N865F

Part: SKIN — CRACKED (ZONE 100) · airframe 80,720 hrs · 27,266 cycles

FUSELAGE SKIN CRACKED AT FS 8.000 AIR CONDITIONING CONDENSER EXHAUST DOOR CUTOUT UPPER AFT CORNER CRACK LENGTH APPROX 2".

Part: LONGERON — CRACKED (ZONE 100) · airframe 80,720 hrs · 27,266 cycles

LONGERON 35RIS CRACKED FROM STA 1343-1348 (5").

Part: ATTACH FITTING — CRACKED (ZONE 200) · airframe 80,720 hrs · 27,266 cycles

FUSELAGE FRAME TO CUSP FITTING CRACKED APPROX 5" AT STA 717.75.

Part: LONGERON — CRACKED (BS 1343-1349) · airframe 80,720 hrs · 27,266 cycles

LONGERON 34R IS CRACKED FROM STA 1343-1349.

Part: SKIN — CRACKED (BS 1756-1760) · airframe 79,807 hrs · 26,956 cycles

FOUND 2 EACH CRACKS IN FUSELAGE SKIN APPROX AT STA 1760 LT SIDE MID POINT VERTICALLY. ONE CRACK APPROX 2 INCHES LONG BETWEEN L13L AND L14L AND ONE CRACK APPROX 1 INCH LONG BETWEEN L14L AND L15L. CRACKS WILL BE REPAIRED IAW DWG 53-09405-1.

Part: SKIN — DAMAGED (BS 365-377) · airframe 79,779 hrs · 26,947 cycles

FUSELAGE DAMAGED BY FORKLIFT BETWEEN LONGERON 26 AND 27 AT STA 370. REPAIRED IAW DWG 53-09382-1.

Part: COMPRESSOR — STALLED (NR 1 ENGINE) · airframe 79,272 hrs · 26,693 cycles

NR 1 ENGINE COMPRESSOR STALLED AT 1000 FT AND WAS SECURED. ENGINE WAS RELIT PRIOR TO LANDING. ENGINE POWER ASSURANCE RUN ON GROUND DETECTED NO DISCREPANCIES.

Part: STRINGER — CORRODED (FUSELAGE) · airframe 78,924 hrs · 26,501 cycles

COCKPIT SUB FLOOR STRINGER DOUBLER WITH CORROSION AT STA -117.00 CPCP 455R 0552.

Part: PANEL — CORRODED (COCKPIT) · airframe 78,924 hrs · 26,501 cycles

COCKPIT SUBFLOOR PRESSURE PANEL EXISTING REPAIR WITH CORROSION STA -17.00 LBL 50".

Part: ANGLE — CORRODED (FUSLEAGE) · airframe 78,924 hrs · 26,501 cycles

COCKPIT SUBFLOOR ANGLE WITH CORROSION AT STA 32.000 L-21R CPCP455R 0552.

Part: UNKNOWN — CORRODED (COCKPIT) · airframe 78,924 hrs · 26,501 cycles

FOUND COCKPIT SUBFLOOR WITH CORROSION AT STA.-67.00 L21L CPCP455L 0552.

Part: UNKNOWN — CORRODED (BS 67) · airframe 78,924 hrs · 26,501 cycles

COCKPIT SUBFLOOR INNER AREA WITH CORROSION AT STA 67 L-21R CPCP 455R 0552.

Part: ACCESS DOOR — CORRODED (LT WING) · airframe 78,924 hrs · 26,501 cycles

LT WING XFS 836 OUTBD L/E INNER LOWER SECTION ACCESS DOOR NR 517B JAMB WITH CORROSION CPCP 107L 0552.

Part: SKIN — CORRODED (RUDDER) · airframe 78,924 hrs · 26,501 cycles

RUDDER ZR 168.656 LT EXTERNAL SKIN WITH CORROSION CPCP 6820 0551.

Part: BULKHEAD — CRACKED (BS 1766 L11L) · airframe 78,924 hrs · 26,501 cycles

AFT FLAT PRESSURE BULKHEAD WEB STA 1766 L11L CRACK CPCP 5730 0551.

Part: BULKHEAD — CRACKED (BS 1766 L11-12R) · airframe 78,924 hrs · 26,501 cycles

AFT FLAT PRESSURE BULKHEAD WEB STA 1766 L-11R-12R CRACK CPCP 5730 0551.

