--- title: "ML.A.302 Aircraft maintenance programme — Part-ML · Avioverse" description: "The maintenance of each aircraft shall be organised in accordance with an AMP." url: "https://avioverse.aero/regulations/easa/continuing-airworthiness/part-ml/section-a-technical-requirements/ml-a-302" --- # ML.A.302 Aircraft maintenance programme Annex Vb (Part-ML) · Regulation (EU) No 1321/2014 · EAR revision 2 Sep 2025 IR Implementing rule ## ML.A.302 Aircraft maintenance programme (a) The [maintenance](https://avioverse.aero/glossary/easa/maintenance) of each [aircraft](https://avioverse.aero/glossary/easa/aircraft) shall be organised in accordance with an AMP. (b) The AMP and any subsequent amendments thereto shall be, alternatively: (1) declared by the owner in accordance with point (c)(7) of point ML.A.302, where the [continuing airworthiness](https://avioverse.aero/glossary/easa/continuing-airworthiness) of the aircraft is not managed by a CAMO or CAO; (2) approved by the CAMO or CAO responsible for managing the continuing airworthiness of the aircraft. The owner declaring the AMP in accordance with point (b)(1) or the [organisation](https://avioverse.aero/glossary/easa/organisation) approving the AMP in accordance with point (b)(2) shall keep the AMP updated. (c) The AMP: (1) shall clearly identify the owner of the aircraft and the aircraft to which it relates, including any installed engine and propeller, as applicable; (2) shall include, alternatively: (a) the tasks or inspections contained in the applicable minimum inspection programme (MIP) referred to in point (d); (b) the instructions for continuing airworthiness (ICA) issued by the design approval holder (DAH); (c) the ICA issued by the declarant of a declaration of design compliance. (3) may include additional maintenance actions to those referred to in point (c)(2) or maintenance actions alternative to those referred to in point (c)(2)(b) at the proposal of the owner, CAMO or CAO, once approved or declared in accordance with point (b). Alternative maintenance actions to those referred to in point (c)(2)(b) shall not be less restrictive than those set out in the applicable MIP; (4) shall include all the mandatory continuing airworthiness information, such as repetitive ADs, the airworthiness limitation section (‘ALS’) of the ICAs, and specific maintenance requirements contained in the type certificate data sheet (‘TCDS’); (5) shall identify any additional maintenance tasks to be performed because of the specific aircraft type, aircraft configuration and type and specificity of operation, whereas the following elements shall be taken into consideration as a minimum: (a) specific installed equipment and modifications of the aircraft; (b) repairs carried out in the aircraft; (c) life-limited components and flight-safety-critical components; (d) maintenance recommendations, such as time between overhaul (‘TBO’) intervals, issued through service bulletins, service letters, and other non-mandatory service information; (e) applicable operational directives or requirements related to the periodic inspection of certain equipment; (f) special operational approvals; (g) use of the aircraft and operational environment; (6) shall identify whether the Pilot-owners are authorised to perform maintenance; (7) when declared by the owner, shall contain a signed statement by which the owner declares that this is the AMP for the particular aircraft registration and that he is fully responsible for its content and, in particular, for any deviations from the DAH’s recommendations; (8) when approved by the CAMO or CAO, shall be signed by this organisation, which shall retain records with the justification for any deviation introduced to the DAH’s recommendations; (9) shall be reviewed at least annually in order to assess its effectiveness, and this review shall be performed, alternatively: (a) in conjunction with the airworthiness review of the aircraft by the person who performs such an airworthiness review; (b) by the CAMO or CAO managing the continuing airworthiness of the aircraft in those cases where the review of the AMP is not performed in conjunction with an airworthiness review. If the review shows deficiencies of the aircraft linked with deficiencies in the content of the AMP, the AMP shall be amended accordingly. In this case the person performing the review shall inform the competent authority of the Member State of registry if he does not agree with the measures amending the AMP taken by the owner, CAMO or CAO. The competent authority shall decide which amendments to the AMP are necessary, raising the corresponding findings and, if necessary, reacting in accordance with point ML.B.304. (d) A MIP: (1) shall contain the following inspection intervals: (a) for aeroplanes, touring motor gliders (‘TMGs’) and balloons, every annual or 100-h interval, whichever comes first, to which a tolerance of 1 month or 10 h may be applied. The next interval shall be calculated as from the time the inspection takes place; (b) for sailplanes and powered sailplanes other than TMG, every annual interval to which a tolerance of 1 month may be applied. The next interval shall be calculated as from the time the inspection takes place; (2) shall contain the following, as applicable to the aircraft type: (a) servicing tasks as required by the DAH’s requirements; (b) inspection of markings; (c) review of weighing records and weighing in accordance with Regulation (EU) No 965/2012, Regulation (EU) 2018/395 and Regulation (EU) 2018/1976; (d) operational test of transponder (if installed); (e) functional test of the pitot-static system; (f) in the case of aeroplanes, as applicable to the aircraft power plant: (i) operational tests for power and revolutions per minute (rpm), magnetos, fuel and oil pressure, engine temperatures; (ii) for engines equipped with automated engine control, the published run-up procedure; (iii) for dry-sump engines, engines with turbochargers and liquid-cooled engines, an operational test for signs of disturbed fluid circulation; (iv) in respect of a power plant other than piston engine, the maintenance tasks as defined in the ICA issued by the DAH of the [aeroplane](https://avioverse.aero/glossary/easa/aeroplane); (g) inspection of the condition and attachment of the structural items, systems and components corresponding to the following areas: (i) for aeroplanes: airframe, cabin and cockpit, landing gear, wing and centre section, flight controls, empennage, avionics and electrics, power plant, clutches and gearboxes, propeller and miscellaneous systems, such as the ballistic rescue system; (ii) for sailplanes and powered sailplanes: airframe, cabin and cockpit, landing gear, wing and centre section, empennage, avionics and electrics, power plant (for powered sailplanes) and miscellaneous systems, such as removable ballast and/or drag chute and controls, as well as water ballast system; (iii) for hot-air balloons: envelope, burner, basket, fuel containers, equipment and instruments; (iv) for gas balloons: envelope, basket, equipment and instruments. As long as this Annex does not specify an MIP for aircraft other than aeroplanes, sailplanes and balloons, their AMP shall be based on the ICA issued by the DAH, as referred to in point (c)(2)(b). (e) By derogation from points (b) and (c), a declaration by the owner or an approval by a CAMO or CAO is not required, and an AMP document is not required to be produced when the following conditions are met: (1) all the ICA issued by the DAH are being followed without any deviations; (2) all maintenance recommendations, such as TBO intervals, issued through service bulletins, service letters, and other non-mandatory service information, are being followed without any deviations; (3) there are no additional maintenance tasks to be performed resulting from any of the following: (a) specific installed equipment and modifications of the aircraft; (b) repairs carried out in the aircraft; (c) life-limited components and flight-safety-critical components; (d) special operational approvals; (e) use of the aircraft and operational environment. (4) Pilot-owners are authorised to perform Pilot-owner maintenance. This derogation is not applicable if the pilot-owner or, in case of jointly-owned aircraft, any of the pilot-owners is not authorised to perform Pilot-owner maintenance because this has to be specified in the declared or approved AMP. (f) If the conditions provided for in points (e)(1) to (e)(4) are met, the AMP applicable to the aircraft shall consist of the following: (1) the ICA issued by the DAH; (2) the maintenance recommendations, such as TBO intervals, issued through service bulletins, service letters, and other non-mandatory service information; (3) the mandatory continuing airworthiness information, such as repetitive ADs, the ALS of the ICA and specific maintenance requirements contained in the TCDS; (4) the tasks due to specific operational or airspace directives or requirements in relation to particular instruments and equipment. IR · ML.A.302 — Regulation (EU) No 1321/2014 · Continuing Airworthiness Easy Access Rules · EAR revision 2 Sep 2025 AMC Acceptable means of compliance ## AMC1 ML.A.302 Aircraft maintenance programme (a) The [aircraft](https://avioverse.aero/glossary/easa/aircraft) should only be maintained according to a single [maintenance](https://avioverse.aero/glossary/easa/maintenance) programme at a given point in time. Where an owner wishes to change from one programme to another (e.g. from an AMP based on minimum inspection programme (MIP) to an AMP based on the data issued by the DAH or the declarant of a declaration of design compliance), certain additional maintenance may need to be carried out on the aircraft to implement this transition. (b) The maintenance programme may take the format of the standard template provided in AMC2 ML.A.302 (EASA Form AMP). This maintenance programme may include several aircraft registrations as long as the maintenance requirements for each registration are clearly identified. AMC · AMC1 ML.A.302 — Regulation (EU) No 1321/2014 · ED Decision 2023/013/R · Continuing Airworthiness Easy Access Rules · EAR revision 2 Sep 2025 AMC Acceptable means of compliance ## AMC2 ML.A.302 Aircraft maintenance programme EASA FORM AMP The following EASA Form AMP may be used to produce the AMP: | Part-ML [aircraft](https://avioverse.aero/glossary/easa/aircraft) [maintenance](https://avioverse.aero/glossary/easa/maintenance) programme (AMP) | | | | | | | | | | ---------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------- | ------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------- | - | ----- | ------------------------------------------------------------------------------------------------------------------------------------------------------------- | ----------------------------------------------------------- | ------------- | --- | -- | | Aircraft identification | | | | | | | | | | 1 | Registration(s): | | Type: | | | Serial no(s): | | | | | Owner: | | | | | | | | | Basis for the maintenance programme | | | | | | | | | | 2 | Instructions for [continuing airworthiness](https://avioverse.aero/glossary/easa/continuing-airworthiness) (ICA) | | | Minimum inspection programme (MIP) as detailed in the latest revision of AMC1 ML.A.302(d) Other MIP complying with ML.A.302(d) (List the tasks in Appendix A) | | | | | | Instructions for continuing airworthiness (ICA) | | | | | | | | | | 3 | Equipment manufacturer and type | | | Applicable ICA reference (revision/date not required assuming the latest revision will always be used) | | | | | | For aircraft other than balloons | | | | | | | | | | 3a | Aircraft (other than balloons) | | | | | | | | | 3b | Engine (if applicable) | | | | | | | | | 3c | Propeller (if applicable) | | | | | | | | | For balloons | | | | | | | | | | 3d | Envelope (only for balloons) | | | | | | | | | 3e | Basket(s) (only for balloons) | | | | | | | | | | | | | | | | | | | 3f | Burner(s) (only for balloons) | | | | | | | | | | | | | | | | | | | 3g | Fuel cylinders (only for balloons) | | | | | | | | | | | | | | | | | | | Additional maintenance requirements to the ICA or to the MIP (applicable to all AMPs) | | | | | | | | | | 4 | Indicate whether any of the following types of repetitive maintenance are included in the AMP (when replying ‘YES’, list the specific requirements in Appendix B) | | | | | | Yes | No | | | Maintenance due to specific equipment and modifications | | | | | | | | | | Maintenance due to repairs | | | | | | | | | | Maintenance due to life-limited components (This should be completed only if the MIP is used. Otherwise, this data is already part of the data issued by the DAH or the declarant of a declaration of design compliance used as a basis for the AMP.) | | | | | | | | | | Maintenance due to mandatory continuing airworthiness information (airworthiness limitations (ALIs), certification maintenance requirements (CMRs), specific requirements in the TCDS, etc.) | | | | | | | | | | Maintenance recommendations, such as time between overhaul (TBO) intervals, issued through service bulletins, service letters, and other non-mandatory service information | | | | | | | | | | Maintenance due to repetitive ADs | | | | | | | | | | Maintenance due to specific operational/airspace directives/requirements (altimeter, compass, transponder, etc.) | | | | | | | | | | Maintenance due to the type of operation or operational approvals | | | | | | | | | | Other | | | | | | | | | Maintenance tasks alternative to the ICA (not less restrictive than the MIP) | | | | | | | | | | 5 | Indicate whether there is any maintenance task alternative to the ICA (when replying ‘YES’, list the specific alternative maintenance tasks in Appendix C) | | | | | | Yes | No | | Pilot-owner maintenance (only for balloons not operated under Subpart-ADD, or sailplanes not operated under Subpart-DEC, or other aircraft operated under Part-NCO) Remark: pilot-owner maintenance is not allowed for aircraft operated by a commercial ATO/DTO | | | | | | | | | | 6 | Does the pilot-owner perform pilot-owner maintenance (ref. ML.A.803)? If yes, enter the name of the pilot-owner(s) authorised to perform such maintenance: Pilot-owner name:\_(NOTE)\_\_\_\_\_\_\_\_\_\_\_\_\_\_\_\_\_\_Licence number: (NOTE)\_\_\_\_\_\_\_\_\_\_\_\_\_\_\_\_\_\_ Signature: \_\_\_\_\_\_\_\_\_\_\_\_\_\_\_\_\_\_\_\_\_\_\_\_\_\_\_\_\_\_\_Date: \_\_\_\_\_\_\_\_\_\_\_\_\_\_\_\_\_\_\_\_\_\_\_\_\_\_\_\_\_\_\_\_\_ NOTE: It is possible to refer to a list in the case of jointly owned aircraft. | | | | | | Yes | No | | Approval/declaration of the maintenance programme (select the appropriate option) | | | | | | | | | | 7 | Declaration by the owner: | | | | Approval by the contracted CAMO/CAO: | | | | | | ‘I hereby declare that this is the maintenance programme applicable to the aircraft referred to in block 1, and I am fully responsible for its content and, in particular, for any alternatives tasks to the data issued by the DAH or the declarant of a declaration of design compliance.’ Signature/name/date: | | | | Approval reference no of the CAMO/CAO: Signature/name/date: | | | | | Certification statement | | | | | | | | | | 8 | ‘I will ensure that the aircraft is maintained in accordance with this maintenance programme and that the maintenance programme will be reviewed and updated as required.’ Signed by the person/[organisation](https://avioverse.aero/glossary/easa/organisation) responsible for the continuing airworthiness of the aircraft according to ML.A.201: Owner/Lessee/operator CAMO/CAO Name of owner/lessee/operator or CAMO/CAO approval number: Address: Telephone/fax: Email: Signature/date: | | | | | | | | | 9 | Appendices attached: Appendix A YES NO Appendix B YES NO Appendix C YES NO Appendix D YES NO | | | | | | | | | Appendix A — Minimum inspection programme (MIP) (only applicable if a MIP different from the one described in AMC1 ML.A.302(d) is used — see Section 2 above) | | ------------------------------------------------------------------------------------------------------------------------------------------------------------- | | Detail the tasks and inspections contained in the MIP being used. | | Appendix B — Additional maintenance requirements (include only if necessary — see Section 4 above) | | | | ------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------ | ---------------- | -------------------------------------------------------------------------------------------------- | | This appendix is supposed to include only the tasks which are included in the AMP, either at the recommended interval or at a different one. (All repetitive maintenance tasks not included here, or the interval differences, should be kept by the CAMO/CAO (when contracted) in their files with their corresponding justifications. Appendix D may optionally be used. Nevertheless, the owner/CAMO/CAO is responsible for taking into account all instructions, even if they are not adopted and listed here. The person performing the AR, if reviewing the AMP, is not responsible for the completeness of this appendix, but may do some sampling as part of the investigations and the findings discovered during the physical review). | | | | Task description | References | Interval (tick box if the selected interval differs from that required in the referenced document) | | Maintenance due to specific equipment and modifications | | | | | | | | | | | | Maintenance due to repairs | | | | | | | | | | | | Maintenance due to life-limited components (This should be only completed if the MIP is used. Otherwise, this data is already part of the data used as the basis for the AMP.) | | | | | | | | | | | | Maintenance due to mandatory continuing airworthiness instructions (ALIs, CMRs, specific requirements in the TCDS, etc.) | | | | | | | | | | | | Maintenance recommendations, such as TBO intervals, issued through service bulletins, service letters, and other non-mandatory service information | | | | | | | | Emergency locator transmitters and personal locator beacon — annual testing | EASA SIB 2019-09 | 1 Year | | (if not using MIP or equivalent ICA task) Transponder test | EASA SIB 2011-15 | 2 Years | | | | | | Maintenance due to repetitive ADs | | | | | | | | | | | | Maintenance due to specific operational/airspace