AD 2015-05-08

[Federal Register Volume 80, Number 54 (Friday, March 20, 2015)]
[Rules and Regulations]
[Pages 14805-14807]
From the Federal Register Online via the Government Publishing Office [<a href="http://www.gpo.gov">www.gpo.gov</a>]
[FR Doc No: 2015-05789]



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Federal Register / Vol. 80, No. 54 / Friday, March 20, 2015 / Rules 
and Regulations

[[Page 14805]]



DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2014-0749; Directorate Identifier 2014-NM-051-AD; 
Amendment 39-18118; AD 2015-05-08]
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 
382, 382B, 382E, 382F, and 382G airplanes. This AD was prompted by an 
evaluation by the design approval holder (DAH) indicating that the 
upper and lower rainbow fittings on the outer wing are subject to 
widespread fatigue damage (WFD). This AD requires repetitive 
inspections of the upper and lower rainbow fittings on the outer wing 
to detect cracks propagating from fasteners attaching the fittings to 
skin panels, and related investigative and corrective actions if 
necessary; and replacement of the upper and lower rainbow fittings on 
the outer wing. We are issuing this AD to prevent fatigue cracking of 
the upper and lower rainbow fittings on the outer wing and skin-panel-
to-fitting fastener holes, which could result in reduced structural 
integrity of the airplane and possible separation of the wing from the 
airplane.

DATES: This AD is effective April 24, 2015.
    The Director of the Federal Register approved the incorporation by 
reference of a certain publication listed in this AD as of April 24, 
2015.

ADDRESSES: 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 <a href="/cdn-cgi/l/email-protection#640509174a140b16100508240809070b4a070b09"><span class="__cf_email__" data-cfemail="f6979b85d886998482979ab69a9b9599d895999b">[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. It is also available on the Internet at <a href="http://www.regulations.gov">http://www.regulations.gov</a> by searching for and locating Docket No. FAA-2014-
0749.

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-
0749; 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: <a href="/cdn-cgi/l/email-protection#1a597b6876344d345d687b635a7c7b7b347d756c"><span class="__cf_email__" data-cfemail="84c7e5f6e8aad3aac3f6e5fdc4e2e5e5aae3ebf2">[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 382, 382B, 382E, 
382F, and 382G airplanes. The NPRM published in the Federal Register on 
October 16, 2014 (79 FR 62075). The NPRM was prompted by an evaluation 
by the DAH indicating that the upper and lower rainbow fittings on the 
outer wing are subject to WFD. The NPRM proposed to require repetitive 
inspections of the upper and lower rainbow fittings on the outer wing 
to detect cracks propagating from fasteners attaching the fittings to 
skin panels, and related investigative and corrective actions if 
necessary; and replacement of the upper and lower rainbow fittings on 
the outer wing. We are issuing this AD to prevent fatigue cracking of 
the upper and lower rainbow fittings on the outer wing and skin-panel-
to-fitting fastener holes, which could result in reduced structural 
integrity of the airplane and possible separation of the wing from the 
airplane.

Comments

    We gave the public the opportunity to participate in developing 
this AD. We have considered the comment received. The commenter 
supported the NPRM (79 FR 62075, October 16, 2014).

Conclusion

    We reviewed the relevant data, considered the comments received, 
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 62075, October 16, 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 62075, October 16, 2014).

Related Service Information Under 1 CFR Part 51

    We reviewed Lockheed Martin Aeronautics Company Service Bulletin 
382-57-95, including Appendix A, dated December 16, 2013. The service 
bulletin describes procedures for inspection and replacement of the 
upper and lower rainbow fittings on the outer wing, 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 20 airplanes of U.S. registry.
    We estimate the following costs to comply with this AD:

[[Page 14806]]



                                                 Estimated Costs
----------------------------------------------------------------------------------------------------------------
                                                                                                 Cost on U.S.
              Action                    Labor cost        Parts cost      Cost per product        operators
----------------------------------------------------------------------------------------------------------------
ECSS inspection..................  24 work-hours x $85              $0  $2,040 per           $40,800 per
                                    per hour = $2,040                    inspection cycle.    inspection cycle.
                                    per inspection
                                    cycle.
Bolt hole inspection during        24 work-hours x $85               0  2,040..............  40,800.
 rainbow fitting replacement.       per hour = $2,040.
Replacement of all four rainbow    2,060 work-hours x           28,000  203,100............  4,062,000.
 fittings.                          $85 per hour =
                                    $175,100.
----------------------------------------------------------------------------------------------------------------

