[Federal Register Volume 65, Number 204 (Friday, October 20, 2000)]
[Rules and Regulations]
[Pages 62994-62999]
From the Federal Register Online via the Government Publishing 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