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, 


tkelley on DSK3SPTVN1PROD with PROPOSALS
Federal Register / Vol. 79, No. 48 / Wednesday, March 12, 2014 / Proposed Rules 13939 

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 retained 

in 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 retained 

in 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. 


tkelley on DSK3SPTVN1PROD with PROPOSALS
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 of 

the 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 


tkelley on DSK3SPTVN1PROD with PROPOSALS
Federal Register / Vol. 79, No. 48 / Wednesday, March 12, 2014 / Proposed Rules 13941 

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, 


tkelley on DSK3SPTVN1PROD with PROPOSALS
13942 Federal Register / Vol. 79, No. 48 / Wednesday, March 12, 2014 / Proposed Rules 

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 


tkelley on DSK3SPTVN1PROD with PROPOSALS
Federal Register / Vol. 79, No. 48 / Wednesday, March 12, 2014 / Proposed Rules 13943 

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 


tkelley on DSK3SPTVN1PROD with PROPOSALS
13944 Federal Register / Vol. 79, No. 48 / Wednesday, March 12, 2014 / Proposed Rules 

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 


tkelley on DSK3SPTVN1PROD with PROPOSALS