American Airpower Heritage Museum

PZL-Mielec AN-2

The commercial pilot was entering the airport traffic pattern for landing during a familiarization flight. He reported that he turned on the carburetor heat, switched the fuel tank selector to the right fuel tank, and shortly thereafter, the engine experienced a total loss of power. The pilot attempted numerous times to restart the engine but was unsuccessful. After realizing that he would not be able to reach the runway, he decided to make a forced landing to a small field. During the landing approach, the airplane contacted a power line, nosed over, and came to rest inverted, resulting in substantial damage to the wings and fuselage. During the postaccident examination of the airplane, about 16 ounces of water were removed from the fuel system. Water was present in the lower gascolator, the fine fuel filter (upper gascolator), and subsequent fuel line to the carburetor inlet. A brass screen at the carburetor inlet and 2 carburetor fuel bowl thumb screens also contained corrosion, water, and rust. The approved aircraft inspection checklist called for washing the carburetor and main fuel filter every 50 hours and cleaning and/or replacing the fine fuel filter every 100 hours. The fine fuel filter is not easily accessible and not able to be drained during a preflight inspection. The mechanic who completed the most recent inspection stated that he did not drain or check the fine fuel filter. The last logbook entry that specifically stated the fuel filters were cleaned was about 4 years before the accident.

Beechcraft C-45 Expeditor

During the instructional flight, the instructor shut down the right engine and feathered the propeller. It was subsequently restarted, but the left engine started running rough and began to vibrate. The left engine was shut down and the propeller feathered. Level flight was maintained from power produced by the right engine. The left engine was then restarted but instead of producing thrust, the engine produced more drag so it was secured again. Then the right engine began losing power. Full power was applied but the airplane continued to descend. The instructor lowered the landing gear and while in-transit, the airplane clipped the tops of trees. He was able to guide the airplane between two houses and impacted an open field. The airplane bounced across the road, struck a power pole, and caught fire. The two pilots evacuated the airplane via the main cabin door. Examination at the airport of departure disclosed two pools of oil at the approximate positions of the two engines. There were two trails of oil leading from the parking spot down the taxiway and onto the runway. Both engines were partially disassembled and examined. There was evidence that both engines had failed catastrophically due to oil starvation. The left engine crankshaft was broken and all the piston heads were at the tops of their cylinders. Pieces of metal were recovered from the right engine oil sump. According to the operator, the engine rocker box recovery system must be drained during preflight to avoid hydraulic lock. The instructor stated that when they preflighted the airplane, the drain valves were open (the drained oil is captured and recycled). He thought they had closed both valves. According to the operator, either the pilot's failed to close the drain valves or they were jammed in the open position. The operator said the latter was unlikely "because you can feel it move when you close it."

Lockheed 18 LodeStar

The 18,000- hour pilot was cleared for takeoff in the vintage twin-engine tail wheel equipped airplane on a 9,501- foot by 50- foot runway. The pilot was aware that there was a tailwind from approximately 160 degrees at 10 knots. Shortly after starting the takeoff roll, the airplane swerved to the right. The pilot was able to correct back to the centerline utilizing rudder control. The airplane then swerved to the left, and full right rudder was applied but the swerve could not be corrected. By the time the airplane reached the left edge of the runway, the airplane had not reached its calculated V2 speed of 110 knots. The airplane departed the left side of the runway, went airborne and shortly thereafter, the right wing dropped and contacted the ground. The airplane then spun 180 degrees, impacted the ground, slid backward, and came to rest upright. A post-crash fire consumed the aft fuselage and left wing.

Casa 2.111

The airplane was en route to an air show and was making a refueling stop. The tower controller cleared the pilot to land. The airplane was observed on a 3-mile straight-in final approach when it began a left turn. The controller asked the pilot what his intentions were. The pilot replied, "We just lost our left engine." The pilot then reported that he wasn't going to make it to the airport. Witnesses observed the airplane flying "low to the ground and under-speed for [a] good 4 minutes." The right propeller was turning, but the left propeller was not turning. There was no fire or smoke coming from the left engine. The pilot was "obviously trying to pull up." The airplane "dipped hard left," then struck the ground left wing first. It slid through a chain link fence, struck a parked automobile, and collided with a school bus wash barn. The ensuing fire destroyed the airplane, parked car, and wash barn. Disassembly and examination of both engines disclosed no anomalies that would have been causal or contributory to the accident. According to the Airplane Flight Manual, "Maximum power will probably be required to maintain flight with one engine inoperative. Maximum power at slow air speed may cause loss of directional control."

Martin B-26 Marauder

Witnesses observed the aircraft approximately 250 feet above the ground heading towards the southwest. As the aircraft passed overhead, the 'engines were sputtering.' Approximately 3/4 mile from the witnesses, the aircraft made a 'sharp' right turn, nosed down, and impacted the ground. The engines 'quit' prior to the aircraft turning right. According to the operator, the flight was in preparation for a flight evaluation for the pilot-in-command by an FAA inspector. The pilot reported to Departure Control that he would be 'working on stalls and steep turns,' and the pilot was instructed to 'maintain VFR at or above five thousand five hundred.' The pilot-in-command had accumulated approximately 500 hours in the B-26. Prior to the accident flight, he had flown the B-26 once since October 8, 1993. That flight was on September 26, 1995, for a duration of 30 minutes. Prior to the flight the fuel tanks were 'sticked' and the total fuel was approximately 720 gallons of 100 octane low lead avgas. Examination of the airplane and engines did not disclose any pre mishap discrepancies. Due to the extent of damage, flight control continuity could not be established.