N605AL
Registered owner: ZIPLINE INTERNATIONAL INC, CA (owner ≠ operator)
Operators of this aircraft
Who operated this tail, and how firmly we know it.
No operator established for this aircraft.
Accident & incident history
No NTSB accidents or incidents on file for this aircraft.
Maintenance disclosures
Service Difficulty Reports filed with the FAA for this airframe. Filing is largely voluntary — the number of reports is not a measure of reliability. To verify a report, search its control number at the FAA SDRS site.
522 reports on file, 1997-05-23 – 2011-09-11.
Part: ENGINE — SLOW (NR 4) · airframe 102,222 hrs · 27,528 cycles
REJECTED TAKEOFF DUE TO ASSYMETRICAL THRUST ON TAKEOFF ROLL. THE NR 4 ENGINE SLOW TO ACCELERATE, DID NOT REACH MAX POWER. THE CREW RETURNED TO BLOCKS WITHOUT FURTHER INCIDENT. MX PREFORMED ACCELERATION CHECK, OPS CHECKED GOOD IAW ERH 72.01.1. PREFORMED REJECTED TAKEOFF INSPECTION, NO DEFECTS NOTED IAW MM 13.01.18. ACFT RETURNED TO SERVICE.
Part: DAMPER — DEFECTIVE (RT ELEVATOR) · airframe 101,891 hrs · 27,391 cycles
DURING CLIMB OUT, THE CREW NOTICED AT 250 KNOTS A PULSING IN BOTH CONTROL COLUMNS. THE PULSE INCREASED THROUGH ANY PITCH CHANGE WHETHER USING THE AUTOPILOT OR MANUALLY FLYING THE ACFT (MORE NOTICEABLE PULSE). THEY RETURNED TO DEPARTURE WITHOUT FURTHER INCIDENT. MX TROUBLESHOT ELEVATOR SYS AND FOUND THE RT ELEVATOR DAMPER BAD. THEY REPLACED THE RT ELEVATOR DAMPER. OPS CHECK GOOD IAW MM 27-30-1 AND 27-30-5.
Part: LOCK SENSOR — DEFECTIVE (THRUST REVERSER) · airframe 101,782 hrs · 27,342 cycles
AFTER TAKEOFF, NR 2 THRUST REVERSER LIGHT WAS BLINKING. THE CREW ACTUATED THE EMERGENCY STOW PUMP BUT NO HELP. THEY RETURNED TO DEPARTURE AND UPON LANDING THE LIGHT WENT OUT. MX TROUBLESHOT THE THRUST REVERSER SYS AND FOUND RT UPPER AND LOWER THRUST REVERSER LOCKING SENSORS BAD. THEY REPLACED BOTH LOCKING SENSORS. OPS CHECK GOOD IAW MM 78-35-1. ACFT WAS RETURNED TO SERVICE.
Part: PROXIMITY SWITCH — DEFECTIVE (LT MLG) · airframe 101,439 hrs · 27,139 cycles
AFTER TAKEOFF, WHEN MLG RETRACTED THE DOOR NOT LATCH LIGHT REMAINED ON. THE CREW CYCLED MLG AND LIGHT REMAINED ON. THEY RETURNED TO DEPARTURE WITHOUT FURTHER INCIDENT. MAINTENANCE REPLACED THE LT MLG PROXIMITY SWITCH. OPERATIONAL CHECK GOOD IAW MM 32-60-0. AIRCRAFT WAS RETURNED TO SERVICE.
Part: TARGET — LOOSE (PROX SWITCH) · airframe 101,429 hrs · 27,133 cycles
DURING CLIMBOUT, AFTER GEARS WAS RETRACTED THE DOOR NOT LATCH LIGHT REMAINED ON. THE CREW CYCLED THE GEARS, DOOR NOT LATCH LIGHT STILL REMAINED ON, AFTER ACCOMPLISHING UPLATCH CHECK LIGHT WENT OUT. THEY LANDED WITHOUT FURTHER INCIDENT. MX INSPECTED BOTH LT AND RT DOOR WARNING SWITCHES AND WIRING, FOUND LT PROXIMITY SWITCH TARGET PIVOT BOLT LOOSE. THEY TIGHTEND BOLT. OPS CHECK GOOD IAW WD 32-01-01, MM 32-60-0. ACFT WAS RETURNED TO SERVICE.
Part: SWITCH — CONTAMINATED (MLG) · airframe 101,410 hrs · 27,126 cycles
AFTER TAKEOFF, WHEN GEAR WAS RETRACTED THE DOOR NOT LATCH LIGHT REMAINED ON. THE CREW CYCLED THE GEAR THE DOOR NOT LATCH LIGHT STILL REMAINED ON THE ALT GEAR DOOR LIGHT REMAINED OUT. ON DECENT THE LT ALT GEAR DOOR LIGHT MOMENTARILY FLASHED ON THEN OFF. THEY LANDED WITHOUT FURTHER INCIDENT. MX FOUND THAT SWITCHES COVERED IN GLYCOL. THEY CLEANED THE SWITCHES, OPS CHECK GOOD IAW MM 32-60-0. ACFT WAS RETURNED TO SERVICE.
Earlier reports · 1997–2010 · 516 reports
2010
Part: SKIN — PUNCTURED (ZONE 100) · airframe 101,259 hrs · 27,037 cycles
PUNCTURE IN LT FWD SIDE OF FUSELAGE AFT AND ABOVE OF LT ACM HEAT EXCHANGE LOUVER DOORS. REPAIRED IAW 53-10653-1. ACFT RETURNED TO SERVICE.
Part: TRANSCEIVER — DEFECTIVE (RADIO ALTIMETER) · airframe 100,950 hrs · 26,904 cycles
AFTER TAKEOFF, "TOO LOW" AUDIBLE WARNING WENT OFF WITH BOTH RADIO ALTIMETER FLAGS IN VIEW AND GPWS LIGHT ON. DUE TO FUEL AND RVSM ISSUES THE CREW RETURNED TO DEPARTURE WITHOUT FURTHER INCIDENT. MX REPLACED RADIO ALTIMETER TRANSCEIVER. OPS CHECK GOOD IAW MM 32-42-0. ACFT WAS RETURNED TO SERVICE.
Part: CONNECTOR — DIRTY (SHUTOFF VALVE) · airframe 100,508 hrs · 26,693 cycles
DURING CLIMB OUT NR 4 BLEED AIR SHUTOFF VALVE CLOSED CONFIRMING NO BLEED FROM ENGINE. THE CREW CYCLED SWITCH SEVERAL TIMES AND MOVED THROTTLE WITH NO HELP. ON DESCENT NR 4 BLEED AIR SHUTOFF VALVE OPENED. THEY LANDED AT DEPARTURE WITHOUT FURTHER INCIDENT. MX INSPECTED AND CLEANED CONNECTOR PLUG TO BLEED AIR SHUTOFF VALVE. OPS CHECK GOOD IAW MMK 36-12-9. ACFT WAS RETURNED TO SERVICE.
Part: GUIDE — MISINSTALLED (ZONE 100) · airframe 100,261 hrs · 26,604 cycles
DURING TAKEOFF THE CREW USED EXCESSIVE DOWNWARD FORCE ON ELEVATOR. THEY REJECTED TAKEOFF AND RETURNED TO BLOCKS WITHOUT FURTHER INCIDENT. MX INSPECTED ELEVATORS AND FOUND CABLE GUIDE UNDER F/O`S FLOOR (FWD) NOT PROPERLY INSTALLED, BOLT ON CABLE SECTOR DRIVE RUBBING ON FLOOR FRAME WHEN MOVING COLUMN. THEY REINSTALLED CABLE GUIDE AND TIGHTENED BOLT. OPS CHECK GOOD IAW MM 27-30-0. ACFT WAS RETURNED TO SERVICE.
2009
Part: STEERING SYS — LACK OF LUBE (NLG) · airframe 99,863 hrs · 26,439 cycles
DURING TAKEOFF FROM KLRD THE NOSE WHEEL CONTROL DID NOT RESPOND TO CONTROL WHEEL OR RUDDER. THE CREW ABORTED TAKEOFF AND RETURNED TO BLOCKS WITHOUT FURTHER INCIDENT. MAINTENANCE LUBRICATED NOSE GEAR SREERING SYSTEM. OPERATIONAL CHECK GOOD IAW DACO DC8 MAINTENANCE MANUAL 32-50-0. AIRCRAFT WAS RETURNED TO SERVICE.
Part: SEAL — LEAKING (FUEL TRANSMITTER) · airframe 99,596 hrs · 26,306 cycles
DURING CLIMB-OUT FROM KBFI NUMBER THREE ENGINE FLAMED OUT. THE CREW ACCOMPLISHED QRH CHECKLIST, AND RESTART ATTEMPT, ENGINE WOULD NOT START. THE CREW LANDED IN KPDX WITHOUT FURTHER INCIDENT. MAINTENANCE INSPECTED NUMBER THREE ENGINE AND FOUND FUEL LEAK ON FUEL TRANSMITTER. MAINTENANCE REPLACED SEAL ON TRANSMITTER OUTLET SIDE. OPERATIONAL CHECK GOOD IAW CFM 71-00-00 FAULT 51 PAGE 101-103, DACO MAINTENANCE MANUAL 73-30-1, AND ERH 70.01. AIRCRAFT WAS RETURNED TO SERVICE.
Part: SKIN — MISREPAIRED (ZONE 100) · airframe 99,555 hrs · 26,286 cycles
DURING ROUTINE C CHECK INSPECTION, FOUND IMPROPER REPAIR AT STATION 220.000-240.000 LONGERON 28-31 LEFT. REMOVED FASTENERS AS NEEDED TO PERFORM REPAIR. REMOVED EXISTING REPAIR. FABRICATED NEW SKIN, INTERNAL, AND EXTERNAL DOUBLERS. CLEANED, TREATED, PRIMED AREA, AND REPAIR PARTS. INSTALLED NEW FASTENERS AND REPAIR PARTS IAW SRM 53-2-1 FIGURE 7 TR 53-203 SHEETS 3, 4, 23, AND 24, SRM 51-1-20D, SRM 51-1-8B, SRM 51-1-21, AND SRM 51-3-1.
Part: SKIN — MISREPAIRED (ZONE 100) · airframe 99,555 hrs · 26,286 cycles
DURING ROUTINE C CHECK INSPECTION, FOUND IMPROPER REPAIR AT STATION 480.000 LONGERON 23-24 RIGHT. REMOVED FASTENERS AS NEEDED TO PERFORM REPAIR. REMOVED EXISTING REPAIR. FABRICATED NEW SKIN, INTERNAL, AND EXTERNAL DOUBLERS. CLEANED, TREATED, PRIMED AREA, AND REPAIR PARTS. INSTALLED NEW FASTENERS AND REPAIR PARTS IAW DC8 SRM CHAPTER 53-2-1 FIGURE 7 TR 53-203 SHEETS 3, 4, 23, AND 24, DC8 SRM 51-1-20D, DC8 SRM 51-1-8B, SRM 51-1-21, AND SRM 51-3-1.
Part: LONGERON SPLICE — CRACKED (BS 1770) · airframe 99,555 hrs · 26,286 cycles
DURING ROUTINE C CHECK INSPECTION, FOUND AFT FUSELAGE SPLICE FITTING CRACKED AT STATION 1770.000 LONGERON 17 RIGHT. REMOVED CRACKED FITTING. INSTALLED NEW SPLICE FITTING IAW SRM 51-1-20D, SRM 51-1-21, AND SRM 51-3-1.
Part: FITTING — CRACKED (BS 55) · airframe 99,555 hrs · 26,286 cycles
DURING ROUTINE C CHECK INSPECTION, FOUND FORWARD ACCESSORY COMPARTMENT FITTING CRACKED AT STATION 55.000 RIGHT BUTTOCKS LINE 45. REMOVED CRACKED FITTING. INSTALLED NEW FITTING IAW DC8 SRM 51-1-20D, SRM 51-3-1, ATI REPAIR SPECIFICATION 2003-5, AND SMN-FORM-07 IPI NUMBER 2009402.
Part: FITTING — CRACKED (BS 55) · airframe 99,555 hrs · 26,286 cycles
DURING ROUTINE C CHECK INSPECTION, FOUND FORWARD ACCESSORY COMPARTMENT FITTING CRACKED AT STATION 55.000 RIGHT BOTTOM LINE 45. REMOVED CRACKED FITTING. INSTALLED NEW FITTING IAW DC8 SRM 51-1-20D, SRM 51-3-1, ATI REPAIR SPECIFICATION 2003-5, AND SEMAN FORM-07 IPI NUMBER 2009402.
Part: FITTING — CRACKED (BS 65 L21R) · airframe 99,555 hrs · 26,286 cycles
DURING ROUTINE C CHECK INSPECTION, FOUND FORWARD ACCESSORY COMPARTMENT FITTING CRACKED AT STATION 65.000 LONGERON 21 RIGHT. REMOVED CRACKED FITTING. INSTALLED NEW FITTING IAW DC8 SRM 51-1-20D, SRM 51-3-1, ATI REPAIR SPECIFICATION 2003-5, AND SMN-FORM-07 IPI NR 2009399.
Part: FITTING — CRACKED (BS 70) · airframe 99,555 hrs · 26,286 cycles
DURING ROUTINE C CHECK INSPECTION, FOUND FORWARD ACCESSORY COMPARTMENT FITTING CRACKED AT STATION 70.000 LONGERON 21 RIGHT- RIGHT BOTTOM LONE 50. REMOVED CRACKED FITTING. INSTALLED NEW FITTING IAW DC8 SRM 51-1-20D, SRM 51-3-1, ATI REPAIR SPECIFICATION 2003-5, AND SMN-FORM-07 IPI NUMBER 2009398.
Part: FITTING — CRACKED (ZONE 100) · airframe 99,555 hrs · 26,286 cycles
DURING ROUTINE C CHECK INSPECTION, FOUND AFT CARGO COMPARTMENT FITTING CRACKED AT STATION 1280.000 LONGERON 35 RT. REMOVED CRACKED FITTING. CLEANED, TREATED, AND PRIMED AREA. INSTALLED NEW FITTING IAW SRM 51-1-20D, SRM 51-3-4, AND SRM 51-1-8B.
Part: FITTING — CRACKED (ZONE 100) · airframe 99,555 hrs · 26,286 cycles
DURING ROUTINE C CHECK INSPECTION, FOUND AFT CARGO COMPARTMENT FITTING CRACKED AT STATION 1280.000 LONGERON 35LEFT. REMOVED CRACKED FITTING. CLEANED, TREATED, AND PRIMED AREA. INSTALLED NEW FITTING IAW DC8 SRM 51-1-20D, SRM 51-3-4, AND DC8 SRM 51-1-8B.
Part: SKIN — CRACKED (RUDDER) · airframe 99,555 hrs · 26,286 cycles
DURING ROUTINE C CHECK INSPECTION, FOUND LEFT RUDDER SKIN CRACKED AT STATION ZR 71.437. REMOVED FASTENERS AS NEEDED TO PERFORM REPAIR. REMOVED DAMAGED SKIN. FABRICATED NEW SKIN. CLEANED, TREATED, PRIMED AREA AND REPAIR PART. PERFORMED RUDDER WEIGHT AND BALANCE. FOUND WITHIN LIMITS, MOMENT: 2487.44 IN-LBS. INSTALLED NEW FASTENERS AND REPAIR PART IAW DC8 SRM 55-6-1 FIGURE 1 ITEM "C", DC8 SRM 55-1-0 PAGE 1 AND SRM 51-1-21, DC8 SRM 51-1-8B, AND DC8 SRM 51-1-11.
Part: STRUCTURE — CRACKED (HORIZONTAL STAB) · airframe 99,555 hrs · 26,286 cycles
DURING ROUTINE C CHECK INSPECTION, FOUND LEFT HORIZONTAL STABILIZER CAP CRACKED STATION XE 29.812. REMOVED CRACKED CAP. INSTALLED NEW CAP IAW SRM 51-1-20D, SRM 51-3-1, ATI REPAIR SPECIFICATION NUMBER 2003-05, AND SMN-FORM-07 IPI NUMBER 2009420.
Part: FITTING — CRACKED (BS 717) · airframe 99,555 hrs · 26,286 cycles
DURING ROUTINE C CHECK INSPECTION, FOUND MAIN CARGO COMPARTMENT FITTING CRACKED AT STATION 717.000 LEFT BOTTOM LINE 1. REMOVED CRACKED FITTING. INSTALLED NEW FITTING IAW SRM 51-1-20D, SRM 51-1-21, SRM 51-3-1.
Part: LONGERON — CRACKED (ZONE 100) · airframe 99,555 hrs · 26,286 cycles
DURING ROUTINE C CHECK INSPECTION, FOUND AFT CARGO COMPARTMENT BILGE LONGERON CRACKED STATION 1260.000 - 1280.000 LONGERON 35 RIGHT. REMOVED CRACKED LONGERON. FABRICATED LONGERON, SPLICE, AND DOUBLER. CLEANED, TREATED, PRIMED AREA AND REPAIR PARTS. INSTALLED REPAIR PARTS IAW SRM 53-2-2 FIGURE 13 SHEETS 1-4 TR 53-191, SRM 51-1-20D, SRM 53-4-1 FIGURE 43A SHEET 1 ITEM "N", SRM 51-2-0 FIGURE 50 SHEET 72B, SRM 51-1-8B, SRM 51-1-11, AND SRM 51-3-1.
Part: CARGO TRACK — WORN (BS 1670-1752) · airframe 99,555 hrs · 26,286 cycles
DURING ROUTINE C CHECK INSPECTION, FOUND MAIN CARGO COMPARTMENT NUMBER 4 TRACK LUGS WORN AT STATION 1670.000-1752.000. REMOVED WORN TRACK SEGMENT AND EXISTING SPLICES. FABRICATED TRACK SEGMENT. CLEANED, TREATED, PRIMED AREA AND SEGMENT TRACK AND EXISTING SPLICES. INSTALLED TRACK SEGMENT AND REINSTALLED SPLICES IAW DC8 SRM 53-2-3 FIGURE 14 SHEET 1 PAGES 49-50, DC8 SRM 53-1-0 PAGE 1, SRM 51-3-0, SRM 53-7-3 FIGURE 3D ITEM "S", SRM 51-2-0 FIG 50, DC8 SRM 51-1-8B, DC8 SRM 51-1-11, SRM 51-3-0, AND SRM 51-3-1.
Part: LONGERON — CRACKED (ZONE 100) · airframe 99,555 hrs · 26,286 cycles
DURING ROUTINE C CHECK INSPECTION, FOUND AFT CARGO COMPARTMENT BILGE LONGERON CRACKED AT STATION 1260.000 - 1280.000 LONGERON 36. REMOVED DAMAGED LONGERON SEGMENT. FABRICATED LONGERON SEGMENT EXTRUSION, SPLICE, AND DOUBLER. CLEANED, TREATED, PRIMED AREA AND REPAIR PARTS. INSTALLED REPAIR PARTS IAW SRM 53-2-2 FIGURE 13 SHEETS 1-4 TR 53-191, SRM 51-1-20D, SRM 53-4-1 FIGURE 43 SHEET 1 LETTER "N", SRM 51-2-0 FIGURE 50 SHEET 72B, SRM 51-1-8B, SRM 51-1-11, AND SRM 51-3-1.
Part: LONGERON — CRACKED (ZONE 200) · airframe 99,555 hrs · 26,286 cycles
DURING ROUTINE C CHECK INSPECTION, FOUND AFT FUSELAGE LONGERON CRACKED AT STATION 1786.000 LONGERON 17 RIGHT. REMOVED CRACKED LONGERON. CLEANED, TREATED, AND PRIMED AREA. FABRICATED EXTRUSION LONGERON. INSTALLED REPAIR PART IAW DC8 SRM 53-5-3 FIGURE 5 SHEET 1 ITEM "B", DC8 SRM 53-1-0 PAGE 1, SRM 51-1-20D, SRM 51-1-21, DC8 SRM 51-1-8B, SRM 51-2-0 FIGURE 50 SHEET 37, SRM 51-1-11, AND SRM 51-3-1.
Part: FITTING — CRACKED (ZONE 200) · airframe 99,555 hrs · 26,286 cycles
DURING ROUTINE C CHECK INSPECTION, FOUND MAIN CARGO COMPARTMENT LONGERON BATHTUB FITTING CRACKED AT STATION 902.125 LONGERON 5 LEFT. REMOVED CRACKED BATHTUB FITTING. CLEANED, TREATED, AND PRIMED AREA. INSTALLED NEW BATHTUB FITTING IAW SRM 51-1-20D, SRM 51-1-8B, SRM 51-1-23, AND SRM 51-3-1.
Part: LONGERON — CRACKED (ZONE 100) · airframe 99,555 hrs · 26,286 cycles
DURING ROUTINE C CHECK INSPECTION, FOUND AFT CARGO COMPARTMENT BILGE LONGERON CRACKED STATION 1260.000 - 1280.000 LONGERON 35LEFT. REMOVED CRACKED LONGERON. FABRICATED LONGERON, SPLICE, AND DOUBLER. CLEANED, TREATED, PRIMED AREA AND REPAIR PARTS. INSTALLED REPAIR PARTS IAW SRM 53-2-2 FIGURE 13 SHEETS 1-4 TR 53-191, SRM 51-1-20D, SRM 53-4-1 FIGURE 43A SHEET 1 ITEM "N", SRM 51-2-0 FIGURE 50 SHEET 72B, SRM 51-1-8B, SRM 51-1-11, AND SRM 51-3-1.
Part: LONGERON — CORRODED (ZONE 100) · airframe 99,555 hrs · 26,286 cycles
DURING ROUTINE C CHECK INSPECTION, FOUND AFT CARGO COMPARTMENT BILGE LONGERON CORRODED AT STATION 1490.000 - 1500.000 LONGERON 35 RIGHT. REMOVED CORROSION. FOUND OUT OF LIMITS. REMOVED CORRODED LONGERON. FABRICATED LONGERON SEGMENT, AND SPLICES. PERFORMED HEAT TREATMENT. CLEANED, TREATED, PRIMED AREA AND REPAIR PARTS. INSTALLED REPAIR PARTS IAW SRM 53-2-2 FIGURE 4A, SRM 51-1-8 PAGES 17-18, SRM 53-2-0 PAGE 2P, SRM 53-4-1 FIGURE 43A SHEET 2 LETTER "L", SRM 51-2-0 FIGURE 52, SRM 53-2-2 FIGURE 10 SHEET 2 PAGES 49-50, SRM 53-2-2 FIGURE 10 SHEET 4 TR 53-193, SRM 51-1-1 PAGES 1,13, AND 17, SRM 51-1-8B, SRM 51-1-11, SRM 51-1-21, SRM 51-1-20D, AND SRM 51-3-1.
Part: LONGERON — CRACKED (ZONE 200) · airframe 99,555 hrs · 26,286 cycles
DURING ROUTINE C CHECK INSPECTION, FOUND AFT FUSELAGE LONGERON CRACKED AT STATION 1786.000 LONGERON 17 LEFT. REMOVED CRACKED LONGERON. CLEANED, TREATED, AND PRIMED AREA. FABRICATED EXTRUSION LONGERON. INSTALLED REPAIR PART IAW SRM 53-5-3 FIGURE 5 SHEET 1 ITEM "B", SRM 53-1-0 PAGE 1, SRM 51-1-20D, SRM 51-1-21, SRM 51-1-8B, SRM 51-2-0 FIGURE 50 SHEET 37, SRM 51-1-11, AND SRM 51-3-1.
Part: FITTING — CRACKED (ZONE 100) · airframe 99,555 hrs · 26,286 cycles
DURING ROUTINE C CHECK INSPECTION, FOUND AFT CARGO COMPARTMENT FITTING CRACKED AT STATION 1230.000 LONGERON 32-33 RIGHT. REMOVED CRACKED FITTING. INSTALLED NEW FITTING IAW SRM 51-1-20D, AND SRM 51-3-1.
Part: STRUCTURE — CRACKED (BS 55-70) · airframe 99,555 hrs · 26,286 cycles
DURING ROUTINE C CHECK INSPECTION, FOUND FORWARD ACCESSORY COMPARTMENT LEFT CAP CRACKED STATION 55.000 - 70.000 RIGHT BOTTOM LINE 45. REMOVED CRACKED CAP. INSTALLED NEW CAP IAW DC8 SRM 51-1-20D, SRM 51-3-1, ATI REPAIR SPECIFICATION NUMBER 2003-05, AND SMN-FORM-07 IPI NUMBER 2009403.
Part: STIFFENER — CRACKED (THRUST REVERSER) · airframe 99,555 hrs · 26,286 cycles
DURING ROUTINE C CHECK INSPECTION, FOUND NUMBER 3 ENGINE THRUST REVERSER RIGHT COWLING RAIL FITTING CRACKED AT 6 O'CLOCK POSITION. REMOVED RAIL FITTING FASTENERS. FABRICATED NEW STIFFENER. PROTECTED STIFFENER WITH CHROMIC ANODIZED. INSTALLED NEW FASTENERS, AND STIFFENER IAW DC8 SRM 51-1-21, CFM56-5 CHAPTER 78-32-41 PAGES 909-910 FIGURE 902 SHEETS 1-2, DC8 ENGINE SHOP MANUAL CFM56-5 CHAPTER 78-32-41 FIGURE 901 SHEETS 2-3, AND PAGES 906-907.
Part: SKIN — CRACKED (ZONE 600) · airframe 99,555 hrs · 26,286 cycles
DURING ROUTINE C CHECK INSPECTION, FOUND RIGHT WING UPPER SKIN CRACKED AT STATION XRS 74.000 STRINGER 12. REMOVED FASTENERS AS NEEDED TO PERFORM REPAIR. REMOVED EXISTING REPAIR DOUBLERS. REMOVED DAMAGED AREA. PERFORMED NDT INSPECTION. NO CRACK AND NO CORROSION FOUND. FABRICATED NEW SKIN, INTERNAL, EXTERNAL DOUBLER. CLEANED, TREATED, PRIMED AREA AND REPAIR PARTS. INSTALLED NEW FASTENERS AND REPAIR PARTS IAW FAA FORM 8110-3 DATED 05/12/09, DRAWING ED-4928 DATED 04/09/09, SRM 51-1-20D, SRM 51-3-0, NDT SPM PART 06-10-01-001, SRM 51-10-0, SRM 51-1-12 PAGE 7, DC8 SRM 51-1-8B, SRM 51-1-12 PRC, AND SRM 51-3-1.
Part: FITTING — CRACKED (LT WING TE FLAP) · airframe 99,555 hrs · 26,286 cycles
DURING ROUTINE C CHECK INSPECTION, FOUND LEFT OUTBOARD FLAP INTERIOR FITTING CRACKED AT STATION XF 337.000. REMOVED CRACKED FITTING. CLEANED, TREATED, AND PRIMED AREA. INSTALLED NEW FITTING IAW DC8 SRM 51-1-21, DC8 SRM 51-1-8B, DC8 SRM 51-1-21, ATI REPAIR SPECIFICATION NUMBER 2003-05, AND SMN-FORM-07 IPI NUMBER 2009418.
Part: FITTING — CRACKED (LT WING TE FLAP) · airframe 99,555 hrs · 26,286 cycles
DURING ROUTINE C CHECK INSPECTION, FOUND LEFT OUTBOARD FLAP INTERIOR HAS FITTING CRACKED AT STATION XF 411.000. REMOVED CRACKED FITTING. INSTALLED NEW FITTING IAW SRM 51-3-0, SRM 51-3-1, SRM 51-1-21.
Part: FITTING — CRACKED (HORIZONTAL STAB) · airframe 99,555 hrs · 26,286 cycles
DURING ROUTINE C CHECK INSPECTION, FOUND RIGHT HORIZONTAL STABILIZER FRONT SPAR LOWER FITTING CRACKED AT STATION XFS 60.000. REMOVED CRACKED FITTING. INSTALLED NEW FITTING IAW SRM 51-1-20D, SRM 51-1-21, AND SRM 51-3-1.
Part: STRUCTURE — CRACKED (BS 55-70) · airframe 99,555 hrs · 26,286 cycles
DURING ROUTINE C CHECK INSPECTION, FOUND FORWARD ACCESSORY COMPARTMENT LEFT CAP CRACKED STATION 55.000 - 70.000 LEFT BOTTOM LINE 45. REMOVED CRACKED CAP. INSTALLED NEW CAP IAW DC8 SRM 51-1-20D, SRM 51-3-1, REPAIR SPECIFICATION NR 2003-05, AND SMN-FORM-07 IPI NR 2009405.
Part: SKIN — CRACKED (LT WING TE FLAP) · airframe 99,555 hrs · 26,286 cycles
DURING ROUTINE C CHECK INSPECTION, FOUND LEFT INBOARD FLAP UPPER SKIN CRACKED AT STATION 104.000 - 122.000. REMOVED EXISTING REPAIR. FABRICATED NEW SKIN. CLEANED, TREATED, PRIMED AREA AND REPAIR PART. INSTALLED REPAIR PART IAW SRM 57-7-1 FIGURE 1 ITEM "D", SM 57-1-0 PAGE 1, SRM 51-1-21, SRM 51-1-8B, SRM 51-1-11, SRM 51-3-0, AND SRM 51-3-1.
Part: SKIN — CORRODED (ZONE 100) · airframe 99,555 hrs · 26,286 cycles
DURING ROUTINE C CHECK INSPECTION, FOUND FUSELAGE EXTERIOR LOWER SKIN CORRODED AT STATION 660.000 LONGERON 31 LT. REMOVED CORROSION. FOUND OUT OF LIMITS. REMOVED DAMAGED AREA. FABRICATED NEW SKIN, INTERNAL AND EXTERNAL DOUBLERS. CLEANED, TREATED, PRIMED AREA AND REPAIR PARTS. INSTALLED REPAIR PARTS IAW SRM 53-2-1 FIGURE 7 TR 53-203 SHEETS 4,7,23, AND 24, SRM 51-1-8 PAGE 17-18, SRM 53-2-0 PAGE 2P, SRM 53-4-1 FIGURE 15B ITEM "B", SRM 51-1-8B, SRM 51-1-11, SRM 51-1-21, SRM 51-1-20D, AND SRM 51-3-1.
Part: STRUCTURE — CRACKED (ZONE 100) · airframe 99,555 hrs · 26,286 cycles
DURING ROUTINE C CHECK INSPECTION, FOUND FUSELAGE NOSE SECTION EXTERIOR PRIMARY HEAT EXCHANGER AFT LOWER CORNER CRACKED AT STATION 12.000 LONGERON 27 RIGHT. REMOVED FASTENERS AS NEEDED TO PERFORM REPAIR. REMOVED DAMAGED AREA. PERFORMED NDT INSPECTION. NO CRACK AND NO CORROSION FOUND. FABRICATED REPAIR DOUBLER, AND REPAIR TRIPLER, FILLER. CLEANED, TREATED, PRIMED AREA AND REPAIR PARTS. INSTALLED NEW FASTENERS AND REPAIR PARTS IAW FAA FORM 8110-3 DATED 04-30-09, DRAWING ED-4926 REV "IR" DATED 04-03-09, SRM 51-1-21, SRM 51-3-0, NDT SPM PART 06-10-01-001, SRM 51-1-8B, SRM 51-1-11, SRM 51-1-20D, AND SRM 51-3-1.
Part: FITTING — CRACKED (ZONE 200) · airframe 99,555 hrs · 26,286 cycles
DURING ROUTINE C CHECK INSPECTION, FOUND MAIN CARGO COMPARTMENT FITTING CRACKED AT STATION 781.500 LONGERON 13 RIGHT. REMOVED CRACKED FITTING. CLEANED, TREATED, AND PRIMED AREA. INSTALLED NEW FITTING IAW DC8 SRM 51-1-20D DC8 SRM 51-1-8B, AND SRM 51-3-1.
Part: FITTING — CRACKED (ZONE 200) · airframe 99,555 hrs · 26,286 cycles
DURING ROUTINE C CHECK INSPECTION, FOUND AFT PASSENGER DOOR FITTING CRACKED AT STATION 1621.000. REMOVED CRACKED FITTING. INSTALLED NEW FITTING IAW SRM 51-1-20D, SRM 51-3-1.
Part: STRUCTURE — CRACKED (ZONE 100) · airframe 99,555 hrs · 26,286 cycles
DURING ROUTINE C CHECK INSPECTION, FOUND FUSELAGE NOSE SECTION EXTERIOR PRIMARY HEAT EXCHANGER AFT LOWER CORNER CRACKED AT STATION 12.000 LONGERON 27 LEFT. REMOVED FASTENERS AS NEEDED TO PERFORM REPAIR. REMOVED DAMAGED AREA. PERFORMED NDT INSPECTION. NO CRACK AND NO CORROSION FOUND. FABRICATED REPAIR DOUBLER, AND REPAIR TRIPLER, FILLER. CLEANED, TREATED, PRIMED AREA AND REPAIR PARTS. INSTALLED NEW FASTENERS AND REPAIR PARTS IAW FAA FORM 8110-3 DATED 04-30-09, SEMAN DRAWING ED-4926 REV "IR" DATED 04-03-09, DC8 SRM 51-1-21, SRM 51-3-0, DC8 NDT SPM PART 06-10-01-001, DC8 SRM 51-1-8B, DC8 SRM 51-1-11, SRM 51-1-20D, AND SRM 51-3-1.
Part: FITTING — CRACKED (BS 380) · airframe 99,555 hrs · 26,286 cycles
DURING ROUTINE C CHECK INSPECTION, FOUND MAIN CARGO COMPARTMENT FITTING CRACKED AT STATION 680.000 LONGERON 11 LT. REMOVED CRACKED FITTING. CLEANED, TREATED, PRIMED AREA. INSTALLED NEW FITTING IAW DC8 SRM 51-1-23, SRM 51-1-20D, DC8 SRM 51-1-8B, AND SRM 51-3-1.
Part: STRUCTURE — MISREPAIRED (CARGO DOOR) · airframe 99,555 hrs · 26,286 cycles
DURING ROUTINE C CHECK INSPECTION, FOUND IMPROPER REPAIR ON MAIN CARGO DOOR FORWARD LOWER JAMB CORNER AT STATION 120.000 - 210.000 LONGERON 19-23 LT. REMOVED EXISTING REPAIR. REMOVED DAMAGED AREA. PERFORMED NDT INSPECTION. NO CRACK AND NO CORROSION FOUND. FABRICATED REPAIR DOUBLER, REPAIR TRIPLER, FILLERS, FINGER DOUBLERS. CLEANED, TREATED, AND PRIMED AREA AND REPAIR PARTS. INSTALLED REPAIR PARTS IAW FAA FORM 8110-3 DATED 5/8/09, AD 2006-03.4, SB DC853-079, DRAWING SR08530027, DRAWING ED-4925 DATED 3/30/09, SRM 51-1-21, 51-1-20D, SRM 51-3-0, NDT SPM PART 06-10-01-001, SRM 51-1-8B, SRM 51-1-11, AND SRM 51-3-1.
Part: SKIN — MISREPAIRED (ZONE 100) · airframe 99,555 hrs · 26,286 cycles
DURING ROUTINE C CHECK INSPECTION, FOUND LEFT FUSELAGE SKIN FORWARD OF FLAT AFT PRESSURE BULKHEAD HAS IMPROPER REPAIR AT LONGERON 28. REMOVED FASTENERS AS NEEDED TO PERFORM REPAIR. REMOVED EXISTING REPAIR. REMOVED DAMAGED AREA. FABRICATED NEW SKIN, EXTERNAL, EXTERNAL DOUBLE, FINGER DOUBLERS, AND FILLERS. CLEANED, TREATED, PRIMED AREA AND REPAIR PARTS. INSTALLED NEW FASTENERS AND REPAIR PARTS IAW SRM 51-1-21, SM 51-1-20D, SRM 53-5-3, SRM 51-1-8B, SRM 51-3-0, SRM 51-1-11, SRM 51-3-1, AD 2008-06-23, SB DC8-53A080 IR DATED 06/22/04, SERVICE REWORK DRAWING SR08530032, EO NR 2009303, AND DRAWING ED-4924,
2008
Part: GYRO — FAILED (HSI) · airframe 99,401 hrs · 26,195 cycles
DURING CRUISE FROM KTOL TO KBFI, THE CAPTAINS ADI AND HSI FAILED. THE CREW DIVERTED TO KRFD AND LANDED WITHOUT INCIDENT. MAINTENANCE REPLACED THE FIBER OPTIC VG/DG GYRO. THE OPERATIONAL CHECK WAS GOOD AND THE AIRCRAFT WAS RETURNED TO SERVICE.
Part: WIRE — BROKEN (HYD PUMP) · airframe 98,793 hrs · 25,904 cycles
DURING CRUISE FROM KLRD TO KDFW ,THE CREW OBSERVED ONE OF THE MAIN HYDRAULIC PUMPS WOULD NOT BYPASS. THE CREW DIVERTED TO KIAH AND LANDED WITHOUT INCIDENT. MAINTENANCE INSPECTED THE MAIN HYDRAULIC PUMP SYSTEM AND FOUND A BROKEN WIRE ON THE NUMBER TWO MAIN HYDRAULIC PUMP BYPASS SOLENOID. MAINTENANCE REPAIRED THE BROKEN WIRE ON THE NR 2 HYDRAULIC PUMP BYPASS SOLENOID IAW DOUGLAS DC-8 MM 20-50-1. THE OPERATIONAL CHECK WAS GOOD AND THE AIRCRAFT WAS RETURNED TO SERVICE.
2007
Part: CONNECTOR — DIRTY (SQUAT SWITCH) · airframe 98,397 hrs · 25,747 cycles
DURING CLIMB-OUT FROM KTOL, WHEN LEFT AIR CONDITIONER PACK MADE A LOUD BANG, TURNED ON AND MADE EXCESSIVE NOISE WHILE TURNED ON. THE CREW RETURNED TO KTOL AND LANDED WITHOUT INCIDENT. MAINTENANCE INSPECTED THE AIR CONDITIONER PACK AND FOUND LEFT GROUND CONTROL RELAY STUCK VIA LEFT SQUAT SWITCH CLEANED ELECTRICAL CONNECTOR AND RESEATED TO LEFT SWITCH. OPERATIONAL CHECK WAS GOOD IAW DC8 MAINTENANCE MANUAL 21-55-5. AIRCRAFT WAS RETURNED TO SERVICE.
