Cessna CITATION MUSTANG User 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 sub-
stitute for, any of the manufacturer’s maintenance or flight manuals. The material pre-
sented 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 accor-
dance with Title 14 of the Code of Federal
Regulations (14CFR23) Part 23, including
day, night, visual flight rules (VFR), instru-
ment flight rules (IFR), single pilot, and flight
into known icing conditions. Takeoff and land-
ing 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 require-
ments. Low takeoff and landing speeds permit
operation at small airports. Medium bypass tur-
bofan 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 alert-
ing system (EICAS) is a two-column display on
the left side of the center multifunction display
(MFD). The crew alerting system (CAS) mes-
sages are displayed on the lower left of the
MFD to alert the crew of system emergencies,
abnormal situations, or changes in system op-
eration. 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 all-
metal, 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 dis-
tance, 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)
11.79 FT (3.6 M)
14.35 FT (4.37 M)
40.56 FT (12.36 M)
13.10 FT
(3.99 M)
Figure 1-2. Exterior Three-View Drawing

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18 FEET
(5.50 M)
27 FEET
(8 M)
0 30 60 90 120 150
0 9 18 27 36 45
DISTANCE FEET
DISTANCE METERS
Figure 1-4. Engine Hazard Areas
CURB TO CURB
27.32 FEET
(8.33 M)
11.79 FEET
(3.59 M)
15.53 FEET
(4.734 M)
WING-TIP LIGHT TO
WING TIP LIGHT
54.97 FEET
(16.75 M)
Figure 1-3. Braking Taxi Turning Distance

ENTRANCE DOOR
The cabin entrance door is on the forward left
side of the fuselage (Figure 1-5). The entrance
door opens outboard and forward. It is se-
cured in the closed position with eight lock-
ing pins attached to a handle. The door can be
opened from inside or outside of the airplane.
The exterior handle can be secured with a key.
Ensure that the key is removed from the en-
trance door prior to flight to prevent possible
ingestion of the key into an engine.
An adjustable stop prevents the door from
opening too far. Once the door is fully open,
a hook locks the door into position. To unlatch
the hook and let the door close, a release but-
ton inside the cabin (inside left of door open-
ing) must be pushed (Figure 1-5). This lets the
door move freely.
The locking pins will contact and
damage the painted surface of the
fuselage if an attempt is made to shut
the door with the handle in the closed
(up) position.
The seal system operates passively as the cabin
is pressurized. The seal engages and disen-
gages when the door opens and closes.
A hinged panel at the main cabin door thresh-
old is used as a water barrier during ditching
(Figure 1-6). It hinges up to prevent water
from entering the aircraft, and enables the use
of the entrance door as an exit during ditching.
Water barrier must be raised and
latched into position prior to ditching.
WARNING
CAUTION
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Figure 1-5. Entrance Door, Interior Handle, and Latch Release

NOTE
The water barrier is installed at the
main cabin door threshold. Crew
members should be familiar with its
location and operation; and passen-
gers should be briefed prior to flights
over water.
A monitoring system checks for safe condition
of the door (closed, pins secure, door latched).
There are eight view ports on the inside panel
of the entry door to verify that the eight lock-
ing pins are in the closed position. With the
door closed and handle latched, the pilot
should be able to see the white and green in-
dicators in each port. (Figure 1-7). Three prox-
imity switches verify that the door is closed,
latched, and locked by sensing the position of
targets on the closing mechanism of the door
and signals the condition to the CAS:
• The proximity switch on the doorway
surround structure senses the door after
it is closed.
• After the door is latched, a proximity
switch senses the door pin position.
• As the handle catch is engaged, a prox-
imity switch on the inner handle assem-
bly senses a flag.
If one of the proximity switches does not sense
its target, the CABIN DOOR message appears
on the CAS.
EMERGENCY EXIT
A plug-type emergency exit (escape hatch) is
on the aft right side of the cabin, above the
wing. It opens inboard. The emergency exit
door can be opened from outside or inside
the airplane (Figure 1-8).
The D-shaped inner door handle is recessed be-
hind a magnetic cover. The flush-mounted
outer handle is located at the top of the door.
The outer handle is not directly connected to
the inner handle. The outer handle has a green
indicator to show when the door is latched.
Because no other provisions are provided for
securing the escape hatch when the airplane
is unattended, a safety pin with a REMOVE
BEFORE FLIGHT streamer is placed on the
inside of the hatch. The pilot must ensure this
pin is removed prior to flight. The emergency
exit hatch is not connected to the door warn-
ing circuit.
CABIN
The cabin extends from the forward pressure
bulkhead to the aft pressure bulkhead and
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Figure 1-7. Door Pin Indicator
Figure 1-6. Hinged Panel

