Federal Register / Vol. 80, No. 61 / Tuesday, March 31, 2015 / Proposed Rules 17007 

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. Amend § 39.13 by adding the 

following new airworthiness directive 

(AD): 

Gulfstream Aerospace Corporation: Docket 

No. FAA–2015–0677; Directorate 

Identifier 2013–NM–244–AD. 

(a) Comments Due Date 

We must receive comments by May 15, 

2015. 

(b) Affected ADs 

None. 

(c) Applicability 

This AD applies to all Gulfstream 

Aerospace Corporation Model GVI airplanes, 

certificated in any category. 

(d) Subject 

Air Transport Association (ATA) of 

America Code 36, Pneumatic. 

(e) Unsafe Condition 

This AD was prompted by reports of 

corrosion on in-service air non-return valves. 

We are issuing this AD to ensure the 

flightcrew is provided with procedures to 

mitigate the risks associated with failure of 

the high pressure (HP) Stage 5 air non-return 

valve. Failure of the HP Stage 5 air nonreturn valve in the open position could result 

in engine instability and uncommanded inflight shutdown. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Revision of the Airplane Flight Manual 

(AFM) 

Within 30 days after the effective date of 

this AD: Revise the Emergency Procedures 

section of the AFM by inserting Section 04– 

08–20, Normal Airstart-Automatic; Section 

04–08–30, Manual Airstart-Starter Assist; and 

Section 04–08–40, Manual AirstartWindmilling; of Chapter 04, Emergency 

Procedures; of the Gulfstream GVI (G650) 

AFM, Document Number GAC–AC–G650– 

OPS–0001, Revision 5, dated August 12, 

2013. 

(h) Revision of Maintenance or Inspection 

Program 

Within 30 days after the effective date of 

this AD: Revise the airplane maintenance 

manual or inspection program, as applicable, 

by incorporating the requirement for the HP 

Stage 5 air non-return valve from Section 05– 

10–10, Airworthiness Limitations, of Chapter 

05, Time Limits/Maintenance Checks, of the 

Gulfstream GVI (G650) Maintenance Manual 

(MM), Revision 4, dated September 30, 2013. 

The initial compliance time for replacement 

of the HP Stage 5 air non-return valve is at 

the applicable time specified in Section 05– 

10–10, Airworthiness Limitations, of Chapter 

05, Time Limits/Maintenance Checks, of the 

Gulfstream GVI (G650) MM, Revision 4, 

dated September 30, 2013, or within 30 days 

after the effective date of this AD, whichever 

occurs later. 

(i) No Alternative Actions or Intervals 

After the maintenance or inspection 

program has been revised, as required by 

paragraph (h) of this AD, no alternative 

actions (e.g., inspections) or intervals may be 

used unless the actions or intervals are 

approved as an alternative method of 

compliance in accordance with the 

procedures specified in paragraph (j) of this 

AD. 

(j) Alternative Methods of Compliance 

(AMOCs) 

(1) The Manager, Atlanta Aircraft 

Certification Office (ACO), 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 manager of the ACO, send it to the 

attention of the person identified in 

paragraph (k)(1) of this AD. 

(2) 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. 

(k) Related Information 

(1) For more information about this AD, 

contact Eric Potter, Aerospace Engineer, 

Propulsion and Services Branch, ACE–118A, 

FAA, Atlanta ACO, 1701 Columbia Avenue, 

College Park, GA 30337; phone: 404–474– 

5583; fax: 404–474–5606; email: eric.potter@

faa.gov. 

(2) For service information identified in 

this AD, contact Gulfstream Aerospace 

Corporation, Technical Publications Dept., 

P.O. Box 2206, Savannah, GA 31402–2206; 

telephone 800–810–4853; fax 912–965–3520; 

email pubs@gulfstream.com; Internet http://

www.gulfstream.com/product_support/

technical_pubs/pubs/index.htm. You may 

view this service information at the FAA, 

Transport Airplane Directorate, 1601 Lind 

Avenue SW., Renton, WA. For information 

on the availability of this material at the 

FAA, call 425–227–1221. 

