N722CX
Operators of this aircraft
Who operated this tail, and how firmly we know it.
No operator established for this aircraft.
Accident & incident history
No NTSB accidents or incidents on file for this aircraft.
Maintenance disclosures
Service Difficulty Reports filed with the FAA for this airframe. Filing is largely voluntary — the number of reports is not a measure of reliability. To verify a report, search its control number at the FAA SDRS site.
96 reports on file, 2005-12-15 – 2006-03-24.
Part: VENT — CRACKED (ZONE 100) · airframe 71,621 hrs · 17,096 cycles
DURING ROUTINE C-CHECK INSPECTION, REMOVED THE FWD BUFFET VENT TRIMMER VALVE AND PLUG OUTLET ON FUSELAGE. PERFORMED MAJOR REPAIR IAW DC8 SRM 53-2-1 FIG 7. REMOVED FWD BUFFET VENT TRIMMER VALVE IAW DC-8 MM 38-20-11 PAGES 201-202. REMOVED EXISTING INTERNAL DOUBLER AND REMOVED AREA IAW DC8 SRM 53-2-1 FIG. 1. FABRICATED REPAIR DOUBLER & INTERNAL FINGER DOUBLER & FILLER IAW DC8 SRM 53-2-1 FIG 7, DC-8 SRM 53-4-1 FIG 14B ITEM A, DC-8 SRM 51-9-0 PAGE 10A. CLEANED, TREATED AND PRIMED AREA, REPAIR PARTS IAW DC8 SRM 51-1-8B. APPLIED SEALANT TO FAYING SURFACES IAW DC8 SRM 51-1-11. INSTALLED REPAIR PARTS.
Part: PANEL — DISPLACED · airframe 71,621 hrs · 17,096 cycles
DURING ROUTINE C-CHECK INSPECTION, EO 25-DC8-520 R4 PARTITION UPPER ATTACHMENT RELOCATION TO FS-STC00171 LA-D. PERFORMED ALTERATION MAJOR IAW FAA FORM 8110-3 DATE 10-04-05. EO 25-DC-8-520 REV STATES 4 DATES 11-11-2005, ATI DWG C40-MO2 REV C DATE 10-04-05. FABRICATED DOUBLERS, STRAPS IAW ATI DWG C40-MO2. PERFORMED HEAT TREATMENT TO FITTING IAW DC-8 SRM 51-1-1 PAGES 1, 13, 17. CLEANED, TREATED AND PRIMED AREA & REPAIR PARTS. APPLIED SEALANT TO FAYING SURFACES. INSTALLED REPAIR PART.
Part: NONE — NONE (NONE) · airframe 71,621 hrs · 17,096 cycles
DURING ROUTINE C-CHECK INSPECTION, EO 25-DC8-198 R9 INSTALL COMAT BOX. PERFORMED MAJOR ALTERATION IAW FAA FORM 8110-3 DATE 09-23-05, ATI DWG A95166-4 REV N DATE 09-23-05. INSTALLED COMAT BOX IAW ATI DWG 95166-4. COMPLIED WITH EO 25-DC8-198.
Part: NONE — NONE (NONE) · airframe 71,621 hrs · 17,096 cycles
DURING ROUTINE C-CHECK INSPECTION, ELT ANTENNA REMOVAL AND BLANKING PLATE INSTALLATION. PERFORMED MAJOR REPAIR IAW FAA FORM 8110-3 DATE 02-06-06, ENGINEERING AUTHORIZATION AA71-2 REV IR DATE 01-24-06. REMOVED ELT ANTENNA IAW DC-8 MM 25-60-0 PAGE 201. FABRICATED BLANKING PLATE (AL 7075 T6 0.125) IAW EA AA71-2. CLEANED, TREATED AND PRIMED AREA + BLANKING PLATE IAW DC-8 SRM 51-1-8B. APPLIED SEALANT TO FAYING SURFACE IAW DC-8 SRM 51-1-11. INSTALLED BLANKING PLATE IAW EA AA71-2, DC-8 SRM 51-3-0, DC-8 SRM 51-3-1 (TORQUED).
Part: NONE — NONE (NONE) · airframe 71,621 hrs · 17,096 cycles
DURING C CHECK, INSTALLATION OF DOUBLER ON FS 188.000 L-1 TO L-2R REQUIRED DUE TO SEXTANT EQUIPMENT REMOVAL. PERFORMED MAJOR REPAIR IAW FAA FORM 8110-3 NR 06029 DATED 01-23-06, SEMAN DWG ED-4167 DATE 01-21-06, EO SEMAN # 2006100 DATE 01-23-06. REMOVED EXISTING SPACER, REMOVED DAMAGED AREA IAW SEMAN DWG ED-4167. PERFORMED NDT INSPECTION IAW DC8 NDT SPM PART 06-10-01-001. FAB`D REPAIR DOUBLER, REPAIR TRIPLER, FILLER SKIN, FILLER INTERNAL DOUBLER IAW SEMAN DWG ED-4167. CLEANED, TREATED AND PRIMED AREA, REPAIR PARTS IAW DC8 SRM 51-1-8B. APPLIED SEALANT TO FAYING SURFACES IAW DC8 SRM 51-1-11. INSTALLED REPAIR PARTS IAW SEMAN DWG ED-4167, DC8 SRM 51-1-20D, DC8 SRM 51-3-1 (TORQUED).
Part: DRAIN MAST — PLUGGED (FWD LAVATORY) · airframe 71,621 hrs · 17,096 cycles
DURING ROUTINE C-CHECK INSPECTION, INSTL; FWD LAV DRAIN MAST PLUG AT LOWER CENTER LINE. PERFORMED MAJOR REPAIR IAW FAA FORM 8110-3 DATED 01-19-06, ATI DWG H74-102 REV B DATED 01-19-06, EO SEMAN 2006114 DATED 01-19-06. REMOVED EXISTING DRAIN MAST IAW DC8 SRM 51-3-0. FABRICATED REPAIR DOUBLER (AL7075T6 0.125) IAW ATI DWG H74-102. CLEANED, TREATED AND PRIMED AREA + REPAIR DOUBLER IAW DC8 SRM 51-1-8B. APPLIED SEALANT TO FAYING SURFACES IAW DC8 SRM 51-1-11. INSTALLED REPAIR DOUBLER IAW ATI DWG H74-102, DC8 SRM 51-3-0, DC8 SRM 51-3-1 (TORQUE).
Part: REPAIR — MISINSTALLED (RT AILERON) · airframe 71,621 hrs · 17,096 cycles
DURING ROUTINE C-CHECK INSPECTION, RT INBD AILERON SHOWS SEVERAL SPOTS OF CORROSION AND NON STANDARD REPAIR ON LWR PLATING, STA XA 550.000. PERFORMED MAJOR REPAIR. REMOVED CORROSION, FOUND OUT OF LIMITS. REMOVED EXISTING PANEL PLATING (CORRODED) + REPAIR NON STANDARD. FABRICATED NEW PANEL PLATING (AL2024T3 0.025) + BONDED FINGER DOUBLER (AL 2024T3 0.020) IAW DC8 SRM 57-8-1 FIG 1 ITEM B, K, DWG DOUGLAS 5705334. BONDED BOTH PARTS WITH HYSOL IAW DC8 SRM 51-1-9. CLEANED, TREATED AND PRIMED AREA + NEW PANEL PLATING INTERNAL PART IAW DC8 SRM 51-1-8B. APPLIED SEALANT TO FAYING SURFACE IAW DC8 SRM 51-1-11. INSTALLED NEW PANEL PLATING IAW DC8 SRM 51-1-1.
Part: PLATE — UNKNOWN (BS 460 BL 0) · airframe 71,621 hrs · 17,096 cycles
FWD LAVATORY DRAIN MAST BLANKING PLATE AT 460 BL O REPLACES 53-DC8-928. PERFORMED MAJOR REPAIR IAW FAA FORM 8110-3 DATE 09-21-05, AT SKETCH FO3-RO5 REV. B DATED 09-21-05, EO SEMAN 2006112 DATE 01-05-06. REMOVED (02 EA) EXISTING DRAIN MAST IAW DC-8 SRM 51-3-0. FABRICATED (02 EA) REPAIR DOUBLER AT SKETCH FO3-R05. CLEANED, TREATED AND PRIMED AREA, REPAIR DOUBLERS IAW DC-8 SRM 51-1-8B. APPLIED SEALANT TO FAYING SURFACES IAW DC-8 SRM 51-1-11. INSTALLED REPAIR DOUBLER IAW ATI SKETCH FO3-ROS, DC-8 SRM 51-3-0, DC-8 SRM 51-3-1 (TORQUE).
Part: REPAIR — MISINSTALLED (BS 1540-1550) · airframe 71,621 hrs · 17,096 cycles
DURING C CHECK, 'NON-STANDARD REPAIR ON FUSELAGE EXTERNAL SKIN (STA 1540.000 - 1550.000,L-17R TO L-19R. PERFORMED MAJOR REPAIR IAW DC8 SRM 53-2-1 FIG 7 (SHEET 1, 4, 5). REMOVED NON STANDARD REPAIR IAW DC8 SRM 51-1-21, DC8 SRM 51-1-20D. REMOVED DAMAGED SECTION IAW DC8 SRM 53-2-1 FIG 7 (SHEET 4). FAB`D REPAIR DOUBLER, INTERNAL FINGER DOUBLER, FILLER IAW DC8 SRM 53-2-1 FIG 7 (SHEET 1, 5), DC8 SRM 53-5-2 PG 2 FIG 1 ITEM âEâ. CLEANED, TREATED, PRIMED + REPAIR PARTS IAW DC8 SRM 51-1-8B. APPLIED SEALANT TO FAYING SURFACES IAW DC8 SRM 51-1-11. INSTALLED REPAIR PARTS IAW DC8 SRM 53-2-1 FIG 7 (SHEET 1, 4, 5), DC8 SRM 51-1-21, DC8 SRM 51-1-20D, DC8 SRM 51-3-1 (TORQUE).
Part: NONE — NONE · airframe 71,621 hrs · 17,096 cycles
DURING C CHECK, 'FWD LAVATORY DRAIN HOLE PLUG INSTALLATION REQUIRED, STA 270.000 - 280.000, L-22R TO L-23R. PERFORMED MAJOR REPAIR IAW DC8 SRM 53-2-1 FIG 1 (SHEET 1, 3). REMOVED FASTENERS IAW DC8 SRM 51-3-0. CUT OUT AREA, FABRICATED REPAIR DOUBLER, (02EA) INTERNAL FINGER DOUBLER (AL7075T6 0.040â) IAW DC8 SRM 53-2-1 FIG 7 (SHEET 1, 3), DC8 SRM 53-4-1 FIG 5 ITEM âBâ, DC8 SRM 51-9-0 FIG 68A. CLEANED, TREATED AND PRIMED AREA + REPAIR PARTS IAW DC8 SRM 51-1-8B. APPLIED SEALANT TO FAYING SURFACES IAW DC8 SRM 51-1-11. INSTALLED REPAIR PARTS IAW DC8 SRM 53-2-1 FIG 7 (SHEET 1, 3), DC8 SRM 51-1-21, DC8 SRM 51-1-20D, DC8 SRM 51-3-1 (TORQUE).
Part: FITTING — CORRODED (FUSELAGE) · airframe 71,621 hrs · 17,096 cycles
DURING ROUTINE C-CHECK INSPECTION, AFT CARGO COMPT- AFT SVC DOOR JAMB FITTING CORRODED, STA 1520.000 RBL 50. REMOVED CORROSION FROM FITTING IAW DC-8 SRM 51-1-8 PAGES 17-18. FOUND OUT OF LIMITS IAW DC-8 SRM 53-2-0 PAGE 2P. REMOVED CORRODED FITTING IAW DC-8 SRM 51-1-20D. CLEANED, TREATED AND PRIMED AREA IAW DC-8 SRM 51-1-8B. INSTALLED NEW FITTING IAW DC-8 SRM 51-1-21, DC-8 SRM 51-1-20D, DC-8 SRM 51-3-1 (TORQUE).
Part: LONGERON — CRACKED (BS 208-270) · airframe 71,621 hrs · 17,096 cycles
DURING ROUTINE C CHECK INSPECTION, 'FWD ACCY COMPT- L-34R CRACKED BETWEEN STA 208.000 - STA 270.000. REMOVED CRACKED L-34R IAW DC-8 SRM 51-1-21. CLEANED, TREATED AND PRIMED AREA IAW DC-8 SRM 51-1-8B. INSTALLED NEW LONGERON WITH RIVETS + HILOKS IAW DC-8 SRM 51-1-21, DC-8 SRM 51-1-20D, DC-8 SRM 51-3-1.
Part: PAN — CRACKED (RT WING LE) · airframe 71,621 hrs · 17,096 cycles
DURING ROUTINE C CHECK INSPECTION, RT WING CTR L/E, ZEE-PAN CRACKED 1" AT STA XS 526.000. REMOVED CRACKED ZEE PAN IAW DC8 SRM 51-1-20D ATI REPAIR SPECIFICATION NR 2003-05, DWG DOUGLAS NR 5769 857. PERFORMED HEAT TREATMENT IAW DC8 SRM 51-1-1 PAGES 1, 13, 17. CLEANED, TREATED AND PRIMED AREA, ZEE PAN IAW DC8 SRM 51-1-8 PAGES 17, 18. INSTALLED NEW ZEE PAN IAW DC8 SRM 51-1-20D, DC8 SRM 51-3-1.
