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0°C indicates a short in the selected sensor circuit.
3. Brake Temperature Monitoring System (SPZ-8400 EQUIPPED AIRCRAFT)
A. Description
The Brake Temperature Monitor System (BTMS) on aircraft with SPZ 8400
DAFCS installed is mechanically and electrically the same as that installed
on prior S/N aircraft. Only the display format differs. Temperature data from
the brake temperature probes is supplied to the Data Acquisition Units
(DAUs) that communicate the data for presentation on the CAS display.
The Brake page is selected to the CAS with Line Select Key (LSK) entries
on the Display Controller.
On the CAS, brake temperatures are formatted as bar graphs rising
vertically with temperature. A center bar displays temperature scale
increments in C° X 100, with the temperature of the inner and outer brakes
on the left and right struts aligned on either side of the scale. Above the bar
graph display is a presentation of applied brake pressure for left and right
brakes in increments of psi X 100. Whenever the landing gear is extended,
a readout of the peak temperature recorded during the last brake
application in °C and identification of the brake with the peak temperature
is displayed beneath the bar graphs. The existing record of prior brake
application peak temperature is erased whenever the landing gear is
lowered for landing, and when the aircraft accelerates faster than 60 knots
on take off roll, initiating a new cycle for temperature recording.
If a brake temperature exceeds 625°C ±25°C, the bar graph display for that
brake will be displayed in amber, and a BRAKE OVHT caution message is
displayed on the CAS. The maximum temperature and time (in GMT) of the
exceedance is recorded and is available for display by selecting the
exceedance page on the CAS. The bar graph display will return to the
OPERATING MANUAL
2A-32-00 PRODUCTION AIRCRAFT SYSTEMS
Page 40
January 31/02
Revision 6
normal white color display and the BRAKE OVHT caution message will
clear when the brake cools to 595°C or below.
If an individual brake sensor or monitor circuit malfunctions, the
corresponding bar graph is replaced with a red X. If a DAU fails, both brake
temperature graphs on the strut monitored by the DAU are replaced by X’s
and the peak temperature readout is replaced with amber dashes.
For additional information on the Brake System Temperature displays, refer
to the Honeywell SPZ-8000 or SPZ-8400 Digital Automatic Flight Control
System Pilot Manual for the Gulfstream IV.
4. Controls and Indications:
A. Circuit Breakers (CBs)
The wheels and brakes are protected by the following circuit breakers:
Circuit Breaker Name CB Panel Location Power Source
WHEEL SPEED CPO C-10 Left Main 28V DC Bus (1)
Emergency 28V DC Bus
2B (2)
BTMS (3) CPO D-10 Right Main 28V DC Bus
APPLIED BRAKE
PRESSURE
CPO D-6 Essential 28V DC Bus
BCS CHL #1 (1) CPO A-2 Fwd Emergency Battery
28V DC Bus
BCS CHL #2 (1) CPO B-2 Essential 28V DC Bus
INBD ANTI SKID (2) CPO A-2 Emergency 28V DC Bus 1A
OUTBD ANTI SKID (2) CPO B-2 Emergency 28V DC Bus
2B
WHEEL BRK ACCUM
PRESS
CPO D-3 Essential 28V DC Bus
NOTE(S):
(1)Electronic Brake-by-Wire System
(2) Hydro-Mechanical Analog Braking System
(3) Aircraft with SPZ-8000
B. Caution (Amber) CAS Messages:
Caution CAS messages associated with wheels and brakes are:
CAS Message Cause or Meaning
ANTI-SKID FAIL
(Brake-by-Wire
Normal anti-skid control circuit or other failure: system has
switched to open loop pulsed anti-skid control (bang-bang
braking)
OR: ANTI-SKID switch selected to OFF
ANTI-SKID FAIL
(Hydro-Mechanical
Analog Braking)
Miscompare in 28V DC power supplies or in nutcracker
switches
OR: ANTI-SKID switch selected to OFF or system circuit
problems
OR: Auxiliary hydraulic system fails to energize or
pressure fails to rise within three (3) seconds after brake
pedals are depressed
BRAKE FAIL
(Brake-by-Wire)
Failure of brake system. BCS cannot provide braking
OPERATING MANUAL
PRODUCTION AIRCRAFT SYSTEMS 2A-32-00
Page 41
January 31/02
Revision 6
CAS Message Cause or Meaning
BRAKE FAIL
(Hydro-Mechanical
Analog Braking)
Loss of Combined and Auxiliary hydraulic system
pressure. No braking is available
BRAKE OVHT One or more brake assemblies has exceeded temperature
limit:
• 400°C for S/N 1156-1213 and aircraft with ASC 167
• 625°C for S/N 1214 and subsequent, and S/N 1000-
1213 with ASC 346
　
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