55798 Federal Register / Vol. 80, No. 180 / Thursday, September 17, 2015 / Proposed Rules 

consideration of this request, DOE has 

determined that extending the public 

comment period by reopening to allow 

additional time for interested parties to 

submit comments is appropriate based 

on the foregoing reasons. Accordingly, 

DOE has decided to grant the request 

and reopen the public comment period 

on the NOPR for test procedures for 

small, large, and very large air-cooled 

commercial package air conditioning 

and heating equipment for 15 days to 

allow for additional data and comments 

to be submitted, especially in light of 

the public meeting discussion on 

specific topics. Consequently, DOE will 

consider any comments in response to 

the NOPR received by midnight of 

October 2, 2015, and deems any 

comments received by that time to be 

timely submitted. 

Issued in Washington, DC, on September 

11, 2015. 

Kathleen B. Hogan, 

Deputy Assistant Secretary for Energy 

Efficiency, Energy Efficiency and Renewable 

Energy. 

[FR Doc. 2015–23416 Filed 9–16–15; 8:45 am] 

BILLING CODE 6450–01–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2015–3632; Directorate 

Identifier 2015–NM–023–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) 2014–14– 

06 for all Airbus Model A318–111 and 

–112 airplanes; Model A319–111, –112, 

–113, –114, and –115 airplanes; Model 

A320–111, –211, –212, and –214 

airplanes; and Model A321–111, –112, 

–211, –212, and –213 airplanes. AD 

2014–14–06 currently requires 

inspecting the aft engine mount 

retainers for surface finish, cracks, and 

failure, and replacement if necessary. 

Since we issued AD 2014–14–06, 

inspection results have shown that the 

main cause of crack initiation remains 

the vibration dynamic effect that affects 

both retainers, either with ‘‘dull’’ or 

‘‘bright’’ surface finishes. This proposed 

AD would require repetitive inspections 

for damage, cracks, broken, and missing 

aft engine mount retainers, and 

replacement if necessary. We are 

proposing this AD to detect and correct 

failure of retainer brackets of the aft 

engine mount and consequent loss of 

the locking feature of the nuts of the 

inner and outer pins; loss of the pins 

will result in the aft mount engine link 

no longer being secured to the aft engine 

mount. 

DATES: We must receive comments on 

this proposed AD by November 2, 2015. 

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 Airbus service information 

identified in this proposed AD, contact 

Airbus, Airworthiness Office—EIAS, 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. 

For Goodrich Aerostructures service 

information identified in this proposed 

AD, contact Goodrich Aerostructures, 

850 Lagoon Drive, Chula Vista, CA 

91910–2098; telephone 619–691–2719; 

email jan.lewis@goodrich.com; Internet 

http://www.goodrich.com/TechPubs. 

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– 

3632; 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: 

Sanjay Ralhan, Aerospace Engineer, 

International Branch, ANM–116, 

Transport Airplane Directorate, FAA, 

1601 Lind Avenue SW., Renton, WA 

98057–3356; telephone 425–227–1405; 

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–2015–3632; Directorate Identifier 

2015–NM–023–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 3, 2014, we issued AD 2014– 

14–06, Amendment 39–17901 (79 FR 

42655, July 23, 2014). AD 2014–14–06 

requires actions intended to address an 

unsafe condition on all Model A318– 

111 and –112 airplanes; Model A319– 

111, –112, –113, –114, and –115 

airplanes; Model A320–111, –211, –212, 

and –214 airplanes; and Model A321– 

111, –112, –211, –212, and –213 

airplanes. 

Since we issued AD 2014–14–06, 

Amendment 39–17901 (79 FR 42655, 

July 23, 2014), we have determined that 

additional inspections are necessary to 

address the identified unsafe condition. 

