39798 Federal Register / Vol. 75, No. 133 / Tuesday, July 13, 2010 / Rules and Regulations 

this service information under 5 U.S.C. 

552(a) and 1 CFR part 51. 

(2) For service information identified in 

this AD, contact Aircraft Industries, a.s., Na 

Za ́honech 1177, 686 04 Kunovice, Czech 

Republic; phone: +420 572 817 660; fax: +420 

572 816 112; Internet: http://www.let.cz/; email: ots@let.cz. 

(3) You may review copies of the service 

information incorporated by reference for 

this AD at the FAA, Central Region, Office of 

the Regional Counsel, 901 Locust, Kansas 

City, Missouri 64106. For information on the 

availability of this material at the Central 

Region, call (816) 329–3768. 

(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 June 

28, 2010. 

James E. Jackson, 

Acting Manager, Small Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 2010–16382 Filed 7–12–10; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2010–0382; Directorate 

Identifier 2009–NM–211–AD; Amendment 

39–16361; AD 2010–14–16] 

RIN 2120–AA64 

Airworthiness Directives; Bombardier, 

Inc. Model DHC–8–400, –401, and –402 

Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Final rule. 

SUMMARY: We are superseding an 

existing airworthiness directive (AD) for 

the products listed above. This AD 

results from mandatory continuing 

airworthiness information (MCAI) 

originated 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: 

Several cases have been reported where a 

loss of fluid in the No.2 hydraulic system has 

caused the power transfer unit (PTU) to 

overspeed, resulting in pressure fluctuations 

and increased fluid flow within the No. 1 

hydraulic system. In one case, the hydraulic 

system control logic did not shut down the 

PTU and the overspeed condition persisted, 

resulting in the illumination of the No.1 HYD 

FLUID HOT caution light. 

* * * * * 

The unsafe condition is 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. We 

are issuing this AD to require actions to 

correct the unsafe condition on these 

products. 

DATES: This AD becomes effective 

August 17, 2010. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication listed in this AD 

as of August 17, 2010. 

The Director of the Federal Register 

approved the incorporation by reference 

of certain publications listed in this AD 

as of September 2, 2008 (73 FR 47818, 

August 15, 2008). 

The Director of the Federal Register 

approved the incorporation by reference 

of certain other publications listed in 

this AD as of July 10, 2007 (72 FR 

30968, June 5, 2007). 

ADDRESSES: You may examine the AD 

docket on the Internet at http:// 

www.regulations.gov or in person at the 

U.S. Department of Transportation, 

Docket Operations, M–30, West 

Building Ground Floor, Room W12–140, 

1200 New Jersey Avenue, SE., 

Washington, DC. 

FOR FURTHER INFORMATION CONTACT: 

Fabio Buttitta, Aerospace Engineer, 

Airframe and Mechanical Systems 

Branch, ANE–171, 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 

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 April 21, 2010 (75 FR 

20787), and proposed to supersede AD 

2008–17–06, Amendment 39–15644 (73 

FR 47818, August 15, 2008). That NPRM 

proposed to correct an unsafe condition 

for the specified products. The MCAI 

states: 

Since we issued AD 2008–17–06, a 

modification of the power transfer unit 

(PTU) control logic, including the 

provision of automatic PTU shutdown 

in the event of loss of fluid in the No. 

2 hydraulic system, has been developed. 

The modification addresses the 

identified unsafe condition. In addition, 

the applicability has been revised to 

remove airplanes having serial number 

4185 and subsequent, since an 

equivalent modification has been 

installed in production on these 

airplanes. Transport Canada Civil 

Aviation (TCCA), which is the aviation 

authority for Canada, has issued 

Canadian Airworthiness Directive CF– 

2006–08R1, dated August 31, 2009 

(referred to after this as ‘‘the MCAI’’), to 

correct an unsafe condition for the 

specified products. The MCAI states: 

Several cases have been reported where a 

loss of fluid in the No.2 hydraulic system has 

caused the power transfer unit (PTU) to 

overspeed, resulting in pressure fluctuations 

and increased fluid flow within the No. 1 

hydraulic system. In one case, the hydraulic 

system control logic did not shut down the 

PTU and the overspeed condition persisted, 

resulting in the illumination of the No. 1 

HYD FLUID HOT caution light. 

