CEN16LA100

During the landing roll following a normal touchdown after a personal flight, the pilot felt a vibration in the airframe, and the right main landing gear collapsed. The pilot was unable to maintain directional control, and the airplane departed the side of the runway. A pilot-rated witness confirmed that the landing approach, flare, and touchdown were normal, and the surface wind was about a 20-degree left crosswind at 8 to 10 knots and not gusting at the time of landing. An examination of the airplane revealed the right main landing gear strut assembly failed, and all associated fracture surfaces were consistent with overload. The reason for the overload failure could not be determined.

On January 29, 2016, about 1130 central standard time, a Maule M 7-235C single-engine airplane, N66E, experienced a right main landing gear collapse during landing at the Macon-Fower Municipal Airport (K89), Macon, Missouri. The private pilot was not injured, and the airplane sustained substantial damage to the fuselage and right wing. The airplane was registered to Richardson Companies, Inc., and operated by a private individual as a 14 Code of Federal Regulations Part 91 personal flight. Visual meteorological conditions prevailed at the time of the accident, and no flight plan was filed. The local flight departed at an unknown time. After a normal touchdown on runway 20 and during the landing roll, the pilot felt a vibration in the airframe. Shortly thereafter, the right wing dropped and the pilot lost yaw control. The pilot was unable to maintain directional control, and the airplane departed the left side of the runway. The airplane came to rest upright off the side of the runway. A pilot-rated witness stated the landing approach, flare, and touchdown were normal. He reported the wind at 8 to 10 knots, not gusting, and a 20 degree left crosswind for the landing. Examination of the airplane by a Federal Aviation Administration inspector showed the right main landing gear collapsed and remained partially attached to the fuselage. The right wing strut and right wing were bent. The inspector located the upper half of one bolt that attaches the right main gear strut to the fuselage, and the bolt was sheared. The bolt fracture surface was consistent with an overload failure. The inspector noted the fuselage to main landing gear frame structure was fractured, and the inspector did not see any evidence of corrosion or a preexisting condition that contributed to the failure. The right main landing wheel hub assembly was fractured, and a portion of the hub was not located. The remaining portion of the hub did not display any evidence of corrosion or a preexisting condition that contributed to the failure. The reason for the right main landing gear collapse could not be determined.