N498FE

Part: CONNECTOR — SHORTED (A/C PACK) · airframe 57,345 hrs · 47,158 cycles

DURING CLIMB, ACFT CABIN ACT WAS TOO HIGH. FOUND PACK VALVE C/B POPPED. CABIN ALT STABILIZED AT 8500' AT 20,000 WITH L AFT PACK OPERATING ONLY. TROUBLESHOT SYS, FOUND PACK VALVE BREAKER WOULD RESET MOMENTARILY. CHECKED BOTH FWD PACK SHUTOFF VALVES NO DEFECTS NOTED. FOUND RT PACK FLOW CONTROL VALVE CONNECTOR D870 HAD WIRES W338-010-20 AND W338-105-20 SHORTED TOGETHER CAUSING C/B TO POP. REPAIRED AND REPINNED WIRES AS REQUIRED. INSTALLED CONNECTOR RESET C/B AND PERFORMED OPS CHECK OF BOTH PACK SYS WITH NO DEFECTS NOTED. REF MM. 36-12-061-4 / MM. 21-55-000-5. ACFT OK FOR SERVICE.

Part: STRINGER CLIP — CRACKED (ZONE 100) · airframe 56,536 hrs · 46,536 cycles

ORIGINAL LOST, A86-143 REF AD 92-12-03, AFT PIT BILGE BODY FRAME STR CLIP IS BUCKLED, CRACKED, CORRODED BS 950F, STR 27L (EO 7-5310-7-2354) N00252. REMOVED AND REPLACED STR CLIP AT AFT PIT BILGE BODY FRAME STR 27L, STA 950F, REF SRM 51-30-2 PG 2-4 . THIS IS CLASSIFIED AS A MAJOR REPAIR.

Part: FAIRING — CRACKED (ZONE 500) · airframe 56,536 hrs · 46,536 cycles

LEFT WING INBOARD MID FLAP OUTBOARD JACK SCREW FAIRING INTERIOR SKIN CRACKED AT ATTACH HOLE REPAIRED LEFT WING INBD MID FLAP O/B JACK SCREW FAIRING REF SRM 57-20-4 PG 5 AND SRM 51-30-2 PG 2. THIS IS CLASSIFIED AS A MINOR REPAIR.

Part: STRINGER SPLICE — CORRODED (ZONE 100) · corrosion level 2 · airframe 56,536 hrs · 46,536 cycles

FWD PIT STRINGER SPLICE AT 27L GOING THROUGH STA 680 CORRODED ON OUTBD SIDE REMOVED CORROSION FROM ORIGINAL THICKNESS OF 0.064 INCH FROM BUTT SPLICE STRAP WITH 0.054" REMAINING. OUT-OF-LIMITS DUE TO "NO REWORK PERMITTED IN BUTT SPLICE STRAP". FABRICATED REPAIR DOUBLER, TREATED, PRIMED AND INSTALLED, REFERENCE SRM 53-30-1 FIGURE NR 1 AND EA NR 7-5330-118259. REMOVED CORROSION ON STRINGER SPLICE, FROM ORIGINAL THICKNESS OF 0.056 WITH 0.052 INCH REMAINING, 0.004 LOSS AND IS WITHIN LIMITS. REFERENCE SRM 53-10-1/PAGES 1-2A. CLASSIFIED AS A MAJOR REPAIR.

Part: STRUCTURE — CRACKED (WING TO BODY) · airframe 56,536 hrs · 46,536 cycles

LWR EXT FUSE WING BODY FILLET FAIRING SUPPORT FRAME LWR CHORD ANGLE IS BUCKLED/CRACKED AT I/B END 950A, LBL 14. REPAIRED SUPPORT FRAME LOWER CHORD ANGLE FOR WING TO BODY FAIRING AT 950A, LBL 14 REF SRM 51-40-3. THIS IS CLASSIFIED AS A MINOR.

Part: WEB — CORRODED (ZONE 100) · corrosion level 2 · airframe 56,536 hrs · 46,536 cycles

CORROSION ON WEB TO BODY SKIN ON ANGLE ON WEB BETWEEN BS 950A TO 950B, LBL 18, WL 141 REPLACED WEB AT STA 950 - 950B, LBL AND CLIP AT STA 950A LBL 18 REF BOEING DWG 69-44877 AND SRM 51-30-3. THIS IS CLASSIFIED AS A MINOR REPAIR.

Part: SKIN — CRACKED (R1 DOOR) · airframe 56,536 hrs · 46,536 cycles

MAIN DECK 1R DOOR EXT SKIN IS BUCKLED/CRACKED AT UPPER HINGE CUT OUT UPPER EDGE, 4 INCHES FROM FWD END. REMOVED DAMAGE AND CHECKED WITH HFEC, NO DEFECTS FOUND. REMOVED LINER SUPPORT, VERIFIED MATERIAL, MADE A .040 INSURANCE CUT REF SRM 52-00-3 FIG 3 STEP 2. FABRICATED UPPER DOUBLE, TREATED AND PRIMED. INSTALLED DOUBLER AND PAINTED. THIS IS CLASSIFIED AS A MAJOR REPAIR.

Part: STOP FITTING — GOUGED (ZONE 800) · airframe 56,536 hrs · 46,536 cycles

AFT LOWER NR 3 CARGO DOOR FORWARD FRAME LOWER STOP FITTING GOUGED. DOOR REMOVED REF AMM 52-35-071-4, LWR FORWARD FITTING REMOVED AND INSTALLED REF SRM 51-30-02. DOOR INSTALLED REF AMM 52-35-071, ADJUSTED STOPS. THIS IS CLASSIFIED AS A MAJOR REPAIR.

Part: PANEL — DELAMINATED (ZONE 600) · airframe 56,536 hrs · 46,536 cycles

RIGHT WING L/E LWR PANEL 6402 HAS 2 INCH BY 6 INCH AREA OF DISBOND CORE FROM INNER AND OUTER SURFACES. REPAIRED PANEL 6402 REF SRM 51-40-9 PARAGRAPHS 3D, 4B, 4E, 4F AND AMM 51-20-051-7, 51-20-151-7 TAP TEST GOOD. THIS IS CLASSIFIED AS A MINOR REPAIR.

Part: RIB — CRACKED (HORIZONTAL STAB) · airframe 56,536 hrs · 46,536 cycles

RT HORIZONTAL STAB, AFT SUPPORT RIB IS CRACKED NEAR ELEVATOR ATTACH POINT, ELEVATOR STA 99.79 REMOVED WIPER PLATES, REF SRM 51-30-2. FAB RADIUS FILLER FOR REPAIR, .100" 2024-T3 REF DWG 69-33174. TREATED AND PRIMED REF SRM 51-10-2. INSTALLED REPAIR REF SRM 55-10-4, THIS IS CLASSIFIED AS A MAJOR REPAIR.

Part: SKIN — DENTED (RT ELEVATOR) · airframe 56,536 hrs · 46,536 cycles

RT ELEVATOR LWR SKIN HAS A DENT 97 INCHES FROM I/B EDGE, 7 INCHES FWD OF REAR SPAR. MEASURED DENT FOUND TO BE WITHIN LIMITS, MEASURED DENT Y = .040 A = 4 INCHES FOUND TO BE 100 REF SRM 55-10-1 PG 7 FIG 2. THIS IS CLASSIFIED AS A MINOR REPAIR.

Part: ANGLE — CORRODED (ZONE 100) · corrosion level 2 · airframe 56,536 hrs · 46,536 cycles

CORROSION ON WEB TO BODY SKIN ANGLE ON WEB BETWEEN BS 950A TO 950B, RBL 3, WL 139. REMOVED AND REPLACED INTERCOSTAL WEB AND AFT ATTACH CLIP REF 51-30-2 PG 8. THIS IS CLASSIFIED AS A MINOR REPAIR.

Part: SKIN — GOUGED (ZONE 100) · airframe 56,536 hrs · 46,536 cycles

EXT FUSELAGE SKIN IS GOUGED AT BS 670 O/B OF STR S-28L REMOVED DAMAGED AREA, FABRICATED AND INSTALLED DOUBLER REPAIR REF SRM-30-3 FIG 1. THIS IS CLASSIFIED AS A MAJOR REPAIR AND A CATEGORY "B" REPAIR.

Part: INTERCOSTAL — CRACKED (ZONE 200) · airframe 56,536 hrs · 46,536 cycles

MAIN DECK 1R DR CROSS BEAM, INTERCOSTAL I/B FLANGE IS CRACKED AT 4TH BEAM FROM BOTTOM, 13 INCHES FROM FWD END. REMOVED OLD INTERCOSTAL 4TH FROM BOTTOM 13 INCHES FROM FWD END. HAD SHOP FABRICATE N00557. DRILLED NEW INTERCOSTAL, INSTALLED INTERCOSTAL TREATED AND PRIMED AN PAINTED, EXTERIOR FASTENERS INSTALLED UPPER HINGE COVER PLATE.

Part: BULKHEAD — CORRODED (ZONE 100) · airframe 56,536 hrs · 46,536 cycles

BS 178 BULKHEAD EXT SURFACE WL 187 - 193 LBL 19" TO 24" HAS CORROSION PITS. CHEMICALLY REMOVED CORROSION FROM BS 178 BULKHEAD EXT SURFACE WL 185-193 LBL 19" TO 24". THICKNESS OF MATERIAL IS .055, MATERIAL REMAINING IS .053 A LOSS OF .022 FOUND TO BE WITH-IN LIMITS. TREATED AND PRIMED AREA REF SRM 53-30-1 FIG 1, SRM 53-10-2 PG 7. THIS REPAIR IS CLASSIFIED AS A MINOR REPAIR. LEVEL 1 CORROSION.

Part: STRINGER CLIP — CORRODED (ZONE 100) · corrosion level 2 · airframe 56,536 hrs · 46,536 cycles

STRINGER TIE ON STR 26R AT FS 941A HAS CORROSION ON OUTER SIDE OF TIE. REMOVED DAMAGED STRINGER TIE REPLACED NEW STRINGER TIE, REF SRM 51-30-2 PG1. THIS IS CLASSIFIED AS A MAJOR REPAIR.

