This section of the FEDERAL REGISTER

contains regulatory documents having general

applicability and legal effect, most of which

are keyed to and codified in the Code of

Federal Regulations, which is published under

50 titles pursuant to 44 U.S.C. 1510.

The Code of Federal Regulations is sold by

the Superintendent of Documents. Prices of

new books are listed in the first FEDERAL

REGISTER issue of each week.

Rules and Regulations Federal Register

26711 

Vol. 72, No. 91 

Friday, May 11, 2007 

DEPARTMENT OF AGRICULTURE 

Animal and Plant Health Inspection 

Service 

7 CFR Part 319 

[Docket No. 03–016–4] 

RIN 0579–AC18 

Cut Flowers From Countries With 

Chrysanthemum White Rust 

AGENCY: Animal and Plant Health 

Inspection Service, USDA. 

ACTION: Final rule; stay of certain 

provisions. 

SUMMARY: We recently published a final 

rule amending the cut flowers 

regulations to establish specific 

requirements for the importation of cut 

flowers that are hosts of chrysanthemum 

white rust (CWR) from countries where 

the disease is known to occur. The final 

rule had an effective date of May 3, 

2007. In order to allow affected 

exporters of cut flowers and the national 

plant protection organizations of 

countries where CWR is known to occur 

additional time to make necessary 

preparations to comply with certain 

new inspection and certification 

procedures that will be required as a 

result of the final rule, we are staying a 

portion of the amended regulations for 

30 days from the effective date of our 

final rule. 

DATES: Effective May 11, 2007, 7 CFR 

319.74–2(d)(3) is stayed until June 2, 

2007. 

FOR FURTHER INFORMATION CONTACT: Mr. 

Tony Roman, Import Specialist, 

Commodity Import Analysis and 

Operation, PPQ, APHIS, 4700 River 

Road Unit 133, Riverdale, MD 20737– 

1231; (301) 734–8758. 

SUPPLEMENTARY INFORMATION: 

Background 

The regulations in 7 CFR part 319 

prohibit or restrict the importation of 

plants, plant parts, and related materials 

to prevent the introduction of plant 

pests into the United States. The 

regulations in ‘‘Subpart—Nursery Stock, 

Plants, Roots, Bulbs, Seeds, and Other 

Plant Products,’’ §§ 319.37 through 

319.37–14 (referred to below as the 

nursery stock regulations) restrict, 

among other things, the importation of 

living plants, plant parts, and seeds for 

propagation. Conditions governing the 

importation of cut flowers into the 

United States are contained in ‘‘SubpartCut Flowers’’ (§§ 319.74–1 through 

319.74–4, referred to below as the cut 

flowers regulations). 

On April 3, 2007, we published in the 

Federal Register (72 FR 15805–15812, 

Docket No. 03–016–3) a final rule 

amending the cut flowers regulations to 

establish specific requirements for the 

importation of cut flowers that are hosts 

of chrysanthemum white rust (CWR) 

from countries where the disease is 

known to occur. We also amended the 

nursery stock regulations to update lists 

of countries where CWR is known to 

occur. The final rule had an effective 

date of May 3, 2007. 

We recently received communications 

from industry representatives and the 

Government of Colombia expressing 

concern that the May 3, 2007, effective 

date of the final rule did not allow 

adequate time for those entities to 

prepare to comply with the new 

inspection and certification procedures 

that will be required under § 319.74– 

2(d)(3) of the cut flowers regulations as 

a result of the final rule. A delay in the 

implementation of those new 

requirements was requested. After 

considering those requests, we have 

elected to allow an additional 30 days 

for those entities to prepare to comply 

with those new requirements. To 

provide that additional time, we are 

staying § 319.74–2(d)(3) until June 2, 

2007. 

