N1727T

HISTORY OF FLIGHTOn May 29, 2021, about 1000 mountain daylight time, a Cessna 172S airplane, N1727T, was destroyed when it was involved in an accident near Eden, Utah. The flight instructor and student pilot were fatally injured. The airplane was operated as a Title 14 Code of Federal Regulations Part 91 instructional flight.

According to the airplane operator, ATP Flight School (ATP), the accident flight was an introductory training flight designed to assess the student pilot’s skill level. Federal Aviation Administration automatic dependent surveillance-broadcast (ADS-B) data showed that the flight departed ATP’s local base at Ogden-Hinckley Airport (OGD), Ogden, Utah, about 0941 and immediately turned onto an easterly heading. The ADS-B data ceased 5 miles east of the departure airport about 0946, when the airplane entered Ogden Canyon at an altitude of 6,600 ft mean sea level (msl), which was about 1,000 ft above ground level (agl). The airplane was subsequently tracked by radar 9 miles east of OGD starting about 0949. The airplane flew south and then turned northwest while maintaining an altitude of about 2,000 ft agl. About 0955, the airplane turned to the northeast into a canyon where it began a climb over rising terrain. The last ADS-B targets showed that the airplane maintained an altitude of about 7,550 ft msl (1,000 ft agl), as shown in figure 1. At that altitude, the airplane would have been below ridgelines on both sides of its flightpath, as shown in figure 2. The ADS-B track data ceased at 0956:40.

Figure 1. Flight track of accident airplane.

Figure 2. Canyon topography.

The airplane crashed in a valley between two mountain peaks positioned on a northerly heading. A postimpact fire ensued. A Weber County sheriff’s deputy arrived on scene after receiving a call about a potential airplane crash. He could see smoke as he approached the scene. After arriving on scene, the sheriff’s deputy saw the pilot, who appeared to be badly burned with a head injury. The pilot was able to answer questions at that time. According to the sheriff’s deputy, the pilot stated that he “got caught in a downdraft.” PERSONNEL INFORMATIONAccording to ATP, the flight instructor began training with the school in January 2020, about 6 months after his introductory training flight. He subsequently completed the school’s professional pilot course, including his certified flight instructor instrument certificate and multiengine instructor add-on. In November 2020, the flight instructor completed the school’s indoctrination course, which was focused on company practices and procedures.

The flight instructor started working with students at ATP in December 2020. He instructed a total of 17 students between that time and the date of the accident, including the student pilot during the accident flight. Of those 17 students, 5 were participating in an introductory training flight. Of the four introductory training flights that preceded the accident flight, one involved a student who had no flight experience. The flight instructor demonstrated some maneuvers for that student and did not allow him to fly.

The flight instructor had not taken any of his previous introductory training flight students to Powder Mountain, the location where the accident took place. Those introductory training flights mostly took place about 20 to 30 miles northwest of the airport near the salt flats and over Salt Lake.

The flight instructor who was primarily responsible for training the accident pilot (through his private pilot certificate, instrument rating, commercial single-engine land certificate, and commercial multiengine land add-on) recalled that the pilot "worked hard and prepared well for each lesson.” The flight instructor noted that he “never worried about the accident pilot falling behind” and that the accident pilot’s skill “would not lead him [the flight instructor] to believe that he [the accident pilot] would have flown over Powder Mountain for an introductory flight.” Another instructor who completed about 10 flights with the accident pilot stated that he “excelled at each stage check.” AIRCRAFT INFORMATIONThe airplane’s weight and balance at the time of the accident was computed with a basic empty weight of 1,696 lbs, a combined flight instructor and student pilot weight of 469 lbs, and a fuel weight of 318 lbs, resulting in an estimated ramp weight of 2,483 lbs and takeoff weight of 2,475 lbs (both of which were less than the airplane’s maximum gross weight). The airplane’s estimated center of gravity was near the top of the normal category envelope.