directives/requirements (altimeter, compass, transponder, etc.) | | | | | | | | | | | | Maintenance due to the type of operation or operational approvals | | | | | | | | | | | | Other | | | | | | | | | | | | Appendix C — Maintenance tasks alternative to the ICA (not less restrictive than the MIP) (include only if necessary — see Sections 5 above) | | | | | ------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------ | -------------------- | --------------------------- | ---------------- | | Task description | Recommended interval | Alternative inspection/task | Amended interval | | When the ICA are used as the basis for the AMP, this appendix is used to include the tasks alternative to the ICA, which are included in the AMP. (When a CAMO/CAO is contracted, all elements justifying the deviations from the ICA should be kept by the CAMO/CAO and the organisation should provide a copy of these justifications to the owner.) | | | | | | | | | | | | | | | | | | | | | | | | | Appendix D — Additional information (optional) | | -------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------- | | This appendix may optionally be used to provide additional information, such as the complete list of AMP tasks or the list of documents (e.g. service bulletins) considered during the development of the AMP. | EASA Form AMP, Issue 2 AMC · AMC2 ML.A.302 — Regulation (EU) No 1321/2014 · ED Decision 2023/013/R · Continuing Airworthiness Easy Access Rules · EAR revision 2 Sep 2025 GM Guidance material ## GM1 ML.A.302 Aircraft maintenance programme The responsibilities associated with [maintenance](https://avioverse.aero/glossary/easa/maintenance) programmes developed in accordance with ML.A.302 are the following: (a) If the owner has contracted a CAMO or CAO in order to manage the [continuing airworthiness](https://avioverse.aero/glossary/easa/continuing-airworthiness) of the [aircraft](https://avioverse.aero/glossary/easa/aircraft), this [organisation](https://avioverse.aero/glossary/easa/organisation) is responsible for developing and approving a maintenance programme which: (1) indicates whether this programme is based on data from the DAH or the declarant of a declaration of design compliance, or based on the MIP described in ML.A.302(d); (2) identifies the owner and the specific aircraft, engine, and propeller (as applicable); (3) includes all mandatory continuing airworthiness information and any additional tasks derived from the assessment of the instructions issued by the DAH or the declarant of a declaration of design compliance; (4) justifies any deviations from the instructions issued by the DAH or the declarant of a declaration of design compliance; when those instructions are the basis for the AMP development, these deviations should not fall below the requirements of the MIP; and (5) is customised to the particular aircraft type, configuration and operation, in accordance with ML.A.302(c)(5). (b) If the owner has not contracted a CAMO or CAO in order to manage the continuing airworthiness of the aircraft, then the owner is responsible for developing and declaring the maintenance programme, assuming full responsibility for its content, and for any deviations from the instructions issued by the DAH or the declarant of a declaration of design compliance (ref. ML.A.201(f) and ML.A.302(c)(7)) and the possible consequences of such deviations. In this case, these deviations do not need to be justified, but are to be identified in the AMP. However, the maintenance programme still needs to comply with the requirements contained in ML.A.302(c), in particular with the obligation to not fall below the requirements of the MIP and to comply with the mandatory continuing airworthiness information. (c) The content of the owner-declared maintenance programme cannot be challenged up front either by the competent authority or by the contracted maintenance organisation. This declared maintenance programme is the basis for adequate planning of maintenance, as well as for the ARs and the aircraft continuing airworthiness monitoring (ACAM) inspections in accordance with ML.B.303. Nevertheless, the maintenance programme will be subject to periodic reviews at the occasion of the AR and, in case of discrepancies, linked with deficiencies in the content of the maintenance programme, the owner shall amend the maintenance programme accordingly, as required by ML.A.302(c)(9). (d) When the competent authority is notified of deficiencies linked with the content of the declared maintenance programme for a particular aircraft (in case no agreement is reached between the owner and the AR staff about the changes required in the maintenance programme), the competent authority should contact the owner, request a copy of the maintenance programme, decide which amendment to the AMP is necessary and raise the associated finding (ref. ML.A.302(c)(9)). If necessary, the competent authority may also react in accordance with ML.B.304. Based on the information received, the reported deficiencies and the identified risks, the competent authority may in addition adapt the ACAM programme accordingly (ref. ML.B.303). (e) Although there is no requirement for the owner to send a copy of the maintenance programme to the competent authority, this does not prevent the competent authority from requesting at any time the owner to send information about, or a copy of the AMP, even if deficiencies have not been reported (see AMC1 ML.B.201). (f) Since the maintenance programme has to identify the alternatives tasks to the instructions issued by the DAH or the declarant of a declaration of design compliance, the ARs and ACAM inspections can place emphasis on the inspection of the areas affected by those deviations in order to make sure that the maintenance programme is effective. (g) Since the competent authority is not responsible for the content of a declared maintenance programme, the competent authority does not authorise the accomplishment of the scheduled maintenance to deviate from the AMP content (other than the tolerances provided for in ML.A.302(d)(1)). In such cases, the owner may declare an amended AMP. GM · GM1 ML.A.302 — Regulation (EU) No 1321/2014 · ED Decision 2023/013/R · Continuing Airworthiness Easy Access Rules · EAR revision 2 Sep 2025 GM Guidance material ## GM2 ML.A.302 Aircraft maintenance programme The following table provides a summary of the provisions contained in point ML.A.302 in relation to the content of the [maintenance](https://avioverse.aero/glossary/easa/maintenance) programme, its approval, and its link with the airworthiness review (AR): | | OPTION 1 | OPTION 2 | | ------------------------------------------------- | ------------------------------------------------------------------------------------------------------------------------------------------------ | ------------------------------------------------------------------------------------ | | Responsibility for developing the AMP | Contracted CAMO or CAO | Owner (if allowed under ML.A.201(f)) | | Approval/declaration of the maintenance programme | Approved by the CAMO or CAO, or none required in the case of compliance with ML.A.302(e) | Declaration by the owner or none required in the case of compliance with ML.A.302(e) | | Basis for the maintenance programme | MIP (only applicable to aeroplanes, sailplanes and balloons), or ICA issued by the DAH or declarant of a declaration of design compliance | | | Deviations from the ICA | Deviations from the ICA are justified. The CAMO/CAO keeps a record of the justifications and provides a copy of them to the owner. | Deviations do not need to be justified. | | AMP annual review | In conjunction with the AR, by the AR staff or, if not performed in conjunction with the AR (e.g. in case of ARC extension), by the CAMO or CAO. | | GM · GM2 ML.A.302 — Regulation (EU) No 1321/2014 · Continuing Airworthiness Easy Access Rules · EAR revision 2 Sep 2025 AMC Acceptable means of compliance ## AMC1 ML.A.302(c) Aircraft maintenance programme When evaluating an alternative to a [maintenance](https://avioverse.aero/glossary/easa/maintenance) task issued or recommended by the DAH or the declarant of a declaration of design compliance, such as the extension of TBO intervals, or when considering not to include a maintenance task issued or recommended by the DAH or the declarant of a declaration of design compliance, a risk-based approach should be taken, considering aspects such as the operation of [aircraft](https://avioverse.aero/glossary/easa/aircraft), type of aircraft, hours and years in service, maintenance of the aircraft, compensating measures, redundancy of components, etc. The following table provides more details of aspects that should be considered: | | Examples | | -------------------------------------------------------------------------------------- | --------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------- | | OPS approval | HIGHER RISK: commercial operation, commercial flight training MEDIUM RISK: flight training by an association, non-[commercial specialised operations](https://avioverse.aero/glossary/easa/commercial-specialised-operations) (SPO) LOWER