On March 25, 2003, a Piper PA-28-140 C-GNUD operated by Langley Flying School was involved in an aviation accident near Langley Airport, British Columbia, 6 nm NE, CA. One person was killed. This summary draws on records from the Transportation Safety Board of Canada (TSB).
A student pilot was killed when a Piper PA-28-140 entered an unrecovered spiral dive during a solo training flight near Langley, British Columbia, in 2003.
Flight and Accident Sequence A student pilot departed Langley Airport, British Columbia, in a Piper PA-28-140, registration C-GNUD, serial number 28-7525250, for a local solo training flight to the Glen Valley practice area. After takeoff, the aircraft flew northeast at about 2,200 feet above sea level. Radar data showed gentle and medium turns with 10 to 30 degrees of bank. About 30 minutes after takeoff, from about 2,000 feet above ground level, the aircraft completed three level 360-degree left turns and then entered a rapid left-hand descending turn. Radar contact was lost below 1,600 feet above ground level. Ground observers reported a steep left spiral dive of about three full turns before impact. The aircraft struck the ground at high speed, was destroyed by the collision and post-crash fire, and the pilot was fatally injured. The accident occurred at 1640 Pacific daylight time. ## Weather and Communications Reported weather included a few clouds at 5,000 feet above ground level, a scattered layer at 8,000 feet, surface wind 090° at 3 knots, and visibility 25 miles. Radio communications with Langley tower were routine, and no emergency was reported by other aircraft in the practice area. ## Radar and Engineering Analysis Radar analysis indicated the aircraft entered a steep left turn at about 115 mph, with an abrupt initial roll stabilizing at 40 to 45 degrees of bank. The initial turn covered about 80 degrees of heading with an altitude loss of about 600 feet in about 10 seconds. Observers noted a constant bank angle of about 45 degrees and downward pitch angle of about 20 degrees. TSB Engineering Facility analysis estimated impact speed between 180 and 200 mph. ## Aircraft Certification and Control System The Piper PA-28-140 was certificated under Civil Air Regulations Part 3, which requires longitudinal, directional, and lateral stability. Under CAR Part 3, paragraph 3.114, when trimmed to a specific speed, a push is required to maintain higher speeds, and releasing control force should return airspeed within 10 percent of the trimmed speed. Without pilot input, longitudinal stability should have caused the nose to rise as speed increased from about 115 to 200 mph, aiding recovery. Wreckage inspection found no pre-crash structural or control system failure. ## Control Wheel and Airworthiness Directive Airworthiness Directive 69-22-02, effective 30 July 1979, addressed control wheel cracking near the hub and required replacement with an improved metal component or periodic visual inspection of older wheels. The accident aircraft had older-style wheels receiving required inspections. Plastic hub components were not recovered, likely destroyed by fire. TSB Engineering Branch examination of recovered wheel fragments found predominant overstress fracture due to impact, with minimal fatigue pre-cracks around internal manufacturing cavities. Laboratory tests indicated structural integrity was not compromised. ## Safety Database and Safety Action A review of the Transport Canada service difficulty reporting database found 13 control wheel failure events since the AD was issued. Most were cracks found during periodic maintenance, but at least five referred to breaks during operations, some outside the AD-inspected area. Transport Canada resolved the issue separately in the Safety Action section of the report. ## Pilot Background and Training The pilot held a valid student pilot permit and was training under a Flight Training Unit in compliance with CAR 401.19(b). His initial medical examination was completed in 2001, with no pre-existing condition affecting performance. Because student pilot medical validity was five years, more recent medical information was unavailable. Post-mortem and toxicology examinations found no pre-existing natural disease. Training began in May 2001. Initial sequences and upper air work progressed normally, including steep turns, slow flying, stalls, spins, and spiral dive recoveries. The student received a permit on 20 July 2001 and completed his first solo two days later. On 9 August 2001, during a dual trip to the practice area, the instructor observed difficulty with steep turns, including over-banking up to 65 degrees and insufficient back pressure, resulting in nose drop and spiral dive. Three remedial dual trips were provided before solo authorization. The student took a three-month break in early October 2001, returned in January 2002 for three flights, and did not fly again until March 2003. Following the year-long break, he completed 3.1 hours of dual instruction with two qualified instructors and one hour of solo traffic pattern flight. On 15 March 2003, he reviewed steep turns and spiral dive recoveries, including left and right steep turns and four spiral dive recoveries. Performance was described as good, and neither instructor identified weaknesses affecting safety. ## Findings The solo flight was a logical sequence after dual training following the break, and the student was qualified and authorized under the CARs and FTU practices. The aircraft entered a spiral dive from which the student did not recover. The reason for entry and inability to recover are not known. Radar-observed initial roll and constant pitch and bank angles support that the control system was operating and the pilot was conscious and manipulating controls. The student likely applied neutral aileron and forward control pressure to counter aft column movement from increasing speed, possibly attempting to centralize controls as part of recovery. Medical records showed no pre-existing issue affecting control, though the five-year medical validity reduced ongoing monitoring. Although steep turns were initially weak, remedial instruction and recent evaluation reaffirmed safe performance, with further practice needed to meet private pilot standards. Control continuity and pilot incapacitation were eliminated as causes based on witness descriptions of constant bank and pitch. Broken control wheel components showed internal manufacturing voids did not compromise integrity under FAR 23 testing. Although unrelated to this accident sequence, the SDR database showed at least five control wheel breaks during operations, some outside the AD-inspected area. Transport Canada's effort to improve the AD was added to the Safety Action Taken section.