Federal Register / Vol. 73, No. 177 / Thursday, September 11, 2008 / Rules and Regulations 52777 

Reduction Act of 1995 (44 U.S.C. 3501 

et seq.). 

List of Subjects in 9 CFR Part 77 

Animal diseases, Bison, Cattle, 

Reporting and recordkeeping 

requirements, Transportation, 

Tuberculosis. 

■ Accordingly, we are amending 9 CFR 

part 77 as follows: 

PART 77—TUBERCULOSIS 

■ 1. The authority citation for part 77 

continues to read as follows: 

Authority: 7 U.S.C. 8301–8317; 7 CFR 2.22, 

2.80, and 371.4. 

§ 77.7 [Amended] 

■ 2. Section 77.7, paragraph (b), is 

amended by removing the paragraph 

number ‘‘(1)’’ and by removing 

paragraph (b)(2). 

§ 77.9 [Amended] 

■ 3. Section 77.9 is amended as follows: 

■ a. In paragraph (a), by removing the 

word ‘‘None’’ and adding the words 

‘‘New Mexico’’ in its place. 

■ b. In paragraph (b), by removing the 

paragraph number ‘‘(1)’’ and by 

removing paragraph (b)(2). 

Done in Washington, DC, this 5th day of 

September 2008. 

Kevin Shea, 

Acting Administrator, Animal and Plant 

Health Inspection Service. 

[FR Doc. E8–21117 Filed 9–10–08; 8:45 am] 

BILLING CODE 3410–34–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2008–0449; Directorate 

Identifier 2007–SW–10–AD; Amendment 39–

15669; AD 2008–19–02] 

RIN 2120–AA64 

Airworthiness Directives; Bell 

Helicopter Textron Canada Model 222, 

222B, 222U, 230, and 430 Helicopters 

AGENCY: Federal Aviation 

Administration, DOT. 

ACTION: Final rule. 

SUMMARY: We are superseding an 

existing airworthiness directive (AD) for 

Bell Helicopter Textron Canada (Bell) 

Model 222, 222B, 222U, 230, and 430 

helicopters. That AD currently requires 

visually inspecting the main rotor 

hydraulic actuator support (support) to 

verify the presence of all dowel pins 

and sealant between the support and 

transmission and verifying the proper 

torque of each attaching nut (nut). This 

AD requires the same actions as the 

existing AD and also requires repetitive 

actions at intervals not to exceed 600 

hours time-in-service (TIS) or 12 

months, whichever occurs first. This AD 

is prompted by the discovery that a 12- 

month compliance requirement was 

correctly included in an Emergency AD 

(EAD) that we issued but was 

inadvertently omitted when we 

published the Final rule; request for 

comments following the issuance of the 

EAD. The actions specified by this AD 

are intended to prevent failure of the 

support and subsequent loss of control 

of the helicopter. 

DATES: Effective October 16, 2008. 

The incorporation by reference of Bell 

Helicopter Textron Alert Service 

Bulletin Nos. 222–00–86, 222U–00–57, 

230–00–18, and 430–00–17, all dated 

May 19, 2000, was approved previously 

for incorporation by reference by the 

Director of the Federal Register on 

March 2, 2001 (66 FR 10361, February 

15, 2001). 

ADDRESSES: You may examine the AD 

docket on the Internet at http:// 

regulations.gov or in person at the 

Docket Operations office, U.S. 

Department of Transportation, M–30, 

West Building Ground Floor, Room 

W12–140, 1200 New Jersey Avenue, SE., 

Washington, DC 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 Bell 

Helicopter Textron Canada, 12,800 Rue 

de l’Avenir, Mirabel, Quebec J7J1R4, 

telephone (450) 437–2862 or (800) 363–

8023, fax (450) 433–0272. 

Examining the AD Docket: The AD 

docket contains the Notice of proposed 

rulemaking (NPRM), the economic 

evaluation, any comments received, and 

other information. The street address 

and operating hours for the Docket 

Operations office (telephone (800) 647–

5527) are in the ADDRESSES section of 

this AD. Comments will be available in 

the AD docket shortly after they are 

received. 

