Title

Description

A. AIRCRAFT CONFIGURATION

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, or the declared configuration of a product, as laid down in the airworthiness data sheet (for aircraft subject to a declaration of design compliance), common to all products of that type. With the exception of changes contained in the certification specifications referred to in point 21A.90B of Annex I (Part 21), or points 21L.A.62 or 21L.A.102 of Annex Ib (Part 21 Light) to Regulation (EU) No 748/2012, any changes to type design shall be approved or if relevant, declared and, for those embodied, shall be recorded with the reference to the approval or declaration.

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 to this airworthiness limitation is (are) complied with.

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 21 point 21.A.3B or Part 21 Light point 21L.A.4)

B. AIRCRAFT OPERATION

B.1

Aircraft documents

Aircraft certificates and documents necessary for operations.

B.2

Flight Manual

A manual, associated with the certificate of airworthiness, containing limitations within which operation of the aircraft is to 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 that the aircraft is capable of operating within the approved envelope.

B.4

Markings & placards

Markings and placards are defined in the individual aircraft type design. Some information may also be found in the Type Certificate Data Sheet, the Supplemental Type Certificates, the Flight Manual, the Aircraft Maintenance Manual, the Illustrated Parts Catalogue, airworthiness data sheet (for aircraft subject to a declaration of design compliance), etc.

B.5

Operational requirements

Items required to be installed to perform a specific type of operation.

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 may include, amongst others, the Minimum Equipment List system, the Configuration Deviation List system and deferred defects management.

Title

Description

C. AIRCRAFT MAINTENANCE

C.1

Aircraft Maintenance Programme

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

C.2

Component control

The component control should consider a twofold objective for component maintenance:

— maintenance for which compliance is mandatory;

— maintenance for which compliance is recommended.

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 point 21A.431B of Annex I (Part 21) or points 21L.A.202 or 21L.A.222 of Annex Ib (Part 21 Light) to Regulation (EU) No 748/2012), 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.

C.4

Records

Continuing Airworthiness records are defined in M.A.305 and M.A.306 and related AMC.

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, or the declared configuration of a product, as laid down in the airworthiness data sheet (for aircraft subject to a declaration of design compliance), common to all products of that type. With the exception of changes contained in the certification specifications referred to in point 21A.90B of Part 21 or points 21L.A.62 or 21L.A.102 of Part 21 Light, any changes to type design shall:

-            be approved and, for those embodied, shall be recorded with the reference to the approval; or

-           be subject to a declaration of design compliance and, for those embodied, shall be recorded with the reference to the declaration of design compliance.

Supporting information

Typical inspection items

The type design consists of:

1.          the drawings and specifications, and a listing of those drawings and specifications, necessary to define the configuration and the design features of the product (i.e. the aircraft, its components, etc.) shown to comply with the applicable type-certification basis and environmental protection requirements;

2.          information on materials and processes and on methods of manufacture and assembly of the product necessary to ensure the conformity of the product;

3.          an approved Airworthiness Limitation Section (ALS) of the Instructions for Continued Airworthiness (ICA); and

4.          any other data necessary to allow by comparison the determination of the airworthiness, the characteristics of noise, fuel venting, and exhaust emissions (where applicable) of later products of the same type.

The individual aircraft design is made of the type design supplemented with changes to the type design (e.g. modifications) embodied on the considered aircraft.

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.

1.          Use the current type certificate data sheets or airworthiness data sheet (airframe, engine, propeller as applicable) and check that the aircraft conforms to its type design (correct engine installed, seat configuration, etc.).

2.          Check that changes have been properly approved (approved data is used) or declared (declared data is used).

3.          Check for unintentional deviations from the approved type design or from the design subject to a declaration of design compliance, sometimes referred to as concessions, divergences, or non-conformances, Technical Adaptations, Technical Variations, etc.

4.          Check cabin configuration (LOPA).

5.          Check for embodiment of STC’s, and, if any Airworthiness Limitations Section (ALS)/ FM/MEL/WBM and revisions are needed, they have been approved and complied with.

a.           Aircraft S/N applicable

b.           Applicable engines

c.           Applicable APU

d.           Max. certified or declared weights

e.           Seating configuration

f.            Exits

6.          Check that the individual aircraft design/configuration is properly established and used as a reference.

-           21.A.31

-           21.A.41

-           21.A.90A

-           21.A.90B

-           21L.A.26

-           21L.A.46

-           21L.A.61

-           21L.A.62

-           21L.A.101

-           21L.A.102

-           M.A.304

-           M.A.305

-           M.A.401

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 instructions whose compliance is mandatory as part of the type design. They apply to some scheduled or unscheduled instructions that have been developed to prevent and/or to detect the most severe failure.

They mainly apply to maintenance (mandatory modification, replacement, inspections, checks, etc., but can also apply to instructions to control critical design configurations (for example Critical Design Configuration Control Limitations (CDCCL) for the fuel tank safety).

1.          Check that the Aircraft Maintenance Programme (AMP) reflects airworthiness limitations and associated instructions (standard or alternative) issued by the relevant design approval holders or the declarant of a declaration of design compliance and is approved by the competent authority, if applicable.

2.          Check that the aircraft and the components thereof comply with the approved AMP.

3.          Check the current status of life-limited parts. The current status of life-limited parts is to be maintained throughout the operating life of the part.

Typical Airworthiness Limitation items:

-           Safe Life ALI (SL ALI)/Life-limited parts,

-           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

-           21.A.31

-           21.A.7

-           21L.A.9

-           21L.A.26

-           CS 22.1529

-           CS 23.1529, Appendix G, para. G25.4

-           CS 25.1529, Appendix H, para. H25.4

-           CS 27.1529, Appendix A, para. A27.4

-           CS 29.1529, Appendix A, para. A29.4

-           CS 31HB.82

-           CS-APU 30

-           CS-E 25

-           CS-P 40

-           CS VLR.1529, Appendix A, para. A.VLR.4

-           M.A.302

-           M.A.305

-           M.A.710(a)(7)

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 21 point 21A.3B or Part 21 Light point 21L.A.4).

Supporting information

Typical inspection items

Any Airworthiness Directive issued by a State of Design for an aircraft imported from a third country, or for an engine, propeller, part or appliance imported from a third country and installed on an aircraft registered in a Member State, shall apply unless the Agency has issued a different Decision before the date of entry into force of that airworthiness directive.

1.          Check if all ADs applicable to the airframe, engine(s), propeller(s) and equipment have been incorporated in the AD-status, including their revisions.

2.          Check records for correct AD applicability (including ADs incorrectly listed as non-applicable).

3.          Check by sampling in the current AD status that applicable ADs have been or are 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

-           21.A.3B

-           21.B.326

-           21.B.327

-           21L.A.4

-           21L.B.23

-           21L.B.162

-           M.A.303

-           M.A.305(d) & (h)

-           M.A.401(a) & (b)

-           M.A.501(b)

-           M.A.503(a)

-           M.A.504(a)2

-           M.A.504 & AMC M.A.504(c) § 1 (f)

-           M.A.613 & AMC M.A.613(a) § 2.4.3, 2.5.2, 2.6.1(h) & 2.8(b)

-           M.A.708(b)8

-           M.A.709(a)

-           M.A.710(a)5

-           M.A.801 & AMC M.A.801(h)

B.1

Aircraft documents

Aircraft certificates and documents necessary for operations.

Supporting information

Typical inspection items

The aircraft certificates and documents necessary for operations may include, but are not necessarily limited to:

-           Certificate of Registration;

-           Certificate of Airworthiness;

-           Noise certificate;

-           Aircraft certificate of release to service;

-           Technical log book, if required;

-           Airworthiness Review Certificate;

-           Etc.

1.          Check that all certificates and documents pertinent to the aircraft and necessary for operations (or copies, as appropriate) are on board.

2.          Check C of A modification/Aircraft identification.

3.          Check that noise certificate corresponds to aircraft configuration.

4.          Check Permit to fly and Flight Condition when necessary.

5.          Check that there is an appropriate aircraft certificate of release to service.

Reference documents: EASA

-           Part-21 Subpart H

-           Part 21 Light Subpart H

-           21.A.175

-           21.A.177

-           21.A.182

-           21L.A.144

-           21L.A.145

-           Part-21 Subpart I

-           Part 21 Light Subpart I

-           Part-21 Subpart P

-           Part 21 Light Subpart P

-           Part-21 Subpart Q

-           Part 21 Light Subpart Q

-           21.A.801

-           21.A.807

-           21L.A.253

-           M.A.201(a)(3)

-           M.A.801

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 status/configuration of the aircraft. When it does not, it may provide flight crew members with wrong information.

This may lead to errors and/or to override limitations that could contribute to severe failure.

1.          Check the conformity of the Flight Manual (FM), latest issue, with aircraft configuration, including modification status, (AD, SB, STC etc.).

2.          Check:

-            the FM approval, revision control, Supplement to FM;

-            the impact of modification status on noise and weight & balance;

-            additional required manuals (QRH/FCOM/OM-B etc.);

-            FM limitations.

Reference documents: EASA

-           21.A.174(b)2(iii), (b)3(ii)

-           21.A.204(b)1(ii), (b)2(i)

-           21L.A.143

-           21L.A.163

-           M.A.305, AMC M.A.305(d)

-           M.A.710(a)2

-           M.A.710(c)2

-           AMC M.A.710(a)1

-           AMC M.A.901(d) and (g)

-           M.A.902(b)3

-           AMC M.A.904(a)(2) points 2(c) and 2(k)

-           AMC M.A.904(b) point (c)

B.3

Mass & balance

Mass and balance data is required to make sure that 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 configuration of the aircraft. When it does not, the aircraft might be operated outside the certified or declared operating envelope.

1.          Check that mass and balance report is valid, considering current configuration.

2.          Make sure that modifications and repairs are taken into account in the report.

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

-           M.A.305(d)5

-           M.A.708(b)(10)

-           M.A.710(a)(9), AMC M.A.710(a)1

-           Part-CAT: CAT.POL.MAB.100 and related AMCs/GM

-           Part-NCC: NCC.POL.105 and related AMC/GM

-           Part-NCO: NCO.POL.105 and related AMC/GM

-           Part-SPO: SPO.POL.105 and related AMC/GM

B.4

Markings & placards

Markings and placards are defined in the individual aircraft type design. Some information may also be found in the TCDS, data sheet for airworthiness (Part 21 Light Subpart C), the Supplemental Type Certificates (STCs), the FM, the AMM, the IPC, etc.

Supporting information

Typical inspection items

Markings and placards on instruments, equipment, controls, etc. shall include such limitations or information as necessary for the direct attention of the crew during flight.

Markings and placards or instructions shall be provided to give any information that is essential to the ground handling in order to preclude the possibility of mistakes in ground servicing (e.g. towing, refuelling) that could pass unnoticed and that could jeopardise the safety of the aircraft in subsequent flights.

Markings and placards or instructions shall be provided to give any information essential in the prevention of passenger injuries.

National registration markings must be installed. They include registration, possible flag, fireproof registration plate.

Product data plates must be installed.

When markings and placards are missing, or unreadable, or not properly installed, mistakes or aircraft damages may occur and could subsequently contribute to a severe failure.

1.          Check that the required markings and placards are installed on the aircraft, especially the emergency exit markings instructions and passenger information signs and placards.

2.          Check that all installed placards are readable.

3.          Check the Flight Manual versus the instruments.

(General Aviation usually).

4.          Check registration markings, including State of Registry fireproof nameplate.

5.          Check product data plates.

Examples of markings & placards:

-            door means of opening,

-            each compartment’s weight/load limitation/placards stating limitation on contents,

-            passenger information signs, including no smoking signs,

-            emergency exit marking,

-            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

-           21.A.175

-           21.A.715

-           21.A.801

-           21.A.803

-           21.A.804

-           21.A.805

-           21.A.807

-           21L.A.253

-           21L.A.254

-           21L.A.255

-           relevant CS for the aircraft type being inspected

-           M.A.501

-           M.A.710(c)

-           AMC M.A.504(e)

-           AMC M.A.603(c)

-           AMC M.A.904(a)(2) points 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 code including national requirements.

In case of malfunction, it can create a hazardous situation. Especially emergency equipment needs attention during this inspection.

1.          Check permits & approvals required for type of operation.

2.          Check for the presence and serviceability of equipment required by operational approvals.

3.          Check safety equipment, check that emergency equipment is readily accessible.

Reference documents: EASA

-           M.A.201(a)(2)

-           Part-21 Subpart I

-           Part 21 Light Subpart I

-           Part-CAT, Part-NCC, Part-NCO, Part-SPO Subpart D ‘Instruments, Data and Equipment’.

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 should also consider defects found during the physical inspection.

1.          Check that the deferred defects have been identified, recorded, and rectified/deferred in accordance with approved procedures and within approved time limits.

2.          Check that operations outside published approved or declared (in accordance with Part 21 Light Subpart C) data have only been performed under a Permit to Fly or under flexibility provisions (Article 71 of Regulation (EU) 2018/1139). 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 or declared (in accordance with Part 21 Light Subpart C) 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

-           M.A.301(b)

-           AMC M.A.301(b)

-           M.A.403

-           AMC M.A.710(a)

-           145.A.60

-           AMC 20-8

-           Regulation (EU) No 376/2014

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 scheduled maintenance tasks, the associated procedures and standard maintenance practices. It also includes the reliability programme, when required.

Tasks included in the maintenance programme can originate from:

-           tasks for which compliance is mandatory: instructions specified in repetitive Airworthiness Directives (AD), or in the Airworthiness Limitations Section (ALS), which may include Certification Maintenance Requirements (CMRs). The ALS is included in the Instructions for Continuing Airworthiness (ICA) of a design approval holder or a declarant of a declaration of design compliance;

-           tasks for which compliance is recommended: additional instructions specified in the Maintenance Review Board Report (MRBR), the Maintenance Planning Document (MPD), Service Bulletins (SB), or any other non-mandatory continuing airworthiness information issued by the design approval holder or the declarant of a declaration of design compliance;

-           additional or alternative instructions proposed by the owner or the continuing airworthiness management organisation once approved in accordance with point M.A.302(e).

The AMP shall contain details, including frequency, of all maintenance to be carried out, including any specific tasks linked to the type and the specificity of operations.

Review of AMP contents:

1.          Check that the AMP properly reflects mandatory continuing airworthiness instructions (ALIs, CMRs (the latest source documents’ revision. Sample check that tasks are implemented within approved compliance times and that no tasks have been omitted.

2.          Check how recommended scheduled maintenance tasks (such as TBO intervals, recommended through Service Bulletins, Service Letters, etc., the latest source documents’ revision) are considered when updating the AMP.

3.          Check that the AMP properly reflects the maintenance tasks specified in repetitive ADs.

4.          Check that the AMP properly reflects additional instructions for continuing airworthiness resulting from specific installed equipment or modifications embodied.

5.          Check that the AMP properly reflects additional instructions for continuing airworthiness resulting from repairs embodied.

6.          If applicable, check that the AMP properly reflects additional maintenance tasks required by specific approvals (e.g. RVSM, ETOPS, MNPS, B-RNAV).

7.          Check for any additional scheduled maintenance measures required due to the use of the aircraft and the operational environment.

8.          If applicable, check for proper identification of pilot-owner maintenance tasks and identification of the pilot-owner(s) or the alternative procedure described in AMC M.A.803 point 3.

9.          Check approval status of additional or alternative instructions (M.A.302(e)).

10.        Check if a reliability programme is present and active when required.

11.        Check if the AMP is approved by the competent authority directly, or by the CAMO via indirect approval procedure, or if it is a self-declared maintenance programme.

Review of aircraft compliance with an AMP:

12.        Check if the AMP used is valid for the aircraft, and is reviewed annually.

13.        Check if tasks are performed within the value(s) quoted in AMP and the source documents

14.        Sample check that no task has been omitted without justifications accepted by the Competent Authority (at the time of decision).

15.        Check the reporting of performed scheduled maintenance into the records system.

16.        Analyse the effectiveness of the AMP and reliability by reviewing the unscheduled tasks.

Reference documents: EASA

-           M.A.302 and its AMC

-           M.A.708(b)(1), (b)(2) and (b)(4)

-           M.A.803 and its AMC

C.2

Component control

The component control should consider a twofold objective for component 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 scheduled or unscheduled. Refer to KRE C.1 ‘Aircraft Maintenance Programme’.

Components with a mandatory life limitation must be permanently removed from service when, or before, their operating limitation is exceeded. The life limitation is controlled at the component level (in opposition to aircraft level).

Components which are ‘time-controlled components’ include the following:

-           components for which removal and restoration are scheduled, regardless of their level of failure resistance. Reference is made to hard time components: They are subject to periodic maintenance dealing with a deterioration that is assumed to be predictable (the overall reliability invariably decreases with age): Failure is less likely to occur before restoration is necessary;

-           components for which failure resistance can reduce and drop below a defined level: Inspections are scheduled to detect potential failures. Reference is made to ‘On-condition’ components: They are called such because components, which are inspected, are left in service (no further maintenance action taken) on the condition that they continue to meet specified performance standards.

Notes:

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

1.          Check that the mandatory maintenance tasks are identified as such and managed separately from recommendations.

2.          Sample check installed components (PN and SN) against aircraft records:

a.           Correct Part Number and Serial Number installed.

b.           Correct authorised release document available.

