N721CX
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
MAIN DECK CARGO COMPARTMENT SEAT TRACK HAS CORROSION AT SPLICE STA 590, LBL 48. 32-155.
LEFT WING AILERON CONTROL TAB IS DENTED AND HAS DELAMINATION ON UPPER AND LOWER SURFACES.
RIGHT WING OTBD L/E INBD SECTION LOWER SKIN HAS INTER GRANULAR CORROSION AROUND FASTENERS AT XFS 685.
COCKPIT SUBFLOOR FINGER DOUBLER AT LT SIDE OF CUSP BS 148 IS LIFTED UP DUE TO POSSIBLE CORROSION UNDERNEATH AND FASTENER IS LOOSE.
RT WING OTBD FLAP NR 4 FLAP VANE INBD UPPER SURFACE DENTED WITH DELAMINATION.
COCKPIT SUBFLOOR FINGER DOUBLER AT LT SIDE OF CUSP WEB BS 148 IS LIFTED UP DUE TO POSSIBLE CORROSION UNDERNEATH AND FASTENER IS LOOSE.
COCKPIT SUBFLOOR RT SIDE CUSP AREA BS 148, FINGER DOUBLER HAS MANY BROKEN OFF FASTENERS.
LEFT WING UPPER SKIN HAS CORROSION AROUND FASTENERS BETWEEN STR 10 AND FWD SPAR AND XRS 50-107 28-075.
MAIN DECK CARGO TRACK HAS CORROSION AT SPLICE BS 590, LBL 24.
LEFT WING CENTER L/E UPPER SKIN HAS INTERGRANULAR CORROSION AROUND FASTENER AT XFS 261.500 28-129, REF VT NRC 7000900968.
RT WING OTBD FLAP, NR 4 VANE INBD UPPER SURFACE DENTED WITH DELAMINATION.
MAIN DECK CARGO COMPARTMENT SEAT TRACK HAS CORROSION AT SPLICE BS 590, RBL 60. 32-158.
MAIN DECK CARGO COMPARTMENT SEAT TRACK HAS CORROSION AT SPLICE 995, LBL 45.32-152.
CRACK FOUND AT RT OTBD SIDE OF AFT PRESSURE BULKHEAD WEB BETWEEN LONGHORN 10 AND 11 APPROXIMATELY 2" IN LENGTH . VERIFIED BY FPI AND HFEC INSPECTIONS.
CRACK FOUND AT LT INBD SIDE OF AFT PRESSURE BULKHEAD BETWEEN LONGHORN 10 AND 11 APPROXIMATELY 2.25" IN LENGTH. VERIFIED BY FPI AND HFEDC INSPECTION.
LEFT WING AILERON TRIM TAB IS DENTED ON UPPER AND LOWER SURFACES.
LEFT AFT PASSENGER SLIDE GIRT BAR STORAGE RETAINER BROKEN. ATTACHED GIRT BAR IAW AMM 20-10-0; ACFT WAS GROUNDED.
FLIGHT CONTROLS FELT ABNORMALLY STIFF AILERONS, DURING APPROACH. TROUBLESHOT AILERON SYS IAW MM 27-10-0. FOUND RT AILERON INBD HINGE BEARING FAILED. R & R BEARING IAW MM 27-10-0. FOUND RT AILERON POWER CYLINDER HOT TO THE TOUCH AFTER OPERATING AILERONS. R & R RT AILERON POWER CONTROL CYLINDER AND VALVE IAW MM 27-11-6. SYS OPS CHECKS GOOD. PERFORMED INSP AND OPS CHECK OF RT AILERON TORQUE TUBE AND OVERRIDE MECHANISM IAW MM 27-11-5. NO DEFECTS NOTED. PERFORMED INSP AND CHECK OF AILERON CONTROL CABLES AND PULLEYS IAW MM 27-10-0. NO DEFECTS NOTED.
DURING FLIGHT CONTROL CHECK, AILERON DID NOT RETURN TO CENTER POSITION AND FELT STIFF ON RT MOVEMENT. RETURNED TO BLOCKS. TROUBLESHOT AILERON SYS FOUND TWO PULLEYS DRAGGING ON RT AILERON CABLE AND FAIRLEAD CONTACTING PULLEY. CLEANED AND LUBED PULLEYS AND REPOSITIONED FAIRLEAD. SYS OPS CHECKED GOOD IAW MM 27-10-0.
COMPLIED WITH ATI BIRD STRIKE INSPECTION JOB CARD 13.01-4. DAMAGE WAS FOUND TO NR 13 AND 14 FAN BLADES. R & R 44C1 FAN BLADES IAW AMM 72-21-00. OPS CHECKS GOOD IAW ENGINE RUN HANDBOOK 70.01.
ON POST FLIGHT INSPECTION, FOUND EVIDENCE OF BIRD STRIKE TO THE NR 3 ENGINE. DAMAGE WAS FOUND TO THE NR 12 AND NR 13 FAN BLADES. C/A TO FOLLOW.
PAX AREA EMERGENCY FLASHLIGHT BATTERY DEAD. R & R EMERGENCY FLASHLIGHT BATTERY IAW MM 25-60-0. OPS CHECKS GOOD.
R2 DOOR EVACUATION SLIDE BOTTLE PRESSURE BELOW MINIMUM. R & R R2 DOOR EVACUATION SLIDE ASSY IAW MM 25-60-1. NEXT O/H DUE DATE IS 10/2015. EMERGENCY EQUIPMENT STICKER ATTACHED IAW GMM CHAPTER 3.
DURING AN INSPECTION OF THE RT WING L/E UPPER SKIN CORROSION WAS FOUND AT XW 761.695. REMOVED CORROSION IAW SRM 51-1-8. FOUND OUT OF LIMITS IAW SRM 57-2-0. CUT OUT AFFECTED AREA IAW DWG ED-5526. PERFORMED NDT INSP IAW NDT SPM PART 06-10-01-001. NO DISCREPANCY FOUND. FABRICATED REPAIRING DOUBLER AND FILLER IAW DWG ED-5526 AND DPS 4.710 REV "L". CLEANED, TREATED AND PRIMED AREA AND REPAIRING PARTS IAW SRM 51-1-8B. APPLIED SEALANT TO FAYING SURFACES IAW SRM 51-1-11. INSTALLED REPAIRED PARTS IAW DWG ED-5526 AND SRM 51-1-21, SRM 51-1-20D AND SRM 51-3-1.
DURING AN INSPECTION OF THE RT WING L/E UPPER SKIN CORROSION WAS FOUND AT XFS 791.500. REMOVED CORROSION IAW SRM 51-1-8. FOUND OUT OF LIMITS IAW SRM 57-2-0. CUT OUT AFFECTED AREA IAW SRM 57-2-1, FIG 38, TR 57-85. PERFORMED NDT INSPECTION IAW NDT SPM PART 06-10-01-001. NO DISCREPANCY FOUND. FABRICATED EXTERNAL DOUBLER AND FILLER IAW SRM 57-2-1, FIG 38 TR 57-85, 57-3-2 FIG 7 ITEM "F". CLEANED, TREATED AND PRIMED AREA AND REPAIRING PARTS IAW SRM 51-1-8B. INSTALLED REPAIR PARTS IAW SRM 57-2-1 FIG 8, SRM 51-1-21, SRM 51-1-20D AND SRM 51-3-1.
DURING INSPECTION OF THE RT WING UPPER SKIN, CORROSION WAS FOUND AT XRS 727.000 STRINGER 1. PERFORMED MAJOR REPAIR IAW FORM 8110-3, DATED 08-27-12, DWG ED-5524, DATED 08-23-12.
DURING AN INSPECTION OF THE RT WING UPPER SKIN CORROSION WAS FOUND AT XRS 763.000 BETWEEN S-3 AND S-4. REMOVED CORROSION IAW SRM 51-1-8. FOUND OUT OF LIMITS IAW SRM 57-2-0. PERFORMED NDT INSPECTION IAW NDT SPM PART 06-10-01-0001. NO DISCREPANCY FOUND. PERFORMED FLAP PENNING IAW DPS 4.999 REV "W". FABRICATED REPAIR DOUBLER IAW DWG ED-5525, SRM 57-3-2. FIG 19 ITEM "A" AND DPS 4.710 REV. "L". CLEANED, TREATED AND PRIMED AREA AND REPAIRING PARTS IAW SRM 51-1-8B. APPLIED SEALANT TO FAYING SURFACES IAW SRM 51-1-11. INSTALLED REPAIRING PARTS IAW DWG ED-5525, SRM 51-1-20D AND SRM 51-3-1.
ON ENGINE START, A HOT MUSTY ODOR WAS PRESENT IN THE COCKPIT. AFTER ALL FOUR ENGINES WERE STARTED, THE ODOR EVENTUALLY WENT AWAY. REMOVED, CLEANED AND REINSTALLED AIR DUCTS IAW MM 20-11-0. PERFORMED ENGINES RUN UP AT GROUND IDLE. OPS AND LEAK CHECKED GOOD IAW 70-01.
RIGHT AIR CONDITIONING PACK INOPERATIVE. FOUND RT AIR CONDITIONING PACK FLOW CONTROL VALVE WILL NOT OPEN. R & R RT AIR CONDITIONING PACK FLOW CONTROL VALVE IAW MM 21-55-5. OPS AND LEAK CHECK GOOD.
EMERGENCY FLASHLIGHT IN PASSENGER COMPARTMENT, INBD POSITION HAS WEAK BATTERY. R & R RECHARGEABLE EMERGENCY BATTERY IAW MM 33-50-1. OPS CHECKED GOOD.
DURING ROUTINE C-CHECK INSP FOUND AFT FUSELAGE RT UPPER PART ANGLE CORRODED AT STA 1660.000. REMOVED CORROSION. FOUND OUT OF LIMITS. REMOVED DAMAGED ANGLE. FABRICATED NEW ANGLE, SPLICERS, FILLERS, AND TAPERED SHIMS. PERFORMED HEAT TREATMENT. CLEANED, TREATED, PRIMED AREA AND REPAIR PARTS. INSTALLED REPAIR PARTS IAW SRM CHAP 53-2-5 FIG 16A SHEETS 1-2, SRM 51-1-8, SRM 53-2-0, DPS 4.710 REV "L", SRM 51-1-4, SRM 51-1-6, SRM 51-1-8B, SRM 51-1-20D, AND SRM 51-3-1.
DURING ROUTINE C-CHECK INSP, FOUND RT WING OTBD INNER L/E FWD UPPER SKIN CORRODED AT STA XFS 710.000. REMOVED CORROSION. FOUND OUT OF LIMITS. REMOVED DAMAGED AREA. PERFORMED NDT INSP. NO DISCREPANCY FOUND. FABRICATED REPAIR DOUBLER AND FILLER. CLEANED, TREATED, PRIMED AREA AND REPAIR PARTS. INSTALLED REPAIR PARTS IAW FAA FORM 8110-3, DATED 04/29/11, SMN DWG ED-5363 DATED 04/07/11, SRM 51-1-8, SRM 57-2-0, NDT SPM PART 06-10-01-001, SRM 57-3-2 FIG 6, SHEET 1 ITEM "A", DPS 4.710 REV "L", SRM 51-1-4, DPS 3.69-4 REV "AP", SRM 51-1-8B, SRM 51-1-20D, AND SRM 51-3-1.
DURING ROUTINE C-CHECK INSP, FOUND AFT ACCESSORY COMPARTMENT FLOORBEAM UPPER FLANGE CORRODED AT STA 1420.000 RBL 52. REMOVED CORROSION. FOUND OUT OF LIMITS. REMOVED DAMAGED AREA. FABRICATED ANGLE AND FILLER. CLEANED, TREATED, PRIMED AREA AND REPAIR PARTS. INSTALLED REPAIR PARTS IAW SRM CHAP 51-2-1, FIG 1, TR 51-130, SRM 51-1-8, SRM 53-2-0, SRM 51-2-1 FIG 1, TR 51-130, SRM 51-2-1 FIG 1, TR 51-130, SRM 53-7-2 FIG 9, ITEM "A", SRM 51-2-0, FIG 50, SHEET 72E, DPS 4.710 REV "L", SRM 51-1-8B, SRM 51-1-20D, AND SRM 51-3-1.
DURING ROUTINE C-CHECK INSP, FOUND AFT ACCESSORY COMPARTMENT FRAME CORRODED AT STA 1440.000, LONGERON 36. REMOVED CORROSION. FOUND OUT OF LIMITS. REMOVED DAMAGED AREA. FABRICATED FRAME SEGMENT AND ANGLES. PERFORMED HEAT TREATMENT. CLEANED, TREATED, PRIMED AREA AND REPAIR PARTS. INSTALLED REPAIR PARTS IAW SRM CHAP 53-2-0, FIG 2 SHEET 1 TR 53-110 SHEETS 7/8 TR 53-125, SRM 51-1-8, SRM 53-2-0, SRM 53-4-1 FIG 52 SHEET 10 ITEM "C", SRM 51-1-4, DPS 3.69-4, REV "AP", SRM 51-1-1, DPS 7.00-1 REV "BL", SRM 51-1-8B, SRM 51-1-20D, AND SRM 51-3-1.
DURING ROUTINE C-CHECK INSP FOUND AFT ACCESSORY COMPARTMENT LONGERON 24 RT CORRODED AT STATION 1380.000 - 1400.000. REMOVED CORROSION. FOUND OUT OF LIMITS. REMOVED DAMAGED AREA. FABRICATED LANGERON AND SPLICERS. CLEANED, TREATED, PRIMED AREA AND REPAIR PARTS. INSTALLED REPAIR PARTS IAW SRM CHAP 53-2-2 FIG 10 SHEET 3 TR 53-193 SHEET 4, SRM 51-1-8, DC8 SRM 53-2-0, DC8 SRM 53-2-0 FIGURE 4, SRM 53-2-2 TR 53-193, SRM 53-2-2, FIG 4, SRM 53-4-1 FIG 44B, SHEET 2 ITEM "D", SRM 51-2-0, FIG 50 SHEET 51, SRM 51-2-0 FIGURE 51 SHEET 62, DPS 4.710 REV "L",. SRM 51-1-8B, SRM 53-2-2 FIG 10 SHEET 3, SRM 51-1-20D, AND SRM 51-3-1.
DURING ROUTINE C-CHECK INSP FOUND AFT ACCESSORY COMPARTMENT LONGERON 23 RT CORRODED AT STA 1380.000. REMOVED CORROSION. FOUND OUT OF LIMITS. REMOVED DAMAGED AREA. FABRICATED NEW LONGERON SEGMENT AND SPLICERS. CLEANED, TREATED, PRIMED AREA AND REPAIR PARTS. INSTALLED REPAIR PARTS IAW SRM 53-2-2, FIG 10, SHEET 3, TR 53-193, SHEET 4, SRM 51-1-8, SRM 53-2-0, SRM 53-2-0 FIGURE 4, SRM 53-2-2 TR 53-193, SRM 53-2-2 FIGURE 4, SRM 53-4-1 FIG 44B SHEET 2 ITEM "D", SRM 51-2-0, FIG 50 SHEET 51, SRM 51-2-0, FIG 51 SHEET 62, DPS 4.710 REV "L", SRM 51-1-8B, SRM 51-1-20D, AND SRM 51-3-1.
DURING ROUTINE C-CHECK INSP FOUND AFT ACCESSORY COMPARTMENT AFT BATHTUB FITTING CRACKED AT STA 1530.000 LONGERON 34 RT. REMOVED CRACKED FITTING. INSTALLED NEW FITTING IAW SRM 51-1-20D, SRM 51-1-21 AND SRM 51-3-1.
DURING ROUTINE C-CHECK INSP, FOUND AFT ACCESSORY COMPARTMENT AFT BATHTUB FITTING CRACKED AT STA 1530.000 LONGERON 34 LT. REMOVED CRACKED FITTING. INSTALLED NEW FITTING IAW SRM 51-1-20D, SRM 51-1-21 AND SRM 51-3-1.
DURING ROUTINE C-CHECK INSP FOUND AFT FUSELAGE RT UPPER PART ANGLE CORRODED AT STA 1633.822. REMOVED CORROSION. FOUND OUT OF LIMITS. REMOVED DAMAGED AREA. FABRICATED ANGLE, SPLICES, FILLERS AND TAPERED SHIMS. PERFORMED HEAT TREATMENT. CLEANED, TREATED, PRIMED AREA AND REPAIR PARTS. INSTALLED REPAIR PARTS IAW SRM CHAP 53-2-5, FIG 16A SHEETS 1-2, SRM 51-1-8, SRM 53-2-0, PS 4.710 REV "L", SRM 51-1-4, SRM 51-1-6, SRM 51-1-8B, SRM 51-1-20D, AND SRM 51-3-1.
