N930CE

Part: FITTING — CRACKED (BS 351) · airframe 69,114 hrs · 45,705 cycles

FITTING AT BS 351 LONGERON 32L CRACKED. REPLACED THE DAMAGED FITTING IAW EA 25-2017-138

Part: POSITION SWITCH — STICKING (MLG DOOR) · airframe 68,606 hrs · 45,222 cycles

DURING GEAR RETRACTION, GEAR DOOR OPEN LIGHT AND GEAR RED UNSAFE LIGHTS FOR LEFT AND RIGHT MAIN GEAR ILLUMINATED WITH GEAR HANDLE IN UP POSITION.

Part: SKIN — CRACKED (FUSELAGE) · corrosion level 2

REPAIR OF CRACKS IN FUSELAGE SKIN FS 102.5 BELOW STRINGER R18. REPAIR CRACKS EXTENDING FROM RIVETS IN SKIN AT FS 102.5 STRUCTURAL REPAIR MANUAL 53-01 FIGURE 4 (SHEET 4).

Part: STRUCTURE — CRACKED (FUSELAGE) · corrosion level 2

REPAIR OF 4" CRACK IN FUSELAGE TAIL STA 1205 RT 3 O-CLOCK POSITION. MAJOR REPAIR OF CRACK PER SRM REFERENCE SRM 53-01 FIGURE 4.

Part: SUPPORT BRACKET — CRACKED (RT WING FLAP ACT) · airframe 68,258 hrs · 44,906 cycles

RIGHT FLAP I/B ACTUATOR SUPPORT BRACKET CRACKED.

Part: STRUT — LOW PRESSURE (NLG) · airframe 67,325 hrs · 44,004 cycles

AFTER TAKEOFF COULD NOT RETRACT GEAR, HANDLE WOULD NOT MOVE TO UP POSITION. THE CAUSE WAS THE NLG STRUT WAS LOW ON PRESS.

Part: SKIN — DAMAGED (FUSELAGE)

LIGHTNING STRIKE REPAIR FUSELAGE SKIN BETWEEN STATION 83.550 - 89.050, LONGERON 16R & 17R. MAJOR REPAIR, 3 EACH LIGHTNING STRIKE DAMAGE TO FUSELAGE SKIN.

Part: SKIN — DAMAGED (FUSELAGE)

LIGHTNING STRIKE REPAIR FUSELAGE SKIN BETWEEN STATION 101 - 110, LONGERON 17L & 18L. MAJOR REPAIR. TWO EACH LIGHTNING STRIKE DAMAGE TO FUSELAGE SKIN.

Part: FRAME — CORRODED (FUSELAGE)

FRAME REPAIR STA 180, L-28L TO L-28R. MAJOR REPAIR. FUSELAGE FRAME LOWER FLANGE CORRODED AT STATION 180 BTWN LONGERON 28 LEFT AND LONGERON 28 RIGHT.

Part: FRAME — CRACKED (FUSELAGE)

FRAME REPAIR, STATION 389, LONGERON 12R - 14R. MAJOR REPAIR. FUSELAGE FRAME INBD FLANGE CRACKED AT STATION 389 BETWEEN LONGERON 12R & 14R.

Part: MOUNT — CRACKED (RT SPOILER) · airframe 66,573 hrs · 43,286 cycles

RT INBD SPOILER CONTROL MOUNT BRACKET CRACKED ON REAR SPAR. INSTALLED A REPAIR TO MOUNT BRACKET IAW SRM 51-10-3A, 51-30-2,51-10-2, 51-10-4 AND 51-30-5.

Part: FITTING — CRACKED (BS 600) · airframe 66,573 hrs · 43,286 cycles

RIGHT WING TO FUSELAGE FITTING IS CRACKED AT BS 600-LONGERON 22R. R & R THE FITTING IAW SRM 51-30-5, PGS 12-14, 51-30-01,51-10-4.51-10-2 AND 57-31-4.

Part: FRAME — CORRODED (BS 180) · airframe 66,573 hrs · 43,286 cycles

E & E BAY BILGE AREA FLOOR FRAME HAS CORRISON FROM LONGERON 28L-28R STA 180. R & R SECTION OF FRAME, STA 180, LONGERON 28L-28R IAW SRM 53-03, FIG 5.

