Federal Register / Vol. 80, No. 53 / Thursday, March 19, 2015 / Rules and Regulations 14297 

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 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. 

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 AD: 

2015–06–03 Stemme AG: Amendment 39– 

18121; Docket No. FAA–2015–0633; 

Directorate Identifier 2015–CE–005–AD. 

(a) Effective Date 

This airworthiness directive (AD) becomes 

effective March 24, 2015. 

(b) Affected ADs 

None. 

(c) Applicability 

This AD applies to Stemme AG TSA–M 

Models S6 and S6–RT gliders, all serial 

numbers, certificated in any category. 

(d) Subject 

Air Transport Association of America 

(ATA) Code 27: Flight Controls. 

(e) Reason 

This AD was prompted by mandatory 

continuing airworthiness information (MCAI) 

originated by an aviation authority of another 

country to identify and correct an unsafe 

condition on an aviation product. The MCAI 

describes the unsafe condition as a bending 

defect of the fork head installed in the 

aileron, speed brake, and flap control 

systems. We are issuing this AD to detect and 

correct the bending defect of the fork head 

that could result in failure of the flight 

control system, possibly resulting in loss of 

control. 

(f) Actions and Compliance 

Unless already done, before further flight, 

after March 24, 2015 (the effective date of 

this AD), modify the affected flight control 

systems, or take other actions, following a 

method approved specifically for this AD by 

the FAA, Small Airplane Directorate. Contact 

Stemme AG to obtain FAA-approved repair 

instructions approved specifically for 

compliance with this AD and incorporate 

those instructions. You can find contact 

information for Stemme AG in paragraph 

(i)(2) of this AD. 

Note 1 to paragraph (f) of this AD: At the 

time of issuance of this AD, no design 

solution is available to restore the 

airworthiness of the respective type designs 

to a level corresponding to their approved 

type design specifications. 

(g) Other FAA AD Provisions 

The following provisions also apply to this 

AD: 

(1) Alternative Methods of Compliance 

(AMOCs): The Manager, Standards Office, 

FAA, has the authority to approve AMOCs 

for this AD, if requested using the procedures 

found in 14 CFR 39.19. Send information to 

ATTN: Jim Rutherford, Aerospace Engineer, 

FAA, Small Airplane Directorate, 901 Locust, 

Room 301, Kansas City, Missouri 64106; 

telephone: (816) 329–4165; fax: (816) 329– 

4090; email: jim.rutherford@faa.gov. Before 

using any approved AMOC on any airplane 

to which the AMOC applies, notify your 

appropriate principal inspector (PI) in the 

FAA Flight Standards District Office (FSDO), 

or lacking a PI, your local FSDO. 

(2) Airworthy Product: For any requirement 

in this AD to obtain corrective actions from 

a manufacturer or other source, use these 

actions if they are FAA-approved. Corrective 

actions are considered FAA-approved if they 

are approved by the State of Design Authority 

(or their delegated agent). You are required 

to assure the product is airworthy before it 

is returned to service. 

(h) Special Flight Permit 

Special flight permits are prohibited. 

(i) Related Information 

(1) Refer to MCAI European Aviation 

Safety Agency (EASA) AD No.: 2015–0034– 

E, dated February 27, 2015, for related 

information. You may examine the MCAI on 

the Internet at http://www.regulations.gov by 

searching for and locating Docket No. FAA– 

2015–0633. 

(2) For information concerning this action, 

contact Stemme AG, Flugplatzstra+e F2, Nr. 

6–7, D–15344 Strausberg, Germany; phone: 

+49 (0) 3341/3612 0; fax: none; email: info@

stemme.de; internet: www.stemme.info. 

Issued in Kansas City, Missouri, on March 

12, 2015. 

Robert Busto, 

Acting Manager, Small Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 2015–06296 Filed 3–18–15; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2014–0579; Directorate 

Identifier 2014–SW–020–AD; Amendment 

39–18115; AD 2015–05–05] 

RIN 2120–AA64 

Airworthiness Directives; Agusta 

S.p.A. Helicopters 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule. 

SUMMARY: We are superseding 

Airworthiness Directive (AD) 2014–04– 

14 for Agusta S.p.A. (Agusta) Model 

A109S, AW109SP, A119, and AW119 

MKII helicopters. AD 2014–04–14 

required removing certain rod end 

assemblies from service because of 

reports of fractures. This new AD retains 

the requirements of AD 2014–04–14 but 

expands the scope of applicable rod end 

assemblies. This AD was prompted by 

reports of additional fractured rod end 

assemblies. We are issuing this AD to 

prevent failure of a rod end assembly, 

which could result in damage to the 

main rotor assembly and loss of control 

of the helicopter. 

DATES: This AD is effective April 23, 

2015. 

ADDRESSES: 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/

technical-bulletins. You may view this 

referenced service information at the 

FAA, Office of the Regional Counsel, 


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14298 Federal Register / Vol. 80, No. 53 / Thursday, March 19, 2015 / Rules and Regulations 

Southwest Region, 2601 Meacham 

Blvd., Room 663, Fort Worth, Texas 

76137. 

