WPR09LA268

A loss of engine power during takeoff for undetermined reasons.

The pilot reported that he filled the airplane's fuel tanks prior to flight with aviation gasoline, and performed preflight inspections both before the flight, as well as the day prior. During the takeoff initial climb, the airplane experienced a loss of engine power. The pilot attempted to restart the engine, but ultimately force landed in a field adjacent to the airport. The airplane sustained substantial damage to the wings and fuselage during the impact sequence. Post accident examination of the engine did not reveal any obvious anomalies; however, a fuel sample obtained from one of the wings revealed the presence of a residual quantity of automotive gasoline mixed with aviation gasoline. The owner of the airplane stated that he had used automotive gasoline in the airplane on prior occasions, but had given up the practice about 6 months prior to the accident. The use of automobile gasoline in the airplane is explicitly prohibited by the engine manufacturer for reasons including the potential for vapor lock. Additionally, the engine examination showed multiple indications of an excessively rich mixture, which can also result in a loss of power. Whether one or both of these possibilities resulted in the loss of engine power could not be determined. The pilot reported flight control difficulties during the emergency descent; however, impact damage prevented an accurate assessment of the airplane's control rigging.

HISTORY OF FLIGHT On May 28, 2009, about 0845 mountain daylight time, a Maule M-5-210C, N315X, impacted uneven terrain after experiencing a loss of engine power during takeoff at Ogden-Hinckley Airport, Ogden, Utah. The pilot was operating the airplane under the provisions of 14 Code of Federal Regulations (CFR) Part 91. The certificated airline transport pilot sustained serious injuries. The airplane sustained substantial damage to the forward fuselage and both wings. The local flight departed Ogden about 0845, with a destination of Paradise, California. Visual meteorological conditions prevailed, and no flight plan had been filed. The pilot reported that the intention of the flight was to reposition the airplane to Anchorage, Alaska. Due to the nature of his injuries, he was unable to submit a written report until a month following the accident. He stated that on the day prior to the accident he performed what he described as an in-depth walk around of the airplane. During the inspection he verified that there was about 10 gallons of fuel in each main fuel tank. He subsequently taxied the airplane to the run-up area and performed an uneventful, "in-depth engine run-up check procedure." The pilot reported that the following morning he checked the weather, and then filled both the main and auxiliary fuel tanks with the addition of 43 gallons of 100 low lead aviation gasoline. The pilot then taxied the airplane to runway 34, and completed an uneventful before takeoff check and engine run-up. The pilot reported that during the takeoff roll the engine parameters appeared normal, the airplane rotated, and then continued to accelerate throughout the climb. The airplane continued to climb to about 700 feet above ground level (agl) when the pilot initiated a climbing left turn to the west. About 1,100 foot agl he reduced the propeller speed and manifold pressure to 2,450 rpm and 24 inches, respectively. Shortly thereafter the engine stopped producing power. The propeller continued to rotate, and the pilot rolled the airplane into a 45-degree left bank. He lowered the nose and trimmed the airplane for 80 knots airspeed. He then applied full forward throttle and propeller control, confirmed the mixture was still at a full rich setting, and turned on the auxiliary fuel pump. During the descent he continued with troubleshooting procedures; however, the engine did not restart and he performed a forced landing in a grass field northeast of the airport. He reported that during the descent he experienced difficulties maintaining the correct airspeed and descent rate. Just prior to impact he pulled the throttle, propeller, and fuel mixture controls to the full aft position. The pilot reported that prior to the accident he asked the owner of the airplane if he had ever used automotive gasoline in the airplane, to which he replied that he had not. The NTSB investigator-in-charge interviewed the airplane owner after the accident. The owner stated that he had used automotive gasoline in the airplane in the past, but "had given up that practice" and had been using aviation gasoline since January 2009. He additionally stated that he had brought his use of automobile