20020604013379I

Incident · Minor damage

FAA incident report · Amtr Christaviamk · Sherman, TX · June 4, 2002

Date
June 4, 2002
Place
Sherman, TX
Airport
Sherman Municipal Airport
Phase of flight
Normal Cruise
Operating rules
General operating rules (Part 91)
Damage
Minor damage
Aircraft
N49635
Reported as
Amtr Christaviamk
People aboard
1
Fatal injuries
0
Pilot’s flight hours
3,843 total11 in this make and model149 in the last 90 days

From the FAA’s Accident/Incident Data System (AIDS), through its Aviation Safety Information Portal, as reported. The NTSB investigates accidents separately, and its record of an accident is the fuller one. The aircraft is matched to the registry by N-number and event date, checked against the reported make and model; the registry’s history has gaps, so older matches can be wrong. Compare the reported make and model.

What happened

The FAA’s narrative, in sentence case. The FAA writes it in capitals and removes private details.

(-23) While conducting stall tests in phase I for experimental amateur built, up elevator control was lost. Pilot was able to land using elevator trim, aileron and rudder and throttle. Subsequent investigation by FAA maintenance inspector revealed control rod that fastens the two control sticks separated at the elevator turnbuckle attach point. Water was standing in belly, no drain grommets were installed in fuselage. The failure was around a welded tab. Rust was present in ninety percent of the fractured area. The airplane had not been flown in twelve years and had recently been re-certified into a 25 hour phase 1 after the original owner had passed away.

As the FAA filed it

(-23) WHILE CONDUCTING STALL TESTS IN PHASE I FOR EXPERIMENTAL AMATEUR BUILT, UP ELEVATOR CONTROL WAS LOST. PILOT WAS ABLE TO LAND USING ELEVATOR TRIM, AILERON AND RUDDER AND THROTTLE. SUBSEQUENT INVESTIGATION BY FAA MAINTENANCE INSPECTOR REVEALED CONTROL ROD THAT FASTENS THE TWO CONTROL STICKS SEPARATED AT THE ELEVATOR TURNBUCKLE ATTACH POINT. WATER WAS STANDING IN BELLY, NO DRAIN GROMMETS WERE INSTALLED IN FUSELAGE. THE FAILURE WAS AROUND A WELDED TAB. RUST WAS PRESENT IN NINETY PERCENT OF THE FRACTURED AREA. THE AIRPLANE HAD NOT BEEN FLOWN IN TWELVE YEARS AND HAD RECENTLY BEEN RE-CERTIFIED INTO A 25 HOUR PHASE 1 AFTER THE ORIGINAL OWNER HAD PASSED AWAY.