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[Federal Register Volume 79, Number 180 (Wednesday, September 17, 2014)]
[Proposed Rules]
[Pages 55675-55679]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 2014-22149]

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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2014-0627; Directorate Identifier 2013-NM-217-AD]
RIN 2120-AA64

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

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Notice of proposed rulemaking (NPRM).

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

SUMMARY: We propose to supersede Airworthiness Directive (AD) 2011-09-
03, which applies to all Lockheed Martin Corporation/Lockheed Martin 
Aeronautics Company Model 382, 382B, 382E, 382F, and 382G airplanes. AD 
2011-09-03 currently requires repetitive eddy current inspections to 
detect cracks in the center wing upper and lower rainbow fittings, and 
corrective actions if necessary; and repetitive replacement of rainbow 
fittings, which would extend the repetitive interval for the next 
inspection. Since we issued AD 2011-09-03, analysis of in-service 
cracking has shown that a reduction in the inspection intervals is 
necessary for the upper rainbow fittings. This proposed AD is intended 
to complete certain mandated programs intended to support the airplane 
reaching its limit of validity (LOV) of the engineering data that 
support the established structural maintenance program. This proposed 
AD would require reduced intervals for inspections of the upper rainbow 
fittings. We are proposing this AD to detect and correct fatigue 
cracking of the upper and lower rainbow fittings on the center wings, 
which could grow large and lead to the failure of the fitting and a 
catastrophic failure of the center wing.

DATES: We must receive comments on this proposed AD by November 3, 
2014.

ADDRESSES: You may send comments, using the procedures found in 14 CFR 
11.43 and 11.45, by any of the following methods:
     Federal eRulemaking Portal: Go to http://www.regulations.gov. Follow the instructions for submitting comments.

[[Page 55676]]

     Fax: 202-493-2251.
     Mail: U.S. Department of Transportation, Docket 
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New 
Jersey Avenue SE., Washington, DC 20590.
     Hand Delivery: Deliver to Mail address above between 9 
a.m. and 5 p.m., Monday through Friday, except Federal holidays.
    For service information identified in this proposed AD, contact 
Lockheed Martin Corporation/Lockheed Martin Aeronautics Company, 
Airworthiness Office, Dept. 6A0M, Zone 0252, Column P-58, 86 S. Cobb 
Drive, Marietta, GA 30063; telephone 770-494-5444; fax 770-494-5445; 
email ams.portal@lmco.com; Internet http://www.lockheedmartin.com/ams/tools/TechPubs.html. You may view this referenced service information 
at the FAA, Transport Airplane Directorate, 1601 Lind Avenue SW., 
Renton Washington 98057. 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 http://www.regulations.gov by searching for and locating Docket No. FAA-2014-
0627; 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 proposed AD, the regulatory evaluation, any comments 
received, and other information. The street address for the Docket 
Office (phone: 800-647-5527) is in the ADDRESSES section. Comments will 
be available in the AD docket shortly after receipt.

FOR FURTHER INFORMATION CONTACT: Carl Gray, Aerospace Engineer, 
Airframe Branch, ACE-117A, FAA, Atlanta Aircraft Certification Office 
(ACO), 1701 Columbia Avenue, College Park, Georgia 30337; phone: 404-
474-5554; fax: 404-474-5606; email: carl.w.gray@faa.gov.

SUPPLEMENTARY INFORMATION: 

Comments Invited

    We invite you to send any written relevant data, views, or 
arguments about this proposed AD. Send your comments to an address 
listed under the ADDRESSES section. Include ``Docket No. FAA-2014-0627; 
Directorate Identifier 2013-NM-217-AD'' at the beginning of your 
comments. We specifically invite comments on the overall regulatory, 
economic, environmental, and energy aspects of this proposed AD. We 
will consider all comments received by the closing date and may amend 
this proposed AD because of those comments.
    We will post all comments we receive, without change, to http://www.regulations.gov, including any personal information you provide. We 
will also post a report summarizing each substantive verbal contact we 
receive about this proposed AD.

Discussion

    On April 12, 2011, we issued AD 2011-09-03, Amendment 39-16665 (76 
FR 22311, April 21, 2011), for all Lockheed Martin Corporation/Lockheed 
Martin Aeronautics Company Model 382, 382B, 382E, 382F, and 382G 
airplanes. AD 2011-09-03 requires repetitive eddy current inspections 
to detect cracks in the center wing upper and lower rainbow fittings, 
and corrective actions if necessary; and repetitive replacements of 
rainbow fittings, which would extend the repetitive interval for the 
next inspection. AD 2011-09-03 resulted from reports of fatigue 
cracking of the wing upper and lower rainbow fittings during durability 
testing and on in-service airplanes. Analysis of in-service cracking 
has shown that these rainbow fittings are susceptible to multiple site 
fatigue damage. We issued AD 2011-09-03 to detect and correct such 
fatigue cracks, which could grow large and lead to the failure of the 
fitting and a catastrophic failure of the center wing.

