N51CX
Registered owner: AERODATA LLC, MI (owner ≠ operator)
Operators of this aircraft
Who operated this tail, and how firmly we know it.
No operator established for this aircraft.
Accident & incident history
No NTSB accidents or incidents on file for this aircraft.
Maintenance disclosures
Service Difficulty Reports filed with the FAA for this airframe. Filing is largely voluntary — the number of reports is not a measure of reliability. To verify a report, search its control number at the FAA SDRS site.
17 reports on file, 1996-01-03 – 1997-02-26.
Part: SKIN — CRACKED (RT ELEVATOR)
DURING ROUTINE C-CHECK INSPECTION, THE RIGHT ELEVATOR LOWER SKIN PANEL WAS FOUND TO BE CRACKED AT STATION XE32. REPAIR WAS ACCOMPLISHED BY REMOVAL OF DAMAGED AREA, FABRICATION AND INSTALLATION OF A NEW SKIN PANEL IN ACCORDANCE WITH FAA DER APPROVED DRAWING C05-R14 AND ENGINEERING ORDER 27-DC8-489. ELEVATOR WAS BALANCED IN ACCORDANCE WITH DOUGLAS DC8 SRM 51-4-1.
Part: ACTUATOR — CORRODED (LT MLG)
DURING ROUTINE C-CHECK INSPECTION, THE LEFT MAIN LANDING GEAR RETRACT ACTUATOR PIN BOSS HOLE WAS FOUND TO BE CORRODED. REPAIR WAS ACCOMPLISHED BY OVERSIZING THE BOSS HOLE, FABRICATION AND INSTALLATION OF A OVERSIZE BUSHING IN ACCORDANCE WITH DOUGLAS FAX FILE RKM01862, ACTION 323980 AND ENGINEERING ORDER 32-DC8-485.
Part: ANGLE — CORRODED (BS 1593-1604)
DURING ROUTINE C-CHECK INSPECTION, CORROSION WAS FOUND ON THE RIGHT HAND VERTICAL STABILIZER BASE ATTACH ANGLE AT FUSELAGE STATION 1593 TO 1604. REPAIR WAS ACCOMPLISHED BY CORROSION REMOVAL, FABRICATION AND INSTALLATION OF A REPAIR ANGLE IN ACCORDANCE WITH FAA DER APPROVED DRAWING C05-R13 REV C AND ENGINEERING ORDER 55-DC8-488.
Part: WEB — CORRODED (BS 200)
DURING ROUTINE C-CHECK INSPECTION, CORROSION AND A CRACK WERE FOUND ON THE WEB STRUCTURE FOR ACCESS PANEL 603R AT STATION 200. REPAIR ACCOMPLISHED REMOVAL OF DAMAGED AREA, FABRICATION AND INSTALLATION OF A FILLER AND A REPAIR DOUBLER IN ACCORDANCE WITH FAA DER APPROVED DRAWING C05-R07 AND ENGINEERING ORDER 53-DC8-477.
Part: JAMB — CRACKED (CARGO DOOR)
DURING ROUTINE C-CHECK INSPECTION, THE LOWER AFT, FORWARD CARGO DOOR JAMB WEB WAS FOUND TO BE CRACKED AT FUSELAGE STATION 1160, BETWEEN LONGERONS 30 AND 31 RIGHT. REPAIR WAS ACCOMPLISHED BY STOP DRILLING THE CRACK, FABRICATION AND INSTALLATION OF A REPAIR DOUBLER IN ACCORDANCE WITH FAA DER APPROVED DRAWING C05-R12 AND ENGINEERING ORDER 52-DC8-487.
Part: PLATING — CORRODED (WS 393)
DURING ROUTINE C-CHECK INSPECTION, THE RIGHT WING, UPPER SURFACE EXTERNAL PLATING WAS FOUND WITH A CORROSION BULGE AT STATION XFS393, STRINGER 7. REPAIR WAS ACCOMPLISHED BY REMOVAL OF CORROSION PER DC-8 SRM 57-2-1 FIG 32, SHEET 2, FABRICATION AND INSTALLATION OF A FILLER AND REPAIR DOUBLER IN ACCORDANCE WITH DOUGLAS FAX FILE 97-02-12-003/RRR00036 AND ENGINEERING ORDER 53-DC8-481.