RISK: private | | Flight rules | HIGHER RISK: instrument flight rules (IFR) MEDIUM RISK: visual flight rules (VFR) at night LOWER RISK: VFR by day | | Aircraft weight | HIGHER RISK: Other than ELA1 MEDIUM RISK: [ELA1 aircraft](https://avioverse.aero/glossary/easa/ela1-aircraft) other than light sport aeroplanes (LSA), very light aircraft (VLA), sailplanes and powered sailplanes LOWER RISK: LSA, VLA, sailplanes and powered sailplanes | | Who manages the airworthiness of the aircraft? | HIGHER RISK: owner LOWER RISK: CAMO/CAO | | Who maintains the aircraft? | HIGHER RISK: pilot-owner MEDIUM RISK: independent [certifying staff](https://avioverse.aero/glossary/easa/certifying-staff) LOWER RISK: maintenance [organisation](https://avioverse.aero/glossary/easa/organisation) | | Time in service (flight hours, years) | HIGHER RISK: very high number of hours or years MEDIUM RISK: medium number of hours or years LOWER RISK: low number of hours or years | | Aircraft utilisation | HIGHER RISK: less than 50 h per year MEDIUM RISK: around 200 h per year LOWER RISK: more than 400 h per year | | ACAM findings | HIGHER RISK: numerous findings in ACAM or ramp inspections MEDIUM RISK: few findings in ACAM inspections LOWER RISK: rare findings in ACAM inspections | | System redundancy (for components such as engine/propeller) | HIGHER RISK: single-engined aircraft LOWER RISK: multi-engined aircraft | | Supplementary maintenance measures | HIGHER RISK: no supplementary measures LOWER RISK: supplementary measures (such as oil analysis, engine data monitoring, boroscope inspections, corrosion inspections, etc.) | | Risk factor of the [component](https://avioverse.aero/glossary/easa/component) failure | HIGHER RISK: engine failure on a [helicopter](https://avioverse.aero/glossary/easa/helicopter) MEDIUM RISK: engine failure on an [aeroplane](https://avioverse.aero/glossary/easa/aeroplane) LOWER RISK: sailplane, or powered sailplane | The above information may be useful for CAMOs and CAOs when developing and approving maintenance programmes, and for the AR staff performing ARs and reviewing the effectiveness of the declared maintenance programme. It may also be useful for the owner in order to take an informed decision before introducing deviations from the recommendations issued by the DAH or the declarant of a declaration of design compliance. Nevertheless, as allowed by ML.A.302(c)(7) and explained in GM ML.A.302, when the owner issues a declaration for the maintenance programme, it does not need to justify such deviations. AMC · AMC1 ML.A.302(c) — Regulation (EU) No 1321/2014 · ED Decision 2023/013/R · Continuing Airworthiness Easy Access Rules · EAR revision 2 Sep 2025 AMC Acceptable means of compliance ## AMC1 ML.A.302(c)(9) Aircraft maintenance programme ANNUAL REVIEW OF THE AMP (a) During the annual review of the [maintenance](https://avioverse.aero/glossary/easa/maintenance) programme, as required by point ML.A.302(c)(9), the following should be taken into consideration: (1) the results of the maintenance performed during that year, which may reveal that the current maintenance programme is not adequate; (2) the results of the AR performed on the [aircraft](https://avioverse.aero/glossary/easa/aircraft), which may reveal that the current maintenance programme is not adequate; (3) revisions introduced on the documents affecting the programme basis, such as the ML.A.302(d) MIP or the data issued by the DAH or the declarant of a declaration of design compliance; (4) changes in the aircraft configuration, and type and specificity of operation; (5) changes in the list of pilot-owners; and (6) applicable mandatory requirements for compliance with Part 21 or Part 21 Light, such as airworthiness directives (ADs), airworthiness limitations, certification maintenance requirements and specific maintenance requirements contained in the type certificate data sheet (TCDS) or airworthiness data sheet (for aircraft subject to a declaration of design compliance). (b) When reviewing the effectiveness of the AMP, the AR staff (or the CAMO/CAO staff if the review of the AMP is not performed in conjunction with an AR) may need to review the maintenance carried out during the last 12 months, including unscheduled maintenance. To this end, he or she should receive the records of all the maintenance performed during that year from the owner/CAMO/CAO. (c) When reviewing the results of the maintenance performed during that year and the results of the AR, attention should be paid as to whether the defects found could have been prevented by introducing in the maintenance programme certain recommendations issued by the DAH or the declarant of a declaration of design compliance, which were initially disregarded by the owner, CAMO or CAO. AMC · AMC1 ML.A.302(c)(9) — Regulation (EU) No 1321/2014 · ED Decision 2023/013/R · Continuing Airworthiness Easy Access Rules · EAR revision 2 Sep 2025 GM Guidance material ## GM1 ML.A.302(c)(2)(b) Aircraft maintenance programme ‘DAH’ refers to the holder of a type certificate (TC), restricted type certificate, supplemental type certificate (STC), European Technical Standard Order (ETSO) authorisation, repair or change to the type design. ‘Declarant’ refers to the natural of legal person who has submitted a declaration of design compliance in accordance with Part 21 Light. The ‘instructions for [continuing airworthiness](https://avioverse.aero/glossary/easa/continuing-airworthiness) (‘ICA’) issued by the design approval holder (‘DAH’)’ or the declarant do not include the data issued by another original equipment manufacturer (OEM), except when the ICA issued by the DAH or the declarant make clear reference to such OEM data. Tasks or intervals (e.g. escalations) alternative to those of the ICA issued by the DAH or the declarant and selected by the CAMO or CAO for the AMP do not need to be approved by the competent authority. Justification of these deviations are to be kept by the CAMO or CAO. GM · GM1 ML.A.302(c)(2)(b) — Regulation (EU) No 1321/2014 · ED Decision 2023/013/R · Continuing Airworthiness Easy Access Rules · EAR revision 2 Sep 2025 GM Guidance material ## GM1 ML.A.302(c)(3) Aircraft maintenance programme ALTERNATIVE [MAINTENANCE](https://avioverse.aero/glossary/easa/maintenance) ACTIONS ‘Maintenance actions alternative to those referred to in point (c)(2)(b)’ refer to when the ICA issued by the DAH or the declarant of a declaration of design compliance are used as the basis for the AMP development and the CAMO, CAO or owner (as applicable), when developing the AMP, decides to deviate from certain of these instructions issued by the DAH or the declarant of a declaration of design compliance, introducing, for example, a less frequent interval than or a different task type (inspection instead of check) from the one established by the ICA. These alternative maintenance actions shall not be less restrictive than those set out in the applicable MIP. This means that the extent of the maintenance to be covered by the deviating task cannot be less than the extent of the corresponding task in the MIP in terms of frequency and task type. Examples of alternative maintenance actions: | ICA task | AMP proposed alternative | MIP task | Alternative acceptable Yes/No | | -------------------------------- | ------------------------------------------------------------------------------------------------- | ------------------------------------------ | ----------------------------- | | Inspection XX 6 months interval | Inspection XX 12 months interval | Inspection XX 12 months interval | Yes | | Inspection XX 12 months interval | Inspection XX 24 months interval | Inspection XX 12 months interval | No | | Inspection XX 24 months interval | Inspection XX 36 months interval | Inspection XX 12 months interval | No (24 months to be kept) | | Functional test system XX | Operational test system XX (same interval) or general visual inspection system XX (same interval) | Functional test system XX (same interval) | No\* | | Operational test system XX | Functional test system XX (same interval) | Operational test system XX (same interval) | Yes\* | | Inspection XX 24 months interval | Inspection XX 36 months | None relevant | Yes | | Functional test | General visual inspection | None relevant | Yes | \*A functional test is considered more restrictive than an operational test. Remark: the above does not apply to one-time interval extensions, for which ML.A.302(d)(1) provides 1-month or 10-h tolerance (i.e. permitted variation) for aeroplanes, touring motor gliders (TMGs) and balloons and 1-month tolerance for sailplanes and powered sailplanes other than TMGs. GM · GM1 ML.A.302(c)(3) — Regulation (EU) No 1321/2014 · ED Decision 2023/013/R · Continuing Airworthiness Easy Access Rules · EAR revision 2 Sep 2025 GM Guidance material ## GM1 ML.A.302(c)(4) Aircraft maintenance programme MANDATORY [CONTINUING AIRWORTHINESS](https://avioverse.aero/glossary/easa/continuing-airworthiness) INFORMATION OTHER THAN ADS ‘Mandatory continuing airworthiness information’ other than ADs may be different from one [aircraft](https://avioverse.aero/glossary/easa/aircraft) to an other, depending on the type certification basis used. The aircraft may have been certified before the term ‘ALS (Airworthiness Limitations Section)’ was introduced in the certification specification (or airworthiness code). However, the intent is that the AMP (whether based on MIP or not) includes all mandatory scheduled [maintenance](https://avioverse.aero/glossary/easa/maintenance) requirements identified during the initial airworthiness activity, by the TC holder, STC holder, declarant of a declaration of design compliance and, if applicable, engine TC holder. These requirements may be identified under a variety of designations such as: Airworthiness limitations or Airworthiness limitation items (ALI) Certification maintenance requirements (CMR) Safe life items or safe life limits or safe life limitations Life-limited parts (LLP) Time limits Retirements life Mandatory Inspections or Mandatory Airworthiness Inspections Fuel airworthiness limitations or Fuel tank safety limitations In case of doubt, it is advised to check the TCDS or airworthiness data sheet or contact the DAH or the declarant of a declaration of design compliance. The intervals of the mandatory continuing airworthiness information cannot be extended by a CAMO/CAO. The escalation of such tasks is to be approved by the Agency. GM · GM1 ML.A.302(c)(4) — Regulation (EU) No 1321/2014 · ED Decision 2023/013/R · Continuing Airworthiness Easy Access Rules · EAR revision 2 Sep 2025 AMC Acceptable means of compliance ## AMC1 ML.A.302(d) Aircraft maintenance programme This AMC contains an acceptable MIP for: aeroplanes of 2 730 kg MTOM and below; ELA2 sailplanes and ELA2 powered sailplanes; and ELA2 balloons. These MIPs already comply with the requirements of ML.A.302(d) and may be used in order to define the basic information for the [maintenance](https://avioverse.aero/glossary/easa/maintenance) programme as required by ML.A.302(c)(2)(a). However, the maintenance programme must be customised as required by ML.A.302(c)(5), which may be achieved by using the standard template contained in AMC ML.A.302. It should be noted that using the 1-month tolerance permitted by ML.A.302(d)(1) for the annual inspection may result in an expired ARC. MIP for aeroplanes of 2 730 kg MTOM and below Note: In respect of the power plant, the MIP list of tasks below covers only ‘PISTON ENGINES’ or ‘TURBOPROP ENGINES’. For other types of power plants, consider the tasks as established in the [aircraft](https://avioverse.aero/glossary/easa/aircraft) ICAs related to the power plant. To be performed at every annual/100-h interval, whichever comes first. A tolerance of 1 month or 10 h may be applied. The next interval shall be calculated from the time the inspection takes place. Note 1: Use the manufacturer’s maintenance manual to accomplish each task/inspection. Note 2: Proper operation of backup or secondary systems and components should be performed wherever a check for improper installation/operation is carried out. | Aeroplanes of 2 730 kg MTOM and below | | | ----------------------------------------------------------------------- | ------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------- | | System/[component](https://avioverse.aero/glossary/easa/component)/area | Task and inspection detail | | GENERAL | | | General | Remove or open all necessary inspection plates, access doors, fairings, and cowlings. Clean the aircraft and aircraft engine as required. | | Lubrication/servicing | Lubricate and replenish fluids in accordance with the manufacturer’s requirements. | | Markings | Check that side and underwing registration markings are correct. If applicable, check that an exemption for alternate display is approved. Identification plate for national aviation authority (NAA)-registered aircraft is present, as well as other identification markings on fuselage in accordance with local (national) rules. | | Weighing | Review weighing record to establish accuracy against installed equipment. Weigh the aircraft as required by Part-NCO or Part-SPO, as applicable. | | Service life limits | Check the records that the service life limits and airworthiness limits are within the life time limits of the maintenance programme. | | Software | Check for updated software/firmware status and databases for engine and equipment. | | AIRFRAME | | | Fabric and skin | Inspect for deterioration, distortion, other evidence of failure, and defective or insecure attachment of fittings. NOTE: When checking composite structures, check for signs of impact or pressure damage that may indicate underlying damage. | | Fuselage structure | Check frames, formers, tubular structure, braces, and attachments. Inspect for signs of corrosion and cracks. | | Systems and components | Inspect for improper installation, apparent defects, and unsatisfactory operation. | | Pitot-static system | Inspect for security, damage, cleanliness, and condition. Drain any water from condensation drains. | | General | Inspect for lack of cleanliness and loose equipment that may foul the controls. | | Tow hooks | Inspect for condition of moving parts and wear. Check service life. Carry out operational test. | | CABIN AND COCKPIT | | | Seats, safety belts and harnesses | Inspect for poor condition and apparent defects. Check for service life. | | Windows, canopies and windshields | Inspect for deterioration and damage, and for function of emergency jettison. | | Instrument panel assemblies | Inspect for poor condition, mounting, marking, and (where practicable) improper operation. Check markings of instruments in accordance with the flight manual. | | Flight and engine controls | Inspect for improper installation and improper operation. | | Speed/weight/manoeuvre placard | Check that the placard is correct and legible, and accurately reflects the status of the aircraft. | | All systems | Inspect for improper installation, poor general condition, apparent and obvious defects, and insecurity of attachment. | | LANDING GEAR | | | Shock-absorbing devices | Inspect for improper oleo fluid level. Inspect for wear and deformation of rubber pads, bungees, and springs. | | All units | Inspect for poor condition and insecurity of attachment, including the related structure. | | Retracting and locking mechanism | Inspect mechanism. Operational check. | | Linkages, trusses and members | Inspect for undue or excessive wear fatigue and distortion. | | Steering | Inspect the nose/tail wheel steering for proper function and wear. | | Hydraulic lines | Inspect for leakage. Check condition and replace if necessary. | | Electrical system | Inspect for chafing. Operational check of switches. | | Wheels | Inspect for cracks, defects, and condition of bearings. | | Tires | Inspect for wear and cuts. | | Brakes | Inspect for improper adjustment and wear. Carry out operational test. | | Floats and skis | Inspect for insecure attachment and apparent defects. | | WING AND CENTRE SECTION | | | All components | Inspect all components of the wing and centre section assembly for poor general condition, fabric or skin deterioration, distortion, evidence of failure and insecurity of attachment. | | Connections | Inspect main connections (e.g. between wings, fuselage, wing tips) for proper fit, play within tolerances, wear or corrosion on bolts and bushings. | | FLIGHT CONTROLS | | | Control circuit/stops | Inspect control rods and cables. Check that the control primary stops are secure and make contact. | | Control surfaces | Inspect aileron, flap, elevator, air brake and rudder assemblies, hinges, control connections, springs/bungees, tapes and seals. Check full range of motion and free play. | | Trim systems | Inspect trim surfaces, controls, and connections. Check full range of motion. | | EMPENNAGE | | | All components and systems | Inspect all components and systems that make up the complete empennage assembly for poor general condition, fabric or skin deterioration, distortion, evidence of failure, insecure attachment, improper component installation, and improper component operation. | | AVIONICS AND ELECTRICS | | | Batteries | Inspect for improper installation, improper charge, spillage and corrosion. | | Radio and electronic equipment | Inspect for improper installation and insecure mounting. Carry out ground function test. | | Wiring and conduits | Inspect for improper routing, insecure mounting, and obvious defects. | | Bonding and shielding | Inspect for improper installation, poor condition, chafing and wear of insulation. | | Antennas | Inspect for poor condition, insecure mounting, and improper operation. | | Lights | Operational check of the interior, exterior and instrument lightning | | PISTON ENGINE | | | Engine section | Inspect for visual evidence of oil, fuel or hydraulic leaks and sources of such leaks. | | Studs and nuts | Inspect for looseness, signs of rotation and obvious defects. | | Internal engine | Inspect for proper cylinder compression (record measures for each cylinder) and for metal particles or foreign matter in oil filter, screens and sump drain plugs. | | Engine mounts | Inspect for cracks, looseness of mounting, and looseness of the engine