US Army designation: UC-35B
US Marine Corps designation: UC-35D
TYPE: Business jet.
PROGRAMME: Original Cessna 560 was stretched, higher-performance version of Citation S/II, first flown August 1987 and marketed as Citation V; Citation Ultra introduced from c/n 560-0260, but replaced by current Encore. Prototype Encore, based on rebuilt Citation Ultra, first flown (N560VU) 9 July 1998; announced at NBAA Convention at Las Vegas, Nevada 18 October 1998; first production aircraft (c/n 560-0539) rolled out in early March 2000. FAA certification achieved 26 April 2000; first delivery (N539CE/N5108G) on 29 September 2000 to J R Simplot Company of Boise, Idaho.
CURRENT VERSIONS: Citation Encore: Civilian business jet.
UC-35B: In January 1996, US Army selected Ultra for its C-XX medium-range transport aircraft programme, for which 35 aircraft are required over a five year period; equipped with 0.90x 1.15m (2ft 11½ in 3 ft 9 in) upward-opening clamshell cargo door on port forward fuselage; first order was for two UC-35 As, of which one (95-0123) was delivered in last quarter of 1996; first two serve with 207 AvnCo at Heidelberg, Germany. Subsequent orders for five in each of FY96. FY97, FY98 and FY99; (last two aircraft of this batch are first UC-35Bs), three in 2000 and one in 2001 (delivered December 2001). Total six UC-35Bs, plus 20 earlier UC-35As.
UC-35D: Equivalent version to UC-35B for US Marine Corps.
Citation Excel: Described separately.
CUSTOMERS: Deliveries of Ultra began July 1994; deliveries comprised 24 in 1994, 56 in 1995, 52 in 1996, 47 in 1997, 41 in 1998, 32 in 1999, six in 2000, 37 in 2001, 36 in 2002 and 18 in the first nine months of 2003. Announced customers for Encore include J R Simplot Co of Boise, Idaho, which has ordered two; Taxi Aereo Marilia (TAM) of Brazil (one); Flying Partner CV of Antwerp, Belgium (one). By August 2003 a total of 647 Citation Vs and Encores had been delivered, and total fleet time stood at 2,117,373 flight hours.
COSTS: US$7,576 million, typically equipped (2003).
DESIGN FEATURES: Stretched version of Citation S/II for full eight-seat cabin and with fully enclosed toilet/vanity area; seventh cabin window each side; two baggage compartments outside main cabin. Rear-engined executive jet with low-mounted wing of tapered planform with root gloves; tapered horizontal tail with sweptback fin and fillet.
Encore generally as Citation Ultra and Citation Bravo. Compared to Ultra, has increased wing span; bleed air anti-icing for wing leading-edges; boundary layer energisers and stall fences to improve stall characteristics; trailing-link main landing gear with narrower track; decreased fuel capacity; Pratt & Whitney Canada PW535 turbofans offering 10 per cent increase in thrust and 15 per cent improvement in specific fuel consumption; reduced fuel capacity; fuel heaters obviating the need for additives; digital pressurisation system; improved braking system; single level access electrical junction box; and redesigned interior with increased headroom, new passenger service units, pin-mounted seats for easy removal/replacement and increased serviceability.
Description for Citation Ultra applies also to Citation Encore except as follows:
FLYING CONTROLS: Conventional and manual. Trim tab on port aileron manually actuated; manual rudder trim; electric elevator trim tab with manual standby; hydraulically actuated Fowler flaps; hydraulically actuated airbrake.
STRUCTURE: Two primary, one auxiliary metal wing spars; four fuselage attachment points, conventional ribs and stringers. All-metal pressurised fuselage with fail-safe design providing multiple load paths.
LANDING GEAR: Hydraulically retractable trailing-link tricycle type with single wheel on each unit. Main units retract inward into the wing, nose gear forward. Free-fall and pneumatic emergency extension systems. Goodyear mainwheels with tubeless tyres size 22x8.0-10 (12 ply), pressure 6.90 bar (100 Ib/sq in). Steerable nosewheel (±20°) with Goodyear wheel and tyre size 18x4.4DD (10 ply), pressure 8.27 bar (120 Ib/sq in). Goodyear hydraulic brakes. Parking brake and pneumatic emergency brake system. Anti-skid system standard. Minimum ground turning radius about nosewheel 8.38 m (27 ft 6 in).
POWER PLANT: Two Pratt & Whitney Canada PW535A turbofans, each rated at 15.12 kN (3,400 lb st) at 27°C (80°F). Integral fuel tank in each wing, combined usable capacity 3,047 litres (805 US gallons; 670 Imp gallons).
ACCOMMODATION: Standard seating for seven passengers in four forward-facing and three aft-facing seats, or eight passengers in double-club arrangement, on swivelling and fore/aft/inboard-tracking pedestal seats; refreshment centre in forward cabin area; lavatory/vanity centre with sliding doors to rear, metallic plating on cabin fittings, veneer overlay on armrests, optional pleated window shades and cabin divider mirror standard: space in aft section of cabin for 272 kg (600 lb) of baggage, in addition to baggage compartments in nose and rear fuselage.
