[Federal Register Volume 59, Number 217 (Thursday, November 10, 1994)]
[Unknown Section]
[Page 0]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 94-26875]
[[Page Unknown]]
[Federal Register: November 10, 1994]
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DEPARTMENT OF TRANSPORTATION
14 CFR Part 39
[Docket No. 94-NM-65-AD; Amendment 39-9056; AD 94-22-07]
Airworthiness Directives; McDonnell Douglas Model DC-8-70 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 all McDonnell Douglas Model DC-8-70 series
airplanes, that currently requires replacement of all attachment screws
at the exhaust nozzle plug splice, and a check of nut plates for
running torque and replacement of nut plates, if necessary. This
amendment requires modification of the engine exhaust plug assemblies
as terminating action for the currently required replacement and check.
This amendment is prompted by reports of loose or missing attachments
at the splice joint of the engine forward and aft exhaust plugs, and
loss of the rear exhaust plug following an engine bird strike. The
actions specified by this AD are intended to prevent reduced integrity
of the engine exhaust plug installation, which may lead to separation
of exhaust plugs from the airplane, and create a hazard to persons and
property on the ground.
DATES: Effective December 12, 1994.
The incorporation by reference of certain publications listed in
the regulations is approved by the Director of the Federal Register as
of December 12, 1994.
ADDRESSES: The service information referenced in this AD may be
obtained from McDonnell Douglas Corporation, P.O. Box 1771, Long Beach,
California 90801-1771, Attention: Business Unit Manager, Technical
Administrative Support, Dept. L51, M.C. 2-98. 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 FAA, Transport Airplane Directorate, Los Angeles
Aircraft Certification Office, 3229 East Spring Street, Long Beach,
California; or at the Office of the Federal Register, 800 North Capitol
Street, NW., suite 700, Washington, DC.
FOR FURTHER INFORMATION CONTACT: Robert Baitoo, Aerospace Engineer,
Propulsion Branch, ANM-141L, FAA, Transport Airplane Directorate, Los
Angeles Aircraft Certification Office, 3229 East Spring Street, Long
Beach, California 90806-2425; telephone (310) 988-5245; fax (310) 988-
5210.
SUPPLEMENTARY INFORMATION: A proposal to amend part 39 of the Federal
Aviation Regulations (14 CFR part 39) by superseding AD 83-02-05,
amendment 39-4544 (48 FR 5539, February 7, 1983), which is applicable
to all McDonnell Douglas Model DC-8-70 series airplanes, was published
in the Federal Register on July 27, 1994 (59 FR 38144). The action
proposed to require replacement of all attachment screws at the exhaust
nozzle plug splice, and a check of nut plates for running torque and
replacement of nut plates, if necessary. The action also proposed to
require modification of the engine exhaust plug assemblies; when
accomplished, this modification would terminate the need for the
currently required replacement and check.
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.
One commenter supports the proposed rule.
One commenter requests that the compliance time for the
accomplishment of the modification be extended from the proposed 24
months to 60 months. This commenter states that it would have to
procure additional spare engines and would need to special schedule its
fleet of airplanes to accomplish this modification within the proposed
compliance time. This would entail considerable expense over what was
estimated in the FAA's cost impact analysis. The commenter indicates
that a compliance time of 60 months would allow the modification to be
accomplished during regularly scheduled maintenance, thereby
eliminating any additional expenses.
The FAA does not concur. In developing an appropriate compliance
time for this action, the FAA considered the safety implications, parts
availability, and the practical aspect of installing the required
modification during normal maintenance schedules. In light of this, the
FAA does not consider it appropriate to change the compliance time for
all operators based on the unique circumstances of an individual
operator. On the other hand, paragraph (c) of the AD provides that an
individual may request an adjustment of compliance time that provides
an acceptable level of safety, and this would be the appropriate means
for the commenter to seek the requested relief.
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 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.
There are approximately 110 Model DC-8-70 series airplanes of the
affected design in the worldwide fleet. The FAA estimates that 78
airplanes of U.S. registry will be affected by this AD, that it will
take approximately 46 work hours per airplane to accomplish the
required modification, and that the average labor rate is $55 per work
hour. Required parts will cost approximately $21,400 per airplane.
Based on these figures, the total cost impact of the AD on U.S.
operators is estimated to be $1,866,540, or $23,930 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 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.
Sec. 39.13 [Amended]
2. Section 39.13 is amended by removing amendment 39-4544 (48 FR
5539, February 7, 1983), and by adding a new airworthiness directive
(AD), amendment 39-9056, to read as follows:
94-22-07 McDonnell Douglas: Amendment 39-9056. Docket 94-NM-65-AD.
Supersedes AD 83-02-05, Amendment 39-4544.
Applicability: All Model DC-8-70 series airplanes, certificated
in any category.
Compliance: Required as indicated, unless accomplished
previously.
To prevent reduced integrity of the engine exhaust plug
installation, which may lead to separation of exhaust plugs from the
airplane, and create a hazard to persons and property on the ground,
accomplish the following:
(a) Within 300 flight hours after February 7, 1983 (the
effective date of AD 83-02-05, amendment 39-4544), accomplish the
procedures specified in paragraphs (a)(1) and (a)(2) of this AD in
accordance with McDonnell Douglas DC-8-70 Alert Service Bulletin
A78-107, dated November 30, 1982; McDonnell Douglas DC-8-70 Service
Bulletin 78-107, dated January 16, 1984; or McDonnell Douglas DC-8-
70 Service Bulletin 78-107, Revision 1, dated June 12, 1984.
(1) Replace all NAS560XK4-5 screws with NAS560XK4-4 screws at
the exhaust nozzle plug splice.
(2) Check nut plates for running torque and replace all nut
plates not meeting the minimum run down torque of five inch-pounds.
(b) Within 24 months after the effective date of this AD, modify
the engine exhaust plug assemblies in accordance with McDonnell
Douglas DC-8-70 Service Bulletin 78-112, Revision 2, dated March 8,
1994. Accomplishment of this modification constitutes terminating
action for the replacement and check requirements of paragraph (a)
of this AD.
(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, Los Angeles 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, Los Angeles ACO.
Note: Information concerning the existence of approved
alternative methods of compliance with this AD, if any, may be
obtained from the Los Angeles ACO.
(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.
(e) The modification shall be done in accordance with McDonnell
Douglas DC-8-70 Service Bulletin 78-112, Revision 2, dated March 8,
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 McDonnell Douglas Corporation,
P.O. Box 1771, Long Beach, California 90801-1771, Attention:
Business Unit Manager, Technical Administrative Support, Dept. L51,
M.C. 2-98. Copies may be inspected at the FAA, Transport Airplane
Directorate, 1601 Lind Avenue, SW., Renton, Washington; or at FAA,
Transport Airplane Directorate, Los Angeles Aircraft Certification
Office, 3229 East Spring Street, Long Beach, California 90806-2425;
or at the Office of the Federal Register, 800 North Capitol Street,
NW., suite 700, Washington, DC.
(f) This amendment becomes effective on December 12, 1994.
Issued in Renton, Washington, on October 25, 1994.
Darrell M. Pederson,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 94-26875 Filed 11-9-94; 8:45 am]
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