N571PE
Operators of this aircraft
Who operated this tail, and how firmly we know it.
No operator established for this aircraft.
Accident & incident history
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.
21 reports on file, 1995-02-15 – 1997-02-23.
Part: ANGLE — CRACKED (BS 297)
INSPECTION FOUND A 1.5 INCH CRACK IN ANGLE UNDER CABIN FLOOR AT STA 297, RBL 12. THE CRACK WAS STOP DRILLED, A DOUBLER WAS FABRICATED AND INSTALLED IAW SRM 51-30-2.
Part: STRINGER — CORRODED (BS 950)
INSPECTION FOUND CORROSION IN BILGE AREA OF AFT PIT AT STA 950E, STRINGER 27R. THE CORRODED AREA WAS CUT OUT IAW SRM 53-30-3, A REPAIR WAS FABRICATED AND INSTALLED IAW SRM 53-30-3.
Part: FLOORBEAM — CORRODED (BS 348.2)
INSPECTION FOUND FLOORBEAM CORRODED BETWEEN TIE DOWN TRACKS AND OUTBOARD TO END AT BS 348.2, LT SIDE. THE CORRODED AREA WAS REMOVED, A REPAIR WAS FABRICATED AND INSTALLED IAW SRM 53-10-8.
Part: SKIN — DAMAGED (BS 360)
INSPECTION FOUND DAMAGE IN THE FORM OF MATERIAL LOSS ON EDGE OF SKIN AT LT SIDE OF FUSELAGE, BS 360 BETWEEN STRINGER 17L AND 18L, AT PRODUCTION JOINT. THE AREA WAS BLENDED AND A DOUBLER WAS FABRICATED AND INSTALLED IAW ECRA 5330-02493 AND SRM 53-30-3.
Part: FRAME — CRACKED (BS 783.95)
INSPECTION FOUND A CRACK IN RIGHT FRAME INBOARD FLANGE AT FIRST FASTENER HOLE BELOW FLOORBOARD ATTACH ANGLE AT BS 783.95. THE CRACK LENGTH WAS NOT IDENTIFIED, A REPAIR KIT WAS INSTALLED IAW BOEING DRAWING 65C36280-2.
Part: SKIN — CREASED (BS 1121-1152)
INSPECTION FOUND A 6 INCH CREASE EXTENDING FORWARD OF DOUBLER IN RT AFT FUSELAGE AT BS 1152 TO 1121 BETWEEN STRINGER 22R AND 23R. A REPAIR DOUBLER AND FILLER WERE FABRICATED AND INSTALLED IAW SRM 53-30-2, 51-30-2, 53-30-3 AND 53-30-4.
Part: SKIN — BULGED (RT WING)
INSPECTION FOUND RT WING OUTBOARD LOWER SKIN BULGED JUST AFT OF PANEL NR 7703. THE BULGED AREA WAS CUT OUT, A DOUBLER WAS FABRICATED AND INSTALLED IAW ECRA 5730-01484.
Part: CEILING PANEL — CRACKED (BS 276)
INSPECTION FOUND TWO .125 INCH CRACKS AT ONE FASTENER HEAD IN NLG CEILING PANEL AT BS 276, RBL 14. THE CRACKS WERE ROUTED OUT, A FILLER AND DOUBLER REPAIR WERE FABRICATED AND INSTALLED IAW SRM 51-40-2.
Part: CEILING PANEL — CRACKED (BS 285)
INSPECTION FOUND A .125 INCH CRACK AT TWO EACH FASTENER HEADS IN NLG CEILING PANEL AT BS 285, LBL 4. THE CRACKED AREA WAS CUT OUT, A FILLER AND DOUBLER REPAIR WERE FABRICATED AND INSTALLED IAW SRM 51-40-2.
Part: SKIN — DELAMINATED (LT AILERON)
INSPECTION FOUND LT OUTBOARD AILERON OUTBOARD TRAILING EDGE WEDGE DELAMINATED AND ERODED. SKIN WAS FABRICATED AND INSTALLED IAW SRM 51-40-6.
Part: PULLEY ASSY — WORN (NLG DOOR)
NOSE GEAR FAILED TO RETRACT AFTER TAKEOFF. THE AIRCRAFT WAS RETURNED TO EWR WHERE IT LANDED WITHOUT INCIDENT. MAINTENANCE FOUND NLG DOOR FORWARD PULLEY ASSEMBLY WITH SIGNS OF CONTACTING THE PULLEY FOLLOWUP LINKAGES. THE FORWARD PULLEY ASSEMBLY WAS REMOVED AND REPLACED. IN ADDITION, THE LEFT NOSE WHEEL WELL QUADRANT ASSEMBLY, NLG DOOR FORWARD PULLEY UPPER RADIUS ROD ASSEMBLY AND NOSE GEAR WHEEL WELL DOOR PUSH PULL ROD-B WERE REPLACED DUE TO WEAR. THE NOSE GEAR SHOCK STRUT WAS REPACKED WITH FULL SEAL REPLACEMENT, THE NOSE GEAR WHEEL WELL DOORS WERE ADJUSTED IAW MM 32-22-1, PAGE 501 TO 507. THE NLG WAS SWUNG SEVERAL TIMES WITH NO DEFECTS NOTED.
Earlier reports · 1995–1996 · 10 reports
1996
Part: FLOOR BEAM — CORRODED (BS 1130)
INSPECTION FOUND CORROSION ON FLOOR BEAM AT STA 1130, RT SIDE OF AIRCRAFT. THE FLOOR BEAM WAS REPAIRED IAW ECRA 5310-03297.
Part: DNLOCK SWITCHES — INOPERATIVE (NLG)
IAH - FLT 1902 - THE AIRCRAFT HAD A BRIEF HISTORY OF THE NLG RED UNSAFE LIGHT REMAINING ILLUMINATED AFTER GEAR RETRACTION. THE LIGHT EXTINGUISHED WHEN GEAR WAS CYCLED. MAINTENANCE REMOVED AND REPLACED THE NLG LOCK AND POSITION SWITCHES PER MM 32-61-71, PAGE 401. A NOSE GEAR SWING WAS PERFORMED AND OPERATION CHECKED GOOD. (X)
1995
Part: FUSE — BLOWN (CABIN)
FLT NR 0631 - EWR - A PREFLIGHT INSPECTION, FOUND FORWARD SECTION OF EMERGENCY TRACK LIGHTING INOPERATIVE FROM ROW 1-7. MAINTENANCE FOUND A FUSE BLOWN ON FORWARD POWER SUPPLY. THE FUSE WAS REMOVED AND REPLACED AND OPERATION OF THE LIGHTS WAS RESTORED. (M)
Part: SUPPORT — CRACKED (WS 521)
GSO - INSPECTION FOUND A .5 INCH CRACK IN LEFT WING LOWER TRAILING EDGE SUPPORT CHANNEL AT STATION 521. THE SUPPORT CHANNEL WAS REMOVED AND A NEW CHANNEL WAS INSTALLED IAW EX 5720C01236. (Z)
Part: SUPPORT — CRACKED (WS 469)
GSO - INSPECTION FOUND A .5 INCH CRACK IN LEFT WING LOWER TRAILING EDGE SUPPORT CHANNEL AT STATION 469. THE SUPPORT CHANNEL WAS REMOVED AND A NEW CHANNEL WAS INSTALLED IAW EX 5720C01236 AND CAL DRAWING 5720 DC8908. (Z)
Part: FRAME — CRACKED (BS 760.95)
GSO - INSPECTION FOUND A 1 INCH CRACK IN WEB AT RT STA 760.95 OVERWING EXIT FRAME. THE CRACK WAS LOCATED AT THE FIRST HOLE UNDER FLOOR LINE. THE CRACK WAS REPAIRED BY INSTALLING A REPAIR ANGLE, FILLER, SHIMS, AND SILL SPLICE IAW BOEING DRAWING 65C36279-2. (X)
Part: BRACKET — CRACKED (RT LE FLAP)
GSO - INSPECTION FOUND A .75 INCH CRACK IN RT WING, NR 5 LEADING EDGE SLAT ACTUATOR ATTACH BOLT BRACKET. A REPAIR WAS PERFORMED IAW SRM 51-30-2 AND BOEING DRAWING 65-17276. (X)
Part: ANGLE — CRACKED (BS 700)
GSO - INSPECTION FOUND A 2 INCH CRACK AT BOTH ENDS OF BOTTOM CENTER ANGLE AT FS 700. THE ANGLE WAS REMOVED AND THE CRACKS WERE STOP DRILLED IAW SRM 51-10-1 AND SRM 51-30-2. REPAIRS WERE INSTALLED IAW SRM 51-30-2. (X)
Part: STIFFENER — CORRODED (BS 308)
GSO - INSPECTION FOUND CORRODED STIFFENER ON TOP OF DOG HOUSE AT BS 308. THE STIFFENER WAS REMOVED AND A NEW ONE WAS INSTALLED IAW SRM 51-30-2 AND SRM 51-20-4. (X)
Part: FLOOR BEAM — CRACKED (BS 344)
GSO - INSPECTION FOUND A 1.25 INCH CRACK IN STRAP AT LOWER SIDE OF FLOOR BEAM, BS 344. A REPAIR WAS FABRICATED AND INSTALLED IAW SRM 51-40-3 AND SRM 51-30-2. (X)