AD 2014-20-08

[Federal Register Volume 79, Number 192 (Friday, October 3, 2014)]
[Rules and Regulations]
[Pages 59643-59645]
From the Federal Register Online via the Government Publishing Office [<a href="http://www.gpo.gov">www.gpo.gov</a>]
[FR Doc No: 2014-23378]


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

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2014-0290; Directorate Identifier 2012-NM-210-AD; 
Amendment 39-17981; AD 2014-20-08]
RIN 2120-AA64


Airworthiness Directives; Lockheed Martin Corporation/Lockheed 
Martin Aeronautics Company Airplanes

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Final rule.

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

SUMMARY: We are adopting a new airworthiness directive (AD) for certain 
Lockheed Martin Corporation/Lockheed Martin Aeronautics Company Model 
L-1011 series airplanes. This AD was prompted by reports of cracked rib 
cap castellations. This AD requires repetitive inspections for 
castellation and skin clips cracked or damaged between stringers and 
cracked stringer clips of the wing box pylon back-up structure, and 
front spar to rear spar; repetitive inspections for cracking, damage, 
or failure of the pylon back-up torque box structure; repetitive 
inspections for cracking or damage of the wing box external areas at 
the drag brace aft wing fitting; repetitive inspections of the outer 
surface of the wing upper and lower skins for cracks or damage along 
the rib attachment at the fastener holes and between the two rows of 
attachment; and corrective actions if necessary. We are issuing this AD 
to detect and correct cracked or damaged rib cap castellations, which 
could degrade the structural capabilities of the airplane.

DATES: This AD is effective November 7, 2014.
    The Director of the Federal Register approved the incorporation by 
reference of a certain publication listed in this AD as of November 7, 
2014.

ADDRESSES: For service information identified in this AD, contact 
Lockheed Martin Corporation/Lockheed Martin Aeronautics Company, L1011 
Technical Support Center, Dept. 6A4M, Zone 0579, 86 South Cobb Drive, 
Marietta, GA 30063-0579; telephone 770-494-5444; fax 770-494-5445; 
email <a href="/cdn-cgi/l/email-protection#0e423f3e3f3f207d7b7e7e617c7a4e62636d61206d6163"><span class="__cf_email__" data-cfemail="2d611c1d1c1c035e585d5d425f596d41404e42034e4240">[email&#160;protected]</span></a>; Internet <a href="http://www.lockheedmartin.com/ams/tools/TechPubs.html">http://www.lockheedmartin.com/ams/tools/TechPubs.html</a>. You may view this referenced service 
information at the FAA, Transport Airplane Directorate, 1601 Lind 
Avenue SW., Renton, WA. For information on the availability of this 
material at the FAA, call 425-227-1221.

Examining the AD Docket

    You may examine the AD docket on the Internet at <a href="http://www.regulations.gov">http://www.regulations.gov</a> by searching for and locating Docket No. FAA-2014-
0290; or in person at the Docket Management Facility between 9 a.m. and 
5 p.m., Monday through Friday, except Federal holidays. The AD docket 
contains this AD, the regulatory evaluation, any comments received, and 
other information. The address for the Docket Office (phone: 800-647-
5527) is Docket Management Facility, U.S. Department of Transportation, 
Docket Operations, M-30, West Building Ground Floor, Room W12-140, 1200 
New Jersey Avenue SE., Washington, DC 20590.

FOR FURTHER INFORMATION CONTACT: Carl Gray, Aerospace Engineer, 
Airframe Branch, ACE-117A, FAA, Atlanta Aircraft Certification Office 
(ACO), 1701 Columbia Avenue, College Park, GA 30337; phone: 404-474-
5554; fax: 404-474-5605; email: <a href="/cdn-cgi/l/email-protection#35565447591b421b5247544c755354541b525a43"><span class="__cf_email__" data-cfemail="214240534d0f560f46534058614740400f464e57">[email&#160;protected]</span></a>.

SUPPLEMENTARY INFORMATION:

Discussion

    We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR 
part 39 by adding an AD that would apply to certain Lockheed Martin 
Corporation/Lockheed Martin Aeronautics Company Model L-1011 series 
airplanes. The NPRM published in the Federal Register on May 29, 2014 
(79 FR 30748). The NPRM was prompted by reports of cracked rib cap 
castellations. The NPRM proposed to require repetitive inspections for 
castellation and skin clips cracked or damaged between stringers and 
cracked stringer clips of the wing box pylon back-up structure, and 
front spar to rear spar; repetitive inspections for cracking, damage, 
or failure of the pylon back-up torque box structure; repetitive 
inspections for cracking or damage of the wing box external areas at 
the drag brace aft wing fitting; repetitive inspections of the outer 
surface of the wing upper and lower skins for cracks or damage along 
the rib attachment at the fastener holes and between the two rows of 
attachment; and corrective actions if necessary. We are issuing this AD 
to detect and correct cracked or damaged rib cap castellations, which 
could degrade the structural capabilities of the airplane.

Comments

    We gave the public the opportunity to participate in developing 
this AD. We received no comments on the NPRM (79 FR 30748, May 29, 
2014) or on the determination of the cost to the public.

Conclusion

    We reviewed the relevant data and determined that air safety and 
the public interest require adopting this AD as proposed except for 
minor editorial changes. We have determined that these minor changes:
    <bullet> Are consistent with the intent that was proposed in the 
NPRM (79 FR 30748, May 29, 2014) for correcting the unsafe condition; 
and
    <bullet> Do not add any additional burden upon the public than was 
already proposed in the NPRM (79 FR 30748, May 29, 2014).

Costs of Compliance

    We estimate that this AD affects 26 airplanes of U.S. registry.
    We estimate the following costs to comply with this AD:

                                                 Estimated Costs
----------------------------------------------------------------------------------------------------------------
                                                                                                Cost on U.S.
          Action                  Labor cost          Parts cost       Cost per product          operators
----------------------------------------------------------------------------------------------------------------
Inspections...............  41 work-hours x $85                $0   $3,485 per inspection  $90,610 per
                             per hour = $3,485                       cycle.                 inspection cycle.
                             per inspection cycle.
----------------------------------------------------------------------------------------------------------------


[[Page 59644]]

    We estimate the following costs to do any necessary repairs that 
would be required based on the results of the inspections. We have no 
way of determining the number of aircraft that might need these 
repairs:

                                               On-Condition Costs
----------------------------------------------------------------------------------------------------------------
                Action                        Labor cost               Parts cost            Cost per product
----------------------------------------------------------------------------------------------------------------
Modification (up to 12 rib caps per    96 work-hours x $85 per  $15,000 per rib cap....  $23,160 per rib cap.
 airplane).                             hour = $8,160 per rib
                                        cap.
----------------------------------------------------------------------------------------------------------------

    Other than the modification stated above, we have received no 
definitive data that would enable us to provide cost estimates for the 
crack repair actions specified in this AD.

Paperwork Reduction Act

    A federal agency may not conduct or sponsor, and a person is not 
required to respond to, nor shall a person be subject to penalty for 
failure to comply with a collection of information subject to the 
requirements of the Paperwork Reduction Act unless that collection of 
information displays a current valid OMB control number. The control 
number for the collection of information required by this AD is 2120-
0056. The paperwork cost associated with this AD has been detailed in 
the Costs of Compliance section of this document and includes time for 
reviewing instructions, as well as completing and reviewing the 
collection of information. Therefore, all reporting associated with 
this AD is mandatory. Comments concerning the accuracy of this burden 
and suggestions for reducing the burden should be directed to the FAA 
at 800 Independence Ave. SW., Washington, DC 20591, ATTN: Information 
Collection Clearance Officer, AES-200.

