Airworthiness Directive · Amendment 39-18509 · Wings
Airbus Airplanes
Superseded. A later AD replaced this one: AD 2016-12-09. Comply with the one in force.
This AD applies to the airplanes identified in paragraphs (c)(1) and (c)(2) of this AD, certificated in any category, all manufacturer serial numbers, except those on which Airbus Modification (Mod) 55792 or Mod 55306 has been embodied in production, and except those on which Airbus Repair Instruction R57115092 has been embodied in service on both right-hand (RH) and left-hand (LH) sides.
(1) Airbus Model A330-201, -202, -203, -223, -223F, -243 -243F, -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, -200 Freighter, and -300 series airplanes; and Model A340-200 and -300 series airplanes. This AD was prompted by reports that cracks were found on an adjacent hole of certain frames of the center wing box (CWB). This AD requires removing fasteners, doing a rototest inspection of fastener holes, installing new fasteners, oversizing the holes and doing rototest inspections for cracks if necessary, and repairing any cracking that is found. We are issuing this AD to detect and correct cracking on certain holes of certain frames of the CWB that could affect the structural integrity of the airplane.
Do a rototest inspection of the fastener holes at the frame (FR) 40 vertical web, on both sides, as specified in paragraphs (g)(1) through (g)(6) of this AD, except as required by paragraph (k) of this AD.
(1) For Model A330-300 series airplanes in pre-mod 44360 configuration: At the later of the times specified in paragraphs (g)(1)(i) and (g)(1)(ii) of this AD, inspect below the CWB lower panel reference, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A330-57-3114, dated March 12, 2013.
(i) At the applicable time specified in paragraph 1.E., “Compliance” of Airbus Service Bulletin A330-57-3114, dated March 12, 2013.
(ii) Within 2,400 flight cycles or 24 months after the effective date of this AD, whichever occurs first.
(2) For Model A330-200 series airplanes in post-mod 44360 and pre-mod 49202 configuration: At the later of the times specified in paragraphs (g)(2)(i) and (g)(2)(ii) of this AD, inspect below the CWB lower panel reference, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A330-57-3116, dated March 12, 2013.
(i) At the applicable time specified in paragraph 1.E., “Compliance,” of Airbus Service Bulletin A330-57-3116, dated March 12, 2013.
(ii) Within 2,400 flight cycles or 24 months after the effective date of this AD, whichever occurs first.
(3) For Model A330-200 and -300 series airplanes in pre-mod 55306 and pre-mod 55792 configuration: At the later of the times specified in paragraphs (g)(3)(i) and (g)(3)(ii) of this AD, inspect above the CWB lower panel reference, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A330-57-3115, dated April 4, 2013.
(i) At the applicable time specified in paragraph 1.E., “Compliance” of Airbus Service Bulletin A330-57-3115, dated April 4, 2013.
(ii) Within 2,400 flight cycles or 24 months after the effective date of this AD, whichever occurs first.
(4) For Model A340-200 and -300 series airplanes in pre-mod 44360 configuration: At the later of the times specified in paragraphs (g)(4)(i) and (g)(4)(ii) of this AD, inspect below the CWB lower panel reference, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A340-57-4123, dated March 12, 2013.
(i) At the applicable time specified in paragraph 1.E., “Compliance” of Airbus Service Bulletin A330-57-4123, dated March 12, 2013.
(ii) Within 1,300 flight cycles or 24 months after the effective date of this AD, whichever occurs first.
(5) For Model A340-200 and -300 series airplanes in pre-mod 55306 and pre-mod 55792 configuration: At the later of the times specified in paragraphs (g)(5)(i) and (g)(5)(ii) of this AD, inspect above the CWB lower panel reference, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A340-57-4124, Revision 01, dated August 22, 2013.
(i) At the applicable time specified in paragraph 1.E., “Compliance,” of Airbus Service Bulletin A340-57-4124, Revision 01, dated August 22, 2013.
(ii) Within 1,300 flight cycles or 24 months after the effective date of this AD, whichever occurs first.
(6) For Model A340-200 and -300 series airplanes in post-mod 44360 and pre-mod 49202 configuration: At the later of the times specified in paragraphs (g)(6)(i) and (g)(6)(ii) of this AD, inspect below the CWB lower panel reference, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A340-57-4125, dated March 12, 2013.
(i) At the applicable time specified in paragraph 1.E., “Compliance,” of Airbus Service Bulletin A340-57-4125, dated March 12, 2013.
(ii) Within 1,300 flight cycles or 24 months after the effective date of this AD, whichever occurs first.
If no crack is found during any inspection required by paragraph (g) of this AD, do the actions specified in paragraphs (h)(1) and (h)(2) of this AD.
(1) Before further flight, install new fasteners in the transition fit, in accordance with the Accomplishment Instructions of the applicable service information identified in paragraph (g) of this AD.
(2) Repeat the inspection required by paragraph (g) of this AD thereafter at the applicable time identified in paragraph 1.E., “Compliance,” of the applicable service information identified in paragraph (g) of this AD.
If any crack is found during any inspection required by paragraph (g) of this AD: Before further flight, oversize the holes to the first oversize in comparison with the current hole diameter, and do a rototest inspection for cracks, in accordance with the Accomplishment Instructions of the applicable service information identified in paragraph (g) of this AD.
(1) If no cracking is found during the rototest inspection required by paragraph (i) of this AD, do the actions specified in paragraphs (i)(1)(i) and (i)(1)(ii) of this AD.
(i) Before further flight: Install new fasteners in the transition fit, in accordance with the Accomplishment Instructions of the applicable service information identified in paragraph (g) of this AD.
(ii) Repeat the inspection required by paragraph (g) of this AD thereafter at the applicable time identified in paragraph 1.E., “Compliance,” of the applicable service information identified in paragraph (g) of this AD.
(2) If cracking is found during the rototest inspection required by paragraph (i) of 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).
Accomplishment of the initial and repetitive inspections required by this AD terminates accomplishment of Airworthiness Limitation Items Tasks 57-11-04 and 57-11-02 of the Airworthiness Limitation Section (ALS) Part 2, Damage Tolerant Airworthiness Limitation Items (DT ALI).
(1) Installation of new fasteners, as specified in paragraph (h)(1) of this AD, does not terminate the repetitive inspections required by paragraph (g) of this AD.
(2) Accomplishment of the corrective actions specified in the introductory text of paragraph (i) and paragraph (i)(1) of this AD does not terminate the repetitive inspections required by paragraph (g) of this AD.
(3) Accomplishment of the repair specified in paragraph (i)(2) of this AD does not terminate repetitive inspections required by paragraph (g) of this AD, unless the approved repair method specifies otherwise.
(1) If the applicable service information identified in paragraph (g) of this AD specifies contacting Airbus for appropriate action: 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.
(2) Where paragraph 1.E., “Compliance,” of the applicable service information specified in paragraph (g) of this AD specifies a compliance time in terms of a “Threshold” and “Grace Period,” this AD requires compliance at the later of the applicable threshold and grace period.
(3) Where paragraph 1.E., “Compliance,” of the applicable service information specified in paragraph (g) of this AD specifies a threshold as “before next flight,” this AD requires compliance before the next flight after the applicable finding.
