(f)
All recorded aircraft defects should be reviewed and the possible effects these may have on both normal and standby functions of removed components are to be considered.
(g)
Dedicated control documentation is to be used as detailed by the disassembly plan, to facilitate the recording of all maintenance actions and component removals performed
during the disassembly process. Components found to be unserviceable are to be identified as such and quarantined pending a decision on the actions to be taken. Records of the maintenance accomplished to establish serviceability are to form part of the component maintenance history.
(h)
Suitable MCAR-M Subpart F facilities for the removal and storage of removed components are to be used which include suitable environmental conditions, lighting, access equipment, aircraft tooling and storage facilities for the work to be undertaken. While it may be acceptable for components to be removed, given local environmental conditions, without the benefit of an enclosed facility subsequent disassembly (if required) and storage of the components should be in accordance with manufacturer’s recommendations.
2.8 Used aircraft components maintained by organisations not approved in accordance with MCAR-M Subpart F or MCAR-145.
For used components maintained by a maintenance organisation unapproved under MCAR-M Subpart F or MCAR-145, due care should be exercised before acceptance of such components. In such cases an appropriately rated maintenance organisation approved under MCAR-M Subpart F should establish satisfactory conditions by:
(a)dismantling the component for sufficient inspection in accordance with the appropriate maintenance data,
(b)
replacing of all service life limit components when no satisfactory evidence of life used is available and/or the components are in an unsatisfactory condition,
(c)reassembling and testing as necessary the component,
(d)
completing all certification requirements as specified in MCAR-M.613
In the case of used components maintained by EASA Part-145 or M.A. Subpart F, FAA Part-145 repair station (USA) or by TCCA CAR573 approved maintenance organisations (Canada) that does not hold an MCAR-145 or MCAR-M Subpart F approval, the conditions (a) through (d) described above may be replaced by the following conditions:
(a)availability of an 8130-3 (FAA) or TCCA 24-0078 (TCCA) certificate of release to service.
(b)
verification of compliance with all applicable airworthiness directives, and
(c)verification that the component does not contain repairs or modifications that have not been approved in accordance with MCAR-21.
(d)
inspection for satisfactory condition including in particular damage, corrosion or leakage.
(e)issuance of a CAD Form 1 in compliance with paragraphs 2.2, 2.3 and 2.4.
These alleviated requirements are based on the fact that credit can be taken for their technical capabilities and their competent authority oversight, as attested by the following documents:
.
BASA/MIP-G Maintenance Implementation Procedures Guidance (USA)
.
AAM-G Administrative Arrangement on Maintenance Guidance (Canada)
2.9 Used aircraft components removed from an aircraft involved in an accident or incident.
Such components should only be issued with an CAD Form 1 when processed in accordance with paragraph 2.7 and a specific work order including all additional necessary tests and inspections made necessary by the accident or incident. Such a work order may require input from the TC holder or original manufacturer as appropriate. This work order should be referenced in block 13.
2.
A certificate should not be issued for any component when it is known that the component is unserviceable except in the case of an component undergoing a series of maintenance processes at several approved maintenance organisations and the component needs a certificate for the previous maintenance process carried out for the next approved maintenance organisation to accept the component for subsequent maintenance processes. A clear statement of limitation should be endorsed in block 13.
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