Federal Register / Vol. 75, No. 92 / Thursday, May 13, 2010 / Proposed Rules 26889 

Regulatory Findings 

We have determined that this 

proposed AD would not have federalism 

implications under Executive Order 

13132. Additionally, this proposed AD 

would 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 proposed 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 

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 a draft economic 

evaluation of the estimated costs to 

comply with this proposed AD. See the 

AD docket to examine the draft 

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. 

The Proposed Amendment 

Accordingly, pursuant to the 

authority delegated to me by the 

Administrator, the Federal Aviation 

Administration proposes to amend 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 

adding a new airworthiness directive to 

read as follows: 

Sikorsky Aircraft Corp.: Docket No. FAA– 

2010–0490; Directorate Identifier 2010– 

SW–037–AD. 

Applicability 

Model S–70A and S–70C helicopters, tail 

gearbox output bevel gear (gear), part number 

70358–06620, certificated in any category. 

Compliance 

Required as indicated. 

To prevent a tail rotor separating, loss of 

tail rotor control, and subsequent loss of 

control of the helicopter, do the following: 

(a) Within 500 hours time-in-service (TIS), 

unless accomplished previously, and 

thereafter at intervals not to exceed 500 hours 

TIS, remove the tail rotor servo control and 

pitch beam shaft, and using a Level II 

Ultrasonic Testing Technician or equivalent, 

ultransonic inspect the gear for a crack. 

Ultrasonic inspect the gear by following 

paragraphs A.(5)a. through A(5)n., Note 7, 

Special Service Instructions (SSI) No. 70– 

121A, Revision A, dated May 21, 2009. If you 

find a crack, before further flight, replace the 

gear with an airworthy gear. 

(b) 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, Boston Aircraft 

Certification Office, FAA, ATTN: Terry Fahr, 

Aviation Safety Engineer, Boston Aircraft 

Certification Office, 12 New England 

Executive Park, Burlington, MA 01803, 

telephone (781) 238–7155, fax (781) 238– 

7170, for information about previously 

approved alternative methods of compliance. 

(c) The Joint Aircraft System/Component 

(JASC) Code is: 6520: Tail rotor gearbox. 

Issued in Fort Worth, Texas, on May 3, 

2010. 

Mark R. Schilling, 

Acting Manager, Rotorcraft Directorate, 

Aircraft Certification Service. 

[FR Doc. 2010–11423 Filed 5–12–10; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2010–0488; Directorate 

Identifier 2008–SW–20–AD] 

RIN 2120–AA64 

Airworthiness Directives; Arrow 

Falcon Exporters, Inc. (previously Utah 

State University) et al. Model HH–1K, 

TH–1F, TH–1L, UH–1A, UH–1B, UH–1E, 

UH–1F, UH–1H, UH–1L, and UH–1P 

Helicopters; and Southwest Florida 

Aviation Model UH–1B (SW204 and 

SW204HP) and UH–1H (SW205) 

Helicopters 

AGENCY: Federal Aviation 

Administration, DOT. 

ACTION: Notice of proposed rulemaking 

(NPRM). 

SUMMARY: This document proposes 

adopting a new airworthiness directive 

(AD) for the specified model 

helicopters. The AD would require 

inspecting each affected tail rotor blade 

(blade) forward tip weight retention 

block (tip block) and the aft tip closure 

(tip closure) for adhesive bond voids 

and removing any blade with an 

excessive void from service. This AD 

would also require modifying certain 

blades by installing shear pins and tip 

closure rivets. This proposal is 

prompted by five occurrences of missing 

tip blocks or tip closures resulting in 

minor to substantial damage to blades 

installed on Bell Model 212 and 412 

helicopters. The actions specified by the 

proposed AD are intended to prevent 

loss of a tip block or tip closure, loss of 

a blade, and subsequent loss of control 

of the helicopter. 

DATES: Comments must be received on 

or before July 12, 2010. 

ADDRESSES: Use one of the following 

addresses to submit comments on this 

proposed 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 proposed AD from Bell 


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26890 Federal Register / Vol. 75, No. 92 / Thursday, May 13, 2010 / Proposed Rules 

Helicopter Textron, Inc., P.O. Box 482, 

Fort Worth, Texas 76101, telephone 

(817) 280–3391, fax (817) 280–6466. 

