N568FE

Part: SEAT TRACK — WORN (ZONE 200) · airframe 69,821 hrs · 22,602 cycles

UPPER CARGO SEAT TRACK 28L, FS 1884L TO 1661L HAS WORN LOBES (5 EACH) FS 1871, 1730, 1690, 1681, AND 1664. BLENDED (5 EACH) AREAS STA 1871, 1730, 1690, 1681 AND 1664 SEAT TRACK FOUND TO BE WITHIN LIMITS IAW SRM 53-70-00 FIG 5 EXCEPT STA 1730 FOUND TO BE OUT OF LIMITS IAW SRM 53-70-00 FIG 5. FABRICATED NEW SEAT TRACK ON MAE TRAVELER NR T7/717467 AND 2 EACH HAT SPLICES ON MAE TRAVELER T7/717468 IAW SRM. INSTALLED NEW SEAT TRACK AT UPPER CARGO SEAT TRACK 28L STA 1711 TO STA 1750 IAW SRM 53-70-00 FIG 5.

Part: HEAD — SHEARED (FIRE BOTTLE) · airframe 69,112 hrs · 22,248 cycles

MDIS: PER FLIGHT CREW, ON PREFLIGHT FOUND EAD ALERT NR 2 ENG NR 1 FIRE BOTTLE PRESSURE LOW ALERT AND OVERHEAD DISCHARGE LIGHT ON. WHILE T/S CONFIRMED NR 2 ENG NR 1 FIRE BOTTLE IS DISCHARGED. FOUND ON ENG SIDE OF BOTTLE DISCHARGE HEAD ASSY TO BE SHEARED IN HALF, SEPARATING IT FROM DISCHARGE LINE. REMOVED AND INSTALLED NR 2 ENGINE/APU FIRE EXTINGUISHER CONTAINER. INSTALLED DEPLOYMENT LINE AND DISCHARGE CARTRIDGES, A/C OK TO CONTINUE.

Part: CONNECTOR — DISCONNECTED (NR 2 TRANSDUCER) · airframe 67,608 hrs · 21,551 cycles

AFTER GEAR WAS EXTENDED ON APPROACH GOT "ANTI SKID L FAIL" LEVEL 2 ALERT. RAN QRH PROCEDURE SEVERAL TIMES BUT CONTINUED TO HAVE SAME ALERT. LANDING UNEVENTFUL WITH INSPECTION BY FIRE DEPT PERSONNEL. REMOVED AND REPLACED ANTI-SKID CONTROL UNIT. NO HELP. FOUND NR 1 WHEEL TRANSDUCER WIRING CONNECTOR DISCONNECTED. REINSTALLED NR 1 TRANSDUCER. NO HELP. FOUND NR 2 WHEEL TRANSDUCER ALSO DISCONNECTED. REINSTALLED NR 2 CONNECTOR AND PERFORMED ANTI-SKID TEST. ALL TESTS PASSED.

Part: REPAIR — DAMAGED (FUSELAGE) · airframe 67,325 hrs · 21,426 cycles

DURING AIRPLANE'S CONVERSION FROM P TO F/ACF, FOUND EXISTING REPAIR WITH MISSING MATERIAL ON EDGE AND DENT ON SKIN ON CUT CENTER CARGO DOOR. RECOMMENDED ACTION, TRIMMED OUT DAMAGED EDGE OF JAMB AD REPAIR FOR SRM 53-50-00 FIG 26 VOL 1.

Part: FASTENER — LOOSE · airframe 67,302 hrs · 21,415 cycles

DURING AIRPLANE'S CONVERSION FROM P TO F/ACF, FOUND A LOOSE FASTENER AT STA YN 358.210 (REF. AMERICAN AIRLINES E.S. # ESO 7349 DATED 04 SEPT 86). THE FASTENER WAS REPLACED WITH MS21140-06 BLIND BOLT WITH INSPECTION AT "C" CHECK (REF BOECOM SVC-TUL-999/MEC). PERFORMED CHECK AND FOUND INSTALLED HLT 159-8 FASTENER. NO MORE INSPECTION AND ACTION REQUIRED.

Part: STRINGER — CORRODED (BS 1059-1079) · airframe 67,302 hrs · 21,415 cycles

DURING CONVERSION FROM P TO F/ACF FOUND IN FWD CARGO COMPT B/T STA 1059 AND STA 1079 CORROSION AT STR 52. PERFOMED SKIN REPAIR PER SRM 53-20-00 FIG 47 VOL I. NEW BLANKET HAS BEEN INSTALLED PER SRM 51-35-01 VOL II.

Part: SHEAR TIE — CORRODED (BS 1977 S50R-50L) · airframe 67,302 hrs · 21,415 cycles

DURING AIRPLANE'S CONVERSION FROM P TO F/ACF FOUND IN AFT CARGO COMPT AT STA 1977 FROM STR 50 RT TO STR 50 LT SHEAR CLIP WITH CORROSION. REMOVED CORROSION IAW SRM 53-00-01 FIG 1B VOL I. REMOVED AND REPLACED SHEAR CLIP IAW SRM 51-35-01 VOL II.

