Training Material EASA Part 21 AMC & GM EASA Part 21 Acceptable Means of Compliance ...

390 Pages·2015·5.43 MB·English

Training Material

EASA
Part 21 AMC & GM

EASA Part 21

Acceptable Means of Compliance & Guidance Material
Part 21
Structure AMC & GM to Subpart A
General Provisions
DO/PO
AMC & GM to Subpart J AMC & GM to Subpart G
Design Organisation Approval (DOA) Production Organisation Approval (POA)
DO PO
AMC & GM to Subpart B AMC & GM to Subpart D AMC & GM to Subpart H AMC & GM to Subpart F
Type-Certificates Changes to Certificates of Production
and Type-Certificates Airworthiness without
restricted and and restricted Production
Type-Certificates restricted Certificates of Organisation
Type-Certificates Airworthiness Approval

DO DO PO PO
AMC & GM to Subpart P AMC & GM to Subpart M AMC & GM to Subpart I
Permit to Fly Repairs Noise Certificates
DO/PO DO/PO PO
AMC & GM to Subpart K AMC & GM to Subpart Q AMC & GM to Subpart E AMC & GM to Subpart O
Part and Identification of Supplemental European Technical
Appliances Products, Parts Type-Certificates Standard Order
and Appliances (STC) Authorisation
(ETSO)
DO/PO DO/PO DO DO/PO
DO/PO: For Design / Production Organisations relevant Subparts.

The following Part 21 AMC&GM have been considered and introduced as applicable:

Id. EASA EDD No Date dd.mm.yyyy Topic

[0] 2012/020/R 30.10.2012 Initial Issue 2
(covering 2003/1/RM incl. all 9 amendments and changes related to EU 748/2012)

Apr. 2013 Corrigendum to ED Decision 2012/020/R

[1] 2013/001/R 23.01.2013 CAEP/8 Amendments (Emission Requirements)

[2] 2014/007/R 31.01.2014 Operational Suitability Data (OSD)
[3] 2015/016/R 09.07.2015 Standard Changes / Repairs acc. to CS-STAN ddpConcepts GmbH
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(am Flugplatz Buochs)
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up-to-dateness of the document at any time. In this respect, only the official EASA Tel: [phone]
publications are applicable. www.ddpconcepts.ch
© 2000-2015 by ddpConcepts GmbH First Created: 14. Aug. 2012 more value.
Doc No. 20303001 002, Version 4.0 Last Modified: 10. Aug. 2015
Training Material

EASA
Part 21 AMC & GM

EASA Part 21 AMC & GM

Section A - Technical Requirements

Part 21
Structure AMC & GM to Subpart A
General Provisions
DO/PO
AMC & GM to Subpart J AMC & GM to Subpart G
Design Organisation Approval (DOA) Production Organisation Approval (POA)
DO PO
AMC & GM to Subpart B AMC & GM to Subpart D AMC & GM to Subpart H AMC & GM to Subpart F
Type-Certificates Changes to Certificates of Production
and Type-Certificates Airworthiness without
restricted and and restricted Production
Type-Certificates restricted Certificates of Organisation
Type-Certificates Airworthiness Approval

DO DO PO PO
AMC & GM to Subpart P AMC & GM to Subpart M AMC & GM to Subpart I
Permit to Fly Repairs Noise Certificates
DO/PO DO/PO PO
AMC & GM to Subpart K AMC & GM to Subpart Q AMC & GM to Subpart E AMC & GM to Subpart O
Part and Identification of Supplemental European Technical
Appliances Products, Parts Type-Certificates Standard Order
and Appliances (STC) Authorisation
(ETSO)
DO/PO DO/PO DO DO/PO
DO/PO: For Design / Production Organisations relevant Subparts.
Blue Box: Section A contain AMC&GM.

ddpConcepts GmbH
Aumühlestrasse 10
(am Flugplatz Buochs)

CH – 6373 Ennetbürgen
This document is prepared and maintained with accuracy by ddpConcepts GmbH.

