Airworthiness Directives; The Boeing Company Airplanes, 16173-16175 [2014-06476]

Download as PDF 16173 Rules and Regulations Federal Register Vol. 79, No. 57 Tuesday, March 25, 2014 This section of the FEDERAL REGISTER contains regulatory documents having general applicability and legal effect, most of which are keyed to and codified in the Code of Federal Regulations, which is published under 50 titles pursuant to 44 U.S.C. 1510. The Code of Federal Regulations is sold by the Superintendent of Documents. Prices of new books are listed in the first FEDERAL REGISTER issue of each week. DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2014–0169; Directorate Identifier 2014–NM–020–AD; Amendment 39–17808; AD 2014–06–04] RIN 2120–AA64 Airworthiness Directives; The Boeing Company Airplanes Federal Aviation Administration (FAA), DOT. ACTION: Final rule; request for comments. AGENCY: We are adopting a new airworthiness directive (AD) for certain The Boeing Company Model 747–8 and 747–8F series airplanes powered by certain General Electric (GE) engines. This AD requires removing certain defective software and installing new, improved software. This AD was prompted by a determination that the existing electronic engine control (EEC) software logic can prevent stowage of the thrust reversers (TRs) during certain circumstances, which could cause the TRs to move back to the deployed position. We are issuing this AD to prevent in-flight deployment of one or more TRs due to loss of the TR auto restow function, which could result in inadequate climb performance at an altitude insufficient for recovery, and consequent uncontrolled flight into terrain. SUMMARY: This AD is effective April 9, 2014. We must receive comments on this AD by May 9, 2014. ADDRESSES: You may send comments, using the procedures found in 14 CFR 11.43 and 11.45, by any of the following methods: tkelley on DSK3SPTVN1PROD with RULES DATES: VerDate Mar<15>2010 16:21 Mar 24, 2014 Jkt 232001 • Federal eRulemaking Portal: Go to http://www.regulations.gov. Follow the instructions for submitting comments. • Fax: 202–493–2251. • Mail: U.S. Department of Transportation, Docket Operations, M–30, West Building Ground Floor, Room W12–140, 1200 New Jersey Avenue SE., Washington, DC 20590. • Hand Delivery: U.S. Department of Transportation, Docket Operations, M–30, West Building Ground Floor, Room W12–140, 1200 New Jersey Avenue SE., Washington, DC 20590, between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. Examining the AD Docket You may examine the AD docket on the Internet at http:// www.regulations.gov by searching for and locating Docket No. FAA–2014– 0169; 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: Sue Lucier, Aerospace Engineer, Propulsion Branch, ANM–140S, FAA, Seattle Aircraft Certification Office (ACO), 1601 Lind Avenue SW., Renton, WA 98057– 3356; phone: 425–917–6438; fax: 425– 917–6590; email: suzanne.lucier@ faa.gov. SUPPLEMENTARY INFORMATION: Discussion We determined that the existing EEC software logic can prevent stowage of the TRs if the airplane changes back into air mode during a rejected or bounced landing for certain The Boeing Company Model 747–8 and 747–8F series airplanes powered by certain GE engines. If this occurs and the hydraulic isolation valve closes before the TRs are fully stowed, there is no hydraulic pressure for the auto-restow function and aerodynamic loads could cause the TRs to move back to the deployed position. We are issuing this AD to prevent in-flight deployment of one or more TRs due to loss of the TR auto restow function, which could result in inadequate climb performance at an PO 00000 Frm 00001 Fmt 4700 Sfmt 4700 altitude insufficient for recovery, and consequent uncontrolled flight into terrain. 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 identifying the EEC software, and removing certain defective software and installing new, improved software. The removal and installation must be done in one of the following ways: • In accordance with a method that we approve; or • Using data that meet the certification basis of the airplane, and that have been approved by the Boeing Commercial Airplanes Organization Designation Authorization (ODA) whom we have authorized to make those findings. 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 because the in-flight deployment of a TR due to loss of the TR auto restow function could result in inadequate climb performance at an altitude insufficient for recovery, and consequent uncontrolled flight into terrain. 