### 24789 Federal Register / Vol. 80, No. 84 / Friday, May 1, 2015 / Rules and Regulations

regained; and that the action was based chiefly or solely on reliance on the overpayment.

(b) To establish that the employee’s position has changed for the worse, it must be shown that the decision would not have been made but for the overpayment, and that the decision resulted in a loss.

(c) An example of a ‘‘detrimental reliance’’ would be a decision to sign a lease for a more expensive apartment based chiefly or solely upon reliance on an erroneous calculation of salary, and the funds spent for rent cannot be recovered.

(3) The cost of collecting the claim equals or exceeds the amount of the claim;

(4) The time elapsed between the erroneous payment and discovery of the error and notification of the employee;

(5) Whether failure to make restitution would result in unfair gain to the employee;

(6) Whether recovery of the claim would be unconscionable under the circumstances.

d. The burden is on the employee to demonstrate that collection of the claim would be against equity and good conscience and not in the best interest of the United States.
8. Authorities

a. 5 U.S.C. 5584, ‘‘Claims for Overpayment of Pay and Allowances, and of Travel, Transportation and Relocation Expenses and Allowances.’’

b. 31 U.S.C. 3711, ‘‘Collection and Compromise.’’

c. 31 U.S.C. 3716, ‘‘Administrative Offset.’’ d. 31 U.S.C. 3717, ‘‘Interest and Penalty on Claims.’’

e. 5 CFR part 550, subpart K, ‘‘Collection by Offset from Indebted Government Employees.’’

f. 31 CFR part 5, subpart B, ‘‘Salary Offset.’’ g. Determination with Respect to Transfer of Functions Pursuant to Public Law 104– 316, OMB, December 17, 1996.

9. Cancellation

FLRA Internal Regulation 2790, dated December 29, 1986, is superseded.

[FR Doc. 2015–09999 Filed 4–30–15; 8:45 am]

**BILLING CODE 6727–01–P**

**DEPARTMENT OF TRANSPORTATION**

**Federal Aviation Administration**

**14 CFR Part 39**

**[Docket No. FAA–2015–0936; Directorate Identifier 2015–NM–058–AD; Amendment**  **39–18153; AD 2015–09–07]**

**RIN 2120–AA64**

**Airworthiness Directives; The Boeing Company Airplanes** 

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

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

**SUMMARY :**  We are adopting a new airworthiness directive (AD) for all The Boeing Company Model 787 airplanes. This AD requires a repetitive maintenance task for electrical power deactivation on Model 787 airplanes. This AD was prompted by the determination that a Model 787 airplane that has been powered continuously for 248 days can lose all alternating current (AC) electrical power due to the generator control units (GCUs) simultaneously going into failsafe mode. This condition is caused by a software counter internal to the GCUs that will overflow after 248 days of continuous power. We are issuing this AD to prevent loss of all AC electrical power, which could result in loss of control of the airplane.

**DATES :**  This AD is effective May 1, 2015.

The Director of the Federal Register approved the incorporation by reference of certain publications listed in this AD as of May 1, 2015.

We must receive comments on this AD by June 15, 2015.

**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.

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. 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–
0936. 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– 0936; 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 :**  Kelly McGuckin, Aerospace Engineer, Systems and Equipment Branch, ANM– 130S, FAA, Seattle Aircraft Certification Office (ACO), 1601 Lind Avenue SW., Renton, WA 98057–3356; phone: 425– 917–6490; fax: 425–917–6590; email: Kelly.McGuckin@faa.gov.

**SUPPLEMENTARY INFORMATION :** 

Discussion

We have been advised by Boeing of an issue identified during laboratory testing. The software counter internal to the generator control units (GCUs) will overflow after 248 days of continuous power, causing that GCU to go into failsafe mode. If the four main GCUs (associated with the engine mounted generators) were powered up at the same time, after 248 days of continuous power, all four GCUs will go into failsafe mode at the same time, resulting in a loss of all AC electrical power regardless of flight phase.

