Document ID: chunk:federal_register_of_legislation:F2008L02286:body:0:p2
Version: federal_register_of_legislation:F2008L02286
Segment Type: other
Provision Reference: 
Character Range: 3088–4767

Nos. 145-27-0063, original issue (damper installation), 145-27-0061 Rev. 1 (aileron damper fitting and reinforcement installation), 145-57-0019 Rev. 1 (wing damper fitting installation) and 145-27-0062, original issue (PCA installation), or later revisions approved by the CTA, are no longer subject to the provisions of this AD provided the visual inspection of the PCA and damper terminals and fittings at the wing and aileron sides, for structural integrity, established in the EMB-145 MRB document for every 1000 flight hours, are implemented.

             Note:  DAC AD 1999-02-01R6 refers.
Compliance:     For Requirement 1(a).

                For aircraft equipped with PCA P/N 394900-1003 or 394900-1005, at intervals not exceeding 25 flight hours or 3 operating days, whichever occurs later.

                For aircraft equipped with PCA P/N 394900-1007, at intervals not exceeding 100 flight hours or 14 operating days, whichever occurs later.

                For Requirements 1(b) and 1(c).

                Before later flight.

                For Requirement 2.

                Before the aircraft completes 6000 operating cycles.

                For Requirement 3.

                At intervals not to exceed 500 flight hours.
             This Airworthiness Directive becomes effective on 29 June 2008.

Background:  There have been occurrences of broken rod ends of the aileron PCA in different aircraft, either at the aileron or at the wing structure connection points.  Several failures have also occurred in the aileron PCA fittings at the wing side.

James Coyne
Delegate of the Civil Aviation Safety Authority

24 June 2008