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, the 

economic evaluation, any comments 

received, and other information. The 

street address for the Docket Operations 

Office (phone: 800–647–5527) is U.S. 

Department of Transportation, Docket 

Operations Office, M–30, West Building 

Ground Floor, Room W12–140, 1200 

New Jersey Avenue SE., Washington, 

DC 20590. 

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: 

Discussion 

We issued a notice of proposed 

rulemaking (NPRM) to amend 14 CFR 

part 39 to remove AD 2014–04–14, 

Amendment 39–17773 (79 FR 11699, 

March 3, 2014) for Agusta Model 

A109S, AW109SP, A119, and AW119 

MKII helicopters with a main rotor lag 

damper assembly (lag damper), part 

number (P/N) 109–0112–39–103, 109– 

0112–39–105, 109–0112–05–105, or 

109–0112–05–107, installed with a rod 

end assembly, P/N M004–01H007–041 

or P/N M004–01H007–045, with a serial 

number from 84 through 132 or from 

4964 through 5011, and add a new AD. 

The NPRM published in the Federal 

Register on August 18, 2014 (79 FR 

48698). AD 2014–04–14 required 

removing the rod end assemblies from 

service. AD 2014–04–14 was prompted 

by AD No. 2012–0208, dated October 5, 

2012, issued by EASA, which is the 

Technical Agent for the Member States 

of the European Union, to correct an 

unsafe condition for Agusta Model 

A109LUH, A109S, AW109SP, A119, 

and AW119 MKII helicopters. EASA 

advises of cases of in-flight fractures of 

rod end assembly, P/N M004–01H007– 

045, installed on main rotor lag dampers 

on Model A109LUH and AW109SP 

helicopters. An investigation revealed 

that two batches of rod end assemblies, 

P/N M004–01H007–041 and M004– 

01H007–045, could have cracks, 

according to EASA. EASA states that 

this condition, if not corrected, could 

lead to main rotor damage, possibly 

resulting in loss of control of the 

helicopter. The actions of AD 2014–04– 

14 were intended to prevent such 

damage and loss of control of the 

helicopter. 

Actions Since AD 2014–04–14 Was 

Issued 

Between the time we published the 

NPRM for AD 2014–04–14 (78 FR 

44042, July 23, 2013) and the Final Rule 

for AD 2014–04–14 (79 FR 11699, 

March 3, 2014), EASA issued AD No. 

2013–0290, dated December 9, 2013. 

EASA advises in AD No. 2013–0290 that 

a new case of a fractured rod end 

assembly has been reported and that 

additional batches of rod end assembly, 

P/N M004–01H007–041 and P/N M004– 

01H007–045, as well as batches of P/N 

109–0112–11–101 and P/N 109–0112– 

22–105 could also have cracks. EASA 

expanded the applicability of its AD to 

include the additional rod end 

assemblies. 

We consequently issued the NPRM 

(79 FR 48698, August 18, 2014) to 

amend 14 CFR part 39 to remove AD 

2014–04–14 and add a new AD. The 

NPRM proposed to retain the 

requirements of AD 2014–04–14 but 

expand the scope of applicable rod end 

assemblies. The NPRM also proposed to 

add a provision requiring compliance 

with the AD if the rod end assembly is 

removed during maintenance before 25 

hours time-in-service (TIS). 

Comments 

We gave the public the opportunity to 

participate in developing this AD, but 

we received no comments on the NPRM 

(79 FR 48698, August 18, 2014). 

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 and that air 

safety and the public interest require 

adopting the AD requirements as 

proposed, except we have correctly 

stated the design holder’s name as 

Agusta S.p.A. instead of 

AgustaWestland S.p.A. as specified by 

the current FAA type certificate. This 

change is consistent with the intent of 

the proposals in the NPRM (79 FR 

48698, August 18, 2014) and will not 

increase the economic burden on any 

operator nor increase the scope of the 

AD. 

Differences Between This AD and the 

EASA AD 

The EASA AD calls for replacing 

certain rod end assemblies with 

airworthy rod end assemblies within 25 

hours TIS, 2 months, or the next time 

maintenance of the applicable 

helicopters involves removing the rod 

end assembly. This AD does not have a 

calendar time requirement. The EASA 

AD applies to Agusta Model A109LUH 

helicopters. This AD does not apply to 

Model A109LUH helicopters because 

that model does not have a U.S. type 

certificate. 

Related Service Information 

We reviewed AgustaWestland 

Bollettino Tecnico (BT) No. 109S–49 for 

Model A109S helicopters, BT No. 

109SP–052 for Model AW109SP 

helicopters, and BT No. 119–50 for 

Model A119 and AW119 MKII 

helicopters. All of the BTs are revision 

A, and dated December 3, 2013. The 

BTs specify a one-time inspection of 

each rod end assembly to determine its 

serial number. The BTs then require 

removal from service of certain serialnumbered rod end assemblies because 

fractures had been reported on rod ends 

in these batches. According to the BTs, 

no one was injured in the helicopters, 

and no helicopters were damaged 

because of these fractures. 