Part: STRINGER — CORRODED (BS 1059-1079) · airframe 67,302 hrs · 21,415 cycles

DURING CONVERSION FROM P TO F/ACF, FOUND IN FWD CARGO COMPT B/T STA 1059 AND STA 1079 CORROSION AT STR 52. PERFORMED SKIN REPAIR PER SRM 53-20-00 FIG 7 VOL I. NEW BLANKET HAS BEEN INSTALLED PER SRM 51-35-01 VOL II

Part: NONE — NONE (NONE) · airframe 67,302 hrs · 21,415 cycles

DURING AIRPLANE'S CONVERSION FROM P TO F/ACF FOUND: FOR CUSTOMER REQUEST REPLACE HORIZONTAL STABILAZER CONSTANT SECTION UPPER SKIN PANEL 7. REMOVED AND REPLACED PLANK NR 7 IAW S/B 55-16 FOLLOWING INSTRUCTION AS PER PAR 2, PAGE 17-18, OPTION II. SINGLE PANEL REPLACEMENT OF CONSTANT SECTION, PAGE 27-29, FIG 4; REF EA 8-5510-96087. SKIN PANEL: ALC7204-501 FASTENER KIT: SB10550016-103.

Part: PRESSURE PANEL — CORRODED (CENTER TANK AREA) · airframe 67,302 hrs · 21,415 cycles

DURING AIRPLANE'S CONVERSION FROM P TO F/ACF FOUND: UPPER SURFACE, CENTER TANK, PRESSURE PANEL STA 1381, FROM X = -70 TO X =-105, SEVERE CORROSION. REMOVED RT SLANT PANEL, DISASSEMBLED, REMOVED CORROSION AFT. REMOVED DAMAGED GASKET, CHECKED LIMITS, RESUBMITTED AND AFTER REPAIRED AND INSTALLED NEW GASKET. REMOVED FASTENERS ON UPPER AFT CENTER TANK SKIN, TRIMMED AND REMOVED APB 7070-2 ANGLE. REMOVED CORROSION ON UPPER CENTER TANK SKIN AND ON AFA 0474-2 TEE, RESUBMITTED AND COMPLETED WORK PER ATTACHED EA 8-5710-93836 ANGLE P/N: APB7080U2 QTY: 1 SEAL P/N: AEA0487-2 QTY: 1 EDGE MEMBER SLANT PANEL P/N: AEA 0449-2 QTY: 1.

Part: PRESSURE PANEL — CORRODED (BS 1381) · airframe 67,302 hrs · 21,415 cycles

DURING AIRPLANE'S CONVERSION FROM P TO F/ACF FOUND: UPPER SURFACE, CENTER TANK, PRESSURE PANEL STA 1381, FROM X = -70 TO X =-105, SEVERE CORROSION. REMOVED RIGHT SLANT PANEL, DISASSEMBLIED, REMOVED CORROSION AFT, REMOVED DAMAGED GASKET, CHECKED LIMITS, RESUBMITTED AND AFTER REPAIRED AND INSTALLED NEW GASKET. REMOVED FASTENERS ON UPPER AFT CENTER TANK SKIN, TRIMMED AND REMOVED APB 7070- 2 ANGLE, REMOVED CORROSION ON UPPER CENTER TANK SKIN AND ON AFA 0474-2 TEE, RESUBMITTED AND COMPLETED WORK PER ATTACHED EA 8-5710-93836 ANGLE P/N: APB7080U2 QTY: 1 SEAL P/N: AEA0487-2 QTY: 1 EDGE MEMBER SLANT PANEL P/N: AEA 0449-2 QTY: 1.

Part: STRUCTURE — CORRODED (CENTER WING) · airframe 67,302 hrs · 21,415 cycles

DURING AIRPLANE'S CONVERSION FROM P TO F/ACF FOUND: AT STA 1290, X= -110 CORROSION UNDER FITTING AND UPPER SURFACE CENTER WING. REMOVED FITTING ANB7440-515, SHIM ANB7444-501 AND STIFFENER, REMOVED CORROSION, COMPLETED WORK PER EA 8-5710-93150 ATTACHED.

Part: STRUCTURE — CORRODED (CENTER WING BOX) · airframe 67,302 hrs · 21,415 cycles

DURING AIRPLANE'S CONVERSION FROM P TO F/ACF FOUND CENTER BOX LOWER SURFACE STA XCW 20 LT - XCW 17 RT STRINGER 39, CORROSION ON PREVIOUSLY REWORKED AREA'S. REMOVED CORROSION IAW 57-20-00 FIG 8 SH 2, AND ACCOMPLISHED ATTACHED EA 8-5710-96136.

Part: FITTING — CORRODED (WING CENTER BOX) · airframe 67,302 hrs · 21,415 cycles

DURING AIRPLANE'S CONVERSION FROM P TO F/ACF FOUND: AT STA 1290, X= -110 CORROSION UNDER FITTING AND UPPER SURFACE CENTER WING. REMOVED FITTING ANB7440-515, SHIM ANB7444-501 AND STIFFENER, REMOVED CORROSION, COMPLETED WORK PER EA 8-5710-93150 ATTACHED.

