Airworthiness directives › 2010-04-10
AD 2010-04-10 Airworthiness Directives; Airbus Model A380-841, -842, and -861 Airplanes
Models named: A380-841, -842, -861. Read the applicability below — it usually turns on serial or part numbers too.
Applicability*9
This AD applies to Airbus Model A380-841, -842, and -861 airplanes, certificated in any category, all serial numbers, except airplanes on which Airbus modification 68729 has been done in production.
Compliance
Unless already done, do the following actions. (1) At the applicable time specified in paragraph (f)(1)(i) or (f)(1)(ii) of this AD for the left- and right-hand MFTF#6, do a special detailed (ultrasonic and high-frequency eddy current) inspection of the filet radii of pivot supports, monolithic carbon fibre reinforced plastic structures, and radii of the U-frame, for cracking and delamination in accordance with the Accomplishment Instructions of Airbus Service Bulletin A380-57-8014, dated November 21, 2008; or Airbus Mandatory Service Bulletin A380-57-8014, Revision 01, dated June 5, 2009. After the effective date of this AD, use only Revision 01. (i) For Airbus Model A380-841 and -842 airplanes: Before the MFTF#6 has accumulated 500 total flight cycles since its first installation on an airplane, or within 30 flight hours after May 28, 2009 (the effective date of AD 2009-10-07), whichever occurs later. (ii) For Model A380-861 airplanes: Before the MFTF#6 has accumulated 100 total flight cycles since its first installation on an airplane, or within 30 flight hours after May 28, 2009, whichever occurs later. (2) If no cracking and no delamination are found during any inspection required by paragraph (f)(1) of this AD, repeat the inspections required by paragraph (f)(1) of this AD thereafter at intervals not to exceed the applicable time specified in paragraph (f)(2)(i) or (f)(2)(ii) of this AD. (i) For Model A380-841 and -842 airplanes: 50 flight cycles. (ii) For Model A380-861 airplanes: 10 flight cycles. (3) If any cracking or delamination is found during any inspection required by paragraph (f)(1) or (f)(2) of this AD, before further flight, replace the MFTF#6 with a new or serviceable part, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A380-57-8014, dated November 21, 2008; or Airbus Mandatory Service Bulletin A380-57-8014, Revision 01, dated June 5, 2009. For parts replaced before the effective date of this AD, repeat the inspections specified in paragraph (f)(1) of this AD at the later of the times specified in paragraphs (f)(3)(i) and (f)(3)(ii) of this AD. For parts replaced on or after the effective date of this AD, repeat the inspections specified in paragraph (f)(1) of this AD at the applicable time defined in paragraph (f)(1) of this AD. After the effective date of this AD, use only Revision 01 for the replacement. (i) At the applicable time defined in paragraph (f)(2) of this AD. (ii) At the applicable time defined in paragraph (f)(1) of this AD. New Requirements of This AD
Required actions
Unless already done, do the following actions. (1) At the applicable time specified in paragraph (f)(1)(i) or (f)(1)(ii) of this AD for the left- and right-hand MFTF#6, do a special detailed (ultrasonic and high-frequency eddy current) inspection of the filet radii of pivot supports, monolithic carbon fibre reinforced plastic structures, and radii of the U-frame, for cracking and delamination in accordance with the Accomplishment Instructions of Airbus Service Bulletin A380-57-8014, dated November 21, 2008; or Airbus Mandatory Service Bulletin A380-57-8014, Revision 01, dated June 5, 2009. After the effective date of this AD, use only Revision 01. (i) For Airbus Model A380-841 and -842 airplanes: Before the MFTF#6 has accumulated 500 total flight cycles since its first installation on an airplane, or within 30 flight hours after May 28, 2009 (the effective date of AD 2009-10-07), whichever occurs later. (ii) For Model A380-861 airplanes: Before the MFTF#6 has accumulated 100 total flight cycles since its first installation on an airplane, or within 30 flight hours after May 28, 2009, whichever occurs later. (2) If no cracking and no delamination are found during any inspection required by paragraph (f)(1) of this AD, repeat the inspections required by paragraph (f)(1) of this AD thereafter at intervals not to exceed the applicable time specified in paragraph (f)(2)(i) or (f)(2)(ii) of this AD. (i) For Model A380-841 and -842 airplanes: 50 flight cycles. (ii) For Model A380-861 airplanes: 10 flight cycles. (3) If any cracking or delamination is found during any inspection required by paragraph (f)(1) or (f)(2) of this AD, before further flight, replace the MFTF#6 with a new or serviceable part, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A380-57-8014, dated November 21, 2008; or Airbus Mandatory Service Bulletin A380-57-8014, Revision 01, dated June 5, 2009. For parts replaced before the effective date of this AD, repeat the inspections specified in paragraph (f)(1) of this AD at the later of the times specified in paragraphs (f)(3)(i) and (f)(3)(ii) of this AD. For parts replaced on or after the effective date of this AD, repeat the inspections specified in paragraph (f)(1) of this AD at the applicable time defined in paragraph (f)(1) of this AD. After the effective date of this AD, use only Revision 01 for the replacement. (i) At the applicable time defined in paragraph (f)(2) of this AD. (ii) At the applicable time defined in paragraph (f)(1) of this AD. New Requirements of This AD
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The directive text above is reproduced from the Federal Register, a work of the United States government and in the public domain. The separation into applicability, compliance and required actions is TrackAD's.*1