FOR FURTHER INFORMATION CONTACT: 

Tyrone Millard, Aerospace Engineer, 

FAA, Rotorcraft Directorate, Rotorcraft 

Standards Staff, Fort Worth, Texas 

76193–0110, telephone (817) 222–5439, 

fax (817) 222–5961. 

SUPPLEMENTARY INFORMATION: On 

January 5, 2001, we issued EAD 2001–

01–51 for Bell Model 222, 222B, 222U, 

230, and 430 helicopters which 

requires, at specified time intervals, 

visually inspecting the support for the 

presence of all dowel pins and sealant 

between the support and transmission 

and verifying the proper torque of each 

nut. That action was prompted by the 

failure of a support resulting in an 

accident of a Bell Model 222U 

helicopter. All retaining studs and shear 

pins were found sheared or pulled out 

at the junction between the support and 

transmission case. The requirements of 

that EAD are intended to prevent failure 

of the support and subsequent loss of 

control of the helicopter. 

On February 2, 2001, we issued AD 

2001–01–51, Amendment 39–12105, 

Docket No. 2000–SW–54–AD as a Final 

rule; request for comments (66 FR 

10361, February 15, 2001). Since issuing 

that AD, we discovered that we 

inadvertently omitted the phrase ‘‘or 12 

months, whichever occurs first,’’ from 

compliance paragraph (a) of the 

published final rule AD. Because the 

two versions of AD 2001–01–51 have 

different compliance times, we issued 

an NPRM on April 14, 2008 (73 FR 

21853, April 23, 2008) proposing to 

supersede AD 2001–01–51 and require 

the following: 

• Within 25 hours TIS, and thereafter 

at intervals not to exceed 600 hours TIS 

or 12 months, whichever occurs first: 

• Visually inspecting the support 

and, if any pin is missing or if there is 

no sealant visible, further inspecting the 

support, the transmission case, studs, 

and dowel pins and repairing or 

replacing any unairworthy part before 

further flight; 

• Verifying the torque of the nuts and, 

depending on the location and number 

of loose nuts, before further flight: 

• Removing the support and further 

inspecting the support, transmission 

case, studs, and dowel pins and 

repairing or replacing any unairworthy 

part; and 

• Retorqueing certain nuts; 

• At not less than 20 hours TIS nor 

more than 30 hours TIS after reinstalling 

a support for any reason, verifying the 

torque of the nuts. 

By publishing the NPRM, we gave the 

public an opportunity to participate in 

developing this AD. However, we 

received no comment on the NPRM or 

on our determination of the cost to the 

public. Therefore, based on our review 

and evaluation of the available data, we 

have determined that air safety and the 

public interest require adopting the AD 

as proposed. 

We have reviewed Bell Alert Service 

Bulletin Nos. 222–00–86, 222U–00–57, 

230–00–18, and 430–00–17, all dated 

May 19, 2000 (ASB’s), which specify, 

within 25 hours TIS, conducting a onetime inspection of the support 

installation by accomplishing a torque 

check of the support attaching nuts. In 


rmajette on PRODPC74 with RULES
52778 Federal Register / Vol. 73, No. 177 / Thursday, September 11, 2008 / Rules and Regulations 

addition, a revision to the maintenance 

manual will introduce a recurring 

torque check of the nuts. Transport 

Canada classified these ASB’s as 

mandatory and issued AD No. CF–

2000–29, dated September 6, 2000, to 

ensure the continued airworthiness of 

these helicopters in Canada. 

We estimate that this AD will affect 

145 helicopters of U.S. registry. It will 

take approximately 1⁄2 work hour per 

helicopter to inspect for proper torque, 

and the average labor rate is $80 per 

work hour. The cost for the inspection 

is estimated to be $5,800. Assuming 15 

helicopters require removing the 

support for additional inspections, it 

will take approximately 6 additional 

work hours at $80 per work hour and 

$50 for parts at an additional total cost 

of $7,950. Based on these figures, we 

estimate the total cost impact of this AD 

on U.S. operators to be $13,750, 

assuming no supports are replaced. 

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. 

Therefore, 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); and 

3. 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. 

