Limitations. Table of Contents

Transcription

1 Limitations Table of Contents Limitations Citation/Citation I A-1 General Limitations A-3 Operational Limitations A-5 Single Pilot General and Operational Limitations (501 Models Only) A-9 System Limitations A-11 Limitations Citation II B-1 General Limitations B-1 Operational Limitations B-3 Single Pilot General and Operational Limitations.... 3B-11 System Limitations B-13 Limitations Citation II-627 and Subsequent.... 3C-1 General Limitations C-1 Operational Limitations C-3 System Limitations C-9 Limitations Citation SII D-1 General Limitations D-1 Operational Limitations D-5 System Limitations D-13 Citation I/II/SII For training only 3-1

2 3-2 For training only Citation I/II/SII

3 Limitations C0/CI Limitations Citation/Citation I General Limitations The limitations in this section apply to all models in both aircraft, except where noted. However, varied service bulletins, especially on older models, are too numerous to address in this handbook. Some of these service bulletins that apply to your specific aircraft may slightly alter the following limitations. Please refer to the AFM to verify the limits for your aircraft. Authorized Operations Day and Night VFR and IFR Flight Flight Into Known Icing Conditions Certification Status FAR Part 25 and FAR Part 23 (501) Maneuvers Aerobatic maneuvers, including spins, are prohibited. Flight Crew Requirements Pilot/Copilot See Single Pilot Operation (501 Models Only), page 3-11, for single pilot limitations. Pilot in command must have CE-500 type rating and meet FAR requirements. The copilot shall posess a multi-engine rating, an instrument rating for flight above 18,000 ft or flight into instrument meterological conditions, and meet the requirements of FAR Category II operation requires two pilots. Citation I/II/SII For training only 3A-1 May 2001

4 Passenger Seat Position For all takeoffs and landings: Seats fully upright and outboard Seats adjacent to emergency exit must be fully tracked toward rear of aircraft Maximum Baggage Loads Nose Compartment LBS Aft Cabin LBS Towing Maximum nose gear towing turning angle limit is 95 either side of center. Forcing the nose gear beyond the towing stop (95 limit), shears the bolts attaching the steering gear assembly to the cylinder. 3A-2 For training only Citation I/II/SII

5 Limitations C0/CI Operational Limitations Maximum Weights C0 001 to 070 without SB32-1: Ramp ,000 LBS Takeoff ,850 LBS Landing ,400 LBS Zero Fuel ,400 LBS With SB ,500 LBS With SB ,500 LBS C0 001 to 070 with SB32-1; 071 to 302 without SB32-23: Ramp ,650 LBS Takeoff ,500 LBS Landing ,000 LBS Zero Fuel ,400 LBS With SB ,500 LBS With SB ,500 LBS C0 001 to 070 with SB32-1 and SB32-23; 071 to 302 with SB32-23; 303 to 349 without SB57-12; 001 to 349 with SB57-12: Ramp ,000 LBS Takeoff ,850 LBS Landing ,350 LBS Zero Fuel ,400 LBS With SB ,500 LBS With SB34-23 without SB ,500 LBS Citation I/II/SII For training only 3A-3

6 CI (all): Ramp ,000 LBS Takeoff ,850 LBS Landing ,350 LBS Zero Fuel ,400 LBS With SB ,500 LBS Takeoff weight is limited by most restrictive of: maximum certified T/O weight maximum T/O weight permitted by climb requirements takeoff field length. Landing weight is limited by most restrictive of: maximum certified landing weight maximum landing weight permitted by climb requirements and brake energy limit landing distance. Center of Gravity Moment Envelope See CG charts in Flight Planning chapter. Forward Limit: At 7,500 lbs or less % OF MAC (246.4 AFT OF DATUM) At 11,850 lbs % OF MAC (250.0 AFT OF DATUM) There is a straight line variation between 18.0 and 22.6% MAC. Aft Limit % OF MAC (255.9 AFT OF DATUM) 3A-4 For training only Citation I/II/SII

7 Limitations C0/CI Speed Limits Maximum V MO /M MO (C0): M MO above 26,000 ft M INDICATED V MO 14,000 to 26,000 ft KIAS 14,000 to 28,000 ft (9,500 lb ZFW) KIAS 14,000 to 30,500 ft (10,500 lb ZFW) KIAS V MO sea level to 14,000 ft KIAS Maximum V MO /M MO (CI): M MO above 28,000 ft M INDICATED V MO 14,000 to 28,000 ft KIAS 14,000 to 30,500 ft (9,500 lb ZFW) KIAS V MO sea level to 14,000 ft KIAS Do not exceed these limits in any flight regime (climb, cruise, or descent) unless a higher speed is authorized for flight test or pilot training. Maximum Maneuvering (VA) SEE GRAPH (Figure 3-1, following page) Confine the following to speeds below VA : full rudder application full aileron control application maneuvers involving angle-of-attack near stall. Maximum Flap Extended (V FE ): Full flaps, LAND (40 ) KIAS Partial flaps, T.O.& APPR (15 ) KIAS Maximum Speedbrake Operation (V SB ) NO LIMIT Citation I/II/SII For training only 3A-5

8 Maximum Maneuvering Speeds Citation; Citation I 45,000 INDICATED PRESSURE ALTITUDE - 25,000 FEET WEIGHT - 10,500 LBS MAXIMUM MANUVERING SPEED KNOTS INDICATED PRESSURE ALTITUDE - FEET 40,000 35,000 30,000 25,000 20,000 15, LBS 8500 LBS 9500 LBS MACH ,500 LBS 11,500 LBS 11,850 LBS 10, SEA LEVEL MANUVERING SPEED (VA) - KIAS 3-1 NOTE: The above graph is the most conservative Maximum Maneuvering graph available. Speeds may vary depending on compliance with specific service bulletins. See the Airplane Flight Manual. 3A-6 For training only Citation I/II/SII

