N825BX
Operators of this aircraft
Who operated this tail, and how firmly we know it.
| Operator | Role | Period | Basis |
|---|---|---|---|
| AIR TRANSPORT INTERNATIONAL INC (IXXA) | Operator | on 2001-12-14 | Operator named in NTSB report |
Accident & incident history
Operated by Air Transport International (per NTSB report)
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.
249 reports on file, 1995-01-18 – 2008-09-23.
Part: HYDRAULIC SYSTEM — LOW
DURING CRUISE FROM KSJC TO KRFD, FLT ENGINEER NOTICED HYDRAULIC QUANTITY INDICATOR WAS AT THE BOTTOM OF NORMAL QUANTITY, DID NOT DROP ANY FURTHER DURING THE REST OF THE FLT. THE CREW LANDED IN KTOL WITHOUT FURTHER INCIDENT. MX SERVICED HYDRAULIC SYS, OPS CHECK GOOD IAW DACO DC8 MM 29-00-00. AC WAS RETURNED TO SERVICE.
Part: HOSE — LEAKING (HYD SYSTEM)
AT TOP OF DECENT, THE ACFT LOST HYDRAULIC FLUID DOWN TO THE STAND PIPE. MAINT INSPECTED AND FOUND NR 3 ENGINE HYDRAULIC PUMP HOSE LEAKING, REPLACED NR 3 ENGINE HYDRAULIC PUMP HOSE. OPS CHECK GOOD IAW MM 29-16. AC WAS RETURNED TO SERVICE. (K)
Part: HYDRAULIC SYSTEM — FAILED
AT TOP OF DECENT, THE ACFT LOST HYDRAULIC FLUID DOWN TO THE STAND PIPE. OPEN. (K)
Part: SWITCH — BROKEN (OVERRIDE)
DURING CLIMB-OUT, OVER RIDE TOGGLE SWITCH BROKE OFF. AIRCRAFT RETURNED TO DEPARTURE WITHOUT FURTHER INCIDENT. MAINTENANCE REMOVED AND REPLACED OVER RIDE SWITCH; OPS CHECK GOOD IAW UAL MM 74-20-36. (K)
Earlier reports · 1995–2006 · 245 reports
2006
Part: SKIN — MISREPAIRED (T/E FLAP) · airframe 88,788 hrs · 35,270 cycles
DURING ROUTINE C CHECK INSPECTION, FOUND LEFT INBOARD FLAP UPPER SKIN HAS NON STANDARD REPAIR AT STATION XW104.000. REMOVED EXISTING SKIN WITH NON STANDARD REPAIR. FABRICATED NEW SKIN (AL 2024 T3 0.040â). CLEANED, TREATED AND PRIMED AREA AND NEW SKIN INTERNAL SURFACE. APPLIED SEALANT TO FAYING SURFACES. INSTALLED NEW SKIN IAW DC8 SRM 51-1-21, DC8 SRM 57-1-0 PAGE 1, DC8 SRM 57-7-1 FIG 1 PAGE 2 ITEM âDâ, DC8 SRM 51-1-8B, AND DC8 SRM 51-1-11.
Part: SKIN — CRACKED (ZONE 600) · airframe 88,788 hrs · 35,270 cycles
DURING ROUTINE C CHECK INSPECTION, FOUND NR 4 ALTERNATE TANK CRACKED AT STATION XW485.000, CONFIRMED WITH NDT. REMOVED FASTENERS. REMOVED DAMAGED AREA. PERFORMED NDT INSPECTION. NO CRACKS OR CORROSION FOUND. FABRICATED REPAIR PARTS. CLEANED TREATED AND PRIMED AREA AND REPAIR PARTS. APPLIED SEALANT TO FAYING SURFACES. INSTALLED REPAIR PARTS IAW DC-8 SRM 51-1-20D, DC-8 SRM 51-3-1, DC-8 NDT SPM PART 06-10-01-001, DC-8 SRM 51-1-12 PAGES 7-25, DC-8 SRM 51-1-12, BOEING MSG NR 1-228078928-5 DATED 09-18-06, SEMAN DRAWING ED 4332, SEMAN ENGINEERING ORDER NUMBER 2006729 DATED 10-09-06, AND COMPLETED FAA FORM 8100-9 DATED 10-09-06.
Part: FITTING — CRACKED (BS 1212 L29R) · airframe 88,788 hrs · 35,270 cycles
DURING ROUTINE C-CHECK INSPECTION FOUND FITTING CRACKED AT STA 1212.000 LONGERON 29 RT. REPLACED FITTING AT STA 1212.000 LONGERON 29 RT. IAW SRM 51-1-20D.
Part: SKIN — MISREPAIRED (T/E FLAP) · airframe 88,788 hrs · 35,270 cycles
DURING ROUTINE C CHECK INSPECTION, FOUND RIGHT WING OUTBOARD FLAP LEADING EDGE UPPER SKIN WITH NON STANDARD REPAIR AT STATION XF211.000. REMOVED SKIN WITH NON STANDARD REPAIR. FABRICATED NEW SKIN. CLEANED TREATED AND PRIMED AREA AND NEW SKIN INTERNAL SURFACE. APPLIED SEALANT TO FAYING SURFACES. INSTALLED NEW SKIN IAW DC-8 SRM 57-7-1 FIG 4 PAGES 2 OF 2 TR NR 57-94 DATE 10-01-02, DC-8 SRM 57-1-0, DC-8 SRM 57-7-1 FIG 4 PAGES 2 OF 2 ITEM âCâ, DC-8 SRM 51-1-8B, DC-8 SRM 51-1-11, AND DC-8 SRM 51-1-21.
Part: SKIN — MISREPAIRED (ZONE 600) · airframe 88,788 hrs · 35,270 cycles
DURING ROUTINE C CHECK INSPECTION FOUND RIGHT WING OUTBOARD FLAP UPPER SKIN WITH NON STANDARD REPAIR AT STATION XF445.000. REMOVED SKIN WITH EXISTING NON STANDARD REPAIR. FABRICATED NEW SKIN AND DOUBLER. BONDED BOTH PARTS WITH HYSOL. CLEANED, TREATED AND PRIMED AREA AND INTERNAL SURFACE. APPLIED SEALANT TO FAYING SURFACE. INSTALLED NEW SKIN IAW DC-8 SRM 57-7-1 FIG 4 TR NR 57-94 DATE 10-01-02, DC-8 SRM 57-1-0 PAGE 1, DC-8 SRM 57-7-1 FIG 4 PAGE 2 OF 2 ITEM âUâ AND âQâ, DC-8 SRM 51-1-9, DC-8 SRM 51-1-8B, DC-8 SRM 51-1-11, AND DC-8 SRM 51-1-21.
Part: SKIN — MISREPAIRED (T/E FLAP) · airframe 88,788 hrs · 35,270 cycles
DURING ROUTINE C CHECK INSPECTION, FOUND RIGHT WING OUTBOARD FLAP UPPER SKIN WITH NON STANDARD REPAIR AT STATION XF360.000. REMOVED SKIN WITH EXISTING NON STANDARD REPAIR. FABRICATED NEW SKIN, AND DOUBLER. BONDED BOTH PARTS WITH HYSOL. CLEANED, TREATED AND PRIMED AREA AND INTERNAL SURFACE. APPLIED SEALANT TO FAYING SURFACES. INSTALLED PANEL PLATING IAW DC-8 SRM 57-7-1 FIG 4 TR NR 57-94 DATE 10-01-02, DC-8 SRM 57-1-0 PAGE 1, DC-8 SRM 51-1-21, DC-8 SRM 57-7-1 FIG 4 PAGE 2 OF 2 TR NR 57-94 ITEM âPâ AND âQâ, DC-8 SRM 51-1-9, DC-8 SRM 51-1-8B, DC-8 SRM 51-1-11, AND DC-8 SRM 51-1-21.
Part: SKIN — MISREPAIRED (FUSELAGE) · airframe 88,788 hrs · 35,270 cycles
DURING ROUTINE C CHECK INSPECTION, FOUND EXISTING DOUBLER IMPROPER AT STATION 600.000 LONGERON 30 RIGHT. REMOVED EXISTING DOUBLER. TRIMMED OUT DAMAGED AREA. FABRICATED EXTERNAL REPAIR DOUBLER (AL 7075 T6 0.125), INTERNAL FINGER DOUBLER (AL 7075 T6 0.050â), AND FILLER (AL 7075 T6 0.100). TAPERED REPAIR DOUBLER. CLEANED, TREATED AND PRIMED AREA, AND REPAIR PARTS. APPLIED SEALANT TO FAYING SURFACES. INSTALLED REPAIR PARTS IAW DC-8 SRM 53-2-1 FIG 7 SHEET 1, 2, 5, DC-8 SRM 51-1-21, DC-8 SRM 53-2-1 FIG 7, SHEET 1,3, AND 5, DC-8 SRM 53-4-1 FIG 1 PAGES 3-4 ITEM âAâ, DC-8 SRM 51-9-0 FIG 68A PAGE 10A, DC-8 SRM 51-10-0 FIG 2 SHEET 6 PAGE 30, DC-8 SRM 51-1-8B, DC-8 SRM 51-1-11, DC8 SRM 53-2-1 FIG 7 SHEET 1, 3, AND 5,
Part: SKIN — MISREPAIRED (ZONE 300) · airframe 88,788 hrs · 35,270 cycles
DURING ROUTINE C CHECK INSPECTION, FOUND RIGHT ELEVATOR UPPER SKIN HAS NON STANDARD REPAIR FROM STATION XE116.000 TO STATION XE79.000. REMOVED SKIN WITH EXISTING NON STANDARD REPAIR. FABRICATED NEW SKIN AND FINGER DOUBLER. BONDED BOTH PARTS WITH HYSOL IAW DC-8 SRM 51-1-9. CLEANED, TREATED AND PRIMED AREA AND NEW SKIN INTERNAL SURFACE. APPLIED SEALANT TO FAYING SURFACES. INSTALLED NEW SKIN. BALANCED ELEVATOR. FOUND WITHIN OF TOLERANCE MOMENTS: 1453.88 IN-LBS IAW DC-8 SRM 55-4-1 FIG 1 SHEET 1-2, DC-8 SRM 55-1-0 PAGE 1, DC-8 SRM 51-1-21, DC-8 SRM 55-4-1 FIG 1 SHEET 1-2 ITEM âEâ AND âFâ, DC-8 SRM 51-1-8B, DC-8 SRM 51-1-11, DC-8 SRM 51-1-21, AND DC-8 SRM 51-4-4 PAGES 1-3.
Part: SKIN — MISREPAIRED (T/E FLAP) · airframe 88,788 hrs · 35,270 cycles
DURING ROUTINE C CHECK INSPECTION, FOUND RIGHT INBOARD FLAP UPPER SKIN HAS NON STANDARD REPAIR AT STATION XW105.000. REMOVED EXISTING SKIN WITH NON STANDARD REPAIR. FABRICATED NEW SKIN (AL 2024 T3 0.050â), AND DOUBLER (AL 2024 T3 0.032â). BONDED SKIN AND DOUBLER WITH HYSOL. CLEANED, TREATED AND PRIMED AREA AND SKIN INTERNAL SURFACE. INSTALLED NEW SKIN IAW DC8 SRM 51-1-21, DC8 SRM 57-7-1 FIG 1 PAGE 2, DC8 SRM 57-1-0 PAGE 1, DC8 SRM 57-7-1 FIG 1 PAGE 2 ITEM âFâ AND âNâ, DC8 SRM 51-1-9, AND DC8 SRM 51-1-8B.
Part: SKIN — CRACKED (ZONE 600) · airframe 88,788 hrs · 35,270 cycles
DURING ROUTINE C CHECK INSPECTION, FOUND RIGHT WING INBOARD AILERON LEADING EDGE SKIN CRACKED AT STATION XD525.000. REMOVED DAMAGED SKIN. FABRICATED NEW SKIN. CLEANED, TREATED AND PRIMED AREA AND NEW SKIN INTERNAL SURFACE. APPLIED SEALANT TO FAYING SURFACES. INSTALLED NEW SKIN IAW DC-8 SRM 57-8-1 FIG 1 PAGE 2, DC-8 SRM 57-1-0 PAGE 1, DC-8 SRM 57-8-1 FIG 1 PAGE 2 ITEM âRâ, DC-8 SRM 51-1-8B, DC-8 SRM 51-1-11 AND, DC-8 SRM 51-1-21.
Part: CLAMP — IMPROPER (NR 2 PYLON) · airframe 88,788 hrs · 35,270 cycles
DURING ROUTINE C CHECK INSPECTION, FOUND ON NUMBER 2 PYLON ACCESS DOOR NUMBER 297, GENERATOR FEEDER CABLES ATTACH CLAMP IMPROPER. REMOVED FASTENERS. REMOVED DAMAGED AREA. FABRICATED REPAIR PARTS, (AL 2024 T3 0.016). BONDED BOTH PARTS WITH HYSOL. CLEANED, TREATED AND PRIMED AREA AND INTERNAL SURFACE OF REPAIR PARTS. INSTALLED REPAIR PARTS IAW DC8 SRM 55-2-1 FIG 11 SHEET 1, 4, 9, 11, 12, AND 13, DC-8 SRM 51-1-21, DC-8 SRM 55-4-1 FIG 1 SHEET 1, AND 2 ITEM E AND F, DC-8 SRM 51-1-9, AND DC8 SRM 51-1-8B.
Part: FRAME — CORRODED (BS 600) · airframe 88,788 hrs · 35,270 cycles
DURING ROUTINE C-CHECK INSPECTION, FOUND EXISTING FRAME REPAIR CORRODED AT STA 600 BETWEEN LONGERON 36 AND LONGERON 35 RT. REMOVED EXISTING REPAIR. FABRICATED NEW REPAIR DOUBLER. INTERNAL FINGER DOUBLER AND FILLER. CLEANED, TREATED AND PRIMED AREA AND REPAIR PARTS. APPLIED SEALANT TO FAYING SURFACES. INSTALLED REPAIR PARTS IAW SRM 53-2-1 FIG 7 SHEET 1-3-5, SRM 51-1-21, SRM 51-1-20D, SRM 51-3-1, SRM 53-2-1 FIG 7, SHEET 1-3-5, SRM 53-5-1 FIG 1 PAGE 2 ITEM (E), SRM 51-1-8B, AND SRM 51-1-11.
Part: LONGERON — CORRODED (BS 1566-1766) · airframe 88,788 hrs · 35,270 cycles
DURING ROUTINE C CHECK INSPECTION, FOUND LONGERON 34 RIGHT CORRODED BETWEEN STATION 1566.000 AND STATION 1766.000. REMOVED CORROSION, FOUND OUT OF LIMITS. REMOVED FASTENERS AND REMOVED DAMAGED SECTION. FABRICATED NEW REPAIR PARTS. CLEANED, TREATED AND PRIMED AREA. APPLIED SEALANT TO FAYING SURFACES. INSTALLED NEW REPAIR PARTS IAW DC-8 SRM 53-2-2 FIG 4A, DC-8 SRM 51-1-8 PAGES 17-18, DC-8 SRM 53-2-0 PAGE 2P, DC-8 SRM 53-2-2 FIG 4, DC-8 SRM 53-2-1 FIG 7, SHEET 1 ITEM âAâ, DC-8 SRM 51-2-0 FIG 50 SHEET 27, DC-8 SRM 53-2-2 FIG 10 TR NR 53-193 DATED 03-15-04, DC-8 SRM 51-1-8B, DC-8 SRM 51-1-11, DC-8 SRM 51-1-20D, AND DC-8 SRM 51-3-1.
Part: SKIN — CRACKED (BS 405 L12R) · airframe 88,788 hrs · 35,270 cycles
DURING ROUTINE C CHECK INSPECTION FOUND EXTERNAL SKIN CRACKED AT STATION 405.000, LONGERON 12 RIGHT. CORRECTIVE ACTION: REMOVED FASTENERS. REMOVED DAMAGED AREA. FABRICATED REPAIR PARTS. PERFORMED NDT INSPECTION, NO CRACKS OR CORROSION FOUND. CLEANED, TREATED AND PRIMED AREA AND REPAIR PARTS. APPLIED SEALANT TO FAYING SURFACES. INSTALLED REPAIR PARTS. IAW DC-8 SRM 51-3-1, DC-8 SRM 51-1-20D, DC8 NDT SPM PART 06-10-01-011, DC-8 SRM 51-1-8B, DC-8 SRM 51-1-11, FAA FORM 8100-9 DATED 09-26-06, BOEING MSG # 1-22835486-7 DATED 09-26-06, ROD SKETCH 06-09-25-002, AND SEMAN ENGINEERING ORDER NUMBER 2006727 DATED 09-26-06.
Part: LONGERON — CORRODED (BS 610 S32L) · airframe 88,788 hrs · 35,270 cycles
DURING ROUTINE C-CHECK, INSPECTION FOUND LONGERON 32 LT CORRODED AT STA 610.000. REMOVED CORROSION, FOUND OUT OF LIMITS. REMOVED FASTENERS AND REMOVED DAMAGED SECTION. FABRICATED NEW REPAIR PARTS. CLEANED, TREATED AND PRIMED AREA. APPLIED SEALANT TO FAYING SURFACES. INSTALLED NEW REPAIR PARTS. IAW SRM 53-2-2 FIG. 4A, SRM 53-4-1 FIG 27 ITEM (U), SRM 51-2-0 FIG. 50 SHEET 25, SRM 53-2-2 FIG. 10 SHEET 4, TR NR 53-193 DATE 03-15-04, SRM 53-2-2 FIG. 10 SHEET 1-3. TR NR 53-153 DATE 12-10-02. SRM 51-1-1 PAGES 1, 13, 17, SRM 51-1-8B, SRM 51-1-11, SRM 51-1-20D, AND SRM 51-3-1.
Part: SKIN — MISREPAIRED (NR 2 NACELLE) · airframe 88,788 hrs · 35,270 cycles
DURING ROUTINE C CHECK INSPECTION, FOUND A NON STANDARD REPAIR ON NUMBER 2 PYLON AT STATION XAR0.000. REMOVED EXISTING NON STANDARD REPAIR FROM STATION XAR0.000 TO STATION XE60.000. REMOVED DAMAGED AREA. FABRICATED REPAIR PARTS. BONDED PARTS WITH HYSOL. CLEANED, TREATED AND PRIMED AREA AND REPAIR PARTS. INSTALLED REPAIR PARTS IAW DC-8 SRM 54-3-1, DC-8 SRM 51-1-21, DC-8 SRM 51-1-9, AND DC-8 SRM 51-1-8B.
Part: FITTING — CRACKED (BS 1220 S27R) · airframe 88,788 hrs · 35,270 cycles
DURING ROUTINE C-CHECK INSPECTION, FOUND FITTING CRACKED STA 1220.000 BETWEEN LONGERON 27 RT AND LONGERON 29 RT. REMOVED CRACKED FITTING. FABRICATED NEW FITTING. HEAT TREATED NEW FITTING. PERFORMED NDT INSPECTION, NO CRACKS FOUND. CLEANED, TREATED AND PRIMED AREA AND NEW FITTING. INSTALLED FITTING IAW SRM 51-3-0, SRM 51-3-1, SRM 51-1-1 PAGES 1, 13, 17, NDT SPM PART 08-00-02 TO 07, AND SRM 51-1-8B.
Part: FITTING — CRACKED (LT MLG) · airframe 88,788 hrs · 35,270 cycles
DURING ROUTINE C CHECK INSPECTION, FOUND LEFT MAIN LANDING GEAR LEFT TRAPEZOIDAL FITTING WEB CRACKED AT STATION 902.000. REMOVED CRACKED TRAPEZOIDAL FITTING. CLEANED, TREATED AND PRIMED AREA. INSTALLED NEW TRAPEZOIDAL FITTING AND REINSTALLED INBOARD AND OUTBOARD SPLICE FITTINGS IAW DC-8 SRM 53-1-0 PAGE 1, DC-8 SRM 51-3-0 DC-8 SRM 51-1-8B, DC-8 SRM 51-1-20D, DC-8 SRM 51-1-21, AND DOUGLAS DRAWING NUMBER 5750127.
Part: FITTING — CRACKED (ZONE 100) · airframe 88,788 hrs · 35,270 cycles
DURING ROUTINE C-CHECK INSPECTION FOUND A CRACKED FITTING AT STATION 1260.000 LONGERON 35 RIGHT. REMOVED CRACKED FITTING. FABRICATED FITTING (AL PLATE 7075 T6 51). PERFORMED NDT INSPECTION. CLEANED, TREATED AND PRIMED AREA, AND FITTING. INSTALLED FITTING. IAW SRM 51-1-20D, SRM 51-3-1, SRM 51-1-20D, SRM 51-1-8B, NDT SPM PART 08-00-02 TO 07, ATI REPAIR SPECIFICATION NR 2003-05, AND DWG NR 3750277.
Part: SKIN — MISREPAIRED (RUDDER) · airframe 88,788 hrs · 35,270 cycles
DURING ROUTINE C-CHECK INSPECTION FOUND NON STANDARD REPAIR ON THE LEFT HAND SIDE OF THE RUDDER FROM STATION ZR 178.000 TO STATION ZR 188.781. REMOVED SKIN WITH NON STANDARD REPAIR. FABRICATED NEW SKIN (AL 2024 T3 0.040). CLEANED, TREATED, AND PRIMED AREA, AND NEW SKIN. APPLIED SEALANT TO FAYING SURFACES, AND INSTALLED NEW SKIN. BALANCED RUDDER IAW DC-8 SRM 51-4-6 PAGES 1-5 MOMENT: 250325 IN-LBS IAW DC8 SRM 55-6-1 FIG 1 PAGE 2, DC8 SRM 55-1-0, DC-8 SRM 51-1-21, DC-8 SRM 55-6-1 FIG 1 PAGE 2 ITEM -C-, DC-8 SRM 51-1-8B, DC-8 SRM 51-1-11, AND DC8 SRM 51-1-21.
