Airworthiness Directive · Amendment 39-14532 · Airbus Model A319-131, -132, and -133; A320-232 and -233; and A321-131, -231, and -232 Airplanes
Airbus Model A319-131, -132, and -133; A320-232 and -233; and A321-131, -231, and -232 Airplanes
This AD applies to Airbus Model A319-131, -132, and -133 airplanes; Model A320-232 and -233 airplanes; and Model A321-131, -231, and -232 airplanes; certificated in any category; as identified in Airbus All Operators Telex (AOT) A320-71A1036, Revision 1, dated June 28, 2005.
The FAA is adopting a new airworthiness directive (AD) for certain Airbus Model A319-131, -132, and -133; A320-232 and -233; and A321-131, -231, and -232 airplanes. This AD requires inspecting for cracks or failure of the primary load path components of the engine forward mount, and corrective action if necessary. This AD also requires removing, re-installing, and re-torquing the attachment bolts for the secondary load path. This AD results from a report that, during modification of certain engine forward mount assemblies of the left and right engines done at an engine shop visit, an incorrect torque was applied to the attachment bolts. We are issuing this AD to prevent structural failure of the secondary load path of the forward engine mount, which, if combined with failure of the primary load path, could result in separation of the engine from the airplane.
You are responsible for having the actions required by this AD performed within the compliance times specified, unless the actions have already been done.
Note 1: For the purposes of this AD, a detailed inspection is: “An intensive examination of a specific item, installation, or assembly to detect damage, failure, or irregularity. Available lighting is normally supplemented with a direct source of good lighting at an intensity deemed appropriate. Inspection aids such as mirror, magnifying lenses, etc., may be necessary. Surface cleaning and elaborate procedures may be required.”
Perform a detailed inspection for cracks or failure of the primary load path components of the engine forward mount by doing all the applicable actions in accordance with the procedures in Airbus AOT A320-71A1036, Revision 1, dated June 28, 2005. Perform the actions at the time specified in paragraph (f)(1), (f)(2), or (f)(3) of this AD, as applicable. Do any corrective action before further flight in accordance with the procedures in the AOT.
(1) For Model A321-131, -231, and -232 airplanes: Do the inspection within 5 days after the effective date of this AD.
(2) For Model A319-131, -132, and -133 airplanes: Do the inspection within 10 days after the effective date of this AD.
(3) For Model A320-232 and -233 airplanes: Do the inspection within 10 days after the effective date of this AD.
(g) For all airplanes: At the applicable time specified in paragraph (g)(1) or (g)(2) of this AD, remove, re-install, and re-torque each of the attachment bolts of the engine forward mount assembly in accordance with the procedures in Airbus AOT A320-71A1036, Revision 1, dated June 28, 2005.
(1) If the inspection specified in paragraph (f) of this AD was accomplished after the effective date of this AD: Do the actions within 2,250 flight cycles after accomplishing the inspection.
(2) If the inspection specified in paragraph (f) of this AD was accomplished before the effective date of this AD: Do the actions within 2,250 flight cycles after the effective date of this AD.
Inspections, adjustments or repairs done before the effective date of this AD in accordance with the procedures in Airbus AOT A320-71A1036, dated June 27, 2005, are acceptable for compliance with the corresponding actions required by this AD.
(i) Although Airbus AOT A320-71A1036, Revision 1, dated June 28, 2005, recommends that inspection results be reported to the manufacturer, this AD does not include that requirement.
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.
