N456TW

Substantial
None

W10 TAILWINDS/N: 02-1217

Accident Details

Date
Wednesday, May 31, 2023
NTSB Number
CEN23LA211
Location
Penrose, CO
Event ID
20230601192277
Coordinates
38.431635, -105.112690
Aircraft Damage
Substantial
Highest Injury
None
Fatalities
0
Serious Injuries
0
Minor Injuries
0
Uninjured
2
Total Aboard
2

Probable Cause and Findings

The failure of the right rudder pedal stop due to an inadequate weld, which resulted in a loss of control on the ground.

Aircraft Information

Registration
Make
W10
Serial Number
02-1217
Engine Type
Reciprocating
Year Built
2007
Model / ICAO
TAILWIND
Aircraft Type
Fixed Wing Single Engine
No. of Engines
1
Seats
2
FAA Model
W10 TAILWIND

Registered Owner (Current)

Name
SCHMIDT GAIL M
Address
307 HIGH MEADOWS DR
City
FLORENCE
State / Zip Code
CO 81226-9486
Country
United States

Analysis

On May 31, 2023, about 0930 mountain daylight time, a Wittman W10 Tailwind airplane, N456TW, was substantially damaged when it was involved in an accident at Fremont County Airport (1V6), Penrose, Colorado. The pilot and passenger were not injured. The airplane was operated as a Title 14 Code of Federal Regulations Part 91 personal flight.

The pilot stated the other pilot in the left seat had just completed three uneventful full-stop landings, then he took over the controls and was flying from the right seat. During the takeoff roll, he applied equal pressure to both rudder pedals. Suddenly the right pedal broke forward and the airplane veered off the left side of the runway. The left-seat pilot was unable assist in controlling the airplane before it struck a berm. The airplane came to rest upright with the main landing gear collapsed, which resulted in substantial damage to the right side of the fuselage and engine mounts.

Postaccident examination by the responding Federal Aviation Administration inspector revealed that the right rudder pedal stop, a U-shaped metal rod welded to the rudder pedal torque tube, broke at the weld bead and the right pedal was beyond the normal forward limit. The inspector reported observing no corrosion, but that there was inadequate penetration of the weld between the rudder stop and rudder pedal torque tube. Figure 1 shows the right pedal condition after the accident.

Figure 1. The right side pedals after the accident. The right pedal is forward of the normal limit. The left pedal is at the normal upright position (courtesy of the pilot).

According to the pilot, the airplane was scratch-built from plans and was not assembled from a kit; therefore, the rudder pedals were fabricated by the original builder. The airframe had accumulated 339.2 hours of total time. There had been no discrepancies or recent maintenance completed related to the rudder pedals.

Data Source

Data provided by the National Transportation Safety Board (NTSB). For more information on this event, visit the NTSB Records Search website. NTSB# CEN23LA211