Cap Aviation

CAP 10
ype TOP

Aerobatic two-seat sportplane.

Programme TOP

Derived from Piel CP-30/CP-301 Emeraude, first flown 19 June 1954 and built by amateur constructors
as well as by 11 commercial plants, under various names. Super Emeraude modified with taller fin and
119 kW (160 hp) engine as CP-100 prototype, flown 13 August 1966; with broader chord rudder and 134
kW (180 hp) engine, became prototype CAP 10 B, first flight (F-WOPX) 22 August 1968; further three pre-
series aircraft; certified 4 September 1970; FAA certification for day and night VFR on 13 June 1974.
Produced by Mudry until 1996.

Production transferred to Dijon, beginning with CAP 10 C in 2001. Total fleet time exceeded 500,000 flight
hours by 2005.

Current Versions TOP

CAP 10 B TOP

Previous version; now out of production, but can be upgraded to CAP 10 C in one day's work.

CAP 10 C TOP

Announced in early 1999; features carbon fibre-reinforced wing spar (Mod 000302) for reduced weight
and increased speed and roll rate.

Improvements effected in CAP 10 C include substitution of pushrods for aileron control, replacing cables;
larger (25 per cent) ailerons of increased chord with repositioned axis for faster roll rate, compensated by
two spade-type servos per side; aileron max 'down' deflection increased from 15 to 25º; electric actuation
of flaps; electric fuel gauges and flush filler caps; optional constant-speed propeller (in prospect);
upgraded instrumentation with four standard options; redesigned landing gear to improve ground
handling; local airframe reinforcement and landing gear attachments; and revised canopy design to
reduce cockpit noise levels. Roll rate improved by 30 per cent. New wing available for retrofitting to
existing CAP 10 Bs and is supplied complete with landing gear.

Static test of wing undertaken 27 April 2000; prototype first flight (CAP 10 B HB-SAX retrofitted with new
wing) 5 March 2001; first 'true' CAP 10 C (F-WWNN, c/n 300) first flown 15 May 2001 and following initial
flight testing was delivered to CEV during July. DGAC certification achieved in early 2002. Reregistered
F-GYKA on completion of trials. CAP 10Cs are registered under CAP 10B type certificate. FAA
certification achieved 16 June 2004.

Description refers to CAP 10 C unless otherwise stated.

Customers TOP
Total 284 of earlier versions (including prototypes) built to mid-1999, of which 279 completed by Mudry
before 1996 bankruptcy. Final five produced by Akrotech Europe in temporary factory at Bernay and
include exports to UK (three) and USA (one); last, in 1999, was G-LORN (c/n 282) to UK. Production then
paused, pending launch of CAP 10 C and transfer of production to Dijon. Previous major users, French
Air Force (56) and Mexican Air Force (20) began disposals in 1994-95. Two more recent aircraft operated
by 208 Squadron of South Korean Air Force; French Navy has eight.

First production CAP 10 C (c/n 301; G-CPXC) registered in December 2001 to Cole Aviation in UK; 14th
registered in November 2004; 15th in 2005; customers include SEFA of France (five). By mid-2004 an
additional 45 sets of CAP 10 C wings had been sold to existing CAP 10 B operators.

Costs TOP

EUR162,320 to EUR185,274 depending on equipment level (2004).

Design Features TOP

Simple, sporting lightplane with low, basically elliptical wing, mid-mounted tailplane and curved rudder.

Wing section NACA 23012; dihedral 5º; incidence 0º.

Flying Controls TOP

Conventional and manual. Electric trim tabs on port elevator; balance tab on rudder; tailplane incidence
adjustable on ground; electric three-position (0, 15, 40º) flaps. Control surface deflections: ailerons +25/-
25º, elevators ±25º; rudder ±18º.

Structure TOP

Main spar of carbon fibre caps and birch ply webs; wooden ribs; birch ply skin; carbon fibre wingtips; birch
ply ailerons, flaps, fin/rudder and tailplane/elevator. Wooden fuselage, with okoumé ply upper decking
and polyester fabric covering elsewhere.

Landing Gear TOP

Tailwheel type; fixed. Wing-mounted, trousered, cantilever main legs of light alloy, with integral ERAM
type 9 270 C oleo-pneumatic shock-absorbers. Single wheel on each main unit, tyre size
380×150/15×6.00-5. Solid tailwheel tyre, size 6×2.00. Tailwheel is steerable by rudder linkage but can be
disengaged for ground manoeuvring. Hydraulically actuated mainwheel disc brakes (controllable from port
seat) and parking brake. Dual toe brakes standard. Streamline fairings on mainwheels and legs.

