AD Amdt-39-11202

[Federal Register Volume 64, Number 120 (Wednesday, June 23, 1999)]
[Rules and Regulations]
[Pages 33386-33390]
From the Federal Register Online via the Government Publishing Office [<a href="http://www.gpo.gov">www.gpo.gov</a>]
[FR Doc No: 99-15779]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 97-NM-11-AD; Amendment 39-11202; AD 99-13-08]
RIN 2120-AA64


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

AGENCY: Federal Aviation Administration, DOT.

ACTION: Final rule.

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SUMMARY: This amendment supersedes an existing airworthiness directive 
(AD), applicable to all Lockheed Model L-1011-385 series airplanes, 
that currently requires inspections to detect cracking and other 
discrepancies of certain web-to-cap fasteners of the rear spar between 
inner wing stations 310 and 343, and of the web area around those 
fasteners; and various follow-on actions. That AD also provides for an 
optional modification, which, if accomplished, would defer the 
initiation of the inspections for a certain period of time. This 
amendment requires accomplishment of the previously optional 
modification. This amendment is prompted by an FAA determination that 
the optional terminating modification specified in the existing AD must 
be accomplished within a specified period of time to ensure an 
acceptable level of safety of the affected fleet. The actions specified 
by this AD are intended to prevent fatigue cracking in the web of the 
rear spar of the wing, which could result in failure of the rear spar 
of the wing and consequent fuel spillage.

DATES: Effective July 28, 1999.
    The incorporation by reference of Lockheed L-1011 Service Bulletin 
093-57-218, dated April 11, 1996, as listed in the regulations, was 
approved previously by the Director of the Federal Register as of June 
27, 1996 (61 FR 29642, June 12, 1996).
    The incorporation by reference of certain other publications, as 
listed in the regulations, is approved by the Director of the Federal 
Register as of July 28, 1999.

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, Aerospace Engineer, 
Systems and Flight Test Branch, ACE-116A, FAA, Small Airplane 
Directorate, Atlanta Aircraft Certification Office, One Crown Center, 
1895 Phoenix Boulevard, Suite 450, Atlanta, Georgia 30337-2748; 
telephone (770) 703-6063; fax (770) 703-6097.

SUPPLEMENTARY INFORMATION: A proposal to amend part 39 of the Federal

[[Page 33387]]

Aviation Regulations (14 CFR part 39) by superseding AD 96-12-24, 
amendment 39-9667 (61 FR 29642, June 12, 1996), which is applicable to 
all Lockheed Model L-1011-385 series airplanes, was published in the 
Federal Register on November 25, 1997 (62 FR 62728). The action 
proposed to continue to require inspections to detect cracking and 
other discrepancies of certain web-to-cap fasteners of the rear spar 
between inner wing stations 310 and 343, and of the web area around 
those fasteners; and various follow-on actions. That action also 
proposed to require accomplishment of a previously optional 
modification.
    Interested persons have been afforded an opportunity to participate 
in the making of this amendment. Due consideration has been given to 
the comments received.

Support for the Proposal

    One commenter supports the proposed rule.

Request To Clarify the Inspection Requirements

    One commenter requests clarification of the subsequent inspections 
required by the proposed AD. The commenter states that the proposed AD 
does not clearly address the subsequent inspection program for Model L-
1011-385-3 series airplanes that have accomplished the rear spar 
modification for extensive cracking ``after June 27, 1996,'' because 
paragraph (a)(2) of the proposed AD only addresses spar replacements 
accomplished ``prior to June 27, 1996.''
    The FAA points out that the inspection thresholds in Table I of 
Lockheed Service Bulletin 093-57-218, Revision 1, dated September 9, 
1996 (which is referenced in the final rule as the appropriate source 
of service information), are calculated from the date of accomplishment 
of Lockheed Service Bulletin 093-57-215, dated April 11, 1996. In 
addition, the FAA considers that paragraph (e)(2) of the final rule 
adequately addresses the inspection requirements for operators that 
have accomplished the modification in accordance with Service Bulletin 
093-57-215. No change has been made to paragraph (a)(2) of the final 
rule.

