04 limitations
TRANSCRIPT
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
Limitations – C0/CI
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
3A-4 For training only Citation I/II/SIIJune 1997
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):
MMO above 28,000 ft . . . . . . . . . 0.705 M INDICATED
VMO 14,000 to 28,000 ft . . . . . . . . . . . . . . 277 KIAS
14,000 to 30,500 ft (9,500 lb ZFW) . . . . . . . 262 KIAS
VMO sea level to 14,000 ft . . . . . . . . . . . . . 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
Limitations – C0/CI
Citation I/II/SII For training only 3A-5June 1997
Maximum Maneuvering SpeedsCitation; Citation I
3A-6 For training only Citation I/II/SIIJune 1997
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
Limitations – C0/CI
Citation I/II/SII For training only 3A-7June 1997
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
3A-8 For training only Citation I/II/SIIJune 1997
Limitations – C0/CI
Citation I/II/SII For training only 3A-9June 1997
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).
3A-10 For training only Citation I/II/SIIJune 1997
Limitations – C0/CI
Citation I/II/SII For training only 3A-11June 1997
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.
3A-12 For training only Citation I/II/SIIJune 1997
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.
Limitations – C0/CI
Citation I/II/SII For training only 3A-13June 1997
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%
3A-14 For training only Citation I/II/SIIJune 1997
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
Limitations – C0/CI
Citation I/II/SII For training only 3A-15June 1997
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).
3A-16 For training only Citation I/II/SIIJune 1997
CAUTION: Limit ground operation of pitot/static heat totwo minutes to prevent damage to the angle-of-attacksystem.
Limitations – C0/CI
Citation I/II/SII For training only 3A-17June 1997
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.
3A-18 For training only Citation I/II/SIIJune 1997
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
Limitations – C0/CI
3A-20 For training only Citation I/II/SIIJune 1997
Limitations – C0/CI
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.
3A-22 For training only Citation I/II/SIIJune 1997
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.
Limitations – C0/CI
Citation I/II/SII For training only 3A-23June 1997
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.
3A-24 For training only Citation I/II/SIIJune 1997
Limitations – C0/CI
Citation I/II/SII For training only 3A-25June 1997
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).
3A-26 For training only Citation I/II/SIIJune 1997
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.
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.
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:
– 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 requirementsor brake energy limit
– landing distance.
Limitations – CII
Citation I/II/SII For training only 3B-3June 1997
Center of Gravity Moment EnvelopeSee CG chart in Flight Planning chapter.
Forward Limit:
At 13,300 lbs . . . . . . . . . . . . . . . . . 22.6% OF MAC . . . . . . . . . . . . . . . . . . .(279.8” AFT OF DATUM)
At 12,500 lbs . . . . . . . . . . . . . . . . . 21.8% OF MAC . . . . . . . . . . . . . . . . . . .(279.2” AFT OF DATUM)
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
Citation I/II/SII For training only 3B-5June 1997
Speed LimitsMaximum VMO/MMO – 9,500 Lbs Zero Fuel Weight:
MMO above 28,000 ft . . . . . . . . . 0.705 M INDICATED
VMO 14,000 to 28,000 ft . . . . . . . . . . . . . . 277 KIAS
VMO sea level to 14,000 ft . . . . . . . . . . . . . 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 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
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 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 (VFE):
Full flaps, LAND (40°) . . . . . . . . . . . . . . . 176 KIAS
Partial flaps, T.O.& APPR (15°) . . . . . . . . . . 202 KIAS
Maximum Speedbrake Operation (VSB) . . . . . . . NO LIMIT
Minimum Control – Air (VMCA) . . . . . . . . . . . . . 77 KIAS
Minimum Control – Ground (VMCG) . . . . . . . . . . 62 KIAS
Maximum Tire Ground Speed . . . . . . . . . . . . . 165 KTS
3B-6 For training only Citation I/II/SIIJune 1997
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
Citation I/II/SII For training only 3B-7June 1997
3-2
Takeoff and Landing Operational LimitsMaximum Altitude . . . . . . . . . . . . . . . . . . . 14,000 FT
Maximum Ambient Temperature . . . . . . . . . . ISA +39°C
Minimum Ambient Temperature . . . . . . . . . . . . . . -54°C
Maximum Crosswind . . . . . . . DEMONSTRATED 23 KTS
Maximum Tailwind Component . . . . . . . . . . . . . 10 KTS
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
Citation I/II/SII For training only 3B-9June 1997
Takeoff/Landing/Enroute Temperature LimitationsCitation II
3-3
Load FactorsIn Flight, Flaps:
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
3B-10 For training only Citation I/II/SIIJune 1997
Limitations – CII
Citation I/II/SII For training only 3B-11June 1997
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
3B-12 For training only Citation I/II/SIIJune 1997
Limitations – CII
Citation I/II/SII For training only 3B-13June 1997
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.
