Federal Register / Vol. 75, No. 35 / Tuesday, February 23, 2010 / Rules and Regulations 7931 

ANM–116, Transport Airplane Directorate, 

FAA, 1601 Lind Avenue, SW., Renton, 

Washington 98057–3356; telephone (425) 

227–2848; fax (425) 227–1149. 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. 

(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 

(h) Refer to MCAI Brazilian Airworthiness 

Directive 2008–10–03, effective October 21, 

2008; and Embraer Service Bulletin 190–57– 

0023, dated June 9, 2008; for related 

information. 

Material Incorporated by Reference 

(i) You must use Embraer Service Bulletin 

190–57–0023, dated June 9, 2008, as 

applicable, 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 Empresa Brasileira de 

Aeronautica S.A. (EMBRAER), Technical 

Publications Section (PC 060), Av. Brigadeiro 

Faria Lima, 2170—Putim—12227–901 Sa ̃o 

Jose dos Campos—SP—BRASIL; telephone: 

+55 12 3927–5852 or +55 12 3309–0732; fax: 

+55 12 3927–7546; e-mail: 

distrib@embraer.com.br; Internet: http:// 

www.flyembraer.com. 

(3) 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 or 425–227–1152. 

(4) You may also review copies of the 

service information that is incorporated by 

reference at the National Archives and 

Records Administration (NARA). For 

information on the availability of this 

material at 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 February 

5, 2010. 

Stephen P. Boyd, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2010–3116 Filed 2–22–10; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2010–0038; Directorate 

Identifier 2009–NM–110–AD; Amendment 

39–16203; AD 2010–04–10] 

RIN 2120–AA64 

Airworthiness Directives; Airbus Model 

A380–841, –842, and –861 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) 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: 

During the flight test campaign of the 

A380–861 model (Engine Alliance powered), 

some cracks were found on the Movable Flap 

Track Fairing number 6 (MFTF#6). 

These cracks were located at the pivot 

attachment support-ring and at the U-frame 

in the attachment area to aft-kinematic. In 

addition, delamination has been observed 

within the monolithic Carbon Fibre 

Reinforced Plastic (CFRP) structure around 

the pivot support-ring. 

This condition, if not corrected, could lead 

to in-flight loss of the MFTF#6, potentially 

resulting in injuries to persons on the 

ground. 

* * * * * 

This AD requires actions that are 

intended to address the unsafe 

condition described in the MCAI. 

DATES: This AD becomes effective 

March 10, 2010. 

The Director of the Federal Register 

approved the incorporation by reference 

of certain publications listed in the AD 

as of March 10, 2010. 

On May 28, 2009 (74 FR 22422, May 

13, 2009), the Director of the Federal 

Register approved the incorporation by 

reference of a certain other publication 

listed in the AD. 

We must receive comments on this 

AD by April 9, 2010. 

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– 

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 

W12–40, 1200 New Jersey Avenue, SE., 

Washington, DC, between 9 a.m. and 5 

p.m., Monday through Friday, except 

Federal holidays. 

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 in the ADDRESSES

section. Comments will be available in 

the AD docket shortly after receipt. 

FOR FURTHER INFORMATION CONTACT: 

Todd Thompson, Aerospace Engineer, 

International Branch, ANM–116, 

Transport Airplane Directorate, FAA, 

1601 Lind Avenue, SW., Renton, 

Washington 98057–3356; telephone 

(425) 227–1175; fax (425) 227–1149. 

SUPPLEMENTARY INFORMATION: 

Discussion 

On May 1, 2009, the FAA issued AD 

2009–10–07, Amendment 39–15902 (74 

FR 22422, May 13, 2009). That AD 

required actions intended to address an 

unsafe condition on the products listed 

above. 

Since we issued that AD, the 

European Aviation Safety Agency 

(EASA), which is the Technical Agent 

for the Member States of the European 

Community, has issued EASA 

Airworthiness Directive 2009–0152, 

dated July 14, 2009 (referred to after this 

as ‘‘the MCAI’’), to correct an unsafe 

condition for the specified products. 

The MCAI states: 

During the flight test campaign of the 

A380–861 model (Engine Alliance powered), 

some cracks were found on the Movable Flap 

Track Fairing number 6 (MFTF#6). 

These cracks were located at the pivot 

attachment support-ring and at the U-frame 

in the attachment area to aft-kinematic. In 

addition, delamination has been observed 

within the monolithic Carbon Fibre 

Reinforced Plastic (CFRP) structure around 

the pivot support-ring. 

