[Federal Register Volume 60, Number 242 (Monday, December 18, 1995)]
[Proposed Rules]
[Pages 65032-65035]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 95-30646]



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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 95-NM-88-AD]


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 certain areas of the rear spar caps, web, skin, and certain 
fastener holes; and repair or modification, if necessary. That AD was 
prompted by reports of fatigue cracks in the caps of the wing rear spar 
inboard of inner wing station 346. The actions specified by that AD are 
intended to prevent rupture of the rear spar, which could result in 
extensive damage to the wing and fuel spillage. This action would add 
various improved inspections and follow-on actions, and would require 
that the initial inspections be accomplished at reduced thresholds.

DATES: Comments must be received by February 13, 1996.

ADDRESSES: Submit comments in triplicate to the Federal Aviation 
Administration (FAA), Transport Airplane Directorate, ANM-103, 
Attention: Rules Docket No. 95-NM-88-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; or at 
the FAA, Small Airplane Directorate, Atlanta Aircraft Certification 
Office, Campus Building, 1701 Columbia Avenue, Suite 2-160, College 
Park, Georgia.

FOR FURTHER INFORMATION CONTACT: Thomas Peters, Aerospace Engineer, 
Flight Test Branch, ACE-116A, FAA, Small Airplane Directorate, Atlanta 
Aircraft Certification Office, 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. 

[[Page 65033]]

    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 95-NM-88-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. 95-NM-88-AD, 1601 Lind Avenue, SW., Renton, Washington 
98055-4056.

Discussion

    On August 26, 1993, the FAA issued AD 93-17-10, amendment 39-8681 
(58 FR 54947, October 25, 1993), which is applicable to all Lockheed 
Model L-1011-385 series airplanes. That AD requires inspections to 
detect cracking of certain areas of the rear spar caps, web, skin, and 
certain fastener holes; and repair or modification, if necessary. That 
action was prompted by reports of fatigue cracks in the caps of the 
wing rear spar inboard of inner wing station (IWS) 346. The 
requirements of that AD are intended to prevent rupture of the rear 
spar, which could result in extensive damage to the wing and fuel 
spillage.
    Since the issuance of that AD, the FAA has received additional 
reports of fatigue cracking in the subject areas on these airplanes. 
The airplanes on which the cracking occurred had accumulated fewer 
landings than the number of landings specified as the inspection 
thresholds in AD 93-17-10.

Discussion of Relevant Service Information

    Subsequent to the finding of this new cracking, the manufacturer 
issued, and the FAA reviewed and approved, Lockheed L-1011 Service 
Bulletin 093-57-203, Revision 4, dated March 27, 1995. The revised 
service bulletin describes procedures for inspections to detect 
cracking in certain areas of the rear spar caps, web, skin, and certain 
fastener holes at earlier inspection thresholds than those specified 
previously. The service bulletin revision describes the following 
various improved inspection procedures and follow-on actions:
    1. Repetitive X-ray (radiographic) inspections to detect cracking 
of the upper and lower caps of the rear spar and of the associated web 
and skin areas between IWS 231 and IWS 343. The inspection procedure 
specified in the revised service bulletin has been changed from that 
described in Revision 3 to clarify the location for the X-ray tube head 
for certain exposures.
    2. Repetitive eddy current surface scan inspections to detect 
cracking of the upper spar cap-to-skin and the upper spar cap-to-web 
attachment areas around the fasteners from IWS 310 to the main landing 
gear (MLG) trunnion fitting at approximately IWS 343.
    3. A bolt hole eddy current inspection to detect cracking in the 
1\1/8\-inch diameter fastener hole located inboard of IWS 343. The 
service bulletin specifies that this inspection is accomplished at an 
initial inspection threshold only. (However, the service bulletin also 
specifies that this inspection must be accomplished on any fastener 
hole where the fastener is removed for repair or replacement.)
    4. For airplanes on which cracking is found during the bolt hole 
eddy current inspection of the 1\1/8\-inch diameter fastener hole 
located inboard of IWS 343, the service bulletin describes procedures 
for a bolt hole eddy current inspection to detect cracking at the four 
\5/8\-inch fastener locations directly below the 1\1/8\-inch fastener.
    5. For airplanes on which Option iv or v of Lockheed Repair 
Procedure LCC-7622-368 has not been accomplished, the service bulletin 
describes procedures for subsequent repetitive ultrasonic inspections 
to detect cracking in the fastener hole. These inspections are 
performed in conjunction with eddy current surface scan inspections to 
detect cracking of the upper horizontal edge of the rear spar web, \1/
2\-inch each side of the inboard edge of the MLG trunnion fitting.
    6. Repetitive low frequency eddy current ring probe inspections to 
detect cracking of the upper cap/skin of the rear spar between IWS 310 
to IWS 326 and the cap/web fasteners.
    Since the issuance of AD 93-17-10, the FAA has also reviewed and 
approved later revisions of certain service information specified in 
paragraph (d) of that AD as an alternative method of repairing 
confirmed findings of cracking, as follows:
    1. Lockheed L-1011 Service Bulletin 093-57-196, Revision 6, dated 
December 6, 1994, and Lockheed L-1011 Service Bulletin Change 
Notification 093-57-196, R6-CN1, dated August 22, 1995.
    2. Lockheed L-1011 Service Bulletin 093-57-184, Revision 7, dated 
December 6, 1994, and Lockheed L-1011 Service Bulletin Change 
Notification 093-57-196, R7-CN1, dated August 22, 1995.
    These service bulletins describe procedures for modification of the 
rear spar upper and lower caps between IWS 228 and 346. Among other 
things, these service bulletin revisions were issued to standardize the 
rework of fastener holes, add new instructions to refer to drawings to 
accomplish the modification, clarify miscellaneous information, and to 
reference certain service information for web damage extending beyond 
IWS 327.