HF/ADF Systems� The ADF bearing information may be erratic during HF trans-
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.
3B-14 For training only Citation I/II/SIIJune 1997
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.
3B-16 For training only Citation I/II/SIIJune 1997
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%
Limitations – CII
Citation I/II/SII For training only 3B-17June 1997
Boost Pumps� Turn on boost pumps when FUEL LEVEL LO annunciators
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.
– 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
3B-18 For training only Citation I/II/SIIJune 1997
Jet A, A-1, -2; Jet B; JP-4 AvgasJP-5, JP-8
Fuel Limitations and Adjustments
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
Max Asymmetric 600 lbs 600 lbs 600 lbsFuel
Fuel Control 0.81 0.79 0.73Density
Limitations – CII
Citation I/II/SII For training only 3B-19July 1999
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 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.
3B-20 For training only Citation I/II/SIIJune 1997
Landing Gear and BrakesAnti-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 031-613-8
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
Citation I/II/SII For training only 3B-21July 1999
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 damage prior to each flight.
Engine Operating Limits
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
Thrust Setting Time Limit ITT Temp N2 N1 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°C90 sec (MaxTransient)
Engine Overspeed Limits
3B-22
Limitations – CII
Citation I/II/SII For training only 3B-23June 1997
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 theEngine Maintenance Manual.
���
���
���
���
���
���� � �� ��
����� ����
���
�
���
��
��
�
��
�
��
��
�
� �
�����������
��������� ������������������� ��������������� ����� !���������!��������������� ������ ����������"���#�$����
Inter-Turbine Temperature LimitsStarting Conditions Only
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 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.
� Minimum oil temperature for starting is -40°C (-40°F).
3B-24 For training only Citation I/II/SIIJune 1997
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.
Limitations – CII
Citation I/II/SII For training only 3B-25July 1999
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).
3B-26 For training only Citation I/II/SIIJune 1997
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)
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
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.
� 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
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.
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
– 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 requirementsor brake energy limit
– landing distance.
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
Citation I/II/SII For training only 3C-3June 1997
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
Limitations – CII-627
Citation I/II/SII For training only 3C-5June 1997
Speed LimitsMaximum Operating:
MMO above 30,500 ft . . . . . . . . . 0.705 M INDICATED
VMO sea level to 30,500 ft . . . . . . . . . . . . . 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 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 (VFE):
Full flaps, LAND (40°) . . . . . . . . . . . . . . . 176 KIAS
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
Maximum Speedbrake Operation (VSB) . . . . . . . NO LIMIT
Minimum Control – Air (VMCA) . . . . . . . . . . . . . 77 KIAS
Minimum Control – Ground (VMCG) . . . . . . . . . . 62 KIAS
Autopilot Operation . . . . . . . . 262 KIAS OR 0.705 MACH
3C-6 For training only Citation I/II/SIIJune 1997
Takeoff and Landing Operational LimitsMaximum Altitude . . . . . . . . . . . . . . . . . . . 14,000 FT
Maximum Tailwind Component . . . . . . . . . . . . . 10 KTS
Maximum Crosswind . . . . . . . DEMONSTRATED 23 KTS
Maximum Water/Slush on Runway . . . . . . . . . . . 0.4 IN
Maximum Ambient Temperature . . . . . . . . . . ISA +39°C
Minimum Ambient Temperature . . . . . . . . . . . . . . -54°C
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.
Enroute Operational LimitsMaximum Operating Altitude . . . . . . . . . . . . . 43,000 FT
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
Limitations – CII-627
Citation I/II/SII For training only 3C-7June 1997
3-5
Load FactorsIn Flight, Flaps:
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
3C-8 For training only Citation I/II/SIIJuly 1999
Limitations – CII-627
Citation I/II/SII For training only 3C-9June 1997
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.
