Airworthiness directives › 2016-09-06
AD 2016-09-06 Airworthiness Directives; Airbus Airplanes
Models named: A318-111, -112, A319-111, -113, -114, -115, A320-211, -212, -214, A321-111. Read the applicability below — it usually turns on serial or part numbers too.
Applicability*9
This AD applies to all Airbus airplanes, certificated in any category, identified in paragraphs (c)(1), (c)(2), (c)(3), and (c)(4) of this AD. (1) Model A318-111 and -112 airplanes. (2) Model A319-111, -112, -113, -114, and -115 airplanes. (3) Model A320-211, -212, and -214 airplanes. (4) Model A321-111, -112, -211, -212, and -213 airplanes.
Compliance
Comply with this AD within the compliance times specified, unless already done.
Required actions
At the latest of the times specified in paragraphs (g)(1), (g)(2), and (g)(3) of this AD: Do a detailed inspection of the left and right forward engine mounts for discrepancies (cracking), using a method approved by the Manager, International Branch, ANM-116, Transport Airplane Directorate, FAA. Repeat the inspection thereafter at intervals not to exceed 800 flight cycles. Note 1 to paragraphs (g) and (h) of this AD: Guidance for the inspection and engine mount replacement can be found in Task 712111-210-040 of the Airbus A318/A319/A320/A321 Maintenance Manual. (1) Within 800 flight cycles since the first flight of the airplane. (2) Within 800 flight cycles since the most recent detailed inspection specified in Airbus Airworthiness Limitation Tasks 712111-01-1, 712111-01-2, 712111-01-3, or 712111-01-4, “Detailed Inspection of Forward Engine Mount Installation,” as applicable. (3) Within 800 flight cycles after the effective date of this AD.
Unsafe condition
This AD was prompted by the results of an evaluation by the design approval holder. During a residual fatigue test the forward engine mount failed prior to reaching the threshold/interval for the detailed inspections of the forward engine mounts specified in the airworthiness limitations. We are issuing this AD to detect and correct fatigue cracking in the forward engine mounts. Such cracking could result in reduced structural integrity of the airplane and could lead to in-flight loss of an engine, possibly resulting in reduced controllability of the airplane.
Affected ADs
This AD affects AD 2015-05-02, Amendment 39-18112 (80 FR 15152, March 23, 2015) (“AD 2015-05-02”).
Read the original on the Federal Register →
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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