Monday, March 16, 2015

Component Installation

                                          M.A.501 Installation
               (a) No component may be fitted unless it is in a satisfactory condition, has been
appropriately released to service on a CA Form 1 or equivalent and is marked in
accordance with CAR 21 Subpart Q, unless otherwise specified in CAR 21, CAR 145 or CAR-M Section A, Subpart F.
              (b) Prior to installation of a component on an aircraft the person or approved
maintenance organisation shall ensure that the particular component is eligible
for fitment.
              (c) Standard parts shall only be fitted to an aircraft or a component when the
maintenance data specifies the particular standard part. Standard parts shall only be fitted when accompanied by evidence of conformity traceable to the applicable standard.
             (d) Material being either raw material or consumable material shall only be used on
an aircraft or a component when the aircraft or component manufacturer states so in relevant maintenance data or as specified in CAR -145. Such material shall only be used when the material meets the required specification and has appropriate traceability. All material must be accompanied by documentation clearly relating to the particular material and containing conformity to specification statement plus both the manufacturing and supplier source.
                                  AMC M.A.501 (a) Installation
      1. To ensure a component is in a satisfactory condition, the person referred to under M.A.801 or the approved maintenance organisation should perform checks and verifications.
      2. Performance of above checks and verifications should take place before the component is installed on the aircraft.
     3. The following list, though not exhaustive, contains typical checks to be performed:
            a) verify the general condition of components and their packaging in relation to
damages that could affect the integrity of the components;
            b) verify that the shelf life of the component has not expired;
            c) verify that items are received in the appropriate package in respect of the type of component: e.g. correct ATA 300 or electrostatic sensitive devices packaging, when necessary;
            d) verify that component has all plugs and caps appropriately installed to prevent damage or internal contamination. Tape should not be used to cover electrical connections or fluid fittings/openings because adhesive residues can insulate electrical connections and contaminate hydraulic or fuel units.
     4. The purpose of the CA Form 1 (see also CAR M Appendix II) is to release components after manufacture and to release maintenance work carried out on such components under the approval of a DGCA and to allow components removed from one aircraft/component to be fitted to another aircraft/ component.
      5. For the purpose of CAR - M, a document equivalent to a CA Form 1 may be:
            - a release document issued by an organisation under the terms of a bilateral agreement signed by DGCA
           - EASA Form ONE
           - FAA Form 8130-3
           - Any other form acceptable to DGCA.
6. Any item in storage without CA Form 1 or equivalent cannot be installed on aircraft
registered in India unless CA Form 1 is issued for such item by an appropriately
approved maintenance organisation in accordance with AMC M.A.613 (a)

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