DURING ROUTINE C-CHECK INSP FOUND MAIN CARGO COMPARTMENT RT FITTING AFT LOWER PART CRACKED AT STA 680.000 LONGERON 11 RT. REMOVED CRACKED FITTING. INSTALLED NEW FITTING IAW SRM 51-1-20D AND SRM 51-3-1.
DURING ROUTINE C-CHECK INSP FOUND LT ELEVATOR LOWER SKIN OIL CANNING AT STATION 246.000, XH285.000. REMOVED FASTENERS AS NEEDED TO PERFORM REPAIR. REMOVED DAMAGED SKIN. FABRICATED NEW SKIN AND FINGER DOUBLERS. BONDED PARTS AS NEEDED. CLEANED, TREATED, PRIMED AREA AND REPAIR PARTS. PERFORMED LT ELEVATOR BALANCE FOUND WITHIN LIMITS MOMENT 1443.36 IN-LBS. INSTALLED NEW FASTENERS AND REPAIR PARTS IAW SRM CHAP 55-4-1, FIG 1 SHEET 1-2 ITEMS "E" & "F", DPS 4.710 REV "L", SRM 51-1-21, SRM 55-1-0 PAGE 1, DC8 SRM 51-1-9 TR 51-142, SRM 51-1-9A TR 51-141, DPS 1.950 REV "AR" R-1, SRM 51-1-8B, AND SRM 51-4-4, TR 51-116, PAGES 1-3.
DURING ROUTINE C-CHECK INSP FOUND "D" CARGO DOOR JAMB FITTING CORRODED AT STA 1280.000, LONGERON 34 REMOVED CORRODED FITTING. CLEANED, TREATED AND PRIMED AREA. INSTALLED NEW FITTING IAW SRM 51-1-20D, SRM 51-1-8B, SRM 51-1-20D AND SRM 51-3-1.
DURING ROUTINE C-CHECK INSP FOUND LT ELEVATOR LOWER SKIN OIL CANNING AT STA XAR 0.000 - XE 132.000. REMOVED FASTENERS AS NEEDED TO PERFORM REPAIR. REMOVED DAMAGED SKIN. FABRICATED NEW SKIN AND FINGER DOUBLERS. BONDED PARTS AS NEEDED. CLEANED, TREATED, PRIMED AREA AND REPAIR PARTS. PERFORMED LT ELEVATOR BALANCE FOUND WITHIN LIMITS MOMENT 1443.36 IN-LBS. INSTALLED NEW FASTENERS AND REPAIR PARTS IAW SRM CHAPTER 55-4-1, FIG 1 SHEET 1-2 ITEMS "E" & "F", DPS 4.710 REV "L", SRM 51-1-21, SRM 55-1-0 PAGE 1, SRM 51-1-9 TR 51-142, SRM 51-1-9A TR 51-141, DPS 1.950 REV "AR" R-1, SRM 51-1-8B, AND SRM 51-4-4 TR 51-116, PAGES 1-3.
DURING ROUTINE C CHECK INSP, FOUND LT OTBD FLAP UPPER SKIN WORN AT STA XF 169.000 - 213.000. REMOVED DAMAGED SKIN. FABRICATED NEW SKIN. CLEANED, TREATED, PRIMED AREA AND REPAIR PARTS. INSTALLED REPAIRED PARTS IAW SRM CHAP 57-7-1, FIG 4 ITEM "C", DPS 4.710 REV "L", SRM 51-1-21, SRM 57-1-0 PAGE 1, SRM 51-1-4, DPS 3.69-5 REV "U", SRM 51-1-8B.
DURING REOUTINE C-CHECK INSP FOUND LT INBD FLAP UPPER SKIN DENTED AT STA XW 104.000. REMOVED DAMAGED SKIN. FABRICATED NEW SKIN. CLEANED, TREATED, PRIMED AREA AND REPARED PARTS. INSTALLED REPAR PARTS IAW SRM CHAPTER 57-7-1, FIG 1 ITEM "D", SRM 51-1-21, SRM 57-1-0, PAGE 1, DPS 4.710 REV "L", SRM 51-1-4, DPS 3.69-5 REV "U", SRM 51-1-8B,
DURING ROUTINE C-CHECK, FOUND RT MLG WHEEL WELL TRAPEZOIDAL SUPPORT FITTING CRACKED AT STA 902.000. REMOVED FASTENERS AS NEEDED TO PERFORM REPAIR. REMOVED WING FUSELAGE FILLETS AND ATTACH PARTS TO GAIN ACCESS TO OTD SPLICE FITTING. PERFORMED STOP HOLE AT CRACKS END. PERFORMED NDT INSP. NO DISCREPANCY FOUND. REMOVED OTBD SPLICE FITTING AND BOLTS FROM AREA. PREPARED NEW OTBD SPLICE FITTING. FABRICATED TEMPLATE SHIM. CLEANED, TREATED, PRIMED AREA AND REPAIR PARTS. INSTALLED OTBD SPLICE FITTING AND SHIM. REMOVED INBD SPLICE FITTING AND BOLTS FROM AREA. PREPARED NEW INBD SPLICE FITTING . FABRICATED FILLERS. CLEANED, TREATED, PRIMED AREA AND REPAIR PARTS. INSTALLED REPAIR PARTS IAW S/B 53-061, REV 5, DWG 5616481, SB 53-061 REV 5, SRM 51-3-0, NDT SPM PART 06-10-01-001, SB 53-061 REV 5, AND SRM 51-1-8B.
DURING ROUTINE C-CHECK INSP FOUND RT MLG WHEEL WELL FITTING CRACKED AT STATION 879.000, LONGERON 24 RT. REMOVED CRACKED FRAME FITTING. FABRICATED SPLICERS, SHIMS AND DOUBLERS. CLEANED, TREATED, PRIMED AREA AND REPAIR PARTS. INSTALLED NEW FITTING AND REPAIR PARTS IAW SRM 51-1-20D, SRM 51-3-0, SRM 53-2-0, FIG 8, PAGE 53, SRM 53-2-0, FIGURE 8, SHEETS 1/3/6 PAGE 41/45-46/51-52 CONFIGURATION 501, DPS 4.710 REV "L", SRM 51-1-8B, SRM 51-9-0, AND SRM 51-3-1.
DURING ROUTINE C-CHECK, INSP FOUND LT MLG WHEEL WELL TRAPEZOIDAL SUPPORT FITTING WEB CORRODED AT STA 885.000. REMOVED CORROSION. FOUND OUT OF LIMITS. PERFORMED NDT INSP. NO DISCREPANCY FOUND. FABRICATED REPAIR DOUBLERS. CLEANED, TREATED, PRIMED AREA AND REPAIR PARTS. INSTALLED REPAIR PARTS IAW FAA FORM 8110-3 DATED 04/29/11, DWG ED-5362 DATED 04/06/11, SRM 51-1-8, SRM 53-2-0, NDT SPM PART 06-10-01-001, DWG ED-5362, DPS 4.710 REV "L", SRM 51-1-8B, DWG ED-5362, SRM 51-1-20D, AND SRM 51-3-1.
DURING ROUTINE C-CHECK INSP FOUND RT MLG WHEEL WELL FITTING CRACKED AT STATION 920, LONGERON 24 RT. REMOVED CRACKED FRAME FITTING. FABRICATED SPLICERS, SHIMS AND DOUBLERS. CLEANED, TREATED, PRIMED AREA AND REPAIR PARTS. INSTALLED NEW FITTING AND REPAIR PARTS IAW SRM 51-1-20D, SRM 51-3-0, SRM 53-2-0, FIG 8, PAGE 53, SRM 53-2-0, FIG 8 SHEETS 1/3/6 PAGE 41/45-46/51-52 CONFIGURATION 501, DPS 4.710 REV "L", SRM 51-1-8B, SRM 51-9-0, AND SRM 51-3-1.
DURING ROUTINE C-CHECK INSP FOUND LT WING OTBD L/E LOWER EXTERNAL SKIN CORRODED AROUND FASTENERS AT STA XFS 878.750. REMOVED CORROSION. FOUND OUT OF LIMITS. REMOVED FASTENERS AS NEEDED TO PERFORM REPAIR. REMOVED DAMAGED AREA. PERFORMED NDT INSP. NO DISCREPANCY FOUND. FABRICATED NEW SKIN, INTERNAL AND EXTERNAL DOUBLERS. CLEANED, TREATED, PRIMED AREA AND REPAIR PARTS. INSTALLED NEW FASTENERS AND REPAIR PARTS IAW, SMN DWG ED-5359 DATED 04/12/11, SRM 51-1-8, SRM 57-2-0, NDT SPM PART 06-10-01-001, SRM 57-3-2, FIG 7 ITEM "F", DPS 4.710 REV "L", SRM 51-1-4, DPS 3.69-4 REV "AP", SRM 51-1-8B, SRM 51-1-21, SRM 51-1-20D, AND SRM 51-3-1.
DURING ROUTINE C-CHECK INSP, FOUND NR 4 STUB WING L/E EXTERNAL SKIN CORRODED. REMOVED CORROSION. FOUND OUT OF LIMITS. REMOVED DAMAGED AREA. PERFORMED NDT INSPECTION. NO DISCREPANCY FOUND. FABRICATED NEW SKIN, REPAIR DOUBLER AND FILLER. CLEANED, TREATED, PRIMED AREA AND REPAIR PARTS. INSTALLED REPAIR PARTS IAW FAA FORM 8110-3, DATED 04/22/11, DWG ED-5356 DATED 04/06/11, SRM 51-1-8, SRM 57-2-0, NDT SPM PART 06-10-01-001, DWG ED-5356, DPS 4.710 REV "L", SRM 51-1-4, DPS 3.69-4 REV "AP", SRM 51-1-8B, SRM 51-1-21, SRM 51-1-20D, AND SRM 51-3-1.
DURING CRUISE NR 2 ENGINE OIL PRESSURE LIGHT CAME ON WITH GOOD QTY AND PRESSURE. THE CREW RETARDED THE THROTTLES TO IDLE, THE LIGHT REMAINED ON. THEY SHUTDOWN NR 2 ENGINE IAW ATI COM 3-15-07 AND LANDED IN WSAP WITHOUT FURTHER INCIDENT. MX DEFFERED THE OIL LOW PRESSURE INDICATING LIGHT IAW MEL 79-07-02. MX REPLACED LOW OIL PRESSURE SWICH. OPS CHECK GOOD IAW MM 79-32-2. ACFT WAS RETURNED TO SERVICE.
DURING CRUISE AT FL360, NR 1 ENGINE FLAMED OUT. THE CREW ACCOMPLISHED QRH FLAME OUT/IN FLIGHT START CHECKLIST. ENGINE WOULD NOT START, THE CREW LANDED WITHOUT FURTHER INCIDENT. MX REPLACED THE MAIN ENGINE CONTROLLER. OPS CHECK GOOD IAW ERH 70.01, MM 73-21-10 AND ERH 36.02. ACFT WAS RETURNED TO SERVICE.
DURING CRUISE, LOWER CARGO AFT FIRE WARNING CAME ON, THE CREW DISCHARGED BOTH BOTTLES. THEY LANDED, WITHOUT FURTHER INCIDENT. MAINTENANCE REPLACED LOWER CARGO SMOKE DETECTOR, DIVERTER VALVE AND BOTH FIRE EXTINGUISHER BOTTLES. OPERATIONAL CHECK GOOD IAW MM 26.05. AIRCRAFT WAS RETURNED TO SERVICE.
DURING ROUTINE C CHECK INSP FOUND LT ELEVATOR UPPER SKIN CRACKED AT STA XE 274.875. REMOVED FASTENERS AS NEEDED TO PERFORM REPAIR. REMOVED CRACKED SKIN. FABRICATED NEW SKIN AND FINGER DOUBLERS. BONDED PARTS AS NEEDED WITH HYSOL. CLEANED, TREATED, PRIMED AREA AND REPAIR PARTS. PERFORMED ELEVATOR BALANCE. FOUND WITHIN LIMITS. MOMENT 1476.4 IN-POUNDS. INSTALLED NEW FASTENERS AND REPAIR PARTS IAW SRM CHAPTER 55-4-1 FIGURE 1 SHEETS 1-2, SRM 55-1-0, SRM 51-1-21, SRM 55-4-1, SRM 51-1-9, SRM 51-1-9A, SRM 51-1-8B, AND SRM 51-4-4 PAGES 1-4, TR 51-116.
DURING ROUTINE C CHECK INSP FOUND RT OTBD FLAP OTBD HINGE SUPPORT FITTING CRACKED AT STA XF 339.7332. REMOVED CRACKED FITTING. CLEANED, TREATED, PRIMED AREA. INSTALLED NEW FITTING IAW SB 27-249 REV 1 DATED 07/15/90, DWG 5894377, SB 27-249, SRM 51-1-21, SRM 51-1-20D, SRM 51-3-0, SRM 51-1-8B, SB 27-249, SRM 51-1-21, SRM 51-1-20D, SRM 51-3-0, AND SRM 51-3-1.
DURING ROUTINE C CHECK INSP, FOUND RT HORIZONTAL STABILIZER OTBD L/E HAS DENTS AT STATION XFS 216.250 AND XFS 222.500. REMOVED FASTENERS AS NEEDED TO PERFORM REPAIR. REMOVED EXISTING REPAIR. REMOVED DAMAGED AREA. PERFORMED NDT INS. NO CRACKS OR CORROSION NOTED. FABRICATED DOUBLER AND FILLERS. CLEANED, TREATED, PRIMED AREA AND REPAIR PARTS. INSTALLED NEW FASTENERS AND REPAIR PARTS IAW FORM 8110-3 DATED 02-11-2010, DWG ED-5069 DATED 01-20-2010, SRM 51-1-8B, SRM 51-1-21, SRM 51-1-20D, NDT SPM PART 06-10-01.001, SRM 51-1-8B, SRM 51-1-14, AND SRM 51-3-1.
DURING ROUTINE C CHECK INSP FOUND LT OTBD FLAP T/E LOWER SKIN HAS SEVERAL DENTS AT STA XF 380.000-404.000. REMOVED FASTENERS AS NEEDED TO PERFORM REPAIR. REMOVED DAMAGED SKIN. FABRICATED NEW SKIN, INTERNAL AND EXTERNAL DOUBLERS. BONDED PARTS AS NEEDED WITH HYSOL. CLEANED, TREATED, PRIMED AREA AND REPAIR PARTS. INSTALLED NEW FASTENERS AND REPAIR PARTS IAW SRM CHAPTER 57-7-1 FIGURE 4 TR 57-94, SRM 51-1-21, SRM 57-1-0, SRM 51-1-8B, SRM 57-7-1 FIGURE 4 TR 57-94 ITEMS "U" & "Q", DPS 4.710 REV "L", DC8 SRM 51-1-9 TR 51-142, SRM 51-1-9A TR 51-141, AND DPS 1.950 REV "AR" R-1.
DURING ROUTINE C CHECK INSP FOUND LT OTBD FLAP UPPER SKIN WORN AT STA XF 211.000. REMOVED FASTENERS AS NEEDED TO PERFORM REPAIR. REMOVED DAMAGED SKIN. FABRICATED NEW SKIN, INTERNAL AND EXTERNAL DOUBLERS. BONDED PARTS AS NEEDED WITH HYSOL. CLEANED, TREATED, PRIMED AREA AND REPAIR PARTS. INSTALLED NEW FASTENERS AND REPAIR PARTS IAW SRM CHAPTER 57-7-1 FIGURE 4 TR 57-94, DC8 SRM 51-1-21, SRM 57-1-0, SRM 51-1-8B, SRM 57-7-1 FIGURE 4 TR 57-94 ITEMS "U" & "Q", DPS 4.710 REV "L", SRM 51-1-9 TR 51-142, SRM 51-1-9A TR 51-141, AND DPS 1.950 REV "AR" R-1.