Nevertheless, no liability can be assumed for the accuracy, the completeness and
Tel: [phone]
up-to-dateness of the document at any time. In this respect, only the official EASA www.ddpconcepts.ch
publications are applicable.
© 2000-2015 by ddpConcepts GmbH First Created: 14. Aug. 2012 more value.
Doc No. 20303001 002, Version 4.0 Last Modified: 10. Aug. 2015
Training Material

EASA
Part 21 AMC & GM

EASA Part 21 AMC & GM | Section A |

Subpart A - General Provisions

Part 21
Structure AMC & GM to Subpart A
General Provisions
DO/PO
AMC & GM to Subpart J AMC & GM to Subpart G
Design Organisation Approval (DOA) Production Organisation Approval (POA)
DO PO
AMC & GM to Subpart B AMC & GM to Subpart D AMC & GM to Subpart H AMC & GM to Subpart F
Type-Certificates Changes to Certificates of Production
and Type-Certificates Airworthiness without
restricted and and restricted Production
Type-Certificates restricted Certificates of Organisation
Type-Certificates Airworthiness Approval

DO DO PO PO
AMC & GM to Subpart P AMC & GM to Subpart M AMC & GM to Subpart I
Permit to Fly Repairs Noise Certificates
DO/PO DO/PO PO
AMC & GM to Subpart K AMC & GM to Subpart Q AMC & GM to Subpart E AMC & GM to Subpart O
Part and Identification of Supplemental European Technical
Appliances Products, Parts Type-Certificates Standard Order
and Appliances (STC) Authorisation
(ETSO)
DO/PO DO/PO DO DO/PO
DO/PO: For Design / Production Organisations relevant Subparts.

ddpConcepts GmbH
Aumühlestrasse 10

(am Flugplatz Buochs)
This document is prepared and maintained with accuracy by ddpConcepts GmbH.
CH – 6373 Ennetbürgen
Nevertheless, no liability can be assumed for the accuracy, the completeness and

up-to-dateness of the document at any time. In this respect, only the official EASA
Tel: [phone]
publications are applicable.
www.ddpconcepts.ch
© 2000-2015 by ddpConcepts GmbH First Created: 14. Aug. 2012 more value.
Doc No. 20303001 002, Version 4.0 Last Modified: 10. Aug. 2015
EASA Part 21 AMC & GM
Section A - Technical Requirements
Subpart A - General Provisions

AMC No 1 to 21.A.3A(a) Collection, investigation and analysis of data related to
Flammability Reduction Means (FRM) reliability

Holders of a type certificate, restricted type certificate, supplemental type
Assess Component
certificate or any other relevant approval deemed to have been issued Failures
under Part 21 and which have included a FRM in their design should
assess on an on-going basis the effects of aeroplane component

failures on FRM reliability.

This should be part of the system for collection, investigation and analysis

of data required by 21.A.3A(a). The applicant/holder should do the

following:

(a) Demonstrate effective means to ensure collection of FRM reliability Reliability Data

data. The means should provide data affecting FRM reliability, such as

component failures.

(b) Unless alternative reporting procedures are approved by the Agency,
provide a report to the Agency every six months for the first five Reporting all 6 month
to Agency
years after service introduction.

After that period, continued reporting every six months may be replaced

with other reliability tracking methods found acceptable to the Agency or

eliminated if it is established that the reliability of the FRM meets, and will
continue to meet, the exposure specifications of paragraph M25.1 of
Appendix M to CS-25.

(c) Develop service instructions or revise the applicable aeroplane
Service Instructions
manual, according to a schedule approved by the Agency, to correct any
failures of the FRM that occur in service that could increase any fuel
tank’s Fleet Average Flammability Exposure to more than that specified
by paragraph M25.1 of appendix M to CS-25.
Release and Amendments of AMC No 1 to 21.A.3A(a)
- Released: [0] EASA ED Decision 2012/020/R of 30. Oct. 2012
- Amended by: -

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EASA Part 21 AMC & GM
Section A - Technical Requirements
Subpart A - General Provisions

AMC No 2 to 21.A.3A(a) Collection, investigation and analysis of data related to ETOPS
significant occurrences

(1) Holders of a type-certificate, restricted type-certificate, supplemental
Tracking, Reporting and
type-certificate or any other relevant approval deemed to have been Resolution System
issued under Part 21 and which includes extended range operation
with two-engined aeroplane (ETOPS) capability should implement

a specific tracking, reporting and resolution system for ETOPS

significant occurrences, suitable to ensure the initial and continued
fleet compliance with the applicable ETOPS reliability objectives.

This system should be part of the system for collection, investigation
and analysis of data required by 21.A.3A(a).

Appropriate coordination should exist between engine TC holder, Coordination
propeller TC holder and APU ETSO authorisation holder with the
aircraft TC holder to ensure compliance with the ETOPS reliability

objectives.

AMC 20-6
(2) For tracking, reporting and resolution of ETOPS significant
Occurrence Reporting
occurrences refer to the latest edition of AMC 20-6
(see AMC-20 document).

