Cessna Citation Model Stats

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1 Cessna Citation Model Stats Cessna Citation Sovereign - Dimensions Length 63 ft 6 in (19.35 m) Height 20 ft 4 in (6.20 m) Wingspan 72 ft 4 in (22.04 m) Wing Wing Area Wing Sweep Wheelbase Tread 516 sq ft (48 sq m) 16.3 degrees 27 ft 10 in (8.49 m) 10 ft (3.05 m) Cabin Interior Height Width Length 68 in (1.73 m) 66 in (1.68 m) 25 ft 3 in (7.70 m) Seating Capacity 9-12 Baggage Capacity 1,415 lb (642 kg) 135 cu ft (3.82 cu m) Single Pilot Certified No

2 Wingspan 72 ft 4 in (22.04 m) Height 20 ft 4 in (6.20 m) Length 63 ft 6 in (19.35 m) Weights Maximum Ramp Weight 31,025 lb (14,073 kg) Maximum Takeoff Weight 30,775 lb (13,959 kg) Maximum Landing Weight 27,575 lb (12,508 kg) Maximum Zero Fuel Weight 21,000 lb (9,525 kg) Usable Fuel Capacity 11,390 lb (5,166 kg) 1,700 gal (6,435 l) Basic Operating Weight 18,380 lb (8,337 kg) Useful Load 12,645 lb (5,736 kg) Maximum Payload 2,620 lb (1,188 kg)

3 Full Fuel Payload 1,255 lb (569 kg) Performance Maximum Cruise Speed 458 ktas (848 km/h) Range 3,000 nm (5,556 km) Takeoff Distance 3,650 ft (1,113 m) Landing Distance 2,680 ft (817 m) Maximum Operating Altitude 47,000 ft (14,326 m) Maximum Climb Rate N/A fpm (N/A mpm) Maximum Limit Speed Mach Powerplant Two Pratt & Whitney Canada PW306D turbofan engines are installed on the new Citation Sovereign. The engine is a twin-spool design with a damage resistant wide chord fan. Behind the fan, four axial and one centrifugal compressor stages lead to a high-efficiency, low-emission, through-flow combustor, and five turbine stages. Two-stage variable inlet guide vanes and bleedoff valves are controlled by the FADEC to optimize compressor performance and engine operability. Manufacturer: Pratt & Whitney Canada Model: (2) PW306D Thrust: 5,852 lbf Time Between Overhaul: 6,000 hr

Citation Mustang - Detailed Specifications Performance data is based on the standard Mustang configuration, operating in International Standard Atmosphere (ISA) conditions with zero wind.

4 Citation Mustang - Detailed Specifications Performance data is based on the standard Mustang configuration, operating in International Standard Atmosphere (ISA) conditions with zero wind. Takeoff and landing field lengths are based on a level, hard surface and dry runway. Actual performance will vary with factors such as environmental conditions, aircraft configuration and operational/atc procedures. Dimensions Length 40 ft 7 in (12.37 m) Height 13 ft 5 in (4.09 m) Wingspan 43 ft 2 in (13.16 m) Wing Wing Area Wing Sweep 210 sq ft (20 sq m) 11.0 degrees Wheelbase 14 ft 4 in (4.37 m)

5 Tread 11 ft 10 in (3.61 m) Cabin Interior Height Width Length 54 in (1.37 m) 55 in (1.40 m) 9 ft 9 in (2.97 m) Seating Capacity 5-5 Baggage Capacity 718 lb (326 kg) 63 cu ft (1.78 cu m) Single Pilot Certified Yes Wingspan 43 ft 2 in (13.16 m) Height 13 ft 5 in (4.09 m) Length 40 ft 7 in (12.37 m) Weights Maximum Ramp Weight 8,730 lb (3,960 kg)