Part: RIB — CRACKED (WS 345L) · airframe 67,302 hrs · 21,415 cycles

DURING AIRPLANE'S CONVERSION FROM P TO F/ACF FOUND: LT WING STA XORS 345, BETWEEN STR 13-14, TOP OF THE RIB, CRACK 1 INCH LONG. PERFORMED REPAIR IAW FEDEX EA 8-5710-96133.

Part: FRAME — CRACKED (BS 421) · airframe 67,302 hrs · 21,415 cycles

DURING AIRPLANE'S CONVERSION FROM P TO F/ACF FOUND: STA 421 LT SIDE Z = -60, FRAME WITH CRACK 1 INCH LONG. REPAIR IAW SRM 53-00-01 FIG 8 VOL I.

Part: BULKHEAD — CRACKED (BS 1159) · airframe 67,302 hrs · 21,415 cycles

DURING AIRPLANE'S MODIFICATION FROM P TO F/ACF FOUND CENTER WING, FRONT SPAR, PRESSURE BULKHEAD, STA 1159, X = -10, Z = -75: CRACK 7 INCH LONG. PERFORMED STRIP PAINT AREA, PERFORMED STOP DRILL 5/16'' DIA HOLE AT BOTH ENDS OF CRACK, NDI CHECK IAW CMM 20-20-03, NO MORE CRACKS FOUND. INSTALLED TITANIUM DOUBLER FROM X = -17 TO X = 5.54 AS PER SRM 53-40-00 FIG 17 VOL I.

Part: REPAIR — NONE · airframe 67,302 hrs · 21,415 cycles

DURING AIRPLANE'S MODIFICATION FROM P TO F/ACF FOUND: AIR CONDITIONING COMPT, STA 535, LT SIDE, EXISTING REPAIR AT BULKHEAD. NO ACTION REQUIRED, BULKHEAD WEB REPAIRED PER ENGINEERING ROD 01-03-06-002 AND IS FAA 8110-3 APPROVED ON 2/21/01.

Part: REPAIR — NONE · airframe 67,302 hrs · 21,415 cycles

DURING AIRPLANE'S MODIFICATION FROM P TO F/ACF FOUND: CAC COMPT, BETWEEN STR 50-51 LT, STA 1129 FRAME WITH EXISTING REPAIR. REMOVED EXISTING FRAME REPAIR SPLICE IAW SRM 51-31-01 VOL II AND REPLACED FRAME FROM L48 LT TO L48 RT IAW DWG AAA 7046. FRAME P/N: AAA 7046-3, CLIP P/N: AAA7046-13.

Part: REPAIR — NONE · airframe 67,302 hrs · 21,415 cycles

DURING AIRPLANE'S MODIFICATION FROM P TO F/ACF FOUND: LT WING, LEADING EDGE, XORS 506, EXISTING REPAIR ON LOWER SKIN. NO ACTION REQUIRED. REPAIR MEETS SRM 57-10-00 FIG 68 REQUIREMENTS.

Part: REPAIR — NONE · airframe 67,302 hrs · 21,415 cycles

DURING AIRPLANE'S MODIFICATION FROM P TO F/ACF FOUND: AIR CONDITIONING COMPT, BULKHEAD, RT SIDE, STA 535: EXISTING REPAIR. NO ACTION REQUIRED. BULKHEAD WEB REPAIRED PER ENGINEERING ROD 01-03-06-002 AND IS FAA 8118-3 APPROVED ON 2/21/01.

Part: SKIN — DENTED (LT AILERON) · airframe 67,302 hrs · 21,415 cycles

DURING AIRPLANE'S MODIFICATION FROM P TO F/ACF FOUND: LT WING, INBOARD AILERON, LOWER SIDE, STA XIA = 347-341: 3EA DENT IN AREA 3.4 X 3.7 INCH, MAX DEPTH .190 INCH. NO DAMAGE FOUND AT RIB LOCATION. ACCOMPLISHED LT INBOARD LOWER SKIN REPAIR IAW SRM 57-10-00 FIG 56, VOL I.

Part: REPAIR — NONE · airframe 67,302 hrs · 21,415 cycles

DURING AIRPLANE'S MODIFICATION FROM P TO F/ACF FOUND: LT WING, LEADING EDGE, LOWER SIDE, XORS 506: EXISTING REPAIR. NO ACTION REQUIRED. REPAIR MEETS SRM 57-10-00 FIG 68 REQUIREMENTS.

Part: FASTENER — CORRODED (L/E SLAT) · airframe 67,302 hrs · 21,415 cycles

DURING AIRPLANE'S MODIFICATION FROM P TO F/ACF FOUND: LT WING, DROPPED LEADING EDGE, EXISTING REPAIR DOUBLER ON UPPER SIDE. REMOVED RUST ON FASTENER BY BRUSHING AND REPROTECTED IAW SRM 51-21-01. EXISTING REPAIR IS CONFORM TO SRM 57-10-00 FIG 55 FOLLOWING EO 8-5100-7-50001 CRITERIA.

