(c)  
As a minimum, the assessment will need to satisfy the standards set out in paragraphs 2.5 and 2.6 as appropriate. This should, where known, include the possible need for the alignment of scheduled maintenance that may be necessary to comply with the maintenance programme applicable to the aircraft on which the component is to be installed.

(d)
Irrespective of whether the aircraft holds a certificate of airworthiness or not, the organisation responsible for certifying any removed component should satisfy itself that the manner in which the components were removed and stored are compatible with the standards required by M.A Subpart F.

(e)
A structured plan should be formulated to control the aircraft disassembly process. The disassembly is to be carried out by an appropriately rated organisation under the supervision of certifying staff, who will ensure that the aircraft components are removed and documented in a structured manner in accordance with the appropriate maintenance data and disassembly plan.

(f)  
All recorded aircraft defects should be reviewed and the possible effects these may have on both normal and standby functions of removed compo-nents 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 deci-sion 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 M.A 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 the manufacturer’s recommendations.

2.8. Used  aircraft components maintained by organisations not approved in accordance with M.A Subpart F or Part-145.
For used components maintained by a maintenance organisation not approved under Part-M Subpart F or Part-145, due care should be taken before acceptance of such components. In such cases an appropriately rated maintenance organisa-tion approved under M.A 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-limited components when no satisfactory evidence of life used is available and/or the components are in an unsatisfactory condi-tion,

(c)
reassembling and testing as necessary the component,

(d)
completing all certification requirements as specified in M.A.613.

In the case of used components maintained by an FAA Part-145 repair station (USA) or by TCCA CAR573 approved maintenance organisations (Canada) that does not hold an EASA Part-145 or M.A. 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)  or an Authorized Release Certificate Form One (TCCA),

(b)
verification of compliance with all applicable airworthiness directives,

ED 2010/002/R
Section A
PART-M
Subpart F

ED 2010/002/R
(c)  
verification that the component does not contain repairs or modifications that have not been approved in accordance with Part-21,

(d)
inspection for satisfactory condition including in particular damage, corro-sion or leakage,
　
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