46536 Federal Register / Vol. 78, No. 148 / Thursday, August 1, 2013 / Proposed Rules 

of the local flight standards district office/ 

certificate holding district office. 

(j) Related Information 

(1) For more information about this AD, 

contact Sue Lucier, Aerospace Engineer, 

Propulsion Branch, ANM–140S, 1601 Lind 

Avenue SW., Renton, Washington 98057– 

3352; phone: 425–917–6438; fax: 425–917– 

6590; email: suzanne.lucier@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 206–766–5280; 

Internet https://www.myboeingfleet.com. You 

may review copies of the referenced service 

information at the FAA, Transport Airplane 

Directorate, 1601 Lind Avenue SW., Renton, 

Washington. For information on the 

availability of this material at the FAA, call 

425–227–1221. 

Issued in Renton, Washington, on July 21, 

2013. 

Stephen P. Boyd, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2013–18511 Filed 7–31–13; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2013–0668; Directorate 

Identifier 2013–NM–017–AD] 

RIN 2120–AA64 

Airworthiness Directives; Airbus 

Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Notice of proposed rulemaking 

(NPRM). 

SUMMARY: We propose to adopt a new 

airworthiness directive (AD) for certain 

Airbus Model A300 B4–600 and A300 

B4–600R series airplanes. This proposed 

AD was prompted by reports of cracks 

found in the bottom wing skin stringers 

at rib 14 during full-scale fatigue testing 

and in service. This proposed AD would 

require modifying the profile of stringer 

run-outs at rib 14 of both wings, 

including a high frequency eddy current 

inspection of the fastener holes for 

defects and repair if necessary. We are 

proposing this AD to prevent cracking 

in the bottom wing skin stringers, which 

could result in reduced structural 

integrity of the wings. 

DATES: We must receive comments on 

this proposed AD by September 16, 

2013. 

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 review copies of the 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 

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–2013–0668; Directorate Identifier 

2013–NM–017–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 

The European Aviation Safety Agency 

(EASA), which is the Technical Agent 

for the Member States of the European 

Community, has issued EASA 

Airworthiness Directive 2013–0008R1, 

dated January 22, 2013 (referred to after 

this as the Mandatory Continuing 

Airworthiness Information, or ‘‘the 

MCAI’’), to correct an unsafe condition 

for the specified products. The MCAI 

states: 

During full-scale fatigue testing, cracks 

were detected in the bottom wing skin 

stringers at rib 14. In addition, A300 

aeroplane operators have also reported 

finding cracks in the same area. 

This condition, if not detected and 

corrected, could impair the structural 

integrity of the wings. 

Additional analysis results showed that the 

improved design of the stringer run-out is 

necessary for aeroplanes operating beyond 

the ESG 1 [extended service goal 1: 42,500 

flight cycles]. 

For the reasons described above, this 

[EASA] AD requires the removal of the 

stringer end run-out plate at stringer 19 on 

the bottom wing skin and the re-profiling 

modification of the stringers 10, 11, 12, 17 

and 19. 

* * * * * 

The modification also includes doing 

a high frequency eddy current 

inspection of the fastener holes for 

defects and repair if necessary. You may 

obtain further information by examining 

the MCAI in the AD docket. 

Relevant Service Information 

Airbus has issued Mandatory Service 

Bulletin A300–57–6046, Revision 01, 

dated April 18, 2011. 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 


emcdonald on DSK67QTVN1PROD with PROPOSALS
Federal Register / Vol. 78, No. 148 / Thursday, August 1, 2013 / Proposed Rules 46537 

condition exists and is likely to exist or 

develop on other products of the same 

type design. 

Differences Between This Proposed AD 

and the MCAI or Service Information 

Although Airbus Mandatory Service 

Bulletin A300–57–6046, Revision 01, 

dated April 18, 2011, specifies to 

contact the manufacturer for 

instructions to repair certain conditions, 

this proposed AD would require 

repairing those conditions using a 

method approved by either the Manager, 

International Branch, ANM–116, 

Transport Airplane Directorate, FAA; or 

the EASA (or its delegated agent). 

Costs of Compliance 

We estimate that this proposed AD 

affects 29 airplanes of U.S. registry. 

We estimate the following costs to 

comply with this proposed AD: 

ESTIMATED COSTS

Action Labor cost Parts cost Cost per 

product 

Cost on U.S. 

operators 

Modification of the profile of stringer run-outs.60 work-hours × $85 per hour = 

$5,100.

None ...................................... $5,100 $147,900 

We have received no definitive data 

that would enable us to provide cost 

estimates for any on-condition actions 

specified in this proposed AD. We have 

no way of determining the number of 

aircraft that might need this repair. 

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. 

We prepared a regulatory evaluation 

of the estimated costs to comply with 

this proposed AD and placed it in the 

AD docket. 

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 adding 

the following new AD: 

Airbus: Docket No. FAA–2013–0668; 

Directorate Identifier 2013–NM–017–AD. 

(a) Comments Due Date 

We must receive comments by September 

16, 2013. 

(b) Affected ADs 

None. 

(c) Applicability 

This AD applies to Airbus Model A300 B4– 

601, B4–603, B4–620, and B4–622 airplanes; 

and Airbus Model A300 B4–605R and B4– 

622R airplanes; certificated in any category, 

except airplanes on which Airbus 

Modification 10324 or 10325 has been 

embodied in production. 

(d) Subject 

Air Transport Association (ATA) of 

America Code 57, Wings. 

(e) Reason 

This AD was prompted by reports of cracks 

found in the bottom wing skin stringers at rib 

14 during full-scale fatigue testing and in 

service. We are issuing this AD to prevent 

cracking in the bottom wing skin stringers, 

which could result in reduced structural 

integrity of the wings. 

