N3591P

HISTORY OF FLIGHTOn June 16, 2016, at 0830 eastern daylight time, a Piper PA-31-325, N3591P, was destroyed when it collided with terrain while on approach to University Park Airport (UNV), State College, Pennsylvania. The airline transport pilot and the passenger were fatally injured. The airplane was owned and operated by Aeronational, Inc. Instrument meteorological conditions prevailed, and an instrument flight rules flight plan was filed for the on-demand air taxi flight, which was conducted under the provisions of Title 14 Code of Federal Regulations (CFR) Part 135. The flight departed Washington County Airport (AFJ), Washington, Pennsylvania, about 0800.

According to the operator, the passenger was a regular customer who was routinely flown to UNV. The pilot was familiar with the passenger and the route and had completed the flight numerous times.

Radar and voice communication information from the Federal Aviation Administration (FAA) revealed that, at 0824:35, air traffic control (ATC) provided the pilot with a heading to intercept the final approach course for the instrument landing system RWY 24 approach at UNV and cleared the airplane for the approach. At 0825:30, the pilot was advised that radar services were terminated and was instructed to contact the tower controller at UNV.

At 0825, the pilot contacted the UNV tower controller and announced, "…with you on the approach." The tower controller acknowledged the call and issued a landing clearance, which the pilot acknowledged. There were no further communications with the pilot despite multiple attempts by ATC.

At 0843:50, an airport operations ground vehicle operating at the approach end of runway 24 identified smoke in a wooded area about 1 mile northeast of the airport and notified control tower personnel. The source of the smoke was later identified as the accident airplane. PERSONNEL INFORMATIONThe pilot held an airline transport pilot certificate with ratings for airplane single-engine land, multiengine land, and instrument airplane. His most recent FAA first-class medical certificate was issued March 7, 2016, with the limitation, "Not valid for any class after 3/31/2017." The pilot reported 12,400 total hours of flight experience on the date of the examination, 350 hours of which were during the previous 6 months.

Company training records indicated that the pilot had received the training required by the company's operations and training manuals. The pilot had completed the required annual ground training on January 18, 2016. His last airman competency check was completed satisfactorily on January 18, 2016, in the accident airplane. Pilot duty records indicated compliance with the flight and duty time requirements of Title 14 CFR Part 135. The pilot had just returned from 1 week of vacation, and the accident flight was his first flight since returning to duty. AIRCRAFT INFORMATIONAccording to FAA records, the airplane was manufactured in 1980. Its most recent annual inspection was completed February 19, 2016, at 15,999.6 total aircraft hours, about 44 hours before the accident.

The airplane was equipped with a King KAP/KFC 200 flight control system (autopilot). According to the operating instructions for the airplane's autopilot system, the system's approach mode captures localizer course and glideslope indications when properly configured by the pilot. The system will capture from either above or below the glideslope. No system limitations were published regarding the altitude above the glideslope from which the system would not capture or the rate of descent above which the system would not capture.

A certification engineer for the autopilot manufacturer stated that a descent rate of 1,000 ft per minute (fpm) was "normal" to capture the glideslope from above. The operator's director of operations said that the autopilot in the accident airplane was unlikely to capture the glideslope from above at descent rates greater than 500 fpm.

It could not be determined if the autopilot was in use during the approach, or which operational modes may have been engaged. METEOROLOGICAL INFORMATIONAt 0853, the weather recorded at UNV included an overcast ceiling at 300 ft, calm wind, and visibility 1 statute mile in mist. The temperature was 17°C and the dew point was 17°C; the altimeter setting was 29.80 inches of mercury. AIRMET Sierra for instrument meteorological conditions and mountain obscuration was in effect for the area surrounding the accident site at the time of the accident. AIRPORT INFORMATIONAccording to FAA records, the airplane was manufactured in 1980. Its most recent annual inspection was completed February 19, 2016, at 15,999.6 total aircraft hours, about 44 hours before the accident.

