(b)
Only the authorised certifying staff, according to points M.A.801(b)1, M.A.801(b)2, M.A.801(c), M.A.801(d) or CAR 145 can decide, using M.A.401 maintenance data, whether an aircraft defect hazards seriously the flight safety and therefore decide when and which rectification action shall be taken before further flight and which defect rectification can be deferred. However, this does not apply when:

1.  
the approved minimum equipment list as mandated by the DGCA is used by the pilot and AME; or,

2.  
aircraft defects are defined as being acceptable by DGCA.

(c)
Any aircraft defect that would not hazard seriously the flight safety shall be rectified as soon as practicable, after the date the aircraft defect was first identified and within any limits specified in the maintenance data.

(d)
Any defect not rectified before flight shall be recorded in the M.A.305 aircraft maintenance record system or M.A.306 operator's technical log system as applicable.

Rev 0, dated 2nd March, 2010
SUBPART E

COMPONENTS
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 a conformity to specification statement plus both the manufacturing and supplier source.

M.A.502 Component maintenance
a)  The maintenance of components shall be performed by maintenance organisations appropriately approved in accordance with Section A, Subpart F of CAR-M or with CAR145.
b)  By derogation from paragraph (a), maintenance of a component in accordance with aircraft maintenance data or, if agreed by DGCA, in accordance with component maintenance data, may be performed by an A rated organisation approved in accordance with Section A, Subpart F of CAR-M or CAR 145 as well as by certifying staff referred to in point M.A.801(b)2 only whilst such components are fitted to the aircraft. Nevertheless, such organisation or certifying staff may temporarily remove this component for maintenance, in order to improve access to the component, except when such removal generates the need for additional maintenance not eligible for the provisions of this paragraph. Component maintenance performed in accordance with this paragraph is not eligible for the issuance of a CA Form 1 and shall be subject to the aircraft release requirements provided for in point M.A.801.
c)  By derogation from paragraph (a), maintenance of an engine/Auxiliary Power Unit (APU) component in accordance with engine/APU maintenance data or, if agreed by DGCA, in accordance with component maintenance data, may be performed by a B rated organisation approved in accordance with Section A, Subpart F of CAR-M or
Rev 0, dated 2nd March, 2010 CAR 145 only whilst such components are fitted to the engine/APU. Nevertheless, such B rated organisation may temporarily remove this component for maintenance, in order to improve access to the component, except when such removal generates the need for additional maintenance not eligible for the provisions of this paragraph. 
　
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