Part: PLATING — CORRODED (RT TE FLAP)
DURING ROUTINE C-CHECK INSPECTION, THE RIGHT WING OUTBOARD SLOT UPPER LEADING EDGE PLATING WAS FOUND TO BE CORRODED AT STATION XOLDI 6.224. REPAIR WAS ACCOMPLISHED BY REMOVAL OF THE DAMAGED AREA, FABRICATION AND INSTALLATION OF INTERNAL FILLER AND AN EXTERNAL REPAIR DOUBLER IN ACCORDANCE WITH FAA DER APPROVED DRAWING C05-R04 AND ENGINEERING ORDER 27-DC8-474.
Part: SKIN — CORRODED (BS 1573.5)
DURING ROUTINE C-CHECK INSPECTION, CORROSION WAS FOUND ON THE FUSELAGE EXTERNAL PLATING AT STATION 1573.5, AND LONGERON 28 RIGHT, JUST AFT OF THE EXISTING DRAIN MAST. REPAIR ACCOMPLISHED REMOVAL OF DAMAGED AREA, FABRICATION AND INSTALLATION OF A FILLER AND REPAIR DOUBLER IN ACCORDANCE WITH FAA DER APPROVED DRAWING C05-R10 AND ENGINEERING ORDER 53-DC8-483.
Part: PLATING — CORRODED (BS 1757)
DURING ROUTINE C-CHECK INSPECTION, THREE SHEARED RIVETS AND CORROSION WERE FOUND ON THE EXTERIOR PLATING AT FUSELAGE STATION 1757 RIGHT. REPAIR WAS ACCOMPLISHED BY REMOVAL OF DAMAGED AREA, FABRICATION AND INSTALLATION OF AN INTERNAL FILLER AND EXTERNAL REPAIR DOUBLER IN ACCORDANCE WITH FAA DER APPROVED DRAWING C05-R09 AND ENGINEERING ORDER 53-DC8-479.
Part: AILERON — CRACKED (RT WING)
DURING ROUTINE C-CHECK INSPECTION, THE RIGHT INBOARD AILERON UPPER LEADING EDGE PLATING WAS FOUND TO BE CRACKED AT STATION XA490. REPAIR WAS ACCOMPLISHED BY REMOVAL OF DAMAGED AREA, FABRICATION AND INSTALLATION OF NEW PLATING SECTION IN ACCORDANCE WITH FAA DER APPROVED DRAWING C05-R03 AND ENGINEERING ORDER 27-DC8-473.
Part: SKIN — CORRODED (RT ELEVATOR)
DURING ROUTINE C-CHECK INSPECTION, THE RIGHT ELEVATOR TRAILING EDGE EXTERNAL PLATING WAS FOUND TO BE BULGING AT STATION XE122. REPAIR WAS ACCOMPLISHED BY REMOVAL OF THE DAMAGED AREA, FABRICATION AND INSTALLATION OF A NEW SECTION OF PLATING IN ACCORDANCE WITH DOUGLAS DRAWING SRO8550002, SRM 51-1-21, AND SRM 51-4-4.
Part: AILERON — CORRODED (RT WING)
DURING ROUTINE C-CHECK INSPECTION, THE RIGHT OUTBOARD AILERON LOWER EXTERNAL PLATING WAS FOUND TO HAVE SURFACE CORROSION AND BULGING AT STATION XA615 TO XA642. REPAIR WAS ACCOMPLISHED BY REMOVAL OF THE DAMAGED AREA, FABRICATION AND INSTALLATION OF NEW SECTION OF PLATING IN ACCORDNCE WITH FAA DER APPROVED DRAWING SK97103 AND ENGINEERING ORDER 27-DC8-480. AILERON BALANCED IN ACCORDANCE WITH DOUGLAS SRM 51-4-3.
