N853AX

Part: DOWNLOCK SWITCH — CORRODED (NLG) · airframe 56,478 hrs · 25,094 cycles

AFTER GEAR EXTENSION, NOSE GEAR GREEN LIGHT DID NOT COME ON. NO RED UNSAFE LIGHT ON. REPLACED BULBS, NO HELP. CREW PERFORMED A GO-AROUND, CYCLED GEAR. VISUALLY CHECKED NOSE GEAR DOWN AND LOCKED, MADE NORMAL LANDING. GEAR PINNED AFTER LANDING AND AIRCRAFT TAXIED TO GATE. NOSE GEAR GREEN LIGHT CAME ON AFTER BLOCK IN AT GATE. FOUND NOSE GEAR DOWNLOCK SWITCH AND CONNECTOR CORRODED AND CAUSING INDICATION PROBLEMS. REPLACED CONNECTOR IAW DC-8 MM 20-50-01-2. REPLACED SWITCH IAW DC8 MM 32-60-00. OPS CHECKED GOOD.

Part: FITTING — CRACKED (DOOR FRAME) · airframe 56,434 hrs · 25,060 cycles

NR 3 PIT, AFT LOWER CARGO COMPARTMENT AFT DOOR JAMB FITTING WAS FOUND CRACKED DURING A LINE INSPECTION. REPLACED FITTING IAW DC-8 SRM 51-1-20D.

Part: LONGERON — CRACKED (RT MLG WW) · airframe 56,218 hrs · 24,869 cycles

RT MAIN LANDING GEAR WHEEL WELL LONGERON 24 AT STA. 875 TO 900 TRIPLER SHOWED EVIDENCE OF CRACK. REPAIRED AREA IAW DC-8 SRM 51-1-20D, 53-2-2, AND REA D853-48-35MR.

Part: SKIN — CRACKED (FUSELAGE) · airframe 56,218 hrs · 24,869 cycles

AFT SERVICE DOOR JAMB UPPER AFT CORNER 3 INCHES X 8 INCHES AREA OF LIGHT SURFACE CORROSION AND A .1875 INCH CRACK AT FASTENER HOLE ON EXTERIOR FUSELAGE SKIN. REPAIRED AREA (REMOVED LIGHT SURFACE CORROSION, TRIMMED OUT CRACK, FABRICATED DOUBLERS -19, -21 AND FILLER -23, INSTALLED) IAW DC-8 SRM 51-1-8, 53-2-0, 51-1-21, 51-1-20D, AND REA D853-48038MR.

Part: STRUT — CORRODED (MLG) · airframe 56,218 hrs · 24,869 cycles

RT MAIN LANDING GEAR CYLINDER FORWARD LUG AFT SIDE HAD EVIDENCE OF CORROSION. CORROSION ON RIGHT MAIN LANDING GEAR CYLINDER WAS OUT OF LIMITS. REPLACED RIGHT GEAR WITH A SERVICEABLE ASSEMBLY. TRANSFERRED BRAKE ASSEMBLY 4 EA. IAW DC-8 MM 32-42-01. TRANSFERRED WHEEL ASSEMBLY 4 EA. IAW DC-8 MM 32-40-01. TRANSFERRED 2 EA. ANTI-SKID MANIFOLDS IAW DC-8 MM 32-43-03. TRANSFERRED GEAR STRUT DOOR IAW DC-8 MM 51-3-0. REMOVAL, INSTALL AND OPS CHECK OF THE RT MAIN LANDING GEAR WAS PERFORMED ON N/R 20892/YU892, AND IAW DC-8 MM.

Part: SKIN — CRACKED (RT WING) · airframe 56,218 hrs · 24,869 cycles

11 EACH HOLES HAD CRACK INDICATION ON RIGHT WING 505F PANEL. REMOVED -19 CLIP, FABRICATED NEW CLIP, ALODINED, PRIMED, INSTALLED IAW DC-8 SRM 51-1-8 AND DWG NR 5613609. FABRICATED EXTERNAL DOUBLER AND INNER DOUBLER IAW REA D857-48044MR, ALODINED, PRIMED AND INSTALLED IAW DC-8 SRM 51-1-8 AND REA D857-48044MR. FABRICATED 11 EACH FREEZE PLUGS AND INSTALLED IAW DC-8 SRM 51-1-25.

