34864 Federal Register / Vol. 81, No. 105 / Wednesday, June 1, 2016 / Rules and Regulations 

adding in its place ‘‘paragraph (c) of this 

section’’. 

PART 114—CORPORATE AND LABOR 

ORGANIZATION ACTIVITY 

■ 18. The authority citation for part 114 

continues to read as follows: 

Authority: 52 U.S.C. 30101(8), 30101(9), 

30102, 30104, 30107(a)(8), 30111(a)(8), 

30118. 

§ 114.2 [Amended] 

■ 19. Amend the note to paragraph (b) 

of § 114.2 by removing all references to 

‘‘non-connected’’ and adding in their 

place ‘‘nonconnected’’. 

§ 114.10 [Amended] 

■ 20. Amend the note to paragraph (a) 

of § 114.10 by removing all references to 

‘‘non-connected’’ and adding in their 

place ‘‘nonconnected’’. 

PART 9004—ENTITLEMENT OF 

ELIGIBLE CANDIDATES TO 

PAYMENTS; USE OF PAYMENTS 

■ 21. The authority citation for part 

9004 continues to read as follows: 

Authority: 26 U.S.C. 9004 and 9009(b). 

§ 9004.6 [Amended] 

■ 22. Amend the subject heading to 

paragraph (c) introductory text of 

§ 9004.6 by removing ‘‘Deducation’’ and 

adding in its place ‘‘Deduction’’. 

PART 9034—ENTITLEMENTS 

■ 23. The authority citation for part 

9034 continues to read as follows: 

Authority: 26 U.S.C. 9034 and 9039(b). 

§ 9034.2 [Amended] 

■ 24. Amend paragraph (c)(1)(iii) of 

§ 9034.2 by removing ‘‘11 CFR 110.1 (1), 

(3), (5), and (6)’’ and adding in its place 

‘‘11 CFR 110.1(l)(3), (5), and (6)’’. 

On behalf of the Commission, 

Dated: May 23, 2016. 

Matthew S. Petersen, 

Chairman, Federal Election Commission. 

[FR Doc. 2016–12661 Filed 5–31–16; 8:45 am] 

BILLING CODE 6715–01–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2015–0496; Directorate 

Identifier 2014–NM–101–AD; Amendment 

39–18533; AD 2016–11–06] 

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) 2005–18– 

18 for certain The Boeing Company 

Model 757 airplanes. AD 2005–18–18 

required inspections of certain wire 

bundles in the left and right engine-towing aft fairings for discrepancies; 

installation of back-to-back p-clamps 

between the wire and hydraulic supply 

tube at the aft end of the right-hand strut 

only; and associated re-routing of the 

wire bundles, if necessary. This new AD 

also requires an installation of spiral 

cable wrap on fuel shutoff valve (FSV) 

wires at the aft end of the strut, for both 

left and right engines, and related 

investigative and corrective actions. 

This AD was prompted by a 

determination that the service 

information referenced in AD 2005–18– 

18 did not adequately address FSV 

wires at the aft end of the struts. We are 

issuing this AD to prevent chafing 

between the wire bundle and the 

structure of the aft fairing, which could 

result in electrical arcing and 

subsequent ignition of flammable vapors 

and a possible uncontrollable fire. 

DATES: This AD is effective July 6, 2016. 

The Director of the Federal Register 

approved the incorporation by reference 

of certain publications listed in this AD 

as of July 6, 2016. 

The Director of the Federal Register 

approved the incorporation by reference 

of certain other publications listed in 

this AD as of October 14, 2005 (70 FR 

53554, September 9, 2005). 

ADDRESSES: For service information 

identified in this final rule, 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 view this referenced service 

information at the FAA, Transport 

Airplane Directorate, 1601 Lind Avenue 

SW., Renton, WA 98057. For 

information on the availability of this 

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

It is also available on the Internet at 

http://www.regulations.gov by searching 

for and locating Docket No. FAA–2015– 

0496. 

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–2015– 

0496; 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: 

William Bond, Aerospace Engineer, 

Propulsion Branch, ANM–140L, FAA, 

Los Angeles Aircraft Certification Office 

(ACO), 3960 Paramount Boulevard, 

Lakewood, CA 90712–4137; phone: 

562–627–5253; fax: 562–627–5210; 

email: william.bond@faa.gov. 

SUPPLEMENTARY INFORMATION: 

Discussion 

We issued a notice of proposed 

rulemaking (NPRM) to amend 14 CFR 

part 39 to supersede AD 2005–18–18, 

Amendment 39–14258 (70 FR 53554, 

September 9, 2005) (‘‘AD 2005–18–18’’). 

