SECTION II - OPERATING LIMITATIONS

or Brake Energy Limit . . . . . . . . . . . . Refer to Procedures for Use of Approach and Landing Performance Tables in Section IV Landing Distance . . . . . . . . . . . . . . . . . Refer to Procedures for Use of Approach and Landing Performance Tables in Section IV 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 in Section VI.) 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 525FMA-00 Configuration AA U.S. 2-3 SECTION II - OPERATING LIMITATIONS MODEL 525 Figure 2-1 CENTER-OF-GRAVITY MOMENT ENVELOPE FAA APPROVED 2-4 U.S. Configuration AA 525FMA-00 SECTION II - OPERATING LIMITATIONS MODEL 525 POWERPLANT LIMITATIONS Engine Type . . . . . . . . . . . . . . . . . . . . . . . . . Williams International FJ44-1A Turbofan Engine Operating Limits . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Refer to Figure 2-2 Engine Overspeed Limits . . . . . . . . . . . . . . . . . . . . . . . . Refer to Figures 2-5 and 2-6 Takeoff/Go Around Thrust Setting . . . . . . . . . . . . . . . . . . . . . . . . . Refer to Figure 4-8 Recommended Maximum Continuous Climb Thrust Setting . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Refer to Figures 4-9 and 4-10 Recommended Maximum Continuous Cruise Thrust Setting . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Refer to Figure 4-11 and 4-11A ENGINE OPERATING LIMITS NOTES 1. ENGINE LIMIT: Time is 5 minutes, provided engine limits above are not exceeded, and begins when the throttle lever is advanced for takeoff thrust. THRUST LIMIT: Takeoff thrust (5 minute limit), for engine life to TBO, is defined in Figure 4-8. Performance data, including VMCA in Section IV is based on use of the takeoff thrust setting, (Figure 4-8). 2. Continuous operation is acceptable provided the engine limits above are not exceeded. Recommended maximum continuous climb thrust is defined in Figures 4-9 and 4-10. Recommended maximum continuous cruise thrust is defined in Figure 4-11 and 4-11A. For extended component life, to achieve TBO, the recommended limits should be observed. Performance data in Section IV is based on use of the recommended thrust setting. 3. Minimum oil pressure is 45 PSIG when operating above 80% N2; 35 PSIG when operating below 80% N 2. 4. During idle periods after high thrust operation for up to 5 minutes maximum. 5. During periods of high thrust operation for up to 5 minutes maximum. 6. Maximum allowable cold day start oil pressure is 100 psig for 5 minutes with oil pressure returning to normal range. 7. The engine should not be operated above 85% N2 until oil temperature is above 10°C. Figure 2-2 OPERATING CONDITIONS OPERATING LIMITS THRUST SETTING TIME LIMIT (MINUTES) ITT TEMPERATURE °C N2 % TURBINE RPM N1 % FAN RPM OIL PRESSURE PSIG OIL TEMPERATURE °C START REFER TO FIGURE 2-4 25 PSI MIN. (NOTE 6) -40 TO 121 (NOTE 7) IDLE CONTINUOUS 620 MAX. 56.2 ±1.3 35 MIN. -40 TO 121 (NOTE 7) TAKEOFF (NOTE 1) 820 MAX. 99.3 104.4 45 - 90 10 - 121 MAXIMUM CONTINUOUS (NOTE 2) 796 MAX. 99.3 104.4 45 - 90 (NOTE 3) 10 - 121 TRANSIENT --- REFER TO FIGURE 2-3 REFER TO FIGURE 2-5 REFER TO FIGURE 2-6 25 MIN. (NOTE 4) 100 MAX. (NOTE 5) -- FAA APPROVED 525FMA-00 Configuration AA U.S. 2-5 SECTION II - OPERATING LIMITATIONS MODEL 525 OVER TEMPERATURE LIMITS (EXCEPT STARTING) Figure 2-3 6384C6001 FAA APPROVED 2-6 U.S. Configuration AA 525FMA-00 SECTION II - OPERATING LIMITATIONS MODEL 525 OVER TEMPERATURE LIMITS (STARTING) Figure 2-4 6384C6002 FAA APPROVED 525FMA-00 Configuration AA U.S. 2-7 SECTION II - OPERATING LIMITATIONS MODEL 525 N2 ENGINE OVERSPEED LIMITS Figure 2-5 6384C6003 FAA APPROVED 2-8 U.S. Configuration AA 525FMA-00 SECTION II - OPERATING LIMITATIONS MODEL 525 N 1 ENGINE OVERSPEED LIMITS Figure 2-6 ENGINE START LIMITATIONS (Ground) Over temperature (ITT) Limits . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Refer to Figure 2-4 Maximum Tailwind Component . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 10 Knots Maximum Crosswind Component . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 12 Knots NOTE Thrust attenuator switch must be in AUTO for tailwind within ±30 degrees of the tail. Maximum Time to Light-off . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 10 Seconds NOTE Time to light-off is defined as the time after the throttle lever is moved from OFF to IDLE position until light-off is indicated. (Continued Next Page) 6384C6004 FAA APPROVED 525FMA-01 Configuration AA U.S. 2-9 SECTION II - OPERATING LIMITATIONS MODEL 525 ENGINE START LIMITATIONS (Ground) (Continued) Minimum Ambient Temperature For Battery Start (If Airplane Is Cold Soaked) . . -18°C NOTE f If the airplane is cold soaked below -35°C, it must be preheated or hangared prior to engine start. f If the battery is warm (removed and stored above -18°C) and the engine is preheated, battery starts may be conducted at ambient temperature below -18°C. f EIS may take 1 to 6 minutes to become usable after power is applied when cold soaked between -10°C to -35°C. Maximum Temperature For Engine Start . . . . . . . . . . . . . . . . . . . . . . . . . . ISA + 39°C Maximum Airport Elevation For Ground Battery Start . . . . . . . . . . . . . . . . . 