80 FR 30391 - Airworthiness Directives; Lockheed Martin Corporation/Lockheed Martin Aeronautics Company Airplanes

DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration

Federal Register Volume 80, Issue 102 (May 28, 2015)

We propose to adopt a new airworthiness directive (AD) for certain 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 that a certain circumferential fuselage splice is subject to widespread fatigue damage (WFD). This proposed AD would require an inspection for corrosion and previous repairs, severed stringers, cracking, and loose or distressed fasteners of the forward and aft ends of the stringer splices of certain stringers, inspection for cracking and modification of certain fastener holes common to the stringer and splice member at the forward and aft ends of the splice, and related investigative and corrective actions if necessary. We are proposing this AD to prevent loss of residual strength of a certain circumferential fuselage splice, which could lead to rapid decompression of the cabin and potential loss of the airplane.

[Federal Register Volume 80, Number 102 (Thursday, May 28, 2015)]
[Proposed Rules]
[Pages 30391-30394]
From the Federal Register Online  [www.thefederalregister.org]
[FR Doc No: 2015-12859]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2015-1425; Directorate Identifier 2014-NM-185-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 188 series airplanes. This proposed AD was prompted by an 
evaluation by the design approval holder (DAH) indicating that a 
certain circumferential fuselage splice is subject to widespread 
fatigue damage (WFD). This proposed AD would require an inspection for 
corrosion and previous repairs, severed stringers, cracking, and loose 
or distressed fasteners of the forward and aft ends of the stringer 
splices of certain stringers, inspection for cracking and modification 
of certain fastener holes common to the stringer and splice member at 
the forward and aft ends of the splice, and related investigative and 
corrective actions if necessary. We are proposing this AD to prevent 
loss of residual strength of a certain circumferential fuselage splice, 
which could lead to rapid decompression of the cabin and potential loss 
of the airplane.

DATES: We must receive comments on this proposed AD by July 13, 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; phone: 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-
1425; or in person at the Docket Management Facility between 9 a.m. and 
5 p.m., Monday through Friday,

[[Page 30392]]

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-2015-1425; 
Directorate Identifier 2014-NM-185-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 circumferential fuselage splice at fuselage-station 
(FS) 695 is subject to WFD. The root cause of this WFD is fatigue 
cracks manifesting and growing simultaneously at similar structural 
details and stress levels at the circumferential fuselage splice. 
Fatigue cracking is increasingly likely as the airplane is operated and 
aged, and without intervention, fatigue cracking could lead to loss of 
residual strength of the circumferential fuselage splice at FS 695, 
which could lead to rapid decompression of the cabin area and potential 
loss of the airplane.

Related Service Information Under 1 CFR Part 51

    We reviewed Lockheed Martin Electra Service Bulletin 88/SB-722, 
dated April 30, 2014. This service bulletin describes procedures for 
doing the following actions:
     A general visual inspection (GVI) for corrosion and 
previous repairs, severed stringers, cracking, and loose or distressed 
fasteners of the forward and aft ends of the stringer splices of 
stringers 1-7 and 66-72, and corrective actions if necessary.
     At stringers 1-7 and 66-72, removing the four rivets 
common to the stringer and splice member at the forward and aft ends of 
the splice and doing a bolt hole eddy current (BHEC) inspection or an 
equivalent inspection procedure for cracking in each of the fastener 
holes, and corrective actions if necessary.
     Corrective actions for cracked holes include reaming to 
the maximum permissible hole diameter of the next larger size rivet. If 
a crack indication remains after reaming, this service information 
specifies repairing the cracked stringer.
     If a severed stringer is found during the GVI, doing 
related investigative actions of an eddy current surface scan 
inspection for cracking of the fuselage skin at the skin-to-stringer 
attachments immediately forward and aft of the stringer break and 
confirming skin cracks with a dye penetrant inspection. Corrective 
actions include repairing the severed stringer or skin cracks.
     For holes without crack indications, other specified 
actions include modifying the fastener holes by reaming to a certain 
maximum permissible hole diameter of the same size rivet and installing 
replacement fasteners; or if original hole is larger than the maximum 
permissible diameter, installing the next rivet size and type.
    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.

