[Federal Register Volume 59, Number 219 (Tuesday, November 15, 1994)]
[Unknown Section]
[Page 0]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 94-27473]
[[Page Unknown]]
[Federal Register: November 15, 1994]
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DEPARTMENT OF TRANSPORTATION
14 CFR Part 39
[Docket No. 94-NM-51-AD; Amendment 39-9063; AD 94-23-01]
Airworthiness Directives; McDonnell Douglas Model DC-10 Series
Airplanes
AGENCY: Federal Aviation Administration, DOT.
ACTION: Final rule.
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SUMMARY: This amendment supersedes an existing airworthiness directive
(AD), applicable to certain McDonnell Douglas Model DC-10 series
airplanes, that currently requires inspection of the wing rear spar
lower cap aft tang fastener and the wing trailing edge access door sill
to detect fatigue cracking, and repair, if necessary. This amendment
requires installation of a crack preventative modification of the wing
rear spar lower cap, and follow-on inspections. This amendment is
prompted by reports of additional cracking found in the current
inspection area. The actions specified by this AD are intended to
prevent propagation of cracks in the subject area, which could
compromise the structural integrity of the airplane.
DATES: Effective December 15, 1994.
The incorporation by reference of certain publications, as listed
in the regulations, is approved by the Director of the Federal Register
as of December 15, 1994.
The incorporation by reference of McDonnell Douglas Alert Service
Bulletin A57-123, dated July 25, 1991, listed in the regulations was
approved previously by the Director of the Federal Register as of
October 23, 1991 (56 FR 50650, October 8, 1991).
ADDRESSES: The service information referenced in this AD may be
obtained from McDonnell Douglas Corporation, P.O. Box 1771, Long Beach,
California 90801-1771, Attention: Business Unit Manager, Technical
Administrative support, Dept. L51, M.C. 2-98. 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, 3229 East Spring Street, Long Beach,
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, 3229 East Spring Street, Long
Beach, California 90806-2425; telephone (310) 988-5238; fax (310) 988-
5210.
SUPPLEMENTARY INFORMATION: A proposal to amend part 39 of the Federal
Aviation Regulations (14 CFR part 39) by superseding AD 91-21-05,
amendment 39-8052 (56 FR 50650, October 8, 1991), which is applicable
to certain McDonnell Douglas Model DC-10 series airplanes was published
in the Federal Register on July 22, 1994 (59 FR 37443). That action
proposed to require installation of a crack preventative modification
of the wing rear spar lower cap, and follow-on inspections.
Interested persons have been afforded an opportunity to participate
in the making of this amendment. Due consideration has been given to
the two comments received.
Both commenters support the proposed rule.
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 282 Model DC-10 series airplanes of the
affected design in the worldwide fleet. The FAA estimates that 175
airplanes of U.S. registry will be affected by this AD.
The currently required inspections take approximately 8 work hours
per airplane to accomplish, at an average labor rate of $60 per work
hour. Based on these figures, the total cost impact of the current
inspection requirements of this AD on U.S. operators is estimated to be
$84,000, or $480 per airplane, per inspection.
The modification will take approximately 12 work hours to
accomplish, at an average labor rate of $60 per work hour. Required
parts will cost between $3,730 and $6,730 per airplane, depending upon
the airplane model. Based on these figures, the total cost impact of
the modification requirement of this AD on U.S. operators is estimated
to be between $4,450 and $7,450 per airplane.
The post-modification inspections will take approximately 12 work
hours per airplane to accomplish, at an average labor rate of $60 per
work hour. Based on these figures, the total cost impact of the post-
modification inspection requirements of this AD on U.S. operators is
estimated to be $126,000, or $720 per airplane, per inspection.
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) 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:
94-23-01 McDonnell Douglas: Amendment 39-9063. Docket 94-NM-51-AD.
Supersedes AD 91-21-05, Amendment 39-8052.
Applicability: Model DC-10-10, -10F, and -15 series airplanes,
fuselage numbers through 379 inclusive; and Model DC-10-30, -30F,
and -40 series airplanes, fuselage numbers through 275 inclusive,
certificated in any category.
Compliance: Required as indicated, unless accomplished
previously.
To ensure the structural integrity of these airplanes,
accomplish the following:
(a) Except as provided in paragraphs (b) through (e) of this AD,
prior to the accumulation of 7,000 total landings or within 30 days
after October 23, 1991 (the effective date of AD 91-21-05, amendment
39-8051), whichever occurs later, conduct the initial inspections
specified in either paragraph (a)(1), (a)(2), or (a)(3) of this AD.
