Airworthiness Directive · Amendment 39-13748 · Airbus Model A319-131, -132, and -133; A320-231, -232, and -233; and A321-131 and -231 Series Airplanes
Airbus Model A319-131, -132, and -133; A320-231, -232, and -233; and A321-131 and -231 Series Airplanes
Superseded. A later AD replaced this one: AD 2011-19-01. Comply with the one in force.
This AD applies to Airbus Model A319-131, -132, and -133; A320-231, -232, and -233; and A321-131 and “231 series airplanes; certificated in any category; except those airplanes on which Airbus Modification 32943 has been incorporated in production.
The FAA is adopting a new airworthiness directive (AD) for certain Airbus Model A319-131, -132, and -133; A320-231, -232, and - 233; and A321-131 and -231 series airplanes. This AD requires revising the airplane flight manual (AFM) to advise the flightcrew of procedures associated with the intermittent interruption of the electrical power. Under certain conditions, this AD also requires inspecting for signs of arcing and performing any necessary corrective actions. This AD also provides for optional terminating action for the requirements of the AD. This AD is prompted by reports of fretting and consequent arcing of the electrical harness of the integrated drive generator (IDG) at the pin-to-socket connector at the firewall. We are issuing this AD to prevent transient loss of certain systems and consequent reduced ability of the flightcrew to cope with adverse flight conditions.
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 10 days after the effective date of this AD, revise the Limitations section of the Airbus A318/319/320/321 AFM to include the information in Temporary Revision (TR) 4.02.00/20, dated May 3, 2004. This may be done by inserting a copy of the TR into the AFM. When the TR has been included in general revisions of the AFM, those general revisions may be inserted into the AFM, provided the relevant information in the general revisions is identical to that in the TR.
If an IDG is shut down by the flightcrew in accordance with the TR procedures specified in paragraph (f) of this AD, or if an IDG is shut down automatically, do the actions specified in paragraph (g)(1) or (g)(2) of this AD.
(1) Before further flight, inspect the firewall connector of the affected IDG to detect signs of arcing, in accordance with a method approved by the Manager, International Branch, ANM-116, Transport Airplane Directorate, FAA. If any sign of arcing is detected: Before further flight, either repair the connector or replace the connector with a new connector, in accordance with a method approved by the Manager, International Branch, ANM-116.
(2) Operate the airplane with the affected IDG inoperative in accordance with the provisions and compliance periods specified in the FAA-approved Master Minimum Equipment List. Before further use of the affected IDG, do the actions specified in paragraph (g)(1) of this AD.
Replacement of the IDG harnesses and connectors on both engines in accordance with Airbus Service Bulletin A320-71-1030, dated February 27, 2003, terminates the requirements of this AD.
Note 1: Airbus Service Bulletin A320-71-1030 refers to International Aero Engines Information Bulletin V2500-NAC-70-0736, dated January 28, 2003, as an additional source of information for the harness/connector replacement specified in paragraph (h) of this AD.
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.
Aircraft
