Source: https://regulations.justia.com/regulations/fedreg/2015/11/05/2015-27919.html
Timestamp: 2020-07-13 20:45:50
Document Index: 309280112

Matched Legal Cases: ['art 39', 'art 39', 'art 51', 'art 39', 'art 39', 'ART 39', 'art 39', '§ 39', '§ 39', 'art 51', 'art 39', 'art 39', 'art 1', 'art 1', 'art 39']

Airworthiness Directives; Lockheed Martin Corporation/Lockheed Martin Aeronautics Company Airplanes, 68432-68434 [2015-27919] :: Federal Aviation Administration :: Department Of Transportation :: Regulation Tracker :: Justia
Justia Regulation Tracker Department Of Transportation Federal Aviation Administration Airworthiness Directives; Lockheed Martin Corporation/Lockheed Martin Aeronautics Company Airplanes, 68432-68434 [2015-27919]
Airworthiness Directives; Lockheed Martin Corporation/Lockheed Martin Aeronautics Company Airplanes, 68432-68434 [2015-27919]
Download as PDF 68432 Federal Register / Vol. 80, No. 214 / Thursday, November 5, 2015 / Rules and Regulations www.archives.gov/federal-register/cfr/ibrlocations.html. Issued in Renton, Washington, on October 22, 2015. Jeffrey E. Duven, Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 2015–27688 Filed 11–4–15; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration Examining the AD Docket 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 Federal Aviation Administration (FAA), DOT. ACTION: Final rule. AGENCY: 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 jstallworth on DSK7TPTVN1PROD with RULES SUMMARY: VerDate Sep<11>2014 14:34 Nov 04, 2015 30063; phone: 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–2015–1425. Jkt 238001 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: 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 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 PO 00000 Frm 00012 Fmt 4700 Sfmt 4700 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. E:\FR\FM\05NOR1.SGM 05NOR1 Federal Register / Vol. 80, No. 214 / Thursday, November 5, 2015 / Rules and Regulations • 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. 68433 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 Action Labor cost Parts cost Cost per product Cost on U.S. operators Inspections and Modification ............ 18 work-hours × $85 per hour = $1,530 ....................... $5,000 $6,530 $26,120 under the criteria of the Regulatory Flexibility Act. 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. jstallworth on DSK7TPTVN1PROD with RULES 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 VerDate Sep<11>2014 14:34 Nov 04, 2015 Jkt 238001 List of Subjects in 14 CFR Part 39 Air transportation, Aircraft, Aviation safety, Incorporation by reference, Safety. 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. 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 1. The authority citation for part 39 continues to read as follows: ■ Authority: 49 U.S.C. 106(g), 40113, 44701. § 39.13 [Amended] 2. The FAA amends § 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 PO 00000 Frm 00013 Fmt 4700 Sfmt 4700 (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, E:\FR\FM\05NOR1.SGM 05NOR1 68434 Federal Register / Vol. 80, No. 214 / Thursday, November 5, 2015 / Rules and Regulations specifies to submit certain information to the manufacturer, this AD does not include that requirement. (j) Alternative Methods of Compliance (AMOCs) (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: carl.w.gray@faa.gov. (l) Material Incorporated by Reference jstallworth on DSK7TPTVN1PROD with RULES (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: ams.portal@lmco.com; 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/ibrlocations.html. Issued in Renton, Washington, on October 22, 2015. Jeffrey E. Duven, Manager, Transport Airplane Directorate, Aircraft Certification Service. BILLING CODE 4910–13–P VerDate Sep<11>2014 14:34 Nov 04, 2015 Jkt 238001 Federal Aviation Administration 14 CFR Part 39 (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. [FR Doc. 2015–27919 Filed 11–4–15; 8:45 am] DEPARTMENT OF TRANSPORTATION [Docket No. FAA–2015–0244; Directorate Identifier 2014–NM–127–AD; Amendment 39–18313; AD 2015–22–08] RIN 2120–AA64 Airworthiness Directives; Airbus Airplanes Federal Aviation Administration (FAA), Department of Transportation (DOT). ACTION: Final rule. AGENCY: We are adopting a new airworthiness directive (AD) for all Airbus Model A318, A319, and A320 series airplanes. This AD was prompted by a cracked upper cardan in the main landing gear (MLG). This AD requires revising the maintenance or inspection program, as applicable, to reduce the life limits for the MLG upper cardan for certain installations. We are issuing this AD to prevent failure of the upper cardan in the MLG, which could result in MLG collapse and subsequent damage to the airplane and injury to occupants. DATES: This AD becomes 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: You may examine the AD docket on the Internet at http:// www.regulations.gov/ #!docketDetail;D=FAA-2015-0244; or in person at the 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. For service information identified in this AD, contact Airbus, Airworthiness Office—EIAS, 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex, France; telephone +33 5 61 93 36 96; fax +33 5 61 93 44 51; email account.airwortheas@airbus.com; Internet http:// www.airbus.com. 