Outer Wing Main Landing Gear Support Rib 5 Fitting Inspection / Modification
**** Hidden Message ***** 1/2<BR>EASA AIRWORTHINESS DIRECTIVE<BR>AD No : 2007-0213<BR>Date: 07 August 2007<BR>No person may operate an aircraft to which an Airworthiness Directive applies, except in accordance with the<BR>requirements of that Airworthiness Directive unless otherwise agreed with the Authority of the State of Registry.<BR>Type Approval Holder’s Name :<BR>AIRBUS<BR>Type/Model designation(s) :<BR>A318, A319, A320 and A321 aircraft<BR>TCDS Number: EASA A.064<BR>Foreign AD: Not applicable.<BR>Supersedure: This AD supersedes EASA AD 2006-0069R1<BR>ATA 57 Wings – Outer Wing Main Landing Gear Support Rib 5 Fitting –<BR>Inspection / Modification<BR>Manufacturer(s): AIRBUS (formerly AIRBUS INDUSTRIE)<BR>Applicability: AIRBUS A318, A319, A320 and A321 aircraft, all certified models, all serial<BR>numbers (MSN) except aircraft that have received AIRBUS modification 32025 in<BR>production or AIRBUS Service Bulletin (SB) A320-57-1118 in service.<BR>The requirements of this AD do not apply to a MLG Support Rib 5 Fitting that<BR>has been repaired i.a.w. A319 Structural Repair Manual (SRM) 57-26-13<BR>paragraph 5.C or i.a.w. A320/A321 SRM 57-26-13 paragraph 5.D.<BR>Reason: Several cases of corrosion of the main landing gear (MLG) rib 5 fitting lug bores<BR>have been reported on A320 family aircraft. In some instances, corrosion pits<BR>caused the cracking of the forward lug (sometimes through its complete<BR>thickness). If not detected, the cracking may lead to the complete failure of the<BR>fitting and thus could affect the structural integrity of the MLG installation.<BR>EASA AD 2006-0069 was issued to address this condition and required repetitive<BR>inspections and corrective action, as necessary.<BR>The present AD supersedes AD 2006-0069R1 and mandates a repetitive<BR>inspection program of the MLG rib 5 fitting forward lugs and requires a<BR>modification that is terminating action for the repetitive inspection requirements of<BR>this directive.<BR>Effective Date: 21 August 2007<BR>2/2<BR>Compliance: 1. Inspections :<BR>1.1 For A318, A319, A320 aircraft, inspect the forward lug of the MLG<BR>support rib 5 fittings as per the SB A320-57-1138 Revision 01:<BR>• within 150 flight cycles following the last inspection as per AD 2006-<BR>0069R1, if visual<BR>or<BR>• within 940 flight cycles following the last inspection as per AD 2006-<BR>0069R1, if by ultrasound<BR>or<BR>• before next flight following a hard landing.<BR>1.2 For A321 aircraft, inspect the forward lug of the MLG support rib 5<BR>fittings as per the SB A320-57-1138 Revision 01:<BR>• within 100 flight cycles following the last inspection as per AD 2006-<BR>0069R1, if visual<BR>or<BR>• within 630 flight cycles following the last inspection as per AD 2006-<BR>0069R1, if by ultrasound<BR>or<BR>• before next flight following a hard landing.<BR>1.3 For all aircraft, repeat the inspection at intervals defined in SB A320-57-<BR>1138 revision 01;<BR>In case of findings, refer to the SB A320-57-1138 Rev 01 for further<BR>instructions.<BR>2. Final fix :<BR>Within five (5) years after the effective date of this directive, modify the MLG<BR>Rib Bushes in accordance with instructions in Airbus SB A320-57-1118<BR>revision 03.<BR>The embodiment of the SB A320-57-1118 constitutes terminating action and<BR>cancels the repetitive inspection requirements of paragraph 1 of this directive.<BR>The repair of a MLG support rib 5 fitting i.a.w. A319 SRM 57-26-13 paragraph<BR>5.C or A320/A321 SRM 57-26-13 paragraph 5.D, as applicable, constitutes<BR>terminating action and cancels the repetitive inspection requirements of<BR>paragraph 1 of this directive for that support fitting.<BR>Ref. Publications: AIRBUS Service Bulletin (SB) A320-57-1118 at original issue; and SB A320-57-<BR>1138 Revision 01; or later approved revisions of these documents.<BR>Remarks : 1. If requested and appropriately substantiated the responsible EASA<BR>manager for the related product has the authority to accept Alternative<BR>Method of Compliance (AMOCs) for this AD.<BR>2. This AD was posted on 14 March 2007 as PAD 07-040 for consultation until<BR>16 April 2007. The Comment Response Document can be found at<BR>http://ad.easa.europa.eu/ .<BR>3. Enquiries regarding this AD should be addressed to the AD Focal Point,<BR>Certification Directorate, EASA. E-mail ADs@easa.europa.eu<BR>4. For any question concerning the technical content of the requirements in<BR>this AD, please contact AIRBUS - Fax 33 5 61 93 44 51.
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