### 21578 Federal Register / Vol. 78, No. 70 / Thursday, April 11, 2013 / Proposed Rules

paragraph (l)(2) of this AD: Do a detailed inspection of the cam latches and latch pins to detect damage, distress, and incorrect rigging; torque the cross bolts; measure the extension of the latch pins; replace all alloy steel bolts used as latch pin cross bolts with corrosion resistant steel (CRES) bolts; rig the MCD, as applicable; and do all applicable related investigative and corrective actions, in accordance with the Accomplishment Instructions of Boeing Alert Service Bulletin 757–52A0091, dated March 9, 2010, except as required by paragraph (l)(2) of this AD. Do all applicable related investigative and corrective actions at the applicable time specified in paragraph 1.E., ‘‘Compliance’’ of Boeing Alert Service Bulletin 757–52A0091, dated March 9, 2010.
(h) Repetitive Inspections

Repeat the applicable inspections specified in paragraph (g) of this AD, as specified in paragraphs (h)(1), (h)(2), and (h)(3) of this AD, at the applicable times specified in table 1 of paragraph 1.E., ‘‘Compliance,’’ of Boeing Alert Service Bulletin 757–52A0091, dated March 9, 2010. The inspection conditions are defined in Boeing Alert Service Bulletin 757– 52A0091, dated March 9, 2010.

(1) For airplanes found with Inspection Condition 5: Repeat the general visual inspection for broken, cracked, missing, or migrated parts of the cam latches and latch pins.

(2) For airplanes found with Inspection Condition 2, 4.2, or 5: Repeat the detailed inspection for damage, distress, and incorrect rigging of the cam latches and latch pins.

(3) For airplanes found with Inspection Condition 5: Repeat the high frequency eddy current or magnetic particle inspection to detect signs of cracking of cam latches 1 and
2. (i) MCD Post-Rigging Initial Inspections and Related Investigative and Corrective Actions

At the applicable times specified in table 2 of paragraph 1.E., ‘‘Compliance,’’ of Boeing Alert Service Bulletin 757–52A0091, dated March 9, 2010: Do a general visual inspection of the cam latches and latch pins for discrepancies; a detailed inspection of the cam latches and latch pins for discrepancies; and an HFEC or magnetic particle inspection of cam latch 1 and cam latch 2 for cracking; and do all applicable related investigative and corrective actions, except as required by paragraph (l)(2) of this AD; in accordance with the Accomplishment Instructions of Boeing Alert Service Bulletin 757–52A0091, dated March 9, 2010. Do all applicable related investigative and corrective actions at the applicable time specified in paragraph 1.E., ‘‘Compliance,’’ of Boeing Alert Service Bulletin 757–52A0091, dated March 9, 2010.
(j) MCD Post-Rigging Repetitive Inspections

(1) For all airplanes: Repeat the inspections specified in paragraph (i) of this AD, at the applicable times specified in table 2 of paragraph 1.E., ‘‘Compliance,’’ of Boeing Alert Service Bulletin 757–52A0091, dated March 9, 2010.

(2) For airplanes found with Inspection Condition 2 as defined in Boeing Alert Service Bulletin 757–52A0091, dated March 9, 2010: Repeat the detailed inspection for damage, distress, and incorrect rigging of the cam latches and latch pins specified in paragraph (i) of this AD on remaining cam latches and cam pins at the applicable times specified in table 2 of paragraph 1.E., ‘‘Compliance,’’ of Boeing Alert Service Bulletin 757–52A0091, dated March 9, 2010.
(k) Parts Installation Prohibition

As of the effective date of this AD, no person may install an alloy steel bolt as a cross bolt through any latch pin fitting assembly in the lower sill of the MCD on any airplane.
(l) Exceptions to Service Bulletin Specifications

The following exceptions apply in this AD. (1) Where Boeing Alert Service Bulletin 757–52A0091, dated March 9, 2010, specifies a compliance time after the date of that service bulletin, this AD requires compliance within the specified compliance time after the effective date of this AD.

(2) Where Boeing Alert Service Bulletin 757–52A0091, dated March 9, 2010, specifies to contact Boeing for appropriate action: Before further flight, repair the discrepancy in accordance with a method approved by the Manager, Seattle, Aircraft Certification Office (ACO), FAA. For a repair method to be approved, the repair must meet the certification basis of the airplane, and the approval must specifically refer to this AD.
(m) Alternative Methods of Compliance (AMOCs)

(1) The Manager, Seattle 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 the Related Information section of this AD. Information may be emailed to: 9-ANMSeattle-ACO-AMOC-Requests@faa.gov

.