Part: CHANNEL — MISREPAIRED (FUSELAGE) · airframe 67,302 hrs · 21,415 cycles

DURING AIRPLANE'S MODIFICATION FROM P TO F/ACF FOUND: FWD CARGO COMPT STA 959, X= 58, CHANNEL WITH EXISTING REPAIR. REPAIR DOESN'T MEET SRM CRITERIA. REMOVED EXISTING REPAIR AND ACCOMPLISHED NEW SPLICE REPAIR AT STA 1019, X=58, AS PER SRM 53-70-00 FIG 7 SH 5, 6 VOL I.

Part: REPAIR — NONE · airframe 67,302 hrs · 21,415 cycles

DURING AIRPLANE'S MODIFICATION FROM P TO F/ACF FOUND: LT WING, LEADING EDGE, STA XFS 150, EXISTING REPAIR ON EXT SIDE. NO ACTION TAKEN, REPAIR IS CONFORM TO SRM 57-10-00 FIG 40.

Part: REPAIR — NONE · airframe 67,302 hrs · 21,415 cycles

DURING AIRPLANE'S MODIFICATION FROM P TO F/ACF FOUND: CENTER CARGO COMPT STA 1721, EXISTING REPAIR ON BEAM. NO ACTION TAKEN, REPAIR IS CONFORM TO SRM 53-00-01 FIG 9 SH 7.

Part: REPAIR — NONE · airframe 67,302 hrs · 21,415 cycles

DURING AIRPLANE'S MODIFICATION FROM P TO F/ACF FOUND: RIGHT WING, INBOARD FLAP, STA XIFH 140, EXISTING REPAIR WITH CHARRY RIVETS. NO ACTION TAKEN, EXISTING REPAIR MEETS SRM 57-00-01 FIG 4 SH 2 REQUIREMENTS. BLIND FASTENER ACCEPTABLE PER SRM 57-00-01 PAR 14) E) 2) WITH VISUAL INSPECTION AT C-CHECK.

Part: REPAIR — NONE · airframe 67,302 hrs · 21,415 cycles

DURING AIRPLANE'S MODIFICATION FROM P TO F/ACF FOUND: RT WING, LEADING EDGE STA XFS 155, EXISTING REPAIR ON SKIN. NO ACTION TAKEN, REPAIR IS CONFORM TO SRM 57-10-00 FIG 40.

Part: REPAIR — NONE · airframe 67,302 hrs · 21,415 cycles

DURING AIRPLANE'S MODIFICATION FROM P TO F/ACF FOUND: STA 1159, STR 42-43, RT, EXTERNAL REPAIR DOUBLER. NO ACTION TAKEN, REPAIR IS CONFORM TO SR10530073-7003.

Part: REPAIR — NONE · airframe 67,302 hrs · 21,415 cycles

DURING AIRPLANE'S MODIFICATION FROM P TO F/ACF FOUND: CENTER CARGO COMPT, STA 1701, EXISTING REPAIR ON BEAM. NO ACTION TAKEN, REPAIR IS CONFORM TO SRM 543-60-00 FIG 3.

Part: REPAIR — NONE · airframe 67,302 hrs · 21,415 cycles

DURING AIRPLANE'S MODIFICATION FROM P TO F/ACF FOUND: BETWEEN STA 575-595, STR 44-46, LT EXTERNAL REPAIR DOUBLER. NO ACTION REQUIRED, REPAIR MEETS CRITERIA OF SRM 53-20-00 FIG 2.

Part: SKIN — DAMAGED (FUSELAGE) · airframe 67,302 hrs · 21,415 cycles

DURING AIRPLANE'S MODIFICATION FROM P TO F/ACF FOUND STA 889 STR 39-41, RT, EXTERNAL REPAIR DOUBLER. REMOVED EXISTING DOUBLER IAW 51-33-01 VOL II. PERFORMED SKIN REPAIR IAW EA 8-5330-93512.

Part: REPAIR — NONE · airframe 67,302 hrs · 21,415 cycles

DURING AIRPLANE'S MODIFICATION FROM P TO F/ACF FOUND STA 888-905, STR 42-43, RT, FWD CARGO DOOR, LWR FWD ANGLE: EXTERNAL REPAIR DOUBLER. NO ACTION TAKEN, REPAIR MEETS CRITERIA OF SRM 52-10-00 FIG 17.

Part: REPAIR — NONE · airframe 67,302 hrs · 21,415 cycles

DURING AIRPLANE'S MODIFICATION FROM P TO F/ACF FOUND BETWEEN STA 555-575, STR 46-48, LT, EXTERNAL REPAIR DOUBLER. RECOMMENDED ACTION: NO ACTION REQUIRED, REPAIR MEETS SRM 53-20-00 FIG 2 CRITERIA.

Part: REPAIR — NONE · airframe 67,302 hrs · 21,415 cycles

DURING AIRPLANE'S MODIFICATION FROM P TO F/ACF FOUND: BETWEEN STA 695-715, STR 51-52 RT, FLUSH REPAIR. NO ACTION REQUIRED, REPAIR IS PER DWG SR10530038-7013.

