[Federal Register Volume 65, Number 204 (Friday, October 20, 2000)]
[Rules and Regulations]
[Pages 62994-62999]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 00-26590]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. 98-NM-35-AD; Amendment 39-11933; AD 2000-21-01]
RIN 2120-AA64
Airworthiness Directives; Lockheed Model L-1011-385 Series
Airplanes
AGENCY: Federal Aviation Administration, DOT.
ACTION: Final rule.
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SUMMARY: This amendment adopts a new airworthiness directive (AD),
applicable to all Lockheed Model L-1011-385 series airplanes, that
requires repetitive inspections to detect corrosion or fatigue cracking
of certain structural elements of the airplane; corrective action, if
necessary; and incorporation of certain structural modifications. This
amendment is prompted by new recommendations related to incidents of
fatigue cracking and corrosion in transport category airplanes that are
approaching or have exceeded their economic design goal. The actions
specified by this AD are intended to prevent corrosion or fatigue
cracking of certain structural elements, which could result in reduced
structural integrity of the airplane.
DATES: Effective November 24, 2000.
The incorporation by reference of certain publications listed in
the regulations is approved by the Director of the Federal Register as
of November 24, 2000.
ADDRESSES: The service information referenced in this AD may be
obtained from Lockheed Martin Aircraft & Logistics Center, 120 Orion
Street, Greenville, South Carolina 29605. 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, Atlanta Aircraft Certification Office, One
Crown Center, 1895 Phoenix Boulevard, suite 450, Atlanta, Georgia; or
at the Office of the Federal Register,
[[Page 62995]]
800 North Capitol Street, NW., suite 700, Washington, DC.
FOR FURTHER INFORMATION CONTACT: Thomas Peters, Aerospace Engineer,
Systems and Flight Test Branch, ACE-116A, FAA, Atlanta Aircraft
Certification Office, One Crown Center, 1895 Phoenix Boulevard, suite
450, Atlanta, Georgia 30349; telephone (770) 703-6063; fax (770) 703-
6097.
SUPPLEMENTARY INFORMATION: A proposal to amend part 39 of the Federal
Aviation Regulations (14 CFR part 39) to include an airworthiness
directive (AD) that is applicable to all Lockheed Model L-1011-385
series airplanes was published in the Federal Register on June 25, 1999
(64 FR 34170). That action proposed to require repetitive inspections
to detect corrosion or fatigue cracking of certain structural elements
of the airplane; corrective action, if necessary; and incorporation of
certain structural modifications.
Explanation of New Service Information
Since the issuance of the notice of proposed rulemaking (NPRM), the
FAA has reviewed and approved Lockheed Service Bulletin 093-51-040,
Revision 2, dated October 21, 1999. The actions described in Revision 2
of the service bulletin are essentially similar to those described in
Lockheed Service Bulletin 093-51-040, Revision 1, dated October 1, 1997
(which was referenced as the applicable source of service information
for accomplishment of the actions specified in the NPRM). Revision 2 of
the service bulletin corrects and updates certain references, and adds
and revises certain ``notes'' to improve clarity. Therefore, the FAA
finds that either Revision 1 or Revision 2 of Lockheed Service Bulletin
093-51-040 (hereinafter referred to as ``the Collector Service
Bulletin'') is an acceptable source of service information for the
actions required by this AD.
However, certain new revisions of the individual service bulletins
listed in Tables I and II of Revision 2 of the Collector Service
Bulletin have reduced the compliance times for certain actions below
what was specified in the individual service bulletins listed in
Revision 1 of the Collector Service Bulletin. The FAA finds that to
reduce the compliance times in this way would necessitate issuance of a
supplemental NPRM and reopening of the comment period to allow adequate
time for public comment. The FAA finds that it is inappropriate to
further delay issuance of the final rule in this way. Therefore, while
this AD allows accomplishment of the actions in this AD in accordance
with either Revision 1 or Revision 2 of the Collector Service Bulletin,
the applicable compliance thresholds and repetitive intervals are those
listed in the individual service bulletins listed in Tables I and II of
Revision 1. Paragraphs (a)(1) and (a)(2), which specify the compliance
times for paragraph (a) of this AD, reference only Revision 1 of the
Collector Service Bulletin, and a new note, ``Note 2,'' has been added
to this final rule to clarify this issue.