10,000 Feet Maximum Airport Elevation for Ground External Power Start . . . . . . . . . . . 14,000 Feet Minimum Battery Voltage For Battery Start . . . . . . . . . . . . . . . . . . . . . . . . . . . . 24 VDC Minimum/Maximum External Power Current Capacity For Start . . . . . . 800/1100 AMPS NOTE Normal starter current draw is approximately 1000 amperes peak. External power units with variable maximum current shutoff should be set to 1100 amperes. ENGINE START LIMITATIONS (Air) Over Temperature Limits . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Refer to Figure 2-4 Airspeed/Altitude Limits . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Refer to Figure 3-1 Maximum Time to Light Off . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 10 Seconds NOTE Time to light-off is defined as the time after the throttle lever is moved from OFF to IDLE position until light-off is indicated. ENGINE POWER REDUCTION AT HIGH ALTITUDE L and R IGNITION must be selected to ON prior to reducing power to less than 90% N 2 at or above FL350. IGNITION may be returned to NORM after the engines have stabilized at the reduced power setting. 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. STARTER CYCLE LIMITATIONS Starter Limitation . . . . . . Three engine starts per 30 minutes. Three cycles of operation with a 60-second rest period between cycles is permitted. NOTE f This limitation is independent of starter power source: i.e. battery, generator assisted cross start, or external power unit. f Use of an external power source with voltage in excess of 29 VDC or current in excess of 1100 amps may damage the starter. FAA APPROVED 2-10 U.S. Configuration AA 525FMA-01 SECTION II - OPERATING LIMITATIONS MODEL 525 BATTERY LIMITATIONS The battery temperature warning system must be operational for all ground and flight operations. The battery warning system must be operational as verified by a satisfactory preflight test as contained in Section III, ELECTRICAL SYSTEM. If the BATT O'TEMP light illuminates during ground operation, do not take off until the proper maintenance procedures have been accomplished. Battery Cycle Limitations: Three engine starts per hour. Refer to Notes (2) and (3). NOTES 1. If battery limitation is exceeded, ground maintenance procedures are required. 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. 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 2-9). Generator Current (Less than 15 minutes) . . . . . . . . . . . . . . . . . . . . . . . 300 Amperes (15 minutes or more) . . . . . . . . . . . . . . . . . . . . . . . . . 250 Amperes Limit ground operation of pitot/static heat to two minutes to preclude damage to the pitot/ static tubes and angle of attack probe. Prolonged ground operation at high engine RPM with engine, wing, and/or windshield anti-ice on is prohibited. Do not operate with the wing anti-ice on more than one minute after the WING ANTI-ICE L/R annunciators have extinguished. Hot weather avionics operation temperature limitations (OAT greater than ISA+5°C): • Avionics cooling fans must be operational and verified by checking for airflow at glareshield exit vents. • With air conditioning off - Avionics operation is limited to 30 minutes and OAT less than ISA+32°C. • With air conditioning on - Avionics operation is limited to OAT less than or equal to ISA+35°C. • Avionics operation above ISA+35°C is prohibited. WINDSHIELD ICE PROTECTION FLUID Use TT-I-735 isopropyl alcohol for windshield anti-ice. HYDRAULIC FLUID Use MIL-H-83282 Type fluids only. FUEL LIMITATIONS Approved anti-icing additive must be added to all approved fuels not presently containing the additive. FUEL BOOST - ON; when LH and/or RH FUEL LOW LEVEL caution lights illuminate or at 185 pounds or less indicated fuel. Refer to Figure 2-7 for fuels that are approved for use. FAA APPROVED 525FMA-01 Configuration AA U.S. 2-11 SECTION II - OPERATING LIMITATIONS MODEL 525 FUEL LIMITATIONS CAUTION FUEL NOT HAVING ANTI-ICING ADDITIVE PREBLENDED AT THE REFINERY MUST HAVE ANTI-ICING FLUID ADDED. Fuel must contain 0.10 to 0.15 percent (by volume) anti-icing additive per MIL-I-27686 (EGME), or MIL-I-85470 (DIEGME). NOTES (1) Dupont Stadis 450 anti-ice additive or equivalent is permitted to bring