Request for Additional Inspections and a Reduced Inspection 
Threshold

    One commenter requests revising the proposed AD to include 
additional inspections for detecting cracks that originate in the 
fastener holes, and to shorten the inspection thresholds after 
accomplishment of the cold working modification. The commenter adds 
that it recommends accomplishment of the modification as required by 
the proposed AD; however, the commenter does not consider that the 
modification should be used for complete reliance for crack prevention. 
Following accomplishment of the modification, the commenter recommends 
that certain other inspections of the wing rear spar web and upper cap 
be added to the inspection requirements of the proposed AD. The 
commenter suggests adding surface scan inspections using high frequency 
eddy current techniques, and ring probe inspections using low frequency 
eddy current techniques. The commenter also recommends that, instead of 
accomplishing the inspections at 5,000 landings, the inspections be 
accomplished at 500 flight cycles following the cold working 
modification.
    The commenter states that its recommendations are based on its 
service experience and a damage tolerance assessment (DTA). The 
commenter also states that, after modifying its entire fleet of Model 
L-1011-385-3 series airplanes in accordance with paragraph (d) of the 
proposed AD, subsequent cracking was found before 5,000 landings. The 
commenter adds that its service experience indicates that new or 
recurring cracks occur within 500 to 1,000 flight cycles after repair 
of the upper spar cap. In addition, half-crack lengths of approximately 
0.25 inch were found during subsequent inspections, and a DTA of the 
area indicates that inspections at 500 flight cycles are required to 
ensure aircraft safety, regardless of the cold working condition.
    The FAA does not concur that additional inspections should be 
included in the final rule, or that the inspection threshold of 5,000 
landings, as required by paragraphs (d) and (e)(1) of the proposed AD, 
should be reduced to 500 landings. The FAA considers it is likely that 
other factors induced the early cracking found in the operator's 
airplane, and that the 5,000-flight-cycle threshold required by the 
proposed AD is an adequate inspection threshold after accomplishment of 
the fastener hole cold working. The FAA points out that it will 
continue to monitor service findings of modified airplanes and may 
revise the inspection requirements in the future, if necessary. 
However, no changes were made to the inspection thresholds required by 
paragraph (d) or (e)(1) of the final rule.

Explanation of Changes Made to This Final Rule

    The notice of proposed rulemaking (NPRM) references Lockheed 
Service Bulletin 093-57-212, dated November 14, 1994, as amended by 
Change Notification CN1, dated September 27, 1995, as an appropriate 
source of service information for accomplishment of the modifications 
specified in paragraphs (f)(1) and (f)(2) of the NPRM. The FAA finds 
that the procedures in Service Bulletin 093-57-212 are no longer 
necessary because the procedures included in the other service 
bulletins cited in those paragraphs are adequate for accomplishment of 
the actions required by this AD. The references to that service 
bulletin have been removed from the final rule.
    Although the NPRM includes references to certain Change 
Notifications for a number of service bulletins, the FAA has determined 
that it is unnecessary to include those references in the final rule. 
The FAA points out that the Change Notifications did not include any 
substantive changes to the service bulletins, and that such change 
notifications included only minor editorial changes or clarification of 
certain data. The FAA has determined that the service bulletins 
referenced in the final rule include all of the procedures necessary 
for accomplishment of the actions required by this AD. In light of 
this, references to the Change Notifications were deleted from the 
final rule.
    Although the NPRM did not include references to certain earlier 
revision levels of Lockheed Service Bulletins 093-57-184, 093-57-196, 
and 093-57-203, the FAA has determined that references to those earlier 
revision levels should be included in the final rule to give credit to 
any operator that may have accomplished the modification previously in 
accordance with those service bulletins. In light of this, the FAA has 
included references to those earlier service bulletins in NOTE 2, NOTE 
3, and NOTE 4 of this AD. The FAA considers that the service bulletins 
referenced in those notes are adequate for specifying the procedures 
necessary for accomplishment of the actions required by this AD.
    The FAA has added Lockheed Service Bulletin 093-57-203, Revision 4, 
dated March 27, 1995, to paragraph (e)(1) of this AD as an additional 
reference for the accomplishment of the rear spar modification.
    In paragraph (g) of this AD, the FAA has added the word 
``discrepant'' preceding the word ``fasteners'' in the parenthetical 
phrase. This word was

[[Page 33388]]

added to clarify that one of the conditions to be identified during the 
required modification is for ``discrepant fasteners'' rather than just 
``fasteners.''

Conclusion

    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.

