[Federal Register Volume 80, Number 108 (Friday, June 5, 2015)]
[Proposed Rules]
[Pages 32069-32072]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2015-13339]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2015-1419; Directorate Identifier 2014-NM-183-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 all 
Lockheed Martin Corporation/Lockheed Martin Aeronautics Company Model 
188 series airplanes. This proposed AD was prompted by an evaluation by 
the design approval holder (DAH) indicating the left and right lower 
surface panels of the wings are subject to widespread fatigue damage 
(WFD). This proposed AD would require repetitive inspections for 
cracking at these panels, and repair if necessary. The proposed AD 
would also require a one-time bolt-hole eddy current inspection of all 
open holes for cracking, repair if necessary, and modification. We are 
proposing this AD to prevent fatigue cracking of the left and right 
lower surface panels of the wings, which could result in reduced 
structural integrity of the airplane.

DATES: We must receive comments on this proposed AD by July 20, 2015.

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.
     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 [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.

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-2015-
1419; 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: 404-474-5605; email: [email protected].

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-2015-1419; 
Directorate Identifier 2014-NM-183-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,

[[Page 32070]]

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 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 left and right lower surface panels of the wings 
are subject to WFD. The root cause of WFD is fatigue cracks manifesting 
and growing simultaneously at similar structural details and stress 
levels on the outer wings. Fatigue cracking is increasingly likely as 
the airplane is being operated and is aging; without intervention, 
fatigue cracking of the left and right lower surface panels of the 
wings on the inboard and outboard sides of the buttock line (BL) 65 
splice joint could result in reduced structural integrity of the 
airplane.

Related Service Information Under 1 CFR part 51

    We reviewed Lockheed Martin Electra Service Bulletin 88/SB-707C, 
Revision C, dated April 30, 2014. The service information describes 
procedures for repetitive inspections for cracking of the left and 
right lower surface panels of the wings on the inboard and outboard 
sides of the BL 65 splice joint, and repair if necessary. This service 
information also describes procedures for a one-time bolt-hole eddy 
current inspection of all open holes for cracking, repair if necessary, 
and modification of the BL 65 wing root joint. This service information 
is reasonably available because the interested parties have access to 
it through their normal course of business or by the means identified 
in the ADDRESSES section of this NPRM.

Related ADs

    This proposed AD is related to AD 81-03-53, Amendment 39-4243 
(Docket No. 81-NW-7-AD) (46 FR 52090, October 26, 1981); and AD 81-03-
53R1, Amendment 39-4301 (Docket No. 81-NW-97-AD) (47 FR 3347, January 
25, 1982); for all Lockheed Model L-188 series airplanes. AD 81-03-53R1 
requires inspecting for fuel leakage and fatigue cracks, and 
replacement, as necessary, of defective parts on the wing lower BL 65 
splice joints.

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.

Explanation of Compliance Time

    The compliance time for the modification 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 4 airplanes of U.S. 
registry.
    We estimate the following costs to comply with this proposed AD:

                                                 Estimated Costs
----------------------------------------------------------------------------------------------------------------
                                                                                                Cost on U.S.
             Action                  Labor cost        Parts cost      Cost per  product          operators
----------------------------------------------------------------------------------------------------------------
X-ray or ultrasonic inspections  Up to 40                        $0  Up to $3,400.........  Up to $13,600.
                                  work[dash]hours x
                                  $85 per hour = up
                                  to $3,400.
Bolt hole inspections..........  60 work-hours x                  0  $5,100...............  $20,400.
                                  $85 per hour =
                                  $5,100.
Modification...................  400 work-hours x             5,000  $39,000..............  $156,000.
                                  $85 per hour = $
                                  34,000.
----------------------------------------------------------------------------------------------------------------

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

[[Page 32071]]



                                               On-Condition Costs
----------------------------------------------------------------------------------------------------------------
                                                                                                     Cost per
                  Action                                Labor cost                 Parts cost        product
----------------------------------------------------------------------------------------------------------------
Repair....................................  500 work-hours x $85 per hour =                 $0          $42,500
                                             $42,500.
----------------------------------------------------------------------------------------------------------------

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 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 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-2015-1419; Directorate Identifier 2014-NM-183-AD.

