INSTALLATION INSTRUCTIONS AF200-007 - REV E
DATE 2/26/2015
Airfilm Camera Systems
Page
24
of
31
6245 Aerodrome Way Hangar No. 2
Georgetown, Ca 95634
6.3.3 Findings
Satisfactory _________ Altitude Band HP ________ Fuel Gage Reading ________
6.4 FAR § 29.143 Controllability and Maneuverability
6.4.1 Applicable
Regulation
(a) The rotorcraft must be safely controllable and maneuverable -
(1) During steady flight; and
(2) During any maneuver appropriate to the type, including -
(i) Takeoff;
(ii) Climb;
(iii) Level flight;
(iv) Turning flight;
(v) Glide
(vi) Landing (power on and power off);
(b) The margin of cyclic control must allow satisfactory roll and pitch control at
VNE with -
(1) Critical weight;
(2) Critical center of gravity;
(3) Critical rotor rpm; and
(4) Power off (except for helicopters demonstrating compliance with paragraph (f) of
this section) and power on.
(c) A wind velocity of not less than 17 knots must be established in which the
rotorcraft can be operated without loss of control on or near the ground in any maneuver
appropriate to the type (such as crosswind takeoffs, sideward flight, and rearward flight),
with -
(1) Critical weight;
(2) Critical center of gravity;
(3) Critical rotor rpm; and
(4) Altitude, from standard sea level conditions to the maximum altitude capability of
the rotorcraft or 7,000 feet, whichever is less.
(d) The rotorcraft, after failure of one engine in the case of multiengine rotorcraft
that meet Transport Category A engine isolation requirements, or complete engine failure
in the case of other rotorcraft, must be controllable over the range of speeds and altitudes
for which certification is requested when such power failure occurs with maximum
continuous power and critical weight. No corrective action time delay for any condition
following power failure may be less than -
(1) For the cruise condition, one second, or normal pilot reaction time (whichever is
greater); and
(2) For any other condition, normal pilot reaction time.
