AD Amdt-39-9244

[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 [<a href="http://www.gpo.gov">www.gpo.gov</a>]
[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]
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