CIRRUS SR20 and SRV

TYPE: Four-seat lightplane.

PROGRAMME: Development began 1990; mockup revealed at Oshkosh 1994; first flight (N200SR) 31 March 1995; second prototype (N202CD) flown November 1995; FAR Pt 23 certification aircraft (N203FT), designated C-1, made first flight 28 January 1998 after completion of wing redesign to lower stall speed and improve lateral control. By end 1997, the two prototypes had accumulated 1,500 hours of test flying. A second production-standard aircraft (N204CD; C-2) joined the flight test programme on 3 June 1998, committed to trials of fuel and electrical systems and avionics. Recovery parachute trials involved eight deployments, including three for FAA. Late 1998 start of deliveries delayed by decision of avionics supplier, Trimble, to withdraw from general aviation. FAR Pt 23 certification Amdt 47 received 23 October 1998; Transport Canada certification granted in March 2002; first aircraft manufactured to Canadian certification standard delivered 2 April 2002 to Tim Harpell of Toronto. Initial production aircraft first flew (N115CD) 22 March 1999, but lost on followmg day. First delivery (c/n 1005. N415WM) 20 July 1999, at which time 325 on order (although many since upgraded to SR22 orders). Production certificate, to enable Cirrus to carry out its own inspections, awarded 12 June 2000.

CURRENT VERSIONS: SR20: Total 133 delivered to customers by April 2001, when production suspended. MTOW 1,315 kg (2,900 lb).

SR20A: In production from July 2001. Additional 45 kg (100 lb) MTOW; landing light repositioned lower on engine cowling; and optional Goodrich Skywatch and Sandel SN3308 EHSI for traffic information. Upgrades (including MTOW) retrofittable. As described.

SR20 Version 2.0, Version 2.1 and Version 2.2: Upgraded versions available from 2003; launched at EAA Sun 'n' Fun in April 2002. Differ from SR20A principally in having no vacuum instruments and featuring electrical system and avionics packages based on those of the SR22. Version 2.0 has a single-alternator, dual-battery, dual-bus electrical system and features Avidyne FlightMax MFD, single Garmin GNS 430 GPS/com/nav and GNC 250XL GPS/com and S-Tec System 20 autopilot as standard. First delivery in January 2003 to 907th Flight Squadron Aero club at Jameson, Pennsylvania. Version 2.1 adds a dual-alternator electirical system and GNS 430/420 package. Version 2.2 has dual GNS 430s, S-Tec Fifty FiveX autopilot with altitude preselect and Sandel EHSI.

SRV: Basic VFR-only version, introduced at EAA AirVenture, Oshkosh, 29 July 2003, when demonstrator N936CD (c/n 1337) shown. Specification and performance generally as for SR20 except: cruising speed at 75 per cent power 150 kt (278 km/h; 173 mph); range with reserves 634 n miles (1,174 km; 729 miles); max range 865 n miles (1,602 km; 995 miles).

CUSTOMERS: Orders for 552 received by July 2001. Total of 53 delivered in 2001, 105 in 2002, and 86 in the first nine months of 2003. By December 2002, 267 had been registered.

COSTS: SR20 US$229,700; SRV US$189,900 (both 2003).

DESIGN FEATURES: Low-wing, composites construction monoplane with upturned wingtips; mid-set tailplane with horn-balanced elevators; horn-balanced rudder; fixed tab on starboard aileron. First certified aircraft with ballistic parachute as standard equipment (Cirrus Airplane Parachute System or CAPS), fitted just aft of baggage compartment. Wing dihedral 40 30’.

STRUCTURE: Composites monocoque; one-piece main spar attached to fuselage on two locations under front seats; spar carry-through attached to fuselage side-walls. Wing upper and lower surfaces bonded to spars and ribs, forming torsion box. All flying control surfaces are flush-riveted aluminium. Fin integral with fuselage; one-piece tailplane. Cabin incorporates composites roll-cage; acrylic windscreen and windows.

FLYING CONTROLS: Conventional and manual. Actuation by pushrods, cables and bellcranks. Electric trim tabs for roll and pitch activated through springed centring devices; ground-adjustable rudder tab. Three-position flaps.

LANDING GEAR: Fixed, tricycle; composites cantilever main legs; single wheels and speed fairings throughout. Main tyres 15x6.00-6, nosewheel tyre 5.00-5. Hydraulic caliper disk brakes on mainwheels. Castoring nosewheel.

