69860 Federal Register / Vol. 75, No. 220 / Tuesday, November 16, 2010 / Rules and Regulations 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2008–1242; Directorate 

Identifier 96–SW–13–AD; Amendment 39– 

16511; AD 96–18–05 R1] 

RIN 2120–AA64 

Airworthiness Directives; Bell 

Helicopter Textron Canada Model 

206L, 206L–1, and 206L–3 Helicopters 

AGENCY: Federal Aviation 

Administration, DOT. 

ACTION: Final rule. 

SUMMARY: This amendment revises an 

existing airworthiness directive (AD) for 

Bell Helicopter Textron Canada (BHTC) 

Model 206L, 206L–1, and 206L–3 

helicopters with a certain part 

numbered tailboom installed, that 

currently requires a visual inspection of 

the tailboom skin in the areas around 

the nutplates and in the areas of the 

tailboom drive shaft cover retention 

clips for cracks and corrosion using a 

10-power or higher magnifying glass 

until the tailboom is replaced with an 

airworthy tailboom. This action requires 

the same actions as the existing AD, but 

allows a longer interval for the 

repetitive inspections if the tailboom is 

modified to increase its structural 

integrity. Replacement with an 

airworthy tailboom other than a partnumbered tailboom affected by this 

amendment constitutes a terminating 

action for the requirements of this AD. 

This amendment is prompted by an 

accident and several reports of fatigue 

cracks in the tailboom skin in the areas 

around the nutplates for the tail rotor 

fairing and in the areas of the tail rotor 

drive shaft cover retention clips. The 

actions required by this AD are intended 

to prevent failure of the tailboom and 

subsequent loss of control of the 

helicopter. 

DATES: Effective December 21, 2010. 

As of September 16, 1996 (61 FR 

45876, August 30, 1996), the Director of 

the Federal Register approved the 

incorporation by reference of Bell 

Helicopter Textron Inc. Alert Service 

Bulletin 206L–87–47, Revision C, dated 

October 23, 1989, listed in this AD. 

ADDRESSES: 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, or 

at http://www.bellcustomer.com/files/. 

Examining the Docket: You may 

examine the docket that contains this 

AD, any comments, and other 

information on the Internet at http:// 

www.regulations.gov, or at the Docket 

Operations office, West Building 

Ground Floor, Room W12–140, 1200 

New Jersey Avenue, SE., Washington, 

DC. 

FOR FURTHER INFORMATION CONTACT: 

DOT/FAA Southwest Region, Sharon 

Miles, ASW–111, Aviation Safety 

Engineer, Rotorcraft Directorate, 

Regulations and Policy Group, 2601 

Meacham Blvd., Fort Worth, Texas 

76137, telephone (817) 222–5122, fax 

(817) 222–5961. 

SUPPLEMENTARY INFORMATION: A 

proposal to amend 14 CFR part 39 by 

revising AD 96–18–05, Amendment 39– 

9729 (61 FR 45876, August 30, 1996), 

for the specified BHTC Model 206L, 

206L–1, and 206L–3 helicopters, with 

tailboom, part number (P/N) 206–033– 

004–003, –011, –045, or –103, installed, 

was published in the Federal Register 

on November 26, 2008 (73 FR 71955). 

The action proposed to require before 

further flight, unless accomplished 

previously, a visual inspection of the 

tailboom skin for cracks and corrosion 

in the areas around the nutplates for the 

tail rotor fairing and in the areas of the 

tailboom drive shaft cover retention 

clips using a 10-power or higher 

magnifying glass. The action also 

proposed to require the inspections 

repetitively at intervals not to exceed 

100 hours time-in-service (TIS) for 

helicopters that have been modified to 

increase the structural integrity of the 

tailboom in accordance with Bell 

Helicopter Textron Alert Service 

Bulletin No. 206L–87–47, Revision C, 

dated October 23, 1989 (ASB). For 

helicopters that have not been modified 

in accordance with the ASB, we 

proposed to require repetitive 

inspections at intervals not to exceed 

50-hours TIS. That action also proposed 

a terminating action for the repetitive 

inspection requirements by replacing an 

affected tailboom with an airworthy 

tailboom, P/N 206–033–004–143 or 

-177. That action was prompted by an 

accident and several reports of fatigue 

cracks in the tailboom skin in the areas 

around the nutplates for the tail rotor 

fairing, and in the areas of the tail rotor 

drive shaft cover retention clips. 

