Limitations

SECTION II - OPERATING LIMITATIONS
TABLE OF CONTENTS
MODEL 550
OPERATING LIMITATIONS
TABLE OF CONTENTS
Page
OPERATING LIMITATIONS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
2-3
Certification Status
...................................................
2-3
Weight Limitations . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
2-3
Center-of-Gravity Limits . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
2-3
Weight and Balance Data
..............................................
2-3
Powerplant Limitations
................................................
2-3
Engine Fan Inspection . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
2-7
Battery and Starter Cycle Limitations
......................................
2-7
Prolonged Ground Operation . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
2-8
Windshield Ice Protection Fluid
.........................................
2-10
Hydraulic Fluid . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
2-10
Approved Oils . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
2-10
Fuel Limitations
....................................................
2-11
Unusable Fuel . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
2-11
Speed Limitations
..................................................
2-12
Takeoff and Landing Operational Limits
...................................
2-13
Enroute Operational Limits
............................................
2-13
Operations Authorized . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
2-13
Minimum Crew . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
2-13
Load Factor
.......................................................
2-13
Cabin Pressurization Limitations
........................................
2-16
Maneuvers . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
2-16
Passenger Seat Position . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
2-16
Operations in Severe Icing Conditions
....................................
2-16
Airplane Battery
....................................................
2-17
Angle-of-Attack/Stick Shaker System
.....................................
2-17
Instrument Markings . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
2-18
Autopilot . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
2-19
Honeywell Primus-1000 Flight Guidance System
............................
2-19
Standby Flight Instruments
............................................
2-19
Oxygen Mask . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
2-20
Supplemental Oxygen System . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
2-20
High Frequency (HF) Automatic Direction Finder (ADF) Systems
...............
2-20
Thrust Reversers
...................................................
2-20
Ground Idle Switch . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
2-21/2-22
Deice/Anti-ice Systems . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
2-21/2-22
RAT Indicator . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
2-21/2-22
FAA APPROVED
55BFM-08
Configuration AA
U.S.
2-1/2-2
SECTION II - OPERATING LIMITATIONS
MODEL 550
OPERATING LIMITATIONS
NOTICE
CERTIFICATION AND OPERATIONAL LIMITATIONS ARE CONDITIONS OF
THE TYPE AND AIRWORTHINESS CERTIFICATES AND MUST BE
COMPLIED WITH AT ALL TIMES AS REQUIRED BY LAW.
CERTIFICATION STATUS
This airplane is certified in accordance with FAR 25.
WEIGHT LIMITATIONS
Maximum Design Ramp Weight . . . . . . . . . . . . . . . .
Maximum Design Takeoff Weight . . . . . . . . . . . . . . .
Maximum Design Landing Weight
..............
Maximum Design Zero Fuel Weight
.............
15,000 Pounds (6,804 Kilograms)
14,800 Pounds (6,713 Kilograms)
13,500 Pounds (6,123 Kilograms)
11,300 Pounds (5,125 Kilograms)
Takeoff weight is limited by the most restrictive of the following requirements:
Maximum Certified Takeoff Weight
..........
14,800 Pounds (6,713 Kilograms)
Maximum Takeoff Weight Permitted by Climb
Requirements . . . . . . . . . . . . .
Refer to Section IV - Performance, Takeoff Data
Takeoff Field Length . . . . . . . . . .
Refer to Section IV - Performance, Takeoff Data
Landing weight is limited by the most restrictive of the following requirements:
Maximum Certified Landing Weight . . . . . . . . . .
13,500 Pounds (6,123 Kilograms)
Maximum Landing Weight Permitted by Climb Requirements
or Brake Energy Limits
. . Refer to Section IV - Performance, Approach and
Landing Data
Landing Distance . . . . . . . . Refer to Section IV - Performance, Approach and
Landing Data
CENTER-OF-GRAVITY LIMITS
Center-of-Gravity Moment Envelope
.........................
Refer to Figure 2-1
WEIGHT AND BALANCE DATA
The airplane must be operated in accordance with the approved loading schedule.
(Refer to Weight and Balance Data Sheet and Model 550 Citation Bravo Weight and
Balance Manual.)
POWERPLANT LIMITATIONS
Engine Type . . . . . . . . . . . . . . . . . .
Pratt and Whitney Canada Inc. PW530A Turbofan
Engine Operating Limits . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
Refer to Figure 2-2
Inter-Turbine Temperatures Limits
..........................
Refer to Figure 2-3
Engine Overspeed Limits . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
Refer to Figure 2-4
Takeoff/Go-Around Thrust Setting
..........................
Refer to Figure 4-9
Maximum Continuous Thrust Setting
.......................
Refer to Figure 4-10
FAA APPROVED
55BFM-03
Configuration AA
U.S.
2-3
SECTION II - OPERATING LIMITATIONS
MODEL 550
CENTER-OF-GRAVITY LIMITS ENVELOPE GRAPH
FORWARD LIMIT
AT 14,800 POUNDS
FS 280.97, 23.99
PERCENT MAC
AFT LIMIT AT
14,800 POUNDS
FS 285.85, 30.00
PERCENT MAC
MAXIMUM RAMP WEIGHT 15,000
POUNDS (6804 KILOGRAMS)
MAXIMUM TAKEOFF WEIGHT 14,800
POUNDS (6713 KILOGRAMS)
MAXIMUM LANDING WEIGHT 13,500
POUNDS (6123 KILOGRAMS)
MAXIMUM ZERO FUEL WEIGHT 11,300
POUNDS (5125 KILOGRAMS)
AFT LIMIT AT 8,670
POUNDS FS 285.85,
30.00 PERCENT MAC
FORWARD LIMIT
AT 9,147 POUNDS
FS 276.57, 18.54
PERCENT MAC
FORM NUMBER 1986, 16 September 1996
REVISED 23 April 1998
Figure 2-1
2-4
U.S.
Configuration AA
FAA APPROVED
55BFM-07
SECTION II - OPERATING LIMITATIONS
MODEL 550
ENGINE OPERATING LIMITS
OPERATING
CONDITIONS
OPERATING LIMITS
THRUST
SETTING
TIME LIMIT
(MINUTES)
ITT
TEMPERATURE °C
N2 %
TURBINE
RPM
N1 %
FAN RPM
OIL
PRESSURE
PSIG
(NOTE 2)
OIL
TEMPERATURE
°C
TAKEOFF
5
700
100
100
(NOTE 4)
45 TO 140
10 TO 121
MAXIMUM
CONTINUOUS
CONTINUOUS
700
100
100
(NOTE 4)
45 TO 140
10 TO 121
GROUND
IDLE
(NOTE 7)
CONTINUOUS
>>>
45.3 (MIN)
(NOTE 5)
>>>
20 (MIN)
–40 TO 121
FLIGHT
IDLE
(NOTE 7)
CONTINUOUS
580
49.4 (MIN)
(NOTE 6)
>>>
20 (MIN)
–40 TO 121
STARTING
N/A
740
FIGURE 2-3
>>>
>>>
(NOTE 3)
–40 (MIN)
TRANSIENT
20 SEC
740
FIGURE 2-3
102
102
0-250
0 TO 121
NOTES
1.
The maximum start limit is 740°C; refer to Figure 2-3.
2.
Normal oil pressures are 45 to 140 PSIG above 60% TURBINE RPM.
Oil pressures below 45 PSIG are undesirable and should be tolerated
only for the completion of the flight, preferably at reduced power setting.
Oil pressures below 20 PSIG are unsafe and require that either the
engine be shut down or a landing be made as soon as practical, using
the minimum power required to sustain flight.
3.
