Part V - Standard 571 - Maintenance
- Part I
- Part II
- Part III
- Part IV
- Part V
- Chapter 500
- Standard 501
- Chapter 505
- Standard 507
- Standard 509
- Chapter 511
- Chapter 513
- Chapter 516
- Chapter 522
- Chapter 523 (VLA)
- Chapter 523
- Chapter 525
- Chapter 527
- Chapter 529
- Chapter 531
- Chapter 533
- Chapter 535
- Chapter 537
- Chapter 541
- Chapter 549
- Chapter 551
- Standard 561
- Chapter 563
- Chapter 566
- Standard 571
- Standard 573
- Standard 591
- Standard 593
- Part VI
- Part VII
- Part VIII
- Part IX
Canadian Aviation Regulations (CARs) 2017-3
Content last revised: 2010/12/01
STANDARD 571 - MAINTENANCE
Section 571.02 of the Canadian Aviation Regulations (CARs) is applicable to the performance of maintenance or elementary work. It addresses how work should be done, as opposed to what work should be done. For example, required contents of a maintenance schedule, or approval of design data, are not covered by that section but are addressed in Subpart 605 and Subpart 521 of the CARs respectively.
Persons who perform maintenance or elementary work are required to follow the manufacturer’s recommendations, or equivalent practices. Where the recommendations of the aircraft manufacturer are incompatible with those of the engine, propeller, or appliance manufacturer, the recommendations of the aircraft manufacturer shall be used. Where the manufacturer has not made specific recommendations, standard industry practices are to be used. These practices include, but are not limited to, methods published by Transport Canada, a foreign Civil Aviation Authority, the manufacturer of a similar product, or other practices that may not be published provided they are generally accepted by the Canadian aviation industry. Similar requirements apply to the selection of parts, materials, tools and test apparatus.
Subsection 571.02(3) of the CARs requires that persons who perform specified tasks meet the personnel qualification or training standards applicable to the performance of those tasks.
Compliance with section 571.03 of the CARs is the responsibility of the person performing the work. This regulation is applicable to the making of an entry into a technical record, which is distinct from the maintenance release addressed by section 571.10 of the CARs.
(1) A person who performs maintenance or elementary work on an aeronautical product shall ensure that the following information is recorded in the technical records, established in accordance with Subpart 605 of the CARs, for the aeronautical product:
Appendix A of Standard 625 - Aircraft Equipment and Maintenance lists the tasks and conditions associated to elementary work and section 605.94 of the CARs requires that all tasks designated as elementary work be recorded in the journey log.
(a) product identification (aircraft registration marking, nomenclature, type/model number, name of manufacturer, part number, and serial number), unless the entry is being made in technical record that contains this information;
(b) a brief description of the work performed;
(c) where a standard other than the manufacturer’s recommended practice is being used, reference to the standard used in the performance of the work;
(i) If manufacturer’s instructions are being followed and there is no optional method provided to perform the work, it is not necessary to state the standards that were used to perform the work. In cases where optional methods can be used, the method chosen shall be referenced. In cases where damage is being assessed, the extent of the damage and the associated reference to manufacturer’s limitations shall be referenced.
(ii) If this entry constitutes the maintenance release, ensure that the date on which the work was performed is indicated, and that all other requirements of section 571.10 and section 605.93 of the CARs are complied with.
(d) the date on which the maintenance was performed and the identification of the employee who accomplished the task;
(e) where the maintenance involves a repair that includes making and installing repair parts in accordance with subsection 571.06(4) of the CARs, a statement to that effect;
(f) where disassembly is required during performance of work, a general description of any defect found prior to re-assembly;
(g) where a task is partially completed, a general description of any outstanding work, including the specific location of any parts/systems that have been disturbed, is to be recorded. Where the open work lists, inspection sheets or job cards used to accomplish the work clearly indicate any outstanding work, they are acceptable for meeting this requirement; and
(h) where the part has been accepted pursuant to Appendix H of this standard, a statement indicating that it has been inspected and tested to ensure it conforms to its type design and is in a safe condition, and a maintenance release has been issued to that effect.