Part: BUSHING — CORRODED (RT MLG) · airframe 56,218 hrs · 24,869 cycles

RIGHT MAIN LANDING GEAR ATTACH FITTING (TRUNION) HAD BROWN GREASE EMITTING FROM LUGS AT FORWARD AND AFT ATTACH POINTS. REMOVED RIGHT MAIN LANDING GEAR IAW DC-8 MM 32-11-01. REMOVED AND REPLACED TRUNION BUSHINGS IAW DC-8 OHM 13-1-6 AND DAC SB 57-45, DC-8 SRM 51-1-8. REINSTALLED RIGHT MAIN LANDING GEAR IAW DC-8 MM 32-11-01, 32-32-10, 32-32-02, 32-11-03, 32-11-04, 32-43-02, AND 32-41-01. OPS CHECKED GOOD IAW DC-8 MM 32-30-0, 32-43-00, AND 32-32-02. LUBRICATED RIGHT MAIN LANDING GEAR IAW DC-8 MM 12-81-01. LEAK CHECKED GOOD IAW DC-8 MM 29-10-00-6. RIGHT MAIN LANDING GEAR STRUT SERVICE COMPLIED WITH ON JOB CARD 8761002, AND IAW DC-8 MM.

Part: BUSHING — CORRODED (LT MLG TRUNION) · airframe 56,218 hrs · 24,869 cycles

LEFT MAIN LANDING GEAR ATTACH FITTING HAD BROWN GREASE EMITTING FROM LUGS AT BOTH ATTACH POINTS. REMOVED LEFT MAIN LANDING GEAR IAW DC-8 MM 32-11-01. REMOVED AND REPLACED TRUNION BUSHINGS IAW DC-8 OHM 13-1-6 AND DAC SB 57-45 AND DC-8 SRM 51-1-8. REINSTALLED LEFT MAIN LANDING GEAR IAW DC-8 MM 32-11-01, 32-32-10, 32-32-02, 32-11-03, 32-43-02, AND 32-41-01. OPS CHECKED GOOD IAW DC-8 MM 32-30-0, 32-43-00, 32-32-02. LUBIRCATED LEFT MAIN LANDING GEAR IAW DC-8 MM 12-81-01. LEAK CHECK GOOD IAW DC-8 MM 29-10-00-6. LEFT MAIN LANDING GEAR STRUT SERVICE COMPLIED WITH ON JOB CARD 8761001.

Part: SUPPORT FITTING — CORRODED (CENTER WING) · airframe 56,218 hrs · 24,869 cycles

CORROSION ON UPPER CHORD OF CENTER WING REAR SPAR AT PRESSURE BULKHEAD F.S. 855, LEFT BUTT LINE 11 - 21. REMOVED AND INSTALLED BLOWOUT PANEL 3 EA. VERTICAL STIFFENERS, WEB ATTACH ANGLE, DOUBLER, FITTING AND SHEAR WEB ATTACH ANGLE IAW DC-8 SRM 51-30-0 AND 51-1-21. INSTALLED -3, -5, -11 FILLER, -9 AND -7 STRAP IAW DC-8 SRM 53-2-5. INSTALLED SPAR CAP ATTACH ANGLE P/N 3646326-1, 4648716-1 ANGLE WEB AT LEFT BUTT LINE 22 AND 5644011-1 ANGLE IAW DC-8 SRM 53-2-5 AND 51-1-20D.

Part: SKIN — CORRODED (LT WING) · airframe 55,976 hrs · 24,661 cycles

DURING ROUTINE MAINTENANCE, CORROSION WAS DISCOVERED ON THE LEFT WING, UPPER PLATING. REPAIRED AREA IAW REA D857-46919.

Part: POWER SUPPLY — DISCHARGED (CABIN) · airframe 55,895 hrs · 24,594 cycles

UPON MOVING AIRCRAFT, FOUND EMERGENCY POWER SUPPLY INOPERATIVE. REPLACED EMERGENCY POWER SUPPLY. OPS CHECKED GOOD IAW DC-8 AMM 24-28-00-0.

Part: BEARING — BROKEN (AILERON) · airframe 55,673 hrs · 24,423 cycles

AILERONS WERE VERY DIFFICULT TO TURN TO THE LEFT WITH HYDRAULIC POWER ON. REPLACED THE RIGHT AILERON REVERSION MECHANISM BEARING ASSEMBLY FOR TAB LOCKOUT IAW DC-8 OVERHAUL MANUAL 27-6-2. PERFORMED TEST OF REVERSION MECHANISM IAW DC-8 MM 27-11-08. NO DISCREPANCIES NOTED. OPS CHECKED GOOD. MANUAL REVERSION ROLLER BEARING WAS BROKEN IN HALF ON THE RIGHT AILERON POWER PACK.

