[Federal Register Volume 60, Number 161 (Monday, August 21, 1995)]
[Proposed Rules]
[Pages 43417-43420]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 95-20631]
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DEPARTMENT OF TRANSPORTATION
14 CFR Part 39
[Docket No. 95-NM-39-AD]
Airworthiness Directives; McDonnell Douglas Model MD-11 Series
Airplanes and Model DC-10-30, DC-10-40, and KC-10A (Military) Airplanes
AGENCY: Federal Aviation Administration, DOT.
ACTION: Notice of proposed rulemaking (NPRM).
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SUMMARY: This document proposes the adoption of a new airworthiness
directive (AD) that is applicable to certain McDonnell Douglas Model
MD-11 series airplanes and Model DC-10-30, DC-10-40, and KC-10A
(military) airplanes. For Model MD-11 series airplanes, this proposal
would require an inspection to determine the serial number of the
forward trunnion bolts on the main landing gear (MLG), and rework or
replacement of the bolts, if necessary. For Model DC-10-30, DC-
[[Page 43418]]
10-40, and KC-10A (military) airplanes, this proposal would require an
inspection for evidence of missing chrome and for corrosion on the
chrome surfaces, or verification that the forward trunnion bolts have
been chrome plated in a specific manner; and rework or replacement of
the bolts, if necessary. This proposal is prompted by reports of chrome
flaking on the bearing surface of the trunnion bolts due to improper
cleaning of the base material prior to chrome plating. The actions
specified by the proposed AD are intended to prevent premature failure
of the trunnion bolts and subsequent collapse of the MLG as a result of
severe corrosion on the bearing surface and in the mechanical fuse due
to chrome flaking.
DATES: Comments must be received by October 17, 1995.
ADDRESSES: Submit comments in triplicate to the Federal Aviation
Administration (FAA), Transport Airplane Directorate, ANM-103,
Attention: Rules Docket No. 95-NM-39-AD, 1601 Lind Avenue, SW., Renton,
Washington 98055-4056. Comments may be inspected at this location
between 9:00 a.m. and 3:00 p.m., Monday through Friday, except Federal
holidays.
The service information referenced in the proposed rule may be
obtained from McDonnell Douglas Corporation, P.O. Box 1771, Long Beach,
California 90801-1771, Attention: Business Unit Manager, Technical
Administrative Support, Dept. 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.
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:
Comments Invited
Interested persons are invited to participate in the making of the
proposed 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 above. All
communications received on or before the closing date for comments,
specified above, will be considered before taking action on the
proposed rule. The proposals contained in this notice may be changed in
light of the comments received.
Comments are specifically invited on the overall regulatory,
economic, environmental, and energy aspects of the proposed 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 summarizing each FAA-public contact concerned with
the substance of this proposal will be filed in the Rules Docket.
Commenters wishing the FAA to acknowledge receipt of their comments
submitted in response to this notice must submit a self-addressed,
stamped postcard on which the following statement is made: ``Comments
to Docket Number 95-NM-39-AD.'' The postcard will be date stamped and
returned to the commenter.
Availability of NPRMs
Any person may obtain a copy of this NPRM by submitting a request
to the FAA, Transport Airplane Directorate, ANM-103, Attention: Rules
Docket No. 95-NM-39-AD, 1601 Lind Avenue, SW., Renton, Washington
98055-4056.
Discussion
The FAA has received reports of chrome flaking on the bearing
surface of the forward trunnion bolts installed on the main landing
gear (MLG) of McDonnell Douglas Model MD-11 series airplanes and Model
DC-10-30 and -40 airplanes. Such chrome flaking has resulted in severe
corrosion on the bearing surface and in the mechanical fuse. This
condition has been attributed to improper cleaning of the base material
prior to chrome plating. This condition, if not corrected, could result
in premature failure of the trunnion bolts and subsequent collapse of
the MLG.
The FAA has reviewed and approved McDonnell Douglas MD-11 Service
Bulletin 32-45, Revision 1, dated May 1, 1995, which describes
procedures for a visual inspection of Model MD-11 series airplanes to
determine the serial number of the forward trunnion bolts, part number
ARG7558-503 or ARG7558-505, on the right and left MLG's. The service
bulletin also provides procedures for rework or replacement of the
bolts with serviceable parts, if necessary. Accomplishment of the
rework or replacement will minimize the possibility of chrome flaking
on the forward trunnion bolts.
The FAA also has reviewed and approved McDonnell Douglas Service
Bulletin DC10-32-239, Revision 1, dated June 6, 1995, which describes
procedures for a visual inspection of Model DC-10-30, DC-10-40, and KC-
10A (military) airplanes for evidence of missing chrome and for
corrosion on the chrome surfaces of the trunnion bolts, or verification
that the forward trunnion bolts have been chrome plated in a specific
manner. The service bulletin also provides procedures for certain
rework or replacement of the bolts with serviceable parts, if
necessary.
