46546 Federal Register / Vol. 73, No. 155 / Monday, August 11, 2008 / Rules and Regulations 

TABLE 1—MATERIAL INCORPORATED BY REFERENCE—Continued 

Service Bulletin Revision level Date 

Shorts Service Bulletin SD360–55–20 ...................................................................................................... Revision 2 ........... March 29, 2007. 

(1) The Director of the Federal Register 

approved the incorporation by reference of 

Shorts Alert Service Bulletin SD360–55–A21, 

Revision 1, dated March 29, 2007; Shorts 

Service Bulletin SD360–55–20, Revision 1, 

dated June 20, 2005; and Shorts Alert Service 

Bulletin SD360–55–20, Revision 2, dated 

March 29, 2007; in accordance with 5 U.S.C. 

552(a) and 1 CFR part 51. 

(2) On March 14, 2005 (70 FR 9212, 

February 25, 2005), the Director of the 

Federal Register approved the incorporation 

by reference of Short Brothers Alert Service 

Bulletin SD360–55–A21, dated December 16, 

2004. 

(3) On August 3, 2004 (69 FR 38813, June 

29, 2004), the Director of the Federal Register 

approved the incorporation by reference of 

Short Brothers Service Bulletin SD360–55–

20, dated June 26, 2003. 

(4) Contact Short Brothers, Airworthiness & 

Engineering Quality, P.O. Box 241, Airport 

Road, Belfast BT3 9DZ, Northern Ireland, for 

a copy of this service information. You may 

review copies at the FAA, Transport Airplane 

Directorate, 1601 Lind Avenue, SW., Renton, 

Washington; 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. 

Issued in Renton, Washington, on July 23, 

2008. 

Ali Bahrami, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. E8–17744 Filed 8–8–08; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2008–0450; Directorate 

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

15634; AD 2008–16–16] 

RIN 2120–AA64 

Airworthiness Directives; Bell 

Helicopter Textron Canada (BHTC) 

Model 230 Helicopters 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Final rule. 

SUMMARY: We are adopting a new 

airworthiness directive (AD) for BHTC 

Model 230 helicopters. This AD results 

from mandatory continuing 

airworthiness information (MCAI) 

issued by the aviation authority of 

Canada which indicates that the existing 

rigging procedures for the tail rotor 

pitch change mechanism have to be 

changed due to the possibility of parts 

interference. The cumulative effect of 

individual part tolerances resulting in 

the total assemblage of those parts being 

out of tolerance could result in the tail 

rotor yoke striking another part other 

than the flapping stop (parts 

interference) as cited in the MCAI. Also, 

the misalignment of the tail rotor 

counterweight bellcrank may result in 

higher tail rotor pedal forces and a 

higher pilot workload after failure of the 

No. 1 hydraulic system. Both parts 

interference and the misaligned 

counterweight bellcrank create an 

unsafe condition. This AD requires 

actions that are intended to address 

these unsafe conditions. 

DATES: This AD becomes effective on 

September 15, 2008. 

The incorporation by reference of 

certain publications is approved by the 

Director of the Federal Register as of 

September 15, 2008. 

ADDRESSES: You may examine the AD 

docket on the Internet at 

http://www.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, Aviation Safety 

Engineer, FAA, Rotorcraft Directorate, 

Rotorcraft Standards Staff, Fort Worth, 

Texas 76193–0111, telephone (817) 

222–5439, fax (817) 222–5961. 

SUPPLEMENTARY INFORMATION: 

Discussion 

We issued an NPRM to amend 14 CFR 

part 39 to include an AD that would 

apply to the BHTC Model 230 

helicopters on April 14, 2008. That 

NPRM was published in the Federal 

Register on April 23, 2008 (73 FR 

21855). That NPRM proposed to require, 

within the next 150 hours time-inservice (TIS) or at the next annual 

inspection, whichever occurs first, 

adjusting the rigging of the tail rotor 

pitch change mechanism, and if a gap 

exists between the tail rotor yoke and 

the flapping stop, replacing the tail rotor 

yoke with an airworthy tail rotor yoke. 

If no gap exists between the tail rotor 

yoke and the flapping stop at either full 

right or full left pedal position, 

adjusting the tail rotor pitch change 

mechanism and the tail rotor pedal 

forces was proposed. 

Comments 

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. 

Related Service Information 

Bell Helicopter Textron has issued 

Alert Service Bulletin 230–07–36, dated 

January 9, 2007. The actions described 

in the MCAI are intended to correct the 

same unsafe condition as that identified 

in the service information. 

Differences Between This AD and the 

MCAI 

The compliance times in this AD 

differ from the MCAI in that compliance 

is required within the next 150 hours 

TIS or at the next annual inspection, 

whichever occurs first, instead of ‘‘at the 

next 150 hour or annual inspection but 

no later than 31 December 2007.’’

