N489FE

Part: WINDOW — OBSTRUCTED (COCKPIT) · airframe 43,649 hrs · 28,487 cycles

CAPT'S WINDOW WILL NOT OPEN. FOUND TRIM AROUND WINDOW IS NOT INSTALLED PROPERLY. TOO MUCH OF TRIM PROTRUDING ABOVE WINDOW CHANNEL THUS NOT ENOUGH CLEARANCE FOR WINDOW TO CLEAR PANEL. LOOSENED FASTENERS AROUND TRIM PANEL BELOW L-2 WINDOW. PANEL WILL NOT YET MOVE DOWN ENOUGH FOR L-2 WINDOW LOWER ROLLER MECHANISM NOT TO CONTACT UPPER EDGE OF PANEL. PANEL IS PHYSICALLY EXTENDING UP TOO HIGH ABOVE THE SLIDING WINDOW TRACK CAUSING THE ROLLERS AND LOCK MECHANISM OF WINDOW TO RUB ON TOP OF PLASTIC PANEL. COMPLIED WITH EA 7-2510-155488. OK FOR SERVICE.

Part: FLOORBEAM — CORRODED (BS 1070) · corrosion level 2 · airframe 42,631 hrs · 27,705 cycles

FLOORBEAM CORRODED STA 1070, RBL 5 TO RBL 10. CUT OUT DAMAGED AREA, FABRICATED 2 FILLERS, 2 REPAIR ANGLES AND INSTALLED IAW SRM 53-10-8, 51-10-2 AND 51-30-2.

Part: FLOORBEAM — CORRODED (BS 1130) · corrosion level 2 · airframe 42,631 hrs · 27,705 cycles

FLOORBEAM CORRODED AT BS 1130 RBL 30 TO RBL 46. CUT OUT DAMAGED AREA, FABRICATED 2 FLOORBEAM REPAIRS, 1 STRAP, 1 FILLER, 2 ANGLES, 1 STRAP AND 1 FILLER . HEAT TREATED PARTS TO T6 CONDITION IAW FAS ENG REPORT 2-37153-801 REV A AND INSTALLED PARTS IAW 53-10-8 AND 51-10-2.

Part: FLOORBEAM — DAMAGED (BS 1130) · airframe 42,631 hrs · 27,705 cycles

DOUBLE DRILLED HOLES IN FLOORBEAM STA 1130 LBL 47. CUT OUT DAMAGE IN FLOORBEAM DIMS 1" X 1", FABRICATED NEW ANGLE, HEAT TREATED PART TO T6 CONDITION IAW FAS ENG REPORT 2-37153-801 REV A, FABRICATED STRAP, FILLERS AND INSTALLED IAW SRM 51-30-2, 53-10-8, AND 51-10-2.

Part: SKIN — BENT (CARGO DOOR) · airframe 42,631 hrs · 27,705 cycles

MAIN CARGO DOOR AFT EDGE AT STR 10 LT IS BENT OUT. TRIMMED OUT DAMAGED AREA, HFEC INSPECTED CUTOUT WITH NO DEFECTS NOTED IAW NDTM 51-00-00, HFEC INSPECTED HOLES WITH NO DEFECTS NOTED NDTM 51-00-00, FABRICATED DOUBLER, TRIPLER, FILLER AND INSTALLED IAW EA 7-5320-135522.

Part: SKIN — CORRODED (HORIZONTAL STAB) · corrosion level 2 · airframe 42,631 hrs · 27,705 cycles

SURFACE CORROSION UNDER BASE OF NR 2 STATIC WICK ON RT HORIZ STAB OTBD T/E. REMOVED CORROSION AND FOUND OUT OF LIMITS AND CRACKED. TRIMMED OUT DAMAGE, FABRICATED DOUBLER PLATE, TWO FILLERS AND INSTALLED IAW SRM 51-30-2, 51-10-6, 55-20-3 AND 51-80-7.

Part: BEAM — DAMAGED (BS 480-520) · airframe 42,631 hrs · 27,705 cycles

AFTER REMOVING MAIN CARGO DOOR FWD UPPER SILL, FOUND EXISTING OPEN HOLES WITH SHORT SPACING AT STA'S 480, 490, 500 AND 520. DAMAGE REPAIR DOCUMENTED.

Part: BULKHEAD — CRACKED (MLG WW) · airframe 42,631 hrs · 27,705 cycles

RT W/W FWD BULKHEAD IS CRACKED BELOW APU LOAD CONTROL VALVE AT BS 870 RBL 18. REPAIRED RT WHEEL WELL BULKHEAD APU LOAD CONTROL VALVE AREA BS 870 RBL18 IAW SRM 53-10-9 FIG 5, REV 102.

Part: HINGE — WORN (CARGO DOOR) · airframe 42,631 hrs · 27,705 cycles

MAIN CARGO DOOR AFT HINGE SEGMENT HAS EXCESSIVE PLAY. REMOVED HINGE SECTION, FABRICATED NEW HINGE SECTION USING 5212791 PO NR 79014501 DIMS 48 1/2" LONG FOR UPPER SECTION AND 20 1/4" LONG FOR LOWER SECTION AND INSTALLED IAW DWG B27-53-070 REV B.

Part: SKIN — GOUGED (CARGO DOOR) · airframe 42,631 hrs · 27,705 cycles

MAIN CARGO DOOR INNER SURROUND DOUBLER GOUGED AT STA 640 STR 8L. EVALUATED AREA AND FOUND OUT OF LIMITS. REMOVED INNER SKIN DOUBLER SECTION, FABRICATED NEW SKIN AND INSTALLED IAW SRM 53-10-1, 51-30-2, 51-30-5 AND 51-10-2.

Part: SKIN — GOUGED (BS 480 S8L) · airframe 42,631 hrs · 27,705 cycles

MAIN CARGO DOOR INNER SURROUND DOUBLER GOUGED AT STA 480 STR 8L. EVALUATED AREA AND FOUND OUT OF LIMITS. REMOVED INNER SKIN DOUBLER SECTION, FABRICATED NEW SKIN AND INSTALLED IAW SRM 53-10-1, 51-30-2, 51-30-5 AND 51-10-2.

Part: SKIN — GOUGED (DOOR FRAME) · airframe 42,631 hrs · 27,705 cycles

MAIN CARGO DOOR INNER SURROUND DOUBLER GOUGED AT STA 620 TO 640 STR 4L. EVALUATED AREA AND FOUND OUT OF LIMITS. REMOVED INNER SKIN DOUBLER SECTION, FABRICATED NEW SKIN AND INSTALLED IAW SRM 53-10-1, 51-30-2, 51-30-5 AND 51-10-2.

Part: HINGE — WORN (CARGO DOOR) · airframe 42,631 hrs · 27,705 cycles

MAIN CARGO DOOR FWD HINGE SEGMENT HAS EXCESSIVE PLAY. REMOVED HINGE SECTION, FABRICATED NEW HINGE SECTIONS AND INSTALLED IAW DWG B27-53-070 REV B.

Part: SKIN — DAMAGED (FUSLEAGE) · airframe 42,631 hrs · 27,705 cycles

L-1 DOOR UPPER AND LOWER HINGE CUTOUT DOUBLERS HAVE COUNTERSUNK FASTENERS INSTALLED. REMOVED DOUBLERS, FABRICATED 2 NEW DOUBLERS, CADMIUM PLATED DOUBLERS IAW SOPM 20-40-01 AND INSTALLED IAW EO 7-5330-7-2345 PT 2 AND SRM 51-30-2.

Part: SKIN — CRACKED (LT AILERON) · airframe 42,631 hrs · 27,705 cycles

LT INBD AILERON LOWER SURFACE SKIN IS CRACKED AT FWD EDGE. SKIN CRACK FOUND OUT OF LIMITS. CUT OUT DAMAGED AREA DIMS 4 1/2" X 5 1/8", FABRICATED DOUBLER, FILLER AND INSTALLED IAW SRM 57-50-1, 57-50-5, 51-10-1, AND 51-30-2.

Part: SEAT TRACK — CORRODED (100) · corrosion level 2 · airframe 42,631 hrs · 27,705 cycles

SEAT TRACK CORRODED STA 970-990 RBL 24. REMOVED CORROSION AND FOUND OUT OF LIMITS. REMOVED SEAT TRACK SECTION. FABRICATED NEW SECTION USING BAC1520-792 7178-T6511 PO NR 9006020 DIMS 144" AND SPLICE ANGLES USING BAC1503-100122 7178-T6511 PO NR 2912649 DIMS 13 3/4" X 2" AND 1 STRAP USING 7075T-6 .250 PO NR 9008077 DIMS 8" X 2" AND INSTALLED IAW SRM 53-10-1, 53-10-5, 51-10-2 AND 51-30-2.

Part: SKIN — CORRODED (ZONE 100) · corrosion level 2 · airframe 42,631 hrs · 27,705 cycles

FWD PIT - CORROSION ON SKIN AT BS 660 (AFT SIDE) BETWEEN STRINGERS 28R AND 29L. CUT OUT DAMAGED AREA IAW SRM 51-10-1 REV 102. FABRICATED REPAIR DOUBLER, FABRICATED FILLER, INSTALLED REPAIR DOUBLER AND FILLER IAW SRM 51-30-2. FABRICATION IAW SRM 53-30-3, FIG. 3 & 51-10-3.

Part: STRINGER — CRACKED (BS 950D-950F) · corrosion level 2 · airframe 42,631 hrs · 27,705 cycles

AFT PIT STR 27L HAS CORROSION WITH EXFOLIATION AROUND FASTENERS BTWN BS 950D-950F. REMOVED CORROSION AND FOUND OUT OF LIMITS. REMOVED 3 EACH STRINGER SECTIONS, FABRICATED 3 FILLERS AND 4 EACH SPLICES. INSTALLED IAW SRM 51-10-6, 53-10-2, 53-10-3, AND 51-30-2.

Part: SEAT TRACK — CORRODED (BS 950) · corrosion level 2 · airframe 42,631 hrs · 27,705 cycles

CABIN SEAT TRACK BS 950 - 950, 10" LBL 24 OB UPPER FLANGE IS CORRODED AT FASTENERS. REMOVED CORROSION AND FOUND OUT OF LIMITS. REMOVED SEAT TRACK SECTION. FABRICATED NEW SECTION USING BAC1520-792 7178-T6511 PO NR 9006020 DIMS 91" AND INSTALLED IAW SRM 51-10-6, 53-10-5, 51-10-2 AND 51-30-2.

Part: SEAT TRACK — CORRODED (BS 640-660) · airframe 42,631 hrs · 27,705 cycles

CABIN SEAT TRACK BS 640 -660 LBL 56 IB FLANGE HAS SEVERAL SPOTS OF CORROSION. CORROSION FOUND OUT OF LIMITS. REMOVED SEAT TRACK SUPPORT FLANGE. FABRICATED NEW SEAT TRACK SUPPORT FLANGE AND INSTALLED IAW SRM 51-30-2, 51-20-1 AND 51-10-2.

Part: SKIN — CRACKED (BS 720 S27R) · airframe 42,631 hrs · 27,705 cycles

FUSELAGE SKIN LWR SIDE, HAS CRACK STA 720, STR 27R. REPAIRED IAW SRM 53-10-3 FIG 3 AND REPAIRED STRINGER 27R FWD PIT BETWEEN STA 700 TO 720 IAW SRM 53-10-3 FIG 1.

Part: STRINGER — CORRODED (ZONE 100) · corrosion level 2 · airframe 42,631 hrs · 27,705 cycles

CORROSION AROUND FASTENERS AT AFT PIT STA 1030 TO STA 1070 STRINGER 27L. REMOVED CORROSION AND FOUND OUT OF LIMITS. CUTOUT STRINGER DAMAGE, FABRICATED FILLER USING BAC1498-145 7075T-6 PO NR 2905741 DIMS 19" AND SPLICES USING BAC1498-131 7075T-6 PO NR 2912086 DIMS 14" AND INSTALLED IAW SRM 51-10-6, 53-10-1, 53-10-6, AND 51-30-2.

Part: FLOORBEAM — CORRODED (BS 312) · corrosion level 2 · airframe 42,631 hrs · 27,705 cycles

FWD LAV AREA FLOORBEAM ANGLE IS CORRODED AT BS 310 LBL 20. TRIMMED DAMAGE. FABRICATED 2 REPAIR, FABRICATED FILLER, HEAT TREATED PARTS TO T6 CONDITION IAW FAS ENG REPORT 2-37153-801 REV A, AND INSTALLED IAW DWG SR27-53-017 REV A.

Part: SEAT TRACK — CORRODED (ZONE 100) · corrosion level 2 · airframe 42,631 hrs · 27,705 cycles

CABIN SEAT TRACK AT STA 658 LBL 45 INBD FLANGE IS CORRODED. REMOVED SEAT TRACK SECTION BETWEEN STA 650 TO 690 LBL 45 AND 1EA SPLICER IAW SRM 51-30-2, LOCATED AND DRILLED NEW SEAT TRACK AND FABRICATED 1 EA SPLICER 2 EA ANGLES , AND 1 EA STRAP IAW SRM 53-10-5 FIG 1 AND 57-30-5 TREATED AND PRIMED IAW SRM 51-10-2, INSTALLED SEAT TRACK AND SPLICER IAW SRM 51-30-2.

Part: SEAT TRACK — CORRODED (BS 680-690) · airframe 42,631 hrs · 27,705 cycles

CABIN SEAT TRACK STA 680-690 RBL 24 FLANGE AND SPLICE CORRODED. REMOVED SEAT TRACK SECTION IAW SRM 51-30-2, LOCATED AND DRILLED NEW SEAT TRACK AND SPLICER IAW SRM 53-10-2, INSTALLED NEW SEAT TRACK AND SPLICER IAW SRM 51-30-2.

Part: SEAT TRACK — CORRODED (ZONE 100) · corrosion level 2 · airframe 42,631 hrs · 27,705 cycles

CABIN SEAT TRACK AT STA 720B LBL 45 OUTBD FLANGE UPPER SURF. HAS CORROSION. REMOVED SEAT TRACK SECTION LBL 45 BETWEEN STA 690 TO 740 AND 1EA SPLICER IAW SRM 51-30-2, LOCATED AND DRILLED NEW SEAT TRACK IAW SRM 53-10-5 FIG 1 TREATED AND PRIMED IAW SRM 51-10-2, INSTALLED NEW SEAT TRACK & SPLICER IAW SRM 51-30-2.

Part: SEAT TRACK — CORRODED (BS 950A-960) · airframe 42,631 hrs · 27,705 cycles

CABIN SEAT TRACK BS 960-950A RBL 24 IB UPPER FLANGE IS CORRODED AT FASTENERS. REMOVED SEAT TRACK SECTION IAW SRM 51-30-2. LOCATED AND DRILLED NEW SEAT TRACK SECTION AND FABRICATED SPLICE FOR 2EA ANGLES AND 1EA STRAP IAW SRM 53-10-5 FIG1. TREATED AND PRIMED IAW SRM 51-10-2. INSTALLED SEAT TRACK SECTION AND SPLICE IAW SRM 51-30-2 REV 102.

Part: SEAT TRACK — CORRODED (ZONE 100) · corrosion level 2 · airframe 42,631 hrs · 27,705 cycles

CABIN SEAT TRACK AT STA 695 RBL 24 INBD FLANGE AND SPLICE CORRODED REMOVED SEAT TRACK SECTION BETWEEN STA 690 TO 740 RBL24 AND 1 EA SPLICER IAW SRM 51-30-2, FABRICATED NEW SEAT TRACK SECTION FROM BAE 1526-729-7178 T6 511 PO NR 9006020, DIM 172" LONG IAW SRM 53-10-5 FIG. 1 REV 102. TREATED AND PRIMED IAW SRM 51-10-2, INSTALLED SEAT TRACK SECTION AND 1 EA SPLICER IAW SRM 51-30-2.

Part: FLOORBEAM — CRACKED (BS 312) · airframe 42,631 hrs · 27,705 cycles

FWD LAV AREA -FLOOR SUPPORT ANGLE IS CRACKED AT FASTENER HOLE, BS 312, BL 0. TRIMMED DAMAGE. FABRICATED 2 REPAIR ANGLES, FABRICATED FILLER, HEAT TREATED PARTS TO T6 CONDITION IAW FAS ENG REPORT 2-37153-801 REV A, AND INSTALLED IAW DWG SR27-53-017 REV A.

Part: STRINGER — CRACKED (BS 720B S15R) · airframe 42,631 hrs · 27,705 cycles

CABIN STRINGER 15 RT B.S. 720B PLUS 4" HAS END CRACKED AT FASTENER. REMOVED FASTENERS AND CUTOUT DAMAGED AREA, FABRICATED REPAIR "U" CHANNEL, FILLER AND FILLER TAPER . INSTALLED IAW SRM 51-30-2, 53-10-3, AND 51-10-2.

Part: SEAT TRACK — CORRODED (BS 556) · corrosion level 2 · airframe 42,631 hrs · 27,705 cycles

CABIN FLOOR TRACK B.S. 556 BL 0 LOWER SURF. HAS A CORROSION BULGE. REMOVED CORROSION AND FOUND OUT OF LIMITS. REMOVED SEAT TRACK SECTION AT STA 480 TO 600 BL0 AND 2 EACH SERVICEABLE SPLICER SEAT TRACKS, LOCATED AND DRILLED NEW SEAT TRACK SECTION USING BAC1520-792 7178-T6511 PO 9006020 DIMS 120" AND INSTALLED SEAT TRACK AND SPLICER SECTIONS IAW SRM 51-10-6, 53-10-1, 53-10-2 AND 51-30- 2.

Part: KEELBEAM — CRACKED (BS 872) · airframe 42,631 hrs · 27,705 cycles

LT KEELBEAM CRACKED BS 872 BETWEEN FASTENERS. TRIMMED OUT DAMAGE, FABRICATED REPAIR DOUBLER, CAD PLATED DOUBLER, HEAT TREATED DOUBLER AND INSTALLED IAW EA 7-5310-137782.

