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thrust as necessary to assist in stopping the airplane if required.
NOTE: For airplanes 1000 thru 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 airplane and active taxiways/runways.
4. DO NOT SET THE PARKING BRAKE. Chock the nose gear tire if
possible.
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. Refer
to GIV AFM Appendix C for Brake Kinetic Energy and Carbon Brake
Cooling chart data. (Chart shown on QRH page PC-14.)
IN FLIGHT:
1. Altitude ...... 20,000 FT OR BELOW (DESCEND IF NECESSARY)
2. Airspeed................................................................. 225 KCAS MAX
3. Landing Gear ....................................................................EXTEND
4. Airspeed................................................................. 250 KCAS MAX
Continued on next page →
Quick Reference Handbook
REVISION 7 ABNORMAL / EMERGENCY PROCEDURES
May 30/02 (HMAB) Page EB - 7
BTMS OVHT Light On or BRAKE OVHT Message (HMAB), ctd…
AFM 3-06-60
5. BTMS.............................................................................. MONITOR
NOTE: Landing gear should remain extended for minimum of ten (10)
minutes after the BTMS OVHT light is extinguished. Brake
temperature(s) should be monitored to ensure decreasing trend.
6. Airspeed .................................................................225 KCAS MAX
7. Landing Gear.................................................................. RETRACT
8. BTMS / OVHT Light............................................. CHECKED / OUT
NOTE: An inspection of overheated wheels, tires, brakes, and wheel
speed sensors should be accomplished before next flight. Refer to GIV
AFM Appendix C for Brake Kinetic Energy and Carbon Brake Cooling
chart data. (Chart shown on QRH page PC-14.)
END
Anti-Skid Failure (HMAB) AFM 3-02-40
FOR AIRPLANES SN 1183, 1214 AND SUBS
A failure occurring in the brake system which renders the anti-skid
inoperative will be indicated by illumination of the ANTI-SKID FAIL
amber message on the EICAS.
There is no automatic reversion to auxiliary braking unless the
combined/utility hydraulic system fails.
If the anti-skid switch is left ON there may still be anti-skid protection on
one pair of wheels (inboard or outboard). With the anti-skid switch OFF
all anti-skid protection is disabled.
Braking with the ANTI-SKID FAIL message illuminated should be
performed using the Anti-Skid Off Braking procedure in this section.
END
Quick Reference Handbook
ABNORMAL / EMERGENCY PROCEDURES REVISION 7
Page EB - 8 (HMAB) May 30/02
Anti-Skid Off Braking (HMAB) AFM 3-02-50
FOR AIRPLANES SN 1183, 1214 AND SUBS
During takeoff with anti-skid inoperative or selected OFF, wheel
spindown function will be functional.
Takeoff with the anti-skid inoperative or selected OFF:
1. ANTI-SKID Switch.....................................................................OFF
2. Applied Brake Pressure Display.........................SELECT ON DU 4
Approach and landing with anti-skid inoperative:
1. ANTI-SKID Switch...................................................................... ON
2. Applied Brake Pressure Display.........................SELECT ON DU 4
3. Maximum Reverse Thrust.................................................... APPLY
4. Immediately upon landing or at takeoff abort, the pilot should
smoothly apply brakes to approximately 300 psi as advised by the
copilot. In an anti-skid inoperative situation, the pilot should devote
his attention to airplane control and the copilot should monitor
applied brake pressure and advise the pilot of corrections needed
　
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