9 Limitations C0/CI Minimum Control: Air (V MCA ).. BELOW STALL SPEED FOR ALL WEIGHTS Ground (V MCG ) KIAS Maximum Tire Ground Speed: C0 001 to 070, without SB32-1 or SB KTS C0 001 to 070 with SB32-1 or SB21-9 and 071 to 349; CI KTS Autopilot Operation: C0 without SB KIAS/0.705M C0 with SB57-12; CI KIAS/0.705M Maximum Landing Gear Speeds: V LE KIAS V LO KIAS Turbulent Air Penetration.... RECOMMENDED 180 KIAS Takeoff and Landing Operational Limits Maximum Altitude: C0 001 to 070 without SB32-1 or SB ,000 FT C0 001 to 070 with SB32-1 or SB21-9; C0 071 and subsequent; CI ,000 FT Maximum Tailwind Component KTS Maximum Crosswind DEMONSTRATED 25 KTS Maximum Water/Slush on Runway IN Maximum Ambient Temperature ISA + 39 C (71 F) Minimum Ambient Temperature C (-65 F) Autopilot must be off for takeoff/landing. Vertical navigation system must be off below 500 ft AGL. Citation I/II/SII For training only 3A-7

10 Enroute Operational Limits Maximum Operating Altitude: C0 001 to 213 without SB ,000 FT C0 001 to 213 with SB21-9; C0 214 and subsequent; CI ,000 FT Temperature Limits C (-65 F) TO ISA + 39 C (71 F) Generator Load: To 35,000 ft A Above 35,000 ft A Load Factors In Flight, Flaps: Up (0 ) TO +3.8 G T.O. & APPR to LAND (15 to 40 ) TO +2.0 G These accelerations limit angle-of-bank in turns and severity of pullup maneuvers. Landing G 3A-8 For training only Citation I/II/SII

11 Limitations C0/CI Single Pilot General and Operational Limitations (501 Models Only) Conduct single pilot operations according to data established for C0 and CI, with the following additional constraints. SP Certification Status FAR Part 23 SP Requirements Pilot must sit in the left seat. The following equipment must be operating: one autopilot with approach coupling one flight director one boom microphone or headset-mounted microphone transponder identifier switch on pilot s control wheel. The pilot must have a CE-500 type rating and meet the requirements of FAR for single pilot operation (501 models only). Citation I/II/SII For training only 3A-9

12 3A-10 For training only Citation I/II/SII

13 Limitations C0/CI System Limitations Avionics and Communications Angle-of-Attack May be used as reference, but does not replace primary airspeed indicator as a primary instrument. Autopilot One pilot must remain in his seat with seat belt fastened during all AP operations. AP current monitor must be functionally tested prior to inflight use (C0 275 and subsequent; CI). Autopilot must be off for takeoff/landing. Dual Flight Director Installation The copilot s second attitude indicating system must be installed and remain operating throughout the flight for those aircraft equipped with dual flight directors. HF/ADF Systems The ADF bearing information may be erratic during HF transmissions. If this occurs, disregard ADF bearing during transmission periods. Drag Chute (Optional) The aircraft s nose wheel must be on the ground for drag chute operation. Maximum speed for drag chute deployment is 125 KIAS. Simultaneous use of drag chute and thrust reversers is prohibited. If chute deploys or jettisons above 110 kts, inspect the mechanism for possible damage. Citation I/II/SII For training only 3A-11

14 Electrical and Lighting Battery If BATT O HEAT annunciator illuminates during ground operation, do not take off until proper maintenance is accomplished. Limit engine starts to three per hour. If battery limitation is exceeded, accomplish a deep cycle including a capacity check to detect possible cell damage. See Maintenance Manual for procedure. NOTE: Three generator-assisted cross-starts are equal to one battery start. C0 001 to 274: Three external power starts are equal to one battery start. C0 275 and subsequent; CI: Do not count external power start as battery cycle. Generator Operating Limits Generator Load: To 35,000 ft A Above 35,000 ft A Continuous operation of the starter-generator above 325A is prohibited. Starter Limitation Limit starter to three engine starts per 30 minutes with a 30- second rest between cycles. This limitation is independent of the starter power source (i.e., battery, generator-assisted cross-start, or GPU). External Power Limitation With GPU connected to aircraft, limit GPU output to maximum of 1,000 amps and 28V DC. Exceeding these limits may damage the starter. 3A-12 For training only Citation I/II/SII

15 Limitations C0/CI Fuel System Fuel remaining in the fuel tank when the quantity indicator reads zero is not usable in flight. Anti-Ice Additive Anti-icing must be added to all fuels that do not contain the additive. Military JP-4, JP-5, and JP-8 have refinery preblended anti-icing. WARNING: Anti-icing additives containing ethylene glycol monomethyl ether (EGME) or diethylene glycol monomethyl ether (DIEGME) are harmful if inhaled, swallowed or absorbed through the skin, and cause eye irritation. Also, they are combustible. Before using this material, refer to all safety information on the container. Additive Concentration Range Minimum Maximum Hi-Flo EGME 20 fluid ounces 20 fluid ounces per 260 gallons per 104 gallons 0.06% 0.15% DIEGME 20 fluid ounces 20 fluid ounces per 156 gallons per 104 gallons 0.10% 0.15% CAUTION: Ensure that additive is directed into flowing fuel stream and additive flow is started after fuel flow. The additive should be stopped before fuel flow stops. Do not allow concentrated additive to contact coated interior of the fuel tank or the aircraft s painted surface. Citation I/II/SII For training only 3A-13

16 Boost Pumps Turn on boost pumps when FUEL LEVEL LO annunciators illuminate or indicated fuel is below 170 lbs. Check that the CB is in. Fuel Imbalance Maximum Fuel Imbalance LBS Aviation Gasoline All grades of MIL-G-5572 avgas are permitted for a maximum of 50 hours or 3,500 gallons between overhauls, provided: maximum fuel and ambient air temperature is within limits +32 C (90 F) boost pumps are on hours of avgas usage are entered in engine logbook maximum operating altitude is 25,000 ft. Jet Fuel The following fuels are approved per specification CPW 204, commercial kerosene: Jet A, Jet A-1, A-2, and Jet B JP-4, JP-5, and JP-8 3A-14 For training only Citation I/II/SII

