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 


jlentini on DSKJ8SOYB1PROD with RULES
69862 Federal Register / Vol. 75, No. 220 / Tuesday, November 16, 2010 / Rules and Regulations 

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 address for the 

Docket Office (phone: 800–647–5527) is 

Document Management Facility, U.S. 

Department of Transportation, Docket 

Operations, M–30, West Building 

Ground Floor, Room W12–140, 1200 

New Jersey Avenue, SE., Washington, 

DC 20590. 

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 

address: ann.johnson@faa.gov. 

SUPPLEMENTARY INFORMATION: 

Airworthiness Directive 2008–26–10, 

Amendment 39–15776 (73 FR 78939, 

December 24, 2008), currently requires 

inspecting the alternate static air source 

selector valve to assure that the part 

number identification placard does not 

obstruct the alternate static air source 

selector valve port. If the part number 

identification placard obstructs the port, 

this AD also requires removing the 

placard, assuring that the port is 

unobstructed, and reporting to the FAA 

if obstruction is found for certain Cessna 

172, 175, 177, 180, 182, 185, 206, 207, 

208, 210, 303, 336, and 337 series 

airplanes. 

As published, the Information 

Heading and the Summary sections of 

the AD incorrectly included Cessna 188 

series airplanes. The Unsafe Condition 

section is incorrectly designated as 

paragraph (e) instead of paragraph (d). 

Also, the mailing address for the report 

specified in the Compliance section, 

paragraph (f)(2), and in Figure 1 is 

incorrectly stated as 1804 instead of 

1801. 

No other part of the preamble or 

regulatory information has been 

changed; therefore, only the changed 

portion of the final rule is being 

published in the Federal Register. 

The effective date of AD 2008–26–10 

remains January 5, 2009. 

Correction of Non-Regulatory Text 

In the Federal Register of December 

24, 2008, AD 2008–26–10; Amendment 

39–15776 is corrected as follows: 

On page 78939, in the second column, 

on line 10, under the heading 

DEPARTMENT OF 

TRANSPORTATION, remove 188 from 

affected series airplanes. 

On page 78939, in the second column, 

on line 19, under the heading 

DEPARTMENT OF 

TRANSPORTATION, in the SUMMARY

section, remove 188 from affected series 

airplanes. 

Correction of Regulatory Text 

§ 39.13 [Corrected] 

In the Federal Register of December 

24, 2008, AD 2008–26–10; Amendment 

39–15776 is corrected as follows: 

On page 78942, in the first column, 

under the Unsafe Condition section, 

change paragraph (e) to (d). 

On page 78943, in the second column, 

in paragraph (f)(2), on line 3, change 

1804 to 1801. 

On page 78943, in Figure 1, in the 

address for the Wichita Manufacturing 

Inspection District Office, change 1804 

to 1801. 

Issued in Kansas City, Missouri, on 

November 4, 2010. 

James E. Jackson, 

Acting Manager, Small Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 2010–28579 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–2010–1126; Directorate 

Identifier 2010–SW–078–AD; Amendment 

39–16515; AD 2010–18–52] 

RIN 2120–AA64 

Airworthiness Directives; MD 

Helicopters, Inc. Model MD900 

Helicopters 

AGENCY: Federal Aviation 

Administration, DOT. 

ACTION: Final rule; request for 

comments. 

SUMMARY: This document publishes in 

the Federal Register an amendment 

adopting Emergency Airworthiness 

Directive (AD) 2010–18–52 which was 

sent previously to all known owners 

and operators of MD Helicopters, Inc. 

(MDHI) Model MD900 helicopters by 

individual letters. This AD requires 

visually inspecting the main rotor hub 

(hub) for a crack. If a crack is found, this 

AD requires, before further flight, 

replacing the unairworthy hub with an 

airworthy hub. Additionally, if a 

cracked hub is found, this AD requires 

reporting the finding to the Los Angeles 

Aircraft Certification Office within 10 

days of finding the crack. This AD is 

prompted by two reports of cracks 

detected in the hub in the area near the 

flex beam bolt hole locations during 

maintenance on two MDHI Model 

MD900 helicopters. The actions 

specified by this AD are intended to 

detect a crack in the hub and prevent 

failure of the hub and subsequent loss 

of control of the helicopter. 

DATES: Effective December 1, 2010, to all 

persons except those persons to whom 

it was made immediately effective by 

Emergency AD 2010–18–52, issued on 

August 23, 2010, which contained the 

requirements of this amendment. 

Comments for inclusion in the Rules 

Docket must be received on or before 

January 18, 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 MD 

Helicopters, Inc., 4555 East McDowell 

Road, Mesa, Arizona 85215–9734, USA, 

telephone (480) 346–6300 or (800) 388– 

3378, fax (480) 346–6813, or at 

serviceengineering@mdhelicopters.com. 

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: 

Roger Durbin, Aviation Safety Engineer, 

FAA, Los Angeles Aircraft Certification 

Office, Airframe Branch, 3960 

Paramount Blvd., Lakewood, California 

90712, telephone (562) 627–5233, fax 

(562) 627–5210. 

SUPPLEMENTARY INFORMATION: On August 

18, 2010, we issued Emergency AD 

2010–18–51. That Emergency AD was 

prompted by two reports of cracks 

detected in the hub in the area near the 

flex beam bolt hole locations during 


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