Federal Register / Vol. 80, No. 110 / Tuesday, June 9, 2015 / Rules and Regulations 32451 

(3) For Bombardier service information 

identified in this AD, contact Bombardier, 

Inc., Q-Series Technical Help Desk, 123 

Garratt Boulevard, Toronto, Ontario M3K 

1Y5, Canada; telephone 416–375–4000; fax 

416–375–4539; email thd.qseries@

aero.bombardier.com; Internet http://

www.bombardier.com. 

(4) For Parker service information 

identified in this AD, contact Parker 

Aerospace, 14300 Alton Parkway, Irvine, CA, 

92618; phone: 949–833–3000; Internet: 

http://www.parker.com. 

(5) 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. 

(6) 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 May 1, 

2015. 

Jeffrey E. Duven, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 2015–11389 Filed 6–8–15; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2015–1936; Directorate 

Identifier 2014–SW–005–AD; Amendment 

39–18170; AD 2015–11–07] 

RIN 2120–AA64 

Airworthiness Directives; Agusta 

S.p.A. Helicopters 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Final rule; request for 

comments. 

SUMMARY: We are adopting a new 

airworthiness directive (AD) for certain 

Agusta S.p.A. Model AB412 and AB412 

EP helicopters. This AD requires 

inspecting the tail rotor (T/R) drive shaft 

flanged adapter (adapter) for a crack and 

removing the adapter from service if 

there is a crack. This AD is prompted by 

a report of a crack found in an adapter. 

These actions are intended to detect a 

crack in the adapter and prevent failure 

of the T/R drive shaft, which could 

result in reduced control of the 

helicopter. 

DATES: This AD becomes effective June 

24, 2015. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain document listed in this AD 

as of June 24, 2015. 

We must receive comments on this 

AD by August 10, 2015. 

ADDRESSES: You may send comments by 

any of the following methods: 

• Federal eRulemaking Docket: Go to 

http://www.regulations.gov. Follow the 

online instructions for sending your 

comments electronically. 

• Fax: 202–493–2251. 

• Mail: Send comments to the U.S. 

Department of Transportation, Docket 

Operations, M–30, West Building 

Ground Floor, Room W12–140, 1200 

New Jersey Avenue SE., Washington, 

DC 20590–0001. 

• Hand Delivery: Deliver to the 

‘‘Mail’’ address between 9 a.m. and 5 

p.m., Monday through Friday, except 

Federal holidays. 

Examining the AD Docket 

You may examine the AD docket on 

the Internet at http://

www.regulations.gov or in person at the 

Docket Operations Office between 9 

a.m. and 5 p.m., Monday through 

Friday, except Federal holidays. The AD 

docket contains this AD, the European 

Aviation Safety Agency (EASA) 

Emergency AD (EAD), any incorporated 

by reference service information, any 

comments received, and other 

information. The street address for the 

Docket Operations Office (telephone 

800- 647–5527) is in the ADDRESSES

section. Comments will be available in 

the AD docket shortly after receipt. 

For service information identified in 

this AD, contact AgustaWestland, 

Product Support Engineering, Via del 

Gregge, 100, 21015 Lonate Pozzolo (VA) 

Italy, ATTN: Maurizio D’Angelo; 

telephone 39–0331–664757; fax 39– 

0331–664680; or at http://

www.agustawestland.com/technicalbulletins. You may review the 

referenced service information at the 

FAA, Office of the Regional Counsel, 

Southwest Region, 2601 Meacham 

Blvd., Room 663, Fort Worth, Texas 

76137. It is also available on the Internet 

at http://www.regulations.gov in Docket 

No. FAA–2015–1936. 

FOR FURTHER INFORMATION CONTACT: 

Robert Grant, Aviation Safety Engineer, 

Safety Management Group, FAA, 2601 

Meacham Blvd., Fort Worth, Texas 

76137; telephone (817) 222–5110; email 

robert.grant@faa.gov. 

SUPPLEMENTARY INFORMATION: 

Comments Invited 

This AD is a final rule that involves 

requirements affecting flight safety, and 

we did not provide you with notice and 

an opportunity to provide your 

comments prior to it becoming effective. 