Part: EADI — FAILED (COCKPIT) · airframe 98,218 hrs · 25,674 cycles
DURING TAKEOFF ROLL PRIOR TO 80 KIAS, FIRST OFFICER'S EADI WENT BLANK WITH FLAGS IN VIEW, BAR WITH ATT IN VIEW, GA .AND INST 2 FLAG. THE CREW REJECTED TAKEOFF AND RETURNED TO BLOCKS AT KIAH WITH OUT INCIDENT. MAINTENANCE INSPECTED AND FOUND NUMBER 2 INSTRUMENT RACK LOOSE. MAINTENANCE RESECURED INSTRUMENT RACK OPERATIONAL CHECK GOOD IAW ATI DC8 MAINTENANCE MANUAL 34-01-07. AIRCRAFT WAS RETURNED TO SERVICE.
Part: ENGINE — OVERTEMP (NR 1) · airframe 98,044 hrs · 25,618 cycles
DURING CLIMB-OUT FROM KTOL, THE CREW PERFORMED MAX POWER TAKEOFF TO COMPLY WITH SEVEN DAY REQUIREMENT. NR ONE EGT WENT TO 906 FOR 2 SECONDS AFTER ROTATION, (N1 POWER SET FOR MAX 91.5 AFTER ROTATION N1 INCREASED TO 93.0 AND EGT FOLLOWED). NUMBER 4 EGT WENT TO 911 AFTER ROTATION. N1 POWER SET FOR MAX AT 91.5, AFTER CLIMB N1 INCREASED TO 93.5 AND EGT FOLLOWED EGT AT 911 JUST MOMENTARILY. THE CREW RETURNED TO KTOL AND LANDED WITHOUT INCIDENT. MAINTENANCE PERFORMED PMC DROP CHECK ADJUSTED MECHANICAL POWER TRIM, PERFORMED MAX POWER RUN ALL PARAMETERS ARE WITH IN LIMITS OPERATIONAL CHECK WAS GOOD. AIRCRAFT WAS RETURNED TO SERVICE.
Part: CABLE — OUT OF ADJUST (NR 4 VSV) · airframe 97,315 hrs · 25,382 cycles
DURING TAKEOFF ROLL AT ABOUT 90 KNOTS, THE CREW HEARD TWO LOUD POPPING NOISES. THE CREW ABORTED THE TAKEOFF. ENGINE ANTI-ICE WAS ON. MAX POWER WAS SET 87 PERCENT N1. THE CREW RETURNED TO PARKING. MAINTENANCE INSPECTED THE AIRCRAFT AND COMPLIED WITH CFM56 MM 71-00 CODE 41. AN ADJUSTMENT WAS MADE TO NUMBER 4 ENGINE VSV FEEDBACK CABLE. NO OTHER DEFECTS WERE FOUND. MAINTENANCE PERFORMED AN ACCELERATION CHECK AND MAX POWER RUN ALL ENG PARAMETERS WERE NORMAL IAW ATI ERH 70.01. TAXIED THE AIRCRAFT IAW ATI ERH 9.01.1. NO DEFECTS WERE FOUND. THE AIRCRAFT WAS RETURNED TO SERVICE.
2006
Part: LINK — UNLATCHED (ZONE 700) · airframe 96,744 hrs · 25,185 cycles
AFTER TAKE OFF FROM KTOL, WITH THE GEAR HANDLE SELECTED UP A LOUD BANGING NOISE STARTED WITH GEAR INDICATING UP AND LOCKED. THE NOISE MODERATELY CONTINUED WITH A VIBRATION FELT IN THE NOSE WHEEL WELL AREA. THE VIBRATION INCREASED WITH AN INCREASE IN AIRSPEED. THE CREW RETURNED TO KTOL AND LANDED WITHOUT INCIDENT. MAINTENANCE INSPECTED THE NOSE GEAR AREA AND FOUND THE RIGHT HAND FORWARD LINK NOT LATCHING. MAINTENANCE REPLACED THE RIGHT HAND LINK AND ADJUSTED THE LEFT HAND LINK. IAW DC-8 MM 32-22-1. THE OPERATIONAL CHECK WAS GOOD AND THE AIRCRAFT WAS RETURNED TO SERVICE.
Part: LINKAGE — OUT OF ADJUST (NLG DOOR) · airframe 96,669 hrs · 25,173 cycles
AFTER TAKEOFF FROM PHIK WHEN THE GEAR WAS RAISED A LOUD RUMBLE WAS HEARD AND VIBRATION FELT COMING FROM THE NOSE GEAR AREA. THE CREW RETURNED TO PHIK AND LANDED WITHOUT INCIDENT. MAINTENANCE INSPECTED THE NOSE GEAR AREA AND FOUND THE RIGHT HAND FORWARD DOOR WAS NOT CLOSING TIGHT AGAINST THE DOOR STOP. MAINTENANCE ADJUSTED THE NOSE GEAR DOOR LINKAGE PER DACO MM 32-22-1. THE OPERATIONAL CHECK WAS GOOD AND THE AIRCRAFT WAS RETURNED TO SERVICE.
Part: CONNECTING ROD — OUT OF ADJUST (NLG DOOR) · airframe 96,648 hrs · 25,167 cycles
DURING CLIMB FROM LEVT WHEN THE LANDING GEAR WAS RAISED THE AIRCRAFT BEGAN TO MAKE A LOUD RUMBLE IN THE NOSE GEAR AREA. THE CREW LOWERED THE GEAR AND THE NOISE CONTINUED, THE NOISE WOULD INCREASE WITH AN INCREASE IN AIRSPEED. THE CREW RAISED THE LANDING GEAR AND INSPECTED THE NOSE GEAR THROUGH THE INSPECTION HOLE, NO VISABLE DEFECTS WERE NOTED. THE CREW LOWERED THE GEAR AND ONE LOUD POP WAS HEARD AND THE RUMBLE BECAME LESS NOTICEABLE. MAINTENANCE INSPECTED THE NOSE GEAR DOORS, AND FOUND THE MOST FORWARD NOSE GEAR DOOR CONNECTING RODS OUT OF ADJUSTMENT, AND FOUND THE SEAL MISSING FROM THE LEFT HAND AFT NOSE GEAR DOOR. MAINTENANCE ADJUSTED THE CONNECTING RODS AND INSTALLED THE MISSING SEAL IAW DC8 MM 32-22-0
Part: FASTENER — LOOSE (NLG WW) · airframe 96,648 hrs · 25,166 cycles
DURING CLIMB FROM LEVT WHEN GEAR WAS RETRACTED A CONTINOUS BANGING NOISE WAS HEARD AND FELT IN NOSE AREA. UPLATCH CHECK WAS GOOD, THE CREW LOWERED THE GEAR AND THE NOISE AND VIBRATION CONTINUED. THE CREW RETURNED TO LEVT AND THE LANDING WAS UNEVENTFUL. MAINTENANCE INSPECTED THE NOSE GEAR AREA AND FOUND THE RIGHT HAND MOST FORWARD TUNNEL PANEL MISSING HARDWARE AND THE BULB SEAL ON THE LEFT AFT NOSE GEAR DOOR WAS LOOSE AND FLOPPING. MAINTENANCE SECURED THE TUNNEL PANEL AND REMOVED THE DAMAGED BULB SEAL. THE AIRCRAFT WAS RETURNED TO SERVICE.
Part: LONGERON — CRACKED (ZONE 100) · airframe 96,561 hrs · 25,131 cycles
DURING ROUTINE C-CHECK INSPECTION FOUND LONGERON 35 RT CRACKED BETWEEN STA 1340.000 AND STA 1350.000. REMOVED FASTENERS, REMOVED CRACKED LONGERON SEGMENT. FABRICATED NEW LONGERON EXTRUSION P/N 2753715/7075 T651. FABRICATED SPLICE FROM AL 7075 T651. PERFORMED NDT INSPECTION. CLEANED, TREATED AND PRIMED AREA AND REPAIR PARTS. APPLIED SEALANT TO FAYING SURFACES. INSTALLED REPAIR PARTS. IAW MFG MESSAGE 1-216533783-2 DATE 08-03-06, SRM 53-2-2 FIG. 4A, SRM 53-4-1 FIG. 43A SHEET 1 ITEM (N), SRM 51-2-0 FIG. 50 (SHEET 72B), DC-8 SRM 53-2-2 FIG. 10 TR NR 53-193, TR NR 53-153, NDT SPM PART 08-00-02 TO 07, SRM 53-2-2 PAGE 2 OF 2 FIG. 10 (SHEET 4), SRM 51-1-8B, SRM 51-1-11, SRM 51-1-20D, . SRM 51-1-20D, AND SRM 51-3-1.
Part: SKIN — MISREPAIRED (ZONE 100) · airframe 96,561 hrs · 25,131 cycles
DURING ROUTINE C-CHECK INSPECTION FOUND NON STANDARD REPAIR AT BS 1400 BETWEEN LONGERON 31 RIGHT AND LONGERON 30 RIGHT. REMOVED EXISTING NON STANDARD REPAIR. REMOVED DAMAGED AREA. PERFORMED NDT INSPECTION. FABRICATED REPAIR DOUBLER AND FILLER. CLEANED, TREATED AND PRIMED AREA AND REPAIR PARTS. APPLIED SEALANT TO FAYING SURFACES. INSTALLED REPAIR PARTS DC-8 SRM 51-1-20D, DC-8 SRM 51-3-1, DC-8 SRM 51-1-21, DC-8 NDT SPM PART 06-10-01-001, DC-8 SRM 51-1-8B, DC-8 SRM 51-1-11, SEMAN DRAWING NUMBER ED 4303 DATED 08-03-06, AND SEMAN ENGINEERING ORDER NUMBER 2006665 DATE 08-15-06. COMPLETED FAA FORM 8110-3 DATED 08-15-06.
Part: SKIN — CRACKED (BS 1746) · airframe 96,561 hrs · 25,131 cycles
DURING ROUTINE C-CHECK INSPECTION FOUND EXTERNAL FUSELAGE SKIN CRACKED. AT STATION 1746.000, BETWEEN LONGERON 14 LT AND LONGERON 15 LT. REMOVED FASTENERS. REMOVED DAMAGED AREA. FABRICATED EXTERNAL REPAIR DOUBLER (AL 7075 T6 0.071) AND INTERNAL FINGER DOUBLERS (AL 7075 T6 0.040â), AND FILLER (AL 7075 T6 0.063). CLEANED, TREATED AND PRIMED AREA AND REPAIR PARTS. APPLIED SEALANT TO FAYING SURFACES. INSTALLED REPAIR PARTS IAW SRM 53-2-1 FIG. 7, SHEETS 1, AND 3, SRM 51-1-21, SRM 51-1-20D, SRM 51-3-1, SRM 51-1-20D, SRM 53-5-3 FIG. 1 ITEM (D), SRM 51-1-8B, AND SRM 51-1-11.
Part: LONGERON — CRACKED (ZONE 100) · airframe 96,561 hrs · 25,131 cycles
DURING ROUTINE C-CHECK INSPECTION FOUND LONGERON 35 RT CRACKED AT STA 1350.000. REMOVED FASTENERS IAW SRM 51-1-20D. REMOVED CRACKED LONGERON SEGMENT. FABRICATED NEW LONGERON FROM EXTRUSION P/N 2641455/ 7075 T651. FABRICATED SPLICE. PERFORMED NDT INSPECTION. CLEANED, TREATED AND PRIMED AREA AND REPAIR PARTS. APPLIED SEALANT TO FAYING SURFACES INSTALLED REPAIR PARTS. SRM 53-2-2 FIG.4A, SRM 53-2-2 FIG. 10 TR NR 53-153, TR NR 53-193, SRM 51-1-20D, SRM 51-3-1, MFG MESSAGE 1-214355818-2 DATE 07-27-06, SRM 53-4-1 FIG. 43A (SHEET 2) ITEM (K), SRM 51-2-0 FIG. 50 (SHEET 62), NDT PART 08-00-02 TO 07, SRM 53-2-2 PAGE 2 OF 2 FIG. 10 (SHEET 4) GENERAL NOTES NR 22, SRM 51-1-8B, AND SRM 51-1-11.
Part: LONGERON — CRACKED (ZONE 100) · airframe 96,561 hrs · 25,131 cycles
DURING ROUTINE C-CHECK INSPECTION FOUND LONGERON 36 CRACKED AT STATION 1350.000. REMOVED FASTENERS. TRIMMED OUT CRACKED LONGERON SEGMENT. FABRICATED NEW LONGERON FROM EXTRUSION P/N 2641455, (AL 7075 T651). FABRICATED SPLICE (AL 7075 T651). PERFORMED NDT INSPECTION. CLEANED, TREATED AND PRIMED AREA AND REPAIR PARTS. APPLIED SEALANT TO FAYING SURFACES. INSTALLED REPAIR PARTS IAW BOEING MESSAGE 1-214355818-2 DATE 07-27-06, DC-8 SRM 53-2-2 FIG 4A, DC-8 SRM 51-1-20D, DC-8 SRM 53-4-1 FIG 43A SHEET 2 ITEM -K-, DC-8 SRM 51-2-0 FIG 50 SHEET 62, DC-8 SRM 53-2-2 FIG 10 TR 53-193, TR 53-153, DC-8 NDT SPM PART 08-00-02 TO 07, DC-8 SRM 53-2-2 PAGE 2 OF 2 FIG 10 (SHEET 4), DC-8 SRM 51-1-8B, DC-8 SRM 51-1-11, AND DC-8
Part: FITTING — CRACKED (FUSELAGE) · airframe 96,561 hrs · 25,131 cycles
DURING ROUTINE C CHECK INSPECTION, FOUND LONGERON 19 RT FITTING CRACKED AT STATION STA 822.500. REMOVED CRACKED END FITTING IAW SRM 51-1-20D. FABRICATED NEW END FITTING (AL PLATE 7075-T651) IAW ATI REPAIR SPECIFICATION NR 2003-05, MFG DRAWING NR 4751640. PERFORMED NDT INSPECTION IAW NDT SPM PART 08-00-02 TO 07. CLEANED, TREATED AND PRIMED AREA AND END FITTING IAW SRM 51-1-8B. INSTALLED END FITTING IAW SRM 51-1-20D, SRM 51-3-1.
Part: TORQUE TUBE — WORN (CONTROL COLUMN) · airframe 96,561 hrs · 25,131 cycles
DURING ROUTINE C CHECK INSPECTION FOUND CONTROL COLUMN TORQUE TUBE WITH DEEP WEAR. REPLACED DAMAGED TORQUE TUBE. CLEANED, TREATED AND PRIMED AREA. IAW SRM 51-1-21, SRM 51-1-20D. SRM 51-1-8B. SRM 51-1-21, SRM 51-1-20D, SRM 51-3-1, AND SRM 27-267 REV. 2 DATE 01-20-88.
Part: FITTING — CRACKED (ZONE 200) · airframe 96,561 hrs · 25,131 cycles
DURING ROUTINE C-CHECK INSPECTION FOUND A CRACKED FITTING AT STATION 978.000 LONGERON 18 RT. REMOVED DAMAGED FITTING. CLEANED, TREATED AND PRIMED AREA. INSTALLED NEW FITTING IAW SRM 51-3-0, SRM 51-3-1, AND SRM 51-3-0.
Part: LONGERON — CORRODED (BS 200-180) · airframe 96,561 hrs · 25,131 cycles
DURING ROUTINE C-CHECK INSPECTION FOUND LONGERON 36 CORRODED FROM BS 200-180. REMOVED CORROSION. FOUND OUT OF LIMITS. REMOVED CORRODED SPLICE FITTING. FABRICATED NEW SPLICE FITTING (AL 7075 O 0.071). HEAT TREATED 7075 O TO 7075 T6. CLEANED, TREATED AND PRIMED SPLICE FITTING. INSTALLED SPLICE FITTING IAW DC-8 SRM 51-1-20D, DC-8 SRM 51-3-1, DC-8 SRM 51-1-8 PAGES 17-18, DC-8 SRM 53-2-0 PAGE 2P, DC-8 SRM 51-1-20D, DC-8 SRM 53-4-1 FIG 28 ITEM N, DC-8 SRM 51-1-1 PAGES 1, 13, 17, AND DC-8 SRM 51-1-8B.
Part: BULKHEAD — CORRODED (ZONE 200) · airframe 96,561 hrs · 25,131 cycles
DURING ROUTINE C-CHECK INSPECTION FOUND HORIZONTAL PRESSURE WALL CORRODED AT STATION -12.000 LBL 50. REMOVED FASTENERS. REMOVED CORROSION, FOUND OUT OF LIMITS. REMOVED DAMAGED AREA. PERFORMED NDT INSPECTION NO CRACKS OR CORROSION FOUND AFTER DAMAGE REMOVED. FABRICATED NEW PANEL SEGMENT (AL 2024 T3 0.050â), EXTERNAL REPAIR DOUBLER (AL 2024 T3 0.063â) AND INTERNAL REPAIR FINGER DOUBLER (AL 2024 T3 0.032â). CLEANED, TREATED, PRIMED AREA AND REPAIR PARTS. APPLIED SEALANT TO FAYING SURFACES. INSTALLED REPAIR PARTS IAW SRM 51-1-21, SRM 51-1-20D, SRM 51-3-1, DRAWING NR ED 4302, DATE 07-31-06, EO NR 2006645, SRM 51-1-21, SRM 51-1-20D, SRM 51-3-0, SRM 51-1-8, SRM 53-2-0 PAGE 2P, NDT SPM PART 06-10-01-001, SRM 51-1-8B,
Part: SKIN — CRACKED (ZONE 800) · airframe 96,561 hrs · 25,131 cycles
DURING ROUTINE C-CHECK INSPECTION FOUND LEFT HAND PASSENGER DOOR LOWER AREA CRACKED AT STATION 35.000. REMOVED FASTENERS IAW DC-8 SRM 51-1-21, REMOVED DAMAGED AREA. FABRICATED REPAIR DOUBLER AND FILLER (AL 7075 T6 0.050â) IAW DC-8 SRM 52-2-0 FIG 4, (SHEET 3), DC-8 SRM 52-3-1 FIG 1 ITEM L, DC-8 SRM 51-9-0 FIG 68A. CLEANED, TREATED AND PRIMED REPAIR AREA AND REPAIR PARTS IAW DC-8 SRM 51-1-8B. APPLIED SEALANT TO FAYING SURFACES IAW DC-8 SRM 51-1-11. INSTALLED REPAIR PARTS IAW DC-8 SRM 52-2-0 FIG 4 SHEET 3, DC-8 SRM 51-1-21.
Part: SKIN — NICKED (T/E FLAP) · airframe 96,561 hrs · 25,131 cycles
DURING ROUTINE C CHECK INSPECTION FOUND LT WING IB FLAP UPPER SKIN REPAIR NICKED AT STATION XW104.000. REMOVED DAMAGED SKIN IAW SRM 51-1-0 PAGE 1, SRM 51-1-21. FABRICATED NEW SKIN (AL 2024 T3 0.040â) CLEANED, TREATED AND PRIMED AREA AND SKIN INTERNAL SURFACE, IAW SRM 51-1-8B. APPLIED SEALANT TO FAYING SURFACES, IAW SRM 51-1-11. INSTALLED PLATING. IAW SRM 51-1-21, AND SRM 57-7-1 FIG. 1.
Part: SKIN — CORRODED (ZONE 500) · airframe 96,561 hrs · 25,131 cycles
DURING ROUTINE C-CHECK INSPECTION FOUND LT WING IB LEADING EDGE UPPER SKIN WITH CORROSION AROUND FASTENERS FROM STA XFS7.500 TO STA XFS13.750. REMOVED CORROSION, FOUND OUT OF LIMITS FABRICATED REPAIR DOUBLER (AL 7075 T6 0.125â). CLEANED, TREATED AND PRIMED AREA AND REPAIR DOUBLER INTERNAL SURFACE. APPLIED SEALANT TO FAYING SURFACES. INSTALLED REPAIR PARTS IAW SRM 57-2-1 FIG. 37, SRM 51-3-0, SRM 51-1-21, SRM 51-1-20D, SRM 51-3-1, SRM 51-1-8 PAGES 17-18, SRM 57-2-1 FIG. 37, SRM 57-2-1 FIG. 37 NOTE 6, AND 7, SRM 51-1-8B, AND SRM 51-1-11.
Part: SKIN — MISREPAIRED (RT AILERON) · airframe 96,561 hrs · 25,131 cycles
DURING ROUTINE C-CHECK INSPECTION FOUND RIGHT HAND INBOARD AILERON LOWER SKIN HAS NON STANDARD REPAIR BETWEEN STATIONS XA 578.000 AND XA 603.000. REMOVED SKIN WITH NON STANDARD REPAIR. FABRICATED NEW SKIN (AL 2024 T3 0.025) AND DOUBLER (AL 2024 T3 0.020). BONDED BOTH PARTS WITH HYSOL. CLEANED, TREATED AND PRIMED AREA AND NEW SKIN INTERNAL SURFACE. APPLIED SEALANT TO FAYING SURFACES. INSTALLED NEW SKIN IAW DC-8 SRM 51-1-21, DC-8 SRM 57-8-1 FIG 4, DC-8 SRM 57-1-0 PAGE 1, DC-8 SRM 51-1-21, DC-8 SRM 57-8-1 FIG 4 ITEM B, K, DC-8 SRM 51-1-9, DC-8 SRM 51-1-8B, AND DC-8 SRM 51-1-11.
Part: SKIN — MISREPAIRED (ZONE 300) · airframe 96,561 hrs · 25,131 cycles
DURING ROUTINE C-CHECK INSPECTION FOUND LT. ELEVATOR UPPER SKIN HAS A NON STANDARD REPAIR AT STATION XE312.500. REMOVED SKIN WITH EXISTING NON STANDARD REPAIR. FABRICATED NEW SKIN AND FINGER DOUBLER (AL 2024 T3 0.016â). BONDED BOTH PARTS WITH HYSOL. CLEANED, TREATED AND PRIMED AREA AND NEW SKIN INTERNAL SURFACE. APPLIED SEALANT TO FAYING SURFACES. INSTALLED PANEL PLATING. PERFORMED LT ELEVATOR BALANCING IAW SRM 51-4-4 PAGES 1-4. FOUND WITH TOLERANCE (MOMENT : 1461.40 IN-LBS). IAW SRM 55-4-1 FIG. 1, SRM 55-1-0 PAGE 1, SRM 51-1-21, SRM 55-4-1 FIG. 1 SHEET 1, AND 2 ITEM (E) AND (F), SRM 51-1-4, SRM 51-1-8B, SRM 51-1-11, AND SRM 51-1-21.
Part: SKIN — DENTED (ZONE 300) · airframe 96,561 hrs · 25,131 cycles
DURING ROUTINE C-CHECK INSPECTION FOUND LT ELEVATOR UPPER SKIN DENTED FROM STATION XE74.469 TO STATION XE104.031. REMOVED DAMAGED SKIN. FABRICATED NEW SKIN AND FINGER DOUBLER WITH (AL 2024 T3 0.016â). BONDED BOTH PARTS WITH HYSOL. CLEANED, TREATED AND PRIMED AREA AND NEW SKIN INTERNAL SURFACE. APPLIED SEALANT TO FAYING SURFACES. INSTALLED NEW SKIN. IAW SRM 51-1-21, SRM 55-4-1 FIG. 1, AND 2, SRM 55-1-0 PAGE 1, SRM 51-1-21, SRM 55-4-1 FIG. 1 SHEET 1, AND 2 ITEM (E) AND (F), SRM 51-1-9,SRM 51-1-8B, AND SRM 51-1-11.
Part: SKIN — NICKED (ZONE 500) · airframe 96,561 hrs · 25,131 cycles
DURING ROUTINE C-CHECK INSPECTION FOUND LT WING OB FLAP LOWER SKIN TRAILING EDGE SKIN NICKED BETWEEN STATIONS XF415.000 AND XF435.000. REMOVED DAMAGED SKIN. FABRICATED NEW SKIN (AL 2024 T3 0.025â) AND DOUBLER (AL 2024 T3 0.020â). BONDED BOTH PARTS WITH HYSOL. CLEANED, TREATED AND PRIMED AREA AND NEW SKIN. APPLIED SEALANT TO FAYING SURFACES. INSTALLED NEW SKIN IAW SRM 51-1-21, SRM 57-7-1 FIG. 4 T.R. NR 57-94 DATE 10-01-02, SRM 57-1-0 PAGE 1, SRM 51-1-21, SRM 57-7-1 FIG. 4 ITEM U, Q, SRM 51-1-9, SRM 51-1-8B, SRM 51-1-11.
Part: SKIN — DAMAGED (ZONE 500) · airframe 96,561 hrs · 25,131 cycles
DURING ROUTINE C-CHECK INSPECTION FOUND LT WING OB LEADING EDGE LOWER SKIN HOLES AND DENTED, AT STATION XFS710.000. REMOVED FASTENERS. REMOVED DAMAGED AREA. PERFORMED NDT INSPECTION NO CRACKS OR CORROSION FOUND. FABRICATED REPAIR DOUBLER, AND FILLERS.050). CLEANED, TREATED AND PRIMED AREA, SKIN FILLER, AND REPAIR DOUBLER INTERNAL SURFACE. APPLIED SEALANT TO FAYING SURFACES. INSTALLED REPAIR PARTS IAW SRM 51-1-21, SRM 51-3-0, SRM 51-1-20D, SRM 51-3-1, SRM 51-1-11, SRM 51-1-8B, SRM 51-1-21, DC-8 NDT SPM PART 06-10-01-001,COMPLETED FAA FORM 8110-3 NUMBER 06361 DATED 08-03-06, DRAWING NR ED 4288 DATED 07-25-06, EO NR 2006596 DATED 08-03-06.
Part: SKIN — CRACKED (ZONE 500) · airframe 96,561 hrs · 25,131 cycles
DURING ROUTINE C-CHECK INSPECTION, FOUND LT WING UPPER SKIN CRACKED, AT STATION 69.500. REMOVED FASTENERS. REMOVED DAMAGED AREA. PERFORMED NDT INSPECTION, NO CRACKS OR CORROSION FOUND AFTER DAMAGE REMOVED. FABRICATED DOUBLER, FILLER, HEAT TREATED DOUBLER. CLEANED, TREATED, PRIMED AREA AND REPAIR PARTS. APPLIED SEALANT TO FAYING SURFACES. INSTALLED REPAIR PARTS IAW SRM 57-2-1, SRM 51-1-20D, SRM 51-3-1, IAW NDT SPM PART 08-00-02 TO 07, SRM 57-3-3, SRM 51-10-0, IAW SRM 51-1-1, IAW SRM 51-1-8B, IAW SRM 51-1-11.
Part: SKIN — MISREPAIRED (ZONE 200) · airframe 96,561 hrs · 25,131 cycles
DURING ROUTINE C-CHECK INSPECTION FOUND EXTERNAL FUSELAGE FORWARD PASSENGER DOOR UPPER CORNER HAS NON STANDARD REPAIR. REMOVED EXISTING NON STANDARD REPAIR. PERFORMED NDT INSPECTION NO CRACKS OR CORROSION FOUND. FABRICATED REPAIR DOUBLER (AL 7075 T6 0.063), AND REPAIR TRIPLER (AL 7075 T6 0.080â). CLEANED, TREATED AND PRIMED AREA AND REPAIR PARTS. APPLIED SEALANT TO FAYING SURFACES. INSTALLED REPAIR PARTS IAW SRM 51-1-21, SRM 51-3-0, SRM 51-1-11, SRM 51-1-8B, SRM 51-1-20D, NDT SPM PART 06-10-01-001, AD 2000-20-08, S/B DC-8 53-075, MFG DRAWINGS NRS SR08530021, AND 5750776.
Part: SKIN — DAMAGED (ZONE 600) · airframe 96,561 hrs · 25,131 cycles
DURING ROUTINE C-CHECK INSPECTION FOUND RT WING IB LEADING EDGE IB SLOT UPPER SKIN HOLES ELONGATED, AT STATION XS250.089. REMOVED FASTENERS. REMOVED DAMAGED AREA. PERFORMED NDT INSPECTION, NO CRACKS, OR CORROSION FOUND. FABRICATED REPAIR DOUBLER, INTERNAL DOUBLER, AND FILLER. CLEANED, TREATED AND PRIMED AREA, FILLER, INTERNAL DOUBLER, AND REPAIR DOUBLER INTERNAL SURFACE. APPLIED SEALANT TO FAYING SURFACES. INSTALLED REPAIR PARTS. IAW SRM 51-1-20D, SRM 51-3-1, COMPLETED FAA FORM 8110-3 NR 06340 DATED 07-25-06, DRAWING NR ED 4296 DATED 07-22-06, EO NR 2006610 DATE 07-25-06, SRM 51-1-21, SRM 51-3-0, NDT SPM PART 06-10-01-001, SRM 51-1-8B, SRM 51-1-11.
Part: SKIN — DAMAGED (ZONE 600) · airframe 96,561 hrs · 25,131 cycles
DURING ROUTINE C-CHECK INSPECTION FOUND RT WING CENTER LEADING EDGE OB SLOT UPPER SKIN HOLES ELONGATED AT STATION XOLDI6.225. REMOVED FASTENERS. REMOVED DAMAGED AREA. PERFORMED NDT INSPECTION NO CRACKS OR CORROSION FOUND AFTER DAMAGE REMOVAL. FABRICATED REPAIR DOUBLER, INTERNAL DOUBLER, AND FILLER. CLEANED, TREATED AND PRIMED AREA, FILLER, INTERNAL SURFACE OF REPAIR DOUBLER, AND INTERNAL DOUBLER. APPLIED SEALANT TO FAYING SURFACES. INSTALLED REPAIR PARTS IAW SRM 51-1-21, SRM 51-3-0, SRM 51-1-20D, SRM 51-3-1, NDT SPM PART 06-10-01-001, SRM 51-1-8B, SRM 51-1-11, DRAWING NR ED 4297 DATE 07-24-06, ENGINEERING ORDER NR 2006611 DATE 07-25-06. COMPLETED FAA FORM 8110-3 NUMBER 06340 DATED 07-25-06.
Part: SKIN — MISREPAIRED (ZONE 600) · airframe 96,561 hrs · 25,131 cycles
DURING ROUTINE C-CHECK INSPECTION FOUND RT WING CENTER LEADING EDGE OB SLOT UPPER SKIN WITH NON STANDARD REPAIR AT STA XS520.168. REMOVED EXISTING REPAIR. REMOVED DAMAGED AREA. PERFORMED NDT INSPECTION, NO CRACKS OR CORROSION FOUND AFTER DAMAGE REMOVED. FABRICATED REPAIR DOUBLER (AL 7075 T6 0.071), INTERNAL DOUBLER, AND FILLER (AL 7075 T6 0.063). CLEANED, TREATED AND PRIMED AREA, INTERNAL DOUBLER, FILLER, AND REPAIR DOUBLER INTERNAL SURFACE. APPLIED SEALANT TO FAYING SURFACES. INSTALLED REPAIR PARTS. IAW DRAWING NR ED 4298 DATED 07-25-06, SRM 51-1-21, SRM 51-3-0, SRM 51-1-20D, SRM 51-3-1, NDT SPM PART 06-10-01-001, SRM 51-1-8B, AND SRM 51-1-11. COMPLETED FAA FORM 8110-3 NR 06341 DATED 07-25-06.
Part: FRAME — CRACKED (FUSELAGE) · airframe 96,561 hrs · 25,131 cycles
DURING ROUTINE C-CHECK INSPECTION FOUND FRAME CRACKED AT STATION 55.000, LONGERON 24 RIGHT. REMOVED EXISTING REPAIR DOUBLER IAW SRM 51-1-21 (XFS 591.250). REMOVED CORROSION (XFS 566.250 â XFS 578.750) IAW SRM 51-1-8 PAGES 17-18. FOUND OUT OF LIMITS IAW SRM 57-2-1 FIG 2G. REMOVED DAMAGED AREA IAW SEMAN DRAWING ED 4287. PERFORMED NDT INSPECTION IAW DC-8 NDT SPM PART 06-10-01-001, NO CRACKS OR CORROSION FOUND. FABRICATED REPAIR DOUBLER (AL 7075 T6 0.063) AND SKIN FILLERS (AL 7075 T6 0.050â) IAW SEMAN DWG NUMBER EO 4287. CLEANED, TREATED AND PRIMED AREA, SKIN FILLER, AND REPAIR DOUBLER INTERNAL SURFACE IAW SEMAN ENGINEERING ORDER NUMBER 2006595 DATED 08-01-06, SRM 51-1-8B. APPLIED SEALANT TO FAYING SURFACE
Part: SKIN — NICKED (T/E FLAP) · airframe 96,561 hrs · 25,131 cycles
DURING ROUTINE C-CHECK INSPECTION FOUND LEFT HAND WING OUTBOARD FLAP LOWER SKIN NICKED FROM STATION XF 415.000 TO STATION XF 425.000. REMOVED DAMAGED SKIN IAW DC-8 SRM 57-1-0 PAGE 1, DC-8 SRM 51-1-21. FABRICATED NEW SKIN (AL 2024 T3 0.032â) AND DOUBLER (AL 2024 T3 0.020â) IAW DC-8 SRM 57-7-1 FIG 4 ITEM P, Q. BONDED BOTH PARTS WITH HYSOL IAW DC-8 SRM 51-1-9. CLEANED, TREATED AND PRIMED AREA AND PANEL SKIN INTERNAL SURFACE IAW DC-8 SRM 51-1-8B. APPLIED SEALANT TO FAYING SURFACES IAW DC-8 SRM 51-1-11. INSTALLED PANEL SKIN IAW DC-8 SRM 51-1-21.
Part: SKIN — CORRODED (FUSELAGE) · airframe 96,561 hrs · 25,131 cycles
DURING ROUTINE C-CHECK INSPECTION FOUND EXTERNAL FUSELAGE SKIN CORRODED AT STATION 902.000 LONGERON 13 RIGHT. REMOVED FASTENERS IAW DC-8 SRM 51-1-21, DC-8 SRM 51-3-0. REMOVED CORROSION IAW DC-8 SRM 51-1-8 PAGES 17-18 FOUND OUT OF LIMITS IAW DC-8 SRM 53-2-0 PAGE 2P. REMOVED DAMAGED AREA IAW SEMAN DRAWING ED 4300. PERFORMED NDT INSPECTION IAW DC-8 NDT SPM PART 06-10-01-001. FABRICATED REPAIR DOUBLER (AL 7075 T6 0.063â), REPAIR TRIPLER (AL 7075 T6 0.071â), AND SKIN FILLER (AL 7075 T6 0.125â) IAW SEMAN DRAWING NUMBER EO 4300. CLEANED, TREATED AND PRIMED REPAIR AREA, AND REPAIR PARTS, IAW DC-8 SRM 51-1-8B. APPLIED SEALANT TO FAYING SURFACES IAW ENGINEERING ORDER SEMAN NUMBER 2006633 DATE 08-03-06, DC-8 SRM 51
Part: SKIN — DENTED (LT WING) · airframe 96,561 hrs · 25,131 cycles
DURING ROUTINE C-CHECK INSPECTION FOUND LEFT HAND OUTER WING, OUTBOARD LEADING EDGE DENTED, FROM STATION XFS 885.000 TO STATION XFS 920.000. REMOVED DAMAGED SKIN IAW DC-8 SRM 57-1-0 PAGE 1, DC-8 SRM 51-1-21, DC-8 SRM 51-3-0. FABRICATED SKIN (AL 7075 T6 0.050â) IAW DC-8 SRM 57-3-3 FIG 8 ITEM A. CLEANED, TREATED AND PRIMED AREA AND SKIN INTERNAL SURFACE IAW DC-8 SRM 51-1-8B. BONDED PLATING WITH INNER DOUBLER IAW DC-8 SRM 51-1-9 (HYSOL) DC-8 SRM 51-1-21, DC-8 SRM 51-3-0, DC-8 SRM 51-3-1, DC-8 SRM 57-3-3 FIG 8.
Part: SKIN — MISREPAIRED (RT ELEVATOR) · airframe 96,561 hrs · 25,131 cycles
DURING ROUTINE C CHECK INSPECTION FOUND RIGHT HAND ELEVATOR LOWER SKIN WITH NON STANDARD REPAIR AT STATION XE39.188. REMOVED FASTENERS IAW SRM 51-1-21. REMOVED DAMAGED AREA. FABRICATED NEW REPAIR, AND FILLERS (AL 2024 T3 0.016â) IAW SRM 55-2-1 FIG. 11 (SHEET 4, 6, 9), SRM 55-4-1 FIG. 1 (SHEET 1, 2) ITEM E AND F. BONDED BOTH PART WITH HYSOL IAW SRM 51-1-9. CLEANED, TREATED AND PRIMED AREA , AND NEW REPAIR INTERNAL SURFACE IAW SRM 51-1-8B. INSTALLED REPAIR PARTS IAW SRM 55-2-1 FIG. 11 (SHEET 4, 6, 9, 11)., SRM 51-1-21, SRM 55-2-1 FIG. 11.
Part: SKIN — MISREPAIRED (ZONE 300) · airframe 96,561 hrs · 25,131 cycles
DURING ROUTINE C-CHECK INSPECTION FOUND LT ELEVATOR LOWER SKIN WITH A NON STANDARD REPAIR FROM STA XE55.062 TO STA XE60.125. REMOVED SKIN WITH EXISTING NON STANDARD REPAIR. FABRICATED NEW SKIN AND FINGER DOUBLER WITH (AL 2024 T3 0.016). BONDED BOTH PARTS WITH HYSOL. CLEANED, TREATED AND PRIMED AREA AND NEW SKIN INTERNAL SURFACE. APPLIED SEALANT TO FAYING SURFACES. INSTALLED NEW SKIN IAW SRM 51-1-21, SRM 55-4-1 FIG. 1 SHEET 1, AND 2, SRM 57-1-0 PAGE 1, SRM 55-4-1 FIG. 1, SHEET 1, AND 2 ITEM (E) AND (F), SRM 51-1-9, SRM 51-1-8B, SRM 51-1-11.
