[Federal Register Volume 78, Number 11 (Wednesday, January 16, 2013)]
[Proposed Rules]
[Pages 3363-3365]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2013-00803]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2012-1318; Directorate Identifier 2012-NM-104-AD]
RIN 2120-AA64


Airworthiness Directives; the Boeing Company Airplanes

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Notice of proposed rulemaking (NPRM).

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SUMMARY: We propose to adopt a new airworthiness directive (AD) for 
certain The Boeing Company Model 747-200B, 747-300, 747-400, 747-400D, 
747-400F series airplanes, and Model 767 series airplanes, powered by 
General Electric (GE) CF6-80C2 engines. This proposed AD was prompted 
by reports of failure of the electro-mechanical brake flex shaft (short 
flexshaft) of the thrust reverser actuation system (TRAS). This 
proposed AD would require replacing the short flexshaft on each engine 
with a new short flexshaft, testing of the electro-mechanical brake and 
center drive unit (CDU) cone brake to verify the holding torque, and 
performing related investigative and corrective actions if necessary. 
We are proposing this AD to prevent an uncommanded in-flight thrust 
reverser deployment and consequent loss of control of the airplane.

DATES: We must receive comments on this proposed AD by March 4, 2013.

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: Deliver to Mail address above between 9 
a.m. and 5 p.m., Monday through Friday, except Federal holidays.
    For service information identified in this proposed 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 review copies of the 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.

Examining the AD Docket

    You may examine the AD docket on the Internet at http://www.regulations.gov; 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 proposed 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: Tung Tran, Aerospace Engineer, 
Propulsion Branch, ANM-140S, Seattle Aircraft Certification Office 
(ACO), FAA, 1601 Lind Avenue SW., Renton, WA 98057-3356; phone: 425-
917-6505; fax: 425-917-6590; email: [email protected].

SUPPLEMENTARY INFORMATION: 

Comments Invited

    We invite you to send any written relevant data, views, or 
arguments about this proposal. Send your comments to an address listed 
under the ADDRESSES section. Include ``Docket No. FAA-2012-1318; 
Directorate Identifier 2012-NM-104-AD'' at the beginning of your 
comments. We specifically invite comments on the overall regulatory, 
economic, environmental, and energy aspects of this proposed AD. We 
will consider all comments received by the closing date and may amend 
this proposed 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 proposed AD.

Discussion

    We have received multiple reports of failure of the short flexshaft 
of the TRAS on Model 747 and 767 airplanes powered with GE CF6-80C2 
engines. The TRAS brake was installed as a third lock to prevent an 
uncommanded thrust reverser deployment on Model 747 and 767 airplanes 
powered by GE CF6-80C2 engines. The failed short flexshafts were found 
to have cores that had become sheared and unbraided. A new short 
flexshaft design has been developed that incorporates a better end 
fitting attachment and a larger core diameter with the core wound 
specifically for use on a left and right thrust reverser half to 
increase its resistance to failure. We are proposing this AD to prevent 
an uncommanded in-flight thrust reverser deployment and consequent loss 
of control of the airplane.

Other Related Rulemaking

    On August 13, 2003, we issued AD 2003-16-16, Amendment 39-13269 (68 
FR 51439, August 27, 2003), for Model 747-400 series airplanes equipped 
with GE Model CF6-80C2 series engines. AD 2003-16-16 requires 
repetitive tests of the cone brake of the CDU of the thrust reversers, 
and corrective actions if necessary; installation of a TRAS lock and 
various related modifications and installations. Following installation 
of the TRAS lock, this action also requires repetitive functional tests 
of the TRAS lock, and corrective action if necessary.
    On July 18, 2000, we issued AD 2000-15-04, Amendment 39-11833 (65 
FR 47252, August 2, 2000), for Model 747-200 and -300 series airplanes 
equipped with GE Model CF6-80C2 series engines with Power Management 
Control engine controls. AD 2000-15-04 requires various inspections and 
functional tests to detect discrepancies of the thrust reverser control 
and indication system, and correction of any discrepancy found; and 
installation of a terminating modification, and repetitive functional 
tests of that installation, and repair, if necessary.
    On April 26, 2000, we issued AD 2000-09-04, Amendment 39-11712 (65 
FR 25833, May 4, 2000), for Model 767 series airplanes equipped with GE 
Model CF6-80C2 series engines. AD 2000-09-04 requires tests, 
inspections, and adjustments of the thrust reverser system; and 
installation of a terminating modification, and repetitive follow-on 
actions.