17 Limitations C0/CI Fuel Limitations and Adjustments Jet A, A-1, -2; Jet B; JP-4 Avgas JP-5, JP-8 Min Fuel Temp., -20 F -65 F -65 F T.O. (-29 C) (-54 C) (-54 C) Max Fuel Temp 118 F 118 F 90 F (48 C) (48 C) (32 C) Max Altitude 35,000 ft 1 35,000 ft 1 25,000 ft 41,000 ft 2 41,000 ft 2 Max Asymmetric 800 lbs 800 lbs 800 lbs Fuel Fuel Control Density 1 C0 001 to 213 without SB C0 001 to 213 with SB 21-9; C0 214 to 233; 235 to 249; CI Citation I/II/SII For training only 3A-15

18 Hydraulic System Approved Fluids Skydrol 500 A, B, B-4, C or LD-4 Hyjet, Hyjet W, III, IV or IVA. Ice and Rain Protection Engine Anti-Ice System Engine anti-ice is required for taxi, takeoff, and in flight when operating in visible moisture with OAT at +4 to -30 C (+40 to -22 F). For sustained ground operations, operate for one out of every four minutes at 65% turbine RPM or above. CAUTION: Limit ground operation of pitot/static heat to two minutes to prevent damage to the angle-of-attack system. Windshield Alcohol Anti-Ice System Use TT-I-735 isopropyl alcohol for windshield anti-ice. The backup alcohol system is sufficient for 10 minutes. Windshield Bleed Air Anti-Ice System Activate windshield bleed air when operating in visible moisture with OAT at +4 to -30 C (+40 to -22 F) to prevent ice on windshield. Wing Deice System Wing deice is required in flight when wing ice builds up to 1/4 to 1/2 inch thickness (use stall strip as gage). 3A-16 For training only Citation I/II/SII

19 Limitations C0/CI Landing Gear and Brakes Approved Nose Tires Goodyear 184F10-1 and 184F10-2 Goodrich Brake and Optional Anti-Skid Systems Emergency Air Pressure ,800 TO 2,000 PSI Relief valve ruptures at 4,000 PSI. Tire Pressures Main Wheels: C0 001 to 051 without SB (+3,-1) PSI C0 052 to 070 without SB (+3,-1) PSI C0 001 to 070 with SB32-1; C0 071 and sub.; CI ±5 PSI Nose Wheel ±5 PSI Speeds Tire Ground Speed: C0 001 to 070 without SB32-1 or SB KTS C0 001 to 070 with SB32-1 or SB21-9; C0 071 to 349; CI KTS Maximum Landing Gear Operating (V LO /V LE ) KIAS If installed, the anti-skid must be operative for takeoff and landing on sod/dirt or gravel runways. Citation I/II/SII For training only 3A-17

20 Oxygen The standard diluter-demand oxygen mask must be positioned around the neck above FL250 to qualify as quick-donning. The optional pressure-demand sweep-on oxygen mask must be properly stowed to qualify as quick-donning. Thrust Reversers Reduce reverse thrust power to the idle reverse detent position at 60 KIAS on landing roll. Maximum allowable thrust reverser deployed time is 15 minutes in any one hour period. Thrust reversing on sod/dirt or gravel runways is prohibited. Simultaneous use of the drag chute and thrust reversers is prohibited. Maximum reverse thrust setting is limited to takeoff thrust. CAUTION: Do not advance primary throttle after moving thrust reverser lever to stow until the UNLOCK light extinguishes. Engine static ground operation is limited to less than 80% N1, for ambient temperature at sea level above 46 C (114 F). WARNING: Do not attempt to restow reversers and takeoff once reversers have started to deploy. 3A-18 For training only Citation I/II/SII

21 Limitations C0/CI Powerplant Pratt and Whitney Turbofan JT15D-1, 1A or 1B Thrust Takeoff, Standard Day at Sea Level ,200 LBS Engine Fan Inspection To ensure accurate fan speed thrust indication, inspect fan for damage prior to each flight. Engine Operating Limits Thrust Setting Time Limit ITT Temp N 2 N 1 Oil Press Oil Temp Takeoff 5 minutes 700 C 95% RPM 99% RPM (1) 65 to 80 PSIG 10 C to red line 102.1% RPM (1A) % RPM (1B) Max Continuous Continuous 680 C 95% RPM 99% RPM (1) 65 to 80 PSIG 0 C to red line 102.1% RPM (1A) % RPM (1B) Max Cruise Continuous 670 C 95% RPM 99% RPM (1) 65 to 80 PSIG 0 C to red line 102.1% RPM (1A) % RPM (1B) Idle Continuous 580 C 46% RPM ±0.5% 35 PSIG (min) -40 C to red line Start 700 C (2 sec) -40 C (min) Acceleration 700 C 95% RPM 99% RPM (1) 0 C to red line 102.1% RPM (1A) % RPM (1B) 1 C0 001 to 350 with JT15D-1A engines not modified by SB must use JT15D-1 limitations NOTE: The red line on the oil temperature indicator dictates oil temperature limitation. Some indicators are red-lined at 115 C and other at 121. In either case, do not exceed the red line indication. Citation I/II/SII For training only 3A-19

22 3A-20 For training only Citation I/II/SII

23 Limitations C0/CI Engine Overspeed Limits Model State Log Book Entry Required Refer to Engine Maintenance Manual Fan Speed Turbine Speed Turbine Speed Fan Speed JT15D-1 Transient 99 to 110% RPM 95 to 97% RPM Exceeds 97% RPM Exceeds 110% RPM Steady 99 to 105% RPM Exceeds 95% RPM Exceeds 105% RPM JT15D-1A Transient to 110% RPM 95 to 97% RPM Exceeds 97% RPM Exceeds 110% RPM Steady to 105% RPM Exceeds 95% RPM Exceeds 102.1% RPM JT15D-1B Transient to 110% RPM 95 to 97% RPM Exceeds 97% RPM Exceeds 110% RPM Steady to 105% RPM Exceeds 95% RPM Exceeds 105% RPM Citation I/II/SII For training only 3A-21

24 Inter-Turbine Temperature Limits Starting Conditions Only INVESTIGATE CAUSE FOR ALL TEMPERATURES EXCEEDING AREA A ENVELOPE. REFER TO ENGINE MAINTENANCE MANUAL. 650 INTER-TURBINE TEMPERATURE ( C) AREA A ENVELOPE TIME (SECOND) All Conditions Except Starting If the inter-turbine temperature (ITT) exceeds 700 C or if 680 C is exceeded for more than five minutes, refer to the Engine Maintenance Manual. 3A-22 For training only Citation I/II/SII

