[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
