SECTION II - OPERATING LIMITATIONS

Landing Distance . . . . . . . . Refer to Section IV - Performance, Approach and Landing Data CENTER-OF-GRAVITY LIMITS Center-of-Gravity Moment Envelope . . . . . . . . . . . . . . . . . . . . . . . . . Refer to Figure 2-1 WEIGHT AND BALANCE DATA The airplane must be operated in accordance with the approved loading schedule. (Refer to Weight and Balance Data Sheet and Model 550 Citation Bravo Weight and Balance Manual.) POWERPLANT LIMITATIONS Engine Type . . . . . . . . . . . . . . . . . . Pratt and Whitney Canada Inc. PW530A Turbofan Engine Operating Limits . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Refer to Figure 2-2 Inter-Turbine Temperatures Limits . . . . . . . . . . . . . . . . . . . . . . . . . . Refer to Figure 2-3 Engine Overspeed Limits . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Refer to Figure 2-4 Takeoff/Go-Around Thrust Setting . . . . . . . . . . . . . . . . . . . . . . . . . . Refer to Figure 4-9 Maximum Continuous Thrust Setting . . . . . . . . . . . . . . . . . . . . . . . Refer to Figure 4-10 CERTIFICATION AND OPERATIONAL LIMITATIONS ARE CONDITIONS OF THE TYPE AND AIRWORTHINESS CERTIFICATES AND MUST BE COMPLIED WITH AT ALL TIMES AS REQUIRED BY LAW. NOTICE FAA APPROVED 55BFM-03 Configuration AA U.S. 2-3 SECTION II - OPERATING LIMITATIONS MODEL 550 Figure 2-1 FORM NUMBER 1986, 16 September 1996 REVISED 23 April 1998 CENTER-OF-GRAVITY LIMITS ENVELOPE GRAPH MAXIMUM RAMP WEIGHT 15,000 MAXIMUM TAKEOFF WEIGHT 14,800 MAXIMUM LANDING WEIGHT 13,500 MAXIMUM ZERO FUEL WEIGHT 11,300 POUNDS (6804 KILOGRAMS) POUNDS (6713 KILOGRAMS) POUNDS (6123 KILOGRAMS) POUNDS (5125 KILOGRAMS) FORWARD LIMIT AT 14,800 POUNDS FS 280.97, 23.99 PERCENT MAC AFT LIMIT AT 14,800 POUNDS FS 285.85, 30.00 PERCENT MAC FORWARD LIMIT AT 9,147 POUNDS FS 276.57, 18.54 PERCENT MAC AFT LIMIT AT 8,670 POUNDS FS 285.85, 30.00 PERCENT MAC FAA APPROVED 2-4 U.S. Configuration AA 55BFM-07 SECTION II - OPERATING LIMITATIONS MODEL 550 ENGINE OPERATING LIMITS NOTES 1. The maximum start limit is 740°C; refer to Figure 2-3. 2. Normal oil pressures are 45 to 140 PSIG above 60% TURBINE RPM. Oil pressures below 45 PSIG are undesirable and should be tolerated only for the completion of the flight, preferably at reduced power setting. Oil pressures below 20 PSIG are unsafe and require that either the engine be shut down or a landing be made as soon as practical, using the minimum power required to sustain flight. 3. For starting, oil pressure may exceed 140 PSIG (not to exceed 250 PSIG) for up to 300 seconds. 4. N 1% Fan RPM is limited to either 100% N 1 or the appropriate thrust setting chart in Section IV (Standard Charts), whichever is less. 5. Ground idle (LOW) turbine RPM is 45.3 minimum, pressurization bleed air OFF, and oil temperature stabilized. Maximum ground idle (LOW) turbine RPM should not exceed the HI setting. 6. Flight idle (HI) turbine RPM is 49.4 +1.0%, -0%, pressurization bleed air OFF and oil temperature stabilized. 7. With pressurization bleed air ON, idle speeds may be up to 1.5% N 2 less than noted above. Figure 2-2 OPERATING CONDITIONS OPERATING LIMITS THRUST SETTING TIME LIMIT (MINUTES) ITT TEMPERA- TURE °C N 2 % TURBINE RPM N1 % FAN RPM OIL PRESSURE PSIG (NOTE 2) OIL TEMPERATURE °C TAKEOFF 5 700 100 100 (NOTE 4) 45 TO 140 10 TO 121 MAXIMUM CONTINUOUS CONTINUOUS 700 100 100 (NOTE 4) 45 TO 140 10 TO 121 GROUND IDLE (NOTE 7) CONTINUOUS >>> 45.3 (MIN) (NOTE 5) >>> 20 (MIN) –40 TO 121 FLIGHT IDLE (NOTE 7) CONTINUOUS 580 49.4 (MIN) (NOTE 6) >>> 20 (MIN) –40 TO 121 STARTING N/A 740 FIGURE 2-3 >>> >>> (NOTE 3) –40 (MIN) TRANSIENT 20 SEC 740 FIGURE 2-3 102 102 0-250 0 TO 121 FAA APPROVED 55BFM-10 Configuration AA U.S. 2-5 SECTION II - OPERATING LIMITATIONS MODEL 550 INTER-TURBINE TEMPERATURE LIMITS Figure 2-3 A B C AREA A - NO ACTION REQUIRED 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 6584C6049 6584C6050 A B C STARTING CONDITIONS ONLY ALL CONDITIONS EXCEPT STARTING FAA APPROVED 2-6 U.S. Configuration AA 55BFM-00 SECTION II - OPERATING LIMITATIONS MODEL 550 ENGINE OVERSPEED LIMITS Figure 2-4 ENGINE FAN INSPECTION To assure accurate fan speed thrust indication, inspect the fan for damage prior to each flight. NOTE Refer to the exterior inspection in the Normal Procedures Section of this manual for engine duct and fan inspection. BATTERY AND STARTER CYCLE LIMITATIONS Starter Limitation . . . . . . . Three engine starts per 30 minutes. Three cycles of operation with a 30-second rest period between cycles is permitted. NOTE This limitation is independent of starter power source: i.e., battery, generator assisted cross start, or external power unit. (Continued Next Page)

















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A B AREA A - NO ACTION REQUIRED AREA B - RECORD IN ENGINE LOG BOOK AREA C - RETURN ENGINE TO AN OVERHAUL FACILITY 6584C6051 FAA APPROVED I55BFM-08 Configuration AA U.S. 2-7 SECTION II - OPERATING LIMITATIONS MODEL 550 BATTERY AND STARTER CYCLE LIMITATIONS (Continued) Battery Limitation . . . . . . . Three engine starts per hour. Refer to notes 2 and 3. NOTE 1. If battery limitation is exceeded, a deep cycle including a capacity check must be accomplished to detect possible cell damage. Refer to Chapter 24 of the Maintenance Manual for procedure. 2. Three generator assisted cross starts are equal to one battery start. 3. If an external power unit is used for start, no battery cycle is counted. 4. Use of an external power source with voltage in excess of 28 VDC or current in excess of 1000 amps may damage the starter. PROLONGED GROUND OPERATION Continuous engine ground static operation up to and including five minutes at takeoff thrust is limited to ambient temperatures not to exceed 39°C above ISA. (Refer to Figure 4-9). Continuous ground operation of the starter-generator above 315 amperes is prohibited. Limit ground operation of pitot/static heat to two minutes to preclude damage to the pitot/ static tubes and the angle-of-attack probe. Timing for Avionics Ambient Temperature limits begins when all avionics are powered on. (Refer to Figure 2-5.) FAA APPROVED 2-8 U.S. Configuration AA 55BFM-09 SECTION II - OPERATING LIMITATIONS MODEL 550 AVIONICS AMBIENT TEMPERATURE LIMIT NOTE Timing for these limitations begins when all avionics are powered on. Figure 2-5 FAA APPROVED I55BFM-08 Configuration AA U.S. 2-9 SECTION II - OPERATING LIMITATIONS MODEL 550 WINDSHIELD ICE PROTECTION FLUID Use TT-I-735 isopropyl alcohol for windshield anti-ice. HYDRAULIC FLUID Use Skydrol 500B-4, or LD-4; or Hyjet, Hyjet IVA or IVA Plus only. APPROVED