[Federal Register: September 2, 2004 (Volume 69, Number 170)]
[Rules and Regulations]
[Page 53605-53607]
From the Federal Register Online via GPO Access [wais.access.gpo.gov]
[DOCID:fr02se04-3]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. 2002-NM-327-AD; Amendment 39-13779; AD 2004-18-02]
RIN 2120-AA64
Airworthiness Directives; Boeing Model 737-600, 737-700, 737-
700C, 737-800, and 737-900 Series Airplanes
AGENCY: Federal Aviation Administration, DOT.
ACTION: Final rule.
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SUMMARY: This amendment adopts a new airworthiness directive (AD),
applicable to certain Boeing Model 737-600, 737-700, 737-700C, 737-800,
and 737-900 series airplanes, that requires measuring the electrical
resistance of the support bracket for the fire extinguisher bottle
located in the left main landing gear wheel well to ensure that it does
not exceed the maximum allowed resistance; and corrective actions, if
necessary. This action is necessary to prevent high electrical
resistance in the squib firing circuit, which could result in
insufficient electrical current to fire the fire extinguisher bottle
squib and discharge the fire extinguishing agent, which could lead to
an uncontrolled engine fire. This action is intended to address the
identified unsafe condition.
DATES: Effective October 7, 2004.
The incorporation by reference of a certain publication listed in
the regulations is approved by the Director of the Federal Register as
of October 7, 2004.
ADDRESSES: The service information referenced in this AD may be
obtained from Boeing Commercial Airplanes, P.O. Box 3707, Seattle,
Washington 98124-2207. This information may be examined at the Federal
Aviation Administration (FAA), Transport Airplane Directorate, Rules
Docket, 1601 Lind Avenue, SW., Renton, Washington; or at the National
Archives and Records Administration (NARA). For information on the
availability of this material at NARA, call (202) 741-6030, or go to:
http://www.archives.gov/federal_register/code_of_federal_regulations/ibr_locations.html
.
FOR FURTHER INFORMATION CONTACT: Doug Pegors, Aerospace Engineer;
Propulsion Branch, ANM-140S, FAA, Seattle Aircraft Certification
Office, 1601 Lind Avenue, SW., Renton, Washington; telephone (425) 917-
6504; fax (425) 917-6590.
SUPPLEMENTARY INFORMATION: A proposal to amend part 39 of the Federal
Aviation Regulations (14 CFR part 39) to include an airworthiness
directive (AD) that is applicable to certain Boeing Model 737-600, 737-
700, 737-700C, 737-800, and 737-900 series airplanes was published in
the Federal Register on December 4, 2003 (68 FR 67812). That action
proposed to require measuring the electrical resistance of the support
bracket for the fire extinguisher bottle located in the left main
landing gear wheel well to ensure that it does not exceed the maximum
allowed resistance; and corrective actions, if necessary.
Comments
Interested persons have been afforded an opportunity to participate
in the making of this amendment. Due consideration has been given to
the comments received.
Support for the Proposal
Two commenters, who do not have airplanes affected by the proposed
AD, either do not object to or agree with the proposed AD.
[[Page 53606]]
Request To Give Credit for Boeing Telex
One commenter, an airplane operator, noted that the actions
proposed in the notice of proposed rulemaking (NPRM) are based on
Boeing Telex M-7200-02-01401, dated September 9, 2002. The operator
states that immediate action based on the telex was necessary due to
safety concerns, and it did not wait for Boeing to issue the related
service bulletin before taking the necessary actions. The commenter
proposes that the telex should be included in the final rule as an
acceptable means for compliance with the proposed actions.
We agree with the commenter. We have included Boeing Telex M-7200-
02-01401, dated September 9, 2002, in a new paragraph (c) of the final
rule to allow credit for accomplishment of the required actions per
that telex.
Request To Include New Revision of Service Bulletin
Another commenter, the airplane manufacturer, requests that Boeing
Alert Service Bulletin 737-26A1118, Revision 1, dated April 8, 2004, be
included as the appropriate source of service information for the final
rule. The commenter states that a typographical error in the original
release of the service bulletin (dated October 17, 2002) makes it
impossible for any correctly configured airplane to pass the continuity
test in the work instructions. In addition, as noted in the NPRM, the
original release of the service bulletin did not have explicit
instructions for reworking the terminal installation if the resistance
requirement is not met. The commenter states that, if Revision 1 of the
service bulletin is included in the final rule, paragraph (b)
(``Additional Rework'') should be deleted, and paragraph (a) should be
revised to exclude a reference to paragraph (b).
We partially agree with the commenter's request. In a further
engineering review, we determined that there is no typographical error
in the original release of the service bulletin that makes it
impossible for airplanes to pass the continuity test. However, we have
revised the applicability section and paragraphs (a) and (b) of the
final rule to include Revision 1 of the service bulletin, which is the
most current source of service information for the actions in this AD.
We have not deleted paragraph (b), but instead have revised it to allow
operators to rework the terminal installation in accordance with either
Revision 1 of the service bulletin, or in accordance with a method
approved by the FAA, as proposed in the NPRM. The new paragraph (c) of
this final rule also allows credit for actions done in accordance with
the original issue of the service bulletin.
