Federal Register / Vol. 79, No. 37 / Tuesday, February 25, 2014 / Rules and Regulations 10333 

(or their delegated agent). You are required 

to assure the product is airworthy before it 

is returned to service. 

(j) Related Information 

(1) Refer to Mandatory Continuing 

Airworthiness Information (MCAI) Canadian 

Airworthiness Directive CF–2012–32, dated 

December 13, 2012, for related information. 

This MCAI may be found in the AD docket 

on the Internet at http://

www.regulations.gov/

#!documentDetail;D=FAA-2013-0705-0002. 

(2) Service information identified in this 

AD that is not incorporated by reference may 

be viewed at the addresses specified in 

paragraphs (k)(3) and (k)(4) of this AD. 

(k) 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) Bombardier Service Bulletin 700–30– 

021, Revision 01, dated November 21, 2012. 

(ii) Reserved. 

(3) For service information identified in 

this AD, contact Bombardier, Inc., 400 CoˆteVertu Road West, Dorval, Que ́bec H4S 1Y9, 

Canada; telephone 514–855–5000; fax 514– 

855–7401; email thd.crj@

aero.bombardier.com; Internet http://

www.bombardier.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 January 

22, 2014. 

Jeffrey E. Duven, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 2014–02523 Filed 2–24–14; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2014–0035; Directorate 

Identifier 2013–SW–036–AD; Amendment 

39–17734; AD 2014–02–06] 

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 Agusta 

S.p.A. (Agusta) Model AB412 

helicopters. This AD requires visually 

inspecting the main rotor swashplate 

outer ring (outer ring) for a crack and 

replacing that outer ring if a crack 

exists. This AD is prompted by two 

cases of cracks caused by fatigue on 

certain outer rings. These actions are 

intended to prevent the failure of the 

outer ring, which would lead to loss of 

main rotor blade pitch control and 

subsequently loss of helicopter control. 

DATES: This AD becomes effective 

March 12, 2014. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain document listed in this AD 

as of March 12, 2014. 

We must receive comments on this 

AD by April 28, 2014. 

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) AD, 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 Agusta Westland, 

Customer Support & Services, Via Per 

Tornavento 15, 21019 Somma Lombardo 

(VA) Italy, ATTN: Giovanni Cecchelli; 

telephone 39–0331–711133; fax 39 0331 

711180; or at http://

www.agustawestland.com/technicalbullettins. 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. 

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 

EASA, which is the Technical Agent 

for the Member States of the European 

Union, has issued EASA AD No. 2013– 

0152–E, dated July 17, 2013, to correct 

an unsafe condition for the Agusta 

Model AB412 helicopter. EASA advises 


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10334 Federal Register / Vol. 79, No. 37 / Tuesday, February 25, 2014 / Rules and Regulations 

that two cases of cracks were reported 

in the outer ring, part number (P/N) 

412–010–407–105. A subsequent 

investigation revealed that ‘‘fatigue 

failure’’ caused the cracks. EASA states 

that ‘‘this condition, if not detected and 

corrected, could lead to the loss of main 

rotor blade pitch control, possibly 

resulting in loss of control of the 

helicopter.’’ EASA calls for repetitive 

inspections of the affected outer rings 

for a crack and replacing the outer ring 

with an improved outer ring, P/N 412– 

010–107–117, if a crack is found. If the 

outer ring has not been replaced, the AD 

requires replacing each outer ring, P/N 

412–010–407–105, with an improved 

outer ring, P/N 412–010–107–117, 

within 300 flight hours or 8 months, 

whichever occurs first. Replacement 

with an improved outer ring is 

terminating action for the repetitive 

inspections, EASA states. 

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, 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 EASA and determined the 

unsafe condition exists and is likely to 

exist or develop on other helicopters of 

these same type designs. 

Related Service Information 

AgustaWestland S.p.A. issued Alert 

Bollettino Tecnico No. 412–134 on July 

15, 2013 (BT), to warn that two cases of 

cracking in the outer ring, P/N 412–010– 

407–105, have been reported, both 

attributed to fatigue failure. The BT calls 

for visually inspecting the outer ring for 

a crack with a 5X magnifying glass and 

a bright light. The BT added that the 

inspection must occur within 5 flight 

hours from when the BT was issued and 

within intervals of 25 flight hours 

thereafter until the outer ring is 

replaced. The deadline to replace the 

outer ring with outer ring, P/N 412– 

010–407–117, is 300 flight hours or no 

later than April 15, 2014, whichever 

comes first. Outer ring, P/N 412–010– 

407–105, was not to be used after April 

15, 2014, the BT stated. 

AD Requirements 

This AD requires: 

• Within 5 hours time-in-service 

(TIS), and thereafter at intervals not to 

exceed 25 hours TIS, visually inspecting 

the swashplate outer ring, P/N 412–010– 

407–105, for cracks, using a 5X 

magnifying glass and a bright light. If a 

crack exists, before further flight, 

removing the swashplate outer ring from 

service. 

• Within 300 hours TIS or 8 months, 

whichever occurs first, removing the 

swashplate outer ring, P/N 412–010– 

407–105, from service. 

• Not installing a swashplate outer 

ring, P/N 412–010–407–105, on any 

helicopter. 

Differences Between This AD and the 

EASA AD 

This AD prohibits installation of a 

swashplate outer ring, P/N 412–010– 

407–105, while the EASA AD allows 

installation of this part under certain 

conditions. 

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 products 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): 

2014–02–06 Agusta S.p.A.: Amendment 39– 

17734; Docket No. FAA–2014–0035; 

Directorate Identifier 2013–SW–036–AD. 