As an interim action to avoid possible loss 

of both the No. 1 and No. 2 hydraulic 

systems, the Airplane Flight Manual (AFM) 

has been revised to include pulling the HYD 

PWR XFER circuit breaker in the event of the 

loss of all hydraulic fluid in the No. 2 

hydraulic system. 

Insertion of the resultant Temporary 

Amendment (TA) No. 13 into the AFM was 

mandated in the original issue of this 

[Canadian] directive. This instruction * * * 

remains in effect until * * * this [revised] 

directive is accomplished. 

Revision 1 of this directive * * * 

mandates modification of the PTU control 

logic, including the provision of automatic 

PTU shutdown in the event of loss of fluid 

in the No. 2 hydraulic system. In addition, 

the applicability of the [Canadian] directive 

has been revised to remove aircraft Serial 

Number (SN) 4185 and subsequent, since an 

equivalent modification has been installed in 

production on these aircraft. 

The unsafe condition is 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. You 

may obtain further information by 

examining the MCAI in the AD docket. 

Comments 

We gave the public the opportunity to 

participate in developing this AD. We 

received no comments on the NPRM or 

on the determination of the cost to the 

public. 

Conclusion 

We reviewed the available data and 

determined that air safety and the 

public interest require adopting the AD 

as proposed. 

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 


jlentini on DSKJ8SOYB1PROD with RULES
Federal Register / Vol. 75, No. 133 / Tuesday, July 13, 2010 / Rules and Regulations 39799 

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 our FAA 

policies. Any such differences are 

highlighted in a NOTE within the AD. 

Costs of Compliance 

We estimate that this AD will affect 

about 42 products of U.S. registry. 

The actions that are required by AD 

2008–17–06 and retained in this AD 

take about 1 work-hour per product, at 

an average labor rate of $85 per work 

hour. Required parts cost about $0 per 

product. Based on these figures, the 

estimated cost of the currently required 

actions is $85 per product. 

We estimate that it will take about 165 

work-hours per product to comply with 

the new basic requirements of this AD. 

The average labor rate is $85 per workhour. Required parts will cost about 

$10,982 per product. Where the service 

information lists required parts costs 

that are covered under warranty, we 

have assumed that there will be no 

charge for these parts. As we do not 

control warranty coverage for affected 

parties, some parties may incur costs 

higher than estimated here. Based on 

these figures, we estimate the cost of 

this AD to the U.S. operators to be 

$1,050,294, or $25,007 per product. 

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. 

Examining the AD 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 the NPRM, the regulatory 

evaluation, any comments received, and 

other information. The street address for 

the Docket Operations 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 

removing Amendment 39–39–15644 (73 

FR 47818, August 15, 2008) and adding 

the following new AD: 

2010–14–16 Bombardier, Inc.: Amendment 

39–16361. Docket No. FAA–2010–0382; 

Directorate Identifier 2009–NM–211–AD. 

Effective Date 

(a) This airworthiness directive (AD) 

becomes effective August 17, 2010. 

Affected ADs 

(b) This AD supersedes AD 2008–17–06, 

Amendment 39–15644. 

Applicability 

(c) This AD applies to Bombardier, Inc. 

Model DHC–8–400, –401, and –402 

airplanes, certificated in any category; serial 

numbers 4001, 4003, 4004, 4006, and 4008 

through 4184 inclusive. 

Subject 

(d) Air Transport Association (ATA) of 

America Code 29: Hydraulic power. 

Reason 

(e) The mandatory continuing 

airworthiness information (MCAI) states: 

Several cases have been reported where a 

loss of fluid in the No.2 hydraulic system has 

caused the power transfer unit (PTU) to 

overspeed, resulting in pressure fluctuations 

and increased fluid flow within the No. 1 

hydraulic system. In one case, the hydraulic 

system control logic did not shut down the 

PTU and the overspeed condition persisted, 

resulting in the illumination of the No. 1 

HYD FLUID HOT caution light. 

As an interim action to avoid possible loss 

of both the No. 1 and No. 2 hydraulic 

systems, the Airplane Flight Manual (AFM) 

has been revised to include pulling the HYD 

PWR XFER circuit breaker in the event of the 

loss of all hydraulic fluid in the No. 2 

hydraulic system. 

