N10236
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.
36 reports on file, 1995-06-28 – 1998-08-26.
Part: SOLENOID — INOPERATIVE (CONTROL LEVER)
THE LANDING GEAR HANDLE WOULD NOT MOVE PAST OFF POSITION TO UP UNLESS OVERRIDE TRIGGER WAS PULLED AFTER TAKEOFF. MAINTENANCE FOUND THE LANDING GEAR CONTROL LEVER LOCK SOLENOID AT FAULT. THE LEVER LOCK SOLENOID WAS REMOVED AND REPLACED IAW MM 32-31-31. IN ADDITION, THE AIR/GROUND SAFETY SENSORS WERE ADJUSTED IAW MM 32-09-200. A FULL GEAR RETRACTION WAS PERFORMED IAW MM 32-32-0 WITH ALL INDICATIONS AND GEAR HANDLE OPERATING NORMALLY.
Part: LINE — LEAKING (NR 5 LE SLAT)
THE B SYSTEM HYDRAULIC QUANTITY DECREASED TO 1.8 GALLONS IN FLIGHT AND WAS ACCOMPANIED BY ILLUMINATION OF THE B SYSTEM LOW QUANTITY LIGHT. THE ABNORMAL CHECKLIST WAS ACCOMPLISHED AND THE AIRCRAFT LANDED WITHOUT INCIDENT. MAINTENANCE FOUND THE NR 5 LEADING EDGE SLAT ACTUATOR LINE LEAKING. THE LINE WAS REMOVED AND REPLACED. LEAK AND OPERATIONAL CHECKS WERE GOOD.
Part: SIGN — SHORTED (CABIN)
THE CREW REPORTED SMOKE APPEARED MOMENTARILY IN CABIN AT PUSH TIME. MAINTENANCE FOUND THE NO SMOKING FASTEN SEAT BELT SYSTEM INOPERATIVE WITH THE ROW 6 ABC OVERHEAD PSU BASE ASSEMBLY SHORTED OUT. THE WIRES FOR PSU AT ROW 6 ABC WERE CUT AND STOWED AND THE SYSTEM WAS PLACARDED INOPERATIVE.
Earlier reports · 1995–1997 · 33 reports
1997
Part: FRAME — CORRODED (BS 987)
INSPECTION FOUND CABIN FLOOR FRAME CORRODED AT STA 987 FROM BL 55L TO BL 55R. THE CORRODED UPPER CAP WAS REMOVED IAW SRM 51-30-2. A NEW UPPER CAP WAS FABRICATED AND INSTALLED IAW SRM 51-10-2 AND 51-30-2.
Part: SUPPORT — CORRODED (BS 328-344)
INSPECTION FOUND FLOOR SUPPORT UPPER PLATE CORRODED AT STA 328 TO 344, RBL 10. THE FLOOR SUPPORT WAS REMOVED AND A NEW SUPPORT WAS FABRICATED AND INSTALLED IAW SRM 53-10-2 AND 51-10-2.
Part: FLOORBEAM — CORRODED (BS 328)
INSPECTION FOUND FLOORBEAM UPPER CAP AND WEB CORRODED INSIDE E AND E COMPARTMENT AT BS 328. THE CORRODED SECTION OF BEAM CAP WAS REMOVED AND A NEW SECTION AND SPLICE ANGLES WERE FABRICATED AND INSTALLED IAW SRM 53-10-2. THE CORRODED SECTION OF FLOORBEAM WEB WAS REMOVED AND FILLERS AND DOUBLER WERE FABRICATED AND INSTALLED IAW SRM 51-40-2 AND 51-10-2.
Part: FLOORBEAM — CORRODED (BS 344)
INSPECTION FOUND FLOORBEAM UPPER T-CAP CORRODED AT STA 344 FROM LBL 24 TO RBL 24. THE CORRODED FLOORBEAM CAP WAS REMOVED, A REPLACEMENT CAP AND SPLICES WERE FABRICATED AND INSTALLED IAW SRM 53-10-9 AND 53-30-2.
