[Federal Register Volume 60, Number 227 (Monday, November 27, 1995)]
[Rules and Regulations]
[Pages 58212-58213]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 95-28797]



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DEPARTMENT OF TRANSPORTATION
14 CFR Part 39

[Docket No. 95-NM-50-AD; Amendment 39-9433; AD 95-24-01]


Airworthiness Directives; McDonnell Douglas Model DC-10-10 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-10-10 series airplanes, that 
requires inspections of the wings to detect cracks in the aft spar 
lower cap, in certain stringer butterfly clips on the bulkheads, and in 
certain fastener holes; and repair, if necessary. This amendment also 
requires modification of those areas of the wings, which terminates the 
repetitive inspection requirements. This amendment is prompted by 
reports indicating that, during fatigue testing of the wing structure, 
cracks developed in the aft spar lower cap, in certain stringer 
butterfly clips, and in certain fastener holes due to fatigue-related 
stress. The actions specified by this AD are intended to prevent such 
fatigue-related cracking, which could lead to the failure of the aft 
spar cap and consequently could reduce the structural integrity of the 
wing.

DATES: Effective December 27, 1995.
    The incorporation by reference of certain publications listed in 
the regulations is approved by the Director of the Federal Register as 
of December 27, 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, Department 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: John Cecil, Aerospace Engineer, 
Airframe Branch, ANM-120L, FAA, Transport Airplane Directorate, Los 
Angeles Aircraft Certification Office, 3960 Paramount Boulevard, 
Lakewood, California 90712-4137; telephone (310) 627-5322; 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-10-10 
series airplanes was published in the Federal Register on June 16, 1995 
(60 FR 31649). That action proposed to require repetitive eddy current 
inspections of the wings to detect cracks in the aft spar lower cap; in 
the stringer butterfly clips on the bulkheads at stations 
Xors=372.000 and Xors=402.000; and in the fastener holes of 
the access doors of the inboard upper surface. That action also 
proposed to require modification of those areas of the wings, which 
would constitute terminating action for the required repetitive 
inspections.
    Interested persons have been afforded an opportunity to participate 
in the making of this amendment. Due consideration has been given to 
the single comment received.
    The commenter supports the proposed rule.
    After careful review of the available data, including the comment 
noted above, the FAA has determined that air safety and the public 
interest require the adoption of the rule as proposed.
    There are approximately 53 Model DC-10-10 series airplanes of the 
affected design in the worldwide fleet. The FAA estimates that 53 
airplanes of U.S. registry will be affected by this AD, that it will 
take approximately 262 work hours per airplane to accomplish the 
required actions, and that the average labor rate is $60 per work hour. 
Required parts will cost approximately $125,609 per airplane. Based on 
these figures, the cost impact of the AD on U.S. operators is estimated 
to be $7,490,437, or $141,329 per airplane.
    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.
    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 

[[Page 58213]]
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 USC 106(g), 40101, 40113, 44701.


Sec. 39.13  [Amended]

    2. Section 39.13 is amended by adding the following new 
airworthiness directive:

95-24-01 McDonnell Douglas: Amendment 39-9433. Docket 95-NM-50-AD.

    Applicability: Model DC-10-10 series airplanes, as listed in 
McDonnell Douglas DC-10 Service Bulletin 57-36, Revision 7, dated 
December 11, 1992, certificated in any category.

    -Note 1: This AD applies to each airplane identified in the 
preceding applicability provision, regardless of whether it has been 
otherwise 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 (c) of this AD 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.

    Note -2: Inspections and modifications required by paragraphs 
(g) and (h) of AD 94-23-01, amendment 39-9063, accomplished prior to 
the effective date of this amendment in accordance with McDonnell 
Douglas DC-10 Service Bulletin 57-123, dated June 8, 1993, or 
McDonnell Douglas DC-10 Service Bulletin 57-36, Revision 6, dated 
February 25, 1991, are considered acceptable for compliance with the 
applicable inspections and modifications required by this amendment 
for the affected structure.

    -To prevent fatigue-related cracking, which could lead to the 
failure of the aft spar cap and subsequent reduced structural 
integrity of the wing, accomplish the following: -
    (a) Prior to the accumulation of 15,000 total landings or within 
2,000 landings after the effective date of this AD, whichever occurs 
later, perform an eddy current inspection of the wings to detect 
cracks in the aft spar lower cap, in the stringer butterfly clips on 
the bulkheads at stations Xors=372.000 and Xors=402.000, 
and in the fastener holes of the access doors of the inboard upper 
surface, in accordance with McDonnell Douglas DC-10 Service Bulletin 
57-36, Revision 7, dated December 11, 1992. -
    (1) If no cracks are detected, repeat the inspection thereafter 
at intervals not to exceed 2,000 landings until the modification 
required by paragraph (b) of this AD is accomplished. -
    (2) If any crack is detected, prior to further flight, repair in 
accordance with a method approved by the Manager, Los Angeles 
Aircraft Certification Office (ACO), FAA, Transport Airplane 
Directorate. -
    (b) Prior to the accumulation of 42,000 total landings or within 
5 years after the effective date of this AD, whichever occurs later, 
modify the aft spar lower cap, the stringer butterfly clips on the 
bulkheads at stations Xors=372.000 and Xors=402.000, and 
the fastener holes of the access doors of the inboard upper surface 
of the wings, in accordance with McDonnell Douglas DC-10 Service 
Bulletin 57-36, Revision 7, dated December 11, 1992. Accomplishment 
of this modification constitutes terminating action for the 
repetitive inspection requirement 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 ACO. 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 3: 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 inspections, repair, and modification shall be done in 
accordance with McDonnell Douglas DC-10 Service Bulletin 57-36, 
Revision 7, dated December 11, 1992. 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, Department 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. 
-
    (f) This amendment becomes effective on December 27, 1995.

    Issued in Renton, Washington, on November 9, 1995.
S.R. Miller,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 95-28797 Filed 11-24-95; 8:45 am]
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