53308 Federal Register / Vol. 76, No. 166 / Friday, August 26, 2011 / Rules and Regulations 

code_of_federal_regulations/ 

ibr_locations.html. 

Issued in Renton, Washington, on August 

2, 2011. 

Ali Bahrami, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 2011–21625 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–2007–27747; Directorate 

Identifier 2007–CE–030–AD; Amendment 

39–16782; AD 2009–10–09 R2] 

RIN 2120–AA64 

Airworthiness Directives; Cessna 

Aircraft Company Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule; request for 

comments. 

SUMMARY: We are revising an existing 

airworthiness directive (AD) for certain 

Cessna Aircraft Company (Cessna) 

Models 150F, 150G, 150H, 150J, 150K, 

150L, 150M, A150K, A150L, A150M, 

F150F, F150G, F150H, F150J, F150K, 

F150L, F150M, FA150K, FA150L, 

FRA150L, FA150M, FRA150M, 152, 

A152, F152, and FA152 airplanes. That 

AD currently requires either installing a 

placard prohibiting spins and other 

acrobatic maneuvers in the airplane or 

replacing the rudder stop, the rudder 

stop bumper, and the attachment 

hardware with a rudder stop 

modification kit. This new AD requires 

a change to the modification kit and 

removal of a small amount of material 

from the rudder horn assembly for those 

that have not yet complied with the 

existing AD or for those who can not 

comply with the existing AD (because 

they were unable to obtain full rudder 

travel with the existing kits). This AD 

was prompted by operators who have 

reported difficulty in obtaining full 

rudder travel with the existing 

modification kit. We are issuing this AD 

to revise the kits to use longer rivets and 

allow a small amount of material to be 

removed from the rudder horn 

assembly, which allows operators to 

obtain full rudder travel. 

DATES: This AD is effective September 

12, 2011. 

The Director of the Federal Register 

approved the incorporation by reference 

of certain publications listed in the AD 

as of September 12, 2011. 

We must receive any comments on 

this AD by October 11, 2011. 

ADDRESSES: You may send comments by 

any of the following methods: 

• 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. 

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. You 

may review copies of the referenced 

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. 

Examining the AD Docket 

You may examine the AD docket on 

the Internet at http:// 

www.regulations.gov; or in person at the 

Docket Management Facility 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 Office (phone: 800–647– 

5527) is in the ADDRESSES section. 

Comments will be available in the AD 

docket shortly after receipt. 

FOR FURTHER INFORMATION 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. 

SUPPLEMENTARY INFORMATION: 

Discussion 

On October 27, 2009, we issued AD 

2009–10–09 R1, amendment 39–16074 

(74 FR 57408, November 6, 2009), for 

certain Cessna Aircraft Company 

(Cessna) Models 150F, 150G, 150H, 

150J, 150K, 150L, 150M, A150K, A150L, 

A150M, F150F, F150G, F150H, F150J, 

F150K, F150L, F150M, FA150K, 

FA150L, FRA150L, FA150M, FRA150M, 

152, A152, F152, and FA152 airplanes. 

That AD requires installation of a 

placard prohibiting spins and other 

acrobatic maneuvers in the airplane or 

replacement of the rudder stop, rudder 

stop bumper, and attachment hardware 

with a new rudder stop modification kit 

and replacement of the safety wire with 

jamnuts. The revision was issued to 

clarify certain model and serial number 

designations, remove the duplicate 

requirement of replacing the safety wire 

with jamnuts, and clarify the 

conditional acceptability of using 

modification kit part number (P/N) 

SK152–25 as a terminating action to that 

AD. That AD resulted from follow-on 

investigations of two accidents where 

the rudder was found in the over-travel 

position with the stop plate hooked over 

the stop bolt heads. While neither of the 

accident aircraft met type design, 

investigations revealed that aircraft in 

full conformity with type design can 

exceed the travel limits set by the 

rudder stops. We issued that AD to 

prevent the rudder from traveling past 

the normal travel limit. Operation in 

this non-certificated control position is 

unacceptable and could cause 

undesirable consequences, such as 

contact between the rudder and the 

elevator. 

Actions Since AD Was Issued 

Since we issued AD 2009–10–09 R1 

(74 FR 57408, November 6, 2009), 

compliance with the existing AD 

required operators to check for full 

rudder travel with the installation of the 

existing kits (P/N SK152–24A and P/N 

SK152–25A). Some operators have 

reported difficulty in obtaining full 

rudder travel with these kits. To correct 

this issue, Cessna has revised the kits to 

use longer rivets and allow a small 

amount of material to be removed from 

the rudder horn assembly, which allows 

operators to obtain full rudder travel. 