We explained in the proposed rule 

that preceded our April 3, 2007, final 

rule, as well as in the final rule itself, 

that we have been administratively 

regulating cut flowers from countries 

where CWR is known to occur since 

1974, and that those measures have 

been effective in preventing the 

introduction of CWR on cut flowers 

from those countries. During the time 

that § 319.74–2(d)(3) is stayed, we will 

continue to apply our existing 

administrative restrictions on cut 

flowers from countries where CWR is 

known to occur. 

Authority: 7 U.S.C. 450, 7701–7772, and 

7781–7786; 21 U.S.C. 136 and 136a; 7 CFR 

2.22, 2.80, and 371.3. 

Done in Washington, DC, this 3rd day of 

May 2007. 

Kevin Shea, 

Acting Administrator, Animal and Plant 

Health Inspection Service. 

[FR Doc. E7–9151 Filed 5–10–07; 8:45 am] 

BILLING CODE 3410–34–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2005–23809; Directorate 

Identifier 2005–NE–52–AD; Amendment 39– 

15048; AD 2007–10–07] 

RIN 2120–AA64 

Airworthiness Directives; Turbomeca 

Arriel 2B Series Turboshaft Engines 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Final rule; request for 

comments. 

SUMMARY: We are superseding an 

existing airworthiness directive (AD) by 

adopting a new 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: 

The deterioration of the splines on the 

HP/LP pump assembly drive shaft may 

eventually interrupt fuel supply and cause 

uncommanded in-flight engine shutdown. 

The result may be an emergency autorotation 

landing or, at worst, an accident. 

Two cases of in-flight shutdown resulting 

from splines deterioration have been reported 

for the ARRIUS 2B1 engine, which has the 

same HP/LP pump drive design as the 

ARRIEL 2. These cases prompted us to 

require the inspection at 500 hours and each 

time the HMU is removed/installed. 

This AD modifies the content of the 

previous DGAC France AD F–2005–188 

(EASA Approval Number 2005–6408) in 

adding a one time inspection within 30 


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26712 Federal Register / Vol. 72, No. 91 / Friday, May 11, 2007 / Rules and Regulations 

operating hours from effective date of this AD 

as well as HMU re-installation according to 

a maintenance task modified to avoid this 

kind of wrong assembly. This has been set up 

following one case of improper clipping of 

the coupling shaft onto the drive gear shaft, 

which resulted in an uncommanded in-flight 

engine shutdown (on a twin engine 

rotorcraft). This precaution measure has been 

taken only on engines powering single engine 

rotorcraft. 

This AD requires actions that are 

intended to address the unsafe 

condition described in the MCAI. 

DATES: This AD becomes effective May 

29, 2007. 

The Director of the Federal Register 

approved the incorporation by reference 

of Turbomeca Mandatory Service 

Bulletin No. 292 73 2812, Update No. 4, 

dated January 2, 2007, listed in the AD, 

as of May 29, 2007. 

We must receive comments on this 

AD by June 11, 2007. 

ADDRESSES: You may send comments by 

any of the following methods: 

• DOT Docket Web Site: Go to 

http://dms.dot.gov and follow the 

instructions for sending your comments 

electronically. 

• Fax: (202) 493–2251. 

• Mail: Docket Management Facility, 

U.S. Department of Transportation, 400 

Seventh Street, SW., Nassif Building, 

Room PL–401, Washington, DC 20590–

0001. 

• Hand Delivery: Room PL–401 on 

the plaza level of the Nassif Building, 

400 Seventh Street, SW., Washington, 

DC, between 9 a.m. and 5 p.m., Monday 

through Friday, except Federal holidays. 

• Federal eRulemaking Portal: http:// 

www.regulations.gov. Follow the 

instructions for submitting comments. 

Examining the AD Docket 

You may examine the AD docket on 

the Internet at http://dms.dot.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 this 

AD, the regulatory evaluation, any 

comments received, and other 

information. The street address for the 

Docket Office (telephone (800) 647–

5227) is in the ADDRESSES section. 

Comments will be available in the AD 

docket shortly after receipt. 

