17076 Federal Register / Vol. 78, No. 54 / Wednesday, March 20, 2013 / Rules and Regulations 

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 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 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 a regulatory evaluation 

of the estimated costs to comply with 

this AD and placed it in the AD docket. 

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 regulatory 

evaluation, any comments received, and 

other information. The street address for 

the Docket Operations office (phone: 

(800) 647–5527) is provided in the 

ADDRESSES section. Comments will be 

available in the AD docket shortly after 

receipt. 

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: 

2013–05–19 Rolls-Royce Deutschland Ltd & 

Co KG: Amendment 39–17391; Docket 

No. FAA–2012–1031; Directorate 

Identifier 2012–NE–31–AD. 

(a) Effective Date 

This airworthiness directive (AD) becomes 

effective April 24, 2013. 

(b) Affected ADs 

None. 

(c) Applicability 

This AD applies to Rolls-Royce 

Deutschland Ltd & Co KG (RRD) Tay 611–8 

turbofan engines, serial numbers 16245, 

16256, 16417, 16418, 16584, 16585, 16639, 

16640, 16701, 16702, 16813, 16814, 16853, 

16854, 16879, 16880, 16898, 16905, 16906, 

16911, 16923, 16935, and 16936, with a date 

of the last shop visit before December 8, 

2006. 

(d) Reason 

This AD was prompted by a recent quality 

review determination that bolts with reduced 

material properties may have been installed 

in some engines. We are issuing this AD to 

prevent uncontained turbine disc fracture 

and damage to the airplane. 

(e) Actions and Compliance 

Unless already done, for engines with a 

date of the last shop visit before December 8, 

2006, do the following actions: 

(1) If engine cycles accumulated since the 

last engine shop visit is 5,400 cycles or more 

on the effective date of this AD, inspect the 

bolts installed in the low-pressure turbine 

(LPT) stage 1 static seal and high-pressure 

turbine (HPT) stage 1 air seal support within 

100 engine cycles-in-service after the 

effective date of this AD. 

(2) If engine cycles accumulated since the 

last engine shop visit is fewer than 5,400 

cycles on the effective date of this AD, 

inspect the bolts installed in the LPT stage 

1 static seal and HPT stage 1 air seal support 

before accumulating 5,500 engine cycles 

since the last engine shop visit. 

(3) If you find any broken bolt, brown bolt, 

or bolt with a rough oxidized surface, then 

replace all bolts of the inspected engine 

flange with new bolts before further flight. 

(f) Installation Prohibition 

After the effective date of this AD, do not 

install any HPT module and/or LPT module 

into any engine, or any engine onto an 

airplane, unless the bolts have been 

inspected and replaced if necessary, as 

specified in paragraph (e) of this AD. 

(g) Alternative Methods of Compliance 

(AMOCs) 

The Manager, Engine Certification Office, 

FAA, may approve AMOCs to this AD. Use 

the procedures found in 14 CFR 39.19 to 

make your request. 

(h) Related Information 

(1) For more information about this AD, 

contact Frederick Zink, Aerospace Engineer, 

Engine Certification Office, FAA, Engine & 

Propeller Directorate, 12 New England 

Executive Park, Burlington, MA 01803; 

phone: 781–238–7779; fax: 781–238–7199; 

email: frederick.zink@faa.gov. 

(2) Refer to European Aviation Safety 

Agency AD 2012–0163, dated August 28, 

2012, and RRD Alert Service Bulletin TAY– 

72–A1696, Revision 1, dated June 11, 2012, 

for related information. 

(3) For service information identified in 

this AD, contact Rolls-Royce Deutschland Ltd 

& Co KG, Eschenweg 11, Dahlewitz, 15827 

Blankenfelde-Mahlow, Germany; phone: 49 0 

33–7086–1200 (direct 1016); fax: 49 0 33– 

7086–1212. You may view this service 

information at the FAA, Engine & Propeller 

Directorate, 12 New England Executive Park, 

Burlington, MA. For information on the 

availability of this material at the FAA, call 

781–238–7125. 