Part: SKIN — CRACKED (ZONE 100) · airframe 56,536 hrs · 46,536 cycles

MLG WW KEEL BEAM LWR EXT SKIN PANEL AT BS 940 TO 950-12, LBL 5-RBL 5 2 EA CRACKED FASTENER HOLES BS 947, RBL 5 (MKD). REMOVED DAMAGE AND FABRICATED A REPAIR FILLER AND A REPAIR DOUBLER. TREATED, PRIMED AND PAINTED ALL REPAIR PARTS AND INSTALLED. EDGE SEALED REPAIR DOUBLER. REFERENCE SRM 51-40-2/FIGURE NR 1 AND BOEING DOCUMENT NR 65-18636/ITEM NR 280. CLASSIFIED AS A MAJOR REPAIR.

Part: STRUCTURE — CRACKED (NR 2 NACELLE) · airframe 56,536 hrs · 46,536 cycles

NR 2 ENGINE LEFT FWD COWLING OUTER AFT CORNER MULTIPLE LAYERS OF SHEET METAL ARE CRACKED. REMOVED DAMAGED AREA REF SRM 51-40-2. MATERIAL ID AT 2024 T3 .080 REF SRM 65-10-3 A48140 FOR DOUBLER. MATERIAL ID AT 2024 T3 .100 A 11734 REF SRM 54-30-2 FOR FILLER. TREATED AND PRIMED DOUBLER AND FILLER REF SRM 51-10-2 PG 7 PG 2. INSTALLED DOUBLER AND FILLER WET WITH SEALANT REF SRM 54-10-3 PG 24. APPLIED TEFLON FINISH REF AMM 51-20-071-7. FABRICATION OF DOUBLER SRM 54-10-3, FILLER SRM 51-30-3. THIS IS CLASSIFIED AS A MINOR REPAIR.

Part: SHEAR TIE — CORRODED · corrosion level 2 · airframe 56,536 hrs · 46,536 cycles

FWD PIT SHEAR TIE STA 520 BETWEEN STR 28L-28R CORRODED. REMOVED FASTENER'S TO ACCESS CORROSION IN REF TO SRM 51-30-2 PG 2. REMOVED CORROSION ON FWD SIDE OF SHEAR TIE BS 520 STR 28L-28R IN REF TO SRM 53-10-1. CHECK SHEAR TIE FOR MAT'L LOSS ORIGINAL THICKNESS .042 INCH. REMOVED .003 INCH, REMAINING MAT'L .039 INCH. PER ITEM 3 MAT'L LOSS IS LESS THAN 109.3 IS WITHIN LIMITS REF SRM 53-10-1 FIG 1. TREATED AND PRIMED SHEAR TIE IN REF TO SRM 51-10-2 PG 7. PAINTED SHEAR TIE IN REF TO M/M 51-20-151-07. REINSTALLED FASTENERS IN REF TO SRM 51-30-2 PG 2. THIS IS CLASSIFIED AS A MINOR REPAIR.

Part: FITTING — CRACKED (ZONE 800) · airframe 56,536 hrs · 46,536 cycles

MAIN DECK 1R DR BOTTOM CROSS BEAM AFT STOP FITTING IS CRACKED REMOVED AND REPLACED STOP FITTING REF SRM 51-30-2. DOOR ADJUSTEMENT ACCOMPLISED ON W/0 40304 N00067, THIS IS CLASSIFIED AS A MINOR REPAIR.

Part: SKIN — CORRODED (ZONE 100) · corrosion level 2 · airframe 56,536 hrs · 46,536 cycles

MLG W/W KEEL BEAM LWR EXT SKIN PANEL AT BS 940 TO 950 PLUS 12, LBL 5- RBL 5 HAS SEVERAL AREAS OF CORROSION REMOVED AREAS OF CORROSION. REMOVED 0.005 INCH FROM ORIGINAL SKIN THICKNESS OF 0.071 INCH. 0.066 INCH REMAINING AND SKIN PANEL IS WITHIN LIMITS. TREATED, PRIMED AND PAINTED AFFECTED AREA. REFERENCE SRM 51-10-6/PAGES 12-15, SRM 53-10-1/FIGURES 1 AND 2 MM 51-20-021-7, MS51-20-031-7 AND MM 51-20-013-7. CLASSIFIED AS A MAJOR REPAIR, LEVEL 1 CORROSION.

Part: FAIRING — CRACKED (ZONE 600) · airframe 56,536 hrs · 46,536 cycles

RT WING NR 6 FLAP TRACK FWD FAIRING HAS SEVERAL CRACKS REMOVED FASTENERS AND FABRICATED NEW REPAIR DOUBLER. INSTALLED NEW DOUBLER REF SRM 57-20-4 FIG 1. TREATED AND PRIMED AND PAINTED REF SRM 51-10-2 P2. THIS IS CLASSIFIED AS A MINOR REPAIR.

Part: STRINGER CLIP — CRACKED (ZONE 100) · airframe 56,536 hrs · 46,536 cycles

AFT PIT BILGE BODY FRAME, STR CLIP IS BUCKLED/CRACKED, BS 970, STR 27L. REMOVED AND REPLACED STRINGER CLIP AT BS 970, STRINGER 27L. IAW SRM 51-30-2, SRM 51-30-5. THIS IS CLASSIFIED AS A MINOR REPAIR.

Part: FLOOR SUPPORT — CORRODED (ZONE 200) · corrosion level 2 · airframe 56,536 hrs · 46,536 cycles

FLOOR SUPPORT CORRODED AT BS 344, LBL 30 REMOVED CORROSION ON FLOOR SUPPORT STA 344, LBL 30, REF SRM 51-10- 6 PG 12. MATERIAL LOSS 50 PERCENT. FOUND TO BE OUT OF LIMITS, REF SRM 53-10-1 PG 1-3. FABRICATED NEW FLOOR SUPPORT AND SHIM, REF BOEING DWG 65-96173. TREATED AND PRIMED AND PAINTED AND INSTALLED FLOOR SUPPORT REF SRM 51-10-2 AND AMM 51-10-151-7, SRM 51-30-2. THIS IS CLASSIFIED AS A MINOR REPAIR.

Part: BRACKET — CRACKED (ZONE 100) · airframe 56,536 hrs · 46,536 cycles

E/E COMPARTMENT LEFT SIDE E1-1 RACK, SHELF FOR POWER SUPPLY TRANSFER RECTIFIER UNIT CRACKED AT FOWARD INBOARD SIDE. REMOVED MOUNTING SHELF, REMOVED DAMAGED BRACKET, FABRICATED NEW BRACKET, TREATED AND PRIMED AND INSTALLED BRACKET, RE SECURED E1-1 SHELF. REF DWG 69-20261, SRM 51-30-2 PG 2, 51-10-2 PG 1.

Part: PANEL — CRACKED (ZONE 100) · airframe 56,536 hrs · 46,536 cycles

LOWER PANEL 3456 RT IS CRACKED WITH ERODED AREA FLAME SPRAY. REPLACED CRACK AND FLAME SPRAY ON PANEL 3456 REF SRM 51-40-9 PARAGRAPHS 3D, 4E, 4F AND AMM 51-20-051-7. THIS IS CLASSIFIED AS A MINOR REPAIR.

Part: SHEAR TIE — CORRODED (ZONE 100) · corrosion level 2 · airframe 56,536 hrs · 46,536 cycles

FWD PIT SHEAR TIE CORRODED, STA 660 BETWEEN STR 27R - 26R REMOVED CORROSION ON FWD SHEAR TIE STA 660 STR 27R - 26R REF SRM 51-10-6 PG 12 ORIGINAL MATERIAL .050". MATERIAL REMAINING .035", MATERIAL LOSS .015". FOUND OUT OF LIMITS REF SRM 53-10-1 PG 1-2. FABRICATED NEW SHEAR TIE NOTE ID 60-4493, 7075 T-6 EXTRUSION REF BOEING DWG 69-43683. TREATED AND PRIMED AND INSTALLED SHEAR TIE, REF SRM 51-10-2, 51-30-2. THIS IS CLASSIFIED A MAJOR REPAIR.

Part: STRINGER CLIP — DAMAGED (BS 950A S27L) · airframe 56,536 hrs · 46,536 cycles

STRINGER CLIP CRACKED ON STR 27L FS 950A REMOVED DAMAGED CLIP, REPLACED CLIP, REF SRM 51-30-2. THIS IS CLASSIFIED AS A MAJOR REPAIR.

Part: ATTACH BRACKET — CRACKED (ZONE 800) · airframe 56,536 hrs · 46,536 cycles

MAIN ENTRY DOOR 1-L, S/N 261, UPPER AFT LINER ATTACH BRACKET IS CRACKED REMOVED BRACKET IN REF TO SRM 51-30-2 PG 2, VERIFIED MAT'L AS 2024 T3 .040" IN REF TO DWG 65-49652-5 FABRICATED NEW ANGLE IN REF TO DWG 65-49652-5. TREATED AND PRIMED ANGLE IN REF TO SRM 51-10-2 PG 2, APPLIED FX P/N FX65-49652-5 IN REF TO GMM 7-0-1001. INSTALLED NEW ANGLE IN REF TO 51-30-2 PG 2. CLASSIFIED AS A MINOR REPAIR.

Part: SUPPORT — CRACKED (PAX DOOR) · airframe 56,408 hrs · 46,435 cycles

FORWARD ENTRY DOOR LOWER AND UPPER AFT LATCH TORQUE TUBE SUPPORT CASTING HAS PARTIALLY DETACHED FROM DOOR FRAME AND FRAME IS CRACKED ON BOTH UPPER AND LOWER ATTACH POINTS. REMOVED AND REPLACED L1 FORWARD ENTRY DOOR PER 727-200 MM 52-11-001-4/ADJUSTMENT TEST GOOD PER 727-200MM 52-11-001-5. PREMATURE REMOVAL/INSTALLATION.

Part: DOOR — MALFUNCTIONED · airframe 55,605 hrs · 45,823 cycles

CREW ENTRY DOOR SHOWED CLOSED AND LOCKED WITH HANDLE FULL DOWN AND DOOR LIGHT OUT. AIRCRAFT WOULD NOT PRESSURIZE. RTB, UPON INITAL INSP FOUND ROLLERS ON AFT SIDE OF DOOR NOT IN TRACKS ON THE UPPER AND LOWER TRACK. UNABLE TO OPEN DOOR. AFTER OFF LOAD VISUALLY INSPECTED DOOR AND FOUND AFT LOWER ROLLER OUT OF POSITION. RAISED DOOR HANDLE WITH MINIMAL PRESSURE AND DOOR OPENED. VISUALLY INSPECTED DOOR ROLLERS AND GUIDES NO PROBLEM NOTED. OPENED AND CLOSED DOOR A NUMBER OF TIMES WITH NO NOTICEABLE PROBLEMS OR EXCESS PRESSURE REQUIRED TO CLOSE DOOR.

