[Federal Register: December 1, 2003 (Volume 68, Number 230)]
[Rules and Regulations]
[Page 67024-67025]
From the Federal Register Online via GPO Access [wais.access.gpo.gov]
[DOCID:fr01de03-5]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. 2003-NM-140-AD; Amendment 39-13373; AD 2003-24-04]
RIN 2120-AA64
Airworthiness Directives; Boeing Model 747-400 and -400F 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 747-400 and -400F series airplanes.
This action requires replacing the rudder feel, centering, and trim
mechanism with a new or serviceable rudder feel, centering, and trim
mechanism. This action is necessary to prevent degradation/loss of
rudder feel and centering, which could result in increased pilot
workload and could lead to loss of control of the airplane. This action
is intended to address the identified unsafe condition.
DATES: Effective December 16, 2003.
The incorporation by reference of Boeing Service Bulletin 747-27-
2392, dated February 20, 2003, as listed in the regulations, is
approved by the Director of the Federal Register as of December 16,
2003.
Comments for inclusion in the Rules Docket must be received on or
before January 30, 2004.
ADDRESSES: Submit comments in triplicate to the Federal Aviation
Administration (FAA), Transport Airplane Directorate, ANM-114,
Attention: Rules Docket No. 2003-NM-140-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: 9-anm-iarcomment@faa.gov. Comments sent via fax or the Internet must
contain ``Docket No. 2003-NM-140-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 for Windows 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: Doug Tsuji, Aerospace Engineer,
Systems and Equipment Branch, ANM-130S, FAA, Seattle Aircraft
Certification Office, 1601 Lind Avenue, SW., Renton, Washington 98055-
4056; telephone (425) 917-6487; fax (425) 917-6590.
SUPPLEMENTARY INFORMATION: The FAA has received reports from the
manufacturer of Boeing Model 747-400 series airplanes, indicating that
there have been two cases of shafts in the rudder feel, centering, and
trim mechanisms with either elongated holes or extra holes and drill
starts. The shafts were found installed on airplanes in the factory.
The cause of the discrepancies in the shafts is due to manufacturing
and quality deficiencies at the supplier. This condition, if not
corrected, could result in degradation/loss of rudder feel and
centering, which could result in increased pilot workload and could
lead to loss of control of the airplane.
Explanation of Relevant Service Information
The FAA has reviewed and approved Boeing Service Bulletin 747-27-
2392, dated February 20, 2003, which describes procedures for replacing
the rudder feel, centering, and trim mechanism with a new or
serviceable rudder feel, centering, and trim mechanism. Accomplishment
of the actions specified in the 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 degradation/loss of rudder feel and centering,
which could result in increased pilot workload and could lead to loss
of control of the airplane. This AD requires replacing the rudder feel,
centering, and trim mechanism with a new or serviceable rudder feel,
centering, and trim mechanism. The actions are required to be
accomplished in accordance with the service bulletin described
previously.
Cost Impact
None of the Model 747-400 and -400F series 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 12 work hours to
accomplish the required actions, at an average labor rate of $65 per
work hour. Required parts would cost $25,537. Based on these figures,
the cost impact of this AD would be $26,317 per airplane.
The manufacturer may cover the cost of replacement parts associated
with this AD, subject to warranty conditions. Manufacturer warranty
remedies may also be available for labor costs associated with this AD.
As a result, the costs attributable to the proposed AD may be less than
stated above.
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
[[Page 67025]]
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 2003-NM-140-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
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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
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:
2003-24-04 Boeing: Amendment 39-13373. Docket 2003-NM-140-AD.
Applicability: Model 747-400 and -400F series airplanes, line
numbers 1254 through 1293 inclusive, certificated in any category.
Compliance: Required as indicated, unless accomplished
previously.
To prevent degradation/loss of rudder feel and centering, which
could result in increased pilot workload and could lead to loss of
control of the airplane, accomplish the following:
Service Bulletin References
(a) The term ``service bulletin'' as used in this AD, means the
Accomplishment Instructions of Boeing Service Bulletin 747-27-2392,
dated February 20, 2003.
Corrective Actions
(b) Within 36 months after the effective date of this AD,
replace the feel, centering, and trim mechanism with a new or
serviceable rudder feel, centering, and trim mechanism per the
service bulletin.
Alternative Methods of Compliance
(c) 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
(d) The actions shall be done in accordance with Boeing Service
Bulletin 747-27-2392, dated February 20, 2003. 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, PO 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
(e) This amendment becomes effective on December 16, 2003.
Issued in Renton, Washington, on November 20, 2003.
Vi L. Lipski,
Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 03-29530 Filed 11-28-03; 8:45 am]
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