SKIN — DAMAGED (FLOOR PANEL) · airframe 79,161 hrs · 78,310 cycles

CABIN FLOOR PANEL 58D HAS PUNCTURE IN TOP SKIN FABRICATED HAT CHANNEL, IAW SRM 53-05, PG 9-10. REMOVED DAMAGE FROM FLOOR PANEL TOP SKIN IAW SRM 53-01, PG 6, FIG 1 REPAIRED FLOOR PANEL IAW SRM 53-01, PG 1-2, 6-7, TREATED AND PRIMED FLOOR PANEL AND HAT CHANNEL IAW SRM 51-10-3, PG 40-41, SRM 51-10-3, PG 31-32. INSTALLED NEW HAT CHANNEL IAW SRM 51-30-2, PG 4, SRM 51-20-0, PG 10-11.

Part: FLOOR PANEL — CORRODED (COCKPIT) · airframe 79,161 hrs · 78,310 cycles

COCKPIT FLOOR PNL JUST AFT OF 14 RT SIDE HAS CORROSION ON UPPER SURFACE. REMOVED FLOOR PANEL IAW DC9-A-20-10-00-401-926A-A. REMOVED CORR IAW DC9 SRM 51-10-3, PG 46-48, OUT OF LIMITS IAW SRM 53-01, PG 6-7. REMOVED HAT CHANNELS IAW SRM 51-30-2, PARA.7, FABBED FLOOR PANEL IAW SRM 51-10-04. TREATED AND PRIMED FLOOR PANEL IAW SRM 51-10-3. INSTALLED HAT CHANNELS IAW SRM 51-30-2 AND SRM 51-30-1.

Part: SKIN — DENTED (FLOOR PANEL) · airframe 79,161 hrs · 78,310 cycles

CABIN FLOOR PNL 42D HAS SEVERAL DENTS IN TOP SKIN, OUT OF LIMITS IAW SRM 53-05, PGS 9-1 1, DUE TO CRACKS PRESENT IN DENTS. REMOVED 5 HAT CHANNELS IAW SRM 51-30-02, PG 28, TO FABRICATE NEW PANEL. FABRICATED FROM 7075T6.025", BATCH NR 0001825209, IAW SRM 51-30-2, PGS 1-4, PRIMED, IAW SRM 51-10-3, PGS 40-42, 30-31.

Part: NUT PLATE — CORRODED (FUSELAGE) · airframe 79,161 hrs · 78,310 cycles

PASSENGER CABIN FLOORBOARD 20-50 HAS CORROSION AND DAMAGED NUT PLATE OFF ACFT. BLENDED OUT, FOUND TO BE OUT OF LIMITS IAW SRM 53-01, PG 5 PANEL, LOCATED AND DRILLED HOLES IAW SRM 51-10-4, PG 1, TREATED AND PRIMED IAW SRM 51-10-3, PG 5-31 (ON PASSENGER CABIN FLOORBOARD 20-50 (ORIG MAT .040, DAMAGE DIM. L-12", W-3", D-.035). INSP BY, AND RII COMPLETED.

Part: TORQUE BOX — GOUGED (FWD CARGO DOOR) · airframe 79,161 hrs · 78,310 cycles

FWD CARGO DOOR CUTOUT TORQUE BOX LWR WEB GOUGED & PUNCTURED, FS 265-270. CUT OUT DAMAGED AREA IAW SRM 53-01, PG 25, FABRICATED REPAIR DOUBLER AND FILLER, AND INSTALLED REPAIR PARTS IAW SRM 53-01, PG 25, AND SRM 53-30-05, PG 12, AND SRM 51-30-2, AT FWD CARGO DOOR CUTOUT TORQUE BOX WEB. NDT NOTED NO CRACKS IAW SRM 06-10-01.001, TREATED AND PRIMED PARTS IAW SRM 51-10-03, PG 30,32, (STA 265-270).

Part: SKIN — DENTED (HORIZONTAL STAB) · airframe 79,161 hrs · 78,310 cycles

RT HORIZ STAB ELEVATOR T/E LOWER SURFACE SKIN WITH DENT AT STA XE 213.6 OUT OF LIMITS IAW SRM 51-50-2, PAGE11, REMOVED DAMAGED AREA IAW SRM 55-03, FG 14, FABRICATED, LOCATED, AND DRILLED FINGER DOUBLERS, NEW SKIN PANEL, STRAP,SHIMS & INST ALL PARTS IAW SRM 55-03, FIG 14. REMOVED RT CONTROL TAB PUSHROD AND RT GEARED TAB IAW SRM 55-20-1, INST RT ELEVATOR CONTROL TAB PUSHROD IAW AMM 27-30-03-201, COMPLETED.

