Velocity | Edge GX570 | M2 S & D

Exhibit A
PA No. _________________
Specification &
Description
Preliminary
August 2011
Units 525-0800 to TBD
Please Sign and Date:
Purchaser: _________________________________________
Seller: ______________________________________________
S P E C I F I C AT I O N A N D D E S C R I P T I O N
UNITS 525-0800 TO TBD
AUGUST 2011
PRELIMINARY
Citation Marketing
Cessna Aircraft Company
P.O. Box 7706
Wichita, Kansas 67277-7706
Copyright 2011 Cessna Aircraft Company
August 2011, Preliminary
INTRODUCTION
This document is published for the purpose of providing
general information for the evaluation of the design, performance, and equipment of the Cessna Citation M2,
Units 525-0800 to TBD. This document supersedes all
previous Specification and Description documents and
describes only the Cessna Citation M2 Model 525, its
powerplants and equipment.
Due to the time span between the date of this
Specification and Description and the scheduled delivery
date of the Aircraft, Cessna reserves the right to revise
the Specification whenever occasioned by product
improvements, government regulations or other good
cause as long as such revisions do not result in a material reduction in performance.
For additional information contact:
Citation Marketing
Cessna Aircraft Company
P.O. Box 7706
Wichita, Kansas 67277-7706
Telephone: 316-517-6449
Telefax: 316-517-6640
In the event of any conflict or discrepancy between this
document and the terms and conditions of the Purchase
Agreement to which it is incorporated, the terms and
conditions of the Purchase Agreement govern.
WARNING: This product contains Halon 1211, Halon 1301, and also R-134A. Furthermore, the product was manufactured with 1-1-1
Trichloroethane, substances which harm public health and environment by destroying ozone in the upper atmosphere.
1
August 2011, Preliminary
TA B L E O F C O N T E N T S
Cessna Citation M2 Specification and Description
Section
Page
1. General Description . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3
1.1 Certification . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3
1.2 Approximate Dimensions . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3
1.3 Design Weights and Capacities . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 6
2. Performance . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 6
3. Structural Design Criteria . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 7
4. Fuselage . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 7
5. Wing . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 7
6. Empennage . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 7
7. Landing Gear . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 8
8. Powerplants . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 8
9. Systems . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 8
9.1 Flight Controls . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 8
9.2 Fuel System . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 8
9.3 Hydraulic System . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 9
9.4 Electrical System . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 9
9.5 Pressurization and Environmental Systems . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 9
9.6 Oxygen System . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 9
9.7 Ice and Rain Protection . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .10
10. Flight Compartment, Instrumentation and Avionics . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 10
10.1 General . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 10
10.2 Instrument and Control Panels . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 10
10.3 Avionics . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 12
10.4 Miscellaneous Cockpit Equipment . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 15
11. Interior . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 16
11.1 General . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 16
11.2 Standard Interior Configuration . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 17
11.3 Baggage . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 17
12. Exterior . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 18
13. Additional Equipment . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 18
14. Emergency Equipment . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 18
15. Documentation and Technical Publications . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 18
16. Computerized Maintenance Record Service (CESCOM) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 19
17. Limited Warranties . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 19
17.1 Cessna Citation M2 Limited Warranty . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 19
17.2 Williams FJ44 Limited Engine Warranty . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 20
18. Citation M2 Crew Training Agreement . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 21
FIGURE I — CITATION M2 EXTERIOR DIMENSIONS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 4
FIGURE II — CITATION M2 INTERIOR DIMENSIONS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5
FIGURE III — CITATION M2 INSTRUMENT PANEL AND PEDESTAL LAYOUT . . . . . . . . . . . . . . . . . . . . . . . . . . . 11
FIGURE IV — CITATION M2 STANDARD FLOORPLAN . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 16
2
August 2011, Preliminary
M A N U FA C T U R E R
C E S S N A A I R C R A F T C O M PA N Y
MODEL
525
1. GENERAL DESCRIPTION
The Cessna Citation M2 is a low-wing aircraft with
retractable tricycle landing gear and a T-tail. A pressurized cabin accommodates a crew of two and up to six
passengers. Two FADEC controlled Williams
International Co., LLC (Williams) FJ44 turbofan engines
are pylon-mounted on the rear fuselage. Fuel stored in
the wings offers generous range for missions typical of
this class aircraft. Space for baggage is provided in the
nose and tailcone.
Multiple structural load paths and system redundancies
have been built into the aluminum airframe. Metal bonding techniques have been used in many areas for added
strength and reduced weight. Certain parts with non-critical loads such as the nose radome and fairings are
made of composite materials to save weight. The airframe design incorporates anti-corrosion applications
and lightning protection.
Cessna offers a third-party training package for pilots
and mechanics, and various manufacturers’ warranties
as described in this book. Cessna's worldwide network
of authorized service centers provides a complete
source for all servicing needs.
1.1 Certification
The Model 525 is certified to the requirements of U.S. 14
CFR Part 23 including day, night, VFR, IFR, and flightinto-known icing conditions. It is also certified for single
pilot operations. The Citation M2 is compliant with all
RVSM certification requirements. (Note: specific
approval is required for operation within RVSM airspace;
Cessna offers a no charge service to assist with this
process.)
The Purchaser is responsible for obtaining aircraft operating approval from the relevant civil aviation authority.
International certification requirements may include
modifications and/or additional equipment; such costs
are the responsibility of the Purchaser.
1.2 Approximate Dimensions
Overall Height . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 13 ft 9 in (4.19 m)
Overall Length . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 42 ft 7 in (12.98 m)
Overall Width . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 46 ft 11 in (14.30 m)
Wing
Span (does not include tip lights) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 46 ft 7 in (14.20 m)
Area . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 240.0 ft2 (22.30 m2)
Sweepback (at 35% chord) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 0 degrees
Horizontal Tail
Span (tip to tip) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 18 ft 5 in (5.61 m)
Area . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 60.7 ft2 (5.64 m2)
Sweepback (at 70% chord) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 0 degrees
Vertical Tail
Height . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 6 ft 5 in (1.96 m)
Area . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 46.8 ft2 (4.35 m2)
Sweepback (at 25% chord) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 49 degrees
Cabin Interior
Height (maximum over aisle) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 57 in (1.45 m)
Width (trim to trim) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 58 in (1.47 m)
Length (forward pressure bulkhead to aft pressure bulkhead) . . . . . . . . . . . . . . . . . . . . . . . . . . . 15 ft 9 in (4.80 m)
Landing Gear
Tread (main to main) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 13 ft 0 in (3.96 m)
Wheelbase (nose to main) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 15 ft 4 in (4.67 m)
3
August 2011, Preliminary
1. GENERAL DESCRIPTION (Continued)
46 ft 11 in (14.30 m)
18 ft 5 in (5.61 m)
13 ft 0 in
(3.96 m)
13 ft 9 in
(4.19 m)
15 ft 4 in (4.67 m)
42 ft 7 in (12.98 m)
FIGURE I — CITATION M2 EXTERIOR DIMENSIONS
4
August 2011, Preliminary
1. GENERAL DESCRIPTION (Continued)
107 in
(2.72 m)
57 in
(1.45 m)
25 in
(.64 m)
58 in (1.47 m)
20 in (.51 m)
51 in
(1.30 m)
11 in
(.28 m)
24 in
(.61 m)
15 in
(.38 m)
19 in
(.48 m)
29 in
(.74 m)
57 in
(1.45 m)
FIGURE II — CITATION M2 INTERIOR DIMENSIONS
5
August 2011, Preliminary
1. GENERAL DESCRIPTION (Continued)
1.3 Design Weights and Capacities
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)
Standard Empty Weight * . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 6,773 lb (3,072 kg)
Useful Load . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 4,009 lb (1,818 kg)
Fuel Capacity (useable) at 6.70 lb/gal . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3,309 lb (1,501 kg)
* Standard empty weight includes unusable fuel, full oil, standard interior, and standard avionics.