Part: REPAIR — MISINSTALLED (CARGO DOOR) · airframe 54,698 hrs · 45,072 cycles

EXISTING REPAIR ON NR 3 CARGO DOORFWD TO AFT EDGE EXTERNAL SKIN DOES NOT COMPLY WITH EXISTING FAA DATA. REMOVED OLD DOUBLER AND DAMAGED SKIN IWA SRM 51-30-2 & 52-00-3 FIG3 INSTALLED REPAIR PARTS IAW SRM 51-30-2. REINSTALLED REMOVED FOR ACCESS IAW SRM 51-30-2.

Part: SKIN — CHAFED (RT WING TE) · airframe 54,698 hrs · 45,072 cycles

RT WING FIXED TRAILING EDGE HAS CHAFE MARK AND SPOTS OF GOUGES FROM WS 224.5 TO WS 625.0 (SKIN UNDER FWD END OF SPOILER.) FABRICATED AND INSTALLED NEW STRAPS IAW SRM 57-30-2 REPLACEMENT PARTS FABRICATED ON TRAVELERS T5/564670,T5/564665,T5/564668,T5/564644,

Part: FLANGE — WORN (FUSELAGE) · airframe 54,698 hrs · 45,072 cycles

AFT LWR. FUSELAGE FLANGE FOR NR 2 ENG LWR COWLING FWD EDGE CONTACT IS WORN. REMOVED AREA OF DAMAGE SRM51-10-01 &51-30-2.FABRICATED REPLACEMENT STRUCTURE P/N 65-23687-21 & SPLICE PARTS FABRICATED ON TRAVELER T5/565148. LOCATED DRILLED AND INSTALLED IAW SRM 51-30-2 APPLIED TEFLON COATING IAW MM 51-20-071-7.

Part: STRINGER — CRACKED (LT WING) · airframe 54,698 hrs · 45,072 cycles

LEFT WING STA 686.5 UPPER STRINGER 13 HAS A CRACK IN THE LOWER TAB SECTION THAT ATTACHES TO THE RIB PROTRUDING FROM UNDER RADIUS FILLER, REMOVE DAMAGE AND REPAIRS IAW BOEING S/B 727-57A159.

Part: REPAIR — MISINSTALLED (FUSELAGE) · airframe 54,698 hrs · 45,072 cycles

EXISTING REPAIRS 2 AT AFT AIR STAIR CUT OUT FWD CORNERS DO NOT COMPLY WITH FAA DATA. REMOVED RT AND LT REPAIR DOUBLERS IAW SRM 51-30-2. PERFORMED HFEC INSPECTION PER NTM-PT6 51-00-00 TO MARK THE END OF CRACKS. NO CRACKS NOTED BEYOND STOP DRILL. FABRICATED 2 REPAIR DOUBLERS PER SRM 51-40-2 AND SR27-53-024. INSTALLED LT DOUBLER AND FILLER PER SRM 51-30-2. INSTALLED RT DOUBLER PER SRM 51-30-2.

Part: BEAM — CORRODED (FUSELAGE) · airframe 54,698 hrs · 45,072 cycles

FOUND HORIZONTAL WALKWAY BEAM CHORD IS CORRODED AT STA 304 LEFT HAND SIDE OF NOSE LANDING GEAR WHEEL WELL. REMOVED WALKWAY BEAM IAW SRM 51-30-2, REMOVED FLOOR WEBS IAW SRM 51-30-2, REPLACED NEW WALKING BEAM CHORD IAW SRM 51-30-2, APPLIED LEVELING COMPOUND IAW SRM 51-30-4 AND INSTALLED FLOOR WEBS IAW SRM 51-30-2, REPAIR IS CLASSIFIED AS MAJOR.

Part: STRINGER — MISDRILLED (FUSELAGE) · airframe 54,698 hrs · 45,072 cycles

FOUND MCD STRINGER 4L AT STA 450 HAS TOOLING MARKS AND 2 DRILLED MARKS ON OUTBD SIDE OF STRINGER, AFTER BLENDING AND FOUND OUT OF LIMITS PER SRM 5310-01, FIG 1, REMOVED AND REPLACED ALL DAMAGE PARTS IAW SRM 51-30-3.

Part: REPAIR — UNKNOWN (FUSELAGE) · airframe 54,698 hrs · 45,072 cycles

FOUND PREVIOUSLY REPAIR INSTALLED AT STA. 400, STR 22L WAS ACCOMPLISHED IAW SRM 53-30-3 FIG.3 BASED ON AN EXTERNAL VISUAL EVALUATION, CONSISTS OF LOCATION, SHAPE, SIZE, MATERIAL TYPE AND THICKNESS, FASTENERS NUMBERS AND SPACING, GENERAL WORKMANSHIP AND REPAIR IS CLASSIFIED AS MAJOR.

Part: DOUBLER — DEBONDED (FUSELAGE) · airframe 54,698 hrs · 45,072 cycles

FOUND INTERNAL DOUBLER DISBONDED ON FUSELAGE SKIN AT B.L. 0, STRINGER 30 AT STA 700 TO STA 720. REMOVED AND REPLACED DOUBLER IAW SRM 53-30-3 AND SRM 51-30-2.

Part: REPAIR — UNKNOWN (FUSELAGE) · airframe 54,698 hrs · 45,072 cycles

FOUND PREVIOUSLY REPAIR INSTALLED AT STA 1050, STR 19L WAS ACCOMPLISHED IAW SRM 53-30-3, FIG 3 BASED ON AN EXTERNAL VISUAL EVALUATION CONSISTS OF LOCATION, SHAPE, SIZE, MATERIAL TYPE AND THICKNESS, FASTENERS NUMBERS AND SPACING, GENERAL WORKMANSHIP AND REPAIR IS CLASSIFIED AS MAJOR.

Part: REPAIR — UNKNOWN (FUSELAGE) · airframe 54,698 hrs · 45,072 cycles

FOUND PREVIOUSLY REPAIR INSTALLED AT STA 720, STR 23L WAS ACCOMPLISHED IAW SRM 53-30-3, FIG 1 BASED ON AN EXTERNAL VISUAL EVALUATION CONSISTS OF LOCATION, SHAPE, SIZE, MATERIAL TYPE AND THICKNESS, FASTENER NUMBERS AND SPACING, GENERAL WORKMANSHIP AND REPAIR IS CLASSIFIED AS MAJOR.

Part: REPAIR — UNKNOWN (FUSELAGE) · airframe 54,698 hrs · 45,072 cycles

FOUND PREVIOUSLY REPAIR INSTALLED AT STA 500, STR 27R WAS ACCOMPLISHED IAW SRM 53-30-3 FIG 2 BASED ON AN EXTERNAL VISUAL EVALUATION CONSISTS OF LOCATION, SHAPE, SIZE, MATERIAL TYPE AND THICKNESS, FASTENERS NUMBERS AND SPACING, GENERAL WORKMANSHIP AND REPAIR IS CLASSIFIED AS MAJOR.

Part: REPAIR — UNKNOWN (FUSELAGE) · airframe 54,698 hrs · 45,072 cycles

FOUND PREVIOUSLY REPAIR INSTALLED ABOVE AIRSTAIRS CONTROL PANEL WAS ACCOMPLISHED IAW SRM 53-30-3 FIG 1, BASED ON AN EXTERNAL VISUAL EVALUATION CONSISTS OF LOCATION, SIZE, SHAPE, MATERIAL TYPE AND THICKNESS, FASTENER NUMBERS AND SPACING, GENERAL WORKMANSHIP AND REPAIR IS CLASSIFIED AS MAJOR.

Part: REPAIR — UNKNOWN (FUSELAGE) · airframe 54,698 hrs · 45,072 cycles

FOUND PREVIOUSLY REPAIR INSTALLED AT STA 950E, STR 29R WAS ACCOMPLISHED IAW SRM 53-30-3 FIG 1 BASED ON AN EXTERNAL VISUAL EVALUATION CONSISTS OF LOCATION, SHAPE, SIZE, MATERIAL TYPE AND THICKNESS, FASTENER NUMBERS AND SPACING, GENERAL WORKMANSHIP AND REPAIR IS CLASSIFIED AS MAJOR.

Part: REPAIR — UNKNOWN (LT WING) · airframe 54,698 hrs · 45,072 cycles

FOUND PREVIOUSLY REPAIR INSTALLED AT UPPER SURFACE OF LT WING TIP WAS ACCOMPLISHED IAW SRM 57-20-1 FIG 2, BASED ON AN EXTERNAL VISUAL EVALUATION CONSISTS OF LOCATION, SIZE, SHAPE, MATERIAL TYPE AND THICKNESS, FASTENERS NUMBER AND SPACING, GENERAL WORKMANSHIP AND REPAIR IS CLASSIFIED AS MAJOR.

Part: REPAIR — UNKNOWN (FUSELAGE) · airframe 54,698 hrs · 45,072 cycles

FOUND PREVIOUSLY REPAIR INSTALLED AT STA 660, STR 27R WAS ACCOMPLISHED IAW SRM 53-30-3 FIG 14, BASED ON AN EXTERNAL EVALUATION CONSISTS OF LOCATION, SHAPE, SIZE, MATERIAL TYPE AND THICKNESS, FASTENER NUMBERS AND SPACING, GENERAL WORKMANSHIP AND REPAIR IS CLASSIFIED AS MAJOR.

Part: REPAIR — UNKNOWN (FUSELAGE) · airframe 54,698 hrs · 45,072 cycles

FOUND PREVIOUSLY REPAIR INSTALLED AT STA 720, STR 28R WAS ACCOMPLISHED IAW SRM 53-30-3 FIG1, BASED ON AN EXTERNAL VISUAL EVALUATION CONSISTS OF LOCATION, SIZE, SHAPE, MATERIAL TYPE AND THICKNESS, FASTENER NUMBERS AND SPACING, GENERAL WORKMANSHIP AND REPAIR IS CLASSIFIED AS MAJOR.

Part: REPAIR — UNKNOWN (FUSELAGE) · airframe 54,698 hrs · 45,072 cycles

FOUND PREVIOUSLY REPAIR INSTALLED AT STA 680, STR 27R WAS ACCOMPLISHED IAW SRM 53-30-3 FIG 24, BASED ON AN EXTERNAL EVALUATION CONSISTS OF LOCATION, SHAPE, SIZE, MATERIAL TYPE AND THICKNESS, FASTENER NUMBERS AND SPACING, GENERAL WORKMANSHIP AND REPAIR IS CLASSIFIED AS MAJOR.

