Federal Register / Vol. 80, No. 161 / Thursday, August 20, 2015 / Rules and Regulations 50551 

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 

We have determined that 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 to the extent that it justifies 

making a regulatory distinction; 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 

removing Airworthiness Directive (AD) 

2001–13–51, Amendment 39-12443 (66 

FR 48535, September 21, 2001), and 

adding the following new AD: 

2015–17–02 Bell Helicopter Textron 

Canada (Bell): Amendment 39–18235; 

Docket No. FAA–2014–0643; Directorate 

Identifier 2013–SW–059–AD. 

(a) Applicability 

This AD applies to Model 206L–4, 407, 

427, and 429 helicopters with an engine-totransmission driveshaft assembly 

(driveshaft), part number (P/N) 206–340– 

300–105, installed, certificated in any 

category. 

(b) Unsafe Condition 

This AD defines the unsafe condition as 

failure of a driveshaft due to cracking of the 

flex frame on the forward end of the 

driveshaft. This condition could result in loss 

of drive to the main rotor system and a 

subsequent emergency forced landing. 

(c) Affected ADs 

This AD supersedes AD 2001–13–51, 

Amendment 39–12443, Docket No. 2001– 

SW–29–AD (66 FR 48535, September 21, 

2001). 

(d) Effective Date 

This AD becomes effective September 24, 

2015. 

(e) Compliance 

You are responsible for performing each 

action required by this AD within the 

specified compliance time unless it has 

already been accomplished prior to that time. 

(f) Required Actions 

(1) Within 50 hours time-in-service (TIS), 

determine whether driveshaft, P/N 206–340– 

300–105, has ever been installed on a Bell 

Model 407 helicopter, and record this on the 

component history card or equivalent record. 

If driveshaft, P/N 206–340–300–105, has ever 

been installed on a Bell Model 407 

helicopter: 

(i) For Bell Model 206L–4, 407, and 427 

helicopters, within 25 hours TIS, inspect 

each driveshaft for a crack, a loose bolt or 

nut, and red powder residue. If there is a 

crack, a loose bolt or nut, or red powder 

residue, replace the driveshaft with an 

airworthy driveshaft before further flight. 

(ii) For all affected Bell model helicopters, 

on or before accumulating 1,250 hours TIS, 

replace each driveshaft with an airworthy 

driveshaft. 

(2) Do not install driveshaft, P/N 206–340– 

300–105, on any helicopter if it has ever been 

installed on a Bell Model 407 helicopter. 

(g) Special Flight Permit 

Special flight permits are prohibited. 

(h) Alternative Methods of Compliance 

(AMOCs) 

(1) The Manager, Safety Management 

Group, FAA, may approve AMOCs for this 

AD. Send your proposal to: Matthew Fuller, 

Aviation Safety Engineer, Safety Management 

Group, Rotorcraft Directorate, FAA, 10101 

Hillwood Pkwy, Fort Worth, Texas 76177; 

telephone (817) 222–5110; email 9-ASWFTW-AMOC-Requests@faa.gov. 

(2) For operations conducted under a 14 

CFR part 119 operating certificate or under 

14 CFR part 91, subpart K, we suggest that 

you notify your principal inspector, or 

lacking a principal inspector, the manager of 

the local flight standards district office or 

certificate holding district office before 

operating any aircraft complying with this 

AD through an AMOC. 

(i) Additional Information 

(1) Bell Alert Service Bulletin (ASB) No. 

206L–01–123, Revision A, dated February 22, 

2006; ASB No. 427–01–04, Revision A, dated 

March 31, 2006; and ASB No. 407–01–45, 

Revision B, dated April 23, 2013, which are 

not incorporated by reference, contain 

additional information about the subject of 

this AD. For service information identified in 

this AD, contact Bell Helicopter Textron 

Canada Limited, 12,800 Rue de l’Avenir, 

Mirabel, Quebec J7J1R4; telephone (450) 

437–2862 or (800) 363–8023; fax (450) 433– 

0272; or at http://www.bellcustomer.com/

files/. You may review a copy of the service 

information at the FAA, Office of the 

Regional Counsel, Southwest Region, 10101 

Hillwood Pkwy, Room 6N–321, Fort Worth, 

Texas 76177. 

(2) The subject of this AD is addressed in 

Transport Canada Civil Aviation (TCCA) AD 

No. CF–2002–03R3, Revision 3, dated 

September 26, 2013. You may view the TCCA 

AD on the Internet at http://

www.regulations.gov in Docket No. FAA– 

2014–0643. 

(j) Subject 

Joint Aircraft Service Component (JASC) 

Code: 6300 Main Rotor Drive System. 