Discussion of the Proposed Action

    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 93-17-10 to continue to require 
inspections to detect cracking of certain areas of the rear spar caps, 
web, skin, and certain fastener holes; and repair or modification, if 
necessary. The proposed AD would add various improved inspections and 
follow-on actions, and would require that the initial inspections be 
accomplished at reduced thresholds. The inspections, follow-on actions, 
and modification would be required to be accomplished in accordance 
with the service bulletin described previously. The repair would be 
required to be accomplished in accordance with a method approved by the 
FAA or in accordance with the Lockheed Model L-1011 Structural Repair 
Manual.
    Operators should note that only the inspection procedures (and 
follow-on actions) described in Lockheed L-1011 Service Bulletin 093-
57-203 would be required by this proposal. In a separate AD action [AD 
94-05-01, amendment 39-8839 (59 FR 10275, March 4, 1994)], the FAA 
previously addressed the portion of that service bulletin that deals 
with the modification

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 would be affected by this proposed AD.
    The actions that are currently required by AD 93-17-10 take 

[[Page 65034]]
    approximately 21 work hours per airplane to accomplish, at an average 
labor rate of $60 per work hour. Based on these figures, the cost 
impact on U.S. operators of the actions currently required is estimated 
to be $148,680, or $1,260 per airplane.
    The new actions 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 requirements of this AD is estimated to 
be $453,120, or $3,840 per airplane.
    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.

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), 40101, 40113, 44701.


Sec. 39.13  [Amended]

    2. Section 39.13 is amended by removing amendment 39-8681 (58 FR 
54947, October 25, 1993), and by adding a new airworthiness directive 
(AD), to read as follows:

Lockhead Aeronautical Systems Company: Docket 95-NM-88-AD. 
Supersedes AD 93-17-10, Amendment 39-8681.

    Applicability: All Model L-1011-385-1, L-1011-385-1-14, L-1011-
385-1-15, and L-1011-385-3 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 use the authority 
provided in paragraph (d) of this AD to request approval from the 
FAA. This approval may address either no action, if the current 
configuration eliminates the unsafe condition; or different actions 
necessary to address the unsafe condition described in this AD. Such 
a request should include an assessment of the effect of the changed 
configuration on the unsafe condition addressed by this AD. In no 
case does the presence of any modification, alteration, or repair 
remove any airplane from the applicability of this AD.

    Compliance: Required as indicated, unless accomplished 
previously.

    Note 2: Paragraphs (a)(1) and (b) of this AD restate the 
requirement for repetitive inspections and follow-on actions 
contained in paragraphs (a) and (b) of AD 93-17-10. Therefore, for 
operators who have previously accomplished at least the initial 
inspection in accordance with AD 93-17-10, paragraphs (a)(1) and (b) 
of this AD require that the next scheduled inspection be performed 
within 2,000 flight cycles after the last inspection performed in 
accordance with paragraphs (a) and (b) of AD 93-17-10.

    To prevent rupture of the rear spar, which could result in 
extensive damage to the wing and fuel spillage, accomplish the 
following:
    (a) Perform inspections and various follow-on actions to detect 
cracking in the areas specified in and in accordance with Part II of 
the Accomplishment Instructions of the Lockheed service documents 
listed below. After the effective date of this AD, the inspections 
and follow-on actions shall be performed only at the times specified 
in and in accordance with Revision 4 of Lockheed L-1011 Service 
Bulletin 093-57-203. [The inspections and follow-on actions 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.]
     Lockheed L-1011 Service Bulletin 093-57-203, Revision 
3, dated October 28, 1991; or
     Lockheed L-1011 Service Bulletin Service Bulletin 093-
57-203, Revision 3, dated October 28, 1991, as amended by Lockheed 
L-1011 Service Bulletin Change Notification 093-57-203, R3-CN1, 
dated June 22, 1992; or
     Lockheed L-1011 Service Bulletin 093-57-203, Revision 
4, dated March 27, 1995.
    (1) For airplanes on which the inspections required by AD 93-17-
10, amendment 39-8681, have been initiated prior to the effective 
date of this AD: Perform the inspections and follow-on actions at 
the times specified in Table I of Lockheed L-1011 Service Bulletin 
Change Notification 093-57-203, R3-CN1, dated June 22, 1992, or 
within 6 months after November 24, 1993 (the effective date of AD 
93-17-10, amendment 39-8681), whichever occurs later.

    Note 3: As allowed by the phrase, ``unless accomplished 
previously,'' if the inspections and follow-on actions required by 
this paragraph were conducted prior to November 24, 1993, in 
accordance with Lockheed L-1011 Service Bulletin 093-57-203, 
Revision 2, dated January 25, 1991, those inspections need not be 
repeated.

    (2) For airplanes on which the inspections required by AD 93-17-
10, amendment 39-8681, have not been initiated prior to the 
effective date of this AD: Perform the inspections and follow-on 
actions 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 the effective date of this AD, whichever occurs later.
    (b) If no cracking is found, perform the repetitive inspections 
and follow-on actions specified in the Accomplishment Instructions 
of the Lockheed service documents listed below thereafter at 
intervals not to exceed 2,000 flight cycles. After the effective 
date of this AD, the inspections and follow-on actions shall be 
performed only in accordance with Revision 4 of Lockheed L-1011 
Service Bulletin 093-57-203.
     Lockheed L-1011 Service Bulletin 093-57-203, Revision 
3, dated October 28, 1991; or
     Lockheed L-1011 Service Bulletin 093-57-203, Revision 
3, dated October 28, 1991, as amended by Lockheed L-1011 Service 
Bulletin Change Notification 093-57-203, R3-CN1, dated June 22, 
1992; or
     Lockheed L-1011 Service Bulletin 093-57-203, Revision 
4, dated March 27, 1995;

[[Page 65035]]

    (c) If any finding of cracking is confirmed, prior to further 
flight, accomplish paragraph (c)(1), (c)(2), or (c)(3) of this AD.
    (1) 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 required by paragraph (b) of this 
AD. Or
    (2) 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 (b) of this AD. Or
    (3) Modify the rear spar upper and lower caps between IWS 228 
and 346 in accordance with the Lockheed service bulletins listed 
below, as applicable. 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 093-57-203, Revision 
4, dated March 27, 1995.

    Note 4: Accomplishment of the modification specified in 
paragraph (c)(3) 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;
     Lockheed L-1011 Service Bulletin 093-57-203, Revision 
3, dated October 28, 1991; or
     Lockheed L-1011 Service Bulletin 093-57-203, Revision 
3, dated October 28, 1991, as amended by Change Notification 093-57-
203, R3-CN1, dated June 22, 1992.
    (d) 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 5: Information concerning the existence of approved 
alternative methods of compliance with this AD, if any, may be 
obtained from the Atlanta ACO.

    (e) 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 December 11, 1995.
Darrell M. Pederson,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 95-30646 Filed 12-15-95; 8:45 am]
BILLING CODE 4910-13-U