Part: DOWNLOCK SWITCH — CORRODED (RT MLG) · airframe 78,718 hrs · 26,384 cycles

ON LANDING AT KYIP, RT MAIN GEAR DOWN AND SAFE GREEN LIGHT WOULD NOT ILLUMINATE. FLEW BY TOWER TO SEE IF LANDING GEAR WAS DOWN. EMERGENCY VEHICLES STANDING BYE ON LANDING. AFTER ENGINE SHUTDOWN LIGHT CAME ON. COMPLIED WITH MURRAY ABNORMAL CHECK LIST. REMOVED AND REPLACED DEFECTIVE RT MLG DOWNLOCK SWITCH IAW DC8 MM 32-60-0 AND MURRAY AIR GMM CHAPTER 4 PAGE 4-2-4 LANDING GEAR (G). SYSTEM OPS CHECK GOOD.

Part: DOWNLOCK SWITCH — CORRODED (RT MLG) · airframe 78,718 hrs · 26,384 cycles

ON LANDING AT KYIP-RT MAIN GEAR DOWN AND SAFE GREEN LIGHT WOULD NOT ILLUMINATE. FLEW BY TOWER TO SEE IF LANDING GEAR WAS DOWN. EMERGENCY VEHICLES STANDING BYE ON LANDING. AFTER ENGINE SHUTDOWN LIGHT CAME ON, COMPLIED WITH MURRAY ABNORMAL CHECK LIST. REMOVED AND REPLACED DEFECTIVE RT MLG DOWNLOCK SWITCH IAW DC8 MM 32-60-0 AND MURRAY AIR GMM CHAPTER 4 PAGE 4-2-4 LANDING GEAR (G). SYSTEM OPS CHECK GOOD.

Part: FRAME — CORRODED (FUSELAGE) · corrosion level 2 · airframe 78,474 hrs · 26,181 cycles

DURING COCKPIT AREA CORROSION INSPECTION PER AD92-22-07 (CPCP 5), LEVEL 2 CORROSION WAS FOUND ON RT FRAME AT FS -67, L23R AND ADJACENT AREA. AFFECTED AREA IS IN PROCESS OF BEING REPAIRED.

Part: FRAME — CORRODED (FUSELAGE) · corrosion level 2 · airframe 78,474 hrs · 26,181 cycles

DURING COCKPIT AREA CORROSION INSPECTION PER AD92-22-07 (CPCP 5), LEVEL 2 CORROSION WAS FOUND ON RT FRAME AT FS -67, L23R AND ADJACENT AREA. AFFECTED AREA IS IN PROCESS OF BEING REPAIRED.

Part: TRANSFORMER — BROKEN (COCKPIT LIGHTS) · airframe 78,378 hrs · 26,114 cycles

PILOTS OVERHEAD PANEL LIGHTS INOP, GLOW FUSE ON FOLLOWED BY SMOKE.

Part: CONNECTOR — DIRTY (LT MLG) · airframe 77,744 hrs · 25,851 cycles

LEFT MAIN GEAR DOWN AND LOCK SAFE LIGHTS DID NOT COME ON. PERFORMED ABNORMAL CHECKLIST. AFTER LANDING LIGHT CAME ON.

Part: UPLOCK — OUT OF RIG (RT MLG) · airframe 77,744 hrs · 25,851 cycles

AFTER MAIN LANDING GEAR RETRACTION GEAR HANDLE IN THE UP POSITION, DOOR NOT LATCH LIGHT REMAINS ON. POSITION GEAR HANDLE IN THE UP-LATCH CHECK POSITION, DOOR NOT LATCHED LIGHT, GEAR NOT LATCHED LIGHT AND ALTERNATE RIGHT HAND DOOR NOT LATCHED LIGHT REMAINS ON, PUT FLAPS TO 23 DEGREES POSITION AND GEAR HANDLE IN THE UP POSITION, ALL LIGHTS OUT.

Part: FITTING — CRACKED (LT WING) · airframe 76,922 hrs · 25,385 cycles

DURING FUEL TANK MAINTENANCE DETECTED LT WING NR 2 MAIN FUEL TANK CRACKED STRINGER END FITTING AT STA.XRS 78,S61.

Part: FRAME — CRACKED (FUSELAGE) · airframe 76,922 hrs · 25,385 cycles

DURING CPCP TASK NR 5570-0551 FORWARD LOWER CARGO COMPARTMENT FORWARD FRAME FITTING CRACKED AT FS299 BETWEEN LONGERON 32R AND 33R.

Part: SKIN — CORRODED (FUSELAGE) · corrosion level 2 · airframe 76,922 hrs · 25,385 cycles

DURING CPCP TASK 5600-0551 FOUND AFT ACCESSORY COMPARTMENT FS 1640 BETWEEN LONGERON 32R AND 33R. FASTENERS PULLING THROUGH FUSELAGE SKIN AND IDENTIFIED AS LEVEL 2 CORROSION.

Part: HINGE FITTING — CRACKED (LT AILERON) · airframe 76,922 hrs · 25,385 cycles

VISUALLY DETECTED LT OB AILERON CENTER HINGE FITTING CRACKED.

