[Federal Register Volume 66, Number 162 (Tuesday, August 21, 2001)]
[Rules and Regulations]
[Pages 43770-43773]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 01-20804]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 2000-NM-410-AD; Amendment 39-12381; AD 2001-16-12]
RIN 2120-AA64


Airworthiness Directives; McDonnell Douglas Model DC-10-10, -15, 
-30, and -30F (KC-10A Military) Series Airplanes, and Model MD-10-10F 
and -30F 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-10-10, -15, -30, 
and -30F (KC-10A military) series airplanes, and Model MD-10-10F and -
30F series airplanes, that currently requires repetitive inspections to 
determine the condition of the lockwires on the forward engine mount 
bolts and correction of any discrepancies found. That AD also provides 
for optional terminating actions for the repetitive inspections. This 
amendment requires accomplishment of the previously optional 
terminating actions. This amendment is prompted by a report of 
discrepant forward engine mount bolts at the number 3 engine. The 
actions specified by this AD are intended to

[[Page 43771]]

prevent broken lockwires, which could result in loosening of the engine 
mount bolts, and consequent separation of the engine from the airplane.

DATES: Effective September 25, 2001.
    The incorporation by reference of McDonnell Douglas DC-10 Service 
Bulletin 71-133, Revision 6, dated June 30, 1992; McDonnell Douglas 
Service Bulletin DC10-71-159, dated September 6, 1995; and McDonnell 
Douglas Service Bulletin DC10-71-159, Revision 01, dated July 28, 1997; 
as listed in the regulations, is approved by the Director of the 
Federal Register as of September 25, 2001.
    The incorporation by reference of McDonnell Douglas Alert Service 
Bulletin DC10-71A159, Revision 1, dated January 31, 1995; as listed in 
the regulations, was approved previously by the Director of the Federal 
Register as of November 10, 1999 (64 FR 54202, October 6, 1999).

ADDRESSES: The service information referenced in this AD may be 
obtained from Boeing Commercial Aircraft Group, Long Beach Division, 
3855 Lakewood Boulevard, Long Beach, California 90846, Attention: Data 
and Service Management, Dept. C1-L5A (D800-0024). 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, 
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: Ron Atmur, Aerospace Engineer, 
Airframe Branch, ANM-120L, FAA, Los Angeles Aircraft Certification 
Office, 3960 Paramount Boulevard, Lakewood, California 90712-4137; 
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) by superseding AD 95-04-07 R2, 
amendment 39-11354 (64 FR 54202, October 6, 1999), which is applicable 
to certain McDonnell Douglas Model DC-10-10, -15, -30, and -30F (KC-10A 
military) series airplanes, and Model MD-10-10F and -30F series 
airplanes, was published in the Federal Register on March 21, 2001 (66 
FR 15817). The action proposed to continue to require repetitive 
inspections to determine the condition of the lockwires on the forward 
engine mount bolts and correction of any discrepancies found. The 
action also proposed to require accomplishment of the previously 
optional terminating actions.

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 Proposed Rule

    Two commenters express support for the proposed rule.

Request To Revise Applicability and Clarify Terminating Actions

    One commenter requests that the ``Applicability'' of the proposed 
rule be revised to specify that it would not apply to certain airplanes 
on which, not only McDonnell Douglas DC-10 Service Bulletin 71-133, 
Revision 6, dated June 30, 1992, has been accomplished (as specified in 
the applicability of the proposed rule); but also would not apply to 
certain airplanes on which McDonnell Douglas Service Bulletin DC10-71-
159, dated September 6, 1995, or Revision 01, dated July 28, 1997, has 
been accomplished. The commenter also requests that paragraph (b) of 
the proposed rule be clarified to specify that, for certain models, the 
terminating action may be accomplished in accordance with either 
McDonnell Douglas Service Bulletin 71-133, or McDonnell Douglas Service 
Bulletin DC10-71-159. The commenter states that the proposed rule, as 
written, implies that both service bulletins must be accomplished for 
the terminating action.
    The FAA agrees with the commenter, and has determined that 
clarification is needed. It is the intent of the FAA to permit 
terminating action to be completed in accordance with either of the 
referenced service bulletins. We have revised the ``Applicability'' and 
paragraph (b) of the final rule to specify that, for certain models, 
compliance with the terminating action may be accomplished by either of 
the service bulletins noted above. Since the terminating actions for 
Model DC-10-30 and -30F (KC-10A military) series airplanes are now 
completely addressed in paragraph (b) of the final rule, we have 
revised paragraph (c) of the final rule to remove reference to those 
models and specify that the applicability of paragraph (c) of the final 
rule applies only to McDonnell Douglas Model DC-10-10 and -15 series 
airplanes, and Model MD-10-10F series airplanes.

