### 47818 Federal Register / Vol. 73, No. 159 / Friday, August 15, 2008 / Rules and Regulations Authority: 12 U.S.C. 4001

– 4010, 12 U.S.C. 5001
– 5018. ■ 2. The Fourth District routing symbol list in appendix A is revised to read as follows: Appendix A to Part 229—Routing Number Guide to Next-Day Availability Checks and Local Checks * * * * * Fourth Federal Reserve District [Federal Reserve Bank of Cleveland] Head Office 0220 2220 0223 2223 0410 2410 0412 2412 0420 2420 0421 2421 0422 2422 0423 2423 0430 2430 0432 2432 0433 2433 0434 2434 0440 2440 0441 2441 0442 2442 0515 2515 0519 2519 0720 2720 0724 2724 0740 2740 0749 2749 0813 2813 0830 2830 0839 2839 0863 2863 * * * * *

By order of the Board of Governors of the Federal Reserve System, acting through the Secretary of the Board under delegated authority, August 11, 2008. Robert deV. Frierson, Deputy Secretary of the Board. [FR Doc. E8

– 18850 Filed 8

– 14
– 08; 8:45 am] **BILLING CODE 6210 –**  **01 –**  **P DEPARTMENT OF TRANSPORTATION**  **Federal Aviation Administration 14 CFR Part 26**  **[Docket No. FAA –**  **2004 –**  **18379; Amendment No. 26**  **– 0]**  **RIN 2120 –** **AI31 Enhanced Airworthiness Program for**  **Airplane Systems/Fuel Tank Safety (EAPAS/FTS); Technical Correction**  **AGENCY :**  Federal Aviation Administration (FAA), DOT. **ACTION :**  Final rule; technical correction. **SUMMARY :**  This final rule corrects a subpart heading in the Code of Federal Regulations. The heading was inadvertently misstated when the FAA published the rule in November 2007. **EFFECTIVE DATE :**  This final rule is effective August 15, 2008. **FOR FURTHER INFORMATION CONTACT :**  Annette K. Kovite, ANM

– 113, Standardization Branch, Federal Aviation Administration, 1601 Lind Avenue, SW., Renton, WA 98057, telephone: 425

– 227
– 1262, facsimile: 425
– 227
– 1320, e-mail: Annette.Kovite@faa.gov. **SUPPLEMENTARY INFORMATION :**  Background

On November 8, 2007, the FAA published a final rule to establish part 26 in the Code of Federal Regulations (72 FR 63364). The heading for subpart B of that part contained the phrase ‘‘ aging systems ’’ instead of the intended ‘‘ airplane systems. ’’ This final rule corrects that error. Justification for Immediate Adoption

Because this action corrects merely a typographical error, the FAA finds that notice and public comment under 5 U.S.C. 553(b) is unnecessary. For the same reason, the FAA finds that good cause exists under 5 U.S.C. 553(d) for making this rule effective upon publication. List of Subjects in 14 CFR Part 26

Aircraft, Aviation safety, Continued airworthiness. ■ In consideration of the foregoing, the Federal Aviation Administration amends Chapter I of Title 14, Code of Federal Regulations part 26 as follows: **PART 26 —**  **CONTINUED AIRWORTHINESS AND SAFETY**  **IMPROVEMENTS FOR TRANSPORT CATEGORY AIRPLANES**  ■ 1. The authority citation for part 26 continues to read as follows:

Authority: 49 U.S.C. 106(g), 40113, 44701, 44702 and 44704. **Subpart B —**  **Enhanced Airworthiness Program for Airplane Systems**  ■ 2. The heading for subpart B is revised to read as set forth above.

