N958AT

Part: BOTTLE — LOW PRESSURE (TAILCONE SLIDE) · airframe 49,882 hrs · 34,472 cycles

TAIL CONE SLIDE BOTTLE IN THE RED. REMOVED SLIDE S/N 1277 & INSTALLED SLIDE S/N 1399 PER AMDS WORK CARD 2561-9006. (LP5175880)

Part: LENS — DAMAGED (EMERGENCY LIGHT) · airframe 46,534 hrs · 32,319 cycles

EMERGENCY EXIT COVER DIFFUSER LENS DAMAGED. REPAIRED THE LENS. OK FOR SERVICE.

Part: LONGERON — DAMAGED (FUSELAGE) · airframe 44,238 hrs · 30,669 cycles

LEFT FUSELAGE LONGERON L26 DAMAGED BETWEEN Y351 AND Y370. REMOVED DAMAGED SECTION, FABRICATED NEW STR FROM FACTORY SPLICE POINT Y380-Y408 TO NEW POINT Y351-Y370. OK TO TREAT AND PAINT. TREATED AND PAINTED IAW P/S 900-2-4, NR 2. OK TO INSTALL LONGERON L26 BETWEEN Y351 AND Y370. INSTALLED NEW LONGERON L26 IAW SRM 53-00-05. RII C/W, INSTALL OK.

Part: SUPPORT — CRACKED (FUSELAGE) · airframe 43,942 hrs · 30,447 cycles

CRACKED BULKHEAD DIVISOR SUPPORT, STA Y=655, X=22Z=-10 AT FORWARD CARGO COMPARTMENT. BULKHEAD DIVISOR SUPPORT STA Y=655, X=22 Z=-10 WAS REPAIRED WITH ER/A 547883-14, REV ORIGINAL AND ETI-17-16-093. CRACK 0.187" WEIGHT REPAIR, PARTS 0.32LB. ASSOCIATED ER/A 00-547883, ADDED FOR AC 9517.

Part: FITTING — CRACKED (FUSELAGE) · airframe 43,941 hrs · 30,446 cycles

CRACKED CLIP AT STA Y=1152 BETWEEN LONGERONS 3R/2R. CLIP WAS REPLACED IAW ER/A 547861-14 REV ORIGINAL.

Part: PAN — CRACKED (CARGO DOOR) · airframe 43,941 hrs · 30,446 cycles

CRACK ON OUTER PAN STA Y=954, BEAM 1 FORWARD EDGE AT AFT CARGO COMPARTMENT DOOR, C2, CARD 11, ZONE 810. PAN WAS REPAIRED IAW ETI-17-16-081 AND ER/A 547860-14, REV ORIGINAL. LONGERON CRACK 0.128".

Part: SKIN — WORN (RT WING) · airframe 43,941 hrs · 30,446 cycles

WORN RT WING LOWER SKIN BETWEEN STA SXR 69 AND XRS 111.500. REPAIR OF WORN AREA AT RT WING LOWER SKIN WAS PERFORMED WITH ER/A 547869-14, REV ORIGINAL.

Part: BEAM — CRACKED (FUSELAGE) · airframe 43,941 hrs · 30,446 cycles

CRACKED BEAM 1 ON FORWARD EDGE OF AFT CARGO COMPARTMENT STA Y=954, REF CARD 11, ZONE 810, CARD 45 ZONE 810. BEAM 1 WAS REPAIRED IAW ETI-17-16-081 REV 2 AND ER/A 547860-14, REV ORIGINAL. LONG CRACK 0.156".

Part: BEAM — CRACKED (NLG WW) · airframe 43,941 hrs · 30,446 cycles

CRACKED DOOR JAMB BEAM STA Y=47, RT SIDE AT NLG WW. DOOR JAMB BEAM WAS REPAIRED. ER/A 547858-14, REV ORIGINAL.

Part: DOOR FRAME — CORRODED (FUSELAGE) · corrosion level 2 · airframe 43,941 hrs · 30,446 cycles

CORROSION ON LOWER DOOR JAMB FROM STA Y=954 TO Y=994 AT AFT CARGO COMPARTMENT, SM, C2, CARD 27, ZONE 810. DUE TO EXCESIVE CORROSION WAS REPLACED IAW SRM 53-20-15, FIG 201, 51-41-05, AND 51-41-02. RII COMPLETED.

Part: SKIN — CRACKED (CARGO DOOR) · airframe 43,941 hrs · 30,446 cycles

WEAR AND CRACK ON OUTER SKIN STA Y=972 BETWEEN BEAM 1 AND 2 JUST ABOVE OF HANDLE RELEASE AT AFT CARGO COMPARTMENT DOOR. SKIN STA Y=972 BETWEEN BEAM 1 AND 2 JUST ABOVE OF HANDLE RELEASE WAS REPAIRED IAW SRM 52-30-01, FIG 201, LENGTH CRACK 0.300".

Part: LONGERON — CORRODED (FUSELAGE) · corrosion level 2 · airframe 43,941 hrs · 30,446 cycles

EXCESSIVE CORROSION ON LONGERON 630 BETWEEN STA 960-1010, IN REF CARD 10, ZONE 180. SECTION OF LONGERON WAS REPLACED IAW SRM 53-20-05, REPAIR 1, 51-41-05, 51-40-08, AND 51-10-04, PAR 15, 21, 26, AND 37. RII COMPLETED.

Part: PAN — CRACKED (FUSELAGE) · airframe 43,941 hrs · 30,446 cycles

CRACKED PAN BETWEEN BEAM 7/8, STA 161.3 AT FWD ENTRY DOOR, CARD 18, ZONE 820. PAN WAS REPAIRED IAW 717, ETI-17-16-073, REV 1 AND ER/A 547853-14, REV ORIGINAL.

Part: SKIN — WORN (FUSELAGE) · airframe 43,941 hrs · 30,446 cycles

WEAR ON FUSELAGE SKIN IN LONGERON 20RT BETWEEN STA Y=520-526, SM, CARD 27, ZONE 110. DAMAGE WAS REPAIRED IAW ETI-17-16-084, REV 1 AND ER/A 547867-14, REV ORIGINAL. RII COMPLETED.

Part: CHANNEL — CRACKED (RT MLG DOOR) · airframe 43,941 hrs · 30,446 cycles

CRACKED FORWARD CHANNEL STA Y=757 AT RT MLG DOOR LOWER SECTION SM, MLG, CARD 1, ZONE 720. CHANNEL WAS REPAIRED IAW ETI-17-16-077 REV 1 AND ER/A 547857-14, REV ORIGINAL.

Part: ANGLE — CRACKED (CARGO DOOR) · airframe 43,941 hrs · 30,446 cycles

CRACK ON ANGLE STA Y=994, INNER SIDE BEAM 3 AT AFT CARGO COMPARTMENT DOOR. CRACKED ANGLE STA Y994 WAS REMOVED AND NEW ANGLE WAS INSTALLED IAW SRM 51-41-05. PARA 8, LONG CRACK 0.35".

Part: SKIN — WORN (FUSELAGE) · airframe 43,941 hrs · 30,446 cycles

WEAR ON FUSELAGE SKIN IN LONGERON 21RT BETWEEN STA Y=503-508,SM, CARD 28, ZONE 110. WEAR ON FUSELAGE SKIN IN LONGERON 21RT BETWEEN STA Y=503-508 OUT OF LIMITS. ORIGINAL THICKNESS 0.050" REMAINING THICKNESS 0.035", DAMAGE WAS REPAIRED IAW ETI-17-16-084, REV 1 AND ER/A 547867-14, REV ORIGINAL. IAW ER/A 547867-14, REV ORIGINAL SECTION II. RII COMPLETED.

Part: STOP FITTING — CRACKED (CARGO DOOR) · airframe 43,941 hrs · 30,446 cycles

CRACK ON DOOR STOP FITTING STA, Y=994, BEAM 3 AT AFT CARGO COMPARTMENT DOOR. DOOR STOP FITTING STA Y=994, BEAM 3 AT AFT CARGO COMPARTMENT DOOR WAS REPLACED IAW SRM 51-41-01 AND 51-41-05, IPC 52-33-01-01, FIG 01.

Part: ACCESS PANEL — CORRODED (WING) · corrosion level 2 · airframe 43,941 hrs · 30,446 cycles

CORROSION ON FUEL ACCESS PLATE 520JB COUNTERSINK. 2EA IN REF ORNRC 64, ACFT ZONE 000, CARD 110, ZONE 000, CORROSION WAS REMOVED IAW SRM 54-10-01, COUNTERSINK WERE MEASURED WITH 0.610", 0.607", AND 0.610". ADJACENT HOLES THEREFORE IS OUT OF LIMITS IAW SRM 57-10-01, PAR 5B, CONDITION II AND ACCESS WAS REPLACED.

Part: PAN — CRACKED (CARGO DOOR) · airframe 43,941 hrs · 30,446 cycles

CRACK ON INNER PAN STA Y=427 BEAM 1 AT FWD CARGO COMPARTMENT DOOR, SM, C1, CARD 33, ZONE 810. INNER PAN WAS REPAIRED IAW SRM 52-30-02, REPAIR 1, FIG 1, FIG 201, LONG CRACK 1.312". RII COMPLETED.

Part: INTERCOSTAL — CRACKED (FUSELAGE) · airframe 43,941 hrs · 30,446 cycles

CRACKED INTERCOSTAL BETWEEN Y=617 TO Y=636 X=0 AT CEILING AREA OF FWD CARGO COMPARTMENT. C1, SM, CARD 26, ZONE 120 CRACK ON INTERCOSTAL WAS REPAIRED IAW SRM 53-00-00, FIG 201, CRACK LENGTH 1.093".

Part: ACCESS PANEL — DAMAGED (RT PYLON) · airframe 43,941 hrs · 30,446 cycles

ELONGATED HOLE AND TOOL MARKS ON LOWER ACCESS 440 INBD AT RT PYLON SM, E/P, CARD 40, ZONE 000. TOOL MARKS AND ELONGATED HOLE WERE REPAIRED IAW SRM 54-00-00, FIG 201, SRM 51-10-04, PAR 15, 21.

Part: LONGERON — CORRODED (FUSELAGE) · corrosion level 2 · airframe 43,941 hrs · 30,446 cycles

EXCESSIVE CORROSION ON LONGERON 30 BETWEEN STA 218 TO 237 AT FWD CARGO COMPARTMENT IN REF CARD 15, ZONE 120, CARD 45, ZONE 120. DUE TO EXCESSIVE DAMAGED SECTION OF LONGERON 30 BETWEEN STA 150 TO 227 WAS REPLACED IAW SRM 53-10-05, 51-41-02, AND 51-41-05.