6 Maximum Takeoff Weight 8,645 lb (3,921 kg) Maximum Landing Weight 8,000 lb (3,629 kg) Maximum Zero Fuel Weight 6,750 lb (3,062 kg) Usable Fuel Capacity 2,580 lb (1,170 kg) 385 gal (1,457 l) Basic Operating Weight 5,590 lb (2,536 kg) Useful Load 3,140 lb (1,424 kg) Maximum Payload 1,160 lb (526 kg) Full Fuel Payload 560 lb (254 kg) Performance Maximum Cruise Speed 340 ktas (630 km/h) Range 1,150 nm (2,130 km) Takeoff Distance 3,110 ft (948 m) Landing Distance 2,380 ft (725 m) Maximum Operating Altitude 41,000 ft (12,497 m) Maximum Climb Rate 3,010 fpm (917 mpm) Maximum Limit Speed Mach Powerplant Two dual-channel FADEC-controlled, Pratt & Whitney Canada PW615F-A turbofan engines are installed on the Mustang. The engine is a 2.8:1 bypass ratio, counter-rotating twin-spool design with three compression stages and two turbine stages. It produces 1,460 pounds (6.49 kn) of thrust at sea level,

static conditions, flat-rated up to 77 F (25 C). The FADEC system also provides time-limited dispatch, diagnostics, and engine synchronization according to switch position.

7 static conditions, flat-rated up to 77 F (25 C). The FADEC system also provides time-limited dispatch, diagnostics, and engine synchronization according to switch position. Manufacturer: Pratt & Whitney Model: (2) PW615F-A Thrust: 1,460 lbf Time between overhaul: 3,500 hr Citation M2 - Detailed Specifications Performance data is based on the standard M2 configuration, operating in International Standard Atmosphere (ISA) conditions with zero wind. Takeoff and landing field lengths are based on a level, hard surface and dry runway. Actual performance will vary with factors such as environmental conditions, aircraft configuration and operational/atc procedures. Preliminary data, subject to change.

Dimensions Length 42 ft 7 in (12.98 m) Height 13 ft 11 in (4.24 m) Wingspan 47 ft 3 in (14.40 m) Wing Wing Area Wing Sweep 240 sq ft (22 sq m) 0.0 degrees Wheelbase 15 ft 4 in (4.67 m) Tread 13 ft (3.

8 Dimensions Length 42 ft 7 in (12.98 m) Height 13 ft 11 in (4.24 m) Wingspan 47 ft 3 in (14.40 m) Wing Wing Area Wing Sweep 240 sq ft (22 sq m) 0.0 degrees Wheelbase 15 ft 4 in (4.67 m) Tread 13 ft (3.96 m) Cabin Interior Height Width Length 57 in (1.45 m) 58 in (1.47 m) 11 ft (3.35 m) Seating Capacity 7-7 Baggage Capacity 725 lb (329 kg) 46 cu ft (1.29 cu m) Single Pilot Certified Yes Wingspan 47 ft 3 in (14.40 m)

9 Height 13 ft 11 in (4.24 m) Length 42 ft 7 in (12.98 m) Weights Maximum Ramp Weight 10,800 lb (4,899 kg) Maximum Takeoff Weight 10,700 lb (4,853 kg) Maximum Landing Weight 9,900 lb (4,491 kg) Maximum Zero Fuel Weight 8,400 lb (3,810 kg) Usable Fuel Capacity 3,309 lb (1,501 kg) 494 gal (1,870 l) Basic Operating Weight 6,991 lb (3,171 kg) Useful Load 3,809 lb (1,728 kg) Maximum Payload 1,409 lb (639 kg) Full Fuel Payload 500 lb (227 kg) Performance Maximum Cruise Speed 400 ktas (741 km/h) Range 1,300 nm (2,408 km)

Takeoff Distance 3,250 ft (991 m) Landing Distance 2,640 ft (805 m) Maximum Operating Altitude 41,000 ft (12,497 m) Maximum Climb Rate N/A fpm (N/A mpm) Maximum Limit Speed 0.