Costs of Compliance 

We estimate that this AD will affect 

about 20 helicopters of U.S. registry. We 

also estimate that it will take 2 workhours per helicopter to adjust the 


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Federal Register / Vol. 73, No. 155 / Monday, August 11, 2008 / Rules and Regulations 46547 

rigging of the tail rotor pitch change 

mechanism. The average labor rate is 

$80 per work-hour. A replacement yoke 

will cost about $21,218, assuming the 

part is no longer under warranty. 

However, because the service 

information lists this part as covered 

under warranty, we have assumed that 

there will be no charge for this part, if 

needed. Therefore, as we do not control 

warranty coverage for affected parties, 

some parties may incur costs higher 

than estimated here. Based on these 

assumptions and figures, we estimate 

the cost of the AD on U.S. operators to 

be $3,200, or $160 per helicopter. 

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 

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. 

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: 

2008–16–16 Bell Helicopter Textron 

Canada: Amendment 39–15634; Docket 

No. FAA–2008–0450; Directorate 

Identifier 2007–SW–39–AD. 

Effective Date 

(a) This airworthiness directive (AD) 

becomes effective on September 15, 2008. 

Other Affected ADs 

(b) None. 

Applicability 

(c) This AD applies to Bell Helicopter 

Textron Canada (BHTC) Model 230 

helicopters, certificated in any category. 

Reason 

(d) This AD results from mandatory 

continuing airworthiness information (MCAI) 

issued by the aviation authority of Canada 

which indicates that the existing rigging 

procedures for the tail rotor pitch change 

mechanism have to be changed due to the 

possibility of parts interference. This 

‘‘possibility of parts interference’’ occurs 

because the cumulative effect of the 

tolerances on the various parts may result in 

the total assemblage outboard of the 

counterweight bellcrank being out of 

tolerance and the tail rotor yoke may contact 

nut, part number (P/N) 222–012–737–001, 

before contacting the flapping stop. Further, 

the manufacturer has indicated that the tail 

rotor counterweight bellcranks may be 

misaligned, resulting in higher tail rotor 

pedal forces and higher pilot workload after 

failure of the No. 1 hydraulic system. Both 

the parts interference and the higher pedal 

forces constitute unsafe conditions. 

Actions and Compliance 

(e) Within the next 150 hours time-inservice (TIS) or at the next annual inspection, 

whichever occurs first, unless already done, 

do the following: 

(1) Adjust the rigging of the tail rotor pitch 

change mechanism in accordance with the 

Accomplishment Instructions, paragraphs 1 

and 2, in Bell Helicopter Textron Alert 

Service Bulletin 230–07–36, dated January 9, 

2007 (ASB). 

(2) If either at full left pedal position or full 

right pedal position a gap exists between the 

tail rotor yoke and the flapping stop, replace 

the tail rotor yoke with an airworthy tail rotor 

yoke. 

(3) If no gap exists between the tail rotor 

yoke and the flapping stop at either full right 

or full left pedal position, measure the gap 

between the tail rotor yoke and nut, P/N 222–

012–731–001, adjust the tail rotor pitch 

change mechanism, and adjust the tail rotor 

pedal forces in accordance with the 

Accomplishment Instructions, paragraphs 4. 

through 6. of the ASB. 

Differences Between This AD and the MCAI 

(f) This AD requires compliance within the 

next 150 hours TIS or at the next annual 

inspection, whichever occurs first, instead of 

‘‘at the next 150 hour or annual inspection 

but no later than 31 December 2007.’’

Other Information 

(g) Alternative Methods of Compliance 

(AMOCs): The Manager, Safety Management 

Group, FAA, has the authority to approve 

AMOCs for this AD, if requested using the 

procedures found in 14 CFR 39.19. Send 

information to ATTN: Tyrone Millard, 

Aviation Safety Engineer, FAA, Rotorcraft 

Directorate, Rotorcraft Standards Staff, Fort 

Worth, Texas 76193–0111, telephone (817) 

222–5439, fax (817) 222–5961. 

Related Information 

(h) MCAI Transport Canada Airworthiness 

Directive CF–2007–12, dated August 24, 

2007, contains related information. 

Air Transport Association of America (ATA) 

Tracking Code 

(i) ATA Code JASC 6720, Tail Rotor 

Control System, Tail Rotor Pitch Change. 

Material Incorporated by Reference 

(j) You must use the specified portions of 

Bell Helicopter Textron Alert Service 

Bulletin 230–07–36, dated January 9, 2007, to 

do the actions required. 

(1) The Director of the Federal Register 

approved the incorporation by reference of 

this service information under 5 U.S.C. 

552(a) and 1 CFR part 51. 

(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. 

Issued in Fort Worth, Texas on July 27, 

2008. 

Mark R. Schilling, 

Acting Manager, Rotorcraft Directorate, 

Aircraft Certification Service. 

[FR Doc. E8–17990 Filed 8–8–08; 8:45 am] 

BILLING CODE 4910–13–P 


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