[Federal Register Volume 60, Number 201 (Wednesday, October 18, 1995)]
[Rules and Regulations]
[Pages 53860-53862]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 95-25028]
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DEPARTMENT OF TRANSPORTATION
14 CFR Part 39
[Docket No. 94-NM-254-AD; Amendment 39-9392; AD 95-21-07]
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 Lockheed Model L-1011-385 series airplanes, that requires
modifications of various fluid drainage areas of the fuselage. This
amendment is prompted by incidents involving corrosion and fatigue
cracking in transport category airplanes that are approaching or have
exceeded their economic design goal; these incidents have jeopardized
the airworthiness of the affected airplanes. The actions specified by
this AD are intended to prevent degradation of the structural
capabilities of the affected airplanes due to problems associated with
corrosion.
DATES: Effective November 17, 1995.
The incorporation by reference of certain publications listed in
the regulations is approved by the Director of the Federal Register as
of November 17, 1995.
ADDRESSES: The service information referenced in this AD may be
obtained from Lockheed Aeronautical Systems Support Company, Field
Support Department, Dept. 693, Zone 0755, 2251 Lake Park Drive, Smyrna,
Georgia. 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, Small Airplane Directorate, Campus
Building, 1701 Columbia Avenue, Suite 2-160, College Park, Georgia
30337-2748; or at the Office of the Federal Register, 800 North Capitol
Street, NW., suite 700, Washington, DC.
FOR FURTHER INFORMATION CONTACT: Thomas Peters, Flight Test Branch,
ACE-160A, FAA, Atlanta Aircraft Certification Office, Small Airplane
Directorate, Campus Building, 1701 Columbia Avenue, Suite 2-160,
College Park, Georgia 30337-2748; telephone (404) 305-7367; fax (404)
305-7348.
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 Model L-1011-385 series airplanes
was published in the Federal Register on February 22, 1995 (60 FR
9796). That action proposed to require the accomplishment of
modifications, installations, and other actions relative to fluid
drainage areas of the fuselage.
Interested persons have been afforded an opportunity to participate
in the making of this amendment. Due consideration has been given to
the comments received.
One commenter supports the proposal.
One commenter requests that the proposal be revised to remove the
requirement to comply with the procedures described in Lockheed Service
Bulletin 093-53-095, Revision 2, dated June 22, 1987. This specific
service bulletin describes procedures for installing drainage
provisions at the pressure deck of the nose landing gear. The commenter
states that these procedures are listed as part of Corrosion Task C-53-
110-05 in the Model L-1011 Corrosion Prevention and Control Program
(Lockheed Document LR 31889), and are mandated by AD 93-20-03,
amendment 39-8710 (58 FR 60775, November 18, 1993). The FAA does not
concur. Corrosion Task C-53-110-05 entails an inspection for corrosion
of the pressure deck area above the nose landing gear compartment. An
additional part of that Task is the installation of an insulation
standoff modification that is described in Appendix D of Lockheed
Document
[[Page 53861]]
LR 31889. However, the actions proposed in the notice, and described in
Lockheed Service Bulletin 093-53-095, go beyond those currently
mandated by AD 93-20-03. These new actions require the installation of
two drain valves and the installation of additional drain holes. The
FAA has determined that these actions must be accomplished in order to
positively address the unsafe condition presented by the problems
associated with corrosion.
This commenter also requests that the final rule be revised to
allow the installation of any of the optional insulation standoffs
specified in Appendix D [``Insulation Batts Standoffs (Bilges)''] of
Lockheed Document LR 31889. The commenter points out that Lockheed
Service Bulletin 93-53-095 specifically calls for the installation of
stud-type standoffs, but Appendix D of the Lockheed Document allows the
use of several options for maintaining a space between structure and
insulation. This particular commenter, a U.S. operator, elected to
install (previously) the ``egg crate'' option, and requests that the AD
indicate that use of such an option is considered to be in compliance
with the intent of the rule. The FAA concurs. A new Note 4 has been
added to the final rule to specify this.
Paragraph (a)(2) of the final rule has been revised to correct a
typographical error that appeared in the published version of the
notice. In the notice, the compliance terminology of that paragraph was
stated as, ``* * * that has exceeded the IA for that zone as December
17, 1994* * *'' However, it should have read, ``* * * as of December
17, 1994* * *'' The final rule has been corrected accordingly.
Additionally, the final rule has been revised to clarify that the
issuance date of Lockheed Document LR 31889 is April 15, 1994.
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.
There are approximately 241 Model L-1011-385 series airplanes of
the affected design in the worldwide fleet. The FAA estimates that 117
airplanes of U.S. registry will be affected by this proposed AD. It
will take approximately 236 work hours per airplane to accomplish the
required actions, including time to gain access and close up. The
average labor rate is currently $60 per work hour. Based on these
figures, the total cost impact of the requirements of this AD on U.S.
operators is estimated to be $1,656,720, or $14,160 per airplane.