measures approximately 14 feet in length, 4.7
feet in width, and 4.5 feet in height. Figure 1-
9 shows the interior arrangements. Refer to
Figure 1-10 for interior dimensions.
The standard interior arrangement consists of
two aft-facing and two forward-facing passen-
ger seats. There is a toilet on the right side of
the fuselage, abeam the cabin entry door. The
toilet is not equipped with a safety belt and can-
not be occupied during taxi, takeoff, or landing.
The cabin area has dropout, constant-flow
oxygen masks for emergency use.
The cabin overhead panels contain individual
air vent outlets and seat lighting for passen-
ger comfort.
FLIGHT COMPARTMENT
The airplane is equipped with dual controls, in-
cluding control yokes, brakes, and rudder ped-
als at each crew seat. There are two adjustable
seats with seat belts and shoulder harnesses.
TAIL CONE COMPARTMENT
The tail cone compartment is an unpressurized
area and contains major components of the en-
vironmental, electrical distribution, flight con-
trols, and engine fire extinguishing systems.
Access is through the tail cone baggage door on
the left side of the fuselage below the engine.
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EXTERIOR
INTERIOR
Figure 1-8. Emergency Exit
Figure 1-9. Interior Arrangements

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34.24 IN.
(870 MM)
55.00 IN.
(1,397 MM)
54.00 IN.
(1,372 MM)
FS
144.00 IN.
(3,658 MM)
FS
321.00 IN.
(8,153 MM)
FS
202.76 IN.
(5,150 MM)
A
A
FORWARD
PRESSURE
BULKHEAD
FORWARD
DIVIDER
(0.53 IN. THICK)
(13 MM THICK)
AFT PRESSURE
BULKHEAD
24.00 IN.
(610 MM)
46.00 IN.
(1,168 MM)
54.00 IN.
(1,372 MM)
117.71 IN.
(2,990 MM)
58.76 IN.
(1,493 MM)
VIEW A-A
PASSENGER
COMPARTMENT
FLIGHT
COMPARTMENT
Figure 1-10. Interior Dimensions

This door opens the tail cone baggage compart-
ment (Figure 1-11), which holds 300 pounds.
The tail cone compartment door is secured at
the aft side by mechanical latches and a key
lock and is hinged at the left forward edge. The
door is secured by a key lock, which is mon-
itored by the CAS.An amberAFT DOOR mes-
sage appears if the door is unlocked.
A light switch on the right side of the door open-
ing is powered from the battery bus and provides
illumination of the tail cone area for preflight
inspection purposes. If the manual switch is
left on, a microswitch in the door track extin-
guishes the light when the door is closed.
WING
The wing assembly attaches to the bottom of the
fuselage and is constructed of aluminum. Each
wing is also a fuel tank. Electromechanical
speedbrakes and flaps, and hydraulically actu-
ated main landing gear are attached to each
wing (Figure 1-12).
An aileron fence is attached to the inboard side
of each aileron.
The wing leading edges are deiced by inflat-
able deice boots, which are inflated by regu-
lated engine bleed-air. Vortex generators and
stall strips are attached to the leading edge
boots (Figure 1-13).
EMPENNAGE
The empennage consists of a vertical stabilizer
with T-tail mounted horizontal stabilizers
(Figure 1-14). The leading edges of the hori-
zontal and vertical stabilizers are deiced by in-
flatable deice boots.
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Figure 1-12. Wing Trailing Edge
Figure 1-13. Stall Strips
Figure 1-14. Empennage
Figure 1-11. Tail Cone Baggage Door

