Part-M / AMC Amendment 9 / GM Amendment 3

Annex to ED Decision 2013/005/R

European Aviation Safety Agency

Acceptable Means of Compliance (AMC) and Guidance Material (GM) to Part-M

Annex to ED Decision 2013/005/R

I. Draft Decision Part-M - Annex to Decision 2013/005/R Annex I and Annex VIII to ED Decision 2003/19/RM of the Executive Director of the Agency of 28 November 2003, on ‘Acceptable means of compliance and guidance material to Commission Regulation (EC) No 2042/2003 of 20 November 2003 on the continuing airworthiness of aircraft and aeronautical products, parts and appliances, and on the approval of organisations and personnel involved in these tasks’, are hereby amended as follows: The text of the amendment is arranged to show deleted text, new text or new paragraph as shown below: 1. deleted text is shown with a strike through: deleted 2. new and changed text is highlighted with grey shading: new

Annex to ED Decision 2013/005/R

1. In AMC M.B.303 (b), now AMC1 M.B.303(b), the order of the subparagraphs is changed and the text is amended as follows: AMC1 M.B.303(b) Aircraft continuing airworthiness monitoring (*) SCOPE OF SURVEYS 2.1. The competent authority should undertake sample product surveys of aircraft on its register to verify that: (a) the condition of an aircraft as sampled is to a standard acceptable for the Certificate of Airworthiness/Airworthiness Review Certificate to remain in force, (b) the operator/owner’s management of the airworthiness of the aircraft is effective, (c) the approvals and licenses granted to organisations and persons continue to be applied in a consistent manner to achieve the required standards. A physical inspection of the aircraft is necessary during each ACAM survey (ramp or in-depth). 1.2. Sample product surveys of aircraft include: (a) in-depth surveys carried out during extensive maintenance that fully encompass selected aspects of an aircraft’s airworthiness, (b) ramp surveys carried out during aircraft operations to monitor the apparent condition of an aircraft’s airworthiness. (c) in-flight surveys, as deemed necessary by the competent authority. 3. When performing a ramp survey, the inspector(s) should make all possible efforts to avoid an unreasonable delay of the aircraft inspected. 2. A new AMC2 is added for M.B.303(b), it incorporates elements from AMC M.B.303(d), which is deleted. AMC2 M.B.303(b) Aircraft continuing airworthiness monitoring IN-DEPTH SURVEY 1. An ACAM in-depth survey is a sample inspection of the key risk elements (KREs) and should be performed during scheduled/extensive maintenance. Appendix III to GM 1 to M.B.303(b) provides guidance on KREs that can be used for planning and/or analysis of the inspections. 2. The survey should be a ‘deep cut’ through the elements or systems selected. 3. The record of an ACAM inspection should identify which KREs were inspected. 3. A new AMC is added for M.B.303(b): AMC3 M.B.303(b) Aircraft continuing airworthiness monitoring* KEY RISK ELEMENTS 1. The following KREs should be used for aircraft continuing airworthiness monitoring: (a) Type design and changes to type design (b) Airworthiness limitations (c) Airworthiness Directives

Annex to ED Decision 2013/005/R

(d) Aircraft documents (e) Flight Manual (f) Mass & Balance (g) Markings & placards (h) Operational requirements (i) Defect management (j) Aircraft Maintenance Programme (k) Component control (l) Repairs (m) Records 2. These KREs and their detailed components should be adapted to the complexity of the aircraft type being surveyed by retaining only those items that are applicable and relevant for the particular aircraft type. 4. New GM is added for M.B.303(b): GM1 M.B.303(b) Aircraft continuing airworthiness monitoring* KEY RISK ELEMENTS The KREs define the scope of continuing airworthiness. The list of KREs is intended to provide the basis for planning and control of the ACAM survey programme. It will ensure that the programme covers all aspects of continuing airworthiness. While it is not required to cover all KREs during a given inspection, the ACAM survey programme needs to ensure that there is no omission, i.e. certain KRE are never inspected. * See Appendices to Part-M - Appendix III to GM 1 M.B.303(b) 5. AMC M.B.303(d) is deleted, it is replaced by the new AMC2 to M.B.303(b) and new GM 1 to M.B.303(b). AMC M.B.303 (d) Aircraft continuing airworthiness monitoring 1. Appendix III to this AMC is an example format for an annual in depth survey programme. A sample of the 14 key risk airworthiness elements identified on the example should be assessed during each survey and the survey should include the aircraft as the product sample. The survey should be a ‘deep cut’ through the elements or systems selected and all findings should be recorded. Surveyors/inspectors in conjunction with the owners, operators and maintenance organisations should identify the root cause of each confirmed finding. 2. In addition, an annual ramp survey programme should be developed based on geographical locations, taking into account airfield activity, and focusing on key issues that can be surveyed in the time available without unnecessarily delaying the aircraft. 3. Surveyors/inspectors should be satisfied that the root cause found and the corrective actions taken are adequate to correct the deficiency and to prevent re-occurrence. 4. Where the aircraft continuing airworthiness monitoring survey visit can be linked to the oversight of an approved organisation then credit can be taken in the monitoring process of that approved organisation. 6. Appendix III to AMC M.B.303(d) is renumbered ‘Appendix III to GM1 M.B.303(b)’ and replaced by the following document:

