Bridger Aerospace

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: 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: BRACKET — CRACKED (ZONE 100) · airframe 11,998 hrs · 10,962 cycles

LEFT & RIGHT AFT MOUNT BRACKETS ON STRAKES CRACKED/BROKEN. LH PN: 553-26-12-375 RH PN: 553-26-12-376.

Part: NONE — NONE · airframe 10,646 hrs · 5,656 cycles

THE WHEEL AND BRAKES ON THE LH MAIN LANDING GEAR CAUGHT FIRE DURING A LONG TAXI FOR A DEPARTURE. THE INITIAL PICTURES SHOWED ALL COMPONENTS INTACT. THE AIRCRAFT WAS THEN TOWED ON A DOLLY TO THE FBO.

Part: WIRE — BURNED (ZONE 200) · airframe 10,639 hrs · 5,654 cycles

DC POWER SYSTEM WIRE 1P45B TO LH VOLTAGE METER CHAFFED IN OVERHEAD PANEL ON AIRCRAFT STRUCTURE SHORTING TO GROUND. CURRENT HEATED THE WIRE FROM THE VOLTAGE METER IN THE OVERHEAD PANEL TO THE CONTACTOR IN THE JUNCTION BOX LOCATED IN THE AFT EQUIPMENT BAY. THE EXCESSIVE HEAT OF THE WIRE CAUSED THE TWO WIRES GOING TO THE FUSE TO SHORT TOGETHER BYPASSING THE FUSE. WITHOUT CIRCUIT PROTECTION THE WIRE BURNT UNTIL THE WIRE BROKE. HEAT FROM THE AFFECTED WIRE CAUSED DAMAGE TO THE ENTIRE BUNDLE IN THE OVERHEAD PANEL. INSULATION BETWEEN WIRE BUNDLE AND FUSELAGE SKIN WAS BURNT IN TWO LOCATIONS. SYSTEMS AFFECTED INCLUDE DC POWER, ENGINE CONTROL, ENGINE INSTRUMENT, HEATING, DE-ICING AND VENTILATION, LIGHTING, IGNITION, AND WARNING EMERGENCY. THE AIRCRAFT RETURNED FROM FLIGHT 5/16/22 AND THE PILOT REPORTED AN INOP. VOLTAGE METER. THE TROUBLESHOOTING THAT FOLLOWED LED TO THE DISCOVERY OF THE ISSUE.

Part: FUEL — FAULTY · airframe 11,066 hrs · 11,034 cycles

ON LANDING, THE PILOTS NOTICED THE LEFT ENGINE HAD SHUT DOWN. THEY WERE ABLE TO SECURE THE ENGINE AND CLEAR THE RUNWAY, BUT NEEDED TO BE TOWED BACK TO THE MAINTENANCE HANGAR. POST FLIGHT MAINTENANCE RUNS DISCOVERED THE SUSPECTED FAILURE OF THE UNDERSPEED GOVERNOR IN THE FUEL CONTROL UNIT.

Part: ENGINE — FLAMED OUT (NR 1) · airframe 10,658 hrs · 10,829 cycles

162AL WAS ON A NON-REVENUE REPOSITIONING FLIGHT FROM BZN TO MSO FOR TRAINING, ONE CREW ON BOARD (PILOT), NO PASSENGERS. THE PILOT NOTICED #1 ENGINE INSTRUMENTS INDICATED A ROLL BACK ON SHORT FINAL AFTER EXITING ICING CONDITIONS, THE PILOT LANDED STRAIGHT AHEAD WITHOUT INCIDENT. ALL AIRCRAFT SYSTEMS FOUND OPERATIONAL AFTER MAINTENANCE INSPECTION AND MAINTENANCE TEST FLIGHT. FLAME OUT SUSPECTED DUE TO ICE INGESTION.

Part: SKIN — CRACKED (VERTICAL STAB) · airframe 6,236 hrs · 6,804 cycles

FOUND CRACK IN VERTICAL TAIL SKIN ABOVE "PYRAMID" IN DOUBLER. INSTALLED 5" ACCESS HOLE IN LH VERTICAL SKIN IN REFERENCE TO GTEC, INC ENGINEERING. FOUND MID SPAR CRACKED ON RH SIDE OPPOSITE OF CRACK IN SKIN. INSTALLED A DOUBLER ON THE LH AND RH FLANGE OF THE MID SPAR.