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INTRODUCTIONThis manual provides a description of the major
airframe and engine systems in the CessnaCitation 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 makeupof the airplane
and gives an overview of the systems.
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GENERALThe Citation Mustang is certified in accor-dance with
Title 14 of the Code of FederalRegulations (14CFR23) Part 23,
includingday, night, visual flight rules (VFR), instru-ment flight
rules (IFR), single pilot, and flightinto known icing conditions.
Takeoff and land-ing performance and other special conditioncert
ification requirements are similar to14CFR Part 25. The Mustang
meets 14CFR
Part 36 noise standards, and meets 14CFRPart 34 fuel venting and
exhaust emissionstandards. It combines systems simplicity withease
of access to reduce maintenance require-ments. Low takeoff and
landing speeds permitoperation at small airports. Medium bypass
tur-bofan engines contribute to overall operatingefficiency and
performance.
CHAPTER 1AIRCRAFT GENERAL
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The Citation Mustang is equipped with aGarmin G-1000 integrated
avionics system.This three-panel display system integrates
flightinstruments, flight guidance, navigation, andcommunication
systems. Also integrated intothe avionics system are the master
warning andmaster caution systems and hazard avoidancesystems. The
engine indication and crew alert-ing system (EICAS) is a two-column
display onthe left side of the center multifunction display(MFD).
The crew alerting system (CAS) mes-sages are displayed on the lower
left of theMFD to alert the crew of system emergencies,abnormal
situations, or changes in system op-eration. EICAS and CAS will be
referred tooften in the following chapters.
DIMENSIONSFigure 1-2 shows a three-view drawing of theCitation
Mustang containing the approximateexterior and cabin
dimensions.
WEIGHT LIMITATIONS• Maximum ramp
weight ............................... 8,730 pounds
• Maximum takeoff weight .............................. 8,645
pounds
• Maximum landing weight .............................. 8,000
pounds
STRUCTURESThe Citation Mustang (Figure 1-1) is an all-metal,
pressurized, low-wing monoplane witha swept T-tail. The interior
has provisions forup to four passengers and two crewmembers.It has
one cabin entry door and one emergencyexit. The aircraft has
baggage compartmentsin the nose and tail cone. Two
pylon-mountedPratt & Whitney PW615F turbofan enginesare on the
rear fuselage.
Figure 1-3 shows braking taxi turning dis-tance, and Figure 1-4
is a diagram of enginehazard 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 amonitoring system,
which provides a specificCAS message for that door if it is not
properlyclosed. However, if the monitoring system forthe cabin or
nose baggage doors fail to pass atest on the ground, stops
operating, or does notindicate normal operating condition, the
amberCHECK 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 CURB27.32 FEET
(8.33 M)
11.79 FEET(3.59 M)
15.53 FEET(4.734 M)
WING-TIP LIGHT TOWING TIP LIGHT
54.97 FEET(16.75 M)
Figure 1-3. Braking Taxi Turning Distance
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ENTRANCE DOORThe cabin entrance door is on the forward leftside
of the fuselage (Figure 1-5). The entrancedoor opens outboard and
forward. It is se-cured in the closed position with eight lock-ing
pins attached to a handle. The door can beopened 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 possibleingestion of the key into an engine.
An adjustable stop prevents the door fromopening too far. Once
the door is fully open,a hook locks the door into position. To
unlatchthe 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 thedoor move freely.
The locking pins will contact anddamage the painted surface of
thefuselage if an attempt is made to shutthe door with the handle
in the closed(up) position.
The seal system operates passively as the cabinis 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
waterfrom entering the aircraft, and enables the useof the entrance
door as an exit during ditching.
Water barrier must be raised andlatched into position prior to
ditching.
WARNING
CAUTION
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Figure 1-5. Entrance Door, Interior Handle, and Latch
Release
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NOTEThe water barrier is installed at themain cabin door
threshold. Crewmembers should be familiar with itslocation and
operation; and passen-gers should be briefed prior to flightsover
water.
A monitoring system checks for safe conditionof the door
(closed, pins secure, door latched).There are eight view ports on
the inside panelof the entry door to verify that the eight lock-ing
pins are in the closed position. With thedoor closed and handle
latched, the pilotshould 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 oftargets on the closing mechanism of the doorand signals
the condition to the CAS:
• The proximity switch on the doorwaysurround structure senses
the door afterit is closed.
• After the door is latched, a proximityswitch 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 senseits target, the
CABIN DOOR message appearson the CAS.
