N8076U

Part: TIRE — FAILED (MLG) · airframe 80,621 hrs · 33,197 cycles

ON LANDING TIRES NR 3 & 4 BLEW. REMOVED AND INSPTED AXEL THREADS. REPLACED NR 3 & 4 WHEEL ASSEMBLIES IAW DC-8 MM 32-41-05. FOUND MLG ANTI-SKID INOP, TROUBLESHOT SYSTEM, FOUND BAD ANTI-SKID CONTROL VALVE. REMOVED AND REPLACED CONTROL VALVE IAW DC-8 MM 32-43-3. OPS CHECK AND LEAK CHECK GOOD IAW DC-8 MM 32-03-03.

Part: SPLICE — CRACKED (FUSELAGE) · airframe 80,621 hrs · 33,197 cycles

DURING A MAINTENANCE VISIT FOUND A CRACK ALONG RADIUS OF THE STRESS PANEL ATTACH POINT END SPLICE AT STA Y=780 AND X=-12, DAMAGE EXCEEDED LIMITATIONS IAW DC-8 SRM. REMOVED DAMAGE, TREATED AREA IAW DC-8 SRM 51-1-8. RECEIVED PART AND INSTALLED IAW DC-8 SRM 51-3-0 AND 51-1-8 FIG 1F.

Part: ANGLE — CORRODED (STA 1168 L36) · airframe 80,621 hrs · 33,197 cycles

DURING A MAINTENANCE VISIT FOUND A DENT TO THE DOOR JAMB FRAME IN C-CARGO COMPT AT STA 1169 AND LBL 14 WATERLINE -58, DAMAGE EXCEEDED LIMITATIONS IAW DC-8 SRM. REMOVED DAMAGE, TREATED AREA IAW DC-8 SRM 51-1-8. FABRICATED AND INSTALLED REPAIR IAW DC-8 SRM 51-1-21 AND EA PD-08-53-075. (CORROSION DAMAGE RECORDED IN EWA CORROSION PROGRAM).

Part: WEB — CRACKED (FUSELAGE) · airframe 80,621 hrs · 33,197 cycles

DURING A MAINTENANCE VISIT FOUND A CRACK TO THE SIDE CUSP WEB AT STA 880 RT, DAMAGE EXCEEDED LIMITATIONS IAW DC-8 SRM. REMOVED DAMAGE, TREATED AREA IAW DC-8 SRM 51-1-8. FABRICATED AND INSTALLED REPAIR IAW DC-8 SRM 53-2-0 AND 51-1-21.

Part: WEB — CRACKED (FUSELAGE) · airframe 80,621 hrs · 33,197 cycles

DURING A MAINTENANCE VISIT FOUND A CRACK TO THE CUSP WEB AT STA 880 LT, DAMAGE EXCEEDED LIMITATIONS IAW DC-8 SRM. RECEIVED REPAIR AND INSTALLED IAW DC-8 SRM 51-1-21 AND 53-2-0.

Part: INTERCOSTAL — CRACKED (FUSELAGE) · airframe 80,621 hrs · 33,197 cycles

DURING A MAINTENANCE VISIT FOUND A CRACK TO THE INTERCOSTAL AND DOUBLER BETWEEN FLOORBEAMS AT STA 320 - 324 AND X+40 Z-2, DAMAGE EXCEEDED LIMITATIONS IAW DC-8 SRM. REMOVED DAMAGE, TREATED AREA IAW DC-8 SRM 51-1-8. FABRICATED AND INSTALLED REPAIR IAW DC-8 SRM 51-1-21 AND 53-01-0.

Part: ANGLE — CRACKED (FUSELAGE) · airframe 80,621 hrs · 33,197 cycles

DURING A MAINTENANCE VISIT FOUND A CRACK TO THE FAIRING ATTACH ANGLE AT STA 640, DAMAGE EXCEEDED LIMITATIONS IAW DC-8 SRM. REMOVED DAMAGE, TREATED AREA IAW DC-8 SRM 51-1-8. FABRICATED AND INSTALLED REPAIR IAW DC-8 SRM 51-1-24 AND 51-1-21.

Part: SEAT TRACK — CORRODED (FUSELAGE) · airframe 80,621 hrs · 33,197 cycles

DURING A MAINTENANCE VISIT FOUND CORROSION DAMAGE TO THE TRACK AT FASTENER HOLE AT FS 1482 AND X=50R, DAMAGE EXCEEDED LIMITATIONS IAW DC-8 SRM. REMOVED DAMAGE, TREATED AREA IAW DC-8 SRM 51-1-8. RECEIVED PART AND INSTALLED IAW DC-8 SRM 53-2-3 FIG 1F. (CORROSION DAMAGE RECORDED IN EWA CORROSION PROGRAM).

Part: INTERCOSTAL — CRACKED (FUSELAGE) · airframe 80,621 hrs · 33,197 cycles

DURING A MAINTENANCE VISIT FOUND A CRACK TO THE INTERCOSTAL BETWEEN STA 1380 - 1400 AND LBL -18 WATERLINE -35, DAMAGE EXCEEDED LIMITATIONS IAW DC-8 SRM. REMOVED DAMAGE, TREATED AREA IAW DC-8 SRM 51-1-8. FABRICATED AND INSTALLED REPAIR IAW DC-8 SRM 51-1-24, 51-1-5 AND 51-1-20D.

Part: ANGLE — CRACKED (RT RAM AIR DUCT) · airframe 80,621 hrs · 33,197 cycles

DURING A MAINTENANCE VISIT FOUND A CRACK TO THE BLEED AIR CONNECTOR DOOR LANDING AT THE RT RAM AIR INLET, DAMAGE EXCEEDED LIMITATIONS IAW DC-8 SRM. REMOVED DAMAGE, TREATED AREA IAW DC-8 SRM 51-1-8. FABRICATED AND INSTALLED REPAIR IAW DC-8 SRM 53-2-0.

Part: FITTING — CORRODED (FUSELAGE) · airframe 80,621 hrs · 33,197 cycles

DURING A MAINTENANCE VISIT FOUND CORROSION DAMAGE TO THE RIGHT WHEEL WELL FITTING AT STA 899 AND L23R, DAMAGE EXCEEDED LIMITATIONS IAW DC-8 SRM. REMOVED DAMAGE, TREATED AREA IAW DC-8 SRM 51-1-8. RECEIVED PART AND INSTALLED IAW DC-8 SRM 51-3-0 FIG 1F. (CORROSION DAMAGE RECORDED IN EWA CORROSION PROGRAM).

Part: LONGERON — CORRODED (FUSELAGE) · airframe 80,621 hrs · 33,197 cycles

DURING A MAINTENANCE VISIT FOUND CORROSION DAMAGE TO THE TOP SIDE FRAME AT STA 1080 RBL-48 THROUGH LBL 448 AND ABOVE LONGERON L33.35, DAMAGE EXCEEDED LIMITATIONS IAW DC-8 SRM. /////CORRECTIVE ACTION///// REMOVED DAMAGE, TREATED AREA IAW DC-8 SRM 51-1-8. FABRICATED AND INSTALLED REPAIR IAW DC-8 SRM 51-1-24 AND EA PD 08-53-064. (CORROSION DAMAGE RECORDED IN EWA CORROSION PROGRAM).

Part: SKIN — CRACKED (RT WING) · airframe 80,621 hrs · 33,197 cycles

DURING A MAINTENANCE VISIT FOUND A CRACK TO THE HEAT VENT ON THE RT WING CENTER L/E INTERIOR AT STA 352, DAMAGE EXCEEDED LIMITATIONS IAW DC-8 SRM. REMOVED DAMAGE, ALODINED AND PRIMED AREA IAW DC-8 SRM 51-1-8. FABRICATED AND INSTALLED REPAIR IAW DC-8 SRM 57-2-0 AND EA PD08-57-036.

Part: SEAT TRACK — CORRODED (FUSELAGE) · airframe 80,621 hrs · 33,197 cycles

DURING A MAINTENANCE VISIT FOUND CORROSION DAMAGE TO THE SEAT TRACK AT STA 190 - 205, DAMAGE EXCEEDED LIMITATIONS IAW DC-8 SRM. REMOVED DAMAGE, TREATED AREA IAW DC-8 SRM 51-1-8. RECEIVED PART AND INSTALLED IAW DC-8 SRM 53-2-3. CORROSION DAMAGE RECORDED IN EWA CORROSION PROGRAM.

Part: SEAT TRACK — CORRODED (FUSELAGE) · airframe 80,621 hrs · 33,197 cycles

DURING A MAINTENANCE VISIT FOUND CORROSION DAMAGE ON THE AFT SIDE OF THE NR 3 LEFT SEAT TRACK AT STA 230 - 240 AND LBL 25 - 29, DAMAGE EXCEEDED LIMITATIONS IAW DC-8 SRM. REMOVED DAMAGE, TREATED AREA IAW DC-8 SRM 51-1-8. RECEIVED PART AND INSTALLED IAW DC-8 SRM 53-2-3, 57-1-8 FIG 1F. CORROSION DAMAGE RECORDED IN EWA CORROSION PROGRAM.

Part: SEAT TRACK — CORRODED (FUSELAGE) · airframe 80,621 hrs · 33,197 cycles

DURING A MAINTENANCE VISIT FOUND CORROSION DAMAGE TO THE SEAT TRACK AT STA Y398-428 AND X23-X27, DAMAGE EXCEEDED LIMITATIONS IAW DC-8 SRM. REMOVED DAMAGE, TREATED AREA IAW DC-8 SRM 51-1-8. RECEIVED PART AND INSTALLED IAW DC-8 SRM 53-2-3 FIG F. CORROSION DAMAGE RECORDED IN EWA CORROSION PROGRAM.

Part: FITTING — CORRODED (CARGO DOOR FRAME) · airframe 80,621 hrs · 33,197 cycles

DURING A MAINTENANCE VISIT FOUND CORROSION DAMAGE ON THE FITTING INSIDE BOTTOM LIGHTENING HOLE ON THE FWD CARGO NR 2 DOOR CUTOUT AFT JAMB AT STA 565 AND L33R, DAMAGE EXCEEDED LIMITATIONS IAW DC-8 SRM. REMOVED DAMAGE, TREATED AREA IAW DC-8 SRM 51-1-8. FABRICATED AND INSTALLED REPAIR IAW DC-8 SRM 51-1-21 FIG F. CORROSION DAMAGE RECORDED IN EWA CORROSION PROGRAM.

Part: DOUBLER — CRACKED (CARGO DOOR) · airframe 80,621 hrs · 33,197 cycles

DURING A MAINTENANCE VISIT FOUND A CRACK TO THE FWD CARGO COMPT DOOR LEFT EDGE EXTERIOR, DAMAGE EXCEEDED LIMITATIONS IAW DC-8 SRM. REMOVED DAMAGE, TREATED AREA IAW DC-8 SRM 51-1-8. FABRICATED AND INSTALLED REPAIR IAW DC-8 SRM 51-1-21, 51-1-20D AND PD-05-52-002.

Part: SKIN — CRACKED (FUSELAGE) · airframe 80,621 hrs · 33,197 cycles

DURING A MAINTENANCE VISIT FOUND A CRACK TO THE HOT AIR VENTS ON THE LT WING L/E AT STA 282, 341 AND 285, DAMAGE EXCEEDED LIMITATIONS IAW DC-8 SRM. REMOVED DAMAGE, TREATED AREA IAW DC-8 SRM 51-1-8. FABRICATED AND INSTALLED REPAIR IAW EA PD08-57-041.

Part: SEAT TRACK — CORRODED (CABIN) · airframe 80,621 hrs · 33,197 cycles

DURING A MAINTENANCE VISIT FOUND CORROSION DAMAGE ON THE SEAT TRACK AT STA 1620 - 1640 AND LT X+44, DAMAGE EXCEEDED LIMITATIONS IAW DC-8 SRM. REMOVED DAMAGE, TREATED AREA IAW DC-8 SRM 51-1-8. RECEIVED PART AND INSTALLED IAW DC-8 SRM 53-2-0 AND 53-2-3 FIG 1. (CORROSION DAMAGE RECORDED IN EWA CORROSION PROGRAM).

Part: ANGLE — CRACKED (LT WING) · airframe 80,621 hrs · 33,197 cycles

DURING A MAINTENANCE VISIT FOUND A CRACK ON FWD SIDE OF SUPPORT FRAME ON THE LT WING TRAILING EDGE FLAP WELL AT STA XW 27, DAMAGE EXCEEDED LIMITATIONS IAW DC-8 SRM. REMOVED DAMAGE, TREATED AREA IAW DC-8 SRM 51-1-8. FABRICATED AND INSTALLED NEW ANGLE IAW DC-8 SRM 51-1-20D.

Part: FITTING — CRACKED (KEELBEAM) · airframe 80,621 hrs · 33,197 cycles

DURING A MAINTENANCE VISIT FOUND A CRACK IN THE RADIUS OF THE RIGHT SIDE KEEL BEAM SUPPORT FITTING AT STA Y+791 X-1, DAMAGE EXCEEDED LIMITATIONS IAW DC-8 SRM. REMOVED DAMAGE, TREATED AREA IAW DC-8 SRM 51-1-8. FABRICATED AND INSTALLED FITTING IAW DC-8 SRM 51-1-20D, 51-3-0 AND 53-31-1 PAGE 1.

Part: FRAME — CORRODED (FUSELAGE) · airframe 80,621 hrs · 33,197 cycles

DURING A MAINTENANCE VISIT FOUND CORROSION DAMAGE TO THE RT WHEEL WELL FRAME AT STA 879 ABOVE L24R, DAMAGE EXCEEDED LIMITATIONS IAW DC-8 SRM. REMOVED DAMAGE, TREATED AREA IAW DC-8 SRM 51-1-8. FABRICATED AND INSTALLED REPAIR IAW DC-8 SRM 53-2-6, 51-1-24 AND 51-1-20D FIG 5. (CORROSION DAMAGE RECORDED IN EWA CORROSION PROGRAM).

Part: FLOORBEAM — CORRODED (FUSELAGE) · airframe 80,621 hrs · 33,197 cycles

DURING A MAINTENANCE VISIT FOUND CORROSION DAMAGE TO THE FLOORBEAM TOP STRAP AT STA 1580 AND X+30 THROUGH X+43, DAMAGE EXCEEDED LIMITATIONS IAW DC-8 SRM. REMOVED DAMAGE, TREATED AREA IAW DC-8 SRM 51-1-8. FABRICATED AND INSTALLED SUPPORT IAW DC-8 SRM 51-1-4 AND 51-1-24. CORROSION DAMAGE RECORDED IN EWA CORROSION PROGRAM.

Part: SEAT TRACK — CORRODED (FUSELAGE) · airframe 80,621 hrs · 33,197 cycles

DURING A MAINTENANCE VISIT FOUND CORROSION DAMAGE TO THE SEAT TRACK AT STA 1660-1675 AND X-43 TO X-45, DAMAGE EXCEEDED LIMITATIONS IAW DC-8 SRM. REMOVED DAMAGE, TREATED AREA IAW DC-8 SRM 51-1-8. FABRICATED AND INSTALLED PART IAW DC-8 SRM 53-2-0 AND 51-1-8 PAGE 1F. CORROSION DAMAGE RECORDED IN EWA CORROSION PROGRAM.

Part: FRAME — CORRODED (FUSELAGE) · airframe 80,621 hrs · 33,197 cycles

DURING A MAINTENANCE VISIT FOUND CORROSION DAMAGE ON FRAME SPLICE FWD SIDE OF FRAME AT STA 520 AND L36, DAMAGE EXCEEDED LIMITATIONS IAW DC-8 SRM. REMOVED DAMAGE, TREATED AREA IAW DC-8 SRM 51-1-8. FABRICATED AND INSTALLED REPAIR IAW DC-8 SRM 53-2-0, 51-1-20D AND 53-41-1 FIG 2. (CORROSION DAMAGE RECORDED IN EWA CORROSION PROGRAM).

Part: SEAT TRACK — CORRODED (CABIN) · airframe 80,621 hrs · 33,197 cycles

DURING A MAINTENANCE VISIT FOUND CORROSION DAMAGE ON THE SEAT TRACK FLANGE AT STA 1362 AND X+=45 Z+0, DAMAGE EXCEEDED LIMITATIONS IAW DC-8 SRM. REMOVED DAMAGE, TREATED AREA IAW DC-8 SRM 51-1-8. RECEIVED PART AND INSTALLED IAW DC-8 SRM 53-2-3 FIG 1F. (CORROSION DAMAGE RECORDED IN EWA CORROSION PROGRAM).

Part: FRAME — CORRODED (FUSELAGE) · airframe 80,621 hrs · 33,197 cycles

DURING A MAINTENANCE VISIT FOUND CORROSION DAMAGE TO THE FRAME AT STA 540 AND L29L TO 36, DAMAGE EXCEEDED LIMITATIONS IAW DC-8 SRM. REMOVED DAMAGE, TREATED AREA IAW DC-8 SRM 51-1-8. FABRICATED AND INSTALLED REPAIR IAW DC-8 SRM 53-2-0 AND 51-1-21 FIG 1B. CORROSION DAMAGE RECORDED IN EWA CORROSION PROGRAM.

Part: SEAT TRACK — CORRODED (FUSELAGE) · airframe 80,621 hrs · 33,197 cycles

DURING A MAINTENANCE VISIT FOUND CORROSION DAMAGE TO THE SEAT TRACK AT STA 1600 AND X+45 X+44, DAMAGE EXCEEDED LIMITATIONS IAW DC-8 SRM. REMOVED DAMAGE, TREATED AREA IAW DC-8 SRM 51-1-8. RECEIVED PART AND INSTALLED IAW DC-8 SRM 53-2-3 FIG 1F. (CORROSION DAMAGE RECORDED IN EWA CORROSION PROGRAM).

Part: SEAT TRACK — CORRODED (FUSELAGE) · airframe 80,621 hrs · 33,197 cycles

DURING A MAINTENANCE VISIT FOUND CORROSION DAMAGE TO THE SEAT TRACK AT STA 1660-1680 AND X+44, DAMAGE EXCEEDED LIMITATIONS IAW DC-8 SRM. REMOVED DAMAGE, TREATED AREA IAW DC-8 SRM 51-1-8. RECEIVED PART AND INSTALLED IAW DC-8 SRM 53-2-3 PG 35. CORROSION DAMAGE RECORDED IN EWA CORROSION PROGRAM.

Part: SKIN — CRACKED (FUSELAGE) · airframe 80,621 hrs · 33,197 cycles

DURING A MAINTENANCE VISIT FOUND A CRACK TO THE HOT AIR VENT ON THE LT WING CENTER L/E AT STA 347 - 354, DAMAGE EXCEEDED LIMITATIONS IAW DC-8 SRM. REMOVED DAMAGE, TREATED AREA IAW DC-8 SRM 51-1-8. FABRICATED AND INSTALLED REPAIR IAW EA PD08-57-041.

Part: SKIN — CRACKED (FUSELAGE) · airframe 80,621 hrs · 33,197 cycles

DURING A MAINTENANCE VISIT FOUND A CRACK TO THE HOT AIR VENT ON THE LT WING CENTER L/E AT STA 366 - 360, DAMAGE EXCEEDED LIMITATIONS IAW DC-8 SRM. REMOVED DAMAGE, TREATED AREA IAW DC-8 SRM 51-1-8. FABRICATED AND INSTALLED REPAIR IAW EA PD08-57-041.

Part: BRACKET — CRACKED (BULKHEAD) · airframe 80,621 hrs · 33,197 cycles

DURING A MAINTENANCE VISIT FOUND A CRACK TO THE UPPER MOUNTING BRACKET ON THE FWD ACCESSORY COMPT AFT BULKHEAD AT STA 70 X-3, DAMAGE EXCEEDED LIMITATIONS IAW DC-8 SRM. REMOVED DAMAGE, TREATED AREA IAW DC-8 SRM 51-1-8. FABRICATED AND INSTALLED PART IAW DC-8 SRM 51-1-4, 51-1-5 AND 51-31 PAGE 1.

Part: LONGERON — CORRODED (FUSELAGE) · airframe 80,621 hrs · 33,197 cycles

DURING A MAINTENANCE VISIT FOUND CORROSION DAMAGE ON UPPER SIDE OF LONGERON AT STA 500 AND L31R, DAMAGE EXCEEDED LIMITATIONS IAW DC-8 SRM. REMOVED DAMAGE, TREATED AREA IAW DC-8 SRM 51-1-8. FABRICATED AND INSTALLED REPAIR IAW DC-8 SRM 53-2-1 FIG 7 AND 53-2-0. (CORROSION DAMAGE RECORDED IN EWA CORROSION PROGRAM).

Part: FRAME — CORRODED (FUSELAGE) · airframe 80,621 hrs · 33,197 cycles

DURING A MAINTENANCE VISIT FOUND CORROSION DAMAGE TO THE FRAME IN THE FWD CARGO COMPT AT STA 600 AND L31L TO L27R, DAMAGE EXCEEDED LIMITATIONS IAW DC-8 SRM. REMOVED DAMAGE, TREATED AREA IAW DC-8 SRM 51-1-8. FABRICATED AND INSTALLED REPAIR IAW DC-8 SRM 51-1-20D AND EA PD08-53-073. (CORROSION DAMAGE RECORDED IN EWA CORROSION PROGRAM).

Part: SEAT TRACK — CORRODED (FUSELAGE) · airframe 80,621 hrs · 33,197 cycles

DURING A MAINTENANCE VISIT FOUND CORROSION DAMAGE TO THE SEAT TRACK AT FS 1680-1700 AND X=25, DAMAGE EXCEEDED LIMITATIONS IAW DC-8 SRM. REMOVED DAMAGE, TREATED AREA IAW DC-8 SRM 51-1-8. RECEIVED PART AND INSTALLED IAW DC-8 SRM 53-2-3 PG 35. CORROSION DAMAGE RECORDED IN EWA CORROSION PROGRAM.

Part: FITTING — CORRODED (FUSELAGE) · airframe 80,621 hrs · 33,197 cycles

DURING A MAINTENANCE VISIT FOUND IG CORROSION DAMAGE TO THE T-ANGLE BELOW FLOOR LEVEL ATTACHED TO SKIN AT STA 920 AND L21R TO L22R, DAMAGE EXCEEDED LIMITATIONS IAW DC-8 SRM. REMOVED DAMAGE, TREATED AREA IAW DC-8 SRM 51-1-8. RECEIVED PART AND INSTALLED IAW DC-8 SRM 53-2-0 AND 53-4-1 FIG 51. (CORROSION DAMAGE RECORDED IN EWA CORROSION PROGRAM).

Part: LONGERON — CORRODED (FUSELAGE) · airframe 80,621 hrs · 33,197 cycles

DURING A MAINTENANCE VISIT FOUND CORROSION DAMAGE TO THE LONGERON AROUND FASTENERS AT STA 1070 TO 1080 AND L36, DAMAGE EXCEEDED LIMITATIONS IAW DC-8 SRM. REMOVED DAMAGE, TREATED AREA IAW DC-8 SRM 51-1-8. FABRICATED AND INSTALLED REPAIR IAW DC-8 SRM 53-2-0 AND 53-4-1 FIG 1. (CORROSION DAMAGE RECORDED IN EWA CORROSION PROGRAM).

Part: FLOORBEAM — CORRODED (CABIN) · airframe 80,621 hrs · 33,197 cycles

DURING A MAINTENANCE VISIT FOUND CORROSION DAMAGE TO THE FLOORBEAM AROUND HUCKBOLTS AT STA 920 AND -21-X61 THROUGH -X67, DAMAGE EXCEEDED LIMITATIONS IAW DC-8 SRM. REMOVED DAMAGE, TREATED AREA IAW DC-8 SRM 51-1-8. RECEIVED PART AND INSTALLED IAW DC-8 SRM 53-2-0 AND PD-08-53-059. (CORROSION DAMAGE RECORDED IN EWA CORROSION PROGRAM).

Part: WEB — CRACKED (CARGO DOOR) · airframe 80,621 hrs · 33,197 cycles

DURING A MAINTENANCE VISIT FOUND CORROSION DAMAGE AND A CRACK TO THE DOOR WEB AT FWD END OF C-BAGGAGE DOOR AT STA 1172 AND -X10, DAMAGE EXCEEDED LIMITATIONS IAW DC-8 SRM. REMOVED DAMAGE, TREATED AREA IAW DC-8 SRM 51-1-8. FABRICATED AND INSTALLED REPAIR IAW DC-8 SRM 52-2-0, 51-1-21 AND 52-2-0 FIG 4. CORROSION DAMAGE RECORDED IN EWA CORROSION PROGRAM.

Part: SKIN — CRACKED (FUSELAGE) · airframe 80,621 hrs · 33,197 cycles

DURING A MAINTENANCE VISIT FOUND A CRACK TO THE RT WING CENTER L/E INTERIOR HEAT VENT AT STA 302 AND 408, DAMAGE EXCEEDED LIMITATIONS IAW DC-8 SRM. REMOVED DAMAGE, TREATED AREA IAW DC-8 SRM 51-1-8. FABRICATED AND INSTALLED REPAIR IAW DC-8 SRM 57-2-0 AND EA PD08-57-036.

Part: STRAP — CORRODED (FUSELAGE) · airframe 80,621 hrs · 33,197 cycles

DURING A MAINTENANCE VISIT FOUND CORROSION DAMAGE TO THE INTERCOSTAL STRAP OVER FRAME AT STA 1080 ABOVE L35R, DAMAGE EXCEEDED LIMITATIONS IAW DC-8 SRM. REMOVED DAMAGE, TREATED AREA IAW DC-8 SRM 51-1-8. FABRICATED AND INSTALLED REPAIR IAW DC-8 SRM 53-2-0, 51-1-4, 51-1-24, 51-1-21 AND 51-1-20D FIG 1F. (CORROSION DAMAGE RECORDED IN EWA CORROSION PROGRAM).