Part: ACCESS PANEL — CORRODED (WING) · corrosion level 2 · airframe 44,977 hrs · 31,178 cycles

CORROSION ON FUEL ACCESS PLATE 620QB COUNTERSINK. (1EA) CORROSION ON FUEL ACCESS PLATE 620QB COUNTERSINK WAS REMOVE AND MEASURED AND FOUND ONE HOLE OUT OF LIMITS .609". THEREFORE WAS REPAIRED WITH BUSHING PER SRM 57-10-01.

Part: ACCESS PANEL — CORRODED (WING) · corrosion level 2 · airframe 44,977 hrs · 31,178 cycles

CORROSION ON FUEL ACCESS PLATE 520GB COUNTERSINK. (2EA) CORROSION ON FUEL ACCESS PLATE 520GB COUNTERSINK WAS REMOVED AND MEASURE AND FOUND TWO HOLES OUT OF LIMITS .603" AND .606". THEREFORE WAS REPAIRED WITH BUSHINGS PER SRM 57-10-01.

Part: ACCESS PANEL — CORRODED (VERTICAL STAB) · corrosion level 2 · airframe 44,501 hrs · 30,851 cycles

CORROSION ON DORSAL FIN JUST ON SETTLEMENT AREA OF ACCESS PANEL 370 AL. FABRICATED NEW AND REPLACED IAW SRM 51-41-02, 51-20-09, 51-10-04 PAR 15 AND 21, AND DWG 5911432 REV "CF".

Part: ACCESS PANEL — CORRODED (WING) · corrosion level 2 · airframe 44,977 hrs · 31,178 cycles

CORROSION ON FUEL ACCESS PLATE 620PB COUNTERSINK. (2EA) CORROSION ON FUEL ACCESS PLATE 620PB COUNTERSINK WAS REMOVED AND MEASURE AND FOUND TWO HOLES OUT OF LIMITS .608" AND .613". THEREFORE WERE REPAIRED WITH BUSHINGS PER SRM 57-10-01.

Part: ACCESS PANEL — CORRODED (WING) · corrosion level 2 · airframe 44,977 hrs · 31,178 cycles

CORROSION ON FUEL ACCESS PLATE 620LB COUNTERSINK. (2EA) CORROSION ON FUEL ACCESS PLATE 620LB COUNTERSINK WAS REMOVED AND MEASURED AND FOUND TWO HOLES OUT OF LIMITS .608" AND .613". THEREFORE WAS REPAIRED WITH BUSHINGS PER SRM 57-10-01.

Part: FRAME — CRACKED (BS 693) · airframe 43,941 hrs · 30,446 cycles

CRACKED FRAME BS 693 BETWEE1 LONGERONS 26 & 27R. THE FRAME WAS REPLACED.

Part: ACCESS PANEL — CORRODED (WING) · corrosion level 2 · airframe 44,501 hrs · 30,851 cycles

CORROSION ON SETTLEMENT AND COUNTERSINK FUEL ACCESS PLATE 620HB. CORROSION ON SETTLEMENT AND COUNTERSINK AREA OF FUEL ACCESS PLATE 620HB WERE REMOVED AND MEASURED AND FOUND OUT OF LIMITS WITH 3 HOLES ADJACENT "0.556" "0.556" "0.556" THEREFORE WAS REPLACED PER SRM 51-10-04 AND 57-10-01.

Part: ACCESS PANEL — CORRODED (WING) · corrosion level 2 · airframe 44,501 hrs · 30,851 cycles

CORROSION ON SETTLEMENT AND COUNTERSINK FUEL ACCESS PLATE 520LB. CORROSION ON FUEL ACCESS PLATE 520LB WAS REMOVED IAW SRM 51-10-04 AND WAS MEASURED AND FOUND OUT OF LIMITS WITH 3 HOLES ADJACENT 0.553", 0.553", 0.553" THEREFORE WAS REPLACED PER SRM 51-10-04 AND 57-10-01.

Part: ACCESS PANEL — CORRODED (LT WING) · corrosion level 2 · airframe 44,977 hrs · 31,178 cycles

CORROSION ON SETTLEMENT AND COUNTERSINK LT FUEL TANK ACCESS PLATE 520FT. CORROSION ON SETTLEMENT AND COUNTERSINK AREA OF FUEL ACCESS PLATE 520FT WAS REMOVED AND MEASURED AND 4 COUNTERSINK WERE FOUND OUT OF LIMITS .664" .667" .665" .670" THEREFORE WERE REPAIRED WITH BUSHINGS AND SETTLEMENT AREA REMAINING THICKNESS IS .177" THEREFORE IS WITH LIMIT PER SRM 57-10-01 AND 51-10-04.

Part: ACCESS PANEL — CORRODED (WING) · corrosion level 2 · airframe 44,501 hrs · 30,851 cycles

CORROSION ON SETTLEMENT AND COUNTERSINK FUEL ACCESS PLATE 520HB. CORROSION ON SETTLEMENT AND COUNTERSINK AREA OF FUEL ACCESS PLATE 520HB WERE REMOVED AND MEASURED AND FOUND OUT OF LIMIT WITH 3 ADJACENT HOLES 0.563", 0.558", 0.555" THEREFORE WAS REPLACED PER SRM 51-10-04 AND 57-10-01.

Part: ACCESS PANEL — CORRODED (WING) · corrosion level 2 · airframe 44,501 hrs · 30,851 cycles

CORROSION ON COUNTERSINK FUEL ACCESS PLATE 620GB. CORROSION ON SETTLEMENT AND COUNTERSINK AREA OF FUEL ACCESS PLATE NR 620GB WERE REMOVED AND MEASURED AND FOUND OUT OF LIMIT WITH 3 HOLES ADJACENT 0.540", 0.560", 0.560" THEREFORE WAS REPLACED PER SRM 51-10-04 AND 57-10-01.

Part: BEAM — CRACKED (L1 DOOR) · airframe 43,941 hrs · 30,446 cycles

CRACKED FWD EDGE BEAM NR 7 AT L1 DOOR. BEAM WAS REPAIRED IAW SRM 52-10-02 REPAIR 13 FIGURE 202.

Part: ACCESS PANEL — CORRODED (WING) · corrosion level 2 · airframe 44,501 hrs · 30,851 cycles

CORROSION ON COUNTERSINK AND SETTLEMENT AREA OF FUEL ACCESS PLATE 620EB. CORROSION ON COUNTERSINK OF FUEL ACCESS PLATE 620 EB WAS REMOVED IAW SRM 51-10-04 AND WAS MEASURED MAX DIAMETER ALLOWED IS 0.532 AND MAX DIAMETER MEASURED IS 0.565 IN 3 HOLES ADJACENT THEREFORE IS OUT OF LIMITS IAW SRM 57-10-01. MAGNETIC DRIPLESS FUEL MEASURING STICK HOUSING WAS INTERCHANGE AT NEW ACCESS PLATE IAW AMM 28-42-01 AND FUEL ACCESS PLATE WAS REPLACED AND P/N WAS VERIFIED WITH IPC 57-23-01.

Part: ACCESS PANEL — CORRODED (WING) · corrosion level 2 · airframe 44,501 hrs · 30,851 cycles

CORROSION ON COUNTERSINK AND SETTLEMENT AREA OF FUEL ACCESS PLATE 620MB. CORROSION ON COUNTERSINK OF FUEL ACCESS PLATE 620MB WAS REMOVED IAW SRM 51-10-04 AND WAS MEASURED MAX DIAMETER ALLOWED IS 0.532" AND MAX DIAMETER MEASURE IS 0.58" IN 3 HOLES ADJACENT THEREFORE IS OUT OF LIMITS IAW SRM 57-10-01 CONDITION II (1)(A). REPLACE ACCESS PLATE AND VERIFIED WITH IPC 57-23-01.

Part: SKIN — CRACKED (BS 1037) · airframe 43,941 hrs · 30,446 cycles

CRACK ON EXTERNAL FUSELAGE SKIN BS 1037 BETWEEN LONGERONS 13 & 14L. THE SKIN WAS REPAIRED IAW ER/A 547828-14.

Part: ACCESS PANEL — CORRODED (WING) · corrosion level 2 · airframe 44,501 hrs · 30,851 cycles

CORROSION ON COUNTERSINK AND SETTLEMENT AREA OF FUEL ACCESS PLATE 620JB. CORROSION ON COUNTERSINK AND SETTLEMENT AREA OF FUEL ACCESS PLATE 620JB WERE REMOVED AND FOUND OUT OF LIMITS WITH 3 ADJACENT HOLES .555" .545" .545" THEREFORE WAS REPLACED PER SRM 51-10-04 AND 57-10-01 AMM 28-42-01.

Part: SKIN — CRACKED (BS 1022) · airframe 43,941 hrs · 30,446 cycles

CRACK ON EXTERNAL FUSELAGE SKIN BS 1022 BETWEE1 LONGERONS 3 - 14L. THE SKIN WAS REPAIRED IAW ER/A 547827-14.

Part: ACCESS PANEL — CORRODED (WING) · corrosion level 2 · airframe 44,501 hrs · 30,851 cycles

CORROSION ON SETTLEMENT AND COUNTERSINK FUEL ACCESS PLATE 520EB. CORROSION ON COUNTERSINK WAS REMOVED IAW SRM 51-10-04 AND WAS MEASURED AND FOUND OUT OF LIMITS WITH 3 ADJACENT HOLES 0.535" 0.554" AND .540" IAW SRM 57-10-01 MAGNETIC DRIPLESS FUEL MEASURING STICK HOUSING WAS INTERCHANGE AT NEW ACCESS PLATE IAW AMM 28-42-01 AND FUEL ACCESS PLATE WAS REPLACED AND P/N WAS VERIFIED WITH IPC 57-23-01.

Part: ACCESS PANEL — CORRODED (WING) · corrosion level 2 · airframe 44,501 hrs · 30,851 cycles

CORROSION ON SETTLEMENT AND COUNTERSINK FUEL ACCESS PLATE 520MB. CORROSION ON FUEL ACCESS PLATE WAS REMOVED IAW SRM 51-10-04 AND WAS MEASURED ON COUNTERSINK AND FOUND OUT OF LIMITS WITH 3 ADJACENT HOLES 0.554" 0.551" AND 0.549" IAW SRM 57-10-01. MAGNETIC DRIPLESS FUEL MEASURING STICK HOUSING WAS INTERCHANGE AT NEW ACCESS PLATE. ACCESS PLATE WAS REPLACED AND VERIFIED WITH IPC 57-23-01.

Part: ACCESS PANEL — CORRODED (WING) · corrosion level 2 · airframe 44,496 hrs · 30,845 cycles

CORROSION ON FUEL ACCESS PANEL COUNTERSINK & SETTLEMENT AREA. THE ACCESS PANEL CANNOT BE REPAIRED UNDER CONDITIONS I AND II THEREFORE WAS REPLACED IAW SRM 57-10-01 STEP 5, C(1).

