N16815

Part: FLOOR PANEL — DELAMINATED (FS 1117-1174) · airframe 49,657 hrs · 38,165 cycles

INSPECTION FOUND MAIN CABIN CENTER FLOOR PANEL DELAMINATED AT FS 1117-1174. A NEW FLOOR PANEL WAS INSTALLED IAW ECRA 5320-01265.

Part: FLOOR PANEL — PUNCTURED (FS 256-313) · airframe 49,660 hrs · 38,167 cycles

INSPECTION FOUND CABIN FLOOR PANEL PUNCTURED AT FS 256-313. THE FLOOR PANEL WAS REMOVED AND A NEW PANEL WAS INSTALLED IAW SRM 51-30-1 AND ECRA 5320-01265.

Part: INTERCOSTAL — CRACKED (R-1 DOOR) · airframe 49,657 hrs · 38,165 cycles

INSPECTION FOUND A 7" CRACK IN R-1 DOOR INNER INTERCOSTA UNDER HINGE ATTACH POINT. THE R-1 DOOR WAS REMOVED IAW MM 52-41-00. THE CRACK WAS STOP DRILLED AND A REPAIR CAP AND FITTING WERE INSTALLED IAW SRM 52-05, FIGURE 5. REINSTALLED R-1 DOOR IAW MM 52-41-00.

Part: SKIN — DENTED (T/E FLAP) · airframe 49,657 hrs · 38,165 cycles

INSPECTION FOUND RT WING O/B FLAP O/B TRAILING EDGE SKIN LOWER SURFACE DENTED. THE SKIN WAS REMOVED IAW SRM 51-30-2 AND THE SUPPORT RIBS WERE FOUND DAMAGED. NEW RIBS AND A REPAIR DOUBLER WERE INSTALLED AND THE SKIN WAS REINSTALLED IAW SRM 51-10-4, 51-10-3, 57-01, FIGURE 3, AND 51-30-2.

Part: PAN — GOUGED (R1 DOOR) · airframe 49,657 hrs · 38,165 cycles

INSPECTION FOUND R-1 DOOR LOWER PAN GOUGED AT RIVNUTS. THE PAN SUPPORT WAS REMOVED FOR ACCESS IAW SRM 51-30-02. A REPAIR ANGLE AND DOUBLER WAS INSTALLED IAW ECRA 5240-01386. THE SUPPORT PAN WAS REINSTALLED IAW SRM 51-30-2.

Part: MOUNT — CORRODED (R/W I/B FLAP) · airframe 49,657 hrs · 38,165 cycles

INSPECTION FOUND R/H WING I/B FLAP HINGE #2 CORRODED IN BOTTOM MOUNT HOLE. THE HOLE WAS REAMED AND TWO BUSHINGS WERE INSTALLED IAW EA 9-2750-2-A0914 AND ECRA 2750-01333.

Part: FRAME — CORRODED (FS 1271) · airframe 49,657 hrs · 38,165 cycles

INSPECTION FOUND FRAME CORRODED AT FS 1271 FROM LONGERON 27L TO 27R. THE CORRODED AREA OF FRAME WAS CUT OUT IAW SRM 53-03, FIGURE 2A. A REPAIR WAS INSTALLED IAW SRM 53-05, FIGURE 2A, 53-10-3, AND 53-03, FIGURE 2A.

Part: WEB — CRACKED (FUSELAGE) · airframe 49,657 hrs · 38,165 cycles

INSPECTION FOUND A 1 INCH CRACK IN L-1 DOOR TORQUE BOX WEB TANG. THE CRACKED AREA OF WEB TANG WAS TRIMMED OUT AND A DOUBLER AND FILLER WERE INSTALLED IAW EA 9-5314-2-A0905 AND ECRA 5310-04170.

Part: ANGLE — CRACKED (FWD CARGO DR) · airframe 49,657 hrs · 38,165 cycles

INSPECTION FOUND A 1" CRACK IN T-ANGLE AT FORWARD CARGO DOOR UPPER INTERNAL PAN AFT OF FORWARD HINGE. THE T-ANGLE WAS REMOVED AND A NEW T-ANGLE WAS INSTALLED IAW SRM 51-30-5.

Part: BRACKET — CRACKED (FWD CARGO DR) · airframe 49,657 hrs · 38,165 cycles

INSPECTION FOUND A 1" CRACK IN T-BRACKET OF FORWARD CARGO DOOR UPPER INTERNAL PAN FORWARD OF AFT HINGES. THE BRACKET WAS REMOVED AND A NEW BRACKET WAS INSTALLED IAW SRM 51-30-5.

Part: CHANNEL — CRACKED (L/H MLG DOOR) · airframe 49,657 hrs · 38,165 cycles

INSPECTION FOUND A 1" CRACK IN L/H MLG DOOR CHANNEL AT FORWARD END OF DOOR JUST ABOVE DOOR SEAL. A REPAIR DOUBLER WAS INSTALLED IAW EA 9-5281-2-A0904 AND ECRA 5280-01267.

