70098 Federal Register / Vol. 75, No. 221 / Wednesday, November 17, 2010 / Rules and Regulations 

since-new, whichever occurs first, 

unless the actions have already been 

done. 

Inspection for Nonconforming Land 

Balance-Cuts 

(f) For CT7–9C and –9C3 engines with 

a GGT shaft, P/N 6068T44P02, that has 

a S/N listed in Table 1 of this AD, 

installed, inspect the shaft for 

nonconforming land balance-cuts. Use 

the Accomplishment Instructions 

3.A.(1) through 3.A.(4) of GE CT7–TP 

Alert Service Bulletin 72–A0501, 

Revision 01, dated March 3, 2010, to 

perform the inspection. 

(g) If you find any nonconforming 

land balance-cuts, remove the shaft from 

service. 

Alternative Methods of Compliance 

(h) The Manager, Engine Certification 

Office, has the authority to approve 

alternative methods of compliance for 

this AD if requested using the 

procedures found in 14 CFR 39.19. 

Related Information 

(i) For more information about this 

AD, contact Walter Meibaum, Aerospace 

Engineer, Engine Certification Office, 

FAA, Engine & Propeller Directorate, 12 

New England Executive Park, 

Burlington, MA 01803; telephone (781) 

238–7119; fax (781) 238–7199; e-mail: 

walter.meibaum@faa.gov. 

Material Incorporated by Reference 

(j) You must use GE CT7–TP Alert 

Service Bulletin 72–A0501, Revision 01, 

dated March 3, 2010, to do the actions 

required by this AD, unless the AD 

specifies otherwise. 

(1) The Director of the Federal 

Register approved the incorporation by 

reference of GE CT7–TP Alert Service 

Bulletin 72–A0501, Revision 01, dated 

March 3, 2010, under 5 U.S.C. 552(a) 

and 1 CFR part 51. 

(2) For service information identified 

in this AD, contact General Electric 

Company, GE–Aviation, Room 285, 1 

Neumann Way, Cincinnati, Ohio 45215; 

e-mail geae.aoc@ge.com; telephone 

(513) 552–3272; fax (513) 552–3329. 

(3) You may review copies of the 

service information at the FAA, 12 New 

England Executive Park, Burlington, 

MA. For information on the availability 

of this material at the FAA, call (781) 

238–7125. 

(4) You may also review copies of the 

service information that is incorporated 

by reference at the National Archives 

and Records Administration (NARA). 

For information on the availability of 

this material at an NARA facility, call 

202–741–6030, or go to http:// 

www.archives.gov/federal_register/

code_of_federal_regulations/ibr_

locations.html. 

Issued in Burlington, Massachusetts, on 

October 29, 2010. 

Peter A. White, 

Assistant Manager, Engine & Propeller 

Directorate, Aircraft Certification Service. 

[FR Doc. 2010–28449 Filed 11–16–10; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2010–0522; Directorate 

Identifier 2010–CE–022–AD; Amendment 

39–16506; AD 2010–23–17] 

RIN 2120–AA64 

Airworthiness Directives; Various 

Aircraft Equipped With Rotax Aircraft 

Engines 912 A Series Engines 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Final rule. 

SUMMARY: We are adopting a new 

airworthiness directive (AD) for the 

products listed above. 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 MCAI describes the unsafe 

condition as: 

This Airworthiness Directive (AD) results 

from reports of cracks in the engine 

crankcase. Austro Control GmbH (ACG) 

addressed the problem by issuing AD No 

107R3 which was superseded by ACG AD A– 

2004–01. 

The present AD supersedes the ACG AD 

A–2004–01. On one hand, introduction by 

Rotax of an optimized crankcase assembly 

has permitted to reduce applicability of the 

new AD, when based on engines’ serial 

numbers (s/n). On the other hand, 

applicability is extended for some engines 

that may have been fitted with certain 

crankcase s/n, supplied as spare parts. 

In addition, accomplishment instructions 

given through the relevant Service Bulletins 

(SB) have been detailed to better locate 

engine’s areas that are to be scrutinised. 

We are issuing this AD to require 

actions to correct the unsafe condition 

on these products. 

DATES: This AD becomes effective 

December 22, 2010. 

On December 22, 2010, the Director of 

the Federal Register approved the 

incorporation by reference of certain 

publications listed in this AD. 