DURING ROUTINE C CHECK INSP FOUND LT INBD AILERON LOWER SKIN CRACKED AT STA XA 502.000. REMOVED FASTENERS AS NEEDED TO PERFORM REPAIR. REMOVED CRACKED SKIN. FABRICATED NEW SKIN. CLEANED, TREATED, PRIMED AREA AND REPAIR PARTS. PERFORMED LT INBD AILERON BALANCE. FOUND WITHIN LIMITS MOMENT: 3325.0 IN-POUNDS. INSTALLED NEW FASTENERS AND REPAIR PARTS IAW DWG 5705334, SRM 57-1-0, SRM 51-1-21 SRM 51-1-8B, DWG 5705334, DPS 4.710 REV "L", SRM 57-8-1 FIGURE1 ITEM "C", AND SRM 51-4-1 PAGES 1-3.
DURING ROUTINE C CHECK INSP, FOUND LT OTBD FLAP LOWER SKIN DENTED AT STA XF 169.000-213.000. REMOVED FASTENERS AS NEEDED TO PERFORM REPAIR. REMOVED DAMAGED SKIN. FABRICATED NEW SKIN, INTERNAL AND EXTERNAL DOUBLERS. BONDED PARTS AS NEEDED WITH HYSOL. CLEANED, TREATED, PRIMED AREA AND REPAIR PARTS. INSTALLED NEW FASTENERS AND REPAIR PARTS IAW SRM CHAPTER 57-7-1 FIGURE 4 TR 57-94, SRM 51-1-21, SRM 57-1-0, SRM 51-1-8B, SRM 57-7-1 FIGURE 4 TR 57-94 ITEMS "U" & "Q", DPS 4.710 REV "L", SRM 51-1-9 TR 51-142, SRM 51-1-9A TR 51-141, AND DPS 1.950 REV "AR" R-1.
DURING ROUTINE C CHECK INSP FOUND RT WING INBD L/E SLANT PANEL UPPER SKIN CORRODED AT STA XFS 70.000 - 160.000. REMOVED FASTENERS AS NEEDED TO PERFORM REPAIR. REMOVED CORROSION. FOUND OUT OF LIMITS. FABRICATED NEW SKIN, INTERNAL AND EXTERNAL DOUBLERS. CLEANED, TREATED, PRIMED AREA AND REPAIR PARTS. INSTALLED NEW FASTENERS AND REPAIR PARTS IAW SRM CHAPTER 57-2-1 FIGURE 37, SRM 51-1-8, SRM 51-1-8B, SRM 51-1-21, SRM 51-1-20D, 51-3-1, AND J/C 28.01-6.
DURING ROUTINE C CHECK INSP FOUND RT OTBD AILERON LOWER SKIN L/E DEFORMED AT STA XA 724.000. REMOVED FASTENERS AS NEEDED TO PERFORM REPAIR. REMOVED DAMAGED SKIN. FABRICATED NEW SKIN. CLEANED, TREATED, PRIMED AREA AND REPAIR PARTS. PERFORMED BALANCE. FOUND WITHIN LIMITS MOMENT: 3349.4 INCH-POUNDS. INSTALLED NEW FASTENERS AND REPAIR PARTS IAW SRM CHAPTER 57-8-1 FIGURE 4, SRM 51-1-21, SRM 57-1-0, SRM 51-1-8B, SRM 57-8-1 FIGURE 1 ITEM "H", DPS 4.710 REV "L", AND SRM 51-4-3 PAGES 1-3.
DURING ROUTINE C CHECK INSP FOUND RT OTBD FLAP LOWER SKIN DENTED AT STA XF 380.000. REMOVED FASTENERS AS NEEDED TO PERFORM REPAIR. REMOVED DAMAGED SKIN. FABRICATED NEW SKIN, INTERNAL AND EXTERNAL DOUBLERS. BONDED PARTS AS NEEDED WITH HYSOL. CLEANED, TREATED, PRIMED AREA AND REPAIR PARTS. INSTALLED NEW FASTENERS AND REPAIR PARTS IAW SRM CHAPTER 57-7-1 FIGURE 4 TR 57-94, SRM 51-1-21, SRM 57-1-0, SRM 51-1-8B, SRM 57-7-1 FIGURE 4 TR 57-94 ITEMS "U" & "Q", DPS 4.710 REV "L", SRM 51-1-9 TR 51-142, SRM 51-1-9A TR 51-141, AND DPS 1.950 REV "AR" R-1.
DURING ROUTINE C CHECK INSP FOUND LT INBD FLAP UPPER SKIN WORN AT STA XW 106.000. REMOVED FASTENERS AS NEEDED TO PERFORM REPAIR. REMOVED DAMAGED SKIN. FABRICATED NEW SKIN, INTERNAL AND EXTERNAL DOUBLERS. BONDED PARTS AS NEEDED WITH HYSOL. CLEANED, TREATED, PRIMED AREA AND REPAIR PARTS. INSTALLED NEW FASTENERS AND REPAIR PARTS IAW SRM CHAPTER 57-7-1 FIGURE 4 TR 57-94, SRM 51-1-21, SRM 57-1-0, SRM 51-1-8B, SRM 57-7-1 FIGURE 4 TR 57-94 ITEMS "U" & "Q", DPS 4.710 REV "L", SRM 51-1-9 TR 51-142, SRM 51-1-9A TR 51-141, AND DPS 1.950 REV "AR" R-1.
DURING ROUTINE C CHECK INSP FOUND LT OTBD FLAP LOWER SKIN DENTED AT STA XF 104.000-115.000. REMOVED FASTENERS AS NEEDED TO PERFORM REPAIR. REMOVED DAMAGED SKIN. FABRICATED NEW SKIN, INTERNAL AND EXTERNAL DOUBLERS. BONDED PARTS AS NEEDED WITH HYSOL. CLEANED, TREATED, PRIMED AREA AND REPAIR PARTS. INSTALLED NEW FASTENERS AND REPAIR PARTS IAW SRM CHAPTER 57-7-1 FIGURE 4 TR 57-94, SRM 51-1-21, SRM 57-1-0, SRM 51-1-8B, SRM 57-7-1 FIGURE 4 TR 57-94 ITEMS "U" & "Q", DPS 4.710 REV "L", SRM 51-1-9 TR 51-142, SRM 51-1-9A TR 51-141, AND DPS 1.950 REV "AR" R-1.
DURING ROUTINE C CHECK INSP, FOUND VERTICAL STABILIZER L/E SKIN CRACKED AT STA ZFS 179.750. REMOVED FASTENERS AS NEEDED TO PERFORM REPAIR. REMOVED DAMAGED AREA, PERFORMED EDDY CURRENT INSP. NO DISCREPANCY FOUND. FABRICATED INTERNAL, EXTERNAL DOUBLERS AND FILLERS. CLEANED, TREATED, AND PRIMED AERA AND REPAIR PARTS INSTALLED NEW FASTENERS AND REPAIR PARTS IAW FAA FORM 8110-3 DATED 02-05-2010, DWG ED-5068, SRM 51-1-21, 51-1-20D, NDT SPM MANUAL PART 06.10.01-001, SRM 51-1-8B, SRM 55-2-0, SRM 51-1-11, 51-1-21, 51-1-20D, 51-1-26 AND SRM 51-3-1.
DURING ROUTINE C CHECK INSP FOUND THE FWD PASSENGER DOOR OUTER SKIN UPPER PART EDGE BROKEN AND AFT UPPER CORNER DENTED. STRIPPED PAINT. REMOVED SKIN. FABRICATED NEW SKIN. CLEANED, TREATED, AND PRIMED AREA AND REPAIR PARTS. INSTALLED SKIN IAW SRM 52-3-2 FIGURE 1, SRM 53-1-0, MM 51-20-00, SRM 51-1-21, SRM 52-1-0, AND SRM 51-1-8B.
DURING APPROACH FOR LANDING WITH GEAR LOWERED RT MAIN GEAR LIGHT DID NOT ILLUMINATE. CREW CYCLED GEAR SEVERAL TIMES BEFORE GETTING A GEAR DOWN INDICATION, THEY LANDED WITHOUT FURTHER INCIDENT. MX INSPECTED THE RT MLG AND FOUND EXCESSIVE AMOUNT OF DIRT AND LUBE ON DOWN LOCK SWITCH CONTACT AREA. THEY CLEANED OFF CONTACT AREA. OPS CHECK GOOD IAW MM 32-60-0. ACFT WAS RETURNED TO SERVICE.
DURING APPROACH, WITH GEAR LOWERED, RT MAIN GEAR LIGHT DID NOT ILLUMINATE. THE CREW CYCLED GEAR SEVERAL TIMES BEFORE GETTING GEAR DOWN INDICATION, THEY LANDED WITHOUT FURTHER INCIDENT. MX INSPECTED ALL SWITCHES ON THE RT MLG AND LUBED GEAR. OPS CHECK GOOD IAW MM 32-60-0. ACFT WAS RETURNED TO SERVICE.
DURING CRUISE, NR 1 ENGINE FIRE WARNING CAME ON, CREW SHUTDOWN NR 1 ENGINE AND DISCHARGED BOTH FIRE BOTTLES. RETURNED AND LANDED WITHOUT FURTHER INCIDENT. MX INSPECTED AND FOUND LOW RESISTANCE FROM NR 1 FIRE DETECTOR PIN L TO GROUND. MX REPLACED NR 1 FIRE DETECTOR CONNECTOR AND LT PYLON LOOP CONNECTOR AND BOTH FIRE BOTTLES. OPERATIONAL CHECK GOOD IAW MM 26-10-0, AND 26-20-1. AIRCRAFT WAS RETURNED TO SERVICE.
DURING CRUISE, NR 1 ENGINE FIRE WARNING WENT OFF. THE CREW SHUT DOWN NUMBER ONE ENGINE AND DISCHARGED ONE BOTTLE. THE CREW LANDED WITHOUT FURTHER INCIDENT. MAINTENANCE REPLACED ALL FIRE LOOPS, NR 1 FIRE CONTROL UNIT AND ONE FIRE BOTTLE. OPERATIONAL CHECK GOOD IAW MM 26-10-1, 26-10-4, AND 26-20-1. AIRCRAFT WAS RETURNED TO SERVICE.
FLIGHT ATN103/KWRI TO PANC - DURING CRUISE FROM KWRI BOTH PILOT`S AND COPILOT`S YOKE TRIM SWITCHES INOPERATIVE. THE CREW DIVERTED TO KTOL AND LANDED WITHOUT INCIDENT. MAINTENANCE REPLACED RT LONG TRIM ACTUATOR, OPERATIONAL CHECK GOOD IAW 27-41-10. ACFT WAS RETURNED TO SERVICE. (S)
DURING ROUTINE C CHECK INSPECTION, FOUND IMPROPER REPAIR RT WING OUTBOARD SLOT VANE LEADING EDGE AT STATION XOLDI 6.224. REMOVED FASTENERS AS NEEDED TO PERFORM REPAIR. REMOVED EXISTING REPAIR. REMOVED DAMAGED AREA. PERFORMED NDT INSPECTION. NO CRACK, NO CORROSION FOUND. FABRICATED REPAIR DOUBLERS, FILLERS, AND INTERNAL DOUBLERS. CLEANED, TREATED AND PRIMED AREA AND REPAIR PARTS. INSTALLED NEW FASTENERS AND REPAIR PARTS AT STATION XOLDI 6.224-XOLDO 67.000 IAW FAA FORM 8110-3 08378 DATED 07/11/2008, SEMAN DRAWING ED-4809 DATED 06/23/08, 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. (S)
DURING ROUTINE C CHECK INSPECTION, FOUND IMPROPER REPAIR RT WING OUTBOARD SLOT VANE LEADING EDGE AT STATION XOLDI 6.224. REMOVED FASTENERS AS NEEDED TO PERFORM REPAIR. REMOVED EXISTING REPAIR. REMOVED DAMAGED AREA. PERFORMED NDT INSPECTION. NO CRACK, NO CORROSION FOUND. FABRICATED REPAIR DOUBLERS, FILLERS, AND INTERNAL DOUBLERS. CLEANED, TREATED AND PRIMED AREA AND REPAIR PARTS. INSTALLED NEW FASTENERS AND REPAIR PARTS AT STATION XOLDI 6.224 - XOLDO 67.000 IAW FAA FORM 8110-3 08378 DATED 07/11/2008. SEMAN DRAWING ED-4809 DATED 06/23/08, 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. (S)
DURING ROUTINE C CHECK INSPECTION, FOUND ELONGATED HOLES ON RT WING INBOARD SLOT VANE LEADING EDGE AT STATION XILD 7095.000. REMOVED FASTENERS AS NEEDED TO PERFORM REPAIR. REMOVED DAMAGED PLATING. FABRICATED NEW SKIN. CLEANED, TREATED AND PRIMED AREA AND REPAIR PARTS. INSTALLED NEW FASTENERS AND REPAIR PARTS AT STATION XILD 7095.000-XS 247.000 IAW DC8 SR 57-3-2 FIGURE 10 PAGE 22 ITEM F, DC8 SRM 57-1-0 PAGE 1, SRM 51-1-21, DC8 SRM 51-1-8B, DC8 SRM 51-1-11, SRM 51-3-0 AND SRM 51-3-1. (S)
DURING ROUTINE C CHECK INSPECTION, FOUND MAIN CARGO COMPARTMENT FRAME CLIP CRACK AT STATION XF 350.000 LONGERON 21. REMOVED CRACKED FRAME CLIP. FABRICATED FRAME CLIP. PERFORMED HEAT TREATMENT. PERFORMED NDT INSPECTION, NO CRACK NO CORROSION. CLEANED, TREATED AND PRIMED AREA AND FRAME CLIP. INSTALLED FRAME CLIP DC8 SRM 51-1-20D, ATI REPAIR SPECIFICATION 2003-05 AND SEMAN ED 4814, DC8 SRM 51-1-1 PAGE 1,13, 17, DACO DPS 4.707, DC8 SRM 51-1-8B, DC8 SRM 51-1-11, SRM 51-1-20D AND 51-3-1. (S)
DURING ROUTINE C CHECK INSPECTION, FOUND MAIN CARGO COMPARTMENT FRAME CLIP CRACK AT STATION XF 350.000 LONGERON 21. REMOVED CRACKED FRAME CLIP. FABRICATED FRAME CLIP. PERFORMED HEAT TREATMENT. PERFORMED NDT INSPECTION, NO CRACK NO CORROSION. CLEANED, TREATED AND PRIMED AREA AND FRAME CLIP. INSTALLED FRAME CLIP DC8 SRM 51-1-20D, ATI REPAIR SPECIFICATION 2003-05 AND SEMAN ED 4814, DC8 SRM 51-1-1 PAGE 1,13,17, DACO DPS 4.707, DC8 SRM 51-1-8B, DC8 SRM 51-1-11, SRM 51-1-20D AND 51-3-1. (S)
DURING ROUTINE C CHECK INSPECTION, FOUND LT WING CRACKED ON LEADING EDGE UPPER SKIN AT STATION XCW 69.500. REMOVED FASTENERS AS NEEDED TO PERFORM REPAIR. REMOVED DAMAGED AREA. PERFORMED NDT INSPECTION. NO CRACK, NO CORROSION, FABRICATED DOUBLER, FILLER PLUG. PERFORMED HEAT TREATMENT, CLEANED TREATED AND PRIMED AREA AND REPAIR PARTS. INSTALLED NEW FASTENERS AND REPAIR PARTS IAW DC8 SRM 57-2-1 FIGURE 20 SHEETS 1,2,3 DC8 SRM 51-1-20D, DCA SRM 57-2-1 FIGURE 20 SHEET 1, DC8 SRM 51-1-12 FIGURE 7, DC8 NDT SPM PART 06-10-01-001, SRM 57-3-2 FIGURE 15 ITEM "J", SRM 51-10-0 FIGURE 21, DC8 SRM 51-1-1 PAGES 1,13 AND 17, DC8 SRM 51-1-8, AND SRM 51-1-11. (S)
DURING ROUTINE C CHECK INSPECTION, FOUND EXTERIOR FUSELAGE "B" DOOR JAMB WORN AT STATION 503.000 LONGERON 27-28 RIGHT. REMOVED FASTENERS AS NEEDED TO PERFORM REPAIR. REMOVED DAMAGED AREA. PERFORMED NDT INSPECTION. NO CRACK, NO CORROSION FOUND. FABRICATED REPAIR DOUBLER, FILLER. CLEANED, TREATED AND PRIMED AREA AND REPAIR PARTS. INSTALLED NEW FASTENERS AND REPAIR PARTS IAW DC8 SRM 51-1-11, SRM 51-3-1, FAA FORM 8110-3 08378 DATED 07/11/08, SEMAN DRAWING ED-4808 DATED 06/20/08, DC8 SRM 51-1-21, SRM 51-1-20D, DC8 NDT SPM PART 06-10-01-001, DC8 SRM 51-1-8B. (S)