Cost Impact

    There are approximately 235 Lockheed 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 
AD.
    The actions that are currently required by AD 96-12-24, and 
retained in this AD, take approximately 13 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 $91,260, or $780 per airplane.
    The actions that are required by this new AD will take 
approximately 100 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 new requirements of this AD on U.S. operators is 
estimated to be $702,000, or $6,000 per airplane.
    The cost impact figures discussed above are 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.

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.
    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 39-9667 (61 FR 
29642, June 12, 1996), and by adding a new airworthiness directive 
(AD), amendment 39-11202, to read as follows:

99-13-08  Lockheed: Amendment 39-11202. Docket 97-NM-11-AD. 
Supersedes AD 96-12-24, Amendment 39-9667.

    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 
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 (h)(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 prevent fatigue cracking on the web of the rear spar of the 
wing, which could result in failure of the rear spar of the wing and 
consequent fuel spillage, accomplish the following:

Restatement of Actions Required by AD 96-12-24, Amendment 39-9667

    (a) Perform a visual inspection to detect signs of cracking and 
other discrepancies (i.e., corrosion, fastener looseness, nicks, 
scratches, or other surface damage) of the web-to-cap fasteners of 
the rear spar between inner wing stations (IWS) 310 and 343, as 
specified in Figure 2 of Lockheed Service Bulletin 093-57-218, dated 
April 11, 1996, or Revision 1, dated September 9, 1996; and of the 
web area around those fasteners; in accordance with Part I of the 
Accomplishment Instructions of that service bulletin. Perform the 
inspection at the applicable time specified in paragraph (a)(1) or 
(a)(2) of this AD.
    (1) Except as provided by paragraph (a)(2) of this AD: Perform 
the initial inspection prior to the accumulation of the number of 
landings specified as the ``inspection threshold'' in Table I of 
Lockheed Service Bulletin 093-57-218, dated April 11, 1996, or 
Revision 1, dated September 9, 1996, or within 10 days after June 
27, 1996 (the effective date of AD 96-12-24, amendment 39-9667), 
whichever occurs later.
    (2) For airplanes on which the wing rear spar has been modified 
prior to June 27, 1996, in accordance with one of the Lockheed 
service bulletins listed in paragraph (a)(2)(ii) of this AD, 
accomplish the inspection as follows:
    (i) Perform the initial inspection prior to the accumulation of 
the number of landings specified as the ``inspection threshold'' in 
Table I of Lockheed Service Bulletin 093-57-218, dated April 11, 
1996, or Revision 1, dated September 9, 1996, calculated from the 
time the wing rear spar was modified (rather than from the date of 
manufacture of the airplane), or within 10 days after June 27, 1996, 
whichever occurs later.
    (ii) This paragraph applies to airplanes on which the wing rear 
spar has been modified in accordance with one of the following 
service bulletins:
    <bullet> Lockheed Service Bulletin 093-57-184, Revision 6, dated 
October 28, 1991, or Revision 7, dated December 6, 1994; or
    <bullet> Lockheed Service Bulletin 093-57-196, Revision 5, dated 
October 28, 1991, or Revision 6, dated December 6, 1994; or
    <bullet> Lockheed Service Bulletin 093-57-203, Revision 3, dated 
October 28, 1991, or Revision 4, dated March 27, 1995; or
    <bullet> Lockheed Service Bulletin 093-57-215, dated April 11, 
1996.
    (b) If no sign of cracking or other discrepancy is found during 
the inspection required by paragraph (a) of this AD, repeat that 
inspection thereafter at intervals not to exceed the number of 
landings specified as the ``repeat visual inspection interval'' in 
Table I of Lockheed Service Bulletin 093-57-218, dated April 11, 
1996, or Revision 1, dated September 9, 1996.
    (c) If any sign of cracking is found during an inspection 
required by paragraph (a) or (b) of this AD, prior to further 
flight, perform either eddy current surface scan inspections, or 
bolt hole eddy current inspections, as appropriate, to confirm 
cracking, in accordance with Lockheed Service Bulletin 093-57-218, 
dated April 11, 1996, or Revision 1, dated September 9, 1996.

[[Page 33389]]

    (1) If no cracking is confirmed, repeat the inspection specified 
in paragraph (a) of this AD at intervals not to exceed the number of 
landings specified as the ``repeat visual inspection interval'' in 
Table I of the service bulletin.
    (2) If any cracking is confirmed, prior to further flight, 
repair it in accordance with the service bulletin.