Part: SKIN — GOUGED (R/H ELEVATOR) · airframe 49,657 hrs · 38,165 cycles

INSPECTION FOUND R/H ELEVATOR LOWER SKIN SURFACE O/B OF TRIM TAB PUSH ROD FAIRING GOUGED. THE SKIN WAS REMOVED AND A REPAIR DOUBLER WAS INSTALLED IAW SRM 51-70-2 AND 55-03.

Part: WEB — CORRODED (STA 370) · airframe 49,657 hrs · 38,165 cycles

INSPECTION FOUND FORWARD CARGO TORQUE BOX WEB CORRODED AROUND FASTENER HOLES AT STA 370. THE TORQUE BOX WEB AND SUPPORT ANGLE WERE REMOVED IAW SRM 51-10-4 AND 51-30-2. A REPAIR WEB AND SUPPORT ANGLE WERE INSTALLED IAW SRM51-30-2.

Part: SPLICE — CORRODED (FUSELAGE) · airframe 49,657 hrs · 38,165 cycles

INSPECTION FOUND LONGERON 29L SPLICE CORRODED IN FORWARD CARGO AREA AT FS 225. THE LONGERON SPLICE WAS REMOVED AND A NEW SPLICE WAS INSTALLED IAW SRM 53-01, FIGURE 1, 51-30-2, 51-10-4, AND 51-30-5.

Part: FRAME — CORRODED (FS 522) · airframe 49,657 hrs · 38,165 cycles

INSPECTION FOUND MID CARGO FRAME CORRODED AT FS 522 BETWEEN LONGERONS 28L AND 28R. THE CORRODED AREA OF FRAME WAS REMOVED AND A REPAIR WAS INSTALLED IAW SRM 53-03 AND 51-30-5.

Part: SKIN — GOUGED (R/H ELEVATOR) · airframe 49,657 hrs · 38,165 cycles

INSPECTION FOUND R/H ELEVATOR SKIN LOWER SURFACE JUST OUTBOARD OF #2 HINGE MOUNTING PAD GOUGED. THE SKIN PANEL WAS REMOVED AND A NEW SKIN PANEL WAS INSTALLED IAW SRM 51-30-2.

Part: SKIN — DENTED (LH "0" SLAT) · airframe 49,657 hrs · 38,165 cycles

INSPECTION FOUND L/H "0" SLAT EXTERNAL SKIN DENTED. THE SKIN AND ATTACHING PARTS WERE REMOVED IAW SRM 51-30-6 AND 51-30-1. A DOUBLER WAS INSTALLED IAW SRM 57-09, FIGURE 10A. THE SKIN AND ATTACHING PARTS WERE REINSTALLED IAW SRM 51-30-6 AND 51-30-1.

Part: WEB — CORRODED (FUSELAGE) · airframe 49,657 hrs · 38,165 cycles

INSPECTION FOUND CUSP WEB CORRODED AT FS 160 - 200, RBL 35 TO RBL 50. THE WEB WAS REMOVED AND A NEW WEB WAS INSTALLED IAW SRM 51-30-2 AND 53-10-1.

Part: SKIN — DENTED (RUDDER TAB) · airframe 49,657 hrs · 38,165 cycles

INSPECTION FOUND RUDDER CONTROL TAB SKIN DENTED IN THE LOWER LEFT SIDE. THE RUDDER TAB WAS REMOVED IAW MM 27-20-02. THE TAB WAS REPAIRED, WEIGHED, AND BALANCED IAW SRM 55-40-1. THE TAB WAS INSTALLED AND THROW CHECKS WERE COMPLETED IAW MM 27-20-02.

Part: SEAT TRACK — CORRODED (FS 1174-1309) · airframe 49,657 hrs · 38,165 cycles

INSPECTION FOUND L/H O/B SEAT TRACK CORRODED AT FS 1174-1309. THE SEAT TRACK WAS REMOVED AND A NEW SEAT TRACK WAS INSTALLED IAW SRM 51-30-1 AND 51-10-3.

Part: FLOOR PANEL — PUNCTURED (FS 389-408) · airframe 49,657 hrs · 38,165 cycles

INSPECTION FOUND CABIN R/H I/B FLOOR PANEL PUNCTURED AT FS 389-408. A NEW PANEL WAS INSTALLED IAW ECRA 5320-01265 AND SRM 51-30-1.

Part: SPACER — CORRODED (MID CARGO DR) · airframe 49,657 hrs · 38,165 cycles

INSPECTION FOUND MID CARGO DOOR LOWER JAMB BEAM SPACER CORRODED AROUND RIVNUTS. THE SPACER WAS REMOVED AND A NEW SPACER WAS INSTALLED IAW SRM 51-30-4 AND 51-10-4.