(a) Applicability 

This AD applies to Agusta S.p.A. Model 

AB412 helicopters with a swashplate outer 

ring part number (P/N) 412–010–407–105 

installed, certificated in any category. 

(b) Unsafe Condition 

This AD defines the unsafe condition as a 

crack in the main rotor swashplate outer ring. 

This condition could result in the loss of 

main rotor blade pitch control and 

subsequent loss of control of the helicopter. 

(c) Effective Date 

This AD becomes effective March 12, 2014. 

(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. 


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Federal Register / Vol. 79, No. 37 / Tuesday, February 25, 2014 / Rules and Regulations 10335 

(e) Required Actions 

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

and thereafter at intervals not to exceed 25 

hours TIS, visually inspect the swashplate 

outer ring, P/N 412–010–407–105, for a 

crack, using a 5X or higher power magnifying 

glass and a bright light and referring to 

Figures 1 and 2 in AgustaWestland S.p.A. 

Alert Bollettino Tecnico No. 412–134, dated 

July 15, 2013. If a crack exists, before further 

flight, remove the swashplate outer ring from 

service. 

(2) Within 300 hours TIS or 8 months, 

whichever occurs first, remove the 

swashplate outer ring, P/N 412–010–407– 

105, from service. 

(3) Do not install a swashplate outer ring, 

P/N 412–010–407–105, on any helicopter. 

(f) 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. 

(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. 

(g) Additional Information 

The subject of this AD is addressed in the 

European Aviation Safety Agency (EASA) AD 

No. 2013–0152–E, dated July 17, 2013. You 

may view the EASA AD on the Internet at 

http://www.regulations.gov in Docket No. 

FAA–2014–0035. 

(h) Subject 

Joint Aircraft Service Component (JASC) 

Code: 6230, Main Rotor Mast/Swashplate. 

(i) 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) AgustaWestland S.p.A. Alert Bollettino 

Tecnico No. 412–134, dated July 15, 2013. 

(ii) Reserved. 

(3) For AgustaWestland service 

information identified in this AD, contact 

AgustaWestland, Customer Support & 

Services, Via Per Tornavento 15, 21019 

Somma Lombardo (VA) Italy, ATTN: 

Giovanni Cecchelli; telephone 39- 0331– 

711133; fax 39 0331 711180; or at http://

www.agustawestland.com/technicalbullettins. 

(4) You may view this service information 

that is incorporated by reference at the 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 January 16, 

2014. 

Lance T. Gant, 

Acting Directorate Manager, Rotorcraft 

Directorate, 

Aircraft Certification Service. 

[FR Doc. 2014–01956 Filed 2–24–14; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2013–0699; Directorate 

Identifier 2012–NM–198–AD; Amendment 

39–17751; AD 2014–03–13] 

RIN 2120–AA64 

Airworthiness Directives; Fokker 

Services B.V. Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Final rule. 

SUMMARY: We are adopting a new 

airworthiness directive (AD) for certain 

Fokker Services B.V. Model F.28 Mark 

0070 and 0100 airplanes. This AD was 

prompted by three reports of cracking in 

the rear pressure bulkhead (RPBH) web. 

This AD requires inspecting the RPBH 

web for cracking, and repairing if 

necessary. We are issuing this AD to 

detect and correct cracking of the RPBH 

web, which could result in in-flight 

decompression of the airplane and 

possible injury to the occupants. 

DATES: This AD becomes effective April 

1, 2014. 

The Director of the Federal Register 

approved the incorporation by reference 

of certain publications listed in this AD 

as of April 1, 2014. 

ADDRESSES: You may examine the AD 

on the Internet at http://

www.regulations.gov/

#!docketDetail;D=FAA-2013-0699; or in 

person at the 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 Fokker Services B.V., 

Technical Services Dept., P.O. Box 

1357, 2130 EL Hoofddorp, the 

Netherlands; telephone +31 (0)88–6280– 

350; fax +31 (0)88–6280–111; email 

technicalservices@fokker.com; Internet 

http://www.myfokkerfleet.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. 

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 Fokker Services B.V. 

Model F.28 Mark 0070 and 0100 

airplanes. The NPRM published in the 

Federal Register on August 23, 2013 (78 

FR 52465). The NPRM was prompted by 

three reports of cracking in the rear 

pressure bulkhead (RPBH) web. The 

NPRM proposed to require inspecting 

the RPBH web for cracking, and 

repairing if necessary. We are issuing 

this AD to detect and correct cracking of 

the RPBH web, which could result in inflight decompression of the airplane and 

possible injury to the occupants. 

The European Aviation Safety Agency 

(EASA), which is the Technical Agent 

for the Member States of the European 

Community, has issued EASA 

Airworthiness Directive 2012–0219, 

dated October 19, 2012 (referred to after 

this as the Mandatory Continuing 

Airworthiness Information, or ‘‘the 

MCAI’’), to correct an unsafe condition 

for the specified products. The MCAI 

states: 

Three reports have been received of a crack 

in the rear pressure bulkhead (RPBH) web, 

just below the horizontal beam XI between 

buttock lines BL425L and BL425R, in the 

centre web bay below the pressure relief 

valves. 

This condition, if not detected and 

corrected, could result in an exponential 

crack growth rate, possibly leading to failure 

of the affected RPBH web, resulting in inflight decompression of the aeroplane and 

possible injury to occupants. 

A repetitive inspection requirement has 

been published in issue 10 of Fokker Services 

[Airworthiness Limitations Section] ALS 

Report SE–623 under task number 534106– 

00–05. The threshold to start this ALS-task is 

30,000 [total] flight cycles (FC). However, it 

is known that many aeroplanes have already 

exceeded this threshold. 


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