For starting, oil pressure may exceed 140 PSIG (not to exceed 250
PSIG) for up to 300 seconds.
4.
N1% Fan RPM is limited to either 100% N1 or the appropriate thrust
setting chart in Section IV (Standard Charts), whichever is less.
5.
Ground idle (LOW) turbine RPM is 45.3 minimum, pressurization bleed
air OFF, and oil temperature stabilized. Maximum ground idle (LOW)
turbine RPM should not exceed the HI setting.
6.
Flight idle (HI) turbine RPM is 49.4 +1.0%, -0%, pressurization bleed
air OFF and oil temperature stabilized.
7.
With pressurization bleed air ON, idle speeds may be up to 1.5% N2
less than noted above.
Figure 2-2
FAA APPROVED
55BFM-10
Configuration AA
U.S.
2-5
SECTION II - OPERATING LIMITATIONS
MODEL 550
INTER-TURBINE TEMPERATURE LIMITS
STARTING CONDITIONS ONLY
ALL CONDITIONS EXCEPT STARTING
C
C
B
B
A
A
AREA
AREA
A
B
AREA
C
- NO ACTION REQUIRED
- (1) DETERMINE CAUSE AND CORRECT
- (2) INSPECT HOT SECTION USING BORESCOPE
- (3) RECORD IN ENGINE LOG BOOK.
- RETURN ENGINE TO AN OVERHAUL FACILITY
6584C6049
6584C6050
Figure 2-3
2-6
U.S.
Configuration AA
FAA APPROVED
55BFM-00
SECTION II - OPERATING LIMITATIONS
MODEL 550
ENGINE OVERSPEED LIMITS
C
C
B
B
A
A
AREA
AREA
AREA
A
B
C
- NO ACTION REQUIRED
- RECORD IN ENGINE LOG BOOK
- RETURN ENGINE TO AN OVERHAUL FACILITY
6584C6051
Figure 2-4
ENGINE FAN INSPECTION
To assure accurate fan speed thrust indication, inspect the fan for damage prior to each
flight.
NOTE
Refer to the exterior inspection in the Normal Procedures Section of this
manual for engine duct and fan inspection.
BATTERY AND STARTER CYCLE LIMITATIONS
Starter Limitation
.......
Three engine starts per 30 minutes.
Three cycles of
operation with a 30-second rest period between cycles is
permitted.
NOTE
This limitation is independent of starter power source: i.e., battery,
generator assisted cross start, or external power unit.
(Continued Next Page)
I
FAA APPROVED
55BFM-08
Configuration AA
U.S.
2-7
SECTION II - OPERATING LIMITATIONS
MODEL 550
BATTERY AND STARTER CYCLE LIMITATIONS (Continued)
Battery Limitation
.......
Three engine starts per hour. Refer to notes 2 and 3.
NOTE
1.
2.
3.
4.
If battery limitation is exceeded, a deep cycle including a capacity
check must be accomplished to detect possible cell damage. Refer
to Chapter 24 of the Maintenance Manual for procedure.
Three generator assisted cross starts are equal to one battery start.
If an external power unit is used for start, no battery cycle is counted.
Use of an external power source with voltage in excess of 28 VDC or
current in excess of 1000 amps may damage the starter.
PROLONGED GROUND OPERATION
Continuous engine ground static operation up to and including five minutes at takeoff
thrust is limited to ambient temperatures not to exceed 39°C above ISA. (Refer to Figure
4-9).
Continuous ground operation of the starter-generator above 315 amperes is prohibited.
Limit ground operation of pitot/static heat to two minutes to preclude damage to the pitot/
static tubes and the angle-of-attack probe.
Timing for Avionics Ambient Temperature limits begins when all avionics are powered
on. (Refer to Figure 2-5.)
2-8
U.S.
Configuration AA
FAA APPROVED
55BFM-09
SECTION II - OPERATING LIMITATIONS
MODEL 550
AVIONICS AMBIENT TEMPERATURE LIMIT
NOTE
Timing for these limitations begins when all avionics are powered on.
Figure 2-5
I
FAA APPROVED
55BFM-08
Configuration AA
U.S.
2-9
SECTION II - OPERATING LIMITATIONS
MODEL 550
WINDSHIELD ICE PROTECTION FLUID
Use TT-I-735 isopropyl alcohol for windshield anti-ice.
HYDRAULIC FLUID
Use Skydrol 500B-4, or LD-4; or Hyjet, Hyjet IVA or IVA Plus only.
APPROVED OILS
The following oils are approved for use:
MOBIL JET OIL II
MOBIL JET OIL 254
CASTROL 5000
EXXON TURBO OIL 2380
ROYCO TURBINE OIL 500
ROYCO TURBINE OIL 560
AERO SHELL TURBINE OIL 500
AERO SHELL TURBINE OIL 560
In addition, oils listed for the engine in the latest revision to Pratt and Whitney Canada
Inc. Maintenance Manual P/N 30J1112 are approved.
CAUTION
WHEN CHANGING FROM AN EXISTING LUBRICANT FORMULATION TO
A
“THIRD
GENERATION”
LUBRICANT
FORMULATION
(AERO
SHELL/ROYCO TURBINE OIL 560 OR MOBIL JET 254) THE ENGINE
MANUFACTURER STRONGLY RECOMMENDS THAT SUCH A CHANGE
SHOULD ONLY BE MADE WHEN AN ENGINE IS NEW OR FRESHLY
OVERHAULED. FOR ADDITIONAL INFORMATION ON USE OF THIRD
GENERATION OILS, REFER TO THE ENGINE MANUFACTURER’S
PERTINENT OIL SERVICE BULLETINS.
Should oils of nonapproved brands or of different viscosities become intermixed, drain
and flush complete oil system and refill with an approved oil in accordance with Engine
Maintenance Manual instructions.
Minimum oil temperature for starting is –40°C.
I
2-10
U.S.
Configuration AA
FAA APPROVED
55BFM-08
SECTION II - OPERATING LIMITATIONS
MODEL 550
FUEL LIMITATIONS
The following fuels are approved for use in accordance with Figure 2-6.
COMMERCIAL KEROSENE JET A, JET A-1, JET B, JP-4, JP-5 and JP-8 per CPW
204 specification.
NOTE
JP-4, JP-5 and JP-8 type fuels have anti-icing additive preblended by the
refinery.
Refer to Section III, Normal Procedures for blending and
checking fuel anti-ice additives.
Boost Pumps - ON; when low fuel lights illuminate or at approximately 200 pounds or less
indicated fuel. To crossfeed, turn boost pump OFF on side opposite selected tank.
FUEL LIMITATIONS AND ADJUSTMENTS
FUEL GRADE
FUEL
SPECIFICATION
MINIMUM FUEL
TEMPERATURE
(TAKEOFF)
MAXIMUM FUEL
TEMPERATURE
(TAKEOFF)
JET A
ASTM-D1655
-35°C
+56°C
JET A-1
ASTM-D1655
-40°C
+56°C
JET B *
ASTM-D1655
-45°C
+56°C
JP-4 *
MIL-T-5624
-54°C
+56°C
JP-5
MIL-T-5624
-40°C
+56°C
JP-8
MIL-T-83133
-40°C
+56°C
* Refer to Figure 2-6A for altitude operating limitations with JET B or JP-4 fuel.
Figure 2-6
Maximum asymmetrical fuel differential for normal operations
..........
Maximum emergency asymmetrical fuel differential
..................
200 pounds
600 pounds
NOTE
Flight characteristics requirements were not demonstrated with unbalanced
fuel above 200 pounds.
UNUSABLE FUEL
Fuel remaining in the fuel tanks when the fuel quantity indicator reads zero is not usable
in flight.