Actions Since AD 2011-09-03, Amendment 39-16665 (76 FR 22311, April 21, 
2011), Was Issued

    Since we issued AD 2011-09-03, Amendment 39-16665 (76 FR 22311, 
April 21, 2011), analysis of in-service cracking has shown that the 
initial and repetitive inspection schedules for the upper rainbow 
fitting need to be revised to reduce the probability of failure until 
the rainbow fitting is replaced.
    We have also revised paragraphs (i) and (k) of AD 2011-09-03, 
Amendment 39-16665 (76 FR 22311, April 21, 2011) to clarify the rainbow 
fitting is replaced with a new rainbow fitting, as specified in 
Lockheed Service Bulletin 382-57-82, Revision 4, including Appendixes A 
and B, dated May 20, 2009; and Lockheed Service Bulletin 382-57-82, 
including Appendices A and B, Revision 6, dated July 11, 2013.

Relevant Service Information

    We reviewed Lockheed Service Bulletin 382-57-82, including 
Appendices A, B, and C, Revision 6, dated July 11, 2013. The compliance 
times are reduced, but the procedures are unchanged from those 
described in Lockheed Service Bulletin 382-57-82, including Appendices 
A, B, and C, dated April 25, 2008.

FAA's Determination

    We are proposing this AD because we evaluated all the relevant 
information and determined the unsafe condition described previously is 
likely to exist or develop in other products of the same type design.

Proposed AD Requirements

    This proposed AD would retain all of the requirements of AD 2011-
09-03, Amendment 39-16665 (76 FR 22311, April 21, 2011). This proposed 
AD would reduce compliance times for initial and repetitive inspections 
of the upper rainbow fitting.
    We have clarified the replacement process to more closely match the 
intent of the service information to replace affected fittings with new 
replacement fittings.

Differences Between This Proposed AD and the Service Information

    Where Lockheed Service Bulletin 382-57-82, including Appendices A, 
B, and C, Revision 6, dated July 11, 2013, does not specify a 
corrective action or states ``taking appropriate corrective action,'' 
this NPRM proposes to require repairing those conditions using a method 
approved by the Manager, Atlanta Aircraft Certification Office, FAA.

Costs of Compliance

    We estimate that this proposed AD affects 14 airplanes of U.S. 
registry.
    We estimate the following costs to comply with this proposed AD:

[[Page 55677]]

                                                 Estimated Costs
----------------------------------------------------------------------------------------------------------------
                                                                                                 Cost on U.S.
             Action                     Labor cost          Parts cost     Cost per product        operators
----------------------------------------------------------------------------------------------------------------
Inspection of upper and lower    20 work-hours x $85 per           (\1\)  $1,700, per         $23,800, per
 fitting [retained actions from   hour = $1,700 per                        inspection cycle.   inspection cycle.
 AD 2011[dash]09[dash]03,         inspection cycle.
 Amendment 39[dash]16665 (76 FR
 22311, April 21, 2011)].
Fitting replacement [retained    2,438 work-hours x $85          $40,000  $247,230, per       $3,461,220, per
 actions from AD                  per hour = $207,230                      replacement.        replacement.
 2011[dash]09[dash]03,            per replacement.
 Amendment 39[dash]16665 (76 FR
 22311, April 21, 2011)].
----------------------------------------------------------------------------------------------------------------
\(1)\ None.

    This proposed AD reduces the compliance times for the upper rainbow 
fitting inspections and adds no additional economic burden.

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

    We have determined that this proposed AD would not have federalism 
implications under Executive Order 13132. This proposed AD would 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 the proposed 
regulation:
    (1) Is not a ``significant regulatory action'' under Executive 
Order 12866,
    (2) Is not a ``significant rule'' under the 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.

The Proposed Amendment

    Accordingly, under the authority delegated to me by the 
Administrator, the FAA proposes to amend 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. Amend Sec.  39.13 by removing Airworthiness Directive (AD) 2011-09-
03, Amendment 39-16665 (76 FR 22311, April 21, 2011), and adding the 
following new AD:

Lockheed Martin Corporation/Lockheed Martin Aeronautics Company: 
Docket No. FAA-2014-0627; Directorate Identifier 2013-NM-217-AD.

 (a) Comments Due Date

    The FAA must receive comments on this AD action by November 3, 
2014.

