CAE SimuFlite Citation Bravo Pilot Training Manual

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Citation Bravo

Pilot Training Manual

Revision 2

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Page 1 Citation Bravo Pilot Training Manual Revision 2 cae.com...
Page 2 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. Copyright 2013, CAE, Inc.
Page 3 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.
Page 4 CAE SimuFlite Citation Bravo Developed for Training Purposes March 2009...
Page 5 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. Citation Bravo Developed for Training Purposes March 2009...
Page 6 CAE SimuFlite Citation Bravo Developed for Training Purposes March 2009...
Page 7 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. Citation Bravo Developed for Training Purposes September 2005...
Page 8 CAE SimuFlite Citation Bravo Developed for Training Purposes September 2005...
Page 9: Table Of Contents
Fire Protection ......2-32 Flight Controls Systems ..... . 2-33 Citation Bravo Developed for Training Purposes...
Page 10 Flight Management System (with or without Unilink) ......2- Citation Bravo Developed for Training Purposes September 2005...
Page 11: Authorized Operations
18,000 ft or flight into instrument meteorolog- ical conditions, and meet the requirements of FAR 61.55. Category II operation requires two pilots who are qualified in accordance with FAR 61.3. Citation Bravo Developed for Training Purposes September 2005...
Page 12: Noise Levels
For all takeoffs and landings, the following apply. the emergency exit is facilitated by moving the adjacent seat aft. Seats must be fully upright and outboard. The seat aft of emergency exit must be in the most aft position. Citation Bravo Developed for Training Purposes March 2009...
Page 13: Operational Limits
Aft Limit ........30.0% OF MAC (285.85” AFT OF DATUM) Citation Bravo Developed for Training Purposes...
Page 14: Center Of Gravity Limits
CAE SimuFlite Center of Gravity Limits Citation Bravo Developed for Training Purposes September 2005...
Page 15: Speed Limits
40,000 35,000 30,000 25,000 20,000 15,000 10,000 5000 MANEUVERING SPEED (V ) - KIAS EXAMPLE: Pressure Altitude - 25,000 FEET Weight - 11,500 POUNDS (5216 Kilograms) Maximum Maneuvering Speed - 176 KNOTS Citation Bravo Developed for Training Purposes September 2005...
Page 16 ) ....89 KIAS Autopilot Operation ....275 KIAS or 0.700 MACH 2-10 Citation Bravo Developed for Training Purposes September 2005...
Page 17: Takeoff And Landing Operational Limits
Minimum Ambient Temperature ......-54°C ture from Figure 2-3 (AFM Figure 2- 7), whichever is less. Takeoff/Landing/Enroute Temperature Limitations AMBIENT AIR TEMPERATURE - °C Citation Bravo 2-11 Developed for Training Purposes September 2005...
Page 18: Enroute Operational Limits
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. 2-12 Citation Bravo Developed for Training Purposes March 2009...
Page 19 Air Traffic Control to facilitate a route or conditions with Engine Anti-Ice an altitude change to exit the icing conditions turned ON, the Citation Bravo Since the autopilot, when installed and operating, may mask tactile AFM requires adding 4 KIAS to all computed approach Ref.
Page 20 If the flaps are extended, do not retract them until the airframe is clear of ice. Report these weather conditions to Air Traffic Control. 2-14 Citation Bravo Developed for Training Purposes March 2009...
Page 21: System Data
The vertical navigation system must be off below 500 ft AGL. HF/ADF System The ADF bearing information may be erratic when keying the HF transmitter. If this occurs, disregard the ADF bearing during transmis- sion periods. Citation Bravo 2-15 Developed for Training Purposes September 2005...
Page 22 Crew qualification and ual P/N A28-1146-109-00 revision 00 or later revision for the Cessna Letter of Authority from the FAA Citation Bravo must be immediately available to the flight crew. are required to conduct Category II Approach Operations. Both flight director and auto pilot coupled Category II approaches are not approved using the Honeywell P-1000 EFIS displays.
Page 23: Electrical And Lighting Systems
Above 35,000 Ft ........315 AMPS Citation Bravo...
Page 24: Fuel
104 gallons (0.15%) Military JP-5 and JP-8 have anti-icing preblended by the DIEGME 20 fluid ounces per 20 fluid ounces per refinery. 156 gallons 104 gallons Table 2-B; Fuel Anti-icing Additive 2-18 Citation Bravo Developed for Training Purposes March 2009...
Page 25: Hydraulic Fluid
Fuel remaining in the fuel tanks when the fuel quantity indicator reads zero is not usable in flight. Hydraulic Fluid Use Skydrol 500B-4, C, or LD-4; or use Hyjet, Hyjet IV or IVA plus. Citation Bravo 2-19 Developed for Training Purposes September 2005...
Page 26: Ice And Rain Protection
Wing deice is required in flight when wing ice builds up to ¼ to ½ inch thickness. Do Not operate deice boots below -40°C. Pitot Static Limit ground operation of pitot/static heat to 2 minutes ON with 2 minutes OFF between cycles to prevent system damage. 2-20 Citation Bravo Developed for Training Purposes March 2009...
Page 27: Landing Gear And Brakes
Limit engine static ground operation to idle power if thrust revers- ers are deployed. Do not use thrust reversers during touch and go landings. Citation Bravo 2-21 Developed for Training Purposes March 2009...
Page 28: Pneumatic And Pressurization Systems
Vapor Cycle Air Conditioning Operation of the air conditioning system is prohibited for any of the following conditions: pressure altitude above 18,000 ft either generator inoperative ambient temperatures less than -21°C (-5°F). 2-22 Citation Bravo Developed for Training Purposes March 2009...
Page 29: Powerplant – Pratt And Whitney
If oils of nonapproved brands or of different viscosities become intermixed, drain and flush the complete oil system, then refill with an approved oil according to the Engine Maintenance Man- ual instructions. Minimum oil temperature for start is -40°C. Citation Bravo 2-23 Developed for Training Purposes September 2005...
Page 30 To ensure accurate fan speed thrust indication, inspect fan for damage prior to each flight. Engine Operating Limits , opposite page. Table 2-D Engine Overspeed Limits , page 2-26. Figure 2-4 2-24 Citation Bravo Developed for Training Purposes September 2005...
Page 31 6. Flight (HI) idle turbine RPM is 49.4 +1.0/-0% with ignition ON, pressurization bleed air OFF and oil temperature stabilized. 7. With pressurization bleed air ON, idle speeds may be up to 1.5% N less than noted above. Citation Bravo 2-25 Developed for Training Purposes...
Page 32 CAE SimuFlite Engine Overspeed Limits ITT Limits For starting conditions, see Figure 2-5. For all conditions except starting, see Figure 2-6. 2-26 Citation Bravo Developed for Training Purposes September 2005...
Page 33 AREA B - (1) DETERMINE CAUSE AND CORRECT - (2) INSPECT HOT SECTION USING BORESCOPE - (3) RECORD IN ENGINE LOG BOOK AREA C - RETURN ENGINE TO AN OVERHAUL FACILITY Citation Bravo 2-27 Developed for Training Purposes September 2005...
Page 34 Limit ground operation of pitot/static heat to two minutes to pre- cluded damage to the pitot/static heater and AOA probe. Operation in GND bleed air mode at settings greater than 70% N for the right engine is prohibited. 2-28 Citation Bravo Developed for Training Purposes September 2005...
Page 35: Instrument Markings
Green Band ........200 TO 700°C Citation Bravo...
Page 36 Normal Operating ......45 TO 100% RPM 2-30 Citation Bravo Developed for Training Purposes...
Page 37: System Data Summaries
BATT O’TEMP annunciator/gauge Battery temperature gauge Master warning AC FAIL annunciator INVTR 1/2 FAIL annunciator Master warning Protection Circuit Breakers Current limiters Relays Generator Control Units (GCUs) External power overvoltage/overcurrent sensor Citation Bravo 2-31 Developed for Training Purposes March 2009...
Page 38: Fire Protection
600 ± 75 PSI at 70° F. FIRE DET SYS L/R amber annunciator Protection Circuit breakers A thermal discharge valve provides overpressure relief for each bottle. Miscellaneous Two 125 in fire bottles are in the tailcone area. 2-32 Citation Bravo Developed for Training Purposes March 2009...
Page 39: Flight Controls Systems
Yaw damper engages automatically via AP/ENGAGE switch or when YD ENGAGE switch is pressed Turn knob on autopilot control panel must be centered in detent and DG-1 or DG-2 aligned to engage autopilot. Citation Bravo 2-33 Developed for Training Purposes March 2009...
Page 40 Stall Warning – Stick Shaker Power Sources Left Main DC extension bus Control Rotary TEST switch Left main gear squat switch Monitor Stall warning Stick Shaker Protection SPEED BRAKES circuit breaker 2-34 Citation Bravo Developed for Training Purposes March 2009...
Page 41: Fuel System
Crossfeed INTRANSIT light FUEL FLOW gauge FUEL QTY indicator Protection Circuit breaker Prist (not required; but recommended) Fuel Filters Fuel Firewall shutoff valves Motive flow shutoff valve Emergency fuel shutoff valve Citation Bravo 2-35 Developed for Training Purposes March 2009...
Page 42: Hydraulic System
TR isolation valve to stop flammable liquid flow to the affected engine. Refer to appropriate system section for protection in a specific aircraft system. 2-36 Citation Bravo Developed for Training Purposes March 2009...
Page 43: Ice And Rain Protection
Rotary TEST SELECTOR switch - W/S TEMP Monitor W/S AIR O’HEAT annunciator Bleed air noise Protection Circuit breakers Windshield bleed air valve - fail safe (open) Overtemp transmitter Manual bleed air control valves Citation Bravo 2-37 Developed for Training Purposes March 2009...
Page 44 On the second cycle, both wing boots inflate. Vacuum deflates the boots between cycles. 2-38 Citation Bravo Developed for Training Purposes March 2009...
Page 45 Ground valve Pressurization takeoff modes Thrust reversers Radar forced standby Bleed air ground - right engine Stick shaker and stick shaker test Right main gear squat switch Thrust reversers Stick shaker test Citation Bravo 2-39 Developed for Training Purposes September 2005...
Page 46: Landing Gear And Brakes
Brake fluid reservoir (preflight) Brake pedal feel Protection Circuit breakers Left main gear squat switch Mechanical downlock Gear/Flap warning horn Miscellaneous Anti-skid must be operative for takeoff and landing on sod/dirt or gravel runways. 2-40 Citation Bravo Developed for Training Purposes March 2009...
Page 47: Oxygen Systems
CB is on left power junction box and is not accessible in flight. Overpressure vent: Cylinder pressure exceeding 2,500 PSI ruptures green disc at end of overpressure vent (flush- mounted in fuselage); oxygen discharges overboard. Citation Bravo 2-41 Developed for Training Purposes March 2009...
Page 48 TEMPERATURE CONTROL SELECTOR PRESS SOURCE selector Bleed air shutoff/flow control valves Monitor Cabin temperature air duct sensors Annunciators AIR DUCT O’HEAT EMER PRESS ON BLD AIR GND ACM O’PRESS Protection Circuit breakers 2-42 Citation Bravo Developed for Training Purposes March 2009...
Page 49: Pneumatic Systems
W/S BLEED AIR manual shutoff valves Monitor Annunciators BLD AIR GND EMER PRESS ON ACM O’PRESS ENG ANTI ICE L/R SURFACE DEICE W/S AIR O’HEAT AIR DUCT O’HEAT Protection Circuit breakers Fail safe valves Sensors Citation Bravo 2-43 Developed for Training Purposes March 2009...
Page 50 CAB ALT 10K FT BLD AIR GND EMER PRESS ON CABIN ALT/DIFF PRESS indicator Protection Cabin altitude limit valves Circuit breakers Emergency dump valve Oxygen system Passenger oxygen system baro-sensor 10,000 ft cabin sensor 2-44 Citation Bravo Developed for Training Purposes March 2009...
Page 51: Thrust Reverser System
Emergency stow system – Bypasses normal stows sys- tem with override command to stow. THRUST REVERSER L/R (7.5A) circuit breakers Citation Bravo 2-45 Developed for Training Purposes September 2005...
Page 52: Citation Bravo Developed For Training Purposes
CAE SimuFlite 2-46 Citation Bravo Developed for Training Purposes September 2005...
Page 53: Afm Supplements
Cockpit masks are assumed to be at the normal setting at 20,000 ft with a respiratory rate of 10 liters per minute - body temperature pressure saturated and at 100% setting above 20,000 ft. Citation Bravo 2-47 Developed for Training Purposes...
Page 54 (to subscribers) or obtained from authorized Global Wulfs- berg installation centers or update centers. The fuel management mode is for advisory purposes only, and it should not replace the airplane primary fuel flow and fuel quantity gauges. 2-48 Citation Bravo Developed for Training Purposes March 2009...
Page 55: Gravel Runway Modification
Nosewheel steering must be disengaged for takeoff and/or landing operations on a gravel runway. Use of thrust reverser power above flight idle power is prohibited on gravel runways. Citation Bravo 2-49 Developed for Training Purposes March 2009...
Page 56: Honeywell Primus-1000 Flight Guidance System
Verify the P-1000 system as operational per a satisfactory pre- flight test as contained in the NORMAL procedures. Dual PFD SG reversion to the MFD is prohibited. Flight Director and autopilot coupled VOR approaches without DME are not approved. 2-50 Citation Bravo Developed for Training Purposes September 2005...
Page 57: Honeywell Lsz-850 Lightning Sensor System
28 days; updating to be accomplished with the Universal Avi- onics update disk or equivalent. The fuel management mode is for advisory purposes only and it does not replace the airplane primary fuel flow and fuel quantity systems. Citation Bravo 2-51 Developed for Training Purposes September 2005...
Page 58 VNAV Operation with FMS Software MOD Levels 601.X and 602.X The UNS-1Csp displayed VNAV information is advisory informa- tion only. FMS VNAV cannot be coupled to the autopilot or flight director. 2-52 Citation Bravo Developed for Training Purposes September 2005...
Page 59 When conducting missed approach procedures, autopilot coupled operation is prohibited until the flight crew has established a rate of climb that ensures all altitude requirements of the procedure will be met. Citation Bravo 2-53 Developed for Training Purposes September 2005...
Page 60 CAE SimuFlite 2-54 Citation Bravo Developed for Training Purposes September 2005...
Page 61 Monitoring callouts and verbal or physical responses. The Maneuvers chapter pictorially illustrates normal and emer- gency profiles. Additionally, written descriptions are included for most phases of flight with one or both engines operating. Citation Bravo Developed for Training Purposes September 2005...
Page 62 CAE SimuFlite Citation Bravo Developed for Training Purposes September 2005...
Page 63 Lastly, the pilot returns to the interior of the aircraft to check the passenger compartment and cockpit for flight readiness. Citation Bravo 3A-1 Developed for Training Purposes September 2005...
Page 64 CAE SimuFlite 3A-2 Citation Bravo Developed for Training Purposes September 2005...
Page 65 Cabin Inspection ......3A-43 Cockpit Inspection ......3A-45 Citation Bravo 3A-3...
Page 66 CAE SimuFlite 3A-4 Citation Bravo Developed for Training Purposes September 2005...
Page 67 Two elements are inherent in the execution of normal procedures: use of either the cockpit layout or event cues to prompt the correct switch and/or control positions. use of normal checklists as “done” lists. Citation Bravo 3A-5 Developed for Training Purposes September 2005...
Page 68 CAE SimuFlite Cockpit Flow Pattern 3A-6 Citation Bravo Developed for Training Purposes September 2005...
Page 69 Exterior Light Switches ....... . . OFF Citation Bravo 3A-7...
Page 70 Trim......... . THREE SET Rudder, Aileron, and Elevator correctly positioned. 3A-8 Citation Bravo Developed for Training Purposes September 2005...
Page 71 Windshield Heat Manual Control Knobs ....OFF Vapor Cycle Air Conditioner ......OFF Citation Bravo 3A-9...
Page 72 CAE SimuFlite 3A-10 Citation Bravo Developed for Training Purposes September 2005...
Page 73 Battery Switch......... OFF All Other Switches ......OFF (or NORM) Citation Bravo 3A-11...
Page 74 CAE SimuFlite 3A-12 Citation Bravo Developed for Training Purposes September 2005...
Page 75 Check particularly for damage, fluid leakage, security of access panels, and removal of keys from locks. Remove all covers from the pitot tubes, static ports, probes, and engine inlets and exhausts. Citation Bravo 3A-13 3A-14 Developed for Training Purposes...
Page 76 CAE SimuFlite Preflight Inspection Walkaround Path 3A-14 Citation Bravo Developed for Training Purposes March 2009...
Page 77 (LEFT XDCR), right transducer failure (RIGHT XDCR), left and right squat switch disagreement (SQUAT DISAGREE), control valve failure (VALVE), and control unit failure (CONTROL). 5. Baggage Door: Check that the door is firmly closed and locked. Citation Bravo 3A-15 Developed for Training Purposes March 2009...
Page 78 CAE SimuFlite 3A-16 Citation Bravo Developed for Training Purposes March 2009...
Page 79 Check for proper inflation, 120 ± 5 PSI. 9. Pitot Tubes: The tubes are in a cooling cycle. Check the left tube, then move around the nose and check the right. Check that both are clear and warm. Citation Bravo 3A-17 Developed for Training Purposes July 2004...
Page 80 CAE SimuFlite 3A-18 Citation Bravo Developed for Training Purposes July 2004...
Page 81 5. Oxygen Blowout Disc: Check that the green disc is in place. If it is missing, the oxygen bottle is empty. 6. Overboard Vent Lines: Check that the following vent lines are clear: vacuum, brake reservoir, alcohol, gear and brake/gear pneumatic pressure. Citation Bravo 3A-19 Developed for Training Purposes March 2009...
Page 82 CAE SimuFlite 3A-20 Citation Bravo Developed for Training Purposes March 2009...
Page 83 10. Angle-of-Attack Vane: Carefully check the vane for heating well as ease and range of rotation. 11. Bottom Antennas: Check condition of the antennas. Citation Bravo 3A-21 Developed for Training Purposes March 2009...
Page 84 CAE SimuFlite 3A-22 Citation Bravo Developed for Training Purposes March 2009...
Page 85 ( B O T T O M O F W I N G ) Q U I C K D R A I N V A L V E S ( 1 T O 4 ) 3A-1 Citation Bravo 3A-23 Developed for Training Purposes...
Page 86 CAE SimuFlite 3A-24 Citation Bravo Developed for Training Purposes March 2009...
Page 87 14. Fuel Tank Vent: Check that vent is clear to preclude a negative WARNING: Anti-ice additive is pressure buildup that could cause tank to collapse Figure 3A-2 toxic. Observe proper safety pre- cautions. (UNDERSIDE) 3A-2 Citation Bravo 3A-25 Developed for Training Purposes March 2009...
Page 88 CAE SimuFlite 3A-26 Citation Bravo Developed for Training Purposes March 2009...
Page 89 Check flap(s) for Refer to Figure 3A-3 18. Speedbrakes: Check upper ( ) and lower ( ) assemblies for security ( Figure 3A-3 3A-3 Citation Bravo 3A-27 Developed for Training Purposes March 2009...
Page 90 CAE SimuFlite 3A-28 Citation Bravo Developed for Training Purposes July 2004...
Page 91 If oils of non-approved brands or of different viscosities become inter- mixed, drain and flush the com- plete oil system and refill with approved oil according to engine maintenance manual instructions. Citation Bravo 3A-29 Developed for Training Purposes March 2009...
Page 92 CAE SimuFlite 3A-30 Citation Bravo Developed for Training Purposes July 2004...
Page 93 Check for two static wicks on the elevator; replace wicks if missing. Check left horizontal stabilizer de-ice boots for cuts and delamination. secure. Citation Bravo 3A-31 Developed for Training Purposes July 2004...
Page 94 CAE SimuFlite 3A-32 Citation Bravo Developed for Training Purposes July 2004...
Page 95 NOTE: SB550 -78-03: Thrust 9. Windshield Heat Exchanger Overboard Exhaust: Check Reverser Throttle Load Limiter that the exhaust is clear and free of obstructions.(No Illustration) : Modification. Citation Bravo 3A-33 Developed for Training Purposes March 2009...
Page 96 CAE SimuFlite 3A-34 Citation Bravo Developed for Training Purposes July 2004...
Page 97 If oils of non-approved brands or of different viscosities become intermixed, drain and flush the complete oil system and refill with approved oil according to engine maintenance manual. Citation Bravo 3A-35 Developed for Training Purposes March 2009...
Page 98 CAE SimuFlite 3A-36 Citation Bravo Developed for Training Purposes July 2004...
Page 99 4. Recognition, Landing (4A), Navigation, and Anti- Collision Lights ( Check lenses for cracks and integrity SPEEDBRAKE AILERON FLAP AILERON TRIM TAB 3A-4 Citation Bravo 3A-37 Developed for Training Purposes July 2004...