Relevant Service Information 

We reviewed Cessna Aircraft 

Company Service Bulletin SEB01–1, 

Revision 1, dated March 22, 2011; 

Cessna Aircraft Company Service Kit 

SK152–24B, dated March 22, 2011; and 

Cessna Aircraft Company Service Kit 

SK152–25B, dated March 22, 2011. The 

service information describes 

procedures for replacement of the 

rudder stop, rudder stop bumper, and 

attachment hardware with a new rudder 

stop modification kit. 

FAA’s Determination 

We are issuing this AD because we 

evaluated all the relevant information 

and determined the unsafe condition 

described previously is likely to exist or 

develop in other products of the same 

type design. 

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Federal Register / Vol. 76, No. 166 / Friday, August 26, 2011 / Rules and Regulations 53309 

AD Requirements 

This AD requires installation of a 

placard prohibiting spins and other 

acrobatic maneuvers in the airplane or 

replacement of the rudder stop, rudder 

stop bumper, and attachment hardware 

with a new rudder stop modification kit. 

Change to Existing AD 

This AD would retain certain 

requirements of AD 2009–10–09 R1 (74 

FR 57408, November 6, 2009). Since AD 

2009–10–09 R1 was issued, the AD 

format has been revised, and certain 

paragraphs have been rearranged. As a 

result, the corresponding paragraph 

identifiers have changed in this AD, as 

listed in the following table: 

REVISED PARAGRAPH IDENTIFIER

Requirement in AD 

2009–10–09 R1 

Corresponding 

requirement in this 

AD 

paragraph (e) paragraph (g) 

paragraph (f) paragraph (h) 

FAA’s Justification and Determination 

of the Effective Date 

This action incorporates revised 

modification kits that can be used by all 

airplanes that would need the 

modification incorporated in the future 

and does not require any additional 

work for those airplanes with the 

modification already incorporated (see 

table 3). Therefore, we find that notice 

and opportunity for prior public 

comment are unnecessary and that good 

cause exists for making this amendment 

effective in less than 30 days. 

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 before it becomes effective. 

However, we invite you to send any 

written data, views, or arguments about 

this AD. Send your comments to an 

address listed under the ADDRESSES

section. Include the docket number 

FAA–2007–27747 and directorate 

identifier 2007–CE–030–AD at the 

beginning of your comments. We 

specifically invite comments on the 

overall regulatory, economic, 

environmental, and energy aspects of 

this AD. We will consider all comments 

received by the closing date and may 

amend this AD because 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 we receive 

about this AD. 

Costs of Compliance 

We estimate that this AD affects 

17,090 airplanes of U.S. registry. 

Estimated Costs 

We estimate the following costs to do 

the insertion of the operational 

limitation: 

Action Labor cost Parts cost Cost per 

product 

Cost on U.S. 

operators 

Insert limitations and placard ........................ 1 work-hour × $85 per hour = $85 ............... Not applicable .. $85 $1,452,650 

We estimate the following costs to do 

the modification: 

Action Labor cost Parts cost Cost per 

product 

Cost on U.S. 

operators 

Install a rudder stop modification kit ............ 4 work-hours × $85 per hour = $340 .......... $90 $430 $7,348,700 

The new requirements of this AD add 

no additional economic burden. The 

increased estimated cost of this AD is 

due to increased labor cost from 2009 

when AD 2009–10–09 R1 (74 FR 57408, 

November 6, 2009) was issued. 

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 

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 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. 

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53310 Federal Register / Vol. 76, No. 166 / Friday, August 26, 2011 / Rules and Regulations 

§ 39.13 [Amended] 

■ 2. The FAA amends § 39.13 by 

removing airworthiness directive (AD) 

2009–10–09 R1, Amendment 39–16074 

(74 FR 57408, November 6, 2009), and 

adding the following new AD: 

2009–10–09 R2 Cessna Aircraft Company: 

Amendment 39–16782; Docket No. 

FAA–2007–27747; Directorate Identifier 

2007–CE–030–AD. 

(a) Effective Date 

This AD is effective September 12, 2011. 

(b) Affected ADs 

This AD revises AD 2009–10–09 R1, 

Amendment 39–16074 (74 FR 57408, 

November 6, 2009). 

