[Federal Register Volume 65, Number 159 (Wednesday, August 16, 2000)]
[Rules and Regulations]
[Pages 49899-49901]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 00-20505]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. 99-NM-233-AD; Amendment 39-11863; AD 2000-16-08]
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 supersedes an existing airworthiness directive
(AD), applicable to certain Lockheed Model L-1011-385 series airplanes,
that currently requires repetitive inspections to detect cracking of
the canted pressure bulkhead at fuselage station (FS) 1212, and
repetitive inspections to detect cracking of the web at the fastener
rows of the vertical stiffener-to-web; and repair or replacement of the
web with a new web, if necessary. This amendment requires that the
initial inspections be accomplished at a reduced threshold. This
amendment is prompted by a report of fatigue cracking of the canted
pressure bulkhead at FS 1212. The actions specified by this AD are
intended to detect and correct fatigue cracking of the canted pressure
bulkhead at FS 1212, which could result in blowout of a panel between
adjacent stiffeners and consequent cabin depressurization.
DATES: Effective September 20, 2000.
The incorporation by reference of Lockheed Service Bulletin 093-53-
277, Revision 1, dated November 19, 1998, as listed in the regulations,
is approved by the Director of the Federal Register as of September 20,
2000.
The incorporation by reference of Lockheed Service Bulletin 093-53-
277, dated July 2, 1996, as listed in the regulations, was approved
previously by the Director of the Federal Register as of October 25,
1996 (61 FR 53044, October 10, 1996).
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, Small Airplane Directorate, 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.
FOR FURTHER INFORMATION CONTACT: Thomas Peters, Program Manager,
Program Management and Services Branch, ACE-118A, FAA, Small Airplane
Directorate, 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) by superseding AD 96-20-10,
amendment 39-9776 (61 FR 53044, October 10, 1996), which is applicable
to certain Lockheed Model L-1011-385 series airplanes, was published in
the Federal Register on October 6, 1999 (64 FR 54230). The action
proposed to supersede AD 96-20-10 to continue to require repetitive
inspections to detect cracking of the canted pressure bulkhead at FS
1212, and repetitive inspections to detect cracking of the web at the
fastener rows of the vertical stiffener-to-web; and repair or
replacement of the web with a new web, if necessary. The action also
proposed to require that the initial inspections be accomplished at a
reduced threshold.
Comment Received
Interested persons have been afforded an opportunity to participate
in the making of this amendment. Due consideration has been given to
the single comment received.
The commenter requests that the FAA revise paragraphs (b)(1)(i) and
(b)(1)(ii) of the proposal to reference section 53-11-00, Figure 854,
of the L-1011 Structural Repair Manual (SRM), dated March 15, 1999.
Lockheed Repair Drawing LCC-7622-385 is referenced in the proposal as
the appropriate source of service information for identifying areas in
which cracking may be found. The commenter indicates that the drawing
has been revised and incorporated into the SRM since the release of
Lockheed Service Bulletin 093-53-277, Revision 1, dated November 19,
1998. The commenter states that confusion could arise due to the nature
of certain LCC drawings that are not formally controlled or released;
operators could have the outdated version of the drawing on file. The
revised LCC drawing and new SRM figure provide more detail of the
inspection area and more detail of the repair instructions on the
bulkhead than those specified in the original version of the drawing.
The FAA concurs with the commenter's request to reference the
revised service information, and has revised the final rule
accordingly. However, the FAA finds that both repair drawings
adequately identify the areas in which cracking may be found.
Therefore, the FAA has added a note to the final rule to give
operators credit for using the version of the repair drawing cited in
the proposal.
Conclusion
After careful review of the available data, including the comment
noted above, the FAA has determined that air safety and the public
interest require the adoption of the rule with the change previously
described. The FAA has determined that this change will neither
increase the economic burden on any operator nor increase the scope of
the AD.
Cost Impact
There are approximately 235 airplanes of the affected design in the
worldwide fleet. The FAA estimates that 116 airplanes of U.S. registry
will be affected by this AD. The requirements of this AD will not add
any new additional economic burden on affected operators other than the
costs that are associated with beginning the inspection at an earlier
time than would have been required by AD 96-20-10 (initial inspection
is now required within 18,000 flight cycles, rather than 20,000 flight
cycles).
The actions that are currently required by AD 96-20-10, and are
retained in this AD, take approximately 5 work hours per airplane to
accomplish, at an average labor rate of $60 per work hour. Based on
these figures, the cost impact of the currently required actions on
U.S. operators is estimated to be $34,800, or $300 per airplane, per
inspection cycle.
The 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.
[[Page 49900]]
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 removing amendment 39-9776 (61 FR
53044, October 10, 1996), and by adding a new airworthiness directive
(AD), amendment 39-11863, to read as follows:
2000-16-08 Lockheed: Amendment 39-11863. Docket 99-NM-233-AD.