Page 100 CAE SimuFlite 3A-38 Citation Bravo Developed for Training Purposes July 2004...
Page 101 FUEL TANK FILL CAP FUEL TANK VENT QUICK DRAIN VALVES VENT (UNDERSIDE) QUICK DRAIN VALVES (1 TO 4) (BOTTOM OF WING) (UNDERSIDE) FILTER DRAIN (1 TO 5) (BOTTOM OF WING) 3A-5 Citation Bravo 3A-39 Developed for Training Purposes March 2009...
Page 102 CAE SimuFlite LEFT WING 3A-40 Citation Bravo Developed for Training Purposes March 2009...
Page 103 17. Wing Inspection Light: Check for condition. 18. Cabin Door Seal: Check for rips, tears, and folding. FILL CAP FUEL TANK VENT QUICK DRAIN VALVES (UNDERSIDE) (1 TO 4) (BOTTOM OF WING) 3A-6 Citation Bravo 3A-41 Developed for Training Purposes March 2009...
Page 104 CAE SimuFlite 3A-42 Citation Bravo Developed for Training Purposes July 2004...
Page 105 ). The pressure gauge on each should read in the white (Figure 3A-10 arc, or 150 PSI. Documents: Check that airworthiness and registration certificates are on board and displayed Figure 3A-11 3A-7 3A-9 3A-8 3A-10 3A-11 Citation Bravo 3A-43 Developed for Training Purposes March 2009...
Page 106 Passenger Oxygen Supply Valve: Check that the Oxygen Con- for takeoff if the oxygen level indi- trol Valve rotary knob is in NORMAL. cates below the normal green band. Oxygen Quantity: Check oxygen quantity ( Figure 3A-13 3A-12 3A-13 3A-44 Citation Bravo Developed for Training Purposes March 2009...
Page 107 First Aid Kit: Check that it is on board and adequately equipped For Commercial operations, no items may be missing Figure 3A-14). from the First Aid Kit at dispatch 3A-14 Citation Bravo 3A-45 Developed for Training Purposes March 2009...
Page 108 CAE SimuFlite 3A-46 Citation Bravo Developed for Training Purposes July 2004...
Page 109 This section outlines and expands normal operating procedures and includes applicable cautions and warnings. Also present-ed Normal are cold weather operations as well as parking, mooring, and short-term aircraft storage requirements. Procedures Chapter 3B Citation Bravo 3B-1 Developed for Training Purposes September 2005...
Page 110 CAE SimuFlite 3B-2 Citation Bravo Developed for Training Purposes September 2005...
Page 111 Conducive Weather Conditions ....3B-36 Exiting Procedures ......3B-37 Citation Bravo 3B-3...
Page 112 Performance Computations, Takeoff ... . .3B-53 Securing Overnight or for an Extended Period (Aircraft Unattended) ... 3B-54 3B-4 Citation Bravo Developed for Training Purposes March 2009...
Page 113 Anti-Skid ......... . . ON Citation Bravo...
Page 114 Adjust rudder pedals; depress the tab on inboard side, move the pedals fore or aft into one of the three positions, and then release the tab. Check pedals locked in the desired position. 3B-6 Citation Bravo Developed for Training Purposes March 2009...
Page 115 LO FUEL LEVEL Lights extinguished. After light off occurs, at approximately 30 to 44% turbine RPM, the GCU opens the starter relay, terminates ignition and fuel boost and turns off the start button and the instrument flood lights. Citation Bravo 3B-7 Developed for Training Purposes March 2009...
Page 116 Verify that the power unit is off by confirming DC battery voltage on the voltmeter, (less than 28V DC). Generator Switches (if external power used for start) . . GEN The generators may not come on until the external power is removed. 3B-8 Citation Bravo Developed for Training Purposes March 2009...
Page 117 Aileron and Rudder Trim ......SET Check the aileron and rudder trim correctly set. Citation Bravo 3B-9...
Page 118 All flags in view. d. Command cue (if selected) bias from view. e. Test light illuminates in upper left corner of PFDs f. Autopilot tests OK in autopilot test screen 3B-10 Citation Bravo Developed for Training Purposes March 2009...
Page 119 Check that no warning flags are visible. Check that the heading instruments are in agreement (EHSI, Standby HSI and magnetic compass). Check that the VSIs are at zero. Ensure that the GYRO SLAVE switches are in AUTO. Citation Bravo 3B-11 Developed for Training Purposes March 2009...
Page 120 Crew Briefing ......COMPLETED Refer to the Standard Operating Procedures (SOPS) chapter for detailed explanation of items on the takeoff briefing. 3B-12 Citation Bravo Developed for Training Purposes March 2009...
Page 121 Annunciator Panel ..CLEAR except GROUND IDLE light All annunciator lights should be extinguished with the exception of GROUND IDLE, and ENG ANTI-ICE if that system is selected at a low power system. Citation Bravo 3B-13 Developed for Training Purposes March 2009...
Page 122 FAN or TURB position. Check that the engine instruments remain within limits. N RPM increases with altitude; throttle adjustments will be necessary to maintain specified thrust setting. 3B-14 Citation Bravo Developed for Training Purposes March 2009...
Page 123 +10°C or colder indicated OAT and any time icing is occurring. The pitot and static anti-ice is normally operated during flight. Citation Bravo 3B-15 Developed for Training Purposes March 2009...
Page 124 Recognition Lights ....... . . ON Speed Brakes......AS REQUIRED 3B-16 Citation Bravo Developed for Training Purposes March 2009...
Page 125 Engine Sync ........OFF Citation Bravo...
Page 126 Depress the AP/TRIM DISC switch on either control wheel. With tion is not available below 12 kts Groundspeed. the yaw damper off, the pilot has complete rudder authority for landing. 3B-18 Citation Bravo Developed for Training Purposes March 2009...
Page 127 The aircraft tends to pitch upward during reverser deployment. Therefore, maintain forward nose-down elevator pressure on the yoke during reverser deployment; especially at high speeds, such as a rejected takeoff or no-flap landing. Citation Bravo 3B-19 Developed for Training Purposes March 2009...
Page 128 (no modulation or “pumping”) to nance is required before next brake pedals. flight. Speedbrakes ....EXTEND (after touchdown) 3B-20 Citation Bravo Developed for Training Purposes March 2009...
Page 129 Radar ......... . OFF Do not operate the radar within 15 ft. of personnel or flammable or explosive material. Citation Bravo 3B-21 Developed for Training Purposes...
Page 130 Battery Switch........OFF Move the BATT switch to OFF Care should be exercised that it is not placed in EMER. The emergency bus items will drain the battery significantly over an extended period. 3B-22 Citation Bravo Developed for Training Purposes March 2009...
Page 131 Foul Weather Window/Door ..CLOSED AS NECESSARY EROS Oxygen Masks. . .REMOVE FROM THE AIRCRAFT IF COCKPIT TEMPERATURES ARE ANTICIPATED TO BE BELOW 0°C FOR EXTENDED PERIODS, AS SPECI- FIED IN THE BRAVO AFM SUPPLEMENT. Citation Bravo 3B-23 Developed for Training Purposes March 2009...
Page 132 CAE SimuFlite Protective Covers ENGINE EXHAUST COVERS 3B-2 ENGINE INLET COVER GENERATOR INLET COVER PITOT TUBE COVERS (3) 3B-3 3B-1 3B-24 Citation Bravo Developed for Training Purposes September 2005...
Page 133 SECURED TO PARKING APRON Foul Weather Window/ Door ....CLOSED AS NECESSARY NOSE GEAR MAIN GEAR 3B-4 Citation Bravo 3B-25 Developed for Training Purposes September 2005...
Page 134 Observe the aircraft taxi turning with brakes and towbar turning dis- the tug. tances depicted on (following pages). Figure 3B-6 Figure 3B-7 WHEEL NOSE AXLE TOWBAR 3B- 5 3B-26 Citation Bravo Developed for Training Purposes March 2009...
Page 135 Expanded Normal Procedures Towing Turning Distances WALL TO WALL 52.15 FT 26.07 FT 18.47 FT 6.54 FT 23.50 FT CURB TO CURB 25.01 FT 3B-6 Citation Bravo 3B-27 Developed for Training Purposes September 2005...
Page 136 CAE SimuFlite Talking Turning Distances WALL TO WALL 65.24 FT CURB TO CURB 32.66 FT 13.07 FT 19.59 FT 3B-7 3B-28 Citation Bravo Developed for Training Purposes September 2005...
Page 137 Tow Bar ........REMOVED Citation Bravo 3B-29...
Page 138 Static Ground Cable ..... . CONNECTED Tow Cables and Towing Adapters ... . REMOVED 3B-30 Citation Bravo Developed for Training Purposes September 2005...
Page 139 Refer to expanded normal procedure for details. Main Gear Wheels ......CHOCKED Citation Bravo 3B-31 Developed for Training Purposes...
Page 140 CAE SimuFlite 3B-32 Citation Bravo Developed for Training Purposes September 2005...
Page 141 Doors ......CLOSED AND LOCKED Performance Computations, Takeoff Make takeoff performance computations in accordance with the FAA approved AFM. Citation Bravo 3B-33 Developed for Training Purposes March 2009...
Page 142 CAE SimuFlite 3B-34 Citation Bravo Developed for Training Purposes September 2005...
Page 143 Following extended high-altitude flight, frost can form at ambient tem- peratures above freezing on the wing's underside in the fuel tank areas. Refueling the aircraft with warmer fuel usually melts the frost. Citation Bravo 3B-35 Developed for Training Purposes March 2009...
Page 144 The following weather conditions may be conducive to severe inflight icing: visible rain at temperatures below 0°C ambient air temperature droplets that splash, stick or splatter on impact at temperatures below 0°C ambient air temperature 3B-36 Citation Bravo Developed for Training Purposes March 2009...
Page 145 If the flaps are extended, do not retract them until the airframe is clear of ice. Report these weather conditions to Air Traffic Control. Citation Bravo 3B-37 Developed for Training Purposes March 2009...
Page 146 OFF. operation on snow, slush, or wet surfaces operation near other aircraft, equipment, and buildings presence of deicing fluid and its type, dilution strength, and application method. 3B-38 Citation Bravo Developed for Training Purposes March 2009...
Page 147 Mechanically remove snow and ice from the engine inlet. Check the first stage fan blades for freedom of movement. If engine does not rotate freely, deice engine with hot air. Citation Bravo 3B-39 Developed for Training Purposes...
Page 148 When unsure of wing cleanliness, perform a "hands on" inspection to verify that all wing surfaces are clean of ice, snow, and frost. 3B-40 Citation Bravo Developed for Training Purposes September 2005...
Page 149 Use hot air carefully around windows. Excessive temperatures on windows can crack or craze cold windows. Exercise extreme care when using hot air to prevent damage to hoses, painted surfaces, and acrylic, plastic, fiberglass, and rubber components. Citation Bravo 3B-41 Developed for Training Purposes September 2005...
Page 150 The time of protec- tion will be shortened in: heavy weather conditions heavy precipitation rates or high moisture content high wind velocity jet blast when aircraft skin temperature is lower than OAT. 3B-42 Citation Bravo Developed for Training Purposes September 2005...
Page 151 The time of protec- tion will be shortened in: heavy weather conditions heavy precipitation rates or high moisture content high wind velocity jet blast when aircraft skin temperature is lower than OAT. Citation Bravo 3B-43 Developed for Training Purposes September 2005...
Page 152 The time of protec- tion will be shortened in: heavy weather conditions heavy precipitation rates or high moisture content high wind velocity jet blast when aircraft skin temperature is lower than OAT. 3B-44 Citation Bravo Developed for Training Purposes September 2005...
Page 153 A stronger mix can be used under the latter conditions. Table 3B:B: Type II Fluid Holdover Times To be applied before first step fluid freezes, typically within 3 minutes. Clean aircraft may be anti-iced with cold fluid. Citation Bravo 3B-45 Developed for Training Purposes September 2005...
Page 154 To be applied before first step fluid freezes, typically within 3 minutes. Clean aircraft may be anti-iced with cold fluid. CAUTION: Aircraft skin tem- perature and OAT may differ sig- nificantly. 3B-46 Citation Bravo Developed for Training Purposes September 2005...
Page 155 NOTE: SHADED AREAS INDICATE ESSENTIAL AREAS TO BE DEICED. NOTE: MINIMUM DIRECT SPRAY AREAS INCLUDE ENGINE INLETS, ENGINE EXHAUST , RAM AIR INLETS, BRAKES, PITOT HEADS, STATIC PORTS,WINDSHIELD, CABIN WINDOWS, AND AOA VANES 3B-8 Citation Bravo 3B-47 Developed for Training Purposes September 2005...
Page 156 NOTE: SHADED AREAS INDICATE ESSENTIAL AREAS TO BE ANTI-ICED. NOTE: MINIMUM DIRECT SPRAY AREAS INCLUDE ENGINE INLETS, ENGINE EXHAUST , RAM AIR INLETS, BRAKES, PITOT HEADS, STATIC PORTS,WINDSHIELD, CABIN WINDOWS, AND AOA VANES 3B-9 3B-48 Citation Bravo Developed for Training Purposes September 2005...
Page 157 Aircraft Deicing ......COMPLETED For different deicing fluids, the times of protection (the holdover times) vary considerably. Furthermore, these times depend to a large extent on meteorological conditions. Citation Bravo 3B-49 Developed for Training Purposes September 2005...
Page 158 For ground operation, the system should be turned on one minute out of four with N set above 65%. 3B-50 Citation Bravo Developed for Training Purposes September 2005...
Page 159 To ensure the aircraft is configured for takeoff, recheck the flap position indicator. Temperature Control ... . CONSIDER REDUCING TEMP FROM FULL HOT TO AVOID DUCT O'HEAT ANNUNCIATOR. ON TAKEOFF Citation Bravo 3B-51 Developed for Training Purposes March 2009...
Page 160 Rudder Pedal Steering ..USED FOR DIRECTIONAL CONTROL, IF POSSIBLE Rudder and differential braking may also be used as necessary for directional control. Reduce brake pressure if directional control problems are encountered because of excessive anti-skid cycling. 3B-52 Citation Bravo Developed for Training Purposes September 2005...
Page 161 Windshield Bleed Air ..... . . LOW OR HI Use windshield bleed air and the defog fan to clear the windshield. Performance Computations, Takeoff Make takeoff performance computations in accordance with the FAA approved AFM. Citation Bravo 3B-53 Developed for Training Purposes March 2009...
Page 162 Doors ........CLOSED Close the main cabin, baggage compartment, and access doors to keep snow or rain out of the aircraft. 3B-54 Citation Bravo Developed for Training Purposes March 2009...
Page 163 If your flight department has an SOP, we encourage you to use it during your training. If your flight department does not already have one, we welcome your use of the CAE SimuFlite SOP. Chapter 3C Corporate pilots carefully developed this SOP. A product of their experience, it is the way CAE SimuFlite conducts its flight operations.
Page 164 CAE SimuFlite 3C-2 Citation Bravo Developed for Training Purposes September 2005...
Page 165 Pre-Departure Briefings ......3C-8 Advising of Aircraft Configuration Change ..3C-8 Transitioning from Instruments to Visual Conditions . . 3C-8 Citation Bravo 3C-3 Developed for Training Purposes...
Page 166 Landing ........3C-31 3C-4 Citation Bravo Developed for Training Purposes...
Page 167 The PF is responds to the bility for flight control of the air- aircraft to a safe operating envelope. craft, whether manual or automatic. checklist items designated as PF by visual confirmation oral response. Citation Bravo 3C-5 Developed for Training Purposes September 2005...
Page 168 The PM will be responsible action obtains verification from the for verifying checklists items as other pilot that he is moving the cor- appropriate. rect control or switch prior to initiat- ing the action. 3C-6 Citation Bravo Developed for Training Purposes September 2005...
Page 169 “Abort” and executes the announces the NAVAID to be set. In rejected takeoff procedure. tuning the primary NAVAID, in par- ticular, the PM coordinates with the PF to ensure proper selection Citation Bravo 3C-7 Developed for Training Purposes September 2005...
Page 170 However, the PF may request a changeover to visual traffic pattern callouts. 3C-8 Citation Bravo Developed for Training Purposes September 2005...
Page 171 ACTION Confirm assigned runway for takeoff and check heading indicator agreement CALL “Assigned runway confirmed, heading checked” CALL “Takeoff checklist.” ACTION Complete Takeoff checklist. CALL “Takeoff checklist complete.” Citation Bravo 3C-9 Developed for Training Purposes August 2010...
Page 172 CALL “70 kts crosscheck.” At V CALL “V .” ACTION Move hand from throttles to yoke. At V CALL “Rotate.” ACTION Rotate to a approximately 10 -12° pitch attitude for takeoff. 3C-10 Citation Bravo Developed for Training Purposes September 2005...
Page 173 At V2+10 KIAS (and upon reaching level-off altitude, if Single Engine) CALL “V +10 KIAS” CALL “Flaps up.” CALL “Flaps selected UP.” When indicator shows “Flaps indicate Up” Citation Bravo 3C-11 Developed for Training Purposes March 2009...
Page 174 CALL “Transition Altitude checklist complete.” At 1,000 Ft Below Assigned Altitude CALL “_____ (altitude) for ______ (altitude).” (e.g., “9,000 for 10,000.” CALL “_____ (altitude) for ______ (altitude).” (e.g., “9,000 for 10,000.” 3C-12 Citation Bravo Developed for Training Purposes September 2005...
Page 175 ACTION Complete Cruise checklist. CALL “Cruise checklist complete.” Altitude Deviation in Excess of 100 ft. CALL “Altitude.” CALL “Correcting.” Course Deviation in Excess of One Half Dot CALL “Course.” CALL “Correcting.” Citation Bravo 3C-13 Developed for Training Purposes September 2005...
Page 176 CALL “Altimeter set _____.” ACTION Complete Transition Level checklist. CALL “Transition Level checklist complete.” At 10,000 ft. CALL “10,000 ft.” CALL “Check. Speed 250 knots.” Maintain sterile cockpit below 10,000 ft. above airport surface. 3C-14 Citation Bravo Developed for Training Purposes September 2005...
Page 177 FAF altitude DA/MDA altitude field elevation missed approach heading altitude intentions abnormal implications Accomplish as many checklist items as possible. The Approach checklist must be completed prior to the initial approach fix. Citation Bravo 3C-15 Developed for Training Purposes September 2005...
Page 178 CALL “Localizer/course CALL “Localizer/course alive alive.”” At initial Downward Movement of Glideslope Raw Data Indicator CALL “Glideslope alive.” CALL “Glideslope alive.” When Annunciator Indicates Localizer Capture CALL “Localizer captured.” CALL “Localizer captured.” 3C-16 Citation Bravo Developed for Training Purposes September 2005...
Page 179 PM changes to the ILS frequency. This should be no later than at completion of the FAF crosscheck, if required. The PM should tune and identify his NAV radios to the specific approach and monitor. Citation Bravo 3C-17 Developed for Training Purposes September 2005...
Page 180 When within 500 ft. above touchdown, the aircraft must be within the approach window. If the aircraft is not within this window, a missed approach must be executed. 3C-18 Citation Bravo Developed for Training Purposes September 2005...
Page 181 PNF transitions to instruments. DA(H) CALL ”Minimums. Runway (or visual reference _____ o’clock.” ACTION Announces intentions. CALL “Going visual.Land.” or “Missed Approach.” ACTION As PF goes visual, PNF transitions to instruments Citation Bravo 3C-19 Developed for Training Purposes September 2005...
Page 182 CALL “Gear up.” CALL “Gear selected up.” When gear indicates up, “Gear indicates up.” ACTION Announce heading and altitude for missed approach, select PF’s Flight Director HDG mode, and arm FLC. 3C-20 Citation Bravo Developed for Training Purposes March 2009...
Page 183 At or Below V CALL “V .” or “V minus _____ (knots below V ).” CALL “Correcting.” Rate of Descent Exceeds 1,000 FPM CALL “Sink _____ (amount) hundred and (increasing, holding, decreasing).” CALL “Correcting.” Citation Bravo 3C-21 Developed for Training Purposes September 2005...
Page 184 When flaps indicate APPROACH, “Flaps indicate APPROACH.” At Initial Convergence of Course Deviation Bar CALL “localizer/course CALL “Localizer/course alive.” alive.” When Annunciators Indicate Course Capture CALL “Localizer/course CALL “Localizer/course captured.” captured.” 3C-22 Citation Bravo Developed for Training Purposes September 2005...
Page 185 (recommended 1,000 agree minimum, 1,500 Set minimum of 100 maximum vertical ft above MDA above) speed). in altitude alerter. Check PF and PM instruments. Call FAF inbound. Citation Bravo 3C-23 Developed for Training Purposes September 2005...
Page 186 ACTION Increase power for level (at or near power settings for level flight at initial altitude altitude prior to FAF). At 100 ft. Above MDA CALL “100 ft. to minimums.” CALL “Check.” 3C-24 Citation Bravo Developed for Training Purposes September 2005...
Page 187 CALL Going Visual. Land.” or “Missed Approach.” When leaving MDA, CALL “Flaps LAND.” CALL “Flaps selected LAND.” When flaps indicate LAND.” “Flaps indicate LAND.” CALL “Airspeed with relation to V and IVSI descent rate.” Citation Bravo 3C-25 Developed for Training Purposes September 2005...