25 Limitations C0/CI Engine Oil The following oils are approved for use: Mobil Jet Oil II and 254 Exxon Turbo Oil 2380 Castrol 5000 Aeroshell Turbine Oil 500 and 560 Royco Turbine Oil 500 and 560. In addition, oils listed for the engine in the latest revision to Pratt and Whitney Canada, Inc. Bulletin No are approved. CAUTION: The engine manufacturer strongly recommends that when changing from a existing lubricant formulation to a third generation lubricant formulation (e.g. Aeroshell/Royco Turbine Oil 560 or Mobil Jet 254), such a change be made only when an engine is new or freshly overhauled. For additional information refer to the engine manufacturer s pertinent oil service bulletins. When adding a dissimilar oil, use any approved oil brand if the total quantity of added oil does not exceed two U.S. quarts in any 400-hour period. If more than two U.S. quarts of dissimilar oil brands must be added, drain and flush the complete oil system, then refill with a single brand of approved oil according to Engine Maintenance Manual instructions. If oils of nonapproved brands or of different viscosities become inter-mixed, drain and flush the complete oil system and refill with an approved oil according to Engine Maintenance Manual instructions. Minimum oil temperature for starting is -40 C (-40 F). Citation I/II/SII For training only 3A-23

26 Prolonged Ground Operation Continuous ground operation of starter/generator above 325A is prohibited. Limit ground operation of pitot/static heat to two minutes to prevent damage to angle-of-attack system. 3A-24 For training only Citation I/II/SII

27 Limitations C0/CI Pneumatic and Pressurization Cabin Overhead Fan To meet smoke detection criteria, operate fan in HI or LOW when the aft baggage compartment dividers are closed. If fan is inoperative or off, display on the fixed portion of the aft divider a placard reading, PRIVACY CURTAIN AND DOOR MUST BE OPEN UNLESS TOILET IS OCCUPIED. Cabin Pressurization Limits Normal Cabin Pressurization Differential: C0 001 to 213 without SB TO 7.6 PSID C0 001 to 213 with SB21-9; C0 214 and subsequent; CI TO 8.5 PSID Maximum Differential (Relief Valve Setting): C0 001 to 213 without SB PSID C0 001 to 213 with SB21-9; C0 214 and subsequent; CI PSID Freon Air Conditioning (Optional Cessna Installed) Operation of the air conditioning system is prohibited for any of the following conditions: pressure altitude above 18,000 ft right generator inoperative ambient temperatures less than -21 C (-5 F). Citation I/II/SII For training only 3A-25

28 3A-26 For training only Citation I/II/SII

29 Limitations Citation II General Limitations Authorized Operations Day and Night VFR and IFR Flight Flight Into Icing Conditions Maximum Baggage Loads Nose Compartment LBS Aft Tailcone Compartment LBS Aft Cabin LBS Certification Status FAR Part 25; FAR Part 23 (551) Emergency Exit The emergency exit door pin must be removed before flight. Maneuvers No aerobatic maneuvers, including spins No intentional stalls above 25,000 ft or at engine speeds between 61.0 and 65.0% N 1 Citation I/II/SII For training only 3B-1

30 Flight Crew Requirements Pilot/Copilot See Single Pilot General and Operational Limitations, on page 3-37, for single pilot limitations. Pilot in command must have CE-500 type rating and meet FAR requirements. The copilot shall posess a multi-engine rating, an instrument rating for flight above 18,000 ft or flight into instrument meterological conditions, and meet the requirements of FAR Category II operation requires two pilots qualified in accordance with FAR Passenger Seat Position For all takeoffs and landings: Seats fully upright and outboard Seats aft of emergency exit in most aft position. Towing Maximum nose gear towing turning angle limit is 95 either side of center. Forcing the nose gear beyond the towing stop (95 limit), shears the bolts attaching the steering gear assembly to the cylinder. 3B-2 For training only Citation I/II/SII July 1999

31 Limitations CII Operational Limitations Maximum Weights Ramp ,500 LBS Takeoff ,300 LBS Landing ,700 LBS Zero Fuel ,500 LBS Zero Fuel, Optional ,000 LBS Takeoff weight is limited by most restrictive of: maximum certified T/O weight maximum T/O weight permitted by climb requirements takeoff field length. Landing weight is limited by most restrictive of: maximum certified landing weight maximum landing weight permitted by climb requirements or brake energy limit landing distance. Citation I/II/SII For training only 3B-3

32 Center of Gravity Moment Envelope See CG chart in Flight Planning chapter. Forward Limit: At 13,300 lbs % OF MAC (279.8 AFT OF DATUM) At 12,500 lbs % OF MAC (279.2 AFT OF DATUM) At 8,540 lbs or less % OF MAC (276.1 AFT OF DATUM) There is a straight line variation between 18.0 and 22.6% of MAC. Aft Limit % OF MAC (285.8 AFT OF DATUM) 3B-4 For training only Citation I/II/SII

33 Limitations CII Speed Limits Maximum V MO /M MO 9,500 Lbs Zero Fuel Weight: M MO above 28,000 ft M INDICATED V MO 14,000 to 28,000 ft KIAS V MO sea level to 14,000 ft KIAS Do not exceed these limits in any flight regime (climb, cruise, or descent) unless a higher speed is authorized for flight test or pilot training. Maximum V MO /M MO 11,000 Lbs Zero Fuel Weight: M MO Above 30,500 ft M V MO Sea Level to 30,500 ft KIAS Do not exceed these limits in any flight regime (climb, cruise, or descent) unless a higher speed is authorized for flight test or pilot training. Maximum Maneuvering (V A ) SEE CHART (Figure 3-2, page 3-33) Confine the following to speeds below VA : full rudder application full aileron control application maneuvers involving angle of attack near stall. Maximum Flap Extended (V FE ): Full flaps, LAND (40 ) KIAS Partial flaps, T.O.& APPR (15 ) KIAS Maximum Speedbrake Operation (V SB ) NO LIMIT Minimum Control Air (V MCA ) KIAS Minimum Control Ground (V MCG ) KIAS Maximum Tire Ground Speed KTS Citation I/II/SII For training only 3B-5

