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N711PS accident description

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Crash location Unknown
Nearest city Cheyenne, WY
41.139981°N, 104.820246°W

Tail number N711PS
Accident date 21 Apr 1995
Aircraft type Beech 60
Additional details: None

NTSB description


On April 21, 1995, at 1016 mountain daylight time, a Beech 60, N711PS, was destroyed when it collided with a ground structure in Cheyenne, Wyoming. The commercial pilot was fatally injured. The personal flight, conducted under Title 14 CFR Part 91, originated in Cheyenne at 1006. Instrument meteorological conditions prevailed at the time, and an instrument flight rules (IFR) flight plan had been filed.

According to the Denver Automated Flight Service Station (AFSS), the pilot obtained a weather briefing, filed an IFR flight plan, and took off from Cheyenne at 1006, en route to Colorado Springs, Colorado. A family member said the pilot was en route to a pilot safety clinic. An Air National Guard C-130 hydraulics mechanic witnessed the takeoff of a light twin engine airplane answering the description of N711PS. He said that just before and during rotation to liftoff, he heard a very loud, high pitch whine. The noise "sounded like a turbo" and then stopped abruptly as the airplane passed his position.

The Cheyenne control tower was closed for renovation. As a result, the pilot contacted the Denver Air Route Traffic Control Center shortly after takeoff. According to a taped recording of communications, the pilot reported he had "a problem" and wanted to return for landing. The controller asked the pilot if he was declaring an emergency and the pilot replied, "I have an overboost situation, here. I want to come back and check it out." He was subsequently cleared for the ILS (instrument landing system) runway 26 approach.

NTAP (National Track Analysis Program) radar plots were reviewed and showed N711PS south of the airport and on an easterly heading. The target subsequently joined the localizer and tracked inbound on the ILS 26 localizer course. Radar contact was lost just inside to Horse LOM (locator outer marker).

An Army helicopter mechanic, driving past the Frontier Shopping Mall on Dell Range Boulevard, observed the airplane emerge from the low overcast in a wings-level descent. He said he thought the pilot had executed the VOR-A approach because he was northeast of the airport and travelling in a southwest direction.

He heard the engines "spool up," then the airplane pitched over to a near-vertical attitude and dove into a shopping center parking lot on the airport perimeter. The witness said the airplane struck and destroyed a mall sign and exploded on impact. A secondary explosion followed shortly thereafter.


A review of the airplane maintenance records disclosed the left and right turbochargers were original equipment and were installed after having been overhauled in December and March of 1974, respectively. On July 9, 1993, the left turbocharger wastegate was replaced but no reason was given as to why. The right turbocharger wastegate was not replaced at that time. There were no entries to indicate either turbocharger had been overhauled in the following 21 years of continuous service. The engines had been factory remanufactured and were re-installed on the airplane on June 11, 1974. Analysis of engine oil samples had been routinely performed. The report on the analysis done in April 1995 indicated the left engine oil sample was normal, but the right engine oil sample indicated "critical conditions! Bearing overlay wear. . .piston and liner wear. . .check for proper start-up and operating oil pressures. . .check for excessive blow-by or low compression (emphasis added)." The airplane had received routine annual inspections.


The airplane came to rest next to the shopping center mall sign. There were no skewed ground scars. The engines and propellers were inside craters next to the nose section. The tail section, according to photographs taken immediately after the accident, was leaning against the sign, but was laying inverted next to the fuselage when examined. Numerous small pieces of wreckage was strewn across a grass median and onto the adjacent boulevard. Other small pieces of wreckage were scattered in the parking lot.


An autopsy was conducted by Dr. Patrick C. Allen of Forensic Pathology Consultants, Loveland, Colorado. Toxicological screens were conducted by FAA's Civil Aeromedical Institute (CAMI) and the Wyoming State Crime Laboratory. According to its toxicology report, the Wyoming State Crime Laboratory reported no evidence of drugs or alcohol in urine. Carbon monoxide, however, was measured at 9 percent.


The engines, turbochargers, and propellers were disassembled and inspected at the facilities of Beegles Aircraft Company, Greeley, Colorado, on May 16, 17, and 18, 1995.

Rotational scoring was noted in the turbine section of the left turbocharger (s/n DAR0104). The wastegate, or exhaust bypass valve, was found in the open (spring-loaded) or low boost position. The turbine shaft had fractured in torsional overload.

Rotational scoring was also noted in the turbine section of the right turbocharger (s/n DAR0121). Both bearing journals had been rebored and were 0.010 oversized --- an unapproved repair, according to the manufacturer. The bottom portion of the wastegate butterfly valve that attaches the valve to the input shaft was severely eroded. The pin was missing and the valve was free to rotate on the shaft. The valve was in a closed or high boost position.

Disassembly of the left engine disclosed no anomalies. Disassembly of the right engine disclosed a hole burned through the exhaust valve of number 1 cylinder. The TIT (turbine inlet temperature) probe was burned away. There was no evidence that the right engine was incapable of producing power.

According to a technical representative of Hartzell Propellers, both the left and right propellers were found in positions consistent with, and indicative of, the low pitch/high RPM range.

It was estimated that at the time of the accident, the gross weight of N711PS was 6,100 pounds. Referring to the Cheyenne 1024 meteorological observation (altimeter setting, 29.92 inches of mercury; 33 degrees F. or 0.5 degrees C.), the pressure altitude was computed to be 6,156 feet MSL. According to the performance section of the FAA approved Beech 60/A60 Flight Manual, the airplane should be capable of climbing 370 feet per minute with one engine operating. Additionally, it was computed that the airplane's service and absolute ceilings were 16,100 and 18,200 feet, respectively.


The wreckage was released to the owner's representative on May 18, 1995.

(c) 2009-2018 Lee C. Baker / Crosswind Software, LLC. For informational purposes only.