[Federal Register Volume 60, Number 201 (Wednesday, October 18, 1995)]
[Rules and Regulations]
[Pages 53860-53862]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 95-25028]



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DEPARTMENT OF TRANSPORTATION
14 CFR Part 39

[Docket No. 94-NM-254-AD; Amendment 39-9392; AD 95-21-07]


Airworthiness Directives; Lockheed Model L-1011-385 Series 
Airplanes

AGENCY: Federal Aviation Administration, DOT.

ACTION: Final rule.

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SUMMARY: This amendment adopts a new airworthiness directive (AD), 
applicable to Lockheed Model L-1011-385 series airplanes, that requires 
modifications of various fluid drainage areas of the fuselage. This 
amendment is prompted by incidents involving corrosion and fatigue 
cracking in transport category airplanes that are approaching or have 
exceeded their economic design goal; these incidents have jeopardized 
the airworthiness of the affected airplanes. The actions specified by 
this AD are intended to prevent degradation of the structural 
capabilities of the affected airplanes due to problems associated with 
corrosion.

DATES: Effective November 17, 1995.
    The incorporation by reference of certain publications listed in 
the regulations is approved by the Director of the Federal Register as 
of November 17, 1995.

ADDRESSES: The service information referenced in this AD may be 
obtained from Lockheed Aeronautical Systems Support Company, Field 
Support Department, Dept. 693, Zone 0755, 2251 Lake Park Drive, Smyrna, 
Georgia. This information may be examined at the Federal Aviation 
Administration (FAA), Transport Airplane Directorate, Rules Docket, 
1601 Lind Avenue, SW., Renton, Washington; or at the FAA, Atlanta 
Aircraft Certification Office, Small Airplane Directorate, Campus 
Building, 1701 Columbia Avenue, Suite 2-160, College Park, Georgia 
30337-2748; or at the Office of the Federal Register, 800 North Capitol 
Street, NW., suite 700, Washington, DC.

FOR FURTHER INFORMATION CONTACT: Thomas Peters, Flight Test Branch, 
ACE-160A, 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: A proposal to amend part 39 of the Federal 
Aviation Regulations (14 CFR part 39) to include an airworthiness 
directive (AD) that is applicable to Model L-1011-385 series airplanes 
was published in the Federal Register on February 22, 1995 (60 FR 
9796). That action proposed to require the accomplishment of 
modifications, installations, and other actions relative to fluid 
drainage areas of the fuselage.
    Interested persons have been afforded an opportunity to participate 
in the making of this amendment. Due consideration has been given to 
the comments received.
    One commenter supports the proposal.
    One commenter requests that the proposal be revised to remove the 
requirement to comply with the procedures described in Lockheed Service 
Bulletin 093-53-095, Revision 2, dated June 22, 1987. This specific 
service bulletin describes procedures for installing drainage 
provisions at the pressure deck of the nose landing gear. The commenter 
states that these procedures are listed as part of Corrosion Task C-53-
110-05 in the Model L-1011 Corrosion Prevention and Control Program 
(Lockheed Document LR 31889), and are mandated by AD 93-20-03, 
amendment 39-8710 (58 FR 60775, November 18, 1993). The FAA does not 
concur. Corrosion Task C-53-110-05 entails an inspection for corrosion 
of the pressure deck area above the nose landing gear compartment. An 
additional part of that Task is the installation of an insulation 
standoff modification that is described in Appendix D of Lockheed 
Document 

[[Page 53861]]
LR 31889. However, the actions proposed in the notice, and described in 
Lockheed Service Bulletin 093-53-095, go beyond those currently 
mandated by AD 93-20-03. These new actions require the installation of 
two drain valves and the installation of additional drain holes. The 
FAA has determined that these actions must be accomplished in order to 
positively address the unsafe condition presented by the problems 
associated with corrosion.
    This commenter also requests that the final rule be revised to 
allow the installation of any of the optional insulation standoffs 
specified in Appendix D [``Insulation Batts Standoffs (Bilges)''] of 
Lockheed Document LR 31889. The commenter points out that Lockheed 
Service Bulletin 93-53-095 specifically calls for the installation of 
stud-type standoffs, but Appendix D of the Lockheed Document allows the 
use of several options for maintaining a space between structure and 
insulation. This particular commenter, a U.S. operator, elected to 
install (previously) the ``egg crate'' option, and requests that the AD 
indicate that use of such an option is considered to be in compliance 
with the intent of the rule. The FAA concurs. A new Note 4 has been 
added to the final rule to specify this.
    Paragraph (a)(2) of the final rule has been revised to correct a 
typographical error that appeared in the published version of the 
notice. In the notice, the compliance terminology of that paragraph was 
stated as, ``* * * that has exceeded the IA for that zone as December 
17, 1994* * *'' However, it should have read, ``* * * as of December 
17, 1994* * *'' The final rule has been corrected accordingly.
    Additionally, the final rule has been revised to clarify that the 
issuance date of Lockheed Document LR 31889 is April 15, 1994.
    After careful review of the available data, including the comments 
noted above, the FAA has determined that air safety and the public 
interest require the adoption of the rule with the changes previously 
described. The FAA has determined that these changes will neither 
increase the economic burden on any operator nor increase the scope of 
the AD.
    There are approximately 241 Model L-1011-385 series airplanes of 
the affected design in the worldwide fleet. The FAA estimates that 117 
airplanes of U.S. registry will be affected by this proposed AD. It 
will take approximately 236 work hours per airplane to accomplish the 
required actions, including time to gain access and close up. The 
average labor rate is currently $60 per work hour. Based on these 
figures, the total cost impact of the requirements of this AD on U.S. 
operators is estimated to be $1,656,720, or $14,160 per airplane.
    The total cost impact figure discussed above is based on 
assumptions that no operator has yet accomplished any of the 
requirements of this AD action, and that no operator would accomplish 
those actions in the future if this AD were not adopted.
    The regulations adopted herein will 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 final 
rule does not have sufficient federalism implications to warrant the 
preparation of a Federalism Assessment.
    For the reasons discussed above, I certify that this action (1) is 
not a ``significant regulatory action'' under Executive Order 12866; 
(2) is not a ``significant rule'' under DOT Regulatory Policies and 
Procedures (44 FR 11034, February 26, 1979); and (3) 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 final evaluation has been prepared for this action 
and it is contained in the Rules Docket. A copy of it may be obtained 
from the Rules Docket at the location provided under the caption 
ADDRESSES.

List of Subjects in 14 CFR Part 39

    Air transportation, Aircraft, Aviation safety, Incorporation by 
reference, Safety.

Adoption of the Amendment

    Accordingly, pursuant to the authority delegated to me by the 
Administrator, the Federal Aviation Administration amends 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 USC 106(g), 40101, 40113, 44701.


Sec. 39.13  [Amended]

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

95-21-07 Lockheed: Amendment 39-9392. Docket 94-NM-254-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 
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 (b) 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.
    To prevent structural failure due to the problems associated 
with corrosion accomplish the following:
    (a) Accomplish the modifications, installations, and inspections 
described in the Lockheed service bulletins listed in Section 7.2 of 
Lockheed Document Number LR 31889, ``Corrosion Prevention and 
Control Program, TriStar L-1011,'' Revision A, dated April 15, 1994 
(hereafter referred to as ``the Document''), in accordance with the 
following schedule:

    Note 2: Airplanes on which the modifications, installations, and 
inspections required by this paragraph have been accomplished prior 
to the effective date of this AD or during production are considered 
to be in compliance with this paragraph.

    Note 3: Airplanes on which the modifications, installations, and 
inspections required by this paragraph have been accomplished 
previously in accordance with an earlier version of the applicable 
service bulletin listed in Section 7.2 of the Document, are 
considered to be in compliance with this paragraph.

    Note 4: In lieu of the installation of insulation batts 
standoffs (stud-type) specified in Lockheed Service Bulletin 093-53-
095, Revision 2, dated June 22, 1987, operators may install any of 
the optional insulation batts standoffs specified in Appendix D of 
the Document. Such installation is considered to be in compliance 
with these requirements of this AD.

    Note 5: ``Airplane zones,'' ``implementation ages,'' and 
``repeat intervals,'' as referred to in this paragraph, are 
specified in Section 4.3 of the Document.

    (1) For modifications, installations, and inspections located in 
an airplane zone that has not yet exceeded the ``implementation 
age'' (IA) for that zone as of December 17, 1994 (one year after the 
effective date of AD 93-20-03, amendment 39-8710): Compliance is 
required no later than the IA plus the repeat (R) interval for the 
applicable zone.
    (2) For modifications, installations, and inspections located in 
an airplane zone that 

[[Page 53862]]
has exceeded the IA for that zone as of December 17, 1994: Compliance 
is required within one R interval for that zone, measured from 
December 17, 1994.
    (3) For airplanes that are 20 years old or older as of December 
17, 1994: Accomplishment of the modifications, installation, and 
inspections is required within one R interval for the applicable 
airplane zone, but not to exceed 6 years, measured from December 17, 
1994, whichever occurs first.
    (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), ACE-115A, 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 6: 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.
    (d) The actions shall be done in accordance with Lockheed 
Document Number LR 31889, ``Corrosion Prevention and Control 
Program, TriStar L-1011,'' Revision A, dated April 15, 1994, which 
contains the following list of effective pages:

------------------------------------------------------------------------
                                   Revision level                       
           Page No.                shown on page      Date shown on page
------------------------------------------------------------------------
0.1-0.4, 0.6, 1.1, 1.3, 2.1,    Original...........  March 15, 1991.    
 2.2, 3.1-3.4, 4.1-4.8, 4.12,                                           
 4.14, 4.15, 4.20, 4.24, 4.28,                                          
 4.30-4.33, 4.36-4.41, 5.2,                                             
 6.1, A.1, A.2, B.3, B.5-B.13,                                          
 C.2-C.10.                                                              
0.5, 1.2, 4.9-4.11, 4.13, 4.16- Revision A.........  April 15, 1994.    
 4.19, 4.21-4.23, 4.25-4.27,                                            
 4.29, 4.34, 4.35, 5.1, 7.1-                                            
 7.4, B.2, B.4, C.1, D.1.                                               
------------------------------------------------------------------------

    This incorporation by reference was approved by the Director of 
the Federal Register in accordance with 5 U.S.C. 552(a) and 1 CFR 
part 51. Copies may be obtained from Lockheed Aeronautical Systems 
Support Company, Field Support Department, Dept. 693, Zone 0755, 
2251 Lake Park Drive, Smyrna, Georgia. Copies may be inspected at 
the FAA, Transport Airplane Directorate, 1601 Lind Avenue, SW., 
Renton, Washington; or at the FAA, Atlanta Aircraft Certification 
Office, Small Airplane Directorate, Campus Building, 1701 Columbia 
Avenue, Suite 2-160, College Park, Georgia; or at the Office of the 
Federal Register, 800 North Capitol Street, NW., suite 700, 
Washington, DC.
    (e) This amendment becomes effective on November 17, 1995.

    Issued in Renton, Washington, on October 3, 1995.
Darrell M. Pederson,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 95-25028 Filed 10-17-95; 8:45 am]
BILLING CODE 4910-13-U