Relevant Service Information

    We reviewed Boeing Alert Service Bulletin 747-78A2185, dated 
October 26, 2010; and Boeing Alert Service Bulletin 767-78A0100, dated 
October 26, 2010. This service information describes procedures for 
replacing the short flexshaft of each thrust reverser

[[Page 3364]]

half of each engine with a new short flexshaft.
    We reviewed Boeing Service Bulletin 747-78A2166, Revision 3, dated 
July 29, 2004 (for Model 747 airplanes); Boeing Alert Service Bulletin 
767-78A0081, Revision 2, dated April 19, 2001 (for Model 767-200, -300, 
and -300F airplanes); and Boeing Alert Service Bulletin 767-78A0088, 
dated April 19, 2001 (for Model 767-400ER airplanes). This service 
information describes a functional test of the electro-mechanical brake 
and CDU cone brake to verify the holding torque, and related 
investigative and corrective actions if necessary.
    The related investigative action for the electro-mechanical brake 
is a general visual inspection of the short flexshaft for twisting, 
breaking, or other damage.
    The corrective action for the electro-mechanical brake is 
replacement of the long flexshaft between the CDU and the upper angle 
gearbox with a new flexshaft; replacement of the short flexshaft 
between the upper angle gearbox and the electro-mechanical brake with a 
new flexshaft; and replacement of the electromechanical brake with a 
new electromechanical brake if the required torque value cannot be 
reached after the previous flexshaft replacements.
    The corrective action for a CDU cone brake test failure is 
replacement of the CDU cone brake with a new CDU cone brake.

FAA's Determination

    We are proposing 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 these same type 
designs.

Proposed AD Requirements

    This proposed AD would require accomplishing the actions specified 
in the service information described previously.

Costs of Compliance

    We estimate that this proposed AD affects 298 airplanes of U.S. 
registry.
    We estimate the following costs to comply with this proposed AD:

                                                 Estimated Costs
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                                                                                     Cost per      Cost on U.S.
                Action                         Labor cost           Parts cost        product        operators
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Replacement Model 747 airplanes (72     8 work-hours x $85 per           $15,244         $15,924      $1,146,528
 airplanes).                             hour = $680.
Replacement Model 767 airplanes (226    4 work-hours x $85 per             7,622           7,962       1,799,412
 airplanes).                             hour = $340.
Functional test Model 747 airplanes     12 work-hours x $85 per                0           1,020          73,440
 (72 airplanes).                         hour = $1,020.
Functional test Model 767 airplanes     12 work-hours x $85 per                0           1,020         230,520
 (226 airplanes).                        hour = $1,020.
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     We have received no definitive data that would enable us to 
provide cost estimates for the on-condition actions specified in this 
proposed AD.

Authority for This Rulemaking

    Title 49 of the United States Code specifies the FAA's authority to 
issue rules on aviation safety. Subtitle I, section 106, describes the 
authority of the FAA Administrator. Subtitle VII: Aviation Programs, 
describes in more detail the scope of the Agency's authority.
    We are issuing this rulemaking under the authority described in 
Subtitle VII, Part A, Subpart III, Section 44701: ``General 
requirements.'' Under that section, Congress charges the FAA with 
promoting safe flight of civil aircraft in air commerce by prescribing 
regulations for practices, methods, and procedures the Administrator 
finds necessary for safety in air commerce. This regulation is within 
the scope of that authority because it addresses an unsafe condition 
that is likely to exist or develop on products identified in this 
rulemaking action.

Regulatory Findings

    We determined that this proposed AD would not have federalism 
implications under Executive Order 13132. This proposed AD would 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 this proposed 
regulation:
    (1) Is not a ``significant regulatory action'' under Executive 
Order 12866,
    (2) Is not a ``significant rule'' under the 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.

The Proposed Amendment

    Accordingly, under the authority delegated to me by the 
Administrator, the FAA proposes to amend 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):

The Boeing Company: Docket No. FAA-2012-1318; Directorate Identifier 
2012-NM-104-AD.

(a) Comments Due Date

    We must receive comments by March 4, 2013.

(b) Affected ADs

    This AD affects AD 2003-16-16, Amendment 39-13269 (68 FR 51439, 
August 27, 2003); AD 2000-15-04, Amendment 39-11833 (65 FR 47252, 
August 2, 2000); and AD 2000-09-04, Amendment 39-11712 (65 FR 25833, 
May 4, 2000).

(c) Applicability

    This AD applies to The Boeing Company airplanes, certificated in 
any category, powered by General Electric (GE) CF6-80C2 engines, as 
identified in paragraphs (c)(1) and (c)(2) of this AD.
    (1) Model 747-200B, 747-300, 747-400, 747-400D, and 747-400F 
series airplanes, as identified in Boeing Alert Service Bulletin 
747-78A2185, dated October 26, 2010.

