Federal Register / Vol. 78, No. 159 / Friday, August 16, 2013 / Rules and Regulations 49915 

(ii) Reserved. 

(3) For Boeing 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. 

(4) You may view this service information 

at FAA, Transport Airplane Directorate, 1601 

Lind Avenue SW., Renton, Washington 

98057–3356. For information on the 

availability of this material at the FAA, call 

425–227–1221. 

(5) You may view this service information 

that is incorporated by reference at the 

National Archives and Records 

Administration (NARA). For information on 

the availability of this material at NARA, call 

202–741–6030, or go to: http://www.archives.

gov/federal-register/cfr/ibr-locations.html. 

Issued in Renton, Washington, on July 21, 

2013. 

Stephen P. Boyd, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2013–18122 Filed 8–15–13; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2012–1321; Directorate 

Identifier 2011–NM–147–AD; Amendment 

39–17528; AD 2013–15–12] 

RIN 2120–AA64 

Airworthiness Directives; Airbus 

Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Final rule. 

SUMMARY: We are superseding 

airworthiness directive (AD) 2004–15– 

07, for certain Airbus Model A310 series 

airplanes. AD 2004–15–07 required 

repetitive inspections for fatigue 

cracking of the area around the fasteners 

of the landing plate of the aileron access 

doors of the bottom skin panel of the 

wings, and related corrective action. AD 

2004–15–07 also provided for an 

optional terminating action to end the 

repetitive inspections. This new AD 

reduces the initial inspection 

compliance time and intervals, and 

provides additional terminating action 

options. This AD was prompted by a 

reassessment of a previous fatigue 

threshold and inspection interval, 

which resulted in a determination that 

reduced inspection thresholds and 

intervals for accomplishment of the 

tasks are necessary. We are issuing this 

AD to detect and correct fatigue 

cracking of the area around the fasteners 

of the landing plate of the aileron access 

doors and the bottom skin panel of the 

wings, which could result in reduced 

structural integrity of the wings. 

DATES: This AD becomes effective 

September 20, 2013. 

The Director of the Federal Registe 

approved the incorporation by reference 

of certain publications listed in this AD 

as of September 20, 2013. 

The Director of the Federal Register 

approved the incorporation by reference 

of certain other publications listed in 

this AD as of August 31, 2004 (69 FR 

44592, July 27, 2004). 

ADDRESSES: You may examine the AD 

docket on the Internet at http:// 

www.regulations.gov or in person at the 

U.S. Department of Transportation, 

Docket Operations, M–30, West 

Building Ground Floor, Room W12–140, 

1200 New Jersey Avenue SE., 

Washington, DC. 

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: 

Discussion 

We issued a notice of proposed 

rulemaking (NPRM) to amend 14 CFR 

part 39 to include an AD that would 

apply to the specified products. The 

NPRM was published in the Federal 

Register on February 5, 2013 (78 FR 

8054), and proposed to supersede AD 

2004–15–07, Amendment 39–13741 (69 

FR 44592, July 27, 2004). The NPRM 

proposed to correct an unsafe condition 

for the specified products. The 

European Aviation Safety Agency 

(EASA), which is the Technical Agent 

for the Member States of the European 

Community, has issued EASA 

Airworthiness Directive 2011–0125, 

dated June 30, 2011 (referred to after 

this as ‘‘the MCAI’’), to correct an unsafe 

condition for the specified products. 

The MCAI states: 

DGAC [Direction Ge ́ne ́rale de l’Aviation 

Civile] France issued AD 2003–242(B) [which 

corresponds to FAA AD 2004–15–07, 

Amendment 39–13741 (69 FR 44592, July 27, 

2004)] to require an inspection programme 

for aeroplanes with pre- and post-Airbus 

modification 05106 configurations (Airbus 

SB A310–57–2004) in order to detect any 

crack located on the trailing edge of the wing 

bottom skin No. 2 panel of the all-speedaileron servo control bay. A crack at this 

location, if not detected and corrected, would 

propagate towards the wing rear spar and 

ultimately into the wing fuel tank area. 

Undetected cracks would affect the structural 

integrity of the [left hand] LH and/or [right 

hand] RH wing. 

Since issuance of DGAC France AD 2003– 

242(B) [which corresponds to FAA AD 2004– 

15–07, Amendment 39–13741 (69 FR 44592, 

July 27, 2004)], a reassessment of the 

previous fatigue threshold and inspection 

interval has been completed. As a result of 

the reassessment, the inspection thresholds 

and intervals for accomplishment of the tasks 

as defined in Airbus SB A310–57–2082 have 

been adjusted and reduced. Airbus SB A310– 

57–2082 Revision 03 has been published, in 

which the compliance time periods for these 

inspection thresholds and intervals have 

been amended. 

