## 75291 Federal Register / Vol. 78, No. 238 / Wednesday, December 11, 2013 / Proposed Rules

(a) Comments Due Date

We must receive comments by January 27,
2014.
(b) Affected ADs

None. (c) Applicability

This AD applies to all BAE SYSTEMS (OPERATIONS) LIMITED Model BAe 146– 100A, –200A, and –300A airplanes; and Model Avro 146–RJ70A, 146–RJ85A, and 146–RJ100A airplanes; certificated in any category; all models, all serial numbers.
(d) Subject

Air Transport Association (ATA) of America Code 32, Landing Gear.
(e) Reason

This AD was prompted by reports of cracking of the main fitting of the nose landing gear (NLG). We are issuing this AD to prevent collapse of the NLG, which could lead to degradation of direction control on the ground or an un-commanded turn to the left and a consequent loss of control of the airplane on the ground, possibly resulting in damage to the airplane and injury to occupants. (f) Compliance

Comply with this AD within the compliance times specified, unless already done.
(g) Revise Maintenance or Inspection Program

Within 30 days after the effective date of this AD: Revise the maintenance or inspection program to incorporate a new safe-life limitation of the NLG main fitting, as specified by BAE Systems BAe 146 Series/ AVRO 146–RJ Series Aircraft Maintenance Manual, Revision 108, dated September 15, 2012. Comply with all applicable instructions and airworthiness limitations included in BAE Systems BAe 146 Series/ AVRO 146–RJ Series Aircraft Maintenance Manual, Revision 108, dated September 15, 2012. The initial compliance times for doing the actions is at the applicable times specified in BAE Systems BAe 146 Series/ AVRO 146–RJ Series Aircraft Maintenance Manual, Revision 108, dated September 15, 2012, or within 30 days after the effective date of this AD, whichever is later.
(h) No Alternative Actions, Intervals, and/or Critical Design Configuration Control Limitations (CDCCLs)

After accomplishing the revision required by paragraph (g) of this AD, no alternative actions (e.g., inspections), intervals, or CDCCLs may be used unless the actions, intervals, or CDCCLs are approved as an alternative method of compliance (AMOC) in accordance with the procedures specified in paragraph (j)(1) of this AD.
(i) Parts Installation Limitation

As of the effective date of this AD, no person may install an NLG main fitting, having a part number identified in paragraph 1.A., Tables 1., 2., and 3. of BAE SYSTEMS (OPERATIONS) LIMITED Inspection Service Bulletin ISB.32–186, dated April 12, 2012, unless it is in compliance with the requirements of this AD.
(j) 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: Todd Thompson, Aerospace Engineer, International Branch, ANM–116, Transport Airplane Directorate, FAA, 1601 Lind Avenue SW., Renton, WA 98057–3356; telephone 425–227–1175; 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) Airworthy Product: For any requirement in this AD to obtain corrective actions from a manufacturer, use these actions if they are FAA-approved. Corrective actions are considered FAA-approved if they were approved by the State of Design Authority (or its delegated agent, or the design approval holder with a State of Design Authority’s design organization approval). For a repair method to be approved, the repair approval must specifically refer to this AD. You are required to ensure the product is airworthy before it is returned to service.

(k) Related Information

(1) Refer to Mandatory Continuing Airworthiness Information (MCAI) EASA Airworthiness Directive 2012–0191R1, dated November 6, 2012, for related information. This MCAI may be found in the AD docket on the Internet at http://www.regulations.gov.

(2) For service information identified in this AD, contact BAE SYSTEMS (OPERATIONS) LIMITED, Customer Information Department, Prestwick International Airport, Ayrshire, KA9 2RW, Scotland, United Kingdom; telephone +44 1292 675207; fax +44 1292 675704; email RApublications@baesystems.com; Internet http://www.baesystems.com/Businesses/ RegionalAircraft/index.htm. You may review copies of 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 November 29, 2013. John P. Piccola, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service.
[FR Doc. 2013–29514 Filed 12–10–13; 8:45 am]

**BILLING CODE 4910–13–P** 

### DEPARTMENT OF TRANSPORTATION

**Federal Aviation Administration**

**14 CFR Part 39**

**[Docket No. FAA–2013–1025; Directorate Identifier 2013–NM–096–AD]** 

**RIN 2120–AA64**



### Airworthiness Directives; Bombardier, **Inc. Airplanes**

**AGENCY**

### : Federal Aviation Administration (FAA), DOT.

**ACTION** 

### : Notice of proposed rulemaking (NPRM).

**SUMMARY**

### : We propose to adopt a new airworthiness directive (AD) for certain Bombardier, Inc., Model DHC–8–102, –103, and –106 airplanes; and DHC–8– 200 and DHC–8–300 series airplanes. This proposed AD was prompted by a report of a beta warning horn (BWH) system failing to activate when the beta mode was triggered. This proposed AD would require modifying the BWH microswitch installation. We are proposing this AD to prevent the inadvertent activation of ground beta mode during flight, which could lead to engine overspeed, engine damage or failure, and consequent reduced controllability of the airplane.

