CAE SimuFlite Citation Bravo Installation guide

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Pilot Training Manual
Pilot Training Manual
Citation Bravo
Citation XLS
Revision 2
Revision 0

Printed in the United States of America.
Excerpted Materials used in this Publication
have been reproduced with permission of
the Cessna Aircraft Company.
Copyright 2013, CAE, Inc.
All Rights Reserved
NOTICE: This Citation Bravo Initial Pilot Training Manual is
to be used for Aircraft familiarization and training purposes
only. It is not to be used as, nor considered a substitute for,
the manufacturer’s Pilot or Maintenance Manual.

Introduction
Citation Bravo Developed for Training Purposes 1-1
March 2009
Welcome to
CAE
SimuFlite
Welcome to CAE SimuFlite!
Our goal is a basic one: to enhance your safety, proficiency and
professionalism within the aviation community. All of us at
CAE SimuFlite know that the success of our company depends
upon our commitment to your needs. We strive for excellence
by focusing on our service to you.
We urge you to participate actively in all training activities.
Through your involvement, interaction, and practice, the full
value of your training will be transferred to the operational
environment. As you apply the techniques presented through
CAE SimuFlite training, they will become “second nature” to
you.
Thank you for choosing CAE SimuFlite. We recognize that
you have a choice of training sources. We trust you will find us
committed to providing responsive, service-oriented training
of the highest quality.
Our best wishes are with you for a most successful and
rewarding training experience.
The Staff of CAE SimuFlite

1-2 Developed for Training Purposes Citation Bravo
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CAE SimuFlite

Introduction
Citation Bravo Developed for Training Purposes 1-3
March 2009
Using this
Manual
This manual is a stand-alone document appropriate for various
levels of training. Its purpose is to serve as an informational
resource and study aid.
The Quick Reference chapter provides limitations and other data
for quick review.
The Operating Procedures section contains chapters that pro-
vide a pictorial preflight inspection of the aircraft, normal proce-
dures in an expanded format, standard operating procedures,
maneuvers, and other information for day-to-day operations.
The Flight Planning chapter covers weight and balance and per-
formance; a sample problem is included.
The Systems section is subdivided by aircraft system. Each sys-
tem chapter contains a discussion of components, preflight and
servicing procedures, and abnormal and emergency procedures.
At the beginning of the Systems section, a list of systems is cross-
referenced to ATA codes to facilitate further self-study, if desired,
with the manufacturer’s manuals.
The graphics (right) in this manual direct your attention to a spe-
cific location in the cockpit. A shaded area locates various instru-
ments or switches shown in the adjacent photographs.

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Quick Reference
Citation Bravo Developed for Training Purposes 2-1
September 2005
Quick
Reference
This chapter contains the aircraft’s operating limits and require-
ments as well as system by system charts summarizing compo-
nents, power sources, distribution, monitors, and specific
limitations. All limitations are printed in bold italic.
It also contains sections on supplement-directed limitations and
operations, instrument markings, and operations in the United
Kingdom.
This chapter is intended to serve as a convenient reference.