Part: FITTING — CRACKED (BS 1160) · airframe 88,788 hrs · 35,270 cycles
DURING ROUTINE C CHECK INSPECTION, FOUND FRAME FITTING CRACKED AT STATION FS 1160.000 LONGERON 27 RIGHT RBL 44. REMOVED CRACKED FITTING. FABRICATED NEW FITTING. HEAT TREATED NEW FITTING. PERFORMED NDT INSPECTION. NO CRACKS OR CORROSION FOUND. CLEANED, TREATED AND PRIMED AREA AND NEW FITTING. INSTALLED NEW FITTING IAW DC-8 SRM 51-3-1, DC-8 SRM 51-1-20D, DC-8 SRM 51-1-1 PAGES 1, 13, 17, DC-8 NDT SPM PART 08-00-02 TO 07, DC-8 SRM 51-1-8B, AND SEMAN DRAWING NUMBER 4708061.
Part: FITTING — CRACKED (ZONE 700) · airframe 88,788 hrs · 35,270 cycles
DURING ROUTINE C CHECK INSPECTION, FOUND RIGHT MAIN LANDING GEAR RIGHT HAND TRAPEZOIDAL FITTING OUTBOARD FLANGE CRACKED, AT STATION 902.000. REMOVED CRACKED TRAPEZOIDAL FITTING. CLEANED, TREATED AND PRIMED AREA. INSTALLED NEW TRAPEZOIDAL FITTING AND OUTBOARD SPLICE FITTING, P/N 5894269-4 AND REINSTALLED INBOARD, SPLICE FITTING IAW DC-8 SRM 53-1-0 PAGE 1, DC-8 SRM 51-3-0,DC-8 SRM 51-1-8B, DC-8 SRM 51-1-20D, DC-8 SRM 51-1-21, DC-8 SRM 51-3-0, DC-8 SRM 51-3-1DOUGLAS DRAWING NUMBER 5750127 AND NUMBER 57500092.
Part: FITTING — CRACKED (BS 240) · airframe 88,788 hrs · 35,270 cycles
DURING ROUTINE C-CHECK INSPECTION FOUND A CRACKED FITTING AT STATION 240.000 LONGERON 36. REMOVED CRACKED FITTING. FABRICATED FITTING (AL PLATE 7075 T6 51). PERFORMED NDT INSPECTION. NO CRACKS OR CORROSION FOUND. CLEANED, TREATED AND PRIMED AREA, AND FITTING. INSTALLED FITTING. IAW SRM 51-1-20D, SRM 51-3-1. SRM 51-1-20D, SRM 51-1-8B, NDT SPM PART 08-00-02 TO 07, AND ATI REPAIR SPECIFICATION NR 2003-05 AND DWG NR 4705984.
Part: LONGERON — CRACKED (FUSELAGE) · airframe 88,788 hrs · 35,270 cycles
DURING ROUTINE C-CHECK INSPECTION FOUND CRACKED LONGERON AT STATION 1770.000 LONGERON 17 LEFT. REMOVED DAMAGED LONGERON. CLEANED, TREATED, AND PRIMED AREA, AND NEW LONGERON. INSTALLED LONGERON (EXTRUSION P/N S1616757) IAW DC8 SRM 53-1-0, DC-8 SRM 51-1-20D, DC-8 SRM 51-1-8B, DC8 SRM 53-5-1 FIG 7 SHEET 1 PAGE 22 ITEM -B-, DC-8 SRM 51-2-0 FIG 50 SHEET 37, DC-8 SRM 51-1-21, DC-8 SRM 51-3-0, DC8 SRM 51-1-20D, AND DC8 SRM 51-3-1.
Part: FRAME — MISREPAIRED (BS 1580 S20-21L) · airframe 88,788 hrs · 35,270 cycles
DURING ROUTINE C-CHECK INSPECTION FOUND FRAME WITH NON STANDARD REPAIR AT STATION 1580.000 BETWEEN LONGERON 20 LT AND LONGERON 21 LT. REMOVED FASTENERS. REMOVED DAMAGED AREA. PERFORMED NDT INSPECTION, AFTER DAMAGE REMOVED, NO CRACKS OR CORROSION FOUND. FABRICATED REPAIR DOUBLER (AL 7075 T6 0.071), INTERNAL DOUBLER AND SKIN FILLER. 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 51-1-20D, SRM 51-3-1, SRM 51-1-8B, SRM 51-1-11, NDT SPM PART 06-10-01-001, DWG NR ED 4325 DATE 09-15-06, EO NR 2006712 DATE 09-29-06. COMPLETED FAA FORM 8110-3 NR 06464 DATE 09-29-06.
Part: FITTING — CORRODED (FUSELAGE) · airframe 88,788 hrs · 35,270 cycles
DURING ROUTINE C CHECK INSPECTION, FOUND FITTING CORRODED AT STATION 75.000, LONGERON 29 LEFT. REMOVED CORROSION. FOUND OUT ALLOWABLE LIMITS. REMOVED DAMAGED FITTING. CLEANED, TREATED AND PRIMED AREA. INSTALLED NEW FITTING IAW DC-8 SRM 51-1-21, DC-8 SRM 51-3-0, DC-8 SRM 51-3-1, DC-8 SRM 51-1-8 PAGES 17-18, DC-8 SRM 53-2-0 PAGE 2P, AND DC-8 SRM 51-1-8B.
Part: LONGERON — CRACKED (FUSELAGE) · airframe 88,788 hrs · 35,270 cycles
DURING ROUTINE C-CHECK INSPECTION FOUND A CRACKED LONGERON AT STATION 1776.000 LONGERON 17 RIGHT. REMOVED CRACKED LONGERON. CLEANED, TREATED AND PRIMED AREA, AND NEW LONGERON. INSTALLED NEW LONGERON (EXTRUSION P/N S1616757) IAW DC8 SRM 53-5-1 FIG 7 SHEET 1 PAGE 22 ITEM -B-, DC-8 SRM 51-2-0 FIG 50 SHEET 37, DC-8 SRM 51-1-21, DC-8 SRM 51-3-0, DC8 SRM 51-1-20D, DC8 SRM 51-3-1 DC8 SRM 53-1-0, DC-8 SRM 51-1-20D, DC-8 SRM 51-1-8B.
Part: SKIN — CRACKED (ZONE 100) · airframe 88,788 hrs · 35,270 cycles
DURING ROUTINE C CHECK INSPECTION FOUND EXTERNAL SKIN CRACKED AT STATION -12 LONGERON 27 LEFT. REMOVED FASTENERS. REMOVED DAMAGED AREA. PERFORMED NDT INSPECTION. NO CRACKS OR CORROSION FOUND. FABRICATED REPAIR PARTS. CLEANED, TREATED AND PRIMED AREA AND REPAIR PARTS. APPLIED SEALANT TO FAYING SURFACES. INSTALLED REPAIR PARTS IAW ALL SRMS AND DRAWINGS.
Part: SKIN — MISREPAIRED (BS 1384 L35R) · airframe 88,788 hrs · 35,270 cycles
DURING ROUTINE, C-CHECK INSPECTION FOUND EXISTING REPAIR AT STATION 1384 LONGERON 35.5 RT DOES NOT MEET THE DTA REQUIREMENTS OF MDC 91K0262. REMOVED EXISTING REPAIR. FABRICATED REPAIR PARTS. CLEANED, TREATED AND PRIMED AREA AND REPAIR PARTS. APPLIED SEALANT TO FAYING SURFACES. INSTALLED REPAIR PARTS. IAW SRM 53-2-1 FIG 7 SHEET 1-3, SRM 51-1-21, SRM 51-1-20D, SRM 51-3-1, SRM 53-4-1 FIG. 16 SHEET 2 PAGE 34 ITEM (B), SRM 51-9-0 FIG. 68A, SRM 51-1-8B, SRM 51-1-11.
Part: SKIN — MISREPAIRED (ZONE 100) · airframe 88,788 hrs · 35,270 cycles
DURING ROUTINE C CHECK INSPECTION FOUND EXISTING REPAIR AT STATION 8 LONGERON 28.5 RIGHT DOES NOT MEET THE DTA REQUIREMENTS OD MDC 91K0262. REMOVED EXISTING REPAIR DOUBLER. FABRICATED REPAIR PARTS. CLEANED, TREATED AND PRIMED AREA AND REPAIR PARTS. APPLIED SEALANT TO FAYING SURFACES. INSTALLED REPAIR PARTS. IAW DC-8 SRM 51-1-21, DC-8 SRM 51-1-20D,DC-8 SRM 51-1-8B,DC-8 SRM 51-1-11, BOEING MSG 1-227056808-8 DATED 09-25-06. SEMAN ENGINEERING ORDER NUMBER 2006711 DATED 09-25-06.IAW BOEING MSG 1-227056808-8,ROD SKETCH 06-09-001, SEMAN ENGINEERING DRAWING NUMBER 4324 DATED 9-9-06, COMPLETED FAA FORM 8100-9 DATED 09-25-06.
Part: SKIN — MISREPAIRED (ZONE 200) · airframe 88,788 hrs · 35,270 cycles
DURING ROUTINE C-CHECK INSPECTION FOUND EXISTING REPAIR AT STATION FS 29 LONGERON 9.75 LT, DOES NOT MEET CURRENT SRM CRITERIA. REMOVED EXISTING REPAIR. PERFORMED NDT INSPECTION, NO CRACKS OR CORROSION FOUND. FABRICATED REPAIR PARTS. CLEANED TREATED AND PRIMED AREA AND REPAIR PARTS. APPLIED SEALANT TO FAYING SURFACES. INSTALLED REPAIR PARTS. IAW SRM 51-1-21, SRM 51-1-20D, 51-3-0, NDT SPM PART 06-10-01-001, SRM 51-1-8B, SRM 51-1-11, 51-3-1, A.D. 2000-20-08, S/B 53-075, AND DWG NR SR08530021.
Part: SKIN — MISREPAIRED (ZONE 500) · airframe 88,788 hrs · 35,270 cycles
DURING ROUTINE C-CHECK INSPECTION, FOUND LT WING IB FLAP EXISTING LOWER. SKIN DOUBLER IMPROPER FROM STATION XW2.000 TO XW91.000. REMOVED EXISTING SKIN. FABRICATED NEW SKIN AND INTERNAL DOUBLER. 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 57-7-1 FIG 1 PAGE 2, SRM 57-1-0 PAGE 1, SRM 57-7-1 FIG 1 PAGE 2 ITEM (B) AND (L), SRM 51-1-9, SRM 51-1-8B, AND SRM 51-1-11.
Part: SKIN — MISREPAIRED (BS 248) · airframe 88,788 hrs · 35,270 cycles
DURING ROUTINE C CHECK INSPECTION, FOUND IMPROPER REPAIR AT STATION 248, LONGERON 26 RIGHT. REMOVED EXISTING REPAIR DOUBLER. REMOVED DAMAGED AREA. PERFORMED NDT INSPECTION. NO CRACKS OR CORROSION. FABRICATED REPAIR PARTS. CLEANED, TREATED AND PRIMED AREA AND REPAIR PARTS. APPLIED SEALANT TO FAYING SURFACES. INSTALLED REPAIR PARTS IAW DC-8 SRM 51-1-21, DC-8 SRM 51-1-20D, DC-8 SRM 51-3-0, DC-8 SRM 51-3-1, DC-8 SRM 51-3-0, DC-8 SRM 51-1-8B, DC-8 SRM 51-1-11, DC-8 NDT SPM PART 06-10-01-001 SEMAN ENGINEERING DRAWING NUMBER 4323 DATE D09-14-06, SEMAN ENGINEERING ORDER NUMBER 2006707 DATED 09-15-06. COMPLETED FAA FORM 8110-3 NUMBER 06437 DATED 09-15-05.
Part: SKIN — MISREPAIRED (FUSELAGE) · airframe 88,788 hrs · 35,270 cycles
DURING ROUTINE C-CHECK INSPECTION FOUND IMPROPER REPAIR DOUBLER AT BS 1752 LONGERON 16.5 LT. REMOVED EXISTING REPAIR DOUBLER. REMOVED DAMAGED AREA. FABRICATED REPAIR DOUBLER, INTERNAL FINGER DOUBLER, AND FILLER. CLEANED, TREATED AND PRIMED AREA, AND REPAIR PARTS. APPLIED SEALANT TO FAYING SURFACES. INSTALLED REPAIR PARTS. IAW SRM 53-2-1 FIG 7 SHEET 1-3-5, SRM 51-1-21, SRM 53-5-1, FIG. 1 PAGE 2 ITEM (D), SRM 51-1-8B, SRM 51-1-11, SRM 51-1-20D, AND SRM 51-3-1.
Part: SKIN — CRACKED (ZONE 500) · airframe 88,788 hrs · 35,270 cycles
DURING ROUTINE C CHECK INSPECTION, FOUND LEFT WING CENTER LEADING EDGE UPPER SKIN CRACKED AT STATION XFS360.000. REMOVED FASTENERS AS NEEDED. REMOVED DAMAGED AREA. FABRICATED REPAIR PARTS. CLEANED, TREATED AND PRIMED AREA, AND REPAIR PARTS. APPLIED SEALANT TO FAYING SURFACES. INSTALLED REPAIR IAW DC-8-SRM 57-2-1 FIGURE 38 PAGE 2 TR NUMBER 57-85 DATED 11/22/00, DC-8-SRM 51-1-21, DC-8-SRM 57-2-1, DC-8-SRM 57-3-1 FIGURE 4 SHEET 2 PAGE 8 ITEM A, DC-8-SRM 51-1-8B AND DC-8-SRM 51-1-11.
Part: SKIN — MISREPAIRED (FUSELAGE) · airframe 88,788 hrs · 35,270 cycles
DURING ROUTINE C CHECK INSPECTION, FOUND EXISTING REPAIR DOES NOT MEET DTA REQUIREMENTS OF MDC 941K0262, AT STATION 8 LONGERON 32.5 LEFT. REMOVED EXISTING REPAIR. REMOVED DAMAGED AREA. PERFORMED NDT INSPECTION, NO CRACKS OR CORROSION FOUND. FABRICATED REPAIR DOUBLER (AL 7075 T6 0.063â), AND FILLER (AL 7075 T6 0.050â). CLEANED, TREATED AND PRIMED AREA AND REPAIR PARTS. APPLIED SEALANT TO FAYING SURFACES. INSTALLED REPAIR PARTS IAW DC-8 SRM 51-1-20D, DC-8 SRM 51-3-1, DC8 SRM 51-1-21, DC8 SRM 51-3-0, DC-8 SRM 51-1-8B, DC-8 SRM 51-1-11, DC-8 NDT SPM PART 06-10-01-001, SEMAN DRAWING NUMBER 4322 DATED 09-09-06, SEMAN ENGINEERING ORDER NUMBER 2006706 DATED 09-15-06. COMPLETED FAA FORM 8110-3 NUMBER 06437 DATED
Part: SKIN — MISREPAIRED (TE FLAPS) · airframe 88,788 hrs · 35,270 cycles
DURING ROUTINE C CHECK INSPECTION, FOUND LEFT INBOARD FLAP EXISTING UPPER SKIN DOUBLER IMPROPER AT STATION, XW38.000. REMOVED EXISTING SKIN WITH EXISTING IMPROPER REPAIR. FABRICATED NEW SKIN WITH AL 2024 T3 0.025â AND BONDED DOUBLER AL 2024 T3 0.020â. 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 57-7-1 FIG 1 PAGE 2, DC-8 SRM 57-1-0 PAGE 1, DC-8 SRM 51-1-21, DC-8 SRM 57-7-1 FIG 1 PAGE 2 ITEM âAâ AND âLâ, DC-8 SRM 51-1-9, DC-8 SRM 51-1-8B, AND DC-8 SRM 51-1-11.
Part: SKIN — MISREPAIRED (ZONE 100) · airframe 88,788 hrs · 35,270 cycles
DURING ROUTINE C-CHECK INSPECTION FOUND EXISTING DOUBLER AT STATION 1761 LONGERON 16.5 LT FAILED DTA REQUIREMENTS OF MDC 91K0262 REPORT. REMOVED EXISTING REPAIR DOUBLER. FABRICATED REPAIR DOUBLER, INTERNAL FINGER DOUBLER, AND FILLER. CLEANED, TREATED AND PRIMED AREA, AND REPAIR PARTS. APPLIED SEALANT TO FAYING SURFACES. INSTALLED REPAIR PARTS. IAW SRM 53-2-1 FIG 7 SHEET 1-3-5, SRM 51-1-20D, SRM 53-5-1 FIG. 1 PAGE 2 ITEM E, SRM 51-1-8B, SRM 51-1-11, SRM 51-1-21, AND SRM 51-3-1.
Part: SKIN — MISREPAIRED (PAX DOOR) · airframe 88,788 hrs · 35,270 cycles
DURING ROUTINE C CHECK INSPECTION, FOUND PASSENGER DOOR UPPER AFT CORNER. REPAIR FALLS INTO GROUP 2 PER SERVICE BULLETIN DC 8 53.075, AND AD 2000-20-08 GROUP 2. WITHIN 2,000 LANDINGS OR 3 YEARS AFTER THE EFFECTIVE DATE ACCOMPLISH THE PREVENTATIVE MODIFICATION IAW SERVICE BULLETIN DC8 53.075. AT STATION 1655, LONGERON 9.25 LEFT. REMOVED REPAIR DOUBLER, AND EXISTING TRIPLER. PERFORMED NDT INSPECTION NO CRACKS OR CORROSION FOUND. FABRICATED REPAIR DOUBLER, AND REPAIR TRIPLER. CLEANED, TREATED AND PRIMED AREA, REPAIR DOUBLER AND TRIPLER. APPLIED SEALANT TO FAYING SURFACES. INSTALLED REPAIR PARTS IAW DC8 SRM 51-1-21, DC-8 SRM 51-1-20D, DC-8 SRM 51-3-1, DC-8 NDT SPM PART 06-10-01-001, DC-8 SRM 51-1-8B, DC8 SRM
Part: SKIN — MISREPAIRED (ZONE 100) · airframe 88,788 hrs · 35,270 cycles
DURING ROUTINE C-CHECK INSPECTION, FOUND EXISTING REPAIR AT STATION 1430 LONGERON 36 IN CLOSE PROXIMITY TO ANOTHER EXISTING REPAIR AT THE LOWER SIDE OF (D) PIT DOOR. INCORPORATED BOTH REPAIRS INTO ONE REPAIR. (D) PIT DOOR CORNER REPAIR. REMOVED EXISTING REPAIRS. FABRICATED REPAIR PARTS. CLEANED, TREATED AND PRIMED AREA AND NEW REPAIR PARTS. APPLIED SEALANT TO FAYING SURFACES. INSTALLED NEW REPAIR PARTS, (P/N 56155372-71N) IAW SRM 53-4-1 FIG 16 SHEET 2 PAGE 34 ITEM (B), MFG DRAWING NR 5779936, SRM 51-1-21, SRM 51-1-20D, SRM 51-3-1, SRM 53-1-0 PAGE 1, SRM 51-1-8B, AND SRM 51-1-11.
Part: SKIN — MISREPAIRED (BS 370 S25R) · airframe 88,788 hrs · 35,270 cycles
DURING ROUTINE C CHECK INSPECTION, FOUND IMPROPER EXISTING REPAIR AT STATION 370 LONGERON 25.5 RIGHT. REMOVED EXISTING REPAIR. REMOVED DAMAGED AREA. PERFORMED NDT INSPECTION NO CRACKS OR CORROSION FOUND. FABRICATED REPAIR PARTS. CLEANED, TREATED AND PRIMED AREA AND REPAIR PARTS. APPLIED SEALANT TO FAYING SURFACES. INSTALLED REPAIR PARTS IAW DC-8 SRM 51-1-21, DC-8 SRM 51-1-20D, DC-8 SRM 51-3-1, DC-8 SRM 51-3-0, DC-8 NDT SPM PART 06-10-01-001, DC-8 SRM 51-1-8B, DC-8 SRM 51-1-11, SEMAN ENGINEERING DRAWING NUMBER 4329 DATED 09-12-06, SEMAN ENGINEERING ORDER NUMBER 2006718 DATED 09-15-06. COMPLETED FAA FORM 8110-3 NUMBER 06437 DATED 09-15-05.
Part: SKIN — DAMAGED (ZONE 500) · airframe 88,788 hrs · 35,270 cycles
DURING ROUTINE C CHECK INSPECTION, FOUND LEFT WING SLOT VANE SKIN HOLES ELONGATED AT STATION XS 250.000. REMOVED FASTENERS. REMOVED DAMAGED AREA. PERFORMED NDT INSPECTION AFTER DAMAGE REMOVED, NO CRACKS OR CORROSION FOUND. FABRICATED REPAIR DOUBLER, INTERNAL DOUBLER, AND SKIN FILLER. CLEANED, TREATED AND PRIMED AREA, AND REPAIR PARTS. APPLIED SEALANT TO FAYING SURFACES. INSTALLED REPAIR PARTS IAW DC-8 SRM 51-1-21, DC-8 SRM 51-3-0, DC-8 SRM 51-1-20D, DC-8 SRM 51-3-1, DC-8 SRM 51-1-8B, SRM 51-1-11, DC-8 NDT SPM PART 06-10-01-001, DC-8 SRM 51-1-8B, SRM 51-1-11, SEMAN DRAWING NUMBERED 4325 DATED 09-15-06, SEMAN EO NR 2006712 DATED 09-29-06, COMPLETED FAA FORM 8110-3 NR 06464 DATED 09-29-06.
Part: SKIN — MISREPAIRED (FUSELAGE) · airframe 88,788 hrs · 35,270 cycles
DURING ROUTINE C CHECK INSPECTION, FOUND EXISTING REPAIR AT STATION 370 LONGERON 30.5 RIGHT DOES NOT MEET DTA REQUIREMENTS OF MDC 91K0262 REPORT. REMOVED EXISTING REPAIR. REMOVED DAMAGED AREA. FABRICATED REPAIR PARTS. TREATED AND PRIMED AREA AND REPAIR PARTS. APPLIED SEALANT TO FAYING SURFACES. INSTALLED REPAIR PARTS, IAW SEMAN ENGINEERING ORDER NUMBER 206719 DATED 09/29/06, SEMAN DRAWING NUMBER 4330 DATED 9/14/06, DC-8 SRM 51-1-20D, DC-8 SRM 51-1-1AND DC-8-SRM 51-1-8.
Part: SKIN — MISREPAIRED (ZONE 100) · airframe 88,788 hrs · 35,270 cycles
DURING ROUTINE C CHECK, MODIFY CARGO DOOR JAMB CORNERS AT STATION 1420 LONGERON 34.5 RIGHT IAW AD 2004-06-06. REMOVED EXISTING REPAIR. FABRICATED REPAIR PARTS. CLEANED TREATED AND PRIMED AREA AND REPAIR PARTS. APPLIED SEALANT TO FAYING SURFACES. INSTALLED REPAIR PARTS IAW DC8 SRM 53-4-1 FIG 16 SHEET 2, DC8 SRM 53-1-0 PAGE 1, DC8 SRM 51-1-21, DC-8 SRM 51-1-8B, DC8 SRM 51-1-11, DC-8 SRM 53-4-1 FIG 16 SHEET 2 PAGE 34 ITEM âBâ, DC-8 SRM 51-1-21, DC-8 SRM 51-1-20D, DC-8 SRM 51-3-1, DOUGLAS DRAWING NUMBER 5779936.
Part: TRANSMITTER — FAILED (HYD SYSTEM) · airframe 88,488 hrs · 35,182 cycles
DURING CRUISE FROM KTOL TO CYJT, CREW NOTICED THE HYDRAULIC PRESSURE DROPPED TO 2000 POUNDS OF PRESSURE. THE CREW ELECTED TO RETURN TO KTOL AND SAFELY LANDED. MAINTENANCE REPLACED THE HYDRAULIC PRESSURE TRANSMITTER. THE HYDRAULIC SYSTEM OPERATIONAL CHECK WAS GOOD AND THE AIRCRAFT WAS RETURNED TO SERVICE.
Part: ADI — FAULTY (NR 1) · airframe 88,327 hrs · 35,113 cycles
DURING CRUISE FROM KMIA THE CAPTAINS ADI DISPLAYED BOTH FLIGHT DIRECTOR AND GYRO FLAGS, FLAGS STAYED IN VIEW FOR APPROXIMATELY 1-2 MINUTES THEN WENT AWAY FOR APPROXIMATELY 5 MINUTES, THEN INTERMITTENTLY DISPLAYED AFTER THAT. THE CREW RETURNED TO KMIA AND LANDED. MAINTENANCE REPLACED THE NUMBER 1 FOG GYRO, INSTRUMENT AMPLIFIER AND THE NUMBER 1 ADI. THE OPERATIONAL CHECK WAS GOOD AND THE AIRCRAFT WAS RETURNED TO SERVICE.
Part: ACTUATOR — INOPERATIVE (HORZ STAB) · airframe 87,687 hrs · 34,799 cycles
DURING CLIMB OUT FROM CAPTAINS AND FIRST OFFICERS YOKE TRIM SWITCHES STOPPED WORKING AT TOP OF CLIMB. THE CREW ELECTED TO RETURN TO DEPARTURE AND LANDED WITH OUT INCIDENT. MAINTENANCE REMOVED AND REPLACED THE TRIM SERVO ACTUATOR AND ALL WORK DONE WAS IAW APPLICABLE MANUALS. AIRCRAFT WAS RETURNED TO SERVICE.
2005
Part: LONGERON — CORRODED (ZONE 100) · airframe 85,823 hrs · 34,028 cycles
DURING ROUTINE C-CHECK FOUND LONGERON CORRODED AT STATION 1702 LONGERON 28 LEFT. REMOVED DAMAGED, FABRICATED REPAIR PARTS, LOCATED, DRILLED, TREATED, PRIMED AND INSTALLED REPAIR PARTS IAW COOPESA EO COO-8-53-426-04.
Part: REPAIR — TEMPORARY (ZONE 100) · airframe 85,823 hrs · 34,028 cycles
DURING ROUTINE C-CHECK, TO COMPLY WITH DTA REQUIREMENTS, REMOVED EXISTING EXTERNAL FUSELAGE DOUBLER AT STATION 1715 LONGERON 26 RIGHT. FABRICATED REPAIR PARTS, LOCATED, DRILLED, TREATED, PRIMED, AND INSTALLED NEW DOUBLER REPAIR AT STATION 1670 TO 1753, LONGERON 24 RIGHT TO LONGERON 30 RIGHT IAW COOPESA EO COO-8-53-413-04.
Part: FITTING — CRACKED (ZONE 100) · airframe 85,823 hrs · 34,028 cycles
DURING ROUTINE C-CHECK FOUND LONGERON 34 LEFT AT STATION 690 TO 778 CORRODED. REMOVED CORROSION, TREATED AND PRIMED. DURING CORROSION REMOVAL FOUND FITTING CRACKED AT LONGERON 34 LEFT STATION 765 TO 778. FABRICATED NEW FITTING, LOCATED, DRILLED, TREATED, PRIMED, AND INSTALLED NEW FITTING IAW DC8 SRM 53-20-0, 51-1-8, 53-2-0 AND, 51-1-20.
Part: FRAME — CORRODED (ZONE 100) · airframe 85,823 hrs · 34,028 cycles
DURING ROUTINE C-CHECK FOUND FRAME CORRODED AT STATION 1260 LONGERON 33 RIGHT TO LONGERON 34 RIGHT. FABRICATED REPAIR PARTS, LOCATED, DRILLED, TREATED, PRIMED, AND INSTALLED REPAIR PARTS AND FASTENERS IAW DC8 SRM 51-2-1, 53-4-1, 51-1-4, 51-1-5 AND 51-1-8.
Part: WEB — CRACKED (ZONE 200) · airframe 85,823 hrs · 34,028 cycles
DURING ROUTINE C CHECK, FOUND EXTERNAL FUSELAGE FORWARD BULKHEAD UPPER WEB CRACKED AT STATION -165 BETWEEN +X17 AND +Z23. REMOVED DAMAGED AREA. FABRICATED DOUBLER, LOCATED, DRILLED, TRIMMED, TREATED, PRIMED, INSTALLED DOUBLER, AND FASTENERS AT STATION -165 FROM +X17 TO +Z23. IAW SRM 53-2-0, 51-1-21, 51-1-5, AND 51-1-8.
Part: SUPPORT — CORRODED (ZONE 100) · airframe 85,823 hrs · 34,028 cycles
DURING ROUTINE C-CHECK FOUND SUPPORT CORRODED AT STATION 300 LONGERON 29 LEFT. FABRICATED NEW SUPPORT, LOCATED, DRILLED, TREATED, PRIMED, AND INSTALLED NEW SUPPORT AND FASTENERS IAW DC8 SRM 53-2-0, 51-1-20 AND 51-1-8.
2004
Part: DOUBLER — DAMAGED (FUSELAGE) · airframe 85,823 hrs · 34,028 cycles
DURING ROUTINE C-CHECK REMOVED EXISTING FUSELAGE SKIN REPAIR DT STATION 410 LONGERON 35 RT DUE TO DTA REQUIREMENTS. REMOVED AFFECTED FASTENERS AND DOUBLER. FABRICATED NEW REPAIR PARTS, LOCATED, DRILLED, REMOVED, TREATED, PRIMED, INSTALLED NEW REPAIR PARTS AND FASTENERS FROM STATION 397 TO STATION 422 BETWEEN LONGERON 34 RT TO 34 LT IAW SRM 53-2-1, 51-1-4, 51-1-5, AND 51-1-8.
Part: REPAIR — TEMPORARY (ZONE 100) · airframe 85,823 hrs · 34,028 cycles
DURING ROUTINE C-CHECK, TO COMPLY WITH DTA REQUIREMENTS REMOVE EXISTING FASTENERS AND EXISTING FUSELAGE DOUBLER AT STATION 107 LONGERON 35 RIGHT. INSTALL REPAIR AT FUSELAGE SKIN SECTION FROM STATION 98.5 TO STATION 114.5 BETWEEN LONGERON 34 LEFT TO LONGERON 35 RIGHT. FABRICATE REPAIR PARTS, LOCATED, DRILLED, TREATED, PRIMED, INSTALLED REPAIR PARTS AND FASTENERS IAW COOPESA EO COO-8-53-408-04 DATED 10/23/04.
Part: REPAIR — SCHEDULED MAINT (ZONE 100) · airframe 85,823 hrs · 34,028 cycles
DURING ROUTINE C-CHECK REMOVE EXISTING FUSELAGE SKIN REPAIR LOCATED AT STATION 220 LONGERON 35 RIGHT DUE TO DTA REQUIREMENTS. REMOVED NECESSARY FASTENERS, AND EXISTING DOUBLER, REMOVED DAMAGE. FABRICATED REPAIR PARTS, LOCATED, DRILLED, REMOVED, TERATED, PRIMED, INSTALLED NEW REPAIR PARTS ANS FASTENERS FROM STATION 211 TO STATION 236, BETWEEN LONGERON 34 RIGHT AND 33 LEFT IAW COOPESA EO COO -8-53-405-4
Part: FRAME — CORRODED (ZONE 100) · airframe 85,823 hrs · 34,028 cycles
DURING ROUTINE C-CHECK FOUND LOWER CHORD AT STATION 70 BETWEEN LONGERONS 35 RIGHT AND 34 LEFT CORRODED. REMOVED DAMAGED AREA, FABRICATED REPAIR PARTS, LOCATED, DRILLED, TRIMMED, TREATED, PRIMED, AND INSTALLED REPAIR PARTS AND NEW FASTENERS IAW COOPESA EO COO-8-53-440-04.
Part: RIB — CRACKED (RT WING) · airframe 85,823 hrs · 34,028 cycles
DURING ROUTINE C CHECK, FOUND RIGHT WING RIB WEB CRACKED AT STATION XRS6. REMOVED DAMAGE. FABRICATED DOUBLER, LOCATED, DRILLED, TRIMMED, TREATED, PRIMED, INSTALLED REPAIR DOUBLER, AND FASTENERS AT RIGHT HAND WING STATION XRS6 IAW DC8 SRM 57-2-0, 51-1-21, 57-5-0, 51-1-4, 51-1-5, AND 51-1-8.
Part: SKIN — DELAMINATED (SPOILER)
RT WING, SPOILER PN 56551671, SN 2740 UPPER SKIN DELAMINATED AT STA XRS 218. (K)
Part: SKIN — CORRODED (FUSELAGE)
FUSELAGE AFT CENTER SECTION, LOWER PLATING (PN 57799293) CORRODED FROM STA 980 TO STA 1040 BETWEEN LONGERON 35L AND 35R. (K)
Part: SKIN — CORRODED (FUSELAGE)
LOWER FUSELAGE SKIN WITH CORROSION AT Y STA 622.0, BETWEEN LONG 27L AND LONG 30L. (K)
Part: SKIN — DENTED (ZONE 300) · airframe 85,823 hrs · 85,823 cycles
DURING ROUTINE C CHECK, FOUND EMPENNAGE RIGHT HAND ELEVATOR UPPER AND LOWER SKIN DENTED IN SEVERAL AREAS. REMOVED RIGHT HAND ELEVATOR. REMOVED RIGHT HAND ELEVATOR UPPER AND LOWER SKIN SECTION FROM STATION XE 132.531 TO XE251.562. FABRICATED REPAIR PARTS, LOCATED, DRILLED, TRIMMED, TREATED, PRIMED, INSTALLED NEW SKIN SECTION AND NEW FASTENERS. INSTALLED RIGHT HAND ELEVATOR ON EMPENNAGE IAW DC8 MM 27-30-1, 27-31-01, DC8 SRM 51-1-9, 55-4-1, 51-1-5, AND 51-1-8.
Part: SKIN — CORRODED (ZONE 100) · airframe 85,823 hrs · 34,028 cycles
DURING ROUTINE C-CHECK FOUND EXTERNAL FUSELAGE SKIN CORRODED FROM STATION 660 TO STATION 662 AT LONGERON 33 LEFT. REMOVED DAMAGED SKIN. FABRICATED FILLER, DOUBLER, AND TRIPLER. LOCATED DRILLED TRIMMED TREATED, PRIMED, AND INSTALLED REPAIR PARTS AND NEW FASTENERS IAW COOPESA EO COO-8-53-410-04.
Part: WEB — CRACKED (FUSELAGE) · airframe 85,823 hrs · 34,028 cycles
DURING ROUTINE C-CHECK FOUND WEB CRACKED ST STATION 30 -X48. REMOVED DAMAGE. FABRICATED REPAIR DOUBLER, LOCATED, DRILLED, TRIMMED, TREATED, PRIMED, INSTALLED REPAIR DOUBLER AND FASTENERS AT STATION 30 TO 33.5 AT -X48. IAW SRM 53-2-0, 51-1-4, 51-1-5, AND 51-1-8.
Part: SKIN — CORRODED (BS 620-630) · airframe 85,823 hrs · 34,028 cycles
DURING ROUTINE C-CHECK FOUND EXTERNAL FUSELAGE SKIN FROM STATION 620 TO 630 AT LONGERONS 29 LEFT AND 30 LEFT. REMOVED DAMAGED SKIN AREA. FABRICATED REPAIR PARTS, LOCATED, DRILLED, TRIMMED, TREATED, PRIMED, AND INSTALLED REPAIR PARTS AND NEW FASTENERS IAW COOPESA EO COO-8-53-407-4.
Part: WEB — CRACKED (ZONE 200) · airframe 85,823 hrs · 34,028 cycles
DURING ROUTINE C-CHECK FOUND WEB CRACKED ST STATION 30 -X48. REMOVED DAMAGE. FABRICATRED REPAIR DOUBLER, LOCATED, DRILLED, TRIMMED, TREATED, PRIMED, INSTALLED REPAIR DOUBLER AND FASTENERS AT STATION 30 AND 33.5 AT -X48. IAW SRM 53-2-0, 51-1-4, 51-1-5, AND 51-1-8.
Part: INTERCOSTAL — CRACKED (FUSELAGE) · airframe 85,823 hrs · 34,028 cycles
DURING ROUTINE CHECK, FOUND A CRACKED INTERCOSTAL FROM STATION 1140 TO STATION 1160 AT LONGERON 14 RT. REMOVED FASTENERS AS NEEDED TO REMOVE DAMAGED INTERCOSTAL. FABRICATED NEW INTERCOSTAL, LOCATED, DRILLED, TRIMMED, TREATED, PRIMED, INSTALLED NEW INTERCOSTAL AND FASTENERS FROM STATION 1140 TO STATION 1160 AT LONGERON 14 RT IAW SRM 53-2-0, 51-1-20, 51-1-21, 51-1-4, 51-1-5, AND 51-1-8.
Part: FRAME — CRACKED (ZONE100) · airframe 85,823 hrs · 34,028 cycles
DURING ROUTINE C-CHECK FOUND FRAME CRACKED AT STATION 420 LONGERON 35 RIGHT. REMOVED DAMAGE, FABRICATED REPAIR PARTS, LOCATED, DRILLED, TRIMMED, TREATED, PRIMED AND INSTALLED REPAIR PARTS AND NEW FASTENERS AT STATION 420 BETWEEN LONGERONS 33 LEFT AND 35 LEFT IAW DC8 SRM 51-2-1, 51-1-4, 51-1-5, AND 51-1-8.
Part: REPAIR — TEMPORARY (ZONE 100) · airframe 85,823 hrs · 34,028 cycles
DURING ROUTINE C-CHECK TO COMPLY WITH DTA REQUIREMENTS REMOVED EXISTING EXTERNAL DOUBLER AT STATION 1702 LONGERON 26 LEFT. FABRICATED REPAIR PARTS, LOCATED, DRILLED, TREATED, PRIMED, AND INSTALLED NEW REPAIR DOUBLER AT STATION 1690 TO 1713 LONGERON 24 LEFT TO LONGERON 30 LEFT IAW COOPWSA EO COO-8-53-409-04.
Part: RIB — CRACKED (LT WING) · airframe 85,823 hrs · 34,028 cycles
DURING ROUTINE C CHECK, FOUND LEFT WING LEADING EDGE UPPER RIB CRACKED AT STATION XFS 464.000. REMOVED DAMAGE. FABRICATED REPAIR PARTS, LOCATED, DRILLED, TRIMMED, TREATED, PRIMED, INSTALLED REPAIR PARTS AND NEW FASTENERS AT LEFT WING LEADING EDGE UPPER RIB AT STATION XFS464.000. IAW DC8 SRM 57-3-1, 51-1-4, 51-1-5, AND 51-1-8.
Part: STRAP — CRACKED (LT WING) · airframe 85,823 hrs · 34,028 cycles
DURING ROUTINE C CHECK, FOUND LEFT WIND CENTER LEADING EDGE RIB SUPPORT STRAP CRACKED AT STATION XFS 366.500. REMOVE DAMAGED STRAP. FABRICATED NEW STRAP, LOCATED, DRILLED, TRIMMED, TREATED, PRIMED, INSTALLED NEW STRAP AND FASTENERS AT LEFT WING CENTER LEADING EDGE STATION XFS 366.500 IAW DC8 SRM 57-1-0, AND 51-1-20.
Part: REPAIR — DAMAGED (BS 1360) · airframe 85,823 hrs · 34,028 cycles
DURING ROUTINE C-CHECK REPLACED EXISTING FUSELAGE SKIN REPAIR DUE TO DTA REQUIREMENTS AT STATION 1360 LONGERON 16 LT SIDE. REMOVED NECESSARY FASTENERS AND EXISTING REPAIR. FABRICATED DOUBLER AND FILLER, LOCATED, DRILLED, TRIMMED, TREATED, PRIMED, INSTALLED DOUBLER, FILLER, AND FASTENERS WET WITH SEALANT FROM STATION 1358 TO STATION 1378 BETWEEN LONGERON 14 LT AND LONGERON 16 LT. IAW SRM 53-2-0, 51-1-4, 51-1-5, AND 51-1-8.
Part: STRAP — CRACKED (LT WING) · airframe 85,823 hrs · 34,028 cycles
DURING ROUTINE C CHECK, FOUND LEFT WIND CENTER LEADING EDGE RIB SUPPORT STRAP CRACKED AT STATION XFS 347.750. REMOVE DAMAGED STRAP. FABRICATED NEW STRAP, LOCATED, DRILLED, TRIMMED, TREATED, PRIMED, INSTALLED NEW STRAP AND FASTENERS AT LEFT WING CENTER LEADING EDGE STATION XFS 347.750. IAW DC8 SRM 57-1-0, AND 51-1-20.
Part: REPAIR — DAMAGED (BS 1735-1750) · airframe 85,823 hrs · 34,028 cycles
DURING ROUTINE C-CHECK REPLACED EXISTING FUSELAGE SKIN REPAIR FROM STATION 1735 TO STATION 1750 BETWEEN LONGERON 14 RT AND 17 RT DUE TO DTA REQUIREMENTS. REMOVED FASTENERS AS NEEDED, AND EXISTING REPAIR. FABRICATED DOUBLER AND FILLERS, LOCATED, DRILLED, TRIMMED, TREATED, PRIMED, INSTALLED FILLERS, DOUBLER, AND FASTENERS WET WITH SEALANT FROM STATION 1735 TO STATION 1750 BETWEEN LONGERON 14 RT AND LONGERON 17 RT IAW SRM 53-2-1, 53-5-1, 51-1-5 AND 51-1-8.
Part: PANEL — CORRODED (VERTICAL STAB) · airframe 85,817 hrs · 34,027 cycles
VERTICAL STABILIZER, LT SIDE PANEL CORRODED AND DELAMINATED, LOCATED FROM STA ZR 253.000 TO STA ZV 299.125. (K)
Part: SKIN — CORRODED (FUSELAGE) · airframe 86 hrs · 34 cycles
LOWER FUSELAGE SKIN WITH CORROSION AT Y-STA 680.0 AND Y-STA 687.0, BETWEEN LONG 31R AND LONG 34R. (K)
Part: FITTING — CRACKED (FUSELAGE) · airframe 86 hrs · 34 cycles
FWD CARGO COMPARTMENT FROM Y-STA 440 TO Y-STA 460, LONGERON 31R SPLICE FITTING, PN 3750257-1, CRACKED. (K)
Part: SKIN — CRACKED (FUSELAGE) · airframe 86 hrs · 34 cycles
FWD PASSENGER DOOR HOLD OPEN PAN, PN 4643785, AND FUSELAGE EXTERNAL SKIN CRACKED AT Y-STA 15.000. (K)
Part: FITTING — CORRODED (MAIN CABIN)
MAIN CARGO CABIN, SUPPORT FITTING, PN 4597643-1, CORRODED AT Y-STA 60-X65, Z 0 INCH. (K)
Part: FITTING — CRACKED (T/E FLAP) · airframe 85,823 hrs · 34,028 cycles
DURING ROUTINE C CHECK, FOUND LEFT WING TRAILING EDGE FLAP DRIVE LINK FITTING CRACKED AT STATION XW 97.906. REMOVED DRIVE LINK. REMOVED DAMAGED DRIVE LINK FITTING. RECEIVED NEW DRIVE LINK FITTING AND INSTALLED NEW FITTING AT STATION 97.906. INSTALLED DRIVE LINK FORWARD ATTACH POINT IAW DC8 MM 27-21-4.
Part: DOUBLER — DAMAGED (FUSELAGE) · airframe 85,823 hrs · 34,028 cycles
DURING ROUTINE C CHECK REPLACE EXTERNAL FUSELAGE SKIN REPAIR AT STATION 1795 LONGERON 35 LT DUE TO DTA REQUIREMENTS. REMOVED FASTENERS NEEDED TO PERFORM REPAIR, AND EXISTING DOUBLER. FABRICATED REPAIR PARTS, LOCATED, DRILLED TREATED, PRIMED, INSTALLED REPAIR PARTS, AND NEW FASTENERS FROM STATION 1258 TO STATION 1277 BETWEEN LONGERON 35 RT TO LONGERON 34 LT. IAW SRM 53-2-1, 51-1-4, 51-1-5 AND 51-1-8.
Part: REPAIR — SCHEDULED MAINT (ZONE 100) · airframe 85,823 hrs · 34,028 cycles
DURING ROUTINE C CHECK REMOVE EXISTING EXTERNAL SKIN REPAIR AT STATION 172 LONGERON 35 RIGHT DUE TO DTA REQUIREMENTS. REMOVED FASTENERS AS NEEDED AND EXISTING DOUBLER. FABRICATED NEW REPAIR PARTS, LOCATED, DRILLED, REMOVED, TREATED, PRIMED, INSTALLED NEW REPAIR PARTS AND NEW FASTENERS AT STATION 169.5 TO STATION 182.5 BETWEEN LONGERON 34 RIGHT AND 34 LEFT IAW COOPESA E.O. COO-8-53-406-04.
Part: REPAIR — TEMPORARY (ZONE 100) · airframe 85,823 hrs · 34,028 cycles
DURING ROUTINE C-CHECK, TO COMPLY WITH DTA REQUIREMENT REMOVED EXISTING DOUBLER AT STATION 74 LONGERON 35 RIGHT. FABRICATED REPAIR PARTS, LOCATED, DRILLED, TREATED, PRIMED, INSTALLED REPAIR PARTS, AND FASTENERS AT STATION 70 TO 78.5, LONGERONS 34 LEFT TO LONGERON 35 RIGHT IAW COPESA EO COO-8-53-404-04.
Part: DOUBLER — DAMAGED (FUSELAGE) · airframe 85,823 hrs · 34,028 cycles
DURING ROUTINE C-CHECK, REPLACE EXISTING FUSELAGE SKIN REPAIR LOCATED AT STATION 1686 LONGERON 35 RT DUE TO DTA REQUIREMENTS. REMOVED FASTENERS NEEDED TO PERFORM REPAIR. REMOVED EXISTING DOUBLER. REMOVED DAMAGE, FABRICATED REPAIR PARTS, LOCATED, DRILLED, TREATED, PRIMED, INSTALLED REPAIR PARTS AND FASTENERS. IAW EO COO-8-53-423-4.
Part: DOUBLER — DAMAGED (FUSELAGE) · airframe 85,823 hrs · 34,028 cycles
DURING ROUTINE C-CHECK REPLACE EXISTING FUSELAGE SKIN REPAIR AT STATION 1144 LONGERON 35 RT DUE TO DTA REQUIREMENTS. REMOVED AFFECTED FASTENERS AND EXISTING REPAIR. REMOVED DAMAGE. FABRICATED REPAIR PARTS, LOCATED, DRILLED, TRIMMED TREATED, PRIMED INSTALLED REPAIR PARTS, AND NEW FASTENERS FROM STATION 1137.5 TO STATION 1151 BETWEEN LONGERON 34 RT TO LONGERON 35 LT IAW COOPESA EO COO -8-53-411-04.
Part: SKIN — CORRODED (ZONE 100) · airframe 85,823 hrs · 34,028 cycles
DURING ROUTINE C-CHECK FOUND EXTERNAL FUSELAGE SKIN CORRODED AT STATION 680, LONGERON 33 LEFT AND 34 LEFT. REMOVED DAMAGE, FABRICATED REPAIR PARTS. LOCATED, DRILLED, TREATED, PRIMED, AND INSTALLED REPAIR PARTS AT STATION 674 TO STATION 696 BETWEEN LONGERON 31 RIGHT AND 34 RIGHT IAW COOPESA EO COO-8-53-385-04.
Part: SKIN — CRACKED (ZONE 600) · airframe 85,823 hrs · 34,028 cycles
DURING ROUTINE C CHECK, FOUND RIGHT WING UPPER SKIN CRACKED AT STATION XFS 132.250. REMOVED FASTENERS AS NEEDED TO PERFORMED REPAIR. REMOVED DAMAGE. FABRICATED DOUBLER AND FILLER, LOCATED, DRILLED, TRIMMED, TREATED, PRIMED, INSTALLED DOUBLER, FILLER AND NEW FASTENERS WET WITH SEALANT FROM STATION XFS 116.250 TO 132.250 AT FRONT SPAR IAW COOPESA E.O. COO-8-57-384-04 DATED 10/12/2004.
Part: SKIN — CRACKED (ZONE 600) · airframe 85,823 hrs · 34,028 cycles
DURING ROUTINE C CHECK, FOUND RIGHT HAND WING SKIN CRACKED AT STATION 143.000. REMOVED FUEL DUCTS. REMOVED FASTENERS AS NEEDED. REMOVED DAMAGE. FABRICATED REPAIR PARTS, LOCATED, DRILLED, TRIMMED, TREATED, PRIMED, INSTALLED NEW REPAIR PARTS AND FASTENERS WET WITH SEALANT FROM STATION XRS 60-300 TO 88.050 BETWEEN CENTER SPAR AND STRINGER NUMBER 10 IAW DC8 MM 28-25-16, DC8 SRM 57-2-1, 51-1-12, 51-1-4, 51-1-5, AND 51-1-8.
Part: DOUBLER — DAMAGED (FUSELAGE) · airframe 85,823 hrs · 34,028 cycles
DURING ROUTINE C-CHECK REMOVED EXISTING FUSELAGE SKIN REPAIR LOCATED AT STATION 550, LONGERON 35 RT. REMOVED NECESSARY FASTENERS AND EXISTING REPAIR. FABRICATED NEW REPAIR PARTS, LOCATED, DRILLED REMOVED, TREATED, PRIMED, INSTALLED NEW REPAIR PARTS, AND FASTENERS, AT STATION 525 TO STATION 552.5 LONGERON 34 RT TO LONGERON 35 LT. IAW EO COO-8-53-400-04.
Part: DOUBLER — DAMAGED (FUSELAGE) · airframe 85,823 hrs · 34,028 cycles
DURING ROUTINE C-CHECK REMOVED EXISTING EXTERNAL FUSELAGE SKIN REPAIR AT STATION 543 LONGERON 35 RT DUE TO DTA REQUIREMENTS. REMOVED NECESSARY FASTENERS AND EXISTING SKIN REPAIR. REMOVED DAMAGE. FABRICATED REPAIR PARTS, LOCATED, DRILLED, REMOVED, TREATED, PRIMED, INSTALLED NEW REPAIR PARTS AND FASTENERS, FROM STATION 525 TO STATION 552.5 BETWEEN LONGERON 34 RT AND LONGERON 35 LT. IAW EO COO-8-53-400-4
Part: REPAIR — TEMPORARY (ZONE 100) · airframe 85,823 hrs · 34,028 cycles
DURING ROUTINE C-CHECK TO COMPLY WITH DTA REQUIREMENTS REMOVED EXISTING DOUBLER AT STATION 1544 LONGERON 35 RIGHT. FABRICATED REPAIR PARTS, LOCATED, DRILLED, TREATED, PRIMED, AND INSTALLED NEW REPAIR PARTS AND FASTENERS AT STATION 1537 TO STATION 1551 BETWEEN LONGERON 34 LEFT TO LONGERON 34 RIGHT IAW DC8 SRM 53-21-2, 51-1-5, AND 51-1-8.
Part: DOUBLER — DAMAGED (FUSELAGE) · airframe 85,823 hrs · 34,028 cycles
DURING ROURINE C-CHECK REPLACE EXTERNAL FUSELAGE SKIN AT STATION 1695 LONGERON 36 REPAIR DUE TO DTA REQUIREMENTS. REMOVED EXISTING REPAIR. REMOVED DAMAGE, FABRICATED REPAIR PARTS, LOCATED, DRILLED, REMOVED, TREATED, PRIMED AND INSTALLED REPAIR PARTS AND INSTALLED NEW FASTENERS. IAW EO COO-8-53-423-04.
Part: DOUBLER — DAMAGED (FUSELAGE) · airframe 85,823 hrs · 34,028 cycles
DURING ROUTINE C-CHECK REMOVED EXISTING FUSELAGE SKIN REPAIR LOCATED AT STATION 543 LONGERON 35 RT DUE TP DTA REQUIREMENTS. REMOVED AFFECTED FASTENERS AND EXISTING SKIN REPAIR. FABRICATED REPAIR PARTS, LOCATED, DRILLED,REMOVED, TREATED, PRIMED, INSTALLED REPAIR PARES, AND NEW FASTENERS FROM STATION 525 TO STATION 552.5 BETWEEN LONGERON 34 RT TO LONGERON 35 LT. IAW EO COO-8-53-400-04.
Part: SKIN — DELAMINATED (LT IB FLAP) · airframe 85,823 hrs · 34,028 cycles
DURING ROUTINE C-CHECK FOUND LT WING IB FLAP TRAILING EDGE PANEL UPPER SKIN DELAMINATED. REMOVED FASTENEERS AS NEEDED TO PERFORM REPAIR. REMOVED DAMAGED SKIN SECTION. FABRICATED FINGER DOUBLERS AND NEW UPPER SKIN SECTION. LOCATED, DRILLED, TRIMMED, TREATED, PRIMED, AND INSTALLED NEW UPPER SKIN SECTION AND NEW FASTENERS FROM STATION XW91 TO STATION XW104. IAW SRM 57-2-1, 51-1-21, 51-1-9A, 51-1-4, 51-1-5, AND 51-1-8.
Part: SKIN — CRACKED (ZONE 500) · airframe 85,823 hrs · 34,028 cycles
DURING ROUTINE C CHECK FOUND LEFT HAND WING UPPER SKIN CRACKED AT STATION XRS 22.7 AT CENTER SPAR. REMOVED ALL FASTENERS COMMON TO REPAIR AREA. REMOVED DAMAGE. FABRICATED REPAIR PARTS, LOCATED, DRILLED, TRIMMED, TREATED, PRIMED, AND INSTALLED NEW REPAIR PARTS AND FASTENERS WET WITH SEALANT FROM STATION XRS 27.750 TO STATION XRS 6.750 BETWEEN STRINGER 9 AND STRINGER 10 IAW COOPESA EO COO-8-57-381-04.
Part: SUPPORT BEAM — CRACKED (FUSELAGE) · airframe 85,823 hrs · 34,028 cycles
DURING ROUTINE C CHECK, FOUND EMERGENCY EXIT DOOR BEAM INBOARD CHORD CRACKED AT CENTER SECTION FROM STATION 1110.000 TO STATION 1140.000 AT STOP FITTING 7. REMOVED FASTENERS AS NEEDED TO REMOVE DAMAGED CHORD. FAB`D NEW CHORD, LOCATED, DRILLED, TRIMMED, TREATED, PRIMED, INSTALLED NEW CHORD AND FASTENERS FROM STATION 1110.000 TO STATION 1140.000 AT STOP FITTING 7 IAW DC8 SRM 52-1-0, 51-1-21, AND 51-1-8.
Part: ANGLE — CRACKED (FUSELAGE) · airframe 85,823 hrs · 34,028 cycles
DURING ROUTINE C CHECK, FOUND EXTERNAL FUSELAGE ANGLE CRACKED AT STATION 810 AT +X18. REMOVED DAMAGE. FABRICATED REPAIR ANGLE, LOCATED, DRILLED, TRIMMED, TREATED, PRIMED, INSTALLED REPAIR ANGLE AND FASTENERS AT STATION 810 BETWEEN +X17.5 AND +X31 IAW DC8 SRM 53-2-0, 51-1-20, 51-1-21, 53-2-0, 51-1-4, 51-1-5, AND 51-1-8.
Part: SKIN — DENTED (ZONE 300) · airframe 85,823 hrs · 34,028 cycles
DURING ROUTINE C CHECK FOUND VERTICAL STABILIZER LEADING EDGE DENTED OUT OF LIMITS AT STATION ZFS149. REMOVED DAMAGE. FABRICATED FILLER AND DOUBLER. LOCATED, DRILLED, TRIMMED, TREATED, PRIMED, INSTALLED FILLER, DOUBLER, AND FASTENERS WET WITH SEALANT FROM STATION ZFS 133.5 TO STATION ZFS149. IAW SRM 55-2-1, 55/5/1, 51-1-4, 51-1-5, AND 51-1-8.
Part: ANGLE — CRACKED (FUSELAGE) · airframe 85,823 hrs · 34,028 cycles
DURING ROUTINE C CHECK, FOUND EXTERNAL FUSELAGE ANGLE CRACKED AT STATION 810 AT +X2. REMOVED DAMAGE. FABRICATED REPAIR ANGLE, LOCATED, DRILLED, TRIMMED, TREATED, PRIMED, INSTALLED REPAIR ANGLE AND FASTENERS AT STATION 810 BETWEEN +X2 AND +X12. IAW DC8 SRM 53-2-0, 51-1-20, 51-1-21, 53-2-0, 51-1-4, 51-1-5, AND 51-1-8.
Part: ATTACH FITTING — CRACKED (FUSELAGE) · airframe 85,823 hrs · 34,028 cycles
DURING ROUTINE C CHECK, FOUND AFT FUSELAGE LONGERON ATTACH FITTING CRACKED AT STATION 1690 LONGERON 28 LEFT. REMOVED FASTENERS AS NEEDED TO REMOVE DAMAGED FITTING. FABRICATED NEW FITTING, LOCATED, DRILLED, TREATED, PRIMED, INSTALLED NEW LONGERON ATTACH FITTING AND FASTENERS AT STATION 1690 LONGERON 28 LEFT IAW DC8 MM 20-16-0, DC8 SRM 53-2-0, 51-3-1, AND 51-1-8.
Part: ATTACH FITTING — CRACKED (ZONE 100) · airframe 85,823 hrs · 34,028 cycles
DURING ROUTINE C-CHECK FOUND LONGERON ATTACH FITTING CRACKED AT STATION 1690 LONGERON 23 RIGHT. REMOVED DAMAGED FITTING, FABRICATED NEW FITTING. LOCATED, DRILLED, TREATED, PRIMED AND INSTALLED NEW LONGERON ATTACH FITTING IAW DC8 MM 20-16-0, DC8 SRM 51-3-1, 51-1-8, MDC 93K-393 NDT SPM, DPS 4-999, AND DPS 7-05-3.
Part: BEAM — CRACKED (SERVICE DOOR) · airframe 85,823 hrs · 34,028 cycles
DURING ROUTINE C CHECK, FOUND AFT SERVICE DOOR BEAM NUMBER 1 CRACKED AT AFT SECTION. REMOVED SERVICE DOOR. REMOVED FASTENERS AS NEEDED TO REMOVE DAMAGED BEAM. FAB`D NEW BEAM. LOCATED, DRILLED, TRIMMED, TREATED, PRIMED, INSTALLED NEW BEAM NUMBER 1 AND FASTENERS IN AFT SERVICE DOOR. INSTALLED AFT SERVICE DOOR, RIGGED, AND LEAK CHECKED IAW DC8 MM 52-10-12, 52-10-16, 52-10-05, 21-30-05, DC8 SRM 52-1-0, 51-1-4, 51-1-5, AND 51-1-8.
Part: DOUBLER — CORRODED (ZONE 100) · airframe 85,823 hrs · 34,028 cycles
DURING ROUTINE C-CHECK FOUND CENTER FUEL TANK LOWER DOUBLER SKIN BETWEEN FRONT SPAR STATION 683.055 AND STRINGER 65 CORRODED. REMOVED CORROSION, FABRICATED REPAIR PARTS, LOCATED, DRILLED, TREATED, PRIMED, INSTALLED REPAIR PARTS, AND FASTENERS. IAW COOPESA EO COO-8-57-388-04.
Part: CUSP WEB — CORRODED (ZONE 100) · airframe 85,823 hrs · 34,028 cycles
DURING ROUTINE C-CHECK FOUND RT CUSP HORIZONTAL FLANGE CORRODED AT STATION 30 LONGERON 21 RT. REMOVED AIR CONDITIONING DUCTS. REMOVED DAMAGE. FABRICATED REPAIR PARTS, LOCATED, DRILLED, TRIMMED, TREATED, PRIMED, INSTALLED REPAIR PARTS AND FASTENERS AT STATION 30 LONGERON 21 RT. INSTALLED AIR CONDITIONING DUCTS IAW SRM 53-2-0, 51-3-0, 51-3-1, 51-1-4, 51-1-5, AND 51-1-8, MM 20-11-0.
Part: SKIN — DELAMINATED (ZONE 600) · airframe 85,823 hrs · 34,028 cycles
DURING ROUTINE C-CHECK FOUND RT WING IB FLAP OB VANE UPPER SKIN DELAMINATED. REMOVED FLAP VANE. REMOVED DELAMINATED SKIN, PERFORMED HOT BOND TO DAMAGED AREA. INSTALLED VANE. IAW MM 27-51-14, SRM 51-1-9A.
Part: ATTACH FITTING — CORRODED (ZONE 100) · airframe 85,823 hrs · 34,028 cycles
DURING ROUTINE C-CHECK FOUND MAIN CARGO CABIN SUPPORT END FITTING CORRODED AT STATION Y55 -X65 Z0. REMOVED FASTENERS AS NEEDED TO REMOVE END FITTING. MANUFACTURED NEW END FITTING, LOCATED, DRILLED, TREATED, PRIMED, INSTALLED NEW END FITTING AND FASTENERS AT STATION Y55 -X65 Z0. IAW SRM 51-3-0, 51-1-20, 51-3-1, AND 51-1-8.
Part: WEB — CORRODED (ZONE 200) · airframe 85,823 hrs · 34,028 cycles
DURING ROUTINE C CHECK, FOUND FLOOR PANEL CORRODED FROM STATION 40 TO STATION 55 BETWEEN +X60 AND -X60.7=0. REMOVED FASTENERS AS NEEDED. REMOVED DAMAGED FLOOR PANEL WEB. FAB`D NEW WEB, LOCATED, DRILLED, TREATED, PRIMED, AND INSTALLED NEW FLOOR PANEL WEB FROM STATION 40 TO STATION 55 BETWEEN +X60 AND -X60.7=0 IAW DC8 SRM 51-1-21, 53-7-1, 51-1-4, 51-1-5, AND 51-1-8.
Part: SKIN — PUNCTURED (T/E FLAP VANE) · airframe 85,823 hrs · 34,028 cycles
DURING ROUTINE C CHECK FOUND RIGHT HAND WING INBOARD FLAP OUTBOARD VANE UPPER SIDE SKIN PUNCTURED. REMOVED VANE. REMOVED DAMAGED. MANUFACTURED REPAIR PARTS, PERFORMED HOT BOND. INSTALLED VANE. IAW DC8 MM 27-51-14, DC8 SRM 51-1-9A.
Part: DOUBLER — CRACKED (FUSELAGE) · airframe 85,823 hrs · 34,028 cycles
DURING ROUTINE C CHECK, FOUND EXISTING DOUBLER CRACKED AT STATION 1620 BETWEEN LONGERON 17 LEFT AND 24 LEFT. REMOVED FASTENERS AS NEEDED TO REMOVE DAMAGED DOUBLER. FABRICATED NEW DOUBLER, LOCATED, DRILLED, TRIMMED, TREATED, PRIMED, INSTALLED NEW DOUBLER AND FASTENERS AT STATION 1620 BETWEEN LONGERON 17 LEFT NAD 24 LEFT IAW DC8 SRM 53-2-0, 51-1-21, 51-3-0, 51-1-4, 51-1-5, AND 51-1-8.
Part: DOUBLER — CRACKED (FUSELAGE) · airframe 85,823 hrs · 34,028 cycles
DURING ROUTINE C-CHECK, FOUND EXISTING DOUBLER CRACKED AT STATION 1620 BETWEEN LONGERON 17 LEFT AND 24 LEFT. REMOVED FASTENERS AS NEEDED TO REMOVE DAMAGED DOUBLER. FABRICATED NEW DOUBLER, LOCATED, DRILLED, TRIMMED, TREATED, PRIMED, INSTALLED NEW DOUBLER AND FASTENERS AT STATION 1620 BETWEEN LONGERON 17 LEFT AND 24 LEFT IAW DC8 SRM 53-2-0, 51-1-21, 51-3-0, 51-1-4, 51-1-5, AND 51-1-8.
Part: WEB — CRACKED (FUSELAGE) · airframe 85,823 hrs · 34,028 cycles
DURING ROUTINE C CHECK, FOUND WEB CRACKED FROM STATION 920 TO 940 AT -X25, Z0. REMOVED DAMAGE. FABRICATED FILLER AND DOUBLER, LOCATED, DRILLED, TRIMMED, TREATED, PRIMED, INSTALLED FILLER AND REPAIR DOUBLER AND FASTENERS FROM STATION 935.250 TO STATION 938.750 BETWEEN -X23.250 AND -X26.750, Z0 IAW DC8 SRM 53-2-0, 51-1-4, 51-1-5, AND 51-1-8.
