53312 Federal Register / Vol. 76, No. 166 / Friday, August 26, 2011 / Rules and Regulations 

10–09 R1 (74 FR 57408, November 6, 2009) 

are approved as AMOCs for this AD. 

(k) Related Information 

For more information about this AD, 

contact Ann Johnson, Aerospace Engineer, 

FAA, Wichita Aircraft Certification Office, 

1801 Airport Road, Room 100, Wichita, 

Kansas 67209; telephone: (316) 946–4105; 

fax: (316) 946–4107; e-mail: 

ann.johnson@faa.gov. 

(l) Material Incorporated by Reference 

(1) You must use the following service 

information to do the actions required by this 

AD, unless the AD specifies otherwise. The 

Director of the Federal Register approved the 

incorporation by reference (IBR) under 5 

U.S.C. 552(a) and 1 CFR part 51 of the 

following service information on September 

12, 2011: 

(i) Cessna Aircraft Company Service 

Bulletin SEB01–1, Revision 1, dated March 

22, 2011; 

(ii) Cessna Aircraft Company Service Kit 

SK152–25B, dated March 22, 2011; and 

(iii) Cessna Aircraft Company Service Kit 

SK152–24B, dated March 22, 2011. 

(2) For service information identified in 

this AD, contact Cessna Aircraft Company, 

Product Support, P.O. Box 7706, Wichita, KS 

67277; telephone: (316) 517–5800; fax: (316) 

517–7271; Internet: http://www.cessna.com. 

(3) You may review copies of the service 

information at the FAA, Small Airplane 

Directorate, 901 Locust, Kansas City, 

Missouri 64106. For information on the 

availability of this material at the FAA, call 

(816) 329–4148. 

(4) You may also review copies of the 

service information that is incorporated by 

reference at the National Archives and 

Records Administration (NARA). For 

information on the availability of this 

material at an NARA facility, call 202–741– 

6030, or go to http://www.archives.gov/ 

federal_register/code_of_federal_regulations/ 

ibr_locations.html. 

Issued in Kansas City, Missouri, on August 

11, 2011. 

John Colomy, 

Acting Manager, Small Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 2011–21210 Filed 8–25–11; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2011–0861; Directorate 

Identifier 2010–SW–092–AD; Amendment 

39–16778; AD 2011–17–14] 

RIN 2120–AA64 

Airworthiness Directives; Agusta 

S.p.A. Model A109A and A109AII 

Helicopters 

AGENCY: Federal Aviation 

Administration, DOT. 

ACTION: Final rule; request for 

comments. 

SUMMARY: This amendment adopts a 

new airworthiness directive (AD) for the 

specified Agusta S.p.A. (Agusta) 

helicopters with a certain tail rotor 

special hub plug (hub plug) installed. 

This action requires a one-time 

inspection to determine the tightening 

torque value of the hub plug, and 

depending on the inspection results, 

replacing certain parts or disassembling 

the tail rotor hub and blades assembly 

and inspecting for damage. If the 

tightening torque value is between 600 

kgcm and 700 kgcm, the lock washer 

and o-ring must be replaced with 

airworthy parts, and no further action is 

required. If the tightening torque value 

is greater than 700 kgcm, the hub plug 

must be replaced with an airworthy 

part. Torque the new hub plug to the 

specified tightening torque between 600 

and 700 kgcm. If the tightening torque 

value of the hub plug is less than 600 

kgcm, the tail rotor hub and blades 

assembly must be disassembled and 

inspected for damage. If a part is found 

that is outside allowable damage 

tolerances, that part must be replaced 

with an airworthy part. This 

amendment is prompted by the 

discovery that a wrong tightening torque 

value for the hub plug was contained in 

a revision to the helicopter maintenance 

manual. The actions specified in this 

AD are intended to detect an improperly 

torqued hub plug that could lead to tail 

rotor failure and subsequent loss of 

control of the helicopter. 

DATES: Effective September 12, 2011. 

The incorporation by reference of 

certain publications listed in the 

regulations is approved by the Director 

of the Federal Register as of September 

12, 2011. 

Comments for inclusion in the Rules 

Docket must be received on or before 

October 25, 2011. 

ADDRESSES: Use one of the following 

addresses to submit comments on this 

AD: 

• Federal eRulemaking Portal: Go to 

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

instructions for submitting comments. 

• Fax: (202) 493–2251. 

• Mail: U.S. Department of 

Transportation, Docket Operations, 

M–30, West Building Ground Floor, 

Room W12–140, 1200 New Jersey 

Avenue, SE., Washington, DC 20590. 

