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|  MIL-C-18244A(WEP)
Cockpit Control Motion - The control surface motion required to accomplish
3.1.1.3.7
augmentation functions shall not be reflected aircraft's cockpit control. In addition there shall
be no random spurious stick motion associated with any automatic flight control mode.
Automatic Trim - Means shall be provided to automatically reduce the
3.1.1.3.8
control system trim error to essentially zero. Such a means shall operate at a rate which does not
significantly affect the transient performance of the automatic flight control system. Automatic trim
shall be operational during the guidance and pilot assist modes only.
Manual Trim - Powered manual trim shall be made inoperative when the
3.1.1.3.9
automatic flight control system is engaged, The circuitry shall be arranged so as to minimize the
effect of a failure in the automatic flight control system on the manual trim operation after the auto-
matic flight control system is disengaged,
Control Stick (or Wheel) Maneuvering - Where control stick maneuvering is
3.1.1.3.10
a system requirment, provisions shall be made so that the pilot shall have full capability to maneuver
the aircraft within control forces and maneuver limits specfied in Specification MIL-F-8785 or the
applicable system specification. This maneuvering capability shall be possible at any time when the
automation flight control system is engaged by using the normal aircraft controls. Unless otherwise
specified in the applicable system specification, design shall be such as to allow the pilot to super-
impose his control stick maneuvering commands over those of external guidance system signals.
Cross control between the pitch and roll force sensors shall not exceed one percent of the applied
forces.
Vernier Control - When control stick steering is a requirement, means shall
3.1.1.3.10.1
be provided to apply vernier attitude control unless changes commensurate with the minimum maneu-
ver requirements can be added by control stick steering commands.
Control Stick Maneuvering Modes - Control stick steering modes shall
3.1.1.3.10.2
operate as follows:
(a) Control Augmentation Mode - This mode shall provide those
features as required by 3.1.1.1.1. The pilot's force on the
stick or wheel shall superimpose the commanded maneuver
signal onto the augmentation signal,
(b) Pilot Relief Mode - This mode shall provide the augmentation
features of part (a) above and in addition those outlined by
3.1.1.1.2, parts (a) and (b).
Interlocks - Interlocks to prevent engagement of the automatic flight control
3.1.1.3.11
system in the absence of proper hydraulic pressure, electrical power of the proper voltage, proper
gyro rotor speed, adequate warm-up, and normal overall operation shall be provided as part of the
automatic flight control system. It shall not be possible to engage incompatible functions. Interlocks
shall also be provided tO prevent power from being applied to the system if lack of power to the servo
units prevents synchronization. In the event of failure of any one of the hydraulic or electrical power
sources, the automatic flight control system shall become disengaged within 0.3 second.
Structural Protection - Means shall be provided to prevent automatic flight
3.1.1.3.12
control system malfunctions from producing airplane loads in excess of the airplane limit load factor.
Due to consideration shall be given tO the fact that during rapid roll maneuvers the load factor of one
of the wings is higher than than determined by the center of gravity acceleration. Mess proven
unnecessary, the protective device for high roll performance aircraft shall respond to an appropriate
combination of lift, roll velocity, and roll acceleration.
Ground Check - The structual protective means shall be such that it can be
3.1.1.3.12.1
conveniently ground-checked by the pilot.
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