Part: SEAT TRACK — CORRODED (FS 1032-1309) · airframe 49,657 hrs · 38,165 cycles

INSPECTION FOUND CABIN L/H CENTER SEAT TRACK CORRODED AT FS 1032-1309. THE SEAT TRACK WAS REMOVED AND A NEW SEAT TRACK WAS INSTALLED IAW SRM 51-30-1, 51-30-2, 51-30-5, 51-10-4, 51-10-3, AND 53-05, FIGURE 4F.

Part: SEAT TRACK — CORRODED (FS 845-1032) · airframe 49,657 hrs · 38,165 cycles

INSPECTION FOUND R/H I/B SEAT TRACK CORRODED AT FS 845-1032. THE SEAT TRACK WAS REMOVED AND A NEW SEAT TRACK WAS INSTALLED WITH SPLICES IAW SRM 53-05, FIGURE 4F AND 51-10-3.

Part: FLOOR PANEL — BROKEN (FS 1079-1155) · airframe 49,657 hrs · 38,165 cycles

INSPECTION FOUND CABIN L/H O/B FLOOR PANELS BROKEN OFF AT FASTENER HOLES AT FS 1079-1155 AND FS 1155-1250. THE PANELS WERE REPAIRED IAW SRM 51-70-1.

Part: SKIN — DENTED (FS 494 & 522) · airframe 49,657 hrs · 38,165 cycles

INSPECTION FOUND L/H EXTERIOR FUSELAGE SKIN DENTED AT FS 522 ABOVE L25 AND AT FS 494 ABOVE L25. THE DENTS WERE COLD WORKED IAW SRM 53-04, FIGURE 38. A DOUBLER WAS INSTALLED AT EACH LOCATION IAW SRM 53-04, FIGURE 38, 51-10-4, AND 51-30-2.

Part: FLOOR PANEL — DELAMINATED (COCKPIT) · airframe 49,657 hrs · 38,165 cycles

INSPECTION FOUND COPILOT'S I/B FLOOR PANEL DELAMINATED. THE FLOOR PANEL WAS REMOVED AND A NEW FLOOR PANEL WAS INSTALLED IAW SRM 53-30-01, 53-21-0, SHEET 23, 51-30-1, AND 51-30-2.

Part: SEAT TRACK — CORRODED (STA 1108-1309) · airframe 49,657 hrs · 38,165 cycles

INSPECTION FOUND L/H SEAT TRACK CORRODED AT STA 1108-1309. THE SEAT TRACK WAS REMOVED AND A NEW SEAT TRACK AND SPLICE WERE INSTALLED IAW SRM 51-30-1.

Part: WEB — CORRODED (FUSELAGE) · airframe 49,657 hrs · 38,165 cycles

INSPECTION FOUND CUSP WEB CORRODED AT FS 200-237, RBL 44 TO RBL 56. THE CORRODED SECTION OF CUSP WEB WAS REMOVED AND A NEW CUSP WEB WAS INSTALLED IAW SRM 51-30-02.

Part: ANGLE — CORRODED (FUSELAGE) · airframe 49,657 hrs · 38,165 cycles

INSPECTION FOUND R-1 DOOR CUSP ANGLE CORRODED AT FS 203. THE CORRODED SECTION OF CUSP ANGLE WAS CUT OUT IAW SRM 51-30-1. A CUSP ANGLE AND SPLICE WERE INSTALLED IAW SRM 53-05, FIGURE 55, SHEET 2.

Part: PAN — CRACKED (CARGO DOOR) · airframe 49,657 hrs · 38,165 cycles

INSPECTION FOUND DOOR PAN CRACKED AROUND BOTTOM STOP AT AFT CARGO DOOR AFT SIDE. A DOUBLER AND FILLER WERE INSTALLED IAW SRM 52-05, FIGURE 1 & 4 AND ECRA 5230-01540.

Part: WEB — CRACKED (FUSELAGE) · airframe 49,657 hrs · 38,165 cycles

INSPECTION FOUND CUSP WEB CRACKED AFT OF L-2 DOOR AT STA 1174, LBL 60. THE CUSP WEB WAS REMOVED AND A NEW CUSP WEB WAS INSTALLED IAW SRM 51-30-2 AND 51-30-1.

Part: SKIN — GOUGED (FUSELAGE) · airframe 49,657 hrs · 38,165 cycles

INSPECTION FOUND RT FUSELAGE EXTERNAL SKIN DENTED AND GOUGED BELOW NR 2 ENGINE APRON AT STA 1309. THE DAMAGED AREA WAS REMOVED IAW SRM 53-04, FIGURE 38. A REPAIR DOUBLER AND SKIN PLUG WAS INSTALLED IAW SRM 53-04, FIGURE 38 AND 51-30-2.

Part: SKIN — GOUGED (FWD CARGO DR) · airframe 49,657 hrs · 38,165 cycles

INSPECTION FOUND FORWARD CARGO DOOR EXTERNAL SKIN GOUGED BELOW HANDLES. A REPAIR DOUBLER WAS INSTALLED IAW SRM 52-05, FIGURE 1 AND 52-05.

