### 42724 Federal Register / Vol. 78, No. 137 / Wednesday, July 17, 2013 / Proposed Rules

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 adding the following new AD:

Pilatus Aircraft Ltd.: Docket No. FAA–2013– 0610; Directorate Identifier 2013–CE– 017–AD.
(a) Comments Due Date

We must receive comments by September 3, 2013. (b) Affected ADs

None. (c) Applicability

This AD applies to Pilatus Aircraft Ltd. Model PC–12/47E airplanes, serial numbers 545, and 1001 through 1450, certificated in any category. (d) Subject

Air Transport Association of America (ATA) Code 34: Navigation.
(e) Reason

This proposed AD results from mandatory continuing airworthiness information (MCAI) originated by an aviation authority of another country to identify and correct an unsafe condition on an aviation product. The MCAI describes the unsafe condition as common grounding of both the pilot Primary Flight Display (PFD) and the Electronic Standby Instrument System (ESIS). If the common ground fails both navigations systems could fail simultaneously, which could result in loss of control. We are issuing this proposed AD to require actions to address the unsafe condition on these products.
(f) Actions and Compliance

Unless already done, within 3 months after the effective date of this AD, modify the ESIS return wire ground connections following the accomplishment instructions in Pilatus Aircraft Ltd. PC–12 Service Bulletin No. 34– 038, dated March 26, 2013.
(g) Other FAA AD Provisions

The following provisions also apply to this AD:

(1) Alternative Methods of Compliance (AMOCs): The Manager, Standards Office, FAA, has the authority to approve AMOCs for this AD, if requested using the procedures found in 14 CFR 39.19. Send information to ATTN: Doug Rudolph, Aerospace Engineer, FAA, Small Airplane Directorate, 901 Locust, Room 301, Kansas City, Missouri 64106; telephone: (816) 329–4059; fax: (816) 329– 4090; email:. Before using any approved AMOC on any airplane to which the AMOC applies, notify your appropriate principal inspector (PI) in the FAA Flight Standards District Office (FSDO), or lacking a PI, your local FSDO.

(2) Airworthy Product: For any requirement in this AD to obtain corrective actions from a manufacturer or other source, use these actions if they are FAA-approved. Corrective actions are considered FAA-approved if they are approved by the State of Design Authority (or their delegated agent). You are required to assure the product is airworthy before it is returned to service.
(h) Related Information

Refer to MCAI European Aviation Safety Agency (EASA) AD No.: 2013–0114, dated May 28, 2013, for related information, which can be found in the AD docket on the Internet at http://www.regulations.gov. For service information related to this AD, contact Pilatus Aircraft LTD., Customer Service Manager, CH–6371 STANS, Switzerland; telephone: +41 (0) 41 619 65 01; fax: +41 (0) 41 619 65 76; Internet: http:// www.pilatus-aircraft.com/#32. You may review copies of the referenced service information at the FAA, Small Airplane Directorate, 901 Locust, Kansas City, Missouri 64106. For information on the availability of this material at the FAA, call (816) 329–4148.

Issued in Kansas City, Missouri, on July 11,
2013. John Colomy, Acting Manager, Small Airplane Directorate, Aircraft Certification Service.

[FR Doc. 2013–17142 Filed 7–16–13; 8:45 am]

**BILLING CODE 4910–13–P**

**DEPARTMENT OF TRANSPORTATION**

**Federal Aviation Administration**

**14 CFR Part 39**

**[Docket No. FAA–2013–0611; Directorate Identifier 2013–CE–019–AD]** 

**RIN 2120–AA64**

**Airworthiness Directives; Beechcraft Corporation Airplanes** 

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

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

**SUMMARY :**  We propose to supersede airworthiness directive (AD) 2011–27– 51 that applies to certain Beechcraft Corporation Models 1900, 1900C, and 1900D airplanes. AD 2011–27–51 currently requires inspecting the elevator bob-weight and attaching linkage for correct installation and for damage or deformation to the weight and/or weight bracket with corrective action as necessary. Since we issued AD2011–27–51, a secondary elevator bobweight stop bolt has been designed. This proposed AD would require installation of the secondary elevator bob-weight stop bolt. The elevator bob-weight (stabilizer weight) traveling past its stop bolt may allow the attaching linkage to move over-center and lead to reduced nose down elevator control, which could result in loss of control. We are proposing this AD to correct the unsafe condition on these products.