AD 2005–18–18 applied to certain The 

Boeing Company Model 757–200, 

–200PF, –200CB, and –300 series 

airplanes. The NPRM published in the 

Federal Register on March 27, 2015 (80 

FR 16318) (‘‘the NPRM’’). The NPRM 

was prompted by a report that the 

service information referenced in AD 

2005–18–18 did not adequately address 

FSV wires at the aft end of the strut, for 

both left and right engine struts. The 

NPRM proposed to continue to require 

inspections of certain wire bundles in 

the left and right engine-to-wing aft 

fairings for discrepancies; installation of 

back-to-back p-clamps between the wire 

and hydraulic supply tube at the aft end 

of the right-hand strut only; and 

associated re-routing of the wire 

bundles, if necessary. The NPRM also 

proposed to require installation of 

tetrafluoroethylene spiral cable wrap on 

the FSV wires at the aft end of the strut 

that would provide additional wiring 

protection. We are issuing this AD to 

prevent chafing between the wire 

bundle and the structure of the aft 


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Federal Register / Vol. 81, No. 105 / Wednesday, June 1, 2016 / Rules and Regulations 34865 

fairing, which could result in electrical 

arcing and subsequent ignition of 

flammable vapors and a possible 

uncontrollable fire. 

Comments 

We gave the public the opportunity to 

participate in developing this AD. The 

following presents the comments 

received on the NPRM and the FAA’s 

response to each comment. 

Request To Clarify Certain 

Requirements 

Boeing requested clarification of the 

actions required by paragraph (g) of the 

proposed AD. Boeing suggested that 

paragraph (g) of the proposed AD be 

revised to add a statement to clarify that 

no further work would be required if the 

requirements of AD 2005–18–18 have 

already been accomplished. 

We agree to provide clarification. In 

paragraph (g) of this AD, we restated the 

requirements of paragraph (f) of AD 

2005–18–18. Paragraph (f) of this AD 

states, ‘‘Comply with this AD within the 

compliance times specified, unless 

already done.’’ If operators have already 

done the actions required by paragraph 

(f) of AD 2005–18–18, they have already 

done the actions required by paragraph 

(g) of this AD. If operators have not 

already done the actions required by 

paragraph (g) of this AD before the 

effective date of the AD, then they must 

use the most recent revision of the 

service information. We have not 

changed this AD in this regard. 

Request To Clarify Certain Compliance 

Time Requirements 

Boeing requested clarification of the 

compliance times stated in paragraph 

(h) of the proposed AD. Boeing stated 

that there is confusion between ‘‘Within 

60 months after the effective date of this 

AD . . . ,’’ as stated in the first sentence 

of the paragraph for the spiral cable 

wrap installation, and ‘‘. . . before 

further flight,’’ as stated in the second 

sentence for the related investigative 

and corrective actions. Boeing suggested 

that the second sentence be deleted 

from paragraph (h) of the proposed AD. 

We do not agree to revise paragraph 

(h) of this AD. The installation of the 

spiral cable wrap includes related 

investigative and corrective actions, i.e., 

doing inspections for damaged wire 

bundles, repairing damaged wires, and 

testing certain fuel shutoff wires. These 

related investigative and corrective 

actions must be done before further 

flight after damage is found. We have 

not changed the AD in this regard. 

Request To Provide Credit for Required 

Service Information 

FedEx requested that the proposed 

AD be revised to add a paragraph 

granting credit for accomplishing 

Boeing Service Bulletin 757–28A0073 or 

757–28A0074, both Revision 2, both 

dated June 4, 2009, before the effective 

date of the AD. FedEx stated that they 

had already accomplished the 

requirements on airplanes in their fleet. 

We agree to clarify. The intent of 

paragraph (f) of this AD is to provide 

relief for accomplishing the 

requirements of this AD before the 

effective date of this AD. Therefore, this 

AD already includes the credit 

requested by the commenter. We have 

not changed this AD in this regard. 

Request To Allow Credit for Previous 

AMOC Approvals 

United Airlines (UAL) requested that 

a paragraph be added to the proposed 

AD to allow credit for all previously 

approved AMOC letters that affect 

Boeing Service Bulletin 757–28A0073 or 

757–28A0074. 

We do not agree to add a new 

paragraph to this AD. Credit is already 

provided in paragraph (i)(4) of this AD, 

which specifies that AMOCs approved 

for AD 2005–18–18 are also acceptable 

as AMOCs for the corresponding 

provisions of paragraph (g) of this AD. 