Power Plant TOP

One 134 kW (180 hp) Textron Lycoming AEIO-360-B2F flat-four engine, driving a Hoffmann HO29HM-
189-170 two-blade, fixed-pitch wooden propeller; optional Evra 3.180-170-H5.F. Standard fuel tank aft of
engine fireproof bulkhead, usable capacity 72 litres (19.0 US gallons; 15.8 Imp gallons); total 75 litres
(19.8 US gallons; 16.5 Imp gallons). Auxiliary tank, usable capacity 78 litres (20.6 US gallons; 17.2 Imp
gallons), total capacity 79 litres (20.8 US gallons; 17.3 Imp gallons), beneath baggage compartment, must
be empty for aerobatics. Inverted fuel and oil (Aviat/Christen) systems permit continuous inverted flight.

Accommodation TOP
Side-by-side adjustable seats for two persons, with provision for back parachutes, under rearward-sliding
and jettisonable moulded transparent canopy. Five-point aerobatic shoulder harness standard. Leather
upholstery optional. Space for 20 kg (44 lb) of baggage aft of seats in training and touring models.

Systems TOP

Electrical system includes Delco-Rémy 40 A engine-driven alternator and STECO ET24 Ni/Cd battery.

Avionics TOP

Bendix/King and Garmin suites optional.

Comms TOP

Optional KY97A VHF com; GMA 340 audio panel and Sigtronics SPA400 intercom; GTX 320 or GTX 327
transponder; ACK 30 encoder; EBC 102A ELT.

Flight TOP

Garmin GNC 250 XL, GNS 420 or GNS 430 GPS; GI 106A VOR/ILS; Sandel SN3308 EHSI.

Instrumentation TOP

ASI (kt and mph); altimeter; VSI; recording g-meter; positive/negative slip indicator; compass; tachometer;
fuel gauges; oil pressure/temperature, EGT and CHT gauges; and manifold pressure/fuel flow gauge, all
standard. Artificial horizon, turn co-ordinator, and directional gyro optional or standard according to
selected equipment fit level.

Equipment TOP

Panel light, cockpit light, landing light, navigation and strobe lights, external power socket, aerobatic
sighting device, and canopy cover, all optional.

Dimensions, External

Wing span 8.08 m (26 ft 6 in)

Wing aspect ratio 6.0
Length overall 7.16 m (23 ft 6 in)
Height overall 2.55 m (8 ft 4½ in)
Tailplane span 2.90 m (9 ft 6 in)
Wheelbase 4.30 m (14 ft 1¼ in)
Wheel track 2.06 m (6 ft 9 in)
Propeller diameter 1.90 m (6 ft 2¾ in)

Dimensions, Internal

Cabin: Length 1.05 m (3 ft 5½ in)

Max width 1.05 m (3 ft 5½ in)
Max height 0.98 m (3 ft 2½ in)

Areas

Wings, gross 10.85 m2 (116.8 sq ft)

Vertical tail surfaces (total) 1.32 m2 (14.25 sq ft)
Horizontal tail surfaces (total) 1.86 m2 (20.02 sq ft)

Weights and Loadings (A: Aerobatic, U: Utility)

Weight empty, equipped 540 kg (1,190 lb)

Max baggage weight: A nil
U 50 kg (110 lb)
Fuel weight: A 54 kg (119 lb)
U 108 kg (238 lb)
Max T-O weight: A 780 kg (1,719 lb)
U 830 kg (1,830 lb)
Max landing weight 800 kg (1,764 lb)
Max wing loading: A 71.9 kg/m2 (14.72 lb/sq ft)
U 76.5 kg/m2 (15.67 lb/sq ft)
Max power loading: A 5.82 kg/kW (9.56 lb/hp)
U 6.19 kg/kW (10.16 lb/hp)

Performance

Never-exceed speed (VNE) 183 kt (340 km/h; 211 mph)

Max level speed at S/L and 148 kt (274 km/h; 170 mph)
cruising speed at 75% power
at FL80
Stalling speed: clean 53 kt (99 km/h; 61 mph)
flaps down 46 kt (85 km/h; 53 mph) IAS
Max rate of climb at S/L 488 m (1,600 ft)/min
Service ceiling 5,000 m (16,400 ft)
T-O run 350 m (1,150 ft)
T-O to 15 m (50 ft) 395 m (1,300 ft)
Landing from 15 m (50 ft) 600 m (1,970 ft)
Landing run 360 m (1,185 ft)
Range with max fuel 521 n miles (965 km; 600
miles)
g limits: A +6/-4
U +4.4/-1.8