You may examine the comments to 

this proposed AD in the AD docket on 

the Internet at http:// 

www.regulations.gov. 

FOR FURTHER INFORMATION CONTACT: 

DOT/FAA Southwest Region, Michael 

Kohner, ASW–170, Aviation Safety 

Engineer, Rotorcraft Directorate, 

Rotorcraft Certification Office, 2601 

Meacham Blvd., Fort Worth, Texas 

76137, telephone (817) 222–5170, fax 

(817) 222–5783. 

SUPPLEMENTARY INFORMATION: 

Comments Invited 

We invite you to submit any written 

data, views, or arguments regarding this 

proposed AD. Send your comments to 

the address listed under the caption 

ADDRESSES. Include the docket number 

‘‘FAA–2010–0488, Directorate Identifier 

2008–SW–20–AD’’ at the beginning of 

your comments. We specifically invite 

comments on the overall regulatory, 

economic, environmental, and energy 

aspects of the proposed AD. We will 

consider all comments received by the 

closing date and may amend the 

proposed AD in light of those 

comments. 

We will post all comments we 

receive, without change, to http:// 

www.regulations.gov, including any 

personal information you provide. We 

will also post a report summarizing each 

substantive verbal contact with FAA 

personnel concerning this proposed 

rulemaking. Using the search function 

of the docket Web site, you can find and 

read the comments to any of our 

dockets, including the name of the 

individual who sent or signed the 

comment. You may review the DOT’s 

complete Privacy Act Statement in the 

Federal Register published on April 11, 

2000 (65 FR 15477). 

Examining the Docket 

You may examine the docket that 

contains the proposed AD, any 

comments, and other information 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. 

Discussion 

This document proposes adopting a 

new AD for the specified model 

helicopters. The AD would require 

inspecting each affected blade tip block 

and the tip closure for adhesive bond 

voids and removing from service any 

blade with an excessive void. This AD 

would also require modifying certain 

blades by installing shear pins and tip 

closure rivets. This proposal is 

prompted by five occurrences of missing 

tip blocks or tip closures resulting in 

minor to substantial damage to blades 

installed on Bell 212 and 412 

helicopters. This condition, if not 

corrected, could result in loss of a tip 

block or tip closure, loss of a blade, and 

subsequent loss of control of the 

helicopter. 

AD 2002–09–04, Amendment 39– 

12737 (67 FR 22349, May 3, 2002) was 

issued for the Bell Model 205A, 205A– 

1, 205B, 212, 412, 412CF, and 412EP 

helicopters and contained the same 

requirements proposed in this AD. AD 

2007–22–02, Amendment 39–15238 (72 

FR 60760, October 26, 2007), 

superseded AD 2002–09–04 to expand 

the applicability to include other part 

and serial-numbered blades. Some of 

the blades in the applicability of AD 

2007–22–02 are eligible for installation 

on helicopters included in this 

proposed AD. The helicopters included 

in this proposal may have an FAAapproved modification that increases 

the helicopter’s power rating to the 

equivalent of the twin-engine Bell 

Model 205B or 212 helicopter power 

rating. The Bell Model 205B and 212 

helicopters are addressed in AD 2007– 

22–02. Consequently, the inspections 

and modifications required by AD 

2007–22–02 also need to be mandated 

for the helicopters included in this 

proposal. 

We have reviewed Bell Helicopter 

Textron Alert Service Bulletin No. 212– 

00–111, Revision D, dated March 18, 

2005 (ASB), which describes procedures 

for inspecting and modifying certain 

blades. The ASB was issued as a result 

of an investigation of an in-flight loss of 

a tail rotor blade tip block, part number 

(P/N) 212–010–750–105. The 

investigation revealed the countersunk 

screws retaining the tip block were 

installed incorrectly, resulting in 

inadequate tip block retention. Reports 

have also been submitted about loss of 

the tip closures from other blades 

possibly due to inadequate adhesive 

bonding in this area. 

We have identified an unsafe 

condition that is likely to exist or 

develop on other helicopters of these 

same type designs. Therefore, the 

proposed AD would require the 

following: 

• Inspecting the affected blades’ tip 

block and tip closure for voids. 

• Removing any blade that has a void 

in excess of specified limitations. 

• Modifying certain blades by 

installing shear pins. 

• Modifying all affected blades by 

installing tip closure rivets and 

reidentifying the modified blades by 

adding an ‘‘FM’’ after the P/N. 

The actions would be required to be 

done by following specified portions of 

the ASB described previously. 

We estimate that this proposed AD 

would affect 716 helicopters of U.S. 

registry, but only 25 of those helicopters 

will have the increased power rating. It 

would take about 1 work hour to review 

the helicopter records. Also, it would 

take about 3 work hours to inspect the 

affected blades, install the shear pins 

and tip closure rivets, reidentify, and 

dynamically balance the blade set at an 

average labor rate of $85 per work hour. 

Required supplies would cost about $45 

per helicopter. Based on these figures, 

the total cost impact of the proposed AD 

on U.S. operators would be $68,360. 

These costs are assuming that the 

records review to determine the 

applicability would be accomplished on 

the entire fleet of 716 helicopters. These 

costs also assume that the blade sets are 

installed on 25 helicopters with the 

FAA-approved modification and that 

those helicopters would need to be 

inspected and repaired. 

Regulatory Findings 

We have determined that this 

proposed AD would not have federalism 

implications under Executive Order 

13132. Additionally, this proposed AD 

would 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 proposed 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 

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 a draft economic 

evaluation of the estimated costs to 

comply with this proposed AD. See the 

AD docket to examine the draft 

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, 


cprice-sewell on DSKHWCL6B1PROD with PROPOSALS
Federal Register / Vol. 75, No. 92 / Thursday, May 13, 2010 / Proposed Rules 26891 

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. 

The Proposed Amendment 

Accordingly, pursuant to the 

authority delegated to me by the 

Administrator, the Federal Aviation 

Administration proposes to amend 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 

adding a new airworthiness directive to 

read as follows: 

Arrow Falcon Exporters, Inc. (previously 

Utah State University); Firefly Aviation 

Helicopter Services (previously Erickson 

Air-Crane Co.); California Department of 

Forestry; Garlick Helicopters, Inc.; 

Global Helicopter Technology, Inc.; 

Hagglund Helicopters, LLC (previously 

Western International Aviation, Inc.); 

International Helicopters, Inc.; Precision 

Helicopters, LLC; Robinson Air Crane, 

Inc.; San Joaquin Helicopters 

(previously Hawkins and Powers 

Aviation, Inc.); S.M.&T. Aircraft 

(previously US Helicopters, Inc., UNC 

Helicopter, Inc., Southern Aero 

Corporation, and Wilco Aviation); Smith 

Helicopters; Southern Helicopter, Inc.; 

Southwest Florida Aviation 

International, Inc. (previously Jamie R. 

Hill and Southwest Florida Aviation); 

Tamarack Helicopters, Inc. (previously 

Ranger Helicopter Services, Inc.); US 

Helicopter, Inc. (previously UNC 

Helicopter, Inc.); West Coast 

Fabrication; and Williams Helicopter 

Corporation (previously Scott Paper Co.) 

Model HH–1K, TH–1F, TH–1L, UH–1A, 

UH–1B, UH–1E, UH–1F, UH–1H, UH–1L, 

and UH–1P Helicopters; and Southwest 

Florida Aviation Model UH–1B (SW204 

and SW204HP) and UH–1H (SW205) 

Helicopters: Docket No. FAA–2010– 

0488; Directorate Identifier 2008–SW– 

20–AD. 

Applicability: Model HH–1K, TH–1F, TH– 

1L, UH–1A, UH–1B, UH–1E, UH–1F, UH–1H, 

UH–1L, and UH–1P helicopters, and 

Southwest Florida Aviation Model UH–1B 

series (SW204 series and SW204HP) and 

UH–1H series (SW205 series) helicopters, 

with a tail rotor blade (blade), part number 

(P/N) 212–010–750–009 through –129, all 

serial numbers except serial numbers with a 

prefix of ‘‘A’’ or ‘‘AFS,’’ and the number 

11926, 13351, 13367, 13393, 13400, 13402, 

13515, 13540, 13568, 13595 through 13602, 

13619, and subsequent larger numbers, 

installed, certificated in any category. 

Compliance: Within 100 hours time-inservice, unless accomplished previously. 