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–2015–0244. FOR FURTHER INFORMATION CONTACT: Sanjay Ralhan, Aerospace Engineer, SUMMARY: PO 00000 Frm 00014 Fmt 4700 Sfmt 4700 International Branch, ANM–116, Transport Airplane Directorate, FAA, 1601 Lind Avenue SW., Renton, WA 98057–3356; telephone 425–227–1405; fax 425–227–1149. 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 Airbus Model A318, A319, and A320 series airplanes. The NPRM published in the Federal Register on March 5, 2015 (80 FR 11964). The European Aviation Safety Agency (EASA), which is the Technical Agent for the Member States of the European Union, has issued EASA Airworthiness Directive 2014–0141, dated June 4, 2014 (referred to after this as the Mandatory Continuing Airworthiness Information, or ‘‘the MCAI’’), to correct an unsafe condition for all Airbus Model A318, A319, and A320 series airplanes. The MCAI states: During an A320–200 77T main landing gear (MLG) fatigue test by Messier BugattiDowty (MBD), an upper cardan was found with a crack, emanating from the grease hole/ main lug intersection. The affected upper cardan, Part Number (P/N) 201163620, is listed in the applicable Airworthiness Limitations Section (ALS) Part 1 with a demonstrated fatigue life of 60,000 landings. This condition, if not corrected, could lead to MLG upper cardan failure, possibly resulting in MLG collapse and subsequent damage to the aeroplane and injury to occupants. Prompted by these findings and further to analysis, it has been decided to reduce the life limit for certain installations of the P/N 201163620 MLG upper cardan. For the reasons described above, this AD requires implementation of the new life limits, as applicable, and replacement of any affected MLG upper cardan units that have already exceeded the reduced limit. The reduced life limits for the affected MLG upper cardan are expected to be incorporated in a next revision of the Airbus A318/A319/A320/A321 ALS Part 1. You may examine the MCAI in the AD docket on the Internet at http:// www.regulations.gov/ #!documentDetail;D=FAA-2015-02440003. Comments We gave the public the opportunity to participate in developing this AD. The following presents the comments received on the NPRM (80 FR 11964, March 5, 2015) and the FAA’s response to each comment. Request To Extend the Compliance Time Delta Airlines (DAL) requested that paragraph (g) of the proposed AD (80 FR E:\FR\FM\05NOR1.SGM 05NOR1
[Pages 68432-68434]
[FR Doc No: 2015-27919]
[Docket No. FAA-2015-1425; Directorate Identifier 2014-NM-185-AD;
Amendment 39-18312; AD 2015-22-07]
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
DATES: This AD is effective December 10, 2015.
reference of a certain publication listed in this AD as of December 10,
Drive, Marietta, GA 30063; phone: 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
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; or in person at the Docket Management Facility between 9 a.m. and
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
residual strength of a certain circumferential fuselage splice, which
could lead to rapid decompression of the cabin and potential loss of
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.
NPRM (80 FR 30391, May 28, 2015) for correcting the unsafe condition;
already proposed in the NPRM (80 FR 30391, May 28, 2015).
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
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 the original hole is larger than the
maximum permissible diameter, installing the next rivet size and type.
Inspections and Modification........  18 work-hours x $85 per          $5,000           $6,530          $26,120
2015-22-07 Lockheed Martin Corporation/Lockheed Martin Aeronautics
Company: Amendment 39-18312 ; Docket No. FAA-2015-1425; Directorate
Identifier 2014-NM-185-AD.
This AD is effective December 10, 2015.
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
(g) Inspections, Modification, Related Investigative Actions, and
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
(1) If, during any inspection required by paragraph (g) of this
AD, any corrosion or previous repair is found, before further
(2) If, during any inspection required by paragraph (g) of this
AD, any loose or distressed fastener is found, before further
Although Lockheed Martin Electra Service Bulletin 88/SB-722,
dated April 30, 2014,
For more information about this AD, Carl Gray, Aerospace
(i) Lockheed Martin Electra Service Bulletin 88/SB-722, dated
(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: ams.portal@lmco.com; Internet http://www.lockheedmartin.com/ams/tools/TechPubs.html.
Issued in Renton, Washington, on October 22, 2015.
[FR Doc. 2015-27919 Filed 11-4-15; 8:45 am]