[Federal Register Volume 64, Number 122 (Friday, June 25, 1999)]
[Proposed Rules]
[Pages 34170-34173]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 99-16157]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 98-NM-35-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 adoption of a new airworthiness 
directive (AD) that is applicable to all Lockheed Model L-1011-385 
series airplanes. This proposal would require repetitive inspections to 
detect corrosion or fatigue cracking of certain structural elements of 
the airplane; corrective action, if necessary; and incorporation of 
certain structural modifications. This proposal is prompted by new 
recommendations related to incidents of fatigue cracking and corrosion 
in transport category airplanes that are approaching or have exceeded 
their economic design goal. The actions specified by the proposed AD 
are intended to prevent corrosion or fatigue cracking of certain 
structural elements, which could result in reduced structural integrity 
of the airplane.

DATES: Comments must be received by August 9, 1999.


[[Page 34171]]


ADDRESSES: Submit comments in triplicate to the Federal Aviation 
Administration (FAA), Transport Airplane Directorate, ANM-114, 
Attention: Rules Docket No. 98-NM-35-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 30349; 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 98-NM-35-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. 98-NM-35-AD, 1601 Lind Avenue, SW., Renton, Washington 
98055-4056.

Discussion

    In April 1988, a transport category airplane managed to land after 
tiny cracks in rivet holes in the upper fuselage linked together, 
causing structural failure and explosive decompression. An 18-foot 
section ripped from the fuselage. This accident focused greater 
attention on the problem of aging aircraft.
    Subsequently, in June 1988, the FAA sponsored a conference on aging 
airplane issues, which was attended by representatives of the aviation 
industry from around the world. It became obvious that, because of the 
tremendous increase in air travel, the relatively slow pace of new 
airplane production, and the apparent economic feasibility of operating 
older technology airplanes rather than retiring them, increased 
attention needed to be focused on this aging fleet and maintaining its 
continued operational safety.
    The Air Transport Association (ATA) of America and the Aerospace 
Industries Association (AIA) of America committed to identifying and 
implementing procedures to ensure continuing structural airworthiness 
of aging transport category airplanes. The Airworthiness Assurance 
Working Group (AAWG), with representatives from the aircraft operators, 
manufacturers, regulatory authorities, and other aviation 
representatives, was originally established in August 1988. The 
objective of the AAWG was to sponsor ``Task Groups'' to:
    1. Select service bulletins, applicable to each airplane model in 
the transport fleet, to be recommended for mandatory modification of 
aging airplanes,
    2. Develop corrosion-directed inspections and prevention programs,
    3. Review the adequacy of each operator's structural maintenance 
program,
    4. Review and update the Supplemental Structural Inspection 
Documents (SSID),
    5. Assess repair quality.
    The Structures Task Group (STG) assigned to review the Lockheed 
Model L-1011-385 series airplanes was formed in 1988, and included 
operators of Model L-1011-385 series airplanes, Lockheed, the FAA, and 
observers from regulatory agencies. Certain recommendations made by the 
STG (pursuant to Item 1., described previously) are contained in 
Lockheed Service Bulletin 093-51-035, Revision 1, dated December 16, 
1991. The FAA previously issued AD 94-05-01, amendment 39-8839 (59 FR 
10275, March 4, 1994), to require the structural inspections and the 
modifications recommended in that document.
    Since the issuance of that AD, the STG has recommended 
accomplishment of certain other structural inspections to detect 
corrosion or fatigue cracking of certain structural elements of the 
airplane, and incorporation of certain structural modifications. 
Corrosion or fatigue cracking of certain structural elements, if not 
detected and corrected, could result in reduced structural integrity of 
the airplane.

Explanation of Relevant Service Information

    Lockheed has issued Service Bulletin 093-51-040, Revision 1, dated 
October 1, 1997 (hereinafter referred to as the ``Collector Service 
Bulletin''). The Collector Service Bulletin describes certain 
repetitive inspections to detect corrosion or fatigue cracking of 
certain structural elements of the airplane, including the area around 
the two aft passengers doors and the fuselage-to-underwing longeron 
area at butt line 94.5. The Collector Service Bulletin also describes 
structural modifications of various elements of the airplane that have 
been recommended by the STG, including modification of the retract 
actuators of the main landing gear, modification of the bulkhead at 
fuselage station 1363, and replacement of the wing rear spar web (for 
Model L-1011-385-3 series airplanes). The Collector Service Bulletin 
also references appropriate sources of accomplishment instructions for 
the structural inspections and modifications.
    The FAA has reviewed and approved the Collector Service Bulletin. 
Accomplishment of the actions specified in the Collector Service 
Bulletin is intended to adequately address the identified unsafe 
condition.