Part: FRAME — BENT (BS 580 S17R) · airframe 42,631 hrs · 27,705 cycles

CABIN FRAME BS 580 AT STRINGER 17 RT INSIDE FLANGE IS BENT IN. CUT OUT DAMAGED SECTION. FABRICATED FRAME DOUBLER REPAIR AND FILLER, HEAT TREATED MATERIAL TO T6 CONDITION IAW FAS ENGINEERING REPORT 2-37153-801 REV A AND INSTALLED IAW SRM 51-40-3, 51-30-5, 51-10-2 AND 51-30-2.

Part: SEAT TRACK — CORRODED (BS 950-950A) · corrosion level 2 · airframe 42,631 hrs · 27,705 cycles

CABIN SEAT TRACK BS 950, 10" - 950A LBL 24 OB UPPER FLANGE HAS CORROSION AT FASTENERS. REMOVED CORROSION AND FOUND OUT OF LIMITS. REMOVED SEAT TRACK SECTION. FABRICATED NEW SEAT TRACK SECTION AND SPLICE ANGLES AND ONE PLATE. INSTALLED IAW SRM 51-10-6, 53-10-5, 51-10-2 AND 51-30-2.

Part: STRINGER — CRACKED (BS 720B S15R) · airframe 42,631 hrs · 27,705 cycles

CABIN STRINGER 15 RT BS 720B PLUS 15" HAS END CRACKED AT FASTENER. REMOVED FASTENERS AND CUTOUT DAMAGED AREA, FABRICATED REPAIR "U" CHANNEL, FILLER AND FILLER TAPER. INSTALLED IAW SRM 51-30-2, 53-10-3, AND 51-10-2.

Part: STRUCTURE — CRACKED (LT WING TE FLAP) · airframe 42,631 hrs · 27,705 cycles

LT INBD MID-FLAP T/E LOWER CHORD CRACKED WBL106. REMOVED CRACKED ANGLES AT WBL 106 AND 146, FABRICATED NEW ANGLES AND INSTALLED AT WBL 106 AND 146 IAW SRM 51-30-2, 51-40-4, 51-10-2 AND 51-10-1.

Part: FLOORBEAM — CORRODED (BS 560) · corrosion level 2 · airframe 42,631 hrs · 27,705 cycles

CABIN FLOORBEAM BS 560 LBL 24- 45 UPPER FLANGE LOWER SURF HAS CORROSION AT N/P'S. REMOVED CORROSION IAW SRM 51-10-6, UT INSPECTED AREA IAW NDTM 51-00-00 FIG 3 PART 4, FOUND OUT OF LIMITS IAW PF SRM (ER 01-049) 53-10-1 FIG 4B REV C, REMOVED STIFFENER FOR ACCESS IAW 51-30-2 CUT OUT DAMAGED AREA IAW SRM 53-10-8 FIG 8 DETAIL II, FABRICATED REPAIR PARTS IAW SRM 53-10-8 FIG 8, TREATED AND PRIMED REPAIR PARTS IAW SRM 51-10-2, INSTALLED REPAIR PARTS AND STIFFENERS AT CABIN FLOORBEAM BS 560 LBL 24-45 IAW SRM 53-10-8 FIG 8.

Part: SILL — CRACKED (BS 495) · airframe 42,631 hrs · 27,705 cycles

MAIN CARGO DOOR UPPER SILL STA 495 STR 3L CRACK ORIGINATING FROM FASTENER. REMOVED FASTENER AND VERIFIED CRACK, REMOVED MAIN CARGO DOOR UPPER SILL AT STA 480 TO 530 AND ATTACHING SUPPORTS, LOCATED AND DRILLED NEW SILL AND INSTALLED NEW SILL AND ATTACHING SUPPORTS IAW DWG 53FX1467 AND EA 7-5310-135523.

Part: ANGLE — CRACKED (RT WING TE FLAP) · airframe 42,631 hrs · 27,705 cycles

RT OTBD MID-FLAP AFT UPPER CHORD ANGLE CRACKED WS 470. FLAP REMOVED AND REPLACED DUE TO DAMAGE BEYOND REPAIR LIMITS.

Part: ACCESSORY UNIT — ILLUMINATED (MLG) · airframe 41,916 hrs · 27,165 cycles

LANDING GEAR HANDLE FAILED TO RETRACT ABOVE OFF POSITION AFTER TAKEOFF, ACCOMPANIED BY ILLUMINATION OF ALL LIGHTS ON GEAR ANNUNCIATOR LIGHT PANEL UP FRONT AND RT MAIN GEAR DOOR LIGHT ON S/O PANEL. RAN QRH BUT FAILED 1ST TEST STEP. RECONFIGURED FOR LANDING WITH NORMAL INDICATIONS. UNEVENTFUL LANDING. REPLACED LANDING GEAR ACCESSORY UNIT AND TEST GOOD IAW MM 32-09-122-5.

Part: INTERCOSTAL — CORRODED (FUSELAGE) · corrosion level 2 · airframe 41,401 hrs · 26,773 cycles

MAIN DECK FLOORBEAM U CHANNEL INTERCOSTAL IS CORRODED, BS 1133, RBL 62, WL 208. REMOVED CORROSION AND FOUND CHANNEL TO BE OUT OF LIMITS. RECEIVED NEW CHANNEL/SUPPORT AND DRILLED HOLES, REFERENCE BOEING DOCUMENT NR 65-19606/ITEM -109, CLASSIFIED AS A MINOR REPAIR.

Part: DOOR FRAME — DAMAGED (ZONE 800) · airframe 40,944 hrs · 26,432 cycles

CABIN AFT LT SERVICE DOOR, FWD FRAME HAS 2 WORN AREAS, CAUSED BY A DRILL BIT AND SCREW TOO LONG. LOCATED JUST INBD OF FWD UPPER TORQUE TUBE LATCH CRANK, AREA MARKED. INSTALLED NEW FRAME REF, SRM 51-30-2 PG 2. INSTALLED NEW SEAL REF MM 52-12-011-4 PG 1. REINSTALLED AND ADJUSTED DOOR REF MM 52 14-000-4 PG1. OPS CHECKED GOOD, THIS IS CLASSIFIED AS A MAJOR REPAIR.

Part: SUPPORT ANGLE — CRACKED (ZONE 600) · airframe 40,944 hrs · 26,432 cycles

RT WING ROOT UPPER TE COMPOSITE PANEL INBD SUPPORT ANGLES (2EA ) ARE CRACKED, WBL 70. REMOVED CRACKED ANGLES, REF SRM 51-30-2, DRILLED NEW ANGLES TO FIT, REF 51-10-1. INSTALL, REF 51-030-2. THIS IS CLASSIFIED AS A MINOR REPAIR.

Part: FRAME — CRACKED (ZONE 300) · airframe 40,944 hrs · 26,432 cycles

NR 2 ENG INLET DUCT HOUSING, FRAME IS CRACKED, LOCATED AT BS 1233 AND LT SIDE OF VERTICAL STAB FWD SPAR FWD AND AFT SIDE OF FRAME CRACKED REMOVED DAMAGE BY CUTTING FRAME AND FRAME ANGLE. FABRICATED REPLACEMENT SECTION OF FRAME AND FRAME ANGLE, FRAME REPAIR ANGLE, FRAME ANGLE REPAIRS AND FILLERS AND INSTALLED ABOVE PARTS. REF BOEING DOCUMENT NR 65C 15812 AND SRM 51-40-3/ FIGURE NR 1/PAGES 1-6. THIS IS CLASSIFIED AS A MAJOR REPAIR.

Part: SKIN — DELAMINATED (RUDDER) · airframe 40,944 hrs · 26,432 cycles

VERTICAL STAB, UPPER RUDDER TAB HAS SPOT OF SKIN DISBOND, 2" BY 3" AREA AT 25" UP FROM LWR END 1" AFT OF FWD EDGE. REPAIRED UPPER RUDDER TAB REF SRM 51-40-20 PAR 7, 8, 14, 15, 19-22 AND APPLIED EXTERIOR PROTECTIVE FINISH REF MM 51-20-151-7.

Part: BRACKET — CRACKED (ZONE 600) · airframe 40,944 hrs · 26,432 cycles

RT WING, OTBD FLAP, INBD FLAP TRACK FAIRING IS CRACKED, AT CHANNEL SUPPORT ANGLE 16 INCHES AFT OF FWD EDGE, RT SIDE REMOVED DAMAGED TEE AND INSTALLED NEW ONE IAW SRM 51-30-2 AND 51-30-5 PG 5. THIS IS CLASSIFIED AS A MINOR REPAIR.

Part: ANGLE — CRACKED (ZONE 500) · airframe 40,944 hrs · 26,432 cycles

LEFT WING LE NR 2 SLAT, ACTUATOR LWR FAIRING SUPPORT ANGLE CRACKED ON INBD SIDE FWD FASTENER LOCATION. REMOVED CRACKED ANGLE ON L/E NR 2 SLAT ACTUATOR FAIRING SUPPORT IAW SRM 51-30-02 PG 1. LOCATED DRILLED, TREATED, PRIMED AND PAINTED IAW SRM'S 51-10-1 PG 10, 51-10-2 PG 1. INSTALLED ANGLE IAW SRM 51-30-2 PG 14. THIS IS CLASSIFIED AS A MINOR REPAIR.

