Descripcion boeing 727 ata 31 - instruments

1. LINE AND BASE MAINTENACE TRAINING
INSTRUMENTS
B727-200
AIRWAYS CONSULTORIA AERONÁUTICA LTDA

2. AIRWAYS TREINAMENTOS INSTRUMENTS
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MATERIAL DIDÁTICO
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AIRCRAFT PANEL - DESCRIPTION AND OPERATION
1 . General
A. The layout of the instrument panels in the control cabin is illustrated on next page.
B. The pilots' main panels consist of the captain's panel, the engine panel, the lightshield and the first officer's
panel. The instruments on the captain's and the first officer's panels are generally duplicates of each other to
enable either pilot to fly the airplane.
C. The pilots' overhead panel is installed in the center of the ceiling immediately above the windows.
D. The pilots' electronic panels consist of a forward panel, immediately below the center panel, and an aft
panel on the control stand.
E. The third crewman's instrument panels consist of indicators and switches to monitor and control the airplane
performance.
F. Auxiliary panels consist of observer's panels and the pilots' side panels.
2 . Instrument Indicators
A. There are principally three types of instrument indicators. They are the clamp, bezel, and rear-mounted
types.
B. The clamp-type indicator is held in position by a spring clamp which is fastened to the rear of the front panel
or module with a clamp retaining screw. The clamp is tightened around the indicator by a clamp adjustment
screw; thereby, holding the indicator in position.

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C. The bezel-type indicator is held in position similar to the clamp type indicator. A bezel is mounted on the
front of the panel; otherwise the indicators are secured in an identical manner.
D. The rear-mounted type indicator is held in position with three retaining screws which holds the flange on the
indicator flush with the rear of the instrument panel.

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FLIGHT DATA RECORD
1 . General
A. The expandable flight data acquisition and recording system (EFDARS) records selected items of flight data
obtained during the latest 25 hours of operation of the airplane. The data is obtained from other airplane
systems as well as from sensors which provide data exclusively to the EFDARS. Switches on the flight data
entry panel may be used to enter documentary data into the system. This data includes date, flight number, of
the flight, gross weight, and identification numbers of the captain and first officer. The input signals are
reconditioned, and digitized as required, multiplexed, and magnetically recorded. Monitor circuits within the
major units provide fault signals to turn on status lights on the flight data entry panel in the event of unit failure.
B. The EFDARS consists of a flight data acquisition unit (FDAU), a digital flight data recorder (DFDR), a flight
data entry panel (FDEP), sensors, and interconnecting wiring.
C. The EFDARS is turned on automatically when the airplane leaves the ground. The system may also be
turned on by the GROUND TEST switch on the FDEP.
D. An extension cable is built into the airplane to facilitate use of the system. The cable has connectors at the
shelf stanchion adjacent to the FDAU and at the middle web behind the third crewman's panel. It is used
to connect the portable tester to the FDAU allowing the tester to be used in the flight compartment.
E. Operating power for the system is 115 volts ac supplied from the radio bus No. 2 through the FLIGHT
RECORDER 115 VAC circuit breaker on P18.
Synchro excitation voltage is supplied from the 26-volt ac radio bus No. 2 through the FLIGHT RECORDER
26 VAC circuit breaker on P18.

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2 . Flight Data Acquisition Unit
A. The FDAU is installed in E3-3 in the main equipment center. It processes all input signals to prepare them
for recording. Electronic circuits in the FDAU provide isolation; perform the functions of preconditioning,
multiplexing, scaling, and synchronization to convert the signals to standard digital format; and transmit the
processed signals to the DFDR for recording. During multiplexing, controlled electronic switches allow only the
selected parameter to be processed by the system.
B. The FDAU provides two separate 5-volt dc outputs for potentiometer excitation and a 28-volt dc output for
accelerometer excitation.
C. Status monitor circuits within the FDAU provide a fault signal to turn on the FDAU STATUS light on the
FDEP in the event of failure within the unit.
D. A connector on the front of the unit provides for interface with portable test equipment.

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CLOCKS
1 . General
A. Clocks are installed on the captain's, first officer's, and third crewman's instrument panels. A single pulse
generator installed in P6 panel provides time signals to captain's and first officer's clocks. The clocks are
intended as the flight crews' primary time reference. The system , consisting of the three clocks, the pulse
generator, and the captain's and first officer's remote event timing switches, receives operating power from the
hot battery bus and is on as long as the battery has a charge.

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AURAL WARNING SYSTEM
A. The aural warning systems provide the flight crew with audible signals to warn of unsafe or abnormal
conditions on the airplane. The circuits, which produce the sounds, are contained in the aural warning devices
box.
The devices box also provides chime sounds which signal a ground station call (if activated) or crew call. On
some aircraft the 65-54499 Series aural warning devices box has been replaced by the 69-78214-1 Series
aural warning module. The aural warning systems consist of landing gear warning, speed brake/flap position
warning, takeoff warning, cabin altitude pressure warning, mach airspeed warning, and fire detection warning.
B. The landing gear warning system consists of an accessory unit, a thrust lever actuated throttle switch for
each engine, a position switch for each landing gear, a flap position switch, and the aural warning system
continuous horn circuit.
C. The speed brake/flap position warning system consists of a flaps up position switch, a speed brake lever
landing warning switch, a time delay relay, and the aural warning system intermittent horn circuit.
D. On airplanes with the thrust lever activated takeoff warning system, the takeoff warning system consists of
the engine No. 3 thrust lever actuated throttle switch, a flap position switch, the upper and lower stabilizer trim
switches, a speed brake lever switch, and the aural warning system intermittent horn circuit.
E. On airplanes with the EPR activated takeoff warning system, the takeoff warning system consists of the
thrust lever actuated throttle switches for engines No. 1 and 3, a flap position switch, the upper and lower
stabilizer trim switches, a speed brake lever switch, the printed circuit cards for engines No. 1 and 3 which
contain the EPR control logic and test circuits, and the aural warning system intermittent horn circuit.
On some airplanes, the takeoff warning system includes two slat extend relays.

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F. The cabin altitude pressure warning system consists of an altitude pressure switch, a warning horn relay
and cutout switch, and the aural warning system intermittent horn circuit. The mach airspeed warning system
consists of mach airspeed transducer switches and an audible signaling device in the aural warning devices
box. The fire detection warning system consists of detector circuits, audible-signaling devices, and a sound
cutout switch with associated relays.
G. The aural warning system receives 28-volt dc power from the P6 and P18 load control centers and 115-volt
ac power from the P6 load control center. Power distribution to the system is shown on Fig. 2.

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