44812 Federal Register / Vol. 81, No. 132 / Monday, July 11, 2016 / Proposed Rules 

(ii) Have not changed your policies 

and practices with regard to disclosing 

nonpublic personal information from 

the policies and practices that were 

disclosed to the customer under 

§ 1016.6(a)(2) through (5) and (9) in the 

most recent privacy notice provided 

pursuant to this part. 

(2) Delivery of annual privacy notice 

after financial institution no longer 

meets requirements for exception. If you 

have been excepted from delivering an 

annual privacy notice pursuant to 

paragraph (e)(1) of this section and 

change your policies or practices in 

such a way that you no longer meet the 

requirements for that exception, you 

must comply with paragraph (e)(2)(i) or 

(e)(2)(ii) of this section, as applicable. 

(i) Changes preceded by a revised 

privacy notice. If you no longer meet the 

requirements of paragraph (e)(1) of this 

section because you change your 

policies or practices in such a way that 

§ 1016.8 requires you to provide a 

revised privacy notice, you must 

provide an annual privacy notice in 

accordance with the timing 

requirements in paragraph (a) of this 

section, treating the revised privacy 

notice as an initial privacy notice. 

(ii) Changes not preceded by a revised 

privacy notice. If you no longer meet the 

requirements of paragraph (e)(1) of this 

section because you change your 

policies or practices in such a way that 

§ 1016.8 does not require you to provide 

a revised privacy notice, you must 

provide an annual privacy notice within 

60 days of the change in your policies 

or practices that causes you to no longer 

meet the requirements of paragraph 

(e)(1). 

(iii) Example. You change your 

policies and practices in such a way that 

you no longer meet the requirements of 

paragraph (e)(1) of this section effective 

April 1 of year 1. Assuming you define 

the 12-consecutive-month period 

pursuant to paragraph (a) of this section 

as a calendar year, if you were required 

to provide a revised privacy notice 

under § 1016.8 and you provided that 

notice on March 1 of year 1, you must 

provide an annual privacy notice by 

December 31 of year 2. If you were not 

required to provide a revised privacy 

notice under § 1016.8, you must provide 

an annual privacy notice by May 30 of 

year 1. 

■ 4. Section 1016.9 is amended by 

revising paragraph (c) to read as follows: 

§ 1016.9 Delivering privacy and opt out 

notices. 

* * * * * 

(c) Annual notices only. You may 

reasonably expect that a customer will 

receive actual notice of your annual 

privacy notice if: 

(1) The customer uses your Web site 

to access financial products and services 

electronically and agrees to receive 

notices at the Web site, and you post 

your current privacy notice 

continuously in a clear and conspicuous 

manner on the Web site; or 

(2) The customer has requested that 

you refrain from sending any 

information regarding the customer 

relationship, and your current privacy 

notice remains available to the customer 

upon request. 

* * * * * 

Dated: June 29, 2016. 

Richard Cordray, 

Director, Bureau of Consumer Financial 

Protection. 

[FR Doc. 2016–16132 Filed 7–8–16; 8:45 am] 

BILLING CODE 4810–AM–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2015–3985; Directorate 

Identifier 2014–NM–182–AD] 

RIN 2120–AA64 

Airworthiness Directives; Airbus 

Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Supplemental notice of 

proposed rulemaking (NPRM); 

reopening of comment period. 

SUMMARY: We are revising an earlier 

proposed airworthiness directive (AD) 

to supersede Airworthiness Directive 

(AD) 2010–04–03, for all Airbus Model 

A310 series airplanes. AD 2010–04–03 

currently requires accomplishing 

repetitive detailed inspections for 

cracking around the fastener holes in 

certain wing top skin panels between 

the front and rear spars on the left- and 

right-hand sides of the fuselage, and 

repair if necessary. The NPRM proposed 

to continue to require the repetitive 

detailed inspections, and would also 

require supplemental repetitive 

ultrasonic inspections for cracking 

around the fastener holes in wing top 

skin panels 1 and 2 at rib 2, and repair 

if necessary. This action revises the 

NPRM by expanding the inspection area 

to include rib 3 due to widespread 

fatigue damage. We are proposing this 

supplemental NPRM (SNPRM) to detect 

and correct fatigue cracking around the 

fastener holes, which could result in 

reduced structural integrity of the 

airplane. Since these actions impose an 

additional burden over those proposed 

in the NPRM, we are reopening the 

comment period to allow the public the 

chance to comment on these proposed 

changes. 

DATES: We must receive comments on 

this SNPRM by August 25, 2016. 