Issued in Renton, Washington, on March 

19, 2015. 

Jeffrey E. Duven, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 2015–07301 Filed 3–30–15; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2015–0678; Directorate 

Identifier 2013–NM–207–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) 2013–13– 

04, for certain Airbus Model A318, 

A319, A320, and A321 series airplanes. 

AD 2013–13–04 currently requires 

installing a power interruption 

protection circuit for the landing gear 

control interface unit (LGCIU). Since we 

issued AD 2013–13–04, we have 

determined that additional work is 

necessary to adequately address the 

identified unsafe condition. This 

proposed AD would require a new 

modification of any previously modified 

LGCIU. This proposed AD would also 

require revising the maintenance or 

inspection program to reduce a certain 

functional check interval. This proposed 

AD also adds airplanes to the 

applicability. We are proposing this AD 

to prevent untimely unlocking and/or 

retraction of the nose landing gear 

(NLG), which, while on the ground, 

could result in injury to ground 

personnel and damage to the airplane. 

DATES: We must receive comments on 

this proposed AD by May 15, 2015. 

ADDRESSES: You may send comments by 

any of the following methods: 


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• 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 AD, contact Airbus, Airworthiness 

Office—EAS, 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. 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– 

0678; 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–2015–0678; Directorate Identifier 

2013–NM–207–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 June 14, 2013, we issued AD 

2013–13–04, Amendment 39–17492 (78 

FR 41286, July 10, 2013). AD 2013–13– 

04 requires actions intended to address 

an unsafe condition on certain Airbus 

Model A318, A319, A320, and A321 

series airplanes. Since we issued AD 

2013–13–04, Amendment 39–17492 (78 

FR 41286, July 10, 2013), the European 

Aviation Safety Agency (EASA), which 

is the Technical Agent for the Member 

States of the European Community, has 

issued EASA Airworthiness Directive 

2013–0202, dated September 5, 2013 

(referred to after this as the Mandatory 

Continuing Airworthiness Information, 

or ‘‘the MCAI’’), to correct an unsafe 

condition for Airbus Model A318–111, 

–112, –121, and –122 airplanes; Model 

A319–111, –112, –113, –114, –115, 

–131, –132, and –133 airplanes; Model 

A320–211, –212, –214, –231, –232, and 

–233 airplanes; and Model A321–111, 

–112, –131, –211, –212, –213, –231, and 

–232 airplanes. The MCAI states: 

After a push back from the gate, an A320 

aeroplane was preparing to initiate taxi, 

when an uncommanded nose landing gear 

(NLG) retraction occurred, causing the nose 

of the aeroplane to hit the ground. 

Investigations revealed that the retraction 

was caused by a combination of a power 

interruption to Landing Gear Control and 

Interface Units (LGCIU) and an internal 

hydraulic leak through the landing gear (LG) 

selector valve 40GA. 

Deeper investigations have revealed that 

LGCIU power interruption appears during 

engine start at each flight. Even though no 

incident has been reported in service, it has 

been determined that a non-compliance to 

the safety objective exists when combined 

with a dormant single failure of the selector 

valve seal leaking. 

This condition, if not corrected, could lead 

to further incidents of untimely unlocking 

and/or retraction of the NLG which, while on 

the ground, could result in injury to ground 

personnel and damage to the aeroplane. 

To address the possible hydraulic leak of 

the LG selector valve, EASA issued AD 2007– 

0065 [http://ad.easa.europa.eu/blob/easa_

ad_2007_0065.pdf/AD_2007-0065] currently 

at Revision 2. 

To address the risk of untimely unlocking 

and/or retraction of the NLG, EASA issued 

AD 2011–0202 [http://ad.easa.europa.eu/

blob/easa_ad_2011_0202.pdf/AD_2011-0202] 

to require installation of a power interruption 

protection circuit to the LGCIU and 

accomplishment of associated modifications. 

