Airworthiness Directive · Amendment 39-14123 · Airbus Model A319, A320, and A321 Series Airplanes
Airbus Model A319, A320, and A321 Series Airplanes
Superseded. A later AD replaced this one: AD 2006-11-04. Comply with the one in force.
This AD applies to Airbus Model A319, A320, and A321 series airplanes, certificated in any category; except those on which Airbus Modification 32025 was done during production.
The FAA is adopting a new airworthiness directive (AD) for certain Airbus Model A319, A320, and A321 series airplanes. This AD requires a one-time ultrasonic inspection for certain airplanes, and repetitive detailed inspections for all airplanes, for cracking in the forward lug of the support rib 5 fitting of both main landing gear (MLG), and repair if necessary. This AD also provides for optional terminating actions. This AD is prompted by a report of a crack found in the forward lug of the right-hand MLG rib 5 fitting during greasing of both MLG pintle bearings. We are issuing this AD to find and fix cracking in the forward lug of the MLG, which could result in failure of the lug and consequent collapse of the MLG during 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.
For Model A319 and A320 series airplanes having serial numbers 537 through 625 inclusive: At the earliest of the times specified in paragraphs (f)(1), (f)(2), and (f)(3) of this AD; perform a one-time ultrasonic inspection for cracking in the forward lug of the support rib 5 fitting of the left- and right-hand MLG by doing all the actions specified in the Accomplishment Instructions of Airbus Service Bulletin A320-57A1136, dated January 26, 2005. Repair any cracking before further flight, according to a method approved by either the Manager, International Branch, ANM-116, Transport Airplane Directorate, FAA; or the Direction Générale de l'Aviation Civile (DGAC) (or its delegated agent).
(1) Within 750 flight cycles after the effective date of this AD.
(2) Within 600 flight hours after the effective date of this AD.
(3) Within 100 days after the effective date of this AD.
Perform a detailed inspection for cracking in the forward lug of the support rib 5 fitting of the left- and right-hand MLG at the time specified in paragraph (g)(1) or (g)(2) of this AD, as applicable, and repair any cracking before further flight, according to a method approved by either the Manager, International Branch, ANM-116; or the DGAC (or its delegated agent). Accomplishing the actions specified in the Airbus A318/A319/A320/A321 Non-destructive Testing Manual, Chapter 51-90-00, revision dated February 2003, is one approved method for performing the detailed inspection. Repeat the inspection thereafter at intervals not to exceed 750 flight cycles, 600 flight hours, or 100 days, whichever occurs earliest.
(1) For Model A319 and A320 series airplanes having serial numbers 537 through 625 inclusive: Do the detailed inspection within 100 days after the effective date of this AD or at the earliest of the times specified in paragraphs (g)(1)(i), (g)(1)(ii), and (g)(1)(iii) of this AD, whichever is later.
(i) Within 750 flight cycles after accomplishing the ultrasonic inspection.
(ii) Within 600 flight hours after accomplishing the ultrasonic inspection.
(iii) Within 100 days after accomplishing the ultrasonic inspection.
(2) For all other airplanes: Do the detailed inspection at the earliest of the times specified in paragraphs (g)(2)(i), (g)(2)(ii), and (g)(2)(iii) of this AD.
(i) Within 750 flight cycles after the effective date of this AD.
(ii) Within 600 flight hours after the effective date of this AD.
(iii) Within 100 days after the effective date of this AD.
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.”
Modification of the lugs of the support rib 5 fitting of the left- and right-hand MLG and accomplishment of all related investigative actions and all applicable corrective actions in accordance with Airbus Service Bulletin A320-57-1118, dated September 5, 2002; or Revision 01, dated August 28, 2003; constitutes compliance with the requirements of this AD.
(i) Repair of the forward lugs of the support rib 5 fitting of the left- and right-hand MLG in accordance with Airbus A319 Structural Repair Manual, Chapter 5.C., 57-26-13: Airbus A320 Structural Repair Manual, Chapter 5.D., 57-26-13; and Airbus A321 Structural Repair Manual, Chapter 5.D., all revisions dated November 1, 2004, constitutes compliance with the requirements of this AD.
