NTSB Identification: WPR13FA284
14 CFR Part 91: General Aviation
Accident occurred Sunday, June 23, 2013 in Boulder City, NV
Aircraft: BEECH A45, registration: N434M
Injuries: 2 Fatal.

This is preliminary information, subject to change, and may contain errors. Any errors in this report will be corrected when the final report has been completed. NTSB investigators either traveled in support of this investigation or conducted a significant amount of investigative work without any travel, and used data obtained from various sources to prepare this aircraft accident report.

On June 23, 2013, about 1443 Pacific daylight time, a Beech A45, N434M, collided with terrain during a forced landing near Boulder City, Nevada. The airplane was registered to, and operated by, Jet Test and Transport LLC under the provisions of 14 Code of Federal Regulations (CFR) Part 91. The commercial pilot with a certified flight instructor (CFI) certificate and one passenger sustained fatal injuries; the airplane sustained substantial damage to the wings and fuselage from impact forces. The cross-country personal flight departed Chandler, Arizona, at an undetermined time with a planned destination of North Las Vegas Airport, Las Vegas, Nevada. Visual meteorological (VMC) conditions prevailed, and no flight plan had been filed.

Preliminary information from the Federal Aviation Administration (FAA) indicated that the pilot contacted Las Vegas Terminal Radar Approach Control (LAS TRACON). The airplane was at 9,500 feet mean sea level (msl); the pilot requested priority handling because an engine chip light had illuminated. Shortly thereafter, the pilot stated that he had lost a cylinder, declared an emergency, and he was going to attempt to land at Boulder City Municipal Airport (BVU). The pilot reported that he was at 3,800 feet with the landing gear down, and the situation was under control. TRACON approved him to switch to the BVU common traffic advisory frequency, but there was no other contact from the pilot.

The IIC and investigators from the FAA examined the wreckage at the accident scene.

The debris path was about 80 feet long and 80 feet wide. The main wreckage came to rest upright, and was 40 feet from the first identified point of contact (FIPC), which was a circular ground scar with a narrow ground scar to the right that was perpendicular to the debris path. At the end of the narrow ground scar were red lens fragments that were strewn several feet along the direction of the debris path. The three-bladed propeller separated, and was in the FIPC.

About 6 feet into the debris path along the centerline was a piece of engine cowling, the number six cylinder, and the number six connecting rod. The piston remained within the cylinder, but the piston pin was missing, and the boss area was damaged. The connecting rod exhibited crush damage at the piston pin end, which was somewhat rectangular in shape. The cap remained attached to the connecting rod with a bolt on one side; the nut was loose, and the cap rotated freely on the bolt. The other cap bolt remained in place, but the nut was off and not recovered.

The front of the airplane from the front cockpit forward sustained heavy crush damage. The wings bent up about 45°; the engine remained attached, but angled down so that the propeller flange was on the ground. The crankcase had a hole from the number six cylinder base across the top and halfway to the number five cylinder base. Case pieces were scattered across the top of the engine. The inside of the engine in this area exhibited numerous strike marks and damage. The crankshaft journal was not scarred or discolored.

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