Authority for This Rulemaking

    Title 49 of the United States Code specifies the FAA's authority to 
issue rules on aviation safety. Subtitle I, section 106, describes the 
authority of the FAA Administrator. Subtitle VII: Aviation Programs, 
describes in more detail the scope of the Agency's authority.
    We are issuing this rulemaking under the authority described in 
Subtitle VII, Part A, Subpart III, Section 44701: ``General 
requirements.'' Under that section, Congress charges the FAA with 
promoting safe flight of civil aircraft in air commerce by prescribing 
regulations for practices, methods, and procedures the Administrator 
finds necessary for safety in air commerce. This regulation is within 
the scope of that authority because it addresses an unsafe condition 
that is likely to exist or develop on products identified in this 
rulemaking action.

Regulatory Findings

    This AD will not have federalism implications under Executive Order 
13132. This AD 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.
    For the reasons discussed above, I certify that this AD:
    (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),
    (3) Will not affect intrastate aviation in Alaska, and
    (4) 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.

List of Subjects in 14 CFR Part 39

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

Adoption of the Amendment

    Accordingly, under the authority delegated to me by the 
Administrator, the FAA amends 14 CFR part 39 as follows:

PART 39--AIRWORTHINESS DIRECTIVES

0
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]

0
2. The FAA amends Sec.  39.13 by adding the following new airworthiness 
directive (AD):

2014-20-08 Lockheed Martin Corporation/Lockheed Martin Aeronautics 
Company: Amendment 39-17981; Docket No. FAA-2014-0290; Directorate 
Identifier 2012-NM-210-AD.

(a) Effective Date

    This AD is effective November 7, 2014.

(b) Affected ADs

    None.

(c) Applicability

    This AD applies to Lockheed Martin Corporation/Lockheed Martin 
Aeronautics Company Model L-1011-385-1, L-1011-385-1-14, L-1011-385-
1-15, and L-1011-385-3 airplanes, certificated in any category, as 
identified in Lockheed Martin Service Bulletin 093-57-207, Revision 
5, dated November 14, 2008.

(d) Subject

    Air Transport Association (ATA) of America Code 57, Wings.

(e) Unsafe Condition

    This AD was prompted by reports of cracked rib cap 
castellations. We are issuing this AD to detect and correct cracked 
or damaged rib cap castellations, which could degrade the structural 
capabilities of the airplane.

(f) Compliance

    Comply with this AD within the compliance times specified, 
unless already done.

(g) Repetitive Wing Inspections

    For Model L-1011-385-1, L-1011-385-1-14, L-1011-385-1-15, and L-
1011-385-3 airplanes, serial numbers 1189 and subsequent: At the 
applicable compliance time specified in paragraphs (h)(1), (h)(2), 
and (h)(3) of this AD, do the inspections specified in paragraphs 
(g)(1) through (g)(4) of this AD. Repeat the inspections thereafter 
at intervals not to exceed 3,600 flight cycles or 7,200 flight 
hours, whichever occurs first.
    (1) Do a detailed inspection for castellation and skin clips 
cracked or damaged (including cracks, loose or missing fasteners, 
oversized and missed drilled fastener holes, corrosion, dents, 
scratches and other signs of distress) between stringers and cracked 
stringer clips of the wing box pylon back-up structure, and front 
spar to rear spar, in accordance with the Accomplishment 
Instructions of Lockheed Martin Service Bulletin 093-57-207, 
Revision 5, dated November 14, 2008.
    (2) Do a general visual inspection for cracking or damage 
(including cracks, loose or missing fasteners, oversized and missed 
drilled fastener holes, corrosion, dents, scratches and other signs 
of distress) of the pylon back-up torque box structure, in 
accordance with the Accomplishment Instructions of Lockheed Martin 
Service Bulletin 093-57-207, Revision 5, dated November 14, 2008.
    (3) Do a general visual inspection for cracking, damage 
(including cracks, loose or missing fasteners, oversized and missed 
drilled fastener holes, corrosion, dents, scratches and other signs 
of distress), or failure of the wing box external areas at the

