N14208

No registry detail on file · not in current registry

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.

12 reports on file, 1995-05-10 – 1998-04-27.

FLUID LOSS; WARNING INDICATION · 1998-04-27 Matched by certificate designator
ATA 2910

Part: HYD LINES — PUNCTURED (LT ELEV PCU)

THE A SYSTEM HYDRAULIC FLUID LEVEL DROPPED TO ZERO WHILE ON DESCENT INTO PHL. THE AIRCRAFT LANDED WITHOUT INCIDENT. MAINTENANCE FOUND TWO HYDRAULIC FLEX LINES AT LT ELEVATOR PCU PUNCTURED. THE FLEX LINES WERE REMOVED AND REPLACED. LEAK AND OPERATIONAL CHECKS WERE GOOD.

Source: SDR CALA9800702
FLUID LOSS; WARNING INDICATION · 1997-12-01 Matched by certificate designator
ATA 2910

Part: LINE — LEAKING (A-HYD SYST)

THE AIRCRAFT LOST A-HYDRAULIC SYSTEM WHILE EN ROUTE. THE AIRCRAFT WAS DIVERTED TO BUF WHERE IT LANDED WITHOUT INCIDENT. MAINTENANCE FOUND THE LEFT WING AFT SPAR PRESSURE HYDRAULIC LINE LEAKING. A FLEX LINE WAS INSTALLED AND A DIP WAS ISSUED TO REPLACE THE LINE WITHIN 500 FLIGHTS OR 1200 HOURS, WHICHEVER COMES FIRST. LEAK CHECKS WERE GOOD.

Source: SDR CALA9701684
FLT CONT AFFECTED · 1997-08-22 Matched by certificate designator
ATA 2720

Part: PCU — INOPERATIVE (RUDDER)

A/C ATTEMPTED TO BANK LT WITH YAW DAMPER ON AND AUTOPILOT ENGAGED WHILE CLIMBING THRU 17,000 FT. THE YAW DAMPER WAS SWITCHED OFF AND ROLL ARRESTED. BANK ANGLE DID NOT EXCEED 15 DEG. APPROPRIATE CHECKLISTS COMPLETED AND THE FLT CONTINUED W/O PROBLEM. THE RUDDER PCU WAS R/R'D AND FUNCTIONAL CHECKS GOOD IAW MM 27-21-91. IN ADDITION, FCD 2210-01265 AUTOPILOT MAJOR COMPONENTS INSPECTION WAS COMPLIED WITH, ALL CHECKS GOOD. THE UNIT COMPLETED TOP ASSY RECEIVING TESTING AT PARKER PER OVERHAUL MANUAL WITH ONLY MINOR DEVIATIONS. PARKER CONCLUDED THAT NO DISCREPANCIES WERE FOUND WHICH WOULD HAVE LEAD TO AN ANOMALY IN RUDDER PCU OPERATION.

Source: SDR CALA9701243
FALSE WARNING · 1995-06-07 Matched by certificate designator
ATA 3260

Part: UPLOCK SENSOR — INOPERATIVE (RT MLG)

FLT NR 9860 - CLE - THE RT MLG RED UNSAFE LIGHT REMAINED ILLUMINATED AFTER GEAR RETRACTION. CYCLING THE GEAR DID NOT HELP. THE AIRCRAFT WAS RETURNED TO CLE WHERE IT LANDED WITHOUT INCIDENT. THE RT MLG UPLOCK SENSOR WAS REMOVED AND REPLACED. THE GEAR WAS SWUNG AND OPERATION AND INDICATIONS CHECKED GOOD. (M)

Source: SDR CAL950463
OTHER · 1995-05-10 Matched by certificate designator
ATA 5311

Part: FRAME — CORRODED (FS 529)

GSO - INSPECTION FOUND CORROSION ON FRAME ABOVE STRINGER 26R AT STATION 529. A NEW FRAME AND SPLICE WERE FABRICATED AND INSTALLED IAW SRM 53-10-3 AND 51-30-2. (W)

