[Federal Register Volume 65, Number 159 (Wednesday, August 16, 2000)]
[Rules and Regulations]
[Pages 49899-49901]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 00-20505]


-----------------------------------------------------------------------

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 99-NM-233-AD; Amendment 39-11863; AD 2000-16-08]
RIN 2120-AA64


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

AGENCY: Federal Aviation Administration, DOT.

ACTION: Final rule.

-----------------------------------------------------------------------

SUMMARY: This amendment supersedes an existing airworthiness directive 
(AD), applicable to certain Lockheed Model L-1011-385 series airplanes, 
that currently requires repetitive inspections to detect cracking of 
the canted pressure bulkhead at fuselage station (FS) 1212, and 
repetitive 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 requires that the 
initial inspections be accomplished at a reduced threshold. This 
amendment is prompted by a report of fatigue cracking of the canted 
pressure bulkhead at FS 1212. The actions specified by this AD are 
intended 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.

DATES: Effective September 20, 2000.
    The incorporation by reference of Lockheed Service Bulletin 093-53-
277, Revision 1, dated November 19, 1998, as listed in the regulations, 
is approved by the Director of the Federal Register as of September 20, 
2000.
    The incorporation by reference of Lockheed Service Bulletin 093-53-
277, dated July 2, 1996, as listed in the regulations, was approved 
previously by the Director of the Federal Register as of October 25, 
1996 (61 FR 53044, October 10, 1996).

ADDRESSES: The service information referenced in this AD may be 
obtained from Lockheed Martin Aircraft & Logistics Center, 120 Orion 
Street, Greenville, South Carolina 29605. 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, Small Airplane Directorate, Atlanta Aircraft 
Certification Office, One Crown Center, 1895 Phoenix Boulevard, suite 
450, Atlanta, Georgia; or at the Office of the Federal Register, 800 
North Capitol Street, NW., suite 700, Washington, DC.

FOR FURTHER INFORMATION CONTACT: Thomas Peters, Program Manager, 
Program Management and Services Branch, ACE-118A, FAA, Small Airplane 
Directorate, Atlanta Aircraft Certification Office, One Crown Center, 
1895 Phoenix Boulevard, suite 450, Atlanta, Georgia 30349; telephone 
(770) 703-6063, fax (770) 703-6097.

SUPPLEMENTARY INFORMATION: A proposal to amend part 39 of the Federal 
Aviation Regulations (14 CFR part 39) by superseding AD 96-20-10, 
amendment 39-9776 (61 FR 53044, October 10, 1996), which is applicable 
to certain Lockheed Model L-1011-385 series airplanes, was published in 
the Federal Register on October 6, 1999 (64 FR 54230). The action 
proposed to supersede AD 96-20-10 to continue to require repetitive 
inspections to detect cracking of the canted pressure bulkhead at FS 
1212, and repetitive 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 action also 
proposed to require that the initial inspections be accomplished at a 
reduced threshold.

Comment Received

    Interested persons have been afforded an opportunity to participate 
in the making of this amendment. Due consideration has been given to 
the single comment received.
    The commenter requests that the FAA revise paragraphs (b)(1)(i) and 
(b)(1)(ii) of the proposal to reference section 53-11-00, Figure 854, 
of the L-1011 Structural Repair Manual (SRM), dated March 15, 1999. 
Lockheed Repair Drawing LCC-7622-385 is referenced in the proposal as 
the appropriate source of service information for identifying areas in 
which cracking may be found. The commenter indicates that the drawing 
has been revised and incorporated into the SRM since the release of 
Lockheed Service Bulletin 093-53-277, Revision 1, dated November 19, 
1998. The commenter states that confusion could arise due to the nature 
of certain LCC drawings that are not formally controlled or released; 
operators could have the outdated version of the drawing on file. The 
revised LCC drawing and new SRM figure provide more detail of the 
inspection area and more detail of the repair instructions on the 
bulkhead than those specified in the original version of the drawing.
    The FAA concurs with the commenter's request to reference the 
revised service information, and has revised the final rule 
accordingly. However, the FAA finds that both repair drawings 
adequately identify the areas in which cracking may be found.
    Therefore, the FAA has added a note to the final rule to give 
operators credit for using the version of the repair drawing cited in 
the proposal.

Conclusion

    After careful review of the available data, including the comment 
noted above, the FAA has determined that air safety and the public 
interest require the adoption of the rule with the change previously 
described. The FAA has determined that this change will neither 
increase the economic burden on any operator nor increase the scope of 
the AD.

Cost Impact

    There are approximately 235 airplanes of the affected design in the 
worldwide fleet. The FAA estimates that 116 airplanes of U.S. registry 
will be affected by this AD. The requirements of this AD will not add 
any new additional economic burden on affected operators other than the 
costs that are associated with beginning the inspection at an earlier 
time than would have been required by AD 96-20-10 (initial inspection 
is now required within 18,000 flight cycles, rather than 20,000 flight 
cycles).
    The actions that are currently required by AD 96-20-10, and are 
retained in this AD, take approximately 5 work hours per airplane to 
accomplish, at an average labor rate of $60 per work hour. Based on 
these figures, the cost impact of the currently required actions on 
U.S. operators is estimated to be $34,800, or $300 per airplane, per 
inspection cycle.
    The 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.

[[Page 49900]]

Regulatory Impact

    The regulations adopted herein will not have a substantial direct 
effect 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, it 
is determined that this final rule does not have federalism 
implications under Executive Order 13132.
    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 U.S.C. 106(g), 40113, 44701.


Sec. 39.13  [Amended]

    2. Section 39.13 is amended by removing amendment 39-9776 (61 FR 
53044, October 10, 1996), and by adding a new airworthiness directive 
(AD), amendment 39-11863, to read as follows:

2000-16-08 Lockheed: Amendment 39-11863. Docket 99-NM-233-AD. 
Supersedes AD 96-20-10, Amendment 39-9776.

    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)(1) 
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:

Repetitive Inspections

    (a) Perform a detailed 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 Service 
Bulletin 093-53-277, dated July 2, 1996, or Revision 1, dated 
November 19, 1998; at the earlier of the times specified in 
paragraphs (a)(1) and (a)(2) of this AD. Thereafter, repeat these 
inspections at intervals not to exceed 1,000 flight cycles.
    (1) Prior to the accumulation of 20,000 total flight cycles, or 
within 60 days after October 25, 1996 (the effective date of AD 96-
20-10), whichever occurs later; or
    (2) Prior to the accumulation of 18,000 total flight cycles, or 
within 60 days after the effective date of this AD, whichever occurs 
later.

    Note 2: For the purposes of this AD, a detailed visual 
inspection is defined as: ``An intensive visual examination of a 
specific structural area, system, installation, or assembly to 
detect damage, failure, or irregularity. Available lighting is 
normally supplemented with a direct source of good lighting at 
intensity deemed appropriate by the inspector. Inspection aids such 
as mirror, magnifying lenses, etc., may be used. Surface cleaning 
and elaborate access procedures may be required.''

Repair

    (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 
Lockheed Service Bulletin 093-53-277, dated July 2, 1996, or 
Revision 1, dated November 19, 1998, repair in accordance with 
Section 53-11-00, Figure 854, of the L-1011 Structural Repair Manual 
(SRM), dated March 15, 1999. Accomplishment of a repair in 
accordance with this paragraph constitutes terminating action for 
the repetitive inspections required by paragraph (a) of this AD at 
the repaired location only. Or
    (ii) If the cracking is found in an area that is not specified 
in Lockheed Service Bulletin 093-53-277, dated July 2, 1996, or 
Revision 1, dated November 19, 1998, repair in accordance with a 
method approved by the Manager, Atlanta Aircraft Certification 
Office (ACO), FAA, Small Airplane Directorate.

    Note 3: Lockheed Repair Drawing LCC-7622-385 also is considered 
an acceptable source of service information for the accomplishment 
of the requirements of paragraph (b)(1)(i) of this AD.

    (2) Replace the entire web with a new web in accordance with 
Lockheed Service Bulletin 093-53-277, dated July 2, 1996, or 
Revision 1, dated November 19, 1998. Such replacement constitutes 
terminating action for the repetitive inspections required by 
paragraph (a) of this AD.

Alternative Methods of Compliance

    (c)(1) 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.
    (2) Alternative methods of compliance, approved previously in 
accordance with AD 96-20-10, amendment 39-9776, are approved as 
alternative methods of compliance with paragraph (b) of this AD.

    Note 4: Information concerning the existence of approved 
alternative methods of compliance with this AD, if any, may be 
obtained from the Atlanta ACO.

Special Flight Permits

    (d) Special flight permits may be issued in accordance with 
Secs. 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.

Incorporation by Reference

    (e) Except as provided by paragraph (b)(1)(ii) of this AD, the 
actions shall be done in accordance with Lockheed Service Bulletin 
093-53-277, dated July 2, 1996; or Lockheed Service Bulletin 093-53-
277, Revision 1, dated November 19, 1998. Revision 1 of Lockheed 
Service Bulletin 093-53-277 contains the following list of effective 
pages:

[[Page 49901]]



----------------------------------------------------------------------------------------------------------------
                                              Revision level shown on
                Page number                             page                        Date shown on page
----------------------------------------------------------------------------------------------------------------
1-3, 5....................................  1..........................  November 19, 1998.
4, 6-9....................................  Original...................  July 2, 1996.
----------------------------------------------------------------------------------------------------------------

    (1) The incorporation by reference of Lockheed L-1011 Service 
Bulletin 093-53-277, Revision 1, dated November 19, 1998, is 
approved by the Director of the Federal Register, in accordance with 
5 U.S.C. 552(a) and 1 CFR part 51.
    (2) The incorporation by reference of Lockheed Service Bulletin 
093-53-277, dated July 2, 1996, was approved previously by the 
Director of the Federal Register as of October 25, 1996 (61 FR 
53044, October 10, 1996).
    (3) Copies may be obtained from Lockheed Martin Aircraft & 
Logistics Center, 120 Orion Street, Greenville, South Carolina 
29605. Copies may be inspected at the FAA, Transport Airplane 
Directorate, 1601 Lind Avenue, SW., Renton, Washington; or at the 
FAA, Small Airplane Directorate, Atlanta Aircraft Certification 
Office, One Crown Center, 1895 Phoenix Boulevard, suite 450, 
Atlanta, Georgia; or at the Office of the Federal Register, 800 
North Capitol Street, NW., suite 700, Washington, DC.
    (f) This amendment becomes effective on September 20, 2000.

    Issued in Renton, Washington, on August 8, 2000.
Donald L. Riggin,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 00-20505 Filed 8-15-00; 8:45 am]
BILLING CODE 4910-13-U