Federal Register / Vol. 78, No. 192 / Thursday, October 3, 2013 / Rules and Regulations 61173 

We prepared a regulatory 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): 

200X–19–17 Rolls-Royce plc Amendment 

39–17599; Docket No. FAA–2013–0029; 

Directorate Identifier 2013–NE–01–AD. 

(a) Effective Date 

This AD becomes effective November 7, 

2013. 

(b) Affected ADs 

None. 

(c) Applicability 

This AD applies to all Rolls-Royce plc (RR) 

RB211–535E4–B–37 series turbofan engines. 

(d) Unsafe Condition 

This AD was prompted by recalculating the 

lives of certain rotating life limited parts 

(LLPs) operated to certain flight profiles. We 

are issuing this AD to prevent the failure of 

rotating LLPs, which could result in 

uncontained failure of the engine and 

damage to the airplane. 

(e) Actions and Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(1) Within 30 days after the effective date 

of this AD, for engines that have operated to 

Flight Profile D or E, recalculate the life of 

the low-pressure (LP) turbine disc stage 2, 

intermediate-pressure (IP) compressor rotor 

shaft (stage 1 to 6), high-pressure (HP) 

compressor rear rotor shaft assembly, and HP 

turbine disc installed on that engine. Use the 

part lives, prorated life formulas, and flight 

profiles in Appendices 2, 4, and 5 of RR Alert 

Non-Modification Service Bulletin (NMSB) 

No. RB.211–72–AG875, dated December 13, 

2012, to make that calculation. 

(2) Within 30 days after the effective date 

of this AD, for engines that will operate to 

Flight Profile D or E, assign the maximum 

approved lives defined in Appendix 2 of RR 

Alert NMSB No. RB.211–72–AG875, dated 

December 13, 2012, to the LP turbine disc 

stage 2, IP compressor rotor shaft (stage 1 to 

6), HP compressor rear rotor shaft assembly, 

and HP turbine disc based on the flight 

profile that will be flown. 

(3) For engines that have only operated to, 

and will continue to operate to, Flight Profile 

C, as defined in Appendix 5 of RR Alert 

NMSB No. RB.211–72–AG875, dated 

December 13, 2012, no further action is 

required by this AD. 

(4) After the effective date of this AD, for 

engines that incorporate an LP turbine disc 

stage 2, IP compressor rotor shaft (stage 1 to 

6), HP compressor rear rotor shaft assembly, 

or HP turbine disc whose part life is defined 

by paragraph (e)(1) of this AD, that have an 

engine shop visit (ESV) before reaching the 

part life assigned in paragraph (e)(2) of this 

AD, remove each part from service before the 

part exceeds the part life assigned in 

paragraph (e)(2). 

(5) For those engines that incorporate an 

LP turbine disc stage 2, IP compressor rotor 

shaft (stage 1 to 6), HP compressor rear rotor 

shaft assembly, or HP turbine disc whose part 

life is defined by paragraph (e)(1) of this AD, 

that do not have an ESV after the effective 

date of this AD before the part exceeds the 

part life assigned in paragraph (e)(2) of this 

AD, remove the part from service at the next 

ESV. 

(f) Installation Prohibition 

Any LP turbine disc stage 2, IP compressor 

rotor shaft (stage 1 to 6), HP compressor rear 

rotor shaft assembly, or HP turbine disc 

whose part life is defined by paragraph (e)(1) 

of this AD that is re-installed in any engine 

after the effective date of this AD must be 

removed from service before the part exceeds 

the part life assigned in paragraph (e)(2) of 

this AD. 

(g) Definition 

For the purpose of this AD, ESV is 

whenever engine maintenance performed 

prior to reinstallation requires the separation 

of a pair of major mating engine module 

flanges. Separation of flanges solely for the 

purpose of shipment without subsequent 

internal maintenance is not an ESV. 

Separation of the external gearbox engine 

mating flanges or removal of the external 

gearbox is also not classified as a shop visit. 

(h) Alternative Methods of Compliance 

(AMOCs) 

The Manager, Engine Certification Office, 

may approve AMOCs for this AD. Use the 

procedures found in 14 CFR 39.19 to make 

your request. 

