N541NY
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.
26 reports on file, 1995-06-06 – 1997-08-08.
Part: LONGERON — CORRODED (BS 1076)
INSPECTION FOUND LONGERON 25L CORRODED ON HORIZONTAL FLANGE AT STA 1076. THE CORROSION WAS REMOVED AND A REPAIR WAS INSTALLED IAW ECRA 5314-01001.
Part: ANGLE — CRACKED (RT MLG WW)
INSPECTION FOUND A 2 INCH CRACK IN ANGLE AT RT WHEEL WELL FORWARD OUTBOARD DOOR JAMB. THE CRACKED AREA WAS CUT OUT, DOUBLERS WERE FABRICATED AND INSTALLED IAW SRM 51-70-12, FIGURE 1.
Part: SUPPORT — CRACKED (BS 540)
INSPECTION FOUND A 1.25 INCH CRACK IN FLOOR SUPPORT AT STA 540, CENTERLINE. A DOUBLER WAS INSTALLED IAW SRM 51-70-12.
Part: FRAME — CORRODED (BS 847)
INSPECTION FOUND CENTER FLOOR RIGHT SUPPORT FRAME CORRODED AT STA 847, JUST AFT OF AFT BAGGAGE BIN DOOR. THE SUPPORT FRAME WAS REPLACED IAW SRM 51-10-02.
Part: SKIN — CRACKED (RUDDER)
INSPECTION FOUND THREE .5 INCH CRACKS IN RUDDER ON LT SIDE AT TOP. A DOUBLER WAS INSTALLED IAW SRM 55-01, FIGURE 2.
Part: LONGERON — CRACKED (BS 737)
INSPECTION FOUND TWO .5 INCH CRACKS IN LONGERON 5L AT STA 737. A NEW LONGERON SPLICE WAS INSTALLED IAW SRM 53-02, FIGURE 18 AND SRM 51-30-0.
Part: LONGERON — CRACKED (BS 680)
INSPECTION FOUND A .5 INCH CRACK IN LONGERON 5L AT STA 680. A NEW LONGERON SPLICE WAS INSTALLED IAW SRM 53-02, FIGURE 18 AND SRM 51-30-0.
Part: LONGERON — CRACKED (BS 148)
INSPECTION FOUND A .75 INCH CRACK IN LONGERON 4L AT STA 148. A SPLICE WAS FABRICATED AND INSTALLED IAW SRM 53-02, FIGURE 18.
Part: FRAME — CRACKED (BS 446)
INSPECTION FOUND TWO 1 INCH CRACKS IN BELTFRAME AT STA 446, LONGERON 5L. THE CRACKED AREA WAS REMOVED, A REPAIR ANGLE, FILLER, AND DOUBLER WERE INSTALLED IAW SRM 53-03, FIGURE 4.
Part: BULKHEAD T-CAP — CORRODED (FWD PRESS BLKHD)
INSPECTION FOUND FORWARD PRESSURE BULKHEAD T-CAP CORRODED JUST AFT OF EXT POWER BOX. THE CORRODED SECTION OF T-CAP WAS REMOVED AND REPLACED IAW ECRA 5310-03544.
Part: SKIN — CRACKED (LT MLG DOOR)
INSPECTION FOUND A 2.25 INCH CRACK AT AFT OUTBOARD CORNER AND A 2.125 CRACK AT FORWARD INBOARD CORNER OF LT MLG INBOARD DOOR. REPAIRED IAW SRM 52-05.
Part: DOUBLER — CRACKED (PAX DOOR)
INSPECTION FOUND A .25 INCH CRACK IN MAIN CABIN DOOR DOUBLER ABOVE BOTTOM DOOR HINGE. REPAIRED IAW SRM 52-01.
Part: SKIN — CRACKED (NLG DOORWAY)
INSPECTION FOUND BOTH THE LEFT AND RIGHT NOSE WHEEL WELL AFT DOOR AFT HINGE CUTOUT REPAIR DOUBLERS CRACKED. THE CRACKS WERE .25 AND .1875 INCH LENGTH, RESPECTIVELY. REPAIR WAS INSTALLED IAW SRM 51-10-0.
Part: WEB — CRACKED (CARGO DOOR)
INSPECTION FOUND A 2 INCH CRACK IN FORWARD CARGO DOOR WEB INSIDE DOOR AT LOWER FORWARD DOOR STOP AREA. A NEW WEB WAS INSTALLED IAW SRM 51-10-2.
