NTSB investigations · 1
Matched to this aircraft by N223AC and the event date: up to this one’s cancellation.
Service difficulty reports · 11
Matched to this aircraft by N-number and event date, checked against the reported serial number, make and model.
SDR MDR04043Compressor Wheel · crackedA CRACK WAS FOUND IN THE BLADE RETENTION HOLE OF THE 2ND STAGE COMPRESSOR DISK. COMPRESSOR SN 677782, WAS REMOVED FOR HSI/OVERHAUL. DURING THE INSPECTION PROCESS, NDT DETECTED A CRACK IN THE BLADE RETENTION HOLE, CENTER LAND USING EDDY CURRENT. THE CRACK WASDR JYD2004F00003Compressor Wheel · crackedA CRACK WAS FOUND IN THE BLADE RETENTION HOLE OF THE 2ND STAGE COMPRESSOR DISK. COMPRESSOR, SN 677782, WAS REMOVED FOR HSI/OVERHAUL. DURING THE INSPECTION PROCESS, NDT DETECTED A CRACK IN THE BLADE RETENTION HOLE, CENTER LAND USING EDDY CURRENT. THE CRACK WSDR MDR03036Housing · crackedTHE TGB CENTER HOUSING WAS FOUND CRACKED WHILE INSTALLED ON THE AIRCRAFT. IT WAS REMOVED PREMATURELY ON DECEMBER 20, 2000. THE SHOP DETECTED THE CRACK VISUALLY. THE CRACK BEGAN AT THE SECOND ROSAN STUD CLOCKWISE FROM THE ROSAN SEAT PAD LOCATED 34 DEGREES FRSDR MDR03029Housing · crackedTGB CTR HSG FOUND CRACKED WHILE INSTALLED ON AC. IT WAS REMOVED PREMATURELY HAVING A TSO OF 974.7 HR. VISUALLY DETECTED INDIC IN OB WEB OF LT MOUNTING LUG. HSG WAS LOCALLY FPI INSPECTED TO VERIFY. NO IND WAS NOTED. AREA WAS STRIPPED, LIGHTLY ABRADED WITH SSDR MDR03018Strap · crackedTHE STRAP IS CRACKED N THE OUTBOARD SIDE OF THE BLADE, APPROXIMATELY 9.125 INCHES FROM THE TRAILING EDGE. THE CRACK STARTS AT THE CUFF END OF THE BLADE AND EXTENDS APPROXIMATELY 1.25 INCHES TOWARDS THE TIP END OF THE BLADE. THE CRACK STARTS WHERE THE BACK WASDR JYD2002F00003Spar · crackedMAIN ROTOR BLADE CRACKED. DURING POST-FLIGHT INSPECTION, AND REQUIRED COMPLIANCE WITH SB, (BLADE INSPECTION METHOD) INDICATION WAS FOUND ON BLADE (SN 64M-6547-5926) BLADE WAS REMOVED. CRACK WAS DETECTED ON TOP SIDE BETWEEN POCKET NR8 AND NR9. CRACK LENGTH ASDR JYD2002F00002Disk · crackedCRACK FOUND IN BLADE PIN RETENTION HOLE OF 2ND STAGE COMPRESSOR DISK. COMPRESSOR (SN 677810) REMOVED FOR OVERHAUL. DURING INSPECTION PROCESS, NDT DETECTED A CRACK IN BLADE PIN RETENTION HOLE, CENTER LAND, USING EDDY CURRENT. CRACK VERIFIED BY FMPI. HOLDINGSDR JYD2002F00000Spar · crackedCRACK WAS FOUND ON THE TIP END OF MAIN ROTOR BLADE SPAR (PN 641520504102/ SN 64-65325910). DURING POST FLIGHT INSPECTION, FIELD CREW VISUALLY DETECTED A CRACK INDICATION ON TOP SIDE OF SPAR. TOTAL CRACK LENGTH IS APPROX. 2 INCHES LONG WITH 1.5 INCHES EXTENDSDR JYD2001F00000Hinge Pin · crackedS-64F MAIN ROTOR HEAD HINGE PINS DO OCCASIONALLY CRACK FROM DAMPER NUT SAFETY HOLES (APPROX 15 PER CENT OF THE TIME), BUT TYPICALLY THE CRACKS TRAVEL OUTBOARD TO THE EDGE OF THE HINGE PIN. HINGE PIN SN A04100236 CRACKED INBOARD THROUGH THE THREADS INTO THE THSDR 20010606CW005Hinge Pin · crackedS-64F MAIN ROTOR HEAD HINGE PINS DO OCCASIONALLY CRACK FROM DAMPER NUT SAFETY HOLES (APPROX. 15 PERCENT OF THE TIME), BUT TYPICALLY THE CRACKS TRAVEL OUTBOARD TO THE EDGE OF THE HINGE PIN. HINGE PIN SN A041-00236 CRACKED INBOARD THROUGH THE THREADS INTO THE TSDR 20010427CW007Shaft · crackedDURING OVERHAUL, MAGNETIC PARTICLE INSPECTION REVEALED MULTIPLE INDICATION IN THE LOWER SPLINE AREA OF MAIN ROTOR SHAFT. LONGEST INDICATION MEASURED APPROX .500 INCH IN LENGTH, BEGINNING IN THE ROOT AREA EXTENDING OVER SPLINE FACE, DOWN TO THE NEXT ADJACENT R
Other aircraft with N223AC · 1
The FAA can assign a mark to another aircraft once a registration is cancelled. N223AC is registered now to the first aircraft listed.