AD 2013-26-14

You are responsible for having the actions required by this AD performed within the compliance times specified, unless the actions have already been done.

This paragraph restates the requirements of paragraph (f) of AD 2008-08-04, Amendment 39-15456 (73 FR 19975, April 14, 2008), with changes. Except for airplanes on which Airbus modification 32025 has been accomplished in production, within 8 days after June 7, 2006 (the effective date of AD 2006-11-04, Amendment 39-14608 (71 FR 29578, May 23, 2006)), or before further flight after a hard landing, whichever is first: Perform a detailed inspection for cracking in the forward lug of the support rib 5 fitting of the left- and right-hand MLG, and, if any crack is found, replace the MLG fitting with a new fitting before further flight, in accordance with a method approved by the Manager, International Branch, ANM-116, Transport Airplane Directorate, FAA, or the European Aviation Safety Agency (EASA) (or its delegated agent). Repeat the inspection thereafter at intervals not to exceed 8 days, or before further flight after a hard landing, whichever is first. As of May 19, 2008 (the effective date of AD 2008-08-04), the repetitive inspections required by paragraph (k) of this AD must be accomplished in lieu of the repetitive inspections required by this paragraph.

This paragraph restates the provisions of paragraph (g) of AD 2008-08-04, Amendment 39-15456 (73 FR 19975, April 14, 2008), with revised service information. Performing an ultrasonic inspection for cracking in the forward lug of the support rib 5 fitting of the left- and right-hand MLG, in accordance with an applicable method specified in paragraph (h)(1) or (h)(2) of this AD, is an acceptable alternative method of compliance for the initial and repetitive inspections required by paragraph (g) of this AD.

(1) In accordance with a method approved by the Manager, International Branch, ANM-116, or the EASA (or its delegated agent).

(2) In accordance with Task 57-29-03-270-801-A-01, Gear Rib Forward Lug Attachment for the Main Gear Before Modification 32025J2211, of Subject 57-29-03, Inspection of the Gear Rib Forward and Aft Lug Attachment for the Main Gear (for Model A318, A319, and A320 series airplanes); or Task 57-29-04-270-801-A-01, Gear Rib Forward Lug Attachment for the Main Gear Before Modification 32025J2211, of Subject 57-29-04, Inspection of the Gear Rib Forward and Aft Lug Attachment for the Main Gear (for Model A321 series airplanes); both of Chapter 57, Wings, of the Airbus A318/A319/A320/A321 Nondestructive Testing Manual, Revision 89, dated August 1, 2011.

This paragraph restates the provisions of paragraph (h) of AD 2008-08-04, Amendment 39-15456 (73 FR 19975, April 14, 2008), with changes. Repair of the forward lugs of the support rib 5 fitting of the left- and right-hand MLG done before the effective date of this AD, in accordance with a method approved by the Manager, International Branch, ANM-116, or the EASA (or its delegated agent), constitutes terminating action for the requirements of paragraphs (g), (h), (k), (l), and (m) of this AD.

To identify affected airplanes in paragraphs (k), (m), and (o) of this AD, this AD refers to the following conditions:

(1) Airplanes on which the modification of the MLG rib bushes specified in Airbus Mandatory Service Bulletin A320-57-1118 has been done.

(2) Airplanes on which a repair of the MLG support rib 5 fitting, as specified in paragraph 5.C. of Subsection 57-26-13, Attachments—Main Landing Gear, of the Airbus A319 Structural Repair Manual (SRM), Revision November 1, 2004; paragraph 5.D. of Subsection 57-26-13, Attachments—Main Landing Gear, of the Airbus A320 SRM, Revision November 1, 2004; or paragraph 5.D. of Subsection 57-26-13, Attachments—Main Landing Gear, of the Airbus A321 SRM, Revision February 1, 2005; as applicable; has been done.

(3) Airplanes on which replacement in service of the MLG support rib 5 specified in Airbus Repair Instruction R572-58507 and Airbus Repair Drawing R572-58209, or Airbus Repair Instruction R572-45020 and Airbus Repair Drawing R572-45019, as applicable, has been done.

This paragraph restates the requirements of paragraph (i) of AD 2008-08-04, Amendment 39-15456 (73 FR 19975, April 14, 2008), with changes. For airplanes on which none of the actions specified in paragraphs (j)(1), (j)(2), and (j)(3) of this AD have been done, except for airplanes on which Airbus modification 32025 has been accomplished: At the applicable time specified in paragraphs (k)(1) and (k)(2) of this AD, or before further flight after a hard landing, whichever is first, do a visual inspection or ultrasonic inspection for cracking in the forward lug of the support rib 5 fitting of the left and right MLG, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A320-57-1138, Revision 01, dated October 27, 2006. Repeat the inspection thereafter at the applicable interval specified paragraphs (k)(1) and (k)(2) of this AD, or before further flight after a hard landing, whichever is first, until the modification required by paragraph (m) of this AD has been accomplished. Accomplishing the initial inspection terminates the requirements of paragraph (g) of this AD.

(1) For Model A318, A319, and A320 airplanes, inspect at the applicable times specified in paragraphs (k)(1)(i) and (k)(1)(ii) of this AD.

(i) If the most recent inspection is a detailed inspection done in accordance with paragraph (g) of this AD: Inspect within 150 flight cycles after the most recent detailed inspection. Repeat the inspection thereafter at intervals not to exceed 150 flight cycles after a visual inspection.

(ii) If the most recent inspection is an ultrasonic inspection done in accordance with paragraph (h) of this AD: Inspect within 940 flight cycles after the most recent ultrasonic inspection. Repeat the inspection thereafter at intervals not to exceed 940 flight cycles after an ultrasonic inspection.

