[Federal Register Volume 67, Number 137 (Wednesday, July 17, 2002)]
[Rules and Regulations]
[Pages 46844-46846]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 02-17550]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. 2000-NM-367-AD; Amendment 39-12821; AD 2002-14-21]
RIN 2120-AA64
Airworthiness Directives; Boeing Model 737-600, -700, and -800
Series Airplanes
AGENCY: Federal Aviation Administration, DOT.
ACTION: Final rule.
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SUMMARY: This amendment supersedes an existing airworthiness directive
(AD), applicable to certain Boeing Model 737-600, -700, and -800 series
airplanes, that currently requires repetitive inspections to detect
discrepancies of the quick-disconnect coupling on the fuel hose located
at the fan case firewall; corrective action, if necessary; and
installation of a clamp shell on the coupling to prevent separation of
the coupling halves. This amendment limits the applicability of the
existing requirements, clarifies certain existing requirements, and
requires removal of the clamp shell installed previously and
replacement of the existing quick-disconnect fuel supply hose,
coupling, and strut fitting with new, fixed-B-nut-type parts. Such
replacement ends the requirement for repetitive inspections. The
actions specified by this AD are intended to prevent major fuel leakage
due to excessive wear of the quick-disconnect coupling on the fuel
hose, fire in the engine nacelle, and consequent loss of thrust from
the affected engine, which could result in reduced controllability of
the airplane. This action is intended to address the identified unsafe
condition.
DATES: Effective August 21, 2002.
The incorporation by reference of Boeing Alert Service Bulletin
737-73A1011, Revision 2, dated July 13, 2000, as listed in the
regulations, is approved by the Director of the Federal Register as of
August 21, 2002.
The incorporation by reference of Boeing Alert Service Bulletin
737-73A1011, dated November 25, 1998, as listed in the regulations, was
approved previously by the Director of the Federal Register as of
February 19, 1999 (64 FR 5590, February 4, 1999).
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: Douglas Pegors, Aerospace Engineer,
Propulsion Branch, ANM-140S, FAA, Seattle Aircraft Certification
Office, 1601 Lind Avenue, SW., Renton, Washington 98055-4056; telephone
(425) 227-1446; fax (425) 227-1181.
SUPPLEMENTARY INFORMATION: A proposal to amend part 39 of the Federal
Aviation Regulations (14 CFR part 39) by superseding AD 99-03-08,
amendment 39-11022 (64 FR 5590, February 4, 1999), which is applicable
[[Page 46845]]
to certain Boeing Model 737-600, -700, and -800 series airplanes, was
published in the Federal Register on April 4, 2002 (67 FR 16064). That
action proposed to continue to require repetitive inspections to detect
discrepancies of the quick-disconnect coupling on the fuel hose located
at the fan case firewall; corrective action, if necessary; and
installation of a clamp shell on the coupling to prevent separation of
the coupling halves. That action also proposed to limit the
applicability of the existing requirements, clarify certain existing
requirements, and require removal of the clamp shell installed
previously and replacement of the existing quick-disconnect fuel supply
hose, coupling, and strut fitting with new, fixed-B-nut-type parts.
Such replacement would end the requirement for repetitive inspections.
Comments
Interested persons have been afforded an opportunity to participate
in the making of this amendment. No comments were submitted in response
to the proposal or the FAA's determination of the cost to the public.
Explanation of Change Made to Proposal
For clarification, the FAA has revised the definition of a
``general visual inspection'' in this final rule.
Conclusion
The FAA has determined that air safety and the public interest
require the adoption of the rule with the change previously described.
The FAA has determined that this change will neither increase the
economic burden on any operator nor increase the scope of the AD.
Cost Impact
There are approximately 560 airplanes of the affected design in the
worldwide fleet. The FAA estimates that 271 airplanes of U.S. registry
will be affected by this AD.
