[Federal Register Volume 64, Number 79 (Monday, April 26, 1999)]
[Rules and Regulations]
[Pages 20144-20146]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 99-10183]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. 98-NM-199-AD; Amendment 39-11147; AD 99-09-14]
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 all Lockheed Model L-1011-385 series airplanes,
that currently requires inspections to detect cracking of fuselage
station (FS) 983 main frame (left and right sides), and repair, if
necessary. That AD was prompted by reports of cracks found in the left
and right sides of the FS 983 main frame, below the level of the cabin
floor. This amendment adds a new requirement to review the airplane
maintenance records to determine if a crack within the FS 983 main
frame web was detected previously, and if repair of any such crack was
deferred; and repetitive inspections, if necessary, until
accomplishment of a repair. This amendment also adds terminating action
for the repetitive inspections. The actions specified by this AD are
intended to prevent cracking of the FS 983 frame, which could result in
reduced structural integrity of the fuselage.
DATES: Effective June 1, 1999.
The incorporation by reference of Lockheed Tristar L-1011 Service
Bulletin 093-53-266, dated March 2, 1992; as revised by Change
Notification CN1, dated July 10, 1992, as listed in the regulations, is
approved by the Director of the Federal Register as of June 1, 1999.
The incorporation by reference of Lockheed Service Bulletin 093-53-
264, dated October 4, 1991, was approved previously by the Director of
the Federal Register as of December 18, 1991 (56 FR 61361, December 3,
1991).
ADDRESSES: The service information referenced in this AD may be
obtained from Lockheed Martin Aircraft & Logistics Centers, 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
[[Page 20145]]
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, Aerospace Engineer,
Systems and Flight Test Branch, ACE-116A, 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 91-21-51,
amendment 39-8099 (56 FR 61361, December 3, 1991), which is applicable
to all Lockheed Model L-1011-385 series airplanes, was published in the
Federal Register on August 19, 1998 (63 FR 44411). The action proposed
to require inspections to detect cracking of fuselage station (FS) 983
main frame (left and right sides), and repair, if necessary. The action
also proposed to add a new requirement to review the airplane
maintenance records to determine if a crack within the FS 983 main
frame web was detected previously, and if repair of any such crack was
deferred; and repair, prior to further flight, if necessary.
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.
Request To Revise Certain Requirements of Proposed Rule
One commenter requests that paragraph (f) of the proposed rule be
revised to read, ``For aircraft with previously deferred cracks,
continue the current repetitive inspection at the limits given in AD
91-21-51, paragraph (e). Repair of these cracks must be accomplished in
accordance with Lockheed Service Bulletin 093-53-266, dated March 2,
1992, within 18 months after the effective date of this AD.'' The
commenter states that, as paragraph (f) is worded in the proposed rule,
the operator would have to repair any cracks that were deferred in
accordance with the requirements in paragraph (e), prior to further
flight. This could result in airplanes being immediately out of
compliance as of the effective date of the final rule.
The FAA concurs that paragraph (f) of the proposed rule could be
misinterpreted as suggested by the commenter. The FAA's intent was that
the repair be accomplished prior to further flight after the
determination that is required by the first sentence of paragraph (f).
To accommodate the commenter's concern, the FAA has revised paragraph
(f) of this AD to require the repetitive inspections to continue until
accomplishment of the repair. In addition, a new paragraph (g) has been
added to require accomplishment of the repair within 18 months after
the effective date of this AD.
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 described
previously. 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 235 airplanes of the affected design in the
worldwide fleet. The FAA estimates that 117 airplanes of U.S. registry
will be affected by this AD.
The external eddy current inspection that currently is required by
AD 91-21-51, and is retained in this AD, takes approximately 1 work
hour 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 inspection on U.S. operators is estimated to be $7,020, or $60
per airplane.
The internal visual and eddy current inspections that currently are
required by AD 91-21-51, and retained in this AD, take approximately 1
work hour per airplane to accomplish, at an average labor rate of $60
per work hour. Based on these figures, the cost impact of these
inspections on U.S. operators is estimated to be $7,020, or $60 per
airplane, per inspection cycle.
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.
Should an operator be required to accomplish the necessary repair
of cracking, it would take approximately 30 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 repair required by this AD on
U.S. operators is estimated to be $1,800 per airplane.
Regulatory Impact
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 U.S.C. 106(g), 40113, 44701.
Sec. 39.13 [Amended]
2. Section 39.13 is amended by removing amendment 39-8099 (56 FR
61361, December 3, 1991), and by adding a new airworthiness directive
(AD), amendment 39-11147, to read as follows:
99-09-14 Lockheed: Amendment 39-11147. Docket 98-NM-199-AD.
Supersedes AD 91-21-51, amendment 39-8099.
Applicability: All Model L-1011-385 series airplanes,
certificated in any category.
