Pt. 135, App. B

14 CFR Ch. I (1-1-19 Edition)

(3) In determining the probable operating
combinations and durations of essential
loads for the power failure conditions described in paragraphs (1) and (2) of this paragraph, it is permissible to assume that the
power loads are reduced in accordance with a
monitoring procedure which is consistent
with safety in the types of operations authorized.
60. Ventilation. The ventilation system of
the airplane must meet FAR 23.831, and in
addition, for pressurized aircraft, the ventilating air in flight crew and passenger compartments must be free of harmful or hazardous concentrations of gases and vapors in
normal operation and in the event of reasonably probable failures or malfunctioning of
the ventilating, heating, pressurization, or
other systems, and equipment. If accumulation of hazardous quantities of smoke in the
cockpit area is reasonably probable, smoke
evacuation must be readily accomplished.
Electrical Systems and Equipment
61. General. The electrical systems and
equipment of the airplane must meet FAR
23.1351, and the following:
(a) Electrical system capacity. The required
generating capacity, and number and kinds
of power sources must - 
(1) Be determined by an electrical load
analysis; and
(2) Meet FAR 23.1301.
(b) Generating system. The generating system includes electrical power sources, main
power busses, transmission cables, and associated control, regulation and protective devices. It must be designed so that - 
(1) The system voltage and frequency (as
applicable) at the terminals of all essential
load equipment can be maintained within
the limits for which the equipment is designed, during any probable operating conditions;

(2) System transients due to switching,
fault clearing, or other causes do not make
essential loads inoperative, and do not cause
a smoke or fire hazard;
(3) There are means, accessible in flight to
appropriate crewmembers, for the individual
and collective disconnection of the electrical
power sources from the system; and
(4) There are means to indicate to appropriate crewmembers the generating system
quantities essential for the safe operation of
the system, including the voltage and current supplied by each generator.
62. Electrical equipment and installation.
Electrical equipment, controls, and wiring
must be installed so that operation of any
one unit or system of units will not adversely affect the simultaneous operation of
any other electrical unit or system essential
to the safe operation.
63. Distribution system. (a) For the purpose
of complying with this section, the distribution system includes the distribution busses,
their associated feeders, and each control
and protective device.
(b) Each system must be designed so that
essential load circuits can be supplied in the
event of reasonably probable faults or open
circuits, including faults in heavy current
carrying cables.
(c) If two independent sources of electrical
power for particular equipment or systems
are required under this appendix, their electrical energy supply must be ensured by
means such as duplicate electrical equipment, throwover switching, or multichannel
or loop circuits separately routed.
64. Circuit protective devices. The circuit
protective devices for the electrical circuits
of the airplane must meet FAR 23.1357, and
in addition circuits for loads which are essential to safe operation must have individual and exclusive circuit protection.

APPENDIX B TO PART 135 - AIRPLANE FLIGHT RECORDER SPECIFICATIONS
Parameters

Range

Installed system 1 minimum
accuracy (to recovered data)

Relative time (from recorded
on prior to takeoff).
Indicated airspeed ..................

25 hr minimum ...............

Section0.125% per hour .................

1 ........................

1 sec.

Vso to VD (KIAS) .............

1 ........................

1% 3.

Altitude ....................................

1 ........................

25 to 150

Magnetic heading ...................
Vertical acceleration ...............

Section1,000 ft. to max cert.
alt. of A/C.
360Section ................................
Section3g to + 6g ...................

Section5% or Section10 kts., whichever is
greater. Resolution 2 kts.
below 175 KIAS.
Section100 to Section700 ft. (see Table 1,
TSO C51-a).
Section5Section .........................................
Section0.2g in addition to Section0.3g
maximum datum.

1Section
0.03g.

Longitudinal acceleration ........

Section1.0g ...............................

1 ........................
4 (or 1 per second where
peaks, ref. to
1g are recorded).
2 ........................

Pitch attitude ...........................

100% of usable ..............

1 ........................

0.8Section

Section1.5% max. range excluding
datum error of Section5%.
Section2Section .........................................

Sampling interval (per second)

Resolution 4
read out

0.01g.

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