Federal Register / Vol. 78, No. 11 / Wednesday, January 16, 2013 / Proposed Rules 3363 

Issued in Kansas City, Missouri, on January 

10, 2013. 

John Colomy, 

Acting Manager, Small Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 2013–00807 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–2012–1318; Directorate 

Identifier 2012–NM–104–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 747–200B, 

747–300, 747–400, 747–400D, 747–400F 

series airplanes, and Model 767 series 

airplanes, powered by General Electric 

(GE) CF6–80C2 engines. This proposed 

AD was prompted by reports of failure 

of the electro-mechanical brake flex 

shaft (short flexshaft) of the thrust 

reverser actuation system (TRAS). This 

proposed AD would require replacing 

the short flexshaft on each engine with 

a new short flexshaft, testing of the 

electro-mechanical brake and center 

drive unit (CDU) cone brake to verify 

the holding torque, and performing 

related investigative and corrective 

actions if necessary. We are proposing 

this AD to prevent an uncommanded inflight thrust reverser deployment and 

consequent loss of control of the 

airplane. 

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 

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: 

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. 

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– 

2012–1318; Directorate Identifier 2012– 

NM–104–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 multiple reports of 

failure of the short flexshaft of the TRAS 

on Model 747 and 767 airplanes 

powered with GE CF6–80C2 engines. 

The TRAS brake was installed as a third 

lock to prevent an uncommanded thrust 

reverser deployment on Model 747 and 

767 airplanes powered by GE CF6–80C2 

engines. The failed short flexshafts were 

found to have cores that had become 

sheared and unbraided. A new short 

flexshaft design has been developed that 

incorporates a better end fitting 

attachment and a larger core diameter 

with the core wound specifically for use 

on a left and right thrust reverser half to 

increase its resistance to failure. We are 

proposing this AD to prevent an 

uncommanded in-flight thrust reverser 

deployment and consequent loss of 

control of the airplane. 

Other Related Rulemaking 

On August 13, 2003, we issued AD 

2003–16–16, Amendment 39–13269 (68 

FR 51439, August 27, 2003), for Model 

747–400 series airplanes equipped with 

GE Model CF6–80C2 series engines. AD 

2003–16–16 requires repetitive tests of 

the cone brake of the CDU of the thrust 

reversers, and corrective actions if 

necessary; installation of a TRAS lock 

and various related modifications and 

installations. Following installation of 

the TRAS lock, this action also requires 

repetitive functional tests of the TRAS 

lock, and corrective action if necessary. 

On July 18, 2000, we issued AD 2000– 

15–04, Amendment 39–11833 (65 FR 

47252, August 2, 2000), for Model 747– 

200 and –300 series airplanes equipped 

with GE Model CF6–80C2 series engines 

with Power Management Control engine 

controls. AD 2000–15–04 requires 

various inspections and functional tests 

to detect discrepancies of the thrust 

reverser control and indication system, 

and correction of any discrepancy 

found; and installation of a terminating 

modification, and repetitive functional 

tests of that installation, and repair, if 

necessary. 

On April 26, 2000, we issued AD 

2000–09–04, Amendment 39–11712 (65 

FR 25833, May 4, 2000), for Model 767 

series airplanes equipped with GE 

Model CF6–80C2 series engines. AD 

2000–09–04 requires tests, inspections, 

and adjustments of the thrust reverser 

system; and installation of a terminating 

modification, and repetitive follow-on 

actions. 

Relevant Service Information 

We reviewed Boeing Alert Service 

Bulletin 747–78A2185, dated October 

26, 2010; and Boeing Alert Service 

Bulletin 767–78A0100, dated October 

26, 2010. This service information 

describes procedures for replacing the 

short flexshaft of each thrust reverser 


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3364 Federal Register / Vol. 78, No. 11 / Wednesday, January 16, 2013 / Proposed Rules 

half of each engine with a new short 

flexshaft. 

We reviewed 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); and Boeing Alert Service 

Bulletin 767–78A0088, dated April 19, 

2001 (for Model 767–400ER airplanes). 

This service information describes a 

functional test of the electro-mechanical 

brake and CDU cone brake to verify the 

holding torque, and related investigative 

and corrective actions if necessary. 

The related investigative action for 

the electro-mechanical brake is a general 

visual inspection of the short flexshaft 

for twisting, breaking, or other damage. 

The corrective action for the electromechanical brake is replacement of the 

long flexshaft between the CDU and the 

upper angle gearbox with a new 

flexshaft; replacement of the short 

flexshaft between the upper angle 

gearbox and the electro-mechanical 

brake with a new flexshaft; and 

replacement of the electromechanical 

brake with a new electromechanical 

brake if the required torque value 

cannot be reached after the previous 

flexshaft replacements. 

The corrective action for a CDU cone 

brake test failure is replacement of the 

CDU cone brake with a new CDU cone 

brake. 

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 these same 

type designs. 

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 298 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 

Replacement Model 747 airplanes (72 airplanes).8 work-hours × $85 per hour = $680 ............. $15,244 $15,924 $1,146,528 

Replacement Model 767 airplanes (226 airplanes).4 work-hours × $85 per hour = $340 ............. 7,622 7,962 1,799,412 

Functional test Model 747 airplanes (72 airplanes).12 work-hours × $85 per hour = $1,020 ........ 0 1,020 73,440 

Functional test Model 767 airplanes (226 airplanes).12 work-hours × $85 per hour = $1,020 ........ 0 1,020 230,520 

We have received no definitive data 

that would enable us to provide cost 

estimates for the on-condition actions 

specified in this proposed AD. 

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), 

(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– 

2012–1318; Directorate Identifier 2012– 

NM–104–AD. 

(a) Comments Due Date 

We must receive comments by March 4, 

2013. 

(b) Affected ADs 

This AD affects AD 2003–16–16, 

Amendment 39–13269 (68 FR 51439, August 

27, 2003); AD 2000–15–04, Amendment 39– 

11833 (65 FR 47252, August 2, 2000); and AD 

2000–09–04, Amendment 39–11712 (65 FR 

25833, May 4, 2000). 

(c) Applicability 

This AD applies to The Boeing Company 

airplanes, certificated in any category, 

powered by General Electric (GE) CF6–80C2 

engines, as identified in paragraphs (c)(1) and 

(c)(2) of this AD. 

(1) Model 747–200B, 747–300, 747–400, 

747–400D, and 747–400F series airplanes, as 

identified in Boeing Alert Service Bulletin 

747–78A2185, dated October 26, 2010. 


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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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