[Federal Register Volume 62, Number 62 (Tuesday, April 1, 1997)]
[Proposed Rules]
[Pages 15429-15431]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 97-8125]
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Proposed Rules
Federal Register
________________________________________________________________________
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. 62, No. 62 / Tuesday, April 1, 1997 /
Proposed Rules
[[Page 15429]]
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. 96-NM-257-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 various types of
inspections to detect fatigue cracking of certain areas of the rear
spar caps, web, skin, and certain fastener holes; and repair or
modification, if necessary. This action would reduce the repetitive
inspection interval for all of the currently required inspections,
except for the x-ray inspections. It also would revise the terminating
modification provision for some airplanes. This proposal is prompted by
reports of cracks found during the currently-required inspections,
which had progressed to lengths greater than predicted. The actions
specified by the proposed AD are intended to ensure that fatigue
cracking is detected and corrected in a timely manner before it can
lead to rupture of the rear spar, extensive damage to the wing, and
spillage of fuel.
DATES: Comments must be received by May 9, 1997.
ADDRESSES: Submit comments in triplicate to the Federal Aviation
Administration (FAA), Transport Airplane Directorate, ANM-103,
Attention: Rules Docket No. 96-NM-257-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, 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.
FOR FURTHER INFORMATION CONTACT: Thomas Peters, Aerospace Engineer,
Systems and Flight Test Branch, ACE-116A, 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:
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 96-NM-257-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-103, Attention: Rules
Docket No. 96-NM-257-AD, 1601 Lind Avenue, SW., Renton, Washington
98055-4056.
Discussion
On March 28, 1996, the FAA issued AD 96-07-13, amendment 39-9563
(61 FR 16379, April 15, 1996), applicable to all Lockheed Model L-1011-
385 series airplanes. That AD requires repetitive visual, x-ray, eddy
current, and ultrasonic inspections to detect fatigue cracking of
certain areas of the rear spar caps, web, skin, and certain fastener
holes; and repair or modification, if necessary. It also provides for
modification of the rear spar upper and lower caps between Inner Wing
Station (IWS) 228 and 346 as terminating action for the requirements of
the AD.
AD 96-07-13 was prompted by reports of fatigue cracking that
occurred in these areas. The requirements of that AD are intended to
ensure that fatigue cracking is detected and corrected in a timely
manner. Such cracking, if not corrected, could lead to rupture of the
rear spar and, consequently, result in extensive damage to the wing and
spillage of fuel.
Actions Since Issuance of Previous Rule
Since the issuance of AD 96-07-13, the FAA has received reports
indicating that fatigue cracks detected during inspections performed in
accordance with that AD had progressed to lengths greater than
predicted. One finding indicated that a crack apparently had grown
substantially during the repetitive inspection period. These new data
indicate that, in order to detect and correct the subject fatigue
cracking before it can progress to critical lengths, the currently
required inspections must be performed more frequently.
Additionally, the manufacturer has notified the FAA that the
modification of the rear spar upper and lower caps on Model L-1011-385-
3 airplanes, which was described in Part I of Lockheed Service Bulletin
093-57-203, Revision 4, dated March 27, 1995, has been superseded by a
web replacement that is described in Lockheed Service Bulletin 093-57-
215.
[[Page 15430]]
Explanation of Relevant Service Information
The FAA has reviewed and approved Lockheed Service Bulletin 093-57-
203, Revision 5, dated April 22, 1996, which describes procedures for
conducting repetitive inspections to detect fatigue cracking in the
inboard web periphery from IWS 346 to IWS 228. It recommends that the
inspections be repeated at shorter intervals than those recommended in
Revision 4 of this service bulletin (dated March 27, 1995). The shorter
intervals will ensure that cracking is detected in a more timely
manner.
Additionally, Revision 5 does not contain procedures for the
modification of the rear spar upper and lower caps for Model L-1011-
385-3 airplanes, which was contained in Revision 4. That modification
has been revised, and the procedures for it are now contained in
Lockheed L-1011 Service Bulletin 093-57-215, dated April 11, 1996.
