46548 Federal Register / Vol. 73, No. 155 / Monday, August 11, 2008 / Rules and Regulations 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2007–0178; Directorate 

Identifier 2007–SW–20–AD; Amendment 39–

15622; AD 2008–16–04] 

RIN 2120–AA64 

Airworthiness Directives; Bell 

Helicopter Textron Canada (BHTC) 

Model 222, 222B, and 222U 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 222, 222B, and 222U helicopters. 

This AD results from mandatory 

continuing airworthiness information 

(MCAI) issued by an aviation authority 

of another country to identify and 

correct an unsafe condition on an 

aviation product. The aviation authority 

of Canada, with which we have a 

bilateral agreement, states in the MCAI: 

‘‘It has been determined that the 

existing rigging procedures for the tail 

rotor pitch change mechanism have to 

be changed due to 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) 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. 

We are issuing this AD to require 

actions that are intended to address 

these unsafe conditions. 

DATES: This AD becomes effective on 

September 15, 2008. 

The Director of the Federal Register 

approved the incorporation by reference 

of certain publications listed in this AD 

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, 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–

5227) 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 following BHTC 

helicopters: 

Model Serial No. (S/N) 

222 ............................ 47006 through 47089. 

222B .......................... 47131 through 47156. 

222U .......................... All. 

That NPRM was published in the 

Federal Register on November 16, 2007 

(72 FR 64542). That NPRM proposed to 

correct an unsafe condition for the 

specified products. The MCAI states: ‘‘It 

has been determined that the existing 

rigging procedures for the tail rotor 

pitch change mechanism have to be 

changed due to possibility of parts 

interference.’’ 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, the tail rotor yoke 

may contact the nut, part number (P/N) 

222–012–731–001, before contacting the 

flapping stop, resulting in less tail rotor 

travel. Additionally, 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 #1 hydraulic system. 

Both the parts interference and the 

higher pedal forces constitute unsafe 

conditions. You may obtain further 

information by examining the MCAI and 

any related service information in the 

AD docket. 

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. 

Relevant Service Information 

Bell Helicopter Textron has issued 

Alert Service Bulletin (ASB) No. 222–

07–104 and ASB No. 222U–07–75, both 

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 AD 

We have reviewed the MCAI and 

related service information and, in 

general, agree with their substance. 

However, this AD requires compliance 

within the next 150 hours time-inservice 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.’’ In 

making this change, we do not intend to 

differ substantively from the 

information provided in the MCAI. This 

difference is highlighted in the 

‘‘Differences Between this AD and the 

MCAI’’ section in the AD. 

Costs of Compliance 

We estimate that this AD will affect 

about 86 products of U.S. registry. Also, 

we estimate that it will take 2 workhours per product to comply with the 

basic requirements of this AD. 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. Therefore, as we do not 

control warranty coverage for affected 

parties, some parties may incur costs 

higher than estimated here. Based on 

these figures, we estimate the cost of the 

AD on U.S. operators to be $13,760, 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 


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Federal Register / Vol. 73, No. 155 / Monday, August 11, 2008 / Rules and Regulations 46549 

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 

product(s) 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: 

2008–16–04 Bell Helicopter Textron 

Canada: Amendment 39–15622; Docket 

No. FAA–2007–0178; Directorate 

Identifier 2007–SW–20–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 the Model 222, serial 

numbers (S/N) 47006 through 47089; Model 

222B, S/N 47131 through 47156, and Model 

222U, all S/N, helicopters, certificated in any 

category. 

Reason 

(d) The mandatory continuing 

airworthiness information (MCAI) states: ‘‘It 

has been determined that the existing rigging 

procedures for the tail rotor pitch change 

mechanism have to be changed due to 

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 

the nut, part number (P/N) 222–012–731–

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 #1 hydraulic system. Both the 

parts interference and the higher pedal forces 

constitute unsafe conditions. This AD 

requires actions that are intended to address 

these 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 actions: 

(1) Adjust the rigging of the tail rotor pitch 

change mechanism in accordance with the 

Accomplishment Instructions, paragraphs 1 

and 2, of the applicable Bell Helicopter 

Textron Alert Service Bulletin (ASB) listed in 

the following Table 1: 

TABLE 1 

Helicopter model Applicable ASB No. & 

date 

222 and 222B ........... No. 222–07–104, 

dated January 9, 

2007. 

222U .......................... No. 222U–07–75, 

dated January 9, 

2007. 

(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 left 

pedal position or full right 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 

applicable ASB listed in Table 1 of this AD. 

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, 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 has the 

authority to approve AMOCs for this AD, if 

requested using the procedures found in 14 

CFR 39.19. 

Related Information 

(h) MCAI Transport Canada Airworthiness 

Directive No. CF–2007–07, dated April 11, 

2007, contains related information. 

Air Transport Association of America (ATA) 

Tracking Code 

(i) Air Transport Association of America 

(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 ASB No. 222–07–104 

or No. 222U–07–75, both 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., Fort Worth, 

Texas 76193; 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 18, 

2008. 

Mark R. Schilling, 

Acting Manager, Rotorcraft Directorate, 

Aircraft Certification Service. 

[FR Doc. E8–17991 Filed 8–8–08; 8:45 am] 

BILLING CODE 4910–13–P 


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