JAR-E 800 Удар от птици и всмукване на птици

• 
  всмукване симулиращо случаен сблъсък с ято птици в рамките на една секунда;
  
• 
  2 минути работа без преместване на ръчката за управление режимите на работа на двигателя;
  
• 
  3 минути работа на режим 75% от режима на изпитание съгласно JAR-E 800(c)(1)(i);
  
• 
  6 минути работа на режим 60% от режима на изпитание съгласно JAR-E 800(c)(1)(i);
  
• 
  1 минута работа на режим “Малък газ” при подход за кацане;
  
• 
  2 минути работа на режим 75% от режима на изпитание съгласно JAR-E 800(c)(1)(i);
  
• 
  стабилизиране на режим “Малък газ” и изключване на двигателя
  

Тези времетраения са времената определени за отделните работни режими на двигателя, а ръчката за управление режимите на работа на двигателите се премества между всеки от режимите за по-малко от 10 секунди.

• 
  всмукване симулиращо случаен сблъсък с ято птици в рамките на една секунда ;
  
• 
  3 минути работа на режим 75% от режима на изпитание съгласно JAR-E 800(c)(1)(i);
  
• 
  90 секунди работа на режим съответстващ на стендови “Малък газ”;
  
• 
  30 секунди работа на 75% от режима на изпитание съгласно JAR-E 800(c)(1)(i);
  
• 
  стабилизиране на режим “Малък газ” и изключване на двигателя.
  

Тези времетраения са времената определени за отделните работни режими на двигателя, а ръчката за управление режимите на работа на двигателите се премества между всеки от режимите за по-малко от 10 секунди.

(2) Критерии за одобрение. Всмукването не трябва да причинява:

• 
  повече от 25% постоянна загуба на мощност или теглителна сила
  
• 
  да се изключи двигателя по време на изпитанието
  

(3) В допълнение, освен за двигателите предназначени за роторни ВС, трябва да се докаже, чрез подходящи изпитание, анализи или и чрез двете, че когато целия възел на първа степен на ротора е обект на въздействие на количество и маса средни по големина птици указани в колона 3 на Таблица А ударили най-критичните места от първа степен на ротора, резултата от това няма да е такъв, че да направи неспособен двигателя да отговаря на приетите критерии на JAR-E 800(c)(2).

Failure

(a) It shall be demonstrated that any single

compressor or turbine blade will be contained

after failure and that no hazardous condition can

arise to the aircraft as a result of other Engine

damage likely to occur before Engine shut down

following a blade failure.

(b) Where, in the failure analysis of JAR–E

510, reliance is placed on the shedding of turbine

blades in order to protect the rotating system in

overspeed conditions, tests shall be made to

demonstrate that –

[ (1) The shedding will occur at a speed

which :

maximum Engine speed to be approved

(including the Maximum Engine

Overspeed) and,

(ii) allows the rotor to comply

with JAR–E 840. ]

(2) No conditions hazardous to the

aircraft are likely to arise as a consequence of

the blades shedding.

[Amdt. 11, 01.11.01]

(1) Разлитане ще се възникне при честота на въртене на ротора на двигателя при която:

(ii) позволява ротора да съответства на JAR-E 840.

(a) If approval of a Maximum Engine Over-torque

is sought for an Engine incorporating a

free power turbine, compliance with this

paragraph must be demonstrated by test.

(1) The test may be run, if desired, as

part of the Endurance Test of JAR-E 740.

Alternatively, evidence may be provided from

tests of a complete Engine or equivalent testing

of individual groups of components.

(2) On conclusion of such tests, the

stripped condition of the Engine or individual

groups of components shall be satisfactory for

continued running.

(b) The test conditions must be as follows:

(1) A total of 15 minutes run at the

Maximum Engine Over-torque to be approved.

This may be done in separate runs, each being

of at least 2½-minutes duration.

(2) A power turbine rotational speed

equal to the highest speed at which the

maximum over-torque can occur in service, but

not more than the limit speed of Take-off or

OEI ratings of a duration longer than 2

minutes.

(3) For Engines incorporating a

reduction gearbox, a gearbox oil temperature

equal to the maximum temperature at which the

maximum over-torque could occur in service;

for other Engines, an oil temperature within the

normal operating range.

(4) A turbine entry gas temperature

equal to the maximum steady state temperature

to be approved for use during periods longer

than 20 seconds when operating at conditions

not associated with 30-Second or 2-Minute

OEI Power ratings, unless it can be shown that

other testing provides substantiation of the

temperature effects when considered in

combination with the other parameters

indentified in JAR–E 820(b)(1), (b)(2) and

(b)(3). ]

[Ch. 10, 15.8.99; Amdt. 11, 01.11.01]

(a) General

(1) Where the Engine incorporates

more than one main rotating system, the

following requirements apply to each system.

(2) The test may be run, if desired, as

part of the Endurance Test. Alternatively, test

evidence from an Engine of similar design may

be provided.

(3) On conclusion of such testing, the

stripped condition of the Engine shall be

satisfactory for continued running.