POWER PLANT: One 149 kW (200 hp) Teledyne Continental IO-360-ES flat-six engine driving a two-blade Hartzell BHC-J2YF-1BF/F7694 propeller (three-blade 1.88 m; 6 ft 2 in PHC-J3YF-1MF/F77392-1 propeller optional). Single fuel tank in each wing, each of 113.5 litres (30.0 US gallons; 25.0 Imp gallons) capacity, of which 212 litres (56.0 US gallons; 46.7 Imp gallons) usable. Oil capacity 7.6 litres (2.0 US gallons; 1.7 Imp gallons).

ACCOMODATION: Four 26 g energy attenuating seats in pairs; two forward-hinged passenger doors. Dual controls. Baggage compartment door aft of cabin on port side of fuselage. Interior reflects modern motorcar design.

SYSTEMS: Single-axis S-Tec System 20 autopilot with GPS; dual-axis S-Tec System 30 and Fifty FiveX optional; 24 V DC power system with 28 V 75 A alternator and 24 V 10 Ah battery. 12 V power port.

AVIONICS: Garmin integrated package.

Comms: GNS 430 colour GPS/com/nav IFR approach-certified GPS plus back-up, GNS 250XL GPS/com, GMA 340 audio panel and GTX 327 transponder. Options include GNS 420 colour GPS/com and/or additional GNS 430 (back-up IFR GPS).

Flight: Garmin GI 106 GPS/VOR/LOC/GSI. S-Tec System FortyX autopilot. Options include Goodrich Stormscope WX-500, S-Tec System FiftyX or FiftyFiveX, Goodrich Skywatch system, GI 102 or second GI 106.

Instrumentation: Avidyne Entegra PFD and FlightMax EX3000C MFD standard, EX5000C optional.

EQUIPMENT: Integral ballistic recovery parachute (Cirrus Airplane Parachute System); vertical descent rate 7.3 m (24 ft)/s at S/L. Navigation, landing and strobe lights standard.

DIMENSIONS, EXTERNAL:
Wing span 10.85 (35 ft 7 in)
Wing aspect ratio 9.1
Length overall 7.92 (26 ft 0 in)
Height overall 2.59 (8 ft 6 in)
Tailplane span 3.93 m (12 ft 10 3/4 in)
Wheel track 3.38 (11 ft 1 in)
Wheelbase 2.29 m (7 ft 6 in)
Propeller diameter (two blade) 1.93 m (6 ft 4 in)
Cabin doors (each): Height 0.94 m (3 ft 1 in)
Width 0.86 m (2 ft 10 in)
DIMENSIONS, INTERNAL:
Cabin: Length 3.30 m (10 ft 10 in)
- Max width 1.24 m (4 ft 1 in)
- Max height 1.27 m (4 ft 2 in)
AREAS:
Wings, gross 12.56 m2 (135.2 sq ft)
Horizontal tail 3.48 m2 (37.50 sq ft)
WEIGHTS AND LOADINGS:
Weight empty 939 kg (2,070 lb)
Max fuel weight 163 kg (360 lb)
Max T-O weight 1,360 kg (3,000 lb)
Max wing loading 108.3 kg/m2 (22.19 lb/sq ft)
Max power loading 9.12 kg/kW (15.00 lb/hp)
PERFORMANCE:
Never-exceed speed (Vne) 200 kt (370 km/h; 230 mph)
Cruising speed at 2,440 m (8,000 ft) at 75% power 156 kt (289 km/h; 180 mph)
Manoeuvring speed 135 kt (250 km/h; 155 mph) IAS
Stalling speed: flaps up 64 kt (119 km/h; 74 mph) IAS
flaps down 54 kt (100 km/h; 63 mph) IAS
Max rate of climb at S/L 274 m (900 ft)/min
Service ceiling 5,335 m (17,500 ft)
T-O run 435 m (1,430 ft)
T-O and landing from 15 m (50 ft) 622 m (2,040 ft)
Landing run 309 m (1,014 ft)
Range with reserves:
at 75% at power 733 n miles (1,357 km; 843 miles)
at econ cruise 882 n miles (1,633 km; 1,015 miles)
g limits +3.8/-1.9

 

Index Facebook Search Index Facebook Search