Airworthiness Directive · Amendment 39-18093 · Wings
Airbus Airplanes
This AD applies to the Airbus airplanes identified in paragraphs (c)(1) and (c)(2) of this AD, certificated in any category, all manufacturer serial numbers.
(1) Airbus Model A300 B2-1A, B2-1C, B2K-3C, and B2-203 airplanes; Model A300 B4-2C, B4-103, and B4-203 airplanes; Model A300 B4-601, B4-603, B4-620, B4-622, B4-605R, B4-622R, F4-605R, and F4-622R airplanes; and Model A300 C4-605R Variant F airplanes.
(2) Airbus Model A310-203, -204, -221, -222, -304, -322, -324, and -325 airplanes.
We are superseding Airworthiness Directive (AD) 2007-03-18, AD 2008-17-02, AD 2012-08-03, and AD 2012-15-14, for certain Airbus Model A300 B4-2C, B4-103, and B4-203 airplanes; Model A300 B4-600, B4-600R, and F4-600R series airplanes, and Model A300 C4-605R Variant F airplanes (collectively called Model A300-600 series airplanes); and Model A310 series airplanes. AD 2007-03-18, AD 2008-17-02, AD 2012-08- 03, and AD 2012-15-14 required repetitive inspections of the forward lugs of the aft bearing at rib 5 of the main landing gear (MLG) on the left-hand (LH) and right-hand (RH) wings, and repair if necessary; and installation of new bushes with increased interference fit in the forward lug of the aft bearing at rib 5 of the MLG on the LH and RH wings. This new AD adds airplanes to the applicability; and adds, for certain airplanes, repetitive inspections of the MLG rib 5 aft bearing forward lugs, and repair if necessary. This AD was prompted by reports of cracking in the forward lug of the MLG rib 5 aft bearing attachment. We are issuing this AD to detect and correct cracking of the forward lugs of the aft bearing at rib 5 of the MLG on the LH and RH wings, which could affect the structural integrity of the MLG attachment, resulting in possible MLG collapse during landing or rollout.
This paragraph restates the requirements of paragraph (f) of AD 2008-17-02, Amendment 39-15640 (73 FR 47032, August 13, 2008). For Model A310 airplanes, except for those where LH and RH wing MLG rib 5 forward lugs have been repaired by installation of oversized interference fit bushes as per Airbus A310 Repair Instruction R572-49121, or which have had Airbus Service Bulletin A310-57-2090 (Airbus Modification 13329) embodied in service: Do the actions specified in paragraphs (g)(1), (g)(2), and (g)(3) of this AD, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A310-57A2088, dated November 6, 2006.
(1) Before the accumulation of 12,000 total flight cycles, or within 14 days after February 6, 2007 (the effective date of AD 2007-02-09, Amendment 39-14896 (72 FR 2612, January 22, 2007)), whichever occurs later: Perform a detailed visual inspection of the LH and RH wing MLG rib 5 aft bearing forward lugs.
(2) If any crack is detected at LH and/or RH aft bearing forward lug, contact Airbus and proceed with the replacement before next flight.
(3) Repeat the inspection at intervals not exceeding 100 flight cycles.
This paragraph restates the requirements of paragraph (g) of AD 2008-17-02, Amendment 39-15640 (73 FR 47032, August 13, 2008), with new service information for paragraphs (h)(2), (h)(3), and (h)(4)(ii) of this AD, and specific delegation approval language in paragraphs (h)(3) and (h)(4)(ii) of this AD. For Model A310 airplanes, except for those where LH and RH wing MLG rib 5 forward lugs have been repaired by installation of oversized interference fit bushes as per Airbus A310 Repair Instruction R572-49121, or which have had Airbus Service Bulletin A310-57-2090 (Airbus Modification 13329) embodied in service: Before the accumulation of 12,000 total flight cycles or before the accumulation of 12,000 flight cycles on MLG rib 5, or within 14 days after September 17, 2008 (the effective date of AD 2008-17-02), whichever occurs latest, perform either a detailed visual inspection (DVI) or an ultrasonic inspection of the LH and RH MLG rib 5 aft bearing forward lug for cracks, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A310-57-2091, excluding Appendix 01, dated May 22, 2007. If a MLG rib 5 has been replaced on one side only, then the LH and RH must be considered separately. Doing this inspection ends the requirements of paragraph (g) of this AD for that MLG rib 5 only.