Annex to ED Decision 2013/005/R

Appendix III to GM1 M.B.303(b) ‘KEY RISK ELEMENTS’

Title Description

The type design is the part of the approved configuration of a product, as laid down in the TCDS, common to all products of Type design and that type. With the exception of changes contained in the certification specifications referred to in Part 21 point 21A.90B or A.1 changes to type 21A.431B of the Annex (Part 21) any changes to type design shall be approved and, for those embodied, shall be recorded design with the reference to the approval.

Airworthiness An airworthiness limitation is a boundary beyond which an aircraft or a component thereof must not be operated, unless the A.2 limitations instruction(s) associated to this airworthiness limitation is (are) complied with.

An Airworthiness Directive means a document issued or adopted by the Agency, which mandates actions to be performed Airworthiness on an aircraft to restore an acceptable level of safety, when evidence shows that the safety level of this aircraft may A.3 Directives otherwise be compromised. (Part 21A.3B)

B.1 Aircraft documents Aircraft certificates and documents necessary for operations.

A manual, associated with the certificate of airworthiness, containing limitations within which operation of the aircraft is to B.2 Flight Manual be considered airworthy and, instructions and information necessary to the flight crew members for the safe operation of the aircraft.

B.3 Mass & balance Mass and balance data is required to make sure the aircraft is capable of operating within the approved envelope. Markings and placards are defined in the individual aircraft type design. Some information may also be found in the Type B.4 Markings & placards Certificate Data Sheet, the Supplemental Type Certificates, the Flight Manual, the Aircraft Maintenance Manual, the Illustrated Parts Catalogue, etc.

Operational Items required to be installed to perform a specific type of operation B.5 requirements

Defect management requires a system whereby information on faults, malfunctions, defects and other occurrences that cause or might cause adverse effects on the continuing airworthiness of the aircraft is captured. This system should be B.6 Defect management properly documented. It may include, amongst others, the Minimum Equipment List system, the Configuration Deviation List system and deferred defects management.

A document which describes or incorporates by reference the specific scheduled maintenance tasks and their frequency of Aircraft Maintenance C.1 completion, the associated maintenance procedures and related standard maintenance practices necessary for the safe Programme operation of those aircraft to which it applies.

The component control should consider a twofold objective for components maintenance: C.2 Component control - maintenance for which compliance is mandatory; - maintenance for which compliance is recommended.

Annex to ED Decision 2013/005/R

Title Description

All repairs and unrepaired damage/degradations need to comply with the instructions of the appropriate maintenance manual (e.g. the SRM, the AMM, the CMM) . With the exception of repairs contained in the certification specifications referred to in Part 21 point 21A.90B or 21A.431B of the Annex (Part 21), all repairs not defined in the appropriate maintenance manual C.3 Repairs need to be appropriately approved and recorded with the reference to the approval. This includes any damage or repairs to the aircraft/engine(s)/propeller(s), and their components. Continuing Airworthiness records are defined in M.A.305 and M.A.306 and related AMCs. C.4 Records

Annex to ED Decision 2013/005/R

A.1 Type design and changes to type design The type design is the part of the approved configuration of a product, as laid down in the TCDS, common to all products of that type. With the exception of changes contained in the certification specifications referred to in Part 21 point 21A.90B or 21A.431B of the Annex (Part 21) any changes to type design shall be approved and, for those embodied, shall be recorded with the reference to the approval.