Part: REPAIR — NONE · airframe 67,302 hrs · 21,415 cycles

DURING AIRPLANE'S MODIFICATION FROM P TO F/ACF FOUND: CTR CARGO DOOR, EXTERNAL SIDE SKIN 2 EA REPAIR. NO ACTION REQUIRED, REPAIR MEETS CRITERIA OF SRM 52-10-00 FIG 17.

Part: REPAIR — NONE (NONE) · airframe 67,302 hrs · 21,415 cycles

DURING AIRPLANE'S MODIFICATION FROM P TO F/ACF FOUND: BETWEEN STA 1099-1139, STR 46-48, LT, EXTERNAL REPAIR DOUBLER. NO ACTION REQUIRED, REPAIR IS CONFORM TO SRM 53-20-00 FIG 6 BEFORE MARCH 2000.

Part: REPAIR — NONE · airframe 67,302 hrs · 21,415 cycles

DURING AIRPLANE'S MODIFICATION FROM P TO F/ACF MODIFICATION FOUND: STA 959, STR 39-42 RT, EXTERNAL REPAIR DOUBLER. NO ACTION REQUIRED, REPAIR IS CONFORM TO SRM 53-50-00 FIG 9 SH 1.

Part: REPAIR — NONE · airframe 67,302 hrs · 21,415 cycles

DURING AIRPLANE'S MODIFICATION FROM P TO F/ACF FOUND BETWEEN STA 275-304 STR 28-29 LT, 2 FLUSH PATCH WITH INTERNAL DOUBLER. NO ACTION REQUIRED. REPAIR IS CONFORM TO SRM 53-20-00 FIG 11.

Part: SKIN — DAMAGED (RT WING) · airframe 67,302 hrs · 21,415 cycles

DURING AIRPLANE'S MODIFICATION FROM P TO F/ACF FOUND RT WING LE XORS 280: EXTERNAL SKIN WITH MISSING MATERIAL. REPAIRED FLANGE RIB IAW SRM 57-00-01 FIG 10 VOL I AND REPLACED SKIN IAW SRM 51-35-01.

Part: REPAIR — NONE · airframe 67,302 hrs · 21,415 cycles

DURING AIRPLANE'S MODIFICATION FROM P TO F/ACF FOUND BETWEEN STA 475-505 STR 30-32 LT, EXTERNAL REPAIR DOUBLER. NO ACTION REQUIRED, THE REPAIR IS ALREADY APPROVED BY A.A. ES 07349.

Part: REPAIR — NONE · airframe 67,302 hrs · 21,415 cycles

DURING AIRPLANE'S MODIFICATION FROM P TO F/ACF FOUND: BETWEEN STA 979-999 STR 36-39, RIGHT, EXTERNAL REPAIR DOUBLER. NO ACTION REQUIRED, REPAIR IS CONFORM TO SRM 53-20-00 FIG 6 SH 3.

Part: RIB — CRACKED (WING) · airframe 67,302 hrs · 21,415 cycles

DURING AIRPLANE'S CONVERSION FROM P TO F/ACF FOUND: XORS 345 BETWEEN STR 42 AND STR 43 RIGHT WING, REWORKED AREA 0.354 X 0.354 INCH AND CRACK 0.275 INCH LONG ON RIB ANGLE. TRIMMED LEG CAP FLUSH TO HORIZONTAL LEG TO COMPLETELY REMOVE CRACK, AND INSTALLED T-ANGLE REPAIR IAW SRM 57-20-00 FIG 27 VOL I.

Part: REPAIR — NONE (FUSELAGE) · airframe 67,302 hrs · 21,415 cycles

DURING AIRPLANE'S MODIFICATION FROM P TO F/ACF FOUND: STA 1781 STR 39-41 RIGHT, EXTERNAL REPAIR DOUBLER. EXISTING REPAIR WILL BE MODIFIED DURING P TO F CONVERSION (NC 30008).

Part: RIB — CRACKED (RT WING) · airframe 67,302 hrs · 21,415 cycles

DURING AIRPLANE'S CONVERSION FROM P TO F/ACF FOUND: XORS 345 BETWEEN STR 42 AND STR 43 RIGHT WING, REWORKED AREA 0.354 INCH X 0.354 INCH AND CRACK 0.275 INCH LONG ON RIB ANGLE. TRIMMED LEG CAP FLUSH TO HORIZONTAL LEG TO COMPLETELY REMOVE CRACK, AND INSTALLED T-ANGLE REPAIR IAW SRM 57-20-00 FIG 27 VOL I.

Part: SEAT TRACK — MISOVERHAULED (FUSELAGE) · airframe 67,302 hrs · 21,415 cycles

DURING AIRPLANE'S CONVERSION FROM P TO F/ACF FOUND: WRONGLY PERFORMED AT THE STA 774 AND STA 672 A CUT TRACK X = =107.250. THE CORRECT CUT IS AT STA 665. CUT SEAT TRACK AT STA 799 AND PERFORMED A NEW SPLICE REPAIR AT STA 799, IAW SRM 53-70-00 FIG I VOL I.