Part: SKIN — DENTED (STA 218) · airframe 49,657 hrs · 38,165 cycles

INSPECTION FOUND FUSELAGE EXTERNAL SKIN DENTED AT STA 218, LONGERON 16L AND 18L. THE DENTS WERE COLD WORKED IAW SRM 53-04, FIGURE 38. DOUBLERS WERE INSTALLED IAW SRM 53-10, FIGURE 38 AND 51-10-4.

Part: SEAT TRACK — CORRODED (STA 798-1108) · airframe 49,657 hrs · 38,165 cycles

INSPECTION FOUND CABIN SEAT TRACK CORRODED AT STA 798-1108. THE SEAT TRACK WAS REMOVED AND A NEW SEAT TRACK WAS INSTALLED IAW SRM 51-30-1.

Part: FLOOR PANEL — DELAMINATED (FS 927-1155) · airframe 49,657 hrs · 38,165 cycles

INSPECTION FOUND CABIN L/H I/B FLOOR PANEL DELAMINATED AT FS 1079-1155 AND R/H I/B FLOOR PANEL WAS DELAMINATED AT FS 927-1003. NEW FLOOR PANELS WERE INSTALLED IAW ECRA 5320-01265.

Part: FLOOR PANEL — DELAMINATED (FS 807-946) · airframe 49,657 hrs · 38,165 cycles

INSPECTION FOUND R/H I/B FLOOR PANELS DELAMINATED AT FS 826-927. A CENTER PANEL AT FS 886-946 AND CENTER & RIGHT CENTER PANELS AT FS 807-826 WERE FOUND DELAMINATED. NEW PANELS WERE INSTALLED IAW ECRA 5320-01265.

Part: FLOOR PANEL — DELAMINATED (FS 769-886) · airframe 49,657 hrs · 38,165 cycles

INSPECTION FOUND L/H I/B FLOOR PANEL PUNCTURED AT FS 769-826 AND L/H I/B FLOOR PANEL AT FS 864-886 WAS DELAMINATED. THE FLOOR PANELS WERE REPLACED IAW ECRA 5320-01265.

Part: FLOOR PANEL — DELAMINATED (PNLS B-K) · airframe 49,657 hrs · 38,165 cycles

INSPECTION FOUND CABIN FLOOR PANELS B-K DELAMINATED. NEW FLOOR PANELS WERE INSTALLED IAW ECRA 5320-01265.

Part: FLOOR PANEL — DELAMINATED (PNLS M-P) · airframe 49,657 hrs · 38,165 cycles

INSPECTION FOUND CABIN FLOOR PANELS M-P DELAMINATED. NEW FLOOR PANELS WERE INSTALLED IAW ECRA 5320-01265.

Part: FLOOR PANEL — DELAMINATED (FS 826-1003) · airframe 49,657 hrs · 38,165 cycles

INSPECTION FOUND CABIN CENTER FLOOR PANELS DELAMINATED AT FS 826-886 AND AT FS 945-1003. NEW FLOOR PANELS WERE INSTALLED IAW ECRA 5320-01265.

Part: FLOOR PANEL — DELAMINATED (FS 1079-1174) · airframe 49,657 hrs · 38,165 cycles

INSPECTION FOUND CABIN R/H I/B AND CENTER FLOOR PANELS AT FS 1117-1174 DELAMINATED AND CENTER PANEL AT FS 1079-1117 DELAMINATED. NEW FLOOR PANELS WERE INSTALLED IAW ECRA 5320-01265.

Part: FLOOR PANEL — DELAMINATED (FS 1174-1361) · airframe 49,657 hrs · 38,165 cycles

INSPECTION FOUND MAIN CABIN CENTER FLOOR PANELS DELAMINATED AT FS 1174-1250 AND FS 1309-1361. A R/H I/B FLOOR PANEL WAS DELAMINATED AT FS 1250-1309. A NEW FLOOR PANELS WERE INSTALLED IAW ECRA 5320-01265.

Part: FLOOR PANEL — DELAMINATED (FS 693-769) · airframe 49,657 hrs · 38,165 cycles

INSPECTION FOUND MAIN CABIN R/H CENTER AND L/H CENTER FLOOR PANELS DELAMINATED AT FS 693-769. NEW PANELS WERE INSTALLED IAW ECRA 5320-01265.

Part: SEAT TRACK — CORRODED (FS 798-874) · airframe 49,657 hrs · 38,165 cycles

INSPECTION FOUND R/H CENTER SEAT TRACK CORRODED AT FS 798-874. THE SEAT TRACK WAS REMOVED AND A NEW SEAT TRACK WAS INSTALLED IAW SRM 51-30-2, 51-30-5, AND 51-30-3.

Part: SKIN — DENTED (FS 275) · airframe 49,657 hrs · 38,165 cycles

INSPECTION FOUND FUSELAGE EXTERNAL SKIN DENTED AT FS 275, LONGERON 17L. THE DENTED AREA OF SKIN WAS REMOVED IAW SRM 51-30-2. NEW SKIN WAS INSTALLED IAW SRM 51-30-2, 51-30-5, AND ECRA 5330-02445.

Part: SKIN — DAMAGED (FUSELAGE) · airframe 49,657 hrs · 38,165 cycles

INSPECTION FOUND FUSELAGE SKIN CREASED AT STA 180, LONGERON 23R. THE CREASED AREA WAS CUT OUT IAW SRM 53-04, FIGURE 12, PAGE 35. A REPAIR DOUBLER AND FINGER DOUBLER WAS INSTALLED IAW SRM 53-04, FIGURE 12, PAGE 35, 51-10-4, 53-30-5, AND 51-30-2.

Part: SKIN — DENTED (STA 389) · airframe 49,657 hrs · 38,165 cycles

INSPECTION FOUND L/H LOWER EXTERNAL FUSELAGE SKIN DENTED AT STA 389, LONGERON 29L. THE DENT WAS COLD FORMED AND A DOUBLER WAS INSTALLED IAW SRM 51-10-3 AND 53-05, FIGURE 38.

Part: WEB — CRACKED (FUSELAGE) · airframe 49,657 hrs · 38,165 cycles

INSPECTION FOUND FORWARD ENTRY CUSP WEB CRACKED BETWEEN FS 160 AND 200, RBL 30. THE CRACKED AREA WAS CUT OUT AND A REPAIR DOUBLER WAS INSTALLED IAW SRM 53-01, FIGURE 2, 51-10-3, AND 51-30-2.

Part: WEB — CORRODED (FUSELAGE) · airframe 49,657 hrs · 38,165 cycles

INSPECTION FOUND FORWARD ENTRY CUSP WEB CORRODED BETWEEN FS 200 AND 205, LBL 10 TO RBL 10. A REPAIR DOUBLER WAS INSTALLED IAW SRM 53-01, FIGURE 1 AND 51-30-2.

Part: WEB — CRACKED (FUSELAGE) · airframe 49,657 hrs · 38,165 cycles

INSPECTION FOUND A 3 INCH CRACK IN FORWARD ENTRY CUSP WEB AT FS 158, RBL 3. THE CRACKED AREA WAS CUT OUT AND A REPAIR DOUBLER WAS INSTALLED IAW SRM 53-01, FIGURE 2, 51-10-3, AND 51-30-2.

Part: WEB — CRACKED (FUSELAGE) · airframe 49,657 hrs · 38,165 cycles

INSPECTION FOUND A 3.5 INCH CRACK IN FORWARD ENTRY CUSP WEB AT FS 161, RBL 5. THE CRACKED AREA WAS ROUTED OUT AND A REPAIR DOUBLER WAS INSTALLED IAW SRM 53-01, FIGURE 2, 51-10-3, AND 51-30-2.

Part: WEB — CORRODED (FUSELAGE) · airframe 49,657 hrs · 38,165 cycles

INSPECTION FOUND FORWARD ENTRY CUSP WEB CORRODED AT FS 180-200 BETWEEN RBL 7 AND LBL 10. A REPAIR DOUBLER WAS INSTALLED IAW SRM 53-01, FIGURE 2, 51-10-3, AND 51-30-2.

Part: WEB — PUNCTURED (FUSELAGE) · airframe 49,657 hrs · 38,165 cycles

INSPECTION FOUND CABIN SUBFLOOR PUNCTURED AT FS 160, RBL 12 AND FS 180, RBL 10. THE PUNCTURED AREAS WERE REMOVED IAW SRM 53-01, FIGURE 1. A REPAIR DOUBLER AND FILLER WERE INSTALLED AT EACH LOCATION IAW SRM 53-01, FIGURE 1, 51-10-3, 51-30-1, AND 51-30-2.

Part: WEB — CORRODED (FUSELAGE) · airframe 49,657 hrs · 38,165 cycles

INSPECTION FOUND FORWARD ENTRY CUSP WEB CORRODED AT FS 160-209, LBL 42-50. THE FASTENERS WERE REMOVED AND THE CORRODED AREA WAS CUT OUT IAW SRM 51-10-4 AND 53-01, FIGURE 2. A REPAIR DOUBLER WAS INSTALLED IAW SRM 51-10-2, 51-10-3, AND 51-30-2.

Part: FRAME — CORRODED (BS 180)

INSPECTION FOUND FRAME IN E&E BAY AT STA 180 LONGERON 30 CORRODED. THE CORROSION WAS REMOVED IAW SRM 51-10-3. A ROLLED Z-FRAME REPAIR SPLICE WAS INSTALLED IAW SRM 53-03, FIGURE 2A.

Part: SUPPORT — CORRODED (BS 541)

FWD CARGO STA 541 FLOOR SUPPORT IS CORRODED JUST ABOVE LONG 27R. REMOVED DAMAGED FLOOR SUPPORT FABRICATED AND INSTALLED NEW SUPPORT PER SRM 53-01, 53-30-2, AND 51-10-3.