Supporting information Typical inspection items

The type design consists of: 1. Use the current type certificate data sheets (airframe, engine, propeller as applicable) 1. the drawings and specifications, and a listing of those drawings and check that the aircraft conforms to its type design (correct engine installed, seat configuration, etc.). and specifications, necessary to define the configuration and the design features of the product (i.e. the aircraft, its 2. Check that changes have been approved properly (approved data is used, and a components, etc.) shown to comply with the applicable type- direct relation to the approved data). certification basis and environmental protection requirements; 3. Check for unintentional deviations from the approved type design, sometimes referred 2. information on materials and processes and on methods of to as concessions, divergences, or non-conformances, Technical Adaptations, manufacture and assembly of the product necessary to ensure Technical Variations, etc. the conformity of the product; 4. Check cabin configuration (LOPA). 3. an approved Airworthiness Limitation Section (ALS) of the 5. Check for embodiment of STC’s, and, if any Airworthiness Limitations Section (ALS)/ Instructions for Continued Airworthiness (ICA); and FM/MEL/WBM and revisions are needed, they have been approved and complied with. 4. any other data necessary to allow by comparison the a. Aircraft S/N applicable determination of the airworthiness, the characteristics of noise, b. Applicable engines fuel venting, and exhaust emissions (where applicable) of later products of the same type. c. Applicable APU The individual aircraft design is made of the type design d. Max. certified weights supplemented with changes to the type design (e.g. modifications) e. Seating configuration embodied on the considered aircraft. f. Exits Depending on the product State of Design, Bilateral Agreements 6. Check that the individual aircraft design/configuration is properly established and and/or Agency decisions on acceptance of certification findings used as a reference. exist and should be taken into account.

Reference documents: EASA - EASA Part 21.A.31 - EASA Part 21.A.41 - EASA Part 21.A.61 - EASA Part 21.A.90A - EASA Part 21.A.90B - EASA Part M.A.304 - EASA Part M.A.305 - EASA Part M.A.401

Annex to ED Decision 2013/005/R

A.2 Airworthiness limitations An airworthiness limitation is a boundary beyond which an aircraft or a component thereof must not be operated, unless the instruction(s) associated with this airworthiness limitation is complied with.

Supporting information Typical inspection items

Airworthiness limitations are exclusively associated with 1. Check that the Aircraft Maintenance Programme (AMP) reflects airworthiness instructions whose compliance is mandatory as part of the type limitations and associated instructions (standard or alternative) issued by the relevant design. They apply to some scheduled or unscheduled instructions design approval holders and is approved by the competent authority. that have been developed to prevent and/or to detect the most 2. Check that the aircraft and the components thereof comply with the approved AMP. severe failure. 3. Check the current status of life-limited parts. The current status of life-limited parts is They mainly apply to maintenance (mandatory modification, to be maintained throughout the operating life of the part. replacement, inspections, checks, etc., but can also apply to Typical Airworthiness Limitation items: instructions to control critical design configurations (for example Critical Design Configuration Control Limitations (CDCCL) for the - Safe Life ALI (SL ALI)/Life limited parts, fuel tank safety). - Damage Tolerant ALI (DT ALI)/Structure, including ageing aircraft structure, - Certification Maintenance Requirements (CMR), - Ageing Systems Maintenance (ASM), including Airworthiness Limitations for Electrical Wiring Interconnection System (EWIS), - Fuel Tank Ignition Prevention (FTIP)/Flammability Reduction Means (FRM), - CDCCL, check wiring if any maintenance carried out in same area - wiring separation, - Ageing fleet inspections mandated through ALS or AD are included in the AMP.

Reference documents: EASA - EASA Part 21A.31 - EASA Part 21A.61 - EASA CS 22.1529 - EASA CS 23.1529, Appendix G, para. G25.4 - EASA CS 25.1529, Appendix H, para. H25.4 - EASA CS 27.1529, Appendix A, para. A27.4 - EASA CS 29.1529, Appendix A, para. A29.4 - EASA CS 31HB.82 - EASA CS-APU 30 - EASA CS-E 25 - EASA CS-P 40 - EASA CS VLR.1529, Appendix A, para. A.VLR.4 - EASA Part M.A.302 - EASA Part M.A.305 - EASA Part M.A.710(a)(7)

Annex to ED Decision 2013/005/R

A.3 Airworthiness Directives An Airworthiness Directive means a document issued or adopted by the Agency, which mandates actions to be performed on an aircraft to restore an acceptable level of safety, when evidence shows that the safety level of this aircraft may otherwise be compromised (Part 21A.3B).

