[Federal Register Volume 60, Number 105 (Thursday, June 1, 1995)]
[Rules and Regulations]
[Pages 28524-28525]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 95-12826]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. 94-NM-176-AD; Amendment 39-9244; AD 95-11-11]
Airworthiness Directives; McDonnell Douglas Model DC-10-10, -15,
-30, -40, and KC-10 (Military) 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 McDonnell Douglas DC-10 and KC-10 series
airplanes, that requires repetitive eddy current inspections to detect
fatigue cracking of the pylon aft bulkhead flange, upper pylon box web,
fitting radius, and adjacent tangent areas; and repair, if necessary.
This amendment is prompted by fatigue cracking found in the wing pylon
aft bulkheads on two airplanes. The actions specified by this AD are
intended to prevent failure of the wing pylon aft bulkhead due to
fatigue cracking, which could lead to separation of the engine and
pylon from the airplane.
DATES: Effective July 3, 1995.
The incorporation by reference of certain publications listed in
the regulations is approved by the Director of the Federal Register as
of July 3, 1995.
ADDRESSES: The service information referenced in this AD may be
obtained from McDonnell Douglas Corporation, 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, Los Angeles Aircraft Certification Office,
Transport Airplane Directorate, 3960 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: Maureen Moreland, Aerospace Engineer,
Airframe Branch, ANM-120L, Los Angeles Aircraft Certification Office,
FAA, Transport Airplane Directorate, 3960 Paramount Boulevard,
Lakewood, California 90712; telephone (310) 627-5238; fax (310) 627-
5210.
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 McDonnell Douglas DC-10
and KC-10 series airplanes was published in the Federal Register on
January 18, 1995 (60 FR 3590). That action proposed to require
repetitive eddy current inspections to detect fatigue cracking of the
pylon aft bulkhead flange, upper pylon box web, fitting radius, and
adjacent tangent areas; and repair, if necessary.
Interested persons have been afforded an opportunity to participate
in the making of this amendment. Due consideration has been given to
the comments received.
One commenter supports the proposal.
Another commenter expresses concern that enough spare parts may not
be available to affected operators to comply with the proposed rule.
This commenter requests that the FAA require the McDonnell Douglas
Corporation to stock enough spare aft bulkheads and attachment hardware
prior to release of the final rule in order to accommodate operators
that may need to replace cracked parts. The FAA does not concur with
this request. The FAA has received no indication that a problem exists
with regard to the availability of parts associated with the
requirements of this AD action. This AD mandates inspections to detect
cracks in various items, and repair of any items that are found to be
cracked. Such repair would be required in order to keep the airplane
airworthy, regardless of whether or not this AD is issued. If the
availability of repair parts should become a problem, paragraph (d) of
this final rule provides operators with the opportunity to request use
of an alternative method of compliance with the AD until parts can be
located.
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 as proposed.
There are approximately 436 Model DC-10 and KC-10 series airplanes
of the affected design in the worldwide fleet. The FAA estimates that
269 airplanes of U.S. registry will be affected by this AD, that it
will take approximately 8 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 $129,120, or $480 per airplane, per
inspection cycle.
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)
[[Page 28525]] 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 adding the following new
airworthiness directive:
95-11-11 McDonnell Douglas: Amendment 39-9244. Docket 94-NM-176-AD.
Applicability: Model DC-10-10, -15, -30, -40, and KC-10
(military) series airplanes; as listed in McDonnell Douglas Alert
Service Bulletin A54-106, Revision 2, dated November 3, 1994;
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 (d) 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 prevent failure of the wing pylon aft bulkhead due to fatigue
cracking, which could lead to separation of the engine and pylon
from the airplane, accomplish the following:
(a) Prior to the accumulation of 1,800 landings after the
effective date of this AD, conduct an eddy current inspection to
detect fatigue cracks in the pylon aft bulkhead flange, upper pylon
box web, fitting radius, and adjacent tangent areas, in accordance
with McDonnell Douglas Alert Service Bulletin A54-106, Revision 2,
dated November 3, 1994. Repeat this inspection thereafter at
intervals not to exceed 1,800 landings.
(b) If any crack(s) is found during any inspection required by
paragraph (a) of this AD, prior to further flight, repair in
accordance with a method approved by the Manager, Los Angeles
Aircraft Certification Office (ACO), FAA, Transport Airplane
Directorate.
(c) Accomplishment of the gap inspection and necessary shimming
in accordance with ``Phase III,'' as specified in McDonnell Douglas
Alert Service Bulletin A54-106, Revision 2, dated November 3, 1994,
constitutes terminating action for the inspections required by
paragraph (a) of this AD.
(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 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.
(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.
(f) The inspection shall be done in accordance with McDonnell
Douglas Alert Service Bulletin A54-106, Revision 2, dated November
3, 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, 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, Los Angeles Aircraft Certification Office, Transport Airplane
Directorate, 3960 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 July 3, 1995.
Issued in Renton, Washington, on May 19, 1995.
Darrell M. Pederson,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 95-12826 Filed 5-31-95; 8:45 am]
BILLING CODE 4910-13-U
