[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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