• Hand Delivery: U.S. Department of 

Transportation, Docket Operations, 

M–30, West Building Ground Floor, 

Room W12–140, 1200 New Jersey 

Avenue, SE., Washington, DC 20590, 

between 9 a.m. and 5 p.m., Monday 

through Friday, except Federal holidays. 

You may get the service information 

identified in this AD from 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. 

Examining the Docket: You may 

examine the docket that contains the 

AD, any comments, and other 

information 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 Docket 

Operations office (telephone (800) 647– 

5527) is located in Room W12–140 on 

the ground floor of the West Building at 

the street address stated in the 

ADDRESSES section. Comments will be 

available in the AD docket shortly after 

receipt. 

FOR FURTHER INFORMATION CONTACT: 

Sharon Miles, Aerospace Engineer, 

FAA, Rotorcraft Directorate, Regulations 

and Policy Group, 2601 Meacham Blvd., 

Fort Worth, Texas 76137; telephone: 

(817) 222–5122; fax: (817) 222–5961. 

SUPPLEMENTARY INFORMATION: 

Discussion 

The European Aviation Safety Agency 

(EASA), which is the Technical Agent 

for the Member States of the European 

Union, has issued EASA Emergency AD 

No. 2010–0222–E, dated October 22, 

2010 (EAD 2010–0222–E), to correct an 

unsafe condition for the specified 

Agusta model helicopters with a hub 

plug, part number (P/N) 109–0133–18– 

103, installed. EASA advises that a 

mistaken value of the tightening torque 

of the hub plug has been discovered in 

the maintenance manual of A109A and 

A109AII helicopters. The investigation 

carried out by Agusta has revealed that 

the wrong value of the tightening torque 

of the hub plug was introduced with 

Revision 9 of the A109A and A109AII 

Helicopter Maintenance Manual, dated 

June 15, 2009. EASA states that this 

condition could ultimately lead to a tail 

rotor malfunction. The actions specified 

in this AD are intended to detect an 

improperly torqued hub plug that could 

lead to tail rotor failure and subsequent 

loss of control of the helicopter. 

Related Service Information 

Agusta has issued Mandatory Alert 

Bollettino Tecnico No. 109–132, dated 

October 22, 2010 (BT), which specifies 

performing a one-time inspection of the 

hub plug to verify the right tightening 

torque value, and provides instruction 

to restore the correct installation. If the 

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Federal Register / Vol. 76, No. 166 / Friday, August 26, 2011 / Rules and Regulations 53313 

tightening torque value is at least 600 

kgcm, the BT specifies removing the 

lock washer, P/N 109–0133–17–103, 

and the o-ring, P/N MS29561–119, and 

replacing each part with a new part. If 

the tightening torque value is lower than 

the minimum required 600 kgcm, the 

BT specifies instructions to inspect the 

tail rotor hub and blade assembly, P/N 

109–0131–02 (all dash numbers), for 

damage. If a damaged part is found that 

is outside the allowable damage 

tolerances, the BT specifies replacing 

the part with a new part. The BT also 

specifies restoring the tightening torque 

value of the hub plug to between 600 

kgcm and 700 kgcm. EASA classified 

this service bulletin as mandatory and 

issued EAD 2010–0222–E to ensure the 

continued airworthiness of these 

helicopters. 

FAA’s Evaluation and Unsafe Condition 

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, their 

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 

the same type design. 

Differences Between This AD and the 

EASA AD 

This AD uses the term ‘‘hours time-inservice’’ to describe compliance times, 

and the EASA AD uses the term ‘‘flight 

hours’’. This AD specifies compliance 

with the requirements of this AD within 

5 hours time-in-service (TIS) or 8 days, 

whichever occurs first. The EASA 

Emergency AD specifies compliance 

within 5 hours TIS, but no later than 

November 30, 2010, whichever occurs 

first. This AD addresses corrective 

action if the tightening torque of the hub 

plug is greater than the required value 

of 700 kgcm. 

FAA’s Determination and Requirements 

of This AD 

This unsafe condition is likely to exist 

or develop on other helicopters of the 

same type design. Therefore, this AD is 

being issued to detect an improperly 

torqued hub plug that could lead to tail 

rotor failure and subsequent loss of 

control of the helicopter. This AD 

requires within 5 hours TIS or 8 days, 

whichever comes first, the following: 

• Determine if the tightening torque 

value of the hub plug, P/N 109–0133– 

18–103, is between 600 kgcm and 700 

kgcm. 

• If the tightening torque value of the 

hub plug is between 600 and 700 kgcm, 

replace the lock washer, P/N 109–0133– 

17–103, and the o-ring, P/N MS29561– 

119, with an airworthy part. 

