[Federal Register Volume 64, Number 122 (Friday, June 25, 1999)]
[Proposed Rules]
[Pages 34170-34173]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 99-16157]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. 98-NM-35-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 adoption of a new airworthiness
directive (AD) that is applicable to all Lockheed Model L-1011-385
series airplanes. This proposal would 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. This proposal 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 the proposed AD
are intended to prevent corrosion or fatigue cracking of certain
structural elements, which could result in reduced structural integrity
of the airplane.
DATES: Comments must be received by August 9, 1999.
[[Page 34171]]
ADDRESSES: Submit comments in triplicate to the Federal Aviation
Administration (FAA), Transport Airplane Directorate, ANM-114,
Attention: Rules Docket No. 98-NM-35-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 Martin Aircraft & Logistics Center, 120 Orion
Street, Greenville, South Carolina 29605. 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-35-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-35-AD, 1601 Lind Avenue, SW., Renton, Washington
98055-4056.
Discussion
In April 1988, a transport category airplane managed to land after
tiny cracks in rivet holes in the upper fuselage linked together,
causing structural failure and explosive decompression. An 18-foot
section ripped from the fuselage. This accident focused greater
attention on the problem of aging aircraft.
Subsequently, in June 1988, the FAA sponsored a conference on aging
airplane issues, which was attended by representatives of the aviation
industry from around the world. It became obvious that, because of the
tremendous increase in air travel, the relatively slow pace of new
airplane production, and the apparent economic feasibility of operating
older technology airplanes rather than retiring them, increased
attention needed to be focused on this aging fleet and maintaining its
continued operational safety.
The Air Transport Association (ATA) of America and the Aerospace
Industries Association (AIA) of America committed to identifying and
implementing procedures to ensure continuing structural airworthiness
of aging transport category airplanes. The Airworthiness Assurance
Working Group (AAWG), with representatives from the aircraft operators,
manufacturers, regulatory authorities, and other aviation
representatives, was originally established in August 1988. The
objective of the AAWG was to sponsor ``Task Groups'' to:
1. Select service bulletins, applicable to each airplane model in
the transport fleet, to be recommended for mandatory modification of
aging airplanes,
2. Develop corrosion-directed inspections and prevention programs,
3. Review the adequacy of each operator's structural maintenance
program,
4. Review and update the Supplemental Structural Inspection
Documents (SSID),
5. Assess repair quality.
The Structures Task Group (STG) assigned to review the Lockheed
Model L-1011-385 series airplanes was formed in 1988, and included
operators of Model L-1011-385 series airplanes, Lockheed, the FAA, and
observers from regulatory agencies. Certain recommendations made by the
STG (pursuant to Item 1., described previously) are contained in
Lockheed Service Bulletin 093-51-035, Revision 1, dated December 16,
1991. The FAA previously issued AD 94-05-01, amendment 39-8839 (59 FR
10275, March 4, 1994), to require the structural inspections and the
modifications recommended in that document.
Since the issuance of that AD, the STG has recommended
accomplishment of certain other structural inspections to detect
corrosion or fatigue cracking of certain structural elements of the
airplane, and incorporation of certain structural modifications.
Corrosion or fatigue cracking of certain structural elements, if not
detected and corrected, could result in reduced structural integrity of
the airplane.
Explanation of Relevant Service Information
Lockheed has issued Service Bulletin 093-51-040, Revision 1, dated
October 1, 1997 (hereinafter referred to as the ``Collector Service
Bulletin''). The Collector Service Bulletin describes certain
repetitive inspections to detect corrosion or fatigue cracking of
certain structural elements of the airplane, including the area around
the two aft passengers doors and the fuselage-to-underwing longeron
area at butt line 94.5. The Collector Service Bulletin also describes
structural modifications of various elements of the airplane that have
been recommended by the STG, including modification of the retract
actuators of the main landing gear, modification of the bulkhead at
fuselage station 1363, and replacement of the wing rear spar web (for
Model L-1011-385-3 series airplanes). The Collector Service Bulletin
also references appropriate sources of accomplishment instructions for
the structural inspections and modifications.
The FAA has reviewed and approved the Collector Service Bulletin.
Accomplishment of the actions specified in the Collector Service
Bulletin is intended to adequately address the identified unsafe
condition.
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 require accomplishment of the actions specified in
the service bulletin described previously, except as discussed below.
[[Page 34172]]
Other Relevant Rulemaking
The FAA previously has issued AD 98-10-14, amendment 39-10526 (63
FR 26966, May 15, 1998), applicable to all Lockheed Model L-1011-385
series airplanes, to require various inspections to detect cracking of
certain areas of the rear spar caps, web, skin, and certain fastener
holes; and follow-on actions. Accomplishment of the terminating
modification listed in Lockheed Service Bulletin 093-57-215 (referenced
in Table II of the Collector Service Bulletin), as required by
paragraph (e) of this proposed AD; would constitute terminating action
for the inspection requirements of AD 98-10-14 for the affected
airplanes.