**DATES :**  We must receive comments on this proposed AD by September 3, 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, M– 30, West Building Ground Floor, Room


### 42725 Federal Register / Vol. 78, No. 137 / Wednesday, July 17, 2013 / Proposed Rules

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 AD, contact Beechcraft Corporation at P.O. Box 85, Wichita, Kansas 67201– 0085; telephone: (800) 429–5372 or (316) 676–3140; Internet: http:// www.beechcraft.com. Beechcraft Corporation publishes service information for the Beechcraft Corporation airplanes affected by this AD action. You may review copies of the referenced service information at the FAA, Small Airplane Directorate, 901 Locust, Kansas City, Missouri 64106. For information on the availability of this material at the FAA, call (816) 329–
4148. 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 :**  Don Ristow, Aerospace Engineer, Wichita ACO, FAA, 1801 Airport Road, Room 100, Wichita, Kansas 67209; telephone: (316) 946–4120; fax: (316) 946–4107; email: donald.ristow@faa.gov.

**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–2013–0611; Directorate Identifier 2013–CE–019–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

On January 6, 2012, we issued AD 2011–27–51, Amendment 39–16915 (77 FR 2439, January 18, 2012), for certain Hawker Beechcraft Corporation Models 1900, 1900C, and 1900D airplanes. AD 2011–27–51 requires inspecting the elevator bob-weight and attaching linkage for correct installation and for damage or deformation to the weight and/or weight bracket with corrective action as necessary. AD 2011–27–51 resulted from reports of the elevator bob-weight (stabilizer weight) traveling past its stop bolt and allowing the attaching linkage to move over-center, which could lead to reduced nose down elevator control. We issued AD 2011– 27–51 to detect and correct conditions that could result in reduced nose down elevator control and loss of control. Actions Since AD 2011–27–51 Was Issued

Since we issued AD 2011–27–51 (77 FR 2439, January 18, 2012), Beechcraft Corporation designed a secondary elevator bob-weight stop bolt to reduce the possibility of the bob-weight from traveling past the stop bolt.

Relevant Service Information

We reviewed Hawker Beechcraft Corporation Safety Communique  ́ No. 321, dated December 2011, and Beechcraft Corporation Mandatory Service Bulletin No. SB 27–4119, dated June 2013. The service information describes procedures for inspecting the elevator bob-weight and attaching linkage for correct installation and for damage or deformation to the weight and/or weight bracket. The service information also describes procedures for installing the secondary elevator bob-weight stop bolt, Kit 114–5060.

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 retain all of the requirements of AD 2011–27–51 (77 FR 2439, January 18, 2012). This proposed AD would also add the requirement to install the secondary elevator bob-weight stop bolt, Kit 114–
5060. Costs of Compliance

We estimate that this proposed AD affects 165 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

Inspection of the elevator bob-weight and

attaching linkage. 1 work-hour × $85 per hour = $85 ........... Not applicable ........... $85 $14,025

Installation of the secondary elevator bobweight stop bolt, Kit 114-5060. 4 work-hours × $85 per hour = $340 ....... $2,740 ....................... 3,080 508,200

The on-condition costs for any corrective action that may be necessary based on the above inspection would vary from airplane to airplane, and we have no way of determining that cost.

The cost of the inspection is a retained cost from AD 2011–27–51 (77 FR 2439, January 18, 2012) and does not add a burden over what was already imposed. 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


### 42726 Federal Register / Vol. 78, No. 137 / Wednesday, July 17, 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 have 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 that the 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) 2011–27–51, Amendment 39–16915 (77 FR 2439, January 18, 2012), and adding the following new AD:
Beechcraft Corporation: Docket No. FAA– 2013–0611; Directorate Identifier 2013–
CE–019–AD.

(a) Comments Due Date

The FAA must receive comments on this AD action by September 3, 2013.