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 require accomplishment of the actions specified in 
the service bulletin described previously, except as discussed below.

[[Page 34172]]

Other Relevant Rulemaking

    The FAA previously has issued AD 98-10-14, amendment 39-10526 (63 
FR 26966, May 15, 1998), applicable to all Lockheed Model L-1011-385 
series airplanes, to require various inspections to detect cracking of 
certain areas of the rear spar caps, web, skin, and certain fastener 
holes; and follow-on actions. Accomplishment of the terminating 
modification listed in Lockheed Service Bulletin 093-57-215 (referenced 
in Table II of the Collector Service Bulletin), as required by 
paragraph (e) of this proposed AD; would constitute terminating action 
for the inspection requirements of AD 98-10-14 for the affected 
airplanes.

Differences Between This Proposed Rule and the Service Bulletin

    Operators should note that Table II of the Collector Service 
Bulletin references structural inspections specified in Lockheed 
Service Bulletins 093-53-268, Revision 1, dated July 2, 1996, and 093-
53-272, Revision 1, dated March 17, 1997. However, the FAA previously 
issued AD 99-08-20, amendment 39-11128 (64 FR 18324, April 14, 1999), 
applicable to all Lockheed Model L-1011-385 series airplanes, to 
require the structural inspections specified in Lockheed Service 
Bulletins 093-53-268, Revision 1, and 093-53-272, dated November 12, 
1996. The FAA has determined that the procedures described in Lockheed 
Service Bulletin 093-53-272, Revision 1, are substantially similar to 
those specified in the original issue of that service bulletin. 
Therefore, paragraph (b) of this proposed AD specifies that structural 
inspections in accordance with Lockheed Service Bulletins 093-53-268, 
Revision 1, and 093-53-272, Revision 1, would not be required by this 
AD.
    Operators also should note that the Collector Service Bulletin 
specifies that installation of the modifications in Lockheed Service 
Bulletins 093-53-268, Revision 1, and 093-53-272, terminates the 
inspections specified in Lockheed Service Bulletins 093-53-268, 
Revision 1, and 093-53-272, Revision 1. However, this proposed AD 
specifies that installation of those modifications does not constitute 
terminating action for the subject inspections. AD 99-08-20 does not 
provide for termination of the inspections by installation of the 
modifications, though that AD does specify that inspections may be 
deferred for 18,000 landings, if modifications in accordance with 
Lockheed Service Bulletins 093-53-268, Revision 1, and 093-53-272 are 
accomplished.
    Operators also should note that, for airplanes that have exceeded 
the later of the inspection thresholds specified in Lockheed Service 
Bulletin 093-57-203, Revision 5, dated April 22, 1996, the Collector 
Service Bulletin specifies a grace period of 5 years or 5,000 flight 
cycles after April 11, 1996 (the initial release date of Lockheed 
Service Bulletin 093-57-215), for accomplishment of the terminating 
modification described in Lockheed Service Bulletin 093-57-215, dated 
April 11, 1996. This proposed rule specifies a grace period for that 
modification of 2 years or 2,000 flight cycles after the effective date 
of this AD. The proposed grace period was developed by taking into 
account the manufacturer's recommended grace period of five years after 
April 11, 1996, as well as the length of time that is normally required 
for the rulemaking process to be completed. In consideration of both of 
these factors, the FAA finds that a grace period of 2 years or 2,000 
flight cycles after the effective date of the AD is adequate to ensure 
the continued safety of the transport airplane fleet. The FAA also 
finds that such a grace period will provide operators with slightly 
more time than what was specified in the Collector Service Bulletin to 
accomplish the terminating modification.

Cost Impact

    There are approximately 214 airplanes of the affected design in the 
worldwide fleet. The FAA estimates that 107 airplanes of U.S. registry 
would be affected by this proposed AD.
    It would take approximately 315 work hours per airplane to 
accomplish the proposed inspections, at an average labor rate of $60 
per work hour. Based on these figures, the cost impact of the 
inspections proposed by this AD on U.S. operators is estimated to be 
$2,022,300, or $18,900 per airplane, per inspection cycle.
    It would take approximately 3,385 work hours per airplane to 
accomplish the proposed modifications, at an average labor rate of $60 
per work hour. Required parts would cost approximately $242,000 per 
airplane. Based on these figures, the cost impact of the modifications 
proposed by this AD on U.S. operators is estimated to be $47,625,700, 
or $445,100 per airplane.
    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 adding the following new 
airworthiness directive:

Lockheed: Docket 98-NM-35-AD.

