Accident Overview
On February 23, 2016, at 1115 eastern standard time, a Cirrus Design Corp. SR22, registration N256CD, was substantially damaged during impact with terrain after the deployment of the Cirrus Airplane Parachute System (CAPS). The accident occurred near Palatka Municipal Airport (28J) in Palatka, Florida, following a partial loss of engine power. The private pilot, the sole occupant, received minor injuries.
Flight Details
Visual meteorological conditions prevailed at the time of the accident, and an instrument flight rules flight plan had been filed. The flight departed from Sanford-Lee County Airport (TTA) in Sanford, North Carolina, at about 0820, destined for Leesburg International Airport (LEE) in Leesburg, Florida. The flight was conducted under 14 CFR Part 91 as a personal flight.
Events Leading to the Accident
The pilot reported that while in cruise flight at 7,000 feet mean sea level (msl), he initiated a descent in preparation for arrival at the destination airport. Shortly after beginning the descent, he retarded the throttle "slightly," and the power dropped dramatically, possibly to idle. The propeller continued to rotate, but the pilot did not check the tachometer. He requested and received vectors from air traffic control to the nearest airport and turned toward 28J. During the descent, the pilot cycled fuel tanks, adjusted the mixture, switched magnetos, and moved the throttle full forward and back to idle—all with no effect on engine power. When he determined that the airplane could not reach the airport, he deployed the CAPS at about 1,000 feet msl.
Location and Damage
The airplane came to rest in a residential area, 2.8 nautical miles southeast of 28J, between a backyard shed and a recreational vehicle trailer. The parachute was entangled in power lines. The propeller and nosewheel sustained damage, and the left aileron had separated from the wing. A Federal Aviation Administration inspector noted that both wing fuel tanks were approximately half-full of fuel.
Post-Accident Examination
The airplane was recovered to a storage facility, where the engine was examined. No preimpact mechanical malfunctions were identified. With the engine still installed on the airframe, an engine test-run was performed. The engine started after two revolutions and ran continuously. After a brief warmup, the throttle was advanced to 1,700 rpm for a magneto check, during which the rpm drop was about 100 rpm for each magneto. The throttle was then advanced to full power momentarily, reaching 2,500 rpm, then retarded to idle, where the engine speed dropped to about 800 rpm. The mixture control was then pulled to the idle/cut position, and the engine ceased running.
Engine Monitor Data
Data from an onboard engine monitor were downloaded and plotted. Review of the data revealed no anomalies prior to or after the reduction in engine power and subsequent loss of engine power.