Comments
Interested persons have been afforded an opportunity to participate
in the making of this amendment. Due consideration has been given to
the comments received.
Support for the Proposed Rule
One commenter supports the proposed rule.
Provide Grace Period for Certain Inspections in Paragraph (a)
One commenter notes that, though paragraph (a)(2) of the proposed
rule provides a grace period of ``one repetitive interval after the
effective date of this AD'' for the inspections specified in paragraph
(a) of the proposed rule, certain inspections are one-time inspections
and, therefore, do not have a repetitive interval.
The commenter makes no specific request for a change to the
proposed rule. However, the FAA infers that the commenter is requesting
that the FAA clarify the grace period for accomplishment of the subject
one-time inspections. The FAA concurs that some clarification is
needed, and notes that the inspections without repetitive intervals in
Table I reference ``Footnote 3,'' which provides a grace period of the
``next 'C' check not to exceed 14 months for aircraft exceeding
threshold.'' The FAA finds that a grace period of 14 months is adequate
to ensure that the unsafe condition is addressed in a timely manner,
without adversely affecting the safety of the airplane fleet.
Therefore, paragraph (a)(2) of this AD has been revised to specify a
grace period of 14 months after the effective date of this AD for the
service bulletins listed in Tables I and II of the Collector Service
Bulletin that do not specify a repetitive interval.
Eliminate Duplicate Requirements
One commenter questions whether the repetitive inspections
specified in Lockheed Service Bulletin 093-53-258, Revision 1, dated
April 4, 1996, as listed in Table II of the Collector Service Bulletin,
should be included in the proposed rule. The commenter notes that these
inspections are already required by AD 95-17-03, amendment 39-9332 (60
FR 40753, August 10, 1995).
The commenter makes no specific request for a change to the
proposed rule; however, the FAA infers that it is requesting that this
AD eliminate the inspections in Lockheed Service Bulletin 093-53-258,
Revision 1, from the requirements of this AD. The FAA concurs. While
the AD referenced by the commenter requires inspections with the
original issue of Lockheed Service Bulletin 093-53-258, dated February
20, 1990, the FAA finds that the inspections in accordance with that
bulletin, as required by AD 95-17-03, are acceptable for compliance
with this AD. Therefore, the FAA has revised paragraph (b) of this AD
to state that the structural inspections specified in Lockheed Service
Bulletin 093-53-258, Revision 1, are not required by this AD, and that
equivalent inspections are already required by AD 95-17-03. The
modifications of Lockheed Service Bulletin 093-53-258, Revision 1, that
terminate the inspections currently required by AD 95-17-03 are
required by this AD.
The same commenter questions why the inspections in Lockheed
Service Bulletin 093-57-203, Revision 5, dated April 22, 1996, are
included in the requirements of paragraph (a) of the proposed AD. The
commenter points out that paragraph (e) of the proposed rule would
require installation of the terminating modification in Lockheed
Service Bulletin 093-57-215, dated April 11, 1996, which eliminates the
need for the inspections in Lockheed Service Bulletin 093-57-203,
Revision 5.
The FAA concurs with the commenter's intent, though not for the
reason stated by the commenter. Accomplishment of the inspections
described in Lockheed Service Bulletin 093-57-203 is necessary to
ensure continued safety of the airplane fleet until accomplishment of
Lockheed Service Bulletin 093-57-215. However, the FAA notes that
inspections similar to those specified in Lockheed Service Bulletin
093-57-203, Revision 5, are currently required by AD 98-10-14,
amendment 39-10526 (63 FR 26966, May 15, 1998). (AD 98-10-14 requires
inspections in accordance with Lockheed Service Bulletin 093-57-203,
Revision 4, dated March 27, 1995, or Revision 6, dated August 18,
1997.) Thus, including these inspections in this AD would unnecessarily
duplicate compliance requirements. Therefore, paragraph (b) of this AD
has been revised to state that the structural
[[Page 62996]]
inspections specified in Lockheed Service Bulletin 093-57-203, Revision
5, are not required by this AD, and that equivalent inspections are
already required by AD 98-10-14. The terminating modifications of
Lockheed Service Bulletin 093-57-215 are required by this AD.
