PR SYNC 2
LE E
OAT

SAFE
EOT RTR RTR
FUEL BOOST PUMP CONTROL

PWR SELF DSCRM ON +ON OFF OFF AUDIO

TEST ON ON
NO. 1 NO. 2
ONON INOP

I R OFF OFF
PUMP
PUMP
C
M OFF
FAIL
BRT D / U D / U BRT
PARKING BRAKE
BATT & ESNTL BUS
ESNTL DC FUEL BATT WARN
B
DIM L / R L / R DIM
ONPRIME BUSDC AC & FIRE DSPL POS DSPL POSA
B
CHAFF
505 55T5 5
DISPENSE
A
T
CPLT
PLT
+
MODE MODE
T SPLY CONV EXT PWR BOOST CONTR EXTGH P.PGM ALT/P/R ADJ
1.4 BIT
U 1.4
WARN CONTR
T
DEC INCUTIL T OP ONAPU NXT SELBUS CDU APU
I
B
U

NOTE
S DCLT ACK DCLT
CP.PGM PGM OFF
L 5555 55
B
CONTR FIRE GEN DC U BKUP CONTR
INST DET CONTR SPLY S INST

IGNITION SWITCH IS
LOCATED ON LEFT SIDE
AB0697

OF CENTER CONSOLE.
SA

Figure 2-7. Lower Console
should display 888, and three RTR OVERSPEED lights on the PDUs should be on.
2.8.2.2 Dim Control. The DIM control allows the pilot to set a desired display light level of the CDU and PDUs in accordance with the ambient light, or override the auto-dim sensors. If the auto-dim circuitry should fail or malfunction, turn the DIM control fully clockwise to regain illumination of the CDU and PDUs.
2.8.2.3 CDU and PDU Digital Control. An ON, OFF DIGITS control switch is on the CDU (Figure 2-8) to turn on or off the digital readout displays on the CDU and PDUs. If a digital processor fails, all digital displays will go off.
2.8.3 Pilot’s Display Unit (PDU). The PDU (Figure 2-8) displays to the pilot engine power turbines speed (% RPM 1 and 2), rotor speed (% RPM R), and torque (% TRQ). Readings are shown by ascending and descending columns of multicolored lights (red, yellow, and green) measured against vertical scales. A TEST switch provides a means of electrically checking all PDU scale lamps and digital readouts. When the TEST switch is pressed, all PDU scale lamps should light and digital readouts should display
188. The % RPM indicators contain low range turnoff be-low the normal operating range. Three overspeed lights at the top will go on from left to right when a corresponding rotor speed of 127%, 137%, and 142% is reached. Once a light is turned on, a latch prevents it from going off until reset by maintenance. Power for the PDUs is from No. 1 and No. 2 ac and dc primary buses through circuit breakers marked NO. 1 AC INST/NO. 1 DC INST and NO.2AC INST/NO. 2 DC INST respectively. See Figure 5-1 for instrument markings.
2.9 DOORS AND WINDOWS.
2.9.1 Cockpit Doors. The crew compartment is reached through two doors, one on each side of the cockpit. The doors swing outward and are hinged on the forward side (Figure 2-1). Each door has a window for ventilation. In-
stalled on the back of each door is a latch handle to allow unlatching the door from either inside or outside the cock-pit. Emergency release handles are on the inside frame of each door (Figure 9-1). They allow the cockpit doors to be jettisoned in case of an emergency. There is an emergency release pull tab on the inside forward portion of each cock-pit door window for pilot egress.
2.9.2 Cabin/Cargo Doors.

Do not put pressure on bubble during ob-servation. Excessive pressure or loading could cause bubble seal to loosen, causing loss of window.
During operation of the air conditioner system, the right cabin door should re-main closed. If opening is required, the right cabin door should not remain open for more than one minute, due to heat from ECS.
Aft sliding doors are on each side of the cabin/cargo compartment (Figure 2-1). Single-action door latches allow the doors to be latched in the fully open or fully closed positions. Each of the two doors incorporate two jettison-able windows, for emergency exit (Figure 9-1). One win-
　
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