NTSB CAROL · Event
Event LAX00LA311
Registry · N7SZ
FAA Aircraft Registry record.
Make / Model
LANCAIR LANCAIR IV
Year of manufacture
2014
Engine
CONT MOTOR IO-550-N (310 hp)
Seats / Engines
2 seats · 1 engine
Last airworthiness date
20140314
ADS-B equipped
Yes — Mode-S A95184
Registrant of record
ZULU AVIATION LLC
Source: FAA Aircraft Registry (releasable master file).
Aircraft involved
Probable cause & findings
The fracture and separation of a control rod in the cyclic flight control system.
Factual narrative
On August 26, 2000, at 0906 hours Pacific daylight time, a Perrucci Revolution Mini-500 experimental helicopter, N7SZ, was substantially damaged during a forced landing near Gridley, California. The student pilot was not injured. Visual meteorological conditions prevailed and no flight plan was filed for the local area personal flight, which departed from the owner's property in Gridley about 0840. The amateur built helicopter was operated by the owner under 14 CFR Part 91. The pilot reported that, while making a turn at 700 feet agl, he felt something break and the fore-and-aft portion of the cyclic flight control system became inoperative (disconnected). He lowered the collective control, reduced engine power, and made a run-on landing in an open field. During the landing the toe of one skid "dug in" and the helicopter came to rest on its side. Postaccident examination revealed that a push-pull tube in the cyclic control system fractured circumferentially in the wall at one end near where a through-bolt attached the rod end fitting to the tube. The assembly was Revolution Helicopters part number 0165. While maneuvering at 700 feet agl, the pilot of the amateur-built helicopter felt something "break" and the fore-and-aft portion of the cyclic flight control system became inoperative (disconnected). He lowered the collective control, reduced engine power, and made a run-on landing in an open field. During the landing the toe of one skid "dug in" and the helicopter came to rest on its side. Postaccident examination revealed that a push-pull tube in the cyclic control system fractured circumferentially in the wall at one end near where a through-bolt attached the rod end fitting to the tube. Source: NTSB Aviation Accident Database (Pre-2008 Archive) Retrieved: 2026-02-12
Verbatim from NTSB's published report. Source file
NTSB_2000_LAX00LA311.txt.
Findings + structured fields enriched from FAA avall.mdb.
Full investigation docket on
data.ntsb.gov ↗.
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