The European Aviation Safety Agency 

(EASA), which is the Technical Agent 

for the Member States of the European 

Union, has issued EASA Airworthiness 

Directive 2015–0021, dated February 13, 

2015 (referred to after this as the 

Mandatory Continuing Airworthiness 

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

an unsafe condition. The MCAI states: 

During in-service inspections, several aft 

engine mount retainers, fitted on aeroplanes 

equipped with CFM56–5A/5B engines, have 

been found broken. The results of the initial 

investigations highlighted that two different 

types of surface finish had been applied 

(respectively bright and dull material 

finishes), and that dull finish affects the 

strength of the retainer with regard to fatigue 

properties of the part. The pins which attach 

the engine link to the aft mount are secured 


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by two nuts, which do not have a self-locking 

feature; this function is provided by the 

retainer brackets. In case of failure of the 

retainer bracket, the locking feature of the 

nuts of the inner and outer pins is lost; as a 

result, these nuts could subsequently become 

loose. 

In case of full loss of the nuts, there is the 

potential to also lose the pins, in which case 

the aft mount link will no longer be secured 

to the aft engine mount. The same locking 

feature is used for the three link assemblies 

of the aft mount. 

This condition, if not detected and 

corrected, could lead to in-flight loss of an aft 

mount link, possibly resulting in damage to 

the aeroplane and injury to person on the 

ground. 

To address this potential unsafe condition, 

EASA issued AD 2013–0050 (http:// 

ad.easa.europa.eu/blob/ 

easa_ad_2013_0050_superseded.pdf/ 

AD_2013-0050_1 [which corresponds to FAA 

AD 2014–14–06, Amendment 39–17901 (79 

FR 42655, July 23, 2014)] to require detailed 

inspections (DET) of the aft engine mount 

retainers and the replacement of all retainers 

with dull finish with retainers having a 

bright finish. 

Since that [EASA] AD was issued, 

inspection results have shown that the main 

cause of crack initiation remains the 

vibration dynamic effect that affects both 

retainers, either with ‘‘dull’’ or ‘‘bright’’ 

surface finishes. The non-conforming ‘‘dull’’ 

surface’s pitting is an aggravating factor. 

For the reasons described above, this 

[EASA] AD retains the requirements of EASA 

AD 2013–0050, which is superseded, and 

requires repetitive DET of all aft engine 

mount retainers and, depending on findings 

[damaged, cracked, broken, or missing 

retainers], their replacement. 

This [EASA] AD is considered to be an 

interim action, pending development and 

availability of a final solution. 

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– 

3632. 

Related Service Information Under 1 

CFR Part 51 

Airbus has issued Service Bulletin 

A320–71–1060, dated October 9, 2014. 

This service information describes 

procedures for inspection of the aft 

engine mount retainers for surface finish 

(dull or bright), for damaged, cracked, 

broken, or missing retainers, and 

replacement. 

Goodrich Aerostructures has issued 

Service Bulletin RA32071–160, dated 

September 18, 2014. This service 

information describes procedures for 

inspection of the aft engine mount inner 

retainers for cracks or failure, and 

replacement. 

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 of 

this NPRM. 

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 these same 

type designs. 

Explanation of ‘‘RC’’ Procedures and 

Tests in Service Information 

The FAA worked in conjunction with 

industry, under the Airworthiness 

Directive Implementation Aviation 

Rulemaking Committee (ARC), to 

enhance the AD system. One 

enhancement was a new process for 

annotating which procedures and tests 

in the service information are required 

for compliance with an AD. 

Differentiating these procedures and 

tests from other tasks in the service 

information is expected to improve an 

owner’s/operator’s understanding of 

crucial AD requirements and help 

provide consistent judgment in AD 

compliance. The procedures and tests 

identified as Required for Compliance 

(RC) in any service information have a 

direct effect on detecting, preventing, 

resolving, or eliminating an identified 

unsafe condition. 

As specified in a NOTE under the 

Accomplishment Instructions of the 

specified Airbus service information, 

procedures and tests that are identified 

as RC in any service information must 

be done to comply with the proposed 

AD. However, procedures and 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 alternative method of compliance 

(AMOC), provided the procedures and 

tests identified as RC can be done and 

the airplane can be put back in a 

serviceable condition. Any substitutions 

or changes to procedures or tests 

identified as RC will require approval of 

an AMOC. 

Costs of Compliance 

We estimate that this proposed AD 

affects 922 airplanes of U.S. registry. 

The actions required by AD 2014–14– 

06, Amendment 39–17901 (79 FR 

42655, July 23, 2014), 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 are required by AD 2014– 

14–06 is $255 per inspection cycle per 

product (for two engines). 

We also estimate that it would take 

about 10 work-hours per product to 

comply with the basic requirements of 

this proposed AD, and 1 work-hour per 

product to report inspection findings. 

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

estimate the cost of this proposed AD on 

U.S. operators to be $862,070, or $935 

per product. 

In addition, we estimate that any 

necessary follow-on actions would take 

about 2 work-hours and require parts 

costing $10,000, for a cost of $10,170 

per product. We have no way of 

determining the number of aircraft that 

might need these actions. 

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 


tkelley on DSK3SPTVN1PROD with PROPOSALS
55800 Federal Register / Vol. 80, No. 180 / Thursday, September 17, 2015 / Proposed Rules 

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 

removing Airworthiness Directive (AD) 

2014–14–06, Amendment 39–17901 (79 

FR 42655, July 23, 2014), and adding the 

following new AD: 

Airbus: Docket No. FAA–2015–3632; 

Directorate Identifier 2015–NM–023–AD. 

(a) Comments Due Date 

We must receive comments by November 

2, 2015. 

(b) Affected ADs 

This AD replaces AD 2014–14–06, 

Amendment 39–17901 (79 FR 42655, July 23, 

2014). 

(c) Applicability 

This AD applies to the Airbus airplanes 

identified in paragraphs (c)(1) through (c)(4) 

of this AD, certificated in any category, all 

manufacturer serial numbers. 

(1) Airbus Model A318–111 and –112 

airplanes. 

(2) Airbus Model A319–111, –112, –113, 

–114, and –115 airplanes. 

(3) Airbus Model A320–211, –212, and 

–214 airplanes. 

(4) Airbus Model A321–111, –112, –211, 

–212, and –213 airplanes. 

(d) Subject 

Air Transport Association (ATA) of 

America Code 71, Powerplant. 

(e) Reason 

This AD was prompted by inspection 

results that have shown that the main cause 

of crack initiation in the aft engine mount 

retainers is the vibration dynamic effect that 

affects both retainers, either with ‘‘dull’’ or 

‘‘bright’’ surface finishes. We are issuing this 

AD to detect and correct failure of retainer 

brackets of the aft engine mount and 

consequent loss of the locking feature of the 

nuts of the inner and outer pins; loss of the 

pins will result in the aft mount engine link 

no longer being secured to the aft engine 

mount. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Retained Inspection, With No Changes 

This paragraph restates the requirements of 

paragraph (g) of AD 2014–14–06, 

Amendment 39–17901 (79 FR 42655, July 23, 

2014), with no changes. Within 3 months 

after August 27, 2014 (the effective date of 

AD 2014–14–06): Do a detailed inspection of 

the aft engine mount retainers for surface 

finish (dull or bright), and for cracks and 

failure, in accordance with Section 4.2.2, 

‘‘Inspection Requirements,’’ of Airbus Alert 

Operators Transmission (AOT) A71N001–12, 

Rev. 2, dated February 27, 2013, except as 

specified in paragraph (h) of this AD. 

(h) Retained Exception to Paragraph (g) of 

This AD, With No Changes 

This paragraph restates the requirements of 

paragraph (h) of AD 2014–14–06, 

Amendment 39–17901 (79 FR 42655, July 23, 

2014), with no changes. The actions required 

by paragraph (g) of this AD are not required 

to be done on airplanes with manufacturer 

serial numbers 4942 and higher, provided a 

review of maintenance records verifies that 

no aft engine mount retainers have been 

replaced since first flight of the airplane. 