Issued in Washington, DC, on August 11, 2008. Pamela Hamilton-Powell, Director, Office of Rulemaking, Aviation Safety. [FR Doc. E8

– 18859 Filed 8

– 14
– 08; 8:45 am] **BILLING CODE 4910 –**  **13 –**  **P DEPARTMENT OF TRANSPORTATION**  **Federal Aviation Administration 14 CFR Part 39**  **[Docket No. FAA –**  **2008 –**  **0864; Directorate Identifier 2008**  **– NM**  **– 120**  **– AD; Amendment**  **39 –**  **15644; AD 2008 –**  **17 –**  **06] RIN 2120**  **– AA64**  **Airworthiness Directives; Bombardier Model DHC**  **– 8**  **– 400 Series Airplanes**  **AGENCY :**  Federal Aviation Administration (FAA), Department of Transportation (DOT). **ACTION :**  Final rule; request for comments. **SUMMARY :**  The FAA is superseding an existing airworthiness directive (AD) that applies to certain Bombardier Model DHC

– 8
– 400 series airplanes. The existing AD currently requires revising the Limitations section of the airplane flight manual (AFM) to include procedures for pulling the ‘‘ HYD PWR XFER ’’ circuit breaker in the event of the loss of all hydraulic fluid in the No. 1 or No. 2 hydraulic system. This AD requires a revision to the AFM to include additional procedures for ensuring that the ‘‘ PTU CNTRL ’’ switch is Normal, the ‘‘ PTU CNTRL ON ’’ advisory light is out, and the ‘‘ HYD PWR XFER ’’ circuit breaker is pulled in the event of the illumination of the ‘‘ #2 HYD ISO VALVE ’’ caution light. This AD resulted from low No. 2 hydraulic pressure in-flight, which caused the power transfer unit to overspeed, and the fluid flow within the No. 1 hydraulic system to increase. We are issuing this AD to prevent possible loss of both the No. 1 and No. 2 hydraulic systems, resulting in the potential loss of several functions essential for safe flight and landing of the airplane. **DATES :**  This AD becomes effective September 2, 2008.

The Director of the Federal Register approved the incorporation by reference of certain publications listed in the AD as of September 2, 2008.

On July 10, 2007 (72 FR 30968, June 5, 2007), the Director of the Federal Register approved the incorporation by reference of certain other publications.

We must receive any comments on this AD by September 15, 2008. **ADDRESSES :**  You may send comments by any of the following methods:

• 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

–

### 47819 Federal Register / Vol. 73, No. 159 / Friday, August 15, 2008 / Rules and Regulations 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.

For service information identified in this AD, contact Bombardier, Inc., Bombardier Regional Aircraft Division, 123 Garratt Boulevard, Downsview, Ontario M3K 1Y5, Canada. 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 this AD, 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. **FOR FURTHER INFORMATION CONTACT :**  Fabio Buttitta, Aerospace Engineer, Systems and Flight Test Branch, ANE

– 172, FAA, New York Aircraft Certification Office, 1600 Stewart Avenue, Suite 410, Westbury, New York 11590; telephone (516) 228

– 7303; fax (516) 794

– 5531. **SUPPLEMENTARY INFORMATION :**  Discussion

On May 25, 2007, the FAA issued AD 2007
– 12
– 03, amendment 39

– 15081 (72 FR 30968, June 5, 2007). That AD applies to certain Bombardier Model DHC

– 8
– 400 series airplanes. That AD requires revising the airplane flight manual (AFM) to include procedures for pulling the ‘‘ HYD PWR XFER ’’ circuit breaker in the event of the loss of all hydraulic fluid in the No. 1 or No. 2 hydraulic system. That AD resultedfrom low No. 2 hydraulic pressure inflight, which caused the power transfer unit (PTU) to overspeed, and the fluid flow within the No. 1 hydraulic system to increase. The actions specified in that AD are intended to prevent possible loss of both the No. 1 and No. 2 hydraulic systems, resulting in the potential loss of several functions essential for safe flight and landing of the airplane. Actions Since AD Was Issued

Since we issued AD 2007

– 12
– 03, Transport Canada Civil Aviation (TCCA), which is the airworthiness authority for Canada, advises that it has received an additional report of loss of the No. 2 hydraulic system on a Model DHC

– 8
– 402 airplane, causing the PTU to overspeed, increasing the fluid flow within the No. 1 hydraulic system. Investigation revealed that, after the caution light for the No. 2 hydraulic system had illuminated, the PTU was left in the ‘‘ ON ’’ position. The flightcrew had followed AFM procedures, as specified in the AFM revision required by AD 2007

– 12
– 03, and did not pull the circuit breaker because the hydraulic fluid from the No. 2 system was not completely depleted.

