SYS and R SYS) at 3000 psi each. In the event of a single hydraulic system
failure, the actuators will remain powered by the operative hydraulic system.
2. Description of Subsystems, Units and Components:
A. Automatic Hardover Prevention:
Each aileron actuator incorporates a hardover prevention system which
compares inputs and outputs. If inputs to, and outputs from, either actuator
do not agree for over 0.5 second, hydraulic pressure from both hydraulic
systems to both actuators is shut off simultaneously and a message will be
displayed on the Crew Alerting System (CAS) display. The ailerons are still
operative, but without benefit of hydraulic boost. The hardover prevention
system receives power from the Left and Right Essential DC Bus.
B. Aileron Control Separation:
The aileron control systems are dual and separable. In the unlikely event
that a single aileron control system were to become jammed, an aileron
disconnect system provides the means to separate the left and right
ailerons from each other. This is accomplished through the use of an
aileron disconnect system, located on the right side of the cockpit center
pedestal and labeled AIL DISC on its protective cover.
The aileron disconnect system consists of the protective cover, the aileron
disconnect handle (labeled AIL DISC) and a power assist trigger (labeled
LIFT). If a jammed aileron is detected, the protective cover is raised and
the AIL DISC handle is pulled. With the handle fully extended, the pilot’s
and copilot’s control wheels are separated and the aileron systems are fully
isolated and independent – the pilot controls the left aileron and the copilot
controls the right aileron. The immovable aileron side will remain
immovable and the movable side is now free to be used to control the
aircraft. If the power assist trigger was NOT used to actuate the AIL DISC
handle, the aileron disconnect system can be reset at the discretion of the
flight crew.
If the force required to pull the AIL DISC handle is too great, the power
assist trigger, located under the AIL DISC handle, is pulled. This actuates a
gas-spring cartridge, providing between 110 to 150 pounds of controlled
force to fully extend the handle and separate the aileron control systems.
NOTE:
If the power assist trigger was used to actuate the AIL
DISC handle, the system cannot be reset without the
use of special tools.
C. Flight Spoiler Supplementation:
The outboard two spoilers on each wing act as flight spoilers in conjunction
with the ailerons to improve roll response of the aircraft. Their function as
supplements to the ailerons is fully automatic and transparent to the crew.
Spoiler travel will vary in accordance with the control wheel inputs up to a
maximum of 47(±3) degrees upward deflection. The spoilers are
hydraulically powered, normally by both L SYS and R SYS, but will function
normally with only one source of hydraulic pressure. The operation of flight
spoilers (as well as ground spoilers and speed brakes) can be inhibited
using the SPOILER CONTROL switch, located on the left side of the
OPERATING MANUAL
PRODUCTION AIRCRAFT SYSTEMS 2A-27-00
Page 23
May 22/01
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