Since an unsafe condition has been identified that is likely to
exist or develop on other products of this same type design, this
proposal would require the following:
For Model MD-11 series airplanes, this proposal would require an
inspection to determine the serial number of the forward trunnion
bolts, and rework or replacement of the bolts with serviceable parts,
if necessary. The actions would be required to be accomplished in
accordance with the MD-11 service bulletin described previously.
For Model DC-10-30, DC-10-40, and KC-10A (military) airplanes, this
proposal would require an inspection for evidence of missing chrome and
for corrosion on the chrome surfaces, or verification that the forward
trunnion bolts have been chrome plated in a specific manner; and rework
or replacement of the bolts with serviceable parts, if necessary. A
portion of the rework would be required to be accomplished in
accordance with the Component Maintenance Manual or a method approved
by the FAA. Other corrective actions would be required to be
accomplished in accordance with the DC-10 service bulletin described
previously.
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
[[Page 43419]]
been included in this notice to clarify this long-standing requirement.
There are approximately 414 Model MD-11 series airplanes and Model
DC-10-30, DC-10-40, and KC-10A (military) airplanes of the affected
design in the worldwide fleet. The FAA estimates that 196 airplanes of
U.S. registry would be affected by this proposed AD, that it would take
approximately 1 work hour per airplane to accomplish the proposed
actions, and that the average labor rate is $60 per work hour. Based on
these figures, the total cost impact of the proposed AD on U.S.
operators is estimated to be $11,760, or $60 per airplane.
The total cost impact figure discussed above is based on
assumptions that no operator has yet accomplished any of the proposed
requirements of this AD action, and that no operator would accomplish
those actions in the future if this AD were not adopted.
The regulations proposed herein would 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
proposal would not have sufficient federalism implications to warrant
the preparation of a Federalism Assessment.
For the reasons discussed above, I certify that this proposed
regulation (1) is not a ``significant regulatory action'' under
Executive Order 12866; (2) is not a ``significant rule'' under the DOT
Regulatory Policies and Procedures (44 FR 11034, February 26, 1979);
and (3) if promulgated, 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 copy of the draft
regulatory evaluation prepared for this action is contained in the
Rules Docket. A copy of it may be obtained by contacting the Rules
Docket at the location provided under the caption ADDRESSES.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation safety, Safety.
The Proposed Amendment
Accordingly, pursuant to the authority delegated to me by the
Administrator, the Federal Aviation Administration proposes to amend
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 USC 106(g), 40101, 40113, 44701.
Sec. 39.13 [Amended]
2. Section 39.13 is amended by adding the following new
airworthiness directive:
McDonnell Douglas: Docket 95-NM-39-AD.
Applicability: Model MD-11 series airplanes, as listed in
McDonnell Douglas MD-11 Service Bulletin 32-45, Revision 1, dated
May 1, 1995; and Model DC-10-30, DC-10-40, and KC-10A (military)
airplanes, as listed in McDonnell Douglas DC-10 Service Bulletin
DC10-32-239, Revision 1, dated June 6, 1995; 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 (e) 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 premature failure of the trunnion bolts and
subsequent collapse of the main landing gear (MLG), accomplish the
following:
(a) For Model MD-11 series airplanes: Within 18 months after the
effective date of this AD, perform a visual inspection to determine
the serial number of the forward trunnion bolts, part number
ARG7558-503 or ARG7558-505, on the right and left MLG's, in
accordance with McDonnell Douglas MD-11 Service Bulletin 32-45,
Revision 1, dated May 1, 1995.
(1) If the serial number of the trunnion bolt is STR0217,
STR0232, STR0237 through STR0242 inclusive, or STR0244 through
STR0284 inclusive; or if the trunnion bolt has been chrome plated in
accordance with the Component Maintenance Manual (CMM), Chapter 20-
10-02, Revision 31, dated September 1, 1991, since original
manufacture: No further action is required by this AD.
(2) For trunnion bolts other than those identified in paragraph
(a)(1) of this AD: Prior to further flight, remove the chrome
plating on the trunnion bolt, replace the plating, and reinstall the
reworked trunnion bolt; or replace the trunnion bolt with a
serviceable part; in accordance with McDonnell Douglas MD-11 Service
Bulletin 32-45, Revision 1, dated May 1, 1995.
(b) For Model MD-11 series airplanes: As of the effective date
of this AD, no person shall install a trunnion bolt having part
number ARG7558-503 or ARG7558-505 on the right or left MLG of any
airplane unless the bolt meets the condition specified in either
paragraph (b)(1), (b)(2), or (b)(3) of this AD.