(c) Applicability 

(c) This AD applies to the following 

airplane models and serial numbers that are 

certificated in any category: 

TABLE 1—APPLICABILITY

Models Serial Nos. 

(1) 150F ....................................... 15061533 through 15064532. 

(2) 150G ...................................... 15064533 through 15064969 and 15064971 through 15067198. 

(3) 150H ...................................... 15067199 through 15069308 and 649. 

(4) 150J ....................................... 15069309 through 15071128. 

(5) 150K ....................................... 15071129 through 15072003. 

(6) 150L ....................................... 15072004 through 15075781. 

(7) 150M ...................................... 15075782 through 15079405. 

(8) A150K .................................... A1500001 through A1500226. 

(9) A150L ..................................... A1500227 through A1500432 and A1500434 through A1500523. 

(10) A150M .................................. A1500524 through A1500734 and 15064970. 

(11) F150F ................................... F150–0001 through F150–0067. 

(12) F150G .................................. F150–0068 through F150–0219. 

(13) F150H .................................. F150–0220 through F150–0389. 

(14) F150J ................................... F150–0390 through F150–0529. 

(15) F150K .................................. F15000530 through F15000658. 

(16) F150L ................................... F15000659 through F15001143. 

(17) F150M .................................. F15001144 through F15001428. 

(18) FA150K ................................ FA1500001 through FA1500081. 

(19) FA150L ................................ FA1500082 through FA1500120. 

(20) FA150L or FRA150L ............ FA1500121 through FA1500261 that are equipped with FKA150–2311 and FKA150–2316, or FRA1500121

through FRA1500261. 

(21) FA150M or FRA150M .......... FA1500262 through FA1500336 that are equipped with FKA150–2311 and FKA150–2316, or FRA1500262 

through FRA1500336. 

(22) 152 ....................................... 15279406 through 15286033. 

(23) A152 ..................................... A1520735 through A1521049, A1500433, and 681. 

(24) F152 ..................................... F15201429 through F15201980. 

(25) FA152 .................................. FA1520337 through FA1520425. 

Note: AD 2009–10–09 R1 (74 FR 57408, 

November 6, 2009) clarified the applicability 

of AD 2009–10–09 (74 FR 22429, May 3, 

2009), eliminated a duplicate requirement for 

replacement of safety wire with jamnuts, and 

clarified the intent of the conditional 

acceptability of using modification kit part 

number (P/N) SK152–25 as a terminating 

requirement to the AD. No further action is 

required for those already in compliance 

with AD 2009–10–09 R1, which included 

verification of full rudder travel as part of the 

kit work. 

(d) Subject 

Joint Aircraft System Component (JASC)/ 

Air Transport Association (ATA) of America 

Code 2720, Rudder Control System. 

(e) Unsafe Condition 

Aircraft in full conformity with type design 

can exceed the travel limits set by the rudder 

stops. We are issuing this AD to prevent the 

rudder from traveling past the normal travel 

limit. Operation in this non-certificated 

control position is unacceptable and could 

cause undesirable consequences, such as 

contact between the rudder and the elevator. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Actions 

To address this problem, you must do 

either the actions in option 1 or option 2 of 

this AD, unless already done: 

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Federal Register / Vol. 76, No. 166 / Friday, August 26, 2011 / Rules and Regulations 53311 

TABLE 2—ACTIONS, COMPLIANCE AND PROCEDURES

Actions Compliance Procedures 

(1) Option 1: For all airplanes that do not have 

modification kits P/N SK152–25B or P/N 

SK152–24B installed (or the other kits allowed by Table 3), do the following: 

(i) Insert the following text into the Limitations section of the FAA-approved airplane flight manual (AFM), and pilot’s 

operating handbook (POH): ‘‘INTENTIONAL SPINS AND OTHER ACROBATIC/AEROBATIC MANEUVERS PROHIBITED PER AD 2009–10–09. NOTE: 

THIS AD DOES NOT PROHIBIT PERFORMING INTENTIONAL STALLS.’’ 

(ii) Fabricate a placard (using at least 1⁄8- 

inch letters) with the following words and 

install the placard on the instrument 

panel within the pilot’s clear view: ‘‘INTENTIONAL SPINS AND OTHER ACROBATIC/AEROBATIC MANEUVERS 

PROHIBITED PER AD 2009–10–09.’’ 

(iii) The AFM and POH limitations in paragraph (g)(1)(i) of the AD and the placard 

in paragraph (g)(1)(ii) of this AD may be 

removed after either paragraph (g)(2)(i) 

or paragraph (g)(2)(ii) of this AD is done. 