ADDRESSES: You may examine the AD 

docket on the Internet at http:// 

www.regulations.gov or in person at 

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 service information identified in 

this AD, contact BRP–Powertrain GMBH 

& Co KG, Welser Strasse 32, A–4623 

Gunskirchen, Austria; phone: (+43) (0) 

7246 601–0; fax: (+43) (0) 7246 6370; 

Internet: http://www.rotax.com. You 

may review copies of the referenced 

service information at the FAA, Small 

Airplane Directorate, 901 Locust, 

Kansas City, Missouri 64106. For 

information on the availability of this 

material at the FAA, call 816–329–4148. 

FOR FURTHER INFORMATION CONTACT: 

Sarjapur Nagarajan, Aerospace Engineer, 

FAA, Small Airplane Directorate, 901 

Locust, Room 301, Kansas City, 

Missouri 64106; telephone: (816) 329– 

4145; fax: (816) 329–4090 e-mail: 

sarjapur.nagarajan@faa.gov. 

SUPPLEMENTARY INFORMATION: 

Discussion 

We issued a notice of proposed 

rulemaking (NPRM) to amend 14 CFR 

part 39 to include an AD that would 

apply to the specified products. That 

NPRM was published in the Federal 

Register on May 21, 2010 (75 FR 28504). 

That NPRM proposed to correct an 

unsafe condition for the specified 

products. The MCAI states: 

This Airworthiness Directive (AD) results 

from reports of cracks in the engine 

crankcase. Austro Control GmbH (ACG) 

addressed the problem by issuing AD No 

107R3 which was superseded by ACG AD A– 

2004–01. 

The present AD supersedes the ACG AD 

A–2004–01. On one hand, introduction by 

Rotax of an optimized crankcase assembly 

has permitted to reduce applicability of the 

new AD, when based on engines’ serial 

numbers (s/n). On the other hand, 

applicability is extended for some engines 

that may have been fitted with certain 

crankcase s/n, supplied as spare parts. 

In addition, accomplishment instructions 

given through the relevant Service Bulletins 

(SB) have been detailed to better locate 

engine’s areas that are to be scrutinised. 

Comments 

We gave the public the opportunity to 

participate in developing this AD. We 

have considered the comment received. 

Request To Change AD 2002–16–26 

Robert Seton of Rotech Research 

Canada Ltd. requested information 

regarding if AD 2006–16–26 would be 

changed to incorporate the same 

terminating action specified in this AD. 

We infer that he wants us to supersede 


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AD 2002–16–26 with a new AD that 

incorporates the same terminating 

action. Mr. Seton also commented there 

was confusion regarding the starting 

serial number range for the new 

crankcase. 

We agree with the comment that AD 

2002–16–26 should be superseded. AD 

2002–16–26 does address the same 

unsafe condition, but that AD applies to 

a different group of products. On 

October 4, 2010, AD 2010–20–23, 

Amendment 39–16458 (75 FR 61046, 

October 4, 2010) was published and is 

effective on November 8, 2010. AD 

2010–20–23 supersedes AD 2002–16–26 

and added the following terminating 

action: 

(k) Installing a crankcase that has a S/N 

above 27811 terminates the inspection 

requirements of paragraphs (g)(1) through 

(g)(4) and (h) of this AD. 

The wording for the applicable starting 

S/N for the terminating action in AD 

2010–20–23 is slightly different than 

what was in the proposed rulemaking 

for this final rule AD. To clarify the 

starting S/N for the terminating action, 

we changed the starting S/N in this final 

rule AD action to match AD 2010–20– 

23. 

Conclusion 

We reviewed the available data, 

including the comment received, and 

determined that air safety and the 

public interest require adopting the AD 

with the changes described previously. 

We determined that these changes will 

not increase the economic burden on 

any operator or increase the scope of the 

AD. 

Differences Between This AD and the 

MCAI or Service Information 

We have reviewed the MCAI and 

related service information and, in 

general, agree with their substance. But 

we might have found it necessary to use 

different words from those in the MCAI 

to ensure the AD is clear for U.S. 

operators and is enforceable. In making 

these changes, we do not intend to differ 

substantively from the information 

provided in the MCAI and related 

service information. 

We might also have required different 

actions in this AD from those in the 

MCAI in order to follow FAA policies. 

Any such differences are highlighted in 

a Note within the AD. 

Costs of Compliance 

We estimate that this AD will affect 

60 products of U.S. registry. We also 

estimate that it will take about 3 workhours per product to comply with the 

basic requirements of this AD. The 

average labor rate is $85 per work-hour. 

Based on these figures, we estimate 

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

to be $15,300, or $255 per product. 

