04 Limitations

Citation I/II/SII For training only 3-1June 1997

LimitationsTable of ContentsLimitations – Citation/Citation I . . . . . . . . . . . . . 3A-1

General Limitations . . . . . . . . . . . . . . . . . . . . 3A-3

Operational Limitations . . . . . . . . . . . . . . . . . . . 3A-5

Single Pilot General and Operational Limitations(501 Models Only) . . . . . . . . . . . . . . . . . . . . . 3A-9

System Limitations . . . . . . . . . . . . . . . . . . . .3A-11

Limitations – Citation II . . . . . . . . . . . . . . . . . . 3B-1

General Limitations . . . . . . . . . . . . . . . . . . . . . 3B-1

Operational Limitations . . . . . . . . . . . . . . . . . . . 3B-3

Single Pilot General and Operational Limitations . . . . 3B-11

System Limitations . . . . . . . . . . . . . . . . . . . . 3B-13

Limitations – Citation II-627 and Subsequent . . . . 3C-1

General Limitations . . . . . . . . . . . . . . . . . . . . . 3C-1

Operational Limitations . . . . . . . . . . . . . . . . . . . 3C-3

System Limitations . . . . . . . . . . . . . . . . . . . . . 3C-9

Limitations – Citation SII . . . . . . . . . . . . . . . . . 3D-1

General Limitations . . . . . . . . . . . . . . . . . . . . . 3D-1

Operational Limitations . . . . . . . . . . . . . . . . . . . 3D-5

System Limitations . . . . . . . . . . . . . . . . . . . . 3D-13

3-2 For training only Citation I/II/SIIJune 1997

Limitations – Citation/Citation I

General LimitationsThe limitations in this section apply to all models in both aircraft,except where noted. However, varied service bulletins, espe-cially on older models, are too numerous to address in thishandbook. Some of these service bulletins that apply to yourspecific 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/CopilotSee Single Pilot Operation (501 Models Only), page 3-11, forsingle pilot limitations.

� Pilot in command must have CE-500 type rating and meetFAR 61.58 requirements.

� The copilot shall posess a multi-engine rating, an instrumentrating for flight above 18,000 ft or flight into instrument metero-logical conditions, and meet the requirements of FAR 61.55.

� Category II operation requires two pilots.

Limitations – C0/CI

Citation I/II/SII For training only 3A-1May 2001

Passenger Seat PositionFor all takeoffs and landings:

� Seats fully upright and outboard

� Seats adjacent to emergency exit must be fully trackedtoward rear of aircraft

Maximum Baggage LoadsNose Compartment . . . . . . . . . . . . . . . . . . 350 LBS

Aft Cabin . . . . . . . . . . . . . . . . . . . . . . . . 650 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 gearassembly to the cylinder.

3A-2 For training only Citation I/II/SIIJune 1997


Citation I/II/SII For training only 3A-3June 1997

Operational LimitationsMaximum Weights C0 001 to 070 without SB32-1:

Ramp . . . . . . . . . . . . . . . . . . . . . . . 11,000 LBS

Takeoff . . . . . . . . . . . . . . . . . . . . . . 10,850 LBS

Landing . . . . . . . . . . . . . . . . . . . . . . 10,400 LBS

Zero Fuel . . . . . . . . . . . . . . . . . . . . . 8,400 LBS

With SB34-15 . . . . . . . . . . . . . . . . . . 9,500 LBS

With SB34-23 . . . . . . . . . . . . . . . . . 10,500 LBS

C0 001 to 070 with SB32-1; 071 to 302 without SB32-23:

Ramp . . . . . . . . . . . . . . . . . . . . . . . 11,650 LBS

Takeoff . . . . . . . . . . . . . . . . . . . . . . 11,500 LBS

Landing . . . . . . . . . . . . . . . . . . . . . . 11,000 LBS

Zero Fuel . . . . . . . . . . . . . . . . . . . . . . 8,400 LBS

With SB34-15 . . . . . . . . . . . . . . . . . . 9,500 LBS

With SB34-23 . . . . . . . . . . . . . . . . . 10,500 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 . . . . . . . . . . . . . . . . . . . . . . . 12,000 LBS

Takeoff . . . . . . . . . . . . . . . . . . . . . . 11,850 LBS

Landing . . . . . . . . . . . . . . . . . . . . . . 11,350 LBS

Zero Fuel . . . . . . . . . . . . . . . . . . . . . . 8,400 LBS

With SB34-15 . . . . . . . . . . . . . . . . . . 9,500 LBS

With SB34-23 without SB57-12 . . . . . . 10,500 LBS


CI (all):

Ramp . . . . . . . . . . . . . . . . . . . . . . . 12,000 LBS

Takeoff . . . . . . . . . . . . . . . . . . . . . . 11,850 LBS

Landing . . . . . . . . . . . . . . . . . . . . . . 11,350 LBS

Zero Fuel . . . . . . . . . . . . . . . . . . . . . . 8,400 LBS

With SB34-15 . . . . . . . . . . . . . . . . . . 9,500 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 requirementsand brake energy limit

– landing distance.

Center of Gravity Moment EnvelopeSee CG charts in Flight Planning chapter.

Forward Limit:

At 7,500 lbs or less . . . . . . . . . . . . . 18.0% OF MAC . . . . . . . . . . . . . . . . . . .(246.4” AFT OF DATUM)

At 11,850 lbs . . . . . . . . . . . . . . . . . 22.6% OF MAC . . . . . . . . . . . . . . . . . . .(250.0” AFT OF DATUM)

There is a straight line variation between 18.0 and 22.6%MAC.

Aft Limit . . . . . . . . . . . . . . . . . . . . 30.0% OF MAC . . . . . . . . . . . . . . . . . . . . .(255.9” AFT OF DATUM)

Speed LimitsMaximum VMO/MMO (C0):

MMO above 26,000 ft . . . . . . . . . 0.705 M INDICATED

VMO 14,000 to 26,000 ft . . . . . . . . . . . . . . 289 KIAS

14,000 to 28,000 ft (9,500 lb ZFW) . . . . . . . 277 KIAS

14,000 to 30,500 ft (10,500 lb ZFW) . . . . . . 262 KIAS

VMO sea level to 14,000 ft . . . . . . . . . . . . . 262 KIAS

Maximum VMO/MMO (CI):


VMO 14,000 to 28,000 ft . . . . . . . . . . . . . . 277 KIAS

14,000 to 30,500 ft (9,500 lb ZFW) . . . . . . . 262 KIAS


Do not exceed these limits in any flight regime (climb,cruise, or descent) unless a higher speed is authorized forflight 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 (VFE):

Full flaps, LAND (40°) . . . . . . . . . . . . . . . 176 KIAS

Partial flaps, T.O.& APPR (15°) . . . . . . . . . . 202 KIAS

Maximum Speedbrake Operation (VSB) . . . . . . . NO LIMIT



Maximum Maneuvering SpeedsCitation; Citation I


45,000

40,000

35,000

30,000

25,000

20,000

15,000

10,000

5000

SEA LEVEL

7500 LBS

8500 LBS

9500 LBS

10,500 LBS

11,500 LBS

11,850 LBS

MACH 0.7

120 140 160 180MANUVERING SPEED (VA) - KIAS

200 220 240 260

IND

ICA

TE

D P

RE

SS

UR

E A

LTIT

UD

E -

FE

ET

INDICATED PRESSURE ALTITUDE - 25,000 FEETWEIGHT - 10,500 LBSMAXIMUM MANUVERING SPEED - 190 KNOTS

NOTE: The above graph is the most conservativeMaximum Maneuvering graph available. Speeds may varydepending on compliance with specific service bulletins.See the Airplane Flight Manual.