Part: LONGERON — CORRODED (FUSELAGE) · airframe 80,621 hrs · 33,197 cycles

DURING A MAINTENANCE VISIT FOUND CORROSION DAMAGE AROUND FASTENERS ON THE LONGERON AT STA 1060 TO 1070 AND L33L, DAMAGE EXCEEDED LIMITATIONS IAW DC-8 SRM. REMOVED DAMAGE, TREATED AREA IAW DC-8 SRM 51-1-8. FABRICATED AND INSTALLED REPAIR IAW DC-8 SRM 53-2-0, 53-4-1 AND 51-1-20D FIG 4. (CORROSION DAMAGE RECORDED IN EWA CORROSION PROGRAM).

Part: FITTING — CORRODED (FUSELAGE) · airframe 80,621 hrs · 33,197 cycles

DURING A MAINTENANCE VISIT FOUND CORROSION DAMAGE TO THE FITTING FOR FRAME TO FUSELAGE FWD SIDE OF FITTING AT STA Y=880 AND L21R-L22R, DAMAGE EXCEEDED LIMITATIONS IAW DC-8 SRM. REMOVED DAMAGE, TREATED AREA IAW DC-8 SRM 51-1-8. RECEIVED PART AND INSTALLED IAW DC-8 SRM 53-2-0, 51-1-24 AND 51-1-20D. CORROSION DAMAGE RECORDED IN EWA CORROSION PROGRAM.

Part: SKIN — CRACKED (CENTER WING) · airframe 80,621 hrs · 33,197 cycles

DURING A MAINTENANCE VISIT FOUND A CRACK TO THE RT WING CENTER L/E HOT AIR VENT AT STA 419, DAMAGE EXCEEDED LIMITATIONS IAW DC-8 SRM. FABRICATED AND INSTALLED REPAIR IAW DC-8 SRM 51-1-8 AND EAPD08-57-036.

Part: ANGLE — CRACKED (FUSELAGE) · airframe 80,621 hrs · 33,197 cycles

DURING A MAINTENANCE VISIT FOUND A CRACK TO THE MAIN CABIN FLOORBEAM TO BULKHEAD ATTACH ANGLE, DAMAGE EXCEEDED LIMITATIONS IAW DC-8 SRM. REMOVED DAMAGE, TREATED AREA IAW DC-8 SRM 51-1-8. FABRICATED AND INSTALLED REPAIR IAW DC-8 SRM 51-1-21, 51-1-24, 51-1-5 AND EA PD-05-53-068.

Part: BRACKET — MISSING (FUSELAGE) · airframe 80,621 hrs · 33,197 cycles

DURING A MAINTENANCE VISIT FOUND A MISSING BRACKET THAT ATTACHES TO LONGERON AT STA 1480 AND X AXIS -29 L31R, DAMAGE EXCEEDED LIMITATIONS IAW DC-8 SRM. REMOVED DAMAGE, TREATED AREA IAW DC-8 SRM 51-1-8. FABRICATED AND INSTALLED REPAIR IAW DC-8 SRM 51-1-4, 51-1-24 AND 51-1-8 PG 1 NR 3.

Part: SKIN — CRACKED (RT WING) · airframe 80,621 hrs · 33,197 cycles

DURING A MAINTENANCE VISIT FOUND A CRACK TO THE HEAT VENT ON THE RT WING O/B LEADING EDGE INTERIOR SKIN AT STA 594, DAMAGE EXCEEDED LIMITATIONS IAW DC-8 SRM. REMOVED DAMAGE, TREATED AREA IAW DC-8 SRM 51-1-8. FABRICATED AND INSTALLED REPAIR IAW DC-8 SRM 57-2-0 AND EA PD08-57-034.

Part: ANGLE — CRACKED (FUSELAGE) · airframe 80,621 hrs · 33,197 cycles

DURING A MAINTENANCE VISIT FOUND A CRACK TO THE MAIN CABIN FLOORBEAM TO BULKHEAD ATTACH ANGLE AT FS 70 AND X+25, DAMAGE EXCEEDED LIMITATIONS IAW DC-8 SRM. REMOVED DAMAGE, TREATED AREA IAW DC-8 SRM 51-1-8. FABRICATED AND INSTALLED NEW ANGLE IAW DC-8 SRM 51-1-21, 51-1-24, 51-1-5 AND PD-08-53-068.

Part: SKIN — CRACKED (FUSELAGE) · airframe 80,621 hrs · 33,197 cycles

DURING A MAINTENANCE VISIT FOUND LONGATED HOLES AND A CRACK TO THE LT WING LEADING EDGE O/B AT FS 841 - 853, DAMAGE EXCEEDED LIMITATIONS IAW DC-8 SRM. REMOVED DAMAGE, TREATED AREA IAW DC-8 SRM 51-1-8. FABRICATED AND INSTALLED REPAIR IAW DC-8 SRM 51-1-21 AND EA PD08-57-035.

Part: BRACKET — CRACKED (BULKHEAD) · airframe 80,621 hrs · 33,197 cycles

DURING A MAINTENANCE VISIT FOUND A CRACK TO THE LOWER MOUNTING BRACKET ON THE FWD ACCESSORY COMPT AFT BULKHEAD AT FS 70 X-6, DAMAGE EXCEEDED LIMITATIONS IAW DC-8 SRM. REMOVED DAMAGE, TREATED AREA IAW DC-8 SRM 51-1-8. FABRICATED AND INSTALLED REPAIR IAW DC-8 SRM 51-1-4 AND 51-1-21 PAGE 1.

Part: ANGLE — CRACKED (LAV OVERHEAD) · airframe 80,621 hrs · 33,197 cycles

DURING A MAINTENANCE VISIT FOUND A CRACKED STRAP ON THE MAIN CABIN LAV OVERHEAD CEILING FRAME ASSY, DAMAGE EXCEEDED LIMITATIONS IAW DC-8 SRM. REMOVED DAMAGE, TREATED AREA IAW DC-8 SRM 51-1-8. FABRICATED AND INSTALLED REPAIR IAW DC-8 SRM 51-1-21 AND EA PD08-25-006.

Part: INTERCOSTAL — CRACKED (FUSELAGE) · airframe 80,621 hrs · 33,197 cycles

DURING A MAINTENANCE VISIT FOUND A 1.5 INCH CRACK IN CARGO BAY B INTERCOSTAL BETWEEN FRAMES Y=300 TO Y=520 AND XCW=68, DAMAGE EXCEEDED LIMITATIONS IAW DC-8 SRM. REMOVED DAMAGE, TREATED AREA IAW DC-8 SRM 51-1-8. FABRICATED AND INSTALLED REPAIR IAW DC-8 SRM 53-2-0 AND 53-2-3.