The airplane was equipped with a King KAP/KFC 200 flight control system (autopilot). According to the operating instructions for the airplane's autopilot system, the system's approach mode captures localizer course and glideslope indications when properly configured by the pilot. The system will capture from either above or below the glideslope. No system limitations were published regarding the altitude above the glideslope from which the system would not capture or the rate of descent above which the system would not capture.

A certification engineer for the autopilot manufacturer stated that a descent rate of 1,000 ft per minute (fpm) was "normal" to capture the glideslope from above. The operator's director of operations said that the autopilot in the accident airplane was unlikely to capture the glideslope from above at descent rates greater than 500 fpm.

It could not be determined if the autopilot was in use during the approach, or which operational modes may have been engaged. WRECKAGE AND IMPACT INFORMATIONThe accident site was about 1 nautical mile (nm) from the threshold of runway 24 and about 2 nm beyond the final radar return at an elevation of 1,200 ft mean sea level. The wreckage was examined at the accident site, and all major components were accounted for at the scene.

The wreckage path was located in densely wooded terrain and extended about 450 ft on a magnetic heading of 223°. The initial impact points were in treetops about 70 ft above the ground, and tree trunks and branches displayed impact fractures and sharp, angular cuts along the length of the wreckage path. Both wings were fragmented along the path. Both engines and each main landing gear were separated and scattered along the wreckage path.

The fuselage and empennage came to rest upright facing the direction of travel. The instrument panel, cockpit, and cabin area were destroyed by postcrash fire.

Control continuity could not be established due to extensive impact damage; however; parts associated with the wings, flaps, and ailerons were identified. Sheet metal and cabling associated with the empennage, horizontal and vertical stabilizers, and the elevators were identified, and the cable attach points at all primary flight controls were secure.

Examination of the landing gear and components associated with the flap system were consistent with a 15° flap extension and the landing gear in the down and locked position at the time of impact.

The propeller systems were attached to their respective engines, and all propeller blades exhibited similar twisting, bending, leading edge gouging, and chordwise scratching. Several tree branches and trunks displayed deep, angular cuts and paint transfers consistent with propeller blade contact.

The engines were each damaged by impact and postcrash fire. The left engine displayed extensive thermal damage. The magnesium oil sump and the accessories mounted to the accessory section were consumed by fire, and the damage and contamination produced by the fire precluded rotation of the engine. The single-drive, dual magneto was consumed by fire and could not be tested. Borescope examination of the cylinders revealed normal operational deposits and wear and no preimpact anomalies.

The right engine displayed extensive thermal damage. Impact damage to the No. 2 cylinder precluded rotation of the engine. The single-drive, dual magneto was damaged by fire and would not produce spark when rotated. Borescope examination of the cylinders revealed normal operational deposits and wear and no evidence of preimpact anomalies. The No. 2 cylinder was removed, and the engine was rotated by hand at the propeller. Continuity was confirmed from the powertrain through the valvetrain to the accessory section. Compression was confirmed on all cylinders using the thumb method, with the exception of the No. 2 cylinder. ADDITIONAL INFORMATIONPerformance Study

An airplane performance study was conducted based on radar data. As the airplane crossed the precision final approach fix (PFAF), 6.7 nm from the runway threshold, the airplane was 800 ft above the glideslope. As the airplane crossed the PENUE locator outer marker (LOM), 5.5 nm from the runway threshold, the airplane was 500 ft above the glideslope. When radar contact was lost 3.2 nm from the threshold, the airplane was about 250 ft above the glideslope.

At PENUE LOM and at the last radar return, the airplane's position and altitude would have correlated to a full-downward deflection of the glideslope indication in the cockpit.

Interpolation of radar data revealed that, during the last 2 minutes of the accident flight, the airplane's rate of descent increased from 400 fpm to greater than 1,700 fpm. During the final minute of the flight, the rate decreased briefly to 1,000 fpm before radar contact was lost.

Company Standard Operating Procedures (SOP)

According to the operator's SOP, Stabilized Approach, "Flight should be stabilized by 1000 feet HAT [Height Above Touchdown] in IMC [instrument meteorological conditions]…" and further stipulated, "If an unexpected, sustained rate of descent greater than 1000 feet per minute (fpm) is encountered during the approach, a missed approach should be performe...