N16895
Registered owner: LUXAIR LLC, TX (owner ≠ operator)
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.
65 reports on file, 1995-01-03 – 2002-05-27.
Part: BATTERY PACK — DISCHARGED (CABIN) · airframe 48,907 hrs · 24,085 cycles
THE OVERHEAD EMERGENCY LIGHTS AT ROW 5-9 STAYED ON WHEN POWER WAS SECURED DURING TEST. THE EMERGENCY LIGHT B5-101 BATTERY PACK WAS REMOVED AND REPLACED IAW MM 33-53-00.
Part: WIRE — BROKEN (EXIT LIGHT) · airframe 48,907 hrs · 24,085 cycles
INSPECTION FOUND THE L-2 DOOR EMERGENCY EXIT LIGHTS INOPERATIVE. REPAIRED BROKEN WIRE IAW STANDARD WIRING PRACTICES 20-10-03 AND OPEARTION CHECKED GOOD IAW MM 33-53-00.
Part: SKIN — DENTED (STA 1212) · airframe 48,907 hrs · 24,085 cycles
INSPECTION FOUND FUSELAGE BELLY SKIN DENTED AT STA 1212, L29L TO L29R. THE AREA WAS REPAIRED IAW ECRA 5331-01114 AND EA 9-5330-2-A0954.
Part: FRAME — CORRODED (STA 1322) · airframe 48,907 hrs · 24,085 cycles
INSPECTION FOUND FRAME CORRODED IN AFT PIT AT STA 1322, RBL 29-30. REMOVED TWO INTERCOSTALS AND TWO BULKHEAD ATTACH ANGLES TO GAIN ACCESS TO FRAME. INSTALLED NEW FRAME IAW SRM 51-30-2 AND 51-30-5. REINSTALLED INTERCOSTALS AND BULKHEAD ATTACH ANGLES. ALSO INSTALLED SHEAR TIE AND REPAIR SPLICE IAW SRM 51-30-5 AND 51-30-2.
Part: WEB — CORRODED (FUSELAGE) · airframe 48,907 hrs · 24,085 cycles
L2 DOORWAY CUSP WEB CORRODED LBL 44 TO LBL 54 AT STATION FS 1168. REMOVED AND REPLACED WEB AND STIFFENER PER SRM 51-30-2 AND 51-30-5.
Part: WEB — CORRODED (FUSELAGE) · airframe 48,907 hrs · 24,085 cycles
AFT PIT WEB CORRODED AT STATION 1322 - 1309 R28 - R27. REMOVED, FABRICATED AND REINSTALLED INTERCOSTAL PER SRM 51-30-5 AND 51-30-2.
Part: FRAME — CORRODED (FS1309-1322) · airframe 48,907 hrs · 24,085 cycles
AFT PIT STATION 1322 - 1309 AT L28 - L27 FRAME CORRODED. REMOVED FABRICATED AND REINSTALLED FRAME PER SRM 53-01 FIG1, 51-30-2, 51-30-5, AND 51-10-03.
Part: SKIN — DENTED (ELEVATOR) · airframe 48,907 hrs · 24,085 cycles
LEFT ELEVATOR LOWER SKIN DENTED. REMOVED ELEVATOR, REPAIRED AND BALANCED PER SRM 55-03 FIG 14, 55-20-2. REINSTALLED PER MM 27-30-02 AND 27-30-00.
Part: TRIM TAB — GOUGED (AILERON) · airframe 48,907 hrs · 24,085 cycles
RIGHT AILERON CONTROL TAB UPPER SURFACE GOUGED. REMOVED, REPAIRED, AND BALANCED CONTROL TAB PER MM 27-10-02, SRM 51-70-1, AND SRM 57-50-1. REINSTALLED PER MM 27-10-02.
Part: FRAME — CHAFED (FUSELAGE) · airframe 48,907 hrs · 24,085 cycles
AFT ACCESSORY COMPARTMENT FRAME AT STATION 1380 LEFT SIDE HAS CHAFED FRAME WEB. CUT OUT DAMAGED AREA OF WEB, FABRICATED AND INSTALLED REPAIR PER SRM 53-01 FIG 94.
