N401TZ
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.
17 reports on file, 2006-11-11 – 2007-11-28.
Part: SPAR — CRACKED · airframe 46,892 hrs · 32,847 cycles
REPAIRED VERTICAL CRACK FROM HOLE C-DOWN TO EDGE OF CUT OUT OF LT REAR SPAR UPPER CHORD BY OVERSIZING HOLE, FABRICATING AND INSTALLING BUSHING IAW REO-L0152 REV IR DATED 11-21-07 FAA FORM 8100-9. THIS IS A TIME LIMITED REPAIR, REPEAT INSPECTION REQUIRED AT 4500 AIRCRAFT CYCLES.
Part: BATTERY — UNSERVICEABLE (EMERGENCY LIGHTS) · airframe 46,636 hrs · 32,709 cycles
EGRESS LIGHTS AT R-2 DOOR REMAIN ON RESET, NO HELP. REMOVED AND REPLACED CHARGER IAW AMM AT R-2 DOOR O/H. OPS CHECKS GOOD. (K)
Part: UNKNOWN — MALFUNCTIONED (CABIN PRESSURE)
DURING CLIMB PRESS DIFF INCREASED TO 7.0 AT 26000 FT (5000 FT CABIN) DIFF REMAINED AT 7.0 AS AIRCRAFT AND CABIN CONTINUED TO CLIMB UNTIL AT 34,000 FT, DIFF WAS STILL 7.0 AND CABIN WAS 8500 FT, ABOVE 34,000 FT DIFF BEGAN TO INCREASE, PERFORMED AMM 21-31-00 SYS TEST OK. PRESSURIZE AC TO 8.5 PSI AC MAINTAIN PRESS, NO LEAKS NOTED, INSPECTED ALL DOORS, WINDOWS NO LEAKS NOTED. (K)
Part: UNKNOWN — UNKNOWN (CABIN PRESSURE)
CABIN ALTITUDE WARNING HORN SOUNDED WHILE CLIMBING THROUGH FL 360. DONNED OX MASK, REQUESTED DESCENT AND WHILE PERFORMING CHECK LIST THE CABIN BEGAN TO DESCEND AND PRESSURIZATION WAS RESTORED. VISUALLY INSPECTED AFT PRESSURE BULKHEAD SEAL, NO DEFECTS NOTED. PERFORMED PRESS CONTROL SYS OPERATIONAL TEST IAW MM 21-31-00, PGS 201-205. OPS CHECK STATIS OK FOR SERVICE. (K)
Earlier reports · 2006 · 13 reports
2006
Part: SKIN — DENTED (CARGO DOOR) · airframe 44,360 hrs · 31,411 cycles
FWD CARGO DOOR SKIN HAS DENTS LOCATED 14.0 INCHES FROM FWD ENTRY AND 26.0 INCH FROM BOTTOM EDGE FOUND DENTS OUT OF LIMITS. C/W ERA 733-52N-6054 REPAIR IS CONSIDERED A TIME LIMITED REPAIR FOR 24 MONTHS FROM THE REF C APPROVAL DATE WITH A DETAILED INSPECTION EVERY 1000 FLIGHT CYCLES AND MUST BE REPLACED WITH A PERM REPAIR BY RESKIN OF THE DOOR THE REPEAT INSPECTION. (K)
Part: POST — CORRODED (FUSELAGE) · airframe 44,268 hrs · 31,355 cycles
AFT LAV POST HAS CORROSION AT LWR END. REPLACED AFT LAV FWD POST IAW EA, STA 1000, LBL 12. (K)
Part: STRAP — CORRODED (FUSELAGE) · airframe 44,268 hrs · 31,355 cycles
AFT CARGO COMP BETWEEN STA 772, WL 155.5 AND BL 13R STRAP CORROSION. REMOVED CORROSION ORIGINAL MATERIAL THICKNESS 063, MATERIAL LOSS 005, WITHIN LIMITS IAW SRM. TREATED AND PRIMED AREA.