(1) If no crack is detected during any inspection required by paragraph (h) of this AD: Repeat the applicable inspection at the time specified in paragraph (h)(1)(i) or (h)(1)(ii) of this AD.
(i) Repeat the DVI thereafter at intervals not to exceed 100 flight cycles.
(ii) Repeat the ultrasonic inspection thereafter at intervals not to exceed 825 flight cycles.
(2) Replacement of the MLG rib 5 bushes with new bushes with high interference fit in the aft bearing forward lugs of MLG rib 5, in accordance with the Accomplishment Instructions of a service bulletin specified in paragraph (h)(2)(i), (h)(2)(ii), or (h)(2)(iii) of this AD, ends the repetitive inspections required by paragraph (h)(1) of this AD for that MLG rib 5 only. As of the effective date of this AD, use only Airbus Mandatory Service Bulletin A310-57-2090, Revision 03, dated January 23, 2012, for the actions specified in this paragraph.
(i) Airbus Service Bulletin A310-57-2090, Revision 01, dated December 19, 2007.
(ii) Airbus Mandatory Service Bulletin A310-57-2090, Revision 02, dated June 18, 2010.
(iii) Airbus Mandatory Service Bulletin A310-57-2090, Revision 03, dated January 23, 2012.
(3) If any crack is detected during the DVI required by paragraph (h) of this AD: Before further flight, contact Airbus for replacement instructions and replace the MLG rib 5 bushes before further flight. As of the effective date of this AD: Before further flight, replace 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). Repeat the applicable inspection in paragraph (h) of this AD at the time specified in paragraph (h)(1)(i) or (h)(1)(ii) of this AD. Accomplishing the replacement of the MLG rib 5 bushes with new bushes with high interference fit in the aft bearing forward lugs of MLG rib 5, in accordance with the Accomplishment Instructions of a service bulletin specified in paragraph (h)(2)(i), (h)(2)(ii), or (h)(2)(iii) of this AD, ends the repetitive inspections required by paragraph (h)(1) of this AD for that MLG rib 5 only.
(4) If any crack is detected during the ultrasonic inspection required by paragraph (h) of this AD, before further flight, accomplish the actions specified in paragraph (h)(4)(i) or (h)(4)(ii) of this AD, as applicable.
(i) If any crack is not visible on MLG rib 5: Before further flight, repair MLG rib 5 using Airbus A310 Repair Instruction R572-49121, Issue C, dated May 2007. After embodiment of the repair instruction, no further actions are necessary as required by paragraphs (g) and (h) of this AD and specified in Airbus Service Bulletin A310-57-2091, excluding Appendix 01, dated May 22, 2007, for that MLG rib 5 only.
(ii) If any crack is visible on MLG rib 5: Before further flight, contact Airbus for rib replacement instructions, and replace before further flight. As of the effective date of this AD: Before further flight, replace using a method approved by the Manager, International Branch, ANM-116, Transport Airplane Directorate, FAA; or the EASA; or Airbus's EASA DOA. Repeat the applicable inspection in paragraph (h) of this AD at the time specified in paragraph (h)(1)(i) or (h)(1)(ii) of this AD. Accomplishing the replacement of the MLG rib 5 bushes with new bushes with high interference fit in the aft bearing forward lugs of MLG rib 5, in accordance with the Accomplishment Instructions of a service bulletin specified in paragraph (h)(2)(i), (h)(2)(ii), or (h)(2)(iii) of this AD, ends the repetitive inspections required by paragraph (h) of this AD for that MLG rib 5 only.
Note 1 to paragraph (h) of this AD: The ultrasonic inspection will detect any crack at an early stage and will limit the risk of extensive repairs. This earlier crack detection is not possible with the DVI.
This paragraph restates the requirements of paragraph (g) of AD 2012-08-03, Amendment 39-17019 (77 FR 24367, April 24, 2012), and applies to the airplanes identified in paragraph (j) of this AD. Within 30 months after May 29, 2012 (the effective date of AD 2012-08-03), install new bushes with increased interference fit in the gear rib 5 aft bearing forward lug on the LH and RH wings, in accordance with the Accomplishment Instructions of the applicable service bulletin specified in paragraph (i)(1), (i)(2), or (i)(3) of this AD; except as specified in paragraph (k) of this AD.