For the purpose of this section, the following definition applies:
“an AMO category appropriate to the work performed” - means a category, issued pursuant to subsection 573.02(3) of the CARs, identifying the product being maintained or the process being performed.
(i) The provision of section 571.04 of the CARs applies to persons performing specialized maintenance, not to those persons who certify the performance of that work. Section 571.11 of the CARs addresses the certification of maintenance.
(ii) Processes, specifically welding and nondestructive testing, and aeronautical products for which an AMO Certificate can be issued are listed in section 573.02 of Standard 573.
(iii) In the case of engine overhaul, an AMO with only an engine category can perform the overhaul, provided that any specialized NDT/welding forming part of the overhaul is carried out by an AMO approved for those processes.
(iv) For clarification purposes, an aircraft engine “crankcase” does not include a reduction gear case or an accessory case.
(v) In the case of avionics, standard test equipment refers to test equipment intended primarily for on-aircraft use that provides go/no-go or numerical indications that do not require subjective interpretation on the part of the user. Standard test equipment includes, but is not limited to: multi-meters, direct reading gauges, pitot static test sets, fuel system capacitance test sets, dead weight testers, land compass, and ramp checking equipment.
(a) "Avionics Systems" refers to equipment and systems of the kinds listed in subsection 573.02(4) of standard 573.
(b) "Instruments" includes Engine Monitor Systems, Fuel Flow Systems, and other types of stand-alone instrumentation.
(c) "Standard Test Equipment" refers to test equipment of the type(s) defined in Note (v) above.
(d) Equivalency of LRUs with hardware (Part Number) and/or software status changes is verified by the aircraft or the equipment manufacturer's service instructions.
Aeroplanes or helicopters used by approved flight training units (FTUs) are operated pursuant to Part IV of the CARs, while aircraft used commercially are operated pursuant to Part VII of the CARs. Section 571.05 of the CARs is applicable to the performance of maintenance on such aircraft, or on parts installed on such aircraft.
Maintenance of aeronautical products installed on aeroplanes or helicopters operated pursuant to Part IV of the CARs or aircraft operated pursuant to Part VII of the CARs shall be performed under the control of an AMO approved pursuant to section 573.02 of the CARs. Maintenance of parts, prior to installation on an aircraft operated under Parts IV or VII of the CARs, can be performed outside an AMO, provided the work is subject to a maintenance arrangement made pursuant to section 573.11 of the CARs.
(1) The following definitions apply to this section:
For convenience, the Subpart 101 definition is reproduced here.
“major modification” - means an alteration to the type design of an aeronautical product in respect of which a type certificate has been issued that has other than a negligible effect on the weight and centre-of-gravity limits, structural strength, performance, power plant operation, flight characteristics or other qualities affecting its airworthiness or environmental characteristics; (modification majeure)
For convenience, the Subpart 101 definition is reproduced here.
"major repair" - means a repair to an aeronautical product in respect of which a type certificate has been issued, that causes the aeronautical product to deviate from the type design defined by the type certificate, where the deviation from the type design has other than a negligible effect on the weight and centre-of-gravity limits, structural strength, performance, power plant operation, flight characteristics or other qualities affecting the aeronautical product's airworthiness or environmental characteristics; (réparation majeure)
“acceptable data” - includes:
(a) drawings and methods recommended by the manufacturer of the aircraft, component, or appliance;
(b) Transport Canada advisory documents; and,
(c) advisory documents issued by foreign airworthiness authorities with whom Canada has entered into airworthiness agreements or memoranda of understanding such as current issues of Advisory Circular 43.13-1 and -2 issued by the FAA, Civil Aviation Information Publications (CAIPs) issued by the Civil Aviation Authority (CAA) of the United Kingdom, or Advisory Circular, Joint (ACJs) issued by the Joint Aviation Authority (JAA) or Acceptable Means of Compliance (AMC) issued by the European Aviation Safety Agency (EASA); and,
“approved data” - includes:
(a) type certificates, supplemental type certificates, part design approvals, Canadian technical standard order (CAN-TSO) design approvals or repair design approvals, including equivalent foreign documents which have undergone the type design examination process set-out in Subpart 521 of the CARs or are otherwise accepted in Canada; and
(b) other drawings and methods approved by the Minister or a delegate in conformity with paragraph 4.2(o) and subsection 4.3(1) of the Aeronautics Act. (données approuvées)
