80 FR 68432 - Airworthiness Directives; Lockheed Martin Corporation/Lockheed Martin Aeronautics Company Airplanes

DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration

Federal Register Volume 80, Issue 214 (November 5, 2015)

Page Range		68432-68434
FR Document		2015-27919

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 circumferential fuselage splice at fuselage-station (FS) 695 is subject to widespread fatigue damage (WFD). This AD requires 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 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.

Federal Register, Volume 80 Issue 214 (Thursday, November 5, 2015)

[Federal Register Volume 80, Number 214 (Thursday, November 5, 2015)]
[Rules and Regulations]
[Pages 68432-68434]
From the Federal Register Online  [www.thefederalregister.org]
[FR Doc No: 2015-27919]


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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; 
Amendment 39-18312; AD 2015-22-07]
RIN 2120-AA64


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

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Final rule.

-----------------------------------------------------------------------

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 circumferential 
fuselage splice at fuselage-station (FS) 695 is subject to widespread 
fatigue damage (WFD). This AD requires 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 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.

DATES: This AD is effective December 10, 2015.
    The Director of the Federal Register approved the incorporation by 
reference of a certain publication listed in this AD as of December 10, 
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; 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. It is also available on the Internet at http://www.regulations.gov by searching for and locating Docket No. FAA-2015-
1425.

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, 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 May 28, 2015 
(80 FR 30391). The NPRM was prompted by an evaluation by the DAH 
indicating that a certain circumferential fuselage splice is subject to 
WFD. The NPRM proposed to 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 issuing 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.

Comments

    We gave the public the opportunity to participate in developing 
this AD. We received no comments on the NPRM (80 FR 30391, May 28, 
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:
     Are consistent with the intent that was proposed in the 
NPRM (80 FR 30391, May 28, 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 30391, May 28, 2015).

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.

[[Page 68433]]

     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 the 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 
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:

                                                 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 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):

2015-22-07 Lockheed Martin Corporation/Lockheed Martin Aeronautics 
Company: Amendment 39-18312 ; Docket No. FAA-2015-1425; Directorate 
Identifier 2014-NM-185-AD.

(a) Effective Date

    This AD is effective December 10, 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; 
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,

[[Page 68434]]

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 
(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, 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].

(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-722, dated 
April 30, 2014.
    (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; phone: 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 October 22, 2015.
Jeffrey E. Duven,
Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 2015-27919 Filed 11-4-15; 8:45 am]
BILLING CODE 4910-13-P

68432 Federal Register / Vol. 80, No. 214 / Thursday, November 5, 2015 / Rules and Regulations

www.archives.gov/federal-register/cfr/ibr- 30063; phone: 770–494–5444; fax: 770– residual strength of a certain
locations.html. 494–5445; email: ams.portal@lmco.com; circumferential fuselage splice, which
Issued in Renton, Washington, on October Internet http:// could lead to rapid decompression of
22, 2015. www.lockheedmartin.com/ams/tools/ the cabin and potential loss of the
Jeffrey E. Duven, TechPubs.html. You may view this airplane.
Manager, Transport Airplane Directorate,
referenced service information at the
Comments
Aircraft Certification Service. FAA, Transport Airplane Directorate,
1601 Lind Avenue SW., Renton, WA. We gave the public the opportunity to
[FR Doc. 2015–27688 Filed 11–4–15; 8:45 am]
For information on the availability of participate in developing this AD. We
BILLING CODE 4910–13–P
this material at the FAA, call 425–227– received no comments on the NPRM (80
1221. It is also available on the Internet FR 30391, May 28, 2015) or on the
at http://www.regulations.gov by determination of the cost to the public.
DEPARTMENT OF TRANSPORTATION
searching for and locating Docket No. Conclusion
Federal Aviation Administration FAA–2015–1425.
We reviewed the relevant data and
Examining the AD Docket determined that air safety and the
14 CFR Part 39
You may examine the AD docket on public interest require adopting this AD
[Docket No. FAA–2015–1425; Directorate the Internet at http:// as proposed except for minor editorial
Identifier 2014–NM–185–AD; Amendment changes. We have determined that these
www.regulations.gov by searching for
39–18312; AD 2015–22–07] minor changes:
and locating Docket No. FAA–2015–
RIN 2120–AA64 1425; or in person at the Docket • Are consistent with the intent that
Management Facility between 9 a.m. was proposed in the NPRM (80 FR
Airworthiness Directives; Lockheed and 5 p.m., Monday through Friday, 30391, May 28, 2015) for correcting the
Martin Corporation/Lockheed Martin except Federal holidays. The AD docket unsafe condition; and
Aeronautics Company Airplanes contains this AD, the regulatory • Do not add any additional burden
evaluation, any comments received, and upon the public than was already
AGENCY: Federal Aviation proposed in the NPRM (80 FR 30391,
Administration (FAA), DOT. other information. The address for the
Docket Office (phone: 800–647–5527) is May 28, 2015).
ACTION: Final rule.
Docket Management Facility, U.S. Related Service Information Under 1
SUMMARY: We are adopting a new Department of Transportation, Docket CFR Part 51
airworthiness directive (AD) for certain Operations, M–30, West Building
We reviewed Lockheed Martin Electra
Lockheed Martin Corporation/Lockheed Ground Floor, Room W12–140, 1200
Service Bulletin 88/SB–722, dated April
Martin Aeronautics Company Model New Jersey Avenue SE., Washington,
30, 2014. This service bulletin describes
188 series airplanes. This AD was DC 20590.
procedures for doing the following
prompted by an evaluation by the FOR FURTHER INFORMATION CONTACT: Carl actions:
design approval holder (DAH) Gray, Aerospace Engineer, Airframe • A general visual inspection (GVI)
indicating that the circumferential Branch, ACE–117A, FAA, Atlanta for corrosion and previous repairs,
fuselage splice at fuselage-station (FS) Aircraft Certification Office (ACO), 1701 severed stringers, cracking, and loose or
695 is subject to widespread fatigue Columbia Avenue, College Park, GA distressed fasteners of the forward and
damage (WFD). This AD requires an 30337; phone: 404–474–5554; fax: 404– aft ends of the stringer splices of
inspection for corrosion and previous 474–5605; email: carl.w.gray@faa.gov. stringers 1–7 and 66–72, and corrective
repairs, severed stringers, cracking, and SUPPLEMENTARY INFORMATION: actions if necessary.
loose or distressed fasteners of the • At stringers 1–7 and 66–72,
forward and aft ends of the stringer Discussion
removing the four rivets common to the
splices of certain stringers, inspection We issued a notice of proposed stringer and splice member at the
for cracking and modification of certain rulemaking (NPRM) to amend 14 CFR forward and aft ends of the splice and
fastener holes common to the stringer part 39 by adding an AD that would doing a bolt hole eddy current (BHEC)
and splice member at the forward and apply to certain Lockheed Martin inspection or an equivalent inspection
aft ends of the splice, and related Corporation/Lockheed Martin procedure for cracking in each of the
investigative and corrective actions if Aeronautics Company Model 188 series fastener holes, and corrective actions if
necessary. We are issuing this AD to airplanes. The NPRM published in the necessary.
prevent loss of residual strength of the Federal Register on May 28, 2015 (80 • Corrective actions for cracked holes
circumferential fuselage splice at FS FR 30391). The NPRM was prompted by include reaming to the maximum
695, which could lead to rapid an evaluation by the DAH indicating permissible hole diameter of the next
decompression of the cabin and that a certain circumferential fuselage larger size rivet. If a crack indication
potential loss of the airplane. splice is subject to WFD. The NPRM remains after reaming, this service
DATES: This AD is effective December proposed to require an inspection for information specifies repairing the
10, 2015. corrosion and previous repairs, severed cracked stringer.
The Director of the Federal Register stringers, cracking, and loose or • If a severed stringer is found during
approved the incorporation by reference distressed fasteners of the forward and the GVI, doing related investigative
of a certain publication listed in this AD aft ends of the stringer splices of certain actions of an eddy current surface scan
jstallworth on DSK7TPTVN1PROD with RULES