Part: PLUG — INSTALLED (LAV DRAIN) · airframe 71,621 hrs · 17,096 cycles
DURING C CHECK, 'LAVATORY DRAIN HOLE PLUG INSTALLATION REQUIRED (STA 240.000 - 260.000, L-19R TO L-18R). PERFORMED MAJOR REPAIR IAW FAA FORM 8110-3 NR 06029 DATED 01-23-06, SEMAN DWG ED-4168 DATED 01-21-06, EO SEMAN NR 2006101 DATED 01-23-06. REMOVED EXISTING DRAIN WASTE HOLE, REMOVED AREA IAW SEMAN DWG ED-4168. PERFORMED NDT INSP IAW DC8 NDT SPM PART 06-10-01-001. FABRICATED EXTERNAL REPAIR DOUBLER (AL7075T6 0.063â). CLEANED, TREATED AND PRIMED AREA + REPAIR PARTS IAW DC8 SRM 51-1-8B. APPLIED SEALANT TO FAYING SURFACES IAW DC8 SRM 51-1-11. INSTALLED REPAIR PARTS IAW SEMAN DWG ED-4168, DC8 SRM 51-1-20D, DC8 SRM 51-3-1 (TORQUE).
Part: SKIN — CRACKED (RT WING) · airframe 71,621 hrs · 17,096 cycles
DURING ROUTINE C-CHECK INSPECTION, RT WING NR 4 WING DOUBLER LWR SKIN CRACKED .25 INCH, XS 520.222. PERFORMED MAJOR REPAIR IAW DC8 SRM 57-2-1A FIG 1 PAGE 3. REMOVED CRACKED DOUBLER IAW DC8 SRM 51-1-20D. STOP DRILLED CRACK. FABRICATED EXTERNAL REPAIR DOUBLER (AL7075 T6 0.063) IAW DC8 SRM 57-2-1A FIG 1. CLEANED, TREATED AND PRIMED AREA & REPAIR PARTS INNER FACE IAW DC8 SRM 51-1-8B. APPLIED SEALANT TO FAYING SURFACE IAW DC8 SRM 51-1-11. INSTALLED REPAIR PARTS IAW DC8 SRM 57-2-1A FIG 1 PAGE 3, DC-8 SRM 51-1-21, DC-8 SRM 51-1-20D AND DC-8 SRM 51-3-1 (TORQUE).
Part: SKIN — CORRODED (RUDDER) · airframe 71,621 hrs · 17,096 cycles
DURING C CHECK INSPECTION, LT RUDDER EXTERNAL SKIN CORRODED, STA ZR 257.906. PERFORMED MAJOR REPAIR IAW DC8 SRM 55-6-1. REMOVED CORROSION IAW DC8 SRM 51-1-8 PG 17-18. FOUND OUT OF LIMITS IAW DC8 SRM 55-2-0 PG 12. REMOVED CORRODED PLATING IAW DC8 SRM 55-1-0, DC8 SRM 51-1-21. FABRICATED NEW PLATING + BONDED FINGER DOUBLER (AL2024T30 0.016) IAW DC8 SRM 55-6-1 FIG 1 ITEM âAâ. BONDED BOTH PARTS WITH HYSOL IAW DC8 SRM 51-1-9. CLEANED, TREATED AND PRIMED AREA + NEW PANEL PLATING IAW DC8 SRM 51-1-8B. APPLIED SEALANT TO FAYING SURFACES IAW DC8 SRM 51-1-11. INSTALLED NEW PANEL PLATING IAW DC8 SRM 51-1-21. REFER TO NR 2849 FOR BALANCING.
Part: AILERON — CORRODED (RT WING) · airframe 71,621 hrs · 17,096 cycles
DURING ROUTINE C-CHECK INSPECTION, RT WING INBOARD AILERON WITH CORROSION AND NON STANDARD REPAIR IN LOWER PLATING AT STA XA 550.00. PERFORMED MAJOR REPAIR. REMOVED CORROSION, FOUND OUT OF LIMITS. REMOVED EXISTING PANEL PLATING (CORRODED) + REPAIR NON STANDARD. FABRICATED NEW PANEL PLATING (AL2024T3 0.025) + BONDED FINGER DOUBLER (AL 2024T3 0.020) IAW DC8 SRM 57-8-1 FIG 1 ITEM B, K, DWG DOUGLAS 5705334. BONDED BOTH PARTS WITH HYSOL IAW DC8 SRM 51-1-9. CLEANED, TREATED AND PRIMED AREA + NEW PANEL PLATING INTERNAL PART IAW DC8 SRM 51-1-8B. APPLIED SEALANT TO FAYING SURFACE IAW DC8 SRM 51-1-11. INSTALLED NEW PANEL PLATING IAW DC8 SRM 51-1-1.
Part: SKIN — CORRODED (LT WING FLAP) · airframe 71,621 hrs · 17,096 cycles
DURING C CHECK INSPECTION, LT OTBD FLAP, T/E INTERNAL PART LWR SKIN CORRODED XF 415.000 XF 435.000. PERFORMED MAJOR REPAIR IAW DC8 SRM 57-7-1 FIG 4, TR NR 57-94 DATE 10-01-02. REMOVED CORROSION IAW DC8 SRM 51-1-8 PG 17-18. FOUND OUT OF LIMITS IAW DC8 SRM 57-2-0 PAGE 16. REMOVED CORRODED PANEL PLATING IAW DC8 SRM 57-1-0 PAGE 1, DC8 SRM 51-1-21. FAB`D NEW PLATING + BONDED FINGER DOUBLER IAW DC8 SRM 57-7-1 FIG 4 ITEM âUâ, âQâ. BONDED PLATING + FINGER DOUBLER WITH HYSOL IAW DC8 SRM 51-1-9. CLEANED, TREATED AND PRIMED AREA + NEW PANEL PLATING INTERNAL PART IAW DC8 SRM 51-1-8B. APPLIED SEALANT TO FAYING SURFACES IAW DC8 SRM 51-1-11. INSTALLED NEW PLATING IAW DC8 SRM 51-2-1
Part: FLOORBEAM — CORRODED (BS 1548) · airframe 71,621 hrs · 17,096 cycles
DURING C CHECK, MAIN CARGO COMPT FLOORBEAM UPPER FLANGE CORRODED AT STA 1548.000 BL 0. PERFORMED MAJOR REPAIR IAW DC8 SRM 51-2-1 FIG 1 (SHEET 8), TR NR 51-130 DATED 01-26-04. REMOVED CORROSION IAW DC8 SRM 51-1-8 PG 17-18. FOUND OUT OF LIMITS IAW DC8 SRM 53-2-0 PG 2P. REMOVED FASTENERS IAW DC8 SRM 51-1-20D. CUT OUT CORRODED SECTION + FAB`D REPAIR ANGLE + (02EA) FILLER IAW DC8 SRM 51-2-1 FIG 1 (SHEET 8), DC8 SRM 53-5-2 FIG 3 (SHEET 2) ITEM âDâ, DC8 SRM 51-2-0 FIG 50 (SHEET 6). CLEANED, TREATED AND PRIMED AREA + REPAIR PARTS IAW DC8 SRM 51-1-8B. APPLIED SEALANT TO FAYING SURFACES IAW DC8 SRM 51-1-11. INSTALLED REPAIR PARTS IAW DC8 SRM 51-2-1 FIG 1 (SHEET 8, 12), DC8 SRM 51-1-20D, DC8 SRM 51-3-1 (TORQUE)
Part: SKIN — CORRODED (RT WING TE FLAP) · airframe 71,621 hrs · 17,096 cycles
DURING C CHECK INSPECT, RT WING INBD FLAP UPPER SKIN CORRODED AT STA XW 1.00. PERFORMED MAJOR REPAIR IAW DC8 SRM 57-7-1 FIG 1. REMOVED CORROSION IAW DC8 SRM 51-1-8 PG 17-18. FOUND OUT OF LIMITS IAW DC8 SRM 57-2-0 PG 16. REMOVED CORRODED PANEL PLATING IAW DC8 SRM 57-1-0 PAGE 1, DC8 SRM 51-1-21. FABRICATED NEW PLATING, BONDED FINGER DOUBLER IAW DC8 SRM 57-7-1 FIG 1 ITEM A, L. BONDED BOTH PARTS WITH HYSOL IAW DC8 SRM 51-1-9. CLEANED, TREATED AND PRIMED AREA, INNER FACE OF NEW PANEL PLATING IAW DC8 SRM 51-1-8B. APPLIED SEALANT TO FAYING SURFACE IAW DC8 SRM 51-1-11. INSTALLED NEW PANEL PLATING IAW DC8 SRM 51-1-1.
Part: SKIN — CORRODED (RUDDER) · airframe 71,621 hrs · 17,096 cycles
DURING ROUTINE C CHECK INSPECTION, RT RUDDER EXTERNAL SKIN CORRODED, STA ZR 110.750. PERFORMED MAJOR REPAIR IAW DC-8 SRM 55-6-1 FIG 1. REMOVED CORROSION IAW DC-8 SRM 51-1-8 PAGES 17-18. FOUND OUT OF LIMITS IAW DC-8 SRM 57-2-0 PAGE 12. REMOVED CORRODED PANEL PLATING IAW DC-8 SRM 55-1-0 PAGE 1, DC-8 SRM 51-1-21. FABRICATED NEW PLATING & BONDED FINGER DOUBLER IAW DC-8 SRM 55-6-1 FIG 1 ITEM âAâ. BONDED BOTH PARTS WITH HYSOL IAW DC-8 SRM 51-1-9. CLEANED, TREATED AND PRIMED AREA, INNER FACE OF NEW PLATING IAW DC-8 SRM 51-1-8B. APPLIED SEALANT TO FAYING SURFACES IAW DC-8 SRM 51-1-11. INSTALLED NEW PANEL PLATING IAW DC-8 SRM 51-1-21.
Part: FLOORBEAM — CORRODED (BS 1500) · airframe 71,621 hrs · 17,096 cycles
DURING ROUTINE C-CHECK INSPECTION, AFT CARGO COMPT - FLOORBEAM UPPER FLANGE CORRODED; STA 1500.000 RBL 42 - RBL 50. PERFORMED MAJOR REPAIR IAW DC8 SRM 51-2-1 FIG 1 (SHEET 9), TR 51-130 DATED 01-26-04. REMOVED FASTENERS IAW DC8 SRM 51-1-21. REMOVED DAMAGED SECTION IAW DC8 SRM 51-2-1 FIG 1 (SHEET 9). FABRICATED REPAIR ANGLE (EXTRUSION 7075T6511 0.170) & FILLER (EXTRUSION 7075T6511) IAW DC8 SRM 51-2-1 FIG 1 (SHEET 9, 12), DC8 SRM 53-7-2 FIG 9 ITEM C, DC8 SRM 51-2-0 FIG 50 (SHEET 73). CLEANED, TREATED AND PRIMED IAW DC8 SRM 51-1-8B. APPLIED SEALANT TO FAYING SURFACES IAW DC8 SRM 51-1-11. INSTALLED REPAIR PARTS IAW DC8 SRM 51-2-1 FIG 1 (SHEET 9, 12), DC8 SRM 51-1-21, DC8 SRM 51-1-20D, DC8 SRM 51-3-1 (TORQUE).
Part: SKIN — CRACKED (TE FLAP) · airframe 71,621 hrs · 17,096 cycles
DURING ROUTINE C CHECK INSPECTION, RT OTBD FLAP PANEL UPPER SKIN CRACKED 1", AT STA XF 415.000. PERFORMED MAJOR REPAIR IAW DC-8 SRM 57-2-5 FIG 1 (SHEET 1-2). REMOVED FASTENERS IAW DC-8 SRM 51-1-21. REMOVED DAMAGED SECTION IAW DC-8 SRM 57-2-5 FIG 1. FAB`D NEW PLATING SEGMENT + SPLICE + FILLER IAW DC-8 SRM 57-2-5 FIG 1 (SHEET 1,2), DC-8 SRM 57-7-1 FIG 4, TR # 57-94 ITEM Q U. CLEANED, TREATED AND PRIMED AREA + REPAIR PARTS IAW DC-8 SRM 51-1-8B. APPLIED SEALANT TO FAYING SURFACES IAW DC-8 SRM 51-1-11. INSTALLED REPAIR PARTS IAW DC-8 SRM 57-2-5 FIG 1 (SHEET 1,2), DC-8 SRM 51-1-21, DC-8 SRM 51-3-0, DC-8 SRM 51-3-1.