Supporting information Typical inspection items

Any Airworthiness Directive issued by a State of Design for an 1. Check if all ADs applicable to the airframe, engine(s), propeller(s) and equipment aircraft imported from a third country, or for an engine, have been incorporated in the AD-status, including their revisions. propeller, part or appliance imported from a third country and 2. Check records for correct AD applicability (including ADs incorrectly listed as noninstalled on an aircraft registered in a Member State, shall apply applicable). unless the Agency has issued a different Decision before the date 3. Check by sampling in the current AD status that applicable ADs have been or are of entry into force of that airworthiness directive. planned to be (as appropriate) carried out within the requirements of these Airworthiness Directives, unless otherwise specified by the Agency (AMOC). 4. Check that applicable ADs related to maintenance are included into the Aircraft Maintenance Programme. 5. Check that task-cards correctly reflect AD requirements or refer to procedures and standard practises referenced in ADs. 6. Sample during a physical survey some ADs for which compliance can be physically checked.

Reference documents: EASA - EASA PART 21.A.3B - EASA PART 21.B.60 - EASA PART 21.B.326 - EASA PART 21.B.327 - EASA PART M.A.201 & AMC M.A.201(h) § 4 - EASA PART M.A.303 - EASA PART M.A.305 § (d) & (h) - EASA PART M.A.401 § (a) & (b) - EASA PART M.A.501 § (b) - EASA PART M.A.503 § (a) - EASA PART M.A.504 § (a) 2 - EASA PART M.A.504 & AMC M.A.504(c) § 1 (f) - EASA PART M.A.613 & AMC M.A.613(a) § 2.4.3, 2.5.2, 2.6.1(h) & 2.8(b) - EASA PART M.A.708 § (b)8 - EASA PART M.A.709(a) - EASA PART M.A.710 § (a)5 - EASA PART M.A.801 & AMC M.A.801(h)

Annex to ED Decision 2013/005/R

B.1 Aircraft documents Aircraft certificates and documents necessary for operations.

Supporting information Typical inspection items

The aircraft certificates and documents necessary for operations 1. Check that all certificates and documents pertinent to the aircraft and necessary for may include, but are not necessarily limited to: operations (or copies, as appropriate) are on board. - Certificate of Registration; 2. Check C of A modification/Aircraft identification. - Certificate of Airworthiness; 3. Check that noise certificate corresponds to aircraft configuration. - Noise certificate; 4. Check Permit to fly and Flight Condition when necessary. - Aircraft certificate of release to service; 5. Check that there is an appropriate aircraft certificate of release to service. - Technical log book, if required; - Airworthiness Review Certificate; - Etc.

Reference documents: EASA - EASA Part 21 Subpart H - 21.A.175 - 21.A.177 - 21.A.182 - Part 21 Subpart I - Part 21 Subpart P - EASA Part 21 Subpart Q - 21.A.801 - 21.A.807 - EASA Part M.A.201(a)(2) - EASA Part M.A 801

Annex to ED Decision 2013/005/R

B.2 Flight Manual A manual, associated with the certificate of airworthiness, containing operational limitations, instructions and information necessary for the flight crew members for the safe operation of the aircraft.

Supporting information Typical inspection items

The Flight Manual needs to reflect the current 1. Check the conformity of the Flight Manual (FM), latest issue, with aircraft status/configuration of the aircraft. When it does not, it may configuration, including modification status, (AD, SB, STC etc.). provide flight crew members with wrong information. 2. Check: This may lead to errors and/or to override limitations that could - the FM approval, revision control, Supplement to FM; contribute to severe failure. - the impact of modification status on noise and weight & balance; - additional required manuals (QRH/FCOM/OM-B etc.); - FM limitations.

Reference documents: EASA - EASA Part 21.A.174(b), 2(iii), (b), 3(ii) - EASA Part 21.A.204(b)1(ii), (b)2(i) - EASA Part M.A. 305, AMC M.A. 305(d) - EASA Part M.A.710(a), 2 - EASA Part M.A. 710(c), 2 - EASA AMC M.A.710(a), 1 - EASA AMC M.A.901(b), (g) - EASA AMC M.A.902(b), 3 - EASA AMC M.A.904(a), 2(c) and (k) - EASA AMC M.A.904(b), (c)

Annex to ED Decision 2013/005/R

B.3 Mass & balance Mass and balance data is required to make sure the aircraft is capable of operating within the approved envelope.

