Code of Federal Regulations - Title 14

830

14 CFR Ch. I (1–1–14 Edition)

Pt. 29, App. C

must be designed so that the standby bat-
teries may not be used for engine starting.

(b)

Miscellaneous requirements. (1) Instru-

ment systems and other systems essential
for IFR flight that could be adversely af-
fected by icing must be provided with ade-
quate 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 dis-
connect 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 instru-
ment 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 ad-
versely 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 op-
erating system;

(ii) Additional instruments, systems, or

equipment may not be connected to an oper-
ating system for a second pilot unless provi-
sions are made to ensure the continued nor-
mal functioning of the required instruments
in the event of any malfunction of the addi-
tional instruments, systems, or equipment
which is not shown to be extremely improb-
able;

(iii) The equipment, systems, and installa-

tions 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 ad-
ditional crew-member action, after any sin-
gle failure or combination of failures that is
not shown to be extremely improbable; and

(iv) For single-pilot configurations, instru-

ments which require a static source must be
provided with a means of selecting an alter-
nate source and that source must be cali-
brated.

(6) In determining compliance with the re-

quirements of § 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 § 29.1381(a),
thunderstorm lights which provide high in-
tensity white flood lighting to the basic
flight instruments must be provided. The
thunderstorm lights must be installed to
meet the requirements of § 29.1381(b).

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 en-

velope, 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 rec-
ommended procedures in the event of sta-
bility augmentation or electrical system
failures; and

(c)

Performance. If V

differs from V

climb performance at V

and with maximum

continuous power throughout the ranges of
weight, altitude, and temperature for which
approval is requested.

[Amdt. 29–21, 48 FR 4392, Jan. 31, 1983, as
amended by Amdt. 29–31, 55 FR 38967, Sept.
21, 1990; 55 FR 41309, Oct. 10, 1990; Amdt. 29–
40, 61 FR 21908, May 10, 1996; Amdt. 29–51, 73
FR 11002, Feb. 29, 2008]

PPENDIX

ART

29—I

CING

ERTIFICATION

(a)

Continuous maximum icing. The max-

imum continuous intensity of atmospheric
icing conditions (continuous maximum
icing) is defined by the variables of the cloud
liquid water content, the mean effective di-
ameter of the cloud droplets, the ambient air
temperature, and the interrelationship of
these three variables as shown in Figure 1 of
this appendix. The limiting icing envelope in
terms of altitude and temperature is given in
Figure 2 of this appendix. The interrelation-
ship of cloud liquid water content with drop
diameter and altitude is determined from
Figures 1 and 2. The cloud liquid water con-
tent for continuous maximum icing condi-
tions of a horizontal extent, other than 17.4
nautical miles, is determined by the value of
liquid water content of Figure 1, multiplied
by the appropriate factor from Figure 3 of
this appendix.

(b)

Intermittent maximum icing. The inter-

mittent maximum intensity of atmospheric
icing conditions (intermittent maximum
icing) is defined by the variables of the cloud
liquid water content, the mean effective di-
ameter of the cloud droplets, the ambient air
temperature, and the interrelationship of
these three variables as shown in Figure 4 of
this appendix. The limiting icing envelope in
terms of altitude and temperature is given in
Figure 5 of this appendix. The interrelation-
ship of cloud liquid water content with drop
diameter and altitude is determined from
Figures 4 and 5. The cloud liquid water con-
tent for intermittent maximum icing condi-
tions of a horizontal extent, other than 2.6
nautical miles, is determined by the value of
cloud liquid water content of Figure 4 multi-
plied by the appropriate factor in Figure 6 of
this appendix.

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