Release and Amendments of AMC No 2 to 21.A.3A(a)
- Released: [0] EASA ED Decision 2012/020/R of 30. Oct. 2012
- Amended by: -

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document at any time. In this respect, only the official EASA publications are applicable. Page 1 of 1
EASA Part 21 AMC & GM
Section A - Technical Requirements
Subpart A - General Provisions

GM 21.A.3A(a) The system for collection, investigation and analysis of data

In the context of this requirement the word «Collection» means, the
Collection
setting up, of systems and procedures which will enable relevant
malfunctions, failures and defects to be properly reported when they
occur.
Release and Amendments of GM 21.A.3A(a)
- Released: [0] EASA ED Decision 2012/020/R of 30. Oct. 2012
- Amended by: -

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EASA Part 21 AMC & GM
Section A - Technical Requirements
Subpart A - General Provisions

AMC 21.A.3A(b)(2) Reporting to the Agency

Within the overall limit of 72 hours the degree of urgency for submission
72 hours
of a report should be determined by the level of hazard judged to have
resulted from the occurrence.

Where an occurrence is judged by the person identifying the possible

unsafe condition to have resulted in an immediate and particularly
Unsafe conditions
significant hazard the Agency (or the competent authority of the Member
State as required) expects to be advised immediately and by the fastest

possible means (telephone, fax, email, telex, etc.) of whatever details
Initial Report
are available at that time.

This initial report must be followed up by a full written report within 72

hours.

A typical example would be an uncontained engine failure resulting in

damage to aircraft primary structure.

Delay
Where the occurrence is judged to have resulted in a less immediate
and less significant hazard, report submission may be delayed up to the
maximum of three days in order to provide more details.
Release and Amendments of AMC 21.A.3A(b)(2)
- Released: [0] EASA ED Decision 2012/020/R of 30. Oct. 2012
- Amended by: -

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document at any time. In this respect, only the official EASA publications are applicable. Page 1 of 1
EASA Part 21 AMC & GM
Section A - Technical Requirements
Subpart A - General Provisions

GM 21.A.3A(b) Occurrence reporting

For occurrence reporting, refer the latest edition of AMC 20-8,
AMC 20-8
(see AMC 20 document). Occurrence Reportung
Release and Amendments of GM 21.A.3A(b)
- Released: [0] EASA ED Decision 2012/020/R of 30. Oct. 2012
- Amended by: -

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document at any time. In this respect, only the official EASA publications are applicable. Page 1 of 1
EASA Part 21 AMC & GM
Section A - Technical Requirements
Subpart A - General Provisions

AMC 21.A.3B(b) Unsafe condition

An unsafe condition exists if there is factual evidence (from service

experience, analysis or tests) that:

(a) An event may occur that would result in fatalities, usually with
the loss of the aircraft, or reduce the capability of the aircraft or the Fatalities

ability of the crew to cope with adverse operating conditions to the

extent that there would be:

(i) A large reduction in safety margins or functional capabilities, or

(ii) Physical distress or excessive workload such that the flight crew

cannot be relied upon to perform their tasks accurately or

completely, or
(iii) Serious or fatal injury to one or more occupants

unless it is shown that the probability of such an event is within the
limit defined by the applicable certification specifications, or

Fatal injury to persons
(b) There is an unacceptable risk of serious or fatal injury to
other than occupants
persons other than occupants, or

(c) Design features intended to minimise the effects of survivable Intended Function

accidents are not performing their intended function.

Note 1: Non-compliance with applicable certification specifications
is generally considered as an unsafe condition, unless it is shown that
possible events resulting from this non-compliance do not constitute an
unsafe condition as defined under paragraphs (a), (b) and (c).

Note 2: An unsafe condition may exist even though applicable
airworthiness requirements are complied with.

Note 3: The above definition covers the majority of cases where the
Agency considers there is an unsafe condition.
There may be other cases where overriding safety considerations may
lead the Agency to issue an airworthiness directive.

Note 4: There may be cases where events can be considered as an
unsafe condition if they occur too frequently (significantly beyond the
applicable safety objectives) and could eventually lead to consequences
listed in paragraph (a) in specific operating environments.
Although having less severe immediate consequences than those listed
in paragraph (a), the referenced events may reduce the capability of the
aircraft or the ability of the crew to cope with adverse operating
conditions to the extent that there would be, for example, a significant
reduction in safety margins or functional capabilities, a significant
increase in crew workload, or in conditions impairing crew efficiency, or
discomfort to occupants, possibly including injuries.

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EASA Part 21 AMC & GM
Section A - Technical Requirements
Subpart A - General Provisions

Release and Amendments of AMC 21.A.3B(b)
- Released: [0] EASA ED Decision 2012/020/R of 30. Oct. 2012
- Amended by: -

This document is prepared and maintained with accuracy by ddpConcepts GmbH | CH-6373 Ennetbürgen.
Last Accuracy Check: 14. July 2014
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document at any time. In this respect, only the official EASA publications are applicable. Page 2 of 2