Event MIA00LA263

Factual narrative

On September 16, 2000, about 1000 eastern daylight time, a Grumman AA-5, N7196L, registered to Positive Attitudes, Inc., experienced a loss of engine power shortly after takeoff from the Zephyrhills Municipal Airport, Zephyrhills, Florida. Visual meteorological conditions prevailed at the time and no flight plan was filed for the 14 CFR Part 91 personal flight. The airplane was substantially damaged and the private-rated pilot and one passenger were not injured. One passenger sustained minor injuries. The flight originated about 1 minute earlier from the Zephyrhills Municipal Airport. The pilot stated that the aircraft preflight and engine run-up before departure were uneventful. The flight departed and during the initial climb at approximately 350 feet above ground level (agl), he noted that the airplane did not appear to be ascending as expected. He looked at the tachometer which was indicating between 1,900 and 2,000 rpm and, "...checked throttle and mixture which were both OK." He also scanned the gauges and switches on the instrument panel which were also indicating "OK." He advised his passengers of the situation and maneuvered the airplane for a landing in a field. He noted trees that were ahead and applied aft elevator control input to intentionally stall the airplane; it dropped and impacted the ground then slid approximately 60-70 feet before coming to rest upright. Both passengers reported that the airplane impacted the ground "real hard." The accident site was located approximately 1 mile north of the airport. The airplane was recovered and according to the FAA certificated mechanic who recovered it, the carburetor bowl was drained and found to contain 2.5 ounces of fuel; no contaminants were noted. Some automotive fuel was present. The mechanic also indicated that he smelled fuel on the ground during recovery and that there was no fuel remaining in the fuel tanks when he recovered the airplane. Examination of the airplane following recovery by an FAA airworthiness inspector revealed the mixture control cable was broken aft of the mixture control arm at the carburetor. An approximate 3-inch section of the cable remained secured to the mixture control arm which was found in the idle cutoff position. A bracket located in the engine compartment approximately 4.5 inches aft of the carburetor that secures the mixture control cable was noted to be displaced approximately 1.5 inches to the left; the cable housing remained secured to the bracket. The swivel assembly in the mixture control arm was installed upside down contrary to the illustrations in the maintenance manual and the illustrated parts catalog. The damaged propeller was removed from the airplane and a serviceable propeller was installed for the attempted engine run that was performed with FAA oversight. The engine was started and operated to 2,300 rpm. A check of each magneto during the engine run revealed that the left magneto had a broken "P" lead; the right magneto drop was noted to be "OK." Also during the engine run, a "tinny rattling noise" was heard. The engine was secured and a rattling sound was heard when the muffler struck by hand. The muffler was removed and cut open which revealed that both end caps of the flame tube were separated and loose inside the muffler. Copies of the FAA inspector statements are an attachment to this report. The muffler and broken mixture control cable were retained for further examination by the NTSB Materials Laboratory located in Washington, D.C. Metallurgical examination of the mixture control cable revealed the fracture location of the wire was 0.14 inches forward of the end of the housing when the cable was straight and with the knob pushed in all of the way. The solid wire of the cable was worn adjacent to the fracture surface with the greatest wear on the wire located within approximately 0.34 inches aft and 0.09 inches forward of the fracture location. The worn surface was located at the outside radius of the bend (on the right side of the cable). Fatigue was noted emanating from multiple origins at the worn surface of the wire adjacent to the fracture surface. The area of the fatigue region was less than 10 percent of the total fracture surface area. The remaining fracture surface had dimpled fracture features consistent with overstress fracture. The fracture surfaces of the forward and aft pieces of the control cable were fit together which formed an angle of 129 degrees relative to each other with a bend radius of approximately 0.17 inches at the cable centerline. The direction of the deformation in the cable was such that the angle of the bend pointed to aircraft right. Examination of the muffler revealed the interior of the muffler had a generally corroded appearance, and the perforated inner cylinder wall thickness appeared thinner nearest the fracture locations where the end caps were located. Pieces were missing from the inner cylinder. Impact damage to the exterior of the muffler was noted and one of the separated end caps was deformed which was associated with the exterior crushing. Portions of the fracture surfaces on each end cap had a relatively shiny appearance consistent with little or no oxidation. A copy of the metallurgy report is an attachment to this report. The airplane was manufactured in 1974, and had accumulated approximately 2,246 hours since then at the time of the accident. There was no record that the mixture control cable had been replaced since the airplane was manufactured. The muffler was replaced with an "overhauled" unit on August 11, 1993. The muffler had been in service for 408 hours at the time of the accident as determined by the tachometer. The airplane was inspected last on October 26, 1999, in accordance with an annual inspection and had accumulated approximately 44 hours since then at the time of the accident. Excerpts from the maintenance records are an attachment to this report. The airplane minus the retained mixture control cable was released to Mr. Steven M. Homenda, insurance adjuster for Universal Loss Management, Inc., on September 20, 2000. The muffler was retained on November 15, 2000. The retained mixture control cable and muffler were released to Mr. Steven M. Homenda, on July 13, 2001. The pilot noted the airplane was not climbing as expected and a decreased engine rpm. He checked the throttle and mixture controls then with obstructions ahead, intentionally stalled the airplane; a hard landing resulted. The mixture control arm was in the idle cutoff position and the mixture control cable was fractured aft of the mixture control arm. A bracket near the carburetor securing the mixture cable was displaced to the left 1.5 inches. The swivel assembly in the mixture control arm was installed upside down. Post accident, the engine was operated to 2,300 rpm. Both ends of the flame tube of the muffler were found separated following the engine run. One of the flame tube ends was impact damaged; portions of the fracture surfaces on both flame tube ends had a relatively shiny appearance. Wear and fatigue noted on the mixture control cable adjacent to the fracture area; bending overstress to the right on the remaining fracture surface. The mixture control cable had not been replaced since airplane manufacture in 1974. The airplane had accumulated 2,246 hours since then, 44 hours since the last annual inspection 11 months earlier, and 408 hours since an overhauled muffler was installed. Source: NTSB Aviation Accident Database (Pre-2008 Archive) Retrieved: 2026-02-12