Supporting information Typical inspection items

The mass and balance report needs to reflect the actual 1. Check that mass and balance report is valid, considering current configuration. configuration of the aircraft. When it does not, the aircraft might 2. Make sure that modifications and repairs are taken into account in the report. be operated outside the certified operating envelope. 3. Check that equipment status is recorded on the mass and balance report. 4. Compare current mass and balance report with previous report for consistency.

Reference documents: EASA - EASA Part M.A.305(d)5 - EASA Part M.A.708(b)(10) - EASA Part M.A.710(a)(9),AMC M.A.710 (1) - EASA Part-CAT: CAT.POL.MAB.100 and related AMCs/GM

Annex to ED Decision 2013/005/R

B.4 Markings & placards Markings and placards are defined in the individual aircraft type design. Some information may also be found in the TCDS, the Supplemental Type Certificates (STC), the FM, the AMM, the IPC, etc.

Supporting information Typical inspection items

Markings and placards on instruments, equipment, controls, etc. 1. Check that the required markings and placards are installed on the aircraft, shall include such limitations or information as necessary for the especially the emergency exit markings instructions and passenger information direct attention of the crew during flight. signs and placards. Markings and placards or instructions shall be provided to give 2. Check that all installed placards are readable. any information that is essential to the ground handling in order 3. Check the Flight Manual versus the instruments. to preclude the possibility of mistakes in ground servicing (e.g. (General Aviation usually). towing, refuelling) that could pass unnoticed and that could 4. Check registration markings, including State of Registry fireproof nameplate. jeopardise the safety of the aircraft in subsequent flights. 5. Check product data plates. Markings and placards or instructions shall be provided to give any information essential in the prevention of passenger injuries. Examples of markings & placards: National registration markings must be installed. They include - door means of opening, registration, possible flag, fireproof registration plate. - each compartment’s weight/load limitation/placards stating limitation on Product data plates must be installed. contents, When markings and placards are missing, or unreadable, or not - passenger information signs, including no smoking signs, properly installed, mistakes or aircraft damages may occur and - emergency exit marking, could subsequently contribute to a severe failure. - pressurised cabin warning, - calibration placards, - cockpit placards and instrument markings, - O² system information data, - accesses to the fuel tanks with flammability reduction means (CDCCL), - fuelling markings (fuel vent, fuel dip stick markings), - EWIS identification, - towing limit markings, - break-in markings, - inflate tyres with nitrogen, - RVSM + static markings.

Reference documents: EASA - EASA Part 21A.175 - EASA Part 21A.715 - EASA Part 21A.801 - EASA Part 21A.803 - EASA Part 21A.804

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- EASA Part 21A.805 - EASA Part 21A.807 - relevant CS for the aircraft type being inspected - EASA Part M.A.501 - EASA Part M.A.710(c) - EASA AMC M.A.504(e) - EASA AMC M.A.603(c) - EASA AMC M.A.904(a)(2), para. 2.f. & 2.k.

B.5 Operational requirements Requirements for the type of operation are complied with (e.g. equipment, documents, approvals).

Supporting information Typical inspection items

This includes all equipment required by the applicable operational 1. Check permits & approvals required for type of operation. code including national requirements. 2. Check for the presence and serviceability of equipment required by operational In case of malfunction, it can create a hazardous situation. approvals. Especially emergency equipment needs attention during this 3. Check safety equipment, check that emergency equipment is readily accessible. inspection.

Reference documents: EASA - EASA Part M.A.201(a)(2) - EASA Part 21 Subpart I - EASA Part-CAT, Subpart D ‘Instruments, Data and Equipment’

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B.6 Defect management Defect management requires a system whereby information on faults, malfunctions, defects and other occurrences that cause or might cause adverse effects on the continuing airworthiness of the aircraft is captured. This system should be properly documented. It includes, amongst others, the MEL system, the CDL system and deferred defects management.

Supporting information Typical inspection items

This KRE addresses the effectiveness of defect management, it 1. Check that the deferred defects have been identified, recorded, and should also consider defects found during the physical inspection. rectified/deferred in accordance with approved procedures and within approved time limits. 2. Check that operations outside published approved data have only been performed under a Permit to Fly or under flexibility provisions (Basic Regulation Article 14). Sample on: a. TLB and hold item list, b. maintenance task cards, c. engine shop report, d. (major) component shop report, e. maintenance/repair/modification working party files after embodiment of modifications or repairs, f. occurrence reporting data, g. communications between the user of maintenance data and the maintenance data author in case of inaccurate, incomplete, ambiguous procedures and practices. 3. Check that the consequences of the deferral have been managed with Operation/Crew. 4. Check that defects are being deferred in accordance with approved data (current revision of the MEL, CDL, aircraft maintenance programme). 5. Compare physical location of parts/serial numbers with recorded locations to identify undocumented parts swaps for troubleshooting.

