[Federal Register Volume 63, Number 226 (Tuesday, November 24, 1998)]
[Rules and Regulations]
[Pages 64846-64848]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 98-31171]



[[Page 64846]]

-----------------------------------------------------------------------

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 97-NM-14-AD; Amendment 39-10902; AD 98-24-17]
RIN 2120-AA64


Airworthiness Directives; McDonnell Douglas Model DC-10-10, -30, 
and -40 Series Airplanes

AGENCY: Federal Aviation Administration, DOT.

ACTION: Final rule.

-----------------------------------------------------------------------

SUMMARY: This amendment adopts a new airworthiness directive (AD), 
applicable to certain McDonnell Douglas Model DC-10-10, -30, and -40 
series airplanes, that requires replacement of certain taper-lok 
attachments and forward trunnion bolts with new components that attach 
the left and right main landing gear (MLG) to each wing. This amendment 
is prompted by a report indicating that, due to overstrength of the 
forward trunnion bolt, an MLG broke away and ruptured a wing fuel tank 
while an airplane was being operated off the runway. The actions 
specified by this AD are intended to ensure that the MLG separates from 
the wing when it is subjected to unpredictable overloads during 
abnormal operations, and to prevent consequent primary structural 
damage to the airplane.

DATES: Effective December 29, 1998.
    The incorporation by reference of certain publications listed in 
the regulations is approved by the Director of the Federal Register as 
of December 29, 1998.

ADDRESSES: The service information referenced in this AD may be 
obtained from the Boeing Company, Douglas Products Division, 3855 
Lakewood Boulevard, Long Beach, California 90846, Attention: Technical 
Publications Business Administration, Dept. 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, Transport Airplane Directorate, 
Los Angeles Aircraft Certification Office, 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: Ronald Atmur, Aerospace Engineer, 
Airframe Branch, ANM-120L, FAA, Los Angeles Aircraft Certification 
Office, 3960 Paramount Boulevard, Lakewood, California 90712; telephone 
(562) 627-5224; fax (562) 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-10-10, -30, and -40 series airplanes was published in the Federal 
Register on January 22, 1998 (63 FR 3267). That action proposed to 
require replacement of certain taper-lok attachments and forward 
trunnion bolts with new components that attach the left and right main 
landing gear (MLG) to each wing.

Comments Received

    Interested persons have been afforded an opportunity to participate 
in the making of this amendment. Due consideration has been given to 
the comments received.

Support for the Proposal

    Several commenters support the proposed rule.

Request to Extend Compliance Time

    One commenter requests that the compliance time for accomplishing 
the proposed replacement of certain taper-lok attachments and forward 
trunnion bolts be extended from the proposed 5 years to 6 years. The 
commenter states that such an extension will allow the replacement to 
be accomplished during a regularly scheduled heavy maintenance visit, 
and thereby eliminate any additional expenses that would be associated 
with special scheduling. The FAA does not concur. In developing an 
appropriate compliance time for this action, the FAA considered not 
only the degree of urgency associated with addressing the unsafe 
condition, the availability of required parts, normal maintenance 
schedules, and the significant amount of time that is necessary to 
perform the replacement. In consideration of all of these factors, the 
FAA has determined that further delay of this replacement is not 
appropriate. However, under the provision of paragraph (g) of the final 
rule, the FAA may approve requests for adjustments to the compliance 
time if sufficient data are submitted to substantiate that such an 
adjustment would provide an acceptable level of safety.

Request That Credit Be Given for Previous Replacements

    One commenter recommends that the FAA revise the proposed rule to 
specify that operators will be given ``credit'' for having previously 
accomplished the actions specified in the proposed rule. The FAA does 
not consider that a change to the final rule is necessary. Operators 
are given credit for work previously performed by means of the phrase 
in the ``Compliance'' section of the AD that states, ``Required as 
indicated, unless accomplished previously.'' Therefore, in the case of 
this AD, if the required replacement has been accomplished prior to the 
effective date of this AD, this AD does not require that it be 
repeated.

Request That the Forward Trunnion Bolt Be Inspected

    One commenter requests that the FAA ensure that the ``forward'' 
trunnion bolt is replaced, not the ``aft'' trunnion bolt. The FAA finds 
that the forward trunnion bolt was addressed correctly in the proposed 
rule. No change to the final rule is necessary.

Request To Ensure That Other AD's Do Not Conflict With This AD

    One commenter requests that the FAA ensure that requirements of AD 
96-16-01, amendment 39-9701 (61 FR 39312, July 29, 1996), and AD 96-03-
05, amendment 39-9502 (61 FR 5281, February 12, 1996), do not conflict 
with the requirements of the proposed AD. The commenter states that 
these two AD's already require installation and modification of the 
trunnion bolts in accordance with McDonnell Douglas Service Bulletins 
DC10-57-78 and DC10-57-82. The commenter also states that these AD's 
have introduced a new trunnion bolt part number for Model DC-10-30 
series airplanes (reference McDonnell Douglas Service Bulletin DC10-32-
239, Revision 1) that is not included in Service Bulletin DC10-57-82.
    The FAA finds that clarification is necessary. Both AD 96-16-01 and 
AD 96-03-05 require either removing the chrome plating on the trunnion 
bolt, replacing the plating, and reinstalling the reworked bolt; or 
replacing the trunnion bolt with a serviceable bolt. Replacement of the 
subject trunnion bolts in accordance with either of these AD's 
constitutes terminating action for the requirement to replace the 
trunnion bolts, as required by paragraphs (a)(2), (c)(1), and (c)(2) of 
this AD. The FAA has revised the final rule by including new paragraphs 
(e) and (f) to clarify this point. Paragraph (d) of this AD also 
addresses a similar point for Model DC-10-30 and DC-10-40 series 
airplanes.

Conclusion

    After careful review of the available data, including the comments 
noted above, the FAA has determined that air

[[Page 64847]]

safety and the public interest require the adoption of the rule with 
the changes previously described. The FAA has determined that these 
changes will neither increase the economic burden on any operator nor 
increase the scope of the AD.

Cost Impact

     For McDonnell Douglas Model DC-10-10 Series Airplanes
    There are approximately 119 Model DC-10-10 series airplanes of the 
affected design in the worldwide fleet, and 108 airplanes of U.S. 
registry that will be affected by the requirements for replacement of 
taper-lok attachments and forward trunnion bolts. The FAA estimates 
that it will take approximately 462 work hours per airplane to 
accomplish these required actions, and that the average labor rate is 
$60 per work hour. Required parts will cost approximately $47,000 per 
airplane. Based on these figures, the cost impact of these required 
actions on U.S. operators is estimated to be $8,069,760, or $74,720 per 
airplane.
    There are approximately 111 Model DC-10-10 series airplanes of the 
affected design in the worldwide fleet, and 82 airplanes of U.S. 
registry that will be affected by the requirements for replacement of 
larger attach bolts and installation of bolt retainers. The FAA 
estimates that it will take approximately 500 work hours per airplane 
to accomplish these required actions, and that the average labor rate 
is $60 per work hour. Required parts will cost approximately $11,734 
per airplane. Based on these figures, the cost impact of these required 
actions on U.S. operators is estimated to be $3,422,188, or $41,734 per 
airplane.
     For McDonnell Douglas Model DC-10-30 and DC-10-40 Series 
Airplanes
    There are approximately 168 Model DC-10-30 and DC-10-40 series 
airplanes of the affected design in the worldwide fleet, and 82 
airplanes of U.S. registry that are identified as Groups I and II 
airplanes in the relevant service bulletins and that will be affected 
by the requirements for replacement of larger attach bolts, 
installation of bolt retainers, and replacement of forward trunnion 
bolts. The FAA estimates that it will take approximately 576 work hours 
per airplane to accomplish these required actions, and that the average 
labor rate is $60 per work hour. Required parts will cost approximately 
$20,000 per airplane. Based on these figures, the cost impact of these 
required actions on U.S. operators is estimated to be $4,473,920, or 
$54,560 per airplane.
    There are approximately 20 Model DC-10-30 and DC-10-40 series 
airplanes of the affected design in the worldwide fleet, and 6 
airplanes of U.S. registry that are identified as Group III airplanes 
in the relevant service bulletins and that will be affected by the 
requirements for replacement of forward trunnion bolts. The FAA 
estimates that it will take approximately 76 work hours per airplane to 
accomplish this required action, and that the average labor rate is $60 
per work hour. Required parts will cost approximately $15,800 per 
airplane. Based on these figures, the cost impact of this required 
action on U.S. operators is estimated to be $122,160, or $20,360 per 
airplane.
    The cost impact figures discussed above are 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.
    However, the FAA has been advised that the following actions have 
been accomplished on Model DC-10-10 series airplanes in accordance with 
the requirements of this AD:
     Taper-lok attachments and forward trunnion bolts have been 
replaced on 77 U.S.-registered airplanes. Therefore, the future 
economic cost impact of those actions on U.S. operators is now only 
$2,316,320.
     Larger attach bolts have been replaced and bolt retainers 
have been installed on 77 U.S.-registered airplanes. Therefore, the 
future economic cost impact of those actions on U.S. operators is now 
only $208,670.
    The FAA also has been advised that the following actions have been 
accomplished on Model DC-10-30 and DC-10-40 series airplanes in 
accordance with the requirements of this AD:
     Forward trunnion bolts and larger attach bolts have been 
replaced and bolt retainers have been installed on 40 U.S.-registered 
airplanes identified as Groups I and II airplanes in the relevant 
service bulletins. Therefore, the future economic cost impact of those 
actions on U.S. operators is now only $2,291,520.
     Forward trunnion bolts have been replaced on 3 U.S.-
registered airplanes identified as Group III airplanes in the relevant 
service bulletins. Therefore, the future economic cost impact of this 
action on U.S. operators is now only $61,080.

