[Federal Register Volume 63, Number 160 (Wednesday, August 19, 1998)]
[Proposed Rules]
[Pages 44411-44413]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 98-22241]
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Proposed Rules
Federal Register
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This section of the FEDERAL REGISTER contains notices to the public of
the proposed issuance of rules and regulations. The purpose of these
notices is to give interested persons an opportunity to participate in
the rule making prior to the adoption of the final rules.
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Federal Register / Vol. 63, No. 160 / Wednesday, August 19, 1998 /
Proposed Rules
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. 98-NM-199-AD]
RIN 2120-AA64
Airworthiness Directives; Lockheed Model L-1011-385 Series
Airplanes
AGENCY: Federal Aviation Administration, DOT.
ACTION: Notice of proposed rulemaking (NPRM).
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SUMMARY: This document proposes the supersedure of 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 action would 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. The actions specified by the proposed AD are
intended to prevent cracking of the FS 983 frame, which could result in
reduced structural integrity of the fuselage.
DATES: Comments must be received by October 5, 1998.
ADDRESSES: Submit comments in triplicate to the Federal Aviation
Administration (FAA), Transport Airplane Directorate, ANM-114,
Attention: Rules Docket No. 98-NM-199-AD, 1601 Lind Avenue, SW.,
Renton, Washington 98055-4056. Comments may be inspected at this
location between 9:00 a.m. and 3:00 p.m., Monday through Friday, except
Federal holidays.
The service information referenced in the proposed rule may be
obtained from Lockheed Aeronautical Systems Support Company (LASSC),
Field Support Department, Dept. 693, Zone 0755, 2251 Lake Park Drive,
Smyrna, Georgia 30080. This information may be examined 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.
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:
Comments Invited
Interested persons are invited to participate in the making of the
proposed rule by submitting such written data, views, or arguments as
they may desire. Communications shall identify the Rules Docket number
and be submitted in triplicate to the address specified above. All
communications received on or before the closing date for comments,
specified above, will be considered before taking action on the
proposed rule. The proposals contained in this notice may be changed in
light of the comments received.
Comments are specifically invited on the overall regulatory,
economic, environmental, and energy aspects of the proposed rule. All
comments submitted will be available, both before and after the closing
date for comments, in the Rules Docket for examination by interested
persons. A report summarizing each FAA-public contact concerned with
the substance of this proposal will be filed in the Rules Docket.
Commenters wishing the FAA to acknowledge receipt of their comments
submitted in response to this notice must submit a self-addressed,
stamped postcard on which the following statement is made: ``Comments
to Docket Number 98-NM-199-AD.'' The postcard will be date stamped and
returned to the commenter.
Availability of NPRMs
Any person may obtain a copy of this NPRM by submitting a request
to the FAA, Transport Airplane Directorate, ANM-114, Attention: Rules
Docket No. 98-NM-199-AD, 1601 Lind Avenue, SW., Renton, Washington
98055-4056.
Discussion
On November 5, 1991, the FAA issued AD 91-21-51, amendment 39-8099
(56 FR 61361, December 3, 1991), applicable to all Lockheed Model L-
1011-385 series airplanes, to require inspections to detect stress
corrosion cracking of fuselage station (FS) 983 main frame (left and
right sides), and repair, if necessary. That action was prompted by
reports of cracks found in the left and right sides of FS 983 main
frame, below the level of the cabin floor. The requirements of that AD
are intended to prevent cracks in the fuselage frame, which, if not
corrected, could result in reduced structural integrity of the
fuselage.
That AD also contained a provision that, if a single crack was
detected that was completely contained within a certain area of the FS
983 main frame web, repair of the crack was not required. In lieu of
repair, the cracked area could be treated with corrosion inhibitor and
inspected repetitively using internal visual and eddy current
techniques. In the preamble to AD 91-21-51, the FAA indicated that
these repetitive inspections were considered ``interim action'' and
that further rulemaking action was being considered. The FAA now has
determined that further rulemaking action is indeed necessary. As a
follow-on action from that determination, the FAA is now proposing to
mandate repair of any crack for which repair was deferred. Such repair
would constitute terminating action for the repetitive inspection
requirement.