This condition, if not corrected, could lead 

to in-flight loss of the MFTF#6, potentially 

resulting in injuries to persons on the 

ground. 

To prevent the risk of a MFTF#6 

detachment, EASA AD 2008–0216 (which 

corresponds to FAA AD 2009–10–07) 

required an inspection programme in order to 

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7932 Federal Register / Vol. 75, No. 35 / Tuesday, February 23, 2010 / Rules and Regulations 

detect cracks before they become critical and 

in case of findings to replace the MFTF#6. 

This AD, which supersedes EASA AD 

2008–0216: 

• Cancels the MFTF#6 General Visual 

Inspection requirement, 

• Refers to Airbus Service Bulletin A380– 

57–8014 Revision 1 * * * 

• Introduces an optional terminating 

action [installing reinforced part]. 

AD 2009–10–07 applies to all Airbus 

Model A380–841, –842, and –861 

airplanes. This AD retains the 

requirements of AD 2009–10–07. 

Airplanes were removed from the 

applicability of AD 2009–10–07 by 

excluding airplanes on which Airbus 

modification 68729 is done in 

production. This AD also revises the 

compliance time for the inspections of 

replaced parts. The compliance time is 

reduced for certain parts and extended 

for certain other parts, depending on the 

flight cycles since first installation of 

the part. The replacement parts must be 

inspected within the thresholds 

specified in paragraph (f)(1) of this AD. 

Relevant Service Information 

Since we issued AD 2009–10–07, 

Airbus has issued Mandatory Service 

Bulletin A380–57–8014, Revision 01, 

dated June 5, 2009; and Service Bulletin 

A380–57–8017, dated June 5, 2009. 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 the State of 

Design Authority, we have been notified 

of the unsafe condition described in the 

MCAI and service information 

referenced above. We are issuing this 

AD because we evaluated all pertinent 

information and determined the unsafe 

condition exists and is likely to exist or 

develop on other products of the same 

type design. 

There are no products of this type 

currently registered in the United States. 

However, this rule is necessary to 

ensure that the described unsafe 

condition is addressed if any of these 

products are placed on the U.S. Register 

in the future. 

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. 

Any such differences are highlighted in 

a NOTE within the AD. 

FAA’s Determination of the Effective 

Date 

Since there are currently no domestic 

operators of this product, notice and 

opportunity for public comment before 

issuing this AD are unnecessary. 

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–2010–0038; 

Directorate Identifier 2009–NM–110– 

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 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 39–15902 (74 FR 

22422, May 13, 2009) and adding the 

following new AD: 

2010–04–10 Airbus: Amendment 39–16203. 

Docket No. FAA–2010–0038; Directorate 

Identifier 2009–NM–110–AD. 

Effective Date 

(a) This airworthiness directive (AD) 

becomes effective March 10, 2010. 

Affected ADs 

(b) This AD supersedes AD 2009–10–07, 

Amendment 39–15902. 

Applicability 

(c) This AD applies to Airbus Model A380– 

841, –842, and –861 airplanes, certificated in 

any category, all serial numbers, except 

airplanes on which Airbus modification 

68729 has been done in production. 

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Federal Register / Vol. 75, No. 35 / Tuesday, February 23, 2010 / Rules and Regulations 7933 

Subject 

(d) Air Transport Association (ATA) of 

America Code 57: Wings. 

Reason 

(e) The mandatory continued airworthiness 

information (MCAI) states: 

During the flight test campaign of the 

A380–861 model (Engine Alliance powered), 

some cracks were found on the Movable Flap 

Track Fairing number 6 (MFTF#6). 

These cracks were located at the pivot 

attachment support-ring and at the U-frame 

in the attachment area to aft-kinematic. In 

addition, delamination has been observed 

within the monolithic Carbon Fibre 

Reinforced Plastic (CFRP) structure around 

the pivot support-ring. 

This condition, if not corrected, could lead 

to in-flight loss of the MFTF#6, potentially 

resulting in injuries to persons on the 

ground. 

To prevent the risk of a MFTF#6 

detachment, EASA AD 2008–0216 required 

an inspection programme in order to detect 

cracks before they become critical and in case 

of findings to replace the MFTF#6. 