NOSE SECTION
The nose section is an unpressurized storage
area. Various hydraulics components, pneu-
matic bottles, oxygen bottle, fresh-air duct,
and radar antenna are located in this com-
partment (Figure 1-15). The nose storage
compartment holds up to 20-cubic feet (320-
pounds) of baggage. It has two swing-up doors
(left and right). Each door has a mechanical
lock. Each door has a key-operated cam lock,
forward pin latch, and two independent pad-
dle latches. The pin latch shows orange when
not latched. Each latch has a switch and in-
dicates the latch position with the amber
NOSE DOOR L-R CAS message.
A manual light switch is in the compartment
(Figure 1-16). If the manual light switch is left
on, a microswitch at the left and right storage
door assembly extinguishes the storage com-
partment light when the doors are closed.
An over-center gas spring on each door holds
the door in the full open position until the
door is closed manually.
Ensure that the keys are removed from both
nose compartment doors prior to flight to pre-
vent possible ingestion of a key into an engine.
SYSTEMS
ELECTRICAL SYSTEM
The Mustang is an all-DC aircraft. The 28-
VDC electrical power is supplied by two
starter-generators and one 24-volt, 28 amp-
hour sealed lead acid battery.An optional bat-
tery is a 24-volt, 28 amp-hour NiCad battery.
An external power receptacle is below the
right engine pylon.
For convenience of pilot and passengers, two
DC power outlets are provided in the cabin,
powered by the DC system through a con-
verter. One DC outlet is in the cabinet behind
the copilot seat and the other is in the aft cen-
ter console.
FUEL SYSTEM
The fuel system has two distinct, identical
halves. Each wing tank stores and supplies the
fuel to its respective engine. Fuel transfer
capability is provided. Fuel is heated through
an oil-to-fuel heat exchanger (PRIST is not
required).
ENGINES
Two pylon-mounted Pratt & Whitney PW615F
turbofan engines are on the rear fuselage, and
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Figure 1-16. Nose Baggage Light
Figure 1-15. Nose Storage Compartment

