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15. Gust Lock . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . INSTALL
16. Rudder Gust Lock. . . . . . . . . . . . . . . . . . . . . . . . . . . LOCK (unless airplane will be towed)
CAUTION
Towing the airplane with the Rudder Gust Lock engaged will damage the
nosewheel steering mechanism.
17. Engine Oil Level . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CHECK (10 minutes after shutdown)
3-150 AA 510FM-07
MODEL 510 SECTION III - OPERATING PROCEDURES
NORMAL PROCEDURES
FAA APPROVED
Configuration U.S.
QUICK TURN AROUND
1. Exterior Inspection . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . COMPLETE
2. Circuit Breakers . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . IN
3. L/R GEN Switches . . . . . . . . . . . . . . . . . GEN (OFF if ground power is to be used for start)
4. STBY INST Switch . . . . . . . . . . . . . . . . . . . . . . BATT TEST (5 seconds) then STBY INST
5. Ground Power Unit (if desired) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CONNECTED
6. BATT Switch . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . BATT
7. PARKING BRAKE. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . SET
8. AVN PWR Switch . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . ON
9. ATIS/Clearance. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . AS REQUIRED
10. Rotary TEST Switch . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . WARNING SYSTEMS CHECK
11. Fuel Quantity and Balance . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CHECK
12. Pilot, Passenger, Cargo, and Fuel Weights . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . ENTER
13. Avionics Flight Plan (if desired). . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . ENTER
14. AVN PWR Switch . . . . . . . . . . . . . . . . . . . . . . . . . . OFF (if ground power is not connected)
15. WING/STAB Deice System (if required) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CHECK
a. Pitot-Static Switch. . . . . . . . . . . . . . . . . . . . . . . . . . . RESET STALL WARN then OFF
16. LANDING GEAR Handle . . . . . . . . . . . DOWN; THREE GREEN LIGHTS/NO RED LIGHT
17. OXYGEN SUPPLY Handle . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . PUSHED IN
18. All other switches . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OFF or NORM
19. THROTTLES . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CUTOFF
20. Refer to Normal Procedures, BEFORE STARTING ENGINES.
TURBULENT AIR PENETRATION
Flight through severe turbulence should be avoided if possible. The following procedures are
recommended for flight in severe turbulence.
1. Airspeed . . . . . . . . . . . . . . . . . . . . . APPROXIMATELY 160 KIAS (do not chase airspeed)
NOTE
The igniters may come on automatically in turbulence.
2. Maintain a constant attitude without chasing the altitude. Avoid sudden large control
movements.
3. Operation of autopilot is recommended in basic modes only (ROL and PIT only).
4. PAX SAFETY Switch . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . PAX SAFETY
510FM-07 AA 3-151
SECTION III - OPERATING PROCEDURES MODEL 510
NORMAL PROCEDURES
FAA APPROVED
U.S. Configuration
FLIGHT INTO ICING
Flight into known icing is the intentional flight into icing conditions that are known to exist by either
visual observation or pilot weather report information. Icing conditions exist any time the indicated
RAT is +10°C or below, and visible moisture in any form is present.
Engine and windshield anti-ice should be selected ON anytime the indicated RAT is +10°C or below,
and visible moisture in any form is present. WING/STAB DEICE should be selected as soon as ice is
observed to accrue anywhere on the airplane. If ice remains on the airplane during approach and
landing, maximum flap extension is limited to the TO/APR position.
Ice accumulations significantly alter the shape of airfoils and increase the weight of the airplane.
Flight with ice accumulated on the airplane will increase stall speeds and alter the speeds for
optimum performance. Flight at high angle-of-attack (low airspeed) can result in ice building on the
underside of the wings and the horizontal stabilizer aft of areas protected by the deice boots.
　
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本文鏈接地址：Citation Mustang airplane flight manual 1(102)