North Little Rock, AR, USA
N6770X
CESSNA 310F
The commercial pilot was conducting a checkride in the multi-engine airplane with an airline transport pilot-certificated designated pilot examiner. The pilot reported that, during the initial climb after takeoff, the left engine experienced a partial loss of power. At this time, the airplane was climbing at its single-engine best rate-of-climb speed (Vyse). The pilot reported that he was able to maintain control of the airplane with partial right rudder and right aileron inputs, and chose not to shut down and secure the engine because it was still providing "positive thrust." The examiner reportedly agreed with the decision to keep the engine running and to make left turns in the traffic pattern due to the increased number of landing options in that direction. The left turns, toward the partially running left engine, would have decreased the directional control of the airplane. While on the downwind leg of the traffic pattern, the left engine lost further power, and the pilot then attempted to feather the left propeller. Although he moved the left propeller control full aft, the propeller did not feather. Radar data indicated a continual loss of airspeed as the airplane turned from the upwind to downwind leg and from the downwind leg toward the airport. The airplane reached a maximum altitude about 255 ft above ground level on the downwind leg. As it turned toward the airport, the airplane collided with terrain in a 45° left bank and slight nose-down pitch attitude and was subsequently destroyed by a postcrash fire. The postaccident airframe, engine, and propeller examinations did not reveal any evidence of a mechanical malfunction that would have prevented normal operation; however, the airplane sustained significant postimpact fire damage, which prevented a full assessment of the fuel system and its configuration at the time of the accident. Examination of left propeller determined it was not in a feathered position at the time of impact, and that both blades appeared to be at or near the start lock position. The propeller was equipped with start locks that engaged below 800 rpm to prevent feathering of the blades during engine shutdown on the ground. In the event of an in-flight engine shutdown, the propeller must be feathered before engine speed decays to 800 rpm. It is likely that the pilot allowed the left engine rpm to decay below the start lock engagement speed, which prevented the propeller from feathering and, instead, remain windmilling. This would have resulted in a large amount of parasitic drag and a significant decrease of the airplane's single-engine climb performance. Due to the windmilling propeller, it is likely that the airplane would not have been able to maintain altitude even if the pilot had maintained Vyse; however, the pilot should have maintained this speed to minimize altitude loss and maintain controllability of the airplane. As the pilot maneuvered the airplane back toward the airport, he allowed the airspeed to decay such that the airplane no longer had the flight control authority to counteract the yaw and roll produced by the operating right engine, which resulted in a loss of control at a low altitude.
HISTORY OF FLIGHTOn May 5, 2016, about 1331 central daylight time, a Cessna 310F twin-engine airplane, N6770X, impacted terrain following a loss of control during approach for landing at North Little Rock Municipal Airport (ORK), North Little Rock, Arkansas. The designated pilot examiner was fatally injured and the commercial pilot sustained serious injuries. The airplane was destroyed by a postimpact fire. The airplane was registered to and operated by Lashbrook, Inc., under the provisions of Title 14 Code of Federal Regulations (CFR) Part 91. Day visual meteorological conditions (VMC) prevailed, and no flight plan was filed for the local instructional flight, which was originating at the time of the accident. The accident occurred during an airline transport pilot checkride administered by a Federal Aviation Administration (FAA) designated pilot examiner. The pilot successfully completed the oral examination before the flight. Following the oral examination, the pilot and examiner discussed the planned sequence for the checkride, which was to depart ORK under visual flight rules, conduct maneuvers south of the airport, then conduct multiple instrument approach procedures to a nearby airport before returning to ORK. The pilot reported that he and the examiner also agreed to work together if an actual emergency occurred during the flight. The pilot stated that he and the examiner did not identify any anomalies with the airplane during the preflight inspection. He noted that the fuel tanks were filled before the flight, and that the fuel samples collected during the preflight inspection did not contain water or particulates. The pilot stated that the left engine started uneventfully. The examiner used a fuel crossfeed procedure to start the right engine using the left