2. PERFORMANCE
All performance data is based on a standard aircraft configuration, operating in International Standard Atmosphere
conditions with zero wind. Takeoff and landing field
lengths are based on a level, hard surface, dry runway.
Actual performance will vary with individual airplanes and
other factors such as environmental conditions, aircraft
configuration, and operational/ATC procedures.
Takeoff Runway Length . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3,250 ft (991 m)
(Maximum Takeoff Weight, Sea Level, ISA,
Balanced Field Length per Part 25, 15° Flaps)
Climb Performance . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 25 min to 41,000 ft (12,497 m)
(Maximum Takeoff Weight, Sea Level, ISA)
Maximum Altitude . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 41,000 ft (12,497 m)
Maximum Cruise Speed (±3%) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 400 KTAS (741 km/hr, 460 mph)
(Mid-Cruise Weight, 31,000 ft (9,449 m), ISA)
NBAA IFR Range (100 nm alternate) (± 4%) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1,300 nm (2,408 km, 1,496 mi)
(Maximum Takeoff Weight, Full Fuel, Optimal Climb
and Descent, Maximum Cruise Thrust at 41,000 feet)
Landing Runway Length . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2,590 ft (789 m)
(Maximum Landing Weight, Sea Level, ISA, per Part 25)
Certificated Noise Levels
Takeoff . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 73.5 EPNdB
Sideline . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 85.2 EPNdB
Landing . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 88.5 EPNdB
6
August 2011, Preliminary
3. STRUCTURAL DESIGN CRITERIA
The Citation M2 airframe is conventional in design,
incorporating aluminum alloys, steel and other materials as appropriate. Engineering principles using multiple load paths, low stress levels and small panel size
are incorporated in the primary structure. Design
maneuver limit load factors are -1.52 Gs to +3.8 Gs.
Ultimate loads are defined as 1.5 times the limit loads.
The structure supports a nominal maximum cabin pressure differential of 8.5 psi (.59 bar).
Limit Speeds
VMO at Sea Level to 30,500 ft (9,296 m) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 263 KIAS (487 km/hr, 303 mph)
MMO at 30,500 ft (9,296 m) and above . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Mach 0.71 (indicated)
Flap Extension Speeds
VFE 0° to 15° Extension . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 200 KIAS (370 km/hr, 230 mph)
VFE 15° to 35° Extension . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 161 KIAS (298 km/hr, 185 mph)
Landing Gear Operating and Extended Speed
VLO (retracting) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 175 KIAS (324 km/hr, 201 mph)
VLO (extending) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 186 KIAS (344 km/hr, 214 mph)
VLE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 186 KIAS (344 km/hr, 214 mph)
4. FUSELAGE
The Model 525 fuselage has a constant circular cross
section and is attached to the wing without any cutouts
for the spar. A dropped isle from just behind the cockpit
through the lavatory makes moving about the cabin easier. The keyed cabin door is located on the forward lefthand side of the fuselage. It has 12 locking pins and two
pressure seals and is hinged forward with a folding twostep entry stair mounted just inside the entrance. A plugtype emergency exit is located on the aft right-hand side
of the cabin. The windshields are designed to meet bird
resistance requirements of 14 CFR Part 25. Framing
assemblies surround the main door opening, emergency
exit, and windshields to provide structural continuity.
The nose section includes a generous baggage compartment from which the avionics bay, oxygen bottle,
and windshield alcohol supply are accessible. Behind
the composite radome is the high-resolution weather
radar antenna and processor.
The aft fuselage houses the major components of the
hydraulic, environmental, electrical distribution, flight control, and engine fire extinguishing systems. A baggage
compartment is also located in the tailcone. External
access to both the equipment and the baggage area is
provided through a baggage door on the lower left-hand
side of the aft fuselage and removable exterior panels.
5. WING
The straight wing design of the M2 incorporates a natural laminar flow airfoil. The wing structure is a three spar
design with a shallow drop in the center section to permit attachment of the fuselage without interruption of the
cabin cross-section. Five degrees dihedral contributes to
lateral stability.
Integral fuel tanks are located in each wing. Control surfaces on the wing include outboard ailerons, wide span
flaps with a lift-dump feature, and upper and lower surface
speed brakes. The left-hand aileron incorporates a trim tab.
The wing leading edges are anti-iced using engine bleed
air. Aluminum fairings blend the wing and fuselage for
minimum drag. The landing lights consist of industry
proven OSRAM LED technology and are integrated with
a Pulselight system which are mounted below the fuselage in the fairing. The wing tips include LED position
and anti-collision lights and static wicks.
6. EMPENNAGE
The empennage section is a T-tail design with a onepiece horizontal stabilizer. The horizontal stabilizer's leading edge is equipped with pneumatic de-ice boots. The
rudder and the elevators have pilot-controlled trim tabs. A
tail logo light is standard with a red LED ground recognition
light mounted on the top.
7
August 2011, Preliminary
7. LANDING GEAR
The main and nose landing gear each use a single
wheel assembly. The landing gear retraction system is
electrically controlled and hydraulically actuated and
takes less than 6 seconds to cycle. Each main gear is a
trailing link type and retracts inboard into the wing. The
nose gear retracts forward into the fuselage nose section and, when retracted, is enclosed by doors. The nose
wheel has a chined tire for water and slush deflection.
Emergency landing gear extension is accomplished by
manual release of the uplocks for free fall followed by
use of the pneumatic blow-down system.
The landing gear may be extended at speeds up to 186
KIAS. A warning horn will sound with the gear retracted
if airspeed is below 130 KIAS and either throttle is
retarded below approximately 85% N2. The nose gear is
mechanically steered by the rudder pedals to 20
degrees either side of center. For ground handling maximum deflection of the nosewheel is 95 degrees either
side of center.
Multiple disc anti-skid brakes are installed on the main
gear wheels. An independent, electrically driven
hydraulic system provides the power for braking with a
pneumatic system for back-up. Anti-skid protection is
available at speeds above 12 knots.
8. POWERPLANTS
Two Williams FJ44 turbofan engines are installed, one
on each side of the rear fuselage in easily accessible
nacelles. This engine is a 2.58:1 bypass, twin-spool
design with 3 compression stages and 3 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).
time-limited dispatch (TLD) and diagnostics. Electrical
power for the FADECs comes from engine driven permanent magnet alternators (PMAs) rectified to DC. There are
two PMAs mounted to each engine. In the event that both
PMAs fail on one engine, the FADEC on that side will draw
from main DC power.