The airplane’s rate of climb was calculated using performance charts from the manufacturer’s pilot’s operating handbook. The calculations assumed a 2,550-lb gross airplane weight and an estimated ambient temperature of 12°C (which was based on the airplane’s last recorded altitude of 7,550 ft msl and the 10°C ambient temperature at that point along with the factored standard lapse rate). The calculations showed that, under normal operating conditions, the airplane required a minimum of 2 minutes 49 seconds to climb 1,000 ft (to about 8,750 ft msl) to overfly the mountain peak ahead of the airplane’s flightpath. This calculation also assumed that the airplane did not exceed an indicated airspeed of 72 to 73 knots. At this airspeed and distance to the mountain peak (based on the airplane’s last radar point), the airplane would have reached the peak in 3 minutes 31 seconds. METEOROLOGICAL INFORMATIONThe 0600 upper air sounding wind profile indicated wind speeds of about 10 knots by 7,000 ft msl 20 knots from 14,000 ft msl and above. A sounding analysis indicated the possibility of mountain wave conditions about 10,000 ft msl with updraft and downdraft speeds of about 500 ft per minute near the accident site.

The area discussion forecast for the Salt Lake City area stated that a northwest wind was anticipated through daytime hours with some high clouds and visual flight rules conditions throughout the day. This forecast did not indicate any potential for mountain wave activity on the day of the accident. No significant meteorological information advisories, airmen meteorological advisories, or center weather advisories were active for the time of the accident.

The pilot did not receive weather information for the accident flight from Leidos flight service. No evidence indicated that the pilot requested weather information from ForeFlight before the accident flight. AIRPORT INFORMATIONThe airplane’s weight and balance at the time of the accident was computed with a basic empty weight of 1,696 lbs, a combined flight instructor and student pilot weight of 469 lbs, and a fuel weight of 318 lbs, resulting in an estimated ramp weight of 2,483 lbs and takeoff weight of 2,475 lbs (both of which were less than the airplane’s maximum gross weight). The airplane’s estimated center of gravity was near the top of the normal category envelope.

The airplane’s rate of climb was calculated using performance charts from the manufacturer’s pilot’s operating handbook. The calculations assumed a 2,550-lb gross airplane weight and an estimated ambient temperature of 12°C (which was based on the airplane’s last recorded altitude of 7,550 ft msl and the 10°C ambient temperature at that point along with the factored standard lapse rate). The calculations showed that, under normal operating conditions, the airplane required a minimum of 2 minutes 49 seconds to climb 1,000 ft (to about 8,750 ft msl) to overfly the mountain peak ahead of the airplane’s flightpath. This calculation also assumed that the airplane did not exceed an indicated airspeed of 72 to 73 knots. At this airspeed and distance to the mountain peak (based on the airplane’s last radar point), the airplane would have reached the peak in 3 minutes 31 seconds. WRECKAGE AND IMPACT INFORMATIONThe airplane was located in a valley between two mountain peaks positioned on a northerly heading and was consumed by postimpact fire. The accident site was located at a field elevation of about 8,000 ft msl. All major sections of the airplane were accounted for at the accident site. The debris field was small and comprised mostly windshield fragments. The first point of impact was marked by a tree located 30 ft west of the main wreckage.

Flight control continuity for the elevator and rudder was traced from the cockpit to their respective control surfaces. The aileron flight control cables were traced from the left and right wing roots to the respective bellcranks. The cockpit was destroyed by postcrash fire, and the left and right aileron control cable sections from the cockpit to the wing roots were not identified.

The elevator trim actuator measured 1.37 inches, consistent with a 5° trim tab upward deflection, and the flap actuator displayed 0.25 inches of exposed jackscrew, consistent with the flaps in the retracted position.

The engine was damaged by postcrash fire. Mechanical continuity was established throughout the rotating group, valve train, and accessory section as the crankshaft was manually rotated at the propeller. Thumb compression was achieved at cylinder Nos. 2 and 4, and the valves displayed normal lift when the crankshaft was rotated. Cylinder Nos. 1 and 3 exhibited low compression, and the valves displayed some lift during rotation, but the push rods and shrouds were damaged by fire. The magnetos were also damaged by fire and could not be rotated by hand. All eight spark plugs were gray in appearance, consistent with normal wear. Examination of the interior components of the engine using a lighted borescope revealed no indications of catastrophic failure.

Both propeller blades remained attached to the crankshaft at the propeller flange. One propeller blade was bent toward the blade face about midspan and was partially melted at the blade tip. The other propeller blade was bent aft at the blade root.

The postaccident examin...