[Federal Register Volume 79, Number 200 (Thursday, October 16, 2014)]
[Proposed Rules]
[Pages 62075-62079]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2014-24549]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2014-0749; Directorate Identifier 2014-NM-051-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).

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SUMMARY: We propose to adopt a new airworthiness directive (AD) for 
certain Lockheed Martin Corporation/Lockheed Martin Aeronautics Company 
Model 382, 382B, 382E, 382F, and 382G airplanes. This proposed 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 proposed AD would 
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

[[Page 62076]]

and corrective actions if necessary; and replacement of the upper and 
lower rainbow fittings on the outer wing. We are proposing 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: We must receive comments on this proposed AD by December 1, 
2014.

ADDRESSES: You may send comments, using the procedures found in 14 CFR 
11.43 and 11.45, by any of the following methods:
    <bullet> Federal eRulemaking Portal: Go to http://www.regulations.gov. Follow the instructions for submitting comments.
    <bullet> Fax: 202-493-2251.
    <bullet> 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.
    <bullet> 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 <a href="/cdn-cgi/l/email-protection#7819150b5608170a0c19143814151b17561b1715"><span class="__cf_email__" data-cfemail="4e2f233d603e213c3a2f220e22232d21602d2123">[email protected]</span></a>; 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.

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-
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 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, GA 30337; phone: 404-474-
5554; fax: 404-474-5606; email: <a href="/cdn-cgi/l/email-protection#591a382b35770e771e2b3820193f3838773e362f"><span class="__cf_email__" data-cfemail="5a193b2836740d741d283b231a3c3b3b743d352c">[email protected]</span></a>.

SUPPLEMENTARY INFORMATION: 

Comments Invited

    We invite you to send any written relevant data, views, or 
arguments about this proposal. Send your comments to an address listed 
under the ADDRESSES section. Include ``Docket No. FAA-2014-0749; 
Directorate Identifier 2014-NM-051-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

    Structural fatigue damage is progressive. It begins as minute 
cracks, and those cracks grow under the action of repeated stresses. 
This can happen because of normal operational conditions and design 
attributes, or because of isolated situations or incidents such as 
material defects, poor fabrication quality, or corrosion pits, dings, 
or scratches. Fatigue damage can occur locally, in small areas or 
structural design details, or globally. Global fatigue damage is 
general degradation of large areas of structure with similar structural 
details and stress levels. Multiple-site damage is global damage that 
occurs in a large structural element such as a single rivet line of a 
lap splice joining two large skin panels. Global damage can also occur 
in multiple elements such as adjacent frames or stringers. Multiple-
site-damage and multiple-element-damage cracks are typically too small 
initially to be reliably detected with normal inspection methods. 
Without intervention, these cracks will grow, and eventually compromise 
the structural integrity of the airplane, in a condition known as WFD. 
As an airplane ages, WFD will likely occur, and will certainly occur if 
the airplane is operated long enough without any intervention.
    The FAA's WFD final rule (75 FR 69746, November 15, 2010) became 
effective on January 14, 2011. The WFD rule requires certain actions to 
prevent structural failure due to WFD throughout the operational life 
of certain existing transport category airplanes and all of these 
airplanes that will be certificated in the future. For existing and 
future airplanes subject to the WFD rule, the rule requires that DAHs 
establish a limit of validity (LOV) of the engineering data that 
support the structural maintenance program. Operators affected by the 
WFD rule may not fly an airplane beyond its LOV, unless an extended LOV 
is approved.
    The WFD rule (75 FR 69746, November 15, 2010) does not require 
identifying and developing maintenance actions if the DAHs can show 
that such actions are not necessary to prevent WFD before the airplane 
reaches the LOV. Many LOVs, however, do depend on accomplishment of 
future maintenance actions. As stated in the WFD rule, any maintenance 
actions necessary to reach the LOV will be mandated by airworthiness 
directives through separate rulemaking actions.
    In the context of WFD, this action is necessary to enable DAHs to 
propose LOVs that allow operators the longest operational lives for 
their airplanes, and still ensure that WFD will not occur. This 
approach allows for an implementation strategy that provides 
flexibility to DAHs in determining the timing of service information 
development (with FAA approval), while providing operators with 
certainty regarding the LOV applicable to their airplanes.
    This proposed AD was prompted by an evaluation by the DAH 
indicating that the upper and lower rainbow fittings of the outer wing 
are subject to WFD. Analysis of in-service cracking has shown that 
these fittings are susceptible to multiple site damage, and actions are 
required to ensure that cracking does not occur in the skin-panel-to-
fitting fastener holes, resulting in an unacceptable reduction in 
residual strength. Fatigue cracking of the upper and lower rainbow 
fittings of the outer wing and skin-panel-to-fitting fastener holes 
could result in reduced structural integrity of the airplane and 
possible separation of the wing from the airplane.

