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and would otherwise encounter a sudden full brake application.
Speed signals from the WSSs are used to provide a ground spoiler activation
signal in the event of a malfunction in the nutcracker switches. Automatic ground
spoiler activation is provided on landing when the system is armed, flaps are
extended to a least 22° and both nutcracker switches are in the ground (weighton-
wheels) mode. If a nutcracker switch fails to transition to the ground mode on
landing , then speed signals from the WSSs can prompt activation. When at least
one wheel on each strut spins up to approximately fifty-six (56) knots, the ground
spoilers are activated. The spoiler activation signal provided by the WSSs is
preserved until the wheels slow to approximately thirty-nine (39) to twenty-two
(22) knots, at which time the electrical signal generated by the WSSs is too weak
to maintain automatic ground spoiler deployment and the spoilers will stow.
For aircraft S/N 1000 - 1143 with ASC 166/166A incorporated, and S/N 1144 and
subsequent, a circuit similar to the ground spoiler activation circuit is installed for
activation of the thrust reversers. If WSSs on at least one wheel of each strut
indicate a rotation speed of fifty-seven (57) knots, thrust reversers may be
deployed even if the nutcracker system has not transferred to the ground (weighton-
wheels) mode.
2A-32-45: Brake Temperature Monitoring System (BTMS)
1. General Description
The temperature of each main landing gear brake is monitored by a probe
incorporated into one of the brake assembly bolts on each wheel. The probes are
resistance type devices (RTDs) that vary resistance to electrical current with
temperature at a predetermined rate. Brake temperatures sensed by the probes
are transmitted for view on cockpit displays. Electrical power for the temperature
probes and monitoring circuits is provided by 28V DC through the BTMS circuit
breaker at position D-10 on the CPO.
Temperature readings and overheat warning displays are presented in two
different formats. For aircraft with SPZ 8000 DAFCS, a Brake Temperature
Monitoring System (BTMS) panel, is installed in the cockpit center console
beginning with aircraft S/N 1156, and available for installation in prior aircraft S/Ns
as ASC 167. For aircraft with SPZ 8400 DAFCS, temperature readings and
overheat warnings are displayed on the EICAS.
2. Brake Temperature Monitoring System (SPZ-8000 AIRCRAFT)
A. Description
A Brake Temperature Monitor System (BTMS) panel is installed in aircraft
S/Ns 1156 through 1252 (except S/N 1236) and those aircraft S/Ns 1000-
1155 retrofitted with ASC 137. The BTMS panel, shown in Figure 16, is
located on the cockpit center console (location optional) and contains a
temperature gage with readout selector, an overheat light, and a test
switch. The temperature readout selector is normally positioned to ALL. In
this position, the highest temperature of the four main landing gear brakes
is displayed on the temperature gage. The selector is rotated to monitor the
temperature of each individual brake. If temperature limits for the type of
brake installed are exceeded, the OVHT light on the BTMS panel
OPERATING MANUAL
PRODUCTION AIRCRAFT SYSTEMS 2A-32-00
Page 39
January 31/02
Revision 6
illuminates. If the OVHT light on the BTMS panel is illuminated, rotating the
temperature display selector through the brake positions will determine
which brake(s) is overheating. On aircraft S/Ns 1156-1167, a temperature
limit exceedance also prompts the illumination of the master caution lights,
and an illumination of the BRAKE TEMP light installed above the pilot
primary flight display. An amber BRAKE OVHT message is also
annunciated on the EICAS for aircraft S/Ns 1168 -1252.
NOTE:
Temperature limits for ABS brakes are 400° ±10°C -
the OVHT light will remain on until the brake(s) has
cooled below 370°C. For Dunlop brakes the
temperature limit is 625° ±25° C - the OVHT light will
remain on until the brake(s) has cooled to below
595°C.
The TEST push-button on the BTMS verifies that system circuits are
operating properly. With the temperature selector switch in the ALL
position, the test function checks all four wheel circuits and the over
temperature warning circuit. A proper test is indicated by a temperature
gage reading of 425°C to 475°C (for both ABS and Dunlop brakes) and the
illumination of the OVHT light. If either of these conditions is not valid,
selecting each wheel brake with the readout selector and pressing the
TEST push-button will identify the faulty circuit. A temperature reading of
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湾流4操作手册 Gulfstream IV Operating Manual 2(89)