as of December 10, 2015. stringers, inspection for cracking and inspection for cracking of the fuselage
ADDRESSES: For service information modification of certain fastener holes skin at the skin-to-stringer attachments
identified in this AD, contact Lockheed common to the stringer and splice immediately forward and aft of the
Martin Corporation/Lockheed Martin member at the forward and aft ends of stringer break and confirming skin
Aeronautics Company, Airworthiness the splice, and related investigative and cracks with a dye penetrant inspection.
Office, Dept. 6A0M, Zone 0252, Column corrective actions if necessary. We are Corrective actions include repairing the
P–58, 86 S. Cobb Drive, Marietta, GA issuing this AD to prevent loss of severed stringer or skin cracks.

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Federal Register / Vol. 80, No. 214 / Thursday, November 5, 2015 / Rules and Regulations 68433

• For holes without crack indications, maximum permissible diameter, Costs of Compliance
other specified actions include installing the next rivet size and type.
modifying the fastener holes by reaming This service information is reasonably We estimate that this AD affects 4
to a certain maximum permissible hole available because the interested parties airplanes of U.S. registry.
diameter of the same size rivet and have access to it through their normal We estimate the following costs to
installing replacement fasteners; or if course of business or by the means comply with this AD:
the original hole is larger than the identified in the ADDRESSES section of
this AD.

ESTIMATED COSTS
Cost per Cost on
Action Labor cost Parts cost product U.S. operators

Inspections and Modification ............ 18 work-hours × $85 per hour = $1,530 ....................... $5,000 $6,530 $26,120