3-1



Minimum Control:

Air (VMCA) . . BELOW STALL SPEED FOR ALL WEIGHTS

Ground (VMCG) . . . . . . . . . . . . . . . . . . . . 55 KIAS

Maximum Tire Ground Speed:

C0 001 to 070, without SB32-1 or SB21-9 . . . 139 KTS

C0 001 to 070 with SB32-1 or SB21-9 and 071 to 349; CI . . . . . . . . . . . 165 KTS

Autopilot Operation:

C0 without SB57-12 . . . . . . . . . . . 289 KIAS/0.705M

C0 with SB57-12; CI . . . . . . . . . . . 277 KIAS/0.705M

Maximum Landing Gear Speeds:

VLE . . . . . . . . . . . . . . . . . . . . . . . . . . . . 176 KIAS

VLO . . . . . . . . . . . . . . . . . . . . . . . . . . 176 KIAS

Turbulent Air Penetration . . . . RECOMMENDED 180 KIAS

Takeoff and Landing Operational LimitsMaximum Altitude:

C0 001 to 070 without SB32-1 or SB21-9 . . . 12,000 FT

C0 001 to 070 with SB32-1 or SB21-9; C0 071 and subsequent; CI . . . . . . . . . . 14,000 FT

Maximum Tailwind Component . . . . . . . . . . . . . 10 KTS

Maximum Crosswind . . . . . . . DEMONSTRATED 25 KTS

Maximum Water/Slush on Runway . . . . . . . . . . . 0.75 IN

Maximum Ambient Temperature . . . . . . ISA + 39°C (71°F)

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

� Autopilot must be off for takeoff/landing.� Vertical navigation system must be off below 500 ft AGL.

Enroute Operational LimitsMaximum Operating Altitude:

C0 001 to 213 without SB21-9 . . . . . . . . . 35,000 FT

C0 001 to 213 with SB21-9;C0 214 and subsequent; CI . . . . . . . . . . . 41,000 FT

Temperature Limits . . . -54°C (-65°F) TO ISA + 39°C (71°F)

Generator Load:

To 35,000 ft . . . . . . . . . . . . . . . . . . . . . . . 400A

Above 35,000 ft . . . . . . . . . . . . . . . . . . . . . 325A

Load FactorsIn Flight, Flaps:

Up (0°) . . . . . . . . . . . . . . . . . . . . -1.52 TO +3.8 G

T.O. & APPR to LAND (15° to 40°) . . . . . 0.0 TO +2.0 G

These accelerations limit angle-of-bank in turns and severity of pullup maneuvers.

Landing . . . . . . . . . . . . . . . . . . . . . . . . . . +3.5 G




Single Pilot General and Operational Limitations (501 Models Only)Conduct single pilot operations according to data establishedfor 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 therequirements of FAR 61.57 for single pilot operation (501models only).




System LimitationsAvionics and Communications

Angle-of-Attack� May be used as reference, but does not replace primary air-

speed indicator as a primary instrument.

Autopilot� One pilot must remain in his seat with seat belt fastened dur-

ing 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 thoseaircraft equipped with dual flight directors.

HF/ADF Systems� The ADF bearing information may be erratic during HF trans-

missions. If this occurs, disregard ADF bearing during trans-mission 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 mech-

anism for possible damage.

Electrical and Lighting

Battery� If BATT O’HEAT annunciator illuminates during ground oper-

ation, do not take off until proper maintenance is accom-plished.

� Limit engine starts to three per hour. If battery limitation isexceeded, accomplish a deep cycle including a capacitycheck to detect possible cell damage. See MaintenanceManual for procedure.

Generator Operating LimitsGenerator Load:

To 35,000 ft . . . . . . . . . . . . . . . . . . . . . . . 400A

Above 35,000 ft . . . . . . . . . . . . . . . . . . . . . 325A� 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 ofthe starter power source (i.e., battery, generator-assistedcross-start, or GPU).

External Power Limitation� With GPU connected to aircraft, limit GPU output to maxi-

mum of 1,000 amps and 28V DC. Exceeding these limitsmay damage the starter.


NOTE: Three generator-assisted cross-starts are equalto one battery start. C0 001 to 274: Three externalpower starts are equal to one battery start. C0 275 andsubsequent; CI: Do not count external power start asbattery cycle.



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 pre-blended anti-icing.

CAUTION: Ensure that additive is directed into flowingfuel stream and additive flow is started after fuel flow. Theadditive should be stopped before fuel flow stops. Do notallow concentrated additive to contact coated interior ofthe fuel tank or the aircraft’s painted surface.

WARNING: Anti-icing additives containing ethylene glycolmonomethyl ether (EGME) or diethylene glycol monomethylether (DIEGME) are harmful if inhaled, swallowed orabsorbed through the skin, and cause eye irritation. Also,they are combustible. Before using this material, refer to allsafety information on the container.

Additive Concentration Range

Minimum Maximum

Hi-Flo EGME 20 fluid ounces 20 fluid ouncesper 260 gallons per 104 gallons

0.06% 0.15%

DIEGME 20 fluid ounces 20 fluid ouncesper 156 gallons per 104 gallons

0.10% 0.15%


Boost Pumps� Turn on boost pumps when FUEL LEVEL LO annunciators

illuminate or indicated fuel is below 170 lbs. Check that theCB is in.

Fuel ImbalanceMaximum Fuel Imbalance . . . . . . . . . . . . . . . 800 LBS

Aviation Gasoline� All grades of MIL-G-5572 avgas are permitted for a maxi-

mum of 50 hours or 3,500 gallons between overhauls, pro-vided:

– 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



Fuel Limitations and Adjustments

Jet A, A-1, -2; Jet B; JP-4 AvgasJP-5, JP-8

Min Fuel Temp., -20°F -65°F -65°FT.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 ft1 35,000 ft1 25,000 ft41,000 ft2 41,000 ft2

Max Asymmetric 800 lbs 800 lbs 800 lbsFuel

Fuel Control 0.81 0.79 0.73Density

1 C0 001 to 213 without SB21-9

2 C0 001 to 213 with SB 21-9; C0 214 to 233; 235 to 249; CI

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 outof every four minutes at 65% turbine RPM or above.

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 mois-

ture with OAT at +4 to -30°C (+40 to -22°F) to prevent ice onwindshield.

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).


CAUTION: Limit ground operation of pitot/static heat totwo minutes to prevent damage to the angle-of-attacksystem.