Part: REPAIR — MISINSTALLED (TE FLAP) · airframe 71,621 hrs · 17,096 cycles
DURING ROUTINE C-CHECK INSPECTION, LT OUTBD FLAP T/E UPPER SURFACE HAS NO STANDARD REPAIR, STA XF 403.000. PERFORMED MAJOR REPAIR IAW DC8 SRM 57-7-1 FIG 4, TR 57-94 DATE 10-01-02. REMOVED PANEL PLATING WITH NON STANDARD REPAIR IAW DC8 SRM 57-1-0, DC8 SRM 51-1-21. FABRICATED NEW PLATING (AL 2024 T30 0.025) BONDED FINGER DOUBLER (AL 2024 T3 0.020) IAW DC8 SRM 57-7-1 FIG 4. BONDED PANEL PLATING & FINGER DOUBLER WITH HYSOL IAW DC-8 SRM 51-1-9. CLEANED, TREATED AND PRIMED AREA, NEW PANEL PLATING INTERNAL PART IAW DC8 SRM 51-1-8B. APPLIED SEALANT TO FAYING SURFACE IAW DC8 SRM 51-1-11 PG 9. INSTALLED NEW PLATING IAW DC8 SRM 51-1-21.
Part: FITTING — CRACKED (FUSELAGE) · airframe 71,621 hrs · 17,096 cycles
DURING ROUTINE C-CHECK INSPECTION, FWD CARGO COMPT STRUCTURE UNDER CROSS-SLIDE DOOR -B- HAS CRACKED FITTING STA 540.000 BETWEEN L-26L AND L-27L. REMOVED CRACKED FITTING IAW DC-8 SRM 51-1-20D. CLEANED, TREATED AND PRIMED AREA IAW DC-8 SRM 51-1-8B. INSTALLED NEW FITTING IAW DC-8 SRM 51-1-21, DC-8 SRM 51-1-20D, DC-8 SRM 51-3-1 (TORQUE).
Part: SKIN — CORRODED (RUDDER) · airframe 71,621 hrs · 17,096 cycles
DURING ROUTINE C-CHECK INSPECTION, RT RUDDER EXTERNAL SKIN CORRODED, STA ZR 276.531. PERFORMED MAJOR REPAIR. REMOVED CORROSION IAW DC-8 SRM 51-1-8 PAGES 17-18. FOUND OUT OF LIMITS IAW DC-8 SRM 55-2-0 PAGE 12. REMOVED CORRODED PANEL PLATING IAW DC-8 SRM 55-1-0, DC-8 SRM 51-1-21. FABRICATED NEW PANEL PLATING + BONDED FINGER DOUBLER (ALCLAD 7075 T6 0.016) IAW DC-8 SRM 55-6-1 FIG 1 ITEM A. BONDED BOTH PARTS WITH HYSOL IAW DC-8 SRM 51-1-9. CLEANED, TREATED AND PRIMED AREA + NEW PANEL PLATING IAW DC-8 SRM 51-1-8B. APPLIED SEALANT TO FAYING SURFACES IAW DC-8 SRM 51-1-11. INSTALLED NEW PANEL PLATING IAW DC-8 SRM 51-1-21, DC-8 SRM 51-3-0, DC-8 SRM 51-3-1 (TORQUE) REFER TO N/R 2849 FOR BALANCING.
Part: FITTING — CORRODED (FUSELAGE) · airframe 71,621 hrs · 17,096 cycles
DURING ROUTINE C-CHECK INSPECTION, FWD ACCY COMPT FITTING CORRODED AT STA 270.000, L-29 (RT). REMOVED CORROSION ON FITTING IAW DC-8 SRM 51-1-8 PAGES 17-18. FOUND OUT OF LIMITS IAW DC-8 SRM 53-2-0 PAGE 2P. REMOVED CORRODED FITTING IAW DC-8 SRM 51-1-21. CLEANED, TREATED AND PRIMED AREA IAW DC-8 SRM 51-1-8B. INSTALLED NEW FITTING IAW DC-8 SRM 51-1-21, DC-8 SRM 51-1-20D, DC-8 SRM 51-3-1 (TORQUE).
Part: SKIN — CORRODED (RT WING) · airframe 71,621 hrs · 17,096 cycles
DURING ROUTINE C-CHECK INSPECTION, RT WING CTR L/E LWR EXTERNAL SKIN CORRODED AT STA XFS 435.789. PERFORMED MAJOR REPAIR IAW FAA FORM 8110-3 06007 DATED 01-06-06, SEMAN DWG ED-4142 DATED 01-04-06, ED SEMAN 2005 1554 DATED 01-06-06. REMOVED CORROSION IAW DC8 SRM 51-1-8 PAGES 17-18. FOUND OUT OF LIMITS IAW DC-8 SRM 57-2-1 FIG 2G. REMOVED CORRODED SECTION IAW SEMAN DWG ED-4142. PERFORMED NDT INSPECTION IAW DC8 NDT SPM PART 06-10-01-001. FABRICATED REPAIR DOUBLER (AL 7075 T6 0.071) & FILLER AL 7075 T6 0.063) IAW SEMAN DWG ED-4142. CLEANED TREATED; PRIMED AREA & REPAIR PARTS INNER FACE IAW DC8 SRM 51-1-8B. APPLIED SEALANT TO FAYING SURFACES IAW DC8 SRM 51-1-11. INSTALLED REPAIR PARTS. (TORQUE)
Part: SKIN — CRACKED (LT WING) · airframe 71,621 hrs · 17,096 cycles
DURING C-CHECK INSPECTION, LT WING - UPPER SKIN CRACKED .5 INCH, AT STA XRS 110.000, S-16. PERFORMED MAJOR REPAIR IAW FAA FORM 8110-3 06006 DATED 01-05-06, SEMAN DWG ED-4141 DATED 01-03-06, EO SEMAN 20051523 DATED 01-05-06. REMOVED FASTENERS. CUT OUT DAMAGED SECTION IAW SEMAN DWG ED-4141. PERFORMED NDT INSP IAW DC8 NDT SPM PART 06-10-01-001. FABRICATED REPAIR DOUBLER (AL7075T6 0.190) & FILLER (AL7075T6 0.175) AND TAPERED DOUBLER FROM 0.190 TO 0.063 IAW SEMAN DWG ED-4141. CLEANED, TREATED AND PRIMED AREA & REPAIR PARTS INNER FACE IAW DC8 SRM 51-1-8B. APPLIED SEALANT TO FAYING SURFACES IAW DC8 SRM 51-1-11. INSTALLED REPAIR PARTS IAW SEMAN DWG ED-4141, DC8 SRM 51-1-20D, DC8 SRM 51-3-1 (TORQUE).
Part: FITTING — CRACKED (BS 1180-1200) · airframe 71,621 hrs · 17,096 cycles
DURING ROUTINE C CHECK INSPECTION, AFT CARGO COMPT SPLICE FITTING CRACKED 1 1/2" BS 1180.000 - 1200.000, L-36). REMOVED CRACKED SPLICE FITTING IAW DC8 SRM 51-1-20D. CLEANED, TREATED, PRIMED AREA IAW DC8 SRM 51-1-8B. INSTALLED NEW SPLICE FITTING IAW DC8 SRM 51-1-20D, DC8 SRM 51-3-1 (TORQUE).
Part: SKIN — CORRODED (RUDDER) · airframe 71,621 hrs · 17,096 cycles
DURING ROUTINE C-CHECK INSPECTION, RT RUDDER EXTERNAL SKIN CORRODED, STA ZR 319.063. PERFORMED MAJOR REPAIR IAW DC-8 SRM 55-6-1 FIG 1. REMOVED CORROSION IAW DC-8 SRM 51-1-8 PAGES 17-18. FOUND OUT OF LIMITS IAW DC-8 SRM 55-2-0 PAGE 12. REMOVED CORRODED PANEL PLATING IAW DC-8 SRM 55-1-0, DC-8 SRM 51-1-21. FABRICATED NEW PANEL PLATING + BONDED FINGER DOUBLER (ALCLAD 7075 T6 0.016) IAW DC-8 SRM 55-6-1 FIG 1 ITEM -A-. BONDED BOTH PARTS WITH HYSOL IAW DC-8 SRM 51-1-9. CLEANED, TREATED AND PRIMED AREA + NEW PANEL PLATING IAW DC-8 SRM 51-1-8B. APPLIED SEALANT TO FAYING SURFACES IAW DC-8 SRM 51-1-11. INSTALLED NEW PANEL PLATING (TORQUE) REFER TO N/R 2849 FOR BALANCING.
Part: FITTING — CORRODED (THRUST REVERSER) · airframe 71,621 hrs · 17,096 cycles
DURING ROUTINE C-CHECK INSPECTION, NR 3 ENGINE - RAIL FITTING CORRODED AT 12 O' CLOCK POSITION, YN 278.000 (RT SIDE). REMOVED LEVEL I CORROSION FROM RAIL FITTING IAW DC-8 SRM 51-1-8 PAGES 17-18 (MATERIAL THICKNESS: 0.130, BLEND OUT: 0.005, REMAINING THICKNESS: 0.125) FOUND WITHIN ALLOWABLE LIMITS IAW CFM56 MM 78-31-20 PAGES 609-610. CLEANED, TREATED AND PRIMED IAW DC-8 SRM 51-1-8B.
Part: REPAIR — MISINSTALLED (ZONE 100) · airframe 71,621 hrs · 17,096 cycles
DURING C CHECK INSPECT, EXTERNAL FUSELAGE LT AFT HEAT EXCHANGER RT LWR CORNER HAS NON STANDARD REPAIR. PERFORMED MAJOR REPAIR IAW FAA FORM 8110-3 NR 05582 DATED 12-23-05 SEMAN DWG NR ED-4131 DATED 12-20-05, ED SEMAN NR 2005 1436 DATED 12-23-05. REMOVED NON STANDARD REPAIR IAW DC8 SRM 51-1-20D. REMOVED DAMAGED SECTION IAW SEMAN DWG ED-4131. PERFORMED NDT INSP. IAW DC8 NDT SPM PART 06-10-01-001 FAB`D REPAIR DOUBLER + REPAIR TRIPLER + FILLER IAW SEMAN DWG ED-4131 CLEANED TREATED; PRIMED AREA + REPAIR PARTS IAW DC8 SRM 51-1-8B. APPLIED SEALANT TO FAYING SURFACES IAW DC8 SRM 51-1-11 INSTALLED REPAIR PARTS IAW SEMAN DWG ED-4131, DC8 SRM 51-1-21, DC8 SRM 51-1-20D, DC8 SRM 51-3-1 (TORQUE).
Part: FITTING — CORRODED (THRUST REVERSER) · airframe 71,621 hrs · 17,096 cycles
DURING ROUTINE C-CHECK INSPECTION, NR 3 ENGINE - RAIL FITTING CORRODED, YN 278.000 AT 12 O'CLOCK POSITION (LT SIDE). REMOVED AND REPLACED NR 3 ENGINE LT TRANSLATING COWL IAW CFM 56 MM 78-31-20 PAR 3A-3B, PG 402, 422. REFER TO JC SVC-7003-7104 FOR OPS CHECK.
Part: SKIN — DENTED (TE FLAP) · airframe 71,621 hrs · 17,096 cycles
DURING ROUTINE C CHECK INSPECTION, RT OUTBD FLAP PANEL LWR SKIN DENTED, AT STA XF 420.000. PERFORMED MAJOR REPAIR IAW DC-8 SRM 57-2-1 FIG 2Q. REMOVED FASTENERS IAW DC-8 SRM 51-1-21. REMOVED DAMAGED SECTION IAW DC-8 SRM 57-2-1 FIG 2Q. FABRICATED EXTERNAL REPAIR DOUBLER (ALCLAD 2024 T3 0.050) IAW DC-8 SRM 57-2-1 FIG 2Q, DC-8 SRM 57-7-1 FIG 4, TR # 57-94 ITEM U Q DATED 10-01-02. CLEANED, TREATED AND PRIMED AREA + EXTERNAL REPAIR DOUBLER IAW DC-8 SRM 51-1-8B. INSTALLED EXTERNAL REPAIR DOUBLER IAW DC-8 SRM 57-2-1 FIG 2Q, DC-8 SRM 51-1-9 (HYSOL), DC-8 SRM 51-1-21.
Part: LONGERON — CRACKED (FUSELAGE) · airframe 71,621 hrs · 17,096 cycles
DURING ROUTINE C-CHECK INSPECTION, FWD CARGO COMPT L-34L CRACKED BETWEEN STA 600.000 AND STA 620.000. PERFORMED MAJOR REPAIR. REMOVED FASTENERS, REMOVED LONGERON SEGMENT. FABRICATED SPLICES (02 EA) (EXTRUSION BAR 7075 T6 51) FABRICATED NEW LONGERON SEGMENT (EXTRUSION 7075 T6 51) PERFORMED HEAT TREATMENT TO SPLICES (7075 T6 5 TO 7075 T6) IAW DC-8 SRM 51-1-1 PAGES 1, 13, 17. PERFORMED NDT INSPECTION IAW DC-8 NDT SPM PART 08-00-02- TO 07. CLEANED, TREATED AND PRIMED AREA + REPAIR PARTS IAW DC-8 SRM 51-1-8B. APPLIED SEALANT TO FAYING SURFACES IAW DC-8 SRM 51-1-11. INSTALLED REPAIR PARTS IAW DC-8 SRM 53-2-2 PAGE 6 FIG 4A, DC-8 SRM 53-2-2 FIG 10, DC-8 SRM 51-1-20D, DC-8 SRM 51-3-1 (TORQUED).
