Quad City Challenger updates, updates to the Quad City Challenger.

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1983 - The nose shaft is strengthened by changing from 1 inch X .090 2024 T3 aluminum to  1 inch X .120.

  1984 - The Rotax 447 powered Challenger II prototype is designed, built, tested and production begins.

  1984 - The KFM engine used on the Challenger single-seaters is dropped in favor of Rotax engines.

  1984 - Nylon cores are installed in control sticks at their pivot points, also in 2CT-3  fuselage cross members where the control sticks are attached to the fuselage. This  provides a tighter 'feel' as well as preventing wear and play at pivot points.

  1984 - A nylon core is installed in rear fuselage boom tube (2FB11) to prevent wear and  play in elevator bell crank pivot point.

  1984 - Elevator bell crank horns are changed from 2024 T3 aluminum to stainless steel to   prevent elongation of holes over time.

  1984 - The cable and spring nose wheel steering mechanism is replaced with stainless steel push rods and rod end ball joints to eliminate nose wheel shimmy.

  1984 - The FB11 fuselage cross tube is modified and strengthened by double sleeving in   6061 T6 aluminum.

  1984 - The nose shaft is further strengthened with a T outer sleeve in Chromoly steel.

  1984 - Fabric and Lexan doors are introduced for the single-seat Challenger.

  1984 - The leading edge of both stabilizers are strengthened by double sleeving with 6061 T6 aluminum to prevent wear at attach points.

  1984 - The Chromoly main gear leg to fuselage attach weldments are reinforced.

  1985 - A batch of Hegar reduction drive prop shafts were supplied to the factory undersized. The top pulley bearings would eventually rotate on the shaft causing wear. Owners encountering a faulty shaft were asked to return it to the factory for replacement with the correct shaft at no charge.

  1985 - Rotax mufflers were reinforced at Quad City Aircraft with two welded steel straps to prevent muffler cracking.

  1985 - CSR2, CSR-4 and CSR-6 ribs are added to provide additional bracing for the 2 FB-2 cockpit rail.

  1985 - A stainless steel wrap around exhaust mount was developed to prevent cracking of the Rotax muffler.

  1985 - An optional long range 10 US gallon tank and supporting tray were introduced to  increase endurance to over 3 hours.

  1985 - Main wheel brakes are introduced.

  1985 - An additional attach point on aileron bell crank (1 inch lower than previous) for the aileron pushrod is provided to allow the option of adjusting the ailerons for more aggressive response.

  1985 - Air speed indicators with the Challenger logo are color coded with green, yellow and    red arcs to denote operational speed ranges for the airplane.

  1985 - A triangular gusset is installed to strengthen the junction of the FB11 cross tube  and the 2FB11 rear fuselage boom tube.

  1986 - An additional attach point (1 inch inboard from previous) is provided on the rudder  horns to allow the option of adjusting the rudder for more aggressive response.

  1986 - Flaperons are introduced as an option that reduce stall speed by 5 mph and provide  the function of an in cabin trim system.

  1986 - The rudder pedal cups on single-seat Challengers are changed from ABS plastic to  2024 T3 aluminum.

  1986 - Octagonal steel washers are introduced to prevent chafing between the brake drum   and the wheel that would result in movement of the wheel halves and eventually causing  flat tires.

  1986 - Two large triangular boxed gussets are added to further strengthen the junction of  the FB11 cross tube and the 2FB11 rear fuselage boom tube.

  1986 - Hegar V-belt reduction drive ratio is changed from 2.1 to 1 to 2.2 to 1. This larger top pulley and new ratio greatly reduced harmonics, smoothing operation as well as  allowing greater fuselage clearance for the propeller.

  1986 - The dorsal fin is shortened 1 inch to enhance propeller clearance.

  1986 - The standard propeller diameter is increased from 52 inches to 54, providing an increase in the rate and angle of climb.

  1986 - An optional winter enclosure comprising a wrap around windshield and pair of removable doors are introduced that permit comfortable cold weather operation of the aircraft with cabin heat as well as open air (convertible) operation in the summer.

  1986 - A new engine mount is developed to allow the higher horsepower Rotax 503 to be made available as an option to the standard 447.

  1986 - The Hegar 4 V-belt reduction drive system is replaced with an HTD cog belt system which provides the positive engagement of a tooth belt with the vibration dampening advantages of a reinforced rubber belt. The new system also greatly simplifies belt tensioning and eliminates the previous potential problems of V-belt slippage if adjusted too loosely or excessive crankshaft bearing wear if adjusted too tightly.

  1987 - The zero porosity Dacron covering used on the fuselage, tail feathers, ailerons and wing tips is replaced with pre sewn socks of Stits certified aircraft fabric.

  1987 - The elevator shape is changed from rectangular with a straight trailing edge to one with a curved trailing edge for improved aesthetics.

  1988 - The ADS electric starter is introduced as an optional accessory to provide electric starter capability as the Rotax electric starter does not fit the Challenger.

  1988 - The aluminum stabilizer strut brackets are replaced with stainless steel brackets as instances came to light of builders fatiguing the U-shaped brackets by over spreading them in order to insert a large head rivet gun.

  1988 - The number of stainless steel rivets attaching the inboard aileron hinges is doubled.

  1988 - The 503 powered Challenger II Special is introduced as a clipped wing version (26 foot span in US, 28 foot span in Canada) of the two-seater. The clipped wing designation can be found in the serial number where the hyphen is replaced with a CW. Higher cruise and top speeds accompanied with increased roll rates are the primary differences. Initial flight testing includes a 2500 mile cross country flight (with 2 other Challengers) from Moline Illinois to Lakeland, Florida and return.

  1988 - The single-seat fabric and Lexan doors are replaced with a full wrap around Lexan enclosure as on the two-seat airplanes.

  1988 - The lower engine formers are lowered to provide greater clearance between fuselage and engine to facilitate spark plug access and provide room for a cabin adjustable heater system.

  1988 - Stits certified aircraft fabric becomes available as a zero cost option for the wings to provide longer service life and improved appearance over the old style pre-colored Dacron sailcloth wing covers. A Stits rib kit is made available so older style Dacron wings can be updated to use Stits fabric. Later on the Superflite brand of the same fabric comes into use.

  1988 - The Dacron pre-colored sailcloth wing covers are modified to incorporate 12 ribs per wing in place of the previous 6.

  1988 - Optional streamlined strut and gear fairings become available that reduce the engine off sink rate of the large wing two-seater from 500 ft/min to 330 ft/min greatly enhancing the plane's soaring capability. The streamlined fairings also increase cruise and maximum speeds by 7 miles per hour.

  1988 - Stainless steel jury strut attach brackets are introduced to replace the 6061 T6 aluminum brackets when using the streamlined fairings. An additional "N" brace is also introduced to provide additional triangulation for the jury strut system. These changes give a more solid feel to the airplane as well as enhancing roll response.

  1988 - A 26 foot span Rotax 447 powered clip wing Special version of the single-seater is introduced.

  1989 - Rod end ball joints are introduced in place of clevis forks and pins on the elevator push rods to prevent play developing in the system.

  1989 - Brakes are now supplied pre-welded to the axles to simplify assembly.

  1989 - An optional smoked glass tinted Lexan windshield and winter enclosure becomes available to enhance appearance, decrease summer cabin temperatures and reduce eye strain in bright conditions.

  1989 - The aileron control system geometry is changed to provide lighter stick forces.

1989 - Fiberglass droop wing tips are introduced as a cosmetic option after Challengers so equipped win major awards at Oshkosh and Sun 'N Fun. 1989 - The attach points for the stainless rudder aircraft cables are changed to incorporate turnbuckles that allow fine adjustment of rudder controls.

  1989 - The Hirth 2703 single ignition engine is introduced as an alternative option to the Rotax 503.

Flying on floats - some things you should consider. Click here for more information.

  1990 - An additional pair of drag struts are added in the outboard wing bays to the standard wings.

  1990 - An adjustment system is introduced to simplify brake adjustment.

  1990 - The long awaited aircraft version of the Rotax 503 is introduced providing many improvements over the earlier snowmobile derived engine. 

The major benefits include; 
Dual ignition that provides 2 redundant electrical systems. Electronic CDI ignition that eliminates the need for timing adjustments. A larger crankshaft with improved bearings that greatly increase the engine's overhaul intervals and reliability. A more efficient fuel burn from the 2 spark plugs per cylinder which reduces fuel consumption at cruise from 3.8 gallons per hour to 2.8 gallons per hour and thereby significantly increases range and endurance. A dual ball joint exhaust system isolates the muffler from vibration and eliminates the need for muffler reinforcement by the Challenger factory as well as improving engine breathing. These changes result in a significant improvement in performance (400 to 500 RPM) that increase the standard Challenger II cruise speed to 80 MPH, and maximum speed to 95 MPH as well as increasing the rate and angle of climb.