Part: REPAIR — UNKNOWN (FUSELAGE) · airframe 54,698 hrs · 45,072 cycles

FOUND PREVIOUSLY REPAIR INSTALLED AT STA. 520, STR 27R WAS ACCOMPLISHED IAW SRM 53-30-3 FIG 3 BASED ON AN EXTERNAL VISUAL EVALUATION CONSISTS OF LOCATION, SHAPE, SIZE, MATERIAL TYPE AND THICKNESS, FASTENERS NUMBERS AND SPACING, GENERAL WORKMANSHIP AND REPAIR IS CLASSIFIED AS MAJOR.

Part: REPAIR — UNKNOWN (FUSELAGE) · airframe 54,698 hrs · 45,072 cycles

FOUND PREVIOUSLY 2 REPAIRS INSTALLED AT FWD CARGO DOOR WAS ACCOMPLISHED IAW SRM 52-00-3 FIG 3 AND 4, BASED ON AN EXTERNAL EVALUATION CONSISTS OF LOCATION, SHAPE, SIZE, MATERIAL TYPE AND THICKNESS, FASTENERS NUMBERS AND SPACING, GENERAL WORKMANSHIP AND REPAIR IS CLASSIFIED AS MAJOR.

Part: REPAIR — UNKNOWN (FUSELAGE) · airframe 54,698 hrs · 45,072 cycles

FOUND PREVIOUSLY REPAIR INSTALLED AT STA 300 ABOVE RT NLG DOOR WAS ACCOMPLISHED IAW SRM 53-30-3 FIG 14, BASED ON AN EXTERNAL EVALUATION CONSISTS OF LOCATION, SHAPE, SIZE, MATERIAL TYPE AND THICKNESS, FASTENER NUMBERS AND SPACING, GENERAL WORKMANSHIP AND REPAIR IS CLASSIFIED AS MAJOR.

Part: REPAIR — UNKNOWN (FUSELAGE) · airframe 54,698 hrs · 45,072 cycles

FOUND PREVIOUSLY REPAIR INSTALLED AT STA 445, STR 17R WAS ACCOMPLISHED IAW SRM 53-30-3 FIG 1, BASED ON AN EXTERNAL VISUAL EVALUATION CONSISTS OF LOCATION, SHAPE, SIZE, MATERIAL THICKNESS AND TYPE, FASTENER NUMBER AND SPACING, GENERAL WORKMANSHIP AND REPAIR IS CLASSIFIED AS MAJOR.

Part: REPAIR — UNKNOWN (FUSELAGE) · airframe 54,698 hrs · 45,072 cycles

FOUND PREVIOUSLY REPAIR INSTALLED AT STA 370, STR 24L WAS ACCOMPLISHED IAW SRM 53-30-3, FIG 4, BASED ON AN EXTERNAL VISUAL EVALUATION CONSISTS OF LOCATION, SHAPE, SIZE, MATERIAL TYPE AND THICKNESS, FASTENER NUMBERS AND SPACING, GENERAL WORKMANSHIP AND REPAIR IS CLASSIFIED AS MAJOR.

Part: REPAIR — UNKNOWN (LT WING) · airframe 54,698 hrs · 45,072 cycles

FOUND PREVIOUSLY 2 REPAIRS INSTALLED ON LT WING TIP LOWER SURFACE WAS ACCOMPLISHED IAW SRM 57-20-5 FIG 1, BASED ON EXTERNAL VISUAL EVALUATION CONSISTS OF LOCATION, SHAPE, SIZE, MATERIAL TYPE AND THICKNESS, FASTENERS NUMBERS AND SPACING, GENERAL WORKMANSHIP AND REPAIR IS CLASSIFIED AS MAJOR.

Part: REPAIR — UNKNOWN (FUSELAGE) · airframe 54,698 hrs · 45,072 cycles

FOUND PREVIOUSLY REPAIR, INSTALLED AT STA 1330 ABOVE AIRSTAIRS CUTOUT RT SIDE WAS ACCOMPLISHED IAW SRM 53-30-3 FIG 3, BASED ON AN EXTERNAL VISUAL EVALUATION CONSISTS OF LOCATION, SHAPE, SIZE, MATERIAL THICKNESS AND TYPE, FASTENER NUMBERS AND SPACING, GENERAL WORKMANSHIP AND REPAIR IS CLASSIFIED AS MAJOR.

Part: REPAIR — UNKNOWN (BS 1130) · airframe 54,698 hrs · 45,072 cycles

FOUND PREVIOUSLY REPAIR INSTALLED AT STA 1130, STR 22L WAS ACCOMPLISHED IAW SRM 53-30-3 FIG 1 BASED ON AN EXTERNAL VISUAL EVALUATION CONSISTS OF LOCATION, SHAPE, SIZE, MATERIAL TYPE AND THICKNESS, FASTENER NUMBERS AND SPACING, GENERAL WORKMANSHIP AND REPAIR IS CLASSIFIED AS MAJOR.

Part: REPAIR — UNKNOWN (FUSELAGE) · airframe 54,698 hrs · 45,072 cycles

FOUND PREVIOUSLY REPAIR INSTALLED AT STA 970, STR 25L WAS ACCOMPLISHED IAW SRM 53-30-3 FIG 14, BASED ON AN EXTERNAL EVALUATION CONSISTS OF LOCATION, SHAPE, SIZE, MATERIAL TYPE AND THICKNESS, FASTENERS NUMBERS AND SPACING, GENERAL WORKMANSHIP AND REPAIR IS CLASSIFIED AS MAJOR,

Part: REPAIR — UNKNOWN (BS 1325) · airframe 54,698 hrs · 45,072 cycles

FOUND PREVIOUSLY REPAIR INSTALLED AT STA 1325 ABOVE AIRSTAIRS CUTOUT WAS ACCOMPLISHED IAW SRM 51-40-2 FIG 1, BASED ON AN EXTERNAL VISUAL EVALUATION CONSIST OF LOCATION, SHAPE, SIZE, MATERIAL THICKNESS AND TYPE, FASTENERS SPACING AND NUMBERS, GENERAL WORKMANSHIP AND REPAIR IS CLASSIFIED AS MAJOR.

Part: REPAIR — UNKNOWN (FUSELAGE) · airframe 54,698 hrs · 45,072 cycles

FOUND PREVIOUSLY REPAIR INSTALLED AT STA.1323 LT SIDE BELOW PYLON TRAILING EDGE WAS ACCOMPLISHED IAW SRM 51-40-2, FIG 1, BASED ON AN EXTERNAL EVALUATION CONSISTS OF LOCATION, SIZE, SHAPE, MATERIAL TYPE AND THICKNESS, FASTENERS NUMBERS AND SPACING, GENERAL WORKMANSHIP AND REPAIR IS CLASSIFIED AS MAJOR.

Part: REPAIR — UNKNOWN (RT WING) · airframe 54,698 hrs · 45,072 cycles

FOUND PREVIOUSLY REPAIR INSTALLED AT RT WING OB OF LANDING LIGHT WAS ACCOMPLISHED IAW SRM 57-30-4, BASED ON AN EXTERNAL VISUAL EVALUATION, CONSISTS OF LOCATION, SHAPE, SIZE, MATERIAL THICKNESS AND TYPE, FASTENERS NUMBER AND SPACING, GENERAL WORKMANSHIP AND REPAIR IS CLASSIFIED AS MAJOR.

Part: REPAIR — UNKNOWN (FUSELAGE) · airframe 54,698 hrs · 45,072 cycles

FOUND PREVIOUSLY REPAIR INSTALLED AT FWD OF NR 2 ENGINE LT SIDE WAS ACCOMPLISHED IAW SRM 51-40-2, FIG 1, BASED ON AN EXTERNAL VISUAL EVALUATION CONSISTS OF LOCATION, SHAPE, SIZE, MATERIAL TYPE AND THICKNESS, FASTENER NUMBERS AND SPACING, GENERAL WORKMANSHIP AND REPAIR IS CLASSIFIED AS MAJOR.

Part: REPAIR — UNKNOWN (FUSELAGE) · airframe 54,698 hrs · 45,072 cycles

FOUND PREVIOUSLY REPAIR INSTALLED AT STA 188 25L WAS ACCOMPLISHED IAW SRM 53-30-3, FIG 1 BASED ON AN EXTERNAL VISUAL EVALUATION CONSISTS OF LOCATION, SIZE, SHAPE, MATERIAL TYPE AND THICKNESS, FASTENERS SPACING AND NUMBERS, GENERAL WORKMANSHIP AND REPAIR IS CLASSIFIED AS MAJOR.

Part: REPAIR — UNKNOWN (FUSELAGE) · airframe 54,698 hrs · 45,072 cycles

FOUND PREVIOUSLY REPAIR INSTALLED AT STA 420, STR 8-9L WAS ACCOMPLISHED IAW SRM 53-30-3 FIG 1, BASED ON AN EXTERNAL VISUAL EVALUATION CONSISTS OF LOCATION, SHAPE, SIZE, MATERIAL TYPE AND THICKNESS, FASTENER NUMBERS AND SPACING, GENERAL WORKMANSHIP AND REPAIR IS CLASSIFIED AS MAJOR.

Part: REPAIR — UNKNOWN (KRUEGER FLAP) · airframe 54,698 hrs · 45,072 cycles

FOUND PREVIOUSLY REPAIR INSTALLED AT NR 3 KRUGER FLAP WAS ACCOMPLISHED IAW SRM 57- 50-3, FIG 3 BASED ON AN EXTERNAL VISUAL EVALUATION CONSISTS OF LOCATION, TYPE, SIZE, SHAPE, MATERIAL THICKNESS AND TYPE, FASTENER NUMBER AND SPACING, GENERAL WORKMANSHIP, REPAIR IS CLASSIFIED AS MAJOR.

Part: REPAIR — UNKNOWN (KRUEGER FLAP) · airframe 54,698 hrs · 45,072 cycles

FOUND PREVIOUSLY REPAIR INSTALLED AT NR 2 KRUGER FLAP WAS ACCOMPLISHED IAW SRM 57- 50-3, FIG. 3, BASED ON AN EXTERNAL VISUAL EVALUATION CONSISTS OF LOCATION, TYPE, SHAPE, SIZE, MATERIAL THICKNESS AND TYPE, FASTENER NUMBER AND SPACING, GENERAL WORKMANSHIP, REPAIR IS CLASSIFIED AS MAJOR.

