NTSB Factual Report

HISTORY OF FLIGHT

On August 31, 2012, about 1140 Pacific daylight time (PDT), a Beech G35, N4454D, encountered clear air turbulence while on descent to Oceano County Airport, Oceano, California. The owner/pilot was operating the airplane under the provisions of 14 Code of Federal Regulations (CFR) Part 91. The commercial pilot and two passengers were not injured; the airplane sustained substantial damage to the fuselage structure. The cross-country personal flight departed Tulare, California, about 1100, with a planned destination of Oceano. Visual meteorological conditions prevailed, and no flight plan had been filed.

The pilot reported that while in descent to land at Oceano at 2,500 feet he encountered a turbulence event that lasted about 2 seconds. He stated that his indicated airspeed was about 180 miles per hour; he immediately reduced power, and slowed the airplane to about 140 miles per hour. He continued the approach without incident and landed.

After landing, the pilot observed deformities along the fuselage, and determined that further examination of the airplane was warranted. Maintenance personnel examined the airplane, and discovered substantial damage to the tail section of the fuselage.

The pilot notified the NTSB on September 6, 2012, after he was advised by the maintenance personnel of the damage.

TESTS AND RESEARCH

The airplane was examined and documented on September 11, 2012, by investigators from the FAA and the airplane manufacturer's representative. A complete copy of the examination report is attached to the accident docket.

The examination report documented the following damage to the airplane:

REAR FUSELAGE

Wrinkles were observed to the left and right side fuselage skins that ran from the top of the fuselage diagonally down and aft. The lower fuselage skin was torn. Wrinkles were present in the lower fuselage that radiated from the left bottom corner of the fuselage and from the right bottom corner of the fuselage. The left and right side I-stringers, which join the two bottom sides of the fuselage side skins to the lower fuselage skin, were buckled. The bulkhead was cracked in three areas around the bulkheads inner lightening hole cut-out.

An interior inspection noted that the I-stringers and G-stringers were buckled in the area of the bulkhead.

FLIGHT CONTROLS

The left elevator was determined to have a 19.87 in.-lbs. trailing edge heavy moment, and the right elevator was determined to have a 19.86 in.-lbs. trailing edge heavy moment. These values exceed the published Shop Manual limits for the trailing edge heavy moment airworthiness specification.

The manufacturer's representative stated that the rear fuselage damage to the fuselage sides and lower skin observed was consistent with damage seen on other G35 airplanes that had experienced turbulence while in high speed descents; a one-time overload in a tail downward direction.

The presence of the abundance of oil and grime in the rear fuselage, and the lack of oil and grime in the bulkhead cracks were consistent with the cracks having occurred recently.

ADDITIONAL INFORMATION

A review of the Beechcraft Bonanza G35 Pilot's Operating Handbook and FAA Approved Airplane Flight Manual, P/N 35-590072-9A4, Section II Limitations, page 2-3 airspeed limitation values and page 2-4 airspeed indicator markings, states airspeeds and conditions associated with those airspeeds as follows:

Normal Operating Range

Green arc on the airspeed indicator face

66 to 176 mph

Caution Operating Range

Yellow arc on the airspeed indicator face

176 to 202 mph

Maneuvering speed

Va 131 mph (at maximum gross weight)

Do not make full or abrupt control movements above this speed

Maximum structural cruising

Vc speed is 176 mph

Do not exceed this speed except in smooth air and then only with caution.

A review of the FAA Pilot's Handbook of Aeronautical knowledge revealed the following:

Design maneuvering speed (Va)—the maximum speed at which the structural design's limit load can be imposed (either by gusts or full deflection of the control surfaces) without causing structural damage. It is important to consider weight when referencing this speed. For example,

Va may be 100 knots when an airplane is heavily loaded, but only 90 knots when the load is light.

The pilot reported that the accident airplane was being operated in the Yellow or Caution airspeed range, which is greater than the Va airspeed. At airspeeds greater than Va, the airplane can sustain structural damage during operation.

An unairworthy airframe material condition, such as the observed cracks in the FS272 fuselage bulkhead and the elevator trailing edge heavy moments, would act to lower Va by an unknown amount.

NTSB Probable Cause

The pilot’s exceedance of the design maneuvering speed during descent in turbulence, which resulted in structural damage to the aft fuselage.