Part: SEAT TRACK — CORRODED (FS1174-1309) · airframe 48,907 hrs · 24,085 cycles
LEFT OUTBOARD SEAT TRACK HAS EXFOLIATION CORROSION STATION 1174 TO 1309. REMOVED AND REPLACED SEAT TRACK PER SRM 51-30-5 AND 51-30-1.
Part: RIB DOUBLER — CRACKED (HORIZ STAB LE) · airframe 48,907 hrs · 24,085 cycles
HORIZONTAL STABILIZER RIGHT INBOARD LEADING EDGE OF ELEVATOR INTERNAL RIB DOUBLER CRACKED BELOW DUCT COUPLING. REMOVED AND REPLACED RIB DOUBLER PER SRM 51-30-2.
Part: FRAME — CHAFED (FS1401) · airframe 48,907 hrs · 24,085 cycles
TAIL COMPARTMENT STATION 1401 AT LONGERON 21 R FRAME HAS DEEP CHAFE. BLENDED DAMAGE AND INSTALLED REPAIR PER SRM 51-30-2, 51-30-5, AND 53-03 FIG 4.
Part: SEAT TRACK — WORN (F/O SEAT) · airframe 48,907 hrs · 24,085 cycles
FIRST OFFICER UPPER AND LOWER SEAT TRACK WORN. REMOVED AND REPLACED SEAT TRACK PER SRM 51-30-1, 51-30-2, AND 51-10-4.
Part: INTERCOSTAL — CORRODED (FS 1136-1155) · airframe 48,907 hrs · 24,085 cycles
AFT PIT F/S 1136 TO 1155 LONGERON 30 INTERCOSTAL CORRODED. REMOVED AND REPLACED INTERCOSTAL PER SRM 51-30-5.
Part: INTERCOSTAL · airframe 48,907 hrs · 24,085 cycles
F/S 1212 LONGERON 28 RIGHT INTERCOATAL CORRODED 1"X1". INSTALLED NEW INTERCOSTAL IAW SRM 51-30-5.
Part: INTERCOSTAL · airframe 48,907 hrs · 24,085 cycles
F/S 1193 LONGERON 28 RIGHT INTERCOSTAL CORRODED 20"X1". INSTALLED NEW INTERCOSTAL T & L ANGLES IAW SRM 51-30-5.
Part: FRAME · airframe 48,907 hrs · 24,085 cycles
AFT PIT, F/S 1041, LONGERON 30 FRAME ATTACH ANGLE CORRODED - 80". REPLACED FRAME ANGLE IAW SRM 51-30-5.
Part: FRAME · airframe 48,907 hrs · 24,085 cycles
TAIL COMPARTMENT RH SIDE STA 1446 AT LONGERON 18R FRAME HAS DEEP 1"X1" CHAFE. INSTALLED ANGLE AND FILLER IAW SRM 51-30-5, 51-30-2, 51-70-5, FIG 1.
Part: SKIN · airframe 48,907 hrs · 24,085 cycles
SKIN DAMAGED AFT OF PITOT TUBE AT STA 76 R/S FWD OF COCKPIT WINDOW 3"X4". INSTALLED CLASS II REPAIR IAW SRM 53-04 FIG 12B.
Part: SKIN — CHAFED (CARGO DOOR) · airframe 48,907 hrs · 24,085 cycles
MID CARGO DOOR LOWER AFT CORNER SKIN CHAFED. INSTALLED DOUBLER IAW SRM 51-30-1 AND 51-30-5.
Part: SKIN — DENTED (CARGO DOOR) · airframe 48,907 hrs · 24,085 cycles
MID CARGO DOOR, OUTER SKIN HAS A SHARP DENT. INSTALLED REPAIR DOUBLER AND FILLER IAW SRM 51-30-2, 52-05, FIG 1.
Part: FRAME — CHAFED (FUSELAGE) · airframe 48,907 hrs · 24,085 cycles
TAIL COMPARTMENT STA 1418 AT LONGERON 15R FRAME HAS DEEP CHAFE. INSTALLED REPAIR AND SHIMS IAW SRM 51-30-2, 51-30-5, 53-03, FIG 4.