• If the tightening torque value of the 

hub plug is greater than 700 kgcm, 

replace the hub plug, P/N 109–0133– 

18–103 with an airworthy part. Torque 

the hub plug to the specified tightening 

torque between 600 and 700 kgcm. 

• If the tightening torque value of the 

hub plug is less than the required 

minimum 600 kgcm, remove the tail 

rotor hub and blades assembly, P/N 

109–0131–02 (all dash numbers), and 

inspect the broaching and bearing faces 

of the trunnion, P/N 109–0131–05 or 

109–8131–33, for spalling, fretting, or 

wear. Inspect the hub plug, the spacers, 

P/N 109–0133–16–103 and 109–0130– 

89–1, and the static stop, P/N 109– 

0130–27–5, for damage or corrosion. 

Inspect the broaching of the output 

drive shaft, P/N 109–0445–08–3 or 109– 

0445–08–7, for fretting or wear. If a part 

is found that is outside allowable 

damage tolerances, remove the 

unairworthy part and replace it with an 

airworthy part. 

Accomplish the actions by following 

specified portions of the service bulletin 

described previously. The short 

compliance time involved is required 

because the previously described 

critical unsafe condition can adversely 

affect the structural integrity and 

controllability of the helicopter. 

Therefore, the actions specified in this 

AD are required within 5 hours TIS or 

8 days, whichever occurs first, a very 

short compliance time, and this AD 

must be issued immediately. 

Since a situation exists that requires 

the immediate adoption of this 

regulation, it is found that notice and 

opportunity for prior public comment 

hereon are impracticable, and that good 

cause exists for making this amendment 

effective in less than 30 days. 

Costs of Compliance 

We estimate that this AD will affect 

about 63 helicopters of U.S. registry. We 

estimate the costs to accomplish the 

requirements of this AD as follows: 

Action Number of work hours × 

labor rate 

Labor 

cost 

Parts 

cost 

Cost per 

aircraft Affected fleet size Fleet cost 

Determine the tightening 

torque value of the hub 

plug (one-time inspection).

0.25 hrs × labor rate of $85 $21 0 $21 63 .......................................... $1,323 

Replace lock washer and Oring.2.0 hrs × labor rate of $85 ... 170 287 457 56 (assume 89% of fleet) ..... 25,592 

Replace hub plug .................. 2.0 hrs × labor rate of $85 ... 170 850 1020 1 (assume 1% of the fleet .... 1020 

Replace Trunnion, Hub Plug, 

Spacers, Static Stop.

5.0 hrs. × labor rate of $85 .. 425 8,884 9,309 7 (assume 10% of fleet) ....... 65,163 

Total cost impact for this 

AD.

............................................... ................ ................ .................... ............................................... 93,098 

Comments Invited 

This AD is a final rule that involves 

requirements that affect flight safety and 

was not preceded by notice and an 

opportunity for public comment; 

however, we invite you to submit any 

written data, views, or arguments 

regarding this AD. Send your comments 

to an address listed under ADDRESSES. 

Include ‘‘Docket No. FAA–2011–0861; 

Directorate Identifier 2010–SW–092– 

AD’’ at the beginning of your comments. 

We specifically invite comments on the 

overall regulatory, economic, 

environmental, and energy aspects of 

the AD. We will consider all comments 

received by the closing date and may 

amend the AD in light of those 

comments. 

We will post all comments we 

receive, without change, to http:// 

www.regulations.gov, including any 

personal information you provide. We 

will also post a report summarizing each 

substantive verbal contact with FAA 

personnel concerning this AD. Using the 

search function of the docket Web site, 

you can find and read the comments to 

any of our dockets, including the name 

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53314 Federal Register / Vol. 76, No. 166 / Friday, August 26, 2011 / Rules and Regulations 

of the individual who sent the 

comment. You may review the DOT’s 

complete Privacy Act Statement in the 

Federal Register published on April 11, 

2000 (65 FR 19477–78). 

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 the 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 AD. See the AD docket to examine 

the economic evaluation. 

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. 

List of Subjects in 14 CFR Part 39 

Air transportation, Aircraft, Aviation 

safety, Incorporation by reference, 

Safety. 

Adoption of the Amendment 

Accordingly, pursuant to the 

authority delegated to me by the 

Administrator, the Federal Aviation 

Administration amends Part 39 of the 

Federal Aviation Regulations (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. Section 39.13 is amended by adding 

a new airworthiness directive to read as 

follows: 

2011–17–14 AGUSTA S.p.A.: Amendment 

39–16678; Docket No. FAA–2011–0861; 

Directorate Identifier 2010–SW–092–AD. 