New Requirements of This AD

Modification

    (d) Except as provided by paragraph (e) or (f) of this AD, as 
applicable: Within 12 months after the effective date of this AD, 
modify the web-to-cap fastener holes of the rear spar between IWS 
299 and IWS 343 in accordance with Part II of the Accomplishment 
Instructions of Lockheed Service Bulletin 093-57-218, Revision 1, 
dated September 9, 1996. Within 5,000 landings following 
accomplishment of the modification, perform the visual inspection 
required by paragraph (a) of this AD. Thereafter, repeat that 
inspection at intervals not to exceed the number of landings 
specified as the ``repeat visual inspection interval'' in Table I of 
Lockheed Service Bulletin 093-57-218, Revision 1, dated September 9, 
1996.
    (e) For Model L-1011-385-3 series airplanes: Accomplishment of 
the modification specified in paragraph (e)(1) or (e)(2) of this AD, 
within 12 months after the effective date of this AD, constitutes an 
acceptable alternative to the modification specified in paragraph 
(d) of this AD.
    (1) Modify the upper and lower caps of the rear spar between IWS 
228 and IWS 346 in accordance with Part I of the Accomplishment 
Instructions of Lockheed Service Bulletin 093-57-203, Revision 3, 
dated October 28, 1991; or Revision 4, dated March 27, 1995. Within 
5,000 landings following accomplishment of the modification, perform 
the visual inspection required by paragraph (a) of this AD. 
Thereafter, repeat that inspection at intervals not to exceed the 
number of landings specified as the ``repeat visual inspection 
interval'' in Table I of Lockheed Service Bulletin 093-57-218, 
Revision 1, dated September 9, 1996. Or
    (2) Modify the left and right wing rear spars in accordance with 
the Accomplishment Instructions of Lockheed Service Bulletin 093-57-
215, dated April 11, 1996. Within the thresholds specified in Table 
I of Lockheed Service Bulletin 093-57-218, Revision 1, dated 
September 9, 1996 (calculated from the date of installation of 
Lockheed Service Bulletin 093-57-215, dated April 11, 1996), perform 
the visual inspection required by paragraph (a) of this AD. 
Thereafter, repeat that inspection at intervals not to exceed the 
number of landings specified as the ``repeat visual inspection 
interval'' in Table I of Lockheed Service Bulletin 093-57-218, 
Revision 1, dated September 9, 1996.

    Note 2: Accomplishment of the modification of the upper and 
lower caps of the rear spar between IWS 228 and IWS 346, in 
accordance with the Accomplishment Instructions of Lockheed Service 
Bulletin 093-57-203, dated July 25, 1988, Revision 1, dated August 
11, 1989, or Revision 2, dated January 25, 1991, is considered 
acceptable for compliance with the modification specified in 
paragraph (e)(1) of this amendment.

    (f) For Model L-1011-385-1 series airplanes: Accomplishment of 
the modification specified in paragraph (f)(1) or (f)(2) of this AD, 
within 12 months after the effective date of this AD, constitutes an 
acceptable alternative to the modification specified in paragraph 
(d) of this AD.
    (1) Modify the inboard and outboard rear spars in accordance 
with the Accomplishment Instructions of Lockheed Service Bulletin 
093-57-184, Revision 6, dated October 28, 1991; or Revision 7, dated 
December 6, 1994. Within the thresholds specified in Table I of 
Lockheed Service Bulletin 093-57-218, Revision 1, dated September 9, 
1996 (calculated from the date of installation of Lockheed Service 
Bulletin 093-57-184, Revision 6, dated October 28, 1991, or Revision 
7, dated December 6, 1994), perform the visual inspection required 
by paragraph (a) of this AD. Thereafter, repeat that inspection at 
intervals not to exceed the number of landings specified as the 
``repeat visual inspection interval'' in Table I of Lockheed Service 
Bulletin 093-57-218, Revision 1, dated September 9, 1996. Or
    (2) Modify the inboard and outboard rear spars in accordance 
with the Accomplishment Instructions of Lockheed Service Bulletin 
093-57-196, Revision 5, dated October 28, 1991; or Revision 6, dated 
December 6, 1994. Within the thresholds specified in Table I of 
Lockheed Service Bulletin 093-57-218, Revision 1, dated September 9, 
1996 (calculated from the date of installation of Lockheed Service 
Bulletin 093-57-196, Revision 5, dated October 28, 1991, or Revision 
6, dated December 6, 1994), perform the visual inspection required 
by paragraph (a) of this AD. Thereafter, repeat that inspection at 
intervals not to exceed the number of landings specified as the 
``repeat visual inspection interval'' in Table I of Lockheed Service 
Bulletin 093-57-218, Revision 1, dated September 9, 1996.

    Note 3: Accomplishment of the modification of the inboard and 
outboard rear spars, in accordance with the Accomplishment 
Instructions of Lockheed Service Bulletin 093-57-184, Revision 2, 
dated October 12, 1988; Revision 3, dated August 11, 1989, Revision 
4, dated May 16, 1990; or Revision 5, dated May 23, 1990, is 
considered acceptable for compliance with the modification specified 
in paragraph (f)(1) of this amendment.
    Note 4: Accomplishment of the modification of the inboard and 
outboard rear spars, in accordance with the Accomplishment 
Instructions of Lockheed Service Bulletin 093-57-196, Revision 1, 
dated October 25, 1988; Revision 2, dated July 31, 1989; Revision 3, 
dated March 7, 1990; or Revision 4, dated July 1, 1991, is 
considered acceptable for compliance with the modification specified 
in paragraph (f)(2) of this amendment.

    (g) If any condition (i.e., number of discrepant fasteners per 
stiffener bay, or cracking) is identified during the accomplishment 
of the modification specified in Lockheed Service Bulletin 093-57-
218, Revision 1, dated September 9, 1996, and that condition exceeds 
the limits specified in paragraph B.(3) of Part II of the 
Accomplishment Instructions of the service bulletin, prior to 
further flight, repair in accordance with a method approved by the 
Manager, Atlanta Aircraft Certification Office (ACO), FAA, Small 
Airplane Directorate.

Alternative Method of Compliance

    (h)(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.
    (h)(2) Alternative methods of compliance, approved previously in 
accordance with AD 96-12-24, amendment 39-9667, are approved as 
alternative methods of compliance with paragraph (d) of this AD.
    Note 5: 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

    (i) 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.

Incorporation by Reference

    (j) Except as provided by paragraph (g) of this AD, the actions 
shall be done in accordance with the following service bulletins, as 
applicable:
    <bullet> Lockheed Service Bulletin 093-57-184, Revision 6, dated 
October 28, 1991; or Lockheed Service Bulletin 093-57-184, Revision 
7, dated December 6, 1994;
    <bullet> Lockheed Service Bulletin 093-57-196, Revision 5, dated 
October 28, 1991; or Lockheed Service Bulletin 093-57-196, Revision 
6, dated December 6, 1994;
    <bullet> Lockheed Service Bulletin 093-57-203, Revision 3, dated 
October 28, 1991; or Lockheed Service Bulletin 093-57-203, Revision 
4, dated March 27, 1995;
    <bullet> Lockheed Service Bulletin 093-57-215, dated April 11, 
1996; and
    <bullet> Lockheed Service Bulletin 093-57-218, dated April 11, 
1996; or Lockheed Service Bulletin 093-57-218, Revision 1, dated 
September 9, 1996.
    Revision 1 of Lockheed Service Bulletin 093-57-218 contains the 
following list of effective pages:

------------------------------------------------------------------------
                                  Revision level
            Page No.              shown on page     Date shown on page
------------------------------------------------------------------------
1, 2, 4-9, 13-18...............  1..............  Sept. 9, 1996.
3, 10-12, 19...................  Original.......  Apr. 11, 1996.
------------------------------------------------------------------------

    (1) The incorporation by reference of Lockheed Service Bulletin 
093-57-218, dated April 11, 1996, was approved previously by the 
Director of the Federal

[[Page 33390]]

Register as of June 27, 1996 (61 FR 29642, June 12, 1996).
    (2) The incorporation by reference of the remainder of the 
service bulletins listed above is approved by the Director of the 
Federal Register in accordance with 5 U.S.C. 552(a) and 1 CFR part 
51.
    (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.
    (k) This amendment becomes effective on July 28, 1999.

    Issued in Renton, Washington, on June 15, 1999.
Dorenda D. Baker,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 99-15779 Filed 6-22-99; 8:45 am]
BILLING CODE 4910-13-U