Part: SKIN — CRACKED (FUSELAGE) · airframe 79,161 hrs · 78,310 cycles

FUSELAGE LT SIDE, STA Y130.5, EXTERNAL EXISTING REPAIR DOUBLER HAS CRACK. REMOVED EXTERNAL REPAIR DOUBLER AT LT IAW SRM 51-30-5, REQUESTED NDT FOR NO CRACKS NOTED IAW NDT SPM 06-10-01.001, RECEIVED, LOCATED, DRILLED, AND PRIMED EXTERNAL REPAIR DOUBLER & INSTALLED EXTERNAL REPAIR DOUBLER,& CONICAL WASHERS IAW DCP-53-04.

Part: SKIN — DENTED (CARGO DOOR) · airframe 79,161 hrs · 78,310 cycles

AFT CARGO COMPARTMENT DOOR OUTER SKIN WITH DENT AT STA Y1076, BETWEEN NR 1 AND NR 2 BEAMS. DAMAGED AREA, STA Y1076, IN LIMITS IAW DC9 SRM 53-04, PER STEP 3 FOUND TO BE OUT OF LIMITS DUE TO PROXIMITY AT FRAME IAW DC9 SRM 53-04. COLD FORMED SKIN BACK TO ORIGINAL CONTOUR AT DENTED AREA IAW DC9 SRM 53-04, FIG 38, INSTALLED INTERNAL DOUBLER AT AFT CARGO DOOR IAW DC9 SRM 51-10-3, PAGE 40, 31, PARA 21, 14 AND SRM 53-04 FIG 38.

Part: SKIN — WORN (PAX DOOR) · airframe 79,161 hrs · 78,310 cycles

FWD PASSENGER ENTRANCE DOOR OUTER SKIN REPAIR DOUBLER CUTOUT WITH WEAR AND SHARP EDGES, AT HOLD-OPEN HOOK LOCATION. REMOVED REPAIR DOUBLER IAW 51-30-2, INSP HFEC NO CRACK NOTED FABED DOUBLER SRM DC9 52-05, FIG 20A, TREATED AND PRIMED. INST DOUBLER SRM 52-05, PG 50, FIG 20A, SRM 51-10-3, PG 5, 31.

Part: SKIN — CRACKED (BS 130) · airframe 79,161 hrs · 78,310 cycles

FUSELAGE LT SIDE, STA Y 130.5+Z22, EXTERNAL EXISTING REPAIR DOUBLER WITH CRACK. REMOVED DOUBLER AT LT STA 130.5+Z22 IAW SRM 51-30-5, REQ NDT FOR NO CRACKS NOTED IAW NDT PM 06-10-01. 001, RECEIVED, LOCATED, DRILLED AND PRIMED DOUBLER & INST DOUBLER, AND CONICAL WASHERS IAW SRM 53-04, FIG 24 & ID IAW PS 900S-1 NR 4. INST 2 EA STRAPS IAW SRM 53-04, FIG 24, PG 129, LT STA 130.5+Z22.

Part: SKIN — DENTED (FUSELAGE) · airframe 79,161 hrs · 78,310 cycles

LOWER FUSELAGE STA Y343.5 BETWEEN LONG 20 RT AND 21RT EXT SKIN WITH DENT. MEASURED PER DC9 SRM 53-04, PG 217, FIG 38, COLD-FORMED SKIN BACK TO ORIGINAL CONTOUR PER SRM 53-04, FIG 38, CONDITION 2. HFEC SURFACE INSP PER NDT SPM 06-10-01.001, NO CRACKS NOTED ON DENT, FABBED DOUBLER PER DC9 SRM 53-04, FIG 38, PG 11, 20. TREATED AND PRIMED DOUBLER PER DC9 SRM 51-10-3, PG 40, 31, PAR 21, 14 INSTALLED DOUBLER PER DC9 SRM 53-04, FIG 38, PAGE 11, 20.

Part: BATTERY PACK — INOPERATIVE (EMERGENCY LIGHT) · airframe 1,890 hrs · 1,649 cycles

DURING LINE CHECK, MX FOUND THAT SEVERAL OF THE OVERHEAD EMERGENCY ESCAPE LIGHTS IN THE CABIN WERE INOPERATIVE. MX REPLACED THE BATTERY PACK AND THE LIGHTS RETURNED TO AN OPS CONDITION.