(i) Retained Repetitive Inspection and 

Retainer Replacement for Dull Finish 

Retainers, With No Changes 

This paragraph restates the requirements of 

paragraph (i) of AD 2014–14–06, Amendment 

39–17901 (79 FR 42655, July 23, 2014), with 

no changes. If, during the detailed inspection 

required by paragraph (g) of this AD, any 

installed dull finish aft engine mount retainer 

is found without cracks and not failed: Do 

the actions specified in paragraphs (i)(1) and 

(i)(2) of this AD. 

(1) Within 25 flight cycles after doing the 

actions required by paragraph (g) of this AD: 

Repeat the detailed inspection specified in 

paragraph (g) of this AD. 

(2) Within 50 flight cycles after doing the 

first detailed inspection specified in 

paragraph (g) of this AD: Replace all dull 

finish retainers with new retainers, in 

accordance with Section 4.2.3.1, 

‘‘Replacement Procedure,’’ of Airbus AOT 

A71N001–12, Rev. 2, dated February 27, 

2013. 

(j) Retained Replacement of Cracked or 

Failed Retainers, With No Changes 

This paragraph restates the requirements of 

paragraph (j) of AD 2014–14–06, Amendment 

39–17901 (79 FR 42655, July 23, 2014), with 

no changes. If, during any detailed inspection 

specified in paragraph (g) of this AD, any 

installed aft engine mount retainer is found 

cracked or failed: Before further flight, 

replace all affected aft engine mount retainers 

with new retainers, in accordance with 

Section 4.2.3, ‘‘Replacement Procedure,’’ of 

Airbus AOT A71N001–12, Rev. 2, dated 

February 27, 2013. 

(k) Retained Parts Prohibition, With No 

Changes 

This paragraph restates the requirements of 

paragraph (k) of AD 2014–14–06, 

Amendment 39–17901 (79 FR 42655, July 23, 

2014), with no changes. As of August 27, 

2014 (the effective date of AD 2014–14–06), 

no person may install any aft engine mount 

retainer with a dull finish on any airplane. 

The instructions of Airbus AOT A71N001– 

12, Rev. 2, dated February 27, 2013; or the 

Accomplishment Instructions of Goodrich 

Service Bulletin RA32071–146, Rev. 2, dated 

July 26, 2012; may be used to verify the 

correct finish of the part. 

(l) Retained Credit for Previous Actions, 

With No Changes 

This paragraph restates the provisions of 

paragraph (l) of AD 2014–14–06, Amendment 

39–17901 (79 FR 42655, July 23, 2014), with 

no changes. This paragraph provides credit 

for actions required by paragraphs (g), (i), and 

(j) of this AD, if those actions were performed 

before August 27, 2014 (the effective date of 

AD 2014–14–06) using Airbus AOT 

A71N001–12, Rev. 1, dated August 9, 2012, 

which is not incorporated by reference in this 

AD. 

(m) New Requirement of This AD: Repetitive 

Inspections 

At the latest of the applicable times 

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

(m)(3) of this AD: Do a detailed inspection for 

damaged, cracked, broken, or missing aft 

engine mount retainers, in accordance with 

the Accomplishment Instructions of Airbus 

Service Bulletin A320–71–1060, dated 

October 9, 2014; or Goodrich Service Bulletin 

RA32071–160, dated September 18, 2014. 

Repeat the inspection of the aft engine mount 


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retainers thereafter at intervals not to exceed 

12 months. 

(1) Within 12 months since the date of 

issuance of the original airworthiness 

certificate or the date of issuance of the 

original export certificate of airworthiness. 

(2) Within 12 months after installation of 

new retainers. 

(3) Within 9 months after the effective date 

of this AD. 

(n) New Requirement of This AD: 

Replacement of Retainers With Findings 

If, during any detailed inspection specified 

in paragraph (m) of this AD, any installed aft 

engine mount retainer is found damaged, 

cracked, broken, or missing: Before further 

flight, replace all affected aft engine mount 

retainers with new retainers, in accordance 

with the Accomplishment Instructions of 

Airbus Service Bulletin A320–71–1060, 

dated October 9, 2014. 

(o) New Requirement of This AD: No 

Terminating Action 

Replacement of retainers on an airplane, as 

required by paragraph (n) of this AD, does 

not constitute terminating action for the 

repetitive inspections required by paragraph 

(m) of this AD for that airplane. 