3.          Check the current status of time-controlled components, with due consideration to deferred items. They must identify:

a.           The affected components (Part Number and Serial Number).

b.           For components subject to a repetitive task: the task description and reference, the applicable threshold/interval, the last accomplishment data (date, the component’s total accumulated life in Hours, Cycles, Landings, Calendar time, as necessary) and the next planned accomplishment data.

c.           For components subject to an unscheduled task: the task description and reference, the accomplishment data (date, the component’s total accumulated life in Hours, Cycles, Landings, Calendar time, as necessary). Pay attention to ETOPS and CDCCL components.

4.          Check current status of life-limited parts. This status can be requested upon each transfer throughout the operating life of the part:

a.           The life limitation, the component’s total accumulated life, and the life remaining before the component’s life limitation is reached (indicating Hours, Cycles, Landings, Calendar time, as necessary).

b.           If relevant for the determination of the remaining life, a full installation history indicating the number of hours, cycles or calendar time relevant to each installation on these different types of aircraft/engine.

5.          Check if the aircraft maintenance programme and reliability programme results impact the component control.

6.          Check that life-limited and time controlled components are correctly marked during a physical survey.

Reference documents: EASA

-           21.A.805

-           21L.A.252

-           M.A.302

-           M.A.305

-           M.A.501

-           M.A.503

-           M.A.710

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 point 21A.431B of Part 21 or points 21L.A.202 or 21L.A.222 of Part 21 Light, 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 not be limited to the damage assessment, the rationale for the classification of the repair, the evidence that the repair has been designed in accordance with approved or declared (in accordance with Part 21 Light Subpart C) data, i.e. by reference to the appropriate manual, procedure or to a Part 21 or Part 21 Light repair design approval (or if relevant, the declaration), the drawings/material and accomplishment instructions, as well as the maintenance and operational instructions.

‘Repair status’ means a list of: 

-           the repairs embodied since the original delivery of (and still existent upon) the aircraft/engine/propeller/component; and

-           the un-repaired damage/degradations.

It also includes, either directly or by reference to supporting documentation (i.e. repair files), the substantiating data supporting compliance with the applicable airworthiness requirements. 

The repair status should identify the repair file reference, the 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.

1.          Sample the repair status to confirm it appropriately traces repairs and un-repaired damage/deteriorations.

2.          Sample repair files (at least one file for each type of repaired items) to check that repaired and unrepaired damage/deterioration have been assessed against the latest published approved repair data.

3.          Check that repair instructions detailed in the repair file comply with published approved repair data.

4.          Check that major repairs resulting in new or amended airworthiness limitations and associated mandatory instructions (including ageing aircraft programme) have been included in the aircraft maintenance programme.

5.          Check that new or amended maintenance instructions resulting from repairs have been considered for inclusion in the aircraft maintenance programme.

6.          Compare the repair status and the physical status of the repaired aircraft/engine(s)/propeller(s), and their repaired components (physical survey) in order to confirm the accuracy of the repair status. Sample embodied repairs to check their conformity against the repair files (physical survey).

Reference documents: EASA

-           21.A.431A

-           21.A.431B

-           21L.A.201

-           21L.A.202

-           21L.A.221

-           21L.A.222

-           M.A.304

-           AMC M.A.304

-           M.A.305

-           AMC M.A.305

-           M.A.401

-           AMC M.A.401

C.4

Records

Continuing Airworthiness records are defined in M.A.305 and M.A.306 and related AMC.

Supporting information

Typical inspection items

Retention/Transfer of the records is required so that the status of the aircraft and its components can be readily established at any time.

Task accomplishment is scheduled (one time or periodically), or unscheduled (e.g. following an event). Aircraft continuing airworthiness records (refer to logbooks, technical logbooks, component log cards or task cards) shall provide the status with regard to:

-           scheduled tasks:

-            one-time: life-limited parts status, modification status, repair status.

-            repetitive: maintenance programme status.

-           unscheduled tasks.

1.          Check the aircraft continuing airworthiness record system: M.A.305 and M.A.306, as applicable, require that certain records are kept for defined periods.

Pay attention to the continuity, integrity and traceability of records:

a.           integrity: Check that the data recorded is legible,

b.           continuity: Check that records are available for the applicable retention period,

c.           traceability: Check the link between operator/CAMO and maintenance documentation, traceability to approved or declared (in accordance with Part 21 Light Subpart C) data, traceability to appropriate release documents, etc.

2.          If applicable, make sure that the tech log system is used correctly, including:

a.           current aircraft release to service (including the maintenance statement) issued and

b.           pre-flight inspections signed-off by authorised persons;

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

-           M.A.305

-           M.A.306

-           M.A.307

-           M.A.801

-           AMC M.A.305

-           AMC M.A.306

-           AMC M.A.307