Federal Register / Vol. 79, No. 33 / Wednesday, February 19, 2014 / Rules and Regulations 9389 

inspection for damaged (worn, torn, or 

abraded) and missing shims and seals, 

between the nacelle lower fairing and the 

underwing box of both the left-hand and 

right-hand engine nacelles, in accordance 

with the Accomplishment Instructions of 

Avions de Transport Re ́gional Service 

Bulletin ATR42–54–0029; or ATR72–54– 

1023; both dated July 18, 2012; as applicable. 

If any seal or shim is damaged or missing, 

before further flight, replace, as applicable, in 

accordance with the Accomplishment 

Instructions of Avions de Transport Re ́gional 

Service Bulletin ATR42–54–0029; or ATR72– 

54–1023; both dated July 18, 2012; as 

applicable. 

(h) Reporting 

At the applicable time specified in 

paragraph (h)(1) or (h)(2) of this AD: Submit 

a report using the applicable 

Accomplishment Report of Avions de 

Transport Re ́gional Service Bulletin ATR42– 

54–0029; or ATR72–54–1023; both dated July 

18, 2012; to ATR Engineering, Service 

Bulletin Group, 1 Allee Pierre Nadot, 31712 

Blagnac Cedex, France; phone: +33 (0) 5 62 

21 62 21; fax: +33 (0) 5 62 21 69 41; email: 

techdesk@atr.fr. 

(1) If the inspection was done on or after 

the effective date of this AD: Submit the 

report within 30 days after the inspection. 

(2) If the inspection was done before the 

effective date of this AD: Submit the report 

within 30 days after the effective date of this 

AD. 

(i) Other FAA AD Provisions 

The following provisions also apply to this 

AD: 

(1) Alternative Methods of Compliance 

(AMOCs): The Manager, International 

Branch, ANM–116, Transport Airplane 

Directorate, 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 International Branch, send it to ATTN: 

Tom Rodriguez, Aerospace Engineer, 

International Branch, ANM–116, Transport 

Airplane Directorate, FAA, 1601 Lind 

Avenue SW., Renton, WA 98057–3356; 

telephone 425–227–1137; fax 425–227–1149. 

Information may be emailed to: 9-ANM-116- 

AMOC-REQUESTS@faa.gov. 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. 

(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. 

(3) Reporting Requirements: A federal 

agency may not conduct or sponsor, and a 

person is not required to respond to, nor 

shall a person be subject to a penalty for 

failure to comply with a collection of 

information subject to the requirements of 

the Paperwork Reduction Act unless that 

collection of information displays a current 

valid OMB Control Number. The OMB 

Control Number for this information 

collection is 2120–0056. Public reporting for 

this collection of information is estimated to 

be approximately 5 minutes per response, 

including the time for reviewing instructions, 

completing and reviewing the collection of 

information. All responses to this collection 

of information are mandatory. Comments 

concerning the accuracy of this burden and 

suggestions for reducing the burden should 

be directed to the FAA at: 800 Independence 

Ave. SW., Washington, DC 20591, Attn: 

Information Collection Clearance Officer, 

AES–200. 

(j) Related Information 

Refer to Mandatory Continuing 

Airworthiness Information (MCAI) European 

Aviation Safety Agency (EASA) 

Airworthiness Directive 2012–0160, dated 

August 24, 2012, for related information. 

This MCAI may be found in the AD docket 

on the Internet at http://

www.regulations.gov/

#!documentDetail;D=FAA-2013-0799-0002. 

(k) Material Incorporated by Reference 

(1) The Director of the Federal Register 

approved the incorporation by reference 

(IBR) of the service information listed in this 

paragraph under 5 U.S.C. 552(a) and 1 CFR 

part 51. 

(2) You must use this service information 

as applicable to do the actions required by 

this AD, unless this AD specifies otherwise. 

(i) ATR Service Bulletin ATR42–54–0029, 

dated July 18, 2012. 

(ii) ATR Service Bulletin ATR72–54–1023, 

dated July 18, 2012. 

