Airworthiness Directive · Amendment 39-18679 · Fuselage
Airbus Airplanes
This AD applies to the airplanes identified in paragraphs (c)(1) and (c)(2) of this AD, certificated in any category, manufacturer serial numbers (MSNs) 1 through 1,600 inclusive.
(1) Airbus Model A330-201, -202, -203, -223, -243, -301, -302, -303, -321, -322, -323, -341, -342, and -343 airplanes.
(2) Airbus Model A340-211, -212, -213, -311, -312, and -313 airplanes.
We are adopting a new airworthiness directive (AD) for certain Airbus Model A330-200 and -300 series airplanes; and Model A340-200 and -300 series airplanes. This AD was prompted by a determination that the compliance times for certain post-repair inspections and certain allowable damage limits (ADLs) must be reduced in order to address fatigue. This AD requires identifying any repairs and ADLs used to assess or control any structural damage on certain structural areas, and corrective action if necessary. We are issuing this AD to prevent fatigue damage on primary structure and structural repairs, which could result in reduced structural integrity of the airplane.
(1) At the applicable times in paragraphs (g)(1)(i) through (g)(1)(x) of this AD, review the airplane maintenance records to identify any structural repair manual (SRM) ADLs used to assess or control any structural damage or any structural repair accomplished as specified in an SRM, as applicable, that have been applied on the applicable areas as specified in paragraphs (g)(2)(i) through (g)(2)(iv) of this AD. If the review of the airplane maintenance records is inconclusive or the records are unavailable, inspect the airplane to identify any SRM ADL used to assess or control any structural damage or any structural repair accomplished in accordance with a SRM, as applicable, using a method approved by Manager, International Branch, ANM-116, Transport Airplane Directorate, FAA; or the European Aviation Safety Agency (EASA); or Airbus's EASA Design Organization Approval (DOA).
(i) For Model A330-200 pre-mod 49144 airplanes, with left-hand (LH) and right-hand (RH) mid passenger (PAX) door surround panels, as specified in Airbus Service Bulletin A330-53-3232, dated November 4, 2014: Within 12 months after the effective date of this AD.
(ii) For Model A330-200 pre-mod 49144 airplanes, with forward cargo door, emergency exit door/PAX door 3, aft cargo door, bulk cargo door, and aft PAX door surround panels; as specified in Airbus Service Bulletin A330-53-3232, dated November 4, 2014: Within 24 months after the effective date of this AD.
(iii) For Model A330-300 pre-mod 49144 airplanes and Model A340-200 and -300 pre-mod 49144 airplanes, with mid PAX door surround panels, forward cargo door, emergency exit door/PAX door 3, aft cargo door, bulk cargo door, and aft PAX door surround panels; as specified in Airbus Service Bulletin A330-53-3232, dated November 4, 2014; or Airbus Service Bulletin A340-53-4222, dated November 25, 2014; as applicable: Within 24 months after the effective date of this AD.
(iv) For Model A330-201, -202, -203, -223, -243, -301, -302, -303, -321, -322, -323, -341, -342, and -343 and Model A340-211, -212, -213, -311, -312, and -313, all post-mod 40347 airplanes, with forward PAX door surround panels with an ADL with a temporary life limit; as specified in Airbus Service Bulletin A330-53-3233, dated September 26, 2014; or Airbus Service Bulletin A340-53-4223, dated September 26, 2014; as applicable: Within 12 months after the effective date of this AD.
(v) For Model A330-201, -202, -203, -223, -243, -301, -302, -303, -321, -322, -323, -341, -342, and -343 and Model A340-211, -212, -213, -311, -312, and -313, all post-mod 40347 airplanes, with forward PAX door surround panels with an ADL with a Permanent Acceptance; as specified in Airbus Service Bulletin A330-53-3233, dated September 26, 2014; or Airbus Service Bulletin A340-53-4223, dated September 26, 2014; as applicable: Within 24 months after the effective date of this AD.
(vi) For Model A330-201, -202, -203, -223, -243, -301, -302, -303, -321, -322, -323, -341, -342, and -343 airplanes and Model A340-211, -212, -213, -311, -312, and -313 airplanes; stringer 9 junction between frame (FR) 10 and FR13; as specified in Airbus Service Bulletin A330-53-3235, Revision 01, dated January 14, 2015; or Airbus Service Bulletin A340-53-4225, Revision 01, dated January 14, 2015; as applicable: Within 12 months after the effective date of this AD.
(vii) For Model A340-200 and -300 Weight Variant (WV)00s airplanes; forward and rear fuselage; as specified in Airbus Service Bulletin A340-53-4224, dated December 15, 2014: Within 12 months after the effective date of this AD.