34 Autopilot Operation: 9,500 ZFW KIAS/0.705M 9,500 ZFW (Below 14,000 ft) KIAS 11,000 ZFW KIAS/0.705M Landing Gear Speeds: With SB (Increased Maximum Gear Extend Speed): V LE V MO V LO (Extending) KIAS V LO (Retracting) KIAS Without SB : V LE KIAS V LO KIAS With Gravel Runway Kit: V LE KIAS V LO KIAS Turbulent Air Penetration.... RECOMMENDED 180 KIAS 3B-6 For training only Citation I/II/SII

35 Limitations CII Maximum Maneuvering Speeds Citation II 3-2 Citation I/II/SII For training only 3B-7

36 Takeoff and Landing Operational Limits Maximum Altitude ,000 FT Maximum Ambient Temperature ISA +39 C Minimum Ambient Temperature C Maximum Crosswind DEMONSTRATED 23 KTS Maximum Tailwind Component KTS Maximum Water/Slush on Runway IN Autopilot/yaw damper must be off for takeoff/landing. Vertical navigation system must be off below 500 ft AGL. Anti-skid must be operable for takeoff and landing on sod/dirt or gravel runways. Goodyear Tire part numbers 184F08-1 and 184F13-3 and Goodrich Tire part number are the only approved nose tires. The nose tire must be inflated to 120 ±5 PSI. Enroute Operational Limits Maximum Operating Altitude ,000 FT Temperature Limits SEE GRAPH (Figure 3-3) Generator Load: Units 115 to 126 and 128 to 295 without SB : Up to 25,000 ft A Above 25,000 ft A Units 002 to 114; 115 to 126 and 128 to 295 with SB ; Unit 296 and subsequent: Up to 35,000 ft A Above 35,000 ft A 3B-8 For training only Citation I/II/SII July 1999

37 Limitations CII Takeoff/Landing/Enroute Temperature Limitations Citation II 3-3 Citation I/II/SII For training only 3B-9

38 Load Factors In Flight, Flaps: Up (0 ) TO +3.8G AT 13,300 LBS T.O. & APPR to LAND (15 to 40 ) TO +2.0G AT 13,300 LBS These accelerations limit angle-of-bank in turns and severity of pullup maneuvers. Landing G AT 12,700 LBS 3B-10 For training only Citation I/II/SII

39 Limitations CII Single Pilot General and Operational Limitations (551 Models only) Conduct single pilot operations according to data established for Citation II with the following additional constraints. SP Certification Status FAR Part 23 SP Requirements Pilot must sit in the left seat. The following equipment must be operating: one autopilot with approach coupling one flight director one boom microphone or headset-mounted microphone transponder identifier switch on pilot s control wheel. The pilot must have a CE-500 type rating and meet the requirements of FAR Single pilot operation is prohibited when operating from gravel runways. SP Maximum Weight Limits Ramp ,700 LBS Takeoff ,500 LBS Landing ,000 LBS SP Landing Gear Main Wheel Tire Pressure ±5 PSI Nose Wheel Tire Pressure ±5 PSI Citation I/II/SII For training only 3B-11

40 3B-12 For training only Citation I/II/SII

41 Limitations CII System Limitations Avionics and Communications Angle-of-Attack May be used as a reference, but does not replace the primary airspeed indicator. Autopilot One pilot must remain in his seat with seat belt fastened during AP operation. AP current monitor must be functionally tested prior to inflight use. AP operation is prohibited above 14,500 ft if the torque monitor (AP TORQUE annunciator) does not test per AFM, Section IV (CII 162 and subsequent). Autopilot/yaw damper must be off for takeoff/landing. Vertical navigation system must be off below 500 ft AGL. Autopilot/Flight Director For CII 162 and subsequent without H mod on the flight director, flight director back course approaches (coupled or uncoupled) are prohibited without an operating radio altimeter. CII 418 and subsequent should have H mod. The H mod circuitry in flight director computer provides pseudo signals to flight director when radio altimeter is inoperative or not installed; therefore, the limitation for back course approaches is removed. Dual Flight Director Installation The copilot s second attitude indicating system must be installed, be operational, and remain operating throughout the flight for those aircraft equipped with dual flight directors. The dual flight director dual AC power distribution system must function normally as verified by performing a preflight test of the AC system. Citation I/II/SII For training only 3B-13

42 HF/ADF Systems The ADF bearing information may be erratic during HF transmissions. If this occurs, disregard the ADF bearing during transmission periods. Drag Chute The aircraft s nose wheel must be on the ground for drag chute operation. Maximum speed for drag chute deployment is 125 KIAS. Simultaneous use of drag chute and thrust reversers is prohibited. If the chute deploys or jettisons above 110 kts, inspect the mechanism for possible damage. 3B-14 For training only Citation I/II/SII

43 Limitations CII Electrical and Lighting Systems Battery If BATT O HEAT annunciator illuminates during ground operation, do not take off until proper maintenance is accomplished. Limit engine starts to three per hour. If a battery limitation is exceeded, accomplish a deep cycle with a capacity check to detect possible cell damage. Refer to the Maintenance Manual for the procedure. NOTE: Three generator-assisted cross-starts equal one battery start. Do not count an external power engine start as battery cycle. Generator Operating Limits Generator Load: Units 115 to 126 and 128 to 295 without SB : Up to 25,000 ft A Above 25,000 ft A Units 002 to 114; 115 to 126 and 128 to 295 with SB ; Unit 296 and subsequent: Up to 35,000 ft A Above 35,000 ft A GPU Limitation With GPU connected to aircraft, limit GPU output to a maximum of 1,000A and adjust the voltage to 28.5V DC with no load. Exceeding these limits may damage the starter. Starter Limitation Limit the starter to three engine starts per 30 minutes with a 30-second rest between cycles. Citation I/II/SII For training only 3B-15 July 1999