DURING ROUTINE C-CHECK INSPECTION, FOUND LT WING CRACKED ON LEADING EDGE UPPER SKIN AT STATION XCW 69.500. REMOVED FASTENERS AS NEEDED TO PERFORM REPAIR. REMOVED DAMAGED AREA. PERFORMED NDT INSPECTION. NO CRACK, NO CORROSION, FABRICATED DOUBLER, FILLER PLUG. PERFORMED HEAT TREATMENT CLEANED, TREATED AND PRIMED AREA AND REPAIR PARTS. INSTALLED NEW FASTENERS AND REPAIR PARTS IAW SRM 57-2-1 FIGURE 20 SHEETS 1, 2, 3 SRM 51-1-20D, SRM 57-2-1 FIGURE 20 SHEET 1, SRM 51-1-12 FIGURE 7, NDT SPM PART 06-10-01-001, SRM 57-3-2 FIGURE 15 ITEM "J", SRM 51-10-0 FIGURE 21, SRM 51-1-1 PAGES 1, 13 AND 17 SRM 51-1-8, AND SRM 51-1-11. (S)
DURING ROUTINE C CHECK INSPECTION, FOUND EXTERIOR FUSELAGE "B" DOOR JAMB WORN AT STATION 503.000 LONGERON 27-28 RT. REMOVED FASTENERS AS NEEDED TO PERFORM REPAIR. REMOVED DAMAGED AREA. PERFORMED NDT INSPECTION. NO CRACK, NO CORROSION FOUND. FABRICATED REPAIR DOUBLER, FILLER. CLEANED, TREATED AND PRIMED AREA AND REPAIR PARTS. INSTALLED NEW FASTENERS AND REPAIR PARTS IAW DC8 SRM 51-1-11, SRM 51-3-1, FAA FORM 8110-3 08378 DATED 07/11/08, SEMAN DRAWING ED4808 DATED 06/20/08, DC8 SRM 51-1-21, SRM 51-1-20D, DC8 NDT SPM PART 06-10-01-001, DC8 SRM 51-1-8B. (S)
DURING ROUTINE C CHECK INSPECTION, FOUND AFT FUSELAGE EXTERNAL SKIN HAS A CRACK AT STATION 1606.000-1604.000 LONGERON 10 RIGHT. REMOVED FASTENERS AS NEEDED TO PERFORM REPAIR. REMOVED DAMAGED AREA. FABRICATED REPAIR DOUBLER, INTERNAL FINGER DOUBLER, AND FILLER. CLEANED, TREATED AND PRIMED AREA AND REPAIR PARTS. INSTALLED NEW FASTENERS AND REPAIR PARTS IAW DC8 SRM 53-2-1 FIGURE 7 SHEET 1,3, AND 5, SRM 53-5-2 FIGURE 1 ITEM "D", DC8 SRM 51-1-8B, SRM 51-1-11, SRM 51-1-20D, AND SRM 51-3-1. (S)
DURING ROUTINE C CHECK INSPECTION, FOUND AFT FUSELAGE EXTERNAL SKIN HAS A CRACK AT STATION 1606.000-1604.000 LONGERON 10RT. REMOVED FASTENERS AS NEEDED TO PERFORM REPAIR. REMOVED DAMAGED AREA. FABRICATED REPAIR DOUBLER, INTERNAL FINGER DOUBLER, AND FILLER. CLEANED, TREATED AND PRIMED AREA AND REPAIR PARTS. INSTALLED NEW FASTENERS AND REPAIR PARTS IAW DC8 SRM 53-2-1 FIGURE 7 SHEET 1, 3 AND 5 SRM 53-5-2 FIGURE 1 ITEM "D", DC8 SRM 51-1-8B, SRM 51-1-11, SRM 51-1-21, SRM 51-1-20D, AND SRM 51-3-1. (S)
DURING ROUTINE C-CHECK INSPECTION, FOUND RT WING TRAILING EDGE STIFFENER CRACKED AT STATION XW 19.000. REMOVED CRACKED STIFFENER. FABRICATED STIFFENER. PERFORMED NDT INSPECTION. NO CRACK, NO CORROSION FOUND. CLEANED, TREATED AND PRIMED AREA AND STIFFENER. INSTALLED STIFFENER IAW DC8 SRM 51-1-20D, ATI REPAIR SPECIFICATION 2003-05, ED SEMAN 4816 DATED 07/14/2008, DACO DPS 4.707, DC8 SRM 51-1-8B, DC8 SRM 51-1-21, AND SRM 51-3-1. (S)
DURING ROUTINE C CHECK INSPECTION, FOUND COCKPIT FINGER DOUBLER WITH CORROSION AT STATION FS 188.000-208.000 LT BOTTOM LINE 60. REMOVED CORROSION. FOUND OUT OF LIMITS. REMOVED DAMAGED AREA. PERFORMED NDT INSPECTION. NO CRACK NO CORROSION FOUND FABRICATED SEGMENT PANEL, EXTERNAL REPAIR DOUBLERS, INTERNAL REPAIR FINGER DOUBLER, STRAPS, AND INTERNAL REPAIR FINGER DOUBLER. CLEANED, TREATED AND PRIMED AREA AND REPAIR PARTS. INSTALLED REPAIR PARTS IAW DC8 SRM 51-1-11, FAA FORM 8110-3 08378 DATED 07/11/08 SEMAN DRAWING ED-4805 DATED 06/24/08, DC8 SRM 51-1-8B PAGES 17-18, DC8 SRM 53-2-0 PAGE 2-M, DC8 NDT SPM PART 06-10-01-001, AND DC8 SRM 51-1-8B. (S)
DURING ROUTINE C CHECK INSPECTION, FOUND RT WING TRAILING EDGE STIFFENER CRACKED AT STATION XW 19.000. REMOVED CRACKED STIFFENER. FABRICATED STIFFENER. PERFORMED NDT INSPECTION. NO CRACK, NO CORROSION FOUND. CLEANED, TREATED AND PRIMED AREA AND STIFFENER. INSTALLED STIFFENER IAW DC8 SRM 51-1-20D, ATI REPAIR SPECIFICATION 2003-05, ED SEMAN 4816 DATED 07/14/2008, DACO DPS 4.707, DC8 SRM 51-1-8B, DC8 SRM 51-1-21, AND SRM 51-3-1. (S)
DURING ROUTINE C CHECK INSPECTION, FOUND RT WING CENTER LEADING EDGE UPPER SKIN HAS IMPROPER REPAIR AT STATION 285.250. REMOVED FASTENERS AS NEEDED TO PERFORM REPAIR. REMOVED EXISTING REPAIR. REMOVED DAMAGED AREA. PERFORMED NDT INSPECTION. NO CRACK, NO CORROSION FOUND. FABRICATED REPAIR DOUBLER, FILLERS. CLEANED, TREATED AND PRIMED AREA AND REPAIR PARTS. INSTALLED NEW FASTENERS AND REPAIR PARTS IAW FAA FORM 8110-3 08379 DATED 07/11/08, SEMAN DRAWING ED48-10 DATED 06/24/08, DC8 SRM 51-1-8B, DC8 SRM 51-1-21, SRM 51-3-0, DC8 NDT SPM PART 06-10-01-001, DC8 SRM 51-1-11, SRM 51-3-0, SRM 51-1-20D, AND SRM 51-3-1. (S)
DURING ROUTINE C CHECK INSPECTION, FOUND LT OUTBOARD FLAP SKIN ON EXHAUST GATE WORN AT STATION XF 250.000. REMOVED FASTENERS AS NEEDED TO PERFORM REPAIR. REMOVED DAMAGED PLATING. FABRICATED NEW SKIN. CLEANED, TREATED AND PRIMED AREA AND REPAIR PART. INSTALLED NEW FASTENERS AAND REPAIR PARTS IAW DC8 SRM 57-7-1 FIGURE 4 TR 57-94 DATED 10-01-02, DC8 SRM 57-1-0 PAGE 1, SRM 51-1-21, DC8 SRM 57-7-1 FIGURE 4 ITEM "C" TR 57-94, DC8 SRM 51-1-8B, DC8 SRM 51-1-11, AND SRM 51-1-21. (S)
DURING ROUTINE C CHECK INSPECTION, FOUND LT OUTBOARD FLAP SKIN ON EXHAUST GATE WORN AT STATION XF 250.000. REMOVED FASTENERS AS NEEDED TO PERFORM REPAIR. REMOVED DAMAGED PLATING. FABRICATED NEW SKIN. CLEANED, TREATED AND PRIMED AREA AND REPAIR PART. INSTALLED NEW FASTENERS AND REPAIR PARTS IAW DC8 SRM 57-7-1 FIGURE 4 TR 57-94 DATED 10-01-02, DC8 SRM 57-1-0 PAGE 1, SRM 51-1-21, DC8 SRM 57-7-1 FIGURE 4 ITEM "C" TR 57-94, DC8 SRM 51-1-8B, DC8 SRM 51-1-11, AND SRM 51-1-21. (S)
DURING ROUTINE C CHECK INSPECTION, FOUND RT WING OUTBOARD AILERON UPPER SKIN IMPROPER REPAIRS AT STATION XA 630.000-724.000. REMOVED FASTENERS AS NEEDED TO PERFORM REPAIR. REMOVED EXISTING REPAIR. FABRICATED NEW SKIN, DOUBLER. BONDED PARTS AS NEEDED WITH HYSOL. CLEANED, TREATED AND PRIMED AREA AND REPAIR PART. PERFORMED BALANCE FOUND WITHIN LIMITS MOMENT =3326.3 IN-LB. INSTALLED NEW FASTENERS AND REPAIR PARTS AT STATION XW 546.000-XA 724.000 IAW DC8 SRM 57-8-1 FIGURE 4 ITEM "F" AND "G", DC8 SRM 57-1-0 PAGE 1, SRM 51-1-21, DOUGLAS DRAWING 5763133, DC8 SRM 51-1-9 TR 51-142, SRM 51-1-9A TR 51-141, DC8 SRM 51-1-8B, IAW DC8 SRM 51-4-3 PAGES 1-6, DC8 SRM 51-1-11, AND SRM 51-1-21. (S)
DURING ROUTINE C CHECK INSPECTION, FOUND RT WING OUTBOARD AILERON UPPER SKIN IMPROPER REPAIRS AT STATION XA 630.000-724.000. REMOVED FASTENERS AS NEEDED TO PERFORM REPAIR, REMOVED EXISTING REPAIR. FABRICATED NEW SKIN, DOUBLER. BONDED PARTS AS NEEDED WITH HYSOL. CLEANED, TREATED AND PRIMED AREA AND REPAIR PART. PERFORMED BALANCE, FOUND WITHIN LIMITS MOMENT = 3326.3 IN-LB. INSTALLED NEW FASTENERS AND REPAIR PARTS AT STATION XW 546.000-XA 724.000 IAW DC8 SRM 57-8-1 FIGURE 4 ITEM "F" AND "G", DC8 SRM 57-1-0 PAGE 1, SRM 51-1-21, DOUGLAS DRAWING 5763133, DC8 SRM 51-1-9 TR 51-142, SRM 51-1-9A TR 51-141, DC8 SRM 51-1-8B, IAW DC8 SRM 51-4-3 PAGES 1-6, DC8 SRM 51-1-11, AND SRM 51-1-21. (S)
DURING ROUTINE C CHECK INSPECTION, FOUND RT WING INBOARD FLAP UPPER PANEL HAS IMPROPER REPAIR AND DENTS AT STATION XW 3000 TO STATION XW 92.000. REMOVED FASTENERS AS NEEDED TO PERFORM REPAIR. REMOVED EXISTING REPAIR. FABRICATED NEW SKIN, AND BONDED DOUBLER. BONDED PARTS AS NEEDED WITH HYSOL. CLEANED, TREATED AND PRIMED AREA AND REPAIR PARTS. INSTALLED NEW FASTENERS AND REPAIR PARTS IAW DC8 SRM 57-7-1 FIGURE 1 PAGE 2, DC8 SRM 57-1-0 PAGE 1, SRM 51-3-0, SRM 51-1-21, DC8 SRM 57-7-1 FIG 1 ITEM "A", DC8 SRM 51-1-9 TR 51-142, SRM 51-1-9A TR 51-141, DC8 SRM 51-1-8B, DC8 SRM 51-1-1, SRM 51-3-0, AND SRM 51-3-1. (S)
DURING ROUTINE C CHECK INSPECTION, FOUND RT WING OUTBOARD FLAP PANEL UPPER PART HAS IMPROPER REPAIR AT STATION 360.000. REMOVED FASTENERS AS NEEDED TO PERFORM REPAIR. REMOVED EXISTING REPAIR. FABRICATED NEW SKIN. CLEANED, TREATED AND PRIMED AREA AND REPAIR PART. INSTALLED NEW FASTENERS AND REPAIR PARTS AT STATION XF345.000-360.000 IAW DC8 SRM 57-1-0 PAGE 1, SRM 51-1-21, DC8 SRM 57-7-1 FIGURE 4 ITEM "B" TR 57-94 DATED 10-01-2002, DC8 SRM 51-1-8B, DC8 SRM 51-1-11, SRM 51-3-0, AND SRM 51-3-1. (S)
DURING ROUTINE C CHECK INSPECTION, FOUND RT WING INBOARD FLAP UPPER PANEL HAS IMPROPER REPAIR AND DENTS AT STATION XW 3000 TO STATION XW 92.000. REMOVED FASTENERS AS NEEDED TO PERFORM REPAIR. REMOVED EXISTING REPAIR. FABRICATED NEW SKIN, AND BONDED DOUBLER. BONDED PARTS AS NEEDED WITH HYSOL. CLEANED, TREATED AND PRIMED AREA AND REPAIR PARTS. INSTALLED NEW FASTENERS AND REPAIR PARTS IAW DC8 SRM 57-7-1 FIGURE 1 PAGE 2, DC8 SRM 57-1-0 PAGE 1, SRM 51-3-0, SRM 51-1-21, DC8 SRM 57-7-1 FIG 1 ITEM "A", DC8 SRM 51-1-9 TR 51-142, SRM 51-1-9A TR 51-141, DC8 SRM 51-1-8B, DC8 SRM 51-1-11, SRM 51-3-0 AND SRM 51-3-1. (S)
DURING ROUTINE C CHECK INSPECTION, FOUND RT WING OUTBOARD FLAP PANEL UPPER PART HAS IMPROPER REPAIR AT STATION 360.000. REMOVED FASTENERS AS NEEDED TO PERFORM REPAIR. REMOVED EXISTING REPAIR. FABRICATED NEW SKIN. CLEANED, TREATED AND PRIMED AREA AND REPAIR PART. INSTALLED NEW FASTENERS AND REPAIR PARTS AT STATION XF 345.000-360.000 IAW DC8 SRM 57-1-0 PAGE 1, SRM 51-1-21, DC8 SRM 57-7-1 FIGURE 4 ITEM "B" TR 57-94 DATED 10-01-2002, DC8 SRM 51-1-8B, DC8 SRM 51-1-11, SRM 51-3-0, AND SRM 51-3-1. (S)
DURING ROUTINE C CHECK INSPECTION, FOUND ACCESSORY COMPARTMENT FRAME CRACKED AT STATION 255.000 LONGERON 25LT. REMOVED DAMAGED FRAME SEGMENT. FABRICATED NEW SEGMENT. PERFORMED HEAT TREATMENT. CLEANED, TREATED AND PRIMED AREA AND REPAIR PARTS. INSTALLED REPAIR PARTS IAW DC8 SRM 53-2-0 FIGURE 2 SHEET 5 TR 53-125 DATED 8/31/01, SHEET 6 PAGES 5-6, DC8 SRM 51-1-8B, SRM 53-2-0 FIGURE 2 SHEET 1, SRM 53-3-2 FIGURE 3 SHEET 2A ITEM "U", SRM 53-3-2 FIGURE 3 SHEET 2, SRM 51-2-0 FIGURE 52 SHEET 1, SRM 53-2-0 FIGURE 2 SHEET 7-8 TR 53-110 DATED 11-10-00, DC8 SRM 51-1-1 PAGES 1,13,17, SRM 51-1-11, SRM 51-1-20D, AND SRM 51-3-1. (S)
