Норми за летателна годност

1.1 JAR–E is based on BCAR Section C, and is termed ‘Joint Aviation Requirements for Engines’

or ‘JAR–E’.

2 PRESENTATION

2.1 The requirements of JAR–E are presented in two columns on loose pages, each page being

identified by the date of issue or the Change number under which it is amended or reissued.

2.2 Explanatory notes not forming part of the JAR text appear in a smaller typeface.

Sub-headings are in italic typeface.

2.3 New, amended and corrected text is enclosed within heavy brackets.

(a) This JAR–E contains the airworthiness

requirements for aircraft Engines.

(b) The requirements of Section 1 apply to

all Engines unless their design is such as to render

any requirement inappropriate or inadequate. In

such cases, the Authority will modify the

requirements in order to achieve an equivalent

standard of safety.

(c) Reserved

(d) The requirements of Sub-Section A apply

to all Engines. Additional requirements for Piston

Engines installed in aeroplanes are detailed in the

Sub-Sections B and C and for all Turbine Engines

in Sub-Sections D and E.

(e) Any necessary variations of the

requirements of Sub-Sections B and C for Piston

Engines intended for use in rotorcraft will be

decided in consultation with the Authority.

[Ch. 8, 4.5.90; Ch. 10, 15.8.99]

(а) Този JAR-E съдържа изискванията за летателна годност на двигатели за ВС.

(d) Изискванията на Глава “А” се отнасят за всички двигатели. Детайлизирани допълнителни изисквания за буталните двигатели поставени на самолети са изложени в глави “В” и “С”, а за всички газотурбинни двигатели в глави “D” и “Е”.

(See ACJ E 20)

(a) The Engine manufacturer shall provide a

list of all the parts and equipment, including

references to the relevant drawings, which defines

the type certification configuration of the Engine.

(b) The Engine manufacturer shall declare

under JAR–E 30 the aircraft requirements code

which is assumed as being applicable to the

intended installation of the Engine.

(c) The Engine manufacturer shall define

those aircraft parts and equipment that may be

mounted on, or driven by, the Engine, which are

not part of the declared Engine configuration and

therefore are not covered by the Engine Type

Certificate.

(d) Manuals shall be provided containing

instructions for installing and operating the

Engine that are acceptable to the Authority. The

Engine installation instructions shall include a

definition of the physical and functional interfaces

with the aircraft and the aircraft equipment.

(e) Engine performance data, compatible

with the Engine acceptance and operating

limitations, shall be provided for aircraft

certification performance, handling and stressing

purposes. The data shall be such that the

power/thrust of a ‘minimum’ and a ‘maximum’

Engine can be derived and shall include means of

determining the effects on performance of

variations of Engine bleed and power off-take,

forward speed, ambient pressure, temperature and

humidity.

[Ch. 10, 15.8.99]

(See ACJ E 25)

(a) Except as provided by JAR–E 25(d),

manual(s) shall be provided containing

instructions which are acceptable to the Authority

for continued airworthiness of the Engine. They

must be updated as necessary according to

changes to existing instructions or changes in

Engine definition.

(b) The instructions for continued

airworthiness must contain a section titled

Airworthiness Limitations that is segregated and

clearly distinguishable from the rest of the

document(s). This section must set forth each

mandatory replacement time, inspection interval

and related procedure required for type

certification, must be approved by the Authority

and must contain a legible statement in a

prominent location which states that this section is

approved by the Authority and that any variation

must be approved.

(c) The following information must be

considered, as appropriate, for inclusion into the

manual(s) required by JAR–E 25(a).

(1) A detailed description of the Engine

and its components, systems and installations.

(2) Installation instructions, including

proper procedures for uncrating, de inhibiting,

acceptance checking, lifting and attaching

accessories, with any necessary checks.

(3) Basic control and operating

information describing how the Engine

components, systems and installations operate.

Information describing the methods of starting,

running, testing and stopping the Engine or its

components and systems including any special

procedures and limitations that apply.

(4) Servicing information that covers

details regarding servicing points, capacities of

tanks, reservoirs, types of fluids to be used,

pressures applicable to the various systems,

locations of lubrication points, lubricants to be

used and equipment required for servicing.

(5) Scheduling information for each

part of the Engine that provides the

recommended periods at which it should be

cleaned, inspected, adjusted, tested and

lubricated, and the degree of inspection, the

applicable serviceability limits, and work

recommended at these periods. Necessary

cross-references to the Airworthiness

Limitations section must also be included. In

addition, the applicant must include, if

appropriate, an inspection programme that

includes the frequency of the inspections

necessary to provide for the continued

airworthiness of the Engine.

(6) Troubleshooting information

describing probable malfunctions, how to

recognise those malfunctions and the remedial

action for those malfunctions.

(7) Information describing the order

and method of removing the Engine and its

parts and replacing parts, the order and method

of disassembly and assembly, with any

necessary precautions to be taken. Instructions

for proper ground handling, crating and

shipping must also be included.

(8) Cleaning and inspection

instructions that cover the material and

apparatus to be used and methods and

precautions to be taken. Methods of inspection

must also be included.

(9) Details of repair methods for worn

or otherwise substandard parts and components

along with the information necessary to

determine when replacement is necessary.

Details of all relevant fits and clearances.

(10) Instructions for testing including

test equipment and instrumentation.

(11) Instructions for storage preparation,

including any storage limits.

(12) A list of the tools and equipment

necessary for maintenance and directions as to

their method of use.

(d) (1) Except as provided in JAR–

E 25(d)(2), the instructions for continued

airworthiness may be incomplete at the time of

the Type Certification provided the Authority

has approved a programme which ensures their

completion prior to issuance of a standard

Certificate of Airworthiness for the aircraft

with the Engine installed.

