Document ID: chunk:federal_register_of_legislation:F2005L03888:body:0:p2
Version: federal_register_of_legislation:F2005L03888
Segment Type: other
Provision Reference: 
Character Range: 3043–5264

at intervals not to exceed 200 TEs or 35 hours time in service, whichever occurs first, perform a main rotor blade torque event inspection.

                If a crack is found, before further flight, replace the affected blade with a serviceable blade.

             Note 1:  MD Helicopters Inc. Maintenance Manual CSP-HMI-2, Revision 36, Section 62-10-00, paragraph 8, Main Rotor Blade Torque Event Inspection, pertains to the subject of this Directive.

             Note 2:  MDHI Maintenance Manual CSP-HMI-2, Section 20-30-00 Main Rotor Blade Painting, pertains to the subject of this Directive.  This section of the maintenance manual recommends painting the inboard 24-inches (not to be exceeded) of the blade gloss white to aid in detecting a crack; and if this is done, painting all blades alike and rebalancing them.

             Note 3:  TEs are used only to establish an additional inspection interval and not to establish an alternate retirement life.
Compliance:     1. Within 50 hours time in service after 7 December 2005, unless already accomplished.

                2. As specified in Requirement 2.
             This Amendment becomes effective on 7 December 2005.
Background:  The FAA required certain actions in response to several reports, including a recent report dated 24 July 2003, of blade cracks due to a high number of TEs per hour.  The actions specified in this Directive are intended to prevent fatigue cracking of the blade, blade failure, and subsequent loss of control of the helicopter.

   Amendment 1 is issued in response to a new FAA AD, which revises model applicability, adds MDHI part-numbered blades, removes any reference to the life limits of the blades, changes the requirements for inspecting the blades, and revises the STC applicability.  The FAA AD also provides that compliance with portions of certain documents constitutes alternative methods of compliance, contains editorial changes for clarification, and makes some corrections.  The FAA AD was prompted by additional reports of cracked blades and by comments received in response to FAA AD 2003-24-01.

David Villiers
Delegate of the Civil Aviation Safety Authority

1 December 2005