Page 188 CALL “Gear up.” CALL “Gear selected up.” When gear indicates up, “Gear indicates up.” ACTION Announce heading and altitude for missed approach, select PF’s Flight Director HDG mode, and arm FLC 3C-26 Citation Bravo Developed for Training Purposes March 2009...
Page 189 CALL “Flaps selected UP.” When flaps indicate UP, “Flaps indicate UP.” At 1,500 ft. (Minimum) Above Airport Surface and Workload Permitting CALL “Climb checklist.” ACTION Complete Climb checklist. CALL “Climb checklist complete.” Citation Bravo 3C-27 Developed for Training Purposes March 2009...
Page 190 At or Below V CALL “V .” or minus _____ (knots below V .).” CALL “Correcting.” Descent is ±200 FPM of Briefed Rate CALL “Sink _____ (amount) hundred and (increasing, holding, decreasing).” CALL “Correcting.” 3C-28 Citation Bravo Developed for Training Purposes September 2005...
Page 191 CALL “Gear selected down.” When gear indicates down, “Gear indicates down.” ACTION Complete Before Landing checklist except for full flaps and yaw damper. CALL “Airspeed with relation to V and IVSI descent rate.” Citation Bravo 3C-29 Developed for Training Purposes September 2005...
Page 192 At 1,000 ft. Above Airport Surface CALL “1,000 ft. AGL.” CALL “Check.” At 500 ft. Above Airport Surface CALL “500 ft. AGL.” CALL “Check.” At 200 ft. Above Airport Surface CALL “2500 ft. AGL.” CALL “Check.” 3C-30 Citation Bravo Developed for Training Purposes September 2005...
Page 193 CALL “50 ft.” At Touchdown CALL “Extend Speedbrakes.” ACTION Extend speedbrakes CALL “Speedbrakes extended.” At Thrust Reverser Deployment CALL “Six Lights.” At Thrust Reverser Idle Speed (60 KIAS) CALL “60 kts. Idle Deploy.” Citation Bravo 3C-31 Developed for Training Purposes March 2009...
Page 194 CAE SimuFlite 3C-32 Citation Bravo Developed for Training Purposes March 2009...
Page 195 This chapter presents descriptions of various maneuvers and tech- niques applicable to normal and single engine operations. The second part of this chapter contains pictorial examples of selected Chapter 3D maneuvers. Citation Bravo 3D-1 For Training Purposes Only October 2013...
Page 196 3D-2 Citation Bravo For Training Purposes Only October 2013...
Page 197 Additional Instrument Systems ....3D-17 Normal Descent ......3D-17 Citation Bravo 3D-3...
Page 198 Normal Takeoff ......3D-29 Rejected Takeoff ......3D-31 3D-4 Citation Bravo For Training Purposes Only October 2013...
Page 199 Missed Approach ......3D-55 Flap Inoperative Approach and Landing (Zero Flap Approach and Landing) ... . . 3D-57 Citation Bravo 3D-5 For Training Purposes Only...
Page 200 3D-6 Citation Bravo For Training Purposes Only October 2013...
Page 201 Taxiing the turn with idle thrust. The addi- tional speed prevents the aircraft Operation Prior to taxiing the Citation Bravo, from stopping during the turn and complete all items of the Before Taxi then requiring excess thrust to move checklist. Obtain clearance from the again.
Page 202 Obtain the required takeoff power throughout a crosswind takeoff are settings from the manufacturer’s critical. The PF is responsible for AFM or from the CAE SimuFlite manipulating the control wheel and Citation Bravo Operating Hand- uses the conventional aileron into the book.
Page 203 ITT and RPM limits. from the same source as the cabin Observe the differential pressure/ underfloor ducting; use them as a cabin altitude and cabin vertical reference for temperature adjust- Citation Bravo 3D-9 For Training Purposes Only October 2013...
Page 204 7. If turbulence is penetrated with a dual flameout occurring. the autopilot on, engage the Soft 3D-10 Citation Bravo For Training Purposes Only October 2013...
Page 205 Steep Turns Refer to the profile on page 3D-37. Steep turns (e.g., 45° bank) confirm aerodynamic principle that Citation Bravo 3D-11 For Training Purposes Only October 2013...
Page 206 Speed brakes/Spoilers Retract Note: This will improve lift and stall margin. Return to desired Flight Path Note: Apply gentle action for recovery to avoid secondary stalls, and then return to desired flightpath. 3D-12 Citation Bravo For Training Purposes Only October 2013...
Page 207 6. Regain control of aircraft and a stall (i.e., airframe buffet, or stick recover to maneuvering speed and shaker, whichever occurs first), flight path appropriate for the air- simultaneously accomplish planes’s configuration Citation Bravo 3D-13 For Training Purposes Only October 2013...
Page 208 The pilot should also demonstrate will- Positive recovery from the aerody- ingness to trade altitude for airspeed namic stall or approach to stall takes 3D-14 Citation Bravo For Training Purposes Only October 2013...
Page 209 KIAS precedence over minimizing alti- Above 14,000 MSL 265 KIAS. tude loss.  If endurance is a factor, determine the recommended holding speed for the Citation Bravo 3D-15 For Training Purposes Only October 2013...
Page 210 Instrument Approach existing flight weight from the Hold- ing Chart in the CAE SimuFlite Cita- Considerations tion Bravo Operating Handbook or the Several factors should be considered manufacturer’s Performance Manual. prior to commencing an approach in Slow to holding speed within three a high performance jet aircraft.
Page 211 Continue to monitor the differential pressure, cabin altitude, and cabin vertical speed gauges throughout descent. The most comfortable con- dition occurs when cabin descent is distributed over the majority of the aircraft descent time. Citation Bravo 3D-17 For Training Purposes Only October 2013...
Page 212 FASTEN SEAT BELT sign and Before Landing checklist after turn- NO SMOKING sign illuminated, ing outbound from the approach fix. oxygen availability to passengers 3D-18 Citation Bravo For Training Purposes Only October 2013...
Page 213 5. Maintain airspeed at V Landing) +wind factor (V Refer to the profile on page 3D-57. The Citation Bravo has only one 6. At or before DA, establish visual approved flap position for landing contact with the runway. (full flaps). Landing with other than 7.
Page 214 5. Reduce power to climb N . At control wheel when deploying the the relatively light gross weight at trust reversers to prevent the aircraft 3D-20 Citation Bravo For Training Purposes Only October 2013...
Page 215 7. Confirm the level-off altitude and When flown at the correct approach heading/course needed airspeeds, the Citation Bravo nor- missed approach. Comply with the mally falls into Approach Category published missed approach instruc- B for straight in approaches. Due to...
Page 216 IDLE immediately if the aircraft ing the reverser levers in the idle starts to slide sideways. Strong con- thrust setting for FOD protection and sideration should be given for only noise abatement. REVERSE/IDLE slippery surfaces. 3D-22 Citation Bravo For Training Purposes Only October 2013...
Page 217 After Landing checklist. The engines should be operated at idle for at least one minute prior to shut- down; taxi time may be included. After the aircraft is parked, complete the Shutdown checklist. Citation Bravo 3D-23 For Training Purposes Only October 2013...
Page 218 3D-24 Citation Bravo For Training Purposes Only October 2013...
Page 219 If rudder trim is used during approach to counter asymmetric thrust, zero the rudder trim prior to or during the landing power reduction to prevent unwanted yaw. Thrust reduction and flare are similar to a normal landing. Citation Bravo 3D-25 For Training Purposes Only October 2013...
Page 220 , set climb power, then continue the climb on the published missed approach. When time permits, the PM sets the PF’s heading bug on the missed approach heading and selects the 3D-26 Citation Bravo For Training Purposes Only October 2013...
Page 221 Single Engine Non-Precision Approach and Landing  Go-Around/Missed Approach  Visual Approach/Balked Landing  Circling Approach  Single Engine Go-Around/Missed Approach  Flap Inoperative Approach and Landing (Zero Flap Approach  and Landing). Citation Bravo 3D-27 For Training Purposes Only October 2013...
Page 222 Citation Bravo 3D-28 For Training Purposes Only October 2013...
Page 223 Maneuvers Normal Static or Rolling Takeoff Citation Bravo 3D-29 For Training Purposes Only October 2013...
Page 224 Maneuvers Normal Static or Rolling Takeoff 3D-29 3D-30 Citation Bravo For Training Purposes Only October 2013...
Page 225 Maneuvers Rejected Takeoff Citation Bravo 3D-31 For Training Purposes Only October 2013...
Page 226 Maneuvers Rejected Takeoff 3D-31 3D-32 Citation Bravo For Training Purposes Only October 2013...
Page 227 Maneuvers Engine Failure Above V Citation Bravo 3D-33 For Training Purposes Only October 2013...
Page 228 Maneuvers Engine Failure Above V 3D-33 3D-34 Citation Bravo For Training Purposes Only October 2013...
Page 229 Maneuvers Steep Turns Citation Bravo 3D-35 For Training Purposes Only October 2013...
Page 230 Maneuvers Steep Turns 3D-35 3D-36 Citation Bravo For Training Purposes Only October 2013...
Page 231 Maneuvers Maneuver Based Approach to Stalls Citation Bravo 3D-37 For Training Purposes Only October 2013...
Page 232 Maneuvers 3D-37 3D-38 Citation Bravo For Training Purposes Only October 2013...
Page 233 Maneuvers Scenario Based Approach to Stalls Citation Bravo 3D-39 For Training Purposes Only October 2013...
Page 234 Maneuvers 3D-39 3D-40 Citation Bravo For Training Purposes Only October 2013...
Page 235 Maneuvers Typical Precision Approach and Landing Citation Bravo 3D-41 For Training Purposes Only October 2013...
Page 236 Maneuvers Typical Precision Approach and Landing 3D-41 3D-42 Citation Bravo For Training Purposes Only October 2013...
Page 237 Maneuvers Single Engine Precision Approach and Landing Citation Bravo 3D-43 For Training Purposes Only October 2013...
Page 238 Maneuvers Single Engine Precision Approach and Landing 3D-43 3D-44 Citation Bravo For Training Purposes Only October 2013...
Page 239 Maneuvers Typical Non-Precision Approach and Landing Citation Bravo 3D-45 For Training Purposes Only October 2013...
Page 240 Maneuvers Typical Non-Precision Approach and Landing 3D-45 3D-46 Citation Bravo For Training Purposes Only October 2013...
Page 241 Maneuvers Single Engine Non-Precision Approach and Landing Citation Bravo 3D-47 For Training Purposes Only October 2013...
Page 242 Maneuvers Single Engine Non-Precision Approach and Landing 3D-47 3D-48 Citation Bravo For Training Purposes Only October 2013...
Page 243 Maneuvers Go-Around/Missed Approach Citation Bravo 3D-49 For Training Purposes Only October 2013...
Page 244 Maneuvers Go-Around/Missed Approach 3D-49 3D-50 Citation Bravo For Training Purposes Only October 2013...
Page 245 Maneuvers Visual Approach/Balked Landing Citation Bravo 3D-51 For Training Purposes Only October 2013...
Page 246 Maneuvers Visual Approach Balked Landing) 3D-51 3D-52 Citation Bravo For Training Purposes Only October 2013...
Page 247 Maneuvers Circling Approach Citation Bravo 3D-53 For Training Purposes Only October 2013...
Page 248 Maneuvers Circling Approach 3D-53 3D-54 Citation Bravo For Training Purposes Only October 2013...
Page 249 Maneuvers Single Engine Go-Around/Missed Approach Citation Bravo 3D-55 For Training Purposes Only October 2013...
Page 250 Maneuvers Single Engine Go-Around/ Missed Approach 3D-55 3D-56 Citation Bravo For Training Purposes Only October 2013...
Page 251 Maneuvers Flaps Inoperative Approach and Landing Citation Bravo 3D-57 For Training Purposes Only October 2013...
Page 252 Maneuvers Flap Inoperative Approach and Landing 3D-57 3D-58 Citation Bravo For Training Purposes Only October 2013...
Page 253 Charts needed for any computations appear opposite the proce- Chapter 4 dural steps. While arm is read in inches and moment is read in inch-pounds, the notations “inches” or “in/lbs” are omitted. Citation Bravo Developed for Training Purposes September 2005...
Page 254 CAE SimuFlite Citation Bravo Developed for Training Purposes September 2005...
Page 255 Landing Weight and Moment ....4-52 Landing CG Limits ......4-54 Citation Bravo Developed for Training Purposes...
Page 256 Simplified Takeoff Criteria ..... . .4-96 Single Engine Takeoff Flight Path Distances ..4-97 Citation Bravo Developed for Training Purposes...
Page 257 Bravo Operating Manual for long range cruise information. For maximum groundspeed considerations, this chapter assumes Citation Bravo maximum thrust setting for the atmospheric condi- tions present for the cruise leg to the primary destination and maximum range cruise setting for the leg to the alternate.
Page 258 CAE SimuFlite Citation Bravo Developed for Training Purposes September 2005...
Page 259 Headwind Component ....... . 0 KTS Distance From Destination ......100 NM Citation Bravo Developed for Training Purposes...
Page 260 CAE SimuFlite Citation Bravo Developed for Training Purposes September 2005...
Page 261 11,898 lbs (14,800 lbs minus summary estimate burn of 2,902 lbs). Assume the aircraft has executed a missed approach and must now climb to altitude for the trip to the alternate. Citation Bravo Developed for Training Purposes September 2005...
Page 262 CAE SimuFlite 4-10 Citation Bravo Developed for Training Purposes September 2005...
Page 263 This yields summary estimates of 3.3 hrs and 4,412 lbs fuel. After aircraft loading and flight plan fuel requirements are determined, takeoff, climb, and landing gross weights should be rechecked for com- pliance with Flight Manual criteria. Citation Bravo 4-11 4-12 Developed for Training Purposes...
Page 264 CAE SimuFlite Maximum Cruise Thrust\ Ignition System 19,000 Feet 19,000 Feet Conditions Cruise – 85.1% N1 Conditions: Anti-ice Systems – OFF Two Engines Operating 4-1A 4-1B 4-12 Citation Bravo Developed for Training Purposes September 2005...
Page 265 A takeoff weight of 14,800 lbs is desired; the additional weight above the basic empty weight, payload, and minimum fuel requirement is composed of tankered fuel. Citation Bravo 4-13 Developed for Training Purposes September 2005...
Page 266 5. Add or subtract the correction factor to/from the previously deter- mined climb distance. Because this is a headwind correction, subtracting 10 NM from 114 yields the corrected climb distance, or 104 NM. 4-14 Citation Bravo Developed for Training Purposes September 2005...
Page 267 Flight Planning Cruise Climb Time, Distance, Fuel, and Rate of Climb CONDITIONS: Speed – 220 KIAS Pressure Altitude – SEA LEVEL Anti-Ice Systems – OFF Citation Bravo 4-15 Developed for Training Purposes September 2005...
Page 268 The climb distance previously determined is 104 NM. The descent L = Climb Distance distance previously determined is 90 NM. Thus, the cruise distance D = Descent Distance is 606 NM (800 minus (104 plus 90) equals 606). 4-16 Citation Bravo Developed for Training Purposes September 2005...
Page 269 Anti-ice Systems – OFF* Gear – UP Fuel Consumption – 600 LBS/HR Flaps – UP (300 LBS/HR/ENGINE) * When the anti-ice systems are ON, decrease 6%. Time and fuel used remain the same Citation Bravo 4-17 Developed for Training Purposes September 2005...
Page 270 3. Move to the right to the forecast cruise wind column (50 kts head- total cost. Hence the saying, “fuel wind) and read the specific range in nautical miles/100 lbs fuel is cheap.” (40.3). 4-18 Citation Bravo Developed for Training Purposes September 2005...
Page 271 Flight Planning Cruise 39,000 Feet CONDITIONS: Anti-ice Systems – OFF Two Engines Operating Citation Bravo 4-19 Developed for Training Purposes September 2005...
Page 272 For a longer trip length, the time at cruise should be based on the true airspeed for each subsequent hour. As the aircraft weight decreases the true airspeed increases with the same power setting. 4-20 Citation Bravo Developed for Training Purposes September 2005...
Page 273 Flight Planning Cruise 39,000 Feet CONDITIONS: Anti-ice Systems – OFF Two Engines Operating Citation Bravo 4-21 Developed for Training Purposes September 2005...
Page 274 4. Add the fuel values to determine fuel required at cruise. Adding the 917 lbs for the first hour to the 804 lbs for the final 52 minutes yields a total cruise fuel consumption of 1,721 lbs. 4-22 Citation Bravo Developed for Training Purposes September 2005...
Page 275 Flight Planning Cruise 39,000 Feet CONDITIONS: Anti-ice Systems – OFF Two Engines Operating Citation Bravo 4-23 Developed for Training Purposes September 2005...
Page 276 That is, 40% of the distance to the alternate is in the descent. The fuel required to the alternate airport is the sum of the fuel requirements for the climb, cruise, and descent segments enroute to the alternate. 4-24 Citation Bravo Developed for Training Purposes September 2005...
Page 277 Gear – UP Fuel Consumption – 600 LBS/HR Flaps – UP (300 LBS/HR/ENGINE) * When the anti-ice systems are ON, decrease the distance 6%. Time and fuel used remain the same. Citation Bravo 4-25 Developed for Training Purposes September 2005...
Page 278 12,313 lbs, interpolate between 12,000 lbs and 13,000 lbs. 2. Read the data block. The figures for the alternate climb are 6 minutes, 22 NM, and 193 lbs of fuel. 4-26 Citation Bravo Developed for Training Purposes September 2005...
Page 279 Flight Planning Cruise Climb Time, Distance, Fuel and Rate of Climb CONDITIONS: Speed – 220 KIAS Pressure Altitude – SEA LEVEL Anti-ice Systems – OFF Citation Bravo 4-27 Developed for Training Purposes September 2005...
Page 280 The cruise time is 0.1141 hours, thus 0.1141 times 1,234 is 141 lbs. 6. Add fuel and time values for all alternate segments. Flight Segment Time (Minutes) Fuel (lbs) Climb 6.00 Cruise 7.00 Descent 9.50 TOTAL 22.50 4-28 Citation Bravo Developed for Training Purposes September 2005...
Page 281 Flight Planning Cruise 19,000 Feet CONDITIONS: Anti-ice Systems – OFF Two Engines Operating Citation Bravo 4-29 Developed for Training Purposes September 2005...
Page 282 Alternate 0:22.5 Reserve + 829 TOTAL FUEL REQUIRED 4,008 2:58 The original estimates of the trip time and fuel requirements were 3.3 hrs (or 3:18 hrs/min) and 4,421 lbs of fuel. 4-30 Citation Bravo Developed for Training Purposes September 2005...
Page 283 Flight Planning Cruise 19,000 Feet CONDITIONS: Anti-ice Systems – OFF Two Engines Operating 4-10 Citation Bravo 4-31 Developed for Training Purposes September 2005...
Page 284 CAE SimuFlite 4-32 Citation Bravo Developed for Training Purposes September 2005...
Page 285 Precise weight and balance computations are essential elements of flight planning. Accuracy of these computations helps to ensure a safe Balance flight. This section reviews the procedures for computing weight and balance data. Citation Bravo 4-33 Developed for Training Purposes September 2005...
Page 286 Landing weight is limited by the most restrictive of: maximum certified landing weight maximum landing weight permitted by climb require- ments or brake energy limit landing distance. 4-34 Citation Bravo Developed for Training Purposes September 2005...
Page 287 100 equals 295.75.) Note that you do not have to enter the Center-of-Gravity Limits Envelope Graph at this time. Record this information on the Weight and Balance form, hereafter referred to as the loading schedule (Figure 4-13). Citation Bravo 4-35 4-36 Developed for Training Purposes...
Page 288 THRUST SETTING MAXIMUM COMPARE AND SELECT ANTI-ICE ON OR OFF? STRUCTURAL LOWEST WEIGHT WEIGHT LIMITS FINISHED TAKEOFF / GO-AROUND THRUST SETTING MAXIMUM CONTINOUS THRUST SETTING ANTI- ICE ON OR OFF? FINISHED 4-36 Citation Bravo Developed for Training Purposes September 2005...
Page 289 Flight Planning Weight and Balance Form (Loading Schedule) Citation Bravo WEIGHT MOMENT/ ITEM PAYLOAD COMPUTATION S (POUNDS) WEIGHT MOMENT/ ITEM 1. BASIC EMPTY WEIGHT (INCHES) (POUNDS) * Airplane CG = _______ 295.75 8,850 26,173.88 OCCUPANTS PAYLOAD PILOT 131.0 ZERO FUEL WEIGHT...
Page 290 3. Add all weights and moments to arrive at total payload figures. Transfer the information to the appropriate columns and rows of the loading schedule (Figure 4-15 Weight Moment Baggage 371.80 Crew 471.05 Passengers 1,030 2,680.05 Cabinet 80.88 TOTAL 1,600 3,604.33 4-38 Citation Bravo Developed for Training Purposes September 2005...
Page 291 (10,450 lbs) derives the CG arm. Then, multiply the result by 100 to yield the aircraft’s Center-of-Gravity in inches (284.95). Note that you do not have to enter the Center-of Gravity Limits Envelope Graph at this time, Citation Bravo 4-39 4-40 Developed for Training Purposes...
