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

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-returnvalve. Failure of the HP Stage 5 air nonreturn valve in the open position could resultin 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; andSection 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:


## 17008 Federal Register / Vol. 80, No. 61 / Tuesday, March 31, 2015 / Proposed Rules

• 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


## 17009 Federal Register / Vol. 80, No. 61 / Tuesday, March 31, 2015 / Proposed Rules

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 inparagraphs (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.


## 17010 Federal Register / Vol. 80, No. 61 / Tuesday, March 31, 2015 / Proposed Rules

(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 (NO X 

### ) from Units 1 and 2 at Coronado. While the plant-wide limit for the NO X 

### 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: