EASA AD No.: 2011-0011 

EASA Form 110 Page 1/4 

EASA AIRWORTHINESS DIRECTIVE 

AD No.: 2011- 0011 

Date: 21 January 2011 

Note: This Airworthiness Directive (AD) is issued by EASA, acting in accordance with 

Regulation (EC) No 216/2008 on behalf of the European Community, its Member States and 

of the European third countries that participate in the activities of EASA under Article 66 of 

that Regulation.

This AD is issued in accordance with EC 1702/2003, Part 21A.3B. In accordance with EC 2042/2003 Annex I, Part M.A.301, the 

continuing airworthiness of an aircraft shall be ensured by accomplishing any applicable ADs. Consequently, no person may operate 

an aircraft to which an AD applies, except in accordance with the requirements of that AD, unless otherwise specified by the Agency 

[EC 2042/2003 Annex I, Part M.A.303] or agreed with the Authority of the State of Registry [EC 216/2008, Article 14(4) exemption]. 

Type Approval Holder’s Name : 

AIRBUS

Type/Model designation(s) : 

A319, A320 and A321 aeroplanes 

TCDS Number : EASA A.064 

Foreign AD : Not applicable 

Supersedure : This AD supersedes EASA AD 2007-0213 dated 07 August 2007. 

ATA 57 Wings – Outer Wing Main Landing Gear Support Rib 5 Fitting – 

Inspection / Modification 

Manufacturer(s): Airbus (formerly Airbus Industrie) 

Applicability: Airbus A319-111, A319-112, A319-113, A319-114, A319-115, A319-131, 

A319-132, A319-133, A320-111, A320-211, A320-212, A320-214, A320-231, 

A320-232, A320-233, A321-111, A321-112, A321-131, A321-211, A321-212, 

A321-213, A321-231 and A321-232 aeroplanes, all manufacturer serial 

numbers, except aeroplanes on which Airbus modification 32025 has been 

embodied in production on Left-Hand (LH) and Right-Hand (RH) wings. 

Reason: Several cases of corrosion of the Main Landing Gear (MLG) support Rib 5 

fitting lug bores have been reported on A320 family aeroplanes. In some 

instances, corrosion pits caused the cracking of the forward lug (sometimes 

through its complete thickness). If not detected, the cracking may lead to the 

complete failure of the fitting and thus could affect the structural integrity of 

the MLG installation. 

EASA AD 2007-0213 was issued to address this condition and required a 

repetitive inspection program of the MLG support Rib 5 fitting forward lugs 

and, as terminating action, the embodiment of Airbus Service Bulletin (SB) 

A320-57-1118. 

After that AD was issued, a case of Rib 5, ruptured at the 4 o’clock position, 

was discovered on an aeroplane on which the terminating action of EASA 

AD 2007-0213 had already been embodied in accordance with Airbus SB 

A320-57-1118. 

Investigation of that case revealed that corrosion damage and cracking that 

should have been removed by repair machining was below the level of 

detectability of the Non Destructive Test (NDT) technique that cleared the 
EASA AD No.: 2011-0011 

EASA Form 110 Page 2/4 

surfaces prior to bush installation. 

This condition, if not detected and corrected, could affect the structural 

integrity of the aeroplane. 

It has also been established that all A318 aeroplanes have had Airbus 

modification 32025 embodied in production on both LH and RH wings, which 

is a one-way interchangeable (non-reversible) modification. Consequently, 

the unsafe condition addressed by AD 2007-0213 cannot occur or develop 

on those aeroplanes. 

For the reasons described above, this AD, which supersedes EASA AD 

2007-0213: 

- retains the requirements of EASA AD 2007-0213 for aeroplanes on which 

the MLG Rib Bushes have not been modified/repaired in accordance with 

the instructions of Airbus SB A320-57-1118, or Airbus SRM 57-26-13, or 

the identified Airbus Repair Instructions, as applicable, and 

- requires, for all aeroplanes on which Airbus SB A320-57-1118 has been 

embodied in service, or on which Airbus SRM 57-26-13 or the identified 

Airbus Repair Instructions have been applied, a repetitive inspection 

program of the MLG support Rib 5 fitting forward lugs and, depending on 

findings, the accomplishment of the associated corrective actions, and

- reduces the Applicability by deleting A318 aeroplanes.

Effective Date: 04 February 2011 

Required Action(s) 

and Compliance 

Time(s): 

Required as indicated, unless already accomplished: 

For the purpose of this AD : 

- “Action A” is defined as the modification of the MLG Rib Bushes in 

accordance with the instructions of Airbus SB A320-57-1118 at any 

revision 

- “Action B” is defined as the repair of the MLG Support Rib 5 fitting in 

accordance with: 

- Airbus A319 Structural Repair Manual (SRM) 57-26-13 paragraph 5.C 

or 

- Airbus A320/A321 SRM 57-26-13 paragraph 5.D, or 

- Airbus Repair Instruction R572-58376 at issue C. 

- “Action C” is defined as the replacement in service of the MLG Support 

Rib 5 in accordance with: 

- Airbus Repair Instructions R572-58507 and R572-58209, or 

- Airbus Repair Instructions R572-45020 and R572-45019. 

(1) Within the threshold indicated in Table 1 of this AD, as applicable, 

inspect the forward lug of each LH and RH MLG support Rib 5 fitting 

on which none of the actions, Action A, B or C as outlined above, 

has been performed, in accordance with the instructions of Airbus SB 

A320-57-1138 Revision 01. Thereafter, repeat the inspection at 

intervals not to exceed those defined in Paragraph 1.E.(2)(a)3 of 

Airbus SB A320-57-1138 Revision 01, as applicable. 

Table 1 – Inspection Threshold 

Aeroplane type(s) Compliance Time 

A319 and A320 

• within 150 flight cycles (FC) following the 

last visual inspection carried out in 

compliance with EASA AD 2007-0213, or 

• within 940 FC following the last ultrasonic 

inspection carried out in compliance with 

EASA AD 2007-0213, or 

• before next flight following a hard landing. 
EASA AD No.: 2011-0011 

EASA Form 110 Page 3/4 

A321 

• within 100 FC following the last visual 

inspection carried out in compliance with 

EASA AD 2007-0213, or 

• within 630 FC following the last ultrasonic 

inspection carried out in compliance with 

EASA AD 2007-0213, or 

• before next flight following a hard landing. 

(2) If, during any inspection as required by paragraph (1) of this AD, any 

discrepancy (as defined in Airbus SB A320-57-1138 Revision 01) is 

found, apply the associated corrective actions in accordance with the 

instructions and within the applicable compliance time, as defined in 

Paragraph 1.E.(2)(a)3 of Airbus SB A320-57-1138 Revision 01. 

(3) Except for aeroplanes on which LH and RH MLG Rib 5 fittings have 

been replaced in accordance with Action C, within 5 years after 21 

August 2007 [the effective date of EASA AD 2007-0213], modify the 

MLG Rib Bushes in accordance with the instructions of Airbus SB 

A320-57-1118 Revision 03 or a later approved revision. 

(4) Modification of a MLG Rib 5 support fitting as required by paragraph 

(3) of this AD constitutes terminating action for the inspection 

requirements of paragraph (1) of this AD for that MLG Rib 5 support 

fitting. 

(5) Within the threshold indicated in Table 2 of this AD, as applicable, 

perform a detailed visual inspection of the forward lug of each LH and 

RH MLG support rib 5 fitting on which one of the actions, Action A or 

B, has been performed, in accordance with the instructions of Airbus 

Alert SB A320-57A1166. Thereafter, repeat the inspection at intervals 

not to exceed 500 FC. 

Table 2 – Detailed visual inspection threshold 

Compliance Time - whichever occurs later:

• Within 2 000 FC after modification of the MLG support Rib 5 

fitting in accordance with Action A or as required by 

paragraph (3) of this AD, or after repair of the MLG support 

Rib 5 fitting in accordance with Action B, as applicable, 

or 

• Within 250 FC, without exceeding 3 months, after the 

effective date of this AD. 

(6) If, during any inspection as required by paragraph (5) of this AD, any 

discrepancy (as defined in Airbus Alert SB A320-57A1166) is found, 

before next flight, contact Airbus for approved corrective action 

instructions and accomplish those instructions accordingly. 

(7) Replacement of a MLG Support Rib 5 fitting at any position (LH or RH) 

in accordance with Action C constitutes terminating action for the 

inspection requirements of paragraph (1) or (5) of this AD, as 

applicable, for the MLG Support Rib 5 fitting at that position. 

Ref. Publications: Airbus SB A320-57-1118 Revision 03. 

Airbus SB A320-57-1138 Revision 01. 

Airbus Alert SB A320-57A1166 Original issue. 

Airbus Repair Instructions R572-58376 Issue C, R572-58507 Issue A, 

R572-58209 Issue A, R572-45020 Issue A and R572-45019 Issue A. 
EASA AD No.: 2011-0011 

EASA Form 110 Page 4/4 

The use of later approved revisions or issues of these documents is 

acceptable for compliance with the requirements of this AD. 

Remarks : 1. If requested and appropriately substantiated, EASA can approve 

Alternative Methods of Compliance for this AD. 

2. The required actions and the risk allowance have granted the issuance 

of a Final AD with Request for Comments, postponing the public 

consultation process after publication. 

3. Enquiries regarding this AD should be referred to the Airworthiness 

Directives, Safety Management & Research Section, Certification 

Directorate, EASA. E-mail ADs@easa.europa.eu 

4. For any question concerning the technical content of the requirements in 

this AD, please contact: AIRBUS – Airworthiness Office – EAS, 

Fax +33 5 61 93 44 51, E-mail: account.airworth-eas@airbus.com