Part: SHEAR TIE · airframe 48,907 hrs · 24,085 cycles
AFT PIT F/S 1193 LONGERON 30 SHEAR TIE IS CORRODED 0.5 INCHES. REMOVED AND REINSTALLED NEW SHEAR TIE IAW SRM 51-30-2.
Part: SEAT TRACK · airframe 48,907 hrs · 24,085 cycles
SEAT TRACK AT F/S 390 RH O/B IS HEAVILY CORRODED APPROXIMATELY 4"X19'. REMOVED AND REINSTALLED AIR GRILL F/S 200-484 RH O/B IAW SRM 51-30-1. REMOVED AND REINSTALLED FLOOR PANELS F/S 256-465 RH O/B IAW SRM 51-30-1. INSTALLED NEW SEAT TRACK, SPLICE, & FITTING IAW SRM 53-05 FIG 4, SRM 51-30-01 & 51-30-05.
Part: WEB · airframe 48,907 hrs · 24,085 cycles
CUSP WEB L/S AFT OF L-2 DOOR IS CORRODED 20"X38". REMOVED WEB IAW SRM 53-01. INSTALLED WEB IAW SRM 51-30-2 & 51-30-5, 53-01 FIG 1.
Part: SKIN · airframe 48,907 hrs · 24,085 cycles
ONE INCH DENT AT F/S 237, 17L-18L. REF. NON ROUTINE 4684047, REPAIRED DENT AT STA 229 PER ECRA 5330-03055.
Part: INTERCOSTAL · airframe 48,907 hrs · 24,085 cycles
AFT PIT F/S 1146 TO 1155 BETWEEN LONGERON 30 & 29R INTERCOSTAL CORROSION 10 INCHES LONG. REMOVED INTERCOSTAL IAW SRM 51-30-2 AND 51-30-5. REPLACED INTERCOSTAL IAW SRM 51-30-2 & 51-30-5.
Part: SKIN · airframe 48,907 hrs · 24,085 cycles
RIGHT FORWARD FUSELAGE SKIN HAS 2" CREASE BETWEEN LONGERON 25 & LONGERON 26 AT APPROXIMATELY F/S 141. CUT OUT DAMAGE IAW SRM53-04 FIG 38, SHEET 34. INSTALLED REPAIR PARTS IAW SRM 53-04 FIG 38, SHEET 34.
Part: SEAT TRACK · airframe 48,907 hrs · 24,085 cycles
CAPTAINS UPPER AND LOWER SEAT TRACKS WORN, REPAIRED AND REINSTALLED TRACKS IAW SRM 51-30-1 & 53-40-01.
Part: SEAT TRACK · airframe 48,907 hrs · 24,085 cycles
CABIN FLOOR SEAT TRACK RBL 24 F/S 984 AND 1003 HAS SURFACE CORROSION. REMOVED SEAT RACK FROM STA 789-1032 RBL24 IAW SRM 51-30-5 AND INSTALLED NEW TRACK IAW SRM 53-05.
Part: SHEAR TIE · airframe 48,907 hrs · 24,085 cycles
F/S 1309 BETWEEN LONGERON 41L AND 15L SHEAR TIE IS CRACKED 12 INCHES. REMOVED OUTER CHORD, DOUBLER AND SHEAR TIE IAW SRM 51-10-4 AND SRM 51-31-1. INSTALLED NEW SHEAR TIE IAW 51-10-4 AND 51-30-5. INSTALLED CHORD, DOUBLER AND STIFFNER IAW SRM 51-30-5 AND 51-30-2.
Part: SHEAR TIE · airframe 48,907 hrs · 24,085 cycles
F/S 1309 BETWEEN LONGERON 14R AND 15R SHEAR TIE IS CRACKED 12 INCHES. REMOVED OUTER CHORD DOUBLER AND SHEAR TIE IAW SRM 51-30-4 AND 51-30-5. INSTALLLED SHEAR TIE, OUTER CHORD, DOUBLER AND STIFFER IAW SRM 51-30-5 AND 51-30-2.
