Bell Helicopter Textron 47 (All Variants
Bell Helicopter Textron 47 (All Variants) Series Helicopters
Bell Helicopter Textron 47 (All Variants) Series Helicopters
| AD/BELL 47/102 | Main Rotor Blades Box Beam Clips | 8/2009 DM |
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| Applicability: | Model 47, 47B, 47B3, 47D, 47D1, 47E, 47G, 47G-2, 47G-2A, 47G-2A-1, 47G-3, 47G-3B, 47G-3B-1, 47G-3B-2, 47G-3B-2A, 47G-4, 47G-4A, 47G-5, 47G-5A,47H-1, 47J, 47J-2, 47J-2A and 47K helicopters, with a main rotor blade part number and serial number listed below, installed:Blade Part Number Blade Serial Number047-110-250-021 A-303, A-304, A-312 or A-316047-110-250-023 A-298, A-301 or A-305 |
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| Requirement: | Visually inspect the entire length of each main rotor blade from the main rotor blade tip to the root in accordance with Part II of the Accomplishment Instructions, paragraphs 1. through 8. of Bell Helicopter Textron Inc. Alert Service Bulletin (ASB) No. 47-08-25, 26 May 2008, or later FAA approved revision; and referring to the depictions in Figures 1 and 2 of ASB No. 47-08-25, and Figure 1 of this Directive for correct installation.Figure 1 - Correct Installation of Clip for Box Beam |
| If a main rotor blade is found with an incorrectly installed clip, before further flight, replace that unserviceable main rotor blade with a serviceable main rotor blade that has a clip that is installed correctly.Special flight permits may be issued to operate the helicopter to a location where the requirements of this Directive can be accomplished, provided the one-time ferry flight does not exceed 5 hours time in service.Note 1: Figure 3 of the Requirement document depicts a clip installed incorrectly.Note 2: FAA AD 2009-12-01 Amdt 39-15924 refers. | |
| Compliance: | Within 10 hours time in service after 29 June 2009, unless already accomplished. |
| This Airworthiness Directive becomes effective on 29 June 2009. | |
| Background: | The FAA received a report of a main rotor blade with an incorrectly installed clip. The actions required by this Directive are intended to prevent a main rotor blade spar crack as a result of an incorrectly installed clip, loss of a main rotor blade, and subsequent loss of control of the helicopter. |
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David Villiers
Delegate of the Civil Aviation Safety Authority
18 June 2009