Landing Gear and Brakes

Approved Nose Tires� Goodyear 184F10-1 and 184F10-2� Goodrich 031-613-8

Brake and Optional Anti-Skid SystemsEmergency Air Pressure . . . . . . . . . 1,800 TO 2,000 PSI

Relief valve ruptures at 4,000 PSI.

Tire PressuresMain Wheels:

C0 001 to 051 without SB32-1 . . . . . . . 79 (+3,-1) PSI

C0 052 to 070 without SB32-1 . . . . . . . 90 (+3,-1) PSI

C0 001 to 070 with SB32-1; C0 071 and sub.; CI . . . . . . . . . . . . . . 100 ±5 PSI

Nose Wheel . . . . . . . . . . . . . . . . . . . . . 120 ±5 PSI

SpeedsTire Ground Speed:

C0 001 to 070 without SB32-1 or SB21-9 . . . . 139 KTS

C0 001 to 070 with SB32-1 or SB21-9; C0 071 to 349; CI . . . . . . . . . . . . . . . . . 165 KTS

Maximum Landing Gear Operating (VLO/VLE) . . . . . . . . . . . . . . . . . 176 KIAS

� If installed, the anti-skid must be operative for takeoff andlanding on sod/dirt or gravel runways.


Oxygen� The standard diluter-demand oxygen mask must be posi-

tioned around the neck above FL250 to qualify as quick-don-ning.

� The optional pressure-demand sweep-on oxygen mask mustbe properly stowed to qualify as quick-donning.

Thrust Reversers� Reduce reverse thrust power to the idle reverse detent posi-

tion at 60 KIAS on landing roll.� Maximum allowable thrust reverser deployed time is 15 min-

utes 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.

� Engine static ground operation is limited to less than 80% N1,for ambient temperature at sea level above 46°C (114°F).

CAUTION: Do not advance primary throttle after mov-ing thrust reverser lever to stow until the UNLOCK lightextinguishes.

WARNING: Do not attempt to restow reversers andtakeoff once reversers have started to deploy.

Citation I/II/SII For training onlyJune 1997

Powerplant – Pratt and Whitney TurbofanJT15D-1, 1A or 1BThrustTakeoff, Standard Day at Sea Level . . . . . . . . 2,200 LBS

Engine Fan Inspection� To ensure accurate fan speed thrust indication, inspect fan

for damage prior to each flight.

Engine Operating Limits

NOTE: The red line on the oil temperature indicator dictates oil temperature limitation. Some indicators arered-lined at 115°C and other at 121°. In either case, donot exceed the red line indication.

Thrust Setting Time Limit ITT Temp N2 N1 Oil Press Oil Temp

Takeoff 5 minutes 700°C 95% RPM 99% RPM (1) 65 to 80 PSIG 10°C to red line102.1% RPM (1A)1

103.4% RPM (1B)

Max Continuous Continuous 680°C 95% RPM 99% RPM (1) 65 to 80 PSIG 0°C to red line102.1% RPM (1A)1

103.4% RPM (1B)

Max Cruise Continuous 670°C 95% RPM 99% RPM (1) 65 to 80 PSIG 0°C to red line102.1% RPM (1A)1

103.4% 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 line102.1% RPM (1A)1

103.4% RPM (1B)

1 C0 001 to 350 with JT15D-1A engines not modified by SB500-72-3 must use JT15D-1 limitations

3A-19




3A-21Citation I/II/SII For training onlyJune 1997

Engine Overspeed Limits

Log Book Entry Required Refer to Engine Maintenance ManualModel State

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 102.1 to 110% RPM 95 to 97% RPM Exceeds 97% RPM Exceeds 110% RPM

Steady 102.1 to 105% RPM –– Exceeds 95% RPM Exceeds 102.1% RPM

JT15D-1B Transient 103.4 to 110% RPM 95 to 97% RPM Exceeds 97% RPM Exceeds 110% RPM

Steady 103.4 to 105% RPM –– Exceeds 95% RPM Exceeds 105% RPM

Inter-Turbine Temperature LimitsStarting Conditions Only

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 theEngine Maintenance Manual.


750

700

650

600

550

5000 5 10 15

TIME (SECOND)IN

TE

R-T

UR

BIN

E T

EM

PE

RA

TU

RE

(°C

)

AREA “A”ENVELOPE

INVESTIGATE CAUSE FORALL TEMPERATURESEXCEEDING AREA “A”ENVELOPE. REFER TOENGINE MAINTENANCEMANUAL.



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 toPratt and Whitney Canada, Inc. Bulletin No. 7001 areapproved.

� When adding a dissimilar oil, use any approved oil brand if thetotal quantity of added oil does not exceed two U.S. quarts inany 400-hour period. If more than two U.S. quarts of dissimi-lar oil brands must be added, drain and flush the complete oilsystem, then refill with a single brand of approved oil accord-ing to Engine Maintenance Manual instructions.

� If oils of nonapproved brands or of different viscosities becomeinter-mixed, drain and flush the complete oil system and refillwith an approved oil according to Engine Maintenance Manualinstructions.

� Minimum oil temperature for starting is -40°C (-40°F).

CAUTION: The engine manufacturer strongly recom-mends that when changing from a existing lubricant for-mulation to a third generation lubricant formulation (e.g.Aeroshell/Royco Turbine Oil 560 or Mobil Jet 254), sucha change be made only when an engine is new or fresh-ly overhauled. For additional information refer to theengine manufacturer’s pertinent oil service bulletins.

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.




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 ANDDOOR MUST BE OPEN UNLESS TOILET IS OCCUPIED.”

Cabin Pressurization LimitsNormal Cabin Pressurization Differential:

C0 001 to 213 without SB21-9 . . . . . . 0.0 TO 7.6 PSID

C0 001 to 213 with SB21-9;C0 214 and subsequent; CI . . . . . . 0.0 TO 8.5 PSID

Maximum Differential (Relief Valve Setting):

C0 001 to 213 without SB21-9 . . . . . . . . . . 8.0 PSID

C0 001 to 213 with SB21-9;C0 214 and subsequent; CI . . . . . . . . . . . 8.8 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 3B-1June 1997

Limitations – Citation II

General LimitationsAuthorized Operations� Day and Night� VFR and IFR Flight� Flight Into Icing Conditions

Maximum Baggage LoadsNose Compartment . . . . . . . . . . . . . . . . . . 350 LBS

Aft Tailcone Compartment . . . . . . . . . . . . . . . 200 LBS

Aft Cabin . . . . . . . . . . . . . . . . . . . . . . . . 600 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% N1

3B-2 For training only Citation I/II/SIIJuly 1999

Flight Crew Requirements – Pilot/CopilotSee Single Pilot General and Operational Limitations, on page3-37, for single pilot limitations.� Pilot in command must have CE-500 type rating and meet

FAR 61.58 requirements.� The copilot shall posess a multi-engine rating, an instrument

rating for flight above 18,000 ft or flight into instrument metero-logical conditions, and meet the requirements of FAR 61.55.

� Category II operation requires two pilots qualified in accor-dance with FAR 61.3.

Passenger Seat Position� For all takeoffs and landings:� Seats fully upright and outboard� Seats aft of emergency exit in most aft position.



Operational LimitationsMaximum WeightsRamp . . . . . . . . . . . . . . . . . . . . . . . . 13,500 LBS

Takeoff . . . . . . . . . . . . . . . . . . . . . . . . 13,300 LBS

Landing . . . . . . . . . . . . . . . . . . . . . . . 12,700 LBS

Zero Fuel . . . . . . . . . . . . . . . . . . . . . . . 9,500 LBS

Zero Fuel, Optional . . . . . . . . . . . . . . . . . 11,000 LBS� Takeoff weight is limited by most restrictive of:



– takeoff field length.� Landing weight is limited by most restrictive of:


– maximum landing weight permitted by climb requirementsor brake energy limit


Limitations – CII


Center of Gravity Moment EnvelopeSee CG chart in Flight Planning chapter.

Forward Limit:



At 8,540 lbs or less . . . . . . . . . . . . . 18.0% OF MAC . . . . . . . . . . . . . . . . . . .(276.1” AFT OF DATUM)

There is a straight line variation between 18.0 and 22.6%of MAC.

Aft Limit . . . . . . . . . . . . . . . . . . . 30.0% OF MAC . . . . . . . . . . . . . . . . . . .(285.8” AFT OF DATUM)

3B-4 For training only Citation I/II/SIIJune 1997

Limitations – CII


Speed LimitsMaximum VMO/MMO – 9,500 Lbs Zero Fuel Weight:


VMO 14,000 to 28,000 ft . . . . . . . . . . . . . . 277 KIAS



Maximum VMO/MMO – 11,000 Lbs Zero Fuel Weight:

MMO Above 30,500 ft . . . . . . . . . . . . . . . . . 0.705 M

VMO Sea Level to 30,500 ft . . . . . . . . . . . . 262 KIAS


Maximum Maneuvering (VA) . . . . . . . . . . . SEE CHART . . . . . . . . . . . . . . . . . . . . .(Figure 3-2, page 3-33)




– maneuvers involving angle of attack near stall.



Partial flaps, T.O.& APPR (15°) . . . . . . . . . . 202 KIAS


Minimum Control – Air (VMCA) . . . . . . . . . . . . . 77 KIAS

Minimum Control – Ground (VMCG) . . . . . . . . . . 62 KIAS

Maximum Tire Ground Speed . . . . . . . . . . . . . 165 KTS


Autopilot Operation:

9,500 ZFW . . . . . . . . . . . . . . . . . 277 KIAS/0.705M

9,500 ZFW (Below 14,000 ft) . . . . . . . . . . . 262 KIAS

11,000 ZFW . . . . . . . . . . . . . . . . 262 KIAS/0.705M

Landing Gear Speeds:

With SB550-32-14 (Increased Maximum Gear ExtendSpeed):

VLE . . . . . . . . . . . . . . . . . . . . . . . . . . . VMO

VLO (Extending) . . . . . . . . . . . . . . . . . 250 KIAS

VLO (Retracting) . . . . . . . . . . . . . . . . . 200 KIAS

Without SB550-32-14:

VLE . . . . . . . . . . . . . . . . . . . . . . . . 176 KIAS

VLO . . . . . . . . . . . . . . . . . . . . . . . . 176 KIAS

With Gravel Runway Kit:

VLE . . . . . . . . . . . . . . . . . . . . . . . . 200 KIAS

VLO . . . . . . . . . . . . . . . . . . . . . . . . 200 KIAS

Turbulent Air Penetration . . . . RECOMMENDED 180 KIAS

Maximum Maneuvering Speeds Citation II

Limitations – CII


3-2

Takeoff and Landing Operational LimitsMaximum Altitude . . . . . . . . . . . . . . . . . . . 14,000 FT

Maximum Ambient Temperature . . . . . . . . . . ISA +39°C

Minimum Ambient Temperature . . . . . . . . . . . . . . -54°C



Maximum Water/Slush on Runway . . . . . . . . . . . 0.4 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 031-613-8 are the only approvednose tires. The nose tire must be inflated to 120 ±5 PSI.

Enroute Operational LimitsMaximum Operating Altitude . . . . . . . . . . . . . 43,000 FT

Temperature Limits . . . . . . . . . . . . . . . . SEE GRAPH . . . . . . . . . . . . . . . . . . . . . . . . . . . .(Figure 3-3)

Generator Load:

Units 115 to 126 and 128 to 295 without SB550-54-04:

Up to 25,000 ft . . . . . . . . . . . . . . . . . . . . 400A

Above 25,000 ft . . . . . . . . . . . . . . . . . . . . 250A

Units 002 to 114; 115 to 126 and 128 to 295 with SB550-54-04; Unit 296 and subsequent:

Up to 35,000 ft . . . . . . . . . . . . . . . . . . . . 400A

Above 35,000 ft . . . . . . . . . . . . . . . . . . . . 325A

3B-8 For training only Citation I/II/SIIJuly 1999

Limitations – CII


Takeoff/Landing/Enroute Temperature LimitationsCitation II

3-3


Up (0°) . . . . . . . . . . . -1.52 TO +3.8G AT 13,300 LBS

T.O. & APPR to LAND(15° to 40°) . . . . . . . . . . 0.0 TO +2.0G AT 13,300 LBS

These accelerations limit angle-of-bank in turns andseverity of pullup maneuvers.

Landing . . . . . . . . . . . . . . . . . +3.75G AT 12,700 LBS


Limitations – CII


Single Pilot General andOperational Limitations(551 Models only)Conduct single pilot operations according to data establishedfor 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 61.57.� Single pilot operation is prohibited when operating from gravel

runways.

SP Maximum Weight LimitsRamp . . . . . . . . . . . . . . . . . . . . . . . . 12,700 LBS

Takeoff . . . . . . . . . . . . . . . . . . . . . . . . 12,500 LBS

Landing . . . . . . . . . . . . . . . . . . . . . . . 12,000 LBS

SP Landing GearMain Wheel Tire Pressure . . . . . . . . . . . . . 100 ±5 PSI

Nose Wheel Tire Pressure . . . . . . . . . . . . . 120 ±5 PSI


Limitations – CII


System LimitationsAvionics and CommunicationsAngle-of-Attack� May be used as a reference, but does not replace the pri-

mary 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 moni-

tor (AP TORQUE annunciator) does not test per AFM, SectionIV (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 oruncoupled) are prohibited without an operating radio altimeter.

� CII 418 and subsequent should have “H” mod. The “H” modcircuitry in flight director computer provides pseudo signals toflight director when radio altimeter is inoperative or notinstalled; therefore, the limitation for back course approachesis removed.

Dual Flight Director Installation� The copilot’s second attitude indicating system must be

installed, be operational, and remain operating throughout theflight for those aircraft equipped with dual flight directors.

� The dual flight director dual AC power distribution system mustfunction normally as verified by performing a preflight test ofthe AC system.


missions. If this occurs, disregard the ADF bearing duringtransmission 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 pro-

hibited.� If the chute deploys or jettisons above 110 kts, inspect the

mechanism for possible damage.