Costs of Compliance 

We estimate that this AD affects 91 

helicopters of U.S. Registry and that 

labor costs average $85 a work-hour. 

Based on these estimates, we expect the 

following costs: 

• Replacing a rod end assembly 

requires 1.5 work-hours for a labor cost 

of $128. Parts cost $3,918 for a total cost 

of $4,046 per helicopter, $368,186 for 

the U.S. fleet. 

According to the manufacturer’s 

service information, costs of this AD 

may be covered under warranty, thereby 

reducing the cost impact on affected 

individuals. We do not control warranty 

coverage by manufacturers. 

Accordingly, we have included all costs 

in our cost estimate. 

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. 


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Federal Register / Vol. 80, No. 53 / Thursday, March 19, 2015 / Rules and Regulations 14299 

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, 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) 

2014–04–14, Amendment 39–17773 (79 

FR 11699, March 3, 2014), and adding 

the following new AD: 

2015–05–05 Agusta S.p.A.: Amendment 39– 

18115; Docket No. FAA–2014–0579; 

Directorate Identifier 2014–SW–020–AD. 

(a) Applicability 

This AD applies to the following 

helicopters, certificated in any category: 

(1) Agusta S.p.A. (Agusta) Model A109S 

and AW109SP helicopters, with a main rotor 

lag damper assembly (lag damper), part 

number (P/N) 109–0112–39–103 or 109– 

0112–39–105, installed on rod end assembly, 

P/N M004–01H007–041 with a serial number 

(S/N) 1 through 202; or rod end assembly, P/ 

N M004–01H007–045 with a S/N 1RW 

through 202RW or 4964 through 5011. 

(2) Agusta Model A119 and AW119 MKII 

helicopters, with a lag damper, P/N 109– 

0112–05–105 or 109–0112–05–107, installed 

on rod end assembly, P/N 109–0112–11–101 

with a S/N 1 through 78; or rod end 

assembly, P/N 109–0112–11–105 with a S/N 

1RW through 78RW; or rod end assembly, P/ 

N M004–01H007–045 with a S/N 1RW 

through 202RW or 4964 through 5011. 

(b) Unsafe Condition 

This AD defines the unsafe condition as a 

crack in a rod end assembly, which could 

result in fracture of the rod end assembly, 

damage to the main rotor, and subsequent 

loss of control of the helicopter. 

(c) Affected ADs 

This AD supersedes AD 2014–04–14, 

amendment 39–17773 (79 FR 11699, March 

3, 2014). 

(d) Effective Date 

This AD becomes effective April 23, 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 25 hours time-in-service or the 

next time maintenance of the helicopter 

involves removing the rod end assembly, 

whichever occurs first, remove the rod end 

assembly from service. 

(2) Do not install a rod end assembly, P/ 

N M004–01H007–041 with a S/N 1 through 

202; P/N M004–01H007–045 with a S/N 1RW 

through 202RW or 4964 through 5011; P/N 

109–0112–11–101 with a S/N 1 through 78; 

or P/N 109–0112–11–105 with a S/N 1RW 

through 78RW, on any helicopter. 

(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. 

(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 

(1) AgustaWestland S.p.A. Bollettino 

Tecnico (BT) No. 109S–49, BT No. 109SP– 

052, and BT No. 119–50, all Revision A, and 

all dated December 3, 2013, which are not 

incorporated by reference, contain additional 

information about the subject of this AD. 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 a copy of the 

service information at the FAA, Office of the 

Regional Counsel, Southwest Region, 2601 

Meacham Blvd., Room 663, Fort Worth, 

Texas 76137. 

(2) The subject of this AD is addressed in 

the European Aviation Safety Agency (EASA) 

AD No. 2013–0290, dated December 9, 2013. 

You may view the EASA AD on the Internet 

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

FAA–2014–0579. 

(i) Subject 

Joint Aircraft Service Component (JASC) 

Code: 6200, Main Rotor System. 

Issued in Fort Worth, Texas, on March 4, 

2015. 

Bruce E. Cain, 

Acting Directorate Manager, Rotorcraft 

Directorate, Aircraft Certification Service. 

[FR Doc. 2015–05715 Filed 3–18–15; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2014–1001; Directorate 

Identifier 2014–CE–034–AD; Amendment 

39–18103; AD 2015–04–01] 

RIN 2120–AA64 

Airworthiness Directives; Short 

Brothers & Harland Ltd. Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule; correction. 

SUMMARY: The FAA is correcting an 

airworthiness directive (AD) that 

published in the Federal Register. That 

AD applies to all Short Brothers & 

Harland Ltd. Model SC–7 Series 3 

airplanes. The amendment number in 

the Agency Identification Numbers in 

the preamble section of the AD is 

incorrect. Although no other part of the 

preamble or regulatory information has 

been corrected, we are publishing the 

entire rule in the Federal Register. 

DATES: This final rule is effective March 

30, 2015. 

ADDRESSES: You may examine the AD 

docket on the Internet at http:// 


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