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BRAKE PEDAL
(Brake-by-Wire)
Malfunctioning brake pedal
C. Advisory (Blue) CAS Messages
Advisory CAS messages associated with the brake system are:
CAS Message Cause or Meaning
BRAKE MAINT REQ’D
(Brake-by-Wire)
(For S/N 1000-1213 with ASC 190, 266, or 296)
If message is displayed after landing gear retraction and
extinguishes approximately five (5) seconds later, the auto
spin-down feature has failed
BRAKE MAINT REQ’D
(Hydro-Mechanical
Analog Braking)
(For S/N 1214 and subsequent)
If message is displayed during takeoff, landing ground roll,
or during flight with the landing gear extended, a wheel
speed sensor (WSS) miscompare lasting more than five
(5) seconds has been detected
5. Built-in Test (BIT) - HMAB System
The Anti-skid Test pushbutton, shown in Figure 11, is used to initiate a system BIT
test from the cockpit. Pressing the pushbutton performs the same function as
pressing the System Test button on the face of the Skid Control Box (ECU) in the
avionics equipment rack, illustrated in Figure 17. For a valid test, the following
indications should appear.
• The Anti-skid Test switch illuminates IN TEST
• Amber ANTISKID FAIL and BRAKE FAIL messages appear on EICAS
• Blue BRAKE MAINT REQ’D message appears on EICAS
• System Test light illuminates on the Skid Control Box (ECU)
6. Built-in Test Equipment (BITE) – Brake-by Wire System
Pressing the BRAKE TEST pushbutton, shown in Figure 18 will initiate a brake
system test. During the test, the following indications are displayed.
• Amber ANTISKID FAIL, BRAKE FAIL, and BRAKE PEDAL FAIL messages
appear on EICAS
• Blue BRAKE MAINT REQ’D message appears on the EICAS
• The pushbutton illuminates IN TEST
• The BITE indicator illuminates on the ECU
If one (or more) of the indications fails to appear during the BITE test, a fault is
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indicated. Faults may be isolated by rotating the selector on the front of the ECU.
See the illustration in Figure 19
NOTE:
BIT or BITE tests should be performed at taxi speeds
less than 10 knots. For the duration of the BIT or BITE
tests, normal anti-skid operation is interrupted.
7. Limitations:
Takeoff is prohibited with BRAKE FAIL or BRAKE PEDAL message displayed.
Takeoff is permitted with Anti-Skid system inoperative, provided Ground Spoilers
are operative, 20° flaps are used, and the Cowl and Wing Anti-Icing systems are
not used.
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ABS Brake Components
Figure 12
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Dunlop Brake Components
Figure 13
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HMAB Hydraulic Schematic
Figure 14
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2A-32-50: Nose Wheel Steering System
1. General Description:
The aircraft has a steerable nose wheel operated by an electronic and hydraulic
steer-by-wire system using inputs from a control wheel mounted on the pilot side
console or inputs from rudder pedal position. Hydraulic pressure from the
Combined powers nose wheel steering.The nose wheel may be turned 78° (± 2°)
left or right of center with the cockpit control wheel, or 7° (±1°) using only rudder
pedal input. Control wheel and rudder pedal inputs are additive, but total nose
wheel displacement from center is limited to 80° (±2°) by mechanical stops. Nose
wheel steering must be selected ON with the guarded system switch next to the
control wheel. The system switch and other system components and controls are
Brake-by-Wire Hydraulic Schematic
Figure 15
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2A-32-00 PRODUCTION AIRCRAFT SYSTEMS
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Brake Temperature
Monitoring System Panel
(SPZ-8000 Aircraft)
Figure 16
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Skid Control Box (ECU)
for HMAB Anti-skid
Figure 17
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Brake Test Pushbutton for
Brake-by-Wire System
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湾流4操作手册 Gulfstream IV Operating Manual 2(91)