FAA APPROVED
55BFM-10
Configuration AJ
U.S.
2-11
SECTION II - OPERATING LIMITATIONS
MODEL 550
JET B/JP-4 FUEL OPERATING LIMITATIONS
Figure 2-6A
SPEED LIMITATIONS
Maximum Operating Limit Speeds
0.700 Mach (Indicated)
MMO (Above 27,900 Feet) . . . . . . . . . . . . . . . . . . . . . . . . .
VMO (Between 8000 Feet and 27,900 Feet)
.......................
275 KIAS
VMO (Between Sea Level and 8000 Feet)
........................
260 KIAS
The maximum operating limit speeds may not be deliberately exceeded in any
regime of flight (climb, cruise or descent) unless a higher speed is authorized for
flight test or pilot training.
........................
Refer to Figure 2-7
Maximum Maneuvering Speeds - VA
Full application of rudder and aileron controls as well as maneuvers that involve
angles-of-attack near the stall should be confined to speeds below maximum
maneuvering speed.
Maximum Flap Extended Speed - VFE
Full Flaps - LAND Position (40°)
...............................
174 KIAS
Partial Flaps - T.O. & APPR Position (15°)
.......................
200 KIAS
.......................
260 KIAS
Maximum Landing Gear Extended Speed - VLE
.............
250 KIAS
Maximum Landing Gear Operating Speed - VLO (Extending)
- VLO (Retracting)
.............
200 KIAS
Maximum Speed Brake Operation Speed - VSB
........................
No Limit
. Refer to Section IV, Performance General
Minimum Control Speeds (VMCA and VMCG)
Autopilot Operation . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
275 KIAS or 0.700 MACH
I
2-12
U.S.
Configuration AJ
FAA APPROVED
55BFM-08
SECTION II - OPERATING LIMITATIONS
MODEL 550
FUEL LIMITATIONS
The following fuels are approved for use in accordance with Figure 2-6.
COMMERCIAL KEROSENE JET A, JET A-1, JP-5 and JP-8 per CPW 204
specification.
NOTE
JP-5 and JP-8 type fuels have anti-icing additive preblended by the refinery.
Refer to Section III, Normal Procedures for blending and checking fuel
anti-ice additives.
Boost Pumps - ON; when low fuel lights illuminate or at approximately 200 pounds or less
indicated fuel. To crossfeed, turn boost pump OFF on side opposite selected tank.
FUEL LIMITATIONS AND ADJUSTMENTS
FUEL GRADE
FUEL
SPECIFICATION
MINIMUM FUEL
TEMPERATURE
(TAKEOFF)
MAXIMUM FUEL
TEMPERATURE
(TAKEOFF)
JET A
ASTM-D1655
-35°C
+56°C
JET A-1
ASTM-D1655
-40°C
+56°C
JP-5
MIL-T-5624
-40°C
+56°C
JP-8
MIL-T-83133
-40°C
+56°C
Figure 2-6
Maximum asymmetrical fuel differential for normal operations
..........
Maximum emergency asymmetrical fuel differential
..................
200 pounds
600 pounds
NOTE
Flight characteristics requirements were not demonstrated with unbalanced
fuel above 200 pounds.
UNUSABLE FUEL
Fuel remaining in the fuel tanks when the fuel quantity indicator reads zero is not usable
in flight.
FAA APPROVED
55BFM-10
Configuration AK
U.S.
2-11.1
SECTION II - OPERATING LIMITATIONS
MODEL 550
SPEED LIMITATIONS
Maximum Operating Limit Speeds
MMO (Above 27,900 Feet) . . . . . . . . . . . . . . . . . . . . . . . . .
0.700 Mach (Indicated)
.......................
275 KIAS
VMO (Between 8000 Feet and 27,900 Feet)
VMO (Between Sea Level and 8000 Feet)
........................
260 KIAS
The maximum operating limit speeds may not be deliberately exceeded in any
regime of flight (climb, cruise or descent) unless a higher speed is authorized for
flight test or pilot training.
Maximum Maneuvering Speeds - VA
........................
Refer to Figure 2-7
Full application of rudder and aileron controls as well as maneuvers that involve
angles-of-attack near the stall should be confined to speeds below maximum
maneuvering speed.
Maximum Flap Extended Speed - VFE
Full Flaps - LAND Position (40°)
...............................
174 KIAS
Partial Flaps - T.O. & APPR Position (15°)
.......................
200 KIAS
.......................
260 KIAS
Maximum Landing Gear Extended Speed - VLE
Maximum Landing Gear Operating Speed - VLO (Extending)
.............
250 KIAS
- VLO (Retracting)
.............
200 KIAS
........................
No Limit
Maximum Speed Brake Operation Speed - VSB
Minimum Control Speeds (VMCA and VMCG)
. Refer to Section IV, Performance General
Autopilot Operation . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
275 KIAS or 0.700 MACH
I
2-12.1 U.S.
Configuration AK
FAA APPROVED
55BFM-08
SECTION II - OPERATING LIMITATIONS
MODEL 550
TAKEOFF AND LANDING OPERATIONAL LIMITS
Maximum Altitude Limit
.......................................
14,000 Feet
Maximum Tailwind Components
..................................
10 Knots
Maximum Ambient Temperature
. . . . . . . . . ISA +39°C (Refer to Figures 2-8 and 4-5)
Minimum Ambient Temperature
....................................
–54°C
Takeoffs and landings are limited to paved runways
Engine synchronizer must be OFF for takeoff and landing.
The autopilot and yaw damper must be OFF for takeoff and landing.
Goodyear part numbers 184F08-1 and BFGoodrich/Michelin part number 031-613-8, are
the only nose tires approved. Tire pressure for the nose gear is 120 PSIG (±5 PSIG,
unloaded); 125 PSIG (±5 PSIG, loaded).
Maximum Tire Ground Speed
...................................
All Vertical navigation systems must be OFF below 500 feet AGL.
165 Knots
Takeoffs and landings are limited to paved runways unless equipped with optional Gravel
Runway Modification, either factory installed or through appropriate Cessna Service
Bulletin.
The nosewheel must be in firm contact with the ground prior to extending speed brakes
and/or deploying thrust reversers.
ENROUTE OPERATIONAL LIMITS
Maximum Operating Altitude
...................................
45,000 Feet
Maximum Operating Altitude (Single Pressurization Source)
...........
43,000 Feet
Maximum Ambient Temperature
...........................
Refer to Figure 2-8
Minimum Ambient Temperature
............................
Refer to Figure 2-8
Generator Load . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
400 Amperes Up to 35,000 Feet
315 Amperes Above 35,000 Feet
OPERATIONS AUTHORIZED
This airplane is approved for day, night, VFR and IFR, and flight into known icing
conditions.
MINIMUM CREW
Minimum Flight Crew for All Operations
.....................
1 Pilot and 1 Copilot
LOAD FACTOR
In Flight
Flaps UP Position (0°)
. . . . –1.44 to +3.6 Gs at 14,800 Pounds (6,713 Kilograms)
Flaps T.O. & APPR to LAND Position
(15° To 40°) . . . . . . . . . . 0.0 to +2.0 Gs at 14,800 Pounds (6,713 Kilograms)
These accelerations limit the angle-of-bank in turns and limit the severity of
pull-up maneuvers.
Landing
Flaps - T.O. & APPR to LAND Position
(15° to 40°) . . . . . . . . . . . . . .
+3.38 Gs at 13,500 Pounds (6,123 Kilograms)
I
FAA APPROVED
55BFM-10
Configuration AA
U.S.
