CITATION MUSTANG OPERATING MANUAL CHAPTER 1 …CITATION MUSTANG OPERATING MANUAL 510OM-00 1-9 Figure 1-12. Wing Trailing Edge Figure 1-13. Stall Strips Figure 1-14. Empennage Figure

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.

CITATION MUSTANG OPERATING MANUAL

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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

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

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

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

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

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,

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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Documents

CITATION MUSTANG OPERATING MANUAL CHAPTER 1 …CITATION MUSTANG OPERATING MANUAL 510OM-00 1-9 Figure 1-12. Wing Trailing Edge Figure 1-13. Stall Strips Figure 1-14. Empennage Figure