Airworthiness Directive · Amendment 39-22543 · Fuselage
Airbus SAS Airplanes
This AD applies to Airbus SAS Model airplanes specified in paragraphs (c)(1) through (4) of this AD, certificated in any category, as identified in European Union Aviation Safety Agency (EASA) AD 2023-0009, dated January 16, 2023 (EASA AD 2023-0009).
(1) Model A318-111, -112, -121, and -122 airplanes.
(2) Model A319-111, -112, -113, -114, -115, -131, -132, and -133 airplanes.
(3) Model A320-211, -212, -214, -216, -231, -232, and -233 airplanes.
(4) Model A321-111, -112, -131, -211, -212, -213, -231, and -232 airplanes.
The FAA is superseding Airworthiness Directive (AD) 2020-06- 10, which applied to certain Airbus SAS Model A318 series airplanes; Model A319-111, -112, -113, -114, -115, -131, -132, and -133 airplanes; Model A320-211, -212, -214, -216, -231, -232, and -233 airplanes; and Model A321-111, -112, -131, -211, -212, -213, -231, and -232 airplanes. AD 2020-06-10 required repetitive inspections for cracking of the vertical stiffeners of the left- and right-hand sides of the window frames and corrective actions if necessary. Since the FAA issued AD 2020-06-10, it was determined that certain compliance times need to be reduced. This AD retains the requirements of AD 2020-06-10, with amended compliance times, as specified in a European Union Aviation Safety Agency (EASA) AD, which is proposed for incorporation by reference (IBR). The FAA is issuing this AD to address the unsafe condition on these products.
Except as specified in paragraph (h) of this AD: Comply with all required actions and compliance times specified in, and in accordance with, EASA AD 2023-0009.
(1) Where EASA AD 2023-0009 refers to its effective date, this AD requires using the effective date of this AD.
(2) Where EASA AD 2023-0009 refers to August 1, 2019 (the effective date of EASA AD 2019-0173), this AD requires using May 4, 2020 (the effective date of AD 2020-06-10).
(3) This AD does not adopt the “Remarks” section of EASA AD 2023-0009.
(4) Paragraph (3) of EASA AD 2023-0009 specifies to report inspection results to Airbus within a certain compliance time. For this AD, report inspection results (in case of findings only) at the applicable time specified in paragraph (h)(4)(i) or (ii) of this AD.
(i) If the inspection was done on or after the effective date of this AD: Submit the report within 90 days after the inspection.
(ii) If the inspection was done before the effective date of this AD: Submit the report within 90 days after the effective date of this AD.
(5) Where paragraph (5) of EASA AD 2023-0009 specifies credit for certain actions, this AD provides credit for using the torque values specified in Section 13 of the Airbus technical adaptations (TAs) identified in paragraphs (h)(5)(i) through (vi) of this AD, when installing a certain eccentric referenced in “Airbus SB A320-53-1402 original issue” or “Airbus SB A320-53-1403 original issue,” as specified in the applicable TA, before the effective date of this AD.
(i) Airbus TA 80662272/007/2019, Issue 1, dated August 29, 2019.
(ii) Airbus TA 80662272/008/2019, Issue 1, dated August 29, 2019.
(iii) Airbus TA 80662272/009/2019, Issue 1, dated August 29, 2019.
(iv) Airbus TA 80662272/010/2019, Issue 1, dated August 29, 2019.
(v) Airbus TA 80696258/006/2019, Issue 1, dated October 29, 2019.
(vi) Airbus TA 80696258/007/2019, Issue 1, dated October 29, 2019.
(6) Where Table 1 of EASA AD 2023-0009 specifies configurations, replace the text “post SB” with “post embodiment of SB” and replace the text “pre SB” with “pre embodiment of SB.”
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.