Part: REPAIR — NONE (FUSELAGE) · airframe 67,302 hrs · 21,415 cycles

DURING AIRPLANE'S MODIFICATION FROM P TO F/ACF FOUND: STA 1711 STR 40-42 RIGHT, EXTERNAL REPAIR DOUBLER. REPAIR MEETS SRM 53-50-00 FIG 9 CRITERIA, EXISTING REPAIR REMOVED TO ACCOMPLISH NRC N00307.

Part: ATTACH FITTING — CORRODED (RT WING FLAP) · airframe 67,302 hrs · 21,415 cycles

DURING AIRPLANE'S CONVERSION FROM P TO F/ACF FOUND: RT WING, OUTBOARD FLAP, INBD ATTACH BRACKET, CORROSION ON LOWER ATTACK SURFACE, INSIDE THE BORES AND IN THE LATERAL BORE OF THE FITTING. REMOVED FAIRING ATTACHING STRUCTURE IAW SRM 51-35-01 VOL II. SENT OUT HINGE BRACKET TO AN AUTHORIZED VENDOR FOR IRAN/OVERHAUL IAW CMM 57-44-09. AFTER RECEIVING SERVICEABLE HINGE BRACKET, REINSTALLED FAIRING ATTACHING STRUCTURE IAW SRM 51-35-01 VOL II. RIGHT INBOARD FWD HINGE BRACKET P/N: ARC0502-502.

Part: ATTACH BRACKET — CORRODED (TE FLAP) · airframe 67,302 hrs · 21,415 cycles

DURING AIRPLANE'S CONVERSION FROM P TO F/ACF FOUND RT WING, OUTBD FLAP, INBD ATTACH BRACKET, CORROSION ON LOWER ATTACK SURFACE, INSIDE THE BORES AND IN THE LATERAL BORE OF THE FITTING. REMOVED FAIRING ATTACHING STRUCTURE IAW SRM 51-35-01. SENT OUT FOR IRAN/OVERHAUL INBD HINGE BRACKET TO AN AUTHORIZED VENDOR IAW CMM 57-44-09. AFTER RECEIVING OF SERVICEABLE HINGE BRACKET REINSTALL FAIRING IAW SRM 51-35-01. RT INBD HINGE BRACKET. P/N ARC0502

Part: REPAIR — NONE · airframe 67,302 hrs · 21,415 cycles

DURING AIRPLANE'S MODIFICATION FROM P TO F/ACF FOUND BETWEEN STA 840-859, STR 39-42, RT, 3 EA FLUSH PATCH WITH INTERNAL DOUBLER. NO ACTION REQUIRED. REPAIR IS CONFORM TO SRM 53-20-00 FIG 13 SH 8/9. PERFORMED EA 8-5330-94668 PART 1 INSPECTION. NO DEFECT FOUND.

Part: SKIN — DENTED (ELEVATOR) · airframe 67,302 hrs · 21,415 cycles

DURING AIRPLANE'S MODIFICATION FROM P TO F/ACF FOUND: 4 EA DENT ON THE UPPER SKIN OF DETACHABLE ELEVATOR OF LEFT HORIZONTAL STABILAZER. REMOVED LT DETACHABLE ELEVATOR IAW MM 27-30-01; REMOVED L/E PANELS FOR ACCESS IAW SRM 51-31-01 VOL II. CUT OUT DAMAGED AREA, BETWEEN XE 72.575 AND XE 79, AND REPAIR IAW SRM 55-10-00 FIG 7. AT STA XE 89, DRILLED 3/16 HOLE AND INSTALLED RIVET IAW SRM 55-00-01 FIG 1A. REINSTALLED DETACHABLE ELEVATOR IAW MM 27-30-01.

Part: SKIN — DENTED (ELEVATOR) · airframe 67,302 hrs · 21,415 cycles

DURING AIRPLANE'S MODIFICATION FROM P TO F/ACF FOUND 2EA DENT AND 1EA NICK OF 5 INCH LONG ON THE UPPER SKIN OF DETACHABLE ELEVATOR OF RT HORIZONTAL STABILIZER. REMOVED DETACHABLE IAW MM 27-30-01; PERFORMED CUT OUT DENTED AREA FROM STA XE 72.575 TO XE 84.00 AND REPAIRED IAW SRM 55-10-00 FIG 7. AT STA XE 90.000 REPAIRED IAW SRM 55-10-01 FIG 7. REINSTALLED DETACHABLE ELEVATOR IAW MM 27-30-01.

Part: NONE — NONE (NONE) · airframe 67,302 hrs · 21,415 cycles

DURING AIRPLANE'S MODIFICATION FROM P TO F/ACF FOUND: STA 1159, STR 37-40 RT, EXTERNAL REPAIR DOUBLER. NO ACTION REQUIRED, REPAIR IS CONFORM TO SRM 53-40-00 FIG 8; PERFORMD E.A 8-5330- 94669 PART 1 INSPECTION.

Part: REPAIR — NONE (FUSELAGE) · airframe 67,302 hrs · 21,415 cycles

DURING AIRPLANE'S MODIFICATION FROM P TO F/ACF FOUND: BETWEEN STA 824-840 STR 49-50 LT, FLUSH PATCH WITH INTERNAL DOUBLER. NO ACTION REQUIRED: EXISTING REPAIR IS CONFORM TO SRM 53-20-00 FIG 13 SH 8, PERFORMED INSPECTION IAW EA 8-53-30-94668 PT 1.

Part: REPAIR — NONE (FUSELAGE) · airframe 67,302 hrs · 21,415 cycles

DURING AIRPLANE'S MODIFICATION FROM P TO F/ACF FOUND: 1EA FLUSH PATCH WITH INTERNAL DOUBLER, BETWEEN STA 824-840 STR 49-50 RT. NO ACTION REQUIRED: EXISTING REPAIR IS CONFORM TO SRM 53-20-00 FIG 13 SH 8, PERFORMED INSPECTION PER EA 8-5330-94668 PT 1.

Part: REPAIR — NONE (FUSELAGE) · airframe 67,302 hrs · 21,415 cycles

DURING AIRPLANE'S MODIFICATION FROM P TO F/ACF FOUND STA1159 STR 37-40 LT, EXTERNAL REPAIR DOUBLER. NO ACTION REQUIRED. THE REPAIR IS CONFORM TO SRM 53-40-00 FIG 8, PERFORMED E.A. 8-5330-94669 PT 1. NO DEFECT FOUND.

Part: REPAIR — NONE (FUSELAGE) · airframe 67,302 hrs · 21,415 cycles

DURING AIRPLANE'S MODIFICATION FROM P TO F/ACF FOUND BETWEEN STA 421-430 STR 35-36 LT, 1EA FLUSH PATCH WITH INTERNAL DOUBLER. NO ACTION REQUIRED, THE REPAIR IS CONFORM TO SRM 53-20-00 FIG 13 SH 4. PERFORMED EA 8-5330-94667 PT 1 INSPECTION, NO DEFECT FOUND.

Part: SKIN — BULGED (BS 959) · corrosion level 2 · airframe 67,302 hrs · 21,415 cycles

DURING AIRPLANE'S MODIFICATION FROM P TO F/ACF FOUND: AT STA 959 STR 47 LT SIDE ON EXTERNAL SURFACE, INSTALLED 12 EA CHERRY RIVETS AND NOTED BULGING WITH SUSPECT CORROSION. REMOVED FASTENERS IAW SRM 51-31-01 VOL II AND FOUND SEVERE CORROSION. PERFORMED REPAIR IAW SRM 53-20-00 FIG 6 SH 5 VOL I.

Part: REPAIR — UNKNOWN (ELEVATOR) · airframe 67,302 hrs · 21,415 cycles

DURING AIRPLANE'S MODIFICATION FROM P TO F/ACF FOUND: INSTALLED REPAIR ON LT OUTBOARD ELEVATOR LOWER SKIN AT STA XE 347.948. THE EXISTING REPAIR COMPLY SRM 55-10-00 FIG 1 FOLLOWING FEDEX EO 8-5100-7-5001 PT2.

Part: REPAIR — UNKNOWN (FUSELAGE) · airframe 67,302 hrs · 21,415 cycles

DURING AIRPLANE'S MODIFICATION FROM P TO F/ACF FOUND: STA 1248-1256, LT SIDE, STR 25-27, EXISTING REPAIR ON JAMB DOOR. ADDED 2 EA RIVETS IAW SRM 53-50-00 FIG 19 SH 1. REPAIR MEETS SRM 53-50-00 FIG 19 REQUIREMENTS.

Part: REPAIR — UNKNOWN (FUSELAGE) · airframe 67,302 hrs · 21,415 cycles

DURING AIRPLANE'S MODIFICATION FROM P TO F/ACF FOUND: STA 1248-1256 RT SIDE, EXISTING REPAIR ON JAMB DOOR STR 27-25. REPAIR MEETS SRM 53-50-00 FIG 19 CRITERIA, BUT MUST BE ADDED 2EA RIVETS IAW SRM 53-50-00 FIG 19 SH 1.

Part: REPAIR — UNKNOWN (HORIZONTAL STAB) · airframe 67,302 hrs · 21,415 cycles

DURING AIRPLANE'S MODIFICATION FROM P TO F/ACF FOUND: RT HORIZONTAL STABILIZER, FOUND REPAIR DOUBLER ON UPPER FRONT SPAR CAP, 4.5 X 18 INCHES. THE EXISTING REPAIR COMPLY ROD SKETCH 94-07-02-006 FOLLOWING FEDEX EO 8-5100-7- 5001 PT 2 CRITERIA.

Part: INTERCOSTAL — BROKEN (BS 859-879) · airframe 67,302 hrs · 21,415 cycles

DURING AIRPLANE'S CONVERSION FROM P TO F/ACF FOUND: FWD CARGO COMPT BETWEEN STA 859 - 879, STR 40-41 RT, INTERCOSTAL BROKEN. CUT OUT DAMAGED AREA AND INSTALLED DOUBLER PER SRM 53-00-01 FIG 4 SH 2.