Explanation of Relevant Service Information
The FAA has reviewed and approved Lockheed Tristar L-1011 Service
Bulletin 093-53-266, dated March 2, 1992, as revised by Change
Notification CN1, dated July 10, 1992; which describes, among other
things, procedures for repairing cracking of the FS 983 main frame web.
The service bulletin specifies that repair of any such cracking may be
accomplished in
[[Page 44412]]
accordance with Lockheed Drawing LCC-7622-327 (for Lockheed Model L-
1011-385 series airplanes having serial numbers 1002 through 1012
inclusive), or LCC-7622-325 (for Lockheed Model L-1011-385 series
airplanes having serial numbers 1013 through 1250 inclusive); or
partial frame replacement may be accomplished in accordance with
Lockheed Drawing LCC-7622-326 (for all Lockheed Model L-1011-385 series
airplanes).
Explanation of Requirements of Proposed Rule
Since an unsafe condition has been identified that is likely to
exist or develop on other products of this same type design, the
proposed AD would supersede AD 91-21-51 to continue to require
inspections to detect cracking of the FS 983 main frame (left and right
sides), and repair, if necessary. The proposed AD adds a 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, if necessary. Accomplishment of
such repair would constitute terminating action for the repetitive
inspection requirements of this proposed AD. The actions would be
required to be accomplished in accordance with the service bulletin
described previously, except as discussed below.
Differences Between Proposed Rule and Service Bulletin
Operators should note that, unlike the procedures described in
Lockheed Tristar L-1011 Service Bulletin 093-53-266, as revised by
Change Notification CN1, this proposed AD would not permit long-term
repetitive inspections of main frame web areas with only a single crack
to continue in lieu of accomplishment of a repair. The FAA has
determined that long-term continued operational safety will be better
assured by modifications or repairs to remove the source of the
problem, rather than by repetitive inspections. Long-term inspections
may not be providing the degree of safety assurance necessary for the
transport airplane fleet. This, coupled with a better understanding of
the human factors associated with numerous repetitive inspections, has
led the FAA to consider placing less emphasis on special procedures and
more emphasis on modifications. The proposed repair requirement is in
consonance with these considerations.
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
would be affected by this proposed AD.
The external eddy current inspection that currently is required by
AD 91-21-51, and that would be 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 this
inspection on U.S. operators is estimated to be $7,020, or $60 per
airplane.
The internal visual and eddy current inspection that currently is
required by AD 91-21-51, and that would be 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 this inspection 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 current or proposed
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 repair of cracking
that is proposed in this AD, 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 proposed by
this AD on U.S. operators is estimated to be $210,600, or $1,800 per
airplane.
Regulatory Impact
The regulations proposed herein would 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
proposal would not have sufficient federalism implications to warrant
the preparation of a Federalism Assessment.
For the reasons discussed above, I certify that this proposed
regulation (1) is not a ``significant regulatory action'' under
Executive Order 12866; (2) is not a ``significant rule'' under the DOT
Regulatory Policies and Procedures (44 FR 11034, February 26, 1979);
and (3) if promulgated, 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 copy of the draft
regulatory evaluation prepared for this action is contained in the
Rules Docket. A copy of it may be obtained by contacting the Rules
Docket at the location provided under the caption ADDRESSES.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation safety, Safety.
The Proposed Amendment
Accordingly, pursuant to the authority delegated to me by the
Administrator, the Federal Aviation Administration proposes to amend
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), to read as follows:
Lockheed: 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.
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)(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
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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 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 if repair of
any such crack was deferred in accordance with paragraph (e) of AD
91-21-51, amendment 39-8099. For any crack for which repair has been
deferred, prior to further flight, repair the crack 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.
(g)(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.
(g)(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.
(h) 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.
Issued in Renton, Washington, on August 12, 1998.
John J. Hickey,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 98-22241 Filed 8-18-98; 8:45 am]
BILLING CODE 4910-13-U