Transport Canada, the airworthiness 

authority for Canada, notified the FAA 

that an unsafe condition may exist on 

BHTC Model 206L, 206L–1, and 206L– 

3 helicopters. Transport Canada advises 

that there has been one accident and 

several reports of fatigue cracks in the 

tailboom skin in the areas around the 

nutplates for the tail rotor fairing, and 

in the areas of the tail rotor drive shaft 

cover retention clips. 

This helicopter model is 

manufactured in Canada and is type 

certificated for operation in the United 

States under the provisions of 14 CFR 

21.29 and the applicable bilateral 

agreement. When AD 96–18–05 was 

issued, the type certificate for these 

affected model helicopters was in the 

U.S. and the FAA had oversight 

responsibility for these model 

helicopters. Transport Canada issued an 

AD following the FAA AD, except that 

Transport Canada required modifying 

the tailboom in accordance with the 

ASB and increasing the inspection 

interval to 100 hours TIS. Subsequently, 

these type certificates were transferred 

to Canada. 

Interested persons have been afforded 

an opportunity to participate in the 

making of this amendment. No 

comments were received on the 

proposal or the FAA’s determination of 

the cost to the public. The FAA has 

determined that air safety and the 

public interest require the adoption of 

the rule as proposed with only minor, 

non-substantive changes. 

We estimate that this AD will affect 

551 helicopters of U.S. registry. We also 

estimate that it will take about 0.8 work 

hour to inspect and 8 work hours per 

helicopter to modify a helicopter, at an 

average labor rate of $85 per work hour. 

If a helicopter is modified to increase 

the inspection intervals, required parts 

will cost approximately $385. Based on 

these figures, we estimate the total cost 

impact of the AD on U.S. operators to 

be $423,168 per year, assuming all the 

helicopters are unmodified and twelve 

50-hour TIS inspections per helicopter. 

If we assume that all helicopters are 

modified at the beginning of the year, 

the cost impact of the AD on U.S. 

operators will be $776,359 for the first 

year, assuming there are six 100-hour 

TIS inspections the first year, and 

$211,584 for each year thereafter. 

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); and 


jlentini on DSKJ8SOYB1PROD with RULES
Federal Register / Vol. 75, No. 220 / Tuesday, November 16, 2010 / Rules and Regulations 69861 

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. 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 

removing Amendment 39–9729 (61 FR 

45876, August 30, 1996), and by adding 

a new airworthiness directive (AD), to 

read as follows: 

96–18–05 R1 Bell Helicopter Textron 

Canada: Amendment 39–16511. Docket 

No. FAA–2008–1242; Directorate 

Identifier 96–SW–13–AD. Revises AD 

96–18–05, Amendment 39–9729. 

Applicability: Model 206L, 206L–1, and 

206L–3 helicopters, with tailboom, part 

number (P/N) 206–033–004–003, –011, –45, 

–045, or –103, installed, certificated in any 

category. 

Compliance: Required as indicated. 

To prevent failure of the tailboom and 

subsequent loss of control of the helicopter, 

accomplish the following: 

(a) Before further flight, unless 

accomplished previously, using a 10-power 

or higher magnifying glass, inspect the 

tailboom for cracks or corrosion in 

accordance with the Accomplishment 

Instructions, Part II, steps (1) through (7), of 

Bell Helicopter Textron Alert Service 

Bulletin No. 206L–87–47, Revision C, dated 

October 23, 1989 (ASB). 