(2) Availability of some manual or

portion of the instructions for continued

airworthiness, dealing with overhaul or other

forms of heavy maintenance, may be delayed

until after the Engine has entered service. In

such cases, the Engine Type Certificate Data

Sheet will incorporate a note prohibiting the

corresponding heavy maintenance of Engines

until the instructions are available.

[Ch. 10, 15.8.99]

(b) Инструкциите за поддържане на летателната годност трябва да съдържат Част озаглавена “Ограничения на летателната годност”, която е отделена и ясно различима от останалата част от документацията на изделието. Тази част трябва да формулира всяка задължителна замяна по време, интервал на инспектиране и свързаните с това процедури, необходими за изготвяне на типовия сертификат, които трябва да са одобрени от Въздухоплавателната администрация и трябва да съдържат четливо изложение на видно място, което да оповестява, че настоящата част е одобрена от Въздухоплавателната администрация, както и че всички промени трябва да се одобрят от Въздухоплавателната администрация.

(6) Информация за откриване и отстраняването на неизправности, описваща вероятни неизправности, начина на разпознаването им и ремонтните действия за отстраняването им.

(See ACJ E 30)

(a) In the course of establishing compliance

with JAR–E certain assumptions have to be made

concerning the conditions that may be imposed on

the Engine when it is eventually installed in the

aircraft. In order that the validity of the conditions

assumed in the Engine certification may be

assessed for any particular installation, the Engine

manufacturer shall submit, prior to Engine

certification, the details of the assumptions made

(see ACJ E 30). These assumptions shall be

included in the installation instructions for the

Engine required under JAR–E 20(d).

[Ch. 8, 4.5.90; Ch. 10, 15.8.99]

(a) Power ratings shall be established for

Take-off Power and/or Thrust and for Maximum

Continuous Power and/or Thrust, for all Engines.

(b) If desired by the Applicant other ratings

may also be established as –

(1) Piston Engines –

(i) Maximum Recommended

Cruising Power.

(ii) Maximum Best Economy

Cruising Power.

(2) Turbine Engines for Multi-engined

(i) 2 ½-Minute OEI Power/Thrust.

(ii) Continuous OEI Power/

Thrust.

(i) 2 ½-Minute OEI Power.

(ii) Continuous OEI Power.

(iii) 30-Minute OEI Power.

(c) The Engine thrust and/or power ratings

will be based on standard atmospheric conditions,

with no air bleed for aircraft services and with

only those accessories installed which are

essential for Engine functioning, including

controls, unless otherwise declared in the Engine

Type Certificate Data Sheet.

(d) Operating limitations appropriate to the

intended operating conditions for the Engine shall

be established (see ACJ E 40(d)).

(e) The Engine’s rated Powers/Thrusts and

any operating limitations established under this

JAR–E 40 which must be respected by the crew of

an aircraft shall be listed in the Engine Type

Certificate Data Sheet specified in JAR–21.41.

The Engine Type Certificate Data Sheet shall also

identify, or make reference to, all other

information found necessary for the safe operation

of the Engine.

(f) The ratings established under this

JAR–E 40 must be defined for the lowest

power/thrust that all Engines of the same type

may be expected to produce under the conditions

used to determine these ratings. The Engine Type

Certificate Holder must define the minimum

testing and associated conditions necessary for

ensuring that the Engines will comply with this

objective. (See ACJ E 40(f).)

[Ch. 7, 24.1.86; Ch. 9, 21.10.94; Ch. 10, 15.8.99]

(b) По желание на “кандидатстващия”, могат също да се установят и други характерни режими, като например:

(1) За бутални двигатели -

(i) Максимална препоръчителна крейсерска мощност;

(ii) Максимална най-икономична крейсерска мощност.
(2) за газотурбинните двигатели на многодвигателни самолети -

(i) 2Ѕ-минути режим на мощността/ теглителна сила с един отказал двигател;

(ii) Продължителен режим на мощността/ теглителна сила с един отказал двигател.
(3) за газо-турбинните двигатели на много-двигателни роторни ВС

(i) 2Ѕ-минути режим на мощността с един отказал двигател;

(ii) Продължителен на мощността с един отказал двигател;

(iii) 30-минутен на мощността с един отказал двигател.

(See AMJ 20X-1)

(a) For Turbine Engines, the Engine

controlsystem, including a thrust reverser control

if applicable, shall be designed to –

(1) Provide a progressive means of

selecting Engine power/thrust with adequate

sensitivity and accuracy covering the whole

range of declared operating conditions.

(2) Enable selected value(s) of relevant

control parameter(s) to be maintained and the

Engine kept within the approved operating

limits over changing atmospheric conditions in

the declared operating range without the need

for continual manual adjustment.

(3) Enable the Engine to function

satisfactorily under all likely control system

movements by the pilot appropriate to the

particular flight phase.

(4) Retain the ability to control the

Engine safely under the appropriate failure

conditions determined from the Failure

Analysis.

(5) Ensure that the above

characteristics are not affected unacceptably by

the operation of permitted variables such as air

bleed, and where appropriate, enable the

operation and control of such functions to be

effected safely.

(b) Engine and Propeller controls shall be

designed so that their functioning will not be

adversely affected by the declared environmental

conditions.

(c) Engine automatic controlling systems

shall be segregated, mechanically and electrically,

from any associated instrumentation systems to

the extent necessary to ensure that the probability

of a fault in either system resulting in hazardous

operation of the other is Extremely Remote.

(d) Where any Engine condition is controlled

by an automatic controlling system, a statement of

the overall limits of accuracy of the controlling

system shall be submitted to the Authority. In

determining the Engine performance and

operating limitations, account will be taken of the

declared overall limits of accuracy. (See also

JAR–E 60.)