(1) Airbus Mandatory Service Bulletin A300-57-0249, Revision 03, dated January 18, 2012 (for Model A300 B4-2C, B4-103, and B4-203 airplanes).
(2) Airbus Mandatory Service Bulletin A300-57-6106, Revision 03, dated January 26, 2012 (for Model A300-600 series airplanes).
(3) Airbus Mandatory Service Bulletin A310-57-2090, Revision 03, dated January 23, 2012 (for Model A310 series airplanes).
For airplanes identified in paragraphs (j)(1), (j)(2), and (j)(3) of this AD: Do the actions required by paragraph (i) of this AD.
(1) Airbus Model A300 B4-2C, B4-103, and B4-203 airplanes; all serial numbers; except airplanes on which the MLG rib 5 forward lugs of the LH and RH wings have been repaired by installation of oversized interference fit bushes specified in Airbus Repair Instruction R57240221, or those on which the LH and RH wings have had Airbus Service Bulletin A300-57-0249 embodied in service.
(2) Airbus Model A300 B4-601, B4-603, B4-620, and B4-622 airplanes; Airbus Model A300 B4-605R and B4-622R airplanes; Airbus Model A300 F4-605R and F4-622R airplanes; and Airbus Model A300 C4-605R Variant F airplanes; all serial numbers; except airplanes on which the MLG rib 5 forward lugs of the LH and RH wings have been repaired by installation of oversized interference fit bushes specified in Airbus Repair Instruction R57240221, or those on which the LH and RH wings have had Airbus Service Bulletin A300-57-6106 embodied in service.
(3) Airbus Model A310-203, -204, -221, -222, -304, -322, -324, and -325 airplanes; all serial numbers; except airplanes on which the MLG rib 5 forward lugs of the LH and RH wings have been repaired by installation of oversized interference fit bushes specified in Airbus Repair Instruction R57249121, or those on which the LH and RH wings have had Airbus Service Bulletin A310-57-2090 embodied in service.
This paragraph restates the requirements of paragraph (h) of AD 2012-08-03, Amendment 39-17019 (77 FR 24367, April 24, 2012), and applies to the airplanes identified in paragraphs (j)(1), (j)(2), and (j)(3) of this AD. If one wing had rib 5 forward lugs of the MLG repaired by installing oversized interference fit bushes, as specified in Airbus Repair Instruction R57240221 or Airbus Repair Instruction R572-49121, as applicable to the airplane model, then installing new bushes with increased interference fit in the aft bearing forward lug of the gear rib, as specified in paragraph (i) of this AD, is required for the opposite wing only.
This paragraph restates the requirements of paragraph (i) of AD 2012-08-03, Amendment 39-17019 (77 FR 24367, April 24, 2012), and applies to the airplanes identified in paragraphs (j)(1), (j)(2), and (j)(3) of this AD. Installation of new bushes, as specified in paragraph (i) of this AD, is terminating action for the repetitive inspections required by AD 2007-03-18, Amendment 39-14929 (72 FR 5919, February 8, 2007); and by paragraphs (g) and (h) of this AD.
This paragraph restates the requirements of paragraph (g) of AD 2012-15-14, Amendment 39-17143 (77 FR 46937, August 7, 2012), and applies to the airplanes identified in paragraph (n) of this AD. Except as provided by paragraph (o) of this AD: Before the accumulation of 12,000 total flight cycles since new, or within 12,000 flight cycles since the most recent MLG rib 5 replacement, if applicable, or within 10 days after September 11, 2012 (the effective date of AD 2012-15-14, Amendment 39-17143 (77 FR 46937, August 7, 2012)), whichever occurs latest, do a detailed inspection or an ultrasonic inspection for cracking of the LH and RH MLG rib 5 aft bearing forward lugs, in accordance with the Accomplishment Instructions of Airbus Mandatory Service Bulletin A300-57-0251, including Appendix 01, dated August 8, 2007 (for Model A300 B4-103, B4-203, and B4-2C airplanes); or Airbus Mandatory Service Bulletin A300-57-6107, including Appendix 01, dated August 8, 2007 (for Model A300-600 series airplanes). Repeat the applicable inspections thereafter at the applicable interval specified in paragraph (m)(1) or (m)(2) of this AD, until the modification specified in paragraph (q) of this AD is accomplished.