(1) Conduct an eddy current inspection of the wing rear spar
lower cap aft tang, and a dye penetrant inspection of the wing
trailing edge access door sill located between Xors=417.000 and
Xors=424.000, in accordance with Option III of McDonnell
Douglas Alert Service Bulletin A57-123, dated July 25, 1991, or
Revision 1, dated June 8, 1993. In addition, within 1,500 landings
after performing the eddy current and dye penetrant inspections,
conduct the inspections specified in either paragraph (a)(2) or
(a)(3) of this AD, and repeat them thereafter as indicated. Or
(2) Conduct an ultrasonic inspection of the area around the six
wing rear spar lower cap aft tang fastener holes, and a dye
penetrant inspection of the wing trailing edge access door sill
located between stations Xors=417.000 and Xors=424.000, in
accordance with Option II of McDonnell Douglas Alert Service
Bulletin A57-123, dated July 25, 1991, or Revision 1, dated June 8,
1993. Repeat these inspections thereafter at intervals not to exceed
1,900 landings until the modification required by paragraph (g) of
this AD is accomplished. Or
(3) Conduct an eddy current inspection of the six wing rear spar
lower cap aft tang fastener holes, and a dye penetrant inspection of
the wing trailing edge access door sill located between stations
Xors=417.000 and Xors=424.000, in accordance with Option I
of McDonnell Douglas Alert Service Bulletin A57-123, dated July 25,
1991, or Revision 1, dated June 8, 1993. Repeat these inspections
thereafter at intervals not to exceed 3,300 landings until the
modification required by paragraph (g) of this AD is accomplished.
(b) The requirements of paragraph (c) of this AD apply to
airplanes on which both of the following actions have been
accomplished:
(1) A dye penetrant inspection of the wing trailing edge access
door sill located between stations Xors=417.000 and
Xors=422.000 has been accomplished prior to October 23, 1991,
in accordance with McDonnell Douglas Service Bulletin 57-61,
Revision 2, dated August 15, 1990; and
(2) An eddy current inspection of the wing rear spar lower cap
aft tang has been accomplished prior to October 23, 1991, per DC-10
Supplemental Inspection Document, Principal Structural Element (PSE)
57.10.007 and 57.10.008, in accordance with McDonnell Douglas
Service Bulletin 57-61, Revision 2, dated August 15, 1990.
(c) For airplanes specified in paragraph (b) of this AD: Conduct
the initial inspections specified in either paragraph (c)(1) or
(c)(2) of this AD within 1,500 landings after accomplishing the
inspections (dye penetrant and eddy current) specified in paragraph
(b) of this AD, or within 30 days after October 23, 1991, whichever
occurs later.
(1) Conduct an ultrasonic inspection of the area around the six
wing rear spar lower cap aft tang fastener holes, and a dye
penetrant inspection of the wing trailing edge access door sill
located between stations Xors=417.000 and Xors=424.000, in
accordance with Option II of McDonnell Douglas Alert Service
Bulletin A57-123, dated July 25, 1991, or Revision 1, dated June 8,
1993. Repeat these inspections thereafter at intervals not to exceed
1,900 landings until the modification required by paragraph (g) of
this AD is accomplished. Or
(2) Conduct an eddy current inspection of the six wing rear spar
lower cap aft tang fastener holes, and a dye penetrant inspection of
the wing trailing edge access door sill located between stations
Xors=417.000 and Xors=424.000, in accordance with Option I
of McDonnell Douglas Alert Service Bulletin A57-123, dated July 25,
1991, or Revision 1, dated June 8, 1993. Repeat these inspections
thereafter at intervals not to exceed 3,300 landings until the
modification required by paragraph (g) of this AD is accomplished.
(d) The requirements of paragraph (e) of this AD apply to
airplanes on which both of the following actions have been
accomplished:
(1) A dye penetrant inspection of the wing trailing edge access
door sill located between stations Xors=417.000 and
Xors=422.000 has been accomplished prior to October 23, 1991,
in accordance with McDonnell Douglas Service Bulletin 57-61,
Revision 2, dated August 15, 1990; and
(2) An eddy current inspection of the wing rear spar lower cap
aft tang fastener holes located between stations Xors=417.000
and Xors=422.000 has been accomplished prior to October 23,
1991, per DPS 4.735-9, in accordance with McDonnell Douglas Service
Bulletin 57-61, Revision 2, dated August 15, 1990.