Dual channel Full Authority Digital Engine Controls
(FADECs) provide automation and efficiency in engine management. Detents in the throttle quadrant for takeoff (TO),
maximum continuous (MCT), high speed cruise (CRU) give
pilots the optimal power settings for each phase of flight
based on ambient conditions. The system also provides
The FJ44 engine incorporates a modular design and
multiple borescope ports for easier maintenance and
inspections. Engine overhaul is required at 3,500 hour
intervals. A continuous loop fire detection system monitors the nacelle area to detect and warn if a fire occurs.
A fire extinguishing system is supplied.
9. SYSTEMS
9.1 Flight Controls
Dual flight controls are provided consisting of control
wheel columns, adjustable rudder pedals, brakes and
mechanical nose wheel steering. Pushrod, bellcrank, sector, and cable systems are used to actuate the rudder, elevator, and ailerons. Corrosion resistant stainless steel
cables are used in all primary and secondary systems.
8
is for lift dump and increased drag only during landing
and will automatically cause the speed brakes to deploy.
Speed brakes extend above and below each wing and
may be extended in flight at any speed. However, they
will automatically retract anytime either engine’s throttle
lever is in a high thrust position. The flaps and the speed
brakes are electrically controlled and hydraulically actuated.
Trim wheels installed on the pedestal control mechanical
trim tabs for the left aileron, elevators and rudder. The elevator trim also has an electric actuator controlled by
switches on each pilots' control wheel. A yaw damper system in the tail works with the autopilot to augment stability at high altitudes, however, it is not required for dispatch.
An integral control lock below the pilot's panel holds the
rudder, elevators, ailerons, and throttles during storage.
9.2 Fuel System
Wide span flaps are controlled by a handle on the
pedestal with detents at 15, 35, and 60 degrees. Any
intermediate position from zero to 35 degrees may be
selected in flight. The 60 degree position, or ground flaps,
One electric boost pump in each tank sump delivers fuel
during engine start, fuel transfer, and as activated by low
fuel pressure. Each engine has an engine driven fuel
pump and a fuel delivery unit (FDU) controlled by the
The M2 has two integral fuel tanks, one per wing, providing a total of 3,302 pounds (1,497 kg) of usable fuel.
System operation is fully automatic throughout the normal flight profile with each engine receiving fuel from its
respective wing tank. Fuel is heated through an oil heat
exchanger and anti-ice additives are not required.
August 2011, Preliminary
9. SYSTEMS (Continued)
respective FADEC to deliver high pressure fuel to the
engine. Some of that high pressure fuel from the FDU is
routed back to a motive flow ejector pump in each fuel
tank sump to generate the low pressure fuel supply
required by the FDU and by the one motive flow scavenge pump per tank located near each sump. Fuel may
be transferred from tank to tank as needed. A vented
surge tank is integrated near each wing tip.
Fuel levels are monitored by six passive capacitance
probes per wing and one dual channel signal conditioner for
accurate quantity indications which are shown on the multifunction display. Refueling is accomplished through over
wing filler ports with flush mounted caps.
9.3 Hydraulic System
The hydraulic system is an open-center design providing
1,500 psi (103.4 bar) on demand to operate the landing
gear, speed brakes, and flaps. Two engine-driven
pumps, one located on each engine, supply hydraulic
pressure. Either pump can supply enough pressure and
flow to operate the system. An independent hydraulic
system, driven by an electric motor, operates the wheel
brakes and anti-skid system, and charges the emergency accumulator.
9.4 Electrical System
The M2 electrical power generation and distribution system features traditional parallel bus architecture designed
to provide 600 amperes at 29 volts DC from two engine
driven 300 ampere starter/generators. One 44 amperehour nickel cadmium battery is used for initial engine starts
and serves as a limited backup to the generators.
Each generator is connected to a remote digital generator control unit (GCU) in the tailcone. The two GCUs are
connected to each other to allow proportionate load
sharing. If one generator becomes disabled in flight, the
vapor cycle air conditioning system, if in use, and the
interior electrical equipment, will automatically load shed
to prevent overloading the remaining generator. All other
systems are supplied by the remaining generator
through the respective main and crossfeed busses.
All system controls are located on the left-hand power
switch panel and the indications are displayed on the
MFD EIS window for voltage and generators amperage.
Left and right circuit breaker panels are positioned on
the cockpit sidewall within easy reach of each pilot. A
junction box is accessible through the aft baggage com-
partment. The battery, with quick disconnect, is positioned just left of the baggage compartment door behind
an easy access panel. An external power receptacle is
provided below the left engine pylon.
A sealed lead acid 24V, 16a-hr auxiliary battery is
installed in the nose over the landing gear well. During
normal operation the battery works in conjunction with
the primary ships battery to allow for all aircraft systems,
including avionics, to be powered on during engine
starts. The auxiliary battery is also used to provide additional battery capacity during emergency operation.
A 500 watt inverter supplies 110 volt AC power to three
outlets: one in the copilot's sidewall and two in the cabin.
9.5 Pressurization and Environmental Systems
Engine bleed air is tapped to pressurize the M2 cabin.
The pressurization control system automatically schedules cabin altitude and change rate while maintaining a
nominal maximum pressure differential of 8.5 psi. Cabin
altitude and rate of change are automatically managed
by a digital, auto-schedule controller. A nominal maximum differential pressure of 8.5 psi (.59 bar) permits a
sea level cabin altitude up to 22,027 feet (6,714 m),
increasing to 8,000 feet (2,438 m) at the maximum
cruise altitude of 41,000 feet (12,497 m). The MFD displays all pressurization parameters and the GTCs provide pilot interface for entry of landing field elevation.
Engine bleed air is also used to heat the cabin and to
defog the windows. A vapor cycle air conditioning system provides cooling and may be operated anytime in
the air, or on the ground when ground power is connected or when the right engine is running. In flight, the system automatically shuts down if one generator falls off
line. A cockpit thermostat permits automatic temperature
control and a five-position flow divider allows proportioning of the airflow.
9.6 Oxygen System
A 50 cubic foot (1.42 m3) oxygen bottle, located in the
nose, is provided with a high pressure gauge and bottlemounted pressure regulator. Quick-donning pressure
demand masks with microphones are provided at each
crew seat, while automatic dropout constant-flow oxygen
masks are provided at each passenger seat and above
the toilet. Oxygen flow to the cabin is controlled by a
sequencing regulator valve for optimal passenger usage.
9
August 2011, Preliminary
9. SYSTEMS (Continued)
9.7 Ice and Rain Protection
Engine bleed air is used for anti-ice protection of the
engine inlets, pylon inlet ducts, wings, and windshields.
The pilot's windshield also utilizes a back-up alcohol
anti-ice system. The horizontal stabilizer leading edges
are fitted with pneumatic de-ice boots, inflated by
engine bleed air (23 psi service air system). A timer
manages the inflation cycle. The pitot tubes, static
ports, and the AOA sensor are electrically anti-iced. Two
windshield ice detection lights are mounted on the
glareshield and a wing inspection light is positioned on
the left side of the fuselage to assist in the detection of
ice buildup during night flights.
Windshield rain removal is accomplished with engine
bleed air during normal operations and by mechanically actuated rain doors to provide deflected airflow in
heavy rain.
1 0 . F L I G H T C O M PA R T M E N T, I N S T R U M E N T AT I O N A N D A V I O N I C S
10.1 General
The Citation M2 features the Garmin G3000 advanced
avionics system, a large-format glass cockpit with integrated sensors and lightweight modular avionics. The
system presents to the crew all the flight, navigation, and
situational inputs, as well as aircraft systems information, for a precise picture of the total flying environment.