Source: SDR CAL950402
OTHER · 1995-05-10 Matched by certificate designator
ATA 5311

Part: FRAME — CRACKED (FS 460)

GSO - INSPECTION FOUND A .5 INCH CRACK IN FRAME BETWEEN S22L AND S23L AT STATION 460. THE CRACKED FRAME WAS REMOVED AND A NEW FRAME AND DOUBLERS WERE INSTALLED IAW BOEING PRINT NR 65C25113. (W)

Source: SDR CAL950398
OTHER · 1995-05-10 Matched by certificate designator
ATA 5330

Part: SKIN — CRACKED (WL 207.5)

GSO - INSPECTION FOUND FUSELAGE SKIN FASTENER HOLES CRACKED IN SEVERAL PLACES BETWEEN WL 207.5 AND 234.35, SECTION 41. THE CRACKS WERE APPROXIMATELY .25 INCH LONG. THE CRACKED AREA WAS REMOVED. DOUBLERS AND FILLERS WERE FABRICATED AND INSTALLED IAW EA 5310-01188 AND SRM 51-30-2. (W)

Source: SDR CAL950405
OTHER · 1995-05-10 Matched by certificate designator
ATA 5311

Part: FRAME — CRACKED (FS 480)

GSO - INSPECTION FOUND A .75 INCH CRACK IN FRAME BETWEEN S20L AND S21L AT STATION 480. THE CRACKED SECTION OF FRAME WAS CUOTUT. A NEW SECTION OF FRAME WAS INSTALLED IAW BOEING DRAWING NR 65C25113 AND EA 5310-01211. (W)

Source: SDR CAL950399
OTHER · 1995-05-10 Matched by certificate designator
ATA 5311

Part: FRAME — CRACKED (FS 440)

GSO - INSPECTION FOUND A .5 INCH CRACK IN FRAME BETWEEN S20L AND S21L AT STATION 440. THE FRAME WAS REMOVED AND REPLACED IAW BOEING DRAWING NR 65C25113 AND EA 5310-01211. (W)

Source: SDR CAL950401
OTHER · 1995-05-10 Matched by certificate designator
ATA 5330

Part: SKIN — CRACKED (BS 188-251.6)

GSO - INSPECTION FOUND FUSELAGE SKIN FASTENER HOLES CRACKED IN SEVERAL LOCATIONS BETWEEN BS 188-251.6 RIGHT SIDE. THE CRACKS WERE APPROXIMATELY .25 INCH LONG. THE CRACKED SECTION OF SKIN WAS REMOVED. REPAIR DOUBLER S AND FILLERS WERE FABRICATED AND INSTALLED IAW EA 5310-01188 AND SRM 51-30-2. (W)

Source: SDR CAL950404
OTHER · 1995-05-10 Matched by certificate designator
ATA 5330

Part: SKIN — CRACKED (FS 908)

GSO - INSPECTION FOUND A .5 INCH CRACK IN EXTERNAL SKIN AT STRINGER 4L, STATION 908. THE CRACKED AREA WAS CUTOUT. A FILLER AND DOUBLER REPAIR WAS FABRICATED AND INSTALLED IAW SRM 53-30-3 AND 51-30-2. (W)

Source: SDR CAL950403
OTHER · 1995-05-10 Matched by certificate designator
ATA 5311

Part: FRAME — CRACKED (FS 500)

GSO - INSPECTION FOUND A .5 INCH CRACK IN FRAME BETWEEN S20L AND S21L AT STATION 500. THE CRACKED SECTION OF FRAME WAS CUTOUT. A NEW SECTION OF FRAME WAS FABRICATED AND INSTALLED IAW BOEING BLUE PRINT NR 65C25113 AND EA 5310-01211. (W)

Source: SDR CAL950400