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 a repetitive maintenance task for electrical power deactivation.

Interim Action

We consider this AD interim action. The manufacturer is currently developing a GCU software upgrade that will address the unsafe condition identified in this AD. Once this software is developed, approved, and available, we might consider additional rulemaking.
FAA’s Justification and Determination of the Effective Date

An unsafe condition exists that requires the immediate adoption of this AD. The FAA has found that the risk to the flying public justifies waiving notice and comment prior to adoption of this rule. If the four main GCUs were


### 24790 Federal Register / Vol. 80, No. 84 / Friday, May 1, 2015 / Rules and Regulations

powered up at the same time, after 248 days of continuous power, all four GCUs will go into failsafe mode at the same time, resulting in a loss of all AC electrical power regardless of flight phase. Loss of all AC electrical power can result in loss of control of the airplane. Therefore, we find that notice and opportunity for prior public comment are impracticable 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 was not preceded by notice and an opportunity for public comment. 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–2015–0936 and Directorate Identifier 2015–NM–058–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. Related Service Information Under 1 CFR Part 51

We reviewed Boeing Multi Operator Message MOM–MOM–15–0248–01B, dated April 19, 2015; and Boeing Multi Operator Message MOM–MOM–15– 0248–01B(R1), dated April 20, 2015. The service information describes procedures for electrical power deactivation of Model 787 airplanes. This service information is reasonably available at http://www.regulations.gov by searching for and locating Docket No. FAA–2015–0936. Or see **ADDRESSES** for other ways to access this service information. Costs of Compliance

We estimate that this AD affects 28 airplanes of U.S. registry. We estimate the following costs to comply with this AD:



### E STIMATED 

### COSTS

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

Electrical power

deactivation. 1 work-hour × $85 per hour = $85 per deactivation cycle. $0 $85 per deactivation cycle ........... $2,380 per deactivation cycle.

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):
2015–09–07 The Boeing Company: Amendment 39–18153; Docket No. FAA–2015–0936; Directorate Identifier 2015–NM–058–AD.
(a) Effective Date

This AD is effective May 1, 2015.

(b) Affected ADs

None.
(c) Applicability

This AD applies to all The Boeing Company Model 787 airplanes, certificated in any category. (d) Subject

Air Transport Association (ATA) of America Code 24, Electrical power.

(e) Unsafe Condition

This AD was prompted by the determination that a Model 787 airplane that has been powered continuously for 248 days can lose all alternating current (AC) electrical power due to the generator control units (GCUs) simultaneously going into failsafe mode. This condition is caused by a software counter internal to the GCUs that will overflow after 248 days of continuous power. We are issuing this AD to prevent loss of all AC electrical power, which could result in loss of control of the airplane.
(f) Compliance

Comply with this AD within the compliance times specified, unless already done.
(g) Repetitive Maintenance Task: Electrical Power Deactivation

At the latest of the times specified in paragraphs (g)(1), (g)(2), and (g)(3) of this AD, accomplish electrical power deactivation on


### 24791 Federal Register / Vol. 80, No. 84 / Friday, May 1, 2015 / Rules and Regulations

the airplane, in accordance with step 2) in ‘‘DESIRED ACTION’’ of Boeing Multi Operator Message MOM–MOM–15–0248– 01B, dated April 19, 2015; or Boeing Multi Operator Message MOM–MOM–15–0248– 01B(R1), dated April 20, 2015. The main and auxiliary power unit (APU) batteries do not need to be disconnected when performing the electrical power deactivation. Repeat the electrical power deactivation thereafter at intervals not to exceed 120 days.

(1) Within 120 days after the last electrical power deactivation in accordance with step 2) in ‘‘DESIRED ACTION’’ of Boeing Multi Operator Message MOM–MOM–15–0248– 01B, dated April 19, 2015; or Boeing Multi Operator Message MOM–MOM–15–0248– 01B(R1), dated April 20, 2015.