FOR FURTHER INFORMATION CONTACT: 

Christopher Spinney, Aerospace 

Engineer, Engine Certification Office, 

FAA, Engine and Propeller Directorate, 

12 New England Executive Park, 

Burlington, MA 01803; e-mail: 

Christopher.spinney@faa.gov; telephone 

(781) 238–7175; fax (781) 238–7199. 

SUPPLEMENTARY INFORMATION: 

Streamlined Issuance of AD 

The FAA is implementing a new 

process for streamlining the issuance of 

ADs related to MCAI. This streamlined 

process will allow us to adopt MCAI 

safety requirements in a more efficient 

manner and will reduce safety risks to 

the public. This process continues to 

follow all FAA AD issuance processes to 

meet legal, economic, Administrative 

Procedure Act, and Federal Register 

requirements. We also continue to meet 

our technical decision-making 

responsibilities to identify and correct 

unsafe conditions on U.S.-certificated 

products. 

This AD references the MCAI and 

related service information that we 

considered in forming the engineering 

basis to correct the unsafe condition. 

The AD contains text copied from the 

MCAI and for this reason might not 

follow our plain language principles. 

Discussion 

The European Aviation Safety Agency 

(EASA), which is the Technical Agent 

for the Member States of the European 

Community, has issued AD 2007–0044, 

dated February 27, 2007 (referred to 

after this as ‘‘the MCAI’’), to correct an 

unsafe condition for the specified 

products. The MCAI states: 

The deterioration of the splines on the 

HP/LP pump assembly drive shaft may 

eventually interrupt fuel supply and cause 

uncommanded in-flight engine shutdown. 

The result may be an emergency autorotation 

landing or, at worst, an accident. 

Two cases of in-flight shutdown resulting 

from splines deterioration have been reported 

for the ARRIUS 2B1 engine, which has the 

same HP/LP pump drive design as the 

ARRIEL 2. These cases prompted us to 

require the inspection at 500 hours and each 

time the HMU is removed/installed. 

This AD modifies the content of the 

previous DGAC France AD F–2005–188 

(EASA Approval Number 2005–6408) in 

adding a one time inspection within 30 

operating hours from effective date of this AD 

as well as HMU re-installation according to 

a maintenance task modified to avoid this 

kind of wrong assembly. This has been set up 

following one case of improper clipping of 

the coupling shaft onto the drive gear shaft, 

which resulted in an uncommanded in-flight 

engine shutdown (on a twin engine 

rotorcraft). This precaution measure has been 

taken only on engines powering single engine 

rotorcraft. 

You may obtain further information by 

examining the MCAI in the AD docket. 

This AD supersedes AD 2006–21–10, 

Amendment 39–14795 (71 FR 61634, 

October 19, 2006), which we issued in 

response to DGAC France AD F–2005–

188. 

Relevant Service Information 

Turbomeca has issued Mandatory 

Service Bulletin No. 292 73 2812, 

Update No. 4, dated January 2, 2007. 

The actions described in this service 

information are intended to correct the 

unsafe condition identified in the 

MCAI. 

FAA’s Determination and Requirements 

of This AD 

This product has been approved by 

the aviation authority of another 

country, and is approved for operation 

in the United States. Pursuant to our 

bilateral agreement with this State of 

Design Authority, they have notified us 

of the unsafe condition described in the 

MCAI and service information 

referenced above. We are issuing this 

AD because we evaluated all the 

information provided by the State of 

Design Authority and determined the 

unsafe condition exists and is likely to 

exist or develop on other products of the 

same type design. This AD requires the 

following: 

• Visually inspecting splines of the 

coupling shaft assembly and the HP 

pump drive gear shaft for wear, within 

30 hours-in-service from the effective 

date of this AD for engines that were 

previously inspected using Update 2 of 

MSB 292 73 2812; 

• For engines that were not 

previously inspected using Update 2 of 

MSB 292 73 2812, visual inspection 

within 50 hours-in-service after the 

effective date of this AD for hydraulic 

mechanical units (HMUs) that have 

accumulated 450 or more hours timesince-new (TSN) or time-since-overhaul 

(TSO) on the effective date of this AD; 

• For HMUs that have fewer than 450 

hours TSN or TSO on the effective date 

of this AD, visual inspection after 

accumulating 450 hours TSN or TSO, 

but before accumulating 500 hours TSN 

or TSO; 

• Repetitive inspections every time 

you remove or install the HMU. 

