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7. If brake pressure indications are normal, use CAUTION in normal braking.
8. If abnormal or no brake pressure indications occur, ANTI-SKID Switch..........................OFF
9. Depress brake pedals individually (pilot or copilot) and verify applied brake pressure is
appropriate for brake pedal deflection.
10. If brake pressure indications are normal, refer to ANTI-SKID OFF BRAKING Procedure,
this Section.
11. If abnormal or no brake pressure indications occur, BCS 1 circuit breaker .................... PULL
12. Depress brake pedals individually (pilot or copilot) and verify applied brake pressure is
appropriate for brake pedal deflection.
13. If brake pressure indications are normal, refer to ANTI-SKID OFF BRAKING procedure
this Section.
14. If abnormal or no brake pressure indications occur, BCS 1 circuit breaker ..................RESET
15. ANTI-SKID Switch ............................................................................................................. ON
GULFSTREAM AEROSPACE
GIV AIRPLANE FLIGHT MANUAL
SECTION 3
ABNORMAL
PROCEDURES
FAA APPROVED 3-39
31 May 2000
16. BCS 2 Circuit Breaker ..................................................................................................... PULL
NOTE: Pulling this circuit breaker causes three (3) amber and one (1) blue brake messages to
illuminate on EICAS.
17. Depress brake pedals individually (pilot or copilot) and verify applied brake pressure is
appropriate for brake pedal deflection.
18. If brake pressure indications are normal, use CAUTION in normal braking.
19. If abnormal brake pressure indications occur, use LANDING WITH APPLIED BRAKE
PRESSURE INDICATED procedure, this Section.
20. If NO brake pressure indications occur, refer to Section 4, EMERGENCY BRAKES
procedure.
GULFSTREAM AEROSPACE
GIV AIRPLANE FLIGHT MANUAL
SECTION 3
ABNORMAL
PROCEDURES
3-40 FAA APPROVED
31 May 2000
3-06-60: BTMS OVHT Light On or Brake OVHT Message:
ON THE GROUND
If the OVHT light on the BTMS display and the amber BRAKE OVHT CAS message
illuminates during ground operations:
1. Determine which brake is causing the OVHT light by slowly rotating the BTMS selector
switch through each position and checking for brake temperatures exceeding:
NOTE: For SPZ 8400 equipped airplanes, BTMS display is available only on BRAKES System
page. All four (4) brake temperatures are displayed simultaneously on the BRAKES
System page.
A. 400° ±10° (Non ASC 190/Non ASC 266 airplanes SN 1000 thru 1213 with ASC 167)
B. 625° ±25° (ASC 190/ASC 266 airplanes SN 1000 thru 1213 with ASC 346 and SN
1214 and subs.)
2. Avoid using the brake(s) that exceed the OVHT limit. Use reverse thrust as necessary to
assist in stopping the aircraft if required.
NOTE: For airplanes 1000 through 1143 without ASC 166: Use of Thrust Reversers is limited
to one (1) minute every thirty (30) minutes.
3. If possible, expeditiously move the airplane to an uncongested area clear of other aircraft
and active taxiways/runways.
4. DO NOT SET THE PARKING BRAKE. Chock the nose gear tire if possible.
GULFSTREAM AEROSPACE
GIV AIRPLANE FLIGHT MANUAL
SECTION 3
ABNORMAL
PROCEDURES
FAA APPROVED 3-41
31 May 2000
5. Monitor temperature of all brakes for trend information:
A. If temperatures continue to rise or remain above the OVHT limit for more than five (5)
minutes, expect wheel fuse plugs to release. EVACUATE all personnel and remain
clear of the main landing gear area for a minimum of thirty (30) minutes.
CAUTION: DO NOT ATTEMPT TO TAKEOFF WITH THE BRAKE OVHT LIGHT
ON. THERE MAY NOT BE SUFFICIENT BRAKE KINETIC ENERGY
AVAILABLE IN THE EVENT OF A REJECTED TAKEOFF OR TIRE
FAILURE MAY OCCUR DURING TAKEOFF ROLL.
NOTE: A visual inspection of the overheated wheels, tires, and brakes should be
accomplished prior to the next flight.
B. If the temperatures have peaked and the OVHT light extinguishes, the tires should be
inspected for proper inflation and the brakes inspected for obvious damage before
continuing the departure.
NOTE: The flight crew should consider brake energy requirements for subsequent
departures with elevated brake temperatures. See Appendix C for Brake Kinetic
Energy and Brake Cooling chart data.
IN-FLIGHT
1. Altitude ................................................................ 20,000 ft. or Below (Descend If Necessary)
2. Airspeed......................................................................................................... 225 KCAS MAX
3. Landing Gear ............................................................................................................. EXTEND
　
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