Part: FLOORBEAM — CORRODED (BS 312)
INSPECTION FOUND FLOORBEAM UPPER CAP CORRODED AT STA 312, RT OUTBOARD END. THE CORRODED SECTION WAS REMOVED IAW SRM 51-30-2, REPAIR FILLER AND ANGLES WERE FABRICATED AND INSTALLED IAW SRM 53-10-9, 51-10-2, AND 51-30-2.
Part: FLOORBEAM — CORRODED (BS 1016)
INSPECTION FOUND FLOORBEAM CORRODED AT STA 1016, LBL 1.5 AND LBL 9. THE FLOORBEAM WAS REPAIRED IAW ECRA 5310-03623.
Part: SUPPORT — CORRODED (BS 328-344)
INSPECTION FOUND FLOOR SUPPORT CORRODED AT STA 328 TO 344, LBL 10. THE FLOOR SUPPORT WAS REMOVED IAW SRM 53-10-2. A NEW SUPPORT WAS FABRICATED AND INSTALLED IAW SRM 53-10-2 AND 51-10-2.
Part: SUPPORT — CORRODED (BS 294.5-312)
INSPECTION FOUND FLOOR SUPPORT CORRODED AT STA 294.5 TO 312, RBL 10. THE FLOOR SUPPORT WAS REMOVED AND A NEW SUPPORT WAS FABRICATED AND INSTALLED IAW SRM 53-10-2 AND 51-10-2.
Part: WEB — CORRODED (BS 330-340)
INSPECTION FOUND WEB CORRODED AT BS 330 TO 340, RT CUSP. THE CORROSION WAS REMOVED IAW SRM 51-10-6, A REPAIR DOUBLER WAS FABRICATED AND INSTALLED IAW SRM 51-40-2, 51-10-2, AND 51-30-2.
Part: ANGLE — CORRODED (BS 797)
INSPECTION FOUND CORROSION IN ANGLE AT BS 797, S26L. THE CORRODED AREA WAS CUT OUT IAW SRM 53-10-3, FIGURE NR 1, AN ANGLE REPAIR WAS FABRICATED AND INSTALLED IAW SRM 51-10-3, 51-10-2, AND 51-30-0.
Part: HYD LINE — CRACKED (NR 1 ENGINE)
THE AIRCRAFT LOST A-HYDRAULIC SYSTEM WHILE EN ROUTE. THE HYDRAULIC LOSS CHECKLIST WAS COMPLETED AND THE AIRCRAFT LANDED AT EWR WITHOUT INCIDENT. MAINTENANCE FOUND NR 1 ENGINE A-SYSTEM HYDRAULIC PRESSURE LINE CRACKED. THE HYDRAULIC PRESSURE LINE WAS REMOVED AND REPLACED. IN ADDITION, THE NR 1 AND NR 2 ENGINE DRIVEN HYDRAULIC PUMPS WERE REMOVED AND REPLACED. LEAK AND OPERATIONAL CHECKS WERE GOOD.
1996
Part: STRINGER — CRACKED (RT AC BAY)
RIGHT A/C BAY OUTBOARD SIDE APPROX 1.5 LONG CRACK EXTENDING UNDER STIFFENER AT FUSELAGE STATION. REMOVED STIFFENER, STOP DRILLED CRACK, AND INSTALLED PER SRM 51-10-1 AND 51-30-2.
Part: BATTERY PACK — DISCHARGED (L2 DOOR)
L2 DOOR MOUNTED ESCAPE SLIDE LIGHT INOP. REPLACED BATTERY PACK PER MM 33-51-63.