(b) Affected ADs

    This AD replaces AD 2011-09-03, Amendment 39-16665 (76 FR 22311, 
April 21, 2011.

(c) Applicability

    This AD applies to all Lockheed Martin Corporation/Lockheed 
Martin Aeronautics Company Model 382, 382B, 382E, 382F, and 382G 
airplanes, certificated in any category.

(d) Subject

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

(e) Unsafe Condition

    This AD was prompted by an analysis of in-service cracking that 
has shown that the rainbow fittings are susceptible to multiple site 
fatigue damage. We are issuing this AD to detect and correct fatigue 
cracking of the upper and lower rainbow fittings on the center 
wings, which could grow large and lead to the failure of the fitting 
and a catastrophic failure of the center wing.

(f) Compliance

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

(g) Retained Initial Inspections

    This paragraph restates the requirements of paragraph (g) of AD 
2011-09-03, Amendment 39-16665 (76 FR 22311, April 21, 2011), with 
revised service information. Except as required by paragraph (m) of 
this AD, at the later of the times specified in paragraphs (g)(1) 
and (g)(2) of this AD: Do eddy current inspections to detect 
cracking of the center wing upper and lower rainbow fittings on the 
left and right side of the airplane. Do the actions in accordance 
with the Accomplishment Instructions of Lockheed Service Bulletin 
382-57-82, Revision 4, including Appendixes A and B, dated May 20, 
2009; or Lockheed Service Bulletin 382-57-82, including Appendices A 
and B, Revision 6, dated July 11, 2013. If any crack is found during 
the inspections required by this paragraph, before further flight, 
do the actions required by paragraph (k) of this AD. Doing the 
requirements of paragraph (m) of this AD terminates the requirements 
of this paragraph for the affected upper rainbow fitting only. As of 
the effective date of this AD, only use Lockheed Service Bulletin 
382-57-82, including Appendices A and B, Revision 6, dated July 11, 
2013, for accomplishing the actions specified in this paragraph.
    (1) Before the accumulation of 15,000 total flight hours on the 
rainbow fitting.
    (2) Within 365 days or 600 flight hours on the rainbow fitting 
after May 26, 2011, (the effective date of AD 2011-09-03, Amendment 
39-16665 (76 FR 22311, April 21, 2011)), whichever occurs first.

(h) Retained Repetitive Inspection Schedule

    This paragraph restates the requirements of paragraph (h) of AD 
2011-09-03, Amendment 39-16665 (76 FR 22311, April 21, 2011), with a 
new exception. Except as required by paragraph (n) of this AD, 
repeat the inspection required by paragraph (g) of this AD at 
intervals not to exceed 3,600 flight hours on the center wing, until 
the rainbow fitting has accumulated 30,000 total flight hours. If 
any crack is found during the inspections required by paragraph (h) 
of this AD, before further flight, do the actions required by 
paragraph (k) of this AD. Doing

[[Page 55678]]

the requirements of paragraph (n) of this AD terminates the 
requirements of this paragraph for the affected upper rainbow 
fitting only.

(i) Retained Rainbow Fitting Replacements

    This paragraph restates the requirements of paragraph (i) of AD 
2011-09-03, Amendment 39-16665 (76 FR 22311, April 21, 2011), with 
revised service information. Before the accumulation of 30,000 
flight hours on the rainbow fitting, or within 600 flight hours 
after May 26, 2011, (the effective date of AD 2011-09-03, Amendment 
39-16665 (76 FR 22311, April 21, 2011)), whichever occurs later: 
Replace the rainbow fitting with a new rainbow fitting, do all 
related investigative actions, and do all applicable corrective 
actions, in accordance with paragraph 2.C. of the Accomplishment 
Instructions of Lockheed Service Bulletin 382-57-82, Revision 4, 
including Appendix C, dated May 20, 2009, except as required by 
paragraph (l) of this AD; or Lockheed Service Bulletin 382-57-82, 
including Appendix C, Revision 6, dated July 11, 2013, except as 
required by paragraph (l) of this AD. Replace the rainbow fitting 
thereafter at intervals not to exceed 30,000 flight hours. As of the 
effective date of this AD, only use Lockheed Service Bulletin 382-
57-82, including Appendix C, Revision 6, dated July 11, 2013, for 
accomplishing the actions specified in this paragraph.