Request To Acknowledge Superseding Requirement
One commenter notes that the inspections specified in Lockheed
Service Bulletin 093-53-249 are currently required as part of the
requirements of AD 94-05-01, amendment 39-8839 (59 FR 10275, March 4,
1994). (AD 94-05-01 requires accomplishment of Lockheed Service
Bulletin 093-51-035, dated June 28, 1990--an older ``Collector''
service bulletin.) However, the proposed AD would reduce the repetitive
inspection interval for the inspections in that bulletin from 5,000 to
4,500 flight cycles. The commenter requests that language be added to
the proposed rule to acknowledge that accomplishment of the repetitive
inspections in Lockheed Service Bulletin 093-53-249, Revision 3, dated
February 28, 1994, at 4,500 flight cycle intervals, in accordance with
this AD, eliminates the need to record accomplishment of the
inspections in that service bulletin as required by AD 94-05-01. The
commenter notes that this will eliminate confusion and dual compliance
tracking for operators.
The FAA partially concurs with the commenter's request. Because AD
94-05-01 requires accomplishment of another ``Collector'' service
bulletin, which lists numerous service bulletins, the FAA is unable to
revise the requirement to accomplish the actions in only one of those
service bulletins without superseding that entire AD. Such an action
cannot be undertaken in the context of this rulemaking action.
Therefore, all of the requirements of AD 94-05-01 are still applicable.
As noted by the commenter, this results in two parallel inspection
requirements; operators will be responsible for tracking compliance for
both requirements. However, the FAA notes that the inspection in
accordance with Lockheed Service Bulletin 093-53-249, Revision 3, need
only be accomplished at the 4,500-flight-cycle interval required by
this AD. To clarify this, a new note ``Note 3'' has been added
following paragraph (a)(2) of this AD, to state, ``The inspections
specified in Lockheed Service Bulletin 093-53-249, Revision 3, dated
February 28, 1994, are included in the requirements of both AD 94-05-
01, amendment 39-8839, and paragraph (a) of this AD. Inspections in
accordance with Lockheed Service Bulletin 093-53-249, Revision 3, at
the interval specified in Table I of Lockheed Service Bulletin 093-51-
040, Revision 1, as required by this AD, are acceptable for compliance
with the inspections in accordance with Lockheed Service Bulletin 093-
53-249, Revision 3, required by AD 94-05-01.''
Require Overhaul of Main Landing Gear Actuator
One commenter states that one of the purposes of Revision 1 of the
Collector Service Bulletin was to require overhaul of the main landing
gear (MLG) actuator within 10 years after previous modification or
overhaul. The proper procedures for the MLG overhaul are described in
Change Notice (CN) 1, dated September 21, 1998, for Lockheed Service
Bulletin 093-32-238, Revision 3. However, Revision 1 of the Collector
Service Bulletin references Lockheed Service Bulletin 093-32-238,
Revision 3, with no mention of CN 1. The commenter asserts that the
proposed AD would not mandate the MLG overhaul as intended.
The commenter makes no specific request for a change to the
proposed AD. However, the FAA infers that the commenter is requesting
that the proposed rule be revised to reference CN 1 of the subject
service bulletin. The FAA partially concurs. The FAA acknowledges that
the current version of Lockheed Service Bulletin 093-32-238 is Revision
3, as revised by CN 1. The FAA also notes that Revision 2 of the
Collector Service Bulletin incorporates the correct reference. However,
to revise the proposed AD to specify overhaul of the MLG actuator in
accordance with Lockheed Service Bulletin 093-32-238, Revision 3, as
revised by CN 1, would necessitate reopening the comment period to
allow adequate time for public comment. Because of the criticality of
the unsafe condition addressed in this AD, the FAA finds that to delay
issuance of the final rule in this way would be inappropriate. However,
the FAA is considering further rulemaking to ensure that overhaul of
the MLG actuator is accomplished in a timely manner in accordance with
Lockheed Service Bulletin 093-32-238, Revision 3, as revised by CN 1. A
new paragraph, paragraph (e), has been added to this final rule (and
subsequent paragraphs have been reordered accordingly) to specify that
overhaul of the main landing gear actuator in accordance with Lockheed
Service Bulletin 093-32-238, Revision 3, dated April 11, 1996, as
listed in Table II of Lockheed Service Bulletin 093-51-040, Revision 1,
dated October 1, 1997, is not required by paragraph (d) of this AD.
Extend Compliance Times
One commenter expresses concern regarding the inspections specified
in Lockheed Service Bulletin 093-53-270, Revision 1, dated August 23,
1996, and the modification specified in Lockheed Service Bulletin 093-
53-271, dated October 18, 1995. The commenter operates several
airplanes modified in accordance with a certain supplemental type
certificate. The configuration of those airplanes will necessitate
request for approval of alternative methods of compliance (AMOC) for
the actions specified in these service bulletins. The commenter is
concerned that it will not be able to accomplish the AMOC's within the
compliance time proposed in this AD for those actions.
The commenter makes no specific request for a change to this AD.
However, the FAA infers that it is requesting extension of the
compliance time for the subject requirements. The FAA does not concur
that such an extension is appropriate. The inspection threshold of
13,000 or 9,000 flight cycles (depending on airplane configuration) and
repetitive inspection interval of 2,500 flight cycles for the actions
in Lockheed Service Bulletin 093-53-270, Revision 1, and the threshold
of 20,000 flight cycles for the actions in Lockheed Service Bulletin
093-53-271, were established based on consideration of structural
damage risk, damage probability, and damage growth rate. As noted by
the commenter, if the commenter's unique circumstances make it
impossible to comply with the requirements of this AD as written, it
will need to submit a request for approval of an AMOC, in accordance
with paragraph (g) of this AD. The FAA finds that the compliance time
is adequate for the commenter to submit its request for approval of an
AMOC and for the FAA to review the request. No change to the final rule
is necessary in this regard.
Clarify Terminating Action
One commenter requests that the proposed rule be revised to clearly
indicate which revisions of the service bulletins associated with the
rear spar modification are acceptable for terminating the rear spar
inspections described in Lockheed Service Bulletin 093-57-203 (which,
as described previously, are currently required by AD 98-10-14). The
commenter notes that Revision 1 of the Collector Service Bulletin lists
Lockheed Service Bulletin 093-57-184, Revisions 2 through 7, and
Service Bulletin 093-57-196, Revisions
[[Page 62997]]
1 through 6, as acceptable sources for instructions for the rear spar
modifications. However, AD 98-10-14 lists only Lockheed Service
Bulletin 093-57-184, Revision 6, dated October 28, 1991, and Revision
7, dated December 6, 1994, and Service Bulletin 093-57-196, Revision 5,
dated October 28, 1991, and Revision 6, dated December 6, 1994, as
sources of service information for the modifications of the rear spar
to terminate the repetitive inspections required by AD 98-10-14.
The FAA does not concur and has determined that no change to the
final rule is necessary relevant to the commenter's request. This
determination is based on the following:
As explained previously, structural inspections equivalent
to those specified in Lockheed Service Bulletin 093-57-203, Revision 5,
are required by AD 98-10-14. [Paragraph (b) of this final rule has been
revised to clarify this information.]
AD 98-10-14 correctly states terminating action for the
requirements of that AD. Therefore, use of any other revision to
accomplish the modifications would necessitate request for approval of
an AMOC in accordance with paragraph (c) of AD 98-10-14.
Current revisions of the referenced modification
bulletins, as well as Revision 2 of the Collector Service Bulletin
(described previously), correctly indicate which revisions are
acceptable for terminating the inspections in Lockheed Service Bulletin
093-57-203.
Section 2.B. of Revisions 1 and 2 of the Collector Service
Bulletin (page 9) states, ``Aircraft effectivity, inspection
thresholds, and repeat inspection intervals are shown for convenience,
and in the event of conflicts, the individual service bulletin shall
take precedence.''
Increase Compliance Threshold
One commenter requests an increase in the compliance threshold for
the modification of the rear spar on Model L-1011-385-3 series
airplanes specified in Lockheed Service Bulletin 093-57-215, dated
April 11, 1996, as listed in Table II of the Collector Service
Bulletin. The commenter states that the proposed compliance threshold
would preclude accomplishment of the rear spar modification during a
regularly scheduled maintenance visit, thus increasing the cost of the
modification for operators. The commenter requests that the compliance
time be increased to coincide with the compliance threshold for a
similar modification on Model L-1011-385-1 series airplanes. The
commenter points out that current proposed thresholds for inspection
and modification of the rear spar on the Model L-1011-385-3 series
airplanes are lower, in terms of accumulated flight cycles, and
earlier, in terms of design-life goal, than currently required actions
on the Model L-1011-385-1 series airplanes. The commenter separately
notes that while the L-1011-385-1 series airplanes are approaching 83
percent of the 36,000 flight-cycle design-life goal, the L-1011-385-1-
14, L-1011-385-1-15, and L-1011-385-3 series airplanes are at less than
50 percent of this goal. The commenter justifies its request on the
basis that Model L-1011-385-3 series airplanes are younger and
accumulate flight cycles at a lower rate than L-1011-385-1 series
airplanes.
The FAA does not concur with the commenter's request to increase
the compliance threshold. The proposed compliance time for the
modification of the rear spar on Model L-1011-385-3 series airplanes is
based on established service history and predicted fatigue cracking.
The FAA has determined that the unique characteristics of Model L-1011-
385-3 series airplanes (principally, higher fuel loading than on Model
L-1011-385-1 series airplanes) make it necessary to require
modification of the rear spar at a lower threshold relative to the
Model L-1011-385-1 series. Because of these unique characteristics,
inspection thresholds and repetitive intervals are consistently lower
for actions affecting the wing rear spar on Model L-1011-385-3 series
airplanes than for actions affecting the same area on Model L-1011-385-
1 series airplanes. No change to the final rule is necessary in this
regard.
Remove Inspection Requirement for Certain Airplanes
One commenter requests that any airplane on which a rear spar
modification has been installed previously be excluded from the
requirement to accomplish Lockheed Service Bulletin 093-57-194,
Revision 3, dated April 11, 1994, as listed in Table II of the
Collector Service Bulletin. The commenter states that it sees little
benefit in listing this requirement for any airplanes subject to AD 94-
05-01, and the requirement should only apply to airplanes on which the
rear spar has not been modified.
The FAA does not concur that any change to this AD is necessary.
For the service bulletin referenced by the commenter, Table II of the
Collector Service Bulletin clearly states, ``Rear spar web replacement
per Service Bulletin 093-57-184, 093-57-196, or 093-57-215 terminates
these requirements.'' The FAA finds that no clarification and no change
to the final rule is necessary in this regard.
Remove Terminating Modification Requirement
One commenter requests that Lockheed Service Bulletin 093-53-256,
Revision 1, dated October 7, 1991, be removed from the listing of
structural modifications in Table II of the Collector Service Bulletin.
The commenter points out that there are certain inspection findings
addressed by repetitive inspections and not by the immediate
installation of a terminating modification.
The FAA does not concur with the commenter's request. The intent of
this AD is that the inspections specified in Table II of the Collector
Service Bulletin be accomplished according to the schedule cited in
that bulletin, and that the specified terminating or corrective action
be accomplished, unless otherwise noted in this AD. For the specific
service bulletin referenced by the commenter, Table II states,
``Terminate repeat inspections of Part I by performing Part II
inspection and disposition of inspection findings per Service Bulletin
093-53-256 R1.'' The FAA finds that these instructions are clear, and
no change to the final rule is necessary in this regard.
Acknowledge Incorrect Reference to Service Bulletin in Table II
One commenter points out that Lockheed Service Bulletin 093-53-271,
dated October 18, 1995, listed in Table II of the Collector Service
Bulletin, is not an inspection bulletin. The commenter notes that
inspections are contained in Lockheed Service Bulletin 093-53-A271, as
required by AD 95-10-17, amendment 39-9234 (60 FR 26683, May 18, 1995).
The commenter makes no specific request for a change to the
proposal. The FAA infers that the commenter is requesting that the FAA
acknowledge that there are no inspections in accordance with Lockheed
Service Bulletin 093-53-271. The FAA does not concur with the
commenter's request. The listing in Table II of the Collector Service
Bulletin for Lockheed Service Bulletin 093-53-271 refers to Lockheed
Service Bulletin 093-53-A271, dated April 25, 1995, as the correct
source of information for accomplishment of the inspections. The
commenter is correct that AD 95-10-17 does require inspections in
accordance with Lockheed Service Bulletin 093-53-A271, dated April 25,
1995. However, Revision 2 of the Collector Service Bulletin correctly
notes that the
[[Page 62998]]
inspections required by that AD are one-time only. The FAA now finds
that it is necessary for the inspections in that bulletin to be
accomplished repetitively. For the inspections associated with Lockheed
Service Bulletin 093-53-271 (meaning the inspections of Lockheed
Service Bulletin 093-53-A271, dated April 25, 1995), Revision 1 of the
Collector Service Bulletin specifies repetitive intervals varying from
3,500 to 6,500 flight cycles, depending on the method of inspection.
The FAA has determined that the inspections and repetitive intervals
specified in Revision 1 of the Collector Service Bulletin are adequate
to ensure the safety of the airplane fleet. No change to the final rule
is necessary in this regard.
Conclusion
After careful review of the available data, including the comments
noted above, the FAA has determined that air safety and the public
interest require the adoption of the rule with the changes previously
described. The FAA has determined that these changes will neither
increase the economic burden on any operator nor increase the scope of
the AD.
Cost Impact
There are approximately 214 Model L-1011-385 series airplanes of
the affected design in the worldwide fleet. The FAA estimates that 107
airplanes of U.S. registry will be affected by this AD.
It will take approximately 315 work hours per airplane to
accomplish the required inspections, at an average labor rate of $60
per work hour. Based on these figures, the cost impact of the
inspections required by this AD on U.S. operators is estimated to be
$2,022,300, or $18,900 per airplane, per inspection cycle.
It will take approximately 3,385 work hours per airplane to
accomplish the required modifications, at an average labor rate of $60
per work hour. Required parts will cost approximately $242,000 per
airplane. Based on these figures, the cost impact of the modifications
required by this AD on U.S. operators is estimated to be $47,625,700,
or $445,100 per airplane.
The cost impact figures discussed above are 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. The cost impact figures discussed
in AD rulemaking actions represent only the time necessary to perform
the specific actions actually required by the AD. These figures
typically do not include incidental costs, such as the time required to
gain access and close up, planning time, or time necessitated by other
administrative actions.
Regulatory Impact
The regulations adopted herein will not have a substantial direct
effect 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, it
is determined that this final rule does not have federalism
implications under Executive Order 13132.
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.
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 adding the following new
airworthiness directive:
2000-21-01 Lockheed: Amendment 39-11933. Docket 98-NM-35-AD.
Applicability: All Model L-1011-385 series 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 (g) 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 corrosion or fatigue cracking of certain structural
elements, which could result in reduced structural integrity of the
airplane, accomplish the following:
Inspections
(a) Except as provided by paragraph (b) of this AD, perform
structural inspections to detect corrosion or fatigue cracking of
certain structural elements of the airplane, in accordance with the
applicable service bulletins listed under ``Service Bulletin Number,
Revision, and Date'' in Tables I and II of Lockheed Service Bulletin
093-51-040, Revision 1, dated October 1, 1997, or Revision 2, dated
October 21, 1999. Perform the initial inspections at the later of
the times specified in paragraphs (a)(1) and (a)(2) of this AD.