Page 292 Weight and Balance Record for information. (Subtotal) * * *Enter the Center-of-Gravity Limits Envelope Graph to veri - fy airplane is loaded within approved limits. 58.10 4-15 NOTE : Fuel weight 4-14 based on 6.75 lbs/gal. 4-40 Citation Bravo Developed for Training Purposes September 2005...
Page 293 Weighing Form. If the airplane has been altered, refer to (Subtotal) the Weight and Balance Record for information. * * *Enter the Center-of-Gravity Limits Envelope Graph to veri- fy airplane is loaded within approved limits. 4-16 Citation Bravo 4-41 Developed for Training Purposes September 2005...
Page 294 5113.50 4300 12,324.58 4400 12,614.68 1900 5399.84 2000 5686.38 4500 12,904.81 2100 5973.10 4600 13,195.06 2200 6260.01 4700 13,485.06 2300 6547.09 4800 13,774.99 2400 6834.36 4860 13,948.20 2500 7121.76 4-17 4,550 4-42 Citation Bravo Developed for Training Purposes September 2005...
Page 295 Weighing Form. If the airplane has been altered, refer to (Subtotal) the Weight and Balance Record for information. * * *Enter the Center-of-Gravity Limits Envelope Graph to veri- fy airplane is loaded within approved limits. 4-18 Citation Bravo 4-43 Developed for Training Purposes September 2005...
Page 296 100 to yield the Center-of-Gravity in inches (285.52). Note that you do not have to enter the Center-of-Gravity Limits Envelope Graph at this time. Record these values on the loading schedule ( Figure 4-19 4-44 Citation Bravo Developed for Training Purposes September 2005...
Page 297 Weighing Form. If the airplane has been altered, refer to (Subtotal) the Weight and Balance Record for information. * * *Enter the Center-of-Gravity Limits Envelope Graph to veri- fy airplane is loaded within approved limits. 4-19 Citation Bravo 4-45 Developed for Training Purposes September 2005...
Page 298 1800 5113.50 4300 12,324.58 1900 5399.84 4400 12,614.68 2000 5686.38 4500 12,904.81 4600 13,195.06 2100 5973.10 2200 6260.01 4700 13,485.06 2300 6547.09 4800 13,774.99 2400 6834.36 4860 13,948.20 4-20 2500 7121.76 4-46 Citation Bravo Developed for Training Purposes September 2005...
Page 299 Weighing Form. If the airplane has been altered, refer to (Subtotal) the Weight and Balance Record for information. * * *Enter the Center-of-Gravity Limits Envelope Graph to veri- fy airplane is loaded within approved limits. 4-21 Citation Bravo 4-47 Developed for Training Purposes September 2005...
Page 300 Projecting up from 285.46 to the takeoff weight (14,800 lbs) confirms that the aircraft is within limits for takeoff. 3. Record takeoff weight CG on the loading schedule ( Figure 4-24 4-48 Citation Bravo Developed for Training Purposes September 2005...
Page 301 Flight Planning Center of Gravity Limits 14,800 lbs 42,248.84 285.46 4-22 Citation Bravo 4-49 Developed for Training Purposes September 2005...
Page 302 4300 12,324.58 1,863 5,293.89 1900 5399.84 4400 12,614.68 2000 5686.38 4500 12,904.81 2100 5973.10 4600 13,195.06 2200 6260.01 4700 13,485.06 2300 6547.09 4800 13,774.99 2400 6834.36 4860 13,948.20 2500 7121.76 4-23 4-50 Citation Bravo Developed for Training Purposes September 2005...
Page 303 Weighing Form. If the airplane has been altered, refer to (Subtotal) the Weight and Balance Record for information. * * *Enter the Center-of-Gravity Limits Envelope Graph to veri- fy airplane is loaded within approved limits. 4-24 Citation Bravo 4-51 Developed for Training Purposes September 2005...
Page 304 CG limits for takeoff. Projecting up from 284.84 to 12,313 lbs confirms that the aircraft is within limits for landing. 3. Record landing weight CG on the loading schedule Figure 4-26 4-52 Citation Bravo Developed for Training Purposes September 2005...
Page 305 Flight Planning Center of Gravity Limits 12,313 LBS 35,072.10 284.84 4-25 Citation Bravo 4-53 Developed for Training Purposes September 2005...
Page 306 Weighing Form. If the airplane has been altered, refer to (Subtotal) the Weight and Balance Record for information. * * *Enter the Center-of-Gravity Limits Envelope Graph to veri- fy airplane is loaded within approved limits. 4-26 4-54 Citation Bravo Developed for Training Purposes September 2005...
Page 307 Both throttles were brought to idle immediately after brake application. Directional control was maintained through the rudder pedals and differential braking as required. Citation Bravo 4-55 Developed for Training Purposes September 2005...
Page 308 The pressure at sea level (standard datum plane) is 29.92 inHg (1013.2 Mb). The temperature gradient from sea level to the altitude at which the temperature is –56.6° C will be –1.98° C per 1,000 ft. 4-56 Citation Bravo Developed for Training Purposes September 2005...
Page 309 Reference zero – The point in the takeoff flight path at which the air- craft is 35 ft above the takeoff surface and at the end of the takeoff dis- tance required. Citation Bravo 4-57 Developed for Training Purposes September 2005...
Page 310 VMCA is a function of engine thrust, which varies with altitude and tempera- ture. The VMCA presented in AFM Section IV was determined for maximum thrust. VMCA = 78 KIAS. 4-58 Citation Bravo Developed for Training Purposes September 2005...
Page 311 Wind – The wind velocities recorded as variables on the charts of the AFM are understood as the headwind or tailwind components of the actual winds at 30 ft above the runway surface (i.e., tower winds). Citation Bravo 4-59 Developed for Training Purposes...
Page 312 CAE SimuFlite 4-60 Citation Bravo Developed for Training Purposes September 2005...
Page 313 ZF – RWY RQD – Computed Landing Field Length GROSS WEIGHT– Landing Weight NOTES: FLAPS – Landing Flap Setting PWR – Takeoff/Go-Around N Thrust Setting Approach Climb Speed APP – NOTES Citation Bravo 4-61 Developed for Training Purposes September 2005...
Page 314 3. Move left to the edge of the chart to obtain the headwind/tailwind component (14 kts). 4. Move down from the intersection to the bottom of the chart to obtain the crosswind component (5 kts). The maximum demonstrated crosswind is not exceeded. 4-62 Citation Bravo Developed for Training Purposes September 2005...
Page 315 Flight Planning Crosswind Component 4-27 Citation Bravo 4-63 Developed for Training Purposes September 2005...
Page 316 1. Enter the appropriate altitude block (2,000 ft) from the left at the ambient temperature (20°). 2. Read the maximum takeoff weight permitted by climb requirements. In this case, the maximum allowable weight is 14,800 lbs for either flap setting. 4-64 Citation Bravo Developed for Training Purposes September 2005...
Page 317 Pounds Permitted by Climb Requirements CONDITIONS: Anti-ice Systems – OFF Flaps – 15° Where conditions allow for 0° or 15° setting. 15° flap setting is desired for the shorter takeoff distance. 4-29 Citation Bravo 4-65 Developed for Training Purposes September 2005...
Page 318 7. Check the Takeoff Correction factors ( ) for any needed Figure 4-32 GROSS WEIGHT adjustments. 14,800 FLAPS In this case, no adjustments are required for runway gradient or anti-ice systems. POWER CLIMB 4,200 RETURN CLEARANCE 4-66 Citation Bravo Developed for Training Purposes September 2005...
Page 319 V With flaps 15°, the obstacle is 5,900 ft from reference zero Ta keoff prohibited for corrected takeoff field lengths greater than 11,000 ft. (4,800 plus 1,100 equals 5,900). 4-32 Citation Bravo 4-67 4-68 Developed for Training Purposes September 2005...
Page 320 Some conditions do not meet climb requirements. Obtain allowable weight from maximum takeoff weight tables Some conditions do not meet climb requirements. Obtain allowable weight from maximum takeoff weight tables 4-30 4-31 4-68 Citation Bravo Developed for Training Purposes September 2005...
Page 321 DOWN TRANSITION TO UP WING FLAP DEGREES 15 TRANSITIONING TO UP SPEED BRAKES RETRACT RETRACT RETRACT INOPERATIVE ENGINE WINDMILLING WINDMILLING WINDMILLING 4-33 OPERATIVE ENGINE TO THRUST TO THRUST TO THRUST AIRSPEED TRANSITIONING TO V Citation Bravo 4-69 Developed for Training Purposes March 2009...
Page 322 6.13% gradient is required. If a flaps 15° takeoff is required due to a short runway, the aircraft weight must be reduced below 14,800 lbs to clear the obstacle. 4-70 Citation Bravo Developed for Training Purposes March 2009...
Page 323 When comparing flap setting performance for both aircraft at the same weight and atmospheric conditions, remember that a flaps 15° aircraft always requires a shorter takeoff field length; a flaps 0° always requires a greater climb gradient. Citation Bravo 4-71 4-72 Developed for Training Purposes September 2005...
Page 324 Landing Gear – UP Inoperative Engine – WINDMILLING Landing Gear – UP Inoperative Engine – WINDMILLING Speedbrakes – RETRACTED Operative ENgine – TAKEOFF THRUST Speedbrakes – RETRACTED Operative – TAKEOFF THRUST 4-34 4-35 4-72 Citation Bravo Developed for Training Purposes September 2005...
Page 325 Single Engine Takeoff Flight Path – Flaps 15° First and Second Segment, 35 FT to 400 FT CONDITIONS: Landing Gear – DOWN/UP Airspeed – V Speedbrakes – RETRACTED Inoperative Engine – WINDMILLING Operative Engine – TAKEOFF THRUST 4-37 Citation Bravo 4-73 Developed for Training Purposes July 2004...
Page 326 From this example using the FAR Part 135 factor, the aircraft 4,800 landing weight must be lowered to meet the 5,300 ft of runway RETURN length. CLEARANCE Enter the Emergency Return V of 117 on the TOLD card. 4-74 Citation Bravo Developed for Training Purposes July 2004...
Page 327 To obtain landing distance with negative (downhill) runway gradient, refer to landing procedures . • For use in an emergency that requires a landing at weight in excess of the maximum design landing weight of 13,500 pounds . 4-38 Citation Bravo 4-75 Developed for Training Purposes...
Page 328 2. Move left to the edge of the chart and read the fan speed (86.9% N 4-76 Citation Bravo Developed for Training Purposes July 2004...
Page 329 4. Move down to the bottom of the chart from the intersection to obtain the crosswind component. NOTES: The crosswind component is less than 3.5 kts; for conservatism, use 4 kts. The maximum demonstrated crosswind component is not exceeded. 4-41 Citation Bravo 4-77 4-78 Developed for Training Purposes September 2005...
Page 330 CAE SimuFlite Takeoff/Go-Around Thrust Setting Maximum Continuous Thrust Settingt Conditions: Anti-ice Systems – OFF 90.7 % 86.9% 4-40 4-39 4-78 Citation Bravo Developed for Training Purposes September 2005...
Page 331 Crosswind Component KT S 3. 5 KT S 4-42 Citation Bravo 4-79 Developed for Training Purposes September 2005...
Page 332 (2%),. Read the maximum landing weight wight permitted. The maximum lading weight for all gradients shown is 13,500 lbs. The landing weight for this example, 12.313 lbs is well below the limit. 4-80 Citation Bravo Developed for Training Purposes September 2005...
Page 333 Maximum Landing Weight Pounds Permitted by Climb Requirements or Brake Energy Limits CONDITIONS: Anti-ice Systems – OFF Landing Flaps – FULL Landing Gear – UP Approach Flaps – 15° Speedbrakes – RETRACTED 4-43 Citation Bravo 4-81 Developed for Training Purposes September 2005...
Page 334 107 + 10 + 10 + 0 = 127 KIAS Find V by adding 30 kts to V 107 + 30 = 137 8. Enter this information on the TOLD card. 4-82 Citation Bravo Developed for Training Purposes September 2005...
Page 335 Thrust – IDLE Airspeed – V At 50 FT Speedbrakes – EXTEND AFTER TOUCHDOWN Some conditions may be brake energy of climb limited. Obtain allowable weight form maximum landing weight tables 4-44 Citation Bravo 4-83 Developed for Training Purposes September 2005...
Page 336 2. Move left to the edge of the chart to obtain the fan speed (89.8% N1). GROSS WEIGHT 12,500 3. Enter this number in the GO AROUND PWR block of the TOLD card. FLAPS FULL GO AROUND 89.8% 4,600 NOTES: 4-84 Citation Bravo Developed for Training Purposes September 2005...
Page 337 Flight Planning Takeoff/Go Around Thrust Setting 89.8% 25°C 4-45 Citation Bravo 4-85 Developed for Training Purposes September 2005...
Page 338 CAE SimuFlite 4-86 Citation Bravo Developed for Training Purposes September 2005...
Page 339 This section provides information for specific instances outside normal routines addressed elsewhere in this manual. These procedures provide Information an awareness and understanding of situations that may be encountered and should not be confused with normal performance procedures. Citation Bravo 4-87 Developed for Training Purposes September 2005...
Page 340 The approach climb gradient initially is 9.6%; because the anti-ice systems are on, this is reduced by 3 to 6%. The landing climb gradient initially is 27.8%; because the anti-ice systems are on, this is reduced by 6 to 17%. 4-88 Citation Bravo Developed for Training Purposes September 2005...
Page 341 0.4 inches of water. 8. If the adjusted V is greater than V , the value of V must be used for V Citation Bravo 4-89 4-90 Developed for Training Purposes September 2005...
Page 342 * To obtain approach climb gradients with anti-ice ON, reduce the following gradients by 3 to 6%. * To obtain approach climb gradients with anti-ice ON, reduce the following gradients by 6 to 17% 4-46 4-47 4-90 Citation Bravo Developed for Training Purposes September 2005...
Page 343 81.7% RPM 81.7% RPM Climb Fan Table 4-D; Simplified takeoff Criteria When conditions are other than those specified in the simpli- fied criteria, the appropriate tabulated data must be referenced. Citation Bravo 4-91 4-92 Developed for Training Purposes September 2005...
Page 344 Landing distance is 2,980 ft multiplied by 2.4, or 7,152 ft. (3) * For use in an emergency that requires a landing a landing at weight in excess of the maximum design landing weight of 13,500 lbs. 4-49 4-92 Citation Bravo Developed for Training Purposes September 2005...
Page 345 35 to 1,500 ft. All of these tables function in the same manner. Review the flight segments as they appear below ( Figure 4-50) Each of the flight segments has a distinctive configuration. 4-50 Citation Bravo 4-93 Developed for Training Purposes September 2005...
Page 346 Horizontal Distance to End of Acceleration Segment ..14,921 FT Total Horizontal Distance to 1,500 Ft....46,222 FT 4-94 Citation Bravo Developed for Training Purposes September 2005...
Page 347 Flight Planning Single Engine Takeoff Flight Path Distances – Feet Flaps 15°/4000 Ft CONDITIONS: Refer to page preceding this table 4-51 Citation Bravo 4-95 Developed for Training Purposes September 2005...
Page 348 CAE SimuFlite 4-96 Citation Bravo Developed for Training Purposes September 2005...
Page 349 Pneumatic (36) ......PNEUMATIC Pressurization (21) ......PNEUMATIC Citation Bravo Developed for Training Purposes...
Page 350 Windows (56) ....AIRCRAFT OVERVIEW Wings (57) ..... . AIRCRAFT OVERVIEW Citation Bravo Developed for Training Purposes...
Page 351 Unit numbers are assigned consecutively as construction begins; each number remains with its aircraft regardless of the model serial number later assigned. On all Citation Bravo model aircraft, both the serial and unit num- ber are stamped into the aircraft identification plate. Citation Bravo...
Page 352 CAE SimuFlite 5A-2 Citation Bravo Developed for Training Purposes July 2004...
Page 353 Engine Exhaust Plume ......5A-21 Service Bulletins......5A-23 Citation Bravo 5A-3...
Page 354: Aircraft Features Diagram
WINDOW EMERGENCY EXIT CABIN DOOR WING PYLON NACELLE SPEEDBRAKE AILERON AILERON FLAP TRIM TAB HORIZONTAL STABILIZER RAM AIR INLETS ELEVATOR RUDDER VERTICAL ELEVATOR STABILIZER TRIM TAB VERTICAL FIN RUDDER TRIM TAB 5A-4 Citation Bravo Developed for Training Purposes July 2004...
Page 355 550-0801 thru -0808 incorporating SB 550- 03-03 and SB 550-34-70, 550-0809 thru - 0820, -0822, and -0823 incorporating SB 550-34-64 and SB 550-34-70 and 550-0821,-0824, -0825 and 550-0826 thru -0847 incorporating SB 550-34-70. Citation Bravo 5A-5 Developed for Training Purposes July 2004...
Page 356: Airplane Configuration Codes
Due to Situations that change on a day-to-day basis, the manufacturer may issue new service bulletins requiring the creation of new/additional configuration codes. Consult you AFM for the most recent codes. 5A-6 Citation Bravo Developed for Training Purposes March 2009...
Page 357: Airframe Description
Aircraft Overview Airframe The Cessna Citation Bravo is certified pylon skin. In addition, seals separate in accordance with FAR Part 25 air- the pylons from thrust reverser fair- Description worthiness standards for two pilots, ings. Fuel and hydraulic lines mount...
Page 358: Pressurized Compartment
0.05 inch ing the manual switch to OFF thick; and an inner pane of stretched removes power from the light. acrylic 0.414 inch thick. 5A-4 5A-3 5A-5 5A-8 Citation Bravo Developed for Training Purposes July 2004...
Page 359: Entrance Door
The window opens a retainer that forms a continuous inward by releasing a latch at the top ring around the door. 5A-7 5A-6 5A-8 Citation Bravo 5A-9 Developed for Training Purposes July 2004...
Page 360 CABIN DOOR (not locked) cir- until a spring-loaded door stop holds cuit and the DOOR SEAL (not the door open, then return the handle inflated) circuit. to the stowed position. 5A-9 5A-11 5A-10 5A-10 Citation Bravo Developed for Training Purposes March 2009...
Page 361: Optional Cargo Door
The locking mechanism at the bottom of the door. for each door operates independently. 5A-12 Citation Bravo 5A-11 Developed for Training Purposes July 2004...
Page 362: Emergency Exit
A rubber surized using bleed air from the bulb-type seal around the edge of the door provides a pressure seal. Holes engines. Inspection holes for the 5A-14 5A-13 5A-12 Citation Bravo Developed for Training Purposes July 2004...
Page 363: Passenger Compartment
An center and forward seats may face overhead compartment above the forward or aft, depending on config- lighted work area provides addi- uration. Foldout tables are available tional storage. 5A-15 5A-16 Citation Bravo 5A-13 Developed for Training Purposes July 2004...
Page 364: Aft Cabin Baggage Compartment
5A-19 5A-17 5A-18 5A-14 Citation Bravo Developed for Training Purposes July 2004...
Page 365: Tailcone Baggage Compartment
Each wing attaches to the stub (Figure 5A-22). tailcone wing with upper and lower main and equipment access door is on the tail rear spar fittings. 5A-20 5A-21 5A-22 Citation Bravo 5A-15 Developed for Training Purposes July 2004...
Page 366: Fuel Tanks
Each 360 gallon tank has an and rudder trim tab. overwing fueling port (Figure 5A-26). 5A-24 5A-23 5A-25 5A-26 5A-16 Citation Bravo Developed for Training Purposes July 2004...
Page 367 A tailskid on the lower aft portion of avionics flux detector cable assem- the tail section (Figure 5A-28) pre- bly connectors, and deice boot vents fuselage damage if overrota- assemblies. tion occurs. 5A-27 5A-28 Citation Bravo 5A-17 Developed for Training Purposes July 2004...
Page 368 CAE SimuFlite 5A-18 Citation Bravo Developed for Training Purposes July 2004...
Page 369: Aircraft Dimensions
Forward Divider to Aft Pressure Bulkhead ..20.90 Feet Height, Aisle to Ceiling ..... 4.75 Feet 19.00 FEET Citation Bravo 5A-19 Developed for Training Purposes...
Page 370 CAE SimuFlite 5A-20 Citation Bravo Developed for Training Purposes July 2004...
Page 371: Danger Areas
The draw increases close to sonnel, small articles, and sensitive the nacelle. equipment. ENGINE INTAKE WEATHER RADAR OPERATING ENGINE EXHAUST 9' 0" 45' 0" 35' 0" 240' 0" 5A-29 Citation Bravo 5A-21 Developed for Training Purposes July 2004...
Page 372 CAE SimuFlite 5A-22 Citation Bravo Developed for Training Purposes July 2004...
Page 373: Service Bulletins
Meggitt Standby Flight Display Improvements UNITS: 0809 to 0820, 0822 and 0823 SB550-11-01-M T ype (Added Code) Sequential Number fo r AT A Code AT A Code Service Bulletin Identifier/ Aircraft Model 5A-30 Citation Bravo 5A-23 Developed for Training Purposes July 2004...
Page 374 CAE SimuFlite 5A-24 Citation Bravo Developed for Training Purposes July 2004...
Page 375 For a detailed description of and operating procedures for a par- ticular piece of equipment, refer to the applicable pilot’s guide. Citation Bravo 5B-1 Developed for Training Purposes Septmember 2005...
Page 376 CAE SimuFlite 5B-2 Citation Bravo Developed for Training Purposes Septmember 2005...
Page 377 Marker Beacon Receivers ....5B-33 Automatic Direction Finder ....5B-34 Citation Bravo 5B-3...
Page 378 EADI Caution/Failure Annunciations ... 5B-66 EADI Displays and Annunciations ... . . 5B-66 5B-4 Citation Bravo Developed for Training Purposes Septmember 2005...
Page 379 Dual PFD Attitude Failure ....5B-91 Autopilot Hardover ......5B-91 Citation Bravo 5B-5...