(p) New Requirement of This AD: Required 

Reporting 

Submit a report of positive findings of any 

inspection required by paragraph (m) of this 

AD to Airbus at the applicable time specified 

in paragraph (p)(1) or (p)(2) of this AD. The 

report must include the inspection results, a 

description of any discrepancies found, the 

airplane serial number, and the number of 

landings and flight hours on the airplane. 

(1) If the inspection was done on or after 

the effective date of this AD: Submit the 

report within 30 days after the inspection. 

(2) If the inspection was done before the 

effective date of this AD: Submit the report 

within 30 days after the effective date of this 

AD. 

(q) 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: 

Sanjay Ralhan, Aerospace Engineer, 

International Branch, ANM–116, Transport 

Airplane Directorate, FAA, 1601 Lind 

Avenue SW., Renton, WA 98057–3356; 

telephone 425–227–1405; fax 425–227–1149. 

Information may be emailed to: 9-0ANM-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 European Aviation Safety Agency 

(EASA); or Airbus’s EASA Design 

Organization Approval (DOA). If approved by 

the DOA, the approval must include the 

DOA-authorized signature. 

(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. 

(4) Required for Compliance (RC): If any 

Airbus 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 a 

serviceable condition. Any substitutions or 

changes to procedures or tests identified as 

RC require approval of an AMOC. 

(r) Special Flight Permits 

Special flight permits, as described in 

Section 21.197 and Section 21.199 of the 

Federal Aviation Regulations (14 CFR 21.197 

and 21.199), are not allowed. 

(s) Related Information 

(1) Refer to Mandatory Continuing 

Airworthiness Information (MCAI) European 

Aviation Safety Agency Airworthiness 

Directive 2015–0021, dated February 13, 

2015, 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– 

2015–3632. 

(2) For Airbus service information 

identified in this AD, contact Airbus, 

Airworthiness Office—EIAS, 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. 

(3) For Goodrich Aerostructures service 

information identified in this AD, contact 

Goodrich Aerostructures, 850 Lagoon Drive, 

Chula Vista, CA 91910–2098; telephone 619– 

691–2719; email jan.lewis@goodrich.com; 

Internet http://www.goodrich.com/TechPubs. 

(4) 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 

September 9, 2015. 

Michael Kaszycki, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2015–23328 Filed 9–16–15; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF COMMERCE 

National Oceanic and Atmospheric 

Administration 

15 CFR Part 922 

Initiation of Review of Management 

Plan and Regulations of the Monterey 

Bay National Marine Sanctuary; Intent 

To Conduct Scoping and Prepare Draft 

Environmental Impact Statement and 

Management Plan; Correction 

AGENCY: Office of National Marine 

Sanctuaries (ONMS), National Ocean 

Service (NOS), National Oceanic and 

Atmospheric Administration (NOAA), 

Department of Commerce (DOC). 

ACTION: Correction. 

SUMMARY: On August 27, 2015, NOAA 

published a notice of intent in the 

Federal Register (80 FR 51973) to 

initiate public scoping for the 

management plan review for Monterey 

Bay National Marine Sanctuary 

(MBNMS). This notice alerts the public 

of the addition of a public scoping 

meeting in Half Moon Bay on October 

14, 2015. It also makes a correction to 

the docket number for submission of 

public comments on the online 

rulemaking portal at 

www.regulations.gov. The correct docket 

number is NOAA–NOS–2015–0099. The 

end of the scoping period remains 

October 30, 2015. 

DATES: NOAA will accept public 

comments on the notice of intent 

published at 80 FR 51973 (August 27, 

2015) through October 30, 2015. 

Locations and dates for public scoping 

meetings remain the same as described 

in the notice of intent, with the addition 

of a meeting on October 14, 2015 from 

6 p.m. to 8 p.m. at the Half Moon Bay 

Yacht Club in Half Moon Bay, CA. 

ADDRESSES: You may submit comments 

on this document, identified by NOAA– 


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