(2) For Model A321 airplanes, inspect at the applicable times specified in paragraphs (k)(2)(i) and (k)(2)(ii) of this AD.

(i) If the most recent inspection is a detailed inspection done in accordance with paragraph (g) of this AD: Inspect within 100 flight cycles after the most recent detailed inspection. Repeat the inspection thereafter at intervals not to exceed 100 flight cycles after a visual inspection.

(ii) If the most recent inspection is an ultrasonic inspection done in accordance with paragraph (h) of this AD: Inspect within 630 flight cycles after the most recent ultrasonic inspection. Repeat the inspection thereafter at intervals not to exceed 630 flight cycles after an ultrasonic inspection.

This paragraph restates the requirements of paragraph (j) of AD 2008-08-04, Amendment 39-15456 (73 FR 19975, April 14, 2008). If any cracking is found during any inspection required by paragraph (k) of this AD: Before further flight, repair or replace the cracked MLG fitting, in accordance with a method approved by the Manager, International Branch, ANM-116, or the EASA (or its delegated agent).

This paragraph restates the requirements of paragraph (k) of AD 2008-08-04, Amendment 39-15456 (73 FR 19975, April 14, 2008), with revised service information. Except for airplanes on which the actions specified in paragraph (j)(1) or (j)(3) of this AD have been done, and except for airplanes on which Airbus modification 32025 have been done: Within 60 months after May 19, 2008 (the effective date of AD 2008-08-04), modify the rib bushings of the left and right MLG, by accomplishing all of the applicable actions specified in the Accomplishment Instructions of Airbus Mandatory Service Bulletin A320-57-1118, Revision 05, dated July 23, 2012, except that the liquid penetrant inspection specified in this service information is not required by this AD. Accomplishing this modification terminates the requirements of paragraphs (g) and (k) of this AD, and then the requirements of paragraph (n) of this AD must be done.

For airplanes on which the actions specified in paragraph (j)(1), (j)(2), or (m) of this AD have been done: At the later of the times specified in paragraphs (n)(1) and (n)(2) of this AD, do a detailed inspection for cracks of the forward lug of each left-hand and right-hand MLG support rib 5 fitting, in accordance with the Accomplishment Instructions of Airbus Mandatory Service Bulletin A320-57A1166, Revision 01, dated October 19, 2011. Repeat the inspection thereafter at intervals not to exceed 500 flight cycles.

(1) Within 2,000 flight cycles after accomplishing the modification specified in paragraph (j)(1) or (m) of this AD, or the repair specified in paragraph (j)(2) of this AD, as applicable.

(2) Within 250 flight cycles after the effective date of this AD, without exceeding 3 months after the effective date of this AD.

If any crack is detected during any inspection required by paragraph (n) of this AD: Before further flight, repair using a method approved by either the Manager, International Branch, ANM-116, FAA, or the EASA (or its delegated agent).

Replacement of a MLG support rib 5 fitting at any position (left-hand or right-hand), as specified in paragraph (j)(3) of this AD, terminates the requirements of paragraphs (k) and (n) of this AD for the MLG support rib 5 fitting at that position.

For airplanes on which the actions specified in paragraph (j)(3) of this AD have been done: Within 60 months after the replacement or within 500 flight cycles after the effective date of this AD, whichever occurs later, do a detailed inspection of the forward lug of each left-hand and right-hand MLG support rib 5 fitting that has been replaced, in accordance with the Accomplishment Instructions of Airbus Mandatory Service Bulletin A320-57A1166, Revision 01, dated October 19, 2011. Repeat the inspection thereafter at intervals not to exceed 500 flight cycles.

For airplanes on which Airbus modification 32025 has been done: At the applicable time specified in paragraph (r)(1) (r)(2), (r)(3), or (r)(4) of this AD, do a detailed inspection for cracks of the forward lug of each left-hand and right-hand MLG support rib 5 fitting, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A320-57-1168, dated November 7, 2011. Repeat the inspection thereafter at intervals not to exceed 500 flight cycles.

(1) For airplanes on which the MLG support rib 5 has not been modified or repaired since the first flight of the airplane as of the effective date of this AD: Within 60 months after the first flight of the airplane, or within 500 flight cycles after the effective date of this AD, whichever occurs later.

(2) For airplanes on which the MLG support rib 5 has been replaced as specified in paragraph (j)(3) of this AD as of the effective date of this AD: Within 60 months after the replacement of the MLG support rib 5, or within 500 flight cycles after the effective date of this AD, whichever occurs later.

(3) For airplanes on which the MLG support rib 5 has been repaired according to the SRM or a repair approval sheet as of the effective date of this AD: At the later of the times specified in paragraph (r)(3)(i) or (r)(3)(ii) of this AD.

(i) Within 2,000 flight cycles after the repair.

(ii) Within 250 flight cycles or 3 months after the effective date of this AD, whichever occurs first.

(4) For airplanes having a manufacturer serial number (S/N) listed in figure 1 to paragraph (r)(4) of this AD, and on which the MLG support rib 5 has been inspected before the effective date of this AD according to specific Airbus repair instructions or technical disposition: At the later of the times specified in paragraph (r)(4)(i) or (r)(4)(ii) of this AD.

(i) Within 2,000 flight cycles after the last inspection done using specific Airbus repair instructions or a technical disposition, or within 60 months since first flight of the airplane, whichever occurs later.

(ii) Within 250 flight cycles or 3 months after the effective date of this AD, whichever occurs first.

If any crack is detected during any inspection required by paragraph (q) or (r) of this AD: Before further flight, repair using a method approved by either the Manager, International Branch, ANM-116, FAA, or the EASA (or its delegated agent).