10 Takeoff Distance 3,250 ft (991 m) Landing Distance 2,640 ft (805 m) Maximum Operating Altitude 41,000 ft (12,497 m) Maximum Climb Rate N/A fpm (N/A mpm) Maximum Limit Speed Mach Powerplant Two Williams FJ44 turbofan engines are installed on the Citation M2. This engine is a 2.58:1 bypass, twin-spool design with three compression stages and three turbine stages and produces 1,965 pounds (8.74 kn) of takeoff thrust at sea level, static conditions, flat-rated up to 72 F (22 C). Dual-channel full authority digital engine controls (FADECs) provide automation and efficiency in engine management. Manufacturer: Williams International Model: (2) FJ44-1AP-21 Thrust: 1,965 lbf Time Between Overhaul: 4,000 hr

11 Citation CJ2+ - Detailed Specifications Performance data is based on the standard CJ2+ configuration, operating in International Standard Atmosphere (ISA) conditions with zero wind. Takeoff and landing field lengths are based on a level, hard surface and dry runway. Actual performance will vary with factors such as environmental conditions, aircraft configuration and operational/atc procedures. Dimensions Length 47 ft 8 in (14.53 m) Height 14 ft (4.27 m) Wingspan 49 ft 10 in (15.19 m) Wing Wing Area Wing Sweep 264 sq ft (25 sq m) 0.0 degrees Wheelbase 17 ft 10 in (5.44 m) Tread 15 ft 11 in (4.85 m) Cabin Interior Height Width Length 57 in (1.45 m) 58 in (1.47 m) 13 ft 7 in (4.14 m) Seating Capacity 8-9 Baggage Capacity 1,000 lb (454 kg) 65 cu ft (1.84 cu m) Single Pilot Certified Yes

Landing Weight 11,525 lb (5,228 kg) Maximum Zero Fuel Weight 9,700 lb (4,400 kg) Usable Fuel Capacity 3,930

12 Wingspan 49 ft 10 in (15.19 m) Height 14 ft (4.27 m) Length 47 ft 8 in (14.53 m) Weights Maximum Ramp Weight 12,625 lb (5,727 kg) Maximum Takeoff Weight 12,500 lb (5,670 kg) Maximum Landing Weight 11,525 lb (5,228 kg) Maximum Zero Fuel Weight 9,700 lb (4,400 kg) Usable Fuel Capacity 3,930 lb (1,783 kg) 587 gal (2,221 l) Basic Operating Weight 8,010 lb (3,633 kg) Useful Load 4,615 lb (2,093 kg) Maximum Payload 1,690 lb (767 kg)

13 Full Fuel Payload 685 lb (311 kg) Performance Maximum Cruise Speed 418 ktas (774 km/h) Range 1,613 nm (2,987 km) Takeoff Distance 3,360 ft (1,024 m) Landing Distance 2,980 ft (908 m) Maximum Operating Altitude 45,000 ft (13,716 m) Maximum Climb Rate 4,120 fpm (1,256 mpm) Maximum Limit Speed Mach Powerplant Producing 2,490 pounds (11.08 kn) of thrust at sea level, the CJ2+ is powered by two Williams FJ44-3A- 24 turbofan engines. Even at the maximum takeoff weight with every passenger seat filled, the CJ2+ will still travel more than 1,150 nautical miles (2,130 km). Take on runways as short as 3,360 feet (1,024-m) and use less fuel than other jets in the category. Climb directly to 45,000 feet (13,716 m) in just 28 minutes eight minutes faster than the original CJ2. With the addition of full-authority digital engine controls (FADEC) in every CJ, engine control is simplified, reducing pilot workload during the busiest phases of flight. It also ensures proper power output, engine synchronization, and maximum fuel efficiency. Manufacturer: Williams International Model (Number): FJ44-3A-24 (2) Thrust: 2,490 lbf each (11.08 kn) Time Between Overhauls: 4,000 hrs

14 Citation CJ3 - Detailed Specifications Performance data is based on the standard CJ3 configuration, operating in International Standard Atmosphere (ISA) conditions with zero wind. Takeoff and landing field lengths are based on a level, hard surface and dry runway. Actual performance will vary with factors such as environmental conditions, aircraft configuration and operational/atc procedures. Dimensions Length 51 ft 2 in (15.59 m) Height 15 ft 2 in (4.62 m) Wingspan 53 ft 4 in (16.26 m) Wing Wing Area Wing Sweep 294 sq ft (27 sq m) 0.0 degrees Wheelbase 20 ft (6.10 m) Tread 16 ft (4.88 m) Cabin Interior Height Width Length 57 in (1.45 m) 58 in (1.47 m) 15 ft 8 in (4.78 m) Seating Capacity 7-8 Baggage Capacity 1,000 lb (454 kg) 65 cu ft (1.84 cu m)