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Quick Reference
Citation Bravo Developed for Training Purposes 2-3
September 2005
Table of
Contents
General Limitations . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2-5
Authorized Operations . . . . . . . . . . . . . . . . . . . . . . . . 2-5
Baggage . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2-5
Certification Status . . . . . . . . . . . . . . . . . . . . . . . . . . . 2-5
Emergency Exit Door Pin . . . . . . . . . . . . . . . . . . . . . . 2-5
Maneuvers . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2-5
Minimum Crew . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2-5
Noise Levels . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2-6
Passenger Seat Position . . . . . . . . . . . . . . . . . . . . . . . 2-6
Operational Limits . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2-7
Maximum Design Weights . . . . . . . . . . . . . . . . . . . . . 2-7
Center of Gravity Moment Envelope . . . . . . . . . . . . . . 2-7
Center of Gravity Limits . . . . . . . . . . . . . . . . . . . . . . . . 2-8
Speed Limits . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2-9
Takeoff and Landing Operational Limits . . . . . . . . . . 2-11
Enroute Operational Limits . . . . . . . . . . . . . . . . . . . . 2-12
Load Factors . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2-12
Icing Factors
(Airworthiness Directive 98-04038) . . . . . . . . . . . . . . 2-13
System Data . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2-15
Avionics and Communications . . . . . . . . . . . . . . . . . 2-15
Electrical and Lighting Systems . . . . . . . . . . . . . . . . 2-17
Fuel . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2-18
Hydraulic Fluid . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2-19
Ice and Rain Protection . . . . . . . . . . . . . . . . . . . . . . . 2-20
Landing Gear and Brakes . . . . . . . . . . . . . . . . . . . . . 2-21
Miscellaneous Systems . . . . . . . . . . . . . . . . . . . . . . . 2-21
Pneumatic and Pressurization Systems . . . . . . . . . . 2-22
Powerplant – Pratt and Whitney . . . . . . . . . . . . . . . . 2-23
Instrument Markings . . . . . . . . . . . . . . . . . . . . . . . . . . 2-29
System Data Summaries . . . . . . . . . . . . . . . . . . . . . . . 2-31
Electrical Systems . . . . . . . . . . . . . . . . . . . . . . . . . . . 2-31
Fire Protection . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2-32
Flight Controls Systems . . . . . . . . . . . . . . . . . . . . . . 2-33

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Fuel System . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2-35
Hydraulic System . . . . . . . . . . . . . . . . . . . . . . . . . . . 2-36
Ice and Rain Protection . . . . . . . . . . . . . . . . . . . . . . 2-37
Landing Gear and Brakes . . . . . . . . . . . . . . . . . . . . 2-40
Oxygen Systems . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2-42
Pneumatic Systems . . . . . . . . . . . . . . . . . . . . . . . . . 2-43
Thrust Reverser System . . . . . . . . . . . . . . . . . . . . . . 2-46
AFM Supplements . . . . . . . . . . . . . . . . . . . . . . . . . . . 2-47
EROS Oxygen Mask . . . . . . . . . . . . . . . . . . . . . . . . 2-47
Flood Cooling System . . . . . . . . . . . . . . . . . . . . . . . 2-47
Global GNS-XLS Flight Management System
(Single or Dual) . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2-48
Gravel Runway Modification . . . . . . . . . . . . . . . . . . 2-49
Honeywell Primus-1000 Flight Guidance System . . 2-50
Honeywell LSZ-850 Lightning Sensor System . . . . . 2-51
UNS-1Csp (Single) or UNS-1K (Single or Dual)
Flight Management System
(with or without Unilink) . . . . . . . . . . . . . . . . . . . . . . . . . .2-

Quick Reference
Citation Bravo Developed for Training Purposes 2-5
September 2005
General
Limitations
Authorized Operations
nDay and night
nVFR and IFR flight
nFlight into icing conditions
Baggage
Nose . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 350 LBS MAXIMUM
Aft Cabin Storage . . . . . . . . . . . . . . . . . . . . . . . . 600 LBS MAXIMUM
Aft Cabin Storage Floor Load Limit . . . . . .120 LBS/SQ FT MAXIMUM
Tailcone Compartment:
Forward of Cargo Net. . . . . . . . . . . . . . . . . . . . . . . . . . . . 300 LBS
Aft of Cargo Net . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 200 LBS
TOTAL . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 500 LBS
Certification Status
nFAR, Part 25
Emergency Exit Door Pin
nThe emergency exit door pin must be removed prior to flight.
Maneuvers
nNo acrobatic maneuvers, including spins.
nNo intentional stalls above 25,000 ft.
Minimum Crew
nPilot and copilot
nThe pilot in command must have a CE-500 type rating and meet
the requirements of FAR 61.58.
nThe copilot shall possess a multi-engine rating, an instrument rat-
ing for flight above 18,000 ft or flight into instrument meteorolog-
ical conditions, and meet the requirements of FAR 61.55.
nCategory II operation requires two pilots who are qualified in
accordance with FAR 61.3.
NOTE: Nose baggage compart-
ment limit is 350 lbs maximum; this
decreases as optional equipment is
installed.