Part: ACCESS PANEL — CORRODED (WING) · corrosion level 2 · airframe 44,496 hrs · 30,845 cycles

CORROSION ON FUEL ACCESS PANEL COUNTERSINK & SETTLEMENT AREA. THE ACCESS PANEL CANNOT BE REPAIRED UNDER CONDITIONS I AND II THEREFORE WAS REPLACED IAW SRM 57-10-01 STEP 5, C(1).

Part: FRAME — CRACKED (BS 693) · airframe 43,941 hrs · 30,446 cycles

CRACKED FRAME BS 693 BETWEEN LONGERONS 26 & 27L AT INNER SURFACE OF LOWER FUSELAGE. DAMAGE FRAME WAS REMOVED IAW SRM 51-41-02, 51-41-05, 51-41-03, NEW FRAME WAS DRILLED IAW SRM 51-40-08 AND WAS TREATED AND PAINTED IAW SRM 51-10-04 PER 21 AND 15, NEW FRAME WAS INSTALLED IAW SRM 51-41-02 AND 51-41-05.

Part: FRAME — CRACKED (BS 674) · airframe 43,941 hrs · 30,446 cycles

CRACKED FRAME BS 674 BETWEEN LONGERONS 25 & 26R . FRAME REMOVED IAW SRM 51-41-02, 51-41-05 AND 51-41-03, REPAIRED IAW SRM 51-70-11 REPAIR 1 AND INSTALLED IAW SRM 51-41-02 AND 51-41-05.

Part: FRAME — CRACKED (BS 674) · airframe 43,941 hrs · 30,446 cycles

CRACKED FRAME BS 674 BETWEEN LONGERONS 25 & 26L. THE FRAME WAS REMOVED IAW SRM 51-41-02, 51-41-05, 51-41-03, REPAIRED IAW SRM 51-70-11 REPAIR 1 AND INSTALLED IAW SRM 51-41-02 AND 51-41-05.

Part: CUSP WEB — CORRODED (BS 368) · corrosion level 2 · airframe 44,496 hrs · 30,845 cycles

CORROSION ON RT CUSP WEB BS 368. THE CUSP WEB WAS REPAIRED IAW SRM 53-00-55 REP. 4 FIG. 212

Part: SEAT TRACK — CORRODED (FUSELAGE) · corrosion level 2 · airframe 43,941 hrs · 30,446 cycles

CORROSION OUT OF LIMITS ON RT SEAT TRACK X=44 BETWEEN STA Y=589 TO 645 AT CABIN FLOOR STRUCTURE, CFS, IN REF TO ON RC 20, AC ZONE 200, CARD 74 ZONE 200. RT SEAT TRACK X=44, STA Y=589 TO 645 WAS REPLACED IAW SRM 53-20-52, FIG 1, 51-30-07, FIG 18, SRM 41-41-01. RII COMPLETED.

Part: PAN — WORN (DOOR) · corrosion level 2 · airframe 43,941 hrs · 30,446 cycles

WEAR RT PAN INTERNAL STRUCTURE NEAR LOWER HINGE ALSO LT SIDE AT AFT CABIEN PRESSURE BULKHEAD EMERGENCY EXIT DOOR. SM, CARD 15, ZONE 820. LT PAN INTERNAL STRUCTURE WAS REPAIRED IAW SRM 52-10-02, REP 15, FIG 201 AND RT PAN INTERNAL STRUCTURE WAS BLENDED OUT, UT WAS ACCOMPLISHED ORIGINAL THICKNESS 0.050". REMAINING THICKNESS 0.037, THEREFORE, IT IS OUT LIMITS AND RT SIDE WAS REPAIRED IAW SRM 52-10-2, PR 4 A, OPTION 1, FIG 201, REPAIR 16. EQUIPMENT: PANAMETRICS NDT. RII COMPLETED.

Part: CUSP WEB — CORRODED (FUSELAGE) · corrosion level 2 · airframe 43,941 hrs · 30,446 cycles

EXCESSIVE CORROSION ON RT CUSP WEB, STA Y=460 IN REF CARD 24, ZONE 200. CARD 79, ZONE 200. DUE TO EXCESSIVE DAMAGE CUSP WEB MUST BE REPAIRED. FASTENERS WERE REMOVED IAW SRM 51-41-02, PAR 7C, DAMAGE WAS REMOVED IAW SRM 53-00-55, HFEC INSPECTION WAS ACCOMPLISHED ALONG TRIM LINE, NO CRACKS WERE FOUND IAW NDT SPM 06-10-01. 001. REPAIR PARTS WERE FABRICATED IAW SRM 53-00-55, REPAIR PARTS WERE INSTALLED IAW SRM 53-00-55, AND CIC WAS APPLIED IAW SRM 51-10-04. RII COMPLETED.

Part: CUSP WEB — CORRODED (FUSELAGE) · corrosion level 2 · airframe 43,941 hrs · 30,446 cycles

EXCESSIVE CORROSION ON RT CUSP WEB STA Y=401 IN REF CARD 24, ZONE 200, CARD 78, ZONE 200. DUE EXCESSIVE DAMAGE WAS REPAIRED IAW SRM 53-00-55 FIG 225, SHEET 7 OF 10. HFEC INSPECTION WAS ACCOMPLISHED ON RT CUSP WEB, STA Y=401, NO CRACKS WERE FOUND AFTER TRIMMING OUT IAW NDT SPM 06-10-01.001, PHASE C2D, CN 925. RII COMPLETED.

Part: CUSP WEB — CORRODED (FUSELAGE) · corrosion level 2 · airframe 43,941 hrs · 30,446 cycles

EXFOLIATE CORROSION ON LT CUSP WEB FROM STA 976 TO 986, ON REF CARD 32, ZONE 200, CARD 85, ZONE 200. DAMAGE AREA ON LT CUSP WEB FROM STA 976 TO 986 WAS REMOVED AND REPAIRED IAW SRM 53-00-55, REPAIR 4. RII COMPLETED.

Part: CUSP WEB — CORRODED (FUSELAGE) · corrosion level 2 · airframe 43,941 hrs · 30,446 cycles

EXCESSIVE CORROSION ON RT CUSP WEB, STA Y=368, IN REF CARD 24, ZONE 200. CARD 77, ZONE 200. CUSP WEB WAS REPAIRED IAW SRM 53-00-55, REP 4, FIG 212, HFEC INSPECTION WAS ACCOMPLISHED AFTER DAMAGE REMOVAL, FITTING STRAP & SEAT TRACK WERE REMOVED AND INSTALLED IAW SRM 51-41-05, 51-41-01. CIC WAS APPLIED AT ZONE REPAIR IAW SRM 51-10-04.

Part: ACCESS PANEL — CORRODED (WING) · corrosion level 2 · airframe 43,941 hrs · 30,446 cycles

CORROSION ON COUNTERSINK AND SETTLEMENT AREA OF FUEL ACCESS PLATE 620 AT, AYP, CARD 32, ZONE 600. CORROSION ON COUNTERSINK WAS REMOVED ON FUEL ACCESS PLATE 620 AT IAW SRM 51-10-04 AND DAMAGE WAS FOUND AND FUEL ACCESS PLATE 620 AT WAS REPLACED DUE TO EXCESSIVE CORROSION.

Part: ACCESS PANEL — CORRODED (WING) · corrosion level 2 · airframe 43,941 hrs · 30,446 cycles

CORROSION ON SETTLEMENT AND COUNTERSINK OF FUEL ACCESS PLATE 520CB, SM, LW, CARD 60, ZONE 000. CORROSION ON SETTLEMENT AND COUNTERSINK AREA OF FUEL ACCESS PLATE NR 520CB WAS REMOVED AND MEASURED AND FOUND OUT OF LIMITS WITH 3 ADJACENT HOLES 0.535", 0.535", 0.540" THEREFORE WAS REPLACED IAW SRM 57-10-01 AND 51-10-04.

Part: ACCESS PANEL — CORRODED (WING) · corrosion level 2 · airframe 43,941 hrs · 30,446 cycles

CORROSION ON SETTLEMENT AND COUNTERSINK OF FUEL ACCESS PLATE NR 520 DB, SM, LW, CARD 58, ZONE 000. CORROSION ON SETTLEMENT AND COUNTERSINK OF FUEL ACCESS PLATE NR 520DB WAS REMOVED AND MEASURED AND FOUND OUT OF LIMITS WITH 3 ADJANCENT HOLES 0.551", 0.540", 0.550" THEREFORE WAS REPLACED IAW SRM 57-10-01 AND 51-10-04.

Part: PAN — CRACKED (EMERGENCY EXIT) · airframe 43,941 hrs · 30,446 cycles

CRACK ON INNER PAN FORWARD SIDE BETWEEN BEAM 4 TO 5 AT FORWARD LT OVERWING EMERGENCY EXIT, SM, CARD 9, ZONE 820. PAN WAS REPAIRED IAW SRM 52-20-02, FIG 201, LENGTH OF CRACK 0.750".

Part: CHANNEL — CRACKED (FLOOR PANEL) · airframe 43,941 hrs · 30,446 cycles

CRACKED CHANNEL OF FLOOR PANEL NR 222, SM, CARD 28, ZONE 000. FLOOR PANEL WAS REPAIRED IAW SRM 53-20-50 AND 51-41-02.

Part: CUSP WEB — CORRODED (FUSELAGE) · corrosion level 2 · airframe 43,941 hrs · 30,446 cycles

EXCESSIVE CORROSION ON RT CUSP WEB STA Y 546, IN REF CARD 24, ZONE 200. CARD 81, ZONE 200, RT CUSP WEB, STA Y:546 WAS REPAIRED IAW SRM 53-00-55, FIG 216. HFEC INSPECTION WAS ACCOMPLISHED ON RT CUSP WEB STA Y 546, NO CRACKS WERE FOUND AFTER CUTOUT IAW NDT SPM 06-10-01.001.

Part: CUSP WEB — CORRODED (FUSELAGE) · corrosion level 2 · airframe 43,941 hrs · 30,446 cycles

EXCESSIVE CORROSION ON RT CUSP WEB, STA Y=493 IN REF CARD 24, ZONE 200, CARD 80, ZONE 200. DAMAGED CUSP WEB WAS REPAIRED IAW SRM 53-00-55, FIG 215. HFEC INSPECTION WAS ACCOMPLISHED ON RT CUSP WEB, STA Y=493. NO CRACKS WERE FOUND AFTER TRIMMING OUT IAW NDT SPM 06-10-01-001.

Part: ACCESS PANEL — CORRODED (WING) · corrosion level 2 · airframe 43,941 hrs · 30,446 cycles

CORROSION ON COUNTERSINK AND SETTLEMENT AREA OF FUEL ACCESS PLATE 670DT, AYP, CARD 30, ZONE 600. CORROSION ON COUNTERSINK OF FUEL ACCESS PLATE 670DT WAS REMOVED IAW SRM 51-10-04 AND WAS MEASURED AND FOUND OUT OF LIMITS WITH 3 ADJACEND HOLES 0.670", 0.673 AND 0.675" AND WAS REPLACED IAW SRM 57-10-01, CONDITION II, 1, A.