15 Single Pilot Certified Yes Wingspan 53 ft 4 in (16.26 m) Height 15 ft 2 in (4.62 m) Length 51 ft 2 in (15.59 m) Weights Maximum Ramp Weight 14,070 lb (6,382 kg) Maximum Takeoff Weight 13,870 lb (6,291 kg) Maximum Landing Weight 12,750 lb (5,783 kg) Maximum Zero Fuel Weight 10,510 lb (4,767 kg) Usable Fuel Capacity 4,710 lb (2,136 kg) 703 gal (2,661 l) Basic Operating Weight 8,760 lb (3,973 kg) Useful Load 5,310 lb (2,409 kg)

16 Maximum Payload 1,750 lb (794 kg) Full Fuel Payload 600 lb (272 kg) Performance Maximum Cruise Speed 416 ktas (770 km/h) Range 1,875 nm (3,472 km) Takeoff Distance 3,180 ft (969 m) Landing Distance 2,770 ft (844 m) Maximum Operating Altitude 45,000 ft (13,716 m) Maximum Climb Rate 4,478 fpm (1,365 mpm) Maximum Limit Speed Mach Powerplant Two, dual-channel FADEC-controlled, Williams FJ44-3A turbofan engines are installed on the CJ3. The engine is a medium-bypass, twin-spool design with five compression stages and three turbine stages. It produces 2,820 pounds (12.54 kn) of thrust at sea level, static conditions, flat-rated up to 79 F (26 C). The FADEC system also provides time-limited dispatch, diagnostics, and engine synchronization. Manufacturer: Williams International Model: (2) FJ44-3A Thrust: 2,820 lbf Time Between Overhaul: 4,000 hrs

Citation CJ4 - Detailed Specifications Performance data is based on the standard CJ4 configuration, operating in International Standard Atmosphere (ISA) conditions with zero wind.

17 Citation CJ4 - Detailed Specifications Performance data is based on the standard CJ4 configuration, operating in International Standard Atmosphere (ISA) conditions with zero wind. Takeoff and landing field lengths are based on a level, hard surface and dry runway. Actual performance will vary with factors such as environmental conditions, aircraft configuration and operational/atc procedures. Dimensions Length 53 ft 4 in (16.26 m) Height 15 ft 4 in (4.67 m) Wingspan 50 ft 10 in (15.49 m) Wing Wing Area 330 sq ft (31 sq m)

18 Wing Sweep 12.5 degrees Wheelbase 21 ft 2 in (6.45 m) Tread 12 ft 4 in (3.76 m) Cabin Interior Height Width Length 57 in (1.45 m) 58 in (1.47 m) 17 ft 4 in (5.28 m) Seating Capacity 8-9 Baggage Capacity 1,040 lb (472 kg) 77 cu ft (2.18 cu m) Single Pilot Certified Yes Wingspan 50 ft 10 in (15.49 m) Height 15 ft 4 in (4.67 m) Length 53 ft 4 in (16.26 m)

19 Weights Maximum Ramp Weight 17,230 lb (7,815 kg) Maximum Takeoff Weight 17,110 lb (7,761 kg) Maximum Landing Weight 15,660 lb (7,103 kg) Maximum Zero Fuel Weight 12,500 lb (5,670 kg) Usable Fuel Capacity 5,828 lb (2,644 kg) 870 gal (3,293 l) Basic Operating Weight 10,430 lb (4,731 kg) Useful Load 6,800 lb (3,084 kg) Maximum Payload 2,070 lb (939 kg) Full Fuel Payload 972 lb (441 kg) Performance Maximum Cruise Speed 451 ktas (835 km/h) Range 1,920 nm (3,556 km) Takeoff Distance 3,190 ft (972 m) Landing Distance 2,740 ft (835 m) Maximum Operating Altitude 45,000 ft (13,716 m) Maximum Climb Rate 3,854 fpm (1,175 mpm) Maximum Limit Speed Mach Powerplant