Part: FITTING — CORRODED (CARGO DOOR) · airframe 76,922 hrs · 25,385 cycles

EXTERNAL FUSELAGE SKIN HAS A BULGE AT FS 315 LONGERON 33R FOUND DURING C-CHECK. FOUND FORWARD LOWER BELLY CARGO (A PIT) DOOR STRUCTURE FITTING CORRODED-TASK CARD #0323.

Part: FITTING — CORRODED (CARGO DOOR) · airframe 76,922 hrs · 25,385 cycles

EXTERNAL FUSELAGE SKIN HAS A BULGE AT FS 324 LONGERON 33R FOUND DURING C-CHECK. FOUND FORWARD LOWER BELLY CARGO (A-PIT) DOOR STRUCTURE FITTING CORRODED.

Part: FRAME — CORRODED (FUSELAGE) · corrosion level 2 · airframe 76,922 hrs · 25,385 cycles

DURING CPCP TASK 5570-0551 FORWARD LOWER CARGO COMPARTMENT CIRCUMFERENTIAL FRAME LOWER LEG CORRODED AT FS 80 BETWEEN LONGERON 36R AND 35R AND IDENTIFIED AS LEVEL 2 CORROSION.

Part: SKIN — CRACKED (NR 2 PYLON) · airframe 76,922 hrs · 25,385 cycles

VISUALLY DETECTED CRACK IN PREVIOUS DOUBLER LEFT WING LEADING EDGE AT NR 2 ENGINE PYLON CUTOUT.

Part: CLIP — CRACKED (FUSELAGE) · corrosion level 2 · airframe 76,922 hrs · 25,385 cycles

DURING CPCP TASK 5690-0551 AFT CARGO FS 1210 LONGERON 33R CORRODED AND CRACKED 2 EACH FITTING CLIPS AND INDENTIFED AS LEVEL 2 CORROSION

Part: DUCT — DELAMINATED (NR 2 ENGINE) · airframe 76,922 hrs · 25,385 cycles

NR 2 ENGINE LT ENGINE COWL TRANSITION DUCT DELAMINATED ON INBOARD SIDE.

Part: DOUBLER — CRACKED (FUSELAGE) · corrosion level 2 · airframe 76,922 hrs · 25,385 cycles

DURING CPCP TASK 5570-0551 FORWARD LOWER CARGO COMPARTMENT INTERIOR SKIN DOUBLER CORRODED AND CRACKED AT FS270 LONGERON 31L AND IDENTIFIED AS LEVEL 2 CORROSION.

Part: FITTING — CRACKED (FUSELAGE) · corrosion level 2 · airframe 76,922 hrs · 25,385 cycles

DURING CPCP TASK 5590-0551 AFT CARGO FS 1160 LONGERON 35R AND 34R FITTING CRACKED AND IDENTIFIED AS LEVEL 2 CORROSION.

Part: LONGERON — CORRODED (FUSELAGE) · corrosion level 2 · airframe 76,922 hrs · 25,385 cycles

DURING CPCP TASK NR 5570-0551 FORWARD LOWER CARGO COMPARTMENT CORROSION ON LONGERON 30L AT FS 270 AND IDENTIFIED AS LEVEL 2 CORROSION.

Part: FITTING — CORRODED (FUSELAGE)

EXTERNAL FUSELAGE SKIN HAS A BULGE AT FS315, LONGERON NR 33R. FOUND DOOR STRUCTURE FITTING CORRODED (FS 315, LONGERON 33R). REMOVED AND REPLACED FITTING IAW DC8, SRM 53-2-0, FIG 2D. CORROSION REMOVED IAW DC SRM 51-1-8.

Part: SKIN — CRACKED (FUSELAGE) · airframe 76,557 hrs · 25,163 cycles

DURING COMPLIANCE WITH A/D 2000-20-08 AND REMOVAL OF TEMPORARY EXTERNAL REPAIR AT LEFT FRONT PAX ENTRANCE DOOR UPPER FORWARD CORNER, VISUALLY DETECTED ONE ADDITIONAL FUSELAGE SKIN CRACK TERMINATING AT RIVET FASTENER 3 FASTENERS UP FROM PREVIOUS CRACK REPAIRED BY CUTOUT AND FILLER METHOD. EXTENDED CUTOUT AND FILLER IN FUSELAGE SKIN"REPAIR ZONE"TO REMOVE SKIN CRACK.INSTALLED PREVENTATIVE REPAIR I/A/W DAC S/B 53-075 & SERVICE REWORK DRAWING SR08530021.