Page 380 PRESS SOURCE AUX GEAR CONTROL 1. PULL & TURN NORMAL AUTO CKPT CABIN TEE HANDLE 45° CW TO DOWN UNLOCK 2. PULL ROUND FLOWDISTR PRESS SYSTEM SELECT KNOB TO BLOW GEAR DOWN 5B-6 Citation Bravo Developed for Training Purposes March 2009...
Page 381 Avionics CAE SimuFlite Center Pedestal and Side Consoles Citation Bravo 5B-7 5B-8 Developed for Training Purposes September 2005...
Page 382 GAIN RADA ONLY COURSE HEADING COURSE EMER EMER HEAD OXYGEN HEAD OXYGEN MASK PUSH PUSH PUSH MASK SYNC PHONE PHONE OXYGEN CONTROL HEADSET HEADSET BANK LIMIT DESCEND TURN CLIMB ENGAG ENGAG 5B-8 Citation Bravo Developed for Training Purposes March 2009...
Page 383: Pitot/Static System Schematic
AZ-850 AIR DATA AIR DATA PROBE COMPUTER COMPUTER DECODER UPPER UPPER PORT PORT MIDDLE MIDDLE ELECTRICAL PORT PORT PITOT PRESSURE LOWER LOWER STATIC STATIC PORT PORT STATIC PRESSURE PORTS PORTS Citation Bravo 5B-9 5B-10 Developed for Training Purposes September 2005...
Page 384 CAE SimuFlite Primus System Diagram C-14D 5B-10 Citation Bravo Developed for Training Purposes March 2009...
Page 385: Flight Data Systems
Avionics Flight Data The Citation Bravo is equipped with Of these six functional groups, the a Honeywell Primus 1000 Integrated airspeed, altitude, and vertical speed Systems Avionics Flight Guidance System, displays are addressed in this sec- which is a complete automatic flight tion.
Page 386 The Emergency bus provides 28V DC for the standby pitot/static anti-ice system. 5B-5 5B-6 5B-7 5B-12 Citation Bravo Developed for Training Purposes March 2009...
Page 387: Air Data System
DIGITAL DISPLAY DISPLAY 9 AIRSPEED VSPEED V SPEED BUGS DIGITAL DISPLAY DISPLAY .410 M .410 M 8 MACH DISPLAY 8 MACH DISPLAY LOW SPEED LOW SPEED AWARENESS BAR AWARENESS BAR 5B-8 Citation Bravo 5B-13 Developed for Training Purposes March 2009...
Page 388 ) horn prediction of what the airspeed will sounds until the airspeed is reduced be in ten seconds if the current rate below the limit speed. of change is maintained. 5B-10 5B-9 5B-14 Citation Bravo Developed for Training Purposes March 2009...
Page 389 When the airspeed trend vector Label Color Speed Definition SPEED Magenta Takeoff Decision Cyan Takeoff Rotations White Takeoff Safety Cyan Single Engine Enroute Climb Magenta Approach Green Landing Configuration Table 5B-A; V Bug Identification SPEED Citation Bravo 5B-15 Developed for Training Purposes March 2009...
Page 390 As the V are set on SPEEDS digits, tick marks, and chevrons, and the MFD menu, the digital readouts places a red X over the tape. follow the readout on the MFD and 5B-16 Citation Bravo Developed for Training Purposes March 2009...
Page 391: Altitude Display
AND SCALE LINE BELOW 10000 FEET MARK 14000 ALTITUDE LOW ALTITUDE BAROMETRIC SELECT BUG AWARENESS ALTIMETER SETTING 29.92 IN 29.92 IN INCHES METRIC 3047 M 3047 M HECTOPASCALS ALTITUDE DIGITAL 5B-11 DISPLAY Citation Bravo 5B-17 Developed for Training Purposes September 2005...
Page 392 TA 14.5 - 12 VOR1 ° 27.4 1000 TCAS 45.0 AUTO 1000 GSPD VOR2 STAB GSPD VNAV VSPEEDS TERR BARO ALTITUDE BAROMETRIC PRESELECT ADJUSTMENT GSPD 5B-12 5B-18 Citation Bravo Developed for Training Purposes September 2005...
Page 393: Vertical Speed Display
Vertical Speed Display Vertical speed data is developed in the MADCs, the IC-600 DGCs, for- wards the digital formatted data to the PFDs where it is generated into a visual display. Citation Bravo 5B-19 Developed for Training Purposes March 2009...
Page 394: Standby Airspeed/Altitude/Attitude/Indicator
A moving tape, calibrated REFERENCE LINE in 100-ft increments, on the right VS DIGITAL side of the display includes a rolling 1500 DISPLAY digit depiction of altitude. VERTICAL VS TARGET SPEED INDICATOR 5B-13 5B-14 5B-20 Citation Bravo Developed for Training Purposes March 2009...
Page 395: Aoa System
Meggitt display is the glareshield similar to the cross pointer flight director display, this unit does not contain flight director command 5B-16 5B-15 Citation Bravo 5B-21 Developed for Training Purposes March 2009...
Page 396: Signal Generation
Caution area; aircraft approaching critical AOA 0.85 to 1.0 Warning zone just prior to stall buffet and continuing to full stall; stick shaker actuates at 0.79 to 0.88 Table 5B-B; Angle-of-Attack Indicator Legend 5B-22 Citation Bravo Developed for Training Purposes March 2009...
Page 397: Power Supply And Anti-Icing
AOA correct; speed is on Green circle illuminates reference AOA is slightly low; speed Green circle dims and yellow chevron increase from reference illuminates AOA low Yellow chevron illuminates Table 5B-C; AOA Indexer Annunciation Citation Bravo 5B-23 Developed for Training Purposes September 2005...
Page 398 STBY/TIMER XPDR 1 PUSH XPDR 2 PUSH 5B-18 EMER COMM 1 COMM PASS SPKR COMM AUTO SPKR IDENT VOLUME VOICE HDPH 5B-19 MUTE PASS SPKR M A S T E R 5B-24 Citation Bravo Developed for Training Purposes September 2005...
Page 399: Avionics Equipment
EMER/COMM 1 bypasses the audio con/Transmitter (ELT) amplifier, necessitating the use of a headset to receive, and volume con- static discharging trol is available only at the radio. optional flitefone passenger address and entertainment. Citation Bravo 5B-25 Developed for Training Purposes September 2005...
Page 400: Vhf Comm Transceivers
EMER. set (STBY) frequency in the right COMM 1 transmit and audio are window of the CHAN display. operative and NAV 1 audio may be received. 5B-26 Citation Bravo Developed for Training Purposes September 2005...
Page 401 Channel 1 and dashes are in steps of 50-kHz when it is pushed displayed in the STBY window. PULL STBY CHAN COMM1 PULL CHAN TEST PULL STBY CHAN COMM2 PULL CHAN TEST 5B-21 5B-20 Citation Bravo 5B-27 Developed for Training Purposes September 2005...
Page 402: Hf Communication (Optional)
The direct tuning mode is a backup ness of the display to compensate for mode which allows frequency changes in the ambient light level. changes to be made directly into the (A3J) 5B-22 5B-28 Citation Bravo Developed for Training Purposes September 2005...
Page 403 1,000 channel other than zero is not Hz tone to break the squelch of selected. some stations. Citation Bravo 5B-29 Developed for Training Purposes September 2005...
Page 404: Cockpit Voice Recorder
February 1, 2009; and urged users to switch to 406 MHz beacons. The intro- duction of the new 406 MHz ELT also introduced new technologies and increased capabilities of ELT's when interfaced with onboard FMS/GPS 5B-23 equipment. 5B-30 Citation Bravo Developed for Training Purposes March 2009...
Page 405: Static Discharging
C406-N has an inter- nects the Push-To-Talk (PTT) switch nal FMS/GPS interface capability. on the side of the phone to the HF 5B-25 radio to key the HF microphone, and Citation Bravo 5B-31 Developed for Training Purposes March 2009...
Page 406: Navigation
BELT is selected. Navigation Navigation equipment includes: VHF Navigation (VHF NAV) 5B-26 Marker beacon receivers Automatic Direction Finder (ADF) Compass systems Standby HSI Flight Management System (FMS) Optional flight data recorder. 5B-28 5B-27 5B-32 Citation Bravo Developed for Training Purposes March 2009...
Page 407: Marker Beacon Receivers
The marker bea- and new frequencies with one touch. cons annunciated The STBY window is then available appropriately colored letters: a blue for a new pretuned frequency. Citation Bravo 5B-33 Developed for Training Purposes September 2005...
Page 408: Automatic Direction Finder
PFDs, which must be selected on the unmodulated. respective display controllers, and a 5B-34 Citation Bravo Developed for Training Purposes September 2005...
Page 409: Compass Systems
The copilot's IC-600 does not have an time. When the time reaches:00, it autopilot computer. Therefore, select- begins to count up and the display ing AP XFER FD 2 on the autopilot flashes for about 15 seconds. Citation Bravo 5B-35 Developed for Training Purposes September 2005...
Page 410 2.5° to 5.0° per 29.92 XPDR AP XFER ENG ALT FD 1 AP XFER PRI SEC FD 2 5B-31 5B-30 5B-29 5B-36 Citation Bravo Developed for Training Purposes September 2005...
Page 411: Standby Hsi
When the standby HSI the displayed heading and the received functions with the battery switch in signal becomes excessive. EMER, ADF is not available. 5B-32 Citation Bravo 5B-37 Developed for Training Purposes March 2009...
Page 412: Flight Management System
VNAV guidance is not provided to sensors is filtered within the FMS to the flight director or autopilot when derive a “best computed position”. in the approach mode. 5B-33 5B-38 Citation Bravo Developed for Training Purposes March 2009...
Page 413: Digital Flight Recorder (Optional)
DATA RCDR FAIL light on the used only after failure of the auto- annunciator panel illuminates if the matic inputs and must be updated FDR malfunctions or power to the sys- every five minutes. tem fails. Citation Bravo 5B-39 Developed for Training Purposes September 2005...
Page 414: Pulse Equipment
5B-35) both Modes A and C, making it each pilot. The transponder receives unnecessary to select SBY. interrogating pulse signals on 1030 5B-34 5B-36 5B-35 5B-40 Citation Bravo Developed for Training Purposes September 2005...
Page 415 3. Depress the VFR pushbutton mit Mode S reply pulses. The ID (function select knob) while holding 4096 code appears on the right side the IDT button depressed. of the display with altitude indicated Citation Bravo 5B-41 Developed for Training Purposes September 2005...
Page 416: Distance Measuring Equipment
DME on the also annunciates in the KDI-572 dis- DME selector switch on the audio play to warn that the DME is in the control panel (see Figure 5B-37 HOLD mode. next page.) 5B-42 Citation Bravo Developed for Training Purposes September 2005...
Page 417 ON LEFT PFD ON RIGHT PFD HOLD (SELECTABLE FROM (SELECTABLE FROM BENDIX / KING LEFT PFD CONTROLLER) RIGHT PFD CONTROLLER) DME INFORMATION DISPLAYED (TYPICALLY VOR 1 ON RIGHT VOR 2 ON LEFT) 5B-37 Citation Bravo 5B-43 Developed for Training Purposes September 2005...
Page 418: Radio Altimeter
550 ft is reached. At touchdown, the radio altitude decision height warn- altitude awareness display ing sounds when the aircraft reaches reaches the horizon line. the radio altitude set on the pilot's EADI; audible "minimums" is heard. 5B-44 Citation Bravo Developed for Training Purposes September 2005...
Page 419 EMS failure time the actual altitude is displayed. flags and annunciators in the flight The decision height window dis- director mode selector. plays dashes when the TEST button Citation Bravo 5B-45 Developed for Training Purposes September 2005...
Page 420 MODE VNAV AFIS PLAN TUNE MODE HOLD ± GLOBA ENTER STAB SECT PULL GMAP STAB SECT TEST PULL GMAP TEST GAIN RADA GAIN RADA COURSE HEADING COURSE PUSH PUSH PUSH SYNC 5B-46 Citation Bravo Developed for Training Purposes September 2005...
Page 421: Weather Radar
RCT overrides the GAIN control In the ground-mapping mode, the setting causing the receiver gain to system uses black, cyan, yellow, and be fixed and calibrated. magenta to represent reflected signal Citation Bravo 5B-47 Developed for Training Purposes September 2005...
Page 422 MFD. If in the PLAN mode, the selec- OFF condition above the button. tion of the MAP mode is forced when STAB - Permits disabling the WX is selected. antenna stabilization causing the 5B-48 Citation Bravo Developed for Training Purposes September 2005...
Page 423 – RCT/TGT RCT (Green) FLIGHT PLAN NONE FPLN (Green) – FPLN/TGT FPLN (Green) – GMAP NONE GMAP (Green) – GMPA (Green) VAR (Green) Table 5B-D; PFD WX Radar Operating Mode Annunciators Citation Bravo 5B-49 Developed for Training Purposes September 2005...
Page 424 CAE SimuFlite 5B-50 Citation Bravo Developed for Training Purposes September 2005...
Page 425: Other Instruments
Pressing the incremented by the CTL button to CTL button again resets ET to zero. A flight time alarm mode is also pro- change the time. Pressing SEL steps 5B-38 Citation Bravo 5B-51 Developed for Training Purposes September 2005...
Page 426: Outside Air Temperature
5V AC for lighting. The temper- the instrument rotates when the hour ature probe in the left rudder fin ram meter is in operation. air inlet provides this information. 5B-39 5B-41 5B-40 5B-52 Citation Bravo Developed for Training Purposes March 2009...
Page 427: Flight Control Systems
RI-553 Remote Instrument organizes the information into the Controller. correct formats, and transmits the for- Information displayed by the IC-600 mats to the display units. DGC includes heading, course, radio Citation Bravo 5B-53 Developed for Training Purposes September 2005...
Page 428: Autopilot
PITCH wheel (pitch load and fatigue during long flights. axis) and TURN (roll axis) knob. 5B-42 5B-54 Citation Bravo Developed for Training Purposes September 2005...
Page 429 The elevator trim indicator shows an engages the autopilot and yaw out of trim condition in the direction damper simultaneously. Pressing the indicated by the illumination of the 5B-44 5B-45 5B-43 Citation Bravo 5B-55 Developed for Training Purposes September 2005...
Page 430 5B-56 Citation Bravo Developed for Training Purposes September 2005...
Page 431: Display Guidance Computer Interface
Once the control surface maneuvering without disengaging any reaches the commanded position, the selected flight director modes. Citation Bravo 5B-57 Developed for Training Purposes September 2005...
Page 432: Flight Director
5B-58 Citation Bravo Developed for Training Purposes September 2005...
Page 433: Accelerometers
Pressing the SC/CP button on the dis- proportional to the aircraft's acceler- play controller selects magenta flight ation to the IC-600 DGCs. N AV A P R A LT F LC VNAV 5B-46 Citation Bravo 5B-59 Developed for Training Purposes September 2005...
Page 434: Flight Instruments
OFF turns off the PFD and reverts Both command modes displays a the display, through the backup nose up pitch attitude of 12° when mode, to the MFD. Go-Around switch on the throttle is pressed. 5B-60 Citation Bravo Developed for Training Purposes March 2009...
Page 435 7MIN PLAB1 PBDO1 LL01 PLAB2 KDVT TCAS TEST RA 12.5 + 12 TA 14.5 - 12 TCAS 45.0 AUTO GSPD STAB VNAV VSPEEDS TERR TCAS NORM EMER PLAN BARO 5B-47 MODE Citation Bravo 5B-61 Developed for Training Purposes September 2005...
Page 436: Pfd Bezel Controller
Pressing the WX button with emergency checklists. If a symbol the PLAN view displayed replaces it generator fails, reversionary switch- with the MAP view. ing is available through the controller. 5B-62 Citation Bravo Developed for Training Purposes September 2005...
Page 437: Mfd Bezel Controller
The first menu button next to the left system VNAV function is advisory rotary knob is a return button that only and does not interface with the recalls the main menu. autopilot/flight director. Citation Bravo 5B-63 Developed for Training Purposes September 2005...
Page 438: Symbol Generators
1 on the EADI display of both PFDs. trols the copilot's. HDG REV ATT REV ADC REV COURSE HEADING COURSE LEFT FLOOD LTS PUSH PUSH PUSH SYNC 5B-48 PANEL LIGH 5B-49 5B-64 Citation Bravo Developed for Training Purposes September 2005...
Page 439 1000 system and it annunciates an amber ADC 2 or ADC 1 on the is first push to the opposite side, second EADI display of both PFDs. push to the original side, etc. Citation Bravo 5B-65 Developed for Training Purposes September 2005...
Page 440: Eadi Display
The EADI area of the PFD displays bers [(I) to (22)] in the following dis- the following caution or failure cussion to locate the items on the annunciations EADI Display Diagram, next page. 5B-50 5B-66 Citation Bravo Developed for Training Purposes September 2005...
Page 441 NOTES: 1. SYMBOL IS SHOWN FOR FORMAT AND LOCATION. NOT ALL THE SYMBOLS SHOWN MAY SIMULTANEOUSLY OCCUR ON AN ACTUAL DISPLAY. 2. SOURCE ANNUNCIATORS NOT DISPLAYED WHEN NORMAL ON-SIDE SOURCE IS SELECTED, UNLESS BOTH PILOTS ARE USING THE SAME SOURCE. Citation Bravo 5B-67 Developed for Training Purposes September 2005...
Page 442 MAX SPD MIN SPD VOR1 1000 ADF2 AIRCRAFT SYMBOL (CROSSPOINTERS) 5.0 MIN COMPARISON MONITORS RADIO PITCH GLIDESCOPE HEADING ATTITUDE AND ROLL AND LOCALIZER (HDG) (RA) (PIT , ROL, ATT) (GS, LOC, ILS) 5B-68 Citation Bravo Developed for Training Purposes September 2005...
Page 443 VNAV captured to ALT BC armed to BC captured ASEL armed to ALT VAPP armed to V captured ALT captured to ALT GS armed to GS captured Table 5B-F; Mode Transitions Citation Bravo 5B-69 Developed for Training Purposes September 2005...
Page 444 PFD, above the verti- The MIN decision height does not cal deviation scale. A green CAT2 annunciate until it is armed, which approach window (8) also appears 5B-70 Citation Bravo Developed for Training Purposes September 2005...
Page 445 VNAV button course by the flight director also on the mode selector, which must be removes the vertical deviation scale. active for the system to fly VNAV. Citation Bravo 5B-71 Developed for Training Purposes September 2005...
Page 446 1.85 in for each 1 g of lateral Either setting the value at zero ft or acceleration. an invalid RA removes the digital display and label from the PFD. 5B-72 Citation Bravo Developed for Training Purposes September 2005...
Page 447 **These comparisons are only active during flight director, localizer, and glideslope capture with both NAV receivers tuned to a LOC localizer Table 5B-G; Compared Signals vs. Displayed Cautionary Symbols Citation Bravo 5B-73 Developed for Training Purposes September 2005...
Page 448: Ehsi Display
A green TGT indi- director mode selector. The mode cates that target mode has been and bearing pointers available enabled on the weather radar. depend upon optional equipment 5B-74 Citation Bravo Developed for Training Purposes September 2005...
Page 449: Ehsi Displays And Annunciations
Flying above 70° north latitude scale of the bearing pointer of the requires an upgraded compass instal- selected failed equipment. lation because the true heading sym- bols are not supported in this system. Citation Bravo 5B-75 Developed for Training Purposes September 2005...
Page 450 399 MIN PRCHDG GSPD BEARING 999 KTS SOURCES ADF1 ADF2 VOR1 VOR2 NOTE: HEADING SOURCE ANNUNCIATIONS NOT DISPLAYED WHEN NORMAL ON-SIDE SOURCE IS SELECTED, UNLESS BOTH PILOTS ARE ON THE SAME SOURCE. 5B-76 Citation Bravo Developed for Training Purposes September 2005...
Page 451 Gyro-stabilized magnetic compass to FMS, both CDIs will display FMS information appears on a standard type information in amber. compass dial (6) format that rotates Citation Bravo 5B-77 Developed for Training Purposes September 2005...
Page 452 FROM symbol. The two-dot scale repre- indicator is a solid black triangle sents NAV deviation from the behind the symbol. If VOR is 5B-78 Citation Bravo Developed for Training Purposes September 2005...
Page 453 > 0.6 NM 0.3 NM 0.15 NM FMS WIth GPS Invalid Enroute > 10.0 NM 5.0 NM 2.5 NM Terminal Approach > 2.0 NM 1.0 NM 0.5 NM Table 5B-H; Lateral Deviation Scaling Citation Bravo 5B-79 Developed for Training Purposes September 2005...
Page 454 FMS way- yellow depending upon the NAV point alert when it is displayed. source or the type of EHSI display or annunciator. 5B-80 Citation Bravo Developed for Training Purposes September 2005...
Page 455: Excessive Attitude Display
(that sur- rounds the captured lateral or ver- vertical, lateral, and non-synched tical flight director modes). flight director mode annunciations BARO 5B-49 Citation Bravo 5B-81 Developed for Training Purposes September 2005...
Page 456: Attitude And Heading Reference
In MAN, nals proportional to the gyro dis- manual gyro alignment is through a placement. spring-return L/R SLAVE switch. 5B-82 Citation Bravo Developed for Training Purposes September 2005...
Page 457: Rate Gyro
IC-600 DGC. The flight director portional to the rate-of-turn. drives the rate-of-turn display. Citation Bravo 5B-83 Developed for Training Purposes September 2005...
Page 458 CAE SimuFlite 5B-84 Citation Bravo Developed for Training Purposes September 2005...
Page 459: Preflight And Procedures
(refer to the CAE warm-up after cold soak. Over 20 from the static ports. Running the SimuFlite Citation Bravo Operating minutes may be required at temper- back of a finger from the aircraft Handbook for a detailed checklist): atures below -30 °...
Page 460: Autopilot Torque Failure
The autopilot may loss (PITOT & STATIC switch OFF) be transferred to the operative side. or an equipment malfunction. 5B-86 Citation Bravo Developed for Training Purposes September 2005...
Page 461: Loss Of Tas Input To Fms
