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criteria. In addition to utilizing these selection criteria, when a contracting agency enters into a contract both for the processing of donated food and the purchase of the end products produced from the donated food, the procurement standards set forth in 2 CFR part 200, subpart D and Appendix II, Contract Provisions for Non-Federal Entity Contracts Under Federal Awards and USDA implementing regulations at 2 CFR part 400 and part 416 must be followed. Recipient agencies which purchase end products produced under Statewide agreements are also required to comply with 2 CFR part 200, subpart D and USDA implementing regulations at 2 CFR part 400 and part 416. Contracting agencies shall not enter into contracts with processors which cannot demonstrate the ability to meet the terms and conditions of the regulations and the distributing agency agreements; furnish prior to the delivery of any donated foods for processing, a performance bond, an irrevocable letter of credit or an escrow account in an amount sufficient to protect the contract value of donated food on hand and on order; demonstrate the ability to distribute end products to eligible recipient agencies; provide a satisfactory record of integrity, business ethics and performance and provide adequate storage.
* * * * *

Dated: October 24, 2016. Telora T. Dean, Acting Administrator, Food and Nutrition Service.
[FR Doc. 2016–26329 Filed 10–31–16; 8:45 am]

**BILLING CODE 3410–30–P**

**DEPARTMENT OF TRANSPORTATION**

**Federal Aviation Administration**

**14 CFR Part 39**

**[Docket No. FAA–2012–1293; Directorate Identifier 2012–NE–45–AD; Amendment 39–**  **18700; AD 2016–22–11]**

**RIN 2120–AA64**

**Airworthiness Directives; Engine Alliance Turbofan Engines** 

**AGENCY :**  Federal Aviation Administration (FAA), DOT.

**ACTION :**  Final rule; request for
comments.

**SUMMARY :**  We are superseding airworthiness directive (AD) 2013–02– 06 for all Engine Alliance (EA) GP7270 and GP7277 turbofan engines with certain part number (P/N) high-pressure turbine (HPT) stage 2 nozzle segments installed. AD 2013–02–06 required initial and repetitive borescope inspections (BSI) and removal from service of these nozzles before further flight if one or more burn holes were detected in any HPT stage 2 nozzle segment. AD 2013–02–06 also required removal from service of these HPT stage 2 nozzle segments at the next engine shop visit. This AD requires the same inspections as AD–2013–02–06, requires removal of affected HPT stage 2 nozzles at next piece-part exposure, and adds certain P/Ns to the applicability. This AD was prompted by another report of inadequate cooling of the HPT stage 1 shroud and stage 2 nozzle, leading todamage to the HPT stage 2 nozzle, burnthrough of the turbine case, and in-flight shutdown. We are issuing this AD to prevent HPT stage 2 nozzle failure, uncontrolled fire, in-flight shutdown, and damage to the airplane.

**DATES :**  This AD is effective November 16, 2016.

We must receive any comments on this AD by December 16, 2016.

**ADDRESSES :**  You may send comments, using the procedures found in 14 CFR 11.43 and 11.45, 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 20590, between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. Examining the AD Docket

You may examine the AD docket on the Internet at http:// www.regulations.gov by searching for and locating Docket No. FAA–2012– 1293; 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 street address for the Docket Office (phone: 800–647– 5527) is in the **ADDRESSES** section. Comments will be available in the AD docket shortly after receipt.

**FOR FURTHER INFORMATION CONTACT :**  Martin Adler, Aerospace Engineer, Engine & Propeller Directorate, FAA, 1200 District Avenue, Burlington, MA 01803; phone: 781–238–7157; fax: 781– 238–7199; email: martin.adler@faa.gov.