2-13
SECTION II - OPERATING LIMITATIONS
MODEL 550
MAXIMUM MANEUVERING SPEEDS
EXAMPLE:
Pressure Altitude - 25,000 FEET
Weight - 11,500 POUNDS (5216 Kilograms)
Maximum Maneuvering Speed - 176 KNOTS
6584C6054A
Figure 2-7
I
2-14
U.S.
Configuration AA
FAA APPROVED
55BFM-10
SECTION II - OPERATING LIMITATIONS
MODEL 550
TAKEOFF/LANDING/ENROUTE
TEMPERATURE LIMITATIONS
NOTE:
Ambient Air Temperature Limit is Indicated Ram Air Temperature (RAT)
adjusted for Ram rise (refer to Figure 4-2).
6585C1006A
Figure 2-8
I
FAA APPROVED
55BFM-10
Configuration AA
U.S.
2-15
SECTION II - OPERATING LIMITATIONS
MODEL 550
CABIN PRESSURIZATION LIMITATIONS
Normal Cabin Pressurization Limitations
. . . . . . . . 0.0 to 8.9 PSI, ±0.1 PSI Differential
Single pressurization source maximum operation altitude
..............
43,000 feet
MANEUVERS
No acrobatic maneuvers, including spins, are approved.
above 25,000 feet.
No intentional stalls permitted
PASSENGER SEAT POSITION
For all takeoffs and landings, seats must be fully upright and outboard. The seat just aft
of the emergency exit must be to the most aft position (toward rear of airplane). Seats
near the exit door must be positioned to allow access.
OPERATIONS IN SEVERE ICING CONDITIONS
WARNING
SEVERE ICING MAY RESULT FROM ENVIRONMENTAL CONDITIONS
OUTSIDE OF THOSE FOR WHICH THE AIRPLANE IS CERTIFIED.
FLIGHT IN FREEZING RAIN, FREEZING DRIZZLE, OR MIXED ICING
CONDITIONS (SUPERCOOLED LIQUID WATER AND ICE CRYSTALS)
MAY RESULT IN ICE BUILD-UP ON PROTECTED SURFACES
EXCEEDING THE CAPABILITY OF THE ICE PROTECTION SYSTEM, OR
MAY RESULT IN ICE FORMING AFT OF THE PROTECTED SURFACES.
THIS ICE MAY NOT SHED WHEN THE ICE PROTECTION SYSTEMS ARE
USED, AND MAY SERIOUSLY DEGRADE THE PERFORMANCE AND
CONTROLLABILITY OF THE AIRPLANE.
All wing icing inspection lights must be operative prior to flight into known or forecast
icing conditions at night.
NOTE
This supersedes relief provided by the Master Minimum Equipment List.
Severe icing conditions that exceed those for which the airplane is certificated shall be
determined by the following visual cues:
1. Unusually extensive ice accumulation on the airframe and windshield in areas not
normally observed to collect ice.
2. Accumulation of ice on the upper surface of the wing aft of the protected area.
If one or more of these visual cues exist:
1. Use of the autopilot is prohibited.
2. Immediately request priority handling from Air Traffic Control to facilitate a route or
altitude change to exit the icing conditions.
3. Leave flaps in current position, do not extend or retract.
4. Avoid abrupt and excessive maneuvering that may exacerbate control difficulties.
5. If unusual or uncommanded roll control movement is observed, reduce
angle-of-attack.
Since the autopilot, when installed and operating , may mask tactile cues that indicate
adverse changes in handling characteristics, use of the autopilot is prohibited when:
1. Unusual lateral trim is required while the airplane is in icing conditions.
2. Autopilot trim warnings are encountered while the airplane is in icing
conditions.
I
2-16
U.S.
Configuration AA
FAA APPROVED
55BFM-10
SECTION II - OPERATING LIMITATIONS
MODEL 550
AIRPLANE BATTERY
If the BATT O’TEMP light illuminates during ground operation, do not take off until after
the proper maintenance procedures have been accomplished.
ANGLE-OF-ATTACK/STICK SHAKER SYSTEM
The angle-of-attack (AOA) indicating system may be used as a reference system but
does not replace the airspeed display in the PFD as a primary instrument. The AOA
gage and Low Airspeed Awareness (LAA) indications must be verified in flight against
Airplane Flight Manual speeds prior to use as a reference.
The angle-of-attack system can be used as a reference for approach speed (1.3 VS1) at
all airplane weights and center-of-gravity locations at zero, takeoff/approach and landing
flap positions. 1.3 Vs1 is indicated by approximately .6 on the AOA gage and by the top
of the white tape on the pilot's and copilot's airspeed indicators.
If the stick shaker does not operate during the warning system test, it must be repaired
before flight.
I
FAA APPROVED
55BFM-08
Configuration AA
U.S.
2-17
SECTION II - OPERATING LIMITATIONS
MODEL 550
INSTRUMENT MARKINGS
Left and Right Oil Pressure Indicators
.......................
Red Line - 20 PSI
Yellow Band - 20 to 45 PSI
Green Band - 45 to 140 PSI
Red Triangle - 250 PSI
Left and Right Turbine RPM
Indicators . . . . . . . . . . . . . . . . . . .
Red Light and Flashing Readout - 100% RPM
Normal Operating - 45 to 100% RPM
Left and Right Oil Temperature Indicators
Airspeed Indicator
.....................
Red Line - 121°C
Green Band - 0 to 121°C
...................
Below 8000 feet MSL: Red Line - 260 KIAS
Between 8000 feet and 45,000 feet MSL: Red Line - 275 KIAS
- 0.700 Mach
Left and Right Inter-Turbine Temperature
Indicators . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
Red Triangle - 740°C
Red Line - 700°C
Green Band - 200 to 700°C
Left and Right Fan RPM Indicators
.........................
Red Line - 100.0%
(Refer to Section IV for Thrust Setting Limits)
Green Band - 20 to 100.0%
Left and Right Ammeter Indicators
Cabin Differential Pressure Indicator
Oxygen Pressure Indicator
........................
Red Line - 400 Amps
Yellow Arc - 315 to 400 Amperes
........................
Red Line - 8.9 PSI
Green Arc - 0.0 to 8.9 PSI
..............................
Red Line - 2000 PSI
Yellow Arc - 0.0 to 400 PSI
Green Arc - 1600 to 1800 PSI
Brake and Gear Pneumatic Pressure Indicator
(In Right Nose Compartment)
...............
Brake Hydraulic Accumulator Pressure
Indicator (In Left Nose Compartment)
I
2-18
U.S.
Wide Red Arc - Above 2050 PSI
Narrow Red Arc - 0.0 to 1600 PSI
Yellow Arc - 1600 to 1800 PSI
Wide Green Arc - 1800 to 2050 PSI
........
Light Green Arc - Static Pressure
Dark Green Arc - Pressurized Pressure
Configuration AY
FAA APPROVED
55BFM-10
SECTION II - OPERATING LIMITATIONS
MODEL 550
AIRPLANE BATTERY
If the BATT O’TEMP light illuminates during ground operation, do not take off until after
the proper maintenance procedures have been accomplished.
ANGLE-OF-ATTACK/STICK SHAKER SYSTEM
The angle-of-attack (AOA) indicating system may be used as a reference system but
does not replace the airspeed display in the PFD as a primary instrument. The AOA
gage and Low Airspeed Awareness (LAA) indications must be verified in flight against
Airplane Flight Manual speeds prior to use as a reference.
The angle-of-attack system can be used as a reference for approach speed (1.3 VS1) at
all airplane weights and center-of-gravity locations at zero, takeoff/approach and landing
flap positions. 1.3 Vs1 is indicated by approximately .6 on the AOA gage and by the top
of the white tape on the pilot's and copilot's airspeed indicators.
If the stick shaker does not operate during the warning system test, it must be repaired
before flight.
I
FAA APPROVED
55BFM-08
Configuration AA
U.S.
2-17
SECTION II - OPERATING LIMITATIONS
MODEL 550
INSTRUMENT MARKINGS
Left and Right Oil Pressure Indicators
.......................
Red Line - 20 PSI
Yellow Band - 20 to 45 PSI
Green Band - 45 to 140 PSI
Red Triangle - 250 PSI
Left and Right Turbine RPM
Indicators . . . . . . . . . . . . . . . . . . .
Red Light and Flashing Readout - 100% RPM
Normal Operating - 45 to 100% RPM
Left and Right Oil Temperature Indicators
Airspeed Indicator
.....................
Red Line - 121°C
Green Band - 0 to 121°C
...................
Below 8000 feet MSL: Red Line - 260 KIAS
Between 8000 feet and 45,000 feet MSL: Red Line - 275 KIAS
- 0.700 Mach
Left and Right Inter-Turbine Temperature
Indicators . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
Red Triangle - 740°C
Red Line - 700°C
Green Band - 200 to 700°C
Left and Right Fan RPM Indicators
.........................
Red Line - 100.0%
(Refer to Section IV for Thrust Setting Limits)
Green Band - 20 to 100.0%
Left and Right Ammeter Indicators
Cabin Differential Pressure Indicator
Oxygen Pressure Indicator
........................
Red Line - 400 Amps
Yellow Arc - 315 to 400 Amperes
........................
Red Line - 8.9 PSI
Green Arc - 0.0 to 8.9 PSI
..............................
Red Line - 2000 PSI
Yellow Arc - 0.0 to 400 PSI
Green Arc - 1600 to 1800 PSI
Brake and Gear Pneumatic Pressure Indicator
(In Right Nose Compartment)
...............
Brake Hydraulic Accumulator Pressure
Indicator (In Left Nose Compartment)
I
2-18.1 U.S.
Wide Red Arc - Above 2050 PSI
Narrow Red Arc - 0.0 to 1600 PSI
Yellow Arc - 1600 to 1800 PSI
Wide Green Arc - 1800 to 2050 PSI
........
Light Green Arc - Static Pressure
Dark Green Arc - Pressurized Pressure
Configuration BC
FAA APPROVED
55BFM-10
SECTION II - OPERATING LIMITATIONS
MODEL 550
AIRPLANE BATTERY
If the BATT O’TEMP light illuminates during ground operation, do not take off until after
the proper maintenance procedures have been accomplished.
ANGLE-OF-ATTACK/STICK SHAKER SYSTEM
The angle-of-attack (AOA) indicating system may be used as a reference system but
does not replace the airspeed display in the PFD as a primary instrument. The AOA
gage and Low Airspeed Awareness (LAA) indications must be verified in flight against
Airplane Flight Manual speeds prior to use as a reference.
The angle-of-attack system can be used as a reference for approach speed (1.3 VS1) at
all airplane weights and center-of-gravity locations at zero, takeoff/approach and landing
flap positions. 1.3 VS1 is indicated by approximately .6 on the AOA gage and by the top
of the white tape on the pilot's and copilot's airspeed indicators.
If the stick shaker does not operate during the warning system test, it must be repaired
before flight.
I
FAA APPROVED
55BFM-08
Configuration AA
U.S.
2-17
SECTION II - OPERATING LIMITATIONS
MODEL 550
INSTRUMENT MARKINGS
Oil Pressure Indicators
Scale Markings
..................................
Red Triangle 251 PSI
Red Line (MAX) f141 PSI
Green Band f45 to <141 PSI
Yellow Band >20 to <45 PSI
Red Line (MIN) e20 PSI
Analog Tape . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
Red f251 PSI
Red f141 PSI (f20 sec)
White f 45 to <141 PSI
Yellow > 20 to < 45 PSI
Red e20 PSI
NOTE
f In reversionary mode the oil pressure indication will be digital only and
the color of the digits will correspond to the scale range colors listed
above.
f Tape and digital readout (reversionary mode) will turn yellow or red if
outside normal operating limits.
f White analog tape or green digits (reversionary mode) represents green
band.
f During engine start and shutdown, the yellow and redline range changes
will be suppressed. The red triangle will still be active.
f For engine start, the oil pressure may exceed 140 PSI (not to exceed
250 PSI) for up to 300 seconds. The analog tape will turn red 20
seconds after the engine reaches idle speed if 140 PSI is still exceeded.
Turbine (N2) RPM Indicators
Digital Readout
...................................
Red f100.1% RPM
Green <100.1% RPM
Oil Temperature Indicators
Scale Markings
....................................
Red Line >121°C
Green Band f10 to e121°C
Analog Tape . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
Red >121°C
White f10 to e121°C
NOTE
f In reversionary mode the oil temperature indication will be digital only
and the color of the digits will correspond to the scale range colors listed
above.
f Tape and digital readout (reversionary mode) will turn red if outside
normal operating limits.
f White analog tape or green digits (reversionary mode) represents green
band.
(Continued Next Page)
I
2-18.2 U.S.
Configuration AZ
FAA APPROVED
55BFM-10
SECTION II - OPERATING LIMITATIONS
MODEL 550
INSTRUMENT MARKINGS (Continued)
Inter-Turbine Temperature Indicators
Engine Start:
Scale Markings
...................................
Red Triangle 740°C
Red Line f701°C
Analog Tape . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
Red f701°C
White f150°C to <701°C
Digital Readout . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
Red f701°C
Green f150°C to <701°C
NOTE
f Tape and digital readout will turn red if outside normal operating limits.
f Engine Running Red Line does not apply while ITT Start Limit (Red
Triangle) is displayed.
f White analog tape represents green band.
Engine Running:
Scale Markings
....................................
Red Line f701°C
Analog Tape . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
Red f701°C
White f150°C to <701°C
Digital Readout . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
Red f701°C
Green f150°C to <701°C
NOTE
f Tape and digital readout will turn red if outside normal operating limits.
f White analog tape represents green band.
Fan (N1) RPM Indicators (Refer to Section IV for Thrust Setting Limits)
Scale Markings
................................
Analog Tape . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
Digital Readout
....................................
Red Line 100.0% RPM
Red f100.1% RPM
White <100.1% RPM
Red f100.1% RPM
Green <100.1% RPM
NOTE
f Tape and digital readout will turn red if outside normal operating limits.
f White analog tape represents green band.
(Continued Next Page)
I
FAA APPROVED
55BFM-10
Configuration AZ
U.S. 2-18.2A
SECTION II - OPERATING LIMITATIONS
MODEL 550
INSTRUMENT MARKINGS (Continued)
Airspeed Indicator
...................
Below 8000 feet MSL: Red Line - 260 KIAS
Between 8000 feet and 43,000 feet MSL: Red Line - 275 KIAS
- 0.700 Mach
Left and Right Ammeter Indicators
Cabin Differential Pressure Indicator
Oxygen Pressure Indicator
........................
Red Line - 400 Amps
Yellow Arc - 315 to 400 Amperes
........................
Red Line - 8.9 PSI
Green Arc - 0.0 to 8.9 PSI
..............................
Red Line - 2000 PSI
Yellow Arc - 0.0 to 400 PSI
Green Arc - 1600 to 1800 PSI
Brake and Gear Pneumatic Pressure Indicator
(In Right Nose Compartment)
...............
Brake Hydraulic Accumulator Pressure
Indicator (In Left Nose Compartment)
I
2-18.2B
U.S.
Wide Red Arc - Above 2050 PSI
Narrow Red Arc - 0.0 to 1600 PSI
Yellow Arc - 1600 to 1800 PSI
Wide Green Arc - 1800 to 2050 PSI
........
Light Green Arc - Static Pressure
Dark Green Arc - Pressurized Pressure
Configuration AZ
FAA APPROVED
55BFM-10
SECTION II - OPERATING LIMITATIONS
MODEL 550
AIRPLANE BATTERY
If the BATT O’TEMP light illuminates during ground operation, do not take off until after
the proper maintenance procedures have been accomplished.
ANGLE-OF-ATTACK/STICK SHAKER SYSTEM
The angle-of-attack (AOA) indicating system may be used as a reference system but
does not replace the airspeed display in the PFD as a primary instrument. The AOA
gage and Low Airspeed Awareness (LAA) indications must be verified in flight against
Airplane Flight Manual speeds prior to use as a reference.
The angle-of-attack system can be used as a reference for approach speed (1.3
all airplane weights and center-of-gravity locations at zero, takeoff/approach and
flap positions. 1.3 VS1 is indicated by approximately .6 on the AOA gage and by
of the white tape on the pilot's and copilot's airspeed indicators.
VS1) at
landing
the top
If the stick shaker does not operate during the warning system test, it must be repaired
before flight.
I
FAA APPROVED
55BFM-08
Configuration AA
U.S.
2-17
SECTION II - OPERATING LIMITATIONS
MODEL 550
INSTRUMENT MARKINGS
Oil Pressure Indicators
Scale Markings
..................................
Red Triangle 251 PSI
Red Line (MAX) f141 PSI
Green Band f45 to <141 PSI
Yellow Band >20 to <45 PSI
Red Line (MIN) e20 PSI
Analog Tape . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
Red f251 PSI
Red f141 PSI (f20 sec)
White f 45 to <141 PSI
Yellow > 20 to < 45 PSI
Red e20 PSI
NOTE
f In reversionary mode the oil pressure indication will be digital only and
the color of the digits will correspond to the scale range colors listed
above.
f Tape and digital readout (reversionary mode) will turn yellow or red if
outside normal operating limits.
f White analog tape or green digits (reversionary mode) represents green
band.
f During engine start and shutdown, the yellow and redline range changes
will be suppressed. The red triangle will still be active.
f For engine start, the oil pressure may exceed 140 PSI (not to exceed
250 PSI) for up to 300 seconds. The analog tape will turn red 20
seconds after the engine reaches idle speed if 140 PSI is still exceeded.
Turbine (N2) RPM Indicators
Digital Readout
...................................
Red f100.1% RPM
Green <100.1% RPM
Oil Temperature Indicators
Scale Markings
....................................
Red Line >121°C
Green Band f10 to e121°C
Analog Tape . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
Red >121°C
White f10 to e121°C
NOTE
f In reversionary mode the oil temperature indication will be digital only
and the color of the digits will correspond to the scale range colors listed
above.
f Tape and digital readout (reversionary mode) will turn red if outside
normal operating limits.
f White analog tape or green digits (reversionary mode) represents green
band.
(Continued Next Page)
I
2-18.3 U.S.
Configuration BD
FAA APPROVED
55BFM-10
SECTION II - OPERATING LIMITATIONS
MODEL 550
INSTRUMENT MARKINGS (Continued)
Inter-Turbine Temperature Indicators
Engine Start:
Scale Markings
...................................
Red Triangle 740°C
Red Line f701°C
Analog Tape . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
Red f701°C
White f150°C to <701°C
Digital Readout . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
Red f701°C
Green f150°C to <701°C
NOTE
f Tape and digital readout will turn red if outside normal operating limits.
f Engine Running Red Line does not apply while ITT Start Limit (Red
Triangle) is displayed.
f White analog tape represents green band.
Engine Running:
Scale Markings
....................................
Red Line f701°C
Analog Tape . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
Red f701°C
White f150°C to <701°C
Digital Readout . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
Red f701°C
Green f150°C to <701°C
NOTE
f Tape and digital readout will turn red if outside normal operating limits.
f White analog tape represents green band.
Fan (N1) RPM Indicators (Refer to Section IV for Thrust Setting Limits)
Scale Markings
................................
Analog Tape . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
Digital Readout
....................................
Red Line 100.0% RPM
Red f100.1% RPM
White <100.1% RPM
Red f100.1% RPM
Green <100.1% RPM
NOTE
f Tape and digital readout will turn red if outside normal operating limits.
f White analog tape represents green band.
(Continued Next Page)
I
FAA APPROVED
55BFM-10
Configuration BD
U.S. 2-18.3A
SECTION II - OPERATING LIMITATIONS
MODEL 550
INSTRUMENT MARKINGS (Continued)
Airspeed Indicator
...................
Below 8000 feet MSL: Red Line - 260 KIAS
Between 8000 feet and 43,000 feet MSL: Red Line - 275 KIAS
- 0.700 Mach
Left and Right Ammeter Indicators
Cabin Differential Pressure Indicator
Oxygen Pressure Indicator
........................
Red Line - 400 Amps
Yellow Arc - 315 to 400 Amperes
........................
Red Line - 8.9 PSI
Green Arc - 0.0 to 8.9 PSI
..............................
Red Line - 2000 PSI
Yellow Arc - 0.0 to 400 PSI
Green Arc - 1600 to 1800 PSI
Brake and Gear Pneumatic Pressure Indicator
(In Right Nose Compartment)
...............
Brake Hydraulic Accumulator Pressure
Indicator (In Left Nose Compartment)
I
2-18.3B
U.S.
Wide Red Arc - Above 2050 PSI
Narrow Red Arc - 0.0 to 1600 PSI
Yellow Arc - 1600 to 1800 PSI
Wide Green Arc - 1800 to 2050 PSI
........
Light Green Arc - Static Pressure
Dark Green Arc - Pressurized Pressure
Configuration BD
FAA APPROVED
55BFM-10
SECTION II - OPERATING LIMITATIONS
MODEL 550
AUTOPILOT
1.
2.
3.
One pilot must remain in his seat with the seat belt fastened during all autopilot
operations.
Autopilot operation is prohibited if any comparison monitor annunciator illuminates in
flight.
Minimum autopilot use height for enroute is 1000 feet AGL. Minimum autopilot use
height for approaches is 180 feet AGL.
HONEYWELL PRIMUS-1000 FLIGHT GUIDANCE SYSTEM
1.
2.
3.
4.
5.
6.
7.
8.
9.
10.
The Honeywell P-1000 Integrated Flight Control System Pilot’s Manual P/N
A28-1146-109-00 revision 00 or later revision for the Cessna 550 Citation Bravo,
must be immediately available to the flight crew.
Both flight director and autopilot coupled Category II approaches are not approved
using the Honeywell P-1000 EFIS displays.
EFIS ground operation with the pilot’s NOSE AVN FAN FAIL annunciator light
illuminated is limited to 30 minutes or until either PFD HOT or MFD HOT annunciator
light illuminates, whichever occurs first.
Dispatch is prohibited if the PFD HOT, MFD HOT or IC HOT annunciator light is
illuminated.
Dispatch is prohibited following a flight during which the PFD HOT, MFD HOT or IC
HOT annunciator light was illuminated, until the condition is identified and corrected.
The pilot’s and copilot's PFDs must be installed and operational in the normal
(non-reversionary) mode for takeoff.
The P-1000 system must be verified to be operational by a satisfactory preflight test
as contained in the NORMAL procedures.
Dual PFD SG reversion to the MFD is prohibited.
Flight director and autopilot coupled VOR approaches without DME are not
approved.
