N16813

Part: FLOOR PANEL — CORRODED (FS 160-200) · airframe 50,195 hrs · 39,422 cycles

INSPECTION FOUND FORWARD ENTRY FLOOR PANEL AT R-1 DOOR JAMB CORRODED, FS 160-200, RBL 48. THE FLOOR PANEL AND SUPPORT WERE REMOVED AND A NEW FLOOR PANEL AND SUPPORT WERE INSTALLED IAW SRM 51-10-4, 53-30-1, AND 51-30-1.

Part: FLOOR PANEL — DELAMINATED (FS 1003-1079) · airframe 50,168 hrs · 39,405 cycles

INSPECTION FOUND MAIN CABIN R/H I/B FLOOR PANEL DELAMINATED AT FS 1003-1079. A NEW FLOOR PANEL WAS INSTALLED IAW ECRA 5320-01265.

Part: FLOOR PANEL — DELAMINATED (AFT COCKPIT) · airframe 50,088 hrs · 39,358 cycles

INSPECTION FOUND CAPTAIN'S R/H SIDE AFT FLOORBOARD DELAMINATED. THE FLOOR PANEL WAS REMOVED AND A NEW PANEL WAS INSTALLED IAW SRM 51-30-01.

Part: DOOR FRAME — DENTED (FUSELAGE) · airframe 50,072 hrs · 39,347 cycles

INSPECTION FOUND R-1 DOOR JAMB DENTED AT AFT LATCHING MECHANISM. THE BAYONET ROLLER ATTACH ARM WAS REMOVED IAW SRM 51-30-01. A REPAIR DOUBLER AND SHIM WERE INSTALLED IAW SRM 51-30-2. A NEW DOOR STOP WAS INSTALLED IAW SRM 51-30-5. THE BAYONET ROLLER ATTACH ARM WAS REINSTALLED IAW SRM 51-30-01.

Part: SKIN — DENTED (FS 120) · airframe 50,072 hrs · 39,347 cycles

INSPECTION FOUND L/H FORWARD FUSELAGE EXTERNAL SKIN DENTED AT FS 120, LONGERON 18L. THE DENT WAS COLD WORKED AND A REPAIR DOUBLER WAS INSTALLED IAW EA 9-5331-2-A0902 AND ECRA 5331-01095.

Part: ANGLE — CORRODED (FUSELAGE) · airframe 50,072 hrs · 39,347 cycles

INSPECTION FOUND LT CUSP ANGLE CORRODED ON UPPER SURFACE AT AFT END OF L-1 DOOR ENTRANCE, STA 186. THE AREA WAS REPAIRED IAW EA 9-5310-2-A0895 AND ECRA 5310-04156.

Part: SLAT — DENTED (R/H WING, #2) · airframe 50,072 hrs · 39,347 cycles

INSPECTION FOUND R/H WING #2 SLAT DENTED AT LEADING EDGE. THE DENT WAS FILLED IAW SRM 57-03, FIGURE 20A & B.

Part: FLOOR SUPPORT — CORRODED (FUSELAGE) · airframe 50,072 hrs · 39,347 cycles

INSPECTION FOUND MID CARGO RT BULKHEAD FLOOR SUPPORT CORRODED AT FS 541. THE FLOOR SUPPORT WAS REMOVED AND A NEW FLOOR SUPPORT WAS INSTALLED IAW SRM 51-30-2, 51-10-4, AND 51-10-3.

Part: DOOR FRAME — CRACKED (FUSELAGE) · airframe 50,072 hrs · 39,347 cycles

INSPECTION FOUND A 5 INCH CRACK IN DOOR JAMB SKIN TANG AT AFT END OF L-1 DOOR, FS 207, LONGERON 11L. A 1 INCH CRACK WAS FOUND IN THE DOOR JAMB SKIN TANG AT FS 207, LONGERON 15L. THE CRACKED AREA WERE TRIMMED OUT IAW ECRA 5310-04155. FILLER AND DOUBLER WERE INSTALLED AT EACH LOCATION IAW SRM 51-10-4, 51-10-3, AND ECRA 5310-04155.

Part: SKIN — DENTED (AFT CARGO DR) · airframe 50,072 hrs · 39,347 cycles

INSPECTION FOUND AFT CARGO DOOR EXTERIOR SKIN DENTED. THE SKIN WAS REPAIRED IAW SRM 52-05, PAGE 2.

Part: DOUBLER — CRACKED (FWD CARGO DR) · airframe 50,072 hrs · 39,347 cycles

INSPECTION FOUND A 3" CRACK IN EXISTING DOUBLER REPAIR AT LOWER FORWARD CARGO DOOR. THE EXISTING DOUBLER WAS REMOVED AND THE CRACK WAS STOP DRILLED IAW SRM 51-10-4. A NEW DOUBLER WAS INSTALLED IAW SRM 52-33, FIGURE 1, 51-10-3, 51-10-4, AND 51-30-4.

Part: WEB — CORRODED (FS 336) · airframe 50,072 hrs · 39,347 cycles

INSPECTION FOUND FORWARD PIT(TORQUE BOX) FWD CLOSEOUT AT LIGHTENING HOLE(SLANT PANEL) CORRODED AT AND AROUND FASTENER HOLES AT FS 336. REMOVED FITTING, WEB, AND ANGLE IAW SRM 51-30-1 AND 51-30-2. A NEW WEB AND ANGLE WERE INSTALLED IAW SRM 51-10-4, 51-10-3, AND 51-30-2. INSTALLED FITTING IAW SRM 51-30-1.

