[Federal Register Volume 64, Number 120 (Wednesday, June 23, 1999)]
[Rules and Regulations]
[Pages 33386-33390]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 99-15779]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. 97-NM-11-AD; Amendment 39-11202; AD 99-13-08]
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 and other
discrepancies of certain web-to-cap fasteners of the rear spar between
inner wing stations 310 and 343, and of the web area around those
fasteners; and various follow-on actions. That AD also provides for an
optional modification, which, if accomplished, would defer the
initiation of the inspections for a certain period of time. This
amendment requires accomplishment of the previously optional
modification. This amendment is prompted by an FAA determination that
the optional terminating modification specified in the existing AD must
be accomplished within a specified period of time to ensure an
acceptable level of safety of the affected fleet. The actions specified
by this AD are intended to prevent fatigue cracking in the web of the
rear spar of the wing, which could result in failure of the rear spar
of the wing and consequent fuel spillage.
DATES: Effective July 28, 1999.
The incorporation by reference of Lockheed L-1011 Service Bulletin
093-57-218, dated April 11, 1996, as listed in the regulations, was
approved previously by the Director of the Federal Register as of June
27, 1996 (61 FR 29642, June 12, 1996).
The incorporation by reference of certain other publications, as
listed in the regulations, is approved by the Director of the Federal
Register as of July 28, 1999.
ADDRESSES: The service information referenced in this AD may be
obtained from Lockheed Martin Aircraft & Logistics Center, 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 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 30337-2748;
telephone (770) 703-6063; fax (770) 703-6097.
SUPPLEMENTARY INFORMATION: A proposal to amend part 39 of the Federal
[[Page 33387]]
Aviation Regulations (14 CFR part 39) by superseding AD 96-12-24,
amendment 39-9667 (61 FR 29642, June 12, 1996), which is applicable to
all Lockheed Model L-1011-385 series airplanes, was published in the
Federal Register on November 25, 1997 (62 FR 62728). The action
proposed to continue to require inspections to detect cracking and
other discrepancies of certain web-to-cap fasteners of the rear spar
between inner wing stations 310 and 343, and of the web area around
those fasteners; and various follow-on actions. That action also
proposed to require accomplishment of a previously optional
modification.
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 Proposal
One commenter supports the proposed rule.
Request To Clarify the Inspection Requirements
One commenter requests clarification of the subsequent inspections
required by the proposed AD. The commenter states that the proposed AD
does not clearly address the subsequent inspection program for Model L-
1011-385-3 series airplanes that have accomplished the rear spar
modification for extensive cracking ``after June 27, 1996,'' because
paragraph (a)(2) of the proposed AD only addresses spar replacements
accomplished ``prior to June 27, 1996.''
The FAA points out that the inspection thresholds in Table I of
Lockheed Service Bulletin 093-57-218, Revision 1, dated September 9,
1996 (which is referenced in the final rule as the appropriate source
of service information), are calculated from the date of accomplishment
of Lockheed Service Bulletin 093-57-215, dated April 11, 1996. In
addition, the FAA considers that paragraph (e)(2) of the final rule
adequately addresses the inspection requirements for operators that
have accomplished the modification in accordance with Service Bulletin
093-57-215. No change has been made to paragraph (a)(2) of the final
rule.
Request for Additional Inspections and a Reduced Inspection
Threshold
One commenter requests revising the proposed AD to include
additional inspections for detecting cracks that originate in the
fastener holes, and to shorten the inspection thresholds after
accomplishment of the cold working modification. The commenter adds
that it recommends accomplishment of the modification as required by
the proposed AD; however, the commenter does not consider that the
modification should be used for complete reliance for crack prevention.
Following accomplishment of the modification, the commenter recommends
that certain other inspections of the wing rear spar web and upper cap
be added to the inspection requirements of the proposed AD. The
commenter suggests adding surface scan inspections using high frequency
eddy current techniques, and ring probe inspections using low frequency
eddy current techniques. The commenter also recommends that, instead of
accomplishing the inspections at 5,000 landings, the inspections be
accomplished at 500 flight cycles following the cold working
modification.
