Federal Register / Vol. 78, No. 95 / Thursday, May 16, 2013 / Rules and Regulations 28729 

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 

removing airworthiness directive (AD) 

2010–15–51, Amendment 39–16397 (75 

FR 50863, August 18, 2010), and adding 

the following new AD: 

2013–09–06 Agusta S.p.A.: Amendment 39– 

17448; Docket No. FAA–2012–0695; 

Directorate Identifier 2011–SW–031–AD. 

(a) Applicability 

This AD applies to Agusta Model A119 and 

AW119 MKII helicopters, with pilot control 

box assembly (control box), part number 

(P/N) 109–0010–81–103, and co-pilot control 

box, P/N 109–0010–81–107, installed, 

certificated in any category. 

(b) Unsafe Condition 

This AD defines the unsafe condition as a 

rotary variable differential transformer 

(RVDT) locking pin, which could move out 

of position and result in loss of manual 

throttle control of the engine and subsequent 

loss of control of the helicopter. 

(c) Affected ADs 

This AD supersedes AD 2010–15–51, 

Amendment 39–16397 (75 FR 50863, August 

18, 2010). 

(d) Effective Date 

This AD becomes effective June 20, 2013. 

(e) 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. 

(f) Required Actions 

(1) Within 5 hours time-in-service (TIS), 

and thereafter at intervals not to exceed 50 

hours TIS, remove the cover of the pilot and 

co-pilot RVDT control box assemblies and 

inspect the locking pins for proper position 

by following the Compliance Instructions, 

Parts I and II, paragraphs 2. through 4.1 for 

the pilot control box assembly and 

paragraphs 5. through 7.1 for the co-pilot 

control box assembly, of Agusta Bollettino 

Tecnico No. 119–39, Revision A, dated May 

23, 2011. 

(2) If during the inspection the locking pin 

is recessed or extended in excess of 2.0 

millimeters from the face of the pin bore, or 

missing, before further flight, replace the 

RVDT control box with an airworthy RVDT 

control box that has been modified in 

accordance with paragraph (f)(3) of this AD. 

(3) Within 8 months, 

(i) Modify the pilot RVDT control box 

assembly, P/N 109–0010–81–103, by 

reference to Figures 1 through 7 and in 

accordance with the Compliance 

Instructions, Part III, paragraphs 5.1 through 

5.16 of Agusta Bollettino Tecnico No. 119– 

39 Revision A, dated May 23, 2011; and 

(ii) Modify the co-pilot RVDT control box 

assembly, P/N 109–0010–81–107, by 

reference to Figures 1 through 7 and in 

accordance with the Compliance 

Instructions, Part III, paragraphs 3.1 through 

3.16 of Agusta Bollettino Tecnico No. 119– 

39, Revision A, dated May 23, 2011. 

(4) Modifying the pilot and copilot RVDT 

control box assemblies in accordance with 

paragraph (f)(3) of this AD constitutes 

terminating action for the requirements of 

this AD. 

(g) Alternative Methods of Compliance 

(AMOCs) 

(1) The Manager, Safety Management 

Group, FAA, may approve AMOCs for this 

AD. Send your proposal to: Robert Grant, 

Aviation Safety Engineer, Safety Management 

Group, FAA, 2601 Meacham Blvd., Fort 

Worth, Texas 76137; telephone (817) 222– 

5110; email robert.grant@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. 

(h) Additional Information 

The subject of this AD is addressed in 

European Aviation Safety Agency AD 2011– 

0095–E, dated May 24, 2011. 

(i) Subject 

Joint Aircraft Service Component (JASC) 

Code: 6700: Rotors Flight Control. 

(j) 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) Agusta Bollettino Tecnico No. 119–39 

Revision A, dated May 23, 2011. 

(ii) Reserved. 

(3) For Agusta service information 

identified in this AD, contact Agusta 

Westland, Customer Support & Services, Via 

Per Tornavento 15, 21019 Somma Lombardo 

(VA) Italy, ATTN: Giovanni Cecchelli; 

telephone 39–0331–711133; fax 39 0331 

711180; or at http:// 

www.agustawestland.com/technicalbullettins. 

(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 April 26, 

2013. 