In addition, we estimate that any 

necessary follow-on actions will take 

about 20 work-hours and require parts 

costing $6,500, for a cost of $8,200 per 

product. We have no way of 

determining the number of products 

that may need these actions. 

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. 

For the reasons discussed above, I 

certify this AD: 

(1) Is not a ‘‘significant regulatory 

action’’ under Executive Order 12866; 

(2) Is not a ‘‘significant rule’’ under 

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 regulatory evaluation 

of the estimated costs to comply with 

this AD and placed it in the AD Docket. 

Examining the AD Docket 

You may examine the AD docket on 

the Internet at http:// 

www.regulations.gov; or in person at the 

Docket Management Facility between 9 

a.m. and 5 p.m., Monday through 

Friday, except Federal holidays. The AD 

docket contains the NPRM, the 

regulatory evaluation, any comments 

received, and other information. The 

street address for the Docket Office 

(telephone (800) 647–5527) is in the 

ADDRESSES section. Comments will be 

available in the AD docket shortly after 

receipt. 

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: 

2010–23–17 Various Aircraft: Amendment 

39–16506; Docket No. FAA–2010–0522; 

Directorate Identifier 2010–CE–022–AD. 

Effective Date 

(a) This airworthiness directive (AD) 

becomes effective December 22, 2010. 

Affected ADs 

(b) None. 

Applicability 

(c) This AD applies to all serial numbers 

(S/N) of the following aircraft, equipped with 

a Rotax Aircraft Engines 912 A series engine 

with a crankcase assembly S/N up to and 

including S/N 27811, certificated in any 

category: 


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Type certificate holder Aircraft model Engine model 

Aeromot-Industria Mecanico Metalurgica ltda ....................... AMT–200 ............................................................................. 912 A2 

Diamond Aircraft Industries ................................................... HK 36 R ‘‘SUPER DIMONA’’ ............................................... 912 A 

Diamond Aircraft Industries GmbH ....................................... HK 36 TS .............................................................................

HK 36 TC .............................................................................

912 A3 

912 A3 

Diamond Aircraft Industries Inc. ............................................ DA20–A1 .............................................................................. 912 A3 

HOAC-Austria ........................................................................ DV 20 KATANA ................................................................... 912 A3 

Iniziative Industriali Italiane S.p.A. ........................................ Sky Arrow 650 TC ............................................................... 912 A2 

SCHEIBE-Flugzeugbau GmbH ............................................. SF 25C ................................................................................. 912 A2 or 912 A3 

Subject 

(d) Air Transport Association of America 

(ATA) Code 72: Engine. 

Reason 

(e) The mandatory continuing 

airworthiness information (MCAI) states: 

This Airworthiness Directive (AD) results 

from reports of cracks in the engine 

crankcase. Austro Control GmbH (ACG) 

addressed the problem by issuing AD No 

107R3 which was superseded by ACG AD A– 

2004–01. 

The present AD supersedes the ACG AD 

A–2004–01. On one hand, introduction by 

Rotax of an optimized crankcase assembly 

has permitted to reduce applicability of the 

new AD, when based on engines’ serial 

numbers (s/n). On the other hand, 

applicability is extended for some engines 

that may have been fitted with certain 

crankcase s/n, supplied as spare parts. 

In addition, accomplishment instructions 

given through the relevant Service Bulletins 

(SB) have been detailed to better locate 

engine’s areas that are to be scrutinised. 

The aim of this AD is to ensure that the 

requested engine power is available at any 

time to prevent a sudden loss of power that 

could lead to a hazardous situation in a low 

altitude phase of flight. 

The MCAI requires inspecting certain 

crankcases for cracks and replacing the 

crankcase if cracks are found. 

Actions and Compliance 

(f) Unless already done, do the following 

actions: 

(1) Within the next 50 hours time-inservice (TIS) after December 22, 2010 (the 

effective date of this AD), inspect the engine 

crankcase for cracks following Rotax Aircraft 

Engines Service Bulletin SB–912–029 R3, 

dated July 11, 2006. Repetitively thereafter 

do the inspection at each 100-hour, annual, 

or progressive inspection or within 110 hours 

TIS since last inspection, whichever occurs 

first. 

(2) If cracks in the engine crankcase are 

found during any inspection required by 

paragraph (f)(1) of this AD, before further 

flight, replace the crankcase following Rotax 

Aircraft Engines Service Bulletin SB–912– 

029 R3, dated July 11, 2006. 

(3) Installing a crankcase that has a S/N 

above 27811 terminates the inspection 

requirements of paragraph (f)(1) of this AD. 

