AD 2003-14-10

[Federal Register Volume 68, Number 138 (Friday, July 18, 2003)]
[Rules and Regulations]
[Pages 42583-42585]
From the Federal Register Online via the Government Publishing Office [<a href="http://www.gpo.gov">www.gpo.gov</a>]
[FR Doc No: 03-17693]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 2002-NM-205-AD; Amendment 39-13229; AD 2003-14-10]
RIN 2120-AA64


Airworthiness Directives; Boeing Model 767-200 and -300 Series 
Airplanes

AGENCY: Federal Aviation Administration, DOT.

ACTION: Final rule; request for comments.

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SUMMARY: This amendment adopts a new airworthiness directive (AD), 
applicable to certain Boeing Model 767-200 and -300 series airplanes. 
This action requires modification of the wire bundles of the video 
control center (VCC) of the passenger address and entertainment system, 
and an operational test if necessary. This action is necessary to 
prevent chafing of the wire bundles of the VCC against the rudder and/
or elevator control cables, which could result in arcing of the wires 
in the wire bundles and severing of the cables. Severed cables, if 
combined with an engine-out during takeoff, or a high crosswind during 
takeoff or landing, could result in reduced controllability of the 
airplane. This action is intended to address the identified unsafe 
condition.

DATES: Effective August 4, 2003.
    The incorporation by reference of certain publications listed in 
the regulations is approved by the Director of the Federal Register as 
of August 4, 2003.
    Comments for inclusion in the Rules Docket must be received on or 
before September 16, 2003.

ADDRESSES: Submit comments in triplicate to the Federal Aviation 
Administration (FAA), Transport Airplane Directorate, ANM-114, 
Attention: Rules Docket No. 2002-NM-205-AD, 1601 Lind Avenue, SW., 
Renton, Washington 98055-4056. Comments may be inspected at this 
location between 9 a.m. and 3 p.m., Monday through Friday, except 
Federal holidays. Comments may be submitted via fax to (425) 227-1232. 
Comments may also be sent via the Internet using the following address: 
<a href="/cdn-cgi/l/email-protection#21180c404f4c0c484053424e4c4c444f55614740400f464e57"><span class="__cf_email__" data-cfemail="5d64703c333070343c2f3e3230303833291d3b3c3c733a322b">[email&#160;protected]</span></a>. Comments sent via fax or the Internet must 
contain ``Docket No. 2002-NM-205-AD'' in the subject line and need not 
be submitted in triplicate. Comments sent via the Internet as attached 
electronic files must be formatted in Microsoft Word 97 or 2000 or 
ASCII text.
    The service information referenced in this AD may be obtained from 
Boeing Commercial Airplane Group, P.O. Box 3707, Seattle, Washington 
98124-2207. This information may be examined at the FAA, Transport 
Airplane Directorate, 1601 Lind Avenue, SW., Renton, Washington; or at 
the Office of the Federal Register, 800 North Capitol Street, NW., 
suite 700, Washington, DC.

FOR FURTHER INFORMATION CONTACT: Barbara Mudrovich, Aerospace Engineer, 
Systems and Equipment Branch, ANM-130S, FAA, Seattle Aircraft 
Certification Office, 1601 Lind Avenue, SW., Renton, Washington 98055-
4056; telephone (425) 917-6477; fax (425) 917-6590.

SUPPLEMENTARY INFORMATION: During post-delivery modifications of 
certain Boeing Model 767-200 and -300 series airplanes, the 
manufacturer found that the rudder cables and the First Officer's 
elevator control cables may come in contact with the video control 
center (VCC) wires, which could result in possible chafing and 
subsequent arcing of the wires in the wire bundles and severing of the 
cables. Severed cables, if combined with an engine-out during takeoff, 
or a high crosswind during takeoff or landing, could result in reduced 
controllability of the airplane.

Explanation of Relevant Service Information

    We have reviewed and approved the following Boeing alert service 
bulletins:

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          Service bulletin                 Revision level                Date                     Model
----------------------------------------------------------------------------------------------------------------
767-23A0147, including Appendix A...  Original...............  April 6, 2000..........  767-300
767-23A0154.........................  Original...............  March 15, 2001.........  767-300
767-23A0155, including Appendix A...  Original...............  March 29, 2001.........  767-300
767-23A0156, including Appendix A...  Original...............  April 19, 2001.........  767-200, -300
767-23A0157.........................  Original...............  May 3, 2001............  767-300
----------------------------------------------------------------------------------------------------------------

These service bulletins describe procedures for modification of the 
wire bundles of the VCC of the passenger address and entertainment 
system. The modification includes, but is not limited to, installation 
of a wiring shroud and associated hardware between the VCC master 
control unit wiring and the flight control cables; re-routing of the 
VCC wire bundles above the flight control pulley box; and replacement 
of existing clamps with new clamps; as applicable. Service bulletins 
767-23A0154 and 767-23A0157 also describe procedures for an operational 
test after accomplishment of the modification. Accomplishment of the 
actions specified in the applicable service bulletin is intended to 
adequately address the identified unsafe condition.

Explanation of Requirements of the Rule

    Since an unsafe condition has been identified that is likely to 
exist or develop on other airplanes of the same type design that may be 
registered in the United States at some time in the future, this AD is 
being issued to prevent chafing of the wire bundles of the VCC against 
the rudder and/or elevator control cables, which could result in arcing 
of the wires in the wire bundles and severing of the cables. Severed 
cables, if combined with an engine-out during takeoff, or a high 
crosswind during takeoff or landing, could result in reduced 
controllability of the airplane. This AD requires modification of the 
wire bundles of the VCC of the passenger address and entertainment 
system. The actions are required to be accomplished in accordance with 
the applicable service bulletin described previously, except as 
discussed below.

[[Page 42584]]

Difference Between the Service Bulletins and This AD

    Although the service bulletins recommend accomplishing the 
specified actions at the earliest maintenance opportunity when manpower 
and materials are available, we have determined that such an imprecise 
compliance time would not address the identified unsafe condition in a 
timely manner. In developing an appropriate compliance time for this 
AD, we considered not only the manufacturer's recommendation, but the 
degree of urgency associated with addressing the subject unsafe 
condition, the average utilization of the affected fleet, and the time 
necessary to perform the modification (2 work hours). In light of all 
of these factors, we find a 6-month compliance time for completing the 
required actions to be warranted, in that it represents an appropriate 
interval of time allowable for affected airplanes to continue to 
operate without compromising safety.

Changes to 14 CFR Part 39/Effect on the AD

    On July 10, 2002, the FAA issued a new version of 14 CFR part 39 
(67 FR 47997, July 22, 2002), which governs the FAA's airworthiness 
directives system. The regulation now includes material that relates to 
altered products, special flight permits, and alternative methods of 
compliance. Because we have now included this material in part 39, we 
no longer need to include it in each individual AD; however, this AD 
identifies the office authorized to approve alternative methods of 
compliance.

Revised Labor Rate

    We have reviewed the figures we have used over the past several 
years to calculate AD costs to operators. To account for various 
inflationary costs in the airline industry, we find it necessary to 
increase the labor rate used in these calculations from $60 per work 
hour to $65 per work hour. The cost impact information, below, has been 
revised to reflect this increase in the specified hourly labor rate.

Cost Impact

    None of the airplanes affected by this action are on the U.S. 
Register. All airplanes included in the applicability of this rule 
currently are operated by non-U.S. operators under foreign registry; 
therefore, they are not directly affected by this AD action. However, 
the FAA considers that this rule is necessary to ensure that the unsafe 
condition is addressed in the event that any of these subject airplanes 
are imported and placed on the U.S. Register in the future.
    Should an affected airplane be imported and placed on the U.S. 
Register in the future, it would require approximately 2 work hours to 
accomplish the required modification, at an average labor rate of $65 
per work hour. Parts cost would be between $64 and $915 per airplane. 
Based on these figures, the cost impact of the modification required by 
this AD would be between $194 and $1,045 per airplane.

Determination of Rule's Effective Date

    Since this AD action does not affect any airplane that is currently 
on the U.S. register, it has no adverse economic impact and imposes no 
additional burden on any person. Therefore, prior notice and public 
procedures hereon are unnecessary and the amendment may be made 
effective in less than 30 days after publication in the Federal 
Register.

Comments Invited

    Although this action is in the form of a final rule and was not 
preceded by notice and opportunity for public comment, comments are 
invited on this rule. Interested persons are invited to comment on this 
rule by submitting such written data, views, or arguments as they may 
desire. Communications shall identify the Rules Docket number and be 
submitted in triplicate to the address specified under the caption 
ADDRESSES. All communications received on or before the closing date 
for comments will be considered, and this rule may be amended in light 
of the comments received. Factual information that supports the 
commenter's ideas and suggestions is extremely helpful in evaluating 
the effectiveness of the AD action and determining whether additional 
rulemaking action would be needed.
    Submit comments using the following format:
    [sbull] Organize comments issue-by-issue. For example, discuss a 
request to change the compliance time and a request to change the 
service bulletin reference as two separate issues.
    [sbull] For each issue, state what specific change to the AD is 
being requested.
    [sbull] Include justification (e.g., reasons or data) for each 
request.
    Comments are specifically invited on the overall regulatory, 
economic, environmental, and energy aspects of the rule that might 
suggest a need to modify the rule. All comments submitted will be 
available, both before and after the closing date for comments, in the 
Rules Docket for examination by interested persons. A report that 
summarizes each FAA-public contact concerned with the substance of this 
AD will be filed in the Rules Docket.
    Commenters wishing the FAA to acknowledge receipt of their comments 
submitted in response to this rule must submit a self-addressed, 
stamped postcard on which the following statement is made: ``Comments 
to Docket Number 2002-NM-205-AD.'' The postcard will be date stamped 
and returned to the commenter.

