21236 Federal Register / Vol. 78, No. 69 / Wednesday, April 10, 2013 / Rules and Regulations 

Issued in Fort Worth, Texas, on January 22, 

2013. 

Kim Smith, 

Directorate Manager, Rotorcraft Directorate, 

Aircraft Certification Service. 

[FR Doc. 2013–07932 Filed 4–9–13; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2012–0809; Directorate 

Identifier 2011–NM–135–AD; Amendment 

39–17361; AD 2013–04–04] 

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 

airplanes equipped with Rolls-Royce 

RB211–535E engines. That AD currently 

requires repetitive inspections for signs 

of damage of the aft hinge fittings and 

attachment bolts of the thrust reversers, 

and related investigative and corrective 

actions if necessary. The existing AD 

also provides for an optional 

terminating modification for the 

repetitive inspections. For certain 

airplanes, this new AD adds a one-time 

inspection of the washers installed 

under the attachment bolts of the aft 

hinge fittings for correct installation 

sequence, and reinstallation if 

necessary. This new AD also adds an 

option for installing a redesigned aft 

hinge fitting with the trim already done, 

instead of trimming an existing or new 

hinge fitting, which is included in the 

existing optional terminating 

modification. This AD was prompted by 

reports of incorrectly installed washers 

under the attachment bolts of the aft 

hinge fittings of the thrust reversers. We 

are issuing this AD to prevent failure of 

the attachment bolts and consequent 

separation of a thrust reverser from the 

airplane during flight, which could 

result in structural damage to the 

airplane. 

DATES: This AD is effective May 15, 

2013. 

The Director of the Federal Register 

approved the incorporation by reference 

of certain publications listed in the AD 

as of May 15, 2013. 

The Director of the Federal Register 

approved the incorporation by reference 

of certain other publications listed in 

this AD as of August 6, 2008 (73 FR 

37786, July 2, 2008). 

ADDRESSES: For service information 

identified in this AD, contact Boeing 

Commercial Airplanes, Attention: Data 

& Services Management, P. O. Box 3707, 

MC 2H–65, Seattle, Washington 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, 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: 

Nancy Marsh, Aerospace Engineer, 

Airframe Branch, ANM–120S, FAA, 

Seattle Aircraft Certification Office, 

1601 Lind Avenue SW., Renton, 

Washington 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 2008–13–20, 

Amendment 39–15583 (73 FR 37786, 

July 2, 2008). That AD applies to the 

specified products. The NPRM 

published in the Federal Register 

August 16, 2012 (77 FR 49396). That 

NPRM proposed to continue to require 

repetitive inspections for signs of 

damage of the aft hinge fittings and 

attachment bolts of the thrust reversers, 

and related investigative and corrective 

actions if necessary. That NPRM also 

proposed to continue to provide for an 

optional terminating modification for 

the repetitive inspections. For certain 

airplanes, that NPRM proposed to add a 

one-time inspection of the washers 

installed under the attachment bolts of 

the aft hinge fittings for correct 

installation sequence, and reinstallation 

if necessary. That NPRM also proposed 

to add an option for installing a 

redesigned aft hinge fitting with the trim 

already done, instead of trimming an 

existing or new hinge fitting, which is 

included in the existing optional 

terminating modification. 

Comments 

We gave the public the opportunity to 

participate in developing this AD. The 

following presents the comments 

received on the proposal (77 FR 49396, 

August 16, 2012) and the FAA’s 

response to each comment. 

Support for the NPRM (77 FR 49396, 

August 16, 2012) 

Boeing concurred with the content of 

the NPRM (77 FR 49396, August 16, 

2012). 

FedEx Express stated that it is 

accomplishing the actions specified in 

the NPRM (77 FR 49396, August 16, 

2012), and determined that its regular 

maintenance check schedule is not 

adversely affected by the specified 

actions. 

Request To Address Effects of NPRM 

(77 FR 49396, August 16, 2012) on 

Winglets 

Aviation Partners Boeing (APB) stated 

that it has reviewed the NPRM (77 FR 

49396, August 16, 2012), and Boeing 

Special Attention Service Bulletin 757– 

54–0049, Revision 1, dated September 

23, 2009, and Revision 2, dated July 27, 

2011; and Boeing Special Attention 

Service Bulletin 757–54–0050, Revision 

1, dated October 7, 2009, and Revision 

2, dated July 27, 2011; and has 

determined that the installation of 

winglets, per Supplemental Type 

Certificate (STC) ST01518SE, ‘‘does not 

affect them.’’ 

