### 12617 Federal Register / Vol. 76, No. 45 / Tuesday, March 8, 2011 / Proposed Rules

Dated: March 2, 2011. Otto Barry Bird, Chief Counsel.
[FR Doc. 2011–5128 Filed 3–7–11; 8:45 am]

**BILLING CODE 3510–WH–P**

**DEPARTMENT OF TRANSPORTATION**

**Federal Aviation Administration**

**14 CFR Part 39**

**[Docket No. FAA–2011–0153; Directorate Identifier 2010–NM–022–AD]** 

**RIN 2120–AA64**

**Airworthiness Directives; The Boeing Company Model 777–200 and –300**  **Series 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 Model 777–200 and –300 series airplanes. This proposed AD would require removing the electrical system control panel, changing the wiring, installing a new electrical power control panel, and installing new operational software for the electrical load management system and configuration database. This proposed AD results from an in-flight entertainment (IFE) systems review. We are proposing this AD to ensure that the flightcrew is able to turn off electrical power to the IFE system 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.

**DATES :**  We must receive comments on this proposed AD by April 22, 2011.

**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 20590, 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, Washington 98124– 2207; telephone 206–544–5000, extension 1; fax 206–766–5680; e-mail me.boecom@boeing.com; 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. 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 (telephone 800–647–5527) is in the

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

**FOR FURTHER INFORMATION CONTACT :**  Joe Salameh, Aerospace Engineer, Systems and Equipment Branch, ANM–130S, FAA, Seattle Aircraft Certification Office, 1601 Lind Avenue, SW., Renton, Washington 98057–3356; telephone (425) 917–6454; fax (425) 917–6590.

**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–2011–0153; Directorate Identifier 2010–NM–022–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 In response to numerous reports of smoke or flames in the passenger cabin of various models of transport category airplanes, we conducted a comprehensive in-flight entertainment (IFE) systems review. Earlier investigation of the reports had revealed that the source of the smoke and flames was from cabin IFE system components, including electronic seat boxes mounted under passenger seats, IFE wirings, IFE monitors, cabin lighting, wall outlets, and other non-essential cabin electrical systems.

The systems review disclosed 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 offpower to the IFE system and other nonessential electrical systems, if not corrected, 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.

Relevant Service Information

We have reviewed Boeing Service Bulletin 777–24–0074, Revision 1, dated October 5, 2006. This service bulletin describes procedures for removing the electrical power control panel, changing the wiring, and installing a new electrical power control panel having the two new cabin power control switches.

Boeing Service Bulletin 777–24–0074, Revision 1, dated October 5, 2006, also specifies prior or concurrent accomplishment of Boeing Service Bulletin 777–24–0070, dated April 4, 2002, which describes procedures for installing new operational software (OPS) for the electrical load management system and new configuration database software.

Boeing Service Bulletin 777–24–0074, Revision 1, dated October 5, 2006, refers to Boeing Component Service Bulletin 233W3202–24–04, Revision 1, dated September 25, 2003, as an additional source of guidance for installing the passenger compartment electrical power isolation switches. FAA’s Determination and Requirements of This Proposed AD

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


### 12618 Federal Register / Vol. 76, No. 45 / Tuesday, March 8, 2011 / Proposed Rules

type designs. This proposed AD would require accomplishing the actions specified in the service information described previously. Costs of Compliance
We estimate that this proposed AD would affect 42 airplanes of U.S. registry. The following table provides the estimated costs for U.S. operators to comply with this proposed AD.



### TABLE

### —E STIMATED 

### C OSTS

Action Work hours Average labor rate per hour Parts Cost per product Number of U.S.- registered airplanes Fleet cost

Modification .......................................................................................... 4 $85 $751 $1,091 42 $45, 822 Concurrent modification (Boeing Service Bulletin 777–24–0070) ....... 2 85 0 170 42 7,140

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), and

3. 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.

You can find our regulatory evaluation and the estimated costs of compliance in the AD Docket. 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:
The Boeing Company: Docket No. FAA– 2011–0153; Directorate Identifier 2010– NM–022–AD.

Comments Due Date

(a) We must receive comments by April 22,
2011.

Affected ADs

(b) None.
Applicability

(c) This AD applies to The Boeing Company Model 777–200 and –300 series airplanes, certificated in any category, as identified in Boeing Service Bulletin 777–24– 0074, Revision 1, dated October 5, 2006.
Subject

(d) Air Transport Association (ATA) of America Code 24: Electrical power.

Unsafe Condition

(e) This AD results from an in-flight entertainment (IFE) systems review. We are issuing this AD to ensure that the flightcrew is able to turn off electrical power to the IFE system 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 electricalpower to the IFE system and other nonessential 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.
Compliance

(f) You are responsible for having the actions required by this AD performed within the compliance times specified, unless the actions have already been done.

Modification

(g) Within 60 months after the effective date of this AD, remove the electrical power control panel, change the wiring, and install a new electrical power control panel, in accordance with Boeing Service Bulletin 777–24–0074, Revision 1, dated October 5,
2006.

Note 1: Boeing Service Bulletin 777–24– 0074, Revision 1, dated October 5, 2006, refers to Boeing Component Service Bulletin 233W3202–24–04, Revision 1, dated September 25, 2003, as an additional source of guidance for installing the passenger compartment electrical power isolation switches.