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 and Directorate Identifier 2014–NM–020–AD at the beginning of your comments. We specifically invite comments on the overall regulatory, economic, E:\FR\FM\25MRR1.SGM 25MRR1 16174 Federal Register / Vol. 79, No. 57 / Tuesday, March 25, 2014 / Rules and Regulations environmental, and energy aspects of this AD. We will consider all comments received by the closing date and may amend this AD because of those comments. We will post all comments we receive, without change, to http:// www.regulations.gov, including any personal information you provide. We will also post a report summarizing each substantive verbal contact we receive about this AD. Costs of Compliance We estimate that this AD affects 7 airplanes of U.S. registry. We estimate the following costs to comply with this AD: ESTIMATED COSTS Action Labor cost Parts cost Cost per product Cost on U.S. operators Remove/install new software .......................... 6 work-hours × $85 per hour = $510 ............. $0 $510 $3,570 Authority for This Rulemaking List of Subjects in 14 CFR Part 39 altitude insufficient for recovery, and uncontrolled flight into terrain. 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. Air transportation, Aircraft, Aviation safety, Incorporation by reference, Safety. (f) Compliance tkelley on DSK3SPTVN1PROD 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: (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. VerDate Mar<15>2010 16:21 Mar 24, 2014 Jkt 232001 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): ■ 2014–06–04 The Boeing Company: Amendment 39–17808; Docket No. FAA–2014–0169; Directorate Identifier 2014–NM–020–AD. (a) Effective Date This AD is effective April 9, 2014. (b) Affected ADs None. (c) Applicability This AD applies to The Boeing Company Model 747–8 and 747–8F series airplanes, certificated in any category, powered by General Electric (GE) Aviation GEnx-2B67 or GEnx-2B67B engines. (d) Subject Joint Aircraft System Component (JASC) Code 7600, Engine Controls. (e) Unsafe Condition This AD was prompted by a determination that the existing electronic engine control (EEC) software logic can prevent stowage of the thrust reversers (TRs) during certain circumstances, which could cause the TRs to move back to the deployed position. We are issuing this AD to prevent in-flight deployment of one or more TRs due to loss of the TR auto restow function, which could result in inadequate climb performance at an PO 00000 Frm 00002 Fmt 4700 Sfmt 4700 Comply with this AD within the compliance times specified, unless already done. (g) Removal/Installation of Certain EEC Software For airplanes having any EEC software part number identified in paragraph (g)(1), (g)(2), or (g)(3) of this AD: Within 90 days after the effective date of this AD, remove the EEC software, as applicable; and install new EEC software that is approved by the FAA. (1) Software C032: GE P/N 2124M22P05, EEC kit number 738L370G02, Boeing P/N GEC43–2124–2205. (2) Software C040: GE P/N 2124M22P07, EEC kit number 738L370G04, Boeing P/N GEC43–2124–2207. (3) Software C045: GE P/N 2124M22P08, EEC kit number 738L370G05, Boeing P/N GEC43–2124–2208. (h) Parts Installation As of the effective date of this AD, no person may install EEC software having any P/N identified in paragraph (g)(1), (g)(2), or (g)(3) of this AD on any airplane. (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)(1) 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 Sue Lucier, Aerospace Engineer, Propulsion Branch, ANM–140S, FAA, Seattle Aircraft Certification Office (ACO), 1601 Lind Avenue SW., Renton, WA 98057–3356; E:\FR\FM\25MRR1.SGM 25MRR1 Federal Register / Vol. 79, No. 57 / Tuesday, March 25, 2014 / Rules and Regulations phone: 425–917–6438; fax: 425–917–6590; email: suzanne.lucier@faa.gov. (k) Material Incorporated by Reference None. Issued in Renton, Washington, on March 14, 2014. Jeffrey E. Duven, Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 2014–06476 Filed 3–24–14; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 97 [Docket No. 30947; Amdt. No. 3581] Standard Instrument Approach Procedures, and Takeoff Minimums and Obstacle Departure Procedures; Miscellaneous Amendments Federal Aviation Administration (FAA), DOT. ACTION: Final rule. AGENCY: FOR FURTHER INFORMATION CONTACT: This rule establishes, amends, suspends, or revokes Standard Instrument Approach Procedures (SIAPs) and associated Takeoff Minimums and Obstacle Departure Procedures for operations at certain airports. These regulatory actions are needed because of the adoption of new or revised criteria, or because of changes occurring in the National Airspace System, such as the commissioning of new navigational facilities, adding new obstacles, or changing air traffic requirements. These changes are designed to provide safe and efficient use of the navigable airspace and to promote safe flight operations under instrument flight rules at the affected airports. SUMMARY: This rule is effective March 25, 2014. The compliance date for each SIAP, associated Takeoff Minimums, and ODP is specified in the amendatory provisions. The incorporation by reference of certain publications listed in the regulations is approved by the Director of the Federal Register as of March 25, 2014. ADDRESSES: Availability of matters incorporated by reference in the amendment is as follows: For Examination— 1. FAA Rules Docket, FAA Headquarters Building, 800 Independence Avenue SW., Washington, DC 20591; tkelley on DSK3SPTVN1PROD with RULES DATES: VerDate Mar<15>2010 16:21 Mar 24, 2014 Jkt 232001 2. The FAA Regional Office of the region in which the affected airport is located; 3. The National Flight Procedures Office, 6500 South MacArthur Blvd., Oklahoma City, OK 73169 or, 4. 