Part: STRINGER CLIP — CORRODED (ZONE 200) · corrosion level 2 · airframe 40,944 hrs · 26,432 cycles

AFT PIT STA 1130 LBL 21 WL 140, STRINGER CLIP UNDER "Z" ANGLE HAS LIGHT CORROSION. REMOVED STRINGER CLIP. FABRICATED AND HEAT TREATED NEW CLIP TO 7075 T6. TREATED, PRIMED, PICKED UP HOLES, AND INSTALLED NEW CLIP. REF: SRM 51-30-2, PG 1-12/51-10-1, PG 12/51-10-2, PG 1 BOEING DWG 69-44104-9. THIS IS CLASSIFIED AS A MAJOR REPAIR.

Part: STRINGER CLIP — CRACKED (ZONE 200) · airframe 40,944 hrs · 26,432 cycles

POOR WORKMANSHIP, STRINGER TIE CLIP ON STR NR 1 AT FS 334 BENT/CRACKED CUSTOMER REQUEST REMOVED ELECTRIC BOX (FWD ENTRY LIGHT BALLAST). REMOVED DAMAGED CLIP. FABRICATED NEW CLIP REF BOEING DWG 65-45313. TREATED PRIMED CLIP REF SRM 51-20-1. INSTALLED CLIP REF SRM 51-30-2. INSTALLED FWD ENTRY LIGHT BALLAST ASSY MM 33-10-00. THIS REPAIR IS CLASSIFIED AS A MAJOR REPAIR.

Part: FRAME — GOUGED (ZONE 200) · airframe 40,944 hrs · 26,432 cycles

PREVIOUS DAMAGE: LT FUSE (SAT 680) STR 14L, FRAME ABOVE 14L HAS DEEP GOUGES BLENDED DAMAGED AREA ORIGINAL MATERIAL .045" MATERIAL LOSS .015" MATERIAL REMAINING .030" AND IS OUT OF LIMITS REF SRM 53-10-1. REMOVED DAMAGED SECTION, FABRICATED REPAIR SPLICE. INSTALLED NEW FRAME SECTION AND FRAME REPAIR SPLICE REF EA NR 7-5310-113101-FUSELAGE-MAIN FRAME.

Part: STRINGER CLIP — DAMAGED (ZONE 200) · airframe 40,944 hrs · 26,432 cycles

POOR WORKMANSHIP/CUSTOMER REQUEST, STRINGER TIE CLIP ON STR 2R AT FS 334 DAMAGED FROM MISDRILLED FASTENER HOLE REMOVED DAMAGED STRINGER CLIP. VERIFIED MATERIAL AND FABRICATED NEW STRINGER CLIP. TREATED AND PRIMED STRINGER CLIP, DRILLED UP AND INSTALLED NEW STRINGER CLIP REF SRM 51-10-2, BOEING PARTS LIST PL65-45313, BOEING DRAWING 65-45313, SRM 51-30-2 THIS IS CLASSIFIED AS A MAJOR REPAIR.

Part: FRAME — CRACKED (ZONE 100) · airframe 40,944 hrs · 26,432 cycles

RIGHT LOWER FUSELAGE PANEL NR 3438, INBOARD FORMER RIB AT CENTER OF ACCESS PANEL CUT-OUT CRACKED AT OUTBOARD ATTACH POINT ON INNER SIDE. REPLACED Z ANGLE IAW BOEING DWG 65-25581, THIS IS CLASSIFIED AS A MINOR REPAIR.

Part: SKIN — DELAMINATED (RUDDER) · airframe 40,944 hrs · 26,432 cycles

VERTICAL STAB UPPER RUDDER TAB UPPER END POTTING BROKEN OPEN AND SKIN DISBONDED ON BOTH SIDES, LEFT SIDE 6-12" FWD OF T/E, RIGHT 5-13" AND DOWN 4" ALSO T/E TIP CORNER OPEN. REPAIRED UPPER RUDDER TAB ON LEFT AND RIGHT SIDES REF SRM 51-40-20 PAR 7, 8, 14, 15, AND 20-22, TAP CHECKS GOOD COOK TICKET ATTACHED, "THIS IS CLASSIFIED AS A MAJOR REPAIR".

Part: SKIN — DAMAGED (ZONE 200) · airframe 40,944 hrs · 26,432 cycles

AFT FUSELAGE AT FS 1320 IN SECTION 48 ZONE, SKIN HAS 2 PREVIOUS PUNCTURES FILLED WITH SEALANT ON LT SIDE OF A/C BETWEEN STRINGERS 3L AND 6L JUST BELOW VERTICAL STAB. REMOVED DAMAGE SRM 53-30-3 FIG 13A. FABRICATED REPAIR DOUBLER SRM 53-30-3 FIG 13 A. NDT AT STR 3L AND 6L IAW 727 MAN PART 4 51-00-00 FIG 2, PART 6 51-00-00 FIG 23 ORG "T" .055, REMAINING "T" .052, LOSS .003 AT 6L, NO DEFECTS AT 3L AND 6L. ALODINED AND PRIMED DOUBLER AT 3L AND AREA AT 6L SRM 51-10-2 PG 7 AND 8. INSTALLED DOUBLER AT 3L SRM 53-30-3 PG 74C. PAINTED AREAS AT 3L AND 6L SRM 53-30-3 PG 74C. THIS IS CLASSIFIED AS A MAJOR REPAIR.

Part: STRINGER CLIP — CORRODED (ZONE 100) · corrosion level 2 · airframe 40,944 hrs · 26,432 cycles

AFT PIT STA 1030 LBL 23" WL 147, STRINGER CLIP HAS LIGHT CORROSION. REMOVED DAMAGED STRINGER CLIP, FABRICATED NEW CLIP TREATED, PRIMED AND INSTALLED REF 51-30-2, THIS IS CLASSIFIED AS A MAJOR REPAIR.

Part: ANGLE — CRACKED (NR 2 INLET) · airframe 40,944 hrs · 26,432 cycles

NR 2 ENG INLET DUCT HOUSING FRAME-TO-LEADING EDGE OF VERTICAL STAB ATTACH CLIP ON RT SIDE IS CRACKED LOCATED AT STA 1233 REMOVED CRACKED ATTACH CLIP, FABRICATED NEW CLIP AND INSTALLED. REF BOEING DOCUMENT NR 69-14476/ID NR 0001/ITEM NR 14/FRAME 1 OF 2 AND SRM 51-30-2. CLASSIFIED AS A MAJOR REPAIR.

Part: ANGLE — CRACKED (ZONE 300) · airframe 40,944 hrs · 26,432 cycles

NR 2 ENG INLET DUCT HOUSING FRAME-TO-VERTICAL STAB LEADING EDGE ATTACH CLIP IS CRACKED. LOCATED ON LT SIDE STA 1233. REMOVED CRACKED ATTACHED BRACKET, FABRICATED NEW ATTACH CLIP AND INSTALLED. REF BOEING DOCUMENT NR 69-14476 AND SRM 51-30-02. CLASSIFIED AS A MAJOR REPAIR.

Part: BRACKET — CRACKED (ZONE 100) · airframe 40,944 hrs · 26,432 cycles

CROSS BRACKET INSIDE GROUND POWER PLUG ACCESS DOOR HAS CRACKED ATTACH BRACKET AT TOP AFT ATTACH POINT REMOVED CRACKED BRACKET IN REF TO SRM 51-30-2. FABRICATED NEW BRACKET IN REF TO DWG 69-22670-5. INSTALLED NEW BRACKET IN REF TO SRM 51-30-2. THIS IS CLASSIFIED AS A MINOR REPAIR.

Part: ANGLE — CORRODED (ZONE 100) · corrosion level 2 · airframe 40,944 hrs · 26,432 cycles

AFT CARGO COMPARTMENT "Z" ANGLE HAS CORROSION IN 2 LOCATIONS FROM STA 950B TO 950E, RBL 24, WL 156 BLENDED CORROSION ON "Z" ANGLE STA 950B OUT OF LIMITS PER SRM 51-40-3. BLEND CORROSION AT STA 950D. REMOVED .005' FROM ORIGINAL THICKNESS OF .056, WITHIN LIMITS REF SRM 53-10-1. THIS IS CLASSIFIED AS A MINOR REPAIR.

Part: STRINGER SPLICE — CORRODED (ZONE 100) · corrosion level 2 · airframe 40,944 hrs · 26,432 cycles

AFT PIT STA 1010, LBL 23, WL 150 STRINGER SPLICE HAS CORROSION. REMOVED OLD SPLICE, REMOVED CORROSION FROM STRINGER, ORIGINAL MATERIAL .070". REMOVED .005, REMAINING .065", FOUND TO BE WITH IN LIMITS. FABRICATED NEW STRINGER SPLICE, TREATED AND PRIMED, INSTALLED, REF SRM 51-10-2 PG 2, SRM 51-30-2 PG 2, SRM 53-10-1 FIG 5. THIS IS CLASSIFIED AS A MINOR REPAIR. LEVEL 1 CORROSION.