(b) Test Conditions

(1) A 15-minute period at Maximum

Overspeed shall be run at the declared

maximum turbine-entry and oil-inlet

temperatures. If necessary to achieve this, the

Engine may be made non-standard in

agreement with the Authority. If, however, the

maximum overspeed cannot occur at the

maximum turbine-entry temperature due to

limitation of the fuel flow, the highest

temperature which could occur shall be used.

(2) If it is necessary to test individual

spools separately, the gas temperature

conditions shall be the maximum for the actual

spool under test.

(3) Where desired, the test may be

made up of a number of separate runs giving a

total time of 15 minutes on each main rotating

system, the time of each individual run being at

least 2½-minutes.

[Ch. 7, 24.1.86]

2. 
   Условия на изпитанието.
   

(1) Двигателят трябва да работи 15-минутен период на режим, съответстващ на максимално-допустимото превишаване на честотата на въртене при декларирана максимална температура на входа в газовата турбина и температура на маслото на входа. Ако е необходимо да се постигне това, двигателят може да се направи нестандартен с одобрението на Въздухоплавателната администрация. Ако обаче максималното превишаване на честотата на въртене не може да стане при максимална температура на входа в газовата турбина поради ограничения в разхода на гориво, трябва да се използва максималната температура, която може да се достигне.

(See ACJ E 840)

(a) For each fan, compressor, and turbine

rotor, it shall be established by test, analysis, or

combination thereof, that a rotor which has the

most adverse combination of material properties

and dimensional tolerances allowed by its type

design will not burst when it is operated in the

Engine for five minutes at whichever of the

conditions defined in JAR–E 840(b) is the most

critical with respect to the integrity of such a

rotor.

determined by either JAR–E 840(b)(3) or (b)(4),

but the associated failure condition is of a sudden

transient nature, such as loss of load, and it

precludes any further operation of the affected

rotor, then the time period of that failure

condition is an acceptable duration for showing

compliance by means of an engine test provided

the required test speeds are achieved. Test rotors

which do not have the most adverse combination

of material properties and dimensional tolerances

must comply at appropriately adjusted test

parameters, e.g. speed, temperature, loads.

(b) When determining the operating

conditions applicable to each rotor for compliance

with JAR–E 840(a) and (c), each of the following

speeds must be evaluated in conjunction with their

associated temperatures and temperature

gradients, throughout the Engine's operating

envelope :

(1) 120% of the maximum permissible

rotor speeds associated with any of the ratings

except OEI ratings of less than 2½-minutes.

(2) 115% of the maximum permissible

rotor speeds associated with any OEI ratings of

less than 2½-minutes.

(3) 105% of the highest rotor speed that

would result from either -

(i) The failure of the component

or system which, in a representative

installation of the Engine, is the most

critical with respect to overspeeding

when operating at any rating condition

except OEI ratings of less than 2½-minutes,

or

(ii) The failure of any component

of the Engine, in combination with any

other failure of a component or system

that would not normally be detected

during a routine pre-flight check or

during normal flight operation that is the

most critical with respect to

overspeeding, except as provided by

JAR–E 840(c), when operating at any

rating condition except OEI ratings of

less than 2½-minutes.

(4) 100% of the highest rotor speed that

would result from the failure of the component

or system which, in a representative installation

of the Engine, is the most critical with respect

to overspeeding when operating at any OEI

ratings of less than 2½-minutes.

(c) The highest overspeed which will result

from a complete loss of load on a turbine rotor,

unless it can be shown to be Extremely Remote

under the provisions of JAR-E 850, must be

included in the overspeeds considered under each

of JAR–E 840(b)(3)(i), (ii) and (b)(4),

irrespective of whether it is the result of a failure

within the Engine or external to the Engine.

Overspeeds resulting from any other single

failure must be considered. Overspeeds resulting

from multiple failures must also be considered

unless they can be shown to be Extremely

Remote.

turbine rotor, it shall be established by test,

analysis, or combination thereof, that a rotor

which has the most adverse combination of

material properties and dimensional tolerances

allowed by its type design and which is operated

in the Engine for five minutes at 100% of the most

critical speed and temperature conditions resulting

from any failure or combination of failures

considered under JAR–E 840(b)(3) and (b)(4),

will meet the acceptance criteria prescribed below

in JAR–E 840(d)(1) and (d)(2).

However, where the failure condition is of a

sudden transient nature, such as loss of load, and

it precludes any further operation of the affected

rotor, the time period of that failure condition is

an acceptable duration for showing compliance by

means of an engine test. ]

[ Test rotors which do not have the most

adverse combination of material properties and

dimensional tolerances must comply at

appropriately adjusted test parameters, e.g. speed,

temperature, loads.

(1) Growth of the rotor while it is

operating at the applicable conditions must not

cause the Engine to:

(i) catch fire,

(ii) release hazardous fragments

through the Engine's casing or result in a

hazardous failure of the Engine's casing,

(iii) generate loads greater than

those ultimate loads for which the

Engine's mountings have been designed

in compliance with JAR–E 100(b), or

(iv) lose the capability of being

shut down.

(2) After the applicable period of operation,

the rotor must not exhibit conditions such as

cracking or distortion which preclude the safe

operation of the Engine during any likely

continued operation following such an overspeed

event in service. ]

[Ch. 7, 24.1.86; Amdt. 11, 01.11.01]