(viii) For Model A340-200 and -300 WV00s airplanes; nose forward and center fuselage; as specified in Airbus Service Bulletin A340-53-4224, dated December 15, 2014: Within 24 months after the effective date of this AD.
(ix) For Model A330-200 and -300 pre-mod 49144 airplanes, and Model A340-200 and -300 WV20s airplanes; forward and rear fuselage, nose forward and center fuselage; as specified in Airbus Service Bulletin A330-53-3234, dated December 8, 2014; or Airbus Service Bulletin A340-53-4224, dated December 15, 2014; as applicable: Within 24 months after the effective date of this AD.
(x) For Model A330-200 and -300 post-mod 49144 airplanes and Model A340-200 and -300 post-mod 49144 airplanes; nose forward and center fuselage; as specified in Airbus Service Bulletin A330-53-3234, dated December 8, 2014; or Airbus Service Bulletin A340-53-4224, dated December 15, 2014; as applicable: Within 24 months after the effective date of this AD.
(2) Applicable areas (on both LH and RH sides) are identified in paragraphs (g)(2)(i) through (g)(2)(iv) of this AD.
(i) Door cut-out corners of door surrounding panels (forward cargo door, mid PAX door, emergency exit door/PAX door 3, aft cargo door, bulk cargo door, aft PAX door), as specified in Airbus Service Bulletin A330-53-3232, dated November 4, 2014; or Airbus Service Bulletin A340-53-4222, dated November 25, 2014; as applicable.
(ii) Forward PAX door surround panels, as specified in Airbus Service Bulletin A330-53-3233, dated September 26, 2014; or Airbus Service Bulletin A340-53-4223, dated September 26, 2014; as applicable.
(iii) Fuselage skin doubler repairs, as specified in Airbus Service Bulletin A330-53-3234, dated December 8, 2014; or Airbus Service Bulletin A340-53-4224, dated December 15, 2014; as applicable.
(iv) Stringer 9 junction between FR10 and FR13, as specified in Airbus Service Bulletin A330-53-3235, Revision 01, dated January 14, 2015; or Airbus Service Bulletin A340-53-4225, Revision 01, dated January 14, 2015; as applicable.
If, during any review or inspection required by paragraph (g)(1) of this AD, it is determined that an SRM ADL was used on an area specified in paragraphs (g)(2)(i) through (g)(2)(iv) of this AD to assess or control any structural damage, or any structural repair of an area specified in paragraphs (g)(2)(i) through (g)(2)(iv) of this AD was accomplished as specified in the instructions of the applicable SRM revision dated before April 2013 or SRM temporary revision (TR) dated before November 28, 2014: Within the applicable compliance time specified in paragraphs (g)(1)(i) through (g)(1)(x) of this AD, do the actions specified in paragraphs (h)(1) or (h)(2) of this AD, as applicable.
(1) Revise the maintenance or inspection program, as applicable, with the applicable revised thresholds and intervals for the identified structural repairs embodied on the airplane, and accomplish all updated inspections, in accordance with the Accomplishment Instructions of the applicable service information identified in paragraphs (g)(2)(i) through (g)(2)(iv) of this AD, except as required by paragraphs (h)(1)(i) and (h)(1)(ii) of this AD.
(i) Where the applicable service information identified in paragraphs (g)(2)(i) through (g)(2)(iv) of this AD specifies to contact Airbus for specific assessment, revise the maintenance or inspection program and accomplish all updated inspections, as applicable, using a method approved by the Manager, International Branch, ANM-116, Transport Airplane Directorate, FAA; or EASA; or Airbus's EASA DOA.
(ii) Where the applicable service information identified in paragraphs (g)(2)(i) through (g)(2)(iv) of this AD specifies “current SRM,” no SRM revision dated before April 2013 or SRM TR dated before November 28, 2014, is considered a “current SRM.”
(2) For any repair that was previously allowed in any revision of the Airbus A330 or A340 SRM, as applicable, dated before April 2013; or in any SRM TR dated before November 28, 2014, to the applicable SRM, and is no longer allowed by the applicable SRM revision dated on or after April 2013: Make an assessment using a method approved by the Manager, International Branch, ANM-116, Transport Airplane Directorate, FAA; or the EASA; or Airbus's EASA DOA; and perform necessary corrective actions at the applicable times identified therein.
As of the effective date of this AD, for any structural damage in the areas identified in paragraphs (g)(2)(i) through (g)(2)(iv) of this AD that has exceeded the ADL, no repair or replacement may be done using an Airbus A330 or A340 SRM dated before April 2013, or any Airbus A330 or A340 SRM TR dated before November 28, 2014.