**DATES** 

### : We must receive comments on this proposed AD by January 27, 2014.

**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 service information identified in this proposed AD, contact Bombardier, Inc., Q-Series Technical Help Desk, 123 Garratt Boulevard, Toronto, Ontario M3K 1Y5, Canada; telephone 416–375– 4000; fax 416–375–4539; email thd.qseries@aero.bombardier.com; Internet http://www.bombardier.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.


## 75292 Federal Register / Vol. 78, No. 238 / Wednesday, December 11, 2013 / Proposed Rules

Examining the AD Docket

You may examine the AD docket on the Internet at http:// www.regulations.gov; or in person at the Docket Operations office between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. The AD docket contains this proposed AD, regulatory evaluation, any comments received, and other information. The street address for the Docket Office (telephone (800) 647– 5527) is in the **ADDRESSES** 

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

**FOR FURTHER INFORMATION CONTACT**

### : Kent Fredrickson, Aerospace Engineer, Propulsion and Flight Test Branch, ANE–173, FAA; New York Aircraft Certification Office, 1600 Stewart Avenue, Suite 410, Westbury, New York 11590; telephone 516–228–7364; fax
516–794–5531.

**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–2013–1025; Directorate Identifier 2013–NM–096–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

Transport Canada Civil Aviation (TCCA), which is the aviation authority for Canada, has issued Canadian Airworthiness Directive CF–2012–01R1, dated March 6, 2013 (referred to after this as the Mandatory Continuing Airworthiness Information, or ‘‘the MCAI’’), to correct an unsafe condition for the specified products. The MCAI
states:
* * * * *

During an on-ground Beta Warning Horn (BWH) system check conducted in the wake of an in-flight Beta range operation incident on a DHC–8 Series 200 aeroplane, it was discovered that the BWH system failed to activate when the Beta mode was triggered.

An investigation by Bombardier had determined that the deformation of the flexible center console cover could cause the BWH system triggering microswitch to malfunction, resulting in dormant failure of the BWH system. To mitigate the safety risk by minimizing the risk exposure period, [TCCA] * * * mandate[d] a 50 hours periodic operational test of the BWH system functionality.

To address the root cause of the subject problem, Bombardier has issued Service Bulletin (SB) 8–76–33 that modifies the BWH microswitch installation by replacing the BWH microswitch attachment bracket with a new, more robust bracket that is not affected by deformation of the center console cover. [TCCA] AD CF–2012–01 is therefore revised to mandate compliance with SB 8–76–33 as terminating action for the 50 hours periodic operational test requirement.


### The unsafe condition is the inadvertent activation of ground beta mode during flight, which could lead to engine overspeed, engine damage or failure, and consequent reduced controllability of the airplane. You may examine the MCAI in the AD docket on the Internet
at http://www.regulations.gov by searching for and locating it in Docket No. FAA–2013–1025.

Relevant Service Information

Bombardier, Inc., has issued Service Bulletin 8–76–33, dated December 13, 2012. The actions described in this service information are intended to correct the unsafe condition identified in the MCAI.
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 the same type design.
Differences Between This Proposed AD and the MCAI or Service Information

Although the MCAI includes an operational test of the BWH system, this proposed AD does not require that action. Once the actions required by this AD are done, the modification of the BWH microswitch installation adequately addresses the identified unsafe condition. Also, AD 2005–13–35, Amendment 39–14172 (70 FR 48854, August 22, 2005), for all Bombardier, Inc., Model DHC–8–100, DHC–8–200, and DHC–8–300 series airplanes, includes a requirement for certain airplanes to perform operational checks of the beta lockout system. This difference has been coordinated with TCCA.
Costs of Compliance

We estimate that this proposed AD affects 94 airplanes of U.S. registry. We estimate the following costs to comply with this proposed AD:



### E STIMATED 

### COSTS

Action Labor cost Parts cost Cost per product Cost on U.S. operators

Modification ............................. 7 work-hours × $85 per hour = $595 ..................................... $117 $712 $66,928