(i) Material Incorporated by Reference 

None. 

Issued in Burlington, Massachusetts, on 

March 7, 2013. 

Colleen M. D’Alessandro, 

Assistant Manager, Engine & Propeller 

Directorate, Aircraft Certification Service. 

[FR Doc. 2013–06170 Filed 3–19–13; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2012–0795; Directorate 

Identifier 2008–SW–53–AD; Amendment 39– 

17395; AD 2013–05–23] 

RIN 2120–AA64 

Airworthiness Directives; Eurocopter 

France Helicopters 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule. 

SUMMARY: We are adopting a new 

airworthiness directive (AD) for 

Eurocopter France (Eurocopter) Model 

AS332C, L, and L1 helicopters to 

require a one-time inspection of the 

main rotor head (MRH) swash-plate 

upper bearing (bearing) for a nonsmooth point (friction point). This AD 

was prompted by a report of the 

premature deterioration of the MRH 

bearing of the rotating star installed on 

a Model AS332L1 helicopter. The 

actions of this AD are intended to detect 

deterioration of the MRH bearing and to 

prevent overloading the scissor links 

which drive the main rotor system, 

failure of the scissors links, and 

subsequent loss of control of the 

helicopter. 

DATES: This AD is effective April 24, 

2013. 

ADDRESSES: For service information 

identified in this AD, contact American 

Eurocopter Corporation, 2701 Forum 


wreier-aviles on DSK5TPTVN1PROD with RULES
Federal Register / Vol. 78, No. 54 / Wednesday, March 20, 2013 / Rules and Regulations 17077 

Drive, Grand Prairie, Texas 75053–4005; 

telephone (800) 232–0323; or at http:// 

www.eurocopter.com. 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. 

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, any 

incorporated-by-reference service 

information, 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: Gary 

Roach, Aviation Safety Engineer, 

Regulations and Policy Group, 

Rotorcraft Directorate, FAA, 2601 

Meacham Blvd., Fort Worth, Texas 

76137; telephone (817) 222–5110; email 

gary.b.roach@faa.gov. 

SUPPLEMENTARY INFORMATION: 

Discussion 

On July 30, 2012, at 77 FR 44509, the 

Federal Register published our notice of 

proposed rulemaking (NPRM), which 

proposed to amend 14 CFR part 39 to 

include an AD that would apply to 

Eurocopter Model AS332C, L, and L1 

helicopters with a certain MRH. That 

NPRM proposed to require inspecting 

the MRH bearing for a non-smooth point 

(friction point), and if there is a friction 

point in the bearing, then replacing the 

MRH with an airworthy MRH, or if there 

is not a friction point in the bearing, 

then further inspecting the grease 

expelled from the MRH swash-plate for 

metal particles. The NPRM also 

proposed to require that if there is a 

metal particle in the grease expelled 

from the MRH swash-plate, replacing 

the MRH with an airworthy MRH, or if 

there is not a metal particle in the 

grease, measuring the force required to 

rotate the MRH swash-plate and 

inspecting certain MRH swash-plate 

assemblies for vertical play in the 

bearing to determine the airworthiness 

of the MRH. The proposed requirements 

were intended to detect deterioration of 

the MRH bearing and to prevent 

overloading the scissor links which 

drive the main rotor system, failure of 

the scissors links, and subsequent loss 

of control of the helicopter. 

The European Aviation Safety Agency 

(EASA), which is the Technical Agent 

for the Member States of the European 

Union, issued EASA Emergency AD No. 