Part: LONGERON — CORRODED (BS 286.000) · airframe 71,621 hrs · 17,096 cycles
DURING ROUTINE C-CHECK INSPECTION, FWD CARGO COMPT - L-36 CORRODED AT STA 286.000. REMOVED LEVEL I CORROSION IAW DC-8 SRM 51-1-8 PAGES 17-18 MEASURED: THICKNESS: 0.120, BLEND OUT: 0.003, REMAINING THICKNESS: 0.117. FOUND WITHIN ALLOWABLE LIMITS IAW DC-8 SRM 53-2-0 FIG 16 SHEET 3. CLEANED, TREATED AND PRIMED IAW DC-8 SRM 51-1-8B.
Part: SKIN — CORRODED (VERTICAL STAB) · airframe 71,621 hrs · 17,096 cycles
DURING ROUTINE C-CHECK INSPECTION, RT VERT STAB SKIN CORRODED, AT STA ZR 101.856. REMOVED LEVEL 1 CORROSION IAW DC-8 SRM 51-1-8 PAGES 17-18. MEASURED: THICKNESS 0.025, BLEND OUT 0.002, REMAINING MATERIAL 0.023 FOUND WITHIN ALLOWABLE LIMITS IAW DC-8 SRM 55-2-0 FIG 6 SHEET 1. CLEANED, TREATED AND PRIMED IAW DC-8 SRM 51-1-8B.
Part: LONGERON — CRACKED (BS 600-620 L33L) · airframe 71,621 hrs · 17,096 cycles
DURING ROUTINE C CHECK INSPECTION, FWD CARGO COMPT L-33L CRACKED, STA 600.000 - STA 620.000. REMOVED CORROSION FROM FWD CARGO COMPT INTERNAL SKIN (SAT 570.000 â 580.000, L-29R TO L-29R TO L-26R) IAW DC-8 SRM 51-1-8 PAGES 17-18 (MATERIAL THICKNESS: 0.063â, BLENDOUT: 0.004, REMAINING THICKNESS: 0.059). FOUND WITHIN ALLOWABLE LIMITS IAW DC-8 SRM 53-2-0 FIG 1F SHEET 3. CLEANED, TREATED AND PRIMED IAW DC-8 SRM 51-1-8B.
Part: VANE — DAMAGED (TE FLAP) · airframe 71,621 hrs · 17,096 cycles
DURING C-CK, LT WING OTBD FLAP VANE HOLES ELONGATED , XOLDI 6.224. PERFORMED MAJOR REPAIR IAW FAA FORM 8110-3 NR 05587 DATED 12-29-05 SEMAN DWG NR ED-4122 DATED 12-28-05, ED SEMAN NR 2005 1453. REMOVED EXISTING REPAIR DOUBLER IAW DC8 SRM 51-1-21, DC8 SRM 51-1-20D, DC8 SRM 51-3-0. CUT OUT DAMAGED SECTION IAW SEMAN DWG # ED-4122 PERFORMED NDT INSP IAW DC8 NDT SPM PART 06-10-01-001. FAB`D REPAIR DOUBLER + FILLER + INTERNAL DOUBLER IAW SEMAN DWG # ED-4122 CLEANED TREATED; PRIMED AREA + REPAIR PARTS INNER FACE IAW DC8 SRM 51-1-8B APPLIED SEALANT TO FAYING SURFACES IAW DC8 SRM 51-1-11 INSTALLED REPAIR PARTS IAW SEMAN DWG # ED-4122 DC8 SRM 51-1-21, DC8 SRM 51-3-0, DC8 SRM 51-1-20D, DC8 SRM 51-3-1 (TORQUE)
Part: SKIN — CORRODED (AILERONS) · airframe 71,621 hrs · 17,096 cycles
DURING ROUTINE C CHECK INSPECTION, LT OUTBD AIL LWR SKIN CORRODED, STA XA 726.000. PERFORMED MAJOR REPAIR IAW DC8 SRM 57-8-1 FIG 4. REMOVED CORROSION FROM LT OTBD AIL LWR SKIN, STA 726.000 IAW DC-8 SRM 51-1-8 PAGES 17-18. FOUND OUT OF LIMITS IAW DC-8 SRM 57-2-0 PAGE 16. REMOVED DAMAGED PANEL PLATING IAW DC8 SRM 57-1-0 PAGE 1, DC8 SRM 51-1-21. FAB`D NEW PANEL PLATING + FINGER DOUBLER IAW DC8 SRM 57-8-1 FIG 4 ITEM E, L IAW DC-8 SRM 57-8-1 FIG 4. BLENDED BOTH PARTS IAW DC-8 SRM 51-1-9 (HYSOL). CLEANED, TREATED AND PRIMED AREA + INNER FACE OF NEW PLATING IAW DC8 SRM 51-1-8B. APPLIED SEALANT TO FAYING SURFACE IAW DC8 SRM 51-1-11. INSTALLED NEW PANEL PLATING IAW DC8 SRM 51-1-21.
Part: SKIN — DENTED (TE FLAP) · airframe 71,621 hrs · 17,096 cycles
DURING ROUTINE C CHECK INSPECTION, ON RIGHT OUTBOARD FLAP, A SMALL DENT WAS FOUND ON UPPER SKIN AT STA XF 217, DUE TIME CHANGE. PERFORMED MAJOR REPAIR IAW DC8 SRM 57-7-1 FIG 4, TR 57-94, EO SEMAN 20051460 DATED 12-16-05. REMOVED DAMAGED PLATING IAW DC8 SRM 57-1-0, DC8 SRM 51-1-21. FABRICATED NEW PLATING IAW DC8 SRM 57-7-1 FIG 4, TR 57-94 ITEM C DATED 10-01-02. CLEANED, TREATED AND PRIMED INNER FACE OF NEW PLATING IAW DC8 SRM 51-1-8B. APPLIED SEALANT TO FAYING SURFACE IAW DC8SRM 51-1-11 PG 9. INSTALLED NEW PLATING IAW DC8 SRM 51-1-21.
Part: SKIN — CRACKED (ZONE 800) · airframe 71,621 hrs · 17,096 cycles
DURING ROUTINE C CHECK INSPECTION, NR 12 ACCESS DOOR EXTERNAL SKIN CRACKED 1/2". PERFORMED MAJOR REPAIR IAW DC-8 SRM 52-8-2 FIG 1 (SHEET 1), BOEING MESSAGE NR 1-151096062-2 DATED 01-12-06. REMOVED DAMAGED SKIN IAW DC-8 SRM 52-1-0 PAGE 1, DC-8 SRM 51-1-21. FABRICATED NEW SKIN IAW DC-8 SRM 52-8-2 FIG 1 (SHEET 1) ITEM DC-8 SRM 51-9-0 PAGE 10A, BOEING MESSAGE 1-151096062-2. CLEANED, TREATED AND PRIMED NEW SKIN IAW DC-8 SRM 51-1-8B. INSTALLED NEW SKIN IAW DC-8 SRM 51-1-21, DC-8 SRM 51-1-11 PAGE 9.
Part: FLOORBEAM — CORRODED (BS 1440) · airframe 71,621 hrs · 17,096 cycles
DURING C CHECK INSPECT, AFT CARGO COMPT BEAM FLOOR WEB CORRODED , STA 1440.000 RBL 45. PERFORMED MAJOR REPAIR IAW DC8 SRM 51-2-1 FIG 1 (SHEET 2, 12), TR 51-130 DATED 01-26-04. REMOVED FASTENERS IAW DC8 SRM 51-1-20D. REMOVED CORROSION IAW DC8 SRM 51-1-8 PG 17-18. FOUND OUT OF LIMITS IAW DC8 SRM 53-2-0 PG 2P. CUT OUT CORRODED SECTION, FABRICATED REPAIR ANGLE, FILLER WEB, REPAIR DOUBLER, SPACER WEB IAW DC8 SRM 51-2-1 FIG 1 (SHEET 2, 12), DC8 SRM 53-7-2 FIG 9 ITEM B, DC8 SRM 51-2-0 FIG 50 (SHEET 71). CLEANED, TREATED AND PRIMED AREA, REPAIR PARTS IAW DC8 SRM 51-1-11. INSTALLED REPAIR PARTS IAW DC8 SRM 51-2-1 FIG 1 (SHEET 2, 12), DC8 SRM 51-1-20D, DC8 SRM 51-3-1 (TORQUE).
Part: SKIN — CRACKED (RT WING LE) · airframe 71,621 hrs · 17,096 cycles
DURING C CHECK, RT WING OTBD L/E LWR PART SKIN CRACKED ½, XFS 710.000. PERFORMED MAJOR REPAIR IAW FAA FORM 8110-3 NR 06014 DATED 01-11-06, SEMAN DWG ED-4144 DATED 01-06-06, EO SEMAN NR 20051569 DATED 01-11-06. REMOVED FASTENERS IAW DC8 SRM 51-1-21, DC8 SRM 51-3-0. REMOVED DAMAGED SECTION IAW SEMAN DWG ED-4144. PERFORMED NDT INSP IAW DC8 NDT SPM PART 06-10-01-001. FAB`D REPAIR DOUBLER (AL7075T6 0.063â) + FILLER (AL7075T6 0.050â) IAW SEMAN DWG ED-4144. CLEANED, TREATED AND PRIMED AREA + REPAIR PARTS INNER FACE IAW DC8 SRM 51-1-8B. APPLIED SEALANT TO FAYING SURFACES IAW DC8 SRM 51-1-11. INSTALLED REPAIR PARTS IAW SEMAN DWG ED-4144, DC8 SRM 51-1-21, DC8 SRM 51-3-0, DC8 SRM 51-1-20D, DC8 SRM 51-3-1 (TORQUE).
Part: SKIN — CORRODED (FUSELAGE) · airframe 71,621 hrs · 17,096 cycles
DURING ROUTINE C-CHECK INSPECTION, FWD CARGO COMPT INTERNAL SKIN CORRODED BETWEEN STA 570.000 AND STA 580.000, L-29R - L-26R. REMOVED CORROSION FROM FWD CARGO COMPT INTERNAL SKIN (SAT 570.000, 580.000, L-29R TO L-29R TO L-26R) IAW DC-8 SRM 51-1-8 PAGES 17-18 (MATERIAL THICKNESS: 0.063, BLENDOUT: 0.004, REMAINING THICKNESS: 0.059). FOUND WITHIN ALLOWABLE LIMITS IAW DC-8 SRM 53-2-0 FIG 1F SHEET 3. CLEANED, TREATED AND PRIMED IAW DC-8 SRM 51-1-8B.
Earlier reports · 2005 · 50 reports
2005
Part: SKIN — CORRODED (LT WING) · airframe 71,621 hrs · 17,096 cycles
DURING INSPECT, LT WING OTBD L/E HAS NON STANDARD REPAIR, XW 485.000. PERFORMED REPAIR IAW FAA FORM 8110-3 # 05582 DATE 12-23-05, SEMAN DWG # ED 4125 DATE 12-22-05 AND EO SEMAN # 20051456 DATE 12-23-05. REMOVED NON STANDARD REPAIR IAW DC-8 SRM 51-1-21, DC-8 SRM 51-3-0. REMOVED DAMAGED AREA IAW SEMAN DWG ED-4125. PERFORMED NDT INSPECT IAW DC-8 NDT IAW DC-8 NDT SPM PART 06-10-01-001. FAB`D REPAIR DOUBLER AND FILLER IAW SEMAN DWG # ED 4125. CLEANED, TREATED AND PRIMED AREA + REPAIR PARTS INTERNAL PART IAW DC-8 SRM 51-1-8B. APPLIED SEALANT TO FAYING SURFACES IAW DC-8 SRM 51-1-11. INSTALLED REPAIR PARTS IAW SEMAN DWG ED 4125, DC-8 SRM 51-1-21, DC-8 SRM 51-3-0, DC-8 SRM 51-1-20D AND DC-8 SRM 51-3-1.
Part: REPAIR — IMPROPER (RT WING) · airframe 71,621 hrs · 17,096 cycles
DURING ROUTINE C-CHECK INSPECTION, RT WING L/E HAS NON STANDARD REPAIR, XFS 761.695. PERFORMED MAJOR REPAIR IAW FAA FORM 8110-3, 06014 DATED 01-1-06, SEMAN DWG ED-4135 DATED 01-06-06, ED SEMAN 2005 1472 DATED 01-11-06. REMOVED NON STANDARD REPAIR IAW DC8 SRM 51-1-21. CUT OUT DAMAGED SECTION IAW SEMAN DWG ED-4135. FABRICATED REPAIR DOUBLER (AL 7075 T6 0.063) + (02 EA) FILLERS (AL 7075 T6 0.050) IAW SEMAN DWG ED-4135. CLEANED TREATED; PRIMED AREA + REPAIR PARTS IAW DC8 SRM 51-1-8B, APPLIED SEALANT TO FAYING SURFACES IAW DC8 SRM 51-1-11. INSTALLED REPAIR PARTS IAW SEMAN DWG ED-4135, DC8 SRM 51-3-0, DC8 SRM 51-1-21, DC8 SRM 51-3-1 (TORQUE).
Part: SKIN — DAMAGED (T/E FLAP) · airframe 71,621 hrs · 17,096 cycles
DURING ROUTINE C-CHECK INSPECTION, RT OB FLAP HAS A NON STANDARD REPAIR ON UPPER SKIN, STA XF 210.000PERFORMED MAJOR REPAIR IAW SRM 57-7-1 FIG 4, TR NR 57-94, EO SEMAN NR 20051460 DATED 12-16-05. REMOVED DAMAGED PLATING IAW SRM 57-1-0, SRM 51-1-21. FABRICATED NEW PLATING (AL2024T30 0.040â) IAW SRM 57-7-1 FIG 4, TR NR 57-94 ITEM C DATED 10-01-02. CLEANED, TREATED AND PRIMED INNER FACE OF NEW PLATING IAW SRM 51-1-8B. APPLIED SEALANT TO FAYING SURFACE IAW SRM 51-1-11 PG 9. INSTALLED NEW PLATING IAW SRM 51-1-21.
Part: FITTING — CRACKED (FUSELAGE) · airframe 71,621 hrs · 17,096 cycles
DURING ROUTINE C-CHECK INSPECTION, MAIN CARGO COMPT FITTING CRACKED 3, AT STA 1530.000, L-26R. REMOVED CRACKED FITTING IAW DC-8 SRM 51-1-21. CLEANED, TREATED AND PRIMED AREA IAW DC-8 SRM 51-1-8B. INSTALLED NEW FITTING WITH HI-LOKS IAW DC-8 SRM 51-1-20D, DC-8 SRM 51-3-1 (TORQUE).
Part: FITTING — CRACKED (BS 822.500) · airframe 71,621 hrs · 17,096 cycles
DURING ROUTINE C-CHECK INSPECTION, MAIN CARGO CMPT - WING CENTER SECTION FITTING CRACKED 3, AT STA 822.500, L-22R. REMOVED CRACKED FITTING IAW DC-8 SRM 51-1-20D. FABRICATED NEW FITTING IAW ATI REPAIR SPECIFICATION 2003-05, DOUGLAS DWG 4753360. PERFORMED NDT INSP IAW DC-8 NDT SPM PART 08-00-02-07. CLEANED, TREATED AND PRIMED AREA & NEW FITTING IAW DC-8 SRM 51-1-8B. INSTALLED NEW FITTING IAW DC-8 SRM 51-1-20D, DC-8 SRM 51-3-1.
Part: FITTING — CORRODED (ZONE 600) · airframe 71,621 hrs · 17,096 cycles
DURING ROUTINE C-CHECK INSPECTION, NR 4 ENGINE RIGHT T/R RAIL FITTING CORRODED AT 12 O`CLOCK POSITION (THRUST REVERSER). REMOVED LEVEL I CORROSION FROM RAIL FITTING IAW DC-8 SRM 51-1-8 PAGES 17-18 (MATERIAL THICKNESS: 0.133, BLEND OUT: 0.003, REMAINING THICKNESS: 0.130) FOUND WITHIN ALLOWABLE LIMITS IAW CFM MM 78-31-20 PAGES 609-610. CLEANED, TREATED AND PRIMED IAW DC-8 SRM 51-1-8B.
Part: REPAIR — MISINSTALLED (WS 304) · airframe 71,621 hrs · 17,096 cycles
DURING ROUTINE C-CHECK, RT WING - CTR L/E LWR PART HAS NON STANDARD REPAIR, XFS 304.000. PERFORMED MAJOR REPAIR IAW FAA FORM 8110-3 06006 DATED 01-05-06, SEMAN DWG ED-4134 DATED 01-04-06, ED SEMAN 2005 1471 DATED 01-05-06. REMOVED NON STANDARD REPAIR IAW DC8 SRM 51-1-21. STOP DRILLER CRACK END IAW SEMAN DWG ED-4134. PERFORMED NDT INSP IAW DC8 NDT SPM PART 06-10-01-001, FABRICATED REPAIR DOUBLER (AL 7075 T6 0.071) IAW SEMAN DWG ED-4134. CLEANED TREATED; PRIMED AREA & REPAIR DOUBLER IAW DC8 SRM 51-1-8B, APPLIED SEALANT TO FAYING SURFACES IAW DC8 SRM 51-1-11. INSTALLED REPAIR PARTS IAW SEMAN DWG ED-4134, DC8 SRM 51-1-21, DC8 SRM 51-1-20D, DC-8 SRM 51-3-0, DC8 SRM 51-3-1 (TORQUE).
Part: FITTING — CRACKED (1530 L24R) · airframe 71,621 hrs · 17,096 cycles
DURING ROUTINE C CHECK INSPECTION, MAIN CARGO CMPT FITTING CRACKED 3, AT STA 1530.000, L-24R. REMOVED CRACKED FITTING IAW DC8 SRM 51-1-20D. CLEANED, TREATED AND PRIMED AREA IAW DC8 SRM 51-1-8B. INSTALLED NEW FITTING WITH FASTENERS (HI-LOKS) IAW DC8 SRM 51-1-20D, DC8 SRM 51-3-1.
Part: LONGERON — CRACKED (BS 1617) · airframe 71,621 hrs · 17,096 cycles
DURING ROUTINE C CHECK INSPECTION, AFT FUSELAGE.- CRACKED 3, L-17L STA 1617.000. PERFORMED MAJOR REPAIR IAW SRM 53-5-2 FIG. 5. REMOVED CRACKED L-17L IAW SRM 53-1-0, SRM 51-1-20D. FABRICATED NEW LONGERON (EXTRUSION P/N S1616757) IAW SRM 53-5-2 FIG. 5 (SHEET 1) ITEM B, SRM 51-2-0 FIG. 50. CLEANED, TREATED AND PRIMED AREA IAW SRM 51-1-8B. APPLIED SEALANT TO FAYING SURFACES IAW SRM 51-1-11 PAGE 9. INSTALLED NEW LONGERON IAW SRM 51-1-20D, SRM 51-3-1 (TORQUE).
Part: VANE — DAMAGED (TE FLAP) · airframe 71,621 hrs · 17,096 cycles
C-CHECK INSPECTION, LT WING INBD FLAP VANE HOLES ELONGATED, XILD 42. PERFORMED MAJOR REPAIR. REMOVED FASTENERS, REMOVED DAMAGED SECTION. PERFORMED NDT INSPECTION. FABRICATED REPAIR DOUBLER (AL7075T60.070) & FILLER (AL7075T60.063) & INTERNAL DOUBLER (AL7075T60.063). CLEANED, TREATED; PRIMED AREA & REPAIR PARTS INNER SIDE. APPLIED SEALANT TO FAYING SURFACES IAW DC8 SRM 51-1-11 PG 9. INSTALLED REPAIR PARTS IAW SEMAN DWG ED-4120, DC8 SRM 51-1-20D, DC8 SRM 51-3-0, DC8 SRM 51-3-1 (TORQUE).
Part: FITTING — CORRODED (FUSELAGE) · airframe 71,621 hrs · 17,096 cycles
DURING ROUTINE C-CHECK INSPECTION, FWD ACCY COMPT INTERNAL PART FITTING CORRODED AT STA 270.000, L-30 (RT)REMOVED CORROSION FROM FITTING IAW SRM 51-1-8 PAGES 17-18. FOUND OUT OF LIMITS IAW SRM 53-2-0 PAGE 2A. REMOVED CORRODED FITTING IAW SRM 51-1-21. CLEANED, TREATED AND PRIMED AREA IAW SRM 51-1-8B. INSTALLED NEW FITTING IAW SRM 51-1-21, SRM 51-1-20D, SRM 51-3-1 (TORQUE).
Part: LONGERON — CRACKED (BS 1617) · airframe 71,621 hrs · 17,096 cycles
DURING ROUTINE C-CHECK INSPECTION, AFT FUS CRACKED 2, STA FS 1617.000 L.17R. PERFORMED MAJOR REPAIR IAW SRM 53-5-2 FIG. 5. REMOVED CRACKED L-17R IAW SRM 53-1-0, SRM 51-1-20D. FABRICATED NEW LONGERON (EXTRUSION P/N S1616757) IAW SRM 53-5-2 FIG. 5 (SHEET 1) ITEM B, SRM 51-2-0 FIG. 50. CLEANED, TREATED AND PRIMED AREA IAW SRM 51-1-8B. APPLIED SEALANT TO FAYING SURFACES IAW SRM 51-1-11 PAGE 9. INSTALLED NEW LONGERON IAW SRM 51-1-20D, SRM 51-3-1 (TORQUE).
Part: SKIN — CORRODED (XFS 566.250) · airframe 71,621 hrs · 17,096 cycles
DURING ROUTINE C-CHECK INSP, LT WING OB L/E CORRODED, XFS 566.250 (LWR SURFACE) PERFORMED MAJOR REPAIR IAW FAA FORM 8110-3 NR 05582 DATE 12-23-05, DWG NR ED 4126 DATE 12-21-05 EO NR 20051457 DATE 12-23-05 REMOVED FASTENERS IAW SRM 51-1-21, DC8 SRM 51-1-20D . REMOVED CORROSION IAW SRM 51-1-8 PAGES 17-18 FOUND OUT OF LIMITS IAW SRM 57-2-1 FIG 2G. REMOVED CORRODED AREA IAW DWG ED 4126 PERFORMED NDT INSPECTION IAW NDT SRM PART 06-10-01-001 FABRICATED REPAIR DOUBLER (AL7075T60.063) FILLER.
Part: SKIN — DENTED (FUSLEAGE) · airframe 71,621 hrs · 17,096 cycles
DURING ROUTINE C-CHECK INSPECTION, EXTERNAL FUS FWD CARGO COMPT AFT CARGO DOOR SKIN WITH (06EA) DENTS. PERFORMED MAJOR REPAIR IAW DC8 SRM 57-2-0 FIG 2A (SHEET 1), TR 57-84 DATED 08-01-00. REMOVED NON STANDARD REPAIR IAW DC8 SRM 51-1-21. REMOVED DAMAGED SECTION IAW DC-8 SRM 57-2-0 FIG 2A (SHEET 1). FABRICATED NEW EXT REPAIR DOUBLER , FILLER IAW DC8 SRM 57-2-0 FIG 2A (SHEET 1), DC-8 SRM 57-3-2 FIG 31. CLEANED, TREATED AND PRIMED AREA INNER SIDE IAW DC8 SRM 51-1-8B. APPLIED SEALANT TO FAYING SURFACE IAW DC8 SRM 51-1-11. INSTALLED REPAIR PARTS IAW DC8 SRM 57-2-0 FIG 2A (SHEET 1), DC-8 SRM 51-1-21.
Part: SKIN — MISREPAIRED (RT WING) · airframe 71,621 hrs · 17,096 cycles
DURING ROUTINE C-CHECK INSPECTION, RT WING - T/E LWR SKIN NON STANDARD REPAIR, XW 762.000. PERFORMED MAJOR REPAIR IAW DC8 SRM 57-2-0 FIG 2A (SHEET 1), TR 57-84 DATED 08-01-00. REMOVED NON STANDARD REPAIR IAW DC8 SRM 51-1-21. REMOVED DAMAGED SECTION IAW DC-8 SRM 57-2-0 FIG 2A (SHEET 1). FABRICATED NEW EXT REPAIR DOUBLER (AL 2024 T3 0.040) + FILLER (ALCLAD 2024 T3 0.020) IAW DC8 SRM 57-2-0 FIG 2A (SHEET 1), DC-8 SRM 57-3-2 FIG 31. CLEANED, TREATED AND PRIMED AREA INNER SIDE IAW DC8 SRM 51-1-8B. APPLIED SEALANT TO FAYING SURFACE IAW DC8 SRM 51-1-11. INSTALLED REPAIR PARTS IAW DC8 SRM 57-2-0 FIG 2A (SHEET 1), DC-8 SRM 51-1-21.
Part: LONGERON — CRACKED (FUSELAGE) · airframe 71,621 hrs · 17,096 cycles
DURING ROUTINE C-CHECK INSPECTION, AFT CARGO COMPT L-36 CRACKED 1.5 (STA 1180.000-1190.000). PERFORMED MAJOR REPAIR. REMOVED FASTENERS, REMOVED CRACKED LONGERON SEGMENT IAW DC-8 SRM 53-2-2- FIG 13 (SHEET 3, 4). FABRICATED NEW LONGERON SEGMENT P/N S2753715 EXTRUSION AL 7075 T6 511 IAW DC-8 SRM 53-4-1 FIG 44B ITEM R, DC-8 SRM 51-2-0 FIG 50 (SHEET 2B), DWG DACO 5750322 + SPLICE (AL 7075 T6 51 0.755) + DOUBLER (AL 7075 T6 0.160) IAW DC-8 SRM 53-2-2- FIG 13 (SHEET 3, 4). CLEANED, TREATED AND PRIMED AREA + REPAIR PARTS IAW DC-8 SRM 51-1-8B. APPLIED SEALANT TO FAYING SURFACES IAW DC-8 SRM 51-1-11. INSTALLED REPAIR PARTS IAW DC-8 SRM 53-2-2 FIG 13 (SHEET 3, 4), DC-8 SRM 51-1-20D, DC-8 SRM 51-3-1 (TORQUED).