Differences Between the 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. 


pwalker on PROD1PC71 with RULES
Federal Register / Vol. 72, No. 91 / Friday, May 11, 2007 / Rules and Regulations 26713 

Any such differences are described in a 

separate paragraph of the AD. These 

requirements take precedence over the 

actions copied from the MCAI. 

FAA’s Determination of the Effective 

Date 

An unsafe condition exists that 

requires the immediate adoption of this 

AD. The FAA has found that the risk to 

the flying public justifies waiving notice 

and comment prior to adoption of this 

rule because the compliance time 

required to correct the unsafe condition 

does not allow opportunity for prior 

public comment. Therefore, we 

determined that notice and opportunity 

for public comment before issuing this 

AD are impracticable and that good 

cause exists for making this amendment 

effective in fewer than 30 days. 

Comments Invited 

This AD is a final rule that involves 

requirements affecting flight safety, and 

we did not precede it by notice and 

opportunity for public comment. We 

invite you to send any written relevant 

data, views, or arguments about this AD. 

Send your comments to an address 

listed under the ADDRESSES section. 

Include ‘‘Docket No. FAA–2005–23809; 

Directorate Identifier 2005–NE–52–AD’’

at the beginning of your comments. We 

specifically invite comments on the 

overall regulatory, economic, 

environmental, and energy aspects of 

this AD. We will consider all comments 

received by the closing date and may 

amend this AD because of those 

comments. 

We will post all comments we 

receive, without change, to http:// 

dms.dot.gov, including any personal 

information you provide. We will also 

post a report summarizing each 

substantive verbal contact we receive 

about this AD. 

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 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 regulatory 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 

removing Amendment 39–14795 (71 FR 

61634, October 19, 2006) and by adding 

the following new AD: 

2007–10–07 Turbomeca: Amendment 39–

15048.; Docket No. FAA–2005–23809; 

Directorate Identifier 2005–NE–52–AD. 

Effective Date 

(a) This airworthiness directive (AD) 

becomes effective May 29, 2007. 

Affected ADs 

(b) This AD supersedes AD 2006–21–10. 

Applicability 

(c) This AD applies to Turbomeca Arriel 

2B, 2B1, and 2B1A turboshaft engines. These 

engines are installed on, but not limited to, 

Eurocopter AS350B3 and EC130B4 

helicopters. 

Reason 

(d) European Aviation Safety Agency 

(EASA) AD No. 2007–0044, dated April 27, 

2007, states: 

The deterioration of the splines on the HP/ 

LP pump assembly drive shaft may 

eventually interrupt fuel supply and cause 

uncommanded in-flight engine shutdown. 

The result may be an emergency autorotation 

landing or, at worst, an accident. 

Two cases of in-flight shutdown resulting 

from splines deterioration have been reported 

for the ARRIUS 2B1 engine, which has the 

same HP/LP pump drive design as the 

ARRIEL 2. These cases prompted us to 

require the inspection at 500 hours and each 

time the HMU is removed/installed. 

This AD modifies the content of the 

previous DGAC France AD F–2005–188 

(EASA Approval Number 2005–6408) in 

adding a one time inspection within 30 

operating hours from effective date of this AD 

as well as HMU re-installation according to 

a maintenance task modified to avoid this 

kind of wrong assembly. This has been set up 

following a one case of improper clipping of 

the coupling shaft onto the drive gear shaft, 

which resulted in an uncommanded in-flight 

engine shutdown (on a twin engine 

rotorcraft). This precaution measure has been 

taken only on engines powering single engine 

rotorcraft. 

Actions and Compliance 

(e) Unless already done, do the following 

actions. 

(f) Perform an initial visual inspection of 

the splines of the coupling assembly and the 

high pressure (HP) pump drive gear shaft for 

wear. Use 2.A. through 2.C.(2) of the 

Instructions to be Incorporated of Turbomeca 

Mandatory Service Bulletin (MSB) No. 292 

73 2812, Update No. 4, dated January 2, 2007, 

as follows: 

(1) Inspect within 30 hours-in-service from 

the effective date of this AD for engines that 

were previously inspected using Update 2 of 

MSB 292 73 2812. 

(2) For engines that were not previously 

inspected using Update 2 of MSB 292 73 

2812, inspect as follows: 

(i) Inspect within 50 hours-in-service after 

the effective date of this AD for hydraulic 

mechanical units (HMUs) that have 

accumulated 450 or more hours time-sincenew (TSN) or time-since-overhaul (TSO) on 

the effective date of this AD. Replace the 

HMU if worn beyond limits. 

(ii) Inspect after accumulating 450 hours 

TSN or TSO, but before accumulating 500 

hours TSN or TSO for HMUs that have fewer 

than 450 hours TSN or TSO on the effective 

date of this AD. Replace the HMU if worn 

beyond limits. 

Repetitive Visual Inspections 

(g) Thereafter, perform a visual inspection 

of the splines of the coupling shaft assembly 

and the HP pump drive gear shaft for wear 

every time you remove the HMU. Use 2.A. 

through 2.C.(2) of the Instructions to be 

Incorporated of Turbomeca MSB No. 292 73 

2812, Update No. 4, dated January 2, 2007. 

Replace the HMU and coupling shaft 

assembly if worn beyond limits. 


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26714 Federal Register / Vol. 72, No. 91 / Friday, May 11, 2007 / Rules and Regulations 

FAA AD Differences 

(h) None. 

Other FAA AD Provisions 

(i) The following provisions also apply to 

this AD: 

(1) Alternative Methods of Compliance 

(AMOCs): The Manager, Engine Certification 

Office, FAA, has the authority to approve 

AMOCs for this AD, if requested using the 

procedures found in 14 CFR 39.19. 

(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, under the 

provisions of the Paperwork Reduction Act, 

the Office of Management and Budget (OMB) 

has approved the information collection 

requirements and has assigned OMB Control 

Number 2120–0056. 

Related Information 

(j) Refer to European Aviation Safety 

Agency AD 2007–0044, dated February 27, 

2007, for related information. 

(k) Contact Christopher Spinney, 

Aerospace Engineer, Engine Certification 

Office, FAA, Engine and Propeller 

Directorate, 12 New England Executive Park, 

Burlington, MA 01803; e-mail: 

Christopher.spinney@faa.gov; telephone 

(781) 238–7175; fax (781) 238–7199, for more 

information about this AD. 

Material Incorporated by Reference 

(l) You must use Turbomeca Mandatory 

Service Bulletin No. 292 73 2812, Update No. 

4, dated January 2, 2007, 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 Turbomeca, 40220 Tarnos—

France; Tel (33) 05 59 74 40 00; Telex 570 

042; Fax (33) 05 59 74 45 15. 

(3) You may review copies at the FAA, 

New England Region, Office of the Regional 

Counsel, 12 New England Executive Park, 

Burlington, MA; 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 Burlington, Massachusetts, on 

May 4, 2007. 

Peter A. White, 

Acting Manager, Engine and Propeller 

Directorate, Aircraft Certification Service. 

[FR Doc. E7–8991 Filed 5–10–07; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2007–28009; Directorate 

Identifier 2007–NE–16–AD; Amendment 39–

15047; AD 2007–10–06] 

RIN 2120–AA64 

Airworthiness Directives; Turbomeca 

Arriel 2B1 Turboshaft Engines 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Final rule; request for 

comments. 