Part: FITTING — CRACKED (ZONE 200) · airframe 85,823 hrs · 34,028 cycles
DURING ROUTINE C CHECK FOUND LONGERON 1 FITTING CRACKED AT STATION 650. REMOVED FASTENERS AS NEEDED TO REMOVE DAMAGED FITTING. MANUFACTURED NEW FITTING, LOCATED DRILLED TREATED, PRIMED, INSTALLED FITTING AND FASTENERS WET WITH SEALANT AT LONGERON 1 STATION 650 IAW SRM 51-1-20, 51-1-21, 53-2-0 AND 51-1-8.
Part: ANGLE — CRACKED (HORIZ STAB) · airframe 85,823 hrs · 34,028 cycles
DURING ROUTINE C CHECK, FOUND LEFT HORIZONTAL STABILIZER INBOARD TRAILING EDGE LOWER ANGLE CRACKED AT STATION XE 29.77. REMOVED DAMAGE, FABRICATED REPAIR PART, LOCATED, DRILLED, TRIMMED, TREATED, PRIMED, INSTALLED REPAIR PART AND FASTENERS IN LEFT HORIZONTAL STABILIZER TRAILING EDGE LOWER ANGLE AT STATION XE 29.77 IAW DC8 SRM 51-2-1, 51-1-4, 51-1-5 AND 51-1-8.
Part: ANGLE — CRACKED (ZONE 200) · airframe 85,823 hrs · 34,028 cycles
DURING ROUTINE C-CHECK FOUND RIGHT HAND CUSP CRACKED AT STATION 1050 LONGERON 21 RIGHT. CLEANED DAMAGED AREA, FABRICATED REPAIR PARTS, LOCATED, DRILLED, TREATED, PRIMED, AND INSTALLED REPAIR PARTS AND FASTENERS IAW DC8 SRM 51-21-1, 51-2-1, 51-1-5 AND 51-1-8.
Part: FRAME — CRACKED (ZONE 200)
DURING ROUTINE C-CHECK FOUND LT FRAME CRACKED AT STATION 1978. REMOVED EXISTING FASTENERS, AND FRAME. FABRICATED FRAME, LOCATED, DRILLED TRIMMED, TREATED, PRIMED, INSTALLED FRAME AND FASTENERS WET WITH SEALANT. IAW SRM 53-2-051-1-21, 53-5-1, 51-1-4, 51-1-5, AND 51-1-8.
Part: WEB — CRACKED (ZONE 100) · airframe 85,823 hrs · 34,028 cycles
DURING ROUTINE C CHECK, FOUND WEB CRACKED IN THE AFT CARGO COMPARTMENT, AFT DOOR JAMB FROM STATION 1440 TO STATION 1446 BETWEEN LONGERON 32 RT AND LONGERON 34 RT. REMOVED DAMAGED AREA. FABRICATED DOUBLER, LOCATED, DRILLED, TRIMMED, TREATED, PRIMED, INSTALLED DOUBLER AND FASTENERS FROM STATION 1440 TO STATION 1446 BETWEEN LONGERON 32 RIGHT AND LONGERON 34 RT IAW SRM 53-2-0, 51-4-5, AND 51-1-8.
Part: SKIN — CORRODED (LT WING) · airframe 85,823 hrs · 34,028 cycles
DURING ROUTINE C-CHECK FOUND LT WING UPPER SURFACE CORRODED BEOND LIMITS AT STATION XRS111.000 AT FORWARD SPAR. REMOVED FASTENERS AS NEEDED. REMOVED DAMAGE. FABRICATED REPAIR DOUBLER, LOCATED, DRILLED, TRIMMED, TREATED, PRIMED, AND INSTALLED NEW REPAIR DOUBLER AND FASTENERS WET WITH SEALANT FROM STATION XRS100.5 TO STATION 120.0 AT FRONT SPAR IAW EO COO-8-57-380-04 DATED 10/12/2004.
Part: SKIN — CORRODED (ZONE 500) · airframe 85,823 hrs · 34,028 cycles
DURING ROUTINE C CHECK, FOUND THE LT WING UPPER SURFACE CORRODED AT STATION XFS304. REMOVED LEFT WING CENTER SECTION LEADING EDGE TO FACILITATE REPAIR. REMOVED DAMAGE. FABRICATED FILLER AND DOUBLER. LOCATED, DRILLED, REMOVED, TREATED, PRIMED, AND INSTALLED FILLER, DOUBLER AND FASTENERS WET WITH SEALANT FROM STATION XFS304 TO XFS344. INSTALLED LEFT WING CENTER SECTION LEADING EDGE IAW DC8 SRM 57-2-1, 57-20-2, 51-1-5, AND 51-1-8.
Part: SKIN — DENTED (ZONE 600) · airframe 85,823 hrs · 34,028 cycles
DURING ROUTINE C CHECK, FOUND RIGHT WING OUTBOARD FLAP LOWER SKIN DENTED AT STATION XF208. REMOVED FASTENERS AS NEEDED TO REMOVE RIGHT WING OUTBOARD FLAP LOWER SKIN FROM STATION XF169 TO STATION XF213. FABRICATED, NEW SKIN AND FINGER DOUBLERS, LOCATED, DRILLED, TREATED, PRIMED, AND INSTALLED NEW SKIN AND FINGER DOUBLERS FROM STATION XF169 TO STATION XF213. IAW DC8 SRM 57-2-0, 51-1-21, 51-1-9, 57-7-1, 51-1-5, AND 51-1-8.
Part: RIB — CRACKED (ZONE 600) · airframe 85,823 hrs · 34,028 cycles
DURING ROUTINE C-CHECK, FOUND RIGHT WING LEADING EDGE CAVITY RIB CRACKED AT STATION XFS 397.75. REMOVED DAMAGE. FABRICATED REPAIR PART, LOCATED, DRILLED, TRIMMED, TREATED, PRIMED, INSTALLED REPAIR PART AND NEW FASTENERS AT RIGHT WING LEADING EDGE CAVITY AT STATION XFS 397.75 IAW DC8 SRM 57-2-0, 51-1-20, 51-1-4, 51-1-5, AND 51-1-8.
Part: LONGERON — CRACKED (ZONE 200) · airframe 85,823 hrs · 34,028 cycles
DURING ROUTINE C-CHECK FOUND LONGERON CRACKED AT STATION 280 LONGERON 7 RIGHT. CLEANED DAMAGE FABRICATED REPAIR PARTS, LOCATED, DRILLED, TREATED, PRIMED, AND INSTALLED REPAIR PARTS AND FASTENERS IAW DC8 SRM 53-2-2, 53-4-1, AND 51-1-8.
Part: SKIN — DELAMINATED (ZONE 600) · airframe 85,823 hrs · 34,028 cycles
DURING ROUTINE C CHECK, FOUND RIGHT HAND WING SPOILER NUMBER 3 DELAMINATED AT STATION XRS 218. REMOVED RIGHT HAND NUMBER 3 SPOILER. REMOVED UPPER, LOWER SKIN AND HONEYCOMB CORE. FABRICATED NEW REPAIR PARTS. INSTALLED AND BONDED REPAIR PARTS IN NUMBER 3 RIGHT HAND SPOILER. INSTALLED NUMBER 3 RIGHT HAND SPOILER, RIGGED AND OPERATIONAL CHECK GOOD IAW DC8 MM27-61-1, AND COOPESA EO COO-CMP-8-57-412-04 DATED10/28/2004.
Part: SKIN — DENTED (ZONE 500) · airframe 85,823 hrs · 34,028 cycles
DURING ROUTINE C-CHECK FOUND LT WING IB TRAILING EDGE FLAP LOWER SURFACE DENTED OUT OF LIMITS AT STATION XW39 AFT AREA. REMOVED DAMAGE. FABRICATED FILLER AND DOUBLER. LOCATED, DRILLED, TRIMMED, TREATED, PRIMED, AND INSTALLED FILLER AND DOUBLER WET WITH SEALANT FROM STATION XW34 TO STATION XW44. IAW SRM 57-2-5, 51-1-5, AND 51-1-8.
Part: SUPPORT CHANNEL — CRACKED (ZONE 100) · airframe 85,823 hrs · 34,028 cycles
DURING ROUTINE C CHECK FOUND FLOOR SUPPORT CHANNEL CRACKED IN THE AFT CARGO COMPARTMENT AT STATION 1263 BETWEEN LONGERON 33 LEFT AND 34 LEFT. REMOVED FASTENERS AS NEEDED TO REMOVE DAMAGED FLOOR SUPPORT CHANNEL, FABRICATED NEW FLOOR SUPPORT CHANNEL, LOCATED, DRILLED, TRIMMED, TREATED, PRIMED, INSTALLED NEW FLOOR SUPPORT CHANNEL, AND FASTENERS AT STATION 1263 BETWEEN LONGERON 33 LEFT AND 34 LEFT. IAW DC8 SRM 51-2-0, 51-1-21, 51-1-4, 51-1-5 AND 51-1-8.
Part: SKIN — DENTED (ZONE 500) · airframe 85,823 hrs · 34,028 cycles
DURING ROUTINE C CHECK, FOUND LEFT WING INBOARD TRAILING EDGE FLAP LOWER SURFACE DENTED OUT OF LIMITS AT STATION XW39. REMOVED DAMAGE. FABRICATED FILLER AND DOUBLER. LOCATED, DRILLED, REMOVED, TREATED, PRIMED, AND INSTALLED FILLER AND DOUBLER WET WITH SEALANT FROM STATION XW39 TO STATION XW45 IAW DC8 SRM 57-2-5, 51-1-5, AND 51-1-8.
Part: RIB — CRACKED (ZONE 600) · airframe 85,823 hrs · 34,028 cycles
DURING ROUTINE C-CHECK, FOUND RIGHT WING LEADING EDGE CAVITY RIB CRACKED AT STATION XFS 404. REMOVED DAMAGE. FABRICATED REPAIR PART, LOCATED, DRILLED, TRIMMED, TREATED, PRIMED, INSTALLED REPAIR PART AND NEW FASTENERS AT RIGHT WING LEADING EDGE CAVITY AT STATION XFS 404 IAW DC8 SRM 57-2-0, 51-1-20, 51-1-4, 51-1-5, AND 51-1-8.
Part: BULKHEAD — CRACKED (FUSELAGE) · airframe 85,823 hrs · 34,028 cycles
DURING ROUTINE C CHECK, FOUND WEB CRACKED AT STATION -175 FORWARD BULKHEAD LOWER SECTION. REMOVED FASTENERS AS NEEDED TO REMOVE DAMAGED WEB. FABRICATED WEB, LOCATED, DRILLED, TRIMMED, TREATED, PRIMED, INSTALLED NEW WEB AND FASTENERS AT STATION -175 FORWARD BULKHEAD LOWER SECTION. IAW DC8 SRM 51-1-21, 51-1-4, 51-1-5, AND 51-1-8.
Part: RIB — CRACKED (FUSELAGE) · airframe 85,823 hrs · 34,028 cycles
DURING ROUTINE C CHECK, FOUND RIB CRACKED AT STATION -175 FORWARD BULKHEAD RIGHT LOWER SECTION. REMOVED FASTENERS AS NEEDED TO REMOVE DAMAGED RIB. FABRICATED NEW RIB, LOCATED, DRILLED, TRIMMED, TREATED, PRIMED, INSTALLED NEW RIB AND FASTENERS AT STATION -175 FORWARD BULKHEAD RIGHT LOWER SECTION IAW DC8 SRM 51-1-21, 51-1-4, 51-1-5, AND 51-1-8.
Part: SKIN — DENTED (ZONE 500) · airframe 85,823 hrs · 34,028 cycles
DURING ROUTINE C-CHECK FOUND LT WING IB TRAILING EDGE FLAP UPPER SURFACE DENTED OUT OF LIMITS AT STATION XW35. REMOVED DAMAGE, FABRICATED FILLER AND DOUBLER. LOCATED, DRILLED, TRIMMED, TREATED, PRIMED, AND INSTALLED FILLER AND DOUBLER WET WITH SEALANT FROM STATION XW32 TO STATION XW39. IAW SRM 57-2-5, 51-1-5, AND 51-1-8.
Part: WEB — CRACKED (ZONE 100) · airframe 85,823 hrs · 34,028 cycles
DURING ROUTINE C-CHECK, FOUND WEB CRACKED IN THE AFT CARGO COMPARTMENT STATION 1267 BETWEEN +X40 AND -Z8. REMOVED DAMAGED AREA. FABRICATED DOUBLER, LOCATED, DRILLED, TRIMMED, TREATED, PRIMED, INSTALLED DOUBLER AND FASTENERS FROM STATION 1265 TO 1269 BETWEEN +X40 AND -Z8. IAW DC8 SRM 53-2-0, 51-4-5, 51-1-4, AND 51-1-8.
Part: SKIN — CRACKED (LT IB FLAP) · airframe 85,823 hrs · 34,028 cycles
DURING ROUTINE C-CHECK FOUND LT WING IB FLAP LEADING EDGE UPPER SKIN CRACKED AT STATION XW84. REMOVED FLAP VANE, AND NOSE PANEL TO FACILITATE REPAIR. REMOVED DAMAGE. FABRICATED FILLER AND DOUBLER. LOCATED, DRILLED, TRIMMED, TREATED, PRIMED, AND INSTALLED DOUBLER, FILLER, AND FASTENERS WET WITH SEALANT FROM STATION XW 81.5 TO STATION 86.5. INSTALLED FLAP VANE AND NOSE PANEL. IAW MM 27-51-14, OHM 27-27-1, SRM 57-2-1,57-7-1, 51-1-5 AND 51-1-8.
Part: LONGERON — CRACKED (ZONE 200) · airframe 85,823 hrs · 34,028 cycles
DURING ROUTINE C-CHECK FOUND A CRACKED LONGERON AT STATION 1747 LONGERON 15 RIGHT. CLEANED DAMAGED AREA, FABRICATED REPAIR PARTS, LOCATED, DRILLED TREATED, PRIMED, AND INSTALLED REPAIR PARTS AND FASTENERS IAW DC8 SRM 53-2-2, 52-1-5, AND 51-1-8.
Part: LONGERON — CRACKED (ZONE 200) · airframe 85,823 hrs · 34,028 cycles
DURING ROUTINE C-CHECK FOUND LONGERON CRACKED AT STATION 100 LONGERON 7 RIGHT. REMOVED DAMAGE. FABRICATED REPAIR PARTS, LOCATED, DRILLED, TREATED, PRIMED, AND INSTALLED REPAIR PARTS AND FASTENERS IAW DC8 SRM 53-2-2, 53-4-1, 51-1-5 AND 51-1-8.
Part: FRAME — CRACKED (ZONE 200) · airframe 85,823 hrs · 34,028 cycles
DURING ROUTINE C-CHECK FOUND RT FRAME CRACKED AT STATION 1978. REMOVED EXISTING FASTENERS, AND FRAME. FABRICATED FRAME, LOCATED, DRILLED TRIMMED, TREATED, PRIMED, INSTALLED FRAME AND FASTENERS WET WITH SEALANT. IAW DC8 SRM 53-2-051-1-21, 53-5-1, 51-1-4, 51-1-5, AND 51-1-8.
Part: LONGERON — CRACKED (ZONE 200) · airframe 85,823 hrs · 34,028 cycles
DURING ROUTINE C-CHECK FOUND LONGERON CRACKED AT STATION 100 LONGERON 9 RIGHT. REMOVED DAMAGE. FABRICATED REPAIR PARTS, LOCATED, DRILLED, TREATED, PRIMED, AND INSTALLED REPAIR PARTS AND FASTENERS IAW DC8 SRM 53-2-2, 53-4-1, 51-1-5 AND 51-1-8.
Part: SKIN — DENTED (ZONE 600) · airframe 85,823 hrs · 34,028 cycles
DURING ROUTINE C CHECK, FOUND RIGHT WING OUTBOARD FLAP LOWER SKIN DENTED BETWEEN STATION XF309 AND XF333. REMOVED FASTENERS AS NEEDED. REMOVED LOWER SKIN SECTION. FABRICATED NEW SKIN SECTION AND FILLERS. LOCATED, DRILLED, TRIMMED, TREATED, PRIMED, AND INSTALLED NEW SKIN AND NEW FASTENERS WET WITH SEALANT FROM STATION XF309 TO STATION XF333 IAW DC8 SRM 57-2-0, 51-1-21, 51-1-5, AND 51-1-8.
Part: SUPPORT FITTING — CRACKED (LT WING) · airframe 85,823 hrs · 34,028 cycles
DURING ROUTINE C CHECK, FOUND LEFT WING FLAP CANOE FITTING UPPER SUPPORT CRACKED AT STATION XRS 235. REMOVED FASTENERS AS NEEDED TO REMOVE DAMAGED FITTING. FABRICATED NEW SUPPORT, LOCATED, DRILLED, TRIMMED, TEREATED, PRIMED, INSTALLED NEW SUPPORT AND FASTWENERS ON LEFT HAND WING FLAP CANOE AT STATION XRS 235. IAW SRM 51-1-21, 51-1-4, 51-1-5, AND 51-1-8.
Part: LONGERON — CORRODED (ZONE 100) · airframe 85,823 hrs · 34,028 cycles
DURING ROUTINE C-CHECK FOUND LONGERON 28 RIGHT CORRODED AT STATION 330 TO 370. REMOVED DAMAGED LONGERON SECTION. FABRICATED REPAIR PARTS. LOCATED, DRILLED, TREATED, PRIMED, AND INSTALLED REPAIR PARTS IAW COOPESA EO COO-8-53-377-04.
Part: SKIN — DENTED (ZONE 600) · airframe 85,823 hrs · 34,028 cycles
DURING ROUTINE C CHECK, FOUND RIGHT WING OUT BOARD FLAP DENTED AT STATION XW384. REMOVED FASTENERS AS NEEDED. REMOVED DAMAGE. FABRICATED REPAIR PARTS, LOCATED, DRILLED TRIMMED, TREATED, PRIMED, INSTALLED NEW REPAIR PARTS AND NEW FASTENESR WET WITH SEALANT FROM STATION WX382 TO STATION XW385 IAW DC8 SRM 57-2-5, 51-1-5, AND 51-1-8.
Part: SKIN — DENTED (ZONE 600) · airframe 85,823 hrs · 34,028 cycles
DURING ROUTINE C CHECK, FOUND RIGHT WING INBOARD FLAP TRAILING EDGE HAS SEVERAL DENTS BETWEEN STATIONS XW64 AND XW101. REMOVED DAMAGED SKIN. FABRICATED REPAIR PARTS, LOCATED, DRILLED, TRIMMED, TREATED PRIMED, INSTALLED REPAIR PARTS AND NEW FASTENERS. IAW DC8 SRM 57-1-0, 51-1-21, 51-1-9, 51-1-5, AND 51-1-8.
Part: RIB — CRACKED (ZONE 600) · airframe 85,823 hrs · 34,028 cycles
DURING ROUTINE C CHECK, FOUND RIGHT WING TRAILING EDGE UPPER RIB CRACKED AT STATION XW65. REMOVED FASTENERS AS NEEDED TO REMOVE DAMAGED RIB. FABRICATED NEW RIB. LOCATED, DRILLED TRIMMED, TREATED, PRIMED, INSTALLED NEW RIB AND FASTENERS AT RIGHT WING TRAILING EDGE STATION XW65. IAW DC8 SRM 57-1-0, 51-1-20, 51-1-21, 51-3-0, 51-1-4, 51-1-5, AND 51-1-8.
Part: CLOSEOUT PANEL — CORRODED (WING) · airframe 85,823 hrs · 37,028 cycles
DURING ROUTINE C-CHECK FOUND AFT WING FILLET PANEL NUMBER 161X SKIN DISBONDED AND CORRODED. FABRICATED NEW PANEL, LOCATED, DRILLED, TREATED, PRIMED, AND INSTALLED NEW FILLET PANEL IAW COOPESA EO COO-8-53-431-04.
Part: SKIN — DENTED (ZONE 600) · airframe 85,823 hrs · 34,028 cycles
DURING ROUTINE C-CHECK, FOUND RIGHT WING INBOARD FLAP LOWER SURFACE HAS SEVERAL DENTS BETWEEN STATION XW15 AND XW45. REMOVED DAMAGED SKIN. FABRICATED REPAIR PARTS. PERFORMED HOT BOND TO DAMAGED AREA IAW DC8 SRM 57-1-0, 51-1-9, 51-1-5 AND 51-1-8.
Part: SKIN — DENTED (RT OB FLAP) · airframe 85,823 hrs · 34,028 cycles
DURING ROUTINE C-CHECK FOUND RT WING OB FLAP UPPER LEADING EDGE SKIN DENTED AT STATION XF 418. REMOVED DAMAGED. FABRICATED REPAIR PART, LOCATED, DRILLED, TRIMMED, TREATED, PRIMED, INSTALLED REPAIR PART AND NEW FASTENERS AT RT WING OB FLAP UPPER LEADING EDGE AT STATION XF 418. IAW SRM 57-2-0, 51-1-21, 51-3-0, 51-1-5, AND 51-1-8.
Part: STRAP — CORRODED (ZONE 100) · airframe 85,823 hrs · 34,028 cycles
DURING ROUTINE C-CHECK FOUND CORROSION ON WING FILLET STRAPS AT STATION 980 TO 1160. REMOVED DAMAGED STRAPS. FABRICATED NEW STRAPS, LOCATED, DRILLED, TREATED, PRIMED, AND INSTALLED NEW STRAPS AND FASTENERS IAW DC8 SRM 53-2-0, 51-1-8, 51-1-4, AND 51-1-5.
