## 13938 Federal Register / Vol. 79, No. 48 / Wednesday, March 12, 2014 / Proposed Rules

130S, Seattle Aircraft Certification Office, 1601 Lind Avenue SW., Renton, WA 98057– 3356; phone: (425) 917–6418; fax: (425) 917– 6590; email: marie.hogestad@faa.gov

.

(2) For service information identified in this AD, contact Boeing Commercial Airplanes, Attention: Data & Services Management, P.O. Box 3707, MC 2H–65, Seattle, WA 98124–2207; telephone 206– 544–5000, extension 1; fax 206–766–5680;

Internet https://www.myboeingfleet.com. You may view this referenced service information at the FAA, Transport Airplane Directorate, 1601 Lind Avenue SW., Renton, WA 98057– 3356. For information on the availability of this material at the FAA, call 425–227–1221.

Issued in Renton, Washington, on February

28, 2014. Jeffrey E. Duven, Manager, Transport Airplane Directorate, Aircraft Certification Service.

[FR Doc. 2014–05426 Filed 3–11–14; 8:45 am]

**BILLING CODE 4910–13–P**



### DEPARTMENT OF TRANSPORTATION

**Federal Aviation Administration**

**14 CFR Part 39**

**[Docket No. FAA–2014–0142; Directorate Identifier 2012–NM–161–AD]** 

**RIN 2120–AA64**



### Airworthiness Directives; Airbus **Airplanes**

**AGENCY** 

### : Federal Aviation Administration (FAA), DOT.

**ACTION** 

### : Notice of proposed rulemaking (NPRM).

**SUMMARY** 

### : We propose to supersede Airworthiness Directive (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 C4– 605R Variant F airplanes (collectively called A300–600 series airplanes); and Model A310 series airplanes. AD 2008– 17–02, AD 2012–08–03, and AD 2012– 15–14 currently require 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 righthand (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. Since we issued AD 2008–17–02, AD 2012–08–03, and AD 2012–15–14, we have received two reports of ruptured MLG rib 5 forward lugs that had been modified (bushes with increased interference fit). This proposed AD would add airplanes to the applicability; and would add, for certain airplanes, repetitive inspections of the MLG rib 5 aft bearing forward lugs, and repair if necessary. We are proposing 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.

**DATES** 

### : We must receive comments on this proposed AD by April 28, 2014.

**ADDRESSES** 

### : You may send comments by any of the following methods:

• Federal eRulemaking Portal: Go to http://www.regulations.gov. Follow the instructions for submitting comments.

• Fax: (202) 493–2251.

• Mail: U.S. Department of Transportation, Docket Operations, M– 30, West Building Ground Floor, Room W12–140, 1200 New Jersey Avenue SE., Washington, DC 20590.

• Hand Delivery: U.S. Department of Transportation, Docket Operations, M– 30, West Building Ground Floor, Room W12–140, 1200 New Jersey Avenue SE., Washington, DC, between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays.

For service information identified in this proposed AD, contact Airbus SAS— Airworthiness Office—EAL, 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex, France; telephone +33 5 61 93 36 96; fax +33 5 61 93 45 80; email airworthiness.A330–A340@airbus.com;

Internet http://www.airbus.com. You may view this referenced service information at the FAA, Transport Airplane Directorate, 1601 Lind Avenue SW., Renton, WA. For information on the availability of this material at the FAA, call 425–227–1221.

Examining the AD Docket

You may examine the AD docket on
the Internet at http:// www.regulations.gov by searching for and locating Docket No. FAA–2014– 0142; or in person at the Docket Management Facility between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. The AD docket contains this proposed AD, the regulatory evaluation, any comments received, and other information. The street address for the Docket Operations office (telephone (800) 647–5527) is in
the **ADDRESSES** 

### section. Comments will be available in the AD docket shortly after receipt.

**FOR FURTHER INFORMATION CONTACT** 

### : Dan Rodina, Aerospace Engineer, International Branch, ANM–116, Transport Airplane Directorate, FAA, 1601 Lind Avenue SW., Renton, WA 98057–3356; telephone (425) 227–2125; fax (425) 227–1149. **SUPPLEMENTARY INFORMATION** 

### :

Comments Invited

We invite you to send any written relevant data, views, or arguments about this proposed AD. Send your comments
to an address listed under the

**ADDRESSES** 

### section. Include ‘‘Docket No. FAA–2014–0142; Directorate Identifier 2012–NM–161–AD’’ at the beginning of your comments. We specifically invite comments on the overall regulatory, economic, environmental, and energy aspects of this proposed AD. We will consider all comments received by the closing date and may amend this proposed AD based on those comments.

