Airworthiness Directives; The Boeing Company Airplanes, 24789-24791 [2015-10066]

Download as PDF 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 Cancellation FLRA Internal Regulation 2790, dated December 29, 1986, is superseded.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] mstockstill on DSK4VPTVN1PROD with RULES RIN 2120–AA64 Airworthiness Directives; The Boeing Company Airplanes Federal Aviation Administration (FAA), DOT. ACTION: Final rule; request for comments. AGENCY: Examining the AD Docket We are adopting a new airworthiness directive (AD) for all The SUMMARY: VerDate Sep<11>2014 15:47 Apr 30, 2015 Jkt 235001 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 https://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 https:// www.regulations.gov by searching for and locating Docket No. FAA–2015– 0936. You may examine the AD docket on the Internet at https:// www.regulations.gov by searching for PO 00000 Frm 00011 Fmt 4700 Sfmt 4700 24789 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 E:\FR\FM\01MYR1.SGM 01MYR1 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 https:// 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 https://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: ESTIMATED COSTS Action Labor cost Electrical power deactivation. Parts cost Cost per product 1 work-hour × $85 per hour = $85 per deactivation cycle. $0 $85 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. mstockstill on DSK4VPTVN1PROD with RULES 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: VerDate Sep<11>2014 15:47 Apr 30, 2015 Jkt 235001 (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. PO 00000 Frm 00012 Fmt 4700 Sfmt 4700 Cost on U.S. operators $2,380 per deactivation cycle. 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 E:\FR\FM\01MYR1.SGM 01MYR1 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. mstockstill on DSK4VPTVN1PROD with RULES (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, VerDate Sep<11>2014 15:47 Apr 30, 2015 Jkt 235001 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 https:// 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 Federal Aviation Administration (FAA), DOT. ACTION: Final rule. AGENCY: 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 SUMMARY: PO 00000 Frm 00013 Fmt 4700 Sfmt 4700 24791 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 https:// 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 https:// 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 E:\FR\FM\01MYR1.SGM 01MYR1

Agencies

[Federal Register Volume 80, Number 84 (Friday, May 1, 2015)]
[Rules and Regulations]
[Pages 24789-24791]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2015-10066]


=======================================================================
-----------------------------------------------------------------------

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 https://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 https://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 https://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

[[Page 24790]]

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 https://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 https://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:

                                                 Estimated Costs
----------------------------------------------------------------------------------------------------------------
                                                                                                Cost on U.S.
            Action                  Labor cost          Parts cost      Cost per product          operators
----------------------------------------------------------------------------------------------------------------
Electrical power deactivation  1 work-hour x $85                 $0   $85 per deactivation  $2,380 per
                                per hour = $85 per                     cycle.                deactivation cycle.
                                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

0
1. The authority citation for part 39 continues to read as follows:

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


Sec.  39.13  [Amended]

0
2. The FAA amends Sec.  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

[[Page 24791]]

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-AMOC-Requests@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 https://www.archives.gov/federal-register/cfr/ibr-locations.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

This site is protected by reCAPTCHA and the Google Privacy Policy and Terms of Service apply.