[Federal Register Volume 62, Number 62 (Tuesday, April 1, 1997)]
[Proposed Rules]
[Pages 15429-15431]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 97-8125]


 ========================================================================
 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.
 
 ========================================================================
 

  Federal Register / Vol. 62, No. 62 / Tuesday, April 1, 1997 / 
Proposed Rules  

[[Page 15429]]



DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 96-NM-257-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 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 action would reduce the repetitive 
inspection interval for all of the currently required inspections, 
except for the x-ray inspections. It also would revise the terminating 
modification provision for some airplanes. This proposal is prompted by 
reports of cracks found during the currently-required inspections, 
which had progressed to lengths greater than predicted. The actions 
specified by the proposed 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: Comments must be received by May 9, 1997.

ADDRESSES: Submit comments in triplicate to the Federal Aviation 
Administration (FAA), Transport Airplane Directorate, ANM-103, 
Attention: Rules Docket No. 96-NM-257-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, 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.

FOR FURTHER INFORMATION CONTACT: Thomas Peters, Aerospace Engineer, 
Systems and Flight Test Branch, ACE-116A, FAA, Atlanta Aircraft 
Certification Office, Small Airplane Directorate, Campus Building, 1701 
Columbia Avenue, Suite 2-160, College Park, Georgia 30337-2748; 
telephone (404) 305-7367; fax (404) 305-7348.

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 96-NM-257-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-103, Attention: Rules 
Docket No. 96-NM-257-AD, 1601 Lind Avenue, SW., Renton, Washington 
98055-4056.

Discussion

    On March 28, 1996, the FAA issued AD 96-07-13, amendment 39-9563 
(61 FR 16379, April 15, 1996), applicable to all Lockheed Model L-1011-
385 series airplanes. That AD requires repetitive visual, x-ray, eddy 
current, and ultrasonic 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. It also provides for 
modification of the rear spar upper and lower caps between Inner Wing 
Station (IWS) 228 and 346 as terminating action for the requirements of 
the AD.
    AD 96-07-13 was prompted by reports of fatigue cracking that 
occurred in these areas. The requirements of that AD are intended to 
ensure that fatigue cracking is detected and corrected in a timely 
manner. Such cracking, if not corrected, could lead to rupture of the 
rear spar and, consequently, result in extensive damage to the wing and 
spillage of fuel.

Actions Since Issuance of Previous Rule

    Since the issuance of AD 96-07-13, the FAA has received reports 
indicating that fatigue cracks detected during inspections performed in 
accordance with that AD had progressed to lengths greater than 
predicted. One finding indicated that a crack apparently had grown 
substantially during the repetitive inspection period. These new data 
indicate that, in order to detect and correct the subject fatigue 
cracking before it can progress to critical lengths, the currently 
required inspections must be performed more frequently.
    Additionally, the manufacturer has notified the FAA that the 
modification of the rear spar upper and lower caps on Model L-1011-385-
3 airplanes, which was described in Part I of Lockheed Service Bulletin 
093-57-203, Revision 4, dated March 27, 1995, has been superseded by a 
web replacement that is described in Lockheed Service Bulletin 093-57-
215.

[[Page 15430]]

Explanation of Relevant Service Information

    The FAA has reviewed and approved Lockheed Service Bulletin 093-57-
203, Revision 5, dated April 22, 1996, which describes procedures for 
conducting repetitive inspections to detect fatigue cracking in the 
inboard web periphery from IWS 346 to IWS 228. It recommends that the 
inspections be repeated at shorter intervals than those recommended in 
Revision 4 of this service bulletin (dated March 27, 1995). The shorter 
intervals will ensure that cracking is detected in a more timely 
manner.
    Additionally, Revision 5 does not contain procedures for the 
modification of the rear spar upper and lower caps for Model L-1011-
385-3 airplanes, which was contained in Revision 4. That modification 
has been revised, and the procedures for it are now contained in 
Lockheed L-1011 Service Bulletin 093-57-215, dated April 11, 1996.

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 96-07-13. It would continue to require 
the same 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. However, except for the currently 
required x-ray inspections, these inspections would be required to be 
repeated at shorter intervals. These actions would be required to be 
accomplished in accordance with Revision 5 of Lockheed Service Bulletin 
093-57-203, described previously.
    This new proposed AD would continue to provide for terminating 
action for the repetitive inspections, as was provided in AD 96-07-13. 
However, terminating action for Model L-1011-385-3 airplanes would be 
required to be accomplished in accordance with the procedures specified 
in Lockheed L-1011 Service Bulletin 093-57-215.

Cost Impact

    There are approximately 236 Lockheed Model L-1011-385 series 
airplanes of the affected design in the worldwide fleet. The FAA 
estimates that 118 airplanes of U.S. registry would be affected by this 
proposed AD.
    The inspections that are proposed in this AD action would 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.
    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 removing amendment 39-9563 (61 FR 
16379, April 15, 1996), and by adding a new airworthiness directive 
(AD), to read as follows:

Lockheed: 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 
otherwise 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 5, dated April 
22, 1996.

[[Page 15431]]

    (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 5 of the Lockheed service bulletins. 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 5 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 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:

     Lockheed L-1011 Service Bulletin 093-57-184, Revision 
6, dated October 28, 1991
     Lockheed L-1011 Service Bulletin 093-57-184, Revision 
7, dated December 6, 1994
     Lockheed L-1011 Service Bulletin 093-57-196, Revision 
5, dated October 28, 1991
     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 5, 
dated April 22, 1996; 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 5, dated April 22, 1996.
    (1) If no cracking is found: Repeat the inspections and follow-
on actions in accordance with the times specified in Table I 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 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 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 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.

    Issued in Renton, Washington, on March 25, 1997.
Darrell M. Pederson,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 97-8125 Filed 3-31-97; 8:45 am]
BILLING CODE 4910-13-U