fuel up to 300 conductive units, but not to exceed 1 ppm (parts per million). (2) SOHIO Biobor JF biocide additive is approved at a concentration not to exceed 20 ppm (270 ppm total additive) of elemental boron. (3) EGME/DIEGME additive is approved at a concentration not to exceed 0.15 percent volume. Figure 2-7 APPROVED OILS Exxon 2380 oil may be used pure or mixed with Mobil Jet II oil only for a maximum of 25 hours run time between major periodic Inspections. Record in the engine log book the total amount of run time with Exxon 2380 oil. Following any usage of Exxon 2380 oil, the oil tank must be drained, flushed with Mobil Jet II oil, and serviced with pure Mobil Jet II oil. (Definition of oil flush is removal of chip collector screens, and pouring one quart of Mobil Jet II oil through the oil fill port). The maximum permissible oil consumption during normal operation (engine running), is 0.023 gallons per hour during normal operation. NOTE During in-flight windmilling, the engine will vent oil overboard. Typical consumption is approximately 0.20 gallons per hour. GRADE (TYPE) (REFER TO CAUTION AND NOTE 1 BELOW) SPECIFICATION MINIMUM FUEL TEMPERATURE °C/°F MAXIMUM FUEL TEMPERATURE °C/°F JET A JET A1 JET B ASTM-D1655 -29/-20.2 -29/-20.2 -54/-65 57.2/135 57.2/135 57.2/135 JP-4 JP-5 MIL-T-5624 -54/-65 -29/-20.2 57.2/135 57.2/135 JP-8 MIL-T-83133 -29/-20.2 57.2/135 APPROVED BRAND SPECIFICATION Mobil Jet II MIL-L-23699 Mobil 254 MIL-L-23699 Exxon 2380 (Emergency only) MIL-L-23699 FAA APPROVED 2-12 U.S. Configuration AA 525FMA-00 SECTION II - OPERATING LIMITATIONS MODEL 525 UNUSABLE FUEL Fuel remaining in the fuel tanks when the fuel quantity indicator reads zero is not usable in flight. SPEED LIMITATIONS Maximum Operating Limit Speeds MMO (Above 30,500 Feet) . . . . . . . . . . . . . . . . . . . . . . . . . 0.710 Mach (Indicated) V MO (Between Sea Level and 30,500 Feet) . . . . . . . . . . . . . . . . . . . . . . . 263 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 2-8 Full application of rudder and aileron controls as well as maneuvers that involve angle-of-attack near the stall should be confined to speeds below maximum maneuvering speed. Refer to LOAD FACTOR limitations for pitch maneuvering limitations. Maximum Flap Extended Speed - VFE Partial Flaps - TAKEOFF & APPROACH Position (15°) . . . . . . . . . . . . . . 200 KIAS Full Flaps - LAND Position (35°) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 161 KIAS Ground Flaps (60°) . . . . . . . . . . . . . . . . . Intentional Selection Prohibited In Flight Maximum Speed With Flaps Failed to Ground Flaps (60°) . . . . . . . . . . . 140 KIAS Maximum Landing Gear Extended Speed - VLE . . . . . . . . . . . . . . . . . . . . . . . 186 KIAS Maximum Landing Gear Operating Speed - VLO . . . . . . . . . . . . . . . . . . . . . . 186 KIAS Maximum Speed Brake Operation Speed - V SB . . . . . . . . . . . . . . . . . . . . . . . . No Limit Maximum Autopilot Operation Speed . . . . . . . . . . . . . . . . . . 263 KIAS or 0.710 MACH NOTE For minimum control speeds (VMCA, and VMCG) refer to the respective definition in Section IV, Performance - General. WARNING THE GROUND FLAPS POSITION IS NOT LOCKED OUT IN FLIGHT. SELECTION OF GROUND FLAPS WILL SIGNIFICANTLY INCREASE DRAG AND SINK RATE. TAKEOFF AND LANDING OPERATIONAL LIMITS Maximum Altitude Limit . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 14,000 Feet Maximum Tailwind Component . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 10 Knots Maximum Ambient Temperature . . . . . . . . . ISA +39°C (Refer to Figures 2-9 and 4-7) Minimum Ambient Temperature . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . –53°C The maximum intentional asymmetric fuel differential is 200 pounds, however, controllability for safe return and landing has been demonstrated with an emergency asymmetrical difference of 600 pounds. (Continued Next Page) FAA APPROVED 525FMA-01 Configuration AA U.S. 2-13 SECTION II - OPERATING LIMITATIONS MODEL 525 TAKEOFF AND LANDING OPERATIONAL LIMITS (Continued) Takeoff with thrust attenuators stowed is prohibited for flaps 0° and for flaps 15° corrected takeoff field lengths greater than 4500 feet. The autopilot and yaw damper must be OFF for takeoff and landing. Engine synchronizer must be OFF for takeoff and landing. Cabin must be depressurized for takeoff and landing. Speed brakes must be retracted prior to 50 feet on landing. Touch and Go landings utilizing ground flaps are prohibited. Goodyear tire part number 184F68-1, and tire part numbers 030-611-0 and 031-613-8 (manufactured by BFGoodrich/Michelin) are the only nose tires approved. The nose tire must be inflated to 120 PSI +5 or –5 PSI. Maximum Tire Ground Speed . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 165 Knots ENROUTE OPERATIONAL LIMITS Maximum Operating Altitude . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 41,000 Feet Maximum Temperature . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Refer to Figure 2-9 Minimum Temperature . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Refer to Figure 2-9 Generator Load . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 300 Amperes Up to 41,000 Feet OPERATIONS AUTHORIZED This airplane is approved for day and night, VFR, IFR flight and flight into known icing when the required equipment is installed as defined within the KINDS OF OPERATIONS EQUIPMENT LIST. Acrobatic maneuvers, including spins, are prohibited. Intentional stalls with flaps at other than zero or with gear down are prohibited above 18,000 feet. MINIMUM CREW Except where otherwise prescribed by applicable operating limitations, Minimum crew for all operations: 1 Pilot, provided: a. The pilot holds a CE525(S), single pilot, type rating. b. The airplane is equipped for single pilot operation as specified in the Kinds of Operations Equipment List. c. The pilot must occupy the left pilot’s seat. Or: 1 Pilot and 1 Copilot provided: a. The pilot in command holds a CE525(S) or CE525 (second-in-command required) type rating. FAA APPROVED 2-14 U.S. Configuration AA 525FMA-01 SECTION II - OPERATING LIMITATIONS MODEL 525 MAXIMUM MANEUVERING SPEEDS EXAMPLE: Pressure Altitude - 32,500 FEET Weight - 10,600 POUNDS Maximum Maneuvering Speed - 198 KNOTS Figure 2-8 FAA APPROVED 525FMA-00 Configuration AA U.S. 2-15 SECTION II - OPERATING LIMITATIONS MODEL 525 TAKEOFF/LANDING/ENROUTE TEMPERATURE LIMITATIONS Figure 2-9 * Maximum Enroute Operating Temperature Limit is ISA +39°C ambient temperature adjusted for Ram Rise (Refer to Figure 4-3) or the Indicated RAM Air Temperature (RAT) from Figure 2-9, whichever is less. 6384C6005 FAA APPROVED 2-16 U.S. Configuration AA 525FMA-00 SECTION II - OPERATING LIMITATIONS MODEL 525 LOAD FACTOR In Flight Flaps UP Position (0°) . . . . . . . . . . . . . . . . . . . –1.52 to +3.6G at 10,600 Pounds Flaps TAKEOFF & APPROACH to LAND Position (15° to 35°) . . . . . . . . . . . . . . . . . . . . . . . . . . 0.0 to +2.0G at 10,600 Pounds These accelerations limit the angle-of-bank in turns and limit the severity of pull-up and push-over maneuvers. CABIN PRESSURIZATION LIMITATIONS Normal Cabin Pressurization Limitations . . . . . . . . . . . . . . . . 0.0 to 8.6 PSI Differential PASSENGER SEATING For all takeoffs and landings, adjustable seats must be fully upright and outboard. Maximum passenger seating, not including 2 crew seats, is five (six with optional belted toilet installed). AUDIO CONTROL PANEL Operation of the audio panel in the passenger speaker (PASS SPKR) mode is limited to required passenger briefings or emergencies. NOTE • The same side cockpit speaker is muted when PASS SPKR is selected with the audio control panel rotary switch. All incoming transmissions and auxiliary audio warnings (GPWS and TCAS, if installed) will be received only through the opposite side speaker. If both audio control switches are selected to PASS SPKR, both cockpit speakers become muted. Avoid selecting both switches to PASS SPKR at the same time. • With passenger speaker mode selected and microphone selector switch selected to oxygen mask, the cockpit speaker will not receive voice interphone communications from the oxygen mask microphone of the opposite side pilot. • Headset audio is not affected when PASS SPKR mode is selected. FAA APPROVED 525FMA-01 Configuration AA U.S. 2-17 SECTION II - OPERATING LIMITATIONS MODEL 525 INSTRUMENT MARKINGS ENGINE INDICATING SYSTEM FAN (N1) RPM INDICATORS Scale Markings . . . . . . . . . . . . . . . . . Red Line 104.5% RPM Tape/Pointer/Digital Readout . . . . . . . Red 105.4% RPM 104.5 - 105.3% RPM for 20 Sec Yellow 104.5% 105.3% < 20 Sec Tape/Pointer . . . . . . . . . . . . . . . . . . . . White 104.4% RPM Digital Readout . . . . . . . . . . . . . . . . . . Green 104.4% RPM NOTE • Tape, Pointer and Digital Readout will turn red or yellow if outside normal operating limits. • Pointer and Digital Readout will flash for 5 seconds and then remain steady if outside normal operating limits. • White Tape Pointer represents green band. INTER-TURBINE TEMPERATURE INDICATORS Engine Start Scale Markings . . . . . . . . . . . . . . . . . Red Triangle 1002°C Red Line 822°C Yellow Band 798°C - 820°C Tape/Pointer . . . . . . . . . . . . . . . . . . . . Red 1002°C White 1000°C NOTE • Tape will turn red and Pointer will flash red for five seconds and then remain steady red if outside normal starting operating limits. • Engine