Part: REPAIR — UNKNOWN (BS 1315-1301) · airframe 67,302 hrs · 21,415 cycles

DURING AIRCRAFT'S P TO F/ACF CONVERSION FOUND: AT STA 1315-1301 STR 27-25 RT SIDE, EXISTING REPAIR ON JAMB DOOR. REMOVED EXISTING REPAIR DOUBLER, PERFORMED HFEC INSPECTION AND INSTALLED NEW REPAIR IAW SRM 5350-00 FIG 19 SH 2.

Part: REPAIR — UNKNOWN (FUSELAGE) · airframe 67,302 hrs · 21,415 cycles

DURING AIRPLANE'S CONVERSION FROM P TO F/ACF FOUND: 1EA EXISTING REPAIR ON AFT LOWER CARGO DOOR, EXTERNAL UPPER AFT SIDE (7 INCH X 5 INCH). REPAIR IS CONFORM TO SRM 52-10-00 FIG 17.

Part: REPAIR — UNKNOWN (RT WING) · airframe 67,302 hrs · 21,415 cycles

DURING AIRPLANE'S CONVERSION FROM P TO F/ACF FOUND: 1EA EXISTING REPAIR ON RT WING, STA 1159 BTW STR 28-29. REPAIR IS CONFORM TO SRM 57-20-00 FIG 6 SH 3 FOLLOWING EO 8-5100-7-5001 PT 2 CRITERIA.

Part: DOOR FRAME — CRACKED (FUSELAGE) · airframe 67,302 hrs · 21,415 cycles

DURING AIRPLANE'S P TO F MODIFICATION FOUND INTERNAL FUSELAGE: CRACK .300" LONG ON WEB OF JAMB DOOR, STA 1256, L16 RT. PERFORMED STOP DRILL CRACK AND NDI. INSTALLED REPAIR DOUBLER IAW SRM 53-50-00 FIG 19, VOL I.

Part: DOOR FRAME — CRACKED (FUSELAGE) · airframe 67,302 hrs · 21,415 cycles

DURING AIRPLANE'S P TO F MODIFICATION FOUND INTERNAL FUSELAGE: CRACK .300" LONG ON WEB OF JAMB DOOR STA 1256 L 16, RT. STOP DRILL CRACK, PERFORMED NDI, INSTALLED REPAIR DOUBLER IAW SRM 53-50-00 FIG 19 VOL I.

Part: REPAIR — UNKNOWN (DOOR FRAME) · airframe 67,302 hrs · 21,415 cycles

DURING AIRPLANE'S P TO F MODIFICATION FOUND AT STA 1305-1316 STR 25-27 LT SIDE, EXISTING REPAIR ON JAMB DOOR. PERFORMED HFEC INSPECTION, REMOVED EXISTING REPAIR DOUBLER AND INSTALLED A NEW ONE IAW SRM 53-50-00 FIG 19, SH 2.

Part: SKIN — CORRODED (BS 1119) · airframe 67,302 hrs · 21,415 cycles

DURING AIRPLANE' S P TO F MODIFICATION FOUND: STA 1119 BETWEEN STR 34-37 RT SIDE, EXT SURFACE WITH CORROSION AND SOME RIVETS WITH HEAD BROKEN. CUT SKIN BETWEEN STR 42-43 RT SIDE AT STA 1104, PERFORMED REPAIR IAW SRM 543-20-00 FIG 12 SH 6.

Part: SKIN — CORRODED (FUSELAGE) · airframe 67,302 hrs · 21,415 cycles

DURING AIRPLANE'S P TO F MODIFICATION FOUND STA 1139 STR 46-47 ON EXT SURFACE RIVETS WITH HEAD BROKEN AND SKIN BULGING. SUSPECT CORROSION. CUT OUT DAMAGED SKIN BETWEEN STR 45 AND STR 46 LT SIDE AT STA 1145, AND PERFORMED REPAIR IAW SRM 53-20-00 FIG 12 SH 4 & 5 VOL I.

Part: REPAIR — IMPROPER (BS 475-480) · airframe 67,302 hrs · 21,415 cycles

DURING AIRPLANE' S P TO F MODIFICATION FOUND: AT STA 475-480, STR 30 RT, 1EA EXT REPAIR DOUBLER. REMOVED AND SCRAPPED EXISTING REPAIR DOUBLER IAW SRM 51-33-01, PERFORMED NEW REPAIR PER SRM 53-20-00 FIG 6 SH 15.

Part: SKIN — CORRODED (BS 348) · airframe 67,302 hrs · 21,415 cycles

DURING AIRPLANE' S P TO F MODIFICATION FOUND: AT STA 348 STR 24-28 LT, BULGING ON SKIN WITH HL NOT INSTALLED CORRECTLY. REMOVED FRAME IAW SRM 51-33-01 AND SRM 51-35-01. PERFORMED SKIN AND DYE CHECK IAW CMM 20-30-02, INSTALLED FINGER DOUBLER IAW SRM 53-20-00 FIG 13 SH 2 VOL I. INSTALLED FRAME. FRAME, P/N ABA7037-9.