[Federal Register Volume 66, Number 124 (Wednesday, June 27, 2001)]
[Rules and Regulations]
[Pages 34091-34094]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 01-15934]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. 2000-NM-308-AD; Amendment 39-12287; AD 2001-13-07]
RIN 2120-AA64
Airworthiness Directives; Boeing Model 737-300, 737-400, 737-500,
737-600, 737-700, 737-800, 757-200, 757-200PF, 757-200CB, and 757-300
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 737-300, 737-400, 737-500, 737-600,
737-700, 737-800, 757-200, 757-200PF, 757-200CB, and 757-300 series
airplanes. This AD requires a test of the two electrical circuits that
close the fuel shutoff valve on the wing spar, and repair, if
necessary. This action is necessary to prevent inability to shut off
the flow of fuel to an engine after an uncontained engine failure,
which could result in a fire spreading to other parts of the airplane.
This action is intended to address the identified unsafe condition.
DATES: Effective August 1, 2001.
The incorporation by reference of certain publications listed in
the regulations is approved by the Director of the Federal Register as
of August 1, 2001.
ADDRESSES: 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 Federal
Aviation Administration (FAA), Transport Airplane Directorate, Rules
Docket, 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: Kathrine Rask, Aerospace Engineer,
Propulsion Branch, ANM-140S, FAA, Seattle Aircraft Certification
Office, 1601 Lind Avenue, SW., Renton, Washington 98055-4056; telephone
(425) 227-1547; fax (425) 227-1181.
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 737-300, 737-
400, 737-500, 737-600, 737-700, 737-800, 757-200, 757-200PF, 757-200CB,
and 757-300 series airplanes was published in the Federal Register on
December 29, 2000 (65 FR 82957). That action proposed to require a test
of the two electrical circuits that close the fuel shutoff valve on the
wing spar, and repair, if necessary.
Explanation of New Relevant Service Information
The FAA has reviewed and approved Boeing Service Bulletin 737-28-
1164, Revision 1, dated May 10, 2001, which describes procedures for a
one-time test of the two electrical circuits that close the fuel
shutoff valve on each wing spar to determine if there is continuity,
and location and repair of any discontinuity. The procedures described
in Revision 1 of the service bulletin are essentially similar to those
described in the original issue of the service bulletin, dated August
24, 2000, which was listed in the proposed rule as the appropriate
source of service information for Boeing Model 737-300, 737-400, and
737-500 series airplanes. Revision 1 merely corrects the location of
two electrical connectors. Accomplishment of the actions specified in
Revision 1 of the service bulletin is intended to adequately address
the identified unsafe condition.
In consideration of this new service information, the FAA has
revised paragraph (a) of this final rule to refer to Boeing Service
Bulletin 737-28-1164, Revision 1, in addition to the original issue of
the service bulletin, as an acceptable source of service information
for accomplishment of paragraph (a) on Boeing Model 737-300, -400, and
-500 series airplanes.
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.
[[Page 34092]]
Support for the Proposal
Two commenters support the proposed rule.
Provide Credit for Use of Telexes
One commenter requests that the FAA revise the proposed AD to give
credit for accomplishment of the proposed actions using the following
telexes:
Boeing All Base Telex M-7200-00-01064, dated April 24,
2000
Boeing Telex SWA-DAL-00-00182H, dated March 27, 2000
Boeing Telex CAL-IAH-00-00681H, dated April 7, 2000
Boeing All Base Telex M-7200-00-01231, dated May 31, 2000
Boeing Telex AAL-AFW-00-00324H, dated March 27, 2000
The commenter states that the instructions in these telexes are
consistent with those in the service bulletins referenced in the
proposed AD. The airplane manufacturer issued the telexes to provide
adequate instructions to operators that wanted to perform the tests on
their airplanes before the applicable service bulletins were available.
The FAA concurs with the commenter's request, and has added Note 3
to this AD to give credit for using the referenced telexes to
accomplish the requirements of this AD before the effective date of
this AD.
Revise Cost Impact Estimate
Two commenters state that the proposed actions have already been
accomplished on certain airplanes in their fleets. The FAA infers that
the commenters are requesting that the FAA revise the ``Cost Impact''
section of the proposed AD to reflect the accomplishment of the
proposed requirements on some airplanes. The FAA concurs with the
commenters' request and has revised the ``Cost Impact'' section of this
AD to reflect that some airplanes have already complied with this AD.
One commenter states that the test, as proposed, takes two hours.