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: 

Two cases of flameout have been reported 

on Arriel 2B1 engines: One when lowering 

collective pitch on ground at landing and one 

when switching from Flight Position to idle 

Position on ground. 

Both flameout events are explained as 

follows: 

In case of stepper motor loss of steps to a 

value below the ‘‘level 1 failure’’ detection 

threshold, the fuel flow of the anti-flameout 

limit can be reduced. 

The reduction can be sufficient to cause an 

engine flameout when decreasing rapidly the 

demand for power (it can therefore also 

happen in-flight). 

This condition may lead to an 

uncommanded in-flight shutdown. On a 

single-engine helicopter, the result may be an 

emergency autorotation landing or, at worst, 

an accident. 

To prevent this, software version 5.02 (TU 

144C) increases the anti-flameout limit in the 

event of small stepper motor loss of steps 

(below the ‘‘level 1 failure’’ detection 

threshold). 

This AD requires actions that are 

intended to address the unsafe 

condition described in the MCAI. 

DATES: This AD becomes effective May 

29, 2007. 

The Director of the Federal Register 

approved the incorporation by reference 

of Turbomeca Mandatory Service 

Bulletin (MSB) No. 292 73 2144, dated 

January 5, 2007, listed in the AD as of 

May 29, 2007. 

We must receive comments on this 

AD by June 11, 2007. 

ADDRESSES: You may send comments by 

any of the following methods: 

• DOT Docket Web Site: Go to 

http://dms.dot.gov and follow the 

instructions for sending your comments 

electronically. 

• Fax: (202) 493–2251. 

• Mail: Docket Management Facility, 

U.S. Department of Transportation, 400 

Seventh Street, SW., Nassif Building, 

Room PL–401, Washington, DC 20590–

0001. 

• Hand Delivery: Room PL–401 on 

the plaza level of the Nassif Building, 

400 Seventh Street, SW., Washington, 

DC, between 9 a.m. and 5 p.m., Monday 

through Friday, except Federal holidays. 

• Federal eRulemaking Portal: http:// 

www.regulations.gov. Follow the 

instructions for submitting comments. 

Examining the AD Docket 

You may examine the AD docket on 

the Internet at http://dms.dot.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 this 

AD, the regulatory evaluation, any 

comments received, and other 

information. The street address for the 

Docket Office (telephone (800) 647–

5227) is in the ADDRESSES section. 

Comments will be available in the AD 

docket shortly after receipt. 

FOR FURTHER INFORMATION CONTACT: 

Christopher Spinney, Aerospace 

Engineer, Engine Certification Office, 

FAA, Engine and Propeller Directorate, 

12 New England Executive Park, 

Burlington, MA 01803; e-mail: 

Christopher.spinney@faa.gov; telephone 

(781) 238–7175; fax (781) 238–7199. 

SUPPLEMENTARY INFORMATION: 

Streamlined Issuance of AD 

The FAA is implementing a new 

process for streamlining the issuance of 

ADs related to MCAI. This streamlined 

process will allow us to adopt MCAI 

safety requirements in a more efficient 

manner and will reduce safety risks to 

the public. This process continues to 

follow all FAA AD issuance processes to 

meet legal, economic, Administrative 

Procedure Act, and Federal Register 

requirements. We also continue to meet 

our technical decision-making 

responsibilities to identify and correct 

unsafe conditions on U.S.-certificated 

products. 

This AD references the MCAI and 

related service information that we 

considered in forming the engineering 

basis to correct the unsafe condition. 

The AD contains text copied from the 

MCAI and for this reason might not 

follow our plain language principles. 

Discussion 

The European Aviation Safety Agency 

(EASA), which is the Technical Agent 

for the Member States of the European 


pwalker on PROD1PC71 with RULES