Part: SKIN — CORRODED (ZONE 100) · airframe 85,823 hrs · 34,028 cycles
DURING ROUTINE C-CHECK FOUND CORROSION AT FORWARD CARGO COMPARTMENT INNER SKIN STATION 280. REMOVED DAMAGED AREA, FABRICATED REPAIR PARTS, LOCATED, DRILLED, TREATED, PRIMED, AND INSTALLED NEW REPAIR PARTS AND FASTENERS AT STATION 276.5 TO 280 BETWEEN LONGERON 35 RIGHT AND 35 LEFT IAW DC8 SRM 53-2-0, 51-1-4, 51-3-0, 53-4-1 AND 51-1-8.
Part: SKIN — CRACKED (ZONE 200) · airframe 85,823 hrs · 34,028 cycles
DURING ROUTINE C-CHECK FOUND EXTERNAL FUSELAGE SKIN CRACKED AT STATION 17 BETWEEN LONGERONS 14 LEFT ANF 17 LEFT, FORWARD ENTRANCE HOLD OPEN PAN AREA. REMOVED DAMAGE. FABRICATED REPAIR PARTS, LOCATED, DRILLED, TREATED, PRIMED, AND INSTALLED REPAIR PARTS AND FASTENERS IAW COOPESA EO COO-8-53-376-04.
Part: BEAM — CRACKED (ZONE 800) · airframe 85,823 hrs · 34,028 cycles
DURING ROUTINE C-CHECK FOUND FORWARD ENTRY DOOR NR 1 BEAM CRACKED. REMOVED DAMAGE, FABRICATED REPAIR PARTS, LOCATED, DRILLED, TREATED, PRIMED, AND INSTALLED REPAIR PARTS AND FASTENERS IAW DC8 SRM 52-2-0, 52-3-1, 51-1-4, 51-1-5, AND 51-1-8.
Part: SKIN — DENTED (ZONE 100) · airframe 85,823 hrs · 34,028 cycles
DURING ROUTINE C-CHECK FOUND AFT CARGO DOOR SKIN DENTED AT STATION 1402 TO 1407.7 NUMBER 4 BEAM AND LOWER FRAME. REMOVED AFT CARGO DOOR. REMOVED DAMAGED AREA, FABRICATED REPAIR PARTS, LOCATED, DRILLED, TREATED, PRIMED, AND INSTALLED REPAIR PARTS AND NEW FASTENERS. INSTALLED AND ADJUSTED DOOR IAW DC8 MM 52-32-1, DC8 SRM 52-2-3, 52-4-1, AND 51-1-8.
Part: WEB — CRACKED (FUSELAGE) · airframe 85,823 hrs · 34,028 cycles
DURING ROUTINE C CHECK, FOUND EXTERNAL FUSELAGE WEB CRACKED AT STATION 857 AT -X16. REMOVED DAMAGE. FABRICATED FILLER AND DOUBLER, LOCATED, DRILLED, TRIMMED, TREATED, PRIMED, INSTALLED FILLER, DOUBLER AND FASTENERS AT STATION 857 FROM -X11 TO -X21 IAW DC8 SRM 53-2-0, 53-8-1, 51-1-4, 561-1-5 AND 51-1-8.
Part: WEB — CRACKED (FUSELAGE) · airframe 85,823 hrs · 34,028 cycles
DURING ROUTINE C CHECK, FOUND EXTERNAL FUSELAGE WEB CRACKED AT STATION 810 AT -X68. REMOVED DAMAGED. FABRICATED FILLER AND DOUBLER, LOCATED, DRILLED, TRIMMED, TREATED, PRIMED, INSTALLED FILLER, DOUBLER AND FASTENERS AT STATION 810 BETWEEN -X50 AND -X70 IAW DC8 SRM 53-2-0, 53-8-1, 51-1-4, 561-1-5 AND 51-1-8.
Part: SUPPORT ANGLE — CRACKED (FUSELAGE) · airframe 85,823 hrs · 34,028 cycles
DURING ROUTINE C CHECK, FOUND EXTERNAL FUSELAGE SUPPORT ANGLE CRACKED AT STATION 640 BETWEEN +X70 AND -Z35. REMOVED FASTENERS AS NEEDED TO REMOVE DAMAGED SUPPORT ANGLE. FABRICATED NEW SUPPROT ANGLE, LOCATED, DRILLED, TREATED, PRIMED, INSTALLED NEW SUPPORT ANGLE AND FASTENERS AT STATION 640 BETWEEN +X70 AND -Z35. IAW DC8 SRM 53-2-1, 51-1-20, 51-1-4, 51-1-5, AND 51-1-8.
Part: ANGLE — CRACKED (FUSELAGE) · airframe 85,823 hrs · 34,028 cycles
DURING ROUTINE C CHECK, FOUND EXTERNAL FUSELAGE ANGLE CRACKED AT STATION 980 BETWEEN +X65 TO -Z54. REMOVED FASTENERS AS NEEDED TO REMOVE DAMAGED ANGLE. FABRICATED NEW ANGLE, LOCATED, DRILLED, TRIMMED, TREATED, PRIMED, INSTALLED NEW EXTERNAL FUSELAGE ANGLE AND FASTENERS AT STATION 980 BETWEEN +X65 AND -Z54 IAW 53-8-1, 51-1-4, 51-1-5, AND 51-1-8.
Part: SUPPORT — CRACKED (FUSELAGE) · airframe 85,723 hrs · 34,028 cycles
DURING ROUTINE C CHECK FOUND A CRACKED LATERAL SUPPORT IN THE AFT CARGO COMPARTMENT AT STATION 1160 LONGERON 27 LEFT. REMOVED DAMAGE. FABRICATED REPAIR PARTS, LOCATED, DRILLED, TRIMMED, TREATED, PRIMED, INSTALLED REPAIR PARTS, AND NEW FASTENERS FROM STATION 1155 AND 1160 BETWEEN +X50 AND +X54. IAW DC8 SRM 53-2-0, 51-1-5, AND 51-1-8.
Part: SUPPORT — CRACKED (FUSELAGE) · airframe 85,823 hrs · 34,028 cycles
DURING ROUTINE C CHECK, FOUND A CRACKED LATERAL SUPPORT IN THE AFT CARGO COMPARTMENT AT STATION 1140 LONGERON 27 LEFT. REMOVED DAMAGE. FABRICATED REPAIR PARTS, LOCATED, DRILLED, TRIMMED, TREATED, PRIMED, INSTALLED REPAIR PARTS, AND NEW FASTENERS FROM STATION 1138 AND 1142 BETWEEN +X50 AND +X54 IAW DC8 SRM 53-2-0, 51-1-5, AND 51-1-8.
Part: DOUBLER — WORN (FUSELAGE) · airframe 85,723 hrs · 34,028 cycles
DURING ROUTINE C CHECK, FOUND EXTERNAL FUSELAGE DOUBLER WORN AT STATION 980 BETWEEN +X65 TO -Z54. REMOVED FASTENERS AS NEEDED TO REMOVE DAMAGED DOUBLER. FABRICATED NEW ANGLE, LOCATED, DRILLED, TRIMMED, TREATED, PRIMED, INSTALLED NEW EXTERNAL FUSELAGE DOUBLER AND FASTENERS AT STATION 980 BETWEEN +X65 AND -Z54. IAW 53-8-1, 51-1-4, 51-1-5, AND 51-1-8.
Part: LONGERON — TOOL DAMAGE (ZONE 100) · airframe 85,823 hrs · 34,028 cycles
DURING ROUTINE C-CHECK FOUND A FITTING WITH A DOUBLE HOLE AT STATION 580 OVER LONGERON 33 RIGHT. FABRICATED NEW FITTING. LOCATED, DRILLED, TREATED, PRIMED, AND INSTALLED NEW FITTING IAW DC8 SRM 53-2-0, 51-1-21, AND 51-1-8.
Part: RIB — CRACKED (ZONE 200) · airframe 85,823 hrs · 34,028 cycles
DURING ROUTINE C-CHECK FOUND FORWARD ENTRY DOOR CUT OUT, AFT RIB CRACKED BETWEEN LONGERON 19 LT AND 20 LT. REMOVED FASTENERS AS NEEDED TO REMOVE DAMAGED RIB. FABRICATED NEW RIB, LOCATED, DRILLED,TREATED, PRIMED, INSTALLED NEW RIB AND NEW FASTENERS. IAW SRM 53-2-0, 51-1-20, 51-1-21, 51-1-4, 51-1-5, AND 51-1-8.
Part: RIB — CRACKED (ZONE 600) · airframe 85,823 hrs · 34,028 cycles
DURING ROUTINE C CHECK, FOUND RIGHT HAND WING LEADING EDGE CAVITY AT STATION XFS410.25 AND 416.500 UPPER RIBS CRACKED. REMOVED NEEDED FASTENERS. REMOVED DAMAGE. FABRICATED REPAIR PARTS, LOCATED, TRIMMED, TREATED, PRIMED, AND INSTALLED REPAIR PARTS AND NEW FASTENERS IAW DC87 SRM 57-2-0, 51-1-20, 51-1-4, 51-1-5, AND 51-1-8.
Part: SKIN — CRACKED (ZONE 800) · airframe 85,823 hrs · 34,028 cycles
DURING ROUTINE C-CHECK FOUND SKIN CRACKED AT AFT CARGO BASKET DOOR AFT RIGHT UPPER CORNER APPROXIMATELY STATION 1200. REMOVED CARGO DOOR. REMOVED DAMAGED SKIN. FABRICATED REPAIR PARTS, LOCATED, DRILLED, TREATED, PRIMED, AND INSTALLED REPAIR PARTS. INSTALLED AND ADJUSTED CARGO DOOR IAW SC8 SRM 52-2-0, 52-4-0, AND 51-1-8, DC8 MM 52-31-1.
Part: RIB — CRACKED (ZONE 600) · airframe 85,823 hrs · 34,028 cycles
DURING ROUTINE C-CHECK, FOUND RT WING LEADING EDGE LOWER RIB CRACKED AT STATION XFS360. REMOVED DAMAGE. FABRICATED REPAIR PART, LOCATED, DRILLED, TREATED, PRIMED, INSTALLED REPAIR PART AND NEW FASTENERS AT RT WING LEADING EDGE STATION XFS360. IAW SRM 57-2-0, 51-1-4, 51-1-5, AND 51-1-8.
Part: SKIN — CORRODED (VERTICAL STAB) · airframe 85,823 hrs · 34,028 cycles
DURING ROUTINE C CHECK, FOUND VERTICAL STABILIZER LEFT SIDE PANEL INTERNAL SKIN CORRODED BETWEEN STATION ZR253 AND STATION ZR299.125. REMOVED EXISTING STRUCTURE FROM DAMAGED PANEL. FABRICATED NEW SKIN PANEL AND STIFFENERS. LOCATED, DRILLED, TRIMMED, TREATED, PRIMED, INSTALLED STRUCTURE, NEW STIFFENERS, AND FASTENERS WET WITH SEALANT. YAW COPES EGO. COO-8-55-382-04 DATED 10/12/2004.
Part: WEB — CRACKED (FUSELAGE) · airframe 85,823 hrs · 34,028 cycles
DURING ROUTINE C CHECK, FOUND EXTERNAL FUSELAGE WEB CRACKED AT STATION 857 AND +X16. REMOVED DAMAGED AREA. FABRICATED DOUBLER AND FILLERS, LOCATED, DRILLED, TRIMMED, TREATED, PRIMED, INSTALLED NEW DOUBLER, FILLERS AND FASTENERS AT STATION 857 FROM +X11 TO +X19.5. IAW DC8 SRM 53-8-1, 51-1-4, 51-1-5, AND 51-1-8.
Part: SUPPORT ANGLE — CORRODED (FUSELAGE) · airframe 85,823 hrs · 34,028 cycles
DURING ROUTINE C CHECK, FOUND FLOOR SUPPORT ANGLE CORRODED IN THE FORWARD CARGO COMPARTMENT BETWEEN STATION 580 AND 637 AT LONGERON 33 RIGHT. REMOVED FASTENERS AS NEEDED TO REMOVE DAMAGED FLOOR SUPPROT ANGLE. FABRICATED NEW ANGLE. LOCATED, DRILLED, TRIMMED, TREATED, PRIMED, INSTALLED NEW FLOOR SUPPORT ANGLE AND FASTENERS FROM STATION 580 TO STATION 637 AT LONGERON 33 RIGHT IAW DC8 SRM 53-2-0, 51-1-21, 51-1-4, 51-1-5, AND 51-1-8.
Part: ANGLE — CRACKED (FUSELAGE) · airframe 85,823 hrs · 34,028 cycles
DURING ROUTINE C CHECK, FOUND EXTERNAL FUSELAGE ANGLE CRACKED AT STATION 857 AND +X16. REMOVED FASTENERS AS NEEDED TO REMOVE DAMAGED ANGLE. FABRICATED NEW ANGLE, LOCATED, DRILLED, TRIMMED, TREATED, PRIMED, INSTALLED NEW ANGLE AND FASTENERS AT STATION 857 FROM +X13 TO +X22.5 IAW DC8 SRM 53-8-1, 51-1-4, 51-1-5, AND 51-1-8.
Part: ANGLE — CORRODED (ZONE 100) · airframe 85,823 hrs · 34,028 cycles
DURING ROUTINE C-CHECK FOUND ANGLE CORRODED AT STATION 297 LONGERON 29 LEFT. REMOVED ANGLE, FABRICATED NEW ANGLE, LOCATED, DRILLED, TREATED, PRIMED, AND INSTALLED NEW ANGLE WITH NEW HI-LOKS AND RIVETS IAW DC8 SRM 51-1-21, 51-1-4, 51-1-5, AND 51-1-8.
Part: WEB — CRACKED (FUSELAGE) · airframe 85,823 hrs · 34,028 cycles
DURING ROUTINE C CHECK, FOUND A CRACKED WEB AT EXTERNAL FUSELAGE STATION 781.5 +X18. REMOVED HYDRAULIC LINES FOR ACCESS. REMOVED ACCESS PANEL. REMOVED DAMAGE. FABRICATED REPAIR PARTS, LOCATED, DRILLED, TRIMMED, TREATED, PRIMED, INSTALLED NEW REPAIR PARTS AND FASTENERS AT STATION 781.5 BETWEEN +X6 AND +X44. INSTALLED ACCESS PANEL, AND HYDRAULIC LINES, AND LEAK CHECKED IAW DC8 MM 20-12-0, 20-16-0, 29-00-00 DC8 SRM 53-2-0, 53-8-1, 51-1-4, 51-1-5, AND 51-1-8.
Part: SKIN — DENTED (RT ELEVATOR) · airframe 85,823 hrs · 34,028 cycles
DURING ROUTINE C CHECK, FOUND RIGHT ELEVATOR UPPER SKIN DENTED OUT OF LIMITS AT STATION XE 111.006. REMOVED DAMAGE, FABRICATED FILLER AND DOUBLER. LOCATED, DRILLED, REMOVED, TREATED, PRIMED, INSTALLED REPAIR PARTS, AND FASTENERS WET WITH SEALANT FROM STATION XE 106 TO STATION 117 IAW DC8 SRM 55-2-1, 51-1-4, 51-1-5, AND 51-1-8.
Part: RIB — CRACKED (ZONE 600) · airframe 8,823 hrs · 34,028 cycles
DURING ROUTINE C CHECK FOUND RT WING LEADING EDGE UPPER RIB CRACKED AT STATION XFS722.500. REMOVED DAMAGE. FABRICATED REPAIR PART, LOCATED, DRILLED, TRIMMED, TREATED, PRIMED, INSTALLED REPAIR PART AND NEW FASTENERS AT RT WING UPPER LEADING EDGE STATION XFS722.500. IAW SRM 57-2-0, 51-1-4, 51-1-5, AND 51-1-8.
Part: DOUBLER — CORRODED (FUSELAGE) · airframe 85,823 hrs · 34,028 cycles
DURING ROUTINE C CHECK, FOUND LOWER FUSELAGE DOUBLER CORRODED FROM STATION 690 TO 778. REMOVED FASTENERS AS NEEDED TO REMOVE EXISTING DAMAGED DOUBLER. FABRICATED NEW DOUBLER, LOCATED, DRILLED, TRIMMED, TREATED, PRIMED, INSTALLED NEW DOUBLER, AND FASTENERS WET WITH SEALANT FROM STATION 690 TO 778. IAW DC8 SRM 53-2-0, 51-1-5, AND 51-1-8.
Part: WEB — CRACKED (FUSELAGE) · airframe 85,823 hrs · 34,028 cycles
DURING ROUTINE C CHECK, FOUND A CRACKED WEB AT EXTERNAL FUSELAGE STATION 778.5 BETWEEN LONGERON 33 RIGHT AND 35 RIGHT. REMOVED HYDRAULIC LINES FOR ACCESS. REMOVED ACCESS PANEL. REMOVED DAMAGE. FABRICATED REPAIR PARTS, LOCATED, DRILLED, TRIMMED, TREATED, PRIMED, INSTALLED NEW REPAIR PARTS AND FASTENERS AT STATION 786.5 BETWEEN +X6 AND +X44. INSTALLED ACCESS PANEL, AND HYDRAULIC LINES, AND LEAK CHECKED IAW DC8 MM 20-12-0, 20-16-0, 29-00-00 DC8 SRM 53-2-0, 53-8-1, 51-1-4, 51-1-5, AND 51-1-8.
Part: RIB — CRACKED (ZONE 600) · airframe 85,823 hrs · 34,028 cycles
DURING ROUTINE C CHECK FOUND RT WING LEADING EDGE LOWER RIB CRACKED AT STATION XFS635. REMOVED DAMAGE. FABRICATED REPAIR PART, LOCATED, DRILLED, TREATED, PRIMED, INSTALLED REPAIR PART AND NEW FASTENERS AT RT WING LEADING EDGE STATION XFS635. IAW SRM 57-2-0, 51-1-20, 51-1-4, 51-1-5, AND 51-1-8.
Part: WEB — CRACKED (ZONE 600) · airframe 85,823 hrs · 34,028 cycles
DURING ROUTINE C-CHECK FOUND RT WING LEADING EDGE UPPER WEB CRACKED AT STATION XFS610. REMOVED FASTENERS AS NEEDED TO REMOVE DAMAGED WEB. FABRICATED NEW WEB, LOCATED, DRILLED, TRIMMED, TREATED, PRIMED, INSTALLED NEW WEB AND NEW FASTENERS AT RT WING UPPER LEADING EDGE STATION XFS610. IAW SRM 57-2-0, 51-1-4, 51-1-5, AND 51-1-8.
Part: FRAME — CORRODED (FUSELAGE) · airframe 85,823 hrs · 34,028 cycles
DURING ROUTINE C CHECK, FOUND FRAME CORRODED AT STATION 1978 -X2. FABRICATED NEW FRAME, LOCATED, DRILLED, TREATED, PRIMED, INSTALLED FRAME AND FASTENERS AT STATION 1798 IAW DC8 SRM 53-2-0, 51-1-21, 53-5-1, 51-1-4, 51-1-5, AND 51-1-8. SEE SDR IXXA060030S.
Part: SPLICE — BROKEN (BS 440-460) · airframe 85,823 hrs · 34,028 cycles
DURING ROUTINE C-CHECK FOUND LONGERON SPLICE BROKEN AT STATION 440 TO STATION 460 LONGERON 31 RIGHT. FABRICATED NEW SPLICE, LOCATED, DRILLED, TREATED, PRIMED, AND INSTALLED, NEW SPLICE AND FASTENERS IAW DC8 SRM 53-2-0, 51-1-20, AND 51-1-8.
Part: SKIN — DENTED (ZONE 800) · airframe 85,823 hrs · 34,028 cycles
DURING ROUTINE C-CHECK FOUND FORWARD CARGO DOOR DENTED AT STATION 523 BETWEEN LONGERON 31 RIGHT AND 32 LEFT. REMOVED DOOR. REMOVED DAMAGED AREA, FABRICATED REPAIR PARTS, LOCATED, DRILLED, PRIMED AND INSTALLED REPAIR PARTS. INSTALLED AND ADJUSTED DOOR IAW DC8 MM 52-30-02, DC8 SRM 52-2-3, 52-4-1, 51-1-5, AND 51-1-8.
Part: SUPPORT ANGLE — CRACKED (FUSELAGE) · airframe 85,823 hrs · 34,028 cycles
DURING ROUTINE C CHECK FOUND A CRACKED SUPPORT ANGLE AT EXTERNAL FUSELAGE STATION 781.5, +X65. REMOVED DAMAGE. FAB`D REPAIR ANGLE, LOCATED, DRILLED, TRIMMED TREATED, PRIMED, INSTALLED REPAIR ANGLE AND NEW FASTENERS AT EXTERNAL FUSELAGE STATION 781.5, +X65. IAW DC8 SRM 53-2-0, 51-1-20, 51-1-21, 51-1-4, 51-1-5, AND 51-1-8.
Part: RIB — CRACKED (ZONE 600) · airframe 85,823 hrs · 34,028 cycles
DURING ROUTINE C CHECK FOUND RT WING LEADING EDGE UPPER RIB CRACKED AT STATION XFS672. REMOVED DAMAGE. FABRICATED REPAIR PART, LOCATED, DRILLED, TREATED, PRIMED, INSTALLED REPAIR PART AND NEW FASTENERS AT RT WING LOWER LEADING EDGE STATION XFS672. IAW SRM 57-2-0, 51-1-4, 51-1-5, AND 51-1-8.
Part: RIB — CRACKED (ZONE 600) · airframe 85,823 hrs · 34,028 cycles
DURING ROUTINE C CHECK FOUND RT WING LEADING EDGE UPPER RIB CRACKED AT STATION XFS735. REMOVED DAMAGE. FABRICATED REPAIR PART, LOCATED, DRILLED, TREATED, PRIMED, INSTALLED REPAIR PART AND NEW FASTENERS AT RT WING UPPER LEADING EDGE STATION XFS735. IAW SRM 57-2-0,57-1-20D 51-1-4, 51-1-5, AND 51-1-8.