DURING ROUTINE C CHECK INSPECTION, FOUND RT WING LEADING EDGE LOWER SKIN CORRODED AT STATION XW 736.000-761.000. REMOVED CORROSION. FOUND OUT OF LIMITS. REMOVED CORRODED SKIN. FABRICATED NEW SKIN. CLEANED, TREATED AND PRIMED AREA AND REPAIR PART. INSTALLED REPAIR PARTS IAW DC8 SRM 57-3-2 FIGURE 8 PAGE 19 ITEM "A", DC8 SRM 51-1-8 PAGES 17-18, DC8 SRM 57-2-0 FIGURE 7, DC8 SRM 57-1-0 PAGE 1, SRM 51-1-21, DC8 SRM 51-1-8B, DC8 SRM 51-1-11, SRM 51-1-20D, AND 51-3-1. (S)
DURING ROUTINE C CHECK INSPECTION, FOUND FUSELAGE EXTERNAL PART PRIMARY HEAT EXCHANGER LOWER AFT CORNER CRACKED AT STATION 188.000 LONGERON 27LT. REMOVED FASTENERS AS NEEDED TO PERFORM REPAIR. REMOVED DAMAGED AREA. PERFORMED NDT INSPECTION. NO CRACK, NO CORROSION FOUND. FABRICATED EXTERNAL REPAIR DOUBLER, EXTERNAL REPAIR TRIPLER, AND FILLER. CLEANED, TREATED AND PRIMED AREA AND REPAIR PARTS. INSTALLED NEW FASTENERS AND REPAIR PARTS IAW FAA FORM 8110-3 08378 DATED 7/11/08, SEMAN DRAWING ED4804 DATED 06/23/08, DC8 SRM 51-1-21, SRM 51-3-0, DC8 NDT SPM PART 06-10-01-001, DC8 SRM 51-1-8B, SRM 51-1-11, SRM 51-1-20D, SRM 51-3-0, AND SRM 51-3-1. (S)
DURING ROUTINE C CHECK INSPECTION, FOUND MIDDLE ACCESSORY COMPARTMENT BULKHEAD CRACKED AT STATION 680.000 LT BOTTOM LINE 20-30. REMOVED FASTENERS AS NEEDED TO PERFORM REPAIR. REMOVED EXISTING DOUBLER AND SPLICE. REMOVED DAMAGED AREA. FABRICATED DOUBLER, DOME SEGMENT, SPLICE, DOUBLER, FINGER DOUBLER, FILLER. PERFORMED HEAT TREATMENT. CLEANED, TREATED AND PRIMED AREA AND REPAIR PARTS. INSTALLED NEW FASTENERS AND REPAIR PARTS IAW DC8 SRM 53-2-5 FIGURE 13 SHEET 1 T/R 53-177 SHEETS 1-2 DATED 9/20/03, DC8 SRM 51-1-1 PAGES 1, 13 AND 17, DC8 SRM 51-1-8B, 51-1-11, 51-1-21, 51-1-20D, AND 51-3-1. (S)
DURING ROUTINE C CHECK INSPECTION, FOUND AC COMPARTMENT CLIP CORRODED AT STATION 235.000 LONGERON 31LT. REMOVED CORROSION. FOUND OUT OF LIMITS. REMOVED CORRODED CLIP. FABRICATED NEW CLIP. CLEANED, TREATED AND PRIMED CLIP. INSTALLED CLIP IAW DC8 SRM 51-1-20D, SRM 51-3-1, DC8 SRM 51-1-8 PAGED 17-18, DC8 SRM 53-2-0 PAGE 2P, DC8 SRM 51-1-20D, DC8 SRM 53-2-0, DC8 SRM 51-1-8B. (S)
DURING ROUTINE C CHECK INSPECTION, FOUND AFT CARGO BAY LONGERON 36 CORRODED AT STATION 1320.000-1340.000. REMOVED CORROSION. FOUND OUT OF LIMITS. REMOVED FASTENERS AS NEEDED TO PERFORM REPAIR. REMOVED DAMAGED LONGERON SEGMENT. FABRICATED SPLICE OF EXTRUSION. CLEANED, TREATED AND PRIMED AREA AND SPLICE. INSTALLED NEW FASTENERS AND LONGERON SEGMENT IAW SRM 53-2-2 PAGE 6 FIGURE 4A, SRM 51-1-8 PAGES 17-18, SRM 53-2-0 PAGE 2P, SRM 53-2-2 FIGURE 10 SHEET 2, SRM 53-2-2 FIG 10 SHEET 4 TR 53-193 DATED 03/15/04, SRM 51-1-8B, SRM 51-2-0 FIGURE 52 SHEET 1, SRM 51-2-0 FIGURE 50 SHEET 65, SRM 53-4-1 FIGURE 44B SHEET 2 ITEM "L", SRM 51-1-20D, AND SRM 51-3-1. (S)
DURING ROUTINE C CHECK INSPECTION, FOUND RT WING LEADING EDGE LOWER SKIN CORRODED AT STATION XW 736.000-761.000. REMOVED CORROSION. FOUND OUT OF LIMITS. REMOVED CORRODED SKIN. FABRICATED NEW SKIN. CLEANED, TREATED AND PRIMED AREA AND REPAIR PART. INSTALLED REPAIR PARTS IAW DC8 SRM 57-3-2 FIGURE 8 PAGE 19 ITEM "A", DC8 SRM 51-1-8 PAGES 17-18, DC8 SRM 57-2-0 FIGURE 7, DC8 SRM 57-1-0 PAGE 1, SRM 51-1-21, DC8 SRM 51-1-8B, DC8 SRM 51-1-11, SRM 51-1-20D, AND 51-3-1. (S)
DURING ROUTINE C CHECK INSPECTION, FOUND AFT CARGO COMPARTMENT LONGERON-36 CORRODED AT STATION 1320.000-1340.000. REMOVED CORROSION. FOUND OUT OF LIMITS. REMOVED FASTENERS AS NEED TO PERFORM REPAIR. REMOVED DAMAGED LONGERON SEGMENT. FABRICATED SPLICE OF EXTRUSION. CLEANED, TREATED AND PRIMED AREA AND SPLICE. INSTALLED NEW FASTENERS AND LONGERON SEGMENT IAW DC8 SRM 53-2-2 PAGE 6 FIGURE 41, DC8 SRM 51-1-8 PAGES 17-18, DC8 SRM 53-2-0 PAGE 2P, DC8 SRM 53-2-2 FIGURE 10 SHEET 2, SRM 53-2-2 FIG 10 SHEET 4 TR 53-193 DATED 03/15/04, DC8 SRM 51-1-8B, SRM 51-2-0 FIGURE 52 SHEET 1, SRM 51-2-0 FIGURE 50 SHEET 65, SRM 53-4-1 FIGURE 44B SHEET 2 ITEM "L", SRM 51-1-20D, AND SRM 51-3-1. (S)
DURING ROUTINE C CHECK INSPECTION, FOUND ACND COMPARTMENT CLIP CORRODED AT STATION 235.000 LONGERON 31 LEFT. REMOVED CORROSION. FOUND OUT OF LIMITS. REMOVED CORRODED CLIP. FABRICATED NEW CLIP. CLEANED, TREATED AND PRIMED CLIP. INSTALLED CLIP IAW DC8 SRM 51-1-20D, SRM 51-3-1, DC8 SRM 51-1-8 PAGES 17-18, DC8 SRM 53-2-0 PAGE 2P, DC8 SRM 51-1-20D, DC8 SRM 53-2-0, DC8 SRM 51-1-8B. (S)
DURING ROUTINE C CHECK INSPECTION, FOUND RT WING AUXILIARY SPARS STIFFENER CORRODED AT STATION XW 33.000. REMOVED CORROSION. FOUND OUT OF LIMITS. REMOVED CORRODED STIFFENER. FABRICATED STIFFENER. CLEANED, TREATED AND PRIMED AREA AND STIFFENER. INSTALLED STIFFENER IAW DC8 SRM 51-1-8 PAGES 17-18, DC8 SRM 57-2-0 PAGE 16, DC8 SRM 51-1-21, SRM 51-1-20D, DC8 SRM 57-2-0 PAGE 1, DC8 SRM 51-1-8B, AND SRM 51-3-1. (S)
DURING ROUTINE C-CHECK INSPECTION, FOUND FUSELAGE EXTERNAL PART PRIMARY HEAT EXCHANGER LOWER AFT CORNER CRACKED AT STATION 188.000 LONGERON 27LEFT. REMOVED FASTENERS AS NEEDED TO PERFORM REPAIR. REMOVED DAMAGED AREA. PERFORMED NDT INSPECTION. NO CRACK, NO CORROSION FOUND. FABRICATED EXTERNAL REPAIR DOUBLER, EXTERNAL REPAIR TRIPLER, AND FILLER. CLEANED, TREATED AND PRIMED AREA AND REPAIR PARTS. INSTALLED NEW FASTENERS AND REPAIR PARTS IAW FAA FORM 8110-3 08378 DATE 7/11/08, SEMAN DRAWING ED-4804 DATED 06/23/08, DC8 SRM 51-1-21, SRM 51-3-0, DC8 NDT SPM PART 06-10-01-001, DC8 SRM 51-1-8B, SRM 51-1-11, SRM 51-1-20D, SRM 51-3-0, AND SRM 51-3-1. (S)
DURING ROURTINE C CHECK INSPECTION, FOUND AFT FUSELAGE SPLICE FITTING CRACKED AT STATION FS 1610.000 LONGERON 17RIGHT. REMOVED CRACKED SPLICE FITTING. CLEANED, TREATED AND PRIMED AREA. INSTALLED NEW SPLICE FITTING IAW DC8 SRM 51-1-21, SRM 51-1-20D, DC8 SRM 51-1-8B, AND SRM 51-3-1. (S)
DURING ROUTINE C CHECK INSPECTION, FOUND AFT FUSELAGE SPLICE FITTING CRACKED AT STATION FS 1610.000 LONGERON 17RT. REMOVED CRACKED SPLICE FITTING. CLEANED, TREATED AND PRIMED AREA. INSTALLED NEW SPLICE FITTING IAW DC8 SRM 51-1-21, SRM 51-1-20D, DC8 SRM 51-1-8B, AND SRM 51-3-1. (S)
DURING ROUTINE C CHECK INSPECTION, FOUND AFT FUSELAGE CRACKED AT STATION FS 1610.000 LONGERON 17 RIGHT. REMOVED DAMAGED LONGERON. CLEANED, TREATED AND PRIMED AREA. INSTALLED LONGERON IAW DC8 SRM 53-5-2 FIGURE 5 SHEET 1 PAGE 16 ITEM "B", DC8 SRM 51-1-8B, DC8 SRM 53-1-0 PAGE 1, SRM 51-1-21, 51-1-20D, SRM 51-2-0 FIGURE 50 SHEET 37, 51-3-0, AND SRM 51-3-1. (S)
DURING ROUTINE C CHECK INSPECTION, FOUND AFT FUSELAGE CRACKED AT STATION FS 1610.000 LONGERON 17LEFT. REMOVED DAMAGED LONGERON. CLEANED, TREATED AND PRIMED AREA. INSTALLED LONGERON. IAW DC8 SRM 53-5-2 FIGURE 5 SHEET 1 PAGE 16 ITEM "B", DC8 SRM 51-1-8B, DC8 SRM 53-1-0 PAGE 1, SRM 51-1-21, 51-1-20D, SRM 51-2-0 FIGURE 50 SHEET 37, 51-3-0, AND SRM 51-3-1. (S)
DURING ROUTINE C CHECK INSPECTION, FOUND AFT FUSELAGE CRACKED AT STATION FS 1610.000 LONGERON 17 LT. REMOVED DAMAGED LONGERON. CLEANED, TREATED AND PRIMED AREA. INSTALLED LONGERON IAW DC8 SRM 53-5-2 FIGURE 5 SHEET 1 PAGE 16 ITEM "B", DC8 SRM 51-1-8B, DC8 SRM 53-1-0 PAGE 1, SRM 51-1-21, 51-1-20D, SRM 51-2-0 FIGURE 50 SHEET 37, 51-3-0, AND SRM 51-3-1. (S)
DURING ROUTINE C-CHECK INSPECTION, FOUND AFT FUSELAGE CRACKED AT STATION FS 1610.000 LONGERON 17 RT. REMOVED DAMAGED LONGERON. CLEANED, TREATED AND PRIMED AREA. INSTALLED LONGERON. IAW DC8 SRM 53-5-2 FIGURE 5 SHEET 1 PAGE 16 ITEM "B", DC8 SRM 51-1-8B, DC8 SRM 53-1-0 PAGE 1, SRM 51-1-21, 51-1-20D, SRM 51-2-0 FIGURE 50 SHEET 37, 51-3-0, AND SRM 51-3-1. (S)
DURING ROUTINE C CHECK INSPECTION, FOUND IMPROPER REPAIR ON LT WING INBOARD SLOT VANE LEADING EDGE AT STATION XILD 7095.000. REMOVED FASTENERS AS NEEDED TO PERFORM REPAIR. REMOVED EXISTING REPAIR. FABRICATED NEW SKIN. CLEANED, TREATED AND PRIMED AREA AND REPAIR PART. INSTALLED NEW FASTENERS AND REPAIR PARTS IAW DC8 SRM 57-3-2 FIGURE 10 PAGE 22 ITEM "F", DC8 SRM 57-1-0 PAGE 1, SRM 51-1-21, DC8 SRM 51-1-8B, DC8 SRM 51-1-11, SRM 51-3-0, AND SRM 51-31-1. (S)
DURING ROUTINE C CHECK INSPECTION, FOUND IMPROPER REPAIR ON LT WING INBOARD SLOT VANE LEADING EDGE AT STATION XILD 7095.000. REMOVED FASTENERS AS NEEDED TO PERFORM REPAIR. REMOVED EXISTING REPAIR. FABRICATED NEW SKIN. CLEANED, TREATED AND PRIMED AREA AND REPAIR PART. INSTALLED NEW FASTENERS AND REPAIR PARTS IAW DC8 SRM 57-3-2 FIGURE 10 PAGE 22 ITEM "F", DC8 SRM 57-1-0 PAGE 1, SRM 51-1-21, DC8 SRM 51-1-8B, DC8 SRM 51-1-1, SRM 51-3-0, AND SRM 51-3-1. (S)
DURING ROUTINE C CHECK INSPECTION, FOUND NICKS RT WING OUTBOARD FLAP UPPER SKIN AT STATION XF 345.000. REMOVED FASTENERS AS NEEDED TO PERFORM REPAIR. REMOVED DAMAGED AREA. FABRICATED NEW SKIN. CLEANED, TREATED AND PRIMED AREA AND REPAIR PART. INSTALLED NEW FASTENERS AND REPAIR PARTS AT STATION XF 345.000-360.000 IAW DC8 SRM 57-7-1 FIGURE 4 TR 57-94 DATED 10-01-2002, DC8 SRM 57-1-0 PAGE 1, SRM 51-1-21, DC8 SRM 51-1-8B, DC8 SRM 51-1-11, SRM 51-3-0, AND SRM 51-3-1. (S)
DURING ROUTINE C CHECK INSPECTION, FOUND NICKS RT WIND OUTBOARD FLAP UPPER SKIN AT STATION XF 345.000. REMOVED FASTENERS AS NEEDED TO PERFORM REPAIR, REMOVED DAMAGED AREA. FABRICATED NEW SKIN. CLEANED, TREATED AND PRIMED AREA AND REPAIR PART. INSTALLED NEW FASTENERS AND REPAIR PARTS AT STATION XF 345.000-360.000 IAW DC8 SRM 57-7-1 FIGURE 4 TR 57-94 DATED 10-01-2002, DC8 SRM 57-1-0 PAGE 1, SRM 51-1-21, DC8 SRM 51-1-8B, DC8 SRM 51-1-11, SRM 51-3-0, AND SRM 51-3-1. (S)
DURING ROUTINE C CHECK INSPECTION, FOUND ELONGATED HOLES ON RT WING INBOARD SLOT VANE LEADING EDGE AT STATION XILD 7095.000. REMOVED FASTENERS AS NEEDED TO PERFORM REPAIR. REMOVED DAMAGED PLATING, FABRICATED NEW SKIN. CLEANED, TREATED AND PRIMED AREA AND REPAIR PARTS. INSTALLED NEW FASTENERS AND REPAIR PARTS AT STATION XILD 7095.000 - XS 247.000 IAW DC8 SRM 57-3-2 FIGURE 10 PAGE 22 ITEM F, DC8 SRM 57-1-0 PAGE 1, SRM 51-1-21, DC8 SRM 51-1-8B, DC8 SRM 51-1-11, SRM 51-3-0 AND SRM 51-3-1. (S)
DURING ROUTINE C CHECK INSPECTION, FOUND LT WING OUTBOARD FLAP UPPER SKIN WORN AT STATION XF 211.000. REMOVED FASTENERS AS NEEDED TO PERFORM REPAIIR. REMOVED DAMAGED AREA. FABRICATED NEW SKIN. CLEANED, TREATED AND PRIMED AREA AND REPAIR PART. INSTALLED NEW FASTENERS AND REPAIR PARTS IAW DC8 SRM 57-7-1 FIGURE 4 TR 57-94, DC8 SRM 57-1-0 PAGE 1, SRM 51-1-21, DC8 SRM 51-1-8B, DC8 SRM 57-7-1 FIGURE 4 ITEM "C" TR 57-94 DATED 10/01/02, DC8 SRM 51-1-11, SRM 51-3-0, AND SRM 51-3-1. (S)