Part: BOLT — LOOSE (MLG) · airframe 40,546 hrs · 26,129 cycles

AFTER T/O LANDING GEAR FAILED TO RETRACT RAN THE "LANDING GEAR LEVER LATCH FAILED TO RELEASE" CHECKLIST TEST NR 1 FAIL, TEST 2&3 PASSED. RETURN TO MEMPHIS NORMAL LANDING. FOUND LEFT MAIN GEAR SAFETY SENSOR ACTUATOR CENTER PIVOT BOLT LOOSE AND NUT BACKED OFF TO LAST THREAD CAUSING EXCESSIVE GAP TO SENSORS. REPLACED NUT AND IAW B727-200 AMM 32-09-221-4. GAP NOW WITHIN LIMITS. SWUNG GEAR IAW B727-200 AMM 32-61-001-5, ALL CHECKS GOOD.

Part: CLAMP — LOOSE (NR 3 ENGINE) · airframe 39,889 hrs · 25,639 cycles

NR 3 ENG STRUT OVERHEAT LIGHT ILLUM IN FLIGHT. C/W WITH CFM RED TABS, WAS ABLE TO GET LT EXTINGUISHED & RETURNED TO MEM. FOUND 2 CLAMPS ON THE 8TH STAGE CHECK VLV & 3 JOINTS NEAR THE STRUT LOOP LEAKING. REMOVED AND REPLACED THE 2 CLAMPS AND REMOVED SHIMS FROM LEAKING JOINTS PER MM 36-00-001-2. ONE JOINT CONNECTION WAS FOR THE 13TH STG DUCT GOING TO THE HEAT EXCHANGER AT THE FIRE FEED SEAL CLOSE TO THE STRUT OVERHEAT SENSING ELEMENT. NO LEAKS IN STUB WING FOUND AFTER CORRECTIVE ACTION. RAN NR 3 ENG FOR 15 MINUTES AT 74 PERCENT N2 W/BOTH PACKS ON FOR MAX BLEED OFF. NO STRUT OVERHEAT INDICATED. CLAMP P/N VC113-350-E.

Part: CONTROLLER — MALFUNCTIONED (CABIN PRESSURE) · airframe 39,718 hrs · 25,508 cycles

AUTO AND STBY CONTROLLERS WOULD NOT MAINTAIN CABIN PRESSURIZATION. OUTFLOW VALVE SHOWED FULL CLOSED UNTIL DESCENDING THROUGH 4000 FT MSL THEN WENT FULL 31,000 FT CABIN ALTITUDE WAS 12,000 FT AND CLIMBING 600 FPM IN ALL MODES. CLOSING CARGO HEAT OUTFLOW ONLY SHOWED CLIMB RATE AT 19,000 FT CABIN ALTITUDE WAS 8,000 FT. R&R THE CABIN PRESSURE CONTROL AND THE CABIN PRESS CONTROL PANEL PER 727-200 MM 21-31-010-4 TESTED SYS WITH NR 1 AND NR 3 ENG RUN PER MM 21-31-0 AND THE JRH. CHECKED A/C OK FOR FLIGHT.

Part: DUCT — LOOSE (BLEED SYSTEM) · airframe 39,157 hrs · 25,072 cycles

ENG 3 STRUT OVERHEAT LIGHT ILLUMINATED, COMPLETED QRH PROC AND ISOLATED ENG NR 3 BLEED AIR. LIGHT EXTINGUISHED WHEN NR 3 BLEED AIR SW AND NR 2 PACK SW TURNED OFF AND NR 3 THROTTLE RETURNED TO IDLE. LIGHT REMAINED OFF THROUGH REST OF FLIGHT. 13 OCT 05 REMOVED AND REPLACED GROUND PNEU DUCT AND GASKETS AND CLAMP PER MM 36-00-001-2, LEAKS CKS GOOD ON APU. SEE TSI 26-13/8048 FOR FURTHER ACTIONS REQUIRED PER MOCC. 14 OCT 05 AS PER MOCC REQUEST AND AS A PRECAUTIONARY MEASURE REMOVED AND REPLACED THE OVERHEAT DETECTOR OF THE NR 3 ENGINE. PERFORMED HIGH PWR RUN AS PER JRH. ALL ENG INDICATIONS NORMAL. OVERHEAT LIGHT NEVER ILLUMINATED. A/C OK FOR SERVICE.

Part: ATTACH FITTING — CORRODED (NR 7 FLAP TRACK) · airframe 39,028 hrs · 24,975 cycles

NR 7 FLAP TRACK FWD ATTACH FITTING IS CORRODED. REPLACED NR 7 FLAP TRACK FWD ATTACH FITTING IAW BOEING DWG 65-17357, OHM 20-50-03, MM 28-11-00.

Part: STRINGER — CORRODED (FUSELAGE) · airframe 39,028 hrs · 24,975 cycles

CORROSION ON STR 18A LT SIDE. REPAIRED STR 18A LT SIDE PER SRM 51-30-02, SRM 53-10-01 AND BOEING DWG 65-16334.

Part: STRUCTURE — CORRODED (FUSELAGE) · airframe 39,028 hrs · 24,975 cycles

FOUND CORROSION IN BOLT HOLES AT BS 360, STR 26 LT TO EXCEED THE TOLERANCES ALLOWED BY FEDEX SR27-53-021. REMOVED CORROSION FROM BOLT HOLES AT BS 360, STR 26L AND REPAIRED PER EA 7-5310- 91340.

Part: FLOORBEAM — UNKNOWN (CABIN) · airframe 39,028 hrs · 24,975 cycles

EVALUATE TO DETERMINE IF REPAIR IS MAJOR OR MINOR AND IF REPAIR IS IN ACCORDANCE WITH FAA APPROVED DATA, (FLOORBEAM REPAIR AT BS 380, RBL 52-63). EMOVED EXISTING REPAIR B/S 380 RBL 52-63 FABRICATED & INSTALLED NEW REPAIR IAW FED EX SR DRW 52-034E THIS IS A MAJOR REPAIR

Part: FLOORBEAM — CORRODED (FUSELAGE) · airframe 39,028 hrs · 24,975 cycles

BS 277, LBL 14, WL 208 CORROSION ON FLOORBEAM. INSTALLED REPAIR PER SRM 51-40-4, THIS REPAIR IS MAJOR

Part: SKIN — UNKNOWN (FUSELAGE) · airframe 39,028 hrs · 24,975 cycles

EVALUATE TO DETERMINE IF REPAIR IS MAJOR OR MINOR AND IF REPAIR IS IN ACCORDANCE WITH FAA APPROVED DATA, (EXTERNAL REPAIR BS 1015, STR 29L, BL 0, 9 X 8 INCHES). REMOVED EXISTING REPAIR, INSTALLED FABRICATED REPAIR PER SRM 53-30-3 FIG 3A.

Part: SKIN — UNKNOWN (FUSELAGE) · airframe 39,028 hrs · 24,975 cycles

EVALUATE TO DETERMINE IF REPAIR IS MAJOR OR MINOR AND IF REPAIR IS IN ACCORDANCE WITH FAA APPROVED DATA, (EXTERNAL REPAIR BS 1158, STR 29R, BL 0, 7.5 X 5 INCHES).

Part: SKIN — UNKNOWN (FUSELAGE) · airframe 39,028 hrs · 24,975 cycles

EVALUATE TO DETERMINE IF REPAIR IS MAJOR OR MINOR AND IF REPAIR IS IN ACCORDANCE WITH FAA APPROVED DATE, (EXTERNAL REPAIR BS 690, STR 28R 18 X 12 INCHES). REMOVED AND REPLACED EXTERNAL REPAIR BS690, STR. 28R, IAW SRM 53-30-3. FIG 3A.

Part: STRINGER — UNKNOWN (FUSELAGE) · airframe 39,028 hrs · 24,975 cycles

EVALUATE TO DETERMINE IF REPAIR IS MAJOR OR MINOR AND IF REPAIR IS IN ACCORDANCE WITH FAA APPROVED DATA, (STRINGER REPAIR STR 28L, BS 700, WL 148). REMOVED PREVIOUS STR. REPAIR SPLICE AND REPAIR SECTION BS 700 720 2" STR 28L WL 148, PER SRM 51-30-2. FABRICATED, ALODINE, PRIMED PAINTED AND INSTALLED NEW STR REPAIR AND REPAIR STR. SECTION BS 700-720 2, STR 28L PER 53-10-3, SHT 1-4, DETAIL 1 AND TABLE II SRM 51-10-2 AND SRM 51-30-2.

Part: SKIN — UNKNOWN (FUSELAGE) · airframe 39,028 hrs · 24,975 cycles

EVALUATE TO DETERMINE IF REPAIR IS MAJOR OR MINOR AND IF REPAIR IS IN ACCORDANCE WITH FAA APPROVED DATA, EXTERNAL REPAIR B/S 1105 STR 25-26L. INSTALLED EXTERNAL REPAIR DOUBLER PER SRM 53-30-3 MINOR REPAIR.

Part: FLOORBEAM — CORRODED (FUSELAGE) · airframe 39,028 hrs · 24,975 cycles

BS 344 FLOORBEAM CORROSION FOUND ALONG TOP OF FLANGE IN VARIOUS PLACES.

Part: SUPPORT — CORRODED (FUSELAGE) · airframe 39,028 hrs · 24,975 cycles

CORROSION ON 740, LBL 8, WL 148, UNDER ACCESS PANEL 3348L. SKIN SUPPORT WAS FOUND TO BE OUT OF LIMITS. REMOVED AND REPLACED SKIN SUPPORT BS 740, LBL 8, WL 148 PER SRM 51-30-2 AND SRM 53-10-1

Part: FRAME — DAMAGED (FUSELAGE) · airframe 39,028 hrs · 24,975 cycles

BS 360 FRAME HAS MECHANICAL DAMAGE FWD OF STR 5L. REPAIRED DAMAGED FRAME PER SRM 51-40-3. (CLOSED)

Part: SKIN — CHAFED (N/A) · airframe 39,028 hrs · 24,975 cycles

PREVIOUS REPAIR IS CHAFED AT BS 720D 12, STRINGER 19 LEFT. REPLACED CHAFFED REPAIR AT BS 720D 12, STR 19L, IAW SRM 51-10-1 AND 51-10-2. (CLOSED)

Part: SKIN — GOUGED (FUSELAGE) · airframe 39,028 hrs · 24,975 cycles

GOUGE IN FUSELAGE SKIN AT BS 430, JUST BELOW STR. 18R. CUT OUT DAMAGE IN SKIN BS 430 R, STR 18 IAW SRM 53-30-3 FABRICATED, INSTALLED PARTS PER SRM 53-30-3. (CLOSED)

Part: STRINGER CLIP — CRACKED (FUSELAGE) · airframe 39,028 hrs · 24,975 cycles

FUSELAGE UPPER LOBE STRINGER CLIP IS CRACKED BS 990 STR-6R. REMOVED AND REPLACED CRACKED STR. CLIP AT BS 990 STR 6R IAW SRM 51-30-2.

Part: STRINGER CLIP — CRACKED (FUSELAGE) · airframe 39,028 hrs · 24,975 cycles

FUSE UPR LOBE STRINGER CLIP IS CRACKED BS 950A STR-7R. REMOVED AND REPLACED UPPER LOBE STR CLIP AT 950A, STR 7R IAW SRM 51-20-1, 51-10-3, 51-30-2, 51-10-2.

Part: STRINGER CLIP — CRACKED (FUSELAGE) · airframe 39,028 hrs · 24,975 cycles

FUSELAGE UPPER LOBE STRINGER CLIP IS CRACKED BS 990 STR-9R. FABRICATED NEW STR CLIP AND INSTALLED STR CLIP AT BS 990 STR-9R IAW SRM 51-30-2.

Part: DOOR FRAME — GOUGED (FUSELAGE) · airframe 39,028 hrs · 24,975 cycles

FWD ENTRY DOOR, UPPER FRAME UPPER SURFACE IS GOUGED WHERE 3 BRACKETS WERE IMPROPERLY REMOVED AND REMAINS OF BRACKETS ARE STILL UNDER HILOCK HEADS. REMOVED AND REPLACED UPPER FRAME PER SRM 51-30-2.

Part: STRINGER CLIP — CRACKED (FUSELAGE) · airframe 39,028 hrs · 24,975 cycles

FUSELAGE UPPER LOBE STRINGER CLIP IS CRACKED BS 950C STR-7R. REMOVED AND REPLACED UPPER LOBE STR CLIP AT BS 950C STR 7R. IAW SRM 51-20-1, 51-10- 3, 51-30-2, 51-10-2.

Part: FRAME — DENTED (FUSELAGE) · airframe 39,028 hrs · 24,975 cycles

BS 600 MULTIPLE FRAME DENTS ABOVE & BELOW STRINGER 23L AT BS 600. REPAIRED FRAME BS 600, ABOVE AND BELOW STR 23L, INSTALLED REPAIR IAW SRM 51-40-3, 53- 10-1.

Part: STRINGER CLIP — CRACKED (FUSLAGE) · airframe 39,028 hrs · 24,975 cycles

FUSELAGE UPPER LOBE STRINGER CLIP IS CRACKED BS 950B STR-6R. REMOVED AND REPLACED UPPER LOBE STR. CLIP BS 950B, STR 6R IAW SRM 51-30-2.

Part: FRAME — GOUGED (FUSELAGE) · airframe 39,028 hrs · 24,975 cycles

AFT CARGO FRAME IS GOUGED TOP OF FRAME AT NUTPLATE HOLE BS 1148 BETWEEN STR 25L-26L. REPAIRED AFT CARGO FRAME AT NUTPLATE HOLE BS 1148 STR 25L-26L IAW SRM 51-30-2, 53- 10-1, 51-40-3.

Part: STRINGER CLIP — CRACKED (FUSELAGE) · airframe 39,028 hrs · 24,975 cycles

FUSELAGE UPPER LOBE STRINGER CLIP IS CRACKED BS 950C STR-3R. REPLACED STRINGER CLIP BS950C STR 3R IN UPPER FUSELAGE PER SRM 51-30-2, 51-10-2, 51- 20-1, 51-30-5, 51-30-6.

Part: DOOR FRAME — CORRODED (E/E BAY) · airframe 39,028 hrs · 24,975 cycles

CORROSION ON E-BAY DOOR FRAME BS 423 BL 0. BLENDED CORROSION FROM E-BAY FRAME BS 423 BL 0 FOUND TO BE WITHIN LIMITS PER SRM 53-10-1

Part: STRUCTURE — GOUGED (FUSELAGE) · airframe 39,028 hrs · 24,975 cycles

BS 1352 IS GOUGED AT 3 O'CLOCK, WORN FROM 5-6 O'CLOCK AND MISSING RUBSTRIP FROM 1-6 O'CLOCK. (OPEN)

Part: FRAME — DENTED (FUSELAGE) · airframe 39,028 hrs · 24,975 cycles

NBS 580 MULTIPLE FRAME DENTS ABOVE AND BELOW STRINGER 23L AT BS 580. DENT FOUND TO BE OUT OF LIMITS, REMOVED DAMAGE PER SRM 53-40-3 FABRICATED REPAIR DOUBLER, DRILLED, ALLODINED, PAINTED AND INSTALLED PER SRM 51-40-3, 51-10-2, 51-40-3.

Part: DOOR FRAME — CORRODED (FUSELAGE) · airframe 39,028 hrs · 24,975 cycles

E-BAY BODY DOOR FRAME AT BS 449 LBL 2-RBL 2 CORRODED. REPLACED E-BAY BODY DOOR FRAME AT BS 449, PER SRM 51-30-2 AND 51-10-3 AND 51-30-5

Part: TRANSMITTER — MALFUNCTIONED (HYD QTY IND) · airframe 37,554 hrs · 23,878 cycles

DESCENDING THRU FL190, HYDRAULIC SYSTEM -A- QUANTITY INDICATED ZERO (PRESSURE GOOD AT 3000 PSI). COMPLIED WITH QRH. AFTER 15 MINUTES AND BEING LEVEL AT 12,000 FOR OVER 5 MINUTES. HYD SYSTEM -A- QUANTITY SLOWLY BEGAN MOVING TO 6.0 GALLONS AND THEN 5.5 GALLONS. MANUAL GEAR EXTENSION WAS COMPLETED PER QRH. REMOVED AND REPLACED SYSTEM -A- HYD QTY TRANSMITTER REF 29-33-001-4, OPS CHECK GOOD.

Part: SKIN — CORRODED (FUSELAGE) · airframe 36,783 hrs · 23,240 cycles

CORROSION UNDER EDGE OF RIGHT RAM AIR DOOR ACTUATOR PANEL. CORROSION OUT OF LIMITS, REPAIRED IAW EA 7-5330-68147.

Part: SKIN — DENTED (FUSELAGE) · airframe 36,783 hrs · 23,240 cycles

OIL CAN DENT IN SKIN AT BS 211, RBL 23, WL 182. REMOVED DAMAGED AREA OF SKIN. FABRICATED REPAIR DOUBLER. INSTALLED REPAIR IAW SRM 53-30-3.

Part: FRAME — DENTED (FUSELAGE) · airframe 36,783 hrs · 23,240 cycles

DENT IN FRAME, BS 950C STR 26L. REPAIR FRAME IAW SRM.

Part: SKIN — DENTED (FUSELAGE) · airframe 36,783 hrs · 23,240 cycles

OIL CAN DENT IN SKIN AT BS 190, RBL 22, WL 182. REMOVED DAMAGED AREA OF SKIN. FABRICATED REPAIR DOUBLER, AND INSTALLED REPAIR IAW SRM 53-30-3.

Part: SKIN — DENTED (FUSELAGE) · airframe 36,783 hrs · 23,240 cycles

DENTS IN SKIN, BS 660 - 670, S22R. REPAIRED DENTS IN SKIN IAW SRM.

Part: SKIN — DAMAGED (FUSELAGE) · airframe 36,783 hrs · 23,240 cycles

FUSELAGE SKIN DAMAGED AT BS 1050, STR 19R, JUST BELOW THE LAP. REPAIRED SKIN IAW SRM.

Part: TORQUE TUBE — DISCONNECTED (T/E FLAP) · airframe 36,267 hrs · 22,823 cycles

ON DEPARTURE OUTBOARD FLAPS WENT ASYMMETRIC WITH ONE NEEDLE IND. RECONNECTED TORQUE TUBE PER MM 27-51-00-5. OPS CHECK GOOD.

Part: BULB — FAULTY (NR 2 CSD)

01-297 NR 2 CSD TEMP ROSE TO 140 DEG AND STAB AFT THROTTLE RETARD IDLE TEMP DOWN 100 DEG. REMOVED AND REPLACED CSD OIL TEMP BULB, COOLER AND FILTER.

Part: SKIN — CRACKED (NR 4 SLAT) · airframe 34,848 hrs · 21,761 cycles

DURING ROUTINE INSP, NR 4 SLAT FOUND CRACKED AT O/B ACTUATOR ATTACH ANGLE. REMOVED AND REPLACED PER IAW MM 27-81-11-04.

Part: SKIN — CRACKED (LE FLAP) · airframe 34,848 hrs · 21,761 cycles

DURING ROUTINE INSP, LEFT I/B FOREFLAP FOUND CRACKED ON I/B END. REMOVED AND REPLACED FOREFLAP PER IAW SRM 51-40-6.

Part: SKIN — DELAMINATED (AILERON TAB) · airframe 34,848 hrs · 21,761 cycles

DURING ROUTINE INSP, LEFT WING O/B AILERON TAB FOUND DELAMINATED. REMOVED AND REPLACED PER IAW MM 27-10-41-04.

Part: SKIN — CRACKED (NR 4 SLAT) · airframe 34,848 hrs · 21,761 cycles

DURING ROUTINE INSP, NR 4 SLAT FOUND TO HAVE 2 INCH CRACK ON INTERIOR RADIUS 5 INCHES O/B OF THE ACTUATOR. REMOVED AND REPLACED PER IAW MM 27-81-011-04.

Part: MOUNT — CRACKED (RT FLAP FAIRING) · airframe 34,848 hrs · 21,791 cycles

DURING ROUTINE INSP, FWD I/B MOUNT FOR THE RIGHT I/B FLAP FAIRING FOUND CRACKED. STOP DRILL CRACK, FAB AND INSTALLED PER IAW SRM 51-40-2.

Part: SKIN — CRACKED (NR 5 SLAT) · airframe 34,848 hrs · 21,761 cycles

DURING ROUTINE INSP, NR 5 SLAT FOUND CRACKED BEYOND PREVIOUS STOP DRILL IN O/B ANGLE AT THE ACTUATOR ROD END. STOP DRILLED CRACK, FAB, INSTALLED PER IAW SRM 57-50-3.

Part: CLIP — CRACKED (FUSELAGE) · airframe 34,848 hrs · 21,761 cycles

DURING ROUTINE INSP, TIE CLIP AT BS 660, STR 3R FOUND CRACKED. REMOVED AND REPLACED PER IAW SRM 51-30-2.

Part: CABLE — FRAYED (ESCAPE SLIDE) · airframe 34,848 hrs · 21,761 cycles

DURING ROUTINE INSP, FWD ENTRY DOOR EMERGENCY ESCAPE SLIDE GIRT WAS FOUND FRAYED. REMOVED AND REPLACED PER IAW MM 25-60-015-2.

Part: SEAT TRACK — CORRODED (FUSELAGE) · airframe 34,848 hrs · 21,761 cycles

DURING ROUTINE INSP, NR 4 SEAT TRACK FOUND CORRODED BEYOND LIMITS AT BS 580. REMOVED AND REPLACED FAB PER IAW SRM 53-10-5.

Part: ANGLE — CORRODED (CARGO BAY) · airframe 34,848 hrs · 21,761 cycles

DURING ROUTINE INSP, UPPER SUPPORT FOR THE AFT BAGGAGE BIN BULKHEAD FOUND CORRODED BEYOND LIMITS BS 1166, BL 0. REMOVED, REPLACED AND FAB PER IAW SRM 51-40-3.

Part: THROTTLE — FAILED (NR 2 ENGINE)

NR 2 ENGINE THROTTLE WOULD NOT RETARD. *S/D* PERFORMED THRUST LEVER FRICTION BRAKE ADJUSTMENT IAW MM 76-11-1. AC OK FOR SERVICE.

Part: WIRE — BROKEN (NLG)

NOSE GEAR UNSAFE LIGHT CAME ON. ABLE TO GET 3 GREEN, BUT NOT EXTINGUISH THE NOSE GEAR RED LIGHT. NOSE GEAR VIEW PORT WAS USED BUT NOT ABLE TO SEE ALIGNMENT STRIPES. MANUAL EXTENSION OF NOSE GEAR DID NOT EXTINGUISH THE LIGHT. AFT LOW PASS, UNEVENTFUL LAND ACCOMPLISH. TOWER CONFIRM GEAR APPEAR DOWN. REPEAT WRITEUP. *S/D* REMOVED AND REPLACED WIRE W1386-018-20. RESAFTIED CONNECTORS.

Part: RELAY — FAILED (CONTROL WHEEL)

97-223 - CONTROL WHEEL TRIM SWITCHES INOP BOTH SIDES. REPLACED R-29 PHASE SEQUENCE RELAY. SYSTEM G/CS NORMAL.

Part: AUX SPAR — CRACKED (WS 120)

AUX SPAR IS CRACKED, FWD OF NR 8 SPOILER FITTING. *S/D* REPAIRED AUX SPAR CHORD FWD OF NR 8 SPOILER FITTING, ALL WORK DONE IAW FED-EX EA 7-5710-38120.

Part: FRAME — CRACKED (BS 600)

CRACK IN FRAME AT FASTENER HOLE BS 600, RBL 3, WL 157. *S/D* REPAIRED FRAME AT BS 600, RBL 3, WL 157 IAW FED-EX SRM 51-40-3.

Part: FRAME — CRACKED (BS 620)

CRACK IN FRAME AT FASTENER HOLE BS 620, RBL 3, WL 157. *S/D* REPAIRED FRAME AT BS 620, RBL 3, WL 157 IAW FED-EX SRM 51-40-3.

Part: FRAME — DENTED (BS 1030)

AFT BAY TOP OF FRAME DENTED AT BS 1030, RBL 28, WL 145. *S/D* REMOVED DAMAGED AREA AND REPAIRED FRAME AT BS 1030, RBL 28, WL 145 IAW FED-EX SRM 51-40-3.

Part: COMPRESSOR — STALLED (RT ENGINE)

AFTER TAKEOFF AND CLIMBING THROUGH 1,000 FEET, THE AIRCRAFT EXPERIENCED AN APPARENT COMPRESSOR STALL. AIRCRAFT SURGED WITH A NOTICEABLE ROLL TO THE LEFT AND ACTIVATION OF THE AUTO PACK TRIP SYSTEM. DUMPED FUEL AND RETURNED FOR LANDING. VISUALLY INSPECTED ALL 3 ENGINES INTAKE AND EXHAUST, NO DAMAGE NOTED. TAXIED AIRCRAFT TO RUN-UP AREA AND RAN ALL ENGINES AT TAKEOFF EPR, ALL PARAMETERS WITHIN JET RUN HANDBOOK LIMITS. AIRCRAFT OK FOR FLIGHT.

Part: WARNING LIGHT — ILLUMINATED (CARGO DOOR)

AT FLT 330 MACH .80, THE MCD LIGHT ANNUNCIATOR LIGHT ILLUMINATED, WENT OUT BRIEFLY CAME BACK ON. A/C WAS HOLDING PRESS GOOD. C/W DOOR ANNUNCIATOR, CKLIST AND DIVERTED TO DEN. AFTER DEPRESS LIGHT WENT OUT CARGO DOOR LOCK ANNUNCIATOR INOP. DEFER PER MEL 52-4A, CATEGORY A, CONTROL NR 1006012, EXP 10-8-95. CARGO DOOR WARNING SYS OPS CK OK PER MM 52-70-09. INBOUND CREW REPORTED NO PROBLEMS WITH DOOR WARNING LIGHT.

Part: CIRCUIT CARD — FAILED (FLIGHT DECK)

T/O ABORTED AT 110 KTS, BECAUSE OF WARNING LIGHT, ALT ALERT, 3 REVERSERS, ALL GEAR WARNING LIGHTS GEAR PANEL. REMOVED AND REPLACED MASTER DIM AND TEST MODULE CARD.

Part: STRINGER — CORROSION (BS 625)

FWD CARGO BAY HAD CORROSION ON STR 27R AT BS 625. REMOVED AND REPLACED DAMAGED AREA OF STA 625 STR 27R PER FEDEX SRM 53-10-3.

Part: FLOORBEAM — DAMAGED (BS 1110)

WHILE WORKING NR O652 DISCOVERED DAMAGE TO FLOORBEAM WEB AT BS 1110 BL 0 WL 207. PREVIOUSLY CAUSED DURING INSTALLATION OF HAYES CARGO MOD. REPAIRED FLOORBEAM PER FEDEX EA 7-5310-25620.

Part: SKIN — CORRODED (BS 950)

CORROSION (71C209-02), ON SKIN BS 950F PLUS 12 TO 974, BETWEEN STR 29 AND 30R AFT CARGO BAY. CUT OUT DAMAGED AREAS OF SKIN FROM BS 950F PLUS 12 TO 974, BETWEEN STR 29 AND 30R. REPAIRED CUT OUT AREAS IAW FEDEX SRM 53-30-3.