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 96-07-13. It would continue to require
the same types of inspections to detect fatigue cracking of certain
areas of the rear spar caps, web, skin, and certain fastener holes; and
repair or modification, if necessary. However, except for the currently
required x-ray inspections, these inspections would be required to be
repeated at shorter intervals. These actions would be required to be
accomplished in accordance with Revision 5 of Lockheed Service Bulletin
093-57-203, described previously.
This new proposed AD would continue to provide for terminating
action for the repetitive inspections, as was provided in AD 96-07-13.
However, terminating action for Model L-1011-385-3 airplanes would be
required to be accomplished in accordance with the procedures specified
in Lockheed L-1011 Service Bulletin 093-57-215.
Cost Impact
There are approximately 236 Lockheed Model L-1011-385 series
airplanes of the affected design in the worldwide fleet. The FAA
estimates that 118 airplanes of U.S. registry would be affected by this
proposed AD.
The inspections that are proposed in this AD action would take
approximately 64 work hours per airplane to accomplish, at an average
labor rate of $60 per work hour. [This work hour estimate assumes that
X-ray inspections are done of both upper and lower caps, and that the
ultrasonic inspection indicates cracking in each of five bolt holes
(per wing), thus requiring subsequent bolt hole eddy current
inspections to confirm crack findings. The estimate includes
inspections of both wings.] Based on these figures, the cost impact on
U.S. operators of the proposed inspection requirements of this AD is
estimated to be $453,120, or $3,840 per airplane, per inspection cycle.
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 removing amendment 39-9563 (61 FR
16379, April 15, 1996), and by adding a new airworthiness directive
(AD), to read as follows:
Lockheed: Docket 96-NM-257-AD. Supersedes AD 96-07-13, Amendment 39-
9563.
Applicability: All Model L-1011-385-1, L-1011-385-3, L-1011-385-
1-14, and L-1011-385-1-15 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 request approval for an
alternative method of compliance in accordance with paragraph (c) 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 rupture of the rear spar due to the problems
associated with fatigue cracking, which could result in extensive
damage to the wing and fuel spillage, accomplish the following:
Note 2: The inspections and follow-on actions described in
Lockheed L-1011 Service Bulletin 093-57-203 include:
--repetitive X-ray (radiographic) inspections;
--repetitive eddy current surface scan inspections;
--bolt hole eddy current inspections at various locations;
--repetitive ultrasonic inspections in conjunction with eddy current
surface scan inspections (for certain airplanes); and
--repetitive low frequency eddy current ring probe inspections.
(a) For airplanes on which the inspections and follow-on actions
required by AD 96-07-13, amendment 39-9563, have been initiated
prior to the effective date of this AD: At the times specified in
Table I of Lockheed L-1011 Service Bulletin 093-57-203, Revision 4,
dated March 27, 1995; or within 6 months after May 15, 1996 (the
effective date of AD 96-07-13, amendment 39-9563), whichever occurs
later:
Perform initial inspections and various follow-on actions to
detect cracking in the areas specified in, at the times indicated
in, and in accordance with Lockheed L-1011 Service Bulletin 093-57-
203, Revision 4, dated March 27, 1995, or Revision 5, dated April
22, 1996.
[[Page 15431]]
(1) If no cracking is found, repeat the repetitive inspections
and follow-on actions in accordance with Table I of the Lockheed
service bulletin. As of the effective date of this AD, these actions
shall be repeated at the times specified only in accordance with
Table 1 of Revision 5 of the Lockheed service bulletins. To avoid
unnecessary grounding of airplanes that are currently being
inspected in accordance with the schedule specified in Revision 4 of
the Lockheed service bulletin, the next repeated action that is to
be accomplished after the effective date of this AD shall be
performed at the time specified in Table I of Revision 5 of the
Lockheed service bulletin, or within 30 days after the effective
date of this AD, whichever occurs later.