(i) Related Information 

(1) For more information about this AD, 

contact Robert Green, Aerospace Engineer, 

Engine Certification Office, FAA, Engine & 

Propeller Directorate, 12 New England 

Executive Park, Burlington, MA 01803; 

phone: 781–238–7754; fax: 781–238–7199; 

email: robert.green@faa.gov. 

(2) Refer to European Aviation Safety 

Agency AD 2012–0265, dated December 18, 

2012, for related information. You may 

examine the AD on the Internet at http://

www.regulations.gov/

#!documentDetail;D=FAA-2013-0029-0007. 

(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) Rolls-Royce plc Alert Non-Modification 

Service Bulletin No. RB.211–72–AG875, 

dated December 13, 2012. 

(ii) Reserved. 

(3) For Rolls-Royce plc service information 

identified in this AD, contact Rolls-Royce 

plc, Corporate Communications, P.O. Box 31, 

Derby, England, DE248BJ; phone: 011–44– 

1332–242424; fax: 011–44–1332–249936; 

email: http://www.rolls-royce.com/contact/

civil_team.jsp; or download from https://

www.aeromanager.com. 

(4) You may view this service information 

at FAA, Engine & Propeller Directorate, 12 

New England Executive Park, Burlington, 

MA. For information on the availability of 

this material at the FAA, call 781–238–7125. 

(5) You may view this service information 

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 Burlington, Massachusetts, on 

September 16, 2013. 

Carlos A. Pestana, 

Acting Directorate Assistant Manager, Engine 

& Propeller Directorate, Aircraft Certification 

Service. 

[FR Doc. 2013–23452 Filed 10–2–13; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2012–0998; Directorate 

Identifier 2011–NM–249–AD; Amendment 

39–17605; AD 2013–19–23] 

RIN 2120–AA64 

Airworthiness Directives; The Boeing 

Company Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule. 

SUMMARY: We are adopting a new 

airworthiness directive (AD) for certain 

The Boeing Company Model 737–600, 

–700, –700C, –800, –900, and –900ER 

series airplanes. This AD was prompted 

by a new revision to the airworthiness 

limitations of the maintenance planning 

data (MPD) document. This AD requires 

revising the maintenance program to 

update inspection requirements to 

detect fatigue cracking of principal 


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61174 Federal Register / Vol. 78, No. 192 / Thursday, October 3, 2013 / Rules and Regulations 

structural elements (PSEs). We are 

issuing this AD to detect and correct 

fatigue cracking of various principal 

structural elements (PSEs), which could 

adversely affect the structural integrity 

of these airplanes. 

DATES: This AD is effective November 7, 

2013 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication listed in the AD 

as of November 7, 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, 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, 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. 

SUPPLEMENTARY INFORMATION: 

Discussion 

We issued a notice of proposed 

rulemaking (NPRM) to amend 14 CFR 

part 39 to include an AD that would 

apply to the specified products. The 

NPRM published in the Federal 

Register on September 24, 2012 (77 FR 

58791). The NPRM proposed to require 

revising the maintenance program to 

update inspection requirements to 

detect fatigue cracking of PSEs. 

Comments 

We gave the public the opportunity to 

participate in developing this AD. The 

following presents the comments 

received on the proposal (77 FR 58791, 

September 24, 2012) and the FAA’s 

response to each comment. 

Requests To Use the Most Recent MPD 

Document 

Boeing and American Airlines (AAL) 

requested that the most recent MPD 

document be incorporated into the 

NPRM (77 FR 58791, September 24, 

2012). 

Boeing stated that the NPRM (77 FR 

58791, September 24, 2012) should 

reference Subsection B, AWLs— 

Structural Inspections, of Section 9, 

‘‘Airworthiness Limitations (AWLs) and 

Certification Maintenance Requirements 

(CMRs),’’ of Boeing 737–600, –700, 

–700C, –800, –900, and –900ER MPD 

Document, D626A001–CMR, Revision 

December 2011. Boeing stated that this 

is the most recent MPD document and 

that this revision incorporates more 

stringent restrictions that should be 

included before the final rule is issued. 