Part: PANEL — DENTED (LT WING) · airframe 96,561 hrs · 25,131 cycles
DURING ROUTINE C CHECK INSPECTION, FOUND LT WING IB UPPER PANEL DENTED, AT STATION XW40.000. REMOVED DAMAGED SKIN IAW SRM 57-1-0 PAGE 1, SRM 51-1-21. FABRICATED SKIN WITH (AL 2024 T3 0.025) AND BONDED DOUBLER (AL 2024 T3 0.020) IAW SRM 57-7-1 FIG. 1 ITEM A, L, SRM 57-7-1 PAGE 1. BONDED BOTH PARTS WITH HYSOL IAW SRM 51-1-9. CLEANED, TREATED AND PRIMED INTERNAL SURFACE. IAW SRM 51-1-8B. APPLIED SEALANT TO FAYING SURFACES IAW SRM 51-1-11. INSTALLED NEW SKIN, IAW SRM 51-1-21.
Part: SKIN — CORRODED (LT WING) · airframe 96,561 hrs · 25,131 cycles
DURING ROUTINE C-CHECK INSPECTION FOUND LT WING OB LEADING EDGE LOWER SKIN CORRODED FROM STA XFS566.250 TO STA XFS578.750. REMOVED EXISTING REPAIR DOUBLER IAW SRM 51-1-21 (XFS591.250). REMOVED CORROSION IAW SRM 51-1-8 PAGES 17-18. FOUND OUT OF LIMITS IAW SRM 57-2-1 FIG. 2G. REMOVED DAMAGED AREA IAW DRWG ED 4287. PERFORMED NDT INSPECTION IAW NDT SPM PART 06-10-01-001 NO CRACKS OR CORROSION FOUND. FABRICATED REPAIR DOUBLER (AL 7075 T6 0.063) AND FILLERS (AL 7075 T6 0.050) IAW DWG NR 4287. CLEANED, TREATED AND PRIMED AREA AND SKIN FILLER AND REPAIR DOUBLER INTERNAL SURFACE, IAW SRM 51-1-8B. APPLIED SEALANT TO FAYING SURFACES IAW SRM 51-1-11. INSTALLED REPAIR PARTS IAW DRAWING NR ED 4287, SRM 51-1-21, SRM 51-3-0, S
Part: REPAIR — MISREPAIRED (ZONE 500) · airframe 96,561 hrs · 25,131 cycles
DURING ROUTINE C-CHECK INSPECTION FOUND LEFT HAND WING INBOARD LEADING EDGE UPPER SKIN WITH A NON STANDARD REPAIR AT STATION XCW69.00. REMOVED EXISTING REPAIR, IAW DC-8 SRM 51-1-21, DC-8 SRM 51-3-0. FABRICATED REPAIR DOUBLER (AL 7075 T6 0.071) IAW SEMAN DRAWING NUMBER ED 4299. CLEANED AND APPLIED POLYURETHANE TOP-COATING IAW DC-8 SRM 51-1-12 PAGES 7-25. APPLIED SEALANT TO FAYING SURFACES IAW DC-8 SRM 51-1-11. INSTALLED REPAIR PARTS IAW SEMAN DRAWING ED 4299, DC-8 SRM 51-1-21, DC-8 SRM 51-3-0, DC-8 SRM 51-1-20D, DC-8 SRM 51-3-1. SEMAN EO NUMBER 2006630 DATE 08-03-06. FAA FORM 8110-3 NUMBER 06361 DATED 08-03-06 COMPLETED.
Part: SKIN — MISREPAIRED (ZONE 600) · airframe 96,561 hrs · 25,131 cycles
DURING ROUTINE C-CHECK INSPECTION FOUND RIGHT HAND WING OUTBOARD LEADING EDGE INTERNAL SURFACE UPPER SKIN WITH A NON STANDARD REPAIR FROM STATION XFS 560.000 TO STATION XFS 622.500. REMOVED EXISTING REPAIR IAW DC-8 SRM 57-1-0 PAGE 1, DC-8 SRM 51-1-21. FABRICATED NEW SKIN, (AL 2024 T3 0.025) AND DOUBLER (AL 2024 T3 0.020) IAW DC-8 SRM 57-7-1 FIG 4 ITEM U, Q. BONDED BOTH PARTS WITH HYSOL IAW DC-8 SRM 51-1-9. CLEANED, TREATED AND PRIMED REPAIR AREA AND NEW SKIN IAW DC-8 SRM 51-1-8B. APPLIED SEALANT TO FAYING SURFACES IAW DC-8 SRM 51-1-11. INSTALLED PANEL SKIN IAW DC-8 SRM 51-1-21
Part: SKIN — MISREPAIRED (ZONE 500) · airframe 96,561 hrs · 25,131 cycles
DURING ROUTINE C-CHECK INSPECTION FOUND LEFT HAND WING CENTER LEADING EDGE UPPER SKIN WITH NON STANDARD REPAIR FROM STATION XFS 360.250 TO STATION XFS 410.250. REMOVED EXISTING REPAIR IAW DC-8 SRM 51-1-20D. REMOVED DAMAGED AREA. FABRICATED REPAIR DOUBLER (AL 7075 T6 0.063) IAW DC-8 SRM 57-2-1 FIG 44 (SHEET 1-8), DC-8 SRM 57-3-3 FIG 5 (SHEET 1) ITEM A. CLEANED, TREATED AND PRIMED REPAIR AREA, AND REPAIR DOUBLER INTERNAL SURFACE IAW DC-8 SRM 51-1-8B. APPLIED SEALANT TO FAYING SURFACES IAW DC-8 SRM 51-1-11. INSTALLED REPAIR DOUBLER IAW DC-8 SRM 57-2-1 FIG 44 TR 57-102 (SHEET 1, 5, 6, 8) DC-8 SRM 51-1-21, DC-8 SRM 51-1-20D, DC-8 SRM 51-3-1.
Part: SKIN — MISREPAIRED (ZONE 300) · airframe 96,561 hrs · 25,131 cycles
DURING ROUTINE C-CHECK INSPECTION FOUND RIGHT HAND HORIZONTAL STABILIZER OUTBOARD LEADING EDGE WITH NON STANDARD REPAIR FROM STATION XFS 272.150 TO STATION XFS 285.000. REMOVED NON STANDARD REPAIR IAW DC-8 SRM 51-1-21, TRIMMED OUT DAMAGED AREA AND FABRICATED REPAIR DOUBLER AND FILLER (AL 7075 T6 0.050â) IAW DC-8 SRM 5-2-1 FIG 4, DC-8 SRM 55-3-1 FIG 1 (SHEET 1-2) ITEM-A. CLEANED, TREATED AND PRIMED REPAIR AREA, FILLER, AND REPAIR DOUBLER INTERNAL SURFACE IAW DC-8 SRM 51-1-8B. APPLIED SEALANT TO FAYING SURFACES IAW DC-8 SRM 51-1-11. INSTALLED REPAIR PARTS IAW DC-8 SRM 55-2-1 FIG 4, DC-8 SRM 51-1-21A, DC-8 SRM 51-1-21.
Part: SKIN — CORRODED (ZONE 600) · airframe 96,561 hrs · 25,131 cycles
DURING ROUTINE C-CHECK INSPECTION FOUND RIGHT HAND WING INBOARD LEADING EDGE UPPER SKIN CORRODED FROM STATION XW5.000 TO STATION XW22.000. REMOVED FASTENERS IAW DC-8 SRM 51-1-21, DC-8 SRM 51-3-0. REMOVED CORROSION IAW DC-8 SRM 1-1-8 FOUND OUT OF LIMITS. REMOVED DAMAGED AREA. FABRICATED EXTERNAL REPAIR DOUBLER (AL 7075 T6 0.125â) IAW DC-8 SRM 57-2-1 FIG 37. CLEANED AREA AND APPLIED POLYURETHANE TOP COATING ON EXTERNAL REPAIR DOUBLER INTERNAL SURFACE IAW DC-8 SRM 51-1-21. APPLIED SEALANT TO FAYING SURFACES IAW DC-8 SRM 51-1-12. INSTALLED EXTERNAL REPAIR DOUBLER IAW DC-8 SRM 57-25-1 FIG 37, DC-8 SRM 51-1-21, DC-8 SRM 51-3-0, DC-8 SRM 51-1-20D, DC-8 SRM 51-3-1.
Part: SKIN — DENTED (ZONE 300) · airframe 96,561 hrs · 25,131 cycles
DURING ROUTINE C-CHECK INSPECTION FOUND RT HORIZONTAL STABILIZER OB LEADING EDGE DENTED FROM STA XFS222.500, TO STA XFS241.250. REMOVED FASTENERS IAW SRM 51-1-21, SRM 51-1-21A. TRIMMED OUT DAMAGED AREA AND FABRICATED REPAIR DOUBLER , AND FILLER (AL 7075 T6 0.050â) IAW SRM 5-2-1 FIG. 4, SRM 55-3-1 FIG. 1. (SHEET 1-2) ITEM (A). CLEANED, TREATED AND PRIMED REPAIR AREA, FILLER, AND REPAIR DOUBLER INTERNAL SURFACE, IAW SRM 51-1-8B. APPLIED SEALANT TO FAYING SURFACES IAW SRM 51-1-11. INSTALLED REPAIR PARTS IAW SRM 55-2-1 FIG. 4, SRM 51-1-21A, SRM 51-1-21.
Part: SKIN — MISREPAIRED (ELEVATOR) · airframe 96,561 hrs · 25,131 cycles
DURING ROUTINE C-CHECK INSPECTION FOUND LT ELEVATOR LOWER SKIN WITH A NON STANDARD REPAIR FROM STA XE301.656 TO STA XE312.500. REMOVED SKIN WITH EXISTING NON STANDARD REPAIR. FABRICATED NEW SKIN AND FINGER DOUBLER WITH (AL 2024 T3 0.016â). BONDED BOTH PARTS WITH HYSOL. CLEANED, TREATED AND PRIMED AREA AND NEW SKIN INTERNAL SURFACE. APPLIED SEALANT TO FAYING SURFACES. INSTALLED NEW SKIN. IAW SRM 55-4-1 FIG. 1 SHEETS 1 AND 2, ITEM (E) AND (F), SRM 55-1-0 PAGE 1, SRM 51-1-21, SRM 51-1-9, SRM 51-1-8B, SRM 51-1-11.
Part: SKIN — MISREPAIRED (LT WING SLAT) · airframe 96,561 hrs · 25,131 cycles
DURING ROUTINE C-CHECK INSPECTION, LT WING OB FLAP UPPER SKIN NO STANDARD REPAIR NEAR XF 169 TO XF 213.000. PERFORMED MAJOR REPAIR IAW SRM 57-7-1 FIG. 4 T.R. 57-94 DATE 10-01-02. REMOVED PANEL PLATING WITH NO STANDARD REPAIR EXISTING IAW SRM 51-1-21. FABRICATED PANEL PLATING WITH PLATING & DOUBLER IAW SRM 57-7-1 FIG. 4 ITEM (P) AND (Q). BONDED BOTH PARTS WITH HYSOL IAW SRM 51-1-4. CLEANED, TREATED AND PRIMED AREA & PANEL PLATING INTERNAL PART IAW SRM 51-1-8B. APPLIED SEALANT TO FAYING SURFACES IAW SRM 51-1-11. INSTALLED PANEL PLATING IAW SRM 51-1-21.
Part: STRUCTURE — MISREPAIRED (HORIZONTAL STAB) · airframe 96,561 hrs · 25,131 cycles
DURING ROUTINE C CHECK INSPECTION, EMPENNAGE RT HORIZONTAL STABILIZER INBD L/E FWD PART WITH NON STANDARD REPAIR, XFS 141.250 - XFS 147.500.
Part: SKIN — MISREPAIRED (ZONE 300) · airframe 96,561 hrs · 25,131 cycles
DURING ROUTINE C-CHECK INSPECTION FOUND RT HORIZONTAL STABILIZER IB LEADING EDGE WITH NON STANDARD REPAIR BETWEEN STATIONS XFS. 172.500, AND STATION 178.750. REMOVED NON STANDARD REPAIR IAW SRM 51-1-21. TRIMMED OUT DAMAGED AREA AND FABRICATED REPAIR DOUBLER AND FILLER (AL 7075 T6 0.050â) IAW SRM 55-2-1 FIG. 4, SRM 55-3-1 FIG. 1. (SHEET 1-2) ITEM (A). CLEANED, TREATED AND PRIMED REPAIR AREA, FILLER, AND REPAIR DOUBLER INTERNAL SURFACE. IAW SRM 51-1-8B. APPLIED SEALANT TO FAYING SURFACES IAW SRM 51-1-11. INSTALLED REPAIR PARTS IAW SRM 55-2-1 FIG. 4, SRM 51-1-21, SRM 55-2-1 FIG. 4.
Part: SKIN — MISREPAIRED (CARGO DOOR) · airframe 96,561 hrs · 25,131 cycles
DURING ROUTINE C-CHECK INSPECTION FOUND D-PIT BELLY DOOR LOWER AFT CORNER HAS A NON STANDARD REPAIR IAW SB 53-078. REMOVED EXISTING SKIN WITH NON STANDARD REPAIR. FABRICATED NEW SKIN. CLEANED, TREATED AND PRIMED AREA AND NEW SKIN. APPLIED SEALANT TO FAYING SURFACES. INSTALLED NEW SKIN IAW DOUGLAS DRAWING NUMBER 5779936, DC-8 SRM 53-4-1 FIG 17A (SHEET 2), DC-8 SRM 51-1-21, DC-8 SRM 51-1-20D, DC-8 SRM 51-3-1, DC-8 SRM 53-4-1 FIG 17A (SHEET 2), DC-8 SRM 53-1-0 PAGE 1, DC-8 SRM 51-1-21, DC-8 SRM 51-1-8B, AND DC-8 SRM 51-1-11.
Part: SKIN — CRACKED (RT WING) · airframe 96,561 hrs · 25,131 cycles
DURING ROUTINE C CHECK INSPECTION, RT WING - PNEU HOLE LWR SKIN CRACKED ¾ APPROX XFS 597.500.
Part: SKIN — CORRODED (ZONE 500) · airframe 96,561 hrs · 25,131 cycles
DURING ROUTINE C-CHECK INSPECTION, FOUND LEFT WING LEADING EDGE UPPER SKIN CORRODED, AT STATION XF 566.250. REMOVED FASTENERS IAW DC-8 SRM 51-1-21. REMOVED CORROSION IAW DC-8 SRM 51-1-8 PAGES 17-18. FOUND OUT OF LIMITS IAW DC-8 SRM 57-2-1 FIG 2G. TRIMMED OUT DAMAGED AREA AND FABRICATED REPAIR DOUBLER (AL 7075 T6 0.063â) AND FILLER (AL 7075 T6 0.050â) IAW DC-8 SRM 57-2-1 FIG 38, DC-8 SRM 57-3-3 FIG 6 SHEET 1 ITEM A. CLEANED, TREATED AND PRIMED AREA, FILLER, AND REPAIR DOUBLER. PRIMED INTERNAL SURFACES IAW DC-8 SRM 51-1-8B. APPLIED SEALANT TO FAYING SURFACES IAW DC-8 SRM 51-1-11. INSTALLED REPAIR PARTS IAW DC-8 SRM 57-2-1 FIG 38 DC-8 SRM 51-1-21, DC-8 SRM 51-1-20D, DC-8 SRM 51-3-1.
Part: SKIN — MISREPAIRED (ZONE 300) · airframe 96,561 hrs · 25,131 cycles
DURING ROUTINE C-CHECK INSPECTION FOUND LEFT HAND HORIZONTAL STABILIZER OUTBOARD LEADING EDGE WITH NON STANDARD REPAIR FROM STATION XFS 178.750 TO STATION XFS 185.000. REMOVED EXISTING REPAIR IAW DC-8 SRM 51-1-21, DC-8 SRM 51-3-0. REMOVED DAMAGED AREA IAW SEMAN DRAWING NUMBER ED 4295 DATED 7/26/06. PERFORMED NDT INSPECTION IAW DC-8 NDT SPM PART 06-10-01-001 NO CRACKS OR CORROSION FOUND AFTER DAMAGE REMOVED. FABRICATED REPAIR DOUBLER, AND SKIN FILLER IAW SEMAN DWG NUMBER ED 4295. CLEANED, TREATED AND PRIMED AREA, SKIN FILLER, AND REPAIR DOUBLER INTERNAL SURFACE IAW DC-8 SRM 51-1-8B. APPLIED SEALANT TO FAYING SURFACES IAW DC-8 SRM 51-1-11. INSTALLED REPAIR PARTS IAW SEMAN DRAWING NUMBER ED 4295 DATE 07-26-
Part: SKIN — MISREPAIRED (ZONE 300) · airframe 96,561 hrs · 25,131 cycles
DURING ROUTINE C-CHECK INSPECTION FOUND LT HORIZONTAL STABILIZER IB LEADING EDGE WITH NON STANDARD REPAIR FROM STATION XFS 110.000 TO STATION XFS 116.250. REMOVED NON STANDARD REPAIR IAW SRM 51-1-21. TRIMMED OUT DAMAGED AREA. FABRICATED REPAIR DOUBLER, AND FILLER, (AL 7075 T6 0.050â) IAW SRM 55-2-1 FIG 4, DC-8 SRM 55-3-1 FIG 1 SHEET 1-2 ITEM -A-. CLEANED, TREATED AND PRIMED AREA, FILLER, AND REPAIR DOUBLER INTERNAL SURFACE IAW SRM 51-1-8B. APPLIED SEALANT TO FAYING SURFACES IAW SRM 51-1-11. INSTALLED REPAIR PARTS IAW SRM 55-2-1 FIG 4, SRM 51-1-21, AND SRM 55-2-1 FIG 4.
Part: REPAIR — IMPROPER (RT WING) · airframe 96,561 hrs · 25,131 cycles
DURING ROUTINE C CHECK INSPECTION, RT WING.- OTBD L/E EXTERNAL PART NON STANDARD REPAIR WITH CHERRY MAX; XFS 603.750 XFS 610.000.
Part: REPAIR — IMPROPER (RT WING) · airframe 96,561 hrs · 25,131 cycles
DURING ROUTINE C CHECK INSPECTION, RT WING. - OTBD L/E EXTERNAL SECTION WITH NON STANDARD REPAIR XFS 872.000 - XFS 885.000.
Part: SKIN — DENTED (HORIZONTAL STAB) · airframe 96,561 hrs · 25,131 cycles
DURING ROUTINE C-CHECK INSPECTION FOUND RT HORIZONTAL STABILIZER IB LEADING EDGE DENTED BETWEEN STA XFS103.750 AND STA XFS128.750. REMOVED FASTENERS. REMOVED DAMAGE. FABRICATED REPAIR PARTS. LOCATED, DRILLED, TRIMMED, TREATED, PRIMED AND INSTALLED REPAIR PARTS. IAW SRM 55-2-1, SRM 51-1-21, SRM 51-1-20D, SRM 55-3-1, SRM 51-1-8, AND 51-1-11.
Part: SKIN — MISREPAIRED (LT WING) · airframe 96,561 hrs · 25,131 cycles
DURING ROUTINE C-CHECK INSPECTION FOUND LT WING SLOT VANE SKIN HAS NON STANDARD REPAIR AT STATION XOLDO 66. REMOVED EXISTING REPAIR IAW SRM 51-1-21, SRM 51-3-0. REMOVED DAMAGED AREA IAW DWG ED 4294 DATE 07-24-06. PERFORMED NDT INSPECTION IAW NDT SPM PART 06-10-01-001 NO CRACKS, OR CORROSION FOUND. FABRICATED REPAIR DOUBLER (AL 7075 T6 0.071) AND INTERNAL DOUBLER (AL 7075 T6 0.063) AND FILLER (AL 7075 T6 0.063) IAW DWG NR EO 4294. CLEANED, TREATED AND PRIMED AREA, FILLER , INTERNAL DOUBLER, AND REPAIR DOUBLER INTERNAL SURFACE IAW SRM 51-1-8B. APPLIED SEALANT TO FAYING SURFACES IAW SRM 51-1-11. INSTALLED REPAIR PARTS IAW NR ED 4294, EO NR 2006603 DATE 07-25-06, SRM 51-1-21, SRM 51-3-0, SRM 51-1-20D, SRM 51-3-1,
Part: SKIN — MISREPAIRED (LT WING SLAT) · airframe 96,561 hrs · 25,131 cycles
DURING C-CHECK, FOUND LT WING SLOT VANE SKIN WITH NON STANDARD REPAIR AT STATION XILD 42. REMOVED NON STANDARD REPAIR. TRIMMED OUT DAMAGED AREA. PERFORMED NDT INSPECTION, NO CRACKS OR CORROSION FOUND AFTER TRIM OUT. FABRICATED REPAIR DOUBLER (AL 7075 T6 0.071), INTERNAL DOUBLER (AL 7075 T6 0.063), AND FILLER (AL 7075 T6 0.063â). CLEANED, TREATED AND PRIMED AREA, FILLER, AND REPAIR DOUBLER INTERNAL PART. APPLIED SEALANT TO FAYING SURFACES IAW SRM 51-1-11. INSTALLED REPAIR PARTS IAW DRAWING ED 4293, SRM 51-1-21, SRM 51-3-0, SRM 51-1-20D, SRM 51-3-1. DATED 07-25-06, DWG NR ED 4293 DATE 07-22-06, EO NR 2006602 DATE 07-25-06.
Part: REPAIR — IMPROPER (LT WING) · airframe 96,561 hrs · 25,131 cycles
DURING ROUTINE C CHECK INSPECTION, LT WING L/E HAS NON STANDARD REPAIR, XFS 544.000 - XFS 560.000.
Part: SKIN — MISREPAIRED (ZONE 500) · airframe 96,561 hrs · 25,131 cycles
DURING ROUTINE C-CHECK INSPECTION, FOUND LEFT WING SLOT VANE SKIN HAS NON STANDARD REPAIR AT STATION, SOLDO 6.224. REMOVED NON STANDARD REPAIR. TRIMMED OUT DAMAGED AREA IAW SEMAN DRAWING, ED-4292. PERFORMED NDT INSPECTION IAW DC-8 NDT SPM PART 06-10-01-001. NO CRACKS OR CORROSION FOUND. FABRICATED REPAIR DOUBLER (AL 7075 T6 0.071â), INTERNAL DOUBLER, AND FILLER, (AL 7075 T6 0.063â) IAW SEMAN DWG 4292. CLEANED, TREATED AND PRIMED AREA, FILLER, AND REPAIR DOUBLER (INTERNAL PART) IAW DC-8 SRM 51-1-8B. APPLIED SEALANT TO FAYING SURFACES IAW SEMAN DWG EO-4292 DATE 07-24-06, EO SEMAN 2006601 DATE 07-25-06. DC-8 SRM 51-1-11. INSTALLED REPAIR PARTS (TORQUED).
2005
Part: INDICATOR — READS HIGH (EGT) · airframe 95,370 hrs · 24,523 cycles
DURING CLIMB-OUT FROM KLRD TO KMEM, NR 1 EGT INDICATED TO 912 DEGREES. TEMP DECREASED AS THROTTLE WAS PULLED BACK. TEMP WAS AT 912 FOR APPROX 5 SECONDS, OAT WAS 34 DEGREES C, N1 SETTING 91.3% AND THE INDICATOR WAS FLASHING 912 DEGREES. THE CREW DIVERTED A/C DIRECTLY TO KTOL WERE IT LANDED W/O INCIDENT. MX PERFORMED AN INSPECTION OF THE NR 1 ENGINE AND NO DEFECTS WERE NOTED. ALSO, CHECKED EGT HARNESS AND IT CHECKED GOOD. MX ALSO PERFORMED A POWER ASSURANCE CHECK AND FOUND NR 1 EGT READING HIGH. REMOVED AND REPLACED NR 1 EGT INDICATOR. RAN POWER ASSURANCE CHECK AND THE EGT TEST WAS GOOD IN ACCORDANCE WITH THE ERH AND CFM MANUALS. AIRCRAFT WAS RETURNED TO SERVICE.
Part: ENGINE — FLAMED OUT (NR 3) · airframe 94,697 hrs · 24,248 cycles
ON CLIMB NR 3 ENG FLAMED OUT 32,000 FT, NO AUDIBLE/VISUAL ENG STALL OR VIBRATION. WEATHER VMC THROUGHOUT CLIMB. ENG FLAMED OUT N1 30%, N2 15% & OIL PRESSURE 3 PSI. GEN WENT OFF LINE, IGNITION NOT ON. FUEL CONFIG NORMAL, FUEL TEMP TANK -5C & FUEL PRESSURE AFTER FLAMEOUT 7 PSI ENG MOTORING 18% N2. ATTEMPTED RESTART AFTER RUNNING ABNORMAL ENGINE CHECKLIST. RECYCLED FIRE HANDLE, ATTEMPTED RESTART DESCENDING 21,000 FT, STARTER RESET & ALL 4 CROSSFEEDS IN POSITION. ENG RESTARTED 17,000, PARAMETERS NORMAL. LANDED WITH ALL 4 MOTORS RUNNING AND NO FURTHER PROBLEMS THROUGHOUT FLIGHT. MX PERFORMED CFM MM 71-00-00 FAULT 51, T/S TREE, PERFORMED POWER RUN. ENGINE INDICATIONS NORMAL, NO DEFECTS NOTED.
2004
Part: PANEL — DENTED (MLG WW) · airframe 93,578 hrs · 23,843 cycles
DURING ROUTINE C CHECK, FOUND LEFT AFT WHEEL WELL PANEL 161X DENTED ON OUTER SKIN. REMOVED DAMAGED AREA. FABRICATED REPAIR PARTS, LOCATED, TRIMMED, TREATED, APPLIED ADHESIVE, CURED, AND PRIMED REPAIR PARTS IAW DC8 SRM 51-1-9A, 53-8-3, 51-1-15, AND 51-1-8.
Part: HINGE FITTING — CRACKED (ZONE 500) · airframe 93,578 hrs · 23,843 cycles
DURING ROUTINE C CHECK FOUND LEFT WING INBOARD AILERON UPPER INBOARD HINGE FITTING CRACKED. REMOVED FASTENERS AS NEEDED TO REMOVE DAMAGED HINGE FITTING. RECEIVED NEW PART, LOCATED, DRILLED, DEBURRED, PRIMED, INSTALLED NEW FITTING AND NEW FASTENERS. RIGGED AILERON IAW DC8 MM 27-11-1, 20-16-0, 27-11-2, 27-10-0, DC8 SRM 51-1-20D, 51-3-0, AND 51-1-21A
Part: ANGLE — CRACKED (ZONE 600) · airframe 93,578 hrs · 23,843 cycles
DURING ROUTINE C CHECK, FOUND RIGHT WING LOWER SURFACE INBOARD OF NUMBER 1 SPOILER PANEL ATTACH ANGLE CRACKED. REMOVED DAMAGE. FABRICATED REPAIR ANGLES, LOCATED, DRILLED, TRIMMED, DEBURRED, TREATED, PRIMED, INSTALLED REPAIR ANGLES AND NEW FASTENERS AT RIGHT WING LOWER SURFACE INBOARD OF NUMBER 1 SPOILER PANEL ATTACH ANGLE IAW 57-2-0, 51-1-20D, 51-9-0, 51-3-2, 51-1-8, AND 57-5-2.
Part: FRAME — CORRODED (ZONE 100) · airframe 93,578 hrs · 23,843 cycles
DURING ROUTINE C CHECK FOUND CORRODED FRAME AT STATION 220 LONGERON 36. REMOVED CORROSION,. ORIGINAL THICKNESS .100 REMOVED .040 MATERIAL, OUT OF LIMITS. REMOVED DAMAGED AREA. FABRICATED REPAIR PARTS, LOCATED, DRILLED, TRIMMED, DEBURRED, TREATED, PRIMED, INSTALLED REPAIR PARTS, AND NEW FASTENERS AT STATION 220 LONGERON 36. IAW SRM 51-1-8, AND 53-2-0.
Part: FRAME — CORRODED (ZONE 100) · airframe 93,578 hrs · 23,843 cycles
DURING ROUTINE C-CHECK FOUND CORRODED FRAME AT STATION 140 LONGERON 36. REMOVED CORROSION,. ORIGINAL THICKNESS, .080 REMOVED .040 MATERIAL, OUT OF LIMITS. REMOVED DAMAGED AREA. FABRICATED REPAIR PARTS, LOCATED, DRILLED, DEBURRED, TREATED, PRIMED, INSTALLED REPAIR PARTS, AND NEW FASTENERS AT STATION 140 LONGERON 36 . IAW SRM 51-1-8, AND 53-2-0
Part: FRAME — CORRODED (ZONE 100) · airframe 93,578 hrs · 23,843 cycles
DURING ROUTINE C-CHECK FOUND CORRODED FRAME AT STATION 180 LONGERON 36. REMOVED CORROSION, ORIGINAL THICKNESS .100 REMOVED .040 MATERIAL, OUT OF LIMITS. REMOVED DAMAGED AREA. FABRICATED REPAIR PARTS, LOCATED, DRILLED, DEBURRED, TREATED, PRIMED, INSTALLED REPAIR PARTS, AND NEW FASTENERS. IAW SRM 51-1-8, AND 53-2-0.
Part: SKIN — CORRODED (ZONE 100) · airframe 93,578 hrs · 23,483 cycles
DURING ROUTINE C-CHECK FOUND INTERNAL SKIN CORROSION AT STATION 610 BETWEEN LONGERON 33 RIGHT AND 34 RIGHT. REMOVED FASTENERS AS NEEDED TO REMOVE DAMAGE. FABRICATED REPAIR PARTS, LOCATED, DRILLED, TRIMMED, DEBURRED, TREATED, PRIMED, INSTALLED REPAIR PARTS, AND NEW FASTENERS FROM STATION 620 TO 640 BETWEEN LONGERON 35 LEFT TO 33 RIGHT IAW DC8 SRM 51-1-21, 51-1-20D, 53-2-1, 51-1-4, AND 51-1-8.
Part: ANGLE — GOUGED (ZONE 600) · airframe 93,578 hrs · 23,843 cycles
DURING ROUTINE C CHECK, FOUND RIGHT WING JOINT AREA BETWEEN INBOARD AND OUTBOARD FLAPS, AREA ON UPPER OUTBOARD FLAP ANGLE GOUGED. REMOVED DAMAGE. FABRICATED REPAIR PART. LOCATED, DRILLED TRIMMED, DEBURRED, TREATED, PRIMED, INSTALLED REPAIR PART AND NEW FASTENERS AT RIGHT WING JOINT AREA BETWEEN INBOARD AND OUTBOARD FLAPS, AREA ON UPPER OUTBOARD FLAP ANGLE IAW DC8 SRM 57-2-0, 51-9-0, AND 51-1-20D.
Part: SEAT TRACK — WORN (FUSELAGE) · airframe 93,578 hrs · 23,843 cycles
DURING ROUTINE C-CHECK FOUND CAPTAIN'S OUTBOARD SEAT TRACK HAS EXCESSIVE WEAR AROUND LOCKPIN HOLES. REMOVED FASTENERS AS NEEDED TO REMOVE DAMAGED SEAT TRACK SECTION. FABRICATED REPAIR PARTS, LOCATED, DRILLED, DEBURRED, TREATED, PRIMED, INSTALLED REPAIR PARTS AND NEW FASTENERS AT CAPTAIN'S OUTBOARD SEAT TRACK IAW DC8 SRM 53-2-3, 51-1-8, AND 51-1-20D.
Part: FRAME — CORRODED (FUSELAGE) · airframe 93,578 hrs · 23,843 cycles
DURING ROUTINE C-CHECK, FOUND CORRODED FRAME AT STATION 70 BETWEEN LONGERON 31 RIGHT AND 32 RIGHT. REMOVED FASTENERS AS NEEDED TO REMOVE ATTACHING FRAME STRUCTURE. REMOVED FASTENERS AS NEEDED TO REMOVE DAMAGED FRAME. RECEIVED NEW FRAME, FABRICATED FRAME SPLICE REPAIR PARTS. LOCATED NEW FRAME AND FRAME SPLICE REPAIR PARTS LOCATED, DRILLED, TRIMMED, DEBURRED, TREATED, PRIMED. INSTALLED NEW FRAME AND FRAME SPLICE REPAIR PARTS, AND NEW FASTENERS. RE-ATTACHED FRAME STRUCTURE IAW DC8 SRM 53-2-5, 51-1-21, 51-3-0, 51-1-20D, 53-2-0, AND 51-1-8.
Part: SKIN — DENTED (ZONE 600) · airframe 93,578 hrs · 23,843 cycles
DURING ROUTINE C CHECK, FOUND RIGHT WING DENTED AT STATION XFS-45 OUTBOARD OF LIFT ATTACH POINT. REMOVED FASTENERS AS NEEDED TO REMOVE DAMAGE. REMOVED DAMAGED AREA. FABRICATED REPAIR PARTS, LOCATED, DRILLED, TRIMMED, DEBURRED, TREATED, PRIMED, INSTALLED REPAIR PARTS AND NEW FASTENERS WET WITH SEALANT AT RIGHT WING STATION XFS-45. SEALED REPAIR IAW 57-2-1, AND 51-1-8.
Part: SKIN — CRACKED (ZONE 600) · airframe 93,578 hrs · 23,843 cycles
DURING ROUTINE C CHECK, FOUND RIGHT WING INBOARD AILERON TP SIDE ABOVE AILERON TRIM LINKAGE SKIN CORRODED. REMOVED FASTENERS AS NEEDED TO REMOVE DAMAGE. FABRICATED REPAIR PARTS, LOCATED, DRILLED, TRIMMED, DEBURRED. TREATED, PRIMED, INSTALLED REPAIR PARTS AND NEW FASTENERS IAW DC8 SRM 57-2-0, 57-8-0, 51-1-4, 51-1-21, AND 51-1-8.
Part: ANGLE — CRACKED (ZONE 600) · airframe 93,578 hrs · 23,843 cycles
DURING ROUTINE C CHECK, FOUND RIGHT WING INBOARD FLAP OUTBOARD ANGLE CRACKED. REMOVED FASTENERS AS NEEDED TO REMOVE DAMAGED ANGLE. FABRICATED NEW ANGLE, LOCATED, DRILLED, TRIMMED, DEBURRED, TREATED, PRIMED, INSTALLED NEW ANGLE, AND FASTENERS AT RIGHT WING INBOARD FLAP OUTBOARD ANGLE. IAW DC8 SRM 51-1-21, 51-2-0, AND 51-1-8.
Part: FRAME — CRACKED (ZONE 200) · airframe 93,578 hrs · 23,843 cycles
DURING ROUTINE C-CHECK FOUND FRAME CRACKED AT STATION 1580 LONGERON 21 LEFT. REMOVED FASTENER AS NEEDED TO REMOVE DAMAGED FRAME SECTION. FABRICATED REPAIR PARTS, LOCATED, TRIMMED, DEBURRED, TREATED, PRIMED, INSTALLED REPAIR PARTS AND NEW FASTENERS AT STATION 1580 LONGERON 21 LEFT IAW DC8 SRM 53-2-0, 51-1-20D, 51-1-8 AND 51-1-21.
Part: FRAME — CRACKED (ZONE 200) · airframe 93,578 hrs · 23,843 cycles
DURING ROUTINE C-CHECK FOUND FRAME CRACKED AT STATION 1580 LONGERON 21 RIGHT. REMOVED FASTENER AS NEEDED TO REMOVE DAMAGED FRAME SECTION. FABRICATED REPAIR PARTS, LOCATED, TRIMMED, DEBURRED, TREATED, PRIMED, INSTALLED REPAIR PARTS AND NEW FASTENERS AT STATION 1580 LONGERON 21 RIGHT IAW DC8 SRM 53-2-0, 51-1-20D, AND 51-1-21.
Part: SUPPORT CHANNEL — BROKEN (ZONE 200) · airframe 93,578 hrs · 23,843 cycles
DURING ROUTINE C-CHECK FOUND HAT CHANNEL BROKEN AT STATION 1586 LONGERON 21 RIGHT. REMOVED FASTENERS AS NEEDED TO REMOVE DAMAGED HAT CHANNEL SECTION. FABRICATED REPAIR PARTS. LOCATED, DRILLED, TRIMMED, DEBURRED, TREATED, PRIMED, INSTALLED REPAIR PARTS AND NEW FASTENERS AT STATION 1586 LONGERON 21 RIGHT IAW DC 8 SRM 51-3-0, 53-2-0, 51-1-8 AND 51-1-21.
Part: FLAP TRACK — GOUGED (ZONE 600) · airframe 93,578 hrs · 23,843 cycles
DURING ROUTINE C CHECK, FOUND RIGHT HAND OUTBOARD FLAP LEADING EDGE INBOARD HINGE AT FLAP STATION XRS-230.000 ICE DOOR INBOARD TRACK GOUGED. REMOVED FASTENERS AS NEEDED TO REMOVE DAMAGED TRACK. FABRICATED NEW TRACK, LOCATED, DRILLED, TRIMMED, DEBURRED, TREATED, PRIMED, INSTALLED NEW TRACK AND FASTENERS AT RIGHT HAND OUTBOARD FLAP LEADING EDGE INBOARD HINGE AT FLAP STATION XRS-230.000 ICE DOOR INBOARD TRACK IAW DC8 SRM 51-1-21, 51-1-8, 51-1-8B, 51-3-0, 51-1-4 AND 57-2-0.
Part: VANE — GOUGED (ZONE 600) · airframe 93,578 hrs · 23,843 cycles
DURING ROUTINE C CHECK, FOUND RIGHT WING FLAP NUMBER 2 FIXED VANE OUTBOARD UPPER EDGE GOUGED. REMOVED DAMAGED AREA. FABRICATED REPAIR PARTS, LOCATED, TRIMMED, ALODINED, INSTALLED AND CURED ALL REPAIR PARTS ON RIGHT WING FLAP NUMBER 2 FIXED VANE, PRIMED AND SEALED IAW DC8 SRM 51-1-9A, 57-7-0,51-1-15, AND 51-1-8.
