Cessna 525 Citation CJ1

TYPE: Light business jet.

COUNTRY OF ORIGIN: United States of America

PROGRAMME: Original CitationJet announced at NBAA Conventron 1989 as replacement for Citation 500 and I (production of which stopped 1985); first flight of FJ44 turbofans in Citation 500 April 1990; first flight of CitationJet (N525CJ) 29 April 1991; first flight of second (preproductron) prototype 20 November 1991; FAA certification for single-pilot operation received 16 October 1992; first customer delivery 31 March 1993. Russian certification achieved 4 September 1998. RVSM Group approval granted by FAA in January 2000.
Replacement Citation CJ1 announced at NBAA Convention 19 October 1998; first aircraft (N31CJ) completed late 1999; FAA certification 16 February 2000; first customer delivery 31 March 2000 to the Commercial Envelope Company of Deer Park, New York; 500th Cessna 525 series, a CJ1 rolled out 7 June 2002. By June 2002 a total of 493 Model 525s were in service, at which time their flight time totalled more than 550,000 hours.

CUSTOMERS: Total 359 CitationJets, plus three prototypes, delivered up to early 2000, when manufacture turned to CJ1. Total of 175 CJ1s delivered by 30 September 2003, including 30 delivered in 2002 and 16 in the first nine months of 2003. Recent customers include Avemex SA of Toluca, Mexico (one); Taxi Marilia (TAM) of Brazil (three, including c/n 0500); Atlas Air Service GmbH of Germany (four), and Cessna's TAG Aviation USA's fractional ownership operation, CitationShares, which has received one, and the Chilean Air Force, which took delivery of three in November 2001. Total fleet time (CJ and CJ1) 697,488 hours in August 2003.

COSTS: US$4,024 million, typically equipped (2003).

DESIGN FEATURES: Small business jet of conventional appearance; wings attached below fuselage; T tail; tapered wings and tailplane; podded engines mounted clear of upper rear fuselage. Natural Laminar Flow (NLF) aerofoil section. CJ1 is generally identical to CitationJet; increased maximum T-O, ramp and landing weights to provide improved range/payload; Pro Line 21 avionics.

FLYING CONTROLS: Conventional and manual. Ailerons and elevators horn balanced; trim tab on port aileron; trim tabs on rudder and both elevators; hydraulically actuated single-slotted flaps, deflections 15, 35 and 60°, last-named for ground use only, and selectable to any intermediate position between 0 and 35°. Speed brake in upper and lower surface of each wing.

STRUCTURE: All-metal. Three-spar wing.

LANDING GEAR: Hydraulically retractable tricycle type, with single wheel on each unit. Trailing-link main units retract inward into wing; nose gear retracts forward. Main tyres 22x7.75-10 (8 ply) tubeless; nose 18x4.4 (6 ply) tubeless.

POWER PLANT: Two 8.45 kN (1,900 lb st) Williams FJ44-1A turbofans pod-mounted, with thrust attenuators. Two independent fuel systems, with fuel contained in integral wing tanks, and single filler port in each wing; see under Weights and Loadings.

ACCOMMODATION: Crew of two on flight deck. Main cabin with standard seating for five passengers, one on sidewaysfacing seat at front of cabin, with four in club arrangement; tray tables which stow in elbow rails, and individual reading lights and ventilation ducts, standard.

SYSTEMS: Digitally controlled pressurisation system, maximum differential 0.58 bar (8.5 lb/sq in).

AVIONICS: Rockwell Collins Pro Line 21 as core system.
Comms: Honeywell CNI5000 radios and radio altimeter.
Radar: Rockwell Collins RTA 800 colour weather radar.
Flight: Bendix/King KLN-900 FMS. Dual VHF nav receivers, ADF, DME, RMl, Bendix/King KLN-900 GPS.
Instrumentation: Two-tube EFIS with 203 x 253 mm (8 X 10 in) adaptive flight displays (third optional), LCD attitude director indicator (ADI) and horizontal situation indicator (HSl) for co-pilot.

DIMENSIONS, EXTERNAL:
Wing span 14.26 m (46 ft 91/2 m)
Wing aspect ratio 9.1
Length overall 12.98 m (42 ft 7 in)
Height overall 4.20 m (13 ft 91/4 in)
Tailplane span 5.64 m (18 ft 6 in)
Wheel track 3.96 m (13 ft 0 in)
Wheelbase 4.68 m (15 ft 41/4 in)
Crew/passenger door: Height 1.29 m (4 ft 23/4 in)
Width 0.60 m (1 ft 111/2 in)
DIMENSIONS, INTERNAL:
Cabin:
- Length: between pressure bulkheads 4.80 m (15 ft 9 in)
- excl cockpit 3.35 m (11 ft 0 in)
- Max width 1.47 m (4 ft 10 in)
- Max height 1.45 m (4 ft 9 in)
Baggage compartment volume:
- nose 0.58 m3 (20.4 cu ft)
- cabin 0.11 m3 (4.0 cu ft)
- tailcone 0.86 m3 (30.2 cu ft)
- total 1.55 m3 (54.6 cu ft)
AREAS:
Wings, gross 22.30 m2 (240.0 sq ft)
Vertical tail surfaces (total, incl tab) 4.35 m2 (46.8 sq ft)
Horizontal tail surfaces (total, incl tabs) 5.64 m2 (60.7 sq ft)
WEIGHTS AND LOADINGS:
Weight empty, typically equipped 3,025 kg (6,670 lb)
Max usable fuel weight 1,460 kg (3,220 lb)
Payload with max fuel, single pilot 306 kg (675 lb)
Max T-O weight 4,808 kg (10,600 lb)
Max landing weight 4,445 kg (9,800 lb)
Max ramp weight 4.853 kg (10,700 lb)
Max wing loading 215.6 kg/m2 (44.17 lb/sq ft)
Max power loading 284 kg/kN (2.79 lb/lb st)
PERFORMANCE:
Max operating speed (VMO):
S/L to FL305 263 kt (487 km/h; 302 mph) IAS
above FL305 M0.71
Max cruising speed at 3,992 kg (8,800 lb) AUW at FL350 381 kt (706 km/h; 438 mph)
Stalling speed, landing configuration at max landing
weight
83 kt (154 km/h; 96 mph) CAS
Max rate of climb at S/L 985 m (3,230 ft)/min
Rate of climb at S/L, OEI 259 m (850 ft)/min
Max certified altitude 12,500 m (41,000 ft)
Service ceiling, OEI 6,462 m (21,200 ft)
FAR Pt 25 T-O field length: 1.000 m (3.280 ft)
Landing field length 841 m (2,760 ft)
IFR range with 100 n mile (185 km; 115 mile) alternate
and 45 min reserves
1.248 n miles (2,311 km; 1,436 miles)
VFR range with reserves 1.475 n miles (2,731 km; 1,697 miles)
OPERATIONAL NOISE LEVELS:
TO 73.6 EPNdB
Approach 89.7 EPNdB
Sideline 83.6 EPNdB
 

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