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ASN Wikibase Occurrence # 133851
Last updated: 5 April 2019
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Date:28-MAY-1996
Time:07:11
Type:Silhouette image of generic MD60 model; specific model in this crash may look slightly different
McDonnell Douglas MD 600N
Owner/operator:McDonnell Douglas Helicopter Systems (MDHS)
Registration: N600RN
C/n / msn: RN001
Fatalities:Fatalities: 0 / Occupants: 1
Other fatalities:0
Aircraft damage: Written off (damaged beyond repair)
Category:Accident
Location:Thermal, CA -   United States of America
Phase: Manoeuvring (airshow, firefighting, ag.ops.)
Nature:Test
Departure airport:Thermal (TRM), CA
Destination airport:
Investigating agency: NTSB
Narrative:
On May 28, 1996, about 0711 hours Pacific daylight time a McDonnell Douglas MD-600 helicopter, N600RN, was destroyed during flight tests at Thermal, California. The pilot was not injured. The helicopter was in a flight test program for FAA certification under 14 CFR Part 27. The specific test point at the time of the mishap was part of a flight strain survey and involved cyclic control reversals.

The pilot set the parameters and executed the cyclic inputs as planned. Almost simultaneous with the aft movement of the cyclic there was a loud noise and immediate vibrations in the aircraft and controls. There was a chase aircraft for the mission and the chase pilot advised that the tail boom had been struck by a main rotor blade and had separated from the airframe. The pilot of the mishap aircraft then experimented with powered flight, but found that the right yaw was not controllable. He elected to continue the power off autorotation with a controllable left yaw. The autorotation was continued to a vacant field with some piles of brush and other desert debris. The pilot used available rotor rpm, cyclic, and collective control to execute a modified autorotation landing. The resultant landing was onto a brush pile with some skid and main rotor blade damage. The engine exhaust was adjacent to dry brush and grass which resulted in a grass fire. The ground fire destroyed the helicopter.
PROBABLE CAUSE:inadequate design of the stress limits for cyclic control of the helicopter.

Sources:

https://www.ntsb.gov/aviationquery/brief.aspx?ev_id=20001208X05818&key=1


Revision history:

Date/timeContributorUpdates
12-Feb-2013 06:42 TB Updated [Aircraft type, Operator, Narrative]
27-Feb-2013 07:59 TB Updated [Time, Aircraft type, Operator, Nature, Departure airport, Source]
21-Dec-2016 19:26 ASN Update Bot Updated [Time, Damage, Category, Investigating agency]

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