The commenter states that its recommendations are based on its
service experience and a damage tolerance assessment (DTA). The
commenter also states that, after modifying its entire fleet of Model
L-1011-385-3 series airplanes in accordance with paragraph (d) of the
proposed AD, subsequent cracking was found before 5,000 landings. The
commenter adds that its service experience indicates that new or
recurring cracks occur within 500 to 1,000 flight cycles after repair
of the upper spar cap. In addition, half-crack lengths of approximately
0.25 inch were found during subsequent inspections, and a DTA of the
area indicates that inspections at 500 flight cycles are required to
ensure aircraft safety, regardless of the cold working condition.
The FAA does not concur that additional inspections should be
included in the final rule, or that the inspection threshold of 5,000
landings, as required by paragraphs (d) and (e)(1) of the proposed AD,
should be reduced to 500 landings. The FAA considers it is likely that
other factors induced the early cracking found in the operator's
airplane, and that the 5,000-flight-cycle threshold required by the
proposed AD is an adequate inspection threshold after accomplishment of
the fastener hole cold working. The FAA points out that it will
continue to monitor service findings of modified airplanes and may
revise the inspection requirements in the future, if necessary.
However, no changes were made to the inspection thresholds required by
paragraph (d) or (e)(1) of the final rule.
Explanation of Changes Made to This Final Rule
The notice of proposed rulemaking (NPRM) references Lockheed
Service Bulletin 093-57-212, dated November 14, 1994, as amended by
Change Notification CN1, dated September 27, 1995, as an appropriate
source of service information for accomplishment of the modifications
specified in paragraphs (f)(1) and (f)(2) of the NPRM. The FAA finds
that the procedures in Service Bulletin 093-57-212 are no longer
necessary because the procedures included in the other service
bulletins cited in those paragraphs are adequate for accomplishment of
the actions required by this AD. The references to that service
bulletin have been removed from the final rule.
Although the NPRM includes references to certain Change
Notifications for a number of service bulletins, the FAA has determined
that it is unnecessary to include those references in the final rule.
The FAA points out that the Change Notifications did not include any
substantive changes to the service bulletins, and that such change
notifications included only minor editorial changes or clarification of
certain data. The FAA has determined that the service bulletins
referenced in the final rule include all of the procedures necessary
for accomplishment of the actions required by this AD. In light of
this, references to the Change Notifications were deleted from the
final rule.
Although the NPRM did not include references to certain earlier
revision levels of Lockheed Service Bulletins 093-57-184, 093-57-196,
and 093-57-203, the FAA has determined that references to those earlier
revision levels should be included in the final rule to give credit to
any operator that may have accomplished the modification previously in
accordance with those service bulletins. In light of this, the FAA has
included references to those earlier service bulletins in NOTE 2, NOTE
3, and NOTE 4 of this AD. The FAA considers that the service bulletins
referenced in those notes are adequate for specifying the procedures
necessary for accomplishment of the actions required by this AD.
The FAA has added Lockheed Service Bulletin 093-57-203, Revision 4,
dated March 27, 1995, to paragraph (e)(1) of this AD as an additional
reference for the accomplishment of the rear spar modification.
In paragraph (g) of this AD, the FAA has added the word
``discrepant'' preceding the word ``fasteners'' in the parenthetical
phrase. This word was
[[Page 33388]]
added to clarify that one of the conditions to be identified during the
required modification is for ``discrepant fasteners'' rather than just
``fasteners.''
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 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.
Cost Impact
There are approximately 235 Lockheed Model L-1011-385 series
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 actions that are currently required by AD 96-12-24, and
retained in this AD, take approximately 13 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 currently required actions on
U.S. operators is estimated to be $91,260, or $780 per airplane.
The actions that are required by this new AD will take
approximately 100 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 new requirements of this AD on U.S. operators is
estimated to be $702,000, or $6,000 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.
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 39-9667 (61 FR
29642, June 12, 1996), and by adding a new airworthiness directive
(AD), amendment 39-11202, to read as follows:
99-13-08 Lockheed: Amendment 39-11202. Docket 97-NM-11-AD.
Supersedes AD 96-12-24, Amendment 39-9667.
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 (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 fatigue cracking on the web of the rear spar of the
wing, which could result in failure of the rear spar of the wing and
consequent fuel spillage, accomplish the following:
Restatement of Actions Required by AD 96-12-24, Amendment 39-9667
(a) Perform a visual inspection to detect signs of cracking and
other discrepancies (i.e., corrosion, fastener looseness, nicks,
scratches, or other surface damage) of the web-to-cap fasteners of
the rear spar between inner wing stations (IWS) 310 and 343, as
specified in Figure 2 of Lockheed Service Bulletin 093-57-218, dated
April 11, 1996, or Revision 1, dated September 9, 1996; and of the
web area around those fasteners; in accordance with Part I of the
Accomplishment Instructions of that service bulletin. Perform the
inspection at the applicable time specified in paragraph (a)(1) or
(a)(2) of this AD.
(1) Except as provided by paragraph (a)(2) of this AD: Perform
the initial inspection prior to the accumulation of the number of
landings specified as the ``inspection threshold'' in Table I of
Lockheed Service Bulletin 093-57-218, dated April 11, 1996, or
Revision 1, dated September 9, 1996, or within 10 days after June
27, 1996 (the effective date of AD 96-12-24, amendment 39-9667),
whichever occurs later.
(2) For airplanes on which the wing rear spar has been modified
prior to June 27, 1996, in accordance with one of the Lockheed
service bulletins listed in paragraph (a)(2)(ii) of this AD,
accomplish the inspection as follows:
(i) Perform the initial inspection prior to the accumulation of
the number of landings specified as the ``inspection threshold'' in
Table I of Lockheed Service Bulletin 093-57-218, dated April 11,
1996, or Revision 1, dated September 9, 1996, calculated from the
time the wing rear spar was modified (rather than from the date of
manufacture of the airplane), or within 10 days after June 27, 1996,
whichever occurs later.
(ii) This paragraph applies to airplanes on which the wing rear
spar has been modified in accordance with one of the following
service bulletins:
Lockheed Service Bulletin 093-57-184, Revision 6, dated
October 28, 1991, or Revision 7, dated December 6, 1994; or
Lockheed Service Bulletin 093-57-196, Revision 5, dated
October 28, 1991, or Revision 6, dated December 6, 1994; or
Lockheed Service Bulletin 093-57-203, Revision 3, dated
October 28, 1991, or Revision 4, dated March 27, 1995; or
Lockheed Service Bulletin 093-57-215, dated April 11,
1996.
(b) If no sign of cracking or other discrepancy is found during
the inspection required by paragraph (a) of this AD, repeat that
inspection thereafter at intervals not to exceed the number of
landings specified as the ``repeat visual inspection interval'' in
Table I of Lockheed Service Bulletin 093-57-218, dated April 11,
1996, or Revision 1, dated September 9, 1996.
(c) If any sign of cracking is found during an inspection
required by paragraph (a) or (b) of this AD, prior to further
flight, perform either eddy current surface scan inspections, or
bolt hole eddy current inspections, as appropriate, to confirm
cracking, in accordance with Lockheed Service Bulletin 093-57-218,
dated April 11, 1996, or Revision 1, dated September 9, 1996.
[[Page 33389]]
(1) If no cracking is confirmed, repeat the inspection specified
in paragraph (a) of this AD at intervals not to exceed the number of
landings specified as the ``repeat visual inspection interval'' in
Table I of the service bulletin.
(2) If any cracking is confirmed, prior to further flight,
repair it in accordance with the service bulletin.