Running Red Line and Yellow Band do not apply while ITT Start Limit (Red Triangle) is in view. • White Tape Pointer represents Green band. Engine Running Scale Markings . . . . . . . . . . . . . . . . . Red Line 822°C Yellow Band 798°C - 820°C Tape/Pointer . . . . . . . . . . . . . . . . . . . . Red 822°C 798°C - 820°C for 5 min Yellow 798°C - 820°C for < 5 min White 796°C NOTE • Tape will turn red or yellow, the Pointer will flash red or yellow for five seconds and then remain steady if outside normal operating limits. • White Tape Pointer represents Green band. (Continued Next Page) FAA APPROVED 2-18 U.S. Configuration AA 525FMA-00 SECTION II - OPERATING LIMITATIONS MODEL 525 INSTRUMENT MARKINGS (Continued) TURBINE (N 2) RPM INDICATORS Digital Readout . . . . . . . . . . . . . . . . . . Red 99.4% RPM Green 99.3% RPM NOTE Digital Readout will flash red for five seconds and then remain steady if outside normal operating limits. OIL TEMPERATURE INDICATORS Scale Markings . . . . . . . . . . . . . . . . . Red Band 122°C Yellow Band 9°C Green Band 10°C - 121°C Pointer . . . . . . . . . . . . . . . . . . . . . . . . Red 122°C Yellow 9°C Green 10°C - 121°C Digital Readout Red 122°C Yellow 9°C NOTE • Pointer and Digital Readout will flash red or yellow for five seconds and then remain steady if outside normal operating limits. • Digital Readout is displayed only when temperature is outside normal operating limits. OIL PRESSURE INDICATORS Scale Markings . . . . . . . . . . . . . . . . . Red Band 24 PSI 101 PSI Yellow Band 25 - 34 PSI 91 - 100 PSI Green Band 35 - 90 PSI NOTE Oil Pressure Indicator Scale Markings do not change with varying N2. N2 < 80% Pointer . . . . . . . . . . . . . . . . . . . . . . . . Red 24 PSI 25 - 34 PSI 5 min 91 - 100 PSI 5 min 101 PSI Yellow 25 - 34 PSI <5 min 91 - 100 PSI <5 min Green 35 - 90 PSI (Continued Next Page) FAA APPROVED 525FMA-00 Configuration AA U.S. 2-19 SECTION II - OPERATING LIMITATIONS MODEL 525 INSTRUMENT MARKINGS (Continued) OIL PRESSURE INDICATORS (continued) Digital Readout Red 24 PSI 25 - 34 PSI 5 min 91 - 100 PSI 5 min 101 PSI Yellow 25 - 34 PSI <5 min 91 - 100 PSI <5 min N2 80% Pointer . . . . . . . . . . . . . . . . . . . . . . . . Red 34 PSI 91 - 100 PSI 5 min 101 PSI Yellow 35 - 44 PSI 91 - 100 PSI <5 min Green 45 - 90 PSI Digital Readout Red 34 PSI 91 - 100 PSI 5 min 101 PSI Yellow 35 - 44 PSI 91 - 100 PSI <5 min NOTE • Pointer and Digital Readout will flash red or yellow for five seconds and then remain steady if outside normal operating limits. • Digital Readout is displayed only when temperature is outside normal operating limits. OTHER INSTRUMENTS Airspeed Indicator . . . . . . . . . . . . . . . . . . . . . . . . . . . Red Line: 263 KIAS (0.71 MACH) Ammeter Indicators . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Red Line: 300 Amps Cabin Differential Pressure Indicator . . . . . . . . . . . . . . . . . . . . . . . . . Red Line: 8.6 PSI Green Arc: 0.0 - 8.6 PSI Oxygen Pressure Indicator . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Red Line: 2000 PSI Yellow Arc: 0 - 400 PSI Green Arc:1600 - 1800 PSI Brake and Gear Pneumatic Pressure . . . . . . . . . . . . . . . . Wide Red Arc: > 2050 PSI Indicator (In nose compartment) Narrow Red Arc: 0 - 1600 PSI Wide Yellow Arc: 1600 - 1800 PSI Wide Green Arc: 1800 - 2050 PSI Brake Hydraulic Accumulator . . . . . . . . . . . . . . . . . . Narrow Red Arc: Underpressure Pressure Indicator Light Gray Arc: Precharge Pressure (In nose compartment) Yellow Arc: Caution Wide Green Arc: Normal Operating Range Wide Red Arc: Overpressure FAA APPROVED 2-20 U.S. Configuration AA 525FMA-01 SECTION II - OPERATING LIMITATIONS MODEL 525 ENGINE INDICATING SYSTEM (EIS) If the airplane is cold soaked to a temperature between -10°C and -35°C, the liquid crystal display may experience a delay of 1 to 6 minutes, after battery power is applied, before they become useable. Preheating the cabin to 0°C or above will improve this delay to 1 minute or less. ROCKWELL COLLINS FCS-3000 INTEGRATED FLIGHT CONTROL SYSTEM 1. The Rockwell Collins Pro Line 21 Avionics System Pilot's Guide for Cessna CitationJet Publication Number 523-0780351-00X117 (X is a variable and changes with revision number), dated 02/07/00 or later revision must be immediately available to the flight crew. 2. One pilot must remain in his/her seat with the seat belt fastened during all autopilot operations. 3. Operating in the composite mode is limited to training and display failure conditions. 4. The pilot's PFD (and copilot's if installed) and MFD must be installed and operational in the normal mode for takeoff. 