ASN logo
ASN Wikibase Occurrence # 32230
Last updated: 23 October 2020
This information is added by users of ASN. Neither ASN nor the Flight Safety Foundation are responsible for the completeness or correctness of this information. If you feel this information is incomplete or incorrect, you can submit corrected information.

Type:Silhouette image of generic UH1 model; specific model in this crash may look slightly different
Bell 204/UH-1L
Registration: N70410
C/n / msn: 6214
Fatalities:Fatalities: 0 / Occupants: 1
Other fatalities:0
Aircraft damage: Written off (damaged beyond repair)
Location:Grace, Idaho -   United States of America
Phase: En route
Nature:External load operation
Departure airport:
Destination airport:
Investigating agency: NTSB
During log slinging operations the restricted category UH-1L rotorcraft's T53-L-13B military engine experienced a total loss of power. The pilot dropped the log load and autorotated into a small, upsloping, cleared area within the surrounding wooded terrain landing hard. Postcrash examination of the engine revealed that the centrifugal impeller had separated due to fatigue cracking in one of the drain holes.

An Airworthiness Directive (AD) had been issued relative to the -08 impeller but did not include the 07 impeller (installed in the accident engine). The -07 and -08 impellers are essentially identical with the exception that the -07 impeller is found on military variants of the engine whereas the -08 is found only on civilian variants. As the -07 impeller was not included in the AD, the operator was not required to conduct the appropriate inspections described in the mandated service bulletin.

Additionally, the AD did not require a cycle count for the impeller as addressed in the service bulletin, thus rendering the service bulletin unusable even if it had been mandated for the -07 impeller.

The National Transportation Safety Board determines the probable cause(s) of this accident as follows: the fatigue failure of the centrifugal impeller and the lack of suitable terrain for a forced landing. Factors contributing to the accident were: the lack of required compliance with the FAA Airworthiness Directive by the operator, the insufficiently defined FAA procedure within the AD (failure to include the -07 impeller and establish a cycle count program), and inadequate rotor RPM.

Sources: [NTSB Identification: SEA95LA221]

Revision history:

27-Sep-2008 01:00 ASN archive Added
30-Oct-2011 06:38 Dr. John Smith Updated [Total fatalities, Total occupants, Other fatalities, Location, Country, Phase, Nature, Source, Damage, Narrative]

Corrections or additions? ... Edit this accident description