EMERGENCY EXITA plug-type emergency exit (escape hatch) ison the
aft right side of the cabin, above thewing. It opens inboard. The
emergency exitdoor can be opened from outside or insidethe airplane
(Figure 1-8).
The D-shaped inner door handle is recessed be-hind a magnetic
cover. The flush-mountedouter handle is located at the top of the
door.The outer handle is not directly connected tothe inner handle.
The outer handle has a greenindicator to show when the door is
latched.
Because no other provisions are provided forsecuring the escape
hatch when the airplaneis unattended, a safety pin with a
REMOVEBEFORE FLIGHT streamer is placed on theinside of the hatch.
The pilot must ensure thispin is removed prior to flight. The
emergencyexit hatch is not connected to the door warn-ing
circuit.
CABINThe cabin extends from the forward pressurebulkhead to the
aft pressure bulkhead and
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Figure 1-7. Door Pin Indicator
Figure 1-6. Hinged Panel
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measures approximately 14 feet in length, 4.7feet in width, and
4.5 feet in height. Figure 1-9 shows the interior arrangements.
Refer toFigure 1-10 for interior dimensions.
The standard interior arrangement consists oftwo aft-facing and
two forward-facing passen-ger seats. There is a toilet on the right
side ofthe fuselage, abeam the cabin entry door. Thetoilet is not
equipped with a safety belt and can-not be occupied during taxi,
takeoff, or landing.
The cabin area has dropout, constant-flowoxygen masks for
emergency use.
The cabin overhead panels contain individualair vent outlets and
seat lighting for passen-ger comfort.
FLIGHT COMPARTMENTThe airplane is equipped with dual controls,
in-cluding control yokes, brakes, and rudder ped-als at each crew
seat. There are two adjustableseats with seat belts and shoulder
harnesses.
TAIL CONE COMPARTMENTThe tail cone compartment is an
unpressurizedarea 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 onthe left side of the fuselage below the engine.
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EXTERIOR
INTERIORFigure 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)
FS144.00 IN.
(3,658 MM)
FS321.00 IN.
(8,153 MM)
FS202.76 IN.
(5,150 MM)
A
A
FORWARDPRESSUREBULKHEAD
FORWARDDIVIDER
(0.53 IN. THICK)(13 MM THICK)
AFT PRESSUREBULKHEAD
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
PASSENGERCOMPARTMENT
FLIGHTCOMPARTMENT
Figure 1-10. Interior Dimensions
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This door opens the tail cone baggage compart-ment (Figure
1-11), which holds 300 pounds.
The tail cone compartment door is secured atthe aft side by
mechanical latches and a keylock and is hinged at the left forward
edge. Thedoor is secured by a key lock, which is mon-itored by the
CAS. An amber AFT 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 providesillumination of the tail cone area
for preflightinspection purposes. If the manual switch isleft on, a
microswitch in the door track extin-guishes the light when the door
is closed.
WINGThe wing assembly attaches to the bottom of thefuselage and
is constructed of aluminum. Eachwing is also a fuel tank.
Electromechanicalspeedbrakes and flaps, and hydraulically actu-ated
main landing gear are attached to eachwing (Figure 1-12).
An aileron fence is attached to the inboard sideof each
aileron.
The wing leading edges are deiced by inflat-able deice boots,
which are inflated by regu-lated engine bleed-air. Vortex
generators andstall strips are attached to the leading edgeboots
(Figure 1-13).
EMPENNAGEThe empennage consists of a vertical stabilizerwith
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
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NOSE SECTIONThe nose section is an unpressurized storagearea.
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 storagecompartment holds up to 20-cubic
feet (320-pounds) of baggage. It has two swing-up doors(left and
right). Each door has a mechanicallock. Each door has a
key-operated cam lock,forward pin latch, and two independent
pad-dle latches. The pin latch shows orange whennot latched. Each
latch has a switch and in-dicates the latch position with the
amberNOSE DOOR L-R CAS message.
A manual light switch is in the compartment(Figure 1-16). If the
manual light switch is lefton, a microswitch at the left and right
storagedoor assembly extinguishes the storage com-partment light
when the doors are closed.
An over-center gas spring on each door holdsthe door in the full
open position until thedoor is closed manually.
Ensure that the keys are removed from bothnose compartment doors
prior to flight to pre-vent possible ingestion of a key into an
engine.
SYSTEMS
ELECTRICAL SYSTEMThe Mustang is an all-DC aircraft. The 28-VDC
electrical power is supplied by twostarter-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 theright engine pylon.
For convenience of pilot and passengers, twoDC power outlets are
provided in the cabin,powered by the DC system through a
con-verter. One DC outlet is in the cabinet behindthe copilot seat
and the other is in the aft cen-ter console.
