[Federal Register Volume 63, Number 160 (Wednesday, August 19, 1998)]
[Proposed Rules]
[Pages 44411-44413]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 98-22241]


      
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 Proposed Rules
                                                 Federal Register
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 This section of the FEDERAL REGISTER contains notices to the public of 
 the proposed issuance of rules and regulations. The purpose of these 
 notices is to give interested persons an opportunity to participate in 
 the rule making prior to the adoption of the final rules.
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  Federal Register / Vol. 63, No. 160 / Wednesday, August 19, 1998 / 
Proposed Rules  

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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 98-NM-199-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 supersedure of an existing 
airworthiness directive (AD), applicable to all Lockheed Model L-1011-
385 series airplanes, that currently requires inspections to detect 
cracking of fuselage station (FS) 983 main frame (left and right 
sides), and repair, if necessary. That AD was prompted by reports of 
cracks found in the left and right sides of the FS 983 main frame, 
below the level of the cabin floor. This action would add a new 
requirement to review the airplane maintenance records to determine if 
a crack within the FS 983 main frame web was detected previously, and 
if repair of any such crack was deferred; and repair, prior to further 
flight, if necessary. The actions specified by the proposed AD are 
intended to prevent cracking of the FS 983 frame, which could result in 
reduced structural integrity of the fuselage.

DATES: Comments must be received by October 5, 1998.

ADDRESSES: Submit comments in triplicate to the Federal Aviation 
Administration (FAA), Transport Airplane Directorate, ANM-114, 
Attention: Rules Docket No. 98-NM-199-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 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 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-199-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-199-AD, 1601 Lind Avenue, SW., Renton, Washington 
98055-4056.

Discussion

    On November 5, 1991, the FAA issued AD 91-21-51, amendment 39-8099 
(56 FR 61361, December 3, 1991), applicable to all Lockheed Model L-
1011-385 series airplanes, to require inspections to detect stress 
corrosion cracking of fuselage station (FS) 983 main frame (left and 
right sides), and repair, if necessary. That action was prompted by 
reports of cracks found in the left and right sides of FS 983 main 
frame, below the level of the cabin floor. The requirements of that AD 
are intended to prevent cracks in the fuselage frame, which, if not 
corrected, could result in reduced structural integrity of the 
fuselage.
    That AD also contained a provision that, if a single crack was 
detected that was completely contained within a certain area of the FS 
983 main frame web, repair of the crack was not required. In lieu of 
repair, the cracked area could be treated with corrosion inhibitor and 
inspected repetitively using internal visual and eddy current 
techniques. In the preamble to AD 91-21-51, the FAA indicated that 
these repetitive inspections were considered ``interim action'' and 
that further rulemaking action was being considered. The FAA now has 
determined that further rulemaking action is indeed necessary. As a 
follow-on action from that determination, the FAA is now proposing to 
mandate repair of any crack for which repair was deferred. Such repair 
would constitute terminating action for the repetitive inspection 
requirement.

Explanation of Relevant Service Information

    The FAA has reviewed and approved Lockheed Tristar L-1011 Service 
Bulletin 093-53-266, dated March 2, 1992, as revised by Change 
Notification CN1, dated July 10, 1992; which describes, among other 
things, procedures for repairing cracking of the FS 983 main frame web. 
The service bulletin specifies that repair of any such cracking may be 
accomplished in

[[Page 44412]]

accordance with Lockheed Drawing LCC-7622-327 (for Lockheed Model L-
1011-385 series airplanes having serial numbers 1002 through 1012 
inclusive), or LCC-7622-325 (for Lockheed Model L-1011-385 series 
airplanes having serial numbers 1013 through 1250 inclusive); or 
partial frame replacement may be accomplished in accordance with 
Lockheed Drawing LCC-7622-326 (for all Lockheed Model L-1011-385 series 
airplanes).

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 supersede AD 91-21-51 to continue to require 
inspections to detect cracking of the FS 983 main frame (left and right 
sides), and repair, if necessary. The proposed AD adds a requirement to 
review the airplane maintenance records to determine if a crack within 
the FS 983 main frame web was detected previously, and if repair of any 
such crack was deferred; and repair, if necessary. Accomplishment of 
such repair would constitute terminating action for the repetitive 
inspection requirements of this proposed AD. The actions would be 
required to be accomplished in accordance with the service bulletin 
described previously, except as discussed below.

Differences Between Proposed Rule and Service Bulletin

    Operators should note that, unlike the procedures described in 
Lockheed Tristar L-1011 Service Bulletin 093-53-266, as revised by 
Change Notification CN1, this proposed AD would not permit long-term 
repetitive inspections of main frame web areas with only a single crack 
to continue in lieu of accomplishment of a repair. The FAA has 
determined that long-term continued operational safety will be better 
assured by modifications or repairs to remove the source of the 
problem, rather than by repetitive inspections. Long-term inspections 
may not be providing the degree of safety assurance necessary for the 
transport airplane fleet. This, coupled with a better understanding of 
the human factors associated with numerous repetitive inspections, has 
led the FAA to consider placing less emphasis on special procedures and 
more emphasis on modifications. The proposed repair requirement is in 
consonance with these considerations.

Cost Impact

    There are approximately 235 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 external eddy current inspection that currently is required by 
AD 91-21-51, and that would be retained in this AD, takes approximately 
1 work hour per airplane to accomplish, at an average labor rate of $60 
per work hour. Based on these figures, the cost impact of this 
inspection on U.S. operators is estimated to be $7,020, or $60 per 
airplane.
    The internal visual and eddy current inspection that currently is 
required by AD 91-21-51, and that would be retained in this AD, takes 
approximately 1 work hour per airplane to accomplish, at an average 
labor rate of $60 per work hour. Based on these figures, the cost 
impact of this inspection on U.S. operators is estimated to be $7,020, 
or $60 per airplane, per inspection cycle.
    The cost impact figures discussed above are based on assumptions 
that no operator has yet accomplished any of the current or proposed 
requirements of this AD action, and that no operator would accomplish 
those actions in the future if this AD were not adopted.
    Should an operator be required to accomplish the repair of cracking 
that is proposed in this AD, it would take approximately 30 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 repair proposed by 
this AD on U.S. operators is estimated to be $210,600, or $1,800 per 
airplane.

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 39-8099 (56 FR 
61361, December 3, 1991), and by adding a new airworthiness directive 
(AD), to read as follows:

Lockheed: Docket 98-NM-199-AD. Supersedes AD 91-21-51, amendment 39-
8099.

    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 (g)(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 cracking in the fuselage station (FS) 983 frame, 
which could result in reduced structural integrity of the fuselage, 
accomplish the following:

Restatement of Requirements of AD 91-21-51, Amendment 39-8099

    (a) Within 20 days after December 18, 1991 (the effective date 
of AD 91-21-51, amendment 39-8099), inspect the left and right sides 
of FS 983 main frame from waterline (WL) 175 to WL 200 to detect 
cracks using a high frequency eddy current procedure, in accordance 
with paragraph A. of the Accomplishment Instructions of

[[Page 44413]]

Lockheed Service Bulletin 093-53-264, dated October 4, 1991. At the 
operator's option, the internal inspection required by paragraph (d) 
below may be used in lieu of the external inspection.
    (b) If cracks that extend into the main frame caps are found 
during the inspection performed in accordance with paragraph (a) of 
this AD, prior to further flight, repair in accordance with a method 
approved by the Manager, Atlanta Aircraft Certification Office 
(ACO), FAA, Small Airplane Directorate.
    (c) Within 60 days after December 18, 1991, perform an internal 
visual and eddy current inspection of the FS 983 main frame cap and 
web in accordance with paragraph B. of the Accomplishment 
Instructions of Lockheed Service Bulletin 093-53-264, dated October 
4, 1991.
    (d) If cracks in the following locations are found during the 
inspection required by paragraph (c) of this AD, prior to further 
flight, repair in accordance with a method approved by the Manager, 
Atlanta ACO.
    (1) Any crack extending into the main frame caps.
    (2) Any crack extending into the web-to-cap radius.
    (3) Any crack extending into a web area outside the shaded area 
shown in Figure 1, Sheet 3, of Lockheed Service Bulletin 093-53-264, 
dated October 4, 1991.
    (4) More than 1 crack within the main frame web area shown in 
Figure 1, Sheet 3, of Lockheed Service Bulletin 093-53-264, dated 
October 4, 1991.
    (e) If, during the inspection required by paragraph (c) of this 
AD, a single crack is found that is completely contained within the 
main frame web area shown in Figure 1, Sheet 3, of Lockheed Service 
Bulletin 093-53-264, dated October 4, 1991: Prior to further flight, 
treat the cracked section of the web with corrosion inhibitor in 
accordance with the service bulletin. Thereafter, repeat the 
inspections at intervals not to exceed 90 days, using the internal 
inspection procedure required by paragraph (c) of this AD.

New Requirements of This AD

    (f) Within 18 months after the effective date of this AD, review 
the airplane maintenance records to determine if a crack within the 
main frame web area has been detected previously, and if repair of 
any such crack was deferred in accordance with paragraph (e) of AD 
91-21-51, amendment 39-8099. For any crack for which repair has been 
deferred, prior to further flight, repair the crack in accordance 
with Lockheed Tristar L-1011 Service Bulletin 093-53-266, dated 
March 2, 1992; as revised by Change Notification CN1, dated July 10, 
1992. Accomplishment of such repair constitutes terminating action 
for the repetitive inspections required by paragraph (e) of this AD.

    Note 2: Lockheed Tristar L-1011 Service Bulletin 093-53-266, 
dated March 2, 1992; as revised by Change Notification CN1, dated 
July 10, 1992; references Lockheed Drawings LCC-7622-325, LCC-7622-
326, and LCC-7622-327, as additional sources of service information 
to accomplish repairs.

    (g)(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.
    (g)(2) Alternative methods of compliance, approved previously in 
accordance with AD 91-21-51, amendment 39-8099, are approved as 
alternative methods of compliance with the inspection requirements 
of paragraphs (a) and (c) of this AD, and the repair/modification 
requirements of paragraphs (b) and (d) of this AD.

    Note 3: Information concerning the existence of approved 
alternative methods of compliance with this AD, if any, may be 
obtained from the Atlanta ACO.

    (h) 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 August 12, 1998.
John J. Hickey,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 98-22241 Filed 8-18-98; 8:45 am]
BILLING CODE 4910-13-U