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ground, since this would place the nutcracker switches in the air mode,
interrupting the circuits to aircraft systems that are dependent upon ground
(weight-on-wheels) mode for proper operation (this action would retract the
solenoid pin from the landing gear lever, allowing the handle to be placed in
the up position).
E. Brake Nutcracker Override Switch (Brake-by-Wire System Only)
During flight with the nutcracker switches in the air (weight-off-wheels)
mode, hydraulic pressure is removed from the main landing gear brakes.
Brake operation and correct brake pressure application may be tested in
flight by depressing the Brake Nutcracker Override Switch on the center
pedestal, shown in Figure 18. With the switch depressed, brake pressure
may be applied with the landing gear retracted. With the EICAS selected to
the hydraulics system page (SPZ-8000) or the brakes system page (SPZ-
8400) depressing either set of brake pedals will result in the applied brake
pressure indicated on the brake system page, allowing verification of brake
operation prior to landing.
4. Limitations
A. Landing Gear Extended Speed (VLE / MLE)
Do not exceed 250 KCAS / 0.70 MT with landing gear extended (gear
doors open or closed).
B. Landing Gear Operation Speeds (VLO / MLO)
(1) Normal Operation:
Do not lower or raise landing gear at speeds in excess of 225 KCAS
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/ 0.70 MT.
(2) Alternate Operation:
Do not lower landing gear using alternate system at speeds in
excess of 175 KCAS.
C. Landing Gear Extension / Operation Altitudes
Maximum operating altitude for extending landing gear or flying with
landing gear extended is 20,000 ft. MSL.
D. Speed Brakes Extension With Landing Gear Extended
During flight, speed brakes are not to be extended with flaps set at 39°, or
with the landing gear extended.
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Landing Gear Lever Linkage
Figure 7
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Landing Gear Control
Panel
Figure 8
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Emergency Gear Extension Controls
Figure 9
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Emergency Extension Bottle
Figure 10
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2A-32-00 PRODUCTION AIRCRAFT SYSTEMS
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Nutcracker Switch Test
Pushbutton
Figure 11
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2A-32-40: Wheels and Brakes System
1. General Description
The GIV aircraft is equipped with one of two types of main landing gear wheels/
brakes and tires, and one of two types of braking systems, depending upon serial
number (S/N) and/or Aircraft Service Change (ASC) retrofitted into the aircraft.
Aircraft S/N 1000 through S/N 1213 (with the exception of S/N 1183) are equipped
with main landing gear wheels and brakes manufactured by Aircraft Braking
Systems (ABS) and tires manufactured by Goodyear, speed rated at 182 knots.
Beginning with S/N 1214, aircraft were equipped with main landing gear wheels /
brakes manufactured by Dunlop, and Goodyear tires. The later model GIV
wheels/brakes and tires are speed rated at 195 knots, and thus support increased
speeds associated with higher gross weight takeoffs. Any aircraft not equipped
with Dunlop wheels/brakes may optionally have them retrofitted with the
installation of ASC 266.
Aircraft S/N 1000 through S/N 1213 (with the exception of S/N 1183) are equipped
with an electronic braking system that transmits signals proportional to cockpit
brake pedal movement to a Brake Electronic Control Unit that then applies
hydraulic pressure to the brakes in response to the variable electric signal. This
type of braking system is commonly referred to as Brake-by-Wire. Beginning with
S/N 1214, aircraft are equipped with a Hydro-Mechanical Analog Braking system
(HMAB). In the HMAB system, the cockpit brake pedals are mechanically
connected to valves that apply hydraulic pressure to the brakes in response to
brake pedal displacement. Aircraft produced prior to S/N 1214 may have the
HMAB system retrofitted with the installation of ASC 307. Both braking systems
incorporate full anti-skid protection. Each of the primary braking systems is
supplemented with an independent emergency/parking brake system that uses
　
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