2008–0172–E, dated September 9, 2008 

(EAD No. 2008–0172–E), to correct an 

unsafe condition for the Eurocopter 

Model AS 332 C, C1, L, and L1 

helicopters, with an MRH, part number 

(P/N) 332A31–0001–05 or P/N 332A31– 

0001–06, having a serial number (S/N) 

of M172, M216, M261, M308, M547, 

M677, M811, or M936, and having 

‘‘logged less than 275 flight hours since 

the last overhaul or repair.’’ EASA states 

that Eurocopter received a report of 

deterioration of an MRH bearing on an 

MRH that was installed on an AS 332 

L1 helicopter. The AS 332 L1 helicopter 

had logged 72 flight hours since the last 

overhaul. EASA states that there was an 

onset of vibrations in flight and these 

vibrations were due to premature 

deterioration of the upper bearing of the 

MRH swash-plate. They state that this 

condition, if not corrected, ‘‘could lead 

to failure of the scissors links and 

consequently to the control loss of the 

helicopter.’’ 

Comments 

We gave the public the opportunity to 

participate in developing this AD, but 

we did not receive any comments on the 

NPRM (77 FR 44509, July 30, 2012). 

FAA’s Determination 

These helicopters have been approved 

by the aviation authority of France and 

are approved for operation in the United 

States. Pursuant to our bilateral 

agreement with France, 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. 

Related Service Information 

Eurocopter has issued one Emergency 

Alert Service Bulletin (EASB) with two 

different numbers, both Revision 0, and 

both dated September 8, 2008: EASB 

No. 62.00.73 for Model AS332C, L, and 

L1 helicopters and non-FAA type 

certificated Model C1 helicopters; and 

EASB No. 62.00.30 for non-FAA type 

certificated Model 532 UC, AC, UL, AL, 

SC, and UE military helicopters. EASB 

No. 62.00.73 specifies checking for the 

absence of a friction point in the MRH 

bearing. If there is no friction point, 

EASB No. 62.00.73 specifies checking 

the condition of the grease in the swashplate assembly by lubricating the swashplate, rotating it by hand, and 

determining if the expelled grease 

contains traces of metal particles. If the 

expelled grease does not contain traces 

of metal particles, EASB No. 62.00.73 

specifies checking the swash-plate 

‘‘rotation torque’’ using a spring scale. If 

the rotation torque is less than 5.5 kg, 

EASB No. 62.00.73 specifies checking 

the bearing for vertical play. If there is 

a friction point, the expelled grease 

contains traces of metal particles, the 

rotation torque is equal to or greater 

than 5.5 kg, or there is vertical play in 

the bearing, EASB No. 62.00.73 specifies 

removing the MRH and sending it to an 

approved repair station. EASA classified 

this EASB as mandatory and issued 

EAD No. 2008–0172–E to ensure the 

continued airworthiness of these 

helicopters. 

Differences Between This AD and the 

EASA AD 

The EASA Emergency AD includes 

Model AS332C1 helicopters. This AD 

does not include this model helicopter 

since it is not type certificated in the 

U.S. The EASA AD does not include 

S/Ns M561, M859, M935, M938, and 

M942, whereas this AD does include 

those S/Ns. The EASA Emergency AD 

requires operators to comply with the 

requirements no later than the ‘‘next last 

flight of the day.’’ Our AD requires the 

actions to be accomplished within 5 

hours TIS. Also, the EASA Emergency 

AD is applicable to the specified 

helicopters having logged less than 275 

flight hours since the last overhaul or 

repair, whereas our AD only applies to 

the specified helicopters having less 

than 275 hours TIS since the last 

overhaul of the MRH. 

Costs of Compliance 

We estimate that this AD will affect 6 

helicopters of U.S. Registry. We estimate 

that operators may incur the following 

costs in order to comply with this AD. 

It will take approximately 1 work-hour 

per helicopter to accomplish the 

inspection of the MRH bearing for a 

friction point, inspection of the swashplate grease for any metal particles, 

measurement of the swash-plate force to 

rotate, and inspection of the bearing for 

vertical play. It will take approximately 

60 work-hours to replace the MRH. 

These actions will be accomplished at 

an average labor rate of $85 per workhour. We estimate the parts cost of 

replacing an MRH will be 

approximately $20,000. Based on these 

figures, we estimate the total cost of this 


wreier-aviles on DSK5TPTVN1PROD with RULES
17078 Federal Register / Vol. 78, No. 54 / Wednesday, March 20, 2013 / Rules and Regulations 

AD on U.S. operators is $25,610, 

assuming that all affected helicopters 

are inspected and that one MRH in the 

fleet will need to be replaced. 