Part: BEAM — CRACKED (FUSELAGE) · airframe 43,941 hrs · 30,446 cycles

CRACKS ON BEAM 1 FWD AND AFT EDGE AT FWD ENTRY DOOR. BEAM WAS REPAIRED IAW SRM 52-10-02, FIG 201 AND FIG 202 TYPE A. CRACKS OF .650" AND .850".

Part: SKIN — CRACKED (FUSELAGE) · airframe 43,941 hrs · 30,446 cycles

CRACK ON EXTERNAL FUSELAGE SKIN BETWEEN LONGERON 14 RT, STA Y=1086, CARD 10, ZONE 200. AREA WAS REPAIRED IAW ER/A 547824-14, REV ORIGINAL. PERFORM EXTERNAL GVI ON REPAIR EVERY 3,000 FLIGHT CYCLES IAW ER/A 547824-14, REV ORIGINAL, SEC II AND FOLLOW UP WITH LOG 2568619. RII COMPLETED.

Part: ACCESS PANEL — CORRODED (WING) · corrosion level 2 · airframe 43,941 hrs · 30,446 cycles

CORROSION ON FUEL ACCESS PLATE, COUNTERSINK, SETTLEMENT AREA, 141AL. CORROSION ON FUEL ACCESS PLATE 141AL, COUNTERSINK AND SETTLEMENT AREA WAS REMOVED AND FOUND OUT OF LIMITS WITH 3 ADJACENT HOLES .665", .665", .665". THEREFORE WAS REPLACED IAW SRM 51-10-04 AND 57-10-01.

Part: ACCESS PANEL — CORRODED (WING) · corrosion level 2 · airframe 43,941 hrs · 30,446 cycles

CORROSION ON SETTLEMENT AND COUNTERSINKS FUEL TANK ACCESS PLATE NR 520DT. CORROSION ON SETTLEMENT AND COUNTERSINK AREA WAS REMOVED. FUEL ACCESS PLATE NR 520DT AND FOUND OUT OF LIMITS 3 ADJACENT HOLES 0.715", 0.710", 0.710". THEREFORE WAS REPLACED IAW SRM 51-10-04 AND 57-10-01.

Part: SKIN — CRACKED (FUSELAGE) · airframe 43,941 hrs · 30,446 cycles

CRACK ON EXTERNAL FUSELAGE SKIN BETWEEN LONGERON 13 RT AND 14 RT, STA Y=1074 TO Y=1078, CARD 9, ZONE 200. AREA WAS REPAIRED IAW ER/A 547824-14, REV ORIGINAL. PERFORM EXTERNAL GVI AN REPAIR EVERY 3,000 FLIGHT CYCLCES IAW ER/A 547824-14, REV ORIGINAL SEC II AND FOLLOW UP. RII COMPLETED.

Part: FITTING — CRACKED (EMERGENCY EXIT) · airframe 43,941 hrs · 30,446 cycles

CRACK ON CLIP BEAM 1 AFT SIDE AT FWD LT OVERWING EMERGENCY EXIT. CLIP WAS REPLACED IAW SRM 51-41-01, 51-41-02, 51-41-05, AND DWG 9957735.

Part: PAN — CRACKED (FUSELAGE) · airframe 43,941 hrs · 30,446 cycles

CRACK ON UPPER FWD RING PAN STA Y=756, RT AT PAX CABIN, CARD 29, ZONE 201. UPPER FWD RING PAN WAS REPAIRED IAW SRM 56-20-02, FIG 202, TYPE B. CRACK L=0.523" HFEC WAS PERFORMED ON TRIMMED AREA AND NO CRACKS FOUND AT TIME OF INSPECTION.

Part: PAN — CRACKED (FUSELAGE) · airframe 43,941 hrs · 30,446 cycles

CRACK ON LOWER FWD RING PAN, STA Y=636 RT AT PASSENGER CABIN. SM, CARD 30, ZONE 201. LOWER FWD RING PAN WAS REPAIRED IAW SRM 56-20-02, FIG 202, TYPE B. LONG CRACK L= 0.510" HFEC PERFORMED TRIMMED AREA AND NO CRACKS FOUND AT TIME OF INSPECTION.

Part: ANGLE — CRACKED (FUSELAGE) · airframe 43,941 hrs · 30,446 cycles

CRACKED ANGLE TIP STA Y=120, X=-53, Z=0 AT COCKPIT STRUCTURE. RT SIDE. CARD 27, ZONE 210. ANGLE WAS REPLACED IAW SRM 51-41-02, 51-41-05, 51-41-08, 51-20-09, 51-40-08, 51-10-04, PAR 14, 21, AND DWG 9911559, REV A.

Part: PAN — CRACKED (FUSELAGE) · airframe 43,941 hrs · 30,446 cycles

CRACK ON UPPER AFT RING PAN STA Y=851 RT AT PAX CABIN, SM, CARD 25, ZONE 201. UPPER AFT RING PAN WAS REPAIRED IAW SRM 56-20-02, FIG 202, TYPE B. L= 0.420", HFEC WAS PERFORMED ON TRIMMED OUT AREA AND NO CRACKS FOUND AT TIME OF INSPECTION.

Part: PAN — CRACKED (FUSELAGE) · airframe 43,941 hrs · 30,446 cycles

CRACK ON UPPER AFT RING PAN STA Y=832 LH AT PAX, CABIN. UPPER AFT RING PAN WAS REPAIRED IAW SRM 56-20-02, FIG 202, TYPE B. CRACK L =0.510". HFEC WAS PERFORMED ON TRIMMED AREA AND NO CRACKS WERE FOUND AT TIME OF INSPECTION.

Part: CUSP WEB — CRACKED (FUSELAGE) · airframe 43,941 hrs · 30,446 cycles

CRACKED LT CUSP WEB STA, Y=225, X=59 AT PAX CABIN. DAMAGE WAS REMOVED AND CUSP WEB WAS REPAIRED IAW SRM 53-00-55, FIG 216.

Part: PAN — CRACKED (FUSELAGE) · airframe 43,941 hrs · 30,446 cycles

CRACK ON LOWER FWD RING PAN STA Y=636 LT AT PAX CABIN, CARD 28, ZONE 201. LOWER RING PAN WAS REPAIRED IAW SRM 56-20-02, FIG 202, TYPE B. CRACK L=0.480", HFEC WAS PERFORMED ON TRIMMED AREA AND NO CRACKS WERE FOUND AT TIME OF INSPECTION.

Part: SUPPORT — CORRODED (FUSELAGE) · corrosion level 2 · airframe 43,941 hrs · 30,446 cycles

CORROSION ON TEE SUPPORT X=57 FROM STA 203 TO 219, W1, SM, CARD 44, ZONE 200. CORROSION ON TEE SUPPORT X= 57 FROM STA Y=203 TO Y=219 DUE EXCESSIVE DAMAGE WAS REPLACED IAW DWG 9936535, REV CS, SRM 51-41-02, 51-41-05, 51-41-08, 51-30-08.

Part: PAN — CRACKED (FUSELAGE) · airframe 43,941 hrs · 30,446 cycles

CRACK ON LOWER FWD T-RING PAN STA Y=655 LT AT PAX CABIN, CARD 27, ZONE 201. LOWER FWD RING PAN WAS REPAIRED IAW SRM 56-20-02, FIG 202, TYPE B. HFEC WAS PERFORMED ON TRIMMED AREA AND NO CRACKS WERE FOUND AT TIME OF INSPECTION, CRACK L=0.450".

Part: FLOOR SUPPORT — CRACKED (FUSELAGE) · airframe 43,941 hrs · 30,446 cycles

CRACKED FLOOR SUPPORT ON STA Y=655 X=15 AT PASSENGER CABIN, SM, CARD 71, ZONE 200. NEW FLOOR SUPPORT WAS INSTALLED IAW SRM 51-41-05, 53-20-51, FIG 1 ID 2, 51-40-08, 51-40-03, PAR 17, AND 51-10-04, PAR 15/21, 37.

Part: FAIRING — CRACKED (RT ELEVATOR) · airframe 43,941 hrs · 30,446 cycles

CRACK ON INBD GEARED TAB PUSH-ROD FAIRING AT RT ELEVATOR SURFACE. CARD 18, ZONE 340. FAIRING WAS STOP DRILLED IAW SRM 51-00-00, FIG 201, SHEET 2 OF 2 AND REPAIRED IAW SRM 55-00-00 FIG 201 SHEET 2 OF 2 DIMENTION CRACK 0.958".

Part: BRACKET — CRACKED (RT ELEVATOR) · airframe 43,941 hrs · 30,446 cycles

CRACKED BRACKET TO ATTACH ACTUATOR EYEBOLT WITH ATTACH POINT EYEBOLT, STA XE=49 AT RT HORIZONTAL STABILIZER, CARD 7, ZONE 340. SUMMARY BRACKET WAS REPLACED IAW AMM 27-33-01 AND CMM 27-30-2.

Part: FLOOR SUPPORT — CORRODED (FUSELAGE) · corrosion level 2 · airframe 43,941 hrs · 30,446 cycles

SEVERAL CORROSION POINTS ON FLOOR SUPPORT X-44 FROM STA 160 TO 200, W1, SM, CARD 33, ZONE 200. FLOOR SUPPORT X-44 WAS REPLACED IAW SRM 53-10-51 AND SRM 51-41-02, DUE TO EXCESSIVE DAMAGE.

Part: WEB — CORRODED (FUSELAGE) · corrosion level 2 · airframe 43,941 hrs · 30,446 cycles

CORROSION ON WEB X=-56, RT STA Y=1053 AT PAX CABIN. SM, CARD 60, ZONE 200. DUE EXCESIVE CORROSION, WEB WAS REPLACED IAW DWG NR 9981474, REV L TREATED, PAINTED, AND INSTALLED SRM 51-10-04 PAR 21 & 15; 51-22-01; 51-41-02.

Part: WARNING MESSAGE — FALSE ACTIVATION · airframe 42,415 hrs · 29,232 cycles

CLIMBING THROUGH 10,000 FT, RECEIVED "BUS AC GS OFF" WARNING. DECLARED EMERGENCY AND RETURNED TO DEPARTURE. CREW REPORT INDICATED THE EMERGENCY POWER ON LIGHT WAS ILLUMINATED. PERFORMED FUNCTIONAL CHECKS WITH NO FAULTS FOUND. REPLACED APCDU, EMERGENCY DC POWER RELAYS, LT & RT PCDU'S. REPLACED LT & RT & EXT POWER RELAYS WITH ALL CHECKS NORMAL. PERFORMED FUNCTIONAL CHECK FLIGHT WITH NO ISSUES NOTED.

