Joint Aviation Requirements jar–29 Large Rotorcraft Joint Aviation Authorities

(a) Each engine must have an independent oil

system that can supply it with an appropriate

quantity of oil at a temperature not above that safe

for continuous operation.

(b) The usable oil capacity of each system

may not be less than the product of the endurance

of the rotorcraft under critical operating

conditions and the maximum allowable oil

consumption of the engine under the same

conditions, plus a suitable margin to ensure

adequate circulation and cooling. Instead of a

rational analysis of endurance and consumption, a

usable oil capacity of 3.8 litres (0.83 Imperial

gallon/1 US gallon) for each 151.4 litres (33.3

Imperial gallons/40 US gallons) of usable fuel

may be used for reciprocating engine installations.

(c) Oil-fuel ratios lower than those

prescribed in sub-paragraph (b) of this paragraph

may be used if they are substantiated by data on

the oil consumption of the engine.

(d) The ability of the engine oil cooling

provisions to maintain the oil temperature at or

below the maximum established value must be

shown under the applicable requirements of JAR

29.1041 to 29.1049.

МАСЛЕНА СИСТЕМА

(a) Installation. Each oil tank

installation must meet the requirements of JAR

29.967.

space must be provided so that –

(1) Each oil tank used with a

reciprocating engine has an expansion space of

not less than the greater of 10% of the tank

capacity or 1.9 litres (0.42 Imperial gallon/

0.5 US gallon), and each oil tank used with a

turbine engine has an expansion space of not

less than 10% of the tank capacity;

(2) Each reserve oil tank not directly

connected to any engine has an expansion

space of not less than 2% of the tank capacity;

and

(3) It is impossible to fill the expansion

normal ground attitude.

(c) Filler connections. Each recessed oil

tank filler connection that can retain any

appreciable quantity of oil must have a drain that

discharges clear of the entire rotorcraft. In

addition –

(1) Each oil tank filler cap must

provide an oil-tight seal under the pressure

expected in operation;

(2) For Category A rotorcraft, each oil

tank filler cap or filler cap cover must

incorporate features that provide a warning

when caps are not fully locked or seated on the

filler connection; and

(3) Each oil filler must be marked

under JAR 29.1557 (c) (2).

(d) Vent. Oil tanks must be vented as

follows:

(1) Each oil tank must be vented from

the top part of the expansion space so that

venting is effective under all normal flight

conditions.

(2) Oil tank vents must be arranged so

that condensed water vapour that might freeze

and obstruct the line cannot accumulate at any

point.

(e) Outlet. There must be means to prevent

any object that might obstruct the flow of oil through

the system. No oil tank outlet may be enclosed by a

screen or guard that would reduce the flow of oil

below a safe value at any operating temperature.

There must be a shutoff valve at the outlet of each oil

tank used with a turbine engine unless the external

portion of the oil system (including oil tank supports)

is fireproof.

(f) Flexible liners. Each flexible oil tank

liner must be approved or shown to be suitable for

the particular installation.

Each oil tank must be designed and installed so

that –

(a) It can withstand, without failure, any

be subjected in operation; and

(b) It meets the requirements of JAR 29.965,

except that instead of the pressure specified in

JAR 29.965 (b) –

(1) For pressurised tanks used with a

turbine engine, the test pressure may not be

less than 34.45 kPa (5 psi) plus the maximum

operating pressure of the tank; and

(2) For all other tanks, the test pressure

may not be less than 34.45 kPa (5 psi).

Всеки маслен резервоар трябва да e проектиран и монтиран така, че:

(a) Each oil line must meet the requirements

of JAR 29.993.

(b) Breather lines must be arranged so that –

(1) Condensed water vapour that might

freeze and obstruct the line cannot accumulate

at any point;

(2) The breather discharge will not

constitute a fire hazard if foaming occurs, or

cause emitted oil to strike the pilot’s

windshield; and

(3) The breather does not discharge

into the engine air induction system.

(a) Each turbine engine installation must

incorporate an oil strainer or filter through which

all of the engine oil flows and which meets the

following requirements:

(1) Each oil strainer or filter that has a

bypass must be constructed and installed so

that oil will flow at the normal rate through the

rest of the system with the strainer or filter

completely blocked.

(2) The oil strainer or filter must have

the capacity (with respect to operating

limitations established for the engine) to ensure

that engine oil system functioning is not

impaired when the oil is contaminated to a

degree (with respect to particle size and

density) that is greater than that established for

the engine under JAR–E.

(3) The oil strainer or filter, unless it is

installed at an oil tank outlet, must incorporate

a means to indicate contamination before it

reaches the capacity established in accordance

with subparagraph (a) (2) of this paragraph.

(4) The bypass of a strainer or filter

must be constructed and installed so that the

release of collected contaminants is minimised

by appropriate location of the bypass to ensure

that collected contaminants are not in the

bypass flow path.

(5) An oil strainer or filter that has no

bypass, except one that is installed at an oil

tank outlet, must have a means to connect it to

the warning system required in JAR 29.1305

(a) (18).

(b) Each oil strainer or filter in a powerplant

installation using reciprocating engines must be

constructed and installed so that oil will flow at

the normal rate through the rest of the system with

the strainer or filter element completely blocked.