For the reasons stated above, this [EASA] 

AD retains the requirements of the DGAC 

France AD 2003–242(B) [which corresponds 

to FAA AD 2004–15–07, Amendment 39– 

13741 (69 FR 44592, July 27, 2004)], which 

is superseded, and requires implementation 

of the amended inspection programme. 

Corrective action includes doing a 

permanent repair (installing a repair 

plate and new landing plates), a 

temporary repair (crack-stop drilling 

and application of a protective coating) 

followed by repetitive inspections until 

a permanent repair is done, and a repair 

approved by the FAA or EASA (or its 

delegated agent). This AD also adds 

optional permanent repairs. 

The initial inspection compliance 

times are dependent on the 

configuration (modification status, 

repair status, and crack length), and 

type of use (short range, long range, and 

normal). For airplanes without 

temporary repairs, the initial inspection 

compliance time ranges between 2,000 

total flight cycles or 10,200 total flight 

hours, whichever occurs first; and 

12,000 total flight cycles or 24,000 total 

flight hours, whichever occurs first. If 

the total flight cycles or total flight 

hours compliance time has been 

exceeded, the initial inspection 

compliance time (grace period) ranges 

between 200 flight cycles or 1,000 flight 

hours, to within 1,000 flight cycles or 

2,800 flight hours, whichever occurs 

first. 

For airplanes with temporary repairs, 

the initial inspection compliance time is 

dependent on crack length and ranges 

between 7 flight cycles or 35 flight 

hours, whichever occurs first, since the 

repair; to within 100 flight cycles or 200 

flight hours, whichever occurs first, 

since the repair. 

For airplanes with a temporary repair, 

the compliance time for completing the 

permanent repair ranges between 35 

flight cycles or 175 flight hours, 

whichever occurs first, after completing 

the temporary repair; to within 500 

flight cycles or 1,000 flight hours, 


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whichever occurs first, after completing 

the temporary repair. 

You may obtain further information 

by examining the MCAI in the AD 

docket. 

Comments 

We gave the public the opportunity to 

participate in developing this AD. We 

considered the comment received. 

Request To Change Service Information 

Reference 

FedEx stated that paragraph (n)(1)(iii) 

in the NPRM (78 FR 8054, February 5, 

2013) should refer to Airbus Mandatory 

Service Bulletin A310–57–2082, 

Revision 02, dated October 17, 2008, 

instead of Airbus Service Bulletin 

A310–57–2082, dated June 11, 2002. 

FedEx noted that paragraph (n)(1)(i) also 

refers to Airbus Service Bulletin A310– 

57–2082, dated June 11, 2002. 

We agree to change the reference, and 

have changed paragraph (n)(1)(iii) in 

this AD accordingly. 

Conclusion 

We reviewed the available data, 

including the comment received, and 

determined that air safety and the 

public interest require adopting the AD 

with the changes described previously— 

and minor editorial changes. We have 

determined that these changes: 

• Are consistent with the intent that 

was proposed in the NPRM (78 FR 8054, 

February 5, 2013) for correcting the 

unsafe condition; and 

• Do not add any additional burden 

upon the public than was already 

proposed in the NPRM (78 FR 8054, 

February 5, 2013). 

Costs of Compliance 

We estimate that this AD will affect 

about 58 products of U.S. registry. 

The actions that were required by AD 

2004–15–07, Amendment 39–13741 (69 

FR 44592, July 27, 2004), and are 

retained in this AD take about 2 workhours per product, at an average labor 

rate of $85 per work hour. Based on 

these figures, the estimated cost of the 

currently required actions is $170 per 

product. 

We estimate that it will take about 4 

work-hours per product to comply with 

the new basic requirements of this AD. 

The average labor rate is $85 per workhour. Based on these figures, we 

estimate the cost of this AD to the U.S. 

operators to be $19,720, or $340 per 

product. 

We have received no definitive data 

that would enable us to provide cost 

estimates for the on-condition actions 

specified in this AD. We have no way 

of determining the number of products 

that may need these actions. 

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 AD will not 

have federalism implications under 

Executive Order 13132. This AD will 

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 that this AD: 

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 AD and placed it in the AD docket. 

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 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. 

