[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