Part: SKIN — CRACKED (FUSELAGE) · airframe 76,520 hrs · 25,142 cycles

DURING B-4 CHECK, FOUND RIVET POPPED AT FUSELAGE STATION -12, LEFT LONGERON NR 30. INVESTGATION REVEALED STRESS CRACK IN FUSELAGE SKIN AT RIVET HEAD. REMOVED DAMAGE SKIN, CLEANED AND TREATED IAW DC8 SRM 51-1-8 AND REPAIRED IAW DC8 SRM 53-2-0 /51-1-21 AND REFINISHED.

Part: FITTING — CORRODED (FUSELAGE) · airframe 76,397 hrs · 25,096 cycles

DURING COMPLIANCE OF BOEING S/B 53-61 R4 DURING DISASSEMBLY FOR REPLACEMENT OF CRACKED RT MLG SUPPORT FITTING DURING DISASSEMBLY FOUND RT LONGERON NR 24 FUSELAGE FRAME FITTING CORRODED.

Part: SUPPORT FITTING — CRACKED (FUSELAGE) · airframe 76,397 hrs · 25,096 cycles

DURING COMPLIANCE BOEING S/B DC8-53-061R4 VISUALLY DETECTED RT MLG SUPPORT FITTING CRACKED IN TWO PLACES. UPPER AREA .875 INCH AND AFT UPPER AREA CRACK EXTENDING UP AND OUT INTO SUPPORT FITTING FLANGE.

Part: SUPPORT FITTING — CRACKED (FUSELAGE) · airframe 76,397 hrs · 25,096 cycles

DURING COMPLIANCE WITH BOEING S/B DC8-53-61 R4, VISUALLY DETECTED LEFT HAND WHEEL WELL TRAPEZOID FITTING CRACKED AND EXTENDING FROM BOLT HOLE APPROXIMATELY 2.25 INCHES.

Part: FLOORBEAM — CORRODED (FUSELAGE) · corrosion level 2 · airframe 76,322 hrs · 25,051 cycles

DURING CPCP 18 MONTH INSPECTION, AFT ACCESSORY COMPARTMENT INTERIOR. DETECTED LEVEL 2 CORROSION OF UPPER TEE OF FORWARD FLANGE OF FLOORBEAM 11.5 INCHES INBOARD OF RIGHT FUSELAGE CUSP LINE 1.75 INCHES LONG.

Part: FITTING — CRACKED (THRUST REVERSER) · airframe 76,161 hrs · 24,960 cycles

ON POST FLIGHT INSPECTION WITH NR 4 ENGINE THRUST REVERSER (T/R) TRANSLATING RING EXTENDED FOUND LOWER AFT T/R TRACK SUPPORT FITTING MOUNTED ON BOTTOM CENTER LINE OF ENGINE EXHAUST NOZZLE OUTBOARD FLANGE CRACKED THROUGHOUT BOLT HOLE.

Part: SPAR CAP — CRACKED (LT WING) · airframe 76,152 hrs · 24,953 cycles

DURING COMPLIANCE OF MCDONNELL DOUGLAS DC-8 S/B 57-90 R5 (NPRM 99-NM-60-AD) DETECTED CRACK ATLOWER FORWARD SPAR AT ATTACH FASTENERS STA XFS 524. CRACK BEYOND S/B 57-90 R5 REPAIR LIMITS.

Part: COWLING — CORROSION (NR 4 ENGINE)

DURING A MAINTENANCE VISIT, FOUND CORROSION DAMAGE TO NR 4 ENGINE, RIGHT SIDE AFT FAN COWLING, ZEE CLOSE-OUT. REMOVED DAMAGED SECTION, TREATED AREA IAW DC-8 SRM 51-1-8. FABRICATED AND INSTALLED REPAIR DOUBLER IAW FAA APPROVED DER TIMCO ENGINEERING SKETCH REO-04439.

Part: COWLING — CORRODED (NR 1 ENGINE)

DURING A MAINTENANCE VISIT, FOUND CORROSION DAMAGE TO NR 1 ENGINE RIGHT SIDE FAN COWLING, ZEE CLOSE-OUT. REMOVED DAMAGED SECTION, TREATED AREA IAW DC-8 SRM 51-1-8. FABRICATED AND INSTALLED REPAIR DOUBLER IAW FAA APPROVED DER TIMCO ENGINEERING SKETCH REO-04480.

Part: COWL — WORN (NR 1 ENGINE)

DURING A MAINTENANCE VISIT, FOUND NR 1 ENGINE FAN COWLING, ZEE CLOSE-OUT WORN. FABRICATED AND INSTALLED NEW ZEE CLOSE-OUT, (P/N 575716-503), IAW FAA APPROVED DER TIMCO ENGINEERING SKETCH REO-04413.

