Document ID: FAA-2010-1159-0001
Agency: faa
Document Type: Rule
Title: Airworthiness Directives: Boeing Co. Model 747-400 and -400D Series Airplanes
Posted Date: 2010-12-01T05:00Z

[Federal Register: December 1, 2010 (Volume 75, Number 230)]
[Proposed Rules]               
[Page 74663-74665]
From the Federal Register Online via GPO Access [wais.access.gpo.gov]
[DOCID:fr01de10-23]                         

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Proposed Rules
                                                Federal Register
________________________________________________________________________

This section of the FEDERAL REGISTER contains notices to the public of 
the proposed issuance of rules and regulations. The purpose of these 
notices is to give interested persons an opportunity to participate in 
the rule making prior to the adoption of the final rules.

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[[Page 74663]]

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2010-1159; Directorate Identifier 2010-NM-006-AD]
RIN 2120-AA64

 
Airworthiness Directives; The Boeing Company Model 747-400 and -
400D Series Airplanes

AGENCY: Federal Aviation Administration, DOT.

ACTION: Notice of proposed rulemaking (NPRM).

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SUMMARY: We propose to adopt a new airworthiness directive (AD) for 
certain Model 747-400 and -400D series airplanes. This proposed AD 
would require a general visual inspection to determine the routing of 
the wire bundles in the number two and number three engine pylons near 
the leading edge, and related investigative and corrective actions, if 
necessary. For certain airplanes, this proposed AD would also require 
certain concurrent actions. This proposed AD results from a report of a 
fuel leak from the drain line of the number two engine pylon. We are 
proposing this AD to detect and correct chafing of the main fuel feed 
tube and the alternating current motor-driven hydraulic pump wire 
bundle, which could lead to arcing from the exposed wire to the fuel 
feed tube, and could result in a fire or explosion.

DATES: We must receive comments on this proposed AD by January 18, 
2011.

ADDRESSES: You may send comments by any of the following methods:
     Federal eRulemaking Portal: Go to http://
www.regulations.gov. Follow the instructions for submitting comments.
     Fax: 202-493-2251.
     Mail: U.S. Department of Transportation, Docket 
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New 
Jersey Avenue, SE., Washington, DC 20590.
     Hand Delivery: U.S. Department of Transportation, Docket 
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New 
Jersey Avenue, SE., Washington, DC 20590, between 9 a.m. and 5 p.m., 
Monday through Friday, except Federal holidays.
    For service information identified in this proposed AD, contact 
Boeing Commercial Airplanes, Attention: Data & Services Management, 
P.O. Box 3707, MC 2H-65, Seattle, Washington 98124-2207; telephone 206-
544-5000, extension 1; fax 206-766-5680; e-mail me.boecom@boeing.com; 
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, Washington. 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 (telephone 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, FAA, Seattle Aircraft Certification 
Office, 1601 Lind Avenue, SW., Renton, Washington 98057-3356, telephone 
(425) 917-6505; fax (425) 917-6590.

SUPPLEMENTARY INFORMATION:

Comments Invited

    We invite you to send any written relevant data, views, or 
arguments about this proposed AD. Send your comments to an address 
listed under the ADDRESSES section. Include ``Docket No. FAA-2010-1159; 
Directorate Identifier 2010-NM-006-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 received a report of a Model 747-400 airplane arriving at a gate 
with a fuel leak from the drain line of the number two engine pylon. An 
investigation revealed that the alternating current motor-driven pump 
wire bundle was incorrectly routed and touching the fuel feed tube, 
which caused chafing of the fuel feed tube and the resultant leak. If 
not detected and corrected, chafing of the main fuel feed tube and the 
alternating current motor-driven hydraulic pump wire bundle could lead 
to arcing from the exposed wire to the fuel feed tube, and could result 
in a fire or explosion.

Related AD

    We issued AD 92-27-13, amendment 39-8448 (58 FR 5920, January 25, 
1993), on December 17, 1992, for Model 747-400 series airplanes. We 
issued that AD to require repetitive inspections to detect damage, 
chafing, and improper clearance between the electrical power feeder 
cables and engine fuel supply tube, and corrective actions, if 
necessary; and modification of the electrical power feeder cable 
installation.

