AD Amdt-39-9317

[Federal Register Volume 60, Number 144 (Thursday, July 27, 1995)]
[Rules and Regulations]
[Pages 38477-38478]
From the Federal Register Online via the Government Publishing Office [<a href="http://www.gpo.gov">www.gpo.gov</a>]
[FR Doc No: 95-18087]



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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 94-NM-253-AD; Amendment 39-9317; AD 95-04-07 R1]


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; correction.

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SUMMARY: This amendment clarifies information in an existing 
airworthiness directive (AD), applicable to certain McDonnell Douglas 
Model DC-10 series 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. The actions specified in 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 clarifies the procedures for accomplishing the optional 
terminating action on engines 1, 2, and 3. This amendment is prompted 
by communications received from affected operators indicating that 
those procedures were unclear.

DATES: Effective March 17, 1995.

    The incorporation by reference of certain publications listed in 
the regulations was approved previously by the Director of the Federal 
Register as of March 17, 1995 (60 FR 11617, March 2, 1995).

ADDRESSES: The service information referenced in this AD may be 
obtained from McDonnell Douglas Corporation, 3855 Lakewood Boulevard, 
Long Beach, California 90846, Attention: Technical Publications 
Business Administration, Department 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, Los Angeles Aircraft Certification Office, 
Transport Airplane Directorate, 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: Maureen Moreland, Aerospace Engineer, 
Airframe Branch, ANM-120L, FAA, Transport Airplane Directorate, Los 
Angeles Aircraft Certification Office, 3960 Paramount Boulevard, 
Lakewood, California 90712; telephone (310) 627-5238; fax (310) 627-
5210.

SUPPLEMENTARY INFORMATION: On February 16, 1995, the FAA issued AD 95-
04-07, amendment 39-9159 (60 FR 11617, March 2, 1995), which is 
applicable to certain McDonnell Douglas Model DC-10-10, -15, and -30 
airplanes, and KC-10A (military) airplanes. That AD requires visual 
inspections to determine the condition of the lockwires on the forward 
engine mount bolts on engines 1, 2, and 3, and correction of 
discrepancies found. That AD also requires that operators report the 
results of the visual inspections to the FAA. Additionally, that AD 
provides for the termination of the visual inspections by installing 
retainers on the engine mount bolts on Model DC-10-30 airplanes and KC-
10A airplanes in accordance with Revision 6 of McDonnell Douglas DC-10 
Service Bulletin 71-133, dated June 30, 1992. That action was prompted 
by reports indicating that the lockwires on the forward engine mount 
bolts were stretched or broken. The actions required 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.
    Since the issuance of that AD, the FAA has received communication 
from affected operators indicating that the procedures for 
accomplishing the optional terminating action on engines 1, 2, and 3 
are unclear. These operators have indicated that the service 
information contained in McDonnell Douglas DC-10 Service Bulletin 71-
133, Revision 6, dated June 30, 1992 (which is referenced in the AD as 
the appropriate source of service information) does not describe 
procedures to accomplish the optional terminating action for engine 2. 
These operators have requested that the FAA clarify AD 95-04-07 to 
indicate exactly how to accomplish the optional terminating action for 
engine 2.
    In considering this request, and upon further review of the 
procedures contained in that service bulletin, the FAA concurs that 
clarification is necessary.
    It was the FAA's intent to include all engines in the provision for 
the optional terminating action. As such, the intent of paragraph (c) 
was to allow termination of the inspection for any engine on which 
retainers on the engine mount bolts had been installed. The FAA finds 
that although Figure 6 of the service bulletin does not describe 
procedures for installing retainers on the forward engine mount bolts 
on engine 2, the method for installing the retainers on engine 2 does 
not differ from the method for installing the retainers on engines 1 
and 3, which is described in Figure 6 of the service bulletin. 
Therefore, the FAA has determined that paragraph (c) must be revised to 
reference Figure 6 of McDonnell Douglas DC-10 Service Bulletin 71-133, 
Revision 6, dated June 30, 1992, as the appropriate source of service 
information to accomplish the optional terminating action on engine 2, 
as well as engines 1 and 3. 

