[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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