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

[Federal Register Volume 80, Number 191 (Friday, October 2, 2015)]
[Rules and Regulations]
[Pages 59568-59570]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2015-24839]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2015-0493; Directorate Identifier 2014-NM-184-AD; 
Amendment 39-18283; AD 2015-20-05]
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 adopting a new airworthiness directive (AD) for certain 
Lockheed Martin Corporation/Lockheed Martin Aeronautics Company Model 
188 series airplanes. This AD was prompted by an evaluation by the 
design approval holder (DAH) indicating that the upper and lower wing 
skin planks at the attachment of the main landing gear (MLG) ribs at 
certain wing-stations are subject to widespread fatigue damage (WFD). 
This AD requires an inspection (for cracking) and modification of the 
chordwise fastener rows of the upper and lower wing planks at the 
attachments to the MLG ribs at certain wing-stations. We are issuing 
this AD to prevent fatigue cracking of the upper and lower wing skin 
planks at the attachment of the MLG ribs, which could result in failure 
of the wing.

DATES: This AD is effective November 6, 2015.
    The Director of the Federal Register approved the incorporation by 
reference of a certain publication listed in this AD as of November 6, 
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 [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-2015-
0493.

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-
0493; 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: 404-474-5605; email: [email protected].

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 188 series 
airplanes. The NPRM published in the Federal Register on March 24, 2015 
(80 FR 15525). The NPRM was prompted by an evaluation by the DAH 
indicating that the upper and lower wing skin planks at the attachment 
of the MLG ribs at certain wing-stations are subject to WFD. The NPRM 
proposed to require an inspection (for cracking) and modification of 
the chordwise fastener rows of the upper and lower wing planks at the 
attachments to the MLG ribs at certain wing-stations. We are issuing 
this AD to prevent fatigue cracking of the upper and lower wing skin 
planks at the attachment of the MLG ribs, which could result in failure 
of the wing.

Comments

    We gave the public the opportunity to participate in developing 
this AD. We received no comments on the NPRM (80 FR 15525, March 24, 
2015) 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 (80 FR 15525, March 24, 2015) for correcting the unsafe condition; 
and
    <bullet> Do not add any additional burden upon the public than was 
already proposed in the NPRM (80 FR 15525, March 24, 2015).
    We also determined that these changes will not increase the 
economic burden on any operator or increase the scope of this AD.

Related Service Information Under 1 CFR Part 51

    We reviewed Lockheed Martin Electra Service Bulletin 88/SB-721, 
dated April 30, 2014. This service information describes procedures for 
doing a bolt-hole eddy current (BHEC) inspection for cracking and 
repair of cracking. This service information also describes procedures 
for modification of the chordwise fastener rows of the upper and lower 
wing planks at the attachments to the MLG ribs at wing-station (WS) 167 
and WS 209 by removing the original fasteners and replacing them with 
new first oversize fasteners of the same type or approved substitute 
type for original fasteners. 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 AD.

Costs of Compliance

    We estimate that this AD affects 4 airplanes of U.S. registry.
    We estimate the following costs to comply with this AD:

[[Page 59569]]



                                                 Estimated Costs
----------------------------------------------------------------------------------------------------------------
                                                                                    Cost per       Cost on U.S.
               Action                        Labor cost           Parts cost        product         operators
----------------------------------------------------------------------------------------------------------------
Inspection and Modification.........  560 work-hours x $85             $5,000          $52,600         $210,400
                                       per hour = $47,600.
----------------------------------------------------------------------------------------------------------------

    We have received no definitive data that will enable us to provide 
cost estimates for the on-condition actions 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):

2015-20-05 Lockheed Martin Corporation/Lockheed Martin Aeronautics 
Company: Amendment 39-18283; Docket No. FAA-2015-0493; Directorate 
Identifier 2014-NM-184-AD.

(a) Effective Date

    This AD is effective November 6, 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 57, Wings.

(e) Unsafe Condition

    This AD was prompted by an evaluation by the design approval 
holder indicating that the upper and lower wing skin planks at the 
attachment of the main landing gear (MLG) ribs at certain wing-
stations are subject to widespread fatigue damage. We are issuing 
this AD to prevent fatigue cracking of the upper and lower wing skin 
planks at the attachment of the MLG ribs, which could result in 
failure of the wing.

(f) Compliance

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

(g) Inspection, Modification, and Corrective Action

    At the later of the times specified in paragraphs (g)(1) and 
(g)(2) of this AD: Remove the chordwise fastener rows of the upper 
and lower wing planks at the attachments to the MLG ribs at wing-
station (WS) 167 and WS 209; do a bolt-hole eddy current (BHEC) 
inspection to detect cracking of the fastener rows; and replace the 
original fasteners with new, first oversize fasteners; in accordance 
with the Accomplishment Instructions of Lockheed Martin Electra 
Service Bulletin 88/SB-721, dated April 30, 2014. If any cracking is 
found during any inspection required by this paragraph: Before 
further flight, repair the cracking, in accordance with the 
Accomplishment Instructions of Lockheed Martin Electra Service 
Bulletin 88/SB-721, dated April 30, 2014.
    (1) At the applicable time specified table 1 of paragraph 1.E., 
``Compliance,'' of Lockheed Martin Electra Service Bulletin 88/SB-
721, dated April 30, 2014. Where table 1 of paragraph 1.E., 
``Compliance,'' of Lockheed Martin Electra Service Bulletin 88/SB-
721, dated April 30, 2014, specifies ``Flt. Hrs,'' this AD specifies 
``total flight hours.''
    (2) Within 365 days or 600 flight hours after the effective date 
of this AD, whichever occurs first.

(h) No Reporting

    Although Lockheed Martin Electra Service Bulletin 88/SB-721, 
dated April 30, 2014, specifies to submit certain information to the 
manufacturer, this AD does not include that requirement.

(i) 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) 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.

(j) Related Information

    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].

(k) 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 Electra Service Bulletin 88/SB-721, dated 
April 30, 2014.

[[Page 59570]]

    (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 [email protected]; Internet http://www.lockheedmartin.com/ams/tools/TechPubs.html.
    (4) 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.
    (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: http://www.archives.gov/federal-register/cfr/ibr-locations.html.

    Issued in Renton, Washington, on September 18, 2015.
Dorr M. Anderson,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 2015-24839 Filed 10-1-15; 8:45 am]
 BILLING CODE 4910-13-P

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