Rebel Technical Specifications
Introduction • Description • Specs • Performance • FAQ • Order Info
The structure of the Murphy Rebel has been
designed to meet the airworthiness standards of the U.S.A. FAR Part
23, Subpart C, the U.K. BCAR Section S. and the Canadian TP10141E.
Depending on the gross weight and power selected, it will comply
with the acceleration factors and airspeeds specified for the
normal, utility or aerobatic categories of Part 23.
In general, the structure is conventional and
compliance with these standards has been demonstrated by detailed
analysis using well established methods. In many areas of the
primary structure the strength is set by the minimum gauges of
available material and the margins of safety are very large. A major
portion of the wing structure is redundant and a full scale
component has been tested to support the analysis.
The maximum design loads on the horizontal tail
result from a combination of Balancing and Gust loads at V (D) on
the flight envelope. In addition to the analysis, this structure has
been tested to ultimate loads.
The fuselage is a rugged metal box for
"crash-worthiness", stiffened with a substantial main frame to
support the undercarriage and provide a carry-through structure for
the wing reactions. Engine mounting pick-up points have been
designed for a range of engines up to 160 HP. Provision has been
made for up to three seat and harness attachments that will accept
load factors in excess of 9 G. The fuselage strength has been
verified by static tests.
Since the structure is governed to a major extent
by minimum gauges of stiffness (EI) considerations, high strength
alloys with debatable characteristics from the standpoint of
corrosion and fatigue are not required. Most of the preliminary
structure is comprised of flat skins or formed parts using 6061-T6
alloy. Margins of safety on joints are large and "fail safe"
provisions have been made in many instances.
| GENERAL SPECIFICATIONS |
| Gross Weight |
1650 LB. |
| Empty Weight * |
800-950 lb. |
| G-Loading (Normal Category) |
+5.7 -3.8 |
| Power Range |
80-160 HP |
| Wing Span |
30' 0" |
| Length |
21' 4" |
| Fuselage Width |
44" |
| Wing Chord |
60" |
| Airfoil |
4415 (MODIFIED) |
| * Note: Rotax 912
UL is 1057 lb. gross weight to conform to Canadian Advanced
Ultralight Regulation TP 101.41. Empty weights may vary due to
Avionics, Instruments, type and amount of paint and upholstery |
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