75684 Federal Register / Vol. 81, No. 211 / Tuesday, November 1, 2016 / Rules and Regulations 

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 to 

damage 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 2 

nozzle 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 2 

nozzle 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 


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

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. 


jstallworth on DSK7TPTVN1PROD with RULES
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: 


jstallworth on DSK7TPTVN1PROD with RULES