(3) For service information identified in 

this AD, contact ATR—GIE Avions de 

Transport Re ́gional, 1, Alle ́e Pierre Nadot, 

31712 Blagnac Cedex, France; telephone +33 

(0) 5 62 21 62 21; fax +33 (0) 5 62 21 67 18; 

email continued.airworthiness@atr.fr; 

Internet http://www.aerochain.com. 

(4) You may view this 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. 

(5) You may view this service information 

that is incorporated by reference at the 

National Archives and Records 

Administration (NARA). For information on 

the availability of this material at NARA, call 

202–741–6030, or go to: http://

www.archives.gov/federal-register/cfr/ibrlocations.html. 

Issued in Renton, Washington, on January 

21, 2014. 

Jeffrey E. Duven, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 2014–02774 Filed 2–18–14; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2014–0054; Directorate 

Identifier 2014–NM–001–AD; Amendment 

39–17754; AD 2014–03–17] 

RIN 2120–AA64 

Airworthiness Directives; Bombardier, 

Inc. Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Final rule; request for 

comments. 

SUMMARY: We are adopting a new 

airworthiness directive (AD) for certain 

Bombardier, Inc. Model CL–600–1A11 

(CL–600), CL–600–2A12 (CL–601), and 

CL–600–2B16 (CL–601–3A, CL–601–3R, 

and CL–604 Variants) airplanes. This 

AD requires repetitive inspections for 

fractured or incorrectly oriented 

fasteners on the inboard flap hinge-box 

forward fittings on both wings, and 

fastener replacement if necessary. This 

AD was prompted by two reports of 

fractured fastener heads found on the 

inboard flap hinge-box forward fitting. 

We are issuing this AD to detect and 

correct incorrectly oriented or fractured 

fasteners, which could result in 

detachment of the flap hinge-box and 

the flap surface, and consequent 

reduced controllability of the airplane. 

DATES: This AD becomes effective 

March 6, 2014. 

The Director of the Federal Register 

approved the incorporation by reference 

of certain publications listed in this AD 

as of March 6, 2014 

We must receive comments on this 

AD by April 7, 2014. 

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, between 9 a.m. and 5 

p.m., Monday through Friday, except 

Federal holidays. 

For service information identified in 

this AD, contact Bombardier, Inc., 400 

Coˆte-Vertu Road West, Dorval, Que ́bec 


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H4S 1Y9, Canada; telephone 514–855– 

5000; fax 514–855–7401; email thd.crj@

aero.bombardier.com; Internet http://

www.bombardier.com. You may view 

this 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 by searching for 

and locating it in Docket No. FAA– 

2014–0054; or in person at the Docket 

Operations office between 9 a.m. and 5 

p.m., Monday through Friday, except 

Federal holidays. The AD docket 

contains this AD, the regulatory 

evaluation, any comments received, and 

other information. The street address for 

the Docket Operations 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: 

Ricardo Garcia, Aerospace Engineer, 

Airframe and Mechanical Systems 

Branch, ANE–171, FAA, New York 

Aircraft Certification Office, 1600 

Stewart Avenue, Suite 410, Westbury, 

NY 11590; telephone (516) 228–7331; 

fax (516) 794–5531. 

SUPPLEMENTARY INFORMATION: 

Discussion 

Transport Canada Civil Aviation 

(TCCA), which is the aviation authority 

for Canada, has issued Canadian 

Airworthiness Directive CF–2013–39, 

dated December 6, 2013 (referred to 

after this as the Mandatory Continuing 

Airworthiness Information, or the ‘‘the 

MCAI’’), to correct an unsafe condition 

for the specified products. The MCAI 

states: 

There have been two in-service reports of 

a fractured fastener head, on the inboard flap 

hinge-box forward fitting at Wing Station 

(WS) 76.50, found during a routine 

maintenance inspection. Investigation 

revealed that the installation of these 

fasteners on the inboard flap hinge-box 

forward fittings at WS 76.50 and WS 127.25, 

on both wings, does not conform to the 

engineering drawings. Incorrect installation 

may result in premature failure of the 

fasteners attaching the inboard flap hinge-box 

forward fitting. Failure of the fasteners could 

lead to the detachment of the flap hinge box 

and consequently the detachment of the flap 

surface. The loss of a flap surface could 

adversely affect the continued safe operation 

of the aeroplane [consequent reduced 

controllability of the airplane]. 