Three liquid crystal displays (LCDs) offer high resolution,
wide viewing angles, and clear sunlight readability.
Complete flight management functionality and a three
axis digital autopilot ease the workload for one or two
pilots.
10.2 Instrument and Control Panels
A. Installed on Center Glareshield Panel:
•
•
•
•
•
•
LH and RH Master Caution / Master Warning Lights
LH and RH Engine Fire Control Switches
Reversionary and Dimming Controls
Flight Director / Autopilot Controller
Electronic Standby Instrument System
LH and RH Display Control Units
B. Installed on Instrument Panel (left to right):
•
•
•
•
10
Electrical Power Panel
LH Primary Flight Display (PFD)
Multi-Function Display (MFD)
RH Primary Flight Display (PFD)
C. Installed on Tilt Panel (left to right):
•
•
•
•
•
•
•
•
•
•
•
•
Pressurization Controls
Ice Protection Controls
Windshield Anti-ice Controls
Fuel Controls
Ignition Controls
Landing Gear Control Module
Lighting Controls
Emergency Comm Switch
Event Marker
Cockpit Voice Recorder Controller
Flight Hour Meter
ELT Remote Switch
D. Installed on Pedestal:
•
•
•
•
•
•
•
•
•
•
GTC 570 (2) each
Engine Start Control
Engine Power Levers
Flap Control Handles
Speed Brake Control
Elevator Trim Control and Indicator
Takeoff / Go-Around Button
Rudder Trim Control
Aileron Trim Control
Environmental Controls
E. Installed Beneath the Instrument Panel:
•
•
•
•
•
Emergency Brake Handle
Parking Brake Handle
Emergency Gear Release
Control Locks
Rain Removal levers
August 2011, Preliminary
1 0 . F L I G H T C O M PA R T M E N T, I N S T R U M E N T AT I O N A N D A V I O N I C S
(Continued)
1 - Power Panel
11 - Multi-Function Display (MFD)
2 - Radio Call Placard
12 - LH Tilt Panel Including Ice Protection,
Pressurization, Fuel and Engine Controls
3 - Master Caution / Warning Annunciators
4 - Display Control Unit
5 - Standby Flight Display
6 - Left Engine Fire Warning and Extinguisher Bottle
Arm / Discharge Button
7 - Dimming and Reversion Control
8 - Flight Director / Autopilot Mode Controller
9 - Right Engine Fire Warning and Extinguisher
Bottle Arm / Discharge Button
13 - Landing Gear Panel
14 - Touch-Screen Controller
15 - Aft Pedestal Panel Including Engine Start and
Environmental Controls
16 - RH Tilt Panel Including Lighting Controls
17 - Flight Hour Meter
18 - CVR Control Head (Optional)
19 - ELT Switch
10 - Primary Flight Displays (PFD) Left and Right
FIGURE III — CITATION M2 INSTRUMENT PANEL AND PEDESTAL LAYOUT
11
August 2011, Preliminary
1 0 . F L I G H T C O M PA R T M E N T, I N S T R U M E N T AT I O N A N D A V I O N I C S
(Continued)
10.3 Avionics
Described below is the Citation M2 standard avionics
suite as referred to in section 17, Limited Warranties.
The Garmin G3000 is an integrated avionics and flight
guidance system providing flight, navigation, communication, surveillance, situational awareness, and aircraft
systems status and alerting on three large glass displays.
A. Electronic Flight Instrument System (EFIS)
The G3000 system utilizes three 14.1 inch (diagonal)
Control display units (GDU1400W) as Primary Flight
Displays (PFD) and Multi-Function Display (MFD). All
three are WXGA Liquid Crystal Displays (LCD) with LED
backlighting and a resolution of 1280 x 800.
Behind the MFDs and within the pressure vessel are the
two remote audio processors (GMA 36). Located in the
nose of the aircraft are the main Garmin Interface
Adapter Units (GIA 63W) incorporating all communication, navigation, automatic flight control, and extensive
data management functions. These two interface
adapter units are directly linked to the AHRS, ADCs,
transponders, audio controllers, and Engine/interface
units (GEA 71, located in the tail cone). Data from each
source is processed and sent to the PFDs and MFD.
Ethernet architecture and various ARINC cabling are
used for high-speed data transfer. Most components are
line replaceable units (LRUs) contained in individual
trays and racks.Two glareshield cooling fans continuously circulate cockpit air around the avionics.
B. Primary Flight Display (PFD)
The following elements are shown on the PFDs in normal mode: attitude (full screen horizon line), altitude tape
(feet or meters with six-second trend vectors), airspeed
tape (with six-second trend vectors), Mach, vertical
speed, flap limit speeds, slip/skid, heading, horizontal
situation, glide slope, flight director (cross pointer or single cue), navigation and communication frequencies
(active and standby), navigation station/waypoint identification, track, distance, transponder code, altimeter setting (inches or hectopascals), clock, timer (up or down),
temperature (RAT), ISA deviation, and many other
items. V-speeds can be automatically generated or are
entered manually by the pilot and will appear on the airspeed tape. At the bottom edge of the display several
menu items are shown directly above corresponding soft
12
keys on the bezel. The soft keys are used to select the
menu and submenu items. Selection of the "Inset" soft
key places a smaller version of the MFD navigation map
in the lower corner of the PFD for added situational
awareness. The Crew Alerting (CAS) information will be
presented on the PFDs.
C. Multi-Function Display
The MFD serves primarily as a moving map and EIS
platform. The moving map may be populated with a wide
variety of information including traffic, terrain, airborne
weather radar, data link weather, political and airspace
boundaries, airports, navaids, way points, cities, roads,
Garmin FlightCharts and Safe Taxi, and many others, all
at various ranges, The pilot may choose a north-up or
track-up orientation. These and many other options may
be selected using the soft keys along the bottom edge of
the bezel or by using the touch screen GTC 570. A subscription though Garmin is required for database
updates.
D.
Secondary Controller
The GCU 275 is a PFD controller used to perform inset
map panning and ranging, to adjust the barometric setting, and to access often used and high-workload flight
planning functions such as the active flight plan on the
lower inset window on the PFD. The GCU 275 will also
control the MFD unit when it is operating in reversionary
mode and presenting primary flight information.
E. Engine Indicating (EIS) and Crew Alerting
System (CAS)
The EIS information is presented on the left side of the
MFD and includes: engine speeds and temperatures; oil
pressures and temperatures; fuel flow, quantity and temperature; oxygen pressure and electrical and pressurization systems data. The Crew Alerting (CAS) is presented
on the lower part of each PFD and shows colored text
messages as determined by system inputs. Up to 10
messages are shown in the CAS box; additional messages may be scrolled into view by using the PFD soft
keys. Pre-programmed logic determines the color, order,
and flashing characteristics of all messages.
Each display may show the essential components of the
EIS and CAS in reversionary mode. Reversion may be
selected manually for either the pilot or copilot side using
switches located below the glareshield.
August 2011, Preliminary
1 0 . F L I G H T C O M PA R T M E N T, I N S T R U M E N T AT I O N A N D A V I O N I C S
(Continued)
F.