to the engine-mount attachment. | | Flexible vibration dampeners | Inspect for poor condition and deterioration. | | Engine controls | Inspect for defects, improper travel, and improper safe tying. | | Lines, hoses and clamps | Inspect for leaks, improper condition, and looseness. | | Exhaust stacks | Inspect for cracks, defects, and improper attachment. | | Turbocharger and intercooler | Inspect for leaks, improper condition, and looseness of connections and fittings. Check MP controller or density controller for leakage and free movement of controls. Check waste gate or overpressure relief valve for free movements. | | Heating | Inspect cabin heating heat exchanger for improper condition and function. For exhaust heat exchanger, check CO (Carbon Monoxide) concentration. | | Liquid cooling systems | Inspect for leaks and proper fluid level. | | Electronic engine control | Inspect for signs of chafing, and proper electronics and sensor installation. | | Accessories | Inspect for apparent defects in security of mounting. | | All systems | Inspect for improper installation, poor general condition, defects and insecure attachment. | | Cowling | Inspect for cracks and defects. Check cowling flaps. | | Cooling baffles and seals | Inspect for defects, improper attachment, and wear. | | TURBOPROP ENGINE | | | Incoming power check | Perform in accordance with the graphs found in the engine maintenance manual (EMM). | | Inertial separator | Functional check | | Engine cowling | Remove, inspect for damage. | | General condition | Inspect for oil, fuel, bleed-air or other leaks. | | 1st stage compressor blades | Remove screen, check for foreign object debris (FOD) or other damage. | | P3 filter | Replace | | Oil filter | Inspection and cleaning | | Fuel low pressure filter | Replace | | Fuel high pressure filter | Inspection and cleaning | | Oil scavenge filter | Inspection and cleaning | | Chip detector | Inspection and cleaning | | Exhaust duct | Inspection | | Starter/generator brushes | Inspection for proper length | | Ignitor/glow plugs | Functional check | | Overspeed governor | Inspect for oil leaks. | | Governor and beta-valve | Inspect for oil leaks or binding of controls. | | Propeller | Inspect blades for damage and hub leaks. | | (if installed) fire detector loop or sense module | Functional check | | Engine cowling | Install | | Power check | Perform in accordance with the graphs found in the EMM, record values. | | Oil level | Check within 10 minutes after shutdown. | | FUEL | | | Fuel tanks | Inspect for leaks and improper installation and connection. Verify proper sealing and function of tank drains. | | CLUTCHES AND GEARBOXES | | | Filters, screens, and chip detectors | Inspect for metal particles and foreign matter. | | Exterior | Inspect for oil leaks. | | Output shaft | Inspect for excessive bearings’ play and condition. | | PROPELLER | | | Propeller assembly | Inspect for cracks, nicks, binds, and oil leakage. | | Propeller bolts | Inspect for proper installation, looseness, signs of rotation, and lack of safe tying. | | Propeller control mechanism | Inspect for improper operation, insecure mounting, and restricted travel. | | Anti-icing devices | Inspect for improper operation and obvious defects. | | MISCELLANEOUS | | | Ballistic rescue system | Inspect for proper installation, unbroken activation mechanism, proper securing while on ground, validity of inspection periods of pyrotechnic devices, and parachute-packing intervals. | | Other miscellaneous items | Inspect installed miscellaneous items that are not otherwise covered by this listing for improper installation and improper operation. | | OPERATIONAL AND FUNCTIONAL CHECKS | | | Power and revolutions per minute (rpm) | Check that power output, static and idle rpm are within published limits. | | Magnetos | Check for normal function. | | Fuel and oil pressure | Check that they are within normal values. Check fuel pumps for proper operation. | | Engine temperatures | Check that they are within normal values. | | Engine | For engines equipped with automated engine control (e.g. FADEC), perform the published run-up procedure and check for discrepancies. | | Engine | For dry-sump engines, engines with turbochargers and liquid-cooled engines, check for signs of disturbed fluid circulation. | | Pitot-static system | Perform functional check. | | Transponder | Perform operational check. | | Ice protection | Perform operational check of ice protection system. | | Fuel quantity indication | Check the fuel quantity indication for proper indication. | | Caution and warning | Operational check of cautions and warnings lights. | MIP for ELA2 sailplanes and ELA2 powered sailplanes To be performed: every 100-h/annual interval (for TMGs), whichever comes first; or every annual interval (for the rest). A tolerance of 1 month or 10 h, as applicable, may be applied. The next interval shall be calculated from the time the inspection takes place. Note 1: Use the manufacturer’s maintenance manual to accomplish each task/inspection. Note 2: In the case of TMGs, it is acceptable to control the hours of use of the aircraft, engine and propeller as separate entities. Any maintenance check to be carried out between two consecutive 100-h/annual inspections may be performed separately on the aircraft, engine and propeller, depending on when each element reaches the corresponding hours. However, at the time of the 100-h/annual, all the elements must be covered. Note 3: Proper operation of backup or secondary systems and components should be carried out wherever a check for improper installation/operation is performed. | ELA2 sailplanes and ELA2 powered sailplanes | | | ----------------------------------------------------------------------------------------------------------------------------------------------------------------- | ----------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------- | | System/component/area | Task and inspection detail | | GENERAL | | | General — all tasks | The aircraft must be clean prior to inspection. Inspect for security, damage, wear, integrity, whether drain/vent holes are clear, for signs of overheating, leaks, chafing, cleanliness and condition, as appropriate to the particular task. Whilst checking composite structures, check for signs of impact or pressure damage that may indicate underlying damage. | | Lubrication/servicing | Lubricate and replenish fluids in accordance with the manufacturer’s requirements. | | Markings | Check that side and underwing registration markings are correct. If applicable, check that an exemption for alternate display is approved, if identification plate for NAA-registered aircraft is present, and if other identification markings on fuselage are in accordance with local (national) rules. | | Weighing | Review weighing record to establish accuracy against installed equipment. Weigh the aircraft as required by the relevant Regulation for air operations. | | AIRFRAME | | | Fuselage paint/gel coat | Inspect external surface and fairings, gel coat, fabric covering or metal skin, and paintwork. | | Fuselage structure | Check frames, formers, tubular structure, skin, and attachments. Inspect for signs of corrosion on tubular framework. | | Nose fairing | Inspect for evidence of impact with ground or objects. | | Release hook(s) | Inspect nose and centre of gravity, release hooks and controls. Check operational life. Carry out operational test. If more than one release hook or control is fitted, check operation of all release hooks from all positions. | | Pitot/ventilator | Check alignment of probe, check operation of ventilator. | | Pitot-static system | Inspect pitot probes, static ports, and all tubing (as accessible) for security, damage, cleanliness, and condition. Drain any water from condensate drains. | | Bonding/vents drains | Check all bonding leads and straps. Check that all vents and drains are clear from debris. | | CABIN AND COCKPIT | | | Cleanliness/loose articles | Check under cockpit floor/seat pan and in rear fuselage for debris and foreign items. | | Canopy, locks and jettison | Inspect canopy, canopy frame and transparencies for cracks, unacceptable distortion, and discolouration. Check operation of all locks and catches. Carry out an operational test of the canopy jettison system from all positions. | | Seat/cockpit floor | Inspect seat(s). Check that all loose cushions are correctly installed and, as appropriate, that energy-absorbing foam cushions are fitted correctly. Ensure that all seat adjusters fit and lock correctly. | | Harness(es) | Inspect all harnesses for condition, and wear of all fastenings, webbing, and fittings. Check operation of release and adjustments. | | Rudder pedal assemblies | Inspect rudder pedal assemblies and adjusters. Inspect cables for wear and damage. | | Instrument panel assemblies | Inspect instrument panel and all instruments/equipment. Check if instrument readings are consistent with ambient conditions. Check marking of all switches, circuit breakers, and fuses. Check operation of all installed equipment, as possible in accordance with the manufacturer’s instructions. Check