Homer, LA, USA
N335JT
Thompson Angel Hawk II
The private pilot reported that, during the accident flight, he planned to take off and circle the experimental, amateur-built airplane above the runway to check engine operation. Just after takeoff, the engine began sputtering. He made a left 180° turn to return to the runway and during the turn, the engine experienced a total loss of power. He stated that the airplane stalled when he was in the turn and he did not have enough time to recover before impacting the ground. The airplane had accumulated about 47 hours of run time and was in the initial flight test stage when the accident occurred. The pilot reported that he had been having trouble with increased cylinder head temperatures on the converted automotive engine. The engine had experienced a total loss of power during a previous flight, but the pilot was able to land the airplane without incident. Following that event, he replaced some ignition system components and adjusted the valves. He was then able to start the engine and reported that it "ran fine" during subsequent test runs. Postaccident examination of the airplane revealed that the fuel mixture was not adjustable in the cockpit. Examination of the engine revealed that there was melted plastic material inside the distributor rotor and the distributor drive shaft. The condition of the spark plugs was consistent with an overly lean fuel mixture and/or high temperature operation. It is likely that the melted distributor rotor was the result of the engine's high operating temperatures; the degradation of the distributor and its drive shaft would have resulted in a shift in ignition timing and a subsequent loss of engine power.
On June 9, 2017, about 0830 central daylight time, an amateur built Angel Hawk II airplane, N335JT, collided with terrain during a forced landing near the Homer Municipal Airport (5F4), Homer, Louisiana. The pilot/airplane builder was seriously injured, and the airplane was substantially damaged. The airplane was registered to a private individual and was being operated by the pilot as a 14 Code of Federal Regulations Part 91 personal flight. Visual flight rules conditions existed near the accident site at the time of the accident, and a flight plan had not been filed for the local flight. The airplane departed 5F4 just before the accident.The pilot reported that he had been having trouble with increased cylinder head temps on the engine, a VW Type 1. During one flight, the engine popped and quit when he was on downwind and he landed the airplane back on the runway. He couldn't get the engine to restart. He replaced some ignition system components and adjusted the valves which were too tight. He was then able to start the engine and it ran fine during run-up tests. The plan for the accident flight was takeoff and circle above the runway to make sure the engine was running ok. Just after takeoff, the engine began sputtering. He made a left 180° turn to return to the runway and during the turn, the engine lost all power. He stated that the airplane stalled when he was in the turn and he did not have enough time to recover before contacting the ground. The engine was originally a Volkswagen 1.6L Type 1, which had been converted by the pilot to a variation of the Volkswagen 1.9L Type 4. The fuel mixture adjustment was pre-set at the carburetor and not adjustable in the cockpit. The ignition system included a single battery, ignition coil, centrifugal advance distributor, points, condenser and one spark plug per cylinder. The lubrication system had an added external sump attached beneath the oil drain with steel braided hose connecting to a "spin-on" type oil filter mounted on the firewall. The engine had about 47 hours of operating time since new. A postaccident examination of the engine was conducted by a Federal Aviation Administration airworthiness inspector. The examination revealed there was melted plastic material inside the distributor rotor and the distributor drive shaft. The inspector reported that the condition of the spark plugs was indicative of a lean fuel mixture/high temperature operation. The engine timing could not be determined.
A total loss of engine power due to the engine’s unresolved high operating temperatures, which resulted in failure of the distributor rotor and drive shaft, and the pilot’s failure to maintain airspeed during the subsequent forced landing, which resulted in an aerodynamic stall and loss of control.
Source: NTSB Aviation Accident Database
Aviation Accidents App
In-Depth Access to Aviation Accident Reports