Part: LIGHT — INOPERATIVE (COCKPIT) · airframe 55,566 hrs · 24,332 cycles

EMERGENCY EXIT LIGHT DISARM LIGHT, AMBER LIGHT WAS INOP. RELAMPED, OPS CHECKED NORMAL, REF DC-8 MM 33L.

Part: FITTING — CORRODED (FUSELAGE) · corrosion level 2 · airframe 55,359 hrs · 24,164 cycles

RIGHT MAIN LANDING GEAR WHEEL WELL, LONGERON 24 RIGHT, FITTING HAD EXFOLIATION CORROSION AT STATION 879. REMOVED CORRODED FITTING. FABRICATED REPAIR PARTS IAW DC-8 SRM 53-2-0. INSTALLED NEW FITTING AND REPAIR PARTS IAW DC-8 SRM 53-2-0.

Part: FITTING — CORRODED (FUSELAGE) · corrosion level 2 · airframe 55,359 hrs · 24,164 cycles

FORWARD CARGO, STATION 320, BETWEEN LONGERON 28 LEFT - LONGERON 29 LEFT, Z-ANGLE CORRODED. REMOVED OLD FITTING. RECEIVED NEW FITTING P/N 3155822-505N. FABRICATED REPAIR ANGLES IAW DC-8 SRM 53-2-0.

Part: FITTING — CORRODED (FUSELAGE) · corrosion level 2 · airframe 55,359 hrs · 24,164 cycles

FORWARD CARGO, STATION LONGERON 29 LEFT AND LONGERON 30 LEFT Z-ANGLE CORRODED. REMOVED CORRODED FITTING. RECEIVED NEW FITTING P/N 3755822-505N. FABRICATED REPAIR ANGLES IAW DC-8 SRM 53-2-0. INSTALLED Z-FITTING AND REPAIR ANGLES IAW DC-8 SRM 53-2-0.

Part: SPAR — CORRODED (LEFT WING) · airframe 55,359 hrs · 24,164 cycles

LEFT WING, FORWARD SPAR CAP AT XFS 520.76 HOLE HAD A CRACK INDICATION WITH HFEC DETERMINE CRACK LENGH AND LOCATION IAW ES00046. REPAIRED CRACKED HOLE IAW DAC DWG 4709980 AND DC-8 SRM 51-1-25. ALODINED AND PRIMED IAW DC-8 SRM 51-1-8.

Part: SKIN — CORRODED (RIGHT WING) · airframe 55,359 hrs · 24,164 cycles

RIGHT WING, TOP SURFACE BY STATION XRS 172, CORROSION ON SKIN. REPAIRED IAW ABX REA D857-40949-MR AND DC8 SRM 57-2-0, 51-1-26, 51-1-8 AND 51-1-20D.

Part: STRINGER — CRACKED (FUSELAGE) · airframe 55,359 hrs · 24,164 cycles

UPPER LEFT STRINGER 1 WAS CRACKED AT FS 1870, ABOVE BULKHEAD IN TAIL CONE FORWARD AREA. REPAIRED AREA IAW DC-8 SRM 51-1-21, 51-1-20, 51-1-8, 53-2-0 AND REA D853-40948MR.

Part: SPLICE — CRACKED (FUSELAGE) · airframe 55,359 hrs · 24,164 cycles

AFT CARGO, FS 1040 - 1060, LONGERON 31 RIGHT, SPLICE FITTING WAS CRACKED. RECEIVED NEW FITTING P/N 3750257-1. INSTALLED IAW DC-8 SRM 51-1-20D. REMOVED DAMAGED FITTING IAW DC-8 SRM 51-3-2.

Part: HYDRAULIC SYSTEM — LOW (MAIN) · airframe 55,242 hrs · 24,083 cycles

THE GENERAL HYDRAULIC SYSTEM NEEDED SERVICED. THE SYSTEM INDICATED ZERO DURING APPROACH AND LANDING. MAINTENANCE SERVICED THE GENERAL HYDRAULIC SYSTEM IAW DC-8 MAINTENANCE MANUAL.

Part: CONTROL VALVE — FAILED (NLG) · airframe 55,019 hrs · 23,925 cycles

THE NOSE LANDING GEAR FAILED TO RETRACT AFTER TAKEOFF FROM ILN. THE CREW COMPLETED THE ABNORMAL CHECKLIST AND RE-CYCLED THE LANDING GEAR. THE AIRCRAFT WAS INSPECTED FOR AND COMPLETED A MAINTENANCE FERRY FLIGHT FROM EWR TO ILN. ILN MAINTENANCE INSPECTED AND REPLACED THE NOSE LANDING GEAR CONTROL VALVE IAW DC-8 MM. OPS CHECKS WERE COMPLETED AND THE AIRCRAFT WAS RETURNED TO SERVICE.

Part: HANDLE — DEFECTIVE (COCKPIT DOOR)

UNABLE TO OPEN COCKPIT DOOR FROM INSIDE COCKPIT. REPAIRED COCKPIT DOOR HANDLE, OPS CHECKED GOOD.

Part: LOCK — DEFECTIVE (COCKPIT DOOR)

DURING PREFLIGHT INSPECTION, THE COCKPIT DOOR LOCK WAS INOPERATIVE. THE DOOR WOULD NOT UNLOCK WHEN CLOSED. INSTALLED NEW LATCH HANDLE AS REQUIRED, OPS CHECKED GOOD.

Part: WINDOW — LACK OF LUBE (COCKPIT)

UNABLE TO OPEN CAPTAIN'S CLEARVIEW WINDOW (EMERGENCY EXIT). LUBRICATED CAPTAIN'S CLEARVIEW WINDOW LINKAGE, OPS CHECKED GOOD.

Part: ENGINE — FAILED (NR 1)

DURING CLIMB, NR 1 ENGINE CREATED LOUD BANG. N1 AND N2 RPM DROPPED BY ONE HALF, EGT WENT TO 640 DEGREES. ENGINE ANTI-ICE WAS ON. SHUT ENGINE DOWN. FIRE BOTTLES WERE NOT USED. REPLACED NR 1 ENGINE.

Part: BEAM — CRACKED (FUSELAGE)

AT C-CHECK, CRACKS WERE FOUND IN THE J-BEAM WHICH IS ATTACHED TO THE AFT FACE OF THE AFT PRESSURE BULKHEAD. THE CRACKS ORIGINATE IN THE RADII ADJACENT TO ATTACH BOLT APPROXIMATELY ONE INCH EACH SIDE OF THE AIRCRAFT CENTERLINE. SUBMITTER STATED THE CRACKS APPEAR TO OCCUR UNDER NORMAL OPERATING CONDITIONS AND ARE POSSIBLY CAUSED BY THE COMBINED FORCES OF CABIN PRESSURE AGAINST THE FRONT FACE OF THE BULKHEAD AND TENSION FROM THE 13 FLIGHT CONTROL CABLES WHICH ARE ROUTED THROUGH PULLEYS ATTACHED TO THE J-BEAM AND RECOMMENDED THE FOLOWING: PERFORM PERIODIC INSPECTIONS OF ALL DC-8 AIRCRAFT WITH FLAT AFT PRESSURE BULKHEADS, AND, REPAIR CRACKS PER DC-8 SRM 53-2-5 FIG 26.

Part: BEAM — CRACKED (FUSELAGE)

AT C-CHECK, CRACKS WERE FOUND IN THE J-BEAM WHICH IS ATTACHED TO THE AFT FACE OF THE AFT PRESSURE BULKHEAD. THE CRACKS ORIGINATE IN THE RADII ADJACENT TO ATTACH BOLTS APPROXIMATELY ONE INCH EACH SIDE OF THE AIRCRAFT CENTERLINE. SUBMITTER STATED THE CRACKS APPEAR TO OCCUR UNDER NORMAL OPERATING CONDITIONS AND ARE POSSIBLY CAUSED BY THE COMBINED FORCES OF CABIN PRESSURE AGAINST THE FRONT FACE OF THE BULKHEAD AND TENSION FROM THE 13 FLIGHT CONTROL CABLES WHICH ARE ROUTED THROUGH PULLEYS ATTACHED TO THE J-BEAM AND SUBMITTER RECOMMENDED THE FOLLOWING: PERFORM PERIODIC INSPECTIONS OF ALL DC-8 AIRCRAFT WITH FLAT AFT PRESSURE BULKHEADS, AND, REPAIR CRACKS PER DC-8 SRM 53-2-5 FIG 26.

