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 AD 

2011–27–51, 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 


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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: 

ESTIMATED 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 


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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-weight 

stop 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, 


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

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 to 

the 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. 


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