To prevent loss of the forward tip weight 

retention block (tip block) or aft tip closure 

(tip closure), loss of the blade, and 

subsequent loss of control of the helicopter, 

do the following: 

Note 1: A blade inspected and modified by 

following either AD 2002–09–04 or 2007–22– 

02, for the Bell Helicopter Textron (Bell) 

Model 205A, 205A–1, 205B, 212, 412, 412CF, 

and 412EP helicopters satisfies the 

requirements of this AD. 

(a) Inspect the tip block and tip closure of 

each blade for voids. Remove from service 

any blade with a void in excess of that 

allowed by the applicable maintenance or 

Component Repair and Overhaul Manual 

limitations. 

(b) Inspect the tip block attachment 

countersink screws in the four locations to 

determine if the head of each countersunk 

screw is flush with the surface of the 

abrasion strip. The locations of these four 

screws are depicted on Figure 1 of Bell Alert 

Service Bulletin 212–00–111, Revision D, 

dated March 18, 2005 (ASB). If any of these 

screws are set below the surface of the 

abrasion strip or are covered with filler 

material, install shear pins by following the 

Accomplishment Instructions, Part A, Shear 

Pin Installation paragraphs, of the ASB. 

(c) Install the tip closure rivets on each 

blade, re-identify the modified blade by 

adding an ‘‘FM’’ after the P/N, and 

dynamically balance the tail rotor hub 

assembly by following the Accomplishment 

Instructions, Part B, Aft Tip Closure Rivet 

Installation paragraphs, of the ASB. 

(d) 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 

Certification Office, Rotorcraft Directorate, 

ATTN: DOT/FAA Southwest Region, Michael 

Kohner, ASW–170, Aviation Safety Engineer, 

2601 Meacham Blvd., Fort Worth, Texas 

76137, telephone (817) 222–5170, fax (817) 

222–5783, for information about previously 

approved alternative methods of compliance. 

Issued in Fort Worth, Texas, on May 3, 

2010. 

Mark R. Schilling, 

Acting Manager, Rotorcraft Directorate, 

Aircraft Certification Service. 

[FR Doc. 2010–11419 Filed 5–12–10; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 71 

Proposed Modification of the Detroit, 

MI, Class B Airspace Area; Public 

Meetings 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Notice of public meetings. 

SUMMARY: This notice announces three 

fact-finding informal airspace meetings 

to solicit information from airspace 

users and others concerning a proposal 

to revise the Class B airspace area at 

Detroit, MI. The purpose of these 

meetings is to provide interested parties 

an opportunity to present views, 

recommendations, and comments on the 

proposal. All comments received during 

these meetings will be considered prior 

to any revision or issuance of a notice 

of proposed rulemaking. 

DATES: The informal airspace meetings 

will be held on Tuesday, July 20, 2010, 

at 1:30 p.m.; Wednesday, July 21, 2010, 

at 5 p.m.; and Thursday, July 22, 2010, 

at 7:30 p.m. Comments must be received 

on or before September 6, 2010. 

ADDRESSES: (1) The meeting on 

Tuesday, July 20, 2010, will be held at 

Troy Holiday Inn, 2537 Rochester Court, 

Troy, MI 48083. (2) The meeting on 

Wednesday, July 21, 2010, will be held 

at Eastern Michigan University, Student 

Event Center, Ballroom B, 2nd Floor, 

900 Oakwood Street, Ypsilanti, MI 

48197. (3) The meeting on Thursday, 

July 22, 2010, will be held at Monroe 

Holiday Inn Express, 1225 North Dixie 

Highway, Monroe, MI 48162. 

Comments: Send comments on the 

proposal, in triplicate, to: Anthony D. 

Roetzel, Manager, Operations Support 

Group, Central Service Center, Air 

Traffic Organization, Federal Aviation 

Administration, 2601 Meacham 

Boulevard, Fort Worth, Texas 76137, or 

by fax to (817) 321–7649. 

FOR FURTHER INFORMATION CONTACT: Tim 

Funari, FAA Detroit Metro (DTW) 

ATCT, Building 801, Detroit Metro 

Airport, Detroit, MI 48242; (734) 955– 

5000. 

SUPPLEMENTARY INFORMATION: 


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