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The brakes and steering isolation switch is on the HYD
control panel on the overhead switch panel (fig. 2-1-10
and 2-1-14). It is labeled BRK STEER, ON, and OFF. The
switch isolates the brakes and steering hydraulic subsystems
from the rest of the utility hydraulic system in the
event of a leak in the subsystem. The normal position of
the switch is ON. The switch is guarded to ON. Setting the
switch to OFF, closes the power steering and brakes
valve on the utility system pressure control module, isolating
the brakes and steering subsystem. With the
switch at OFF, limited brake application are available due
to an emergency brake accumulator in the brake subsystem.
Power to operate the isolation valve is from the No.
1 DC bus through the HYDRAULICS BRAKE STEER
circuit breaker on the No. 1 PDP.
2-1-11. Instrument and Control Panels.
NOTE
The NVG overhead switch panels are shown.
Description of control panels and operating
procedures reflect NVG configuration only.
Figures 2-1-5 and 2-1-6 show center and canted
consoles. 712 Figures 2-1-7 through 2-1-10 show the
copilot instrument panel, center instrument panel, pilot
instrument panel, and the NVG overhead switch panel.
714A Figures 2-1-11 through 2-1-14 show the copilot
instrument panel, center instrument panel, pilot instrument
panel, and the NVG overhead switch panel.
2-1-12. Personnel/Cargo Doors.
Entry can be made through either the main cabin door or the
cargo door and ramp.
2-1-13. Main Cabin Door.
The main cabin entrance (15, fig. FO-1) door is on the right
side of the cargo compartment. The door is divided into two
sections: the upper section containing a jettisonable panel
and the lower section forming the entrance step. When
opened, the upper section slides upward on overhead rails
and the lower section swings downward. When closed, the
two sections mate to form the complete door. Handles are
provided on both the outside and the inside of the door for
accessibility. Refer to Chapter 5 for the allowable airspeed
imposed on the helicopter while operating with the cabin
entrance door sections in various positions.
2-1-14. Cargo Door and Ramp.
Chapter 6 provides a detailed description and operation of
the cargo door and ramp.
2-1-15. Pilot and Copilot Sliding Windows.
The upper section of each jettisonable door (39, fig. FO-1)
in the cockpit contains a sliding window. The window slides
fore and aft and is locked and unlocked by a handle at the
forward end of the jettisonable door. The handle is moved
forward to lock the window and aft to unlock the window.
2-1-16. Seats.
The pilot’s and copilot’s seats (9 and 40, fig. FO-1) are on
tracks to permit forward and aft, vertical and reclining position
adjustments. Bungee cords in each seat exert an upward
force on the seat when it is down or tilted.
2-1-17. Seat Fore-and-Aft Lever.
A fore and aft control lever (14, fig. 2-1-3) for horizontal seat
adjustment is on the right side of each seat support carriage.
When the lever is pulled UP, the seat is unlocked and can
be moved along the tracks on the cockpit floor. When the
lever is released, the seat is locked in position horizontally.
The total range of the horizontal movement is 4 inches in 1
inch increments.
2-1-18. Seat Vertical Lever.
Vertical seat adjustment (15, fig. 2-1-3) is controlled by a
lever on the right side of each seat. When this lever is pulled
UP, the seat is unlocked and can be moved vertically along
a track through a range of 5 inches. The range is divided into
1/2 inch increments. When the lever is released, the seat is
locked in position vertically.
CAUTION
With the seat in the full up rotation position
(zero tilt) the seat may not be able to
be locked in the full down vertical position.
Ensure the seat is locked when adjusting
the vertical axis, especially when
the seat is in full up rotation position (zero
tilt).
2-1-19. Seat Rotation Lever.
A control lever (20, fig. 2-1-3) for adjusting the seat reclining
position is on the left side of each seat. When this lever is
pulled UP, the seat is unlocked and can be rotated through
a 15º tilt range divided into four equal increments. The seat,
in effect, is pivoted up and down around a horizontal axis.
When the lever is released, the seat is locked in the selected
tilt position.
2-1-20. Armored Seats.
Both the pilot and the copilot seats are equipped with a
combination of fixed and adjustable ceramic armor panels
(fig. 2-1-15). Fixed panels are installed under the back and
　
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