Federal Register / Vol. 78, No. 136 / Tuesday, July 16, 2013 / Rules and Regulations 42411 

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 

helicopters identified in this rulemaking 

action. 

Regulatory Findings 

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 

DOT Regulatory Policies and Procedures 

(44 FR 11034, February 26, 1979); 

(3) Will not affect intrastate aviation 

in Alaska to the extent that it justifies 

making a regulatory distinction; 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. We prepared an 

economic evaluation of the estimated 

costs to comply with this AD and placed 

it in the AD docket. 

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): 

2013–12–05 Eurocopter Deutschland GmbH 

Helicopters: Amendment 39–17483; 

Docket No. FAA–2013–0018; Directorate 

Identifier 2010–SW–060–AD. 

(a) Applicability 

This AD applies to Model MBB–BK 117 C– 

2 helicopters with a bevel gear, part number 

(P/N) 4639 310 065, installed in the tail rotor 

intermediate gear box (IGB), P/N 4639 002 

007, certificated in any category. 

(b) Unsafe Condition 

This AD defines the unsafe condition as 

failure of a bevel gear, failure of the tail rotor 

IGB, and subsequent loss of control of the 

helicopter. 

(c) Effective Date 

This AD becomes effective August 20, 

2013. 

(d) Compliance 

You are responsible for performing each 

action required by this AD within the 

specified compliance time unless it has 

already been accomplished prior to that time. 

(e) Required Actions 

Within 30 days, do the following: 

(1) Determine if a bevel gear with a serial 

number (S/N) listed in Table 1 of Eurocopter 

Alert Service Bulletin MBB BK117 C–2–04A– 

005, Revision 2, dated April 28, 2010 (ASB), 

is installed in the IGB. 

(i) If a bevel gear listed in Table 1 of the 

ASB is installed in the IGB, record the 

reduced life limit of the bevel gear onto the 

component history card or equivalent record 

of the IGB. 

(ii) If the bevel gear life limit has been 

reached or is exceeded, before further flight, 

replace the bevel gear with an airworthy 

bevel gear. 

(2) Revise the Airworthiness Limitations 

section of the maintenance manual by 

reducing the retirement life for each IGB 

bevel gear, P/N 4639 310 065, that has a S/ 

N listed in Table 1 of the ASB to the life limit 

corresponding to that S/N. 

(f) Alternative Methods of Compliance 

(AMOCs) 

(1) The Manager, Safety Management 

Group, FAA, may approve AMOCs for this 

AD. Send your proposal to: Chinh Vuong, 

Aviation Safety Engineer, Safety Management 

Group, Rotorcraft Directorate, FAA, 2601 

Meacham Blvd., Fort Worth, Texas 76137; 

telephone (817) 222–5110; email 

chinh.vuong@faa.gov. 

(2) For operations conducted under a 14 

CFR part 119 operating certificate or under 

14 CFR part 91, subpart K, we suggest that 

you notify your principal inspector, or 

lacking a principal inspector, the manager of 

the local flight standards district office or 

certificate holding district office, before 

operating any aircraft complying with this 

AD through an AMOC. 

(g) Additional Information 

The subject of this AD is addressed in 

European Aviation Safety Agency (EASA) AD 

No. 2010–0096, dated May 25, 2010. You 

may view the EASA AD at http:// 

www.regulations.gov by searching for and 

locating it in Docket No. FAA–2013–0018. 

(h) Subject 

Joint Aircraft Service Component (JASC) 

Code: 6520, Tail Rotor Gearbox. 

(i) 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 the AD specifies otherwise. 

(i) Eurocopter Alert Service Bulletin MBB 

BK117 C–2–04A–005, Revision 2, dated April 

28, 2010. 

(ii) Reserved. 

(3) For Eurocopter service information 

identified in this AD, contact American 

Eurocopter Corporation, 2701 N. Forum 

Drive, Grand Prairie, TX 75052; telephone 

(972) 641–0000 or (800) 232–0323; fax (972) 

641–3775; or at http://www.eurocopter.com/ 

techpub. 

(4) You may view this service information 

at FAA, Office of the Regional Counsel, 

Southwest Region, 2601 Meacham Blvd., 

Room 663, Fort Worth, Texas 76137. For 

information on the availability of this 

material at the FAA, call (817) 222–5110. 

(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 Fort Worth, Texas, on June 13, 

2013. 

Kim Smith, 

Directorate Manager, Rotorcraft Directorate, 

Aircraft Certification Service. 