Regulatory Impact

    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. 106(g), 40113, 44701.


Sec. 39.13  [Amended]

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

98-24-17  McDonnell Douglas: Amendment 39-10902. Docket 97-NM-14-AD.

    Applicability: Model DC-10-10, DC-10-30, and DC-10-40 series 
airplanes, certificated in any category; as listed in the following 
McDonnell Douglas service bulletins:
     McDonnell Douglas DC-10 Service Bulletin 57-78, 
Revision 1, dated August 26, 1986;
     McDonnell Douglas DC-10 Service Bulletin 57-79, 
Revision 1, dated September 21, 1979, as revised by McDonnell 
Douglas DC-10 Service Bulletin Change Notification 57-79, dated 
January 23, 1980; and
     McDonnell Douglas DC-10 Service Bulletin 57-82, dated 
February 19, 1980.

    Note 1: This AD applies to each airplane identified in the 
preceding applicability

[[Page 64848]]

provision, regardless of whether it has been 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 request approval for an alternative method of 
compliance in accordance with paragraph (g) of this AD. The request 
should include an assessment of the effect of the modification, 
alteration, or repair on the unsafe condition addressed by this AD; 
and, if the unsafe condition has not been eliminated, the request 
should include specific proposed actions to address it.

    Compliance: Required as indicated, unless accomplished 
previously.
    To ensure that the main landing gear (MLG) separates from the 
wing when it is subjected to unpredictable overloads during abnormal 
operations, and to prevent consequent primary structural damage to 
the airplane, accomplish the following:
    (a) For Model DC-10-10 series airplanes, as listed in McDonnell 
Douglas DC-10 Service Bulletin 57-78, Revision 1, dated August 26, 
1986: Within 5 years after the effective date of this AD, accomplish 
the requirements of paragraphs (a)(1) and (a)(2) of this AD, in 
accordance with the service bulletin.
    (1) Replace 24 TL taper-lok attachments that attach the left and 
right MLG attach fitting assemblies on each wing with heat-treat TLH 
taper-lok attachments in accordance with the service bulletin. And
    (2) Replace each forward trunnion bolt on the left and right MLG 
of each wing with a ``zero margin'' trunnion bolt in accordance with 
the service bulletin.

    Note 2: Replacement of taper-lok attachments and forward 
trunnion bolts accomplished prior to the effective date of this AD 
in accordance with McDonnell Douglas DC-10 Service Bulletin 57-78, 
dated February 19, 1980, is considered acceptable for compliance 
with the requirements of paragraphs (a)(1) and (a)(2) of this AD.

