### 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


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

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:



### E STIMATED 

### C OSTS

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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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