OILS The following oils are approved for use: MOBIL JET OIL II EXXON TURBO OIL 2380 AERO SHELL TURBINE OIL 500 MOBIL JET OIL 254 ROYCO TURBINE OIL 500 AERO SHELL TURBINE OIL 560 CASTROL 5000 ROYCO TURBINE OIL 560 In addition, oils listed for the engine in the latest revision to Pratt and Whitney Canada Inc. Maintenance Manual P/N 30J1112 are approved. CAUTION WHEN CHANGING FROM AN EXISTING LUBRICANT FORMULATION TO A “THIRD GENERATION” LUBRICANT FORMULATION (AERO SHELL/ROYCO TURBINE OIL 560 OR MOBIL JET 254) THE ENGINE MANUFACTURER STRONGLY RECOMMENDS THAT SUCH A CHANGE SHOULD ONLY BE MADE WHEN AN ENGINE IS NEW OR FRESHLY OVERHAULED. FOR ADDITIONAL INFORMATION ON USE OF THIRD GENERATION OILS, REFER TO THE ENGINE MANUFACTURER’S PERTINENT OIL SERVICE BULLETINS. Should oils of nonapproved brands or of different viscosities become intermixed, drain and flush complete oil system and refill with an approved oil in accordance with Engine Maintenance Manual instructions. Minimum oil temperature for starting is –40°C. FAA APPROVED I2-10 U.S. Configuration AA 55BFM-08 SECTION II - OPERATING LIMITATIONS MODEL 550 FUEL LIMITATIONS The following fuels are approved for use in accordance with Figure 2-6. COMMERCIAL KEROSENE JET A, JET A-1, JET B, JP-4, JP-5 and JP-8 per CPW 204 specification. NOTE JP-4, JP-5 and JP-8 type fuels have anti-icing additive preblended by the refinery. Refer to Section III, Normal Procedures for blending and checking fuel anti-ice additives. Boost Pumps - ON; when low fuel lights illuminate or at approximately 200 pounds or less indicated fuel. To crossfeed, turn boost pump OFF on side opposite selected tank. FUEL LIMITATIONS AND ADJUSTMENTS * Refer to Figure 2-6A for altitude operating limitations with JET B or JP-4 fuel. Figure 2-6 Maximum asymmetrical fuel differential for normal operations . . . . . . . . . . 200 pounds Maximum emergency asymmetrical fuel differential . . . . . . . . . . . . . . . . . . 600 pounds NOTE Flight characteristics requirements were not demonstrated with unbalanced fuel above 200 pounds. UNUSABLE FUEL Fuel remaining in the fuel tanks when the fuel quantity indicator reads zero is not usable in flight. FUEL GRADE FUEL SPECIFICATION MINIMUM FUEL TEMPERATURE (TAKEOFF) MAXIMUM FUEL TEMPERATURE (TAKEOFF) JET A ASTM-D1655 -35°C +56°C JET A-1 ASTM-D1655 -40°C +56°C JET B * ASTM-D1655 -45°C +56°C JP-4 * MIL-T-5624 -54°C +56°C JP-5 MIL-T-5624 -40°C +56°C JP-8 MIL-T-83133 -40°C +56°C FAA APPROVED 55BFM-10 Configuration AJ U.S. 2-11 SECTION II - OPERATING LIMITATIONS MODEL 550 JET B/JP-4 FUEL OPERATING LIMITATIONS Figure 2-6A SPEED LIMITATIONS Maximum Operating Limit Speeds MMO (Above 27,900 Feet) . . . . . . . . . . . . . . . . . . . . . . . . . 0.700 Mach (Indicated) V MO (Between 8000 Feet and 27,900 Feet) . . . . . . . . . . . . . . . . . . . . . . . 275 KIAS V MO (Between Sea Level and 8000 Feet) . . . . . . . . . . . . . . . . . . . . . . . . 260 KIAS The maximum operating limit speeds may not be deliberately exceeded in any regime of flight (climb, cruise or descent) unless a higher speed is authorized for flight test or pilot training. Maximum Maneuvering Speeds - V A . . . . . . . . . . . . . . . . . . . . . . . . Refer to Figure 2-7 Full application of rudder and aileron controls as well as maneuvers that involve angles-of-attack near the stall should be confined to speeds below maximum maneuvering speed. Maximum Flap Extended Speed - VFE Full Flaps - LAND Position (40°) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 174 KIAS Partial Flaps - T.O. & APPR Position (15°) . . . . . . . . . . . . . . . . . . . . . . . 200 KIAS Maximum Landing Gear Extended Speed - VLE . . . . . . . . . . . . . . . . . . . . . . . 260 KIAS Maximum Landing Gear Operating Speed - VLO (Extending) . . . . . . . . . . . . . 250 KIAS - VLO (Retracting) . . . . . . . . . . . . . 200 KIAS Maximum Speed Brake Operation Speed - V SB . . . . . . . . . . . . . . . . . . . . . . . . No Limit Minimum Control Speeds (VMCA and V MCG) . Refer to Section IV, Performance General Autopilot Operation . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 275 KIAS or 0.700 MACH FAA APPROVED I2-12 U.S. Configuration AJ 55BFM-08 SECTION II - OPERATING LIMITATIONS MODEL 550 FUEL LIMITATIONS The following fuels are approved for use in accordance with Figure 2-6. COMMERCIAL KEROSENE JET A, JET A-1, JP-5 and JP-8 per CPW 204 specification. NOTE JP-5 and JP-8 type fuels have anti-icing additive preblended by the refinery. Refer to Section III, Normal Procedures for blending and checking fuel anti-ice additives. Boost Pumps - ON; when low fuel lights illuminate or at approximately 200 pounds or less indicated fuel. To crossfeed, turn boost pump OFF on side opposite selected tank. FUEL LIMITATIONS AND ADJUSTMENTS Figure 2-6 Maximum asymmetrical fuel differential for normal operations . . . . . . . . . . 200 pounds Maximum emergency asymmetrical fuel differential . . . . . . . . . . . . . . . . . . 600 pounds NOTE Flight characteristics requirements were not demonstrated with unbalanced fuel above 200 pounds. UNUSABLE FUEL Fuel remaining in the fuel tanks when the fuel quantity indicator reads zero is not usable in flight. FUEL GRADE FUEL SPECIFICATION MINIMUM FUEL TEMPERATURE (TAKEOFF) MAXIMUM FUEL TEMPERATURE (TAKEOFF) JET A ASTM-D1655 -35°C +56°C JET A-1 ASTM-D1655 -40°C +56°C JP-5 MIL-T-5624 -40°C +56°C JP-8 MIL-T-83133 -40°C +56°C FAA APPROVED 55BFM-10 Configuration AK U.S. 2-11.1 SECTION II - OPERATING LIMITATIONS MODEL 550 SPEED LIMITATIONS Maximum Operating Limit Speeds MMO (Above 27,900 Feet) . . . . . . . . . . . . . . . . . . . . . . . . . 0.700 Mach (Indicated) V MO (Between 8000 Feet and 27,900 Feet) . . . . . . . . . . . . . . . . . . . . . . . 275 KIAS V MO (Between Sea Level and 8000 Feet) . . . . . . . . . . . . . . . . . . . . . . . . 260 KIAS The maximum operating limit speeds may not be deliberately exceeded in any regime of flight (climb, cruise or descent) unless a higher speed is authorized for flight test or pilot training. Maximum Maneuvering Speeds - V A . . . . . . . . . . . . . . . . . . . . . . . . Refer to Figure 2-7 Full application of rudder and aileron controls as well as maneuvers that involve angles-of-attack near the stall should be confined to speeds below maximum maneuvering speed. Maximum Flap Extended Speed - VFE Full Flaps - LAND Position (40°) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 174 KIAS Partial Flaps - T.O. & APPR Position (15°) . . . . . . . . . . . . . . . . . . . . . . . 200 KIAS Maximum Landing Gear Extended Speed - VLE . . . . . . . . . . . . . . . . . . . . . . . 