22182 Federal Register / Vol. 78, No. 72 / Monday, April 15, 2013 / Rules and Regulations 

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 this AD: 

1. Is not a ‘‘significant regulatory 

action’’ under Executive Order 12866; 

2. Is not a ‘‘significant rule’’ under the 

DOT Regulatory Policies and Procedures 

(44 FR 11034, February 26, 1979); and 

3. 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 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 AD: 

2013–05–04 Rolls-Royce plc: Amendment 

39–17376; Docket No. FAA–2013–0196; 

Directorate Identifier 2013–NE–03–AD. 

(a) Effective Date 

This airworthiness directive (AD) becomes 

effective April 30, 2013. 

(b) Affected ADs 

None. 

(c) Applicability 

This AD applies to Rolls-Royce plc (RR) 

RB211-Trent 970–84, RB211-Trent 970B–84, 

RB211-Trent 972–84, RB211-Trent 972B–84, 

RB211-Trent 977–84, RB211-Trent 977B–84, 

and RB211-Trent 980–84 turbofan engines 

that incorporate RR production Modification 

72–G585 or modified in-service through RR 

Service Bulletin (SB) 72–G585, any revision, 

with a Module 33 installed having a serial 

number (S/N) prior to HC0320, except S/Ns 

HC0277, HC0281, HC0294, HC0301, HC0309, 

HC0313, HC0315, and HC0318. 

(d) Reason 

This AD was prompted by the failure of an 

oil pump drive shear neck due to a piston 

ring seal that was not seated properly in the 

intermediate pressure compressor rear stub 

shaft (IPC RSS) groove. We are issuing this 

AD to prevent failure of the oil pump drive 

shear neck, which could result in loss of oil 

pressure in one or more engines and reduced 

control of the airplane. 

(e) Actions and Compliance 

Unless already done, do the following. 

(1) Within 50 engine flight cycles after the 

effective date of this AD, inspect the IPC RSS 

piston ring in accordance with the 

instructions of paragraph (d)(2) of RR 

Repeater Technical Variance 129978, Issue 2, 

dated December 20, 2012. 

(2) For an engine that is not in service on 

the effective date of this AD, before returning 

the engine to service, inspect the IPC RSS 

piston ring on-wing in accordance with 

paragraph (d)(2) of RR Repeater Technical 

Variance 129978, Issue 2, dated December 20, 

2012; or in shop using paragraph (d) of RR 

Repeater Technical Variance 129994, Issue 1, 

dated December 19, 2012. 

(3) If, during the inspections required by 

paragraph (e) of this AD, you find that the 

piston ring seal is not seated properly in the 

IPC RSS groove or is not intact, replace the 

piston ring seal or piston ring assembly 

before returning the engine to service. 

(f) Credit for Previous Actions 

If you performed the inspection in 

paragraph (e) of this AD before the effective 

date of this AD in accordance with RR 

Repeater Technical Variance 129978, Issue 1, 

dated December 19, 2012; RR Repeater 

Technical Variance 129940, Issue 1, dated 

December 20, 2012, or Airbus QSR RR/L/EN/ 

12–0005, as applicable, you have met the 

inspection requirement of this AD. 

(g) 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. 

(h) Related Information 

(1) For more information about this AD, 

contact Frederick Zink, Aerospace Engineer, 

Engine Certification Office, FAA, Engine & 

Propeller Directorate, 12 New England 

Executive Park, Burlington, MA 01803; 

phone: 781–238–7779; fax: 781–238–7199; 

email: frederick.zink@faa.gov. 

(2) Refer to MCAI European Aviation 

Safety Agency AD 2012–0273, dated 

December 21, 2012, for related information. 

(i) Material Incorporated by Reference 

(1) The Director of the Federal Register 

approved the incorporation by reference 

(IBR) of the service information listed in this 

paragraph under 5 U.S.C. 552(a) and 1 CFR 

part 51. 

(2) You must use this service information 

as applicable to do the actions required by 

this AD, unless the AD specifies otherwise. 

(i) RR Repeater Technical Variance 129994, 

Issue 1, dated December 19, 2012. 

(ii) RR Repeater Technical Variance 

129978, Issue 2, dated December 20, 2012. 

(3) For 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: 011–44–1332–245418, or email: 

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

civil_team.jsp. 

(4) You may view this service information 

at the 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 

March 1, 2013. 

Robert J. Ganley, 

Acting Manager, Engine & Propeller 

Directorate, Aircraft Certification Service. 

[FR Doc. 2013–08445 Filed 4–12–13; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2012–0933; Directorate 

Identifier 2012–NM–107–AD; Amendment 

39–17411; AD 2013–07–07] 

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 all The 

Boeing Company Model 737–600, –700, 

–700C, –800, –900, and –900ER series 

airplanes. This AD was prompted by 

reports of an incorrect procedure used 

to apply the wear and corrosion 

protective surface coating to attach pins 

of the horizontal stabilizer rear spar. 

This AD requires inspecting to 

determine the part number of the attach 

pins of the horizontal stabilizer rear 

spar, and replacing certain attach pins 

with new, improved attach pins. We are 

issuing this AD to prevent premature 

failure of the attach pins, which could 

cause reduced structural integrity of the 

horizontal stabilizer to fuselage 

attachment, resulting in loss of control 

of the airplane. 

DATES: This AD is effective May 20, 

2013. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication listed in the AD 

as of May 20, 2013. 

ADDRESSES: For service information 

identified in this AD, contact Boeing 

Commercial Airplanes, Attention: Data 

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Federal Register / Vol. 78, No. 72 / Monday, April 15, 2013 / Rules and Regulations 22183 

& Services Management, P.O. Box 3707, 

MC 2H–65, Seattle, WA 98124–2207; 

telephone 206–544–5000, extension 1; 

fax 206–766–5680; Internet https:// 

www.myboeingfleet.com. You may 

review copies of the referenced service 

information at the FAA, Transport 

Airplane Directorate, 1601 Lind Avenue 

SW., Renton, WA. For information on 

the availability of this material at the 

FAA, call 425–227–1221. 

Examining the AD Docket 

You may examine the AD docket on 

the Internet at http:// 

www.regulations.gov; or in person at the 

Docket Management Facility between 9 

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

Friday, except Federal holidays. The AD 

docket contains this AD, the regulatory 

evaluation, any comments received, and 

other information. The address for the 

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

Document Management Facility, U.S. 

Department of Transportation, Docket 

Operations, M–30, West Building 

Ground Floor, Room W12–140, 1200 

New Jersey Avenue SE., Washington, 

DC 20590. 

FOR FURTHER INFORMATION CONTACT: 

Nancy Marsh, Aerospace Engineer, 

Airframe Branch, ANM–120S, FAA, 

Seattle Aircraft Certification Office, 

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. That 

NPRM published in the Federal 

Register on September 12, 2012 (77 FR 

56170). That NPRM proposed to require 

inspecting to determine the part number 

of the attach pins of the horizontal 

stabilizer rear spar, and replacing 

certain attach pins with new, improved 

attach pins. 

Comments 

We gave the public the opportunity to 

participate in developing this AD. The 

following presents the comments 

received on the proposal (77 FR 56170, 

September 12, 2012) and the FAA’s 

response to each comment. 

Concurrence With NPRM (77 FR 56170, 

September 12, 2012) 

Boeing concurs with the content of 

the proposed rule (77 FR 56170, 

September 12, 2012). 

Request for Alternative Method of 

Compliance (AMOC) to Inspections 

Required by AD 2004–05–19, 

Amendment 39–13514 (69 FR 10921, 

March 9, 2004; Corrected April 13, 

2004 (69 FR 19313)) 

Europe Airpost requested that a 

statement be included in the NPRM (77 

FR 56170, September 12, 2012) that 

approves installation of the horizontal 

stabilizer rear spar attachment pins part 

number (P/N) 180A1612–7 and 

180A1612–8 as an AMOC to the 

inspections required by AD 2004–05– 

19, Amendment 39–13514 (69 FR 

10921, March 9, 2004; corrected April 

13, 2004 (69 FR 19313)) provided that 

the special inspections specified in the 

Boeing maintenance planning data 

(MPD) document are performed. 

We agree with the request. We have 

added paragraph (j) to this final rule to 

state that accomplishing the actions 

required by paragraphs (g) and (h) of 

this AD terminates the requirements of 

paragraphs (a), (b), (c), (d), and (e) of AD 

2004–05–19 Amendment 39–13514 (69 

FR 10921, March 9, 2004; corrected 

April 13, 2004 (69 FR 19313)), for rear 

spar attach pins only. 