This AD, which supersedes EASA AD 

2008–0216: 

• Cancels the MFTF#6 General Visual 

Inspection requirement, 

• Refers to Airbus Service Bulletin A380– 

57–8014 Revision 1, * * * 

• Introduces an optional terminating 

action. 

Restatement of Requirements of AD 2009– 

10–07, With Revised Inspection, Service 

Information, and Compliance Time for the 

Inspection of Replaced Parts 

Actions and Compliance 

(f) Unless already done, do the following 

actions. 

(1) At the applicable time specified in 

paragraph (f)(1)(i) or (f)(1)(ii) of this AD for 

the left- and right-hand MFTF#6, do a special 

detailed (ultrasonic and high-frequency eddy 

current) inspection of the filet radii of pivot 

supports, monolithic carbon fibre reinforced 

plastic structures, and radii of the U-frame, 

for cracking and delamination in accordance 

with the Accomplishment Instructions of 

Airbus Service Bulletin A380–57–8014, 

dated November 21, 2008; or Airbus 

Mandatory Service Bulletin A380–57–8014, 

Revision 01, dated June 5, 2009. After the 

effective date of this AD, use only Revision 

01. 

(i) For Airbus Model A380–841 and –842 

airplanes: Before the MFTF#6 has 

accumulated 500 total flight cycles since its 

first installation on an airplane, or within 30 

flight hours after May 28, 2009 (the effective 

date of AD 2009–10–07), whichever occurs 

later. 

(ii) For Model A380–861 airplanes: Before 

the MFTF#6 has accumulated 100 total flight 

cycles since its first installation on an 

airplane, or within 30 flight hours after May 

28, 2009, whichever occurs later. 

(2) If no cracking and no delamination are 

found during any inspection required by 

paragraph (f)(1) of this AD, repeat the 

inspections required by paragraph (f)(1) of 

this AD thereafter at intervals not to exceed 

the applicable time specified in paragraph 

(f)(2)(i) or (f)(2)(ii) of this AD. 

(i) For Model A380–841 and –842 

airplanes: 50 flight cycles. 

(ii) For Model A380–861 airplanes: 10 

flight cycles. 

(3) If any cracking or delamination is found 

during any inspection required by paragraph 

(f)(1) or (f)(2) of this AD, before further flight, 

replace the MFTF#6 with a new or 

serviceable part, in accordance with the 

Accomplishment Instructions of Airbus 

Service Bulletin A380–57–8014, dated 

November 21, 2008; or Airbus Mandatory 

Service Bulletin A380–57–8014, Revision 01, 

dated June 5, 2009. For parts replaced before 

the effective date of this AD, repeat the 

inspections specified in paragraph (f)(1) of 

this AD at the later of the times specified in 

paragraphs (f)(3)(i) and (f)(3)(ii) of this AD. 

For parts replaced on or after the effective 

date of this AD, repeat the inspections 

specified in paragraph (f)(1) of this AD at the 

applicable time defined in paragraph (f)(1) of 

this AD. After the effective date of this AD, 

use only Revision 01 for the replacement. 

(i) At the applicable time defined in 

paragraph (f)(2) of this AD. 

(ii) At the applicable time defined in 

paragraph (f)(1) of this AD. 

New Requirements of This AD 

Actions and Compliance 

(g) Unless already done, do the following 

actions. 

(1) In case of MFTF#6 replacement, submit 

a report using Appendix 01 of Airbus Service 

Bulletin A380–57–8014, dated November 21, 

2008, to Airbus Central Entity, Dept SEES5, 

1, Rond Point Maurice Bellonte, 31707 

Blagnac, France; e-mail 

Frederic.molinier@airbus.com; at the 

applicable time specified in paragraph 

(g)(1)(i) or (g)(1)(ii) of this AD. The report 

must include the serial number of the 

removed MFTF#6, the associated airplane 

manufacturer serial number, and the number 

of flight cycles accumulated by the MFTF#6 

at the time of removal. 

(i) If the MFTF#6 replacement was done on 

or after the effective date of this AD: Submit 

the report within 30 days after the MFTF#6 

removal. 

(ii) If the MFTF#6 replacement was done 

before the effective date of this AD: Submit 

the report within 30 days after the effective 

date of this AD. 

(2) Replacement of the MFTF#6 with a 

reinforced MFTF#6, in accordance with the 

Accomplishment Instructions of Airbus 

Service Bulletin A380–57–8017, dated June 

5, 2009, terminates the requirements of this 

AD. 