Limitations – CII

Citation I/II/SII For training only 3B-15July 1999

Electrical and Lighting SystemsBattery� If BATT O’HEAT annunciator illuminates during ground opera-

tion, 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 todetect possible cell damage. Refer to the MaintenanceManual for the procedure.

Generator Operating Limits

Generator Load:

Units 115 to 126 and 128 to 295 without SB550-54-04:

Up to 25,000 ft . . . . . . . . . . . . . . . . . . . . 400A

Above 25,000 ft . . . . . . . . . . . . . . . . . . . . 250A

Units 002 to 114; 115 to 126 and 128 to 295 with SB550-54-04; Unit 296 and subsequent:

Up to 35,000 ft . . . . . . . . . . . . . . . . . . . . 400A

Above 35,000 ft . . . . . . . . . . . . . . . . . . . . 325A

GPU Limitation� With GPU connected to aircraft, limit GPU output to a maxi-

mum of 1,000A and adjust the voltage to 28.5V DC with noload. 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.

NOTE: Three generator-assisted cross-starts equalone battery start. Do not count an external powerengine start as battery cycle.









Minimum Maximum


0.06% 0.15%


0.10% 0.15%

Limitations – CII



illuminate or indicated fuel is 169 lbs or less.

DifferentialMaximum Asymmetrical Difference . . . . . . . . . . 600 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.


– hours of avgas use are entered in the engine logbook




– Jet A, Jet A-1, Jet A-2, and Jet B





Min Fuel Temp., -29°C -54°C -54°CT.O.

Min Fuel Temp., -23°C -54°C -54°CStart

Max Fuel Temp 50°C 50°C 32°C

Max Altitude 43,000 ft 43,000 ft 18,000 ft



Limitations – CII


Hydraulic SystemApproved Fluids� Skydrol 500 A, B, B-4, C or LD-4� Hyjet, Hyjet W, III, or IV.

Ice and Rain ProtectionEngine 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. Forsustained ground operations, operate for one out of four min-utes at 65% turbine RPM.



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.


to 1/2 inch thickness.


Landing Gear and BrakesAnti-Skid� Anti-skid must be operative for takeoff and landing on

sod/dirt or gravel runways.


BrakesEmergency Air Pressure . . . . . . . . . 1,800 TO 2,050 PSI

Accumulator Precharge Static . . . . . . . . . . 675 ±25 PSI

Pressurized . . . . . . . . . . . . . . . . . . 900 to 1,300 PSI

Tire PressuresMain Wheels . . . . . . . . . . . . . . . . . . . . . 108 ±5 PSI

Nose Wheel . . . . . . . . . . . . . . . . . . . . . 120 ±5 PSI

Strut InflationMain Gear . . . . . . . . . . . . . . . . . . . 1 TO 2 INCHES

Nose Gear . . . . . . . . . . . . . . . . . . . . . . 5 INCHES

Limitations – CII


Oxygen System� The standard diluter-demand oxygen mask must be posi-

tioned around the neck above FL250 to qualify as quick-don-ning.

� The optional pressure-demand sweep-on oxygen mask mustbe 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% N1 for ambient temper-atures below -18°C.

� Maximum allowable thrust reverser deployed time is 15 min-utes in any one hour period.

� Limit engine static ground operation to less than 80% N1 forambient 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 pro-

hibited.� 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.

Powerplant – Pratt and Whitney TurbofanJT15D-4 or JT15D-4B� Aircraft with SB550-71-3 are restricted to 180-day operation.

Engine Fan Inspection� To ensure accurate fan speed thrust indication, inspect fan



For training only Citation I/II/SIIJune 1997

No Action Required Log Book Entry Required Refer to Engine Maintenance ManualState

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


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°C90 sec (MaxTransient)


3B-22

Limitations – CII


All Conditions Except Starting� If the inter-turbone temperature (ITT) exceeds 700°C or if


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– Castrol 5000


– Royco Turbine Oil 500 and 560

– Engine oils listed in the latest revision of Pratt and WhitneyCanada Inc. SB 7001.

� When mixing brands of oil, use any approved oil brand if thetotal quantity of added oil does not exceed two U.S. quarts inany 400-hour period. If more than two U.S. quarts of dissimi-lar oil brands must be added, drain and flush the complete oilsystem, then refill with a single brand of approved oil accord-ing to Engine Maintenance Manual instructions.

� If oils of nonapproved brands or of different viscosities becomeinter-mixed, drain and flush the complete oil system and refillwith an approved oil according to Engine Maintenance Manualinstructions.




Limitations – CII


Loaner Engines� Aircraft incorporating SB550-71-03 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 tempera-tures not exceeding ISA +39°C.

� Continuous ground operation of starter/generator amperageabove 325A is prohibited.

� Limit ground operation of pitot/static heat to two minutes toprevent 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% N2 is pro-hibited.

Pneumatic and Pressurization SystemsCabin 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 ISOCCUPIED must be displayed on the fixed portion of the aftdivider.

Cabin Pressurization LimitsNormal Cabin Pressurization . . . . . . . . . 0.0 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).


Citation I/II/SII For training only 3C-1June 1997

Limitations – Citation II-627 and Subsequent

General LimitationsAuthorized Operations� Day and Night� VFR and IFR Flight� Flight Into Icing Conditions

Maximum Baggage LoadsNose Compartment . . . . . . . . . . . . . . . . . . 350 LBS . . . . . . . . . . . . . . . .(LESS OPTIONAL EQUIPMENT)

Aft Tailcone Compartment . . . . . . . . . . . . . . . 200 LBS

Aft Cabin . . . . . . . . . . . . . . . . . . . . . . . . 600 LBS

Certification Status� FAR, Part 25; FAR, Part 23 (551)




3C-2 For training only Citation I/II/SIIJuly 1999

Flight Crew Requirement – Pilot/Copilot� Pilot in command must have CE-500 type rating and meet

FAR 61.58 requirements.� The copilot shall posess a multi-engine rating, an instrument

rating for flight above 18,000 ft or flight into instrument metero-logical conditions, and meet the requirements of FAR 61.55.


Passenger Seat Position� For all takeoffs and landings:� Seats fully upright and outboard� Seats aft of emergency exit in most aft position



Operational LimitationsMaximum Design WeightsRamp . . . . . . . . . . . . . . . . . . . . . . . . 14,300 LBS

Takeoff . . . . . . . . . . . . . . . . . . . . . . . . 14,100 LBS

Landing . . . . . . . . . . . . . . . . . . . . . . . 13,500 LBS

Zero Fuel . . . . . . . . . . . . . . . . . . . . . . 11,000 LBS� Takeoff weight is limited by the most restrictive of:

– maximum certified T/O weight 14,100 lbs


– takeoff field length.� Landing weight is limited by the most restrictive of:

– maximum certified landing weight 13,500 lbs



Center of Gravity Moment EnvelopeSee CG chart in Flight Planning chapter.

Forward Limit at 8,540 lbs or less . . . . . . 18.0% OF MAC . . . . . . . . . . . . . . . . . . . . 276.10” AFT OF DATUM)

Forward Limit at 14,100 lbs . . . . . . . . . . 23.3% OF MAC . . . . . . . . . . . . . . . . . . . .(280.40” AFT OF DATUM)

There is a straight line variation between 18.0 and 23.3%of MAC.