Part: LAMP — INOPERATIVE (EMERGENCY LIGHT) · airframe 78,940 hrs · 78,137 cycles

DURING LINE CHECK, MX FOUND THAT ALL OF THE EMERGENCY PATHWAY LIGHTS FOR THE CATWALK IN THE TAIL COMPARTMENT WERE INOPERATIVE. MX REPLACED THE FAILED LAMPS IN THE TAIL CONE EMERGENCY FLOOD LIGHT ASSEMBLIES AND FUNCTIONALLY CHECKED THE SYS.

Part: SKIN — CRACKED (FUSELAGE) · airframe 78,870 hrs · 78,082 cycles

RIGHT AFT CANTED FRAME STA 1339 LONGERON 18 SKIN HAS A CRACK. REPAIRED CRACKED SKIN PER SRM 53-01 FIG 2.

Part: SKIN — CRACKED (FUSELAGE) · airframe 78,870 hrs · 78,082 cycles

RIGHT AFT CANTED FRAME AREA STA, 1303 BETWEEN LONGERON 14 & 15R. SKIN CRACKED JUST BELOW EXISTING REPAIR. REPAIRED CRACKED SKIN PER SRM 53-01 FIG 2.

Part: BATTERY PACK — INOPERATIVE (EMERGENCY LIGHT) · airframe 78,806 hrs · 78,029 cycles

DURING LINE CHECK, MX FOUND THAT THE EMERGENCY PATHWAY LIGHTING IN ROWS 59 OF THE CABIN WERE INOPERATIVE. MX REPLACED THE BATTERIES IN THE POWER SUPPLY AND THE LIGHTS RETURNED TO AN OPS CONDITION.

Part: LIGHT — INOPERATIVE (CABIN) · airframe 75,661 hrs · 75,292 cycles

DURING LINE CHECK, MAINTENANCE FOUND THAT THE EMERGENCY PATHWAY LIGHTING FOR THE CATWALK IN THE TAIL COMPARTMENT WAS INOPERATIVE. MAINTENANCE REPLACED THE LIGHT ASSEMBLIES, BULBS, BATTERIES AND THEN PERFORMED A SATISFACTORY FUNCTIONAL CHECK OF THEM.

Part: BATTERY PACK — INOPERATIVE (EMERGENCY LIGHTS) · airframe 75,562 hrs · 75,202 cycles

ESCAPE PATH EMERGENCY LIGHTS QUICKLY DIMES OUT IN FIRST CLASS SEATS, AND ROWS 14 - 18 INOPERATIVE. REPLACED DOOR 1R BATTERY PACK, AND REPLACED LIGHT ASSEMBLY AT SEAT 1C.

Part: POWER SUPPLY — INOPERATIVE (EMERGENCY LIGHT) · airframe 75,080 hrs · 74,789 cycles

DURING LINE CHECK, MX FOUND THE THE FWD OVERWING EMERGENCY EXIT SIGNS WERE INOPERATIVE. MX REPLACED THE PWR SUPPLY AND THE LIGHS RETURNED TO AN OPERATIONAL CONDITION. (K)

Part: RELAY — INOPERATIVE (EMERGENCY LIGHTS)

DURING LINE CHECK, MX FOUND THAT THE RT EXTERIOR EMERGENCY FLOOD LIGHT WAS INOPERATIVE. MX REPLACED THE PERTINENT POWER RELAY AND THE LIGHTS RETURNED TO AN OPERATIONAL CONDITION. (K)

Part: BATTERY — DISCHARGED (CABIN) · airframe 74,703 hrs · 74,457 cycles

DURING LINE CHECK MX FOUND THAT THE EMERGENCY PATHWAY LIGHTING IN ROWS 9-13 OF THE CABIN WERE INOPERATIVE. MX REPLACED THE BATTERIES IN THE POWER SUPPLY AND THE LIGHTS RETURNED TO AN OPERATIONAL CONDITION.

Part: BATTERY PACK — INOPERATIVE (EMERGENCY LIGHTS) · airframe 73,753 hrs · 73,568 cycles

DURING LINE CHECK, MAINTENANCE FOUND THAT THE EMERGENCY EXIT SIGN LIGHT FOR THE FWD LEFT OVERWING HATCH WAS INOPERATIVE. MAINTENANCE REPLACED THE BATTERY AT ROW 14 AND THE TRANSFORMER AT ROW 14-15. OPERATIONAL CHECK WAS GOOD.