AOA sensor the AP/TRIM DISC button. Ensure becomes iced, the stick shaker, AOA the autopilot remains OFF. gauges, and low airspeed awareness systems may not function. 5B-51 Citation Bravo 5B-87 Developed for Training Purposes March 2009...
Page 462: Single Primary Flight Display Failure
Continue the flight using the second- temperature to help prevent over- ary heading source. heating. 5B-88 Citation Bravo Developed for Training Purposes September 2005...
Page 463: Display Guidance Computer Cooling Fan Failure
However, restoring landing. Land as soon as practicable. power will likely result in another Citation Bravo 5B-89 Developed for Training Purposes September 2005...
Page 464: Symbol Generator Failure
Be aware that the red X symbol indi- not illuminate unless there is an avi- cates a loss of data reaching the tube onics system failure. itself, and therefore, this indication appearing may indicate a failure in 5B-90 Citation Bravo Developed for Training Purposes September 2005...
Page 465: Emergency Procedures
Emergency procedures for the avi- onics systems include (refer to the Dual PFD Heading Failure CAE SimuFlite Citation Bravo Autopilot Hardover Operating Handbook for a detailed checklist): Illumination of the HDG annunciator...
Page 466 CAE SimuFlite 5B-92 Citation Bravo Developed for Training Purposes September 2005...
Page 467 Battery bus, which also serves as the input for ground power. Two static inverters convert DC to AC. Four distribution buses carry power from the inverters. Lighting on the Citation Bravo includes cockpit, passenger cabin, cargo and service compartment, exterior, and emergency lights. Citation Bravo...
Page 468 CAE SimuFlite 5C-2 Citation Bravo Developed for Training Purposes September 2005...
Page 469 Circuit Breakers ......5C-17 Current Limiters ......5C-17 Citation Bravo 5C-3...
Page 470 Data Summary ......5C-41 Electrical Systems Data ..... 5C-41 5C-4 Citation Bravo Developed for Training Purposes September 2005...
Page 471 EMERGENCY BUS LH CROSSOVER BUS LH MAIN BUS EXTENSION RH CROSSOVER BUS RH MAIN BUS EXTENSION 26V AC BUS NO. 1 & 2 115V AC BUS NO. 1 & 2 Citation Bravo 5C-5 5C-6 Developed for Training Purposes September 2005...
Page 472 ENTR LTS/EXIT SIGNS VOLTMETER (battery switch in BATT or EMER) FLOOD LIGHTS LH/RH IGNITION PWR (SEC) LH/RH START CONTROL (PRI) LH/RH START LIGHT (PRI) TAILCONE LIGHTS VOLTMETER (battery switch in BATT or EMER) 5C-6 Citation Bravo Developed for Training Purposes September 2005...
Page 473: Dc System
The generators supply power to the be shut down during single generator Main buses through power relays. operation due to its high amp draw. 5C-1 Citation Bravo 5C-7 Developed for Training Purposes March 2009...
Page 474: Generator Control Units
Main bus connection are automatic the operating generator increases to through the GCU; once the generator meet the demand because the buses reaches operating speed, the genera- are tied together. 5C-4 5C-3 5C-2 5C-8 Citation Bravo Developed for Training Purposes September 2005...
Page 475: Gen Off Annunciators
Hot Battery bus via the battery relay. for five to ten minutes, or the Emer- The generators can only charge the gency bus only for 30 minutes. battery with the switch in BATT. 5C-6 5C-5 Citation Bravo 5C-9 Developed for Training Purposes March 2009...
Page 476: Voltmeter
An accurate check of one Depending on battery switch posi- generator is obtained only with the tion, the emergency relay connects opposite one off the line. 5C-7 5C-8 5C-10 Citation Bravo Developed for Training Purposes September 2005...
Page 477: Battery Overheat Warning
The aircraft (Figure 5C-10). tion the battery per the aircraft requires a GPU capable of producing Maintenance Manual. 5C-9 5C-10 Citation Bravo 5C-11 Developed for Training Purposes March 2009...
Page 478: Gpu Protection
Left and Right Main buses are also in the power junction box. The system consists of a battery dis- connect relay, an over-voltage moni- tor and an over-voltage logic relay. 5C-12 Citation Bravo Developed for Training Purposes September 2005...
Page 479: Dc Distribution Buses
RH MAIN LH MAIN POWER RELAY BATT BUS BATT BUS POWER BATTERY POWER RELAY RELAY RELAY START START RELAY RELAY HOT BATT BATT BATT EXTERNAL BATTERY POWER DISCONNECT RELAY RELAY 5C-11 Citation Bravo 5C-13 Developed for Training Purposes September 2005...
Page 480: Emergency Bus
NAV No. 1 Voltmeter *The pilot’s Audio panel is switched to the Emergency Bus when the battery switch is in the EMER position. Table 5C-A; Equipment Powered by the Emergency Bus 5C-14 Citation Bravo Developed for Training Purposes September 2005...
Page 481: Dc Relays
BATT EMERGENCY EMER LH MAIN POWER RH MAIN RELAY BATT BUS POWER BATTERY POWER RELAY RELAY RELAY START START RELAY RELAY HOT BATT BATT EXTERNAL BATTERY POWER DISCONNECT RELAY RELAY 5C-12 Citation Bravo 5C-15 Developed for Training Purposes March 2009...
Page 482: Battery Disable Relay
GPU supplies power to the placing the generator control switch Hot Battery bus. Once a generator in the momentary RESET position. begins supplying power, the relay 5C-16 Citation Bravo Developed for Training Purposes September 2005...
Page 483: Circuit Breakers
A current limiter actuates automati- engine’s starter/generator drive cally, but cannot be reset; once a cur- Cross-generator assisted start. during the second start. rent limiter opens, it must be replaced before dispatch. Citation Bravo 5C-17 Developed for Training Purposes March 2009...
Page 484: Gpu Start
EMERGENCY EMER POWER LH MAIN RH MAIN RELAY BATT BUS POWER BATTERY POWER RELAY RELAY RELAY START START RELAY RELAY HOT BATT BATT BATT EXTERNAL BATTERY POWER DISCONNECT RELAY RELAY 5C-13 5C-18 Citation Bravo Developed for Training Purposes September 2005...
Page 485 BATT EMERGENCY EMER POWER LH MAIN RH MAIN RELAY BATT BUS POWER BATTERY POWER RELAY RELAY RELAY START START RELAY RELAY HOT BATT BATT EXTERNAL BATTERY POWER DISCONNECT RELAY RELAY 5C-14 Citation Bravo 5C-19 Developed for Training Purposes September 2005...
Page 486: Battery Start
BATT EMERGENCY EMER POWER LH MAIN RH MAIN RELAY BATT BUS POWER BATTERY POWER RELAY RELAY RELAY START START RELAY RELAY HOT BATT BATT EXTERNAL BATTERY POWER DISCONNECT RELAY RELAY 5C-15 5C-20 Citation Bravo Developed for Training Purposes March 2009...
Page 487: Cross-Generator Assisted Start
BATT EMERGENCY EMER POWER LH MAIN RH MAIN RELAY BATT BUS POWER BATTERY POWER RELAY RELAY RELAY START START RELAY RELAY HOT BATT BATT EXTERNAL BATTERY POWER DISCONNECT RELAY RELAY 5C-16 Citation Bravo 5C-21 Developed for Training Purposes March 2009...
Page 488 INVERTER 400Hz 400Hz INVERTER FAIL 2 AC INV AC INV NO. 1 NO. 2 INV 1 28V DC 28V DC LH MAIN BUS EXT RH MAIN BUS EXT INV 2 5C-17 5C-22 Citation Bravo Developed for Training Purposes March 2009...
Page 489: Ac System
Electrical AC System The Citation Bravo AC electrical sys- separate sources. The No. 1 inverter receives power from the Left Main facing page) uses (Figure 5C-17, Extension bus through the AC two inverters to convert Direct Cur- INVERTER NO. 1 CB and the No. 2...
Page 490: Switching Relays
If In the case of an inverter failure, the the fault has cleared, the correspond- pilot must select the opposite ing inverter annunciator light extin- inverter by positioning the INV 1/ 5C-24 Citation Bravo Developed for Training Purposes March 2009...
Page 491: Buses
Standby HSI is provided by an internal static inverter in the pilot’s C-14D directional gyro. In this case, the DG static inverter also provides its own AC power. Table 5C-B; Inverter-Powered Systems Citation Bravo 5C-25 Developed for Training Purposes March 2009...
Page 492: Generator Reset Decision Tree
Less Than 10V DC Normal 28.5V DC GEN SW - LEAVE OFF GEN SW - GEN (RESET NOT FUNCTIONAL) GEN SW - LEAVE OFF GEN SW - GEN (RESET NOT FUNCTIONAL) 5C-26 Citation Bravo Developed for Training Purposes March 2009...
Page 493: Preflight And Procedures
GEN. If the generator does not reset, gle generator failure and a single turn it OFF and continue the flight inverter failure. Please refer to the with the one operating generator SimuFlite Citation Bravo Operating (see Decision Tree). Handbook for complete procedures. Citation Bravo 5C-27...
Page 494: Single Inverter Failure
Attempt to restore at least one Refer to the AC schematic for a list- inverter by resetting and/or pulling ing of systems powered by the AC the inverter CBs. If one or both 5C-28 Citation Bravo Developed for Training Purposes March 2009...
Page 495: Battery Overheat
See Table 5C-C for systems made than generator voltage in 30 seconds inoperative with the battery switch to 2 minutes, monitor the battery in EMER and the generator switches overheat annunciator for possible OFF. change. Citation Bravo 5C-29 Developed for Training Purposes March 2009...
Page 496 If there is no DC power loss, the bat- tery relay is stuck closed. Turn both of the manual windshield bleed air 5C-30 Citation Bravo Developed for Training Purposes March 2009...
Page 497: Electrical Fire Or Smoke
Limit operating generator may be restored when Table 5C-C load to 400 amps to 35,000 ft. and to the left generator is turned on when 315 amps above 35,000 ft. landing is assured. Citation Bravo 5C-31 Developed for Training Purposes March 2009...
Page 498 DOWN and select flaps LAND. tors, and the standby altimeter/air- Maintain airspeed at V for the speed indicator vibrator. Ensure that landing. the cabin services (refreshment cen- ter, cabin lights) are OFF. 5C-32 Citation Bravo Developed for Training Purposes September 2005...
Page 499: Lighting
Electrical Lighting Lighting on the Citation Bravo by a post light. Secondary lighting includes interior, exterior, and emer- includes the cockpit floodlights, an gency lighting. Interior lighting alternate engine instrument flood- includes systems for the cockpit, light, and two map lights.
Page 500 Electroluminescent panels are on the power from the Right Crossover bus instrument panel, side consoles, and through the RH PANEL circuit control pedestal. The EL PANEL breaker. circuit breaker supplies 28V DC 5C-22 5C-23 5C-21 5C-34 Citation Bravo Developed for Training Purposes September 2005...
Page 501: Passenger Compartment
If the input voltage to the aft The light operates when power is on inverter drops below 20V, the lights the aircraft. automatically shift to bright. Once 5C-26 5C-25 5C-24 Citation Bravo 5C-35 Developed for Training Purposes September 2005...
Page 502: Cargo And Service Compartment Lighting
Placing the switch in SEAT BELT microswitch control the lights. illuminates the FASTEN SEAT BELT 5C-28 5C-27 5C-29 5C-30 5C-36 Citation Bravo Developed for Training Purposes September 2005...
Page 503: Exterior Lighting
Extension bus through the NAVI- Exterior lighting consists of: GATION LIGHTS circuit breaker. navigation The NAV switch on the pilot's Anti-collision switch panel controls the lights. Beacon 5C-32 5C-31 5C-33 5C-34 Citation Bravo 5C-37 Developed for Training Purposes September 2005...
Page 504 Turning the receives 28V DC power from the switches ON illuminates the lights Right Main DC bus through the RH once the main gear doors open. 5C-36 5C-35 5C-38 Citation Bravo Developed for Training Purposes September 2005...
Page 505 J box). The TAIL FLOOD cuit breaker on the left circuit switch on the pilot's switch panel breaker panel. The WING INSP controls these lights. switch on the pilot's switch panel controls the light. 5C-37 Citation Bravo 5C-39 Developed for Training Purposes September 2005...
Page 506: Emergency Lighting
5Gs or more. 0801 thru 0808 only) Normally, the Hot Battery bus pro- Meggitt display tube (Units 0809 vides power for battery charging and and subsequent) operation of the lights. During 5C-40 Citation Bravo Developed for Training Purposes September 2005...
Page 507: Electrical Systems Data
BATT O'TEMP/ >160°F annunciator MASTER CAUTION and WARNING AC FAIL annunciator INVTR FAIL 1/2 annunciators MASTER CAUTION and WARNING Protection Circuit Breakers Current Limiters Relays Generator Control Units (GCUs) External power overvoltage/overcurrent sensor Citation Bravo 5C-41 Developed for Training Purposes March 2009...
Page 508 CAE SimuFlite 5C-42 Citation Bravo Developed for Training Purposes September 2005...
Page 509 Fire This chapter describes the Citation Bravo fire protection system, which consists of an engine fire detection/extinguishing system Protection and manually operated fire extinguishers for use inside the pres- sure vessel. The entire fire detection system senses and indicates the presence...
Page 510 CAE SimuFlite 5D-2 Citation Bravo Developed for Training Purposes September 2005...
Page 511 Data Summary ......5D-13 Fire Protection Data ......5D-13 Citation Bravo 5D-3...
Page 512: Fire Protection System Schematic
NORMAL 125 CU. IN. CBrF PRESSURIZED TO 600 ± 75 PRESSURIZED TO 600 ± 75 PSI AT 70 ° F PSI AT 70 ° F HALON 1301 HALON 1301 FIRE LOOP FIRE LOOP 5D-4 Citation Bravo Developed for Training Purposes March 2009...
Page 513: Engine Fire Detection System
(Figure of flexible, stainless steel for each engine, are in the aft fuse- 5D-1) cable contains a 28 V DC energized lage section and accessible through the tailcone compartment door. 5D-1 Citation Bravo 5D-5 Developed for Training Purposes March 2009...
Page 514 ). The control unit has an internal 5D-2 systems. It will not trigger the red test resistor that is applied to master warning reset light. 5D-3 5D-2 5D-2 5D-6 Citation Bravo Developed for Training Purposes September 2005...
Page 515: Engine Fire Switchlights
BOTTLE 1 ARMED PUSH EMER UNLOCK FIRE DEPLOY NORMAL 5D-4 Citation Bravo 5D-7 Developed for Training Purposes March 2009...
Page 516: Fire Extinguisher Bottle
BOTTLE 1 or 2 ARMED PUSH The ENGINE FIRE switchlight switchlight. This directs 28V DC to selects the correct cartridge. 5D-5 5D-8 Citation Bravo Developed for Training Purposes September 2005...
Page 517: Portable Fire Extinguishers
The only way to for class B and C fires and contains verify the bottle has discharged is to 4.5 lbs of Halon 1211, which is nitrogen-charged to 125 PSI. 5D-6 Citation Bravo 5D-9 Developed for Training Purposes March 2009...
Page 518 CAE SimuFlite 5D-10 Citation Bravo Developed for Training Purposes September 2005...
Page 519: Preflight And Procedures
BOT- START DISENGAGE pushbutton. TLE ARMED PUSH lights. PRESSURE - TEMPERATURE CORRECTION TABLE ° C TEMP IND. PRESS ° C +100 +125 TEMP IND. PRESS 13218-2 5D-8 Citation Bravo 5D-11 Developed for Training Purposes March 2009...
Page 520: Engine Fire Detection System Failure
Altitude, accelerate to V + 10 protection system. Please refer to KIAS (if not already); then retract your SimuFlite Citation Bravo Oper- the flaps." Accomplish the check- ating Handbook for specific detailed list items for Engine Fire in Flight checklists.
Page 521: Fire Protection Data
BOTTLE 1/2 ARMED PUSH switchlights F/W SHUTOFF L/R annunciators Fire bottle pressure gauges (Pre-flight only) Protection Overpressure/pressure relief valve on each fire bottle Circuit breakers Two 125 in fire bottles in tailcone area Miscellaneous Citation Bravo 5D-13 Developed for Training Purposes March 2009...
Page 522 CAE SimuFlite 5D-14 Citation Bravo Developed for Training Purposes September 2005...
Page 523 Flight The primary flight controls of the Citation Bravo consist of the ailerons, elevators, and rudder. The mechanically driven flight Controls controls operate through input received from the cockpit via direct cable. The secondary flight controls of the Citation Bravo consist of Chapter 5E wing flaps and speedbrakes.
Page 524 CAE SimuFlite 5E-2 Citation Bravo Developed for Training Purposes September 2005...
Page 525 Flaps ........5E-20 Speedbrakes ......5E-20 Citation Bravo 5E-3...
Page 526: Primary Flight Controls Diagram
CAE SimuFlite Primary Flight Controls Diagram RUDDER RUDDER SERVO AND TRIM TAB AILERON ELEVATOR TRIM TABS ELEVATOR AILERON TRIM TAB 5E-4 Citation Bravo Developed for Training Purposes September 2005...
Page 527: Primary Flight Controls
Full travel of the tab is which move the ailerons to the 20 ± 1° up and down. desired position. 5E-2 5E-1 Citation Bravo 5E-5 Developed for Training Purposes September 2005...
Page 528: Elevators
ELEVATORS ELEVATOR TRIM TABS 5E-3 5E-4 5E-5 5E-6 Citation Bravo Developed for Training Purposes September 2005...
Page 529: Electric Pitch Trim System
The der bellcrank. The torque tube trans- Left Main Extension bus supplies mits rudder bellcrank movement electrical power for the motor. information to deflect the rudder. 5E-8 5E-7 5E-6 Citation Bravo 5E-7 Developed for Training Purposes September 2005...
Page 530: Autopilot/Yaw Damper
Disengage the yaw damper by press- The cockpit indicator on the center ing either the AP/TRIM DISC pedestal has neutral, full left, and switch or the YAW DAMPER button full right positions. 5E-9 5E-10 5E-8 Citation Bravo Developed for Training Purposes March 2009...
Page 531: Control Lock
To engage (return to the horizontal position). the control lock, align the nosewheel Check flight controls for proper movement before flight. 5E-11 Citation Bravo 5E-9 Developed for Training Purposes September 2005...
Page 532 CAE SimuFlite 5E-10 Citation Bravo Developed for Training Purposes September 2005...
Page 533: Speedbrakes System Schematic
ABOVE 85% N 2 EXTEND EXTEND RETURN FLOW RETURN FLOW EXTEND RETURN FLOW EXTEND EXTEND HOLDING HOLDING EXTEND HOLDING RELAY RELAY RETRACT RETRACT RELAY RETRACT (IN TAILCONE) (IN TAILCONE) (IN TAILCONE) Citation Bravo 5E-11 Developed for Training Purposes March 2009...
Page 534: Secondary Flight Controls Diagram
CAE SimuFlite Secondary Flight Controls Diagram WING FLAP SPEEDBRAKE (UPPER & LOWER SURFACE) 5E-12 Citation Bravo Developed for Training Purposes September 2005...
Page 535: Secondary Flight Controls
( Figure 5E- include the up and down position following page) hold the lower switches and an arm and cam unit. speedbrake panels up. 5E-12 5E-13 Citation Bravo 5E-13 Developed for Training Purposes March 2009...
Page 536: Speedbrake Switch
This creates a hydraulic lock and brakes and electrically returns the holds the speedbrakes open. The speedbrake switch to the RETRACT hydraulic bypass valve then reopens position. 5E-16 5E-15 5E-14 5E-14 Citation Bravo Developed for Training Purposes March 2009...
Page 537: Stall Warning
The stall strips provide a warning at approximately + 10 and V + 5 (landing). 5E-17 Citation Bravo 5E-15 Developed for Training Purposes September 2005...
Page 538 CAE SimuFlite 5E-16 Citation Bravo Developed for Training Purposes September 2005...
Page 539: Preflight And Procedures
The following is a brief explanation steps, please refer to your CAE not executed correctly, the deploy- of the abnormal procedures for the SimuFlite Citation Bravo Operating ing T/R's will lift the nosewheel off flight controls system. The abnormal Handbook.
Page 540: Landing With Failed Primary Flight Control Cable
Please refer to your Simu- the speedbrakes as soon as possible. flite Citation Bravo Operating Hand- Differential braking is used for direc- book for complete procedures. tional control, as well as for nosewheel steering.
Page 541: Data Summaries
Yaw damper engages automatically via AP ENGAGE switch or when YD ENGAGE switch is pressed Turn knob on autopilot control panel must be centered in detent and DG-1 or DG-2 aligned to engage autopilot Citation Bravo 5E-19 Developed for Training Purposes March 2009...
Page 542: Flaps
SPEED BRAKE circuit breaker Miscellaneous SPEEDBRAKES retract automatically and cannot be extended at power settings representing above 85% Throttle Cable Position; SPEEDBRAKES cannot be manually held in the extended position with the speedbrake switch 5E-20 Citation Bravo Developed for Training Purposes March 2009...
Page 543 Fuel The Citation Bravo fuel system is two distinct, yet identical sys- tems: one for the left engine and one for the right engine. Wing System tanks store the fuel for use by the engines. Each wing holds approximately 360 U.S. gallons of usable fuel for a total aircraft capacity of 720 U.S.
Page 544 CAE SimuFlite 5F-2 Citation Bravo Developed for Training Purposes September 2005...
Page 545 Preflight Inspection ......5F-19 Servicing........5F-19 Citation Bravo 5F-3...
Page 546 Fuel System Data ......5F-23 5F-4 Citation Bravo Developed for Training Purposes September 2005...
Page 547 Fuel System Citation Bravo 5F-5 Developed for Training Purposes September 2005...
Page 548: Fuel System Schematic