Therefore, we find that the AFM revision required by AD 2007

– 12
– 03 does not adequately prevent possible loss of both the No. 1 and No. 2 hydraulic systems, resulting in the potential loss of several functions essential for safe flight and landing of the airplane. The hydraulic power transfer system on the Model DHC

– 8
– 400 and DHC

– 8
– 401 airplanes are similar to those on the affected Model DHC

– 8
– 402 airplanes. Therefore, all of the models are subject to the same unsafe condition. Relevant Service Information

Bombardier has issued the temporary amendments specified in the following table (AD 2007

– 12
– 03 refers to Issue 1 of Bombardier Temporary Amendments 13, all dated July 14, 2005, as appropriate sources of service information for accomplishing the required AFM revision). 

### R EVISED 

### AFM T EMPORARY 

### A MENDMENTS
For model— Use Bombardier temporary amendment— Issue— Dated— To Bombardier Dash 8 Q400 airplane flight

manual— DHC–8–400 airplanes ................................ 13 3 June 9, 2008 .............................................. PSM 1–84–1A. DHC–8–401 airplanes ................................ 13 3 June 9, 2008 .............................................. PSM 1–84–1A. DHC–8–402 airplanes ................................ 13 3 June 9, 2008 .............................................. PSM 1–84–1A.

The procedures specified in Issue 3 for addressing the loss of all hydraulic fluid in the No. 1 and No. 2 hydraulic systems are identical to those specified in Issue 1. Issue 3 has been revised to include procedures for ensuring that the PTU is disabled when the fluid level in the No. 2 hydraulic system falls to a value where the PTU becomes a hazard to the No. 1 hydraulic system. This is achieved by ensuring that the ‘‘ PTU CNTRL ’’ switch is Normal, the ‘‘ PTU CNTRL ON ’’ advisory light is out, and the ‘‘ HYD PWR XFER ’’ circuit breaker is pulled in the event of the illumination of the ‘‘ #2 HYD ISO VALVE ’’ caution light. TCCA previously mandated Issue 1 ( ‘‘ or later ’’ ) of the service information and issued Canadian airworthiness directive CF

– 2006
– 08, dated April 26, 2006 (referred to after this as ‘‘ the MCAI ’’ ), to ensure the continued airworthiness of these airplanes in Canada. 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 the State of Design Authority, we have been notified of the unsafe condition described in the MCAI and service information referenced above. We are proposing this AD because we evaluated all pertinent information and determined an unsafe condition exists and is likely to exist or develop on other products of the same type design.

Therefore, we are issuing this AD to supersede AD 2007

– 12
– 03. This new AD retains the requirements of the existing AD. This AD also requires a revision to the Normal and Abnormal Procedures section of the AFM to include procedures for ensuring that the ‘‘ PTU CNTRL ’’ switch is Normal, the ‘‘ PTU CNTRL ON ’’ advisory light is out, and the ‘‘ HYD PWR XFER ’’ circuit breaker is pulled in the event of the illumination of the ‘‘ #2 HYD ISO VALVE ’’ caution light.

In addition, AD 2007

– 12
– 03 specifies to revise the Limitations section of the AFM; however, this AD specifies to revise the Normal and Abnormal Procedures section.

### 47820 Federal Register / Vol. 73, No. 159 / Friday, August 15, 2008 / Rules and Regulations Interim Action

We consider this AD interim action. The manufacturer is currently developing a modification that will address the unsafe condition identified in this AD. Once this modification is developed, approved, and available, we might consider additional rulemaking. FAA ’ s Justification and Determination of the Effective Date

Fluid loss in the No. 2 hydraulic system causing a PTU overspeed and increased fluid flow in the No. 1 hydraulic system could cause the loss of several functions essential for safe flight and landing of the airplane. Because of our requirement to promote safe flight of civil aircraft, and thus the critical need to ensure the proper functioning of the No.1 and No. 2 hydraulic systems and the short compliance time involved with this action, this AD must be issued immediately.