Part: FRAME — CORRODED (FUSELAGE) · airframe 80,621 hrs · 33,197 cycles

DURING A MAINTENANCE VISIT FOUND CORROSION DAMAGE TO THE FRAME LEG ON FWD SIDE AT FS 1200 AND L34R-L34R, DAMAGE EXCEEDED LIMITATIONS IAW DC-8 SRM. REMOVED DAMAGE, TREATED AREA IAW DC-8 SRM 51-1-8. FABRICATED AND INSTALLED REPAIR IAW DC-8 SRM 53-2-0, 51-1-4 (FIG 23) AND 51-1-20D PG 7. (CORROSION DAMAGE RECORDED IN EWA CORROSION PROGRAM).

Part: MEC — OUT OF ADJUST (NR 2 ENGINE)

NR 2 ENG SLOW TO ACCELERATE TO IDLE DURING START, SLOW TO CUTBACK. FUEL FLOW AND EGT HIGHER THAN 1, 3 & 4. AFTER V1 EGT WENT TO 905 DEG, 908 MOMENTARLEY, REDUCED N1 BY 2 PERCENT TO MAINTAIN EGT BELOW LIMITS. ACCOMPLISHED IN FLT SHUTDOWN AND RETURNED TO MMMX. WINDMILLING TIME 21 MIN AND OIL PRESS 0 PSI. PERFORMED STATIC RIG CHECK ON THE VBV AND VSV RIGGING TO MEC TO ENGINE NR 2. ENGINE RUN OPS CHECKS OK IAW MM 73-21-10.

Part: EGT INDICATOR — FAILED (NR 4)

AFTER V1, NR 4 EGT MOMENTARILY WENT TO 907 DEG. REDUCED N1 1 PERCENT TO MAINTAIN EGT BELOW LIMITS. ACCOMPLISHED IN FLT SHUTDOWN, DUMPED FUEL, RETURNED TO MMMX. WINDMILL TIME 25 MIN AND OIL PRESS 0 PSI. REMOVED AND REPLACED NR 4 EGT INDICATOR AS REQUIRED. OPS CHECKS NORMAL.

Part: DOUBLER — DAMAGED (BS 330)

DURING A MAINTENANCE VISIT, FOUND EXTEROIR, SKIN DOUBLER GOUGED AND TORN, AT STA 330 AND LONGERON 36. REMOVED DAMAGED SECTION, TREATED AREA IAW DC-8 SRM 51-1-8. FABRICATED AND INSTALLED REPAIR DOUBLER IAW FAA APPROVED TIMCO DER ENGINEERING SKETCH REO-05348.

Part: BUSHING — DAMAGED (RT MLG)

DURING A MAINTENANCE VISIT, FOUND RIGHT SIDE, MAIN LANDING GEAR, SIDE BRACE, LINK ASSEMBLY, BORE BUSHING WAS REMOVED TO REMOVE CORROSION, DURING PROCEDURES OVERSIZED HOLE. REPAIRED HOLE AND BUSHING, IAW FAA APPROVED TIMCO DER ENGINEERING SKETCH REO-05311.

Part: SUPPORT — DAMAGED (FUSELAGE)

DURING A MAINTENANCE VISIT, FOUND PREVIOUS REPAIR TO FLOOR SUPPORT STRUT, DAMAGED CAUSED BY IMPACT FROM CARGO. REMOVED DAMAGED SECTION, FABRICATED AND INSTALLED REPAIR IAW FAA APPROVED TIMCO ENGINEERING SKETCH REO-05298.

Part: STIFFENER — CORRODED (VERT STAB)

DURING A MAINTENANCE VISIT, FOUND VERTICAL STABILIZER, INNER SPAR STIFFENER WITH CORROSION BEYOND LIMITS IAW DC-8 SRM. REMOVED DAMAGED SECTION, TREATED AREA IAW DC-8 SRM 51-1-8. FABRICATED AND INSTALLED REPAIR DOUBLER IAW FAA APPROVED TIMCO DER ENGINEERING SKETCH REO-05303.

Part: FITTING — CORRODED (BS 798)

DURING A MAINTENANCE VISIT, FOUND FITTING (P/N 5641008-502) WITH CORROSION DAMAGE BEYOND LIMITS IAW DC-8 SRM AT STA 798. REMOVED DAMAGED FITTING, TREATED AREA IAW DC-8 SRM 51-1-8. FABRICATED NEW FITTING BY MATERIAL SUBSTITUTION, INSTALLED IAW FAA APPROVED TIMCO DER ENGINEERING SKETCH REO-05278.

Part: SKIN — CHAFED (RT TE FLAP)

DURING A MAINTENANCE VISIT, FOUND RIGHT WING, OUTBOARD FLAP, LOWER SKIN WITH CHAFING CAUSED BY FAIRING RUBBING THE SKIN. REMOVED DAMAGED SECTION, TREATED AREA IAW DC-8 SRM 51-1-8. FABRICATED AND INSTALLED REPAIR DOUBLER IAW FAA APPROVED TIMCO DER ENGINEERING SKETCH REO-05280.

Part: FRAME — DAMAGED (BS 1000)

DURING A MAINTENANCE VISIT, FOUND FRAME WITH ELONGATED HOLES, AT STA 1000 AND FOUND LONGERON 35 LEFT WITH CORROSION DAMAGE. REMOVED DAMAGED SECTIONS FROM FRAME, AND CORROSION FROM LONGERON 35L, TREATED AREA IAW DC-8 SRM 51-1-8. FABRICATED AND INSTALLED REPAIRS IAW FAA APPROVED TIMCO DER ENGINEERING SKETCH REO-05276.

Part: FLOORBEAM — CORRODED (BS 1300)

DURING A MAINTENANCE VISIT, FOUND FLOORBEAM, UPPER FLANGE WITH CORROSION DAMAGED BEYOND LIMITS IAW DC-8 SRM AT STA 1300. REMOVED DAMAGED SECTION, TREATED AREA IAW DC-8 SRM 51-1-8. FABRICATED AND INSTALLED REPAIR STRAPS IAW FAA APPROVED TIMCO ENGINEERING SKETCH REO-05217.

Part: PANEL — CRACKED (HYD SERVICE DOOR)

DURING A MAINTENANCE VISIT FOUND LEFT WING, HYDRAULIC SERVICE DOOR, PANEL (-3), CRACKED AND CHAFED ON FLANGE. REMOVED DAMAGED SECTION, FABRICATED AND INSTALLED REPAIR IAW FAA APPROVED TIMCO DER ENGINEERING SKETCH REO-05230.

Part: FRAME — CORRODED (BS 1260)

DURING A MAINTENANCE VISIT, FOUND FRAME INBOARD FLANGE WITH CORROSION DAMAGED BEYOND LIMITS IAW DC-8 SRM AT STA 1260 BETWEEN LONGERONS 25 LEFT AND 26 LEFT. REMOVED DAMAGED SECTION, TREATED AREA IAW DC-8 SRM 51-1-8. FABRICATED AND INSTALLED REPAIR DOUBLER IAW FAA APPROVED TIMCO DER ENGINEERING SKETCH REO-05224.