When NAV mode is engaged for enroute navigation, and VOR is the source, HDG
mode must be engaged prior to changing the active VOR frequency. After positive
acquisition of the new VOR frequency and course, reselect NAV mode and verify
capture and tracking of the new course.
STANDBY FLIGHT INSTRUMENTS
1.
2.
A satisfactory preflight test must be accomplished on the standby gyro system.
The standby flight instruments, ATT, ALT/ASI and HSI must be functioning prior to
takeoff.
FAA APPROVED
55BFM-10
Configuration AD
U.S.
2-19
SECTION II - OPERATING LIMITATIONS
MODEL 550
OXYGEN MASK
The pressure demand sweep-on oxygen mask must be properly stowed to qualify as a
quick-donning oxygen mask.
NOTE
Headsets, eyeglasses or hats worn by the crew may interfere with the
quick-donning capabilities of the oxygen masks.
SUPPLEMENTAL OXYGEN SYSTEM
Continuous use of the supplemental oxygen is prohibited above:
25,000 feet when passengers are using dropout oxygen masks.
37,000 feet with crew only using pressure demand sweep-on oxygen masks.
HIGH FREQUENCY (HF) AUTOMATIC DIRECTION FINDER (ADF)
SYSTEMS
The ADF bearing information may be erratic when keying the HF transmitter. Should this
occur, disregard the ADF bearing during periods of transmission.
THRUST REVERSERS
Reverse thrust power must be reduced to the idle reverse detent position at 60 KIAS on
landing roll.
Maximum reverse thrust setting is limited to 82.3% N1 for ambient temperatures at or
above -18°C, and 76% N1 for ambient temperautres below -18°C.
Maximum allowable thrust reverser deployed time is 15 minutes in any one-hour period.
Engine static ground operation is limited to idle power (if thrust reversers are deployed).
Use of thrust reversers is prohibited during touch and go landings.
The thrust reverser(s) must be verified to be operational by the Before Takeoff test in
Section III Normal Procedures.
Use of thrust reversers is prohibited at speeds greater than 115 KIAS. Nose down
column pressure is required with thrust reversers deployed at speeds greater than 60
KIAS.
The use of thrust reversers to back the airplane is prohibited.
2-20
U.S.
Configuration AA
FAA APPROVED
55BFM-10
SECTION II - OPERATING LIMITATIONS
MODEL 550
AUTOPILOT
1.
2.
3.
One pilot must remain in his seat with the seat belt fastened during all autopilot
operations.
Autopilot operation is prohibited if any comparison monitor annunciator illuminates in
flight.
Minimum autopilot use height for enroute is 1000 feet AGL. Minimum autopilot use
height for approaches is 180 feet AGL.
HONEYWELL PRIMUS-1000 FLIGHT GUIDANCE SYSTEM
1.
2.
3.
4.
5.
6.
7.
8.
9.
10.
The Honeywell P-1000 Integrated Flight Control System Pilot’s Manual P/N
A28-1146-109-00 revision 00 or later revision for the Cessna 550 Citation Bravo,
must be immediately available to the flight crew.
Both flight director and autopilot coupled Category II approaches are not approved
using the Honeywell P-1000 EFIS displays.
EFIS ground operation with the pilot’s NOSE AVN FAN FAIL annunciator light
illuminated is limited to 30 minutes or until either PFD HOT or MFD HOT annunciator
light illuminates, whichever occurs first.
Dispatch is prohibited if the PFD HOT, MFD HOT or IC HOT annunciator light is
illuminated.
Dispatch is prohibited following a flight during which the PFD HOT, MFD HOT or IC
HOT annunciator light was illuminated, until the condition is identified and corrected.
The pilot’s and copilot's PFDs must be installed and operational in the normal
(non-reversionary) mode for takeoff.
The P-1000 system must be verified to be operational by a satisfactory preflight test
as contained in the NORMAL procedures.
Dual PFD SG reversion to the MFD is prohibited.
Flight director and autopilot coupled VOR approaches without DME are not
approved.
When NAV mode is engaged for enroute navigation, and VOR is the source, HDG
mode must be engaged prior to changing the active VOR frequency. After positive
acquisition of the new VOR frequency and course, reselect NAV mode and verify
capture and tracking of the new course.
STANDBY FLIGHT INSTRUMENTS
1.
2.
3.
A satisfactory preflight test must be accomplished on the standby gyro system.
The standby flight instruments, ATT, ALT/ASI and HSI must be functioning prior to
takeoff.
The Meggitt standby flight display is not approved for instrument approaches.
FAA APPROVED
55BFM-10
Configuration AE
U.S.
2-19.1
SECTION II - OPERATING LIMITATIONS
MODEL 550
OXYGEN MASK
The pressure demand sweep-on oxygen mask must be properly stowed to qualify as a
quick-donning oxygen mask.
NOTE
Headsets, eyeglasses or hats worn by the crew may interfere with the
quick-donning capabilities of the oxygen masks.
SUPPLEMENTAL OXYGEN SYSTEM
Continuous use of the supplemental oxygen is prohibited above:
25,000 feet when passengers are using dropout oxygen masks.
37,000 feet with crew only using pressure demand sweep-on oxygen masks.
HIGH FREQUENCY (HF) AUTOMATIC DIRECTION FINDER (ADF)
SYSTEMS
The ADF bearing information may be erratic when keying the HF transmitter. Should this
occur, disregard the ADF bearing during periods of transmission.
THRUST REVERSERS
Reverse thrust power must be reduced to the idle reverse detent position at 60 KIAS on
landing roll.
Maximum reverse thrust setting is limited to 82.3% N1 for ambient temperatures at or
above -18°C, and 76% N1 for ambient temperautres below -18°C.
Maximum allowable thrust reverser deployed time is 15 minutes in any one-hour period.
Engine static ground operation is limited to idle power (if thrust reversers are deployed).
Use of thrust reversers is prohibited during touch and go landings.
The thrust reverser(s) must be verified to be operational by the Before Takeoff test in
Section III Normal Procedures.
Use of thrust reversers is prohibited at speeds greater than 115 KIAS. Nose down
column pressure is required with thrust reversers deployed at speeds greater than 60
KIAS.
The use of thrust reversers to back the airplane is prohibited.
2-20
U.S.
Configuration AA
FAA APPROVED
55BFM-10
SECTION II - OPERATING LIMITATIONS
MODEL 550
AUTOPILOT
1.
2.
3.
One pilot must remain in his seat with the seat belt fastened during all autopilot
operations.
Autopilot operation is prohibited if any comparison monitor annunciator illuminates in
flight.
Minimum autopilot use height for enroute operation is 1000 feet AGL. Minimum
autopilot use height for approaches is 180 feet AGL.
HONEYWELL PRIMUS-1000 FLIGHT GUIDANCE SYSTEM
1.
2.
3.
4.
5.
6.
7.
8.
9.
10.
The Honeywell P-1000 Integrated Flight Control System Pilot’s Manual P/N
A28-1146-109-00 revision 00 or later revision for the Cessna 550 Citation Bravo,
must be immediately available to the flight crew.
Both flight director and autopilot coupled Category II approaches are not approved
using the Honeywell P-1000 EFIS displays.
EFIS ground operation with the pilot’s NOSE AVN FAN FAIL annunciator light
illuminated is limited to 30 minutes or until either PFD HOT or MFD HOT annunciator
light illuminates, whichever occurs first.
Dispatch is prohibited if the PFD HOT, MFD HOT or IC HOT annunciator light is
illuminated.
Dispatch is prohibited following a flight during which the PFD HOT, MFD HOT or IC
HOT annunciator light was illuminated, until the condition is identified and corrected.