Air Data and Attitude information
The pitot-static system includes two electrically heated
pitot and static sources. Each is cross-plumbed into dual
air data computers (ADCs) located in the forward nose
behind the radar bulkhead. The ADCs perform source
error corrections and calculate indicated airspeed, true
airspeed, mach number, vertical speed, density altitude,
pressure altitude, and total temperature for output to the
Interface Adapters and the PFDs.
In addition, ADC output is received by the Attitude and
Heading Reference Systems (AHRS). Two solid state
digital AHRS reside behind the MFD and are each tied to
the three-axis magnetometers located in the tail. The
AHRS are capable of in-flight and on-the-move initialization. Output from the AHRS is received and processed
by the Interface Adapter Units and the PFDs. The system meets RVSM requirements.
Input from an electrically heated stall warning vane on
the right side of the forward cabin is processed by the
Interface Adapter Units for display on the PFDs and for
input to the aural warning system.
G. VHF Communications Transceivers
Dual VHF communications transceivers are part of the
Interface Adapter units and produce 16 watts of transmission power. They are compliant with European 8.33
kHz channel spacing requirements. Tuning and management is accomplished through dual touch screen
GTC 570 controllers. There is also an emergency radio
tuning switch located on the right side tilt panel that will
tune the VHF radio to 121.5 bypassing all other tuning
controls.
H. Remote Audio Processor
Dual GMA 36 Remote Audio Processors controlled
through the dual GTC 570 touch screen controllers provide transmitter section for microphone inputs and direct
audio outputs from all receivers to the speakers and/or
headphones at each crew station. The system includes
crew and cabin intercom and the ability to record and
playback up to 2 ½ minutes of incoming audio. Two
handheld microphones are connected to the audio
processors and installed on each of the control columns.
I.
Navigation
Dual Garmin navigation receivers located in the
Interface Adapter Units provide VOR, Localizer and
Glideslope functions. The Marker Beacon receivers are
integrated into the Audio Processors. Navigation information is displayed on both PFDs and the reversionary
mode of the MFD. Tuning and management is accomplished through the dual touch screen controllers.
J. Global Positioning System (GPS)
Each Interface Adapter Unit includes a WAAS capable
GPS receiver. Both receivers are capable of monitoring
12 channels to provide satellite-based position data for
use by the FMS.
K. Flight Management System (FMS)
The Garmin FMS provides a multiple waypoint navigation solution suitable for enroute, terminal, and WAAS
precision approach navigation. The touch screen controllers (GTC570) on the pedestal are the FMS interface
to the MFD. It includes controls for selection and manipulation of moving map functions such as range and pan.
Each PFD calculates and displays the current flight plan
using the onside GPS sensor. Automatic GPS sensor
reversion occurs in the event the onside sensor is
degraded or failed.
Airway flight planning, plain language identifiers, airport
communication and navigation frequency lookup features are included. Flight plans may be created, stored,
accessed, and activated as needed and are shown on
the MFD moving map. Both lateral and vertical modes
(to the final approach fix) may be displayed and coupled
to the autopilot. Present position referenced geopolitical
and airspace boundaries, and airways may be overlaid
on any of the FMS map formats.
Precision guidance from the FMS meets the operational
requirements of oceanic/remote, NAT MNPS, RNP10,
and RNP5/BRNAV. The navigation database requires
periodic updates via subscription and must be uploaded
to the aircraft through the upper SD flash card port on
each of the three displays.
L. Automatic Flight Control System (AFCS)
Automatic flight control is provided in the M2 by the
Garmin GFC 700 system. The autopilot system (AP)
includes dual flight director computers (integrated in the
Interface Adapter Units), a single Garmin Mode
Controller (GMC 710), and four electric servos for roll,
yaw, pitch, and pitch trim.
13
August 2011, Preliminary
1 0 . F L I G H T C O M PA R T M E N T, I N S T R U M E N T AT I O N A N D A V I O N I C S
(Continued)
The GMC 710 Mode Controller, located just below the
glareshield, enables the selection of flight director and
autopilot modes for either pilot. The AFCS modes may
be hand flown using the flight director command bars or
coupled to the autopilot for automatic flight. Selection of
the autopilot will automatically enable the flight director.
Modes of operation include attitude, heading, altitude,
speed, and vertical speed, as well as VNAV and the various NAV radio and GPS navigation modes. In addition,
the AFCS provides a takeoff/go-around mode activated
by a button on the left throttle handle. Control Wheel
Steering (CWS) and AP disconnect functions are controlled via switches on each yoke.
The pitch trim servo also provides electric pitch trim
when the autopilot is not engaged, through yoke mounted trim switches. The yaw servo may be activated by the
pilot during normal maneuvers to provide Dutch roll
damping and turn coordination. Or, it will automatically
engage with autopilot activation.
M. Transponders
The Garmin GTX 33D transponders reply to Mode A,
Mode C, and Mode S interrogation. Ground stations can
interrogate Mode S Transponders individually using a
24-bit ICAO Mode S address (unique to the aircraft), and
the ground station can interrogate the transponder for its
transponder data capability and the aircraft's Flight ID
(registration number or other call sign). The GTX 33D
transponders also feature Extended Squitter that provides Automatic Dependent Surveillance-Broadcast
(ADS-B) capability to improve situational awareness and
flight safety. ADS-B capability automatically transmits
position, velocity, and heading information to other aircraft and ground stations to provide surveillance of airto-air traffic and aircraft in remote areas not currently
covered by radar.
N. Weather Avoidance Radar
The Garmin GWX 70 is a solid state radar with 40 watts
of transmit power and Altitude Compensated Tilt (ACT).
The radar supports display of different weather data on
multiple display units simultaneously. Doppler capability
is an option on the GWX 70 which adds the ability to see
frequency shifts that are caused when an object reflecting the radar pulse is moving relative to the radar itself.
The addition of Doppler adds the two distinct advantages of Turbulence Detection and Ground Clutter
Suppression.
14
O. XM Weather Receiver
The Garmin GDL 69 is a remote satellite radio receiver
that is capable of receiving XM Weather which is displayed on the PFDs and/or MFD. The receiver operates
in the S-band frequency range and provides a continuous downlink capability at any altitude throughout North
America. Optionally, XM Radio Audio can be received
through this unit.
P. DME
A single Collins DME-4000 provides the ability to monitor as many as three active DME stations simultaneously. This allows full time distance display of pilot-selected
VHF navaids, along with the enhancement of FMS position determination through the use of non-displayed
DME channels. Tuning and management is accomplished through the GTCs.
Q. Radio Altimeter
The Collins ALT-4000 Radio Altimeter system provides
height above the terrain from 2,500 feet (762 m) to
touchdown. This information is integrated with functions
in the EFIS, TCAS, and TAWS and is presented on the
PFDs.
R. Traffic Collision Avoidance System (TCAS I)
The Garmin GTS 855 is a TCAS I system that improves
situational awareness by tracking all Mode C and S aircraft and displaying their locations on the PFDs and/or
MFD. In addition to the display, Traffic Alerts are given
aurally through the aircraft audio system.
S. Terrain Avoidance Warning System (TAWS)
The Garmin Terrain Avoidance Warning System is a
Class B TAWS. The system provides basic terrain awareness and ground proximity alerting. Terrain information is
displayed in standard colors on the MFD and gives both
audible and visual warnings as required. The terrain
database resides in the secure digital data storage cards
located in the lower port on the right hand side of each
PFD and MFD bezel. Data is independently processed
by each of the three Display Units for display either when
pilot selected or when activated by ground proximity criteria.