Request To Revise Wording Regarding Anodize Coating
The same commenter requests that the following sentence in the
``Discussion'' section of the NPRM be revised: ``During manufacture,
the anodize coating was not removed properly from the holes in the
support bracket into which the ground studs are inserted, thereby
increasing the electrical resistance between the studs and the
bracket.'' The commenter notes that the anodize coating surrounding the
hole was also improperly prepared for an electrical bond.
We partially agree with the commenter's request, which provides a
more accurate description of the unsafe condition. However, the
``Discussion'' paragraph is included in an NPRM as a description of the
unsafe condition to provide adequate information to the public during
the comment period. The ``Discussion'' paragraph is not included in the
final rule. Therefore, we have not changed the information in the final
rule, but have provided the commenter's information above for the sake
of accuracy.
Conclusion
After careful review of the available data, including the comments
noted above, the FAA has determined that air safety and the public
interest require the adoption of the rule with the changes previously
described. The FAA has determined that these changes will neither
increase the economic burden on any operator nor increase the scope of
the AD.
Cost Impact
There are approximately 133 airplanes of the affected design in the
worldwide fleet. The FAA estimates that 28 airplanes of U.S. registry
will be affected by this AD, that it will take approximately 2 work
hours per airplane to accomplish the required actions, and that the
average labor rate is $65 per work hour. Based on these figures, the
cost impact of the AD on U.S. operators is estimated to be $3,640, or
$130 per airplane.
The cost impact figure discussed above is based on assumptions that
no operator has yet accomplished any of the requirements of this AD
action, and that no operator would accomplish those actions in the
future if this AD were not adopted. The cost impact figures discussed
in AD rulemaking actions represent only the time necessary to perform
the specific actions actually required by the AD. These figures
typically do not include incidental costs, such as the time required to
gain access and close up, planning time, or time necessitated by other
administrative actions.
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:
2004-18-02 Boeing: Amendment 39-13779. Docket 2002-NM-327-AD.
Applicability: Model 737-600, 737-700, 737-700C, 737-800, and
737-900 series airplanes, as listed in Boeing Alert Service Bulletin
737-26A1118, Revision 1, dated April 8, 2004; certificated in any
category.
Compliance: Required as indicated, unless accomplished
previously.
To prevent high electrical resistance in the squib firing
circuit, which could result in
[[Page 53607]]
insufficient electrical current to fire the fire extinguisher bottle
squib and discharge the fire extinguishing agent, which could lead
to an uncontrolled engine fire, accomplish the following:
Inspection, Rework, Replacement, Relocation, and Installation
(a) Except as provided by paragraph (b) of this AD: Within 90
days after the effective date of this AD, measure the electrical
resistance of the dual ground studs of the support brackets for the
fire extinguisher bottle located in the left main landing gear wheel
well (including the applicable corrective actions) by accomplishing
all actions specified in the Accomplishment Instructions of Boeing
Alert Service Bulletin 737-26A1118, Revision 1, dated April 8, 2004.
Do the actions per the service bulletin. Any applicable corrective
action must be accomplished prior to further flight.
Additional Rework
(b) If, when accomplishing the bond resistance measurement
described in Figure 4 of Boeing Alert Service Bulletin 737-26A1118,
Revision 1, dated April 8, 2004, the resistance is found to be
greater than 1.0 milliohms (0.001 ohms): Before further flight, do
the actions in paragraph (b)(1) or (b)(2) of this AD.
(1) Rework the terminal installation per Figure 4 of the service
bulletin.
(2) Rework the terminal installation per a method approved by
the Manager, Seattle Aircraft Certification Office, FAA.
Actions Accomplished per Boeing Telex and Previous Issue of Service
Bulletin
(c) Actions accomplished before the effective date of this AD
per Boeing Telex M-7200-02-01401, dated September 9, 2002; or Boeing
Alert Service Bulletin 737-26A1118, dated October 17, 2002; are
considered acceptable for compliance with the corresponding action
specified in this AD.
Alternative Methods of Compliance
(d) In accordance with 14 CFR 39.19, the Manager, Seattle
Aircraft Certification Office, 1601 Lind Avenue, SW., Renton,
Washington 98055-4056, is authorized to approve alternative methods
of compliance (AMOCs) for this AD.
Incorporation by Reference
(e) Unless otherwise specified in this AD, the actions shall be
done in accordance with Boeing Alert Service Bulletin 737-26A1118,
Revision 1, dated April 8, 2004. 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 Airplanes, 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
National Archives and Records Administration (NARA). For information
on the availability of this material at NARA, call (202) 741-6030,
or go to: http://www.archives.gov/federal_register/code_of_federal_regulations/ibr_locations.html
.
Effective Date
(f) This amendment becomes effective on October 7, 2004.
Issued in Renton, Washington, on August 20, 2004.
Kevin M. Mullin,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 04-19855 Filed 9-1-04; 8:45 am]
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