Casualties unknown

2001-01-09: PIPER PA-28R-201T (G-SHUG) — Wycombe Air Park, Buckinghamshire, GB

Wycombe Air Park, Buckinghamshire, GB

On January 9, 2001, a PIPER PA-28R-201T (registration G-SHUG) was involved in an aviation accident near Wycombe Air Park, Buckinghamshire, GB. Investigators recorded the probable cause as: A split in the rubber connection hose leading from the turbocharger caused the loss of engine power. This summary draws on records from the UK Air Accidents Investigation Branch (AAIB).

Sourcesthe UK Air Accidents Investigation Branch (AAIB)Primary reportUpdated 1785053200Data APIEditorial standards
Aircraft registered G-SHUG
Aircraft registered G-SHUG. Photo: Mike Burdett from CROMER, UK / CC BY-SA 2.0, via Wikimedia Commons

A Piper PA-28R-201T, G-SHUG, experienced a reduction in engine power during take-off at Wycombe Air Park, leading to an aborted take-off and runway excursion with right main landing gear collapse. No injuries occurred.

Accident Details

On 9 January 2001 at 1748 UTC, a Piper PA-28R-201T (registration G-SHUG) was conducting a private night flight from Wycombe Air Park, Buckinghamshire. The pilot, holding a Private Pilot's Licence with IMC and Night Rating, had been cleared for take-off on Runway 25. The runway had a dry asphalt surface with a published take-off run of 735 metres. The reported surface wind was 050°/05 kt, visibility 8 km, and QNH 1012 hPa.

Sequence of Events

Late in the take-off run, after crossing the intersection with Runway 17/35, the pilot noticed a reduction in engine power. He decided to abort the take-off, closed the throttle, and applied maximum braking. The aircraft ran off the end of the runway surface, skidded on the grass, and the right main landing gear leg collapsed. The aircraft came to rest approximately 40 metres beyond the threshold of Runway 07. Both occupants, wearing lap and diagonal seatbelts, were uninjured and vacated the aircraft. Airfield fire and rescue services arrived promptly, and local fire and rescue services were also alerted.

Inspection Findings

An engineering inspection by a local maintenance organisation identified a split in the rubber connection hose leading from the turbocharger as the cause of the loss of engine power. The subsequent overrun was partly due to the tailwind in the direction of take-off.

Damage

Damage was limited to the right main landing gear and minor airframe damage.

Probable cause

A split in the rubber connection hose leading from the turbocharger caused the loss of engine power.