(Paragraph (g) of this AD restates the 

requirements of paragraph (f) of AD 

2005–18–18.) Paragraph (h) of this AD is 

a new requirement and AMOCs cannot 

be approved for that paragraph until this 

AD is published. We have not changed 

this AD in this regard. 

Request To Provide Relief for Model 

757–300 Airplanes Similar to Relief 

Provided to Model 757–200 Airplanes 

UAL requested relief for Model 757– 

300 airplanes that is similar to that 

provided to the Model 757–200 

airplanes in FAA AMOC letter 757– 

28A0073–AMOC–01. 

We agree. The issue that the AMOC 

letter addresses (for Boeing Service 

Bulletin 757–28A0073, Revision 2, 

dated June 4, 2009) also exists in Boeing 

Service Bulletin 757–28A0074, Revision 

2, dated June 4, 2009. We have revised 

paragraphs (g) and (h) of this AD to 

include a statement that where Boeing 

Service Bulletin 757–28A0074, Revision 

2, dated June 4, 2009, states ‘‘SWPM 20– 

10–11, Table IX,’’ this AD instead 

requires ‘‘SWPM 20–10–11, ‘Minimum 

Clearance’ Table.’’ 

Request To Incorporate Proposed AD 

Requirements Into the Maintenance 

Planning Data (MPD) Document 

UAL requested that the proposed AD 

be revised to require incorporation of a 

required repetitive inspection of the 

modification into the MPD requirements 

for Model 757 Heavy Check intervals, 

preferably at intervals of 3,000 flight 

cycles or 20 months. UAL suggested that 

this addition to the MPD could ensure 

the long-term integrity of the 

modification. 

We do not agree to require a revision 

to the MPD. We infer that the term 

‘‘modification’’ used by UAL is 

intended to refer to the corrective 

actions required by paragraph (g) of this 

AD, and the cable wrap installation and 

related investigative and corrective 

actions required by paragraph (h) of this 

AD. These actions required by 

paragraphs (g) and (h) of this AD are 

considered to provide long-term 

integrity of the ‘‘modification’’ and 

maintain an acceptable level of safety. 

However, we encourage operators to 

proactively revise their maintenance 

programs in accordance with FAA 

regulations to address problems or 

issues as they arise. We have not 

changed this AD in this regard. 

Effect of Winglets on Accomplishment 

of the Proposed Actions 

Aviation Partners Boeing (APB) stated 

that the installation of winglets per 

Supplemental Type Certificate (STC) 

ST01518SE (http://rgl.faa.gov/

Regulatory_and_Guidance_Library/

rgstc.nsf/0/

312bc296830a925c86257c85006d1b1f/

$FILE/ST01518SE.pdf) does not affect 

accomplishment of the manufacturer’s 

service instructions. 

We agree with the commenter that 

STC ST01518SE (http://rgl.faa.gov/

Regulatory_and_Guidance_Library/

rgstc.nsf/0/

312bc296830a925c86257c85006d1b1f/

$FILE/ST01518SE.pdf) does not affect 

the accomplishment of the 

manufacturer’s service instructions. 

Therefore, the installation of STC 

ST01518SE does not affect the ability to 

accomplish the actions required by this 

AD. We have not changed this AD in 

this regard. 

Change Made to the Format of 

Paragraph (g) of This AD 

We have revised the format of 

paragraph (g) of this AD by converting 

Table 1 to paragraph (g)(1) to text in 

paragraph (g). This change to the format 

does not affect the requirements of 

paragraphs (g), (g)(1), or (g)(2) of this 

AD. 


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34866 Federal Register / Vol. 81, No. 105 / Wednesday, June 1, 2016 / Rules and Regulations 

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 changes described previously 

and minor editorial changes. We have 

determined that these minor changes: 

• Are consistent with the intent that 

was proposed in the NPRM for 

correcting the unsafe condition; and 

• Do not add any additional burden 

upon the public than was already 

proposed in the NPRM. 

We also determined that these 

changes will not increase the economic 

burden on any operator or increase the 

scope of this AD. 

Related Service Information Under 1 

CFR Part 51 

We reviewed Boeing Alert Service 

Bulletins 757–28A0073 and 757– 

28A0074, both Revision 2, both dated 

June 4, 2009. The service information 

describes procedures for inspecting 

certain wire bundles in the left and right 

engine-to-wing aft fairings for 

discrepancies; installing back-to-back pclamps between the wire and hydraulic 

supply tube at the aft end of the righthand strut only; associated re-routing of 

the wire bundles, if necessary; and 

installing spiral cable wrap on FSV 

wires on the aft ends of the left and right 

engine struts, and related investigative 

and corrective actions. This service 

information is reasonably available 

because the interested parties have 

access to it through their normal course 

of business or by the means identified 

in the ADDRESSES section. 