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each produces approximately 1,460 pounds
of thrust (sea level ISA + 10°C).
To improve automation and efficiency, the en-
gines are controlled by dual-channel full au-
thority digital engine controls (FADECs).
Engines are started with electrical starter-gen-
erators, which are powered by the onboard
battery or a ground power unit (GPU).
Ice-protection, fire-detection, and fire-extin-
guishing systems are provided for each en-
gine. The engine pylons have ram-air inlets and
exhausts to provide cooling airflow through the
cabin air heat exchangers.
ICE PROTECTION SYSTEM
Anti-ice protection is provided to the engine in-
lets, and deice protection is provided to the
wings, and empennage by engine bleed air.
Engine bleed air directly heats the engine in-
lets and generator cooling inlets. The wings,
vertical tail, and horizontal stabilizers are de-
iced by boots inflated by engine bleed air reg-
ulated to 20 psig (service air). The windshields
are electrically anti-iced and defogged. Electric
heat also anti-ices the pitot-static systems, stall-
warning vane, and engine inlet-mounted T2
sensors. Ice detection lights on the glareshield
help the pilot detect icing on the windshield.
A light on the outside left fuselage helps the
pilot detect icing on the wings.
HYDRAULIC SYSTEM
A single electrically driven hydraulic pump
supplies pressure for operation of the landing
gear and wheel brakes through a closed center
system. The main gear are equipped with hy-
draulically operated antiskid-controlled wheel
brakes. Pneumatic backup is available for emer-
gency landing gear extension and braking.
FLIGHT CONTROLS
Primary flight control is accomplished through
conventional cable-operated surfaces. An
aileron-rudder interconnect provides improved
lateral stability. Trimming is provided by
aileron, elevator, and rudder tabs. The eleva-
tor trim is both mechanically and electrically
actuated. Aileron and rudder trim are electri-
cally activated. The flaps are electrically ac-
tuated and are on the trailing edges of the
wing. Electrically powered speedbrakes are on
the upper and lower wing surfaces. Nosewheel
steering is mechanically controlled by the rud-
der pedals through steering bungees.
ENVIRONMENTAL SYSTEM
The aircraft has a two-zone automatic temper-
ature control system that is split into cabin and
cockpit. An independent vapor cycle air-con-
ditioning system provides cooling to the cabin
and cockpit.
Conditioned engine bleed air is used for cabin
pressurization and temperature control. Cabin
pressurization is controlled by an autosched-
uling pressurization system. The crew need
only to adjust destination elevation any time
prior to or during flight and the controller au-
tomatically controls cabin pressure for oper-
ation at the highest practical differential
pressure with minimum rates and changes.
A 22-cubic-foot oxygen bottle (40-cubic-foot
optional) supplies oxygen to the quick-donning
masks for the crew and automatic dropout
masks for each passenger. If cabin altitude
becomes excessive, passenger oxygen masks
deploy automatically (by electrical release)
and can be deployed manually (by oxygen
pressure) upon pilot command.
AVIONICS
The Mustang uses a Garmin G1000 three-dis-
play “glass cockpit” to present most indica-
tions for flight instrumentation, navigation,
avionics, and aircraft systems. The displays in-
clude two 10.4-inch primary flight displays
(for pilot and copilot) and a 15-inch multifunc-
tion display.
The standard factory-installed avionics pack-
age includes the fully integrated flight in-
struments, flight guidance, communications,

and navigation systems. The navigation sys-
tem includes GPS, ground-based navigation,
and is WAAS-capable. An integrated engine
indicating and crew alerting system (EICAS)
is included. The Garmin G1000 system man-
ages the instrument and engine displays, the
autopilot, flight guidance systems, and the
flight director. Terrain and traffic avoidance
systems and color radar are standard equip-
ment. Data link weather capability is available
with subscription.
PUBLICATIONS
The following publications must be immedi-
ately available to the flight crew:
• FAA-approved Airplane Flight Manual
(AFM) contains the limitations, data per-
tinent to takeoffs and landings, and
weight and balance data. Information in
the AFM always takes precedence over
any other publication.
• FAA-approved Citation Mustang
Abbreviated Checklist—Normal
Procedures contains abbreviated normal
operating procedures and abbreviated
performance data. If any doubt exists or
if the conditions are not covered by the
checklist, the AFM must be consulted.
• FAA-approved Citation Mustang
Abbreviated Checklist—Emergency/
Abnormal Procedures contains emer-
gency and abnormal procedures. If any
doubt exists or if the conditions are not
covered by the checklist, the AFM must
be consulted.
•Garmin G1000 Cockpit Reference Guide
for the Citation Mustang
Other publications that are not required to be
in the aircraft include:
•Operating Manual
•Garmin G1000 Pilot’s Guide for the
Cessna Citation Mustang
• FAA-approved Weight and Balance
Manual
SINGLE-PILOT
OPERATION
The following are required when the airplane
is operated with a crew of one pilot, per ap-
plicable operating rules:
1. Operable GFC-700 Autopilot
2. Headset with microphone (must be worn)
3. FAA-approved Pilots’ Abbreviated
Normal Procedures Checklist (as revised)
4. FAA-approved Pilots’ Abbreviated
Emergency and Abnormal Procedures
Checklist (as revised)
5. Provisions for storage and retention of
navigation charts, accessible to the pilot
from the pilot station
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