List of Subjects in 14 CFR Part 39 

Air transportation, Aircraft, Aviation 

safety, Incorporation by reference, 

Safety. 

Adoption of the Amendment 

Accordingly, under the authority 

delegated to me by the Administrator, 

the FAA amends 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 

removing airworthiness directive (AD) 

2004–15–07, Amendment 39–13741 (69 

FR 44592, July 27, 2004), and adding the 

following new AD: 

2013–15–12 Airbus: Amendment 39–17528. 

Docket No. FAA–2012–1321; Directorate 

Identifier 2011–NM–147–AD. 

(a) Effective Date 

This airworthiness directive (AD) becomes 

effective September 20, 2013. 

(b) Affected ADs 

This AD supersedes AD 2004–15–07, 

Amendment 39–13741 (69 FR 44592, July 27, 

2004). 

(c) Applicability 

This AD applies to Airbus Model A310– 

203, –204, –221, –222, –304, –322, –324, and 

–325 airplanes, certificated in any category, 

all serial numbers; except for airplanes 

identified in paragraphs (c)(1) and (c)(2) of 

this AD. 

(1) Airplanes that have been modified in 

service according to Airbus Service Bulletin 

A310–57–2081 or during production by 

Airbus modification 12525. 

(2) Airplanes that have been repaired 

according to Airbus Repair Inspection R573– 

49243 or R573–49237. 

(d) Subject 

Air Transport Association (ATA) of 

America Code 57, Wings. 

(e) Reason 

This AD was prompted by a reassessment 

of the previous fatigue threshold and 

inspection interval specified in AD 2004–15– 

07, Amendment 39–13741 (69 FR 44592, July 

27, 2004), which resulted in a determination 

that reduced inspection thresholds and 

intervals for accomplishment of the tasks are 

necessary. We are issuing this AD to detect 

and correct fatigue cracking of the area 

around the fasteners of the landing plate of 

the aileron access doors and the bottom skin 

panel of the wings, 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 


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compliance times specified, unless the 

actions have already been done. 

(g) Retained Repetitive Inspections for 

Airplanes Without Airbus Modification 5106 

This paragraph restates the requirements of 

paragraph (a) of AD 2004–15–07, 

Amendment 39–13741 (69 FR 44592, July 27, 

2004). For airplanes on which Airbus 

Modification 5106 (Airbus Service Bulletin 

A310–57–2004, Revision 2, dated March 5, 

1990, which is not incorporated by reference 

in this AD) has not been done as of August 

31, 2004 (the effective date of AD 2004–15– 

07): Within 2,000 flight cycles after August 

31, 2004 (the effective date of AD 2004–15– 

07), or within 3,000 flight cycles after the last 

inspection done per paragraph (k) of AD 98– 

26–01, Amendment 39–10942 (63 FR 69179, 

December 16, 1998), whichever is first; do a 

high frequency eddy current (HFEC) 

inspection for cracking of the area around the 

fasteners of the landing plate of the wing 

bottom skin panel No. 2 of the left and right 

wings. Do the inspection per the 

Accomplishment Instructions of Airbus 

Service Bulletin A310–57–2082, dated June 

11, 2002. If no cracking is found, repeat the 

inspection thereafter at intervals not to 

exceed 1,900 flight cycles, until 

accomplishment of the terminating action 

specified in paragraph (j) of this AD. 

Accomplishment of the inspection required 

by paragraph (k) of this AD terminates the 

requirements of paragraph (g) of this AD. 

(h) Retained Repetitive Inspection for 

Airplanes With Airbus Modification 5106 

This paragraph restates the requirements of 

paragraph (b) of AD 2004–15–07, 

Amendment 39–13741 (69 FR 44592, July 27, 

2004). For airplanes on which Airbus 

Modification 5106 has been done as of 

August 31, 2004 (the effective date of AD 

2004–15–07): Do the HFEC inspection 

required by paragraph (g) of this AD at the 

applicable time specified in paragraph (h)(1), 

(h)(2), (h)(3), or (h)(4) of this AD. If no 

cracking is found, repeat the inspection 

thereafter at intervals not to exceed 1,900 

flight cycles, until accomplishment of the 

terminating action specified in paragraph (j) 

of this AD. Accomplishment of the 

inspection required by paragraph (k) of this 

AD terminates the requirements of paragraph 

(h) of this AD. 