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/code_of_federal_ regulations/ibr_locations.html. Availability—All SIAPs and Takeoff Minimums and ODPs are available online free of charge. Visit http:// www.nfdc.faa.gov to register. Additionally, individual SIAP and Takeoff Minimums and ODP copies may be obtained from: 1. FAA Public Inquiry Center (APA– 200), FAA Headquarters Building, 800 Independence Avenue SW., Washington, DC 20591; or 2. The FAA Regional Office of the region in which the affected airport is located. Richard A. Dunham III, Flight Procedure Standards Branch (AFS–420), Flight Technologies and Programs Divisions, Flight Standards Service, Federal Aviation Administration, Mike Monroney Aeronautical Center, 6500 South MacArthur Blvd. Oklahoma City, OK. 73169 (Mail Address: P.O. Box 25082, Oklahoma City, OK 73125) Telephone: (405) 954–4164. SUPPLEMENTARY INFORMATION: This rule amends Title 14 of the Code of Federal Regulations, Part 97 (14 CFR part 97), by establishing, amending, suspending, or revoking SIAPS, Takeoff Minimums and/or ODPS. The complete regulators description of each SIAP and its associated Takeoff Minimums or ODP for an identified airport is listed on FAA form documents which are incorporated by reference in this amendment under 5 U.S.C. 552(a), 1 CFR part 51, and 14 CFR 97.20. The applicable FAA Forms are FAA Forms 8260–3, 8260–4, 8260– 5, 8260–15A, and 8260–15B when required by an entry on 8260–15A. The large number of SIAPs, Takeoff Minimums and ODPs, in addition to their complex nature and the need for a special format make publication in the Federal Register expensive and impractical. Furthermore, airmen do not use the regulatory text of the SIAPs, Takeoff Minimums or ODPs, but instead refer to their depiction on charts printed by publishers of aeronautical materials. The advantages of incorporation by reference are realized and publication of the complete description of each SIAP, Takeoff Minimums and ODP listed on PO 00000 Frm 00003 Fmt 4700 Sfmt 4700 16175 FAA forms is unnecessary. This amendment provides the affected CFR sections and specifies the types of SIAPs and the effective dates of the, associated Takeoff Minimums and ODPs. This amendment also identifies the airport and its location, the procedure, and the amendment number. The Rule This amendment to 14 CFR part 97 is effective upon publication of each separate SIAP, Takeoff Minimums and ODP as contained in the transmittal. Some SIAP and Takeoff Minimums and textual ODP amendments may have been issued previously by the FAA in a Flight Data Center (FDC) Notice to Airmen (NOTAM) as an emergency action of immediate flight safety relating directly to published aeronautical charts. The circumstances which created the need for some SIAP and Takeoff Minimums and ODP amendments may require making them effective in less than 30 days. For the remaining SIAPS and Takeoff Minimums and ODPS, an effective date at least 30 days after publication is provided. Further, the SIAPs and Takeoff Minimums and ODPS contained in this amendment are based on the criteria contained in the U.S. Standard for Terminal Instrument Procedures (TERPS). In developing these SIAPS and Takeoff Minimums and ODPs, the TERPS criteria were applied to the conditions existing or anticipated at the affected airports. Because of the close and immediate relationship between these SIAPs, Takeoff Minimums and ODPs, and safety in air commerce, I find that notice and public procedures before adopting these SIAPS, Takeoff Minimums and ODPs are impracticable and contrary to the public interest and, where applicable, that good cause exists for making some SIAPs effective in less than 30 days. Conclusion The FAA has determined that this regulation only involves an established body of technical regulations for which frequent and routine amendments are necessary to keep them operationally current. It, therefore—(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) ; and (3) does not warrant preparation of a regulatory evaluation as the anticipated impact is so minimal. For the same reason, the FAA certifies that this amendment will not have a significant economic impact on a substantial E:\FR\FM\25MRR1.SGM 25MRR1