(b) Affected ADs

This AD supersedes AD 2011–27–51, Amendment 39–16915 (77 FR 2439, January 18, 2012).
(c) Applicability

This AD applies to the following Beechcraft Corporation airplanes, certificated in any category:

Models Serial Nos.

(1) 1900 ....................................................................................................................... ...... UA–3. (2) 1900C ........................................................................................................................... UB–1 through UB–74 and UC–1 through UC–174. (3) 1900C (Military) ............................................................................................................ UD–1 through UD–6. (4) 1900D ........................................................................................................................... UE–1 through UE–439.

(d) Subject

Joint Aircraft System Component (JASC)/ Air Transport Association (ATA) of America Code 27, Flight Controls.

(e) Unsafe Condition

This AD was prompted by reports of the elevator bob-weight (stabilizer weight) traveling past its stop bolt and allowing the attaching linkage to move over-center, which could lead to reduced nose down elevator control. Also, Beechcraft Corporation designed a secondary elevator bob-weightstop bolt to reduce the possibility of the bobweight from traveling past the stop bolt. We are issuing this AD to prevent the elevator bob-weight (stabilizer weight) traveling past its stop bolt and allowing the attaching linkage to move over-center and lead to reduced nose down elevator control, which could result in loss of control.
(f) Compliance

Comply with this AD within the compliance times specified, unless already done. Paragraph (g) of this AD only applies to airplanes where the inspection required by AD 2011–27–51 (77 FR 2439, January 18, 2012) has not been done.
(g) Retained Inspections

Within the next 10 hours time-in-service (TIS) after January 18, 2012 (the effective date of AD 2011–27–51 (77 FR 2439, January 18, 2012)), inspect the elevator bob-weight installation for the following conditions specified in paragraphs (g)(1) through (g)(4) in this AD. Use Hawker Beechcraft Corporation Safety Communique  ́ No. 321, dated December 2011 (which is incorporated by reference in AD 2011–27–51).

(1) The correct positioning of the elevator control column link assembly, (part number (P/N) 101–524112–1 (1900/1900C) or P/N 101–524112–5 (1900D)). With the elevator control column in the full nose down position (control column forward), the link must form an angle between the link attachment point at the control column and the bell crank pivot point as shown in the Hawker Beechcraft Corporation Safety Communique  ́ photo labeled ‘‘Correct Link Orientation.’’ The link should be trailing aft from the control column assembly.

Note 1 to paragraphs (g)(1) and (g)(2) of this AD: The term ‘‘nose down’’ corresponds to the airplane nose down, down elevator, and control column forward position as used in this AD and Hawker Beechcraft Corporation Safety Communique  ́ No. 321, dated December 2011.

(2) The clearance of the bob-weight stop bolt. With the elevator control column in the full nose down position (control column forward), the stabilizer weight stop bolt must have positive clearance with the face of the stabilizer weight.

(3) The condition of the bob-weight and alignment with the stop bolt. Inspect for evidence of scraping along either side of the weight by the stop bolt. With side pressure applied by hand to the stabilizer weight, no part of the stop bolt should protrude beyond the face of the stabilizer weight on either edge.

(4) The condition of the bob-weight support bracket. Inspect for evidence of damage or deformation by contact with the weight assembly.
(h) Installation of Kit 114–5060

Within the next 600 hours TIS after the effective date of this AD, install the secondary elevator bob-weight stop bolt, Kit 114–5060, following Beechcraft Corporation Mandatory Service Bulletin No. SB 27–4119, dated June 2013.
(i) Corrective Actions

If any discrepancies are found during the inspection required in paragraph (g) of this AD, including all subparagraphs, and during the installation required in paragraph (h) of this AD, before further flight, contact Beechcraft Corporation Technical Support. If a deviation from FAA-approved type design is required, then request an alternative method of compliance (AMOC) as described in paragraph (j) of this AD. You may contact Beechcraft Technical Support by telephone at (800) 429–5372 or (316) 676–3140.
(j) Alternative Methods of Compliance (AMOCs)

(1) The Manager, Wichita 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.

(2) Before using any approved AMOC, notify your appropriate principal inspector,


### 42727 Federal Register / Vol. 78, No. 137 / Wednesday, July 17, 2013 / Proposed Rules

or lacking a principal inspector, the manager of the local flight standards district office/ certificate holding district office.

