[Federal Register Volume 61, Number 114 (Wednesday, June 12, 1996)]
[Rules and Regulations]
[Pages 29642-29645]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 96-14692]



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DEPARTMENT OF TRANSPORTATION
14 CFR Part 39

[Docket No. 96-NM-104-AD; Amendment 39-9667; AD 96-12-24]
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 all Lockheed Model L-1011-385 series airplanes. This 
action requires inspections to detect cracking and other discrepancies 
of certain web-to-cap fasteners of the rear spar between inner wing 
stations (IWS) 310 and 343, and of the web area around those fasteners; 
and various follow-on actions. This AD also provides for an optional 
modification which, if accomplished, will defer the initiation of the 
inspections for a certain period of time. This amendment is prompted by 
a report of fatigue cracking in the web of the rear spar of the wing. 
The actions specified in this AD are intended to prevent such fatigue 
cracking, which could result in failure of the rear spar of the wing 
and consequent fuel spillage.

DATES: Effective June 27, 1996.
    The incorporation by reference of certain publications listed in 
the regulations is approved by the Director of the Federal Register as 
of June 27, 1996.
    Comments for inclusion in the Rules Docket must be received on or 
before August 12, 1996.

ADDRESSES: Submit comments in triplicate to the Federal Aviation 
Administration (FAA), Transport Airplane Directorate, ANM-103, 
Attention: Rules Docket No. 96-NM-104-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, 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, 
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: Thomas Peters, Aerospace Engineer, 
Branch, ACE-116A, 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: The FAA received a report indicating that 
fatigue cracking was found on the web of the rear spar of the wing on a 
Lockheed Model L-1011-385 series airplane that had accumulated 
approximately 18,900 total landings. The crack, which was 24 inches 
long, grew rapidly in a downward direction at a 45-degree angle and 
stopped behind the trunnion fitting of the main landing gear. 
Consequently, the airplane began leaking fuel during final taxi.
    Fatigue cracking in the web of the rear spar of the wing can 
originate in the fasteners common to the web and the vertical leg of 
the upper cap. Such cracking can grow and remain undetected for a 
significant period of

[[Page 29643]]

time because the crack can propagate on the interior (fuel side) of the 
web before it breaches the aft side (flap side) of the web. Such 
fatigue cracking, if not detected and corrected in a timely manner, 
could result in failure of the rear spar of the wing and consequent 
fuel spillage.

Other Relevant Rules

    The FAA previously issued AD 96-07-13, amendment 39-9563 (61 FR 
16379, April 15, 1996), which requires various X-ray, eddy current, and 
ultrasonic inspections to detect fatigue cracking of certain areas of 
the rear spar caps, web, skin, and certain fastener holes; and repair 
or modification, if necessary. The inspections are required to be 
repeated at intervals of 2,000 flight cycles. That AD was prompted by 
reports of fatigue cracks in the caps, web, and skin of the wing rear 
spar inboard of inner wing station 346. The actions specified by that 
AD are intended to prevent rupture of the rear spar, which could result 
in extensive damage to the wing and fuel spillage.
    The fatigue cracking that was the subject of the recent in-service 
incident, described above, indicates that fatigue cracking in the area 
of the web of the rear spar of the wing apparently can occur and 
propagate at a faster rate and at a reduced threshold than previously 
realized. In light of this, the FAA is considering revising AD 96-07-13 
to reduce the repetitive inspection intervals to ensure that fatigue 
cracking can be found in a more timely manner. (The FAA indicated this 
in the preamble to that AD.)

Explanation of Relevant Service Information

    The FAA has reviewed and approved Lockheed L-1011 Service Bulletin 
093-57-218, dated April 11, 1996. Part I of the service bulletin 
describes procedures for repetitive visual inspections to detect 
fatigue cracking and other discrepancies (i.e., corrosion, fastener 
looseness, nicks, scratches, or other surface damage) of certain web-
to-cap fasteners of the rear spar between inner wing stations (IWS) 310 
and 343, and of the web area around those fasteners; and various 
follow-on actions. The follow-on actions include repetitive visual 
inspections, eddy current surface scan (ECSS) inspections, bolt hole 
eddy current (BHEC) inspections, and repair.
    Part II of the service bulletin describes procedures for an 
optional modification that will allow the initiation of the visual 
inspections to be deferred for a period of time. The modification 
involves removing certain web-to-cap fasteners, verifying that the 
subject fastener holes are free of cracks, cold working the fastener 
holes, and replacing the fasteners with oversize fasteners.

Explanation of the Requirements of the Rule

    Since an unsafe condition has been identified that is likely to 
exist or develop on other Model L-1011-385 series airplanes of the same 
type design, this AD is being issued 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. This AD requires 
repetitive visual inspections to detect cracking and other 
discrepancies of certain web-to-cap fasteners of the rear spar between 
IWS 310 and IWS 343, and of the web area around those fasteners; and 
various follow-on actions. This AD also provides for an optional 
modification which, if accomplished, will allow the initiation of the 
visual inspections to be deferred for a certain period of time. The 
actions are required to be accomplished in accordance with the Lockheed 
service bulletin described previously.
    The inspections that are required by this AD are in addition to--
not in lieu of--those currently required by AD 96-07-13, amendment 39-
9563.

Differences between the Rule and the Referenced Service Information

    Operators should note that, although the Lockheed service bulletin 
specifies that the manufacturer must be contacted for disposition of 
certain conditions, this AD requires that the repair of those 
conditions be accomplished in accordance with a method approved by the 
Manager, Atlanta Aircraft Certification Office (ACO), FAA, Small 
Airplane Directorate.

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-104-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.

[[Page 29644]]

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:

96-12-24 Lockheed: Amendment 39-9667. Docket 96-NM-104-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 request approval for an 
alternative method of compliance in accordance with paragraph (e) 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:
    (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; 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 
within 10 days after the effective date of this AD, whichever occurs 
later.
    (2) For airplanes on which the wing rear spar has been modified 
prior to the effective date of this AD 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, 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 the effective date of this AD, 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.-
    (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 (ECSS) inspections, or bolt hole eddy 
current (BHEC) inspections, as appropriate, to confirm cracking, in 
accordance with Lockheed Service Bulletin 093-57-218, dated April 11, 
1996. -
    (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 1 of the service bulletin. -
    (2) If any cracking is confirmed, prior to further flight, repair 
it in accordance with the service bulletin. -
    (d) Accomplishment of the modification specified in Part II of the 
Accomplishment Instructions of Lockheed Service Bulletin 093-57-218, 
dated April 11, 1996, and in accordance with that service bulletin, 
allows the visual inspections required by paragraph (a) of this AD to 
be deferred for the period specified in paragraph (d)(2) of this AD. -
    (1) If any condition (i.e., number of fasteners per stiffener bay, 
or cracking) is identified during the accomplishment of the 
modification that 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. -
    (2) 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 the service bulletin. -
    (e) 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, 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.

     -(f) 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. -
    (g) The actions shall be done in accordance with Lockheed L-1011 
Service Bulletin 093-57-218, dated April 11, 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, Field 
Support Department, Dept. 693, Zone 0755, 2251 Lake Park Drive, Smyrna, 
Georgia 30080. 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. -
    (h) This amendment becomes effective on June 27, 1996.


[[Page 29645]]


    Issued in Renton, Washington, on June 5, 1996.
James V. Devany,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 96-14692 Filed 6-11-96; 8:45 am]
BILLING CODE 4910-13-U