The inspection that is currently required by AD 99-03-08 takes
approximately 1 work hour per airplane to accomplish, at an average
labor rate of $60 per work hour. Based on these figures, the cost
impact of the currently required inspection on U.S. operators is
estimated to be $16,260, or $60 per airplane, per inspection cycle.
For airplanes on which it has not already been accomplished during
production, the installation of a clamp shell required by AD 99-03-08
takes approximately 2 work hours per airplane to accomplish, at an
average labor rate of $60 per work hour. Required parts are provided by
the manufacturer at no cost to the operators. Based on these figures,
the cost impact of the currently required installation is estimated to
be $120 per airplane.
The new replacement that is required in this AD action will take
approximately 4 work hours per airplane to accomplish, at an average
labor rate of $60 per work hour. Required parts will be provided by the
manufacturer at no cost to the operators. Based on these figures, the
cost impact of the replacement on U.S. operators is estimated to be
$65,040, or $240 per airplane.
The cost impact figures discussed above are 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
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 removing amendment 39-11022 (64 FR
5590, February 4, 1999), and by adding a new airworthiness directive
(AD), amendment 39-12821, to read as follows:
2002-14-21 Boeing: Amendment 39-12821. Docket 2000-NM-367-AD.
Supersedes AD 99-03-08, Amendment 39-11022.
Applicability: Model 737-600, -700, and -800 series airplanes,
listed in Group I or II of Boeing Alert Service Bulletin 737-
73A1011, Revision 2, dated July 13, 2000; certificated in any
category.
Note 1: This AD applies to Model 737-700 series airplanes in an
increased-gross-weight configuration, as listed in the service
bulletin referred to in the applicability statement of this AD.
Note 2: 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 (f)(1)
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 major fuel leakage due to excessive wear of the
quick-disconnect coupling on the fuel hose, fire in the engine
nacelle, and consequent loss of thrust from the affected engine,
which could result in reduced controllability of the airplane,
accomplish the following:
Restatement of Requirements of AD 99-03-08
Repetitive Inspections and Corrective Actions
(a) For airplanes listed in Group I of Boeing Alert Service
Bulletin 737-73A1011, Revision 2, dated July 13, 2000: Within 7 days
after February 19, 1999 (the effective date of AD 99-03-08,
amendment 39-11022), perform a general visual inspection to detect
discrepancies (i.e., fuel leakage, wear of the
[[Page 46846]]
lock teeth, or missing lock pins on the coupling nut) of the quick-
disconnect coupling on the fuel hose located at the fan case
firewall, in accordance with Boeing Alert Service Bulletin 737-
73A1011, dated November 25, 1998; or Revision 2, dated July 13,
2000.
(1) If no discrepancy is detected, repeat the inspection
thereafter at intervals not to exceed 500 flight hours, until the
installation required by paragraph (b) of this AD is accomplished.
(2) If any discrepancy is detected, prior to further flight,
perform follow-on corrective actions, as applicable, in accordance
with TABLE 1. of the Accomplishment Instructions of the alert
service bulletin, and repeat the inspection thereafter at the time
specified in TABLE 1. of the Accomplishment Instructions of the
alert service bulletin.
Installation of Clamp Shell and Repetitive Inspections
(b) For airplanes listed in Group I of Boeing Alert Service
Bulletin 737-73A1011, Revision 2, dated July 13, 2000: Within 30
days after February 19, 1999, install an Aeroquip Clamp Shell,
having part number (P/N) AE20074-165, on the quick-disconnect
coupling on the fuel hose, which is located at the fan case
firewall, in accordance with Boeing Alert Service Bulletin 737-
73A1011, dated November 25, 1998; or Revision 2, dated July 13,
2000. Accomplishment of such installation terminates the repetitive
inspection requirements of paragraphs (a)(1) and (a)(2) of this AD.