Aft Limit . . . . . . . . . . . . . . . . . . . . . 30.0% OF MAC . . . . . . . . . . . . . . . . . . . . .(285.8” AFT OF DATUM)

Limitations – CII-627


Weight and Balance� Operate the aircraft in accordance with the approved loading

schedule. (Refer to Weight and Balance Data Sheet andModel 550 Citation II Weight and Balance Manual.)

Maximum Maneuvering Speeds Citation II-627 and subsequent

3C-4 For training only Citation I/II/SIIJune 1997

3-4



Speed LimitsMaximum Operating:




Maximum Maneuvering (VA) . . . . . . . . . . . SEE CHART . . . . . . . . . . . . . . . . . . . . . . . . . . . .(Figure 3-4)







Partial flaps, T.O.& APPR (15%) . . . . . . . . . 202 KIAS

Maximum Landing Gear Extended (VLE) . . . . . . 262 KIAS

Maximum Landing Gear Operating:

(VLO – Extending) . . . . . . . . . . . . . . . . . . 250 KIAS

(VLO – Retracting) . . . . . . . . . . . . . . . . . 200 KIAS




Autopilot Operation . . . . . . . . 262 KIAS OR 0.705 MACH








Maximum Ground Tire Speed . . . . . . . . . . . . . 165 KTS� Goodyear tire part numbers 184F08-1 and 184F13-3 and

Goodrich nose tire part number 031-613-8 are the only nosetires 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.


Temperature Limits . . . . . . . . . . . . . . . . SEE GRAPH . . . . . . . . . . . . . . . . . . . . . . . . . . . .(Figure 3-5)

Generator Load:

To 35,000 ft . . . . . . . . . . . . . . . . . . . . . . . 400A

Above 35,000 ft . . . . . . . . . . . . . . . . . . . . . 325A

Takeoff/Landing/Enroute Temperature LimitationsCitation II-627 and subsequent



3-5


Up (0°) . . . . . . . . . . . -1.52 TO +3.8 G AT 14,100 LBS

T.O. & APPR to LAND(15° to 40°) . . . . . . . . . 0.0 TO +2.0 G AT 14,100 LBS

These accelerations limit angle-of-bank in turns andseverity of pull-up maneuvers.

Landing, Flaps – T.O. & APPR to LAND(15° to 40°) . . . . . . . . . . . . . . . +3.5G AT 13,500 LBS




System LimitationsAvionics and CommunicationsAngle-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 flapsat zero, takeoff, takeoff/approach and landing positions.

Automatic Director Finder Systems (ADF)� The ADF bearing information may be erratic during HF trans-

mission. If this occurs, disregard the ADF bearing duringtransmission periods.


ing 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 NormalProcedures in the AFM.

� Autopilot/yaw damper must be off for takeoff/landing.

Standby Gyro Horizon� A satisfactory preflight test must be accomplished.

Electrical and Lighting SystemsBattery� Limit engine starts to three per hour. If battery limitation is

exceeded, accomplish a deep cycle with a capacity check todetect possible cell damage (see cycle procedure inMaintenance Manual).

� If the BATT O’TEMP annunciator illuminates during groundoperation, do not take off until proper maintenance is accom-plished.

Generator Operating LimitsGenerator Load:

To 35,000 ft . . . . . . . . . . . . . . . . . . . . . . . 400A

Above 35,000 ft . . . . . . . . . . . . . . . . . . . . . 325A� 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 withno 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, generator-

assisted cross-start, or GPU), the starter is limited to threeengine starts per 30 minutes, and three cycles of operationwith a 30-second rest between cycles.


NOTE: Three generator-assisted cross-starts equalone battery start. Do not count an external powerengine start as a battery cycle.










Minimum Maximum


0.06% 0.15%


0.10% 0.15%





Aviation Gasoline� All grades of MIL-G-5572 avgas are permitted for a maxi-

mum of 50 hours or 3,500 gallons between overhauls, pro-vided 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 engineoperation equals 70 gals gasoline.)



– Jet A, Jet A-1, A-2, and Jet B










Max Asymmetric 600 lbs 600 lbs 600 lbsFuel Differential

Fuel Control 0.81 0.79 0.73Density Adjust.for Optimum Engine Accel.


Ice and Rain ProtectionEngine 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. (Forsustained ground operations, operate for one out of four min-utes at 65% turbine RPM.




when operating in visible moisture with OAT at +4 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.


to 1/2 inch thickness.







Tire Pressures Main Wheels . . . . . . . . . . . . . . . . . . . . . 115 ±5 PSI

Nose Wheel . . . . . . . . . . . . . . . . . . . . . 120 ±5 PSI



Nose Gear . . . . . . . . . . . . . . . . . . . . . . 5 INCHES


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.










NOTE: Headsets, eyeglasses, or hats worn by thecrew may interfere withthe quick-donning capabilities ofthe oxygen masks.



Powerplant – Pratt and Whitney Turbofan JT15D-4Engine Fan Inspection� To ensure accurate fan speed thrust indication, inspect fan







Max Cruise Continuous 670°C 96% RPM 104% RPM 70 to 85 PSIG 0° to 121°C


Start –– 700°C (2 sec) –– –– –– -40°C (min)

Transient –– 700°C 96% RPM 104% RPM 95 PSIG 0° to 121°C(90 sec)

AREA A – ENGINE LOGBOOKENTRY REQUIRED.

AREA B – REFER TO ENGINEMAINTENANCE MANUALFOR CORRECTIVE ACTION.ENGINE LOGBOOKENTRY REQUIRED.

BBA

NO ACTION REQUIRED

TIME – MINUTES

TURBINE OVERSPEED LIMITS

20 SECS 1 MIN 2 MIN

92

94

96

98

100

102

104

106

108

110

112

TU

RB

INE

SP

EE

D –

PE

RC

EN

T R

PM

AREA A – ENGINE LOGBOOKENTRY REQUIRED.

AREA B – REFER TO ENGINEMAINTENANCE MANUALFOR CORRECTIVE ACTION.ENGINE LOGBOOKENTRY REQUIRED.

BA

NO ACTION REQUIRED

TIME – MINUTES

FAN OVERSPEED LIMITS

20 SECS 1 MIN 2 MIN

102

104

106

108

110

112

FAN

SP

EE

D –

PE

RC

EN

T R

PM

A

3C-17


All Conditions Except Starting� If the inter-turbine temperature (ITT) exceeds 700°C or if



750

700

650

600

550

5000 5 10 15

TIME (SECOND)IN

TE

R-T

UR

BIN

E T

EM

PE

RA

TU

RE

(°C

)

AREA “A”ENVELOPE

INVESTIGATE CAUSE FOR ALLTEMPERATURES EXCEEDINGAREA “A” ENVELOPE. REFERTO CHAPTER 77 OF THEAIRPLANE MAINTENANCEMANUAL. ENGINE LOGBOOKENTRY REQUIRED.






– Castrol 5000



– Engine oils listed in the latest revision of Pratt and WhitneyCanada Inc. SB 7001.