Part: BULB — ODOR (CABIN LIGHT) · airframe 42,284 hrs · 29,128 cycles

ON DESCENT, AROUND 12,000 FT INTO DESTINATION, A SMOKE ODOR WAS NOTED AROUND SEAT ROWS 13-14. THE COCKPIT CREW DECARED AN EMERGENCY AND FOLLOWED THE SMOKE/FUMES CHECKLIST. THE ODOR CLEARED AND THE ACFT LANDED UNEVENTFULLY WITH NO FURTHER ISSUE. THE ISSUE WAS ISOLATED TO A POPPED HALOGEN READING LIGHT BULB AT SEAT 14C. THE READING LIGHT WAS DEFERRED IAW NEF 33-23-01 AND REPAIR WILL BE ACCOMPLISHED.

Part: BATTERY PACK — INOPERATIVE (EMERGENCY LIGHTS) · airframe 42,223 hrs · 29,076 cycles

DURING LINE CHECK, MAINTENANCE FOUND THAT THE EMERGENCY LIGHTING IN THE COCKPIT WAS INOPERATIVE. MAINTENANCE REPLACED THE BATTERY PACKS AND OPS CHECKED GOOD.

Part: SKIN — DAMAGED (BD 229-266) · airframe 41,769 hrs · 28,722 cycles

FOUND DAMAGE AFT OF MAIN CABIN DOOR ON EXT ACFT SKIN. REPAIRED IAW ER/A 537987-14. MAJOR REPAIR.

Part: BATTERY PACK — INOPERATIVE (EMERGENCY LIGHTS) · airframe 41,206 hrs · 28,244 cycles

DURING LINE CHECK, FOUND EMERGENCY LIGHTS ABOVE WINDOWS AT 19AB AND 19 CDE WERE INOPERATIVE. REPLACED BATTERY PACK CHARGER AND BATTERY AT B5-121 AND CHECKS OK. LP 7277197.

Part: POWER SUPPLY — INOPERATIVE (EMERGENCY LIGHTS) · airframe 40,790 hrs · 27,902 cycles

DURING LINE VISIT, NOTED TAIL COMPARTMENT WALKWAY EMERGENCY LIGHTS WERE INOPERATIVE. REPLACED POWER SUPPLY & BATTERY PACK IN AFT DROP CEILING IAW AMM 33-51-03. OPS TEST OF EMERGENCY LIGHT SYS NORMAL IAW AMM 33-51-00.

Part: ELECTRICAL SYS — UNKNOWN · airframe 40,459 hrs · 27,651 cycles

THE FLIGHT CREW RETURNED TO DEPARTURE DUE TO LOSS OF BOTH AC BUSSES AND SUBSEQUENT ERRATIC CYCLING OF AC ELECTRICAL POWER. AT THE TIME OF THIS ODI EVENT, THE RT IDG WAS DEFERRED DUE TO A RT GENERATOR OFF MESSAGE ON A PRIOR LEG. PERFORMED TROUBLESHOOTING IAW FIM 24-08-00-810 801. NO FAULTS ON EPCU OR ANY PCDU. RAN BOTH ENGINES WITH APU RUNING AND NOT RUNNING WITH NO TROUBLE FOUND. ALL BUSS TIE FUNCTIONS WERE NORMAL. REPLACED LT BUSS TIE CONTACTOR, PDCU, AND LT GENERATOR CONTACTOR IAW AMM 24-21. REPLACED RT PDCU, RT GENERATOR RELAY, BUSS TIE RELAY AND EPCU AMM 24-21. PERFORMED RESISTANCE CHECK RT PDCU AND RT GENERATOR AND PIN TENSION CHECK OF SAME IAW WDM 24-21-21-02. RAN BOTH ENGINES AND POWER TRANSFERRED BUSSES LT TO RT, RT TO LT, APU TO RT & APU TO LT WITH ALL CHECKED NORMAL IAW AMM 24-10. THE ACFT HAS RETURNED TO SERVICE.

Part: LENS — CRACKED (CABIN) · airframe 39,266 hrs · 26,644 cycles

R1 DOOR EMER LIGHT LENS COVER AFT OF DOOR CRACKED. R & R LENS IAW MM.

Part: LENS — CRACKED (CABIN) · airframe 39,266 hrs · 26,644 cycles

EMERGENCY LIGHT LENS CRACKED AT RT AFT OVERWING EXIT. R & R LENS IAW MM.

Part: LENS — CRACKED (CABIN) · airframe 39,266 hrs · 26,644 cycles

R1 DOOR EMER LIGHT LENS COVER ABOVE DOOR CRACKED. R & R LENS IAW MM.

Part: CHARGER — INOPERATIVE (CABIN) · airframe 38,401 hrs · 26,086 cycles

FORWARD EMER LIGHTS INOPERATIVE AT STATION 188 RT SIDE. R & R BATTERY CHARGER IAW MM.

Part: CHARGER — INOPERATIVE (CABIN) · airframe 38,401 hrs · 26,086 cycles

FORWARD EMER LIGHTS INOPERATIVE AT STATION 180, LT SIDE. R & R B5-235 BATTERY CHARGER IAW MM.

Part: CHARGER — INOPERATIVE (CABIN) · airframe 38,401 hrs · 26,086 cycles

EMERGENCY LIGHT BATTERY ASSEMBLY B5-119 INOPERATIVE. R & R BATTERY CHARGER IAW MM.

Part: CHARGER — INOPERATIVE (CABIN) · airframe 38,401 hrs · 26,086 cycles

EMERGENCY LIGHT BATTERY ASSEMBLY B5-118 INOPERATIVE. R & R BATTERY CHARGER IAW MM.

Part: LIGHT — BROKEN (CABIN) · airframe 38,401 hrs · 26,086 cycles

FIRST CLASS CEILING EXIT LIGHT ASSEMBLY BROKEN. R & R LIGHT IAW AMM.

Part: DOUBLER — CRACKED (FUSELAGE) · airframe 38,401 hrs · 26,086 cycles

FLOOR SUPPORT WEB DOUBLER CRACKED AT BS 148, LONGERON 8R. REPAIRED DOUBLER IAW SRM.

Part: CONNECTOR — BROKEN (CABIN) · airframe 38,401 hrs · 26,086 cycles

L1 DOOR EMER EXIT SIGN ABOVE DOOR CONNECTOR BROKEN. RECONNECTED CONNECTOR IAW AMM.

Part: FORMER — CORRODED (FUSELAGE) · airframe 38,401 hrs · 26,086 cycles

FRAME FORMER CORRODED AT BS 1037, BETWEEN LONGERON 28L TO 28R. R & R FORMER IAW SRM.

Part: CREASE BEAM — CORRODED (FUSELAGE) · airframe 38,401 hrs · 26,086 cycles

CREASE BEAM WEB CORRODED BETWEEN BS 170 TO 202, BL 58R. REPAIRED BEAM IAW SRM.

Part: DOUBLER — CRACKED (FUSELAGE) · airframe 38,401 hrs · 26,086 cycles

FLOOR SUPPORT WEB DOUBLER CRACKED BETWEEN BS 166 TO BS 170. REPAIRED DOUBLER IAW SRM.

Part: WEB — CORRODED (FUSELAGE) · airframe 38,401 hrs · 26,086 cycles

R1 DOOR EMER EVAC SLIDE FWD GIRT BAR FITTING FLOOR WEB CORRODED. REPAIRED WEB IAW SRM & DWG.

Part: FITTING — CORRODED (R1 DOOR) · airframe 38,401 hrs · 26,086 cycles

R1 DOOR EMER EVAC SLIDE FWD GIRT BAR FITTING CORRODED. R & R FITTING IAW SRM & DWG.

Part: SEAT TRACK — CORRODED (COCKPIT) · airframe 38,401 hrs · 26,086 cycles

FLIGHT COMPARTMENT, FIRST OFFICERS OTBD SEAT TRACK CORRODED BETWEEN BS 138 TO BS 148, LONGERON 30R. R & R SEAT TRACK IAW SRM & DWG.

Part: ANGLE — CORRODED (FUSELAGE) · airframe 38,401 hrs · 26,086 cycles

FLOOR SUPPORT ANGLE CORRODED BETWEEN BS 125 TO BS 148, BETWEEN X-49 TO X-52. R & R ANGLE IAW SRM & DWG.

Part: FITTING — CORRODED (R1 DOOR) · airframe 38,401 hrs · 26,086 cycles

R1 DOOR EMER EVAC SLIDE AFT GIRT BAR FITTING CORRODED. R & R FITTING IAW SRM & DWG.

Part: SKIN — CRACKED (FUSELAGE) · airframe 38,401 hrs · 26,086 cycles

FUSELAGE SKIN CRACKED AT AFT EDGE OF AFT CARGO DOOR CUT OUT 3 INCHES BELOW LONGERON 25R. REPAIRED SKIN IAW EA.

Part: DOUBLER — CRACKED (FUSELAGE) · airframe 38,401 hrs · 26,086 cycles

TAIL COMPARTMENT RT VENT BOX DOUBLER CRACKED AT TOP AFT EDGE BS 1200. REPAIRED DOUBLER IAW SRM.

Part: RIB — CRACKED (LE SLAT) · airframe 38,401 hrs · 26,086 cycles

LEFT WING NR 5 LT SLAT LE OTBD SKIN RIB CRACKED. R & R RIB IAW SRM & DWG.

Part: BATTERY PACK — WEAK (CABIN) · airframe 39,243 hrs · 26,626 cycles

EMERGENCY EXIT LIGHT BATTERY LOW POWER AT BS 1043. R & R BATTERY PACK IAW SIP.

Part: COVER — LOOSE (R1 DOOR) · airframe 37,845 hrs · 25,719 cycles

R1 DOOR EMERGENCY EVAC SLIDE COVER LOOSE. SECURE SLIDE IAW MM.

Part: LATCH — DIRTY (GIRT BAR) · airframe 37,161 hrs · 25,285 cycles

R1 DOOR EMERGENCY EVAC SLIDE GIRT BAR DOESN'T INSERT PROPERLY INTO FLOOR FITTINGS. CLEANED & LUBED GIRT BAR LATCHES IAW ISP.

Part: COVER — LOOSE (R1 DOOR) · airframe 362,210 hrs · 24,707 cycles

R1 DOOR SLIDE COVER LOOSE. SECURED SLIDE PER MM.

Part: BATTERY PACK — DISCHARGED (FLASHLIGHT) · airframe 35,931 hrs · 24,530 cycles

BOTH FLASHLIGHTS AT AFT F/A STATION DISCHARGED. REMOVED AND REPLACED BATTERY PACKS ON BOTH AFT FLASHLIGHTS AND RE-INSTALLED IN CRADLE IN PROPER POSITION.