We will post all comments we receive, without change, to http:// www.regulations.gov, including any personal information you provide. We will also post a report summarizing each
substantive verbal contact we receive about this proposed AD.

Discussion

On July 31, 2008, we issued AD 2008– 17–02, Amendment 39–15640 (73 FR 47032, August 13, 2008), for certain Model A310 airplanes.

On April 5, 2012, we issued AD 2012– 08–03, Amendment 39–17019 (77 FR 24367, April 24, 2012), for certain Model A300 B4–2C, B4–103, B4–203,
B4–601, B4–603, B4–620, B4–622, B4– 605R, B4–622R, F4–605R, F4–622R, C4– 605R Variant F airplanes; and Model
A310–203, –204, 221, –222, –304, –322, –324, and –325 airplanes.

On July 23, 2012, we issued AD 2012– 15–14, Amendment 39–17143 (77 FR 46937, August 7, 2012), for certain Model A300 B4–2C, B4–103, B4–203,
B4–601, B4–603, B4–620, B4–622, B4– 605R, B4–622R, F4–605R, and F4–622R, and C4–605R Variant F airplanes.

AD 2008–17–02, Amendment 39– 15640 (73 FR 47032, August 13, 2008); AD 2012–08–03, Amendment 39–17019 (77 FR 24367, April 24, 2012); and AD 2012–15–14, Amendment 39–17143 (77 FR 46937, August 7, 2012); require
actions intended to address an unsafe condition on the products listed above.

Since we issued AD 2008–17–02, Amendment 39–15640 (73 FR 47032, August 13, 2008); AD 2012–08–03, Amendment 39–17019 (77 FR 24367, April 24, 2012); and AD 2012–15–14, Amendment 39–17143 (77 FR 46937, August 7, 2012); the European Aviation Safety Agency (EASA), which is the Technical Agent for the Member States of the European Community, has issued
EASA Airworthiness Directive 2012– 0176, dated September 7, 2012, corrected September 20, 2012 (referred to after this as the Mandatory Continuing Airworthiness Information,


## 13939 Federal Register / Vol. 79, No. 48 / Wednesday, March 12, 2014 / Proposed Rules

or ‘‘the MCAI’’), to correct an unsafe condition for the specified products.
The MCAI states:

Several cases of corrosion of the Main Landing Gear (MLG) Rib 5 aft fitting forward lug have been reported on A310 family aeroplanes. In some instances, corrosion pits caused the cracking of the forward lug.

This condition, if not detected and corrected, may lead to the complete failure of the fitting and thus could affect the structural integrity of the MLG installation.

EASA ADs 2006–0372R1 ( http:// ad.easa.europa.eu/blob/easa

_ ad

_ 2006

_ 0372

_ R1

_ superseeded.pdf/AD

_ 2006-0372R1

_ 1 ), 2007–0195 ( http://ad.easa.europa.eu/blob/

easa

_ ad

_ 2007

_ 0195

_ superseded.pdf/AD

_ 2007-0195

_ 1 ) [which corresponds with FAA AD 2008–17–02, Amendment 39–15640 (73 FR 47032, August 13, 2008), 2010–0250 ( http://ad.easa.europa.eu/blob/easa

_ ad

_ 2010

_ 0250

_ superseded.pdf/AD

_ 2010-0250

_ 1 ) [which corresponds with FAA AD 2012– 15–14, Amendment 39–17143 (77 FR 46937, August 7, 2012)] and 2010–0251 ( http:// ad.easa.europa.eu/blob/easa

_ ad

_ 2010

_ 0251

_ superseded.pdf/AD

_ 2010-0251

_ 1 ) [which corresponds with FAA AD 2012–08–03, Amendment 39–17019 (77 FR 24367, April 24, 2012)] were issued to address this condition and required a repetitive inspection programme of the MLG Rib 5 fitting forward lugs and, as terminating action, the embodiment of mandatory design change (bushes with increased interference fit).

