Document ID: chunk:federal_register_of_legislation:F2007L04506:body:0:p2
Version: federal_register_of_legislation:F2007L04506
Segment Type: other
Provision Reference: 
Character Range: 3013–4548

of the effective date of this Directive:

                        Carry out the requirements of Requirement 3.a. concurrent with the requirements of Requirement 2 of this Directive.

                Note 3:  Transport Canada AD CF-2005-34R1 refers.
Compliance:     For Requirements 1 and 2:  Within 24 months after 27 October 2005.

                For Requirement 3.a:  Within 12 months after 20 December 2007, unless already accomplished.

                The compliance time for Requirements 1 and 2 remains unchanged by this issue of the Directive.
                This Amendment becomes effective on 20 December 2007.
Background:     During testing of the cockpit door, it was observed that the door lower hinge block rotated which resulted in disengagement of the mating hinge pin and excessive door deflection.  The lower hinge block rotated because it was attached to its support structure with only one attachment bolt, which prevented it from reacting to any moment force.  This condition, if not corrected, could result in breakage and uncontrolled release of the cockpit door under certain decompression situations.

                Amendment 1 is issued in response to a revision of the related Transport Canada AD, which requires rework of the cockpit door striker plate and replacement of the latch block for affected aircraft serial numbers, and additionally, clarifies the Modsums required prior to incorporation of Requirement 2.

David Villiers
Delegate of the Civil Aviation Safety Authority

7 November 2007