[Federal Register Volume 60, Number 49 (Tuesday, March 14, 1995)]
[Rules and Regulations]
[Pages 13623-13624]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 95-5782]
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DEPARTMENT OF TRANSPORTATION
14 CFR Part 39
[Docket No. 94-NM-147-AD; Amendment 39-9171; AD 95-06-01]
Airworthiness Directives; Boeing Model 747-200 and -300 Series
Airplanes Equipped With General Electric CF6-80C2 Series Engines
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 747-200 and -300 series airplanes,
that requires various inspections and functional tests of the thrust
reverser control and indication system, and correction of any
discrepancy found. This amendment is prompted by an investigation to
determine the controllability of Model 747 series airplanes following
an in-flight thrust reverser deployment, which has revealed that, in
the event of thrust reverser deployment during high-speed climb or
during cruise, these airplanes could experience control problems. The
actions specified by this AD are intended to ensure the integrity of
the fail safe features of the thrust reverser system by preventing
possible failure modes in the thrust reverser control system that can
result in inadvertent deployment of a thrust reverser during flight.
DATES: Effective April 13, 1995.
The incorporation by reference of certain publications listed in
the regulations is approved by the Director of the Federal Register as
of April 13, 1995.
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: G. Michael Collins, Aerospace
Engineer, Propulsion Branch, ANM-140S, FAA, Transport Airplane
Directorate, Seattle Aircraft Certification Office, 1601 Lind Avenue,
SW., Renton, Washington 98055-4056; telephone (206) 227-2689; fax (206)
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 747-200 and -
300 series airplanes was published in the Federal Register on November
8, 1994 (59 FR 55595). That action proposed to require various
inspections and functional tests of the thrust reverser control and
indication system on certain Model 747-200 and -300 series airplanes,
and the correction of any discrepancy found during the inspections and
tests.
Interested persons have been afforded an opportunity to participate
in the making of this amendment. Due consideration has been given to
the two comments received.
Both commenters support the proposed rule.
As a result of recent communications with the Air Transport
Association (ATA) of America, the FAA has learned that, in general,
some operators may misunderstand the legal effect of AD's on airplanes
that are identified in the applicability provision of the AD, but that
have been altered or repaired in the area addressed by the AD. The FAA
points out that all airplanes identified in the applicability provision
of an AD are legally subject to the AD. If an airplane has been altered
or repaired in the affected area in such a way as to affect compliance
with the AD, the owner or operator is required to obtain FAA approval
for an alternative method of compliance with the AD, in accordance with
the paragraph of each AD that provides for such approvals. A note has
been added to this final rule to clarify this requirement.
The FAA has recently reviewed the figures it has used over the past
several years in calculating the economic impact of AD activity. In
order to account for various inflationary costs in the airline
industry, the FAA has determined that it is necessary to increase the
labor rate used in these calculations from $55 per work hour to $60 per
work hour. The economic impact information, below, has been revised to
reflect this increase in the specified hourly labor rate.
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.
There are approximately 9 Model 747-200 and -300 series airplanes
of the affected design in the worldwide fleet. The FAA estimates that 2
airplanes of U.S. registry will be affected by this AD, that it will
take approximately 33 work hours per airplane to accomplish the
required actions, and that the average labor rate is $60 per work hour.
Based on these figures, the total cost impact of the AD on U.S.
operators is estimated to be $3,960, or $1,980 per airplane.
The total 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.
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 [[Page 13624]] 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. App. 1354(a), 1421 and 1423; 49 U.S.C.
106(g); and 14 CFR 11.89.
39.13 [Amended]
2. Section 39.13 is amended by adding the following new
airworthiness directive:
95-06-01 Boeing: Amendment 39-9171. Docket 94-NM-147-AD.
Applicability: Model 747-200 and -300 series airplanes equipped
with General Electric CF6-80C2 series engines with Power Management
Control (PMC) engine controls, 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 use the authority
provided in paragraph (e) to request approval from the FAA. This
approval may address either no action, if the current configuration
eliminates the unsafe condition; or different actions necessary to
address the unsafe condition described in this AD. Such a request
should include an assessment of the effect of the changed
configuration on the unsafe condition addressed by this AD. In no
case does the presence of any modification, alteration, or repair
remove any airplane from the applicability of this AD.
Compliance: Required as indicated, unless accomplished
previously.
To ensure the integrity of the fail safe features of the thrust
reverser system, accomplish the following:
(a) Within 90 days after the effective date of this AD, perform
tests of the position switch module and the cone brake of the center
drive unit (CDU) on each thrust reverser, and perform an inspection
to detect damage to the bullnose seal on the translating sleeve on
each thrust reverser, in accordance with paragraphs III.A. through
III.C. of the Accomplishment Instructions of Boeing Service Bulletin
747-78A2130, dated May 26, 1994. Repeat the tests and inspection
thereafter at intervals not to exceed 1,000 hours time-in-service.
(b) Within 9 months after the effective date of this AD, perform
inspections and functional tests of the thrust reverser control and
indication system in accordance with paragraphs III.D. through
III.F., III.H., and III.I. of the Accomplishment Instructions of
Boeing Service Bulletin 747-78A2130, dated May 26, 1994. Repeat
these inspections and functional tests thereafter at intervals not
to exceed 18 months.
(c) If any of the inspections and/or functional tests required
by this AD cannot be successfully performed, or if any discrepancy
is found during those inspections and/or functional tests,
accomplish either paragraph (c)(1) or (c)(2) of this AD.
(1) Prior to further flight, correct the discrepancy found, in
accordance with Boeing Alert Service Bulletin 747-78A2130, dated May
26, 1994. Or
(2) The airplane may be operated in accordance with the
provisions and limitations specified in an operator's FAA-approved
Minimum Equipment List (MEL), provided that no more than one thrust
reverser on the airplane is inoperative.
(d) Within 10 days after performing each initial inspection and
test required by this AD, submit a report of the inspection and/or
test results, both positive and negative, to the FAA, Seattle
Aircraft Certification Office (ACO), ANM-100S, 1601 Lind Avenue,
SW., Renton, Washington 98055-4056; fax (206) 227-1181. Information
collection requirements contained in this regulation have been
approved by the Office of Management and Budget (OMB) under the
provisions of the Paperwork Reduction Act of 1980 (44 U.S.C. 3501 et
seq.) and have been assigned OMB Control Number 2120-0056.
(e) 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.
(f) 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.
(g) The inspections, corrections of discrepancies, and tests
shall be done in accordance with Boeing Alert Service Bulletin 747-
78A2130, dated May 26, 1994. 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.
(h) This amendment becomes effective on April 13, 1995.
Issued in Renton, Washington, on March 3, 1995.
Darrell M. Pederson,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 95-5782 Filed 3-13-95; 8:45 am]
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