[Federal Register Volume 65, Number 10 (Friday, January 14, 2000)]
[Rules and Regulations]
[Pages 2289-2291]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 00-878]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. 99-NM-58-AD; Amendment 39-11512; AD 2000-01-14]
RIN 2120-AA64
Airworthiness Directives; Boeing Model 777 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 777 series airplanes, that requires
the replacement of fuse pins in the attachment fittings and support
fittings of the main landing gear with new, improved fuse pins. This
amendment is prompted by a report of corrosion of a
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fuse pin of a similar design on the main landing gear of a Boeing Model
767 series airplane. The actions specified by this AD are intended to
prevent corrosion and subsequent fracture of the fuse pins, which could
result in collapse of the main landing gear and the loss of the inboard
flap and spoilers.
DATES: Effective February 18, 2000.
The incorporation by reference of certain publications listed in
the regulations is approved by the Director of the Federal Register as
of February 18, 2000.
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: Stan Wood, Aerospace Engineer,
Airframe Branch, ANM-120S, FAA, Transport Airplane Directorate, Seattle
Aircraft Certification Office, 1601 Lind Avenue, SW., Renton,
Washington 98055-4056; telephone (425) 227-2772; 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 Boeing Model 777 series airplanes
was published in the Federal Register on August 20, 1999 (64 FR 45476).
That action proposed to require the replacement of fuse pins in the
attachment fittings and support fittings of the main landing gear with
new, improved fuse pins.
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.
Request To Correct Error in Statement of Unsafe Condition
One commenter states that the unsafe condition, as stated in the
notice of proposed rulemaking (NPRM), is incorrect, and requests that
it be corrected. The NPRM states that fracture of the fuse pins could
result in collapse of the main landing gear and the loss of the inboard
flap and outboard spoilers. The commenter states that the inboard
spoilers, not the outboard, could be lost. The FAA concurs with the
commenter's request and its rationale and has revised this final rule
accordingly.
Request To Reference New Service Information
One commenter requests that the NPRM be revised to reference Boeing
Service Bulletin 777-57A0029, Revision 1, dated August 12, 1999, as the
source of service information for the accomplishment of the actions
required by this AD. (The NPRM references Boeing Alert Service Bulletin
777-57A0029, dated December 22, 1998, as the appropriate source of
service information.)
The FAA concurs with the commenter's request. Since the issuance
of the NPRM, the FAA has reviewed and approved Boeing Service Bulletin
777-57A0029, Revision 1. The FAA has determined that Revision 1 of the
service bulletin adds no new requirements, but provides clarification
of some instructions, which will assist operators in accomplishing the
requirements of this AD. Therefore, the FAA has revised paragraph (a)
of the final rule to reference Boeing Service Bulletin 777-57A0029,
Revision 1, in addition to the original issue of Boeing Alert Service
Bulletin 777-57A0029, as appropriate sources of service information.
In addition, the FAA finds that Revision 1 of the service bulletin
eliminates one airplane from the effectivity listing. (The intent of
the service bulletin was accomplished on that airplane during
production.) Therefore, the applicability of this final rule has been
revised to state that this AD is applicable to airplanes listed in
Boeing Service Bulletin 777-57A0029, Revision 1, rather than airplanes
listed in the original issue of Boeing Alert Service Bulletin 777-
57A0029 (as proposed in the NPRM). The FAA finds that this revision
does not necessitate reopening the comment period, because it is
relieving in nature (the change reduces the applicability of this AD by
one airplane). Also, one airplane has been subtracted from the number
of affected airplanes in the worldwide fleet, as stated in the cost
impact section of the preamble of this final rule.
Request To Revise Compliance Time
One commenter requests that the FAA revise the compliance threshold
of this AD from 48 months since date of manufacture to 1,500 days since
the delivery date of the airplane. The commenter states that 1,500 days
would better align with operators' scheduled maintenance intervals. The
commenter also states that ``'date of manufacture' is ill-defined.''
The FAA does not concur with the commenter's requests. The FAA
finds that there is no technical justification for changing the
threshold from 48 months to 1,500 days, as the commenter requests. In
developing an appropriate compliance time for this AD, the FAA
considered not only the manufacturer's recommendation in the service
bulletin, but the degree of urgency associated with addressing the
subject unsafe condition. The FAA finds a compliance time of 48 months
since date of manufacture or 18 months after the effective date of the
AD, whichever occurs later, for initiating the required actions to be
warranted, in that it represents an appropriate interval of time
allowable for affected airplanes to continue to operate without
compromising safety. In addition, the FAA points out that the
compliance time proposed in the NPRM is essentially the same as that
recommended by the manufacturer in the service bulletin (48 months
after delivery or 18 months after receipt of the service bulletin,
whichever is later). With regard to referring to the delivery date of
the airplane, rather than the date of manufacture, the FAA finds that
there is no technical justification for such a change. The FAA refers
to ``date of manufacture'' rather than ``delivery date'' of an airplane
because the airplane may not be ``delivered'' until long after it is
manufactured. Also, the date of manufacture can be readily discovered
through the serial number of the airplane. 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 162 Model 777 series airplanes of the
affected design in the worldwide fleet. The FAA estimates that 34
airplanes of U.S. registry will be affected by this AD, that it will
take between 5 and 39 work hours per airplane to accomplish the
required actions, and that the average labor rate is $60 per work hour.
Required parts will cost between $3,090 and $8,710 per airplane. Based
on these figures, the cost impact of the AD on U.S. operators is
estimated to be
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between $3,390 and $11,050 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.
Regulatory Impact
The regulations adopted herein will not have substantial direct
effects 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, in
accordance with Executive Order 12612, it is determined that this final
rule does not have sufficient federalism implications to warrant the
preparation of a Federalism Assessment.
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:
2000-01-14 Boeing: Amendment 39-11512. Docket 99-NM-58-AD.
Applicability: Model 777 series airplanes, as listed in Boeing
Service Bulletin 777-57A0029, Revision 1, dated August 12, 1999;
certificated in any category.
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 (c) 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 corrosion and subsequent fracture of the fuse pins in
the main landing gear attachment and support fittings, which could
result in collapse of the main landing gear and the loss of the
inboard flap and spoilers, accomplish the following:
Replacement
(a) Within 48 months since date of manufacture, or 18 months
after the effective date of this AD, whichever occurs later, replace
the main landing gear fuse pins with new, improved fuse pins in
accordance with Boeing Alert Service Bulletin 777-57A0029, dated
December 22, 1998; or Boeing Service Bulletin 777-57A0029, Revision
1, dated August 12, 1999.
Spares
(b) As of the effective date of this AD, no person shall install
a main landing gear fuse pin having part number 112W1728-1,
112W1728-3, or 115W1670-1 on any airplane.
Alternative Methods of Compliance
(c) 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, Transport Airplane Directorate. 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 2: 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
(d) 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
(e) The actions shall be done in accordance with Boeing Alert
Service Bulletin 777-57A0029, dated December 22, 1998; or Boeing
Service Bulletin 777-57A0029, Revision 1, dated August 12, 1999.
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.
(f) This amendment becomes effective on February 18, 2000.
Issued in Renton, Washington, on January 7, 2000.
Donald L. Riggin,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 00-878 Filed 1-13-00; 8:45 am]
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