[Federal Register Volume 64, Number 220 (Tuesday, November 16, 1999)]
[Rules and Regulations]
[Pages 62109-62110]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 99-29471]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
RIN 2120-AA64
[Docket No. 99-NM-101-AD; Amendment 39-11417; AD 99-23-21]
Airworthiness Directives; Boeing Model 757 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 757 series airplanes, that requires
a modification of the reverse thrust lever assemblies and replacement
of the spring bumper assemblies of the thrust reverser sleeves with new
assemblies. This amendment is prompted by an FAA review of the thrust
reverser system on all transport category airplanes including the
Boeing Model 757 series airplane. The actions specified by this AD are
intended to prevent operation with an energized sync lock or
malfunctioning sleeve locking devices, which could result in the
deployment of a thrust reverser in flight and subsequent reduced
controllability of the airplane.
DATES: Effective December 21, 1999.
The incorporation by reference of certain publications listed in
the regulations is approved by the Director of the Federal Register as
of December 21, 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: Kathrine Rask, Aerospace Engineer,
Propulsion Branch, ANM-140S, FAA, Transport Airplane Directorate,
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 757 series
airplanes was published in the Federal Register on August 23, 1999 (64
FR 45927). That action proposed to require a modification of the
reverse thrust lever assemblies and replacement of the spring bumper
assemblies of the thrust reverser sleeves with new assemblies.
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.
Conclusion
The FAA has determined that air safety and the public interest
require the adoption of the rule as proposed.
Cost Impact
There are approximately 308 airplanes of the affected design in the
worldwide fleet.
The FAA estimates that the modification of the reverse thrust lever
assemblies will be required to be accomplished on 169 U.S. registered
airplanes. It will take approximately 8 work hours per airplane to
accomplish the required modification at an average labor rate of $60
per work hour. Required parts will cost approximately $29 per airplane.
Based on these figures, the cost impact of this required modification
on U.S. operators is estimated to be $86,021, or $509 per airplane.
The FAA estimates that the replacement of the spring bumper
assemblies will be required to be accomplished on 92 U.S. registered
airplanes. It will take approximately 10 work hours per airplane to
accomplish the required replacement at an average labor rate of $60 per
work hour. Required parts will cost approximately
[[Page 62110]]
$5,178 per airplane. Based on these figures, the cost impact of this
required replacement on U.S. operators is estimated to be $531,576, or
$5,778 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.
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:
99-23-21 Boeing: Amendment 39-11417. Docket 99-NM-101-AD.
Applicability: Model 757 series airplanes, as listed in Boeing
Service Bulletin 757-76-0009, Revision 1, dated December 3, 1998, or
Boeing Service Bulletin 757-78-0012, dated August 31, 1989;
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 operation with an energized sync lock or
malfunctioning sleeve locking devices, which could result in
deployment of a thrust reverser in flight and subsequent reduced
controllability of the airplane, accomplish the following:
(a) For airplanes listed in Boeing Service Bulletin 757-76-0009,
Revision 1, dated December 3, 1998: Within 2 years after the
effective date of the AD, replace the reverse thrust switches and
actuators with improved switches and actuators, and modify the
reverse lever links and thrust control levers in accordance with the
service bulletin.
Note 2: Modifications accomplished prior to the effective date
of this AD in accordance with Boeing Service Bulletin 757-76-0009,
dated November 8, 1990, are considered acceptable for compliance
with the applicable action specified in this amendment.
(b) For airplanes listed in Boeing Service Bulletin 757-78-0012,
dated August 31, 1989: Within 2 years after the effective date of
the AD, replace the spring bumper assemblies of the thrust reverser
sleeve with improved assemblies in accordance with the service
bulletin.
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 3: 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
Secs. 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 Service
Bulletin 757-76-0009, Revision 1, dated December 3, 1998, or Boeing
Service Bulletin 757-78-0012, dated August 31, 1989, 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.
(f) This amendment becomes effective on December 21, 1999.
Issued in Renton, Washington, on November 4, 1999.
D.L. Riggin,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 99-29471 Filed 11-15-99; 8:45 am]
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