[Federal Register Volume 60, Number 227 (Monday, November 27, 1995)]
[Rules and Regulations]
[Pages 58210-58212]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 95-28796]



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DEPARTMENT OF TRANSPORTATION
14 CFR Part 39

[Docket No. 95-NM-49-AD; Amendment 39-9435; AD 95-24-03]


Airworthiness Directives; McDonnell Douglas Model DC-10-10, -30, 
and -40 Series Airplanes, and KC-10 (Military) 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 Model DC-10, -30, and -40 
series airplanes, and KC-10 (military) airplanes, that requires 
inspections to detect corrosion or cracking of the lower front spar cap 
and the skin panel of the horizontal stabilizer, and repair of corroded 
or cracked parts. This amendment also requires eventual modification of 
the horizontal stabilizer, which terminates the inspection 
requirements. This action is prompted by reports indicating that 
corrosion, 

[[Page 58211]]
caused by water entrapment, was found on the horizontal stabilizer. The 
actions specified by this AD are intended to prevent water entrapment 
and subsequent damage to the horizontal stabilizer, which could result 
in reduced controllability of the airplane.

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 Model 
DC-10, -30, and -40 series airplanes, and KC-10 (military) airplanes 
was published in the Federal Register on June 13, 1995 (60 FR 31124). 
That action proposed to require repetitive visual inspections to detect 
corrosion or cracking of the lower front spar cap and the skin panel of 
the horizontal stabilizer, and repair of corroded or cracked parts. 
That action also proposed to require the eventual modification of the 
lower front spar cap and the lower front skin panel of the horizontal 
stabilizer, which would constitute terminating action for the 
repetitive inspection requirements.
    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 286 Model DC-10-10, DC-10-30, and DC-10-40 
airplanes, and KC-10 (military) airplanes of the affected design in the 
worldwide fleet. The FAA estimates that 142 airplanes of U.S. registry 
will be affected by this AD, that it will take approximately 26 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 
cost impact of the AD on U.S. operators is estimated to be $221,520, or 
$1,560 per airplane.
    The FAA estimates that it will take approximately 241 work hours 
per airplane to accomplish the terminating modification, at an average 
labor rate of $60 per work hour. Required parts would cost 
approximately $124,906 per airplane. Based on these figures, the cost 
impact of the terminating modification is estimated to be $19,789,972, 
or $139,366 per airplane.
    Based on the figures discussed above, the estimated cost impact of 
the requirements of this AD is expected to total $20,011,492, or 
$140,926 per airplane. This estimated cost impact figure 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 USC 106(g), 40101, 40113, 44701.


Sec. 39.13  [Amended]

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

95-24-03 McDonnell Douglas: Amendment 39-9435. Docket 95-NM-49-AD.

    Applicability: Model DC-10-10, -30, and -40 airplanes, and KC-10 
(military) airplanes; as listed in McDonnell Douglas Service 
Bulletin 55-14, Revision 6, dated January 11, 1993, 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.
    To prevent reduced controllability of the airplane, due to a 
damaged horizontal stabilizer, accomplish the following: -
    (a) Within one year after the effective date of this AD, perform 
a visual inspection to detect corrosion or cracking of the lower 
front spar cap and skin panel of the horizontal stabilizer, in 
accordance with McDonnell Douglas DC-10 Service Bulletin 55-14, 
Revision 5, dated August 24, 1990, or Revision 6, dated January 11, 
1993.
    (1) If no corrosion or cracking is found during this inspection, 
repeat this inspection thereafter at intervals not to exceed one 
year, until the modification required by paragraph (b) of this AD is 
accomplished.
    (2) If any corrosion or cracking is found during this 
inspection, prior to further flight, 

[[Page 58212]]
repair the corrosion and/or cracking, and add drain holes, in 
accordance with Table 1 of the service bulletin. Accomplishment of 
these repairs and modification constitutes terminating action for 
the repetitive inspection requirements of this AD.
    (b) Perform the modification of the lower front spar cap and the 
skin panel of the horizontal stabilizer in accordance with McDonnell 
Douglas Service Bulletin 55-14, Revision 5, dated August 24, 1990, 
or Revision 6, dated January 11, 1993, at the applicable time 
specified in paragraph (b)(1) or (b)(2) of this AD. Accomplishment 
of this modification constitutes terminating action for the 
repetitive inspection requirements of this AD. -
    (1) For Model DC-10-10 airplanes: Accomplish the modification 
prior to the accumulation of 42,000 total landings, or within five 
years after the effective date of the AD, whichever occurs later. -
    (2) For Model DC-10-30 and DC-10-40 airplanes: Accomplish the 
modification prior to the accumulation of 30,000 total landings, or 
within five years after the effective date of this AD, whichever 
occurs later. -
    (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 2: 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 actions shall be done in accordance with McDonnell 
Douglas Service Bulletin 55-14, Revision 5, dated August 24, 1990, 
or Revision 6, dated January 11, 1993. 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. 95-28796 Filed 11-24-95; 8:45 am]
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