Part: SKIN — GOUGED (PANEL #1613) · airframe 50,072 hrs · 39,347 cycles

INSPECTION FOUND LOWER SURFACE OF SKIN PANEL #1613 GOUGED AT R/H I/B FLAP T/E AREA. THE PANEL SKIN WAS REMOVED AND NEW SKIN WAS INSTALLED IAW SRM 51-30-2, 57-50-9, AND 51-10-3.

Part: ANGLE — CORRODED (FS 1338) · airframe 50,072 hrs · 39,347 cycles

INSPECTION FOUND JACK SUPPORT ANGLE CORRODED IN CHANNEL AREA AT BOTTOM OF APB, FS 1338, LONGERON 30. THE JACK SUPPORT ANGLE AND VERTICAL CHANNEL STRINGER TIE FITTINGS WERE REMOVED IAW SRM 51-30-2 AND 51-30-5. A NEW ANGLE WAS INSTALLED WITH TIE FITTINGS IAW SRM 51-10-4, 51-10-3, 51-30-2, AND 51-30-5.

Part: PAN — CORRODED (FWD CARGO DR) · airframe 50,072 hrs · 39,347 cycles

INSPECTION FOUND FORWARD PIT DOOR PAN BETWEEN TWO LOWER STOPS AT DRAIN HOLE CORRODED. THE CORRODED AREA WAS CUT OUT IAW SRM 53-05, FIGURE 44. A NEW LOWER PAN AND REPAIR ANGLES WERE INSTALLED IAW SRM 51-10-4, 53-05, FIGURE 44, 51-30-1, 51-30-2, 51-30-5, AND 51-10-3.

Part: WEB — CORRODED (FUSELAGE) · airframe 50,072 hrs · 39,347 cycles

INSPECTION FOUND MAIN CABIN CUSP WEB CORRODED AT FS 202-218, RBL 54. THE WEB WAS REMOVED AND A NEW WEB WAS INSTALLED IAW SRM 51-30-02, 51-10-4, AND 51-10-3.

Part: FLOOR PANEL — PUNCTURED (STA 256-313) · airframe 50,072 hrs · 39,347 cycles

INSPECTION FOUND R/H CABIN FLOOR PANEL PUNCTURED AT STA 256-313 SIDEWALL SUPPORT STRUCTURE. THE FLOOR PANEL WAS REMOVED AND A NEW PANEL WAS INSTALLED IAW SRM 51-30-1, 51-10-4, AND ECRA 5320-01265.

Part: WEB — CORRODED (FUSELAGE) · airframe 50,072 hrs · 39,347 cycles

INSPECTION FOUND CUSP WEB CORRODED AT LOWER CORNER FORWARD END OF R-1 DOOR JAMB, FS 160 - 238. THE LOWER DOOR PAN, TWO TORQUE BOX WEB PANELS, STRAPS, AND COMPOSITE CHANNEL WERE REMOVED TO GAIN ACCESS. THE CUSP WEB WAS REPLACED IAW SRM 53-05, FIGURE 55. REINSTALLED ALL REMOVED PANELS AND PARTS IAW SRM 51-30-2.

Part: WEB — CORRODED (FUSELAGE) · airframe 50,072 hrs · 39,347 cycles

INSPECTION FOUND FORWARD ENTRY SUBFLOOR CORRODED AT FS 160 - 200, RBL 56. THE FLOOR SUPPORTS AND WEB SUPPORTS WERE REMOVED TO GAIN ACCESS TO SUBFLOOR. THE SUBFLOOR WAS REMOVED AND A NEW SUBFLOOR WAS INSTALLED WITH WEB AND FLOOR SUPPORTS IAW SRM 53-14-1, 51-30-02, 51-30-05, AND 51-30-08.

Part: CARGO TRACK — CORRODED (FUSELAGE) · airframe 50,072 hrs · 39,347 cycles

INSPECTION FOUND FORWARD PIT RT SIDE CARGO TIE DOWN TRACK CORRODED AT LOWER SIDE OF FASTENER HOLES FROM FS 218 TO FORWARD DOOR FRAME. THE TIE DOWN TRACK AND ATTACHING ANGLE WERE REMOVED AND A NEW TRACK AND ATTACH ANGLE WERE INSTALLED IAW SRM 51-30-2 AND 51-30-1.

Part: FLOOR SUPPORT — CORRODED (FUSELAGE) · airframe 50,072 hrs · 39,347 cycles

INSPECTION FOUND FLOOR SUPPORT IN CENTER CARGO PIT CORRODED ON UPPER SURFACE AT FS 636 FROM LONGERON 29R-28L. THE FLOOR SUPPORT WAS REMOVED AND A NEW FLOOR SUPPORT WAS INSTALLED IAW SRM 51-30-2.

Part: FLOOR SUPPORT — CORRODED (FUSELAGE) · airframe 50,072 hrs · 39,347 cycles

INSPECTION FOUND FLOOR SUPPORT CORRODED AT FS 160 - 195, LBL 56. THE FLOOR SUPPORT WAS REMOVED AND A NEW FLOOR SUPPORT WAS INSTALLED IAW SRM 51-10-4 AND 51-30-2.

