[Federal Register Volume 64, Number 193 (Wednesday, October 6, 1999)]
[Rules and Regulations]
[Pages 54202-54203]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 99-25932]
[[Page 54202]]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. 99-NM-14-AD; Amendment 39-11354; AD 95-04-07 R2]
RIN 2120-AA64
Airworthiness Directives; McDonnell Douglas Model DC-10-10, -15,
and -30 Airplanes, and KC-10A (Military) Airplanes
AGENCY: Federal Aviation Administration, DOT.
ACTION: Final rule.
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SUMMARY: This amendment revises an existing airworthiness directive
(AD), applicable to certain McDonnell Douglas Model DC-10-10, -15, and
-30 airplanes, and KC-10A (military) airplanes, that currently requires
inspections to determine the condition of the lockwires on the forward
engine mount bolts and correction of any discrepancies found. That
amendment also provides for termination of the inspections for some
airplanes by installing retainers on the bolts. That AD was prompted by
reports of stretched or broken lockwires on the forward engine mount
bolts. The actions specified by that AD are intended to prevent broken
lockwires, which could result in loosening of the engine mount bolts,
and subsequent separation of the engine from the airplane. This
amendment provides an additional optional terminating modification and
clarification of the requirements of the previous optional terminating
modification, and removes the reporting requirements for the repetitive
inspections.
DATES: Effective November 10, 1999.
The incorporation by reference of certain publications, as listed
in the regulations, was approved previously by the Director of the
Federal Register as of March 17, 1995 (60 FR 38477, July 27, 1995).
ADDRESSES: The service information referenced in this AD may be
obtained from The Boeing Company, Douglas Products Division, 3855
Lakewood Boulevard, Long Beach, California 90846, Attention: Technical
Publications Business Administration, Dept. C1-L51 (2-60). 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, 3936 Paramount Boulevard,
Lakewood, California; or at the Office of the Federal Register, 800
North Capitol Street, NW., suite 700, Washington, DC.
FOR FURTHER INFORMATION CONTACT: Ron Atmur, Aerospace Engineer,
Airframe Branch, ANM-120L, FAA, Transport Airplane Directorate, Los
Angeles Aircraft Certification Office, 3960 Paramount Boulevard,
Lakewood, California 90712-4137; telephone (562) 627-5224; fax (562)
627-5210.
SUPPLEMENTARY INFORMATION: A proposal to amend part 39 of the Federal
Aviation Regulations (14 CFR part 39) by revising AD 95-04-07 R1,
amendment 39-9317 (60 FR 38477, July 27, 1995), which is applicable to
certain McDonnell Douglas Model DC-10-10, -15, and -30 airplanes, and
KC-10A (military) airplanes, was published in the Federal Register on
July 21, 1999 (64 FR 39104). The action proposed to revise AD 95-04-07
R1 to continue to require inspections to determine the condition of the
lockwires on the forward engine mount bolts and correction of any
discrepancies found. The action also proposed to continue to provide
for termination of the inspections for some airplanes by installing
retainers on the bolts. In addition, the action proposed to provide an
additional optional terminating modification and clarification of the
requirements of the previous optional terminating modification, and
proposed to remove the reporting requirements for the repetitive
inspections.
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 389 airplanes of the affected design in the
worldwide fleet. The FAA estimates that 229 airplanes of U.S. registry
will be affected by this AD.
The inspections that are currently required by AD 95-04-07 R1, and
retained in this AD, will take approximately 2 work hours per airplane
to accomplish, at an average labor rate of $60 per hour. Based on these
figures, the cost impact of the currently required inspections on U.S.
operators is estimated to be approximately $27,480, or $120 per
airplane, per inspection cycle.
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.
Should an operator elect to accomplish the optional terminating
modification, as specified in AD 95-04-07 R1, and the requirements
clarified in this AD, it will take approximately 4 work hours per
airplane to accomplish, at an average labor rate of $60 per hour.
Required parts will cost between $2,744 and $2,822 per airplane. Based
on these figures, the cost impact of the optional terminating
modification specified by AD 95-04-07 R1 on U.S. operators is estimated
to be between $2,984 and $3,062 per airplane.
Should an operator elect to accomplish the optional terminating
modification specified in McDonnell Douglas Service Bulletin DC10-71-
159 that will be provided by this AD, it will take approximately 16
work hours per airplane to accomplish this required action, at an
average labor rate of $60 per work hour. Required parts will cost
between $2,744 and $2,822 per airplane. Based on these figures, the
cost impact of the optional terminating modification provided for by
this AD on U.S. operators is estimated to be between $3,704 and $3,782
per airplane.
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.
[[Page 54203]]
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 revising amendment 39-9317 (60 FR
38477, July 27, 1995), and by adding a new airworthiness directive
(AD), amendment 39-11354, to read as follows:
95-04-07 R2 McDonnell Douglas: Amendment 39-11354. Docket 99-NM-
14-AD. Revises AD 95-04-07 R1, Amendment 39-9317.
Applicability: Model DC-10-30 and KC-10A (military) airplanes on
which bolt retainers have not been installed on the engine mount in
accordance with McDonnell Douglas DC-10 Service Bulletin 71-133,
Revision 6, dated June 30, 1992; and all Model DC-10-10 and -15
airplanes; 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 (d) 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 broken lockwires, which could result in loosening of
the engine mount bolts, and subsequent separation of the engine from
the airplane, accomplish the following:
Restatement of Requirements of AD 95-04-07 R1, Amendment 39-9317
(a) Within 120 days after March 17, 1995 (the effective date of
AD 95-04-07 R1, amendment 39-9317), unless accomplished previously
within the last 750 flight hours prior to March 17, 1995, perform a
visual inspection to detect broken lockwires on the forward engine
mount bolts on engines 1, 2, and 3, in accordance with McDonnell
Douglas Alert Service Bulletin DC10-71A159, Revision 1, dated
January 31, 1995.
(1) If no lockwire is found broken, repeat the inspection
thereafter at intervals not to exceed 750 flight hours.
(2) If any lockwire is found broken, prior to further flight:
Check the torque of the bolt, install a new lockwire, and install a
torque stripe on the bolt, in accordance with the alert service
bulletin. Thereafter at intervals not to exceed 750 flight hours,
perform a visual inspection to detect misalignment of the torque
stripes, and repeat the inspection to detect broken lockwires, in
accordance with the alert service bulletin.
Optional Terminating Actions
(b) For Model DC-10-30 airplanes and KC-10A (military) airplanes
only: Installation of retainers on the engine mount bolts of engines
1, 2, or 3 in accordance with the procedures depicted in Figure 6 of
Revision 6 of McDonnell Douglas DC-10 Service Bulletin 71-133, dated
June 30, 1992, constitutes terminating action for the requirements
of this AD for that engine.
(c) For Model DC-10-10, -15, and -30 airplanes and KC-10A
(military) airplanes: Modification of the forward engine mount bolts
for engine 1, 2, or 3 in accordance with McDonnell Douglas Service
Bulletin DC10-71-159, dated September 6, 1995, or Revision 01, dated
July 28, 1997, constitutes terminating action for the requirements
of this AD for that engine.
Alternative Methods of Compliance
(d) 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 2: Information concerning the existence of approved
alternative methods of compliance with this AD, if any, may be
obtained from the Los Angeles ACO.
Special Flight Permits
(e) 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
(f) Except as provided by paragraphs (b) and (c) of this AD, the
actions shall be done in accordance with McDonnell Douglas Alert
Service Bulletin DC10-71A159, Revision 1, dated January 31, 1995.
This incorporation by reference was approved previously by the
Director of the Federal Register as of March 17, 1995 (60 FR 38477,
July 27, 1995). Copies may be obtained from The Boeing Company,
Douglas Products Division, 3855 Lakewood Boulevard, Long Beach,
California 90846, Attention: Technical Publications Business
Administration, Dept. C1-L51 (2-60). Copies may be inspected at the
FAA, Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton,
Washington; or at the FAA, Transport Airplane Directorate, Los
Angeles Aircraft Certification Office, 3936 Paramount Boulevard,
Lakewood, California; or at the Office of the Federal Register, 800
North Capitol Street, NW., suite 700, Washington, DC.
(g) This amendment becomes effective on November 10, 1999.
Issued in Renton, Washington, on September 29, 1999.
D.L. Riggin,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 99-25932 Filed 10-5-99; 8:45 am]
BILLING CODE 4910-13-U