Insertion of the resultant Temporary 

Amendment (TA) No. 13 into the AFM was 

mandated in the original issue of this 

[Canadian] directive. This instruction * * * 

remains in effect until * * * this [revised] 

directive is accomplished. 

Revision 1 of this directive * * * 

mandates modification of the PTU control 

logic, including the provision of automatic 

PTU shutdown in the event of loss of fluid 

in the No. 2 hydraulic system. In addition, 

the applicability of the [Canadian] directive 

has been revised to remove aircraft Serial 

Number (SN) 4185 and subsequent, since an 

equivalent modification has been installed in 

production on these aircraft. 

The unsafe condition is 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 

(f) You are responsible for having the 

actions required by this AD performed within 

the compliance times specified, unless the 

actions have already been done. 

RESTATEMENT OF REQUIREMENTS OF 

AD 2007–12–03 AIRPLANE FLIGHT 

MANUAL (AFM) REVISION 

(g) Within 14 days after July 10, 2007 (the 

effective date of AD 2007–12–03, 

Amendment 39–15081, which was 

superseded by AD 2008–17–06), 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 


jlentini on DSKJ8SOYB1PROD with RULES
39800 Federal Register / Vol. 75, No. 133 / Tuesday, July 13, 2010 / Rules and Regulations 

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. 

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. 

Restatement of Requirements of AD 2008– 

17–06: AFM Revision 

(h) Within 14 days after September 2, 2008 

(the effective date of AD 2008–17–06), 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 (g) 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. 

New Requirements of This AD: Actions 

(i) Within 6,000 flight hours after the 

effective date of this AD, modify the PTU 

control logic, in accordance with the 

Accomplishment Instructions of Bombardier 

Service Bulletin 84–29–22, Revision A, dated 

February 24, 2009. Doing this modification 

terminates the requirements of paragraphs (g) 

and (h) of this AD, and after the modification 

has been done, the AFM limitation required 

by paragraphs (g) and (h) of this AD may be 

removed from the AFM. 

(j) Modifying the PTU control logic is also 

acceptable for compliance with the 

requirements of paragraph (i) of this AD if 

done before the effective date of this AD, in 

accordance with Bombardier Service Bulletin 

84–29–22, dated December 5, 2008. 

FAA AD Differences 

Note 2: This AD differs from the MCAI 

and/or service information as follows: No 

differences. 

Other FAA AD Provisions 

(k) The following provisions also apply to 

this AD: 

(1) Alternative Methods of Compliance 

(AMOCs): The Manager, New York Aircraft 

Certification Office (ACO), 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: 

Program Manager, Continuing Operational 

Safety, FAA, New York ACO, 1600 Stewart 

Avenue, Suite 410, Westbury, New York 

11590; telephone 516–228–7300; fax 516– 

794–5531. Before using any approved AMOC 

on any airplane to which the AMOC applies, 

notify your principal maintenance inspector 

(PMI) or principal avionics inspector (PAI), 

as appropriate, or lacking a principal 

inspector, your local Flight Standards District 

Office. The AMOC approval letter must 

specifically reference this AD. 

(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 

(44 U.S.C. 3501 et seq.), the Office of 

Management and Budget (OMB) has 

approved the information collection 

requirements and has assigned OMB Control 

Number 2120–0056. 

Related Information 

(l) Refer to MCAI Canadian Airworthiness 

Directive CF–2006–08R1, dated August 31, 

2009; the Bombardier temporary 

amendments specified in Tables 1 and 2; and 

Bombardier Service Bulletin 84–29–22, 

Revision A, dated February 24, 2009; for 

related information. 

Material Incorporated by Reference 

(m) You must use Bombardier Service 

Bulletin 84–29–22, Revision A, dated 

February 24, 2009, and the applicable 

temporary amendment identified in Table 3 

of this AD; as applicable; to do the actions 

required by this AD, unless the AD specifies 

otherwise. 

