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the switch must be moved in order for the trim to move. If either side of either switch is detected
separately for more than 3 seconds, electric pitch trim is disabled and PTRM will be annunciated on
both PFDs. Pitch trim will remain disabled until all commands return to the inactive state.
The pilot’s electric elevator trim switch has priority over the copilot switch and will operate the trim,
interrupting and overriding actuation of the copilot’s switch. In the event of a trim runaway, the AP/
TRIM DISC button on either control wheel will stop the trim motion as long as the button is held
down. Momentarily arming the pitch trim system (LEFT side of switch) will disconnect the autopilot
but leave the yaw damper engaged. Electric trim is provided as a function of the autopilot. Therefore,
if the autopilot is inoperative, electric trim will not be available. Power is provided from the AFCS
circuit breaker on the left circuit breaker panel.
AILERON TRIM
Aileron trim is controlled by a knob on the aft side of the pedestal. To operate, the knob must be
pushed in and rotated in the desired direction. Aileron trim position is indicated on the EICAS display
as an analog pointer. If display reversion is selected, aileron trim position is not displayed. In the
event of an aileron trim runaway, the AP/TRIM DISC button on either control wheel will stop the trim
motion as long as the button is held down. Power is provided from the AILERON TRIM circuit
breaker on the left circuit breaker panel.
RUDDER TRIM
Rudder trim is controlled by a split switch on the aft side of the pedestal. To operate, both portions of
the switch must be moved in the desired direction. Rudder trim position is indicated on the EICAS
display as an analog pointer. If display reversion is selected, rudder trim position is not displayed. In
the event of a rudder trim runaway, the AP/TRIM DISC button on either control wheel will stop the
trim motion as long as the button is held down. Power is provided from the RUDDER TRIM circuit
breaker on the left circuit breaker panel.
510FM-07 AA 3-177
SECTION III - OPERATING PROCEDURES MODEL 510
NORMAL PROCEDURES
FAA APPROVED
U.S. Configuration
WARNING SYSTEMS TEST
The rotary test selector switch is located on the upper right side of the instrument panel and offers a
means of testing visual and aural warning systems. A light above the test selector switch illuminates
when the test selector switch is in any position other than OFF.
POSITION INDICATIONS
FIRE WARN
• Red L ENG FIRE and R ENG FIRE switches illuminate.
• Master Warning Lights illuminate.
LANDING
GEAR
• 3 green gear downlock lights illuminate.
• Red gear UNLOCK light illuminates.
• Gear warning horn sounds. Alternates between pilot and copilot speakers.
CABIN ALT
• Red CABIN ALT message appears.
• Amber CABIN ALT message appears.
STALL
• Amber STALL WARN FAIL message appears.
• Stall warning tone sounds and alternates between pilot and copilot speakers.
• Amber STALL WARN HTR message appears.
• White STALL WARN HI message appears.
FLAPS
• The flap indicator on the MFD is replaced with a red “X” for 3 seconds.
• Amber FLAPS FAIL message appears.
• Amber STALL WARN FAIL message appears for 3 seconds.
OVER
SPEED
• The overspeed warning tone sounds and alternates between pilot and copilot
speakers.
ANTI SKID
• Amber ANTISKID FAIL message appears for 6 seconds.
• White NO TIRE SPINDOWN message appears for 6 seconds.
ANNU
• MASTER CAUTION illuminates and cannot be cancelled.
• MASTER WARNING illuminates and cannot be cancelled.
• Autopilot Mode Control Panel indicators illuminate.
• Audio panel indicators illuminate.
• Red “DUMP” illuminates on Cabin Dump switch.
• Test audio tone sounds.
3-178.1 AG 510FM-07
MODEL 510 SECTION IV - PERFORMANCE
GENERAL
FAA APPROVED
Configuration U.S.
PERFORMANCE
TABLE OF CONTENTS
Page
GENERAL. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 4-3/4-4
STANDARD CHARTS. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 4-15/4-16
TAKEOFF . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 4-37/4-38
APPROACH AND LANDING . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 4-227/4-228
510FM-05 AA 4-1/4-2
　
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本文鏈接地址：Citation Mustang airplane flight manual 1(122)