Accident Pilatus PC-12/45 N922RG, Tuesday 14 December 2004
ASN logo
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.

Date:Tuesday 14 December 2004
Time:14:30 LT
Type:Silhouette image of generic PC12 model; specific model in this crash may look slightly different    
Pilatus PC-12/45
Owner/operator:Greenhill Aviation Co., LLC
Registration: N922RG
MSN: 409
Year of manufacture:2001
Total airframe hrs:599 hours
Engine model:Pratt & Whitney Canada PT6A-67B
Fatalities:Fatalities: 0 / Occupants: 5
Other fatalities:0
Aircraft damage: Substantial
Location:South Bend, Indiana -   United States of America
Phase: Unknown
Departure airport:South Bend Regional, IN (SBN/KSBN)
Destination airport:White Plains-Westchester County Airport, NY (HPN/KHPN)
Investigating agency: NTSB
Confidence Rating: Accident investigation report completed and information captured
The airplane was substantially damaged during a forced landing following a loss of engine power. The pilot stated that shortly after takeoff, the engine "abruptly and smoothly rolled back." Movement of the power control lever had no effect. He stated that use of the manual override (MOR) system did not restore engine power. He secured the engine and executed a forced landing on a roadway. The airplane's wing struck two utility poles during rollout. Data downloaded from the accident aircraft indicated that the recorded engine interstage turbine temperature (ITT) exceeded published limits during the event. The post accident engine inspection revealed turbine damage consistent with an over-temperature event. The inspection also revealed a leak in the compressor discharge pressure (CDP) sensor bellows within the fuel control unit (FCU). The leak prevented the bellows assembly from responding to throttle inputs and resulted in the FCU providing minimum fuel flow to the engine regardless of the throttle setting. Following this accident an improved FCU design which incorporated a more robust bellows design was released and retrofited into the entire in-service and production fleet. The airframe manufacturer issued a revision to the pilot's operating handbook to provide an improved procedure for use in the event of an in-flight engine power loss. It also updated information regarding the Manual Override (MOR) system.

Probable Cause: Failure of the fuel control unit (FCU) bellows which resulted in a significant loss of engine power and the pilot's encounter with unsuitable terrain during the subsequent forced landing. A contributing factor was the pilot's inadvertent exceedence of the engine temperature limitations during use of the manual override (MOR) system. Additional factors were the roadway and the utility poles struck during the forced landing.

Accident investigation:
Investigating agency: NTSB
Report number: CHI05LA045
Status: Investigation completed
Duration: 2 years 1 month
Download report: Final report



Revision history:

11-Oct-2022 14:50 ASN Update Bot Added

Corrections or additions? ... Edit this accident description

The Aviation Safety Network is an exclusive service provided by:
Quick Links:

CONNECT WITH US: FSF on social media FSF Facebook FSF Twitter FSF Youtube FSF LinkedIn FSF Instagram

©2024 Flight Safety Foundation

1920 Ballenger Av, 4th Fl.
Alexandria, Virginia 22314