� If necessary to replenish oil with a brand other than thatremaining in the tank, use any approved oil brand if the totalquantity of added oil does not exceed two U.S. quarts in any400-hour period. If more than two U.S. quarts of a dissimilaroil brand must be added, drain and flush the complete oilsystem, then refill with a single brand of approved oil accord-ing to Engine Maintenance Manual instructions.

� If oils of nonapproved brands or of different viscositiesbecome inter-mixed, drain and flush the complete oil systemand refill with an approved oil according to EngineMaintenance Manual instructions.



Loaner Engines� Aircraft incorporating SB550-71-03 are restricted to 90-day

operation only.


including five minutes at takeoff thrust, to ambient tempera-tures not exceeding 39°C above ISA.


� Limit ground operation of pitot/static heat to two minutes toprevent damage to the pitot-static heater.

� Operation in the GND bleed mode at power settings greaterthan 70% turbine RPM (N2) for the right engine is prohibited.




Pneumatic and Pressurization SystemsCabin Pressurization Limits

Normal Cabin Pressurization . . . . . . 0.0 TO 8.8 ±0.1 PSID

Flood Cooling� Operation of the 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).


Citation I/II/SII For training only 3D-1June 1997

Limitations – Citation SII

General LimitationsAuthorized Operations� Day and Night� VFR and IFR Flight� Flight Into Icing Conditions (Figure 3-6)� Engine anti-ice must be on during ground and flight opera-

tions when icing conditions exist or are anticipated (visiblemoisture with OAT between +10°C and -30°C).

Maximum Baggage LoadsNose Compartment:

With SBS550-30-15(Anti-Ice System Improvement) . . . . . . . . . 330 LBS

Without SBS550-30-15 . . . . . . . . . . . . . . . 350 LBS

Aft Cabin . . . . . . . . . . . . . . . . . . . . . . . . 600 LBS

Tailcone Compartment:

Without Freon Air-Conditioning:

Forward of Cargo Net . . . . . . . . . . . . . . 300 LBS

Aft of Cargo Net . . . . . . . . . . . . . . . . . . 200 LBS

TOTAL . . . . . . . . . . . . . . . . . . . . . . . 500 LBS

With Freon Air-Conditioning . . . . . . . . . . . 300 LBS

There is no distinction between forward or aft of cargo net.

3D-2 For training only Citation I/II/SIIJuly 1999

Required Minimum Engine Ice ProtectionFluid Quantity

Certification Status� FAR, Part 25




3-6

Flight Crew Requirements – Pilot/Copilot� Pilot in command must have CE-500 type rating and meet

FAR 61.58 requirements.� The copilot shall posess a multi-engine rating, an instrument rat-

ing for flight above 18,000 ft or flight into instrument meterolog-ical conditions, and meet the requirements of FAR 61.55.


Passenger Seat Position� For all takeoffs and landings:� Seats fully upright and outboard� Seats aft of emergency exit must be in most aft position.



Limitations – SII

Citation I/II/SII For training only 3D-3July 1999

3D-4 For training only Citation I/II/SIIJune 1997

Limitations – SII


Operational LimitationsMaximum WeightsSII 001 to 085 without SBS550-11-1:

Ramp . . . . . . . . . . . . . . . . . . . . . . . 14,900 LBS

Takeoff . . . . . . . . . . . . . . . . . . . . . . 14,700 LBS

Landing . . . . . . . . . . . . . . . . . . . . . . 14,000 LBS

Zero Fuel . . . . . . . . . . . . . . . . . . . . . 11,000 LBS

SII 001 to 085 with SBS550-11-1; 086 and subsequent:

Ramp . . . . . . . . . . . . . . . . . . . . . . . 15,300 LBS

Takeoff . . . . . . . . . . . . . . . . . . . . . . 15,100 LBS

Landing . . . . . . . . . . . . . . . . . . . . . . 14,400 LBS

Zero Fuel . . . . . . . . . . . . . . . . . . . . . 11,200 LBS

Maximum takeoff and landing weights may be additionallyrestricted due to altitude, temperature, and field length.

� Takeoff weight is limited by most restrictive of:



– takeoff field length.� Landing weight is limited by most restrictive of:





Center of Gravity Moment EnvelopeSII 001 to 085 without SBS550-11-1:

Forward Limit:

At 9,600 lbs or less . . . . . . . . . . . . . . 15.0% MAC . . . . . . . . . . . . . . . . .(273.71” AFT OF DATUM)

At 14,700 lbs . . . . . . . . . . . . . . . . . 19.92% MAC . . . . . . . . . . . . . . . . .(277.69” AFT OF DATUM)

There is a straight line variation between 15.0 and19.92% MAC.

Aft Limit at 14,700 lbs or less . . . . . . . . . . 28.0% MAC . . . . . . . . . . . . . . . . . . .(284.23” AFT OF DATUM)


Forward Limit:

At 9,600 Lbs . . . . . . . . . . . . . . . . . . 15.0% MAC . . . . . . . . . . . . . . . . .(273.71” AFT OF DATUM)

At 15,100 Lbs . . . . . . . . . . . . . . . . . 20.3% MAC . . . . . . . . . . . . . . . . .(277.99” AFT OF DATUM)

There is a straight line variation between 15.0 and 20.3%MAC.

Aft Limit at 14,700 Lbs or Less . . . . . . . . . 28.0% MAC . . . . . . . . . . . . . . . . . . .(284.23” AFT OF DATUM)

Speed LimitsMMO above 29,315 ft . . . . . . . . . . . 0.721M INDICATED

VMO 8,000 to 29,315 ft . . . . . . . . . . . . . . . . 276 KIAS

VMO below 8,000 ft . . . . . . . . . . . . . . . . . . 261 KIAS

Do not exceed these limits in any flight regime (climb, cruise,or descent) unless a higher speed is authorized for flight testor pilot training.

Maximum Maneuvering (VA) . . . . . . . . . . . SEE CHART . . . . . . . . . . . . . . . . . . . . .(Figure 3-7, page 3-81)






Full flaps, LAND (35°) 172 KIAS

Partial flaps, T.O./T.O.& APPR (7°/20°) 200 KIAS

7° flap performance is available on SII 057 and subsequentand 001 to 056 with SBS550-27-2.




Autopilot Operation . . . . . . . . . . . . . 276 KIAS/0.721M

Limitations – SII


Landing Gear Speeds:

Without SBS550-32-8 (Increased Maximum Gear Extend Speed):

VLE . . . . . . . . . . . . . . . . . . . . . . . . 172 KIAS

VLO . . . . . . . . . . . . . . . . . . . . . . . . 172 KIAS

With SBS550-32-8:

VLE . . . . . . . . . . . . . . . . . . . . . . . . . . . VMO

VLO (Extending) . . . . . . . . . . . . . . . . . 250 KIAS

VLO (Retracting) . . . . . . . . . . . . . . . . . 200 KIAS

With Gravel Runway Kit and SBS550-32-8:

VLE . . . . . . . . . . . . . . . . . . . . . . . . . . . 200 KIAS

VLO . . . . . . . . . . . . . . . . . . . . . . . . 200 KIAS

Maximum Tire Ground Speed . . 165 KTS RECOMMENDED





Maximum Tailwind Components . . . . . . . . . . . . 10 KTS


Maximum Crosswind with T/Rs deployed . . . . . . . 25 KTS� Autopilot/yaw damper must be off for takeoff/landing.� Vertical navigation system must be off below 500 ft AGL.