Part: SHEAR TIE · airframe 48,907 hrs · 24,085 cycles
AFT PIT, F/S 1212 LONGERON 30 SHEAR TIE HAS 3 INCHES OF CORROSION. REMOVED SHEAR TIE IAW SRM 51-30-2. INSTALLED NEW SHEAR TIE IAW SRM 51-30-2.
Part: WEB — CORRODED (FUSELAGE) · airframe 48,907 hrs · 24,085 cycles
CUSP WEB IS CRACKED AND CORRODED AT STA 218 L18R RBL 56. CUT OUT CORRODED AREA IAW SRM 53-01, FIG 4. FABRICATED NEW DOUBLER IAW SRM 55-14-2 AND 53-01, FIG 4. INSTALLED DOUBLER IAW SRM 51-30-2.
Part: SKIN — DAMAGED (FUSELAGE) · airframe 48,907 hrs · 24,085 cycles
INSPECTION FOUND A CREASE IN FUSELAGE SKIN AT STA 218 BETWEEN STRINGER 16R AND 17R. THE CREASED AREA WAS REMOVED IAW SRM 53-04, FIGURE 38. A DOUBLER WAS INSTALLED IAW SRM 51-10-04 AND 53-04, FIGURE 38.
Part: SKIN — DAMAGED (FUSELAGE) · airframe 48,907 hrs · 24,085 cycles
INSPECTION FOUND A CREASE IN FUSELAGE SKIN AT STA 420 AND 446 BETWEEN STRINGER 22L AND 23L. THE CREASED AREAS WERE CUT OUT IAW SRM 53-04, FIGURE 38. A DOUBLER, FILLER, AND FINGER DOUBLER WERE INSTALLED AT EACH LOCATION IAW SRM 53-04, FIGURE 38.
Part: PAN — CRACKED (CARGO DOOR) · airframe 48,907 hrs · 24,085 cycles
INSPECTION FOUND A 1 INCH CRACK IN FORWARD CARGO DOOR PAN AT FORWARD AND AFT SIDE. THE CRACK WAS LOCATED AT RADIUS BELOW LATCH. THE CRACKS WERE STOP DRILLED IAW SRM 52-05, FIGURE 26A. REPAIR ANGLES WERE INSTALLED AT EACH LOCATION IAW SRM 52-05, FIGURE 26A.
Part: STIFFENER — CORRODED (FS1322 LONG30) · airframe 24,085 hrs · 48,907 cycles
VERTICAL STIFFENER FOR ATTACH ANGLE FOR FRAME CORRODED AT FS 1322 LONGERON 30. REMOVED AND REINSTALLED FABRICATED ANGLE PER SRM 51-30-2, 51-30-5, AND 53-01 FIG1.
Part: WEB — CRACKED (FS200 14L) · airframe 24,085 hrs · 48,907 cycles
FORWARD ENTRY DOOR JAMB INNER WEB CRACKED AT STATION 200 LONGERON 14L. INSTALLED REPAIR PER EC/RA 5314-01011 AND EA 9-5314-2-A0950.
Part: SKIN — DENTED (STA 232) · airframe 48,907 hrs · 24,085 cycles
INSPECTION FOUND TWO DENTS IN THE FUSELAGE SKIN AT STA 232, LONGERON 17R. THE DENTS WERE REMOVED AND A DOUBLER WAS INSTALLED IAW SRM 53-04, FIGURE 38, 51-10-4, AND 51-30-2.
Earlier reports · 1995–2001 · 24 reports
2001
Part: SPAR — CRACKED (VERTICAL STAB) · airframe 46,481 hrs · 22,777 cycles
INSPECTION FOUND A .5 INCH CRACK IN VERTICAL STABILIZER LT FRONT SPAR AT CANTED FRAME STA 1388. THE CRACK WAS LOCATED NINE INCHES UP FROM BOTTOM END. THE SPAR WAS REPAIRED IAW ECRA 5510-01581.
Part: CLIP — OUT OF ADJ (TAILCONE) · airframe 46,481 hrs · 22,777 cycles
THE INTERIOR TAIL CONE RELEASE HANDLE PULL FORCE WAS EXCESSIVE. THE TAIL CONE HANDLE CLIPS WERE ADJUSTED IAW MM 53-53-00.