    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 (f) of 
this AD. The request should include an assessment of the

[[Page 34173]]

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 corrosion or fatigue cracking of certain structural 
elements, which could result in reduced structural integrity of the 
airplane, accomplish the following:

Inspections

    (a) Except as provided by paragraph (b) of this AD, perform 
structural inspections to detect corrosion or fatigue cracking of 
certain structural elements of the airplane, in accordance with the 
applicable service bulletins listed under ``Service Bulletin Number, 
Revision, and Date'' in Tables I and II of Lockheed Service Bulletin 
093-51-040, Revision 1, dated October 1, 1997. Perform the initial 
inspections at the later of the times specified in paragraphs (a)(1) 
and (a)(2) of this AD. Thereafter, repeat each inspection at an 
interval not to exceed that specified in the applicable service 
bulletin.
    (1) Prior to the threshold specified in the individual service 
bulletin listed in Table I or II of Lockheed Service Bulletin 093-
51-040, Revision 1, as applicable.
    (2) Within one repetitive interval after the effective date of 
this AD, as specified in the individual service bulletin listed in 
Table I or II of Lockheed Service Bulletin 093-51-040, Revision 1, 
as applicable.
    (b) The structural inspections specified in Lockheed Service 
Bulletins 093-53-268, Revision 1, dated July 2, 1996, and 093-53-
272, Revision 1, dated March 17, 1997; as listed in Table II of 
Lockheed Service Bulletin 093-51-040, Revision 1, dated October 1, 
1997; are not required by this AD. The inspections specified in 
these service bulletins are required by AD 99-08-20, amendment 39-
11128.

Corrective Action

    (c) If any cracking is detected during any inspection required 
by paragraph (a) of this AD, prior to further flight, accomplish the 
actions specified in paragraph (c)(1), (c)(2), (c)(3), or (c)(4) of 
this AD.
    (1) Repair in accordance with the applicable service bulletin 
referenced in Table I or II of Lockheed Service Bulletin 093-51-040, 
Revision 1, dated October 1, 1997.
    (2) Repair in accordance with the applicable section of the 
Lockheed L-1011 Structural Repair Manual.
    (3) Accomplish the terminating modification in accordance with 
the applicable service bulletin referenced in Table I or II of 
Lockheed Service Bulletin 093-51-040, Revision 1, dated October 1, 
1997.
    (4) Repair in accordance with a method approved by the Manager, 
Atlanta Aircraft Certification Office (ACO), FAA, Small Airplane 
Directorate.

Terminating Action

    (d) Install the terminating modification referenced in each 
service bulletin listed in Table II of Lockheed Service Bulletin 
093-51-040, Revision 1, dated October 1, 1997; in accordance with 
the applicable service bulletin listed under ``Service Bulletin 
Number, Revision, and Date'' in Table II of Lockheed Service 
Bulletin 093-51-040, Revision 1. Except as provided by paragraph (e) 
of this AD, install each modification at the later of the times 
specified in paragraphs (d)(1) and (d)(2) of this AD. Such 
installation constitutes terminating action for the applicable 
structural inspection required by paragraph (a) of this AD.

    Note 2: Installation of the terminating modifications specified 
in Lockheed Service Bulletin 093-53-268, Revision 1, dated July 2, 
1996, and Lockheed Service Bulletin 093-53-272, dated November 12, 
1996, does not constitute terminating action for the repetitive 
inspection requirements of AD 99-08-20, amendment 39-11128.

    (1) Prior to the threshold specified in the applicable service 
bulletin listed in Table II of Lockheed Service Bulletin 093-51-040, 
Revision 1.
    (2) Within 5 years or 5,000 flight cycles after the effective 
date of this AD, whichever occurs first.
    (e) At the later of the times specified in paragraphs (e)(1) and 
(e)(2) of this AD: Install the terminating modification listed in 
Lockheed Service Bulletin 093-57-215, as referenced in Table II of 
Lockheed Service Bulletin 093-51-040, Revision 1, dated October 1, 
1997. Such installation constitutes terminating action for the 
inspections required by AD 98-10-14, amendment 39-10526.
    (1) Prior to the threshold specified in Lockheed Service 
Bulletin 093-57-203, Revision 5, dated April 22, 1996.
    (2) Within 2 years or 2,000 flight cycles after the effective 
date of this AD, whichever occurs first.

Alternative Methods of Compliance

    (f) 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 3: 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

    (g) 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 June 18, 1999.
Kalene C. Yanamura,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 99-16157 Filed 6-24-99; 8:45 am]
BILLING CODE 4910-13-U