Document ID: chunk:federal_register_of_legislation:F2006L01572:body:0:p2
Version: federal_register_of_legislation:F2006L01572
Segment Type: other
Provision Reference: 
Character Range: 3016–5527

paragraph 3 of the Accomplishment Instructions of Hamilton Sundstrand ASB No. 14RF- 9-61-A146.

                  (b) Perform a 2nd inspection for delamination in accordance with paragraph 3 of the Accomplishment Instructions of Hamilton Sundstrand ASB No.
                  14RF-9-61-A146.

                4. Blades That Fail Inspection

                Remove propeller blades from service that fail inspection.

                5. Blade Removal From Service

                Remove from service all blades of the "+E'' repair configuration having SNs below 885751.

                6. "+E'' repair configuration having SNs below 885751.

                Do not install any blades of the "+E'' repair configuration having SNs below 885751, onto any propeller.

             Note 4:  Hamilton Sundstrand ASB No. 14RF-9-61-A147, dated 19 April 2006, contains information on upgrading the removed blades to the "+E2'' repair configuration.

                7. Inspection Reporting Requirement

                Record the inspection data on a copy of the data sheet.  The data sheet is on page 10 of ASB No. 14RF-9-61-A145 and ASB No. 14RF-9-61-A146.  Report the inspection data to Hamilton Sundstrand, fax 0011-1-800-654-5107, and CASA via the SDR reporting system.

             Note 5:  FAA AD 2006-10-07 Amdt 39-14591 refers.
Compliance:     1. Within 10 flight cycles or 5 days after the effective date of this AD, whichever occurs first.

                2. After accumulating an additional 500 flight cycles or by 1 July 2006, whichever occurs first, after the effective date of this AD.

                  3. (a) Before installing the blade.

                  3. (b) At least 7 days after installing the blade, but no later than 60 days after the initial inspection.

                4. Before further flight, after the effective date of this AD.

                5. By 1 March 2007.

                6. After 1 March 2007.

                7. Within 10 days after each blade inspection, unless previously accomplished.
             This Airworthiness Directive becomes effective on 25 May 2006.
Background:  This AD results from reports of delaminated blade fibreglass repair patches that allowed corrosion to form on the aluminium blade spar under the patch.  The requirements of this AD are to prevent blade failure that could result in separation of a propeller blade and loss of control of the aeroplane.

James Coyne
Delegate of the Civil Aviation Safety Authority

22 May 2006