Note 1: The service information is a 

combined service bulletin for both the 912 

type (Service Bulletin SB–912–029 R3, dated 

July 11, 2006) and 914 type (Service Bulletin 

SB–914–018, Revision 3, dated July 11, 2006) 

engines. This AD does not reference Service 

Bulletin SB–914–018, Revision 3, dated July 

11, 2006, because this AD does not apply to 

the 914 series engines. This unsafe condition 

for the 914 type engines is the subject of AD 

2010–20–23. 

FAA AD Differences 

Note 2: This AD differs from the MCAI 

and/or service information as follows: No 

differences. 

Other FAA AD Provisions 

(g) The following provisions also apply to 

this AD: 

(1) Alternative Methods of Compliance 

(AMOCs): The Manager, Standards Office, 

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: Sarjapur Nagarajan, Aerospace 

Engineer, FAA, Small Airplane Directorate, 

901 Locust, Room 301, Kansas City, Missouri 

64106; telephone: (816) 329–4145; fax: (816) 

329–4090; e-mail: 

sarjapur.nagarajan@faa.gov. Before using any 

approved AMOC on any airplane to which 

the AMOC applies, notify your appropriate 

principal inspector (PI) in the FAA Flight 

Standards District Office (FSDO), or lacking 

a PI, your local FSDO. 

(2) Airworthy Product: For any requirement 

in this AD to obtain corrective actions from 

a manufacturer or other source, use these 

actions if they are FAA-approved. Corrective 

actions are considered FAA-approved if they 

are approved by the State of Design Authority 

(or their delegated agent). You are required 

to assure the product is airworthy before it 

is returned to service. 

(3) Reporting Requirements: For any 

reporting requirement in this AD, a federal 

agency may not conduct or sponsor, and a 

person is not required to respond to, nor 

shall a person be subject to a penalty for 

failure to comply with a collection of 

information subject to the requirements of 

the Paperwork Reduction Act unless that 

collection of information displays a current 

valid OMB Control Number. The OMB 

Control Number for this information 

collection is 2120–0056. Public reporting for 

this collection of information is estimated to 

be approximately 5 minutes per response, 

including the time for reviewing instructions, 

completing and reviewing the collection of 

information. All responses to this collection 

of information are mandatory. Comments 

concerning the accuracy of this burden and 

suggestions for reducing the burden should 

be directed to the FAA at: 800 Independence 

Ave. SW., Washington, DC 20591, Attn: 

Information Collection Clearance Officer, 

AES–200. 

Special Flight Permit 

(h) We are limiting the special flight 

permits for this AD by the following 

conditions if the crankcase is cracked or 

there is evidence of oil leakage from the 

crankcase: 

(1) Perform a leak check as follows: 

(i) Clean the crankcase surface to remove 

any oil. 

(ii) Warm up the engine to a minimum oil 

temperature of 50 degrees C (120 degrees F). 

Information about warming up the engine 

can be found in the applicable line 

maintenance manual. 

(iii) Accelerate the engine to full throttle 

and stabilize at full throttle speed for a time 

period of 5 to 10 seconds. Information about 

performing a full throttle run can be found 

in the applicable line maintenance manual. 

(iv) Shutdown after running the engine at 

idle only long enough to prevent vapor locks 

in the cooling system and fuel system. 

(v) Inspect the crankcase for evidence of oil 

leakage. Oil wetting is permitted, but oil 

leakage of more than one drip in 3 minutes 

after engine shutdown is not allowed. 

(2) Check the crankcase mean pressure to 

confirm that it is 1.46 pounds-per-square 

inch gage (psig) (0.1 bar) or higher when 

checked at takeoff power to ensure proper 

return of oil from the crankcase to the oil 

tank. Information about checking crankcase 

mean pressure is available in the Lubrication 

System section of the applicable engine 

installation manual. 

(3) A ferry flight is not allowed if oil 

leakage exceeds one drip in 3 minutes or if 

crankcase mean pressure is below 1.46 psig. 

Related Information 

(i) Refer to MCAI EASA AD No.: 2007– 

0025, dated February 1, 2007, for related 

information. 

Material Incorporated by Reference 

(j) You must use Rotax Aircraft Engines 

Service Bulletin SB–912–029 R3, dated July 

11, 2006, to do the actions required by this 

AD, unless the AD specifies otherwise. 

(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 BRP–Powertrain GMBH & 

Co KG, Welser Strasse 32, A–4623 

Gunskirchen, Austria; phone: (+43) (0) 7246 

601–0; fax: (+43) (0) 7246 6370; Internet: 

http://www.rotax.com. 

