Airworthiness Directive · Amendment 39-18906 · Engine exhaust
Airbus Airplanes
This AD applies to the Airbus airplanes, certificated in any category, identified in paragraphs (c)(1) through (c)(4) of this AD, all manufacturer serial numbers.
(1) Airbus Model A318-111 and -112 airplanes.
(2) Airbus Model A319-111, -112, -113, -114, and -115 airplanes.
(3) Airbus Model A320-211, -212, and -214 airplanes.
(4) Airbus Model A321-111, -112, -211, -212, and -213 airplanes.
We are adopting a new airworthiness directive (AD) for all Airbus Model A318-111 and -112 airplanes; Model A319-111, -112, -113, - 114, and -115 airplanes; Model A320-211, -212, and -214 airplanes; and Model A321-111, -112, -211, -212, and -213 airplanes. This AD was prompted by reports of cracks in certain pivot fittings of a CFM56 engine's thrust reverser (T/R). This AD requires repetitive inspections for cracking and corrosion of certain pivot fittings of a CFM56 engine's T/R, and corrective actions if necessary. We are issuing this AD to address the unsafe condition on these products.
At the applicable compliance time specified in paragraph (h) of this AD: Do a high frequency eddy current (HFEC) inspection for cracking and corrosion of each T/R pivot fitting specified in paragraphs (g)(1) and (g)(2) of this AD, and do all applicable corrective actions, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A320-70-1003, Revision 01, dated December 28, 2015; and Goodrich Aerostructures Service Bulletin RA32078-137, Rev. 3, dated March 14, 2016; as applicable; except as required by paragraph (i) of this AD. Do all applicable corrective actions before further flight. Repeat the inspection of the T/R pivot fittings thereafter at intervals not to exceed 60 months or 12,000 flight cycles, whichever occurs first.
(1) The 3 o'clock position T/R pivot fittings having part numbers (P/N) that are provided in paragraphs (g)(1)(i) through (g)(1)(iv) of this AD.
(i) P/N 321-200-850-6.
(ii) P/N 321-200-851-6.
(iii) P/N 321-200-852-6.
(iv) P/N 321-200-853-6.
(2) The 9 o'clock position T/R pivot fittings having P/Ns that are provided in paragraphs (g)(2)(i) through (g)(2)(iv) of this AD.
(i) P/N 321-200-800-6.
(ii) P/N 321-200-801-6.
(iii) P/N 321-200-802-6.
(iv) P/N 321-200-803-6.
At the later of the times specified in paragraphs (h)(1) and (h)(2) of this AD, do the initial inspection specified in paragraph (g) of this AD. If maintenance records cannot conclusively determine the T/R flight cycles accumulated since first installation, or the time since new, do the initial inspection required by paragraph (g) of this AD at the compliance time specified in paragraph (h)(2) of this AD.
(1) Before exceeding 10 years or 24,000 total flight cycles accumulated by the T/R, whichever occurs first since first installation on an airplane.
(2) Within 36 months or 7,200 flight cycles accumulated by the T/R, whichever occurs first after the effective date of this AD.
(1) If any crack is found during any inspection required by this AD: Before further flight, repair using a method approved by the Manager, International Branch, ANM-116, Transport Airplane Directorate, FAA; or the European Aviation Safety Agency (EASA); or Airbus's EASA Design Organization Approval (DOA).
(2) If any corrosion is found during any inspection required by this AD and Goodrich Aerostructures Service Bulletin RA32078-137, Rev. 3, dated March 14, 2016, specifies obtaining a damage disposition from Goodrich Aerostructures: Before further flight, repair using a method approved by the Manager, International Branch, ANM-116, Transport Airplane Directorate, FAA; or the EASA; or Airbus's EASA DOA.
(3) Dispatch of an airplane equipped with a T/R pivot fitting(s) having a part number identified in paragraph (g)(1) or (g)(2) of this AD, as specified in Master Minimum Equipment List (MMEL) 78-30-01 (deactivation of the affected T/Rs), is permitted provided the limitations specified in MMEL 78-30-01 have been followed.
As of the effective date of this AD, no person may install on any airplane a T/R pivot fitting having a part number specified in paragraph (g)(1) or (g)(2) of this AD, unless it is determined, prior to installation, that the T/R pivot fitting has accumulated less than 10 years and fewer than 24,000 total flight cycles since its first installation on an airplane, or less than 60 months and fewer than 12,000 flight cycles after having passed an inspection, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A320-70-1003, Revision 01, dated December 28, 2015; and Goodrich Aerostructures Service Bulletin RA32078-137, Rev. 3, dated March 14, 2016.
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.