Request for Exclusions 

Delta Air Lines (Delta) requested that 

we provide exclusions in paragraph (g) 

of the NPRM (77 FR 56170, September 

12, 2012) for certain airplanes that may 

not be affected by the discrepant 

stabilizer pins. Delta stated that 

airplanes that were not delivered 

between August 1, 2006, and July 31, 

2008, have not had the terminating 

action accomplished according to AD 

2004–05–19, Amendment 39–13514 (69 

FR 10921, March 9, 2004; corrected 

April 13, 2004 (69 FR 19313)), and did 

not have maintenance done in 

accordance with the MPD, would not 

need to be inspected. Delta also 

requested that we provide exclusions to 

paragraph (i) of the NPRM because spare 

pins having P/N 180A1612–3 and 

180A1612–4 delivered by Boeing Spares 

before June 30, 2006, and after June 17, 

2008, are not suspected of having 

unapproved surface coatings. 

We disagree with the request to 

change paragraphs (g) and (i) in this 

final rule. Although Boeing has 

specified certain airplane delivery dates 

associated with the discrepant pins, as 

well as delivery dates for pins suspected 

to be discrepant and distributed as spare 

parts, other factors make identification 

of the affected airplanes difficult. 

Stabilizers are rotable components, and 

therefore stabilizer attach pins may be 

different from those delivered with the 

airplane. To assist operators in 

inspecting for the suspect pins, 

paragraph (g) of this final rule (as 

proposed in the NPRM (77 FR 56170, 

September 12, 2012)) allows for a 

records search to be used to confirm the 

part number of the rear spar attachment 

pin, if such a record search is 

conclusive. No change has been made to 

this final rule in this regard. 

Request To Include AD 2004–05–19, 

Amendment 39–13514 (69 FR 10921, 

March 9, 2004; corrected April 13, 2004 

(69 FR 19313)) 

Europe Airpost requested that we 

revise the NPRM (77 FR 56170, 

September 12, 2012) to include AD 

2004–05–19, Amendment 39–13514 (69 

FR 10921, March 9, 2004; corrected 

April 13, 2004 (69 FR 19313)), as a 

related AD in paragraph (b) of the 

NPRM. The commenter stated that the 

new AD will affect AD 2004–05–19 

because attach pins having P/Ns 

180A1612–3 and 180A1612–4 could 

also have been installed as a terminating 

action for AD 2004–05–19. 

We agree with the commenter and 

have revised paragraph (b) of this final 

rule accordingly. 

Request To Allow Re-Installation of 

Serviceable Attach Pins 

Japan Airlines (JAL) requested that we 

revise the NPRM (77 FR 56170, 

September 12, 2012) to allow for reinstallation of attach pins having P/N 

180A1612–3 and 180A1612–4 that are 

found to be serviceable. JAL agrees that 

replacement of the attach pins would 

have to be done before 56,000 total 

flight cycles, but notes that routine 

maintenance inspections of the pins 

require pin removal prior to the 56,000 

flight cycle threshold. JAL concluded 

that when these inspections are 

accomplished prior to that threshold, 

paragraphs (h) and (i) of the NPRM 

would prohibit re-installation of the 

pins, even if they are found to be 

serviceable. 

We partially agree with the request. 

We agree that re-installation of the pins 

having P/Ns 180A1612–3 and 

180A1612–4 that have been inspected in 

accordance with Special Structural 

Inspections of Section 9, ‘‘Airworthiness 

Limitations (AWLs) and Certification 

Maintenance Requirements (CMRs),’’ of 

Boeing 737–600/700/700C/800/900/ 

900ER Maintenance Planning Data 

(MPD) Document D626A001–CMR, 

Revision 09, may be acceptable for 

compliance; however, the commenter 

did not state which revision of the MPD 

would be used. As numerous revisions 

of the MPD exist and many new 

revisions are released each year, this 

approval is most effectively 

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22184 Federal Register / Vol. 78, No. 72 / Monday, April 15, 2013 / Rules and Regulations 

accomplished using the procedures in 

paragraph (k) of this AD. No change has 

been made to the AD in this regard. 

We have revised paragraph (h) of this 

AD to state that airplanes having line 

numbers 1 through 3534 inclusive 

having an attach pin P/N 180A1612–3 

or 180A1612–4 must be replaced with a 

new attach pin P/N 180A1612–7 or 

180A1612–8, respectively, prior to the 

accumulation of 56,000 total flight 

cycles on the pin, or within 3,000 flight 

cycles after the effective date of this AD, 

whichever occurs later. 

STC Winglet Comment 

Aviation Partners Boeing stated that 

the installation of winglets per STC 

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

Regulatory_and_Guidance_Library/

rgstc.nsf/0/408E012E008616A7862578

880060456C?OpenDocument&

Highlight=st00830se) does not affect the 

accomplishment of the manufacturer’s 

service instructions. 

We have added paragraph (c)(2) to 

this AD to state that installation of STC 

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

Regulatory_and_Guidance_Library/

rgstc.nsf/0/408E012E008616A786257

8880060456C?OpenDocument&

Highlight=st00830se) does not affect 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 is not necessary to 

comply with the requirements of 14 CFR 

39.17. For all other AMOC requests, the 

operator must request approval for an 

AMOC in accordance with the 

procedures specified in paragraph (k) of 

this AD. 

Other Changes to the NPRM (77 FR 

56170, September 12, 2012) 

We have clarified paragraph (i)(1) of 

this AD to state that on certain airplanes 

installation of an attach pin having P/N 

180A1612–3 or 180A1612–4 is not 

acceptable for compliance unless the 

actions required by paragraphs (g) and 

(h) of this AD are accomplished on that 

airplane. 

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 

56170, September 12, 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 56170, 

September 12, 2012). 

We also determined that these 

changes 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 1,050 

airplanes of U.S. registry. 

We estimate the following costs to 

comply with this AD: 

ESTIMATED COSTS

Action Labor cost Parts cost Cost per 

product 

Cost on U.S. 

operators 

Inspection and attach pin replacement ........ 39 work-hours × $85 per hour = $3,315 ...... Up to $6,312 ..... $9,627 Up to $10,108,350. 

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 

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): 

2013–07–07 The Boeing Company: 

Amendment 39–17411; Docket No. 

FAA–2012–0933; Directorate Identifier 

2012–NM–107–AD. 

(a) Effective Date 

This AD is effective May 20, 2013. 

(b) Affected ADs 

This AD affects certain requirements of AD 

2004–05–19, Amendment 39–13514 (69 FR 

10921, March 9, 2004; corrected April 13, 

2004 (69 FR 19313)). 

(c) Applicability 

(1) This AD applies to all The Boeing 

Company Model 737–600, –700, –700C, 

–800, –900, and –900ER series airplanes, 

certificated in any category. 

(2) Installation of Supplemental Type 

Certificate (STC) ST00830SE (http://rgl.faa.

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Federal Register / Vol. 78, No. 72 / Monday, April 15, 2013 / Rules and Regulations 22185 

gov/Regulatory_and_Guidance_Library/rgstc.

nsf/0/408E012E008616A7862578880060

456C?OpenDocument&Highlight=st00830se) 

does not affect the ability to accomplish the 

actions required by this AD. Therefore, for 

airplanes on which STC ST00830SE is 

installed, a ‘‘change in product’’ alternative 

method of compliance (AMOC) approval 

request is not necessary to comply with the 

requirements of 14 CFR 39.17. For all other 

AMOC requests, the operator must request 

approval for an AMOC in accordance with 

the procedures specified in paragraph (k) of 

this AD. 

(d) Subject 

Joint Aircraft System Component (JASC)/ 

Air Transport Association (ATA) of America 

Code 55, Stabilizers. 

(e) Unsafe Condition 

This AD was prompted by reports of an 

incorrect procedure used to apply the wear 

and corrosion protective surface coating to 

attach pins of the horizontal stabilizer rear 

spar. We are issuing this AD to prevent 

premature failure of the attach pins, which 

could cause reduced structural integrity of 

the horizontal stabilizer to fuselage 

attachment, resulting in loss of control of the 

airplane. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Part Number (P/N) Inspection 

For airplanes having line numbers 1 

through 3534 inclusive: Before the 

accumulation of 56,000 total flight cycles, or 

within 3,000 flight cycles after the effective 

date of this AD, whichever occurs later, 

inspect to determine the part number of the 

attach pins of the horizontal stabilizer rear 

spar. A review of airplane maintenance 

records is acceptable in lieu of this 

inspection if the part number of the attach 

pin can be conclusively determined from that 

review. 

(h) Replacement 

If, during the inspection required by 

paragraph (g) of this AD, any horizontal 

stabilizer rear spar attach pin has P/N 

180A1612–3 or 180A1612–4, prior to the 

accumulation of 56,000 total flight cycles on 

the pin, or within 3,000 flight cycles after the 

effective date of this AD, whichever occurs 

later, replace with a new attach pin having 

P/N 180A1612–7 or 180A1612–8, 

respectively, in accordance with the 

Accomplishment Instructions of Boeing 

Special Attention Service Bulletin 737–55– 

1093, dated April 9, 2012. 

(i) Parts Installation Limitation and 

Prohibition 

(1) For airplanes having line numbers 1 

through 3534 inclusive: As of the effective 

date of this AD, no person may install an 

attach pin of the horizontal stabilizer rear 

spar having P/N 180A1612–3 or 180A1612– 

4 on any airplane; unless the actions required 

by paragraph (g) and (h) of this AD have been 

done on that airplane. 

(2) For airplanes having line numbers 3535 

and subsequent: As of the effective date of 

this AD, no person may install an attach pin 

of the horizontal stabilizer rear spar having 

P/N 180A1612–3 or 180A1612–4 on any 

airplane. 

(j) Terminating Action for AD 2004–05–19, 

Amendment 39–13514 (69 FR 10921, March 

9, 2004; corrected April 13, 2004 (69 FR 

19313)) 

Accomplishment of the actions required by 

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

the requirements of paragraphs (a), (b), (c), 

(d), and (e) of AD 2004–05–19, Amendment 

39–13514 (69 FR 10921, March 9, 2004; 

corrected April 13, 2004 (69 FR 19313)) for 

the rear spar attach pins only. 

(k) Alternative Methods of Compliance 

(AMOCs) 

(1) The Manager, Seattle Aircraft 

Certification Office (ACO), FAA, has the 

authority to approve AMOCs for this AD, if 

requested using the procedures found in 14 

CFR 39.19. In accordance with 14 CFR 39.19, 

send your request to your principal inspector 

or local Flight Standards District Office, as 

appropriate. If sending information directly 

to the manager of the ACO, send it to the 

attention of the person identified in the 

Related Information section of this AD. 

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

(2) Before using any approved AMOC, 

notify your appropriate principal inspector, 

or lacking a principal inspector, the manager 

of the local flight standards district office/ 

certificate holding district office. 

(3) 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. 

(l) 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, 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. 

(i) Boeing Special Attention Service 

Bulletin 737–55–1093, dated April 9, 2012. 

(ii) Reserved. 

(3) For service information identified in 

this AD, contact Boeing Commercial 

Airplanes, Attention: Data & Services 

Management, P.O. Box 3707, MC 2H–65, 

Seattle, WA 98124–2207; telephone 206– 

544–5000, extension 1; fax 206–766–5680; 

Internet https://www.myboeingfleet.com. 

(4) You may view this service information 

at 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. 

(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 March 

28, 2013. 

Ali Bahrami, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 2013–08193 Filed 4–12–13; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2012–0497; Directorate 

Identifier 2011–NM–140–AD; Amendment 

39–17415; AD 2013–07–11] 

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 

777–200, –200LR, –300, and –300ER 

series airplanes. That AD currently 

requires inspecting for scribe lines in 

the skin along lap joints, butt joints, 

certain external doublers, and the large 

cargo door hinges, and doing related 

investigative and corrective actions if 

necessary. This new AD adds an 

inspection for scribe lines where 

external decals have been applied or 

removed across lap joints, large cargo 

door hinges, and external doublers, and 

related investigative and corrective 

actions if necessary. This AD was 

prompted by a determination that scribe 

lines could occur where external decals 

are installed or removed across lap 

joints, large cargo door hinges, or 

external doublers. We are issuing this 

AD to detect and correct scribe lines, 

which can develop into fatigue cracks in 

the skin. Undetected fatigue cracks can 

grow and cause sudden decompression 

of the airplane. 

DATES: This AD is effective May 20, 

2013. 

The Director of the Federal Register 

approved the incorporation by reference 

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