Quad City Challenger
| Quad City Challenger |
|
|
| Challenger II |
| Role |
ultralight aircraft |
| Manufacturer |
Quad City Aircraft Corporation |
| First flight |
1983 |
| Produced |
1983-present |
| Number built |
3571 (2011)[1] |
| Unit cost |
USD$32,500 (completed aircraft cost, Challenger II LSS XL-65 model, 2011)[1] |
| Variants |
Excalibur Aircraft Excalibur |
The Quad City Challenger is a family of one and two seats-in-tandem, pusher configuration, tricycle landing gear ultralight aircraft that is designed and produced by Quad City Aircraft Corporation of Quad Cities, Illinois. The Challenger was first introduced in 1983.[1][2][3]
Design and development
The Challenger ultralight is a high wing, tricycle gear kit aircraft with a frame structure built from 6061-T6 aluminum alloy tubing fastened with aircraft grade AN bolts and rivets and covered with either presewn Dacron envelopes or standard aircraft fabric. The engine is mounted in pusher configuration and turns the propeller through a reduction drive that uses a cogged tooth rubber belt.[4]
The kit can be purchased in 4 major sub-kits: the Tail Assembly, Fuselage, Wings, and Engine. The factory kit is supplied with the most difficult mechanical work already completed. This includes the primary fuselage framework along with the controls and the basic wing structures assembled at the factory. The kit builder is required to finish the smaller structural components, cover the aluminum frames with fabric, seal and paint the fabric and do the final assembly.[4]
The aircraft has the ability to soar with its motor switched off.[5]
The Challenger design has been criticized for its landing gear, which is a rigid cable-braced type and is subject to being bent during hard landings. A number of after-market suppliers have designed steel gear legs as replacements for the stock landing gear in an attempt to rectify this problem.[6][7]
Variants
- Challenger I (Challenger UL)
- Single seat, 31.5 ft (9.6 m) wingspan gives lower stall speed. Can be fitted with a variety of engines Qualifies as a US "Experimental - Amateur-Built", Light sport aircraft or with F-33 engine as a US FAR 103 Ultralight Vehicle, 800 reported completed and flown by the fall of 2011.[1][1][3][8]
- Challenger I Special
- Single seat, 26 ft (7.9 m) wingspan gives faster roll rate. Engines 40 hp (30 kW) Rotax 447, 50 hp (37 kW) Rotax 503, 64 hp (48 kW) 582 or 60 hp (45 kW) HKS 700E. Qualifies as a US Experimental - Amateur-Built or Light sport aircraft, 300 reported completed and flown by the fall of 2011.[1][3][8]
- Challenger II
- Two seats in tandem, 31.5 ft (9.6 m) wingspan provides more lift and lower stall speed. Can be equipped with floats. Engines 40 hp (30 kW) Rotax 447, 50 hp (37 kW) Rotax 503, 64 hp (48 kW) 582 or 60 hp (45 kW) HKS 700E. Qualifies as a US Experimental - Amateur-Built or Light sport aircraft, 2000 reported completed and flown by the fall of 2011.[1][3][8]
- Challenger II Special
- Two seats in tandem, 26 ft (7.9 m) wingspan gives faster roll rate. Engines 40 hp (30 kW) Rotax 447, 50 hp (37 kW) Rotax 503, 64 hp (48 kW) 582 or 60 hp (45 kW) HKS 700E. Qualifies as a US Experimental - Amateur-Built or Light sport aircraft, 350 reported completed and flown by the fall of 2011.[1][3][8]
- Challenger II CW LSS
- Two seats in tandem, 26 ft (7.9 m). Engine 50 hp (37 kW) Rotax 503. Qualifies as a US Light sport aircraft, 110 reported completed and flown by the fall of 2011.[1]
- Challenger II LSS XL-65
- Two seats in tandem, 29 ft (8.8 m). Engine 65 hp (48 kW) Rotax 582. Qualifies as a US Light sport aircraft, ten reported completed and flown by the fall of 2011.[1]
Specifications (Challenger II)
Data from Challenger.ca[9][10]
General characteristics
- Crew: one
- Capacity: one passenger
- Length: 20 ft (6.1 m)
- Wingspan: 31 ft 6 in (9.6 m)
- Height: 6 ft 0 in (1.83 m)
- Wing area: 177 sq ft (16.47 sq m)
- Empty weight: 460 lb (140 kg)
- Useful load: 500 lb (227 kg)
- Max takeoff weight: 960 lb (435 kg)
- Powerplant: 1 × Rotax 503 twin cylinder inline two stroke piston aircraft engine, 50 hp (38 kW)
- Propellers: 1 propeller, 1 per engine
Performance
See also
- Related development
- Aircraft of comparable role, configuration and era
References
- ^ a b c d e f g h i j Vandermeullen, Richard: 2011 Kit Aircraft Buyer's Guide, Kitplanes, Volume 28, Number 12, December 2011, page 66 Belvoir Publications. ISSN 0891-1851
- ^ Challenger Advanced Ultralight & Light Sport Aircraft - National Ultralight Canada & Quad City U.S
- ^ a b c d e Kitplanes Staff: 2008 Kit Aircraft Directory, page 67, Kitplanes Magazine December 2007 Volume 24, Number 12, Belvior Publications, Aviation Publishing Group LLC.
- ^ a b Cliche, Andre: Ultralight Aircraft Shopper's Guide 8th Edition, pages B-11 & B-71. Cybair Limited Publishing, 2001. ISBN 0-9680628-1-4
- ^ National Ultralight (undated). "Ten Best Reasons". http://www.challenger.ca/tenbest.html. Retrieved 2009-09-24.
- ^ Cliche, Andre: Ultralight Aircraft Shopper's Guide 8th Edition, pages B-75. Cybair Limited Publishing, 2001. ISBN 0-9680628-1-4
- ^ Freedom Flight (undated). "Back 40 Gear Leg - The Best Gear Available for your Challenger". http://www.ultralightassembly.com/back40.htm. Retrieved 2009-10-04.
- ^ a b c d Quad City Aircraft Corporation (undated). "Basic Models". http://www.quadcitychallenger.com/qc-mods.html. Retrieved 2009-09-24.
- ^ National Ultralight (undated). "Challenger II Performance". http://www.challenger.ca/airplane_performance_table.html. Retrieved 2009-09-24.
- ^ National Ultralight (undated). "Challenger II Specifications". http://www.challenger.ca/airplane_specifications_table.html. Retrieved 2009-09-24.
External links