[Federal Register Volume 64, Number 215 (Monday, November 8, 1999)]
[Proposed Rules]
[Pages 60750-60753]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 99-29180]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 99-NM-252-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 to revise 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 station (IWS) 310 and IWS 343, and of the web area 
around those fasteners; various follow-on actions; and modification of 
the web-to-cap fastener holes of the rear spar between IWS 299 and IWS 
343, which, when accomplished, defers the initiation of the inspections 
for a certain period of time. The actions specified by that 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. This action would, for certain airplanes, 
extend the compliance time for the modification of the web-to-cap 
fastener holes, and would eliminate references to modification of the 
outboard spar.

DATES: Comments must be received by December 23, 1999.

ADDRESSES: Submit comments in triplicate to the Federal Aviation 
Administration (FAA), Transport Airplane Directorate, ANM-114, 
Attention: Rules Docket No. 99-NM-252-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 30337-2748; 
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 99-NM-252-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. 99-NM-252-AD, 1601 Lind Avenue, SW., Renton, Washington 
98055-4056.

Discussion

    On June 15, 1999, the FAA issued AD 99-13-08, amendment 39-11202 
(64 FR 33386, June 23, 1999), applicable to all Lockheed Model L-1011-
385 series airplanes, to require inspections to detect cracking and 
other discrepancies of certain web-to-cap fasteners of the rear spar 
between inner wing station (IWS) 310 and IWS 343, and of the web area 
around those fasteners; various follow-on actions; and modification of 
the web-to-cap fastener holes of the rear spar between IWS 299 and IWS 
343, which, when accomplished, defers the initiation of the inspections 
for a certain period of time. That action was prompted by an FAA 
determination that a modification of certain web-to-cap fastener holes 
must be accomplished within a specified period of time to ensure an 
acceptable level of safety of the affected fleet. The requirements of 
that 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.

Actions Since Issuance of Previous Rule

    Since the issuance of that AD, the FAA has determined that a 
reference to Table 1 of Lockheed Service Bulletin 093-57-218, Revision 
1, dated September 9, 1996, which contains appropriate thresholds for 
accomplishment of the modification of the web-to-cap fastener holes, 
was inadvertently omitted from paragraph (d) of AD 99-13-08. For 
certain airplanes, this omission results in a shorter compliance time 
for accomplishing the modification than what was recommended in 
Lockheed Service Bulletin 093-57-218, Revision 1. The FAA finds that 
such a short compliance time is unnecessarily restrictive, and that it 
is necessary to

[[Page 60751]]

revise the existing AD to increase the inspection threshold to that 
recommended by the manufacturer.
    In addition, since the issuance of AD 99-13-08, the FAA has 
determined that the text of paragraph (f) of that AD [which describes 
an acceptable alternative, for certain airplanes, to accomplishment of 
paragraph (d) of that AD that also will defer the initiation of 
inspections for a certain period of time] specifies certain areas that 
do not, for the purposes of this AD, require modification. Paragraphs 
(f)(1) and (f)(2), as well as Notes 3 and 4, of the existing AD specify 
modification of the inboard and outboard rear spars. The FAA has 
previously determined that modification of the outboard rear spars is 
not necessary, and the service bulletins referenced in these sections 
do not describe procedures for modification of the outboard rear spars. 
Therefore, the FAA finds that, in order to alleviate any unnecessary 
burden on operators of the subject airplanes who elect to accomplish 
this option to attain compliance, and to make the requirements of the 
AD consistent with the procedures specified in the service bulletins 
referenced, it is necessary to revise paragraphs (f)(1) and (f)(2) and 
Notes 3 and 4 to eliminate reference to the outboard rear spar.

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 revise AD 99-13-08 to continue to require inspections 
to detect cracking and other discrepancies of certain web-to-cap 
fasteners of the rear spar between IWS 310 and IWS 343, and of the web 
area around those fasteners; various follow-on actions; and 
modification of the web-to-cap fastener holes of the rear spar between 
IWS 299 and IWS 343, which, when accomplished, defers the initiation of 
the inspections for a certain period of time. This action proposes to 
extend the compliance time for the modification of the web-to-cap 
fastener holes for certain airplanes, and to eliminate references to 
modification of the outboard spar. The actions would continue to be 
required to be accomplished in accordance with the service bulletins 
described previously in AD 99-13-08.

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 would be affected by this 
proposed AD. The proposed requirements of this AD would not add any new 
additional economic burden on affected operators. Also, because the 
existing AD states the cost impact only for the required modification 
and not for the acceptable alternatives that were provided for certain 
airplanes, no change to the cost impact information is necessary. The 
current costs associated with this amendment are reiterated in their 
entirety (as follows) for the convenience of affected operators:
    The inspections that are currently required by AD 99-13-08 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 inspections on U.S. operators is 
estimated to be $91,260, or $780 per airplane, per inspection cycle.
    The modification that is currently required by AD 99-13-08 takes 
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 currently required modification 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 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 39-11202 (64 FR 
33386, June 23, 1999), and by adding a new airworthiness directive 
(AD), to read as follows:

Lockheed: Docket 99-NM-252-AD. Revises AD 99-13-08, Amendment 39-
11202.

    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.

Restatement of Actions Required by AD 99-13-08, Amendment 39-11202

Inspections

    (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 station (IWS) 310 and IWS 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

[[Page 60752]]

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 was 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.

Repetitive Inspections

    (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.

Corrective Actions

    (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.
    (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.

Modification

    (d) Except as provided by paragraph (e) or (f) of this AD, as 
applicable: Prior to the accumulation of the number of landings 
specified as the threshold in Table 1 of Lockheed Service Bulletin 
093-57-218, Revision 1, dated September 9, 1996; or within 12 months 
after July 28, 1999 (the effective date of AD 99-13-08, amendment 
39-11202); whichever occurs later; 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 July 28, 1999, 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 July 28, 1999, constitutes an acceptable 
alternative to the modification specified in paragraph (d) of this 
AD.
    (1) Modify the inboard 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 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 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 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

[[Page 60753]]

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, or AD 99-13-08, 
amendment 39-11202, 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.

    Issued in Renton, Washington, on November 2, 1999.
D.L. Riggin,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 99-29180 Filed 11-5-99; 8:45 am]
BILLING CODE 4910-13-P