Part: FRAME — CRACKED (BS 255.000) · airframe 71,621 hrs · 17,096 cycles
DURING ROUTINE C-CHECK INSP, FWD ACCY COMPT INTERNAL PART BETWEEN L-25L AND L-24L, AT STA 255.000 HAS FRAME CRACKED (1.5 INCH). PERFORMED MAJOR REPAIR IAW SRM 53-2-1 FIG.74 (SHEET 1,3). REMOVED FASTENERS IAW SRM 51-1-21. REMOVED DAMAGED SECTION. FABRICATED EXTERNAL REPAIR DOUBLER (ALCLAD 7075 T6 0.071) AND (02 EA) INTERNAL FINGER DOUBLER (ALCLAD 7075 T6 0.040â) IAW SRM 53-2-1 FIG. 7 (SHEET 1,3), SRM 53-4-1 FIG. 5 ITEM B, SRM 51-9-0 FIG. 68A. CLEANED, TREATED AND PRIMED AREA + REPAIR DOUBLER IAW SRM 51-1-8B. APPLIED SEALANT TO FAYING SURFACES IAW SRM 51-1-11 PAGE 9. INSTALLED REPAIR DOUBLER IAW SRM 53-2-1 FIG. 7 (SHEET 1,3), SRM 51-1-21, SRM 51-1-20D, SRM 51-3-1 (TORQUE).
Part: SKIN — WORN (XF 224.000) · airframe 71,621 hrs · 17,096 cycles
DURING ROUTINE C-CHECK INSPECTION, RT OB FLAP UPPER SKIN WORN, STA XF 224.000. PERFORMED MAJOR REPAIR IAW SRM 57-2-1 FIG. 2Q. REMOVED FASTENERS IAW SRM 51-1-21. REMOVED DAMAGED SECTION IAW SRM 57-2-1 FIG. 2Q. FABRICATED EXTERNAL REPAIR DOUBLER (ALCLAD 2024 T3 0.050) IAW SRM 57-2-1 FIG. 2Q, SRM 57-7-1 FIG. 4, TR NR 57-94 ITEM (C) DATED 10-01-02. CLEANED, TREATED AND PRIMED AREA AND EXTERNAL REPAIR DOUBLER IAW SRM 51-1-8B. INSTALLED EXTERNAL REPAIR DOUBLER IAW SRM 57-2-1 FIG. 2Q, SRM 51-1-9 (HYSOL), SRM 51-1-21.
Part: REPAIR — MISINSTALLED (XW 762.000) · airframe 71,621 hrs · 17,096 cycles
DURING ROUTINE C CHECK INSPECTION, LT WING.- OB L/E HAS NON STANDARD REPAIR, XW 762.000. PERFORMED MAJOR REPAIR IAW FAA FORM 8110-3 NR 06006 DATED 01-05-06 REMOVED NON-STANDARD REPAIR IAW SRM 51-1-21, SRM 51-1-20D DC8 SRM 51-3-0 REMOVED DAMAGED SECTION IAW DWG NR ED-4128 PERFORMED NDT INSP IAW NDT SPM PART 06-10-01-001 FABRICATED REPAIR DOUBLER (AL7075T60.063) FILLER (AL7075T60.050) IAW DWG NR ED-4128 CLEANED TREATED; PRIMED AREA, FILLER, REPAIR DOUBLER INNER FACE IAW SRM 51-1-8B APPLIED SEALANT TO FAYING SURFACES IAW SRM 51-1-11 INSTALLED REPAIR PARTS IAW DWG NR ED-4128, SRM 51-1-21, SRM 51-1-20D, SRM 51-3-0, SRM 51-3-1 (TORQUE).
Part: SKIN — CORRODED (LT WING) · airframe 71,621 hrs · 17,096 cycles
DURING INSPECT, LT WING CTR L/E EXT LWR SKIN CORRODED, XFS 304.000. PERFORMED REPAIR IAW FAA FORM 8110-3 NR 05586 DATE 12-28-05, SEMAN DWG NR ED 4123 DATE 12-27-05 AND EO SEMAN NR 20051454 DATE 12-28-05. REMOVED FASTENERS IAW DC-8 SRM 51-1-21 AND DC-8 SRM 51-3-0. REMOVED CORROSION IAW DC-8 RM 51-1-8 PAGES 17-18. FOUND OUT OF LIMITS IAW DC-8 SRM 57-2-1 FIG. 2G. REMOVED CORRODED AREA IAW SEMAN DWG ED-4123. PERFORMED NDT INSPECT IAW DC-8 NDT IAW DC-8 NDT SPM PART 06-10-01-001. FAB`D REPAIR DOUBLER (ALCLAD 7075 T6 0.071â) + FILLER (ALCLAD 7075 T6 0.063) IAW SEMAN DWG # ED 4123. CLEANED, TREATED AND PRIMED AREA & REPAIR PARTS INTERNAL PART IAW DC-8 SRM 51-1-8B. APPLIED SEALANT TO FAYING SURFACES IAW DC-8 SRM 51-1-1
Part: SKIN — CORRODED (LT WING) · airframe 71,621 hrs · 17,096 cycles
DURING INSPECT, LT WING CTR L/E LWR PART SKIN CORRODED, XFS 341.000. PERFORMED REPAIR IAW FAA FORM 8110-3 NR 05586 DATE 12-28-05, SEMAN DWG NR ED 4124 DATE 12-22-05, EO SEMAN NR 20051455 DATE 12-28-05. REMOVED FASTENERS IAW DC-8 SRM 51-1-21, DC-8 SRM 51-3-0. REMOVED CORROSION IAW DC-8 SRM 51-1-8 PAGES 17-18. FOUND OUT OF LIMITS IAW DC-8 SRM 57-2-1 FIG 2G. REMOVED CORRODED AREA IAW SEMAN DWG ED 4124. PERFORMED NDT INSPECT IAW DC-8 NDT IAW DC-8 NDT SPM PART 06-10-01-001. FAB`D REPAIR DOUBLER (ALCLAD 7075 T6 0.071â) + FILLER (ALCLAD 7075 T6 0.063) IAW SEMAN DWG NR ED 4124. CLEANED, TREATED AND PRIMED AREA + REPAIR PARTS INTERNAL PART IAW DC-8 SRM 51-1-8B. APPLIED SEALANT TO FAYING SURFACES IAW DC-8 SRM 51-1-11. I
Part: SKIN — CORRODED (BS 480) · airframe 71,621 hrs · 17,096 cycles
C-CHECK INSPECTION, EXTERNAL FUS LWR EXTERNAL SKIN CORRODED BETWEEN L33 AND L35R, STA 480.000 STATION 500. PERFORMED MAJOR REPAIR. REMOVED FASTENERS, REMOVED CORROSION. FOUND OUT OF LIMITS. REMOVED CORRODED SECTION. PERFORMED NDT INSPECTION. FABRICATED REPAIR DOUBLER (ALCLAD 7075 T6 0.071) & REPAIR TRIPLER (ALCLAD 7075 T6 0.090) & FILLER SKIN (ALCLAD 7075 T6 0.063) & FILLER INTERNAL DOUBLER (ALCLAD 7075 T6 0.071). CLEANED, TREATED AND PRIMED AREA & REPAIR PARTS IAW DC-8 SRM 51-1-8B. APPLIED SEALANT TO FAYING SURFACES IAW DC-8 SRM 51-1-11. INSTALLED REPAIR PARTS IAW SEMAN DWG ED 4117, DC-8 SRM 51-1-20D, DC-8 SRM 51-3-1 (TORQUE).
Part: VANE — DAMAGED (T/E FLAP) · airframe 71,621 hrs · 17,096 cycles
DURING INSPECT, LT WING OUTBD VANE FWD HOLES ELONGATED, XOLDO 66.000. PERFORMED MAJOR REPAIR IAW FAA FORM 8110-3 NR 05586 DATE 12-28-05, SEMAN DWG NR ED 4121 DATE 12-23-05 AND EO SEMAN NR 20051452 DATE 12-28-05. REMOVED FASTENERS IAW DC-8 SRM 51-1-21. REMOVED AREA IAW SEMAN DWG ED-4121. PERFORMED NDT INSPECT IAW DC-8 NDT IAW DC-8 NDT SPM PART 06-10-01-001. FAB`D REPAIR DOUBLER (ALCLAD 7075 T6 0.071) + FILLER (ALCLAD 7075 T6 0.063â) + INTERNAL DOUBLER (ALCLAD 7075 T6 0.063â) IAW SEMAN DWG NR ED 4121. CLEANED, TREATED AND PRIMED AREA + REPAIR PARTS INTERNAL PART IAW DC-8 SRM 51-1-8B. INSTALLED REPAIR PARTS IAW SEMAN DWG ED 4121, DC-8 SRM 51-1-21, DC-8 SRM 51-3-0, DC-8 SRM 51-1-20D AND DC-8 SRM 51-3-1 (TQ).
Part: REPAIR — IMPROPER (T/E FLAP) · airframe 71,621 hrs · 17,096 cycles
DURING INSP, RT INBD FLAP FWD UPPER SURFACE HAS NO STANDARD REPAIR (STA XW 37.000-48.000). PERFORMED MAJOR REPAIR IAW FAA FORM 8110-3 NR 05580 DATE 12-21-05, SEMAN DWG NR ED 4129 DATE 12-20-05, EO SEMAN 20051444 DATE 12-21-05. REMOVED REPAIR IAW DC-8 SRM 51-1-21, DC-8 SRM 51-1-20D. TRIMMED OUT DAMAGED AREA IAW SEMN DWG ED-4129. PERFORMED NDT INSP IAW DC-8 NDT IAW DC-8 NDT SPM PART 06-10-01-001. FAB PLATING SEGMENT (02 EA) INTERNAL SPLICE (02 EA) INTERNAL SHIMS & REPAIR DOUBLERS (04 EA) IAW SEMAN DWG ED 4129. CLEANED, TREATED AND PRIMED AREA & REPAIR PARTS IAW DC-8 SRM 51-1-8B. SEALED FAYING SURFACES IAW DC-8 SRM 51-1-11. INSTALLED REPAIR PARTS IAW SEMAN DWG ED 4129, DC-8 SRM 51-1-12, DC-8 SRM 51-1-20D, D
Part: SKIN — CORRODED (LT WING) · airframe 71,621 hrs · 17,096 cycles
DURING INSPECT, LT WING CTR L/E CORRODED, XFS 422.750. PERFORMED REPAIR IAW FAA FORM 8110-3 # 05587 DATE 12-29-05, SEMAN DWG # ED 4127 DATE 12-28-05 AND EO SEMAN # 20051458 DATE 12-29-05. REMOVED FASTENERS IAW DC-8 SRM 51-1-21. REMOVED CORROSION IAW DC-8 SRM 51-1-8 PAGES 17-18. FOUND OUT OF LIMITS IAW DC-8 SRM 57-2-1 FIG. 2G. REMOVED CORRODED AREA IAW SEMAN DWG ED 4127. PERFORMED NDT INSPECTION IAW DC-8 NDT IAW DC-8 NDT SPM PART 06-10-01-001. FAB`D REPAIR DOUBLER AND FILLER IAW SEMAN DWG # ED 4127. CLEANED, TREATED AND PRIMED AREA AND REPAIR PARTS INTERNAL PART IAW DC-8 SRM 51-1-8B. APPLIED SEALANT TO FAYING SURFACES IAW DC-8 SRM 51-1-11. INSTALLED REPAIR PARTS IAW SEMAN DWG ED 4127, DC-8 SRM 51-1-21, DC-8 SRM
Part: FITTING — CORRODED (BS 270) · airframe 71,621 hrs · 17,096 cycles
DURING ROUTINE C-CHECK INSPECTION, FWD ACCY COMPT INTERNAL PART FITTING CORRODED AT STA 270.000, L-34 (RT). REMOVED CORROSION FROM FITTING IAW DC-8 SRM 51-1-8 PAGES 17-18. FOUND OUT OF LIMITS IAW DC-8 SRM 53-2-0 PAGE 2P. REMOVED CRACKED FITTING IAW DC-8 SRM 51-1-21. CLEANED, TREATED AND PRIMED AREA IAW DC-8 SRM 51-1-8B. INSTALLED NEW FITTING IAW DC-8 SRM 51-1-21, DC-8 SRM 51-1-20D, DC-8 SRM 51-3-1 (TORQUE).
Part: FITTING — CORRODED (ZONE 600) · airframe 71,621 hrs · 17,096 cycles
DURING ROUTINE C-CHECK INSPECTION, NR 4 ENGINE - LEFT T/R RAIL FITTING CORRODED AT 12 O`CLOCK POSITION (THRUST REVERSER). REMOVED LEVEL I CORROSION FROM RAIL FITTING IAW DC-8 SRM 51-1-8 PAGES 17-18 (MATERIAL THICKNESS: 0.133, BLEND OUT: 0.003, REMAINING THICKNESS: 0.130) FOUND WITHIN ALLOWABLE LIMITS IAW CFM MM 78-31-20 PAGES 609-610. CLEANED, TREATED AND PRIMED IAW DC-8 SRM 51-1-8B.