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 

helicopters identified in this rulemaking 

action. 

Regulatory Findings 

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. 

We prepared an economic evaluation 

of the estimated costs to comply with 

this 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. 

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): 

2013–05–23 Eurocopter France 

(Eurocopter): Amendment 39–17395; 

Docket No. FAA–2012–0795; Directorate 

Identifier 2008–SW–53–AD. 

(a) Applicability 

This AD applies to Eurocopter Model 

AS332C, L, and L1 helicopters with a main 

rotor head (MRH), part number (P/N) 

332A31–0001–05 or P/N 332A31–0001–06, 

with a serial number (S/N) M172, M216, 

M261, M308, M547, M561, M677, M811, 

M859, M935, M936, M938, or M942 

installed; having less than 275 hours time-inservice (TIS) since the last overhaul of the 

MRH; certificated in any category. 

(b) Unsafe Condition 

This AD defines the unsafe condition as 

deterioration of the MRH swash-plate upper 

bearing (bearing), which could result in 

overloading the scissor links which drive the 

main rotor system, failure of the scissors 

links, and subsequent loss of control of the 

helicopter. 

(c) Effective Date 

This AD becomes effective April 24, 2013. 

(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 

Within 5 hours TIS: 

(1) Inspect the MRH bearing for a nonsmooth point (friction point) by rotating the 

MRH swash-plate and: 

(i) If there is a friction point in the bearing, 

before further flight, replace the MRH with 

an airworthy MRH. 

(ii) If there is not a friction point in the 

bearing, lubricate the MRH swash-plate and 

rotate it until grease is expelled; inspect the 

expelled grease for metal particles. 

(A) If there is a metal particle in the grease, 

before further flight, replace the MRH with 

an airworthy MRH. 

(B) If there is not a metal particle in the 

grease, measure the force required to rotate 

the MRH swash-plate using a spring scale 

attached to the pitch change rod attachment 

yokes. 

(1) If the force to rotate the MRH swashplate is equal to or greater than 5.5 kg, before 

further flight, replace the MRH with an 

airworthy MRH. 

(2) If the force to rotate the MRH swashplate is less than 5.5 kg, inspect the MRH 

swash-plate assembly for vertical play in the 

bearing. If there is vertical play in the 

bearing, before further flight, replace the 

MRH with an airworthy MRH. 

(2) Before installing an MRH, P/N 332A31– 

0001–05 or P/N 332A31–001–06, with S/N 

M172, M216, M261, M308, M547, M561, 

M677, M811, M859, M935, M936, M938, or 

M942 on any helicopter, inspect the MRH in 

accordance with paragraph (e)(1) 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: Gary Roach, 

Aviation Safety Engineer, Regulations and 

Policy Group, Rotorcraft Directorate, FAA, 

2601 Meacham Blvd., Fort Worth, Texas 

76137; telephone (817) 222–5110; email 

gary.b.roach@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 Emergency Alert Service 

Bulletin, No. 62.00.73, Revision 0, dated 

September 8, 2008, which is not incorporated 

by reference, contains additional information 

about the subject of this AD. For service 

information identified in this AD, contact 

American Eurocopter Corporation, 2701 

Forum Drive, Grand Prairie, Texas 75053– 

4005; telephone (800) 232–0323; or at 

http://www.eurocopter.com. 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 

(France) Emergency AD No. 2008–0172–E, 

dated September 9, 2008. 

(h) Subject 

Joint Aircraft Service Component (JASC) 

Code: 6400, Tail Rotor System. 

Issued in Fort Worth, Texas, on March 7, 

2013. 

Lance T. Gant, 

Acting Directorate Manager, Rotorcraft 

Directorate, Aircraft Certification Service. 

[FR Doc. 2013–06132 Filed 3–19–13; 8:45 am] 

BILLING CODE 4910–13–P 


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