Because an unsafe condition exists that requires the immediate adoption of this AD, we find that notice and opportunity for prior public comment hereon are impracticable and that good cause exists for making this amendment effective in less than 30 days. Comments Invited

This AD is a final rule that involves requirements affecting flight safety, and we did not provide you with notice and an opportunity to provide your comments before it becomes effective. However, we invite you to send any written data, views, or arguments about this AD. Send your comments to an address listed under the **ADDRESSES** section. Include ‘‘ Docket No. FAA

– 2008
– 0864; Directorate Identifier 2008

– NM

– 120
–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:// www.regulations.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 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 a regulatory evaluation of the estimated costs to comply with this AD and placed it in the AD docket. See the **ADDRESSES** section for a location to examine the regulatory evaluation. 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 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. The Federal Aviation Administration (FAA) amends § 39.13 by removing amendment 39

– 15081 (72 FR 30968, June 5, 2007) and adding the following new AD: 2008 – 17 – 06 Bombardier, Inc. (Formerly de Havilland, Inc.): Docket No. FAA

– 2008
– 0864; Directorate Identifier 2008

– NM

– 120
–AD; Amendment 39

– 15644. Effective Date

(a) This AD becomes effective September 2, 2008. Affected ADs

(b) This AD supersedes AD 2007

– 12
– 03. Applicability

(c) This AD applies to Bombardier Model DHC

– 8
– 400, DHC

– 8
– 401, and DHC

– 8
– 402 airplanes, certificated in any category; serial numbers 4001 and 4003 and subsequent. Unsafe Condition

(d) This AD results from low No. 2 hydraulic pressure in-flight, which caused the power transfer unit to overspeed, and the fluid flow within the No. 1 hydraulic system to increase. We are issuing this AD to prevent possible loss of both the No. 1 and No. 2 hydraulic systems, resulting in the potential loss of several functions essential for safe flight and landing of the airplane. Compliance

(e) You are responsible for having the actions required by this AD performed within the compliance times specified, unless the actions have already been done. Requirements of AD 2007
– 12 – 03 Airplane Flight Manual (AFM) Revision

(f) Within 14 days after July 10, 2007 (the effective date of AD 2007

– 12
– 03), revise the Limitations section of the applicable AFM to include the information in the applicable Bombardier temporary amendment specified in Table 1 of this AD, as specified in the temporary amendment. These temporary amendments introduce procedures for pulling the ‘‘ HYD PWR XFER ’’ circuit breaker in the event of the loss of all hydraulic fluid in the No. 1 or No. 2 hydraulic system. Operate the airplane according to the limitations and procedures in the applicable temporary amendment.


### 47821 Federal Register / Vol. 73, No. 159 / Friday, August 15, 2008 / Rules and Regulations T ABLE 

### 1
—AFM T EMPORARY 

### A MENDMENTS
For model
— Use Bombardier temporary amendment
— Issue
—Dated
— To Bombardier Dash 8 Q400 airplane flight manual
— DHC
– 8
– 400 airplanes ................................ 13 1 July 14, 2005 ............................................. PSM 1
– 84
– 1A. DHC
– 8
– 401 airplanes ................................ 13 1 July 14, 2005 ............................................. PSM 1
– 84
– 1A. DHC
– 8
– 402 airplanes ................................ 13 1 July 14, 2005 ............................................. PSM 1
– 84
– 1A.

Note 1: This may be done by inserting a copy of the applicable temporary amendment into the applicable AFM. When the applicable temporary amendment has been included in general revisions of the AFM, the general revisions may be inserted into the AFM, provided the relevant information in the general revisions is identical to that in the temporary amendment. New Requirements of This AD AFM Revision

(g) Within 14 days after the effective date of this AD, revise the applicable AFM Normal and Abnormal Procedures section to include the information in the applicable Bombardier temporary amendment specified in Table 2 of this AD, as specified in the temporary amendment. These temporary amendments introduce additional procedures for ensuring that the ‘‘ PTU CNTRL ’’ switch is Normal, the ‘‘ PTU CNTRL ON ’’ advisory light is out, and the ‘‘ HYD PWR XFER ’’ circuit breaker is pulled in the event of the illumination of the ‘‘ #2 HYD ISO VALVE ’’ caution light. After accomplishing the AFM revision, the AFM limitation required by paragraph (f) in this AD may be removed from the AFM. 