Thereafter, repeat each inspection at an interval not to exceed that
specified in the applicable service bulletin listed in Revision 1 of
Lockheed Service Bulletin 093-51-040.
(1) Prior to the threshold specified in the individual service
bulletin listed in Table I or II of Lockheed Service Bulletin 093-
51-040, Revision 1, as applicable.
(2) Within one repetitive interval after the effective date of
this AD, as specified in the individual service bulletin listed in
Table I or II of Lockheed Service Bulletin 093-51-040, Revision 1,
as applicable; or within 14 months after the effective date of this
AD for the service bulletins in Tables I and II that do not specify
a repetitive interval; as applicable.
Note 2: Operators should note that paragraphs (a)(1) and (a)(2)
of this AD reference only Revision 1 of Lockheed Service Bulletin
093-51-040. Certain new revisions of the individual service
bulletins listed in Tables I and II of Lockheed Service Bulletin
093-51-040, Revision 2, have reduced the compliance times below
those specified in the service bulletin revision levels listed in
Lockheed Service Bulletin 093-51-040, Revision 1. While this AD
allows accomplishment of the actions in this AD in accordance with
either Lockheed Service Bulletin 093-51-040, Revision 1, or Revision
2, the applicable compliance thresholds and repetitive intervals are
those listed in the individual service bulletins listed in Table I
or II of Lockheed Service Bulletin 093-51-040, Revision 1.
Note 3: The inspections specified in Lockheed Service Bulletin
093-53-249, Revision 3, dated February 28, 1994, are included in the
requirements of both AD 94-05-01, amendment 39-8839, and paragraph
(a) of this AD. Inspections in accordance with Lockheed Service
Bulletin 093-53-249, Revision 3, at the interval specified in Table
I of Lockheed Service Bulletin 093-51-040,
[[Page 62999]]
Revision 1, as required by this AD, are acceptable for compliance
with the inspections in accordance with Lockheed Service Bulletin
093-53-249, Revision 3, required by AD 94-05-01.
(b) The following service bulletins listed in Table II of
Lockheed Service Bulletin 093-51-040, Revision 1, dated October 1,
1997, and Revision 2, dated October 21, 1999, are excluded from the
requirements of paragraph (a) of this AD.
(1) The structural inspections specified in Lockheed Service
Bulletins 093-53-268, Revision 1, dated July 2, 1996, and 093-53-
272, Revision 1, dated March 17, 1997, are not required by this AD.
The inspections specified in these service bulletins are required by
AD 99-08-20, amendment 39-11128.
(2) The structural inspections specified in Lockheed Service
Bulletin 093-53-258, Revision 1, dated April 4, 1996, are not
required by this AD. Inspections equivalent to those specified in
that bulletin are required by AD 95-17-03, amendment 39-9332.
(3) The structural inspections specified in Lockheed Service
Bulletin 093-57-203, Revision 5, dated April 22, 1996, are not
required by this AD. Inspections equivalent to those specified in
that bulletin are required by AD 98-10-14, amendment 39-10526.
Corrective Action
(c) If any cracking is detected during any inspection required
by paragraph (a) of this AD, prior to further flight, accomplish the
actions specified in paragraph (c)(1), (c)(2), (c)(3), or (c)(4) of
this AD.
(1) Repair in accordance with the applicable service bulletin
referenced in Table I or II of Lockheed Service Bulletin 093-51-040,
Revision 1, dated October 1, 1997, or Revision 2, dated October 21,
1999.
(2) Repair in accordance with the applicable section of the
Lockheed L-1011 Structural Repair Manual.