260 KIAS Maximum Landing Gear Operating Speed - VLO (Extending) . . . . . . . . . . . . . 250 KIAS - VLO (Retracting) . . . . . . . . . . . . . 200 KIAS Maximum Speed Brake Operation Speed - V SB . . . . . . . . . . . . . . . . . . . . . . . . No Limit Minimum Control Speeds (VMCA and V MCG) . Refer to Section IV, Performance General Autopilot Operation . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 275 KIAS or 0.700 MACH FAA APPROVED I2-12.1 U.S. Configuration AK 55BFM-08 SECTION II - OPERATING LIMITATIONS MODEL 550 TAKEOFF AND LANDING OPERATIONAL LIMITS Maximum Altitude Limit . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 14,000 Feet Maximum Tailwind Components . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 10 Knots Maximum Ambient Temperature . . . . . . . . . ISA +39°C (Refer to Figures 2-8 and 4-5) Minimum Ambient Temperature . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . –54°C Takeoffs and landings are limited to paved runways Engine synchronizer must be OFF for takeoff and landing. The autopilot and yaw damper must be OFF for takeoff and landing. Goodyear part numbers 184F08-1 and BFGoodrich/Michelin part number 031-613-8, are the only nose tires approved. Tire pressure for the nose gear is 120 PSIG (±5 PSIG, unloaded); 125 PSIG (±5 PSIG, loaded). Maximum Tire Ground Speed . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 165 Knots All Vertical navigation systems must be OFF below 500 feet AGL. Takeoffs and landings are limited to paved runways unless equipped with optional Gravel Runway Modification, either factory installed or through appropriate Cessna Service Bulletin. The nosewheel must be in firm contact with the ground prior to extending speed brakes and/or deploying thrust reversers. ENROUTE OPERATIONAL LIMITS Maximum Operating Altitude . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 45,000 Feet Maximum Operating Altitude (Single Pressurization Source) . . . . . . . . . . . 43,000 Feet Maximum Ambient Temperature . . . . . . . . . . . . . . . . . . . . . . . . . . . Refer to Figure 2-8 Minimum Ambient Temperature . . . . . . . . . . . . . . . . . . . . . . . . . . . . Refer to Figure 2-8 Generator Load . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 400 Amperes Up to 35,000 Feet 315 Amperes Above 35,000 Feet OPERATIONS AUTHORIZED This airplane is approved for day, night, VFR and IFR, and flight into known icing conditions. MINIMUM CREW Minimum Flight Crew for All Operations . . . . . . . . . . . . . . . . . . . . . 1 Pilot and 1 Copilot LOAD FACTOR In Flight Flaps UP Position (0°) . . . . –1.44 to +3.6 Gs at 14,800 Pounds (6,713 Kilograms) Flaps T.O. & APPR to LAND Position (15° To 40°) . . . . . . . . . . 0.0 to +2.0 Gs at 14,800 Pounds (6,713 Kilograms) These accelerations limit the angle-of-bank in turns and limit the severity of pull-up maneuvers. Landing Flaps - T.O. & APPR to LAND Position (15° to 40°) . . . . . . . . . . . . . . +3.38 Gs at 13,500 Pounds (6,123 Kilograms) FAA APPROVED I55BFM-10 Configuration AA U.S. 2-13 SECTION II - OPERATING LIMITATIONS MODEL 550 Figure 2-7 6584C6054A EXAMPLE: Pressure Altitude - 25,000 FEET Weight - 11,500 POUNDS (5216 Kilograms) Maximum Maneuvering Speed - 176 KNOTS MAXIMUM MANEUVERING SPEEDS FAA APPROVED I2-14 U.S. Configuration AA 55BFM-10 SECTION II - OPERATING LIMITATIONS MODEL 550 Figure 2-8 6585C1006A TAKEOFF/LANDING/ENROUTE TEMPERATURE LIMITATIONS NOTE: Ambient Air Temperature Limit is Indicated Ram Air Temperature (RAT) adjusted for Ram rise (refer to Figure 4-2). FAA APPROVED I55BFM-10 Configuration AA U.S. 2-15 SECTION II - OPERATING LIMITATIONS MODEL 550 CABIN PRESSURIZATION LIMITATIONS Normal Cabin Pressurization Limitations . . . . . . . . 0.0 to 8.9 PSI, ±0.1 PSI Differential Single pressurization source maximum operation altitude . . . . . . . . . . . . . . 43,000 feet MANEUVERS No acrobatic maneuvers, including spins, are approved. No intentional stalls permitted above 25,000 feet. PASSENGER SEAT POSITION For all takeoffs and landings, seats must be fully upright and outboard. The seat just aft of the emergency exit must be to the most aft position (toward rear of airplane). Seats near the exit door must be positioned to allow access. OPERATIONS IN SEVERE ICING CONDITIONS WARNING SEVERE ICING MAY RESULT FROM ENVIRONMENTAL CONDITIONS OUTSIDE OF THOSE FOR WHICH THE AIRPLANE IS CERTIFIED. FLIGHT IN FREEZING RAIN, FREEZING DRIZZLE, OR MIXED ICING CONDITIONS (SUPERCOOLED LIQUID WATER AND ICE CRYSTALS) MAY RESULT IN ICE BUILD-UP ON PROTECTED SURFACES EXCEEDING THE CAPABILITY OF THE ICE PROTECTION SYSTEM, OR MAY RESULT IN ICE FORMING AFT OF THE PROTECTED SURFACES. THIS ICE MAY NOT SHED WHEN THE ICE PROTECTION SYSTEMS ARE USED, AND MAY SERIOUSLY DEGRADE THE PERFORMANCE AND CONTROLLABILITY OF THE AIRPLANE. All wing icing inspection lights must be operative prior to flight into known or forecast icing conditions at night. NOTE This supersedes relief provided by the Master Minimum Equipment List. Severe icing conditions that exceed those for which the airplane is certificated shall be determined by the following visual cues: 1. Unusually extensive ice accumulation on the airframe and windshield in areas not normally observed to collect ice. 2. Accumulation of ice on the upper surface of the wing aft of the protected area. If one or more of these visual cues exist: 1. Use of the autopilot is prohibited. 2. Immediately request priority handling from Air Traffic Control to facilitate a route or altitude change to exit the icing conditions. 3. Leave flaps in current position, do not extend or retract. 4. Avoid abrupt and excessive maneuvering that may exacerbate control difficulties. 5. If unusual or uncommanded roll control movement is observed, reduce angle-of-attack. Since the autopilot, when installed and operating , may mask tactile cues that indicate adverse changes in handling characteristics, use of the autopilot is prohibited when: 1. Unusual lateral trim is required while the airplane is in icing conditions. 2. Autopilot trim warnings are encountered while the airplane is in icing conditions. FAA APPROVED I2-16 U.S. Configuration AA 55BFM-10 SECTION II - OPERATING LIMITATIONS MODEL 550 AIRPLANE BATTERY If the BATT O’TEMP light illuminates during ground operation, do not take off until after the proper maintenance procedures have been accomplished. ANGLE-OF-ATTACK/STICK SHAKER SYSTEM The angle-of-attack (AOA) indicating system may be used as a reference system but does not replace the airspeed display in the PFD as a primary instrument. The AOA gage and Low Airspeed Awareness (LAA) indications must be verified in flight against Airplane Flight Manual speeds prior to use as a reference. The angle-of-attack system can be used as a reference for approach speed (1.3 V S1) at all airplane weights and center-of-gravity locations at zero, takeoff/approach and landing flap positions. 