Part: SUPPORT ANGLE — CRACKED (ZONE 600) · airframe 93,578 hrs · 23,843 cycles
DURING ROUTINE C CHECK, FOUND RIGHT WING RIGHT OUTBOARD FLAP INBOARD TRAILING EDGE SUPPORT ANGLE CRACKED. REMOVED FASTENERS AS NEEDED TO REMOVE DAMAGE. FABRICATED REPAIR PARTS, LOCATED, DRILLED, TRIMMED, DEBURRED, TREATED, PRIMED, INSTALLED REPAIR PARTS, AND NEW FASTENERS AT RIGHT HAND WING RIGHT HAND OUTBOARD FLAP INBOARD TRAILING EDGE IAW DC8 SRM 57-2-0, 51-1-21 AND 51-1-8.
Part: FLAP TRACK — GOUGED (ZONE 600) · airframe 93,578 hrs · 23,843 cycles
DURING ROUTINE C CHECK, FOUND RIGHT OUTBOARD FLAP OUTBOARD HINGE ICE DOOR TRACK GOUGED. REMOVED FASTENERS AS NEEDED TO REMOVE DAMAGED TRACK. FABRICATED NEW TRACK, LOCATED, DRILLED, TRIMMED, DEBURRED, TREATED, PRIMED INSTALLED NEW TRACK AND FASTENERS AT RIGHT HAND OUTBOARD FLAP OUTBOARD HINGE ICE DOOR TRACK. IAW 51-3-0, 51-1-4, 57-2-0, 51-1-21, AND 51-1-8.
Part: VANE — DELAMINATED (RT TE FLAPS) · airframe 93,578 hrs · 23,843 cycles
DURING ROUTINE C CHECK, FOUND RIGHT WING FLAP NUMBER 1 VANE LOWER INBOARD SECTION DELAMINATED. REPLACED RIGHT WING FLAP NUMBER 1 VANE WITH OVERHAULED UNIT.
Part: ANGLE — CRACKED (ZONE 500) · airframe 93,578 hrs · 23,843 cycles
DURING ROUTINE C CHECK, FOUND NUMBER 1 ENGINE PYLON LOWER AFT SECTION HAS CRACKED RIB ANGLE VERY AFT RIB. REMOVED FASTENERS AS NEEDED TO REMOVE DAMAGED RIB ANGLE. FABRICATED NEW RIB ANGLE, LOCATED, DRILLED, TRIMMED, DEBURRED, PRIMED. INSTALLED NEW RIB ANGLE AND NEW FASTENERS IAW DC8 SRM 51-1-4, 54-2-0 AND 51-1-8.
Part: SKIN — CORRODED (ZONE 800) · airframe 93,578 hrs · 23,843 cycles
DURING ROUTINE C CHECK, FOUND AFT CARGO DOOR INTERIOR SKIN AT UPPER FORWARD STOP CORRODED. REMOVED FASTENERS AS NEEDED TO REMOVE EXISTING DOUBLER. REMOVED DAMAGED AREA. FABRICATED REPAIR PARTS, LOCATED, DRILLED, TRIMMED, DEBURRED, TREATED, PRIMED, INSTALLED REPAIR PARTS AND NEW FASTENERS AT AFT CARGO DOOR INTERIOR SKIN AT UPPER FORWARD STOP IAW DC8 SRM 51-1-21, 52-2-0, 51-3-0, 52-2-3, AND 51-1-8.
Part: WEDGE — CRACKED (ZONE 600) · airframe 93,578 hrs · 23,843 cycles
DURING ROUTINE C-CHECK FOUND RT WING OUTBOARD AILERON OUTBOARD WEDGE TRAILING EDGE GOUGED. PERFORMED HFEC, FOUND WEDGE CRACKED. REMOVED FASTENERS AS NEEDED TO REMOVE DAMAGED. FABRICATED REPAIR PARTS, LOCATED, DRILLED, DEBURRED, TRIMMED, TREATED, PRIMED, INSTALLED REPAIR PARTS AND NEW FASTENERS AT RIGHT WING OUTBOARD AILERON OUTBOARD WEDGE TRAILING EDGE IAW DC8 SRM 57-2-1.
Part: WEB — CRACKED (BS 1164) · airframe 93,578 hrs · 23,843 cycles
DURING ROUTINE C CHECK FOUND A CRACKED WEB AT LIGHTNING HOLE AT STATION 1164 LBL 68 LONGERON 21 LT. REMOVED DAMAGED. FABRICATED DOUBLER, LOCATED, DRILLED, DEBURRED, PRIMED, INSTALLED DOUBLER AND NEW FASTENERS AT STATION 1164 LBL 68. IAW SRM 51-1-21, 53-4-1, AND 51-1-3.
Part: ACCESS PANEL — WORN (ZONE 600) · airframe 93,578 hrs · 23,843 cycles
DURING ROUTINE C CHECK, FOUND NUMBER 3 PYLON FOOTSTOOL ACCESS PANEL HAS SEVERAL AREAS WITH DEEP FRETTING WEAR. FABRICATED NEW FOOTSTOOL ACCESS PANEL, LOCATED, DRILLED, TRIMMED, DEBURRED, TREATED, AND PRIMED NEW FOOTSTOOL ACCESS PANEL IAW DC8 SRM 53-2-0, 51-1-21, AND 51-1-8.
Part: PANEL — GOUGED (ZONE 600) · airframe 93,578 hrs · 23,843 cycles
DURING ROUTINE C-CHECK FOUND NR 4 PYLON WRAP AROUND PANEL HAS 2 EACH DEEP GOUGES. REMOVED DAMAGED AREA. FABRICATED REPAIR PARTS, LOCATED, DRILLED, DEBURRED, TREATED, PRIMED, INSTALLED REPAIR PARTS AND NEW FASTENERS ON NR 4 PYLON WRAP AROUND PANEL. IAW SRM 54-2-0, 54-3-1, 54-2-1, 51-1-21, AND 51-1-8.
Part: DOUBLER — GOUGED (T/E FLAP) · airframe 93,578 hrs · 23,843 cycles
DURING ROUTINE C-CHECK, FOUND LEFT WING INBOARD FLAP UPPER OUTBOARD REPAIR DOUBLER GOUGED. REMOVED FASTENERS AS NEEDED TO REMOVE DAMAGED DOUBLER. FABRICATED NEW DOUBLER, LOCATED, DRILLED, TRIMMED, DEBURRED, TREATED, PRIMED. INSTALLED NEW DOUBLER AND NEW FASTENERS IAW DC8 SRM 57-2-1, 51-1-21, 57-7-0, 51-1-20A AND 51-1-8.
Part: ATTACH ANGLE — CRACKED (ZONE 600) · airframe 93,578 hrs · 23,843 cycles
DURING ROUTINE C-CHECK FOUND RIGHT WING INTERIOR OF PANEL NUMBER 546 FORWARD INBOARD VERTICAL ANGLE CRACKED. REMOVED FASTENERS AS NEEDED TO REMOVE DAMAGED ANGLE. FABRICATED NEW ANGLE, LOCATED, DRILLED, DEBURRED, TRIMMED, TREATED, PRIMED, INSTALLED NEW ANGLE AND NEW FASTENERS RIGHT WING INTERIOR OF PANEL NUMBER 546 FORWARD INBOARD VERTICAL ANGLE IAW DC8 SRM 53-2-0, 51-1-20D, AND 51-1-8.
Part: WEB — CRACKED (ZONE 100) · airframe 93,578 hrs · 23,843 cycles
DURING ROUTINE C-CHECK FOUND WEB CRACKED APPROXIMATELY .5 INCH AT STATION 1906 LONGERON 30 LEFT. REMOVED DAMAGE. FABRICATED DOUBLER, LOCATED, DRILLED, TRIMMED, DEBURRED, TREATED, PRIMED, INSTALLED DOUBLER AND NEW FASTENERS AT STATION 1906 LONGERON 30 LEFT IAW DC8 SRM 53-5-0, 53-2-0, AND 51-1-8.
Part: LONGERON — CORRODED (ZONE 100) · airframe 93,578 hrs · 23,843 cycles
DURING ROUTINE C-CHECK FOUND CORROSION AROUND DOME NUTS AT STATION 44 LONGERON 27 RIGHT. REMOVED CORROSION, OUT OF LIMITS. REMOVED FASTENERS AS NEEDED TO REMOVE DAMAGE SECTION OF LONGERON. FABRICATED REPAIR PARTS, LOCATED, DRILLED, TRIMMED, DEBURRED, TREATED, PRIMED, INSTALLED REPAIR PARTS, AND NEW FASTENERS IAW DC8 SRM 53-2-2, 51-1-8, AND 51-1-21.
Part: PAN — CRACKED (ZONE 100) · airframe 93,578 hrs · 23,843 cycles
DURING ROUTINE C-CHECK FOUND AFT CARGO COMPARTMENT STATION 1120 AND 1160 PAN ABOVE NUMBER 3 CARGO DOOR IS CRACKED AT BOTH ENDS. REMOVED FASTENERS AS NEEDED TO REMOVE PAN. REMOVED DAMAGE. FABRICATED DOUBLERS, LOCATED DRILLED, TRIMMED, DEBURRED, TREATED, PRIMED, INSTALLED DOUBLERS AND NEW FASTENERS. INSTALLED PAN ABOVE NUMBER 3 CARGO DOOR IAW DC8 SRM 55-2-0, 51-3-0, 53-11-2, 51-1-8, AND 51-1-21.
Part: SKIN PANEL — CORRODED (ZONE 100) · airframe 93,578 hrs · 23,843 cycles
DURING ROUTINE C-CHECK FOUND AIR CONDITIONING ACCESSORY COMPARTMENT, INTERIOR STATION 38 BETWEEN LONGERON 32 RT AND LONGERON 33 RT CORRODED. REMOVED FASTENERS AS NEEDED TO PERFORM REPAIR. REMOVED DAMAGED SKIN SECTION, LONGERON 32 RT AND 33 RT. FABRICATED NEW SKIN SECTION AND RECEIVED NEW LONGERONS. LOCATED ALL REPAIR PARTS, DRILLED, DEBURRED, TREATED, PRIMED, INSTALLED ALL REPAIR PARTS, AND NEW FASTENERS WET WITH SEALANT FROM STATION 32 TO 70 LONGERON 31 RT TO 35 RT. IAW DWG NR W20-R01 REV:IR DATED 7/1/04.
Part: WEB — CRACKED (ZONE 100) · airframe 93,578 hrs · 23,843 cycles
DURING ROUTINE C-CHECK FOUND WEB CRACKED APPROXIMATELY .5 INCH AT STATION 1910 LONGERON 30 RIGHT. REMOVED DAMAGE. FABRICATED DOUBLER, LOCATED, DRILLED, TRIMMED, DEBURRED, TREATED, PRIMED, INSTALLED DOUBLER AND NEW FASTENERS AT STATION 1910 LONGERON 30 RIGHT IAW DC8 SRM 53-5-0, 53-2-0, AND 51-1-8.
Part: STIFFENER — CRACKED (ZONE 100) · airframe 93,578 hrs · 23,843 cycles
DURING ROUTINE C CHECK, FOUND HORIZONTAL STIFFENER CRACKED APPROXIMATELY 1 INCH AT STATION 1956 LEFT SIDE. REMOVED FASTENERS AS NEEDED TO REMOVE STIFFENER. REMOVED DAMAGE. FABRICATED DOUBLER, LOCATED, DRILLED, TRIMMED, DEBURRED, TREATED, PRIMED, INSTALLED DOUBLER AND NEW FASTENERS, REINSTALLED STIFFENER AT STATION 1956 IAW DC8 SRM 53-2-0, 51-1-21, 53-5-3, 51-1-20D, AND 51-1-8.
Part: ANGLE — CRACKED (ZONE 500) · airframe 93,578 hrs · 23,843 cycles
DURING ROUTINE C CHECK, FOUND NUMBER 1 ENGINE PYLON LOWER AFT SECTION HAS CRACKED RIB ANGLE EIGHTH FROM FRONT AT SPLICE. REMOVED FASTENERS AS NEEDED TO REMOVE DAMAGED RIB ANGLE. WELDED RIB ANGLE. INSTALLED RIB ANGLE AND NEW FASTENERS, IAW DC8 SRM 51-1-21, AND DC8 DPS 10.255.
Part: PANEL — CRACKED (ZONE 500) · airframe 93,578 hrs · 23,843 cycles
DURING ROUTINE C-CHECK, FOUND NUMBER 1 ENGINE PYLON AFT OUTBOARD SIDE ADAPTER PANEL CRACKED AT FORWARD UPPER PYLON SPAR ATTACH POINT APPROXIMATELY 1/2 INCH. REMOVED FASTENERS AS NEEDED TO PERFORM REPAIR. FABRICATED DOUBLERS, LOCATED, DRILLED, TRIMMED, DEBURRED, TREATED, PRIMED. INSTALLED REPAIR DOUBLERS AND NEW FASTENERS IAW DC8 SERVICE BULLETIN 54-93.
Part: SKIN — GOUGED (LT WING) · airframe 93,578 hrs · 23,843 cycles
DURING ROUTINE C CHECK FOUND LT WING NR 1 MAIN-TANK-VENT FLOAT VALVE JUST OB OF XRS-358 HAS GOUGED UPPER SKIN. REMOVED DAMAGE. FABRICATED REPAIR PARTS, LOCATED, DRILLED, TRIMMED, DEBURRED, TREATED, PRIMED, INSTALLED REPAIR PARTS, NEW FASTENERS AND SEALED REPAIR. IAW SRM 51-10-0, 57-3-0, AND DRAWING W20-R02 REVISION IR DATED 7/2/04.
Part: ANGLE — GOUGED (LT WING) · airframe 93,578 hrs · 23,843 cycles
DURING ROUTINE C-CHECK, FOUND LEFT WING ROOT XFS-970, XW-0 ANGLE GOUGED AT AFT END, NUMBER 1 FLAP ROLLER TRACK. REMOVED FASTENERS AS NEEDED TO REMOVE DAMAGED ANGLE. FABRICATED NEW ANGLE, LOCATED, DRILLED, DEBURRED, TRIMMED, TREATED, PRIMED. INSTALLED NEW ANGLE AND NEW FASTENERS IAW DC8 SRM 51-3-0, 51-1-4, 51-1-8, AND 51-1-21.
Part: LONGERON — CRACKED (ZONE 100) · airframe 93,578 hrs · 23,843 cycles
DURING ROUTINE C-CHECK FOUND STATION 120 TO 140 LONGERON 35 LT CRACKED. REMOVED FASTENERS AS NEEDED TO REMOVED DAMAGED LONGERON SECTION. FABRICATED REPAIR PARTS, LOCATED, DRILLED, DEBURRED, TREATED, PRIMED, INSTALLED NEW REPAIR PARTS AND FASTENERS WET WITH SEALANT AT LONGERON 35 LT FROM STATION 120 TO STATION 140. IAW SRM 53-2-0, 53-2-2, 53-4-1, AND 51-1-8.
Part: FRAME — CORRODED (ZONE 100) · airframe 93,578 hrs · 23,843 cycles
DURING ROUTINE C-CHECK FOUND FORWARD CARGO COMPARTMENT FRAME CORRODED OUT OF LIMITS AT STATION 280 BETWEEN LONGERON 32 RT AND LONGERON 34 RT. REMOVED FASTENERS AS NEEDED TO REPLACE FRAME SEGMENTS. FABRICATED NEW FRAME SEGMENTS, AND REPAIR ANGLES. LOCATED, DRILLED, DEBURRED, TREATED, PRIMED, INSTALLED REPAIR PARTS, AND NEW FASTENERS AT STATION 280 BETWEEN LONGERON 32 RT AND 34 RT. IAW SRM 53-2-0, 51-1-8, 51-1-20D, 53-4-1, 51-1-21, AND 51-3-1.
Part: SPOILER — GOUGED (LT WING) · airframe 93,578 hrs · 23,843 cycles
DURING ROUTINE C CHECK FOUND LT WING NR 2 SPOILER PANEL LOWER OB TRAILING EDGE GOUGED. REMOVED DAMAGE. FABRICATED REPAIR DOUBLER, LOCATED, TRIMMED, AND TREATED. APPLIED ADHESIVE, AND CURED. SEALED EDGES AND PRIMED. IAW SRM 57-7-0, 51-1-8, 51-1-15, AND 51-1-9A.
Part: SKIN — DENTED (ZONE 600) · airframe 93,578 hrs · 23,843 cycles
DURING ROUTINE C-CHECK FOUND RIGHT WING OUTBOARD AILERON UPPER SURFACE DENTED. REMOVED DAMAGE, FABRICATED REPAIR PARTS, LOCATED, DRILLED, TRIMMED, DEBURRED, TREATED, PRIMED, INSTALLED REPAIR PARTS AND NEW FASTENERS AT RIGHT WING OUTBOARD AILERON UPPER SURFACE IAW DC8 SRM 53-3-0, 87-2-3, 51-1-9, 51-1-231, 51-3-0, AND 51-1-8.
Part: SPLICE — CRACKED (ZONE 100) · airframe 93,578 hrs · 23,843 cycles
DURING ROUTINE C CHECK FOUND LONGERON 31 RIGHT OUTBOARD SIDE CENTER SPLICE CRACKED FROM STATION 460 TO STATION 476. REMOVED FASTENERS AS NEEDED TO REMOVE DAMAGED SPLICE. FABRICATED NEW SPLICE, LOCATED, DRILLED, DEBURRED, TREATED, PRIMED, INSTALLED NEW SPLICE AND NEW FASTENERS AT LONGERON 31 RIGHT BETWEEN STATION 460 TO STATION 476. IAW DC8 SRM 51-1-8, 53-2-0, 51-1-20D, AND 51-1-21.
Part: DOUBLER — CRACKED (LT WING) · airframe 93,578 hrs · 23,843 cycles
DURING ROUTINE C-CHECK FOUND LT WING TRAILING EDGE NR 4 SPOILER BAY THIRD RIB FROM FLAP HINGE FORWARD OB SIDE DOUBLER CRACKED AND MISSING FASTENERS. REMOVED DOUBLER. FABRICATED REPAIR PART, LOCATED, DRILLED, TRIMMED, DEBURRED, TREATED, PRIMED, INSTALLED REPAIR PARTS AND NEW FASTENERS IAW SC8 SRM 57-2-0, 57-5-0, AND 51-1-8.
Part: ANGLE — CRACKED (WING) · airframe 93,578 hrs · 23,843 cycles
DURING ROUTINE C CHECK FOUND LT WING AFT WING ROOT, AT STATION XFS-950,AND XW-0, ANGLE PLATE CRACKED. REMOVED FASTENERS AS NEEDED TO REMOVE DAMAGED ANGLE. FABRICATED NEW ANGLE, LOCATED, DRILLED, DEBURRED, TREATED, PRIMED, INSTALLED NEW ANGLE AND NEW FASTENERS. IAW SRM 51-1-21, 51-1-4, 51-1-24, 51-1-8, AND 51-1-20D.
Part: PANEL — DENTED (WING) · airframe 93,578 hrs · 23,843 cycles
DURING ROUTINE C CHECK FOUND LT WING LOWER TRAILING IB FIXED PANEL HAS DENT AFT OF MAIN LANDING GEAR STRUT. REMOVED FASTENERS AS NEEDED TO REMOVE PANEL. REMOVED DAMAGE. FABRICATED REPAIR PARTS, TRIMMED, TREATED, APPLIED ADHESIVE, PERFORMED HOT BOND, INSTALLED PANEL WITH NEW FASTENERS. IAW SRM 20-16-0, 51-3-0, 51-1-9A, 57-31-1, AND 51-1-8.
Part: SILL — TOOL DAMAGE (ZONE 200) · airframe 93,578 hrs · 23,843 cycles
DURING ROUTINE C-CHECK FOUND AFT ENTRANCE DOOR SILL HAS TOOLING DAMAGE AT STATION 1620 LONGERON 20 LT. REMOVED DAMAGE. FABRICATED REPAIR PART. LOCATED, DRILLED, DEBURRED, TREATED, PRIMED, INSTALLED REPAIR PART AND NEW FASTENERS AT STA 1620 LONGERON 20 LT IAW SRM 53-2-0, 51-1-21, 51-1-4, AND 51-1-8.
Part: RIB — GOUGED (LT WING) · airframe 93,578 hrs · 23,843 cycles
DURING ROUTINE C-CHECK, FOUND LT WING TRAILING EDGE NR 4 SPOILER BAY THIRD RIB FROM FLAP HINGE FORWARD OB SIDE GOUGED. REMOVED DAMAGE. FABRICATED REPAIR PARTS, LOCATED, DRILLED, TRIMMED, DEBURRED, TREATED, PRIMED, INSTALLED REPAIR PARTS AND NEW FASTENERS IAW SRM 57-2-0, 57-5-0, AND 51-1-8.
Part: SPOILER — GOUGED (LT WING) · airframe 93,578 hrs · 23,843 cycles
DURING ROUTINE C CHECK FOUND LT WING NR 3 SPOILER PANEL IB TRAILING EDGE GOUGED IN TWO PLACES. REMOVED DAMAGE. FABRICATED REPAIR DOUBLER, LOCATED, TRIMMED, AND TREATED. APPLIED ADHEASIVE, AND CURED. SEALED EDGES AND PRIMED. IAW SRM 57-7-0, 51-1-8, 51-1-15, AND 51-1-9A.
Part: SILL — MISDRILLED (ZONE 200) · airframe 93,578 hrs · 23,843 cycles
DURING ROUTINE C-CHECK FOUND RT SERVICE DOOR SILL (FRAME, WEB AND ANGLE) AT STATION 196 LONGERON 11 RT HAS A FASTENER HOLE DOUBLE DRILLED. REMOVED FASTENERS AS NEEDED TO REMOVE DAMAGE. FABRICATED REPAIR PARTS, LOCATED, DRILLED, DEBURRED, TREATED, PRIMED, INSTALLED REPAIR PARTS AND NEW FASTENERS FROM STATION 176 TO STATION 205 BETWEEN LONGERON 8 RT AND LONGERON 12 RT IAW SRM 53-2-0, 51-1-4, AND 51-1-8.
Part: PANEL — CRACKED (MLG WW) · airframe 93,578 hrs · 23,843 cycles
DURING ROUTINE C CHECK, FOUND NUMBER 1 ENGINE PYLON AFT PYLON ADAPTER PANEL CRACKED APPROXIMATELY 2 1/2 INCHES AT FORWARD ACCESS PANEL. REMOVED FASTENERS AS NEEDED TO REMOVE DAMAGE. FABRICATED DOUBLER, LOCATED, DRILLED, TRIMMED, DEBURRED, TREATED, PRIMED, INSTALLED DOUBLER AND NEW FASTENERS IAW DC8 SRM 54-2-0, 51-1-26, AND 51-1-8.
Part: FLOOR SUPPORT — GOUGED (ZONE 100) · airframe 93,578 hrs · 23,843 cycles
DURING ROUTINE C CHECK, FOUND LEFT FLOOR TRACK FLANGE GOUGED AT STATION 1080. REMOVED FASTENERS AS NEEDED TO REMOVE DAMAGE. FABRICATED NEW FLANGE, LOCATED, DRILLED, TRIMMED, DEBURRED, TREATED, PRIMED, INSTALLED NEW FLANGE AND NEW FASTENERS AT LEFT HAND FLOOR TRACK FLANGE AT STATION 1080 IAW DC8 SRM 53-2-0, 51-4-0, 51-3-0, 51-1-4, AND 51-1-8.
Part: FLOOR SUPPORT — CORRUPTED (ZONE 100) · airframe 93,578 hrs · 23,843 cycles
DURING ROUTINE C CHECK, FOUND FLOOR SUPPORT FLANGE CRACKED AT STATION 1160 LONGERON 31 RIGHT. REMOVED DAMAGE, FABRICATED DOUBLER AND FILLER, LOCATED, DRILLED, TRIMMED, DEBURRED, TREATED, PRIMED, INSTALLED FILLER AND DOUBLER AND NEW FASTENERS AT AT STATION 1160 LONGERON 31 RIGHT IAW DC8 SRM 54-4-1, 53-4-1, 53-2-0, 51-1-20D, 51-1-20A, AND 51-1-8.
Part: FLOOR SUPPORT — CRACKED (ZONE 100) · airframe 93,578 hrs · 23,843 cycles
DURING ROUTINE C CHECK, FOUND FLOOR SUPPORT FLANGE HAS 5 EACH CRACKS AT STATION 1280 LONGERON 31 RIGHT AND 29 LEFT. REMOVED FASTENERS AS NEEDED TO REMOVE DAMAGED FLOOR SUPPORT FLANGE. WELDED CRACKS IAW DC8 DPS 10.225. INSTALLED REPAIRED FLANGE AT AT STATION 1280 LONGERON 31 RIGHT AND 29 LEFT, IAW DC8 SRM 51-1-21, 51-1-8, AND 51-20D.
Part: MEMBRANE — CRACKED (LT WING) · airframe 93,578 hrs · 23,843 cycles
DURING ROUTINE C-CHECK, FOUND LEFT WING LEADING EDGE 522A BAY INBOARD AND FORWARD OF PANEL CUT OUT ANTI-ICE DISCHARGE MEMBRANE CRACKED AT HOLES 3 PLACES .5 INCH EACH XFS395. REMOVED FASTENERS AS NEEDED TO PERFORM REPAIR. FABRICATED REPAIR PART, LOCATED, DRILLED, TRIMMED, DEBURRED, TREATED, PRIMED. INSTALLED REPAIR PART AND NEW FASTENERS IAW DC8 SRM 51-1-21, 57-2-1, AND 51-1-8.
Part: SKIN — CRACKED (ZONE 500) · airframe 93,578 hrs · 23,843 cycles
DURING ROUTINE C CHECK, FOUND NUMBER 1 ENGINE PYLON AFT INBOARD SIDE ADAPTER PANEL CRACKED AT FORWARD UPPER PYLON SPAR ATTACH POINT APPROXIMATELY 1/2 INCH. REMOVED FASTENERS AS NEEDED TO PERFORM REPAIR. FABRICATED DOUBLERS, LOCATED, DRILLED, TRIMMED, DEBURRED, TREATED, PRIMED. INSTALLED REPAIR DOUBLERS AND NEW FASTENERS IAW DC8 SERVICE BULLETIN 54-93.
Part: SUPPORT — CRACKED (ZONE 100) · airframe 93,578 hrs · 23,843 cycles
DURING ROUTINE C CHECK, FOUND RIGHT AFT LOWER CARGO TUNNEL; STATION 1000 RIGHT UPPER HORIZONTAL SIDE WALL SUPPORT CRACKED. REMOVED DAMAGE. FABRICATED REPAIR PARTS, LOCATED, DRILLED, TRIMMED, TREATED, PRIMED, INSTALLED REPAIR PARTS AND NEW FASTENERS AT RIGHT AFT LOWER CARGO TUNNEL; STATION 1000 RIGHT UPPER HORIZONTAL SIDE WALL SUPPORT IAW DC8 SRM 51-1-4, 53-2-0, 51-1-21, 53-2-0, AND 51-1-8.
Part: CUSP WEB — CRACKED (ZONE 100) · airframe 93,578 hrs · 23,843 cycles
DURING ROUTINE C CHECK, FOUND A CRACKED CUSP BETWEEN STATION 980 AND 1000 AT LONGERON 21 RIGHT. REMOVED DAMAGE, FABRICATED REPAIR DOUBLER, LOCATED, DRILLED, TRIMMED, DEBURRED, TREATED, PRIMED, INSTALLED REPAIR DOUBLER AT STATION 980 AND 1000 AT LONGERON 21 RIGHT IAW DC8 SRM 53-2-0, AND 51-1-8.
Part: CUSP WEB — CRACKED (ZONE 100) · airframe 93,578 hrs · 23,843 cycles
DURING ROUTINE C-CHECK FOUND FORWARD CARGO COMPARTMENT BETWEEN STATION 80 AND STATION 100 LONGERON 21 RT 10 INCHES FROM OB CUSP WEB CRACKED. REMOVED DAMAGE. REMOVED FASTENERS AS NEEDED TO PERFORM REPAIR, FABRICATED REPAIR DOUBLER, LOCATED, DRILLED, DEBURED, PRIMED, INSTALLED REPAIR DOUBLER AND NEW FASTENERES AT FORWARD CARGO COMPARTMENT BETWEEN STATION 80 AND STATION 100 LONGERON 21 RT 10 INCHES FROM OB CUSP WEB. IAW SRM 53-4-1, 53-2-0, 51-3-0, 51-1-8, 51-1-21, AND 51-1-20.
Part: DRIVE LINK — CRACKED (T/E FLAP) · airframe 93,578 hrs · 23,843 cycles
DURING ROUTINE C-CHECK, FOUND LEFT WING INBOARD FORWARD FLAP DRIVE LINK ASSEMBLY CRACKED AT ACTUATOR ATTACH POINT -J-, AT WING STATION XW-97.906. REMOVED FASTENERS AS NEEDED TO REMOVE DAMAGED FLAP LINK ASSEMBLY. RECEIVED NEW FLAP DRIVE LINK ASSEMBLY, AND INSTALLED NEW FLAP DRIVE LINK ASSEMBLY AND FASTENERS IAE DC8 MM27-51-4, AND 27-27-4.
Part: SKIN — TORN (ZONE 600) · airframe 93,578 hrs · 23,843 cycles
DURING ROUTINE C CHECK, FOUND RIGHT HAND OUTBOARD FLAP OUTBOARD TRAILING EDGE WEDGE LOWER SKIN GOUGED AND TORN. REMOVED FASTENERS AS NEEDED TO REMOVE DAMAGE. FABRICATED REPAIR PARTS, LOCATED, DRILLED, TRIMMED, DEBURRED, TREATED, PRIMED, INSTALLED REPAIR PARTS AND NEW FASTENERS WET WITH SEALANT AT RIGHT WING OUTBOARD FLAP OUTBOARD TRAILING EDGE WEDGE LOWER SKIN. SEALED AREA. IAW 57-2-5, 51-1-15, 51-3-0 AND 51-1-8.
2003
Part: WARNING LIGHT — ILLUMINATED (NR 3 ENG PANEL) · airframe 92,908 hrs · 23,538 cycles
DURING CLIMB FROM KTOL NR 3 ENGINE EGT STARTED TO FLUCUATE AND WENT OFF SCALE, IT THEN WENT BLANK AND STARTED WORKING AGAIN. ALL OTHER INDICATION NORMAL. CREW RETURNED AIRCRAFT TO KTOL. AN INSPECTION IS ON GOING AS INFORMATION BECOMES AVAILABLE IT WILL BE PROVIDED.
Part: PANEL — FAILED (COCKPIT) · airframe 929,031 hrs · 23,533 cycles
DURING FLIGHT, BACK GROUND LIGHT FOR STAB TRIM STARTED SMOKING. THEN LIGHTS OFF, REPOSITIONED BACK GROUND PANEL STOPPED SMOKING BUT HALF THE LIGHTS WERE INOP. MAINTENANCE REMOVED AND REPLACED STAB TRIM LIGHT PANEL PER ALL APPLICABLE MANUALS AND OPERATIONAL CHECK WAS GOOD. AIRCRAFT WAS RETURNED TO SERVICE.
Part: UPLOCK SWITCH — MALFUNCTIONED (MLG) · airframe 92,464 hrs · 2,339 cycles
ENROUTE FROM KLAX TO KTOL LANDING GEAR UPLATCH CHECK FAILED. CREW CYCLED GEAR UNTIL GOOD CHECK ACHIEVED. AIRCRAFT LANDED WITHOUT INCIDENT IN KTOL. MAINTENANCE INSPECTED SYSTEM CLEANED AND LUBRICATED RT MLG UPLATCH SYSTEM AND ASSOCIATED COMPONENTS. GEAR OPERATIONAL CHECK GOOD. ALL WORK COMPLETED PER APPLICABLE MANUALS AND AIRCRAFT RETURNED TO SERVICE
Part: WIRE HARNESS — DIRTY (EGT) · airframe 91,916 hrs · 23,210 cycles
AFTER TAKEOFF IN CLIMBOUT FROM BDL TO EWR, NR 3 EGT REACHED 999 AND WAS ERRATIC. CREW DIVERTED TO TOL DUE TO NO MAINTENANCE IN EWR. CREW ARRIVED IN TOL WITH AN UNEVENTFUL LANDING. MAINTENANCE INSPECTED THE THERMOCOUPLE WIRING HARNESS FOR CRACKS AND NO DEFECTS WERE NOTED. MAINTENANCE CLEANED PINS FOR THERMOCOUPLE HARNESS AND INSTALLED A NEW HARNESS IN ACCORDANCE WITH CFM MAINTENANCE MANUAL. ENGINES WERE RUN IN ACCORDANCE WITH ATI ENGINE RUN HANDBOOK. ENGINE PARAMETERS WERE NORMAL. OPERATIONAL CHECK WAS GOOD IN ACCORDANCE WITH ATI GENERAL MAINTENANCE MANUAL. AIRCRAFT WAS RETURNED TO SERVICE.
Part: CONNECTOR — LOOSE (MLG DOWNLOCK) · airframe 91,687 hrs · 23,144 cycles
DURING FINAL APPROACH FOR LANDING INTO PHIK. CREW NOTED NOSE LANDING GEAR DOWN AND LOCKED LIGHTS WERE NOT ILLUMINATED. USING VISUAL INDICATOR CREW VERIFIED GEAR WAS SAFE. ADDITIONALLY CREW PERFORMED FLY-BY OF CONTROL TOWER AND AGAIN CONFIRMED GEAR WAS IN SAFE CONDITION. CREW COMPLETED AN UNEVENTFUL LANDING IN PHIK. UPON INSPECTION MAINTENANCE DISCOVERED ELECTRICAL CONNECTOR ON NOSE LANDING GEAR DOWNLOCK SWITCH INSECURE. THIS CONNECTOR WAS SECURED AND THE SYSTEM OPERATIONALLY CHECKED GOOD. ALL WORK WAS PERFORMED PER APPLICABLE MANUALS AND THE AIRCRAFT WAS RETURNED TO SERVICE.
2002
Part: SWITCH — LOOSE (NOSE GEAR) · airframe 91,512 hrs · 203,035 cycles
ON APPROACH TO SAN CREW NOTICED NOSE LANDING GEAR "GREEN" INDICATING LIGHTS NOT ILLUMINATED. CREW FOLLOWED COMPANY PROCEDURE AND RETURNED TO SAN FOR AN UNEVENTFUL LANDING. INSPECTION REVEALED THE NOSE GEAR PROXIMITY SWITCH CONNECTOR HAD BECOME INSECURE. MAINTENANCE SECURED THE CONNECTOR IN ACCORDANCE WITH THE AIRCRAFT MAINTENANCE MANUAL PERFORMED AN OPERATIONAL CHECKOUT OF THE SYSTEM AND RETURNED THE AIRCRAFT TO SERVICE.
Part: CONNECTOR — LOOSE (NLG) · airframe 91,512 hrs · 203,035 cycles
ON APPROACH TO SAN CREW NOTICED NOSE LANDING GEAR GREEN INDICATING LIGHTS NOT ILLUMINATED. CREW FOLLOWED COMPANY PROCEDURE AND RETURNED TO SAN FOR AN UNEVENTFUL LANDING. INSPECTION REVEALED THE NOSE GEAR PROXIMITY SWITCH CONNECTOR HAD BECOME INSECURE. MAINTENANCE SECURED THE CONNECTOR IN ACCORDANCE WITH THE AIRCRAFT MAINTENANCE MANUAL. PERFORMED AN OPERATIONAL CHECKOUT OF THE SYSTEM AND RETURNED THE AIRCRAFT TO SERVICE.
Part: FITTING — LOOSE (RT MLG WW) · airframe 91,228 hrs · 22,936 cycles
EN ROUTE FROM TOL TO ANC, THE FLIGHT CREW NOTICED A DECLINE IN THE MAIN HYDRAULIC QUANTITY SYSTEM. THE FLIGHT CREW FOLLOWED COMPANY PROCEDURES AND CONTINUED TO ANC FOR AN UNEVENTFUL LANDING. MAINTENANCE INSPECTED THE AIRCRAFT WHICH REVEALED A LOOSE FITTING AT THE SWIVEL GLAND IN THE MAIN GEAR ACTUATOR. MAINTENANCE TIGHTENED THE FITTING AND PERFORMED A SUCCESSFUL OPERATIONAL CHECK IAW THE DOUGLAS MM. THE AIRCRAFT WAS RETURNED TO SERVICE.
Part: FITTING — CORRODED (FUSELAGE)
MAIN CARGO CABIN FITTING, CORRODED.
Part: FITTING — CRACKED (FUSELAGE)
AFT CARGO COMPARTMENT FITTING, CRACKED.
Part: SKIN — DAMAGED (ELEVATOR TAB)
HORIZONTAL STABILIZER RIGHT ELEVATOR GEAR TAB SKIN, INTERNAL DOUBLERS AND HONEY COMB CORE DAMAGE.
Part: PANEL — DELAMINATED (LT WING)
LEFT WING, OUTER WING TRAILING EDGE, UPPER FIXED PANEL DELAMINATED.
Part: FLAP — DAMAGED (RT WING)
RIGHT WING INBOARD FLAP BAKELITE, DAMAGED.
Part: STIFFENER — CRACKED (LT WING)
LEFT WING TRAILING EDGE FIXED PANEL STIFFENER, CRACKED.
Part: FITTING — CORRODED (FUSELAGE)
AFT LOWER CARGO COMPARTMENT, FITTING CORRODED.
Part: FITTING — CRACKED (FUSELAGE)
AFT LOWER CARGO COMPARTMENT, FITTING CRACKED.
Part: FITTING — CORRODED (FUSELAGE)
AFT CARGO COMPARTMENT, AT STA 1445 LONGERON 34R LEVEL, SUPPORT FITTING HEAVY CORROSION.
Part: FITTING — CRACKED (FUSELAGE)
AFT CARGO COMPARTMENT FITTING, CRACKED.
Part: ANGLE — CRACKED (FUSELAGE)
AFT CARGO COMPARTMENT SUPPORT ANGLE CRACKED.
Part: FITTING — CORRODED (FUSELAGE)
MAIN CARGO CABIN FITTING, CORRODED.