Since that [EASA] AD was issued, it has 

been discovered that additional work is 

necessary to adequately correct this unsafe 

condition and consequently, Airbus issued 

Service Bulletin (SB) A320–32–1346 to 

Revision 05. An update of the maintenance 

programme is required as well, following the 

required modification. 

For the reasons described above, this 

[EASA] AD retains the requirements of EASA 

AD 2011–0202, which is superseded, and 

requires certain additional actions, as defined 

in the revised Airbus SB, as applicable to 

aeroplane model, and an update of the 

approved maintenance programme. 

The additional actions include a new 

modification of any previously modified 

LGCIU, and reducing a certain 

functional check interval. This proposed 

AD also adds airplanes on which Airbus 

modification 37866 has been embodied 

in production to the applicability. 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– 

0678. 

Related Service Information Under 1 

CFR Part 51 

Airbus has issued Service Bulletin 

A320–32–1346, Revision 05, dated 

January 13, 2012. The service 

information describes procedures for 

modifying the LGCIU. The actions 

described in this service information are 

intended to correct the unsafe condition 

identified in the MCAI. This service 

information is reasonably available; see 

ADDRESSES for ways to access this 

service information. 

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. 

Costs of Compliance 

We estimate that this proposed AD 

affects 851 airplanes of U.S. registry. 

The actions required by AD 2013–13– 

04, Amendment 39–17492 (78 FR 

41286, July 10, 2013), take about 48 

work-hours per product, at an average 

labor rate of $85 per work-hour. 

Required parts will cost about $8,220 


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per product. Based on these figures, the 

estimated cost of the actions that are 

required by AD 2013–13–04 is $12,300 

per product. 

We estimate that it would take about 

46 work-hours per product to comply 

with the new modification in this 

proposed AD. The average labor rate is 

$85 per work-hour. Required parts 

would cost about $9,650 per product. 

Based on these figures, we estimate the 

cost of the new modification on U.S. 

operators to be $11,539,560 or $13,560 

per product. 

We estimate that it would take about 

1 work-hour per product to revise the 

maintenance or inspection program in 

this proposed AD. The average labor 

rate is $85 per work-hour. Based on 

these figures, we estimate the cost of 

revising the maintenance program on 

U.S. operators to be $72,335 or $85 per 

product. 

Authority for This Rulemaking 

Title 49 of the United States Code 

specifies the FAA’s authority to issue 

rules on aviation safety. Subtitle I, 

section 106, describes the authority of 

the FAA Administrator. ‘‘Subtitle VII: 

Aviation Programs,’’ describes in more 

detail the scope of the Agency’s 

authority. 

We are issuing this rulemaking under 

the authority described in ‘‘Subtitle VII, 

Part A, Subpart III, Section 44701: 

General requirements.’’ Under that 

section, Congress charges the FAA with 

promoting safe flight of civil aircraft in 

air commerce by prescribing regulations 

for practices, methods, and procedures 

the Administrator finds necessary for 

safety in air commerce. This regulation 

is within the scope of that authority 

because it addresses an unsafe condition 

that is likely to exist or develop on 

products identified in this rulemaking 

action. 

Regulatory Findings 

We determined that this proposed AD 

would not have federalism implications 

under Executive Order 13132. This 

proposed AD would not have a 

substantial direct effect on the States, on 

the relationship between the national 

Government and the States, or on the 

distribution of power and 

responsibilities among the various 

levels of government. 

For the reasons discussed above, I 

certify this proposed regulation: 

1. Is not a ‘‘significant regulatory 

action’’ under Executive Order 12866; 

2. Is not a ‘‘significant rule’’ under the 

DOT Regulatory Policies and Procedures 

(44 FR 11034, February 26, 1979); 

3. Will not affect intrastate aviation in 

Alaska; and 

4. Will not have a significant 

economic impact, positive or negative, 

on a substantial number of small entities 

under the criteria of the Regulatory 

Flexibility Act. 