Limitations – SII


Maximum Maneuvering Speeds Citation SII

3-7


Ambient Temperature Limits . . . . . . . . . . . SEE GRAPH . . . . . . . . . . . . . . . . . . . . . . . . . . . .(Figure 3-8)

Generator Load . . . . . . . . . . . . . . . . . . . . . . . 300A


Up (0°) . . . . . . . . . . . . . . . . . . . . -1.52 TO +3.8 G

T.O./T.O. & APPR/ LAND (7° to 35°) . . . . 0.0 TO +2.0 G

7° flaps performance available on SII 057 and subse-quent and 001 to 056 with SBS550-27-2.

These accelerations limit angle-of-bank in turns andseverity of pullup maneuvers.

During Landing, Flaps:

T.O. & APPR/LAND (20° to 35°) . . . . . . . . . . . +3.5 G


Limitations – SII


Takeoff/Landing/EnrouteTemperature LimitsCitation SII

3-8


Limitations – SII


System LimitationsAvionics and CommunicationsAngle-of-Attack� AOA may be used as reference, but does not replace the pri-

mary airspeed indicator.� AOA can be used as reference for approach speed (1.3 VSI)

at all aircraft weights and CG locations with flaps at zero,takeoff/approach, and landing positions.

� If AOA or stick shaker is inoperative during warning systemtest, the system must be repaired before flight.


ing all AP operations.� AP current monitor must be functionally tested prior to inflight

use.� AP operation is prohibited above 14,500 ft if torque monitor

does not test per AFM,III.� Autopilot/yaw damper must be off for takeoff/landing.� Vertical navigation system must be off below 500 ft AGL.


missions. If this occurs, disregard ADF bearing during trans-mission periods.

Electrical and Lighting SystemsBattery� If the BATT O’HEAT annunciator illuminates during ground

operation, do not take off until proper maintenance is accom-plished.

� Limit engine starts to three per hour. If the battery limitationis exceeded, accomplish a deep cycle with capacity check todetect possible cell damage. Refer to the MaintenanceManual for procedure.

Enroute Operating Limits

Maximum Generator Load . . . . . . . . . . . . . . . . . 300A

GPU Limitation� With GPU connected to aircraft, limit GPU output to a maxi-

mum of 1,000A and adjust voltage to 28V DC with no load.Exceeding these limits may damage the starter.

Starter Limitation� With external power or generator-assisted cross-start as the

starter power source, limit engine starts to two per 30 min-utes with a 30-second rest between cycles.

� With the battery as the power source, limit engine starts tothree per 30 minutes with a 30-second rest between cycles.

Prolonged Ground Operation� Continuous ground operation of a starter/generator above

225 amps is prohibited.


NOTE: Three generator-assisted cross-starts equalone battery start. Do not count an external powerengine start as battery cycle.

Limitations – SII









Minimum Maximum


0.06% 0.15%


0.10% 0.15%





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 ambient air temperature at takeoff is +32°C.


– hours of avgas usage is entered in the engine logbook




– Jet A, Jet A-1, Jet A-2, and Jet B

– JP-4, JP-5, and JP-8.



Limitations – SII







Emergency 600 lbs 600 lbs 600 lbsAsymmetric Fuel



Ice and Rain ProtectionEngine Anti-Ice System� All surface anti-ice fluids meeting British Deicing Fluid

Specification DTD 406 B (NATO Symbol S-745) are approved.� 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 fourminutes at 65% turbine RPM.

� For flight into known/forecasted icing, the anti-ice fluid reser-voir must be full. For all other flights, a minimum of 1.5 gal-lons or higher as determined from the TKS minimum quanti-ty chart in the AFM.


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 isabove -18°C (0°F).

� Set the W/S BLEED switch to HI (280°F) when OAT is -18°C(0°F) or below.




Limitations – SII






Tire PressuresSII 001 to 085 without SBS550-11-1 (gross weight increase):

Nose/Main Wheels . . . . . . . . . . . . . . . . 120 ±5 PSI


Main Wheels . . . . . . . . . . . . . . . . . . . 125 ±5 PSI

Nose Wheel . . . . . . . . . . . . . . . . . . . . 120 ±5 PSI


Nose Gear . . . . . . . . . . . . . . . . . . . . . 3-5 INCHES


Oxygen System� The standard diluter-demand oxygen mask must be positioned

around the neck above FL 250 to qualify as quick-donning.� The optional pressure-demand sweep-on oxygen mask must

be properly stowed to qualify as quick-donning.










NOTE: The red line on the oil temperature indicator dictates oil temperature limitation. Some indicators arered-lined at 115°C and other at 121°. In either case, donot exceed the red line indication.

Limitations – SII


Powerplant – Pratt and Whitney Turbofan JT15D-4BEngine Fan Inspection� To ensure accurate fan speed thrust indication, inspect fan







Start –– 700°C (2 sec) –– –– –– -40°C (min)

Acceleration –– 710°C 97% RPM 106% RPM –– 0° to 121°C

Log Book Entry Required Refer to Engine Maintenance ManualState

Fan Speed Turbine Speed Turbine Speed Fan Speed

Transient 106 to 112% RPM 96 to 98% RPM Exceeds 99% RPM Exceeds 112% RPM

Steady 106 to 108% RPM –– Exceeds 97% RPM Exceeds 108% RPM


3D-21



� Starting ITT over 500°C is not normal; if this occurs, takeaction as illustrated in the starting envelope.

� All conditions except starting: ITT indications in excess of710°C or 690°C for more than five minutes require referenceto the Engine Maintenance Manual.

700

650

600

550

5000 5 10 15

TIME (SECONDS)

INT

ER

TU

RB

INE

TE

MP

ER

AT

UR

E (

°C)

REFER TO TURBOFANENGINE MAINTENANCEMANUAL

750

Limitations – SII





– Castrol 5000



– Engine oils listed in latest revision of Pratt and WhitneyCanada Inc. SB 7001.

� When mixing brands of oil, use any listed approved oil brandif the total quantity of added oil does not exceed two U.S.quarts in any 400-hour period. If more than two U.S. quartsof dissimilar oil brands are needed, drain and flush completeoil system, then refill with a single brand of approved oil.

� If oils of nonapproved brands or of different viscositiesbecome intermixed, drain and flush the complete oil systemand refill with an approved oil.




including five minutes at takeoff thrust, to ambient tempera-tures not exceeding ISA +39°C.


� Limit ground operation of pitot/static heat to two minutes toprevent damage to AOA system.

� Operation in GND bleed air mode with the right engine set atgreater than 70% N2 is prohibited.

Pneumatic and Pressurization SystemsCabin Pressurization Limits

Normal Cabin Pressurization . . . . . . . . . 0.0 TO 8.8 PSID


Documents

04 Limitations