Differences Between This Proposed Rule and the Service Bulletin
Operators should note that Table II of the Collector Service
Bulletin references 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. However, the FAA previously
issued AD 99-08-20, amendment 39-11128 (64 FR 18324, April 14, 1999),
applicable to all Lockheed Model L-1011-385 series airplanes, to
require the structural inspections specified in Lockheed Service
Bulletins 093-53-268, Revision 1, and 093-53-272, dated November 12,
1996. The FAA has determined that the procedures described in Lockheed
Service Bulletin 093-53-272, Revision 1, are substantially similar to
those specified in the original issue of that service bulletin.
Therefore, paragraph (b) of this proposed AD specifies that structural
inspections in accordance with Lockheed Service Bulletins 093-53-268,
Revision 1, and 093-53-272, Revision 1, would not be required by this
AD.
Operators also should note that the Collector Service Bulletin
specifies that installation of the modifications in Lockheed Service
Bulletins 093-53-268, Revision 1, and 093-53-272, terminates the
inspections specified in Lockheed Service Bulletins 093-53-268,
Revision 1, and 093-53-272, Revision 1. However, this proposed AD
specifies that installation of those modifications does not constitute
terminating action for the subject inspections. AD 99-08-20 does not
provide for termination of the inspections by installation of the
modifications, though that AD does specify that inspections may be
deferred for 18,000 landings, if modifications in accordance with
Lockheed Service Bulletins 093-53-268, Revision 1, and 093-53-272 are
accomplished.
Operators also should note that, for airplanes that have exceeded
the later of the inspection thresholds specified in Lockheed Service
Bulletin 093-57-203, Revision 5, dated April 22, 1996, the Collector
Service Bulletin specifies a grace period of 5 years or 5,000 flight
cycles after April 11, 1996 (the initial release date of Lockheed
Service Bulletin 093-57-215), for accomplishment of the terminating
modification described in Lockheed Service Bulletin 093-57-215, dated
April 11, 1996. This proposed rule specifies a grace period for that
modification of 2 years or 2,000 flight cycles after the effective date
of this AD. The proposed grace period was developed by taking into
account the manufacturer's recommended grace period of five years after
April 11, 1996, as well as the length of time that is normally required
for the rulemaking process to be completed. In consideration of both of
these factors, the FAA finds that a grace period of 2 years or 2,000
flight cycles after the effective date of the AD is adequate to ensure
the continued safety of the transport airplane fleet. The FAA also
finds that such a grace period will provide operators with slightly
more time than what was specified in the Collector Service Bulletin to
accomplish the terminating modification.
Cost Impact
There are approximately 214 airplanes of the affected design in the
worldwide fleet. The FAA estimates that 107 airplanes of U.S. registry
would be affected by this proposed AD.
It would take approximately 315 work hours per airplane to
accomplish the proposed inspections, at an average labor rate of $60
per work hour. Based on these figures, the cost impact of the
inspections proposed by this AD on U.S. operators is estimated to be
$2,022,300, or $18,900 per airplane, per inspection cycle.
It would take approximately 3,385 work hours per airplane to
accomplish the proposed modifications, at an average labor rate of $60
per work hour. Required parts would cost approximately $242,000 per
airplane. Based on these figures, the cost impact of the modifications
proposed 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 proposed requirements
of this AD action, and that no operator would accomplish those actions
in the future if this AD were not adopted.
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 adding the following new
airworthiness directive:
Lockheed: 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 (f) of
this AD. The request should include an assessment of the
[[Page 34173]]
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. 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.
(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.
(b) 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; as listed in Table II of
Lockheed Service Bulletin 093-51-040, Revision 1, dated October 1,
1997; are not required by this AD. The inspections specified in
these service bulletins are required by AD 99-08-20, amendment 39-
11128.
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.
(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.
(4) Repair in accordance with a method approved by the Manager,
Atlanta Aircraft Certification Office (ACO), FAA, Small Airplane
Directorate.
Terminating Action
(d) 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; 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. Except as provided by paragraph (e)
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.
Note 2: 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.
(1) Prior to the threshold specified in the applicable service
bulletin listed in Table II of Lockheed Service Bulletin 093-51-040,
Revision 1.
(2) Within 5 years or 5,000 flight cycles after the effective
date of this AD, whichever occurs first.
(e) At the later of the times specified in paragraphs (e)(1) and
(e)(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. 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
(f) 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 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
(g) 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 June 18, 1999.
Kalene C. Yanamura,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 99-16157 Filed 6-24-99; 8:45 am]
BILLING CODE 4910-13-U