The total cost impact figure discussed above is 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 regulations adopted herein will not have substantial direct
effects on the States, on the relationship between the national
government and the States, or on the distribution of power and
responsibilities among the various levels of government. Therefore, in
accordance with Executive Order 12612, it is determined that this final
rule does not have sufficient federalism implications to warrant the
preparation of a Federalism Assessment.
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 USC 106(g), 40101, 40113, 44701.
Sec. 39.13 [Amended]
2. Section 39.13 is amended by adding the following new
airworthiness directive:
95-21-07 Lockheed: Amendment 39-9392. Docket 94-NM-254-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
otherwise 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 (b) 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 structural failure due to the problems associated
with corrosion accomplish the following:
(a) Accomplish the modifications, installations, and inspections
described in the Lockheed service bulletins listed in Section 7.2 of
Lockheed Document Number LR 31889, ``Corrosion Prevention and
Control Program, TriStar L-1011,'' Revision A, dated April 15, 1994
(hereafter referred to as ``the Document''), in accordance with the
following schedule:
Note 2: Airplanes on which the modifications, installations, and
inspections required by this paragraph have been accomplished prior
to the effective date of this AD or during production are considered
to be in compliance with this paragraph.
Note 3: Airplanes on which the modifications, installations, and
inspections required by this paragraph have been accomplished
previously in accordance with an earlier version of the applicable
service bulletin listed in Section 7.2 of the Document, are
considered to be in compliance with this paragraph.
Note 4: In lieu of the installation of insulation batts
standoffs (stud-type) specified in Lockheed Service Bulletin 093-53-
095, Revision 2, dated June 22, 1987, operators may install any of
the optional insulation batts standoffs specified in Appendix D of
the Document. Such installation is considered to be in compliance
with these requirements of this AD.
Note 5: ``Airplane zones,'' ``implementation ages,'' and
``repeat intervals,'' as referred to in this paragraph, are
specified in Section 4.3 of the Document.
(1) For modifications, installations, and inspections located in
an airplane zone that has not yet exceeded the ``implementation
age'' (IA) for that zone as of December 17, 1994 (one year after the
effective date of AD 93-20-03, amendment 39-8710): Compliance is
required no later than the IA plus the repeat (R) interval for the
applicable zone.
(2) For modifications, installations, and inspections located in
an airplane zone that
[[Page 53862]]
has exceeded the IA for that zone as of December 17, 1994: Compliance
is required within one R interval for that zone, measured from
December 17, 1994.
(3) For airplanes that are 20 years old or older as of December
17, 1994: Accomplishment of the modifications, installation, and
inspections is required within one R interval for the applicable
airplane zone, but not to exceed 6 years, measured from December 17,
1994, whichever occurs first.
(b) 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 Aircraft Certification
Office (ACO), ACE-115A, FAA, Small Airplane Directorate. Operators
shall submit their requests through an appropriate FAA Principal
Maintenance Inspector, who may add comments and then send it to the
Manager, Atlanta ACO.
Note 6: Information concerning the existence of approved
alternative methods of compliance with this AD, if any, may be
obtained from the Atlanta ACO.
(c) 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.
(d) The actions shall be done in accordance with Lockheed
Document Number LR 31889, ``Corrosion Prevention and Control
Program, TriStar L-1011,'' Revision A, dated April 15, 1994, which
contains the following list of effective pages:
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Revision level
Page No. shown on page Date shown on page
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0.1-0.4, 0.6, 1.1, 1.3, 2.1, Original........... March 15, 1991.
2.2, 3.1-3.4, 4.1-4.8, 4.12,
4.14, 4.15, 4.20, 4.24, 4.28,
4.30-4.33, 4.36-4.41, 5.2,
6.1, A.1, A.2, B.3, B.5-B.13,
C.2-C.10.
0.5, 1.2, 4.9-4.11, 4.13, 4.16- Revision A......... April 15, 1994.
4.19, 4.21-4.23, 4.25-4.27,
4.29, 4.34, 4.35, 5.1, 7.1-
7.4, B.2, B.4, C.1, D.1.
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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 Aeronautical Systems
Support Company, Field Support Department, Dept. 693, Zone 0755,
2251 Lake Park Drive, Smyrna, Georgia. Copies may be inspected at
the FAA, Transport Airplane Directorate, 1601 Lind Avenue, SW.,
Renton, Washington; or at the FAA, Atlanta Aircraft Certification
Office, Small Airplane Directorate, Campus Building, 1701 Columbia
Avenue, Suite 2-160, College Park, Georgia; or at the Office of the
Federal Register, 800 North Capitol Street, NW., suite 700,
Washington, DC.
(e) This amendment becomes effective on November 17, 1995.
Issued in Renton, Washington, on October 3, 1995.
Darrell M. Pederson,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 95-25028 Filed 10-17-95; 8:45 am]
BILLING CODE 4910-13-U