Part: POWER SUPPLY — FAILED (CABIN) · airframe 355,100 hrs · 24,257 cycles

EMERGENCY LIGHT POWER SUPPLY BS - 119 FAILS OPS TEST. REMOVED AND REPLACED EMERGENCY LIGHT POWER SUPPLY ASY BS-119 IAW B717 AMM 33-51-01 PERFORMED GOOD OPS TEST OF EMERGENCY LIGHTS IAW B717 AMM 33-51-00.

Part: SEAT TRACK — CORRODED (FUSELAGE) · airframe 355,100 hrs · 24,257 cycles

SEAT TRACK SECTIONS 898 TO 1022 CORRODED AT THE FOLLOWING LOCATIONS: STA 898 RBL 22.5 AND STA 928 RBL 22.5. REMOVE CORROSION ON SEAT TRACK AT RBL 22.5 STA 898 AND 928 MAT LOSS OF .056" IS FOUND TO BE OUT OF LIMITS. CUT OUT SEAT TRACK SECTION.

Part: SEAT TRACK — CORRODED (FUSELAGE) · airframe 355,100 hrs · 24,257 cycles

SEAT TRACK SECTION 898 TO 1022 CORRODED AT STA 928 RBL 44. REMOVED CORROSION RBL 44 SEAT TRACK AT STA 928 MAT LOSS OF .076" IS FOUND TO BE OUT OF LIMITS. CUT OUT RBL 44 SEAT TRACK SECTION STA 898-936 DIM 36". LOCATED, DRILLED AND INSTALLED

Part: FRAME — CORRODED (FUSELAGE) · airframe 355,100 hrs · 24,257 cycles

AFT PIT FRAME AS FS 946 CORRODED ON LOWER/FWD FLANGE AROUND FASTENERS ATTACHING TO LONGERON 30. REMOVE CORROSION FROM STATION 946 FRAME FWD LOWER FLANGE AT LONGERON 30 IAW B717 SRM 51-10-04. UT INSP AREA IAW B717 NDTSPM PT 4, 04-10-01, ORIGIN

Part: FORMER — CORRODED (FUSELAGE) · airframe 355,100 hrs · 24,257 cycles

AFT CARGO PIT BILGE - CORROISON ON FORMER AT FWD SIDE OF FS 927 AND L-30. CUT OUT SECTION OF STATION 927 FORMER AT LONGERON 30, FABRICATED AND INSTALLED REPAIR SPLICES AND FILLER IAW B717 SRM 53-00-06 REPAIR 2, 53-20-07, 51-10-04, 53-00-00, 51-

Part: CUSP WEB — CORRODED (FUSELAGE) · airframe 355,100 hrs · 24,257 cycles

MAIN CABIN CUSP WEB CORRODED AT STA 560 TO 579 RIGHT SIDE. REMOVED AND REPLACED WEB IAW SRM.

Part: CUSP WEB — CORRODED (FUSELAGE) · airframe 355,100 hrs · 24,257 cycles

MAIN CABIN LIGHT CORRODED ON CUSP WEB AT STA 408 TO 427 RIGHT SIDE. REMOVED AND REPLACED WEB IAW SRM.

Part: FASTENER — CORRODED (FUSELAGE) · airframe 355,100 hrs · 24,257 cycles

FORWARD PIT - CORRODED FASTENERS IN LOWER FLANGE OF FRAME (AFT SIDE) AT BS 408 ABOVE L-30. REMOVED AND REPLACED 2 EA FASTENERS IN LOWER FLANGE OF FRAME (AFT SIDE) AT BS 408 ABOVE L-30.

Part: SEAT TRACK — CORRODED (FUSELAGE) · airframe 355,100 hrs · 24,257 cycles

SEAT TRACK SECTION STA 237 TO 585 CORRODED AT STA 286 TO 400 RBL 22.5 AND RBL 44. REPAIRED SEAT TRACK IAW SRM.

Part: SEAT TRACK — CORRODED (FUSELAGE) · airframe 355,100 hrs · 24,257 cycles

SEAT TRACK SECTIONS 898 TO 1022 CORRODED AT STA 898 TO 928 RBL 22.5 AND RBL 44. REMOVED AND REPLACED SEAT TRACK IAW SRM.

Part: SUPPORT — CRACKED (FUSELAGE) · airframe 355,100 hrs · 24,257 cycles

SEAT TRACK SUPPORT AT STA 737, LBL 44 IS CRACKED. REMOVED AND REPLACED SEAT TRACK SUPPORT AT BS 737, LBL 44 IAW B717 SRM 51-40-08 AND 51-41-08.

Part: SHEAR TIE — CORRODED (FUSELAGE) · airframe 355,100 hrs · 24,257 cycles

AFT PIT - CORROSION ON SHEAR TIE AND FRAME AT STA 1002 LONG 30-29L. REMOVED AND REPLACED 9957739-49 FORMER AT STA 1002 LONG 30-29L IAW B717 SRM 51-41-02, 51-40-08, 51-10-04.

Part: SHEAR TIE — CORRODED (FUSELAGE) · airframe 355,100 hrs · 24,257 cycles

SHEAR TIE CORRODED AT STA 908 LONGERON 29L - 29R. REPAIRED SHEAR TIE IAW SRM.

Part: INTERCOSTAL — CRACKED (FUSELAGE) · airframe 355,100 hrs · 24,257 cycles

AFT PIT - FLOOR SUPPORT BRACKET CRACKED - AT STA 817 LONG 30 AFT SECTION. REMOVED AND REPLACED INTERCOSTAL AT STA 817 BULKHEAD ABOVE LONGERON 30 IAW B717 SRM 51-41-05, 51-40-08, 51-20-05

Part: BULKHEAD — CRACKED (FUSELAGE) · airframe 355,100 hrs · 24,257 cycles

AFT PIT - FWD BULKHEAD - LINER SUPPORT STRIP CRACKED AT STA 813 LEFT AND RIGHT SIDES. REMOVED AND REPLACED AFT PIT FWD BULKHEAD 5956040-43, 596040013 5956040-41 AND 5956040-11 INTERCOSTALS IAW B717 SRM 51-41-08 AND 51-41-02

Part: CUSP WEB — CRACKED (FUSELAGE) · airframe 355,100 hrs · 24,257 cycles

CUSP WEB FROM STA 794 TO 813 RT SIDE CRACKED AT 2EA FASTENER HOLES. REMOVED AND REPLACED WEB IAW SRM.

Part: CUSP WEB — CRACKED (FUSELAGE) · airframe 355,100 hrs · 24,257 cycles

CUSP WEB FROM STA 655 TO 715 LT SIDE CRACKED. REMOVED AND REPLACED CUSP WEB IAW SRM.

Part: STRINGER — CRACKED (FUSELAGE) · airframe 355,100 hrs · 24,257 cycles

FUSELAGE INTERNAL AT STA 1133 CRACKED. REMOVED AND REPLACED STRINGER IAW SRM AND DWG.

Part: SIGN — BROKEN (CABIN) · airframe 355,100 hrs · 24,257 cycles

CABIN PASSENGER LT AFT LAV EXIT SIGN IS BROKEN. REMOVED AND REPLACED AFT LT LAV EMERGENCY EXIT SIGN IAW AMM 33-51-18. PERFORMED A SATISFACTORY OPERATIONAL CHECK OF THE AFT LT LAV EMERGENCY EXIT SIGN IAW AMM 33-51-00-710-801.

Part: FRAME — CRACKED (FUSELAGE) · airframe 355,100 hrs · 24,257 cycles

AFT FUSELAGE AT INTERNAL FRAME AREA, RIGHT SIDE AT BS 1144 APPROX, COVER CRACK AT UPPER SIDE. REMOVED DAMAGE, PREPPED AREA, APPLIED REPAIR, PRIED REPAIRED AREA IAW B717 SRM 51-70-09, 51-22-01.

Part: BRACKET — CRACKED (FUSELAGE) · airframe 355,100 hrs · 24,257 cycles

FS 674 LEFT, AFT SIDE OF FRAME, HAS A CRACKED BRACKET BETWEEN L-18L AND L-19L. REMOVED AND REPLACED CRACKED BRACKET, P/N 3920341-501, OF STA 674 BETWEEN L-18L AND L-19L IAW B717 SRM 51-41-05 AND 51-40-08.

Part: STRINGER — CRACKED (FUSELAGE) · airframe 355,100 hrs · 24,257 cycles

FUSELAGE INTERNAL AT STA 133 CRACKED. REPAIRED STRINGER IAW SRM DWG.

Part: RUB STRIP — CRACKED (FUSELAGE) · airframe 355,100 hrs · 24,257 cycles

LEFT WING TO BODY FAIRING AT STA 617 STG 18L RUB STRIP CRACKED. REMOVED AND REPLACED LEFT WING-TO-BODY FAIRING AT STA 617 STR 18L RUBSTRIP P/N 5971042-3, PO 2229024 IAW B717 SRM 51-20-05.

Part: INTERCOSTAL — CRACKED (L1 DOOR) · airframe 355,100 hrs · 24,257 cycles

PASS DOOR LT 1 INTERNAL STRUCTURE INTERCOSTAL CRACKED ON SIDE OF DOOR HANDLE COMPARTMENT. REMOVED AND REPLACED INTERCOSTAL IAW SRM.

Part: SLIDE — UNSERVICEABLE (R1 DOOR) · airframe 355,100 hrs · 24,257 cycles

UPON REMOVAL OF R-1 DOOR EMERGENCY SLIDE FOUND SLIDE TO BE PACKED INCORRECTLY AND MISSING SAFETY PIN. REMOVED AND REPLACED R-1 DOOR EMERGENCY SLIDE IAW B-717 AMM 25-61-03.

Part: BRACKET — CRACKED (LT MLG WW) · airframe 355,100 hrs · 24,257 cycles

LEFT W/W DOOR CUTOUT AT FWD AREA, I/B SIDE 01EA BRACKET CRACKED. REMOVED AND REPLACED 9923459U7 ANGLE IN LEFT WHEEL WELL IAW B717 SRM 51-41-05 AND 51-40-08.

Part: BULKHEAD — CORRODED (RT MLG WW) · airframe 355,100 hrs · 24,257 cycles

RIGHT W/W BULKHEAD AT FLOOR LEVEL CORRODED FROM I/B SIDE THRU O/B SIDE. REPAIRED SKIN IAW NDT SPM.

Part: PAN — CORRODED (FUSELAGE) · airframe 355,100 hrs · 24,257 cycles

AFT CARGO DOOR PAN HAS MULITPLE AREAS OF CORROSION. REMOVED AND REPLACED CORRODED C-2 DOOR JAMB LOWER PAN REPAIR SECTION, P/N J060228-31 IAW B717 SRM 53-20-15 REPAIR 7. REF MDDR NUMBER 238766

Part: BRACKET — CRACKED (RT MLG WW) · airframe 355,100 hrs · 24,257 cycles

RIGHT WHEEL WELL FWD DOOR CUTOUT I/B BRACKET CRACKED. REMOVED AND REPLACED 992349U7 BRACKET IS RT WHEEL WELL IAW B717 SRM 51-41-05 AND 51-40-08.

