spaschal on DSK3GDR082PROD with CFR

Federal Aviation Administration, DOT

Pt. 27, App. C

(i) The controllability and maneuverability requirements in Subpart B of this
part 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; and
(iii) 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 SectionSection 29.1303, 29.1431, and 29.1433
through Amendment 29-14, with the following exceptions and additions:
(a) Flight and Navigation Instruments. (1) A
magnetic gyro-stablized direction indicator
instead of a 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). For two-pilot
configurations, one pilot-s primary indicator
may be designated for this purpose. If standby batteries are provided, they may be
charged from the aircraft electrical system
if adequate isolation is incorporated.
(b) Miscellaneous requirements. (1) Instrument systems and other systems essential
for IFR flight that could be adversely affected by icing must be adequately protected
when exposed to the continuous and intermittent maximum icing conditions defined
in appendix C of Part 29 of this chapter,
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 crewmember 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.
IX. Rotorcraft Flight Manual. A Rotorcraft
Flight Manual or Rotorcraft Flight Manual
IFR Supplement must be provided and must
contain - 
(a) Limitations. The approved IFR flight envelope, the IFR flightcrew composition, the
revised kinds of operation, and the steepest
IFR precision approach gradient for which
the helicopter is approved;
(b) Procedures. Required information for
proper operation of IFR systems and the recommended procedures in the event of stability augmentation or electrical system
failures; and
(c) Performance. If VYI differs from VY,
climb performance at VYI and with maximum
continuous power throughout the ranges of
weight, altitude, and temperature for which
approval is requested.
X. Electrical and electronic system lightning protection. For regulations concerning
lightning protection for electrical and electronic systems, see Section 27.1316.
[Amdt. 27-19, 48 FR 4389, Jan. 31, 1983, as
amended by Amdt. 27-44, 73 FR 11000, Feb. 29,
2008; Amdt. 27-46, 76 FR 33135, June 8, 2011]

APPENDIX C TO PART 27 - CRITERIA FOR
CATEGORY A
C27.1 General.
A small multiengine rotorcraft may not be
type certificated for Category A operation
unless it meets the design installation and
performance requirements contained in this
appendix in addition to the requirements of
this part.
C27.2 Applicable part 29 sections. The following sections of part 29 of this chapter
must be met in addition to the requirements
of this part:

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