Safety record in brief:1 NTSB accident (substantial damage, Jul 2018)6 ADs may apply6 service difficulty reports
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The pilot's inability to maintain yaw control while transitioning to an out of ground effect hover due to a loss of tail rotor effectiveness.
From NTSB records; matched by serial number.Read NTSB report (search CAROL for ERA18LA192)
These match the airframe or engine model. Whether each one applies, and whether it's been complied with, depends on serial numbers, equipment and logbook entries. Applicability must be confirmed by a mechanic against the aircraft's records.
| AD | Subject | Effective | Applies to |
|---|---|---|---|
| 2015-23-01 | Sikorsky Aircraft Corporation (Type Certificate Previously Held by Schweizer Aircraft… | Dec 15, 2015 | Airframe (269D) |
| 2015-11-09 | Sikorsky Aircraft Corporation (Type Certificate Previously Held by Schweizer Aircraft… | Jul 14, 2015 | Airframe (269D)Only with: Ring gear carrier assembly P/N 269A5194 installed. |
| 2010-16-08 | Schweizer Aircraft Corporation (Schweizer) Model 269D Helicopters | Aug 20, 2010 | Airframe (269D) |
| 2003-09-05 | Schweizer Aircraft Corporation Model 269D Helicopters | May 16, 2003 | Airframe (269D)Certain serial numbers: 269D 0001–0022. Only with: Aluminum horizontal stabilizer endplate P/N 269D3413-11 installed. |
| 99-17-10 | Schweizer Aircraft Corporation Model 269A, 269A-1, 269B, 269C, 269C-1, and 269D… | Sep 2, 1999 | Airframe (269D)Only with: Tail rotor swashplate shaft P/N 269A6049-3 installed. |
| AD | Subject | Effective | Applies to |
|---|---|---|---|
| 98-26-06 | Schweizer Aircraft Corporation Model 269D Helicopters | Feb 3, 1999 | Airframe (269D)Only with: Large diameter main rotor hub P/N 269A1002-11 and main rotor drive shaft P/N 269A5305-139, -143, -145, or -147 installed. |
AI-extracted — verify against original. Matched from each AD's applicability section; ADs replaced by a later AD are left out.
Reports of failures and defects that operators and repair stations sent to the FAA since 1995. A report describes one finding; it is not an accident.
UPON INSP OF TAIL ROTOR DAMPER ASSY, CRACK WAS FOUND IN SUPPORT BRACKET ASSY. (PN 269A332511) STOPPED DRILLED CRACK AND REPAIRED WITH A DOUBLER USING 2024T3 .025 FOR REINFORCEMENT PRO SEALED AND RIVETED IN PLACE. (K)
From FAA Service Difficulty Reports; matched by N-number and serial number.UPON INSPECTION OF OIL COOLER FAN ASSY, FOUND MANY CRACKS AROUND THE TOP MOUNT OF SCROLL ASSY. (K)
From FAA Service Difficulty Reports; matched by N-number and serial number.UPON INSPECTION OF OIL COOLER FAN ASSY FOUND MANY CRACKS AROUND THE TOP MOUNT OF SCROLL ASSY. (K)
From FAA Service Difficulty Reports; matched by N-number and serial number.UPON LANDING THE HELICOPTER IN A SLIGHT FWD AND LT MOTION IN FLAT GRASS AREA HEARD SLIGHT CLICK OR CLUNK, PIC DIDN`T SEE ANY DAMAGE, PICKED UP AIRCRAFT TO A HOVER AND GROUND CREW SAW FWD END OF LT SKID TUBE HANGING BELOW THE AIRCRAFT. (K)
From FAA Service Difficulty Reports; matched by N-number and serial number.DURING PRACTICE AUTOROTATION, ENGINE SHUTDOWN DUE TO THROTTLE INADVERTENTLY CLOSING INTO FUEL CUTOFF POSITION. STUDENT`S LEG CONTACTED IDLE, IDLE RELEASE BUTTON ON COLLECTIVE STICK HEAD AND THIS ALLOWED THROTTLE TO ROTATE BEYOND IDLE POSITION. HAVE CONTACTED THE AIRCRAFT MFG PREVIOUSLY DUE TO…
From FAA Service Difficulty Reports; matched by N-number and serial number.FUEL LEAKAGE WAS DETECTED ON BOTH FUEL TANK SUMP PLATES. RH FUEL SUMP PLATE LEAKAGE WAS DRIPPING ONTO FIRESHIELD ABOVE EXHAUST DUCT (ENGINE EXHAUST). SUMP PLATES FASTENERS FOUND WITH CORRECT TORQUE. MOST LIKELY CAUSE IS AGING OF SEALANT BETWEEN CELL AND SUMP PLATES. (MIL-S- 8784B 1/2). SUGGESTION:…
From FAA Service Difficulty Reports; matched by N-number and serial number.