(1) For airplanes that have accumulated 

fewer than 17,000 total flight cycles since the 

date of issuance of the original Airworthiness 

Certificate or the date of issuance of the 

original Export Certificate of Airworthiness, 

whichever is first, as of August 31, 2004 (the 

effective date of AD 2004–15–07, 

Amendment 39–13741 (69 FR 44592, July 27, 

2004)): Inspect prior to the accumulation of 

18,000 total flight cycles. 

(2) For airplanes that have accumulated 

17,000 or more total flight cycles, but fewer 

than 19,001 total flight cycles since the date 

of issuance of the original Airworthiness 

Certificate or the date of issuance of the 

original Export Certificate of Airworthiness, 

whichever is first, as of August 31, 2004 (the 

effective date of AD 2004–15–07, 

Amendment 39–13741 (69 FR 44592, July 27, 

2004)): Inspect within 2,000 flight cycles 

after August 31, 2004 (the effective date of 

AD 2004–15–07). 

(3) For airplanes that have accumulated 

19,001 or more total flight cycles, but fewer 

than 21,001 total flight cycles since the date 

of issuance of the original Airworthiness 

Certificate or the date of issuance of the 

original Export Certificate of Airworthiness, 

whichever is first, as of August 31, 2004 (the 

effective date of AD 2004–15–07, 

Amendment 39–13741 (69 FR 44592, July 27, 

2004)): Inspect with 1,200 flight cycles after 

August 31, 2004 (the effective date of AD 

2004–15–07). 

(4) For airplanes that have accumulated 

21,001 or more total flight cycles since the 

date of issuance of the original Airworthiness 

Certificate or the date of issuance of the 

original Export Certificate of Airworthiness, 

whichever is first, as of August 31, 2004 (the 

effective date of AD 2004–15–07, 

Amendment 39–13741 (69 FR 44592, July 27, 

2004)): Inspect within 500 flight cycles after 

August 31, 2004 (the effective date of AD 

2004–15–07). 

(i) Retained Corrective Action 

This paragraph restates the requirements of 

paragraph (c) of AD 2004–15–07, 

Amendment 39–13741 (69 FR 44592, July 27, 

2004). If any cracking is found during any 

inspection required by paragraph (g) or (h) of 

this AD: Before further flight, do the actions 

required by either paragraph (i)(1) or (i)(2) of 

this AD. 

(1) Do a permanent repair of the area by 

doing the applicable corrective actions per 

the Accomplishment Instructions of Airbus 

Service Bulletin A310–57–2082, dated June 

11, 2002. Accomplishment of the permanent 

repair terminates the repetitive inspections 

required by this AD for the repaired area 

only. 

(2) Do the terminating action specified in 

paragraph (j) of this AD. 

(j) Retained Optional Terminating Action, 

With New Service Information and New 

Options 

This paragraph restates the optional 

terminating action information specified in 

paragraph (d) of AD 2004–15–07, 

Amendment 39–13741 (69 FR 44592, July 27, 

2004), with new service information and new 

options. Modification of the landing plate of 

the aileron access doors of the wing bottom 

skin panel No. 2 of the left and right wings 

by doing all the actions, in accordance with 

the Accomplishment Instructions of Airbus 

Service Bulletin A310–57–2081, dated June 

11, 2002; or Airbus Service Bulletin A310– 

57–2081, Revision 03, dated October 13, 

2010; or by doing the repair in accordance 

with Airbus Repair Instruction R573–49243, 

Revision C, dated July 16, 2003; or Airbus 

Repair Instruction R573–49237, Revision D, 

dated July 16, 2003; which terminates the 

requirements of this AD. Where Airbus 

Service Bulletin A310–57–2081, dated June 

11, 2002; and Airbus Service Bulletin A310– 

57–2081, Revision 03, dated October 13, 

2010; specify contacting the manufacturer for 

disposition of certain repair conditions that 

might be associated with the modification 

procedure, this AD requires that the repair be 

done in accordance with a method approved 

by either the Manager, International Branch, 

ANM–116, Transport Airplane Directorate, 

FAA; the Direction Ge ́ne ́rale de l’Aviation 

Civile (DGAC) (or its delegated agent); or the 

European Aviation Safety Agency (EASA) (or 

its delegated agent). 