This [Canadian] AD mandates a detailed 

visual inspection (DVI) of each inboard flap 

hinge-box forward fitting [for incorrectly 

oriented or fractured fasteners], on both 

wings, and rectification [fastener 

replacement] as required. Incorrectly 

oriented fasteners require repetitive 

inspections until the terminating action 

[fastener replacement] is accomplished. 

You may examine the MCAI on the 

Internet at http://www.regulations.gov 

by searching for and locating it in 

Docket No. FAA–2014–0054. 

Relevant Service Information 

Bombardier has issued Alert Service 

Bulletins: 

• A600–0763, including Appendices 

1 and 2, dated September 26, 2013 (for 

Model CL–600–1A11 (CL–600) 

airplanes); 

• A601–0627, including Appendices 

1 and 2, dated September 26, 2013 (for 

Model CL–600–2A12 (CL–601) and CL– 

600–2B16 (CL–601–3A and CL–601–3R 

Variants) airplanes; 

• A604–57–006, Revision 01, dated 

September 26, 2013, including 

Appendices 1 and 2, dated September 

26, 2013 (for Model CL–600–2B16 (CL– 

604 Variant) airplanes with serial 

numbers 5301 through 5665 inclusive); 

and 

• A605–57–004, Revision 01, dated 

September 26, 2013, including 

Appendices 1 and 2, dated September 

26, 2013 (for Model CL–600–2B16 (CL– 

604 Variant) airplanes with serial 

numbers 5701 through 5920 inclusive). 

The actions described in this service 

information are intended to correct the 

unsafe condition identified in the 

MCAI. 

FAA’s Determination and Requirements 

of This AD 

This product has been approved by 

the aviation authority of another 

country, and is approved for operation 

in the United States. Pursuant to our 

bilateral agreement with the State of 

Design Authority, we have been notified 

of the unsafe condition described in the 

MCAI and service information 

referenced above. We are issuing this 

AD because we evaluated all pertinent 

information and determined the unsafe 

condition exists and is likely to exist or 

develop on other products of the same 

type design. 

FAA’s Determination of the Effective 

Date 

An unsafe condition exists that 

requires the immediate adoption of this 

AD. The FAA has found that the risk to 

the flying public justifies waiving notice 

and comment prior to adoption of this 

rule because incorrectly installed or 

fractured fasteners could result in 

detachment of the flap hinge-box and 

the flap surface, and consequently, 

reduced controllability of the airplane. 

Therefore, we determined that notice 

and opportunity for public comment 

before issuing this AD are impracticable 

and that good cause exists for making 

this amendment effective in fewer than 

30 days. 

Interim Action 

We consider this AD interim action. 

We are currently considering requiring 

replacement of incorrectly oriented 

fasteners, which will constitute 

terminating action for the repetitive 

inspections required by this AD action. 

However, the planned compliance time 

for the replacement would allow enough 

time to provide notice and opportunity 

for prior public comment on the merits 

of the modification. 

Comments Invited 

This AD is a final rule that involves 

requirements affecting flight safety, and 

we did not precede it by notice and 

opportunity for public comment. We 

invite you to send any written relevant 

data, views, or arguments about this AD. 

Send your comments to an address 

listed under the ADDRESSES section. 

Include ‘‘Docket No. FAA–2014–0054; 

Directorate Identifier 2014–NM–001– 

AD’’ at the beginning of your comments. 

We specifically invite comments on the 

overall regulatory, economic, 

environmental, and energy aspects of 

this AD. We will consider all comments 

received by the closing date and may 

amend this AD based on 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 AD. 

Costs of Compliance 

We estimate that this AD affects 105 

airplanes of U.S. registry. 

We also estimate that it will take 

about 1 work-hour per product to 

comply with the basic requirements of 

this AD. The average labor rate is $85 

per work-hour. Based on these figures, 

we estimate the cost of this AD on U.S. 

operators to be $8,925, or $85 per 

product. 