(1) Repeat the detailed inspections at intervals not to exceed 100 flight cycles.
(2) Repeat the ultrasonic inspections at intervals not to exceed 675 flight cycles.
For Airbus Model A300 B4-2C, B4-103, and B4-203 airplanes; Model A300 B4-601, B4-603, B4-620, B4-622, B4-605R, B4-622R, F4-605R, and F4-622R airplanes; and Model A300 C4-605R Variant F airplanes; all serial numbers; except for airplanes identified in paragraphs (n)(1), (n)(2), and (n)(3) of this AD: Do the actions required by paragraph (m) of this AD, except as provided by paragraph (o) of this AD.
(1) Airplanes on which LH and RH wing MLG rib 5 forward lugs have oversized interference fit bushings installed per Airbus Repair Instruction R57240221.
(2) Model A300 B4-103, B4-203, and B4-2C airplanes on which Airbus Service Bulletin A300-57-0249 has been done in service on the LH and RH wings.
(3) Model A300-600 series airplanes on which Airbus Service Bulletin A300-57-6106 has been done in service on the LH and RH wings.
This paragraph restates the requirements of paragraph (h) of AD 2012-15-14, Amendment 39-17143 (77 FR 46937, August 7, 2012), and applies to the airplanes identified in paragraph (n) of this AD on which an inspection required by AD 2007-03-18, Amendment 39-14929 (72 FR 5919, February 8, 2007), has been done as of September 11, 2012 (the effective date of AD 2012-15-14): Within 100 flight cycles after doing the most recent inspection required by AD 2007-03-18, or within 10 days after September 11, 2012, whichever occurs later, do a detailed or ultrasonic inspection as specified in paragraph (m) of this AD. Repeat the applicable inspection thereafter at the times specified in paragraph (m) of this AD.
This paragraph restates the requirements of paragraph (i) of AD 2012-15-14, Amendment 39-17143 (77 FR 46937, August 7, 2012), with specific delegation approval language. If any cracking is detected during any detailed or ultrasonic inspection of the LH and RH MLG rib 5 aft bearing forward lugs required by paragraph (m) of this AD, before further flight, repair using a method approved by Manager, International Branch, ANM-116, Transport Airplane Directorate, FAA; or the EASA; or Airbus's EASA DOA.
This paragraph restates the optional terminating modification of paragraph (j) of AD 2012-15-14, Amendment 39-17143 (77 FR 46937, August 7, 2012), and applies to the airplanes identified in paragraph (n) of this AD. Performing the applicable actions specified in paragraphs (q)(1), (q)(2), (q)(3), and (q)(4) of this AD, in accordance with the Accomplishment Instructions of Airbus Mandatory Service Bulletin A300-57-0249, Revision 02, dated June 18, 2010 (for Model A300 B4-103, B4-203, and B4-2C airplanes); or Airbus Mandatory Service Bulletin A300-57-6106, Revision 03, dated January 26, 2012 (for Model A300-600 series airplanes); terminates the repetitive inspections required by paragraph (m) of this AD.
(1) Perform a general visual inspection and dye penetrant flaw detection inspection for corrosion and damage of the bore and spotfaces of the lug.
(2) Determine that the diameter of the bore of the lug (dimension Y) is within the tolerance specified in the Accomplishment Instructions of Airbus Mandatory Service Bulletin A300-57-0249, Revision 02, dated June 18, 2010 (for Model A300 B4-103, B4-203, and B4-2C airplanes); or Airbus Mandatory Service Bulletin A300-57-6106, Revision 03, dated January 26, 2012 (for Model A300-600 series airplanes).
