Airworthiness Directive · Amendment 39-23020 · Flight controls
Embraer S.A. (Type Certificate Previously Held by Yaborã Indústria Aeronáutica S.A.; Embraer S.A.; Empresa Brasileira de Aeronáutica S.A. (EMBRAER)) Airplanes
This AD applies to all Embraer S.A. (Type Certificate previously held by Yaborã Indústria Aeronáutica S.A.; Embraer S.A.; Empresa Brasileira de Aeronáutica S.A. (EMBRAER)) Model EMB-145, -145ER, -145MR, -145LR, -145XR, -145MP, and -145EP airplanes, certificated in any category.
The FAA is superseding Airworthiness Directive (AD) 2006-20- 08, which applied to all Embraer S.A. Model EMB-145, -145ER, -145MR, - 145LR, -145XR, -145MP, and -145EP airplanes. AD 2006-20-08 required repetitive inspections to detect cracking or failure of the rod ends and fittings of the aileron power control actuator (PCA), and corrective actions if necessary, and provided an optional terminating action. This AD was prompted by a determination that there was an error in identifying a maintenance task number. This AD continues to require the actions in AD 2006-20-08 and corrects an error in a task number, as specified in an Ag[ecirc]ncia Nacional de Avia[ccedil][atilde]o Civil (ANAC) AD, which is incorporated by reference. The FAA is issuing this AD to address the unsafe condition on these products.
Except as specified in paragraphs (h) and (i) of this AD: Comply with all required actions and compliance times specified in, and in accordance with, Agência Nacional de Aviação Civil (ANAC) AD 1999-02-01R7, effective May 6, 2024; as corrected October 11, 2024 (ANAC AD 1999-02-01R7).
(1) Where ANAC AD 1999-02-01R7 refers to “21 jul. 2004,” this AD requires using November 8, 2006 (the effective date of AD 2006-20-08).
(2) This AD does not adopt paragraph (f) of ANAC AD 1999-02-01R7.
(3) Where ANAC AD 1999-02-01R7 specifies “operating days,” this AD requires replacing that text with “days.”
(4) Where paragraphs (a)2. and (a)3. of ANAC AD 1999-02-01R7 specify to replace cracked and failed rod ends and PCA fittings, for this AD, all applicable replacements must be done before further flight.
(5) Where paragraph (a) of ANAC AD 1999-02-01R7 does not specify an initial compliance time for the repetitive inspections, for this AD, the initial compliance time for the inspection is at the applicable time identified in paragraph (h)(5)(i), (ii), or (iii) of this AD.
(i) For airplanes that have PCAs with part number (P/N) 394900-1003 or 394900-1005, do the initial inspection within 3 days after November 8, 2006.
(ii) For airplanes that have PCAs with P/N 394900-1007, do the initial inspection within 14 days after November 8, 2006.
(iii) For airplanes that have PCAs with P/Ns 418800-1001, 418800-1003, 418800-9003, 418800-1005, 418800-9005, 418800-1007, or 418800-9007; and that have new reinforced PCA fittings installed in accordance with paragraph (k) or (l) of AD 2006-20-08 or paragraph (b) of ANAC AD 1999-02-01R7, do the initial inspection within 500 flight hours after November 8, 2006.
(6) Where paragraph (b) of ANAC AD 1999-02-01R7 specifies to accomplish an installation within “6000 operating cycles,” for this AD, the compliance time is at the applicable time specified in paragraph (h)(6)(i) or (ii) of this AD.
(i) For airplanes with PCAs with P/N 394900-1003, 394900-1005, or 394900-1007: At the later of the times in paragraphs (h)(6)(i)(A) or (B) of this AD.
(A) Before the airplane accumulates 6,000 total flight hours.
(B) Within 3 days or 25 flight hours after November 8, 2006 (the effective date of AD 2006-20-08), whichever occurs later.
(ii) For airplanes with PCAs with P/N 418800-1001, 418800-1003, 418800-9003, 418800-1005, 418800-9005, 418800-1007, or 418800-9007: Before the airplane accumulates 6,000 total flight cycles or within 600 flight cycles after November 8, 2006 (the effective date of AD 2006-20-08), whichever occurs later.
(7) Where paragraph (c) of ANAC AD 1999-02-01R7 specifies to do an inspection in accordance with a task, for this AD, inspections done before the effective date of this AD using AMM Task 27-12-01-212-002-A00 or using a method approved by either the Manager, International Validation Branch, FAA, or ANAC (or its delegated agent) are acceptable methods of compliance. Inspections done on or after the effective date of this AD must be done using the task identified in paragraph (c) of ANAC AD 1999-02-01R7 or using a method approved as specified in paragraph (k)(2) of this AD.
(8) Where paragraph (c) of ANAC AD 1999-02-01R7 specifies to accomplish the initial inspection “in conjunction with the new PCA fittings and reinforcement provisions referred on item (b) above,” this AD requires replacing that text with “within 500 flight hours after accomplishing the installation and reinforcements provisions referred to in item (b) above.”
(9) Where paragraph (c) of ANAC AD 1999-02-01R7 specifies to accomplish the inspections “every 500 flight hours” this AD requires replacing that text with “at intervals not to exceed 500 flight hours.”
(10) Where paragraph (d) of ANAC AD 1999-02-01R7 specifies to accomplish the inspections “every 1000 flight hours” this AD requires replacing that text with “at intervals not exceeding 1,000 flight hours.”
The aircraft, engines and makers this AD names, by the model designations in its text. A model listed here may still be outside the AD's serial ranges.
Aircraft
