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 

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: 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. 

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: 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 

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. 


jstallworth on DSK7TPTVN1PROD with RULES
Federal Register / Vol. 80, No. 214 / Thursday, November 5, 2015 / Rules and Regulations 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

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 

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 

■ 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 

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, 


jstallworth on DSK7TPTVN1PROD with RULES
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) 

(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: 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–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. 

[FR Doc. 2015–27919 Filed 11–4–15; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[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 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Final rule. 

SUMMARY: 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, 

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-2015-0244- 

0003. 

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 


jstallworth on DSK7TPTVN1PROD with RULES