Regulatory Impact

    The regulations adopted herein 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. Therefore, it 
is determined that this final rule does not have federalism 
implications under Executive Order 13132.
    For the reasons discussed above, I certify that this action: (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) 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. A final evaluation has been prepared for this action 
and it is contained in the Rules Docket. A copy of it may be obtained 
from the Rules Docket at the location provided under the caption 
ADDRESSES.

List of Subjects in 14 CFR Part 39

    Air transportation, Aircraft, Aviation safety, Incorporation by 
reference, Safety.

Adoption of the Amendment

0
Accordingly, pursuant to the authority delegated to me by the 
Administrator, the Federal Aviation Administration amends part 39 of 
the Federal Aviation Regulations (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. Section 39.13 is amended by adding the following new airworthiness 
directive:

2003-14-10 Boeing: Amendment 39-13229. Docket 2002-NM-205-AD.


[[Page 42585]]


    Applicability: This AD applies to the airplanes listed in Table 
1 of this AD, certificated in any category:

                         Table 1.--Applicability
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              Model--                          As listed in--
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767-200, -300 series airplanes....  Boeing Alert Service Bulletin 767-
                                     23A0156, dated April 19, 2001.
767-300 series airplanes..........  Boeing Alert Service Bulletins 767-
                                     23A0147, dated April 6, 2000; 767-
                                     23A0154, dated March 15, 2001; 767-
                                     23A0155, dated March 29, 2001; and
                                     767-23A0157, dated May 3, 2001.
------------------------------------------------------------------------

    Compliance: Required as indicated, unless accomplished 
previously.
    To prevent chafing of the wire bundles of the video control 
center (VCC) against the rudder and/or elevator control cables, 
accomplish the following:

Modification

    (a) Within 6 months after the effective date of this AD: Modify 
the wire bundles of the VCC of the passenger address and 
entertainment system, and do an operational test if applicable, per 
the Accomplishment Instructions of the applicable Boeing alert 
service bulletin listed in Table 2 of this AD, as follows:

                                           Table 2.--Service Bulletins
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               Model                     Service bulletin           Revision level                Date
----------------------------------------------------------------------------------------------------------------
767-300...........................  767-23A0147, including      Original.............  April 6, 2000.
                                     Appendix A.
767-300...........................  767-23A0154...............  Original.............  March 15, 2001.
767-300...........................  767-23A0155, including      Original.............  March 29, 2001.
                                     Appendix A.
767-200, -300.....................  767-23A0156, including      Original.............  April 300 19, 2001.
                                     Appendix A.
767-300...........................  767-23A0157...............  Original.............  May 3, 2001.
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Alternative Methods of Compliance

    (b) In accordance with 14 CFR 39.19, the Manager, Seattle 
Aircraft Certification Office, FAA, is authorized to approve 
alternative methods of compliance for this AD.

Incorporation by Reference

    (c) The actions shall be done in accordance with the applicable 
Boeing alert service bulletin listed in Table 3 of this AD, as 
follows:

                       Table 3.--Service Bulletins
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            Service bulletin                           Date
------------------------------------------------------------------------
767-23A0147, including Appendix A......  April 6, 2000.
767-23A0154............................  March 15, 2001.
767-23A0155, including Appendix A......  March 29, 2001.
767-23A0156, including Appendix A......  April 19, 2001.
767-23A0157............................  May 3, 2001.
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This incorporation by reference was approved by the Director of the 
Federal Register in accordance with 5 U.S.C. 552(a) and 1 CFR part 
51. Copies may be obtained from Boeing Commercial Airplane Group, 
P.O. Box 3707, Seattle, Washington 98124-2207. Copies may be 
inspected at the FAA, Transport Airplane Directorate, 1601 Lind 
Avenue, SW., Renton, Washington; or at the Office of the Federal 
Register, 800 North Capitol Street, NW., suite 700, Washington, DC.

Effective Date

    (d) This amendment becomes effective on August 4, 2003.

    Issued in Renton, Washington, on July 7, 2003.
Ali Bahrami,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 03-17693 Filed 7-17-03; 8:45 am]
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