N29MW is a 2019 Pilatus Aircraft PC-24. It is a fixed-wing multi-engine aircraft with 9 seats, powered by a Williams FJ 44 series. The registration is active, with the registrant based in Ardmore, PA. Its standard airworthiness certificate was issued in May 2019. It has been registered to its current owner since Aug 2019. This page also carries 1 NTSB event.
- 7 years old
- 1 of 196 Pilatus Aircraft PC-24
2019
That's everything on file so far — TailWiki checks the FAA registry daily and adds new entries as N29MW's record changes.
On May 30, 2011, at an unknown time, a Beech V35B, N29MW, collided with terrain on Rich Mountain, in the Chattahoochee National Forest, Ellijay, Georgia. The airplane sustained substantial damage. The pilot and three passengers received fatal injuries. The airplane had departed from the Gilmer County Airport (49A), Ellijay, Georgia, about 1033 that day. Visual meteorological conditions prevailed and no flight plan had been filed for the personal flight conducted under the provisions of Title 14 Code of Federal Regulations Part 91.
According to a representative from the fix base operator, the out of state pilot arrived to 49A on May 27, 2011 to attend a social event. On May 29, he offered a sightseeing flight which flew over mountainous terrain and over the Carter and Blue Ridge Lakes area. The sightseeing flight returned back to 49A within an hour from its departure. After that flight the airplane was fueled with 32 gallons of aviation fuel and placed in a hangar. On the morning of May 30, the airplane was pulled out of the hanger for another sightseeing flight with different passengers. The airplane departed from runway 21 and was last seen flying in an easterly direction. Friends and family members notified the authorities when the flight did not return. A search & rescue operation was initiated. The wreckage was located on June 1, 2011.
The pilot, age 68, held a private pilot certificate with ratings for airplane single engine and multi-engine land, and instrument airplane. He was issued a third-class medical certificate on March 16, 2011, with limitation of must wear corrective lenses. He documented 2,800 total hours at that time. The pilot’s flight logbook was not recovered and presumed to be among the wreckage.
The Beech V35B was built in 1977, serial number D-10086. On November 23, 1977 the airplane was issued a standard airworthiness certificate and registered in the utility category. The airplane was equipped with a Teledyne Continental Motors IO-520-BA, 285 horsepower rated engine, with a three bladed McCauley, constant speed, propeller. The airplane incorporated a retractable tricycle landing gear and had a “V” tail design for the rudder and elevator flight control surface system. The airplane was maintained in accordance with the manufacturers recommended maintenance program. A review of the airplanes maintenance records revealed the airplane had an annual inspection on the airframe, propeller, and engine on January 10 2011, at which time the airplane had accumulated a total of 3,044 hours, the engine was new with 0 hour, and the propeller had accumulated 895 hours since overhauled. The airplane’s engine had maintenance performed on April 28, 2011.
The closest official weather observation was at the Gilmer County Airport (49A), Ellijay, Georgia, 8 miles southwest of the accident site. The 49A May 30, 2011, 1025 automated weather observing system (AWOS) was wind from 020 degrees at 3 knots; visibility, 10 statute miles; sky clear; temperature 29 degrees Celsius (C); dew point 13 degrees C; altimeter 30.29 inches of mercury; density altitude 3100 feet.
WRECKAGE and IMPACT INFORMATION
The geographical terrain of the accident site was an estimated 270 degrees radius, approximately 1.5 miles in width by 1 mile in length, of rising terrain. The highest terrain being on the northeast section, at an estimated 4,000 feet mean sea level (msl) and lowest terrain located at the south-southwest section, at an estimated 2, 000 feet msl; approximately one mile in width at its widest point. The wreckage was located on the northeast section of the area at an estimated elevation of 2,990 feet msl, about 8 miles from 49A. The wreckage area had numerous trees of average of 70 feet in height with heavy top and ground foliage. Damage to the surrounding foliage at the accident site indicated that the airplane was right wing low and on a 90-degrees heading when it made its initial contact with a tree, at an estimated height of 50 feet above ground level (agl). The airplane’s right wing fuel tip tank was located underneath that area.
The next impact was with trees, about 80 feet from the initial impact point, at an estimated height of 30 feet agl, scrape marks on the tree’s barks were observed, which ran down the trees to where the airplane came to rest, indicative of low forward energy. The airplane came to rest on a 090 degrees heading. Remnants of the airplane were observed flat on the estimated 25-degrees sloped terrain. The airplane’s left wing fuel tip tank was located several feet forward of the main wreckage with thermal damage. The cabin entrance door with impact and thermal damaged was located several feet away from the right side of the main wreckage.