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 

removing Amendment 39–12105 (66 FR 

10361, February 15, 2001), and by 

adding a new airworthiness directive 

(AD), Amendment 39–15669, to read as 

follows: 

2008–19–02 Bell Helicopter Textron 

Canada: Amendment 39–15669, Docket 

No. FAA–2008–0449; Directorate 

Identifier 2007–SW–10–AD. Supersedes 

AD 2001–01–51, Amendment 39–12105, 

Docket No. 2000–SW–54–AD. 

Applicability: Model 222, 222B, 222U, 230, 

and 430 helicopters, with a main rotor 

hydraulic actuator support (support), part 

number (P/N) 222–040–125–001, installed, 

certificated in any category. 

Compliance: Required as indicated, unless 

accomplished previously. 

To prevent failure of the support and 

subsequent loss of control of the helicopter, 

accomplish the following: 

(a) Within 25 hours time-in-service (TIS) 

and thereafter at intervals not to exceed 600 

hours TIS or 12 months, whichever occurs 

first, accomplish the following: 

(1) Visually inspect the support for the 

presence of all dowel pins and for sealant 

between the support and transmission. If any 

pin is missing, or if no sealant is visible, 

before further flight, remove the support and 

further inspect the support, transmission 

case, studs, and dowel pins in accordance 

with the Accomplishment Instructions, 

paragraphs 5 through 7, of the applicable Bell 

Helicopter Textron Alert Service Bulletin 

Nos. 222–00–86, 222U–00–57, 230–00–18, or 

430–00–17, all dated May 19, 2000 (ASB’s). 

Repair or replace any unairworthy support, 

transmission case, stud, or dowel pin before 

further flight. 

(2) Verify the torque of the support 

attaching nuts (nuts). Upper nuts must not 

rotate at a torque less than 40 in-lbs. Lower 

nuts must not rotate at a torque less than 90 

in-lbs. 

(i) If two or more upper nuts rotate at a 

torque less than 40 in-lbs. or two or more 

lower nuts rotate at a torque less than 90 inlbs., before further flight, remove the support 

and further inspect the support, transmission 

case, studs, and dowel pins in accordance 

with the Accomplishment Instructions, 

paragraph 5 through 7, of the applicable 

ASB’s. Repair or replace any unairworthy 

support, transmission case, stud, or dowel 

pin before further flight. 

(ii) If less than two upper nuts rotate at a 

torque less than 40 in-lbs. or less than two 

lower nuts rotate at a torque less than 90 inlbs., before further flight, retorque the upper 

nut to 50 to 70 in-lbs. plus tare and the lower 

nut to 100 to 140 in-lbs. plus tare. 

(b) At not less than 20 hours TIS nor more 

than 30 hours TIS after reinstalling a support 

for any reason, verify the torque of the nuts 

in accordance with paragraph (a)(2) of this 

AD. 

(c) 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, Rotorcraft 

Standards Staff, FAA, ATTN: Tyrone Millard, 

telephone (817) 222–5439, fax (817) 222– 

5961, for information about previously 

approved alternative methods of compliance. 

(d) You must use the specified portions of 

Bell Helicopter Textron Alert Service 

Bulletin Nos. 222–00–86, 222U–00–57, 230– 

00–18, or 430–00–17, all dated May 19, 2000, 

to do the required inspections. 

(1) The Director of the Federal Register 

previously approved the incorporation by 

reference of these service bulletins on March 

2, 2001 (66 FR 10361, February 15, 2001). 

(2) For service information identified in 

this AD, contact Bell Helicopter Textron 

Canada, 12,800 Rue de l’Avenir, Mirabel, 

Quebec J7J1R4, telephone (450) 437–2862 or 

(800) 363–8023, fax (450) 433–0272. 

(3) You may review copies 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/ 

cfr/ibr-locations.html. 

(e) This amendment becomes effective on 

October 16, 2008. 

Note: The subject of this AD is addressed 

in Transport Canada (Canada) AD CF–2000– 

29, dated September 6, 2000. 

Issued in Fort Worth, Texas, on August 13, 

2008. 

Mark R. Schilling, 

Acting Manager, Rotorcraft Directorate, 

Aircraft Certification Service. 

[FR Doc. E8–20979 Filed 9–10–08; 8:45 am] 

BILLING CODE 4910–13–P 


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