(j) Retained Post-Replacement Repetitive Inspections

    This paragraph restates the requirements of paragraph (j) of AD 
2011-09-03, Amendment 39-16665 (76 FR 22311, April 21, 2011), with a 
new exception. For upper and lower rainbow fittings replaced in 
accordance with paragraph (i) or (k) of this AD: Except as required 
by paragraph (o) of this AD, do the eddy current inspections 
specified in paragraph (g) of this AD within 15,000 flight hours 
after doing the replacement and repeat the eddy current inspections 
specified in paragraph (h) of this AD thereafter at intervals not to 
exceed 3,600 flight hours until the rainbow fittings are replaced in 
accordance with paragraph (i) or (k) of this AD. Doing the 
requirements of paragraph (o) of this AD terminates the requirements 
of this paragraph for the affected upper rainbow fitting only.

(k) Retained Replacement, Related Investigative Actions, and Corrective 
Actions

    This paragraph restates the requirements of paragraph (k) of AD 
2011-09-03, Amendment 39-16665 (76 FR 22311, April 21, 2011), with 
revised service information and revised references to inspection 
paragraphs. If, during any inspection required by paragraph (g), 
(h), (m), or (n) of this AD, any crack is detected in the rainbow 
fitting, before further flight, replace the rainbow fitting with a 
new rainbow fitting, do all related investigative actions, and do 
all applicable corrective actions, in accordance with Paragraph 2.C. 
of the Accomplishment Instructions of Lockheed Service Bulletin 382-
57-82, Revision 4, including Appendix C, dated May 20, 2009, except 
as provided by paragraph (l) of this AD; or Lockheed Service 
Bulletin 382-57-82, including Appendix C, Revision 6, dated July 11, 
2013, except as required by paragraph (l) of this AD. As of the 
effective date of this AD, only use Lockheed Service Bulletin 382-
57-82, including Appendix C, Revision 6, dated July 11, 2013, for 
accomplishing the actions specified in this paragraph.

(l) Retained Exceptions to Service Bulletin

    This paragraph restates the requirements of paragraph (l) of AD 
2011-09-03, Amendment 39-16665 (76 FR 22311, April 21, 2011), with 
revised service information. Where Lockheed Service Bulletin 382-57-
82, Revision 4, including Appendixes A, B, and C, dated May 20, 
2009; or Lockheed Service Bulletin 382-57-82, including Appendices 
A, B, and C, Revision 6, dated July 11, 2013; specifies to contact 
the manufacturer for disposition of certain repair conditions or 
does not specify corrective actions if certain conditions are found, 
this AD requires repairing those conditions using 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.

(m) New Requirement: Reduced Initial Compliance Time for Upper Rainbow 
Fittings

    At the applicable compliance time specified in paragraphs (m)(1) 
and (m)(2) of this AD, do eddy current inspections to detect 
cracking of the center wing upper rainbow fittings on the left and 
right side of the airplane. Do the actions in accordance with the 
Accomplishment Instructions of Lockheed Service Bulletin 382-57-82, 
including Appendices A and B, Revision 6, dated July 11, 2013. If 
any crack is found during the inspections required by this 
paragraph, before further flight, do the actions required by 
paragraph (k) of this AD. Doing the requirements of this paragraph 
terminates the requirements of paragraph (g) of this AD for that 
upper rainbow fitting only. Repeat the inspection at the interval 
required by paragraph (n) of this AD.
    (1) For upper rainbow fittings that have accumulated less than 
10,000 total flight hours as of the effective date of this AD, the 
compliance time is at the later of the times in paragraphs (m)(1)(i) 
and (m)(1)(ii) of this AD.
    (i) Before the accumulation of 10,000 total flight hours.
    (ii) Within 365 days or 600 flight hours after the effective 
date of this AD, whichever occurs first.
    (2) For upper rainbow fittings that have accumulated 10,000 
total flight hours or more, but less than 15,000 total flight hours 
as of the effective date of this AD, the compliance time is the 
earlier of the times specified in paragraphs (m)(2)(i) and 
(m)(2)(ii) of this AD.
    (i) Within 365 days or 600 flight hours after the effective date 
of this AD, whichever occurs first.
    (ii) Before the accumulation of 15,000 total flight hours on the 
rainbow fitting.

(n) New Requirement: Reduced Repetitive Inspection Intervals

    For upper rainbow fittings on which the requirements of 
paragraph (g), (h), or (m) of this AD were done, do the next 
inspection at the earlier of the times required in paragraphs (n)(1) 
and (n)(2) of this AD. Thereafter, repeat the inspection required by 
paragraph (m) of this AD at intervals not to exceed 2,500 flight 
hours until the upper rainbow fitting has accumulated 30,000 total 
flight hours. If any crack is found during the inspections required 
by this paragraph, before further flight, do the actions required by 
paragraph (k) of this AD. Doing an inspection required by this 
paragraph terminates the requirements of paragraph (h) of this AD 
for the affected upper rainbow fitting only.
    (1) Within 3,600 flight hours since the last inspection done in 
accordance with paragraph (g), (h), or (m) of this AD, whichever 
occurs latest.
    (2) At the later of the times specified in paragraphs (n)(2)(i) 
and (n)(2)(ii) of this AD.
    (i) Within 2,500 flight hours after the last inspection done in 
accordance with paragraph (g), (h), or (m) of this AD, whichever 
occurs latest.
    (ii) Within 365 days or 600 flight hours after the effective 
date of this AD, whichever occurs first.

