N419BT
Registered owner: BRIDGER AIR TANKER 4 LLC, MT (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.
9 reports on file, 2021-08-31 – 2026-02-04.
Part: ANGLE — CRACKED (ZONE 600) · airframe 6,553 hrs
RIGHT WING IN PNL 841-20 DOUBLER BEHIND VERTICAL ANGLE HAS 3/4 INCH LONG CRACK FS 434 BL 51
Part: PUMP — FAILED (ZONE 100) · airframe 6,553 hrs
RIGHT ENGINE DRIVEN HYDRAULIC PUMP REQUIRES REPAIR OR REPLACEMENT. THE HYDRAULIC PUMP WAS REMOVED & INSTALLED IAW PSP 392 29-11-12 AND SB 215-3134.
Part: SPAR CAP — FAILED (ZONE 300) · airframe 6,553 hrs
R/H FWD HORIZONTAL STABILIZER LOWER SPAR CAP FOUND CRACKED INBOARD OF FINLET ATTACH BRACKET NDT SERVICES FOR RH HORIZONTAL STABILIZER LOWER SPAR CAP CRACK- INSPECTION OF CUT IN SPAR MADE DURING REPAIR. REFER TO 250031-28 FOR ORIGINAL REPAIR RD215-55-47. R/H LOWER SPAR CAP HFEC INSPECTION C/O BY APEX INSPECTIONS ON ATTACHED APEX INSP. WO#20251104JR2 IAW DHC RD215-55-47ISSUE 1 GENERAL NOTE 8. NO DEFECTS NOTED
Part: DRAG ANGLE — FAILED (ZONE 500) · airframe 6,553 hrs
LEFT FWD WING TO FUSELAGE DRAG ANGLE FOUND CRACKED. LT REAR WING TO FUSELAGE DRAG ANGLE CRACKED IN RH AFT WING DOULBLER BEHIND ANGLE IS CRACK: PERFORM AN EDDY CURRENT INSPECTION TO DETECT CRACKING OF THE FUSELAGE FRAME ANGLES AT THE WING FRONT AND REAR SPAR ATTACHMENT TO THE FUSELAGE, IN ACCORDANCE WITH ALERT SERVICE BULLETIN 215-A476, REVISION 4, DATED AUGUST 18, 2000, AT INTERVALS NOT TO EXCEED 415 FLIGHT HOURS OR 1,500 WATER DROPS, WHICHEVER OCCURS FIRST. TASK WORK ORDER 250031 - 421 AND 381
Part: PUMP — MAKING METAL (ZONE 500) · airframe 6,548 hrs · 2,898 cycles
HYDRAULIC SYSTEM FOUND CONTAMINATED WITH METAL FROM FAILED L/H ENGINE-DRIVEN HYDRAULIC PUMP.
Part: SWITCH — INOPERATIVE (CENTER SWITCH) · airframe 5,381 hrs · 2,461 cycles
AIRCRAFT NLG DID NOT RETRACT AFTER TAKEOFF. ABLE TO LAND WITHOUT INCIDENT. UPON INSPECTION, TECHNICIANS FOUND CENTERING SWITCH OUT OF ADJUSTMENT. TECHNICIANS CORRECTED SWITCH. AIRCRAFT MAY HAVE EXPERIENCED A LANDING GEAR OVERSPEED CONDITION SO AN INSPECTION WAS PLANNED AND CONDUCTED. OEM TECH SUPPORT INSTRUCTED TECHNICIANS TO HAVE NOSE LANDING GEAR ATTACHMENT NDT INSPECTED. UPON REMOVAL OF HARDWARE, FOUND THE 2 UPPER NUTPLATES THAT SECURE THE BOLTS THAT ATTACH THE FITTING-HINGE FWD (RH) P/N- 215-34129-1, HAD STRIPPED THREADS. THESE BOLTS WERE NOT FOUND TO HAVE DAMAGED THREADS AND WERE HELD IN PLACE BY LOCTITE ONLY, AS THE NUTPLATE THREADS WERE COMPLETELY STRIPPED!
Part: DRAG ANGLE — CRACKED · airframe 5,352 hrs · 2,445 cycles
R/H H-STAB LOWER FINLET L/H DRAG ANGLE CRACKED
Part: DRAG ANGLE — CRACKED (ZONE 300) · airframe 5,352 hrs · 2,445 cycles
R/H H-STAB LOWER FINLET R/H DRAG ANGLE CRACKED.
Part: SWITCH — FOD (FLAP SYSTEM) · airframe 5,250 hrs · 2,428 cycles
COMING OFF A SCOOP, FLAPS WERE SELECTED 0 FROM 10, AFTER THE SELECTOR WAS MOVED THE INDICATOR STILL SHOWED 10 FLAPS. A VISUAL INSPECTION FROM BOTH PILOTS VERIFIED THE FLAPS WERE STILL AT 10. THE ABNORMAL CHECKLIST WAS RUN AND WE PROCEEDED BACK TO KCIC FOR MAINTENANCE. ROOT CAUSE OF NON-MOVEMENT OF THE SELECTOR SWITCH WAS DETERMINED TO BE F.O.D. ON THE SWITCH LEVER. WITH F.O.D. REMOVED, THERE WAS NORMAL MOVEMENT OF THE SELECTOR SWITCH. ENE