Within the next 100 hours time-in-service 

(TIS) after December 11, 2009 (the effective date retained from AD 2009–10–09 R1 

(74 FR 57408, November 6, 2009)), or within the next 12 months after December 11, 

2009 (the effective date retained from AD 

2009–10–09 R1), whichever occurs first. 

A person authorized to perform maintenance 

as specified in 14 CFR section 43.3 of the 

Federal Aviation Administration Regulations 

(14 CFR 43.3) is required to make the AFM 

and POH changes, fabricate the placard required in paragraph (g)(1)(i) of this AD, and 

make an entry into the aircraft logbook 

showing compliance with the portion of the 

AD per compliance with 14 CFR 43.9. 

(2) Option 2: Install a rudder stop modification 

kit: 

(i) For airplanes with a forged bulkhead, replace the rudder stops, rudder stop 

bumpers, and attachment hardware with 

the new rudder stop modification kit P/N 

SK152–25B. 

(ii) For airplanes with a sheet metal bulkhead, replace the rudder stops, rudder 

stop bumpers, and attachment hardware 

with the new rudder stop modification kit 

P/N SK152–24B. 

(iii) Refer to Table 3 in paragraph (g) of 

this AD for other applicable kit P/Ns. 

Within the next 100 hours TIS after December 

11, 2009 (the effective date retained from 

AD 2009–10–09 R1 (74 FR 57408, November 6, 2009)), or within the next 12 months 

after December 11, 2009 (the effective date 

retained from AD 2009–10–09 R1), whichever occurs first. 

Follow Cessna Aircraft Company Service Bulletin SEB01–1, Revision 1, dated March 22, 

2011; and, as applicable, either Cessna Aircraft Company Service Kit SK152–25B, 

dated March 22, 2011, or Cessna Aircraft 

Company Service Kit SK152–24B, dated 

March 22, 2011. 

(h) Kit Part Number Applicability 

Table 3 of this AD identifies when a kit 

P/N that has already been ordered may be 

used to comply with this AD. All future 

orders received by Cessna for kits P/Ns 

SK152–24, SK152–25, SK152–24A, and SK 

152–25A will automatically be filled with 

P/Ns SK152–24B and SK152–25B, 

respectively. 

TABLE 3—KIT APPLICABILITY

Kit P/N Type of bulkhead Can it be installed to comply with this AD, or will credit be given for compliance with 

previous revisions of this AD? 

(1) SK152–24 ...................... sheet metal ......................... NO. 

(2) SK152–25 ...................... forged ................................. ONLY if washer P/N NAS1149F0332P is used (and this is recorded in the maintenance log), AND full rudder travel can be verified. 

(3) SK152–24A ................... sheet metal ......................... ONLY if full rudder travel can be verified. 

(4) SK152–25A ................... forged ................................. ONLY if full rudder travel can be verified. 

(5) SK152–24B ................... sheet metal ......................... YES. 

(6) SK152–25B ................... forged ................................. YES. 

(i) Credit for Actions Accomplished Using 

Previous Service Information 

Credit will be given for the actions in 

paragraphs (g)(1) and (g)(2) of this AD if 

already done and you were able to verify full 

rudder travel before the effective date of this 

AD per AD 2009–10–09 R1, Amendment 39– 

16074 (74 FR 57408, November 6, 2009); 

Cessna Aircraft Company Service Bulletin 

SEB01–1, dated January 22, 2001; and, as 

applicable, either Cessna Aircraft Company 

Service Kit SK152–25A, Revision A, dated 

February 9, 2001, or Cessna Aircraft 

Company Service Kit SK152–24A, Revision 

A, dated March 9, 2001. 

(j) Alternative Methods of Compliance 

(AMOCs) 

(1) The Manager, Wichita ACO, FAA, has 

the authority to approve AMOCs for this AD, 

if requested using the procedures found in 14 

CFR 39.19. In accordance with 14 CFR 39.19, 

send your request to your principal inspector 

or local Flight Standards District Office, as 

appropriate. If sending information directly 

to the manager of the ACO, send it to the 

attention of the person identified in the 

Related Information section of this AD. 

(2) Before using any approved AMOC, 

notify your appropriate principal inspector, 

or lacking a principal inspector, the manager 

of the local flight standards district office/ 

certificate holding district office. 

(3) AMOCs approved for AD 2009–10–09 

(74 FR 22429, May 3, 2009) and AD 2009– 

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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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