Airworthiness Directives; Boeing Model 747-400 and -400F Series Airplanes

[Federal Register Volume 68, Number 230 (Monday, December 1, 2003)]
[Rules and Regulations]
[Pages 67024-67025]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 03-29530]


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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: 
[email protected]. 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

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

    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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