In addition, we estimate that any 

necessary follow-on actions will take 

about 58 work-hours per product. We 

have no way of determining the number 

of aircraft that might need these actions. 

According to the manufacturer, some 

of the costs of this AD may be covered 

under warranty, thereby reducing the 

cost impact on affected individuals. We 

do not control warranty coverage for 


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Federal Register / Vol. 79, No. 33 / Wednesday, February 19, 2014 / Rules and Regulations 9391 

affected individuals. Therefore, the 

parts costs are not included in our cost 

estimate. 

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 AD will not 

have federalism implications under 

Executive Order 13132. This AD will 

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 this AD: 

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. 

Adoption of the Amendment 

Accordingly, under the authority 

delegated to me by the Administrator, 

the FAA amends 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): 

2014–03–17 Bombardier, Inc.: Amendment 

39–17754. Docket No. FAA–2014–0054; 

Directorate Identifier 2014–NM–001–AD. 

(a) Effective Date 

This AD becomes effective March 6, 2014. 

(b) Affected ADs 

None. 

(c) Applicability 

This AD applies to the Bombardier, Inc. 

airplanes identified in paragraphs (c)(1) 

through (c)(3) of this AD, certificated in any 

category. 

(1) Bombardier, Inc. Model CL–600–1A11 

(CL–600) airplanes, having serial numbers (S/ 

Ns) 1004 through 1085 inclusive. 

(2) Bombardier, Inc. Model CL–600–2A12 

(CL–601) airplanes, having S/Ns 3001 

through 3066 inclusive. 

(3) Bombardier, Inc. Model CL–600–2B16 

(CL–601–3A, CL–601–3R, & CL–604 Variants) 

airplanes, having S/Ns 5001 through 5194 

inclusive, 5301 through 5665 inclusive, and 

5701 through 5920 inclusive. 

(d) Subject 

Air Transport Association (ATA) of 

America Code 57, Wings. 

(e) Reason 

This AD was prompted by two reports of 

fractured fastener heads found on the inboard 

flap hinge-box forward fitting at wing station 

(WS) 76.50. We are issuing this AD to detect 

and correct incorrectly oriented or fractured 

fasteners, which could result in detachment 

of the flap hinge-box and the flap surface, 

and consequent reduced controllability of the 

airplane. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Inspection 

Within 100 flight cycles after the effective 

date of this AD: Do a detailed visual 

inspection for incorrect orientation and any 

fracturing (missing fastener heads) of each 

inboard flap fastener of the hinge-box 

forward fitting at WS 76.50 and WS 127.25, 

on both wings, in accordance with the 

Accomplishment Instructions of the 

applicable service information identified in 

paragraphs (g)(1) through (g)(4) of this AD. 

(1) For Model CL–600–1A11 (CL–600) 

airplanes having S/Ns 1004 through 1085 

inclusive: Bombardier Alert Service Bulletin 

A600–0763, including Appendices 1 and 2, 

dated September 26, 2013. 

(2) For Model CL–600–2A12 (CL–601) 

airplanes having S/Ns 3001 through 3066 

inclusive, and Model CL–600–2B16 (CL– 

601–3A and CL–601–3R Variants) airplanes 

having S/Ns 5001 through 5194 inclusive: 

Bombardier Alert Service Bulletin A601– 

0627, including Appendices 1 and 2, dated 

September 26, 2013. 

(3) For Model CL–600–2B16 (CL–604 

Variant) airplanes having S/Ns 5301 through 

5665 inclusive: Bombardier Alert Service 

Bulletin A604–57–006, Revision 01, dated 

September 26, 2013, including Appendices 1 

and 2, dated September 26, 2013. 

(4) For Model CL–600–2B16 (CL–604 

Variant) airplanes having S/Ns 5701 through 

5920 inclusive: Bombardier Alert Service 

Bulletin A605–57–004, Revision 01, dated 

September 26, 2013, including Appendices 1 

and 2, dated September 26, 2013. 

(h) All Fasteners Correctly Oriented and Not 

Fractured 

If all fasteners are found correctly oriented 

and not fractured (intact) during any 

inspection required by paragraph (g) of this 

AD, no further action is required by this AD. 