AAL stated that the Relevant Service 

Information section and paragraph (g) of 

the NPRM (77 FR 58791, September 24, 

2012) refer to Subsection B, AWLs— 

Structural Inspections, of Section 9, 

‘‘Airworthiness Limitations (AWLs) and 

Certification Maintenance Requirements 

(CMRs),’’ of Boeing 737–600, –700, 

–700C, –800, –900, and –900ER MPD 

Document, D626A001–CMR, Revision 

July 2011. AAL stated that the most 

recent revision of that document is 

Revision August 2012, and that it 

should be incorporated into the NPRM. 

We agree with the commenters’ 

requests. The Relevant Service 

Information section of the NPRM (77 FR 

58791, September 24, 2012) is not 

restated in the final rule. However, we 

have added both Revision December 

2011 and Revision August 2012 of 

Subsection B, AWLs—Structural 

Inspections, of Section 9, 

‘‘Airworthiness Limitations (AWLs) and 

Certification Maintenance Requirements 

(CMRs),’’ of Boeing 737–600, –700, 

–700C, –800, –900, and –900ER MPD 

Document, D626A001–CMR to 

paragraph (g) of this AD as acceptable 

options for doing the actions required 

by this AD. We also re-organized 

paragraph (g) of this AD to improve 

readability. Because Revision August 

2012 of Subsection B, AWLs—Structural 

Inspections, of Section 9, 

‘‘Airworthiness Limitations (AWLs) and 

Certification Maintenance Requirements 

(CMRs),’’ of Boeing 737–600, –700, 

–700C, –800, –900, and –900ER MPD 

Document, D626A001–CMR is a more 

stringent document, we might consider 

future rulemaking to require the actions 

specified in that document. 

Request To Use Later Revisions of the 

Service Information 

All Nippon Airways (ANA) requested 

the use of a later-approved MPD 

document. ANA noted that the NPRM 

(77 FR 58791, September 24, 2012) 

refers to Subsection B, AWLs— 

Structural Inspections, of Section 9, 

‘‘Airworthiness Limitations (AWLs) and 

Certification Maintenance Requirements 

(CMRs),’’ of Boeing 737–600, –700, 

–700C, –800, –900, and –900ER MPD 

Document, D626A001–CMR, Revision 

July 2011, and that the current 

document is Revision December 2011. 

ANA stated that once the NPRM 

becomes a final rule, an alternative 

method of compliance (AMOC) will be 

necessary to do the actions in the latest 

document. ANA also stated that 

airworthiness limitations and CMR 

documents are revised periodically; if 

an AMOC is necessary for each revision 

of the document, it will burden the 

operators. ANA stated that if paragraph 

(g) of the NPRM addresses ‘‘D626A001– 

CMR revision July 2011, or later,’’ then 

an AMOC will not be necessary for each 

later revision of the document. ANA 

stated that, since the document is 

reviewed by the FAA prior to public 

release, the FAA is able to confirm if the 

document meets the adequate level of 

safety. 

We disagree with ANA’s request. We 

cannot use the phrase, ‘‘or later FAAapproved revisions,’’ in an AD when 

referring to the service document 

because doing so violates Office of the 

Federal Register (OFR) regulations for 

approval of materials ‘‘incorporated by 

reference’’ in rules. See 1 CFR 51.1(f). 

In general terms, we are required by 

OFR regulations to either publish the 

service document contents as part of the 

actual AD language; or submit the 

service document to the OFR for 

approval as ‘‘referenced’’ material, in 

which case we may only refer to such 

material in the text of an AD. The AD 

may refer to the service document only 

if the OFR approved it for 

‘‘incorporation by reference.’’ See 1 CFR 

part 51. 