[[Page 59645]]

drag brace aft wing fitting, in accordance with the Accomplishment 
Instructions of Lockheed Martin Service Bulletin 093-57-207, 
Revision 5, dated November 14, 2008.
    (4) Do a general visual inspection for cracking or damage 
(including cracks, loose or missing fasteners, oversized and missed 
drilled fastener holes, corrosion, dents, scratches and other signs 
of distress) of the outer surface of the wing upper and lower skins 
for cracks along the rib attachment at the fastener holes and 
between the two rows of attachments, in accordance with the 
Accomplishment Instructions of Lockheed Martin Service Bulletin 093-
57-207, Revision 5, dated November 14, 2008.

(h) Compliance Times for the Actions Specified in Paragraph (g) of This 
AD

    (1) For airplanes that have not accomplished the inspections 
described in Lockheed Martin Service Bulletin 093-57-207 prior to 
the effective date of this AD: At the later of the compliance times 
specified in paragraphs (h)(1)(i) and (h)(1)(ii) of this AD.
    (i) Before the accumulation of 15,000 total flight cycles or 
27,000 total flight hours, whichever occurs first.
    (ii) Within 1,800 flight cycles or 3,600 flight hours, whichever 
occurs first, after the effective date of this AD.
    (2) For airplanes that have accomplished the inspections 
described in Lockheed Martin Service Bulletin 093-57-207 prior to 
the effective date of this AD: Within 3,600 flight cycles or 7,200 
flight hours, whichever occurs first, after the completion of the 
most recent inspections, except as specified in paragraph (h)(3) of 
this AD.
    (3) For rib caps that have been modified as described in 
Lockheed Martin Service Bulletin 093-57-207: Before the accumulation 
of 15,000 total flight cycles or 27,000 total flight hours, 
whichever occurs first, for that rib cap only.

(i) Corrective Actions

    If any cracking, damage, or failure is found during any 
inspection required by paragraph (g) of this AD: Before further 
flight, do all applicable corrective actions, in accordance with the 
Accomplishment Instructions of Lockheed Martin Service Bulletin 093-
57-207, Revision 5, dated November 14, 2008, except where this 
service bulletin specifies that all other damaged structural items 
should be repaired using the best shop practices, following 
procedures in Structural Repair Manual 57-12-00, this AD requires 
repairing the damage before further flight, in accordance with a 
method approved by the Manager, Atlanta Aircraft Certification 
Office (ACO), FAA. For a repair method to be approved by the 
Manager, Atlanta ACO, as required by this paragraph, the Manager's 
approval letter must specifically refer to this AD.

(j) Reporting

    Submit a report of positive findings of the inspection for 
cracking, damage, or failure required by this AD to the Manager, 
Atlanta ACO, at the applicable time specified in paragraph (j)(1) or 
(j)(2) of this AD. The report must include the inspection results, a 
description of the discrepancies found, the airplane serial number, 
and the number of landings and flight hours on the airplane.
    (1) If the inspection was done on or after the effective date of 
this AD: Submit the report within 30 days after the inspection.
    (2) If the inspection was done before the effective date of this 
AD: Submit the report within 30 days after the effective date of 
this AD.

(k) Paperwork Reduction Act Burden Statement

    A federal agency may not conduct or sponsor, and a person is not 
required to respond to, nor shall a person be subject to a penalty 
for failure to comply with a collection of information subject to 
the requirements of the Paperwork Reduction Act unless that 
collection of information displays a current valid OMB Control 
Number. The OMB Control Number for this information collection is 
2120-0056. Public reporting for this collection of information is 
estimated to be approximately 5 minutes per response, including the 
time for reviewing instructions, completing and reviewing the 
collection of information. All responses to this collection of 
information are mandatory. Comments concerning the accuracy of this 
burden and suggestions for reducing the burden should be directed to 
the FAA at: 800 Independence Ave. SW., Washington, DC 20591, Attn: 
Information Collection Clearance Officer, AES-200.