44 Fuel System Fuel remaining in the fuel tank when the quantity indicator reads zero is not usable in flight. Anti-Ice Additive Anti-icing must be added to all fuels that do not contain the additive. Military JP-4, JP-5, and JP-8 have refinery preblended anti-icing. WARNING: Anti-icing additives containing ethylene glycol monomethyl ether (EGME) or diethylene glycol monomethyl ether (DIEGME) are harmful if inhaled, swallowed or absorbed through the skin, and cause eye irritation. Also, they are combustible. Before using this material, refer to all safety information on the container. Additive Concentration Range Minimum Maximum Hi-Flo EGME 20 fluid ounces 20 fluid ounces per 260 gallons per 104 gallons 0.06% 0.15% DIEGME 20 fluid ounces 20 fluid ounces per 156 gallons per 104 gallons 0.10% 0.15% CAUTION: Ensure that additive is directed into flowing fuel stream and additive flow is started after fuel flow. The additive should be stopped before fuel flow stops. Do not allow concentrated additive to contact coated interior of the fuel tank or the aircraft s painted surface. 3B-16 For training only Citation I/II/SII

45 Limitations CII Boost Pumps Turn on boost pumps when FUEL LEVEL LO annunciators illuminate or indicated fuel is 169 lbs or less. Differential Maximum Asymmetrical Difference LBS Aviation Gasoline All grades of MIL-G-5572 avgas are permitted for a maximum of 50 hours or 3,500 gallons between overhauls, provided: pilot confirms the fuel temperature is within limits maximum fuel and ambient air temperature is +32 C. boost pumps are on hours of avgas use are entered in the engine logbook maximum operating altitude is 18,000 ft. Jet Fuel The following fuels are approved per specification CPW 204, commercial kerosene: Jet A, Jet A-1, Jet A-2, and Jet B JP-4, JP-5, and JP-8 Citation I/II/SII For training only 3B-17

46 Fuel Limitations and Adjustments Jet A, A-1, -2; Jet B; JP-4 Avgas JP-5, JP-8 Min Fuel Temp., -29 C -54 C -54 C T.O. Min Fuel Temp., -23 C -54 C -54 C Start Max Fuel Temp 50 C 50 C 32 C Max Altitude 43,000 ft 43,000 ft 18,000 ft Max Asymmetric 600 lbs 600 lbs 600 lbs Fuel Fuel Control Density 3B-18 For training only Citation I/II/SII

47 Limitations CII Hydraulic System Approved Fluids Skydrol 500 A, B, B-4, C or LD-4 Hyjet, Hyjet W, III, or IV. Ice and Rain Protection Engine Anti-Ice System Engine anti-ice is required for taxi, takeoff, and in flight when operating in visible moisture with OAT at +10 C to -30 C. For sustained ground operations, operate for one out of four minutes at 65% turbine RPM. Windshield Alcohol Anti-Ice System Use TT-I-735 isopropyl alcohol for windshield anti-ice. The backup alcohol system is sufficient for 10 minutes. Windshield Bleed Air Anti-Ice System Windshield bleed air is required to prevent ice on windshield when operating in visible moisture with OAT at +10 C to -30 C. Set the W/S BLEED switch to LO (260 F) when OAT is above -18 C (0 F). Set the W/S BLEED switch to HI (280 F) when OAT is -18 C (0 F) or below. Wing Deice System Wing deice is required in flight when wing ice builds up to 1/4 to 1/2 inch thickness. Citation I/II/SII For training only 3B-19 July 1999

48 Landing Gear and Brakes Anti-Skid Anti-skid must be operative for takeoff and landing on sod/dirt or gravel runways. Approved Nose Tires Goodyear 184F08-1 and 184F13-3 Goodrich Brakes Emergency Air Pressure ,800 TO 2,050 PSI Accumulator Precharge Static ±25 PSI Pressurized to 1,300 PSI Tire Pressures Main Wheels ±5 PSI Nose Wheel ±5 PSI Strut Inflation Main Gear TO 2 INCHES Nose Gear INCHES 3B-20 For training only Citation I/II/SII

49 Limitations CII Oxygen System The standard diluter-demand oxygen mask must be positioned around the neck above FL250 to qualify as quick-donning. The optional pressure-demand sweep-on oxygen mask must be properly stowed to qualify as quick-donning. Thrust Reversers Reduce reverse thrust power to idle reverse at 60 KIAS on landing roll. Limit maximum reverse thrust setting to 94% N1 for ambient temperatures above -18 C and 92% N 1 for ambient temperatures below -18 C. Maximum allowable thrust reverser deployed time is 15 minutes in any one hour period. Limit engine static ground operation to less than 80% N1 for ambient temperature at sea level above 51 C. Do not use thrust reversers during touch and go landings. Thrust reversing on sod/dirt or gravel runways is prohibited. Simultaneous use of drag chute and thrust reversers is prohibited. The aircraft s nose whell must be on the ground for drag chut operation. Maximum speed for drag chute deployment is 125 KIAS. If the chute is deployed or jettisoned above 110 kts, inspect the mechanism for possible damage. Citation I/II/SII For training only 3B-21 July 1999

50 Powerplant Pratt and Whitney Turbofan JT15D-4 or JT15D-4B Aircraft with SB are restricted to 180-day operation. Engine Fan Inspection To ensure accurate fan speed thrust indication, inspect fan for damage prior to each flight. Engine Operating Limits Thrust Setting Time Limit ITT Temp N 2 N 1 Oil Press Oil Temp Takeoff 5 minutes 700 C 96% RPM 104% RPM 70 to 85 PSIG 10 to 121 C Max Continuous Continuous 680 C 96% RPM 104% RPM 70 to 85 PSIG 0 to 121 C Max Cruise Continuous 670 C 96% RPM 104% RPM 70 to 85 PSIG 0 to 121 C Idle Continuous 580 C 49% RPM ±0.5% 35 PSIG (min) -40 to 121 C Start 700 C (2 sec) -40 C (min) Acceleration 700 C 96% RPM 104% RPM 95 PSIG for 0 to 121 C 90 sec (Max Transient) Engine Overspeed Limits State No Action Required Log Book Entry Required Refer to Engine Maintenance Manual Turbine Speed Fan Speed Turbine Speed Turbine Speed Fan Speed Transient 92 to 96% RPM 104to 110% RPM 96 to 98% RPM Exceeds 98% RPM Exceeds 110% RPM Steady 104 to 106% RPM Exceeds 96% RPM Exceeds 104% RPM 3B-22 For training only Citation I/II/SII

