[Federal Register Volume 61, Number 198 (Thursday, October 10, 1996)]
[Rules and Regulations]
[Pages 53044-53046]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 96-25305]


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DEPARTMENT OF TRANSPORTATION
14 CFR Part 39

[Docket No. 96-NM-240-AD; Amendment 39-9776; AD 96-20-10]
RIN 2120-AA64


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

AGENCY: Federal Aviation Administration, DOT.

ACTION: Final rule; request for comments.

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SUMMARY: This amendment adopts a new airworthiness directive (AD) that 
is applicable to certain Lockheed Model L-1011-385 series airplanes. 
This action requires inspections to detect cracking of the canted 
pressure bulkhead at fuselage station (FS) 1212, and inspections to 
detect cracking of the web at the fastener rows of the vertical 
stiffener-to-web; and repair or replacement of the web with a new web, 
if necessary. This amendment is prompted by a report of fatigue 
cracking of the canted pressure bulkhead at FS 1212. The actions 
specified in this AD are intended to detect and correct such fatigue 
cracking, which could result in blowout of a panel between adjacent 
stiffeners and consequent cabin depressurization.

DATES: Effective October 25, 1996.
    The incorporation by reference of certain publications listed in 
the regulations is approved by the Director of the Federal Register as 
of October 25, 1996.
    Comments for inclusion in the Rules Docket must be received on or 
before December 9, 1996.

ADDRESSES: Submit comments in triplicate to the Federal Aviation 
Administration (FAA), Transport Airplane Directorate, ANM-103, 
Attention: Rules Docket No. 96-NM-240-AD, 1601 Lind Avenue, SW., 
Renton, Washington 98055-4056.
    The service information referenced in this AD may be obtained from 
Lockheed Aeronautical Systems Support Company (LASSC), Field Support 
Department, Dept. 693, Zone 0755, 2251 Lake Park Drive, Smyrna, 
Georgia. This information may be examined 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.

FOR FURTHER INFORMATION CONTACT: Curtis Jackson, Aerospace Engineer, 
Airframe Branch, ACE-117A, FAA, Atlanta Aircraft Certification Office, 
Small Airplane Directorate, Campus Building, 1701 Columbia Avenue, 
suite 2-160, College Park, Georgia 30337-2748; telephone (404) 305-
7358; fax (404) 305-7348.

SUPPLEMENTARY INFORMATION: The FAA received a report indicating that 
fatigue cracking was found of the canted pressure bulkhead at fuselage 
station (FS) 1212 on a Lockheed Model L-1011-385 series airplane that 
had accumulated 31,749 total landings. Three vertical cracks, each 
approximately 11 inches long, were found in the areas of left buttock 
line (LBL) 30.0, LBL 10.0, and right buttock line (RBL) 22.5 along the 
fastener rows of the vertical stiffener-to-web. Subsequently, another 
operator found similar fatigue cracking on two other airplanes. Such 
fatigue cracking, if not detected and corrected in a timely manner, 
could result in blowout of a panel between adjacent stiffeners and 
consequent cabin depressurization.

Explanation of Relevant Service Information

    The FAA has reviewed and approved Lockheed L-1011 Service Bulletin 
093-53-277, dated July 2, 1996, which describes procedures for 
repetitive close visual inspections to detect cracking of the entire 
aft surface of the canted pressure bulkhead at FS 1212 between LBL 103 
and RBL 103, and repetitive optical inspections to detect cracking of 
the web at the fastener rows of the vertical stiffener-to-web; and 
repair or replacement of the web with a new web, if necessary.

Explanation of the Requirements of the Rule

    Since an unsafe condition has been identified that is likely to 
exist or develop on other Lockheed Model L-1011-385 series airplanes of 
the same type design, this AD is being issued to detect and correct 
fatigue cracking of the canted pressure bulkhead at FS 1212, which 
could result in blowout of a panel between adjacent stiffeners and 
consequent cabin depressurization. This AD requires repetitive close 
visual inspections to detect cracking of the entire aft surface of the 
canted pressure bulkhead at FS 1212 between LBL 103

[[Page 53045]]

and RBL 103, and repetitive optical inspections to detect cracking of 
the web at the fastener rows of the vertical stiffener-to-web; and 
repair or replacement of the web with a new web, if necessary. The 
inspections, certain repairs, and replacement are required to be 
accomplished in accordance with the service bulletin described 
previously. Other repairs are required to be accomplished in accordance 
with a method approved by the FAA.
    This is considered to be interim action until final action is 
identified, at which time the FAA may consider further rulemaking.