August 2011, Preliminary
1 0 . F L I G H T C O M PA R T M E N T, I N S T R U M E N T AT I O N A N D A V I O N I C S
(Continued)
T. Avionics Dispatch Switch
A Dispatch Power switch in the Electrical Power Panel
allows for limited avionics equipment to be powered for
ground radio calls and FMS flight planning operations
without the battery drain of powering the entire avionics
suite without engines running.
U. Electronic Standby Instrument
The L-3 Communications ESI-1000 Trilogy Electronic
Standby Instrument (ESI) is a solid-state instrument that
provides backup for attitude, altitude, airspeed, and
slip/skid information on a 3.7 inch Liquid Crystal Display
with LED backlight.
A bezel-mounted light sensor provides automatic dimming with manual offset controlled via the menu access
mode. Four soft key buttons on the front of the bezel provide the user with quick access for setting display and
button brightness, barometric setting and access to
menu options.
download, use, and/or read such information at any
time. Purchaser further agrees this perpetual license
runs with and is automatically transferred with the title to
the Aircraft and is binding on any and all subsequent
purchasers of the Aircraft.
10.4 Miscellaneous Cockpit Equipment
• Magnetic Compass
• Eye Position Reference Indicator
• Two Ventilation Air Outlets
• Oxygen System Control
• Two Oxygen Masks
• Parking Brake Control
• Rain Removal Door Control
• Control Lock
• Emergency Brake Control
• Emergency Gear Extension Control
• Two Reading Lights
• Floodlight
V. Emergency Locator Transmitter (ELT)
The Artex C406-N is a three frequency ELT that transmits on the emergency frequencies of 121.5 and 243.0
MHz and the satellite frequency of 406 MHz. It is located in the tailcone and interfaces with the GIA to transmit
the last known aircraft position on the satellite frequency
if activated. (Interface feature disallowed by some certifying agencies.) The C406-N has a remote control
switch panel on the right hand tilt panel and a six-year
lithium battery pack.
W. Maintenance Diagnostics
The G3000 system includes the capability to record specific maintenance diagnostic information, which can be
reviewed on the MFD while on the ground and downloaded for review off the Aircraft. In addition, the M2
incorporates full time data storage through a Cessna
Aircraft Recording System (AReS). AReS records useful
data during the previous 25+ flight hours in non volatile
memory for advanced troubleshooting and analysis by
systems specialists from the Cessna Service and
Support network.
Purchaser agrees that Cessna has a perpetual license
to use all information contained in the Aircraft recording
and/or diagnostic systems for any reason, including
maintenance and accident investigation. Purchaser
expressly provides Cessna with licensed permission to
15
August 2011, Preliminary
11. INTERIOR
11.1 General
The Citation M2 cockpit is designed to provide the crew
with the tools for the job in a comfortable working environment. Single pilot capabilities mean that all essential
controls are within easy reach from the left seat. Each
crew seat is fully adjustable and includes a five-point
restraint system. Left and right hand reading lights, air
outlets, sidewall map pockets, chart cases, and dual
cupholders are provided.
The standard configuration in the Citation M2 features a
side facing seat with an armrest cabinet, a refreshment
center across from the side facing seat and four passenger seats in a center club configuration. A left hand
belted flushing toilet and a center aft coat rod are located in the aft cabin lavatory. A removable curtain provides
privacy.
A five inch dropped aisle, extending from the cockpit
divider aft through the lavatory, provides a cabin height
of 57 inches. The constant cross section of the cabin
provides a continuous width of 58 inches.
(Measurements represent distance between softgoods.)
The cabin is 11 feet long measured from the cockpit
divider to the aft pressure bulkhead.
Included are indirect overhead lights with full dimming
capability. Entrance and emergency exit lights are also
provided in the passenger cabin. Eight elliptical windows
offer exceptional natural lighting throughout the cabin.
Three panes per window and bagged insulation in the
walls contribute to a quiet, comfortable cabin environment. With the exception of the entrance door, each window has pleated manual window shades.
2
2
1
4
6
3
1
5
7
CABIN
DOOR
8
D
9
9
(#3)
(#4)
10
10
11
11
9
9
(#5)
(#6)
12
14
13
EMERGENCY
EXIT
15
D
Each passenger seat is mounted on a pedestal with the
ability to track forward, aft, and laterally. Each seat may
be reclined depending on its position on the pedestal.
The aft cabin divider restricts seat #5 (see diagram).
Individual air outlets and reading lights are provided in
the cabin overhead above each passenger. Dropout,
constant-flow oxygen masks are also installed in the
overhead for emergency use. Cupholder/storage areas
are built into the side ledge next to each seat. A 110 volt
AC outlet is included in the aft dividers behind seats #5
and #6. Also built into the sideledges in the center club
are foldout executive tables with leather table top
inserts.
An extensive selection of carpets, fabrics, leathers, and
matte laminate cabinetry coverings, all burn-resistant,
are included in the base price of the aircraft.
16
FIGURE IV — CITATION M2 STANDARD FLOORPLAN
August 2011, Preliminary
11. INTERIOR (Continued)
11.2 Standard Interior Configuration
The following items are standard in the Citation M2.
Numbered items refer to the cabin diagram (Figure IV).
Cockpit
1. Two crew seats
• Five-Point Restraint System
• Stowable Inboard Armrest
• Fwd & Aft Tracking Lever
• Recline Adjustment Lever
• Height Adjustment Lever
• Adjustable Lumbar
• Seat Back Pocket
• Overwater Life Vest Located In Seat Base
2. Dual cupholders for each crew seat
3. Single 110 volt AC outlet in copilot sidewall
4. LH two-book navigation chart case
5. RH two-book navigation chart case
Not Shown:
• Two monorail sunvisors
• Cockpit assist handle
• Fire extinguisher
Cabin Area
6. LH refreshment center
•
•
•
•
Heated liquid container
Two dispensers for disposable cups
Beverage can storage
Ice chest drawer with removable liner connected to an
overboard drain
• Trash container
7. RH forward divider
• Half-length removable cockpit curtain on the forward
side of the divider may be drawn across aisle through
an overhead track and secured on the LH refreshment
center
8. RH forward side facing seat with armrest storage cabinet
•
•
•
•
Seat restraint
Cupholder/Storage area
Overwater life vest
Storage drawer
9. Pedestal seats: two aft facing and two forward facing
• Forward/aft and inboard/outboard tracking on pedestal
• Adjustable recline
• Seat restraint system including seat belt and retracting
shoulder harness with inertial reel
• Single retractable inboard armrest
• Adjustable headrest
• Overwater life vest stored in seat base
each pedestal seat location
12. LH aft cabin divider with high gloss paint on the
forward side
13. RH aft removable curtain
14. LH aft, belted, flushing toilet
•
•
•
•
Seat restraint
Toilet tissue storage area
Relief tube with overboard drain
Overwater life vest
15. RH aft carpet covered avionics lowboy cabinet,
houses diagnostics and common PC boards
Not Shown:
• Two 110 volt AC outlets behind seats 5 and 6 with 5 amp
maximum per outlet
• Cabin overhead containing oxygen mask, air outlet,
and LED reading light at each passenger seat loca
tion and in the aft lavatory area
• Manual pleated cabin window shades (exposed)
• Indirect overhead LED lighting
• High gloss paint cabinetry finish
• Brushed aluminum hardware finish
• Foldable threshold carpet assembly
• Spare threshold carpet assembly
• Spare center aisle carpet assembly
• Center aft coat rod
• Chime unit
• Fasten seat belt/no smoking and emergency exit signs
(Note: The no smoking sign remains illuminated at all times
unless the optional smoking configuration is ordered.)