[[Page 20146]]
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 (h)(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 prevent cracking in the fuselage station (FS) 983 frame,
which could result in reduced structural integrity of the fuselage,
accomplish the following:
Restatement of Requirements of AD 91-21-51, Amendment 39-8099
(a) Within 20 days after December 18, 1991 (the effective date
of AD 91-21-51, amendment 39-8099), inspect the left and right sides
of FS 983 main frame from waterline (WL) 175 to WL 200 to detect
cracks using a high frequency eddy current procedure, in accordance
with paragraph A. of the Accomplishment Instructions of Lockheed
Service Bulletin 093-53-264, dated October 4, 1991. At the
operator's option, the internal inspection required by paragraph (d)
below may be used in lieu of the external inspection.
(b) If cracks that extend into the main frame caps are found
during the inspection performed in accordance with paragraph (a) of
this AD, prior to further flight, repair in accordance with a method
approved by the Manager, Atlanta Aircraft Certification Office
(ACO), FAA, Small Airplane Directorate.
(c) Within 60 days after December 18, 1991, perform an internal
visual and an eddy current inspection of the FS 983 main frame cap
and web in accordance with paragraph B. of the Accomplishment
Instructions of Lockheed Service Bulletin 093-53-264, dated October
4, 1991.
(d) If cracks in the following locations are found during the
inspection required by paragraph (c) of this AD, prior to further
flight, repair in accordance with a method approved by the Manager,
Atlanta ACO.
(1) Any crack extending into the main frame caps.
(2) Any crack extending into the web-to-cap radius.
(3) Any crack extending into a web area outside the shaded area
shown in Figure 1, Sheet 3, of Lockheed Service Bulletin 093-53-264,
dated October 4, 1991.
(4) More than 1 crack within the main frame web area shown in
Figure 1, Sheet 3, of Lockheed Service Bulletin 093-53-264, dated
October 4, 1991.
(e) If, during the inspection required by paragraph (c) of this
AD, a single crack is found that is completely contained within the
main frame web area shown in Figure 1, Sheet 3, of Lockheed Service
Bulletin 093-53-264, dated October 4, 1991: Prior to further flight,
treat the cracked section of the web with corrosion inhibitor in
accordance with the service bulletin. Thereafter, repeat the
inspections at intervals not to exceed 90 days, using the internal
inspection procedure required by paragraph (c) of this AD.
New Requirements of This AD
(f) Within 18 months after the effective date of this AD: Review
the airplane maintenance records to determine if a crack within the
main frame web area has been detected previously, and to determine
if repair of any such crack was deferred in accordance with
paragraph (e) of AD 91-21-51, amendment 39-8099. For airplanes
having cracks for which a repair has been deferred, continue the
repetitive inspections in accordance with the requirements of
paragraph (e) of this AD, until accomplishment of paragraph (g) of
this AD.
(g) Within 18 months after the effective date of this AD: Repair
any crack for which repair has been deferred as specified in
paragraph (e) of this AD, in accordance with Lockheed Tristar L-1011
Service Bulletin 093-53-266, dated March 2, 1992; as revised by
Change Notification CN1, dated July 10, 1992. Accomplishment of such
repair constitutes terminating action for the repetitive inspections
required by paragraph (e) of this AD.
Note 2: Lockheed Tristar L-1011 Service Bulletin 093-53-266,
dated March 2, 1992; as revised by Change Notification CN1, dated
July 10, 1992; references Lockheed Drawings LCC-7622-325, LCC-7622-
326, and LCC-7622-327, as additional sources of service information
to accomplish repairs.
Alternative Methods of Compliance
(h)(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.
(h)(2) Alternative methods of compliance, approved previously in
accordance with AD 91-21-51, amendment 39-8099, are approved as
alternative methods of compliance with the inspection requirements
of paragraphs (a) and (c) of this AD, and the repair/modification
requirements of paragraphs (b) and (d) of this AD.
Note 3: 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
(i) 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.
Incorporation by Reference
(j) Except as provided by paragraphs (b) and (d) of this AD, the
actions shall be done in accordance with Lockheed Tristar L-1011
Service Bulletin 093-53-266, dated March 2, 1992; as revised by
Change Notification 093-53-266, CN1, dated July 10, 1992; and
Lockheed Service Bulletin 093-53-264, dated October 4, 1991.
(1) The incorporation by reference of Lockheed Tristar L-1011
Service Bulletin 093-53-266, dated March 2, 1992; as revised by
Change Notification 093-53-266, CN1, dated July 10, 1992, 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
093-53-264, dated October 4, 1991, was approved previously by the
Director of the Federal Register as of December 18, 1991 (56 FR
61361, December 3, 1991).
(3) Copies may be obtained from Lockheed Martin Aircraft &
Logistics Centers, 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.
(k) This amendment becomes effective on June 1, 1999.
Issued in Renton, Washington, on April 19, 1999.
D. L. Riggin,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 99-10183 Filed 4-23-99; 8:45 am]
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