Part: CLIP — OUT OF ADJ (TAILCONE) · airframe 46,481 hrs · 22,777 cycles
THE CABIN AFT ENTRY DOOR TAIL CONE RELEASE HANDLE PULL FORCE WAS LOW. THE TAIL CONE HANDLE CLIPS WERE ADJUSTED IAW MM 53-53-00.
Part: CLIP — OUT OF ADJ (TAILCONE) · airframe 46,481 hrs · 22,777 cycles
THE EXTERIOR TAIL CONE RELEASE HANDLE PULL FORCE WAS LOW. THE TAIL CONE HANDLE CLIPS WERE ADJUSTED IAW MM 53-53-00.
Part: FRAME — CRACKED (FUSELAGE) · airframe 46,481 hrs · 22,777 cycles
INSPECTION FOUND A .5 INCH CRACK IN TAIL COMPARTMENT BELTFRAME AT STA 1418, LONGERON 2L TO 2R. REPAIRED IAW DRAWING SR09530003.
Part: BATTERY PACK — DISCHARGED (CABIN) · airframe 46,481 hrs · 22,777 cycles
INSPECTION FOUND FIRST CLASS OVERHEAD EMERGENCY LIGHTS INOPERATIVE. THE EMERGENCY LIGHT BATTERY PACK WAS REMOVED AND REPLACED IAW MM 33-53-00.
Part: WEB — CRACKED (CARGO BAY) · airframe 46,481 hrs · 22,777 cycles
INSPECTION FOUND TWO .5 INCH CRACKS IN FORWARD LOWER SILL PLATE WEB AT AFT BAGGAGE BIN DOOR JAMB AREA. THE SILL PLATE WEB WAS REMOVED AND REPLACED IAW SRM 51-30-0.
Part: PAN — CORRODED (CARGO BAY) · airframe 46,481 hrs · 22,777 cycles
INSPECTION FOUND FORWARD BAGGAGE BIN DOOR PAN CORRODED BETWEEN LOWER DOOR STOPS AT STA 389-408. SPLICES WERE INSTALLED ON FORWARD CARGO DOOR PAN IAW SRM 53-05, FIGURE 44.
1999
Part: CABLES — OUT OF ADJUST (TAIL CONE)
THE TAIL CONE RELEASE PULL WAS BELOW LIMITS WHEN USING INTERIOR OR EXTERIOR TAIL CONE HANDLE. THE CABLES, LATCHES AND CLIPS WERE ADJUSTED IAW MM 53-53-00.
1998
Part: SKIN — DENTED (BS 285)
INSPECTION FOUND A DENT IN FUSELAGE SKIN AND CUSP AT STA 285, LONGERON 18L. A REPAIR WAS INSTALLED IAW ECRA 5330-02752.
Part: PAN — CRACKED (CARGO DOOR)
INSPECTION FOUND A 1 CRACK IN AFT CARGO DOOR PAN. A DOUBLER WAS INSTALLED IAW SRM 52-05, FIGURE 26A.
Part: SEAT TRACK — CORRODED (NR 4 GALLEY)
INSPECTION FOUND NR 4 GALLEY FORWARD AND AFT MOUNT POINT CORRODED IN SEAT TRACK. NEW SECTIONS OF SEAT TRACK WERE INSTALLED IAW SRM 53-05.
Part: SUPPORT — CORRODED (BS 160-200)
INSPECTION FOUND FLOOR SUPPORT CORRODED JUST FORWARD OF LEFT CENTER SEAT TRACK AT STA 160 TO 200. THE FLOOR SUPPORT WAS REPLACED IAW SRM 51-30-2.
Part: BATTERY — DISCHARGED (CABIN)
PORTABLE FLASHLIGHT AT MAIN CABIN DOOR HAS DEAD BATTERY. REPLACED FLASHLIGHT.