Applicability: Models A109A and A109A II 

helicopters, with tail rotor special hub plug 

(hub plug), part number (P/N) 109–0133–18– 

103; certificated in any category. 

Compliance: Required within 5 hours timein-service (TIS) or 8 days, whichever occurs 

first, unless accomplished previously. 

To detect an improperly torqued hub plug 

that could lead to tail rotor failure and 

subsequent loss of control of the helicopter, 

accomplish the following: 

(a) Determine if the tightening torque value 

of the hub plug is between 600 kgcm and 700 

kgcm. 

(b) If the tightening torque value of the hub 

plug is between 600 kgcm and 700 kgcm, 

remove and replace the lock washer, P/N 

109–0133–17–103, and the o-ring, P/N 

MS29561–119, with airworthy parts. 

(c) If the tightening torque value of the hub 

plug is greater than 700 kgcm, remove and 

replace the hub plug, P/N 109–0133–18–103 

with an airworthy part. Torque the hub plug 

to the specified tightening torque between 

600 and 700 kgcm. 

(d) If the tightening torque value of the hub 

plug is less than the 600 kgcm, do the 

following: 

(1) Remove the tail rotor hub and blades 

assembly, P/N 109–0131–02 (all dash 

numbers). 

(2) Inspect the broaching faces (splined 

area ‘‘F’’) and bearing faces (area ‘‘D’’) of the 

trunnion, P/N 109–0131–05 or 109–8131–33, 

for spalling, fretting, or wear by reference to 

Figure 2 of Agusta Mandatory Alert 

Bollettino Tecnico No. 109–132, dated 

October 22, 2010 (BT). If there is spalling, 

fretting, or wear that is outside allowable 

damage tolerances specified in Figure 2 of 

the BT, replace the trunnion with an 

airworthy trunnion. 

(3) Inspect the hub plug, the spacers, P/N 

109–0133–16–103 and 109–0130–89–1, and 

the static stop, P/N 109–0130–27–5, for 

spalling, fretting, wear, or corrosion. If there 

is any spalling, fretting, wear, or corrosion, 

replace the part with an airworthy part. 

(4) Inspect the broaching area ‘‘H’’ of the 

output drive shaft, P/N 109–0445–08–3 or 

109–0445–08–7, of the tail rotor gearbox 

assembly, P/N 109–0440–01, for fretting, 

wear, or other damage by referring to Figure 

3 of the BT. If there is any fretting, wear, or 

other damage of 0.07 mm or more in depth 

between loaded and unloaded areas, replace 

the output drive shaft with an airworthy 

output drive shaft. 

(5) Reinstall the tail rotor hub and blade 

assembly, and tighten the torque on the hub 

plug to between 600 kgcm and 700 kgcm. 

(6) Accomplish a flap axis play inspection, 

a flap hinge friction inspection, and a tail 

rotor dynamic balance. 

(e) To request a different method of 

compliance or a different compliance time 

for this AD, follow the procedures in 14 CFR 

39.19. Contact the Manager, Safety 

Management Group, ATTN: DOT/FAA 

Southwest Region, Sharon Miles, Rotorcraft 

Directorate, Regulations and Policy Group, 

ASW–111, 2601 Meacham Blvd., Fort Worth, 

Texas 76137; telephone: (817) 222–5122; fax: 

(817) 222–5961, for information about 

previously approved alternative methods of 

compliance. 

(f) The Joint Aircraft System/Component 

(JASC) Code is 6500: Tail rotor drive system. 

(g) The inspection shall be done in 

accordance with the specified portions of 

Agusta Mandatory Alert Bollettino Tecnico 

No. 109–132, dated October 22, 2010. The 

Director of the Federal Register approved this 

incorporation by reference in accordance 

with 5 U.S.C. 552(a) and 1 CFR part 51. 

Copies may be obtained from 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. Copies may be inspected at the 

FAA, Office of the Regional Counsel, 

Southwest Region, 2601 Meacham Blvd., 

Room 663, Fort Worth, Texas, or 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/code_

of_federal_regulations/ibr_locations.html. 

(h) This amendment becomes effective on 

September 12, 2011. 

Note: The subject of this AD is addressed 

in the European Aviation Safety Agency 

(Italy), Emergency AD 2010–0222–E, dated 

October 22, 2010. 

Issued in Fort Worth, Texas, on August 8, 

2011. 

Kim Smith, 

Manager, Rotorcraft Directorate, Aircraft 

Certification Service. 

[FR Doc. 2011–21475 Filed 8–25–11; 8:45 am] 

BILLING CODE 4910–13–P 

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