Part: SKIN — CORRODED (FUSELAGE)
LOWER FUSELAGE, SKIN CORRODED - YSTA 1690.0 LONGERON 34 LEFT.
Part: LONGERON — CORRODED (FUSELAGE)
AFT LOWER CARGO COMPARTMENT BETWEEN STA Y1480 TO STA Y1500 LONGERON SPLICE 32 RIGHT, CORRODED.
Part: RUB STRIP — WORN (HORIZONTAL STAB)
FUSELAGE TAIL SECTION, HORIZONTAL STABILIZER FIXED FAIRINGS (RUB PLATES) WITH WEAR IN SEVERAL PLACES.
Part: LONGERON — CRACKED (FUSELAGE)
AFT CARGO COMPARTMENT BETWEEN STA Y 1340 INCH TO STA Y1360 INCH LONG 36 CRACKED.
Part: LONGERON — CRACKED (FUSELAGE)
FWD CARGO COMPARTMENT, STA Y: 387, LONGERON 31 LT, CRACKED.
Part: FITTING — CRACKED (LWR FUSELAGE)
AFT CARGO COMPARTMENT, FITTING, LOCATED AT STA Y= 1140 BETWEEN LONG 33R AND 34R.
Part: FITTING — CRACKED (LWR FUSELAGE)
AFT CARGO COMPARTMENT, FITTING CRACKED, LOCATED AT STA Y=1200 BETWEEN LONG 27L AND LONG 28L.
Part: SPLICE — CORRODED (CARGO BAY)
AFT CARGO COMPARTMENT, BETWEEN STA 1340 AND STA 1360 AT LONG, 28L LEVEL, LONGERON SPLICE (PN 4646163501) CORRODED.
Part: FLOOR SUPPORT — CRACKED (CABIN)
FORWARD CARGO COMPARTMENT, AT Y STA 100, 120, 140, 160, 180, 200, 220, 240, 260, 360, 380, 400, 418, 460, 480, 520, 540, 580, 600, 620, BETWEEN LONG 29 LEFT TO 29 RIGHT, TITANIUM FLOOR SUPPORT ANGLES CRACKED.
Part: LONGERON — CRACKED (FUSELAGE)
AFT CARGO COMPARTMENT, BETWEEN STA Y1340 TO STA Y1360 LONG 35 RIGHT, CRACKED.
Part: FITTING — CRACKED (LWR FUSELAGE)
AFT CARGO COMPARTMENT, FITTING, LOCATED AT STA Y=1240 AT LONG 35R.
Part: FITTING — CRACKED (LWR FUSELAGE)
AFT CARGO COMPARTMENT, FITTING CRACKED, LOCATED AT STA Y =1200 BETWEEN LONG 34R AND LONG 35R.
Part: FLOORBEAM — CORRODED (FUSELAGE)
MAIN CARGO CABIN, FLOORBEAM LOWER CHORD ON STA Y857 BETWEEN +X60 TO -X60, CORRODED.
Part: LONGERON — CRACKED (FUSELAGE)
AFT CARGO COMPARTMENT, STA Y:1354, LONGERON 30R CRACKED.
Part: FITTING — CRACKED (LWR FUSELAGE)
AFT CARGO COMPARTMENT, FITTING, LOCATED AT STA Y=1227 BETWEEN LONG 21R AND 22R.
Part: FLOORBEAM — CORRODED (FUSELAGE)
MAIN CARGO CABIN, FLOORBEAM LOWER CHORD ON STA Y980 BETWEEN +X45 TO -X25 CORRODED.
Part: FRAME — CORRODED (FUSELAGE)
STA 1690 BETWEEN LONGERON 21L AND LONG. 23L FRAME ANGLE CORRODED.
2001
Part: TRANSCEIVER — DEFECTIVE (WEATHER RADAR) · airframe 90,705 hrs · 22,711 cycles
DURING CLIMBOUT, RADAR SMOKING CONTINUOUSLY AND TOTALLY UNUSABLE. REMOVED AND REPLACED WX R/T IAW DC-8 MM 34-40-2. GROUND CHECK AND OPS GOOD.
Part: LONGERON — CORRODED (FUSELAGE) · airframe 90,557 hrs · 22,639 cycles
DURING A MAINTENANCE VISIT FOUND CORROSION DAMAGE TO LONGERON 32R AT STA 100, DAMAGE EXCEEDED LIMITATIONS IAW DC-8 SRM.
Part: SKIN — CORRODED (FUSELAGE) · airframe 90,557 hrs · 22,639 cycles
DURING A MAINTENANCE VISIT FOUND CORROSION DAMAGE TO SKIN AT STA 70 - 110 AND BELOW STR 31R, DAMAGE EXCEEDED LIMITATIONS IAW DC-8 SRM.
Part: FITTING — CORRODED (FUSELAGE) · airframe 90,557 hrs · 22,639 cycles
DISCOVERED CORROSION UNDER THE LAVATORY WHEN PERFORMING FCD A53-4, INSP OF LOWER FUSELAGE. *S/D* REMOVED CORRODED L36 END FITTING I/A/W DC-8 SRM 51-1-21. TREATED, PRIMED & INSTALLED NEW L36 END FITTING I/A/W DC-8 SRM 51-1-8 & 51-1-20D.
Part: INDICATOR — FAULTY (COCKPIT) · airframe 90,512 hrs · 22,621 cycles
NR 4 ENGINE DURING SPOOL UP, N1 RPM INDICATOR HANGS UP BETWEEN 50 TO 70 PERCENT. REMOVED AND REPLACED NR 4 N1 INDICATOR IAW DC-8 MM CH 77-00. OPS CHECKS GOOD ON ENGINE RUN-UP.
Part: CONTROL VALVE — FAILED (MLG) · airframe 90,385 hrs · 22,561 cycles
AFTER TAKEOFF, GEAR UPLATCH CHECK FAILURE. REMOVED AND REPLACED MAIN GEAR CONTROL VALVE IAW M/M 32-32-1 RIGGED IAW M/M 32-31-0 P208. NO LEAKS NOTED ON PRESSURE CHECKS. PERFORMED EXTENSION AND RETRACT ON CHECKS PER M/M 32-30-0. CYCLED GEAR THREE TIMES NO FURTHER PROBLEMS NOTED ON GEAR SWING.
2000
Part: LONGERON — CORRODED (FUSELAGE) · airframe 89,974 hrs · 22,367 cycles
CORROSION AT 33R LONGERON STA 160 TO STA 180. ACCOMPLISHED TEMPORARY REPAIR PER M1206001 AND M1207001 REPAIR IS TO INSPECTED EVERY 50 CYCLES ACCOMPLISH PERMANENT SRM REPAIR NO LATER THAN 300 CYCLES
Part: LATCH — OUT OF POSITION (MLG) · airframe 89,793 hrs · 22,272 cycles
ON GEAR RETRACTION DOORS NOT LATCHED AND GEAR NOT LATCHED REMAINED ILLUMINATED UPON PERFORMING UPLATCH CHECK GEAR LIGHTS REMAINED ILLUMINATED RECYCLED GEAR SEVERAL TIMES NO HELP. PERFORMED LANDING GEAR AND GEAR DOOR INSP IAW DC-8 M/M 3-10-0, NO ABNORMALITES FOUND. FOUND HYD SYS SEL OUT OF DETEND. RESET HYD SELEC HANDLE TO NORM POS, LEFTED AFT IAW DC-8 M/M 7-11-0. PERF GEAR EXT AND RETRACTION IAW DC-8 IAW DC-8 M/M 32-30-0. LANDING GEAR AND DOOR OPS CHECK NORMAL IAW 32-31-0.
Part: SWITCH — FAILED (MLG) · airframe 89,733 hrs · 22,241 cycles
ON GEAR RETRACTION RED DOORS NOT LATCHED AND RED GEAR NOT LATCHED LIGHTS REMAINED ON NOTE: ON GEAR DOWN SELECTING MAIN GEAR GREEN LIGHTS ON AS GEAR HANDLE MAKES MICRO SWITCH.
Part: UPLOCK CABLE — OUT OF POSITION (LT MLG DOOR) · airframe 89,398 hrs · 22,096 cycles
UPON GEAR RETRACTION DOORS NOT LATCHED AND GEAR NOT LATCHED WARNING LIGHTS REMAINED ILLUMINATED. ALT GEAR DOOR LIGHTS MAINS REMAINED OUT. ON POST FLIGHT FOUND LEFT MAIN GEAR DOOR OPEN. FOUND LT MLG DOOR UPLATCH CABLE MISROUTED REPORTED CABLE PERF MLG DOOR FOLLOW UP TEST IAW M/M 52-31-5. PERFORMED MLG DOOR UP LATCH MECH, ADJ AND TEST IAW M/M 32-31-4.
1999
Part: BUSHING — MISALIGNED (TE FLAP)
FOUND DURING D-CHECK, RIGHT INBOARD FLAP OUTBOARD FITTING FORWARD BUSHING NOT. ALIGNED WITH INBOARD BUSHING. REAMED INBOARD FITTING. FABRICATED BUSHING AND INSTALLED PER EO NR 99-186 WITH APPROVED 8110-3 DATED 12/29/99. (M)
Part: BOSS — CORRODED (LT MLG)
DURING D-CHECK, C/W MAIN LANDING GEAR SHOCK STRUT ASSEMBLY RETRACT PIN BOSS AND RETRACT IN INSPECTION PER S/B 32-102 AND MA AI-3210-01:03. C/W MA-A1-3210-01:03, AFTER BLENDING REBORE EXCEEDED LIMITS OF MA. REPAIRED PER EO NR 99-186 WITH APPROVED 8110-3 DATED 11/11/99. C/W S/B 32-102 AND GEAR SWING IAW DC-8 MM 32-30-0. (M)
Part: BOSS — CORRODED (RT MLG)
DURING D-CHECK, C/W MAIN LANDING GEAR SHOCK STRUT ASSEMBLY RETRACT PIN BOSS AND RETRACT PIN INSPECTION PER S/B 32-102 AND MA AI-3210-01:03. COMPLIED WITH MA AI-3210-01:03, AFTER BLENDING REBORE EXCEEDED LIMITS OF MIA. REPAIRED PER EO NR 99-186 WITH APPROVED 8110-3 DATED 11/11/99. C/W S/B 32-102 AND GEAR SWING IAW DC-8 MM 32-30-0. (M)
Part: ATTACH FITTING — CRACKED (CARGO DOOR) · airframe 88,287 hrs · 21,582 cycles
DURING A MAINTENANCE VISIT FOUND LOWER CARGO DOOR JAMB ATTACHMENT FITTING CRACKED AT STA 520 AND LONGERON 31 RIGHT. 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.
Part: ANGLE — CRACKED (FUSELAGE)
FOUND DURING D-CHECK, FORWARD LOWER CARGO BILGE STATION 520 L31R INSIDE DOOR JAM ANGLE CRACKED AND BENT UP. REMOVED ANGLE, FABRICATED DOUBLER IAW DC-8 SRM 51-1-21, 51-1-4. TREATED, PRIMED AND INSTALLED IAW DC-8 SRM 51-1-8, 51-1-21. (M)
Part: VANE — DAMAGED (TE FLAP)
FOUND DURING D-CHECK, LEFT INBOARD FLAP NR 2 VANE INBOARD END SLIDING HINGE COVER TRACK MOUNT HOLES ELONGATED. FABRICATED REPAIR DOUBLER AND INSTALLED PER EO NR 99-186 WITH APPROVED 8110-3 DATED 11/03/99. (M)
Part: VANE — DAMAGED (LT TE FLAP) · airframe 88,287 hrs · 21,582 cycles
DURING A MAINTENANCE VISIT FOUND LEFT WING INBOARD FLAP NR 2 VANE HAS MOUNT HOLE ENLONGATED. DAMAGE EXCEEDED LIMITATIONS IAW DC-8 SRM. REMOVED DAMAGE, TREATED AREA IAW DC-8 SRM 51-1-8. FABRICATED AND INSTALLED REPAIR DOUBLER IAW FAA DER APPROVED ENGINEERING SKETCH EO 99-186.
Part: BELLCRANK — CRACKED (FLAP ACTUATOR)
FOUND DURING D-CHECK, MID WING FLAP CRANK HAS CRACK APPROX .1875 INCH IN LENGTH AT STATION 219 LEFT. REPLACED MIDWING FLAP CRANK IAW DC-8 O/H/M 27-28-8. (M)
Part: FLOORBEAM — CORRODED (FUSELAGE) · airframe 88,287 hrs · 21,582 cycles
DURING MAINTENANCE VISIT FOUND CORROSION DAMAGE TO FLOORBEAM AT STA 1540 XCW 69 LT. DAMAGE EXCEEDED LIMITATIONS IAW DC-8 SRM. REMOVED DAMAGE, TREATED AREA IAW DC-8 SRM 51-1-8. FABRICATED REPAIR ANGLE AND INSTALLED IAW DC-8 SRM 51-1-8, 51-1-21 AND 53-2-0 . (CORROSION DAMAGE RECORDED IN EWA CORROSION PROGRAM).
Part: DUCT — CRACKED (FUSELAGE)
FOUND DURING D-CHECK, LOWER RIGHT AIR CONDITIONING DUCT AND BULKHEAD FEED THROUGH WORN AND CRACKED STATION 8 L32R. STOP DRILLED CRACK AND WELDED. WELDED WORN AREA'S PER EO NR 99-186 WITH APPROVED 8110-3 DATED 12/02/99. (M)
Part: FLOORBEAM — CORRODED (FUSELAGE)
FOUND DURING D-CHECK, UPPER CARGO COMPARTMENT, FLOORBEAM EXFOLIATED STATION 1540 XCW 69 LEFT. REMOVED CORROSION IAW DC-8 SRM 51-1-8. FABRICATED REPAIR ANGLE IAW DC-8 SRM 53-2-0. TREATED, PRIMED AND INSTALLED IAW DC-8 SRM 51-1-8, 51-1-21 AND 53-2-0. (M)
Part: LONGERON — CORRODED (FUSELAGE)
FOUND DURING D-CHECK, RIGHT LONGERON 24 AND FUSELAGE STATION 879 TO STATION 940, CORROSION ON UPPER SURFACE ON FITTING AND 2 PREVIOUS REPAIR DOUBLERS ALSO RUNNING UNDER REPAIR DOUBLERS. REPLACED RIGHT L24 FITTING IAW DOUGLAS L24 REPLACEMENT GUIDE SRM 51-1-20D, 51-3-0, 53-2-2 AND EO NR 99-186 WITH APPROVED 8110-3 DATED 11/16/99. (M)
Part: LONGERON — CORRODED (FUSELAGE) · airframe 88,287 hrs · 21,582 cycles
DURING MAINTENANCE VISIT FOUND CORROSION DAMAGE TO RT LONGERON 24 FROM STA 879 TO STA 960. DAMAGE EXCEEDED LIMITATIONS IAW DC-8 SRM. REMOVED DAMAGE, TREATED AREA IAW DC-8 SRM 51-1-8.
Part: LONGERON — CRACKED (LT WHEEL WELL) · airframe 88,287 hrs · 21,582 cycles
DURING A MAINTENANCE VISIT FOUND LONGERON 24 LEFT CRACKED AT STA 857. DAMAGE EXCEEDED LIMITATIONS IAW DC-8 SRM. REMOVED DAMAGE, TREATED AREA IAW DC-8 SRM 51-1-8. INSTALLED NEW LONGERON 24 LEFT IAW DC-8 SRM 51-1-20D.
Part: BELLCRANK — CRACKED (FLAP ACTUATOR)
FOUND DURING D-CHECK, INBOARD FLAP ACTUATOR ASSY CRANK HAS TWO CRACKS, ONE IS .5 INCH IN LENGTH AND THE OTHER IS .375 INCH LENGTH. REPLACED CRANK IAW DC-8 O/H/M 27-28-9. (M)
Part: LONGERON — CRACKED (FUSELAGE)
FOUND DURING D-CHECK, LEFT W/W LONGERON 24 STATION 857 HAS CRACK 1.5 INCHES LONG. REMOVED AND REPLACED LEFT L24 IAW DC-8 REPLACEMENT GUIDE AND SRM 51-1-21, 51-1-20D AND 53-2-2. (M)
Part: PANEL — DAMAGED (CARGO WALL)
FOUND DURING D-CHECK, REPLACED GIL-LINER FROM STATION 8 TO REAR PRESSURE BULKHEAD. INSTALLED NEW GIL-LINER AND SPLICE STRIPS PER EO NR 99-186 WITH APPROVED 8110-3 DATED 11/30/99. (M)
Part: SKIN — DAMAGED (LT WING)
FOUND DURING D-CHECK, LEFT MID WING LEADING EDGE OUTBOARD END MOUNT HOLES, OVERSIZED, ELONGATED AND GOUGED STATION XS 520.168. REMOVED EXISTING REPAIR DOUBLER IAW DC-8 SRM 51-1-21. FABRICATED NEW DOUBLER. TREATED PRIMED AND INSTALLED IAW DC-8 SRM 51-1-4 AND 51-1-8. INSTALLED DIMPLE WASHER PER EO NR 99-186 WITH APPROVED 8110-3 DATED 12/08/99. (M)
Part: SKIN — DAMAGED (LT WING) · airframe 88,287 hrs · 21,582 cycles
DURING A MAINTENANCE VISIT FOUND LEFT WING, LEADING EDGE, MOUNT HOLES ENLONGATED AT XFS 520.168. DAMAGE EXCEEDED LIMITATIONS IAW DC-8 SRM. REMOVED DAMAGE, TREATED AREA IAW DC-8 SRM 51-1-8. FABRICATED AND INSTALLED REPAIR DOUBLER IAW FAA DER ENGINEERING SKETCH EO 99-186.
Part: SPAR CAP — CRACKED (CENTER WING) · airframe 88,287 hrs · 21,582 cycles
DURING A MAINTENANCE VISIT FOUND RIGHT UPPER SPAR CAP CRACKED AT OUTBOARD AFT ATTACHMENT, DAMAGE EXCEEDED LIMITATIONS IAW DC-8 SRM. /////CORRECTIVE ACTION///// REMOVED DAMAGE, TREATED AREA IAW DC-8 SRM 51-1-8. INSTALLED NEW SPAR CAP IAW DC-8 SRM 51-3-0.
Part: DUCT — CRACKED (FUSELAGE)
FOUND DURING D-CHECK, GROUND PNEUMATIC CONNECTION HAS LEAK IN DUCT UPSTREAM OF COUPLING. STOP DRILLED CRACK. NDT CONFIRMED CRACK HAD BEEN STOPPED. WELDED CRACK IAW MIL-STD-2219. NDT WELD NO FLAWS FOUND PER EO NR 99-186 WITH APPROVED 8110-3 DATED 10/06/99. (M)
Part: SPAR — CRACKED (RT WING)
FOUND DURING D-CHECK, RT AUX SPAR UPPER SPAR CAP CRACKED .625 INCH AT OUTBOARD AFT ATTACH BOLT. REMOVED AND REPLACED RIGHT AUX SPAR UPPER SPAR CAP IAW DC-8 SRM 51-1-24, 51-1-20D AND 51-3-0. (M)
Part: DRAIN LINE — BROKEN (FUSELAGE)
FOUND DURING D-CHECK, EXTERIOR STATION 1382, L36 OVERBOARD DRAIN BROKEN. FABRICATED EXTERNAL DOUBLER AND INSTALLED DRAIN FITTING PER EO NR 99-186 WITH APPROVED 8110-3 DATED 12/09/99. (M)
Part: SKIN — CORRODED (FUSELAGE)
FOUND DURING D-CHECK, FORWARD LOWER CARGO BILGE STATION 620 L36 UNDER FRAME HAS CORROSION (SKIN) FRAME DOUBLER. REMOVED EXISTING DOUBLER IAW DC-8 SRM 51-120. CUTOUT DAMAGED AREA, REMOVED ALL CORROSION. FABRICATED DOUBLER AND FILLER IAW DC-8 SRM 51-1-8 AND 51-1-20D AND EO NR 99-186 WITH APPROVED 8110-3 DATED 12/08/99. (M)
Part: SKIN — CORRODED (FUSELAGE) · airframe 88,287 hrs · 21,582 cycles
DURING A MAINTENANCE VISIT FOUND CORROSION DAMAGE TO INTERNAL SKIN AT LONGERON 36 AND STA 620, DAMAGE EXCEEDED LIMITS IAW DC-8 SRM. REMOVED DAMAGE, TREATED AREA IAW DC-8 SRM 51-1-8. FABRICATED AND INSTALLED FILLER & DOUBLER IAW FAA APPROVED DER ENGINEERING SKETCH 99-186.
Part: LONGERON — CRACKED (FUSELAGE)
FOUND DURING D-CHECK, STATION 1145 TO STATION 1135 CORROSION IN WEB AND CRACK APPROX 6 INCHES LONG UNDER SHEAR FOOT AT CUSP L21L. BLENDED OUT CORROSION, CUT OUT DAMGED AREA. FABRICATED NEW CUSP T, SPLICE AND INSTALLED PER EO NR 99-186 WITH APPROVED 8110-3 DATED 11/19/99. (M)
Part: PANEL — DELAMINATED (FUSELAGE)
FOUND DURING D-CHECK, PANEL 262K AFT RIGHT IS DELAMINATED AND HAS CORROSION. FABRICATED NEW SKIN AND ANGLES. TREATED, PRIMED AND ASSEMBLIED PER EO NR 99-186 WITH APPROVED 8110-3 DATED 12/08/99. (M)
Part: FRAME — CRACKED (FUSELAGE)
FOUND DURING D-CHECK, B CARGO PIT STATION 560 L34R FRAME CRACKED. ROUTED OUT DAMAGED AREA ON FRAME. FABRICATED ANGLE. TREATED, PRIMED AND INSTALLED IAW DC-8 SRM 51-1-21 AND 51-1-20D AND EO NR 99-186 WITH APROVED 8110-3 DATED 12/09/99. (M)
Part: FRAME — CRACKED (FUSELAGE) · airframe 88,287 hrs · 21,582 cycles
DURING A MAINTENANCE VISIT FOUND FRAME CRACKED AT STA 560 AND LONGERON 34 RIGHT. DAMAGE EXCEEDED LIMITATIONS IAW DC-8 SRM. REMOVED DAMAGE, TREATED AREA IAW DC-8 SRM 51-1-8. FABRICATED AND INSTALLED REPAIR IAW FAA DER APPROVED ENGINEERING SKETCH EO 99-186.
Part: DUMP VALVE — CORRODED (LT WING)
FOUND DURING D-CHECK, LEFT FUEL DUMP CHUTE HAS CORROSION IN O-RING CUTOUT. REMOVED CORROSION BY MECHANICAL METHOD. FILLED UNDER CUT AREAS WITH WELD, NDT WELD TO ASSURE NO FLAWS, NONE FOUND. BLEND SMOOTH PER EO NR 99-186 WITH APPROVED 8110-3 DATED 12/08/99. (M)
Part: LONGERON — CORRODED (CARGO BAY) · airframe 88,287 hrs · 21,582 cycles
DURING MAINTENANCE VISIT FOUND CORROSION DAMAGE TO THE WEB BETWEEN STA 1145 TO STA 1135 UNDER THE SHEAR FOOT AT CUSP L21 LT. DAMAGE EXCEEDED LIMITATIONS IAW DC-8 SRM. REMOVED DAMAGE, TREATED AREA IAW DC-8 SRM 51-1-8. FABRICATED AND INSTALLED NEW CUSP T IAW FAA APPROVED DER ENGINEERING SKETCH EO NR 99-186 WITH APPROVED 8110-3 DATED 11/19/99. (CORROSION DAMAGE RECORDED IN EWA CORROSION PROGRAM).
Part: ANGLE — CORRODED (FUSELAGE)
FOUND DURING D-CHECK, UPPER CARGO COMPARTMENT FRAME 1060 AT L36 L ANGLE CORRODED FORWARD SIDE. REMOVED CORROSION IAW DC-8 SRM 51-1-81. REMOVED ANGLE IAW DC-8 SRM 51-1-20, FABRICATED ANGLE. TREATED, PRIMED AND INSTALLED IAW DC-8 SRM 51-1-4, 51-1-8, 51-1-20. (M)
Part: LONGERON — CORRODED (FUSELAGE) · airframe 88,287 hrs · 21,582 cycles
DURING A MAINTENANCE VISIT FOUND CORROSION DAMAGE TO LONGERON 34 RIGHT BETWEEN STA 1160 TO STA 1220, DAMAGE EXCEEDED LIMITS IAW DC-8 SRM. REMOVED DAMAGE, TREATED AREA IAW DC-8 SRM 51-1-8. FABRICATED AND INSTALLED REPAIR FILLER & DOUBLER IAW FAA DER APPROVED ENGINEERING SKETCH 99-186.
Part: ANGLE — CORRODED (FUSELAGE) · airframe 88,287 hrs · 21,582 cycles
DURING A MAINTENANCE VISIT FOUND CORROSION DAMAGE TO ATTACHMENT ANGLE AT STA 1060 AND LONGERON 36, DAMAGE EXCEEDED LIMITS IAW DC-8 SRM. REMOVED DAMAGE, TREATED AREA IAW DC-8 SRM 51-1-8. FABRICATED AND INSTALLED NEW ATTACHMENT ANGLE IAW DC-8 SRM 51-1-20.
Part: LONGERON — CORRODED (FUSELAGE) · airframe 88,287 hrs · 21,582 cycles
DURING A MAINTENANCE VISIT FOUND CORROSION DAMAGE TO LONGERON 35 RIGHT AT STA 1200, DAMAGE EXCEEDED LIMITS IAW DC-8 SRM. REMOVED DAMAGE, TREATED AREA IAW DC-8 SRM 51-1-8. FABRICATED AND INSTALLED REPAIR FILLER & DOUBLER IAW FAA DER APPROVED ENGINEERING SKETCH 99-186.
Part: WEB — CORRODED (FUSELAGE)
FOUND DURING D-CHECK, AFT LOWER CARGO BILGE STATION 1180-1200 L34R TOP WEB HAS CORROSION. REMOVED CORROSION. FABRICATED REPAIR DOUBLER AND INSTALLED PER EO NR 99-186 WITH APPROVED 8110-3 DATED 11/03/99. (M)
Part: LONGERON — CORRODED (FUSELAGE)
FOUND DURING D-CHECK, AFT LOWER CARGO BILGE STATION 1160-1220 L34R RIGHT SIDE CORROSION ON LONGERON ON LONGERON NEXT TO SKIN. REMOVED CORROSION. FABRICATED REPAIR DOUBLER AND INSTALLED PER EO NR 99-186 WITH APPROVED 8110-3 DATED 11/03/99. (M)
Part: LONGERON — CORRODED (FUSELAGE)
FOUND DURING D-CHECK, AFT LOWER CARGO BILGE STATION 1200 L35R TOP OF WEB HAS CORROSION. REMOVED CORROSION. FABRICATED REPAIR DOUBLER AND INSTALLED PER EO NR 99-186 WITH APPROVED 8110-3 DATED 11/03/99. (M)
Part: SKIN — CRACKED (FUSELAGE) · airframe 88,287 hrs · 21,582 cycles
DURING A MAINTENANCE VISIT FOUND EXTERNAL SKIN CRACKED AT STA 1220 AND LONGERON 31 RIGHT. DAMAGE EXCEEDED LIMITATIONS IAW DC-8 SRM. REMOVED DAMAGE, TREATED AREA IAW DC-8 SRM 51-1-8. FABRICATED AND INSTALLED REPAIR IAW FAA DER APPROVED ENGINEERING SKETCH EO 99-186.
Part: SUPPORT BRACKET — CRACKED (FUSELAGE)
FOUND DURING D-CHECK, BETWEEN STATION 1340-1320 AT LONGERON 22 FLOORBEAM SUPPORT CRACKED AND EXFOLIATION. REMOVED FLOORBEAM SUPPORT IAW DC-8 SRM 51-1-20. FABRICATED FLOORBEAM SUPPORT. TREATED, PRIMED AND INSTALLED IAW DC-8 SRM 51-1-8, 51-1-20D, 51-1-21. (M)
Part: SUPPORT BRACKET — CORRODED (FUSELAGE) · airframe 88,287 hrs · 21,582 cycles
DURING MAINTENANCE VISIT FOUND CORROSION DAMAGE TO FLOORBEAM SUPPORT BETWEEN STA 1320 TO STA 1340 AT LONGERON 22. DAMAGE EXCEEDED LIMITATIONS IAW DC-8 SRM. REMOVED DAMAGE, TREATED AREA IAW DC-8 SRM 51-1-8. FABRICATED FLOORBEAM SUPPORT AND INSTALLED IAW DC-8 SRM 51-1-8, 51-1-20D AND 51-1-21. (CORROSION DAMAGE RECORDED IN EWA CORROSION PROGRAM).
Part: FITTING — CRACKED (FUSELAGE)
FOUND DURING D-CHECK, STATION 55 AT XW 32 INCH FLOOR WEB SUPPORT FITTING CRACKED IN CABIN. REMOVED FLOOR WEB SUPPORT FITTING IAW DC-8 SRM 51-1-20D. REPLACED FLOOR WEB SUPPORT FITTING IAW DC-8 SRM 51-30-0. TREATED, PRIMED, AND INSTALLED IAW DC-8 SRM 51-1-21, 51-1-8. (M)
Part: SKIN — CORRODED (FUSELAGE)
FOUND DURING D-CHECK, AFT LOWER CARGO BILGE STATION 1480 L31L AT FRAME FINGER DOUBLER AND SKIN HAS CORROSION. REMOVED CORROSION IAW DC-8 SRM 51-1-8. CUT OFF DAMAGED FINGERS PER EO NR 99-186 WITH APPROVED 8110-3 DATED 12/07/99. (M)
Part: SKIN — CRACKED (FUSELAGE)
FOUND DURING D-CHECK, C-PIT DOOR FUSELAGE CUT OUT AFT LOWE CORNER LOOSE RIVETS AND CRACKED LIP ON FRAME. CUT OFF DAMAGED SEAL DEPRESSOR. FABRICATED TWO REPAIR STRAPS AND INSTALLED PER EO NR 99-186 WITH APPROVED 8110-3 DATED 11/23/99. (M)
Part: FITTING — CRACKED (HORIZONTAL STAB) · airframe 88,287 hrs · 21,582 cycles
DURING A MAINTENANCE VISIT FOUND HORIZONAL STABILIZER FITTING RIGHT SIDE AT STA 1798 AND XCW 47.5. DAMAGE EXCEEDED LIMITATIONS IAW DC-8 SRM. REMOVED DAMAGE, TREATED AREA IAW DC-8 SRM 51-1-8. INSTALLED NEW FITTING IAW DC-8 SRM 51-1-20D.
Part: FITTING — CRACKED (FUSELAGE) · airframe 88,287 hrs · 21,582 cycles
DURING A MAINTENANCE VISIT FOUND MAIN CABIN FLOOR PANEL SUPPORT FITTING AT STA 55 AND BL 32 LEFT. DAMAGE EXCEEDED LIMITATIONS IAW DC-8 SRM. REMOVED DAMAGE, TREATED AREA IAW DC-8 SRM 51-1-8. INSTALLED NEW SUPPORT FITTING IAW DC-8 SRM 51-1-21.
Part: FINGER DOUBLER — CORRODED (FUSELAGE) · airframe 88,287 hrs · 21,582 cycles
DURING A MAINTENANCE VISIT FOUND CORROSION DAMAGE TO FINGER DOUBLER AT STA 1480 AND LONGERON 31 LEFT, DAMAGE EXCEEDED LIMITS IAW DC-8 SRM. REMOVED DAMAGE, TREATED AREA IAW DC-8 SRM 51-1-8. CUT AND REMOVED DAMAGED FINGERS IAW FAA DER APPROVED ENGINEERING SKETCH 99-186.
Part: SUPPORT BRACKET — CRACKED (BS 1340-1320)
FOUND DURING D-CHECK, FOUND BETWEEN STATION 1340-1320 AT LONGERON 22 FLOORBEAM SUPPORT CRACKED AND EXFOLIATED. REMOVED FLOORBEAM SUPPORT IAW DC-8 SRM 51-1-20. FABRICATED FLOORBEAM SUPPORT. TREATED, PRIMED AND INSTALLED IAW DC-8 SRM 51-1-8, 51-1-20D, 51-1-21. (M)
Part: FITTING — CRACKED (FUSELAGE)
FOUND DURING D-CHECK, CABIN STATION 798 XCW 47.5 RIGHT CRACK ON HORIZONTAL FITTING. REMOVED FITTING IAW DC-8 SRM 51-1-20D. INSTALLED NEW FITTING IAW DC-8 SRM 51-1-20D. TREATED AND PRIMED IAW DC-8 SRM 51-1-8. (M)
Part: PLATE — CRACKED (FUSELAGE)
FOUND DURING D-CHECK, MAIN CARGO COMPARTMENT STATION 1680 TO 1700 LEFT SCUFF PLATE PANEL GUIDE CRACKED. STOP DRILLED CRACK. NDT CONFIRMED CRACK HAD BEEN STOPPED. WELDED CRACK IAW MIL-STD-2219 AND NDT WELD NO FLAWS FOUND PER EO NR 99-186 WITH APPROVED 8110-3 DATED 11/24/99. (M)
Part: PLATE — CRACKED (FUSELAGE) · airframe 88,287 hrs · 21,582 cycles
DURING A MAINTENANCE VISIT FOUND EXTERNAL SKIN SCUFF PLATE CRACKED BETWEEN STA 1680 TO STA 1700 AND LONGERON 21 LEFT. DAMAGE EXCEEDED LIMITATIONS IAW DC-8 SRM. REMOVED DAMAGE, TREATED AREA IAW DC-8 SRM 51-1-8. FABRICATED AND INSTALLED REPAIR IAW FAA DER APPROVED ENGINEERING SKETCH EO 99-186.
Part: DOOR FRAME — CRACKED (FUSELAGE)
FOUND DURING D-CHECK, A PIT AT STATION 280 BETWEEN L26 AND 27 RT SIDE CRACK IN FORWARD DOOR FRAME. REPLACED FITTING IAW DC-8 SRM 53-2-0, 51-1-20D AND EO NR 99-186 WITH APPROVED 8110-3 DATED 12/03/99. (M)
Part: FRAME — CRACKED (CARGO DOOR) · airframe 88,287 hrs · 21,582 cycles
DURING A MAINTENANCE VISIT FOUND FORWARD AFT LOWER CARGO DOOR JAMB FRAME CRACKED AT STA 280 BETWEEN LONGERONS 26 RIGHT TO 27 RIGHT. DAMAGE EXCEEDED LIMITATIONS IAW DC-8 SRM. REMOVED DAMAGE, TREATED AREA IAW DC-8 SRM 51-1-8. FABRICATED AND INSTALLED REPAIR IAW FAA DER APPROVED ENGINEERING SKETCH EO 99-186.
Part: FITTING — CORRODED (TE FLAP) · airframe 88,287 hrs · 21,582 cycles
DURING MAINTENANCE VISIT FOUND CORROSION DAMAGE TO NR 3 FLAP CANOE TRAILING EDGE TRACK BOLTS HOLES. DAMAGE EXCEEDED LIMITATIONS IAW DC-8 SRM. REAMED HOLES TO REMOVE CORROSION, TREATED AREA IAW DC-8 SRM 51-1-8. INSTALLED TWO NAS4653151-7-27 BOLTS AND ASSOCIATED HARDWARE IAW FAA APPROVED DER ENGINEERING SKETCH EO 99-186 WITH APPROVED 8110-3 DATED 11/12/99. (CORROSION DAMAGE RECORDED IN EWA CORROSION PROGRAM).
Part: FITTING — CRACKED (FUSELAGE)
FOUND DURING D-CHECK, AFT LOWER CARGO COMPARTMENT STATION 1220 LONGERON L34R-L35R BATH TUB FITTING CRACKED. REMOVED FITTING IAW DC-8 SRM 51-1-20D. FABRICATED ANGLES AND FITTING IAW DC-8 SRM 53-2-0 SHEET 2 F17, 18. TREATED, PRIMED AND INSTALLED ANGLES AND FITTING IAW DC-8 SRM 51-1-8, 51-1-24, 51-1-20D. (M)
Part: FITTING — DAMAGED (FUSELAGE)
FOUND DURING D-CHECK, LT TRAPEZOIDAL FITTING HAS ELONGATED HOLE. REAMED HOLE. FABRICATED BUSHING AND INSTALLED PER EO NR 99-186 WITH APPROVED 8110-3 DATED 11/12/99. (M)
Part: FITTING — CRACKED (CARGO DOOR)
DURING A MAINTENANCE VISIT FOUND LOWER CARGO DOOR JAMB FITTING CRACKED AT STA 1220 BETWEEN LONGERONS 34 RIGHT TO 35 RIGHT. 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 SHEET 2 FIGURE 17 & 18.
Part: RETAINER — CRACKED (A/C DUCT)
FOUND DURING D-CHECK, RETAINER RING CRACKED GROUND AIR CONDITIONER CONNECTOR DUCT TO FUSELAGE ATTACHMENT FORWARD ACCESSORY COMPARTMENT. STOPPED DRILLED CRACKS. NDT CONFIRMED CRACKS HAD BEEN STOPPED. WELDED CRACKS PER MIL-STD-2219 AND NDT WELD. NO FLAWS FOUND PER EO NR 99-186 WITH APPROVED 8110-3 DATED 11/14/99. (M)
Part: FLOORBEAM — CRACKED (FUSELAGE)
FOUND DURING D-CHECK, UPPER CARGO COMPARTMENT FLOOR WEB CRACKED STATION 1580 AND 1600 APPROX 10 INCH FROM LEFT CUSP LINE. REMOVED WEB. FABRICATED NEW WEB OUT OF 2024T3. TREATED AND PRIMED AND INSTALLED IAW DC-8 SRM 53-2-0, 51-1-8, 51-1-21, 51-3-0. (M)
Part: FITTING — CRACKED (FUSELAGE)
FOUND DURING D-CHECK, A PIT AT STATION 340 AT L27R CRACK IN AFT DOOR FRAME. FABRICATED FITTING. TREATED, PRIMED AND INSTALLED IAW DC-8 SRM 51-1-8, 51-1-20D AND 51-3-0. (M)
Part: FITTING — CRACKED (FUSELAGE) · airframe 88,287 hrs · 21,582 cycles
DURING A MAINTENANCE VISIT FOUND FORWARD AFT LOWER CARGO DOOR JAMB FRAME FITTING AT STA 340 AND LONGERON 27 RIGHT. DAMAGE EXCEEDED LIMITATIONS IAW DC-8 SRM. REMOVED DAMAGE, TREATED AREA IAW DC-8 SRM 51-1-8. FABRICATED AND INSTALLED NEW FITTING IAW DC-8 SRM 51-3-0.