20 Two dual-channel, FADEC-controlled, Williams FJ44-4A turbofan engines are installed on the CJ4. This engine is a medium-bypass, twin-spool design with four compression stages and three turbine stages. It produces 3,621 pounds (16.11 kn) of takeoff thrust at sea level, static conditions, flat-rated up to 79 F (26 C). The FADEC system also provides time-limited dispatch, diagnostics, and engine synchronization. Manufacturer: Williams International Model: (2) FJ44-4A Thrust: 3,621 lbf Time Between Overhaul: 5,000 hrs Citation XLS+ - Detailed Specifications Performance data is based on the standard CJ4 configuration, operating in International Standard Atmosphere (ISA) conditions with zero wind. Takeoff and landing field lengths are based on a level, hard surface and dry runway. Actual performance will vary with factors such as environmental conditions, aircraft configuration and operational/atc procedures. Dimensions Length 53 ft 4 in (16.26 m)

21 Height 15 ft 4 in (4.67 m) Wingspan 50 ft 10 in (15.49 m) Wing Wing Area Wing Sweep 330 sq ft (31 sq m) 12.5 degrees Wheelbase 21 ft 2 in (6.45 m) Tread 12 ft 4 in (3.76 m) Cabin Interior Height Width Length 57 in (1.45 m) 58 in (1.47 m) 17 ft 4 in (5.28 m) Seating Capacity 8-9 Baggage Capacity 1,040 lb (472 kg) 77 cu ft (2.18 cu m) Single Pilot Certified Yes Wingspan 50 ft 10 in (15.49 m) Height 15 ft 4 in (4.67 m)

22 Length 53 ft 4 in (16.26 m) Weights Maximum Ramp Weight 17,230 lb (7,815 kg) Maximum Takeoff Weight 17,110 lb (7,761 kg) Maximum Landing Weight 15,660 lb (7,103 kg) Maximum Zero Fuel Weight 12,500 lb (5,670 kg) Usable Fuel Capacity 5,828 lb (2,644 kg) 870 gal (3,293 l) Basic Operating Weight 10,430 lb (4,731 kg) Useful Load 6,800 lb (3,084 kg) Maximum Payload 2,070 lb (939 kg) Full Fuel Payload 972 lb (441 kg) Performance Maximum Cruise Speed 451 ktas (835 km/h) Range 1,920 nm (3,556 km) Takeoff Distance 3,190 ft (972 m)

23 Landing Distance 2,740 ft (835 m) Maximum Operating Altitude 45,000 ft (13,716 m) Maximum Climb Rate 3,854 fpm (1,175 mpm) Maximum Limit Speed Mach Powerplant Two dual-channel, FADEC-controlled, Williams FJ44-4A turbofan engines are installed on the CJ4. This engine is a medium-bypass, twin-spool design with four compression stages and three turbine stages. It produces 3,621 pounds (16.11 kn) of takeoff thrust at sea level, static conditions, flat-rated up to 79 F (26 C). The FADEC system also provides time-limited dispatch, diagnostics, and engine synchronization. Manufacturer: Williams International Model: (2) FJ44-4A Thrust: 3,621 lbf Time Between Overhaul: 5,000 hrs

24 Citation Latitude - Detailed Specifications Performance data is based on the standard CJ4 configuration, operating in International Standard Atmosphere (ISA) conditions with zero wind. Takeoff and landing field lengths are based on a level, hard surface and dry runway. Actual performance will vary with factors such as environmental conditions, aircraft configuration and operational/atc procedures. Dimensions Length 53 ft 4 in (16.26 m) Height 15 ft 4 in (4.67 m) Wingspan 50 ft 10 in (15.49 m) Wing Wing Area Wing Sweep 330 sq ft (31 sq m) 12.5 degrees Wheelbase 21 ft 2 in (6.45 m) Tread 12 ft 4 in (3.76 m) Cabin Interior Height Width Length 57 in (1.45 m) 58 in (1.47 m) 17 ft 4 in (5.28 m) Seating Capacity 8-9 Baggage Capacity 1,040 lb (472 kg) 77 cu ft (2.18 cu m) Single Pilot Certified Yes