Earlier reports · 1996 · 5 reports
1996
Part: CLAMP — BROKEN (NR 4 ENG)
INVESTIGATION OF THIS EVENT FOUND AN ENGINE ANTI-ICE DUCT CLAMP BOLT HAD FAILED ALLOWING BLEED AIR TO ENTER THE ENGINE COWLING. THE HOT AIR DAMAGED THE ENGINE WIRING HARNESS WHICH CAUSED SEVERAL ENGINE INDICATION SYSTEM MALFUNCTIONS. INSPECTION OF THE REMAINING CLAMP FOUND A CRACKED FLANGE. OVERTORQUE OF THE BOLT AND CLAMP ARE SUSPECTED TO BE THE FAILURE MODE OF THIS ASSEMBLY. THE CLAMP ASSY, ANTI-ICE DUCT, WIRING HARNESS AND SEVERAL ASSOCIATED COMPONENTS WERE REPLACED AND THE AIRCRAFT WAS RETURNED TO SERVICE. (M)
Part: CONTROL AMP — INTERMITTENT (COCKPIT)
EN ROUTE BETWEEN ELP AND TOL IN CRUISE FLIGHT AT FL 37, THE MAIN CARGO COMPARTMENT SMOKE DETECTOR LIGHT ILLUMINATED. ATC WAS ADVISED, AND THE AIRCRAFT DIVERTED TO OKC. ON THE GROUND IN OKC, AND AIRCRAFT WAS CHECKED FOR SIGNS OF FIRE, SMOKE, OR ODORS OF COMBUSITON. NONE WERE FOUND IN THE MAIN CARGO COMPARTMENT OR THE BELLY COMPARTMENTS. TROUBLESHOOTING OF THE SMOKE DETECTOR SYSTEM REVEALED A SMOKE DETECTOR CONTROL AMPLIFIER WHICH INTERMITTENTLY PRODUCES A FALSE WARNING LIGHT ON THE GROUND. THE AMPLIFIER WAS REPLACED, AND THE AIRCRAFT RETURNED TO SERVICE. (M)
Part: SMOKE DETECTOR — MALFUNCTIONED (NR 4 CARGO COMPT)
EN ROUTE BETWEEN ELP AND TOL IN CRUISE FLT AT FL 37, THE MAIN CARGO SMOKE DETECTOR LIGHT ILLUMINATED, FOLLOWED BY AN ACRID SMELL. THE FE DONNED A PBE AND ENTERED THE MAIN CARGO COMPARTMENT, BUT SAW NO VISIBLE SMOKE. THE A/C DIVERTED TO OKC, DETAILED INSPECTIONS ACCOMPLISHED. THE SMOKE DETECTOR SYSTEM WAS SMOKE TESTED AND FOUND OPERATIONAL. NO ACRID SMELL COULD BE DETECTED. DURING CARGO OFF LOAD, IT WAS NOTED THAT A RESIDUAL ACRID SMELL WAS PRESENT IN THE NR 4 BELLY CARGO COMPARTMENT. WHEN THAT CARGO WAS TRANSFERRED TO A CONTAINER, THE RESIDUAL ACRID SMELL FOLLOWED. AN INSPECTION OF THAT CARGO REVEALED NO VISIBLE SIGN OF COMBUSTION. REFERENCE IXXA9682. (M)
Part: FUEL PUMP — LEAKING (NR 4 ENGINE)
ON DESCENT INTO SJU, THE NR 4 ENGINE WAS PRECAUTIONARILY SHUT DOWN DUE TO LOW OIL QUANTITY. ON THE GROUND IN SJU, MAINTENANCE DETERMINED THAT THE ENGINE FUEL PUMP GEARBOX DRIVE SEAL WAS LEAKING INTO ITS SPLINE CAVITY. THE DRIVE WAS RESEALED, AND THE ENGINE LEAK CHECKED OK. THE AIRCRAFT WAS RETURNED TO SERVICE. (M)
Part: GRND SHIFT MECH — OUT OF RIG (NLG)
ON DEPARTURE OUT OF EWR, THE LANDING GEAR HANDLE WOULD NOT MOVE TO THE 'RETRACT' POSITION. THE AIRCRAFT APPEARED TO BE STUCK IN THE 'GROUND' MODE. THE AIRCRAFT RETURNED TO EWR FOR MAINTENANCE. THE AIRCRAFT WAS FERRIED TO A MAINTENANCE FACILITY WHERE THE NOSE LANDING GEAR WAS DISASSEMBLED, INSPECTED, AND RESEALED, AND THE GROUND SHIFT MECHANISM WAS RIGGED. THE LANDING GEAR WAS OPERATIONALLY CHECKED AND DETERMINED TO BE OPERATING NORMALLY FOLLOWING THE RE-RIG. THE AIRCRAFT WAS RETURNED TO SERVICE. (M)