48698 Federal Register / Vol. 79, No. 159 / Monday, August 18, 2014 / Proposed Rules 

this proposed AD and placed it in the 

AD docket. 

List of Subjects in 14 CFR Part 39 

Air transportation, Aircraft, Aviation 

safety, Incorporation by reference, 

Safety. 

The Proposed Amendment 

Accordingly, under the authority 

delegated to me by the Administrator, 

the FAA proposes to amend 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): 

Airbus Helicopters Deutschland GmbH 

(Previously Eurocopter Deutschland 

GmbH) (Airbus Helicopters) Helicopters: 

Docket No. FAA–2014–0578; Directorate 

Identifier 2013–SW–048–AD. 

(a) Applicability 

This AD applies to Airbus Helicopters 

Model MBB–BK 117 C–2 helicopters with a 

lateral duplex trim actuator, part number (P/ 

N) 418–00878–050 or P/N 418–00878–051, or 

a longitudinal duplex trim actuator, P/N 418– 

00878–000 or P/N 418–00878–001, installed, 

certificated in any category. 

(b) Unsafe Condition 

This AD defines the unsafe condition as 

loss of a trim actuator output lever 

attachment screw. This condition could 

result in movement of the output lever in an 

axial direction, contact of a bolt connecting 

the control rod to an output lever with the 

actuator housing, and subsequent loss of 

control of the helicopter. 

(c) Comments Due Date 

We must receive comments by October 17, 

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. 

(e) Required Actions 

(1) Within 300 hours time-in-service (TIS), 

apply a torque of 31.0 inch-pounds (3.5 Nm) 

to the self-locking nut (nut) on each lateral 

and longitudinal trim actuator output lever 

and apply a torque marking between the nut 

and the screw. 

(2) Thereafter at intervals not to exceed 400 

hours TIS, visually inspect each nut on each 

lateral and longitudinal trim actuator output 

lever to determine whether the torque is at 

31.0 inch-pounds (3.5 Nm). If the torque is 

not at 31.0 inch-pounds, apply a torque of 

31.0 inch-pounds (3.5 Nm), remove the 

previous torque marking, and apply a new 

torque marking between the nut and the 

screw. 

(3) Do not install a lateral duplex trim 

actuator, part number (P/N) 418–00878–050 

or P/N 418–00878–051, or a longitudinal 

duplex trim actuator, P/N 418–00878–000 or 

P/N 418–00878–001, on any helicopter 

unless each nut has been inspected for 

proper torque in accordance with the 

requirements of this AD. 

(f) Alternative Methods of Compliance 

(AMOCs) 

(1) The Manager, Safety Management 

Group, FAA, may approve AMOCs for this 

AD. Send your proposal to: Matt Wilbanks, 

Aviation Safety Engineer, Regulations and 

Policy Group, Rotorcraft Directorate, FAA, 

2601 Meacham Blvd., Fort Worth, Texas 

76137; telephone (817) 222–5110; email 

matt.wilbanks@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 

(1) Eurocopter Alert Service Bulletin MBB– 

BK117 C–2–67A–020, Revision 0, dated June 

18, 2013, which is not incorporated by 

reference, contains additional information 

about the subject of this AD. For service 

information identified in this AD, contact 

Airbus Helicopters, Inc., 2701 N. Forum 

Drive, Grand Prairie, TX 75052; telephone 

(972) 641–0000 or (800) 232–0323; fax (972) 

641–3775; or at http://

www.airbushelicopters.com/techpub. 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. 

(2) The subject of this AD is addressed in 

the European Aviation Agency (EASA) AD 

No. 2013–0182, dated August 12, 2013. You 

may view the EASA AD on the Internet at 

http://www.regulations.gov in the AD Docket. 

(h) Subject 

Joint Aircraft Service Component (JASC) 

Code: Rotorcraft Flight Control, 6700. 

Issued in Fort Worth, Texas, on August 8, 

2014. 

Lance T. Gant, 

Acting Directorate Manager, Rotorcraft 

Directorate, Aircraft Certification Service. 

[FR Doc. 2014–19506 Filed 8–15–14; 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] 

RIN 2120–AA64 

Airworthiness Directives; Agusta 

S.p.A. Helicopters (Type Certificate 

Currently Held By AgustaWestland 

S.P.A) (AgustaWestland) 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Notice of proposed rulemaking 

(NPRM). 

