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Computer
simulation
The NTSB computer workstation-based flight simulation software
used flight controls, aerodynamic characteristics, and engine
models (developed by Boeing) to derive force and moment time
histories of the airplanes, which can be converted into airplane
motion
Control wheel
steering mode
A position on the two autopilot flight control computers that, when
engaged, allows the autopilot to maneuver the airplane through the
autofilight system in response to control pressure, similar that
required for manual flight, applied by either pilot. The use of
control wheel steering does not disengage the autopilot.
Cross-coupled The ability of the aerodynamic motion about an airplane's control
axes to constantly interact and affect each other in flight.
Crossover speed The speed below which the maximum roll control (full roll
authority provided by control wheel input) can no longer counter
the yaw / roll effects of a rudder deflected to its blowdown limit.
Directional
control
The function that is normally performed by the rudder by pilot
input or yaw damper input (also known as yaw control)
E&E bay An airplane compartment that contains electrical and electronic
components.
Elevator An aerodynamic control surface to the back of the horizontal
stabilizer that moves the airplane's nose up and down to cause the
airplane to climb or descend.
Empennage The tail section of an airplane, including stabilizing and flight
control surfaces
Flap An extendable aerodynamic surface usually located at the trailing
xi
edge of an airplane wing.
G A unit of measurement. One G is equivalent to the acceleration
caused by the earth's gravity (32.174 feet/sec2)
Galling A condition in which microscopic projections or asperities bond at
the sliding interface under very high local pressure. Subsequently,
the sliding forces fracture the bonds, tearing metal from one
surface and transferring it to the other.
Heading The direction (expressed in degrees between 001 and 360) in which
the longitudinal axis of an airplane is point, in relation to north
Hinge moment The tendency of a force to produce movement about a hinge.
Specifically the tendency of the aerodynamic forces acting on a
control surface
Hydraulic fluid Liquid used to transmit and distribute forces to various airplane
components that are being actuated.
Hydraulic
pressure limiter
A device incorporated in the design of the main rudder PCU on 737
next generation (NG) series airplanes to reduce the amount of
rudder deflection when active. It is commanded to limit hydraulic
system A pressure (using a bypass valve) as the airspeed is
increased to greater than 137 knots, and it is reset as the airspeed is
decreased to less than 139 knots.
Hydraulic
pressure reducer
A modification on 737-100 through -500 series airplanes to reduce
the amount of rudder authority available during those phases of
flight when large rudder deflections are not required. The pressure
reducer, added to hydraulic system A near the rudder PCU, will
lower the hydraulic pressure from 3,000 to 1,000 pounds psi on
737-300, -400, and -500 series airplanes or to 1,400 psi on 737-
100, and -200 series airplanes.
Hydraulic system
A
For 737-300, -400, and -500 series airplanes: A system that
includes an engine-drive hydraulic pump and an electrically
powered pump that provides power for the ailerons, rudder,
elevators, landing gear, normal nosewheel steering, alternate
brakes, inboard flight spoilers, left engine thrust reverser, ground
spoilers, the system A autopilot, and the autoslats through the
power transfer unit
Hydraulic system
B
For 737-300, -400, and -500 series airplanes: A system that
includes an engine-drive hydraulic pump and an electrically
powered pump that provides power for the ailerons, rudder,
elevators, trailing edge flaps, leading edge flaps and slats, autoslats,
normal brakes, outboard flight spoilers, right thrust reverse, yaw
damper, the system B autopilot, autobrakes, landing gear transfer
unit, and alternate nose-wheel steering (if installed).
Input shaft of the
737 main rudder
PCU
When rudder motion is commanded, this device moves the primary
and secondary dual-concentric servo valve slides by way of the
primary and secondary internal summing levers to connect
hydraulic pressure and return circuits from hydraulic systems A
and B so that hydraulic pressure is ported to the appropriate slides
of the dual tandem actuator piston to extend or retract the main
rudder PCU piston rod
Interpolation The determination, or approximation of unknown values based on
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本文链接地址：
NTSC Aircraft Accident Report SILKAIR FLIGHT MI 185 BOEING B(4)