“specified data” - is information contained in authoritative documents which, although not approved by the Minister, has been specified by the Minister as appropriate for the purpose of major modifications and major repairs, in conformity with section 571.06 of the CARs. The following are examples of specified data:
(a) drawings or methods described or referenced in Airworthiness Directives;
(b) data issued by the manufacturer or type certificate holder of the aircraft, component or appliance, such as modification orders, service bulletins, or engineering orders, which include a statement of approval by the applicable regulatory authority or a delegated representative of such an authority. Where the data issued by the aircraft manufacturer are incompatible with those of the component or appliance manufacturer, the data of the aircraft manufacturer shall prevail;
(c) manufacturer’s Structural Repair Manuals;
(d) FAA Advisory Circulars AC 43.13-1 and AC 43.13-2, subject to the following conditions:
(i) the aircraft is a small aircraft, and the alteration does not affect dynamic components, rotor blades, structure that is subject to pressurization loads, or the primary structure of a rotorcraft;
(ii) the alteration does not affect an existing limitation (including the information contained on mandatory placards) or change any data contained in the approved sections of the Aircraft Flight Manual, or equivalent;
(iii) the data are appropriate to the product being altered, and are directly applicable to the alteration being made; and,
(iv) the data are not contrary to the aircraft manufacturer’s data.(données specifies)
(2) The criteria to be used to determine which data applies to modifications and repairs is as follows:
(a) All major modifications and major repairs shall be performed in accordance with either “approved” data or “specified” data. A statement of “No technical objection”, or similar wording, by the manufacturer does not constitute “approved”, “acceptable”, or “specified” data and shall not be used without further approval by the Minister.
(b) All other modifications and repairs shall be performed in accordance with “acceptable” data.
Additional guidance for the classification of modifications and repairs can be found in Appendix A of this standard.
(3) Where, pursuant to subsection 571.06(1) of the CARs, a major modification or a major repair is required to be performed in conformity to the applicable technical data and a deviation from specified and/or approved data has occurred, the major modification or major repair shall be subject to re-approval.
(4) Subsection 571.06(1) of the CARs prescribes that the person who performs a major repair or major modification or signs a maintenance release in respect of this modification or repair shall ensure that the technical data used is applicable. Therefore, prior to certification, the person certifying the aforementioned modification or repair shall ensure that any deviation from the original documents is approved.
(5) The person certifying a repair or the incorporation of a modification which includes the making and installing of a part must ensure that the following standards of airworthiness have been complied with:
(a) except as provided in paragraphs (b) and (c), all repair parts must conform with the applicable type design data. Where documents such as Maintenance Manuals, Structural Repair Manuals, or other service information do not provide all of the information required to fully describe the attributes of the part, it is necessary to obtain a copy of the manufacturer’s drawings and all associated specifications;
(b) no repair part made under these provisions shall be marked with the part number specified in the type design;
The provisions of subsection 571.06(4) of the CARs prohibit that a “made” part be marked with the part number specified in the type design, or that the “made” part be offered for sale. Persons making and installing these parts cannot record that the original part was repaired, but shall state that the part was replaced with a made repair part. The individual will not be authorised to state that a new part has been installed, as a “new” part will require a release under Subpart 561 of the CARs manufacturing approval.
(c) subject to subsection (6), where parts are no longer in production by the manufacturer of the part, or an authorised representative, and the type design data for the part is not available, the design data used for the making of the part may be established by inspecting and testing to determine the correct:
(iii) hardness and temper;
(iv) surface finish; and
(v) protective coatings.
(6) Where the repair part constitutes a portion of the primary structure of the aeronautical product, the design data developed in accordance with paragraph (5)(c) above shall be approved pursuant to subsection 571.06(1) of the CARs.
(7) Where, because a modification authorises repetitive re-configurations of an aircraft, separate flight authorities have been issued under Subpart 507 of the CARs, the responsibility for determining which flight authority is in effect with respect to the aircraft rests with the person who carries out the re-configuration of the aircraft. In most cases the person will be an AME. However, where the reconfiguration only involves elementary work, it may be the authorised signatory of an air operator, or a private aircraft owner/operator.