(3) If damage or corrosion is detected during any inspection specified in paragraph (q)(1) of this AD, or if dimension Y is outside the tolerance specified in the Accomplishment Instructions of Airbus Mandatory Service Bulletin A300-57-0249, Revision 02, dated June 18, 2010 (for Model A300 B4-103, B4-203, and B4-2C airplanes); or Airbus Mandatory Service Bulletin A300-57-6106, Revision 03, dated January 26, 2012 (for Model A300-600 series airplanes); repair using a method approved by either the Manager, International Branch, ANM-116, Transport Airplane Directorate, FAA; or EASA; or Airbus's EASA DOA.
(4) Install bushings with an increased interference fit in the aft bearing forward lugs, in accordance with the Accomplishment Instructions of Airbus Mandatory Service Bulletin A300-57-0249, Revision 02, dated June 18, 2010 (for Model A300 B4-103, B4-203, and B4-2C airplanes); or Airbus Mandatory Service Bulletin A300-57-6106, Revision 03, dated January 26, 2012 (for Model A300-600 series airplanes).
This paragraph restates the terminating action statement of paragraph (k) of AD 2012-15-14, Amendment 39-17143 (77 FR 46937, August 7, 2012), and applies to the airplanes identified in paragraph (n) of this AD. Doing the actions required by paragraph (q) of this AD terminates the inspections required by AD 2007-03-18, Amendment 39-14929 (72 FR 5919, February 8, 2007), for that airplane.
This paragraph restates the requirements of paragraph (l) of AD 2012-15-14, Amendment 39-17143 (77 FR 46937, August 7, 2012), and applies to the airplanes identified in paragraph (n) of this AD. Submit a report (including both positive and negative findings), using the applicable report sheet attached to Airbus Mandatory Service Bulletin A300-57-0251, including Appendix 01, dated August 8, 2007 (for Model A300 B4-103, B4-203, and B4-2C airplanes); or Airbus Mandatory Service Bulletin A300-57-6107, including Appendix 01, dated August 8, 2007 (for Model A300-600 series airplanes); of the first inspection required by paragraph (m) of this AD. Submit the report to Airbus, Customer Services Directorate, 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex France, Attn: SEDCC1 Technical Data and Documentation Services; fax: (+33) 5 61 93 28 06; email: sb.reporting@airbus.com; at the applicable time specified in paragraph (s)(1) or (s)(2) of this AD.
(1) If the inspection was done on or after September 11, 2012 (the effective date of AD 2012-15-14, Amendment 39-17143 (77 FR 46937, August 7, 2012)): Submit the report within 30 days after the inspection.
(2) If the inspection was done before September 11, 2012 (the effective date of AD 2012-15-14, Amendment 39-17143 (77 FR 46937, August 7, 2012)): Submit the report within 30 days after September 11, 2012.
For airplanes identified in paragraph (u) of this AD: At the applicable time specified in paragraph (v)(1) or (v)(2) of this AD, do a detailed inspection for cracking, or an ultrasonic inspection for any crack indications of the LH and RH MLG rib 5 aft bearing forward lugs, in accordance with the Accomplishment Instructions of the applicable service bulletin specified in paragraph (t)(1), (t)(2), or (t)(3) of this AD. Repeat the inspection thereafter at intervals not to exceed the applicable time specified in paragraph (v)(3) or (v)(4) of this AD.
(1) Airbus Service Bulletin A300-57-0255, including Inspection Reporting Form, dated January 13, 2012 (for Model A300 B2-1A, B2-1C, B2K-3C, and B2-203 airplanes).
(2) Airbus Service Bulletin A300-57-6112, including Inspection Reporting Form, dated January 13, 2012 (for Model A300 B4-601, B4-603, B4-620, B4-622, B4-605R, B4-622R, F4-605R, and F4-622R airplanes).
(3) Airbus Service Bulletin A310-57-2101, including Inspection Reporting Form, dated January 13, 2012 (for Model A310-203, -204, -221, -222, -304, -322, -324, and -325 airplanes).
For airplanes on which any modification or repair described in the service bulletins identified in paragraph (u)(1), (u)(2), or (u)(3) of this AD, as applicable, has been accomplished in service; and for airplanes with MLG rib 5 already repaired as specified in Airbus Repair Instruction R57240221 or R572-49121, including any airplane with the MLG rib 5 forward lugs repaired on one wing; by installation of oversized interference fit bushes, as specified in Airbus Repair Instruction R57240221 or R572-49121, as applicable: Do the actions required by paragraph (t) of this AD.
