(e)
In addition to the authorised release document, EASA Form 1 or equivalent, the fol-lowing information relevant to any component installed (engine, propeller, engine module or service life-limited component) shall be entered in the appropriate engine or propeller logbook, engine module or service life limited component log card:

1.  
identification of the component; and

2.  
the type, serial number and registration, as appropriate, of the aircraft, engine, propeller, engine module or service life-limited component to which the particu-lar component has been fitted, along with the reference to the installation and removal of the component; and

3.  
the date together with the component’s accumulated total flight time and/or flight cycles and/or landings and/or calendar time, as appropriate; and

4.  
the current paragraph (d) information applicable to the component.

(f)  
The person responsible for the management of continuing airworthiness tasks pur-suant to M.A. Subpart B, shall control the records as detailed in this paragraph and present the records to the competent authority upon request.

(g)
All entries made in the aircraft continuing airworthiness records shall be clear and accurate. When it is necessary to correct an entry, the correction shall be made in a manner that clearly shows the original entry.

ED 2010/002/R  ED 2010/002/R
AMC M.A.305 (d) Aircraft continuing airworthiness record system
The current status of AD should identify the applicable AD including revision or amend-ment numbers. Where an AD is generally applicable to the aircraft or component type but is not applicable to the particular aircraft or component, then this should be identi-fied. The AD status includes the date when the AD was accomplished, and where the AD is controlled by flight hours or flight cycles it should include the aircraft or engine or component total flight hours or cycles, as appropriate. For repetitive ADs, only the last application should be recorded in the AD status. The status should also specify which part of a multi-part directive has been accomplished and the method, where a choice is available in the AD.
The status of current modification and repairs means a list of embodied modification and repairs together with the substantiating data supporting compliance with the airworthi-ness requirements. This can be in the form of a Supplemental Type Certificate (STC), SB, Structural Repair Manual (SRM) or similar approved document.
The substantiating data may include:
(a)
compliance programme; and

(b)
master drawing or drawing list, production drawings, and installation instructions; and

(c)
engineering reports (static strength, fatigue, damage tolerance, fault analysis, etc.); and

(d)
ground and flight test programme and results; and

(e)  
mass and balance change data; and

(f)  
maintenance and repair manual supplements; and

(g)
maintenance programme changes and instructions for continuing airworthiness; and

(h)
aircraft flight manual supplement.

Some gas turbine engines are assembled from modules and a true total time in service for a total engine is not kept. When owners and operators wish to take advantage of the modular design, then total time in service and maintenance records for each module is to be maintained. The continuing airworthiness records as specified are to be kept with the module and should show compliance with any mandatory requirements pertaining to that module.
AMC M.A.305 (d) (4) and AMC M.A.305 (h) Aircraft continuing airworthiness record system
The term ‘service life-limited components’ embraces: (i) components subject to a certified life limit after which the components should be retired, and (ii) components subject to a service life limit after which the components should undergo maintenance to restore their serviceability.
　
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