Hard landing Accident Agusta A119 N119AH, Thursday 22 October 2009
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Date:Thursday 22 October 2009
Time:19:20 LT
Type:Silhouette image of generic A119 model; specific model in this crash may look slightly different    
Agusta A119
Owner/operator:Tristate Careflight LLC
Registration: N119AH
MSN: 14022
Year of manufacture:2001
Total airframe hrs:4122 hours
Engine model:Pratt & Whitney Canada PT6B-37A
Fatalities:Fatalities: 0 / Occupants: 5
Other fatalities:0
Aircraft damage: Substantial
Location:Blythe, California -   United States of America
Phase: En route
Departure airport:Blythe Airport, CA (BLH/KBLH)
Destination airport:Palm Springs, CA (7CA4)
Investigating agency: NTSB
Confidence Rating: Accident investigation report completed and information captured
During the emergency medical service (EMS) flight, while enroute at 4,500 feet mean sea level, the pilot heard a change in the sound of the main rotor system, followed by a vibration in the cyclic. He applied aft cyclic to slow the helicopter and noticed the rotor rpm starting to decay. After he lowered the collective in an attempt to regain rotor rpm everything appeared to stabilize. The pilot then increased the collective to see if he could re-establish cruise power, but the increase in collective resulted in the low rotor aural warning activating. When the pilot lowered the collective, the warning went out, and when he tried to maintain rotor rpm by using the throttle in the manual mode there was no change, which resulted in the warning system activating again. The pilot then lowered the collective, returned the throttle to the normal position and began a descent, touching down in soft dirt and sliding forward before coming to rest upright. The helicopter was substantially damaged as a result of the hard landing, which separated the tail section. During the postaccident examination, the engine was tested in the gas generator and the power turbine modes, as well as the electronic engine control (EEC) and mechanical engine control (MEC) modes. The engine was observed to run normally to all inputs in gas generator, EEC and MEC control modes, with manual override also observed to function normally. During a subsequent engine test a reduction in gas generator speed of 8 percent occurred, with the engine fully recovering power in about 5 seconds. Additional testing could not replicate the power reduction as previously observed, and the reason for the reported loss of engine power could not be definitively determined.

Probable Cause: The loss of engine power during cruise flight for undetermined reasons.

Accident investigation:
Investigating agency: NTSB
Report number: WPR10FA029
Status: Investigation completed
Duration: 2 years and 5 months
Download report: Final report



History of this aircraft

Other occurrences involving this aircraft

12 June 2002 N911SL St. Lucie Co Sheriff 0 Okeechobee, FL sub


Revision history:

03-Oct-2022 11:06 ASN Update Bot Added

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