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

                                               On-Condition Costs
----------------------------------------------------------------------------------------------------------------
                                                                                                     Cost per
                    Action                                Labor cost               Parts cost        product
----------------------------------------------------------------------------------------------------------------
Replacement of one rainbow fitting...........  515 work-hours x $85 per hour =          $7,000          $50,775
                                                $43,775.
----------------------------------------------------------------------------------------------------------------

    We have received no definitive data that would enable us to provide 
cost estimates for on-condition actions for cracking of the skin-panel-
to-fitting fastener holes specified in this AD.

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):

2015-05-08 Lockheed Martin Corporation/Lockheed Martin Aeronautics 
Company: Amendment 39-18118 ; Docket No. FAA-2014-0749; Directorate 
Identifier 2014-NM-051-AD.

(a) Effective Date

    This AD is effective April 24, 2015.

(b) Affected ADs

    None.

(c) Applicability

    This AD applies to Lockheed Martin Corporation/Lockheed Martin 
Aeronautics Company Model 382, 382B, 382E, 382F, and 382G airplanes; 
certificated in any category; having any outer wing serial number 
4542 and subsequent, or any manufacturing end product (MEP) 
replacement outer wing except 14Y series.

(d) Subject

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

(e) Unsafe Condition

    This AD was prompted by an evaluation by the design approval 
holder (DAH) indicating that the upper and lower rainbow fittings on 
the outer wing are subject to widespread fatigue damage (WFD). We 
are issuing this AD to prevent fatigue cracking of the upper and 
lower rainbow fittings on the outer wing and skin-panel-to-fitting 
fastener holes, which could result in reduced structural integrity 
of the airplane and possible separation of the wing from the 
airplane.

(f) Compliance

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

(g) Repetitive Eddy Current Surface Scan (ECSS) Inspections

    At the later of the times specified in paragraphs (g)(1) and 
(g)(2) of this AD: Do an ECSS inspection of the left and right outer 
wing upper and lower rainbow fitting-to-skin-panel attachments to 
detect cracks propagating from fasteners attaching the fittings to 
skin panels, and do all applicable related investigative actions, in 
accordance with the Accomplishment Instructions of Lockheed Martin 
Aeronautics Company Service Bulletin 382-57-95, including Appendix 
A, dated December 16, 2013, except as provided by paragraph (j)(1) 
of this AD. Do all applicable related investigative actions before 
further flight. If any cracking is found during any inspection 
required by this paragraph, before further flight, repair

[[Page 14807]]

the cracking, using a method approved in accordance with the 
procedures specified in paragraph (m) of this AD. Repeat the 
inspection of the left and right outer wing upper and lower rainbow 
fitting-to-skin-panel attachments thereafter at intervals not to 
exceed 2,000 flight hours, except as provided by paragraph (l) of 
this AD.
    (1) Before the accumulation of 30,000 total flight hours on any 
wing.
    (2) Within 365 days or 600 flight hours, whichever occurs first, 
after the effective date of this AD.

(h) Rainbow Fitting Replacement and Inspections

    At the time specified in paragraph (i) of this AD, do the 
actions required by paragraph (h)(1) and (h)(2) of this AD.
    (1) Do a detailed inspection of the wing faying structure for 
damage and cracks, and do an automated bolt hole eddy current 
inspection on all open fastener holes in the mating structure, 
stiffeners, webs and angles for cracking, in accordance with the 
Accomplishment Instructions of Lockheed Martin Aeronautics Company 
Service Bulletin 382-57-95, including Appendix A, dated December 16, 
2013, except as provided by paragraph (j)(1) of this AD.
    (i) If any damage is found during any inspection required by 
paragraph (h)(1) of this AD, before further flight, repair the 
damage, using a method approved in accordance with the procedures 
specified in paragraph (m) of this AD.
    (ii) If any cracking is found during any inspection required by 
paragraph (h)(1) of this AD, before further flight, repair the 
cracking, in accordance with the Accomplishment Instructions of 
Lockheed Martin Aeronautics Company Service Bulletin 382-57-95, 
including Appendix A, dated December 16, 2013, except as provided by 
paragraphs (j)(1) and (j)(2) of this AD.
    (2) Replace the left and right upper and lower rainbow fittings 
of the outer wing with new fittings, in accordance with the 
Accomplishment Instructions of Lockheed Martin Aeronautics Company 
Service Bulletin 382-57-95, including Appendix A, dated December 16, 
2013.

