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[Federal Register Volume 80, Number 196 (Friday, October 9, 2015)]
[Rules and Regulations]
[Pages 61098-61100]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2015-24465]

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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; 
Amendment 39-18279; AD 2015-20-01]
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 all 
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 the left and right lower 
surface panels of the wings are subject to widespread fatigue damage 
(WFD). This AD requires repetitive inspections for cracking at these 
panels, and repair if necessary. The AD also requires a one-time bolt-
hole eddy current inspection of all open holes for cracking, repair if 
necessary, and modification. We are issuing 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: This AD is effective November 13, 2015.
    The Director of the Federal Register approved the incorporation by 
reference of a certain publication listed in this AD as of November 13, 
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 ams.portal@lmco.com; 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-
1419.

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 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: carl.w.gray@faa.gov.

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 all Lockheed Martin 
Corporation/Lockheed Martin Aeronautics Company Model 188 series 
airplanes. The NPRM published in the Federal Register on June 5, 2015 
(80 FR 32069). The NPRM was prompted by an evaluation by the DAH 
indicating the left and right lower surface panels of the wings are 
subject to WFD. The NPRM proposed to require repetitive inspections for 
cracking at these panels, and repair if necessary. The NPRM also 
proposed to require a one-time bolt-hole eddy current inspection of all 
open holes for cracking, repair if necessary, and modification. We are 
issuing 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.

Comments

    We gave the public the opportunity to participate in developing 
this AD. We received no comments on the NPRM (80 FR 32069, June 5, 
2015) or on the determination of the cost to the public.

Conclusion

    We reviewed the available 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:
     Are consistent with the intent that was proposed in the 
NPRM (80 FR 32069, June 5, 2015) for correcting the unsafe condition; 
and
     Do not add any additional burden upon the public than was 
already proposed in the NPRM 80 FR 32069, June 5, 2015).

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 buttock line (BL) 65 splice joint, and repair. This 
service information also describes procedures for a one-time bolt-hole 
eddy current inspection of all open holes for cracking, repair, 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 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 61099]]

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

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

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

    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):

2015-20-01 Lockheed Martin Corporation/Lockheed Martin Aeronautics 
Company: Amendment 39-18279; Docket No. FAA-2015-1419; Directorate 
Identifier 2014-NM-183-AD.

(a) Effective Date

    This AD is effective November 13, 2015.

(b) Affected ADs

    This AD affects 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 81-03-53R1, Amendment 39-4301 
(Docket No. 81-NW-97-AD) (47 FR 3347, 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

[[Page 61100]]

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) 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

    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: carl.w.gray@faa.gov.

(l) 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-707C, 
Revision C, dated April 30, 2014.
    (ii) Reserved.
    (3) 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 ams.portal@lmco.com; Internet http://www.lockheedmartin.com/ams/tools/TechPubs.html.
    (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: http://www.archives.gov/federal-register/cfr/ibr-locations.html.

    Issued in Renton, Washington, on September 17, 2015.
John P. Piccola, Jr.,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 2015-24465 Filed 10-8-15; 8:45 am]
 BILLING CODE 4910-13-P
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