N17543
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, 1996-04-10 – 1998-04-14.
Part: BEAM — CRACKED (R-1 DOOR)
INSPECTION FOUND A 4 CRACK IN R-1 DOOR INTERIOR FORWARD NR 2 BEAM. THE CRACK WAS STOP DRILLED IAW SRM 52-05, FIGURE 25. A J-ANGLE, FITTING, AND SHIMS WERE FABRICATED AND INSTALLED IAW SRM 52-05, FIGURE 25 AND 51-10-3.
Part: COALESCER BAGS — DIRTY (CABIN)
SMOKE APPEARED IN THE CABIN AND COCKPIT AFTER TAKEOFF WITH THE ENGINE AND AIRFOIL ANTI-ICE ON. ALSO, THE RT AIR CONDITIONING SUPPLY TEMP HIGH LIGHT ILLUMINATED. THE AIRFOIL ANTI-ICE WAS TURNED OFF AND THE SMOKE DISSIPATED. THE AIRCRAFT WAS RETURNED TO CLE WHERE IT LANDED WITHOUT INCIDENT. MAINTENANCE FOUND COALESCER BAGS WITH OILY SUBSTANCE, WATER, AND DIRT PRESENT. THE COALESCER BAGS WERE REPLACED. THE ENGINES WERE RUN WITH PACKS AND ANTI-ICE SYSTEMS ON AND NO SMOKE WAS PRESENT.
Earlier reports · 1996–1997 · 15 reports
1997
Part: BRAKE ROTOR — BROKEN (LT MLG)
THE LT MLG BRAKE BEGAN TO DRAG DURING TAXI TO GATE IN TUL. THE FUSE PLUG BLEW AND THE LEFT TIRE (LEFT OUTBOARD MAIN) DEFLATED. MAINTENANCE FOUND THE LEFT BRAKE HAD FAILED AND THE LEFT AXLE OVERHEATED. THE LT MLG SHOCK STRUT PISTON WAS REMOVED AND REPLACED IAW MM 32-11-2, PAGE 401-405. THE NR 1 AND NR 2 BRAKE ASSEMBLIES WERE REMOVED AND REPLACED. IN ADDITION, THE NR 1 AND NR 2 ANTI-SKID TRANSDUCERS AND NR 1 AND NR 2 MAIN TIRE AND WHEEL ASSEMBLIES WERE REMOVED AND REPLACED. TEARDOWN REVEALED THAT A BRAKE ROTOR HAD BROKEN IN HALF DUE TO THERMAL CYCLIC FATIGUE AND HEAVY SHRINKAGE WAS FOUND IN THE OTHER ROTORS AND STATORS.
Part: DUCT — RUPTURED (NR 1 ENGINE)
THE NR 1 ENG POWER LEVER WAS DIFFICULT TO RETARD AFTER TAKEOFF FROM CLE. THE NR 1 ENG FIRE WARNING ACTIVATED 30 SECONDS AFTER SETTING CLIMB POWER. THE FIRE WARNING CEASED AFTER ENG POWER WAS REDUCED TO IDLE. THE A/C WAS RETURNED TO CLE WHERE IT LANDED WITHOUT INCIDENT. MAINTENANCE FOUND SUPPLY DUCT TO NR 1 ENG NOSE COWL ANTI-ICE VALVE RUPTURED. THE ANTI-ICE DUCT WAS REPLACED AND LEAK CHECKS WERE GOOD. IN ADDITION, THE NR 1 ENG POWER LEVER WAS LUBRICATED.
Part: ANGLE — CRACKED (BS 756)
INSPECTION FOUND LT SIDE STA 756 FAIRING ATTACH SUPPORT ANGLE CRACKED IN TWO PLACES. THE CRACKS WERE .25 AND 3 INCH LENGTH. THE SUPPORT ANGLE WAS REMOVED AND REPLACED IAW SRM 53-52-0, 51-30-2, AND 53-01, FIGURE 2.
Part: SPLICE — CORRODED (BS 965)
INSPECTION FOUND STRINGER SPLICE PLATE CORRODED IN AFT PIT AT FS 965, STRINGER 29R. A REPAIR SPLICE WAS FABRICATED AND INSTALLED IAW SRM 51-10-2, 51-10-3, AND 51-30-4.