Part: PAN — CRACKED (CARGO DOOR)
INSPECTION FOUND A 3.5 INCH CRACK IN FORWARD CARGO DOOR PAN. A DOUBLER WAS INSTALLED IAW ECRA 5231-01000.
Part: SKIN — CRACKED (CARGO DOOR)
INSPECTION FOUND A .25 INCH CRACK IN FORWARD CARGO DOOR OUTER SKIN ON AFT EDGE SIXTEEN INCHES UP FROM BOTTOM. REPAIRED IAW SRM 52-01, FIGURE 2.
Part: BRACKET — CRACKED (LT/RT WING)
INSPECTION FOUND A .5 INCH CRACK IN LT AND RT WING NR 4 FLAP HINGE BRACKETS. THE BRACKETS WERE REMOVED AND REPLACED IAW SRM 51-30-0.
Part: ANGLE — CORRODED (BS 110)
INSPECTION FOUND ANGLE CORRODED AT STA 110 NEAR RT NLG BOX SIDEWALL. THE CORRODED SECTION WAS REMOVED AND REPLACED IAW ECRA 5310-03544.
Part: LONGERON — CRACKED (BS 965)
INSPECTION FOUND A .5 INCH CRACK IN LONGERON 16L AND A .5 INCH CRACK IN LONGERON 13R AT STA 965. THE CRACKED AREAS WERE REMOVED AND REPAIRS WERE INSTALLED IAW SRM 53-02, FIGURE 18.
Part: RIB — CRACKED (RT HORIZ STAB)
INSPECTION FOUND A .5 INCH CRACK IN INBOARD UPPER RIB OF RT HORIZONTAL STABILIZER LEADING EDGE. A .5 INCH CRACK WAS FOUND IN SECOND RIB FROM INBOARD END OF LT HORIZONTAL STABILIZER LEADING EDGE. THE CRACKS WERE STOP DRILLED, A DOUBLER WAS FABRICATED AND INSTALLED AT EACH LOCATION IAW SRM 51-30-0 AND 55-02, FIGURE 18.
Part: STIFFENER — CRACKED (BS 579)
INSPECTION FOUND A .5 INCH CRACK IN STIFFENER AT LT FUSELAGE FILLET AREA, STA 579 LONGERON 24L. A REPAIR WAS INSTALLED IAW SRM 53-01, FIGURE 2.
Part: ANGLE — CRACKED (BS 1019)
INSPECTION FOUND A 1 INCH CRACK IN LT PYLON TOP SKIN TO FUSELAGE L-ANGLE AT STA 1019. THE ANGLE WAS REMOVED AND REPLACED IAW SRM 54-04.
Part: ANGLE — CRACKED (DORSAL FIN)
INSPECTION FOUND A .25 INCH CRACK IN LT DORSAL FIN ATTACH ANGLE. THE ATTACH ANGLE WAS REPLACED IAW SRM 51-60-0.
Earlier reports · 1995 · 3 reports
1995
Part: AIR DISTR — SMOKE (CABIN)
FLT NR 1589 - CMH - SMOKE APPEARED IN CABIN ON ROTATION AND INITIAL CLIMB-OUT AND THEN WENT AWAY ON DEPARTURE FROM CMH. THE AIRCRAFT WAS RETURNED TO CMH. THE PASSENGERS WERE EVACUATED VIA THE JETWAY, AS A PRECAUTIONARY MEASURE. THE AIR CONDITIONING SYSTEM WAS TESTED AND NO DISCREPANCIES WERE NOTED. THE ACM OK LEVEL, APU, AND ENGINE BLEEDS WERE ALL CHECKED WITH NO TROUBLE FOUND. THE SMOKE COULD NOT BE DUPLICATED. THE AIRCRAFT HAD BEEN HEAVILY DE-ICED PRIOR TO TAKEOFF. SUBMITTER STATES, INGESTION OF DE-ICING FLUID WAS SUSPECT. (M)
Part: EEL BATTERIES — DISCHARGED (CABIN)
HOU - INSPECTION FOUND THE FIRST CLASS AND FORWARD COACH OVERHEAD EMERGENCY LIGHTS INOPERATIVE. MAINTENANCE FOUND THE BATTERIES DISCHARGED. THE BATTERIES WERE CHARGED AND OPERATION OF THE OVERHEAD EMERGENCY LIGHTS WAS RESTORED. (X)
Part: MEGAPHONE — INOPERATIVE (CABIN)
FLT NR 1805 - CLE - THE FORWARD CABIN MEGAPHONE WAS FOUND INOPERATIVE DURING A PREFLIGHT CHECK. THE FORWARD CABIN MEGAPHONE WAS REPLACED. (M)