However, we invite you to participate in 

this rulemaking by submitting written 

comments, data, or views. We also 

invite comments relating to the 

economic, environmental, energy, or 

federalism impacts that resulted from 

adopting this AD. The most helpful 

comments reference a specific portion of 

the AD, explain the reason for any 

recommended change, and include 

supporting data. To ensure the docket 

does not contain duplicate comments, 

commenters should send only one copy 

of written comments, or if comments are 

filed electronically, commenters should 

submit them only one time. We will file 

in the docket all comments that we 

receive, as well as a report summarizing 

each substantive public contact with 

FAA personnel concerning this 

rulemaking during the comment period. 

We will consider all the comments we 

receive and may conduct additional 

rulemaking based on those comments. 

Discussion 

This AD action was prompted by EAD 

No. 2014–0040–E, dated February 19, 

2014, issued by EASA, which is the 

Technical Agent for the Member States 

of the European Union, to correct an 

unsafe condition for certain 

AgustaWestland S.p.A. Model AB 412 

and AB 412 EP helicopters. EASA 

advises that a crack was found in an 

adapter, part number (P/N) 412–040– 

622–101, installed on a Model AB 412 

EP helicopter. EASA further advises that 

the condition, if not detected and 

corrected, could lead to T/R drive shaft 

failure, possibly resulting in reduced 

control of the helicopter. To address this 

unsafe condition, the EASA EAD 

requires repetitive inspections of 

adapters, P/N 412–040–622–101 and P/ 

N 412–040–623–101, for a crack and 

replacing a cracked adapter. EASA also 

requires reporting and sending the 

cracked adapter to AgustaWestland for 

investigation. 

FAA’s Determination 

These helicopters have been approved 

by the aviation authority of Italy and are 

approved for operation in the United 

States. Pursuant to our bilateral 

agreement with Italy, the EASA, its 

technical representative, has notified us 

of the unsafe condition described in the 

EASA AD. We are issuing this AD 

because we evaluated all information 

provided by the EASA and determined 

the unsafe condition exists and is likely 

to exist or develop on other helicopters 

of these same type designs. 


tkelley on DSK3SPTVN1PROD with RULES
32452 Federal Register / Vol. 80, No. 110 / Tuesday, June 9, 2015 / Rules and Regulations 

Related Service Information Under 1 

CFR Part 51 

AgustaWestland issued Bollettino 

Tecnico No. 412–139, dated February 

19, 2014 (BT), for Model AB412 

helicopters serial number (S/N) 25801 

through 25900, and Model AB412EP 

helicopters S/N 25901 and subsequent. 

The BT states AgustaWestland received 

a report of a crack in an adapter, P/N 

412–040–622–101, installed on a Model 

AB412EP helicopter. The BT also states 

that the investigation to determine the 

root causes of the crack is in progress 

and the BT may be revised according to 

the investigation results. The BT 

specifies a one-time inspection of the 

adapter, P/N 412–040–622–101 and P/N 

412–040–623–101, for the presence of 

cracks, and if there is a crack, replacing 

the drive shaft assembly. The BT also 

specifies reporting a cracked adapter 

and sending affected parts to 

AgustaWestland. 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. 

AD Requirements 

This AD requires an initial and 

recurring visual inspection of the 

adapter, P/N 412–040–622–101 and P/N 

412–040–623–101, installed on certain 

Model AB412 and AB412 EP 

helicopters. If there is a crack in an 

adapter, this AD requires removing the 

adapter from service before further 

flight. This AD also requires visually 

inspecting an adapter before 

installation. 

Differences Between This AD and the 

EASA EAD 

The EASA EAD requires reporting 

and sending any cracked adapter to 

AgustaWestland, whereas this AD does 

not. 

Interim Action 

We consider this AD to be an interim 

action. If final action is later identified, 

we might consider further rulemaking 

then. 

Costs of Compliance 

There are no costs of compliance with 

this AD because there are no helicopters 

with this type certificate on the U.S. 

Registry. 

FAA’s Justification and Determination 

of the Effective Date 

There are no helicopters with this 

type certificate on the U.S. Registry. 