Part: TURBO COMP — DEFECTIVE (NR 2)

NR 2 CTC BEGAN TO HOWL ON DESCENT, ACCOMPANIED BY SMELL LIKE BURNING RUBBER. *S/D* REPLACED NR 2 CTC IAW DC8 MM 21-10-01.

Part: BULKHEAD WEB — CRACKED (FWD FUSELAGE)

RADOME BULKHEAD, RIGHT WEB HAS TWO 15 INCH CRACKS, 6 ABOVE AND BELOW FRP. REPAIRED IAW ABX REA D853-23417 MR.

Part: BULKHEAD TEE CAP — CRACKED (AFT PRESS BLKHD)

AFT PRESS BULKHEAD TEE CAP CRACKED AT LONGERON 10R. REPAIRED IAW DC8 SRM 53-2-5, 51-1-20D AND 51-3-0.

Part: FITTING — CRACKED (BS 860)

MAIN CABIN LONGERON END FITTING AT STATION 860, LONGERON 10R CRACKED. REPAIRED IAW DC8 SRM'S 51-1-24 AND 51-1-20D.

Part: FITTING — CRACKED (WS 74)

STRINGER END FITTING CRACKED AFT SIDE OF STRINGER NR 51 OUTBOARD IN NR 2 MAIN TANK AT STATION 74.000. REPAIRED IAW DC8 SRM 51-1-24 AND 51-1-20D.

Part: FITTING — CRACKED (BS 900)

MAIN CABIN, LONGERON END FITTING AT STATION 900 LONGERON 8R CRACKED. REPAIRED IAW DC8 SRM 51-3-2 AND 51-1-20D.

Part: LONGERON — CORRODED (BS 1230)

AFT LOWER CARGO COMPARTMENT STATION 1230, LONGERON 29L INSIDE TORQUE BOX, WEB CORRODED. REPAIRED IAW ABX REA D853-23409MR REV-A,

Part: FITTING — CRACKED (WS 74)

CRACK IN LOWER NR 2 MAIN TANK JUST INBOARD OF XRS 74 STRINGER NR 51 ON FWD AND AFT SIDE OF SPLICE. REPAIRED TWO CRACKED FITTINGS IAW DC8 SRM'S 51-1-24, 51-1-8, AND 51-1-20D.

Part: TRUNNION — CORRODED (RT MLG)

RIGHT HAND MAIN LANDING GEAR TRUNNION CORRODED. FABRICATED BUSHINGS PER AD 71-25-09 AND ABX REA D832-23410MR.

Part: LONGERON — CRACKED (BS 1790)

LONGERON 2R CRACKED AT STATION 1790 CANTED BULKHEAD. REPAIRED IAW ABX REA D853-23411MR.

Part: FLANGE — CRACKED (AFT PRESS BLKHD)

AFT PRESSURE BULKHEAD AFT SIDE HORIZONTAL BEAM HAS 3 CRACK ON LOWER FLANGE AT AIRCRAFT CENTERLINE. REPAIRED IAW ABX REA D853-23407MR.

Part: BEAM — CRACKED (AFT PRESS BLKHD)

AFT PRESSURE BULKHEAD AFT SIDE, HORIZONTAL BEAM HAS 3.5 CRACK ON LOWER FLANGE AND 1 CRACK ON UPPER FLANGE AT AIRCRAFT CENTERLINE, 24 ABOVE FRP. REPAIRED PER ABX REA D853-23406MR.

Part: FRAME — CORRODED (BS 80)

FORWARD LOWER CARGO CIRCUMFERENTIAL FRAME CORRODED AT STATION 80, LONGERON 29R. REPAIRED IAW DC8 SRM 55-2-2 AND 51-1-9A.

Part: SWITCH — DEFECTIVE (NR 1 ENGINE)

NR 1 ENGINE LOW OIL PRESSURE LIGHT ILLUMINATED ON CLIMBOUT. OIL QUANTITY, TEMPERATURE AND PRESSURE WERE NORMAL. PERFORMED ABNORMAL PROCEDURE. LIGHT REMAINED ON. PRECAUTIONARY ENGINE SHUTDOWN. REPLACED NR 1 ENGINE LOW OIL PRESSURE SWITCH. OPS CHECKED NORMAL IAW DC8 MM 79-32-2.