Agencies

[Federal Register Volume 79, Number 57 (Tuesday, March 25, 2014)]
[Rules and Regulations]
[Pages 16173-16175]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 2014-06476]



========================================================================
Rules and Regulations
                                                Federal Register
________________________________________________________________________

This section of the FEDERAL REGISTER contains regulatory documents 
having general applicability and legal effect, most of which are keyed 
to and codified in the Code of Federal Regulations, which is published 
under 50 titles pursuant to 44 U.S.C. 1510.

The Code of Federal Regulations is sold by the Superintendent of Documents. 
Prices of new books are listed in the first FEDERAL REGISTER issue of each 
week.

========================================================================


Federal Register / Vol. 79, No. 57 / Tuesday, March 25, 2014 / Rules 
and Regulations

[[Page 16173]]



DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2014-0169; Directorate Identifier 2014-NM-020-AD; 
Amendment 39-17808; AD 2014-06-04]
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 certain 
The Boeing Company Model 747-8 and 747-8F series airplanes powered by 
certain General Electric (GE) engines. This AD requires removing 
certain defective software and installing new, improved software. This 
AD was prompted by a determination that the existing electronic engine 
control (EEC) software logic can prevent stowage of the thrust 
reversers (TRs) during certain circumstances, which could cause the TRs 
to move back to the deployed position. We are issuing this AD to 
prevent in-flight deployment of one or more TRs due to loss of the TR 
auto restow function, which could result in inadequate climb 
performance at an altitude insufficient for recovery, and consequent 
uncontrolled flight into terrain.

DATES: This AD is effective April 9, 2014.
    We must receive comments on this AD by May 9, 2014.

ADDRESSES: You may send comments, using the procedures found in 14 CFR 
11.43 and 11.45, by any of the following methods:
     Federal eRulemaking Portal: Go to http://www.regulations.gov. Follow the instructions for submitting comments.
     Fax: 202-493-2251.
     Mail: U.S. Department of Transportation, Docket 
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New 
Jersey Avenue SE., Washington, DC 20590.
     Hand Delivery: U.S. Department of Transportation, Docket 
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New 
Jersey Avenue SE., Washington, DC 20590, between 9 a.m. and 5 p.m., 
Monday through Friday, except Federal holidays.

Examining the AD Docket

    You may examine the AD docket on the Internet at http://www.regulations.gov by searching for and locating Docket No. FAA-2014-
0169; 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: Sue Lucier, Aerospace Engineer, 
Propulsion Branch, ANM-140S, FAA, Seattle Aircraft Certification Office 
(ACO), 1601 Lind Avenue SW., Renton, WA 98057-3356; phone: 425-917-
6438; fax: 425-917-6590; email: suzanne.lucier@faa.gov.

SUPPLEMENTARY INFORMATION:

Discussion

    We determined that the existing EEC software logic can prevent 
stowage of the TRs if the airplane changes back into air mode during a 
rejected or bounced landing for certain The Boeing Company Model 747-8 
and 747-8F series airplanes powered by certain GE engines. If this 
occurs and the hydraulic isolation valve closes before the TRs are 
fully stowed, there is no hydraulic pressure for the auto-restow 
function and aerodynamic loads could cause the TRs to move back to the 
deployed position. We are issuing this AD to prevent in-flight 
deployment of one or more TRs due to loss of the TR auto restow 
function, which could result in inadequate climb performance at an 
altitude insufficient for recovery, and consequent uncontrolled flight 
into terrain.