FAA's Determination

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

Proposed AD Requirements

    This proposed AD would require accomplishing the actions specified 
in the service information described

[[Page 30393]]

previously, except as discussed under ``Differences Between this 
Proposed AD and the Service Information.''

Differences Between This Proposed AD and the Service Information

    Although Lockheed Martin Electra Service Bulletin 88/SB-722, dated 
April 30, 2014, specifies that crack indications should be confirmed by 
an alternate inspection method, this proposed AD would not require that 
action.
    Operators should note that, although the Accomplishment 
Instructions of Lockheed Martin Electra Service Bulletin 88/SB-722, 
dated April 30, 2014, describe procedures for submitting a report of 
damage, this proposed AD would not require that action.
    Lockheed Martin Electra Service Bulletin 88/SB-722, dated April 30, 
2014, does not describe corrective actions if any corrosion or previous 
repair is found, and if any loose or distressed fastener is found. This 
proposed AD would require repair.

Explanation of Proposed 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 per       Cost on U.S.
               Action                        Labor cost           Parts cost        product         operators
----------------------------------------------------------------------------------------------------------------
Inspections and Modification........  18 work-hours x $85 per          $5,000           $6,530          $26,120
                                       hour = $1,530.
----------------------------------------------------------------------------------------------------------------

    We have received no definitive data that would enable us to provide 
cost estimates for the on-condition actions 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 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-2015-1425; Directorate Identifier 2014-NM-185-AD.

(a) Comments Due Date

    We must receive comments by July 13, 2015.

(b) Affected ADs

    None.

(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 53, Fuselage.

(e) Unsafe Condition

    This AD was prompted by an evaluation by the design approval 
holder (DAH) indicating that the circumferential fuselage splice at 
fuselage-station (FS) 695 is subject to widespread fatigue damage 
(WFD). We are issuing this AD to prevent loss of residual strength 
of the circumferential fuselage splice at FS 695, which could lead 
to rapid decompression of the cabin and potential loss of the 
airplane.

(f) Compliance

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

(g) Inspections, Modification, Related Investigative Actions, and 
Corrective Actions

    Before the accumulation of 38,200 total flight hours or within 
30 days after the effective date of this AD, whichever occurs later: 
Do a general visual inspection for corrosion and previous repairs, 
severed stringers, cracking, and loose or distressed fasteners of 
the forward and aft ends of the stringer splices of stringers 1-7 
and 66-72; remove the four rivets common to the stringer and splice 
member at the forward and aft ends of the splice and do a bolt hole 
eddy current inspection or an equivalent inspection procedure for 
cracking in each of the fastener holes; modify the fastener holes;

[[Page 30394]]

and do all applicable related investigative and corrective actions 
and other specified actions; in accordance with the Accomplishment 
Instructions of Lockheed Martin Electra Service Bulletin 88/SB-722, 
dated April 30, 2014, except as specified in paragraph (h) of this 
AD. Do all applicable related investigative and corrective actions 
and other specified actions before further flight. If any repairs 
exceed the repair limits specified in Lockheed Martin Electra 
Service Bulletin 88/SB-722, dated April 30, 2014, before further 
flight, repair using a method approved in accordance with the 
procedures specified in paragraph (j) of this AD.

(h) Corrective Action

    (1) If, during any inspection required by paragraph (g) of this 
AD, any corrosion or previous repair is found, before further 
flight, repair using a method approved in accordance with the 
procedures specified in paragraph (j) of this AD.
    (2) If, during any inspection required by paragraph (g) of this 
AD, any loose or distressed fastener is found, before further 
flight, repair using a method approved in accordance with the 
procedures specified in paragraph (j) of this AD.

(i) Exception

    Although Lockheed Martin Electra Service Bulletin 88/SB-722, 
dated April 30, 2014, specifies to submit certain information to the 
manufacturer, this AD does not include that requirement.

(j) 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 
(j)(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.

(k) Related Information

    (1) For more information about this AD, 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; phone: 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 19, 2015.
Dionne Palermo,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 2015-12859 Filed 5-27-15; 8:45 am]
BILLING CODE 4910-13-P