Airworthiness Directive · Amendment 39-18366 · Power plant
Airbus Airplanes
This AD applies to the airplanes identified in paragraphs (c)(1) and (c)(2) of this AD, certificated in any category.
(1) Airbus Model A319-113 and A319-114 airplanes, all manufacturer serial numbers.
(2) Airbus Model A320-211 and A320-212 airplanes, all manufacturer serial numbers.
We are adopting a new airworthiness directive (AD) for all Airbus Model A319-113 and A319-114 airplanes; and Model A320-211 and A320-212 airplanes. This AD requires identifying affected engines, and doing a torque check of the forward engine bolts on affected engines. This AD would also require, for any bolt rotation that is found, torqueing the bolt and eventually replacing the forward engine mount bolts, nuts, and washers, doing a fluorescent penetrant inspection and dimensional check of the affected bolt holes for local deformation and cracks, and doing corrective actions if necessary. This AD was prompted by an incorrect torque unit for the CFM56-5A engine forward mount fasteners that was inadvertently introduced into a certain Airbus airplane maintenance manual. We are issuing this AD to prevent loose bolts, which, if combined with induced maintenance damage, could lead to forward engine mount failure. An engine mount failure can result in an engine detachment and consequent reduced control of the airplane, damage to the airplane, and injury to persons on the ground.
Within 2 months after the effective date of this AD, accomplish the actions required by paragraphs (g)(1) and (g)(2) of this AD, as applicable.
(1) Identify each CFM56-5A engine that has been installed on the airplane as specified in A318/A319/A320/A321 Airplane Maintenance Manual (AMM) Task 71-00-00-400-040-A01, “Installation of the Power Plant with Engine Positioner TWW-75E,” of an AMM having a revision date between May 2013 and July 2015 (inclusive). A review of airplane maintenance records is acceptable in lieu of this determination if the date of the AMM revision used for the engine installation can be conclusively determined from that review.
(2) For each engine installation determined to be affected as required by paragraph (g)(1) of this AD, check the torque values applied on the forward engine mount bolts, in accordance with the instructions of paragraph 4.2.2 of Airbus Alert Operators Transmission (AOT) A71N010-15, dated September 30, 2015.
If, during the torque check required by paragraph (g)(2) of this AD, any bolt rotation is detected, accomplish the actions required by paragraphs (h)(1) and (h)(2) of this AD.
(1) Before further flight, torque the affected bolt, in accordance with the instructions of paragraph 4.2.3.1 of Airbus AOT A71N010-15, dated September 30, 2015.
(2) During the next engine removal, replace the forward engine mount bolts, nuts, and washers; accomplish a fluorescent penetrant inspection and dimensional check of the pylon bolt holes of the affected forward engine mount platform for local deformation and cracks; and do all applicable corrective actions; in accordance with the instructions of paragraph 4.2.3.2 of Airbus AOT A71N010-15, dated September 30, 2015. Do all applicable corrective actions before further flight.
As of the effective date of this AD, installation of a CFM56-5A engine on an airplane is permitted, provided that the installation is accomplished using the torque values for forward engine mount bolts specified in paragraph 4.2.3.1 of Airbus AOT A71N010-15, dated September 30, 2015.
Note 1 to paragraph (i) of this AD: Additional guidance for the re-torque can be found in Airbus A318/A319/A320/A321 AMM, Task 71-00-00-400-040-A01, “Installation of the Power Plant with Engine Positioner TWW 75E,” dated August 2015.
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.