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 identifying the EEC software, and removing certain 
defective software and installing new, improved software. The removal 
and installation must be done in one of the following ways:
     In accordance with a method that we approve; or
     Using data that meet the certification basis of the 
airplane, and that have been approved by the Boeing Commercial 
Airplanes Organization Designation Authorization (ODA) whom we have 
authorized to make those findings.

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 because the 
in-flight deployment of a TR due to loss of the TR auto restow function 
could result in inadequate climb performance at an altitude 
insufficient for recovery, and consequent uncontrolled flight into 
terrain. 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 and Directorate 
Identifier 2014-NM-020-AD at the beginning of your comments. We 
specifically invite comments on the overall regulatory, economic,

[[Page 16174]]

environmental, and energy aspects of this AD. We will consider all 
comments received by the closing date and may amend this AD because of 
those comments.
    We will post all comments we receive, without change, to http://www.regulations.gov, including any personal information you provide. We 
will also post a report summarizing each substantive verbal contact we 
receive about this AD.

Costs of Compliance

    We estimate that this AD affects 7 airplanes of U.S. registry.
    We estimate the following costs to comply with this AD:

                                                 Estimated Costs
----------------------------------------------------------------------------------------------------------------
                                                                                    Cost per       Cost on U.S.
               Action                        Labor cost           Parts cost        product         operators
----------------------------------------------------------------------------------------------------------------
Remove/install new software.........  6 work-hours x $85 per               $0             $510           $3,570
                                       hour = $510.
----------------------------------------------------------------------------------------------------------------

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):


2014-06-04 The Boeing Company: Amendment 39-17808; Docket No. FAA-
2014-0169; Directorate Identifier 2014-NM-020-AD.

(a) Effective Date

    This AD is effective April 9, 2014.

(b) Affected ADs

    None.

(c) Applicability

    This AD applies to The Boeing Company Model 747-8 and 747-8F 
series airplanes, certificated in any category, powered by General 
Electric (GE) Aviation GEnx-2B67 or GEnx-2B67B engines.

(d) Subject

    Joint Aircraft System Component (JASC) Code 7600, Engine 
Controls.

(e) Unsafe Condition

    This AD was prompted by a determination that the existing 
electronic engine control (EEC) software logic can prevent stowage 
of the thrust reversers (TRs) during certain circumstances, which 
could cause the TRs to move back to the deployed position. We are 
issuing this AD to prevent in-flight deployment of one or more TRs 
due to loss of the TR auto restow function, which could result in 
inadequate climb performance at an altitude insufficient for 
recovery, and uncontrolled flight into terrain.

(f) Compliance

    Comply with this AD within the compliance times specified, 
unless already done.

(g) Removal/Installation of Certain EEC Software

    For airplanes having any EEC software part number identified in 
paragraph (g)(1), (g)(2), or (g)(3) of this AD: Within 90 days after 
the effective date of this AD, remove the EEC software, as 
applicable; and install new EEC software that is approved by the 
FAA.
    (1) Software C032: GE P/N 2124M22P05, EEC kit number 738L370G02, 
Boeing P/N GEC43-2124-2205.
    (2) Software C040: GE P/N 2124M22P07, EEC kit number 738L370G04, 
Boeing P/N GEC43-2124-2207.
    (3) Software C045: GE P/N 2124M22P08, EEC kit number 738L370G05, 
Boeing P/N GEC43-2124-2208.

(h) Parts Installation

    As of the effective date of this AD, no person may install EEC 
software having any P/N identified in paragraph (g)(1), (g)(2), or 
(g)(3) of this AD on any airplane.

(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)(1) 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 Sue Lucier, 
Aerospace Engineer, Propulsion Branch, ANM-140S, FAA, Seattle 
Aircraft Certification Office (ACO), 1601 Lind Avenue SW., Renton, 
WA 98057-3356;

[[Page 16175]]

phone: 425-917-6438; fax: 425-917-6590; email: 
suzanne.lucier@faa.gov.

(k) Material Incorporated by Reference

    None.

    Issued in Renton, Washington, on March 14, 2014.
Jeffrey E. Duven,
Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 2014-06476 Filed 3-24-14; 8:45 am]
BILLING CODE 4910-13-P