Renegade Technical Specifications
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Renegade Stress Analysis
To further support the integrity of the Renegade design, a complete structural analysis has been performed by Mr. Richard Hiscocks, a former Chief Engineer of DeHavilland Aircraft of Canada. This analysis has been provided to numerous foreign regulatory agencies to facilitate acceptance of the design in countries including Japan, England and Germany, to name a few. Shown are the standards which were used by Mr. Hiscocks in performing the analysis.
Renegade Aircraft Structural Analysis
The Design has been analyzed to the following Codes:
- Airworthiness Standards, Chapter 522 Subchapter C - Structures Gliders and Powered Gliders issued by Transport Canada, Jan. 1986
- European Joint Airworthiness Standards JAR 22 Subpart C - Structure
- British Civil Airworthiness Requirements Section S, Small Light Aeroplanes (CAP 482) draft, 1983
- FAA - CFR - Part 23 Airworthiness Standards, Normal, Utility & Acrobatic Category Airplanes Subpart C-Structure, Jan. 1982
Summary: The design described by the basic Drawing List is eligible for certification in the:
- UTILITY CATEGORY at a Gross Weight of 850 lb.to all the above Standards
- ACROBATIC CATEGORY at a Gross Weight of 700 lb. to Part 23 (9g) Standards
- With the Drawing List amended to Dec. 1988 the Design is eligible for approval in the: ACROBATIC CATEGORY OF JAR 22/522 (10.5)
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| General Information
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| GROSS WEIGHT (max) |
950 LB. |
| EMPTY WEIGHT |
420 - 520 LB. |
| G-LOADING @ 750 lb gross) |
+10 -6 |
| G-LOADING @ 950 lb gross) |
+7.9 -4.7 |
| POWER RANGE |
65 - 100 HP |
| WING SPAN (top) |
21' 3 " |
| WING SPAN (bottom) |
19' 10 " |
| LENGTH |
18' 5 " |
| FUSELAGE WIDTH |
26" |
| WING CHORD |
46" |
| TAIL SPAN |
86" |
| AIRFOIL |
23012 (Semi-Sym) |
PLEASE NOTE: The Renegade conforms to Canadian Advanced Ultralight Regulation TP 101.41. Empty weights may vary due to Avionics, Instruments, type and amount of paint and upholstery selected by the individual builder.
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