Part: WEB — CORRODED (FUSELAGE) · airframe 50,072 hrs · 39,347 cycles

INSPECTION FOUND LT FLOOR CUSP WEB BEHIND LAV AREA CORRODED AT FS 218 - 228, LBL 45 - 56. THE CUSP WEB WAS REMOVED AND A NEW WEB WAS INSTALLED IAW SRM 51-30-2, 51-30-5, 51-30-8, 51-10-3, AND 51-10-4.

Part: FLOOR SUPPORT — CORRODED (FUSELAGE) · airframe 50,072 hrs · 39,347 cycles

INSPECTION FOUND FLOOR SUPPORT CORRODED AT FS 157 - 200, RBL 6. THE FLOOR SUPPORT WAS REMOVED AND A NEW FLOOR SUPPORT WAS INSTALLED IAW SRM 51-30-4, 51-10-1, AND 51-10-3.

Part: FLOOR SUPPORT — CRACKED (FUSELAGE) · airframe 50,072 hrs · 39,347 cycles

INSPECTION FOUND A 6 INCH CRACK IN COCKPIT CENTER FLOORBOARD CENTER FLOOR SUPPORT AT FS 140, BL 0. THE FLOOR SUPPORT WAS REMOVED AND A NEW FLOOR SUPPORT WAS INSTALLED IAW SRM 51-30-2, 51-10-4, AND 51-10-3.

Part: FLOOR SUPPORT — CORRODED (FUSELAGE) · airframe 50,072 hrs · 39,347 cycles

INSPECTION FOUND FLOOR SUPPORT CORRODED AT FS 160 - 196, LBL 44. THE FLOOR SUPPORT WAS REMOVED AND A NEW FLOOR SUPPORT WAS INSTALLED IAW SRM 51-10-4, 51-10-3, AND 51-30-2.

Part: WEB — CRACKED (FUSELAGE) · airframe 50,072 hrs · 39,347 cycles

INSPECTION FOUND CUSP WEB CRACKED IN TWO PLACES AT FS 218 - 238, RBL 54. THE WEB WAS REMOVED AND A NEW WEB WAS INSTALLED IAW SRM 51-30-2 AND 51-30-4.

Part: FLOOR SUPPORT — CORRODED (FUSELAGE) · airframe 50,072 hrs · 39,347 cycles

INSPECTION FOUND FLOOR SUPPORT CORRODED AT FS 157 - 198, RBL 45. THE FLOOR SUPPORT WAS REMOVED AND A NEW FLOOR SUPPORT WAS INSTALLED IAW SRM 51-10-4, 51-10-3, AND 51-30-2.

Part: SKIN — DENTED (FS 389) · airframe 50,072 hrs · 39,347 cycles

INSPECTION FOUND L/H FUSELAGE EXTERNAL SKIN CREASED AND DENTED AT FS 389, LONGERON 22L. THE DAMAGED AREA WAS REFORMED AND A DOUBLER WAS INSTALLED IAW SRM 51-10-2, 51-10-4, AND 51-10-3.

Part: FLOOR PANEL — CRACKED (FS 826-927) · airframe 50,072 hrs · 39,347 cycles

INSPECTION FOUND L/H O/B FLOOR PANEL CRACKED AROUND SCREW HOLES AT BOTH ENDS, STA 826-927. A DOUBLER WAS INSTALLED AT EACH END IAW SRM 53-01, FIGURE 4 AND 51-10-3.

Part: FLOOR PANEL — CORRODED (PANEL "F") · airframe 50,072 hrs · 39,347 cycles

INSPECTION FOUND CABIN FLOOR PANEL "F" CORRODED AROUND FASTENER HOLES. THE PANEL WAS REPLACED IAW SRM 53-21-0 AND 51-10-3.

Part: SHEAR TIE — CRACKED (FS 370) · airframe 50,072 hrs · 39,347 cycles

INSPECTION FOUND A 1" CRACK IN FORWARD CARGO SHEAR TIE AT FS 370, LONGERON 22-23L. THE CRACKED AREA WAS REMOVED AND A REPAIR DOUBLER WAS INSTALLED IAW SRM 53-01, FIGURE 7, 53-03, FIGURE 7, AND 51-10-3.

Part: ANGLE — CORRODED (FS 200-214) · airframe 50,072 hrs · 39,347 cycles

INSPECTION FOUND MAIN CABIN WEB ATTACH ANGLE CORRODED AT FS 200-214, LBL 54. THE ANGLE WAS REMOVED AND A NEW ANGLE WAS INSTALLED IAW SRM 51-10-3 AND 51-30-5.

Part: SKIN — DENTED (FS 569) · airframe 50,072 hrs · 39,347 cycles

INSPECTION FOUND R/H FUSELAGE EXTERNAL SKIN DENTED AT FS 579 BETWEEN LONGERONS 20R AND 21R. A REPAIR DOUBLER WAS INSTALLED IAW SRM 53-04, FIGURE 38.

Part: SEAT TRACK — CORRODED (FS 1070-1203) · airframe 50,072 hrs · 39,347 cycles

INSPECTION FOUND MAIN CABIN SEAT TRACK CORRODED AT FS 1070-1203, LBL 25. THE CORRODED SECTION OF SEAT TRACK WAS REMOVED AND A NEW SEAT TRACK WAS INSTALLED IAW SRM 53-05, FIGURE 4, 51-10-4, AND 51-10-3.