Relevant Service Information

    We have reviewed Boeing Service Bulletin 747-29A2114, Revision 1, 
dated July 15, 2010. The service bulletin describes procedures for a 
general visual inspection to determine the routing of the wire bundles 
in the number two and number three engine pylons near the leading edge, 
and related investigative and corrective actions if necessary. Related 
investigative actions include a general visual inspection for damage 
between the wire bundle and the fuel feed tube. Corrective actions 
include repairing the wire bundle, repairing or replacing the fuel feed 
tube where the wire bundle goes across the tube, and changing the 
routing configuration for the wire bundle to above the support bracket.

[[Page 74664]]

    Boeing Service Bulletin 747-29A2114, Revision 1, dated July 15, 
2010, refers to Boeing Alert Service Bulletin 747-24A2168, Revision 1, 
dated December 5, 1991; Boeing Alert Service Bulletin 747-24A2168, 
Revision 2, dated September 24, 1992; or Boeing Service Bulletin 747-
24A2168, Revision 3, dated July 29, 1993; for actions that must be done 
prior to or concurrently with the actions specified in Boeing Service 
Bulletin 747-29A2114, Revision 1, dated July 15, 2010. Boeing Service 
Bulletin 747-24A2168, Revision 3, dated July 29, 1993, specifies, for 
certain airplanes, procedures for installing the cable support brackets 
in the number two and number three strut, and related investigative and 
corrective actions, if necessary. The related investigative action is a 
detailed inspection of the clearance between the bracket and an 
adjacent pneumatic duct. The corrective action is adjusting the 
pneumatic duct, if necessary. AD 92-27-13 refers to Boeing Alert 
Service Bulletin 747-24A2168, Revision 1, dated December 5, 1991; and 
Revision 2, dated September 24, 1992; as appropriate sources of service 
information for doing certain actions required by that AD.

FAA's Determination and Requirements of This Proposed AD

    We are proposing this AD because we evaluated all relevant 
information and determined the unsafe condition described previously is 
likely to exist or develop in other products of the same type design. 
This proposed AD would require accomplishing the actions specified in 
the service information described previously.

Costs of Compliance

    We estimate that this proposed AD would affect 15 airplanes of U.S. 
registry. The following table provides the estimated costs for U.S. 
operators to comply with this proposed AD.

                                                                 Table--Estimated Costs
--------------------------------------------------------------------------------------------------------------------------------------------------------
                                                                                                                          Number of U.S.-
                         Action                             Work hours     Average labor       Parts         Cost per       registered      Fleet cost
                                                                           rate per hour                      product        airplanes
--------------------------------------------------------------------------------------------------------------------------------------------------------
Inspection..............................................               1             $85              $0             $85              15          $1,275
Concurrent Inspection and Bracket Installation..........               6              85               0             510              15           7,650
--------------------------------------------------------------------------------------------------------------------------------------------------------

    The cost estimate figure discussed above is based on assumptions 
that no operator has yet accomplished any of the actions required by 
this proposed AD, and that no operator would accomplish those actions 
in the future if this AD were not adopted. However, we have been 
advised that the concurrent inspection and bracket installation have 
already been done on some affected airplanes. Therefore, the future 
economic cost impact of this rule on U.S. operators is expected to be 
less than the cost impact figure indicated above.

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), and
    3. 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.
    You can find our regulatory evaluation and the estimated costs of 
compliance in the AD Docket.

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

    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]

    2. The FAA amends Sec.  39.13 by adding the following new AD:

The Boeing Company: Docket No. FAA-2010-1159; Directorate Identifier 
2010-NM-006-AD.

Comments Due Date

    (a) We must receive comments by January 18, 2011.

Affected ADs

    (b) AD 92-27-13, Amendment 39-8448, affects this AD.