Part: REPAIR — UNKNOWN (FUSELAGE) · airframe 54,698 hrs · 45,072 cycles

FOUND PREVIOUSLY REPAIR INSTALLED AT STA. 227, STR20L WAS ACCOMPLISHED WITH SRM 53-30-3 FIG. 13, BASED ON AN EXTERNAL EVALUATION CONSISTS OF LOCATION, TYPE, SIZE, TYPE OF MATERIAL AND THICKNESS, FASTENER SPACING AND NUMBERS, GENERAL WORKMANSHIP AND REPAIR IS CLASSIFIED AS MAJOR.

Part: REPAIR — UNKNOWN (KRUEGER FLAP) · airframe 54,698 hrs · 45,072 cycles

FOUND PREVIOUSLY REPAIR INSTALLED AT NR 4 KRUGER FLAP WAS ACCOMPLISHED IAW SRM 57- 50-3, FIG 3 BASED ON AN EXTERNAL VISUAL EVALUATION CONSISTS OF LOCATION, SIZE, SHAPE, MATERIAL THICKNESS AND TYPE, FASTENER NUMBER AND SPACING, GENERAL WORKMANSHIP, REPAIR IS CLASSIFIED AS MAJOR.

Part: REPAIR — UNKNOWN (FUSELAGE) · airframe 54,698 hrs · 45,072 cycles

FOUND EXISTING REPAIR AT STA 710, STR 26L WAS ACCOMPLISHED IAW ISSUED EA 7-5330-70412, BASED ON AN EXTERNAL VISUAL EVALUATION CONSISTS WITH LOCATION, SHAPE, TYPE OF MATERIAL AND THICKNESS, FASTENERS SPACING AND NUMBERS, GENERAL WORKMANSHIP, REPAIR CLASSIFIED AS MAJOR.

Part: REPAIR — UNKNOWN (FUSELAGE) · airframe 54,698 hrs · 45,072 cycles

FOUND PREVIOUSLY REPAIR INSTALLED AT STA. 312, STR 13L WAS ACCOMPLISHED IAW EO 7-5330-7-2345, BASED ON AN EXTERNAL EVAULATION CONSISTS OF LOCATION, TYPE, SHAPE, SIZE, MATERIAL TYPE AND THICKNESS, FASTENER NUMBERS AND SPACING, GENERAL WORKMANSHIP, REPAIR IS CLASSIFIED AS MAJOR.

Part: REPAIR — UNKNOWN (FUSELAGE) · airframe 54,698 hrs · 45,072 cycles

FOUND PREVIOUSLY REPAIR INSTALLED AT STA. 344, STR 7L WAS ACCOMPLISHED IAW EO 7-5340-7-5002 PT1, BASED ON AN EXTERNAL EVAULATION CONSISTS OF LOCATION, SHAPE, SIZE, TYPE, MATERIAL THICKNESS AND TYPE, FASTENER NUMBERS AND SPACING, GENERAL WORKMANSHIP, REPAIR IS CLASSIFIED AS MAJOR.

Part: REPAIR — UNKNOWN (FUSELAGE) · airframe 54,698 hrs · 45,072 cycles

FOUND PREVIOUSLY REPAIR INSTALLED AT STA. 312, STR 13L WAS ACCOMPLISHED IAW EO 7-5330-7-2345, BASED ON AN EXTERNAL EVAULATION CONSISTS OF LOCATION, TYPE, SHAPE, SIZE, MATERIAL TYPE AND THICKNESS, FASTENER NUMBERS AND SPACING, GENERAL WORKMANSHIP, REPAIR IS CLASSIFIED AS MAJOR.

Part: REPAIR — UNKNOWN (FUSELAGE) · airframe 54,698 hrs · 45,072 cycles

FOUND PREVIOUSLY REPAIR INSTALLED AT STA. 312, STR 13L WAS ACCOMPLISHED IAW EO 7-5330-7-2345, BASED ON AN EXTERNAL EVAULATION CONSISTS OF LOCATION, TYPE, SHAPE, SIZE, MATERIAL TYPE AND THICKNESS, FASTENER NUMBERS AND SPACING, GENERAL WORKMANSHIP, REPAIR IS CLASSIFIED AS MAJOR.

Part: REPAIR — UNKNOWN (KRUEGER FLAP) · airframe 54,698 hrs · 45,072 cycles

FOUND PREVIOUSLY REPAIR INSTALLED AT NR 1 KRUGER FLAP WAS ACCOMPLISHED IAW SRM 57-50-3 FIG 11, BASED ON AN EXTERNAL VISUAL EVALUATION CONSISTS OF LOCATION, SIZE, SHAPE, MATERIAL THICKNESS AND TYPE, FASTENERS NUMBER AND SPACING, GENERAL WORKMANSHIP, REPAIR IS CLASSIFIED AS MAJOR.

Part: REPAIR — UNKNOWN (FUSELAEG) · airframe 54,698 hrs · 45,072 cycles

FOUND PREVIOUSLY REPAIR INSTALLED AT ST.312, STR.9L WAS ACCOMPLISHED WITH ISSUED EO 7-5330-7-2345, BASED ON AN EXTERNAL EVAULATION CONSISTS OF LOCATION, SHAPE, SIZE, TYPE OF MATERIAL AND THICKNESS, FASTENER SPACING AND NUMBERS, GENERAL WORKMANSHIP, REPAIR IS CLASSIFIED AS MAJOR.

Part: FIRE WARNING — MALFUNCTIONED (COCKPIT) · airframe 52,498 hrs · 43,386 cycles

AT 900FT ON CLIMBOUT, FIRE WARNING BELL SOUNDED AND ENGINE FIRE WARNING LIGHTS ON INSTRUMENT PANEL ILLUMINATED FOR 2 SECONDS. NO OTHER INDICATIONS AND ALL OTHER SYSTEMS OPERATED NORMALLY. PERFORMED ENGINE FIRE WARNING TEST. TESTED GOOD. COULD NOT DUPLICATE. OK FOR SERVICE.

Part: KEELBEAM — CORRODED (FUSELAGE) · corrosion level 2 · airframe 52,409 hrs · 43,305 cycles

LOWER WEB OF DELTA KEEL BEAM HAS CORROSION ON UPPER SURFACE AROUND SUPPORT STRUCTURE AND LOWER SURFACE AROUND FASTENER HEADS, BS 740-870. REMOVED AND REPLACED LOWER WEB OF DELTA KEEL BEAM BS 740 TO BS 870 RBL 5 TO LBL 5 PER SRM 51-20-1.

Part: STRINGER — CORRODED (FUSELAGE) · corrosion level 2 · airframe 52,409 hrs · 43,305 cycles

CORROSION (C53-113-01,1) IN STR 27L BS 720F + 13 STR 27L BS 720F + 13 FOUND TO BE OUT OF LIMITS. REMOVED STR 27L FROM 720E + 10 TO 720F + 18. FABRICATED REPAIR PARTS AND INSTALLED REPAIR PARTS, ALL WORK DONE IAW SRM 53-10-3. REINSTALLED GASPER AIR FAN, REMOVED FOR ACCESS AND FUNCTIONAL CHECKED. FUNCTIONAL CHECK GOOD. DONE IAW SRM 51-30-2, EXTRUSION BAC1498-131 LOT 504089 AND BAC 1498-147 LOT 504090.

Part: SHEAR TIE — CORRODED (FUSELAGE) · corrosion level 2 · airframe 52,409 hrs · 43,305 cycles

CORROSION (C53-113-01(17) SHEAR TIE BS 560 BETWEEN STR 26-27L. CORROSION ON SHEAR TIE IN A .75 X .75 INCH AREA FOUND TO BE OUT OF LIMITS. REMOVED AND REPLACED SHEAR TIE IAW SRM 53-10-1, 51-30-2, 51-10-2.

Part: SHEAR TIE — CORRODED (FUSELAGE) · corrosion level 2 · airframe 52,409 hrs · 43,305 cycles

CORROSION (C53-113-01,2) ON SHEAR TIE BS 950B, LBL 8-10, WL 140. REMOVED CORROSION ON SHEAR TIE BS 950B LBL 8-10 WL 140 AREA .65 X 5.00 X .013 INCH DEEP FROM ORIGINAL .071 FOUND OUT OF LIMITS PER SRM 53-10-1. REPAIRED SHEAR TIE PER SRM 53-10-4.

Part: SKIN — CRACKED (FUSELAGE) · airframe 52,409 hrs · 43,305 cycles

EXT SKIN IS CRACKED AND BULGED OUTWARD AT BS 700, STR 27 LT. REPAIRED DAMAGED SECTION OF SKIN BS 688 TO BS 714 STR 26 LT PER SRM 53-30-3 FIG 5 AND FED EX EA 7-5330-70412. REMOVED AND REPLACED SHEAR TIE PER SRM 51-20-1, 51-10-2.

Part: WARNING LIGHT — ILLUMINATED (ENG FIRE DETECT) · airframe 52,305 hrs · 43,225 cycles

ON CLIMBOUT OF HARLINGEN ,THE FIRE BELL AND GLARESHIELD LIGHT CAME ON INTERMTTENTLY. NO OTHER INDICATION (MOMENTARY/ INSTANTANEOUS THEN OUT). PERFORM ENGINES FIRE TEST NORMAL, NO DEFECT NOTED. CAN'T DUPLICATE PROBLEM. NO HISTORY. OK FOR SERVICE.

Part: TRANSMITTER — FAULTY (NR 1 ENGINE)

NR 1 ENG OIL PRESS GAUGE IND 20 PSI PRECAUTIONARY SHUTDOWN. REMOVED AND REPLACED NR 1 OIL PRESS TRANSMITTER PER MM 79-33-001-2. OPS & LEAK CHECK GOOD.

Part: SEQUENCE VALVE — CORRODED (LEFT WING)

01-327 AFT GEAR IN UP POSITION L/G DOOR LIGHT REMAIN ON. R/R NR 1 & 2 ENGINE DRIVEN HYD PUMPS PER MM 29-11-000-2. & LG LOCK OPERATING SEQ VALVE.

Part: STRINGER — CRACKED (RT WING)

RT WING VENT STR 13 AT WS 686.50 IS CRACKED AT RIB ATTACH POINT. *S/D* REMOVED AND REPLACED PER IAW FEDEX EA 7-5710-56217.