Part: CUSP WEB — CRACKED (FUSELAGE) · airframe 355,100 hrs · 24,257 cycles

MAIN CABIN CUSP WEB STA 665-715 RIGHT HAS 2 CRACKS. CUT OUT DAMAGED AREAS OF RIGHT CUSP WEB BETWEEN STA 665 AND 715, FABRICATED AND INSTALLED DOUBLERS AND FILLER IAW B717 SRM 53-00-55 REPAIR 4, 53-20-51, 51-40-08, 51-10-04, 51-20-05.

Part: FLOORBEAM — CRACKED (FUSELAGE) · airframe 355,100 hrs · 24,257 cycles

FS 674 L-18L FLOORBEAM WEB CRACKED. REMOVED AND REPLACED BEAM PER SRM.

Part: COVER — CRACKED (LE SLAT) · airframe 355,100 hrs · 24,257 cycles

RIGHT WING NR 4 SLAT TRACK LOWER COVER CRACKED. REMOVED AND REPLACED L/E COVER PLATE (DOOR ASSY) P/N 9971030-506 AS REQUIRED IAW B717 AMM 27-80-01.

Part: BONDING STRAP — CRACKED (RT WING) · airframe 355,100 hrs · 24,257 cycles

RIGHT WING FIXED L/E - THE MOST I/B SIDE OF THE WING - BONDING STRAP CRACKED. REMOVED, FABRICATED, AND INSTALLED UPPER AND LOWER BONDING STRAPS, P/N 5919110-97, IAW B717 SRM 51-41-02, 51-41-05, AND DAC DWG 5919110.

Part: RUB STRIP — CORRODED (FUSELAGE) · airframe 355,100 hrs · 24,257 cycles

WING TO BODY ATTACH AREA RUB STRIPS CORRODED 2 EACH - LT AND RT SIDES APPROX STA 851. REMOVED & REPLACED LT & RT WING TO BODY RUB STRIPS AT APPROX STR 851 IAW B717 SRM 51-20-05.

Part: BRACKET — CRACKED (SLAT TRACK) · airframe 355,100 hrs · 24,257 cycles

RIGHT WING - NR 2 SLAT TRACK - I/B SIDE SPRING DOOR BRACKET CRACKED. REMOVED AND REPLACED SPRING DOOR BRACKET FOR RIGHT NR 2 SLAT, I/B TRACK IAW B717 SRM 51-41-01 AND 51-40-08.

Part: COVER — CRACKED (LE SLAT) · airframe 355,100 hrs · 24,257 cycles

RIGHT WING NR 2 SLAT TRACK LOWER COVER CRACKED. REMOVED, FABRICATED, AND INSTALLED NEW COVER AND SHIM IAW B717 SRM 51-41-01, 51-41-08, 51-10-04, 51-41-02, MD DWG 9922567.

Part: FRAME — CRACKED (FUSELAGE) · airframe 355,100 hrs · 24,257 cycles

FS 715 AT L-18L, FRAME CRACKED AT MAIN FRAME TO OVERWING FLOORBEAM INTERSECTION INTERNAL STRUCTURE. REMOVED AND REPLACED 9923407-503 FRAME AT STA 715 LEFT SIDE IAW B717 SRM 51-41-02, 51-41-05, 51-40-02 AND 51-41-01.

Part: RUB STRIP — CORRODED (FUSELAGE) · airframe 355,100 hrs · 24,257 cycles

WING TO BODY ATTACH AREA RUB STRIPS CORRODED 2 EACH - LT AND RT SIDES APPROX STA 851. REMOVED & REPLACED LT & RT WING TO BODY RUBSTRIPS AT APPROX STR 851 IAW B717 SRM 51-20-05.

Part: FLOOR PANEL — DELAMINATED (MAIN CABIN) · airframe 355,100 hrs · 24,257 cycles

MAIN CABIN FLOOR PANEL 222ADF IS DELAMINATED. REMOVED FLOOR PANEL IAW SRM 51-41-01. FABRICATED NEW FLOOR PANEL IAW SRM 53-20-50. INSTALLED FLOOR PANEL IAW AMM 53-21-0.1

Part: FLOOR PANEL — DELAMINATED (CABIN) · airframe 355,100 hrs · 24,257 cycles

MAIN CABIN FLOOR PANEL 222ACF IS DELAMINATED. REMOVED FLOOR PANEL 222ACF IAW B717 SRM 51-41-01. FABRICATED REPLACEMENT FLOOR PANEL IAW B717 SRM 53-20-50. INSTALLED FLOOR PANEL IAW B717 AMM 53-21-01.

Part: FLOOR PANEL — DELAMINATED (CABIN) · airframe 355,100 hrs · 24,257 cycles

MAIN CABIN FLOOR PANEL 222AEF IS DELAMINATED. REMOVED & REPLACED MAIN CABIN FLOOR PANEL 222AEF IAW B717 SRM 51-41-01. FABRICATED FLOOR PANEL FROM P/N: B227002 TYPE 3 PO: 790191416 DIM 21" X 41" IAW B717 SRM 53-20-50.

Part: FLOOR PANEL — DELAMINATED (CABIN) · airframe 355,100 hrs · 24,257 cycles

MAIN CABIN FLOOR PANEL 222 APF IS DELAMINATED. REMOVED FLOOR PANEL 222APF IAW B717 SRM 51-41-01. FABRICATED NEW PANEL IAW B717 SRM 53-20-50. INSTALLED FLOOR PANEL IAW B717 AMM 53-21-01.

Part: FLOOR PANEL — DELAMINATED (CABIN) · airframe 355,100 hrs · 24,257 cycles

MAIN CABIN FLOOR PANEL 221UF IS DELAMINATED. REMOVED FLOOR PANEL 221UF IAW B717 SRM 51-41-01. FABRICATED FLOOR PANEL 22UF IAW B717 SRM 53-20-50. INSTALLED FLOOR PANEL IAW B717 AMM 53-21-01.

Part: FLOOR PANEL — DELAMINATED (CABIN) · airframe 355,100 hrs · 24,257 cycles

MAIN CABIN FLOOR PANEL 222AHF IS DELAMINATED. REMOVED & REPLACED MAIN CABIN FLOOR PANEL 222AHF IAW B717 SRM 51-41-01. FABRICATED FLOOR PANEL FROM P/N: B227002 TYPE 3 PO: 790191416 DIM 21" X 76" IAW SRM 53-20-50.

Part: FLOOR PANEL — DELAMINATED (CABIN) · airframe 355,100 hrs · 24,257 cycles

MAIN CABIN FLOOR PANEL 222ABF IS DELAMINATED. REMOVED & REPLACED MAIN CABIN FLOOR PANEL 222ABF IAW B717 SRM 51-41-01. FABRICATED FLOOR PANEL FROM P/N: B227002 TYPE PO: 79011911416 DIM 21" X 22" IAW B717 SRM 53-20-50.

Part: FLOOR PANEL — DELAMINATED (CABIN) · airframe 355,100 hrs · 24,257 cycles

MAIN CABIN FLOOR PANEL 222BF IS DELAMINATED. REMOVED FOOR PANEL 222BF IAW B717 SRM 51-41-01. FABRICATED FLOOR PANEL IAW B717 SRM 53-20-50. INSTALLED FOOR PANEL IAW B717 AMM 53-21-01

Part: FLOOR PANEL — DELAMINATED (CABIN) · airframe 355,100 hrs · 24,257 cycles

MAIN CABIN FLOOR PANEL 221 WF IS DELAMINATED. REMOVED FLOOR PANEL 221WF IAW B717 SRM 51-41-01. FABRICATED NEW PANEL IAW B717 SRM 53-20-50. INSTALLED FLOOR PANEL IAW B717 AMM 53-21-01.

Part: SKIN — CRACKED (NLG DOOR) · airframe 355,100 hrs · 24,257 cycles

LEFT NLG STRUT DOOR SKIN CRACKED. REPAIRED SKIN IAW SRM.

Part: FLOOR PANEL — DELAMINATED (CABIN) · airframe 355,100 hrs · 24,257 cycles

MAIN CABIN FLOOR PANEL 222JF IS DELAMINATED. REMOVED FLOOR PANEL 222JF IAW B717 SRM 51-41-01, FABRICATED NEW FLOOR PANEL IAW B717 SRM 53-20-50. INSTALLED FLOOR PANEL IAW B717 AMM 53-21-01.

Part: FLOOR PANEL — DELAMINATED (CABIN) · airframe 355,100 hrs · 24,257 cycles

MAIN CABIN FLOOR PNL 222GF IS DELAMINATED. REMOVED FLOOR PANEL 22GF IAW B717 SRM 51-41-01. FABRICATED REPLACEMENT PANEL IAW B717 SRM 53-20-50. INSTALLED NEW PANEL IAW B717 AMM 53-21-01.

Part: FLOOR PANEL — DELAMINATED (CABIN) · airframe 355,100 hrs · 24,257 cycles

MAIN CABIN FLOOR PANEL 222 AAF IS DELAMINATED. REMOVED CABIN FLOOR PANEL 222AAF IAW B717 SRM 51-41-01. FABRICATED NEW FLOOR PANEL IAW B717 SRM 53-20-50. INSTALLED FLOOR PANEL IAW B717 AMM 53-21-01.

Part: SKIN — CRACKED (NLG DOOR) · airframe 355,100 hrs · 24,257 cycles

RIGHT NLG STRUT DOOR SKIN CRACKED. REPAIRED DOUBLER IAW SRM.

Part: FLOOR PANEL — DELAMINATED (CABIN) · airframe 355,100 hrs · 24,257 cycles

MAIN CABIN FLOOR PANEL 222 QF IS DELAMINATED. REMOVED CABIN FLOOR PANEL 222QF IAW B717 SRM 51-41-01. FABRICATED NEW FLOOR PANEL IAW B717 SRM 53-20-50. INSTALLED NWE FLOOR PANEL IAW B717 AMM 53-21-01.

Part: FLOOR PANEL — DELAMINATED (CABIN) · airframe 355,100 hrs · 24,257 cycles

MAIN CABIN FLOOR PANEL IS DELAMINATED 222RF. REMOVED MAIN CABIN FLOOR PANEL 222RF IAW B717 SRM 51-41-01. FABRICATED REPLACEMENT FLOOR PANEL IAW B717 SRM 53-20-50. INSTALLED NEW PANEL IAW B717 AMM 53-21-01.

Part: PANEL — DELAMINATED (CABIN) · airframe 355,100 hrs · 24,257 cycles

MAIN CABIN FLOOR PANEL 222PF IS DELAMINATED. REMOVED FLOOR PANEL 222PF IAW B717 SRM 51-41-01. FABRICATED NEW FLOOR PANEL IAW B717 SRM 53-20-50. INSTALLED FLOOR PANEL IAW B714 AMM 53-21-01.