(2) Within 120 days after the date of issuance of the original certificate of airworthiness or the date of issuance of the original export certificate of airworthiness.

(3) Within 7 days after the effective date of this AD.
(h) Special Flight Permit

Special flight permits, as described in Section 21.197 and Section 21.199 of the Federal Aviation Regulations (14 CFR 21.197 and 21.199), are not allowed.
(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.
(j) Related Information

For more information about this AD, contact Kelly McGuckin, Aerospace Engineer, Systems and Equipment Branch, ANM–130S, FAA, Seattle Aircraft Certification Office (ACO), 1601 Lind Avenue SW., Renton, WA 98057–3356; phone: 425– 917–6490; fax: 425–917–6590; email: Kelly.McGuckin@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 Multi Operator Message MOM– MOM–15–0248–01B, dated April 19, 2015. The date appears only on the first page of this document.

(ii) Boeing Multi Operator Message MOM– MOM–15–0248–01B(R1), dated April 20, 2015. The date appears only on the first page of this document.

(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 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.

(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 April 23,
2015. Jeffrey E. Duven, Manager, Transport Airplane Directorate, Aircraft Certification Service.

[FR Doc. 2015–10066 Filed 4–30–15; 8:45 am]

**BILLING CODE 4910–13–P**

**DEPARTMENT OF TRANSPORTATION**

**Federal Aviation Administration**

**14 CFR Part 39**

**[Docket No. FAA–2013–0766; Directorate Identifier 2013–NE–26–AD; Amendment 39–**  **18149; AD 2014–17–08R1]**

**RIN 2120–AA64**

**Airworthiness Directives; Pratt & Whitney Canada Corp. Turboprop**  **Engines**

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

**ACTION :**  Final rule.

**SUMMARY :**  We are revising airworthiness directive (AD) 2014–17–08 for all Pratt & Whitney Canada Corp. (P&WC) PT6A– 114 and PT6A–114A turboprop engines. AD 2014–17–08 required initial and repetitive borescope inspections (BSIs) of compressor turbine (CT) blades, and the removal from service of blades that fail inspection. This new AD adds an additional single crystal CT blade, reduces the affected population, and corrects the Credit for Previous Action paragraph. This AD was prompted by P&WC development of an additional single crystal CT blade that corrects the unsafe condition. We are issuing this AD to prevent failure of CT blades, which could result in damage to the engine and damage to the airplane.

**DATES :**  This AD is effective June 5, 2015.

The Director of the Federal Register approved the incorporation by reference of a certain other publications listed in this AD as of October 8, 2014 (79 FR 52172, September 3, 2014).

**ADDRESSES :**  For service information identified in this AD, contact Pratt &Whitney Canada Corp., 1000 MarieVictorin, Longueuil, Quebec, Canada, J4G 1A1; phone: 800–268–8000; fax: 450–647–2888; Internet: www.pwc.ca. You may view this service information at the 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. Certain service information is also available on the Internet at http:// www.regulations.gov by searching for and locating Docket No. FAA–2013–
0766. 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–2013– 0766; 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 :**  Barbara Caufield, Aerospace Engineer, Engine Certification Office, FAA, Engine & Propeller Directorate, 12 New England Executive Park, Burlington, MA 01803; phone: 781–238–7146; fax: 781–238– 7199; email: barbara.caufield@faa.gov.

**SUPPLEMENTARY INFORMATION :** 

Discussion

We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR part 39 to revise AD 2014–17–08, Amendment 39–17961 (79 FR 52172, September 3, 2014), (‘‘AD 2014–17– 08’’). AD 2014–17–08 applied to all P&WC PT6A–114 and PT6A–114A turboprop engines. The NPRM published in the Federal Register on December 1, 2014 (79 FR 71031). The NPRM was prompted by P&WC development of an additional single crystal CT blade that corrects the unsafe condition. The addition of this new part number (P/N) reduces the affected population. The NPRM proposed to retain all the requirements of AD 2014– 17–08. The NPRM also proposed to add