We infer that APB means the 

installation of these winglets does not 

affect accomplishing the NPRM (77 FR 

49396, August 16, 2012). We agree with 

the commenter and have determined 

that this AD should clarify the 

procedures to address these APB 

winglets. We have added a new 

paragraph (c)(2) to this AD to state that 

the installation of STC ST01518SE 

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

_Guidance_Library/rgstc.nsf/0/48E13

CDFBBC32CF4862576A4005

D308B?OpenDocument&High

light=st01518se) does not affect the 

ability to accomplish the actions 

required by this AD. 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 section 39.17 of the 

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Federal Register / Vol. 78, No. 69 / Wednesday, April 10, 2013 / Rules and Regulations 21237 

Federal Aviation Regulations (14 CFR 

39.17). For all other AMOC requests, the 

operator must request approval 

according to paragraph (n) of this AD. 

Request To Withdraw the NPRM (77 FR 

49396, August 16, 2012) 

American Airlines (AAL) stated that 

the existing FAA AD 2008–13–20, 

Amendment 39–15583 (73 FR 37786, 

July 2, 2008), is sufficient to correct the 

unsafe condition identified in the 

NPRM (77 FR 49396, August 16, 2012). 

AAL noted that if an operator deviated 

from the fastener stack-up in Figures 11 

and 12 of Boeing Special Attention 

Service Bulletin 757–54–0049, dated 

July 16, 2007, it should be dealt with on 

a case-by-case basis, and not by issuing 

an industry-wide requirement. 

Although AAL did not make a 

specific request, we infer that it wants 

the NPRM (77 FR 49396, August 16, 

2012) withdrawn. We agree that 

operators with airplanes on which the 

subject modification has been done 

must accomplish a one-time inspection 

and corrective action because the 

washers may have been installed 

backwards. However, we do not agree 

that improper installation of the 

washers using the procedures in Boeing 

Special Attention Service Bulletin 757– 

54–0049, dated July 16, 2007, should be 

dealt with on a case-by-case basis. 

Improper installation would recreate 

the unsafe condition, which must be 

addressed by doing the actions required 

by this AD. In addition, although the 

correct part number for the incorrect 

washer name of ‘‘plain washer’’ is 

identified in Boeing Special Attention 

Service Bulletin 757–54–0049, dated 

July 16, 2007, information for 

substituting other ‘‘plain washers’’ is 

also provided by referring to the 

additional guidance specified in the 

Boeing 757 Structural Repair Manual. 

Therefore, we are issuing this AD 

without further delay, in order to 

eliminate the identified unsafe 

condition of incorrectly installed 

washers under the attachment bolts of 

the aft hinge fittings of the thrust 

reversers. 

Request To Accomplish Certain Steps 

in the Service Information Out of 

Sequence 

AAL asked that it be allowed to 

accomplish certain steps in the 

referenced service information out of 

sequence. AAL stated that Boeing 

Special Attention Service Bulletin 757– 

54–0049, Revision 2, dated July 27, 

2011, removed Note 1 from the Work 

Instructions, and Note 1 allowed 

operators to change the sequence of 

steps for the specified procedures. AAL 

noted that if it is not allowed to 

accomplish certain steps out of 

sequence, it will be prevented from 

accomplishing the actions in that 

service bulletin in a timely manner. 

AAL added that the inspection and 

modification instructions are 

straightforward and are fundamental 

maintenance procedures. 

We agree that certain steps in the 

Work Instructions of Boeing Special 

Attention Service Bulletin 757–54– 

0049, Revision 2, dated July 27, 2011, 

could be accomplished out of sequence; 

however, certain other steps cannot. We 

suggest that AAL provide supporting 

data to Boeing to substantiate that the 

service information can be revised to 

permit accomplishing those steps out of 

sequence when appropriate. AAL may 

also submit a request for approval of an 

alternative method of compliance 

(AMOC), as specified in paragraph (n) of 

this AD, to use for accomplishing those 

steps out of sequence. We have not 

changed the AD in this regard. 

Request To Revise Certain Instructions 

in the NPRM (77 FR 49396, August 16, 

2012) 

AAL asked that only the work steps 

critical to correcting the unsafe 

condition be mandated by the AD. AAL 

stated that ‘‘open and close’’ are part of 

typical maintenance that is fundamental 

to a qualified maintenance facility; 

therefore, the instructions on how an 

operator gets to the steps should not be 

mandated but left to the operator’s 

discretion as the best method to use to 

address the existing unsafe condition. 