2-6 Developed for Training Purposes Citation Bravo
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Noise Levels
nThe Effective Perceived Noise Levels (EPNL) established in compli-
ance with FAR 36 Amendment 20, Stage 3 are shown in Table 2-A.
nThe takeoff weight for these figures was 14,800 lbs; the landing
weight was 13,500 lbs.
nTakeoff and sideline noise levels were established with a climb
speed of 130 KIAS and with 15° flaps. The thrust was reduced at
2,698 ft AGL from the takeoff N1% RPM to 74.3% N1% RPM.
nApproach noise levels were obtained with a 3° glideslope and 40°
flaps
nNo determination has been made by the FAA that these noise levels
are or should be acceptable or unacceptable for operation at, into, or
out of any airport.
Passenger Seat Position
For all takeoffs and landings, the following apply.
nSeats must be fully upright and outboard.
nThe seat aft of emergency exit must be in the most aft position.
Noise Reference PW530A
Sideline 73.7 EPNdB
Takeoff 85.2 EPNdB
Approach 91.2 EPNdB
Table 2-A; Effective Perceived Noise Levels (EPNL)
NOTE: Unobstructed access to
the emergency exit is facilitated by
moving the adjacent seat aft.

Quick Reference
Citation Bravo Developed for Training Purposes 2-7
September 2005
Operational
Limits
Maximum Design Weights
Ramp. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 15,000 LBS
Takeoff . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 14,800 LBS
Landing . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 13,500 LBS
Zero Fuel . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 11,300 LBS
nTakeoff weight is limited by the most restrictive of:
nmaximum certified takeoff weight (14,800 lbs)
nmaximum takeoff weight permitted by climb requirements
ntakeoff field length.
nLanding weight is limited by the most restrictive of:
nmaximum certified landing weight (13,500 lbs)
nmaximum landing weight permitted by climb requirements or
brake energy limit
nlanding distance.
Center of Gravity Moment Envelope
See Figure 2-1, following page.
Forward Limit at 9,147 Lbs or Less . . . . . . . . . . . . 18.54% OF MAC
(276.57” AFT OF DATUM)
Forward Limit at 14,800 Lbs . . . . . . . . . . . . . . . . . . 23.99% OF MAC
280.97” AFT OF DATUM)
There is a straight line variation between 18.54 and 23.99% of
MAC.
Aft Limit . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 30.0% OF MAC
(285.85” AFT OF DATUM)

2-8 Developed for Training Purposes Citation Bravo
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Center of Gravity Limits
2-1

Quick Reference
Citation Bravo Developed for Training Purposes 2-9
September 2005
Speed Limits
Maximum Operating:
MMO Above 27,900 Ft . . . . . . . . . . . . . . . . . 0.700 M INDICATED
VMO 8,000 Ft to 27,900 Ft . . . . . . . . . . . . . . . . . . . . . . . 275 KIAS
VMO Sea Level to 8,000 Ft . . . . . . . . . . . . . . . . . . . . . . . 260 KIAS
Do not exceed these limits in any flight regime (climb, cruise, or
descent) unless a higher speed is authorized for flight test or pilot
training.
Maximum Maneuvering (VA). . . . . . . . SEE CHART (Figure 2-2)
Maximum Maneuvering Speeds
50,000
45,000
40,000
35,000
30,000
25,000
20,000
15,000
10,000
5000
0
PRESSURE ALTITUDE - FEET
120 140 160 180 200 220 240
MANEUVERING SPEED (V
A
) - KIAS
EXAMPLE:
Pressure Altitude - 25,000 FEET
Weight - 11,500 POUNDS (5216 Kilograms)
Maximum Maneuvering Speed - 176 KNOTS
MACH = 0.70
14,800 POUNDS (6713 KGS)
9160 POUNDS (4155 KGS)
10,500 POUNDS (4762 KGS)
11,500 POUNDS (5216 KGS)
12,500 POUNDS (5670 KGS)
13,500 POUNDS (6123 KGS)
14,300 POUNDS (6486 KGS)
8622 POUNDS (3910 KGS)
2-2