Part: SKIN — CORRODED (BS 877-857)
AFT FUSELAGE STATION 877 TO 857 AT STATION 24R LAP JOINT SWOLLEN BETWEEN FASTENER HEADS. REMOVED FASTENERS AT LAP JOINT AND CORROSION PER SRM 51-10-2 AND 51-10-6 AND INSTALLED FASTENERS PER SRM 51-30-2.
Part: SKIN — BULGED (BS 235.8-251.8)
EXTERIOR SKIN ON LEFT SIDE NOSE WHEEL WELL EDGE HAS BULGES AND RIVETS PULLING THROUGH FROM STATION 235.8 TO 251.8. CUT OUT DAMAGED AREA, FABRICATED FILLER AND DOUBLER, INSTALLED PER SRM 53-30-3, 51-30-2, AND 51-10-2.
Part: SKIN — OIL CAN (BS 390)
FUSELAGE SKIN OIL CAN AT BS 390L AND STR 17L. TRIMMED OUT DAMAGED AREA PER SRM 53-30-3, FABRICATED DOUBLER PER SRM 53-30-3 AND 51-10-2, INSTALLED DOUBLER PER SRM 53-30-3 AND 51-30-2.
Part: BULKHEAD — CRACKED (BS 178)
FORWARD FACE OF FORWARD PRESSURE BULKHEAD STATION 178 CRACKED ON RIGHT SIDE ABOVE WL STA 208, APPROX 8. CUT OUT DAMAGED AREA, FABRICATED REPAIR DOUBLER AND FILLERS, INSTALLED PER SRM 53-10-11, 53-30-2, AND 51-10-2.
Part: SKIN — CRACKED (BS 727)
FUSELAGE SKIN CRACKED IN 2 PLACES ON LEFT SIDE BETWEEN STA 727A AND 727B AT STRINGER 18 APPROX 3 EACH. CUT OUT DAMAGED AREA, FABRICATED FILLER AND EXTERNAL DOUBLER AND INSTALLED PER SRM 53-30-3, 53-30-2, AND 51-10-2.
Part: BLKHD WEB — CRACKED (BS 178)
FORWARD FACE OF FORWARD PRESSURE BULKHEAD STATION 178 CRACKED ON LEFT SIDE ABOVE WL 208 APPROX 8. CUT OUT DAMAGED AREA, FABRICATED REPAIR DOUBLER AND FILLER, INSTALLED PER SRM 53-10-11, 51-30-2, AND 51-10-2.
1995
Part: BATTERY PACK — DISCHARGED (LT EMER EXIT)
GSO - AIRCRAFT IN 1/2 D-CHECK, FOUND LEFT EXTERNAL EMERGENCY LIGHT INOP. REPLACED LEFT EXTERNAL EMERGENCY EXIT LIGHT BATTERY PACK AND BATTERY. (M)
Part: FRAME — CRACKED (BS 420)
GSO - INSPECTION FOUND A CRACK IN FRAME AT BS 420 BETWEEN S22R AND S21R AND BETWEEN S21R AND S20R. THE CRACK AT EACH LOCATION WAS APPROXIMATELY .75 INCH LONG. THE CRACKED FRAME SEGMENT WAS REMOVED AND REPLACED IAW BOEING DRAWING 65C25113. (X)
Part: FRAME — CRACKED (BS 500)
GSO - INSPECTION FOUND CRACKS IN FRAME AT BS 500 BETWEEN STR 21L AND STR 22L AND STR 22L AND STR 23L. THE CRACK AT EACH LOCATION WAS APPROXIMATELY .75 INCH LONG. THE CRACKED SEGMENT OF FRAME WAS REMOVED AND REPLACED IAW BOEING DRAWING 65C25113. (X)
Part: FRAME — CRACKED (BS 500)
GSO - AIRCRAFT IN D-CHECK, FOUND CRACK IN FRAME SEGMENT APPROXIMATLY .75 INCH AT BS 500A BETWEEN S20L, S21L, AND ABOVE S23L, REMOVED AND REPLACED. (M0