Part: SKIN — DENTED (BS 110)

DURING A MAINTENANCE VISIT, FOUND DENT TO FUSELAGE SKIN AT STA 114 AND LONGERON 23 LEFT. FABRICATED AND INSTALLED REPAIR DOUBLER IAW FAA APPROVED DER TIMCO ENGINEERING SKETCH REO-04496.

Part: FRAME — DAMAGED (BS 272)

DURING A MAINTENANCE VISIT, FOUND TOOL DAMAGE TO FRAME FLANGE RADIUS, AT STA 272 BETWEEN LONGERONS 32 RIGHT AND 33 RIGHT. FABRICATED AND INSTALLED REPAIR DOUBLER IAW FAA APPROVED DER ENGINEERING SKETCH REO-04411.

Part: FILLET — CORROSION (RT WING)

DURING A MAINTENANCE VISIT, FOUND FILLET PANEL CORRODED RIGHT WING. FILLET PANEL DAMAGED BEYOND SRM REPAIR, FABRICATED AND INSTALLED NEW FILLET PANEL IAW FAA APPROVED DER TIMCO ENGINEERING SKETCH REO-04463.

Part: PLANK — CORROSION (BS 1580-1689)

DURING A MAINTENANCE VISIT, FOUND FLOOR PLANK EDGE CORRODED BEYOND LIMITATIONS IAW DC-8 SRM, AT STA 1580 TO 1689. REMOVED DAMAGED SECTION, TREATED AREA IAW DC-8 SRM 51-1-8. FABRICATED AND INSTALLED REPAIR DOUBLER IAW FAA APPROVED DER TIMCO ENGINEERING SKETCH REO-04415.

Part: FRAME — MISDRILLED (BS 1140)

DURING A MAINTENANCE VISIT, FOUND TOOL DAMAGE TO FRAME FLANGE AT STA 1140 AND LONGERON 36. FABRICATED AND INSTALLED REPAIR DOUBLER IAW FAA APPROVED DER TIMCO ENGINEERING SKETCH REO-04425.

Part: FLOORBEAM — CORROSION (BS 1726)

DURING A MAINTENANCE VISIT, FOUND CORROSION DAMAGE TO FLOORBEAM AT STA 1726.656 AND BL 20 RIGHT. REMOVED DAMAGED SECTION, TREATED AREA IAW DC-8 SRM 51-1-8. FABRICATED AND INSTALLED SPLICE REPAIR IAW FAA APPROVED DER TIMCO ENGINEERING SKETCH REO-04549.

Part: FILLET — CORRODED (LT WING)

DURING A MAINTENANCE VISIT, FOUND CORROSION DAMAGE TO LEFT WING FILLET PANEL, NR 162. REMOVED FILLET PANEL FOR REPLACEMENT, TREATED AREA IAW DC-8 SRM 51-1-8. FABRICATED AND INSTALLED NEW FILLET PANEL IAW FAA APPROVED DER TIMCO ENGINEERING SKETCH REO-04608.

Part: SKIN — CRACKED (WS 207)

DURING A MAINTENANCE VISIT, FOUND LEFT WING, LEADING EDGE, SLANT CRACKED AT XFS=207.5. FABRICATED AND INSTALLED REPAIR DOUBLER IAW FAA APPROVED DER TIMCO ENGINEERING SKETCH REO-04400.

Part: SPAR CAP — CRACKED (WS 519)

DURING A MAINTENANCE VISIT FOUND RIGHT WING, FORWARD SPAR CAP LOWER CRACKED AT XFS=519. FABRICATED AND INSTALLED SPLICE REPAIR IAW FAA APPROVED DER TIMCO ENGINEERING SKETCH REO-04464.

Part: PANEL — MISDRILLED (LT WING)

DURING A MAINTENANCE VISIT, FOUND LEFT WING TRAILING EDGE, PANEL MISDRILLED HOLE, (P/N 5611015-502). FABRICATED AND INSTALLED REPAIR DOUBLER IAW FAA APPROVED DER TIMCO ENGINEERING SKETCH REO-04513.

Part: BRACKET — CORRODED (E/E COMPT)

DURING A MAINTENANCE VISIT FOUND FAN ATTACHMENT MOUNT BRACKET CORRODED IN VARIOUS AREAS, REPLACEMENT PART NOT AVAILABLE. REMOVED BRACKET, TREATED AREA IAW DC-8 SRM 51-1-8. CLEANED BRACKET BY GLASS BEADED AREAS TO REMOVE CORROSION. USED FAA TIMCO DER ENGINEERING SKETCH REO-04501 FOR MATERIAL SPECIFICATIONS.

