Cessna CITATION MUSTANG Operating Manual
INTRODUCTION
This manual provides a description of the major airframe and engine systems in the Cessna
Citation Mustang (Figure 1-1). This material does not supersede, nor is it meant to substitute for, any of the manufacturer’s maintenance or flight manuals. The material presented has been prepared from current design data. Chapter 1 covers the structural makeup
of the airplane and gives an overview of the systems.
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GENERAL
The Citation Mustang is certified in accordance with Title 14 of the Code of Federal
Regulations (14CFR23) Part 23, including
day, night, visual flight rules (VFR), instrument flight rules (IFR), single pilot, and flight
into known icing conditions. Takeoff and landing performance and other special condition
certification requirements are similar to
14CFR Part 25. The Mustang meets 14CFR
Part 36 noise standards, and meets 14CFR
Part 34 fuel venting and exhaust emission
standards. It combines systems simplicity with
ease of access to reduce maintenance requirements. Low takeoff and landing speeds permit
operation at small airports. Medium bypass turbofan engines contribute to overall operating
efficiency and performance.
CHAPTER 1
AIRCRAFT GENERAL
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The Citation Mustang is equipped with a
Garmin G-1000 integrated avionics system.
This three-panel display system integrates flight
instruments, flight guidance, navigation, and
communication systems. Also integrated into
the avionics system are the master warning and
master caution systems and hazard avoidance
systems. The engine indication and crew alerting system (EICAS) is a two-column display on
the left side of the center multifunction display
(MFD). The crew alerting system (CAS) messages are displayed on the lower left of the
MFD to alert the crew of system emergencies,
abnormal situations, or changes in system operation. EICAS and CAS will be referred to
often in the following chapters.
DIMENSIONS
Figure 1-2 shows a three-view drawing of the
Citation Mustang containing the approximate
exterior and cabin dimensions.
WEIGHT LIMITATIONS
• Maximum ramp
weight ............................... 8,730 pounds
• Maximum takeoff
weight.............................. 8,645 pounds
• Maximum landing
weight.............................. 8,000 pounds
STRUCTURES
The Citation Mustang (Figure 1-1) is an allmetal, pressurized, low-wing monoplane with
a swept T-tail. The interior has provisions for
up to four passengers and two crewmembers.
It has one cabin entry door and one emergency
exit. The aircraft has baggage compartments
in the nose and tail cone. Two pylon-mounted
Pratt & Whitney PW615F turbofan engines
are on the rear fuselage.
Figure 1-3 shows braking taxi turning distance, and Figure 1-4 is a diagram of engine
hazard areas.
The aircraft has five doors:
• Entrance door
• Emergency exit (escape hatch)
• Left nose baggage compartment door
• Right nose baggage compartment door
• Aft (tail cone) compartment door
Each door (except the emergency exit) has a
monitoring system, which provides a specific
CAS message for that door if it is not properly
closed. However, if the monitoring system for
the cabin or nose baggage doors fail to pass a
test on the ground, stops operating, or does not
indicate normal operating condition, the amber
CHECK DOORS message appears.
Figure 1-1. Cessna Citation Mustang
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43.17 FT (13.0 M)
Figure 1-2. Exterior Three-View Drawing
11.79 FT (3.6 M)
13.10 FT
(3.99 M)
14.35 FT (4.37 M)
40.56 FT (12.36 M)
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Figure 1-4. Engine Hazard Areas
WING-TIP LIGHT TO
Figure 1-3. Braking Taxi Turning Distance
WING TIP LIGHT
54.97 FEET
(16.75 M)
18 FEET
(5.50 M)
CURB TO CURB
27.32 FEET
(8.33 M)
11.79 FEET
(3.59 M)
15.53 FEET
(4.734 M)
27 FEET
(8 M)
DISTANCE METERS
0 9 18 27 36 45
DISTANCE FEET
0 30 60 90 120 150
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