5. The FCS-3000 system must be verified to be operational by a satisfactory automatic preflight test (no messages on power up) prior to each flight in which the autopilot is to be used. 6. The autopilot Minimum Engage Height is 250 feet AGL. 7. The autopilot Minimum Use Height during cruise is 1000 feet AGL. 8. The autopilot Minimum Use Height during non-precision approaches is 250 feet AGL. 9. The autopilot Minimum Use Height during precision approaches is 71 feet AGL. 10. Category II approaches are not approved. 11. NAV mode during VOR operation. While operating in the NAV mode of the Flight Director using VOR as the active course, and prior to changing the active VOR frequency, the pilot must deselect the NAV mode and select HDG mode. After positive acquisition of the new VOR frequency, reselect the NAV mode of the Flight Director, and verify NAV capture and tracking of new course. 12. During VOR approaches the HDG mode must be selected for the approach until established on the final approach segment after crossing the VOR. The APPR mode may be reselected once the airplane is reestablished on the final approach segment. 13. VOR approaches must be conducted in the APPR mode. STANDBY GYRO HORIZON A satisfactory preflight test must be accomplished on the standby gyro system. FAA APPROVED 525FMA-01 Configuration AA U.S. 2-21 SECTION II - OPERATING LIMITATIONS MODEL 525 OXYGEN MASK 1. Continuous use of the supplemental oxygen system above 25,000 feet cabin altitude with passengers, or above 41,000 feet cabin altitude crew only, is prohibited. NOTE Headsets, eyeglasses or hats worn by the crew may interfere with the quick-donning capabilities of the oxygen masks. 2. For single pilot operations, a crew oxygen mask must be available for a passenger occupying the right crew seat. The mask must be checked during preflight and passenger briefed on its use. ICING LIMITATIONS NOTE • Icing conditions exist when the indicated RAT in flight is +10°C or below, and visible moisture in any form is present. • Icing conditions on the ground exist when the OAT or indicated RAT is +10°C or below and, where surface snow, slush, ice or standing water may be ingested by the engines or freeze on engine nacelles, or engine sensor probes. 1. Minimum engine N 2 speed for effective anti-icing . . . . . . . . . . . . . . . . . . . 70% N2 2. Minimum temperature for operation of tail deicing boots (Indicated RAT) . . -35°C 3. Engine anti-ice shall be ENG ON, (or ENG/WING) for operations with indicated RAT of +10°C or below when flight free of visible moisture cannot be assured. 4. After an icing encounter with inoperative tail deice boots, maximum flap deflection is 15 degrees. Refer to the Flaps Inoperative Approach and Landing Abnormal Procedure for landing with flaps 15 degrees. 5. Minimum airspeed for sustained flight in icing conditions (except approach and landing) is 160 KIAS. 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. (Continued Next Page) FAA APPROVED 2-22 U.S. Configuration AA 525FMA-01 SECTION II - OPERATING LIMITATIONS MODEL 525 OPERATIONS IN SEVERE ICING CONDITIONS (Continued) 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. KINDS OF OPERATIONS EQUIPMENT LIST This airplane may be operated in day or night VFR or IFR and flight into known icing conditions when the appropriate equipment is installed. The following equipment list identifies the systems and equipment upon which type certification for each kind of operation was predicated. The systems and items of equipment listed must be installed and operable unless: 1. The airplane is approved to be operated in accordance with a current Minimum Equipment List (MEL) issued by the FAA. Or; (Continued Next Page) FAA APPROVED 525FMA-00 Configuration AA U.S. 2-23 SECTION II - OPERATING LIMITATIONS MODEL 525 KINDS OF OPERATIONS EQUIPMENT LIST (Continued) 2. An alternate procedure is provided in the FAA Approved Airplane Flight Manual for the inoperative state of the listed equipment and all limitations are complied with. NOTE The following systems and equipment list does not include all equipment required by the FAR Parts 91 and 135 Operating Requirements. It also does not include components obviously required for the airplane to be airworthy such as wings, primary flight controls, empennage, engine, etc. SYSTEM and/or COMPONENT KIND OF OPERATION V F R D A Y V F R N I G H T I F R D A Y I F R N I G H T I C I N G COMMENTS AVIONICS 1) VHF Transceiver 2) Static Wicks 3) Transponder 4) VHF NAV Receiver 5) Cockpit Voice Recorder * 11 * * * * 11 * * * 1* 11 1* 1* * 1* 11 1* 1* * 1* 11 1* 1* * * or as required by operating regulation 15 total installed; 1 may be missing from each control surface * or as required by operating regulation * or as required by operating regulation * required for two