To allow operators to use later 

revisions of the referenced document 

(issued after publication of the AD), 

either we must revise the AD to 

reference specific later revisions, or 

operators must request approval to use 

later revisions as an AMOC with this 

AD under the provisions of paragraph 

(j)(1) of this AD. As stated previously, 

we have added Revision December 2011 


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Federal Register / Vol. 78, No. 192 / Thursday, October 3, 2013 / Rules and Regulations 61175 

and Revision August 2012 of Subsection 

B, AWLs—Structural Inspections, of 

Section 9, ‘‘Airworthiness Limitations 

(AWLs) and Certification Maintenance 

Requirements (CMRs),’’ of Boeing 737– 

600, –700, –700C, –800, –900, and 

–900ER MPD Document, D626A001– 

CMR to paragraph (g) of this AD as 

acceptable options for doing the 

required actions. 

Requests for an AMOC Exception 

WestJet and AAL requested an AMOC 

exception. 

WestJet stated that in paragraph (c)(2) 

of the NPRM (77 FR 58791, September 

24, 2012) the wording ‘‘may not be able 

to’’ implies that if an inspection to a 

modified, altered, or repaired area can 

be accomplished, then an AMOC is not 

required. WestJet also stated that an 

AMOC should not be required for 

Boeing repairs that have damage 

tolerant assessments and for 

supplemental type certificates (STCs) 

that have FAA-approved airworthiness 

limitation structural inspections. 

AAL stated that paragraph (c)(2) of the 

NPRM (77 FR 58791, September 24, 

2012) provides minimal information on 

how operators should address new and 

existing repairs in a PSE area, as defined 

in Subsection B, AWLs—Structural 

Inspections, of Section 9, 

‘‘Airworthiness Limitations (AWLs) and 

Certification Maintenance Requirements 

(CMRs),’’ of Boeing 737–600, –700, 

–700C, –800, –900, and –900ER MPD 

Document, D626A001–CMR, Revision 

July 2011. AAL also stated that all 

repairs in a PSE area that hide a portion 

of the inspection area will need an 

alternate inspection method approved 

by the Seattle Aircraft Certification 

Office to ensure continued damage 

tolerance of the affected structure. AAL 

stated that the current process will 

create an unnecessary burden on 

operators. AAL said that repairs 

approved under section 25.571(b) or 

26.43(d) of the Federal Aviation 

Regulations (14 CFR 25.571(b) and 14 

CFR 26.43(d), respectively) would 

provide the required level of safety for 

the continued damage tolerance of the 

affected structure for the NPRM. 

We disagree with the commenters’ 

requests. The revised set of inspections 

in Subsection B, AWLs—Structural 

Inspections, of Section 9, 

‘‘Airworthiness Limitations (AWLs) and 

Certification Maintenance Requirements 

(CMRs),’’ of Boeing 737–600, –700, 

–700C, –800, –900, and –900ER MPD 

Document, D626A001–CMR, Revision 

July 2011, resulted from an updated 

analysis of The Boeing Company Model 

737–600, –700, –700C, –800, –900, and 

–900ER series airplanes. The analysis 

includes consideration of updated loads 

and flight lengths that increase the 

stresses on the structure. Previously 

approved repairs, modifications, and 

alterations may not include 

consideration of the updated analysis, 

and therefore, a review is required 

before an AMOC can be issued for them. 

Affected operators, however, may 

request approval of an AMOC under the 

provisions of paragraph (j)(1) of this AD 

by submitting data substantiating that 

the change would provide an acceptable 

level of safety. We have not changed 

this final rule in this regard. 

Request To Reference Different 

Advisory Circular (AC) 

AAL requested that the NPRM (77 FR 

58791, September 24, 2012) reference a 

different AC. AAL stated that paragraph 

(c)(2) of the NPRM provides FAA 

guidance for determining the changes 

necessary for the required inspections to 

satisfy the continued damage tolerance 

of the affected structure. AAL stated that 

the NPRM references FAA AC 25.1529– 

1A, dated November 20, 2007 (http://

www.faa.gov/documentLibrary/media/

Advisory_Circular/AC%2025.1529- 

1A.pdf), for guidance regarding 

alternative inspection procedures; 

however, AC 25.1529–1A, dated 

November 20, 2007, applies only to 

airplanes that have a passenger seating 

capacity of less than 30 and a maximum 

payload capacity of less than 7,500 

pounds. AAL stated that FAA AC 120– 

93, dated November 20, 2007 (http://

rgl.faa.gov/Regulatory_and_Guidance_

Library/rgAdvisoryCircular.nsf/0/

f73fd2a31b353a71862573b000521928/

$FILE/AC%20120-93.pdf), refers to the 

damage tolerance inspection for repairs 

and alteration. 

We agree with the commenter’s 

request. We have revised paragraph 

(c)(2) of this AD by specifying FAA AC 

120–93, dated November 20, 2007 

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

Guidance_Library/

rgAdvisoryCircular.nsf/0/

f73fd2a31b353a71862573b000521928/

$FILE/AC%20120-93.pdf), in lieu of 

FAA AC 25.1529–1A, dated November 

20, 2007 (http://www.faa.gov/

documentLibrary/media/Advisory_

Circular/AC%2025.1529-1A.pdf.) 

STC Comment 

Aviation Partners Boeing stated that 

the installation of winglets per STC 

ST00830SE (http://rgl.faa.gov/

Regulatory_and_Guidance_Library/

rgstc.nsf/0/

408e012e008616a7862578880060456c/

$FILE/ST00830SE.pdf) affects the 

accomplishment of the manufacturer’s 

service instructions. 

We have added paragraph (c)(3) of 

this AD to state that installation of STC 

ST00830SE (http://rgl.faa.gov/

Regulatory_and_Guidance_Library/

rgstc.nsf/0/

408e012e008616a7862578880060456c/

$FILE/ST00830SE.pdf) affects the ability 

to accomplish the actions required by 

this AD. Therefore, for airplanes on 

which STC ST00830SE is installed, a 

‘‘change in product’’ AMOC approval 

request might be necessary to comply 

with the requirements of 14 CFR 39.17. 

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 (77 FR 

58791, September 24, 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 58791, 

September 24, 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 1,200 

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 

Document Revision ............................................... 1 work-hour × $85 per hour = $85 ....................... $0 $85 $102,000 


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61176 Federal Register / Vol. 78, No. 192 / Thursday, October 3, 2013 / Rules and Regulations 

Paperwork Reduction Act 

A federal agency may not conduct or 

sponsor, and a person is not required to 

respond to, nor shall a person be subject 

to a penalty for failure to comply with 

a collection of information subject to the 

requirements of the Paperwork 

Reduction Act unless that collection of 

information displays a current valid 

OMB Control Number. The OMB 

Control Number for this information 

collection is 2120–0056. Public 

reporting for this collection of 

information is estimated to be 

approximately 5 minutes per response, 

including the time for reviewing 

instructions, completing and reviewing 

the collection of information. All 

responses to this collection of 

information are mandatory. Comments 

concerning the accuracy of this burden 

and suggestions for reducing the burden 

should be directed to the FAA at: 800 

Independence Ave. SW., Washington, 

DC 20591, Attn: Information Collection 

Clearance Officer, AES–200. 

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 

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 adding 

the following new airworthiness 

directive (AD): 

2013–19–23 The Boeing Company: 

Amendment 39–17605 ; Docket No. 

FAA–2012–0998; Directorate Identifier 

2011–NM–249–AD. 

(a) Effective Date 

This AD is effective November 7, 2013. 

(b) Affected ADs 

None. 

(c) Applicability 

(1) This AD applies to the Boeing Company 

Model 737–600, –700, –700C, –800, –900, 

and –900ER series airplanes, certificated in 

any category, with an original airworthiness 

certificate or original export certificate of 

airworthiness issued before April 3, 2012. 

(2) This AD requires revisions to certain 

operator maintenance documents to include 

new inspections. Compliance with these 

inspections is required by 14 CFR 91.403(c). 

For airplanes that have been previously 

modified, altered, or repaired in the areas 

addressed by these inspections, the operator 

may not be able to accomplish the 

inspections described in the revisions. In this 

situation, to comply with 14 CFR 91.403(c), 

the operator must request approval for an 

alternative method of compliance (AMOC) 

according to paragraph (j) of this AD. The 

request should include a description of 

changes to the required inspections that will 

ensure the continued damage tolerance of the 

affected structure. The FAA has provided 

guidance for this determination in FAA 

Advisory Circular (AC) 120–93, dated 

November 20, 2007 (http://rgl.faa.gov/

Regulatory_and_Guidance_Library/

rgAdvisoryCircular.nsf/0/

f73fd2a31b353a71862573b000521928/$FILE/

AC%20120-93.pdf). 

(3) Installation of Supplemental Type 

Certificate (STC) ST00830SE (http://

rgl.faa.gov/Regulatory_and_Guidance_

Library/rgstc.nsf/0/

408e012e008616a7862578880060456c/

$FILE/ST00830SE.pdf) affects the ability to 

accomplish the actions required by this AD. 

Therefore, for airplanes on which STC 

ST00830SE is installed, a ‘‘change in 

product’’ AMOC approval request might be 

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 52, Doors; 53, Fuselage; 54, Nacelles/

Pylons; 55, Stabilizers; and 57, Wings. 

(e) Unsafe Condition 

This AD was prompted by a new revision 

to the airworthiness limitations of the 

maintenance planning data (MPD) document. 

We are issuing this AD to detect and correct 

fatigue cracking of various principal 

structural elements (PSEs), which could 

adversely affect the structural integrity of 

these airplanes. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Maintenance Program Revision 

(1) Within 12 months after the effective 

date of this AD, revise the maintenance 

program by incorporating the information in 

paragraph (g)(1)(i), (g)(1)(ii), or (g)(1)(iii) of 

this AD, except as provided by paragraph (h) 

of this AD. 

(i) Subsection B, AWLs—Structural 

Inspections, of Section 9, ‘‘Airworthiness 

Limitations (AWLs) and Certification 

Maintenance Requirements (CMRs),’’ of 

Boeing 737–600, –700, –700C, –800, –900, 

and –900ER MPD Document, D626A001– 

CMR, Revision July 2011. 

(ii) Subsection B, AWLs—Structural 

Inspections, of Section 9, ‘‘Airworthiness 

Limitations (AWLs) and Certification 

Maintenance Requirements (CMRs),’’ of 

Boeing 737–600, –700, –700C, –800, –900, 

and –900ER MPD Document, D626A001– 

CMR, Revision December 2011. 

(iii) Subsection B, AWLs—Structural 

Inspections, of Section 9, ‘‘Airworthiness 

Limitations (AWLs) and Certification 

Maintenance Requirements (CMRs),’’ of 

Boeing 737–600, –700, –700C, –800, –900, 

and –900ER MPD Document, D626A001– 

CMR, Revision August 2012. 

(2) The initial compliance time for the 

inspections is within the applicable times 

specified in the documents identified in 

paragraphs (g)(1)(i), (g)(1)(ii), and (g)(1)(iii) of 

this AD, or within 18 months after the 

effective date of this AD, whichever occurs 

later; or within the applicable time specified 

in those documents from the time of 

installation of new parts. 

(3) Reports specified in the documents 

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

and (g)(1)(iii) of this AD may be submitted 

within 10 days after the airplane is returned 

to service, instead of 10 days after each 

individual finding as specified in Section 9 

of the documents identified in paragraphs 

(g)(1)(i), (g)(1)(ii), and (g)(1)(iii) of this AD. 


sroberts on DSK5SPTVN1PROD with RULES
Federal Register / Vol. 78, No. 192 / Thursday, October 3, 2013 / Rules and Regulations 61177 

(h) No Alternative Inspections and 

Inspection Intervals 

After accomplishing the actions required 

by paragraph (g) of this AD, no alternative 

actions (i.e., alternative inspections) or 

inspection intervals may be used or 

incorporated unless the alternative action or 

interval is approved as an AMOC in 

accordance with the procedures specified in 

paragraph (j) of this AD. 

(i) Paperwork Reduction Act Burden 

Statement 

A federal agency may not conduct or 

sponsor, and a person is not required to 

respond to, nor shall a person be subject to 

a penalty for failure to comply with a 

collection of information subject to the 

requirements of the Paperwork Reduction 

Act unless that collection of information 

displays a current valid OMB Control 

Number. The OMB Control Number for this 

information collection is 2120–0056. Public 

reporting for this collection of information is 

estimated to be approximately 5 minutes per 

response, including the time for reviewing 

instructions, completing and reviewing the 

collection of information. All responses to 

this collection of information are mandatory. 