Part: STRINGER — CRACKED (RT WING)

RT WING 2 STRINGER NR 10, AT WS 686.5 IS CRACKED AT RIB ATTACH POINT. *S/D* REMOVED AND REPLACED PER IAW BOEING SB 727-57A159 AND FEDEX EA 7-5710-56217.

Part: ANGLE — CRACKED (RT WING)

RT WING PIE SECTION I/B WEB SUPPORT ANGLE CRACKED AT LOWER END. *S/D* REMOVED, REPLACED AND FAB PER IAW SRM 51-30-2, 51-10-3, AND 51-30-5.

Part: SKIN — CORRODED (FUSELAGE)

FOUND CORROSION ON INNER SKIN AT LAP BS 720B + 10 INCHES, STR 26R, RBL 22. *S/D* REMOVED AND REPLACED PER IAW FEDEX SRM 53-30-3 FIG 6.

Part: SUPPORT — CORRODED (FUSELAGE)

NR 842 CORROSION ON WEB SUPPORT BS 572 - 580, RBL 54, WL 200. ** S/D ** R&R & FAB PER IAW FEDEX SRM 51-10-6, 51-10-2, 51-30-2, AND 51-30-5 BAC SPEC 5300, AND FEDEX DRWG 65-59896.

Part: FRAME — DAMAGED (FUSELAGE)

NR 397 DOUBLE HOLE IN FRAME AT BS 870 JUST O/B OF STRINGER 3R. ** S/D ** R&R PER IAW FEDEX EA 7-5310-56211.

Part: FLOORBEAM — CORRODED (FUSELAGE)

CORROSION ON FASTENER HOLE ON FLOORBEAM BS 1050, LBL 54, WL 208. ** S/D ** R&R PER IAW EA 7-5310-56207, EO 00-5618 AND FEDEX SRM 53-10-18 FIG 3.

Part: FRAME — CORRODED (FUSELAGE)

CORROSION ON AFT FACE OF SHEAR TIE BS 680 BETWEEN STR 25 AND 26R. *S/D* REMOVED AND REPLACED PER IAW FEDEX SRM 53-10-4, 51-30-2.

Part: FLOORBEAM — DAMAGED (FUSELAGE)

FOUND PREVIOUSLY DOUBLE DRILLED HOLE AT BS 480 BL0, WL 208 FLOORBEAM UPPER CHORD FLANGE, AFT SIDE. ** S/D ** R&R PER IAW FEDEX SRM 53-10-8 FIG 3 AND FEDEX EA 7-5310-52494.

Part: FLOORBEAM — CORRODED (FUSELAGE)

NR 459 CORROSION ON FLOORBEAM BS 560, RBL 10, RBL 14, RBL 15, WL 208. ** S/D ** R&R PER IAW FEDEX SRM 53-10-1, 53-10-8 FIG 3 AND FEDEX EA 7-5310-52495.

Part: FLOORBEAM — MISDRILLED (FUSLEAGE)

WHILE WORKING CARD NR 458 SOUND PREVIOUSLY DOUBLE DRILL HOLE AT BS 500, WL 208 FLOORBEAM UPPER CHORD FLANGE FWD SIDE. *S/D* REMOVED AND REPLACED PER FEDEX EO 00-5622, IAW FEDEX SRM 53-10-8 FIG 3 AND FEDEX EA 7-5310-52496.

Part: STIFFENER — CORRODED (FUSELAGE)

CORROSION ON WEB AT VERTICAL BEAM AT BS 1177, BL 0, WL 152. *S/D* REMOVED AND REPLACED PER IAW FEDEX SRM 51-40-04 FIG 1. BLENDED AREA ON AFT SIDE OF 118L BULKHEAD PER FEDEX EA 7-5310-56239.

Part: FLOORBEAM — CORRODED (FUSELAGE)

CORROSION ON FLOORBEAM AT BS 720D, BL0 TO LBL 25 AND BL0 TO RBL 25 AROUND FASTENERS, WL 208. ** S/D ** R&R & FAB PER IAW FEDEX SRM 53-10-8 FIG 8.

Part: FLOORBEAM — CORRODED (FUSELAGE)

CORROSION (SPEC C53-111-01,3) ON FLOORBEAM LOWER FLANGE BS 1070, LBL 8 TO LBL 23, WL 201. *S/D* REMOVED AND REPLACED PER EA 00-5607 AND FEDEX EA 7-5310-53899.

Part: FLOORBEAM — CORRODED (BS 1130)

NR 846, CORROSION ON LOWER CHORD OF BS 1130 FLOORBEAM BL0- RBL 44, WL 201. ** S/D ** R&R PER IAW FEDEX EA 7-5310-52497.

Part: FLOORBEAM — CORRODED (FUSELAGE)

CORROSION (SPEC C53-111-01(3) ON FLOORBEAM LOWER FLANGE BS 1070, LBL 8 TO LBL 23, WL 201. REMOVED AND REPLACED PER EA 00-5607 AND FEDEX EA 7-5310-53899.

Part: DETECTOR — CHAFED (LOWER FUSELAGE)

LWR AFT BODY OVERHEAT CAUTION LIGHT ILLUM WITH NR 2 ENG AND 3 BLDS OPEN AND BOTH PACKS ON. RAN ALL 3 ENG PER JET RUN HDBK FOR 5 MIN, BLDS ON AND NO LEAK FOUND. FOUND LWR AFT LOOP CHAFING. REPOSITION LWR LOOP, OPS CHECK NORMAL PER B727-200 JET RUN HDBK.

Part: BEAM — CRACKED (BS 760)

STA-PAE - WHILE WORKING NR 0490, FOUND LONGITUDINAL BEAM UPPER HORIZONTAL FLANGE TO BE CRACKED AT BS 760, RBL 26, WL 208. REMOVED AND REPLACED LONGITUDINAL BEAM UPPER HORIZONTAL FLANGE AT BS 760 TO BS 850, RBL 26, WL 208 PER BOEING DRAWING 65-16279 AND FED-EX SRM 51-30-2.

Part: FRAME — MISDRILLED (BS 783.95)

WHEN WORKING 7-5310-7-3367A1 PT 4, FOUND PILOT HOLE ON EDGE OF 3RD ABOVE THE FLOOR BS 783.95 RT WL 208. PILOT HOLES ARE IN FRAME ONLY. REPAIRED DAMAGED FRAME IAW FEDEX EA 7-5310-26784.

Part: FRAME — MISDRILLED (BS 783)

WHILE WORKING EO 7-5310-7-3367A1 PT9, FOUND FIVE EXISTING HOLES IN 783 FRAME WHEN DRILLED IN NEW REPAIR WOULD FALL OUT IN RADIUS OF REPAIR ON 783 FRAME RT WL 200 TO 201, 207 AND 214 TO 216. INSTALLED FASTENERS IAW FEDEX EA 7-5310-26784.

Part: FRAME — MISDRILLED (BS 760)

WHEN WORKING 7-5310-7-3367 REV A1 PART 1, FOUND PILOT HOLES ON EDGE OF 3RD AND 4TH EXISTING FASTENER HOLES ABOVE THE FLOOR AT BS 760 LT WL 208. PILOT HOLES ARE IN FRAME ONLY. REPAIRED DAMAGED FRAME IAW FEDEX 7-5310-26784.

Part: FRAME — DENTED (BS 560)

DENT IN FRAME AT BS 560, LBL 38, WL 162. REPAIRED DENT IN FRAME IAW FEDEX SRM 51-40-3. C/A ADDITION.

Part: STRINGER — WORN (VERT STAB)

VERTICAL FIN, BAY NR 9 FIN STA 180.6, STR 7R, WORN FASTENER HOLE AT THE RIB CHORD AND STR. REPAIRED WORN RIB CHORD AND STR PER FEDEX SRM 55-30-4, FIG 1 AND FEDEX EA 7-5510-26736. C/A ADDITION.

Part: STRINGER — CORRODED (BS 1133-1139)

CORROSION (C53-224-04) ON STR 6R, BS 1133 AND BS 1139. REMOVED DAMAGED AREA AND REPAIRED STR IAW FEDEX EA 7-5310-26724.

Part: BEAM — CORROSION (BS 930)

CORROSION AT BS 930 BEAM LOWER CHORD LBL 46-LBL 52, WL 201. REMOVED CORROSION AT BS 930 LOWER CHORD, LBL 46-LBL 52, WL 201. AREA WITHIN LIMITS PER BAC DRAWING 65-19872-3. C/A ADDITION.

Part: STRINGER — CORRODED (BS 600-740)

CORROSION (C53-224-01) ON STR 5R, BS 600-740. REPAIRED OUT OF LIMITS AREA IAW FEDEX EA 7-5310-26724A. C/A ADDITION.

Part: GUSSET — CRACKED (BS 825.95)

GUSSET AT FRAME BS 825.95 IS CRACKED, RBL 65, WL 198. REPAIR ACCOMPLISHED IAW FEDEX EO 7-5310-7-3367A1, PART 6.

Part: FRAME — CORROSION (BS 219.8)

CORROSION (C53-100-01) ON FRAME WEB BS 219.8, LBL 19-32, RBL 16-24, WL 165. CORROSION FOUND TO BE OUT OF LIMITS PER FEDEX 53-10-1. REMOVED WEB AT BS 219.8, TRIM LBL - RBL 25, FABRICATED AND INSTALLED NEW WEB IAW FEDEX SRM 51-40-2.

Part: BLKHD SKIN — DENTED (BS 1342)

WHILE WORKING 7-5310-7-2301G1, FOUND DENT IN 1342 BULKHEAD SKIN APPROX WL 258 LT. REPAIRED DENT AT BS 1342 BULKHEAD, WL 258 LT. ALL WORK DONE PER FEDEX SRM 54-30-03 AND FEDEX EA 7-5310-26290.

Part: FLOOR BEAM — CORRODED (BS 344)

CORROSION (C53-229-01(1) FLOOR BEAM STA 344, LBL 3-58, WL 208.1, UPPER SURFACE OF TOP CHORD, RBL 0-42, WL 208, LOWER SURFACE OF TOP CHORD. TOP CHORD OF THE FLOOR BEAM AT BS 344 WAS FOUND TO BE OUT OF LIMITS IAW FEDEX SRM 53-10-1. REPAIRED FLOOR BEAM AT BS 344 IAW FEEX DRAWING SR 27-53-007.

Part: BEAM — CORRODED (BS 178)

CORROSION WAS FOUND WHILE WORKING NR 0685 ON FLANGE OF BEAM AT BS 178, WL 184-189, LBL 16.