51 Limitations CII Inter-Turbine Temperature Limits Starting Conditions Only INVESTIGATE CAUSE FOR ALL TEMPERATURES EXCEEDING AREA A ENVELOPE. REFER TO CHAPTER 77 OF THE AIRPLANE MAINTENANCE MANUAL. ENGINE LOGBOOK ENTRY REQUIRED. 650 INTER-TURBINE TEMPERATURE ( C) AREA A ENVELOPE TIME (SECOND) All Conditions Except Starting If the inter-turbone temperature (ITT) exceeds 700 C or if 680 C is exceeded for more than five minutes, refer to the Engine Maintenance Manual. Citation I/II/SII For training only 3B-23

52 Engine Oil The following oils are approved for use: Mobil Jet Oil II and 254 Exxon Turbo Oil 2380 Castrol 5000 Aeroshell Turbine Oil 500 and 560 Royco Turbine Oil 500 and 560 Engine oils listed in the latest revision of Pratt and Whitney Canada Inc. SB CAUTION: The engine manufacturer strongly recommends that when changing from a existing lubricant formulation to a third generation lubricant formulation (e.g. Aeroshell/Royco Turbine Oil 560 or Mobil Jet 254), such a change be made only when an engine is new or freshly overhauled. For additional information refer to the engine manufacturer s pertinent oil service bulletins. When mixing brands of oil, use any approved oil brand if the total quantity of added oil does not exceed two U.S. quarts in any 400-hour period. If more than two U.S. quarts of dissimilar oil brands must be added, drain and flush the complete oil system, then refill with a single brand of approved oil according to Engine Maintenance Manual instructions. If oils of nonapproved brands or of different viscosities become inter-mixed, drain and flush the complete oil system and refill with an approved oil according to Engine Maintenance Manual instructions. Minimum oil temperature for starting is -40 C (-40 F). 3B-24 For training only Citation I/II/SII

53 Limitations CII Loaner Engines Aircraft incorporating SB are restricted to 180-day operation only. Prolonged Ground Operation Limit continuous engine ground static operation, up to and including five minutes at takeoff thrust, to ambient temperatures not exceeding ISA +39 C. Continuous ground operation of starter/generator amperage above 325A is prohibited. Limit ground operation of pitot/static heat to two minutes to prevent damage to angle-of-attack system. CII 482, 485, and subsequent: operation in GND bleed air mode with the right engine set greater than 70% N 2 is prohibited. Citation I/II/SII For training only 3B-25 July 1999

54 Pneumatic and Pressurization Systems Cabin Overhead Fan To meet smoke detection criteria, operate fan in HI or LOW when the aft cabin privacy curtain is closed. If the fan inoperative or off, a placard reading PRIVACY CURTAIN AND DOOR MUST BE OPEN UNLESS TOILET IS OCCUPIED must be displayed on the fixed portion of the aft divider. Cabin Pressurization Limits Normal Cabin Pressurization TO 8.8 PSID Pressurization Source Selector CII 001 to 481, 483, 484: Operation in BOTH HI mode is not approved for takeoff, landing, or high power settings. Flood Cooling Operation of the optional flood cooling system is prohibited above 10,000 ft. pressure altitude. Do not use flood cooling for cabin heating. Freon Air Conditioning Operation of the air conditioning system is prohibited for any of the following conditions: pressure altitude above 18,000 ft either generator inoperative ambient temperatures less than -21 C (-5 F). 3B-26 For training only Citation I/II/SII

55 Limitations Citation II-627 and Subsequent General Limitations Authorized Operations Day and Night VFR and IFR Flight Flight Into Icing Conditions Maximum Baggage Loads Nose Compartment LBS (LESS OPTIONAL EQUIPMENT) Aft Tailcone Compartment LBS Aft Cabin LBS Certification Status FAR, Part 25; FAR, Part 23 (551) Emergency Exit The emergency exit door pin must be removed before flight. Maneuvers No aerobatic maneuvers, including spins No intentional stalls above 25,000 ft or at engine speeds between 61.0 and 65.0% N 1 Citation I/II/SII For training only 3C-1

56 Flight Crew Requirement Pilot/Copilot Pilot in command must have CE-500 type rating and meet FAR requirements. The copilot shall posess a multi-engine rating, an instrument rating for flight above 18,000 ft or flight into instrument meterological conditions, and meet the requirements of FAR Category II operation requires two pilots qualified in accordance with FAR Passenger Seat Position For all takeoffs and landings: Seats fully upright and outboard Seats aft of emergency exit in most aft position Towing Maximum nose gear towing turning angle limit is 95 either side of center. Forcing the nose gear beyond the towing stop (95 limit), shears the bolts attaching the steering gear assembly to the cylinder. 3C-2 For training only Citation I/II/SII July 1999

57 Limitations CII-627 Operational Limitations Maximum Design Weights Ramp ,300 LBS Takeoff ,100 LBS Landing ,500 LBS Zero Fuel ,000 LBS Takeoff weight is limited by the most restrictive of: maximum certified T/O weight 14,100 lbs maximum T/O weight permitted by climb requirements takeoff field length. Landing weight is limited by the most restrictive of: maximum certified landing weight 13,500 lbs maximum landing weight permitted by climb requirements or brake energy limit landing distance. Center of Gravity Moment Envelope See CG chart in Flight Planning chapter. Forward Limit at 8,540 lbs or less % OF MAC AFT OF DATUM) Forward Limit at 14,100 lbs % OF MAC ( AFT OF DATUM) There is a straight line variation between 18.0 and 23.3% of MAC. Aft Limit % OF MAC (285.8 AFT OF DATUM) Citation I/II/SII For training only 3C-3

58 Weight and Balance Operate the aircraft in accordance with the approved loading schedule. (Refer to Weight and Balance Data Sheet and Model 550 Citation II Weight and Balance Manual.) Maximum Maneuvering Speeds Citation II-627 and subsequent 3-4 3C-4 For training only Citation I/II/SII