Landing Weight 15,660 lb (7,103 kg) Maximum Zero Fuel Weight 12,500 lb (5,670 kg) Usable Fuel Capacity 5,828

25 Wingspan 50 ft 10 in (15.49 m) Height 15 ft 4 in (4.67 m) Length 53 ft 4 in (16.26 m) Weights Maximum Ramp Weight 17,230 lb (7,815 kg) Maximum Takeoff Weight 17,110 lb (7,761 kg) Maximum Landing Weight 15,660 lb (7,103 kg) Maximum Zero Fuel Weight 12,500 lb (5,670 kg) Usable Fuel Capacity 5,828 lb (2,644 kg) 870 gal (3,293 l) Basic Operating Weight 10,430 lb (4,731 kg) Useful Load 6,800 lb (3,084 kg) Maximum Payload 2,070 lb (939 kg)

26 Full Fuel Payload 972 lb (441 kg) Performance Maximum Cruise Speed 451 ktas (835 km/h) Range 1,920 nm (3,556 km) Takeoff Distance 3,190 ft (972 m) Landing Distance 2,740 ft (835 m) Maximum Operating Altitude 45,000 ft (13,716 m) Maximum Climb Rate 3,854 fpm (1,175 mpm) Maximum Limit Speed Mach Powerplant Two dual-channel, FADEC-controlled, Williams FJ44-4A turbofan engines are installed on the CJ4. This engine is a medium-bypass, twin-spool design with four compression stages and three turbine stages. It produces 3,621 pounds (16.11 kn) of takeoff thrust at sea level, static conditions, flat-rated up to 79 F (26 C). The FADEC system also provides time-limited dispatch, diagnostics, and engine synchronization. Manufacturer: Williams International Model: (2) FJ44-4A Thrust: 3,621 lbf

Time Between Overhaul: 5,000 hrs Citation X - Detailed Specifications Performance data is based on the standard X configuration, operating in International Standard Atmosphere (ISA) conditions with

27 Time Between Overhaul: 5,000 hrs Citation X - Detailed Specifications Performance data is based on the standard X configuration, operating in International Standard Atmosphere (ISA) conditions with zero wind. Takeoff and landing field lengths are based on a level, hard surface and dry runway. Actual performance will vary with factors such as environmental conditions, aircraft configuration and operational/atc procedures. Preliminary data, subject to change. Dimensions Length 73 ft 7 in (22.43 m) Height 19 ft 3 in (5.86 m)

Wingspan 69 ft 2 in (21.09 m) Wing Wing Area Wing Sweep N/A sq ft (N/A sq m) 37.0 degrees Wheelbase 29 ft 11 in (9.11 m) Tread 10 ft 7 in (3.23 m) Cabin Interior Height Width Length 68 in (1.

28 Wingspan 69 ft 2 in (21.09 m) Wing Wing Area Wing Sweep N/A sq ft (N/A sq m) 37.0 degrees Wheelbase 29 ft 11 in (9.11 m) Tread 10 ft 7 in (3.23 m) Cabin Interior Height Width Length 68 in (1.73 m) 66 in (1.68 m) 25 ft 2 in (7.67 m) Seating Capacity 9-12 Baggage Capacity 775 lb (352 kg) 104 cu ft (2.93 cu m) Single Pilot Certified No Wingspan 69 ft 2 in (21.09 m) Height 19 ft 3 in (5.86 m)

29 Length 73 ft 7 in (22.43 m) Weights Maximum Ramp Weight 36,900 lb (16,738 kg) Maximum Takeoff Weight 36,600 lb (16,601 kg) Maximum Landing Weight 32,000 lb (14,515 kg) Maximum Zero Fuel Weight 24,978 lb (11,330 kg) Usable Fuel Capacity 12,931 lb (5,865 kg) 1,930 gal (7,306 l) Basic Operating Weight 22,464 lb (10,189 kg) Useful Load 14,436 lb (6,548 kg) Maximum Payload 2,514 lb (1,140 kg) Full Fuel Payload 1,505 lb (683 kg) Performance Maximum Cruise Speed 527 ktas (976 km/h) Range 3,242 nm (6,004 km) Takeoff Distance 5,280 ft (1,609 m)

Landing Distance 3,430 ft (1,045 m) Maximum Operating Altitude 51,000 ft (15,545 m) Maximum Climb Rate N/A fpm (N/A mpm) Maximum Limit Speed 0.