Part: RIB — CRACKED (NR 5 LE SLAT)

SLAT END FITTING DAMAGED (3 CRACK). REMOVED DAMAGED SLAT END FITTING AND REPLACED WITH NEW PART PER SRM 51-30-8.

Part: GUSSET — CORRODED (BS 427)

FWD CARGO STA 427 JUST INSIDE DOORWAY FLOOR SUPPORT IS CORRODED. REMOVED DAMAGED SECTION. FABRICATED AND INSTALLED NEW SECTION PER SRM 53-01-1, 51-10-3, 53-01, 51-10-4, AND 51-30-2.

Part: FLOOR — CORRODED (BS 207)

E AND E BAY CEILING STA 207 LBL 6 CORROSION ON FLOOR. FABRICATED REPAIR FROM 7075-T6 .020. TREATED, PRIMED, INSTALLED PER SRM 53-01 AND 53-10-3.

Part: SKIN — CRACKED (LE LE SLAT)

LEFT WING NUMBER 0 SLAT LOWER SURFACE IN CENTER AREA HAS A 3 CRACK IN SKIN NEAR TRAILING EDGE OF SLAT. FABRICATED AND INSTALLED REPAIR DOUBLER PER SRM 57-01 AND MM 51-00-00.

Part: SKIN — CRACKED (WS 267)

INSPECTION FOUND A .5 INCH CRACK IN RT WING UPPER SKIN AT I/B SPOILER O/B HINGE, XRS 267. THE PANEL WAS REMOVED IAW MM 27-62-01, SRM 51-30-1, 51-30-2, AND 51-30-5. THE PANEL WAS REPAIRED AND REINSTALLED IAW SRM 51-30-1, 51-30-2, 51-30-5, AND MM 27-62-01.

Part: SKIN — GOUGED (VERT STAB)

INSPECTION FOUND VERTICAL STABILIZER LEADING EGDE SKIN GOUGED AND DENTED AT STA ZFS 159. THE DAMAGED AREA WAS TRIMMED OUT. A DOUBLER AND FILLER REPAIR WAS INSTALLED IAW SRM 55-01, FIGURE 4, 51-10-3, AND 51-30-2.

Part: FLOORBEAM — CORRODED (BS 1174)

INSPECTION FOUND FLOORBEAM AT STA 1174, RBL 22 CORRODED AND CHAFED FROM CARGO DOOR. THE CORROSION WAS REMOVED IAW SRM 51-10-3. A REPAIR FOR THE CHAFING WAS INSTALLED IAW SRM 53-05, FIGURE 86 AND 51-30-5.

Part: SKIN — TORN (RT TE FLAP)

INSPECTION FOUND RT FLAP T/E PANEL CORNER DENTED WITH CORNER TORN OFF. THE PANEL WAS REMOVED, REPAIRED AND REINSTALLED IAW SRM 51-30-1 AND 57-01, FIGURE 3.

Part: SKIN — DENTED (BS 256-1231)

INSPECTION FOUND THE FUSELAGE SKIN DENTED AT STA 256, L22R, STA 490, L23L, AND STA 1231, L22R. THE DENTS WERE REFORMED IAW SRM 53-04, FIGURE 38. DOUBLERS WERE INSTALLED AT EACH LOCATION IAW SRM 53-04, FIGURE 38, 51-30-2, 51-10-4, 51-10-3, AND 51-30-5.

Part: SKIN — DENTED (CARGO DOOR)

INSPECTION FOUND MID CARGO DOOR OUTER SKIN DENTED AT STA 674, L22R. A REPAIR WAS INSTALLED IAW SRM 53-04, FIGURE 38, 52-33-2, FIGURE 1, 52-05, FIGURE 1, AND 52-01, FIGURE 7.

Part: STIFFENER — CRACKED (AFT AIRSTAIR)

INSPECTION FOUND A .75 INCH CRACK IN SUPPORT STIFFENER ON BOTH LEFT AND RIGHT SIDES OF TAIL COMPARTMENT AFT STAIR HINGE AREA. THE CRACKS WERE STOP DRILLED IAW ECRA 5320-01547. A DIP WAS ISSUED TO INSPECT THE AREAS EVERY FIVE DAYS AND TO PERMANENTLY REPAIR WITHIN 30 DAYS.

Part: AXLE PISTON — DAMAGED (NLG)

THE NOSE WHEEL PRODUCED A GRINDING SOUND IN TURNS AFTER LANDING AT ATL. MAINTENANCE FOUND BOTH THE INNER AND OUTER BEARINGS SEIZED TO AXLE RESULTING IN DAMAGE TO AXLE AND NR 2 WHEEL ASSEMBLY. THE NLG AXLE PISTON ASSEMBLY WAS REMOVED AND REPLACED IAW MM 32-21-02, PAGE 801. IN ADDITION, BOTH THE NR 1 AND NR 2 NLG WHEEL ASSEMBLIES WERE REMOVED AND REPLACED IAW MM 32-40-02, PAGE 201. THE NLG WAS SWUNG FOUR TIMES AND OPERATION CHECKED GOOD. A DIP WAS ISSUED FOR A FULL NOSE STRUT RESERVICING WITHIN 50 FLIGHT HOURS.

Part: PAN — CORRODED (AFT LAV)

INSPECTION FOUND A HOLE CORRODED THROUGH AFT LAV PAN AT LOWER DUMP VALVE HANDLE. A DOUBLER WAS INSTALLED IAW ECRA 5330-02583.

Part: CLIP — CRACKED (BS 1309)

INSPECTION FOUND A 1 INCH CRACK IN CLIP AT AFT RT LAV FORWARD SIDE, STA 1309, BETWEEN LONGERON 15 AND 16R. THE CLIP WAS REMOVED AND REPLACED IAW SRM 51-30-0.

Part: WEB — CORRODED (BS 200)

INSPECTION FOUND WEB AFT OF FORWARD ENTRY AFT DOOR JAMB AT STA 200 CORRODED AND SUBFLOOR ALSO HAD CORROSION. THE CORRODED SECTION OF WEB AND SUBFLOOR WERE REMOVED. A NEW SECTION OF WEB AND A SUBFLOOR DOUBLER WERE INSTALLED IAW SRM 51-30 AND 53-01.

Part: ANGLE — CORRODED (BAGGAGE BIN)

INSPECTION FOUND THE AFT BAGGAGE BIN Z-ANGLE BEAM CORRODED. A REPAIR DOUBLER WAS INSTALLED IAW SRM 53-05, FIGURE 63.

Part: SKIN — DAMAGED (BS 503-579)

THE AIRCRAFT WAS STRUCK IN LT FUSELAGE FORWARD OF WING LEADING EDGE BY A POTABLE WATER SERVICE TRUCK. THE SKIN WAS DAMAGED BETWEEN STA 503 AND 522 FROM LONGERON 24L TO 25L AND BETWEEN STA 538 AND 579 BETWEEN LONGERON 23L AND 26L. A REPAIR WAS ACCOMPLISHED IAW ECRA 5310-03562, SRM 53-03-2A, 53-03-3, AND 53-02, FIGURE 18.

Part: ACTUATOR — LEAKING (NLG)

THE NOSE GEAR RED UNSAFE LIGHT REMAINED ILLUMINATED AFTER TAKEOFF. ABNORMAL PROCEDURES WERE COMPLIED WITH, BUT THE LIGHT REMAINED ILLUMINATED. THE AIRCRAFT WAS RETURNED TO LAS WHERE IT LANDED WITHOUT INCIDENT. MAINTENANCE FOUND KNEE HINGE BOLT LOOSE AND RETRACT CYLINDER LEAKING. THE KNEE HINGE BOLT WAS TIGHTENED AND THE RETRACT CYLINDER WAS REPLACED. IN ADDITION, THE UPLOCK SENSOR WAS REPLACED, THE NOSE GEAR WAS SWUNG AND OPERATION CHECKED GOOD.

Part: UPLOCK SENSOR — INOPERATIVE (NLG)

THE NOSE GEAR UNSAFE LIGHT REMAINED ILLUMINATED AFTER GEAR RETRACTION LEAVING ATL. CHECKLIST PROCEDURES WERE COMPLIED WITH AND THE AIRCRAFT WAS RETURNED TO ATL WHERE IT LANDED WITHOUT INCIDENT. MAINTENANCE FOUND THE NOSE GEAR UPLOCK SENSOR AT FAULT. THE SENSOR WAS REMOVED AND REPLACED. THE NOSE GEAR WAS RETRACTED WITH OPERATION AND INDICATIONS CHECKING GOOD.

Part: STRUT — FLAT (NLG)

THE RED NOSE GEAR UNSAFE LIGHT REMAINED ON AFTER GEAR WAS RETRACTED DEPARTING EWR. ABNORMAL PROCEDURES WERE COMPLIED WITH AND THE AIRCRAFT WAS RETURNED TO EWR WHERE IT LANDED WITH THREE LANDING GEAR DOWN INDICATIONS. MAINTENANCE FOUND THE NOSE GEAR STRUT BOTTOMED OUT. THE NOSE GEAR STRUT WAS SERVICED WITH NITROGEN TO PROPER X-DIMENSION. THE NOSE GEAR WAS EXTENDED AND RETRACTED IAW MM 07-00-00. NO DEFECTS WERE NOTED AND ALL GEAR INDICATIONS WERE NORMAL.

Part: SPRING — BROKEN (FLAP HANDLE)

THE FLAPS WOULD NOT FULLY RETRACT AFTER TAKEOFF. THE FLAP HANDLE WOULD NOT STAY IN THE RETRACT POSITION. THE AIRCRAFT WAS RETURNED TO EWR WHERE IT LANDED WITHOUT INCIDENT. MAINTENANCE FOUND THE FLAP HANDLE CONTROL SPRING BROKEN. THE SPRING WAS REMOVED AND REPLACED, AN OPERATIONAL CHECK OF THE FLAPS WAS GOOD.