New Requirements of This AD
Note 3: For the purposes of this AD, a general visual inspection
is defined as: ``A visual examination of an interior or exterior
area, installation, or assembly to detect obvious damage, failure,
or irregularity. This level of inspection is made from within
touching distance unless otherwise specified. A mirror may be
necessary to enhance visual access to all exposed surfaces in the
inspection area. This level of inspection is made under normally
available lighting conditions such as daylight, hangar lighting,
flashlight, or droplight and may require removal or opening of
access panels or doors. Stands, ladders, or platforms may be
required to gain proximity to the area being checked.''
Note 4: Accomplishment of the requirements of paragraphs (a),
(b), and (c) of this AD according to Boeing Alert Service Bulletin
737-73A1011, Revision 1, dated April 15, 1999, is acceptable for
compliance with those paragraphs.
Repetitive Inspections
(c) For airplanes listed in Groups I and II of Boeing Alert
Service Bulletin 737-73A1011, Revision 2, dated July 13, 2000:
Within 1,000 flight hours after installation of the clamp shell
either per paragraph (b) of this AD (for Group I airplanes) or
during production (for Group II airplanes), perform the inspection
specified in paragraph (a) of this AD.
Note 5: The repetitive inspections required by paragraph (c) of
this AD were previously required by paragraph (b) of AD 99-03-08.
(1) If no discrepancy is detected, repeat the inspection
thereafter at intervals not to exceed 1,000 flight hours.
(2) If any discrepancy is detected, prior to further flight,
perform follow-on corrective actions, as applicable, in accordance
with Figures 1 and 3 of the Accomplishment Instructions of the alert
service bulletin, as applicable, and repeat the inspection
thereafter at the time specified in TABLE 1. of the Accomplishment
Instructions of the alert service bulletin.
Replacement of Existing Parts
(d) For airplanes listed in Groups I and II of Boeing Alert
Service Bulletin 737-73A1011, Revision 2, dated July 13, 2000:
Within 3 years after the effective date of this AD, remove the clamp
shell installed per paragraph (b) of this AD (for Group I airplanes)
or during production (for Group II airplanes), and replace the
existing quick-disconnect fuel hose, coupling, and strut fitting
with new, fixed-B-nut-type parts, in accordance with Boeing Alert
Service Bulletin 737-73A1011, Revision 2, dated July 13, 2000. Such
replacement terminates the repetitive inspections required by
paragraphs (a)(1), (a)(2), and (c) of this AD, as applicable.
Spares
(e) After the effective date of this AD, no one may install a
quick-disconnect fuel supply hose, coupling, or strut fitting with a
part number listed in the ``Existing Part Number'' column of the
table under paragraph 2.E. of Boeing Alert Service Bulletin 737-
73A1011, Revision 2, dated July 13, 2000, on any airplane.
Alternative Methods of Compliance
(f)(1) 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.
(2) Alternative methods of compliance, approved previously in
accordance with AD 99-03-08, amendment 39-11022, are approved as
alternative methods of compliance with paragraphs (a), (b), and (c)
of this AD.
Note 6: 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
(g) 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
(h) The actions shall be done in accordance with Boeing Alert
Service Bulletin 737-73A1011, dated November 25, 1998; or Boeing
Alert Service Bulletin 737-73A1011, Revision 2, dated July 13, 2000.
(1) The incorporation by reference of Boeing Alert Service
Bulletin 737-73A1011, Revision 2, dated July 13, 2000, is approved
by the Director of the Federal Register in accordance with 5 U.S.C.
552(a) and 1 CFR part 51.
(2) The incorporation by reference of Boeing Alert Service
Bulletin 737-73A1011, dated November 25, 1998, was approved
previously by the Director of the Federal Register as of February
19, 1999 (64 FR 5590, February 4, 1999).
(3) 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
(i) This amendment becomes effective on August 21, 2002.
Issued in Renton, Washington, on July 8, 2002.
Vi Lipski,
Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 02-17550 Filed 7-16-02; 8:45 am]
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