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: 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 SNPRM, 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 by searching for 

and locating Docket No. FAA–2015– 

3985; 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 

(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. 


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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–2015–3985; Directorate Identifier 

2014–NM–182–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 

We issued a notice of proposed 

rulemaking (NPRM) to amend 14 CFR 

part 39 to supersede AD 2010–04–03, 

Amendment 39–16196 (75 FR 6852, 

February 12, 2010) (‘‘AD 2010–04–03’’). 

AD 2010–04–03 applied to all Airbus 

Model A310 series airplanes. The NPRM 

published in the Federal Register on 

October 13, 2015 (80 FR 61327) (‘‘the 

NPRM’’). The NPRM was prompted by 

development of an ultrasonic inspection 

program to allow for earlier crack 

detection and extend the repetitive 

inspection intervals. The NPRM 

proposed to retain the requirements of 

AD 2010–04–03, and proposed to 

require supplemental repetitive 

ultrasonic inspections for cracking 

around the fastener holes in wing top 

skin panels 1 and 2 at rib 2, and repair 

if necessary. 

Since we issued the NPRM, a 

widespread fatigue damage analysis 

determined that the inspection area 

should be expanded to include cracking 

around the fastener holes in wing top 

skin panels 1 and 2 between the front 

and rear spar at rib 3. 

The European Aviation Safety Agency 

(EASA), which is the Technical Agent 

for the Member States of the European 

Union, has issued EASA Airworthiness 

Directive 2016–0005, dated January 7, 

2016 (referred to after this as the 

Mandatory Continuing Airworthiness 

Information, or ‘‘the MCAI’’), to correct 

an unsafe condition on all Airbus Model 

A310 series airplanes. The MCAI states: 

Following scheduled maintenance, cracks 

were found around the wing top skin panels 

fastener holes at Rib 2, between Stringer 

(STG) 2 and STG14. 

This condition, if not detected and 

corrected, could affect the structural integrity 

of the aeroplane. The General Visual 

Inspection required by the existing 

applicable Airworthiness Limitation Items 

(ALI) tasks may not be adequate to detect 

these cracks. 

To address this issue, Airbus developed an 

inspection programme based on repetitive 

detailed inspections (DET) to ensure that any 

visible cracks in the wing top skin panels 1 

and 2 along Rib 2 are detected in time and 

repaired appropriately. EASA issued [EASA] 

AD 2008–0211 [http://ad.easa.europa.eu/ad/ 

2008-0211, which corresponds to FAA AD 

2010–04–03] to require implementation of 

this inspection programme. 

After that [EASA] AD was issued, Airbus 

improved the inspection programme with an 

ultrasonic inspection to allow earlier crack 

detection, to subsequently reduce the scope 

of potential repair action, and to extend the 

intervals of the repetitive inspections. 

Consequently, EASA issued and AD 2014– 

0200 (later revised), superseding [EASA] AD 

2008–0211, retaining its requirements, and to 

require supplementary repetitive ultrasonic 

inspections [for cracking] of the wing top 

skin panel 1 and 2 between STG2 and STG10 

at Rib 2 [and repair if needed]. 

Since EASA AD 2014–0020R1 was issued, 

a widespread fatigue damage analysis 

concluded that the inspection programme 

has to be extended to include the wing top 

skin panels at Rib 3 attachments. For the 

reasons described above, this [EASA] AD 

retains the requirements of EASA AD 2014– 

0200R1, which is superseded, and extends 

the inspection area to include Rib 3. 

You may examine the MCAI in the 

AD docket on the Internet at http://

www.regulations.gov by searching for 

and locating Docket No. FAA–2015– 

3985. 

Related Service Information Under 1 

CFR Part 51 

Airbus has issued Service Bulletin 

A310–57–2096, Revision 03, dated June 

30, 2015. This service information 

describes procedures for detailed and 

ultrasonic inspections for cracking 

around the fastener holes of wing top 

skin panels 1 and 2, at ribs 2 and 3, on 

the left- and right-hand sides of the 

fuselage. This service information is 

reasonably available because the 

interested parties have access to it 

through their normal course of business 

or by the means identified in the 

ADDRESSES section. 

Comments 

We gave the public the opportunity to 

participate in developing this proposed 

AD. We considered the comment 

received. The commenter, FedEx, 

supported the content of the NPRM and 

is currently complying with the 

requirements. 

FAA’s Determination and Requirements 

of This SNPRM 

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. 

Certain changes described above 

expand the scope of the NPRM. As a 

result, we have determined that it is 

necessary to reopen the comment period 

to provide additional opportunity for 

the public to comment on this SNPRM. 