59 Limitations CII-627 Speed Limits Maximum Operating: M MO above 30,500 ft M INDICATED V MO sea level to 30,500 ft KIAS Do not exceed these limits in any flight regime (climb, cruise, or descent) unless a higher speed is authorized for flight test or pilot training. Maximum Maneuvering (V A ) SEE CHART (Figure 3-4) Confine the following to speeds below VA : full rudder application full aileron control application maneuvers involving angle of attack near stall. Maximum Flap Extended (V FE ): Full flaps, LAND (40 ) KIAS Partial flaps, T.O.& APPR (15%) KIAS Maximum Landing Gear Extended (V LE ) KIAS Maximum Landing Gear Operating: (V LO Extending) KIAS (V LO Retracting) KIAS Maximum Speedbrake Operation (V SB ) NO LIMIT Minimum Control Air (V MCA ) KIAS Minimum Control Ground (V MCG ) KIAS Autopilot Operation KIAS OR MACH Citation I/II/SII For training only 3C-5

60 Takeoff and Landing Operational Limits Maximum Altitude ,000 FT Maximum Tailwind Component KTS Maximum Crosswind DEMONSTRATED 23 KTS Maximum Water/Slush on Runway IN Maximum Ambient Temperature ISA +39 C Minimum Ambient Temperature C Maximum Ground Tire Speed KTS Goodyear tire part numbers 184F08-1 and 184F13-3 and Goodrich nose tire part number are the only nose tires approved. The nose tire must be inflated to 120 ±5 PSI. Vertical navigation (VNAV) must be off below 500 ft AGL. Autopilot and yaw damper must be off for takeoff and landing. Enroute Operational Limits Maximum Operating Altitude ,000 FT Temperature Limits SEE GRAPH (Figure 3-5) Generator Load: To 35,000 ft A Above 35,000 ft A 3C-6 For training only Citation I/II/SII

61 Limitations CII-627 Takeoff/Landing/Enroute Temperature Limitations Citation II-627 and subsequent 3-5 Citation I/II/SII For training only 3C-7

62 Load Factors In Flight, Flaps: Up (0 ) TO +3.8 G AT 14,100 LBS T.O. & APPR to LAND (15 to 40 ) TO +2.0 G AT 14,100 LBS These accelerations limit angle-of-bank in turns and severity of pull-up maneuvers. Landing, Flaps T.O. & APPR to LAND (15 to 40 ) G AT 13,500 LBS 3C-8 For training only Citation I/II/SII July 1999

63 Limitations CII-627 System Limitations Avionics and Communications Angle-of-Attack May be used as reference, but does not replace the primary airspeed indicator. May be used as a reference for approach speed (1.3 VSI ) at all airplane weights and center of gravity locations with flaps at zero, takeoff, takeoff/approach and landing positions. Automatic Director Finder Systems (ADF) The ADF bearing information may be erratic during HF transmission. If this occurs, disregard the ADF bearing during transmission periods. Autopilot One pilot must remain in his seat with seat belt fastened during all AP operations. AP torque monitor must be functionally tested prior to inflight use. AP operation is prohibited above 14,500 ft if torque monitor (AP TORQUE annunciator) does not test per Normal Procedures in the AFM. Autopilot/yaw damper must be off for takeoff/landing. Standby Gyro Horizon A satisfactory preflight test must be accomplished. Citation I/II/SII For training only 3C-9

64 Electrical and Lighting Systems Battery Limit engine starts to three per hour. If battery limitation is exceeded, accomplish a deep cycle with a capacity check to detect possible cell damage (see cycle procedure in Maintenance Manual). NOTE: Three generator-assisted cross-starts equal one battery start. Do not count an external power engine start as a battery cycle. If the BATT O TEMP annunciator illuminates during ground operation, do not take off until proper maintenance is accomplished. Generator Operating Limits Generator Load: To 35,000 ft A Above 35,000 ft A Continuous ground operation of the starter generator above 325A is prohibited. GPU Limits Limits GPU output to 1,000 amps maximum when connected to the aircraft. Adjust power unit to 28.0 volts maximum with no load to prevent damage to starter. Prolonged Ground Operation Continuous ground operation of generator above 325 amps is prohibited. Starter Limits Independent of the power source (i.e., battery, generatorassisted cross-start, or GPU), the starter is limited to three engine starts per 30 minutes, and three cycles of operation with a 30-second rest between cycles. 3C-10 For training only Citation I/II/SII

65 Limitations CII-627 Fuel System Fuel remaining in the fuel tank when the quantity indicator reads zero is not usable in flight. Anti-Ice Additive Anti-icing must be added to all fuels that do not contain the additive. Military JP-4, JP-5, and JP-8 have refinery preblended anti-icing. WARNING: Anti-icing additives containing ethylene glycol monomethyl ether (EGME) or diethylene glycol monomethyl ether (DIEGME) are harmful if inhaled, swallowed or absorbed through the skin, and cause eye irritation. Also, they are combustible. Before using this material, refer to all safety information on the container. Additive Concentration Range Minimum Maximum Hi-Flo EGME 20 fluid ounces 20 fluid ounces per 260 gallons per 104 gallons 0.06% 0.15% DIEGME 20 fluid ounces 20 fluid ounces per 156 gallons per 104 gallons 0.10% 0.15% CAUTION: Ensure that additive is directed into flowing fuel stream and additive flow is started after fuel flow. The additive should be stopped before fuel flow stops. Do not allow concentrated additive to contact coated interior of the fuel tank or the aircraft s painted surface. Citation I/II/SII For training only 3C-11

66 Boost Pumps Turn on boost pumps when FUEL LEVEL LO annunciators illuminate or indicated fuel is 169 lbs or less. Differential Maximum Asymmetrical Difference LBS Aviation Gasoline All grades of MIL-G-5572 avgas are permitted for a maximum of 50 hours or 3,500 gallons between overhauls, provided the following conditions are met. The pilot confirms the fuel temperature is within limits. The maximum fuel and ambient air temperature is +32 C. The boost pumps are on. The avgas usage hours are entered in the engine logbook. (For record-keeping purposes, assume one hour of engine operation equals 70 gals gasoline.) Jet Fuel The following fuels are approved per specification CPW 204, commercial kerosene: Jet A, Jet A-1, A-2, and Jet B JP-4, JP-5, and JP-8 3C-12 For training only Citation I/II/SII