Part: SKIN — CORRODED (BS 70)

DURING A MAINTENANCE VISIT, FOUND FUSLAGE SKIN CORRODED AT STA 70 BETWEEN LONGERONS 28 RIGHT AND 34 RIGHT. REMOVED DAMAGED SECTION, TREATED AREA IAW DC-8 SRM 51-1-8. FABRICATED AND INSTALLED REPAIR DOUBLER IAW FAA APPROVED DER TIMCO ENGINEERING SKETCH REO-04486.

Part: RIB — CRACKED (WS 57.75)

DURING A MAINTENANCE VISIT, FOUND LEFT WING LEADING EDGE, RIB UPPER CAP CRACKED AT XFS=57.750. FABRICATED AND INSTALLED SPLICE REPAIR IAW FAA APPROVED DER TIMCO ENGINEERING SKETCH REO-04474.

Part: FLOORBEAM — DAMAGED (BS 857)

DURING A MAINTENANCE VISIT, FOUND FLOORBEAM WITH TOOL DAMAGE AT STA 857.188 BL 25 RIGHT. FABRICATED AND INSTALLED REPAIR DOUBLER IAW FAA APPROVED DER TIMCO ENGINEERING SKETCH REO-04472.

Part: SPAR CAP — MISDRILLED (WS 304)

DURING A MAINTENANCE VISIT, FOUND TOOL DAMAGE TO LEFT WING, FRONT SPAR CAP AT XFS=304. FABRICATED AND INSTALLED SPLICE REPAIR IAW FAA APPROVED DER TIMCO ENGINEERING SKETCH REO-04456.

Part: SKIN — CORROSION (BS 80)

DURING A MAINTENANCE VISIT, FOUND CORROSION ON FUSELAGE SKIN AT STA 80 TO STA 90 BETWEEN LONGERONS 27 RIGHT AND 28 RIGHT. REMOVED DAMAGED SECTION, TREATED AREA IAW DC-8 SRM 51-1-8. FABRICATED AND INSTALLED REPAIR DOUBLER IAW FAA APPROVED DER TIMCO ENGINEERING SKETCH REO-04506.

Part: PANEL — DAMAGED (LT TE FLAP)

DURING A MAINTENANCE VISIT, NEWLY FABRICATED LEFT SIDE INBOARD FLAP FILLET PANEL NEEDS REPLACEMENT OF BEADED SECTION WITH FLAT SHEET. BEADED SECTION OF LEFT SIDE INBOARD FLAP FILLET PANEL, WAS PLACED WITH FLAT SHEET IAW FAA APPROVED DER TIMCO ENGINEERING SKETCH REO-04449.

Part: SKIN — CORROSION (WS 820)

DURING A MAINTENANCE VISIT, FOUND LEFT WING, LEADING EDGE WITH CORROSION DAMAGE AT XFS=820. REMOVED DAMAGED SECTION, TREATED AREA IAW DC-8 SRM 51-1-8. FABRICATED AND INSTALLED REPAIR DOUBLER IAW FAA APPROVED DER ENGINEERING SKETCH REO-04393.

Part: LONGERON — CORROSION (BS 1160)

DURING A MAINTENANCE VISIT, FOUND LONGERON 34 RIGHT WITH CORROSION DAMAGE AT STA 1160. REMOVED DAMAGED SECTION, TREATED AREA IAW DC-8 SRM 51-1-8. FABRICATED AND INSTALLED SPLICE REPAIR IAW FAA APPROVED DER TIMCO ENGINEERING SKETCH REO-04437.

Part: SKIN — GOUGED (LT TE FLAP)

DURING A MAINTENANCE VISIT, FOUND RIGHT WING OUTBOARD FLAP, LOWER SKIN GOUGED AT XRS=240. FABRICATED AND INSTALLED REPAIR DOUBLER IAW FAA APPROVED DER TIMCO ENGINEERING SKETCH REO-04441.

Part: FITTING — CORROSION (BS 123)

DURING A MAINTENANCE VISIT, FOUND LOWER CARGO DOOR JAMB, ZEE FITTING CORRODED BEYOND LIMITATIONS IAW DC-8 SRM AT STA 123 AND LONGERON 33 LEFT. FABRICATED AND INSTALLED NEW FITTING IAW FAA APPROVED DER TIMCO ENGINEERING SKETCH REO-04484.

Part: SKIN — HOLE (BS 1726)

DURING A MAINTENANCE VISIT REMOVED DRAIN MAST, NO LONGER REQUIRED AT STA 1726.656 BETWEEN LONGERONS 28 LEFT AND 30 LEFT. FABRICATED AND INSTALLED BLANKED PLATES TO COVER HOLES IAW FAA APPROVED DER TIMCO ENGINEERING SKETCH REO-0442.