FAA AD Differences 

Note 1: This AD differs from the MCAI 

and/or service information as follows: No 

differences. 

Other FAA AD Provisions 

(h) The following provisions also apply to 

this AD: 

(1) Alternative Methods of Compliance 

(AMOCs): The Manager, International 

Branch, ANM–116, Transport Airplane 

Directorate, 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: Todd Thompson, 

Aerospace Engineer, International Branch, 

ANM–116, Transport Airplane Directorate, 

FAA, 1601 Lind Avenue, SW., Renton, 

Washington 98057–3356; telephone (425) 

227–1175; fax (425) 227–1149. Before using 

any approved AMOC on any airplane to 

which the AMOC applies, notify your 

appropriate 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 

(i) Refer to Mandatory Continuing 

Airworthiness Information (MCAI) EASA 

Airworthiness Directive 2009–0152, dated 

July 14, 2009; Airbus Service Bulletin A380– 

57–8014, dated November 21, 2008; Airbus 

Mandatory Service Bulletin A380–57–8014, 

Revision 01, dated June 5, 2009; and Airbus 

Service Bulletin A380–57–8017, dated June 

5, 2009; for related information. 

Material Incorporated by Reference 

(j) You must use Airbus Service Bulletin 

A380–57–8014, including Appendix 01, 

dated November 21, 2008; Airbus Mandatory 

Service Bulletin A380–57–8014, Revision 01, 

dated June 5, 2009; and Airbus Service 

Bulletin A380–57–8017, dated June 5, 2009; 

as applicable; 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 

Airbus Mandatory Service Bulletin A380–57– 

8014, Revision 01, dated June 5, 2009; and 

Airbus Service Bulletin A380–57–8017, 

dated June 5, 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 Airbus Service Bulletin A380– 

57–8014, including Appendix 01, dated 

November 21, 2008, on May 28, 2009 (74 FR 

22422, May 13, 2009). 

(3) For service information identified in 

this AD, contact Airbus SAS—EANA 

(Airworthiness Office); 1 Rond Point Maurice 

Bellonte, 31707 Blagnac Cedex, France; 

telephone +33 562 110 253; Fax +33 562 110 

307; e-mail account.airworthA380@airbus.com; Internet http:// 

www.airbus.com. 

(4) You may review copies of the service 

information at the FAA, Transport Airplane 

mstockstill on DSKH9S0YB1PROD with RULES

7934 Federal Register / Vol. 75, No. 35 / Tuesday, February 23, 2010 / Rules and Regulations 

Directorate, 1601 Lind Avenue, SW., Renton, 

Washington. For information on the 

availability of this material at the FAA, call 

425–227–1221 or 425–227–1152. 

(5) 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 February 

5, 2010. 

Stephen P. Boyd, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2010–3121 Filed 2–22–10; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2010–0093; Directorate 

Identifier 97–ANE–06–AD; Amendment 39– 

16198; AD 2010–04–05] 

RIN 2120–AA64 

Airworthiness Directives; McCauley 

Propeller Systems 1A103/TCM Series 

Propellers 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule; request for 

comments. 

SUMMARY: The FAA is superseding an 

existing airworthiness directive (AD) for 

McCauley Propeller Systems 1A103/ 

TCM series propellers. That AD 

requires, for certain serial numbers 

(S/Ns) of McCauley Propeller Systems 

1A103/TCM series propellers, initial 

and repetitive visual and dye penetrant 

inspections for cracks in the propeller 

hub, replacement of propellers with 

cracks that do not meet acceptable 

limits, and rework of propellers with 

cracks that meet acceptable limits. This 

AD requires, for all McCauley Propeller 

Systems 1A103/TCM series propellers, 

the same actions but at reduced 

compliance times. This AD also requires 

inspections of the bolt holes, reaming 

holes if necessary, and inspections of 

steel reinforcement plates and gaskets. 

This AD results from 16 reports received 

of propeller hubs found cracked since 

AD 2003–12–05 was issued. We are 

issuing this AD to prevent propeller 

separation due to hub fatigue cracking, 

which can result in loss of control of the 

airplane. 

DATES: Effective March 10, 2010. The 

Director of the Federal Register 

approved the incorporation by reference 

of certain publications listed in the 

regulations as of March 10, 2010. 

We must receive any comments on 

this AD by April 26, 2010. 

ADDRESSES: Use one of the following 

addresses to comment on this AD. 