• One insertable ashtray
• Fireblocking on all passenger seats
11.3 Baggage
Two separate unpressurized baggage areas provide a
total volume of 45.2 cubic feet (1.28 m3) and a total
weight capacity of 725 pounds (329 kg).
• An LED illuminated 15.0 cubic foot (.42 m3), 400
pound (182 kg) capacity lockable nose baggage
compartment is externally accessible from either side
of the aircraft.
• An LED illuminated 30.2 cubic foot (.86 m3), 325
pound (147 kg) capacity baggage compartment is
located in the tailcone and is externally accessible
through a 20 x 26 inch (.51 x .66 m) lockable door on
the left side beneath the engine pylon.
10. LH/RH executive tables with leather table top inserts
11. LH/RH sideledge with cupholder/storage area at
17
August 2011, Preliminary
12. EXTERIOR
Distinctive exterior styling featuring polyurethane paint in a variety of colors is provided.
13. ADDITIONAL EQUIPMENT
• Two Active Noise Reduction Headsets
• Tailcone Baggage Restraint Strap
• Pitot Covers
• Static Discharge Wick Covers
• Inlet Covers for Engine, Exhaust, Generator, and Pylon
• Tow Straps
• Jack Pad Adapter (nose)
• Emergency Escape Hatch Ground-Locking Pin
14. EMERGENCY EQUIPMENT
•
•
•
•
•
Fire Extinguisher in Cockpit
Individual Overwater Life Vest For Each Seat
Crew and Passenger Oxygen
Exterior LED Emergency Exit Lighting
Emergency Lighting Battery Pack
1 5 . D O C U M E N T AT I O N A N D T E C H N I C A L P U B L I C AT I O N S
•• U.S. Standard Airworthiness Certificate, FAA8100-2;
Export Certificate of Airworthiness, FAA8130-4 or Special
Airworthiness Certificate FAA8130-7 as appropriate
• Airplane Flight Manual
• Pilot's Operating Manual
• Abbreviated Procedures Checklist
• Weight and Balance Report
• Weight and Balance calculator software *
• Citation Performance Calculator (CPC) pending availability
• Cabin Operating Manual
• Passenger Information Cards
• Log Books (Aircraft and Engines)
• Service Bulletins and Service Letters - Engine **
• Maintenance related documents such as Maintenance
Manuals, Illustrated Parts Catalogs, and Wiring Diagrams
for the airframe, interior, avionics, and/or engines *
Cessna will provide Service Bulletins, Service Letters
and manual revisions for documents published by
Cessna for three years beginning from the start date of
airframe warranty.
* These documents are provided on CD-ROM or DVD.
** These publications / revisions are provided by the supplier following delivery.
18
August 2011, Preliminary
16. COMPUTERIZED MAINTENANCE RECORD SERVICE (CESCOM)
Cessna, through the exclusive endorsement of CAMP
Systems International, will provide an online computerized maintenance record service for one (1) full year
from the date of delivery of a Citation M2 to the
Purchaser. This service will provide management and
operations personnel with the reports necessary for the
efficient control of maintenance activities. The service
provides an accurate and simple method of keeping up
with aircraft components, inspections, service bulletins
and airworthiness directives while providing permanent
aircraft records of maintenance performed.
application, show the current status, upcoming scheduled maintenance activity and the history of the aircraft
maintenance which is printable locally. Reports concerning projected annual maintenance requirements, component removal history and fleet-wide component reliability are provided as part of the service.
Services are provided through a secure Internet Site
requiring a computer with Internet connectivity. A local
printer is required to print paper versions of the online
reports and documentation.
Reports, available through an Internet hosted software
17. LIMITED WARRANTIES
The standard Citation M2 Aircraft Limited Warranty
which covers the aircraft, other than Williams engines
and associated engine accessories which are warranted
separately is set forth below. Cessna specifically
excludes vendor subscription services and the availability of vendor service providers for Optional and
Customer Requested Equipment (CRQ) from Cessna's
Limited Aircraft Warranty. Following Cessna's Limited
Warranty, the engine and engine accessory warranty of
Williams is set forth. Both warranties are incorporated by
reference and made part of the Purchase Agreement. All
warranties are administered by Cessna's Citation
Warranty Department.
17.1 Cessna Citation M2 Limited Warranty
(Limited Warranty)
Cessna Aircraft Company (Cessna) expressly warrants
each new Citation M2 Aircraft (exclusive of engines and
engine accessories supplied by Williams which are covered by their separate warranty), including factoryinstalled avionics and other factory-installed optional
equipment to be free from defects in material and workmanship under normal use and service, except as set
forth herein, to the first user for the following periods
after delivery:
(a) Five years or 5,000 operating hours, whichever occurs
first, for Aircraft components manufactured by Cessna;
(b) Five years or 5,000 operating hours, whichever occurs
first, for Garmin Standard Avionics;
(c) Two years for all other Standard Avionics;
(d) Two years for all Optional Avionics
(e) One year for Actuators, ACMs, Brakes, GCUs, Oleos,
Starter Generators, Valves, Windshields, and Vendor items
including engine accessories supplied by Cessna unless
otherwise stated in the Optional Equipment and Selection
Guide;
(f) One year for Customer Requests (CRQs), Interior
Components, Interior Furnishings, and Paint;
Any remaining term of this Limited Warranty is automatically transferred to subsequent purchasers of the aircraft.
Cessna's obligation under this Limited Warranty is limited to repairing or replacing, in Cessna's sole discretion,
any part or parts which: (1) within the applicable warranty period and 120 days of failure, (2) are returned at the
owner's expense to the facility, where the replacement
part is procured, whether Citation Parts Distribution or a
Cessna-owned Citation service facility or a Citation service facility authorized by Cessna to perform service on
the aircraft (collectively "Support Facility"), (3) are
accompanied by a completed claim form containing the
following information: aircraft model, aircraft serial number, customer number, failed part number and serial
number if applicable, failure date, sales order number,
purchased part number and serial number if applicable,
failure codes, and action codes, and (4) are found by
Cessna or its designee to be defective. Replacement
parts must be procured through a Support Facility and
are only warranted for the remainder of the applicable
original aircraft warranty period. A new warranty period is
not established for replacement parts. The repair or
replacement of defective parts under this Limited
Warranty will be made by any Cessna-owned Citation
19
August 2011, Preliminary
17. LIMITED WARRANTIES (Continued)
service facility or a Citation service facility authorized by
Cessna to perform service on the aircraft without charge
for parts and/or labor for removal, installation, and/or
repair. All expedited freight transportation expenses,
import duties, customs brokerage fees, sales taxes and
use taxes, if any, on such warranty repairs or replacement parts are the warranty recipient's sole responsibility. Cessna’s performance under this limited warranty
may be delayed or prohibited if export licenses are
required to be approved by the US Government before
specific spare parts can be shipped to Purchaser in
some foreign countries. (Location of Cessna-owned and
Cessna-authorized Citation service facilities will be furnished by Cessna upon request.)
