Airworthiness Directives; The Boeing Company Airplanes

[Federal Register Volume 79, Number 57 (Tuesday, March 25, 2014)]
[Rules and Regulations]
[Pages 16173-16175]
From the Federal Register Online via the Government Publishing 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:
    <bullet> Federal eRulemaking Portal: Go to http://www.regulations.gov. Follow the instructions for submitting comments.
    <bullet> Fax: 202-493-2251.
    <bullet> 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.
    <bullet> 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: [email protected].

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:
    <bullet> In accordance with a method that we approve; or
    <bullet> 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: [email protected].
    (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: 
[email protected].

(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

The complete text was extracted from the official GovInfo HTML edition for this publication. Acquired 2026-10-09T02:48:56.292930+00:00. Text extraction preserves the recorded source wording; it does not determine current requirements.

Open the captured official edition

Source SHA-256

b7c3cd85017057b099cfdff5181e0a58cda7065a2abb80ff6084c6860d0e250f

Text SHA-256

0581eebc7778fefa4e8c821e77c41db088ccfa69da8b66e9d2af22d6c36bc302