Part: FRAME — CRACKED (BS 500)
GSO - AIRCRAFT IN 1/2 D-CHECK, FOUND CRACK IN FRAME SEGMENT APPROXIMATELY .75 INCH AT BS 500A BETWEEN S20R AND S21R, REMOVED AND REPLACED. (M)
Part: BATTERY PACK — DISCHARGED (RT EMER EXIT)
GSO - EXIT LIGHT INOP. REPLACED RIGHT EXTERNAL EMERGENCY EXIT LIGHT BATTERY PACK AND BATTERY. (M)
Part: FRAME — CRACKED (BS 400)
GSO - AIRCRAFT IN 1/2 D-CHECK, FOUND CRACK APPROXIMATELY .75 INCH IN FRAME SEGMENT AT BS 400 BETWEEN S21L AND S22L, REMOVED AND REPLACED. (M)
Part: FRAME — CRACKED (BS 480)
GSO - AIRCRAFT IN ONE-HALF D-CHECK DURING INSPECTION, FOUND CRACK FRAME SEGMENT APPROXIMATELY .05 INCH AT BS 480 BETWEEN S20L AND S21L. REMOVED AND REPLACED. (X)
Part: SKIN — CRACKED (CARGO DOOR)
GSO - INSPECTION FOUND A .50 INCH CRACK AT FORWARD LOWER CORNER OF AFT CARGO DOOR CUT-OUT, EXTERNAL SKIN. THE CRACKED AREA WAS REMOVED. A FILLER AND DOUBLER REPAIR WAS FABRICATED AND INSTALLED IAW TIMCO ENGINEERING ORDER RFO-01655. (X)
Part: FRAME — CRACKED (BS 460)
GSO - AIRCRAFT IN 1/2 D-CHECK DURING INSPECTION, FOUND CRACK IN FRAME SEGMENT AT BS 460 APPROXIMATELY .75 INCH, BETWEEN S20L AND S21L. REMOVED AND REPAIRED. (X)
Part: FRAME — CRACKED (BS 500B)
GSO - INSPECTION FOUND CRACKS IN FRAME AT BS 500B BETWEEN STR 19L AND STR 20L, AND BETWEEN STR 25L AND STR 27L. THE CRACK AT EACH LOCATION WAS APPROXIMATELY .33 INCH LONG. THE CRACKED SEGMENT OF FRAME WAS REMOVED AND REPLACED IAW BOEING DRAWING 65C25113. (X)
Part: BATTERY PACK — DISCHARGED (L-1 SLIDE LIGHT)
GSO - AIRCRAFT IN 1/2 D-CHECK, FOUND BATTERY PACK INOP. REPLACED BATTERY PACK FOR L-1 SLIDE. (M)
Part: FRAME — CRACKED (BS 420)
GSO - AIRCRAFT IN ONE-HALF D-CHECK. DURING INSPECTION, FOUND CRACK APPROXIMATELY .75 INCH AT BS 420 BETWEEN S21L, S22L, S23L. STOP DRILLED CRACK AND INSTALLED DOUBLER. (X)
Part: HYD LINE — WORN (NLG)
FLT NR 1728 - CLE - THE NOSE LANDING GEAR WOULD NOT RETRACT AFTER TAKEOFF FROM IND. BOTH THE RED AND GREEN LIGHTS REMAINED ON. WHEN THE GEAR HANDLE WAS PLACED DOWN, THE RED LIGHT EXTINGUISHED. THE HYDRAULIC QUANTITY GAUGE DROPPED TO .8 GALS. THE AIRCRAFT WAS RETURNED TO IND WHERE IT LANDED WITHOUT INCIDENT. MAINTENANCE FOUND THE HYDRAULIC PRESSURE LINE TO THE NOSE GEAR LOCK ACTUATOR WORN THROUGH. THE LINE WAS REMOVED AND REPLACED. OPERATIONAL AND LEAK CHECKS WERE GOOD. (M)