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nConfine the following to speeds below VA:
nfull rudder application
nfull aileron control application
nmaneuvers involving angle-of-attack near stall.
Maximum Flap Extended (VFE):
Full Flaps, LAND (40°) . . . . . . . . . . . . . . . . . . . . . . . . . 174 KIAS
Partial Flaps, T.O & APPR (15°) . . . . . . . . . . . . . . . . . . 200 KIAS
Maximum Landing Gear Extended (VLE) . . . . . . . . . . . . . 260 KIAS
Maximum Landing Gear Operating:
(VLO – Extending) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 250 KIAS
(VLO – Retracting). . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 200 KIAS
Maximum Speedbrake Operation (VSB) . . . . . . . . . . . . . . NO LIMIT
Minimum Control – Air (VMCA) . . . . . . . . . . . . . . . . . . . . . . 78 KIAS
Minimum Control – Ground (VMCG) . . . . . . . . . . . . . . . . . . 89 KIAS
Autopilot Operation . . . . . . . . . . . . . . . . . . 275 KIAS or 0.700 MACH

Quick Reference
Citation Bravo Developed for Training Purposes 2-11
September 2005
Takeoff and Landing Operational Limits
Maximum Altitude Limit . . . . . . . . . . . . . . . . . . . . . . . . . . . 14,000 FT
Maximum Ambient Temperature (Figure 2-3) . . . . . . . . . ISA + 39°C
Minimum Ambient Temperature . . . . . . . . . . . . . . . . . . . . . . . . . -54°C
Takeoff/Landing/Enroute Temperature Limitations
NOTE: Maximum enroute operat-
ing temperature limit is ISA +39°C
ambient temperature adjusted for
ram rise (refer to AFM Figure 4-2) or
the Indicated Outside Air Tempera-
ture from Figure 2-3 (AFM Figure 2-
7), whichever is less.
50
40
30
20
10
5
-60 -40 -20 0 20 40 60
AMBIENT AIR TEMPERATURE - °C
PRESSURE ALTITUDE - 1000 FEET
2-3

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Maximum Crosswind . . . . . . . . . . . . . . . . DEMONSTRATED 24 KTS
Maximum Tailwind Component . . . . . . . . . . . . . . . . . . . . . . . 10 KTS
Maximum Tire Groundspeed. . . . . . . . . . . . . . . . . . . . . . . . . 165 KTS
Maximum Water/Slush on Runway . . . . . . . . . . . . . . . . . . 0.4 INCH
Nose Tire Pressure . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 120 ±5 PSI
nThe autopilot and yaw damper must be off for takeoff and land-
ing
nThe vertical navigation system must be off below 500 ft AGL.
nThe Engine synchronizer must be off for takeoff and landing.
nTakeoff and landing are limited to paved runways unless
equipped with optional gravel runway modification.
Enroute Operational Limits
Maximum Operating Altitude . . . . . . . . . . . . . . . . . . . . . . . 45,000 FT
Maximum Ambient Temperature . . . . . . . . . . . . . Refer to Figure 2-2
Minimum Ambient Temperature . . . . . . . . . . . . . . Refer to Figure 2-2
Generator Load:
Up to 35,000 Ft . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 400 AMPS
Above 35,000 Ft. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 315 AMPS
Load Factors
In Flight:
Flaps Up Position (0°). . . . . . . . . . -1.44 to +3.6 G’s at 14,800 LBS
Flaps T.O. & APPR TO LAND
Position (15° to 40°) . . . . . . . . . . . . 0.0 to +2.0 G’s at 14,800 LBS
Landing:
Flaps T.O. & APPR/LAND
Position (15° to 40°) . . . . . . . . . . . . . . . . +3.38 G’s at 13,500 LBS
These accelerations limit the angle-of-bank in turns and severity of pull-up
maneuvers.