FLOW DIVIDER ENGINE-DRIVEN PUMP ENGINE-DRIVEN PUMP 1000 1000 MOTIVE FLOW MOTIVE FLOW AUTOMATIC SHUTOFF ENGINE-DRIVEN PUMP ENGINE-DRIVEN PUMP MOTIVE FLOW MOTIVE FLOW EPA RETURN ENGINE RH ENGINE EPA RETURN ENGINE RH ENGINE Citation Bravo 5F-6 Developed for Training Purposes March 2009...
Page 549: Fuel Storage
The vent quick drains for water and sediment line extends from the surge tank to removal. the sump area. 5F-1 Citation Bravo 5F-7 Developed for Training Purposes March 2009...
Page 550: Fuel Probes
The indicator converts these of the fuel. signals into fuel weight and displays it in pounds per cell. 5F-2 5F-8 Citation Bravo Developed for Training Purposes March 2009...
Page 551: Fuel Flow/Fuel Quantity Indicator
"1888." is disabled at and below 10% turbine Both displays are blank when input speed or with the throttle in CUTOFF. power is removed. 5F-3 5F-4 Citation Bravo 5F-9 Developed for Training Purposes March 2009...
Page 552: Low Level Warning
The locking cap has a chrome LO FUEL PRESS L/R annunciator cover to protect the lock from if the pressure decreases below 4.65 weather. 5F-10 Citation Bravo Developed for Training Purposes March 2009...
Page 553: Drain Valves
OPEN position and detented in the CLOSED Pushing the poppet valve up and position. rotating it counterclockwise locks it in the OPEN position. 5F-6 5F-5 Citation Bravo 5F-11 Developed for Training Purposes September 2005...
Page 554 CAE SimuFlite 5F-12 Citation Bravo Developed for Training Purposes September 2005...
Page 555: Fuel Distribution
ELECTRIC BOOST PRIMARY EJECTOR PUMP PUMP 5F-7 Citation Bravo 5F-13 Developed for Training Purposes September 2005...
Page 556: Transfer Ejector Pumps
FUEL BOOST TRANSFER PUMP NORM NORM 5F-9 5F-8 5F-14 Citation Bravo Developed for Training Purposes March 2009...
Page 557: Fuel Filters And Bypass
The F/W SHUTOFF L/R annuncia- tors illuminate when the fuel and hydraulic firewall shutoff valves to the associated engine are closed. 5F-11 5F-10 Citation Bravo 5F-15 Developed for Training Purposes March 2009...
Page 558 CAE SimuFlite 5F-12 5F-16 Citation Bravo Developed for Training Purposes March 2009...
Page 559: Crossfeed In Transit Light
The crossfeed valves remain closed engine receives fuel from its respec- tive tank. During engine start, the during normal operations. electric boost pump supplies fuel to the engine. Citation Bravo 5F-17 Developed for Training Purposes March 2009...
Page 560: Crossfeed Operations
IN TRANSIT light illumi- is not supplying the fuel. nates. The IN TRANSIT light extin- guishes when the crossfeed valves are fully open. 5F-18 Citation Bravo Developed for Training Purposes March 2009...
Page 561: Servicing And Procedures
Maintain additive concentra- 3. Replace the filler cap. tion range in accordance with instructions in the AFM. Citation Bravo 5F-19 Developed for Training Purposes March 2009...
Page 562: Forced Method
7. Drain residual fuel from tank by the fuel boost pump CBs are in and the wing tank poppet-type drain valves. 5F-20 Citation Bravo Developed for Training Purposes March 2009...
Page 563: Low Fuel Quantity
Con- sider crossfeeding if the fuel level is adequate on the other side. Land as soon as practical. Citation Bravo 5F-21 Developed for Training Purposes March 2009...
Page 564 CAE SimuFlite 5F-22 Citation Bravo Developed for Training Purposes March 2009...
Page 565: Fuel System Data
LO FUEL PRESS (L/R) Crossfeed IN TRANSIT light FUEL FLOW/FUEL QTY indicator Protection Circuit breakers Fuel filters Fuel firewall shutoff valves Motive flow shutoff valve 0.007 engine mechanical emergency fuel cutoff Prist Citation Bravo 5F-23 Developed for Training Purposes March 2009...
Page 566 CAE SimuFlite 5F-24 Citation Bravo Developed for Training Purposes March 2009...
Page 567 Hydraulic The Citation Bravo utilizes an open center (i.e., on demand) hydraulic system. Hydraulic fluid continuously circulates through Systems the system at no more than 60 PSI. When pressure is required, a bypass valve closes and the pressure builds up. A relief valve reg- ulates the pressure between 1,350 and 1,500 PSI.
Page 568 CAE SimuFlite 5G-2 Citation Bravo Developed for Training Purposes September 2005...
Page 569 Data Summary ......5G-9 Hydraulic System ......5G-9 Citation Bravo 5G-3...
Page 570 FILTER PRESSURE SWITCH BYPASS BYPASS LO HYD LEVEL LANDING GEAR PRESS THRUST REVERSERS CHECK VALVE CENTER RELIEF BYPASS VALVE VALVE 1,350 TO (NORMALLY FILTER 1,500 PSI SPEEDBRAKES OPEN) SUPPLY RETURN PRESSURE 5G-4 Citation Bravo Developed for Training Purposes September 2005...
Page 571: Hydraulic System
Hydraulic Systems Hydraulic The Citation BRAVO's open center A plunger type sight gauge attached hydraulic system was chosen for its to the reservoir pro- (Figure 5G-1) light weight, low component wear, vides a visual indication of the reser- System and reduced leakage. The majority voir fluid level.
Page 572: Pumps
HYD PRESS annunciator. 0.45 ±0.10 GPM, the respective LO As pressure decreases below 155 ±5 HYD FLOW L/R annunciator illumi- PSI, the pressure switch extin- guishes the annunciator. 5G-6 Citation Bravo Developed for Training Purposes March 2009...
Page 573: Procedures
The speedbrakes, and tor illuminates indicating the left thrust reversers are not available; the and/or right hydraulic pump flow landing gear is inoperative using rate is below normal (i.e. less than normal procedures. Citation Bravo 5G-7 Developed for Training Purposes September 2005...
Page 574 CAE SimuFlite 5G-8 Citation Bravo Developed for Training Purposes September 2005...
Page 575: Hydraulic System
(at a reduced rate). Pushing the ENG FIRE switchlight closes the correspond- ing hydraulic and fuel firewall shutoff valves and TR isola- tion valve to stop flammable liquid flow to the affected engine. Citation Bravo 5G-9 Developed for Training Purposes March 2009...
Page 576 CAE SimuFlite 5G-10 Citation Bravo Developed for Training Purposes September 2005...
Page 577 Ice and Rain The Citation Bravo utilizes four methods to protect aircraft sur- faces from ice and rain. Protection Engine Bleed air prevents ice formation on the engine bullet nose cone, temperature probe, engine inlet lip, inner stator vanes, and windshield.
Page 578 CAE SimuFlite 5H-2 Citation Bravo Developed for Training Purposes September 2005...
Page 579 Data Summaries ......5H-19 Ice and Rain Protection ..... . . 5H-19 Citation Bravo 5H-3...
Page 580 CAE SimuFlite 5H-4 Citation Bravo Developed for Training Purposes September 2005...
Page 581: Ice And Rain Protection
RAIN REMOVAL WING L.E. ELECTRICALL Y ANGLE-OF-ATTACK ANTI-ICED WING L.E. PNEUMATIC DEICE BOOTS 5H-2 NOSE CONE EMPENNAGE L.E. TEMP PROBE PNEUMATIC STATOR VANES DEICE BOOTS ENGINE INLET (BLEED AIR ANTI-ICED) 5H-1 5H-3 Citation Bravo 5H-5 Developed for Training Purposes March 2009...
Page 582 STATOR BLEED STATOR BLEED AIR VALVE AIR VALVE EXCITER EXCITER LOW TEMP SWITCH (170 ° F) INLET LIP BLEED AIR VALVE LOW TEMP SWITCH (170 ° F) INLET LIP BLEED AIR VALVE 5H-6 Citation Bravo Developed for Training Purposes September 2005...
Page 583: Engine Anti-Ice System
, electrical power routes through a thermal time delay relay and then to the valves. After five seconds, the thermal relay opens to remove power from the valves, so 5H-4 they open. Citation Bravo 5H-7 Developed for Training Purposes March 2009...
Page 584: Inboard Wing Leading Edge Anti-Ice
155°F. 172 ±6°F. When the controller senses 172 ±6°F, it signals the con- trol relay to open; this interrupts power to the heating elements. The relay closes when the temperature of 5H-8 Citation Bravo Developed for Training Purposes March 2009...
Page 585 (abnormal condition that results in annunciator remaining illuminated at all times system is turned on) stator valve not open, which indi- cates throttle not above 60% N a failure of the stator valve Citation Bravo 5H-9 Developed for Training Purposes March 2009...
Page 586 SURFACE DE-ICE RESET CONTROL VALVE AND EJECTOR PRESSURE SWITCH 20 PSI LH HORIZ BOOT RH HORIZ BOOT ENGINE BLEED AIR REGULATED BLEED AIR VERT TAIL VACUUM BOOT PNEUMATIC AIR OVERBOARD EXHAUST 5H-10 Citation Bravo Developed for Training Purposes September 2005...
Page 587: Surface Deice System
20 PSI during the second six-second wing control valves and holds 5.5 cycle. inches Hg vacuum to keep the boots deflated. 5H-7 5H-6 5H-5 Citation Bravo 5H-11 Developed for Training Purposes March 2009...
Page 588 SWITCH 5 PSI RAM AIR RAM AIR IN EXHAUST AIR CONTROL VALVE HEAT EXCHANGER W/S BLEED AIR VALVE VALVE RELAY SUPPLY REGULATED AIR RAM AIR R ENG BLEED AIR L ENG BLEED AIR 5H-12 Citation Bravo Developed for Training Purposes September 2005...
Page 589: Windshield Bleed Air Anti-Ice
(260°F) . The WINDSHIELD BLEED 5H-9) 127 ±5°C. In HI, the air is maintained AIR manual controls for the left and at (280°F) 138 ±5°C. right windshield nozzle assemblies 5H-9 5H-8 Citation Bravo 5H-13 Developed for Training Purposes September 2005...
Page 590: Windshield Overheat Annunciator
Operating with the doors open above 150 KIAS could damage the doors' actuating arms and prevent them from closing properly. 5H-10 5H-14 Citation Bravo Developed for Training Purposes March 2009...
Page 591: Miscellaneous Systems
All nine of (Figure 5H-13). ment by monitoring the drop in the components incorporate electrical amperage to the system. 5H-12 5H-11 5H-13 5H-14 Citation Bravo 5H-15 Developed for Training Purposes September 2005...
Page 592: Pitot/Static Annunciator
CB set and power ice protection on the pilot's wind- applied to the aircraft. PLUG PLUG SIGHT GAGE SIGHT GAUGE VENT LINE VENT LINE RESERVOIR RESERVOIR 5H-15 5H-17 5H-16 5H-16 Citation Bravo Developed for Training Purposes March 2009...
Page 593: Preflight And Procedures
There from the aircraft surfaces and oper- 5H-18 5H-19 Citation Bravo 5H-17 Developed for Training Purposes March 2009...
Page 594: Engine Anti-Ice Failure
Emergency With a momentary illumination of bus. the W/S AIR O'HEAT annunciator, reduce the bleed air reaching the windshield by adjusting the WIND- SHIELD BLEED AIR manual con- 5H-18 Citation Bravo Developed for Training Purposes March 2009...
Page 595: Data Summaries
Left Main Extension bus (pilot side) Emergency DC bus Distribution AOA heater Left/right pitot tubes Left/right static ports Control PITOT & STATIC ANTI-ICE switch Monitor P/S HTR L/R OFF STBY P/S HTR OFF Citation Bravo 5H-19 Developed for Training Purposes March 2009...
Page 596 W/S BLEED AIR switch W/S ALC switch Manual bleed air control valves Rain augmenter door handle Rotary test switch: W/S TEMP position Monitor W/S AIR O'HEAT annunciator Bleed air noise Protection Circuit Breakers 5H-20 Citation Bravo Developed for Training Purposes March 2009...
Page 597 Landing The Citation Bravo landing gear system is a standard tricycle design that is electrically controlled and hydraulically actuated. Gear Each gear assembly has a single tire; the nose gear has a chined tire that deflects water and slush on the runway from the aircraft's engines.
Page 598 CAE SimuFlite 5I-2 Citation Bravo Developed for Training Purposes September 2005...
Page 599 Brake Annunciators ......5I-19 Emergency Braking ......5I-19 Citation Bravo 5I-3...
Page 600 Landing Gear System Data ..... 5I-23 Brakes/Anti-Skid Systems Data ....5I-24 5I-4 Citation Bravo Developed for Training Purposes March 2009...
Page 601 Landing Gear CAE SimuFlite Landing Gear System Citation Bravo 5I-5 5I-6 Developed for Training Purposes September 2005...
Page 602 SOLENOID SOLENOID LH BUS LANDING GEAR CONTROL VALVE STATIC FLUID EXTEND PRESSURE FLUID RETURN AIR PRESSURE CABLE LEFT MAIN RIGHT MAIN GEAR GEAR DOWN DOWN DOWN MICROSWITCH MICROSWITCH MICROSWITCH NOSE GEAR 5I-6 Citation Bravo Developed for Training Purposes March 2009...
Page 603: Landing Gear System
ACTUATOR BRAKE LINES GEAR ASSY 5I-2 OLEO ASSY TRAILING LINK ASSY 5I-1 Citation Bravo 5I-7 Developed for Training Purposes September 2005...
Page 604: Strut And Links
OFF mode above 80% N spring to release the locking ring from the actuator groove. This emergency pressure (inoperative unlocks the actuator for retraction. on the ground) 5I-4 5I-3 5I-8 Citation Bravo Developed for Training Purposes September 2005...
Page 605: Nose Gear
DOWN position, an internal actuator STEERING GEARS STEERING UNIVERSAL STEERING JOINT SHIMMY DAMPER SUPPORT BRACKET FORWARD DOOR LINKAGE HYDRAULIC TRUNNION ACTUATOR ACTUATOR ATTACH FITTING FILL INSTRUCTIONS AFT DOOR LINKAGE PLACARD BONDING JUMPER TORQUE LINKS 5I-5 Citation Bravo 5I-9 Developed for Training Purposes September 2005...
Page 606: Nose Gear Doors
Access to the shimmy damper is minated until all three gear assem- through an access plate in the nose blies are up and locked. baggage compartment floor. 5I-7 5I-6 5I-10 Citation Bravo Developed for Training Purposes September 2005...
Page 607: Audible Indication
UP, and allow the pilot to place the landing all three gear assemblies have locked gear handle in the UP position. securely in the Gear Uplocks. Citation Bravo 5I-11 Developed for Training Purposes March 2009...
Page 608: Emergency Extension
The gear down microswitches open 5I-8 the hydraulic bypass valve to return 5I-12 Citation Bravo Developed for Training Purposes March 2009...
Page 609: Emergency Air Bottle
When the landing gear is down, the microswitches engage and all three 5I-9 green lights illuminate. The red Citation Bravo 5I-13 Developed for Training Purposes March 2009...
Page 610: Nosewheel Spin-Up System (Optional)
BLEED AIR LINE MAGNETIC PICK UP RAM AIR SCOOP 5I-11 5I-10 5I-14 Citation Bravo Developed for Training Purposes March 2009...
Page 611 Landing Gear CAE SimuFlite Brake System Citation Bravo 5I-15 5I-16 Developed for Training Purposes September 2005...
Page 612 SERVO LH MAIN EXT BUS CONTROL VALVE VALVE SWITCH SKID CONTROL ANTI- SKID GENERATOR GENERATOR ANTI-SKID SUPPLY CONTROL RETURN METERED PRESSURE POWER BRAKE PRESSURE LEFT RIGHT WHEEL WHEEL MASTER CYLINDER PRESSURE 5I-16 Citation Bravo Developed for Training Purposes September 2005...
Page 613: Brake System
36Hz able only through the backup pneu- signal for each wheel revolution. matic system. These signals are sent to the control module as a variable frequency. The Citation Bravo 5I-17 Developed for Training Purposes March 2009...
Page 614: Wheel Brakes
A switch on the landing gear control The brakes can operate with or with- enables the power brake system. out anti-skid protection. When the landing gear is down, the 5I-18 Citation Bravo Developed for Training Purposes September 2005...
Page 615: Parking Brake/Valve
The annunciator, the emergency brake valve that electrically connected to the anti- meters air pressure through shuttle skid control box and power brake valves to the brake assemblies in 5I-12 5I-13 Citation Bravo 5I-19 Developed for Training Purposes March 2009...
Page 616 For for several full brake applications the most efficient use of the system, even if landing gear emergency pull the handle gently until sufficient extension was used. 5I-20 Citation Bravo Developed for Training Purposes March 2009...
Page 617: Servicing And Procedures
SKID brakes. Refer to the SimuFlite Operat- (Figure 5I-15) ing Handbook for specific procedures. TEST FIRE ANNU WARN GEAR BATT SPARE TEMP ANTI SKID OVER T/REV SPEED W/S TEMP 5I-14 Citation Bravo 5I-21 Developed for Training Purposes March 2009...
Page 618: Landing Gear Does Not Extend
A wheel brake failure is treated the system failure. Ensure that the same as a power brake system failure; ANTI-SKID switch is on and that use the emergency braking system. the anti-skid CB is engaged 5I-22 Citation Bravo Developed for Training Purposes March 2009...
Page 619: Data Summaries
Ground valve Pressurization takeoff modes Thrust reversers Radar forced standby Bleed air ground - right engine Stick shaker and stick shaker test Right main gear squat switch: Thrust reversers Stick shaker test Citation Bravo 5I-23 Developed for Training Purposes September 2005...
Page 620 Emergency air pressure gauge (Preflight) Brake accumulator Protection Circuit Breakers Emergency air bottle knob Mechanical downlock Gear/flap warning horn Miscellaneous Anti-skid must be operative for takeoff and landing on sod/dirt or gravel runways 5I-24 Citation Bravo Developed for Training Purposes March 2009...
Page 621 The master warning system provides warning of an aircraft equip- ment malfunction, indication of an unsafe operational condition that requires immediate attention, or indication of normal system operation. Citation Bravo 5J-1 Developed for Training Purposes March 2009...
Page 622 CAE SimuFlite 5J-2 Citation Bravo Developed for Training Purposes March 2009...
Page 623 Crew Oxygen Mask ......5J-17 Standard Mask ......5J-17 Citation Bravo 5J-3...
Page 624 Oxygen System ......5J-34 5J-4 Citation Bravo Developed for Training Purposes March 2009...
Page 625 Miscellaneous CAE SimuFlite Thrust Reverser System Citation Bravo 5J-5 5J-6 Developed for Training Purposes March 2009...
Page 626: Thrust Reverser System Schematic
CAE SimuFlite Thrust Reverser System Schematic 5J-6 Citation Bravo Developed for Training Purposes March 2009...
Page 627: Thrust Reversers
Powerplant Thrust Hydraulic Actuating The Citation Bravo external target- type thrust reversers (Figure 5J-1) System use two vertical doors (i.e., buckets) Reversers ) to direct exhaust gases Figure 5J-2 The aircraft hydraulic system provides forward for extra deceleration force pressure to the thrust reverser actua- for ground braking.
Page 628: Actuators
When this high pressure is applied to noids move the control valve. The the actuator, an extend force of control valve directs hydraulic pres- sure to the actuator deploy or stow 5J-8 Citation Bravo Developed for Training Purposes March 2009...
Page 629: Pressure Switch
5J-4 5J-3 Citation Bravo 5J-9 Developed for Training Purposes March 2009...
Page 630: Squat Switches
For deployment, move the reverser lever movement aft to throttle levers to IDLE and the thrust increase power for reverse thrust. 5J-10 Citation Bravo Developed for Training Purposes March 2009...
Page 631: Stowing
Return the thrust reverser levers to levers, in the event of a failure of the stow and deactivate the emergency throttle mounted deploy/stow lever, stow switches. or of the respective 28 Volt Direct Current (VDC) bus. Citation Bravo 5J-11 Developed for Training Purposes March 2009...
Page 632: Abnormal Procedures
The emergency stow switch should maintain 150 KIAS or less during be immediately activated. Ensure the approach. that the thrust reverser levers are 5J-12 Citation Bravo Developed for Training Purposes March 2009...
Page 633: Emergency Equipment
A supplemental kit in the gen mask hanger. tailcone baggage compartment contains an axe, winter clothing, and snow shoes. 5J-5 5J-6 Citation Bravo 5J-13 Developed for Training Purposes March 2009...
Page 634: Oxygen System Schematic
OVERBOARD GAGE DISCHARGE SHUTOFF INDICATOR VALVE KNOB PRESSURE REGULATOR NORMAL CREW MANUAL ONLY DROP 1,600 1,800 FILLER VALVE AND PROTECTIVE CAP OXYGEN CONTROL VALVE OXYGEN CYLINDER HIGH PRESSURE (NOSE-MOUNTED) LOW PRESSURE 5J-14 Citation Bravo Developed for Training Purposes March 2009...
Page 635: Oxygen System
Oxygen Cylinder the system is charged, regardless of the position of the shutoff valve on The Citation Bravo has an oxygen the cylinder. Markings on the gauge cylinder below the right side of the indicate the following pressure: nose compartment.
Page 636: Discharge Indicator
CREW ONLY, (e.g., smoke, fumes), select MAN- NORMAL, MANUAL DROP ( Fig- UAL DROP to route oxygen through ) allows the pilot to select ure 5J-10 the manual control valve. 5J-10 5J-9 5J-16 Citation Bravo Developed for Training Purposes March 2009...
Page 637: Passenger Oxygen
A three-position regula- two-position microphone tor control/selector knob (EMER/ selector switch on each crew- 100%/NORM) on the mask provides member's side console indepen- dently selects either the oxygen the following selections. 5J-11 5J-12 Citation Bravo 5J-17 Developed for Training Purposes March 2009...
Page 638 Each control wheel has a push- SPKR; in this mode, external radio to-talk MIC/OFF/INPH switch transmission is inoperative. to select either (Figure 5J-13) external radio transmission or interphone use via the oxygen mask microphone. 5J-13 5J-18 Citation Bravo Developed for Training Purposes March 2009...
Page 639: Preflight Inspection
2-1/2 to 3 minutes 30,000 1 to 2 minutes 35,000 30 to 60 seconds 40,000 15 to 20 seconds 45,000 9 to 15 seconds Table 5J-A; Average Time of Useful Consciousness Citation Bravo 5J-19 Developed for Training Purposes March 2009...