Part: FLOORBOARD — CRACKED (FUSELAGE) · airframe 88,287 hrs · 21,582 cycles
DURING A MAINTENANCE VISIT FOUND FLOOR PANEL CRACKED BETWEEN STA 1580 TO STA 1600. 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 51-3-0.
Part: FITTING — CRACKED (FUSELAGE) · airframe 88,287 hrs · 21,582 cycles
DURING A MAINTENANCE VISIT FOUND LONGERON 31 LEFT SPLICE FITTING CRACKED BETWEEN STA 200 TO STA 220. DAMAGE EXCEEDED LIMITATIONS IAW DC-8 SRM. REMOVED DAMAGE, TREATED AREA IAW DC-8 SRM 51-1-8. FABRICATED AND INSTALLED NEW SPLICE FITTING IAW DC-8 SRM 51-1-20.
Part: FITTING — CORRODED (RT WING)
FOUND DURING D-CHECK, NR 3 FLAP CANOE T/E CHAFFED TRACK BOLT HOLES HAVE CORROSION EMANATING FROM THEM. REAMED HOLES TO REMOVE CORROSION. TREATED AND PRIMED. INSTALLED TWO NAS4653151-7-27 BOLTS AND ASSOCIATED HARDWARE PER EO NR 99-186 WITH APPROVED 8110-3 DATED 11/12/99. (M)
Part: SKIN — CORRODED (RT WING) · airframe 88,287 hrs · 21,582 cycles
DURING MAINTENANCE VISIT FOUND CORROSION DAMAGE TO ATTACH ANGLE IN FRONT OF RT WING LIGHT LENS COMMON TO FILLET PANEL 262 RIGHTHAND. DAMAGE EXCEEDED LIMITATIONS IAW DC-8 SRM. REMOVED DAMAGE, TREATED AREA IAW DC-8 SRM 51-1-8. FABRICATED AND INSTALLED DOUBLERS IAW FAA APPROVED DER ENGINEERING SKETCH EO 99-186 WITH APPROVED 8110-3 DATED 11/19/99. (CORROSION DAMAGE RECORDED IN EWA CORROSION PROGRAM).
Part: LONGERON — CORRODED (FUSELAGE) · airframe 88,287 hrs · 21,582 cycles
DURING A MAINTENANCE VISIT FOUND CORROSION DAMAGE TO LONGERON 36 BETWEEN STA 720 TO STA 781, DAMAGE EXCEEDED LIMITS IAW DC-8 SRM. REMOVED DAMAGE, TREATED AREA IAW DC-8 SRM 51-1-8. FABRICATED AND INSTALLED FILLER & DOUBLER IAW BOEING M-7200-99-10647 & M7200-99-10680. (CORROSION DAMAGE RECORDED IN EWA CORROSION PROGRAM).
Part: SKIN — CORRODED (FUSELAGE) · airframe 88,287 hrs · 21,582 cycles
DURING A MAINTENANCE VISIT FOUND CORROSION DAMAGE TO INTERNAL SKIN BETWEEN STA. 781 TO STA. 742 AND LONGERON 35 LEFT. DAMAGE EXCEEDED LIMITATIONS IAW DC-8 SRM. REMOVED DAMAGE, TREATED AREA IAW DC-8 SRM 51-1-8. FABRICATED AND INSTALLED REPAIR DOUBLER IAW FAA APPROVED DER ENGINEERING SCRTCH EO 99-186.
Part: SKIN — CORRODED (FUSELAGE)
FOUND DURING D-CHECK, LEFT FILLET SKIN CORROSION AT L35L BETWEEN STATION 781-742. REMOVED CORROSION IAW DC-8 SRM 51-1-8. FABRICATED SPLICE PLATE AND REPLACEMENT SKIN AND INSTALLED PER EO NR 99-186 WITH APPROVED 8110-3 DATED 11/01/99. (M)
Part: ANGLE — CORRODED (RT WING)
FOUND DURING D-CHECK, ATTACH ANGLE IN FRONT OF WING LIGHT LENS CORRODED ON WING FILLET PANEL 262A RIGHT. BLENDED OUT CORROSION. FABRICATED DOUBLERS AND INSTALLED PER EO NR 99-186 WITH APPROVED 8110-3 DATED 11/19/99. (M)
Part: KEELBEAM — CORRODED (FUSELAGE)
FOUND DURING D-CHECK, KEEL BEAM STATION 720 TO 781 HAS EXFOLIATED CORROSION. REMOVED CORROSION IAW DC-8 SRM 51-1-8. FABRICATED FILLER AND DOUBLER AND INSTALLED PER BOEING M-7200-99-10647 AND M7200-99-10680 WITH APPROVED 8110-3 DATED 12/10/99. (M)
Part: SKIN — DAMAGED (RT WING)
FOUND DURING D-CHECK, RIGHT WING LEADING EDGE HAS 4 NUT PLATES MISSING TOP OF L/E STATION XFS 22.75 - 24 AND 103-104.25. INSTALLED NAS 1670-4L FASTENERS WET WITH PR 1422B.5 PER EO NR 99-186 WITH APPROVED 8110-3 DATED 11/24/99. (M)
Part: BRACE — CRACKED (FUSELAGE)
FOUND DURING D-CHECK, CRACK IN FLOOR BRACE AT STATIN 1740 AT XCW 40 LEFT CABIN. REMOVED FLOOR BRACE IAW DC-8 SRM 51-1-4. FABRICATED L ANGLE BRACE. TREATED, PRIMED, INSTALLED IAW DC-8 SRM 51-1-20, 51-1-8. (M)
Part: FLOORBEAM — CORRODED (FUSELAGE) · airframe 88,287 hrs · 21,582 cycles
DURING MAINTENANCE VISIT FOUND CORROSION DAMAGE TO FLOORBEAM AT STA 1580 BETWEEN NR 1 AND NR 2 SEAT TRACK. DAMAGE EXCEEDED LIMITATIONS IAW DC-8 SRM. REMOVED DAMAGE, TREATED AREA IAW DC-8 SRM 51-1-8. FABRICATED AND INSTALLED DOUBLER IAW DC-8 SRM 53-2-0, 51-1-8 & 51-1-20D. (CORROSION DAMAGE RECORDED IN EWA CORROSION PROGRAM).
Part: FLOORBEAM — CORRODED (FUSELAGE)
FOUND DURING D-CHECK, FLOORBEAM AT STATION 1580 BETWEEN NR 1 - NR 2 SEAT TRACKS HAS BLOWOUT OF CORROSION AT NUT PLATE. REMOVED CORROSION IAW DC-8 SRM 51-1-8. FABRICATED DOUBLER, TREATED, PRIMED AND INSTALLED IAW DC-8 SRM 53-2-0, 51-1-8, 51-1-20D. (M)
Part: SEAT TRACK — DAMAGED (FUSELAGE) · airframe 88,287 hrs · 21,582 cycles
DURING A MAINTENANCE VISIT FOUND MAIN CABIN SEAT TRACK BETWEEN STA 120 TO STA 240 AND BL 69 LEFT. 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 53-2-3.
Part: SEAT TRACK — WORN (FUSELAGE)
FOUND DURING D-CHECK, CABIN SEAT TRACK NR 1 XCW 69 LEFT STATION 120-240 WORN. REMOVED SEAT TRACK IAW DC-8 SRM 51-1-21. INSTALLED NEW SEAT TRACK IAW DC-8 SRM 51-1-21, 51-3-0, 51-1-8, 53-2-3. (M)
Part: ANGLE — CORRODED (FUSELAGE) · airframe 88,287 hrs · 21,582 cycles
DURING A MAINTENANCE VISIT FOUND CORROSION DAMAGE TO ATTACHMENT ANGLE AT STA 1050 AND LONGERON 21 LEFT, 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.
Part: FLOORBEAM — CORRODED (FUSELAGE) · airframe 88,287 hrs · 21,582 cycles
DURING MAINTENANCE VISIT FOUND CORROSION DAMAGE TO FLOORBEAM AT STA 1680 BETWEEN SEAT TRACK NR 6 & 7. DAMAGE EXCEEDED LIMITATIONS IAW DC-8 SRM. REMOVED DAMAGE, TREATED AREA IAW DC-8 SRM 51-1-8. FABRICATED AND INSTALLED FLOORBEAM EXTRUSION IAW DC-8 SRM 51-1-8, 51-1-21 AND 51-1-4. (CORROSION DAMAGE RECORDED IN EWA CORROSION PROGRAM).
Part: FLOORBEAM — CORRODED (FUSELAGE)
FOUND DURING D-CHECK, CABIN STATION 1680 FLOORBEAM BETWEEN SEAT TRACK 6-7 HAS EXFOLIATED CORROSION. REMOVED CORROSION IAW DC-8 SRM 51-1-8. FABRICATED FLOORBEAM EXTRUSION. TREATED, PRIMED, AND INSTALLED IAW DC-8 SRM 51-1-8, 51-1-21, 51-1-4. (M)
Part: FITTING — CORRODED (FUSELAGE) · airframe 88,287 hrs · 21,582 cycles
DURING A MAINTENANCE VISIT FOUND CORROSION DAMAGE TO END FITTING AT STA 1220 AND LONGERON 32 RIGHT, DAMAGE EXCEEDED LIMITS IAW DC-8 SRM. REMOVED DAMAGE, TREATED AREA IAW DC-8 SRM 51-1-8. FABRICATED AND INSTALLED NEW FITTING IAW DC-8 SRM 53-2-0 FIGURE SHEET 1.
Part: FITTING — CORRODED (FUSELAGE)
FOUND DURING D-CHECK, AFT LOWER CARGO COMPARTMENT STATION 1220 L32R END FITTING CORRODED. REMOVED FITTING IAW DC-8 SRM 51-1-20D. CUT NEW FITTING IAW DC8 SRM 53-2-0 F2 SHEET 2. TREATED, PRIMED AND INSTALLED FITTING IAW DC-8 SRM 51-1-8, 53-2-0. (M)
Part: PLATE — CRACKED (FUSELAGE) · airframe 88,287 hrs · 21,582 cycles
DURING A MAINTENANCE VISIT FOUND AFT LOWER CARGO DOOR EXTERNAL SKIN SCUFF PLATE CRACKED RIGHT SIDE STA 1240. DAMAGE EXCEEDED LIMITATIONS IAW DC-8 SRM. REMOVED DAMAGE, TREATED AREA IAW DC-8 SRM 51-1-8. FABRICATED AND INSTALLED REPAIR IAW FAA DER APPROVED ENGINEERING SKETCH EO 99-186.
Part: FRAME — CORRODED (FUSELAGE)
FOUND DURING D-CHECK, C PIT STATION 1060 L36 CORROSION ON CIRCUMFERENTIAL FRAME. REMOVED CORROSION IAW DC-8 SRM 51-1-8. FABRICATED NEW FRAME AND DOUBLERS FOR SPLICE IAW DC-8 SRM 51-1-4. TREATED, PRIMED AND INSTALLED IAW DC-8 SRM 51-1-8, 51-1-20D AND EO NR 99-186 WITH APPROVED 8110-3 DATED 12/09/99. (M)
Part: INTERCOSTAL — CORRODED (FUSELAGE) · airframe 88,287 hrs · 21,582 cycles
DURING A MAINTENANCE VISIT FOUND CORROSION DAMAGE TO INTERCOASTAL BETWEEN STA 520 TO STA 560 AND LONGERON 33 RIGHT, DAMAGE EXCEEDED LIMITATIONS IAW DC-8 SRM. REMOVED DAMAGE, TREATED AREA IAW DC-8 SRM 51-1-8. FABRICATED NEW INTERCOASTAL AND INSTALLED IAW DC-8 SRM 51-1-4.
Part: FRAME — CORRODED (FUSELAGE) · airframe 88,287 hrs · 21,582 cycles
DURING A MAINTENANCE VISIT FOUND CORROSION DAMAGE TO FRAME AT STA 1060 AND LONGERON 36, DAMAGE EXCEEDED LIMITS IAW DC-8 SRM. REMOVED DAMAGE, TREATED AREA IAW DC-8 SRM 51-1-8. FABRICATED AND INSTALLED REPAIR FILLER & DOUBLER IAW FAA DER APPROVED ENGINEERING SKETCH 99-186.
Part: PLATE — CRACKED (FUSELAGE)
FOUND DURING D-CHECK, RIGHT AFT PASSENGER DOOR SCUFF PLATE CRACKED IN CORNER AND BROKEN ON ENDS. STOP DRILLED CRACK. NDT CONFIRMED CRACK HAD BEEN STOPPED. WELDED CRACK PER MIL-STD-2219. NDT WELD NO FLAWS FOUND PER EO NR 99-186 WITH APPROVED 8110-3 DATED 11/17/99. (M)
Part: ATTACH FITTING — CRACKED (FUSELAGE) · airframe 88,287 hrs · 21,582 cycles
DURING A MAINTENANCE VISIT FOUND FITTING CRACKED AT STA 1200 AND LONGERON 21 RIGHT. DAMAGE EXCEEDED LIMITATIONS IAW DC-8 SRM. REMOVED DAMAGE, TREATED AREA IAW DC-8 SRM 51-1-8. INSTALLED NEW FITTING IAW DC-8 SRM 51-1-20D.
Part: FITTING — CORRODED (FUSELAGE)
FOUND DURING D-CHECK, A PIT FORWARD STATION 70 L31L END FITTING CORRODED. REMOVED FITTING. REPLACED FITTING IAW DC-8 SRM 51-1-21, 51-1-24. TREATED, PRIMED AND INSTALLED IAW DC-8 SRM 51-1-21D, 53-4-1. (M)
Part: INTERCOSTAL — CORRODED (FUSELAGE)
FOUND DURING D-CHECK, UPPER CARGO COMPT STATION 1380-1400 INTERCOSTAL EXFOLIATED XCW 48 RT. REMOVED CORROSION IAW DC-8 SRM 51-1-8. FABRICATED SECTION OF INTERCOSTAL IAW DC-8 SRM 53-2-0. TREATED, PRIMED AND INSTALLED IAW DC-8 SRM 51-1-8, 51-1-21. (M)
Part: INTERCOSTAL — CORRODED (FUSELAGE) · airframe 88,287 hrs · 22 cycles
DURING A MAINTENANCE VISIT FOUND CORROSION DAMAGE TO INTERCOASTAL BETWEEN STA 1380 TO STA 1400 AND XCW 48 RIGHT, DAMAGE EXCEEDED LIMITS IAW DC-8 SRM. REMOVED DAMAGE, TREATED AREA IAW DC-8 SRM 51-1-8. FABRICATED AND INSTALLED NEW SECTION OF INTERCOASTAL IAW DC-8 SRM 53-2-0.
Part: FITTING — CORRODED (FUSELAGE)
FOUND DURING D-CHECK, AFT LOWER CARGO COMPT STATION 1220 L33R-L34R END FITTING CORRODED. REMOVED FITTING IAW DC-8 SRM 51-1-20D, CUT NEW FITTING IAW DC-8 SRM 53-3-0, 53-20 F2C SHEET 1. TREATED, PRIMED, INSTALLED IAW DC-8 SRM 51-1-8, 51-1-4, 51-1-20D. (M)
Part: BULKHEAD — CRACKED (FUSELAGE)
REAR PRESSURE BULKHEAD CIRCUMFERENTIAL FRAME TOP RIGHT SIDE HAS CRACK STATION 1766-L3R. NDT CONFIMRED END OF CRACK. CUT OUT CRACK SECTION. FABRICATED REPAIR ANGLES. TREATED AND PRIMED. INSTALLED REPAIR PER EO NR 99-186 WITH APPROVED 8110-3 DATED 9/24/99. (M)
Part: FITTING — CORRODED (FUSELAGE) · airframe 88,287 hrs · 21,582 cycles
DURING A MAINTENANCE VISIT FOUND CORROSION DAMAGE TO END FITTING AT STA 1220 BETWEEN LONGERONS 33 RIGHT TO 34 RIGHT, DAMAGE EXCEEDED LIMITS IAW DC-8 SRM. REMOVED DAMAGE, TREATED AREA IAW DC-8 SRM 51-1-8. FABRICATED AND INSTALLED NEW FITTING IAW DC-8 SRM 53-2-0 FIGURE SHEET 1.
Part: FITTING — CORRODED (FUSELAGE) · airframe 88,287 hrs · 21,582 cycles
DURING A MAINTENANCE VISIT FOUND CORROSION DAMAGE TO END FITTING AT STA 70 AND LONGERON 31 LEFT, DAMAGE EXCEEDED LIMITS IAW DC-8 SRM. REMOVED DAMAGE, TREATED AREA IAW DC-8 SRM 51-1-8. FABRICATED AND INSTALLED NEW FITTING IAW DC-8 SRM 53-4-1.
Part: BULKHEAD — CRACKED (FUSELAGE) · airframe 88,287 hrs · 21,582 cycles
DURING A MAINTENANCE VISIT FOUND AFT PRESSURE BULKHEAD CRACKED AT STA 1766 AND LONGERON 3 RIGHT. DAMAGE EXCEEDED LIMITATIONS IAW DC-8 SRM. REMOVED DAMAGE, TREATED AREA IAW DC-8 SRM 51-1-8. FABRICATED AND INSTALLED REPAIR IAW FAA DER APPROVED ENGINEERING SKETCH EO 99-186.
Part: FITTING — CORRODED (FUSELAGE)
FOUND DURING D-CHECK, A PIT FORWARD STATION 70 L31L END FITTING CORRODED. REMOVED FITTING. REPLACED FITTING IAW IAW DC-8 SRM 51-1-21, 51-1-24. TREATED, PRIMED AND INSTALLED IAW DC-8 SRM 51-1-21D, 53-4-1. (M)
Part: FITTING — WORN (FUSELAGE)
FOUND DURING D-CHECK, EXTERIOR DRAIN FITTING WORN STATION 1270 L36. FABRICATED EXTERNAL DOUBLER AND INSTALLED DOUBLER AND DRAIN FITTING PER EO NR 99-186 WITH APPROVED 8110-3 DATED 11/19/99. (M)
Part: FRAME — CORRODED (FUSELAGE)
FOUND DURING D-CHECK, AFT LOWER CARGO BILGE STATION 1220 L36 TO L35R STATION FRAME HAS CORROSION TOP FORWARD SIDE. BLENDED OUT CORROSION USING MECHANICAL METHOD. FABRICATED REPAIR ANGLES. TREATED AND PRIMED. INSTALLED REPAIR PER EO NR 99-186 WITH APPROVED 8110-3 DATED 11/18/99. (M)
Part: FITTING — CRACKED (RT WING FLAP) · airframe 88,287 hrs · 21,582 cycles
DURING A MAINTENANCE VISIT FOUND RIGHT WING FLAP STOP FITTING CRACKED AT XFS 410. DAMAGE EXCEEDED LIMITATIONS IAW DC-8 SRM. REMOVED DAMAGE, TREATED AREA IAW DC-8 SRM 51-1-8. INSTALLED NEW FLAP STOP FITTING IAW DC-8 SRM 51-3-0.
Part: RIB — CRACKED (LT WING) · airframe 88,287 hrs · 21,582 cycles
DURING A MAINTENANCE VISIT FOUND LEFT WING, FLAP WELL, RIB CRACKED AT XRS 178. DAMAGE EXCEEDED LIMITATIONS IAW DC-8 SRM. REMOVED DAMAGE, TREATED AREA IAW DC-8 SRM 51-1-8. FABRICATED AND INSTALLED REPAIR ANGLE IAW FAA DER APPROVED ENGINEERING SKETCH EO 99-186.
Part: SKIN — CORRODED (FUSELAGE) · airframe 88,287 hrs · 21,582 cycles
DURING A MAINTENANCE VISIT FOUND CORROSION DAMAGE TO FINGER DOUBLER BETWEEN STA 1440 TO STA 1460 AND LONGERON 31 RIGHT, DAMAGE EXCEEDED LIMITS IAW DC-8 SRM. REMOVED DAMAGE, TREATED AREA IAW DC-8 SRM 51-1-8. FABRICATED AND INSTALLED NEW FINGER DOUBLER IAW FAA DER APPROVED ENGINEERING SKETCH 99-186.
Part: LONGERON — CORRODED (FUSELAGE) · airframe 88,287 hrs · 21,582 cycles
DURING A MAINTENANCE VISIT FOUND CORROSION DAMAGE TO LONGERON 35 RIGHT BETWEEN STA 1150 TO STA 1160, DAMAGE EXCEEDED LIMITS IAW DC-8 SRM. REMOVED DAMAGE, TREATED AREA IAW DC-8 SRM 51-1-8. BLEND-OUT CORROSION DAMAGE TO A ACCEPTABLE LIMIT IAW FAA DER APPROVED ENGINEERING SKETCH 99-186.
Part: DUCT — DAMAGED (FUSELAGE)
FOUND DURING D-CHECK, HOT AIR DUCTS DAMAGED THROUGH OUT MAIN CABIN. REPAIRED HOT AIR DUCTS PER EO NR 99-186 WITH APPROVED 8110-3 DATED 11/14/99. (M)
Part: FITTING — CRACKED (TE FLAP)
FOUND DURING D-CHECK, RIGHT WING FLAP STATION 410 STOP FITTING CRACKED. REMOVED AND REPLACED FITTING IAW DC-8 SRM 51-3-0. (M)
Part: SKIN — CORRODED (FUSELAGE)
FOUND DURING D-CHECK, AFT LOWER CARGO COMPARTMENT STATION 1440-1460, L31R FINGER DOUBLER HAS CORROSION. REMOVED CORROSION, CUT FINGER DOUBLER OFF. TREATED AND PRIMED. IT IS ACCEPTABLE TO RETURN TO SERVICE PER EO NR 99-186 WITH APPROVED 8110-3 DATED 10/27/99. (M)
Part: RIB — CRACKED (LT WING)
FOUND DURING D-CHECK, CRACK IN RIB AT STATION XRS 178 MIDDLE AFT EDGE IN FLAP WELL LEFT WING. ROUTED OUT CRACK. FABRICATED REPAIR ANGLE AND INSTALLED PER EO NR 99-186 WITH APPROVED 8110-3 DATED 1/27/99. (M)
Part: LONGERON — CORRODED (FUSELAGE)
FOUND DURING D-CHECK, AFT LOWER CARGO BILGE STATION 1150-1160 L35R CORROSION ON TOP OF LONGERON. BLENDED OUT CORROSION USING MECHANICAL METHOD. TREATED AND PRIMED. IT IS ACCEPTABLE TO RETURN TO SERVICE PER EO NR 99-186 WITH APPROVED 8110-3 DATED 11/18/99. (M)
Part: FRAME — CORRODED (FUSELAGE) · airframe 88,287 hrs · 21,582 cycles
DURING A MAINTENANCE VISIT FOUND CORROSION DAMAGE TO FRAME AT STA 1220 BETWEEN LONGERON 36 TO 35 RIGHT, DAMAGE EXCEEDED LIMITS IAW DC-8 SRM. REMOVED DAMAGE, TREATED AREA IAW DC-8 SRM 51-1-8. BLEND-OUT DAMAGE TO A ACCEPTABLE LIMIT IAW FAA DER APPROVED ENGINEERING SKETCH 99-186.
Part: FITTING — CORRODED (FUSELAGE)
FOUND DURING D-CHECK, FORWARD ACCESSORY COMPT LONGERON 31R BOTH END FITTINGS CORRODED STATION 70. REMOVED FITTINGS. REMOVED CORROSION IAW DC-8 SRM 51-1-8, 51-1-21. TREATED, PRIMED AND INSTALLED FITTINGS IAW DC-8 SRM 51-1-8, 53-2-0, 51-1-21D. (M)
Part: FITTING — CORRODED (FUSELAGE) · airframe 88,287 hrs · 21,582 cycles
DURING A MAINTENANCE VISIT FOUND CORROSION DAMAGE TO END FITTING AT STA 70 AND LONGERON 31 RIGHT, DAMAGE EXCEEDED LIMITS IAW DC-8 SRM. REMOVED DAMAGE, TREATED AREA IAW DC-8 SRM 51-1-8. FABRICATED AND INSTALLED NEW FITTING IAW DC-8 SRM 53-4-1.
Part: LONGERON — CORRODED (FUSELAGE) · airframe 88,287 hrs · 21,582 cycles
DURING A MAINTENANCE VISIT FOUND CORROSION DAMAGE TO LONGERON 35 RIGHT BETWEEN STA 55 TO STA 70, DAMAGE EXCEEDED LIMITS IAW DC-8 SRM. REMOVED DAMAGE, TREATED AREA IAW DC-8 SRM 51-1-8. FABRICATED AND INSTALLED NEW LONGERON SECTION IAW DC-8 SRM 51-1-20D.
Part: FITTING — CORRODED (FUSELAGE)
FOUND DURING D-CHECK, A PIT AT STATION 280 AT L33R CORROSION INSIDE LIGHTING HOLE FORWARD DOOR FRAME. REMOVED AND REPLACED FITTING IAW DC-8 SRM 51-1-8 AND 51-1-20. (M)
Part: FITTING — CORRODED (FUSELAGE) · airframe 88,287 hrs · 21,582 cycles
DURING A MAINTENANCE VISIT FOUND CORROSION DAMAGE TO LOWER FORWARD CARGO DOOR JAMB FITTING AT STA 280 AND LONGERON 33 RIGHT, DAMAGE EXCEEDED LIMITS IAW DC-8 SRM. REMOVED DAMAGE, TREATED AREA IAW DC-8 SRM 51-1-8. FABRICATED AND INSTALLED NEW FITTING IAW DC-8 SRM 51-1-20.
Part: LONGERON — CORRODED (FUSELAGE)
FOUND DURNIG D-CHECK, FORWARD ACCESSORY COMPT LONGERON 35 RIGHT HAS CORROSION AT PREVIOUS REPAIR DOUBLER STATION 55 TO 70. REMOVED CORROSION AND PREVIOUS REPAIR IAW DC-8 SRM 51-1-8 AND 51-1-2. FABRICATED NEW SECTION OF LONGERON. TREATED AND PRIMED IAW DC-8 SRM 51-1-8. INSTALLED REPAIR IAW DC-8 SRM 51-1-21 AND 51-1-20D. (M)
Part: SHEAR TIE — CRACKED (FUSELAGE) · airframe 88,287 hrs · 21,582 cycles
DURING A MAINTENANCE VISIT FOUND SHEAR TIE CRACKED AT STA 660 BETWEEN LONGERONS 21 RIGHT TO 22 RIGHT. DAMAGE EXCEEDED LIMITATIONS IAW DC-8 SRM. REMOVED DAMAGE, TREATED AREA IAW DC-8 SRM 51-1-8. FABRICATED AND INSTALLED REPAIR IAW FAA DER ENGINEERING SKETCH EO 99-186.
Part: FITTING — CRACKED (FUSELAGE)
FOUND DURING D-CHECK, CABIN RT SIDE STATION 781.500 XCW 47.5 CRACK ON VERTICAL FITTING ABOVE CENTER FUEL TANK. REMOVED FITTING IAW DC-8 SRM 51-1-21. INSTALLED NEW FITTING IAW DC-8 SRM 51-1-20. TREATED AND PRIMED IAW DC-8 SRM 51-1-8. (M)
Part: ATTACH FITTING — CRACKED (EMPENNAGE) · airframe 88,287 hrs · 21,582 cycles
DURING A MAINTENANCE VISIT FOUND VERTICAL STABILIZER ATTACHMENT FITTING CRACKED AT STA 1781 AND XCW 47.5. DAMAGE EXCEEDED LIMITATIONS IAW DC-8 SRM. REMOVED DAMAGE, TREATED AREA IAW DC-8 SRM 51-1-8. INSTALLED NEW ATTACHMENT FITTING IAW DC-8 SRM 51-1-20D.
Part: SKIN — CORRODED (FUSELAGE)
FOUND DURING D-CHECK, FOUND CORROSION ON FUSELAGE FROM AROUND TAIL SKID FAIRING AND AROUND DOOR 60. REMOVED CORROSION. TREATED AND PRIMED. IT IS ACCEPTABLE TO RETURN TO SERVICE PER EO NR 99-186 WITH APPROVED 8110-3 DATED 11/18/99. (M)
Part: SKIN — CORRODED (RT WING)
FOUND DURING D-CHECK, RIGHT WING NR 3 STUB WING TRAILING EDGE UPPER SCREW HOLES CORRODED AND ELONGATED, XFS 233-245. REAMED HOLES TO .375 COUNTER SINK TO .65. FABRICATED PLUGS AND INSTALLED PER EO NR 99-186 WITH APPROVED 8110-3 DATED 11/15/99. (M)
Part: WEB — DAMAGED (FUSELAGE)
FOUND DURING D-CHECK, CABIN STATION 1630-1660 WEB HAS SEVERAL BROKEN OUT HOLES. REMOVED CRACKED AREA IAW DC-8 SRM 53-2-0. FABRICATED DOUBLER. TREATED, PRIMED, AND INSTALLED IAW DC-8 SRM 51-1-8, 51-1-21. (M)
Part: RIB — DAMAGED (TAILCONE)
FOUND DURING D-CHECK, THROUGH ACCESS PANEL 602 IN TAILCONE ON RIGHT SIDE STATION 1923 1ST RIB PASSED PANEL AFT WORN AREA IN RIB. FABRICATED DOUBLER. TREATED, PRIMED AND INSTALLED IAW DC-8 SRM 51-1-8, 51-1-4 AND 51-1-21. (M)
Part: SKIN — CORRODED (FUSELAGE) · airframe 88,287 hrs · 21,582 cycles
DURING MAINTENANCE VISIT FOUND CORROSION DAMAGE TO FUSELAGE SKIN UNDER TAIL SKID FAIRING. DAMAGE EXCEEDED LIMITATIONS IAW DC-8 SRM. REMOVED DAMAGE, TREATED AREA IAW DC-8 SRM 51-1-8.
Part: SKIN — DENTED (FUSELAGE)
FOUND DURING D-CHECK, DENT IN FUSELAGE AT STATION 25 L32-33L. BLENDED OUT DENT. FINISHED THE TITANIUM PER FACTORY SPECS IT IS ACCEPTABLE TO RETURN TO SERVICE PER EO NR 99-186 WITH APPROVED 8110-3 DATED 11/16/99. (M)
Part: ANGLE — CORRODED (CENTER WING) · airframe 88,287 hrs · 21,582 cycles
DURING A MAINTENANCE VISIT FOUND CORROSION DAMAGE TO EXTERNAL CENTER TANK ATTACHMENT ANGLE BETWEEN STA 710 TO STA 720 AND BL 47R, 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: FRAME — CRACKED (TAIL SECTION) · airframe 88,287 hrs · 21,582 cycles
DURING A MAINTENANCE VISIT FOUND TAIL CONE FRAME CRACKED RIGHT SIDE AT STA 1923. DAMAGE EXCEEDED LIMITATIONS IAW DC-8 SRM. REMOVED DAMAGE, TREATED AREA IAW DC-8 SRM 51-1-8. FABRICATED AND INSTALLED REPAIR DOUBLER IAW DC-8 SRM 51-1-4.
Part: FLOORBEAM — CORRODED (FUSELAGE) · airframe 88,287 hrs · 21,582 cycles
DURING MAINTENANCE VISIT FOUND CORROSION DAMAGE TO FLOORBEAM AT STA 1540 XCW 53 RT. DAMAGE EXCEEDED LIMITATIONS IAW DC-8 SRM. REMOVED DAMAGE, TREATED AREA IAW DC-8 SRM 51-1-8. BLENDED OUT CORROSION BY MECHANICAL METHOD. ORIGINAL THICKNESS .132 FINAL THICKNESS .102. RETURNED TO SERVICE IAW FAA APPROVED DER ENGINEERING SKETCH EO NR 99- 186 WITH APPROVED 8110-3 DATED 11/15/99. (CORROSION DAMAGE RECORDED IN EWA CORROSION PROGRAM).
Part: FITTING — CRACKED (CARGO DOOR) · airframe 88,287 hrs · 21,582 cycles
DURING A MAINTENANCE VISIT FOUND LOWER CARGO DOOR JAMB FITTING CRACKED AT STA 1220 AND LONGERON 23 RIGHT. DAMAGE EXCEEDED LIMITATIONS IAW DC-8 SRM. REMOVED DAMAGE, TREATED AREA IAW DC-8 SRM 51-1-8. INSTALLED NEW FITTING IAW DC-8 SRM 51-3-0.
Part: WEB — CRACKED (FUSELAGE)
FOUND DURING D-CHECK, CABIN WEB UNDER SEAT TRACK NR 1 BETWEEN STATION 140-160 CRACKED AROUND 1 INCH IN DIAMETER. REMOVED CRACKED AREA IAW DC-8 SRM 53-2-0. FABRICATED DOUBLER IAW DC-8 SRM 51-1-4. TREATED, PRIMED, AND INSTALLED IAW DC-8 SRM 51-1-8, 51-1-21. (M)
Part: SKIN — CORRODED (RT WING) · airframe 88,287 hrs · 21,582 cycles
DURING MAINTENANCE VISIT FOUND CORROSION DAMAGE ON NR 3 RIGHT HAND STUB-WING TRAILING EDGE UPPER SCREWS HOLES XFS 233 TO XFS 245. DAMAGE EXCEEDED LIMITATIONS IAW DC-8 SRM. REMOVED DAMAGE, TREATED AREA IAW DC-8 SRM 51-1-8. REAMED HOLES AND FABRICATED PLUGS AND INSTALLED IAW FAA APPROVED DER ENGINEERING SKETCH EO NR 99-186 WITH APPROVED 8110-3 DATED 11/15/99. (CORROSION DAMAGE RECORDED IN EWA CORROSION PROGRAM).
Part: FITTING — CRACKED (FUSELAGE)
FOUND DURING D-CHECK, C PIT DOOR UPPER AFT CUTOUT CORNER STATION 1220 L23R CRACKED FITTING. REMOVED FITTING IAW DC-8 SRM 51-1-20D. LOCATED AND DRILLED REPLACEMENT FITTING IAW DC-8 SRM 51-1-20D. TREATED, PRIMED AND INSTALLED IAW DC-8 SRM 51-120D, 51-1-21, 51-3-0. (M)
Part: SHEAR TIE — CRACKED (FUSELAGE)
FOUND DURING D-CHECK, SHEAR TIE CRACKED AT FRAME STATION 660 L21-22R. STOP DRILLED CRACK. NDT CONFIRMED CRACK HAD BEEN STOPPED. WELDED CRACK PER MIL-STD-2219. NDT WELD NO FLAWS FOUND PER EO NR 99-186 WITH APPROVED 8110-3 DATED 11/15/99. (M)
Part: DOOR FRAME — CORRODED (CARGO DOOR) · airframe 88,287 hrs · 21,582 cycles
DURING MAINTENANCE VISIT FOUND CORROSION DAMAGE TO A-PIT DOOR JAM TORQUE BOX FROM STA. 280 TO STA. 360.DAMAGE EXCEEDED LIMITATIONS IAW DC-8 SRM. REMOVED DAMAGE, TREATED AREA IAW DC-8 SRM 51-1-8. RETURNED AIRCRAFT TO SERVICE IAW FAA APPROVED DER ENGINEERING SKETCH EO 99-186 WITH APPROVED 8110-3 DATED 11/16/99.(CORROSION DAMAGE REPORTED IN EWA CORROSION PROGRAM)
Part: FRAME — CORRODED (FUSELAGE)
FOUND DURING D-CHECK, FORWARD ACCY COMPARTMENT FRAME 70 HAS CORROSION AROUND FASTENERS FROM L30L TO L31L. REMOVED CORROSION. FABRICATED STRAP AND EXTERNAL DOUBLER AND INSTALLED PER EO NR 99-186 WITH APPROVED 8110-3 DATED 11/05/99. (M)
Part: DUCT — CRACKED (FUSELAGE)
FOUND DURING D-CHECK, CABIN AIR DISTRIBUTION DUCT HAS TWO CRACKS ON TOP AT APPROX STATION 1345/1348. STOP DRILLED CRACKS. NDT CONFIRMED CRACKS HAD BEEN STOPPED. WELDED CRACKS. NDT WELDS NO FLAWS FOUND PER EO NR 99-186 WITH APPROVED 8110-3 DATED 11/14/99. (M)
Part: THRESHOLD — CRACKED (FUSELAGE)
FOUND DURING D-CHECK, L1 DOOR THRESHOLD CRACKED. STOP DRILLED CRACK AND WELDED PER EO NR 99-186 WITH APPROVED 8110-3 DATED 11/17/99. (M)
Part: THRESHOLD — CRACKED (FUSELAGE)
FOUND DURING D-CHECK, R2 DOOR THRESHOLD CRACKED. STOP DRILLED CRACK. NDT CONFIRMED CRACK HAD BEEN STOPPED. WELDED CRACK PER MIL-STD-2219, NDT WELD NO FLAWS FOUND PER EO NR 99-186 WITH APPROVED 8110-3 DATED 11/17/99. (M)
Part: SEAT TRACK — BROKEN (FUSELAGE)
FOUND DURING D-CHECK, FUSELAGE SEAT TRACK BROKEN AND WORN FROM STATION 1550-1585 TRACK 2-3. REMOVED SEAT TRACK IAW DC-8 SRM 53-2-3. FABRICATED TRACK SPLICE. TREATED, PRIMED AND INSTALLED IAW DC-8 SRM 53-2-3, 51-1-8 AND 53-1-0. (M)
Part: SEAT TRACK — DAMAGED (FUSELAGE) · airframe 88,287 hrs · 21,582 cycles
DURING A MAINTENANCE VISIT FOUND SEAT TRACK BETWEEN STA 1550 TO STA 1585 AND BL 0. 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 53-2-3.