DURING ROUTINE C CHECK INSPECTION, FOUND IMPROPER REPAIR ON RT WING OUTBOARD SLOT VANE LEADING EDGE AT STATION XOLDO 67.000. REMOVED FASTENERS AS NEEDED TO PERFORM REPAIR. REMOVED EXISTING REPAIR. REMOVED DAMAGED AREA. PERFORMED NDT INSPECTION. NO CRACK, NO CORROSION FOUND. FABRICATED DOUBLERS, FILLERS, INTERNAL DOUBLERS. CLEANED, TREATED AND PRIMED AREA AND REPAIR PARTS. INSTALLED NEW FASTENERS AND REPAIR PARTS AT STATION XOLDI 6.224-XOLDO 67.000 IAW FAA FORM 8110-3 08378 DATED 07/11/2008, SEMAN DRAWING ED-4809 DATED 06/23/08, 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. (S)
DURING ROUTINE C CHECK INSPECTION, FOUND RT WING INBOARD FLAP UPPER SKIN DENTED AT STATION XW 104.000. REMOVED FASTENERS AS NEEDED TO PERFORM REPAIR. REMOVED DAMAGED SKIN. FABRICATED NEW SKIN. CLEANED, TREATED AND PRIMED AREA AND REPAIR PART. INSTALLED NEW FASTENERS AND REPAIR PARTS IAW DC8 SRM 57-7-1 FIGURE 1 ITEM "D", DC8 SRM 57-1-0 PAGE 1, SRM 51-1-21, DC8 SRM 51-1-8B, DC8 SRM 51-1-11, SRM 51-3-0 AND SRM 51-3-1. (S)
DURING ROUTINE C CHECK INSPECTION, FOUND RT WING OUTBOARD FLAP UPPER SKIN SHOWS WEAR AT STATION XF 211.000. REMOVED FASTENERS AS NEEDED TO PERFORM REPAIR. REMOVED DAMAGED AREA. FABRICATED NEW SKIN. CLEANED, TREATED AND PRIMED AREA AND REPAIR PART. INSTALLED NEW FASTENERS AND REPAIR PARTS IAW DC8 SRM 57-7-1 FIGURE 4 TR 57-94 DATED 10-01-02, DC8 SRM 57-1-0 PAGE 1, SRM 51-1-21, DC8 SRM 51-1-8B AND DC8 SRM 51-1-11. (S)
DURING ROUTINE C CHECK, FOUND IMPROPER REPAIR ON LT WING INBOARD SLOT VANE LEADING EDGE AT STATION XILD 7095.000 AND XS 247.000. REMOVED FASTENERS AS NEEDED TO PERFORM REPAIR. REMOVED EXISTING REPAIR. FABRICATED NEW SKIN. CLEANED, TREATED AND PRIMED AREA AND REPAIR PART. INSTALLED NEW FASTENERS AND PLATING IAW DC8 SRM 57-3-2 FIGURE 10 PAGE 22 ITEM "F", DC8 SRM 57-1-0 PAGE 1, SRM 51-1-21, DC8 SRM 51-1-8B, DC8 SRM 51-1-11, SRM 51-3-0, AND SRM 5-3-1. (S)
DURING ROUTINE C CHECK INSPECTION, FOUND LT WING INBOARD FLAP UPPER SKIN HAS IMPROPER REPAIR AT STATION XW 104.000. REMOVED FASTENERS AS NEEDED TO PERFORM REPAIR. REMOVED DAMAGED AREA. FABRICATED NEW SKIN. CLEANED, TREATED AND PRIMED AREA AND REPAIR PART. INSTALLED NEW FASTENERS AND REPAIR PARTS IAW DC8 SRM 57-7-1 FIGURE 1 ITEM "D", DC8 SRM 57-1-0 PAGE 1, SRM 51-1-21, DC8 SRM 51-1-8B, DC8 SRM 51-1-11, SRM 51-3-0, AND SRM 51-3-1. (S)
DURING ROUTINE C CHECK INSPECTION, FOUND RT WING INBOARD SLOT VANE LEADING EDGE HAS ELONGATED HOLES AT STATION XS 247.000. REMOVED FASTENERS AS NEEDED TO PERFORM REPAIR. REMOVED DAMAGED PLATING. FABRICATED NEW SKIN. CLEANED, TREATED AND PRIMED AREA AND REPAIR PART. INSTALLED NEW FASTENERS AND REPAIR PARTS AT STATION XILD 7095.000-XS 247.000 IAW DC8 SRM 57-3-2 FIGURE 10 PAGE 22 ITEM F, DC8 SRM 57-1-0 PAGE 1, SRM 51-1-21, DC8 SRM 51-1-8B, DC8 SRM 51-1-11, SRM 51-3-0, AND SRM 51-3-1. (S)
DURING ROUTINE C CHECK, FOUND IMPROPER REPAIR ON LT WING INBOARD SLOT VANE LEADING EDGE AT STATION XILD 7095.000 AND XS 247.000. REMOVED FASTENERS AS NEEDED TO PERFORM REPAIR. REMOVED EXISTING REPAIR. FABRICATED NEW SKIN. CLEANED, TREATED AND PRIMED AREA AND REPAIR PART. INSTALLED NEW FASTENERS AND PLATING IAW DC8 SRM 57-3-2 FIGURE 10 PAGE 22 ITEM F, DC8 SRM 57-1-0 PAGE 1, SRM 51-1-21, DC8 SRM 51-1-8B, DC8 SRM 51-1-11, SRM 51-3-0, AND SRM 51-3-1. (S)
DURING ROUTINE C CHECK INSPECTION, FOUND RT WING INBOARD SLOT VANE LEADING EDGE HAS ELONGATED HOLES AT STATION XS 247.000. REMOVED FASTENERS AS NEEDED TO PERFORM REPAIR. REMOVED DAMAGED PLATING. FABRICATED NEW SKIN. CLEANED, TREATED AND PRIMED AREA AND REPAIR PART. INSTALLED NEW FASTENERS AND REPAIR PARTS AT STATION XILD 7095.000 - XS 247.000 IAW DC8 SRM 57-3-2 FIGURE 10 PAGE 22 ITEM F, DC8 SRM 57-1-0 PAGE 1, SRM 51-1-21, DC8 SRM 51-1-8B, DC8 SRM 51-1-11, SRM 51-3-0, AND SRM 51-3-1. (S)
DURING ROUTINE C CHECK INSPECTION, FOUND RT WING INBD FLAP UPPER SKIN DENTED AT STATION XW 104.000. REMOVED FASTENERS AS NEEDED TO PERFORM REPAIR. REMOVED DAMAGED SKIN. FABRICATED NEW SKIN. CLEANED, TREATED AND PRIMED AREA AND REPAIR PART. INSTALLED NEW FASTENERS AND REPAIR PARTS IAW DC8 SRM 57-7-1 FIGURE 1 ITEM "D", DC8 SRM 57-1-0 PAGE 1, SRM 51-1-21, DC8 SRM 51-1-8B, DC8 SRM 51-1-11, SRM 51-3-0 AND SRM 51-3-1. (S)
DURING ROUTINE C CHECK INSPECTION, FOUND IMPROPER REPAIR ON RT WING OTBD SLOT VANE LEADING EDGE AT STATION XOLDO 67.000. REMOVED FASTENERS AS NEEDED TO PERFORM REPAIR. REMOVED EXISTING REPAIR. REMOVED DAMAGED AREA. PERFORMED NDT INSPECTION. NO CRACK, NO CORROSION FOUND. FABRICATED DOUBLERS, FILLERS, INTERNAL DOUBLERS. CLEANED, TREATED AND PRIMED AREA AND REPAIR PARTS. INSTALLED NEW FASTENERS AND REPAIR PARTS AT STATION XOLDI 6.224-XOLDO 67.000 IAW FAA FORM 8110-3 08378 DATED 07/11/2008, SEMAN DRAWING ED4809 DATED 06/23/08, 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. (S)
DURING ROUTINE C CHECK INSPECTION, FOUND LT WING INBOARD FLAP UPPER SKIN HAS IMPROPER REPAIR AT STATION XW 104.000. REMOVED FASTENERS AS NEEDED TO PERFORM REPAIR. REMOVED DAMAGED AREA. FABRICATED NEW SKIN. CLEANED, TREATED AND PRIMED AREA AND REPAIR PART. INSTALLED NEW FASTENERS AND REPAIR PARTS IAW DC8 SRM 57-7-1 FIGURE 1 ITEM "D", DC8 SRM 57-1-0 PAGE 1, SRM 51-1-21, DC8 SRM 51-1-8B, DC8 SRM 51-1-11, SRM 51-3-0, AND SRM 51-3-1. (S)
DURING ROUTINE C CHECK INSPECTION, FOUND LT WING OUTBOARD FLAP UPPER SKIN WORN AT STATION XF 211.000. REMOVED FASTENERS AS NEEDED TO PERFORM REPAIR. REMOVED DAMAGED AREA. FABRICATED NEW SKIN. CLEANED, TREATED AND PRIMED AREA AND REPAIR PART. INSTALLED NEW FASTENERS AND REPAIR PARTS IAW DC8 SRM 57-7-1 FIGURE 4 TR 57-94, DC8 SRM 57-1-0 PAGE 1, SRM 51-1-21, DC8 SRM 51-1-8B, DC8 SRM 57-7-1 FIGURE 4 ITEM "C" TR 57-94 DATED 10/01/02, DC8 SRM 51-1-11, SRM 51-3-0, AND SRM 51-3-1. (S)
DURING ROUTINE C CHECK INSPECTION, FOUND RT WING OUTBOARD FLAP UPPER SKIN SHOWS WEAR AT STATION XF 211.000. REMOVED FASTENERS AS NEEDED TO PERFORM REPAIR. REMOVED DAMAGED AREA. FABRICATED NEW SKIN. CLEANED, TREATED AND PRIMED AREA AND REPAIR PART. INSTALLED NEW FASTENERS AND REPAIR PARTS IAW DC8 SRM 57-7-1 FIGURE 4 TR 57-94 DATED 10-01-02, DC8 SRM 57-1-0 PAGE 1, SRM 51-1-21, DC8 SRM 51-1-8B, AND DC8 SRM 51-1-11. (S)
DURING CRUISE FROM KBWI NR 1 FIRE WARNING LIGHT AND BELL CAME ON MOMENTARILY THEN WENT OFF ENGINE WAS SHUTDOWN IAW COM PROCEDURE. THE CREW RETURNED TO KBWI AND LANDED WITHOUT INCIDENT. MAINTENANCE REPLACED HORSESHOE DETECTOR, LT CORE DETECTOR, RT CORE DETECTOR, AND RT FAN DETECTOR. OPERATIONAL CHECK GOOD IAW MM 26-10-1. AIRCRAFT WAS RETURNED TO SERVICE. (A)
DURING CLIMB-OUT FROM MLB AT FL350 NUMBER ONE ENGINE FLAMEOUT. THE CREW ACCOMPLISHED FLAMEOUT PROCEDURES AND DESCENDED TO FL210 FOR ENGINE RESTART. THE ENGINE RESTARTED NORMALLY AND THE CREW CONTINUED FLIGHT AND LANDED IN TOL WITHOUT INCIDENT. MAINTENANCE REMOVED AND REPLACED NUMBER ONE GEAR FUEL BLEED VALVE MOTOR. OPERATIONAL CHECK GOOD IAW CFM MAINTENANCE MANUAL 75-31-10 AND GMM 3.116. AIRCRAFT WAS RETURNED TO SERVICE.
DURING CRUISE FROM LPLA TO KBWI NR 1 ENGINE SHORT CIRCUIT LIGHT CAME ON, THE CREW ACCOMPLISHED EMERGENCY PROCEDURES AND SHUT DOWN NR 1 ENGINE AND LANDED WITHOUT INCIDENT AT KWRI. MAINTENANCE INSPECTED AND CLEANED NR 1 ENGINE FIRE SENSING ELEMENTS CONNECTORS, FOUND NO DEFECTS SYSTEM OPERATIONAL CHECK WAS GOOD IAW DACO DC8 MAINTENANCE MANUAL 26-10-1. AIRCRAFT WAS RETURNED TO SERVICE.
DURING CRUISE FROM KMLB, THE CREW NOTICE THE LEFT PNEUMATIC MANIFOLD READ'S 17 PSI LOWER THAN THE RIGHT SIDE, THE LEFT SIDE READ'S 20 PSI AND THE RIGHT SIDE READ'S 37 PSI. THE LEFT SIDE MANIFOLD COULD NOT REACH 35 PSI TO DO PRESSURE DECAY CHECK, THE LEFT SIDE ONLY WENT TO 28 PSI AT POWER. THE CREW RETURNED TO KMLB, AND LANDED WITHOUT INCIDENT. MAINTENANCE REMOVED AND REPLACED NR 1 AND NR 2 PNEUMATIC REGULATOR VALVE IAW DACO DC-8 MAINTENANCE MANUAL 36-12-1. OPERATIONAL CHECK WAS GOOD. AIRCRAFT WAS RETURNED TO SERVICE.
DURING APPROACH INTO KBWI, THE FLIGHT ATTENDANT NOTICED A FLASH AT THE CIRCUIT PANEL ABOVE THE RIGHT AFT SERVICE DOOR. THE CREW CONTINUED WITH THE APPROACH AND LANDED WITHOUT INCIDENT. MAINTENANCE INSPECTED AND FOUND POWER WIRES CONTACTING LATCH OTHER BEHIND TERMINAL BLOCK, REPOSITIONED WIRES IAW DC8 MAINTENANCE MANUAL 20-512-1. AIRCRAFT WAS RETURNED TO SERVICE.
AFTER TAKEOFF FROM RJTY, THE AIRCRAFT WOULD NOT PRESSURIZE. THE CREW RETURNED TO RJYT AND LANDED WITHOUT INCIDENT. MAINTENANCE INSPECTED THE AIRCRAFT AIR-CONDITIONING PACK SYSTEM AND PERFORMED AN OPERATIONAL CHECK OF THE AIRCRAFT PACK SYSTEM. THE AIRCRAFT SUCCESSFULLY PRESSURIZED DURING THE OPERATIONAL CHECK AND THE AIRCRAFT WAS RETURNED TO SERVICE.
DURING CRUISE FROM RJTY NUMBER ONE ENGINE FLAMED OUT AT FL340. THE CREW RETURNED TO RJTY AND LANDED WITHOUT INCIDENT. MAINTENANCE INSPECTED THE ENGINE, AND NO DEFECTS WERE FOUND. THE FUEL FILTER WAS REMOVED AND NO ABNORMAL CONTAMINATION WAS FOUND. NEW FUEL FILTERS WERE INSTALLED. MAINTENANCE ALSO INSPECTED THE FUEL SYSTEM AND FOUND THE NUMBER ONE MAIN SURGE BOX BAFFLE DOORS IN THE WRONG POSITIONS, AND THE NUMBER ONE TANK SELECTOR VALVE OUT OF RIG. REMOVED AND REINSTALLED THE SURGE BOX BAFFLE DOORS IN THE CORRECT POSITIONS, AND RIGGED THE SELECTOR VALVE. A NEGATIVE PRESSURE CHECK WAS PERFORMED ON THE FUEL FEED LINE TO THE ENGINE, ALL CHECKS WERE WITHIN LIMITS. OPERATIONAL CHECKS WERE SATISFACTORY, AND TH
DURING CLIMBOUT FROM RJTY AT FL390 NUMBER THREE ENGINE FLAMED OUT. THE CREW DESCENDED TO FL320 WITH IGNITERS IN BOTH AND OVERRIDE IN ALL ENGINES. APPROXIMATELY AT FL340 THE ENGINE RESTARTED, ALL INDICATIONS RETURNED TO NORMAL AND THE CREW CONTINUED THE FLIGHT TO WSAP, LANDING WITHOUT INCIDENT. MAINTENANCE INSPECTED THE ENGINE IAW CFM56 MM 71-00-00 FAULT TREE 51. ALL STATIC CHECKS WERE GOOD. THE FUEL FILTER WAS INSPECTED AND NO CONTAMINATION WAS FOUND. THE OPERATIONAL CHECK WAS GOOD AND THE AIRCRAFT WAS RETURNED TO SERVICE.