Issued in Fort Worth, Texas, on August 6, 

2015. 

Larry M. Kelly, 

Acting Directorate Manager, Rotorcraft 

Directorate, Aircraft Certification Service. 

[FR Doc. 2015–20509 Filed 8–19–15; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2014–1051; Directorate 

Identifier 2014–NM–171–AD; Amendment 

39–18239; AD 2015–17–06] 

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 certain 

Airbus Model A319, A320, and A321 

series airplanes. This AD was prompted 

by reports that on airplanes equipped 


rmajette on DSK7SPTVN1PROD with RULES
50552 Federal Register / Vol. 80, No. 161 / Thursday, August 20, 2015 / Rules and Regulations 

with sharklets, discretes (used to 

activate the load alleviation function) 

are connected on various flight 

computers using the same ground point. 

In these cases, the ground point 

segregation is no longer effective, and a 

single failure could lead to loss of 

sharklet identification by flight 

computers causing a return to the wing 

tip fence (no sharklet configuration) 

performance. This AD requires 

modification of the sharklet ground 

connection. We are issuing this AD to 

prevent loss of sharklet identification by 

the flight computers and subsequent 

reduced control of the airplane. 

DATES: This AD becomes effective 

September 24, 2015. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication listed in this AD 

as of September 24, 2015. 

ADDRESSES: You may examine the AD 

docket on the Internet at http://

www.regulations.gov/

#!docketDetail;D=FAA-2014-1051 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.airworth 

eas@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–2014–1051. 

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 certain Airbus Model A319, 

A320, and A321 series airplanes. The 

NPRM published in the Federal 

Register on January 23, 2015 (80 FR 

3520). The NPRM was prompted by 

reports that on airplanes equipped with 

sharklets, discretes (used to activate the 

load alleviation function) are connected 

on various flight computers using the 

same ground point. In these cases, the 

ground point segregation is no longer 

effective and a single failure could lead 

to loss of sharklet identification by flight 

computers causing a return to the wing 

tip fence (no sharklet configuration) 

performance. The NPRM proposed to 

require modification of the sharklet 

ground connection. We are issuing this 

AD to prevent loss of sharklet 

identification by the flight computers 

and subsequent reduced control of the 

airplane. 

The European Aviation Safety Agency 

(EASA), which is the Technical Agent 

for the Member States of the European 

Union, has issued EASA Airworthiness 

Directive 2014–0186, dated August 19, 

2014 (referred to after this as the 

Mandatory Continuing Airworthiness 

Information, or ‘‘the MCAI’’), to correct 

an unsafe condition for certain Airbus 

Model A319, A320, and A321 series 

airplanes. The MCAI states: 

During A320 Neo review, Airbus design 

office identified that on A320 family 

aeroplanes equipped with sharklets, discretes 

used to activate the load alleviation function 

are connected on various flight computers 

using the same ground point. In that case, the 

ground point segregation is no longer 

effective and a single failure could lead to 

loss of sharklet identification by the flight 

computers, inducing a return to the wing tip 

fence (no sharklet configuration) behaviour. 

This condition, if not corrected, could lead 

to reduced control of the aeroplane, 

depending on aeroplane configuration and 

flight phase. 

It has been determined that Airbus mod 

156108 restores the correct segregation. 

However, since introduction of sharklet mod 

160500 and mod 160023, a number of 

aeroplanes equipped with sharklets have 

been delivered without incorporating mod 

156108. In addition, mod 156108 was not 

included in certain SBs [service bulletins] 

that introduce the sharklet device in service 

onto aeroplanes with a reinforced wing, 

previously operated with a wing tip fence. 

Airbus mod 156108 has now been introduced 

into Airbus SB A320–57–1186 at Rev.03 and 

will be introduced at next revisions of SB 

A320–57–1173 and SB A320–57–1187. 

To address this potential unsafe condition, 

Airbus published SB A320–27–1240 for inservice installation of mod 156108. 

For the reasons described above, this AD 

requires modification of the sharklet ground 

connection. 

You may examine the MCAI in the 

AD docket on the Internet at http://

www.regulations.gov/

#!documentDetail;D=FAA-2014-1051- 

0002. 

Comments 

We gave the public the opportunity to 

participate in developing this AD. We 

received no comments on the NPRM (80 

FR 3520, January 23, 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 3520, 

January 23, 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 3520, 

January 23, 2015). 

Related Service Information Under 1 

CFR Part 51 

Airbus has issued Service Bulletin 

A320–27–1240, dated June 18, 2014. 

The service information describes 

procedures for modification of the 

sharklet ground connection. 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 or AD. 