We have received no definitive data under the criteria of the Regulatory at FS 695, which could lead to rapid
that would enable us to provide cost Flexibility Act. decompression of the cabin and potential
estimates for the on-condition actions loss of the airplane.
List of Subjects in 14 CFR Part 39
specified in this AD. (f) Compliance
Air transportation, Aircraft, Aviation Comply with this AD within the
Authority for This Rulemaking safety, Incorporation by reference, compliance times specified, unless already
Title 49 of the United States Code Safety. done.
specifies the FAA’s authority to issue Adoption of the Amendment (g) Inspections, Modification, Related
rules on aviation safety. Subtitle I, Investigative Actions, and Corrective
section 106, describes the authority of Accordingly, under the authority
Actions
the FAA Administrator. Subtitle VII: delegated to me by the Administrator,
the FAA amends 14 CFR part 39 as Before the accumulation of 38,200 total
Aviation Programs, describes in more flight hours or within 30 days after the
detail the scope of the Agency’s follows:
effective date of this AD, whichever occurs
authority. later: Do a general visual inspection for
PART 39—AIRWORTHINESS
We are issuing this rulemaking under corrosion and previous repairs, severed
DIRECTIVES stringers, cracking, and loose or distressed
the authority described in Subtitle VII,
Part A, Subpart III, Section 44701: fasteners of the forward and aft ends of the
■ 1. The authority citation for part 39 stringer splices of stringers 1–7 and 66–72;
‘‘General requirements.’’ Under that continues to read as follows: remove the four rivets common to the
section, Congress charges the FAA with stringer and splice member at the forward
Authority: 49 U.S.C. 106(g), 40113, 44701.
promoting safe flight of civil aircraft in and aft ends of the splice and do a bolt hole
air commerce by prescribing regulations § 39.13 [Amended] eddy current inspection or an equivalent
for practices, methods, and procedures ■ 2. The FAA amends § 39.13 by adding inspection procedure for cracking in each of
the Administrator finds necessary for the fastener holes; modify the fastener holes;
the following new airworthiness and do all applicable related investigative
safety in air commerce. This regulation directive (AD):
is within the scope of that authority and corrective actions and other specified
2015–22–07 Lockheed Martin Corporation/ actions; in accordance with the
because it addresses an unsafe condition Accomplishment Instructions of Lockheed
Lockheed Martin Aeronautics Company:
that is likely to exist or develop on Amendment 39–18312 ; Docket No. Martin Electra Service Bulletin 88/SB–722,
products identified in this rulemaking FAA–2015–1425; Directorate Identifier dated April 30, 2014, except as specified in
action. 2014–NM–185–AD. paragraph (h) of this AD. Do all applicable
related investigative and corrective actions
Regulatory Findings (a) Effective Date and other specified actions before further
This AD will not have federalism This AD is effective December 10, 2015. flight. If any repairs exceed the repair limits
implications under Executive Order specified in Lockheed Martin Electra Service
(b) Affected ADs Bulletin 88/SB–722, dated April 30, 2014,
13132. This AD will not have a before further flight, repair using a method
None.
substantial direct effect on the States, on approved in accordance with the procedures
the relationship between the national (c) Applicability specified in paragraph (j) of this AD.
government and the States, or on the This AD applies to Lockheed Martin
Corporation/Lockheed Martin Aeronautics (h) Corrective Action
distribution of power and
responsibilities among the various Company Model 188A and 188C airplanes, (1) If, during any inspection required by
levels of government. certificated in any category, serial numbers paragraph (g) of this AD, any corrosion or
1001 and subsequent. previous repair is found, before further flight,
For the reasons discussed above, I repair using a method approved in
certify that this AD: (d) Subject accordance with the procedures specified in
(1) Is not a ‘‘significant regulatory Air Transport Association (ATA) of paragraph (j) of this AD.
action’’ under Executive Order 12866, America Code 53, Fuselage. (2) If, during any inspection required by
(2) Is not a ‘‘significant rule’’ under paragraph (g) of this AD, any loose or
(e) Unsafe Condition
jstallworth on DSK7TPTVN1PROD with RULES

DOT Regulatory Policies and Procedures distressed fastener is found, before further
(44 FR 11034, February 26, 1979), This AD was prompted by an evaluation by flight, repair using a method approved in
the design approval holder (DAH) indicating accordance with the procedures specified in
(3) Will not affect intrastate aviation that the circumferential fuselage splice at paragraph (j) of this AD.
in Alaska, and fuselage-station (FS) 695 is subject to
(4) Will not have a significant widespread fatigue damage (WFD). We are (i) Exception
economic impact, positive or negative, issuing this AD to prevent loss of residual Although Lockheed Martin Electra Service
on a substantial number of small entities strength of the circumferential fuselage splice Bulletin 88/SB–722, dated April 30, 2014,

VerDate Sep<11>2014 14:34 Nov 04, 2015 Jkt 238001 PO 00000 Frm 00013 Fmt 4700 Sfmt 4700 E:\FR\FM\05NOR1.SGM 05NOR1

Document Created: 2015-12-14 15:03:55
Document Modified: 2015-12-14 15:03:55

Category		Regulatory Information
Collection		Federal Register
sudoc Class		AE 2.7: GS 4.107: AE 2.106:
Publisher		Office of the Federal Register, National Archives and Records Administration
Section		Rules and Regulations
Action		Final rule.
Dates		This AD is effective December 10, 2015.
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]
FR Citation		80 FR 68432
RIN Number		2120-AA64
CFR Associated		Air Transportation; Aircraft; Aviation Safety; Incorporation by Reference and Safety

80 FR 68432 - Airworthiness Directives; Lockheed Martin Corporation/Lockheed Martin Aeronautics Company Airplanes

DEPARTMENT OF TRANSPORTATIONFederal Aviation Administration

Federal Register Volume 80, Issue 214 (November 5, 2015)

DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration