72552 Federal Register / Vol. 78, No. 232 / Tuesday, December 3, 2013 / Rules and Regulations 

paragraphs (g)(1) and (g)(2) of this AD, in 

accordance with the Accomplishment 

Instructions of Boeing 707 Service Bulletin 

3532, dated January 12, 2012. 

(1) Do either a general visual inspection or 

ultrasonic non-destructive test of the left- and 

right-hand wing fuel tank access doors to 

determine whether impact-resistant access 

doors are installed in the correct locations. If 

any standard access door is found, before 

further flight, replace with an impactresistant access door, in accordance with the 

Accomplishment Instructions of Boeing 707 

Service Bulletin 3532, dated January 12, 

2012. 

(2) Do a general visual inspection of the 

left- and right-hand wing fuel tank impactresistant access doors to verify stencils and 

index markers are applied. If a stencil or 

index marker is missing, before further flight, 

apply stencil or index marker, as applicable, 

in accordance with the Accomplishment 

Instructions of Boeing707 Service Bulletin 

3532, dated January 12, 2012. 

(h) Maintenance Program Revision 

Within 60 days after the effective date of 

this AD, revise the maintenance program to 

incorporate Critical Design Configuration 

Control Limitations (CDCCL) Task 57–AWL– 

01, Impact-Resistant Fuel Tank Access Doors, 

of Subsection B, Airworthiness Limitations 

(AWLs) of the Boeing 707/720 Airworthiness 

Limitations (AWLs) Document D6–7552– 

AWL, Revision September 2012. 

(i) No Alternative Actions, Intervals, and/or 

CDCCLs 

After accomplishing the revision required 

by paragraph (h) of this AD, no alternative 

actions (e.g., inspections), intervals, and/or 

CDCCLs may be used unless the actions, 

intervals, and/or CDCCLs are approved as an 

alternative method of compliance (AMOC) in 

accordance with the procedures specified in 

paragraph (j) of this AD. 

(j) 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 

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 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 Suzanne Lucier, Aerospace Engineer, 

Propulsion Branch, ANM–140S, FAA, Seattle 

Aircraft Certification Office, 1601 Lind 

Avenue SW., Renton, WA 98057–3356; 

phone: 425–917–6438; fax: 425–917–6590; 

email: suzanne.lucier@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) Boeing 707 Service Bulletin 3532, dated 

January 12, 2012. 

(ii) Critical Design Configuration Control 

Limitations (CDCCL) Task 57–AWL–01, 

Impact-Resistant Fuel Tank Access Doors, of 

Subsection B, Airworthiness Limitations 

(AWLs) of the Boeing 707/720 Airworthiness 

Limitations (AWLs) Document D6–7552– 

AWL, Revision September 2012. 

(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 

November 15, 2013. 

John Piccola, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2013–28193 Filed 12–2–13; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2013–0475; Directorate 

Identifier 2013–NE–18–AD; Amendment 39– 

17669; AD 2013–23–14] 

RIN 2120–AA64 

Airworthiness Directives; General 

Electric Company Turbofan Engines 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule. 

SUMMARY: We are adopting a new 

airworthiness directive (AD) for certain 

General Electric Company model GEnx– 

2B67 and GEnx–2B67B turbofan 

engines. This AD was prompted by the 

original equipment manufacturer’s 

disclosure that certain critical rotating 

life-limited parts (LLPs) used in Boeing 

747–8 flight tests had consumed more 

cyclic life than they would have in 

revenue flight cycles. These parts were 

then installed into engines and 

introduced into revenue service without 

adjustment to remaining cyclic life. This 

AD requires a one-time adjustment to 

the cycle counts of those LLPs to 

account for the additional low cycle 

fatigue (LCF) life consumed during 

flight tests. We are issuing this AD to 

prevent the failure of critical rotating 

LLPs, uncontained engine failure, and 

damage to the airplane. 

DATES: This AD is effective January 7, 

2014. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication listed in this AD 

as of January 7, 2014. 

ADDRESSES: For service information 

identified in this AD, contact General 

Electric Company, GE Aviation, Room 

285, 1 Neumann Way, Cincinnati, OH 

45215; phone: 513–552–3272; email: 

geae.aoc@ge.com. You may view this 

service information at the FAA, Engine 

& Propeller Directorate, 12 New England 

Executive Park, Burlington, MA 01803. 

For information on the availability of 

this material at the FAA, call (781) 238– 

7125. 

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 

provided in the ADDRESSES section. 

Comments will be available in the AD 

docket shortly after receipt. 

FOR FURTHER INFORMATION CONTACT: 

Carlos Fernandes, Aerospace Engineer, 

Engine Certification Office, FAA, Engine 

& Propeller Directorate, 12 New England 

Executive Park, Burlington, MA 01803; 

phone: (781) 238–7189; fax: (781) 238– 

7199; email: carlos.fernandes@faa.gov. 