We agree that certain steps in the 

Work Instructions of Boeing Special 

Attention Service Bulletin 757–54– 

0049, Revision 2, dated July 27, 2011, 

may not need to be mandated; however, 

AAL did not provide supporting data of 

which steps in particular. We infer that 

AAL is asking to exclude the 

instructions mandated for access and 

close. Therefore, we have changed 

paragraph (g) of this AD to specify 

accomplishing Part II of the service 

information. We have also changed 

paragraph (l) of this AD to specify 

accomplishing Part IV of the service 

information for the inspection, and Part 

III of the service information for the 

preventive modification. These changes 

exclude Parts I and V of the service 

information which contain the 

instructions for access and close. 

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 change described previously. 

We also determined that this change 

will not increase the economic burden 

on any operator or increase the scope of 

the AD. 

Costs of Compliance 

We estimate that this AD affects 389 

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 

Retained inspections in AD 2008-13-20, 

Amendment 39-15583 (73 FR 37786, 

July 2, 2008).

2 work-hours × $85 per 

hour = $170 per inspection cycle.

$0 $170 per inspection cycle $66,130 per inspection 

cycle. 

Retained optional modification in AD 

2008-13-20, Amendment 39-15583 

(73 FR 37786, July 2, 2008), and new 

optional actions.

61 work-hours × $85 per 

hour = $5,185.

$5,276 $10,461 ............................. Up to $4,069,329. 

New inspection ....................................... 6 work-hours × $85 per 

hour = $510.

$0 $510 .................................. Up to $198,390. 

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21238 Federal Register / Vol. 78, No. 69 / Wednesday, April 10, 2013 / Rules and Regulations 

We have received no definitive data 

that would enable us to provide cost 

estimates for the on-condition actions 

specified in this AD. 

Authority for This Rulemaking 

Title 49 of the United States Code 

specifies the FAA’s authority to issue 

rules on aviation safety. Subtitle I, 

Section 106, describes the authority of 

the FAA Administrator. Subtitle VII, 

Aviation Programs, describes in more 

detail the scope of the Agency’s 

authority. 

We are issuing this rulemaking under 

the authority described in Subtitle VII, 

Part A, Subpart III, Section 44701, 

‘‘General requirements.’’ Under that 

section, Congress charges the FAA with 

promoting safe flight of civil aircraft in 

air commerce by prescribing regulations 

for practices, methods, and procedures 

the Administrator finds necessary for 

safety in air commerce. This regulation 

is within the scope of that authority 

because it addresses an unsafe condition 

that is likely to exist or develop on 

products identified in this rulemaking 

action. 

Regulatory Findings 

We 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) 

2008–13–20, Amendment 39–15583 (73 

FR 37786, July 2, 2008), and adding the 

following new AD: 

2013–04–04 The Boeing Company: 

Amendment 39–17361; Docket No. 

FAA–2012–0809; Directorate Identifier 

2011–NM–135–AD. 

(a) Effective Date 

This AD is effective May 15, 2013. 

(b) Affected ADs 

This AD supersedes AD 2008–13–20, 

Amendment 39–15583 (73 FR 37786, July 2, 

2008). 

(c) Applicability 

(1) This AD applies to The Boeing 

Company Model 757–200, –200CB, –200PF, 

and –300 series airplanes; certificated in any 

category; equipped with Rolls-Royce RB211– 

535E engines. 

(2) Installation of Supplemental Type 

Certificate (STC) ST01518SE (http:// 

rgl.faa.gov/Regulatory_and_Guidance_

Library/rgstc.nsf/0/ 

48E13CDFBBC32CF4862576A4005D308B?

OpenDocument&Highlight=st01518se) does 

not affect the ability to accomplish the 

actions required by this AD. 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. 

(d) Subject 

Joint Aircraft System Component (JASC)/ 

Air Transport Association (ATA) of America 

Code 54, Nacelles/Pylons. 

(e) Unsafe Condition 

This AD results from reports of incorrectly 

installed washers under the attachment bolts 

of the aft hinge fittings of the thrust reversers. 

We are issuing this AD to prevent failure of 

the attachment bolts and consequent 

separation of a thrust reverser from the 

airplane during flight, which could result in 

structural damage to the airplane. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Retained Repetitive Inspections/ 

Investigative and Corrective Actions 

This paragraph restates the requirements of 

paragraph (f) of AD 2008–13–20, Amendment 

39–15583 (73 FR 37786, July 2, 2008), with 

revised service information. At the time 

specified in paragraph 1.E. ‘‘Compliance,’’ of 

Boeing Special Attention Service Bulletin 

757–54–0049 or 757–54–0050, both dated 

July 16, 2007, as applicable; except as 

provided by paragraph (h) of this AD: Do a 

detailed inspection for signs of damage of the 

aft hinge fittings and attachment bolts of the 

thrust reversers by doing all the actions, 

including all applicable related investigative 

and corrective actions, as specified in Part II 

of the Accomplishment Instructions of the 

applicable service bulletin specified in 

paragraph (g)(1), (g)(2), or (g)(3); or paragraph 

(g)(4), (g)(5), or (g)(6) of this AD; as 

applicable. Do all applicable related 

investigative and corrective actions at the 

time specified in paragraph 1.E., 

‘‘Compliance,’’ of the applicable service 

bulletin identified in paragraph (g)(1) or 

(g)(4) of this AD. As of the effective date of 

this AD, only the service bulletin specified in 

paragraph (g)(3) or (g)(6) of this AD, as 

applicable, may be used to accomplish the 

actions required by this paragraph. If any 

damage is found and the service bulletin 

identified in paragraph (g)(1), (g)(2), (g)(3), 

(g)(4), (g)(5), or (g)(6) of this AD specifies to 

contact Boeing for appropriate action: Before 

further flight, repair using a method 

approved in accordance with the procedures 

specified in paragraph (n) of this AD. 

(1) Boeing Special Attention Service 

Bulletin 757–54–0049, dated July 16, 2007. 

(2) Boeing Special Attention Service 

Bulletin 757–54–0049, Revision 1, dated 

September 23, 2009. 

(3) Boeing Special Attention Service 

Bulletin 757–54–0049, Revision 2, dated July 

27, 2011. 

(4) Boeing Service Bulletin 757–54–0050, 

dated July 16, 2007. 

(5) Boeing Special Attention Service 

Bulletin 757–54–0050, Revision 1, dated 

October 7, 2009. 

(6) Boeing Special Attention Service 

Bulletin 757–54–0050, Revision 2, dated July 

27, 2011. 

(h) Retained Exception to Service 

Information 

This paragraph restates the requirements of 

paragraph (g) of AD 2008–13–20, 

Amendment 39–15583 (73 FR 37786, July 2, 

2008). Where Boeing Special Attention 

Service Bulletin 757–54–0049 or Boeing 

Service Bulletin 757–54–0050, both dated 

July 16, 2007; as applicable; specifies 

compliance times relative to the date on the 

service bulletin, this AD requires compliance 

within the specified compliance time after 

August 6, 2008 (the effective date of AD 

2008–13–20). 

(i) Retained Optional Terminating 

Modification 

This paragraph restates the actions 

specified in paragraph (h) of AD 2008–13–20, 

Amendment 39–15583 (73 FR 37786, July 2, 

2008). Accomplishing the preventive 

modification identified in the service bulletin 

specified in paragraph (g)(1), (g)(2), or (g)(3); 

or paragraph (g)(4), (g)(5), or (g)(6) of this AD; 

as applicable; terminates the repetitive 

inspections required by paragraph (g) of this 

AD. 

(j) Retained Concurrent Actions 

This paragraph restates the requirements of 

paragraph (i) of AD 2008–13–20, Amendment 

39–15583 (73 FR 37786, July 2, 2008). Prior 

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Federal Register / Vol. 78, No. 69 / Wednesday, April 10, 2013 / Rules and Regulations 21239 

to or concurrently with accomplishing the 

actions identified in the service bulletin 

specified in paragraph (g)(1), (g)(2), or (g)(3) 

of this AD, as applicable, accomplish the 

replacement specified in Boeing Special 

Attention Service Bulletin 757–54–0015, 

Revision 3, dated September 19, 1996. 

(k) Retained Credit for Previous Actions 

This paragraph restates the provisions of 

paragraph (j) of AD 2008–13–20, Amendment 

39–15583 (73 FR 37786, July 2, 2008). This 

paragraph provides credit for the actions 

required by paragraph (j) of this AD, if those 

actions were performed before August 6, 

2008 (the effective date AD 2008–13–20), 

using Boeing Service Bulletin 757–54–0015, 

dated February 16, 1989; Revision 1, dated 

December 20, 1990; or Revision 2, dated 

April 21, 1994 (which are not incorporated 

by reference in this AD). 

