Airworthiness Directive · Amendment 39-15456 · Airbus Model A318, A319, A320, and A321 Airplanes
Airbus Model A318, A319, A320, and A321 Airplanes
Superseded. A later AD replaced this one: AD 2013-26-14. Comply with the one in force.
This AD applies to Airbus Model A318, A319, A320, and A321 airplanes, certificated in any category, except airplanes on which Airbus Modification 32025 has been accomplished in production.
The FAA is superseding an existing airworthiness directive (AD), which applies to certain Airbus Model A318, A319, A320, and A321 airplanes. That AD currently requires repetitive inspections for cracking in the forward lug of the support rib 5 fitting of both main landing gear (MLG), and repair if necessary. The existing AD also provides optional terminating actions for certain airplanes, as well as other optional methods for complying with the inspection requirements of the existing AD. This new AD continues to require repetitive inspections for cracking in the forward lug of the support rib 5 fitting of the left and right MLG at new repetitive intervals in accordance with new service information, and repair or replacement of any cracked MLG fitting if necessary. This new AD also requires modification of the rib bushings of the left and right MLG, which would end the repetitive inspections. This AD results from cracks found in the forward lug of the MLG support rib 5 fitting. We are issuing this AD to prevent cracking in the forward lug of the MLG, which could result in failure of the lug and consequent collapse of the MLG during takeoff or landing.
You are responsible for having the actions required by this AD performed within the compliance times specified, unless the actions have already been done.
Within 8 days after June 7, 2006 (the effective date of AD 2006-11-04), or before further flight after a hard landing, whichever is first: Perform a detailed inspection for cracking in the forward lug of the support rib 5 fitting of the left- and right-hand MLG, and, if any crack is found, replace the MLG fitting with a new fitting before further flight, in accordance with a method approved by either the Manager, International Branch, ANM-116, FAA; or the European Aviation Safety Agency (EASA) (or its delegated agent). Accomplishing the actions specified in the Airbus A318/A319/A320/A321 Nondestructive Testing Manual, Chapter 51-90-00, Revision dated February 1, 2003, is one approved method for performing the detailed inspection. Repeat the inspection thereafter at intervals not to exceed 8 days, or before further flight after a hard landing, whichever is first. As of the effective date of this AD, the repetitive inspections required by paragraph (i) of this AD must be accomplished in lieu of the repetitive inspections required by this paragraph.
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.”
Performing an ultrasonic inspection for cracking in the forward lug of the support rib 5 fitting of the left- and right-hand MLG in accordance with a method approved by the Manager, International Branch, ANM-116; or the EASA (or its delegated agent; is an acceptable alternative method of compliance for the initial and repetitive inspections required by paragraph (f) of this AD. Doing the actions specified in the Airbus A318/A319/A320/A321 Nondestructive Testing Manual, Chapter 57-29-03, Revision dated February 1, 2005 (for Model A318, A319, and A320 airplanes), or Chapter 57-29-04, Revision dated May 1, 2005 (for Model A321 airplanes), as applicable, is one approved method for performing the ultrasonic inspection.
For Model A319, A320, and A321 airplanes: Repair of the forward lugs of the support rib 5 fitting of the left- and right-hand MLG in accordance with a method approved by the Manager, International Branch, ANM-116; or the EASA (or its delegated agent); constitutes terminating action for the requirements of this AD. Doing the repair in accordance with Airbus A319 Structural Repair Manual (SRM), Chapter 5.C., 57-26-13, Revision dated November 1, 2004; Airbus A320 SRM, Chapter 5.D., 57-26-13, Revision dated November 1, 2004; or Airbus A321 SRM, Chapter 5.D., 57-26-13, Revision dated February 1, 2005; as applicable; is one approved method.
(i) At the applicable time specified in Table 1 of this AD, or before further flight after a hard landing, whichever is first: Do a visual inspection or ultrasonic inspection for cracking in the forward lug of the support rib 5 fitting of the left and right MLG, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A320-57-1138, Revision 01, dated October 27, 2006. Repeat the inspection thereafter at the applicable interval specified in Table 1 of this AD or before further flight after a hard landing, whichever is first, until the modification required by paragraph (k) of this AD has been accomplished. Accomplishing the initial inspection terminates the requirements of paragraph (f) of this AD.
| Airplanes | Initial inspection | Repetitive interval |
|---|---|---|
| Model A318, A319, and A320 airplanes | If the most recent inspection is a detailed inspection done in accordance with paragraph (f) of this AD, inspect within 150 flight cycles after the most recent detailed inspection | Within 150 flight cycles after a visual inspection. |
| If the most recent inspection is an ultrasonic inspection done in accordance with paragraph (g) of this AD, inspect within 940 flight cycles after the most recent ultrasonic inspection | Within 940 flight cycles after an ultrasonic inspection. | |
| Model A321 airplanes | If the most recent inspection is a detailed inspection done in accordance with paragraph (f) of this AD, inspect within 100 flight cycles after the most recent detailed inspection | Within 100 flight cycles after a visual inspection. |
| If the most recent inspection is an ultrasonic inspection done in accordance with paragraph (g) of this AD, inspect within 630 flight cycles after the most recent ultrasonic inspection | Within 630 flight cycles after an ultrasonic inspection. |
If any cracking is found during any inspection required by paragraph (i) of this AD: Before further flight, repair or replace the cracked MLG fitting using a method approved by either the Manager, International Branch, ANM-116, Transport Airplane Directorate, FAA, or the EASA (or its delegated agent).
Within 60 months after the effective date of this AD, modify the rib bushings of the left and right MLG, by accomplishing all of the applicable actions specified in the Accomplishment Instructions of Airbus Service Bulletin A320-57-1118, Revision 03, dated April 23, 2007. Accomplishing the modification terminates the requirements of this AD.
For Model A319, A320, and A321 airplanes, modifying the lugs of the support rib 5 fitting of the left and right MLG is acceptable for compliance with the requirements of paragraph (k) of this AD if done before the effective date of this AD in accordance with one of the following service bulletins: Airbus Service Bulletin A320-57-1118, dated September 5, 2002; Revision 01, dated August 28, 2003; or Revision 02, dated August 2, 2006.