Though the commenter does not specify which airplane model its estimate
applies to, the FAA infers that the commenter is requesting that the
FAA increase the estimate of work hours for Model 737-300, -400, and -
500 series airplanes from one to two work hours. The FAA concurs with
this request, and has revised the ``Cost Impact'' section of this AD
accordingly.
Request To Consider Need for Repetitive Tests
One commenter requests that the FAA and the airplane manufacturer
review the Maintenance Planning Document for the affected airplane
models to assess whether repetitive tests of the circuits subject to
the proposed AD are necessary. The commenter does not request a change
to the proposed rule.
The FAA acknowledges the commenter's concern. At this time, the
Maintenance Planning Document for the Model 737 and 757 series
airplanes includes only a check of the fuel shutoff valve. The
procedure for this check is similar to the functional test that is
performed during production of the airplane, which was described in the
proposed AD, in that the test only verifies that one of the two
circuits needed to supply power for the fuel shutoff valve operates
correctly. The FAA and the airplane manufacturer are coordinating
development of a new functional test that would verify that both
circuits work correctly. No change to the final rule is necessary in
this regard.
Request To Extend Compliance Time
One commenter requests that the FAA extend the compliance time from
6 months to 18 months for the test specified in the proposed AD. The
commenter states that an 18-month compliance time will allow operators
to perform the test in the proposed AD at a regularly scheduled
maintenance interval. The commenter notes that a 6-month compliance
time does not align with the provisions of Air Transport Association
Specification 111, which states, ``to capture the majority of scheduled
maintenance periods, a nominal `intermediate' check described by an
interval of 18 months and an aircraft downtime of one-to-three days
should be considered.''
The FAA does not concur with the commenter's request. The commenter
provides no technical justification for increasing the compliance time
as requested. The unsafe condition addressed by this AD--inability to
shut off the flow of fuel to an engine after an uncontained engine
failure--is a significant safety issue, and the FAA has determined that
the compliance time of 6 months, as proposed, is warranted. This
decision is based on the anticipated rate of latent failures in the
system. In developing an appropriate compliance time for the actions
required by this AD, the FAA considered not only those safety issues,
but the manufacturer's recommendations, parts availability, and the
practical aspect of accomplishing the required test within an interval
paralleling normal scheduled maintenance for the majority of affected
operators. In light of all of these factors, the FAA considers 6 months
an appropriate compliance time wherein safety will not be adversely
affected. No change to the final rule is necessary in this regard.
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 3,403 Model 737-300, 737-400, 737-500, 737-
600, 737-700, 737-800, 757-200, 757-200PF, 757-200CB, and 757-300
airplanes of the affected design in the worldwide fleet.
The FAA estimates that this AD will affect 795 Model 737-300, -400,
and -500 airplanes of U.S. registry. The required test will take
approximately 2 work hours, at an average labor rate of $60 per work
hour. A commenter has advised the FAA that two of these U.S.-registered
airplanes have already been tested according to the requirements of
this AD. Therefore, based on the figures stated above, the FAA
estimates the future cost impact of this AD on U.S. operators of Model
737-300, -400, and -500 series airplanes to be $95,160, or $120 per
airplane.
The FAA estimates that this AD will affect 820 Model 737-600, 737-
700, 737-800, 757-200, 757-200PF, 757-200CB, and 757-300 airplanes of
U.S. registry. The required test will take approximately 3 work hours
on each of these airplanes, at an average labor rate of $60 per work
hour. A commenter has advised the FAA that 30 of these U.S.-registered
airplanes have already been tested according to the requirements of
this AD. Therefore, based on these figures, the FAA estimates the
future cost impact of this AD on U.S. operators of these airplanes to
be $142,200, or $180 per airplane.
The cost impact figures discussed above are based on assumptions
that not all operators have yet accomplished the requirements of this
AD action, and that no more operators would accomplish those actions in
the future if this AD were not adopted. As explained previously,
commenters have advised the FAA that some airplanes have been tested
according to the requirements of this AD, and the estimated future cost
impact has been reduced accordingly in this final rule. The cost impact
figures discussed in AD rulemaking actions represent only the time
necessary to
[[Page 34093]]
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
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:
2001-13-07 Boeing: Amendment 39-12287. Docket 2000-NM-308-AD.
Applicability: The following models and series of airplanes as
listed in the service bulletins below, certificated in any category:
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Boeing special attention
Airplane Model service bulletin
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737-300, 737-400, 737-500................. 737-28-1164, dated August
24, 2000.
