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|  MIL-C-18244A(WEP)
3.1.1.5.4.3
Groundspeed Hold - Where groundspeed hold is a system requirement,
provision shall be made to insert radar groundspeed signals to the cyclic pitch and roll control,
After engagement of the groundspeed hold mode, the groundspeed existing at the time of engagement
shall be held in calm air within + 1 knot or + 2 percent, whichever is greater.
Groundspeed Select - Where groundspeed select is a system requirement
3.1.1.5.4.4
the transition from the airspeed existing at the moment of engagement to the selected airspeed shall
be smooth, and the transient of the groundspeed shall not exhibit a first overshoot higher than 20
percent of the difference between the selected groundspeed and the groundspeed existing at the
moment of engagement.
Vernier Control for Hovering - Vernier control shall be provided for
3.1.1.5.4.5
accurate positioning of the aircraft during hovering, unless control commensurate with the minimum
accuracy requirements can be obtained with the regular controls.
Stability Augmentation - The stability augmentation system shall provide,
3.1.1.5.4.6
as a minimum, those flying qualities specified in Specification MIL-H-8501.
Attitude Hold, Pitch, Roll and Yaw - During the attitude hold mode, the
3.1.1.5.4.7
attitude, in calm air, shall be kept within 1 degree of the referernce attitude. After the automatic
flight control system has been overpowered to change the attitude by 5 degrees, the helicopter shall
return to the reference attitude with the first overshoot not exceeding 20 percent.
Altitude Stabilization -
3.1.1.5.4.8
Barometric Altitude Stabilization - The requirements of 3.1.5.2.6 shall be
3.1.1.5.4.8.1
met within the altitude limits of the aircraft when the aircraft is outside the ground effect. In addition,
the transient after, 2 displacement of approximately 100 feet shall not exhibit a first overshoot in
excess of 20 percent.
Radar Altitude Stabilization - The operational range of the radar altitude
3.1.1.5.4.8.2
control mode shall be as specified in the applicable system specification. Within this range, the
aircraft shall be controlled to the indicated radar altitude with an accuracy, in calm air, of + 7 feet
or + 10 percent, whichever is greater.
Altitude Select - Where altitude select is a system requirement, the
3.1.1.5.4.8.3
transition from any engaged altitude within the operational range of the altitude stabilization mode to
the preselected altitude shall be smooth and shall not show a first overshoot in excess of 20 percent.
Sonar Coupled Operation - Where sonar coupled operation is a system
3.1.1.5.4.9
requirement, the automatic flight control system shall meet the following requirements for submerged
sonar ball and calm air.
Altitude Hold - The preset altitude shall be held to within + 3 feet or 10
3.1.1.5.4.9.1
percent of the preset altitude, whichever is greater. The transient, following a displacement in
altitude of approximately 10 feet, shall not exhibit a first overshoot exceeding 20 percent of the
initial displacement,
Transiational Stability - The cable angle shall be kept within 2 degrees.
3.1.1.5.4.9.2
The first overshoot in the transient following a cable angle displacement of approximately 10 degrees
from the vertical shall not exceed 30 percent of the initial displacement.
Additional Requirements for Convertiplane, VTOL Aircraft - The require-
3.1.1.5.5
ments of these special type aircraft are, in most cases, identical to the requirements for other
conventional and rotary wing aircraft.
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