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2.4 A CAD Form 1 issued in accordance with this paragraph 2 should be issued by signing in block 20 and stating "Inspected" in block 12. In addition, block 13 should specify:
2.4.1 when the last maintenance was carried out and by whom;
2.4.2 if the component is unused, when the component was manufactured and by whom with a cross reference to any original documentation which should be included with the Form;
2.4.3 a list of all airworthiness directives, repairs and modifications known to have been incorporated. If no airworthiness directives or repairs or modifications are known to be incorporated then this should be so stated
2.4.4 detail of life used for service life limited parts being any combination of fatigue, overhaul or storage life;
2.4.5 for any aircraft component having its own maintenance history record, reference to the particular maintenance history record as long as the record contains the detailsthat would otherwise be required in block 13. The maintenance history record and acceptance test report or statement, if applicable, should be attached to the CAD Form 1.
2.5 New / unused aircraft components
2.5.1 Any unused aircraft component in storage without an CAD Form 1 up to the effective date(s) for MCAR-21 that was manufactured by an organisation acceptable to CAD at the time may be issued a CAD Form 1 by an appropriately rated maintenance organisation approved under MCAR-M Subpart F. The CAD Form 1 should be issued in accordance with the following subparagraphs which should be included in a procedure within the maintenance organisation manual.
Note 1: It should be understood that the release of a stored but unused aircraft component in accordance with this paragraph represents a maintenance release under MCAR-M Subpart F and not a production release under MCAR-21. It is not intended to bypass the production release procedure for parts and subassemblies intended for fitment on the manufacturers own production line.
(a)
An acceptance test report or statement should be available for all used and unused aircraft components that are subjected to acceptance testing after manufacturing or maintenance as appropriate.
(b)
The aircraft component should be inspected for compliance with the manufacturer’s instructions and limitations for storage and condition including any requirement for limited storage life, inhibitors, controlled climate and special storage containers. In addition or in the absence of specific storage instructions the aircraft component should be inspected for damage, corrosion and leakage to ensure good condition.
(c)
The storage life used of any storage life limited parts should be established.
2.5.2 If it is not possible to establish satisfactory compliance with all applicableconditions specified in subparagraph 2.5.1 (a) to (c) inclusive the aircraft component should be disassembled by an appropriately rated organisation and subjected to a check for incorporated airworthiness directives, repairs and modifications and inspected/tested in accordance with the manufacturers maintenance instructions to establish satisfactory condition and, if relevant, all seals, lubricants and life limited parts replaced. On satisfactory completion after reassembly a CAD Form 1 may be issued stating what was carried out and the reference of the manufacturers maintenance instructions included.
2.6 Used aircraft components removed from a serviceable aircraft.
2.6.1 Serviceable aircraft components removed from a Maldivian registered aircraft may be issued a CAD Form 1 by an appropriately rated organisation subject to compliance with this subparagraph.
(a)
The organisation should ensure that the component was removed from the aircraft by an appropriately qualified person.
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