Supersedes AD 96-20-10, Amendment 39-9776.
Applicability: Model L-1011-385 series airplanes; serial numbers
1013 through 1250 inclusive; 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 (c)(1)
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 detect and correct fatigue cracking of the canted pressure
bulkhead at fuselage station (FS) 1212, which could result in
blowout of a panel between adjacent stiffeners and consequent cabin
depressurization, accomplish the following:
Repetitive Inspections
(a) Perform a detailed visual inspection to detect cracking of
the entire aft surface of the canted pressure bulkhead at FS 1212
between left buttock line (LBL) 103 and right buttock line (RBL)
103; and perform an optical inspection using a borescope or other
optical device to detect cracking of the web at the fastener rows of
the vertical stiffener-to-web; in accordance with Lockheed Service
Bulletin 093-53-277, dated July 2, 1996, or Revision 1, dated
November 19, 1998; at the earlier of the times specified in
paragraphs (a)(1) and (a)(2) of this AD. Thereafter, repeat these
inspections at intervals not to exceed 1,000 flight cycles.
(1) Prior to the accumulation of 20,000 total flight cycles, or
within 60 days after October 25, 1996 (the effective date of AD 96-
20-10), whichever occurs later; or
(2) Prior to the accumulation of 18,000 total flight cycles, or
within 60 days after the effective date of this AD, whichever occurs
later.
Note 2: For the purposes of this AD, a detailed visual
inspection is defined as: ``An intensive visual examination of a
specific structural area, system, installation, or assembly to
detect damage, failure, or irregularity. Available lighting is
normally supplemented with a direct source of good lighting at
intensity deemed appropriate by the inspector. Inspection aids such
as mirror, magnifying lenses, etc., may be used. Surface cleaning
and elaborate access procedures may be required.''
Repair
(b) If any cracking is found during any inspection required by
paragraph (a) of this AD, prior to further flight, accomplish either
paragraph (b)(1) or (b)(2) of this AD.
(1) Accomplish either paragraph (b)(1)(i) or (b)(1)(ii) of this
AD, as applicable.
(i) If the cracking is found in an area that is specified
Lockheed Service Bulletin 093-53-277, dated July 2, 1996, or
Revision 1, dated November 19, 1998, repair in accordance with
Section 53-11-00, Figure 854, of the L-1011 Structural Repair Manual
(SRM), dated March 15, 1999. Accomplishment of a repair in
accordance with this paragraph constitutes terminating action for
the repetitive inspections required by paragraph (a) of this AD at
the repaired location only. Or
(ii) If the cracking is found in an area that is not specified
in Lockheed Service Bulletin 093-53-277, dated July 2, 1996, or
Revision 1, dated November 19, 1998, repair in accordance with a
method approved by the Manager, Atlanta Aircraft Certification
Office (ACO), FAA, Small Airplane Directorate.
Note 3: Lockheed Repair Drawing LCC-7622-385 also is considered
an acceptable source of service information for the accomplishment
of the requirements of paragraph (b)(1)(i) of this AD.
(2) Replace the entire web with a new web in accordance with
Lockheed Service Bulletin 093-53-277, dated July 2, 1996, or
Revision 1, dated November 19, 1998. Such replacement constitutes
terminating action for the repetitive inspections required by
paragraph (a) of this AD.
Alternative Methods of Compliance
(c)(1) 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.
(2) Alternative methods of compliance, approved previously in
accordance with AD 96-20-10, amendment 39-9776, are approved as
alternative methods of compliance with paragraph (b) of this AD.
Note 4: 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
(d) 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
(e) Except as provided by paragraph (b)(1)(ii) of this AD, the
actions shall be done in accordance with Lockheed Service Bulletin
093-53-277, dated July 2, 1996; or Lockheed Service Bulletin 093-53-
277, Revision 1, dated November 19, 1998. Revision 1 of Lockheed
Service Bulletin 093-53-277 contains the following list of effective
pages:
[[Page 49901]]
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Revision level shown on
Page number page Date shown on page
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1-3, 5.................................... 1.......................... November 19, 1998.
4, 6-9.................................... Original................... July 2, 1996.
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(1) The incorporation by reference of Lockheed L-1011 Service
Bulletin 093-53-277, Revision 1, dated November 19, 1998, is
approved by the Director of the Federal Register, in accordance with
5 U.S.C. 552(a) and 1 CFR part 51.
(2) The incorporation by reference of Lockheed Service Bulletin
093-53-277, dated July 2, 1996, was approved previously by the
Director of the Federal Register as of October 25, 1996 (61 FR
53044, October 10, 1996).
(3) 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; or at the
FAA, Small Airplane Directorate, 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.
(f) This amendment becomes effective on September 20, 2000.
Issued in Renton, Washington, on August 8, 2000.
Donald L. Riggin,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 00-20505 Filed 8-15-00; 8:45 am]
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