  1990 - Optional Mylar coated wing sails are introduced to increase the service life of the Dacron sailcloth wing option.

  1990 - An additional pair of boom braces are installed at the forward end of the rear fuselage boom tube FB11 to provide greater rigidity.

  1990 - A redesigned belt tensioning system is introduced for the Hegar drive eliminating the necessity of a drilled shaft and simplifying adjustment. A stainless steel collar provides redundancy that ensures belt tension even if the securing bolt is insufficiently tightened.

  1991 - An additional lower inboard wing rib is introduced to prevent bowing from over shrinking the underside wing fabric.

  1991 - The Hirth 2703 dual electronic ignition engine is introduced.

  1991 - An optional fiberglass pointed nose fairing is introduced to further streamline the airplane and enhance its appearance.

  1991 - A new optional electric start system is introduced eliminating the maintenance previously required with the older ADS starter.

  1992 - An optional 3 piece fiberglass mid-wing gap cover is introduced to better fair the junction of the windshield with the wing and reduce drag at the propeller hub as well as enhance appearance.

  1992 - The wing tip bow material is changed from 3/4 inch .049 to 7/8 .058 6061 T6 aluminum.

  1992 - A new design of wheel pants is introduced to enhance aerodynamics and appearance.

  1993 - A new fiberglass pointed nose option is introduced for single-seaters.

  1993 - Doubled top and bottom ribs, spaced 6" apart, on inboard end of   wing are sheeted with aluminum to prevent bowing of inboard rib when shrinking fabric.

  1993 - A top to bottom rib stiffener is installed between inboard wing ribs.

  1995 - New 2.6 : 1 Challenger reduction drive replaced the original Hegar drive. This new drive reduces propeller speed, is quieter, and improves performance. The new Challenger drive is taller, allowing a 60" prop in place of the previous 54" prop. This slower turning, longer prop is much more efficient, increasing cruise speed by 10 M.P.H. and climb by 15%.

  1995 - New 60 inch diameter propeller introduced with new drive. Greater propeller  efficiency increases cruise speed by 10 mph and increases climb by 15%.

  1995 - For float users, Puddlejumper Floats Inc. Introduces a new steerable, retractable  nose gear for their amphibious floats that is proprietary to the Challenger.

  1995 - The inboard aileron end ribs are relocated 10 inches out from the old position.

    1996 - The wing span of clip wing Challenger II Specials shipped to Canada is reduced    from 28 to 26 feet to be consistent with clips shipped around the world. This results in  slightly higher speeds and roll rates. The change was enabled by amendments to the Canadian Air Regulations to remove the wing loading limits for ultralights.

  1997 - An attractive pair of fiberglass wing tips is introduced. The new tips extend just 6   inches beyond the ends of the spars (versus 18 inches for the previous tips) thus reducing    the wing span by 2 feet. They increase cruise and top speeds (with resulting gains in economy) while their shape allows the airplane to continue to enjoy very low stall speeds.  

These tips attach in such a way as to greatly stiffen the outer portion of the wing. This in  turn gives the outer ends of the ailerons (the most effective portion) a better bite and in so doing increases the roll rate, particularly with the reduced span.

  1997 - Axle weldments are redesigned to a two part system to increase strength and to  eliminate the need of an axle spacer when mounting wheelpants.

  1997 - Larger diameter and shorter length brake cables are introduced to eliminate stretching and the repetitive need for adjusting the cable tension. A larger brake handle is also introduced to make brake actuation easier and more effective.

  1998 - 2 piece seat cushions are replaced with a one piece design to avoid the problem of the rear seat back cushion being blown out of the plane (and sometimes going through the  prop) while flying solo with the doors off. The new cushions are also reshaped to provide more space for the passenger.

  1998 - The front and rear canvas seat slings are replaced with an aluminum design that is stronger and provides more leg room for both front and rear occupants. As well, the down tubes forming the back of the front seat are closer together so the passenger has significantly more width for their legs. The seat bottoms are hinged for easier access and   inspection of the elevator pushrods.

  1998 - A hinged aluminum access panel to the fuel tank replaces the earlier canvas version.

  1998 - New upper fuselage formers are introduce to ensure adequate clearance between  fuselage fabric and the aileron control cables.

  1998 - The ailerons are shortened at the inboard end in order to reduce adverse yaw as   well as to clean up airflow to the engine and propeller.

  1998 - An aluminum firewall is added to the fuselage down tubes in front of the engine.

  1999 - The nose gear shaft is strengthened by upgrading from 1/8" wall to 1/4" wall

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