(b) For a tailboom that has not been 

modified in accordance with the 

Accomplishment Instructions, Part I of the 

ASB, using a 10-power or higher magnifying 

glass, inspect the tailboom for a crack at 

intervals not to exceed 50 hours time-inservice (TIS) in accordance with the 

Accomplishment Instructions, Part II, steps 

(1) through (7), of the ASB. 

(c) For a tailboom that has been modified 

in accordance with the Accomplishment 

Instructions, Part I of the ASB, using a 10- 

power or higher magnifying glass, inspect the 

tailboom for a crack or corrosion at intervals 

not to exceed 100 hours TIS in accordance 

with the Accomplishment Instructions, Part 

II and Part III of the ASB, except you are not 

required to contact the manufacturer. 

(d) If a crack or corrosion is detected that 

is beyond the repairable limits stated in the 

applicable maintenance manual, remove the 

tailboom and replace it with an airworthy 

tailboom. 

(e) Replacing the tailboom with a tailboom, 

P/N 206–033–004–143 or –177, or an 

airworthy part-numbered tailboom that is not 

listed in the Applicability section of this AD, 

constitutes a terminating action for the 

requirements of this AD. 

(f) 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, FAA, ATTN: DOT/FAA 

Southwest Region, Sharon Miles, Aviation 

Safety Engineer, ASW–111, Rotorcraft 

Directorate, Regulations and Policy Group, 

2601 Meacham Blvd., Fort Worth, Texas 

76137, telephone (817) 222–5122, fax (817) 

222–5961, for information about previously 

approved alternative methods of compliance. 

(g) Special flight permits will not be 

issued. 

(h) You must use Bell Helicopter Textron 

Inc. Alert Service Bulletin 206L–87–47, 

Revision C, dated October 23, 1989, to do the 

actions required by this AD, unless the AD 

specifies otherwise. 

(1) On September 16, 1996 (61 FR 45876, 

August 30, 1996), the Director of the Federal 

Register previously approved the 

incorporation by reference of Bell Helicopter 

Textron Inc. Alert Service Bulletin 206L–87– 

47, Revision C, dated October 23, 1989. 

(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, or at 

http://www.bellcustomer.com/files/. 

(3) You may review copies of the service 

information incorporated by reference for 

this AD at the FAA, Office of the Regional 

Counsel, Southwest Region, 2601 Meacham 

Blvd., Room 663, Fort Worth, Texas. 

(4) You may also review copies of the 

service information incorporated by reference 

for this AD 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. 

(i) This amendment becomes effective on 

December 21, 2010. 

Issued in Fort Worth, Texas, on October 26, 

2010. 

Lance T. Gant, 

Acting Manager, Rotorcraft Directorate, 

Aircraft Certification Service. 

[FR Doc. 2010–28470 Filed 11–15–10; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2008–1328; Directorate 

Identifier 2008–CE–066–AD; Amendment 

39–15776; AD 2008–26–10] 

RIN 2120–AA64 

Airworthiness Directives; Cessna 

Aircraft Company (Cessna) 172, 175, 

177, 180, 182, 185, 206, 207, 208, 210, 

303, 336, and 337 Series Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule; correction. 

SUMMARY: The FAA is correcting an 

airworthiness directive (AD) that was 

published in the Federal Register. That 

AD applies to the products listed above. 

In the Information Heading and in the 

SUMMARY section of the published AD, 

we incorrectly included Cessna 188 

series airplanes. In the Unsafe Condition 

section, we incorrectly designated that 

paragraph as (e) instead of (d). Also in 

the Compliance section, paragraph 

(f)(2), and in Figure 1, we incorrectly 

stated the mailing address for the report. 

We are issuing this document to help 

eliminate any confusion that this AD 

may have created in the Information 

Heading and in the SUMMARY and Unsafe 

Condition sections. This document 

corrects those errors. In all other 

respects, the original document remains 

the same. 

DATES: This final rule is effective 

November 16, 2010. The effective date 

for AD 2008–26–10 remains January 5, 

2009. 

ADDRESSES: You may examine the AD 

docket on the Internet at http:// 

www.regulations.gov; or in person at the 


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