Part: SKIN — GOUGE (BS 312)

AT BS 312, STR 24, WL 158, THERE IS ONE SHEARED FASTENER AND A GOUGE THROUGH SKIN AND FASTENER. BLENDED GOUGE AT BS 312, STR 24, WL 158, OUT OF LIMITS PER FEDEX SRM 53-30-1. REMOVED DAMAGED AREA, INSTALLED EXTERNAL REPAIR PATCH PER FEDEX SRM 53-30-3.

Part: FRAME — DENTED (BS 720)

DENT IN FRAME BS 720A, LBL 31-LBL 37, WL 160. REPAIRED DENT IN FRAME PER FEDEX SRM 51-40-3.

Part: FLOOR BEAM — CORRODED (BS 360)

CORROSION STA 360, FLOOR BEAM WL 208.1, LBL 3-8. REMOVED CORROSION FROM FLOOR BEAM STA 360, WL 208.1, LBL 3.5. AREA WAS 2.5 INCHES BY .25 INCH. ORIGINAL THICKNESS .125 INCH. REMOVED .022 INCH, FOUND TO BE OUT OF LIMITS. FABRICATED AND INSTALLED FILLER WASHER AND REPAIRED PER FEDEX EA 7-5310-26785.

Part: STRINGER — CORROSION (BS 541)

CORROSION ON STR 27R AT BS 541. REPAIRED STR PER FEDEX SRM 53-10-3.

Part: FRAME — GOUGED (BS 500)

GOUGE ON FRAME BS 500 BETWEEN STR 13-14R. REPAIRED DAMAGED FRAME AT BS 500, STR 13-14R PER FEDEX SRM 53-10-4.

Part: FRAME — DOUBLE HOLE (BS 460)

DOUBLE HOLE IN FRAME AT BS 460, STR 7R. REPAIRED DOUBLE HOLE IN FRAME AT BS 460, STR 7R PER FEDEX SRM 53-10-4, FIG 2.

Part: SKIN — CORROSION (BS 750-950)

WHILE WORKING CARD NR 0812, DISCOVERED CORROSION ON SKIN ALONG FAIRING SEAM, BS 950F-1010, STR 21L-20L. REPAIRED DAMAGED SKIN ALONG FAIRING SEAM AT BS 750D-950F PER FEDEX SRM 53-30-3, FIG 14, ALSO REMOVED CORROSION FROM BS 950F-BS 1010 AND FOUND TO BE WITHIN LIMITS PER FEDEX SRM 53-30-1.

Part: SKIN — CORRODED (BS 343-374)

CORROSION ON SKIN AT BS 343-374, STR 27L-R. REMOVED CORROSION AT BS 352-360. FOUND TO BE OUT OF LIMITS IAW FEDEX SRM 53-30-1. FABRICATED AND INSTALLED NEW SKIN PANEL AT BS 352-360, STR 27L-R PER FEDEX SRM 53-30-3.

Part: FLOOR BEAM — CORROSION (BS 1070)

CORROSION (C53-111-01(3)) ON BOTTOM CHORD OF FLOOR BEAM AT BS 1070, WL 200, RBL 51-LBL 42 AT NUTPLATE HOLES. REPAIRED OUT OF LIMITS FLOOR BEAM AT BS 1070, WL 200 FROM SKIN-TO-SKIN. REPAIRED AS PER FEDEX EA 7-5310-26725.

Part: STR SPLICE — CORRODED (BS 1015)

CORROSION (C53-224-04) ON STR 7 SPLICE LT, BS 1015. REMOVED OLD STR SPLICE, STR 7L BS 1015 AND INSTALLED NEW STR SPLICE.

Part: BEAM — CORRODED (BS 760-848)

CORROSION (C53-224-01) FOUND ON TOP CHORD OF LONGITUDINAL BEAM AT BS 760-848, LBL 25, WL 208.1 (OUT OF LIMITS PER FEDEX SRM 53-10-01). REMOVED AND REPLACED TOP CHORD OF LONGITUDINAL BEAM AT BS 760-848, LBL 25, WL 208.1 IAW FEDEX 53-10-01 DUE TO CORROSION OUT OF LIMTS.

Part: FRAME — DENTED (BS 1050)

DENT IN FRAME AT BS 1050 BETWEEN STR 25 AND 26 LBL 30 WL 150. REPAIRED DENT IN FRAME AT BS 1050 BETWEEN STR 25 TO 26 LBL 30 WL 150. ALL WORK DONE PER FEDEX SRM 51-40-03 FIG 1.

Part: FLOORBEAM — CORRODED (BS 720)

CORROSION AROUND FASTENER HOLES ON TOP CHORD OF FLOORBEAM AT BS 720A RBL 21 LBL 10, 16 AND 21 WL 208. TOP CHORD OF FLOORBEAM AT BS 720A LBL RBL 21 WL 208, FOUND TO BE OUT OF LIMITS IAW FEDEX SRM 53-10-1. REPAIRED FLOORBEAM AT BS 720A LBL 32 RBL 34 WL 208 IAW FEDEX SRM 53-10-8.

Part: FRAME — MIS DRILLED (BS 950)

INSTALLATION OF FASTENERS IN FRAME WEB BS 950F, WL 295, LBL 35 WITH IMPROPER SPACING AND FASTENERS DAMAGED. REPAIRED FRAME AT BS 950F, WL 295, LBL 35 PER FEDEX SRM 5-10-4. C/A ADDITION.

Part: BEAM — CORROSION (BS 950)

CORROSION (C53-224-01), AT BS 950 BEAM TOP CHORD LBL TO RBL 27 WL 208.1. REMOVED CORROSION AND REPAIRED OUT OF LIMIT AREAS PER EA 7-5310-26740 AND FEDEX SRM 53-10-01.

Part: FLOORBEAM — DOUBLE DRILLED (BS 580)

UPON REMOVAL OF SEAT TRACK NR0788, FOUND DOUBLE HOLES IN FLOORBEAM BS 580 BL 0 WL 208.5. REPAIRED DOUBLE HOLES IN FLOORBEAM BS 580 BL 0 WL 208.5 IAW FEDEX SRM 53-10-8 FIG 3.

Part: FRAME — GOUGED (BS 480)

GOUGE AT FRAME BS 480 BETWEEN STR 14 TO 13R. REPAIRED FRAME AT BS 480 BETWEEN STR 14 TO 13R PER FEDEX 727 SRM 53-10-4.

Part: FRAME — DENTED (BS 660)

DENT IN FRAME BS 660 RBL 31 TO 36 WL 157. REPAIRED DENT IN FRAME BS 660 RBL 30 TO 43 WL 157 PER FEDEX SRM 51-40-3.

Part: SKIN — DENTED (BS 1304)

WHILE WORKING NR0774, FOUND DENT IN THE FUSELAGE SKIN BS 1304 UNDER STR 17R. REMOVED DAMAGE, FABRICATED DOUBLER, SEALED AND INSTALLED DOUBLER PER FEDEX SRM 53-30-3 FIG 1.

Part: STRINGER — GOUGED (BS 965)

GOUGE IN STR 7 LT, BS 965 WL 285 LBL 58. REMOVED DAMAGED STR AND REPAIRED PER SRM 53-10-3.

Part: FLOORBEAM — CORROSION (BS 400)

CORROSION (C53-224-01, 1) FLOORBEAM STA 400 WL 208.1 LBL 8. FLOORBEAM WAS REPAIRED PER FEDEX B727 SRM 53-10-8 FIG 8 AT STA 400 WL 208.1 LBL 16 TO RBL 9.

Part: SPLICE — DAMAGED (BS 1130)

DRILL START ON FRAME SPLICE BS 1130 BETWEEN STR 6 TO 7R. REMOVED FRAME SPLICE AT BS 1130 BETWEEN STR 6 TO 7R AND INSTALLED NEW FRAME SPLICE.

Part: FRAME — CORRODED (BS 680)

CORROSION (C53-111-01), ON LOWER SIDE OF FLANGE ON BS 680 FRAME BETWEEN STR 23 TO 25L. REPAIRED LOWER SIDE OF FLANGE ON BS 680 FRAME BETWEEN STR 23 TO 25L, DUE TO CORROSION BEING OUT OF LIMITS PER FEDEX SRM 53-10-01.

Part: SKIN — CORRODED (BS 713)

CORROSION (C53-111-01), ON INTERIOR OF SKIN AT BS 713 BETWEEN STR 22 TO 23L. REMOVED CORROSION FROM INTERIOR OF SKIN AT BS 713 BETWEEN STR 22 TO 23L. REMOVED .014 FROM ORIGINAL MATERIAL THICKNESS, IN AN AREA OF 1.5 INCH BY 2.5 INCH BY .050 INCH. CORROSION WAS FOUND TO BE OUT OF LIMITS PER FEDEX SRM 53-30-1. REPAIRED SKIN PER FEDEX 727 SRM 53-30-3.

Part: FRAME — DAMAGED (BS 680)

MECHANICAL DAMAGE ON FRAME BS 680 RBL 38 WL 162. REPAIRED FRAME AT BS 680 RBL 38 WL 162 IAW FEDEX SRM 51-40-3, DUE TO MECHANICAL DAMAGE PER FEDEX SRM 53-10-1.

Part: SKIN — LIGHTNING STRIKE (BS 680)

LIGHTNING STRIKE AT BS 680 RBL 5 WL 148. DUE TO BULGE IN SKIN PATCH AT STA 683 RBL 20 WL 150, THE ORIGINAL SKIN PATCH WAS REPLACED AND ALL WORK WAS DONE IAW FEDEX 727 SRM 53-30-3.

Part: FRAME — DENTED (BS 660)

DENT IN FRAME BS 660 LBL 34 WL 160. REPAIRED DAMAGED FRAME AT BS 660 LBL 34 WL 160 IAW FEDEX B727 SRM 51-40-3.

Part: FRAME — DENTED (BS 1030)

DENT IN FRAME AT BS 1030 BETWEEN STR 25 AND 26 LBL 30 WL 150. REPAIRED DENT IN FRAME AT BS 1030 BETWEEN STR 25 AND 26 LBL 30 WL 150 PER FEDEX SRM 51-40-3.

Part: WEB — CORRODED (BS 219.8)

WHILE WORKING NRO 676, FOUND CORROSION ON AFT SIDE OF WEB STATION 219.8 W/L 214 TO 222, LBL 44. UPON REMOVING CORROSION AFT SIDE OF WEB STATION 219.8 W/L 214 TO 222, LBL 44, FOUND CRACK. REPAIRED WEB IAW FEDEX SRM 51-40-2. CORROSION WAS FOUND TO BE WITHIN LIMITS PER FEDEX SRM 53-10-1.

