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Gulfstream G200 - Trim System
TRIM SYSTEM
HORIZONTAL STABILIZER TRIM SYSTEMS
General
The variable incidence horizontal stabilizer serves for longitudinal
(pitch) aircraft trim. Two independent electrical trim systems ensure the
ability to trim the aircraft if one system fails.
The stabilizer travel is +2.5° to -9.5° which covers the entire flight and
cg envelopes trim requirements.
Normal System
Trim switches, located on top outboard side of pilot and copilot control
wheels, control normal operation. When either trim switch is moved UP
or DOWN, actuator's primary motor energizes to retract or extend the
actuator to desired position. Limit switches are incorporated in the
actuator to restrict stabilizer travel.
Pitch trim tone (from EICAS) sounds whenever normal system
operates. Autopilot trim is also achieved through the normal system.
Mach Trim
Mach trim is operative when autopilot is disengaged. Mach trim is
activated when ADC mach data indicates that longitudinal trim is
necessary (0.79 M
).
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Summary of Contents for Gulfstream G200
- Page 1 Gulfstream G200 - Trim System TRIM SYSTEM HORIZONTAL STABILIZER TRIM SYSTEMS General The variable incidence horizontal stabilizer serves for longitudinal (pitch) aircraft trim. Two independent electrical trim systems ensure the ability to trim the aircraft if one system fails. The stabilizer travel is +2.5° to -9.5° which covers the entire flight and cg envelopes trim requirements.
- Page 2 Gulfstream G200 - Trim System Override System When the primary drive control fails to operate, pressing PITCH TRIM REL. button, located on the control wheel, provides the following functions: • Disconnects power from trim unit primary channel. • Powers up to the secondary channel.
- Page 3 Gulfstream G200 - Trim System LATERAL TRIM SYSTEM Lateral trim is achieved by the ailerons. An electrical trim actuator mounted near the artificial feel system operates the ailerons through the normal control system. The aileron travel, when operated by the trim system, is 1/3 of full aileron travel.
- Page 4 Gulfstream G200 - Trim System TRIM SYSTEMS CONTROLS AND INDICATORS Pitch Trim Switches (2) - Located on each outboard prong of pilot and copilot control wheels. The switches have three positions: Center - Stops horizontal stabilizer trim operation. NOSE DOWN - Momentary position to trim nose down. Spring loaded to center.
- Page 5 Gulfstream G200 - Trim System RUDDER Trim Switch - Has three positions as follows: Center - Stops rudder trim operation. NOSE R - Momentary position. Trims rudder to right. NOSE L - Momentary position. Trims rudder to left. Page 5...
- Page 6 Gulfstream G200 - Trim System PITCH VERT TRIM SYNCH TRIM AP/SP DISC PILOT CONTROL WHEEL PITCH VERT TRIM SYNCH AP/SP DISC FLAP/SLAT CONTR MONITOR AUTO KRUGER RUDDER BIAS COPILOT CONTROL WHEEL HEAT 1 HEAT 2 CONTR RUDDER AIR BRAKE TRIM...
- Page 7 Gulfstream G200 - Trim System SLATS, KRUEGER AND FLAPS SYSTEMS Each wing is equipped with two-piece trailing edge flap, one piece leading edge slat and one piece krueger flap. The flaps and slats are mounted on and guided by rail and rollers assemblies, driven by ball-screw linear actuators.
- Page 8 Gulfstream G200 - Trim System Reversal of flaps or slats position selection when surface is in motion is not recommended. The system should come to a complete stop prior to reversing flaps or slats travel. If a malfunction occurs in slats extension/retraction system, they may be disabled and bypassed by pressing SLAT BYPASS ARM pushbutton, on the pedestal.
- Page 9 Gulfstream G200 - Trim System Figure 5-31. Slats/Flaps System - Block Diagram Page 9...
- Page 10 Gulfstream G200 - Trim System KRUEGER FLAP Figure 5-32. Slats and Flaps Drive Systems - Schematic Page 10...
- Page 11 Gulfstream G200 - Trim System SLATS/FLAPS SYSTEM CONTROLS AND INDICATORS SLATS/KRUEGER/FLAPS Control Lever - Has five positions as follows: UP - Flaps, krueger flaps and slats are up. DN - Slats and krueger flaps are extended, flaps stay retracted 12°; 20°; 40°; - Slats and krueger flaps stay extended.
- Page 12 Gulfstream G200 - Trim System Caution Messages FLAPS UNBAL - Asymmetry between left and right flaps exceeds 1.2° KRUEGER FAIL - Slats are extended and krueger flaps remain retracted KRUEGER UNBAL - Difference between left and right krueger flaps positions SLATS UNBAL - Asymmetry between left and right slats exceeds 1.75°...
- Page 13 Gulfstream G200 - Trim System FLAP/SLAT CONTR MONITOR AUTO KRUGER RUDDER BIAS HEAT 1 HEAT 2 CONTR RUDDER AIR BRAKE TRIM INBD OUTBD HORZ TRIM AILERON Q FEEL TRIM FLIGHT CONTROL ON PEDESTALL SIDE WALL Figure 5-33. Slats/Krueger/Flaps System Controls...
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