Part: WEB — CORRODED (FUSELAGE) · airframe 50,072 hrs · 38,347 cycles

INSPECTION FOUND LT FLOOR CUSP WEB CORRODED ON LOWER SURFACE AT FS 1117. THE CORRODED AREA WAS REMOVED AND A NEW CUSP WEB WAS INSTALLED IAW SRM 51-30-2, 51-10-4, 51-10-3, AND 51-30-1.

Part: SKIN — DENTED (FS 370) · airframe 50,072 hrs · 39,347 cycles

INSPECTION FOUND R/H EXTERNAL FUSELAGE SKIN DENTED AT FS 370 JUST BELOW LONGERON 20R. THE DENTED AREA WAS COLD WORKED AND A REPAIR DOUBLER WAS INSTALLED IAW SRM 53-04, FIGURE 38.

Part: FITTING — CORRODED (FS 1136) · airframe 50,072 hrs · 39,347 cycles

INSPECTION FOUND ATTACH FITTING(FORWARD OF L-2 DOOR) CORRODED AT FS 1136, LBL 56. THE FITTING WAS REMOVED AND A NEW FITTING WAS INSTALLED IAW SRM 51-30-1, 51-30-4, AND 51-10-3.

Part: SKIN — DENTED (FS 541) · airframe 50,072 hrs · 39,347 cycles

INSPECTION FOUND R/H FUSELAGE EXTERNAL SKIN DENTED AT FS 541 BETWEEN LONGERONS 20R AND 21R. A REPAIR DOUBLER WAS INSTALLED IAW SRM 53-04, FIGURE 38.

Part: WEB — CORRODED (FUSELAGE) · airframe 50,072 hrs · 39,347 cycles

INSPECTION FOUND MAIN CABIN CUSP WEB CORRODED AT FS 1174 - 1193, LBL 54. THE CORRODED AREA WAS REMOVED AND A NEW WEB WAS INSTALLED IAW SRM 51-30-2, 51-10-4, AND 51-10-3.

Part: ANGLE — CORRODED (AFT ENTRY DR) · airframe 50,072 hrs · 39,347 cycles

INSPECTION FOUND AFT ENTRY DOOR Z-ANGLE COMMON TO CUSP MEMBRANE CORRODED AT FS 1136-1174, LBL 48.5. THE Z-ANGLE WAS REMOVED AND A NEW ANGLE WAS INSTALLED IAW SRM 51-30-2 AND 51-10-4.

Part: CHANNEL — CORRODED (AFT ENTRY DR) · airframe 50,072 hrs · 39,347 cycles

INSPECTION FOUND AFT ENTRY DOOR SEAL AREA AFT HAT CHANNEL FOR THRESHOLD CORRODED. THE HAT CHANNEL WAS REMOVED AND A NEW CHANNEL WAS INSTALLED IAW SRM 51-30-2 AND 51-10-4.

Part: SEAT TRACK — CORRODED (FS 1097-1215) · airframe 50,072 hrs · 39,347 cycles

INSPECTION FOUND SEAT TRACK CORRODED AT FS 1097-1215, LBL 45. THE SEAT TRACK WAS REMOVED AND A NEW TRACK WAS INSTALLED IAW SRM 51-30-2, 51-10-4, AND 51-10-3.

Part: ANGLE — CORRODED (FS 1140) · airframe 50,072 hrs · 39,347 cycles

INSPECTION FOUND L/H MAIN CABIN T-ANGLE CORRODED AT FS 1140. THE T-ANGLE WAS REMOVED AND A NEW ANGLE WAS INSTALLED IAW SRM 51-10-3, 51-10-4, 51-10-5, AND 51-30-2.

Part: FLOOR PANEL — DELAMINATED (CABIN) · airframe 50,072 hrs · 39,347 cycles

INSPECTION FOUND CABIN FLOOR PANELS I & J AT LT FORWARD ENTRY DELAMINATED. THE FLOOR PANELS WERE REPLACED IAW ECRA 5320-01265.

Part: FLOOR PANEL — DELAMINATED (CABIN) · airframe 50,072 hrs · 39,347 cycles

INSPECTION FOUND CABIN FLOOR PANELS DELAMINATED AT FS 1174 - 1193, RIGHT I/B, FS 1174 - 1287, LEFT O/B, FS 1212 - 1287, CENTER, AND FS 1287 - 1338, CENTER. THE FLOOR PANELS WERE REPLACED IAW ECRA 5320-01265.

Part: FLOOR PANEL — DELAMINATED (CABIN) · airframe 50,072 hrs · 39,347 cycles

INSPECTION FOUND CABIN FLOOR PANELS DELAMINATED AT FS 693 - 769, RIGHT I/B, LEFT I/B, AND CENTER AND FS 769 - 826, CENTER. THE FLOOR PANELS WERE REPLACED IAW ECRA 5320-01265.

Part: FLOOR PANEL — DELAMINATED (CABIN) · airframe 50,072 hrs · 39,347 cycles

INSPECTION FOUND CABIN FLOOR PANELS DELAMINATED FS 1113 - 1155, LEFT I/B, FS 1117 - 1174, RIGHT I/B, FS 1155 - 1212, CENTER, AND FS 1193 - 1250, RIGHT I/B. THE FLOOR PANELS WERE REPLACED IAW ECRA 5320-01265.

