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CUT Severs a deployed towline.
ON Powers ALE-50. With WonW, initiates start-up BIT. Enables the ALE-50 sublevel
on the EW format.
OFF ALE-50 off.
2.20.2.2 ALE-50 BIT Anomalies. There are currently three anomalies related to ALE-50 BIT, which
can corrupt decoy inventory or damage the MPLC. These anomalies have not yet been corrected, so
care should be taken when ALE-50 BIT is run.
1. When a full ALE-50 dispenser has been installed between flights, a full ALE-50 start-up BIT
must be run with WonW, in order to inventory all decoys. If ALE-50 BIT is not run WonW, the
system defaults to the last known inventory (which is two if one was dispensed on the previous
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flight).
2. If the JAMMER switch is placed to OFF while the ALE-50 start-up BIT or IBIT is running, the
decoy inventory can be corrupted and/or the DECOY caution can be inhibited (e.g., no cockpit
indication of a failed decoy is provided).
3. If the ALE-50 BIT is run post-flight after one or more decoys has been dispensed inflight, the
system may arc and damage the MPLC.
Therefore, to avoid the potential loss of ALE-50 operability, aircrew should perform the following
procedures on flights where ALE-50 use is anticipated. Run the ALE-50 start-up BIT and/or IBIT with
WonW prior to flight. Do not place the JAMMER switch to off while ALE-50 BIT is running. If this
occurs, place the JAMMER switch back to ON and run another start-up BIT. Turn the JAMMER
switch OFF inflight prior to landing or, at a minimum, do not cycle the JAMMER switch OFF then ON
or initiate ALE-50 IBIT when WonW post-flight.
2.20.2.3 DECOY Caution. The DECOY caution is set under the following conditions: (1) the hook or
landing gear is lowered with an ALE-50 decoy deployed, (2) a deployed decoy fails (AUTO DEPLOY
option not selected), or (3) the signal was sent to sever a towline but the squib did not fire.
2.21 BIT-STATUS MONITORING SUBSYSTEM
The BIT/status monitoring subsystem, provides the aircrew with a simple display of system status.
Most information is derived from BIT mechanizations within the avionics sets and from non-avionic
built in tests implemented in the computer software for other aircraft subsystems.
The subsystem monitors engine and airframe operational status for unit failures and caution/
advisory conditions when the mission computer system is operating. When the mission computer
system detects a caution/advisory condition, it commands display of the applicable caution or advisory
message on one of the DDIs. If the mission computer system detects a unit failure, it commands the
subsystem to store the applicable maintenance code. The mission computer displays the subsystem
BIT results on one of the DDIs.
Non-BIT equipment status includes configuration ID numbers and INS terminal data.
2.21.1 FIRAMS - Flight Incident Recorder and Aircraft Monitoring Set. The FIRAMS consists of a
signal data computer, a data storage set, an engine fuel display, and a maintenance status panel. The
FIRAMS monitors selected engine, airframe, avionic, non-avionic, fuel gauging and consumable
signals. It also performs conversion of sensed measurements, provides real time clock function, outputs
discrete and analog data to associated equipment, communicates with the mission computer, displays
fuel quantities and engine parameters, and performs fuel system health monitoring. FIRAMS also
provides nonvolatile storage for flight incident, maintenance, tactical and fatigue data, and bulk data
input of tactical mission planning data.
2.21.2 DFIRS - Deployable Flight Incident Recorder Set. The DFIRS system consists of the signal
data recorder (SDR), the data transfer interface unit, and the pyrotechnic release system. The SDR
consists of the flight incident recorder memory, beacon, battery, and antenna. DFIRS is contained in
a deployable aerodynamic airfoil located on the top of the fuselage between the rudders. The DFIRS
system stores up to 30 minutes of flight data and, when activated, deploys the SDR along with a rescue
beacon in an airfoil. The SDR is deployed upon pilot ejection or on ground impact. The data stored on
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the flight incident recorder (FIR) is gathered by the mission computer from aircraft systems. DFIRS
records flight data, cautions, advisories, and spin data. The FIR memory wraps around to the
beginning when the end of memory is reached. Only the last 30 minutes of each flight is retained. The
MC controls the rate and the type of data that is stored. DFIRS data recording starts when both
throttles are advanced past the vertical, launch bar is lowered, ground speed exceeds 50 knots, or
WoffW and airspeed is over 80 knots. DFIRS recording stops 1 minute after WonW, both throttles less
　
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本文鏈接地址：NATOPS Flight Manual 飛行手冊 1(113)