### 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, beforefurther 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 theleft- 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


### 72553 Federal Register / Vol. 78, No. 232 / Tuesday, December 3, 2013 / Rules and Regulations

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.


### 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