(1) Airbus Service Bulletin A300-57-0249, dated May 22, 2007; Revision 01, dated December 19, 2007; or Airbus Mandatory Service Bulletin A300-57-0249, Revision 02, dated June 18, 2010 (for Model A300 B4-2C, B4-103, and B4-203 airplanes).
(2) Airbus Service Bulletin A300-57-6106, dated May 22, 2007; Revision 01, dated January 28, 2008; or Revision 02, dated June 18, 2010 (for Model A300 B4-601, B4-603, B4-605R, B4-620, B4-622, B4-622R, F4-605R, F4-622R, and C4-605R Variant F airplanes).
(3) Airbus Service Bulletin A310-57-2090, dated May 22, 2007; Revision 01, dated December 19, 2007; or Revision 02, dated June 18, 2010 (for Model A310 series airplanes).
This paragraph specifies the compliance times for the actions specified in paragraph (t) of this AD.
(1) For airplanes identified in paragraph (c)(1) of this AD: Do the initial inspection required by paragraph (t) of this AD within 2,500 flight cycles after any modification or repair specified in paragraph (u) of this AD was done, or within 550 flight cycles after the effective date of this AD, whichever occurs later.
(2) For airplanes identified in paragraph (c)(2) of this AD: Do the initial inspection required by paragraph (t) of this AD within 2,500 flight cycles after any modification or repair specified in paragraph (u) of this AD was done, or within 775 flight cycles after the effective date of this AD, whichever occurs later.
(3) For airplanes identified in paragraph (c)(1) of this AD: For the repetitive inspection required by paragraph (t) of this AD, repeat the inspection within 550 flight cycles after any detailed inspection, and within 1,000 flight cycles after any ultrasonic inspection, as applicable.
(4) For airplanes identified in paragraph (c)(2) of this AD: For the repetitive inspection required by paragraph (t) of this AD, repeat the inspection within 775 flight cycles after any detailed inspection, and within 1,300 flight cycles after any ultrasonic inspection, as applicable.
If, during any ultrasonic inspection required by paragraph (t) of this AD, any crack indication is detected: Before further flight, report to Airbus using the applicable report sheet attached to the applicable Airbus service bulletin specified in paragraph (t)(1), (t)(2), or (t)(3) of this AD, and concurrently accomplish a detailed inspection for cracking of the affected MLG rib 5 aft bearing forward lug, in accordance with the Accomplishment Instructions of the applicable Airbus service bulletin specified in paragraph (t)(1), (t)(2), or (t)(3) of this AD. Repeat the detailed inspection thereafter at intervals not to exceed 100 flight cycles.
If any cracking is detected during any detailed inspection required by paragraph (t) or (w) of this AD: Before further flight, repair the cracking using a method approved by the Manager, International Branch, ANM-116, Transport Airplane Directorate, FAA; or the EASA; or Airbus's EASA DOA.
Submit a report (including both positive and negative findings), using the reporting sheet attached to the applicable Airbus service bulletin specified in paragraph (y)(1), (y)(2), or (y)(3) of this AD, of the first inspection required by paragraph (t) of this AD. Submit the report to Airbus, Customer Services Directorate, 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex France, Attn: SEDCC1 Technical Data and Documentation Services; fax: (+33) 5 61 93 28 06; email: sb.reporting@airbus.com. Submit the report within 30 days after the inspection or within 30 days after the effective date of this AD, whichever occurs later.
(1) Airbus Service Bulletin A300-57-0255, including Inspection Reporting Form, dated January 13, 2012 (for Model A300 B2-1A, B2-1C, B2K-3C, and B2-203 airplanes).
(2) Airbus Service Bulletin A300-57-6112, including Inspection Reporting Form, dated January 13, 2012 (for Model A300 B4-601, B4-603, B4-620, B4-622, B4-605R, B4-622R, F4-605R, and F4-622R airplanes).
(3) Airbus Service Bulletin A310-57-2101, including Inspection Reporting Form, dated January 13, 2012 (for Model A310-203, -204, -221, -222, -304, -322, -324, and -325 airplanes).
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.