Part: SKIN — DENTED (R/H WING I/B) · airframe 50,072 hrs · 39,347 cycles

INSPECTION FOUND R/H WING SKIN I/B LOWER SURFACE NICKED AND DENTED. NEW SKIN WAS FABRICATED AND INSTALLED IAW SRM 51-60-4 AND 51-30-2.

Part: FLOOR PANEL — DELAMINATED (FS 1041-1117) · airframe 50,072 hrs · 39,347 cycles

INSPECTION FOUND CABIN FLOOR PANEL DELAMINATED AT STA 1041-1117. THE FLOOR PANEL WAS REPLACED IAW ECRA 5320-01265.

Part: FITTING — CORRODED (FS 160) · airframe 50,072 hrs · 39,347 cycles

INSPECTION FOUND CABIN FRAME TO WEB FITTING CORRODED AT FS 160, RBL 56. THE FRAME FITTING WAS REMOVED AND REPLACED IAW SRM 51-30-01, 51-30-05, AND 51-10-4.

Part: SKIN — DENTED (FS 474) · airframe 50,072 hrs · 39,347 cycles

INSPECTION FOUND L/H FUSELAGE EXTERNAL SKIN DENTED AT FS 474 JUST ABOVE LONGERON 21L. A REPAIR DOUBLER WAS INSTALLED IAW SRM 53-04, FIGURE 3B.

Part: SKIN — DENTED (FS 264) · airframe 50,072 hrs · 39,347 cycles

INSPECTION FOUND L/H FUSELAGE EXTERNAL SKIN DENTED AT FS 264 JUST BELOW LONGERON 23L. A REPAIR DOUBLER WAS INSTALLED IAW SRM 53-04, FIGURE 38, 51-10-3, AND 51-30-2.

Part: FLOOR PANEL — DELAMINATED (COCKPIT) · airframe 50,072 hrs · 39,347 cycles

INSPECTION FOUND COCKPIT FLOOR PANELS B,C,D,&E DELAMINATED. THE FLOOR PANELS WERE REPLACED IAW ECRA 5320-01265.

Part: FLOOR PANEL — DELAMINATED (CABIN) · airframe 50,072 hrs · 39,347 cycles

INSPECTION FOUND CABIN FLOOR PANELS DELAMINATED AT FS 1003 - 1079, LEFT O/B, AND FS 1250 - 1309, RIGHT I/B. THE FLOOR PANELS WERE REPLACED IAW ECRA 5320-01265.

Part: FLOOR PANEL — DELAMINATED (CABIN) · airframe 50,072 hrs · 39,347 cycles

INSPECTION FOUND CABIN FLOOR PANELS DELAMINATED AT FS 828 - 864 (LEFT I/B), FS 864 - 886 (RIGHT I/B), AND FS 864 - 927 (RIGHT I/B). THE PANELS WERE REPLACED IAW ECRA 5320-01265.

Part: FLOOR PANEL — DELAMINATED (CABIN) · airframe 50,072 hrs · 39,347 cycles

INSPECTION FOUND CABIN ENTRY FLOOR PANELS H&K DELAMINATED. THE FLOOR PANELS WERE REPLACED IAW ECRA 5320-01265.

Part: FLOOR PANEL — DELAMINATED (CABIN) · airframe 50,072 hrs · 39,347 cycles

INSPECTION FOUND CABIN FLOOR PANELS DELAMINATED AT FS 828 - 864, RIGHT I/B, AND FS 875 - 886, LEFT I/B. THE FLOOR PANELS WERE REPLACED IAW ECRA 5320-01265.

Part: FLOOR PANEL — DELAMINATED (CABIN) · airframe 50,072 hrs · 39,347 cycles

INSPECTION FOUND CABIN FLOOR PANELS DELAMINATED AT FS 927 - 1003, RIGHT I/B, FS 946 - 1003, CENTER, AND FS 1003 - 1079, RIGHT I/B. THE FLOOR PANELS WERE REPLACED IAW ECRA 5320-01265.

Part: FLOOR PANEL — DELAMINATED (CABIN) · airframe 50,072 hrs · 39,347 cycles

INSPECTION FOUND CABIN FLOOR PANELS DELAMINATED AT FS 160 - 196 (PANELS F&G) AND AT FS 196 - 256 (PANELS M,N, AND O). THE FLOOR PANELS WERE REPLACED IAW ECRA 5320-01265.

Part: SKIN — DENTED (FS 275) · airframe 50,072 hrs · 39,347 cycles

INSPECTION FOUND R/H FUSELAGE SKIN DENTED AT FS 275, LONGERON 24R. THE DENTED AREA WAS REFORMED IAW SRM 51-10-2. A REPAIR DOUBLER WAS INSTALLED IAW SRM 53-04, FIGURE 38, SHEET 22, 51-10-3, AND 51-10-2.

Part: WEB — CRACKED (FUSELAGE) · airframe 50,072 hrs · 39,347 cycles

INSPECTION FOUND A 2 INCH CRACK IN MAIN CABIN CUSP WEB AT FS 1303, LBL 56. THE CRACK WAS STOP DRILLED IAW SRM 53-01, FIGURE 2. A DOUBLER REPAIR WAS INSTALLED IAW SRM 53-05, FIGURE 96, 51-10-4, 51-10-3, AND 51-30-2.

