Airworthiness directives › 2018-25-02
AD 2018-25-02 Airworthiness Directives; Airbus SAS Airplanes
Models named: A318-111, -112, -121, -122, A319-111, -113, -114, -115, -131, -132. Read the applicability below — it usually turns on serial or part numbers too.
Applicability*9
This AD applies to all Airbus SAS airplanes identified in paragraphs (c)(1), (c)(2), (c)(3), and (c)(4) of this AD; certificated in any category; with an original certificate of airworthiness or original export certificate of airworthiness issued on or before October 24, 2017. (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, -233, -251N, and -271N airplanes. (4) Model A321-111, -112, -131, -211, -212, -213, -231, -232, -251N, -253N, -271N, and -272N airplanes.
Compliance
Comply with this AD within the compliance times specified, unless already done.
Required actions
(1) Within 90 days after the effective date of this AD, revise the existing maintenance or inspection program, as applicable, to incorporate the airworthiness limitations (ALIs) specified in Airbus A318/A319/A320/A321 Airworthiness Limitation Section Part 2—Damage Tolerant Airworthiness Limitation Items (DT-ALI), Revision 06, dated April 10, 2017; and Airbus A318/A319/A320/A321 Airworthiness Limitation Section Part 2—Damage Tolerant Airworthiness Limitation Items (DT-ALI), Variation 6.3, dated October 24, 2017. Except for ALIs identified in paragraphs (g)(2) and (g)(3) of this AD, the initial compliance time for accomplishing the actions is at the applicable time identified in the ALIs specified in Airbus A318/A319/A320/A321 Airworthiness Limitation Section Part 2—Damage Tolerant Airworthiness Limitation Items (DT-ALI), Revision 06, dated April 10, 2017, and Airbus A318/A319/A320/A321 Airworthiness Limitation Section Part 2—Damage Tolerant Airworthiness Limitation Items (DT-ALI), Variation 6.3, dated October 24, 2017; or within 90 days after the effective date of this AD; whichever occurs later, without exceeding the inspection intervals in the ALIs required by paragraph (i) of AD 2017-22-03. (2) For airplanes identified in Airbus A318/A319/A320/A321 Airworthiness Limitation Section Part 2—Damage Tolerant Airworthiness Limitation Items (DT-ALI), Variation 6.1, dated May 18, 2017: Concurrently with the revision required by paragraph (g)(1) of this AD, revise the existing maintenance or inspection program, as applicable, to incorporate the ALIs specified in Airbus A318/A319/A320/A321 Airworthiness Limitation Section Part 2—Damage Tolerant Airworthiness Limitation Items (DT-ALI), Variation 6.1, dated May 18, 2017. The initial compliance time for accomplishing the actions is at the applicable time identified in the ALIs specified in Airbus A318/A319/A320/A321 Airworthiness Limitation Section Part 2—Damage Tolerant Airworthiness Limitation Items (DT-ALI), Variation 6.1, dated May 18, 2017; or within 90 days after the effective date of this AD; whichever occurs later, without exceeding the inspection intervals in the ALIs required by paragraph (i) of AD 2017-22-03. (3) For airplanes identified in Airbus A318/A319/A320/A321 Airworthiness Limitation Section Part 2—Damage Tolerant Airworthiness Limitation Items (DT-ALI), Variation 6.2, dated May 24, 2017: Concurrently with the revision required by paragraph (g)(1) of this AD, revise the existing maintenance or inspection program, as applicable, to incorporate the ALIs specified in Airbus A318/A319/A320/A321 Airworthiness Limitation Section Part 2—Damage Tolerant Airworthiness Limitation Items (DT-ALI), Variation 6.2, dated May 24, 2017. The initial compliance time for accomplishing the actions is at the applicable time identified in the ALIs specified in Airbus A318/A319/A320/A321 Airworthiness Limitation Section Part 2—Damage Tolerant Airworthiness Limitation Items (DT-ALI), Variation 6.2, dated May 24, 2017; or within 90 days after the effective date of this AD; whichever occurs later, without exceeding the inspection intervals in the ALIs required by paragraph (i) of AD 2017-22-03.
Unsafe condition
This AD was prompted by an evaluation by the design approval holder, which indicates that principal structural elements and certain life-limited parts are subject to widespread fatigue damage (WFD). We are issuing this AD to prevent fatigue cracking, accidental damage, or corrosion in principal structural elements, and WFD, which could result in reduced structural integrity of the airplane.
Affected ADs
This AD affects AD 2017-22-03, Amendment 39-19083 (82 FR 49091, October 24, 2017) (“AD 2017-22-03”).
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The directive text above is reproduced from the Federal Register, a work of the United States government and in the public domain. The separation into applicability, compliance and required actions is TrackAD's.*1