Autopilot� One pilot must remain in his seat with seat belt fastened dur-
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.
3C-10 For training only Citation I/II/SIIJune 1997
NOTE: Three generator-assisted cross-starts equalone battery start. Do not count an external powerengine start as a battery cycle.
Limitations – CII-627
Citation I/II/SII For training only 3C-11June 1997
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%
3C-12 For training only Citation I/II/SIIJune 1997
Boost Pumps� Turn on boost pumps when FUEL LEVEL LO annunciators
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 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 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
Limitations – CII-627
Citation I/II/SII For training only 3C-13June 1997
Fuel Limitations and Adjustments
Jet A, A-1, -2; Jet B; JP-4 AvgasJP-5, JP-8
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
Max Asymmetric 600 lbs 600 lbs 600 lbsFuel Differential
Fuel Control 0.81 0.79 0.73Density Adjust.for Optimum Engine Accel.
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 +4 to -30°C. (Forsustained ground operations, operate for one out of four min-utes 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 +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.
Wing Deice System� Wing deice is required in flight when wing ice builds up to 1/4
to 1/2 inch thickness.
3C-14 For training only Citation I/II/SIIJune 1997
Limitations – CII-627
Citation I/II/SII For training only 3C-15June 1997
Landing Gear and BrakesAnti-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 031-613-8
Tire Pressures Main Wheels . . . . . . . . . . . . . . . . . . . . . 115 ±5 PSI
Nose Wheel . . . . . . . . . . . . . . . . . . . . . 120 ±5 PSI
BrakesEmergency Air Pressure . . . . . . . . . 1,800 TO 2,050 PSI
Strut InflationMain Gear . . . . . . . . . . . . . . . . . . . 1 TO 2 INCHES
Nose Gear . . . . . . . . . . . . . . . . . . . . . . 5 INCHES
3C-16 For training only Citation I/II/SIIJuly 1999
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% 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.
NOTE: Headsets, eyeglasses, or hats worn by thecrew may interfere withthe quick-donning capabilities ofthe oxygen masks.
Limitations – CII-627
Citation I/II/SII For training onlyJune 1997
Powerplant – Pratt and Whitney Turbofan JT15D-4Engine Fan Inspection� To ensure accurate fan speed thrust indication, inspect fan
for damage prior to each flight.
Engine Operating Limits
Engine Overspeed Limits
Thrust Setting Time Limit ITT Temp N2 N1 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)
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
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.
3C-18 For training only Citation I/II/SIIJune 1997
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.
Limitations – CII-627
Citation I/II/SII For training only 3C-19June 1997
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 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.
� 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.
Loaner Engines� Aircraft incorporating SB550-71-03 are restricted to 90-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 39°C above ISA.
� Continuous ground operation of starter/generator amperageabove 325A is prohibited.
� 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.
3C-20 For training only Citation I/II/SIIJune 1997
Limitations – CII-627
Citation I/II/SII For training only 3C-21June 1997
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).
3C-22 For training only Citation I/II/SIIJune 1997
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
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
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.
� 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 must be 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 gearassembly to the cylinder.
Limitations – SII
Citation I/II/SII For training only 3D-3July 1999
3D-4 For training only Citation I/II/SIIJune 1997
Limitations – SII
Citation I/II/SII For training only 3D-5June 1997
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:
– 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 requirementsor brake energy limit
– landing distance.
3D-6 For training only Citation I/II/SIIJune 1997
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)
SII 001 to 085 with SBS550-11-1; 086 and subsequent:
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)
� 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 (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.
Maximum Speedbrake Operation (VSB) . . . . . . . NO LIMIT
Minimum Control – Air (VMCA) . . . . . . . . . . . . . 83 KIAS
Minimum Control – Ground (VMCG) . . . . . . . . . . 73 KIAS
Autopilot Operation . . . . . . . . . . . . . 276 KIAS/0.721M
Limitations – SII
Citation I/II/SII For training only 3D-7June 1997
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
Takeoff and Landing Operational LimitsMaximum Altitude . . . . . . . . . . . . . . . . . . . 14,000 FT
Maximum Ambient Temperature . . . . . . . . . . ISA +39°C
Minimum Ambient Temperature . . . . . . . . . . . . . . -54°C
Maximum Crosswind . . . . . . . DEMONSTRATED 29 KTS
Maximum Tailwind Components . . . . . . . . . . . . 10 KTS
Maximum Water/Slush on Runway . . . . . . . . . . . 0.5 IN
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.
