Division Embraer EMB-135 and EMB-145 Series Aerop - AD/EMB-145/16 - Ailerons Power Control Actuator and Damper - Embraer EMB-135 and EMB-145 Series Aeroplanes

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.145-27-0062, original issue, or later revisions approved by the CTA.(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".

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.145-27-0062, original issue, or later revisions approved by the CTA.(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 ActionAircraft equipped with new aileron PCA P/N 418800-1001, 418800-1003,418800-9003, 418800-1005, 418800-9005, 418800-1007 or 418800-9007, PCA and damper fittings and reinforcements, and aileron damper P/N 41012130-103 or 41012130-104, installed in production line or by incorporation of the Embraer Service Bulletins Nos. 145-27-0063, original issue (damper installation), 145-27-0061 Rev. 1 (aileron damper fitting and reinforcement installation), 145-57-0019 Rev. 1 (wing damper fitting installation) and 145-27-0062, original issue (PCA installation), or later revisions approved by the CTA, are no longer subject to the provisions of this AD provided the visual inspection of the PCA and damper terminals and fittings at the wing and aileron sides, for structural integrity, established in the EMB-145 MRB document for every 1000 flight hours, are implemented.Note: DAC AD 1999-02-01R6 refers.

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