SUPPLEMENTARY INFORMATION: 

Discussion 

We issued a notice of proposed 

rulemaking (NPRM) to amend 14 CFR 

part 39 by adding an AD that would 


emcdonald on DSK67QTVN1PROD with RULES
Federal Register / Vol. 78, No. 232 / Tuesday, December 3, 2013 / Rules and Regulations 72553 

apply to the specified products. The 

NPRM published in the Federal 

Register on August 5, 2013 (78 FR 

47235). The NPRM proposed to require 

a one-time adjustment to the cycle 

counts of certain critical rotating LLPs 

to account for the additional LCF life 

consumed in Boeing 747–8 flight tests. 

Comments 

We gave the public the opportunity to 

participate in developing this AD. We 

received no comments on the NPRM or 

on the determination of the cost to the 

public. 

Conclusion 

We reviewed the relevant data and 

determined that air safety and the 

public interest require adopting the AD 

as proposed, except for minor editorial 

changes. We have determined that these 

minor changes: 

• Are consistent with the intent that 

was proposed in the NPRM (78 FR 

47235, August 5, 2013) for correcting 

the unsafe condition; and 

• Do not add any additional burden 

upon the public than was already 

proposed in the NPRM. 

Costs of Compliance 

We estimate that this AD affects 4 

engines installed on airplanes of U.S. 

registry. We also estimate that it will 

take about 1 hour per engine to comply 

with this AD. The average labor rate is 

$85 per hour. The prorated cost of 

required parts will be about $50,000 per 

engine. Based on these figures, we 

estimate the cost of this AD to U.S. 

operators to be $200,340. 

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 to the extent that it justifies 

making a regulatory distinction, and 

(4) Will not have a significant 

economic impact, positive or negative, 

on a substantial number of small entities 

under the criteria of the Regulatory 

Flexibility Act. 

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): 

2013–23–14 General Electric Company: 

Amendment 39–17669; Docket No. 

FAA–2013–0475; Directorate Identifier 

2013–NE–18–AD. 

(a) Effective Date 

This AD is effective January 7, 2014. 

(b) Affected ADs 

None. 

(c) Applicability 

This AD applies to certain serial number 

General Electric Company (GE) model GEnx– 

2B67 and GEnx–2B67B turbofan engines. The 

affected engine serial numbers are: 959–102 

through 959–104; 959–107; 959–110 through 

959–111; 959–113 through 959–118; 959– 

121; 959–124 through 959–133; 959–159 

through 959–161; 959–164; 959–176; and 

959–191. 

(d) Unsafe Condition 

This AD was prompted by GE’s report that 

certain critical rotating life-limited parts 

(LLPs) used in Boeing 747–8 flight tests had 

consumed more cyclic life than they would 

have in revenue service flights. These parts 

were then installed into engines and 

introduced into revenue service without 

adjustment to remaining cyclic life. We are 

issuing this AD to prevent the failure of 

critical rotating LLPs, uncontained engine 

failure, and damage to the airplane. 

(e) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(f) Adjust the Cycle Counts of Certain 

Critical Rotating LLPs 

Within 30 days after the effective date of 

this AD, perform a one-time adjustment to 

the cycle count of each part identified in 

paragraph 4, Appendix A, of GE Service 

Bulletin No. GEnx–2B S/B 72–0116, Revision 

1, dated April 23, 2013. 

(g) Alternative Methods of Compliance 

(AMOCs) 

The Manager, Engine Certification Office, 

FAA, may approve AMOCs for this AD. Use 

the procedures found in 14 CFR 39.19 to 

make your request. 

(h) Related Information 

For more information about this AD, 

contact Carlos Fernandes, Aerospace 

Engineer, Engine Certification Office, FAA, 

Engine & Propeller Directorate, 12 New 

England Executive Park, Burlington, MA 

01803; phone: (781) 238–7189; fax: (781) 

238–7199; email: carlos.fernandes@faa.gov. 

(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) General Electric (GE) Service Bulletin 

No. GEnx-2B S/B 72–0116, Revision 1, dated 

April 23, 2013. 

(ii) Reserved. 

(3) For GE service information identified in 

this AD, contact General Electric Company, 

GE Aviation, Room 285, 1 Neumann Way, 

Cincinnati, OH 45215; phone: 513–552–3272; 

email: geae.aoc@ge.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. 


emcdonald on DSK67QTVN1PROD with RULES
72554 Federal Register / Vol. 78, No. 232 / Tuesday, December 3, 2013 / Rules and Regulations 

Issued in Burlington, Massachusetts, on 

November 14, 2013. 

Frank P. Paskiewicz, 

Acting Director, Aircraft Certification Service. 

[FR Doc. 2013–28293 Filed 12–2–13; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2012–1313; Directorate 

Identifier 2012–NM–080–AD; Amendment 

39–17651; AD 2013–22–19] 

RIN 2120–AA64 

Airworthiness Directives; Gulfstream 

Aerospace Corporation Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule. 