3D-8 For training only Citation I/II/SIIJune 1997
Limitations – SII
Citation I/II/SII For training only 3D-9June 1997
Maximum Maneuvering Speeds Citation SII
3-7
Enroute Operational LimitsMaximum Operating Altitude . . . . . . . . . . . . . 43,000 FT
Ambient Temperature Limits . . . . . . . . . . . SEE GRAPH . . . . . . . . . . . . . . . . . . . . . . . . . . . .(Figure 3-8)
Generator Load . . . . . . . . . . . . . . . . . . . . . . . 300A
Load FactorsIn Flight, Flaps:
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
3D-10 For training only Citation I/II/SIIJune 1997
Limitations – SII
Citation I/II/SII For training only 3D-11June 1997
Takeoff/Landing/EnrouteTemperature LimitsCitation SII
3-8
3D-12 For training only Citation I/II/SIIJune 1997
Limitations – SII
Citation I/II/SII For training only 3D-13June 1997
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.
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.� 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.
HF/ADF Systems� The ADF bearing information may be erratic during HF trans-
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.
3D-14 For training only Citation I/II/SIIJune 1997
NOTE: Three generator-assisted cross-starts equalone battery start. Do not count an external powerengine start as battery cycle.
Limitations – SII
Citation I/II/SII For training only 3D-15June 1997
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%
3D-16 For training only Citation I/II/SIIJune 1997
Boost Pumps� Turn on boost pumps when FUEL LEVEL LO annunciators
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 ambient air temperature at takeoff is +32°C.
– boost pumps are on
– hours of avgas usage is 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.
Fuel Limitations and Adjustments
Jet A, A-1, -2; Jet B; JP-4 AvgasJP-5, JP-8
Limitations – SII
Citation I/II/SII For training only 3D-17June 1997
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
Max Asymmetric 200 lbs 200 lbs 200 lbsFuel
Emergency 600 lbs 600 lbs 600 lbsAsymmetric Fuel
Fuel Control 0.81 0.79 0.73Density
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� 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.
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 isabove -18°C (0°F).
� Set the W/S BLEED switch to HI (280°F) when OAT is -18°C(0°F) or below.
Windshield Alcohol Anti-Ice System� Use TT-I-735 isopropyl alcohol for windshield anti-ice. The
backup alcohol system is sufficient for 10 minutes.
3D-18 For training only Citation I/II/SIIJune 1997
Limitations – SII
Citation I/II/SII For training only 3D-19June 1997
Landing Gear and BrakesAnti-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 031-613-8
BrakesEmergency Air Pressure . . . . . . . . . 1,800 TO 2,050 PSI
Tire PressuresSII 001 to 085 without SBS550-11-1 (gross weight increase):
Nose/Main Wheels . . . . . . . . . . . . . . . . 120 ±5 PSI
SII 001 to 085 with SBS550-11-1; 086 and subsequent:
Main Wheels . . . . . . . . . . . . . . . . . . . 125 ±5 PSI
Nose Wheel . . . . . . . . . . . . . . . . . . . . 120 ±5 PSI
Strut InflationMain Gear . . . . . . . . . . . . . . . . . . . 1 TO 2 INCHES
Nose Gear . . . . . . . . . . . . . . . . . . . . . 3-5 INCHES
3D-20 For training only Citation I/II/SIIJune 1997
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.
Thrust Reversers� Reduce reverse thrust power to idle reverse at 60 KIAS on
landing roll.� Limit maximum reverse thrust setting to 95% 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.
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
Citation I/II/SII For training onlyJune 1997
Powerplant – Pratt and Whitney Turbofan JT15D-4BEngine 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 N2 N1 Oil Press Oil Temp
Takeoff 5 minutes 700°C 97% RPM 106% RPM 70 to 85 PSIG 10° to 121°C
Max Continuous Continuous 680°C 97% RPM 106% 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 –– 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
Engine Overspeed Limits
3D-21
3D-22 For training only Citation I/II/SIIJune 1997
Inter-Turbine Temperature LimitsStarting Conditions Only
� 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
Citation I/II/SII For training only 3D-23June 1997
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 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.
� 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� 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 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
3D-24 For training only Citation I/II/SIIJune 1997