Airworthiness Directive · Amendment 39-11757 · Airbus Model A319, A320, and A321 Series Airplanes
Airbus Model A319, A320, and A321 Series Airplanes
Model A319, A320, and A321 series airplanes; manufacturer serial numbers through 0875 inclusive; certificated in any category; except those on which Airbus Service Bulletin A320-32-1189, dated December 23, 1998, has been accomplished; and except those on which it can be shown that one of the following conditions has been met (also see NOTE 1):
(1) The main landing gear (MLG) sliding tubes have never been removed from the airplane;
(2) A magnetic particle non-destructive test (NDT2) inspection has never been accomplished on any of the MLG sliding tubes installed on the airplane; or
(3) If an NDT2 inspection has been accomplished on any of the MLG sliding tubes installed on the airplane, it was accomplished only after removal of the attaching hardware and bushings.
Note 1: Operators should note that complete maintenance records for the life of each MLG sliding tube are necessary in order to make a definitive determination of whether any condition specified in the Applicability of the AD has been met.
Note 2: This AD applies to each airplane identified in the preceding applicability provision, regardless of whether it has been otherwise modified, altered, or repaired in the area subject to the requirements of this AD. For airplanes that have been modified, altered, or repaired so that the performance of the requirements of this AD is affected, the owner/operator must request approval for an alternative method of compliance in accordance with paragraph (c) of this AD. The request should include an assessment of the effect of the modification, alteration, or repair on the unsafe condition addressed by this AD; and, if the unsafe condition has not been eliminated, the request should include specific proposed actions to address it.
This amendment adopts a new airworthiness directive (AD), applicable to certain Airbus Model A319, A320, and A321 series airplanes, that requires repetitive inspections of the sliding tube subassembly on the main landing gear (MLG) to detect cracks, and replacement of a cracked subassembly with a new subassembly. This amendment also eventually requires a more extensive, one-time inspection of the same area and corrective actions, if necessary; which terminates the repetitive inspections. This amendment is prompted by issuance of mandatory continuing airworthiness information by a foreign civil airworthiness authority. The actions specified by this AD are intended to prevent cracking of the MLG sliding tube subassembly, which could result in collapse of the MLG.
To prevent cracking of the sliding tube subassembly of the main landing gear (MLG), which could result in collapse of the MLG, accomplish the following:
(a) Within 500 flight hours after the effective date of this AD, perform a detailed visual inspection to detect cracking of the left-hand and right-hand MLG sliding tube subassemblies, in accordance with paragraph 2.B.(1) of the Accomplishment Instructions of Airbus Service Bulletin A320-32-1189, dated December 23, 1998.
(1) If no crack is found, repeat the inspection at intervals not to exceed 500 flight hours, until the requirements of paragraph (b) of this AD have been accomplished.
(2) If any crack is found, prior to further flight, replace the sliding tube subassembly with a new subassembly, in accordance with the service bulletin. Thereafter, repeat the inspection at intervals not to exceed 500 flight hours, until the requirements of paragraph (b) of this AD have been accomplished.
Note 3: For the purposes of this AD, a detailed visual inspection is defined as: “an intensive visual examination of a specific structural area, system, installation, or assembly to detect damage, failure, or irregularity. Available lighting is normally supplemented with a direct source of good lighting at intensity deemed appropriate by the inspector. Inspection aids such as mirror, magnifying lenses, etc., may be used. Surface cleaning and elaborate access procedures may be required.”
(b) Within 15 months after the effective date of this AD: Remove the jacking dome, the stop washer, the jacking dome bushing, and the harness supports; and perform detailed visual inspections to detect discrepancies (including cracking of the left and right MLG sliding tube subassemblies, and overheat damage of the jacking dome bushing), in accordance with paragraph 2.B.(2) of the Accomplishment Instructions of Airbus Service Bulletin A320-32-1189, dated December 23, 1998. Accomplishment of the requirements of this paragraph constitutes terminating action for the requirements of paragraph (a) of this AD.
(1) If no discrepancy is found, prior to further flight, install a new stop washer and jacking dome bushing, in accordance with the service bulletin. No further action is required by this AD.
(2) If any discrepancy is found, prior to further flight, repair in accordance with a method approved by the Manager, International Branch, ANM-116, FAA, Transport Airplane Directorate; or the Direction Ge ne rale de l'Aviation Civile (DGAC) (or its delegated agent). For a repair method to be approved by the Manager, International Branch, ANM-116, as required by this paragraph, the Manager's approval letter must specifically reference this AD.