Part: FLOOR SUPPORT — CORRODED (FUSELAGE) · airframe 50,072 hrs · 39,347 cycles

INSPECTION FOUND MAIN CABIN FLOOR SUPPORT CORRODED AT FS 1155, LBL 22-45. THE FLOOR SUPPORT WAS REMOVED AND A NEW SUPPORT WAS INSTALLED IAW SRM 51-30-2, 53-11-0, AND 51-10-3.

Part: SKIN — DAMAGED (FUSELAGE) · airframe 50,072 hrs · 39,347 cycles

INSPECTION FOUND FUSELAGE SKIN CREASED AT FS 503, LONGERON 22R. RIVETS WERE REMOVED AND THE SKIN WAS COLD FORMED IAW SRM 51-30-2 AND 53-04. A DOUBLER WAS INSTALLED IAW SRM 51-10-4, 51-10-3, AND 53-04, FIGURE 38, SHEET 22.

Part: WEB — CORRODED (FUSELAGE) · airframe 50,072 hrs · 39,347 cycles

INSPECTION FOUND MAIN CABIN CUSP WEB CORRODED AT FS 200 - 218, LBL 20. THE CORRODED AREA WAS CUT OUT IAW SRM 53-01, FIGURE 1, SHEET 1. A DOUBLER WAS INSTALLED IAW SRM 53-01, FIGURE 1, 51-10-4, 51-10-3, 51-30-2, AND 51-30-8.

Part: SKIN — DAMAGED (FUSELAGE) · airframe 50,072 hrs · 39,347 cycles

INSPECTION FOUND RT FUSELAGE EXTERNAL SKIN CREASED AT FS 351, JUST BELOW LONGERON 23R. RIVETS WERE REMOVED AND THE SKIN WAS COLD FORMED IAW SRM 51-30-2 AND 53-04, FIGURE 38. A DOUBLER WAS INSTALLED IAW SRM 53-04, FIGURE 38 AND 51-10-3.

Part: WEB — CORRODED (FUSELAGE) · airframe 50,072 hrs · 39,347 cycles

INSPECTION FOUND MAIN CABIN CUSP WEB CORRODED UNDER PAN AT FS 140 - 160, RBL 45 - 55. THE DRAIN PAN WAS REMOVED AND THE CORRODED AREA WAS CUT OUT IAW SRM 51-30-1 AND 53-01, FIGURE 2. A DOUBLER WAS INSTALLED IAW SRM 53-14-01, 51-10-3, AND 51-30-2. THE DRAIN PAN WAS REINSTALLED IAW SRM 51-30-1.

Part: SUPPORT — CORRODED (FS 148-160) · airframe 50,072 hrs · 39,347 cycles

INSPECTION FOUND MAIN CABIN PAN SUPPORT CORRODED AT FS 148-160, RBL 54. THE SUPPORT WAS REMOVED AND A NEW SUPPORT WAS INSTALLED IAW SRM 51-30-2, 53-11, FIGURE 22, 51-10-4, AND 51-10-3.

Part: SKIN — DAMAGED (FUSELAGE) · airframe 50,072 hrs · 39,347 cycles

INSPECTION FOUND RT FUSELAGE EXTERNAL SKIN CREASED AT FS 370, JUST BELOW LONGERON 19R. THE AREA WAS COLD WORKED AND A DOUBLER WAS INSTALLED IAW SRM 51-10-3 AND 53-04, FIGURE 38, SHEET 22.

Part: WEB — CRACKED (FUSELAGE) · airframe 50,072 hrs · 39,347 cycles

INSPECTION FOUND A 4 INCH CRACK IN MAIN CABIN CUSP WEB AT FS 1245, LBL 56. THE CRACK WAS STOP DRILLED IAW SRM 53-01, FIGURE 1. A DOUBLER WAS INSTALLED IAW SRM 51-10-4, 51-10-3, 51-30-2, AND 53-01, FIGURE 1.

Part: FLOOR SUPPORT — CORRODED (FUSELAGE) · airframe 50,072 hrs · 39,347 cycles

INSPECTION FOUND LT LAV WALL AND FLOOR SUPPORT CORRODED AT FS 1303 - 1338. THE FLOOR SUPPORT WAS REMOVED AND A NEW FLOOR SUPPORT WAS INSTALLED IAW SRM 51-30-1, 51-10-4, AND 51-10-3.

Part: WEB — CRACKED (FUSELAGE) · airframe 50,072 hrs · 39,347 cycles

INSPECTION FOUND A 6 INCH CRACK IN MAIN CABIN CUSP WEB AT FS 1198, LBL 56. A DOUBLER WAS INSTALLED IAW SRM 51-30-2, 53-01, FIGURE 2, AND 51-10-3.

Part: SKIN — DAMAGED (FUSELAGE) · airframe 50,072 hrs · 39,347 cycles

INSPECTION FOUND LT FUSELAGE EXTERNAL SKIN CREASED FORWARD OF AOA VANE AT FS 70. A NEW DOUBLER WAS INSTALLED IAW SRM 53-01, FIGURE 2, 51-10-4, 51-10-3, AND 51-30-2.

