AD/EMB-145/16 Ailerons Power Control Actuator and Damper (Cth)
AIRWORTHINESS DIRECTIVE
For the reasons set out in the background section, the CASA delegate whose signature appears below issues the following Airworthiness Directive (AD) under subregulation 39.001(1) of CASR 1998. The AD requires that the action set out in the requirement section (being action that the delegate considers necessary to correct the unsafe condition) be taken in relation to the aircraft or aeronautical product mentioned in the applicability section: (a) in the circumstances mentioned in the requirement section; and (b) in accordance with the instructions set out in the requirement section; and (c) at the time mentioned in the compliance section.
Embraer EMB-135 and EMB-145 Series Aeroplanes
| AD/EMB-145/16 | Ailerons Power Control Actuator and Damper | 9/2008 DM |
Applicability: | Embraer EMB-145( ) aircraft. |
Requirement: | 1. For aircraft fitted with Power Control Actuator (PCA) P/N 394900-1003, 394900-1005 or 394900-1007: (a) Perform a repetitive visual inspection of all rod ends and fittings in each PCA (RH and LH) at the aileron and wing structure connection points, using a mirror and flashlight, in accordance with Embraer Service Bulletin No. 145-27-0054 Rev. 2, or later revisions approved by the CTA. (b) If any rod end is found cracked or failed, the PCA must be replaced by PCA P/N 418800-1003, 418800-9003, 418800-1005, 418800-9005, 418800-1007 or 418800-9007, in accordance with Embraer Service Bulletin No. (c) If any PCA fitting in the wing or aileron side is found cracked or failed, replace by new reinforced wing or aileron side PCA fittings in accordance with Embraer Service Bulletins Nos. 145-57-0019 Rev. 1 or 145-27-0061 Rev. 1, as applicable, or later revisions approved by the CTA. 2. Aircraft with PCA P/N 394900-1003, 394900-1005, 394900-1007, 418800-1001, 418800-1003, 418800-9003, 418800-1005, 418800-9005, 418800-1007 or 418800-9007: Install new fittings and reinforcements in accordance with Embraer Service Bulletin Nos. 145-57-0019 Rev. 1 and 145-27-0061 Rev. 1, or later revisions approved by the CTA. 3. Aircraft equipped with new ailerons PCA P/N 418800-1001, 418800-1003, 418800-9003, 418800-1005, 418800-9005, 418800-1007 or 418800-9007, in conjunction with the new PCA fittings and reinforcement provisions as detailed in Requirement 2: Perform the visual inspections in accordance with AMM TASK 27-12-01-212-002-A00, "Aileron PCA Rod Ends/Fitting, Lugs for Integrity and General Condition". |
| Terminating Action Aircraft equipped with new aileron PCA P/N 418800-1001, 418800-1003, Note: DAC AD 1999-02-01R6 refers. | |
Compliance: | For Requirement 1(a). For aircraft equipped with PCA P/N 394900-1003 or 394900-1005, at intervals not exceeding 25 flight hours or 3 operating days, whichever occurs later. For aircraft equipped with PCA P/N 394900-1007, at intervals not exceeding 100 flight hours or 14 operating days, whichever occurs later. For Requirements 1(b) and 1(c). Before later flight. For Requirement 2. Before the aircraft completes 6000 operating cycles. For Requirement 3. At intervals not to exceed 500 flight hours. |
| This Airworthiness Directive becomes effective on 29 June 2008. |
Background: | There have been occurrences of broken rod ends of the aileron PCA in different aircraft, either at the aileron or at the wing structure connection points. Several failures have also occurred in the aileron PCA fittings at the wing side. |
James Coyne
Delegate of the Civil Aviation Safety Authority
24 June 2008
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