G550 Limits Flashcards
Max Speed, use of tiller steering
60 Kts
Min. Control Speed Ground (Vmcg) at 15,000 feet
86 Kts
Min Control Speed Ground (Vmcg) at Sea Level
107 Kts
Min. Control Speed Landing (Vmcl)
110 KCAS
Min. Control Speed Air (Vmca)
112 KCAS
Min. speed in icing conditions
160 KCAS
Max Speed Flaps 39°
170 KCAS / .60 MT
Max speed alternate extension of landing gear handle blow down
(emergency gear handle ops)
175 KCAS
Max tire speed
195.5 KCAS
Max speed with deployed Thrust Reverser
200 KCAS
Maneuvering Speed (Va)
206 KCAS
Yaw Damp Inop greater than 20k ft
(Minimum speed)
Min 210 KCAS
Max Speed Flaps 20°
220 KCAS / .60MT
Max Gear Extension Speed (Vlo)
225 Knots / 0.70 Mach
Turb. Penetration Speed (Vb) less than 10k ft
240 KCAS
Max Gear Extended Operation (Vle)
250 Knots/ 0.70 MT
Max Speed Flaps 10°
250 KCAS / .60MT
Yaw Damp Inop below 10,000 ft
Max 250 KCAS
Max KCAS with Yaw Damp Inop above 10,000 ft
Max 260 KCAS / 0.80 mach
Turb. Penetration Speed (Vb) above 10,000 ft
270 Kts / .80 MT
Vmo below 8,000’ __________
Vmo above 8,000’ __________
Vmo below 8,000’ 300 KCAS
Vmo above 8,000’ 340 KCAS
Maximum Mach with Trim Inoperative
0.80 mach
Max Speeds at FL
Max Speed FL 290-320: 0.85 mach
Max Speed FL 320-440: 0.885 mach
Max Speed FL 440-510: 0.86 mach
Max altitude, APU use during “bleeds off” T/O:
5,000 ft
Max Airport Take-Off Elevation
14,500 ft
Max altitude Flaps 39° or Gear Extended
20,000 ft
Max alt. possible for engine suction fuel feed (without cross flow opened and fuel pump turned on)
20,000 ft
Max altitude wind-milling engine airstart
25,000 ft
Max altitude Flaps 10° or Flaps 20°
25,000 ft
Max altitude APU-assisted engine airstart
30,000 ft
(Engine limit is 25k)
Max altitude Anti-Ice AUTO mode works
35,000 ft
Max altitude APU guaranteed start
39,000 ft
Internal baggage door open, above 40,000’
5 min limit
Max altitude APU may start
43,000 ft
Internal baggage door open, with only one ECS Pack operational, no entry above _________
45,000 ft
Max altitude yaw damp inop
45,000 ft
Max altitude APU operations
45,000 ft
Max altitude single pack operations
48,000 ft
Max Operational altitude
51,000 ft
Max Fuel Imbalance, during takeoff
1,000 lbs
Max Fuel Imbalance, in-flight
2,000 lbs
Max Fuel capacity
41,300 lbs
Max Zero Fuel Weight
54,500 lbs
Max Landing Weight
75,300 lbs
Max Takeoff Weight
91,000 lbs
Max Ramp Weight
91,400 lbs
Min Engine Fuel Temperature
-40° C
Min Fuel Tank Temperature
-37° C
Min Oil Temp for starting engine
-30° C
Cowl Anti-Ice ON (w/ visible moisture)
10° C or below
Min cabin temp before cockpit system pwr
18°C/65°F
Min Oil Temp for T/O Power
20° C
Fuel Tank Temperature Limits
Min -37° C
Max 54° C
Max Engine Fuel Temperature
140° C
Max Residual Engine Temp (TGT) prior to ground start
150° C
Max Engine Oil Temperature
160° C
APU Max Start Temperature
1,050° C
Max tailwind component during takeoff
10kts
Max tailwind component during engine start _______
For acceleration to takeoff with crosswinds above ____ kts, the fan speed is limited to less than 66 % LP RPM until a forward speed of _______ kts has been reached. Above ______ kts forward speed, a slam acceleration to T/O power is required. Add _______ft to the required field length when using this procedure.
20kts x4
600 feet
Max tailwind component during engine start 20kts
For acceleration to takeoff with crosswinds above 20 kts, the fan speed is limited to less than 66 % LP RPM until a forward speed of 20 kts has been reached. Above 20 kts forward speed, a slam acceleration to T/O power is required. Add 600 ft to the required field length when using this procedure.
Max demonstrated crosswind landing
28kts
Max crosswind component during engine start
30kts
Gust Procedure: For winds greater than ___ kts, add ____ the steady state wind plus the entire gust to the VREF speed, up to a maximum addition of ____ kts.