(f) Compliance 

You are responsible for having the actions 

required by this AD performed within the 

compliance times specified, unless the 

actions have already been done. 

(g) Modification of Rib 14 

Before the accumulation of 42,500 total 

flight cycles, or within 2,000 flight cycles 

after the effective date of this AD, whichever 

occurs later, modify the profile of stringer 

run-outs at rib 14 of both wings, including a 

high frequency eddy current inspection of 

the fastener holes for defects and all 

applicable repairs, in accordance with the 

Accomplishment Instructions of Airbus 

Mandatory Service Bulletin A300–57–6046, 

Revision 01, dated April 18, 2011, except as 

required by paragraph (h) of this AD. 

(h) Exception to the Service Information 

Where Airbus Mandatory Service Bulletin 

A300–57–6046, Revision 01, dated April 18, 

2011, specifies to report defects to Airbus, 

this AD requires contacting the Manager, 

ANM–116, International Branch, Transport 

Airplane Directorate, FAA, or the European 

Aviation Safety Agency (EASA) (or its 

delegated agent) for repair instructions and 

doing those repairs before further flight. 

(i) Credit for Previous Actions 

This paragraph provides credit for actions 

required by paragraph (g) of this AD, if those 

actions were performed before the effective 

date of this AD using Airbus Service Bulletin 

A300–57–6046, dated January 18, 1994 

(which is not incorporated by reference). 

(j) 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. 


emcdonald on DSK67QTVN1PROD with PROPOSALS
46538 Federal Register / Vol. 78, No. 148 / Thursday, August 1, 2013 / Proposed Rules 

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; 

telephone (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 standards district office/ 

certificate holding district office. The AMOC 

approval letter must specifically reference 

this AD. 

(2) Airworthy Product: For any requirement 

in this AD to obtain corrective actions from 

a manufacturer or other source, use these 

actions if they are FAA-approved. Corrective 

actions are considered FAA-approved if they 

are approved by the State of Design Authority 

(or their delegated agent). You are required 

to assure the product is airworthy before it 

is returned to service. 

(k) Related Information 

(1) Refer to Mandatory Continuing 

Airworthiness Information (MCAI) European 

Aviation Safety Agency (EASA) 

Airworthiness Directive 2013–0008R1, dated 

January 22, 2013, for related information. 

(2) For service information identified in 

this AD that is not incorporated by reference, 

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 review 

copies of 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 July 21, 

2013. 

Stephen P. Boyd, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2013–18556 Filed 7–31–13; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2013–0666; Directorate 

Identifier 2013–NM–060–AD] 

RIN 2120–AA64 

Airworthiness Directives; The Boeing 

Company Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Notice of proposed rulemaking 

(NPRM). 

SUMMARY: We propose to adopt a new 

airworthiness directive (AD) for all The 

Boeing Company Model 727 airplanes. 

This proposed AD was prompted by 

reports indicating that a standard fuel 

tank access door was located where an 

impact-resistant access door was 

required, and stencils were missing 

from some impact-resistant access 

doors. This proposed AD would require 

an inspection of the left- and right-hand 

wing fuel tank access doors to 

determine that impact-resistant access 

doors are installed in the correct 

locations, and to replace any door with 

an impact-resistant access door if 

necessary. This proposed AD also 

would require an inspection for stencils 

and index markers on impact-resistant 

access doors, and application of new 

stencils or index markers if necessary. 

This proposed AD would also require 

revising the maintenance program to 

incorporate changes to the airworthiness 

limitations section. We are proposing 

this AD to prevent foreign object 

penetration of the fuel tank, which 

could cause a fuel leak near an ignition 

source (e.g., hot brakes), consequently 

leading to a fuel-fed fire. 

DATES: We must receive comments on 

this proposed AD by September 16, 

2013. 

ADDRESSES: You may send comments, 

using the procedures found in 14 CFR 

11.43 and 11.45, 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: Deliver to Mail 

address above between 9 a.m. and 5 

p.m., Monday through Friday, except 

Federal holidays. 

For service information identified in 

this proposed 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 

review copies of the 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 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 Office 

(phone: 800–647–5527) is in the 

ADDRESSES section. Comments will be 

available in the AD docket shortly after 

receipt. 

FOR FURTHER INFORMATION CONTACT: 

Suzanne Lucier, Aerospace Engineer, 

Propulsion Branch, ANM–140S, FAA, 

Seattle Aircraft Certification Office, 

1601 Lind Avenue SW., Renton, WA 

98057–3356; phone: 425–917–6438; fax: 

425–917–6590; email: 

suzanne.lucier@faa.gov. 

SUPPLEMENTARY INFORMATION: 

Comments Invited 

We invite you to send any written 

relevant data, views, or arguments about 

this proposal. Send your comments to 

an address listed under the ADDRESSES

section. Include ‘‘Docket No. FAA– 

2013–0666; Directorate Identifier 2013– 

NM–060–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 because of 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 

We received reports of a standard fuel 

tank access door located where an 

impact-resistant access door is required, 

and stencils missing from some spare 

impact-resistant access doors. This 

condition, if not corrected, could result 

in foreign object penetration of the fuel 

tank, which could cause a fuel leak near 

an ignition source (e.g., hot brakes), 

consequently leading to a fuel-fed fire. 

Relevant Service Information 

We reviewed Boeing Service Bulletin 

727–28–0134, dated January 12, 2012; 

and Critical Design Configuration 

Control Limitation (CDCCL) Task 57– 

AWL–01, ‘‘Impact-Resistant Fuel Tank 

Access Door,’’ of Section 1, 

Airworthiness Limitations (AWLs) of 

Boeing 727–100/200 Airworthiness 

Limitations (AWLs) Document D6– 


emcdonald on DSK67QTVN1PROD with PROPOSALS