Gulfstream G550 Operating Manual Download

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•

The one half (½) second electrical delay

D. Aileron Position Sensing:

The position of each aileron is sensed by a Rotary Variable Displacement
Transducer (RVDT). The RVDTs are installed at the hinge point of the
ailerons, and transmit an electrical signal proportional to the displacement
of the aileron from the neutral position. The signals are communicated to
the autopilot processor modules in the MAUs where, in conjunction with the
Actuator Input / Output Processors (AIOPs), autopilot commands are
formulated for the electric servos in the cable control linkage for the
ailerons. The MAUs also provide aileron position information to the MWS
for generation of the graphic display of control surface position on the Flight
Controls 2/3 synoptic page.

E. Aileron Trim System:

(See Figure 12.)

Only one trim tab is installed for both ailerons, since both the left and right
ailerons work in symmetrically opposite directions through the cable
linkage and mechanical arm connecting both control yokes. The trim tab is
located on the left aileron and is made of carbon epoxy fabric. The aileron
trim tab is a manually operated by cable linkage from the aileron trim wheel
on the aft section of the cockpit center pedestal to the trim tab bellcrank
actuator. Moving the trim wheel to the left positions the trim tab down into
the airstream, deflecting the left aileron up to reduce lift on the left wing,
moving the wing downward. At the same time the connecting linkage
moves the right aileron down to increase lift on the right wing and move the
wing up. The range of travel for the aileron trim tab is 15 degrees up or
down.

The aileron trim tab actuator has ceramic element that is heated to prevent
the actuator from freezing. The actuator is maintained at a constant
temperature of 175°

20°F. The heater is controlled by the AIL TRIM HEAT

circuit breaker on the Right Electronic Equipment Rack (REER) and
receives power from the right main AC bus.

The trim tab is also equipped with a RVDT to provide information to MAU
#1 for the autopilot processor and the MWS for graphic display on synoptic
and system windows.

F. Flight Spoiler Roll Augmentation:

The aircraft is equipped with three spoiler panels on the top surface of each
wing, just forward of the flaps. The spoiler panels are rectangular in shape
and are hinged at the forward edge to allow the panels to pivot upward, into
the airflow over the wing to disrupt lift. The spoiler panels are hydraulically
powered by actuators supplied with three thousand (3,000) psi pressure
from both hydraulic systems. Loss of one hydraulic system will not effect
spoiler operation since a single system supplies sufficient pressure for full
spoiler activation. The spoilers serve three functions:

•

As speed brakes, all six spoilers (three on each wing) are extended
to disrupt airflow over the wing and decrease lift in order to slow the
aircraft and/or increase descent rates

•

On landing, with weight on the wheels, all six panels (three on each
wing) extend to provide aerodynamic drag to aid in slowing the
aircraft

OPERATING MANUAL

PRODUCTION AIRCRAFT SYSTEMS

2A-27-00

Page 39

August 14/03

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