Costs of Compliance 

We estimate that this SNPRM affects 

28 airplanes of U.S. registry. 

We also estimate that it would take 

about 8 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 $19,040, or $680 per product. 

We estimate that it would take about 

15 work-hours per product to do any 

necessary on-condition actions that 

would be required based on the results 

of the inspections. Required parts would 

cost about $10,000 per product. We 

have no way of determining the number 

of aircraft that might 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. 


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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 

removing Airworthiness Directive (AD) 

2010–04–03, Amendment 39–16196 (75 

FR 6852, February 12, 2010), and adding 

the following new AD: 

Airbus: Docket No. FAA–2015–3985; 

Directorate Identifier 2014–NM–182–AD. 

(a) Comments Due Date 

We must receive comments by August 25, 

2016. 

(b) Affected ADs 

This AD replaces AD 2010–04–03, 

Amendment 39–16196 (75 FR 6852, February 

12, 2010) (‘‘AD 2010–04–03’’). 

(c) Applicability 

This AD applies to all Airbus Model A310– 

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

–325 airplanes, certificated in any category, 

all manufacturer serial numbers. 

(d) Subject 

Air Transport Association (ATA) of 

America Code 57, Wings. 

(e) Reason 

This AD was prompted by the 

development of an ultrasonic inspection 

program to allow for earlier crack detection 

and extend the repetitive inspection 

intervals. We are issuing this AD to detect 

and correct fatigue cracking around the 

fastener holes in certain wing top skin panels 

between the front and rear spars on the leftand right-hand sides of the fuselage, which 

could result in reduced structural integrity of 

the airplane. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Repetitive Inspections 

Except as required by paragraph (i) of this 

AD: Within the initial compliance time and 

thereafter at the repetitive intervals specified 

in paragraphs (h)(1) through (h)(3) of this AD, 

as applicable, accomplish the actions 

specified in paragraphs (g)(1) and (g)(2) of 

this AD concurrently and in sequence, in 

accordance with the Accomplishment 

Instructions of Airbus Service Bulletin A310– 

57–2096, Revision 03, dated June 30, 2015, 

except as provided by paragraph (j) of this 

AD. 

(1) Accomplish a detailed inspection for 

cracking around the fastener holes in the 

wing top skin panels 1 and 2, along ribs 2 

and 3, between the front and rear spars on 

the left- and right-hand sides of the fuselage. 

(2) Accomplish an ultrasonic inspection for 

cracking around the fastener holes in the 

wing top skin panels 1 and 2, along ribs 2 

and 3, between stringer (STG) 2 and STG10 

on the left- and right-hand sides of the 

fuselage. 

(h) Compliance Times for Airplanes Not 

Previously Inspected 

(1) For Model A310–203, –204, –221, and 

–222 airplanes: Do the actions required by 

paragraphs (g)(1) and (g)(2) of this AD at the 

later of the times specified in paragraphs 

(h)(1)(i) and (h)(1)(ii) of this AD. Repeat the 

inspections specified in paragraphs (g)(1) and 

(g)(2) of this AD thereafter at intervals not to 

exceed 2,000 flight cycles or 4,100 flight 

hours, whichever occurs first. 

(i) Prior to the accumulation of 18,700 

flight cycles or 37,400 flight hours since first 

flight of the airplane, whichever occurs first. 

(ii) Within 30 days after the effective date 

of this AD. 

(2) For Model A310–304, –322, –324, and 

–325 airplanes having an average flight time 

(AFT) of less than 4 hours: Do the actions 

required by paragraphs (g)(1) and (g)(2) of 

this AD at the later of the times specified in 

paragraphs (h)(2)(i) and (h)(2)(ii) of this AD. 

Repeat the inspections specified in 

paragraphs (g)(1) and (g)(2) of this AD 

thereafter at intervals not to exceed 2,000 

flight cycles or 5,600 flight hours, whichever 

occurs first. 

(i) Prior to the accumulation of 17,300 

flight cycles or 48,400 flight hours since first 

flight of the airplane, whichever occurs first. 

(ii) Within 30 days after the effective date 

of this AD. 

(3) For Model A310–304, –322, –324, and 

–325 airplanes having an AFT of equal to or 

more than 4 hours: Do the actions required 

by paragraphs (g)(1) and (g)(2) of this AD at 

the later of the times specified in paragraphs 

(h)(3)(i) and (h)(3)(ii) of this AD. Repeat the 

inspections specified in paragraphs (g)(1) and 

(g)(2) of this AD thereafter at intervals not to 

exceed 1,500 flight cycles or 7,500 flight 

hours, whichever occurs first. 