Part: SKIN — MISDRILLED (LT WING)

DURING A MAINTENANCE VISIT, FOUND TOOL DAMAGE TO LEFT WING, LEADING EDGE LOWER SKIN AT XFS=285 AND XFS=526. FABRICATED AND INSTALLED REPAIR DOUBLER TO XFS=285 AND 526, IAW FAA APPROVED DER TIMCO ENGINEERING SKETCH REO-04457.

Part: ACCESS PANEL — MISDRILLED (LT WING)

DURING A MAINTENANCE VISIT, FOUND TOOL DAMAGE TO LEFT WING ACCESS PNL: 506B. FABRICATED AND INSTALLED REPAIR DOUBLER IAW FAA APPROVED DER TIMCO ENGINEERING SKETCH REO-04436.

Part: FITTING — CHAFED (WS 98)

DURING A MAINTENANCE VISIT, FOUND LEFT WING CANOE FITTING CHAFED AT STA 97.9. FABRICATED AND INSTALLED REPAIR IAW FAA APPROVED DER TIMCO ENGINEERING SKETCH REO-04453.

Part: SKIN — CRACKED (LT AILERON)

DURING A MAINTENANCE VISIT, FOUND LEFT WING AILERON CRACKED AT XA=621.625. FABRICATED AND INSTALLED SPLICE REPAIR IAW FAA APPROVED DER TIMCO ENGINEERING SKETCH REO-04435.

Part: FITTING — DAMAGED (BS 1170)

DURING A MAINTENANCE VISIT, FOUND BATHTUB, DOOR JAMB FITTING DAMAGED AT STA 1170. FABRICATED NEW FITTING IAW DAC DWG 3754930. ORIGINAL MATERIAL NOT AVAILABLE FOR PURCHASE, REO-04434 PROVIDED SUBSTITUTION 7075-T651 FOR 7075-T6.

Part: SEAT — CRACKED (COCKPIT)

DURING A MAINTENANCE VISIT, FOUND FIRST OBSERVER SEAT BACK CLOSE-OUT WEB CRACKED. CRACK ORIGINATED AT LIGHTNING HOLE AND ENDED AT EDGE. SRM DOES NOT GIVE A SPECIFIC REPAIR. FABRICATED AND INSTALLED REPAIR DOUBLER IAW FAA APPROVED DER TIMCO ENGINEERING SKETCH REO-04433.

Part: FRAME — CORROSION (BS 1060)

DURING A MAINTENANCE VISIT, FOUND FRAME WITH CORROSION DAMAGE AT 1060 BETWEEN LONGERONS 34 RIGHT AND 36. REMOVED DAMAGED SECTION, TREATED AREA IAW DC-8 SRM 51-1-8. FABRICATED AND INSTALLED SPLICE REPAIR IAW FAA APPROVED DER TIMCO ENGINEERING SKETCH REO-04417.

Part: SKIN — GOUGED (RT TE FLAP)

DURING A MAINTENANCE VISIT, FOUND RIGHT WING, FLAP SKIN GOUGED AT XRS=230.5. FABRICATED AND INSTALLED REPAIR DOUBLER IAW FAA APPROVED DER TIMCO ENGINEERING SKETCH REO-04407.

Part: SKIN — DAMAGED (BS 400/418)

DURING A MAINTENANCE VISIT, REMOVED DRAIN MAST, NO LONGER REQUIRED AT STA 400 AND STA 418 BETWEEN LONGERONS 35 RIGHT AND 36. FABRICATE AND INSTALLED BLANK-OFF PLATES TO COVER REMAINING HOLES IAW FAA APPROVED DER ENGINEERING SKETCH REO-04428.

Part: SKIN — CORROSION (BS 450)

DURING A MAINTENANCE VISIT, FOUND FUSELAGE, INTERNAL SKIN WITH CORROSION DAMAGE AT STA 450 BETWEEN LONGERONS 34 LEFT AND 35 LEFT. REMOVED DAMAGED SECTION, TREATED AREA IAW DC-8 SRM 51-1-8. FABRICATED AND INSTALLED REPAIR DOUBLER IAW FAA APPROVED DER TIMCO ENGINEERING SKETCH REO-04405.

Part: FRAME — CORROSION (BS 1020)

DURING A MAINTENANCE VISIT, FOUND FRAME WITH CORROSION DAMAGE AT STA 1020 BETWEEN LONGERONS 34 LEFT TO 34 RIGHT. REMOVED DAMAGE SECTION, TREATED AREA IAW DC-8 SRM 51-1-8. FABRICATED AND INSTALLED SPLICE REPAIR IAW FAA APPROVED DER TIMCO ENGINEERING SKETCH REO-04416.

Part: FAIRING — CHAFED (RT TE FLAP)

DURING A MAINTENANCE VISIT, FOUND RIGHT WING, FLAP TRAILING EDGE FAIRING CHAFED AT OUTBOARD SECTION. FABRICATED AND INSTALLED SPLICE REPAIR IAW FAA APPROVED DER ENGINEERING SKETCH REO-04420.

