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Turn the OXYGEN supply valve to OFF before
pulling the emergency oxygen manual
actuating handle if contamination of the normal
systemi s suspectedF. ailure to do sow ill
inhibit seatpan shuttle valve operation, pmventing
flow of emergency oxygen.
Note
Flow of oxygen from the emergency cylinder
can be stopped by reseating the manual actuation
handle.
2.32 PITOT-STATIC SYSTEM
The pitot-static pmssure system supplies impact (pitot)
andatmospheric(s tatic)pressumtothepilotandRIOflight
instruments, to the CADC, and to the engine AICS programmers.
S omes ystemsm quim staticp ressureo nly; othersr
equire static andp itot pressure( seeF igure 2-82).
The pitot-static system is composed of two separate
systems with individual pitot-static probes, one on each
side of the forward fuselage.
The left pitot pressure (PT) probe supplies the pilot
standby airspeed indicator and the left AICS programmer.
The tight pitot pressure i,PT) probe supplies the RIO
standby airspeed indicator, the right AICS programmer,
and the CADC with airspeed indications. An electrical
PT~pUt~Omtheleft~CSprO~eriSSU~liedto
the CADC backup channel as airspeed indications for
wing sweep.
The left and right forward static ports f&t) are manifolded
to provide static pressure to the pilot standby
airspeed indicator, standby altimeter, vertical speed indicator,
and the CADC. Static pressure from the right
aft (Psz) static ports supply the RIO standby airspeed
indicator, standby altimeter, and the right AICS progmmmer.
The staticp ressurefr om the left aft (PS2)s taticp orts
supply the static pressmct o the left AICS PS sensorA. n
electricalP S input liom the left AICS programmeris sup
plied to the CADC backup channel for wing sweep.
Note
l With the in-flight refueling probe extended,
the pilot and RIO standby altimeters
and airspeed indicators show
erroneousr eadingsb ecauseo f changesi n
airflow around the pitot-static probes.
l The RUDDER AUTH caution light may
illuminate when the in-flight refueling
probe is extended. Press the MASTER
RESET button to reset the light.
2.32.1 Pitot-Static Heat. Bach pitot-static probe is
equipped with electrical beating elements to prevent
icing. Pitot-static heat is controlled by the pilot through
the ANTI-ICE switch on the pilot right console. In
AUTO/OFF, pitot probe heat is available only with weight
off wheels. ORlDE/ON activates the probe heat elements
independently of the weight-on-wheels switch
and illuminates the INLET ICE caution light on the
CAUTION ADVISORY panel. OFF/OFF removes heat
Born the probes.
[-G&q
The ANTI-ICE switch should normally be
in AUTO/OFF during takeoff and landing.
Engine anti-icing has adverse effects on engine
stall margin.
ORIGINAL 2-144
NAVAIR 0%Fl4AAD-1
BACK-UPOXYGENPRESSURE
1
CABIN ALTITUDE 2000 1600 1200 800 400 200
35 & ABOVE 100 80 60 40 20 IO
30 72 58 43 29 14 7
25 52 42 31 21 10 5
20 41 33 24 16 8 4
15 32 26 19 13 6 3
10 27 22 16 10 5 2.9
8 24 19 14 9 4 2.5
5 21 17 12 8 4 2.2
SL. 17 14 10 7 3 1.8
Minutes remaining based on two-man consumption.
Duration data should be used as a guide
Consumotion rate based on 13.1 liters oer minute oer man.
Figure 2-8 1. Oxygen Duration Chart
2.33 CONTROL AND DISPLAY SYSTEM
The control and display system (Figure 2-83) provides
the crew with control and display of navigation,
aircraft status, and flight tactical information. The control
and displays system consists of two display processon
@PI and DP2), three multifunction displays @lot
center MFDI, pilot right MFD2, and RIO MFD3), and
a heads-up display system, cockpit television sensor,
HUD-VIDEO panel, pilot DISPLAYS control panel,
and a multistatus indicator.
The control and display system also sends display
information to the digital display, the radio tiequency
indicator, radio frequency/control indicator, and the
mission video recorder.
The data entry unit is a remote terminal that communicates
with the mission computers via the multiplex
buses.
2.33.1 Display Types. The following types of display
information are provided by the MFD system:
1. Calligraphic or stroke writing is displayed on the
HUD, MFDs, and the DD.
2. Raster video (for example radar, television) generated
internally (VDI formata) or provided by an
&ems1 sensor, with or without a stroke overlay,
is displayed on the MFDs and the DD.
3. Alphanumeric data is displayed on the multistatus
indicator and the radio f?equency and radio
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F-14D 飞行手册 Flight Manual 1(137)
