Piper PA-28-181 Cherokee Archer II G-BXWO Accident at Redhill Airfield

Overview and Flight Details On 23 August 2003 at 0821 UTC, a Piper PA-28-181 Cherokee Archer II, registration G-BXWO, was involved in an accident at Redhill Airfield, Surrey. The aircraft, manufactured in 1981 and powered by a single Lycoming O-360-A4M piston engine, was operating a private flight with two crew members and two passengers on board. No injuries were reported to any occupants. The accident resulted in the collapse of the right main landing gear. ## Pre-Flight and Takeoff The aircraft was part of a group of ten aircraft traveling from various UK airfields to Biarritz, France. The flight from Redhill was planned for Deauville, France, with four occupants, limited baggage, and a 70% full fuel load. Three of the occupants were qualified pilots, including a commercial pilot in the right seat. A weight and balance calculation prepared by a non-handling pilot indicated the aircraft was 21 lb under its maximum takeoff weight of 2,550 lb, with the center of gravity 0.12 inches inside the aft limit. During taxiing for grass Runway 26 L, the aircraft exhibited an unusually nose-up attitude with the nose oleo almost fully extended. Despite an ATC offer to use Runway 01, the pilots selected Runway 26 L due to flatter ground, fewer obstacles, and an additional 46 meters of takeoff run. Engine indications during run-up checks were normal. ## Accident Sequence The takeoff roll was characterized by slow acceleration, and the aircraft lifted off approximately halfway down the runway. At an estimated 50 feet above ground level, both front-seat pilots observed a reduction in engine RPM. The stall warning activated, and the right wing dropped as the commander attempted to maintain a climbing attitude. The right-seat pilot assumed control, closed the throttle, lowered the nose, and directed the aircraft to land straight ahead. The aircraft landed heavily on the right main landing gear, which collapsed and detached as the aircraft came to a stop just beyond the airfield perimeter track. All occupants exited the aircraft through the normal exit without injury. ## Post-Accident Investigation An examination by the aircraft's maintenance company found no engine fault to explain the power loss. However, the engine primer pump was discovered in an unlocked position. Full-power engine tests demonstrated that with the primer unlocked, maximum attainable RPM decreased by 100 RPM. The pilots reported that the primer pump had not been used during the engine start on the day of the accident.