N747CE

Part: SKIN — CORRODED (AFT CARGO DOOR)

AFT CARGO DOOR SKIN REPAIR. TO REPAIR A CORRODED SKIN SEAM AT THE AFT EDGE OF THE MAIN CARGO DOOR AT F/STA 798. PERFORM REPAIRS AT AFT EDGE OF MAIN CARGO DOOR PER DC-6 A&B OVERHAUL MANUAL FIGURE 12-22.

Part: SKIN — CORRODED (BS 82 S1-2R)

UPPER FUSELAGE SKIN CORROSION @ F/STA 157. TO REPAIR CORRODED FUSELAGE SKIN AROUND THE GPS ANTENNA AT F/STA 82 BETWEEN STRINGER 1R & 2R. PERFORM REPAIR PER DC-6 A&B OHM FIGURE 12-22.

Part: SKIN — CORRODED (FWD CARGO DOOR)

FWD CARGO DOOR CORRODED STRUCTURE. TO REPAIR A CORRODED SKIN ON THE MAIN CABIN FORWARD CARGO DOOR AROUND THE DOOR LATCH ASSEMBLY (F/STA 122 APPROXIMATELY). PERFORM REPAIR PER STS EA 80-2021-124.

Part: SKIN — CORRODED (RT WING)

UPPER WING SKIN REMOVAL AND REPLACEMENT, BETWEEN CENTER AND AFT SPARS, BETWEEN W/STA 167R AND 193R. TO REMOVE AND REPLACE A CORRODED SKIN BETWEEN W/STA 167R AND 193R. REMOVE CORRODED SKIN BETWEEN EXISTING SPLICES AT W/STA 167R AND 193R. USING EXISTING SKIN AS A TEMPLATE, MANUFACTURE REPLACEMENT SKIN FROM 7075-T6 0.063". INSTALL A NEW SKIN FOLLOWING THE GUIDANCE OF T.O. 1C-118A-3-1 FIG 2-59 FOR FASTENER TYPE.

Part: SKIN — CRACKED (CENTER LEFT)

CRACKED WING SKIN AT W/STA 207L, STRINGER 20. TO REPAIR A CRACKED WING SKIN AT 4 FASTENER LOCATIONS AT W/STA 207L, STRINGER 20. CUT OUT DAMAGE AND REPAIR WING SKIN PER STS ENGINEERING AUTHORIZATION EA 74-2021-007.

Part: STRINGER — CRACKED (LT WING)

CRACKED WING STRINGER AT W/STA 242L, STRINGER 19. TO REPAIR A CRACKED WING STRINGER AT W/STA 242L, STRINGER 19. RREPAIR CRACKED STRINGER PER STS INSTRUCTIONS IN EA 69-2021-019.

Part: SKIN — DAMAGED (BS 736-743)

FUSELAGE SKIN DAMAGE AT F/STA 736 TO 743 BETWEEN STRINGERS 24 AND 25. TO REPAIR FUSELAGE SKIN DAMAGE CAUSED BY A FORKLIFT. CUT OUT DAMAGE AND PERFORM REPAIR, PER DC-6 A&B SRM FIGURE 12-21 FUSELAGE PLATING REPAIR.

Part: SPRING — BROKEN (HYD BYPASS) · airframe 38,359 hrs

HYDRAULIC BYPASS STUCK IN UP POSITION, UPON INSPECTIN FOUND HYDRAULIC BYPASS RETURN SPRING BROKEN.

Part: FLOORBEAM — CORRODED (BS 240)

CORROSION ON RBL 11.5 FLOOR BEAM AT F/STA 240. TO REINFORCE THE LOWER FLANGE OF THE RBL 11.5 FLOOR BEAM AT F/STA 240, AFTER CORROSION REMOVAL. THE CORROSION IS LOCATED ON THE BOTTOM SIDE OF THE LOWER FLANGE. CLEAN CORROSION AND INSTALL LOWER REINFORCING ANGLE ONLY PER DC-6 A&B OVERHAUL MANUAL FIGURE 12-12.

Part: DOUBLER — CORRODED (NR 3 NACELLE)

REMOVAL AND REPLACEMENT OF CORROSION DOUBLER OUTBOARD OF #3 NACELLE BETWEE CENTER AND AFT SPAR. TO REMOVE AND REPLACE A PREVIOUSLY INSTALLED "CORROSION DOUBLER" BETWEEN W/STA 176R AND 206R BETWEEN CENTER AND REAR SPAR. REMOVE EXISTING DOUBLER AND MANUFACTURE NEW DOUBLER EXTENDING TO W/STA 206R PER USAF SRM T.O. 1C-118A-3-1 FIGURE 2-63 AND DRAWING #1962-01.

Part: STRINGER — CHAFED (FRAME 36)

FUSELAGE STRINGER #14L REPAIR AT F/STA -36. TO REPAIR A CHAFFED HOLE IN STRINGER 14L. TRIM CHAFFED AREA AND REPAIR STRINGER PER DC-6 A&B OVERHAUL MANUAL FIGURE 12-2A.

Part: SKIN — CRACKED (RWS 96)

UPPER WING SKIN CRACKED AT W/STA 96R, STRINGER #3. TO REPAIR A SMALL CRACK AROUND A FUEL QUANTITY PROBE ACCESS HOLE AT W/STA 96R, STRINER 3. TRIM OUT CRACK AND REPAIR SKIN PER DC-6 A&B OVERHAUL MANUAL FIGURE 13-30.

Part: LANDING GEAR — MALFUNCTIONED · airframe 37,625 hrs

DIVERTED AFTER MULTIPLE GEAR DOWN ATTEMPTS WITH NO DOWN AND LOCKED INDICATION ON RIGHT MAIN. AT FAI THERE WAS NO DOWN AND LOCKED INDICATION ON RITGHT MAIN UNTIL 500" AGL DURING ILS APPROACH. , FO SAW GEAR DOWN BUT NO CLEAR DOWN AND LOCKED SIGHTING.

Part: PLATE — CORRODED (FUSELAGE)

CORRODED FLOOR PLATING IN FRONT OF THE MAIN CARGO DOOR BETWEEN F/STA 667 AND 794. TO REPAIR THE CORRODED CABIN FLOOR PLATING JUST INBOARD OF THE MAIN CARGO DOOR. CUT CORRODED SECTION OF FLOOR, 24" WIDE STARTING AT THE LT EDGE OF FLOOR PLATING BETWEEN F/STA 667 AND 794. MANUFACTURE NEW PLATING PER A&B OHM FIGURE 12-5.

Part: SKIN — CORRODED (BS 974) · airframe 36,781 hrs

FUSELAGE SKIN CORRODED AT BS 974, STRINGER 1R. REPAIRED IAW DRAWING 1809-01.

Part: FRAME — CRACKED (FUSELAGE)

CRACKED FUSELAGE FRAME AT FS 1071 STRINGER 14R. REPAIR A 1/4" CRACK IN A FUSELAGE FRAME. THE CRACK GOES FROM STRINGER 14R RELIEF RADIUS TO A RIVET HOLE. INSTALL REPAIR DOUBLER ON CRACKER FRAME AT FS 1071 PER DRAWING 1636-01 AND OVERHAUL MANUAL FIGURE 12-3A.

Part: BEARING — GALLED (LANDING GEAR) · airframe 34,972 hrs

DEPARTING AIRPORT, ACFT LOST NR 4 MLG WHEEL & TIRE ASSEMBLY. ACFT DIVERTED, DECLARED AN EMER HELD OVER TO BURN FUEL OFF FOR LANDING WEIGHT. LANDING WAS FULL STOP & UNEVENTFUL.

Part: DOUBLER — CRACKED (LT WING)

REPLACEMENT OF LANDING DOUBLER IAW SB 799. TWO CRACKS WERE FOUND AT LT WS 214 LOWER ON THE INBD LANDING DOUBLER REQUIRE THE REMOVAL & REPLACEMENT OF THE DOUBLER. NOTE SERVICE BULLETIN 799 ATTACHED TO THIS EO FOR SCOPE OF WORK & REPAIR DATA. NOTE REPLACEMENT DOUBLER IS IN SSID & PSE AREA BUT WILL NOT CHANGE ANY PARAMETERS DUE TO IT BEING A DIRECT REPLACEMENT.

Part: DOUBLER — CORRODED (LT WING)

CORRODED UPPER WING SKIN PROTECTION DOUBLER, LT WS 167.247 TO 191 FROM FRONT TO CTR SPAR. UPPER WING SKIN JUST OTBD OF THE NR 2 NACELLE, FROM FRONT TO CTR SPAR. REMOVE CORRODED DOUBLER & FABRICATE NEW PART FROM ORIGINAL MATERIAL, 2024 T3.071 ALUMINUM. PRIME NEW PART FOR CORROSION PREVENTION. APPLY SEALANT TO ALL FAYING SURFACES & INSTALL NEW DOUBLER, WET. USE FASTENERS OF THE SAME TYPE & DESIGN AS ORIGINALLY INSTALLED. APPLY FINAL PROTECTIVE FINISH COAT FOR CORROSION PREVENTION & CONTROL.

Part: HYDRAULIC LINE — LOOSE (HYDRAULIC SYS) · airframe 34,473 hrs

HYDRAULIC FAILURE ON DECENT, EMER DECLARED & 0 DEGREE FLAP LANDING PERFORMED.

Part: SKIN — CRACKED (ELEVATOR) · airframe 34,100 hrs

THE SKIN FORMING THE TE CLOSE OUT FROM STATION 86 TO 108, BETWEEN THE SPRING TAB & TRIP TAB, IS CRACKED AROUND SOME REPAIR FASTENER HOLES. THE SKIN WILL BE REPLACED TO ELIMINATE THE EXISTING REPAIR. REMOVE EXISTING SKIN, MAKE NEW SKIN FROM 7075-T6 0.016 & INSTALL NEW SKIN WITH NAS1097AD4 USING CR3214-4 IN BLIND AREAS.

Part: SKIN — CORRODED (BS 167) · airframe 33,629 hrs

CORROSION AROUND WINDOW AT BS 167, STRINGER 12R. CORROSION IS LOCATED BETWEEN THE OUTER SKIN & WINDOW CUT OUT DOUBLER. THE OUTER SKIN WILL BE CUT OUT & THE INTERNAL DOUBLER WILL BE CLEANED UP & PROTECTED FOR CORROSION. THE AREA WILL BE REPAIRED WITH A 2024-T3, 0.063 INCHES DOUBLER IAW DWG 1348-01 EO 1348.

Part: EXHAUST PIPE — RUPTURED (NR 2 ENGINE) · airframe 32,290 hrs

NR2 ENGINE FIRE WARNING ON TAKEOFF (ZONE 2 & 3). REPLACED NR 2 ENGINE IAW MM. INSPECTION OF REMOVED ENGINE REVEALED NO FIRE DAMAGE BUT OVERHEAT DAMAGE CAUSED BY A RUPTURED EXHAUST JOINT ON THE NR 9 CYLINDER.