8642 Federal Register / Vol. 81, No. 34 / Monday, February 22, 2016 / Rules and Regulations 

violations occurring after February 22, 

2016. 

SUBCHAPTER C—ENTERPRISES 

PART 1250—FLOOD INSURANCE 

■ 4. The authority citation for part 1250 

continues to read as follows: 

Authority: 12 U.S.C. 4521(a)(4) and 4526; 

28 U.S.C. 2461 note; 42 U.S.C. 4001 note; 42 

U.S.C. 4012a(f)(3), (4), (5), (8), (9), and (10). 

■ 5. Revise § 1250.3(c) to read as 

follows: 

§ 1250.3 Civil money penalties. 

* * * * * 

(c) Amount. The maximum civil 

money penalty amount is $485 for each 

violation that occurs before February 22, 

2016, with total penalties not to exceed 

$140,000. For violations that occur on or 

after February 22, 2016, the civil money 

penalty under this section may not 

exceed $585 for each violation, with 

total penalties assessed under this 

section against an Enterprise during any 

calendar year not to exceed $150,000. 

* * * * * 

Dated: February 15, 2016. 

Melvin L. Watt, 

Director, Federal Housing Finance Agency. 

[FR Doc. 2016–03631 Filed 2–19–16; 8:45 am] 

BILLING CODE 8070–01–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2015–2456; Directorate 

Identifier 2015–NM–032–AD; Amendment 

39–18401; AD 2016–04–07] 

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 767 airplanes. 

This AD was prompted by reports of 

cracking at a central part of the 

structure. This AD requires repetitive 

inspections of the skin hidden by the 

upper and lower splice fittings on both 

sides of the fuselage, and corrective 

action if necessary. We are issuing this 

AD to detect and correct fatigue 

cracking of the hidden fuselage skin and 

cracking, corrosion, and other damage to 

the splice fittings and adjacent visible 

fuselage skin and structure that could 

lead to loss of a primary load path 

between the fuselage and the wing box, 

and consequent reduced structural 

integrity of the airplane. 

DATES: This AD is effective March 28, 

2016. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication listed in this AD 

as of March 28, 2016. 

ADDRESSES: For service information 

identified in this final rule, 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. You 

may view this 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. It is also 

available on the Internet at http://

www.regulations.gov by searching for 

and locating Docket No. FAA–2015– 

2456. 

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–2015– 

2456; 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 

Docket 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: 

Wayne Lockett, Aerospace Engineer, 

Airframe Branch, ANM–120S, FAA, 

Seattle Aircraft Certification Office 

(ACO), 1601 Lind Avenue SW., Renton, 

WA 98057–3356; phone: 425–917–6447; 

fax: 425–917–6590; email: 

wayne.lockett@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 all The Boeing Company Model 

767 airplanes. The NPRM published in 

the Federal Register on July 6, 2015 (80 

FR 38408) (‘‘the NPRM’’). The NPRM 

was prompted by reports of cracking at 

a central part of the structure. The 

NPRM proposed to require repetitive 

inspections of the skin hidden by the 

upper and lower splice fittings on both 

sides of the fuselage, and corrective 

action if necessary. We are issuing this 

AD to detect and correct fatigue 

cracking of the hidden fuselage skin and 

cracking, corrosion, and other damage to 

the splice fittings and adjacent visible 

fuselage skin and structure that could 

lead to loss of a primary load path 

between the fuselage and the wing box, 

and consequent reduced structural 

integrity of 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. Boeing 

stated that it concurs with the NPRM. 

United Parcel Service (UPS) and United 

Airlines stated that they have no 

comments on the NPRM. FedEx Express 

provided information on how the NPRM 

affects its fleet but made no requests. 

Request Clarification on the Effect of 

Winglets on Accomplishment of the 

Proposed Actions 

Aviation Partners Boeing stated that 

accomplishing Supplemental Type 

Certificate (STC) ST01920SE (http://rgl.

faa.gov/Regulatory_and_Guidance_

Library/rgstc.nsf/0/59027f43b9a7486e

86257b1d006591ee/$FILE/

ST01920SE.pdf) does not affect the 

actions specified in the NPRM. 

We concur with the commenter. We 

have redesignated paragraph (c) of the 

proposed AD as paragraph (c)(1) of this 

AD and added new paragraph (c)(2) to 

this AD to state that installation of STC 

ST01920SE does not affect the ability to 

accomplish the actions required by this 

AD. Therefore, for airplanes on which 

STC ST01920SE 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. 