SYSTEMS: Pressurisation system supplied with engine bleed air, maximum pressure differential 0.69 bar (8.9 lb/sq in), maintaining a sea level cabin altitude to 7,189 m (23,586 ft), or a 2,440 m (8,000 ft) cabin altitude to 13,716 m (45,000 ft). Hydraulic system, pressure 103.5 bar (1,500 Ib/sq in), with two pumps to operate flaps landing gear, speed brakes and thrust reversers. Separate hydraulic system for wheel brakes. Electrical system supplied by two 28 V 300 A DC starter/generators, with two 375 VA inverters and 24 V 40 Ah Ni/Cd battery. Oxygen system of 1.81 m3 (64 cu ft) capacity includes two crew demand masks and dropout constant flow masks for passengers. Engine fire detection and extinguishing system. Bleed air anti-icing system for wing leading-edges and engine inlets; pneumatic de-icing boots on tailplane leading-edges.
AVIONICS: Standard avionics package based on Honeywell Primus 1000 digital flight control system with integrated avionics computer.
Comms: Dual Honeywell Primus II transceivers, dual TDR-94 transponders, dual altitude reporting systems and cockpit voice recorder standard.
Radar: Honeywell Primus 660 colour weather radar standard.
Flight: Dual Honeywell Primus II, single Honeywell ADF, ALT-55 radio altimeter, coupled vertical navigation system. Global GNS-XL with GPS, expanded keyboard and colour CDU display standard. Universal Avionics UNS-1Csp FMS optional.
Instrumentation: Three-tube EFIS with 203 x 178 mm (8 X 7 in) CRTs comprising pilot's and co-pilot's primary flight displays (PFDs) and centrally mounted multifunction display (MFD); PFDs integrate functions of five flight mstruments and several sources of navigation data, and provide trend data for airspeed, altitude and rate of climb.
| DIMENSIONS, EXTERNAL: | |
| Wing span | 16.48 m (54 ft 1 in) |
| Wing aspect ratio | 9 |
| Length overall | 14.90 m (48 ft 103/4 in) |
| Height overall | 4.63 m (15 ft 21/4 in) |
| Tailplane span | 6.55 m (21 ft 6 in) |
| Wheelbase | 6.13 m (20 ft 11/4 in) |
| Wheel track | 4.05 m (13 ft 31/2 in) |
| DIMENSIONS, INTERNAL: | |
| Cabin: | |
| - Length; between pressure bulkheads | 6.88 m (22 ft 7 in) |
| - excl cockpit | 5.28 m (17 ft 4 in) |
| - Max width | 1.48 m (4 ft 101/4 in) |
| - Max height | 1.43 m (4 ft 81/2 in) |
| Baggage compartment volume | 1.95 m3 (69 cu ft) |
| AREAS: | |
| Wings, gross | 29.94 m2 (322.3 sq ft) |
| Vertical tail surfaces (total, incl tab) | 4.73 m2 (50.90 sq ft) |
| Horizontal tail surfaces (total) | 7.88 m2 (84.80 sq ft) |
| WEIGHTS AND LOADINGS: | |
| Weight empty, typically equipped | 4,590 kg (10,120 lb) |
| Max fuel | 2.468 kg (5,440 lb) |
| Baggage capacity: | |
| - nose | 141 kg (310 lb) |
| - aft cabin | 272 kg (600 lb) |
| - tailcone | 227 kg (500 lb) |
| Max T-O weight | 7,543 kg (16,630 lb) |
| Max ramp weight | 7,634 kg (16,830 lb) |
| Max landing weight | 6,895 kg (15,200 lb) |
| Max zero-fuel weight | 5,715 kg (12,600 lb) |
| Max wing loading | 251.9 kg/m2 (51.60 Ib/sq ft) |
| Max power loading | 249 kg/kN (2.45 lb/lb st) |
| PERFORMANCE: | |
| Max cruising speed at FL350 | 429 kt (795 km/h; 494 mph) |
| Stalling speed, flaps down | 83 kt (154 km/h; 96 mph) |
| Max rate of climb at S/L | 1,445 m (4,740 ft)/min |
| Time to: FL350 | 12 min |
| FL450 | 28 mm |
| Rate of climb at S/L, OEI | 439 m (1,440 ft)/min |
| Max certified altitude | 13,715 m (45,000 ft) |
| T-O balanced field length | 1,064 m (3,490 ft) |
| Landing field length at max landing weight | 844 m (2,770 ft) |
| NBAA IFR range, 100 n mile (185 km; 115 mile) alternate, plus 45 min reserves | 1,178 n miles (2,182 km; 1,356 miles) |
| Range with max fuel, VFR reserves | 1,970 n miles (3,648 km; 2,267 miles) |
| OPERATIONAL NOISE LEVELS: | |
| T-O | 70.0 EPNdB |
| Approach | 90.5 EPNdB |
| Sideline | 89.8 EPNdB |
