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737-600/700/800/900 AIRCRAFT MAINTENANCE MANUAL
22-31-00-007
* GMT/Date.
* BITE test information.
The autothrottle converts the target N1 values from the FMC to
an equivalent TRA target. The target N1 rating is dependent on
the FMC engaged mode.
Gross weight is used in the go around control logic and
approach control logic.
Minimum airspeed is the lowest airspeed that is acceptable
during VNAV operation.
FMC altitude from the FMC is used for anticipation of altitude
acquire during VNAV operation.
SAT is used to calculate a backup TRA limit value.
The FMC mode discretes are used to determine control law
gains and limits.
GMT and date are used in BITE for fault data storage.
BITE data is used for interactive display on the CDUs.
Radio Altimeter (RA)
The RA receiver/transmitters (R/Ts) send radio altitude to the A/
T. The A/T uses this data to determine control law gains during
approach and as a backup for flare retard.
Autothrottle Servo Motor (ASM)
The ASMs sends this data to the A/T for feedback:
* Servo status
* Measured rate
* Measured torque.
Servo status is the current status of the ASM.
Measured rate is the actual rate (deg/sec) that the ASMs are
moving the thrust levers.
Measured torque is the actual torque that is being exerted to
move the thrust levers.
Electronic Engine Control (EEC)
Each EEC channel sends this data to the A/T:
* Thrust resolver angle (TRA)
* N1 command indicated
* TRA for max forward idle
* Estimated corrected thrust
* TRA for actual N1
A/T SYSTEM - DIGITAL INPUT INTERFACE
EFFECTIVITY
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BOEING PROPRIETARY - Copyright#- Unpublished Work - See title page for details.
737-600/700/800/900 AIRCRAFT MAINTENANCE MANUAL
22-31-00-007
* TRA for N1 target
* TRA for N1 max
* TRA for 5 degree/sec response.
Thrust resolver angle is used by the autothrottle to calculate an
N1 command.
N1 command indicated is used to set a throttle position using
the error between the target N1 (from the FMC) and the
commanded N1 from the EEC.
TRA for maximum forward flat is the throttle angle below which
the engine is in the idle range.
Estimated corrected thrust is used in the reduced go around
control logic.
TRA for actual N1 and TRA for N1 target are used in the N1
mode control logic.
TRA for N1 maximum is used as a reversion limit in the event
that the airplane is dispatched without an operative FMC and as
a protection from excessive throttle angles.
TRA for 5 degree/sec response is used in the retard control
logic.
Air Data Inertial Reference Unit (ADIRU)
The ADIRUs send this air data reference data to the A/T:
* Computed airspeed (CAS)
* Maximum allowable airspeed (VMO/MMO)
* Uncorrected altitude
* Baro corrected altitude
* Mach
* Static air temperature (SAT)
* Total air temperature (TAT)
* Altitude rate
* Static pressure
* Total pressure
* True airspeed
* Angle of attack (AOA).
Computed airspeed is used in the speed mode control logic.
VMO/MMO is used in the speed mode control logic.
Uncorrected altitude is used for autothrottle gain scheduling
and in the maximum allowed N1 calculation.
Mach number is used for speed mode Mach control, weight and
drag calculations.
SAT is used to calculate a backup TRA limit value.
Altitude rate is used in wind detection calculations.
A/T SYSTEM - DIGITAL INPUT INTERFACE
EFFECTIVITY
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BOEING PROPRIETARY - Copyright#- Unpublished Work - See title page for details.
737-600/700/800/900 AIRCRAFT MAINTENANCE MANUAL
22-31-00-007
Static pressure is used for normalizing thrust effects with
altitude.
True airspeed is used for calculating the TAS/CAS conversion.
Angle of attack is used in calculating a backup weight for alpha
floor calculation.
The ADIRUs send this inertial reference data to the A/T:
* Pitch attitude
* Roll attitude
* Body longitudinal acceleration
* Body normal acceleration
* Groundspeed
* Body pitch rate
* Vertical speed.
Pitch attitude is used for compensating the longitudinal
acceleration signal for wind detection.
Roll attitude is used for thrust compensation during airplane
turns.
Body longitudinal acceleration is used for control law damping
and wind detection.
Body normal acceleration is used to derive a vertical speed
signal for wind detection.
Groundspeed is used for cruise speed control to indicate when
　
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