The left aileron, with impact and thermal damage, was located forward of the main wreckage. The airplane’s wings, cockpit, cabin, minus 3 feet of the empennage section were consumed by thermal damage. Landing gear location among the main wreckage and damage was consistent with them in the retracted position. The remaining empennage section was observed crushed and with a twist deformity toward the right (down slope).
The remnant of the emergency locator transmitter (ELT) was located in the thermal damaged fuselage area. The left stabilizer was observed separated and folded over the right stabilizer, which came to rest on the ground. All flight control surfaces, and /or remnants of them, were present at the accident site. Flight control continuity was established up to the control column section, which was consumed by thermal damage. Majority of the fire was concentrated within the wreckage with an estimated 100 feet in diameter of the surrounding ground foliage consumed by fire. The tree top foliage along the energy path and in front of the wreckage was observed with fuel burns.
The firewall and engine, with cowling attached, were intact with impact and thermal damage. Both came to rest on their right side. Engine controls continuity was established from the engine to the thermal damaged engine control levers section. The three bladed propeller remained attached to the engine crankshaft. All three of the propeller blades were loose and rotated freely at the hub. One blade was observed bowed forward. The second blade was observed twisted and bent aft. The third blade was observed bent aft from the hub base. The propeller’s spinner remained intact with minimal damage.
A post recovery wreckage examination was performed by the airframe and engine manufacturer with National Transportation Safety Board (NTSB) oversight. The examination revealed remnants of the engine fuel mixture, propeller, and throttle control cables were consistent with full forward position. Remnants of the engine cowl flap control cable were consistent with the open position. Fuel tank selector position could not be determined due to the thermal damage. The left and right fuel caps were engaged in the adapter ring. The debris free pitot tube was separated and with thermal damage. The left and right flap actuator extension could not be measured due to thermal damage. Molten aluminum captured the flap roller in a position consistent with the left and right flap in the retracted (up) position. The elevator trim actuator measured approximately 0.6 inches, corresponding to an approximate 13 degrees tab down (surface up) position.
The engine exhibited varying degrees of impact and thermal related damage. The thermal damage was concentrated on the aft portion of the engine in addition to the left side cylinders. The upper ignition leads and all fuel and oil hoses on the back side of the engine were with thermal damage. The engine remained attached to the mounting tunnel assembly and various cables, hoses, and wires. The front left engine mount fractured, the other three were intact. Engine accessories remained attached. The fuel pump was removed and rotated freely by hand. The fuel pump drive coupling was intact and undamaged. The fuel pump inlet fitting separated flush with the vapor separator housing. The throttle body and metering assembly exhibited impact related damage with the metering shaft visually bent in an upward orientation. The top spark plugs were removed and the engine was rotated by hand using the propeller flange. Thumb compressions and valve train continuity were established on each of the six cylinders. Accessory gear continuity was established during the rotation of the propeller flange. The engine rotated freely by hand with no binding or stiffness noted. The oil filler cap/dipstick was removed and a small amount of residual oil was observed on the bottom of the dipstick.
The Georgia Bureau of Investigation, Division of Forensic Sciences in Decatur, Georgia, conducted a postmortem examination of the pilot and passengers. The cause of death for all was blunt force trauma and thermal injuries.
The FAA Civil Aeromedical Institute (CAMI) conducted toxicology testing on specimens from the pilot. The tests were negative for carbon monoxide, cyanide, and ethanol. The drug test was positive for Bupropion and Quetiapine.
With the NTSB oversight the engine was run at the manufacturer’s facility. The engine run did not indicate any abnormalities that would have prevented normal operation and production of rated power.
A propeller teardown examination was performed at the manufacturer’s facility with FAA oversight. The examination revealed that all propeller damage were consistent with impact forces. Internal impact marks were consistent with blades in the low pitch position at time of impact. Blade bending, twisting, and overall propeller damage were those associated with power apply at impact.
A research by the Federal Aviation Administration revealed that on May 7, 2010 the airplane’s altimeter had a discrepancy that prevented the instrument from working correctly. The airplane’s maintenance records did not reflect any corrective action to the altimeter.
The drugs detected in the pilot’s toxicology testing are used to treat psychiatric conditions. The uses of those drugs are disqualifying for a FAA medical certificate and were not reported on the pilot’s most recent medical application form. The condition(s) and the medications can degrade mental performance and may result in impaired judgment.
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