AD Amdt-39-10526

[Federal Register Volume 63, Number 94 (Friday, May 15, 1998)]
[Rules and Regulations]
[Pages 26966-26968]
From the Federal Register Online via the Government Publishing Office [<a href="http://www.gpo.gov">www.gpo.gov</a>]
[FR Doc No: 98-12808]



[[Page 26966]]

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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 96-NM-257-AD; Amendment 39-10526; AD 98-10-14]
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 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 
amendment reduces the repetitive inspection interval for all of the 
currently required inspections, except for the X-ray inspections. It 
also revises the terminating modification provision for some airplanes. 
This amendment is prompted by reports of cracks found during the 
currently required inspections, which had progressed to lengths greater 
than predicted. The actions specified by this 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: Effective June 19, 1998.
    The incorporation by reference of certain publications listed in 
the regulations is approved by the Director of the Federal Register as 
of June 19, 1998.
    The incorporation by reference of certain other publications, as 
listed in the regulations, was approved previously by the Director of 
the Federal Register as of May 15, 1996 (61 FR 16379, April 15, 1996).

ADDRESSES: The service information referenced in this AD may be 
obtained from Lockheed Aeronautical Systems Support Company (LASSC), 
Field Support Department, Dept. 693, Zone 0755, 2251 Lake Park Drive, 
Smyrna, Georgia 30080. 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, ACE-116A, Atlanta Aircraft Certification Office, 
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 Atlanta 
Aircraft Certification Office, Crown Center, 1895 Phoenix Boulevard, 
suite 450, Atlanta, Georgia 30337-2748; telephone (770) 703-6067; fax 
(770) 703-6097.

SUPPLEMENTARY INFORMATION: A proposal to amend part 39 of the Federal 
Aviation Regulations (14 CFR part 39) by superseding AD 96-07-13, 
amendment 39-9563 (61 FR 16379, April 15, 1996), which is applicable to 
all Lockheed Model L-1011-385 series airplanes, was published in the 
Federal Register on April 1, 1997 (62 FR 15429). That action proposed 
to supersede AD 96-07-13 to continue to require 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. That action also proposed to reduce the 
repetitive inspection interval for all of the currently required 
inspections, except for the X-ray inspections. Additionally, it 
proposed to revise the terminating modification provision for some 
airplanes.
    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

    Three commenters support the proposed rule.

Require Compliance With New Service Information

    One commenter, the manufacturer, requests that the proposal require 
compliance with Revision 6 of Lockheed L-1011 Service Bulletin 093-57-
203, rather than Revision 5, as cited in the proposal. The manufacturer 
advises that Revision 6 of the service bulletin contains significant 
clarification and simplifies the proposed inspections, which will 
enable operators to perform the proposed inspections in a correct and 
efficient manner. Further, the manufacturer notes that Revision 6 of 
the service bulletin contains no additional procedures to be 
accomplished, and therefore would pose no additional burden on any 
operator.
    The FAA concurs. Since the issuance of the proposed rule, the FAA 
has reviewed and approved Lockheed L-1011 Service Bulletin 093-57-203, 
Revision 6, dated August 18, 1997. The FAA finds that accomplishment of 
certain requirements of this AD in accordance with Revision 5 of the 
subject service bulletin adequately addresses the unsafe condition. 
Therefore, the FAA has revised the final rule to require compliance in 
accordance with Revision 6 of the service bulletin.

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 change previously 
described. The FAA has determined that this change will neither 
increase the economic burden on any operator nor increase the scope of 
the AD.

Cost Impact

    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 AD.
    The actions that are currently required by AD 96-07-13 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 proposed inspection requirements of this AD is 
estimated to be $453,120, or $3,840 per airplane, per inspection cycle. 
This new AD action adds no new costs to affected operators.
    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

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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 39-9563 (61 FR 
16379, April 15, 1996), and by adding a new airworthiness directive 
(AD), amendment 39-10526, to read as follows:

98-10-14  Lockheed: Amendment 39-10526. 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 
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 6, dated August 
18, 1997.
    (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 6 of the Lockheed service bulletin. 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 6 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 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 093-57-215, 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:

<bullet> Lockheed L-1011 Service Bulletin 093-57-184, Revision 6, 
dated October 28, 1991;
<bullet> Lockheed L-1011 Service Bulletin 093-57-184, Revision 7, 
dated December 6, 1994;
<bullet> Lockheed L-1011 Service Bulletin 093-57-196, Revision 5, 
dated October 28, 1991; or
<bullet> 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 6, 
dated August 18, 1997; 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 6, dated August 18, 1997.
    (1) If no cracking is found: Repeat the inspections and follow-
on actions in accordance with the times specified in Table I of 
Revision 6 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 Revision 6 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 Revision 6 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

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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.
    (e) Except as provided by paragraph (a)(2)(i), (a)(2)(ii), 
(b)(2)(i), and (b)(2)(ii) of this AD, the actions shall be done in 
accordance with Lockheed L-1011 Service Bulletin 093-57-203, 
Revision 4, dated March 27, 1995; Lockheed L-1011 Service Bulletin 
093-57-203, Revision 6, dated August 18, 1997; 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; 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; and Lockheed L-1011 Service Bulletin 
093-57-215, dated April 11, 1996.
    (1) The incorporation by reference of Lockheed L-1011 Service 
Bulletin 093-57-203, Revision 6, dated August 18, 1997; and Lockheed 
L-1011 Service Bulletin 093-57-215, dated April 11, 1996; is 
approved by the Director of the Federal Register in accordance with 
5 U.S.C. 552(a) and 1 CFR part 51.
    (2) The incorporation by reference of 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; 
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; and Lockheed L-1011 Service Bulletin 
093-57-203, Revision 4, dated March 27, 1995, was approved 
previously by the Director of the Federal Register as of May 15, 
1996 (61 FR 16379, April 15, 1996).
    (3) Copies may be obtained from Lockheed Aeronautical Systems 
Support Company (LASSC), 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, Systems and Flight Test Branch, ACE-116A, 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.
    (f) This amendment becomes effective on June 19, 1998.

    Issued in Renton, Washington, on May 7, 1998.
John J. Hickey,
Acting Manager, Transport Airplane Directorate Aircraft Certification 
Service.
[FR Doc. 98-12808 Filed 5-14-98; 8:45 am]
BILLING CODE 4910-13-U