Quick Reference
Citation Bravo Developed for Training Purposes 2-13
March 2009
Icing Factors
(Airworthiness Directive 98-04-38)
WARNING
Severe icing may result from environmental conditions outside of those
which the aircraft is certificated. Flight in freezing rain, freezing driz-
zle, or mixed icing conditions (supercooled liquid water and ice crys-
tals) may result in ice build-up on protected surfaces exceeding the
capability of the ice protection system, or may result in ice forming aft
of the protected surfaces. This ice may not be shed using the ice protec-
tion systems, and may seriously degrade the performance and control-
lability of the aircraft.
To minimize the potential hazards associated with operating the aircraft
in severe icing conditions, more clearly defined procedures and limita-
tions are provided as follows:
nDuring flight, severe icing conditions that exceed those for which the
aircraft is certified shall be determined by the following visual cues:
nunusually extensive ice accumulation on the airframe and wind-
shield in areas not normally observed to collect ice
naccumulation of ice on the upper surface of the wing aft of the
protected area
nif one or more of these visual cues exists, immediately request
priority handling from Air Traffic Control to facilitate a route or
an altitude change to exit the icing conditions
nSince the autopilot, when installed and operating, may mask tactile
cues that indicate adverse changes in handling characteristics, USE
OF THE AUTOPILOT IS PROHIBITED when any of the visual
cues specified above exist, or if when unusual lateral trim require-
ments or autopilot trim warnings are encountered while the aircraft is
in icing conditions.
nAll wing icing inspection lights must be operative prior to flight into
known or forecast icing conditions at night
nWing icing inspection lights must be operative prior to flight into
known or forecast icing conditions at night.
Conducive Weather Conditions
The following weather conditions may be conducive to severe inflight
icing:
nvisible rain at temperatures below 0°C ambient air temperature
ndroplets that splash or splatter and stick on impact at temperatures
below 0°C ambient temperature
WARNING: This AD applies to
all aircraft equipped with pneu-
matic deicing boots, certificated in
any category. This AD supersedes
any relief provided by the Master
Minimum Equipment List
(MMEL).
WARNING: When operating
with engine anti-ice system on, or
with residual ice on aircraft, refer
to the AFM, Section IV; Approach
and Landing, residual ice landing
correction factors.
CAUTION: When performing
instrument approaches in Icing
conditions with Engine Anti-Ice
turned ON, the Citation Bravo
AFM requires adding 4 KIAS to all
computed approach Ref. speeds,
due to the extra weight and reduced
aerodynamic performance caused
by possible ice accumulation on
unprotected aircraft surfaces.

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Exiting Procedures
The following procedures for exiting a severe icing environment are
applicable to all flight phases from takeoff to landing. Monitor the
ambient air temperature. While severe icing may form at temperatures
as cold as -18°C or colder, increased vigilance is warranted at tempera-
tures around freezing with visible moisture present. If the visual cues
specified for identifying severe icing conditions are observed, accom-
plish the following.
nImmediately request priority handling from Air Traffic Control to
facilitate a route or an altitude change to exit the icing conditions in
order to avoid extended exposure to flight conditions most severe
than those for which the aircraft is certificated.
nAvoid abrupt and excessive maneuvering that may cause increased
control difficulties.
nDo not engage the autopilot.
nIf the autopilot is engaged, hold the control wheel firmly and disen-
gage the autopilot.
nIf an unusual roll response or uncommanded roll control movement
is observed, reduce the angle-of-attack.
nDo not extend flaps when holding in icing conditions. Operation
with flaps extended can result in a reduced wing angle-of-attack,
with the possibility of ice forming on the upper surface further aft on
the wing than normal, possibly aft of the protected area.
nIf the flaps are extended, do not retract them until the airframe is
clear of ice.
nReport these weather conditions to Air Traffic Control.