(3) You may review copies of the 

referenced service information at the FAA, 

Small Airplane Directorate, 901 Locust, 

Kansas City, Missouri 64106. For information 


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on the availability of this material at the 

FAA, call (816) 329–4148. 

(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. 

Issued in Kansas City, Missouri, on 

November 1, 2010. 

John Colomy, 

Acting Manager, Small Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 2010–27980 Filed 11–16–10; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2010–0490; Directorate 

Identifier 2010–SW–037–AD; Amendment 

39–16514; AD 2010–23–24] 

RIN 2120–AA64 

Airworthiness Directives; Sikorsky 

Aircraft Corporation (Sikorsky) Model 

S–70A and S–70C Helicopters 

AGENCY: Federal Aviation 

Administration, DOT. 

ACTION: Final rule. 

SUMMARY: This amendment adopts a 

new airworthiness directive (AD) for the 

Sikorsky Model S–70A and S–70C 

helicopters. This AD requires an 

ultrasonic test (UT) inspection of the tail 

gearbox output bevel gear (gear) for a 

crack. If you find a crack, replacing the 

gear with an airworthy gear is required 

before further flight. This AD is 

prompted by three gear cracking 

incidents, one of which resulted in the 

tail rotor separating from the helicopter. 

The actions specified by this AD are 

intended to detect a crack in the gear to 

prevent a tail rotor separating, loss of 

tail rotor control, and subsequent loss of 

control of the helicopter. 

DATES: Effective December 22, 2010. 

The incorporation by reference of 

certain publications listed in the 

regulations is approved by the Director 

of the Federal Register as of December 

22, 2010. 

ADDRESSES: You may get the service 

information identified in this AD from 

Sikorsky Aircraft Corporation, Attn: 

Manager, Commercial Technical 

Support, mailstop s581a, 6900 Main 

Street, Stratford, CT, telephone (203) 

383–4866, e-mail address 

tsslibrary@sikorsky.com, or at http:// 

www.sikorsky.com. 

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: 

Michael Schwetz, Aviation Safety 

Engineer, Boston Aircraft Certification 

Office, 12 New England Executive Park, 

Burlington, MA 01803, telephone (781) 

238–7761, fax (781) 238–7170. 

SUPPLEMENTARY INFORMATION: A 

proposal to amend 14 CFR part 39 to 

include an AD for the specified model 

helicopters was published in the 

Federal Register on May 13, 2010 (75 

FR 26888). That action proposed to 

require a UT inspection of the gear for 

a crack and replacing any cracked gear 

before further flight. The proposal was 

prompted by three gear crack incidents, 

one of which resulted in the tail rotor 

separating from the helicopter. The tail 

gearbox on the helicopter where the tail 

rotor separated from the helicopter 

experienced a fracture of the output 

shaft spline that drives the tail rotor 

blades. An investigation into the cause 

of the cracks is ongoing. The unsafe 

condition described previously, if not 

corrected, could result in a tail rotor 

separating, loss of tail rotor control, and 

subsequent loss of control of the 

helicopter. 

We have reviewed Sikorsky Alert 

Service Bulletin No. 70–06–28A, 

Revision A, dated May 21, 2009 (ASB), 

which refers to procedures for a UT 

inspection of the gear in accordance 

with Special Service Instructions (SSI) 

No. 70–121A or latest revision. 

This unsafe condition is likely to exist 

or develop on other helicopters of the 

same type design. Therefore, this AD 

requires a UT inspection of the gear, 

part number 70358–06620, for a crack. 

If a crack is found, this AD requires 

replacing the gear with an airworthy 

gear before further flight. The actions 

are required to be to be done by 

following the SSI described previously. 

We provided the public the 

opportunity to participate in developing 

this AD. We received no comments on 

the proposal or on the determination of 

the cost to the public. Therefore, we are 

adopting the action as proposed with 

only minor non-substantive changes. 

We estimate that this AD affects 5 

helicopters in the U.S. registry. The 

actions will take about 4 work hours per 

helicopter at an average labor rate of $85 

per work hour. Required parts cost 

about $20,000 for each gear. Based on 

these figures, we estimate the total cost 

impact of this AD on U.S. operators to 

be $101,700, assuming the gear is 

replaced on the entire fleet. 

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 

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 AD. 

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 Federal Aviation Administration 

amends part 39 of the Federal Aviation 

Regulations (14 CFR part 39) as follows: 


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