(i) Fractured Fasteners 

If any fastener is found fractured (missing 

fastener head) during any inspection required 

by paragraph (g) of this AD: Before further 

flight, remove and replace all fractured 

fasteners and all incorrectly oriented forward 

and aft fasteners at WS 76.50 and WS 127.25, 

on both wings, in accordance with the 

Accomplishment Instructions of the 

applicable service information identified in 

paragraphs (g)(1) through (g)(4) of this AD. 

After accomplishing the replacement 

required by this paragraph, no further action 

is required by this AD. 

(j) Incorrectly Oriented Fasteners 

If any fastener is found incorrectly oriented 

but none are found to be fractured (fasteners 

found intact) during any inspection required 

by paragraph (g) of this AD: Repeat the 

inspection required by paragraph (g) of this 

AD thereafter at intervals not to exceed 100 

flight cycles until the terminating action 

specified in paragraph (k) of this AD is 

accomplished. 

(k) Optional Terminating Action for 

Incorrectly Oriented Fasteners 

Replacement of all incorrectly oriented 

forward and aft fasteners at WS 76.50 and 

WS 127.25, on both wings, in accordance 

with the Accomplishment Instructions of the 

applicable service information identified in 

paragraphs (g)(1) through (g)(4) of this AD, 

terminates the requirements of paragraph (j) 

of this AD. 

(l) Other FAA AD Provisions 

The following provisions also apply to this 

AD: 

(1) Alternative Methods of Compliance 

(AMOCs): The Manager, New York Aircraft 

Certification Office, ANE–170, 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 ACO, send it to ATTN: Program 

Manager, Continuing Operational Safety, 

FAA, New York ACO, 1600 Stewart Avenue, 

Suite 410, Westbury, NY 11590; telephone 

516–228–7300; fax 516–794–5531. Before 

using any approved AMOC, notify your 

appropriate principal inspector, or lacking a 

principal inspector, the manager of the local 


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flight standards district office/certificate 

holding district office. The AMOC approval 

letter must specifically reference this AD. 

(2) Airworthy Product: For any requirement 

in this AD to obtain corrective actions from 

a manufacturer, use these actions if they are 

FAA-approved. Corrective actions are 

considered FAA-approved if they were 

approved by the State of Design Authority (or 

its delegated agent, or the DAH with a State 

of Design Authority’s design organization 

approval). For a repair method to be 

approved, the repair approval must 

specifically refer to this AD. You are required 

to ensure the product is airworthy before it 

is returned to service. 

(m) Related Information 

Refer to Mandatory Continuing 

Airworthiness Information (MCAI) Canadian 

Airworthiness Directive CF–2013–39, dated 

December 6, 2013, for related information. 

You may examine the MCAI on the Internet 

at http://www.regulations.gov by searching 

for and locating it in Docket No. FAA–2014– 

0054. 

(n) Material Incorporated by Reference 

(1) The Director of the Federal Register 

approved the incorporation by reference 

(IBR) of the service information listed in this 

paragraph under 5 U.S.C. 552(a) and 1 CFR 

Part 51. 

(2) You must use this service information 

as applicable to do the actions required by 

this AD, unless this AD specifies otherwise. 

(i) Bombardier Alert Service Bulletin 

A600–0763, including Appendices 1 and 2, 

dated September 26, 2013. 

(ii) Bombardier Alert Service Bulletin 

A601–0627, including Appendices 1 and 2, 

dated September 26, 2013. 

(iii) Bombardier Alert Service Bulletin 

A604–57–006, Revision 01, dated September 

26, 2013, including Appendices 1 and 2, 

dated September 26, 2013. 

(iv) Bombardier Alert Service Bulletin 

A605–57–004, Revision 01, dated September 

26, 2013, including Appendices 1 and 2, 

dated September 26, 2013. 

(3) For service information identified in 

this AD, contact Bombardier, Inc., 400 CoˆteVertu Road West, Dorval, Que ́bec H4S 1Y9, 

Canada; telephone 514–855–5000; fax 514– 

855–7401; email thd.crj@

aero.bombardier.com; Internet http://

www.bombardier.com. 

(4) You may view this 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. 