Conclusion

    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 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

    There are approximately 389 Model DC-10-10, -15, -30, and -30F (KC-
10A military) series airplanes, and Model MD-10-10F and -30F series 
airplanes, of the affected design in the worldwide fleet. The FAA 
estimates that 229 airplanes of U.S. registry will be affected by this 
AD.
    The actions that are currently required by AD 95-04-07 R2, and 
retained in this AD, take approximately 2 work hours per airplane to 
accomplish, at an average labor rate of $60 per work hour. Based on 
these figures, the cost impact of the currently required actions on 
U.S. operators is estimated to be $27,480, or $120 per airplane, per 
inspection cycle.
    Should an operator be required to accomplish the terminating 
installation specified in McDonnell Douglas DC-10 Service Bulletin 71-
133, it will take approximately 4 work hours per airplane to 
accomplish, at an average labor rate of $60 per hour. Required parts 
will cost between $2,744 and $2,822 per airplane. Based on these 
figures, the cost impact of the terminating installation required by 
this AD on U.S. operators is estimated to be between $2,984 and $3,062 
per airplane.
    Should an operator be required to accomplish the terminating 
modification specified in McDonnell Douglas Service Bulletin DC10-71-
159, it will take approximately 16 work hours per airplane to 
accomplish, at an average labor rate of $60 per work hour. Required 
parts will cost between $2,744 and $2,822 per airplane. Based on these 
figures, the cost impact of the terminating modification required by 
this AD on U.S. operators is estimated to be between $3,704 and $3,782 
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. The cost impact figures discussed 
in AD rulemaking actions represent only the time necessary to perform 
the specific actions actually required by the AD. These figures 
typically do not include incidental costs, such as the time required to 
gain access and close up,

[[Page 43772]]

planning time, or time necessitated by other administrative actions.

Regulatory Impact

    The regulations adopted herein will not have a substantial direct 
effect 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, it 
is determined that this final rule does not have federalism 
implications under Executive Order 13132.
    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 removing amendment 39-11354 (64 FR 
54202, October 6, 1999), and by adding a new airworthiness directive 
(AD), amendment 39-12381, to read as follows:

2001-16-12  McDonnell Douglas: Amendment 39-12381. Docket 2000-NM-
410-AD. Supersedes AD 95-04-07 R2, Amendment 39-11354.
    Applicability: The following airplanes, certificated in any 
category:

------------------------------------------------------------------------
                 Model                         Excluding airplanes
------------------------------------------------------------------------
1. DC-10-30 and -30F (KC-10A military)   On which bolt retainers have
 series airplanes, and MD-10-30F series   been installed on the engine
 airplanes.                               mount per McDonnell Douglas DC-
                                          10 Service Bulletin 71-133,
                                          Revision 6, dated June 30,
                                          1992, or on which the
                                          modification specified in
                                          McDonnell Douglas Service
                                          Bulletin DC10-71-159, dated
                                          September 6, 1995, or Revision
                                          01, dated July 28, 1997, has
                                          been performed.
2. DC-10-10 and -15 series airplanes,    On which the modification
 and Model MD-10-10F series airplanes.    specified in McDonnell Douglas
                                          Service Bulletin DC10-71-159,
                                          dated September 6, 1995, or
                                          Revision 01, dated July 28,
                                          1997, has been done.
------------------------------------------------------------------------


    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 request approval for an 
alternative method of compliance in accordance with paragraph (d)(1) 
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 prevent broken lockwires, which could result in loosening of 
the engine mount bolts, and consequent separation of the engine from 
the airplane, accomplish the following:

