Safety record in brief:1 NTSB accident (substantial damage, Feb 2021)13 ADs may apply9 service difficulty reports
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The pilot’s improper decision to approach the airport and enter a low altitude hover with a gusting quartering tailwind, which resulted in a loss of tail rotor effectiveness during a turn at a low altitude.
From NTSB records; matched by serial number.Read NTSB report (search CAROL for CEN21LA153)
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 |
|---|---|---|---|
| 2016-25-13 | Safran Helicopter Engines, S.A. (Formerly Turbomeca S.A.) Turboshaft Engines | Feb 3, 2017 | Engine (ARRIEL 2B1)Only with: Engine accessory gearbox (AGB) P/N 0292120650 with a machined front casing installed. |
| 2015-13-04 | Turbomeca S.A. Turboshaft Engines | Sep 1, 2015 | Engine (ARRIEL 2B1) |
| 2014-12-05 | Turbomeca S.A. Turboshaft Engines | Aug 4, 2014 | Engine (ARRIEL 2B1) |
| 2014-07-06 | Turbomeca S.A. Turboshaft Engines | May 15, 2014 | Engine (ARRIEL 2B1)Only with: Engines that do not have modification TU157 incorporated. |
| 2012-18-18 | Turbomeca S.A. Turboshaft Engines | Oct 24, 2012 | Engine (ARRIEL 2B1)Only with: Engines not modified by TU166 modification. |
| AD | Subject | Effective | Applies to |
|---|---|---|---|
| 2012-03-11 | Turbomeca S.A. Turboshaft Engines | Mar 20, 2012 | Engine (ARRIEL 2B1) |
| 2011-06-07 | Eurocopter France (Eurocopter) Model EC130 B4 Helicopters | Apr 6, 2011 | Airframe (EC 130 B4)Only with: Flotation gear unit "1G" (1G unit), P/N 350A63256300, installed. |
| 2009-09-03 | Turbomeca S.A. Arriel 2B and 2B1 Turboshaft Engines | Jun 1, 2009 | Engine (ARRIEL 2B1) |
| 2009-08-08 | Turbomeca Arriel 1B, 1D, 1D1, 2B, and 2B1 Turboshaft Engines | Apr 29, 2009 | Engine (ARRIEL 2B1)Serial numbers per Figure 1 of Turbomeca Alert MSB No. A292 72 0827, Version A (Arriel 1B/1D/1D1) and Figure 1 of Turbomeca Alert MSB No. A292 72 2833, Version A (Arriel 2B/2B1), both dated March 20, 2009. Only with: Engines with power turbine modules M04 installed, as listed by SN in the referenced service bulletins. |
| 2009-01-11 | Turbomeca Arriel 2B and 2B1 Turboshaft Engines | Feb 27, 2009 | Engine (ARRIEL 2B1) |
| 2007-19-09 | Turbomeca Arriel 2B1 Turboshaft Engines | Oct 3, 2007 | Engine (ARRIEL 2B1) |
| 2007-10-06 | Turbomeca Arriel 2B1 Turboshaft Engines | May 29, 2007 | Engine (ARRIEL 2B1) |
| 2005-25-13 | Turbomeca Arriel 2B and 2B1 Turboshaft Engines | Dec 28, 2005 | Engine (ARRIEL 2B1)Only with: Engines without modification TU22 incorporated. |
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.
DAMAGE WAS NOTED TO THE X1790.15 FRAME (PN: 350A21-4099) IN THE FORM OF A CHAFE DAMAGE AREA. THE CHAFE DAMAGE IS LOCATED NEAR THE INBOARD RH CAMLOC AND WAS MEASURED TO BE APPROXIMATELY 0.70” X 0.175
From FAA Service Difficulty Reports; matched by N-number and serial number.DAMAGE TO THE AFT LANDING GEAR FITTING (P/N: 350A21-4674.20) IN THE FORM OF A GOUGE / CHAFE. THE DAMAGE IS AT THE TWO HOLES OF THE TWIN CLEVIS, AND WAS MEASURED TO BE APPROXIMATELY 10.381MM (0.409”). THE BOLT HOLE IS ORIGINALLY 10JS13 MM (10.0MM (+/- 0.11)) DIAMETER (0.394” (+/-0.004”)).