Therefore, we believe it is unlikely that 

we will receive any adverse comments 

or useful information about this AD 

from U.S. Operators. 

Since an unsafe condition exists that 

requires the immediate adoption of this 

AD, we determined that notice and 

opportunity for public comment before 

issuing this AD are unnecessary because 

there are none of these helicopters on 

the U.S. Registry and that good cause 

exists for making this amendment 

effective in less than 30 days. 

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 

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, 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 adding 

the following new airworthiness 

directive (AD): 

2015–11–07 Agusta S.p.A.: Amendment 39– 

18170; Docket No. FAA–2015–1936; 

Directorate Identifier 2014–SW–005–AD. 

(a) Applicability 

This AD applies to Model AB412 

helicopters with a serial number (S/N) 25801 

through 25900, and Model AB412 EP 

helicopters with a S/N 25901 and larger, 

certificated in any category. 

(b) Unsafe Condition 

This AD defines the unsafe condition as a 

crack in a tail rotor (T/R) drive shaft flanged 

adapter. This condition could result in 

failure of the T/R drive shaft and reduced 

control of the helicopter. 

(c) Effective Date 

This AD becomes effective June 24, 2015. 

(d) 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. 

(e) Required Actions 

(1) Within 5 hours time-in-service (TIS) 

and thereafter at intervals not to exceed 100 

hours TIS, using a 5X power magnifying glass 

and a light source, visually inspect each 

flanged adapter, part number (P/N) 412–040– 

622–101 and P/N 412–040–623–101, for a 

crack as shown in Figures 1 and 2 of 

AgustaWestland Bollettino Tecnico No. 412– 

139, dated February 19, 2014. 

(2) If there is a crack in a flanged adapter, 

before further flight, remove the flanged 

adapter from service. 

(3) Do not install a flanged adapter, P/N 

412–040–622–101 or P/N 412–040–623–101, 

unless it has been inspected in accordance 

with the requirements of paragraphs (e)(1) 

and (e)(2) of this AD. 

(f) Special Flight Permits 

Special flight permits are prohibited. 

(g) Alternative Methods of Compliance 

(AMOCs) 

(1) The Manager, Safety Management 

Group, FAA, may approve AMOCs for this 

AD. Send your proposal to: Robert Grant, 

Aviation Safety Engineer, Safety Management 

Group, FAA, 2601 Meacham Blvd., Fort 

Worth, Texas 76137; telephone (817) 222– 

5110; email robert.grant@faa.gov. 


tkelley on DSK3SPTVN1PROD with RULES
Federal Register / Vol. 80, No. 110 / Tuesday, June 9, 2015 / Rules and Regulations 32453 

(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. 

(h) Additional Information 

The subject of this AD is addressed in 

European Aviation Safety Agency (EASA) 

Emergency AD (EAD) No. 2014–0040–E, 

dated February 19, 2014. You may view the 

EASA EAD on the Internet at http://

www.regulations.gov in Docket No. FAA– 

2015–1936. 

(i) Subject 

Joint Aircraft Service Component (JASC) 

Code: 6510, Tail Rotor Drive Shaft. 

(j) Material Incorporated by Reference 

(1) The Director of the Federal Register 

approved the incorporation by reference 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) AgustaWestland Bollettino Tecnico No. 

412–139, dated February 19, 2014. 

(ii) Reserved. 

(3) For AgustaWestland service 

information identified in this AD, contact 

AgustaWestland, Product Support 

Engineering, Via del Gregge, 100, 21015 

Lonate Pozzolo (VA) Italy, ATTN: Maurizio 

D’Angelo; telephone 39–0331–664757; fax 

39–0331–664680; or at http://

www.agustawestland.com/technicalbulletins. 

(4) You may view this service information 

at FAA, Office of the Regional Counsel, 

Southwest Region, 2601 Meacham Blvd., 

Room 663, Fort Worth, Texas 76137. For 

information on the availability of this 

material at the FAA, call (817) 222–5110. 

(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 Fort Worth, Texas, on May 26, 

2015. 

