[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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