(a) Comments Due Date

    We must receive comments by July 20, 2015.

(b) Affected ADs

    This AD affects AD 81-03-53, Amendment 39-4243 (Docket No. 81-
NW-7-AD) (46 FR 52090, October 26, 1981); and AD 81-03-53R1, 
Amendment 39-4301 (Docket No. 81-NW-97-AD) (47 FR 3347, January 25, 
1982).

(c) Applicability

    This AD applies to Lockheed Martin Corporation/Lockheed Martin 
Aeronautics Company Model 188A and 188C airplanes, certificated in 
any category, serial numbers 1001 and subsequent.

(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 indicating the left and right lower surface panels of the 
wings are subject to widespread fatigue damage. We are issuing this 
AD to prevent fatigue cracking of the left and right lower surface 
panels of the wings on the inboard and outboard sides of the buttock 
line (BL) 65 splice joint, which could result in reduced structural 
integrity of the airplane.

(f) Compliance

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

(g) Inspections and Repair

    At the later of the times specified in paragraphs (g)(1) and 
(g)(2) of this AD: Inspect for cracking of the inboard and outboard 
sides of the lower splice joint at BL 65, using X-ray, ultrasonic, 
and bolt-hole eddy current inspection techniques, as applicable, and 
repair any cracking found, in accordance with the Accomplishment 
Instructions of Lockheed Martin Electra Service Bulletin 88/SB-707C, 
Revision C, dated April 30, 2014. All applicable repairs must be 
done before further flight. Repeat the inspections at intervals not 
to exceed 2,000 flight hours, until the modification required by 
paragraph (h) of this AD has been done. Accomplishing the 
inspections required by this paragraph terminates the inspections 
required by paragraphs A. and B. of AD 81-03-53, Amendment 39-4243 
(Docket No. 81-NW-7-AD) (46 FR 52090, October 26, 1981); and AD 81-
03-53R1, Amendment 39-4301 (Docket No. 81-NW-97-AD) (47 FR 3347-01, 
January 25, 1982).
    (1) Before the accumulation of 19,000 total flight hours.
    (2) Within 600 flight hours or 365 days after the effective date 
of this AD, whichever occurs first.

(h) Modification

    At the later of the times specified in paragraphs (h)(1) and 
(h)(2) of this AD: Do a bolt-hole eddy current inspection of all 
open holes for cracking, repair any cracking found before further 
flight, and modify the BL 65 wing root lower joint, in accordance 
with the Accomplishment Instructions of Lockheed Martin Electra 
Service Bulletin 88/SB-707C, Revision C, dated April 30, 2014. 
Accomplishing this modification terminates the inspections required 
by paragraph (g) of this AD.
    (1) Before the accumulation of 29,000 total flight hours.
    (2) Within 600 flight hours or 365 days after the effective date 
of this AD, whichever occurs first.

(i) No Reporting Required

    Although Lockheed Martin Electra Service Bulletin 88/SB-707C, 
Revision C, dated April 30, 2014, specifies to submit a report of 
crack findings, this AD does not include that requirement.

(j) 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 (k)(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.

[[Page 32072]]

(k) Related Information

    (1) For more information about this AD, contact Carl Gray, 
Aerospace Engineer, Airframe Branch, ACE-117A, FAA, Atlanta ACO, 
1701 Columbia Avenue, College Park, GA 30337; phone: 404-474-5554; 
fax: 404-474-5605; email: [email protected].
    (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 [email protected]; 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 May 14, 2015.
Jeffrey E. Duven,
Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 2015-13339 Filed 6-4-15; 8:45 am]
 BILLING CODE 4910-13-P