Part: CHANNEL — CRACKED (EXHAUST NOZZLE)

DURING A MAINTENANCE VISIT, FOUND EXHAUST NOZZEL AT 12 O'CLOCK POSITION HAD PREVIOUS REPAIR, AND INTERNAL CHANNEL CRACKED.

Part: SKIN — CRACKED (WS 326)

DURING A MAINTENANCE VISIT, FOUND LEFT WING, LEADING EDGE, LOWER SKIN CRACKED AT XFS=326. FABRICATED AND INSTALLED REPAIR DOUBLER IAW FAA APPROVED DER TIMCO ENGINEERING SKETCH REO-04378.

Part: PRESSURE IND — MALFUNCTIONED (NR 2/3 HYD SYST)

HYD OVER TEMP/AILERON AND RUDDER LIGHT CAME ON DURING FLT. BY-PASSED BOTH ENG PUMPS, THEN ONE AT A TIME (NOTED NO PRESS). HYD QTY NORMAL, AUX PUMP WORKED NORMAL. RAN NR 2 AND NR 3 ENGS CHECKED BOTH ENG HYD SYSTEMS PUMPS, NO DEFECTS NOTED. PRESSURES WERE NORMAL, TEMP WAS NORMAL, ALL LIGHTS NORMAL.

Part: SKIN — CRACKED (WS 69.5)

DURING A PREFLIGHT INSPECTION, FOUND RIGHT WING UPPER SKIN CRACKED AT XCW 69.5 AND STRINGER 1. FERRY FLIGHT FROM KATL TO KMCN FOR REPAIR.

Part: FIRE WARNING — MALFUNCTIONED (NR 2 ENGINE)

INTERMITTENT FIRE WARNING ON NR 2 ENG. SHUT BLEED AIR OFF ON NR 2, NO FURTHER WARNINGS, FIRE WARNING TEST GOOD. COULD NOT DUPLICATE PROBLEM. TIGHTENED PNUE CLAPS ON NR 2 PNUE PRESSURE REG, NO OTHER DEFECTS NOTED. ON GROUND RUN NR 2 ENG FIRE WARNING OPS CHECK GOOD. NR 2 ENG PNEU BLEED SYSTEM OPS CHECKS GOOD AND LEAK CHECKS GOOD.

Part: FIRE LOOP — FAILED (NR 2 ENGINE)

NR 2 ENGINE FIRE WARNING AT CRUISE. SHUT DOWN ENGINE IAW QRH. ALL INDICATIONS OF FIRE WARNING ERASED. REMOVED AND REPLACED LOWER AND UPPER AFT FIRE LOOPS (NR 2 ENG). NR 2 FIRE WARNING SYSTEM OPS CHECK GOOD, NO DEFECT NOTED.

Part: CONNECTOR — LOOSE (NR 2 ENGINE)

ENGINE FIRE WARNING INTERMITTENTLY ON NR 2 ENGINE DURING CLIMBOUT. COMPLIED WITH EWA ENGINE FIRE OR DAMAGE CHECKLIST, SHUT ENGINE DOWN. MAINTENANCE FOUND LOWER FIRE LOOP CANNON PLUG LOOSE. CLEANED AND RESECURED CANNON PLUG, NO DEFECTS FOUND. NR 2 ENGINE FIRE WARNING OPS CHECKED GOOD.

Part: TURBTURBO COMP — ODOR (NR 1)

WITH NR 1 TURBINE OPERATING HAD A BAD BURNED OIL ODOR IN THE COCKPIT. MAINTENANCE TRANSFERED TO DMI LIST PER MEL 21-1-2A CAT C DMI NR 612092 DUE 12/20/96, PLACARD INSTALLED. COULD NOT DUPLICATE PROBLEM ON FLIGHT FROM ALB TO ELP, THIS CLEARS DMI NR 612092.

Part: FIRE LOOP — FAILED (NR 2 ENGINE)

KSEA/KDAY - FLT 025 - DURING CRUISE, NR 2 ENGINE FIRE WARNING SOUNDED. THE AIR CREW DISCHARGED THE O/B FIRE AGENT AND FOLLOWED ENGINE SHUT-DOWN PROCEDURES. MAINTENANCE REMOVED AND REPLACED THE LOWER FIRE LOOP AND THE UPPER REAR FIRE LOOP ELECTRICAL CONNECTOR. MAINTENANCE REMOVED AND REPLACED THE O/B FIRE BOTTLE. AN OPERATIONAL CHECK OF THE FIRE WARNING SYSTEM WAS GOOD ON GROUND RUN. (X)