MLG Rib 5 forward lug on A320 family aeroplanes is a similar design to the A300/ A300–600/A310 family. Since those [EASA] ADs were issued, on two A321 aeroplanes, post modification (bushes with increased interference fit) MLG Rib 5 forward lugs were reportedly found ruptured.

One other case was due to a sealant discrepancy that led to water ingress and consequently corrosion initiation, leading to cracking. Subsequent investigation results have shown that a remaining defect, not removed during the repair, had propagated, resulting in rupture of the lug.

For the reasons stated above, this new [EASA] AD retains the requirements of EASA ADs 2006–0372R1, 2007–0195, 2010–0250 and 2010–0251, which are superseded, expands the applicability to all models and series of A300, A310, A300–600 and A300– 600ST aeroplanes, and requires: —for aeroplanes not yet modified or repaired,

implementation of Modification Service Bulletin (SB) A300–57–0249, A310–57–
2090, A300–57–6106, or A300–57–9019, all at Revision 3, and —for aeroplanes which already embody that

modifications, at original issue or revision 01 or 02 of the applicable SB, or have MLG Ribs already repaired in accordance with Airbus repair instruction R57240221 or R57249121, implementation of an additional inspection programme [repetitive detailed inspection for cracking or ultrasonic inspections for any crack indication] and associated corrective action(s) [detailed inspection for cracking if any crack indication found, and repair]. 

### The unsafe condition is 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. You may
examine the MCAI in the AD docket on
the Internet at http:// www.regulations.gov by searching for and locating it in Docket No. FAA–

2014–0142.

Relevant Service Information

Airbus has issued the following
service information.

• Airbus Alert Service Bulletin A300– 57A0248, dated December 12, 2006;

• Airbus Service Bulletin A300–57– 0255, dated January 13, 2012;

• Airbus Service Bulletin A300–57– 6112, dated January 13, 2012;

• Airbus Service Bulletin A310–57– 2101, dated January 13, 2012.

The actions described in this service
information are intended to correct the
unsafe condition identified in the

MCAI.

FAA’s Determination and Requirements of This Proposed AD

This product has been approved by the aviation authority of another country, and is approved for operation
in the United States. Pursuant to our bilateral agreement with the State of Design Authority, we have been notified
of the unsafe condition described in the
MCAI and service information referenced above. We are proposing this AD because we evaluated all pertinent
information and determined an unsafe condition exists and is likely to exist or develop on other products of the same type design.

In many FAA transport ADs, when the service information specifies to
contact the manufacturer for further instructions if certain discrepancies are found, we typically include in the AD a requirement to accomplish the action using a method approved by either the FAA or the State of Design Authority (or its delegated agent).

We have recently been notified that
certain laws in other countries do not allow such delegation of authority, but some countries do recognize design approval organizations. In addition, we
have become aware that some U.S. operators have used repair instructions that were previously approved by a State of Design Authority or a Design Approval Holder (DAH) as a method of compliance with this provision in FAA ADs. Frequently, in these cases, the previously approved repair instructions come from the airplane structural repair manual or the DAH repair approval statements that were not specifically developed to address the unsafe condition corrected by the AD. Using repair instructions that were not specifically approved for a particular AD creates the potential for doing repairs that were not developed to
address the unsafe condition identified by the MCAI AD, the FAA AD, or the applicable service information, which
could result in the unsafe condition not being fully corrected.

To prevent the use of repairs that were not specifically developed to correct the unsafe condition, certain requirements of this proposed AD specify that the repair approval specifically refer to the FAA AD. This change is intended to clarify the method of compliance and to provide operators with better visibility of repairs that are specifically developed and approved to
correct the unsafe condition. In addition, we use the phrase ‘‘its delegated agent, or the DAH with State of Design Authority design organization approval, as applicable’’ in this proposed AD to refer to a DAH authorized to approve certain required repairs for this proposed AD.