### T ABLE 

### 2
—AFM T EMPORARY 

### A MENDMENTS
For model
— Use Bombardier temporary amendment
— Issue
—Dated
— To Bombardier Dash 8 Q400 airplane flight manual
— DHC
– 8
– 400 airplanes ................................ 13 3 June 9, 2008 .............................................. PSM 1
– 84
– 1A. DHC
– 8
– 401 airplanes ................................ 13 3 June 9, 2008 .............................................. PSM 1
– 84
– 1A. DHC
– 8
– 402 airplanes ................................ 13 3 June 9, 2008 .............................................. PSM 1
– 84
– 1A. Alternative Methods of Compliance (AMOCs)

(h) The Manager, New York Aircraft Certification Office, ANE

– 170, 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: Fabio Buttitta, Aerospace Engineer, Systems and Flight Test Branch, ANE

– 172, FAA, New York Aircraft Certification Office, 1600 Stewart Avenue, Suite 410, Westbury, New York 11590; telephone (516) 228

– 7303; fax (516) 794

– 5531. 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. Related Information

(i) Canadian airworthiness directive CF

– 2006
– 08, dated April 26, 2006, also addresses the subject of this AD. Material Incorporated by Reference (j) You must use the applicable temporary amendment identified in Table 3 of this AD to perform the actions that are required by this AD, unless the AD specifies otherwise. (Only the last pages of the temporary amendments identified in Table 4 of this AD contain the issue date, no other pages of those documents are dated.) 

### T ABLE 

### 3
—A LL 

### M ATERIAL 

### I NCORPORATED BY 

### R EFERENCE Bombardier temporary amendment
—Issue
—Dated
— To Bombardier Dash 8Q400 airplane flight manual
— 13 ..................................................................... 1 July 14, 2005 ......................................... .......... Model 400 PSM 1
– 84
– 1A. 13 ..................................................................... 1 July 14, 2005 ......................................... .......... Model 401 PSM 1
– 84
– 1A. 13 ..................................................................... 1 July 14, 2005 ......................................... .......... Model 402 PSM 1
– 84
– 1A. 13 ..................................................................... 3 June 9, 2008 .......................................... .......... Model 400 PSM 1
– 84
– 1A. 13 ..................................................................... 3 June 9, 2008 .......................................... .......... Model 401 PSM 1
– 84
– 1A. 13 ..................................................................... 3 June 9, 2008 .......................................... .......... Model 402 PSM 1
– 84
– 1A.

(1) The Director of the Federal Register approved the incorporation by reference of the temporary amendments identified in Table 4 of this AD in accordance with 5 U.S.C. 552(a) and 1 CFR part 51. 

### T ABLE 

### 4
— N EW 

### M ATERIAL 

### I NCORPORATED BY 

### R EFERENCE Bombardier temporary amendment
—Issue
—Dated
— To Bombardier Dash 8Q400 airplane flight manual
— 13 ..................................................................... 3 June 9, 2008 .......................................... .......... Model 400 PSM 1
– 84
– 1A. 13 ..................................................................... 3 June 9, 2008 .......................................... .......... Model 401 PSM 1
– 84
– 1A.


### 47822 Federal Register / Vol. 73, No. 159 / Friday, August 15, 2008 / Rules and Regulations T ABLE 

### 4
— N EW 

### M ATERIAL 

### I NCORPORATED BY 

### R EFERENCE Bombardier temporary amendment
—Issue
—Dated
— To Bombardier Dash 8Q400 airplane flight manual
— 13 ..................................................................... 3 June 9, 2008 .......................................... .......... Model 402 PSM 1
– 84
– 1A.

(2) On July 10, 2007 (72 FR 30968, June 5, 2007), the Director of the Federal Register approved the incorporation by reference of the temporary amendments identified in Table 5 of this AD. 

### T ABLE 

### 5
— P REVIOUSLY 

### A PPROVED 

### M ATERIAL 

### I NCORPORATED BY 

### R EFERENCE Bombardier temporary amendment
—Issue
—Dated
— To Bombardier Dash 8Q400 airplane flight manual
— 13 ..................................................................... 1 July 14, 2005 ......................................... .......... Model 400 PSM 1
– 84
– 1A. 13 ..................................................................... 1 July 14, 2005 ......................................... .......... Model 401 PSM 1
– 84
– 1A. 13 ..................................................................... 1 July 14, 2005 ......................................... .......... Model 402 PSM 1
– 84
– 1A.