Relevant Service Information

    We reviewed Lockheed Service Bulletin 382-57-95, including Appendix 
A, dated December 16, 2013. This service bulletin describes procedures 
for repetitive inspections of the upper and lower rainbow fittings on 
the outer wing using an eddy current surface scan (ECSS) to detect 
cracks propagating from fasteners attaching the fittings to skin panels 
and a related

[[Page 62077]]

investigative action of an automated bolt hole eddy current inspection 
to confirm ECSS inspection crack findings if suspected; and corrective 
actions if necessary. Corrective actions include contacting the 
manufacturer for instructions if cracking is found.
    Lockheed Service Bulletin 382-57-95, including Appendix A, dated 
December 16, 2013, also describes procedures for replacing the upper 
and lower rainbow fittings on the outer wing, which includes doing a 
detailed inspection of the wing faying structure for damage (e.g. 
damage includes pitting, and corrosion) and cracks; an automated bolt 
hole eddy current inspection on all open fastener holes in the mating 
structure, stiffeners, webs, and angles for cracking; and corrective 
actions if necessary. Corrective actions include repairing damage and 
cracking in accordance with Lockheed Service Bulletin 382-57-95, 
including Appendix A, dated December 16, 2013; or contacting the 
manufacturer for instructions.

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 designs.

Proposed AD Requirements

    This proposed AD would require accomplishing the actions specified 
in the service information described previously, except as discussed 
under ``Differences Between This Proposed AD and the Service 
Information.''

Differences Between This Proposed AD and the Service Information

    Lockheed Service Bulletin 382-57-95, including Appendix A, dated 
December 16, 2013, specifies to contact the manufacturer for 
instructions on how to repair certain conditions, but this proposed AD 
would require repairing those conditions in one of the following ways:
    <bullet> In accordance with a method that we approve; or
    <bullet> Using data that meet the certification basis of the 
airplane, and that have been approved by the Lockheed Martin 
Corporation/Lockheed Martin Aeronautics Company Designated Engineering 
Representative (DER) whom we have authorized to make those findings.

Explanation of Compliance Time

    The compliance time for the replacement specified in this proposed 
AD for addressing WFD was established to ensure that discrepant 
structure is replaced before WFD develops in airplanes. Standard 
inspection techniques cannot be relied on to detect WFD before it 
becomes a hazard to flight. We will not grant any extensions of the 
compliance time to complete any AD-mandated service bulletin related to 
WFD without extensive new data that would substantiate and clearly 
warrant such an extension.

Costs of Compliance

    We estimate that this proposed AD affects 20 airplanes of U.S. 
registry.
    We estimate the following costs to comply with this proposed AD:

                                                 Estimated Costs
----------------------------------------------------------------------------------------------------------------
                                                             Parts                              Cost on U.S.
              Action                      Labor cost         cost       Cost per product          operators
----------------------------------------------------------------------------------------------------------------
ECSS inspection...................  24 work-hours x $85          $0  $2,040 per inspection  $40,800 per
                                     per hour = $2,040                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 proposed 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 proposed 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

    We 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

[[Page 62078]]

responsibilities among the various levels of government.
    For the reasons discussed above, I certify this 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. The FAA amends Sec.  39.13 by adding the following new airworthiness 
directive (AD):

Lockheed Martin Corporation/Lockheed Martin Aeronautics Company: 
Docket No. FAA-2014-0749; Directorate Identifier 2014-NM-051-AD.

(a) Comments Due Date

    We must receive comments by December 1, 2014.

(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 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 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 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 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 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 (FSLs) and critical design configuration control 
limitations (CDCCLs) 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 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 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

[[Page 62079]]

AD and repeat thereafter at the times specified in paragraph (g) of 
this AD.

(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.
    (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 
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

    (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: 
<a href="/cdn-cgi/l/email-protection#276446554b0970096055465e6741464609404851"><span class="__cf_email__" data-cfemail="ca89abb8a6e49de48db8abb38aacababe4ada5bc">[email protected]</span></a>.
    (2) 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#3f5e524c114f504d4b5e537f53525c50115c5052"><span class="__cf_email__" data-cfemail="b5d4d8c69bc5dac7c1d4d9f5d9d8d6da9bd6dad8">[email protected]</span></a>; Internet http://www.lockheedmartin.com/ams/tools/TechPubs.html. 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.


    Issued in Renton, Washington, on September 23, 2014.
Dionne Palermo,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 2014-24549 Filed 10-15-14; 8:45 am]
BILLING CODE 4910-13-P


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