N112TR

On April 13, 2022, at 0704 mountain daylight time, a Cirrus Design SR22 airplane, N112TR, was substantially damaged when it was involved in an accident near Twin Lakes, Colorado. The pilot sustained minor injuries. The airplane was operated as a Title 14 Code of Federal Regulations Part 91 personal flight.

The pilot reported that he initially leveled off at a cruise altitude of 17,000 ft msl. However, to remain above the cloud tops, he requested to climb to FL210 and then FL230. The climb segments were conducted at full power and full rich mixture. The fuel pump was set to low boost. During the climb from FL210 to FL230, the pilot noted a brief alternate air indication on the PFD. The engine was performing normally and producing full power at that time. Upon leveling off, he reduced engine power to approximately 65% to 75% and adjusted the fuel flow. The alternate air indication extinguished and all engine indications were normal. The pilot noted that he had seen the alternate air indication before and typically reduced engine power “a bit,” which extinguished the indication.

The pilot noted that, about 0657, a “drastic reduction” in engine power occurred. He observed an engine power indication of 10% to 15%. He immediately set the mixture to full rich and the fuel pump to high boost. He then adjusted the power lever in an attempt to restore engine power. None of the actions had any effect. During the descent the flight reentered IMC. After declaring an emergency with Denver Center and establishing best glide airspeed, he turned to a course toward a valley east of the airplane’s current position. About that time, smoke started to enter the cabin and he recalled thinking that restarting the engine was not going to be possible. As the airplane descended through the minimum safe altitude for the mountainous area, the pilot noticed a small circle of yellow/mountain peak appear on the multi-function display (MFD) indicating terrain was near; he decided to set the engine mixture control to idle/cutoff and deploy the CAPS. Once the parachute fully deployed, he turned off the electrical system and secured the cabin for touchdown. He recalled contacting the ground “hard” a few seconds later. The airplane came to rest upright in a mountain valley consisting of rocky terrain and low brush. The left wing was damaged at the main landing gear mounting point during the CAPS assisted touchdown.

A postaccident examination did not reveal any anomalies with respect to the engine itself. The induction air filter and ducting appeared intact and unobstructed. The induction air system alternate air door was intact and secure. It remained closed when magnetically latched and opened when hand/finger pressure was applied. The right turbocharger assembly appeared intact and was unremarkable. The left turbo compressor vanes were curled with corresponding scraping damage to the housing inlet consistent with contact while the vanes were rotating. The turbine vanes appeared intact with no scraping damage noted. The compressor and turbine vanes rotated freely; however, the shaft exhibited a slight amount of axial play.

Data downloaded from the recoverable data module (RDM) revealed several distinct reductions in engine power during the flight which preceded the final loss of engine power and shutdown. About 0636, the engine speed dropped from about 2,625 rpm to about 2,460 rpm with associated drops in manifold pressure and fuel flow. About 2 minutes later, the engine regained power. This power reduction appeared to coincide with the airplane leveling off at 17,000 ft msl before beginning a climb to FL210.

Then, about 0641, a second reduction in engine speed, manifold pressure, and fuel flow occurred that lasted about one minute. This reduction occurred during the climb to FL210. A third reduction in engine power occurred about 0644 and lasted for about 9 minutes. This reduction appeared to coincide with the airplane leveling off at FL230.

About 0657, another loss of engine power occurred. RDM data indicated that the EGT of the six cylinders dropped from about 1,300-1,400° F to about 150° F. Similarly, the TIT of the left and right turbochargers dropped from about 1,550° F to about 150° F. The manifold pressure dropped from about 30 inches of mercury (in Hg) to about 11 in Hg. The fuel flow initially dropped from about 35 gallon per hour (gph) to 9-15 gph, and then it increased to about 25 gph. During this time, the airplane descended from FL23 to about 16,500 ft msl. The airplane’s airspeed decreased from about 125 knots to about 100 knots.

From about 0659 to 0703, the engine appeared to be recovering; the manifold pressure, TITs, and EGTs were intermittently rising, but the engine ultimately lost power completely when the pilot decided to shut down the engine and deploy the CAPS.

The airplane was equipped with a turbonormalizing system, which incorporated a magnetically latched alternate air door to allow warm, unfiltered air to enter the dual turbocharger units in the event of any restrictions to induction air flow. The Pilot’s Operating Handbook supplement noted that in some instances, if there is an unusual surge in engine power, especially at high altitude, the alternate air door may become unlatched. In that event, the door may be relatched by retarding the throttle momentarily.

The airplane flight manual (AFM) supplement for the turbonormalizing system noted the following engine limitation:

“Do not reduce manifold pressure below 15 inches when above 18,000 ft msl.”

The AFM supplement for the turbonormalizing system Section 3 – Emergency Procedures, Unexpected Loss of Manifold Pressure, stated:

“If for any reason the aircraft experiences an unexpected loss of normal manifold pressure the aircraft will typically revert to operation similar to a normally aspirated aircraft at approximately the same altitude.”

Immediate Action:

1. Adjust power to the minimum power setting required for continued flight to a suitable landing location.

2. Adjust mixture so that the EGTs are between 1,300°F and 1,400°F. Depending on the circumstances, this may require substantial readjustment (either richer or leaner) of the mixture after loss of manifold pressure.

3.

The AFM supplement for the turbonormalizing system Section 3A – Abnormal Procedures, Engine Failure in Flight – Retarding Power Lever to Idle, stated:

Below 18,000 feet:

“Retarding the power lever to idle at or near a full rich mixture setting may cause engine combustion to cease, depending on the position of the fuel pump and altitude.”

WARNING

Inadvertent use of the HIGH BOOST/PRIME position of the electric fuel pump with the power lever near or in the idle position may prevent the engine from regaining power when the power lever is advanced.

Above 18,000 feet:

The manifold pressure should be maintained at or above 15” Hg when the aircraft is operating above 18,000 feet. If the manifold pressure is reduced below 15” Hg and the power lever positioned close to or at idle, the engine may cease combustion.