Part: THRESHOLD — CRACKED (FUSELAGE)
FOUND DURING D-CHECK, R1 DOOR THRESHOLD CRACKED. STOP DRILLED CRACK. NDT CONFIRMED CRACK HAD BEEN STOPPED. WELDED CRACK PER MIL-STD-2219. NDT WELD NO FLAWS FOUND PER EO NR 99-186 WITH APPROVED 8110-3 DATED 11/17/99. (M)
Part: BRACE — CORRODED (FUSELAGE)
FOUND DURING D-CHECK, CABIN SCREW HOLE HAS CORROSION AT FLOOR BRACE AT STATION 1680. REMOVED CORROSION IAW DC-8 SRM 51-1-8. REMOVED FLOOR BRACE. FABRICATED FLOOR BRACE TREATED, PRIMED, INSTALLED IAW DC-8 SRM 51-1-8 AND 51-1-21. (M)
Part: FRAME — CRACKED (PAX DOOR) · airframe 88,287 hrs · 21,582 cycles
DURING A MAINTENANCE VISIT FOUND R1 PASSENGER DOOR FRAME CRACKED. DAMAGE EXCEEDED LIMITATIONS IAW DC-8 SRM. REMOVED DAMAGE, TREATED AREA IAW DC-8 SRM 51-1-8. FABRICATED AND INSTALLED REPAIR IAW FAA DER APPROVED ENGINEERING SKETCH EO 99-186.
Part: FRAME — CRACKED (PAX DOOR) · airframe 88,287 hrs · 21,582 cycles
DURING A MAINTENANCE VISIT FOUND R2 PASSENGER DOOR FRAME CRACKED. DAMAGE EXCEEDED LIMITATIONS IAW DC-8 SRM. REMOVED DAMAGE, TREATED AREA IAW DC-8 SRM 51-1-8. FABRICATED AND INSTALLED REPAIR IAW FAA DER APPROVED ENGINEERING SKETCH EO 99-186.
Part: FRAME — CRACKED (PAX DOOR) · airframe 88,287 hrs · 21,582 cycles
DURING A MAINTENANCE VISIT FOUND L1 DOOR FRAME CRACKED. DAMAGE EXCEEDED LIMITATIONS IAW DC-8 SRM. REMOVED DAMAGE, TREATED AREA IAW DC-8 SRM 51-1-8. FABRICATED AND INSTALLED REPAIR IAW FAA DER APPROVED ENGINEERING SKETCH EO 99-168.
Part: FLOOR SUPPORT — CORRODED (FUSELAGE) · airframe 88,287 hrs · 21,582 cycles
DURING A MAINTENANCE VISIT FOUND CORROSION DAMAGE TO FLOOR SUPPORT AT STA 1680, DAMAGE EXCEEDED LIMITS IAW DC-8 SRM. REMOVED DAMAGE, TREATED AREA IAW DC-8 SRM 51-1-8. FABRICATED AND INSTALLED NEW FITTING IAW DC-8 SRM 51-1-21.
Part: SEAT TRACK — DAMAGED (FUSELAGE) · airframe 88,287 hrs · 21,582 cycles
DURING A MAINTENANCE VISIT FOUND MAIN CABIN SEAT TRACK DAMAGE AT 1560 AND BL 69 RIGHT. 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.
Part: SEAT TRACK — WORN (FUSELAGE)
FOUND DURING D-CHECK, CABIN SEAT TRACK NR 5 XCW 0 STATION 240 WORN. REMOVED DAMAGED SEAT TRACK IAW DC-8 SRM 53-2-3, 51-1-21. INSTALL TRACK REPAIR IAW DC 8 SRM 53-2-3. TREATED, PRIMED IAW DC-8 SRM 51-1-8. (M)
Part: SEAT TRACK — DAMAGED (FUSELAGE) · airframe 88,287 hrs · 21,582 cycles
DURING A MAINTENANCE VISIT FOUND SEAT TRACK DAMAGED AT STA 240 AND BL 0. 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 53-2-3.
Part: SEAT TRACK — WORN (FUSELAGE)
FOUND DURING D-CHECK, CABIN SEAT TRACK NR 9 XCW 69 RT STATION 1300 WORN. REMOVED DAMAGED AREA IAW DC-8 SRM 53-2-3. INSTALLED TRACK REPAIR IAW DC-8 SRM 53-2-3. TREATED, PRIMED IAW DC-8 SRM 51-1-8. (M)
Part: SEAT TRACK — WORN (FUSELAGE)
FOUND DURING D-CHECK, CABIN SEAT TRACK NR 8 XCW RIGHT STATION 600 WORN. REMOVED DAMAGED AREA IAW DC-8 SRM 53-2-3. INSTALLED TRACK REPAIR IAW DC-8 SRM 53-2-3. TREATED, PRIMED IAW DC-8 SRM 51-1-8. (M)
Part: SEAT TRACK — DAMAGED (FUSELAGE) · airframe 88,287 hrs · 21,582 cycles
DURING A MAINTENANCE VISIT FOUND SEAT TRACK DAMAGED AT STA 600 AND BL 60 RIGHT. 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 53-2-3.
Part: SEAT TRACK — WORN (FUSELAGE)
FOUND DURING D-CHECK, CABIN SEAT TRACK NR 3 STATION 1580-1610 XCW 55 LEFT WORN. REMOVED DAMAGED AREA IAW DC-8 SRM 51-1-21. INSTALLED TRACK REPAIR IAW DC-8 SRM 51-1-21. TREATED, PRIMED IAW DC-8 SRM 51-1-8. (M)
Part: SPLICE — CRACKED (FUSELAGE)
FOUND DURING D-CHECK, B PIT BETWEEN STATION 200-220 AT L31L CRACK IN DOUBLER IN FACTORY SPLICE. REMOVED FITTING. FABRICATED NEW SPLICE FITTING AND INSTALLED IAW DC-8 SRM 51-1-8 AND 51-1-20. (M)
Part: SEAT TRACK — WORN (FUSELAGE)
FOUND DURING D-CHECK, CABIN SEAT TRACK NR 9 XCW 69 RT STATIN 1560 WORN. REMOVED DAMAGED AREA IAW DC-8 SRM 51-1-21. INSTALLED TRACK REPAIR IAW DC-8 SRM 51-1-21. TREATED, PRIMED IAW DC-8 SRM 51-1-8. (M)
Part: SEAT TRACK — DAMAGED (FUSELAGE) · airframe 88,287 hrs · 21,582 cycles
DURING A MAINTENANCE VISIT FOUND MAIN CABIN SEAT TRACK BETWEEN STA 1580 TO STA 1610 AND BL 55 LEFT. DAMAGE EXCEEDED LIMITATIONS IAW DC-8 SRM. REMOVED DAMAGE, TREATED AREA IAW DC-8 SRM 51-1-8. FABRICATED AND INSTALLED DC-8 SRM 51-1-21.
Part: SEAT TRACK — DAMAGED (FUSELAGE) · airframe 88,287 hrs · 21,582 cycles
DURING A MAINTENANCE VISIT FOUND MAIN CABIN SEAT TRACK AT STA 1300 AND BL 69 RIGHT. 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 53-2-3.
Part: SEAT TRACK — WORN (FUSELAGE)
FOUND DURING D-CHECK, CABIN SEAT TRACK NR 5 XCW 0 STATION 1040 WORN. REMOVED DAMAGED AREA OF SEAT TRACK IAW DC-8 SRM 53-2-3. INSTALLED SEAT TRACK REPAIR IAW DC-8 SRM 53-2-3. TREATED, PRIMED IAW DC-8 SRM 51-1-8. EWA (M)
Part: SEAT TRACK — DAMAGED (FUSELAGE) · airframe 88,287 hrs · 21,582 cycles
DURING A MAINTENANCE VISIT FOUND SEAT TRACK DAMAGED AT STA 680 AND BL 60 RIGHT. 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 53-2-3.
Part: SEAT TRACK — DAMAGED (FUSELAGE) · airframe 88,287 hrs · 21,582 cycles
DURING A MAINTENANCE VISIT FOUND SEAT TRACK DAMAGED AT STA 680 AND BL 0. 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 53-2-3.
Part: SEAT TRACK — DAMAGED (FUSELAGE) · airframe 88,287 hrs · 21,582 cycles
DURING A MAINTENANCE VISIT FOUND MAIN CABIN SEAT TRACK DAMAGED AT STA 1040 AND BL 0. 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 53-2-3.
Part: INTERCOSTAL — CRACKED (FUSELAGE) · airframe 88,287 hrs · 21,582 cycles
DURING A MAINTENANCE VISIT FOUND INTERCOASTAL CRACKED AT STA 1890 AND LONGERON 10 LEFT. DAMAGE EXCEEDED LIMITATIONS IAW DC-8 SRM. REMOVED DAMAGE, TREATED AREA IAW DC-8 SRM 51-1-8. FABRICATED AND INSTALLED NEW INTERCOSTAL IAW DC-8 SRM 51-1-20.
Part: SEAT TRACK — WORN (FUSELAGE)
FOUND DURING D-CHECK, UPPER CARGO COMPT SEAT TRACK NR 2 WORN STATION 240 XCW 60 LEFT. (M)
Part: SEAT TRACK — WORN (FUSELAGE)
FOUND DURNIG D-CHECK, CABIN SEAT TRACK NR 9 XCW 69 RT STATION 82-95 WORN. REMOVED DAMAGED AREA IAW DC-8 SRM 53-2-3. INSTALLED TRACK REPAIR IAW DC-8 SRM 53-2-3. TREATED, PRIMED IAW DC-8 SRM 51-1-8. (M)
Part: WEB — MISDRILLED (WING)
FOUND DURING D-CHECK, HOLE MISDRILLED INSIDE LEFT CENTER TANK AT XCW 69.5 UPPER SURFACE, FUSELAGE STATION 761. BLENDED OUT DRILL START, SPOT FACED. TREATED AND PRIMED. INSTALLED FACTORY FASTENER. IT IS ACCEPTABLE TO RETURN TO SERVICE PER EO NR 99-186 WITH APPROVED 8110-3 DATED 11/12/99. (M)
Part: SEAT TRACK — DAMAGED (FUSELAGE) · airframe 88,287 hrs · 21,582 cycles
DURING A MAINTENANCE VISIT FOUND MAIN CABIN SEAT TRACK DAMAGE BETWEEN STA 82 TO STA 95 AND BL 69 RIGHT. DAMAGE EXCEEDED LIMITATIONS IAW DC-8 SRM. REMOVED DAMAGE, TREATED AREA IAW DC-8 SRM 51-1-8. FABRICATED AND INSTALLED IAW DC-8 SRM 53-2-3.
Part: SEAT TRACK — WORN (FUSELAGE)
FOUND DURING D-CHECK, CABIN SEAT TRACK NR 8 XCW 60 RIGHT STATION 680 WORN. REMOVED DAMAGED AREA IAW DC-8 SRM 53-2-3. INSTALLED TRACK REPAIR IAW DC-8 SRM 53-2-3. TREATED, PRIMED IAW DC-8 SRM 51-1-8. (M)
Part: SEAT TRACK — WORN (FUSELAGE)
FOUND DURING D-CHECK, CABIN SEAT TRACK WORN NR 5 TRACK AT STATION 680. REMOVED DAMAGED AREA IAW DC-8 SRM 53-2-3. INSTALLED REPAIR PLUG IAW DC-8 SRM 52-2-3. TREATED, PRIMED IAW DC-8 SRM 51-1-8. EWA (M)
Part: FITTING — CORRODED (FUSELAGE) · airframe 88,287 hrs · 21,582 cycles
DURING A MAINTENANCE VISIT FOUND CORROSION DAMAGE TO LONGERON 27 RIGHT SPLICE FITTING AT STA 450, DAMAGE EXCEEDED LIMITATIONS IAW DC-8 SRM. REMOVED DAMAGE, TREATED AREA IAW DC-8 SRM 51-1-8. FABRICATED NEW FITTING AND INSTALLED IAW DC-8 SRM 51-1-4.
Part: INTERCOSTAL — CRACKED (FUSELAGE)
FOUND DURING D-CHECK, FUSELAGE STATION 1890 L10 INTERCOSTAL CRACKED. FABRICATED NEW INTERCOSTAL. TREATED, PRIMED AND INSTALLED IAW DC-8 SRM 51-1-4, 51-1-8 AND 51-1-20. (M)
Part: FRAME — CORRODED (FUSELAGE) · airframe 88,287 hrs · 21,582 cycles
DURING MAINTENANCE VISIT FOUND CORROSION DAMAGE TO FRAME AND SHEAR FOOT AT STA 660 FROM LONGERON 34L TO LONGERON 34R. DAMAGE EXCEEDED LIMITATIONS IAW DC-8 SRM. REMOVED DAMAGE, TREATED AREA IAW DC-8 SRM 51-1-8. FABRICATED AND INSTALLED FRAME IAW DC-8 SRM.
Part: FRAME — CORRODED (FUSELAGE)
FOUND DURING D-CHECK, CORROSION ON FRAME AND SHEAR FOOT STATION 660L 34L - 34R MID ACCY COMPT. REMOVED CORROSION IAW DC-8 SRM 51-1-8. FABRICATED FRAME IAW DC-8 SRM 53-1-5. TREATED, PRIMED AND INSTALLED IAW DC-8 SRM 51-1-8, 51-1-21. (M)
Part: SEAT TRACK — DAMAGED (FUSELAGE) · airframe 88,287 hrs · 21,582 cycles
DURING A MAINTENANCE VISIT FOUND MAIN CABIN SEAT TRACK DAMAGE AT STA 1690 AND BL 69 RIGHT. 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 53-2-3.
Part: SEAT TRACK — WORN (FUSELAGE)
FOUND DURING D-CHECK, CABIN SEAT TRACK NR 9 XCW 69 RT STATION 1690 WORN. REMOVED DAMAGED AREA IAW DC-8 SRM 51-1-21, 51-3-0. INSTALLED TRACK REPAIR IAW DC-8 SRM 53-2-3. TREATED, PRIMED IAW DC-8 SRM 51-1-8. (M)
Part: SEAT TRACK — CORRODED (CARGO BAY) · airframe 88,287 hrs · 21,582 cycles
DURING MAINTENANCE VISIT FOUND CORROSION DAMAGE TO SEAT TRACK AT STA 70.0 AFT OF L1 DOOR. DAMAGE EXCEEDED LIMITATIONS IAW DC-8 SRM. REMOVED DAMAGE, TREATED AREA IAW DC-8 SRM 51-1-8. FABRICATED AND INSTALLED REPAIR DOUBLER IAW DC-8 SRM 51-3-3, 53-2-3 AND 53-2-0. (CORROSION DAMAGE RECORDED IN EWA CORROSION PROGRAM).
Part: ANGLE — CORRODED (FUSELAGE)
FOUND DURING D-CHECK, UPPER CARGO COMPT STATION 25 JUST AFT CREW ENTRY DOOR SEAT EXFOLIATED. REMOVED CORROSION IAW DC-8 SRM 51-1-8. FABRICATED REPAIR DOUBLERS AND INSTALLED IAW DC-8 SRM 51-3 -3 AND 53-2-3 AND 53-2-0. (M)
Part: FLOORBOARD — CRACKED (FUSELAGE)
FOUND DURING D-CHECK, FOUND CABIN STATION 45 XCW 53 LEFT - XCW 53 RT FLOOR MEMBRANE NUMEROUS CRACKS. FABRICATED DOUBLER IAW DC-8 SRM 53-2-0, 51-1-4. TREATED, PRIMED, AND INSTALLED DOUBLER IAW DC-8 SRM 51-1-8, 51-1-21, 53-2-0. (M)
Part: FLOORBOARD — CRACKED (FUSELAGE) · airframe 88,287 hrs · 21,582 cycles
DURING A MAINTENANCE VISIT FOUND FLOOR PANEL MEMBRANE CRACKED AT STA 45 AND BL 53 RIGHT. 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 88,287 hrs · 21,582 cycles
DURING A MAINTENANCE VISIT FOUND CORROSION DAMAGE TO FITTING AT STA 70 AND LONGERON 31 LEFT, DAMAGE EXCEEDED LIMITATIONS IAW DC-8 SRM. REMOVED DAMAGE, TREATED AREA IAW DC-8 SRM 51-1-8. RECEIVED NEW FITTING AND INSTALLED IAW DC-8 SRM 53-4-1.
Part: FLOORBEAM — CORRODED (FUSELAGE)
FOUND DURING D-CHECK, TWO NUT PLATES BROKEN OFF AND CORROSION AROUND HOLES ON UNDER SIDE OF FLOORBEAM STATION 760 BETWEEN SEAT TRACKS NR 6 AND NR 7. REMOVED CORROSION BY MECHANICAL METHOD. TREATED AND PRIMED. IT IS ACCEPTABLE TO RETURN TO SERVICE PER EO NR 99-186 WITH APPROVED 8110-3 DATED 11/11/1999. (M)
Part: SPLICE — CORRODED (FUSELAGE) · airframe 88,287 hrs · 21,582 cycles
DURING A MAINTENANCE VISIT FOUND CORROSION DAMAGE TO SPLICE FITTING TO LONGERON 26 RIGHT AT STA 450, DAMAGE EXCEEDED LIMITS IAW DC-8 SRM. REMOVED DAMAGE, TREATED AREA IAW DC-8 SRM 51-1-8. FABRICATED AND INSTALLED NEW FITTING IAW DC-8 SRM 51-1-21.
Part: SPLICE — CORRODED (FUSELAGE)
FOUND DURING D-CHECK, FORWARD LOWER CARGO BILGE STATION 450 L26R LIGHT CORROSION. REMOVED CORROSION, FABRICATED SPLICE IAW DC-8 SRM 51-1-8, 51-1-4. TREATED, PRIMED AND INSTALLED IAW DC-8 SRM 51-1-8, 51-1-21. (M)
Part: FLOORBEAM — CORRODED (STA. 760) · airframe 88,287 hrs · 21,582 cycles
DURING MAINTENANCE VISIT FOUND CORROSION DAMAGE TO FLOORBEAM AT STA 760 BETWEEN SEAT TRACKS NR 6 & NR 7. DAMAGE EXCEEDED LIMITATIONS IAW DC-8 SRM. REMOVED DAMAGE, TREATED AREA IAW DC-8 SRM 51-1-8. REMOVED CORROSION BY MECHANICAL METHOD. RETURNED TO SERVICE PER FAA APPROVED DER ENGINEERING SKETCH EO NR 99-186 WITH APPROVED 8110-3 DATED 11/11/99. (CORROSION DAMAGE RECORDED IN EWA CORROSION PROGRAM).
Part: SEAT TRACK — DAMAGED (FUSELAGE) · airframe 88,287 hrs · 21,582 cycles
DURING A MAINTENANCE VISIT FOUND SEAT TRACK BETWEEN STA 757 TO STA 781 AND BL 69 LEFT. 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 53-2-3.
Part: SEAT TRACK — WORN (FUSELAGE)
FOUND DURING D-CHECK, CABIN SEAT TRACK NR 1 XCW 69 LEFT STATION 757-781 WORN. REMOVED DAMAGED SEAT TRACK IAW DC-8 SRM 51-1-21. INSTALLED SEAT TRACK IAW DC-8 SRM 53-2-3. TREATED, PRIMED, AND INSTALLED 53-2-3, 51-1-8. (M)
Part: FLOOR SUPPORT — CORRODED (CARGO BAY) · airframe 88,287 hrs · 21,582 cycles
DURING MAINTENANCE VISIT FOUND CORROSION DAMAGE TO FLOOR STRINGER BETWEEN STA 960 TO STA 980 AT XCW 10 LT. DAMAGE EXCEEDED LIMITATIONS IAW DC-8 SRM. REMOVED DAMAGE, TREATED AREA IAW DC-8 SRM 51-1-8. REMOVED AND REPLACED STRINGER FITTING IAW DC-8 SRM 51-1-21, 51-1-20 & 51-1-8. (CORROSION DAMAGE RECORDED IN EWA CORROSION PROGRAM).
Part: LONGERON — CORRODED (FUSELAGE) · airframe 88,287 hrs · 21,582 cycles
DURING MAINTENANCE VISIT FOUND CORROSION DAMAGE TO FWD WING ATTACH FITTING L24 LT. DAMAGE EXCEEDED LIMITATIONS IAW DC-8 SRM. REMOVED DAMAGE, TREATED AREA IAW DC-8 SRM 51-1-8. REPLACED LONGERON 24 LT ON NON-ROUTINE NR 1C-055.
Part: LONGERON — CORRODED (FUSELAGE)
FOUND DURING D-CHECK, SEVERAL AREAS OF CORROSION ALONG ENTIRE LENGTH OF FORWARD WING ATTACH FITTING (BATH TUBE FITTING) L24L. REPLACED LONGERON 24 LEFTO N NON-ROUTINE 1C055 W/O NR 1455. (M)
Part: PRESSURE PANEL — CORRODED (CARGO BAY) · airframe 88,287 hrs · 21,582 cycles
DURING MAINTENANCE VISIT FOUND CORROSION DAMAGE TO PRESSURE PANEL FROM STA 857 TO STA 980 AT XCWO-XCW 69 LT. DAMAGE EXCEEDED LIMITATIONS IAW DC-8 SRM. REMOVED DAMAGE, TREATED AREA IAW DC-8 SRM 51-1-8. FABRICATED AND INSTALLED FINGER DOUBLER REPAIR IAW FAA APPROVED DER ENGINEERING SKETCH EO NR 99-186 WITH APPROVED 8110-3 DATED 11/03/99. (CORROSION DAMAGE RECORDED IN EWA CORROSION PROGRAM).
Part: FITTING — CORRODED (FUSELAGE)
FOUND DURING D-CHECK, W/W PRESSURE PANEL ATTACH ANGLE CORRODED STATION 960 TO 980 RBL 8 INCH. REMOVED AND REPLACED ATTACH ANGLE AND STRINGER FITTING IAW DC-8 SRM 51-1-20, 51-1-21 AND 51-1-8. (M)
Part: SKIN — CORRODED (FUSELAGE)
FOUND DURING D-CHECK, UPPER CARGO COMPARTMENT STATION 960-980 XCW 69 LEFT PRESS PANEL EXFOLIATED UNDER FINGER DOUBLER. REMOVED CORROSION. TREATED AND PRIMED. FABRICATED NEW LARGER FINGER DOUBLER AND INSTALLED PER EO NR 99-186 WITH APPROVED 8110-3 DATED 11/03/99. (M)
Part: STRINGER — CORRODED (FUSELAGE)
FOUND DURING D-CHECK, UPPER CARGO COMPARTMENT STATION 960-980 10 INCHES BELOW FLOOR XCW 20 LEFT FLOOR STRINGER SIGNS OF EXFOLIATION. REMOVED AND REPLACED STRINGER FITTING IAW DC-8 SRM 51-1-21, 51-1-20 AND 51-1-8. (M)
Part: SKIN — CORRODED (FUSELAGE)
FOUND DURING D-CHECK, UPPER CARGO COMPARTMENT STATION 857 TO 980 LIGHT SURFACE CORROSION ON PRESSURE PANEL XCWO-XCW 69 LEFT. BLENDED OUT CORROSION. FABRICATED FINGER DOUBLER REPAIR. TREATED AND PRIMED. INSTALLED REPAIR PER EO NR 99-186 WITH APPROVED 8110-3 DATED 11/03/99. (M)
Part: STRINGER — CORRODED (FUSELAGE)
FOUND DURING D-CHECK, UPPER CARGO COMPT STATION 960-980 10 INCHES BELOW FLOOR XCW 10 LEFT FLOOR STRINGER SIGNS OF EXFOLIATION. REMOVED AND REPLACED STRINGER FITTING IAW DC-8 SRM 51-1-21, 51-1-20 AND 51-1-8. (M)
Part: PRESSURE PANEL — CORRODED (FUSELAGE) · airframe 88,287 hrs · 21,582 cycles
DURING MAINTENANCE VISIT FOUND CORROSION DAMAGE TO PRESSURE PANEL FROM STA 960 TO STA 980 AT XCW 69 LT. DAMAGE EXCEEDED LIMITATIONS IAW DC-8 SRM. REMOVED DAMAGE, TREATED AREA IAW DC-8 SRM 51-1-8. FABRICATED AND INSTALLED FINGER DOUBLER IAW FAA APPROVED DER ENGINEERING SKETCH EO NR 99-186 WITH APPROVED 8110-3 DATED 11/03/99. (CORROSION DAMAGE RECORDED IN EWA CORROSION PROGRAM).
Part: FLOOR SUPPORT — CORRODED (CARGO FLOOR) · airframe 88,287 hrs · 21,582 cycles
DURING MAINTENANCE VISIT FOUND CORROSION DAMAGE TO FLOOR STRINGER BETWEEN STA 960 AND STA 980 AT XCW 20 LT. DAMAGE EXCEEDED LIMITATIONS IAW DC-8 SRM. REMOVED DAMAGE, TREATED AREA IAW DC-8 SRM 51-1-8. REMOVED AND REPLACED STRINGER FITTING IAW DC-8 SRM 51-1-8, 51-1-21 AND 51-1-20. (CORROSION DAMAGE RECORDED IN EWA CORROSION PROGRAM).
Part: BRACKET — CORRODED (FUSELAGE) · airframe 88,288 hrs · 21,584 cycles
DURING A MAINTENANCE VISIT FOUND CORROSION DAMAGE TO THE "D" PIT GILL LINER SUPPORT AT STA 1380 TO 1400, 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 AND 51-1-21.
Part: LONGERON — CORRODED (FUSELAGE) · airframe 88,287 hrs · 21,582 cycles
DURING A MAINTENANCE VISIT FOUND CORROSION DAMAGE TO LONGERON 32 RIGHT BETWEEN STA 1160 TO STA 1200, DAMAGE EXCEEDED LIMITS IAW DC-8 SRM. REMOVED DAMAGE, TREATED AREA IAW DC-8 SRM 51-1-8. BLEND-OUT DAMAGE TO A ACCEPTABLE LIMIT IAW FAA DER APPROVED ENGINEERING SKETCH 99-186.
Part: SPAR — MISDRILLED (RT WING)
FOUND DURING D-CHECK, RIGHT WING OUTBOARD LEADING EDGE UPPER SPAR CAP HAS SEVERAL MISDRILLED HOLES AT NUT CHANNEL. DRILLED THE DISCREPANT HOLES ROUND TO ELIMINATE THE DOUBLE DRILLED CONDITION. TREATED AND PRIMED. LEFT OVERSIZED HOLES OPEN. INSTALLED REMAINDER OF GANG CHANNEL PER FACTORY SPECS, PER EO NR 99-186 WITH APPROVED 8110-3 DATED 11/08/99. (M)
Part: LONGERON — CORRODED (FUSELAGE)
FOUND DURING D-CHECK, AFT LOWER BILGE STATION 1160-1200 L32R RIGHT SIDE OF LONGERON HAS CORROSION. BLENDED OUT CORROSION USING MECHANICAL METHOD. APPLIED TWO COATES OF PRIMER AND FINISH PER DC-8 SRM 51-1-8. IT IS ACCEPTABLE TO RETURN TO SERVICE PER EO NR 99-186 WITH APPROVED 8110-3 DATED 11/03/99. (M)
Part: SPAR CAP — CRACKED (LT WING) · airframe 88,287 hrs · 21,582 cycles
DURING A MAINTENANCE VISIT FOUND LEFT WING, FORWARD LOWERS PAR CAP CRACKED AT XFS 520. DAMAGE EXCEEDED LIMITATIONS IAW DC-8 SRM. REMOVED DAMAGE, TREATED AREA IAW DC-8 SRM 51-1-8. FABRICATED AND INSTALLED REPAIR IAW FAA DER ENGINEERING SKETCH EO 99-186.
Part: SHIM — CRACKED (LT WING)
FOUND DURING D-CHECK, LEFT WING FRONT LOWER SPAR CAP STATION XFS 520 SHIM PLATE HAS CRACK APPROX .75 INCH. CUT OUT DOUBLER AT CRACK. FINISHED ENDS OF SHIM SMOOTH. TREATED AND PRIMED. BONDED PIECE OF SHIM IN PLACE. IT IS ACCEPTABLE TO RETURNE TO SERVICE PER EO NR 99-186 WITH APPROVED 8110-3 DATED 11/08/99. (M)
Part: FITTING — CHAFED (LT WING)
FOUND DURING D-CHECK, NR 2 FLAP CANOE XW 98 T/E CHAFFED. REMOVED GOUGES BY BLENDING. TREATED AND PRIMED. IT IS ACCEPTABLE TO RETURN TO SERVICE PER EO NR 99-186 WITH APPROVED 8110-3 DATED 11/03/99. (M)
Part: SKIN — CRACKED (RT WING)
FOUND DURING D-CHECK, RIHT WING L/E NR 3 STUB WING UPPER INBOARD EDGE HAS 6 INCH CRACK STATION EX 257.50. COMBINED REPAIR, ALSO TASK 1B178. CUT OUT DAMAGED AREA. FABRICATED REPLACEMENT SECTION FOR SECTION REMOVED. FABRICATED SPLICE PLATES. TREATED, PRIMED AND INSTALLED PER EO NR 99-186 WITH APPROVED 8110-3 DATED 11/01/99. (M)
Part: SKIN — CRACKED (RT WING) · airframe 88,287 hrs · 21,582 cycles
DURING A MAINTENANCE VISIT FOUND RIGHT WING LEADING EDGE WITH 6 INCH CRACK AT XW 257.5. DAMAGE EXCEEDED LIMITATIONS IAW DC-8 SRM. REMOVED DAMAGE, TREATED AREA IAW DC-8 SRM 51-1-8. FABRICATED AND INSTALLED REPAIR IAW FAA DER APPROVED ENGINEERING SKETCH EO 99-186.
Part: SKIN — DAMAGED (LH WING) · airframe 88,287 hrs · 21,582 cycles
DURING A MAINTENANCE VISIT REMOVED TEMPORARY REPAIR FROM LEFT WING LEADING EDGE AT XFS 250. REMOVED TEMPORARY REPAIR, TREATED AREA IAW DC-8 SRM 51-1-8. FABRICATED AND INSTALLED NEW REPAIR IAW FAA DER APPROVED ENGINEERING SKETCH EO 99-186.
Part: SKIN — LOOSE (LT WING)
FOUND DURING D-CHECK, NR 2 ENGINE STUB WING TEMP REPAIR FR XS 246 - XS 233 PULLING LOOSE BOTTOM SIDE. REMOVED TEMPORARY REPAIR. TREATED AND PRIMED. FABRICATED DOUBLER AND INSTALLED PER EO NR 99-186 WITH APPROVED 8110-3 DATED 10/27/99. (M)
Part: SKIN — DAMAGED (LT WING)
FOUND DURING D-CHECK, NR 2 ENGINE STUB WING SCREWS PULLING THROUGH COUNTER SINKS FR XS 250. REMOVED TEMPORARY REPAIR, TREATED, PRIMED. FABRICATED DOUBLER AND INSTALLED PER EO NR 99-186 WITH APPROVED 8110-3 DATED 10/27/99. (M)
Part: ATTACH FITTING — CRACKED (HORIZONTAL STAB) · airframe 88,287 hrs · 21,582 cycles
DURING A MAINTENANCE VISIT FOUND HORIZONTAL STABILIZER LEFT SIDE ATTACHMENT FITTING CRACKED AT XCW 47.5. DAMAGE EXCEEDED LIMITATIONS IAW DC-8 SRM. REMOVED DAMAGE, TREATED AREA IAW DC-8 SRM 51-1-8. INSTALLED NEW ATTACHMENT FITTING IAW DC-8 SRM 51-1-20D.
Part: FITTING — CRACKED (FUSELAGE)
FOUND DURING D-CHECK, CABIN CRACKED HORIZONTAL FITTING STATION 798 XCW 47.5 LEFT. REMOVED FITTING IAW DC-8 SRM 51-1-21. INSTALLED NEW FITTING IAW DC-8 SRM 51-1-8, 51-1-20D. (M)
Part: FITTING — GOUGED (LT WING)
FOUND DURING D-CHECK, NR 3 CANOE FITTING INBOARD AFT SIDE IS GOUGED. REMOVED GOUGES BY BLENDING SMOOTH. TREATED AND PRIMED. IT IS ACCEPTABLE TO RETURN TO SERVICE PER EO NR 99-186 WITH APPROVED 8110-3 DATED 11/02/99. (M)
Part: FITTING — CRACKED (FUSELAGE)
FOUND DURING D-CHECK, CRACK IN UPPER CUSP CARGO DOOR FRAME ATTACH FITTING FRAME STATION 120 FORWARD ATTACH FITTING. REMOVED AND REPLACED FITTING IAW DC-8 SRM 51-1-8, 51-3-0 AND 51-1-20D. (M)
Part: ATTACH FITTING — CRACKED (FUSELAGE) · airframe 88,287 hrs · 21,582 cycles
DURING A MAINTENANCE VISIT FOUND UPPER CARGO DOOR JAMB FRAME ATTACHMENT FITTING CRACKED AT STA 120 AND LONGERON 21 RIGHT. DAMAGE EXCEEDED LIMITATIONS IAW DC-8 SRM. REMOVED DAMAGE, TREATED AREA IAW DC-8 SRM 51-1-8. INSTALLED NEW FRAME ATTACHMENT FITTING IAW DC-8 SRM 51-3-0.
Part: FLOORBEAM — CORRODED (FUSELAGE) · airframe 88,287 hrs · 21,582 cycles
DURING MAINTENANCE VISIT FOUND CORROSION DAMAGE TO FLOORBEAM AT STA 1320 BETWEEN SEAT TRACK NR 5 AND 6. DAMAGE EXCEEDED LIMITATIONS IAW DC-8 SRM. REMOVED DAMAGE, TREATED AREA IAW DC-8 SRM 51-1-8. FABRICATED AND INSTALLED DOUBLER AND FILLER IAW DC-8 SRM 51-1-21, 51-1-8 AND 51-1-21. (CORROSION DAMAGE RECORDED IN EWA CORROSION PROGRAM).
Part: FRAME — CORRODED (FUSELAGE)
FOUND DURING D-CHECK, CORROSION ON FRAME 1793 IN CHANNEL L32L TO L32R. REMOVED CORROSION IAW DC-8 SRM 51-1-8. FABRICATED DOUBLERS, TREATED, PRIMED AND INSTALLED IAW DC-8 SRM 51-1-8, 53-2-0 AND 51-1-20D. (M)
Part: FLOORBEAM — CORRODED (FUSELAGE)
FOUND DURING D-CHECK, CABIN CORROSION ON FLOORBEAM AT STATION 1320 BETWEEN 5-6 TRACK. REMOVED CORROSION IAW DC-8 SRM 51-1-8. FABRICATED DOUBLER AND FILLER IAW DC-8 SRM 51-1-21, 51-1-4. TREATED, PRIMED AND INSTALLED IAW DC-8 SRM 51-1-8, 51-1-21. (M)
Part: WEB — CORRODED (FUSELAGE) · airframe 88,287 hrs · 21,582 cycles
DURING MAINTENANCE VISIT FOUND CORROSION DAMAGE ON FLOOR WEB BELOW R1 ENTRY DOOR. DAMAGE EXCEEDED LIMITATIONS IAW DC-8 SRM. REMOVED DAMAGE, TREATED AREA IAW DC-8 SRM 51-1-8. RETURNED TO SERVICE IAW FAA APPROVED DER ENGINEERING SKETCH EO NR 99-186 WITH APPROVED 8110-3 DATED 10/20/99. (CORROSION DAMAGE RECORDED IN EWA CORROSION PROGRAM).
Part: FLOORBEAM — CORRODED (FUSELAGE) · airframe 88,287 hrs · 21,582 cycles
DURING MAINTENANCE VISIT FOUND CORROSION DAMAGE TO FLOORBEAM AT STA 1500 XCW 40 AND XCW 53 RT. DAMAGE EXCEEDED LIMITATIONS IAW DC-8 SRM. REMOVED DAMAGE, TREATED AREA IAW DC-8 SRM 51-1-8. FABRICATED AND INSTALLED REPAIR DOUBLER IAW DC-8 SRM 51-1-8, 51-1-20 AND 51-3-0. (CORROSION DAMAGE RECORDED IN EWA CORROSION PROGRAM).
Part: WEB — CORRODED (FUSELAGE)
FOUND DURING D-CHECK, FORWARD RIGHT TYPE 1 DOOR BELOW ON FLOOR WEB UNDERNEATH DOOR MOUNTING BRACKET HAS CORROSION. REMOVED CORROSION BY MECHANICAL METHOD. TREATED AND PRIMED. IT IS ACCEPTABLE TO RETURN TO SERVICE PER EO NR 99-186 WITH APPROVED 8110-3 DATED 10/20/99. (M)
Part: WEB — CORRODED (FUSELAGE)
FOUND DURING D-CHECK, FORWARD LT TYPE 1 DOOR BELOW ON FLOORWEB UNDERNEATH DOOR MOUNTING BRACKET HAS CORROSION. REMOVED CORROSION BY MECHANICAL METHOD. TREATED AND PRIMED. IT IS ACCEPTABLE TO RETURN TO SERVICE PER EO NR 99-186 WITH APPROVED 8110-3 DATED 10/20/99. (M)
Part: SKIN — CORRODED (RT WING)
FOUND DURING D-CHECK, NR 3 RIGHT STUB WING UPPER FASTENER HOLES L/E ATTACH POINT HAVE CORROSION. BLEND OUT CORROSION USING MECHANICAL METHOD. TREATED AND PRIMED. IT IS ACCEPTABLE TO RETURN TO SERVICE PER EO NR 99-186 WITH APPROVED 8110-3 DATED 10/26/99. (M)
Part: ATTACH FITTING — CRACKED (FUSELAGE) · airframe 88,287 hrs · 21,582 cycles
DURING A MAINTENANCE VISIT FOUND CUSP ATTACHMENT FITTING CRACKED AT STA 1160 AND LONGERON 21 LEFT. DAMAGE EXCEEDED LIMITATIONS IAW DC-8 SRM. REMOVED DAMAGE, TREATED AREA IAW DC-8 SRM 51-1-8. INSTALLED NEW CUSP ATTACHMENT FITTING IAW DC-8 SRM 51-1-20D.