Part: SEAT TRACK — CORRODED (BS 160-996) · airframe 66,573 hrs · 43,286 cycles

LIGHT SURFACE CORROSION ON SEAT TRACK, FLOOR ATTACHMENT AREAS IN VARIOUS LOCATIONS IN PASSENGER CABIN, STA 160-996, RBL5435 TO LBL 54.5. REMOVED LIGHT CORROSION AND TREATED AREAS. INSTALLED SEAT TRACK REPAIR STA 408-484, RBL 33 IAW SRM 53-05, FIG 4F AND 51-10-3, PGS 12, 145 & 21.

Part: FRAME — CRACKED (BS 389) · airframe 66,573 hrs · 43,286 cycles

FRAME AT BS 389 BETWEEN LONGERONS 12 - 14R IS CRACKED. REPAIRED SECTION OF FRAME IAW SRM 53-03, FIG 4.

Part: CARGO TRACK — CORRODED (BS 427-513) · airframe 66,573 hrs · 43,286 cycles

FORWARD LOWER CARGO COMPARTMENT CARGO TRACK SUPPORT HAS CORROSION FROM BS 427-513, RBL 14. REMOVED CORROSION FROM AREA. TRACK SUPPORT CHANNEL AND UPPER SUPPORT FLANGE OF INTERCOSTAL WERE REPAIRED/REINFORCED IAW SRM 51-70-5, FIG 1.

Part: FITTING — CRACKED (BS 600) · airframe 66,573 hrs · 43,286 cycles

WING TO FUSELAGE FITTING CRACKED LT SIDE BS 600, LONGERON 22L. R & R THE FITTING IAW SRM 51-30-1, 51-10-02, 51-10-4, 5110-2 AND 57-31-4.

Part: ATTACH ANGLE — CRACKED (RT PYLON) · airframe 66,573 hrs · 43,286 cycles

RIGHT PLYON LOWER ATTACH ANGLE CRACKED AT 996. INSTALLED NEW SECTION OF RT PYLON LOWER ATTACH ANGLE IAW SRM 54-04, FIG 10.

Part: SKIN — DAMAGED (BS 434) · airframe 65,290 hrs · 42,018 cycles

AIRCRAFT WAS STRUCK BY LIGHTNING DURING CLIMB. NO ABNORMAL INDICATIONS AFTER STRIKE. COMPLIED WITH LIGHTNING STRIKE INSPECTION PROCEDURES, IAW EAC POLICIES AND PROCEDURES. TWO BURNED RIVETS WERE FOUND AT LOWER FUSELAGE BS 434 CENTERLINE, INCLUDING CIRCULAR BURN MARKS ON SKIN. REPAIRED DAMAGED SKIN IAW EAC EO 1363.

Part: FITTING — CRACKED (ZONE 800) · airframe 64,752 hrs · 41,470 cycles

LOWER FUSELAGE, AFT CARGO COMPARTMENT DOOR AT BEAM NR 3, FWD BEAM END CRACKED. REPLACED NR 3 DOOR BEAM END FITTING IAW S/B DC-9-52-189 ACOMPLISMENT INSTRUCTIONS, WORK INSTRUCTIONS CONDITION 3, REV 3, DATE FEB 21,2008 AND DWG 5934142, REV H, DATED 12-21-06.

Part: FITTING — CRACKED (ZONE 800) · airframe 64,752 hrs · 41,470 cycles

LOWER FUSELAGE, AFT CARGO COMPARTMENT DOOR AT BEAM NR 1, FWD BEAM END CRACKED. REPLACED DOOR BEAM FITTING IAW S/B DC-9-52-189 ACOMPLISMENT INSTRUCTIONS, WORK INSTRUCTIONS CONDITION 3, REV 3 DATE FEB 21,2008 AND DWG 5934142, REV H, DATED 12-21-06.

Part: FRAME — DAMAGED (ZONE 100) · airframe 64,752 hrs · 41,470 cycles

AFT CARGO COMPARTMENT BS 889 BETWEEN L27 AND 28L FRAME WITH AN ELONGATE HOLE. REPAIRED IAW SRM 53-03 PARA 1C, FIG 2A.

Part: SKIN — DENTED (ZONE 100) · airframe 64,752 hrs · 41,470 cycles

LOWER FUSELAGE BS 248.5 BETWEEN L19 AND 20L SKIN DENTED. REPAIRED SKIN IAW SRM 53-01, FIG 1.