The pilot’s and copilot's PFDs must be installed and operational in the normal
(non-reversionary) mode for takeoff.
The P-1000 system must be verified to be operational by a satisfactory preflight test
as contained in the NORMAL procedures.
Dual PFD SG reversion to the MFD is prohibited.
Flight director and autopilot coupled VOR approaches without DME are not
approved.
When NAV mode is engaged for enroute navigation, and VOR is the source, HDG
mode must be engaged prior to changing the active VOR frequency. After positive
acquisition of the new VOR frequency and course, reselect NAV mode and verify
capture and tracking of the new course.
STANDBY FLIGHT INSTRUMENTS
1.
2.
3.
A satisfactory preflight test must be accomplished on the standby gyro system.
The standby flight instruments, ATT, ALT/ASI and HSI must be functioning prior to
takeoff.
The standby airspeed limitations listed on the ALT/KIAS placard apply only to the
standby indicators and should be used only when both pilot's and copilot's PFD
airspeed tapes are unreliable or inoperative.
FAA APPROVED
55BFM-10
Configuration AC
U.S.
2-19.2
SECTION II - OPERATING LIMITATIONS
MODEL 550
OXYGEN MASK
The pressure demand sweep-on oxygen mask must be properly stowed to qualify as a
quick-donning oxygen mask.
NOTE
Headsets, eyeglasses or hats worn by the crew may interfere with the
quick-donning capabilities of the oxygen masks.
SUPPLEMENTAL OXYGEN SYSTEM
Continuous use of the supplemental oxygen is prohibited above:
25,000 feet when passengers are using dropout oxygen masks.
37,000 feet with crew only using pressure demand sweep-on oxygen masks.
HIGH FREQUENCY (HF) AUTOMATIC DIRECTION FINDER (ADF)
SYSTEMS
The ADF bearing information may be erratic when keying the HF transmitter. Should this
occur, disregard the ADF bearing during periods of transmission.
THRUST REVERSERS
Reverse thrust power must be reduced to the idle reverse detent position at 60 KIAS on
landing roll.
Maximum reverse thrust setting is limited to 82.3% N1 for ambient temperatures at or
above -18°C, and 76% N1 for ambient temperautres below -18°C.
Maximum allowable thrust reverser deployed time is 15 minutes in any one-hour period.
Engine static ground operation is limited to idle power (if thrust reversers are deployed).
Use of thrust reversers is prohibited during touch and go landings.
The thrust reverser(s) must be verified to be operational by the Before Takeoff test in
Section III Normal Procedures.
Use of thrust reversers is prohibited at speeds greater than 115 KIAS. Nose down
column pressure is required with thrust reversers deployed at speeds greater than 60
KIAS.
The use of thrust reversers to back the airplane is prohibited.
2-20
U.S.
Configuration AA
FAA APPROVED
55BFM-10
SECTION II - OPERATING LIMITATIONS
MODEL 550
AUTOPILOT
1.
2.
3.
One pilot must remain in his seat with the seat belt fastened during all autopilot
operations.
Autopilot operation is prohibited if any comparison monitor annunciator illuminates in
flight.
Minimum autopilot use height for enroute is 1000 feet AGL. Minimum autopilot use
height for approaches is 180 feet AGL.
HONEYWELL PRIMUS-1000 FLIGHT GUIDANCE SYSTEM
1.
2.
3.
4.
5.
6.
7.
8.
9.
10.
The Honeywell P-1000 Integrated Flight Control System Pilot’s Manual P/N
A28-1146-109-00 revision 00 or later revision for the Cessna 550 Citation Bravo,
must be immediately available to the flight crew.
Both flight director and autopilot coupled Category II approaches are not approved
using the Honeywell P-1000 EFIS displays.
EFIS ground operation with the pilot’s NOSE AVN FAN FAIL annunciator light
illuminated is limited to 30 minutes or until either PFD HOT or MFD HOT annunciator
light illuminates, whichever occurs first.
Dispatch is prohibited if the PFD HOT, MFD HOT or IC HOT annunciator light is
illuminated.
Dispatch is prohibited following a flight during which the PFD HOT, MFD HOT or IC
HOT annunciator light was illuminated, until the condition is identified and corrected.
The pilot’s and copilot's PFDs must be installed and operational in the normal
(non-reversionary) mode for takeoff.
The P-1000 system must be verified to be operational by a satisfactory preflight test
as contained in the NORMAL procedures.
Dual PFD SG reversion to the MFD is prohibited.
Flight director and autopilot coupled VOR approaches without DME are not
approved.
When NAV mode is engaged for enroute navigation, and VOR is the source, HDG
mode must be engaged prior to changing the active VOR frequency. After positive
acquisition of the new VOR frequency and course, reselect NAV mode and verify
capture and tracking of the new course.
STANDBY FLIGHT INSTRUMENTS
1.
2.
A satisfactory preflight test must be accomplished on the standby gyro system.
The standby flight instruments, ATT, ALT/ASI and HSI must be functioning prior to
takeoff.
FAA APPROVED
55BFM-10
Configuration BB
U.S.
2-19.3
SECTION II - OPERATING LIMITATIONS
MODEL 550
OXYGEN MASK
The pressure demand sweep-on oxygen mask must be properly stowed to qualify as a
quick-donning oxygen mask.
NOTE
Headsets, eyeglasses or hats worn by the crew may interfere with the
quick-donning capabilities of the oxygen masks.
SUPPLEMENTAL OXYGEN SYSTEM
Continuous use of the supplemental oxygen is prohibited above:
25,000 feet when passengers are using dropout oxygen masks.
37,000 feet with crew only using pressure demand sweep-on oxygen masks.
HIGH FREQUENCY (HF) AUTOMATIC DIRECTION FINDER (ADF)
SYSTEMS
The ADF bearing information may be erratic when keying the HF transmitter. Should this
occur, disregard the ADF bearing during periods of transmission.
THRUST REVERSERS
Reverse thrust power must be reduced to the idle reverse detent position at 60 KIAS on
landing roll.
Maximum reverse thrust setting is limited to 82.3% N1 for ambient temperatures at or
above -18°C, and 76% N1 for ambient temperautres below -18°C.
Maximum allowable thrust reverser deployed time is 15 minutes in any one-hour period.
Engine static ground operation is limited to idle power (if thrust reversers are deployed).
Use of thrust reversers is prohibited during touch and go landings.
The thrust reverser(s) must be verified to be operational by the Before Takeoff test in
Section III Normal Procedures.
Use of thrust reversers is prohibited at speeds greater than 115 KIAS. Nose down
column pressure is required with thrust reversers deployed at speeds greater than 60
KIAS.
The use of thrust reversers to back the airplane is prohibited.
2-20
U.S.
Configuration AA
FAA APPROVED
55BFM-10
SECTION II - OPERATING LIMITATIONS
MODEL 550
GROUND IDLE SWITCH
The ground idle switch must be in HIGH position when conducting touch and go
landings.
The ground idle switch must be in HIGH position when making a generator assisted
cross start from an operating engine.
DEICE/ANTI-ICE SYSTEMS
Operation of the deice boots below -40°C is prohibited.
All anti-ice systems must be ON when operating in visible moisture and the indicated
RAT is +10°C or lower.
Limit ground operation of pitot static heat to 2 minutes ON with 2 minutes OFF between
cycles to preclude system damage.
RAT INDICATOR
RAT indications on the ground are unreliable. Use reported surface temperature from
the appropriate ground station for determining takeoff thrust setting.
I
FAA APPROVED
55BFM-08
Configuration AA
U.S. 2-21/2-22