[FR Doc. 2013–14848 Filed 7–15–13; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2012–0864; Directorate 

Identifier 2011–NM–023–AD; Amendment 

39–17496; AD 2013–13–08] 

RIN 2120–AA64 

Airworthiness Directives; The Boeing 

Company Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule. 

SUMMARY: We are superseding an 

existing airworthiness directive (AD) for 

certain The Boeing Company Model 767 

airplanes. That AD currently requires 

sealing certain fasteners and stiffeners 

in the fuel tank, changing certain wire 

bundle clamp configurations on the fuel 

tank walls, inspecting certain fasteners 

in the fuel tanks and determining the 

method of attachment of the vortex 

generators; and performing corrective 

actions if necessary. This new AD adds 

a general visual inspection for the 

presence of a polytetrafluoroethylene 

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42412 Federal Register / Vol. 78, No. 136 / Tuesday, July 16, 2013 / Rules and Regulations 

(TFE) sleeve at the clamp location on 

the rear spar, and installation of a TFE 

sleeve if necessary. This new AD also 

adds airplanes to the applicability. This 

AD was prompted by fuel system 

reviews conducted by the manufacturer, 

and the identification of another 

possible ignition source location. We are 

issuing this AD to prevent possible 

ignition sources in the auxiliary (center) 

fuel tank, main fuel tanks, and surge 

tanks caused by a wiring short or 

lightning strike, which could result in 

fuel tank explosions and consequent 

loss of the airplane. 

DATES: This AD is effective August 20, 

2013. 

The Director of the Federal Register 

approved the incorporation by reference 

of certain publications listed in the AD 

as of August 20, 2013. 

The Director of the Federal Register 

approved the incorporation by reference 

of certain other publications listed in 

this AD as of October 1, 2009 (76 FR 

43621, August 27, 2009). 

ADDRESSES: 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. 

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 AD, the regulatory 

evaluation, any comments received, and 

other information. The address for the 

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

Document 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: 

Rebel Nichols, Aerospace Engineer, 

Propulsion Branch, ANM–140S, FAA, 

Seattle Aircraft Certification Office, 

1601 Lind Avenue SW., Renton, WA 

98057–3356; phone: 425–917–6509; fax: 

425–917–6590; email: 

rebel.nichols@faa.gov. 

SUPPLEMENTARY INFORMATION:

Discussion 

We issued a notice of proposed 

rulemaking (NPRM) to amend 14 CFR 

part 39 to supersede AD 2009–18–02, 

Amendment 39–15998 (74 FR 43621, 

August 27, 2009). AD 2009–18–02 

applied to the specified products. The 

NPRM published in the Federal 

Register on September 6, 2012 (77 FR 

54850). The NPRM proposed to 

continue to require sealing certain 

fasteners and stiffeners in the fuel tank, 

changing certain wire bundle clamp 

configurations on the fuel tank walls, 

inspecting certain fasteners in the fuel 

tanks and determining the method of 

attachment of the vortex generators; and 

performing corrective action if 

necessary. The NPRM also proposed to 

require a general visual inspection for 

the presence of a 

polytetrafluoroethylene (TFE) sleeve at 

the clamp location on the rear spar, and 

installation of a TFE sleeve if necessary. 

The NPRM also proposed to add 

airplanes to the applicability. 

Comments 

We gave the public the opportunity to 

participate in developing this AD. The 

following presents the comments 

received on the proposal (77 FR 54850, 

September 6, 2012) and the FAA’s 

response to each comment. 

United Airlines stated that it has no 

comment for the NPRM (77 FR 54850, 

September 6, 2012). 

Request to Change Acronym 

Boeing requested that we change the 

NPRM (77 FR 54850, September 6, 

2012) to correct an acronym from ‘‘TFE’’ 

to ‘‘PTFE.’’ Boeing stated that the proper 

acronym for polytetrafluoroethylene is 

‘‘PTFE.’’ 

We disagree with changing the 

acronym in this AD. The service 

information required by this AD refers 

to polytetrafluoroethylene as ‘‘TFE’’ 

throughout; therefore, to reduce the 

potential for confusion, we have not 

changed the acronym ‘‘TFE’’ in this AD. 

Request for Credit 

Air New Zealand requested that we 

allow credit for prior incorporation of 

Boeing Service Bulletin 767–57A0102, 

Revision 3, dated December 2, 2010, for 

the requirements of paragraph (j) of the 

NPRM (77 FR 54850, September 6, 

2012). 

