(a) Each automatic pilot system must be designed so that the automatic
pilot can --
(1) Be sufficiently overpowered by one pilot to allow control of the
(2) Be readily and positively disengaged by each pilot to prevent it
from interfering with the control of the rotorcraft.
(b) Unless there is automatic synchronization, each system must have a
means to readily indicate to the pilot the alignment of the actuating
device in relation to the control system it operates.
(c) Each manually operated control for the system's operation must be
readily accessible to the pilots.
(d) The system must be designed and adjusted so that, within the range
of adjustment available to the pilot, it cannot produce hazardous loads on
the rotorcraft, or create hazardous deviations in the flight path, under
any flight condition appropriate to its use, either during normal
operation or in the event of a malfunction, assuming that corrective
action begins within a reasonable period of time.
(e) If the automatic pilot integrates signals from auxiliary controls
or furnishes signals for operation of other equipment, there must be
positive interlocks and sequencing of engagement to prevent improper
(f) If the automatic pilot system can be coupled to airborne navigation
equipment, means must be provided to indicate to the pilots the current
mode of operation. Selector switch position is not acceptable as a means