fuel auxiliary pump. The pilot did not recall why the examiner performed the crossfeed engine start or if he was simply demonstrating the procedure. Following the right engine start, the pilot repositioned the fuel selectors to a normal configuration (left engine using fuel from the left fuel tank, right engine using fuel from the right fuel tank). The pilot stated that he visually verified the correct position of the fuel selectors and felt the associated handle detents. He then verbally confirmed the positions of the fuel selectors before taxiing the airplane from the ramp. The before-takeoff engine runup was uneventful, during which the pilot did not identify any anomalies with either engine or their respective propellers. The pilot completed the before-takeoff checklist, which included verifying that both auxiliary fuel pumps were in the normal "ON" position, before he taxied the airplane onto runway 5 for takeoff. The pilot performed a normal takeoff from runway 5 and retracted the landing gear during initial climb on the upwind leg. He stated that, during initial climb about 700 ft mean sea level (msl), there was a noticeable change in engine sound and the airplane began to yaw left. He reported that the airplane was climbing at 111 mph (single-engine best rate-of-climb speed, Vyse) when the left engine experienced a partial loss of power to 2,200 rpm. He applied partial right rudder and right aileron inputs to correct for the resulting left yaw. He told the examiner that the left engine was still providing "positive thrust" and stated that they both agreed to keep the left engine running. The pilot stated that the airplane was able to climb to 800 ft msl, at which point he and the examiner agreed to make left turns in the traffic pattern due to the increased number of landing options located immediately north and northwest of the airport. The pilot reported that he was able to maintain 800 ft msl during the left turn from the upwind leg to downwind leg. The pilot stated that the left engine lost additional power during the downwind leg and eventually was unable to provide positive thrust, at which time he decided to feather the left propeller and shut down the engine. The pilot recalled moving the left engine throttle to the idle-stop and moving the left propeller control full-aft; however, he did not recall if he moved the left mixture control to the fuel cutoff position. The pilot postulated that the left propeller did not feather, because full right rudder and right aileron inputs were still required to maintain control of the airplane. The pilot then made a left turn from the downwind leg toward the airport. He stated that, during the left turn, the airplane's airspeed continued to decrease, and that the airplane collided with terrain in a 45° left bank and slight nose-down pitch attitude. After the accident, he was able to exit the airplane from the left cabin door with moderate burns to his head and left leg. He made multiple attempts to extricate the unresponsive examiner from the burning wreckage, during which he sustained serious burns to his face and arms. According to available radar track data, the airplane appeared on radar at 800 ft msl at 1329:43, shortly after it had departed runway 5 and did not climb above 800 ft msl during the remainder of the flight. The airplane continued on the upwind leg for about 24 seconds before it entered a left turn to a southwest heading of 225°. The left turn to the downwind leg took about 29 seconds to complete, which corresponded to an average turn rate of about 6° per second and a turn radius of about 1/3 mile. After completing the left turn to the downwind leg, the airplane continued southwest at 800 ft msl until the final recorded radar return at 1330:56. The final radar return was about 0.28 miles northeast of the runway 17 displaced threshold and 845 ft north of the initial impact with the ground. Airplane performance calculations based on available radar track data and meteorological data indicated that the airplane initially maintained a true airspeed between 98 mph and 111 mph during the upwind leg from runway 5; however, the true airspeed decreased to 97 mph during the left turn to the downwind leg. During the final 20 seconds of recorded radar data, the true airspeed continued to decrease to as low as 89 mph. A witness reported seeing the airplane take off from runway 5 and climb to about 500 ft above ground level (agl) before it began to descend in a nose-up pitch attitude. The witness stated that he did not hear any anomalies with the airplane's engines. He reported that the airplane momentarily entered a steep-banked left turn before it reduced its bank angle to maintain a shallow left turn. The witness stated that the airplane continued to descend during the left turn until he lost sight of the airplane behind a hangar. Believing the airplane was going to crash, the witness drove his truck toward the airplane's last observed position. When he reacquired the airplane, it was