[Federal Register Volume 59, Number 110 (Thursday, June 9, 1994)]
[Unknown Section]
[Page 0]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 94-14020]


[[Page Unknown]]

[Federal Register: June 9, 1994]


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DEPARTMENT OF TRANSPORTATION
14 CFR Part 39

[Docket No. 94-NM-32-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 adoption of a new airworthiness 
directive (AD) that is applicable to certain Lockheed Model L-1011-385 
series airplanes. This proposal would require various modifications and 
inspections of the flight controls, doors, and horizontal stabilizers. 
This proposal is prompted by a recommendation by the Systems Review 
Task Force (SRTF) for accomplishment of certain modifications and 
inspections that will enhance the controllability of these airplanes in 
the unlikely event of flight control malfunction or failure. The 
actions specified by the proposed AD are intended to ensure airplane 
survivability in the event of damage to fully powered flight control 
systems.

DATES: Comments must be received by August 3, 1994.

ADDRESSES: Submit comments in triplicate to the Federal Aviation 
Administration (FAA), Transport Airplane Directorate, ANM-103, 
Attention: Rules Docket No. 94-NM-32-AD, 1601 Lind Avenue SW., Renton, 
Washington 98055-4056. Comments may be inspected at this location 
between 9 a.m. and 3 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, suite 210C, 1669 Phoenix Parkway, Atlanta, 
Georgia.

FOR FURTHER INFORMATION CONTACT: Thomas Peters, Aerospace Engineer, 
Flight Test Branch, ACE-160A, FAA, Small Airplane Directorate, Atlanta 
Aircraft Certification Office, Suite 210C, 1669 Phoenix Parkway, 
Atlanta, Georgia 30349; telephone (404) 991-3915; fax (404) 991-3606.

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 94-NM-32-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. 94-NM-32-AD, 1601 Lind Avenue SW., Renton, Washington 98055-
4056.

Discussion

    In July 1989, a transport category airplane was involved in an 
accident in Sioux City, Iowa, resulting in the deaths of 110 passengers 
and one crewmember. The National Transportation Safety Board (NTSB) 
identified the catastrophic disintegration of the stage 1 fan disk of 
one of the engines as a probable cause of the accident. The resulting 
debris damaged the hydraulic systems that power the flight controls, 
resulting in the loss of virtually all control capability.
    Following the accident, the Administrator of the Federal Aviation 
Administration convened a Systems Review Task Force (SRTF) to 
investigate means for enhancing airplane survivability following damage 
to fully powered flight control systems. The SRTF formed working groups 
to perform these investigations for specific airplane models to 
determine what actions could be effective in protecting other transport 
category airplanes with powered flight control systems from similar 
engine or systems failures.
    The SRTF working group assigned to review Lockheed Model L-1011-385 
series airplanes has completed its review of the Model L-1011-385 
design, including existing service bulletins, and has issued a report 
recommending accomplishment of certain modifications and inspections 
described in a Lockheed L-1011-385 service bulletin. A copy of the 
report is contained in the Rules Docket for this AD action.
    The FAA has reviewed and approved Lockheed Service Bulletin 093-27-
301 [``Flight Controls, Modifications and Inspections, Collector 
Service Bulletin'' (CSB)], dated June 9, 1992, which was issued in 
response to the SRTF report. Accomplishment of the inspections and 
modifications specified in the CSB will enhance the controllability of 
the airplane in the unlikely event of flight control malfunction or 
failure.
    The CSB lists 34 individual service bulletins that describe 
procedures for accomplishment of various modifications and inspections 
recommended by the SRTF. The FAA has determined that the modifications 
and inspections described in 8 of the 34 service bulletins identified 
in the CSB must be accomplished in order to ensure airplane 
survivability in the event of damage to fully powered flight control 
systems. All 8 of these service bulletins have been reviewed and 
approved by the FAA. The remaining 26 service bulletins contained in 
the CSB address service problems and systems enhancements that are not 
directly related to increasing in-flight controllability of the 
airplane.
    Six of the eight individual Lockheed service bulletins discussed 
previously describe procedures for various modifications and 
inspections involving the flight controls and are identified as 
follows:
    1. Alert Service Bulletin 093-27-A102, dated March 13, 1974, 
``Flight Controls--Pitch and Roll Disconnects, Inspection of Cable 
Attachments.''
    2. Service Bulletin 093-27-178, dated April 30, 1979, ``Flight 
Controls--Horizontal Stabilizer--Pitch Override Bungee Fasteners Torque 
Verification.''
    3. Service Bulletin 093-27-200, Revision 2, dated September 28, 
1982, ``Flight Controls--Aileron and Horizontal Stabilizer Control 
Systems--Pitch and Roll Disconnect Handle Support Bosses and Disconnect 
Mechanism Inspection/Modification.''
    4. Service Bulletin 093-27-279, Revision 1, dated February 1, 1984, 
``Flight Controls--Stabilizer Servo Cross-Tie Interlock Bungee 
Inspection/Modification and Bracket Modification.''
    5. Service Bulletin 093-27-289, dated December 3, 1984, ``Control 
Wheel Roll Interconnect Inspection.''
    6. Service Bulletin 093-27-292, Revision 3, dated March 28, 1991, 
``Flight Controls--Horizontal Stabilizer Control System--Modification 
of Torque Tube Assembly Support Brackets.
    One of the eight individual service bulletins describes procedures 
for modification of the doors and is identified as follows:
    7. Service Bulletin 093-52-061, Revision 1, dated November 1, 1974, 
``Doors--Ram Air Turbine Doors--Modification of Linkage.
    The eighth individual service bulletin describes procedures for 
modification of the horizontal stabilizers and is identified as 
follows:
    8. Service Bulletin 093-55-030, Revision 1, dated March 20, 1991, 
``Stabilizers--Horizontal Stabilizers--Left and Right Pivot Bearing 
Assembly--Replacement of Setscrews with Safety Wired Fillister Head 
Screws.
    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 various modifications and inspections of the 
flight controls, doors, and horizontal stabilizers. The actions would 
be required to be accomplished in accordance with the CSB described 
previously.
    There are approximately 236 Model L-1011-385 series 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, that 
it would take approximately 87 work hours per airplane to accomplish 
the proposed actions, and that the average labor rate is $55 per work 
hour. Required parts for certain modifications would be supplied by the 
manufacturer at no cost to operators. Required parts for certain other 
modifications would be minimal in cost. Based on these figures, the 
total cost impact of the proposed AD on U.S. operators is estimated to 
be $559,845, or $4,785 per airplane.
    The total cost impact figure discussed above is 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.
    The number of required work hours, as indicated above, is presented 
as if the accomplishment of the actions proposed in this AD were to be 
conducted as ``stand alone'' actions. However, the 4-year compliance 
time specified in paragraph (a) of this proposed AD should allow ample 
time for the modifications and inspections to be accomplished 
coincidentally with scheduled major airplane inspection and maintenance 
activities, thereby minimizing the costs associated with special 
airplane scheduling.
    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 14 
CFR part 39 of the Federal Aviation Regulations as follows:

PART 39--AIRWORTHINESS DIRECTIVES

    1. The authority citation for part 39 continues to read as follows:

    Authority: 49 U.S.C. App. 1354(a), 1421 and 1423; 49 U.S.C. 
106(g); and 14 CFR 11.89.


Sec. 39.13  [Amended]

    2. Section 39.13 is amended by adding the following new 
airworthiness directive:

Lockheed Aeronautical Systems Company: Docket 94-NM-32-AD.

    Applicability: Model L-1011-385 series airplanes; as listed in 
Lockheed Service Bulletin 093-27-301 [``Flight Controls--
Modifications and Inspections--Collector Service Bulletin'' (CSB)], 
dated June 9, 1992; certificated in any category.
    Compliance: Required as indicated, unless accomplished 
previously.
    To ensure airplane survivability in the event of damage to fully 
powered flight control systems, accomplish the following:
    (a) Within 4 years after the effective date of this AD, 
accomplish modifications and inspections of the flight controls, 
modification of the doors, and modification of the horizontal 
stabilizers, in accordance with Lockheed Service Bulletin 093-27-301 
[``Flight Controls--Modifications and Inspections--Collector Service 
Bulletin'' (CSB)], dated June 9, 1992 (hereinafter referred to as 
the CSB). This paragraph requires accomplishment of certain Lockheed 
service bulletins identified in the CSB, as listed below. 
Modifications or inspections accomplished previously in accordance 
with earlier revisions of the service bulletins listed below are 
acceptable for compliance with this AD.

------------------------------------------------------------------------
                                Revision                                
    Service bulletin No.         level            Date of issuance      
------------------------------------------------------------------------
093-27-A102 (Alert Service    Original....  March 13, 1974.             
 Bulletin).                                                             
093-27-178..................  Original....  April 30, 1979.             
093-27-200..................  2...........  September 28, 1982.         
093-27-279..................  1...........  February 1, 1984.           
093-27-289..................  Original....  December 3, 1984.           
093-27-292..................  3...........  March 28, 1991.             
093-52-061..................  1...........  November 1, 1974.           
093-55-030..................  1...........  March 20, 1991.             
------------------------------------------------------------------------

    Note 1: Paragraph (a) of this AD does not require accomplishment 
of any of the service bulletins listed in the CSB other than those 
identified above.

    Note 2: Accomplishment of the actions described in Lockheed 
Service Bulletin 093-27-280, dated December 16, 1983, is considered 
an acceptable means of compliance for accomplishment of the 
inspection and modification described in Lockheed Service Bulletin 
093-27-279, Revision 1, dated February 1, 1984.

    (b) 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 Aircraft Certification 
Office (ACO), FAA, Small Airplane Directorate. 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.

    (c) 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 3, 1994.
Darrell M. Pederson,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 94-14020 Filed 6-8-94; 8:45 am]
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