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AD/CAP 10/13 Amdt 1 - Flight Controls Tie Rod Bolts
Avions Mudry Cap Series AeroplanesAvions Mudry Cap Series Aeroplanes
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Avions Mudry Cap Series Aeroplanes
| AD/CAP 10/13 Amdt 1 | Flight Controls Tie Rod Bolts | 4/2009 |
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| Applicability: | Model CAP 10B aircraft, serial numbers 300 through 317, and CAP 10B aircraft that have embodied APEX change 000302 - carbon fibre wing spars (trademarked asCAP 10C). |
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| Requirement: | 1. Unless the rods and spacers have already been replaced in accordance with the initial issue of this Directive, inspect tie rod spacers part number 11.56.27.038 for condition in accordance with APEX CAP 10C Maintenance Manual Chapter27-10-00 page 6-3.2. If any damaged spacer is found during any inspection, remove tie rod bolts part number 95.56.11.066 and spacers part number 11.56.27.038 and replace them by tie rod bolts part number 95.56.11.418 and spacers part number 11.56.27.138, in accordance with the accomplishment instructions of APEX AIRCRAFT Service Bulletin 040206, original issue, or later EASA approved revision.Removal of tie rod bolts part number 95.56.11.066 and spacers part number 11.56.27.038 and replacement by tie rod bolts part number 95.56.11.418 and spacers part number 11.56.27.138, in accordance with the accomplishment instructions of APEX AIRCRAFT Service Bulletin 040206, original issue, or later EASA approved revision, constitutes terminating action to the requirements of this Directive.After the effective date of this Directive, no person shall install, on any aircraft, tie rod bolts part number 95.56.11.066 and spacers part number 11.56.27.038.Note: EASA AD 2008-0060R1 refers. |
| Compliance: | 1. Within 50 flight hours after 9 April 2009, and thereafter at intervals not to exceed 50 flight hours; unless the rods and spacers have already been replaced.2. Before further flight. |
| This Amendment becomes effective on 9 April 2009. |
| Background: | The manufacturer has determined that the flight controls tie rod bolts currently installed on CAP 10B aircraft are not in accordance with design data. The bolt shank length was found to be too short, and additionally, the material properties of the spacers have been found to be inadequate for the prescribed torque value. Excessive wear on the threads of the bolts could result in play in the flight controls, with consequent control surface vibration which could result in loss of control of the aircraft.Amendment 1 is issued in response to a revision of the related EASA AD, which introduces a repetitive inspection of the spacers, and optional terminating action for replacement of tie rod bolts and spacers by new part number parts. The EASA AD was prompted after investigation of removed spacers revealed no evidence of significant damage. |
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