Costs of Compliance 

We estimate that this AD affects 346 

airplanes of U.S. registry. 

We estimate the following costs to 

comply with this AD: 

ESTIMATED COSTS

Action Labor cost Parts cost Cost per 

product 

Cost on U.S. 

operators 

Inspection of certain wire bundles, and p-clamp installation [retained actions from AD 2005–18–18].Between 16 and 44 

work-hours × $85 per 

hour = Between 

$1,360 and $3,740.

$600 Between $1,960 and 

$4,340.

Between $678,160 

and $1,501,640 

Installation of spiral cable wrap [new action] .......... 10 work-hours × $85 per 

hour = $850.

$10 $860 ............................... $297,560 

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: 

(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) 

2005–18–18, Amendment 39–14258 (70 

FR 53554, September 9, 2005), and 

adding the following new AD: 

2016–11–06 The Boeing Company: 

Amendment 39–18533; Docket No. 

FAA–2015–0496; Directorate Identifier 

2014–NM–101–AD. 

(a) Effective Date 

This AD is effective July 6, 2016. 

(b) Affected ADs 

This AD replaces AD 2005–18–18, 

Amendment 39–14258 (70 FR 53554, 

September 9, 2005) (‘‘AD 2005–18–18’’). 

(c) Applicability 

This AD applies to The Boeing Company 

Model 757–200, –200PF, –200CB, and –300 

series airplanes; certificated in any category; 

equipped with Rolls-Royce engines; as 

identified in Boeing Alert Service Bulletins 

757–28A0073 and 757–28A0074, both 

Revision 2, both dated June 4, 2009. 

(d) Subject 

Air Transport Association (ATA) of 

America Code 28, Fuel. 

(e) Unsafe Condition 

This AD was prompted by a report that the 

service information referenced in AD 2005– 

18–18, did not adequately address fuel 

shutoff valve (FSV) wires at the aft end of the 

strut, for both left and right engine struts. We 

are issuing this AD to prevent chafing 

between the wire bundle and the structure of 

the aft fairing, which could result in 

electrical arcing and subsequent ignition of 

flammable vapors and a possible 

uncontrollable fire. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 


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Federal Register / Vol. 81, No. 105 / Wednesday, June 1, 2016 / Rules and Regulations 34867 

(g) Retained One-Time Inspections/Related 

Investigative and Corrective Actions, With 

New Service Information and an Exception 

to Certain Service Information 

This paragraph restates the requirements of 

paragraph (f) of AD 2005–18–18, with new 

service information and an exception to 

certain service information. Within 60 

months after October 14, 2005 (the effective 

date of AD 2005–18–18), do the actions 

required by paragraphs (g)(1) and (g)(2) of 

this AD. Where Boeing Alert Service Bulletin 

757–28A0074, Revision 2, dated June 4, 

2009, states ‘‘SWPM 20–10–11, Table IX,’’ 

the correct phrase is ‘‘SWPM 20–10–11, 

‘Minimum Clearance’ Table.’’ 

(1) Accomplish the detailed inspections for 

discrepancies of the wire bundles in the left 

and right engine-to-wing aft fairings, and 

applicable and related investigative and 

corrective actions if necessary, as applicable, 

by doing all the actions specified in the 

Accomplishment Instructions of the 

applicable service bulletins listed in 

paragraphs (g)(1)(i) and (g)(1)(ii) of this AD. 

As of the effective date of this AD, use only 

Boeing Alert Service Bulletin 757–28A0073 

or 757–28A0074, both Revision 2, both dated 

June 4, 2009, as applicable. Accomplish any 

related investigative and corrective actions 

before further flight, in accordance with the 

applicable service bulletin. 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.’’ 

(i) For Boeing Model 757–200, –200CB, 

and –200PF series airplanes, use the service 

information identified in paragraphs 

(g)(1)(i)(A), (g)(1)(i)(B), and (g)(1)(i)(C) of this 

AD. 

(A) Boeing Alert Service Bulletin 757– 

28A0073, dated November 20, 2003; 

(B) Boeing Alert Service Bulletin 757– 

28A0073, Revision 1, dated February 24, 

2005. 

(C) Boeing Alert Service Bulletin 757– 

28A0073, Revision 2, dated June 4, 2009. 

(ii) For Boeing Model 757–300 series 

airplanes, use the service information 

identified in paragraphs (g)(1)(ii)(A), 

(g)(1)(ii)(B), and (g)(1)(ii)(C) of this AD. 

