Federal Register / Vol. 78, No. 11 / Wednesday, January 16, 2013 / Proposed Rules 3365 

(2) Model 767–200, –300, –300F, and 

–400ER series airplanes, as identified in 

Boeing Alert Service Bulletin 767–78A0100, 

dated October 26, 2010. 

(d) Subject 

Joint Aircraft System Component (JASC)/ 

Air Transport Association (ATA) of America 

Code 7830, Thrust reverser. 

(e) Unsafe Condition 

This AD was prompted by reports of failure 

of the electro-mechanical brake flex shaft 

(short flexshaft) of the thrust reverser 

actuation system (TRAS). We are issuing this 

AD to prevent an uncommanded in-flight 

thrust reverser deployment and consequent 

loss of control of the airplane. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Flexible Drive Shaft Replacement 

Within 60 months after the effective date 

of this AD, replace the short flexshaft on each 

thrust reverser half of each engine with a new 

short flexshaft, in accordance with the 

Accomplishment Instructions of Boeing Alert 

Service Bulletin 747–78A2185, dated October 

26, 2010; or Boeing Alert Service Bulletin 

767–78A0100, dated October 26, 2010; as 

applicable. 

(h) Functional Test 

Within 2,000 flight hours after 

accomplishment of the short flexshaft 

replacements required by paragraph (g) of 

this AD: Do a functional test on the electromechanical brakes and the cone brake of the 

center drive unit (CDU) to verify the holding 

torque, on all thrust reversers and on all 

engines, in accordance with the 

Accomplishment Instructions of Boeing 

Service Bulletin 747–78A2166, Revision 3, 

dated July 29, 2004 (for Model 747 airplanes); 

Boeing Alert Service Bulletin 767–78A0081, 

Revision 2, dated April 19, 2001 (for Model 

767–200, –300, and –300F airplanes); or 

Boeing Alert Service Bulletin 767–78A0088, 

dated April 19, 2001 (for Model 767–400ER 

airplanes). Repeat the functional test 

thereafter at intervals not to exceed 2,000 

flight hours. 

(i) Corrective Action 

If any functional test required by paragraph 

(h) of this AD fails: Before further flight, do 

related investigative and corrective actions, 

in accordance with the Accomplishment 

Instructions of Boeing Service Bulletin 747– 

78A2166, Revision 3, dated July 29, 2004 (for 

Model 747 airplanes); Boeing Alert Service 

Bulletin 767–78A0081, Revision 2, dated 

April 19, 2001 (for Model 767–200, –300, and 

–300F airplanes); or Boeing Alert Service 

Bulletin 767–78A0088, dated April 19, 2001 

(for Model 767–400ER airplanes); and repeat 

the applicable test or check until successfully 

accomplished. 

(j) Terminating Actions 

(1) Accomplishment of the initial test 

specified in paragraph (h) of this AD 

terminates the requirements of paragraph (e) 

of AD 2003–16–16, Amendment 39–13269 

(68 FR 51439, August 27, 2003). 

(2) Accomplishment of the initial test 

specified in paragraph (h) of this AD 

terminates the requirements of paragraph (g) 

of AD 2000–15–04, Amendment 39–11833 

(65 FR 47252, August 2, 2000). 

(3) Accomplishment of the initial test 

specified in paragraph (h) of this AD 

terminates the requirements of paragraph (f) 

of AD 2000–09–04, Amendment 39–11712 

(65 FR 25833, May 4, 2000). 

(k) Parts Installation Prohibition 

As of the effective date of this AD, no 

person may install a flexshaft having part 

number 3278500–( ) on any airplane. 

(l) Alternative Methods of Compliance 

(AMOCs) 

(1) The Manager, Seattle Aircraft 

Certification Office (ACO), FAA, has the 

authority to approve AMOCs for this AD, if 

requested using the procedures found in 14 

CFR 39.19. In accordance with 14 CFR 39.19, 

send your request to your principal inspector 

or local Flight Standards District Office, as 

appropriate. If sending information directly 

to the manager of the ACO, send it to the 

attention of the person identified in the 

Related Information section of this AD. 

Information may be emailed to: 9-ANMSeattle-ACO-AMOC-Requests@faa.gov. 

(2) Before using any approved AMOC, 

notify your appropriate principal inspector, 

or lacking a principal inspector, the manager 

of the local flight standards district office/ 

certificate holding district office. 

(3) An AMOC that provides an acceptable 

level of safety may be used for any repair 

required by this AD if it is approved by the 

Boeing Commercial Airplanes Organization 

Designation Authorization (ODA) that has 

been authorized by the Manager, Seattle 

ACO, to make those findings. For a repair 

method to be approved, the repair must meet 

the certification basis of the airplane, and the 

approval must specifically refer to this AD. 

(m) Related Information 

(1) For more information about this AD, 

contact Tung Tran, Aerospace Engineer, 

Propulsion Branch, ANM–140S, Seattle 

Aircraft Certification Office (ACO), FAA, 

1601 Lind Avenue SW., Renton, WA 98057– 

3356; phone: 425–917–6505; fax: 425–917– 

6590; email: Tung.Tran@faa.gov. 

(2) For service information identified in 

this AD, contact Boeing Commercial 

Airplanes, Attention: Data & Services 

Management, P.O. Box 3707, MC 2H–65, 

Seattle, 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 425–227–1221. 

Issued in Renton, Washington, on January 

10, 2013. 

Kalene C. Yanamura, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2013–00803 Filed 1–15–13; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2012–1317; Directorate 

Identifier 2011–NM–194–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 Airplanes Model 

737–100, –200, –200C, –300, –400, 

–500, –600, –700, –700C, –800, and 

–900 series airplanes. This proposed AD 

was prompted by a report that the seat 

track attachment of body station 520 

flexible joint is structurally deficient in 

resisting a 9g forward emergency load 

condition in certain seating 

configurations. This proposed AD 

would require replacing the pivot link 

assembly on certain seats, and 

modifying or replacing the seat track 

link assemblies on certain seats. Also, 

for certain airplanes, this proposed AD 

would require installing a new seat 

track link assembly. We are proposing 

this AD to prevent seat detachment in 

an emergency landing, which could 

cause injury to occupants of the 

passenger compartment and affect 

emergency egress. 

DATES: We must receive comments on 

this proposed AD by March 4, 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 


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3366 Federal Register / Vol. 78, No. 11 / Wednesday, January 16, 2013 / Proposed Rules 

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 425–227–1221. 

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 

(phone: 800–647–5527) is in the 

ADDRESSES section. Comments will be 

available in the AD docket shortly after 

receipt. 

FOR FURTHER INFORMATION CONTACT: 

Sarah Piccola, Aerospace Engineer, 

Cabin Safety and Environmental 

Systems Branch, ANM–150S, FAA, 

Seattle Aircraft Certification Office, 

1601 Lind Avenue SW., Renton, WA 

98057–3356; phone: 425–917–6483; fax: 

425–917–6590; email: 

sarah.piccola@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– 

2012–1317; Directorate Identifier 2011– 

NM–194–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 received a report that the seat 

track attachment of body station 520 

flexible joint is structurally deficient in 

resisting a 9g forward emergency load 

condition in certain seating 

configurations. This condition, if not 

corrected, could result in seat 

detachment in an emergency landing 

and cause injury to occupants of the 

passenger compartment and affect 

emergency egress. 

Relevant Service Information 

We reviewed Boeing Service Bulletin 

737–53–1244, Revision 5, dated July 27, 

2011, for Model 737–600, –700, –700C, 

–800, and –900 series airplanes. This 

service bulletin, among other things, 

describes procedures for installing new, 

improved pivot link assemblies. 

We have also reviewed Boeing Special 

Attention Service Bulletin 737–53– 

1260, dated May 7, 2007, for Model 

737–100, –200, –200C, –300, –400, and 

–500 series airplanes. This service 

bulletin describes procedures for 

modifying or replacing the seat track 

link assemblies. 

Concurrent Service Bulletin 

Boeing Special Attention Service 

Bulletin 737–53–1260, dated May 7, 

2007, specifies, for certain airplanes, 

prior or concurrent accomplishment of 

Boeing Service Bulletin 737–53–1120, 

Revision 1, dated May 13, 1993, for 

modifying or installing new seat track 

link assemblies. 

FAA’s Determination 

We are proposing this AD because we 

evaluated all the relevant information 

and determined the unsafe condition 

described previously is likely to exist or 

develop in other products of the same 

type design. 

Proposed AD Requirements 

This proposed AD would require 

accomplishing the actions specified in 

the service information described 

previously. 

Costs of Compliance 

We estimate that this proposed AD 

affects 1,281 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 U.S. 

airplanes 

Cost on U.S. 

operators 

Replacement or modification.Up to 41 work-hours × 

$85 per hour = 

$3,485.

Up to $15,478 ............... Up to $18,963 ............... 1,281 Up to $24,291,603. 

Concurrent installation 

or modification 

(Groups 1, 2, 4, and 5 

airplanes).

Up to 60 work-hours × 

$85 per hour = 

$5,100.

Up to $18,089 ............... Up to $23,189 ............... 214 Up to $4,962,446. 

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), 


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(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 airworthiness 

directive (AD): 

The Boeing Company: Docket No. FAA– 

2012–1317; Directorate Identifier 2011– 

NM–194–AD. 

(a) Comments Due Date 

We must receive comments by March 4, 

2013. 

(b) Affected ADs 

None. 

(c) Applicability 

This AD applies to the airplanes identified 

in paragraphs (c)(1) and (c)(2) of this AD 

certificated in any category. 

(1) The Boeing Company Model 737–100, 

–200, –200C, –300, –400, and –500 series 

airplanes, as identified in Boeing Special 

Attention Service Bulletin 737–53–1260, 

dated May 7, 2007. 

(2) The Boeing Company Model 737–600, 

–700, –700C, –800, and –900 series airplanes, 

as identified in Boeing Service Bulletin 737– 

53–1244, Revision 5, dated July 27, 2011. 