(l) New Requirements of This AD: Inspection 

of Washer Stack up Sequence/Corrective 

Action 

For Group 1, Configuration 2 airplanes 

identified in Boeing Special Attention 

Service Bulletins 757–54–0049 and 757–54– 

0050, Revision 2, both dated July 27, 2011: 

Within 3,000 flight cycles after the effective 

date of this AD, do a detailed inspection of 

the washers installed under the attachment 

bolts of the aft hinge fittings for correct 

installation sequence, in accordance with 

Part IV of the Accomplishment Instructions 

of Boeing Special Attention Service Bulletin 

757–54–0049 or 757–54–0050, both Revision 

2, both dated July 27, 2011, as applicable. If 

an incorrect installation sequence is found, 

before further flight, remove and reinstall the 

washer stack up correctly, in accordance 

with Part III of the Accomplishment 

Instructions of Boeing Special Attention 

Service Bulletin 757–54–0049 or 757–54– 

0050, Revision 2, both dated July 27, 2011, 

as applicable. 

(m) Credit for Previous Actions 

This paragraph provides credit for the 

actions required by paragraph (l) of this AD, 

if those actions were performed before the 

effective date of this AD using Boeing Special 

Attention Service Bulletin 757–54–0049, 

Revision 1, dated September 23, 2009; or 

Boeing Special Attention Service Bulletin 

757–54–0050, Revision 1, dated October 7, 

2009; as applicable. 

(n) 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–ANM– 

Seattle–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 2008–13–20, 

Amendment 39–15583 (73 FR 37786, July 2, 

2008), are approved as AMOCs for the 

corresponding provisions of this AD. 

(o) Related Information 

For more information about this AD, 

contact Nancy Marsh, Aerospace Engineer, 

Airframe Branch, ANM–120S, FAA, Seattle 

Aircraft Certification Office, 1601 Lind 

Avenue SW., Renton, Washington 98057– 

3356; phone: 425–917–6440; fax: 425–917– 

6590; email: nancy.marsh@faa.gov. 

(p) 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 on May 15, 2013. 

(i) Boeing Special Attention Service 

Bulletin 757–54–0049, Revision 2, dated July 

27, 2011. 

(ii) Boeing Special Attention Service 

Bulletin 757–54–0049, Revision 1, dated 

September 23, 2009. 

(iii) Boeing Special Attention Service 

Bulletin 757–54–0050, Revision 2, dated July 

27, 2011. 

(iv) Boeing Special Attention Service 

Bulletin 757–54–0050, Revision 1, dated 

October 7, 2009. 

(4) The following service information was 

approved for IBR on August 6, 2008 (73 FR 

37786, July 2, 2008). 

(i) Boeing Service Bulletin 757–54–0050, 

dated July 16, 2007. 

(ii) Boeing Special Attention Service 

Bulletin 757–54–0015, Revision 3, dated 

September 19, 1996. 

(iii) Boeing Special Attention Service 

Bulletin 757–54–0049, dated July 16, 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, Washington 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, Washington. 

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 February 

8, 2013. 

Ali Bahrami, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 2013–03903 Filed 4–9–13; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 97 

[Docket No. 30893; Amdt. No. 3528] 

Standard Instrument Approach 

Procedures, and Takeoff Minimums 

and Obstacle Departure Procedures; 

Miscellaneous Amendments 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule. 

SUMMARY: This rule establishes, amends, 

suspends, or revokes Standard 

Instrument Approach Procedures 

(SIAPs) and associated Takeoff 

Minimums and Obstacle Departure 

Procedures for operations at certain 

airports. These regulatory actions are 

needed because of the adoption of new 

or revised criteria, or because of changes 

occurring in the National Airspace 

System, such as the commissioning of 

new navigational facilities, adding new 

obstacles, or changing air traffic 

requirements. These changes are 

designed to provide safe and efficient 

use of the navigable airspace and to 

promote safe flight operations under 

instrument flight rules at the affected 

airports. 

DATES: This rule is effective April 10, 

2013. The compliance date for each 

SIAP, associated Takeoff Minimums, 

and ODP is specified in the amendatory 

provisions. 

The incorporation by reference of 

certain publications listed in the 

regulations is approved by the Director 

of the Federal Register as of April 10, 

2013. 

ADDRESSES: Availability of matters 

incorporated by reference in the 

amendment is as follows: 

For Examination— 

1. FAA Rules Docket, FAA 

Headquarters Building, 800 

Independence Avenue SW., 

Washington, DC 20591; 

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