737-600, 737-700, 737-800................. 737-28-1160, Revision 1,
dated October 26, 2000.
757-200, 757-200PF, 757-200CB............. 757-28-0060, Revision 1,
dated October 26, 2000.
757-300................................... 757-28-0061, Revision 1,
dated October 26, 2000.
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Note 1: This AD applies to each airplane identified in the
preceding applicability provision, regardless of whether it has been
modified, altered, or repaired in the area subject to the
requirements of this AD. For airplanes that have been modified,
altered, or repaired so that the performance of the requirements of
this AD is affected, the owner/operator must request approval for an
alternative method of compliance in accordance with paragraph (b) of
this AD. The request should include an assessment of the effect of
the modification, alteration, or repair on the unsafe condition
addressed by this AD; and, if the unsafe condition has not been
eliminated, the request should include specific proposed actions to
address it.
Compliance: Required as indicated, unless accomplished
previously.
To prevent inability to shut off the flow of fuel to an engine
after an uncontained engine failure, which could result in a fire
spreading to other parts of the airplane, accomplish the following:
Test and Repair
(a) Within 6 months after the effective date of this AD, perform
a test to determine if there is continuity or to measure voltage, as
applicable, of the two electrical circuits that close the fuel
shutoff valve on the wing spar. Do the test per Boeing Special
Attention Service Bulletin 737-28-1164, dated August 24, 2000, or
Boeing Service Bulletin 737-28-1164, Revision 1, dated May 10, 2001
(for Boeing Model 737-300, 737-400, and 737-500 series airplanes);
or Boeing Special Attention Service Bulletin 737-28-1160, Revision 1
(for Boeing Model 737-600, 737-700, and 737-800 series airplanes);
Boeing Special Attention Service Bulletin 757-28-0060, Revision 1
(for Boeing Model 757-200, 757-200PF, and 757-200CB series
airplanes); or Boeing Special Attention Service Bulletin 757-28-
0061, Revision 1 (for Boeing Model 757-300 series airplanes); all
dated October 26, 2000; as applicable.
(1) For Boeing Model 737-300, 737-400, and 737-500 series
airplanes: If any discontinuity is detected, prior to further
flight, repair per Boeing Service Bulletin 737-28-1164.
(2) For airplane models other than those listed in paragraph
(a)(1) of this AD: If any measurement is not between 21 and 34 volts
direct current (DC), prior to further flight, repair per the
applicable service bulletin.
Note 2: Tests accomplished per Boeing Special Attention Service
Bulletin 737-28-1160 (for Boeing Model 737-600, 737-700, and 737-800
series airplanes), dated June 5, 2000; Boeing Special Attention
Service Bulletin 757-28-0060 (for Boeing Model 757-200, 757-200PF,
and 757-200CB series airplanes), dated June 15, 2000; or Boeing
Special Attention Service Bulletin 757-28-0061, dated June 15, 2000
(for Boeing Model 757-300 series airplanes); as applicable; are
acceptable for compliance with paragraph (a) of this AD.
Note 3: Tests accomplished prior to the effective date of this
AD per Boeing All Base Telex M-7200-00-01064, dated April 24, 2000;
Boeing Telex SWA-DAL-00-00182H, dated March 27, 2000; Boeing Telex
CAL-IAH-00-00681H, dated April 7, 2000; Boeing All Base Telex M-
7200-00-01231, dated May 31, 2000; or Boeing Telex AAL-AFW-00-
00324H, dated March 27, 2000; are acceptable for compliance with
paragraph (a) of this AD.
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 4: 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.
Incorporation by Reference
(d) The actions shall be done in accordance with Boeing Special
Attention Service Bulletin 737-28-1164, dated August 24, 2000;
Boeing Service Bulletin 737-28-1164, Revision 1, dated May 10, 2001;
Boeing Special Attention Service Bulletin 737-28-1160, Revision 1,
dated October 26, 2000; Boeing Special Attention Service Bulletin
757-28-0060, Revision 1, dated October 26, 2000; or Boeing Special
Attention Service Bulletin 757-28-0061, Revision 1, dated October
26, 2000; as applicable. 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
(e) This amendment becomes effective on August 1, 2001.
[[Page 34094]]
Issued in Renton, Washington, on June 19, 2001.
Kalene C. Yanamura,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 01-15934 Filed 6-26-01; 8:45 am]
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