Part: STRUT — LOW PRESSURE (NLG)

FLT NR 455 - DEN - THE LANDING GEAR WOULD NOT RETRACT AND THE AIRCRAFT WOULD NOT PRESSURIZE AFTER TAKEOFF FROM DEN. THE AIRCRAFT WAS RETURNED TO DEN WHERE IT LANDED WITHOUT INCIDENT. MAINTENANCE SERVICED THE NOSE GEAR STRUT IAW MM 32-21-02. THE GEAR WAS SWUNG SEVERAL TIMES WITH OPERATION CHECKING GOOD. (M)

Part: RETRACT CYLINDER — LEAKING (RT MLG)

FLT NR 1951 - LAS - THE RIGHT HYDRAULIC SYSTEM QUANTITY AND PRESSURE DROPPED WHILE EN ROUTE TO LAS. SMOKE WAS OBSERVED IN THE CABIN AFTER LANDING AT LAS. ALL 3 SLIDES WERE DEPLOYED AND THE PASSENGERS WERE EVACUATED. MAINTENANCE FOUND THE RIGHT MLG ACTUATOR LEAKING CAUSING HYDRAULIC FLUID TO ENTER THE APU INLET WHICH RESULTED IN SMOKE. THE RIGHT MLG ACTUATOR WAS REMOVED AND REPLACED. THE HYDRAULIC SYSTEM WAS SERVICED. THE APU WAS RUN WITH BOTH PACKS AND ENGINES OPERATING AND NO SMOKE WAS OBSERVED IN THE CABIN. IN ADDITION, ALL THREE EMERGENCY EVACUATION SLIDES WERE REMOVED AND REPLACED. (M)

Part: B-NUT — LOOSE (RT HYD SYSTEM)

FLT NR 120 - LGA - THE RIGHT HYDRAULIC SYSTEM EXPERIENCED FLUID LOSS ON APPROACH TO LGA. POWER TO THE AUX AND RIGHT HYDRAULIC PUMPS WERE TURNED OFF. A RIGHT HYDRAULIC OFF APPROACH AND LANDING WAS ACCOMPLISHED WITHOUT INCIDENT. THE RIGHT HYD SYSTEM RESERVOIR WAS SERVICED WITH FLUID. THE AIRCRAFT WAS JACKED AND THE LANDING GEAR, SPOILERS, FLAPS, AND SLATS WERE CYCLED. LEAKAGE WAS FOUND AT THE RIGHT LANDING GEAR CONTROL VALVE B-NUT. THE B-NUT WAS TIGHTENED. THE LANDING GEAR AND FLIGHT CONTROLS WERE CYCLED AGAIN SEVERAL TIMES WITH NO DEFECTS OR FLUID LOSS NOTED. (M)

Part: SUPPORT SHELF — BROKEN (NR 1 ENGINE)

EWR - FLT 0428 - TAKEOFF WAS ABORTED AT LESS THAN 60 KNOTS AFTER TOWER REPORTED SPARKS WERE COMING FROM THE LEFT ENGINE TAILPIPE. MAINTENANCE PERFORMED A BORESCOPE INSPECTION OF THE NR 1 ENGINE AND FOUND DAMAGE TO THE 6TH STAGE COMPRESSOR BLADES. THE NR 1 ENGINE WAS REMOVED AND REPLACED. SDR WILL REMAIN OPEN FOR PART INFORMATION PENDING INVESTIGATION. SUPPLEMENT: TEAR DOWN FINDINGS REVEALED 8TH STAGE STATOR SUPPORT SHELF BROKE AND CAUSED COMPRESSOR DAMAGE. (X)

Part: BEARING — WORN (NLG AXLE)

FLT NR 0692 - EWR - THE NOSE GEAR MADE A GRINDING NOISE WHILE TAXIING. MAINTENANCE FOUND THE NOSE GEAR WHEEL BEARING WORN CAUSING THE WHEEL TO GAUGE AXLE. THE NLG AXLE WAS REMOVED AND REPLACED. THE NOSE GEAR SHOCK STRUCT WAS REPACKED PER MM 32-21-02, PAGE 801. IN ADDITION, BOTH NOSE TIRES WRE REPLACED AS A PRECAUTIONARY MEASURE. (W)

Part: EEL BATTERIES — DISCHARGED (CABIN)

EWR - FLT 0443 - SEVERAL OVERHEAD EMERGENCY EXIT LIGHTS WERE FOUND INOPERATIVE AT ROWS 5-8. THE EMERGENCY LIGHT BATTERY PACK AT STA 427R WAS FOUND INOPERATIVE. THE BATTERIES FOR THE BATTERY PACK WERE REMOVED AND REPLACED. OPERATION OF THE OVERHEAD EMERGENCY LIGHTS AT ROWS 5-8 WAS RESTORED. (X)