    (b) For Model DC-10-10 series airplanes, as listed in McDonnell 
Douglas DC-10 Service Bulletin 57-79, Revision 1, dated September 
21, 1979, as revised by McDonnell Douglas DC-10 Service Bulletin 
Change Notification 57-79, dated January 23, 1980: Within 5 years 
after the effective date of this AD, replace each 1\1/2\-inch-
diameter bolt and bushing that attach the left and right MLG attach 
fitting and rear spar of each wing with a 1\1/4\-inch-diameter bolt, 
and install bolt retainers, in accordance with the service bulletin 
and service bulletin change notification.

    Note 3: Replacement of 1\1/2\-inch-diameter bolts and 
installation of bolt retainers prior to the effective date of this 
AD in accordance with McDonnell Douglas DC-10 Service Bulletin 57-
79, dated June 5, 1979, are considered acceptable for compliance 
with the requirements of paragraph (b) of this AD.

    (c) For Model DC-10-30 and DC-10-40 series airplanes: Except as 
provided by paragraph (d) of this AD, within 5 years after the 
effective date of this AD, accomplish the requirements of paragraph 
(c)(1) or (c)(2) of this AD, as applicable, in accordance with 
McDonnell Douglas DC-10 Service Bulletin 57-82, dated February 19, 
1980.
    (1) For airplanes identified as Groups I and II in the service 
bulletin: Replace each forward trunnion bolt on the left and right 
MLG of each wing with a ``zero margin'' forward trunnion bolt; 
replace each 1\1/2\-inch-diameter bolt and bushing that attach the 
left and right MLG attach fitting and rear spar of each wing with a 
1\1/4\-inch-diameter bolt, and install bolt retainers, in accordance 
with the service bulletin.
    (2) For airplanes identified as Group III in the service 
bulletin: Replace each forward trunnion bolt on the left and right 
MLG of each wing with a ``zero margin'' trunnion bolt in accordance 
with the service bulletin.
    (d) For Model DC-10-30 and DC-10-40 series airplanes: 
Installation of a trunnion bolt having part number (P/N) ARG7558-501 
or P/N ARG7558-507 on the MLG, in accordance with AD 96-03-05, 
amendment 39-9502, constitutes terminating action for the 
requirement to replace the trunnion bolts for that landing gear, as 
required in paragraphs (c)(1) and (c)(2) of this AD.
    (e) For Model DC-10-30 and DC-10-40 series airplanes: 
Replacement of the trunnion bolts with a serviceable part in 
accordance with paragraph (c)(1)(ii)(B) of AD 96-03-05, amendment 
39-9502, constitutes terminating action for the requirement to 
replace the trunnion bolts, as required in paragraphs (c)(1) and 
(c)(2) of this AD.
    (f) For Model DC-10-10 series airplanes: Replacement of the 
trunnion bolts with a serviceable part in accordance with paragraph 
(a)(1)(ii)(B) of AD 96-16-01, amendment 39-9701, constitutes 
terminating action for the requirement to replace the trunnion 
bolts, as required in paragraph (a)(2) of this AD.
    (g) 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 4: Information concerning the existence of approved 
alternative methods of compliance with this AD, if any, may be 
obtained from the Los Angeles ACO.

    (h) 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.
    (i) The actions shall be done in accordance with McDonnell 
Douglas DC-10 Service Bulletin 57-78, Revision 1, dated August 26, 
1986; McDonnell Douglas DC-10 Service Bulletin 57-79, Revision 1, 
dated September 21, 1979, as revised by McDonnell Douglas DC-10 
Service Bulletin Change Notification 57-79, dated January 23, 1980; 
and McDonnell Douglas DC-10 Service Bulletin 57-82, dated February 
19, 1980. 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 the Boeing Company, 
Douglas Products Division, 3855 Lakewood Boulevard, Long Beach, 
California 90846, Attention: Technical Publications Business 
Administration, Dept. C1-L51 (2-60). Copies may be inspected at the 
FAA, Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton, 
Washington; or at the FAA, Transport Airplane Directorate, Los 
Angeles Aircraft Certification Office, 3960 Paramount Boulevard, 
Lakewood, California; or at the Office of the Federal Register, 800 
North Capitol Street, NW., suite 700, Washington, DC.
    (j) This amendment becomes effective on December 29, 1998.

    Issued in Renton, Washington, on November 16, 1998.
Darrell M. Pederson,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 98-31171 Filed 11-23-98; 8:45 am]
BILLING CODE 4910-13-U