AD 2001-14-05

[Federal Register Volume 66, Number 133 (Wednesday, July 11, 2001)]
[Rules and Regulations]
[Pages 36145-36146]
From the Federal Register Online via the Government Publishing Office [<a href="http://www.gpo.gov">www.gpo.gov</a>]
[FR Doc No: 01-17121]



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Federal Register / Vol. 66, No. 133 / Wednesday, July 11, 2001 / 
Rules and Regulations

[[Page 36145]]



DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 2001-NM-188-AD; Amendment 39-12315; AD 2001-14-05]
RIN 2120-AA64


Airworthiness Directives; Boeing Model 737-600, -700, -700C, and 
-800 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) that 
is applicable to all Boeing Model 737-600, -700, -700C, and -800 series 
airplanes. This action prohibits installation of repairs of the 
elevator tab using previously approved repair procedures. This action 
is necessary to prevent installation of repairs of the elevator tab 
that are outside allowable limits, which could result in excessive in-
flight vibrations of the elevator tab, and consequent loss of 
controllability of the airplane.

DATES: Effective July 26, 2001.
    Comments for inclusion in the Rules Docket must be received on or 
before September 10, 2001.

ADDRESSES: Submit comments in triplicate to the Federal Aviation 
Administration (FAA), Transport Airplane Directorate, ANM-114, 
Attention: Rules Docket No. 2001-NM-188-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#556c78343b38783c3427363a3838303b21153334347b323a23"><span class="__cf_email__" data-cfemail="8cb5a1ede2e1a1e5edfeefe3e1e1e9e2f8cceaededa2ebe3fa">[email&#160;protected]</span></a>. Comments sent via fax or the Internet must 
contain ``Docket No. 2001-NM-188-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 98055-
4056.

FOR FURTHER INFORMATION CONTACT: Nancy Marsh, Aerospace Engineer, 
Airframe Branch, ANM-120S, FAA, Seattle Aircraft Certification Office, 
1601 Lind Avenue, SW., Renton, Washington 98055-4056; telephone (425) 
227-2028; fax (425) 227-1181.

SUPPLEMENTARY INFORMATION: The FAA has received numerous reports of in-
flight vibrations of the elevator tab on Model 737-600, -700, and -800 
(``Next Generation'') series airplanes. These vibrations have been 
attributed to loose or missing components of the elevator tab 
assemblies, excessive wear of the elevator tab, excessive tab freeplay, 
and/or tab weight and center of gravity changes.
    In addition, we have determined that repairs of the elevator tab 
done using certain procedures approved before the effective date of 
this AD can adversely affect the weight and center of gravity of the 
elevator tab. Such changes in the tab weight and center of gravity can 
cause excessive in-flight vibration of the elevator tab. Therefore, 
updated limitations on repair procedures are necessary to ensure the 
reliability of the elevator tab in flight. Continued operation of these 
airplanes in such conditions could result in excessive in-flight 
vibrations of the elevator tab, and consequent loss of controllability 
of the airplane.

Explanation of Service Information

    The FAA has reviewed Boeing All Operator Message M-7200-01-00756, 
Revision 1, dated May 29, 2001, which describes allowable repair limits 
for the elevator tab. Repair limits include, but are not limited to, 
the following:
    <bullet> Repair can only be one facesheet (upper or lower skin) and 
honeycomb core in depth.
    <bullet> Repair of damaged honeycomb core by potting is not 
permitted.
    <bullet> Maximum size of damage (allowable damage) that may be 
sealed using aluminum foil tape is 1 inch in diameter.
    <bullet> Maximum damage size that could be repaired using 150 
degree or 200 degree wet layup is .5 inch across the largest dimension.
    <bullet> No 250 degree prepreg repairs are permitted.

Explanation of the 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, this AD is 
being issued to prevent installation of repairs that are outside 
allowable limits of the elevator tab, which could result in excessive 
in-flight vibrations of the elevator tab, consequent loss of the 
elevator tab, and loss of controllability of the airplane. This AD 
prohibits installation of certain repairs of the elevator tab.

Interim Action

    This is interim action. The FAA is working with the manufacturer to 
identify proper action to ensure that unsafe conditions do not exist on 
airplanes that were repaired before the effective date of this AD. If a 
corrective action for the existing repairs is necessary, the FAA may 
consider further rulemaking in this regard.
    The manufacturer also has advised that it currently is developing a 
modification that will positively address the unsafe condition 
addressed by this AD. Once this modification is developed, approved, 
and available, the FAA may consider additional rulemaking.

Determination of Rule's Effective Date

    Since a situation exists that requires the immediate adoption of 
this regulation, it is found that notice and opportunity for prior 
public comment hereon are impracticable, and that good cause exists for 
making this amendment effective in less than 30 days.

Comments Invited

    Although this action is in the form of a final rule that involves 
requirements affecting flight safety and, thus, was not preceded by 
notice and an opportunity for public comment, comments are invited on 
this rule. Interested persons

[[Page 36146]]

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:
    <bullet> 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.
    <bullet> For each issue, state what specific change to the AD is 
being requested.
    <bullet> 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 2001-NM-188-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.
    The FAA has determined that this regulation is an emergency 
regulation that must be issued immediately to correct an unsafe 
condition in aircraft, and that it is not a ``significant regulatory 
action'' under Executive Order 12866. It has been determined further 
that this action involves an emergency regulation under DOT Regulatory 
Policies and Procedures (44 FR 11034, February 26, 1979). If it is 
determined that this emergency regulation otherwise would be 
significant under DOT Regulatory Policies and Procedures, a final 
regulatory evaluation will be prepared and placed in the Rules Docket. 
A copy of it, if filed, 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, Safety.

Adoption of the Amendment

    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]

    2. Section 39.13 is amended by adding the following new 
airworthiness directive:

2001-14-05  Boeing: Amendment 39-12315. Docket 2001-NM-188-AD.
    Applicability: All Model 737-600, -700, -700C, and -800 series 
airplanes, certificated in any category.

    Compliance: Required as indicated, unless accomplished 
previously.
    To prevent installation of repairs of the elevator tab that are 
outside allowable limits, which could result in excessive in-flight 
vibrations of the elevator tab, and consequent loss of 
controllability of the airplane, accomplish the following:

Elevator Tab Repairs

    (a) As of the effective date of this AD, no person shall install 
on any airplane any elevator tab repairs that are NOT done in 
accordance with Boeing All Operator Message M-7200-01-00756, 
Revision 1, dated May 29, 2001.

Alternative Methods of Compliance

    (b) An alternative method of compliance or adjustment of the 
compliance time that provides an acceptable level of safety may be 
used if approved by the Manager, Seattle Aircraft Certification 
Office (ACO), FAA. Operators shall submit their requests through an 
appropriate FAA Principal Maintenance Inspector, who may add 
comments and then send it to the Manager, Seattle ACO.

    Note 1: Information concerning the existence of approved 
alternative methods of compliance with this AD, if any, may be 
obtained from the Seattle ACO.

Special Flight Permits

    (c) Special flight permits may be issued in accordance with 
sections 21.197 and 21.199 of the Federal Aviation Regulations (14 
CFR 21.197 and 21.199) to operate the airplane to a location where 
the requirements of this AD can be accomplished.

Effective Date

    (d) This amendment becomes effective on July 26, 2001.

    Issued in Renton, Washington, on July 2, 2001.
Vi L. Lipski,
Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 01-17121 Filed 7-10-01; 8:45 am]
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