Reference documents: EASA /EU - EASA Part M.A.301(2) - AMC M.A.301-2 - EASA Part M.A.403 - AMC M.A.710(a) Airworthiness review - EASA Part 145.A.60 - EASA Part 145.A.45(c) - EASA Part 21 AMC 20-8 - EU Directive 2003/42/EC on occurrence reporting

Annex to ED Decision 2013/005/R

C.1 Aircraft Maintenance Programme A document which describes the specific scheduled maintenance tasks and their frequency of completion, related standard maintenance practices and the associated procedures necessary for the safe operation of those aircraft to which it applies.

Supporting information Typical inspection items

The Aircraft Maintenance Programme (AMP) is intended to include Review of AMP contents: scheduled maintenance tasks, the associated procedures and 1. Check that the AMP properly reflects mandatory continuing airworthiness standard maintenance practises. It also includes the reliability instructions (ALIs, CMRs (the latest source documents’ revision. Sample check programme, when required. that tasks are implemented within approved compliance times and that no tasks Tasks included in the maintenance programme can originate have been omitted. from: 2. Check how recommended scheduled maintenance tasks (such as TBO intervals, - tasks for which compliance is mandatory: instructions recommended through Service Bulletins, Service Letters, etc…, the latest source specified in repetitive Airworthiness Directives (AD), or in the documents’ revision) are considered when updating the AMP. If applicable, check Airworthiness Limitations Section (ALS), which may include embodiment policy as required by M.A.301 point 7. Certification Maintenance Requirements (CMRs). The ALS is 3. Check that the AMP properly reflects the maintenance tasks specified in repetitive included in the Instructions for Continuing Airworthiness (ICA) ADs. of a design approval holder; 4. Check that the AMP properly reflects additional instructions for continuing - tasks for which compliance is recommended: additional airworthiness resulting from specific installed equipment or modifications instructions specified in the Maintenance Review Board Report embodied. (MRBR), the Maintenance Planning Document (MPD), Service 5. Check that the AMP properly reflects additional instructions for continuing Bulletins (SB), or any other non-mandatory continuing airworthiness resulting from repairs embodied. airworthiness information issued by the design approval holder; 6. If applicable, check that the AMP properly reflects additional maintenance tasks required by specific approvals (e.g. RVSM, ETOPS, MNPS, B-RNAV). - additional or alternative instructions proposed by the owner or the continuing airworthiness management organisation once 7. Check for any additional scheduled maintenance measures required due to the use approved in accordance with point M.A.302(d)(iii); of the aircraft and the operational environment. The AMP shall contain details, including frequency, of all 8. If applicable, check for proper identification of pilot-owner maintenance tasks and maintenance to be carried out, including any specific tasks linked identification of the pilot-owner(s) or the alternative procedure described in AMC to the type and the specificity of operations. M.A.803 point 3. 9. Check approval status of additional or alternative instructions (M.A.302(d)(iii)). 10. Check if a reliability programme is present and active when required.

Review of aircraft compliance with an AMP:

11. Check if the AMP used is valid for the aircraft, is approved and is amended correctly. 12. Check if tasks are performed within the value(s) quoted in AMP and the source documents 13. Sample check that no task has been omitted without justifications accepted by the Competent Authority (at the time of decision).

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14. Check the reporting of performed scheduled maintenance into the records system. 15. Analyse the effectiveness of the AMP and reliability by reviewing the unscheduled tasks.

Reference documents: EASA - EASA Part M.A.302 and its AMC. - EASA Part M.A.708(b)(1), (2), (4) - EASA Part M.A.803 and its AMC

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C.2 Component control The component control should consider a twofold objective for components maintenance: - maintenance for which compliance is mandatory. - maintenance for which compliance is recommended.