(3) Contact Bombardier, Inc., Bombardier Regional Aircraft Division, 123 Garratt Boulevard, Downsview, Ontario M3K 1Y5, Canada, for a copy of this service information. You may review copies at the FAA, Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton, Washington; 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/ibrlocations.html.

Issued in Renton, Washington, on July 31, 2008. Ali Bahrami, Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. E8

– 18683 Filed 8

– 14
– 08; 8:45 am] **BILLING CODE 4910 –**  **13 –**  **P DEPARTMENT OF TRANSPORTATION**  **Federal Aviation Administration 14 CFR Part 39**  **[Docket No. FAA –**  **2008 –**  **0844; Directorate Identifier 2007**  **– SW** **– 23**  **– AD; Amendment 39**  **– 15635; AD 2008**  **– 16**  **– 17]**  **RIN 2120 –**  **AA64 Airworthiness Directives; PZL Swidnik**  **S. A. Model W –**  **3A Helicopters 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 PZL Swidnik S. A. (PZL) Model W

– 3A helicopters. This AD results from mandatory continuing airworthiness information (MCAI) issued by the European Aviation Safety Agency (EASA), which is the Technical Agent for the Member States of the European Community. The MCAI states: ‘‘ In PZL W

– 3A helicopter S/N 37.07.05, and previously also in the PZL W

– 3AS model helicopters, leakage was found in the pipe 37.59.006.00.00 installed in the pressure line of hydraulic system 2, in the part between the hydraulic block and the ground hydraulic unit panel. The hydraulic system in the part between hydraulic blocks and the ground hydraulic unit panel is used only during periodical inspections, for the performance of which it is required to use the hydraulic power unit. This condition, if not corrected, could result in a fire hazard. ’’ The actions specified in this AD are intended to prevent this unsafe condition. **DATES :**  This AD becomes effective on September 2, 2008.

The Director of the Federal Register approved the incorporation by reference of ‘‘ PZL-S  ́ widnik ’’ S.A. Mandatory Bulletin No. BO

– 37
– 07
– 192, dated January 12, 2007, and ‘‘ PZL-S  ́ widnik ’’ Technical Bulletin No. BT

– 37
– 07
– 196, dated April 24, 2007, as of September 2, 2008.

We must receive comments on this AD by October 14, 2008. **ADDRESSES :**  You may send comments by any of the following methods:

• Federal eRulemaking Portal: Go to http://www.regulations.gov. Follow the instructions for submitting your comments electronically.

• 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 WSK ‘‘ PZLS  ́ widnik ’’ S.A., Al. Lotniko  ́ w Polskich 1, 21
– 045 S  ́ widnik, Poland, telephone (+48 81) 468 09 01, 751 20 71, or fax (+48 81) 468 09 19, 751 21 73, e-mail: hem@pzl.swidnik.pl.

Examining the Docket: You may examine the AD docket 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 AD docket contains this AD, any comments received, and other information. The street address for the Docket Operations office (telephone (800) 647

– 5527) is stated in the **ADDRESSES** section of this AD. Comments will be available in the AD docket shortly after receipt. **FOR FURTHER INFORMATION CONTACT :**  Uday Garadi, Aerospace Engineer, Regulations and Policy Group, Rotorcraft Directorate, FAA, Fort Worth, Texas 76193

– 0110, telephone (817) 222
– 5123, fax (817) 222

– 5961. **SUPPLEMENTARY INFORMATION :**  The EASA, which is the Technical Agent for the Member States of the European Community, has issued EASA Emergency AD No. 2007

– 0072R1, dated July 6, 2007 (referred to after this as ‘‘ the MCAI ’’ ), to correct an unsafe condition for the PZL Model W

– 3A helicopters. The MCAI states: ‘‘ In PZL W

– 3A helicopter S/N 37.07.05, and previously also in the PZL W

– 3AS model helicopters, leakage was found in the