spaschal on DSK3GDR082PROD with CFR

Federal Aviation Administration, DOT

Pt. 29, App. B

(d) Any oscillation having a period of 20
seconds or more may not achieve double amplitude in less than 20 seconds.
(e) Any aperiodic response may not achieve
double amplitude in less than 9 seconds.
VII. Stability Augmentation System (SAS)
(a) If a SAS is used, the reliability of the
SAS must be related to the effects of its failure. Any SAS failure condition that would
prevent continued safe flight and landing
must be extremely improbable. It must be
shown that, for any failure condition of the
SAS that is not shown to be extremely improbable - 
(1) The helicopter is safely controllable
when the failure or malfunction occurs at
any speed or altitude within the approved
IFR operating limitations; and
(2) The overall flight characteristics of the
helicopter allow for prolonged instrument
flight without undue pilot effort. Additional
unrelated probable failures affecting the control system must be considered. In addition - 
(i) The controllability and maneuverability requirements in Subpart B must be
met throughout a practical flight envelope;
(ii) The flight control, trim, and dynamic
stability characteristics must not be impaired below a level needed to allow continued safe flight and landing;
(iii) For Category A helicopters, the dynamic stability requirements of Subpart B
must also be met throughout a practical
flight envelope; and
(iv) The static longitudinal and static directional stability requirements of Subpart
B must be met throughout a practical flight
envelope.
(b) The SAS must be designed so that it
cannot create a hazardous deviation in flight
path or produce hazardous loads on the helicopter during normal operation or in the
event of malfunction or failure, assuming
corrective action begins within an appropriate period of time. Where multiple systems are installed, subsequent malfunction
conditions must be considered in sequence
unless their occurrence is shown to be improbable.
VIII. Equipment, systems, and installation.
The basic equipment and installation must
comply with Subpart F of Part 29 through
Amendment 29-14, with the following exceptions and additions:
(a) Flight and navigation instruments. (1) A
magnetic gyro-stabilized direction indicator
instead of the gyroscopic direction indicator
required by Section 29.1303(h); and
(2) A standby attitude indicator which
meets the requirements of SectionSection 29.1303(g)(1)
through (7), instead of a rate-of-turn indicator required by Section 29.1303(g). If standby batteries are provided, they may be charged
from the aircraft electrical system if adequate isolation is incorporated. The system

must be designed so that the standby batteries may not be used for engine starting.
(b) Miscellaneous requirements. (1) Instrument systems and other systems essential
for IFR flight that could be adversely affected by icing must be provided with adequate ice protection whether or not the
rotorcraft is certificated for operation in
icing conditions.
(2) There must be means in the generating
system to automatically de-energize and disconnect from the main bus any power source
developing hazardous overvoltage.
(3) Each required flight instrument using a
power supply (electric, vacuum, etc.) must
have a visual means integral with the instrument to indicate the adequacy of the power
being supplied.
(4) When multiple systems performing like
functions are required, each system must be
grouped, routed, and spaced so that physical
separation between systems is provided to
ensure that a single malfunction will not adversely affect more than one system.
(5) For systems that operate the required
flight instruments at each pilot-s station - 
(i) Only the required flight instruments for
the first pilot may be connected to that operating system;
(ii) Additional instruments, systems, or
equipment may not be connected to an operating system for a second pilot unless provisions are made to ensure the continued normal functioning of the required instruments
in the event of any malfunction of the additional instruments, systems, or equipment
which is not shown to be extremely improbable;
(iii) The equipment, systems, and installations must be designed so that one display of
the information essential to the safety of
flight which is provided by the instruments
will remain available to a pilot, without additional crew-member action, after any single failure or combination of failures that is
not shown to be extremely improbable; and
(iv) For single-pilot configurations, instruments which require a static source must be
provided with a means of selecting an alternate source and that source must be calibrated.
(6) In determining compliance with the requirements of Section 29.1351(d)(2), the supply of
electrical power to all systems necessary for
flight under IFR must be included in the
evaluation.
(c) Thunderstorm lights. In addition to the
instrument lights required by Section 29.1381(a),
thunderstorm lights which provide high intensity white flood lighting to the basic
flight instruments must be provided. The
thunderstorm lights must be installed to
meet the requirements of Section 29.1381(b).
IX. Rotorcraft Flight Manual. A Rotorcraft
Flight Manual or Rotorcraft Flight Manual
IFR Supplement must be provided and must
contain - 

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