524
14 CFR Ch. I (1–1–19 Edition)
Pt. 135, App. B
(3) In determining the probable operating
combinations and durations of essential
loads for the power failure conditions de-
scribed in paragraphs (1) and (2) of this para-
graph, 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 au-
thorized.
60.
Ventilation.
The ventilation system of
the airplane must meet FAR 23.831, and in
addition, for pressurized aircraft, the ven-
tilating air in flight crew and passenger com-
partments must be free of harmful or haz-
ardous concentrations of gases and vapors in
normal operation and in the event of reason-
ably probable failures or malfunctioning of
the ventilating, heating, pressurization, or
other systems, and equipment. If accumula-
tion 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 sys-
tem includes electrical power sources, main
power busses, transmission cables, and asso-
ciated control, regulation and protective de-
vices. 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 de-
signed, during any probable operating condi-
tions;
(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 appro-
priate crewmembers the generating system
quantities essential for the safe operation of
the system, including the voltage and cur-
rent 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 ad-
versely 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 distribu-
tion 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 elec-
trical energy supply must be ensured by
means such as duplicate electrical equip-
ment, 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 es-
sential to safe operation must have indi-
vidual and exclusive circuit protection.
A
PPENDIX
B
TO
P
ART
135—A
IRPLANE
F
LIGHT
R
ECORDER
S
PECIFICATIONS
Parameters Range
Installed system
1
minimum
accuracy (to recovered data)
Sampling inter-
val (per second)
Resolution
4
read out
Relative time (from recorded
on prior to takeoff).
25 hr minimum ...............
±
0.125% per hour .................
1 ........................
1 sec.
Indicated airspeed ..................
V
so
to V
D
(KIAS) .............
±
5% or
±
10 kts., whichever is
greater. Resolution 2 kts.
below 175 KIAS.
1 ........................
1%
3
.
Altitude ....................................
¥
1,000 ft. to max cert.
alt. of A/C.
±
100 to
±
700 ft. (see Table 1,
TSO C51–a).
1 ........................
25 to 150
Magnetic heading ...................
360
°
................................
±
5
°
.........................................
1 ........................
1
°
Vertical acceleration ...............
¥
3g to + 6g ...................
±
0.2g in addition to
±
0.3g
maximum datum.
4 (or 1 per sec-
ond where
peaks, ref. to
1g are re-
corded).
0.03g.
Longitudinal acceleration ........
±
1.0g ...............................
±
1.5% max. range excluding
datum error of
±
5%.
2 ........................
0.01g.
Pitch attitude ...........................
100% of usable ..............
±
2
°
.........................................
1 ........................
0.8
°
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