pilot operations with six passenger seats installed ELECTRICAL 1) Battery 2) Battery Overheat Annunciator 3) DC Generator 4) DC Generator Annunciator 5) DC Loadmeter 6) DC Voltmeter and Select Switch 1 1 2 2 2 1 1 1 2 2 2 1 1 1 2 2 2 1 1 1 2 2 2 1 1 1 2 2 2 1 ENVIRONMENTAL/PRESSURIZATION 1) Pressure Regulating Shutoff Valve 2) Cabin Bleed Air Flow Control Valve 3) Outflow Valve/Safety Valve 4) Primary Door Seal 5) Secondary Door Seal 6) Pressurization Controller 7) Emergency Press Dump Valve 8) Fresh Air Fan (Continued Next Page) 2 2 2 1 1 1 1 1 2 2 2 1 1 1 1 1 2 2 2 1 1 1 1 1 2 2 2 1 1 1 1 1 2 2 2 1 1 1 1 1 required above FL310 FAA APPROVED 2-24 U.S. Configuration AA 525FMA-01 SECTION II - OPERATING LIMITATIONS MODEL 525 KINDS OF OPERATIONS EQUIPMENT LIST (Continued) SYSTEM and/or COMPONENT KIND OF OPERATION V F R D A Y V F R N I G H T I F R D A Y I F R N I G H T I C I N G COMMENTS ENVIRONMENTAL/PRESSURIZATION (Continued) 9) Defog Fan 10) Differential Press/Cabin Altitude Gage 11) Cabin Temperature Control System (except air conditioner) 12) Duct Over Temperature Annunciator 13) Cabin Altitude Warning System 1 1 1 1 1 1 1 1 1 1 1 1 1 1 1 1 1 1 1 1 1 1 1 1 1 required above FL240 EQUIPMENT AND FURNISHINGS 1) Exit Sign (lighted) 2) Seat Belt 3) Shoulder Harness 2 * * 2 * * 2 * * 2 * * 2 * * * one per occupied seat * crew seats and all occupied passenger seats FIRE PROTECTION 1) Engine Fire Detection System 2) Engine Fire Extinguisher System 3) Portable Fire Extinguisher 2 2 1 2 2 1 2 2 1 2 2 1 2 2 1 FLIGHT CONTROLS 1) Flap Position Indicator 2) Flap System (including annunciators) 3) Trim Tab Position Indicator (rudder, aileron, and elevator) 4) Trim Systems (rudder, aileron, and elevator) 5) Stick Shaker System 6) Speed Brake System (both sides) 1 1 3 3 1 1 1 1 3 3 1 1 1 1 3 3 1 1 1 1 3 3 1 1 1 1 3 3 1 1 FAA APPROVED 525FMA-01 Configuration AA U.S. 2-25 SECTION II - OPERATING LIMITATIONS MODEL 525 KINDS OF OPERATIONS EQUIPMENT LIST (Continued) SYSTEM and/or COMPONENT KIND OF OPERATION V F R D A Y V F R N I G H T I F R D A Y I F R N I G H T I C I N G COMMENTS FLIGHT/NAVIGATION INSTRUMENTS 1) PFD (Primary Flight Display) 2) MFD (Multi-Function Display) 3) AHRS 4) ADC 5) Standby Attitude Indicator 6) Standby Airspeed/Altimeter 7) Standby NAV 1 HSI 8) Clock 9) Magnetic Compass 2 1 2 2 1 1 1 0 1 2 1 2 2 1 1 1 0 1 2 1 2 2 1 1 1 1 1 2 1 2 2 1 1 1 1 1 2 1 2 2 1 1 1 1 1 Includes airspeed, altitude, VSI, HSI, attitude Includes engine indicators FUEL/ENGINE 1) Fuel Boost Pumps (including annunciators) 2) Fuel Flow Indicator System 3) Fuel Quantity System 4) Fuel Transfer System (including annunciator) 5) Firewall Shutoff System 6) Fuel Low Level Annunciators 7) Fuel Low Pressure Annunciators 8) Engine Driven Fuel Pump 9) Dual Igniter System, Each Engine (including indicator lights) 10) STBY N 1 11) Engine Oil Pressure Annunciators 12) Hydraulic Pressure On Annunciator 13) Hydraulic Flow Low Annunciators 14) Thrust Attenuators 2 2 2 1 2 2 2 2 2 2 2 1 2 2* 2 2 2 1 2 2 2 2 2 2 2 1 2 2* 2 2 2 1 2 2 2 2 2 2 2 1 2 2* 2 2 2 1 2 2 2 2 2 2 2 1 2 2* 2 2 2 1 2 2 2 2 2 2 2 1 2 2* * For thrust attenuators stowed, multiply flaps 15° takeoff field length and landing distance by 1.05. Takeoff prohibited for flaps 0° and flaps 15° corrected field lengths greater than 4500 feet. FAA APPROVED I2-26 U.S. Configuration AB 525FMA-01 SECTION II - OPERATING LIMITATIONS MODEL 525 KINDS OF OPERATIONS EQUIPMENT LIST (Continued) SYSTEM and/or COMPONENT KIND OF OPERATION V F R D A Y V F R N I G H T I F R D A Y I F R N I G H T I C I N G COMMENTS ENVIRONMENTAL/PRESSURIZATION (Continued) 9) Defog Fan 10) Differential Press/Cabin Altitude Gage 11) Cabin Temperature Control System (except air conditioner) 12) Duct Over Temperature Annunciator 13) Cabin Altitude Warning System 1 1 1 1 1 1 1 1 1 1 1 1 1 1 1 1 1 1 1 1 1 1 1 1 1 required above FL240 EQUIPMENT AND FURNISHINGS 1) Exit Sign (lighted) 2) Seat Belt 3) Shoulder Harness 2 * * 2 * * 2 * * 2 * * 2 * * * one per occupied seat * crew seats and all occupied passenger seats FIRE PROTECTION 1) Engine Fire Detection System 2) Engine Fire Extinguisher System 3) Portable Fire Extinguisher 2 2 1 2 2 1 2 2 1 2 2 1 2 2 1 FLIGHT CONTROLS 1) Flap Position Indicator 2) Flap System (including annunciators) 3) Trim Tab Position Indicator (rudder, aileron, and elevator) 4) Trim Systems (rudder, aileron, and elevator) 5) Stick Shaker System 6) Speed Brake System (both sides) 1 1 3 3 1 1 1 1 3 3 1 1 1 1 3 3 1 1 1 1 3 3 1 1 1 1 3 3 1 1 FAA APPROVED 525FMA-01 Configuration AA U.S. 2-25 SECTION II - OPERATING LIMITATIONS MODEL 525 KINDS OF OPERATIONS EQUIPMENT LIST (Continued) SYSTEM and/or COMPONENT KIND OF OPERATION V F R D A Y V F R N I G H T I F