Applicability

    (c) This AD applies to The Boeing Company Model 747-400 and -
400D series airplanes, certificated in any category; as specified in 
Boeing Alert Service Bulletin 747-29A2114, Revision 1, dated July 
15, 2010.

Subject

    (d) Air Transport Association (ATA) of America Code 29: 
Hydraulic power.

Unsafe Condition

    (e) This AD results from a report of a fuel leak from the drain 
line of the number two engine pylon. The Federal Aviation 
Administration is issuing this AD to detect and correct chafing of 
the main fuel feed tube and the alternating current motor-driven 
hydraulic pump wire bundle, which could lead to arcing from the 
exposed wire to the

[[Page 74665]]

fuel feed tube, and could result in a fire or explosion.

Compliance

    (f) You are responsible for having the actions required by this 
AD performed within the compliance times specified, unless the 
actions have already been done.

Inspection

    (g) Within 24 months after the effective date of this AD, do a 
general visual inspection to determine the routing of the wire 
bundles in the number two and number three engine pylons near the 
leading edge; and do all applicable related investigative and 
corrective actions; in accordance with the Accomplishment 
Instructions of Boeing Service Bulletin 747-29A2114, Revision 1, 
dated July 15, 2010. Do all applicable related investigative and 
corrective actions before further flight.

Concurrent Requirements

    (h) For Model 747-400 series airplanes: Before or concurrently 
with accomplishing the requirements of paragraph (g) of this AD, 
install all applicable cable support brackets in the number two and 
number three engine pylon areas, and do all applicable related 
investigative and corrective actions, in accordance with Phase II of 
Boeing Service Bulletin 747-24A2168, Revision 3, dated July 29, 
1993. Do all applicable related investigative and corrective actions 
before further flight. Doing the actions required by paragraph (c) 
of AD 92-27-13, Amendment 39-8488, is an acceptable method of 
compliance with the installation required by this paragraph.

    Note 1: For the purposes of this AD, a detailed inspection is: 
``An intensive examination of a specific item, installation, or 
assembly to detect damage, failure, or irregularity. Available 
lighting is normally supplemented with a direct source of good 
lighting at an intensity deemed appropriate. Inspection aids such as 
mirror, magnifying lenses, etc., may be necessary. Surface cleaning 
and elaborate procedures may be required.''

Credit for Actions Accomplished in Accordance With Previous Service 
Information

    (i) Actions accomplished before the effective date of this AD, 
in accordance with the Accomplishment Instructions of Boeing Alert 
Service Bulletin 747-29A2114, dated October 1, 2009, are considered 
acceptable for compliance with the corresponding actions specified 
in paragraph (g) of this AD.
    (j) Actions accomplished before the effective date of this AD, 
in accordance with the Accomplishment Instructions of Boeing Alert 
Service Bulletin 747-24A2168, Revision 1, dated December 5, 1991; or 
Revision 2, dated September 24, 1992; are considered acceptable for 
compliance with the corresponding actions specified in paragraph (h) 
of this AD.

Alternative Methods of Compliance (AMOCs)

    (k)(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. Send information to 
ATTN: Tung Tran, Aerospace Engineer, Propulsion Branch, ANM-140S, 
FAA, Seattle Aircraft Certification Office, 1601 Lind Avenue, SW., 
Renton, Washington 98057-3356, telephone (425) 917-6505; fax (425) 
917-6590. Information may be e-mailed to: 9-ANM-Seattle-ACO-AMOC-
Requests@faa.gov.
    (2) To request a different method of compliance or a different 
compliance time for this AD, follow the procedures in 14 CFR 39.19. 
Before using any approved AMOC on any airplane to which the AMOC 
applies, notify your principal maintenance inspector (PMI) or 
principal avionics inspector (PAI), as appropriate, or lacking a 
principal inspector, your local Flight Standards District Office. 
The AMOC approval letter must specifically reference this AD.

    Issued in Renton, Washington, on November 15, 2010.
Ali Bahrami,
Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 2010-30134 Filed 11-30-10; 8:45 am]
BILLING CODE 4910-13-P