Part: FRAME — DENTED (BS 520)

DENT IN FRAME AT BS 520, LBL 32, RBL 46, WL 159 AND 168. REPAIRED DENT IN FRAME AT BS 520, LBL 32, LBL 46, WL 159-168 PER FEDEX SRM 51-40-3.

Part: FLOOR BEAM — CORRODED (BS 328)

CORROSION (C53-224-01(1) FLOOR BEAM STA 328, WL 208.1, LBL 20-LBL 3.

Part: FRAME — DOUBLE HOLE (BS 420)

DOUBLE HOLE IN FRAME AT BS 420, STR 4R. REPAIRED DOUBLE HOLE IN FRAME AT BS 420, STR 4R IAW FEDEX SRM 53-10-4.

Part: FRAME — DENTED (BS 720)

DENT IN FRAME BS 720, LBL 31-37, WL 160. REPAIRED FRAME AT BS 720, LBL 31-37, WL 160 IAW FEDEX SRM 51-40-3.

Part: FRAME — DENTED (BS 520)

DENT IN FRAME AT BS 520, RBL 38-50, WL 172-164. REMOVED DAMAGES AT BS 520, RBL 38-50, WL 172-164. FABRICATED PART, ALODINED, AND PRIMED, AND INSTALLED ON ABOVE AREA, AS PER FEDEX SRM 51-40-3.

Part: SKIN — CRACKED (LT ELEVATOR)

THE LOWER SURFACE OF THE LT ELEVATOR AT ELEVATOR STA 138, 24 INCHES FORWARD OF T/E HAS A PUNCTURE HOLE THAT IS CRACKED. FABRICATED REPAIR PART AND INSTALLED IT ON THE LOWER SURFACE OF THE LT ELEVATOR AT ELEVATOR STA 138, 24 INCHES FORWARD OF THE T/E IAW FEDEX SRM 53-10-3.

Part: STRINGER — CORRODED (BS 1042-1048)

CORROSION (C53-111-01-, 3), ON STR 20L AT BS 1042 TO 1048. REMOVED CORROSION ON STR 20L AT BS 1042 TO 1048. FOUND TO BE OUT OF LIMITS PER FEDEX SRM 53-10-1. REPAIRED STR 20L PER FEDEX SRM 53-10-3.

Part: FRAME — DOUBLE DRILLED (BS 1010)

DOUBLE HOLE IN FRAME WEB BS 1010, WL 295, LBL 33. REMOVED DAMAGED AREA, INSTALLED REPAIR IAW FEDEX SRM 53-10-4. C/A ADDITION.

Part: FLOORBEAM — CORRODED (BS 720)

CORROSION AROUND FASTENER HOLES ON TOP CHORD OF FLOORBEAM AT BS 720A RBL 21 LBL 10, 16 AND 21 WL 208.

Part: FLOORBEAM — CORRODED (BS 540)

CORROSION AROUND FASTENER HOLE ON TOP CHORD OF FLOORBEAM AT BS 540 LBL 10.5 WL 208. REMOVED CORROSION AROUND FASTENER HOLE ON TOP CHORD OF FLOORBEAM AT BS 540 LBL 10.5 WL 208. DAMAGE WAS FOUND TO BE BEYOND LIMITS PER FEDEX SRM 53-10-1. REPAIRED DAMAGED AREA PER FEDEX SRM 53-10-8.

Part: FLOOR BEAM — CORRODED (BS 950)

CORROSION AROUND FASTENER HOLES ON BS 950F, FLOOR UPPER CHORD, RBL 10-RBL 21, WL 208. REPAIRED BS 950F FLOOR BEAM AT RBL 10, WL 208 IAW FEDEX EA 7-5310-26291. C/A ADDITION.

Part: WEB — CORRODED (BS 219.8)

WHILE WORKING NR0676, FOUND CORROSION ON AFT SIDE OF WEB STA 219.8 WL 214 TO 222 LBL 44.

Part: STR CLIP — CRACKED (BS 600)

CRACKED STR CLIP AT BS 600 STR 4R. REMOVED AND REPLACED CRACKED STR CLIP AT BS 600 4R IAW FEDEX SRM 53-10-4.

Part: FRAME — DENTED (BS 500)

DENT IN TOP OF FRAME AT BS 500, LBL 32, WL 158. REPAIRED FRAME AS PER FEDEX SRM 51-40-3 AND 53-10-2 AT BS 500, LBL 32, WL 158.

Part: FLOORBEAM — CORRODED (BS 950)

CORROSION (C53-224-01), ON FLOORBEAM UPPER CHORD AT BS 950D LBL 20 RBL 20 WL 208.1. REPLACED UPPER CHORD FROM BS 950D FLOORBEAM RBL 20 LBL 15 WL 208.1, WORK DONE IAW FEDEX SRM 53-10-8 FIG 3.

Part: SKIN — DENTED (BS 230)

DENT IN SKIN AT BS 230 BETWEEN STR 24-25L. MEASURED DEPTH OF DENT AT .7 INCH BY .035 INCH FOUND TO BE OUT OF LIMITS. REPAIRED DENT PER FEDEX SRM 53-30-3, FIG 13, PG 74-74D. DENT FOUND OUT OF LIMITS PER FEDEX SRM 53-30-1.

Part: FAILSAFE — CORRODED (BS 1030)

CORROSION ON FAILSAFE AT BS 1030, LBL 65, WL 189. REPAIRED FAILSAFE AT BS 1030, LBL 65, WL 189 IAW FEDEX SRM 51-40-4.

Part: BEAM — CORRODED (BS 750)

CORROSION AT BS 750 BEAM UPPER CHORD FROM LBL 27 RBL 27 WL 208.1.

Part: SHEAR TIE — CORRODED (BS 1010)

CORROSION (C53-224-04) ON SHEAR TIE BS 1010, STR 7L. REMOVED CORROSION FROM SHEAR TIE FOUND TO BE OUT OF LIMITS IAW FEDEX SRM 53-10-1. FABRICATED AND INSTALLED NEW SHEAR TIE AT BS 1010, STR 7L.

Part: STRINGER — CORRODED (BS 600-740)

CORROSION (C53-224-01), ON STRINGER NR 5 RT AT BS 600 TO 740.

Part: STRINGER — CORRODED (BS 1042-1048)

CORROSION (C53-111-01-3), ON STRINGER AT BS 1042 TO 1048.

Part: STRINGER — CORRODED (BS 1133/1139)

CORROSION (C53-224-04), ON STRINGER AT BS 1133 AND 1139 STR 6 RT.

Part: STRINGER — CORRODED (BS 1126)

CORROSION (C53-224-04), ON STR 7R BS 1126. BLENDED CORROSION AND FOUND TO BE OUT OF LIMITS IAW FEDEX SRM 53-10-1. REPAIRED STRINGER IAW FEDEX SRM 53-10-3 AND EA 7-5310-26724.

Part: FLOOR BEAM — CORRODED (BS 1130)

CORROSION (C53-111-01(3)) ON BOTTOM CHORD OF FLOOR BEAM BS 1130, LBL 43-RBL 51, WL 200 AT NUTPLATE HOLES. REMOVED CORROSION ON BOTTOM CHORD OF FLOOR BEAM BS 1130, LBL 43-RBL 51. CORROSION FOUND TO BE OUT OF LIMITS AS PER FEDEX SRM 53-10-1. REPAIRED BOTTOM CHORD OF FLOOR BEAM BS 1130, LBL 43-RBL 51 AS PER FEDEX SRM 53-10-8 FIG 2.

Part: FLOORBEAM — CORRODED (BS 1148)

CORROSION (C53-111-01, 2), ON BOTTOM CHORD OF FLOORBEAM BS 1148 LBL 21 RBL 12 WL 200 AT NUTPLATE HOLES. REPAIRED BOTTOM CHORD OF FLOORBEAM BS 1148 LBL 21 RBL 12 WL 200 AT NUTPLATE HOLES PER FEDEX SRM 53-10-1 AND 53-10-8 THAT WAS OUT OF LIMITS.

Part: FLOORBEAM — CORRODED (BS 1070)

CORROSION (C53-111-01-3), ON BOTTOM CHORD OF FLOORBEAM AT BS 1070 WL 200 RBL 51 LBL 42 AT NUTPLATE HOLES.

Part: GUSSET — CRACKED (BS 825.95)

GUSSET AT FRAME BS 825.95 IS CRACKED RBL 65, WL 198.

Part: CHORD — CORRODED (BS 430)

CORROSION AT BS 430 BEAM LOWER CHORD LBL 46 LBL 52 WL 801.

Part: FLAP — CORROSION (NR 5 LE FLAP)

DUE TO EXCESSIVE CORROSION (C57-562-01-2) NR 5 K-FLAP REQUIRES REPLACEMENT. REMOVED AND REPLACED NR 5 K-FLAP IAW FEDEX MM 27-81-1. C/A ADDITION.

Part: COUPLING — LEAKING (NR 1 BLEED)

YMX: AFTER ABOUT 1 HR INTO FLT, LWR AFT BODY OVERHEAT LIGHT CAME ON PERFORMED ABNORMAL CHECKLIST, LIGHT WENT OUT. PROCEDURE STATED LEAK IS BETWEEN BLEED VALVE AND PACK VALVE. (PROBLEM NR 1 BLEED). REMOVED AND REPLACED COUPLING ASSY (ON LINE GOING TO PURGE VALVE) ON LT AIR CLEANER DUE TO LEAKING. LEAK CHECK C/O AND SYSTEM FOUND SERVICEABLE.

Part: PRESS CONTROLLER — FAILED (E/E COMPT)

LOSS OF PRESSURIZATION AT FL 310. UNABLE TO MAINTAIN CABIN PRESS IN AUTO, MANUAL, OR STANDBY MODE. REMOVED AND REPLACED CABIN PRESS CONTROLLER PER MM 21-31-0. CABIN PRESSURE FUNCTION TEST NORMAL PER JRH 7-23.

Part: FIRE WARNING — ACTIVATED (ENGINE)

AFTER T/O FIREBELL RANG MOMENTARILY AND ONE RED LT FLASHED, WAS OVER BEFORE WE COULD DETERMINE SOURCE. TESTED ENG AND W/W FIRE WARNING. CKS NORMAL. NO HISTORY NOTED. SYSTEM OK FOR SERVICE.