Conclusion 

We reviewed the relevant data, 

considered the comments received, and 

determined that air safety and the 

public interest require adopting this AD 

with the change described previously 

and minor editorial changes. We have 

determined that these minor changes: 

• Are consistent with the intent that 

was proposed in the NPRM for 

correcting the unsafe condition; and 

• Do not add any additional burden 

upon the public than was already 

proposed in the NPRM. 

We also determined that these 

changes will not increase the economic 

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Federal Register / Vol. 81, No. 34 / Monday, February 22, 2016 / Rules and Regulations 8643 

burden on any operator or increase the 

scope of this AD. 

Related Service Information Under 1 

CFR Part 51 

We reviewed Boeing Alert Service 

Bulletin 767–53A0263, dated January 

12, 2015. The service information 

describes procedures for repetitive 

inspections of the skin and splice 

fittings at stringer 29, body station 786 

ring chord. 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 affects 430 

airplanes of U.S. registry. We estimate 

the following costs to comply with this 

proposed AD: 

ESTIMATED COSTS

Action Labor cost Parts cost Cost per product Cost on U.S. operators 

Inspection ...................... 9 work-hours × $85 per hour = $765 per inspection cycle.$0 $765 per inspection 

cycle.

$328,950 per inspection 

cycle. 

We have received no definitive data 

that would enable us to provide cost 

estimates for the on-condition actions 

specified in this AD. 

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): 

2016–04–07 The Boeing Company: 

Amendment 39–18401; Docket No. 

FAA–2015–2456; Directorate Identifier 

2015–NM–032–AD. 

(a) Effective Date 

This AD is effective March 28, 2016. 

(b) Affected ADs 

None. 

(c) Applicability 

(1) This AD applies to all The Boeing 

Company Model 767–200, –300, –300F, and 

–400ER series airplanes, certificated in any 

category. 

(2) Installation of Supplemental Type 

Certificate (STC) ST01920SE (http://rgl.faa.

gov/Regulatory_and_Guidance_Library/rgstc.

nsf/0/59027f43b9a7486e86257b1d006591ee/

$FILE/ST01920SE.pdf) does not affect the 

ability to accomplish the actions required by 

this AD. Therefore, for airplanes on which 

STC ST01920SE 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. 

(d) Subject 

Air Transport Association (ATA) of 

America Code 53, Fuselage. 

(e) Unsafe Condition 

This AD was prompted by reports of 

cracking at a central part of the structure that 

includes the station 786 ring chord at the 

tension bolt hole common to the wing front 

spar lower chord and the internal bathtub 

fittings. We are issuing this AD to detect and 

correct fatigue cracking of the hidden 

fuselage skin and cracking, corrosion, and 

other damage to the splice fittings and 

adjacent visible fuselage skin and structure 

that could lead to loss of a primary load path 

between the fuselage and the wing box, and 

consequent reduced structural integrity of the 

airplane. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Inspection 

At the applicable time specified in 

paragraph 1.E., ‘‘Compliance,’’ of Boeing 

Alert Service Bulletin 767–53A0263, dated 

January 12, 2015, except as required by 

paragraph (h) of this AD, do external 

ultrasonic and detailed inspections to detect 

cracking, corrosion, or other damage at the 

splice fitting location, in accordance with the 

Accomplishment Instructions of Boeing Alert 

Service Bulletin 767–53A0263, dated January 

12, 2015. 

(1) If any cracking, corrosion, or other 

damage is not found, repeat the inspections 

at intervals not to exceed 6,000 flight cycles 

or 18,000 flight hours, whichever occurs first. 

Accomplishing a repair as specified in 

paragraph (g)(2) of this AD terminates the 

repetitive inspections in the repaired area 

only. 

(2) If any cracking, corrosion, or other 

damage is found, before further flight, repair 

using a method approved in accordance with 

the procedures specified in paragraph (i) of 

this AD. The repetitive inspections of 

paragraph (g)(1) are terminated in the 

repaired area only. 

(h) Exception to Service Information 

Specifications 

Where Boeing Alert Service Bulletin 767– 

53A0263, dated January 12, 2015, specifies a 

compliance time ‘‘after the original issue date 

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8644 Federal Register / Vol. 81, No. 34 / Monday, February 22, 2016 / Rules and Regulations 

of this Service Bulletin,’’ this AD requires 

compliance within the specified compliance 

time after the effective date of this AD. 

(i) 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 (j) 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, 

modification, or alteration 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. To be 

approved, the repair method, modification 

deviation, or alteration deviation must meet 

the certification basis of the airplane, and the 

approval must specifically refer to this AD. 

(4) For service information that contains 

steps that are labeled as Required for 

Compliance (RC), the provisions of 

paragraphs (i)(4)(i) and (i)(4)(ii) of this AD 

apply. 