**SUPPLEMENTARY INFORMATION :** 

Discussion

On January 15, 2013, we issued AD 2013–02–06, Amendment 39–17327 (78 FR 5710, January 28, 2013), (‘‘AD 2013– 02–06’’), for all Engine Alliance GP7270 and GP7277 turbofan engines with an HPT stage 2 nozzle, P/N 2101M24G01, 2101M24G02, or 2101M24G03, installed. AD 2013–02–06 required initial and repetitive BSIs and removal from service of these nozzles before further flight if any burn holes were detected in the affected nozzles. AD 2013–02–06 also required removal from service of the affected nozzles at the next engine shop visit. AD 2013–02–06 resulted from a report of inadequate cooling of the HPT stage 2 nozzle, leading to damage to the HPT stage 2 nozzle, burn-through of the turbine case, and in-flight shutdown. We issued AD 2013–02–06 to prevent HPT stage 2nozzle failure, uncontrolled fire, inflight shutdown, and damage to the airplane.

Actions Since AD 2013–02–06 Was Issued

Since we issued AD 2013–02–06, we received another report of inadequate cooling of the HPT stage 1 shroud and stage 2 nozzle, leading to damage to the HPT stage 2 nozzle, burn-through of the turbine case, and in-flight shutdown. This event occurred with HPT stage 2 nozzle, P/N 2101M24G04, 2101M24G05, or 2101M24G06 installed. Investigation revealed that the event was caused by damage to the HPT stage 2 nozzle due to inadequate part cooling. We are issuing this AD to prevent HPT stage 2nozzle failure, uncontrolled fire, inflight shutdown, and damage to the airplane.

Related Service Information

We reviewed EA Service Bulletins EAGP7–72–190, dated December 6, 2012 and EAGP7–72–262, Revision No. 5, dated December 18, 2015. This service information describes procedures for inspecting the HPT stage 2 nozzle segments.

FAA’s Determination

We are issuing this AD because we evaluated all the relevant information and determined the unsafe condition described previously is likely to exist or develop in other products of the same type design.
AD Requirements

This AD requires initial and repetitive BSIs of the HPT stage 1 shroud and HPT


### 75685 Federal Register / Vol. 81, No. 211 / Tuesday, November 1, 2016 / Rules and Regulations

stage 2 nozzle segments and removal from service of these nozzle segments before further flight if one or more burn holes are detected on the HPT stage 2 nozzle or if the HPT stage 1 shroud is found distorted. This AD also requires removal from service of any HPT stage 2 nozzle segment, P/N 2101M24G01, 2101M24G02, 2101M24G03, 2101M24G04, 2101M24G05, or 2101M24G06, at next piece-part
exposure. FAA’s Justification and Determination of the Effective Date

No domestic operators use this product. Therefore, we find that notice and opportunity for prior public comment are unnecessary and that good cause exists for making this amendment effective in less than 30 days.

Comments Invited

This AD is a final rule that involves requirements affecting flight safety, and we did not provide you with notice and an opportunity to provide your comments before it becomes effective. However, we invite you to send any written data, views, or arguments about this AD. Send your comments to an address listed under the **ADDRESSES** section. Include the docket number FAA–2012–1293 and Directorate Identifier 2012–NE–45–AD at the beginning of your comments. We specifically invite comments on the overall regulatory, economic, environmental, and energy aspects of this AD. We will consider all comments received by the closing date and may amend this AD because of those
comments.

We will post all comments we receive, without change, to http:// www.regulations.gov, including any personal information you provide. We will also post a report summarizing each substantive verbal contact we receive about this AD. Costs of Compliance

We estimate that this AD will affect no engines installed on airplanes of U.S. registry. We also estimate that it will take about two hours per engine to perform a BSI of the HPT stage 2 nozzle. The average labor rate is $85 per hour. Required parts cost about $504,486 per engine. Based on these figures, we estimate the cost of this AD to U.S. operators to be $0. 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 part 39 of the Federal Aviation Regulations (14 CFR part 39) as follows:

**PART 39—AIRWORTHINESS DIRECTIVES** 

■ 1. The authority citation for part 39 continues to read as follows:

Authority: 49 U.S.C. 106(g), 40113, 44701.

**§ 39.13 [Amended]**

■ 2. The FAA amends § 39.13 by removing airworthiness directive (AD) 2013–02–06, Amendment 39–17327 (78 FR 5710, January 28, 2013) and adding the following new AD: 2016–22–11 Engine Alliance: Amendment 39–18700; Docket No. FAA–2012–1293; Directorate Identifier 2012–NE–45–AD.