From FAA Service Difficulty Reports; matched by N-number and serial number.DAMAGE TO THE FWD BULKHEAD LH PANEL (PN: 350A21-4444.21) IN THE FORM OF 3EA CHAFED AREAS IN THE PART; 2EA OF WHICH ARE LOCATED NEAR STIFFENING FEATURES, AND 1EA IS LOCATED NEAR THE INBOARD EOP. THE 2EA CHAFE DAMAGE AREAS NEAR THE STIFFENING FEATURES WERE MEASURED TO BE APPROXIMATELY 0.15” X 0.05”…
From FAA Service Difficulty Reports; matched by N-number and serial number.DAMAGE TO THE TAIL BOOM LH SKIN (P/N: 350A23-4288.20) IN THE FORM OF A CHAFE DUE TO DRILL START LOCATED AT LOWER FORWARD SIDE OF THE AFT BATTERY BOX AREA. THE DAMAGE MEASURED TO BE APPROXIMATELY 0.1285” X 0.1285” AND 0.0175” DEEP.
From FAA Service Difficulty Reports; matched by N-number and serial number.DURING AAIP A1660 600HR SCHEDULED INSPECTION IT WAS DISCOVERED THAT THE WEB @ STA. 845 RBL 673.5 HAS A CRACK APPROX 2.50 INCHES ON TOP R/H SIDE IN WHICH IS ALMOST IDENTICAL TO EA 17-5310-EA-2632 DATED 01/23/2019 FOR ACFT. 7248. THIS CRACK IS BEYOND LIMITS TO STOP DRILL AND REQUIRES STRUCTUAL SHEET…
From FAA Service Difficulty Reports; matched by N-number and serial number.THE AIRCRAFT FUEL QUANTITY READING DECREASED RAPIDLY IN FLIGHT ON THE VEMD CAUSING THE PILOT TO PERFORM A PRECAUTIONARY LANDING. THE CAUSE WAS THE AFT HOSE FROM THE FUEL SYSTEM NORMALLY PROTRUDING FROM THE BELLY OF THE AIRCRAFT DIRECTLY BELOW THE FUEL CELL WAS CAUGHT AT AN ANGLE IN THE BELLY…
From FAA Service Difficulty Reports; matched by N-number and serial number.DURING A 300 HOUR INSPECTION OF THE HORIZONTAL STABILIZER, FOUND THE UPPER RT ATTACH FITTING BROKEN, AND THE FRAME IN THE TAILBOOM CRACKED.
From FAA Service Difficulty Reports; matched by N-number and serial number.THE PILOT REPORTED THAT UPON TAKEOFF WITH CREW & PATIENT ONBOARD HE HEARD A WARNING TONE AS HE WAS CLIMBING & TRANSITIONING TO FWD FLIGHT. HE IMMEDIATELY REDUCED POWER & GLANCED AT THE CAUTION & WARNING PANEL & VEMD. THERE WAS AN EXCEEDANCE DETECTED INDICATION THAT WAS OBSERVED. THE PILOT…
From FAA Service Difficulty Reports; matched by N-number and serial number.DURING AIR WORTHINESS CHECK, MECHANIC FOUND A CRACK ABOUT 1.5 INCH LONG IN THE UPPER RT CORNER OF THE BATTERY COMPARTMENT ACCESS DOOR OPENING. THE CRACK WAS ORIGINALLY NOTICED IN THE DOUBLER AND UPON FURTHER INSPECTION FOUND A CRACK IN THE SKIN BENEATH THE DOUBLER. OPEN
From FAA Service Difficulty Reports; matched by N-number and serial number.