### According to the manufacturer, some of the costs of this proposed AD may be covered under warranty, thereby reducing the cost impact on affected individuals. We do not control warranty coverage for affected individuals. As a result, we have included all costs in our cost estimate. 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


## 75293 Federal Register / Vol. 78, No. 238 / Wednesday, December 11, 2013 / Proposed Rules

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 adding the following new AD:
Bombardier, Inc.: Docket No. FAA–2013– 1025; Directorate Identifier 2013–NM– 096–AD.
(a) Comments Due Date

We must receive comments by January 27,
2014.
(b) Affected ADs

None. (c) Applicability

This AD applies to Bombardier, Inc., Model DHC–8–102, –103, –106, –201, –202, –301, –311, and –315 airplanes; certificated in any category; serial numbers 003 through 672 inclusive with a beta warning horn (BWH) (Mod 8/2852) incorporated; except for airplanes that have incorporated Bombardier option CR873CH00003, CR873CH00005, CR873SOO8112, or MS8Q902206. (d) Subject

Air Transport Association (ATA) of America Code 31, Instruments; Code 76, Engine Controls.
(e) Reason

This AD was prompted by a report of a BWH system failing to activate when the beta mode was triggered. We are issuing this AD to prevent the inadvertent activation of ground beta mode during flight, which could lead to engine overspeed, engine damage or failure, and consequent reduced controllability of the airplane.
(f) Compliance

Comply with this AD within the compliance times specified, unless already done.
(g) Terminating Modification

Within 6,000 flight hours or 36 months, whichever occurs first, after the effective date of this AD: Modify the BWH microswitch installation by replacing the existing BWH microswitch installation bracket with a new bracket having part number 87610164–003, in accordance with the Accomplishment Instructions of Bombardier Service Bulletin 8–76–33, dated December 13, 2012.
(h) Other FAA AD Provisions

The following provisions also apply to this AD:

(1) Alternative Methods of Compliance (AMOCs): The Manager, New York Aircraft Certification Office (ACO), ANE–170, 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 ACO, send it to ATTN: Program Manager, Continuing Operational Safety, FAA, New York ACO, 1600 Stewart Avenue, Suite 410, Westbury, NY 11590; telephone 516–228–7300; fax 516–794–5531. 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) Airworthy Product: For any requirement in this AD to obtain corrective actions from a manufacturer, use these actions if they are FAA-approved. Corrective actions are considered FAA-approved if they were approved by the State of Design Authority (or its delegated agent, or by the Design Approval Holder with a State of Design Authority’s design organization approval). For a repair method to be approved, the repair approval must specifically refer to this AD. You are required to ensure the product is airworthy before it is returned to service.
(i) Related Information

(1) Refer to Mandatory Continuing Airworthiness Information (MCAI) Canadian Airworthiness Directive CF–2012–01R1, dated March 6, 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 it in Docket No. FAA–2013–1025.

(2) For service information identified in this AD, contact Bombardier, Inc., Q-Series Technical Help Desk, 123 Garratt Boulevard, Toronto, Ontario M3K 1Y5, Canada; telephone 416–375–4000; fax 416–375–4539; email thd.qseries@aero.bombardier.com; Internet http://www.bombardier.com. You may view copies of 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.

Issued in Renton, Washington, on November 29, 2013. Johm P. Piccola, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service.
[FR Doc. 2013–29513 Filed 12–10–13; 8:45 am]

**BILLING CODE 4910–13–P**



### ENVIRONMENTAL PROTECTION **AGENCY**

**40 CFR Part 52**

**[EPA–R09–OAR–2013–0687; FRL9903–99– Region 9]** 



### Approval and Promulgation of **Implementation Plans; State of California; 2012 Los Angeles County**  **State Implementation Plan for 2008 Lead Standard** 

**AGENCY**

### : U.S. Environmental Protection Agency (EPA).

**ACTION** 

### : Proposed rule.

**SUMMARY**

### : EPA is proposing to approve a State implementation plan revision submitted by the State of California to provide for attainment of the 2008 lead national ambient air quality standard in the Los Angeles County nonattainment area. The submitted SIP revision is the Final 2012 Lead State Implementation Plan—Los Angeles County. Specifically, EPA is proposing to approve the emissions inventory, attainment demonstration, the reasonably available control measures/reasonably available control technology, reasonable further progress demonstration, and contingency measures as meeting the requirements of the Clean Air Act and EPA’s implementing regulations for the lead NAAQS.

**DATES** 

### : Any comments must arrive by January 10, 2014.

**ADDRESSES** 

### : Submit comments, identified by docket number EPA–R09– OAR–2013–0687, by one of the following methods: