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VMO .............................................................................................. 330 KIAS
MMO
- with Mach trim operative and Autopilot disengaged.......0.81 MI
- with Mach trim operative or inoperative and
Autopilot engaged
- 26,800 to 36,000 feet ..............................................................0.81 MI
- 36,000 to 40,000 feet .................................................... 0.81-0.80 MI
- Above 40,000 feet..................................................................0.80 MI
- with Mach trim inoperative and Autopilot disengaged
- 23,400 to 42,000 feet ..................................................... 0.76-0.78 MI
- Above 42,000 feet..................................................................0.78 MI
Standby Instruments
VMO .............................................................................................. 325 KIAS
MMO ...................................................................................................0.75 MI
MANEUVERING SPEED VA
Avoid rapid and large alternating control inputs,
especially in combinations with large changes in
pitch, roll or yaw as they may cause structural failure
at any speed, including below VA.
Refer to applicable figure entitled AIRSPEED/MACH LIMITS, this section,
for VA. Maneuvers involving full application of rudder and aileron
controls, as well as maneuvers that involve angles of attack near
stall should be confined to speeds below VA.
MAXIMUM LANDING GEAR OPERATING SPEED VLO.............200 KIAS
MAXIMUM LANDING GEAR EXTENDED SPEED VLE ................260 KIAS
MAXIMUM FLAP EXTENDED SPEED VFE
- Flaps 8° ............................................................................... 250 KIAS
- Flaps 20° ............................................................................. 200 KIAS
- Flaps 40° ............................................................................. 150 KIAS
CAUTION
Limitation
1 6 FM 132
FAA Approved 9-24-2004
AIRSPEED/MACH LIMITS (Cont)
MINIMUM CONTROL SPEED AIR VMCA
VMCA is a function of altitude and temperature. During flight tests, the
aircraft was controllable down to stall speed. The speed shown is the
minimum demonstrated speed corrected for maximum thrust effect
with rudder boost on or off.
VMCA
- Flaps 8° ............................................................................... 103 KIAS
- Flaps 20° ............................................................................. 101 KIAS
MINIMUM CONTROL SPEED GROUND VMCG
VMCG is a function of altitude and temperature. The speed shown is a
maximum, which occurs at maximum thrust conditions.
VMCG
- Rudder Boost On, APR On .............................................. 102 KIAS
- Rudder Boost On, APR Off .............................................. 100 KIAS
Rudder Boost OFF APR On............... ... 125 KIAS
Rudder Boost OFF, APR Off .................................. 123 KIAS
MINIMUM CONTROL SPEED LANDING VMCL
VMCL is a function of altitude and temperature. The speed shown is a
maximum, which occurs at maximum thrust conditions.
VMCL
- Flaps 8° ............................................................................... 105 KIAS
- Flaps 40° ............................................................................... 98 KIAS
TAKEOFF DECISION SPEED V1
Refer to applicable figure entitled TAKEOFF SPEEDS, Section V.
ROTATION SPEED VR
Refer to applicable figure entitled TAKEOFF SPEEDS, Section V.
TAKEOFF SAFETY SPEED V2
Refer to applicable figure entitled TAKEOFF SPEEDS, Section V.
Limitations
FM-132 1-7
FAA Approved 9-24-2004
Change 1
OPERATIONAL LIMITS/REQUIREMENTS
TAKEOFF
Maximum Pressure Altitude.......................................................14,000 feet
Ambient Temperature ........................ Refer to Figure 1-3 and Section V
Tailwind Component
- Aircraft not modified by SB 40-72-01 .................................. 10 knots
- Aircraft modified by SB 40-72-01:
- 12,000 feet and below........................................................ 10 knots
- Above 12,000 feet................................................................. 0 knots
Runway Conditions:
Takeoff is limited to paved runways.
Runway water............................................................3/4 inch (19 mm)
HI FLOW..................................................................................................OFF
Fuel Load ............................. Wings balanced within 200 pounds (91 kg)
EICAS.........................................................................SUMRY or FLT PAGE
　
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