WRENS, GA, USA
N964ST
PIPER PA-32RT-300T
THE PILOT COULD NOT START THE AIRPLANE. ACCORDING TO LINE MAINTENANCE PERSON, THE PILOT WAS ASKED IF HE WANTED A 12 VOLT OR A 24 VOLT JUMP START. THE PILOT REPLIED THAT HE WANTED A 24 VOLT JUMP START. AFTER THE AIRPLANE STARTED THE FLIGHT DEPARTED WITHOUT FURTHER INCIDENT. WHILE CURISING AT 6000 FEET, THE PILOT REPORTED A LOSS OF ENGINE POWER. THE PILOT INFORMED DEPARTURE CONTROL OF HIS PROBLEM AND REQUESTED VECTORS TO THE NEAREST AIRPORT. THE PILOT WAS ISSUED VECTORS TO THE WRENS MEMORIAL AIRPORT; THE AIRPLANE CRASHED IN AN INVERTED ATTITUDE 1/4 MILE SHORT OF RUNWAY.
HISTORY OF FLIGHT On November 1, 1993, at 2220 eastern standard time, a Piper PA- 32RT-300T, N964ST, collided with trees about 600 yards northeast of the Wrens Memorial Airport, Wrens, Georgia. The pilot was attempting an emergency landing when the collision occurred. The flight operated under 14 CFR Part 91 with an instrument flight clearance. Visual weather conditions prevailed at the time of the accident. The airplane was destroyed by impact forces and a post crash fire; four of the five occupants were fatally injured, and the pilot received serious injuries. The flight departed Augusta, Georgia, at 2201. Approximately fifteen minutes into the flight, cruising at 6000 feet, the pilot reported an engine problem. Moments later, the pilot reported to Augusta Departure Control that the engine had stopped. The flight was cleared to the Wrens Memorial Airport that was located seven miles west of the flight's position. Seconds before the collision, a witness reported that the pilot turned on the landing lights, and that the airplane appeared to have been established on a final approach to the southwest runway. The airplane collided with trees prior to reaching the runway. Examination of the engine revealed that there was fracture damage to internal drive gears. The accessory housing was not damaged, externally. PERSONNEL INFORMATION Information on the pilot is included in this report at the data field labeled "First Pilot Information". The pilot's flight logs were not recovered for examination. AIRCRAFT INFORMATION Information on the aircraft is contained in this report at the data field labeled "Aircraft Information". An overview of the engine components is shown in figure 1, as received. A review of the engine maintenance logs disclosed that the last entrance was made on October 25, 1993. At that time, the engine had 2,078 hours of total time, 241.4 of which had been since the last overhaul. The review also revealed that the propeller assembly had been repaired on June 21, 1993, as a result of a propeller strike. The annual inspection of the engine was performed on September 9, 1993. An examination of the engine case disclosed that the engine case had been stamped with the marking "AJAX 93779904" indicating that it was twice subjected to repairs by AJAX. METEOROLOGICAL INFORMATION Visual weather conditions prevailed at the time of the accident. Weather information is contained in the report at the data field labeled "Weather Information". WRECKAGE AND IMPACT INFORMATION The airplane collided with tree 1/4 mile east of the Wrens Memorial Airport in Wrens, Georgia. The metallurgist's examination of engine components disclosed the following: Examination of the front end of the engine case disclosed that a set screw that prevents rotation of the governor drive idler gear shaft inside the bore was missing and a portion of the boss surrounding the screw was broken. The screw had been recovered after the accident during original dissembly of the engine. The governor gear train was disassembled and the liberated gears were examined visually and with the aid of a bench binocular microscope. The governor idler bevel gear and the governor shaft gear teeth had spalling at the pitch line on the pressure faces. Splines on the governor shaft had plastic deformation consistent with heavy loading; The governor idler shaft had circumferential score marks at both ends. Examination of the aft end of the engine case revealed that the boss for the idler gear shaft was broken. Visual and magnified examination revealed that the separation of the boss occurred as a result of overload, and there was no signs of progressive cracking on the fracture surface. The bore in the boss appeared to be fairly cylindrical and was approximately 0.870 inch in diameter. Measurements indicated that the corresponding diameter of the shaft was 0.690 inch. AJAX Aviation , Inc. work order No. 9904, the boss for the idler gear was repaired on May 26, 1992. A representative of AJAX stated that during this repair the bore in the boss was enlarged and a bushing was installed by press fitting. The bushing (or its remnants) was not submitted for examination. AJAX reportedly keeps records of work orders for a duration of only two years. Further inspection of the aft end of the engine revealed that a portion of the magneto gear boss was cut off or ground by a contact with the idler gear teeth. The teeth imprints were visible on the cut surface of the magneto gear boss when viewed under oblique light. The depth of the cut was approximately 0.004 inch. Examination of the accessory housing revealed that a portion of the boss for the idler gear shaft was broken off. The fracture face on the broken off piece was examined with the bench binocular microscope and then at higher magnifications with a scanning electron microscope (SEM). The fracture surface features wee completely obliterated by post fracture damage in some areas. Examination of the undamaged regions showed dimpled fracture mode consistent with an overstress separation. Examination of the forward end of the camshaft revealed no damage to the governor drive gear. The driving faces on the gear teeth were slightly polished, typical of normal tooth wear. Examination of the aft end of the camshaft revealed heavy grinding damage to the forward portions of the top faces in six (6) adjacent teeth of the aft camshaft gear. Substantial portions of the two adjacent teeth were broken off at the forward end of the gear. Magnified inspection disclosed that these teeth broke as a result of overload. Severe plastic deformation and cracking were observed on the forward portions of the top and driving faces of all other gear teeth. The idler gear contains two differing diameter gear teeth. The larger diameter gear teeth (forward teeth) are driven by the crankshaft gear and drives the camshaft gear. The smaller diameter gear teeth (aft teeth) drives the magneto drive gear. Two teeth were missing from the larger diameter gear teeth. All remaining teeth in this gear had either heavy pitting or spalling along the pitch line. Segments of the gear containing the missing teeth were cut off and the fracture faces were examined with the stereomicroscope and then at higher magnifications with the SEM. Approximately 80% of the fracture surface area in the tooth was relatively smooth and contained crack arrest positions characteristic of fatigue cracking. The fatigue cracking originated at the root of the tooth. SEM examination revealed fissuring (micro cracking) in the fatigue zone and dimpled rupture mode in the overstress separation zone. Examination at higher magnifications with SEM revealed micro fissuring, typical of fatigue cracking. The fatigue cracking emanated from an area of the thread root and extended throughout almost the entire fracture surface. Both teeth faces of the larger diameter gear teeth are pressure faces. The fatigue cracking in teeth "1" and "2" originated on the opposite sides of the teeth. The smaller diameter gear teeth also had two missing teeth. Examination revealed that the breakage of this tooth occurred as a result of overstress or after only a few cycles of very high stress. Examination of the magneto drive gear disclosed pitting and spalling along the pitch line of some of the teeth. Plastic deformation of the pressure faces in several teeth and a pattern of tooth contact imprints was consistent with sliding of the mating gear under heavy loading. MEDICAL AND PATHOLOGICAL INFORMATION The pilot expired on January 2, 1994; no autopsy or toxicological examinations were requested. ADDITIONAL INFORMATION The aircraft wreckage was released to: Mr. Phil Connell (operator)
WAS THE FATIQUE FAILURE OF THE IDLER GEAR WHICH RESULTED IN THE COMPLETE LOSS OF ENGINE POWER. A FACTOR WAS THE DARK NIGHT.
Source: NTSB Aviation Accident Database
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