(5) You may view this service information 

that is incorporated by reference at the 

National Archives and Records 

Administration (NARA). For information on 

the availability of this material at NARA, call 

202–741–6030, or go to: http://

www.archives.gov/federal-register/cfr/ibrlocations.html. 

Issued in Renton, Washington, on February 

3, 2014. 

Jeffrey E. Duven, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 2014–02977 Filed 2–18–14; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2013–0210; Directorate 

Identifier 2012–NM–053–AD; Amendment 

39–17744; AD 2014–03–07] 

RIN 2120–AA64 

Airworthiness Directives; The Boeing 

Company Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule. 

SUMMARY: We are superseding 

Airworthiness Directive (AD) 2009–26– 

16 for certain The Boeing Company 

Model MD–11 and MD–11F airplanes. 

AD 2009–26–16 required inspecting to 

determine if wires touch the upper 

surface of the center upper auxiliary 

fuel tank, and marking the location, as 

necessary; inspecting all wire bundles 

above the center upper auxiliary fuel 

tank for splices and damage; inspecting 

for damage to the fuel vapor barrier seal 

and upper surface of the center upper 

auxiliary fuel tank; and performing 

corrective actions, as necessary. AD 

2009–26–16 also required installing 

nonmetallic barrier/shield sleeving, new 

clamps, new attaching hardware, and a 

new extruded channel. This new AD 

requires inspections of additional center 

upper auxiliary fuel tank locations and 

corrective actions as necessary. This AD 

was prompted by reports that identified 

additional locations where inspections 

and corrective actions of the center 

upper auxiliary fuel tank are needed. 

We are issuing this AD to reduce the 

potential of ignition sources inside fuel 

tanks, which, in combination with 

flammable fuel vapors, could result in 

fuel tank explosions and consequent 

loss of the airplane. 

DATES: This AD is effective March 26, 

2014. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication listed in this AD 

as of March 26, 2014. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain other publication listed in 

this AD as of February 4, 2010 (74 FR 

69249, December 31, 2009). 

ADDRESSES: For service information 

identified in this AD, contact Boeing 

Commercial Airplanes, Attention: Data 

& Services Management, 3855 

Lakewood Boulevard, MC D800–0019, 

Long Beach, CA 90846–0001; telephone 

206–544–5000, extension 2; fax 206– 

766–5683; Internet https://

www.myboeingfleet.com. You may view 

this 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 by searching for 

and locating Docket No. FAA–2013– 

0210; 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 AD, the regulatory 

evaluation, any comments received, and 

other information. The address for the 

Docket Office (phone: 800–647–5527) is 

Docket Management Facility, U.S. 

Department of Transportation, Docket 

Operations, M–30, West Building 

Ground Floor, Room W12–140, 1200 

New Jersey Avenue SE., Washington, 

DC 20590. 

FOR FURTHER INFORMATION CONTACT: 

Samuel Lee, Aerospace Engineer, 

Propulsion Branch, ANM–140L, FAA, 

Los Angeles Aircraft Certification 

Office, 3960 Paramount Boulevard, 

Lakewood, CA 90712–4137; phone: 

(562) 627–5262; fax: (562) 627–5210; 

email: samuel.lee@faa.gov. 

SUPPLEMENTARY INFORMATION: 

Discussion 

We issued a notice of proposed 

rulemaking (NPRM) to amend 14 CFR 

Part 39 to supersede AD 2009–26–16, 

Amendment 39–16155 (74 FR 69249, 

December 31, 2009). AD 2009–26–16 

applied to certain The Boeing Company 

Model MD–11 and MD–11F airplanes. 

The NPRM published in the Federal 

Register on March 14, 2013 (78 FR 

16198). The NPRM was prompted by 

reports that identified additional 

locations where inspections and 

corrective actions of the center upper 

auxiliary fuel tank are needed. The 

NPRM proposed to continue to require 

inspecting to determine if wires touch 

the upper surface of the center upper 

auxiliary fuel tank, and marking the 

location, as necessary; inspecting all 

wire bundles above the center upper 

auxiliary fuel tank for splices and 

damage; inspecting for damage to the 


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