(d) Subject 

Joint Aircraft System Component (JASC)/ 

Air Transport Association (ATA) of America 

Code 53, Fuselage. 

(e) Unsafe Condition 

This AD was prompted by a report that a 

Boeing study found that the seat track 

attachment of body station 520 flexible joint 

is structurally deficient in resisting a 9 g 

forward emergency load condition in certain 

seating configurations. We are issuing this 

AD to prevent seat detachment in an 

emergency landing, which could cause injury 

to occupants of the passenger compartment 

and affect emergency egress. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Repair or Replacement of Seat Track 

Link Assembly 

Within 60 months after the effective date 

of this AD, do the actions specified in 

paragraph (g)(1) or (g)(2) of this AD, as 

applicable. 

(1) For Model 737–600, –700, –700C, –800, 

and –900 series airplanes: Install new, 

improved pivot link assemblies, in 

accordance with the Accomplishment 

Instructions of Boeing Service Bulletin 737– 

53–1244, Revision 5, dated July 27, 2011. 

(2) For Model 737–100, –200, –200C, –300, 

–400, and –500 series airplanes: Modify or 

replace, as applicable, the seat track link 

assembly, in accordance with the 

Accomplishment Instructions of Boeing 

Special Attention Service Bulletin 737–53– 

1260, dated May 7, 2007. 

(h) Concurrent Actions 

For airplanes in Groups 1, 2, 4, and 5, as 

identified in Boeing Special Attention 

Service Bulletin 737–53–1260, dated May 7, 

2007: Before or concurrently with the 

accomplishment of the actions specified in 

paragraph (g)(2) of this AD, install a new seat 

track link assembly or modify the seat track 

link assembly, as applicable, in accordance 

with the Accomplishment Instructions of 

Boeing Service Bulletin 737–53–1120, 

Revision 1, dated May 13, 1993. 

(i) Alternative Methods of Compliance 

(AMOCs) 

(1) The Manager, Seattle Aircraft 

Certification Office (ACO), FAA, has the 

authority to approve AMOCs for this AD, if 

requested using the procedures found in 14 

CFR 39.19. In accordance with 14 CFR 39.19, 

send your request to your principal inspector 

or local Flight Standards District Office, as 

appropriate. If sending information directly 

to the manager of the ACO, send it to the 

attention of the person identified in the 

Related Information section of this AD. 

Information may be emailed to: 9-ANMSeattle-ACO-AMOC-Requests@faa.gov. 

(2) Before using any approved AMOC, 

notify your appropriate principal inspector, 

or lacking a principal inspector, the manager 

of the local flight standards district office/ 

certificate holding district office. 

(3) An AMOC that provides an acceptable 

level of safety may be used for any repair 

required by this AD if it is approved by The 

Boeing Commercial Airplanes Organization 

Designation Authorization (ODA) that has 

been authorized by the Manager, Seattle 

ACO, to make those findings. For a repair 

method to be approved, the repair must meet 

the certification basis of the airplane and 14 

CFR 25.571, Amendment 45, and the 

approval must specifically refer to this AD. 

(j) Related Information 

(1) For more information about this AD, 

contact Sarah Piccola, Aerospace Engineer, 

Cabin Safety and Environmental Systems 

Branch, ANM–150S, FAA, Seattle Aircraft 

Certification Office, 1601 Lind Avenue SW., 

Renton, WA 98057–3356; phone: 425–917– 

6483; fax: 425–917–6590; email: 

sarah.piccola@faa.gov. 

(2) For service information identified in 

this AD, contact Boeing Commercial 

Airplanes, Attention: Data & Services 

Management, P.O. Box 3707, MC 2H–65, 

Seattle, 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 425–227–1221. 

Issued in Renton, Washington, on January 

10, 2013. 

Kalene C. Yanamura, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2013–00801 Filed 1–15–13; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF COMMERCE 

International Trade Administration 

19 CFR Part 351 

[Docket No. 121231747–2747–01] 

RIN 0625–AA94 

Modification of Regulation Regarding 

the Extension of Time Limits 

AGENCY: Import Administration, 

International Trade Administration, 

Department of Commerce. 

ACTION: Proposed rule; request for 

comments. 

SUMMARY: The Department of Commerce 

(the Department) proposes to modify its 

regulation concerning the extension of 

time limits for submissions in 

antidumping (AD) and countervailing 

duty (CVD) proceedings. The 

modification, if adopted, will clarify 

that parties may request an extension of 

time limits before any time limit 

established under this part expires. This 

modification will also clarify under 

which circumstances the Department 

will grant untimely- filed requests for 

the extension of time limits. 

DATES: To be assured of consideration, 

comments must be received no later 

than March 18, 2013. 

ADDRESSES: All comments must be 

submitted through the Federal 

eRulemaking Portal at http:// 

www.regulations.gov, Docket No. ITA– 

2012–0006, unless the commenter does 

not have access to the Internet. 

Commenters who do not have access to 

the Internet may submit the original and 

two copies of each set of comments by 

mail or hand delivery/courier. All 


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