Comments concerning the accuracy of this 

burden and suggestions for reducing the 

burden should be directed to the FAA at: 800 

Independence Ave. SW., Washington, DC 

20591, Attn: Information Collection 

Clearance Officer, AES–200. 

(j) Alternative Methods of Compliance 

(AMOCs) 

(1) The Manager, Seattle Aircraft 

Certification Office (ACO), ANM–120S, 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 (k) of this AD. Information may be 

emailed to: 9-ANM-Seattle-ACO-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 

required in the area affected 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. 

(k) 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. 

(l) 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) Section 9, ‘‘Airworthiness Limitations 

(AWLs) and Certification Maintenance 

Requirements (CMRs),’’ of Boeing 737–600, 

–700, –700C, –800, –900, and –900ER 

Maintenance Planning Data (MPD) 

Document, D626A001–CMR, Revision July 

2011. 

(ii) Section 9, ‘‘Airworthiness Limitations 

(AWLs) and Certification Maintenance 

Requirements (CMRs),’’ of Boeing 737–600, 

–700, –700C, –800, –900, and –900ER MPD 

Document, D626A001–CMR, Revision 

December 2011. 

(iii) Section 9, ‘‘Airworthiness Limitations 

(AWLs) and Certification Maintenance 

Requirements (CMRs),’’ of Boeing 737–600, 

–700, –700C, –800, –900, and –900ER MPD 

Document, D626A001–CMR, Revision 

August 2012. 

(3) For Boeing 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. 

(4) 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. 

(5) You may view this service information 

that is incorporated by reference at the 

National Archives and Records 

Administration (NARA). For information on 

the availability of this material at NARA, call 

202–741–6030, or go to: http://

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

Issued in Renton, Washington, on 

September 16, 2013. 

Ross Landes, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2013–23462 Filed 10–2–13; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2013–0833; Directorate 

Identifier 2012–NM–140–AD; Amendment 

39–17615; AD 2013–20–09] 

RIN 2120–AA64 

Airworthiness Directives; Bombardier, 

Inc. Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Final rule; request for 

comments. 

SUMMARY: We are adopting a new 

airworthiness directive (AD) for certain 

Bombardier, Inc. Model CL–215–6B11 

(CL–415 Variant) airplanes. This AD 

requires replacing the panel assembly of 

the main distribution center (MDC) rack. 

This AD was prompted by findings of 

chafed power wires due to flexing of the 

MDC rack panel. We are issuing this AD 

to prevent damage to power wires, 

which could cause simultaneous loss of 

systems such as electrical power, pilot 

indications, and caution/advisory 

lighting systems, which are essential for 

safe flight. 

DATES: This AD becomes effective 

October 18, 2013. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication listed in the AD 

as of October 18, 2013. 

We must receive comments on this 

AD by November 18, 2013. 

ADDRESSES: You may send comments by 

any of the following methods: 

• Federal eRulemaking Portal: Go to 

http://www.regulations.gov. Follow the 

instructions for submitting comments. 

• Fax: (202) 493–2251. 

• Mail: U.S. Department of 

Transportation, Docket Operations, M– 

30, West Building Ground Floor, Room 

W12–140, 1200 New Jersey Avenue SE., 

Washington, DC 20590. 

• Hand Delivery: U.S. Department of 

Transportation, Docket Operations, M– 

30, West Building Ground Floor, Room 

W12–140, 1200 New Jersey Avenue SE., 

Washington, DC, between 9 a.m. and 5 

p.m., Monday through Friday, except 

Federal holidays. 

For service information identified in 

this AD, contact Bombardier, Inc., 400 

Coˆte-Vertu Road West, Dorval, Que ́bec 

H4S 1Y9, Canada; telephone 514–855– 

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

aero.bombardier.com; Internet http://

www.bombardier.com. You may review 

copies of the referenced service 


sroberts on DSK5SPTVN1PROD with RULES