Safety record in brief:1 NTSB accident (substantial damage, Feb 2014)3 ADs may apply3 service difficulty reports
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Individual owners are shown by city and state only.
The pilot's failure to maintain clearance from a power pole during low-altitude maneuvering flight.
From NTSB records; matched by serial number.Read NTSB report (search CAROL for WPR14CA115)
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 |
|---|---|---|---|
| 2009-12-01 | Bell Helicopter Textron, Inc. Model 47, 47B, 47B3, 47D, 47D1, 47E, 47G, 47G-2, 47G-2A… | Jun 29, 2009 | Airframe (47G-5A)Only with: Main rotor blade installed: P/N 047-110-250-021 with S/N A-303, A-304, A-312, or A-316; or P/N 047-110-250-023 with S/N A-298, A-301, or A-305. |
| 2001-17-17 | Bell Helicopter Textron, Inc. Model 47B, 47B-3, 47D, 47D-1, 47G, 47G-2, 47G2A, 47G-2A-1… | Aug 29, 2001 | Airframe (47G-5A)Only with: Main rotor blade grips P/N 47-120-135-2, 47-120-135-3, 47-120-135-5, 47-120-252-1, 47-120-252-7, 47-120-252-11, 74-120-252-11, 74-120-135-5, R47-120-252-11, or R47-120-135-5 installed. |
| 98-07-09 | Bell Helicopter Textron, Inc. Model 47B, 47B-3, 47D, 47D-1, 47G, 47G-2, 47G-2A… | May 6, 1998 | Airframe (47G-5A) |
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.
MAGNETO IDLER GEAR SHAFT BROKE, THE BREAK WAS CAUSED BY A WORN BUSHING ON THE GEAR/SHAFT P/N'S 76091 & 76283 THAT DRIVES IT. THIS IS THE SECOND TIME THIS SHAFT BROKE. TOTAL TIME SINCE OVERHAUL 230 HOURS.
From FAA Service Difficulty Reports; matched by N-number and serial number.MAGNETO DRIVE IDLER GEAR SHAFT FAILED CAUSING BOTH MAGNETOS TO BECOME INOPERATIVE AND THE ENGINE FAILED. THE FAILURE APPEARED TO ORIGINATE AT THE OIL HOLE. TOTAL TIME ON THE ENGINE WAS 4600 HOURS AND TOTAL TIME ON THE PART PROBABLY WAS 4600 HOURS AND THE ENGINE TSO 220 HOURS. THERE WAS NO…
From FAA Service Difficulty Reports; matched by N-number and serial number.DURING 100-HOUR ANNUAL INSPECTION, CRACK NOTED AT FORWARD TRUNNION CLUSTER. AREA WAS STRIPPED OF PAINT AND DYE CHECKED. CRACK CONFIRMED. A BULLETIN WAS ISSUED BY THE MFG 3-7-96. THIS WAS A PMA'D PART.
From FAA Service Difficulty Reports; matched by N-number and serial number.