Airworthiness Directive · Amendment 39-18504 · Periodic inspections
Airbus Airplanes
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.
We are adopting a new airworthiness directive (AD) for all Airbus Model A318-111 and -112 airplanes; Model A319-111, -112, -113, - 114, and -115 airplanes; Model A320-211, -212, and -214 airplanes; and Model A321-111, -112, -211, -212, and -213 airplanes. This AD was prompted by the results of an evaluation by the design approval holder (DAH). 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. This AD requires repetitive detailed inspections of the right and left forward engine mounts, and corrective action if necessary. These inspections are required by AD 2015-05-02. This AD reduces the compliance times for those inspections. 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.
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.
If any discrepancy (cracking) is found during any inspection required by paragraph (g) of this AD: Before further flight, replace the affected forward engine mount with a serviceable part, using a method approved by the Manager, International Branch, ANM-116, Transport Airplane Directorate, FAA; or the European Aviation Safety Agency (EASA); or Airbus's EASA Design Organization Approval (DOA).
Replacement of a forward engine mount does not constitute terminating action for the repetitive inspections required by paragraph (g) of this AD.
Accomplishment of the inspections required by paragraph (g) of this AD terminates the initial and repetitive inspections specified in paragraph (n)(2) of AD 2015-05-02, for Airbus Airworthiness Limitation Tasks 712111-01-1, 712111-01-2, 712111-01-3, and 712111-01-4, “Detailed Inspection of Forward Engine Mount Installation.”
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.