New Requirements of This AD
Modification
(d) Except as provided by paragraph (e) or (f) of this AD, as
applicable: Within 12 months after the effective date of this AD,
modify the web-to-cap fastener holes of the rear spar between IWS
299 and IWS 343 in accordance with Part II of the Accomplishment
Instructions of Lockheed Service Bulletin 093-57-218, Revision 1,
dated September 9, 1996. Within 5,000 landings following
accomplishment of the modification, perform the visual inspection
required by paragraph (a) of this AD. Thereafter, repeat that
inspection at intervals not to exceed the number of landings
specified as the ``repeat visual inspection interval'' in Table I of
Lockheed Service Bulletin 093-57-218, Revision 1, dated September 9,
1996.
(e) For Model L-1011-385-3 series airplanes: Accomplishment of
the modification specified in paragraph (e)(1) or (e)(2) of this AD,
within 12 months after the effective date of this AD, constitutes an
acceptable alternative to the modification specified in paragraph
(d) of this AD.
(1) Modify the upper and lower caps of the rear spar between IWS
228 and IWS 346 in accordance with Part I of the Accomplishment
Instructions of Lockheed Service Bulletin 093-57-203, Revision 3,
dated October 28, 1991; or Revision 4, dated March 27, 1995. Within
5,000 landings following accomplishment of the modification, perform
the visual inspection required by paragraph (a) of this AD.
Thereafter, repeat that inspection at intervals not to exceed the
number of landings specified as the ``repeat visual inspection
interval'' in Table I of Lockheed Service Bulletin 093-57-218,
Revision 1, dated September 9, 1996. Or
(2) Modify the left and right wing rear spars in accordance with
the Accomplishment Instructions of Lockheed Service Bulletin 093-57-
215, dated April 11, 1996. Within the thresholds specified in Table
I of Lockheed Service Bulletin 093-57-218, Revision 1, dated
September 9, 1996 (calculated from the date of installation of
Lockheed Service Bulletin 093-57-215, dated April 11, 1996), perform
the visual inspection required by paragraph (a) of this AD.
Thereafter, repeat that inspection at intervals not to exceed the
number of landings specified as the ``repeat visual inspection
interval'' in Table I of Lockheed Service Bulletin 093-57-218,
Revision 1, dated September 9, 1996.
Note 2: Accomplishment of the modification of the upper and
lower caps of the rear spar between IWS 228 and IWS 346, in
accordance with the Accomplishment Instructions of Lockheed Service
Bulletin 093-57-203, dated July 25, 1988, Revision 1, dated August
11, 1989, or Revision 2, dated January 25, 1991, is considered
acceptable for compliance with the modification specified in
paragraph (e)(1) of this amendment.
(f) For Model L-1011-385-1 series airplanes: Accomplishment of
the modification specified in paragraph (f)(1) or (f)(2) of this AD,
within 12 months after the effective date of this AD, constitutes an
acceptable alternative to the modification specified in paragraph
(d) of this AD.
(1) Modify the inboard and outboard rear spars in accordance
with the Accomplishment Instructions of Lockheed Service Bulletin
093-57-184, Revision 6, dated October 28, 1991; or Revision 7, dated
December 6, 1994. Within the thresholds specified in Table I of
Lockheed Service Bulletin 093-57-218, Revision 1, dated September 9,
1996 (calculated from the date of installation of Lockheed Service
Bulletin 093-57-184, Revision 6, dated October 28, 1991, or Revision
7, dated December 6, 1994), perform the visual inspection required
by paragraph (a) of this AD. Thereafter, repeat that inspection at
intervals not to exceed the number of landings specified as the
``repeat visual inspection interval'' in Table I of Lockheed Service
Bulletin 093-57-218, Revision 1, dated September 9, 1996. Or
(2) Modify the inboard and outboard rear spars in accordance
with the Accomplishment Instructions of Lockheed Service Bulletin
093-57-196, Revision 5, dated October 28, 1991; or Revision 6, dated
December 6, 1994. Within the thresholds specified in Table I of
Lockheed Service Bulletin 093-57-218, Revision 1, dated September 9,
1996 (calculated from the date of installation of Lockheed Service
Bulletin 093-57-196, Revision 5, dated October 28, 1991, or Revision
6, dated December 6, 1994), perform the visual inspection required
by paragraph (a) of this AD. Thereafter, repeat that inspection at
intervals not to exceed the number of landings specified as the
``repeat visual inspection interval'' in Table I of Lockheed Service
Bulletin 093-57-218, Revision 1, dated September 9, 1996.