Part: BUNGEE CYLINDER — DEFECTIVE (NLG) · airframe 49,495 hrs · 39,034 cycles

WHEN GEAR WAS LOWERED FOR LANDING ON APPROACH TO ORD THREE RED UNSAFE LIGHTS WERE ILLUMINATED. A GO-AROUND WAS PERFORMED AND QRH PROCEDURES WERE ACCOMPLISHED WITH SUCCESSFUL GEAR EXTENSION. THE AIRCRAFT LANDED WITHOUT INCIDENT. MAINTENANCE TROUBLESHOOTING FOUND THE NOSE GEAR NOT EXTENDING HYDRAULICALLY. MAINTENANCE FOUND THE NOSE GEAR BUNGEE CYLINDER AT FAULT. THE BUNGEE CYLINDER WAS REMOVED AND REPLACED IAW MM 32-32-7. THE LANDING GEAR CONTROL VALVE WAS REPLACED AS A PRECAUTIONARY MEASURE AND THE SYSTEM WAS TESTED IAW MM 32-32-01.

Part: BATTERY — DISCHARGED (CABIN)

INSPECTION FOUND FORWARD UPPER AREA OF EMERGENCY PATH LIGHTS INOPERATIVE. MAINTENANCE FOUND BATTERIES FAILED IN POWER SUPPLY.. THE POWER SUPPLY WAS REPLACED IAW MM 33-53-00.

Part: SKIN — DELAMINATED (LT SPOILER)

INSPECTION FOUND LEFT WING NR 1 O/B SPOILER DELAMINATED. THE SPOILER WAS REMOVED AND REPLACED IAW MM 27-61-01.

Part: LONGERON — CORRODED (BS 256-275)

INSPECTION FOUND FORWARD CARGO COMPARTMENT LONGERON 30 CORRODED BETWEEN STA 256 AND 275. THE LONGERON SECTION WAS REMOVED AND REPLACED IAW SRM 53-02, FIGURE 14.

Part: LONGERON — CORRODED (BS 465-484)

INSPECTION FOUND LONGERON 30 CORRODED ON O/B SIDE IN FORWARD CARGO COMPARTMENT BETWEEN STA 465 AND 484. THE LONGERON SECTION WAS REPLACED IAW SRM 53-02, FIGURE 18.

Part: TAB — DENTED (RUDDER)

INSPECTION FOUND RT SIDE OF RUDDER TAB DENTED. THE TAB WAS REMOVED AND REPAIRED IAW SRM 55-04, PARAGRAPH 2. THE TAB WAS BALANCED AND REINSTALLED IAW MM 27-20-02.

Part: SEAT TRACK — CORRODED (BS 1155-1174)

INSPECTION FOUND LEFT O/B SEAT TRACK CORRODED FROM STA 1155 TO 1174. THE SEAT TRACK WAS REMOVED AND REPLACED IAW SRM 53-05, FIGURE 4 AND SRM 51-30-2.

Part: PROX SENSOR — INOPERATIVE (RT MLG)

THE RT MLG GREEN LIGHT FLICKERED WHEN GEAR WAS EXTENDED ON APPROACH TO EWR. THE EMERGENCY GEAR HANDLE WAS PULLED AND THE GREEN LIGHT ILLUMINATED STEADILY FOR A NORMAL LANDING. THE GROUND PROXIMITY SENSOR WAS CLEANED. A PROXIMITY SENSOR TEST AND EVALUATION FLIGHT WERE CONDUCTED WITH OPERATION AND INDICATIONS CHECKING GOOD.

Part: STARTER — FAILED (NR 1 ENGINE)

THE A START VALVE LIGHT ILLUMINATED AFTER TAKEOFF FROM CLE. THE LIGHT EXTINGUISHED AFTER ABOUT 30 SECONDS. ENGINE POWER WAS BEING REDUCED, CROSSFEED WAS CLOSED, AND HP BLEED WAS ON HIGH. THE FLIGHT LANDED AT EWR WITHOUT FURTHER PROBLEM. MAINTENANCE FOUND THE NR 1 ENGINE STARTER FAILED. THE STARTER AND STARTER VALVE WERE REMOVED AND REPLACED. THE VENDOR WAS UNABLE TO DETERMINE CAUSE OF FAILURE. THE STARTER WAS FOUND BEYOND ECONOMICAL REPAIR. THE VENDOR FOUND NO TROUBLE WITH THE STARTER SHUTOFF VALVE. IT WAS NOTED, HOWEVER, THAT THE VALVE HAD BEEN IDENTIFIED AS A CHRONIC UNIT.

Part: BRACKET — CRACKED (CARGO DOOR)

INSPECTION FOUND A .5 INCH CRACK IN T-FITTING BRACKET INSIDE FORWARD BAGGAGE DOOR. THE BRACKET WAS REMOVED AND REPLACED IAW SRM 51-00.

Part: FLOOR TRACK — CORRODED (BS 207)

INSPECTION FOUND NR 2 GALLEY OUTBOARD ATTACH FLOOR TRACK AT STA 207 CORRODED. THE CORRODED SECTION WAS REMOVED, A REPLACEMENT SECTION WAS FABRICATED AND INSTALLED IAW SRM 53-05, FIGURE 4F.

Part: SUPPORT — CORRODED (BS 1155-1212)

INSPECTION FOUND FLOOR SUPPORT CORRODED JUST INSIDE DOORWAY WEB AT FS 1155 TO 1212. THE FLOOR SUPPORT WAS REMOVED AND A REPLACEMENT SUPPORT WAS FABRICATED AND INSTALLED IAW SRM 51-30-2 AND 51-10-3.