Concurrent Requirements

(h) Prior to or concurrently with accomplishing the requirements of paragraph (g) of this AD, install the electrical load management system operational software and configuration database software, in accordance with the Accomplishment Instructions of Boeing Service Bulletin 777– 24–0070, dated April 4, 2002.
Alternative Methods of Compliance (AMOCs)

(i)(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. Send information to ATTN: Joe Salameh, Aerospace Engineer, Systems and Equipment Branch, ANM–130S, FAA, Seattle Aircraft Certification Office, 1601 Lind Avenue, SW., Renton, Washington 98057– 3356; telephone (425) 917–6454; fax (425) 917–6590. Information may be e-mailed to: 9- ANM-Seattle-ACO-AMOC-Requests@faa.gov.

(2) To request a different method of compliance or a different compliance time for this AD, follow the procedures in 14 CFR 39.19. 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.


### 12619 Federal Register / Vol. 76, No. 45 / Tuesday, March 8, 2011 / Proposed Rules

Issued in Renton, Washington on February 22, 2011. Kalene C. Yanamura, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service.
[FR Doc. 2011–5158 Filed 3–7–11; 8:45 am]

**BILLING CODE 4910–13–P**

**DEPARTMENT OF TRANSPORTATION**

**Federal Aviation Administration**

**14 CFR Part 39**

**[Docket No. FAA–2011–0155; Directorate Identifier 2009–NM–141–AD]** 

**RIN 2120–AA64**

**Airworthiness Directives; The Boeing Company 737–200, –200C, –300, –400,**  **and –500 Series Airplanes**

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

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

**SUMMARY :**  The FAA proposes to supersede an existing airworthiness directive (AD) that applies to certain Boeing Model 737–200, –200C, –300, –400, and –500 series airplanes. The existing AD currently requires repetitive inspections to find fatigue cracking of certain upper and lower skin panels of the fuselage, and follow-on and corrective actions if necessary. The existing AD also includes a terminating action for the repetitive inspections of certain modified or repaired areas only. This proposed AD would add new inspections for cracking of the fuselage skin along certain chem-milled lines, and corrective actions if necessary. This proposed AD would also reduce certain thresholds and intervals required by the existing AD. This proposed AD results from reports of new findings of vertical cracks in the fuselage skin along the chem-milled steps adjacent to the butt joints. We are proposing this AD to detect and correct fatigue cracking of the skin panels, which could result in sudden fracture and failure of the skin panels of the fuselage, and consequent rapid decompression of the airplane.

**DATES :**  We must receive comments on this proposed AD by April 22, 2011.

**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 20590, 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, Washington 98124– 2207; telephone 206–544–5000, extension 1; fax 206–766–5680; e-mail me.boecom@boeing.com; 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. 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 (telephone 800–647–5527) is in the

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

**FOR FURTHER INFORMATION CONTACT :**  Wayne Lockett, Aerospace Engineer, Airframe Branch, ANM–120S, FAA, Seattle Aircraft Certification Office, 1601 Lind Avenue, SW., Renton, Washington 98057–3356; telephone (425) 917–6447; fax (425) 917–6590; e-mail: wayne.lockett@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–2011–0155; Directorate Identifier 2009–NM–141–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 August 26, 2004, we issued AD 2004–18–06, Amendment 39–13784 (69 FR 54206, September 8, 2004), for certain Model 737–200, –200C, –300, –400, and –500 series airplanes. That AD requires repetitive inspections to find fatigue cracking of certain upper and lower skin panels of the fuselage, and follow-on and corrective actions if necessary. That AD also includes a terminating action for the repetitive inspections of certain modified or repaired areas only. That AD resulted from reports indicating new findings of cracks were found along the edges of the chem-milled pockets in the upper skin at certain stringers. We issued that AD to find and fix fatigue cracking of the skin panels, which could result in sudden fracture and failure of the skin panels of the fuselage, and consequent rapid decompression of the airplane. Actions Since Existing AD Was Issued

Since we issued AD 2004–18–06, we have received reports of new findings of vertical cracks in the fuselage skin along the chem-milled steps adjacent to the butt joints and at certain body stations on airplanes with between 45,100 flight cycles (65,200 flight hours) and 67,400 flight cycles (70,800 flight hours).

A decompression event connected to chem-milled steps occurred in July 2009 (after issuance of Boeing Alert Service Bulletin 737–53A1210, Revision 3,dated July 16, 2009) and resulted in reevaluation of the inspection thresholds and repetitive intervals. The new data and analysis require the repetitive intervals be reduced from those currently specified in Boeing Alert Service Bulletin 737–53A1210, Revision 3, dated July 16, 2009. These new repetitive intervals are defined in the differences section of the NPRM. Explanation of Relevant Service Information

We have reviewed Boeing Alert Service Bulletin 737–53A1210, Revision 2, dated March 3, 2009; and Boeing Alert Service Bulletin 737–53A1210, Revision 3, dated July 16, 2009. Boeing Alert Service Bulletin 737–53A1210, Revision 1, dated October 25, 2001, was referred to as the appropriate source of service information for accomplishing the actions in the existing AD.

Boeing Alert Service Bulletin 737– 53A1210, Revision 2, describes procedures for, among other things,