(o) New Requirement: Reduced Post-Replacement Repetitive Inspections

    For upper rainbow fittings replaced in accordance with paragraph 
(i) or (k) of this AD, do the inspection required by paragraph (m) 
of this AD at the earlier of the compliance times required in 
paragraph (o)(1) and (o)(2) of this AD. Repeat the inspection 
thereafter at intervals not to exceed 2,500 flight hours. Doing the 
inspections required by this paragraph terminates the requirements 
of paragraph (j) of this AD for the affected upper rainbow fitting 
only.
    (1) At the later of the times in paragraphs (o)(1)(i) and 
(o)(1)(ii) of this AD. (i) Within 10,000 total flight hours on the 
upper rainbow fitting.
    (ii) Within 365 days or 600 flight hours after the effective 
date of this AD, whichever occurs first.
    (2) Within 15,000 total flight hours on the upper rainbow 
fitting.

(p) Credit for Previous Actions

    The service information identified in paragraphs (p)(1)(i), 
(p)(1)(ii), (p)(1)(iii), (p)(2), and (p)(3) is not incorporated by 
reference in this AD.
    (1) This paragraph provides credit for actions required by 
paragraphs (g), (h), (i), (j), and (k) of this AD, if those actions 
were performed before the effective date of this AD using the 
service information identified in paragraphs (p)(1)(i), (p)(1)(ii), 
and (p)(1)(iii) of this AD.
    (i) Lockheed Service Bulletin 382-57-82, including Appendices A 
and B, dated December 7, 2004.
    (ii) Lockheed Service Bulletin 382-57-82, Revision 1, including 
Appendices A and B, dated February 24, 2005.

[[Page 55679]]

    (iii) Lockheed Service Bulletin 382-57-82, Revision 2, including 
Appendices A and B, dated February 15, 2007.
    (2) This paragraph restates paragraph (m) of AD 2011-09-03, 
Amendment 39-16665 (76 FR 22311, April 21, 2011). This paragraph 
provides credit for actions required by paragraphs (g), (h), (i), 
(j), and (k) of this AD, if those actions were performed before May 
26, 2011 (the effective date of AD 2011-09-03), using Lockheed 
Service Bulletin 382-57-82, Revision 3, including Appendixes A, B, 
and C, dated April 25, 2008.
    (3) This paragraph provides credit for actions required by 
paragraphs (g), (h), (i), (j), (k), (m), (n), and (o) of this AD, if 
those actions were performed before the effective date of this AD 
using Lockheed Service Bulletin 382-57-82, including Appendices A, 
B, and C, Revision 5, dated August 12, 2010.

(q) Alternative Methods of Compliance (AMOCs)

    (1) The Manager, Atlanta Aircraft Certification Office, 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 (r)(2) 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.
    (3) AMOCs approved for AD 2011-09-03, Amendment 39-16665 (76 FR 
22311, April 21, 2011), are approved as AMOCs for the corresponding 
provisions of this AD.

(r) 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, 
Georgia 30337; phone: 404-474-5554; fax: 404-474-5606; email: 
carl.w.gray@faa.gov.
    (2) For information about AMOCs, contact Hal Horsbough, 
Aerospace Engineer, Airframe Branch, ACE-117A, FAA, Atlanta Aircraft 
Certification Office (ACO), 1701 Columbia Avenue, College Park, 
Georgia 30337; phone: 404-474-5554; fax: 404-474-5606; email: 
hal.horsbough@faa.gov.
    (3) For service information identified in this AD, contact 
Lockheed Martin Corporation/Lockheed Martin Aeronautics Company, 
Airworthiness Office, Dept. 6A0M, Zone 0252, Column P-58, 86 S. Cobb 
Drive, Marietta, GA 30063; telephone 770-494-5444; fax 770-494-5445; 
email ams.portal@lmco.com; Internet http://www.lockheedmartin.com/ams/tools/TechPubs.html. 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.

    Issued in Renton, Washington, on September 9, 2014.
Jeffrey E. Duven,
Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 2014-22149 Filed 9-16-14; 8:45 am]
BILLING CODE 4910-13-P
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