Part: SKIN — CORRODED (ZONE 100) · airframe 85,823 hrs · 34,028 cycles
DURING ROUTINE C-CHECK FOUND CORROSION AND EXISTING BLEND OUTS AT STATION 980 TO 1040 BETWEEN 35 LEFT AND 35 RIGHT. REMOVED CORROSION, MANUFACTURED REPAIR PARTS, LOCATED DRILLED, PRIMES AND INSTALLED REPAIR PARTS AND FASTENERS IAW COOPESA EO COO-8-53-401-04.
Part: STRINGER — CRACKED (HORIZ STAB) · airframe 85,823 hrs · 34,028 cycles
DURING ROUTINE C CHECK, FOUND LEFT HORIZONTAL STABILIZER INNER SPAR BOX UPPER SECTION STRINGER NUMBER 1 CRACKED AT STATION XFS 47.500. STOP DRILLED CRACK. FABRICATED REPAIR PARTS, LOCATED, DRILLED, TREATED, PRIMED, INSTALLED REPAIR PARTS WITH SEALANT BETWEEN THE FAYING SURFACES, AND FASTENERS IAW COOPESA E.O. COO-8-55-390-04 DATED 10/14/2004.
Part: RIB — CRACKED (HORIZ STAB) · airframe 85,823 hrs · 34,028 cycles
DURING ROUTINE C CHECK, FOUND LEFT HAND HORIZONTAL STABILIZER LEADING EDGE INBOARD RIB CRACKED AT STATION XFS 116.250. REMOVED DAMAGE. FAB`D REPAIR PART, LOCATED, DRILLED, TRIMMED, TREATED, PRIMED AND INSTALLED REPAIR PART AT STATION XFS 116.250 IN LEFT HORIZONTAL STABILIZER LEADING EDGE IAW DC8 SRM 55-2-0, 51-1-4, 51-1-5, AND 51-1-8.
Part: SKIN — DENTED (XFS 307.750) · airframe 85,823 hrs · 34,028 cycles
DURING ROUTINE C-CHECK FOUND LT HORIZONTAL STABILIZER LEADING EDGE DENTED AT STATION XFS 307.750. REMOVED DAMAGE. FABRICATED REPAIR PARTS, LOCATED, DRILLED, TRIMMED, TREATED, PRIMED, INSTALLED REPAIR PARTS, AND FASTENERS, WET WITH SEALANT FROM STATION XFS 300 TO STATION XFS 312 IAW SRM 55-2-1, 51-1-4, 51-1-5, AND 51-1-8.
Part: RIB — CRACKED (HORIZ STAB) · airframe 85,823 hrs · 34,028 cycles
DURING ROUTINE C CHECK, FOUND RIGHT HORIZONTAL STABILIZER LEADING EDGE INBOARD RIB CRACKED AT STATION XFS 53.500. REMOVED DAMAGE. FAB`D REPAIR PART, LOCATED, DRILLED, TRIMMED, TREATED, PRIMED AND INSTALLED REPAIR PART AT STATION XFS 53.500 IN RIGHT HORIZONTAL STABILIZER LEADING EDGE IAW DC8 SRM 55-2-0, 51-1-4, 51-1-5, AND 51-1-8.
Part: SKIN — DENTED (VERTICAL STAB) · airframe 85,823 hrs · 34,028 cycles
DURING ROUTINE C-CHECK FOUND VERTICAL STABILIZER LEADING EDGE DENTED AT STATION ZFS 121. REMOVED DAMAGE. FABRICATED FILLER AND DOUBLER, LOCATED, DRILLED, TRIMMED, TREATED, PRIMED, INSTALLED FILLER, DOUBLER AND FASTENERS WET WITH SEALANT FROM STATION ZFS 114.5 TO STATION ZFS 126. IAW SRM 55-2-1, 55-5-1, 51-1-4, 51-1-5, AND 51-1-8.
Part: RIB — CRACKED (HORIZ STAB) · airframe 858,233 hrs
DURING ROUTINE C CHECK, FOUND RIGHT HORIZONTAL STABILIZER LEADING EDGE INBOARD RIB CRACKED AT STATION XFS 141.250. REMOVED DAMAGE. FAB`D REPAIR PART, LOCATED, DRILLED, TRIMMED, TREATED, PRIMED AND INSTALLED REPAIR PART AT STATION XFS 141.250 IN RIGHT HORIZONTAL STABILIZER LEADING EDGE IAW DC8 SRM 55-2-0, 51-1-4, 51-1-5, AND 51-1-8.
Part: SKIN — CRACKED (ZONE 100) · airframe 85,823 hrs · 34,028 cycles
DURING ROUTINE C-CHECK UPON FLIGHT READINESS FOUND SKIN DAMAGED ADJACENT TO GROUND POWER DOOR AREA, UPPER LEFT CORNER, STOP DRILLED. REPAIRED EXTERNAL FUSELAGE SKIN BY REMOVING DAMAGED SKIN, FABRICATED NEW SKIN SECTION AND DOUBLERS, LOCATED REPAIR PARTS, DRILLED, TRIMMED, TREATED, PRIMED, AND INSTALLED REPAIR PARTS AND FASTENERS AT STATION -22 TO STATION -48 BETWEEN LONGERONS 30 RIGHT AND 33 RIGHT IAW COOPESA EO COO-8-53-378-04.
Part: SKIN — DENTED (HORIZ STAB) · airframe 85,823 hrs · 34,028 cycles
DURING ROUTINE C CHECK, FOUND LEFT HORIZONTAL STABILIZER L/E DENTED AT STATION XFS 188.750. REMOVED DAMAGE. FAB`D REPAIR PARTS. LOCATED, DRILLED, REMOVED, TREATED, PRIMED, INSTALLED REPAIR PARTS, AND FASTENERS WET WITH SEALANT FROM STATION XFS 185.5 TO STATION 199.5 IAW DC8 SRM 55-2-1, 55-3-1, 51-1-4, 51-1-5, AND 51-1-8.
Part: CONTROL CABLE — LOOSE (ELEVATOR TRIM) · airframe 84,924 hrs · 33,656 cycles
DURING CLIMB FROM KLAX TO KTOL, AT LOW SPEEDS, CREW HAD ELEVATOR VIBRATION. VIBRATION WENT AWAY WHEN AIRCRAFT REACHED 280 KTS SPEED. CREW CONTINUED FLIGHT TO KTOL. AN INVESTIGATION IS ON GOING. WHEN MORE INFORMATION IS AVAILABLE IT WILL BE PROVIDED. LEFT HAND ELEVATOR CONTROL TAB HAD TRAILING EDGE PLAY. MAINTENANCE FOUND LEFT ELEVATOR TRIM CABLE TENSION LOW. ADJUSTED AND INSPECTED ELEVATOR PER ALL APPLICABLE MANUALS. OPERATIONAL CHECK WAS GOOD AND TEST FLIGHT WAS NOT REQUIRED. AIRCRAFT WAS RETURNED TO SERVICE.
2003
Part: PLATE — LOOSE (NR 4 ENGINE) · airframe 84,469 hrs · 33,420 cycles
JUST AFTER LEVEL OFF AT 33.0 NR 4 ENGINE OIL QUANTITY DECREASED RAPIDLY WITH LOW OIL PRESSURE (13PSI) AND NR 4 OIL PRESS LIGHT ILLUMINATED UP FRONT. ENGINE WAS SHUT DOWN AT 0340Z, WTIH OIL QUANTITY AT 3 QUARTS- OIL PRESSURE WENT TO ZERO AT 0349 AND REMAINED THERE FOR REST OF FLIGHT. MAINTENANCE FOUND COVER PLATE OF STARTER LOOSE. THEY CORRECTED LEAK SOURCE AT STARTER, COMPLIED WITH ATI ENGINE RUN HANDBOOK AND ERH PROCEDURES. NO LEAKS NOTED ON ENGINE RUN. AIRCRAFT WAS RETURNED TO SERVICE.
Part: WIRE HARNESS — DAMAGED (NR 1 ENGINE) · airframe 84,418 hrs · 33,390 cycles
ON TAKEOFF FROM KLRD TO KTOL NR 1 EGT FLUCUATED WILDLY BETWEEN 700 DEGREES AND OFF SCALE HIGH (1000). BOTH ANALOG AND DIGITAL EGT FOLLOWED THROTTLE BUT CONTINUED TO FLUCTUATE ERRATICALLY TO 1000 DEGREES. FUEL FLOW FLUCTUATES 150-200 LBS PRECAUTIONARY ENGINE SHUTDOWN PERFORMED AT 0404Z OIL PRESS 1LB AT 28 N1. N1 AND N2 APPEARED NORMAL, ALL OTHER ENGINE PARAMETERS NORMAL. CREW CONTINUED FLIGHT. MAINTENANCE RAN NR 1 ENG IAW ATI ERH 70.01.01 AND PERFORMED POWER ASSURANCE TEST IAW ATI ERH 91.01.03. NO FLUCUTATION IN ENGINE PARAMETERS NOTED. PIGTAIL FOR NR 1 ENGINE WAS REMOVED AND REPLACED PER ALL APPLICABLE MANUALS. AIRCRAFT WAS RETURNED TO SERVICE.
Part: LINE — CRACKED (OIL SYSTEM) · airframe 84,074 hrs · 33,181 cycles
DURING FLIGHT FROM KSJC TO KTOL, NR 2 OIL PRESSURE LIGHT ILLUMINATED WITH 20 PSI OIL PRESSURE, TEMP 72 DEGREE C AND OIL QUANTITY 3 QUARTS. SHUT DOWN NR 2 ENGINE. CREW LANDED IN TOL WITHOUT INCIDENT. MAINTENANCE FOUND LINE AFT OF OIL PRESSURE TRANSMITTER CRACKED AT FLARE. MAINTENANCE REMOVED AND REPLACED LINE IN ACCORDANCE WITH DOUGLAS AIRCRAFT DC-8 MAINTENANCE MANUAL. OPERATIONAL CHECK GOOD ON GROUND. NO OTHER DEFECTS NOTED. AIRCRAFT WAS RETURNED TO SERVICE.
Part: STATOR VANE — OUT OF RIG (NR 3 ENGINE) · airframe 83,965 hrs · 33,142 cycles
EN ROUTE TO KRFD FROM IAH NR 3 ENGINE COMPRESSER STALLED ON DECELERATION OF DESCENT. ON LEVEL OFF, ENGINE STALLED AGAIN WHEN POWER WAS APPLIED. IT WAS DECIDED TO FLY DIRECT TO TOL. POWER NOT ADJUSTED UNTIL NR 3 ENGINE WAS SHUTDOWN ON FINAL APPROACH TO TOL. MAINTENANCE PERFORMED BORESCOPE INSPECTION, AND NO DEFECTS WERE NOTED. UPON FURTHER INSPECTION VSV AND VBV WERE FOUND OUT OF RIG. MAINTENANCE RE-RIGGED VSV AND VBV IN ACCORDANCE WITH APPLICABLE MANUELS. OPERATIONAL CHECK GOOD. AIRCRAFT WAS RETURNED TO SERVICE.
Part: SHUTOFF VALVE — LOOSE (FUEL) · airframe 83,459 hrs · 32,889 cycles
UPON TAKEOFF ROLL FROM CLT WITH INTENTION TO FLY TO TOL. CREW NOTED NR 4 ENGINE WAS NOT PRODUCING SELECTED POWER. CREW REJECTED TAKEOFF WHEN GROUND SPEED REACHED 80 KNOTS. CREW RETURNED TO BLOCKS. UPON INSPECTION, MAINTENANCE DISCOVERED NR 4 ENG FUEL SHUT OFF LEVER IMPROPERLY SECURED. MAINTENANCE RESECURED FUEL SHUT OFF LEVER. OPERATIONALLY CHECKED ENGINE AND FOUND OPERATION NORMAL. ALL WORK WAS COMPLETED PER THE APPLICABLE MANUALS AND THE AIRCRAFT WAS RETURNED TO SERVICE.
2002
Part: PITOT TUBE — CLOGGED (FUSELAGE) · airframe 83,222 hrs · 32,755 cycles
AFTER TAKE OFF FROM BRO, THE FLIGHT CREW NOTED A DIFFERENCE BETWEEN THE NUMBER ONE AND NUMBER TWO AIRSPEED INDICATORS THAT INCREASED AS THE AIRCRAFTS ALTITUDE INCREASED. THE FLIGHT CREW ADVISED AND COORDINATED WITH ATC TO DETERMINE THE NUMBER TWO AIRSPEED INDICATOR WAS CORRECT. THE FLIGHT CREW, WHILE COORDINATING WITH ATC, RETURNED TO BRO FOR AN UNEVENTFUL LANDING. MAINTENANCE INSPECTED THE AIRCRAFT AND DISCOVERED FOREIGN MATERIAL IN THE NUMBER ONE PITOT TUBE. MAINTENANCE REMOVED THE FOREIGN MATERIAL AND PERFORMED A SUCESSFUL PITOT STATIC CHECK IN ACCORDANCE WITH THE DOUGLAS REPAIR MANUAL. THE AIRCRAFT WAS RETURNED TO SERVICE.
Part: ROD END — STRIPPED (LANDING GEAR) · airframe 83,187 hrs · 32,732 cycles
AFTER TAKE OFF FROM BFI, THE LANDING GEAR DOOR NOT LATCHED LIGHT AND THE GEAR UNSAFE LIGHT REMAINED ILLUMINATED FOLLOWING LANDING GEAR RETRACTION. THE FLIGHT CREW CYCLED THE GEAR AND PERFORMED A SUCESSFUL UP LATCH CHECK, BUT THE LIGHTS REMAINED ILLUMINATED. THE FLIGHT CONTINUED TO TOL WITH AN UNEVENTFUL LANDING. MAINTENANCE INSPECTED THE AIRCRAFT WHICH REVEALED THE ROD END STRIPPED FROM THE BOGIE TRIM CYLINDER. MAINTENANCE REPLACED THE CYLINDER AND PERFORMED SUCESSFUL OPERATIONAL CHECKS IN ACCORDANCE WITH THE DOUGLAS MAINTENANCE MANUAL. THE AIRCRAFT WAS RETURNED TO SERVICE.
Part: PANEL — BURNED (COCKPIT) · airframe 83,096 hrs · 22,687 cycles
WHILE ENROUTE FROM STL TO ELP, SMOKE STARTED TO EMIT FROM THE CENTER CONSOLE AFTER THE AUTO PILOT WAS ENGAGED. THE FLIGHT CREW NOTICED SMALL FLAMES AND EXTINGUISHED THEM WITH A HALON FIRE BOTTLE. THE FLIGHT CREW PULLED AND COLLERED THE CIRCUIT BREAKERS TO THE AUTO PILOT TRIM AND DECLARED AN EMERGENCY LANDING AT ELP. MAINTENANCE INSPECTED THE AIRCRAFT WHICH REVEALED THE STABALIZER TRIM LIGHT PANEL BURNED AND MELTED. MAINTENANCE REPLACED THE LIGHT PANEL AND PERFORMED SUCESSFUL OPERATIONAL CHECKS IN ACCORDANCE WITH THE DOUGLAS MAINTENANCE MANUAL. THE AIRCRAFT WAS RETURNED TO SERVICE.
Part: SKIN — CORRODED (FUSELAGE) · airframe 83,050 hrs · 32,673 cycles
DURING ROUTINE C-CHECK INSPECTION, CORROSION WAS DETECTED AT FUSELAGE STATION 45 LONGERON 29L LOWER AREA. REPAIR ACCOMPLISHED, REMOVAL OF DAMAGED AREA, FABRICATION AND INSTALLATION OF REPAIR DOUBLER IAW THE DOUGLAS SRM.
Part: SKIN — CORRODED (LT WING) · airframe 83,050 hrs · 32,673 cycles
DURING ROUTINE C-CHECK INSPECTION, CORROSION WAS DETECTED ON THE LEFT OUTBOARD SLOT LEADING EDGE AREA ON THE MOUNTING SURFACE WING STATION XFS422.750. REPAIR ACCOMPLISHED, REMOVAL OF CORROSION, FABRICATION AND INSTALLATION OF REPAIR DOUBLERS AND SHIMS IAW THE DOUGLAS SRM.
Part: DOOR FRAME — CORRODED (CARGO DOOR) · airframe 83,050 hrs · 32,673 cycles
DURING ROUTINE C-CHECK INSPECTION, CORROSION WAS DETECTED ON THE FORWARD CARGO COMPARTMENT C1 DOOR JUST BELOW THE AFT LOCK BRACKET. REPAIR ACCOMPLISHED, REMOVAL OF EXISTING REPAIR AND CORROSION, FABRICATION AND INSTALLATION OF NEW EXTENDED FRAME IAW THE DOUGLAS SRM.
Part: DOOR — CRACKED (AFT PASSENGER) · airframe 83,050 hrs · 32,673 cycles
DURING ROUTINE C-CHECK INSPECTION, A CRACK WAS DETECTED ON THE LEFT HAND SIDE OF THE AFT PASSENGER DOOR SKIN IN THE FORWARD LOWER CORNER BELOW AN EXISTING REPAIR AT FUSELAGE STATION 1640 LONGERON 22L. REPAIR ACCOMPLISHED, REMOVAL OF EXISTING DOUBLER, REMOVAL OF DAMAGED AREA, FABRICATION AND INSTALLATION OF REPAIR FILLERS DOUBLERS AND TRIPLERS IN ACCORDANCE WITH THE DOUGLAS STRUCTURAL REPAIR MANUAL AND ENGINEERING AUTHORITY 28276-5248-02-110.
Part: SKIN — CORRODED (CARGO DOOR) · airframe 83,050 hrs · 32,673 cycles
DURING ROUTINE C-CHECK INSPECTION, CORROSION WAS DETECTED ON THE FORWARD CARGO COMPARTMENT AFT DOOR SKIN TOP REAR AREA AT FUSELAGE STATION 557.5 AND LONGERON 27R. REPAIR ACCOMPLISHED, REMOVAL OF DAMAGED AREA, FABRICATION AND INSTALLATION OF REPAIR FILLER AND DOUBLER IAW THE DOUGLAS SRM.
Part: SKIN — CORRODED (FUSELAGE) · airframe 83,050 hrs · 32,673 cycles
DURING ROUTINE C-CHECK INSPECTION, CORROSION WAS DISCOVERED ON THE FUSELAGE SKIN AT FUSELAGE STATION 35 LONGERON 33R. REPAIR ACCOMPLISHED, REMOVAL OF DAMAGED AREA, FABRICATION AND INSTALLATION OF REPAIR FILLER AND DOUBLER IAW THE DOUGLAS SRM AND EA 28276-5384-02-111.
Part: DOOR — CRACKED (FWD ENTRY) · airframe 83,050 hrs · 32,673 cycles
DURING ROUTINE C-CHECK INSPECTION, A CRACK WAS DETECTED AT FUSELAGE STATION 60 LONGERON 21L.REPAIR ACCOMPLISHED, REMOVED DAMAGED AREA AND INTERNAL DOUBLER AND TRIPLER, FABRICATION AND INSTALLATION OF FILLER AND REPAIR DOUBLER AND TRIPLER IN ACCORDANCE WITH THE DOUGLAS STRUCTURAL REPAIR MANUAL
Part: SKIN — GOUGED (FUSELAGE) · airframe 83,050 hrs · 32,673 cycles
DURING ROUTINE C-CHECK INSPECTION, GOUGES WERE DETECTED ON THE FUSELAGE SKIN ABOVE THE FORWARD UPPER CORNER OF THE AFT PIT DOOR CUT OUT, FUSELAGE STATION 1400, LONGERON 24 RT. REPAIR ACCOMPLISHED, BLENDING OF DAMAGED AREA, FABRICATION AND INSTALLATION OF REPAIR EXTERNAL DOUBLER AND TRIPLER IAW DOUGLAS SRM.
Part: SKIN — CORRODED (FUSELAGE) · airframe 83,050 hrs · 32,673 cycles
DURING ROUTINE C-CHECK INSPECTION, CRACKS AND CORROSION WERE DETECTED ON THE FUSELAGE AFT RIGHT DOOR UPPER AFT CUT OUT FUSELAGE STATION 1660 LONGERON 11R. REPAIR ACCOMPLISHED, REMOVAL OF DAMAGED AREA AND INTERNAL DOUBLERS. FABRICATION AND INSTALLATION OF REPAIR FILLERS, DOUBLERS AND TRIPLERS IAW THE DOUGLAS SRM.
Part: SKIN — DENTED (FUSELAGE) · airframe 83,050 hrs · 32,673 cycles
DURING ROUTINE C-CHECK INSPECTION, A DENT WAS DISCOVERED ON THE FUSELAGE EXTERNAL PLATING AT FUSELAGE STATION 1560 LONGERON 25R. REPAIR ACCOMPLISHED REMOVAL OF THE DAMAGED AREA, FABRICATION AND INSTALLATION OF REPAIR DOUBLER AND FILLER IAW THE DOUGLAS SRM.
Part: SKIN — CORRODED (FUSELAGE) · airframe 83,050 hrs · 32,673 cycles
DURING ROUTINE C-CHECK INSPECTION, CORROSION WAS DETECTED ON THE FUSELAGE SEAM LONGERON 11L F/S 1620. REMOVED CORROSION, SEALED AREA, IAW THE DOUGLAS SRM.
2001
Part: CABLE — BROKEN (WING) · airframe 82,406 hrs · 32,328 cycles
ENROUTE FROM ANC TO SEA, AFTER TAKEOFF THE FLIGHT CREW NOTICED A SIGNIFICANT AIRCRAFT ROLL TO THE LEFT AND REQIURED RUDDUR INPUT. THE FLIGHT RETURNED TO ANC FOR AN UNVENTFUL LANDING. MANITHEANCE INSPECTED THE AIRCRAFT WHICH REVEALED A SEGMENT OF THE LEFT WING FLIGHT SPOILER RETRACT CABLE BROKEN. MAINTENANCE REPLACED THE CABLE IN ACCORDANCE WITH THE MAINTENCE MANUAL. THE AIRCRAFT WAS RETURNED TO SERVICE.
