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

[Federal Register Volume 80, Number 68 (Thursday, April 9, 2015)]
[Rules and Regulations]
[Pages 19013-19017]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2015-06785]


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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; 
Amendment 39-18126; AD 2015-06-08]
RIN 2120-AA64


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

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Final rule.

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SUMMARY: We are superseding Airworthiness Directive (AD) 2011-09-03 for 
all Lockheed Martin Corporation/Lockheed Martin Aeronautics Company 
Model 382, 382B, 382E, 382F, and 382G airplanes. AD 2011-09-03 required 
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. This new AD requires 
reduced intervals for inspections of the upper rainbow fittings. This 
AD was prompted by analysis of in-service cracking, which has shown 
that a reduction in the inspection intervals is necessary for the upper 
rainbow fittings. 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.

DATES: This AD is effective May 14, 2015.
    The Director of the Federal Register approved the incorporation by 
reference of a certain publication listed in this AD as of May 14, 
2015.
    The Director of the Federal Register approved the incorporation by 
reference of a certain other publication listed in this AD as of May 
26, 2011 (76 FR 22311, April 21, 2011).

ADDRESSES: For service information identified in this AD, contact 
Lockheed Martin Corporation/Lockheed Martin Aeronautics Company, 
Airworthiness

[[Page 19014]]

Office, Dept. 6A0M, Zone 0252, Column P-58, 86 S. Cobb Drive, Marietta, 
GA 30063; telephone 770-494-5444; fax 770-494-5445; email 
[email protected]; 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. It is also available on the Internet at http://www.regulations.gov by searching for and locating Docket No. FAA-2014-
0627.

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 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: 404-474-5606; email: [email protected].

SUPPLEMENTARY INFORMATION: 

Discussion

    We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR 
part 39 to supersede AD 2011-09-03, Amendment 39-16665 (76 FR 22311, 
April 21, 2011). AD 2011-09-03 applied to all Lockheed Martin 
Corporation/Lockheed Martin Aeronautics Company Model 382, 382B, 382E, 
382F, and 382G airplanes. The NPRM published in the Federal Register on 
September 17, 2014 (79 FR 55675). The NPRM was prompted by analysis of 
in-service cracking, which 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. The NPRM proposed to continue to require 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. This AD reduces compliance times for 
initial and repetitive inspections of the upper rainbow fitting. 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.

Comments

    We gave the public the opportunity to participate in developing 
this AD. We received no comments on the NPRM (79 FR 55675, September 
17, 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 55675, September 17, 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 55675, September 17, 2014).

Related Service Information Under 1 CFR Part 51

    We reviewed Lockheed Martin Aeronautics Company Service Bulletin 
382-57-82, Revision 6, including Appendixes A, B, and C, dated July 11, 
2013. The service information describes procedures for repetitive eddy 
current inspections of the upper and lower rainbow fittings of the 
center wing; repetitive replacement of the upper and lower rainbow 
fittings; and related investigative and corrective actions. This 
service information is reasonably available; see ADDRESSES for ways to 
access this service information.

Costs of Compliance

    We estimate that this AD affects 14 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
----------------------------------------------------------------------------------------------------------------
Inspection of upper and lower     20 work-hours x     None..............  $1,700, per         $23,800, per
 fitting [retained actions from    $85 per hour =                          inspection cycle.   inspection cycle.
 AD 2011[dash]09[dash]03,          $1,700 per
 Amendment 39[dash]16665 (76 FR    inspection cycle.
 22311, April 21, 2011)].
Fitting replacement [retained     2,438 work-hours x  $40,000...........  $247,230, per       $3,461,220, per
 actions from AD                   $85 per hour =                          replacement.        replacement.
 2011[dash]09[dash]03, Amendment   $207,230 per
 39[dash]16665 (76 FR 22311,       replacement.
 April 21, 2011)].
----------------------------------------------------------------------------------------------------------------

    This 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 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,

[[Page 19015]]

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 removing Airworthiness Directive (AD) 
2011-09-03, Amendment 39-16665 (76 FR 22311, April 21, 2011), and 
adding the following new AD:

2015-06-08 Lockheed Martin Corporation/Lockheed Martin Aeronautics 
Company: Amendment 39-18126; Docket No. FAA-2014-0627; Directorate 
Identifier 2013-NM-217-AD.

(a) Effective Date

    This AD is effective May 14, 2015.

(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 Martin Aeronautics Company Service Bulletin 382-
57-82, Revision 6, including Appendixes A and B, 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 Martin Aeronautics Company Service 
Bulletin 382-57-82, Revision 6, including Appendixes A and B, 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 this 
paragraph, before further flight, do the actions required by 
paragraph (k) of this AD. Doing 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 Martin Aeronautics Company 
Service Bulletin 382-57-82, Revision 6, including Appendix C, 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 Martin Aeronautics Company Service Bulletin 382-57-82, 
Revision 6, including Appendix C, 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 Martin 
Aeronautics Company Service Bulletin 382-57-82, Revision 6, 
including Appendix C, dated July 11, 2013, except as required by 
paragraph (l) of this AD. As of the effective date of this AD, only 
use Lockheed Martin Aeronautics Company Service Bulletin 382-57-82, 
Revision 6, including Appendix C, dated July 11, 2013, for 
accomplishing the actions specified in this paragraph.

(l) Retained Exceptions to Service Information

    This paragraph restates the requirements of paragraph (l) of AD 
2011-09-03, Amendment

[[Page 19016]]

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 
Martin Aeronautics Company Service Bulletin 382-57-82, Revision 6, 
including Appendixes A, B, and C, 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 Martin Aeronautics Company 
Service Bulletin 382-57-82, Revision 6, including Appendixes A and 
B, 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 
thereafter 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 Appendixes A 
and B, dated December 7, 2004.
    (ii) Lockheed Service Bulletin 382-57-82, Revision 1, including 
Appendixes A and B, dated February 24, 2005.
    (iii) Lockheed Service Bulletin 382-57-82, Revision 2, including 
Appendixes 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, Revision 5, including 
Appendixes A, B, and C, dated August 12, 2010.

(q) 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 
(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, GA 
30337; phone: 404-474-5554; fax: 404-474-5606; email: 
[email protected].
    (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, GA 
30337; phone: 404-474-5554; fax: 404-474-5606; email: 
[email protected].

(s) 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.
    (3) The following service information was approved for IBR on 
May 14, 2015.
    (i) Lockheed Martin Aeronautics Company Service Bulletin 382-57-
82, Revision 6, including Appendixes A, B, and C, dated July 11, 
2013.
    (ii) Reserved.
    (4) The following service information was approved for IBR on 
May 26, 2011 (76 FR 22311, April 21, 2011).
    (i) Lockheed Service Bulletin 382-57-82, Revision 4, including 
Appendixes A, B, and C, dated May 20, 2009.
    (ii) Reserved.
    (5) For service information identified in this AD, contact 
Lockheed Martin Corporation/Lockheed Martin Aeronautics Company, 
Airworthiness Office, Dept. 6A0M,

[[Page 19017]]

Zone 0252, Column P-58, 86 S. Cobb Drive, Marietta, GA 30063; 
telephone 770-494-5444; fax 770-494-5445; email [email protected]; 
Internet http://www.lockheedmartin.com/ams/tools/TechPubs.html.
    (6) You may view this service information at 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.
    (7) 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: http://www.archives.gov/federal-register/cfr/ibr-locations.html.

    Issued in Renton, Washington, on March 12, 2015.
Jeffrey E. Duven,
Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 2015-06785 Filed 4-8-15; 8:45 am]
 BILLING CODE 4910-13-P

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