Costs of Compliance

We estimate that this proposed AD affects 194 airplanes of U.S. registry.

The actions that are required by AD 2008–17–02, Amendment 39–15640 (73 FR 47032, August 13, 2008), and retained in this proposed AD take about 5 work-hours per product, at an average labor rate of $85 per work-hour. Based on these figures, the estimated cost of the actions that were required by AD 2008–17–02 is $425 per product.

The actions that are required by AD 2012–08–03, Amendment 39–17019 (77 FR 24367, April 24, 2012), and retainedin this proposed AD take about 38 workhours per product, at an average labor rate of $85 per work-hour. Required parts cost about $4,590 per product. Based on these figures, the estimated cost of the actions that were required by AD 2012–08–03 is $7,820 per product.

The actions that are required by AD 2012–15–14, Amendment 39–17143 (77 FR 46937, August 7, 2012), and retainedin this proposed AD take about 3 workhours per product, at an average labor rate of $85 per work-hour. Based on these figures, the estimated cost of the actions that were required by AD 2012– 15–14 is $255 per product.

We also estimate that it would take about 3 work-hours per product to comply with the basic requirements of this proposed AD. The average labor rate is $85 per work-hour. Based on these figures, we estimate the cost of this proposed AD on U.S. operators to be $49,470, or $255 per product.


## 13940 Federal Register / Vol. 79, No. 48 / Wednesday, March 12, 2014 / Proposed Rules

We have received no definitive data that would enable us to provide cost
estimates for the on-condition actions specified in this proposed AD. We have no way of determining the number of products that may need these actions.

According to the manufacturer, some of the costs of this proposed AD may be covered under warranty, thereby reducing the cost impact on affected individuals. We do not control warranty coverage for affected individuals. As a result, we have included all costs in our

cost estimate.

Paperwork Reduction Act

A federal agency may not conduct or sponsor, and a person is not required to respond to, nor shall a person be subject to penalty for failure to comply with a collection of information subject to the requirements of the Paperwork
Reduction Act unless that collection of information displays a current valid
OMB control number. The control
number for the collection of information required by this AD is 2120–0056. The paperwork cost associated with this AD
has been detailed in the Costs of Compliance section of this document and includes time for reviewing instructions, as well as completing and reviewing the collection of information. Therefore, all reporting associated with this AD is mandatory. Comments concerning the accuracy of this burden and suggestions for reducing the burden
should be directed to the FAA at 800 Independence Ave. SW., Washington, DC 20591, ATTN: Information Collection Clearance Officer, AES–200.

Authority for This Rulemaking

Title 49 of the United States Code specifies the FAA’s authority to issue rules on aviation safety. Subtitle I, section 106, describes the authority of
the FAA Administrator. ‘‘Subtitle VII: Aviation Programs,’’ describes in more detail the scope of the Agency’s authority.

We are issuing this rulemaking under the authority described in ‘‘Subtitle VII, Part A, Subpart III, Section 44701: General requirements.’’ Under that section, Congress charges the FAA with promoting safe flight of civil aircraft in air commerce by prescribing regulations for practices, methods, and procedures the Administrator finds necessary for safety in air commerce. This regulation is within the scope of that authority
because it addresses an unsafe condition that is likely to exist or develop on products identified in this rulemaking

action. Regulatory Findings
We determined that this proposed AD would not have federalism implications
under Executive Order 13132. This proposed AD would not have a substantial direct effect on the States, on the relationship between the national Government and the States, or on the distribution of power and responsibilities among the various levels of government.

For the reasons discussed above, I certify this proposed regulation:

1. Is not a ‘‘significant regulatory action’’ under Executive Order 12866;

2. Is not a ‘‘significant rule’’ under the DOT Regulatory Policies and Procedures (44 FR 11034, February 26, 1979);

3. Will not affect intrastate aviation in Alaska; and

4. Will not have a significant economic impact, positive or negative,
on a substantial number of small entities under the criteria of the Regulatory Flexibility Act.

List of Subjects in 14 CFR Part 39

Air transportation, Aircraft, Aviation safety, Incorporation by reference, Safety.