Supporting information Typical inspection items

Depending on each maintenance task, accomplishment is 1. Check that the mandatory maintenance tasks are identified as such and managed scheduled or unscheduled. Refer to KRE C.1 ‘Aircraft Maintenance separately from recommendations. Programme’. 2. Sample check installed components (PN and SN) against aircraft records: Components affected by scheduled maintenance: a. Correct Part Number and Serial Number installed. Life-limited components are of two types: b. Correct authorised release document available. - components subject to a certified life limit; 3. Check the current status of time-controlled components, with due consideration to - components subject to a service life limit. deferred items. They must identify: Components with a certified life-limit must be permanently a. The affected components (Part Number and Serial Number). removed from service when, or before, their operating limitation b. For components subject to a repetitive task: the task description and reference, is exceeded. The life limitation is controlled at the component the applicable threshold/interval, the last accomplishment data (date, the level (in opposition to aircraft level). component’s total accumulated life in Hours, Cycles, Landings, Calendar time, Components subject to a service life (‘time controlled as necessary) and the next planned accomplishment data. components’) include the following: c. For components subject to an unscheduled task: the task description and - components for which removal and restoration are reference, the accomplishment data (date, the component’s total accumulated scheduled, regardless of their level of failure resistance. life in Hours, Cycles, Landings, Calendar time, as necessary). Pay attention to Reference is made to hard time components: They are ETOPS and CDCCL components. subject to periodic maintenance dealing with a deterioration 4. Check current status of life-limited components. This status can be requested upon that is assumed to be predictable (the overall reliability each transfer throughout the operating life of the part: invariably decreases with age): Failure is less likely to occur a. The life limitation, the component’s total accumulated life, and the life before restoration is necessary; remaining before the component’s life limitation is reached (indicating Hours, - components for which failure resistance can reduce and drop Cycles, Landings, Calendar time, as necessary). below a defined level: Inspections are scheduled to detect b. If relevant for the determination of the remaining life, a full installation history potential failures. Reference is made to ‘On-condition’ indicating the number of hours, cycles or calendar time relevant to each components: They are called such because components, installation on these different types of aircraft/engine. which are inspected, are left in service (no further maintenance action taken) on the condition that they 5. Check if the aircraft maintenance programme and reliability programme results continue to meet specified performance standards. impact the component control. Notes: 6. Check that life-limited and time controlled components are correctly marked during a physical survey. 1. Restoration tasks for hard time components are not the same as ‘On-condition’ tasks, since they do not monitor gradual deterioration, but are primarily done to ensure the item may continue to remain in service until the next planned restoration. 2. Components subject to ‘condition-monitoring’ are permitted

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to remain in service without preventive maintenance until functional failure occurs. Reference is made to ‘fly-tofailure’. Such components are subject to unscheduled tasks.

Reference documents: EASA - EASA Part 21.A.805 - EASA Part M.A.302 - EASA Part M.A.305 - EASA Part M.A.501 - EASA Part M.A.503 - EASA Part M.A.710

Annex to ED Decision 2013/005/R

C.3 Repairs All repairs and unrepaired damage/degradations need to comply with the instructions of the appropriate maintenance manual (e.g. the SRM, the AMM, the CMM) . With the exception of repairs contained in the certification specifications referred to in Part 21 point 21A.90B or 21A.431B of the Annex (Part 21), all repairs not defined in the appropriate maintenance manual need to be appropriately approved and recorded with the reference to the approval. This includes any damage or repairs to the aircraft/engine(s)/propeller(s), and their components.

Supporting information Typical inspection items

The data substantiating repairs should include, but is not limited 1. Sample the repair status to confirm it appropriately traces repairs and un-repaired to, the damage assessment, the rationale for the classification of damage/deteriorations. the repair, the evidence the repair has been designed in 2. Sample repair files (at least one file for each type of repaired items) to check that accordance with approved data, i.e. by reference to the repaired and unrepaired damage/deterioration have been assessed against the appropriate manual, procedure or to a Part 21 repair design latest published approved repair data. approval, the drawings/material and accomplishment instructions, 3. Check that repair instructions detailed in the repair file comply with published as well as the maintenance and operational instructions. approved repair data. ‘Repair status’ means a list of: 4. Check that major repairs resulting in new or amended airworthiness limitations and - the repairs embodied since the original delivery of (and still associated mandatory instructions (including ageing aircraft programme) have been existent upon) the aircraft/engine/propeller/component; and included in the aircraft maintenance programme. - the un-repaired damage/degradations. 5. Check that new or amended maintenance instructions resulting from repairs have It also includes, either directly or by reference to supporting been considered for inclusion in the aircraft maintenance programme. documentation (i.e. repair files), the substantiating data 6. Compare the repair status and the physical status of the repaired supporting compliance with the applicable airworthiness aircraft/engine(s)/propeller(s), and their repaired components (physical survey) in requirements. order to confirm the accuracy of the repair status. Sample embodied repairs to The repair status should identify the repair file reference, the check their conformity against the repair files (physical survey). repair classification, the repaired item (i.e. aircraft/engine/propeller/component, and a precise location if necessary), and the date and total life in FH/FC accumulated by the item at the time of repair or finding of the un-repaired damage/degradations. Cross-reference to the aircraft maintenance programme should also be included, as necessary. Depending on the product State of Design, Bilateral Agreements and/or Agency Decisions on acceptance of certification findings exist and should be taken into account for the determination of acceptable data for repairs.

