20200606007859I

On June 6, 2020 at approximately 1415Z, a Piper archer ii, PA-28-181 single engine aircraft, N62147 departed on a VFR flight from the foothills region (kmrn) airport. The instructional flight to accomplish a flight review was conducted in visual meteorological conditions (VMC) under 14 CFR part 91 operating rules. There were two persons on board. No flight plan was filed for the estimated one hour flight.

The flight departed kmrn to the southwest. When the flight reached the planned altitude of 4,500 feet mean sea level (MSL) the pilot performed clearing turns and started to configure for the maneuver slow flight. After slow flight, the pilot pulled back the power and increased pitch to perform a power-off stall. When the wings were buffeting, the aircraft was pitched nose down and throttle was added. As the aircraft was regaining airspeed, the pilot retracted the first notch of flaps. The pilot stated that as soon as the flaps came up, the nose of the aircraft pointed straight at the ground. The aircraft descended rapidly as they experienced a loss of elevator control. As the aircraft gained speed, the nose began to rise and the pilots used the electric trim to try to maintain altitude. An emergency was declared and the aircraft diverted to hickory regional airport (khky) for the larger runways and fire equipment. The aircraft maintained a higher than normal approach speed due to lack of elevator authority. As the aircraft crossed the numbers of the runway, the power was reduced, the aircrafts nose pitched down and a hard landing occurred where the nose wheel impacted the runway first. At that point, the nose wheel separated from the aircraft and it slid to a stop. The two pilots on board did not receive any injuries.

The investigation found that the elevator turnbuckle that attached to the cable was broke in half. A review of the aircrafts logbooks indicated that the stabilator control system inspection was the subject of a service bulletin (sb) no. 1245A and airworthiness directive (AD) docket no. FAA-2012-0731; directorate identifier 2012-CE-020-AD; amendment 39-17334; AD 2013-02-13 effective March 11, 2013. This AD was prompted by reports of control cable assembly failures that may lead to failure of the horizontal stabilator control system and could result in loss of pitch control. This AD requires inspections of the stabilator control system and replacement of parts as necessary.

The service bulletin stated the compliance time was 15 calendar years? Time in service and thereafter to be accomplished on a reoccurring basis at intervals not to exceed 2000 hours operating time or 7 calendar years whichever occurs first.

The last inspection for this AD occurred on 8/21/2014 with 4690.6 hours total time.

At the time of the incident, the aircraft had 5540 hours total time.

The last annual inspection occurred on 9/25/2019 with 5517.5 hours total time

Next concurrence with the AD for the flight controls would have been scheduled to occur in August 2021 as the aircraft would not reach the 2000 hours by that point.

Contacted NTSB, classified as incident, no report number generated

Ptrs EA68202002864