曝光台 注意防骗
网曝天猫店富美金盛家居专营店坑蒙拐骗欺诈消费者
Maximum Flap Extended Speed - VFE
TAKEOFF / APPROACH Detent (15°) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 185 KIAS
LAND Position (30°) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 150 KIAS
Maximum Landing Gear Extended Speed - VLE. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 250 KIAS
Maximum Landing Gear Operating Speed - VLO (Extending). . . . . . . . . . . . . . . . . . . . . . . . 250 KIAS
Maximum Landing Gear Operating Speed - VLO (Retracting) . . . . . . . . . . . . . . . . . . . . . . . 185 KIAS
Maximum Speed Brake Operation Speed - VSB . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . No Limit
Maximum Autopilot Operation Speed . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 250 KIAS or 0.63 Mach
Maximum Tire Ground Speed. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .160 Knots
Minimum Speed in RVSM Airspace . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 110 KIAS
Minimum Speed For Sustained Flight In Icing Conditions
(except takeoff, approach and landing). . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 160 KIAS
Minimum Control Speeds (VMCA and VMCG) . . . . . . . .Refer to Section IV, Performance, GENERAL
2-16 AA 510FM-07
MODEL 510 SECTION II - OPERATING LIMITATIONS
FAA APPROVED
Configuration U.S.
MAXIMUM OPERATING MANEUVERING AIRSPEEDS
Figure 2-12*
510FM-04 AA 2-17
SECTION II - OPERATING LIMITATIONS MODEL 510
FAA APPROVED
U.S. Configuration
TAKEOFF AND LANDING OPERATIONAL LIMITS
Maximum Altitude Limit. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 14,000 Feet
Maximum Tailwind Component. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .10 Knots
Maximum/Minimum Ambient Temperature . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .Refer to Figure 2-13
Maximum Demonstrated Crosswind Component (Not Limiting). . . . . . . . . . . . . . . . . . . . . . .25 Knots
Minimum Fuel Quantity per Wing for Takeoff . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 200 Pounds
The maximum approved fuel imbalance is 200 pounds; however, controllability for safe return and
landing has been demonstrated with an emergency fuel imbalance of 600 pounds.
A satisfactory preflight check of each of the following systems must be accomplished in accordance
with Section Ill, Normal Procedures, prior to takeoff:
• Stall Warning
• Flight Controls
• Flaps
• Standby Instruments
Electric elevator trim system preflight test must be accomplished in accordance with Section III,
Normal Procedures, prior to takeoff.
The autopilot and yaw damper must be disengaged for takeoff and landing.
Dispatch with a ENG CTRL SYS L-R message displayed is prohibited.
Takeoff and landings are limited to paved runway surfaces.
Refer to Section VII for takeoff and landing distance corrections applicable to runway surfaces other
than dry.
Dispatch with antiskid inoperative is prohibited if the forecast conditions for the destination approach
and landing will require the use of STALL WARNING-HIGH (Flap TO/APR) landing data.
Use of flaps in the LAND position is prohibited with ice adhering anywhere on the outside of the
airplane. STALL WARNING-HIGH landing performance data in Section IV is predicated on the use of
Flaps TO/APR for landing.
Speed brakes must be retracted prior to 50-feet AGL before landing (unless required by AFM
procedure).
Cabin must be depressurized for landing.
Takeoff is prohibited with the following forms of contamination:
1. With frost adhering to the following critical areas:
a. Wing Leading Edge
b. Upper Wing Surface
c. Windshield
(Continued Next Page)
2-18 AA 510FM-07
MODEL 510 SECTION II - OPERATING LIMITATIONS
FAA APPROVED
Configuration U.S.
TAKEOFF AND LANDING OPERATIONAL LIMITS (Continued)
2. With ice, snow or slush adhering to the following critical areas:
a. Wing Leading Edge and Upper Wing Surface
b. Flight Control Surfaces including all hinge gaps
c. Horizontal Stabilizer
d. Vertical Stabilizer
e. Engine Inlets
f. Top of Engine Pylons
g. Top of Fuselage
h. Windshield
i. All Static Ports
j. Stall Warning Vane
k. Upper surface of nose forward of the windshield
3. A visual and tactile (hand-on-surface) check of the wing leading edge and the wing upper
surface must be performed to make sure that the wing is free from frost, ice, snow, or slush
中国航空网 www.aero.cn
航空翻译 www.aviation.cn
本文链接地址：
Citation Mustang airplane flight manual 1(12)