TABLE 3—ALL TEMPORARY AMENDMENTS 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. 


jlentini on DSKJ8SOYB1PROD with RULES
Federal Register / Vol. 75, No. 133 / Tuesday, July 13, 2010 / Rules and Regulations 39801 

(1) The Director of the Federal Register 

approved the incorporation by reference of 

Bombardier Service Bulletin 84–29–22, 

Revision A, dated February 24, 2009, under 

5 U.S.C. 552(a) and 1 CFR part 51. 

(2) The Director of the Federal Register 

previously approved the incorporation by 

reference of the service information 

contained in Table 4 of this AD on September 

2, 2008 (73 FR 47818, August 15, 2008). 

TABLE 4—MATERIAL PREVIOUSLY INCORPORATED BY REFERENCE IN AD 2008–17–06 

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. 

13 ............................................................... 3 June 9, 2008 ............. Model 402 PSM 1–84–1A. 

(3) 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—MATERIAL PREVIOUSLY INCORPORATED BY REFERENCE IN AD 2007–12–03 

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. 

(4) For service information identified in 

this AD, contact Bombardier, Inc., 400 CoˆteVertu Road West, Dorval, Que ́bec H4S 1Y9, 

Canada; telephone 514–855–5000; fax 514– 

855–7401; e-mail 

thd.qseries@aero.bombardier.com; Internet 

http://www.bombardier.com. 

(5) You may review copies of the service 

information at the FAA, Transport Airplane 

Directorate, 1601 Lind Avenue, SW., Renton, 

Washington. For information on the 

availability of this material at the FAA, call 

425–227–1221. 

(6) 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 NARA, call 202–741–6030, or go 

to: http://www.archives.gov/federal_register/ 

code_of_federal_regulations/ 

ibr_locations.html. 

Issued in Renton, Washington, on June 25, 

2010. 

Ali Bahrami, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 2010–16434 Filed 7–12–10; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2007–29176; Directorate 

Identifier 2007–NE–38–AD; Amendment 39– 

16365; AD 2010–14–20] 

RIN 2120–AA64 

Airworthiness Directives; McCauley 

Propeller Systems Model 4HFR34C653/ 

L106FA Propellers 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule. 

SUMMARY: The FAA is adopting a new 

airworthiness directive (AD) for 

McCauley Propeller Systems model 

4HFR34C653/L106FA propellers. This 

AD requires a onetime fluorescent 

penetrant inspection (FPI) and eddy 

current inspection (ECI) of the propeller 

hub for cracks. This AD results from 

reports of 10 hubs found cracked during 

propeller overhaul. We are issuing this 

AD to prevent failure of the propeller 

hub, which could cause blade 

separation, damage to the airplane, and 

loss of control of the airplane. 

DATES: This AD becomes effective 

August 17, 2010. The Director of the 

Federal Register approved the 

incorporation by reference of certain 

publications listed in the regulations as 

of August 17, 2010. 

ADDRESSES: You can get the service 

information identified in this AD from 

McCauley Propeller Systems, P.O. Box 

7704, Wichita, KS 67277–7704; 

telephone (800) 621–7767. 

The Docket Operations office is 

located at Docket Management Facility, 

U.S. Department of Transportation, 1200 

New Jersey Avenue, SE., West Building 

Ground Floor, Room W12–140, 

Washington, DC 20590–0001. 

FOR FURTHER INFORMATION CONTACT: Jeff 

Janusz, Aerospace Engineer, Wichita 

Aircraft Certification Office, FAA, Small 

Airplane Directorate, 1801 Airport 

Road, Wichita, KS 67209; e-mail: 

jeff.janusz@faa.gov; telephone (316) 

946–4148; fax (316) 946–4107. 

SUPPLEMENTARY INFORMATION: The FAA 

proposed to amend 14 CFR part 39 with 

a proposed AD. The proposed AD 

applies to McCauley Propeller Systems 

model 4HFR34C653/L106FA propellers. 

We published the proposed AD in the 

Federal Register on September 28, 2007 

(72 FR 55120). We also published a 

supplemental proposed AD in the 

Federal Register on April 13, 2010 (75 

FR 18774). Those actions proposed to 

require a onetime FPI and ECI of the 

propeller hub for cracks. 

Examining the AD 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, the regulatory 

evaluation, any comments received, and 

other information. The street address for 

the Docket Operations office (telephone 

(800) 647–5527) is provided in the 


jlentini on DSKJ8SOYB1PROD with RULES