[[Page 3365]]

    (2) Model 767-200, -300, -300F, and -400ER series airplanes, as 
identified in Boeing Alert Service Bulletin 767-78A0100, dated 
October 26, 2010.

(d) Subject

    Joint Aircraft System Component (JASC)/Air Transport Association 
(ATA) of America Code 7830, Thrust reverser.

(e) Unsafe Condition

    This AD was prompted by reports of failure of the electro-
mechanical brake flex shaft (short flexshaft) of the thrust reverser 
actuation system (TRAS). We are issuing this AD to prevent an 
uncommanded in-flight thrust reverser deployment and consequent loss 
of control of the airplane.

(f) Compliance

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

(g) Flexible Drive Shaft Replacement

    Within 60 months after the effective date of this AD, replace 
the short flexshaft on each thrust reverser half of each engine with 
a new short flexshaft, in accordance with the Accomplishment 
Instructions of Boeing Alert Service Bulletin 747-78A2185, dated 
October 26, 2010; or Boeing Alert Service Bulletin 767-78A0100, 
dated October 26, 2010; as applicable.

(h) Functional Test

    Within 2,000 flight hours after accomplishment of the short 
flexshaft replacements required by paragraph (g) of this AD: Do a 
functional test on the electro-mechanical brakes and the cone brake 
of the center drive unit (CDU) to verify the holding torque, on all 
thrust reversers and on all engines, in accordance with the 
Accomplishment Instructions of Boeing Service Bulletin 747-78A2166, 
Revision 3, dated July 29, 2004 (for Model 747 airplanes); Boeing 
Alert Service Bulletin 767-78A0081, Revision 2, dated April 19, 2001 
(for Model 767-200, -300, and -300F airplanes); or Boeing Alert 
Service Bulletin 767-78A0088, dated April 19, 2001 (for Model 767-
400ER airplanes). Repeat the functional test thereafter at intervals 
not to exceed 2,000 flight hours.

(i) Corrective Action

    If any functional test required by paragraph (h) of this AD 
fails: Before further flight, do related investigative and 
corrective actions, in accordance with the Accomplishment 
Instructions of Boeing Service Bulletin 747-78A2166, Revision 3, 
dated July 29, 2004 (for Model 747 airplanes); Boeing Alert Service 
Bulletin 767-78A0081, Revision 2, dated April 19, 2001 (for Model 
767-200, -300, and -300F airplanes); or Boeing Alert Service 
Bulletin 767-78A0088, dated April 19, 2001 (for Model 767-400ER 
airplanes); and repeat the applicable test or check until 
successfully accomplished.

(j) Terminating Actions

    (1) Accomplishment of the initial test specified in paragraph 
(h) of this AD terminates the requirements of paragraph (e) of AD 
2003-16-16, Amendment 39-13269 (68 FR 51439, August 27, 2003).
    (2) Accomplishment of the initial test specified in paragraph 
(h) of this AD terminates the requirements of paragraph (g) of AD 
2000-15-04, Amendment 39-11833 (65 FR 47252, August 2, 2000).
    (3) Accomplishment of the initial test specified in paragraph 
(h) of this AD terminates the requirements of paragraph (f) of AD 
2000-09-04, Amendment 39-11712 (65 FR 25833, May 4, 2000).

(k) Parts Installation Prohibition

    As of the effective date of this AD, no person may install a 
flexshaft having part number 3278500-( ) on any airplane.

(l) 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 the Related Information 
section 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.
    (3) An AMOC that provides an acceptable level of safety may be 
used for any repair required by this AD if it is approved by the 
Boeing Commercial Airplanes Organization Designation Authorization 
(ODA) that has been authorized by the Manager, Seattle ACO, to make 
those findings. For a repair method to be approved, the repair must 
meet the certification basis of the airplane, and the approval must 
specifically refer to this AD.

(m) Related Information

    (1) For more information about this AD, contact Tung Tran, 
Aerospace Engineer, Propulsion Branch, ANM-140S, Seattle Aircraft 
Certification Office (ACO), FAA, 1601 Lind Avenue SW., Renton, WA 
98057-3356; phone: 425-917-6505; fax: 425-917-6590; email: 
[email protected].
    (2) 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 review copies of the 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.


    Issued in Renton, Washington, on January 10, 2013.
Kalene C. Yanamura,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 2013-00803 Filed 1-15-13; 8:45 am]
BILLING CODE 4910-13-P