Part: DOUBLER — CORRODED (BS 1216)

DURING A MAINTENANCE VISIT, FOUND INNER DOUBLER WITH CORROSION DAMAGE BEYOND LIMITS IAW DC-8 SRM AT STA 1216 BETWEEN LONGERONS 34 RIGHT TO LONGERON 36. REMOVED DAMAGED SECTION, TREATED AREA IAW DC-8 SRM 51-1-8. FABRICATED AND INSTALLED REPAIR DOUBLER IAW FAA APPROVED TIMCO DER ENGINEERING SKETCH REO-05202.

Part: FITTING — MISMANUFACTURED (MLG DOOR ACT)

DURING A MAINTENANCE VISIT, PERFORMED REQUIREMENTS IAW SB 32-171, LEFT AND RIGHT MAIN LANDING GEAR DOOR ACTUATOR ATTACH FITTING NEEDED TO BE SPOTFACED TO INSTALL FASTENERS.

Part: FRAME — CORRODED (BS 1260)

DURING A MAINTENANCE VISIT, FOUND FRAME UPPER FLANGE WITH CORROSION DAMAGE BEYOND LIMITS IAW DC-8 SRM AT STA 1260 BETWEEN LONGERONS 34 LEFT AND 35 RIGHT. REMOVED DAMAGED SECTION, TREATED AREA IAW FAA APPROVED TIMCO DER ENGINEERING SKETCH REO-05188.

Part: FLOORBEAM — CORRODED (BS 920)

DURING A MAINTENANCE VISIT, FOUND FLOORBEAM, VERTICAL FLANGE WITH CORROSION DAMAGE BEYOND LIMITS IAW DC-8 SRM AT STA 920 AND LONGERON 21 LEFT. REMOVED DAMAGED SECTION, TREATED AREA IAW DC-8 SRM. FABRICATED AND INSTALLED REPAIR STRAPS IAW FAA APPROVED TIMCO DER ENGINEERING SKETCH REO-05175.

Part: FRAME — CORRODED (BS 1060)

DURING A MAINTENANCE VISIT, FOUND FRAME FLANGE WITH CORROSION DAMAGED BEYOND LIMITS IAW DC-8 SRM AT STA 1060 AND LONGERON 26 RIGHT. REMOVED DAMAGED SECTION, TREATED AREA IAW DC-8 SRM 51-1-8. FABRICATED AND INSTALLED REPAIR STRAPS IAW FAA APPROVED TIMCO DER ENGINEERING SKETCH REO-05187.

Part: VANE — WORN (RT TE FLAP)

DURING A MAINTENANCE VISIT, FOUND RIGHT WING, OUTBOARD SLOT VANE ATTACHMENT HOLES WORN AND OUT OF ROUND. REMOVED DAMAGED SECTIONS, FABRICATED AND INSTALLED REPAIR IAW FAA APPROVED TIMCO DER ENGINEERING SKETCH REO-05160.

Part: FITTING — GOUGED (RT TE FLAP)

DURING A MAINTENANCE VISIT, FOUND RIGHT WING, FLAP, EXHAUST GATE ACTUATING FITTING GOUGED BEYOND LIMITS IAW DC-8 SRM. REMOVED DAMAGE, INSTALLED REPAIR IAW FAA APPROVED TIMCO DER ENGINEERING SKETCH REO-05157.

Part: DOOR FRAME — MISDRILLED (BS 474.)

DURING A MAINTENANCE VISIT FOUND R1 DOOR JAMB FRAME WITH MISDRILLED HOLE, AT STA 474.347. REMOVED DAMAGED SECTION, TREATED AREA IAW DC-8 SRM 51-1-8. FABRICATED AND INSTALLED REPAIR DOUBLER IAW FAA APPROVED TIMCO DER ENGINEERING SKETCH REO-05138.

Part: FRAME — MISDRILLED (BS 1080)

DURING A MAINTENANCE VISIT, FOUND FRAME WITH MISDRILLED HOLES, AT STA 1080 AND LONGERON 29 LEFT. REMOVED DAMAGED SECTION, TREATED AREA IAW DC-8 SRM 51-1-8. FABRICATED AND INSTALLED REPAIR DOUBLER IAW FAA APPROVED TIMCO DER ENGINEERING SKETCH REO-05133.

Part: PRESSURE PANEL — CORRODED (BS 60)

DURING A MAINTENANCE VISIT, FOUND PRESSURE PANEL WITH CORROSION DAMAGE BEYOND LIMITS IAW DC-8 SRM AT STA -60 AND BLL 30. REMOVED DAMAGED SECTION, TREATED AREA IAW DC-8 SRM 51-1-8. FABRICATED AND INSTALLED REPAIR DOUBLER IAW FAA APPROVED TIMCO DER ENGINEERING SKETCH REO-05143.

Part: LONGERON — CORROSION (BS 160)

DURING A MAINTENANCE VISIT, FOUND LONGERON 20 RIGHT WITH CORROSION DAMAGE BEYOND LIMITS IAW DC-8 SRM AT STA 160. REMOVED DAMAGED SECTION, TREATED AREA IAW DC-8 SRM 51-1-8. FABRICATED AND INSTALLED REPAIR SPLICE IAW FAA APPROVED TIMCO DER ENGINEERING SKETCH REO-05147.

Part: PRESSURE PANEL — CORRODED (BS 15-29)

DURING A MAINTENANCE VISIT, FOUND PRESSURE PANEL WITH CORROSION DAMAGE BEYOND LIMITS IAW DC-8 SRM AT STA -15 TO STA -29 AND BLR 30. REMOVED DAMAGED SECTION, TREATED AREA IAW DC-8 SRM 51-1-8. FABRICATED AND INSTALLED REPAIR DOUBLER IAW FAA APPROVED TIMCO DER ENGINEERING SKETCH REO-05144.

Part: FRAME — CORRODED (BS 1140)

DURING A MAINTENANCE VISIT FOUND FRAME FLANGE WITH CORROSION DAMAGE BEYOND LIMITS IAW DC-8 SRM, AT STA 1140 AND LONGERON 35 LEFT. REMOVED DAMAGED SECTION, TREATED AREA IAW DC-8 SRM 51-1-8. FABRICATED AND INSTALLED REPAIR STRAP IAW FAA APPROVED TIMCO DER ENGINEERING SKETCH REO-05132.

Part: SKIN — DENTED (RUDDER)

DURING A MAINTENANCE VISIT, FOUND RUDDER, LEFT SIDE, SKIN GOUGE/DENTED, AT STA=XR 90. REMOVED DAMAGED SECTION, TREATED AREA IAW DC-8 SRM 51-1-8. FABRICATED AND INSTALLED REPAIR DOUBLER IAW FAA APPROVED TIMCO DER ENGINEERING SKETCH REO-05119.

Part: ANGLE — CORRODED (FUSELAGE)

DURING A MAINTENANCE VISIT, FOUND FLOORBEAM ATTACHMENT ANGLE WITH CORROSION DAMAGED BEYOND LIMITS IAW DC-8 SRM AT STA 857 BLL 16 AND WL -1. REMOVED DAMAGED SECTION, TREATED AREA IAW DC-8 SRM 51-1-8. FABRICATED AND INSTALLED REPAIR IAW FAA APPROVED TIMCO DER ENGINEERING SKETCH REO-05125.

Part: SKIN — GOUGED (LT TE FLAP)

DURING A MAINTENANCE VISIT, FOUND LEFT WING OUTBOARD FLAP WEDGE HAD PREVIOUS BLENDOUT ON TOP INBOARD CORNER AT THE ATTACH SEAM GOUGED, BEYOND LIMITS IAW DC-8 SRM. REMOVED DAMAGED SECTION, TREATED AREA IAW DC-8 SRM 51-1-8. FABRICATED AND INSTALLED REPAIR DOUBLER IAW FAA APPROVED TIMCO DER ENGINEERING SKETCH REO-05117.

Part: DOUBLER — CORRODED (FUSELAGE)

DURING A MAINTENANCE VISIT FOUND FRAME DOUBLER WITH CORROSION DAMAGE, AND WITH MISDRILLED HOLES. REMOVED PREVIOUS DOUBLER REPAIR, TREATED AREA IAW DC-8 SRM 51-1-8. FABRICATED AND INSTALLED NEW DOUBLER REPAIR IAW FAA APPROVED TIMCO DER ENGINEERING SKETCH REO-05106.

Part: SKIN — DAMAGE (BS 250)

DURING CARGO LOADING, K LOADER STRUCK AIRCRAFT FUSELAGE SKIN AT STA 250 AND LONGERON 26 LEFT. DAMAGE IS 2 INCHES BY 3 INCHES, AND 1.250 INCHES ABOVE STATIC PORT. *S/D* AIRCRAFT WAS FERRIED TO KGSO FOR INSPECTION. REMOVED DAMAGE, FABRICATED AND INSTALLED REPAIR DOUBLER IAW FAA APPROVED TIMCO DER ENGINEERING SKETCH REO-04984.

Part: FLAP ACTUATOR — MALFUNCTIONED (LT TE FLAP)

UPON FLAP EXTENSION PAST FLAPS 15 DEG FLAPS SPLIT 6-8 DEG. TRIED TO EXTEND FLAPS SEVERAL TIMES AFTER RETRACTING FLAPS FIRST. FLAPS CONTINUE TO SPLIT PAST 15 DEG, AIRCRAFT ROLLED TO THE LEFT. REMOVED AND REPLACED LEFT WING OUTBOARD FLAP ACTUATOR/LINK ASSY AND LINK BOLT, IAW MM 27-51-9, OPS CHECK NORMAL.

Part: ENGINE — MALFUNCTIONED (NR 4)

NR 4 ENGINE VERY SLOW TO SPOOL AT TAKEOFF AND COULD NOT MAINTAIN MAX POWER DUE HIGH EGT. IN CRUISE EGT AVERAGED 46DEG HIGHER. DURING GROUND RUN OF NR 4 ENGINE, ALL INDICATIONS WERE NORMAL. NO DEFECTS NOTED AT TAKEOFF POWER OR OTHER ENGINE SETTINGS. OKAY FOR CONTINUED SERVICE.

Part: DIAPHRAGM — RUPTURED (HYD ACCUMULATOR)

INSTALLED NEW DIAPHRAGM AND ACCUMULATOR INSTALLED IN AIRCRAFT 6-5-61. ACCUMULATOR REMOVED 7-25-96 FOR INTERNAL FAILURE. FOUND DIAPHRAGM RUPTURED AFTER 225 HOURS TIME IN SERVICE.

Part: BULKHEAD CAP — CORRODED (BS 70)

LOWER BULKHEAD CAP AT Y=70, BETWEEN LONGERONS 31R AND 33R CORRODED AND CRACKED. LOWER BULKHEAD REPAIRED BY DOUBLER REPAIR SECURED WITH HL329-6 HI-LOCKS IAW REO 01903, SRM 51-1-20D, AND TREATED IAW SRM 51-1-8.

Part: BULKHEAD CAP — CORRODED (BS 8)

LOWER BULKHEAD CAP AT Y=8, BETWEEN LONGERONS 32R AND 33R CORRODED AND CRACKED. LOWER BULKHEAD CAP REPAIRED BY DOUBLER REPAIR IAW REO 01903, SRM 51-1-20D AND TREATED IAW DC-8 SRM 51-1-8.

Part: RETRACT PIN — SHEARED (RT MLG)

KDAY/KRDU - FLT 028 - ON TAKEOFF ROLL AT KDAY, AIRCRAFT YAWED TO LEFT. ON GEAR RETRACTION, DOOR LIGHT AND LANDING GEAR UNSAFE LIGHT STAYED ON ALONG WITH RT ALT GEAR DOOR LIGHT. GEAR PLACED DOWN AND ALL INDICATIONS WERE NORMAL. RETURNED TO KDAY. MAINTENANCE FOUND RT MAIN GEAR RETRACT PIN SHEARED OFF STRUT. PREPARED ACFT TO FERRY FOR REPAIRS. SD 05-05-95 - ZANTOP MAINTENANCE REMOVED AND REPLACED RT RETRACT PIN AND REMOVED MINOR CORROSION FROM PIN BOSS IAW MM 32-30-0 AND EWA MAINTENANCE AUTHORIZATION (M.A.) A-3210-01:02. OPS CHECK GOOD.

Part: RETRACT PIN — SHEARED (RT MLG STRUT)

KDAY-KRDU - ON TAKEOFF ROLL AT KDAY AIRCRAFT YAWED TO LEFT. ON GEAR RETRACTION DOOR LIGHT AND LANDING GEAR UNSAFE LIGHT STAYED ON ALONG WITH RT ALT GEAR DOOR LIGHT. GEAR PLACED DOWN AND ALL INDICATIONS WERE NORMAL. RETURNED TO KDAY. MAINTENANCE FOUND RT MAIN GEAR RETRACT PIN SHEARED OFF STRUT. PREPARED AIRCRAFT TO FERRY FOR REPAIRS.