Part: REPAIR — MISINSTALLED (WS 63.75) · airframe 71,621 hrs · 17,096 cycles
DURING ROUTINE C-CHECK INSPECTION, RIGHT WING - INBOARD L/E LWR PART HAS NON STANDARD REPAIR, XFS 63.750. PERFORMED MAJOR REPAIR IAW FAA FORM 8110-3 06006 DATED 01-05-06, SEMAN DWG ED-4133 DATED 02-06-06, ED SEMAN 2005 1470 DATED 01-05-06. REMOVED EXISTING NON STANDARD REPAIR IAW DC8 SRM 51-1-21. FABRICATED REPAIR DOUBLER (AL 7075 T6 0.071) IAW SEMAN DWG ED-4133. CLEANED, TREATED; PRIMED AREA & REPAIR DOUBLER IAW DC8 SRM 51-1-8B, APPLIED SEALANT TO FAYING SURFACES IAW DC8 SRM 51-1-11, INSTALLED REPAIR DOUBLER IAW SEMAN DWG ED-4133, DC8 SRM 51-1-21, DC8 SRM 51-1-20D, DC8 SRM 51-3-1 (TORQUE).
Part: REPAIR — MISINSTALLED (RT WING) · airframe 71,621 hrs · 17,096 cycles
DURING C-CHECK, RT WING - L/E SLOT VANE HAS NON STANDARD REPAIR, XOLDO 66. PERFORMED MAJOR REPAIR IAW FAA FORM 8110-3 05586 DATED 12-28-05, SEMAN DWG ED-4136 DATED 12-23-05, ED SEMAN 2005 1473 DATED 12-28-05. REMOVED NON STANDARD REPAIR. REMOVED DAMAGED SECTION, PERFORMED NDT INSP IAW DC8 NDT SPM PART 06-10-01-001, FABRICATED REPAIR DOUBLER (AL 7075 T6 0.071) & FILLER, INTERNAL DOUBLER (ALCLAD 7075 T6 0.063) IAW SEMAN DWG ED-4136. CLEANED, TREATED; PRIMED AREA & INNER FACE OF REPAIR PARTS IAW DC8 SRM 51-1-8B. APPLIED SEALANT TO FAYING SURFACES IAW DC8 SRM 51-1-11, INSTALLED REPAIR PARTS IAW SEMAN DWG ED-4136, DC8 SRM 51-1-21, DC8 SRM 51-1-20D, DC-8 SRM 51-3-0, DC8 SRM 51-3-1 (TORQUE).
Part: VANE — DAMAGED (RT WING LE) · airframe 71,621 hrs · 17,096 cycles
DURING C-CHECK, RT WING - L/E SLOT VANE HOLE ELONGATED, XOLDI 6.225. PERFORMED MAJOR REPAIR IAW FAA FORM 8110-3 05587 DATED 12-29-05, SEMAN DWG ED-4137 DATED 12-28-05, ED SEMAN 2005 1474 DATED 12-29-05. REMOVED FASTENERS IAW DC8 SRM 51-1-21, DC-8 SRM 51-3-0. REMOVED DAMAGED SECTION IAW SEMAN DWG ED-4137. PERFORMED NDT INSP IAW DC8 NDT SPM PART 06-10-01-001, FABRICATED REPAIR DOUBLER (AL 7075 T6 0.071) & FILLER, INTERNAL DOUBLER (ALCLAD 7075 T6 0.063) IAW SEMAN DWG ED-4137. CLEANED, TREATED; PRIMED AREA & INNER SIDE OF REPAIR PARTS IAW DC8 SRM 51-1-8B. APPLIED SEALANT TO FAYING SURFACES. INSTALLED REPAIR PARTS.
Part: REPAIR — CORRODED (RUDDER) · airframe 71,621 hrs · 17,096 cycles
DURING ROUTINE C-CHECK INSPECTION, RIGHT RUDDER REPAIR DOUBLER EDGES CORRODED, STA ZR 61.156. PERFORMED MAJOR REPAIR IAW DC-8 SRM 55-6-1 FIG 1, EO SEMAN 20051480 DATED 12-20-05. REMOVED CORROSION IAW DC8 SRM 51-1-8 PAGES 17-18. FOUND OUT OF LIMITS IAW SEMAN DC-8 SRM 55-2-0 PAGE 12. REMOVED CORRODED PLATING IAW DC-8 SRM 55-1-0, DC-8 SRM 51-1-21. FABRICATED NEW PLATING (AL 2024 T3 0.040) IAW SEMAN DC-8 SRM 5-6-1 FIG 1 ITEM -C-. CLEANED, TREATED; PRIMED AREA & REPAIR DOUBLER IAW DC8 SRM 51-1-8B. APPLIED SEALANT TO FAYING SURFACES IAW DC8 SRM 51-1-11. INSTALLED NEW PLATING IAW DC8 SRM 51-1-21. FOR REBALANCE SEE N/R 2849.
Part: FITTING — CRACKED (BS 980 L17-18R) · airframe 71,621 hrs · 17,096 cycles
DURING C CHECK, MAIN CARGO COMPT FRAME FITTING 3 CRACK, STA 980.000 L-17R TO L-18R. PERFORMED REPAIR IAW DC8 SRM 53-2-0 FIG 7. REMOVED FASTENERS IAW DC8 SRM 51-1-20D. REMOVED FRAME FITTING SEGMENT (CRACKED) IAW DC8 SRM 53-2-0 FIG 7.. FAB`D SPLICE ANGLE, FILLER 5T6 0.160) IAW DC8 SRM 53-2-0 FIG 7 (SHEET 1-2). PERFORMED HEAT TREATMENT TO SPLICE ANGLE IAW DC8 SRM 51-1-1 PAGES 1, 13, 17. PERFORMED NON DESTRUCTIVE INSPECTION REPORT IAW DC8 NDT SPM PART 08-00-02 TO 07. CLEANED, TREATED AND PRIMED AREA, REPAIR PARTS IAW DC8 SRM 51-1-8B. APPLIED SEALANT TO FAYING SURFACES IAW DC8 SRM 51-1-11. INSTALLED REPAIR PARTS IAW DC8 SRM 53-2-0 FIG 7, DC8 SRM 51-1-20D, DC8 SRM 51-3-1.
Part: VANE — DAMAGED (RT WING LE FLAP) · airframe 71,621 hrs · 17,096 cycles
DURING ROUTINE C CHECK INSPECTION, RT WING L/E SLOT VANE HOLE ELONGATED, XILD 42. PERFORMED MAJOR REPAIR IAW FAA FORM 8110-3 NR 06007 DATED 01-06-06, SEMAN DWG ED-4138 DATED 01-06-06, EO SEMAN NR 20051475 DATED 01-06-06. REMOVED EXISTING REPAIR DOUBLER IAW DC8 SRM 51-3-0, DC8 SRM 51-1-21. REMOVED DAMAGED SECTION IAW SEMAN DWG ED-4138. PERFORMED NDT INSP IAW NDT SPM PART 06-10-01-001. FABRICATED REPAIR DOUBLER (AL 7075T6 0.071), FILLER, INTERNAL DOUBLER (AL7075T6 0.063â) IAW SEMAN DWG ED-4138. CLEANED, TREATED AND PRIMED AREA , REPAIR PARTS IAW DC8 SRM 51-1-8B. INSTALLED REPAIR PARTS IAW SEMAN DWG ED-4138, DC8 SRM 51-1-21, DC8 SRM 51-3-0, DC8 SRM 51-1-20D, DC8 SRM 51-3-1 (TORQUE).
Part: SKIN — CRACKED (RT WING LE) · airframe 71,621 hrs · 17,096 cycles
DURING ROUTINE C CHECK, RT WING OTBD INNER L/E CRACKED .500 XFS 710.000. PERFORMED MAJOR REPAIR IAW FAA FORM 8110-3 NR 06007 DATED 01-06-06, SEMAN DWG ED-4139 DATED 01-04-06, EO SEMAN NR 20051476 DATED 01-06-06. REMOVED FASTENERS IAW DC8 SRM 51-1-21, DC8 SRM 51-3-0. REMOVED DAMAGED SECTION IAW SEMAN DWG ED-4139. PERFORMED NDT INSP IAW DC8 NDT SPM PART 06-10-01-001. FAB`D REPAIR DOUBLER (AL7075T6 0.063), FILLER (AL7075T6 0.050) IAW SEMAN DWG ED-4139. CLEANED, TREATED AND PRIMED AREA, REPAIR PARTS INNER SIDE IAW DC8 SRM 51-1-8B. APPLIED SEALANT TO FAYING SURFACES IAW DC8 SRM 51-1-11. INSTALLED REPAIR PARTS IAW DC8 SRM 51-1-21, SEMAN DWG ED-4139, DC8 SRM 51-3-0, DC8 SRM 51-1-20D, DC8 SRM 51-3-1.
Part: DOOR FRAME — CRACKED (FUSELAGE) · airframe 71,621 hrs · 17,096 cycles
DURING ROUTINE C-CHECK INSPECTION, MAIN CARGO DOOR FRAME FORMER CRACKED 2, STA 470.000 L-21L. PERFORMED MAJOR REPAIR IAW DC8 SRM 53-2-0 FIG 1B (SHEET 3). REMOVED FASTENERS IAW DC8 SRM 51-1-20D. PERFORMED STOP HOLE. FABRICATED ANGLE DOUBLER (7075 O 0.125) IAW DC8 SRM 53-2-0 FIG 1B (SHEET 3), DC8 SRM 51-1-4 (FORMING). HEAT TREATED FROM 7075 O TO 7075 T6 IAW DC8 SRM 51-1-1 PAGES 1, 13, 17. APPLIED SEALANT TO FAYING SURFACES IAW DC-8 SRM 51-1-11. INSTALLED ANGLE DOUBLER IAW DC8 SRM 53-2-0 FIG 1B, DC8 SRM 51-1-21, DC8 SRM 51-3-0, DC-8 SRM 51-1-20D, DC-8 SRM 51-3-1 (TORQUE).
Part: SKIN — CRACKED (ZONE 800) · airframe 71,621 hrs · 17,096 cycles
DURING ROUTINE C-CHECK INSPECTION, FWD PASSENGER DOOR LWR SKIN CRACKED 1 INCH APPROX. PERFORMED MAJOR REPAIR IAW SRM 52-2-0 FIG. 4 (SHEET 3). REMOVED FASTENERS IAW SRM 51-1-21. FABRICATED REPAIR DOUBLER (ALCLAD 7075 T6 0.050â) IAW SRM 52-2-0 FIG. 4 (SHEET 3), SRM 52-3-2 FIG. 1 ITEM L, SRM 51-9-0 FIG. 68A PAGE 10A. CLEANED, TREATED AND PRIMED AREA + REPAIR DOUBLER IAW SRM 51-1-8B. APPLIED SEALANT TO FAYING SURFACES IAW SRM 51-1-11. INSTALLED REPAIR DOUBLER IAW SRM 52-2-0 FIG. 4 (SHEET 3), SRM 51-1-21.
Part: HEAT EXCHANGER — CRACKED (ZONE 100) · airframe 71,621 hrs · 17,096 cycles
DURING ROUTINE C-CHECK INSP, RT AFT HEAT EXCHANGER LT LWR CORNER CRACKED .5 INCH APPROX. PERFORMED MAJOR REPAIR IAW NR 05580 DATE 12-21-05, DWG NR ED 4114 DATE 12-17-05, EO 20051435 DATE 12-21-05. REMOVED FASTENERS IAW SRM 51-1-21. REMOVED DAMAGED SECTION IAW DWG ED-4114. PERFORMED NDT INSPECTION IAW NDT IAW NDT SPM PART 06-10-01-001. FABRICATED REPAIR DOUBLER (ALCLAD 2024 T3 0.050â) + REPAIR TRIPLER (ALCLAD 2024 T3 0.063) + FILLER (ALCLAD 2024 T3 0.100) IAW DWG NR ED 4114. CLEANED, TREATED AND PRIMED AREA + REPAIR PARTS IAW DC-8 SRM 51-1-8B. APPLIED SEALANT TO FAYING SURFACES IAW DC-8 SRM 51-1-11. INSTALLED REPAIR PARTS IAW DWG ED 4114, SRM 51-1-21, SRM 51-1-20D AND SRM 51-3-1 (TORQUE)
Part: SKIN — DENTED (FUSELAGE) · airframe 71,621 hrs · 17,096 cycles
DURING ROUTINE C CHECK INSPECTION, EXTERNAL FUS.- LWR EXTERNAL SKIN DENTED, L-22L STA 364.000. PERFORMED MAJOR REPAIR IAW FAA FORM 8110-3 NR 05582 DATE 12-23-05, SEMAN DWG NR ED 4116 DATE 12-20-05, EO SEMAN 20051439 DATE 12-23-05. REMOVED EXISTING REPAIR DOUBLER IAW DC-8 SRM 51-1-21, PERFORMED NDT INSPECTION IAW DC-8 NDT IAW DC-8 NDT SPM PART 06-10-01-001. FABRICATED REPAIR DOUBLER (ALCLAD 7075 T6 0.080â) + (03 EA) INTERNAL FINGER DOUBLER (ALCLAD 7075 T6 0.032â) IAW SEMAN DWG # ED 4116. CLEANED, TREATED AND PRIMED AREA + REPAIR PARTS IAW DC-8 SRM 51-1-8B. APPLIED SEALANT TO FAYING SURFACES IAW DC-8 SRM 51-1-11. INSTALLED REPAIR PARTS IAW SEMAN DWG ED 4116, DC-8 SRM 51-1-12, DC-8 SRM 51-1-20D, DC-8 SRM 51-3-1.
