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R
W
D
AIL TRIM
NL
RUD TRIM
NR
P604_10_016
DN DN DN
- GEAR - - FLAPS -
STAB
- TRIM -
20
NU
ND
4.0
RUDDER
AIL
LWD RWD
NL NR
P604_10_017
Aileron
Trim
Gauge
Rudder
Trim
Gauge
FLIGHT CONTROLS
10-14 For Training Purposes Only
Sept 04
P I LOT T R A I N I N G GU I D E
Flaps
Two double-slotted flap panels (inboard and outboard) are externally hinged on the
trailing edge of each wing. A flap lever, located on the center pedestal, sends a signal
to the Flap Control Unit (FCU) to initiate flap movement. When the FCU commands a
change in flap position, the flap brakes are released, and two AC-powered motors
mounted on a flap gearbox are energized. The gearbox rotates flex shafts which move
the flap ballscrew actuators, extending or retracting the flaps. When the desired setting
is reached, the motors are deenergized and the flap brakes are applied. The flaps are
mechanically interconnected for simultaneous movement of the inboard and outboard
flap sections.
The flaps may be set to one of four positions: 0, 20, 30, and 45 degrees. A flap gate is
incorporated within the flap lever 20-degree detent. This minimizes the possibility of
accidental flap retraction to 0 degrees during a go-around procedure. Flap position is
displayed on the EICAS Primary Page and the Flight Controls Synoptic Page in both
analog (colored bar) and digital formats. The indications on the EICAS Primary Page
are in view only if the flaps are extended, or if the landing gear is not up and locked.
Flap position and condition is continuously monitored by the Flap Control Unit. In the
event of failure or overheat of a single flap motor (indicated by a FLAPS MOTOR
OVHT status EICAS message) the remaining motor can operate the flaps at half
speed. Complete failure of the flap system, including an asymmetry of > 2.75°, will
generate a FLAPS FAIL caution EICAS message as well an amber symbol on the
EICAS FLIGHT CONTROLS synoptic page.
If the flaps are not set at 20° with the aircraft in takeoff mode, a CONFIG FLAPS
warning EICAS message and aural warning will be displayed/sounded.
Maximum Flap Speeds
To prevent damage, maximum indicated airspeeds for each flap
setting must not be exceeded. These are placarded on the
instrument panel. (See Airplane Flight Manual for current
airspeeds.)
Flap Setting Maximum Airspeed
20 degrees 231 kias
30 degrees 197 kias
45 degrees 189 kias
NOTE
FLIGHT CONTROLS
For Training Purposes Only
Sept 04
10-15
P I LOT T R A I N I N G GU I D E
Flap Schematic
Figure 10-9
FLAP
CONTROL
UNIT
MOTOR
RELAYS
MOTOR
RELAYS
FLAP
POSITION
DIFF.
CLUTCH
GEAR
MOTOR 1
& BRAKE
MOTOR 2
& BRAKE
TORQUE
LIMITER
TORQUE
LIMITER
OVHT OVHT
AC BUS 1 AC BUS 2
RPM RPM
DET. BRAKE
DET. BRAKE
DC BUS 1 DC BUS 2
FLAP MOTOR OVHT FLAP MOTOR OVHT
FLAP FAIL
CONFIG FLAPS
INPUTS
FROM
OTHER
SYSTEMS
MASTER
WARNING
“CONFIG
FLAPS”
EICAS
DCU
EICAS EICAS
DCU DCU
EICAS FLIGHT CONTROLS SYNOPTIC PAGE
(SECONDARY DISPLAY)
Flap
Position
Indicator
P604_10_005
0
20
30
45
0
20
30
45
FLAPS
FLIGHT CONTROLS
AIL
RUDDER
ELEV ELEV
AIL
FLAPS MOTOR OVERHEAT
FLAPS 30
FLIGHT CONTROLS
10-16 For Training Purposes Only
Sept 04
P I LOT T R A I N I N G GU I D E
Flight Spoilers
These provide lift dumping and speed control when airborne, and reduce ground roll
during landing and rejected takeoffs.
Each flight spoiler panel is hydraulically operated by two identical PCUs, powered by
hydraulic systems 1 and 2. The flight spoilers are mechanically controlled by the flight
spoiler control lever on the center pedestal and can be deployed up to a maximum of
40° in flight or on the ground. The flight spoiler control lever travels through nine
detents, allowing the pilot to select variable amounts of flight spoiler deployment.
Spoiler position is indicated on both the EICAS Status and FLIGHT CONTROLS
synoptic pages, using white arrows which move upward toward lines, indicating
relative extension (for the flight spoilers only), and full extension (for both flight and
ground spoilers). When the flight and ground spoilers are fully retracted, all EICAS
spoiler icons and position arrows disappear.
　
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