gasoline to the attention of the pilot. PERSONNEL INFORMATION The pilot, age 49, held an airline transport pilot certificate with ratings for airplane single-engine land and multiengine land. The pilot held a certified flight instructor (CFI) certificate with ratings for airplane single-engine land, multiengine land, and instrument airplane. He reported 5,900 hours total time in all aircraft, with 150 hours in the accident make and model. He reported his principal occupation to be that of a pilot. A review of Federal Aviation Administration (FAA) airman records revealed that the pilot held a first-class medical certificate issued in February 2009, with the limitation that he must have glasses available for near vision. AIRCRAFT INFORMATION The single-engine, high-wing, airplane was manufactured in 1975 and was equipped with a Teledyne Continental Motors (TCM) IO-360-D fuel injected engine, and a McCauley constant speed propeller. A review of the airplane’s maintenance logbooks and tachometer at the accident site revealed that it had accumulated a total flight time since manufacture of 1,613 hours. Additionally, an annual inspection was completed on December 4, 2008, 48.5 flight hours prior to the accident. At that time, the engine had accumulated a total of 1,565.5 flight hours since its manufacture in 1975. According to the logbook, the airplane had not been subject to a major overhaul since its manufacture. The logbooks indicated that on March 22, 2009, two flight hours prior to the accident, the number 5 and number 2 engine pushrod seals were replaced. The final logbook entry dated April 27, 2009, reported the addition of a four point inertia reel safety belt system, and a Maule super skylight kit. The entry stated the "estimated" tachometer time for this entry to be 1,614.0 hours. The airplane was equipped with four wing fuel tanks and a header tank; according to the airplane flight manual, the total fuel capacity was 63 gallons. METEOROLOGICAL INFORMATION The closest aviation weather observation station was located at Ogden-Hinckley Airport. An aviation routine weather report (METAR) for Ogden was issued at 0853 MDT. It reported: winds calm; skies clear; temperature 19 degrees C; dew point 4 degrees C; altimeter 30.13 inches of mercury. WRECKAGE AND IMPACT INFORMATION A Federal Aviation Administration inspector (FAA) responded to the accident site. He examined the gascolator and observed that it was clear of debris, and contained clear blue fluid consistent in color and odor with aviation gasoline. The airplane sustained crush damage from the engine firewall through to the cabin, aft of the wing trailing edges. The left wing separated at its aft spar attach point, was facing forward, and partially attached to the forward spar. The right wing remained partially attached at the forward and aft spar and had become folded down at its intersection with the wing struts. The propeller separated from the crankshaft at the flange, and came to rest about 10 feet forward of the airplane. TESTS AND RESEARCH Engine The engine remained attached to the firewall. The throttle and propeller control cables were continuous from the cabin controls through to their respective engine controls. The fuel mixture cable was continuous from the cabin control through to the engine side of the firewall, where it had become separated from the fuel servo at the mixture arm. The fracture surfaces of the mixture arm and elevator control rod were granular in appearance, with the mixture arm exhibiting a 45-degree sheer lip. The left magneto had become separated from the engine at its mounting flange, and exhibited external damage. The right magneto remained attached to its mounting pad. The ignition cables for both magnetos appeared undamaged. Both magnetos were removed from the engine and tested using a magneto test stand. During the test, sparks were noted at the ignition leads of each magneto. The top spark plugs were removed and visually examined. The electrodes showed normal erosion patterns when compared to the champion AV-27 chart. The electrodes were dark in color with sooty deposits, which indicated carbon fouling when compared with the champion chart. The spark plugs were of type Unison Autolite, part number URHM-38E, which the Teledyne Continental Motors (TCM) representative stated were appropriate for the engine. The FAA inspector tested the magneto switch and did not observe any short-circuits. The fuel manifold valve was disassembled; fuel was noted within its cavity, and its screen was clear of debris. Traces of fuel were observed throughout the engine driven fuel pump, throttle body, and associated supply lines. Inspection of the engine c