(3) AMOCs approved for AD 2011–27–51 (77 FR 2439, January 18, 2012) are approved as AMOCs for the corresponding provisions of this AD.

(k) Related Information

(1) For more information about this AD, contact Don Ristow, Aerospace Engineer, Wichita ACO, FAA, 1801 Airport Road, Room 100, Wichita, Kansas 67209; telephone: (316) 946–4120; fax: (316) 946–4107; email: donald.ristow@faa.gov.

(2) For service information identified in this AD, contact Beechcraft Corporation at P.O. Box 85, Wichita, Kansas 67201–0085; telephone: (800) 429–5372 or (316) 676–3140; Internet: http://www.beechcraft.com. Beechcraft Corporation publishes service information for the Beechcraft Corporation airplanes affected by this AD action. You may review copies of the referenced service information at the FAA, Small Airplane Directorate, 901 Locust, Kansas City, Missouri 64106. For information on the availability of this material at the FAA, call (816) 329–4148.

Issued in Kansas City, Missouri, on July 11,
2013. John Colomy, Acting Manager, Small Airplane Directorate, Aircraft Certification Service.

[FR Doc. 2013–17146 Filed 7–16–13; 8:45 am]

**BILLING CODE 4910–13–P**

**DEPARTMENT OF TRANSPORTATION**

**Federal Aviation Administration**

**14 CFR Part 39**

**[Docket No. FAA–2013–0544; Directorate Identifier 2012–NM–057–AD]** 

**RIN 2120–AA64**

**Airworthiness Directives; the Boeing Company 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 the Boeing Company Model 777–200 series airplanes. This proposed AD was prompted by reports of smoke or flames in the passenger cabin of various transport category airplanes, related tothe wiring for the passenger cabin inflight entertainment (IFE) system, cabin lighting, and passenger seats. This proposed AD would require, for certain airplanes, doing an inspection of the electrical power control panel for a certain part number, and corrective action if necessary; and for certain other airplanes, installing a new electrical power control panel, and making changes to the wiring and certain electrical load management system (ELMS) panels. We are proposing this AD to ensure that the flightcrew is able to turn off electrical power to the IFE systems and other non-essential electrical systems through a switch in the flight compartment in the event of smoke or flames. In the event of smoke or flames in the airplane flight deck or passenger cabin, the flightcrew’s inability to turn off electrical power to the IFE system and other non-essential electrical systems could result in the inability to control smoke or flames in the airplane flight deck or passenger cabin during a non-normal or emergency situation, and consequent loss of control of the airplane.

**DATES :**  We must receive comments on this proposed AD by September 3, 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, 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 Boeing Commercial Airplanes, Attention: Data & Services Management, P.O. Box 3707, MC 2H–65, Seattle, WA 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, WA. For information on the availability of this material at the FAA, call 425–227–2112. 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 :**  Ray Mei, Aerospace Engineer, Systems and Equipment Branch, ANM–130S, FAA, Seattle Aircraft Certification Office, 1601 Lind Avenue SW., Renton, WA 98057–3356; phone: 425–917–6467; fax: 425–917–6590; email: raymont.mei@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– 2013–0544; Directorate Identifier 2012– NM–057–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 have received reports of smoke or flames in the passenger cabin of various transport category airplanes (the Boeing Company Model MD–11 and DC–9 airplanes and Lockheed Martin Corporation/Lockheed Martin Aeronautics Company Model L–1011 series airplanes), related to the wiring for the passenger cabin IFE system, cabin lighting, and passenger seats. In response to these reports of smoke or flames in the passenger cabin of various models of transport category airplanes, we conducted a comprehensive IFE systems review.

The systems review determined that, in order to minimize the risk of smoke or flames in the passenger cabin, a switch is needed in the flight compartment to enable the flightcrew to turn off electrical power to the IFE system and other non-essential electrical systems. In the event of smoke or flames in the airplane flight deck or passenger cabin, the flightcrew’s inability to turn off power to the IFE system and other non-essential electrical systems could result in the inability to control smoke or flames in the airplane flight deck or passenger cabin during a non-normal or emergency situation.