Part: BULKHEAD — CORRODED (ZONE 100) · airframe 64,752 hrs · 41,470 cycles

LOWER FUSELAGE AFT CARGO COMPARTMENT AT BS 996 L23L AFT PRESSURE BULKHEAD WEB CORRODED. REPAIRED PRESSURE BULKHEAD WEB SECTION IAW SRM 53-03 PARA 17, FIG 23.

Part: FITTING — CRACKED (ZONE 800) · airframe 64,752 hrs · 41,470 cycles

LOWER FUSELAGE, AFT CARGO COMPARTMENT DOOR AT BEAM NR 5, AFT BEAM END CRACKED. REPLACED NR 5 DOOR BEAM END FITTING IAW S/B DC-9-52-189 ACOMPLISMENT INSTRUCTIONS, WORK INSTRUCTIONS CONDITION 3, REV 3, DATE FEB 21,2008 AND DWG 5934142, REV H, DATED 12-21-06.

Part: TEE FITTING — CRACKED (ZONE 200) · airframe 64,752 hrs · 41,470 cycles

UPPER FUSELAGE AFT PRESSURE BULKHEAD TEE BETWEEN L15 AND 17L, AT Z=14 AND Z=24 TEE CRACKED. REPLACED PRESSURE BULKHEAD TEE SECTION IAW S/B A53-232 ACCOMPLISHMENT INSTRUCTIONS OPTION II CONDITION 2, FIG 4, REV 2, DATE APRIL 28,95.

Part: SHEAR TIE — CRACKED (ZONE 100) · airframe 64,752 hrs · 41,470 cycles

UPPER FUSELAGE, CARGO CABIN, AT BS 945 BETWEEN L15 TO 16R FRAME SHEAR TIE CRACKED. REPLACED SHEAR TIE IAW SRM 51-01, PARA 2D.

Part: FITTING — CRACKED (ZONE 800) · airframe 64,752 hrs · 41,470 cycles

LOWER FUSELAGE, AFT CARGO COMPARTMENT DOOR AT BEAM NR 2, AFT BEAM END CRACKED. REPLACED NR 2 DOOR BEAM IAW S/B DC-952-189 ACOMPLISMENT INSTRUCTIONS, WORK INSTRUCTIONS CONDITION 3 REV 3 DATE FEB 21, AND DWG 5934142, REV H, DATED12-21-062008.

Part: FRAME — CRACKED (ZONE 100) · airframe 64,752 hrs · 41,470 cycles

CARGO CABIN AT BS 813, L17R, FRAME WEB WITH CRACK. REPAIRED CARGO CABIN FRAME SECTION BS 813 BETWEEN L16 AND 18R DUE TO CRACK IAW SRM 53-03, FIG 32, PARA 26.

Part: FITTING — CRACKED (ZONE 100) · airframe 64,752 hrs · 41,470 cycles

LOWER FUSELAGE FWD CARGO COMPARTMENT, BS 237, ON L24R, FRAME AREA AFT FITTING CRACKED. REPLACED, FRAME FITTING IAW SRM 51-01 PARA 2D.

Part: ACOUSTIC LINER — DELAMINATED (NR 1 ENGINE) · airframe 64,751 hrs · 41,470 cycles

ENGINE NR 1 NOSE COWL ACOUSTIC INNER BARREL INNER SKIN WITH DELAMINATION. THE MENTION DAMAGE WAS REPAIRED UNDER NRI A1B089 4-3 AND EO# COO-CMP9-54-035-13.

Part: FITTING — BROKEN (FUSELAGE) · airframe 64,751 hrs · 4 cycles

DURING THE STRUCTURAL INSPECTION WAS FOUND ON FWD CARGO COMPARMENT STA 237, LONG 24 LEFT FITTING CRACKED. THE MENTIONED FITTING WAS REPLACED PER SRM GUIDELINES.

Part: FITTING — BROKEN (FUSELAGE) · airframe 64,751 hrs · 41,470 cycles

DURING THE STRUCTURAL INSPECTION WAS FOUND ON FWD CARGO COMPARTMENT STA 256, LONG 24 LEFT FITTING CRACKED. THE MENTIONED FITTING WAS REPLACED PER SRM GUIDELINES UNDER WORK ORDER A1B089, SUBJOB: 1, ITEM 78.

Part: FITTING — CRACKED (FUSELAGE) · airframe 64,751 hrs · 41,470 cycles

DURING THE STRUCTURAL INSPECTION WAS FOUND ON FWD CARGO COMPARTMENT STA 237, LONG 24 RIGHT FITTING CRACKED. THE MENTIONED FITTING WAS REPLACED PER SRM GUIDELINES.

Part: FITTING — CRACKED (FUSELAGE) · airframe 64,751 hrs · 41,470 cycles

DURING THE STRUCTURAL INSPECTION WAS FOUND ON FWD CARGO COMPARTMENT STA 256, LONG 24 RIGHT FITTING CRACKED. THE MENTIONED FITTING WAS REPLACED PER SRM GUIDELINES.

Part: SKIN — CRACKED (ZONE 200) · airframe 64,752 hrs · 41,470 cycles

UPPER AFT FUSELAGE BS 1038 LONGERON 14 LT SIDE SKIN CRACKED. REPAIRED IAW SRM 53-04 FIG 18.

Part: FITTING — CRACKED (WING SPAR) · airframe 64,751 hrs · 41,470 cycles

DURING THE STRUCTURAL INSPECTION, "C1" SERVICE ON RT WING FRON SPAR SECTION AT XRS 204, FITTING CRACKED. THE FITTING WAS REPLACED IAW SRM GUIDELINES UNDER W/O A1B038, SUB JOB: 6, ITEM :3.

Part: SKIN — CRACKED (ZONE 200) · airframe 64,752 hrs · 41,470 cycles

UPPER AFT FUSELAGE BS 1038 L14R SKIN CRACKED. REPAIRED SKIN SECTION IAW SRM 53-04, FIG 18.

Part: ANGLE — CRACKED (ZONE 100) · airframe 64,752 hrs · 41,470 cycles

LOWER FUSELAGE AFT CARGO COMPARTMENT BS 889, BETWEEN LONGERON 28-29L, FRAME AREA TITANIUM ANGLE WITH CRACK. DAMAGED ANGLE WAS REPAIRED IAW THE EO COO-9-53-039-13.

Part: ANGLE — CRACKED (ZONE 100) · airframe 64,752 hrs · 41,470 cycles

LOWER FUSELAGE AFT CARGO COMPARTMENT, BS 869 BETWEEN LONGERON 28-30L FRAME AREA, TITANIUM ANGLE WITH CRACK. DAMAGED ANGLE WAS REPAIRED IAW EO COO-9-53-039-13.

Part: FRAME — CRACKED (ZONE 100) · airframe 64,752 hrs · 41,470 cycles

LOWER FUSELAGE FWD CARGO COMPARTMENT, BS 332, BETWEEN LONGERON 28R AND 28L, FRAME AREA, TITANIUM ANGLE WITH CRACK. DAMAGED ANGLE WAS REPAIRED IAW EO COO-9-53-039-13, UNDER THE W/O A1B089, SUBJOB 1, ITEM 91.

Part: ANGLE — CRACKED (ZONE 100) · airframe 64,752 hrs · 41,470 cycles

LOWER FUSELAGE FWD CARGO COMPARTMENT, BS 332 BETWEEN LONGERON 28R AND 28L FRAME AREA, STEEL ANGLE WITH CRACK. DAMAGED ANGLE WAS REPAIRED IAW THE EO COO-9-53-039-13, UNDER THE W/O: A1B089, SUBJOB: 1, ITEM: 91.

Part: ANGLE — CRACKED (ZONE 100) · airframe 64,752 hrs · 41,470 cycles

LOWER FUSELAGE FWD CARGO COMPARTMENT, STA Y:427, BETWEEN LONGERON 24-26L FRAME AREA, TITANIUM ANGLE WITH CRACK. DAMAGED ANGLE WAS REPAIRED IAW E/O COO-9-53-039-13 REQUIREMENTS.

Part: FRAME — GOUGED (BS 435) · airframe 63,637 hrs · 40,381 cycles

FWD CARGO DOOR FRAME WEB REPAIR AT FS 435, GOUGE APPROXIMATELY 2 INCHES ABOVE LONGERON L15 AT FS 435. REMOVE DAMAGE & FABRICATE FILLER FROM MATERIAL SAME AS PARENT 7075-T6 0.071INCHES. FABRICATE DOUBLER FROM 7075-T6 0.80 INCHES TO EXTEND A MINIMUM OF 6 FASTENERS PAST DAMAGE WITH CUT OUTS AROUND LIGHTNING HOLES. INSTALL USING HLT434 FASTENERS SAME DIAMETER AS ORIGINALS.