DURING CRUISE FROM FJDG TO WSAP NR 2 ENGINE FLAMED OUT. THE CREW CONTINUED TO WSAP WHERE THEY LANDED WITHOUT INCIDENT. MAINTENANCE INSPECTED THE ENGINE IAW ALL APPLICABLE DATA. NO DEFECTS WERE FOUND. THE FUEL FILTERS WERE INSPECTED, NO CONTAMINATION FOUND. NEW FUEL FILTERS WERE INSTALLED. MAINTENANCE PERFORMED ENGINE RUNS, ALL PARAMETERS WERE WITHIN LIMITS. THE AIRCRAFT WAS RETURNED TO SERVICE.
DURING CRUISE FROM RJTY TO WSAP AT FL 360 CABIN PRESSURE CONTINUED TO CLIMB. THE CREW PUT BOTH AIR CONDITIONING PACKS TO MAX FLOW AND TRIED TO MAINTAIN CABIN PRESSURE MANUALLY. ALL EFFORTS WERE UNSUCCESSFUL AND THE CABIN CONTINUED TO CLIMB PAST 10,000 FEET. THE CREW PERFORMED A RAPID DEPRESSURIZATION AND EMERGENCY DECENT. ALL OXYGEN MASKS SUCCESSFULLY DEPLOYED. ALL APPLICABLE CHECKLISTS WERE COMPLIED WITH. THE CREW RETURNED TO RJTY AND SAFELY LANDED. MAINTENANCE INSPECTED THE OUTFLOW SYSTEM AND FOUND SOME VISIBLE MOISTURE IN THE OUTFLOW VALVE. MAINTENANCE CLEANED AND LUBRICATED THE OUTFLOW VALVE AND ALL OPERATIONAL CHECKS WERE GOOD. THE AIRCRAFT DECAY CHECK WAS WITH IN LIMITS. THE AIRCRAFT WAS RETURNED TO SERVI
DURING CRUISE FROM RJTY TO FJDG WHILE CLIMBING FROM FL340 TO FL360 ALL FOUR MANIFOLD TEMP LIGHTS ILLUMINATED CAUSING THE LEFT AND RIGHT MANIFOLDS TO OVERTEMP. THE CREW DIVERTED TO RODN AND LANDED SUCCESSFULLY. MAINTENANCE REPLACED THE NUMBER 2 AND NUMBER 3 PRE-COOLER CONTROL VALVES. THE OPERATIONAL CHECK WAS GOOD ON THE GROUND AND THE AIRCRAFT WAS RETURNED TO SERVICE.
DURING CLIMBOUT FROM PKWA TO PHIK PASSING THROUGH FL 330 WITH PRESSURIZATION IN MANUAL MODE CABIN ALT CLIMBED RAPIDLY. UNABLE TO MAINTAIN CABIN WITH MANUAL CONTROL VALVE OR AUTO PRESS. AIRCRAFT RETURNED TO PKWA WITHOUT INCIDENT. MAINTENANCE FOUND OUTFLOW VALVE LINKAGE TO DRIVE SECTION DRY AND REQUIRING LUBE DMI'D AUTO PRESSURIZATION AND MANUAL OPERATION CHECKED OK AFTER LUBE. AIRCRAFT WAS RETURNED TO SERVICE.
IN CLIMB THRU 13000FT RAT 15 DEG, N1 92.0 EGT 880 DEG & RISING WHILE ACCELERATING TO 300KTS. TEMP 880 DEG APPROX 30 SEC BEFORE POWER WAS REDUCED. EGT CONTINUES TO RISE WHILE ATTEMPTING TO SET CLIMB POWER AT OTHER ALTITUDES. ENGINE WAS SLOW TO SPOOL ON T/O. T/S TREES IN CFM56 MM, INSPECTED ENGINE, PCV & EGT THERMOCOUPLE PROBES & HARNESS VISUALLY WITH NO DEFECTS NOTED. CHECKED -NO BLOW THRU- CIT SENSOR. INSPECTED, OPS & RIG CHECKED VSV WITH NO DEFECTS NOTED. INSPECTED, OPS & RIG CHECKED VBV SYSTEM, FOUND VBV STATIC RIG CHECK FAILS. RE-RIGGED VBV FEEDBACK CABLE, OPS CHECK NORMAL. MEC SPECIFIC GRAVITY LOW. ADJUSTED SPEC GRAVITY, PERFORMED MAX POWER ASSURANCE RUN, OPS CHECK GOOD. ACFT RETURNED TO SERVICE.
DURING INSPECTION CHECK WAS FOUND A CORROSION AT RIGHT WING LOWER SKIN OF CENTER EXTENDED LEADING EDGE AROUND WING STATION XFS 360.250, RT. CORROSION WAS REMOVED IAW DC8 SRM 51-1-8 PAGE 20, THICKNESS MEASUREMENT WAS PERFORMED IAW ASTME 797-01 AND IT WAS FOUND OUT OF LIMITS IAW DC8 SRM 57-2-0 PAGE 16. DAMAGE WAS REPAIRED IAW EO ATI-092805 AND EWO ATI-57-062. FAA FORM 8110-3 WAS ISSUED APPROVING THIS REPAIR.
DURING INSPECTION CHECK, FOUND A CORROSION ON ON UPPER SKIN AT PYLON NR 2 LEADING EDGE UPPER SKIN, LT. CORROSION WAS REMOVED IAW DC8 SRM 51-1-8 PAGE 20, THICKNESS MEASUREMENT WAS PERROMED IAW ASTME 797-01 AND IT WAS FOUND OUT OF LIMITS IAW DC8 SRM 57-2-0 PAGE 16. DAMAGE WAS REPAIRED IAW SRM 57-2-1 AND EWO ATI-57-060.
DURING INSPECTION CHECK, FOUND A CORROSION ON UPPER SKIN AT CENTER EXTENDED LEADING EDGE AROUND STA XW 257.500-LT. CORROSION WAS REMOVED IAW DC8 SRM 51-1-8 PAGE 20, THICKNESS MEASUREMENT WAS PERFORMED IAW ASTME 797-01 AND IT WAS FOUND OUT OF LIMITS IAW DC8 SRM 57-2-0 PAGE 16. DAMAGE WAS REPAIRED IAW SRM 57-2-1 FIGURE 38 AND EWO ATI-57-061.
DURING INSPECTION CHECK WAS FOUND A CORROSION ON UPPER SKIN AT OB EXTENDED LEADING EDGE AROUND STA. XFS 791.250 TO 816.000 - LT. DAMAGED AREA WAS CLEANED AND REPAIR DOUBLER WAS FABRICATED AND INSTALLED IAW SRM 57-2-1 FIGURE 38 AND EWO ATI-57-059.
DURING INSPECTION CHECK, CORROSION FOUND ON UPPER SKIN AT OUTBOARD PYLON NR 3 RT. UPPER SKIN AT OUTBOARD PYLON NR 3 WAS REPAIRED IAW SRM 57-2-1 FIG 38 AND EWO ATI-57-057.
DURING INSPECTION CHECK CORROSION WAS FOUND ON INNER EXTENDED LEADING EDGE OUTER UPPER SKIN AROUND STA XFS 207.500 - RT. DAMAGED AREA WAS BLENDED OUT AND REINFORCEMENT DOUBLER WAS FABRICATED AND INSTALLED IAW EO ATI-092305 AND EWO ATI-57-055. FAA FORM 8110-3 WAS ISSUED APPROVING THIS REPAIR.
DURING INSPECTION CHECK, CORROSION WAS FOUND ON CENTER EXTENDED LEADING EDGE OUTER LOWER SKIN AROUND STA XFS 304.00 - RT. DAMAGED AREA WAS REMOVED AND A REINFORCEMENT DOUBLER WAS FABRICATED AND INSTALLED IAW EO ATI-092205 AND EWO ATI-57-054. FAA FORM 8110-3 WAS ISSUED APPROVING THIS REPAIR.
DURING INSPECTION CHECK WAS FOUND A CORROSION ON CENTER EXTENDED LEADING EDGE LOWER SKIN AROUND STA XFS 710.50-RT. DAMAGED AREA WAS BLENDED OUT AND A REINFORCEMENT DOUBLER WAS FABRICATED AND INSTALLED IAW EO ATI-092905 AND EWO ATI-57-063. FAA FORM 8110-3 WAS ISSUED APPROVING THIS REPAIR.
DURING INSPECTION CHECK WAS FOUND A CORROSION ON THE UPPER SKIN AT OB PYLON NR 4-RT. DAMAGED AREA WAS CLEANED AND REPAIR DOUBLER WAS FABRICATED AND INSTALLED IAW SRM 57-2-1 FIG 38 AND EWO ATI 57-058.
DURING INSPECTION CHECK, FOUND CORROSION ON UPPER SKIN AT OUTBOARD EXTENDED LEADING EDGE AROUND STA XFS 591.250 - 603.750 - RT. CORROSION WAS REMOVED IAW SRM DC8 51-1-8 PAGE 20 AND THICKNESS WAS FOUND OUT OF LIMITS IAW DC8 SRM 57-2-0 PAGE 16 AND ASTME 79701. DAMAGE WAS REPAIRED IAW EWO ATI 57-056 AND SRM 57-2-1 FIG 38.
DURING INSPECTION CHECK, FOUND CORROSION ON CENTER EXTENDED LEADING EDGE OUTER LOWER SKIN AROUND STA XOLDI 6.225 - RT. CORROSION WAS REMOVED IAW DC8 SRM 51-1-8 PAGE 20 AND THICKNESS WAS FOUND OUT OF LIMITS IAW SRM 57-2-0 PAGE 16 (MAX: 0.063 IN, MIN: 0.035 IN). DAMAGE WAS REPAIRED IAW EWO ATI 57-053 AND EO ATI-092105. FAA FORM 8110-3 WAS ISSUED APPROVING THIS REPAIR.
DURING INSPECTION CHECK WAS FOUND A CORROSION ON RT WING CENTER LE UPPER EXTERIOR SURFACE, STA XW 408.343. SKIN WAS REPLACED IAW MFG DRAWING 5769857, RIVETS WERE INSTALLED IAW SRM 51-1-21 PAGE 1-7 AND PROTECTIVE TREATMENT WAS APPLIED IAW SRM 51-1-8 PAGE 13-16.
DURING INSPECTION CHECK, FOUND CORROSION ON HORIZONTAL STABILIZER TRAILING EDGE LOWER AND UPPER PANEL. REPAIR ACCOMPLISHED, REMOVED PANEL AND STIFFENER, FABRICATED AND INSTALLED NEW PANEL AND STIFFENER IN ACCORDANCE WITH DRAWINGS 55-05467-1, 55-05467-2, 55-05467-3, 55-05467-4 AND EWO ATI-55-010.
DURING INSPECTION CHECK WAS FOUND A CORROSION ON LT OB FLAP T/E PANEL LWD INNER SKIN, STA XF 415. SKIN WAS REPLACED IAW MFG DRAWING 5654758 (STA XW 407-XF415) AND RIVETS WERE INSTALLED IAW SRM 51-1-21 PAGE 1-7.
DURING INSPECTION CHECK WAS FOUND A CORROSION AND BONDED DOUBLERS DELAMINATED ON LT OB FLAP T/E UPPER INNER SKIN, STA XF 309.0 TO 333.0. SKIN WAS REPLACED IAW MFG DRAWING 5642970, RIVETS WERE INSTALLED IAW SRM 51-1-21 PAGE 1-7 AND PROTECTIVE TREATMENT WAS APPLIED IAW SRM 51-1-8 PAGE 13-16.
DURING INSPECTION CHECK, FOUND CORROSION ON LOWER CARGO DOOR AFT JAMB STA 560 LONGERON 25 TO 33 RT. CORROSION WAS REMOVED IAW DC8 SRM 51-1-8 PAGE 20, THICKNESS MEASUREMENT WAS PERFORMED IAW ASTM 797-0 AND IT WAS FOUND OUT OF LIMITS IAW SRM 53-2-0 PAGE 2P. DAMAGE WAS REMOVED AND REINFORCEMENT DOUBLER WAS INSTALLED IAW EO ATI-091805 AND EWO ATI-53-031.
DURING INSPECTION CHECK WAS FOUND LT OB FLAP T/E PANEL LWD INNER SKIN WITH CORROSION AND BONDED DOUBLER DELAMINANTED, STA XW2-XW91. SKIN ON LT IB FLAP WAS FABRICATED AND INSTALLED IAW MFG DRAWING 5652277, RIVETS WERE INSTALLED IAW SRM 51-1-21 PAGE 1-7.
DURING INSPECTION CHECK WAS FOUND A CORROSION ON LT IB FLAP T/E PANEL LWD OUTER SKIN, STA XW3 TO XW91.LT IB FLAP T/E PANEL LWD OUTER SKIN WAS REPLACED IAW MFG DRAWING 5652277, AND RIVETS WERE INSTALLED IAW SRM 51-1-21 PAGE 1-7.
DURING INSPECTION CHECK WAS FOUND A CORROSION AND BONDED DOUBLERS IN LT OB AILERON UPPER INNER SKIN, STA XA 621 TO XA 724. UPPER SKIN IN LT OB AILERON WAS FABRICATED AND INSTALLED IAW MFG DRAWING 5763133, AND RIVETS WERE INSTALLED IAW SRM 51-1-21 PAGE 1-7.
DURING INSPECTION CHECK, CORROSION WAS FOUND ON LOWER SKIN STA 1530-1536 LONGERON 31RH-31LH.CORROSION WAS REMOVED IAW SRM 51-1-8 PAGE 20, THICKNESS WAS MEASURED IAW ASTME 767-01 AND IT WAS FOUND OUT OF LIMITS. DAMAGE WAS REPAIRED, FABRICATION AND INSTALLATION AN EXTERNAL AND INTERNAL SPLICE, FINGER DOUBLER AND LONGERON STRAP IAW SRM 53-2-1 FIGURE 4 TR 53-172 AND EWO ATI 53-027. SPLICE FITTING PN: 4641326 AT STA FS 1530 WAS FABRICATED AND INSTALLED IAW SRM 51-1-21 PAGE 1-7.
DURING INSPECTION CHECK, FOUND A CORROSION ON FORMER STA 1530 LONGERON 28 - RT. CORROSION WAS REMOVED IAW DC8 SRM 51-1-8 PAGE 20, THICKNESS MEASUREMENT WAS PERFORMED IAW ASTME 797-01 AND IT WAS FOUND OUT OF LIMITS. DAMAGE WAS REPAIRED IAW SRM 53-2-5 FIG 8C-1 AND EWO ATI-53-034.
DURING INSPECTION CHECK WAS FOUND A CORROSION ON RT WING FLAP IB INTERIOR TRAILING EDGE PANEL PLATING. SKIN WAS REPLACED IAW MFG DRAWING 5652277 AND RIVETS WERE INSTALLED IAW SRM 51-1-21 PAGE 1-7.
DURING INSPECTION CHECK, FOUND AN INTERIM REPAIR ON INBOARD FLAP UPPER FWD PLATING BETWEEN STA XW91-80, RT. EXISTING DOUBLER WAS REMOVED AND A NEW REINFORCEMENT DOUBLER WAS INSTALLED IAW EO ATI-091105 AND EWO ATI 57-047.
DURING INSPECTION CHECK, FOUND CORROSION ON INTERNAL SKIN OF PASSENGER WINDOW STA 360 AND 380 LH. CORRODED AREA WAS REMOVED AND REPAIR DOUBLER WAS INSTALLED IAW EWO ATI 53-024, SRM 53-2-0 FIGURE 22A AND BOEING SERVICE REQUEST 1-129925991.
DURING INSPECTION CHECK, A LOOSE RIVET WAS FOUND ON MAIN CARGO DOOR SKIN BETWEEN STA 420-440-LT. AS TEMPORARY REPAIR BLIND RIVETS WILL BE INSTALLED IAW BOEING MESSAGE 1-136637626 AND EWO ATI 52-004. SOLID RIVETS OR HI-LOCKS MUST BE INSTALLED WITHIN 6000 CYCLES.