Kim Smith, 

Directorate Manager, Rotorcraft Directorate, 

Aircraft Certification Service. 

[FR Doc. 2013–10903 Filed 5–15–13; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2012–1109; Directorate 

Identifier 2011–NM–172–AD; Amendment 

39–17455; AD 2013–10–02] 

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 

757–200 and –200PF series airplanes. 

That AD currently requires modifying 

the nacelle strut and wing structure, and 

repairing any damage found during the 

modification. This new AD specifies a 

maximum compliance time limit that 

overrides the optional threshold formula 

results. This AD was prompted by 

reports indicating that the actual 

operational loads applied to the nacelle 

are higher than the analytical loads that 


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28730 Federal Register / Vol. 78, No. 95 / Thursday, May 16, 2013 / Rules and Regulations 

were used during the initial design. 

Subsequent analysis and service history, 

which includes numerous reports of 

fatigue cracking on certain strut and 

wing structure, indicated that fatigue 

cracking can occur on the primary strut 

structure before an airplane reaches its 

design service objective. We are issuing 

this AD to prevent fatigue cracking in 

primary strut structure and consequent 

reduced structural integrity of the strut. 

DATES: This AD is effective June 20, 

2013. 

The Director of the Federal Register 

approved the incorporation by reference 

of certain publications listed in the AD 

as of June 20, 2013. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain other publication listed in 

this AD as of October 16, 2003 (68 FR 

53496, September 11, 2003). 

The Director of the Federal Register 

approved the incorporation by reference 

of certain other publications listed in 

this AD as of November 13, 2000 (65 FR 

59703, October 6, 2000). 

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; 

phone: 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: 

Nancy Marsh, Aerospace Engineer, 

Airframe Branch, ANM–120S, Seattle 

Aircraft Certification Office (ACO), 

FAA, 1601 Lind Avenue SW., Renton, 

WA 98057–3356; phone: 425–917–6440; 

fax: 425–917–6590; email: 

Nancy.Marsh@faa.gov. 

SUPPLEMENTARY INFORMATION: 

Discussion 

We issued a notice of proposed 

rulemaking (NPRM) to amend 14 CFR 

part 39 to supersede AD 2003–18–05, 

Amendment 39–13296 (68 FR 53496, 

September 11, 2003). That AD applies to 

the specified products. The NPRM 

published in the Federal Register on 

October 29, 2012 (77 FR 65506). That 

NPRM proposed to continue to require 

modifying the nacelle strut and wing 

structure, and repairing any damage 

found during the modification. That 

NPRM also proposed to specify a 

maximum compliance time limit that 

overrides the optional threshold formula 

results. 

Comments 

We gave the public the opportunity to 

participate in developing this AD. The 

following presents the comments 

received on the proposal (77 FR 65506, 

October 29, 2012) and the FAA’s 

response to each comment. 

Clarification Regarding the Installation 

of Winglets 

Aviation Partners Boeing (APB) stated 

that it has reviewed the NPRM (77 FR 

65506, October 29, 2012) and the 

‘‘Boeing Service Bulletin’’ and has 

determined that the installation of 

winglets per Supplemental Type 

Certificate (STC) ST01518SE (http:// 

rgl.faa.gov/ 

Regulatory_and_Guidance_Library/ 

rgstc.nsf/0/ 

48e13cdfbbc32cf4862576a4005d308b/ 

$FILE/ST01518SE.pdf) does not affect 

them. APB also stated that it will 

provide supporting data to the FAA 

upon request. 

We agree with the commenter’s 

statement that the installation of 

winglets as specified in STC ST01518SE 

(http://rgl.faa.gov/ 

Regulatory_and_Guidance_Library/ 

rgstc.nsf/0/ 

48e13cdfbbc32cf4862576a4005d308b/ 

$FILE/ST01518SE.pdf) does not affect 

accomplishment of the requirements of 

this AD, and an alternative method of 

compliance (AMOC) is not necessary for 

a ‘‘change in product’’ AMOC approval 

request. We have therefore added this 

provision in new paragraph (c)(2) of this 

AD. 

Statement of Compliance With NPRM 

(77 FR 65506, October 29, 2012) 

Nord Wind Airlines reported the 

status of compliance of its airplanes 

with the NPRM (77 FR 65506, October 

29, 2012). 

No request was submitted by Nord 

Wind Airlines. We have not changed 

this AD in regard to Nord Wind 

Airlines’ comment. 

Statement of Previous Compliance With 

NPRM (77 FR 65506, October 29, 2012) 

FedEx stated that it has previously 

performed the prescribed inspections 

and terminating actions on its airplanes 

and that no further actions are necessary 

for it to be in compliance with the 

NPRM (77 FR 65506, October 29, 2012). 

No request was submitted by FedEx. 

We have not changed this AD in regard 

to FedEx’s comment. 

Change Made to Restated Paragraph (h) 

of This AD 

We have revised the wording in 

paragraph (h) of this AD to clarify the 

applicable service information to be 

used after the effective date of this AD. 

Conclusion 

We reviewed the relevant data, 

considered the comments received, and 

determined that air safety and the 

public interest require adopting the 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 (77 FR 

65506, October 29, 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 65506, 

October 29, 2012). 

Costs of Compliance 

We estimate that this AD affects 278 

airplanes of U.S. registry. 

We estimate the following costs to 

comply with this AD: 


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Federal Register / Vol. 78, No. 95 / Thursday, May 16, 2013 / Rules and Regulations 28731 

ESTIMATED COSTS

Action Labor cost Parts cost Cost per 

product 

Cost on U.S. 

operators 

Modification [retained actions from AD 2003–18–05, 

Amendment 39–13296 (68 FR 53496, September 11, 

2003)].

800 work-hours × $85 per hour = 

$68,000.

$0 $68,000 $18,904,000 

The new requirements of this AD add 

no additional economic burden. 

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 

affected individuals. As a result, we 

have included all costs 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 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) 

2003–18–05, Amendment 39–13296 (68 

FR 53496, September 11, 2003), and 

adding the following new AD: 

2013–10–02 The Boeing Company: 

Amendment 39–17455; Docket No. 

FAA–2012–1109; Directorate Identifier 

2011–NM–172–AD. 

(a) Effective Date 

This AD is effective June 20, 2013. 

(b) Affected ADs 

This AD supersedes AD 2003–18–05, 

Amendment 39–13296 (68 FR 53496, 

September 11, 2003). 

(c) Applicability 

(1) This AD applies to The Boeing 

Company Model 757–200 and –200PF series 

airplanes, certificated in any category, line 

numbers 1 through 735 inclusive, powered 

by Pratt & Whitney engines. 

(2) Supplemental Type Certificate (STC) 

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

Regulatory_and_Guidance_Library/rgstc.nsf/ 

0/48e13cdfbbc32cf4862576a4005d308b/ 

$FILE/ST01518SE.pdf) does not affect the 

ability to accomplish the actions required by 

this AD. Therefore, for airplanes on which 

STC ST01518SE 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 provisions of 

paragraph (k) of this AD. 

(d) Subject 

Joint Aircraft System Component (JASC)/ 

Air Transport Association (ATA) of America 

Code 54, Nacelles/Pylons. 

(e) Unsafe Condition 

This AD was prompted by reports 

indicating that the actual operational loads 

applied to the nacelle are higher than the 

analytical loads that were used during the 

initial design. Subsequent analysis and 

service history, which includes numerous 

reports of fatigue cracking on certain strut 

and wing structure, indicated that fatigue 

cracking can occur on the primary strut 

structure before an airplane reaches its 

design service objective. We are issuing this 

AD to prevent fatigue cracking in primary 

strut structure and consequent reduced 

structural integrity of the strut. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Retained Modification With New Service 

Information and Reduced Compliance Time 

This paragraph restates the requirements of 

paragraph (a) of AD 2003–18–05, 

Amendment 39–13296 (68 FR 53496, 

September 11, 2003), with new service 

information and a reduced compliance time. 

Modify the nacelle strut and wing structure 

on both the left and right sides of the 

airplane, in accordance with Boeing Service 

Bulletin 757–54–0034, dated May 14, 1998; 

Boeing Service Bulletin 757–54–0034, 

Revision 1, dated October 11, 2001; or Boeing 

Service Bulletin 757–54–0034, Revision 2, 

dated May 7, 2009; at the later of the times 

specified in paragraph (g)(1) or (g)(2) of this 

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

Boeing Service Bulletin 757–54–0034, 

Revision 2, dated May 7, 2009, may be used 

to accomplish the actions required by this 

paragraph. 

(1) At the earlier of the times specified in 

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

(i) Prior to the accumulation of 37,500 total 

flight cycles. 

(ii) At the later of the times specified in 

paragraph (g)(1)(ii)(A) or (g)(1)(ii)(B) of this 

AD. 

(A) Within 20 years since the date of 

manufacture. 

(B) Within the compliance time calculated 

using the optional threshold formula 

described in Boeing Service Bulletin 757–54– 

0034, Revision 2, dated May 7, 2009, or 

within 8 years after the effective date of this 

AD, whichever occurs first. 

(2) Within 3,000 flight cycles after 

November 13, 2000 (the effective date of AD 

2000–20–09, Amendment 39–11920 (65 FR 

59703, October 6, 2000)). 

(h) Retained Concurrent Requirements With 

New Service Information 

This paragraph restates the requirements of 

paragraph (b) of AD 2003–18–05, 


erowe on DSK2VPTVN1PROD with RULES
28732 Federal Register / Vol. 78, No. 95 / Thursday, May 16, 2013 / Rules and Regulations 

Amendment 39–13296 (68 FR 53496, 

September 11, 2003), with new service 

information. Except as provided by 

paragraph (j) of this AD: Prior to or 

concurrently with the accomplishment of the 

modification of the nacelle strut and wing 

structure required by paragraph (g) of this 

AD, accomplish the actions specified in 

Boeing Service Bulletin 757–54–0027, 

Revision 1, dated October 27, 1994; and 

Boeing Service Bulletin 757–54–0036, dated 

May 14, 1998, or Boeing Service Bulletin 

757–54–0036, Revision 1, dated July 31, 

2006; as applicable; in accordance with those 

service bulletins. As of the effective date of 

this AD, use only Boeing Service Bulletin 

757–54–0027, Revision 1, dated October 27, 

1994; and Boeing Service Bulletin 757–54– 

0036, Revision 1, dated July 31, 2006; to 

accomplish the applicable requirements of 

this paragraph. 

(i) Retained Repair With New Service 

Information 

This paragraph restates the requirements of 

paragraph (c) of AD 2003–18–05, 

Amendment 39–13296 (68 FR 53496, 

September 11, 2003), with new service 

information. If any damage to airplane 

structure is found during the 

accomplishment of the modification required 

by paragraph (g) of this AD, and Boeing 

Service Bulletin 757–54–0034, dated May 14, 

1998; Boeing Service Bulletin 757–54–0034, 

Revision 1, dated October 11, 2001; or Boeing 

Service Bulletin 757–54–0034, Revision 2, 

dated May 7, 2009; specifies to contact 

Boeing for appropriate action: Before further 

flight, repair the damage using a method 

approved in accordance with the procedures 

specified in paragraph (k) of this AD. 

(j) Retained Modification With New Service 

Information 

This paragraph restates the requirements of 

paragraph (d) of AD 2003–18–05, 

Amendment 39–13296 (68 FR 53496, 

September 11, 2003), with new service 

information. Modify the nacelle strut 

(including replacing the upper link with a 

new, improved part, and modifying the wire 

support bracket attached to the upper link), 

in accordance with Boeing Service Bulletin 

757–54–0036, dated May 14, 1998; or Boeing 

Service Bulletin 757–54–0036, Revision 1, 

dated July 31, 2006; at the earlier of the times 

specified in paragraphs (j)(1) and (j)(2) of this 

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

only Boeing Service Bulletin 757–54–0036, 

Revision 1, dated July 31, 2006, to 

accomplish the requirements of this 

paragraph. 

(1) Prior to or concurrently with 

accomplishment of the modification of the 

nacelle strut and wing structure required by 

paragraph (g) of this AD. 

(2) Prior to the accumulation of 27,000 

total flight cycles (for Model 757–200 series 

airplanes) or 29,000 total flight cycles (for 

Model 757–200PF series airplanes), or within 

2 years after October 16, 2003 (the effective 

date of AD 2003–18–05, Amendment 39– 

13296 (68 FR 53496, September 11, 2003)), 

whichever is later. 

(k) Alternative Methods of Compliance 

(AMOCs) 

(1) The Manager, Seattle Certification 

Office (ACO), FAA, has the authority to 

approve AMOCs for this AD, if requested 

using the procedures found in 14 CFR 39.19. 

In accordance with 14 CFR 39.19, send your 

request to your principal inspector or local 

Flight Standards District Office, as 

appropriate. If sending information directly 

to the manager of the ACO, send it to the 

attention of the person identified in the 

Related Information section of this AD. 

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

(2) Before using any approved AMOC, 

notify your appropriate principal inspector, 

or lacking a principal inspector, the manager 

of the local flight standards district office/ 

certificate holding district office. 

(3) An AMOC that provides an acceptable 

level of safety may be used for any repair 

required by this AD if it is approved by the 

Boeing Commercial Airplanes Organization 

Designation Authorization (ODA) that has 

been authorized by the Manager, Seattle 

ACO, to make those findings. For a repair 

method to be approved, the repair must meet 

the certification basis of the airplane and the 

approval must specifically refer to this AD. 

(4) AMOCs approved previously in 

accordance with AD 2003–18–05, 

Amendment 39–13296 (68 FR 53496, 

September 11, 2003), are approved as 

AMOCs for the corresponding provisions of 

this AD, except for AMOCs that approved a 

revised compliance time. 

(l) Related Information 

For more information about this AD, 

contact Nancy Marsh, Aerospace Engineer, 

Airframe Branch, ANM–120S, Seattle 

Aircraft Certification Office, FAA, 1601 Lind 

Avenue SW., Renton, WA 98057–3356; 

phone: 425–917–6440; fax: 425–917–6590; 

email: Nancy.Marsh@faa.gov. 

(m) 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 June 20, 2013. 

(i) Boeing Service Bulletin 757–54–0034, 

Revision 2, dated May 7, 2009. 

(ii) Boeing Service Bulletin 757–54–0036, 

Revision 1, dated July 31, 2006. 

(4) The following service information was 

approved for IBR on October 16, 2003 (68 FR 

53496, September 11, 2003). 

(i) Boeing Service Bulletin 757–54–0034, 

Revision 1, dated October 11, 2001. 

(ii) Reserved. 

(5) The following service information was 

approved for IBR on November 13, 2000 (65 

FR 59703, October 6, 2000). 

(i) Boeing Service Bulletin 757–54–0027, 

Revision 1, dated October 27, 1994. 

(ii) Boeing Service Bulletin 757–54–0034, 

dated May 14, 1998. 

(iii) Boeing Service Bulletin 757–54–0036, 

dated May 14, 1998. 

(6) For Boeing 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; phone: 

206–544–5000, extension 1; fax: 206–766– 

5680; Internet: https:// 

www.myboeingfleet.com. 

(7) 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. 

(8) 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 6, 

2013. 

Ali Bahrami, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 2013–11387 Filed 5–15–13; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF ENERGY 

Federal Energy Regulatory 

Commission 

18 CFR Part 35 

[Docket No. RM12–3–000] 

Revisions to Electric Quarterly Report 

Filing Process; Availability of Draft 

XML Schema 

AGENCY: Federal Energy Regulatory 

Commission, DOE. 

ACTION: Notification of availability. 

SUMMARY: The Federal Energy 

Regulatory Commission is making 

available on its Web site (http:// 

www.ferc.gov), Extensible Mark-Up 

Language (XML) needed to make 

Electric Quarterly Report (EQR) filings 

with one of the new filing processes 

adopted in Order No. 770, in the 

Commission’s Final Rule, 77 FR 71288 

(November 30, 2012). Please refer to the 

SUPPLEMENTARY INFORMATION Section 

below for details. 

DATES: The XML is now available at the 

links mentioned below. 

FOR FURTHER INFORMATION CONTACT: 

Christina Switzer, Office of the General 

Counsel, Federal Energy Regulatory 

Commission, 888 First St. NE., 

Washington, DC 20426, (202) 502–6379. 

SUPPLEMENTARY INFORMATION: Take 

notice that the Federal Energy 

Regulatory Commission (Commission) is 

making available on its Web site the 


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