(i) If the person reconfiguring the aircraft is unsure of the effect of the reconfiguration, the approved data for the modification should be consulted for guidance.
(ii) This section is not meant to address aircraft operations such as slinging external loads. Flight restrictions for this type of activity are established via the operational rules of Parts VI and VII of the CARs.
The definitions of ‘commercial part’ and ‘standard part’ set out in Subpart 101 of the CARs apply to this Standard and are reproduced below for convenience only.
“commercial part”, in respect of an aircraft, means a part
(a) that is not specifically designed or produced for use as an aeronautical product,
(b) that is made to a specification or catalogue description and marked under an identification scheme of the maker, and
(c) whose failure does not adversely affect the continued safe flight and take-off and landing of the aircraft; (pièce commerciale)
“standard part”, in respect of an aircraft, means a part manufactured in conformity with a specification that
(a) is established, published and maintained by an organization setting consensus standards or by a government agency, and
(b) includes design, manufacturing, test and acceptance criteria and identification requirements; (pièce standard)
The standards of airworthiness applicable to the installation of new parts are as follows:
(a) The requirements detailed in section 571.13 of this standard are met;
Parts and bulk materials provided under this provision do not require an airworthiness certification, but must be identified or be identifiable, through a part number, shipping document, etc.
(b)Parts that were not originally intended for aeronautical use (e.g. automotive voltage regulators, electronic components, air filters), providing the original manufacturer’s part number is shown in the parts list of the next or subsequent higher assembly. Where the original manufacturer’s part number is not shown in a parts list, other data authorised by type design, such as data approved under a supplemental type certificate are to be consulted.
(i) The person installing a replacement electronic component is responsible for ensuring that the replacement part meets the correct tolerance required by the type design. This information can usually be obtained from either a colour code or markings on the original part, or the illustrated parts catalogue of a higher assembly.
(ii) The part may be:
(a) a standard electrical or electronic part, that requires additional processing before it can be used in the intended application;
(b) produced in conformance with a specification published and maintained by a consensus standards organization, a government agency, a holder of a type certificate or in conformance with the manufacturer's internal specifications and standards.
(iii) The specification may include manufacturing controls, quality and reliability test methods, acceptance criteria, and identification requirements. It does not include electrical parameters and test methods which are obtained from the supplier's data sheet. The part is used within the manufacturer's published operating characteristics and environmental ranges.
(c) Parts produced pursuant to an FAA Parts Manufacturer approval (PMA) are eligible for installation on a Canadian aircraft or on an aeronautical product intended for installation on a Canadian aircraft provided that:
(i) the parts are marked in accordance with the part marking requirements set out by the FAA; and
(ii) the parts are accompanied by an authorized release certificate which certifies the parts conform to the applicable design data approved by the FAA or the Minister and indicates the aeronautical product for which they are eligible.
Used FAA PMA parts are to comply with the requirements for installation of used parts in accordance with section 571.08 of the CARs.
(d) Parts manufactured in conformity with a part design approval issued by the Minister are eligible for installation on a Canadian aircraft or on an aeronautical product intended for installation on a Canadian aircraft.
(1) The standards of airworthiness applicable to the installation of used parts are as follows:
(a) the requirements detailed in section 571.13 of this standard are met;
(b) except as provided in (2), used parts shall be accompanied by a maintenance release;
The maintenance release is to cover any maintenance performed on the part including, at least, inspection of the part to verify that it conforms to its approved configuration and is in a safe condition.
(c) the document bearing the maintenance release shall be examined to see if any additional maintenance tasks are required upon installation, and those tasks shall be completed. The maintenance release for the installation of the part includes the release for these tasks.
(2) No maintenance release document is required where the part is an airworthy part that has been removed from an aircraft and installed on another aircraft with no intervening storage period. The identification of the aircraft from which the part was removed, and any other details necessary to establish the technical history of the part, shall be entered in the recipient aircraft’s technical record.
(3) Where a part has been removed for troubleshooting purposes and is subsequently found not to be the cause of the reported problem, details of the reported problem and the method of eliminating the part as a cause of that problem shall be recorded on the documentation accompanying the part, and certified by means of a maintenance release.