The Proposed Amendment

Accordingly, under the authority delegated to me by the Administrator, the FAA proposes to amend 14 CFR part
39 as follows:

**PART 39—AIRWORTHINESS**
**DIRECTIVES**

■ 

### 1. The authority citation for part 39
continues to read as follows:

Authority: 49 U.S.C. 106(g), 40113, 44701.

**§ 39.13 [Amended]**

■ 

### 2. The FAA amends § 39.13 by:

■ 

### a. Removing Airworthiness Directives (AD) 2008–17–02, Amendment 39– 15640 (73 FR 47032, August 13, 2008); AD 2012–08–03, Amendment 39–17019 (77 FR 24367, April 24, 2012); and AD 2012–15–14, Amendment 39–17143 (77 FR 46937, August 7, 2012); and

■ 

### b. Adding the following new AD:

Airbus: Docket No. FAA–2013–0142;
Directorate Identifier 2012–NM–161–AD.

(a) Comments Due Date

We must receive comments by April 28,

2014.

(b) Affected ADs

(1) This AD supersedes the ADs specified in paragraphs (b)(1)(i), (b)(1)(ii), and (b)(1)(iii)
of this AD.

(i) AD 2008–17–02, Amendment 39–15640 (73 FR 47032, August 13, 2008).

(ii) AD 2012–08–03, Amendment 39–17019 (77 FR 24367, April 24, 2012).

(iii) AD 2012–15–14, Amendment 39– 17143 (77 FR 46937, August 7, 2012). (2) This AD affects AD 2007–03–18, Amendment 39–14929 (72 FR 5919, February 8, 2007).

(c) Applicability

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.

(d) Subject

Air Transport Association (ATA) of America Code 57, Wings.

(e) Reason

This AD was prompted by reports of cracking in the forward lug of the main landing gear (MLG) rib 5 aft bearing attachment. We are issuing this AD to detect and correct cracking of the forward lugs ofthe aft bearing at rib 5 of the MLG on the lefthand (LH) and right-hand (RH) wings, which could affect the structural integrity of the MLG attachment, resulting in possible MLG collapse during landing or rollout.

(f) Compliance

Comply with this AD within the compliance times specified, unless already
done.

(g) Retained Repetitive Detailed Inspection
and Corrective Actions

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.

(h) Retained Actions and Compliance

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


## 13941 Federal Register / Vol. 79, No. 48 / Wednesday, March 12, 2014 / Proposed Rules

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) 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.

(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 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 Service Bulletin A310–57–2090, Revision 02, dated June 18, 2010.

(iii) Airbus 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. 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. As of the effective date of this AD, use only Airbus Service Bulletin A310–57–2090, Revision 03, dated January 23, 2012, for the actions specified in this paragraph.

(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 paragraph (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. 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.

(i) Retained Installation

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).

(j) Affected Airplanes for the Actions Required by Paragraph (i) of This AD

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 Mandatory 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 Mandatory Service Bulletin
A310–57–2090 embodied in service.

(k) Retained Exception

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 R57249121, 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.

(l) Retained Terminating Action for Certain Inspections

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.

(m) Retained Repetitive Inspections

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,


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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.

(n) Affected Airplanes for the Actions Required by Paragraph (m) of This AD

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 Mandatory
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 Mandatory Service Bulletin
A300–57–6106 has been done in service on the LH and RH wings.

(o) Retained Exception

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, Amendment 39–17143 (77 FR 46937, August 7, 2012)): 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.

(p) Retained Repair

This paragraph restates the requirements of paragraph (i) of AD 2012–15–14, Amendment 39–17143 (77 FR 46937, August 7, 2012). 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 European Aviation Safety Agency (EASA) (or its delegated agent, or the Design Approval Holder with EASA’s design organization approval, as applicable).

(q) Retained Optional Terminating
Modification

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 the EASA (or its delegated agent, or the Design Approval Holder with EASA’s design organization approval, as applicable).

(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).

(r) Retained Terminating Action for AD 2007–03–18, Amendment 39–14929 (72 FR 5919, February 8, 2007)

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. (s) Retained Reporting
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, 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.