We agree with the request, but 

provide the following clarification. 

Paragraph (j) of this AD specifies the 

compliance time for certain airplanes to 

accomplish the actions of paragraph (h) 

of this AD. We have changed the 

heading for paragraph (j) of this AD to 

focus on the compliance time. 

Paragraph (h) of this AD specifies to do 

the actions in accordance with Boeing 

Service Bulletins 767–57A0102, 

Revision 01, dated November 27, 2007; 

or Revision 4, dated September 20, 

2011. Since paragraph (l)(2) of this AD 

gives credit for Boeing Service Bulletin 

767–57A0102, Revision 3, dated 

December 2, 2010, for accomplishing 

the actions in paragraph (h) of this AD, 

we have not changed the AD in this 

regard. 

STC Winglet Comment 

Aviation Partners Boeing and Air New 

Zealand stated that the installation of 

winglets per STC ST01920SE (http:// 

rgl.faa.gov/Regulatory_and_Guidance_

Library/rgstc.nsf/0/ 

59027F43B9A7486E86257

B1D006591EE?OpenDocument

&Highlight=st01920se) does not affect 

the accomplishment of the 

manufacturer’s service instructions. 

We have added paragraph (c)(2) to 

this AD to state that installation of STC 

ST01920SE does not affect the ability to 

accomplish the actions required by this 

AD. Therefore, for airplanes on which 

STC ST01920SE is installed, a ‘‘change 

in product’’ alternative method of 

compliance (AMOC) approval request is 

not necessary to comply with the 

requirements of 14 CFR 39.17. For all 

other AMOC requests, the operator must 

request approval for an AMOC in 

accordance with the procedures 

specified in paragraph (m) of this AD. 

Conclusion 

We reviewed the relevant data, 

considered the comments received, and 

determined that air safety and the 

public interest require adopting this AD 

with the change described previously 

and minor editorial changes. We have 

determined that these minor changes: 

• Are consistent with the intent that 

was proposed in the NPRM (77 FR 

54850, September 6, 2012) for correcting 

the unsafe condition; and 

• Do not add any additional burden 

upon the public than was already 

proposed in the NPRM (77 FR 54850, 

September 6, 2012). 

We also determined that these 

changes will not increase the economic 

burden on any operator or increase the 

scope of this AD. 

Costs of Compliance 

We estimate that this AD affects 414 

airplanes of U.S. registry. 

We estimate the following costs to 

comply with this AD: 

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Federal Register / Vol. 78, No. 136 / Tuesday, July 16, 2013 / Rules and Regulations 42413 

ESTIMATED COSTS

Action Labor cost Parts cost Cost per 

product 

Number of 

U.S.-registered 

airplanes 

Cost on U.S. 

operators 

Group 1—Seal ends of fasteners— 

Boeing Service Bulletin 

767-57A0100 (retained actions 

from AD 2009–18–02, Amendment 

39–15998 (74 FR 43621, August 

27, 2009)).

6 work-hours × $85 per hour = $510 $0 $510 367 $187,170 

Group 2—Seal ends of fasteners— 

Boeing Service Bulletin 

767-57A0100 (retained actions 

from AD 2009–18–02, Amendment 

39–15998 (74 FR 43621, August 

27, 2009)).

114 work-hours × $85 per hour = 

$9,690.

0 9,690 37 358,530 

Group 3—Inspection—Boeing Service Bulletin 767–57A0100 (retained actions from AD 2009–18– 

02, Amendment 39–15998 (74 FR 

43621, August 27, 2009)).

1 work-hour × $85 per hour = $85 ... 0 85 9 765 

Group 1—Change wire bundle 

clamp configurations, Boeing 

Service Bulletin 767-57A0102 (retained actions from AD 2009–18– 

02, Amendment 39–15998 (74 FR 

43621, August 27, 2009)).

250 work-hours × $85 per hour = 

$21,250.

1,632 22,882 376 8,603,632 

Group 2—Change wire bundle 

clamp configurations, Boeing 

Service Bulletin 767-57A0102 (retained actions from AD 2009–18– 

02, Amendment 39–15998 (74 FR 

43621, August 27, 2009)).

874 work-hours × $85 per hour = 

$74,290.

1,304 75,594 37 2,796,978 

Group 3—Change wire bundle 

clamp configuration and seal fasteners, Boeing Service Bulletin 

767-57A0102 (retained actions 

from AD 2009–18–02, Amendment 

39–15998 (74 FR 43621, August 

27, 2009)).