A drain (or drains) must be provided to allow

safe drainage of the oil system. Each drain must –

(a) Be accessible; and

(b) Have manual or automatic means for

positive locking in the closed position.

(a) Each oil radiator must be able to

withstand any vibration, inertia, and oil pressure

loads to which it would be subjected in operation.

(b) Each oil radiator air duct must be located,

or equipped, so that, in case of fire, and with the

airflow as it would be with and without the engine

operating, flames cannot directly strike the

radiator.

(a) Each oil shutoff must meet the

requirements of JAR 29.1189.

(b) The closing of oil shutoffs may not

prevent autorotation.

(c) Each oil valve must have positive stops

or suitable index provisions in the ‘on’ and ‘off’

positions and must be supported so that no loads

resulting from its operation or from accelerated

flight conditions are transmitted to the lines

attached to the valve.

JAR 29.1019(a) (continued)

(a) The oil system for components of the

rotor drive system that require continuous

lubrication must be sufficiently independent of the

lubrication systems of the engine(s) to ensure –

(1) Operation with any engine

inoperative; and

(2) Safe autorotation.

(b) Pressure lubrication systems for

transmissions and gearboxes must comply with the

requirements of JAR 29.1013, sub-paragraphs (c),

(d) and (f) only, JAR 29.1015, 29.1017, 29.1021,

29.1023 and 29.1337 (d). In addition, the system

must have –

(1) An oil strainer or filter through

which all the lubricant flows, and must –

(i) Be designed to remove from

the lubricant any contaminant which may

damage transmission and drive system

components or impede the flow of

lubricant to a hazardous degree; and

(ii) Be equipped with a bypass

constructed and installed so that –

(A) The lubricant will flow

at the normal rate through the rest

of the system with the strainer or

filter completely blocked; and

(B) The release of collected

contaminants is minimised by

appropriate location of the bypass

to ensure that collected

contaminants are not in the bypass

flow path;

(iii) Be equipped with a means to

indicate collection of contaminants on the

filter or strainer at or before opening of

the bypass;

(2) For each lubricant tank or sump

outlet supplying lubrication to rotor drive

systems and rotor drive system components, a

screen to prevent entrance into the lubrication

system of any object that might obstruct the

flow of lubricant from the outlet to the filter

required by sub-paragraph (b) (1) of this

paragraph. The requirements of sub-paragraph

(b) (1) of this paragraph do not apply to

screens installed at lubricant tank or sump

outlets.

drive system gearboxes must comply with JAR

29.1021 and 29.1337 (d).

1. 
   Експлоатация, когато някой от двигателите не работи; и
   

2. 
   Безопасна авторотация.
   

(b) Системите за смазване под налягане за трансмисии и редуктори трябва да отговарят на изискванията на JAR 29.1013, само подпараграфи (с), (d) и (f), JAR 29.1015, JAR 29.1017, JAR 29.1021, JAR 29.1023 и JAR 29.1337 (d). В допълнение, системата трябва да има:

1. 
   Маслена цедка или филтър, през които да преминава целия смазочен поток и трябва:
   

1. 
   Да бъде проектирана така, че да премахва от смазочния материал всеки замърсител, който би могъл да повреди компонентите на трансмисията и на задвижващата система или да възпрепятства в опасна степен протичането на смазочния материал; и
   

2. 
   Да бъде оборудвана с байпас, конструиран и монтиран така, че:
   

А. Смазочният материал да има нормален разход през останалата част на системата, когато цедката или филтъра са напълно блокиране; и

3. 
   Да бъде оборудвана със средство, което да показва събирането на замърсители на филтъра или цедката при или преди отваряне на байпаса;
   

2. 
   За всеки изход на резервоар със смазочно масло или изход на маслено корито, доставящи смазочно масло за системите за задвижване на носещото витло или за компонентите на системата за задвижване на витлото, екран, който да предпазва от попадане в системата за смазване на всякакви предмети, които биха могли да задръстат протичането на смазочното масло от изхода към филтъра, изискван от подпараграф (b) (1) на този параграф. Изискванията на подпараграф (b)(1) на този параграф не се прилагат за екрани, монтирани към изходите на маслените резервоари или изходи на маслени корита.
   

(с) Системи за смазване с пръскане за редуктори на системи за задвижване на носещото витло трябва да отговарят на условията, указани в JAR 29.1021 и JAR 29.1337(d).

(a) The powerplant and auxiliary power unit

cooling provisions must be able to maintain the

temperatures of powerplant components, engine

fluids, and auxiliary power unit components and

fluids within the temperature limits established for

these components and fluids, under ground, water,

and flight operating conditions for which

certification is requested, and after normal engine

or auxiliary power shut-down, or both.

(b) There must be cooling provisions to

maintain the fluid temperatures in any power

transmission within safe values under any critical

surface (ground or water) and flight operating

conditions.

(c) Except for ground-use-only auxiliary

power units, compliance with sub-paragraphs (a)

and (b) of this paragraph must be shown by flight

tests in which the temperatures of selected

powerplant component and auxiliary power unit

component, engine, and transmission fluids are

obtained under the conditions prescribed in those

paragraphs.