Page 640: Oxygen Duration Charts
2 CABIN 4 CABIN 6 CABIN 8 CABIN 10 CABIN 8,000 10,000 15,000 1000 20,000 1067 25,000 30,000 35,000 40,000 1103 Table 5J-B; Sweep on Oxygen Mask and 64 ft Cylinder 5J-20 Citation Bravo Developed for Training Purposes March 2009...
Page 641: Warning Systems
W/S TEMP Warning Controller senses the fail- 5J-14 ure and causes a steady illumination on the only Master Warning Reset switch that is still receiving power (from the opposite Main Bus). Citation Bravo 5J-21 Developed for Training Purposes March 2009...
Page 642 FMS associated lights will also illuminate. the MASTER WARNING or MASTER CAUTION lights can not be reset when the TEST selector is on the ANNU position. Optional equipment annunciation lights should also illu- minate. Table 5J-C; Rotary Test Switch Position 5J-22 Citation Bravo Developed for Training Purposes March 2009...
Page 643: Annunciator Panels
Miscellaneous CAE SimuFlite Annunciator Panels Citation Bravo 5J-23 5J-24 Developed for Training Purposes March 2009...
Page 644 WARN GEAR COCKPIT BATT SPARE TEMP CABIN AP XFER XPDR ANTI FD 1 ENG ALT SG FAIL SKID GEAR AP XFER PRI SEC OVER UNLOCKED FD 2 T/REV SPEED W/S TEMP 5J-24 Citation Bravo Developed for Training Purposes March 2009...
Page 645: Annunciator Cross- Reference
The red oil pressure warning light advises that the oil PRESS pressure is below safe limits (45 PSI) in left or right engine. Illumination of light also triggers the master warning system which will illuminate the master warning light. Citation Bravo 5J-25 Developed for Training Purposes March 2009...
Page 646 DOOR both of the nose baggage doors is/are not locked. FUEL The amber fuel filter bypass light advises that bypass of FLTR BP the left and/or right fuel filter is impending. 5J-26 Citation Bravo Developed for Training Purposes March 2009...
Page 647 This amber light is blank on airplanes with standard (BLANK) equipment. The amber nose avionics fan fail light advises that the NOSE nose avionics compartment cooling fan has failed AVN FAN Citation Bravo 5J-27 Developed for Training Purposes March 2009...
Page 648 CAUTION annunciator panel light illuminates. If the situation causing RESET the illumination clears, the lights will extinguish, when the MASTER CAUTION is pressed, it will extinguish until another amber annunciator illuminates. 5J-28 Citation Bravo Developed for Training Purposes March 2009...
Page 649 Traffic alert and collision avoidance system auto mode AUTO engaged, will automatically switch the multifunction display to TCAS information. TCAS DSP Only traffic proximity warning will be given and TCAS I display is selected. Citation Bravo 5J-29 Developed for Training Purposes March 2009...
Page 650 Continued operation may cause display failure due to overheating. IC 1 HOT The amber annunciator illuminates if one of the IC-600 IC 2 HOT computers overheats. Continued operation may cause a failure of the IC-600. 5J-30 Citation Bravo Developed for Training Purposes March 2009...
Page 651 When the red light above the rotary TEST switch is off, Test Switch the test system is inoperative and the test system is inoperative and the TEST switch is in OFF. See table 5J- D, for explanations of test positions. Citation Bravo 5J-31 Developed for Training Purposes March 2009...
Page 652 CAE SimuFlite 5J-32 Citation Bravo Developed for Training Purposes March 2009...
Page 653: Data Summaries
Emergency stow system – Bypasses normal stow system with override command to stow. THRU REV LH/RH 7.5A circuit breakers Citation Bravo 5J-33 Developed for Training Purposes March 2009...
Page 654: Oxygen System
OXYGEN/SEAT BELT circuit breaker CB is on left power junction (“J”) box and is THRU REV LH/RH (7.5A)circuit breakers Not Accessible in flight Miscellaneous Oxygen cylinder is below right nose baggage compart- ment floor. 5J-34 Citation Bravo Developed for Training Purposes March 2009...
Page 655 This chapter has two sections. The first section addresses the Chapter 5K pneumatic and air conditioning system of the Citation Bravo. The second section addresses the pressurization system. The bleed air system extracts engine bleed air and transfers it to various other systems (e.g., air conditioning, ice and rain protec-...
Page 656 CAE SimuFlite 5K-2 Citation Bravo Developed for Training Purposes July 2004...
Page 657 Abnormal Procedures......5K-19 Air Duct Overheat......5K-19 Citation Bravo 5K-3...
Page 658 Pressurization ......5K-30 5K-4 Citation Bravo Developed for Training Purposes July 2004...
Page 659 Pneumatic Systems CAE SimuFlite Pneumatic / Air Conditioning System Citation Bravo 5K-5 5K-6 Developed for Training Purposes September 2005...
Page 660 315°F (157°C) PROTECTION BLEED AIR CIRCUIT 410°F (210°C) HEAT-EXCHANGER COOLED BLEED AIR MANUAL COLD CONDITIONED AIR HEAT EXCHANGER COLD MANUAL EMERGENCY LEFT FLOW CONTROL PRESSURIZATION VALVE SHUTOFF VALVE (6 LBS / MIN) 5K-6 Citation Bravo Developed for Training Purposes September 2005...
Page 661: Bleed Air System
Major components of the distribu- tion system include: deice boots, pressurization control, windshield anti-ice, rain removal, cluster assemblies and other pneumatic systems. flow control shutoff valves BLEED AIR CLUSTER TRANSFER TUBES ELBOW ASSEMBLY 5K-1 Citation Bravo 5K-7 Developed for Training Purposes September 2005...
Page 662 ACM. shut-off valves usually remain open. GROUND SHUTOFF VALVE CHECK (MOTOR VALVE) VALVE TO ACM 5K-3 FLOW CONTROL SHUTOFF VALVES (NORMALLY OPEN) EMERGENCY PRESSURE TRANSFER VALVE TUBES (NORMALLY CLOSED) 5K-2 5K-8 Citation Bravo Developed for Training Purposes March 2009...
Page 663: Emergency Pressurization Valve
If a failure of vides cabin pressurization in the the primary pressure switch should event of loss of normal cabin pres- occur, a secondary pressure switch surization through the ACM. Citation Bravo 5K-9 Developed for Training Purposes March 2009...
Page 664: Press Source Selector
The EMER PRESS ON annunciator illu- minates when the emergency pressurization valve opens. Table 5K-A; PRESS SOURCE Switch Selection NORM EMER 5K-4 5K-10 Citation Bravo Developed for Training Purposes March 2009...
Page 665: Pneumatic Bleed Air
PNEUMATIC PRESSURE SYSTEMS REGULATOR SERVICE AIR 23 PSI SERVICE 5K-5 Citation Bravo 5K-11 Developed for Training Purposes September 2005...
Page 666 CAE SimuFlite 5K-12 Citation Bravo Developed for Training Purposes September 2005...
Page 667: Air Conditioning System
HOT AIR DUCT HEAT EXCHANGER COOLING AIR IN HEAT EXCHANGER COOLING AIR OUT THROUGH EXHAUST VENT WATER SEPARATOR AIR OUT TO CABIN WATER SECONDARY STAGE TUBE OF HEAT EXCHANGER TO TURBINE 5K-6 Citation Bravo 5K-13 Developed for Training Purposes September 2005...
Page 668: Temperature Control And Bypass Mixing Valve
Electrical control of the temperature sensor and a duct temperature sensor. INLET WATER DRAIN TUBE VORTEX VANE OUTLET POPPET RELIEF VALVE WATER COALESCER 5K-7 5K-14 Citation Bravo Developed for Training Purposes September 2005...
Page 669: Air Distribution
100°F or from the under-floor same source as the footwarmers. area when temperature in the duct is above 100°F. Citation Bravo 5K-15 Developed for Training Purposes September 2005...
Page 670: Defog Fan
A check valve prevents routes air through ducting forward of reverse flow when the cabin is pres- the instrument panel to cool radios. surized and the system is in OFF. 5K-16 Citation Bravo Developed for Training Purposes September 2005...
Page 671: Vapor Cycle Air Conditioning
(Figure 5K-8). tors - one in the forward cabin and Freon AC panel illuminates when one in the aft cabin - and a tailcone the compressor is powered. mounted condenser/compressor. 5K-8 Citation Bravo 5K-17 Developed for Training Purposes March 2009...
Page 672 CAE SimuFlite 5K-18 Citation Bravo Developed for Training Purposes September 2005...
Page 673: Servicing And Procedures
The combination of an airspeed If the ACM O’PRESS annunciator increase and warmer cabin tempera- illuminates while the aircraft is on the ture selected corrects the problem. ground, the malfunction must be Citation Bravo 5K-19 5K-20 Developed for Training Purposes March 2009...
Page 674 MAX. DIFF. POSITION SWITCH VALVE TAILCONE AREA CLIMB VACUUM SOLENOID EJECTOR/ PRESSURE DIVE REGULATOR SOLENOID (LOCATED MAX. ALT. ON PRIMARY "CABIN LIMIT" OUTFLOW VALVE VALVE) MAX. DIFF. VALVE PRIMARY OUTFLOW VALVE 5K-20 Citation Bravo Developed for Training Purposes September 2005...
Page 675: Pressurization System
CONTROL VALVE MANUAL CONTROL OUTFLOW VALVE SECONDARY VALVE OUTFLOW VALVE AFT PRESSURE BULKHEAD MANUAL PRESSURIZATION PRESSURIZATION INPUT LINE SERVICE AIR INPUT LINE STATIC INPUT LINE VACUUM EJECTOR EXHAUST LINE 5K-9 STATIC PORT Citation Bravo 5K-21 Developed for Training Purposes September 2005...
Page 676: Climb And Dive Solenoid Valves
13,000 ± 1500 feet. If the control 13,000 ±1,500 ft with bleed air vacuum exceeds the barometric available in the distribution system. reference in the cabin altitude limit 5K-22 Citation Bravo Developed for Training Purposes September 2005...
Page 677: Pressurization Controller
AUTO mode and the Cabin rate-of-change is an automatic yellow warning indication will be function of the system and is not extinguished. directly selectable. 5K-10 5K-11 Citation Bravo 5K-23 Developed for Training Purposes September 2005...
Page 678: Differential/Cabin Altimeter
10,000 ±350 ft on increas- sion. The airplane must be on the altitude. annunciator ground to enable the maintenance extinguishes on decreasing altitude mode. Once in the Maintenance prior to reaching 8,450 ft. 5K-12 5K-24 Citation Bravo Developed for Training Purposes September 2005...
Page 679: Air Duct O'heat Annunciator
The cover plate reduces leakage out performing the next step. Rotate the of the tailcone, reducing the amount PRESS SOURCE selector switch to of required pressurization air. LH, RH, or NORMAL to return all the Citation Bravo 5K-25 Developed for Training Purposes March 2009...
Page 680 CAE SimuFlite 5K-26 Citation Bravo Developed for Training Purposes September 2005...
Page 681: Abnormal/Emergency Procedures
SAFETY passenger advisory light guished. Refer to Abnormal Proce- ON. Keep the Cabin Door area clear, dures, USE OF SUPPLEMENTAL descend to a lower altitude, and land OXYGEN. as soon as practical. Citation Bravo 5K-27 Developed for Training Purposes March 2009...
Page 682: Emergency Procedures
(approximately 25 degrees), and execute emergency descent according to SOP's. At no time dur- ing this maneuver is exceeding the aircraft limitations allowed or rec- ommended. 5K-28 Citation Bravo Developed for Training Purposes March 2009...
Page 683: Air Conditioning
CABIN fan PRESS SOURCE selector Bleed air shutoff/flow control valves Monitor Cabin temperature air duct sensors Annunciators AIR DUCT O'HEAT BLD AIR GND ACM O'PRESS EMER PRESS ON Protection Circuit breakers Citation Bravo 5K-29 Developed for Training Purposes March 2009...
Page 684: Engine Bleed Air
Engine anti-ice switches Windshield bleed air switch and manual valves Surface deice switch Monitor Annunciators W/S AIR OVERHEAT SURFACE DEICE EMER PRESS ON L/R ENG ANTI ICE BLEED AIR GND Protection Circuit breakers 5K-30 Citation Bravo Developed for Training Purposes March 2009...
Page 685 CABIN ALT 10,000 FT BLD AIR GND EMER PRESS ON CABIN ALT/DIFF PRESS indicator Protection Cabin altitude limit valves Circuit breakers Emergency dump switch Oxygen system Passenger oxygen system baro-sensor 10,000 ft cabin sensor Citation Bravo 5K-31 Developed for Training Purposes March 2009...
Page 686 CAE SimuFlite 5K-32 Citation Bravo Developed for Training Purposes September 2005...
Page 687 Bravo. The PW530A is a lightweight twin-spool, front turbofan engine that produces 2,887 lbs of static thrust with a high certificated fan speed limit to permit increased cruise thrust. Citation Bravo 5L-1 Developed for Training Purposes March 2009...
Page 688 CAE SimuFlite 5L-2 Citation Bravo Developed for Training Purposes March 2009...
Page 689 Engine Anti-Icing ......5L-23 Engine Inlet Anti-Icing ..... . . 5L-23 Citation Bravo 5L-3...
Page 690 Engine Overspeed Limits..... . . 5L-31 Interturbine Temperature Limits ....5L-32 5L-4 Citation Bravo Developed for Training Purposes March 2009...
Page 691: Pratt & Whitney Pw530A Turbofan Engine
Powerplant CAE SimuFlite Pratt & Whitney PW530A Turbofan Engine Citation Bravo 5L-5 5L-6 Developed for Training Purposes March 2009...
Page 692 BYPASS (N1) TURBINE LOW PRESSURE INTAKE HIGH PRESSURE TURBINE N (CENTRIFUGAL) COMPRESSOR N FRONT IGNITER GEARBOX -STARTER AFT GEARBOX GENERATOR -OIL PUMP — HYDRAULIC PUMP — FUEL PUMP ASSEMBLY — BREATHER 5L-6 Citation Bravo Developed for Training Purposes March 2009...
Page 693: Turbofan Engines
The outer drive shaft connects the axial and centrifugal compressors (impeller) and the high pressure turbine. 5L-2 5L-1 Citation Bravo 5L-7 Developed for Training Purposes March 2009...
Page 694: Low Pressure Compressor Case
EXHAUST NOZZLE/ IGNITER VALVE THRUST REVERSER THERMOCOUPLE RIGHT SIDE OIL TANK SIGHT GLASS FUEL/OIL HEAT EXCHANGER ELECTRONIC FUEL CONTROLLER LEFT SIDE LH PRIMARY BLEED AIR EXCITER SECONDARY ACCESSORY GEARBOX BLEED 5L-3 5L-8 Citation Bravo Developed for Training Purposes March 2009...
Page 695: Turbine Section
Starter/Generator pressor through a shaft. After exiting Fuel Pump the turbine section, the gas stream enters the exhaust duct. Hydraulic Pump Oil Pump Tachometer Generator Citation Bravo 5L-9 Developed for Training Purposes March 2009...
Page 696: Engine Indicating
Fan Speed (N ) Limitations Interturbine Temperature (ITT). show fan speed from 0 to 110% Citation Bravo RPM. A green band on the tape indi- Fan Speed (N Takeoff (5 minutes) ..100%...
Page 697: Ignition System
) Limita- duct, low compressor case, and the accessory gearbox right-hand exhaust nozzle. tions Citation Bravo side. the sensor is directed at the Takeoff (5 minutes) ..100% thermocouples in the inlet and teeth of the FCU drive gearshaft that Maximum Continuous .
Page 698 ENGINE AIR ANTI-ICE BEARING 5 RH/LH MAIN DC BUSES IGNITER START IGNITION BATTERY POWER CB TEMP CITATION BRAVO UNITS 801 AND SUBSEQUENT SCAVENGE ELEMENTS SYSTEM DRAIN FILTER TO BEARINGS 1, 2, 3,4 TO BEARINGS 4 AND 5 % RPM SUPPLY...
Page 699: Powerplant Systems
If the oil passages clog, a to the oil tank. The oil filter is bypass valve opens to route oil equipped with an pressure switch to around the cooler. 5L-5 Citation Bravo 5L-13 Developed for Training Purposes March 2009...
Page 700: Oil Indicating
As the impeller rotates, it slings the oil normal operating pressures. outward. The relatively oil-free air passes through the hollow impeller shaft to a breather adapter where a tube carries it overboard for venting. 5L-14 Citation Bravo Developed for Training Purposes March 2009...
Page 701 STBY WS AIR AIR DCT AVN FAN IDLE MISTRIM P/S HTR ANTI ICE O'HEAT O'HEAT PFD 1 SHUTOFF AOA HTR AP ROLL CHECK SURFACE FAIL O'PRESS MISTRIM PFD 2 DEICE 5L-6 Citation Bravo 5L-15 Developed for Training Purposes March 2009...
Page 702: Fuel And Fuel Control System
COOLER FILTER FUEL PUMP UNIT 1ST STAGE 2ND STAGE AUTOMATIC FUEL SHUTOFF AUTOMATIC MOTIVE FUEL SHUTOFF MOTIVE FLOW FLOW FLOW FLOW METER VALVE METER VALVE MOTIVE FLOW 5L-7 TO FUEL TANK 5L-16 Citation Bravo Developed for Training Purposes March 2009...
Page 703 A valve in the flow divider altitude compensation, deceleration, splits the fuel flow into two streams: idle, and shutdown. one for the Primary Manifold, which governs initial fuel flow during Citation Bravo 5L-17 Developed for Training Purposes March 2009...
Page 704 The returning high pressure SHEATH ADAPTER COMPRESSOR DISCHARGE AIR NOZZLE SLEEVE PRIMARY PASSAGE SECONDARY NOZZLE PASSAGE STARTING FUEL FLOW MAXIMUM FUEL FLOW 5L-8 5L-18 Citation Bravo Developed for Training Purposes March 2009...
Page 705 STBY WS AIR AIR DCT CHECK AVN FAN IDLE MISTRIM P/S HTR ANTI ICE O'HEAT O'HEAT PFD 1 SHUTOFF AOA HTR AP ROLL SURFACE CHECK FAIL O'PRESS MISTRIM DEICE PFD 2 Citation Bravo 5L-19 Developed for Training Purposes March 2009...
Page 706: Ignition System
EXHAUST NOZZLE/ IGNITER VALVE THRUST REVERSER THERMOCOUPLE RIGHT SIDE OIL TANK SIGHT GLASS FUEL/OIL HEAT EXCHANGER ELECTRONIC FUEL CONTROLLER LEFT SIDE LH PRIMARY BLEED AIR EXCITER SECONDARY ACCESSORY GEARBOX BLEED 5L-10 5L-20 Citation Bravo Developed for Training Purposes March 2009...
Page 707: Control And Indication
NORM ANTI ICE / DEICE PITOT & W/S BLEED W/S ALCOHOL SURFACE ENGINE STATIC AUTO RESET LH GYRO SLAVE EXTERIOR LIGHTS VERT GYRO RECOG ANTI WING NORM AUTO COLL INSP 5L-11 Citation Bravo 5L-21 Developed for Training Purposes March 2009...
Page 708: Bleed Air For Pneumatic System
Air flowing through the The engine bleed air system uses vanes provides cooling before dis- high pressure bleed air to provide: charging through holes in the vane Engine bearing sealing trailing edges. 5L-22 Citation Bravo Developed for Training Purposes March 2009...
Page 709: Engine Anti-Icing
HOT AIR MANIFOLD ANTI-ICING AIR DUCTS DOUBLE WALL INLET CONE SHAFT DISCHARGE TO PRIMARY AIR STREAM 5L-12 Citation Bravo 5L-23 Developed for Training Purposes March 2009...
Page 710: Engine Controls
Additionally, the inner stator anti-ice corresponds to the fan and turbine valve position switch extinguishes its speeds of both engines. respective ENG ANTI-ICE annuncia- tor when the solenoid valve is open. 5L-24 Citation Bravo Developed for Training Purposes March 2009...
Page 711 The off and manually synchronize the system then compares the slave engines with the throttle levers. engine to the master engine. If the 5L-13 5L-14 Citation Bravo 5L-25 Developed for Training Purposes March 2009...
Page 712 CAE SimuFlite 5L-26 Citation Bravo Developed for Training Purposes March 2009...
Page 713: Preflight And Procedures
Firewall shutoff valve closed. ing and those listed in P & W SB No. 7001: Exxon Turbo Oil 2380 Aero Shell/Royco Turbine Oil 500 Royco Turbine Oil 560 (third gen- eration oil) Citation Bravo 5L-27 Developed for Training Purposes March 2009...
Page 714: False Engine Start (Engine Does Not Light)
Handbook for detailed check- cautionary engine shutdown. The lists. Emergency procedures for the annunciator is an independent sys- power-plant include: tem from the oil pressure indicator. 5L-28 Citation Bravo Developed for Training Purposes March 2009...
Page 715: Engine Failure Or Fire During Takeoff
ITT, engine vibration, fan/turbine RPM fluctua- Place the throttle in CUTOFF and the tions, abnormal oil temperature, or generator switch in GEN; check that the firewall shutoff valves are open. Citation Bravo 5L-29 Developed for Training Purposes March 2009...
Page 716: Emergency Restart - Two Engines
After the engine stabilizes, position boost pump ignition switches to NORM. It may be neces- sary to select the associated genera- tor RESET position momentarily to reinstate the generator. Monitor ITT 5L-30 Citation Bravo Developed for Training Purposes March 2009...
Page 717: Powerplant Limitations
Turbine Speed Turbine Speed Fan Speed Transient 99 to 102% RPM 100 to 102% 100 to 102% Over 102% Over 102% Steady ----------- 100 to 102% ------------ Over 102% Over 102% Citation Bravo 5L-31 Developed for Training Purposes March 2009...
Page 718 - (1) DETERMINE CAUSE AND CORRECT - (2) INSPECT HOT SECTION USING BORESCOPE - (3) RECORD IN ENGINE LOG BOOK AREA RETURN ENGINE TO OVERHAUL FACILITY NO ACTION REQUIRED TIME (SECONDS) 5L-32 Citation Bravo Developed for Training Purposes March 2009...

CAE SimuFlite Citation Bravo Pilot Training Manual

Quick Reference Table of

Aircraft Overview Table of

Aircraft Features Diagram

Airplane Configuration Codes

Airframe Description

Aircraft Dimensions

Danger Areas

Service Bulletins

Cae Simuflite

Pitot/Static System Schematic

Primus System Diagram

Flight Data Systems

Avionics Equipment

Other Instruments

Flight Control Systems

Preflight and Procedures

Cae Simuflite

DC System

AC System

Generator Reset Decision Tree

Preflight and Procedures

Lighting

Fire Protection Table of

Fire Protection System Schematic

Engine Fire Detection System

Engine Fire Extinguishing System

Preflight and Procedures

Data Summary

Flight Controls Table of

Primary Flight Controls Diagram

Primary Flight Controls

Speedbrakes System Schematic

Secondary Flight Controls Diagram

Secondary Flight Controls

Preflight and Procedures

Data Summaries

Fuel System Table of

Fuel System Schematic

Fuel Storage

Fuel Distribution

Servicing and Procedures

Quick Links

Chapters

Summary of Contents for CAE SimuFlite Citation Bravo