(2) If any finding of cracking is confirmed, prior to further
flight, accomplish paragraph (a)(2)(i), (a)(2)(ii), or (a)(2)(iii)
of this AD.
(i) Repair the cracked area in accordance with a method approved
by the Manager, Atlanta Aircraft Certification Office (ACO), FAA,
Small Airplane Directorate. Thereafter, perform the repetitive
inspections and follow-on actions as specified in paragraph (a)(1)
of this AD.
(ii) Repair the rear spar upper and lower caps between IWS 228
and 346 in accordance with the Lockheed Model L-1011 Structural
Repair Manual. Thereafter, perform the repetitive inspections and
follow-on actions required by paragraph (a)(1) of this AD. Or
(iii) Modify the rear spar upper and lower caps and web in
accordance with the applicable Lockheed service bulletin listed in
this paragraph, below. Accomplishment of the modification
constitutes terminating action for the requirements of this AD.
--Lockheed L-1011 Service Bulletin 093-57-184, Revision 7, dated
December 6, 1994, as amended by Change Notification 093-57-184, R7-
CN1, dated August 22, 1995; or
--Lockheed Service Bulletin 093-57-196, Revision 6, dated December
6, 1994, as amended by Change Notification 093-57-196, R6-CN1, dated
August 22, 1995; or
--Lockheed L-1011 Service Bulletin 093-57-215, dated April 11, 1996.
Modification of Model L-1011-385-3 airplanes must be accomplished in
accordance with this service bulletin.
Note 3: Accomplishment of the modification specified in
paragraph (a)(2)(iii) of this AD prior to the effective date of this
AD in accordance with the following Lockheed service bulletins, as
applicable, is considered to be in compliance with this paragraph:
Lockheed L-1011 Service Bulletin 093-57-184, Revision
6, dated October 28, 1991
Lockheed L-1011 Service Bulletin 093-57-184, Revision
7, dated December 6, 1994
Lockheed L-1011 Service Bulletin 093-57-196, Revision
5, dated October 28, 1991
Lockheed L-1011 Service Bulletin 093-57-196, Revision
6, dated December 6, 1994
(b) For airplanes on which the inspections and follow-on actions
required by AD 96-07-13, amendment 39-9563, have not been initiated
prior to the effective date of this AD: At the times specified in
Table I of Lockheed L-1011 Service Bulletin 093-57-203, Revision 5,
dated April 22, 1996; or within 30 days after the effective date of
this AD; whichever occurs later: Perform initial inspections and
various follow-on actions to detect cracking in the areas specified
in, at the times indicated in, and in accordance with Lockheed L-
1011 Service Bulletin 093-57-203, Revision 5, dated April 22, 1996.
(1) If no cracking is found: Repeat the inspections and follow-
on actions in accordance with the times specified in Table I of the
Lockheed service bulletin.
(2) If any finding of cracking is confirmed: Prior to further
flight, accomplish either paragraph (b)(2)(i), (b)(2)(ii), or
(b)(2)(iii) of this AD.
(i) Repair the cracked area in accordance with a method approved
by the Manager, Atlanta Aircraft Certification Office (ACO), FAA,
Small Airplane Directorate. Thereafter, perform the repetitive
inspections and follow-on actions at the times specified in Table 1
of the Lockheed service bulletin. Or
(ii) Repair the rear spar upper and lower caps between IWS 228
and 346 in accordance with the Lockheed Model L-1011 Structural
Repair Manual. Thereafter, perform the repetitive inspections and
follow-on actions at the times specified in Table 1 of the Lockheed
service bulletin. Or
(iii) Modify the rear spar upper and lower caps and web in
accordance with paragraph (a)(2)(iii) of this AD.
(c) 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 4: Information concerning the existence of approved
alternative methods of compliance with this AD, if any, may be
obtained from the Atlanta ACO.
(d) 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 March 25, 1997.
Darrell M. Pederson,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 97-8125 Filed 3-31-97; 8:45 am]
BILLING CODE 4910-13-U
