SUMTER, SC, USA
N9884U
Grumman American AA-5A
The flight had been airborne about 30 minutes performing airwork, then while flying at 2,000 feet returning to the airport, the CFI noted that the oil pressure was below the lower end of the green arc. He questioned the owner if that was normal; it was not. The engine then began to run rough and began to lose power. Attempts to correct this were unsuccessful. The CFI attempted to perform a forced landing in a field but while on final approach with the throttle still applied, engine power was momentarily restored. He then overflew the intended field and attempted a landing in a freshly plowed field perpendicular to the plowed rows. After touchdown the nose landing gear collapsed and the engine partially separated from the airframe. Disassembly of the engine revealed no evidence of preimpact failure or malfunction. The oil cooler bypass valve was tested which revealed that it did not meet the minimum extension at the midpoint of the test range. The engine had accumulated about 2,091 hours since manufacture with no record of the bypass valve being replaced.
On May 18, 1998, about 1420 eastern daylight time, a Grumman AA-5A, N9884U, registered to a private individual, was substantially damaged during a forced landing in a field near Sumter, South Carolina. Visual meteorological conditions prevailed at the time and no flight plan was filed for the 14 CFR Part 91 instructional flight. The certified flight instructor (CFI) was not injured and the private-rated Biennial Flight Review (BFR) applicant sustained minor injuries. The flight originated about 30 minutes earlier from the Sumter Municipal Airport, Sumter, South Carolina. According to the CFI, the BFR applicant had completed the airwork portion of the flight and was returning to the airport when, while flying at 2,000 feet, he noted that the oil pressure was below the lower red arc. He asked the BFR applicant who was one of three owners of the airplane if that was normal, and the applicant advised no. The flight turned towards the departure airport and about 20 seconds later, the engine began to run rough. The CFI took the controls and executed the emergency procedures to restore engine power which was unsuccessful at that time. The CFI then maneuvered the airplane towards a field and while on final approach with the throttle partially applied, engine power was momentarily restored. The flight was then too fast and the CFI maneuvered the airplane towards another nearby field. The airplane was landed nearly perpendicular to the plowed direction and after touchdown, the nose landing gear collapsed and the engine nearly separated from the airframe. The engine was removed from the airplane and examined by an FAA inspector. Complete disassembly of the engine revealed no evidence or preimpact failure or malfunction; however, the solder at the oil pressure screen was melted, and resolidified. A copy of the FAA inspector statement is an attachment to this report. The oil cooler bypass valve was retained for further examination. Examination of the oil cooler by-pass valve revealed that by design, the valve is to expand a minimum of .160 inch between 150 and 185 degrees Fahrenheit. Testing of the valve at 170 degrees Fahrenheit, revealed it expanded only .105 inch, which is less than the specification. Review of the engine logbook revealed that the engine had accumulated a total time of 2,091 hours since manufacture, with no record of the oil cooler by-pass valve being replaced.
The partial failure of the oil cooler bypass valve which resulted in the over-temperature and loss of oil pressure.
Source: NTSB Aviation Accident Database
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