Part: FLOOR PANEL — DELAMINATED (CABIN) · airframe 355,100 hrs · 24,257 cycles

MAIN CABIN FLOOR PANEL 222LF IS DELAMINATED. REMOVED FLOOR PANEL 222LF IAW B717 SRM 51-41-01. FABRICATE NEW PANEL IAW B717 SRM 53-20-50. INSTALLED NEW PANEL IAW B717 AMM 53-21-01.

Part: FLOOR PANEL — DELAMINATED (CABIN) · airframe 355,100 hrs · 24,257 cycles

MAIN CABIN FLOOR PANEL 222AGF IS DELAMINATED. REMOVED FLOOR PANEL 222AGF IAW B717 SRM 51-41-01. FABRICATED REPLACEMENT FLOOR PANEL IAW B717 SRM 53-20-50. INSTALLED FLOOR PANEL IAW B717 AMM 53-21-01.

Part: FLOOR PANEL — DELAMINATED (CABIN) · airframe 355,100 hrs · 24,257 cycles

MAIN CABIN FLOOR PANEL 222FF IS DELAMINATED. REMOVED FLOOR PANEL 222FF IAW B717 SRM 51-41-01. FABRICATED NEW PANEL IAW B717 SRM 53-20-50. INSTALLED PANEL IAW B717 AMM 53-21-01.

Part: FLOOR PANEL — DELAMINATED (CABIN) · airframe 355,100 hrs · 24,257 cycles

MAIN CABIN FLOOR PANEL 222 DF IS DELAMINATED. REMOVED FLOOR PANEL 222DF IAW B717 SRM 51-41-01. FABRICATED NEW PANEL IAW B717 SRM 53-20-50. INSTALLED FLOOR PANEL IAW B717 AMM 53-21-01.

Part: FLOOR PANEL — DELAMINATED (MAIN CABIN) · airframe 355,100 hrs · 24,257 cycles

MAIN CABIN FLOOR PANEL 222AVF DELAMINATED. FABRICATED FLOOR PANEL IAW SRM 53-20-50.

Part: DOUBLER — CRACKED (RT PYLON) · airframe 355,100 hrs · 24,257 cycles

RIGHT APRON CRACKED AT LWR COWL 2ND LATCH POINT. REMOVED DAMAGE, FABRICATED AND INSTALLED REPAIR DOUBLER AT RIGHT ENGINE APRON AT 2ND FROM AFT LATCH IAW B717 SRM 54-50-02, 51-41-01, 51-41-02, 51-10-04.

Part: DOUBLER — CRACKED (LT PYLON) · airframe 355,100 hrs · 24,257 cycles

LEFT APRON CRACKED AT LOWER COWLING ATTACH POINT. REMOVED AND REPLACED DOUBLER IAW FAS EA AND SRM.

Part: STRUCTURE — CRACKED (LT NACELLE) · airframe 355,100 hrs · 24,257 cycles

LEFT APRON CRACKED AT UPPER COWLING AFT ATTACH POINT. CUT OUT DAMAGE ON LEFT ENGINE SPRON AT UPPER COWLING AFT ATTACH POINT, FABRICATED AND INSTALLED REPAIR DOUBLER AND SHIM IAW B717 SRM 51-41-01, 51-41-02, 54-50-02 REPAIR 1 AND 51-10-04.

Part: SWITCH — FAILED (CABIN) · airframe 34,184 hrs · 23,391 cycles

EMERGENCY EXIT LIGHTS FAILED TEST. REMOVED AND REPLACED SWITCH PER MM.

Part: LIGHT — INOPERATIVE (CABIN)

EMERGENCY LIGHT ASSY DAMAGED AT 24D. REMOVED AND REPLACED EMERGENCY LIGHT ASSY. OK FOR SERVICE REF M/M 33-51.

Part: FRAME — CORRODED (FUSELAGE)

AFT CARGO COMPARTMENT FRAME SECTION, STA 1037 TO 1053, LONG L29L TO L29R, CORROSION. ACCOMPLISHED FRAME SECTION REPLACEMENT PER B717 SRM 53-20-07 FIG 201 REPAIR 3.

Part: FRAME — CORRODED (FUSELAGE)

AFT CARGO COMPARTMENT FRAME SECTION, STA 1022 TO 1053, LONG L29L TO L29R, CORROSION. ACCOMPLISHED FRAME SECTION REPLACEMENT PER B717 SRM 53-20-07 FIG 201 REPAIR 3.

Part: PAN — CORRODED (FUSELAGE)

AFT CARGO DOOR JAMB PAN, CORROSION. ACCOMPLISHED JAMB PAN SPLICE REPAIR PER B717 SRM 53-20-15 FIG 201 REPAIR 7.

Part: SCUFF PLATE — CHAFED (CARGO DOOR)

FWD CARGO DOOR HANDLE CUTOUT, CHAFED. ACCOMPLISHED HANDLE CUTOUT SCUFF PLATE REPAIR PER B717 SRM 32-30-01 FIG 201 REPAIR 1.

Part: LONGERON — CORRODED (FUSELAGE)

AFT CARGO COMPARTMENT LONGERON SECTION, STA 1022 TO 1037, LONG L30, CORROSION. ACCOMPLISHED LONGERON SECTION REPLACEMENT PER B717 SRM 51-41-02 AND B717 SRM 51-41-05.

Part: FLOOR SUPPORT — CORRODED (FUSELAGE)

RIGHT FWD FUSELAGE BELOW CATERING DOOR FLOOR SUPPORT, CORROSION. ACCOMPLISHED FLOOR SUPPORT REPLACEMENT PER B717 SRM 51-41-01.

Part: STRAP — CORRODED (FUSELAGE)

PASSENGER ENTRANCE SCUFF PLATE STRAP, CORROSION. ACCOMPLISHED SCUFF PLATE STRAP REPLACEMENT PER B717 SRM 51-40-02.

Part: SEAT TRACK — CORRODED (FUSELAGE)

CABIN SEAT TRACK, STA 237, RBL 44, CORROSION. ACCOMPLISHED SEAT TRACK SPLICE REPAIR PER DC9 SRM 53-05 FIG 4F.

Part: SEAT TRACK — CORRODED (FUSELAGE)

CABIN SEAT TRACK, STA 200 TO 256, RBL 22, CORROSION. ACCOMPLISHED SEAT TRACK SPLICE REPAIR PER BOEING DWG SR09530085 AND DC9 SRM 53-05 FIG 4F.

Part: PAN — CORRODED (FUSELAGE)

FWD CARGO DOOR JAMB PAN, CORROSION. ACCOMPLISHED JAMB PAN SPLICE REPAIR PER B717 SRM 53-20-15 FIG 201 REPAIR 6.

Part: SEAT TRACK — CORRODED (FUSELAGE)

CABIN SEAT TRACK, STA 165, RBL 7, CORROSION. ACCOMPLISHED SEAT TRACK SPLICE REPAIR PER B717 SRM 51-41-01 AND B717 SRM 51-41-02.

Part: WEB — CRACKED (FUSELAGE)

CABIN LONGERON FINGER WEB, STA 196, LONG L15L, CRACKED. ACCOMPLISHED LONGERON FINGER WEB DOUBLER REPAIR PER B717 SRM 51-70-10 FIG 201 REPAIR 2.

Part: SEAT TRACK — CORRODED (FUSELAGE)

CABIN SEAT TRACK, STA 165, LBL 7, CORROSION. ACCOMPLISHED SEAT TRACK SPLICE REPAIR PER B717 SRM 51-41-05.

Part: FLOOR SUPPORT — CORRODED (FUSELAGE)

CABIN FLOOR SUPPORT, STA 237, LBL 22 TO RBL 22, CORROSION. ACCOMPLISHED FLOOR SUPPORT REPLACEMENT PER B717 SRM 51-41-02.

Part: FLOOR SUPPORT — CORRODED (FUSELAGE)

CABIN FLOOR SUPPORT, STA 200, RBL 57, CORROSION. ACCOMPLISHED FLOOR SUPPORT REPLACEMENT PER B717 SRM 51-41-02.

Part: COMPRESSOR — STALLED (NR 1 ENGINE)

NR 1 ENGINE COMPRESSOR STALL, THEN IN FLIGHT AUTO SHUTDOWN. REMOVED & REPLACED NR 1 ENGINE.

Part: COMPRESSOR — STALLED (RIGHT)

COMPRESSOR STALL RIGHT ENGINE AT FL 180 WITH CLIMB POWER CHANGE TGT 1149. REMOVED AND REPLACED RT ENG PER TASK CARD 603. RAN ENGINE & LEAK & OPS CHECK GOOD.

Part: SKIN — DENTED (FUSELAGE)

DENT ON FUSELAGE STA 239 LONG 17 LT. CUT DAMAGE LT SKIN SECTION BETWEEN STA 229 TO 264 AND LONG 15L TO 18L, INSTALLED NEW SKIN SECTION AND DOUBLER REPAIR PER B717 SRM 53-00-01 FIG 201 SHEET 4 REPAIR 6.

Part: SLIDE — DAMAGED (R1 DOOR)

R1 SLIDE PACK COVER LOOSE AND COVER RIPPED BY CATERING. SLIDE COVER DAMAGED AND SLIDE PIN PULLED OUT OF R1 SLIDE. REMOVED AND REPLACED R1 SLIDE ASSY AND SLIDE COVER ASSY REF MM 25 61.

Part: SKIN — DENTED (FUSELAGE)

TWO DENTS FOUND AFT OF L1 DOOR APPROXIMATELY STATION 235.5 LONGERON 16L. INSTALLED PERMANENT FLUSH REPAIR AT STA 235.5 AND BETWEEN LONGERON 16 AND 17 LEFT IAW B717 SRM 53-00-01 FIG 204. DIMENSIONS OF REPAIR 8.25 X 7.25 INCH.

Part: LINE — LEAKING (HYDRAULIC SYS)

TWENTY MILES FROM MEM RT HYD QTY LOW NR 2 ALERT ILLUMINATED HYD QTY DROPPED TO 2.1. AT 3.1 CAPTAIN DECLARED EMERGENCY. PERFORMED QRH LANDING AND TAXIING PHASE. FOUND RT SPOILER ACT UPPER HYD LINE LEAKING. REPLACED OR PER S/P 20-10. LEAK AND OPS CHECK GOOD AT THIS TIME.

Part: ENGINE — FAILED (LEFT)

LEFT HAND ENGINE, LOUD POP AT FL350. ENGINE WAS NOTICED TO BE SPOOLING DOWN AT IDLE OIL QUANTITY WAS AT 2 QUARTS, OIL PRESSURE -0- AND RED BOX. REMOVED AND REPLACED LEFT HAND ENGINE ASSY.