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2014-0223R1 : Time Limits / Maintenance Checks – ALS Part 1 – Certification Maintenance Requirements – Implementation

Number 2014-0223R1
Issued by Europe  Europe
Issue date 2020-08-25
Effective date 2020-09-01
EASA approval number
Contributor EASA Large Aeroplanes Department
ATA Chapter 05
Approval Holder
/ Type Designation
  • FOKKER SERVICES
    • F27
      • MARK050
      • MARK0502
      • MARK0604
Revision This AD revises EASA AD 2014-0223 dated 08 October 2014.
Correction Not applicable
Supersedure The original issue of this AD superseded EASA AD 2014-0151 dated 20 June 2014.
Publication(s) and related information Fokker 50/60 Instructions for Continued Airworthiness, ALS Part 1, Fokker Services Engineering Report SE-525 issue 6, dated 26 April 2012, or issue 7, dated 26 July 2016. The use of later approved revisions of the above-mentioned document is acceptable for compliance with the requirements of this AD.
PAD number 14-136
Remarks 1. If requested and appropriately substantiated, EASA can approve Alternative Methods of Compliance for this AD. 2. The original issue of this AD was posted on 04 September 2014 as PAD 14-136 for consultation until 02 October 2014. The Comment Response Document can be found in the EASA Safety Publications Tool, in the compressed (zipped) file attached to the record for this AD. 3. Enquiries regarding this AD should be referred to the EASA Programming and Continued Airworthiness Information Section, Certification Directorate. E-mail: ADs[at]easa.europa.eu. 4. Information about any failures, malfunctions, defects or other occurrences, which may be similar to the unsafe condition addressed by this AD, and which may occur, or have occurred on a product, part or appliance not affected by this AD, can be reported to the EU aviation safety reporting system. This may include reporting on the same or similar components, other than those covered by the design to which this AD applies, if the same unsafe condition can exist or may develop on an aircraft with those components installed. Such components may be installed under an FAA Parts Manufacturer Approval (PMA), Supplemental Type Certificate (STC) or other modification.