(e) For airplanes specified in paragraph (d) of this AD: Conduct
the initial inspections specified in either paragraph (e)(1) or
(e)(2) of this AD within 3,300 landings after the accomplishment of
the inspection specified in paragraph (d)(1) of this AD, or within
30 days after October 23, 1991, whichever occurs later.
(1) Conduct an ultrasonic inspection of the area around the six
wing rear spar lower cap aft tang fastener holes, and a dye
penetrant inspection of the wing trailing edge access door sill
located between stations Xors=417.000 and Xors=424.000, in
accordance with Option II of McDonnell Douglas Alert Service
Bulletin A57-123, dated July 25, 1991, or Revision 1, dated June 8,
1993. Repeat these inspections thereafter at intervals not to exceed
1,900 landings until the modification required by paragraph (g) of
this AD is accomplished. Or
(2) Conduct an eddy current inspection of the six wing rear spar
lower cap aft tang fastener holes, and a dye penetrant inspection of
the wing trailing edge access door sill located between stations
Xors=417.000 and Xors=424.000, in accordance with Option I
of McDonnell Douglas Alert Service Bulletin A57-123, dated July 25,
1991, or Revision 1, dated June 8, 1993. Repeat these inspections
thereafter at intervals not to exceed 3,300 landings until the
modification required by paragraph (g) of this AD is accomplished.
(f) If any crack(s) is found during any inspection conducted in
accordance with paragraphs (a) through (e) of this AD, prior to
further flight, repair in a manner approved by the Manager, Los
Angeles Aircraft Certification Office (ACO), FAA, Transport Airplane
Directorate.
(g) Prior to the accumulation of 10,000 total landings, or
within 5 years after the effective date of this AD, whichever occurs
later, accomplish the crack preventative modification in accordance
with McDonnell Douglas Service Bulletin 57-123, dated June 8, 1993.
Accomplishment of this modification constitutes terminating action
for the inspection requirements of paragraphs (a) through (e) of
this AD.
(h) Prior to the accumulation of 10,000 total landings after the
accomplishment of the crack preventative modification required by
paragraph (g) of this AD, conduct an inspection of the wing rear
spar lower cap in accordance with McDonnell Douglas Service Bulletin
57-123, dated June 8, 1993. Repeat this inspection thereafter in
accordance with the following schedule. Any crack(s) found during
any inspection required by this paragraph must be repaired, prior to
further flight, in accordance with a method approved by the Manager,
Los Angeles ACO, FAA, Transport Airplane Directorate.
(1) For Model DC-10-10, -10F, and -15 series airplanes: Repeat
the inspection at intervals not to exceed 4,550 landings.
(2) For Model DC-10-30 and -30F series airplanes: Repeat the
inspection at intervals not to exceed 2,810 landings.
(3) For Model DC-10-40 series airplanes: Repeat the inspection
at intervals not to exceed 3,400 landings.
(i) 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: Information concerning the existence of approved
alternative methods of compliance with this AD, if any, may be
obtained from the Los Angeles ACO.
(j) 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.
(k) The actions shall be done in accordance with McDonnell
Douglas Alert Service Bulletin A57-123, Revision 1, dated June 8,
1993; McDonnell Douglas Service Bulletin 57-123, dated June 8, 1993;
and McDonnell Douglas Service Bulletin 57-61, Revision 2, dated
August 15, 1990. The incorporation by reference of McDonnell Douglas
Alert Service Bulletin 57-61, dated July 25, 1991, was approved
previously by the Director of the Federal Register in accordance
with 5 U.S.C. 552(a) and 1 CFR Part 51 as of October 23, 1991 (56 FR
50650, October 8, 1991). The incorporation by reference of the
remainder of the service documents listed above is 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, P.O. Box 1771, Long Beach, California 90801-1771,
Attention: Business Unit Manager, Technical Administrative support,
Dept. L51, M.C. 2-98. Copies may be inspected at the FAA, Transport
Airplane Directorate, 1601 Lind Avenue, SW., Renton, Washington; or
at the FAA, Los Angeles ACO, Transport Airplane Directorate, 3229
East Spring Street, Long Beach, California; or at the Office of the
Federal Register, 800 North Capitol Street, NW., suite 700,
Washington, DC.
(l) This amendment becomes effective on December 15, 1994.
Issued in Renton, Washington, on November 1, 1994.
S. R. Miller,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 94-27473 Filed 11-14-94; 8:45 am]
BILLING CODE 4910-13-U