List of Subjects in 14 CFR Part 39 

Air transportation, Aircraft, Aviation 

safety, Incorporation by reference, 

Safety. 

The Proposed Amendment 

Accordingly, under the authority 

delegated to me by the Administrator, 

the FAA proposes to amend 14 CFR part 

39 as follows: 

PART 39—AIRWORTHINESS 

DIRECTIVES 

■ 1. The authority citation for part 39 

continues to read as follows: 

Authority: 49 U.S.C. 106(g), 40113, 44701. 

§ 39.13 [Amended] 

■ 2. The FAA amends § 39.13 by 

removing Airworthiness Directive (AD) 

2013–13–04, Amendment 39–17492 (78 

FR 41286, July 10, 2013), and adding the 

following new AD: 

Airbus: Docket No. FAA–2015–0678; 

Directorate Identifier 2013–NM–207–AD. 

(a) Comments Due Date 

We must receive comments by May 15, 

2015. 

(b) Affected ADs 

This AD replaces AD 2013–13–04, 

Amendment 39–17492 (78 FR 41286, July 10, 

2013). 

(c) Applicability 

(1) This AD applies to Airbus Model A318– 

111, –112, –121, and –122 airplanes; Model 

A319–111, –112, –113, –114, –115, –131, 

–132, and –133 airplanes; Model A320–211, 

–212, –214, –231, –232, and –233 airplanes; 

and Model A321–111, –112, –131, –211, 

–212, –213, –231, and –232 airplanes; 

certificated in any category; all manufacturer 

serial numbers. 

(d) Subject 

Air Transport Association (ATA) of 

America Code 32, Landing Gear. 

(e) Reason 

This AD was prompted by a determination 

that additional work is necessary to 

adequately address the identified unsafe 

condition. We are issuing this AD to prevent 

untimely unlocking and/or retraction of the 

nose landing gear (NLG), which, while on the 

ground, could result in injury to ground 

personnel and damage to the airplane. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Retained Modification 

This paragraph restates the requirements of 

paragraph (g) of AD 2013–13–04, 

Amendment 39–17492 (78 FR 41286, July 10, 

2013). For all airplanes except airplanes on 

which Airbus modification 37866 has been 

embodied in production: At the applicable 

compliance time specified in paragraph (g)(1) 

or (g)(2) of this AD: Install a power 

interruption protection circuit for the landing 

gear control interface unit (LGCIU), in 

accordance with the Accomplishment 

Instructions of Airbus Service Bulletin A320– 

32–1346, Revision 04, including Appendices 

01 and 02, dated April 22, 2011 (for Model 

A318, A319, A320, and A321 series airplanes 

other than the Model A319CJ (corporate jet) 

airplanes); or Airbus Service Bulletin A320– 

32–1349, Revision 03, including Appendix 1, 

dated October 5, 2011 (for Model A319CJ 

(corporate jet) airplanes). 

(1) For airplanes that have embodied 

Airbus Modification 38947 specified in 

Airbus Service Bulletin A320–32–1348 

during production or in service: Within 72 

months after August 14, 2013 (the effective 

date of AD 2013–13–04, Amendment 39– 

17492 (78 FR 41286, July 10, 2013)). 

(2) For all airplanes other than those 

identified in paragraph (g)(1) of this AD: 

Within 60 months after August 14, 2013 (the 

effective date of AD 2013–13–04, 

Amendment 39–17492 (78 FR 41286, July 10, 

2013)). 