R D A Y I F R N I G H T I C I N G COMMENTS FLIGHT/NAVIGATION INSTRUMENTS 1) PFD (Primary Flight Display) 2) MFD (Multi-Function Display) 3) AHRS 4) ADC 5) Copilot’s Attitude Indicator 6) Copilot’s HSI Indicator 7) Copilot's VSI 8) Copilot's Sensitive Altimeter 9) Copilot's Airspeed Indicator 10) Standby Attitude Indicator 11) Standby Airspeed/Altimeter 12) Standby NAV 1 HSI 13) Clock 14) Magnetic Compass 1 1 2 1 1 1 0 1 1 1 1 1 0 1 1 1 2 1 1 1 0 1 1 1 1 1 0 1 1 1 2 1 1 1 1 1 1 1 1 1 1 1 1 1 2 1 1 1 1 1 1 1 1 1 1 1 1 1 2 1 1 1 1 1 1 1 1 1 1 1 Includes airspeed, altitude, VSI, HSI, attitude Includes engine indicators FUEL/ENGINE 1) Fuel Boost Pumps (including annunciators) 2) Fuel Flow Indicator System 3) Fuel Quantity System 4) Fuel Transfer System (including annunciator) 5) Firewall Shutoff System 6) Fuel Low Level Annunciators 7) Fuel Low Pressure Annunciators 8) Engine Driven Fuel Pump 9) Dual Igniter System, Each Engine (including indicator lights) 10) STBY N 1 11) Engine Oil Pressure Annunciators 12) Hydraulic Pressure On Annunciator 13) Hydraulic Flow Low Annunciators 14) Thrust Attenuators 2 2 2 1 2 2 2 2 2 2 2 1 2 2* 2 2 2 1 2 2 2 2 2 2 2 1 2 2* 2 2 2 1 2 2 2 2 2 2 2 1 2 2* 2 2 2 1 2 2 2 2 2 2 2 1 2 2* 2 2 2 1 2 2 2 2 2 2 2 1 2 2* * For thrust attenuators stowed, multiply flaps 15° takeoff field length and landing distance by 1.05. Takeoff prohibited for flaps 0° and flaps 15° corrected field lengths greater than 4500 feet FAA APPROVED I2-26.1 U.S. Configuration AC 525FMA-01 SECTION II - OPERATING LIMITATIONS MODEL 525 KINDS OF OPERATIONS EQUIPMENT LIST (Continued) SYSTEM and/or COMPONENT KIND OF OPERATION V F R D A Y V F R N I G H T I F R D A Y I F R N I G H T I C I N G COMMENTS ICE AND RAIN PROTECTION 1) Engine Anti-Ice System (including annunciators) 2) Wing Anti-Ice System (including annunciators) 3) Windshield Anti-Ice System (including annunciators and including rain removal doors) 4) Pitot-Static and AOA Heat (including annunciators) 5) Tail Deice System (including annunciators) 6) Glareshield Ice Detect Lights 2 0 1* 2* 0 0 2 0 1* 2* 0 0 2 0 1* 2* 0 0 2 0 1* 2* 0 2* 2 2 2 2* 1 2* * pilot’s required for ground defog and rain removal * single AOA system * required for night ice detection LANDING GEAR/BRAKES 1) Landing Gear Position Indicator 2) Unsafe Indicator 3) Landing Gear Aural Warning System 4) Emergency Extension System 5) Power Brake System 6) Antiskid System (including annunciator) 7) Emergency Brake System 3 1 1 1 1 1* 1 3 1 1 1 1 1* 1 3 1 1 1 1 1* 1 3 1 1 1 1 1* 1 3 1 1 1 1 1* 1 *For inoperative antiskid, multiply takeoff field length and landing distance by 1.4. LIGHTING 1) Cockpit and Instrument Light System 2) Landing Lights 3) Navigation Light 4) Anti-collision Light (Wing Tip Strobe) 5) Wing Inspection Light 6) Passenger Safety System 0 0 0 0 0 1 1 2 3 2 0 1 0 0 0 0 0 1 1 2 3 2 1* 1 0 0 0 0 1* 1 * required for night ice detection OXYGEN 1) Oxygen System Including Pressure Gage 2) Passenger Masks 3) Crew Oxygen Mask 1 * 2* 1 * 2* 1 * 2* 1 * 2* 1 * 2* required if unpressurized or if flight is above FL240 * one for each occupied seat * one for each occupied crew seat FAA APPROVED 525FMA-00 Configuration AA U.S. 2-27 SECTION II - OPERATING LIMITATIONS MODEL 525 KINDS OF OPERATIONS EQUIPMENT LIST (Continued) SYSTEM and/or COMPONENT KIND OF OPERATION V F R D A Y V F R N I G H T I F R D A Y I F R N I G H T I C I N G COMMENTS WARNING/CAUTION 1) Annunciator Panel 2) Master Caution 3) Master Warning 4) Audio Warnings (red annunciators, engine fire, dual generator fail, autopilot, minimums, altitude, and landing gear) or 4) Tone Warnings (autopilot, minimums, altitude, and landing gear) 5) Overspeed Warning System 6) Miscellaneous Annunciators, (DME, thrust attenuator stow) 1 1 1 * * 1 * 1 1 1 * * 1 * 1 1 1 * * 1 * 1 1 1 * * 1 * 1 1 1 * * 1 * pilot’s is required pilot’s is required * all audio warnings are required (Verbal Warning System) * all audio warnings are required (Tone Warning System) * all are required MISCELLANEOUS EQUIPMENT 1) FAA Approved Airplane Flight Manual 2) Collins Proline 21 Pilot's Guide 3) Approved FMS Pilot’s Manual 4) Hand Microphones 5) Passenger Briefing Cards 1 1 1 2 * 1 1 1 2 * 1 1 1 2 * 1 1 1 2 * 1 1 1 2 * * one required for each occupied seat SINGLE PILOT The following are required when the airplane is operated with a crew of one pilot; per applicable operating rules: 1) Operable FCS-3000 Autopilot. 2) Headset with microphone (must be worn). 3) FAA Approved Pilots’ Abbreviated Checklist, Cessna PN 525CLA-00 or later approved revision. 4) Provisions for storage and retention of navigation charts, accessible to the pilot from the pilot station. FAA APPROVED 2-28 U.S. Configuration AA 525FMA-01