(a) Effective Date

This AD is effective November 16, 2016.

(b) Affected ADs

This AD replaces AD 2013–02–06, Amendment 39–17327 (78 FR 5710, January 28, 2013).
(c) Applicability

This AD applies to all Engine Alliance GP7270 and GP7277 turbofan engines with a high-pressure turbine (HPT) stage 2 nozzle segment, part number (P/N) 2101M24G01, 2101M24G02, 2101M24G03, 2101M24G04, 2101M24G05, or 2101M24G06, installed.

(d) Unsafe Condition

This AD was prompted by a report of inadequate cooling of the HPT stage 1 shroud and stage 2 nozzle, leading to damage to the HPT stage 2 nozzle, burn-through of the turbine case, and in-flight shutdown. We are issuing this AD to prevent HPT stage 2 nozzle failure, uncontrolled fire, in-flight shutdown, and damage to the airplane.
(e) Compliance

Comply with this AD within the compliance times specified, unless already done.

(1) Perform a 360 degree borescope inspection of the HPT stage 1 shroud and stage 2 nozzle as follows:

(i) For engines with nozzles installed at a shop visit that did not include full engine overhaul, borescope inspect the HPT stage 1 shroud and stage 2 nozzle as follows:

(A) If the nozzle has fewer than 1,050 cycles-since-new (CSN) or cycles-since-repair (CSR) on the effective date of this AD, before the nozzle has accumulated 1,100 CSN or CSR.

(B) If the nozzle has 1,050 or more CSN or CSR on the effective date of this AD, within the next 50 cycles.

(ii) For all other engines, borescope inspect the HPT stage 1 shroud and HPT stage 2 nozzle as follows:

(A) If the nozzle has fewer than 1,450 CSN or CSR on the effective date of this AD, before the nozzle has accumulated 1,500 CSN or CSR.

(B) If the nozzle has 1,450 or more CSN or CSR on the effective date of this AD, within the next 50 cycles.

(iii) Thereafter, repetitively borescope inspect the HPT stage 1 shroud and stage 2 nozzle as follows:

(A) For engines with HPT stage 2 nozzle segments, P/N 2101M24G01, 2101M24G02, or 2101M24G03, within every 150 additional cycles-in-service (CIS).

(B) For engines with HPT stage 2 nozzle segments, P/N 2101M24G04, 2101M24G05, or 2101M24G06, within every 300 additional CIS.

(2) If any burn holes are detected through the surface of the nozzle or if the shroud is distorted radially inward with evidence of blade tip rubs, remove the HPT stage 1 shroud and HPT stage 2 nozzle from service before further flight.


### 75686 Federal Register / Vol. 81, No. 211 / Tuesday, November 1, 2016 / Rules and Regulations

(f) Mandatory Terminating Action

Replace HPT stage 2 nozzle segments, P/N 2101M24G01, 2101M24G02, 2101M24G03, 2101M24G04, 2101M24G05, and 2101M24G06, at the next piece-part exposure, with parts eligible for installation.
(g) Definition

For the purpose of this AD, piece-part exposure is when the HPT stage 2 nozzle is removed from the engine and completely disassembled.
(h) 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. You may email your request to: ANE-AD-AMOC@faa.gov.

(i) Related Information

For more information about this AD, contact Martin Adler, Aerospace Engineer, Engine & Propeller Directorate, FAA, 1200 District Avenue, Burlington, MA 01803; phone: 781–238–7157; fax: 781–238–7199; email: martin.adler@faa.gov.
(j) Material Incorporated by Reference

None. Issued in Burlington, Massachusetts, on October 25, 2016. Colleen M. D’Alessandro, Manager, Engine & Propeller Directorate, Aircraft Certification Service.
[FR Doc. 2016–26280 Filed 10–31–16; 8:45 am]