Determination of Rule's Effective Date

    Since a situation exists that requires the immediate adoption of 
this regulation, it is found that notice and opportunity for prior 
public comment hereon are impracticable, and that good cause exists for 
making this amendment effective in less than 30 days.

Comments Invited

    Although this action is in the form of a final rule that involves 
requirements affecting flight safety and, thus, was not preceded by 
notice and an opportunity for public comment, comments are invited on 
this rule. Interested persons are invited to comment on this 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 under the caption 
ADDRESSES. All communications received on or before the closing date 
for comments will be considered, and this rule may be amended in light 
of the comments received. Factual information that supports the 
commenter's ideas and suggestions is extremely helpful in evaluating 
the effectiveness of the AD action and determining whether additional 
rulemaking action would be needed.
    Comments are specifically invited on the overall regulatory, 
economic, environmental, and energy aspects of the rule that might 
suggest a need to modify the 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 that 
summarizes each FAA-public contact concerned with the substance of this 
AD will be filed in the Rules Docket.
    Commenters wishing the FAA to acknowledge receipt of their comments 
submitted in response to this rule must submit a self-addressed, 
stamped postcard on which the following statement is made: ``Comments 
to Docket Number 96-NM-240-AD.'' The postcard will be date stamped and 
returned to the commenter.

Regulatory Impact

    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.
    The FAA has determined that this regulation is an emergency 
regulation that must be issued immediately to correct an unsafe 
condition in aircraft, and that it is not a ``significant regulatory 
action'' under Executive Order 12866. It has been determined further 
that this action involves an emergency regulation under DOT Regulatory 
Policies and Procedures (44 FR 11034, February 26, 1979). If it is 
determined that this emergency regulation otherwise would be 
significant under DOT Regulatory Policies and Procedures, a final 
regulatory evaluation will be prepared and placed in the Rules Docket.A 
copy of it, if filed, 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 U.S.C. 106(g), 40113, 44701.


Sec. 39.13    [Amended]

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

96-20-10  Lockheed: Amendment 39-9776. Docket 96-NM-240-AD.

    Applicability: Model L-1011-385 series airplanes; serial numbers 
1013 through 1250 inclusive; 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 (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 detect and correct fatigue cracking of the canted pressure 
bulkhead at fuselage station (FS) 1212, which could result in 
blowout of a panel between adjacent stiffeners and consequent cabin 
depressurization, accomplish the following:
    (a) Prior to the accumulation of 20,000 total landings, or 
within 60 days after the effective date of this AD, whichever occurs 
later: Perform a close visual inspection to detect cracking of the 
entire aft surface of the canted pressure bulkhead at FS 1212 
between left buttock line (LBL) 103 and right buttock line (RBL) 
103; and perform an optical inspection using a borescope or other 
optical device to detect cracking of the web at the fastener rows of 
the vertical stiffener-to-web; in accordance with Lockheed L-1011 
Service Bulletin 093-53-277, dated July 2, 1996. Thereafter, repeat 
these inspections at intervals not to exceed 1,000 landings.
    (b) If any cracking is found during any inspection required by 
paragraph (a) of this AD, prior to further flight, accomplish either 
paragraph (b)(1) or (b)(2) of this AD.
    (1) Accomplish either paragraph (b)(1)(i) or (b)(1)(ii) of this 
AD, as applicable.
    (i) If the cracking is found in an area that is specified in 
Lockheed Repair Drawing LCC-7622-385, repair in accordance with the 
service bulletin. Accomplishment of a repair constitutes terminating 
action for the repetitive inspections required by paragraph (a) of 
this AD at the repaired location. Or
    (ii) If the cracking is found in an area that is not specified 
in Lockheed Repair Drawing LCC-7622-385, repair in accordance with a 
method approved by the Manager, Atlanta Aircraft Certification 
Office (ACO), FAA, Small Airplane Directorate.
    (2) Replace the entire web with a new web in accordance with the 
service bulletin. Such replacement constitutes terminating action 
for the repetitive inspections required by paragraph (a) 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 2: Information concerning the existence of approved 
alternative methods of compliance with this AD, if any, may be 
obtained from the Atlanta ACO.


[[Page 53046]]


    (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.
    (e) The actions shall be done in accordance with Lockheed 
Service Bulletin 093-53-277, dated July 2, 1996. 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 (LASSC), 
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.
    (f) This amendment becomes effective on October 25, 1996.

    Issued in Renton, Washington, on September 26, 1996.
James V. Devany,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 96-25305 Filed 10-9-96; 8:45 am]
BILLING CODE 4910-13-U