[Federal Register Volume 64, Number 193 (Wednesday, October 6, 1999)]
[Rules and Regulations]
[Pages 54202-54203]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 99-25932]



[[Page 54202]]

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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 99-NM-14-AD; Amendment 39-11354; AD 95-04-07 R2]
RIN 2120-AA64


Airworthiness Directives; McDonnell Douglas Model DC-10-10, -15, 
and -30 Airplanes, and KC-10A (Military) Airplanes

AGENCY: Federal Aviation Administration, DOT.

ACTION: Final rule.

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SUMMARY: This amendment revises an existing airworthiness directive 
(AD), applicable to certain McDonnell Douglas Model DC-10-10, -15, and 
-30 airplanes, and KC-10A (military) airplanes, that currently requires 
inspections to determine the condition of the lockwires on the forward 
engine mount bolts and correction of any discrepancies found. That 
amendment also provides for termination of the inspections for some 
airplanes by installing retainers on the bolts. That AD was prompted by 
reports of stretched or broken lockwires on the forward engine mount 
bolts. The actions specified by that AD are intended to prevent broken 
lockwires, which could result in loosening of the engine mount bolts, 
and subsequent separation of the engine from the airplane. This 
amendment provides an additional optional terminating modification and 
clarification of the requirements of the previous optional terminating 
modification, and removes the reporting requirements for the repetitive 
inspections.

DATES: Effective November 10, 1999.
    The incorporation by reference of certain publications, as listed 
in the regulations, was approved previously by the Director of the 
Federal Register as of March 17, 1995 (60 FR 38477, July 27, 1995).

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, 3936 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, Transport Airplane Directorate, 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 revising AD 95-04-07 R1, 
amendment 39-9317 (60 FR 38477, July 27, 1995), which is applicable to 
certain McDonnell Douglas Model DC-10-10, -15, and -30 airplanes, and 
KC-10A (military) airplanes, was published in the Federal Register on 
July 21, 1999 (64 FR 39104). The action proposed to revise AD 95-04-07 
R1 to continue to require 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 continue to provide 
for termination of the inspections for some airplanes by installing 
retainers on the bolts. In addition, the action proposed to provide an 
additional optional terminating modification and clarification of the 
requirements of the previous optional terminating modification, and 
proposed to remove the reporting requirements for the repetitive 
inspections.

Comments

    Interested persons have been afforded an opportunity to participate 
in the making of this amendment. No comments were submitted in response 
to the proposal or the FAA's determination of the cost to the public.

Conclusion

    The FAA has determined that air safety and the public interest 
require the adoption of the rule as proposed.

Cost Impact

    There are approximately 389 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 inspections that are currently required by AD 95-04-07 R1, and 
retained in this AD, will take approximately 2 work hours per airplane 
to accomplish, at an average labor rate of $60 per hour. Based on these 
figures, the cost impact of the currently required inspections on U.S. 
operators is estimated to be approximately $27,480, or $120 per 
airplane, per inspection cycle.
    The 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.
    Should an operator elect to accomplish the optional terminating 
modification, as specified in AD 95-04-07 R1, and the requirements 
clarified in this AD, 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 optional terminating 
modification specified by AD 95-04-07 R1 on U.S. operators is estimated 
to be between $2,984 and $3,062 per airplane.
    Should an operator elect to accomplish the optional terminating 
modification specified in McDonnell Douglas Service Bulletin DC10-71-
159 that will be provided by this AD, it will take approximately 16 
work hours per airplane to accomplish this required action, 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 optional terminating modification provided for by 
this AD on U.S. operators is estimated to be between $3,704 and $3,782 
per airplane.

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.

[[Page 54203]]

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 revising amendment 39-9317 (60 FR 
38477, July 27, 1995), and by adding a new airworthiness directive 
(AD), amendment 39-11354, to read as follows:

95-04-07  R2  McDonnell Douglas: Amendment 39-11354. Docket 99-NM-
14-AD. Revises AD 95-04-07 R1, Amendment 39-9317.

    Applicability: Model DC-10-30 and KC-10A (military) airplanes on 
which bolt retainers have not been installed on the engine mount in 
accordance with McDonnell Douglas DC-10 Service Bulletin 71-133, 
Revision 6, dated June 30, 1992; and all Model DC-10-10 and -15 
airplanes; certificated in any category.

    Note 1: This AD applies to each airplane identified in the 
preceding applicability 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 (d) 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 subsequent separation of the engine from 
the airplane, accomplish the following:

Restatement of Requirements of AD 95-04-07 R1, Amendment 39-9317

    (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.

Optional Terminating Actions

    (b) For Model DC-10-30 airplanes and KC-10A (military) airplanes 
only: Installation of retainers on the engine mount bolts of engines 
1, 2, or 3 in accordance with the procedures depicted in Figure 6 of 
Revision 6 of McDonnell Douglas DC-10 Service Bulletin 71-133, dated 
June 30, 1992, constitutes terminating action for the requirements 
of this AD for that engine.
    (c) For Model DC-10-10, -15, and -30 airplanes and KC-10A 
(military) airplanes: Modification of the forward engine mount bolts 
for engine 1, 2, or 3 in accordance with McDonnell Douglas Service 
Bulletin DC10-71-159, dated September 6, 1995, or Revision 01, dated 
July 28, 1997, constitutes terminating action for the requirements 
of this AD for that engine.

Alternative Methods of Compliance

    (d) 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.

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) Except as provided by paragraphs (b) and (c) of this AD, the 
actions shall be done in accordance with McDonnell Douglas Alert 
Service Bulletin DC10-71A159, Revision 1, dated January 31, 1995. 
This incorporation by reference was approved previously by the 
Director of the Federal Register as of March 17, 1995 (60 FR 38477, 
July 27, 1995). 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, 3936 Paramount Boulevard, 
Lakewood, California; or at the Office of the Federal Register, 800 
North Capitol Street, NW., suite 700, Washington, DC.
    (g) This amendment becomes effective on November 10, 1999.

    Issued in Renton, Washington, on September 29, 1999.
D.L. Riggin,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 99-25932 Filed 10-5-99; 8:45 am]
BILLING CODE 4910-13-U