(k) New Inspections, Related Investigative 

Actions, and Corrective Actions 

Except as specified in paragraph (m)(1) of 

this AD, at the applicable time specified in 

Paragraph 1.E., ‘‘Compliance,’’ of Airbus 

Mandatory Service Bulletin A310–57–2082, 

Revision 03, dated November 15, 2010: Do an 

HFEC inspection to detect cracking of the 

area around the fasteners of the landing plate 

of the wing bottom skin panel No. 2 of the 

left and right wings; and do all applicable 

corrective actions; in accordance with the 

Accomplishment Instructions of Airbus 

Mandatory Service Bulletin A310–57–2082, 

Revision 03, dated November 15, 2010, 

except as required by paragraph (m)(2) of this 

AD. Do all applicable corrective actions 

before further flight. Repeat the inspection of 

the area around the fasteners of the landing 

plate of the wing bottom skin panel number 

2 of the left and right wings thereafter at the 

applicable intervals, including the 

compliance times for post temporary repair 

inspections, specified in Paragraph 1.E., 

‘‘Compliance,’’ of Airbus Mandatory Service 

Bulletin A310–57–2082, Revision 03, dated 

November 15, 2010, except as specified in 

paragraph (m)(3) of this AD. The temporary 

repair of cracks, as identified in Airbus 

Mandatory Service Bulletin A310–57–2082, 

Revision 03, dated November 15, 2010, does 

not constitute terminating action for the 

repetitive inspections required by this AD. 

Accomplishment of the inspection required 

by this paragraph terminates the 

requirements of paragraphs (g) and (h) of this 

AD. Doing the modification specified in 

paragraph (j) of this AD terminates the 

repetitive inspections required by this 

paragraph. 

(l) New Permanent Repair 

For airplanes on which the temporary 

repair as specified in Airbus Mandatory 

Service Bulletin A310–57–2082 has been 

done: Within the applicable time specified in 

Paragraph 1.E., ‘‘Compliance,’’ of Airbus 

Mandatory Service Bulletin A310–57–2082, 

Revision 03, dated November 15, 2010, do 

the permanent repair, in accordance with the 

Accomplishment Instructions of Airbus 

Mandatory Service Bulletin A310–57–2082, 

Revision 03, dated November 15, 2010, 

except as provided by paragraph (m)(2) of 

this AD. 

(m) New Exceptions to Service Information 

(1) Where Paragraph 1.E., ‘‘Compliance,’’ of 

Airbus Mandatory Service Bulletin A310–57– 

2082, Revision 03, dated November 15, 2010, 

specifies a compliance time ‘‘from receipt of 

this service bulletin,’’ this AD requires 

compliance within the specified compliance 

time after the effective date of this AD. 

(2) Where Airbus Mandatory Service 

Bulletin A310–57–2082, Revision 03, dated 

November 15, 2010, specifies to contact 

Airbus for repair: Before further flight, repair 

the crack using a method approved by either 


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the Manager, International Branch, ANM– 

116; or EASA (or its delegated agent). 

(3) Where Paragraph 1.E., ‘‘Compliance,’’ of 

Airbus Mandatory Service Bulletin A310–57– 

2082, Revision 03, dated November 15, 2010, 

specifies to contact Airbus for inspection 

intervals, this AD requires using an 

inspection interval approved by either the 

Manager, International Branch, ANM–116; or 

EASA (or its delegated agent). 

(n) Credit for Previous Actions 

(1) This paragraph provides credit for the 

actions required by paragraphs (k) and (l) of 

this AD, if those actions were performed 

before the effective date of this AD using the 

service information specified in paragraph 

(n)(1)(i), (n)(1)(ii), or (n)(1)(iii) of this AD. 

(i) Airbus Service Bulletin A310–57–2082, 

dated June 11, 2002. 

(ii) Airbus Service Bulletin A310–57–2082, 

Revision 01, dated August 22, 2003, which is 

not incorporated by reference in this AD. 

(iii) Airbus Mandatory Service Bulletin 

A310–57–2082, Revision 02, dated October 

17, 2008, which is not incorporated by 

reference in this AD. 

(2) This paragraph provides credit for the 

modification of the landing plate of the 

aileron access doors of the wing bottom skin 

panel No. 2 of the left and right wings 

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

actions were performed before the effective 

date of this AD using the service information 

specified in paragraph (n)(2)(i) or (n)(2)(ii) of 

this AD (which is not incorporated by 

reference in this AD), except where this 

service information specifies contacting the 

manufacturer for disposition of certain repair 

conditions that might be associated with the 

modification procedure, this AD requires that 

the repair be done in accordance with a 

method approved by either the Manager, 

International Branch, ANM–116; or the 

EASA (or its delegated agent). 

(i) Airbus Service Bulletin A310–57–2081, 

Revision 01, dated February 26, 2003, which 

is not incorporated by reference in this AD. 

(ii) Airbus Service Bulletin A310–57–2081, 

Revision 02, dated October 18, 2007, which 

is not incorporated by reference in this AD. 