Part: SKIN — CORRODED (RT WING) · airframe 88,287 hrs · 21,582 cycles
DURING MAINTENANCE VISIT FOUND CORROSION DAMAGE ON NR 3 RIGHT HAND STUB-WING UPPER FASTENER ATTACH HOLES. DAMAGE EXCEEDED LIMITATIONS IAW DC-8 SRM. REMOVED DAMAGE, TREATED AREA IAW DC-8 SRM 51-1-8. RETURNED TO SERVICE IAW FAA APPROVED DER ENGINEERING SKETCH EO NR 99-186 WITH APPROVED 8110-3 DATED 10/26/99. (CORROSION DAMAGE RECORDED IN EWA CORROSION PROGRAM).
Part: PIPE — GOUGED (FUEL SYSTEM)
FOUND DURING D-CHECK, FUEL PIPE ASSY P/N 7751562590 HAS 3 DEEP GOUGES AND COUPLING THREADS HAVE DAMAGE. DRILLED NR 30 HOLE IN CENTER OF 3 GOUGES. FABRICATED PATCH AND WELDED IN PLACE. NDT WELD, NO FLAWS FOUND. PRESSURE TESTED TO 90 PSI, NO LEAKS FOUND. DRESSED THREADS PER EO NR 99-186 WITH APPROVED 8110-3 DATED 10/20/99. (M)
Part: FLOORBEAM — CORRODED (FUSELAGE)
FOUND DURING D-CHECK, UPPER CARGO COMPARTMENT STATION 822 LEFT XCW 51 FLOORBEAM HAS AREA OF EXFOLIATION. (M)
Part: LONGERON — CRACKED (FUSELAGE)
FOUND DURING D-CHECK, AFT LOWER CARGO BILGE STATION 1240 L35R TOP OF LONGERON METAL STRIP CRACKED. REMOVED BRACKET IAW DC-8 SRM 51-3-20. FABRICATED METAL STRIP IAW DC-8 SRM 53-2-0. TREATED, PRIMED AND INSTALLED IAW DC-8 SRM 51-1-8, 51-3-0. (M)
Part: SKIN — DAMAGED (LT WING)
FOUND DURING D-CHECK, LEFT INBOARD WING LE 9 TOP MOUNT HOLE COUNTER SINKS ELONGATED. (M)
Part: FRAME — CRACKED (FUSELAGE) · airframe 88,287 hrs · 21,582 cycles
DURING A MAINTENANCE VISIT FOUND FRAME CRACKED AT STA 1580 AND LONGERON 21 LEFT. 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 88,287 hrs · 21,582 cycles
DURING A MAINTENANCE VISIT FOUND CORROSION DAMAGE TO FITTING BETWEEN STA 80 TO STA 100 AND LONGERON 13 RIGHT, DAMAGE EXCEEDED LIMITATIONS IAW DC-8 SRM. REMOVED DAMAGE, TREATED AREA IAW DC-8 SRM 51-1-8. RECEIVED NEW FITTING AND INSTALLED IAW DC-8 SRM 51-1-24.
Part: FLOORBEAM — CORRODED (FUSELAGE)
FOUND DURING D-CHECK, CABIN STATION 1140 XCW 60 LEFT FLOORBEAM AREA EXFOLIATED. REMOVED CORROSION IAW DC-8 SRM 51-1-8. FABRICATED DOUBLER IAW DC-8 SRM 53-2-0. TREATED, PRIMED, INSTALLED IAW DC-8 SRM 51-1-8, 51-1-20D. (M)
Part: FLOORBEAM — CORRODED (FUSELAGE) · airframe 88,287 hrs · 21,582 cycles
DURING MAINTENANCE VISIT FOUND CORROSION DAMAGE TO FLOORBEAM AT STA 1140 XCW 60 LT. DAMAGE EXCEEDED LIMITATIONS IAW DC-8 SRM. REMOVED DAMAGE, TREATED AREA IAW DC-8 SRM 51-1-8. FABRICATED AND INSTALLED DOUBLER IAW DC-8 SRM 53-2-0, 51-1-8 AND 51-1-20D. (CORROSION DAMAGE RECORDED IN EWA CORROSION PROGRAM).
Part: FRAME — CRACKED (FUSELAGE)
FOUND DURING D-CHECK, UPPER CARGO COMPT STATION 1580 UPPER CUSP LINE FRAME CRACKED AND BENT LONGERON 21 LEFT. CUTOUT DAMAGED SECTION IAW DC-8 SRM 53-2-0. FABRICATED REPAIR FILLER AND DOUBLER IAW DC-8 SRM 53-2-0. TREATED AND PRIMED IAW DC-8 SRM 51-1-8. INSTALLED REPAIR IAW DC-8 SRM 53-2-0. (M)
Part: FLOORBOARD — CRACKED (FUSELAGE)
FOUND DURING D-CHECK, FOUND CABIN STATION 1380 FLOOR MEMBRANE CRACKED AT FLOORBEAM. REMOVED MEMBRANE IAW DC-8 SRM 51-1-21. FABRICATED MEMBRANE, TREATED, PRIMED AND INSTALLED IAW DC-8 SRM 51-1-4, 51-1-8, 51-1-21. (M)
Part: FLOORBOARD — CRACKED (FUSELAGE) · airframe 88,287 hrs · 21,582 cycles
DURING A MAINTENANCE VISIT FOUND FLOOR PANEL MEMBRANE AT STA 1380 AND LONGERON 21 LEFT. DAMAGE EXCEEDED LIMITATIONS IAW DC-8 SRM. REMOVED DAMAGE, TREATED AREA IAW DC-8 SRM 51-1-8. FABRICATED AND INSTALLED MEMBRANE IAW DC-8 SRM 51-1-21.
Part: FITTING — CORRODED (FUSELAGE)
FOUND DURING D-CHECK, AFT LOWER CARGO COMPARTMENT STATION 1160-1180 L26R END OF LONGERON HAS CORROSION. REMOVED CORROSION IAW DC-8 SRM 51-1-8. FABRICATED FITTING IAW DC-8 SRM 51-1-4, 51-1-21. TREATED AND PRIMED, AND INSTALLED IAW DC-8 SRM 51-1-8, 51-1-21. (M)
Part: FITTING — CORRODED (FUSELAGE) · airframe 88,287 hrs · 21,582 cycles
DURING A MAINTENANCE VISIT FOUND CORROSION DAMAGE TO END FITTING BETWEEN STA 1160 TO STA 1180 AND LONGERON 26 RIGHT, DAMAGE EXCEEDED LIMITS IAW DC-8 SRM. REMOVED DAMAGE, TREATED AREA IAW DC-8 SRM 51-1-8. FABRICATED AND INSTALLED NEW FITTING IAW DC-8 SRM 53-2-0 FIGURE SHEET 1.
Part: SKIN — CORRODED (FUSELAGE) · airframe 88,287 hrs · 21,582 cycles
DURING MAINTENANCE VISIT FOUND CORROSION DAMAGE TO FWD ACCESSORY COMPARTMENT SKIN ABOVE LONGERON 31 RT AT FUSELAGE STA 42.0. DAMAGE EXCEEDED LIMITATIONS IAW DC-8 SRM. REMOVED DAMAGE, TREATED AREA IAW DC-8 SRM 51-1-8. FABRICATED AND INSTALLED REPAIR DOUBLER IAW FAA DER APPROVED ENGINEERING SKETCH EO 99-186. (CORROSION DAMAGE RECORDED IN EWA CORROSION PROGRAM).
Part: SKIN — CORRODED (FUSELAGE)
FOUND DURING D-CHECK, FORWARD ACCY COMPT CORROSION UNDER DOME NUT AIR CONDITION FRAME JUST ABOVE LONGERON 31 RT STATION 42. BLENDED CORROSION USING MECHANICAL METHOD NOT TO EXCEED .128 REMAINING THICKNESS. TREAT AND PRIME PER EO NR 99-186 WITH APPROVED 8110-3 DATED 10/26/99. (M)
Part: FLOORBOARD — CRACKED (FUSELAGE)
FOUND DURING D-CHECK, UPPER CARGO COMPT FLOOR PANEL 760-1100, 5-6 INCH CRACK ON FLOOR PANEL. CUT OUT DAMAGED AREA IAW DC-8 SRM 53-2-0. FABRICATED REPAIR DOUBLERS. TREATED, PRIMED, INSTALLED IAW DC-8 SRM 51-1-8 AND 53-2-3 AND 51-1-21. (M)
Part: SEAT TRACK — CORRODED (FUSELAGE)
FOUND DURING D-CHECK, UPPER CARGO CARGO COMPT SEAT TRACK XCW.0 STATION 1540 EXFOLIATED.
Part: FLOORBOARD — CRACKED (FUSELAGE) · airframe 88,287 hrs · 21,582 cycles
DURING A MAINTENANCE VISIT FOUND FLOOR PANEL CRACKED BETWEEN STA 760 TO 1100. 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 53-2-3.
Part: FLOORBEAM — CORRODED (FUSELAGE)
FOUND DURING D-CHECK, UPPER CARGO COMPT CORROSION ON FLOORBEAM SEAT TRACK ATTACH POINT XCW 40 RIGHT STATION 1440. (M)
Part: ANGLE — CRACKED (RT WING) · airframe 88,287 hrs · 21,582 cycles
DURING A MAINTENANCE VISIT FOUND RIGHT WING LEADING EDGE INTERNAL ANGLE CRACKED AT XW 230. 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 51-1-4.
Part: ANGLE — CRACKED (RT WING)
FOUND DURING D-CHECK, NR 3 RT STUB WING HAS CRACK INSIDE L/E DOUBLER. REMOVED CRACKED ANGLE. FABRICTED NEW ANGLE, TREATED, PRIMED AND INSTALLED IAW DC-8 SRM 51-1-8, 51-1-4 AND 51-1-20D. (M)
Part: FINGER DOUBLER — CORRODED (FUSELAGE)
FOUND DURING D-CHECK, WHEEL WELL PRESS PANEL HAS CORROSION AROUND RIVETS AND PANEL STATION 902 TO 920 RBL 20 INCH. REMOVED CORROSION IAW DC-8 SRM 51-1-8. FABRICATED FINGER DOUBLER REPAIR. TREATED, PRIMED AND INSTALLED IAW DC-8 SRM 51-1-8 AND 51-1-4 AND 51-1-21. (M)
Part: SEAT TRACK — WORN (FUSELAGE)
FOUND DURING D-CHECK, UPPER CARGO COMPARTMENT SEAT TRACK NR 6 XCW 25 RIGHT STATION 500-510. CUT OUT WORN SECTION OF TRACK. INSTALLED NEW TRACK AND SPLICES IAW DC-8 SRM 53-2-3, 51-1-8 AND 51-3-0. (M)
Part: SEAT TRACK — DAMAGED (FUSELAGE) · airframe 88,287 hrs · 21,582 cycles
DURING A MAINTENANCE VISIT FOUND UPPER CARGO SEAT TRACK DAMAGED BETWEEN STA 500 TO STA 510 AND BL 25 RIGHT. DAMAGE EXCEEDED LIMITATIONS IAW DC-8 SRM. REMOVED DAMAGE, TREATED AREA IAW DC-8 SRM 51-1-8. FABRICATED AND INSTALLED REPAIR SPLICE IAW DC-8 SRM 53-2-3.
Part: FINGER DOUBLER — CORRODED (FUSELAGE) · airframe 88,287 hrs · 21,582 cycles
DURING MAINTENANCE VISIT FOUND CORROSION DAMAGE TO WHEEL WELL PRESSURE PANEL AROUND RIVETS FROM STA 902 TO STA 920 RBL 20.0. DAMAGE EXCEEDED LIMITATIONS IAW DC-8 SRM. REMOVED DAMAGE, TREATED AREA IAW DC-8 SRM 51-1-8. FABRICATED AND INSTALLED FINGER DOUBLERS IAW DC-8 SRM 51-1-8, 51-1-4 & 51-1-21. (CORROSION DAMAGE RECORDED IN EWA CORROSION PROGRAM).
Part: FLOORBEAM — CORRODED (CARGO BAY)
FOUND DURING D-CHECK, UPPE CARGO COMPT STATION 1120 XCW 50 LEFT FLOORBEAM SEAT TRACK MOUNT POINT, AREA OF CORROSION. (M)
Part: LONGERON — CORRODED (FUSELAGE)
FOUND DURING D-CHECK, UPPER CARGO COMPT LONGERON 9 STATION 1300-1340 LT SURFACE CORROSION. REMOVED CORROSION IAW DC-8 SRM 51-1-8. CUTOUT DAMAGED AREA. FABRICATED DOUBLER PARTS IAW DC-8 SRM 53-2-2. TREATED, PRIMED AND INSTALLED IAW DC-8 SRM 51-1-8, 53-2-2. (M)
Part: FLOORBOARD — CORRODED (FUSELAGE)
FOUND DURING D-CHECK, UPPER CARGO COMPT FLOOR PANEL 580-840 AREA OF EXFOLIATION. REMOVED CORROSION IAW DC-8 SRM 51-1-8. FABRICATED REPAIR DOUBLER. TREATED, PRIMED AND INSTALLED IAW DC-8 SRM 51-1-8 AND 53-2-0 AND 51-1-21. (M)
Part: FLOORBEAM — CORRODED (FUSELAGE)
FOUND DURING D-CHECK, UPPER CARGO COMPT FLOORBEAM EXFOLIATED STATION 1500 XCW 50 LEFT. REMOVED CORROSION IAW DC-8 SRM 51-18-8. FABRICATED DOUBLER. TREATED, PRIMED AND INSTALLED IAW DC-8 SRM 51-2-0 AND 51-1-8 AND 51-3-0. (M)
Part: FLOORBEAM — CORRODED (FUSELAGE) · airframe 88,287 hrs · 21,582 cycles
DURING MAINTENANCE VISIT FOUND CORROSION DAMAGE TO FLOORBEAM AT STA 1500 XCW 50 LT. DAMAGE EXCEEDED LIMITATIONS IAW DC-8 SRM. REMOVED DAMAGE, TREATED AREA IAW DC-8 SRM 51-1-8. FABRICATED DOUBLER AND INSTALLED IAW DC-8 SRM 51-2-0, 51-1-8 AND 51-3-0. (CORROSION DAMAGE RECORDED IN EWA CORROSION PROGRAM).
Part: SKIN — CORRODED (FUSELAGE)
FOUND DURING D-CHECK, FUSELAGE CORRODED AROUND NUT PLATE HOLES FOR WING FILLET ATTACH UPPER STATION 980 TO 1120. REMOVED CORROSION IAW DC-8 SRM 51-1-8. FABRICATED DOUBLER IAW DC-8 53-2-1. TREATED, PRIMED AND INSTALLED DOUBLER IAW DC-8 SRM 51-1-8, 51-1-21 AND 51-1-20D. (M)
Part: SKIN — CORRODED (FUSELAGE) · airframe 88,287 hrs · 21,582 cycles
DURING A MAINTENANACE VISIT FOUND CORROSION DAMAGE TO INTERNAL SKIN AT BETWEEN STA 980 TO 1120. DAMAGE EXCEEDED LIMITATIONS IAW DC-8 SRM. REMOVED DAMAGE, TREATED AREA IAW DC-8 SRM 51-1-8. FABRICATED AND INSTALLED REPAIR DOUBLER IAW DC-8 SRM 53-2-1.
Part: FLOORBOARD — CORRODED (CARGO FLOOR) · airframe 88,287 hrs · 21,582 cycles
DURING MAINTENANCE VISIT FOUND CORROSION DAMAGE TO UPPER CARGO COMPARTMENT FLOOR PANEL BETWEEN STA 580 TO STA 840. DAMAGE EXCEEDED LIMITATIONS IAW DC-8 SRM. REMOVED DAMAGE, TREATED AREA IAW DC-8 SRM 51-1-8. FABRICATED AND INSTALLED REPAIR DOUBLER IAW DC-8 SRM 51-1-8, 51-2-0 & 51-1-21. (CORROSION DAMAGE RECORDED IN EWA CORROSION PROGRAM).
Part: LONGERON — CORRODED (CARGO BAY) · airframe 88,287 hrs · 21,582 cycles
DURING MAINTENANCE VISIT FOUND CORROSION DAMAGE TO LONGERON NR 9 BETWEEN STA 1300 TO STA 1340 LT. DAMAGE EXCEEDED LIMITATIONS IAW DC-8 SRM. REMOVED DAMAGE, TREATED AREA IAW DC-8 SRM 51-1-8. FABRICATED AND INSTALLED DOUBLER IAW DC-8 SRM 53-2-2 & 51-1-8. (CORROSION DAMAGE RECORDED IN EWA CORROSION PROGRAM).
Part: FLOOR PANEL — CORRODED (FUSELAGE) · airframe 88,287 hrs · 21,582 cycles
DURING A MAINTENANCE VISIT FOUND CORROSION DAMAGE TO FLOOR PANEL BETWEEN STA 880 TO STA 1100 AND BL 45R, 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 53-2-3.
Part: WEB — CORRODED (FUSELAGE)
FOUND DURING D-CHECK, RIGHT LONGERON AND FUSELAGE WEB ATTACHMENT CORROSION EXIST FROM STATION 879 TO 960. BLENDED OUT CORROSION. TREATED AND PRIMED. IT IS ACCEPTABLE TO RETURN TO SERVICE PER EO NR 99-186 WITH APPROVED 8110-3 DATED 10/11/99. (M)
Part: SKIN — CORRODED (FUSELAGE) · airframe 88,287 hrs · 21,582 cycles
DURING A MAINTENANCE VISIT FOUND CORROSION DAMAGE TO SKIN PANEL 262 BETWEEN STA 960 TO STA 1000 AND LEFT SIDE, DAMAGE EXCEEDED LIMITATIONS IAW DC-8 SRM. REMOVED DAMAGE, TREATED AREA IAW DC-8 SRM 51-1-8. FABRICATED AND INSTALLED NEW PANEL IAW FAA DER APPROVED ENGINEERING SKETCH EO 99-186.
Part: FINGER DOUBLER — CORRODED (FUSELAGE)
FOUND DURING D-CHECK, FINGER DOUBLER CORRODED AND RIVET CORRODED STATION 857 TO 902 CENTER OF AIRCRAFT 10 INCHES BELOW CABIN FLOOR. REMOVED CORROSION IAW DC-8 SRM 51-1-8. FABRICATED FINGER DOUBLER. TREATED, PRIMED AND INSTALLED IAW DC-8 SRM 51-1-8, 51-1-4 AND 51-1-21. (M)
Part: FLOORBEAM — CORRODED (FUSELAGE) · airframe 88,287 hrs · 21,582 cycles
DURING MAINTENANCE VISIT FOUND CORROSION DAMAGE TO FLOOR BEAM AT STA. 1220 XCW 51 R/H. DAMAGE EXCEEDED LIMITATIONS IAW DC-8 SRM.///// CORRECTIVE ACTION ///// REMOVED DAMAGE, TREATED AREA IAW DC-8 SRM 51-1-8. FABRICATED REPAIR DOUBLER AND INSTALLED IAW DC-8 SRM 51-1-4, 51-1-8 AND 51-1- 21. (COROSION DAMAGE RECORDED IN EWA CORROSION PROGRAM)
Part: FINGER DOUBLER — CORRODED (CABIN FLOOR) · airframe 88,287 hrs · 21,582 cycles
DURING MAINTENANCE VISIT FOUND CORROSION DAMAGE FROM FS 857 TO FS 902 AT BL 0.0 BELOW CABIN FLOOR. DAMAGE EXCEEDED LIMITATIONS IAW DC-8 SRM. REMOVED DAMAGE, TREATED AREA IAW DC-8 SRM 51-1-8. FABRICATED AND INSTALLED FINGER DOUBLER IAW DC-8 SRM 51-1-8, 51-1-4 & 51-1-21. (CORROSION DAMAGE RECORDED IN EWA CORROSION PROGRAM).
Part: ANGLE — CORRODED (FUSELAGE) · airframe 88,287 hrs · 21,582 cycles
DURING A MAINTENANCE VISIT FOUND CORROSION DAMAGE TO ATTACHMENT ANGLE AT STA 1540 BL-R 40 AND WL-15, DAMAGE EXCEEDED LIMITS IAW DC-8 SRM. REMOVED DAMAGE, TREATED AREA IAW DC-8 SRM 51-1-8. FABRICATED AND INSTALLED NEW ATTACHMENT ANGLE IAW DC-8 SRM 51-1-21.
Part: ANGLE — CORRODED (FUSELAGE)
FOUND DURING D-CHECK, D PIT STATION1540 BULKHEAD FRAME UPPER ANGLE CORRODED. REMOVED CORROSION IAW DC-8 SRM 51-1-8. FABRICATED ANGLE IAW DC-8 SRM 51-1-5. TREATED, PRIMED AND INSTALLED IAW DC-8 SRM 51-1-8, 51-1-21. (M)
Part: SKIN — CORRODED (FUSELAGE) · airframe 88,288 hrs · 21,584 cycles
DURING A MAINTENANCE VISIT FOUND CORROSION DAMAGE ON BACK SIDE OF WING FILLET PANEL 161F AT STA 880-920, 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.
Part: SKIN — CORRODED (FUSELAGE) · airframe 88,288 hrs · 21,584 cycles
DURING A MAINTENANCE VISIT FOUND CORROSION DAMAGE TO THE WING FILLET PANEL 261C LT TOP FWD CORNER ATTACH ANGLE AT STA 960-990, DAMAGE EXCEEDED LIMITATIONS IAW DC-8 SRM. REMOVED DAMAGE, TREATED AREA IAW DC-8 SRM 5-1-8. FABRICATED AND INSTALLED REPAIR IAW DC-8 SRM 51-1-21 AND 51-1-4.
Part: SKIN — CORRODED (FUSELAGE) · airframe 88,288 hrs · 21,584 cycles
DURING A MAINTENANCE VISIT FOUND CORROSION DAMAGE TO THE WING FILLET PANEL 261E RUB STRIP AT STA 960-980 AND XCW 69, 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 AND 51-1-21.
Part: SKIN — CORRODED (FUSELAGE) · airframe 88,288 hrs · 21,584 cycles
DURING A MAINTENANCE VISIT FOUND CORROSION DAMAGE TO THE ATTACH ANGLE IN FRONT OF WING LENS ON WING FILLET PANEL 261A AT STA 640-660 AND XCW 69, DAMAGE EXCEEDED LIMITATIONS IAW DC-8 SRM. REMOVED DAMAGE, TREATED AREA IAW DC-8 SRM 51-1-8. RECEIVED REPAIR AND INSTALLED IAW DC-8 SRM 53-2-0 AND 51-1-4.
Part: SKIN — CRACKED (EMERGENCY EXIT)
FOUND DURING D-CHECK, LEFT AFT OVERWING EXIT DOOR FOUND CRACK IN DOOR UNDER BOTTOM PLATE THAT WAS REMOVED FOR CORROSION. STOP DRILLED CRACK IAW DC-8 SRM 52-20-0. FABRICATED DOUBLER. TREATED, PRIMED AND INSTALLED IAW DC-8 SRM 51-1-8, 51-1-21D. (M)
Part: DOUBLER — CORRODED (FUSELAGE) · airframe 88,288 hrs · 21,584 cycles
DURING A MAINTENANCE VISIT FOUND CORROSION DAMAGE AROUND SCREW HOLES INSIDE AND OUTSIDE OF THE RT WING FILLET PANEL 262B, 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 51-1-21.
Part: FLOOR PANEL — CORRODED (FUSELAGE) · airframe 88,287 hrs · 21,582 cycles
DURING A MAINTENANCE VISIT FOUND CORROSION DAMAGE TO FLOOR PANEL BETWEEN STA 260 TO STA 280 AND BETWEEN LONGERONS 32 LEFT TO 32 RIGHT, DAMAGE EXCEEDED LIMITATIONS IAW DC-8 SRM. REMOVED DAMAGE, TREATED AREA IAW DC-8 SRM 51-1-8. FABRICATED NEW FLOOR PANEL AND INSTALLED IAW DC-8 SRM 53-2-3.
Part: FLOOR PANEL — CORRODED (FUSELAGE) · airframe 88,287 hrs · 21,582 cycles
DURING A MAINTENANCE VISIT FOUND CORROSION DAMAGE TO FLOOR PANEL BETWEEN STA 260 TO STA 280 AND BETWEEN LONGERONS 32 LEFT TO 32 RIGHT, DAMAGE EXCEEDED LIMITATIONS IAW DC-8 SRM. REMOVED DAMAGE, TREATED AREA IAW DC-8 SRM 51-1-8. FABRICATED NEW FLOOR PANEL AND INSTALLED IAW DC-8 SRM 53-2-3.
Part: FLOOR PANEL — CORRODED (FUSELAGE) · airframe 88,287 hrs · 21,582 cycles
DURING A MAINTENANCE VISIT FOUND CORROSION DAMAGE TO FLOOR PANEL BETWEEN STA 340 TO STA 360 AND BETWEEN LONGERONS 32 LEFT TO 32 RIGHT, DAMAGE EXCEEDED LIMITATIONS IAW DC-8 SRM. REMOVED DAMAGE, TREATED AREA IAW DC-8 SRM 51-1-8. FABRICATED NEW FLOOR PANEL.
Part: FLOOR PANEL — CORRODED (FUSELAGE) · airframe 88,287 hrs · 21,582 cycles
DURING A MAINTENANCE VISIT FOUND CORROSION DAMAGE TO FLOOR PANEL BETWEEN STA 55 TO STA 62 AND BL 48L, DAMAGE EXCEEDED LIMITATIONS IAW DC-8 SRM. REMOVED DAMAGE, TREATED AREA IAW DC-8 SRM 51-1-8. FABRICATED NEW FLOOR PANEL AND INSTALLED IAW DC-8 SRM 51-1-9.
Part: DOOR FRAME — CORRODED (FUSELAGE) · airframe 88,287 hrs · 21,582 cycles
DURING A MAINTENANCE VISIT FOUND CORROSION DAMAGE TO LOWER AFT CARGO DOOR JAMB (FRAME) AT STA 1540 AND LONGERON 33 RIGHT, DAMAGE EXCEEDED LIMITS IAW DC-8 SRM. REMOVED DAMAGE, TREATED AREA IAW DC-8 SRM 51-1-8. FABRICATED AND INSTALLED REPAIR SPLICE IAW DC-8 SRM 51-1-21.
Part: ANGLE — CORRODED (RT MLG WW) · airframe 88,287 hrs · 21,582 cycles
DURING MAINTENANCE VISIT FOUND CORROSION DAMAGE TO WING PRESSURE PANEL ATTACH ANGLE FROM STA 960 TO STA 980 AT RIGHT BUTT LINE8.0. DAMAGE EXCEEDED LIMITATIONS IAW DC-8 SRM. REMOVED DAMAGE, TREATED AREA IAW DC-8 SRM 51-1-8. REMOVED AND REPLACED ATTACH ANGLE AND STRINGER FITTING IAW DC-8 SRM 51-1-20, 51-1-21 AND 51-1-8. (CORROSION DAMAGE RECORDED IN EWA CORROSION PROGRAM).
Part: FRAME — CORRODED (FUSELAGE) · airframe 88,287 hrs · 21,582 cycles
DURING MAINTENANCE VISIT FOUND CORROSION DAMAGE TO UPPER CARGO COMPARTMENT LIGHT AT STA 1200 BETWEEN LONGERON NR 9 & 10 LT. DAMAGE EXCEEDED LIMITATIONS IAW DC-8 SRM. REMOVED DAMAGE,TREATED AREA IAW DC-8 SRM 51-1-8. FABRICATED DOUBLERS AND INSTALLED IAW DC-8 SRM 51-1-8, 51-1-21 & 51-1-4. (CORROSION DAMAGE RECORDED IN EWA CORROSION PROGRAM).
Part: CHANNEL — CORRODED (FUSELAGE) · airframe 88,287 hrs · 21,582 cycles
DURING A MAINTENANCE VISIT FOUND CORROSION DAMAGE TO U-CHANNEL AT STA 98 AND LONGERON 36, DAMAGE EXCEEDED LIMITATIONS IAW DC-8 SRM. REMOVED DAMAGE, TREATED AREA IAW DC-8 SRM 51-1-8. FABRICATED NEW U-CHANNEL AND INSTALLED IAW DC-8 SRM 51-1-4.
Part: FRAME — CORRODED (FUSELAGE)
FOUND DURING D-CHECK, UPPER CARGO COMPT LIGHT SURFACE CORROSION STATION 1200 LONGERON 9-10 LEFT. REMOVED CORROSION IAW DC-8 SRM 51-1-8. FABRICATED DOUBLERS. TREATED, PRIMED AND INSTALLED IAW DC-8 SRM 51-1-8, 51-1-21, 53-2-0 AND 51-1-4. (M)
Part: DOOR FRAME — CORRODED (BULKHEAD)
FOUND DURING D-CHECK, STATION 1540 BULKHEAD DOOR FRAME HAS CORROSION BLISTER 30 INCHES ABOVE L33R. REMOVED CORROSION IAW DC-8 SRM 51-1-8. FABRICATED DOUBLER IAW DC-8 SRM 51-1-4. TREATED, PRIMED AND INSTALLED IAW DC-8 SRM 51-1-8, 51-1-21. (M)
Part: SKIN — CORRODED (LT WING) · airframe 88,288 hrs · 21,584 cycles
DURING A MAINTENANCE VISIT FOUND CORROSION DAMAGE TO THE LT INBOARD FLAP FAIRING PLATE AT XRS 172, 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, 51-1-4, 51-3-0 AND 51-1-21.
Part: PRESSURE PANEL — CORRODED (FUSELAGE) · airframe 88,287 hrs · 21,582 cycles
DURING A MAINTENANCE VISIT FOUND CORROSION DAMAGE TO PRESSURE PANEL BETWEEN STA 880 TO STA 900 AND BL 69L, 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.
Part: ANGLE — CORRODED (FUSELAGE) · airframe 88,287 hrs · 21,582 cycles
DURING A MAINTENANCE VISIT FOUND CORROSION DAMAGE TO ATTACHMENT ANGLE AT STA 680 AND BETWEEN LONGERONS 22 RIGHT TO 23 RIGHT, DAMAGE EXCEEDED LIMITATIONS IAW DC-8 SRM. REMOVED DAMAGE, TREATED AREA IAW DC-8 SRM 51-1-8. FABRICATED AND INSTALLED NEW ATTACHMENT ANGLE IAW DC-8 SRM 51-1-4.
Part: LONGERON — CORRODED (FUSELAGE) · airframe 88,288 hrs · 21,584 cycles
DURING A MAINTENANCE VISIT FOUND CORROSION DAMAGE TO THE LONGERON END FITTINGS AT STA 70 L31R, 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.
Part: LONGERON — CORRODED (FUSELAGE) · airframe 88,287 hrs · 21,582 cycles
DURING A MAINTENANCE VISIT FOUND CORROSION DAMAGE TO LONGERON 30 RIGHT AT STA 25, DAMAGE EXCEEDED LIMITS IAW DC-8 SRM. REMOVED DAMAGE, TREATED AREA IAW DC-8 SRM 51-1-8. FABRICATED AND INSTALLED NEW LONGERON IAW DC-8 SRM 53-2-0.
Part: LONGERON — CORRODED (FUSELAGE)
FOUND DURING D-CHECK, UPPER FUSELAGE CABIN, CORROSION AT L30R STATION 25. REMOVED CORROSION, REMOVED LONGERON IAW DC-8 SRM 51-1-8, 53-2-0. FABRICATED LONGERON. TREATED, PRIMED AND INSTALLED IAW DC-8 SRM 53-2-2, 51-1-8, 51-1-21. (M)
Part: STRAP — CORRODED (FUSELAGE) · airframe 88,288 hrs · 21,584 cycles
DURING A MAINTENANCE VISIT FOUND CORROSION DAMAGE TO THE FLOOR BEAMS METAL STRIP FOR GILL LINER AT STA 1390, 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: FRAME — CORRODED (FUSELAGE) · airframe 88,287 hrs · 21,582 cycles
DURING A MAINTENANCE VISIT FOUND CORROSION DAMAGE TO FRAME STA 781 AND LONGERON 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.
Part: FRAME — CRACKED (HORZONTAL STAB) · airframe 88,287 hrs · 21,582 cycles
DURING A MAINTENANCE VISIT FOUND LEFT HORIZONTAL STABILIZER LEADING EDGE FRAME CRACKED AT XFS 53.75. 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.
Part: SPAR — CRACKED (HORIZ STAB)
FOUND DURING D-CHECK, LEFT INBOARD HORIZ STAB L/E CRACK AT FRAME XFS 53.75 UNDER SKIN EXTENDED PAST STOP DRILL. STOP DRILLED CRACK IAW DC-8 SRM 55-2-0. FABRICATED ANGLE REPAIR. TREATED, PRIMED AND INSTALLED IAW DC-8 SRM 51-1-8, 51-1-4 AND 51-1-20D.(M)
Part: FITTING — CORRODED (FUSELAGE) · airframe 88,287 hrs · 21,582 cycles
DURING A MAINTENANCE VISIT FOUND CORROSION DAMAGE TO FITTING AT STA 400 BETWEEN LONGERON 22 LEFT TO 23 LEFT, DAMAGE EXCEEDED LIMITATIONS IAW DC-8 SRM. REMOVED DAMAGE, TREATED AREA IAW DC-8 SRM 51-1-8. RETURN TO SERVICE, LIMITS ACCEPTABLE IAW FAA DER APPROVED ENGINEERING SKETCH EO 99-186.
Part: FAIRING — CRACKED (FUSELAGE)
FOUND DURING D-CHECK, D PIT AFT DOOR FRAME FAIRING CRACKED. REMOVED FAIRING. FABRICATED FAIRING IAW DC-8 SRM 51-1-4. TREATED, PRIMED, AND INSTALLED IAW DC-8 SRM 51-1-8, 51-3-0. (M)
Part: FAIRING — CRACKED (FUSELAGE)
FOUND DURING D-CHECK, D PIT FORWARD DOOR FRAME, FAIRING CRACKED. REMOVED FAIRING. FABRICATED FAIRING IAW DC-8 SRM 51-1-4. TREATED, PRIMED AND INSTALLED IAW DC-8 SRM 51-1-8, 51-3-0. (M)
Part: SHEAR TIE — CORRODED (FUSELAGE) · airframe 88,287 hrs · 21,582 cycles
DURING A MAINTENANCE VISIT FOUND CORROSION DAMAGE TO SHEAR TIE AT STA 60 AND LONGERON 6 LEFT, DAMAGE EXCEEDED LIMITATIONS IAW DC-8 SRM. REMOVED DAMAGE, TREATED AREA IAW DC-8 SRM 51-1-8. FABRICATED AND INSTALLED NEW FRAME TIE IAW DC-8 SRM 53-2-2.
Part: BRACKET — CORRODED (FUSELAGE) · airframe 88,287 hrs · 21,582 cycles
DURING A MAINTENANCE VISIT FOUND CORROSION DAMAGE TO 2 EACH BRACKETS AT STA -131 AND LONGERON 23 LEFT, 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 88,287 hrs · 21,582 cycles
DURING A MAINTENANCE VISIT FOUND CORROSION DAMAGE TO FITTING AT STA 900 AND LONGERON 24 RIGHT, DAMAGE EXCEEDED LIMITATIONS IAW DC-8 SRM. REMOVED DAMAGE, TREATED AREA IAW DC-8 SRM 51-1-8. RECEIVED NEW FITTING AND INSTALLED IAW DC-8 SRM 51-1-20D.
Part: FITTING — CORRODED (FUSELAGE) · airframe 88,287 hrs · 21,582 cycles
DURING A MAINTENANCE VISIT FOUND CORROSION DAMAGE TO FITTING AT STA 879 AND LONGERON 24 RIGHT, DAMAGE EXCEEDED LIMITATIONS IAW DC-8 SRM. REMOVED DAMAGE, TREATED AREA IAW DC-8 SRM 51-1-8. RECEIVED NEW FITTING AND INSTALLED IAW DC-8 SRM 51-1-20D.
Part: FLANGE — GOUGED (WING)
FOUND DURING D-CHECK, FLANGE ON AFT SIDE OF OUTBOARD W/W AT WING AT WING STATION XRS 90.0 GOUGE APPROX .25 INCH IN DIAMETER. (M)
1998
Part: STRIKER — OUT OF ADJUST (RT MLG)
RIGHT MAIN GEAR DOOR WARNING LIGHT ALTERNATE AND RED DOORS NOT LATCHED LIGHT ON WITH GEAR UP CYCLED GEAR NO HELP. ADJ ALTERNATE LIGHT STRIKER PLATE RIGHT SIDE. ADJ ADJUSTABLE LINK TO MAINTAIN MIN OF 0.010 W/GEAR DOWN AND DOORS OPEN BETWEEN LINK OPS CK OK.
1997
Part: UPLATCH MECH — OUT OF ADJUST (RT MLG DOOR)
DOORS NOT LATCHED LIGHT ON AFTER GEAR RETRACTION. UPLATCH CHECK FAILED. RECYCLED GEAR AND DOORS NOT LATCHED LIGHT AND RIGHT ALTERNATE DOOR LIGHT ON. GEAR UPLATCH CHECK FAILED, AIRSPEED AT 180 KIAS. INCREASED SPEED TO 210 KIAS AND PERFORMED A UPLATCH CHECK AND ALL LIGHT EXTINGUISHED. UNUSUALLY LOUD NOISES WHEN GEAR WAS BEING RETRACTED. CYCLED GEAR ON APPROACH, DOORS NOT LATCHED LIGHT ON. RIGHT ACT DOOR LIGHT CAME ON IMMEDIATE WHEN GEAR LEVER IS MOVED AND IT EXTINGUISHED EARLIER THAN THE LEFT DOOR LIGHT. ADJUSTED RT MAIN GEAR DOOR UP LATCH MECHANISM IAW MM 32-31-4, CHECKS NORMAL AT THIS TIME.