Part: PLATE — DAMAGED (LT MLG) · airframe 81,091 hrs · 31,726 cycles
EN ROUTE FROM SJC TO TOL, AFTER THE LANDING GEAR WAS RETRACTED THE GEAR DOOR WARNING LIGHT REMAINED ILLUMINATED. THE FLIGHT CREW CYCLED THE LANDING GEAR BUT THE WARNING INDICATION REMAINED THE SAME. THE FLIGHT CONTINUED TO TOL FOLLOWING COMPANY PROCEDURES. MAINTENANCE INSPECTED THE AIRCRAFT WHICH REVEALED A DAMAGED GEAR DOOR SWITCH STRIKER ON THE LEFT MAIN GEAR DOOR. MAINTENANCE REPLACED THE STRIKER AND PERFORMED A SUCCESFUL OPERATIONAL CHECK. THE AIRCRAFT WAS RETURNED TO SERVICE.
2000
Part: ACTUATOR — OUT OF ADJ (LT MLG) · airframe 80,263 hrs · 31,349 cycles
EN ROUTE FROM PDX TO TOL, THE LANDING GEAR DOOR AND GEAR UNSAFE WARNING LIGHTS ILLUMINATED AFTER GEAR RETRACTION. THE FLIGHT CREW CYCLED THE GEAR, PERFORMED AN UNSUCCESSFUL GEAR UP LATCH CHECK, THE WARNING INDICATIONS REMAINING THE SAME. THE FLIGHT RETURNED TO PDX FOR AN UNEVENTFUL LANDING. MAINTENANCE INSPECTED THE AIRCRAFT, ADJUSTED THE LEFT MAIN GEAR ACTUATOR IN ACCORDANCE WITH THE MAINTENANCE MANUAL. MAINTENANCE PERFORMED A SUCCESSFUL OPERATIONAL CHECK. THE AIRCRAFT WAS RETURNED TO SERVICE.
Part: WHEEL — VIBRATION (NLG)
RIC - FLT 1721 - EN ROUTE TO TOL, WHEN THE LANDING GEAR WAS RETRACTED A NOISE AND VIBRATION WAS FELT FROM THE NOSE WHEEL WELL AREA. THE FLIGHT CREW REQUESTED EMERGENCY EQUIPMENT AS PRECAUTIONARY, AND RETURNED TO RIC FOR AN UNEVENTFUL LANDING. MAINTENANCE INSPECTED THE AIRCRAFT WHICH REVEALED DICREPANCIES ASSOCIATED WITH THE NOSE TIRE ASSEMBLIES. MAINTENANCE REPLACED THE NOSE TIRE ASSEMBLIES. THE AIRCRAFT WAS RETURNED TO SERVICE. (M)
Part: ACTUATOR — DEFECTIVE (COCKPIT)
TOL - FLT 823 - DURING LANDING IN TOL, WHEN THE SPOILERS WERE DEPLOYED THE FLIGHT CREW SIGHTED SMOKE EMITTING FROM THE CENTER PEDESTAL. MAINTENANCE INSPECTED THE PEDESTAL AREA WHICH REVEALED THE AUTOMATIC SPOILER ACTUATOR DEFECTIVE. MAINTENANCE PLACED THE SYSTEM ON DEFERRAL AND THE AIRCRAFT WAS RETURNED TO SERVICE. (M)
1999
Part: WIRE — BROKEN (COCKPIT)
EN ROUTE FROM DFW TO TOL, SMOKE EMITTED FROM UNDER THE FIRST OFFICER'S INSTRUMENT PANEL, ACCOMPANIED BY AN ODOR. THE FIRST OFFICER'S INSTRUMENT PANEL FLOOD LIGHTING WAS EXTINGUISHED AND ASSOCIATED CIRCUIT BREAKERS OPENED, SMOKE SUBSIDED. THE FLIGHT CONTINUED TO TOL FOR AN UNEVENTFUL LANDING. MAINTENANCE INSPECTED THE INSTRUMENT FLOOD LIGHT CIRCUITY WHICH REVEALED A BROKEN WIRE, WHICH WAS REPAIRED IN ACCORDANCE WITH THE MAINTENANCE MANUAL STANDARD PRACTICES. A SUCCESSFUL OPERATIONAL TEST RETURNED THE AIRCRAFT TO SERVICE.
Part: BRAKE — WORN (NLG)
AFTER TAKEOFF FROM LAX EN ROUTE TO TOL, AFTER GEAR RETRACTION A LOUD NOISE AND VIBRATION WAS NOTICED IN THE COCKPIT. THE CREW CYCLED THE LANDING GEAR BUT THE NOISE RETURNED. THE AIRCRAFT RETURNED TO LAX FOR AN UNEVENTFUL LANDING. MAINTENANCE INSPECTED THE AIRCRAFT WHICH REVEALED THE LEFT GROUND COOLING FAN ACCESS PANEL NOT PROPERLY SECURED, AND WAS CORRECTED. FURTHER INSPECTION FOUND THE NOSE TIRE SPIN BRAKES WORN, AND WERE REPLACE. NO FURTHER DISCREPANCIES WERE NOTED AND THE AIRCRAFT WAS RETURNED TO SERVICE.
1998
Part: FIRE LOOP — DEFECTIVE (NR 1 ENGINE)
EN ROUTE, THE NUMBER ONE ENGINE FIRE WARNING SOUNDED WITH THE MASTER FIRE WARNING LIGHT ILLUMINATED. THE FLIGHT CREW SECURED THE ENGINE FOLLOWING COMPANY PROCEDURES AND DISCHARGED ONE FIRE BOTTLE. THE FIRE WARNING LIGHT EXTINGUSHED FOLLOWING FIRE BOTTLE DISCHARGE. THE FLIGHT CONTINUED TO TOL FOR AN UNEVENTFUL LANDING. MAINTENANCE INSPECTED THE ENGINE AND FOUND NO EVIDENCE OF A FIRE. THE FIRE WARNING LOOPS AND ASSOCIATED WIRING WERE INSPECTED LOCATING A DEFECTIVE FIRE WARNING LOOP, AND WAS REPLACED. MAINTENANCE PERFORMED A SUCCESSFUL OPERATIONAL TEST IN ACCORDANCE WITH THE MAINTENANCE MANUAL.
Part: KEEL BEAM — CORRODED (BS 742 & 781.5)
DURING ROUTINE C-CHECK INSPECTION, CORROSION WAS DETECTED ON LOWER KEEL BEAM CAP BETWEEN FUSELAGE STATIONS 742.2 AND 781.5. REPAIR ACCOMPLISHED CORROSION REMOVAL, FABRICATION AND INSTALLATION TWO REPAIR ANGLES IN ACCORDANCE WITH FAA PER APPROVED DRAWING E78-R02 AND ENGINEERING ORDER 53-DC8-915.
Part: FITTING — CRACKED (BS 700)
DURING ROUTINE C-CHECK INSPECTION, A CRACKED KEEL BEAM LOWER FRAME FITTING WAS FOUND CRACKED AT FUSELAGE STATION 700. REPAIR ACCOMPLISHED REMOVAL OF THE DAMAGED FITTING, FABRICATION AND INSTALLATION A NEW FITTING IN ACCORDANCE WITH DOUGLAS DRAWING 375757 AND ENGINEERING ORDER 53-DC8-921.
Part: FITTING — CRACKED (PAX DOOR)
DURING ROUTINE C-CHECK INSPECTION, FOUND TWO UPPER DOOR STOP FITTING AT THE LEFT AFT PASSENGER DOOR CRACKED. REPAIR ACCOMPLISHED REMOVAL OF THE DAMAGED FITTINGS, FABRICATION AND INSTALLATION TWO NEW FITTINGS IN ACCORDANCE WITH DOUGLAS DRAWING 4640556 AND ENGINEERING ORDER 52-DC8-922.
Part: PLATING — CORRODED (BS 699.5)
DURING ROUTINE C-CHECK INSPECTION, CORROSION WAS DETECTED ON THE LOWER KEEL BEAM EXTERNAL PLATING AT FUSELAGE STATION 699.5. REPAIR ACCOMPLISHED REMOVAL OF THE DAMAGED AREA, FABRICATION AND INSTALLATION NEW EXTERNAL PLATING AND TWO REPAIR DOUBLERS IN ACCORDANCE WITH FAA DER APPROVED DRAWING E78-R01 AND ENGINEERING ORDER 53-DC8-914.
Part: ANGLE — CRACKED (NR 1 & 4 PYLON)
DURING ROUTINE C-CHECK INSPECTION, CRACKS WERE DETECTED ON THE NUMBER ONE AND FOUR INBOARD PYLON ATTACH ANGLE STIFFENERS. REPAIR ACCOMPLISHED REMOVAL OF THE DAMAGED ANGLES, FABRICATION AND INSTALLATION OF TWO NEW ANGLES IN ACCORDANCE WITH DOUGLAS DRAWING 5756791 AND ENGINEERING ORDER 54-DC8-919.
1997
Part: CONNECTOR — DETERIORATED (NR 4 ENGINE)
EN ROUTE LAX TO TOL, THE NR 4 ENGINE FIRE WARNING SOUNDED AND ILLUMINATED. THE CREW ACCOMPLISHED AN ENGINE SHUTDOWN IN ACCORDANCE WITH COMPANY PROCEDURES. THE FLIGHT CONTINUED TO TOL WITH AN UNEVENTFUL LANDING. MAINTENANCE FOUND THE ENGINE COMPARTMENT WIRING AND CONNECTORS DETERIORATED. THE WIRING AND CONNECTORS FOR THE UPPER AND LOWER FIRE LOOPS WERE REPLACED.
Part: FITTING — CRACKED (CARGO DOOR)
DURING ROUTINE C-CHECK INSPECTION, THE LOWER FORWARD CARGO DOOR RIGHT GUIDE FITTING WAS FOUND TO BE CRACKED. REPAIR ACCOMPLISHED BY REMOVAL OF EXISTING FITTING, FABRICATION AND INSTALLATION OF A NEW DOOR GUIDE FITTING IN ACCORDANCE WITH ENGINEERING ORDER 52-DC8-444, SRM 51-1-20, AND FAA DER APPROVED DRAWING 852-020-97.
Part: DOUBLER — CORRODED (BS 336-379)
DURING ROUTINE C-CHECK AND CPCP INSPECTION, A FUSELAGE LOWER SKIN REPAIR DOUBLER WAS FOUND CORRODED AT FUSELAGE STATION 336.5 TO 379.0, BETWEEN LONGERON 32R AND 32L. REPAIR ACCOMPLISHED BY REMOVAL OF CORRODED DOUBLER, FABRICATION AND INSTALLATION OF A REPAIR FILLER AND TWO REPAIR DOUBLERS IN ACCORDANCE WITH ENGINEERING ORDER 53-DC8-441 AND FAA DER APPROVED DRAWING 853-0020-97.
Part: FITTING — CRACKED (WS 485)
DURING ROUTINE CHECK INSPECTION, THE LEFT WING RIB ATTACH FITTING AT STATION XW 485 BETWEEN STRINGERS 63 AND 64 WAS FOUND TO BE CRACKED. REPAIR WAS ACCOMPLISHED BY REMOVAL OF EXISTING RIB FITTING, FABRICATION AND INSTALLATION OF NEW RIB FITTING IN ACCORDANCE WITH ENGINEERING ORDER 57-DC8-445, SRM 57-1-0 AND FAA DER APPROVED DRAWING 857-017-97.
Part: SKIN — CORRODED (BS 445)
DURING ROUTINE C-CHECK INSPECTION, A FUSELAGE SKIN BULGE WAS FOUND ACCOMPANIED BY MISSING RIVET HEADS AT FUSELAGE STATION 445.0, BETWEEN LONGERONS 30LT AND 32LT. REPAIR WAS ACCOMPLISHED BY REMOVING CORRODED AREA, FABRICATION AND INSTALLATION OF AN INTERNAL FINGER DOUBLER AND EXTERNAL REPAIR DOUBLER IN ACCORDANCE WITH ENGINEERING ORDER 53-DC8-438, AND FAA DER APPROVED DRAWING 853-016097.
Part: DOOR — CORRODED (CTR WING)
DURING ROUTINE C-CHECK AND CPCP INSPECTION, CORROSION ON CENTER WING FUEL TANK ACCESS DOOR AT FUSELAGE STATION 742 WAS FOUND. REPAIR WAS ACCOMPLISHED BY REMOVAL OF EXISTING DOOR, FABRICATION AND INSTALLATION OF NEW DOOR IN ACCORDANCE WITH ENGINEERING ORDER 57-DC8-434 AND FAA DER APPROVED DRAWING 857-011097.
Part: FITTING — CORRODED (BS 1690-1700)
DURING ROUTINE C-CHECK AND CPCP INSPECTION, CORROSION WAS FOUND ON AN ATTACH FITTING AT LONGERON 23 LEFT BETWEEN FUSELAGE STATION 1690 AND 1700. REPAIR ACCOMPLISHED BY REMOVAL OF EXISTING FITTING, FABRICATION AND INSTALLATION OF A NEW LONGERON FITTING IN ACCORDANCE WITH ENGINEERING ORDER 53-DC8-433, DRAWING 853-009097.
Part: SKIN — CRACKED (WS 336.5)
DURING ROUTINE C-CHECK INSPECTION, A CRACK ON THE RIGHT WING LEADING EDGE LOWER SURFACE AT STATION XS366.500 WAS FOUND. REPAIR ACCOMPLISHED BY STOP DRILLING THE CRACK AND FABRICATION AND INSTALLATION OF AN EXTERNAL REPAIR DOUBLER IN ACCORDANCE WITH ENGINEERING ORDER 57-DC8-435 AND FAA DER APPROVED DRAWING 857-05-97.
Part: BRACKET — CRACKED (BS 857.125)
DURING ROUTINE C-CHECK INSPECTION, THE SPOILER CONTROL CABLE SUPPORT BRACKET WAS CRACKED AT FUSELAGE STATION 857.125 IN THE RIGHT MAIN GEAR WHEELWELL. REPAIR ACCOMPLISHED REMOVAL OF EXISTING BRACKET, FABRICATION AND INSTALLATION OF THE SUPPORT BRACKET IN ACCORDANCE WITH ENGINEERING ORDER 53-DC8-442, SRM 51-3-0 AND FAA DER APPROVED DRAWING 853-015-97.
Part: SKIN — CRACKED (WS 422.750)
DURING ROUTINE C-CHECK INSPECTION, A CRACK ON THE RIGHT WING LEADING EDGE LOWER SURFACE PLATING AT WING STATION XFS 422.750 WAS FOUND. REPAIR WAS ACCOMPLISHED BY STOP DRILLING THE CRACK, FABRICATION AND INSTALLATION OF AN EXTERNAL REPAIR DOUBLER IN ACCORDANCE WITH ENGINEERING ORDER 57-DC8-447 AND FAA DER APPROVED DRAWING 857-14-97.
Part: LEADING EDGE — CRACKED (WS 422.75)
DURING ROUTINE C-CHECK INSPECTION, A CRACK WAS FOUND ON THE LEFT WING LEADING EDGE LOWER SURFACE AT STATION XRS 422.750. REPAIR WAS ACCOMPLISHED BY STOP DRILLING THE CRACK, FABRICATION AND INSTALLATION OF AN EXTERNAL REPAIR DOUBLER IN ACCORDANCE WITH ENGINEERING ORDER 57-DC8-434 AND FAA DER APPROVED DRAWING 857-04-97.
Part: FRAME — GOUGED (BS 334)
DURING ROUTINE C-CHECK AND CPCP INSPECTION, FUSELAGE FRAME AT STATION 334 BETWEEN LONGERONS 35 LEFT AND 36 LEFT WAS FOUND TO BE DAMAGED. REPAIR WAS ACCOMPLISHED BY REMOVAL OF DAMAGED AREA, FABRICATION AND INSTALLATION OF A REPAIR FILLER AND TWO REPAIR ANGLES IN ACCORDANCE WITH ENGINEERING ORDER 53-DC8-426, AND FAA DER APPROVED DRAWING 853-07-97.
Part: SKIN — CRACKED (BS 10)
DURING ROUTINE C-CHECK INSPECTION, A CRACK WAS FOUND IN THE FUSELAGE SKIN AT STATION 10.000, BETWEEN LONGERONS 28R AND 29R. REPAIR WAS ACCOMPLISHED BY REMOVAL OF THE DAMAGED AREA, FABRICATION, AND INSTALLATION OF REPAIR FILLERS, AND A REPAIR DOUBLER IN ACCORDANCE WITH ENGINEERING ORDER 53-DC8-443 AND FAA DER APPROVED DRAWING 853-021-97.
Part: FRAME — CORRODED (BS 1080)
DURING ROUTINE C-CHECK AND CPCP INSPECTION. CORROSION WAS FOUND ON FUSELAGE FRAME UPPER CAP AT FUSELAGE STATION 1080 BETWEEN LONGERONS 30 LEFT AND 36. REPAIR ACCOMPLISHED BY REMOVING THE CORRODED AREA, FABRICATION AND INSTALLION OF A REPAIR FILLER AND REPAIR DOUBLER IN ACCORDANCE WITH ENGINEERING ORDER 53-DC8-436 AND FAA DER APPROVED DRAWING 853-06-97.
Part: FITTING — CRACKED (BS 980)
DURING ROUTINE C-CHECK AND CPCP INSPECTION, A FLOOR BEAM ATTACH FITTING WAS FOUND CRACKED IN THE MAIN CARGO COMPARTMENT AT FUSELAGE STATION 980. REPAIR WAS ACCOMPLISHED BY REMOVING THE CRACKED FITTING, FABRICATION AND INSTALLATION OF A NEW FITTING IN ACCORDANCE WITH ENGINEERING ORDER 53-DC8-431 AND FAA DER APPROVED DRAWING 853-001-97.
1996
Part: FITTING — CRACKED (BS 220/240)
DURING ROUTINE C-CHECK INSPECTION, A CRACK WAS FOUND ON A LONGERON SPLICE FITTING BETWEEN FUSELAGE STATION 220 AND 240 AT LONGERON 29 RT. REPAIR ACCOMPLISHED BY REMOVAL OF SPLICE FITTING, FABRICATION AND INSTALLATION OF A NEW FITTING IN ACCORDANCE WITH ENGINEERING ORDER 53-DC8-432 AND SRM 53-1-0 AND FAA DER APPROVED DRAWING 853-08-97.
1995
Part: MANIFOLD — CRACKED (NR 3 ENGINE)
ENGINE NR 3 LOW PRESSURE TURBINE COOLING MANIFOLD DISTRIBUTOR, CRACKED AT 10 O'CLOCK POSITION.
Part: FITTING — CRACKED (FWD CARGO DOOR)
FORWARD CARGO COMPARTMENT 'A' DOOR RT, NR 2 FITTING CRACKED.
Part: SKIN — CORRODED (STA Y620 L34L)
FORWARD CARGO COMPARTMENT, STA Y620.00, BETWEEN LONGERON 34L AND 34R, FUSELAGE SKIN CORRODED.
Part: MANIFOLD — CRACKED (INLET PORT RT)
ENGINE NR 1, LOW PRESSURE TURBINE COOLING MANIFOLD DISTRIBUTOR INLET PORT CRACKED AT RIGHT SIDE.
Part: FITTING — CRACKED (LWR FUSELAGE)
DURING ROUTINE C-CHECK INSPECTION, A CRACK WAS LOCATED AT THE FORWARD LOWER CARGO DOOR TRACK FITTING. THE FITTING WAS REMOVED AND MANUFACTURED IAW DRAWING HSE27-53-143 AND THE REMOVED FITTING. THIS DRAWING WAS FAA DER APPROVED. THE FITTING WAS INSTALLED IAW THE AIRCRAFT SRM AND MM. (X)
Part: PANEL — CORRODED (FS 610)
DURING ROUTINE C-CHECK INSPECTION, CORROSION REMOVAL FROM THE EXTERNAL PLATING AT FS 610 BETWEEN LONGERONS 29 AND 31 WENT BEYOND SRM LIMITS. THE DAMAGE WAS REPAIRED IAW DRAWING BSE27-53-140, WHICH WAS FAA DER APPROVED AND E.O. 53-DC8-137. (X)
Part: FITTING — CRACKED (LWR FWD FUSELAGE)
DURING ROUTINE C-CHECK INSPECTION, THE LOWER FORWARD CARGO DOOR, LOCK FITTING WAS FOUND CRACKED. THIS FITTING WAS LOCATED AT THE SECOND POSITION FORWARD. THE FITTING WAS REMOVED AND MANUFACTURED IAW DRAWING HSE27-52-142, WHICH WAS FAA DER APPROVED AND E.O. 52-DC8-136. REMOVAL AND REPLACEMENT OF THE FITTING WAS ACCOMPLISHED IAW AIR MM. (X)
Part: PLATING — CRACKED (LWR FWD FUSELAGE)
DURING ROUTINE C-CHECK INSPECTION, A CRACK WAS FOUND AT THE AFT NOSE WHEELWELL DOOR CUT OUT IN EXTERNAL PLATING. REPAIR OF THE CRACK IN THE LEFT AFT CORNER WAS ACCOMPLISHED BY STOP DRILLING THE CRACK, INSTALLING AN EXTERNAL REPAIR DOUBLER. REPAIR WAS ACCOMPLISHED IAW DRAWING HSE27-53-139, WHICH WAS FAA DER APPROVED AND E.O. 53-DC8-140. (X)