Part: CHANNEL — CORRODED (BS 200)
INSPECTION FOUND J-CHANNELS CORRODED AT STA 200, BL 0 TO RBL 20 AND RBL 24 TO 43 THE CHANNELS WERE REMOVED. NEW, CHANNELS WERE FABRICATED INSTALLED IAW SRM 51-30-2 AND 53-11-1.
Part: CHANNEL — CORRODED (BS 160-237)
INSPECTION FOUND J-CHANNELS CORRODED AT STA 160 TO 237, BL 0 AND STA 160, BL 0 TO LBL 60. THE CHANNELS WERE REMOVED, NEW CHANNELS WERE FABRICATED AND INSTALLED IAW SRM 53-11-1 AND 51-30-2.
Part: BRACKET — CRACKED (NR 2 PYLON)
INSPECTION FOUND A 1 INCH CRACK IN SUPPORT BRACKET OF NR 2 ENGINE PYLON LEADING EDGE. A NEW BRACKET WAS FABRICATED AND INSTALLED IAW SRM 54-04, 51-30-2, AND ECRA 5410-01169.
Part: SUBFLOOR — CORRODED (BS 852)
INSPECTION FOUND SUBFLOOR CORRODED AT STA 852, LBL 44. THE CORRODED AREA WAS REMOVED AND A REPAIR WEB WAS INSTALLED IAW SRM 53-01.
Part: INTERCOSTAL — CORRODED (BS 699-718)
INSPECTION FOUND INTERCOSTAL CORRODED BETWEEN STA 699 AND 718 AT LONGERON 16L. THE INTERCOSTAL WAS REMOVED AND A NEW INTERCOSTAL WAS FABRICATED AND INSTALLED IAW SRM 53-11-3 AND 51-30-2.
Part: FILLET — CRACKED (LT WING)
INSPECTION FOUND A 1 INCH CRACK IN LT WING FILLET PANEL. A REPAIR WAS FABRICATED AND INSTALLED IAW SRM 53-51-0.
Part: SUBFLOOR — CORRODED (BS 237)
INSPECTION FOUND SUBFLOOR CORRODED AT FS 237, LBL 20 TO 44. THE CORRODED AREA WAS REMOVED, A REPAIR WAS FABRICATED AND INSTALLED IAW SRM 53-11-2 AND 53-01, FIGURE 2.
Part: DOUBLER — CORRODED (BS 897)
INSPECTION FOUND DOUBLER CORRODED AT STA 897. THE DOUBLER WAS REMOVED AND A REPLACEMENT WAS FABRICATED AND INSTALLED IAW SRM 53-11-3 AND 51-30-2.
1996
Part: STRUT — FLAT (NLG)
GSO - FLT 1147 - THE LANDING GEAR WOULD NOT RETRACT AFTER TAKEOFF FROM GSO. 'ABNORMAL' PROCEDURES WERE C/W, BUT, THE GEAR HANDLE WOULD ONLY GO TO THE UPLATCH POSITION AND THE AIRCRAFT WOULD NOT PRESSURIZE. THE AIRCRAFT WAS RETURNED TO GSO WHERE IT LANDED WITHOUT INCIDENT. MAINTENANCE FOUND THE NLG STRUT ALMOST FLAT. THE NOSE STRUT WAS FULLY SERVICED PER MM 32-21-2 AND THE SCHRADER VALVE WAS REPLACED. A NOSE GEAR RETRACTION WAS PERFORMED AND OPERATION CHECKED GOOD. (X)
Part: TAB — DELAMINATED (RUDDER)
GSO - INSPECTION FOUND A 2 SQUARE INCH AREA OF RUDDER TAB LEADING EDGE DELAMINATED. THE AREA WAS REPAIRED USING BONDED DOUBLER AND FILLER. A WEIGHT AND BALANCE CHECK OF TAB WAS PERFORMED AFTER REPAIR. (X)
Part: SKIN — CRACKED (VERT STAB)
GSO - INSPECTION FOUND A 4 INCH BY 2 INCH HOLE AND SEVERAL CRACKS TOTALING 12 INCHES IN LENGTH IN SKIN PANEL ABOVE RUDDER ON RIGHT SIDE OF VERTICAL STABILIZER. THE DAMAGED SKIN WAS CUT OUT. A FILLER AND DOUBLER REPAIR WAS FABRICATED AND INSTALLED IAW SRM 55-01 AND SRM 51-30-8. (X)