Part: SUPPORT — CORRODED (BS 1212)

INSPECTION FOUND FLOOR SUPPORT CORRODED IN AFT BAGGAGE COMPARTMENT AT FS 1212 BETWEEN LONGERON 29R AND 28L. THE FLOOR SUPPORT WAS REMOVED AND REPLACED IAW SRM 51-00 AND 51-30-2.

Part: STRINGER — CRACKED (BS 275)

INSPECTION FOUND A 2 INCH CRACK IN STRINGER 17L AT STA 275. REPAIRED IAW SRM 53-02.

Part: FRAME — CRACKED (BS 1446)

INSPECTION FOUND 1/4 CRACKS AT HI-LOK FASTENERS AT CANTED BULKHEAD TO LONGERON ATTACH AREAS, FS 1446, LONGERONS 2R, 3R, AND 4R. REMOVED AND REPLACED FRAME CHORD IAW SRM 53-03.

Part: BRACKET — CRACKED (LT AILERON)

INSPECTION FOUND A .25 INCH CRACK IN LT AILERON NR 4 HINGE BRACKET. THE HINGE BRACKET WAS REMOVED AND REPLACED IAW SRM 51-10-01 AND MM 27-10-0.

Part: BULKHEAD WEB — CRACKED (BS 1463)

INSPECTION FOUND THREE CRACKS IN CANTED BULKHEAD WEB AT FS 1463 BELOW LONGERON 6R IN THE AFT ACCESSORY COMPARTMENT. THE CRACKS MEASURED FROM 1 TO 2 INCHES IN LENGTH. A NEW WEB WAS FABRICATED AND INSTALLED IAW SRM 53-14-4.

Part: RIB — CRACKED (WS 30)

INSPECTION FOUND A 2 INCH CRACK IN LT WING LEADING EDGE RIB AT XRS 30. THE CRACK WAS LOCATED AT FORWARD LOWER AREA BETWEEN NR 2 AND NR 3 SLAT TRACKS. THE CRACK WAS STOP DRILLED, A DOUBLER WAS FABRICATED AND INSTALLED IAW SRM 57-01-0 AND 51-30-0.

Part: SKIN — DENTED (BS 220)

INSPECTION FOUND LT FUSELAGE SKIN DENTED AT FS 220 BETWEEN LONGERONS 18L AND 19L. THE DENTED AREA WAS CUT OUT. FILLER AND DOUBLER WERE FABRICATED AND INSTALLED IAW SRM 53-04.

Part: SKIN — DENTED (BS 235)

INSPECTION FOUND A DENT IN LT FUSELAGE SKIN AT FS 235 BETWEEN LONGERONS 18L AND 16L, ABOVE CUSP LINE. THE SKIN SECTION WAS REMOVED AND REPLACED IAW ECRA 5330-02445.

Part: DOUBLER — CRACKED (NLG DOORWAY)

INSPECTION FOUND A .25 INCH CRACK IN DOUBLER AT CUTOUT FOR RIGHT AFT NOSE WHEEL WELL DOOR AFT HINGE. A .375 INCH CRACK WAS FOUND IN DOUBLER AT CUTOUT FOR LEFT AFT NOSE WHEEL WELL DOOR AFT HINGE. THE DOUBLERS WERE REMOVED, REPLACEMENT DOUBLERS WERE FABRICATED AND INSTALLED IAW SRM 53-05 AND 53-10-3.

Part: DOUBLER — CRACKED (AFT LAV PANEL)

INSPECTION FOUND A .5 INCH CRACK AT UPPER CORNERS AND LOWER FORWARD CORNER OF AFT LAV SERVICE PANEL CUTOUT. THE CRACKED DOUBLERS WERE REMOVED, NEW DOUBLERS WERE FABRICATED AND INSTALLED IAW ECRA 5330-01659.

Part: DOWNLOCK SENSOR — BROKEN WIRE (RT MLG)

THE RT MLG UNSAFE LIGHT REMAINED ILLUMINATED WITH GEAR EXTENSION ON APPROACH. THE GEAR WAS CYCLED WITH NO CHANGE. A TOWER FLY-BY WAS PERFORMED AND GEAR WAS VISUALLY CONFIRMED DOWN AND LOCKED. THE AIRCRAFT LANDED WITHOUT INCIDENT. MAINTENANCE FOUND A BROKEN WIRE ON RT MLG DOWNLOCK SENSOR. THE WIRE WAS REPAIRED AND INDICATIONS CHECKED GOOD.

Part: OIL TUBE — LEAKING (NR 1 ENGINE)

MSY - FLT 1865 - THE NR 1 ENGINE BEGAN TO LOSE OIL WHILE EN ROUTE FROM PBI TO IAH. THE AIRCRAFT WAS DIVERTED TO MSY WHERE IT LANDED WITHOUT INCIDENT. MAINTENANCE FOUND A LEAKING OIL TUBE TO NR 1 ENGINE. THE OIL TUBE WAS REPLACED WITH NEW SEALS INSTALLED. THE ENGINE WAS SERVICED WITH OIL. THE ENGINE WAS RUN AND LEAK CHECKS WERE GOOD. (X)