(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.

(3) An AMOC that provides an acceptable level of safety may be used for any repair required by this AD if it is approved by the Boeing Commercial Airplanes Organization Designation Authorization (ODA) that has been authorized by the Manager, Seattle ACO to make those findings. For a repair method to be approved, the repair must meet the certification basis of the airplane and the approval must specifically refer to this AD.
(n) Related Information

(1) For more information about this AD, contact Kimberly DeVoe, Aerospace Engineer, Cabin Safety and Environmental Systems Branch, ANM–150S, FAA, Seattle Aircraft Certification Office, 1601 Lind Avenue SW., Renton, WA 98057–3356; phone: (425) 917–6495 ; fax: (425) 917–6590; email: kimberly.devoe@faa.gov

.

(2) For service information identified in this AD, contact Boeing Commercial Airplanes, Attention: Data & Services Management, P.O. Box 3707, MC 2H–65, Seattle, Washington 98124–2207; telephone 206–544–5000, extension 1; fax 206–766– 5680; Internet https:// www.myboeingfleet.com . You may review copies of the referenced service information at the FAA, Transport Airplane Directorate, 1601 Lind Avenue SW., Renton, Washington. For information on the availability of this material at the FAA, call 425–227–1221.

Issued in Renton, Washington, on March 28, 2013. Ali Bahrami, Manager, Transport Airplane Directorate, Aircraft Certification Service.

[FR Doc. 2013–08450 Filed 4–10–13; 8:45 am]

**BILLING CODE 4910–13–P**

**DEPARTMENT OF TRANSPORTATION**

**Federal Aviation Administration**

**14 CFR Part 39**

**[Docket No. FAA–2013–0195; Directorate Identifier 2013–NE–08–AD]** 

**RIN 2120–AA64**

**Airworthiness Directives; General Electric Company Turbofan Engines** 

**AGENCY :**  Federal Aviation Administration (FAA), DOT.

**ACTION :**  Notice of proposed rulemaking (NPRM).

**SUMMARY :**  We propose to adopt a new airworthiness directive (AD) for all General Electric Company (GE) model GEnx-2B67 and GEnx-2B67B turbofan engines with booster anti-ice (BAI) air duct, part number (P/N) 2469M32G01, and support bracket, P/N 2469M46G01, installed. This proposed AD was prompted by reports of cracks in the BAI air duct. This proposed AD would require initial and repetitive visual inspections of the BAI air duct, removal from service of the BAI air duct if it fails inspection and, as a mandatory terminating action, the installation of new BAI air duct support brackets. We are proposing this AD to prevent failureof the BAI air duct, resulting in an inflight shutdown of one or more engines, loss of thrust control, and damage to the aircraft.

**DATES :**  We must receive comments on this proposed AD by June 10, 2013.

**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,


### 21579 Federal Register / Vol. 78, No. 70 / Thursday, April 11, 2013 / Proposed Rules

M–30, West Building Ground Floor, Room W12–140, 1200 New Jersey Avenue SE., Washington, DC 20590.

• Hand Delivery: Deliver to Mail address above between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays.

For service information identified in this proposed AD, contact General Electric, One Neumann Way, MD Y–75, Cincinnati, OH; phone: 513–552–2913; email: geae.aoc@ge.com; and Web site: www.GE.com. You may view this service information at the FAA, Engine & Propeller Directorate, 12 New England Executive Park, Burlington, MA. For information on the availability of this material at the FAA, call 781–238–7125. Examining the AD Docket

You may examine the AD docket on the Internet at http:// www.regulations.gov; 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 (phone: 800–647–5527) is in the

**ADDRESSES** section. Comments will be available in the AD docket shortly after receipt.

**FOR FURTHER INFORMATION CONTACT :**  Jason Yang, Aerospace Engineer, Engine Certification Office, FAA, Engine & Propeller Directorate, 12 New England Executive Park, Burlington, MA 01803; phone: 781–238–7747; fax: 781–238– 7199; email: Jason.Yang@faa.gov