still flying in a shallow left turn north of the airport at a slow speed. Although the witness could not hear the airplane's engines from inside his truck, he observed that both propellers were still rotating. The witness stated that the airplane appeared to fly over the water department's storage tanks in what he believed was an attempt to land in a grass area east of runway 17. The witness took a photograph of the airplane shortly before it impacted the ground and burst into flames. According to the file metadata, the photo was captured at 1330:59. A review of the photo established that the airplane was in a 45° left-wing-down bank and a slight nose-low pitch attitude. Additionally, the airplane was on a southerly heading at or below treetop level. A surveillance camera partially captured the impact sequence. The surveillance camera's field of view was aligned to the southwest and focused primarily on an industrial yard located about 450 ft east of the initial impact point. At 1331:00.35, the airplane appeared in the upper right corner of the frame; however, the airplane was partially obscured by a tree that was positioned between the camera and the initial impact point. At 1331:00.54, a fire/explosion emerged and continued to grow as the impact sequence progressed from right to left over a period of about 2.6 seconds. At 1331:02.35, the left engine emerged from the central explosion, tumbling away from the main wreckage, and came to rest in an open field about 1331:07.35. There was a ground fire along the debris path and the associated smoke plumes appeared to drift toward the southeast. There was a power interruption to the surveillance camera between 1331:15.78 and 1337:35.72. When the footage resumed, a majority of the ground fire had subsided; however, the main wreckage remained on fire. There was a second power interruption between 1337:55.76 and 1342:44.66. After the footage resumed, the fire at the main wreckage had been extinguished by responding fire department personnel. PERSONNEL INFORMATION--- Pilot --- According to FAA records, the 30-year-old pilot held a commercial pilot certificate with single-engine land, multi-engine land, and instrument airplane ratings. He was type-rated for the Mitsubishi MU-300 and Hawker 400 twin-turbofan business jets. His most recent FAA first-class medical certificate was issued on November 25, 2015, with no restrictions or limitations. The pilot's application for the airline transport pilot certificate, dated May 4, 2016, listed a total flight time of 950 hours, of which 612 hours were accumulated in multi-engine airplanes. He reported 377 hours of flight experience as pilot-in-command, 194 hours at night, 162 hours in instrument conditions, and 4 hours in Cessna 310F airplanes. The pilot was a captain with the Air National Guard who typically flew four-engine turboprop Lockheed C-130 airplanes. According to available records, the pilot's most recent military flight was flown on April 9, 2016, in a Lockheed C-130H3 airplane. --- Pilot Examiner --- According to FAA records, the 56-year-old pilot examiner held an airline transport pilot certificate with a rating for airplane multi-engine land and commercial privileges for airplane single-engine land and sea. He was type-rated for the Cessna 500, Cessna 560XL, Cessna 650, Dassault Falcon 50, and Dassault Falcon 900 business jets. He also held a flight instructor certificate with airplane single- and multi-engine and instrument airplane ratings. His most recent FAA second-class medical certificate was issued on July 24, 2015, with a limitation for corrective lenses. His initial authorization as an FAA designated pilot examiner was on September 28, 1995, and his latest examiner renewal was approved by the FAA on January 21, 2016. He was designated an examiner for private, commercial, instrument airplane, air transport pilot, flight instructor, flight instructor renewals, sport pilot, and sport pilot instructor certificates. He was authorized to administer checkrides in single-engine land airplanes, single-engine sea airplanes, and small multi-engine airplanes. The pilot examiner's flight history was established using his logbook. The final logbook entry was dated May 2, 2016, at which time he had accumulated 12,214 total hours of flight experience. He had logged 11,967.2 hours as pilot-in-command, 4,217.4 hours in single-engine airplanes, and 7,918.3 hours in multi-engine airplanes. He had accumulated 1,405.7 hours at night, 1,121.9 hours in actual instrument conditions, and 111.9 hours in simulated instrument conditions. He had flown 80.6 hours during the year before the accident, 74.4 hours during the 6 months before the accident, 57.2 hours during the 90 days before the accident, and 17.2 hours during the month before the accident. There was no record that he had flown during the 24 hours before the accident. The examiner had flown 20.2 hours in the accident airplane make/model during year before the accident. His most recent flight review, as required by 14 CFR 61.56, was completed on April 17, 2016. AIRCRAFT INFORMATIONThe airplane, serial number 310-0070, was manufactured in 1961 and was a low-wing monoplane of conventional aluminum semimonocoque construction. The airplane was powered by two 260-horsepower, 6-cylinder, Continental IO-470-D reciprocating engines. The engines provided thrust through two constant-speed, full-feathering, two-blade, Hartzell HC-C2YF-2CUF propellers. The five-seat airplane was equipped with a retractable tricycle landing gear and wing flaps and had a maximum allowable takeoff weight of 4,830 pounds. The airplane had two fuel tanks, one located at each wingtip, and a total fuel capacity of 100 gallons. The FAA issued the airplane a standard airworthiness certificate on February 6, 1961. The owner/operator, Lashbrook Inc., purchased the airplane on May 3, 2015. According to maintenance documentation, the most recent annual and 100-hour inspections were completed on May 1, 2016, at 6,035.3 total airframe hours. The recording hour meter was destroyed during the postimpact fire, which precluded a determination of the airplane's total service time at the time of the accident. The static system, altimeter system, automatic pressure altitude reporting system, and transponder were last tested on May 9, 2014. As of the most recent annual inspection, the left engine, serial number 105176, had accumulated a total service time of 3,020.5 hours since new and 324.2 hours since being overhauled on August 1, 2003. The left propeller, serial number AN7313B, had accumulated a total service time of 720.1 hours since new and 273.4 hours since being overhauled on July 16, 2007. As of the most recent annual inspection, the right engine, serial number 79315, had accumulated a total service time of 5,937.5 hours since new and 1,735.5 hours since being overhauled on April 16, 1990. The right propeller, serial number AN7312B, had accumulated a total service time of 720.1 hours since new and 273.4 hours since being overhauled on July 16, 2007. A postaccident review of the available maintenance records found no history of unresolved airworthiness issues. According to airplane manufacturer documentation, the minimum controllable airspeed (Vmc) for the airplane was 80 mph, the single-engine best angle-of-climb (Vxse) was 95 mph, and Vyse was 111 mph. METEOROLOGICAL INFORMATIONA postaccident review of available meteorological data established that day visual meteorological conditions prevailed at the accident site. The nearest aviation weather reporting station was located at Bill and Hillary Clinton National Airport/Adams Field (LIT), Little Rock, Arkansas, about 7.7 miles south-southeast of the accident site. At 1253, about 38 minutes before the accident, the LIT automated surface observing system reported wind from 320° at 13 knots with wind gusts of 19 knots, 10 miles surface visibility, few clouds at 25,000 ft agl, temperature 24°C, dew point 5°C, and an altimeter setting of 30.01 inches of mercury. At 1353, about 22 minutes after the accident, LIT reported wind from 340° at 7 knots, surface visibility 10 miles, few clouds at 4,500 ft agl, temperature 25°C, dew point 5°C, and an altimeter setting of 29.99 inches of mercury. AIRPORT INFORMATIONThe airplane, serial number 310-0070, was manufactured in 1961 and was a low-wing monoplane of conventional aluminum semimonocoque construction. The airplane was powered by two 260-horsepower, 6-cylinder, Continental IO-470-D reciprocating engines. The engines provided thrust through two constant-speed, full-feathering, two-blade, Hartzell HC-C2YF-2CUF propellers. The five-seat airplane was equipped with a retractable tricycle landing gear and wing flaps and had a maximum allowable takeoff weight of 4,830 pounds. The airplane had two fuel tanks, one located at each wingtip, and a total fuel capacity of 100 gallons. The FAA issued the airplane a standard airworthiness certificate on February 6, 1961. The owner/operator, Lashbrook Inc., purchased the airplane on May 3, 2015. According to maintenance documentation, the most recent annual and 100-hour inspections were completed on May 1, 2016, at 6,035.3 total airframe hours. The recording hour meter was destroyed during the postimpact fire, which precluded a determination of the airplane's total service time at the time of the accident. The static system, altimeter system, automatic pressure altitude reporting syst
The pilot's failure to promptly feather the left propeller upon the initial loss of engine power shortly after takeoff and his failure to maintain airspeed while maneuvering with one engine inoperative, which resulted in a loss of control at a low altitude. Also causal was the partial loss of left engine power during initial climb for reasons that could not be determined because examination of the airplane did not reveal any evidence of mechanical malfunction that would have precluded normal operation.
Source: NTSB Aviation Accident Database
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