FUEL SYSTEMThe fuel system has two distinct, identicalhalves.
Each wing tank stores and supplies thefuel to its respective
engine. Fuel transfercapability is provided. Fuel is heated
throughan oil-to-fuel heat exchanger (PRIST is notrequired).
ENGINESTwo pylon-mounted Pratt & Whitney PW615Fturbofan
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 poundsof 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 onboardbattery 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 andexhausts to provide cooling airflow through thecabin air
heat exchangers.
ICE PROTECTION SYSTEMAnti-ice protection is provided to the
engine in-lets, and deice protection is provided to thewings, 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
windshieldsare electrically anti-iced and defogged. Electricheat
also anti-ices the pitot-static systems, stall-warning vane, and
engine inlet-mounted T2sensors. Ice detection lights on the
glareshieldhelp the pilot detect icing on the windshield.A light on
the outside left fuselage helps thepilot detect icing on the
wings.
HYDRAULIC SYSTEMA single electrically driven hydraulic
pumpsupplies pressure for operation of the landinggear and wheel
brakes through a closed centersystem. The main gear are equipped
with hy-draulically operated antiskid-controlled wheelbrakes.
Pneumatic backup is available for emer-gency landing gear extension
and braking.
FLIGHT CONTROLSPrimary flight control is accomplished
throughconventional cable-operated surfaces. Anaileron-rudder
interconnect provides improvedlateral stability. Trimming is
provided by
aileron, elevator, and rudder tabs. The eleva-tor trim is both
mechanically and electricallyactuated. Aileron and rudder trim are
electri-cally activated. The flaps are electrically ac-tuated and
are on the trailing edges of thewing. Electrically powered
speedbrakes are onthe upper and lower wing surfaces.
Nosewheelsteering is mechanically controlled by the rud-der pedals
through steering bungees.
ENVIRONMENTAL SYSTEMThe aircraft has a two-zone automatic
temper-ature control system that is split into cabin andcockpit. An
independent vapor cycle air-con-ditioning system provides cooling
to the cabinand cockpit.
Conditioned engine bleed air is used for cabinpressurization and
temperature control. Cabinpressurization is controlled by an
autosched-uling pressurization system. The crew needonly to adjust
destination elevation any timeprior to or during flight and the
controller au-tomatically controls cabin pressure for oper-ation at
the highest practical differentialpressure with minimum rates and
changes.
A 22-cubic-foot oxygen bottle (40-cubic-footoptional) supplies
oxygen to the quick-donningmasks for the crew and automatic
dropoutmasks for each passenger. If cabin altitudebecomes
excessive, passenger oxygen masksdeploy automatically (by
electrical release)and can be deployed manually (by oxygenpressure)
upon pilot command.
AVIONICSThe 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,
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and navigation systems. The navigation sys-tem includes GPS,
ground-based navigation,and is WAAS-capable. An integrated
engineindicating and crew alerting system (EICAS)is included. The
Garmin G1000 system man-ages the instrument and engine displays,
theautopilot, flight guidance systems, and theflight director.
Terrain and traffic avoidancesystems and color radar are standard
equip-ment. Data link weather capability is availablewith
subscription.
PUBLICATIONSThe 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, andweight
and balance data. Information inthe AFM always takes precedence
overany other publication.
• FAA-approved Ci ta t ion Mus tangAbbrev ia t ed Check l i s
t—NormalProcedures contains abbreviated normaloperating procedures
and abbreviatedperformance data. If any doubt exists orif the
conditions are not covered by thechecklist, the AFM must be
consulted.
• FAA-app roved Ci ta t i on Mus tangAbbreviated
Checklist—Emergency/Abnormal Procedures contains emer-gency and
abnormal procedures. If anydoubt exists or if the conditions are
notcovered by the checklist, the AFM mustbe consulted.
• Garmin G1000 Cockpit Reference Guidefor the Citation
Mustang
Other publications that are not required to bein the aircraft
include:
• Operating Manual
• Garmin G1000 Pilot’s Guide for theCessna Citation Mustang
• FAA-approved Weight and BalanceManual
SINGLE-PILOT OPERATIONThe following are required when the
airplaneis 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 Pi lo t s ’ Abbrev ia tedNormal Procedures
Checklist (as revised)
4. FAA-approved Pi lo t s ’ Abbrev ia tedEmergency and Abnormal
ProceduresChecklist (as revised)
5. Provisions for storage and retention ofnavigation charts,
accessible to the pilotfrom the pilot station
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