1997
Part: RETRACT CYL — MALFUNCTIONED (NLG)
THE NOSE GEAR UNSAFE LIGHT REMAINED ILLUMINATED WHEN GEAR WAS RETRACTED AFTER TAKEOFF. THE GEAR WAS CYCLED, BUT THE LIGHT REMAINED ON AND THE GEAR DOOR LIGHT WAS ON. THE AIRCRAFT WAS RETURNED TO LAS WHERE IT LANDED WITHOUT INCIDENT. THE AIRCRAFT MADE A FERRY FLIGHT TO LAX FOR MAINTENANCE. MAINTENANCE FOUND NO DISCREPANCIES. AN EXTENSION/RETRACTION TEST WAS PERFORMED IAW MM 32-30-00, PAGE 201-206 AND NO FAULTS WERE NOTED. THE NLG RETRACT CYLINDER WAS REMOVED AND REPLACED AS A PRECAUTIONARY MEASURE. LEAK AND OPERATIONAL CHECKS WERE GOOD.
Part: BATTERIES — DISCHARGED (CABIN)
INSPECTION FOUND OVERHEAD EMERGENCY EXIT LIGHTS INOPERATIVE AT ROWS 28, 29, AND 30. THE BATTERIES IN POWER SUPPLY WERE REPLACED.
Part: DOOR JAMB — CRACKED (RT MLG WW)
INSPECTION FOUND A 1.25 INCH CRACK AT LOWER LEG RADIUS OF RT WHEEL WELL FORWARD DOOR JAMB CHANNEL. A DOUBLER WAS FABRICATED AND INSTALLED IAW SRM 51-01, FIGURE 2.
Part: RIB — CRACKED (LT WING LE)
INSPECTION FOUND A 1 INCH CRACK AT AFT UPPER LEADING EDGE RIB BETWEEN NR 5 AND NR 6 SLAT TRACK, LT WING. THE RIB WAS REPAIRED IAW ECRA 5710-01572.
Part: SKIN — CRACKED (NR 2 LE SLAT)
INSPECTION FOUND A .5 INCH CRACK AT RIVET HOLE OF LT WING NR 2 SLAT LOWER SKIN BETWEEN NR 6 AND NR 7 TRACKS. A DOUBLER WAS FABRICATED AND INSTALLED IAW SRM 57-01.
Part: ANGLE — CRACKED (RT DORSAL)
INSPECTION FOUND A .25 INCH CRACK IN VERTICAL LEG OF RIGHT DORSAL ATTACH ANGLE. THE ATTACH ANGLE WAS REMOVED AND REPLACED IAW ECRA 5340-01012.
1996
Part: C7 BLADE — BROKEN (NR 1 ENGINE)
NUMBER 1 ENGINE COMPRESSOR STALLED TWICE THEN FAILED. SHUT DOWN PROCEDURE ACCOMPLISHED. PRELIM INSP FOUND METAL IN THE TAILPIPE. REPLACED NUMBER 1 ENGINE PER MM 71-00-00. *S/D* SHOP FINDINGS REVEALED A BROKEN C-7 BLADE AS THE PRIMARY CAUSE OF ENGINE FAILURE.
Part: BATTERY PACK — LOW VOLTAGE (COCKPIT ENT)
THE COCKPIT ENTRANCE EMERGENCY LIGHTS WERE FOUND VERY DIM DURING A PREFLIGHT INSPECTION. THE COCKPIT EMERGENCY BATTERY PACK WAS REMOVED AND REPLACED AND THE LIGHTS WERE RESTORED TO NORMAL.
1995
Part: CABLES — OUT OF ADJUST (TAILCONE)
HOU - THE EXTERIOR TAILCONE RELEASE HANDLE REQUIRED LESS THAN 25 POUNDS PULL TO RELEASE THE TAILCONE. THE TAILCONE RELEASE CABLES WERE RIGGED IAW MM 53-53-00, SO THAT HANDLE PULL WAS WITHIN SPECIFICATION. (Z)
Part: EEL WIRING — BROKEN (CABIN)
IAH- FLT 0133 - A SECTION OF CABIN AISLE PATH EMERGENCY LIGHTING WAS FOUND INOPERATIVE DURING A PREFLIGHT CHECK. MAINTENANCE REPLACED SOME FAULTY DIODES, BUT THE PROBLEM WAS REPEATED. A BROKEN WIRE WAS FOUND BY ROW 5. THE WIRE WAS REPAIRED AND OPERATION OF THE AISLE PATH LIGHTING WAS RESTORED. (X)