    Note 1 to paragraph (h) of this AD: AD 2012-06-09, Amendment 39-
16990 (77 FR 21404, April 10, 2012), is related to the rainbow 
fitting replacement. AD 2012-06-09 references the Lockheed Martin 
Model 382, 382B, 382E, 382F, and 382G Series Aircraft Service Manual 
Publication (SMP), Supplemental Structural Inspection Document 
(SSID), SMP 515-C-SSID, Change 1, dated September 10, 2010; which 
contains inspections for the entire Model 382B-H airframe, not just 
the outer wing. Since installing new rainbow fittings, as required 
by paragraph (g) of this AD, resets the accumulated service life on 
certain parts to zero, certain compliance times specified in Table 3 
of this SSID would be affected by the installation of new outer wing 
fittings.


    Note 2 to paragraph (h) of this AD: AD 2011-15-02, Amendment 39-
16749 (76 FR 41647, July 15, 2011), has requirements for fuel system 
limitations and critical design configuration control limitations, 
which might include configuration or parts limitations on areas 
affected by accomplishment of this AD.

(i) Compliance Times for Paragraph (h) of This AD

    At the later of the times specified in paragraph (i)(1) and 
(i)(2) of this AD, do the actions required by paragraph (h) of this 
AD.
    (1) Before the accumulation of 50,000 total flight hours on any 
wing.
    (2) Within 60 days or 100 flight hours, whichever occurs first, 
after the effective date of this AD.

(j) Exceptions to Service Information Specifications

    (1) Although Lockheed Martin Aeronautics Company Service 
Bulletin 382-57-95, including Appendix A, dated December 16, 2013, 
specifies to submit certain information to the manufacturer, this AD 
does not include that requirement.
    (2) Where Lockheed Martin Aeronautics Company Service Bulletin 
382-57-95, including Appendix A, dated December 16, 2013, specifies 
to contact Lockheed for repair instructions, before further flight, 
repair using a method approved in accordance with the procedures 
specified in paragraph (m) of this AD.

(k) Parts Installation Limitation

    After replacement of the left and right upper and lower rainbow 
fittings of the outer wing with new fittings, as required by 
paragraph (h) of this AD, any subsequent rainbow fitting 
replacements must be done using a method approved in accordance with 
the procedures specified in paragraph (m) of this AD.

(l) Outer Wing Flight Hours Adjustment

    For any wing on which the left or right upper and lower rainbow 
fittings of the outer wing have been replaced with new fittings as 
required by paragraph (h) of this AD: Before the accumulation of 
30,000 flight hours after accomplishing the replacement, do the 
inspection required by paragraph (g) of this AD and repeat 
thereafter at the times specified in paragraph (g) of this AD.

(m) Alternative Methods of Compliance (AMOCs)

    (1) The Manager, Atlanta Aircraft Certification Office (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) 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) An AMOC that provides an acceptable level of safety may be 
used for any repair required by this AD if it is approved by a 
Lockheed Martin Corporation/Lockheed Martin Aeronautics Company 
Designated Engineering Representative (DER) that has been authorized 
by the Manager, Atlanta ACO, to make those findings. For a repair 
method to be approved, the repair must meet the certification basis 
of the airplane, and the approval must specifically refer to this 
AD.

(n) Related Information

    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: 
<a href="/cdn-cgi/l/email-protection#b1f2d0c3dd9fe69ff6c3d0c8f1d7d0d09fd6dec7"><span class="__cf_email__" data-cfemail="82c1e3f0eeacd5acc5f0e3fbc2e4e3e3ace5edf4">[email&#160;protected]</span></a>.

(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 Aeronautics Company Service Bulletin 382-57-
95, including Appendix A, dated December 16, 2013.
    (ii) Reserved.
    (3) For Lockheed 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 <a href="/cdn-cgi/l/email-protection#22434f510c524d5056434e624e4f414d0c414d4f"><span class="__cf_email__" data-cfemail="8eefe3fda0fee1fcfaefe2cee2e3ede1a0ede1e3">[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 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.
    (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 March 6, 2015.
Jeffrey E. Duven,
Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 2015-05789 Filed 3-19-15; 8:45 am]
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