(1) The trunnion bolt bears the serial number STR0217, STR0232,
STR0237 through STR0242 inclusive, or STR0244 through STR0284
inclusive; or
(2) The trunnion bolt has been chrome plated in accordance with
the CMM, Chapter 20-10-02, Revision 31, dated September 1, 1991,
since original manufacture; or
(3) The trunnion bolt has been reworked in accordance with
McDonnell Douglas MD-11 Service Bulletin 32-45, Revision 1, dated
May 1, 1995.
(c) For Model DC-10-30, DC-10-40, and KC-10A (military)
airplanes: Within 18 months after the effective date of this AD,
accomplish either paragraph (c)(1) or (c)(2) of this AD, as
applicable, in accordance with McDonnell Douglas DC-10 Service
Bulletin DC10-32-239, Revision 1, dated June 6, 1995.
(1) For airplanes on which the forward trunnion bolts, part
number (P/N) ARG7558-501, installed on the left and right MLG's,
have accumulated 6,000 or more total flight hours or 2,000 or more
total flight cycles as of the date of the inspection: Remove the
bolts and perform a visual inspection for evidence of missing chrome
and for corrosion on the chrome surfaces, in accordance with the
service bulletin.
(i) If no evidence of missing chrome and no corrosion on the
chrome surfaces are found, no further action is required by this AD.
(ii) If any evidence of missing chrome or any corrosion on the
chrome surfaces is found, prior to further flight, accomplish either
paragraph (c)(1)(ii)(A) or (c)(1)(ii)(B) of this AD.
(A) Remove the chrome plating on the trunnion bolt in accordance
with the service bulletin; replace the plating in accordance with
the CMM, Chapter 20-10-02, Revision 31, dated September 1, 1991, or
in accordance with a method approved by a McDonnell Douglas
Designated Engineering Representative (DER) who has been given a
special delegation by the Manager, Los Angeles Aircraft
Certification Office (ACO), FAA, Transport Airplane Directorate, to
make such a finding; and reinstall the reworked bolt in accordance
with the service bulletin. Or
(B) Replace the trunnion bolt with a serviceable part in
accordance with the service bulletin.
(2) For airplanes other than those identified in paragraph
(c)(1) of this AD: Verify whether the forward trunnion bolts, part
number (P/N) ARG7558-501, installed on the left and right MLG's,
have been chrome plated since original manufacture, in accordance
with the CMM, Chapter 20-10-02, Revision 31, dated September 1,
1991, or
[[Page 43420]]
in accordance with a method approved by a McDonnell Douglas DER who has
been given a special delegation by the Manager, Los Angeles ACO, to
make such a finding.
(i) If the bolts have been chrome plated since original
manufacture, in accordance with the CMM, Chapter 20-10-02, Revision
31, dated September 1, 1991, or in accordance with a method approved
by a McDonnell Douglas DER who has been given a special delegation
by the Manager, Los Angeles ACO, to make such a finding: No further
action is required by this AD.
(ii) If any bolt has not been chrome plated since original
manufacture, in accordance with the CMM, Chapter 20-10-02, Revision
31, dated September 1, 1991, or in accordance with a method approved
by a McDonnell Douglas DER who has been given a special delegation
by the Manager, Los Angeles ACO, to make such a finding: Prior to
further flight, accomplish the requirements of either paragraph
(c)(1)(ii)(A) or (c)(1)(ii)(B) of this AD in accordance with the
service bulletin.
(d) For Model DC-10-30, DC-10-40, and KC-10A (military)
airplanes: As of the effective date of this AD, no person shall
install a trunnion bolt, having part number ARG7558-501, on the
right or left MLG of any airplane unless the bolt meets the
condition specified in either paragraph (d)(1), (d)(2), (d)(3), or
(d)(4) of this AD.
(1) The trunnion bolt has been chrome plated in accordance with
the CMM, Chapter 20-10-02, Revision 31, dated September 1, 1991,
since original manufacture; or
(2) The trunnion bolt has been chrome plated in accordance with
a method approved by a McDonnell Douglas DER who has been given a
special delegation by the Manager, Los Angeles ACO, to make such
findings; or
(3) The bolt has been reworked in accordance with McDonnell
Douglas DC-10 Service Bulletin DC10-32-239, Revision 1, dated June
6, 1995; or
(4) The bolt has accumulated 6,000 or more total flight hours or
2,000 or more total flight cycles and has been visually inspected
for evidence of missing chrome and for corrosion on the chrome
surfaces, in accordance with McDonnell Douglas DC-10 Service
Bulletin DC10-32-239, Revision 1, dated June 6, 1995, and no
evidence of missing chrome or corrosion on the chrome surfaces was
found.
(e) 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 ACO. 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.
(f) 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.
Issued in Renton, Washington, on August 15, 1995.
S.R. Miller,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 95-20631 Filed 8-18-95; 8:45 am]
BILLING CODE 4910-13-U