| Crash location | 34.200556°N, 118.358611°W
Reported location is a long distance from the NTSB's reported nearest city. This often means that the location has a typo, or is incorrect. |
| Nearest city | Burbank, CA
37.323275°N, 121.931623°W 294.4 miles away |
| Tail number | N5032C |
|---|---|
| Accident date | 19 Apr 2010 |
| Aircraft type | Beech B35 |
| Additional details: | None |
In the pilot's written statement to the Safety Board, he reported that he was traveling from Modesto, CA, to Burbank, CA. The pilot reported that during descent to Burbank at about 5,000 feet, the airplane was flying at 155-160 miles per hour when it hit slight turbulence while in a 15 degree left turn, and the tail started to flutter. The pilot quickly reduced power and smoothly raised the nose in accordance with the airplane's Pilot Information Manual. This stopped the vibration, which lasted about 3 to 5 seconds. The rest of the approach and landing at the airport was uneventful. During the post-flight inspection, the pilot noticed wrinkles in the left ruddervator. The airplane was inspected by a mechanic, who found that the left ruddervator had a cracked front spar, and the left stabilizer had wrinkled top skin and a cracked rear spar, which was bent up five inches. The pilot did not state if there were any mechanical problems with the airplane prior to the accident.
The airplane's maintenance records were reviewed. In January 2001, the airplane's two rear bulkheads were straightened and redoubled, short cracks were dressed, and new relief flanges were fabricated and installed. Also in January 2001, the empennage skins were redoubled. The airplane was painted as required, the flight controls and systems were reinstalled, and the static control balance was performed. The airplane was inspected for compliance with the pertinent Raytheon (Beechcraft) Service Bulletin. All work was done in accordance with the Service Bulletin, the appropriate Advisory Circular, and the Beechcraft 35 Shop Manual.
In April 2001, the airplane's ruddervators were rebuilt and painted. After the painting, the right ruddervator's static balance was 17.33 inch-pounds (in-lb) moment balance. The left ruddervator's static balance was 17.59 in-lb moment balance. Both static balances were within the Beechcraft Shop Manual's allowable balance parameters of 16.8 to 19.8 in-lb.
In February 2009, the airplane's fuselage and wings were repainted by the owner, then repainted by a certified mechanic shop. The control surfaces were not painted.
After the accident, a mechanic removed and replaced the spars, re-skinned the airplane, used doublers between the spar and the new skin, added a doubler to the center forward of the aft rib, and checked the ruddervator balance. The mechanic stated that the control surface balancing was "perfect."
The pilot reported that he was flying between 155-160 miles per hour (MPH) at the time of the turbulence encounter. The maximum structural cruising airspeed (Vno or Vc) is 161 MPH, and the maneuvering airspeed (Va) is 131 MPH. The pilot was flying above Va when the airplane encountered the turbulence; however, he was not flying above Vno and had no reason to believe that the airplane would encounter turbulence.
The airplane's encounter with turbulence while at an airspeed above maneuvering airspeed, which exceeded the limit load of the stabilizers and ruddervators.