Section 571.13 of the CARs stipulates that if a part is removed from an aeronautical product that is damaged or permanently withdrawn from service, that part is to have a known origin and, as such, be traceable to the manufacturer certificate holder or to an approved aeronautical product, and is to be inspected in accordance with the pertinent instructions for continuing airworthiness (ICA) or approved data.
Pursuant to section 571.09 of the CARs, life-limited parts and assemblies incorporating life-limited parts shall:
(a) have a technical history that includes the total time in service of the life-limited part; and
(b) be installed in accordance with section 571.13 of this standard.
(i) The technical history, referred to in (a), may be limited to providing the traceability of the part to the previous airframe, engine, propeller, appliance, or component from which it was removed, or from which the technical history was obtained.
(ii) For the purpose of this provision, the total time in service of the part is the number of hours, cycles, landings, calendar time or combination thereof, whichever is applicable to the limitation placed on the life of the part, since its initial installation following its manufacture.
(iii) The requirements in respect of the disposal of life-limited parts that have reached their time in service set out in section 571.09 of the CARs.
Pursuant to section 605.85 of the CARs, where an aircraft has undergone maintenance, a maintenance release with respect to maintenance performed shall be completed prior to take off in the affected aircraft. It is a declaration that, with respect to the maintenance performed, the performance rules of section 571.02 of the CARs have been complied with and the applicable standards of airworthiness have been met.
(1) For the purpose of this section the following definitions apply:
“under the person’s supervision” – refers to the person who, by way of the organisation chart or assignment of responsibilities in an approved manual, exercises supervisory authority over a person making a maintenance release.
“similarly worded statement” - means any statement that can be interpreted as conveying the meaning of the maintenance release statement of subsection 571.10(2) of the CARs. This statement may be omitted when the Technical Record, established pursuant to section 605.92 of the CARs, clearly indicates that a signature in a specified signature block constitutes a maintenance release.
(2) Maintenance Release Record Keeping
(a) A maintenance release applies only to the particular maintenance task or tasks to which it relates. Therefore:
(i) it is acceptable to sign a maintenance release in respect of a single task or group of tasks, even if other work is outstanding on the aircraft, provided that the wording of the entry leaves no doubt as to the scope of work being certified; and
(ii) it is the responsibility of the person signing a maintenance release to ensure that the technical record is correct in respect of the status of any outstanding task.
(b) Each maintenance release must include the following information:
(i) product identification (aircraft registration marking, nomenclature, type/model number, name of manufacturer, part number, and serial number), unless the release is being made in an established Technical Record that contains this information;
(ii) a brief description of the work performed, including applicable reference data, when the reference data is not included in the maintenance publications of the manufacturer, and the work order number; and
(iii) where a part that has been accepted pursuant to Appendix H of this standard, a statement included in the certification documents, providing as follows:
“This part has been determined to conform to the approved type design, or to be acceptable under section 571.13 of the CARs”.
(c) The maintenance release shall contain a statement indicating when an airworthy part was removed from an aircraft.
(d)Where a maintenance release is made using an “Authorized Release Certificate” (Form One), Appendix J would normally apply.
Appendix J to this standard contains information to complete Form One, respecting certification of new and used aeronautical products, other than complete aircraft.
(e) Where a maintenance release is made under the authority of an AMO it must include the identification of both the signatory and the AMO. Identification of the signatory may be either by AME licence number, or by other means that clearly identifies the signatory within that organisation.
(f) Where a maintenance release is made by a person holding a restricted certification authority (RCA) issued pursuant to section 571.11 of the CARs, the number of that authority must be entered.
(3) Responsibility for compliance with airworthiness directives (ADs) is assigned to the owner of the aircraft in accordance with section 605.84 of the CARs.
(i) Some inspection check sheets contain a check box with a statement to the effect that “...all applicable ADs have been complied with”. Such a statement transfers this responsibility to the AME signing the maintenance release for the inspection, even though it may be impractical for the AME to undertake the level of research required. Since compliance with ADs are the responsibility of the owner, AMEs should strike out this item on the inspection check sheets that they sign.
(ii) If the owner wishes to have this research undertaken by the AME as a separate maintenance task, it can be raised as a separate item on the work order, work card, or other document detailing the maintenance arrangement.
(4) Notwithstanding the requirement to comply with the Performance Rules in accordance with section 571.02 of the CARs, the following additional standards of airworthiness, developed in conformity with section 571.10 of the CARs, apply with respect to the types of work indicated in the following table of Types of Work:
(i) Section 571.11 of the CARs authorises the holder of an Aircraft Maintenance Engineer (AME) licence with a rating appropriate to the product being maintained to sign any maintenance release.
(ii) To establish what is an appropriate rating, consult Standard 566.
(1) Maintenance performed in a State that is a party to an agreement with Canada, shall be certified by either the holder of a Canadian AME licence, a person who has been authorised under the laws of that State, or a person whose knowledge is determined to be equivalent to the holder of an AME licence pursuant to Subpart 403 of the CARs, as described in subsection (2). Where that work is performed by a foreign maintenance organisation, the maintenance release must be signed by persons qualified pursuant to the local regulations and authorised by the foreign maintenance organisation.
(i) In order to determine if a state is a party to an agreement with Canada, and to establish whether an agreement applies in a particular case, consult the following internet site:
(ii) In addition to providing information concerning aircraft maintenance, some of these agreements also have territorial restrictions. For example, the Bilateral Airworthiness Agreement between Canada and the U.S., is only applicable to work performed in the United States, including Alaska, Hawaii, and Puerto Rico. Under the terms of the bilateral agreement, use of FAA Part 145 “foreign” Repair Stations located elsewhere is not authorised.
(2) For the purpose of executing a maintenance release on Canadian aircraft, bilateral agreements between Canada and another State only have effect within the territory of that State except where:
(a) the agreement specifically provides for such work;
(b) the person certifying the work is working for an organisation that is under the jurisdiction of the state with whom Canada has entered into the agreement; and,
The local TCC is the one having jurisdiction over the geographical area within which the applicant’s approved organization is situated.
(4) On receipt of the application from the responsible TCC, and where the conditions set out in section 571.11 of the CARs have been met, the RCA shall be issued. The RCA shall include the validity period and the scope of work for which it is issued.
Unwillingness on the part of an RCA applicant to pay the remuneration requested by a suitably rated AME who is willing to certify the maintenance, does not constitute valid justification to grant an RCA. The fact that an AMO does not have a suitably endorsed AME on staff is not sufficient justification for issuance of an RCA, if a qualified AME is available in the area.
(5) For the purposes of these standards, the Minister has determined that, in respect of the certification of parts, persons authorised by members of the International Airlines Technical Pool have an equivalent knowledge to that of an AME licensed pursuant to Subpart 403 of the CARs.
(1) A major repair or a major modification shall be reported to the Minister by means of a Major Repair or Major Modification Report in accordance with the specifications set out in Appendix L to this standard.
(i) In conformity with the classification conditions set out in section 571.06 of this standard, examples of reportable major repairs and major modifications could include: spar repair or modification; repair or modification of pressurized fuselage; deviation in configuration from type certification basis; any maintenance that results in an acoustical change; installation of an aeronautical part or equipment that has been subjected to a major repair and or major modification.
(ii) The FAA requires that where a major repair or major modification has been accomplished in Canada on aircraft of United States registry, completion of an FAA Form 337 is required.
(iii) Where a major repair or major modification has been accomplished in the United States on aircraft of Canadian registry, an FAA Form 337 may be provided in lieu of a Major Repair or Major Modification Report.
(2) If major repairs and major modifications are accomplished in accordance with specified data, the information required in the “Description of Work Accomplished” block on the report shall identify the specific data references, for example as found in FAA AC43.13-1, or -2, or both, together with specific reference to the appropriate manufacturer’s installation instructions. A statement such as “performed in accordance with AC43.13-2 and manufacturer’s installation instructions” is not acceptable.