(t) New Repetitive Inspections

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 Mandatory Service Bulletin A300–57–0255, dated January 13, 2012 (for Model A300 B2–1A, B2–1C, B2K–3C, and B2–203 airplanes).

(2) Airbus Mandatory Service Bulletin A300–57–6112, 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 Mandatory Service Bulletin A310–57–2101, dated January 13, 2012 (for Model A310–203, –204, –221, –222, –304, –322, –324, and –325 airplanes).

(u) Affected Airplanes for the Actions Required by Paragraph (t) of This AD

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 R57249121, 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


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Repair Instruction R57240221 or R57249121, 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 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 Airbus Service Bulletin A300–57–6106 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 Airbus Service Bulletin A310–57–2090 Revision 02, dated June 18, 2010 (for Model A310 series airplanes).

(v) Compliance Times for Paragraph (t) of
This AD

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.

(w) New Requirement of This AD: Report and Detailed Inspection

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. (x) New Requirement of This AD: Cracking Repair

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 its delegated agent, or the Design Approval Holder with the EASA design organization approval, as applicable). For a repair method to be approved, the repair approval must specifically refer to this AD.

(y) New Requirement of This AD: Reporting

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 Mandatory Service Bulletin A300–57–0255, dated January 13, 2012 (for Model A300 B2–1A, B2–1C, B2K–3C, and B2–203 airplanes).

(2) Airbus Mandatory Service Bulletin A300–57–6112, 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 Mandatory Service Bulletin A310–57–2101, dated January 13, 2012 (for Model A310–203, –204, –221, –222, –304, –322, –324, and –325 airplanes).

(z) Credit for Previous Actions

(1) This paragraph provides credit for actions required by paragraph (i) of this AD, if those actions were performed before May 29, 2012 (the effective date of AD 2012–08– 03, Amendment 39–17019 (77 FR 24367, April 24, 2012)), using an applicable service bulletin specified in paragraph (z)(1)(i), (z)(1)(ii), or (z)(1)(iii) of this AD.

(i) For Model A300 B4–2C, B4–103, and B4–203 airplanes: The service bulletins are specified in paragraphs (z)(1)(i)(A), (z)(1)(i)(B), and (z)(1)(i)(C) of this AD.

(A) Airbus Service Bulletin A300–57–0249, dated May 22, 2007, which is not incorporated by reference in this AD.

(B) Airbus Service Bulletin A300–57–0249, Revision 01, dated December 19, 2007, which is not incorporated by reference in this AD.

(C) Airbus Mandatory Service Bulletin A300–57–0249, Revision 02, dated June 18,

2010.

(ii) For Model A300–600 series airplanes: The service bulletins are specified in paragraphs (z)(1)(ii)(A), (z)(1)(ii)(B), and (z)(1)(ii)(C) of this AD.

(A) Airbus Service Bulletin A300–57–6106, May 22, 2007, which is not incorporated by
reference in this AD.

(B) Airbus Service Bulletin A300–57–6106, Revision 01, January 28, 2008, which is not incorporated by reference in this AD. (C) Airbus Service Bulletin A300–57–6106, Revision 02, dated June 18, 2010, which is not incorporated by reference in this AD.

(iii) For Model A310 series airplanes: The service bulletins are specified in paragraphs (z)(1)(iii)(A), (z)(1)(iii)(B), and (z)(1)(iii)(C) of
this AD.

(A) Airbus Service Bulletin A310–57–2090, dated May 22, 2007, which is not incorporated by reference in this AD.

(B) Airbus Service Bulletin A310–57–2090, Revision 01, dated December 19, 2007.

(C) Airbus Service Bulletin A310–57–2090, Revision 02, dated June 18, 2010, which is not incorporated by reference in this AD.

(2) This paragraph provides credit for actions required by paragraph (q) of this AD, if those actions were performed before September 11, 2012 (the effective date of AD 2012–15–14, Amendment 39–17143 (77 FR 46937, August 7, 2012)), using an applicable service bulletin specified in paragraphs (z)(2)(i), (z)(2)(ii), (z)(2)(iii), (z)(2)(iv), and (z)(2)(v) of this AD.

(i) For Model A300 B4–2C, B4–103, and
B4–203: Airbus Service Bulletin A300–57– 0249, dated May 22, 2007, which is not incorporated by reference in this AD.

(ii) For Model A300 B4–2C, B4–103, and
B4–203: Airbus Service Bulletin A300–57– 0249, Revision 01, dated December 19, 2007, which is not incorporated by reference in this

AD.

(iii) 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: Airbus Service Bulletin A300–57–6106, dated May 22, 2007, which is not incorporated by reference in this AD.

(iv) 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: Airbus Service Bulletin A300–57–6106, Revision 01, dated January 28, 2008, which is not incorporated by reference in this AD.

(v) 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: Airbus Service Bulletin A300–57–6106, Revision 02, dated June 18, 2010 which is not incorporated by reference in this AD.

(aa) Other FAA AD Provisions

The following provisions also apply to this

AD:

(1) Alternative Methods of Compliance (AMOCs): The Manager, International Branch. ANM–116, Transport Airplane Directorate, FAA, has the authority to approve AMOCs for this AD, if requested using the procedures found in 14 CFR 39.19. In accordance with 14 CFR 39.19, send your request to your principal inspector or local Flight Standards District Office, as appropriate. If sending information directly to the International Branch, send it to ATTN: Dan Rodina, Aerospace Engineer, International Branch, ANM–116, Transport Airplane Directorate, FAA, 1601 Lind Avenue SW., Renton, WA 98057–3356; phone (425) 227–2125; fax (425) 227–1149. Information may be emailed to: 9-ANM-116- AMOC-REQUESTS@faa.gov. Before using any approved AMOC, notify your appropriate principal inspector, or lacking a principal inspector, the manager of the local flight


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standards district office/certificate holding district office. The AMOC approval letter must specifically reference this AD.

(i) AMOCs approved previously for AD 2008–17–02, Amendment 39–15640 (73 FR 47032, August 13, 2008), are approved as AMOCs for the corresponding provisions of paragraphs (g) and (h) of this AD.

(ii) AMOCs approved previously for AD 2012–08–03, Amendment 39–17019 (77 FR 24367, April 24, 2012), are approved as AMOCs for the corresponding provisions of paragraphs (i), (j), and (k) of this AD.

(iii) AMOCs approved previously for AD 2012–15–14, Amendment 39–17143 (77 FR 46937, August 7, 2012), are approved as AMOCs for the corresponding provisions of paragraphs (l), (m), (n), and (o) of this AD.

(2) Airworthy Product: For any requirement
in this AD to obtain corrective actions from a manufacturer, use these actions if they are FAA-approved. Corrective actions are considered FAA-approved if they were approved by the State of Design Authority (or its delegated agent, or the Design Approval Holder with a State of Design Authority’s design organization approval, as applicable). You are required to ensure the product is airworthy before it is returned to service.

(3) Reporting Requirements: A federal agency may not conduct or sponsor, and a person is not required to respond to, nor shall a person be subject to a penalty for failure to comply with a collection of information subject to the requirements of the Paperwork Reduction Act unless that collection of information displays a current
valid OMB Control Number. The OMB
Control Number for this information collection is 2120–0056. Public reporting for
this collection of information is estimated to be approximately 5 minutes per response, including the time for reviewing instructions, completing and reviewing the collection of information. All responses to this collection of information are mandatory. Comments concerning the accuracy of this burden and suggestions for reducing the burden should be directed to the FAA at: 800 Independence Ave. SW., Washington, DC 20591, Attn: Information Collection Clearance Officer,

AES–200.

(bb) Related Information

(1) Refer to Mandatory Continuing Airworthiness Information (MCAI) European Aviation Safety Agency Airworthiness Directive 2012–0176, dated September 7, 2012, corrected September 20, 2012, for related information. This MCAI may be
found in the AD docket on the Internet at http://www.regulations.gov by searching for and locating Docket No. FAA–2014–0142.

(2) For service information identified in this AD, contact Airbus SAS—Airworthiness Office—EAL, 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex, France; telephone +33 5 61 93 36 96; fax +33 5 61 93 45 80; email airworthiness.A330-A340@airbus.com;

Internet http://www.airbus.com. You may view this service information at the FAA, Transport Airplane Directorate, 1601 Lind Avenue SW., Renton, WA. For information on the availability of this material at the FAA, call 425–227–1221. Issued in Renton, Washington, on March 4,

2014. Michael J. Kaszycki, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service.

[FR Doc. 2014–05435 Filed 3–11–14; 8:45 am]

**BILLING CODE 4910–13–P**



### DEPARTMENT OF TRANSPORTATION

**Federal Aviation Administration**

**14 CFR Part 39**

**[Docket No. FAA–2014–0138; Directorate Identifier 2013–NM–020–AD]** 

**RIN 2120–AA64**



### Airworthiness Directives; Airbus **Airplanes**

**AGENCY** 

### : Federal Aviation Administration (FAA), DOT.

**ACTION** 

### : Notice of proposed rulemaking (NPRM).

**SUMMARY** 

### : We propose to supersede airworthiness directive (AD) 95–24–04, that applies to all Airbus Model A300 series 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). AD 95–24– 04 requires repetitive inspections to detect cracks at the aft spar web of the wings, and repair if necessary. Since we issued AD 95–24–04, we have determined that the inspection
threshold and interval must be reduced to allow timely detection of cracks and accomplishment of applicable repairs, because of cracking in the rear spar web of the wings between certain ribs due to fatigue-related high shear stress. This proposed AD would reduce the inspection compliance time and interval, and would expand the applicability to airplanes on which a
certain Airbus modification has been embodied in production and to airplanes on which a certain Airbus
service bulletin has been embodied in service. We are proposing this AD to detect and correct fatigue-related cracking, which could result in reduced structural integrity of the wing.

**DATES** 

### : We must receive comments on this proposed AD by April 28, 2014.

**ADDRESSES** 

### : You may send comments by any of the following methods:

• Federal eRulemaking Portal: Go to http://www.regulations.gov. Follow the instructions for submitting comments.

• Fax: (202) 493–2251.

• Mail: U.S. Department of Transportation, Docket Operations, M– 30, West Building Ground Floor, Room W12–140, 1200 New Jersey Avenue SE., Washington, DC 20590.

• Hand Delivery: U.S. Department of Transportation, Docket Operations, M– 30, West Building Ground Floor, Room W12–140, 1200 New Jersey Avenue SE., Washington, DC, between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays.

For service information identified in this proposed AD, contact Airbus SAS, Airworthiness Office—EAW, 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex, France; telephone +33 5 61 93 36 96; fax +33 5 61 93 44 51; email
account.airworth-eas@airbus.com ; Internet http://www.airbus.com . You may view this referenced service information at the FAA, Transport Airplane Directorate, 1601 Lind Avenue SW., Renton, WA. For information on the availability of this material at the FAA, call 425–227–1221.

Examining the AD Docket

You may examine the AD docket on
the Internet at http:// www.regulations.gov; or in person at the Docket Operations office between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. The AD docket contains this proposed AD, the MCAI, the regulatory evaluation, any comments received, and other
information. The street address for the Docket Operations office (telephone (800) 647–5527) is in the **ADDRESSES** 

### section. Comments will be available in the AD docket shortly after receipt.

**FOR FURTHER INFORMATION CONTACT** 

### : Dan Rodina, Aerospace Engineer, International Branch, ANM–116, Transport Airplane Directorate, FAA, 1601 Lind Avenue SW., Renton, WA 98057–3356; telephone (425) 227–2125; fax (425) 227–1149.

**SUPPLEMENTARY INFORMATION** 

### :

Comments Invited

We invite you to send any written relevant data, views, or arguments about this proposed AD. Send your comments
to an address listed under the

**ADDRESSES** 

### section. Include ‘‘Docket No. FAA–2014–0138; Directorate Identifier 2013–NM–020–AD’’ at the beginning of your comments. We specifically invite comments on the overall regulatory, economic, environmental, and energy aspects of this proposed AD. We will consider all comments received by the closing date and may amend this proposed AD based on those comments.

We will post all comments we receive, without change, to http:// www.regulations.gov, including any personal information you provide. We will also post a report summarizing each