26 work-hours × $85 per hour = 

$2,210.

338 2,548 1 2,548 

All airplanes—Inspection (new action).1 work-hour × $85 per hour = $85 ... 0 85 414 35,190 

We estimate the following costs to do 

any necessary repair that would be 

required based on the results of the 

inspection. We have no way of 

determining the number of aircraft that 

might need this repair: 

ON-CONDITION COSTS

Action Labor cost Parts cost Cost per product 

Seal ends of fasteners—Boeing Service Bulletin 767–57A0100 (retained actions from AD 2009–18–02, Amendment 39–15998 (74 FR 

43621, August 27, 2009)).

6 work-hours × $85 per hour = 

$510.

$0 Up to $510. 

Installation of TFE sleeve—Boeing Service Bulletin 767-57A0102 ....... 1 work-hour × $85 per hour = $85 $0 $85. 

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 have 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: 

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42414 Federal Register / Vol. 78, No. 136 / Tuesday, July 16, 2013 / Rules and Regulations 

(1) Is not a ‘‘significant regulatory 

action’’ under Executive Order 12866, 

(2) Is not a ‘‘significant rule’’ under 

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 

removing airworthiness directive (AD) 

2009–18–02, Amendment 39–15998 (74 

FR 43621, August 27, 2009), and adding 

the following new AD: 

2013–13–08 The Boeing Company: 

Amendment 39–17496; Docket No. 

FAA–2012–0864; Directorate Identifier 

2011–NM–023–AD. 

(a) Effective Date 

This airworthiness directive (AD) is 

effective August 20, 2013. 

(b) Affected ADs 

This AD supersedes AD 2009–18–02, 

Amendment 39–15998 (74 FR 43621, August 

27, 2009). 

(c) Applicability 

(1) This AD applies to The Boeing 

Company Model 767–200, –300, –300F, and 

–400ER series airplanes; certificated in any 

category; as identified in Boeing Service 

Bulletin 767–57A0100, Revision 3, dated July 

28, 2011; and Boeing Service Bulletin 767– 

57A0102, Revision 4, dated September 20, 

2011. 

(2) Installation of Supplemental Type 

Certificate (STC) ST01920SE (http:// 

rgl.faa.gov/Regulatory_and_Guidance_

Library/rgstc.nsf/0/59027F43B9A74

86E86257B1D006591EE?OpenDocument

&Highlight=st01920se) does not affect the 

ability to accomplish the actions required by 

this AD. Therefore, for airplanes on which 

STC ST01920SE is installed, a ‘‘change in 

product’’ alternative method of compliance 

(AMOC) approval request is not necessary to 

comply with the requirements of 14 CFR 

39.17. 

(d) Subject 

Joint Aircraft System Component (JASC)/ 

Air Transport Association (ATA) of America 

Code 57, Wings. 

(e) Unsafe Condition 

This AD was prompted by fuel system 

reviews conducted by the manufacturer. We 

are issuing this AD to prevent possible 

ignition sources in the auxiliary (center) fuel 

tank, main fuel tanks, and surge tanks caused 

by a wiring short or lightning strike, which 

could result in fuel tank explosions and 

consequent loss of the airplane. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Retained Fastener Sealant Application 

This paragraph restates the requirements of 

paragraph (f) of AD 2009–18–02, Amendment 

39–15998 (74 FR 43621, August 27, 2009), 

with revised service information. For 

airplanes identified in Boeing Service 

Bulletin 767–57A0100, Revision 01, dated 

June 19, 2008: Within 60 months after 

October 1, 2009 (the effective date of AD 

2009–18–02), do the actions in paragraph 

(g)(1) or (g)(2) of this AD, as applicable, in 

accordance with the Accomplishment 

Instructions of Boeing Service Bulletin 767– 

57A0100, Revision 01, dated June 19, 2008; 

or Boeing Service Bulletin 767–57A0100, 

Revision 3, dated July 28, 2011. As of the 

effective date of this AD, only Boeing Service 

Bulletin 767–57A0100, Revision 3, dated July 

28, 2011, may be used to accomplish the 

requirements of this paragraph. 

(1) For Groups 1 and 2 airplanes: Seal the 

ends of the fasteners on the brackets that 

hold the vortex generators, and seal the ends 

of the fasteners on certain stiffeners on the 

rear spar, as applicable. 

(2) For Group 3 airplanes: Do a detailed 

inspection to determine the method of 

attachment of the vortex generators and, 

before further flight, do all applicable 

specified corrective actions. 

