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20050430010049I

Incident · Minor damage
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FAA incident report · Amtr VANS RV-8 · Concord, CA · April 30, 2005

FAA Aviation Safety Information Portal

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Date
April 30, 2005 · 13:25 local
Place
Concord, CA
Airport
Buchanan Field
Phase of flight
Roll-Out (Fixed Wing)
Operating rules
General operating rules (Part 91)
Damage
Minor damage
Aircraft
N427GS
Reported as
Amtr VANSRV8
People aboard
2
Fatal injuries
0
Pilot’s flight hours
42 total42 in this make and model25 in the last 90 days
N427GSRegistered now · Stofer Gerhard VANS RV-8S/N 80199 · Built 2004Airframe modelStofer Gerhard VANS RV-8Engine modelAmateur-built UNKNOWN ENG

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) The pilot privacy data omitted was flying the aircraft. On short-final to ccr runway 19R, he was redirected to land runway 19L. Pilot states: as he set-up, the aircraft was in a crab condition. He reports touching down normally on his r/h then l/h MLG, and finally the tail wheel. During rollout, increasing amounts of right rudder and aileron input were required, to the point where he "ran out of controls" in his attempt to remain on the runway pavement. At this point, pilot considered going around, but decided otherwise as the path of departure would have been into the wind sock pole between the runways. The pilot ^privac^ continued the landing. He determined he could exit on taxiway kilo and be out of danger. As the manuever was executed at an approximate speed of 15 knots, the l/h wheel bearing retaining ring failed, causing the wheel to come to a sudden stop, and the aircraft pivoted about that axis. The resulting force wrinkled the fuselage skin immediately forward of the wing. No structural damage resulted. No visible damage occurred to the landing gear. The pilot/owner ^privac^ will have the landing gear alignment checked, and will advise of any hidden damage if discovered.

As the FAA filed it

(-23) THE PILOT ^PRIVACY DA^ WAS FLYING THE AIRCRAFT. ON SHORT-FINAL TO CCR RUNWAY 19R, HE WAS REDIRECTED TO LAND RUNWAY 19L. PILOT STATES: AS HE SET-UP, THE AIRCRAFT WAS IN A CRAB CONDITION. HE REPORTS TOUCHING DOWN NORMALLY ON HIS R/H THEN L/H MLG, AND FINALLY THE TAIL WHEEL. DURING ROLLOUT, INCREASING AMOUNTS OF RIGHT RUDDER AND AILERON INPUT WERE REQUIRED, TO THE POINT WHERE HE "RAN OUT OF CONTROLS" IN HIS ATTEMPT TO REMAIN ON THE RUNWAY PAVEMENT. AT THIS POINT, PILOT CONSIDERED GOING AROUND, BUT DECIDED OTHERWISE AS THE PATH OF DEPARTURE WOULD HAVE BEEN INTO THE WIND SOCK POLE BETWEEN THE RUNWAYS. THE PILOT ^PRIVAC^ CONTINUED THE LANDING. HE DETERMINED HE COULD EXIT ON TAXIWAY KILO AND BE OUT OF DANGER. AS THE MANUEVER WAS EXECUTED AT AN APPROXIMATE SPEED OF 15 KNOTS, THE L/H WHEEL BEARING RETAINING RING FAILED, CAUSING THE WHEEL TO COME TO A SUDDEN STOP, AND THE AIRCRAFT PIVOTED ABOUT THAT AXIS. THE RESULTING FORCE WRINKLED THE FUSELAGE SKIN IMMEDIATELY FORWARD OF THE WING. NO STRUCTURAL DAMAGE RESULTED. NO VISIBLE DAMAGE OCCURRED TO THE LANDING GEAR. THE PILOT/OWNER ^PRIVAC^ WILL HAVE THE LANDING GEAR ALIGNMENT CHECKED, AND WILL ADVISE OF ANY HIDDEN DAMAGE IF DISCOVERED.