Part: FRAME — CRACK (BS 560)

IN THE FWD CARGO BAY THE UPPER FLANGE OF FRAME IS CRACKED AT BS 560 RBL 2, WL 154. REPAIRED UPPER FLANGE OF FRAME AT BS 560 RBL 2 WL 154 IAW SRM 51-40-3.

Part: SPLICE — CORROSION (BS 648-664)

CORROSION ON STR 26R BS 648-664 AND ON STR SPLICE HAT AT BS 680. REMOVED CORROSION WITHIN DAMAGE LIMITATION ON STR AND REPLACED STR SPLICE HAT AT BS 680 STR 26R ALL WORK IAW SRM 51-40-3.

Part: KEEL BEAM — CRACKED (BS 950)

CORROSION ON O/B FLANGE OF STR 29R BS 950E KEEL BEAM. DURING CORROSION REMOVAL DISCOVERED A CRACK RUNNING CLEAR THROUGH KEEL BEAM LOWER FLANGE FROM RADIUS TO RADIUS, AT BS 950E PLUS 3.5 STR 29R CRACK WAS 1.5 LONG. CUT OUT SKIN FOR ACCESS AND REMOVED KEEL BEAM FROM BS 950 TO 980. REPLACED KEEL BEAM AND REPAIRED SKIN CUT OUT PER SRM 53-30-3 FIG 3 AND FEDEX EA 7-5310-25557.

Part: FLOOR BEAM — CORRODED (BS 480)

THE UPPER CHORD OF THE BS 480, FLOOR BEAM IS CORRODED OUT OF LIMITS AT RBL 12, WL 208.5. CUT OUT DAMAGED AREA AND REPAIRED PER SRM 53-10-08, FIG 3.

Part: SKIN — CORRODED (BS 480-500)

BS 480-500 STR 28R-26R. THERE ARE DEEP GOUGES, DENTS AND A SMALL BULGE ON EXTERIOR SKIN. REPAIRED CORRODED SKIN AT BS 496, RBL 7 PER FEDEX SRM 53-30-5.

Part: STRINGER — CORRODED (BS 496)

CORROSION IN FWD CARGO BAY. THERE IS CORROSION ON STR 28R AT BS 496. REPAIRED CORRODED STR 28R AT BS 496 PER FEDEX SRM 53-10-3. REPAIRED CORRODED SKIN FROM NRO 067 AT BS 496 , RBL 7 PER FEDEX SRM 53-30-3.

Part: RIB — CRACK (LT HORIZ STAB)

FLOOR BEAM CORRODED AT BS 460, RBL 12 - 23, WL 208.5. REMOVED CORROSION, FABRICATED AND INSTALLED REPAIR PER SRM 53-10-1 AND 53-10-08.

Part: SHEAR TIE — CORRODED (BS 970)

CORROSION (71C709-02) ON SHEAR TIE LOWER FLANGE BS 970, RBL 3, FWD AND AFT SIDE OF FRAME AFT CARGO BAY. INSTALLED NEW SHEAR TIE OR BS 970 PER SRM 53-10-2.

Part: SEAT TRACK — CORRODED (BS 495-535)

SEAT TRACK CORRODED ALONG FLANGES BS 495-535 AND BS 615, BL 0, WL 208.5. REMOVED, FABRICATED AND INSTALLED SEAT TRACK BS 480-630 PER SRM 53-10-5.

Part: SPAR — CRACKED (RT WING)

NR 6 SLOT CRACKED IN SPAR AT TAI TUBE CUTOUT. STOP DRILLED CRACK AND INSTALLED REPAIR PARTS IAW SRM 57-20-1, 51-30-2 AND FEDEX EA 7-5710-25579.

Part: STRINGER — CRACKED (VERT FIN)

NR 8R STR IS CRACKED IN VERTICAL FIN BAY NR 8 FIN STA 180 WHERE STR ATTACHES TO WEB. REPAIRED NR 8R STR IN VERTICAL FIN, BAY NR 8, FIN STA 180. FEDEX SRM 55-30-4 FIG 1.

Part: SKIN — CORROSION (BS 689-688)

CORROSION ON (INTERIOR) SKIN AT BUTT JOINT BS 680-688 BETWEEN STR 26-27R. REPAIRED CORROSION ON SKIN AT BUTT JOINT BS 680-688 BETWEEN STR 26-27R AS PER FEDEX SRM 53-30-3.

Part: STRINGER — CRACKED (VERT FIN)

STR NR 8R IS CRACKED IN VERTICAL FIN BAY NR 8 AT FIN STA 151.2. REPAIRED STR NR 8R IN VERTICAL FIN BAY NR 8 AT FIN STA 151.2 IAW FEDEX SRM 55-30-4.

Part: FRAME — CRACKED (BS 520)

IN THE FWD CARGO BAY, THE UPPER FLANGE OF FRAME IS CRACKED AT BS 520 LBL 2 WL 154 AND RBL 14 WL 154. FABRICATED DOUBLER, CUT OUT DAMAGE, REPAIRED FRAME PER SRM 51-40-3.

Part: SEAT TRACK — CORRODED (BS 538-550)

SEAT TRACK CORRODED ALONG RT FLANGE BS 538 TO 550 RBL 25 WL 208.5. REMOVED, MACHINE SHOP FABRICATED AND INSTALLED SEAT TRACK FROM BS 480 TO 550.

Part: CHORD — DOUBLE DRILLED (BS 720)

DOUBLE HOLE IN LOWER CHORD OF FLOORBEAM BS 720F LBL 46 WL 201. OVERSIZED HOLE AND INSTALLED HI-LOC PER ENGINEERING REQUEST.

Part: SKIN — CHAFED (BS 720)

UPON REMOVAL OF LT WING PIE SECTION. FOUND CHAFING SPOT 2 INCHES LONG BY 1 INCH WIDE AND .081 DEEP ON STR 19L AT LAP SEAM, STA 720D PLUS 11. REPAIRED DAMAGE PER FEDEX SRM 53-30-3.

Part: TRACK — CORRODED (BS 344-423)

SEAT TRACK CORRODED OUT OF LIMITS BS 344 TO 423 LBL 25 WL 208.5. REMOVED, FABRICATED AND REPLACED SEAT TRACK FROM BS 344 TO 480, WORK PER SRM 51-10-1.

Part: SHEAR TIE — CORRODED (BS 720)

CORROSION ON SHEAR TIE BS 720 BETWEEN STR 27 LT AND RT. REMOVED, FABRICATED AND REPLACED SHEAR TIE SRM 53-10-4.

Part: WEB — CORROSION (BS 791)

AREA OF CORROSION ON LOWER WEB OF DELTA BEAM, OUTER SURFACE AT BS 791 LBL 5. REPAIRED AREA OF CORROSION ON LOWER WEB OF DELTA BEAM, OUTER SURFACE AT BS 791 PER FEDEX SRM 51-40-2 FIG 1.

Part: SHEAR TIE — CORRODED (BS 700)

CORROSION ON SHEAR TIE BS 700 STR 26 AND 27 RIGHT. FOUND CORROSION OUT OF LIMITS. CUT OUT DAMAGE AREA AND REPAIRED PER SRM 53-10-04.

Part: BONDING JUMPER — CORRODED (NR 5 LE FLAP)

CORROSION ON NR 5 K-FLAP BULLNOSE O/B BONDING JUMPER UPPER ATTACH POINT. FOUND CORROSION OUT OF LIMITS. CUT OUT DAMAGE AREA AND REPAIRED PER SRM 57-50-03.

Part: SKIN — DAMAGED (BS 1119)

DENT ON INNER SKIN SURFACE AT BS 1119 LBL 4 (BETWEEN STR 29L-30L). FOUND DENT TO BE OUT OF LIMITS, REMOVED DAMAGE, FABRICATED REPAIR PLATE OUT OF 2024-T3, .071 X 8 INCH X 12 INCH, M459214 AND INSTALLED AS PER FEDEX SRM 53-30-3.

Part: SKIN — DENTED (BS 1214-1221)

DENT AT BS 1214-1221 BETWEEN STR 24-25R. DENT IS 7 INCHES X 5.5 INCHES X .250 INCH DEEP. RECONTOURED DENT TO WITHIN LIMITS. WORK PER SRM 51-40-2.

Part: FRAME — CRACKED (BS 720)

CRACK IN FRAME BS 720 RBL 4 WL 153. REPAIRED FRAME AT BS 720 RBL 4 WL 153 AS PER FEDEX SRM 51-40-2.

Part: FRAME — DOUBLE DRILLED (BS 680)

DOUBLE HOLE IN FRAME AT STR CLIP ON STR 5R AT BS 680. CUT OUT DAMAGED AREA AND REPAIRED PER SRM 53-10-4.

Part: SKIN — CORRODED (BS 1046)

AREA OF CORROSION ON INNER SKIN AT BS 1046 JUST ABOVE STR 28R. FABRICATED REPAIR DOUBLER AND INSTALLED, WORK DONE PER SRM 53-30-3.

Part: FRAME — CRACKED (BS 520)

IN THE FWD CARGO BAG THE UPPER FLANGE AT FRAME IS CRACKED AT BS 520 RBL 42 WL 165. FABRICATED REPAIR DOUBLER AND REPAIRED FRAME PER SRM 51-40-3.