(o) Other FAA AD Provisions 

The following provisions also apply to this 

AD: 

(1) Alternative Methods of Compliance 

(AMOCs): The Manager, International 

Branch, ANM–116, 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; 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. 

(3) Previously Approved AMOCS: AMOCs 

approved previously in accordance with AD 

2004–15–07, Amendment 39–13741 (69 FR 

44592, July 27, 2004), are approved as 

AMOCs for the corresponding provisions of 

this AD. 

(p) Related Information 

(1) Refer to MCAI EASA Airworthiness 

Directive 2011–0125, dated June 30, 2011, for 

related information. 

(2) Service information identified in this 

AD that is not incorporated by reference may 

be obtained at the address specified in 

paragraphs (q)(5) and (q)(6) of this AD. 

(q) Material Incorporated by Reference 

(1) The Director of the Federal Register 

approved the incorporation by reference 

(IBR) of the service information listed in this 

paragraph under 5 U.S.C. 552(a) and 1 CFR 

part 51. 

(2) You must use this service information 

as applicable to do the actions required by 

this AD, unless the AD specifies otherwise. 

(3) The following service information was 

approved for IBR on September 20, 2013. 

(i) Airbus Mandatory Service Bulletin 

A310–57–2082, Revision 03, dated November 

15, 2010. 

(ii) Airbus Repair Instruction R573–49237, 

Revision D, dated July 16, 2003. 

(iii) Airbus Repair Instruction R573–49243, 

Revision C, dated July 16, 2003. 

(iv) Airbus Service Bulletin A310–57– 

2081, Revision 03, dated October 13, 2010. 

(4) The following service information was 

approved for IBR on August 31, 2004 (69 FR 

44592, July 27, 2004). 

(i) Airbus Service Bulletin A310–57–2081, 

dated June 11, 2002. 

(ii) Airbus Service Bulletin A310–57–2082, 

dated June 11, 2002. 

(5) For service information identified in 

this AD, contact Airbus SAS—EAW 

(Airworthiness Office), 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.airwortheas@airbus.com; Internet http:// 

www.airbus.com. 

(6) You may review copies of the 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. 

(7) You may view this service information 

that is incorporated by reference at the 

National Archives and Records 

Administration (NARA). For information on 

the availability of this material at NARA, call 

202–741–6030, or go to: http:// 

www.archives.gov/federal-register/cfr/ibrlocations.html. 

Issued in Renton, Washington, on July 22, 

2013. 

Stephen P. Boyd, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2013–19862 Filed 8–15–13; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF HOMELAND 

SECURITY 

Coast Guard 

33 CFR Part 117 

[Docket No. USCG–2013–0291] 

RIN 1625–AA09 

Drawbridge Operation Regulation; 

Taunton River, Fall River and 

Somerset, MA 

AGENCY: Coast Guard, DHS. 

ACTION: Final rule. 

SUMMARY: The Coast Guard has changed 

the drawbridge operation regulations 

that govern the operation of the 

Veterans Memorial Bridge across the 

Taunton River, mile 2.1, between Fall 

River and Somerset, Massachusetts. The 

bridge owner, Massachusetts 

Department of Transportation, 

submitted a request to reduce the hours 

the bridge is crewed based upon 

infrequent requests to open the draw. It 

is expected that this change to the 

regulations will provide relief to the 

bridge owner from crewing the bridge 

while continuing to meet the reasonable 

needs of navigation. 

DATES: This rule is effective September 

16, 2013. 

ADDRESSES: Documents mentioned in 

this preamble are part of docket USCG– 

2013–0291. To view documents 

mentioned in this preamble as being 

available in the docket, go to http:// 

www.regulations.gov, type in the docket 

number in the ‘‘Search.’’ Box and click 

‘‘SEARCH.’’ Click Open Docket Folder 

on the line associated with this 

rulemaking. You may also visit the 

Docket Management Facility in Room 

W12–140 on the ground floor of the 

Department of Transportation West 

Building, 1200 New Jersey Avenue SE., 

Washington, DC 20590, between 9 a.m. 

and 5 p.m., Monday through Friday, 

except Federal holidays. 

FOR FURTHER INFORMATION CONTACT: If 

you have questions on this rule, call or 

email Mr. John W. McDonald, Project 

Officer, First Coast Guard District Bridge 

Branch, 617–223–8364, 

john.w.mcdonald@uscg.mil. If you have 

questions on viewing the docket, call 


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