Note 3: Accomplishment of the modification of the inboard and
outboard rear spars, in accordance with the Accomplishment
Instructions of Lockheed Service Bulletin 093-57-184, Revision 2,
dated October 12, 1988; Revision 3, dated August 11, 1989, Revision
4, dated May 16, 1990; or Revision 5, dated May 23, 1990, is
considered acceptable for compliance with the modification specified
in paragraph (f)(1) of this amendment.
Note 4: Accomplishment of the modification of the inboard and
outboard rear spars, in accordance with the Accomplishment
Instructions of Lockheed Service Bulletin 093-57-196, Revision 1,
dated October 25, 1988; Revision 2, dated July 31, 1989; Revision 3,
dated March 7, 1990; or Revision 4, dated July 1, 1991, is
considered acceptable for compliance with the modification specified
in paragraph (f)(2) of this amendment.
(g) If any condition (i.e., number of discrepant fasteners per
stiffener bay, or cracking) is identified during the accomplishment
of the modification specified in Lockheed Service Bulletin 093-57-
218, Revision 1, dated September 9, 1996, and that condition exceeds
the limits specified in paragraph B.(3) of Part II of the
Accomplishment Instructions of the service bulletin, prior to
further flight, repair in accordance with a method approved by the
Manager, Atlanta Aircraft Certification Office (ACO), FAA, Small
Airplane Directorate.
Alternative Method 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 96-12-24, amendment 39-9667, are approved as
alternative methods of compliance with paragraph (d) of this AD.
Note 5: 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 paragraph (g) of this AD, the actions
shall be done in accordance with the following service bulletins, as
applicable:
Lockheed Service Bulletin 093-57-184, Revision 6, dated
October 28, 1991; or Lockheed Service Bulletin 093-57-184, Revision
7, dated December 6, 1994;
Lockheed Service Bulletin 093-57-196, Revision 5, dated
October 28, 1991; or Lockheed Service Bulletin 093-57-196, Revision
6, dated December 6, 1994;
Lockheed Service Bulletin 093-57-203, Revision 3, dated
October 28, 1991; or Lockheed Service Bulletin 093-57-203, Revision
4, dated March 27, 1995;
Lockheed Service Bulletin 093-57-215, dated April 11,
1996; and
Lockheed Service Bulletin 093-57-218, dated April 11,
1996; or Lockheed Service Bulletin 093-57-218, Revision 1, dated
September 9, 1996.
Revision 1 of Lockheed Service Bulletin 093-57-218 contains the
following list of effective pages:
------------------------------------------------------------------------
Revision level
Page No. shown on page Date shown on page
------------------------------------------------------------------------
1, 2, 4-9, 13-18............... 1.............. Sept. 9, 1996.
3, 10-12, 19................... Original....... Apr. 11, 1996.
------------------------------------------------------------------------
(1) The incorporation by reference of Lockheed Service Bulletin
093-57-218, dated April 11, 1996, was approved previously by the
Director of the Federal
[[Page 33390]]
Register as of June 27, 1996 (61 FR 29642, June 12, 1996).
(2) The incorporation by reference of the remainder of the
service bulletins listed above is approved by the Director of the
Federal Register in accordance with 5 U.S.C. 552(a) and 1 CFR part
51.
(3) Copies may be obtained from Lockheed Martin Aircraft &
Logistics Center, 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 July 28, 1999.
Issued in Renton, Washington, on June 15, 1999.
Dorenda D. Baker,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 99-15779 Filed 6-22-99; 8:45 am]
BILLING CODE 4910-13-U