(A) Boeing Alert Service Bulletin 757– 

28A0074, dated November 20, 2003. 

(B) Boeing Alert Service Bulletin 757– 

28A0074, Revision 1, dated February 24, 

2005. 

(C) Boeing Alert Service Bulletin 757– 

28A0074, Revision 2, dated June 4, 2009. 

(2) Install back-to-back p-clamps between 

the wire and hydraulic supply tube at the aft 

end of the right-hand strut only; and re-route 

the wire bundles, if necessary; by doing all 

the applicable actions specified in the 

Accomplishment Instructions of the 

applicable service information identified in 

paragraphs (g)(2)(i) through (g)(2)(iv) of this 

AD. As of the effective date of this AD, use 

only the service information identified in 

paragraphs (g)(2)(ii) and (g)(2)(iv) of this AD, 

as applicable. 

(i) Boeing Alert Service Bulletin 757– 

28A0073, Revision 1, dated February 24, 

2005. 

(ii) Boeing Alert Service Bulletin 757– 

28A0073, Revision 2, dated June 4, 2009. 

(iii) Boeing Alert Service Bulletin 757– 

28A0074, Revision 1, dated February 24, 

2005. 

(iv) Boeing Alert Service Bulletin 757– 

28A0074, Revision 2, dated June 4, 2009. 

(h) New Spiral Cable Wrap Installation 

Within 60 months after the effective date 

of this AD, install spiral cable wrap on FSV 

wires at the aft end of the strut, for both left 

and right engines, and do all applicable 

related investigative and corrective actions, 

in accordance with the Accomplishment 

Instructions of Boeing Alert Service Bulletin 

757–28A0073 (for Model 757–200, –200CB, 

and –200PF series airplanes) or 757–28A0074 

(for Model 757–300 series airplanes), both 

Revision 2, both dated June 4, 2009. Where 

Boeing Alert Service Bulletin 757–28A0074, 

Revision 2, dated June 4, 2009, states ‘‘SWPM 

20–10–11, Table IX,’’ the correct phrase is 

‘‘SWPM 20–10–11, ‘Minimum Clearance’ 

Table.’’ Do all applicable related investigative 

and corrective actions before further flight. 

(i) Alternative Methods of Compliance 

(AMOCs) 

(1) The Manager, Los Angeles 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 

paragraph (j) of this AD. Information may be 

emailed to: 9-ANM-LAACO-AMOCRequests@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, 

modification, or alteration required by this 

AD if it is approved by the Boeing 

Commercial Airplanes Organization 

Designation Authorization (ODA) that has 

been authorized by the Manager, Los Angeles 

ACO, to make those findings. To be 

approved, the repair method, modification 

deviation, or alteration deviation must meet 

the certification basis of the airplane, and the 

approval must specifically refer to this AD. 

(4) AMOCs approved for AD 2005–18–18 

are approved as AMOCs for the 

corresponding provisions of paragraph (g) of 

this AD. 

(j) Related Information 

For more information about this AD, 

contact William Bond, Aerospace Engineer, 

Propulsion Branch, ANM–140L, FAA, Los 

Angeles ACO, 3960 Paramount Boulevard, 

Lakewood, CA 90712–4137; phone: 562–627– 

5253; fax: 562–627–5210; email: 

william.bond@faa.gov. 

(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 the AD specifies otherwise. 

(3) The following service information was 

approved for IBR on July 6, 2016. 

(i) Boeing Alert Service Bulletin 757– 

28A0073, Revision 2, dated June 4, 2009. 

(ii) Boeing Alert Service Bulletin 757– 

28A0074, Revision 2, dated June 4, 2009. 

(4) The following service information was 

approved for IBR on October 14, 2005 (70 FR 

53554, September 9, 2005). 

(i) Boeing Alert Service Bulletin 757– 

28A0073, dated November 20, 2003. 

(ii) Boeing Alert Service Bulletin 757– 

28A0073, Revision 1, dated February 24, 

2005. 

(iii) Boeing Alert Service Bulletin 757– 

28A0074, dated November 20, 2003. 

(iv) Boeing Alert Service Bulletin 757– 

28A0074, Revision 1, dated February 24, 

2005. 

(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 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. 

(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 May 17, 

2016. 

Dionne Palermo, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2016–12331 Filed 5–31–16; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2015–1273; Directorate 

Identifier 2014–NM–194–AD; Amendment 

39–18530; AD 2016–11–03] 

RIN 2120–AA64 

Airworthiness Directives; The Boeing 

Company Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule. 


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