Costs of Compliance 

We estimate that this AD affects 46 

airplanes of U.S. registry. 

We also estimate that it will take 

about 14 work-hours per product to 

comply with the basic requirements of 

this AD. The average labor rate is $85 

per work-hour. Required parts will cost 

about $347 per product. Based on these 

figures, we estimate the cost of this AD 

on U.S. operators to be $70,702, or 

$1,537 per product. 

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 


rmajette on DSK7SPTVN1PROD with RULES
Federal Register / Vol. 80, No. 161 / Thursday, August 20, 2015 / Rules and Regulations 50553 

products identified in this rulemaking 

action. 

Regulatory Findings 

We determined that 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 the 

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. 

Examining the AD Docket 

You may examine the AD docket on 

the Internet at http://

www.regulations.gov/

#!docketDetail;D=FAA-2014-1051; 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 street address for the 

Docket Operations office (telephone 

800–647–5527) is in the ADDRESSES

section. 

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): 

2015–17–06 Airbus: Amendment 39–18239. 

Docket No. FAA–2014–1051; Directorate 

Identifier 2014–NM–171–AD. 

(a) Effective Date 

This AD becomes effective September 24, 

2015. 

(b) Affected ADs 

None. 

(c) Applicability 

This AD applies to the Airbus airplanes, 

certificated in any category, identified in 

paragraphs (c)(1), (c)(2), and (c)(3) of this AD, 

all manufacturer serial numbers on which 

Airbus modification (mod) 160500 or mod 

160023 has been embodied in production, 

and those that have been modified in service 

through the Airbus Service Bulletin A320– 

57–1173, A320–57–1186, or A320–57–1187, 

except those on which Airbus mod 156108 

has been embodied in production. 

(1) Model A319–111, –112, –113, –114, 

–115, –131, –132, and –133 airplanes. 

(2) Model A320–211, –212, –214, –231, 

–232, and –233 airplanes. 

(3) Model A321–111, –112, –131, –211, 

–212, –213, –231, and –232 airplanes. 

(d) Subject 

Air Transport Association (ATA) of 

America Code 27, Flight Controls. 

(e) Reason 

This AD was prompted by reports that on 

airplanes equipped with sharklets, discretes 

(used to activate the load alleviation 

function) are connected on various flight 

computers using the same ground point. In 

these cases, the ground point segregation is 

no longer effective, and a single failure could 

lead to loss of sharklet identification by flight 

computers causing a return to the wing tip 

fence (no sharklet configuration) 

performance. We are issuing this AD to 

prevent loss of sharklet identification by the 

flight computers and subsequent reduced 

control of the airplane. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Modification 

Within 24 months after the effective date 

of this AD, modify the sharklet ground 

connection, in accordance with the 

Accomplishment Instructions of Airbus 

Service Bulletin A320–27–1240, dated June 

18, 2014. 

(h) Other FAA AD Provisions 

The following provisions also apply to this 

AD: 

(1) Alternative Methods of Compliance 

(AMOCs): The Manager, International 

Branch, ANM–116, 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 International Branch, send it to ATTN: 

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. 

Information may be emailed to: 9-ANM-116- 

AMOC-REQUESTS@faa.gov. 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. The AMOC approval letter 

must specifically reference this AD. 

(2) Contacting the Manufacturer: For any 

requirement in this AD to obtain corrective 

actions from a manufacturer, the action must 

be accomplished using a method approved 

by the Manager, International Branch, ANM– 

116, Transport Airplane Directorate, FAA; or 

the European Aviation Safety Agency 

(EASA); or Airbus’s EASA Design 

Organization Approval (DOA). If approved by 

the DOA, the approval must include the 

DOA-authorized signature. 

(i) Related Information 

Refer to Mandatory Continuing 

Airworthiness Information (MCAI) EASA 

Airworthiness Directive 2014–0186, dated 

August 19, 2014, for related information. 

This MCAI may be found in the AD docket 

on the Internet at http://

www.regulations.gov/

#!documentDetail;D=FAA-2014-1051-0002. 

(j) 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 this AD specifies otherwise. 

(i) Airbus Service Bulletin A320–27–1240, 

dated June 18, 2014. 

(ii) Reserved. 

(3) 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.airworth-eas@

airbus.com; Internet http://www.airbus.com. 

(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/ibrlocations.html. 

Issued in Renton, Washington, on August 

10, 2015. 

Michael Kaszycki, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2015–20383 Filed 8–19–15; 8:45 am] 

BILLING CODE 4910–13–P 


rmajette on DSK7SPTVN1PROD with RULES