1.3 Vs1 is indicated by approximately .6 on the AOA gage and by the top of the white tape on the pilot's and copilot's airspeed indicators. If the stick shaker does not operate during the warning system test, it must be repaired before flight. FAA APPROVED I55BFM-08 Configuration AA U.S. 2-17 SECTION II - OPERATING LIMITATIONS MODEL 550 INSTRUMENT MARKINGS Left and Right Oil Pressure Indicators . . . . . . . . . . . . . . . . . . . . . . . Red Line - 20 PSI Yellow Band - 20 to 45 PSI Green Band - 45 to 140 PSI Red Triangle - 250 PSI Left and Right Turbine RPM Indicators . . . . . . . . . . . . . . . . . . . Red Light and Flashing Readout - 100% RPM Normal Operating - 45 to 100% RPM Left and Right Oil Temperature Indicators . . . . . . . . . . . . . . . . . . . . . Red Line - 121°C Green Band - 0 to 121°C Airspeed Indicator . . . . . . . . . . . . . . . . . . . Below 8000 feet MSL: Red Line - 260 KIAS Between 8000 feet and 45,000 feet MSL: Red Line - 275 KIAS - 0.700 Mach Left and Right Inter-Turbine Temperature Indicators . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Red Triangle - 740°C Red Line - 700°C Green Band - 200 to 700°C Left and Right Fan RPM Indicators . . . . . . . . . . . . . . . . . . . . . . . . . Red Line - 100.0% (Refer to Section IV for Thrust Setting Limits) Green Band - 20 to 100.0% Left and Right Ammeter Indicators . . . . . . . . . . . . . . . . . . . . . . . . Red Line - 400 Amps Yellow Arc - 315 to 400 Amperes Cabin Differential Pressure Indicator . . . . . . . . . . . . . . . . . . . . . . . . Red Line - 8.9 PSI Green Arc - 0.0 to 8.9 PSI Oxygen Pressure Indicator . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Red Line - 2000 PSI Yellow Arc - 0.0 to 400 PSI Green Arc - 1600 to 1800 PSI Brake and Gear Pneumatic Pressure Indicator (In Right Nose Compartment) . . . . . . . . . . . . . . . Wide Red Arc - Above 2050 PSI Narrow Red Arc - 0.0 to 1600 PSI Yellow Arc - 1600 to 1800 PSI Wide Green Arc - 1800 to 2050 PSI Brake Hydraulic Accumulator Pressure Indicator (In Left Nose Compartment) . . . . . . . . Light Green Arc - Static Pressure Dark Green Arc - Pressurized Pressure FAA APPROVED I2-18 U.S. Configuration AY 55BFM-10 SECTION II - OPERATING LIMITATIONS MODEL 550 AIRPLANE BATTERY If the BATT O’TEMP light illuminates during ground operation, do not take off until after the proper maintenance procedures have been accomplished. ANGLE-OF-ATTACK/STICK SHAKER SYSTEM The angle-of-attack (AOA) indicating system may be used as a reference system but does not replace the airspeed display in the PFD as a primary instrument. The AOA gage and Low Airspeed Awareness (LAA) indications must be verified in flight against Airplane Flight Manual speeds prior to use as a reference. The angle-of-attack system can be used as a reference for approach speed (1.3 V S1) at all airplane weights and center-of-gravity locations at zero, takeoff/approach and landing flap positions. 1.3 Vs1 is indicated by approximately .6 on the AOA gage and by the top of the white tape on the pilot's and copilot's airspeed indicators. If the stick shaker does not operate during the warning system test, it must be repaired before flight. FAA APPROVED I55BFM-08 Configuration AA U.S. 2-17 SECTION II - OPERATING LIMITATIONS MODEL 550 INSTRUMENT MARKINGS Left and Right Oil Pressure Indicators . . . . . . . . . . . . . . . . . . . . . . . Red Line - 20 PSI Yellow Band - 20 to 45 PSI Green Band - 45 to 140 PSI Red Triangle - 250 PSI Left and Right Turbine RPM Indicators . . . . . . . . . . . . . . . . . . . Red Light and Flashing Readout - 100% RPM Normal Operating - 45 to 100% RPM Left and Right Oil Temperature Indicators . . . . . . . . . . . . . . . . . . . . . Red Line - 121°C Green Band - 0 to 121°C Airspeed Indicator . . . . . . . . . . . . . . . . . . . Below 8000 feet MSL: Red Line - 260 KIAS Between 8000 feet and 45,000 feet MSL: Red Line - 275 KIAS - 0.700 Mach Left and Right Inter-Turbine Temperature Indicators . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Red Triangle - 740°C Red Line - 700°C Green Band - 200 to 700°C Left and Right Fan RPM Indicators . . . . . . . . . . . . . . . . . . . . . . . . . Red Line - 100.0% (Refer to Section IV for Thrust Setting Limits) Green Band - 20 to 100.0% Left and Right Ammeter Indicators . . . . . . . . . . . . . . . . . . . . . . . . Red Line - 400 Amps Yellow Arc - 315 to 400 Amperes Cabin Differential Pressure Indicator . . . . . . . . . . . . . . . . . . . . . . . . Red Line - 8.9 PSI Green Arc - 0.0 to 8.9 PSI Oxygen Pressure Indicator . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Red Line - 2000 PSI Yellow Arc - 0.0 to 400 PSI Green Arc - 1600 to 1800 PSI Brake and Gear Pneumatic Pressure Indicator (In Right Nose Compartment) . . . . . . . . . . . . . . . Wide Red Arc - Above 2050 PSI Narrow Red Arc - 0.0 to 1600 PSI Yellow Arc - 1600 to 1800 PSI Wide Green Arc - 1800 to 2050 PSI Brake Hydraulic Accumulator Pressure Indicator (In Left Nose Compartment) . . . . . . . . Light Green Arc - Static Pressure Dark Green Arc - Pressurized Pressure FAA APPROVED I2-18.1 U.S. Configuration BC 55BFM-10 SECTION II - OPERATING LIMITATIONS MODEL 550 AIRPLANE BATTERY If the BATT O’TEMP light illuminates during ground operation, do not take off until after the proper maintenance procedures have been accomplished. ANGLE-OF-ATTACK/STICK SHAKER SYSTEM The angle-of-attack (AOA) indicating system may be used as a reference system but does not replace the airspeed display in the PFD as a primary instrument. The AOA gage and Low Airspeed Awareness (LAA) indications must be verified in flight against Airplane Flight Manual speeds prior to use as a reference. The angle-of-attack system can be used as a reference for approach speed (1.3 V S1) at all airplane weights and center-of-gravity locations at zero, takeoff/approach and landing flap positions. 1.3 V S1 is indicated by approximately .6 on the AOA gage and by the top of the white tape on the pilot's and copilot's airspeed indicators. If the stick shaker does not operate during the warning system test, it must be repaired before flight. FAA APPROVED I55BFM-08 Configuration AA U.S. 2-17 SECTION II - OPERATING LIMITATIONS MODEL 550 INSTRUMENT MARKINGS Oil Pressure Indicators Scale Markings . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Red Triangle 251 PSI Red Line (MAX) f141 PSI Green Band f45 to <141 PSI Yellow Band >20 to <45 PSI Red Line (MIN) e20 PSI Analog Tape . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Red f251 PSI Red f141 PSI (f20 sec) White f 45 to <141 PSI Yellow > 20 to < 45 PSI Red e20 PSI NOTE f In reversionary mode the oil pressure indication will be digital only and the color of the digits will correspond to the scale range colors listed above. f Tape and digital readout (reversionary mode) will turn yellow or red if outside normal operating limits. f White analog tape or green digits (reversionary mode) represents green band. f During engine start and shutdown, the yellow and redline range changes will be suppressed. The red triangle will still be active. f For engine start, the oil pressure may exceed 140 PSI (not to exceed 250 PSI) for up to 300 seconds. The analog tape will turn red 20 seconds after the engine reaches idle speed if 140 PSI is still exceeded. Turbine (N2) RPM Indicators Digital Readout . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Red f100.1% RPM Green <100.1% RPM Oil Temperature Indicators Scale Markings . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Red Line >121°C Green Band f10 to e121°C Analog Tape . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Red >121°C White f10 to e121°C NOTE f In reversionary mode the oil temperature indication will be digital only and the color of the digits will correspond to the scale range colors listed above. f Tape and digital readout (reversionary mode) will turn red if outside normal operating limits. f White analog tape or green digits (reversionary mode) represents green band. (Continued Next Page) FAA APPROVED I2-18.2 U.S. Configuration AZ 55BFM-10 SECTION II - OPERATING LIMITATIONS MODEL 550 INSTRUMENT MARKINGS (Continued) Inter-Turbine Temperature Indicators Engine Start: Scale Markings . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Red Triangle 740°C Red Line f701°C Analog Tape . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Red f701°C White f150°C to <701°C Digital Readout . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Red f701°C Green f150°C to <701°C NOTE f Tape and digital readout will turn red if outside normal operating limits. f Engine Running Red Line does not apply while ITT Start Limit (Red Triangle) is displayed. f White analog tape represents green band. Engine Running: Scale Markings . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Red Line f701°C Analog Tape . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Red f701°C White f150°C to <701°C Digital Readout . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Red f701°C Green f150°C to <701°C NOTE f Tape and digital readout will turn red if outside normal operating limits. f White analog tape represents green band. Fan (N1) RPM Indicators (Refer to Section IV for Thrust Setting Limits) Scale Markings . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Red Line 100.0% RPM Analog Tape . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Red f100.1% RPM White <100.1% RPM Digital Readout . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Red f100.1% RPM Green <100.1% RPM NOTE f Tape and digital readout will turn red if outside normal operating limits. f White analog tape represents green band. (Continued Next Page) FAA APPROVED I55BFM-10 Configuration AZ U.S. 2-18.2A SECTION II - OPERATING LIMITATIONS MODEL 550 INSTRUMENT MARKINGS (Continued) Airspeed Indicator . . . . . . . . . . . . . . . . . . . Below 8000 feet MSL: Red Line - 260 KIAS Between 8000 feet and 43,000 feet MSL: Red Line - 275 KIAS - 0.700 Mach Left and Right Ammeter Indicators . . . . . . . . . . . . . . . . . . . . . . . . Red Line - 400 Amps Yellow Arc - 315 to 400 Amperes Cabin Differential Pressure Indicator . . . . . . . . . . . . . . . . . . . . . . . . Red Line - 8.9 PSI Green Arc - 0.0 to 8.9 PSI Oxygen Pressure Indicator . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Red Line - 2000 PSI Yellow Arc - 0.0 to 400 PSI Green Arc - 1600 to 1800 PSI Brake and Gear Pneumatic Pressure Indicator (In Right Nose Compartment) . . . . . . . . . . . . . . . Wide Red Arc - Above 2050 PSI Narrow Red Arc - 0.0 to 1600 PSI Yellow Arc - 1600 to 1800 PSI Wide Green Arc - 1800 to 2050 PSI Brake Hydraulic Accumulator Pressure Indicator (In Left Nose Compartment) . . . . . . . . Light Green Arc - Static Pressure Dark Green Arc - Pressurized Pressure FAA APPROVED I2-18.2B U.S. Configuration AZ 55BFM-10 SECTION II - OPERATING LIMITATIONS MODEL 550 AIRPLANE BATTERY If the BATT O’TEMP light illuminates during ground operation, do not take off until after the proper maintenance procedures have been accomplished. ANGLE-OF-ATTACK/STICK SHAKER SYSTEM The angle-of-attack (AOA) indicating system may be used as a reference system but does not replace the airspeed display in the PFD as a primary instrument. The AOA gage and Low Airspeed Awareness (LAA) indications must be verified in flight against Airplane Flight Manual speeds prior to use as a reference. The angle-of-attack system can be used as a reference for approach speed (1.3 V S1) at all airplane weights and center-of-gravity locations at zero, takeoff/approach and landing flap positions. 1.3 V S1 is indicated by approximately .6 on the AOA gage and by the top of the white tape on the pilot's and copilot's airspeed indicators. If the stick shaker does not operate during the warning system test, it must be repaired before flight. FAA APPROVED I55BFM-08 Configuration AA U.S. 2-17 SECTION II - OPERATING LIMITATIONS MODEL 550 INSTRUMENT MARKINGS Oil Pressure Indicators Scale Markings . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Red Triangle 251 PSI Red Line (MAX) f141 PSI Green Band f45 to <141 PSI Yellow Band >20 to <45 PSI Red Line (MIN) e20 PSI Analog Tape . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Red f251 PSI Red f141 PSI (f20 sec) White f 45 to <141 PSI Yellow > 20 to < 45 PSI Red e20 PSI NOTE f In reversionary mode the oil pressure indication will be digital only and the color of the digits will correspond to the scale range colors listed above. f Tape and digital readout (reversionary mode) will turn yellow or red if outside normal operating limits. f White analog tape or green digits (reversionary mode) represents green band. f During engine start and shutdown, the yellow and redline range changes will be suppressed. The red triangle will still be active. f For engine start, the oil pressure may exceed 140 PSI (not to exceed 250 PSI) for up to 300 seconds. The analog tape will turn red 20 seconds after the engine reaches idle speed if 140 PSI is still exceeded. Turbine (N2) RPM Indicators Digital Readout . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Red f100.1% RPM Green <100.1% RPM Oil Temperature Indicators Scale Markings . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Red Line >121°C Green Band f10 to e121°C Analog Tape . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Red >121°C White f10 to e121°C NOTE f In reversionary mode the oil temperature indication will be digital only and the color of the digits will correspond to the scale range colors listed above. f Tape and digital readout (reversionary mode) will turn red if outside normal operating limits. f White analog tape or green digits (reversionary mode) represents green band. (Continued Next Page) FAA APPROVED I2-18.3 U.S. Configuration BD 55BFM-10 SECTION II - OPERATING LIMITATIONS MODEL 550 INSTRUMENT MARKINGS (Continued) Inter-Turbine Temperature Indicators Engine Start: Scale Markings . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Red Triangle 740°C Red Line f701°C Analog Tape . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Red f701°C White f150°C to <701°C Digital Readout . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Red f701°C Green f150°C to <701°C NOTE f Tape and digital readout will turn red if outside normal operating limits. f Engine Running Red Line does not apply while ITT Start Limit (Red Triangle) is displayed. f White analog tape represents green band. Engine Running: Scale Markings . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Red Line f701°C Analog Tape . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Red f701°C White f150°C to <701°C Digital Readout . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Red f701°C Green f150°C to <701°C NOTE f Tape and digital readout will turn red if outside normal operating limits. f White analog tape represents green band. Fan (N1) RPM Indicators (Refer to Section IV for Thrust Setting Limits) Scale Markings . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Red Line 100.0% RPM Analog Tape . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Red f100.1% RPM White <100.1% RPM Digital Readout . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Red f100.1% RPM Green <100.1% RPM NOTE f Tape and digital readout will turn red if outside normal operating limits. f White analog tape represents green band. (Continued Next Page) FAA APPROVED I55BFM-10 Configuration BD U.S. 2-18.3A SECTION II - OPERATING LIMITATIONS MODEL 550 INSTRUMENT MARKINGS (Continued) Airspeed Indicator . . . . . . . . . . . . . . . . . . . Below 8000 feet MSL: Red Line - 260 KIAS Between 8000 feet and 43,000 feet MSL: Red Line - 275 KIAS - 0.700 Mach Left and Right Ammeter Indicators . . . . . . . . . . . . . . . . . . . . . . . . Red Line - 400 Amps Yellow Arc - 315 to 400 Amperes Cabin Differential Pressure Indicator . . . . . . . . . . . . . . . . . . . . . . . . Red Line - 8.9 PSI Green Arc - 0.0 to 8.9 PSI Oxygen Pressure Indicator . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Red Line - 2000 PSI Yellow Arc - 0.0 to 400 PSI Green Arc - 1600 to 1800 PSI Brake and Gear Pneumatic Pressure Indicator (In Right Nose Compartment) . . . . . . . . . . . . . . . Wide Red Arc - Above 2050 PSI Narrow Red Arc - 0.0 to 1600 PSI Yellow Arc - 1600 to 1800 PSI Wide Green Arc - 1800 to 2050 PSI Brake Hydraulic Accumulator Pressure Indicator (In Left Nose Compartment) . . . . . . . . Light Green Arc - Static Pressure Dark Green Arc - Pressurized Pressure FAA APPROVED I2-18.3B U.S. Configuration BD 55BFM-10 SECTION II - OPERATING LIMITATIONS MODEL 550 AUTOPILOT 1. One pilot must remain in his seat with the seat belt fastened during all autopilot operations. 2. Autopilot operation is prohibited if any comparison monitor annunciator illuminates in flight. 3. Minimum autopilot use height for enroute is 1000 feet AGL. Minimum autopilot use height for approaches is 180 feet AGL. HONEYWELL PRIMUS-1000 FLIGHT GUIDANCE SYSTEM 1. The Honeywell P-1000 Integrated Flight Control System Pilot’s Manual P/N A28-1146-109-00 revision 00 or later revision for the Cessna 550 Citation Bravo, must be immediately available to the flight crew. 2. Both flight director and autopilot coupled Category II approaches are not approved using the Honeywell P-1000 EFIS displays. 3. EFIS ground operation with the pilot’s NOSE AVN FAN FAIL annunciator light illuminated is limited to 30 minutes or until either PFD HOT or MFD HOT annunciator light illuminates, whichever occurs first. 4. Dispatch is prohibited if the PFD HOT, MFD HOT or IC HOT annunciator light is illuminated. 5. Dispatch is prohibited following a flight during which the PFD HOT, MFD HOT or IC HOT annunciator light was illuminated, until the condition is identified and corrected. 6. The pilot’s and copilot's PFDs must be installed and operational in the normal (non-reversionary) mode for takeoff. 7. The P-1000 system must be verified to be operational by a satisfactory preflight test as contained in the NORMAL procedures. 8. Dual PFD SG reversion to the MFD is prohibited. 9. Flight director and autopilot coupled VOR approaches without DME are not approved. 10. When NAV mode is engaged for enroute navigation, and VOR is the source, HDG mode must be engaged prior to changing the active VOR frequency. After positive acquisition of the new VOR frequency and course, reselect NAV mode and verify capture and tracking of the new course. STANDBY FLIGHT INSTRUMENTS 1. A satisfactory preflight test must be accomplished on the standby gyro system. 2. The standby flight instruments, ATT, ALT/ASI and HSI must be functioning prior to takeoff. FAA APPROVED 55BFM-10 Configuration AD U.S. 2-19 SECTION II - OPERATING LIMITATIONS MODEL 550 OXYGEN MASK The pressure demand sweep-on oxygen mask must be properly stowed to qualify as a quick-donning oxygen mask. NOTE Headsets, eyeglasses or hats worn by the crew may interfere with the quick-donning capabilities of the oxygen masks. SUPPLEMENTAL OXYGEN SYSTEM Continuous use of the supplemental oxygen is prohibited above: 25,000 feet when passengers are using dropout oxygen masks. 37,000 feet with crew only using pressure demand sweep-on oxygen masks. HIGH FREQUENCY (HF) AUTOMATIC DIRECTION FINDER (ADF) SYSTEMS The ADF bearing information may be erratic when keying the HF transmitter. Should this occur, disregard the ADF bearing during periods of transmission. THRUST REVERSERS Reverse thrust power must be reduced to the idle reverse detent position at 60 KIAS on landing roll. Maximum reverse thrust setting is limited to 82.3% N1 for ambient temperatures at or above -18°C, and 76% N1 for ambient temperautres below -18°C. Maximum allowable thrust reverser deployed time is 15 minutes in any one-hour period. Engine static ground operation is limited to idle power (if thrust reversers are deployed). Use of thrust reversers is prohibited during touch and go landings. The thrust reverser(s) must be verified to be operational by the Before Takeoff test in Section III Normal Procedures. Use of thrust reversers is prohibited at speeds greater than 115 KIAS. Nose down column pressure is required with thrust reversers deployed at speeds greater than 60 KIAS. The use of thrust reversers to back the airplane is prohibited. FAA APPROVED 2-20 U.S. Configuration AA 55BFM-10 SECTION II - OPERATING LIMITATIONS MODEL 550 AUTOPILOT 1. One pilot must remain in his seat with the seat belt fastened during all autopilot operations. 2. Autopilot operation is prohibited if any comparison monitor annunciator illuminates in flight. 3. Minimum autopilot use height for enroute is 1000 feet AGL. Minimum autopilot use height for approaches is 180 feet AGL. HONEYWELL PRIMUS-1000 FLIGHT GUIDANCE SYSTEM 1. The Honeywell P-1000 Integrated Flight Control System Pilot’s Manual P/N A28-1146-109-00 revision 00 or later revision for the Cessna 550 Citation Bravo, must be immediately available to the flight crew. 2. Both flight director and autopilot coupled Category II approaches are not approved using the Honeywell P-1000 EFIS displays. 3. EFIS ground operation with the pilot’s NOSE AVN FAN FAIL annunciator light illuminated is limited to 30 minutes or until either PFD HOT or MFD HOT annunciator light illuminates, whichever occurs first. 4. Dispatch is prohibited if the PFD HOT, MFD HOT or IC HOT annunciator light is illuminated. 5. Dispatch is prohibited following a flight during which the PFD HOT, MFD HOT or IC HOT annunciator light was illuminated, until the condition is identified and corrected. 6. The pilot’s and copilot's PFDs must be installed and operational in the normal (non-reversionary) mode for takeoff. 7. The P-1000 system must be verified to be operational by a satisfactory preflight test as contained in the NORMAL procedures. 8. Dual PFD SG reversion to the MFD is prohibited. 9. Flight director and autopilot coupled VOR approaches without DME are not approved. 10. When NAV mode is engaged for enroute navigation, and VOR is the source, HDG mode must be engaged prior to changing the active VOR frequency. After positive acquisition of the new VOR frequency and course, reselect NAV mode and verify capture and tracking of the new course. STANDBY FLIGHT INSTRUMENTS 1. A satisfactory preflight test must be accomplished on the standby gyro system. 2. The standby flight instruments, ATT, ALT/ASI and HSI must be functioning prior to takeoff. 3. The Meggitt standby flight display is not approved for instrument approaches. FAA APPROVED 55BFM-10 Configuration AE U.S. 2-19.1 SECTION II - OPERATING LIMITATIONS MODEL 550 OXYGEN MASK The pressure demand sweep-on oxygen mask must be properly stowed to qualify as a quick-donning oxygen mask. NOTE Headsets, eyeglasses or hats worn by the crew may interfere with the quick-donning capabilities of the oxygen masks. SUPPLEMENTAL OXYGEN SYSTEM Continuous use of the supplemental oxygen is prohibited above: 25,000 feet when passengers are using dropout oxygen masks. 37,000 feet with crew only using pressure demand sweep-on oxygen masks. HIGH FREQUENCY (HF) AUTOMATIC DIRECTION FINDER (ADF) SYSTEMS The ADF bearing information may be erratic when keying the HF transmitter. Should this occur, disregard the ADF bearing during periods of transmission. THRUST REVERSERS Reverse thrust power must be reduced to the idle reverse detent position at 60 KIAS on landing roll. Maximum reverse thrust setting is limited to 82.3% N1 for ambient temperatures at or above -18°C, and 76% N1 for ambient temperautres below -18°C. Maximum allowable thrust reverser deployed time is 15 minutes in any one-hour period. Engine static ground operation is limited to idle power (if thrust reversers are deployed). Use of thrust reversers is prohibited during touch and go landings. The thrust reverser(s) must be verified to be operational by the Before Takeoff test in Section III Normal Procedures. Use of thrust reversers is prohibited at speeds greater than 115 KIAS. Nose down column pressure is required with thrust reversers deployed at speeds greater than 60 KIAS. The use of thrust reversers to back the airplane is prohibited. FAA APPROVED 2-20 U.S. Configuration AA 55BFM-10 SECTION II - OPERATING LIMITATIONS MODEL 550 AUTOPILOT 1. One pilot must remain in his seat with the seat belt fastened during all autopilot operations. 2. Autopilot operation is prohibited if any comparison monitor annunciator illuminates in flight. 3. Minimum autopilot use height for enroute operation is 1000 feet AGL. Minimum autopilot use height for approaches is 180 feet AGL. HONEYWELL PRIMUS-1000 FLIGHT GUIDANCE SYSTEM 1. The Honeywell P-1000 Integrated Flight Control System Pilot’s Manual P/N A28-1146-109-00 revision 00 or later revision for the Cessna 550 Citation Bravo, must be immediately available to the flight crew. 2. Both flight director and autopilot coupled Category II approaches are not approved using the Honeywell P-1000 EFIS displays. 3. EFIS ground operation with the pilot’s NOSE AVN FAN FAIL annunciator light illuminated is limited to 30 minutes or until either PFD HOT or MFD HOT annunciator light illuminates, whichever occurs first. 4. Dispatch is prohibited if the PFD HOT, MFD HOT or IC HOT annunciator light is illuminated. 5. Dispatch is prohibited following a flight during which the PFD HOT, MFD HOT or IC HOT annunciator light was illuminated, until the condition is identified and corrected. 6. The pilot’s and copilot's PFDs must be installed and operational in the normal (non-reversionary) mode for takeoff. 7. The P-1000 system must be verified to be operational by a satisfactory preflight test as contained in the NORMAL procedures. 8. Dual PFD SG reversion to the MFD is prohibited. 9. Flight director and autopilot coupled VOR approaches without DME are not approved. 10. When NAV mode is engaged for enroute navigation, and VOR is the source, HDG mode must be engaged prior to changing the active VOR frequency. After positive acquisition of the new VOR frequency and course, reselect NAV mode and verify capture and tracking of the new course. STANDBY FLIGHT INSTRUMENTS 1. A satisfactory preflight test must be accomplished on the standby gyro system. 2. The standby flight instruments, ATT, ALT/ASI and HSI must be functioning prior to takeoff. 3. The standby airspeed limitations listed on the ALT/KIAS placard apply only to the standby indicators and should be used only when both pilot's and copilot's PFD airspeed tapes are unreliable or inoperative. FAA APPROVED 55BFM-10 Configuration AC U.S. 2-19.2 SECTION II - OPERATING LIMITATIONS MODEL 550 OXYGEN MASK The pressure demand sweep-on oxygen mask must be properly stowed to qualify as a quick-donning oxygen mask. NOTE Headsets, eyeglasses or hats worn by the crew may interfere with the quick-donning capabilities of the oxygen masks. SUPPLEMENTAL OXYGEN SYSTEM Continuous use of the supplemental oxygen is prohibited above: 25,000 feet when passengers are using dropout oxygen masks. 37,000 feet with crew only using pressure demand sweep-on oxygen masks. HIGH FREQUENCY (HF) AUTOMATIC DIRECTION FINDER (ADF) SYSTEMS The ADF bearing information may be erratic when keying the HF transmitter. Should this occur, disregard the ADF bearing during periods of transmission. THRUST REVERSERS Reverse thrust power must be reduced to the idle reverse detent position at 60 KIAS on landing roll. Maximum reverse thrust setting is limited to 82.3% N1 for ambient temperatures at or above -18°C, and 76% N1 for ambient temperautres below -18°C. Maximum allowable thrust reverser deployed time is 15 minutes in any one-hour period. Engine static ground operation is limited to idle power (if thrust reversers are deployed). Use of thrust reversers is prohibited during touch and go landings. The thrust reverser(s) must be verified to be operational by the Before Takeoff test in Section III Normal Procedures. Use of thrust reversers is prohibited at speeds greater than 115 KIAS. Nose down column pressure is required with thrust reversers deployed at speeds greater than 60 KIAS. The use of thrust reversers to back the airplane is prohibited. FAA APPROVED 2-20 U.S. Configuration AA 55BFM-10 SECTION II - OPERATING LIMITATIONS MODEL 550 AUTOPILOT 1. One pilot must remain in his seat with the seat belt fastened during all autopilot operations. 2. Autopilot operation is prohibited if any comparison monitor annunciator illuminates in flight. 3. Minimum autopilot use height for enroute is 1000 feet AGL. Minimum autopilot use height for approaches is 180 feet AGL. HONEYWELL PRIMUS-1000 FLIGHT GUIDANCE SYSTEM 1. The Honeywell P-1000 Integrated Flight Control System Pilot’s Manual P/N A28-1146-109-00 revision 00 or later revision for the Cessna 550 Citation Bravo, must be immediately available to the flight crew. 2. Both flight director and autopilot coupled Category II approaches are not approved using the Honeywell P-1000 EFIS displays. 3. EFIS ground operation with the pilot’s NOSE AVN FAN FAIL annunciator light illuminated is limited to 30 minutes or until either PFD HOT or MFD HOT annunciator light illuminates, whichever occurs first. 4. Dispatch is prohibited if the PFD HOT, MFD HOT or IC HOT annunciator light is illuminated. 5. Dispatch is prohibited following a flight during which the PFD HOT, MFD HOT or IC HOT annunciator light was illuminated, until the condition is identified and corrected. 6. The pilot’s and copilot's PFDs must be installed and operational in the normal (non-reversionary) mode for takeoff. 7. The P-1000 system must be verified to be operational by a satisfactory preflight test as contained in the NORMAL procedures. 8. Dual PFD SG reversion to the MFD is prohibited. 9. Flight director and autopilot coupled VOR approaches without DME are not approved. 10. When NAV mode is engaged for enroute navigation, and VOR is the source, HDG mode must be engaged prior to changing the active VOR frequency. After positive acquisition of the new VOR frequency and course, reselect NAV mode and verify capture and tracking of the new course. STANDBY FLIGHT INSTRUMENTS 1. A satisfactory preflight test must be accomplished on the standby gyro system. 2. The standby flight instruments, ATT, ALT/ASI and HSI must be functioning prior to takeoff. FAA APPROVED 55BFM-10 Configuration BB U.S. 2-19.3 SECTION II - OPERATING LIMITATIONS MODEL 550 OXYGEN MASK The pressure demand sweep-on oxygen mask must be properly stowed to qualify as a quick-donning oxygen mask. NOTE Headsets, eyeglasses or hats worn by the crew may interfere with the quick-donning capabilities of the oxygen masks. SUPPLEMENTAL OXYGEN SYSTEM Continuous use of the supplemental oxygen is prohibited above: 25,000 feet when passengers are using dropout oxygen masks. 37,000 feet with crew only using pressure demand sweep-on oxygen masks. HIGH FREQUENCY (HF) AUTOMATIC DIRECTION FINDER (ADF) SYSTEMS The ADF bearing information may be erratic when keying the HF transmitter. Should this occur, disregard the ADF bearing during periods of transmission. THRUST REVERSERS Reverse thrust power must be reduced to the idle reverse detent position at 60 KIAS on landing roll. Maximum reverse thrust setting is limited to 82.3% N1 for ambient temperatures at or above -18°C, and 76% N1 for ambient temperautres below -18°C. Maximum allowable thrust reverser deployed time is 15 minutes in any one-hour period. Engine static ground operation is limited to idle power (if thrust reversers are deployed). Use of thrust reversers is prohibited during touch and go landings. The thrust reverser(s) must be verified to be operational by the Before Takeoff test in Section III Normal Procedures. Use of thrust reversers is prohibited at speeds greater than 115 KIAS. Nose down column pressure is required with thrust reversers deployed at speeds greater than 60 KIAS. The use of thrust reversers to back the airplane is prohibited. FAA APPROVED 2-20 U.S. Configuration AA 55BFM-10 SECTION II - OPERATING LIMITATIONS MODEL 550 GROUND IDLE SWITCH The ground idle switch must be in HIGH position when conducting touch and go landings. The ground idle switch must be in HIGH position when making a generator assisted cross start from an operating engine. DEICE/ANTI-ICE SYSTEMS Operation of the deice boots below -40°C is prohibited. All anti-ice systems must be ON when operating in visible moisture and the indicated RAT is +10°C or lower. Limit ground operation of pitot static heat to 2 minutes ON with 2 minutes OFF between cycles to preclude system damage. RAT INDICATOR RAT indications on the ground are unreliable. Use reported surface temperature from the appropriate ground station for determining takeoff thrust setting. FAA APPROVED I55BFM-08 Configuration AA U.S. 2-21/2-22