Maintenance Manual XA41/XA42
AMM-XA42-0040-001 C.00
Page
2
Page date:
Chapter 27
25.09.2018
27-00-00 GENERAL
This chapter gives the operation and the adjustment of the flight controls.
It also includes the assembly of the flight controls. Refer to the related chapter for the data on a
specified system.
The standard flight control system of the aircraft is as follows: XA41 with single stick control and XA42
with dual stick control. An elevator on the horizontal stabilizer gives pitch control. Ailerons on the
trailing edge of each wing give roll control. The rudder on the vertical stabilizer gives yaw control.
For the crew members, the aircraft have a control stick and a rudder pedal assembly. Rudder pedal
assemblies are attached as follows: To the fuselage side walls of the XA41 and XA42 rear cockpit, and
to the forward fuselage bulkhead of the XA42 front cockpit. The rudder pedals are adjustable with an
adjuster handle on the rudder pedal assembly. Elevator and aileron controls operate through a system
of push-rods and bell cranks. Cables operate the rudder. An electric actuator operates the trim tab.
The elevator trim tab is operated by an electric actuator and controlled through a switch on the left
side panel.
Figure 27-1: Overview - flight control system XA41 and XA42
Table 27-1: Overview - control surface deflection and play
Ailerons
Elevator
Rudder
Trim tab
Deflection
±30°
±27°
±30°
±3°
Tolerance
+0° -5°
+3° -5°
±3°
±1°
Permitted play*
±1 mm
±1 mm
-
±2 mm
* measured at each trailing edge at the position of maximum chord, while the control sticks are
locked in position. Rudder control: No play is available at the rudder’s trailing edge.
For the measurement form of the control surface deflections, refer to Appendix 7.
Summary of Contents for XA41
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