DURING INSPECTION CHECK WAS FOUND A CORROSION AND BONDED DOUBLER DELAMINATED ON LT WING INTERIOR UPPER SURFACE T/E, STA XW 700 - XW 736.500.SKIN WAS REPLACED IAW MFG DRAWING 5644654, RIVETS WERE INSTALLED IAW SRM 51-1-21 PAGE 1-7 AND ANTI-CORROSIVE TREATMENT WAS APPLIED IAW SRM 51-1-8 PAGE 13-16.
DURING INSPECTION CHECK, FOUND A CORROSION ON LT INBOARD FLAP LWD EXTERIOR SURFACE. SKIN ON LT INBOARD FLAP EXTERIOR SURFACE WAS REPLACED IAW DOUGLAS DRAWING 5642960, AND RIVETS WERE INSTALLED IAW SRM 51-1-21 PAGE 1-7.
DURING INSPECTION CHECK, FOUND A CORROSION ON RT ELEVATOR UPPER SURFACE, STA XE 246.875-XE 272. SKIN WAS REPLACED IAW DOUGLAS DRAWING 5654970 AND RIVETS WERE INSTALLED IAW DC8 SRM 51-1-21 PAGE 1-7.
DURING INSPECTION CHECK, FOUND A CORROSION ON AFT LOWER CARGO FWD DOOR SKIN, STA 1140 - RT. CORROSION WAS REMOVED IAW DC8 SRM 51-1-8 PAGE 20, THICKNESS MEASUREMENT WAS PERFORMED IAW ASTME 797-01 AND IT WAS FOUND OUT OF LIMITS IAW DC8 SRM 52-2-0 PAGE 22. DAMAGE WAS REPAIRED IAW EO ATI-091905 AND EWO ATI-52-003.
DURING INSPECTION CHECK WAS FOUND A OIL CAN ON LOWER SURFACE SKIN STA XE 279.125 TO 288.957 - LT. SKIN WAS REPLACED IAW DRAWING 5654970 ZONE 17 TO 21, RIVETS WERE INSTALLED IAW SRM 51-1-21 PAGE 1-7 AND PROTECTIVE TREATMENT WAS APPLIED IAW SRM 51-1-8 PAGE 13-16.
DURING INSPECTION CHECK, FOUND A CRACK ON LT ELEVATOR LOWER SURFACE, STA XE 149.000. FAIRING WAS FABRICATED AND REPLACED IAW DOUGLAS DRAWING 5655694 VIEW C-C, AND RIVETS WERE INSTALLED IAW DC8 SRM 51-1-21 PAGE 1-7.
DURING INSPECTION CHECK WAS FOUND A CORROSION ON UPPER SKIN AT LEADING EDGE STA XW 408 TO 454, LT.CORROSION ON UPPER SKIN AT LEADING EDGE STA XW 408 TO 454-LT WAS REPAIRED IAW SRM 57-2-1 FIGURE 38 AND EWO ATI 57-043.
DURING INSPECTION CHECK WAS FOUND CORROSION ON INTERNAL SKIN OF PASSENGER WINDOW STA 1120-1140, LEFT. CORRODED AREA WAS REMOVED AND REPAIR DOUBLER WAS INSTALLED IAW EWO ATI-53-021 AND SRM 53-2-0 FIGURE 22A, TR 53-170.
DURING INSPECTION CHECK WAS FOUND A OIL CAN ON LOWER SURFACE SKIN STA XE 89.718 TO 108.843-LT. REPAIR DOUBLER WAS INSTALLED IAW EWO ATI 55-013 AND SRM 55-2-1 FIG 2A.
DURING INSPECTION CHECK WAS FOUND A CORROSION ON DOUBLER AT LEADING EDGE OB SLOT UPPER DOOR LT. CORRODED DOUBLER WAS REMOVED AND NEW REPAIR DOUBLER WAS FABRICATED AND INSTALLED IAW SRM 57-2-1 FIG 12 AND EWO ATI-57-050.
DURING INSPECTION CHECK, FOUND A IMPROPER REPAIR ON FUSELAGE SKIN LOWER DOOR JAMB STA 340-360, LT. DAMAGE WILL BE REPAIRED IAW EWO ATI-53-016 AND FAA FORM 8110-3 MUST BE ISSUED.
DURING INSPECTION CHECK, FOUND A CORROSION ON INNER SKIN STA 1440-1460, LONGERON 22 - RT. CORROSION WAS REMOVED IAW DC8 SRM 51-1-8 PAGE 20, THICKNESS MEASUREMENT WAS PERFORMED IAW ASTM 797-01, AND IT WAS FOUND OUT OF LIMITS IAW DC8 SRM 53-2-0 PAGE 2P. DAMAGE WAS REPAIRED IAW SRM 53-2-1 FIGURE 7 AND EWO ATI 53-023.
DURING INSPECTION CHECK, CORROSION WAS FOUND ON LOWER SKIN STA 208-270 LONGERON 32RH-32 LT. CORROSION WAS REMOVED IAW SRM 51-1-8 PAGE 20, THICKNESS WAS MEASURED IAW ASTME 79701 AND IT WAS FOUND OUT OF LIMITS IAW SRM 53-2-0 PAGE2P. SKIN WAS REPLACED IAW DRAWING 5613862, RIVETS WERE INSTALLED IAW SRM 51-1-21 PAGE 1-7 AND SPLICE REPAIR WAS FABRICATED AND INSTALLED IAW SRM 53-2-1 FIGURE 4 TR 53-172 AND EWO ATI 53-028.
DURING INSPECTION CHECK, FOUND A IMPROPER REPAIR ON FUSELAGE SKIN STA 1500-1530, LONG 17-21, LT. DAMAGE WILL BE REPAIRED IAW EWO ATI-53-017 AND FAA FORM 8110-3 MUST BE ISSUED.
DURING INSPECTION CHECK, FOUND TWO IMPROPER PATCHES AND CORROSION ON RT WING INBOARD FLAP TOP SURFACE, STA XW 31 - XW 92. SKIN ON RT WING INBOARD FLAP WAS REPLACED IAW DOUGLAS DRAWING 5642960 AND RIVETS WERE INSTALLED IAW DC8 SRM 51-1-21 PAGE 1-7.
DURING INSPECTION CHECK, FOUND CHAFING ON CENTER SECTION AT WHEEL WELL VERTICAL WEB, AROUND STA 1060 RT. CHAFING DAMAGE WAS TRIMMED OUT, NEW WEB SEGMENT AND REPAIR DOUBLER STRAP WERE INSTALLED IAW EO ATI-091405 AND EWO ATI-53-025.
DURING INSPECTION CHECK, FOUND CHAFING ON CENTER SECTION AT WHEEL WELL VERTICAL WEB, AROUND STA 1060 LH. CHAFING DAMAGE WAS REMOVED, NEW WEB SEGMENT AND REPAIR DOUBLER STRAP WERE INSTALLED IAW EO ATI-091705 AND EWO ATI-53-029. FAA FORM 8110-3 WAS ISSUED APPROVING THIS REPAIR.
DURING INSPECTION CHECK WAS FOUND A CORROSION ON RT INBOARD FLAP EXTERIOR SURFACE, BETWEEN STA XW3-XW92 (VIEW LOOKING UP). RT WING INBOARD FLAP SKIN WAS REMOVED AND REPLACED IAW DOUGLAS DRAWING 5642960. RIVETS WERE INSTALLED IAW DC8 SRM 51-1-21 PAGE 1 TO 7.
DURING INSPECTION CHECK, FOUND A CORROSION ON INTERNAL SKIN OF PASSENGER WINDOW STA 1160-1180, LT. DAMAGE WILL BE REPAIRED IAW EWO ATI-53-020 AND SRM 53-2-0 FIGURE 22A, TR-53-170.
DURING INSPECTION CHECK, FOUND A CORROSION ON INTERNAL SKIN OF PASSENGER WINDOW STA 640-660, RT. DAMAGE WILL BE REPAIRED IAW EWO ATI-53-018 AND SRM 53-2-0 FIGURE 22A TR-53-170.
DURING INSPECTION CHECK, FOUND A CORROSION ON INTERNAL SKIN OF PASSENGER WINDOW STA 560-580, LT. DAMAGE WILL BE REPAIRED IAW EWO ATI-53-019 AND SRM 53-2-0 FIGURE 22A TR 53-170.
DURING INSPECTION CHECK, FOUND CORROSION ON RT HORIZONTAL STABILIZER UPPER PLATING AT OUTBOARD CENTER SECTION AROUND STA XE 173.656 BETWEEN AUXILIARY AND AFT UPPER SPAR CAP. CORRODED AREA WAS BLEND OUT AND REPAIR DOUBLER WAS INSTALLED IAW EO ATI 091505 AND EWO ATI 55-009. FAA FORM 8110-3 WAS ISSUED APPROVING THIS REPAIR.
DURING INSPECTION CHECK, FOUND A CORROSION ON LT WING OUTBOARD AILERON LWD SKIN, STA XW 565 TO XA 638. SKIN IN LT WING OUTBOARD AILERON WAS REMOVED AND REPLACED IAW DRAWING 5763133 AND RIVETS WERE INSTALLED IAW DC8 SRM 51-1-21 PAGE 1-7.
DURING INSPECTION CHECK, FOUND CORROSION ON LT RUDDER STA´S ZR 335.250, ZR 327 - 319, ZR 310.688, ZR 300 - 290. SKIN WAS REMOVED AND REPLACED IAW DOUGLAS DRAWING 5655077 VIEW A-B&C AND RIVETS WERE INSTALLED IAW DC8 SRM 51-1-21 PAGE 1-7.
DURING INSPECTION CHECK,CORROSION WAS FOUND ON STABILIZER UPPER TRAILING EDGE PLATING STA XE 28-RH. REPAIR ACCOMPLISHED, REMOVAL PANEL AND STIFFENER, FABRICATION AND INSTALLATION NEW PANEL AND STIFFENER IAW DRAWINGS 55-05467-1, 55-05467-2, 55-05467-3, 55-05467-4 AND EWO ATI-55-010.
DURING INSPECTION CHECK WAS FOUND A IMPROPER REPAIR ON WING LEADING EDGE, STA XW 257.50, RT. PERMANENT REPAIR WAS PERFORMED IAW EWO ATI 57-044 AND EO ATI-090905. FAA FORM 8110-3 WAS ISSUED APPROVING THIS REPAIR.
DURING INSPECTION CHECK, FOUND IMPROPER REPAIR ON RT HORIZONTAL STABILIZER L/E DOUBLER STA XFS 210-222.500. EXISTING DOUBLER WAS REMOVED AND A NEW REINFORCEMENT DOUBLER WAS INSTALLED IAW EO ATI 090805 AND EWO ATI-55-006.
DURING INSPECTION CHECK, FOUND LT WING UPPER SKIN PANEL AT STA XW 761.695 DISBONDED. SKIN WAS REMOVED AND REPLACED ON LT WING UPPER PANEL IAW DOUGLAS DRAWING 5644654, RIVETS WERE INSTALLED IAW DC8 SRM 51-1-21 PAGE 1-7 AND PROTECTIVE TREATMENT WAS APPLIED IAW DC8 SRM 51-1-8 PAGE 13-16.
DURING MAINTENANCE CHECK, FOUND RT OUTBOARD FLAP, INBOARD FLAP HINGE FITTING STA XF 219.459 CRACKED. DAMAGE WILL BE REPAIRED IAW EWO ATI-57-041 AND FAA FORM 8110-3 MUST BE ISSUED APPROVING THIS REPAIR.
DURING INSPECTION CHECK, FOUND A CRACK ON CENTER L/E SLOT DOOR PLATING AROUND STA XFS 510.222-LT. DAMAGE WAS REPAIRED IAW EO ATI-092705 AND EWO ATI 57-052.
DURING INSPECTION CHECK WAS FOUND RT OUTBOARD FLAP, INBOARD FLAP HINGE FITTING AT STA XF339.7332 CRACKED. DAMAGE WILL BE REPAIRED IAW EWO ATI-57-042 AND FAA FORM 8110-3 MUST BE ISSUED APPROVING THIS REPAIR.
DURING INSPECTION CHECK, FOUND SOME DENTS ON LT FUSELAGE TAIL CONE STA`S 1746, 1745 AND 1754. SKIN DENTS WILL BE REPAIRED IAW EWO ATI-53-013 AND FAA FORM 8110-3 MUST BE ISSUED APPROVING THIS REPAIR.
DURING INSPECTION CHECK WAS FOUND A OIL CAN ON LOWER SURFACE SKIN STA XE 104.051 TO 108.815 - LT. REPAIR SKIN AND REPAIR SPLICE WERE FABRICATED AND INSTALLED IAW SRM 55-2-1 FIG 2A AND EWO ATI 55-011.
DURING INSPECTION CHECK, FOUND A CORROSION ON LT WING EXTERIOR LWD SURFACE, REAR SPAR BETWEEN STA XW 736.500 - XW 761.0 AND STA XRS 700.000 - XW 736.000. SKIN WAS REMOVED AND REPLACED IAW DOUGLAS DRAWING 5644654, RIVETS WERE INSTALLED IAW DC8 SRM 51-1-21 PAGE 1-7 AND ANTI-CORROSIVE TREATMENT WAS APPLIED IAW DC8 SRM 51-1-8 PAGE 13-16.
DURING INSPECTION CHECK, FOUND A CRACK (1.5 INCHES) ON TOP PANEL PLATING OUTBOARD OF STA XCW 69.5 AND STRINGER 1 RT. DAMAGE WILL BE REPAIRED IAW EWO ATI 57-039 AND SRM 57-2-1 FIG 18A.
DURING INSPECTION CHECK, FOUND A IMPROPER REPAIR ON SKIN STA 460 LONGERON 28-29 RT. PERMANENT REPAIR WILL BE MADE IAW SRM 53-2-1 FIGURE 7 AND EWO ATI-53-012. THIS REPAIR CONSTITUTES A MAJOR REPAIR.
DURING INSPECTION CHECK, FOUND CORROSION ON LH HORIZONTAL STABILIZER LOWER SURFACE SKIN, STATION XE 235. BLEND OUT IN CORRODED AREA WAS PERFORMED AND REPAIR DOUBLER WAS INSTALLED IAW EO ATI-091305 AND EWO ATI 55-007. FAA FORM 8110-3 WAS ISSUED APPROVING THIS REPAIR.
DURING INSPECTION CHECK WAS FOUND A TEMPORAL REPAIR ON SKIN STA 235 LONGERON 24-25-LT. DAMAGE WILL BE REPAIRED IAW EWO ATI-53-011 AND SRM 53-2-1 FIGURE 7. THIS REPAIR CONSTITUTES A MAJOR REPAIR.
DURING INSPECTION CHECK, FOUND A CRACK ON TOP PANEL PLATING AT CENTER SPAR AND STA XRS 74.869 LT. DAMAGE WILL BE REPAIRED IAW EWO ATI 57-040 AND SRM 57-2-1 FIG 17.
DURING INSPECTION CHECK WAS FOUND A CORROSION ON WING UPPER SKIN STA XRS 40.869 REAR SPAR TO AUX SPAR - LT. REPORTED AREA WAS BLENDED OUT AND REINFORCEMENT DOUBLER WAS FABRICATED AND INSTALLED IAW EO ATI-091005 AND EWO ATI 57-045. FAA FORM 8110-3 WAS ISSUED APPROVING THIS REPAIR.
DURING INSPECTION CHECK, FOUND STRESS CORROSION CRACK ON RT WING UPPER EXTERIOR SURFACE STA XRS74 STRINGERS 9 TO 15. DAMAGE WILL BE REPAIRED IAW EWO ATI 57-038 AND FAA FORM 8110-3 MUST BE ISSUED APPROVING THIS REPAIR.
DURING INSPECTION CHECK, FOUND A CRACKED FITTING LONGERON 24 STA 857.125 BATH TUB RT. REPAIR WILL BE MADE IAW EWO ATI 53-015 AND SRM 53-2-2 FIGURE 5, TEMPORARY REVISION 53-123.
DURING INSPECTION CHECK, FOUND A CRACKED FITTING, LONGERON 24 STA 902 LT. REPAIR WILL BE MADE IAW EWO ATI 53-014 AND SRM 53-2-2 FIG 5 TEMPORARY REVISION 53-123.