(i) Prior to the accumulation of 12,800 

flight cycles or 64,300 flight hours since first 

flight of the airplane, whichever occurs first. 

(ii) Within 30 days after the effective date 

of this AD. 

(i) Compliance Times for Airplanes 

Previously Inspected 

For airplanes previously inspected before 

the effective date of this AD using Airbus 

Service Bulletin A310–57–2096, dated May 

6, 2008; Airbus Service Bulletin A310–57– 

2096, Revision 01, dated August 5, 2010; or 

Airbus Service Bulletin A310–57–2096, 

Revision 02, dated March 5, 2014: At the 

applicable compliance times specified in 

paragraphs (i)(1), (i)(2), and(i)(3) of this AD, 

accomplish the actions specified in 

paragraphs (g)(1) and (g)(2) concurrently and 

in sequence, in accordance with the 

Accomplishment Instructions of Airbus 

Service Bulletin A310–57–2096, Revision 03, 

dated June 30, 2015. Repeat the inspections 

specified in paragraphs (g)(1) and (g)(2) of 

this AD thereafter at the repetitive intervals 

specified in paragraphs (h)(1), (h)(2), and 

(h)(3) of this AD, as applicable. 

(1) For Model A310–203, –204, –221, and 

–222 airplanes: Do the actions required by 

paragraphs (g)(1) and (g)(2) of this AD within 

3,500 flight hours or 1,700 flight cycles, 

whichever occurs first since the most recent 

inspection. 

(2) For Model A310–304, –322, –324, and 

–325 airplanes having an AFT of less than 4 

hours: Do the actions required by paragraphs 

(g)(1) and (g)(2) of this AD within 4,600 flight 

hours or 1,600 flight cycles, whichever 

occurs first since the most recent inspection. 

(3) For Model A310–304, –322, –324, and 

–325 airplanes having an AFT of equal to or 

more than 4 hours: Do the actions required 

by paragraphs (g)(1) and (g)(2) of this AD 

within 6,100 flight hours or 1,200 flight 

cycles, whichever occurs first since the most 

recent inspection. 

(j) Compliance Times if No Ultrasonic 

Equipment Is Available 

If no ultrasonic equipment is available for 

the initial or second inspection required by 

paragraph (g) or (h) of this AD, accomplish 

the detailed inspection specified in 

paragraph (g)(1) of this AD within the 

applicable compliance times specified in 

paragraphs (j)(1) and (j)(2) of this AD. After 

accomplishing the detailed inspection, do the 

inspections specified in paragraphs (g)(1) and 

(g)(2) of this AD at the applicable compliance 

times specified by paragraphs (i)(1), (i)(2), 

and (i)(3) of this AD. Subsequently, repeat 

the inspections specified in paragraphs (g)(1) 

and (g)(2) of this AD thereafter at the 

applicable repetitive intervals specified in 

paragraphs (h)(1), (h)(2), and (h)(3) of this 

AD. 

(1) For airplanes not previously inspected 

before the effective date of this AD using the 


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service information identified in paragraph 

(j)(2)(i), (j)(2)(ii), or (j)(2)(iii) of this AD: Do 

the actions required by paragraph (g)(1) of 

this AD within the initial compliance time 

specified by paragraphs (h)(1), (h)(2), and 

(h)(3) of this AD, as applicable. 

(2) For airplanes previously inspected 

before the effective date of this AD using the 

service information identified in paragraph 

(j)(2)(i), (j)(2)(ii), or (j)(2)(iii) of this AD: Do 

the actions required by paragraph (g)(1) of 

this AD within the applicable compliance 

times specified in paragraphs (i)(1), (i)(2), 

and (i)(3) of this AD. 

(i) Airbus Service Bulletin A310–57–2096, 

dated May 6, 2008. 

(ii) Airbus Service Bulletin A310–57–2096, 

Revision 01, dated August 5, 2010. 

(iii) Airbus Service Bulletin A310–57– 

2096, Revision 02, dated March 5, 2014. 

(k) Repair of Cracking 

If any cracking is found during any 

inspection required by paragraph (g), (h), (i), 

or (j) 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 

European Aviation Safety Agency (EASA); or 

Airbus’s EASA Design Organization 

Approval (DOA). Accomplishing the repair 

specified in this paragraph terminates the 

repetitive inspections required by paragraph 

(h), (i), or (j) of this AD, as applicable, for the 

repaired area only. 

(l) Definition of Average Flight Time (AFT) 

For the purposes of this AD, the AFT 

should be established as specified in 

paragraphs (l)(1), (l)(2), and (l)(3) of this AD 

for the determination of the compliance 

times. 