Part: RETRACT MECH — OUT OF ADJUST (LANDING GEAR)

AFTER TAKEOFF AND GEAR RETRACTION, VIBRATION COULD BE FELT AND HEARD FROM NOSE GEAR AREA. ALL INDICATIONS WERE GOOD. RECYCLED GEAR THREE TIMES, ON THIRD TIME, VIBRATION CEASED. REPLACED DOOR BUMPERS, AND PERFORMED ADJUST/TEST IAW DC8 MM 32-20-00, NO DEFECTS NOTED.

Part: VANE — CRACKED (RT TE FLAP)

DURING C-CHECK, FOUND RIGHT WING UPPER MOVEABLE FLAP VANE CRACKED. REPLACED RT FLAP FWD MOVEABLE VANE IAW DC9 MM 27-51-2.

Part: CONTROL CABLE — DEFECTIVE (RT MLG DOOR)

ON CLIMBOUT WITH GEAR HANDLE UP GEAR UNSAFE AND LEFT DOOR NOT LATCHED LIGHTS ILLUMINATED. RECYCLED GEAR TWICE, LIGHTS REMAINED ON. IN CRUISE LEFT DOOR AND LEFT AND RIGHT GEAR NOT LATCHED LIGHTS CAME ON. REPLACED CABLE RUN 112C, RIGHT MLG DOOR LATCH AND ROLLERS. PERFORMED OPERATIONAL CHECK IN ACCORDANCE WITH DC8 MM.

Part: SPRING — OUT OF ADJUST (RT WINDOW)

FIRST OFFICER'S WINDOW WOULD NOT OPEN. REPOSITIONED WINDOW LATCH SPRING. FIRST OFFICER'S WINDOW OPS CHECKED GOOD IAW DC-8 M.M. 56-40.

Part: WINDOW — OUT OF ADJUST (RT COCKPIT)

DURING PREFLIGHT, WAS UNABLE TO OPEN FIRST OFFICER'S CLEARVIEW WINDOW. CLEANED AND LUBRICATED WINDOW AND SEAL. ADJUSTED LOWER AFT HOOK FITTING PER DC-8 MM 56-10-3. OPS CHECKED GOOD.

Part: FITTING — LOOSE (NR 3 PYLON)

WHEN GEAR HANDLE WAS PLACED UP AFTER TAKEOFF, THE AILERON CONTROL MANUAL LIGHT ILLUMINATED ACCOMPANIED BY PRESSURE LOSS. QUANTITY REMAINED AT FULL. PERFORMED GEAR SWING WITH EXTERNAL HYDRAULIC SOURCE AND AILERON POWER ON. FOUND HYDRAULIC LEAK AT NR 3 PYLON AT STOW LATCH VALVE. SECURED FITTING, BLED AIR FROM SYSTEM PER MAINT. TIP. PERFORMED GEAR SWING IAW DC-8 M.M. OPS CHECKED GOOD.

Part: LOCK BAR — OUT OF ADJUST (RT COCKPIT)

FIRST OFFICER'S SLIDING WINDOW/EMERGENCY EXIT WOULD NOT OPEN. ADJUSTED UPPER LOCK BAR IAW DC-8 MM, OPS CHECKED GOOD.

Part: GEAR INDICATION — MALFUNCTIONED (NLG)

ON FINAL WHEN GEAR HANDLE PUT IN DOWN POSITION, NO NOSE GEAR GREEN LIGHT, HAD GEAR UNSAFE LIGHT. RECYCLED GEAR, GOT NORMAL INDICATION. PERFORMED ADJUSTMENT TEST OF NOSE LANDING GEAR SYSTEM IAW DC-8 MM 32-31-0. OPERATIONAL CHECK OF INDICATION AND MECHANICAL SYSTEMS CHECKED NORMAL ON SEVERAL GEAR SWINGS.

Part: GEAR INDICATION — MALFUNCTIONED (NLG)

ON FIRST GEAR EXTENSION ATTEMPT, NOSE GEAR GREEN LIGHT WOULD NOT COME ON. RECYCLED GEAR, HAD A GOOD INDICATION ON SECOND TRY. AIRCRAFT JACKED AND GEAR SWING COMPLIED WITH, NO DEFECTS NOTED IAW DC-8 MM 32-60-0.

Part: TRAPEZOIDAL FTG — CRACKED (LEFT)

FOUND CRACK 1.46 INCHES IN LENGTH ON THE FORWARD END OF TRAPEZOIDAL FITTING, LEFT SIDE. REMOVED TRAPEZOIDAL FITTING, CLEANED AREA AND ANTI-CORROSION TREATED IAW SRM 51-1-8. INSTALLED NEW TRAPEZOIDAL FITTING.