(i) The steps labeled as RC, including 

substeps under an RC step and any figures 

identified in an RC step, must be done to 

comply with the AD. An AMOC is required 

for any deviations to RC steps, including 

substeps and identified figures. 

(ii) Steps not labeled as RC may be 

deviated from using accepted methods in 

accordance with the operator’s maintenance 

or inspection program without obtaining 

approval of an AMOC, provided the RC steps, 

including substeps and identified figures, can 

still be done as specified, and the airplane 

can be put back in an airworthy condition. 

(j) Related Information 

For more information about this AD, 

contact Wayne Lockett, Aerospace Engineer, 

Airframe Branch, ANM–120S, FAA, Seattle 

ACO, 1601 Lind Avenue SW., Renton, WA 

98057–3356; phone: 425–917–6447; fax: 425– 

917–6590; email: wayne.lockett@faa.gov. 

(k) 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 Alert Service Bulletin 767– 

53A0263, dated January 12, 2015. 

(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/ibr-locations.html. 

Issued in Renton, Washington on February 

10, 2016. 

Michael Kaszycki, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2016–03456 Filed 2–19–16; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF ENERGY 

Federal Energy Regulatory 

Commission 

18 CFR Part 157 

[Docket No. RM81–19–000] 

Natural Gas Pipelines; Project Cost 

and Annual Limits 

AGENCY: Federal Energy Regulatory 

Commission, Energy. 

ACTION: Final rule. 

SUMMARY: Pursuant to the authority 

delegated by 18 CFR 375.308(x)(1), the 

Director of the Office of Energy Projects 

(OEP) computes and publishes the 

project cost and annual limits for 

natural gas pipelines blanket 

construction certificates for each 

calendar year. 

DATES: This final rule is effective 

February 22, 2016 and establishes cost 

limits applicable from January 1, 2016 

through December 31, 2016. 

FOR FURTHER INFORMATION CONTACT: 

Marsha K. Palazzi, Chief, Certificates 

Branch 2, Division of Pipeline 

Certificates, (202) 502–6785. 

Section 157.208(d) of the 

Commission’s Regulations provides for 

project cost limits applicable to 

construction, acquisition, operation and 

miscellaneous rearrangement of 

facilities (Table I) authorized under the 

blanket certificate procedure (Order No. 

234, 19 FERC ¶ 61,216). Section 

157.215(a) specifies the calendar year 

dollar limit which may be expended on 

underground storage testing and 

development (Table II) authorized under 

the blanket certificate. Section 

157.208(d) requires that the ‘‘limits 

specified in Tables I and II shall be 

adjusted each calendar year to reflect 

the ‘GDP implicit price deflator’ 

published by the Department of 

Commerce for the previous calendar 

year.’’ 

Pursuant to 375.308(x)(1) of the 

Commission’s Regulations, the authority 

for the publication of such cost limits, 

as adjusted for inflation, is delegated to 

the Director of the Office of Energy 

Projects. The cost limits for calendar 

year 2014, as published in Table I of 

157.208(d) and Table II of § 157.215(a), 

are hereby issued. 

Effective Date 

This final rule is effective February 

22, 2016. The provisions of 5 U.S.C. 804 

regarding Congressional review of Final 

Rules does not apply to the Final Rule 

because the rule concerns agency 

procedure and practice and will not 

substantially affect the rights or 

obligations of non-agency parties. The 

Final Rule merely updates amounts 

published in the Code of Federal 

Regulations to reflect the Department of 

Commerce’s latest annual determination 

of the Gross Domestic Product (GDP) 

implicit price deflator, a mathematical 

updating required by the Commission’s 

existing regulations. 

List of Subjects in 18 CFR Part 157 

Administrative practice and 

procedure, Natural gas, Reporting and 

recordkeeping requirements. 

Issued: February 11, 2016. 

Ann Miles, 

Director, Office of Energy Projects. 

Accordingly, 18 CFR part 157 is 

amended as follows: 

PART 157—[AMENDED] 

■ 1. The authority citation for Part 157 

continues to read as follows: 

Authority: 15 U.S.C. 717–717w, 3301– 

3432; 42 U.S.C. 7101–7352. 

■ 2. Table I in § 157.208(d) is revised to 

read as follows: 

§ 157.208 Construction, acquisition, 

operation, replacement, and miscellaneous 

rearrangement of facilities. 

* * * * * 

(d) * * * 

TABLE I 

Year 

Limit 

Auto. proj. cost 

limit (Col.1) 

Prior notice proj. 

cost limit (Col.2) 

1982 $4,200,000 $12,000,000 

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