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–


sroberts on PROD1PC70 with PROPOSALS
Federal Register / Vol. 73, No. 159 / Friday, August 15, 2008 / Rules and Regulations 47819 

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 resulted 

from 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). 

REVISED AFM TEMPORARY AMENDMENTS

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. 


sroberts on PROD1PC70 with PROPOSALS
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. 


sroberts on PROD1PC70 with PROPOSALS
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TABLE 1—AFM TEMPORARY AMENDMENTS

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. 

TABLE 2—AFM TEMPORARY AMENDMENTS

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.) 

TABLE 3—ALL MATERIAL INCORPORATED BY REFERENCE

Bombardier temporary amendment— Issue— Dated—

To Bombardier Dash 8 

Q400 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. 

TABLE 4—NEW MATERIAL INCORPORATED BY REFERENCE

Bombardier temporary amendment— Issue— Dated—

To Bombardier Dash 8 

Q400 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. 


sroberts on PROD1PC70 with PROPOSALS
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TABLE 4—NEW MATERIAL INCORPORATED BY REFERENCE

Bombardier temporary amendment— Issue— Dated—

To Bombardier Dash 8 

Q400 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. 

TABLE 5—PREVIOUSLY APPROVED MATERIAL INCORPORATED BY REFERENCE

Bombardier temporary amendment— Issue— Dated—

To Bombardier Dash 8 

Q400 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 


sroberts on PROD1PC70 with PROPOSALS