SUMMARY: We are adopting a new 

airworthiness directive (AD) for all 

Gulfstream Aerospace Corporation 

Model GV and GV–SP airplanes. This 

AD was prompted by reports of two 

independent types of failure of the fuel 

boost pump with overheat damage 

found on the internal components and 

external housing on one of the failure 

types, and fuel leakage on the other. 

This AD requires inspecting to 

determine if fuel boost pumps having a 

certain part number are installed, 

replacing the fuel boost pumps having 

a certain part number, and revising the 

airplane maintenance program to 

include revised instructions for 

continued airworthiness. We are issuing 

this AD to prevent fuel leakage in 

combination with a capacitor clearance 

issue, which could result in an 

uncontrolled fire in the wheel well. 

DATES: This AD is effective January 7, 

2014. 

The Director of the Federal Register 

approved the incorporation by reference 

of certain publications listed in this AD 

as of January 7, 2014. 

ADDRESSES: For Gulfstream, Triumph 

Aerostructures, and General Electric 

(GE) Aviation service information 

identified in this AD, contact 

Gulfstream Aerospace Corporation, 

Technical Publications Dept., P.O. Box 

2206, Savannah, GA 31402–2206; 

telephone 800–810–4853; fax 912–965– 

3520; email pubs@gulfstream.com; 

Internet http://www.gulfstream.com/

product_support/technical_pubs/pubs/

index.htm. You may view this 

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/

#!docketDetail;D=FAA-2012-1313; 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: 

Darby Mirocha, Aerospace Engineer, 

Propulsion and Services Branch, ACE– 

118A, FAA, Atlanta Aircraft 

Certification Office, 1701 Columbia 

Avenue, College Park, GA 30337; phone: 

(404) 474–5573; fax: (404) 474–5606; 

email: darby.mirocha@faa.gov. 

SUPPLEMENTARY INFORMATION: 

Discussion 

We issued a notice of proposed 

rulemaking (NPRM) to amend 14 CFR 

part 39 by adding an AD that would 

apply to the specified products. The 

NPRM published in the Federal 

Register on December 26, 2012 (77 FR 

75908). The NPRM proposed to require 

doing an inspection to determine if fuel 

boost pumps having a certain part 

number (P/N) are installed, replacing 

the fuel boost pumps having a certain 

part number, and revising the airplane 

maintenance program to include revised 

instructions for continued 

airworthiness. 

This AD was prompted by reports of 

two independent types of failure of the 

fuel boost pump with overheat damage 

found on the internal components and 

external housing on one of the failure 

types, and fuel leakage on the other. We 

are issuing this AD to prevent fuel 

leakage in combination with a capacitor 

clearance issue, which could result in 

an uncontrolled fire in the wheel well. 

Comments 

We gave the public the opportunity to 

participate in developing this AD. The 

following presents the comments 

received on the NPRM (77 FR 75908, 

December 26, 2012) and the FAA’s 

response to each comment. 

Request To Revise the Precipitating 

Event 

Gulfstream Aerospace Corporation 

(Gulfstream) requested that the 

precipitating event in the SUMMARY

section of the NPRM (77 FR 75908, 

December 26, 2012) be revised to 

provide clarity not provided elsewhere 

in the NPRM—namely, although two 

distinct failure types have been 

reported, there have been no reports of 

any fuel pump exhibiting both failure 

types. 

We agree with Gulfstream’s request. 

We agree that the failures in service 

were separate events and no single 

pump was found with both failure 

modes present. We have changed the 

SUMMARY section and paragraph (e) of 

this final rule to include language 

suggested by the commenter 

emphasizing the independent nature of 

the failure modes. 

Request To Revise the Statement of 

Requirements 

Gulfstream requested that the 

statement of requirements in the 

SUMMARY section of the NPRM (77 FR 

75908, December 26, 2012) be revised. 

Gulfstream proposed to revise the 

wording to read, ‘‘This proposed AD 

would require doing an inspection to 

determine if fuel boost pumps having a 

certain part number are installed, 

replacing the fuel boost pumps having 

a certain part number with a later part 

number, and revising the airplane 

maintenance program to include revised 

instructions for continued airworthiness 

for airplanes with the later pump part 

number installed.’’ Gulfstream stated 

that the rewording increases the content 

clarity in the NPRM. 

We disagree with Gulfstream’s request 

to refer to ‘‘later part numbers’’ because 

this language lacks clarity. This final 

rule requires specific part number 

replacements. Therefore, we would 

need to use specific part numbers to 

identify replacement parts. In addition, 

the intent of the SUMMARY section is to 

provide a brief explanation of the unsafe 

condition and corrective actions; 

therefore, we do not find it appropriate 

to include details regarding specific part 

numbers. We have not changed this 

final rule in this regard. 

Request To Revise the Discussion 

Paragraph of the NPRM (77 FR 75908, 

December 26, 2012) 

Gulfstream requested that the 

Discussion paragraph of the NPRM (77 

FR 75908, December 26, 2012) be 

revised. Gulfstream proposed revising 

the wording to add, ‘‘Additionally, on 

one other fuel pump component, a 


emcdonald on DSK67QTVN1PROD with RULES