Restatement of Requirements of AD 95-04-07 R2, Amendment 39-11354

    (a) Within 120 days after March 17, 1995 (the effective date of 
AD 95-04-07 R1, amendment 39-9317), unless accomplished previously 
within the last 750 flight hours prior to March 17, 1995, perform a 
visual inspection to detect broken lockwires on the forward engine 
mount bolts on engines 1, 2, and 3, in accordance with McDonnell 
Douglas Alert Service Bulletin DC10-71A159, Revision 1, dated 
January 31, 1995.
    (1) If no lockwire is found broken, repeat the inspection 
thereafter at intervals not to exceed 750 flight hours.
    (2) If any lockwire is found broken, prior to further flight: 
Check the torque of the bolt, install a new lockwire, and install a 
torque stripe on the bolt, in accordance with the alert service 
bulletin. Thereafter at intervals not to exceed 750 flight hours, 
perform a visual inspection to detect misalignment of the torque 
stripes, and repeat the inspection to detect broken lockwires, in 
accordance with the alert service bulletin.

Terminating Actions

    (b) For Model DC-10-30 and -30F (KC-10A military) series 
airplanes, and Model MD-10-30F series airplanes: Within 18 months 
after the effective date of this AD, install retainers on the engine 
mount bolts of engine 1, 2, or 3 per the procedures depicted in 
Figure 6 of Revision 6 of McDonnell Douglas DC-10 Service Bulletin 
71-133, dated June 30, 1992; or modify the forward engine mount 
bolts for engine 1, 2, or 3, per McDonnell Douglas Service Bullletin 
DC10-71-159, dated September 6, 1995, or Revision 01, dated July 28, 
1997. Accomplishment of the installation constitutes terminating 
action for the requirements of this AD for that engine.
    (c) For Model DC-10-10 and -15 series airplanes, and Model MD-
10-10F series airplanes: Within 18 months after the effective date 
of this AD, modify the forward engine mount bolts for engine 1, 2, 
or 3, per McDonnell Douglas Service Bulletin DC10-71-159, dated 
September 6, 1995; or Revision 01, dated July 28, 1997. 
Accomplishment of the modification constitutes terminating action 
for the requirements of this AD for that engine.

Alternative Methods of Compliance

    (d)(1) 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. 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.

    (2) Alternative methods of compliance, approved previously in 
accordance with AD 95-04-07 R2, amendment 39-11354, are approved as 
alternative methods of compliance with this AD.

Special Flight Permits

    (e) 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.

Incorporation by Reference

    (f) The actions shall be done in accordance with McDonnell 
Douglas DC-10 Service Bulletin 71-133, Revision 6, dated June 30, 
1992; McDonnell Douglas Service Bulletin DC10-71-159, dated 
September 6, 1995, or McDonnell Douglas Service Bulletin DC10-71-159 
RO1, Revision 01, dated July 28, 1997; and McDonnell Douglas Alert 
Service Bulletin DC10-71A159, Revision 1, dated January 31, 1995; as 
applicable.
    (1) The incorporation by reference of McDonnell Douglas DC-10 
Service Bulletin 71-133, Revision 6, dated June 30, 1992; McDonnell 
Douglas Service Bulletin DC10-71-159, dated September 6, 1995; and 
McDonnell Douglas Service Bulletin DC10-71-159 R01, Revision 01, 
dated July 28, 1997;

[[Page 43773]]

is approved by the Director of the Federal Register in accordance 
with 5 U.S.C. 552(a) and 1 CFR part 51.
    (2) The incorporation by reference of McDonnell Douglas Alert 
Service Bulletin DC10-71A159, Revision 1, dated January 31, 1995, 
was approved previously by the Director of the Federal Register as 
of November 10, 1999 (64 FR 54202, October 6, 1999).
    (3) Copies may be obtained from Boeing Commercial Aircraft 
Group, Long Beach Division, 3855 Lakewood Boulevard, Long Beach, 
California 90846, Attention: Data and Service Management, Dept. C1-
L5A (D800-0024). 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, 3960 
Paramount Boulevard, Lakewood, California; or at the Office of the 
Federal Register, 800 North Capitol Street, NW., suite 700, 
Washington, DC.

Effective Date

    (g) This amendment becomes effective on September 25, 2001.

    Issued in Renton, Washington, on August 13, 2001.
Vi L. Lipski,
Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 01-20804 Filed 8-20-01; 8:45 am]
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