This Limited Warranty applies to only items detailed herein which have been used, maintained, and operated in
accordance with Cessna and other applicable manuals,
bulletins, and other written instructions. However, this
Limited Warranty does not apply to items that have been
subjected to misuse, abuse, negligence, accident, or neglect; to items that have been installed, repaired, or altered
by repair facilities not authorized by Cessna; or to items
that, in the sole judgment of Cessna, have been installed,
repaired, or altered by other than Cessna-owned service
facilities contrary to applicable manuals, bulletins, and/or
other written instructions provided by Cessna so that the
performance, stability, or reliability of such items are
adversely affected. Limited Warranty does not apply to
normal maintenance services (such as engine adjustments, cleaning, control rigging, brake and other mechanical adjustments, and maintenance inspections); or to the
replacement of service items (such as brake linings,
lights, filters, de-ice boots, hoses, belts, tires, and rubberlike items); or to normal deterioration of appurtenances
(such as paint, cabinetry, and upholstery), corrosion or
structural components due to wear, exposure, and neglect.
WITH THE EXCEPTION OF THE WARRANTY OF
TITLE AND TO THE EXTENT ALLOWED BY APPLICABLE LAW, THIS LIMITED WARRANTY IS EXPRESSLY
IN LIEU OF ANY OTHER WARRANTIES, EXPRESSED
OR IMPLIED, IN FACT OR BY LAW, APPLICABLE TO
THE AIRCRAFT. CESSNA SPECIFICALLY DISCLAIMS
AND EXCLUDES ALL OTHER WARRANTIES,
INCLUDING, BUT NOT LIMITED TO, ANY IMPLIED
WARRANTY OF MERCHANTABILITY OR FITNESS
FOR A PARTICULAR PURPOSE. THE AFOREMENTIONED REMEDIES OF REPAIR OR REPLACEMENT
20
ARE THE ONLY REMEDIES UNDER THIS LIMITED
WARRANTY. CESSNA EXPRESSLY AND SPECIFICALLY DISCLAIMS ALL OTHER REMEDIES, OBLIGATIONS, AND LIABILITIES, INCLUDING, BUT NOT LIMITED TO, LOSS OF AIRCRAFT USE, LOSS OF TIME,
INCONVENIENCE, COMMERCIAL LOSS, LOSS OF
PROFITS, LOSS OF GOODWILL, AND ANY AND ALL
OTHER CONSEQUENTIAL AND INCIDENTAL DAMAGES. CESSNA NEITHER ASSUMES NOR AUTHORIZES ANYONE ELSE TO ASSUME ON ITS BEHALF
ANY FURTHER OBLIGATIONS OR LIABILITIES PERTAINING TO THE AIRCRAFT NOT CONTAINED IN
THIS LIMITED WARRANTY. THIS LIMITED WARRANTY SHALL BE CONSTRUED UNDER THE LAWS OF
THE STATE OF KANSAS AND ANY DISPUTES
AND/OR CLAIMS ARISING THEREFROM SHALL BE
EXCLUSIVELY RESOLVED IN THE STATE AND/OR
FEDERAL COURTS LOCATED IN WICHITA, KANSAS.
THE PARTIES HERETO CONSENT TO PERSONAL
JURISDICTION IN THE FORUM CHOSEN.
17.2 Williams’ FJ44 Limited Engine Warranty
TBD
August 2011, Preliminary
1 8 . C I T AT I O N M 2 C R E W T R A I N I N G A G R E E M E N T
Training for one (1) Citation M2 crew will be furnished to
First Retail Purchaser (hereinafter called the “Purchaser”),
subject to the following:
1. A crew shall consist of up to two (2) licensed pilots
with current private or commercial, instrument and multiengine ratings and a minimum of 1,000 hours total airplane pilot time and up to two (2) mechanics with A&P
licenses or equivalent experience.
2. Training shall be conducted by Cessna or by its designated training organization, at Cessna’s option.
a. A simulator shall be utilized which is FAA certified
to provide training for the CE-525 FAA type rating.
b. In lieu of a model specific simulator, training may
be provided in the most appropriate type simulator
available capable of accomplishing the FAA type rating, with differences training provided.
c. Additional training as requested by the customer,
shall be conducted in the customer’s aircraft.
d. Location of training to be Wichita, Kansas, or
unless mutually agreed otherwise. The organization
conducting the training is hereinafter called the
“Trainer.”
3. Training furnished shall consist of the following:
a. Flight training to flight proficiency in accordance with
Trainer's standards aimed toward type certification of
two (2) Captains under applicable Federal Air
Regulations not to exceed five (5) total hours for the
two (2) pilots.
b. Flight simulation training to simulator proficiency in
accordance with Trainer's standards but not to
exceed thirty (30) total hours for both pilots.
c. Ground School training for each pilot and classroom instruction for each mechanic in accordance
with Trainer's standards.
4. Purchaser shall be responsible for:
a. Transportation of crew to and from training site and
for living expenses during training.
b. Providing an interpreter during the course of training for any of Purchaser's crew not conversant with
the English language.
c. Payment to Trainer for additional simulator or flight
training beyond that required to attain proficiency in
accordance with Trainer's standards for the course in
which the pilot is enrolled.
d. All aircraft required for flight training as well as all
landing fees, fuel costs, aircraft maintenance and
insurance and all other direct costs of operation,
including applicable taxes required in connection with
the operation of said aircraft during such flight training.
e. Extra charges, if any, for scheduling pilots in separate training classes.
f. Reimbursing to Cessna the retail rate for training in
the event of training before actual sale/delivery, if
sale/delivery is cancelled.
5. Seller or Trainer shall schedule all training, furnish
Purchaser schedules of training and endeavor to schedule
training at a convenient time for Purchaser. A cancellation
fee of Two Hundred Dollars ($200) will be paid to Cessna
by Purchaser if crew fails to appear for scheduled training,
except for reasons beyond its reasonable control, unless
Purchaser gives Seller written notice of cancellation
received at Wichita, Kansas, at least seven (7) days prior
to scheduled training. In the event of such cancellation
Seller shall reschedule training for the next available class.
6. Neither Seller nor Trainer shall be responsible for the
competency of Purchaser's crew during and after training.
Trainer will make the same efforts to qualify Purchaser's
crew as it makes in training of other Citation M2 crews;
however, Seller and Trainer cannot guarantee Purchaser's
crew shall qualify for any license, certificate or rating.
7. Neither Seller nor Trainer shall be responsible for any
delay in providing training due to causes beyond its or
their reasonable control.
8. All Training furnished to Purchaser under the
Agreement will be scheduled to commence no earlier
than three (3) months prior to delivery and will be completed within twelve (12) months after delivery of the
Aircraft unless mutually agreed otherwise.
Signature of the Purchaser to the Purchase Agreement
to which this Training Agreement is attached as a part of
the Specification and Description shall constitute acceptance by Purchaser of the foregoing terms and conditions
relative to training to be furnished by Seller. Purchaser
agrees that Seller can provide Purchaser’s name and
address to the training organization for the purpose of
coordinating training.
21
Citation Marketing Cessna Aircraft Company, P.O. Box 7706, Wichita, Kansas 67277-7706, Telefax 316-517-6640
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