(3) Accomplish the terminating modification in accordance with
the applicable service bulletin referenced in Table I or II of
Lockheed Service Bulletin 093-51-040, Revision 1, dated October 1,
1997, or Revision 2, dated October 21, 1999.
(4) Repair in accordance with a method approved by the Manager,
Atlanta Aircraft Certification Office (ACO), FAA.
Terminating Action
(d) Except as provided by paragraph (e) of this AD, install the
terminating modification referenced in each service bulletin listed
in Table II of Lockheed Service Bulletin 093-51-040, Revision 1,
dated October 1, 1997, or Revision 2, dated October 21, 1999; in
accordance with the applicable service bulletin listed under
``Service Bulletin Number, Revision, and Date'' in Table II of
Lockheed Service Bulletin 093-51-040, Revision 1 or Revision 2.
Except as provided by paragraph (f) of this AD, install each
modification at the later of the times specified in paragraphs
(d)(1) and (d)(2) of this AD. Such installation constitutes
terminating action for the applicable structural inspection required
by paragraph (a) of this AD.
(1) Prior to the threshold specified in the applicable service
bulletin listed in Table II of Lockheed Service Bulletin 093-51-040,
Revision 1 or Revision 2.
(2) Within 5 years or 5,000 flight cycles after the effective
date of this AD, whichever occurs first.
Note 4: Installation of the terminating modifications specified
in Lockheed Service Bulletin 093-53-268, Revision 1, dated July 2,
1996, and Lockheed Service Bulletin 093-53-272, dated November 12,
1996, does not constitute terminating action for the repetitive
inspection requirements of AD 99-08-20, amendment 39-11128.
(e) Overhaul of the main landing gear actuator in accordance
with Lockheed Service Bulletin 093-32-238, Revision 3, dated April
11, 1996, as listed in Table II of Lockheed Service Bulletin 093-51-
040, Revision 1, dated October 1, 1997, is not required by paragraph
(d) of this AD.
(f) At the later of the times specified in paragraphs (f)(1) and
(f)(2) of this AD: Install the terminating modification listed in
Lockheed Service Bulletin 093-57-215, as referenced in Table II of
Lockheed Service Bulletin 093-51-040, Revision 1, dated October 1,
1997, or Revision 2, dated October 21, 1999. Such installation
constitutes terminating action for the inspections required by AD
98-10-14, amendment 39-10526.
(1) Prior to the threshold specified in Lockheed Service
Bulletin 093-57-203, Revision 5, dated April 22, 1996.
(2) Within 2 years or 2,000 flight cycles after the effective
date of this AD, whichever occurs first.
Alternative Methods of Compliance
(g) 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, Atlanta ACO. Operators shall submit
their requests through an appropriate FAA Principal Maintenance
Inspector, who may add comments and then send it to the Manager,
Atlanta ACO.
Note 5: Information concerning the existence of approved
alternative methods of compliance with this AD, if any, may be
obtained from the Atlanta ACO.
Special Flight Permits
(h) Special flight permits may be issued in accordance with
Secs. 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
(i) Except as provided by paragraphs (c)(2) and (c)(4) of this
AD, the actions shall be done in accordance with Lockheed Service
Bulletin 093-51-040, Revision 1, dated October 1, 1997; or Lockheed
Service Bulletin 093-51-040, Revision 2, dated October 21, 1999.
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 Lockheed Martin Aircraft & Logistics
Center, 120 Orion Street, Greenville, South Carolina 29605. Copies
may be inspected at the FAA, Transport Airplane Directorate, 1601
Lind Avenue, SW., Renton, Washington; at the FAA, Atlanta Aircraft
Certification Office, One Crown Center, 1895 Phoenix Boulevard,
suite 450, Atlanta, Georgia; or at the Office of the Federal
Register, 800 North Capitol Street, NW., suite 700, Washington, DC.
Effective Date
(j) This amendment becomes effective on November 24, 2000.
Issued in Renton, Washington, on October 11, 2000.
Donald L. Riggin,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 00-26590 Filed 10-19-00; 8:45 am]
BILLING CODE 4910-13-P