Lance T. Gant, 

Acting Directorate Manager, Rotorcraft 

Directorate, Aircraft Certification Service. 

[FR Doc. 2015–13343 Filed 6–8–15; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2014–0568; Directorate 

Identifier 2014–NM–075–AD; Amendment 

39–18166; AD 2015–11–03] 

RIN 2120–AA64 

Airworthiness Directives; ATR–GIE 

Avions de Transport Re ́gional 

Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Final rule. 

SUMMARY: We are adopting a new 

airworthiness directive (AD) for certain 

ATR–GIE Avions de Transport Re ́gional 

Model ATR42 and ATR72 airplanes. 

This AD was prompted by reports of 

fuel quantity indication malfunctions 

caused by fuel probe failure. This AD 

requires identifying the part number 

and serial number of the fuel probes, 

and replacing the fuel probes if 

necessary. We are issuing this AD to 

prevent fuel probe failure, which could 

lead to undetected fuel starvation and 

consequent dual engine in-flight flameout. 

DATES: This AD becomes effective July 

14, 2015. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication listed in this AD 

as of July 14, 2015. 

ADDRESSES: You may examine the AD 

docket on the Internet at http://

www.regulations.gov/

#!docketDetail;D=FAA-2014-0568 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 Zodiac Aerospace, 

Technical Publication Department, 61 

Rue Pierre Curie—CS20001, 78373 

Plaisir Cedex, France; phone: +33 (0)1 

61 34 19 24; fax: +33 (0)1 61 34 21 13; 

email: yann.laine@

zodiacaerospace.com; Internet: http://

www.zodiacaerospace.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. You can find 

this information at http://

www.regulations.gov by searching for 

and locating Docket No. FAA–2014– 

0568. 

FOR FURTHER INFORMATION CONTACT: Tom 

Rodriguez, Aerospace Engineer, 

International Branch, ANM–116, 

Transport Airplane Directorate, FAA, 

1601 Lind Avenue SW., Renton, WA 

98057–3356; telephone 425–227–1137; 

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 ATR–GIE Avions de 

Transport Re ́gional Model ATR42 and 

ATR72 airplanes. The NPRM published 

in the Federal Register on August 15, 

2014 (79 FR 48107). The NPRM was 

prompted by reports of fuel quantity 

indication malfunctions caused by fuel 

probe failure. The NPRM proposed to 

require identifying the part number and 

serial number of the fuel probes, and 

replacing the probes if necessary. We 

are issuing this AD to prevent fuel probe 

failure, which could lead to undetected 

fuel starvation and consequent dual 

engine in-flight flame-out. 

The European Aviation Safety Agency 

(EASA), which is the Technical Agent 

for the Member States of the European 

Union, has issued EASA Airworthiness 

Directive 2014–0075R1, dated April 24, 

2014 (referred to after this as the 

Mandatory Continuing Airworthiness 

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

an unsafe condition on certain ATR–GIE 

Avions de Transport Re ́gional Model 

ATR42 and ATR72 airplanes. The MCAI 

states: 

A significant number of fuel probes 

installed on ATR aeroplanes failed during 

production tests and several occurrences of 

fuel quantity indication malfunctions were 

recently reported on in-service aeroplanes. 

The subsequent investigation, conducted 

on the failed parts, confirmed a loss of 

ground connection on the terminal block of 

the fuel probe, due to an incorrect 

application of wiring instructions in 

production during fuel probe manufacturing 

between June 2011 and August 2013. The 

investigation identified a batch of parts, 

suspected to be affected by this 

manufacturing defect. Some of these probes 

were delivered as spares, and operators may 

have installed these probes on their inservice aeroplanes. 

In case an affected fuel probe is installed 

on each wing of an aeroplane, being not 

equipped with an independent fuel low level 

measurement system or an aeroplane 

operated in accordance with ETOPS 

[extended range twin operations] rules, the 

defected fuel probes could indicate a higher 

fuel quantity value than the real quantity of 

the on-board fuel. 

This condition, if not detected and 

corrected, could lead to an undetected fuel 

starvation and consequent dual engine inflight flame out. 


tkelley on DSK3SPTVN1PROD with RULES