Part: SKIN — CRACKED (FUSELAGE) · airframe 73,368 hrs · 73,225 cycles

DURING "H" CHECK, FOUND CRACK IN LT FUSELAGE SKIN AT THE UPPER FORWARD CORNER OF PASSENGER ENTRY DOOR 1L JAMB. REPAIRED PER EA 98-212124 SECTION I. SECTION II REQUIRES REPETITIVE INSPECTIONS EVERY 3,000 CYCLES. SECTION III PERMANENT REPAIR TO BE ACCOMPLISHED ON OR BEFORE 24 MONTHS AFTER SECTION I.

Part: STIFFENER — CRACKED (FUSELAGE) · airframe 73,368 hrs · 73,225 cycles

DURING "H" CHECK, FOUND CRACK IN OUTBOARD LOWER END OF AFT LEFT LAVATORY NR 1 HORIZONTAL STIFFENER AT AFT PRESSURE BULKHEAD. REPAIRED PER EA 98-212123.

Part: BATTERY PACK — INOPERATIVE (EMERGENCY LIGHTS) · airframe 73,350 hrs · 73,211 cycles

THE EMERGENCY PATHWAY LIGHTING AT EACH SEAT IN THE FIRST CLASS SECTION WAS FOUND TO BE INOPERATIVE. THE BATTERY PACKS FOR THOSE ROWS WERE REPLACED AND THE LIGHTS FUNCTIONALLY CHECKED GOOD.

Part: BATTERY PACK — INOPERATIVE (EMERGENCY LIGHTS) · airframe 73,253 hrs · 73,131 cycles

DURING A LINE CHECK, MAINTENANCE FOUND THAT THE EMERGENCY PATHWAY LIGHTING IN THE FIRST CLASS SECTION OF THE CABIN HAD FAILED. MAINTENANCE REPLACED BATTERY PACK AA AND ASSOCIATED FUSE. OPERATIONAL CHECK WAS GOOD AND THE AIRCRAFT RETURNED TO SERVICE.

Part: BATTERY PACK — INOPERATIVE (EMERGENCY LIGHTS) · airframe 72,415 hrs · 72,403 cycles

TAIL COMPARTMENT EMERGENCY LIGHTS INOP. REPLACED BATTERY PACK. OPERATION CHECKS GOOD.

Part: CONTROL PANEL — MALFUNCTIONED (COCKPIT) · airframe 61,075 hrs · 62,076 cycles

CREW NOTICED THE LEFT GENERATOR OFF ANNUNCIATOR DURING TAKEOFF ROLL. ABORTED TAKEOFF AT APPROXIMATELY 120 KTS. THE LEFT GENERATOR INDICATED NO VOLTAGE FREQUENCY AND NO LOAD. MAINTENANCE INSPECTED THE LEFT GENERATOR SYSTEM AND FOUND NO FAULTS BUT REPLACED THE GENERATOR CONTROL PANEL AS A PRECAUTION. OPERATIONAL CHECK GOOD AND AIRCRAFT RETURNED TO SERVICE.

Part: FITTING — CORRODED · corrosion level 2 · airframe 60,613 hrs · 61,667 cycles

During SUV the lower beavertail fitting on the #2 pylon was found with corrosion on the upper and lower surfaces that required replacement. Material AISI 4340 steel forging. Repaired per EA 98-170684

Part: FITTING — CORRODED · corrosion level 2 · airframe 60,613 hrs · 61,667 cycles

During SUV the lower beavertail fitting on the #1 pylon was found with corrosion on the upper and lower surfaces. Made from AISI 4340 steel forging.Repaired per EA 98-170683

Part: FITTING — CORRODED · corrosion level 2 · airframe 60,613 hrs · 61,667 cycles

During SUV corrosion was found on the left wing to the body fitting which required the part to be replaced. Material 7075-T651 Repaired per EA 98-186041.

Part: FITTING — CORRODED · corrosion level 2 · airframe 50,613 hrs · 61,667 cycles

During SUV the upper beavertail fitting on the no 1 pylon was found with corrosion on the upper and lower surfaces. Made from AISI 4340 steel forging.Repaired per EA 98-170682.

Part: LIGHT — INOPERATIVE (TAILCONE) · airframe 58,807 hrs · 60,033 cycles

DURING LINE CHECK, FOUND EMERGENCY LIGHTS FOR AFT EVACUATION SLIDE INOPERATIVE. MAINTENANCE REPLACED THE TAIL CONE LIGHT ASSEMBLY. OPERATIONAL CHECK NORMAL.

Part: LIGHT — INOPERATIVE (TAILCONE) · airframe 58,645 hrs · 59,885 cycles

DURING LINE CHECK, FOUND TAIL CONE EMERGENCY LIGHTING INOPERATIVE. MAINTENANCE RELAMPED LIGHTING IN TAIL CONE. OPERATIONAL CHECK NORMAL.

Part: DUCT — DENTED (RIGHT)

DURING APPROACH INTO DTW, AIRCRAFT ROLLED TO THE LEFT ON SLAT EXTENSION. CREW DECLARED AN EMERGENCY AND AIRCRAFT LANDED SAFELY USING FLAPS ONLY. MAINTENANCE FOUND RIGHT TELESCOPE DUCT DENTED. REPLACED DUCT. OPERATIONAL CHECK NORMAL AIRCRAFT RETURNED TO SERVICE.

Part: BATTERIES — DISCHARGED (CABIN)

DURING LINE CHECK, FOUND EMERGENCY LIGHTS AT AFT OVERWING EXIT INOPERATIVE. MAINTENANCE REPLACED BATTERIES, OPERATIONAL CHECK OK.

Part: RADAR INDICATOR — FAILED (COCKPIT)

AFTER TAKEOFF, RADAR FAILED. SCREEN WENT TO RED THEN MULTI-COLORED. SELECTED STANDBY THEN OFF, AFTER TWO MINUTES RETURNED TO ON. SCREEN WAS BLANK FOR SEVERAL MINUTES THEN RETURNED TO RED THEN MULTI-COLORED. FLIGHT RETURNED TO MSP AND LANDED WITHOUT INCIDENT. REPLACED THE RADAR INDICATOR AND TRANSCEIVER, GROUND OPERATIONAL CHECK OK.

Part: POWER PACK — INOPERATIVE (TAIL CONE)

DURING LINE CHECK, FOUND TAIL CONE CATWALK EMERGENCY LIGHTS INOPERATIVE. REPLACED POWER PACK B5-28, OPERATIONAL CHECK OK.

Part: POWER SUPPLY — INOPERATIVE (TAILCONE)

DURING LINE CHECK, FOUND EMERGENCY LIGHTS OVER TAIL SLIDE AND AT TAILCONE INOPERATIVE. REPLACED POWER SUPPLY B5028. OPERATIONAL CHECK OK.

Part: BATTERIES — DISCHARGED (CABIN)

DURING LINE CHECK, FOUND OVERHEAD EMERGENCY LIGHTS INOPERATIVE ROWS 20-24. REPLACED BATTERIES IN POWER PACK. OPERATIONAL CHECK OK.

Part: P/D VALVE — MALFUNCTIONED (LT ENGINE)

DURING CLIMB, THE LEFT ENGINE OPERATING PARAMETERS BEGAN TO FLUCTUATE. THE AIRCRAFT RETURNED TO MEM AND LANDED WITHOUT INCIDENT. GROUND MAINTENANCE REPLACED P AND D VALVE AND PERFORMED ENGINE GROUND RUN AND LEAK CHECK.

Part: FLOOR CAP — CORRODED (FS 237-265)

DURING H-CHECK, FOUND CORROSION IN THE CENTER LINE FLOOR CAP FROM BS 237 - BS 265. REPAIRED CAP (P/N 5910760-11) PER EA 98-109386.

Part: FRAME — CRACKED (FS 693)

DURING H-CHECK, FOUND A .50 INCH CRACK IN THE FS 693 FRAME AT LONGERON 24L. REPAIRED FRAME (P/N 9919621) PER EA 98-102655.

Part: FLOOR BEAM — CRACKED (FS 237)

DURING H-CHECK, FOUND A TWO-INCH CRACK IN THE FS 237 FLOOR BEAM, LBL 6. REPAIRED BEAM (P/N 9911544-5) PER EA 98-102654.

Part: FITTING — CRACKED (SERVICE DOOR)

DURING H-CHECK, FOUND A CRACK IN THE FORWARD SERVICE DOOR NR 3 BEAM AFT END FITTING. REPLACED THE FITTING PER SRM 51-30-2 AND 51-30-5.