(l) Credit for Previous Actions

    This paragraph provides credit for actions required by 
paragraphs (g) and (i) of this AD, if those actions were performed 
before the effective date of this AD using Lockheed Martin Service 
Bulletin 093-57-207, Revision 3, dated November 22, 1991.

(m) Alternative Methods of Compliance (AMOCs)

    (1) The Manager, Atlanta ACO, FAA, has the authority to approve 
AMOCs for this AD, if requested using the procedures found in 14 CFR 
39.19. In accordance with 14 CFR 39.19, send your request to your 
principal inspector or local Flight Standards District Office, as 
appropriate. If sending information directly to the manager of the 
ACO, send it to the attention of the person identified in paragraph 
(n)(1) of this AD.
    (2) Before using any approved AMOC, notify your appropriate 
principal inspector, or lacking a principal inspector, the manager 
of the local flight standards district office/certificate holding 
district office.

(n) Related Information

    (1) For more information about this AD, contact Carl Gray, 
Aerospace Engineer, Airframe Branch, ACE-117A, FAA, Atlanta Aircraft 
Certification Office (ACO), 1701 Columbia Avenue, College Park, GA 
30337; phone: 404-474-5554; fax: 404-474-5605; email: 
<a href="/cdn-cgi/l/email-protection#086b697a64267f266f7a6971486e6969266f677e"><span class="__cf_email__" data-cfemail="6b080a1907451c450c190a122b0d0a0a450c041d">[email&#160;protected]</span></a>.
    (2) Service information identified in this AD that is not 
incorporated by reference is available at the addresses specified in 
paragraphs (o)(3) and (o)(4) of this AD.

(o) Material Incorporated by Reference

    (1) The Director of the Federal Register approved the 
incorporation by reference (IBR) of the service information listed 
in this paragraph under 5 U.S.C. 552(a) and 1 CFR part 51.
    (2) You must use this service information as applicable to do 
the actions required by this AD, unless the AD specifies otherwise.
    (i) Lockheed Martin Service Bulletin 093-57-207, Revision 5, 
dated November 14, 2008.
    (ii) Reserved.
    (3) For Lockheed service information identified in this AD, 
contact Lockheed Martin Corporation/Lockheed Martin Aeronautics 
Company, L1011 Technical Support Center, Dept. 6A4M, Zone 0579, 86 
South Cobb Drive, Marietta, GA 30063-0579; telephone 770-494-5444; 
fax 770-494-5445; email <a href="/cdn-cgi/l/email-protection#e3afd2d3d2d2cd909693938c9197a38f8e808ccd808c8e"><span class="__cf_email__" data-cfemail="783449484949560b0d0808170a0c3814151b17561b1715">[email&#160;protected]</span></a>; Internet <a href="http://www.lockheedmartin.com/ams/tools/TechPubs.html">http://www.lockheedmartin.com/ams/tools/TechPubs.html</a>.
    (4) You may view this service information at FAA, Transport 
Airplane Directorate, 1601 Lind Avenue SW., Renton, Washington. For 
information on the availability of this material at the FAA, call 
425-227-1221.
    (5) You may view this service information that is incorporated 
by reference at the National Archives and Records Administration 
(NARA). For information on the availability of this material at 
NARA, call 202-741-6030, or go to: <a href="http://www.archives.gov/federal-register/cfr/ibr-locations.html">http://www.archives.gov/federal-register/cfr/ibr-locations.html</a>.

    Issued in Renton, Washington, on September 23, 2014.
Dionne Palermo,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 2014-23378 Filed 10-2-14; 8:45 am]
BILLING CODE 4910-13-P