**BILLING CODE 4910–13–P**

**DEPARTMENT OF TRANSPORTATION**

**Federal Aviation Administration**

**14 CFR Part 39**

**[Docket No. FAA–2016–5423; Directorate Identifier 2016–NE–09–AD; Amendment 39–**  **18694; AD 2016–22–05]**

**RIN 2120–AA64**

**Airworthiness Directives; Pratt & Whitney Division Turbofan Engines** 

**AGENCY :**  Federal Aviation Administration (FAA), DOT.

**ACTION :**  Final rule.

**SUMMARY :**  We are adopting a new airworthiness directive (AD) for certain Pratt & Whitney (PW) PW4164, PW4164–1D, PW4168, PW4168–1D, PW4168A, PW4168A–1D, and PW4170 turbofan engines. This AD was prompted by several instances of fuel leaks on PW engines installed with the Talon IIB combustion chamber configuration. This AD requires initial and repetitive inspections of the affected fuel nozzles and their replacement with parts eligible for installation. We are issuing this AD to prevent failure of the fuel nozzles, which could lead to engine fire and damage to the airplane.

**DATES :**  This AD is effective December 6,
2016.

The Director of the Federal Register approved the incorporation by reference of a certain publication listed in this AD as of December 6, 2016.

**ADDRESSES :**  For service information identified in this final rule, contact Pratt & Whitney Division, 400 Main St., East Hartford, CT 06108; phone: 860–565– 8770; fax: 860–565–4503. You may view this service information at the FAA, Engine & Propeller Directorate, 1200 District Avenue, Burlington, MA. For information on the availability of this material at the FAA, call 781–238–7125. It is also available on the internet at http://www.regulations.gov by searching for and locating Docket No. FAA–2016–
5423. Examining the AD Docket

You may examine the AD docket on the Internet at http:// www.regulations.gov by searching for and locating Docket No. FAA–2016– 5423; 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 :**  Besian Luga, Aerospace Engineer, Engine Certification Office, FAA, Engine & Propeller Directorate, 1200 District Avenue, Burlington, MA 01803; phone: 781–238–7750; fax: 781–238–7199; email: besian.luga@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 certain PW PW4164, PW4164– 1D, PW4168, PW4168–1D, PW4168A, PW4168A–1D, and PW4170 turbofan engines. The NPRM published in the Federal Register on April 20, 2016 (81 FR 23217) (‘‘the NPRM’’). The NPRM was prompted by several instances of fuel leaks on PW engines installed with the Talon IIB combustion chamber configuration. The NPRM proposed to require initial and repetitive inspections of the affected fuel nozzles and their replacement with parts eligible for installation. We are issuing this AD to prevent failure of the fuel nozzles, which could lead to engine fire and damage to the airplane.

Comments

We gave the public the opportunity to participate in developing this AD. The following presents the comments received on the NPRM and the FAA’s response to each comment. Request To Change Definition of Engine Shop Visit

Delta Air Lines (Delta) requested that the definition of an ‘‘engine shop visit’’ be defined as the induction of an engine into the shop for maintenance involving the separation of pairs of major mating engine flanges. Delta requested this change so that the definition of an engine shop visit in this AD would be consistent with prior ADs.

We disagree. The redefined shop visit interval as requested would result in less frequent replacements of fuel nozzles and an unacceptable fleet risk. We did not change this AD.

Conclusion

We reviewed the relevant data, considered the comment received, and determined that air safety and the public interest require adopting this AD as proposed.

Related Service Information Under 1 CFR Part 51

We reviewed PW Alert Service Bulletin (ASB) PW4G–100–A73–45, dated February 16, 2016. The ASB describes procedures for inspecting and replacing the fuel nozzles. This service information is reasonably available because the interested parties have access to it through their normal course of business or by the means identified in the **ADDRESSES** section. Costs of Compliance

We estimate that this AD will affect 72 engines installed on airplanes of U.S. registry. We also estimate that it will take about 2.2 hours per engine to perform each inspection and 48 hours per engine to replace the fuel nozzle. The average labor rate is $85 per hour. We also estimate that parts cost would be $15,780 per engine. Based on these figures, we estimate the cost of this AD on U.S. operators to be $1,443,384. 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: