[Federal Register Volume 60, Number 41 (Thursday, March 2, 1995)]
[Rules and Regulations]
[Pages 11617-11619]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 95-4379]



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DEPARTMENT OF TRANSPORTATION
14 CFR Part 39

[Docket No. 94-NM-253-AD; Amendment 39-9159; AD 95-04-07]


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; request for comments.

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SUMMARY: This amendment adopts a new airworthiness directive (AD) that 
is applicable to certain McDonnell Douglas Model DC-10 series airplanes 
and KC-10A (military) airplanes. This action requires inspections to 
determine the condition of the lockwires on the forward engine mount 
bolts and correction of any discrepancies found. This action also 
provides for termination of the inspections for some airplanes by 
installing retainers on the bolts. This amendment is prompted by 
reports of stretched or broken lockwires on the forward engine mount 
bolts. The actions specified in this 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.

DATES: Effective March 17, 1995.
    The incorporation by reference of certain publications listed in 
the regulations is approved by the Director of the Federal Register as 
of March 17, 1995.
    Comments for inclusion in the Rules Docket must be received on or 
before May 1, 1995.

ADDRESSES: Submit comments in triplicate to the Federal Aviation 
Administration (FAA), Transport Airplane Directorate, ANM-103, 
Attention: Rules Docket No. 94-NM-253-AD, 1601 Lind Avenue, SW., 
Renton, Washington 98055-4056.
    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, Department L51, M.C. 2-98. This information may be examined 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.

FOR FURTHER INFORMATION CONTACT: Maureen A. Moreland, Aerospace 
Engineer, Airframe Branch, ANM-121L, 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 October 10, 1985, the FAA issued AD 85-
22-01, amendment 39-5157, (50 FR 42153, October 18, 1985) applicable to 
certain McDonnell Douglas Model DC-10-10, -15, -30, and -40 airplanes, 
and KC-10A (military) airplanes. That AD requires repetitive 
inspections of the engine-to-pylon forward and aft mount and the engine 
mount bolts; and replacement of the bolts and nuts, torque check of the 
bolts, and installation of a torque stripe on the bolts, if necessary. 
That AD provided for termination of the inspections by replacing the 
engine mount bolts with bolts having a lockwire hole in the bolt head, 
installing tabs with a lockwire hole, and installing lockwires.
    Since the issuance of that AD, the FAA has received reports of 
broken or stretched lockwires on the forward engine mount bolts on 
several Model DC-10-30 airplanes on which the terminating actions 
described in AD 85-22-01 had been accomplished. Investigation has 
revealed that these lockwires may have stretched and eventually broken 
because the foward engine mount bolts had loosened. McDonnell Douglas 
has developed a bolt retainer that will prevent these bolts from 
loosening from the engines of Model DC-10-30 airplanes and KC-10A 
(military) airplanes.
    Additionally, the FAA has received reports of loose bolts on the 
engine [[Page 11618]] mounts of Model DC-10-10 airplane engines. 
However, McDonnell Douglas has not yet developed a bolt retainer for 
Model DC-10-10 or -15 airplanes, or KC-10A airplanes.
    Broken lockwires, if not corrected, could result in loosening of 
the engine mount bolts and subsequent separation of the engine from the 
airplane.
    The lockwires on the forward engine mount bolts of Model DC-10-30 
airplanes are similar to those installed on Model DC-10-10 and -15 
airplanes, and KC-10A airplanes. Therefore, the FAA finds that Model 
DC-10-10 and -15 airplanes, and KC-10A airplanes are also subject to 
the same unsafe condition.
    The FAA has reviewed and approved McDonnell Douglas Alert Service 
Bulletin DC10-71A159, Revision 1, dated January 31, 1995, which 
describes procedures for repetitive visual inspections to detect broken 
lockwires on the forward engine mount bolts on engines 1, 2, and 3. If 
any broken lockwire is found, the service bulletin describes procedures 
to check the torque of the bolt, to install a new lockwire, and to 
install a torque stripe on the bolt. This service bulletin also 
describes procedures for subsequent visual inspections to detect 
misalignment of the torque stripe.
    Since an unsafe condition has been identified that is likely to 
exist or develop on other airplanes of the same type design, this AD is 
being issued to prevent broken lockwires, which could result in 
loosening of the engine mount bolts and subsequent separation of the 
engine from the airplane. This 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. 
The actions are required to be accomplished in accordance with the 
alert service bulletin described previously.
    The required compliance time of 120 days is usually sufficient to 
allow for a brief comment period before adoption of a final rule. In 
this AD, however, that compliance time was selected because of the 
degree of urgency associated with addressing the subject unsafe 
condition and the practical aspects of performing the inspection within 
a maximum interval of time allowable for all affected airplanes to 
continue to operate without compromising safety. Further, the FAA took 
into account the 6-month compliance time recommended by the 
manufacturer, as well as the number of days required for the rulemaking 
process; in consideration of these factors, the FAA finds that 120 days 
after the effective date of this rule will fall approximately at the 
same time as that recommended by the manufacturer.
    This AD also requires that operators report the results of the 
visual inspections to the FAA. The intent of these reports is to enable 
the FAA to determine how widespread the problem of broken lockwires may 
be in the affected fleet. Based on the results of these reports, 
further corrective action may be warranted.
    Since retainers have been developed only for Model DC-10-30 
airplanes and KC-10A airplanes, this AD also 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.
    As a result of recent communications with the Air Transport 
Association (ATA) of America, the FAA has learned that, in general, 
some operators may misunderstand the legal effect of AD's on airplanes 
that are identified in the applicability provision of the AD, but that 
have been altered or repaired in the area addressed by the AD. The FAA 
points out that all airplanes identified in the applicability provision 
of an AD are legally subject to the AD. If an airplane has been altered 
or repaired in the affected area in such a way as to affect compliance 
with the AD, the owner or operator is required to obtain FAA approval 
for an alternative method of compliance with the AD, in accordance with 
the paragraph of each AD that provides for such approvals. A note has 
been included in this rule to clarify this long-standing requirement.
    Since a situation exists that requires the immediate adoption of 
this regulation, it is found that notice and opportunity for prior 
public comment hereon are impracticable, and that good cause exists for 
making this amendment effective in less than 30 days.

Comments Invited

    Although this action is in the form of a final rule that involves 
requirements affecting flight safety and, thus, was not preceded by 
notice and an opportunity for public comment, comments are invited on 
this rule. Interested persons are invited to comment on this rule by 
submitting such written data, views, or arguments as they may desire. 
Communications shall identify the Rules Docket number and be submitted 
in triplicate to the address specified under the caption ADDRESSES. All 
communications received on or before the closing date for comments will 
be considered, and this rule may be amended in light of the comments 
received. Factual information that supports the commenter's ideas and 
suggestions is extremely helpful in evaluating the effectiveness of the 
AD action and determining whether additional rulemaking action would be 
needed.
    Comments are specifically invited on the overall regulatory, 
economic, environmental, and energy aspects of the rule that might 
suggest a need to modify the rule. All comments submitted will be 
available, both before and after the closing date for comments, in the 
Rules Docket for examination by interested persons. A report that 
summarizes each FAA-public contact concerned with the substance of this 
AD will be filed in the Rules Docket.
    Commenters wishing the FAA to acknowledge receipt of their comments 
submitted in response to this rule must submit a self-addressed, 
stamped postcard on which the following statement is made: ``Comments 
to Docket Number 94-NM-253-AD.'' The postcard will be date stamped and 
returned to the commenter.
    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.
    The FAA has determined that this regulation is an emergency 
regulation that must be issued immediately to correct an unsafe 
condition in aircraft, and that it is not a ``significant regulatory 
action'' under Executive Order 12866. It has been determined further 
that this action involves an emergency regulation under DOT Regulatory 
Policies and Procedures (44 FR 11034, February 26, 1979). If it is 
determined that this emergency regulation otherwise would be 
significant under DOT Regulatory Policies and Procedures, a final 
regulatory evaluation will be prepared and placed in the Rules Docket. 
A copy of it, if filed, 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 
[[Page 11619]] 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:

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

    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 (c) 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 in 
accordance with 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.
    (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. 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 McDonnell Douglas 
Corporation, P.O. Box 1771, Long Beach, California 90801-1771, 
Attention: Business Unit Manager, Technical Administrative Support, 
Department L51, M.C. 2-98. Copies may be inspected at the FAA, 
Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton, 
Washington; or at 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.
    (g) This amendment becomes effective on March 17, 1995.

    Issued in Renton, Washington, on February 16, 1995.
Darrell M. Pederson,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 95-4379 Filed 3-1-95; 8:45 am]
BILLING CODE 4910-13-U