(h) Retained Re-Identification of 

Identification Plates 

This paragraph restates the requirements of 

paragraph (h) of AD 2013–13–04, 

Amendment 39–17492 (78 FR 41286, July 10, 

2013). For airplanes on which the installation 

required by paragraph (g) of this AD has been 

done before August 14, 2013 (the effective 

date of AD 2013–13–04, Amendment 39– 

17492 (78 FR 41286, July 10, 2013)) using 

Airbus Service Bulletin A320–32–1346, 

dated December 4, 2008 (for Model A318, 

A319, A320, and A321 series airplanes other 

than Model A319CJ (corporate jet) airplanes): 

Within the applicable times specified in 

paragraphs (g)(1) and (g)(2) of this AD, reidentify the identification plates, in 

accordance with the Accomplishment 

Instructions of Airbus Service Bulletin A320– 

32–1346, Revision 04, including Appendices 

01 and 02, dated April 22, 2011 (for Model 

A318, A319, A320, and A321 series airplanes 

other than Model A319CJ (corporate jet) 

airplanes). 

(i) New Modification 

For airplanes identified in paragraphs 

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

airplanes on which Airbus modification 

37866 has been embodied in production: 

Modify the LGCIU at the applicable time 

specified in paragraph (i)(1), (i)(2), or (i)(3) of 

this AD, in accordance with the 

Accomplishment Instructions of Airbus 

Service Bulletin A320–32–1346, Revision 05, 

dated January 13, 2012, or Airbus Service 

Bulletin A320–32–1349, Revision 03, 

including Appendix 1, dated October 5, 2011 

(for Model A319CJ (corporate jet) airplanes). 

Accomplishing the modification in this 

paragraph terminates the actions required by 

paragraphs (g) and (h) of this AD. 


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(1) For airplanes on which any LG selector 

valve having part number (P/N) 114079019 is 

installed and that have embodied Airbus 

Modification 38947 specified in Airbus 

Service Bulletin A320–32–1348 during 

production or in service: Modify the LGCIU 

within 72 months after the effective date of 

this AD. 

(2) For airplanes on which any LG selector 

valve 40GA having a part number listed in 

paragraphs (i)(2)(i) through (i)(2)(xii) of this 

AD, provided the valve has the marking ‘‘DI’’ 

or ‘‘DI–BE’’ recorded on its amendment 

plates: Modify the LGCIU within 72 months 

after the effective date of this AD. 

(i) P/N 114079001. 

(ii) P/N 114079005. 

(iii) P/N 114079009. 

(iv) P/N 114079013. 

(v) P/N 114079001A. 

(vi) P/N 114079005A. 

(vii) P/N 114079009A. 

(viii) P/N114079015. 

(ix) P/N 114079001AB. 

(x) P/N 114079005AB. 

(xi) P/N 114079009AB. 

(xii) P/N 114079017. 

(3) For all airplanes other than those 

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

this AD: Modify the LGCIU within 60 months 

after the effective date of this AD. 

(j) New Modification for Airplanes 

Previously Modified 

For airplanes that have been modified as of 

the effective date of this AD as specified in 

the applicable service information identified 

in paragraph (j)(1), (j)(2), (j)(3), or (j)(4) of this 

AD, except airplanes on which Airbus 

modification 37866 has been embodied in 

production: Within 72 months after the 

effective date of this AD, do the additional 

modification of the LGCIU, in accordance 

with the Accomplishment Instructions of 

Airbus Service Bulletin A320–32–1346, 

Revision 05, dated January 13, 2012. 

(1) Airbus Service Bulletin A320–32–1346, 

Revision 01, dated October 27, 2009, which 

is not incorporated by reference in this AD. 

(2) Airbus Service Bulletin A320–32–1346, 

Revision 02, dated November 4, 2009, which 

is not incorporated by reference in this AD. 

(3) Airbus Service Bulletin A320–32–1346, 

Revision 03, dated January 7, 2010, which is 

not incorporated by reference in this AD. 

(4) Airbus Service Bulletin A320–32–1346, 

including Appendices 01 and 02, Revision 

04, dated April 22, 2011, which is 

incorporated by reference in AD 2013–13–04, 

Amendment 39–17492 (78 FR 41286, July 10, 

2013). 

