Airspeed Limitations Index

Weight Limitations Index

550-0550 - 550-0626:

Maximum Ramp Weight 13,500 LBS

Maximum Takeoff Weight 13,300 LBS

Maximum Landing Weight 12,700 LBS

Maximum Zero Fuel Weight 11,000 LBS

(550-0505 and earlier: 9500 LBS -standard, 11,000 LBS optional)

550-0627 and after:

Maximum Ramp Weight 14,300 LBS

Maximum Takeoff Weight 14,100 LBS

Maximum Landing Weight 13,500 LBS

Maximum Zero Fuel Weight 11,000 LBS

Note: Maximum takeoff and landing weights may be additionally restricted due to altitude, temperature and field length.

Center of Gravity Limits Index

550-0626 and earlier:

Forward Limit:

8540 LBS or less .............................. 276.10 inches aft of reference datum

13,300 LBS or less .......................... 279.80 inches aft of reference datum

12,500 LBS or less .......................... 279.20 inches aft of reference datum

Aft Limit: ........................................ 285.8 inches aft of reference datum.

550-0627 and after:

14,100 LBS or less .......................... 280.40 inches aft of reference datum.

Aft Limit:

14,100 LBS or less .......................... 285.80 inches aft of reference datum.

Note: It is the responsibility of the pilot to ensure that the airplane is loaded properly. Refer to Weight and Balance Data Sheet for proper loading instructions.

Takeoff and Landing Limitations Index

Maximum Altitude .....................................14,000 Feet

Max Tailwind Component (<0626) ........ . 10 Knots

Crosswind Component (>0627) ............ .23 Knots

Maximum Runway

Water/Slush Accumulation ................... . 0.4 Inches

Maximum Ambient
Temperature ......................................... . ISA + 39°C (130°F)

Minimum Ambient
Temperature ........................................... -54°C (-65°F)

Note: Autopilot and yaw damper must be OFF for takeoff and landing.
Vertical navigation system must be OFF below 500 feet AGL.

Flight Load Factor Limitations Index

550-0626 and earlier at 13,300 LBS maximum takeoff weight

Flaps Up , , + 3.8G, -1.52G

Flaps Down , + 2.OG, 0.0G

Landing + 3.5G

550-0627 and after at 14,100 LBS maximum takeoff weight

Flaps Up ...... + 3.8G, -1.52G
Flaps Down.. + 2.OG, O.OG

Landing ........ + 3.386 at 13,500 LB landing weight

Note: These accelerations limit the angle-of-bank in turns and severity of pullup maneuvers:

Note: This airplane is certificated in the normal category.

The normal category is applicable to aircraft intended for non-aerobatic operations.

Aerobatic maneuvers and spins are prohibited.

No intentional stalls are permitted above 25,000 feet or at any altitude with engine speeds between 61.0% and 65% N1.

550-0626 and earlier

not incorporating SB55-54-4:

Maximum Operating Altitude .......... 43,000 Feet

Temperature Limits ......................... ISA +39°C*

Generator Load

Up to 35,000 Feet ... ..................... 400 Amps

Above 35,000 Feet ...................... 250 Amps

incorporating SB55-54-4:

Maximum Operating Altitude .......... 43,000 Feet

Temperature Limits ......................... ISA +39°C*

Generator Load

Up to 35,000 Feet ... ..................... 400 Amps

Above 35,000 Feet ...................... 325 Amps

550-0627 and after:

Maximum Operating Altitude .......... 43,000 Feet

Temperature Limits.. ………………..ISA +39°C*

Generator Load

Up to 35,000 Feet.. ………………400 Amps

Above 35,000 Feet……………….325 Amps

*Note: Maximum enroute operating temperature limit is ISA +39°C ambient temperature adjusted for ram rise or indicated outside air temperature (IOAT), whichever is less.

The Citation II is approved for the following types of operation when the required equipment is installed and operational as defined within the Federal Aviation Regulations:

1. VFR day

2. VFR night

3. IFR day including Category I and Category II approaches

4. IFR night including Category I and Category II approaches

5. Flight into known icing conditions

Engine Operating Limitations Index

Engine Thrust Rating . ………..2500 LBS each

Battery and Starter Cycle  Index

Whether powered by battery, external power unit, or cross start with generator assist, starter operation is limited to three engine start attempts per 30-minute period, with a minimum 30-second rest period between cycles.

Battery cycling is limited to three engine start attempts per hour.

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.

Note: Starting ITT exceeding 500°C should be investigated in accordance with Maintenance Manual.

Note: If the BATT O'HEAT (BATT O'TEMP, 550-0627 and after) annunciator illuminates during ground operation, do not take off until after the proper maintenance procedures have been accomplished.

Prolonged Ground Operations
Continuous engine ground static operation up to and including five minutes at takeoff thrust is limited to ambient temperatures not to exceed ISA + 39°C. Continuous ground operation of the starter-generator above 325 amps is prohibited. Limit ground operation of pitot/static heat to two minutes to preclude damage to the pitot/static heater. Operation in the GND bleed mode at power settings greater than 70% N2 for the right engine is prohibited.

Oil Limitations Index

Mobile Jet Oil II or 254, Exxon Turbo Oil 2380, Aeroshell Turbine 560 or 500, Castrol 5000, and Royco Turbine Oil 560 or 500. In addition, The engine should be serviced with approved synthetic oils listed in the most current revision of P&WC SIB 7001.

Caution: When changing from an existing lubricant formulation to a "third generation" lubricant formulation (Aero Shell/Royco Turbine Oil 560 or Mobile 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 manufacturers pertinent oil service bulletins.

Note: Do not mix types or brands of oil.

Should it be necessary to replenish oil consumption toss when oil of the same brand (as contents in tank) is unavailable, then the following requirements apply:

1. The total quantity of added oil does not exceed two US quarts in any 400-hour period.

2. If it is required to add more than two US quarts of dissimilar oil brands, drain and flush complete oil system and refill with an approved oil in accordance with Engine Maintenance Manual instructions.

Should oils of non-approved 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.

Note: Minimum starting oil temperature is -40°C.

Fuel Limitations Index

The following approved fuels comply with the latest revision of Pratt & Whitney Canada Specification 204 and Pratt & Whitney Canada Service Bulletin 7144814.

Approved fuels are JET A, JET A-1, JET B, JP-4, JP-5, or JP-8, all with 0.15% PFA55MB anti-icing additive in solution. When preblended fuel is not available, anti-icing additives conforming to MIL-I-27686E (Ethylene Glycol Monomethyl Ether (EGME)) or MIL-1-85470 (Diethylene Glycol Monomethyl Ether (DIEGME)) specifications such as "Prist" may be introduced directly into the nozzle fuel stream during servicing. Concentrations of less than 0.06% (20 fluid ounces of additive per 260 gallons of fuel or more) may be insufficient to prevent fuel system icing or microbiological contamination. Conversely, concentrations of more than 0.15% (20 fluid ounces of additive per 104 gallons of fuel or less) could cause damage to internal components of the fuel system or erroneous fuel quantity indications.

Caution: EGME and DIEGME are aggressive chemicals and should not exceed 0.15% of fuel volume. Improperly handled, these materials will damage the epoxy primer and sealants used in the fuel tanks, O-ring seals, and any part of the airplane's exterior finish with which it comes in contact.

Warning: Anti-icing additives containing EGME or DIEGME are harmful if inhaled, swallowed, or absorbed through the skin, and will cause eye irritation. Refer to all instructions and warnings regarding toxicity and flammability before using these materials.

Fuel Temperature and Density Limitations Index