markings of instruments in accordance with the aircraft flight manual (AFM). | | Oxygen system | Inspect oxygen system. Check bottle hydrostatic-test date expiry in accordance with the manufacturer’s recommendations. Ensure that oxygen installation is recorded on weight and centre-of-gravity schedule. CAUTION: OBSERVE ALL SAFETY PRECAUTIONS. | | Colour-coding of controls | Ensure that controls are colour-coded in accordance with the AFM and in good condition. | | Placards | Check that the placards are correct and legible, and accurately reflect the status of the aircraft in accordance with the AFM. | | LANDING GEAR | | | Front skid/nose wheel and mounts | Inspect for evidence of hard/heavy landings. Check skid wear. Inspect wheel, tyre, and wheel box. Check tyre pressure. | | Main wheel and brake assembly | Check for integrity of hydraulic seals and leaks in pipework. Check life of hydraulic hoses and components, if specified by the manufacturer. Remove brake drums, check brake lining wear. Check disk/drum wear. Refit drum. Check brake adjustment. CAUTION: BRAKE DUST MAY CONTAIN ASBESTOS. Check operation of brake. Check level of brake fluid and replenish, if necessary. Check tyre pressure. CAUTION: CHECK TYPE OF BRAKE FLUID USED AND OBSERVE SAFETY PRECAUTIONS. | | Undercarriage suspension | Check springs, bungees, shock absorbers, and attachments. Check for signs of damage. Service strut, if applicable. | | Undercarriage retract system and doors | Check retraction mechanism and controls, warning system if fitted, gas struts, doors and linkages/springs, over-centre/locking device. Perform retraction test. | | Tail skid/wheel | Inspect for evidence of hard/heavy landings. Check skid wear. Inspect wheel, tyre, and wheel box. Check bond of bonded skids. Check tyre pressure. | | Wheel brake control circuit | Inspect wheel brake control rods/cables. If combined with air brake, ensure correct rigging relationship. Check parking-brake operation, if fitted. | | WING AND CENTRE SECTION | | | Centre section | Inspect wing centre section including fairings for security, damage, and condition. | | Wing attachments | Inspect the structural attachments of the wing. Check for damage, wear, and security. Check for rigging damage. Check condition of wing attachment pins and wing main bolts. | | Winglet/wing extensions | Inspect the structural attachments of winglet and wing attachments. Check for damage, wear, and security. | | Aileron control circuit/stops | Inspect aileron control rods/cables. Check that control stops are secure and make contact. Inspect connecting control devices for security, damage, free play and secure mounting. | | Air brake control circuit | Inspect air brake control rods/cables. Check friction/locking device (if fitted). Inspect connecting control devices for security, damage, free play and secure mounting. Inspect air brake locking for proper adjustment and positive locking. | | Wing struts/wires | Inspect struts for damage and internal corrosion. Re-inhibit struts internally every 3 years or in accordance with the manufacturer’s instructions. | | Wings including underside registration markings | Check mainplane structure externally and internally, as far as possible. Check gel coat, fabric covering, or metal skin. | | Ailerons and controls | Inspect aileron and flaperon assemblies, hinges, control connections, springs/bungees, tapes, and seals. Ensure that seals do not impair the full range of movement. | | Air brakes/spoilers | Inspect air brake/spoiler panel(s) operating rods, closure springs, and friction devices, as fitted. | | Flaps | Check flap system and control. Inspect connecting control devices. | | Control deflections and free play, and record them on worksheets | Check and record range of movements and cable tensions, if specified, and check free play. | | EMPENNAGE | | | Tailplane and elevator | With tailplane de-rigged, check tailplane and attachments, self-connecting and manual control connections. Check gel coat, fabric covering, or metal skin. | | Rudder | Check rudder assembly, hinges, attachments, balance weights. | | Rudder control circuit/stops | Inspect rudder control rods/cables. Check that control stops are secure and make contact. Pay particular attention to wear and security of liners and cables in ‘S’ tubes. | | Elevator control circuit/stops | Inspect elevator control rods/cables. Check that control stops are secure and make contact. Inspect self-connecting control devices. | | Trimmer control circuit | Inspect trimmer control rods/cables. Check friction/locking device. Inspect trim indication for proper adjustment and function. | | Control deflections and free play, and record them on worksheets | Check and record range of movements and cable tensions, if specified, and check free play. | | AVIONICS AND ELECTRICS | | | Electrical installation/fuses | Check all electrical wiring for condition. Check for signs of overheating and poor connections. Check fuses/trips for condition and correct rating. | | Battery security and corrosion | Check battery mounting for security and operation of clamp. Check for evidence of electrolyte spillage and corrosion. Check that battery has correct main fuse fitted. It is recommended to carry out battery capacity test on gliders equipped with radio, used for cross-country, controlled airspace, or competition flying. | | Radio installations and placards | Check radio installation, microphones, speakers and intercom, if fitted. Check that a call sign placard is installed. Carry out ground function test. Record radio type fitted. | | Air speed indicator | Carry out a pitot static leak check and functional check of the airspeed indicator. In case of indications of malfunctions, carry out an airspeed indicator calibration check. | | Altimeter datum | Check barometric subscale by altimeter QNH reading. | | Pitot-static system | Perform pitot static leak check, inspect hoses for condition, operational check. | | Transponder | Perform operational check. | | MISCELLANEOUS | | | Removable ballast | Check removable ballast mountings and securing devices (including fin ballast, if applicable) for condition. Check that ballast weights are painted with conspicuous colour. Check that provision for the ballast is made on the loading placard. | | Drag chute and controls | Inspect chute, packing and release mechanism. Check packing intervals. | | Water ballast system | Check water ballast system, wing and tail tanks, as fitted. Check filling points, level indicators, vents, dump and frost drains for operation and leakage. If loose bladders are used, check for leakage and expiry date, as applicable. | | POWER PLANT (when applicable) NOTE: In the case of sailplanes with electrical or jet engines, follow the maintenance instructions and recommendations of the DAH. | | | Engine pylons and mountings | Inspect engine and pylon installation. Check engine compartment and fire sealing. | | Gas strut | Check gas strut. | | Pylon/engine stops | Check limit stops on retractable pylons. Check restraint cables. | | Electric actuator | Inspect electric actuator, motor, spindle drive, and mountings. | | Electrical wiring | Inspect all electrical wiring. Pay special attention to wiring that is subject to bending during extension and retraction of engine/pylon. | | Limit switches | Check operation of all limit switches and strike plates. Make sure that they are not damaged by impact. | | Fuel tank(s) | Check fuel tank mountings and tank integrity. Check fuel quantity indication system, if fitted. | | Fuel pipes and vents | Check all fuel pipes, especially those subject to bending during extension and retraction of engine/pylon. Check that vents are clear. Make sure that overboard drains do not drain into engine compartment. Check self-sealing. | | Fuel cock or shut-off valve | Check operation of fuel cock or shut-off valve and indications. | | Fuel pumps and filters | Clean or replace filters, as recommended by manufacturer. Check operation of fuel pumps for engine supply or tank replenishment. Check fuel pump controls and indications. | | Decompression valve | Inspect decompression valve and operating control. | | Ignition | Inspect ignition system including spark plugs, distributor and cables for condition and damage. Inspect low-tension and high-tension wiring, connectors, spark plug caps. Check magneto-to-engine timing. | | Propeller | Inspect propeller, hub, folding mechanism, brake, pitch change mechanism, stow sensors. Inspect propeller control for function and condition. | | Doors | Check engine compartment doors, operating cables, rods, and cams. | | Safety springs | Check all safety and counterbalance springs. | | Extension and retraction | Check that extension and retraction operation times are within the limits specified by the manufacturer. Check light indications and interlocks for correct operation. | | Exhaust | Inspect exhaust system, silencer, shock mounts, and links. | | Engine installation | Inspect engine and all accessories. Carry out compression test and record results (for piston engines). Compression test results: No 1 (left/front); and No 2 (right/rear). | | Lubrication | Change engine oil and filter. Replenish oil and additive tanks. | | Engine instruments | Inspect all engine instruments and controls. Check control unit, mounts, bonding and connections. Carry out internal self-test, if fitted. | | Engine battery | If separate from airframe battery, inspect battery and mountings. If main fuse is fitted, check rating and condition. | | Engine battery capacity test | Carry out capacity test. Refer to appropriate manual or guidance. | | Placards | Check that all placards are in accordance with the AFM and legible. | | Oil and fuel leaks | With the engine fully serviced, check the fuel and oil system for leaks. | MIP for ELA2 hot-air balloons To be performed at every 100-h/annual interval, whichever comes first. A tolerance of 1 month or 10 h may be applied. The next interval shall be calculated from the time the inspection takes place. Note 1: Use the manufacturer’s maintenance manual to accomplish each task/inspection. Note 2: Proper operation of backup or secondary systems and components should be carried out wherever a check for improper installation/operation is performed. (a) Envelope | System/component/area | Task and inspection detail | | ------------------------------------------------------ | ----------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------- | | Identification (type/serial number/registration plate) | Check for presence. | | Crown ring | Inspect for damage/corrosion. | | Crown line | Inspect for damage, wear, security of attachment. Check correct length. | | Vertical-/horizontal-load tapes | Inspect joints with the crown ring, top of the envelope and wires. Inspect that all load tapes are undamaged along their entire length. Inspect base horizontal tape and edge of the envelope top. Inspect joint between base horizontal-load tape and vertical-load tapes. | | Envelope fabric | Inspect the envelope fabric panels (including parachute and rotation vents, if fitted) for damage, porosity overheating or weakness. Unrepaired damage is within tolerance provided for by the manufacturer. If substantial fabric porosity is suspected, a flight test should be performed, but only after a grab test has demonstrated that the balloon is safe to fly. Perform grab test in accordance with the manufacturer’s instructions. | | Flying cables | Inspect for damage (particularly heat damage). | | Karabiners | Inspect for damage/corrosion. Operational check of karabiner lock. | | Melting link and ‘tempilabel’ | Check and record maximum temperature indication (flag/tempilabel). | | Control lines and attachments | Inspect for damage wear, security of knots. Check proper length. Check lines attachments for damage, wear, security. | | Envelope pulleys/guide rings | Inspect for damage, wear, free running, contamination, security of attachment. | (b) Burner | System/component/area | Task and inspection detail | | ----------------------------------- | ------------------------------------------------------------------------------------------------------------------------------------------ | | Identification (type/serial number) | Check for presence and verify type/serial number installed. | | Burner frame | Inspect welds for cracking. | | | Inspect tubes for distortion/deformation/cuts/gouges. | | | Inspect frame for security of fasteners (heat shields, flexi-corners). | | | Inspect frame lugs for wear and cracking. | | | Inspect general condition (corrosion, heat shields). | | Gimballing | Operational check of stiffness and security of fasteners. | | Leak check | Perform leak check of the burner. | | Fuel hoses including manifolds | Inspect all hoses for wear, damage, leakage and service life limitations. Inspect O-ring seals, lubricate/replace as required. | | Pressure gauges | Check that the pressure gauge reads correctly, and that lens is present. | | Pilot valves/flame | Check shut-off, free movement, correct function, and lubricate if necessary. | | Whisper valves/flame | Check shut-off, free movement, correct function, and lubricate if necessary. | | Main valves/flame | Check shut-off, free movement, correct function, and lubricate if necessary. | | Coils | Check for damage, distortion, security of fasteners. Inspect welds for cracking. Check security of jets. Tighten or replace, as necessary. | (c) Basket | System/component/area | Task and inspection detail | | ----------------------------------- | -------------------------------------------------------------------------------------------------------------------------------------- | | Identification (type/serial number) | Check for presence. | | Basket walls | Check the general condition of the basket walls. Inspect weave for damage, cracks/holes. Check for no sharp objects inside the basket. | | Basket wires | Inspect for damage, check swaging and eye rings (thimbles). | | Karabiners | Inspect for damage/corrosion. Operational check of karabiner lock. | | Basket floor | Inspect for damage and cracks. | | Runners | Inspect for damage, security of attachment. | | Rawhide | Inspect for damage, wear and attachments to the floor. | | Rope handles | Inspect for damage, security of attachment. | | Cylinder straps | Inspect for damage, deterioration, approved type fitted. | | Padded basket edge trim | Inspect for damage and wear. | | Burner support rods | Inspect for damage, wear and cracking. | | Padded burner support rod covers | Inspect for damage and wear. | | Basket equipment | Check presence and functionality. | | Pilot restraint and anchor | Inspect for security and condition. | | Fire extinguisher | Check expiration date and protection cover. | | First aid kit | Check for completeness and expiration date. | (d) Fuel cylinders | System/component/area | Task and inspection detail | | ----------------------------------- | --------------------------------------------------------------------------------------------- | | Identification (type/serial number) | Check for presence. | | Cylinder | Check if periodic inspections for each cylinder are valid (date) (e.g. 10 years’ inspection). | | Cylinder body | Inspect for damage, corrosion. | | Liquid valve | Inspect for damage, corrosion, correct operation. | | | Inspect O-ring seals, lubricate/replace as required. | | Fixed liquid Level gauge | Inspect for damage, corrosion, correct operation. | | Contents Gauge | Inspect for damage, corrosion, freedom of movement. | | Vapour valve | Inspect for damage, corrosion, correct operation (including regulator). | | | Check quick-release coupling for correct operation, sealing. | | Padded cover | Inspect for damage. Check for correct thickness. | | Pressure relief valve | Inspect for contamination, corrosion. Check service life limit. | | Assembly | Inspect, and test for leaks all pressure-holding joints using leak detector. | | | Perform functional test | (e) Additional equipment | System/component/area | Task and inspection detail | | ------------------------------------------ | ---------------------------------------------------------------------------------------------------------------------------------------------------------------------------- | | Instruments | Perform functional check. | | Quick release | Perform functional check and inspect the condition of the latch, bridle and ropes for wear and deterioration. Check that the karabiners are undamaged and operate correctly. | | Communication/navigation equipment (radio) | Perform operational check. | | Transponder | Perform operational check. | AMC · AMC1 ML.A.302(d) — Regulation (EU) No 1321/2014 · ED Decision 2023/013/R · Continuing Airworthiness Easy Access Rules · EAR revision 2 Sep 2025 GM Guidance material ## GM1 ML.A.302(d)(2) Aircraft maintenance programme OPERATIONAL TEST AND FUNCTIONAL TEST An operational test (or operational check) is a task used to determine that an item is operating normally. It does not require quantitative tolerances. A functional test (or functional check) is a quantitative check to determine if one or more functions of an item performs within the limits specified in the appropriate [maintenance](https://avioverse.aero/glossary/easa/maintenance) data. The measured parameter should be recorded. GM · GM1 ML.A.302(d)(2) — Regulation (EU) No 1321/2014 · ED Decision 2020/002/R · Continuing Airworthiness Easy Access Rules · EAR revision 2 Sep 2025 GM Guidance material ## GM1 ML.A.302(d)(2)(d) Aircraft maintenance programme OPERATIONAL TEST OF TRANSPONDER A transponder test that is carried out in accordance with EASA SIB 2011-15 or US Title 14 CFR Part 43 Appendix F is considered to include the MIP task described in ML.A.302(d)(2)(d). GM · GM1 ML.A.302(d)(2)(d) — Regulation (EU) No 1321/2014 · ED Decision 2020/002/R · Continuing Airworthiness Easy Access Rules · EAR revision 2 Sep 2025 [All rules in SECTION A — TECHNICAL REQUIREMENTS](https://avioverse.aero/regulations/easa/continuing-airworthiness/part-ml/section-a-technical-requirements) Consolidated from the EASA Easy Access Rules (revision 2 Sep 2025, extracted 13 Oct 2026) for convenience. Not the official publication — verify against the Official Journal of the European Union and the EASA publications before operational use.