Part: SKIN — DENTED (BS 356) · airframe 71,621 hrs · 17,096 cycles
DURING ROUTINE C-CHECK INSPECTION, EXTERNAL FUS LWR EXTERNAL SKIN DENTED L-232, STA 356.000. PERFORMED MAJOR REPAIR IAW FAA FORM 8110-3 05582 DATE 12-23-05, SEMAN DWG ED 4116 DATE 12-20-05, EO SEMAN 20051439 DATE 12-23-05. FABRICATED REPAIR DOUBLER & (03 EA) INTERNAL FINGER DOUBLER IAW SEMAN DWG ED 4116 ORIGINAL DOCUMENT CERT.
Part: SKIN — DENTED (BS 403) · airframe 71,621 hrs · 17,096 cycles
C-CHECK INSPECTION, EXTERNAL FUS LWR EXTERNAL SKIN DENTED BETWEEN L-23 & L-24L STA 403. PERFORMED MAJOR REPAIR. REMOVED FASTENERS, DAMAGED FRAME SEGMENT. FABRICATED NEW FRAME SEGMENT, (02 EA) ANGLES. HEAT TREATED FRAME SEGMENT & ANGLES. CLEANED, TREATED AND PRIMED AREA & REPAIR PARTS IAW DC-8 SRM 51-1-8B. APPLIED SEALANT TO FAYING SURFACES IAW DC-8 SRM 51-1-11 PAGE 9. INSTALLED REPAIR PARTS IAW DC-8 SRM 53-2-0 FIG 2 (SHEET 5, 6), DC-8 SRM 51-1-20D, DC-8 SRM 51-3-1 (TORQUE).
Part: FITTING — CRACKED (ZONE 800) · airframe 71,621 hrs · 17,096 cycles
DURING ROUTINE C CHECK INSPECTION, NR 2 ENGINE COWL DOOR RAIL FITTING CRACKED 1, AT STA 254.324 (RT SIDE). REMOVED FASTENERS IAW DC8 SRM 51-3-0, DC8 SRM 51-1-21, DC8 SRM 51-1-21A. PERFORMED STOP HOLE, FABRICATED DOUBLER (17-4PH STAINLESS FLAT BAR) IAW ENG SHOP MANUAL CFM 56-2 78-31-41. CLEANED REPAIR AREA AND APPLIED ALODINE 1500 IAW CFM 56 SPM 70-62-13. INSTALLED DOUBLER IAW ENG SHOP MANUAL CFM 56-2 78-31-41, DC8 SRM 51-3-0, DC8 SRM 51-1-21, DC8 SRM 51-3-1 PG 2A (TORQUE). PAINTED IAW CFM 56 SPM 70-64-16
Part: REPAIR — MISINSTALLED (LT AILERON) · airframe 71,621 hrs · 17,096 cycles
DURING C CHECK, LT INBD AIL LWR SKIN HAS NO STANDARD REPAIR (STA XA 543.000-551.000). PERFORMED MAJOR REPAIR IAW DC8 SRM 57-8-1 FIG 1. REMOVED PANEL PLATING WITH NON STANDARD REPAIR ON IT IAW DC8 SRM 57-1-0, DC8 SRM 51-1-21. FAB`D NEW PLATING (AL2024T30 0.025â), BONDED FINGER DOUBLER (AL2024T3 0.020) IAW DC8 SRM 57-8-1 FIG 1 ITEM âBâ, âKâ, DOUGLAS DWG # 5705334. BONDED BOTH REPAIR PARTS WITH HYSOL IAW DC8 SRM 51-1-9. CLEANED, TREATED AND PRIMED INNER SIDE OF NEW PANEL PLATING IAW DC8 SRM 51-1-8B. APPLYING SEALANT TO FAYING SURFACES IAW DC8 SRM 51-1-11. INSTALLED NEW PANEL PLATING IAW DC8 SRM 51-1-21.
Part: REPAIR — MISINSTALLED (ZONE 800) · airframe 71,621 hrs · 17,096 cycles
DURING ROUTINE C-CHECK INSPECTION, REPAIR ON EXT SKIN OF FWD PASSENGER DOOR HAS IMPROPER FASTENERS PERFORMED MAJOR REPAIR IAW SRM 52-2-0 FIG. 4 (SHEET 3). REMOVED EXISTING REPAIR IAW SRM 51-1-21. FABRICATED REPAIR DOUBLER (ALCLAD 7075 T6 0.050â) IAW SRM 52-2-0 FIG. 4 (SHEET 3), SRM 52-3-2 FIG. 1 ITEM L, SRM 51-9-0 FIG. 68A. CLEANED, TREATED AND PRIMED AREA AND REPAIR DOUBLER IAW SRM 51-1-8B. APPLIED SEALANT TO FAYING SURFACES IAW SRM 51-1-11. INSTALLED REPAIR DOUBLER IAW SRM 52-2-0 FIG. 4 (SHEET 3), SRM 51-1-21.
Part: SKIN — DAMAGED (LT TE FLAP) · airframe 71,621 hrs · 17,096 cycles
DURING INSPECT, LT OB FLAP UPPER SURFACE HAS NO STANDARD REPAIR, STA XF 347.000. PERFORMED MAJOR REPAIR, DWG NR ED 4118 DATE 12-20-05, EO 20051446 DATE 12-21-05. REMOVED NON STANDARD REPAIR IAW SRM 51-1-21. REMOVED DAMAGED SEGMENT IAW DWG ED-4118. PERFORMED NDT INSPECT IAW NDT IAW NDT SPM PART 06-10-01-001. FABD NEW REPAIR PLATING SEGMENT (ALCLAD 2024 T3 0.063) + INTERNAL SPLICE (ALCLAD 2024 T3 0.071â) + (02 EA) REPAIR DOUBLERS (ALCLAD 2024 T3 0.071â) IAW DWG ED 4118. CLEANED, TREATED AND PRIMED AREA + REPAIR PARTS IAW SRM 51-1-8B. APPLIED SEALANT TO FAYING SURFACES IAW SRM 51-1-11 PAGE 9. INSTALLED REPAIR PARTS IAW DWG ED 4118, SRM 51-1-20D, SRM 51-3-1 (TORQUE).
Part: SKIN — CRACKED (XF 212.000) · airframe 71,621 hrs · 17,096 cycles
DURING ROUTINE C-CHECK INSPECTION, LT OB FLAP SKIN CRACKED .5, STA XF 212.000 PERFORMED MAJOR REPAIR IAW SRM 57-2-1 FIG. 2Q, EO NR 20051445 DATED 12-15-051. REMOVED FASTENERS IAW SRM 51-1-21. REMOVED DAMAGED SECTION IAW SRM 57-2-1 FIG. 2Q. FABRICATED EXTERNAL REPAIR DOUBLER (ALCLAD 2024 T3 0.050) IAW SRM 57-2-1 FIG. 2Q, SRM 57-7-1 FIG. 4, TR NR 57-94 ITEM (C) DATED 18-01-02. CLEANED, TREATED AND PRIMED AREA + EXTERNAL REPAIR DOUBLER IAW SRM 51-1-8B. INSTALLED EXTERNAL REPAIR DOUBLER IAW SRM 57-2-1 FIG. 2Q, SRM 51-1-9 (HYSOL), SRM 51-1-21.
Part: SKIN — DAMAGED (ZONE 800) · airframe 71,621 hrs · 17,096 cycles
DURING ROUTINE C-CHECK INSP, LT FWD PASSENGER DOOR DAMAGE. SKIN AT REAR LOWER CORNER HAS BEEN DAMAGED (INCH LONG CUT), NEED TO BE REPAIRED PERFORMED REPAIR IAW AD 2000-20-08, S/B 53-075, DWG NR SR08530021, 5750776, SRM 53-2-0 FIG. 15. TR NR 53-128, 53-196 DATED 01-23-02, 03-26-04. CUT OUT DAMAGED IAW RM 53-2-0 FIG. 15 (SHEET 1) TR NR 53-128. PERFORMED NDT INSP IAW SPM PART 06-10-01-001. FAB REPAIR DOUBLER (ALCLAD 7075 T6 0.063) + REPAIR TRIPLER (ALCLAD 7075 T6 0.080) + FILLER (ALCLAD 7075 T6 0.050) IAW SRM FIG. 185 (SHEET 1), TR NR 53-128, TR NR 53-196. CLEANED, TREATED AND PRIMED AREA + REPAIR PARTS IAW SRM. APPLIED SEALANT TO FAYING SURFACES IAW SRM. INSTALLED REPAIR PARTS IAW SRM. (TORQUE)
Part: WINDSHIELD — CRACKED (COCKPIT) · airframe 71,621 hrs · 17,096 cycles
DURING C-CHECK INSPECTION, COCKPIT LT LATERAL WINDSHIELD CRACKED. PERFORMED MAJOR REPAIR IAW FAA FORM 8110-3 NR 05580. REMOVED FASTENERS IAW DC-8 SRM 51-1-21. REMOVED CORROSION IAW DC-8 RM 51-1-8 PAGES 17-18. FOUND OUT OF LIMITS IAW DC-8 SRN 57-2-0 PAGE 16. REMOVED CORRODED AREA IAW SEMAN DWG ED-4119. PERFORMED NDT INSPECTION IAW DC-8 NDT IAW DC-8 NDT SPM PART 06-10-01-001. FAB`D SOLID SEGMENT REPAIR PLATING & INTERNAL SPLICE & (02 EA) REPAIR DOUBLER IAW SEMAN DWG NR ED 4119. CLEANED, TREATED AND PRIMED AREA & REPAIR PARTS INTERNAL PART IAW DC-8 SRM 51-1-8B. APPLIED SEALANT TO FAYING SURFACES IAW DC-8 SRM 51-1-11. INSTALLED REPAIR PARTS IAW SEMAN DWG ED 4119, DC-8 SRM 51-1-2.
Part: SKIN — CORRODED (LT AILERON) · airframe 71,621 hrs · 17,096 cycles
DURING ROUTINE C-CHECK INSPECTION, DURING ROUTINE C-CHECK INSPECTION, LT IB AIL LWR SKIN CORRODED, STA 593.000. PERFORMED MAJOR REPAIR IAW SRM 52-2-0 FIG. 4 (SHEET 3). REMOVED EXISTING REPAIR IAW SRM 51-1-21. FABRICATED REPAIR DOUBLER (ALCLAD 7075 T6 0.050â) IAW SRM 52-2-0 FIG. 4 (SHEET 3), SRM 52-3-2 FIG. 1. ITEM L, SRM 51-9-0 FIG. 68A. CLEANED, TREATED AND PRIMED AREA REPAIR DOUBLER IAW SRM 51-1-8B. APPLIED SEALANT TO FAYING SURFACES IAW SRM 51-1-11. INSTALLED REPAIR DOUBLER IAW SRM 52-2-0 FIG. 4 (SHEET 3), SRM 51-1-21.
Part: SKIN — CORRODED (LT AILERONS) · airframe 71,621 hrs · 17,096 cycles
DURING C CHECK , LT OUTBD AIL LWR SKIN CORRODED, STA XA 722.000. PERFORMED REPAIR IAW FAA FORM 8110-3 NR 05580 DATE 12-21-05, SEMAN DWG NR ED 4119 DATE 12-20-05 & EO SEMAN NR 20051449 DATE 12-21-05. REMOVED FASTENERS. REMOVED CORROSION. FOUND OUT OF LIMITS IAW DC-8 SRM 57-2-0. REMOVED CORRODED AREA. PERFORMED NDT INSPECTION. FAB`D SOLID SEGMENT REPAIR PLATING, INTERNAL SPLICE, REPAIR DOUBLER9. CLEANED, TREATED AND PRIMED AREA, REPAIR PARTS INTERNAL PART. APPLIED SEALANT TO FAYING SURFACES. INSTALLED REPAIR PARTS. ALL WORK PERFORMED IAW APPLICABLE REFERENCE MATERIALS.
Part: SKIN — CORRODED (ZONE 100) · airframe 71,621 hrs · 17,096 cycles
DURING C CHECK, 2 CORRODED AREAS FOUND ON LOWER FUSELAGE NOSE SECTION AT FOLLOWING LOCATION BS 217 BETWEEN L32 & 31R, BS 223 BETWEEN L32R & 32L, DUE CHANGE. PERFORMED REPAIR IAW DC-8 SRM 53-2-1. REMOVED CORROSION IAW DC8 SRM 51-1-8, FOUND OUT OF LIMITS IAW DC8 SRM 53-2-0. REMOVED CORRODED PLATING SEGMENT. CUT OUT DAMAGED SECTION. FAB`D EXTERNAL SPLICES, INTERNAL FINGER DOUBLER, INTERNAL DOUBLER, TR NR 53-173 DATED 09-20-03. CLEANED, TREATED & PRIMED AREA, REPAIR PART. APPLIED SEALANT TO FAYING SURFACES. INSTALLED NEW PLATING SEGMENT & REPAIR PART. ALL WORK PERFORMED IAW APPLICABLE SRMS.