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The automatic f l i g h t control system (AFCS) provides three-axis flight control,
guidance and s t a b i l i z a t i on using dual-channel computations to drive dual servos
in the r o l l , pitch and yaw axes. The AFCS comprises two complete flight
director systems, an air data system, a two-channel autopilot and a s t a b i l i ty
augmentation system, including yaw damping and Mach trim.
When engaged and coupled to the flight directors, the autopilot controls the
aircraft using the commands generated by either the p i l o t f s or copilot's flight
director computer.
When engaged without a flight director mode selected, manual pitch and roll
commands are inserted using the pitch wheel and turn knob on the autopilot
controller.
When the autopilot is coupled to the flight director, the touch control
steering can be used to manoeuvre the aircraft without disengaging the
autopilot.
Each channel of the three-axis AFCS i s continuously monitored and if a failure
occurs it automatically switches to single channel operation in that axis.
FLIGHT DIRECTOR SYSTEM
The flight director system comprises two complete independent systems (pilotfs
and copilot's). Each system provides a full complement of horizontal and
vertical flight guidance modes, including all radio guidance modes, RNAV
tracking and air data oriented vertical modes.
Each attitude director indicator (ADD has a sphere pitch and roll attitude
presentation. An annunciator panel is located at the top of each ADI to inform
the pilot of mode and submode switching. These panels are constructed so that
no lettering i s visible unless the mode is annunciated.
Each horizontal situation indicator (HSI) operates in conjunction with a
remote, pedestal mounted, heading and course select controller. Each HSI
displays the aircraft's position with respect to various ground-based
navigational aids.
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OPERATING MANUAL
AIR DATA SYSTEM
The air data system receives pitot-static pressures from the pitot-static
system, temperature signals from the total-air-temperature probe and a
barometric setting from the pilot's altimeter. From these inputs, the air data
computer (ADC) computes signals relating to altitude, vertical speed, true
airspeed, Mach number and maximum operating speed that are used to drive the
pilot's altimeter, Mach airspeed indicator, vertical speed indicator,
TAS/SAT/TAT indicator and VNAV computer/controller.
The ADC provides the basic altitude hold and airspeed gain programming
functions, and also vertical speed, airspeed and Mach control functions to the
autopilot, flight director, and stability augmentation systems. Outputs are
also provided for the flap overspeed, stall warning and ATC transponder.
The pilot's altimeter provides a baro-corrected counter-drum pointer display of
the aircraft altitude as determined by the air data computer. Baro set
information from the altimeter is used to correct the air altitude outputs to
the altimeter, VNAV computer/controller and flight director computer altitude
hold functions. The vertical speed indicator provides a pointer display of
vertical speed rates of 0 to +6000 feet per minute.
The Mach/airspeed indicator provides a mechanical counter display of Mach and
servo-driven pointer displays of airspeed (plain white pointer) and maximum
operating airspeed (orange-striped pointer) as computed in the air data
computer. External bugs are provided on the perimeter of the airspeed dial and
can be manually set to desired airspeed references.
The VNAV computer/controller provides for data insertion and display of
altitude alerting, altitude preselect and VNAV information.
AUTOPILOT SYSTEM
The autopilot is a two-axis system designed for fail/passive operation
throughout the flight regime. Duplex servos provide continuous automatic
control and hardover protection following any single failure when both channels
are engaged. If a failure occurs, there is no need to disengage, as there is
no significant flight path deviation; the aircraft continues to track commands
and the pilot is alerted that a failure has occurred. Automatic channel
switching prevents aircraft reactions when an autopilot malfunction occurs
during out-of-trim conditions.
STABILITY AUGMENTATION SYSTEM (Figure 2)
The stability augmentation system provides dual channel yaw damping and single
channel Mach trim. The main components of the system are the stability
augmentation computer, linear yaw actuators, stability augmentation control
panel and a total position transducer.
SECTION 4
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OPERATING MANUAL
　
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