SUMMARY: We propose to supersede 

airworthiness directive (AD) 2014–04– 

14 for AgustaWestland Model A109S, 

AW109SP, A119, and AW119 MKII 

helicopters. AD 2014–04–14 currently 

requires removing certain rod end 

assemblies from service because of 

reports of fractures. Since we issued AD 

2014–04–14, additional fractured rod 

end assemblies have been reported. This 

proposed AD would retain the 

requirements of AD 2014–04–14 but 

expand the scope of applicable rod end 

assemblies. These proposed actions are 

intended 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: We must receive comments on 

this proposed AD by October 17, 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 proposed AD, the 

European Aviation Safety Agency 

(EASA) AD, the economic evaluation, 

any comments received and other 


tkelley on DSK3SPTVN1PROD with PROPOSALS
Federal Register / Vol. 79, No. 159 / Monday, August 18, 2014 / Proposed Rules 48699 

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 proposed 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 review 

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 

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 might result 

from adopting the proposals in this 

document. The most helpful comments 

reference a specific portion of the 

proposal, 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 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 proposed rulemaking. 

Before acting on this proposal, we will 

consider all comments we receive on or 

before the closing date for comments. 

We will consider comments filed after 

the comment period has closed if it is 

possible to do so without incurring 

expense or delay. We may change this 

proposal in light of the comments we 

receive. 

Discussion 

On March 3, 2014, we published AD 

2014–04–14, Amendment 39–17773 (79 

FR 11699) for AgustaWestland 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. AD 2014–04–14 

requires removing the applicable 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 AgustaWestland Model A109LUH, 

A109S, AW109SP, A119, and AW119 

MKII helicopters. EASA advises that 

cases of in-flight fractures of rod end 

assembly, P/N M004–01H007–045, 

installed on main rotor lag dampers 

have been reported 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. According 

to EASA, an investigation concluded 

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 be affected 

by cracks. EASA consequently 

expanded the applicability of its AD to 

include the additional rod end 

assemblies. 

This proposed AD would retain the 

requirements of AD 2014–04–14 but 

expand the scope of applicable rod end 

assemblies. We also propose to add a 

provision in the Required Actions 

section to clarify that the AD must be 

complied with if the rod end assembly 

is removed during maintenance before 

25 hours time-in-service (TIS). 

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 its 

AD. We are proposing this AD because 

we evaluated all known relevant 

information and determined that an 

unsafe condition is likely to exist or 

develop on other products of the same 

type design. 

Related Service Information 

We reviewed AgustaWestland’s 

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. 

Proposed AD Requirements 

This proposed AD would require 

removing the applicable rod end 

assemblies from service within 25 hours 

TIS or the next time maintenance of the 

helicopter involves removing the rod 

end assembly, whichever occurs first. 

The proposed AD would also prohibit 

installing the applicable rod end 

assemblies on any helicopter. 

Differences Between This Proposed 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 proposed AD would 

not have a calendar time requirement. 

The EASA AD applies to 

AgustaWestland Model A109LUH 

helicopters. This proposed AD would 

not apply to Model A109LUH 

helicopters because that model does not 

have a U.S. type certificate. 

Costs of Compliance 

We estimate that this proposed AD 

would affect 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 

would require 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. 


tkelley on DSK3SPTVN1PROD with PROPOSALS
48700 Federal Register / Vol. 79, No. 159 / Monday, August 18, 2014 / Proposed Rules 

According to the manufacturer’s 

service information, costs of this 

proposed 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. 

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 proposed 

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 proposed AD 

would not have federalism implications 

under Executive Order 13132. This 

proposed AD would 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 

this proposed regulation: 

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 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. 

We prepared an economic evaluation 

of the estimated costs to comply with 

this proposed AD and placed it in the 

AD docket. 

List of Subjects in 14 CFR Part 39 

Air transportation, Aircraft, Aviation 

safety, Incorporation by reference, 

Safety. 

The Proposed Amendment 

Accordingly, under the authority 

delegated to me by the Administrator, 

the FAA proposes to amend 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: 

Agusta S.p.A. Helicopters (Type Certificate 

Currently Held By AgustaWestland 

S.p.A) (AgustaWestland): 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) AgustaWestland 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) AgustaWestland 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) Comments Due Date 

We must receive comments by October 17, 

2014. 

(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 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 

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 August 8, 

2014. 

Lance T. Gant, 

Acting Directorate Manager, Rotorcraft 

Directorate, Aircraft Certification Service. 

[FR Doc. 2014–19495 Filed 8–15–14; 8:45 am] 

BILLING CODE 4910–13–P 


tkelley on DSK3SPTVN1PROD with PROPOSALS