Airworthiness Directive · Amendment 39-14379 · Airbus Model A340-200 and A340-300 Series Airplanes
Airbus Model A340-200 and A340-300 Series Airplanes
This AD applies to all Airbus Model A340-211, -212, and -213 and A340-311, -312, and -313 airplanes, certificated in any category.
The FAA is adopting a new airworthiness directive (AD) for all Airbus Model A340-200 and A340-300 series airplanes. This AD requires repetitive inspections for cracking of the junction between the thrust reverser forward frame and the 12 o'clock and 6 o'clock beams; the thrust reverser common fittings; and the thrust reverser J-ring structure at the 12 o'clock and 6 o'clock positions; and related investigative and corrective actions. This AD results from fatigue and damage tolerance testing of the engine thrust reversers which revealed fatigue cracking of the junction between the thrust reverser forward frame and the 12 o'clock beam, and of the thrust reverser J-ring structure. We are issuing this AD to detect and correct such fatigue cracking, which could result in rupture of the J-ring, forward frame, or common fittings; loss of the thrust reverser system; or inadvertent deployment of a thrust reverser in flight and consequent reduced controllability of the airplane.
You are responsible for having the actions required by this AD performed within the compliance times specified, unless the actions have already been done.
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.”
Accomplish detailed and eddy current inspections for cracking of the junction between the thrust reverser forward frame and the 12 o'clock and 6 o'clock beams, and the thrust reverser common fittings, and related investigative and corrective actions, by doing all the actions in accordance with the Accomplishment Instructions of Airbus Service Bulletin A340-78-4028, Revision 01, dated October 23, 2003. Except, if damage is found on the common fittings, repair the damage using a method approved by the Manager, International Branch, ANM-116, Transport Airplane Directorate, FAA. Do the inspections at the later of the times specified in paragraphs (f)(1) and (f)(2) of this AD. Do any related investigative and corrective actions before further flight in accordance with the service bulletin. Repeat the inspections thereafter at intervals not to exceed 4,500 flight cycles on the thrust reverser.
(1) For thrust reversers that have accumulated fewer than 4,500 total flight cycles since new as of the effective date of this AD: Before the accumulation of 4,500 total flight cycles on the thrust reverser since new, or within 2,166 flight cycles after the effective date of this AD, whichever is later.
(2) For thrust reversers that have accumulated 4,500 or more total flight cycles since new as of the effective date of this AD: Before the accumulation of 6,666 total flight cycles on the thrust reverser since new or within 6 months after the effective date of this AD, whichever is later.
Note 2: Airbus Service Bulletin A340-78-4028, Revision 01, dated October 23, 2003, references Rohr Service Bulletin RA34078-71, Revision 1, dated February 7, 2003, as an additional source of service information for accomplishing the applicable actions in paragraph (f) of this AD.
(g) At the later of the times specified in paragraphs (g)(1) and (g)(2) of this AD: Accomplish an eddy current inspection for cracking of the J-ring structure at the 12 o'clock and 6 o'clock positions by doing all the applicable actions in accordance with CFM International CFM56-5C Alert Service Bulletin 78-A0072, Revision 2, dated January 27, 2004, including Rohr Alert Service Bulletin RA340A78-72, Revision 2, dated January 27, 2004. If no cracking is found: Repeat the inspection thereafter at intervals not to exceed 800 flight hours or 175 flight cycles on the thrust reverser, whichever is first.
(1) Before the accumulation of 3,000 total flight cycles on any thrust reverser since new.
(2) Within 800 flight hours or 175 flight cycles after the effective date of this AD, whichever is first.
(h) If any cracking is found at the 12 o'clock position, before further flight, do the actions required by either paragraph (h)(1) or (h)(2) of this AD.
(1) Replace the thrust reverser by doing all the applicable actions in accordance with CFM International CFM56-5C Alert Service Bulletin 78-A0072, Revision 2, dated January 27, 2004, including Rohr Alert Service Bulletin RA340A78-72, Revision 2, dated January 27, 2004.
(2) Modify the J-ring and replace the 12 o'clock fitting by doing all the applicable actions in accordance with CFM International CFM56-5C Alert Service Bulletin 78-A0073, Revision 1, dated January 27, 2004, including Rohr Alert Service Bulletin RA340A78-73, Revision 1, dated January 27, 2004. Except, if any cracking is found on machined parts, repair the damage using a method approved by the Manager, International Branch, ANM-116. Repeat the inspection of the 6 o'clock position only at the time specified in paragraph (g) of this AD.
(i) If cracking is found at the 6 o'clock position: Before further flight, replace the thrust reverser by doing all the applicable actions in accordance with CFM International CFM56-5C Alert Service Bulletin 78-A0072, Revision 2, dated January 27, 2004, including Rohr Alert Service Bulletin RA340A78-72, Revision 2, dated January 27, 2004.
Although Airbus Service Bulletin A340-78-4028, Revision 01, dated October 23, 2003; and CFM International CFM56-5C Alert Service Bulletin 78-A0072, Revision 2, dated January 27, 2004, specify reporting the replacement of any thrust reverser to Airbus or CFM, this AD does not include that requirement.