.
**SUPPLEMENTARY INFORMATION :** 
Comments Invited

We invite you to send any written relevant data, views, or arguments about this proposal. Send your comments to an address listed under the **ADDRESSES** section. Include ‘‘Docket No. FAA– 2013–0195; Directorate Identifier 2013– NE–08–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 because of 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 propose to adopt a new AD for all GE model GEnx-2B67 and GEnx-2B67B turbofan engines with BAI air duct, P/N 2469M32G01, and support bracket, P/N 2469M46G01, installed. This proposed AD was prompted by 11 reports of cracks in the BAI air duct, P/N 2469M32G01, caused by resonant vibration of the BAI valve system. Engineering analysis determined that the single support bracket is not sufficient to prevent the vibration and cracking in the BAI air duct, and that additional support brackets are needed. This proposed AD would require initial visual inspection of the BAI air duct before it reaches 400 cycles since new (CSN), and repetitive visual inspections every 100 cycles thereafter. If the BAI air duct fails inspection, the proposed AD would require removal of the BAI air duct from service. As a mandatory terminating action, the proposed AD would also require installation of new BAI air duct support brackets at the next removal of the BAI air duct, and replacement of the BAI air duct with a duct eligible for installation. This condition, if not corrected, could result in failure of the BAI air duct, resulting in an in-flight shutdown of one or more engines, loss of thrust control, and damage to the aircraft.

Relevant Service Information

We reviewed GE Service Bulletin (SB) No. GEnx-2B S/B 75–0006, dated July 23, 2012, and GE SB No. GEnx-2B S/B 75–0008, Revision 1, dated February 4, 2013. GE SB No. GEnx-2B S/B 75–0006 describes procedures for inspecting and, if necessary, removing and replacing the BAI air duct. GE SB No. GEnx-2B S/B 75–0008, Revision 1, describes procedures for installing new BAI air duct support brackets, and inspection and possible replacement of BAI air ducts.

FAA’s Determination

We are proposing this AD because we evaluated all the relevant information and determined the unsafe condition described previously is likely to exist or develop in other products of the same type design.
Proposed AD Requirements

This proposed AD would require initial and repetitive visual inspections of the BAI air duct, replacement of the BAI air duct if it fails inspection and, as mandatory terminating action, installation of new BAI air duct support brackets. Costs of Compliance
We estimate that this proposed AD affects 16 engines installed on airplanes of U.S. registry. We also estimate that it would take about 4 hours per engine to comply with this proposed AD. The average labor rate is $85 per hour. Required parts would cost about $11,000 per engine. Based on these figures, we estimate the cost of the proposed AD to U.S. operators to be $181,440. 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 to the extent that it justifies making a regulatory distinction, 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.


### 21580 Federal Register / Vol. 78, No. 70 / Thursday, April 11, 2013 / Proposed Rules

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 adding the following new airworthiness directive (AD):
General Electric Company: Docket No. FAA– 2013–0195; Directorate Identifier 2013– NE–08–AD.
(a) Comments Due Date

We must receive comments by June 10,
2013.
(b) Affected ADs

None. (c) Applicability

This AD applies to all General ElectricCompany (GE) model GEnx-2B67 and GEnx2B67B turbofan engines with booster anti-ice (BAI) air duct, part number (P/N) 2469M32G01, and support bracket, P/N 2469M46G01, installed.

(d) Unsafe Condition

This AD was prompted by reports of cracks in the BAI air duct, P/N 2469M32G01. We are issuing this AD to prevent failure of the BAI air duct, resulting in an in-flight shutdown of one or more engines, loss of thrust control, and damage to the aircraft.
(e) Compliance

Comply with this AD within the compliance times specified, unless already done.
(f) Inspection of BAI Air Duct

(1) Perform an initial visual inspection of the BAI air duct, P/N 2469M32G01, for cracks prior to accumulating 400 cycles since new (CSN).

(2) Thereafter, repeat the visual inspection within every 100 cycles since last inspection.

(3) If cracks in the BAI air duct are found during any inspection required by this AD, remove the BAI air duct from service.
(g) Mandatory Terminating Action

As mandatory terminating action to the repetitive inspection requirement of this AD, at the next removal of BAI air duct, P/N 2469M32G01, or if the BAI air duct is found cracked, after the effective date of this AD, do the following:

(1) Install new BAI air duct support brackets, P/Ns 2550M03G01, 2548M66G01, 2548M67P01, 2550M18G01, and 2550M17P01.

(2) Replace the BAI air duct with one that is eligible for installation.

(h) Definitions

For the purpose of this AD, a BAI air duct that is eligible for installation is one that has accumulated 25 CSN or fewer.
(i) Alternative Methods of Compliance (AMOCs)

The Manager, Engine Certification Office, FAA, may approve AMOCs for this AD. Use the procedures found in 14 CFR 39.19 to make your request.
(j) Related Information

(1) For more information about this AD, contact Jason Yang, Aerospace Engineer, Engine Certification Office, FAA, Engine & Propeller Directorate, 12 New England Executive Park, Burlington, MA 01803; phone: 781–238–7747; fax: 781–238–7199; email: Jason.Yang@faa.gov.

(2) Refer to GE Service Bulletin (SB) No. GEnx-2B S/B 75–0006, dated July 23, 2012, and GE SB No. GEnx-2B S/B 75–0008, Revision 1, dated February 4, 2013, for guidance on inspecting and, if necessary, removing and replacing the BAI air duct, as well as procedures for installation of new BAI air duct support brackets.

(3) For service information identified in this proposed AD, contact General Electric, One Neumann Way, MD Y–75, Cincinnati, OH; phone: 513–552–2913; email: geae.aoc@ge.com; and Web site: www.GE.com. You may view this service information at the FAA, Engine & Propeller Directorate, 12 New England Executive Park, Burlington, MA. For information on the availability of this material at the FAA, call
781–238–7125.

Issued in Burlington, Massachusetts, on April 4, 2013. Robert J. Ganley, Acting Assistant Manager, Engine & Propeller Directorate, Aircraft Certification Service.
[FR Doc. 2013–08447 Filed 4–10–13; 8:45 am]

**BILLING CODE 4910–13–P**

**ENVIRONMENTAL PROTECTION AGENCY** 

**40 CFR Part 52**

**[EPA–R09–OAR–2013–0103; FRL–9794–3]**

**Revisions to the California State Implementation Plan, Santa Barbara**  **and San Diego County Air Pollution Control Districts** 

**AGENCY :**  Environmental Protection Agency (EPA).

**ACTION :**  Proposed rule.

**SUMMARY :**  EPA is proposing to approve revisions to the Santa Barbara County Air Pollution Control District (SBCAPCD) and San Diego County Air Pollution Control District (SDCAPCD) portions of the California State Implementation Plan (SIP). These revisions concern volatile organic compound (VOC) emissions from surface coating of aerospace vehicles and components and from wood products coating operations. We are proposing to approve local rules to regulate these emission sources under the Clean Air Act as amended in 1990 (CAA or the Act).

**DATES :**  Any comments on this proposal must arrive by May 13, 2013.

**ADDRESSES :**  Submit comments, identified by docket number EPA–R09– OAR–2013–0103, by one of the following methods:

1. Federal eRulemaking Portal: www.regulations.gov. Follow the on-line instructions.

2. Email: steckel.andrew@epa.gov.
3. Mail or deliver: Andrew Steckel (Air–4), U.S. Environmental Protection Agency Region IX, 75 Hawthorne Street, San Francisco, CA 94105–3901.
Instructions: All comments will be included in the public docket without change and may be made available online at www.regulations.gov, including any personal information provided, unless the comment includes Confidential Business Information (CBI) or other information whose disclosure is restricted by statute. Information that you consider CBI or otherwise protected should be clearly identified as such and should not be submitted through www.regulations.gov or email. www.regulations.gov is an ‘‘anonymous access’’ system, and EPA will not know your identity or contact information unless you provide it in the body of your comment. If you send email directly to EPA, your email address will be automatically captured and included as part of the public comment. If EPA cannot read your comment due to technical difficulties and cannot contact you for clarification, EPA may not be able to consider your comment. Electronic files should avoid the use of special characters, any form of encryption, and be free of any defects or viruses.

Docket: Generally, documents in the docket for this action are available electronically at www.regulations.gov and in hard copy at EPA Region IX, 75 Hawthorne Street, San Francisco, California. While all documents in the docket are listed at www.regulations.gov, some information may be publicly available only at the hard copy location (e.g., copyrighted material, large maps), and some may not be publicly available in either location (e.g., CBI). To inspect the hard copy materials, please schedule an