(h) Retained Wire Bundle Sleeve and Clamp 

Installation and Fastener Sealant 

Application 

This paragraph restates the requirements of 

paragraph (g) of AD 2009–18–02, 

Amendment 39–15998 (74 FR 43621, August 

27, 2009), with revised service information. 

For airplanes identified in Boeing Service 

Bulletin 767–57A0102, Revision 01, dated 

November 27, 2007: Within 60 months after 

October 1, 2009 (the effective date of AD 

2009–18–02), do the actions specified in 

paragraphs (h)(1), (h)(2), and (h)(3) of this 

AD, as applicable, in accordance with the 

Accomplishment Instructions of Boeing 

Service Bulletin 767–57A0102, Revision 01, 

dated November 27, 2007; or Boeing Service 

Bulletin 767–57A0102, Revision 4, dated 

September 20, 2011. As of the effective date 

of this AD, only Boeing Service Bulletin 767– 

57A0102, Revision 4, dated September 20, 

2011, may be used to accomplish the actions 

required by this paragraph. 

(1) Change the wire bundle clamp 

configurations at specified locations on the 

fuel tank walls. 

(2) Seal the fasteners and certain stiffeners 

at specified locations in the fuel tank. 

(3) Do a detailed inspection of the sealant 

of the fasteners in the auxiliary tank center 

bay and rib 28 of the left and right main fuel 

tanks. Seal any unsealed fasteners before 

further flight. 

(i) Definition 

This paragraph restates the information 

specified in Note 1 of AD 2009–18–02, 

Amendment 39–15998 (74 FR 43621, August 

27, 2009). For the purposes of this AD, a 

detailed inspection is: An intensive 

examination of a specific item, installation, 

or assembly to detect damage, failure, or 

irregularity. Available lighting is normally 

supplemented with a direct source of good 

lighting at an intensity deemed appropriate. 

Inspection aids such as mirror, magnifying 

lenses, etc., may be necessary. Surface 

cleaning and elaborate procedures may be 

required. 

(j) Compliance Time for New Wire Bundle 

Sleeve and Clamp Installation and Fastener 

Sealant Application for Newly Added 

Airplanes 

For airplanes identified in Boeing Service 

Bulletin 767–57A0102, Revision 4, dated 

September 20, 2011, but not identified in 

paragraph (h) of this AD: Do the actions 

required by paragraph (h) of this AD within 

60 months after the effective date of this AD. 

(k) New Inspection and Sleeve Installation 

For airplanes identified as Groups 1 and 2 

in Boeing Service Bulletin 767–57A0102, 

Revision 4, dated September 20, 2011: 

Within 60 months after the effective date of 

this AD, do a general visual inspection of the 

clamp location on the rear spar to determine 

whether a polytetrafluoroethylene (TFE) 

sleeve is installed between the clamp and the 

plastic convoluted tube, in accordance with 

Work Package 13 of the Accomplishment 

Instructions of Boeing Service Bulletin 767– 

57A0102, Revision 4, dated September 20, 

2011. 

(1) If a TFE sleeve is not installed between 

the clamp and the plastic convoluted tubing, 

before further flight, install a TFE sleeve, in 

accordance with the Accomplishment 

Instructions of Boeing Service Bulletin 767– 

57A0102, Revision 4, dated September 20, 

2011. 

(2) If a TFE sleeve is installed between the 

clamp and the plastic convoluted tubing, no 

more work is required by this paragraph. 

(l) Credit for Previous Actions 

(1) This paragraph provides credit for the 

actions required by paragraph (g) of this AD, 

if those actions were performed before the 

effective date of this AD using Boeing Service 

Bulletin 767–57A0100, dated August 21, 

2006, which is not incorporated by reference 

in this AD; Revision 1, dated June 19, 2008; 

or Revision 2, dated May 20, 2010, which is 

not incorporated by reference in this AD. 

(2) This paragraph provides credit for the 

actions required by paragraph (h) of this AD, 

if those actions were performed before the 

effective date of this AD using Boeing Service 

Bulletin 767–57A0102, Revision 1, dated 

November 27, 2007; Revision 2, dated 

January 7, 2010, which is not incorporated by 

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Federal Register / Vol. 78, No. 136 / Tuesday, July 16, 2013 / Rules and Regulations 42415 

reference in this AD; or Revision 3, dated 

December 2, 2010, which is not incorporated 

by reference in this AD. 

(m) 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) AMOCs approved previously in 

accordance with AD 2009–18–02, 

Amendment 39–15998 (74 FR 43621, August 

27, 2009), are approved as AMOCs for the 

corresponding provisions of this AD. 

(n) Related Information 

(1) For more information about this AD, 

contact Rebel Nichols, Aerospace Engineer, 

Propulsion Branch, ANM–140S, FAA, Seattle 

Aircraft Certification Office, 1601 Lind 

Avenue SW., Renton, WA 98057–3356; 

phone: 425–917–6509; fax: 425–917–6590; 

email: rebel.nichols@faa.gov. 

(2) Service information identified in this 

AD that is not incorporated by reference may 

be obtained at the address specified in 

paragraph (o)(5) of this AD. 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. 

(o) 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 the AD specifies otherwise. 

(3) The following service information was 

approved for IBR on August 20, 2013. 

(i) Boeing Service Bulletin 767–57A0100, 

Revision 3, dated July 28, 2011. 

(ii) Boeing Service Bulletin 767–57A0102, 

Revision 4, dated September 20, 2011. 

(4) The following service information was 

approved for IBR on October 1, 2009, (74 FR 

43621, August 27, 2009). 

(i) Boeing Service Bulletin 767–57A0100, 

Revision 01, dated June 19, 2008. 

(ii) Boeing Service Bulletin 767–57A0102, 

Revision 01, dated November 27, 2007. 

(5) 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. 

(6) You may view this service information 

at FAA, 1601 Lind Avenue SW., Renton, WA. 

For information on the availability of this 

material at the FAA, call 425–227–1221. 

(7) 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 June 13, 

2013. 

Jeffrey E. Duven, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2013–15526 Filed 7–15–13; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2013–0302; Directorate 

Identifier 2013–NM–019–AD; Amendment 

39–17503; AD 2013–13–15] 

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) 87–02–07, 

which applied to all The Boeing 

Company Model 737–100 and –200 

series airplanes. AD 87–02–07 required 

replacement of certain underwing fuel 

tank access covers with stronger, fireresistant covers. This new AD also 

requires inspecting fuel tank access 

doors to determine that impact-resistant 

access doors are installed in the correct 

locations, inspecting application of 

stencils and index markers of impactresistant access doors, doing corrective 

actions if necessary, revising the 

maintenance program, and adding 

airplanes to the applicability. This AD 

was prompted by reports of standard 

access doors installed where impactresistant access doors are required, and 

reports of impact-resistant doors 

without stencils. We are issuing this AD 

to prevent foreign object penetration of 

the wing tank, which could lead to a 

fuel leak near ignition sources (engine, 

hot brakes), consequently leading to a 

fuel-fed fire. 

DATES: This AD is effective August 20, 

2013. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication listed in the AD 

as of August 20, 2013. 

ADDRESSES: 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 Directate, 1601 Lind Avenue 

SW., Renton, Washington. For 

information on the availability of this 

material at the FAA, call 425–227–1221. 

Examining the AD Docket 

You may examine the AD docket on 

the Internet at http:// 

www.regulations.gov; or in person at the 

Docket Management Facility between 9 

a.m. and 5 p.m., Monday through 

Friday, except Federal holidays. The AD 

docket contains this AD, the regulatory 

evaluation, any comments received, and 

other information. The address for the 

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

Document 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: 

Suzanne Lucier, Aerospace Engineer, 

Propulsion Branch, ANM–140S, FAA, 

Seattle Aircraft Certification Office, 

1601 Lind Avenue SW., Renton, 

Washington 98057–3356; phone: 425– 

917–6438; fax: 425–917–6590; email: 

suzanne.lucier@faa.gov. 

SUPPLEMENTARY INFORMATION: 

Discussion 

We issued a notice of proposed 

rulemaking (NPRM) to amend 14 CFR 

part 39 to supersede AD 87–02–07, 

Amendment 39–5506 (Docket No. 86– 

NM–175–AD; 52 FR 518, January 7, 

1987), (‘‘AD 87–02–07’’). AD 87–02–07 

applied to the specified products. The 

NPRM published in the Federal 

Register on April 10, 2013 (78 FR 

21279). The NPRM proposed to 

continue to require replacement of 

certain underwing fuel tank access 

covers with stronger, fire-resistant 

covers. The NPRM also proposed to 

require inspecting fuel tank access doors 

to determine that impact-resistant 

access doors are installed in the correct 

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