(1) The inspection threshold is defined as 

the total flight hours accumulated (counted 

from take-off to touch-down), divided by the 

total number of flight cycles accumulated at 

the effective date of this AD. 

(2) The initial inspection interval is 

defined as the total flight hours accumulated 

divided by the total number of flight cycles 

accumulated at the time of the initial 

inspection threshold. 

(3) The second inspection interval is 

defined as the total flight hours accumulated 

divided by the total number of flight cycles 

accumulated between the initial and second 

inspection threshold. 

(m) Credit for Previous Actions 

This paragraph provides credit for the 

actions required by paragraph (g)(1) of this 

AD, if those actions were performed before 

the effective date of this AD using the 

applicable service information identified in 

paragraph (m)(1), (m)(2), or (m)(3) of this AD. 

(1) Airbus Service Bulletin A310–57–2096, 

dated May 6, 2008, which was incorporated 

by reference in AD 2010–04–03. 

(2) Airbus Service Bulletin A310–57–2096, 

Revision 01, dated August 5, 2010, which is 

not incorporated by reference in this AD. 

(3) Airbus Service Bulletin A310–57–2096, 

Revision 02, dated March 5, 2014, which is 

not incorporated by reference in this AD. 

(n) 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; 

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) Contacting the Manufacturer: As of the 

effective date of this AD, for any requirement 

in this AD to obtain corrective actions from 

a manufacturer, the action must be 

accomplished using a method approved by 

the Manager, International Branch, ANM– 

116, Transport Airplane Directorate, FAA; or 

the EASA; or Airbus’s EASA DOA. If 

approved by the DOA, the approval must 

include the DOA-authorized signature. 

(3) Required for Compliance (RC): Except 

as required by paragraph (k) of this AD, if any 

service information contains procedures or 

tests that are identified as RC, those 

procedures and tests must be done to comply 

with this AD; any procedures or tests that are 

not identified as RC are recommended. Those 

procedures and tests that are not identified 

as RC may be deviated from using accepted 

methods in accordance with the operator’s 

maintenance or inspection program without 

obtaining approval of an AMOC, provided 

the procedures and tests identified as RC can 

be done and the airplane can be put back in 

an airworthy condition. Any substitutions or 

changes to procedures or tests identified as 

RC require approval of an AMOC. 

(o) Related Information 

(1) Refer to Mandatory Continuing 

Airworthiness Information (MCAI) EASA 

Airworthiness Directive 2016–0005, dated 

January 7, 2016, 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– 

2015–3985. 

(2) For service information identified in 

this 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 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 1, 

2016. 

Phillip Forde, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2016–16210 Filed 7–8–16; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF HOMELAND 

SECURITY 

Coast Guard 

33 CFR Part 100 

[Docket Number USCG–2016–0012] 

RIN 1625–AA08 

Special Local Regulation; Bucksport/

Lake Murray Drag Boat Fall Nationals, 

Atlantic Intracoastal Waterway; 

Bucksport, SC 

AGENCY: Coast Guard, DHS. 

ACTION: Notice of proposed rulemaking. 

SUMMARY: The Coast Guard proposes to 

establish a special local regulation on 

the Atlantic Intracoastal Waterway in 

Bucksport, South Carolina during the 

Bucksport/Lake Murray Drag Boat Fall 

Nationals, on September 10 and 

September 11, 2016. This special local 

regulation is necessary to ensure the 

safety of participants, spectators, and 

the general public during the event. 

This proposed rulemaking would 

prohibit persons and vessels from being 

in the regulated area unless authorized 

by the Captain of the Port Charleston or 

a designated representative. We invite 

your comments on this proposed 

rulemaking. 

DATES: Comments and related material 

must be received by the Coast Guard on 

or before August 10, 2016. 

ADDRESSES: You may submit comments 

identified by docket number USCG– 

2016–0012 using the Federal 

eRulemaking Portal at http://

www.regulations.gov. See the ‘‘Public 

Participation and Request for 

Comments’’ portion of the 

SUPPLEMENTARY INFORMATION section for 

further instructions on submitting 

comments. 

FOR FURTHER INFORMATION CONTACT: If 

you have questions about this proposed 

rulemaking, call or email Lieutenant 

John Downing, Sector Charleston Office 

of Waterways Management, Coast 

Guard; telephone (843) 740–3184, email 

John.Z.Downing@uscg.mil. 

SUPPLEMENTARY INFORMATION: 

I. Table of Abbreviations 

CFR Code of Federal Regulations 


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