Part: FLOOR PANEL — CORRODED (FUSELAGE) · airframe 44,268 hrs · 31,355 cycles
FWD CARGO BAY, THE FWD PORTION OF THE LT TRAP FOR THE FLOOR PANEL IS CORRODED. F/S 472-500, LBL 22. REMOVED CORROSION IAW 53-30-53, ORIGINAL THICKNESS IS 063, REMAINING MATERIAL THICKNESS IS .060 AND FOUND TO BE WITHIN LIMITS IAW SRM 53-30-53, FIG 101. (K)
Part: STRAP — CORRODED (FUSELAGE) · airframe 44,268 hrs · 31,355 cycles
AFT CARGO BAY, LT NR 3 FLOOR STRAP IS CORRODED AS MARKED. F/S 814, LBL 22 (UNDERSIDE). REMOVED CORROSION ON AFT CARGO BAY LT NR 3 FLOOR STRAP F/S 814, LBL 22, IAW MM 51-21-31. ORIGINAL MATERIAL THICKNESS IS 071, MATERIAL LOSS IS .004 AREA FOUND TO BE WITHIN LIMITS IAW SRM 53-60-53. (K)
Part: STRAP — CORRODED (FUSELAGE) · airframe 44,268 hrs · 31,355 cycles
AFT CARGO BAY, LT NR 2 FLOOR STRAP IS CORRODED ON LOWER SIDE THROUGHOUT ITS LENGTH. F/S 727D TO 767 LBL 22. REMOVED CORROSION ON AFT CARGO BAY LT NR 2 FLOOR STRAP F/S 727D TO 767, LBL22 IAW MM. ORIGINAL THICKNESS IS 071, MATERIAL LOSS 014, MAX ALLOWABLE LOSS 007 OUT OF LIMITS IAW SRM. FABRICATED NEW FLOOR STRAP IAW 51-40-05/08. (K)
Part: FLOOR PANEL — CORRODED (CARGO BAY) · airframe 44,268 hrs · 31,355 cycles
AFT CARGO FLOOR PANEL 1534X HAS CORROSION AROUND FASTENER HOLES ON FORWARD F/S 727 TO 732, LBL 20 TO RBL 20 ON ITS UPPER SURFACE. BLENDED AREA AT AFT CARGO FLOOR PANEL 1534X AROUND FASTENER HOLES ON FORWARD END UPPER SURFACE. ORIGINAL THICKNESS IS 080, BLENDED AREA IS L=42 BY W=2 MAX MATERIAL LOSS IS 003 AND IS WITHIN LIMITS IAW SRM 53-30-53, FIG 101. (K)
Part: STRAP — CORRODED (FUSELAGE) · airframe 44,268 hrs · 31,355 cycles
FORWARD CARGO BAY, RT STRAP HAS VISIBLE CORROSION THROUGHOUT F/S 472.5 TO 500 RBL 22. REMOVED CORROSION FROM RT STRAP AT F/S 472.5 TO 500 RBL 22.0 IAW SRM 53-30-53 ORIG MATERIAL THK .063, MATERIAL LOSS .003 WITHIN LIMITS IAW SRM. (K)
Part: FLOOR PANEL — CORRODED (CARGO BAY) · airframe 44,268 hrs · 31,355 cycles
AFT CARGO FLOOR PANEL 1538X HAS CORROSION ALONG EDGE OF PART AS MARKED F/S 946 TO 948, LBL 22 TO RBL 22, UPPER SURFACE. BLENDED AREA, MATERIAL THICKNESS 080, MAX MATERIAL LOSS IS 003 WITHIN LIMITS IAW SRM, FIG 101. TREATED AND PRIMED ARA IAW SRM. (K)
Part: FLOOR PANEL — CORRODED (CARGO BAY)
AFT CARGO FLOOR PANEL 1536X IS CORRODED ESPECIALLY AT DOOR THRESHOLD AREA F/S 767 TO 789 RBL 17 TO 22.0 UPPER SURFACE. BLENDED OUT CORROSION ON UPPER SURFACE OF FLOOR PANEL IAW 53-30-53 WITHIN LIMITS. ORIGINAL MATERIAL .071 MATERIAL LOSS .005. (K)
Part: STRAP — CORRODED (FUSELAGE) · airframe 44,268 hrs · 31,355 cycles
AFT CARGO RT SIDE NR 2 FLOOR STRAP IS CORRODED THROUGHOUT F/S 727D TO 767, RBL 22. REMOVED CORROSION FROM RT NR 2 FLOOR STRAP IN AFT CARGO FROM F/S 727D TO 767, RL 22 IAW B737-300, MM 51-21-31. ORIGINAL THICKNESS IS 071, MATERIAL LOSS IS 016. MAX ALLOWABLE IS 007, OUT OF LIMITS IAW 53-60-53. FAB NEW STRAP IAW SRM 53-60-53. (K)
Part: FLOOR PANEL — CORRODED (FUSELAGE) · airframe 44,268 hrs · 31,355 cycles
AFT CARGO FLOOR PANEL 1535X HAS CORROSION ON EDGES OF THE UPPER SURFACE AS MARKED. REMOVED CORROSION ON FLOOR PANEL 1535X IAW SRM 53-30-53 FIG 101. ORIGINAL THICKNESS IS 080 ENDING THICKNESS IS 076 MATERIAL LOSS IS 004 AND FOUND TO BE WITHIN LIMITS. (K)
Part: SEAT TRACK — CORRODED (FUSELAGE) · airframe 44,268 hrs · 31,355 cycles
CORROSION ON SEAT TRACK IN AFT GALLEY FLOOR BETWEEN COMP 411 ON TOP OF LUGS AND INSIDE TRACK STA 986 TO STA 1016, RBL 16. REMOVED CORROSION .006 MATERIAL LOSS WITHIN LIMITS IAW SRM. TREATED PRIMED AREAS IAW SRM. (K)