ЕЛЕКТРИЧЕСКИ СИСТЕМИ И ОБОРУДВАНЕ

(a) 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 safe operation.

(b) Cables must be grouped, routed, and

spaced so that damage to essential circuits will be

minimised if there are faults in heavy currentcarrying

cables.

installed as follows:

(1) Safe cell temperatures and pressures

must be maintained during any probable

charging and discharging condition. No

uncontrolled increase in cell temperature may

result when the battery is recharged (after

previous complete discharge) –

(i) At maximum regulated

voltage or power;

(ii) During a flight of maximum

duration; and

(iii) Under the most adverse

cooling condition likely in service.

(2) Compliance with sub-paragraph

(c)(1) of this paragraph must be shown by test

unless experience with similar batteries and

installations has shown that maintaining safe

cell temperatures and pressures presents no

problem.

by any battery in normal operation, or as the

result of any probable malfunction in the

charging system or battery installation, may

accumulate in hazardous quantities within the

rotorcraft.

(4) No corrosive fluids or gases that

may escape from the battery may damage

surrounding structures or adjacent essential

equipment.

(5) Each nickel cadmium battery

installation capable of being used to start an

engine or auxiliary power unit must have

provisions to prevent any hazardous effect on

structure or essential systems that may be

caused by the maximum amount of heat the

battery can generate during a short circuit of the

battery or of its individual cells.

(6) Nickel cadmium battery installations

capable of being used to start an engine or

auxiliary power unit must have –

(i) A system to control the

charging rate of the battery automatically so

as to prevent battery overheating;

(ii) A battery temperature sensing

and over-temperature warning system with a

means for disconnecting the battery from its

charging source in the event of an overtemperature

condition; or

(iii) A battery failure sensing and

warning system with a means for

disconnecting the battery from its charging

(a) The distribution system includes the

distribution busses, their associated feeders, and

each control and protective device.

(b) If two independent sources of electrical

power for particular equipment or systems are

in the event of the failure of one power source for

such equipment or system, another power source

(including its separate feeder) must be provided

automatically or be manually selectable to maintain

equipment or system operation.

a) Разпределителната система включва разпределителните клеми, свързаните с тях фидери, и всяко контролни и защитно устройство.

b) Ако от приложим JAR или експлоатационно правило се изискват два независими източника на електрозахранване за конкретно оборудване или системи, в случай на излизане от строя на един от източниците на електроенергия за такова оборудване или система, трябва да се осигури автоматично друг източник на електроенергия (включително неговия отделен фидер) или да се избира ръчно, за да поддържа работата на оборудването или системата.

(a) Automatic protective devices must be used

to minimise distress to the electrical system and

hazard to the rotorcraft in the event of wiring faults

or serious malfunction of the system or connected

equipment.

(b) The protective and control devices in the

generating system must be designed to de-energise

and disconnect faulty power sources and power

transmission equipment from their associated

busses with sufficient rapidity to provide protection

from hazardous overvoltage and other

malfunctioning.

(c) Each resettable circuit protective device

must be designed so that, when an overload or

circuit fault exists, it will open the circuit

regardless of the position of the operating control.

(d) If the ability to reset a circuit breaker or

replace a fuse is essential to safety in flight, that

circuit breaker or fuse must be located and

identified so that it can be readily reset or

replaced in flight.

(e) Each essential load must have individual

circuit protection. However, individual protection

for each circuit in an essential load system (such

as each position light circuit in a system) is not

required.

(f) If fuses are used, there must be spare

fuses for use in flight equal to at least 50% of the

number of fuses of each rating required for

complete circuit protection.

(g) Automatic reset circuit breakers may be

used as integral protectors for electrical

equipment provided there is circuit protection for

the cable supplying power to the equipment.

(a) Components of the electrical system must

meet the applicable fire and smoke protection

provisions of JAR 29.831 and 29.863.

(b) Electrical cables, terminals, and

equipment, in designated fire zones, and that are

used in emergency procedures, must be at least

fire resistant.

installed in the rotorcraft must be selfextinguishing

when tested in accordance with

JAR–25, Appendix F, Part I(a)(3).]

(a) When laboratory tests of the electrical

system are conducted –

(1) The tests must be performed on a

mock-up using the same generating equipment

used in the rotorcraft;

(2) The equipment must simulate the

electrical characteristics of the distribution

wiring and connected loads to the extent

necessary for valid test results; and

(3) Laboratory generator drives must

simulate the prime movers on the rotorcraft

with respect to their reaction to generator

loading, including loading due to faults.

(b) For each flight condition that cannot be

simulated adequately in the laboratory or by ground

tests on the rotorcraft, flight tests must be made.

1. 
   Изпитанията трябва да се извършват върху макет като се използва същого генериращо оборудване, което се използва на ротокрафта;
   

2. 
   Оборудването трябва да симулира електрическите характеристики на разпределителните проводници и свързаните товари до степен, необходима за получаване на валидни резултатите от изпитанията; и
   

3. 
   Задвижващи генераторни устройства в лабораторията трябва да симулират основните задвиждащи мощности на ротокрафта по отношение на тяхната реакция при натоварване от генератора, включително натоварване вследствие от откази.
   

(b) За всяко полетно състояние, което не може да бъде подходящо симулилано в лабораторията или при изпитания в роторкрафта, когато е на земята, трябва да се извършат изпитания в полет.

The instrument lights must –

(a) Make each instrument, switch, and other

device for which they are provided easily

readable; and

(b) Be installed so that –

(1) Their direct rays are shielded from

the pilot’s eyes; and

(2) No objectionable reflections are

visible to the pilot.