30 Landing Distance 3,430 ft (1,045 m) Maximum Operating Altitude 51,000 ft (15,545 m) Maximum Climb Rate N/A fpm (N/A mpm) Maximum Limit Speed Mach Powerplant Two dual-channel FADEC-controlled Rolls-Royce AE3007C2 turbo fan engines power the Citation X. The AE3007C2 features two spools with a 14-stage axial flow compressor, a two-stage high-pressure turbine, and a three-stage low-pressure turbine. The engine has a bypass ratio of 5:1 and a static takeoff thrust at sea level of 7,034 pounds (31.29 kn) flat rated up to 86 F (30 C). Hydraulically actuated, target-type thrust reversers are attached to each engine. An APU is incorporated for engine start and other benefits. Manufacturer: Rolls-Royce Model: (2) AE3007C2 Thrust: 7,034 lbf Time between overhaul: 4,500 hrs

31 Citation Longitude - Detailed Specifications Performance data is based on the standard Longitude configuration, operating in International Standard Atmosphere (ISA) conditions with zero wind. Takeoff and landing field lengths are based on a level, hard surface and dry runway. Actual performance will vary with factors such as environmental conditions, aircraft configuration and operational/atc procedures. Preliminary data, subject to change. Dimensions Length 87 ft (26.52 m) Height 26 ft (7.92 m) Wingspan 86 ft (26.21 m) Wing Wing Area Wing Sweep N/A sq ft (N/A sq m) 30.0 degrees Wheelbase N/A (N/A m) Tread N/A (N/A m) Cabin Interior Height Width Length 72 in (1.83 m) 77 in (1.96 m) 28 ft 11 in (8.81 m) Seating Capacity 8-12 Baggage Capacity N/A lb (N/A kg) 100 cu ft (2.83 cu m)

32 Single Pilot Certified No Wingspan 86 ft (26.21 m) Height 26 ft (7.92 m) Length 87 ft (26.52 m) Weights Maximum Ramp Weight N/A lb (N/A kg) Maximum Takeoff Weight N/A lb (N/A kg) Maximum Landing Weight N/A lb (N/A kg) Maximum Zero Fuel Weight N/A lb (N/A kg) Usable Fuel Capacity N/A lb (N/A kg) N/A gal (N/A l) Basic Operating Weight N/A lb (N/A kg) Useful Load N/A lb (N/A kg)

33 Maximum Payload N/A lb (N/A kg) Full Fuel Payload N/A lb (N/A kg) Performance Maximum Cruise Speed 490 ktas (907 km/h) Range 4,000 nm (7,408 km) Takeoff Distance 5,400 ft (1,646 m) Landing Distance N/A (N/A m) Maximum Operating Altitude 45,000 ft (13,716 m) Maximum Climb Rate N/A fpm (N/A mpm) Maximum Limit Speed Mach Powerplant The Snecma Silvercrest SC-2C is the next-generation business jet engine and is making its debut in the Citation Longitude. With Silvercrest, Snecma gives Citation its best-in-class technologies, based on its long-standing expertise in military aircraft engines, as well as 36 years of experience within the CFM joint venture (GE and Snecma) for the best-selling CFM56 commercial aero-engine. Manufacturer: Snecma Silvercrest SC-2C Thrust: Over 11,000 lbf each at takeoff Fuel burn: 15% lower than engines with similar thrust Noise level: Up to 20 EPNdB vs. Stage 4 Emission: 50% margin vs. CAEP/6

This Flight Planning Guide is published for the purpose of providing specific information for evaluating the performance of the Cessna Corvalis TT.

May 2010 TABLE OF CONTENTS This Flight Planning Guide is published for the purpose of providing specific information for evaluating the performance of the Cessna Corvalis TT. This guide is developed from