(a) EFFECTIVE DATE

    This airworthiness directive (AD) is effective June 26, 2025.

(b) AFFECTED ADS

    This AD replaces AD 2006-20-08, Amendment 39-14777 (71 FR 58487, Octo-
    ber 4, 2006) (AD 2006-20-08).

(c) APPLICABILITY

    This AD applies to all Embraer S.A.  (Type Certificate previously held
    by Yabora Industria Aeronautica S.A.; Embraer S.A.; Empresa Brasileira
    de Aeronautica S.A. (EMBRAER))  Model EMB-145, -145ER, -145MR, -145LR,
    -145XR, -145MP, and -145EP airplanes, certificated in any category.

(d) SUBJECT

    Air Transport Association (ATA) of America Code 27, Flight Controls.

(e) UNSAFE CONDITION

    This AD was prompted by reports of broken rod ends of the aileron pow-
    er control actuator (PCA) at the aileron or at the wing structure con-
    nection points  and a determination  that an incorrect task number was
    published in AD 2006-20-08.  The FAA is issuing  this  AD  to  address
    cracking  or  breaking of the rod ends and  connecting fittings of the
    aileron PCA. The unsafe condition,  if not addressed,  could result in
    reduced controllability of the airplane.

(f) COMPLIANCE

    Comply with this AD within the compliance times specified,  unless al-
    ready done.

(g) REQUIREMENTS

    Except as specified in paragraphs (h) and (i) of this AD:  Comply with
    all required actions and compliance times specified in, and in accord-
    ance with,  Agencia Nacional de Aviacao Civil (ANAC)  AD 1999-02-01R7,
    effective May 6, 2024; as corrected October 11, 2024 (ANAC AD 1999-02-
    01R7).

(h) EXCEPTIONS TO 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 ini-
    tial 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 in-
     spection 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 compli-
    ance 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 inspec-
    tion 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 Valida-
    tion 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 para-
    graph (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."

(i) CREDIT FOR PREVIOUS ACTIONS

    This paragraph provides credit  for the replacement specified in para-
    graph (a)2.  of  ANAC AD 1999-02-01R7  and  the  optional  terminating
    actions specified in paragraph (d) of ANAC AD 1999-02-01R7,  if  those
    actions were performed  before the effective date  of  this  AD  using
    EMBRAER Service Bulletin 145-27-0061, dated October 19, 1999.

(j) NO RETURN OF PARTS

    Although the material  identified in ANAC AD 1999-02-01R7 specifies to
    send removed parts to the parts manufacturer, this AD does not include
    that requirement.

(k) ADDITIONAL AD PROVISIONS

    The following provisions also apply to this AD:

(1) Alternative Methods of Compliance (AMOCs):  The Manager, International
    Validation Branch FAA, has the authority to approve AMOCs for this AD,
    if requested using the procedures found in 14 CFR 39.19. In accordance
    with 14 CFR 39.19,  send your request  to your principal inspector  or
    responsible Flight Standards Office, as appropriate. If sending infor-
    mation directly to the manager of the International Validation Branch,
    send it to the attention of the person  identified in paragraph (l)(1)
    of this AD and email to: AMOC@faa.gov.

(i) Before using any approved AMOC,  notify your appropriate principal in-
    spector, or lacking a principal inspector,  the manager of the respon-
    sible Flight Standards Office.

(ii) AMOCs approved previously for AD 2006-20-08 are approved as AMOCs for
     the corresponding provisions  of  ANAC  AD 1999-02-01R7  that are re-
     quired by paragraph (g) of this AD.

(2) Contacting the Manufacturer:  For any requirement in this AD to obtain
    instructions from a manufacturer,  the  instructions  must  be  accom-
    plished using a method approved by the Manager,  International Valida-
    tion Branch, FAA; or ANAC; or ANAC's authorized Designee.  If approved
    by the ANAC Designee, the approval must include the Designee's author-
    ized signature.

(l) ADDITIONAL INFORMATION

(1) For more information about this AD,  contact Hassan Ibrahim,  Aviation
    Safety Engineer,  FAA,  1600 Stewart Avenue,  Suite 410,  Westbury, NY
    11590; phone: 206-231-3653; email: hassan.m.ibrahim@faa.gov.

(2) For EMBRAER material identified in this AD that is not incorporated by
    reference,  contact  Embraer S.A.,  Technical Publications Section (PC
    060), Av. Brigadeiro Faria Lima, 2170 - Putim - 12227-901 Sao Jose dos
    Campos-SP-Brazil;  telephone +55 12 3927-5852 or +55 12 3309-0732; fax
    +55 12 3927-7546; email distrib@embraer.com.br;website flyembraer.com.

(m) MATERIAL INCORPORATED BY REFERENCE

(1) The Director of the Federal Register  approved  the  incorporation  by
    reference of the material  listed in this paragraph under 5 U.S.C. 552
    (a) and 1 CFR part 51.

(2) You must use this material as applicable to do the actions required by
    this AD, unless this AD specifies otherwise.

(i) ANAC AD 1999-02-01R7, effective May 6, 2024;  as corrected October 11,
    2024.

(ii) [Reserved]

(3) For ANAC material identified in this AD,  contact  ANAC,  Aeronautical
    Products Certification Branch (GGCP), Rua Dr. Orlando Feirabend Filho,
    230-Centro Empresarial Aquarius-Torre B-Andares 14 a 18,  Parque Resi-
    dencial Aquarius, CEP 12.246-190-Sao Jose dos Campos-SP, Brazil; tele-
    phone 55 (12) 3203-6600; email pac@anac.gov.br.  You may find this ma-
    terial on the ANAC website at sistemas.anac.gov.br/certificacao/DA/DAE
    .asp.

(4) You may view this material at the FAA, Airworthiness Products Section,
    Operational Safety Branch,  2200 South 216th St.,  Des Moines, WA. For
    information on the availability of this material at the FAA, call 206-
    231-3195.

(5) You may view this material at the National Archives and Records Admin-
    istration (NARA). For information on the availability of this material
    at NARA,  visit www.archives.gov/federal-register/cfr/ibr-locations or
    email fr.inspection@nara.gov.

Issued on May 5, 2025. Steven W. Thompson, Acting Deputy Director, Compli-
ance & Airworthiness Division, Aircraft Certification Service.

FOR FURTHER INFORMATION CONTACT: Hassan Ibrahim, Aviation Safety Engineer,
FAA, 1600 Stewart Avenue, Suite 410,  Westbury, NY 11590;  phone: 206-231-
3653; email hassan.m.ibrahim@faa.gov.