• Federal eRulemaking Portal: Go to 

http://www.regulations.gov and follow 

the instructions for sending your 

comments electronically. 

• Mail: Docket Management Facility, 

U.S. Department of Transportation, 1200 

New Jersey Avenue, SE., West Building 

Ground Floor, Room W12–140, 

Washington, DC 20590–0001. 

• Hand Delivery: Deliver to Mail 

address above between 9 a.m. and 5 

p.m., Monday through Friday, except 

Federal holidays. 

• Fax: (202) 493–2251. 

FOR FURTHER INFORMATION CONTACT: 

Thomas Teplik, Aerospace Engineer, 

Wichita Aircraft Certification Office, 

FAA, Small Airplane Directorate, 1801 

Airport Road, Room 100, Wichita, KS 

67209; e-mail: thomas.teplik@faa.gov; 

telephone: (316) 946–4196; fax: (316) 

946–4107. 

SUPPLEMENTARY INFORMATION: The FAA 

amends 14 CFR part 39 by superseding 

AD 2003–12–05, Amendment 39–13190 

(68 FR 35155, June 12, 2003). That AD 

requires, for certain S/Ns of McCauley 

Propeller Systems 1A103/TCM series 

propellers, initial and repetitive visual 

and dye penetrant inspections for cracks 

in the propeller hub, replacement of 

propellers with cracks that do not meet 

acceptable limits, and rework of 

propellers with cracks that meet 

acceptable limits. That AD was the 

result of reports of hub cracking on the 

camber (forward) side of the propeller 

hub near the attachment bolt holes on 

certain propellers. That condition, if not 

corrected, could result in propeller 

separation due to hub fatigue cracking, 

which can result in loss of control of the 

airplane. 

Actions Since AD 2003–12–05 Was 

Issued 

Since AD 2003–12–05 was issued, we 

received 16 reports of propeller hubs 

found cracked. Two of the cracks were 

on propellers outside the propeller 

range of serial numbers affected by AD 

2003–12–05. These cracks began at a 

bolt hole and extended through to the 

hub outer surface. These propellers had 

fewer than 3,000 operating hours timein-service (TIS). AD 2003–12–05 

required inspections starting at 3,000 

operating hours TIS. We have not yet 

been able to determine the cause of the 

propeller hub cracking. 

Relevant Service Information 

We have reviewed and approved the 

technical contents of McCauley 

Propeller Systems Alert Service Bulletin 

(ASB) No. ASB221E, dated January 28, 

2010. That ASB describes, for all 

McCauley Propeller Systems 1A103/ 

TCM series propellers, procedures for 

initial and repetitive visual and dye 

penetrant inspections for cracks in the 

propeller hub, removal from service of 

propellers with cracks that do not meet 

acceptable limits, and rework of 

propellers with cracks that meet 

acceptable limits. 

FAA’s Determination and Requirements 

of This AD 

The unsafe condition described 

previously is likely to exist or develop 

on other McCauley Propeller Systems 

1A103/TCM series propellers of the 

same type design. We are issuing this 

AD to prevent propeller separation due 

to hub fatigue cracking, which can 

result in loss of control of the airplane. 

This AD requires, for all McCauley 

Propeller Systems 1A103/TCM series 

propellers, initial and repetitive visual 

and dye penetrant inspections for cracks 

in the propeller hub, including bolt 

holes, reaming holes if necessary, 

inspections of steel reinforcement plates 

and gaskets, removal from service of 

propellers with cracks that do not meet 

acceptable limits, and rework of 

propellers with cracks that meet 

acceptable limits. You must use the 

service information described 

previously to perform the actions 

required by this AD. 

FAA’s Determination of the Effective 

Date 

Since an unsafe condition exists that 

requires the immediate adoption of this 

AD, we have found that notice and 

opportunity for public comment before 

issuing this AD are impracticable, and 

that good cause exists for making this 

amendment effective in less than 30 

days. 

Interim Action 

These actions are interim actions and 

we may take further rulemaking actions 

in the future. 

Comments Invited 

This AD is a final rule that involves 

requirements affecting flight safety and 

was not preceded by notice and an 

opportunity for public comment; 

however, we invite you to send us any 

written relevant data, views, or 

arguments regarding this AD. Send your 

comments to an address listed under 

ADDRESSES. Include ‘‘Docket No. FAA– 

2010–0093; Directorate Identifier 97– 

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