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MACH TRIM
The Mach trim function makes allowances for the rearward shift of the aerodynamic center of pressure as the Mach number increases. Without correction, this shift in the center of pressure decreases longitudinal stability.
The horizontal stabilizer trim control unit automatically adjusts the stabilizer as a function of the Mach number when the autopilot is not engaged.
The Mach trim system, using Mach information from the air data computers (ADCs), varies the angle of incidence of the stabilizer by commanding movement of the horizontal stabilizer actuator.
When Mach trim is active, increasing speed from a trimmed condition results in Mach trim inputting slight nose up trim, increasing the aircraft’s natural speed stability. Likewise, decreasing aircraft speed from a trimmed condition results in Mach trim inputting slight nose down trim.
The Mach trim system is continuously monitored and any fault detected is displayed on the EICAS display.
Sep 13/2004 Flight Crew Operating Manual Volume 2 REV 1 CSP 100-6
10-02-03 SECONDARY FLIGHT CONTROLS (Cont) AILERON TRIM SCHEMATIC
(POSITION TO EICAS
TAB
FLIGHT CONTROLS PAGE)
LEGEND
ELECTRICAL INPUT MEC
H
AN
I
C
AL
I
N
PU
T
CABLE INPUT TRIM MOTOR
CFO1001002_011
Volume 2 Flight Crew Operating Manual CSP 100-6
10-02-04
Sep 13/2004 REV 1
SECONDARY FLIGHT CONTROLS (Cont) HORIZONTAL STABILIZER TRIM SCHEMATIC
PILOT MASTER TRIM COPILOT MASTER DISCONNECT SWITCH
SWITCHES DISCONNECT SWITCH
MIC ID ID MIC
PILOT
COPILOT MASTER
MASTER DISC RELAY
DISC RELAY
STAB
TR
I
M
PRI
LEFT RIGHT
RUD
OFF
MAIN ESS
R
SEC
28 VDC 28 VDC
ST
A
B
PR
I
OF
F
SEC
HSTECU LEFT MAIN
PRIMARY CHANNEL
RIGHT ESS 28 VDC
28 VDC
COMMAND
SECONDARY
HIGH HIGHCHANNEL
STALL
MONITOR
POWER POWER
PUSHER
BREAKER BREAKER
OFF
PRIMARY
SECONDARY ENGAGE
MCU
ENGAGE RELAY
CHANNEL 1
RELAY
CHANNEL 2
HORZONTAL
TO STABILIZER
FGP
BRAKE 1 BRAKE 3
BRAKE 2
MOTOR
LVDT 1
LVDT 2
BRAKE 4
MOTOR
COMM
COMM
HSTA GEARBOX
HORIZONTAL
NO BACK
STABILIZER
TRIM
ACTUATOR
FO1001002_002
Sep 13/2004 Flight Crew Operating Manual Volume 2 REV 1 CSP 100-6
10-02-05 SECONDARY FLIGHT CONTROLS (Cont)
FLAPS
The single-slotted Fowler flaps are electronically controlled and operated by a hydraulic motor in the flap power unit. There are two hydraulic systems. Under normal conditions, the flaps will operate with the right hydraulic system. When ALTN FLAPS is selected ON, flaps will operate from the left hydraulic system and a FLAPS ALT PRESS lamp will illuminate in green on the EICAS. FLAPS RATE LOW (A) CAS will illuminate if the flap control unit is controlling the system at a lower than nominal speed in order to reduce the hydraulic flow. This is the case if either the pressure switches of the hy-draulic system indicate that the engine driven pump for the main system is not working, or the alternate hydraulic supply is selected. Normal flap extension from 0 to 30 does not exceed 20 seconds with the right engine-driven hydraulic pumps operating. However, time extends up to 60-70 seconds while lowering flaps from 0 to 20 in flight when using ALTN FLAPS or when using the right DC hydraulic pump. Each flap panel, one on each wing, has three safe-life flap tracks and is driven by two screw jack actuators. A stainless steel shaft transfers power from the hydraulic motor to each flap actuator. The flap control lever is located on the center pedestal and is recessed to prevent inadvertent operation.
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