Gust Procedure: For winds greater than 10 kts, add 1/2 the steady state wind plus the entire gust to the VREF
speed, up to a maximum addition of 20 kts.
In tailwinds greater than ____ kts, the direction of rotation of LP may be initially reversed.
In tailwinds greater than 10 kts, the direction of rotation of LP may be initially reversed.
If so, the fuel control switch should not be set to run until the LP indication confirms positive rotation.
RADAR Min operational distance from personnel
49 ft
RADAR Min operational distance from refueling ops
300 ft
Max cabin press diff (taxi / takeoff / landing) ____ PSID
Red Cabin Differential CAS / Max press diff _____ PSID
Max cabin press diff (taxi / takeoff / landing) 0.3 PSID
Red Cabin Differential CAS / Max press diff 10.48 PSID
Cabin Pressure LOW CAS Message
Cabin alt. for oxygen mask deployment
14,750 ft +/- 250
G550 APU Start Limitations
When powered by batteries, ___ consecutive start cycles followed by ___ hour cool down.
When powered by an external DC power source, a max of __ start attempts with a ___ minute cool down between each attempt. Allow ___ hour cool down after 3rd attempt.
When powered by batteries, 3 consecutive start cycles
followed by 1 hour cool down.
When powered by an external DC power source, a max of 3 start attempts with a 15 minute cool down between each attempt. Allow 1 hour cool down after 3rd attempt.
G550 Engine Start Limitations
__ start cycles with a maximum of __ minutes per cycle.
Delay 15 seconds between start cycles. After __ start cycles, delay use of the starter for at least ___ minutes.
3 start cycles with a maximum of 3 minutes per cycle.
Delay 15 seconds between start cycles. After 3 start cycles, delay use of the starter for at least 15 minutes.
Starter may be reengaged at HP RPM speeds up to starter cut out of ___% HP RPM
Starter may be reengaged at HP RPM speeds up to starter cut out of 42% HP RPM
Rotor Shaft Bow If the engine has been shutdown for more than ___ minutes but less than __ hours:
Crank engine at max HP RPM for 30 seconds before selecting fuel cntrl to run. It is not unusual for peak EVM value above the alert level (0.80) to be seen during start.
Alternatively, the engine may be cranked for a minimum of ___ seconds at max cranking HP RPM, not more than ___ minutes before a normal engine start.
Rotor Shaft Bow If the engine has been shutdown for more than 20 minutes but less than 5 hours:
Crank engine at max HP RPM for 30 seconds before selecting fuel cntrl to run. It is not unusual for peak EVM value above the alert level (0.80) to be seen during start.
Alternatively, the engine may be cranked for a minimum of 60 seconds at max cranking HP RPM, not more than 20 minutes before a normal engine start.
G550 Time Limitations
Min time, engine idle before shutdown ___ min
Min time, engine idle before takeoff ___ min
Oil QTY checked between __ & ___ min after shutdown
G550 Time Limitations
Min time, engine idle before shutdown 3 min
Min time, engine idle before takeoff 5 min
Oil QTY checked between 5 and 30 min after shutdown
G550 Distance / Length Limitations
Min taxi strip width capable of 180° turn ___ feet
Length of plane:
Wingspan of plane:
Height of tail above the ground:
G550 Distance / Length Limitations
Min taxi strip width capable of 180° turn 62 feet
Length: 96 feet 5 inches
Wingspan: 93 feet 6 inches
Height: 25 feet 11 inches
G550 Flight Load Limitations
Flaps 0° _____g to ______g
Flaps 10° or Flaps 20° ____ to ___g (up to Max T/O Wt)
Flaps 39° __ to ____g (below 75,300 lbs)
Flaps 39° __ to ____g (above 75,300 lbs)
G550 Flight Load Limitations
Flaps 0° -1g to 2.5g
Flaps 10° or Flaps 20° 0 to 2.0g (up to Max T/O Weight)
Flaps 39° 0 to 2.0g (below 75,300 lbs)
Flaps 39° 0 to 1.5g (above 75,300 lbs)
TGT Limits
Maximum Ground Starting TGT: 700° Max Relighting (Airstart): 850°
Max Continuous: 860°
Max Takeoff: 900° (5min DE, 10 min SE)
Max Overspeed: 905° (20 seconds)
LP% RPM Limits
Max Continuous: 101%
Max Takeoff: 101.1% (5min DE, 10 min SE)
Max Overspeed: 101.5% (20 seconds)
Max reverse: 70% (30 seconds)
HP% RPM Limits
Max Continuous: 98.9%
Max Takeoff: 99.6% (5min DE, 10 min SE)
Max Overspeed: 99.8% (20 seconds)