(k) New Maintenance or Inspection Program 

Revision 

Before further flight after accomplishing 

the actions specified in paragraph (i) or (j) of 

this AD or within 7 days after the effective 

date of this AD, whichever occurs later: 

Revise the maintenance or inspection 

program, as applicable, to incorporate Task 

32.30.00.17, ‘‘Functional Check of LGCIU 

Power Supply Relays,’’ of Section C–32 of 

Section C, Systems and Powerplant, of the 

Airbus A318/A319/A320/A321 Maintenance 

Review Board Report, Revision 18, dated 

March 2013. The initial compliance time is 

within 4,000 flight hours after accomplishing 

the additional modification of the LGCIU. 

(l) Credit for Previous Actions 

This paragraph provides credit for A319 

Corporate Jet airplanes for the modification 

required by paragraph (g) of this AD if that 

modification was performed before the 

effective date of this AD using Airbus Service 

Bulletin A320–32–1349, dated December 4, 

2008; Airbus Service Bulletin A320–32–1349, 

Revision 01, dated August 31, 2009; or 

Airbus Service Bulletin A320–32–1349, 

Revision 02, dated June 16, 2010. 

(m) 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-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) AMOCs approved previously for AD 

2013–13–04, Amendment 39–17492 (78 FR 

41286, July 10, 2013) are approved as 

AMOCs for the corresponding provisions of 

this AD. 

(3) 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. 

(n) Related Information 

(1) Refer to Mandatory Continuing 

Airworthiness Information (MCAI) EASA 

Airworthiness Directive 2013–0202, dated 

September 5, 2013, 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–2015–0678. 

(2) For service information identified in 

this AD, contact Airbus, Airworthiness 

Office—EAS, 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 March 

20, 2015. 

Michael Kaszycki, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2015–07281 Filed 3–30–15; 8:45 am] 

BILLING CODE 4910–13–P 

ENVIRONMENTAL PROTECTION 

AGENCY 

40 CFR Part 52 

[EPA–R09–OAR–2015–0165; FRL–9925–31– 

Region 9] 

Promulgation of Air Quality 

Implementation Plans; Arizona; 

Regional Haze Federal Implementation 

Plan; Reconsideration 

AGENCY: Environmental Protection 

Agency. 

ACTION: Proposed rule. 

SUMMARY: The Environmental Protection 

Agency (EPA) is proposing to revise part 

of the Arizona Regional Haze (RH) 

Federal Implementation Plan (FIP) 

applicable to the Coronado Generating 

Station (Coronado). In response to a 

petition for reconsideration from the 

Salt River Project Agricultural 

Improvement and Power District (SRP), 

the owner/operator of Coronado, we are 

proposing to replace a plant-wide 

compliance method with a unit-specific 

compliance method for determining 

compliance with the best available 

retrofit technology (BART) emission 

limits for nitrogen oxides (NOX) from 

Units 1 and 2 at Coronado. While the 

plant-wide limit for the NOX emissions 

from Units 1 and 2 were established as 

0.065 lb/MMBtu, we are proposing a 

unit-specific limit of 0.065 lb/MMBtu 

for Unit 1 and 0.080 lb/MMBtu for Unit 

2. In addition, we are proposing to 

revise the work practice standard in the 

FIP for Coronado. Finally, we are 

proposing to remove the affirmative 

defense for malfunctions from the 

Arizona RH FIP, which applies to both 

Coronado and the Cholla Power Plant 

(Cholla). 

DATES: Written comments must be 

submitted to the designated contact on 

or before May 15, 2015. Requests for a 

public hearing must be received on or 

before April 15, 2015. 

ADDRESSES: Submit your comments, 

identified by docket number EPA–R09– 

OAR–2015–0165, by one of the 

following methods: 


asabaliauskas on DSK5VPTVN1PROD with PROPOSALS