Reference documents: EASA - EASA Part 21.A.431A - EASA Part 21.A.431B - EASA Part M.A.304 - EASA AMC Part M.A.304

Annex to ED Decision 2013/005/R

- EASA Part M.A.305 - EASA AMCs to Part M.A.305 - EASA Part M.A.401 - EASA AMCs to Part M.A.401

C.4 Records Continuing Airworthiness records are defined in M.A.305 and M.A.306 and related AMCs.

Supporting information Typical inspection items

Retention/Transfer of the records is required so that the status of 1. Check the aircraft continuing airworthiness record system: M.A.305 and M.A.306, as the aircraft and its components can be readily established at any applicable, require that certain records are kept for defined periods. time. Pay attention to the continuity, integrity and traceability of records: Task accomplishment is scheduled (one time or periodically), or a. integrity: Check the data recorded is legible, unscheduled (e.g. following an event). Aircraft continuing b. continuity: Check that records are available for the applicable retention period, airworthiness records (refer to logbooks, technical logbooks, component log cards or task cards) shall provide the status with c. traceability: Check the link between operator/CAMO and maintenance regard to: documentation, traceability to approved data, traceability to appropriate release documents, etc. - scheduled tasks: 2. If applicable, make sure that the tech log system is used correctly, including: - one-time: life-limited parts status, modification status, repair status. a. current aircraft release to service (including the maintenance statement) issued and - repetitive: maintenance programme status. b. pre-flight inspections signed-off by authorised persons; - unscheduled tasks.

3. Check that any maintenance required following abnormal operation/event (such as overspeed, overweight operation, hard landing, excessive turbulence, and operation outside of Flight Manual limitations) has been performed, as applicable.

Reference documents: EASA - EASA Part M.A.305 - EASA Part M.A.306 - EASA Part M.A.307 - EASA Part M.A.801 - EASA AMCs to Part M.A.305 - EASA AMCs to Part M.A.306 - EASA AMC to Part M.A.307

Annex to ED Decision 2013/005/R

Abbreviations used: A/C Aircraft ACAM Aircraft Continuous Airworthiness Monitoring AD Airworthiness Directive ALI Airworthiness Limitation Items ALS Airworthiness Limitations Section AMM Aircraft Maintenance Manual AMP Aircraft Maintenance Programme APU Auxiliary Power Unit ASM Ageing Systems Maintenance B-RNAV Basic Area Navigation CAMO Continuing Airworthiness Management Organisation CDL Configuration Deviation List CDCCL Critical Design Configuration Control Limitations CMM Component Maintenance Manual CMR Certification Maintenance Requirement DT Damage Tolerant ED Executive Director of EASA ETOPS Extended Range Operations with Two-engined aeroplanes ETSO European Technical Standard Order EWIS Electrical Wiring Interconnection System EZAP Enhanced Zonal Analysis Procedure FCOM Flight Crew Operations Manual FDR Flight Data Recorder FM Flight Manual FRM Flammability Reduction Means FTIP Fuel Tank Ignition Prevention GA General Aviation ICA Instructions for Continuing Airworthiness IPC Illustrated Parts Catalogue KRE Key Risk Element LHIRF Lightning High Intensity Radiated Field LOPA Layout of Passenger Accommodation MCAI Mandatory Continuing Airworthiness Information MEL Minimum Equipment List MNPS Minimum Navigation Performance Specification MRB Maintenance Review Board MRBR Maintenance Review Board Report MPD Maintenance Planning Document NAA National Aviation Authority OEM Original Equipment Manufacturer OM Operations Manual OM-B Operations Manual Part-B PN Part Number QRH Quick Reference Handbook

Annex to ED Decision 2013/004/R

PWR Power RVSM Reduced Vertical Separation Minima SN Serial Number SB Service Bulletin SM Service Manual SRM Structural Repair Manual STC Supplemental Type Certificate TBO Time Between Overhauls TC Type Certificate TCDS Type Certificate Data Sheet TLB Technical Logbook TSO Technical Standard Order