[Federal Register Volume 61, Number 73 (Monday, April 15, 1996)]
[Rules and Regulations]
[Pages 16379-16382]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 96-8584]
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DEPARTMENT OF TRANSPORTATION
14 CFR Part 39
[Docket No. 95-NM-88-AD; Amendment 39-9563; AD 96-07-13]
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 certain areas
of the rear spar caps, web, skin, and certain fastener holes; and
repair or modification, if necessary. That AD was prompted by reports
of fatigue cracks in the caps, web, and skin of the wing rear spar
inboard of inner wing station 346. The actions specified by that AD are
intended to prevent rupture of the rear spar, which could result in
extensive damage to the wing and fuel spillage. This amendment adds
various improved inspections and follow-on actions, and requires that
the initial inspections be accomplished at reduced thresholds.
DATES: Effective May 15, 1996.
The incorporation by reference of certain publications, as listed
in the regulations, is approved by the Director of the Federal Register
as of May 15, 1996.
The incorporation by reference of certain other publications listed
in the regulations was approved previously by the Director of the
Federal Register as of November 24, 1993 (58 FR 54947, October 25,
1993).
ADDRESSES: The service information referenced in this AD 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
[[Page 16380]]
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, Campus Building, 1701 Columbia Avenue, Suite 2-
160, College Park, 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,
Flight Test Branch, ACE-116A, FAA, Small Airplane Directorate, Atlanta
Aircraft Certification Office, Campus Building, 1701 Columbia Avenue,
Suite 2-160, College Park, Georgia 30337-2748; telephone (404) 305-
7367; fax (404) 305-7348.
SUPPLEMENTARY INFORMATION: A proposal to amend part 39 of the Federal
Aviation Regulations (14 CFR part 39) by superseding AD 93-17-10,
amendment 39-8681 (58 FR 54947, October 25, 1993), which is applicable
to all Lockheed Model L-1011-385 series airplanes, was published in the
Federal Register on December 18, 1995 (60 FR 65032). The action
proposed to continue to require inspections to detect cracking of
certain areas of the rear spar caps, web, skin, and certain fastener
holes; and repair or modification, if necessary. The action proposed to
add various improved inspections and follow-on actions, and to require
that the initial inspections be accomplished at reduced thresholds.
Interested persons have been afforded an opportunity to participate
in the making of this amendment. Due consideration has been given to
the comments received.
Four commenters support the proposed rule.
Two commenters request that the proposed rule be issued without
change, but that the FAA issue subsequent rulemaking to require a
reduced repetitive inspection interval. One commenter expresses concern
that analytical data and service experience do not support the
repetitive inspection interval of 2,000 flight cycles recommended in
Revision 4 of Lockheed L-1011 Service Bulletin 093-57-203. The
commenter states that two inspection opportunities should be provided
to detect cracks prior to the time at which those cracks reach critical
flaw size; the proposed inspection interval will not allow two
inspections to be conducted during the period between the point at
which the crack becomes detectable using the specified inspection
methods and the point at which the crack reaches critical length. The
second commenter, the manufacturer, indicates that analysis of an
incident that occurred subsequent to the issuance of Revision 4 of the
service bulletin revealed a failure mode that had not been evaluated
fully. The manufacturer advises that it intends to revise the service
bulletin to recommend that the repetitive inspection intervals be
reduced and to change the inspection requirements to ensure timely
detection of cracks.
The FAA concurs with the commenters' request. The FAA may consider
additional rulemaking to address the issues discussed by the commenters
once an acceptable inspection interval and other inspections have been
identified.
One commenter requests that the Summary section of the preamble to
the proposed rule be revised to clarify that fatigue cracks were found
in the web and skin, as well as the caps, of the wing rear spar inboard
of inner wing station 346. The FAA concurs, and has made this change to
the pertinent language in the preamble to this final rule.
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 previously
described. The FAA has determined that these changes will neither
increase the economic burden on any operator nor increase the scope of
the AD.
There are approximately 236 Model L-1011-385 series airplanes of
the affected design in the worldwide fleet. The FAA estimates that 118
airplanes of U.S. registry will be affected by this proposed AD.
The actions that are currently required by AD 93-17-10 take
approximately 21 work hours per airplane to accomplish, at an average
labor rate of $60 per work hour. Based on these figures, the cost
impact on U.S. operators of the actions currently required is estimated
to be $148,680, or $1,260 per airplane.
The new actions that are required by this new AD will 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 new requirements of this AD is estimated to be
$453,120, or $3,840 per airplane.
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.
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 39-8681 (58 FR
54947, October 25, 1993), and by adding
[[Page 16381]]
a new airworthiness directive (AD), amendment 39-9563, to read as
follows:
96-07-13 Lockheed Aeronautical Systems Company: Amendment 39-9563.
Docket 95-NM-88-AD. Supersedes AD 93-17-10, Amendment 39-8681.
Applicability: All Model L-1011-385-1, L-1011-385-1-14, L-1011-
385-1-15, and L-1011-385-3 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 (d) 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.
Note 2: Paragraphs (a)(1) and (b) of this AD restate the
requirement for repetitive inspections and follow-on actions
contained in paragraphs (a) and (b) of AD 93-17-10. Therefore, for
operators who have previously accomplished at least the initial
inspection in accordance with AD 93-17-10, paragraphs (a)(1) and (b)
of this AD require that the next scheduled inspection be performed
within 2,000 flight cycles after the last inspection performed in
accordance with paragraphs (a) and (b) of AD 93-17-10.
To prevent rupture of the rear spar, which could result in
extensive damage to the wing and fuel spillage, accomplish the
following:
(a) Perform inspections and various follow-on actions to detect
cracking in the areas specified in and in accordance with Part II of
the Accomplishment Instructions of the Lockheed service documents
listed below. After the effective date of this AD, the inspections
and follow-on actions shall be performed only at the times specified
in and in accordance with Revision 4 of Lockheed L-1011 Service
Bulletin 093-57-203. [The inspections and follow-on actions 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.]
Lockheed L-1011 Service Bulletin 093-57-203, Revision
3, dated October 28, 1991; or
Lockheed L-1011 Service Bulletin 093-57-203, Revision
3, dated October 28, 1991, as amended by Lockheed L-1011 Service
Bulletin Change Notification 093-57-203, R3-CN1, dated June 22,
1992; or
Lockheed L-1011 Service Bulletin 093-57-203, Revision
4, dated March 27, 1995.
(1) For airplanes on which the inspections required by AD 93-17-
10, amendment 39-8681, have been initiated prior to the effective
date of this AD: Perform the inspections and follow-on actions at
the times specified in Table I of Lockheed L-1011 Service Bulletin
Change Notification 093-57-203, R3-CN1, dated June 22, 1992, or
within 6 months after November 24, 1993 (the effective date of AD
93-17-10, amendment 39-8681), whichever occurs later.
Note 3: As allowed by the phrase, ``unless accomplished
previously,'' if the inspections and follow-on actions required by
this paragraph were conducted prior to November 24, 1993, in
accordance with Lockheed L-1011 Service Bulletin 093-57-203,
Revision 2, dated January 25, 1991, those inspections need not be
repeated.
(2) For airplanes on which the inspections required by AD 93-17-
10, amendment 39-8681, have not been initiated prior to the
effective date of this AD: Perform the inspections and follow-on
actions 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 the effective date of this AD, whichever occurs later.
(b) If no cracking is found, perform the repetitive inspections
and follow-on actions specified in the Accomplishment Instructions
of the Lockheed service documents listed below thereafter at
intervals not to exceed 2,000 flight cycles. After the effective
date of this AD, the inspections and follow-on actions shall be
performed only in accordance with Revision 4 of Lockheed L-1011
Service Bulletin 093-57-203.
Lockheed L-1011 Service Bulletin 093-57-203, Revision
3, dated October 28, 1991; or
Lockheed L-1011 Service Bulletin 093-57-203, Revision
3, dated October 28, 1991, as amended by Lockheed L-1011 Service
Bulletin Change Notification 093-57-203, R3-CN1, dated June 22,
1992; or
Lockheed L-1011 Service Bulletin 093-57-203, Revision
4, dated March 27, 1995;
(c) If any finding of cracking is confirmed, prior to further
flight, accomplish paragraph (c)(1), (c)(2), or (c)(3) of this AD.
(1) 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 required by paragraph (b) of this
AD; or
(2) 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 (b) of this AD; or
(3) Modify the rear spar upper and lower caps between IWS 228
and 346 in accordance with the Lockheed service bulletins listed
below, as applicable. 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 L-1011 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 093-57-203, Revision
4, dated March 27, 1995.
Note 4: Accomplishment of the modification specified in
paragraph (c)(3) 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;
Lockheed L-1011 Service Bulletin 093-57-203, Revision
3, dated October 28, 1991; or
Lockheed L-1011 Service Bulletin 093-57-203, Revision
3, dated October 28, 1991, as amended by Change Notification 093-57-
203, R3-CN1, dated June 22, 1992.
(d) 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 5: Information concerning the existence of approved
alternative methods of compliance with this AD, if any, may be
obtained from the Atlanta ACO.
(e) 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.
(f) Certain actions shall be done in accordance with Lockheed L-
1011 Service Bulletin 093-57-203, Revision 4, dated March 27, 1995.
The modification, if accomplished, shall be done in accordance with
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 L-1011 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. The
incorporation by reference of these documents was approved by the
Director of the Federal Register in accordance with 5 U.S.C. 552(a)
and 1 CFR part 51. Certain other actions shall be done in accordance
with Lockheed L-1011 Service Bulletin 093-57-203, Revision 3, dated
October 28, 1991; and Lockheed L-1011 Service Bulletin 093-57-203,
Revision 3, dated October 28, 1991, as amended by Lockheed L-1011
Service Bulletin Change Notification 093-57-203, R3-CN1, dated June
22, 1992. The incorporation by reference of these documents was
approved previously by the Director of the Federal Register, in
accordance with 5 U.S.C. 552(a) and 1 CFR
[[Page 16382]]
part 5,1 as of November 24, 1993 (58 FR 54947, October 25, 1993).
Copies may be obtained from Lockheed Aeronautical Systems Support
Company, Field Support Department, Dept. 693, Zone 0755, 2251 Lake
Park Drive, Smyrna, Georgia 30080. 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, Campus Building, 1701 Columbia
Avenue, Suite 2-160, College Park, Georgia; or at the Office of the
Federal Register, 800 North Capitol Street, NW., suite 700,
Washington, DC.
(g) This amendment becomes effective on May 15, 1996.
Issued in Renton, Washington, on March 28, 1996.
Bill R. Boxwell,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 96-8584 Filed 4-12-96; 8:45 am]
BILLING CODE 4910-13-P