(3) If major repairs and major modifications are accomplished in accordance with the specified data derived from the design approval holder's instructions for continued airworthiness, or from FAA Advisory Circular AC43.13-1, the “Description of Work Accomplished” block shall identify the specific pages, paragraphs, and figures referred to in FAA AC43.13-1, together with the critical dimensions, materials, locations, and processes. This procedure is also applicable to major repairs accomplished in accordance with specified data derived from Structural Repair Manuals. General statements, such as, “performed in accordance with AC43.13-1”are not acceptable.
The following definition applies to this Standard:
“undocumented part” means a part lacking sufficient certification or history to make it eligible for installation on an aircraft without submitting it to a recertification process. (pièce sans appui documentaire)
Pursuant to section 571.13of the CARs, a part is to be inspected and its accompanying documentation verified prior to installation in accordance with a procedure that the Minister finds acceptable, having regard for the safety of the aircraft, to ensure that the part conforms to its type design. In the case of components removed from an aircraft for repair, overhaul or exchange, traceability to their most recent airworthy installation or to their most recent maintenance action will constitute evidence of conformity to type design.
Pursuant to section 571.13 of the CARs and subject to sections 571.07, 571.08, and 571.09 of the CARs, the following standards of airworthiness are applicable to the installation of a part:
(a) except in the case of aircraft that are operated pursuant to a special certificate of airworthiness in the owner-maintenance or amateur-built classification, only parts that are specified in the type design of an aeronautical product, or that are approved alternative parts, are eligible for installation in that product;
An approved alternative part may be a replacement part that has been given either Part Design Approval (TCCA PDA) by Transport Canada or a Parts Manufacturer Approval (FAA PMA) by the Federal Aviation Administration.
(b) where a type certificate holder assigns a proprietary number during the design phase to a standard or commercial part, and the proprietary part number is the only part number shown in the parts catalogue or similar document, only a part bearing the type certificate holder’s proprietary number, or an approved alternative part, shall be installed;
(i) In some cases, the type certificate holder of an aeronautical product will, through the part number contained in the parts catalogue, add a suffix or a prefix to what appears to be a standard industry part. Where this has occurred, the modified part number is accepted as proprietary to the aeronautical product type certificate holder, and the installation of the standard or commercial part is not permitted without an appropriate engineering approval as a modification.
(ii) In many cases, the illustrated parts catalogue may contain a standard or commercial part number. This may be especially true in the case of bearings and electronic components. Standard and commercial parts having the identical part number may be installed regardless of the part manufacturer.
(c) substitution of equivalent standard or commercial parts is permitted only when the substitution does not constitute a major modification in accordance with section 571.06 of the CARs. Substantiation requires that the characteristics of the substituted part meet, or exceed, all of the requirements of the type design of the part being replaced. Reliance on substitution guides alone is not considered adequate. The evaluation of the characteristics of that part is subject to a review of specific type certificate holder’s data such as technical drawings, specification sheets, or substantiation reports associated with that type design;
(d) the part to be installed must be correctly configured for the installation in the aeronautical product; and
(e) prior to installation, the part should be inspected to ensure that it corresponds with its documentation, there are no signs of obvious damage, corrosion or deterioration, and the shelf life, where applicable, has not been exceeded.
Information Note:A person who has reasonable grounds to believe that a part installed or intended for installation in a type certified aeronautical product that was not manufactured or certified in accordance with the applicable regulations of the state of production, or that is improperly marked, or that is documented in such a manner as to mislead with regard to the origin, identity or condition of the part shall submit to the Minister a report of the suspected unapproved part, using the service difficulty reporting system set out in section 521.401 of the CARs.
- Appendix A - Criteria for the Classification of Modifications and Repairs
- Appendix B - Altimeter System Test and Inspection
- Appendix C - Aircraft Weight and Balance Control
- Appendix D - Field Repair of Aircraft Propellers
- Appendix E - Inspection of Aircraft Wooden Components
- Appendix F - ATC Transponder Performance Tests
- Appendix G - Maintenance of Emergency Locator Transmitters (ELTs)
- Appendix H - Process to Evaluate Undocumented Aircraft Parts
- Appendix I - Reserved
- Appendix J - Authorized Release Certificate
- Appendix K - Training to perform Specific Non-destructive Testing (NDT) Tasks
- Appendix L - Conformity Certificate - Repair or Modification
- Appendix M - On Type Maintenance Training Courses