[[Page 38478]]

    Action is taken herein to clarify AD 95-04-07 and to correctly add 
the AD as an amendment to section 39.13 of the Federal Aviation 
Regulations (14 CFR 39.13).
    The final rule is being reprinted in its entirety for the 
convenience of affected operators. The effective date of the rule 
remains March 17, 1995.
    Since this action only clarifies the procedures for accomplishing 
an optional action contained in a final rule, it has no adverse 
economic impact and imposes no additional burden on any person. 
Therefore, notice and public procedures hereon are unnecessary.
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 removing amendment 39-9159 (60 FR 
11617, March 2, 1995), and by adding a new airworthiness directive 
(AD), amendment 39-9317, to read as follows:

95-04-07 R1  McDonnell Douglas: Amendment 39-9317. Docket 94-NM-253-
AD. Revises AD 95-04-07, Amendment 39-9159.

    -Applicability: Model DC-10-30 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; Model DC-10-10 and -15 airplanes; and KC-10A 
(military) 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 use the authority 
provided in paragraph (d) of this AD to request approval from the 
FAA. This approval may address either no action, if the current 
configuration eliminates the unsafe condition; or different actions 
necessary to address the unsafe condition described in this AD. Such 
a request should include an assessment of the effect of the changed 
configuration on the unsafe condition addressed by this AD. In no 
case does the presence of any modification, alteration, or repair 
remove any airplane from the applicability of this AD.

     -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: -
    (a) Within 120 days after the effective date of this AD, unless 
accomplished previously within the last 750 flight hours prior to 
the effective date of this AD, 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. -
    (b) Submit a report of findings of broken lockwires and/or 
misaligned torque stripes found during the inspections required by 
paragraph (a) of this AD to the Manager, Los Angeles Aircraft 
Certification Office, FAA, Transport Airplane Directorate, 3960 
Paramount Boulevard, Lakewood, California 90712; or fax to (310) 
627-5210, at the times specified in either paragraph (b)(1) or 
(b)(2) of this AD, as applicable. The report must include the 
manufacturer's fuselage number of the airplane, number of cycles on 
the airplane, torque value of the bolt, and condition of the 
lockwire (i.e., broken or intact). Information collection 
requirements contained in this regulation have been approved by the 
Office of Management and Budget (OMB) under the provisions of the 
Paperwork Reduction Act of 1980 (44 U.S.C. 3501 et seq.) and have 
been assigned OMB Control Number 2120-0056. -
    (1) For airplanes on which the inspections are accomplished 
after the effective date of this AD: Submit reports within 30 days 
after finding any discrepancy. -
    (2) For airplanes on which the inspections have been 
accomplished prior to the effective date of this AD: Submit the 
initial report within 30 days after the effective date of this AD, 
and subsequent reports within 30 days after finding any discrepancy. 
-
    (c) 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. -
    (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.

    -(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. -
    (f) The inspections shall be done in accordance with McDonnell 
Douglas Alert Service Bulletin DC10-71A159, Revision 1, dated 
January 31, 1995. The installation shall be done in accordance with 
McDonnell Douglas DC-10 Service Bulletin 71-133, Revision 6, dated 
June 30, 1992. The incorporation by reference of these documents was 
approved by the Director of the Federal Register, in accordance with 
5 U.S.C. 552(a) and 1 CFR part 51, as of March 17, 1995 (60 FR 
11617, March 2, 1995). Copies may be obtained from McDonnell Douglas 
Corporation, 3855 Lakewood Boulevard, Long Beach, California 90846, 
Attention: Technical Publications Business Administration, 
Department C1-L51 (2-60). 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, Transport Airplane Directorate, 3960 Paramount Boulevard, 
Lakewood, California; or at the Office of the Federal Register, 800 
North Capitol Street, NW., suite 700, Washington, DC. -
    (g) This amendment is effective on March 17, 1995.

    Issued in Renton, Washington, on July 18, 1995.
Darrell M. Pederson,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 95-18087 Filed 7-26-95; 8:45 am]
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