8554 Federal Register / Vol. 75, No. 37 / Thursday, February 25, 2010 / Proposed Rules 

TABLE 1—AFFECTED CHECK VALVE INSTALLATION—Continued 

Affected check valve installation, identified by FIN 

(functional item number) Compliance time 

(iii) Airplanes having Hydraulic System with FIN 29/1378, FIN 29/1382 

and FIN 29/1394.

Within 30 months after the effective date of this AD. 

(iv) Hydraulic System (A300 airplanes having configuration 01 

‘‘pre-Airbus modification 03079’’ only) FIN 29/1381.

Within 30 months after the effective date of this AD. 

(2) Check valves P/N 2S2794–1 marked 

with an ‘‘R’’ have already been modified in 

accordance with Crissair Service Bulletin 

20070407–29–1 and do not need to be 

replaced. Check valves with P/N 2S2794 are 

not affected and do not need to be replaced. 

(3) As of the effective date of this AD, no 

person may install any Crissair check valve, 

P/N 2S2794–1, on any airplane unless it has 

a serial number other than those listed in 

Appendix 1 of the applicable service bulletin 

identified in Table 2 of this AD, or unless 

check valve P/N 2S2794–1 is marked with an 

‘‘R.’’ 

TABLE 2—SERVICE INFORMATION

Airbus model— Airbus Mandatory Service Bulletin— Revision— Dated— 

A300 airplanes ............................. A300–29–0124, including Appendices 1, 2, and 3 ........................... 02 March 10, 2009. 

A300–600 airplanes ..................... A300–29–6060, including Appendices 1, 2, and 3 ........................... 01 March 10, 2009. 

A310 airplanes ............................. A310–29–2097, including Appendices 1, 2, and 3 ........................... 01 March 19, 2009. 

(4) Submit an inspection report of the 

inspection required by paragraph (f)(1) of this 

AD to Airbus Customer Services Directorate, 

1 Rond Point Maurice Bellonte, 31707 

Blagnac Cedex, France; telephone +33 5 61 

93 33 33; fax +33 5 61 93 42 51; e-mail: 

sb.reporting@airbus.com; at the applicable 

time specified in paragraph (f)(4)(i) or 

(f)(4)(ii) of this AD. The report must include 

the information specified on the inspection 

report sheet provided in the applicable 

service bulletin identified in Table 2 of this 

AD. 

(i) If the inspection was done on or after 

the effective date of this AD: Submit the 

report within 30 days after the inspection. 

(ii) If the inspection was done before the 

effective date of this AD: Submit the report 

within 30 days after the effective date of this 

AD. 

FAA AD Differences 

Note 1: This AD differs from the MCAI 

and/or service information as follows: 

Although the MCAI states not to install the 

part identified in paragraph (f)(3) of this AD 

after accomplishing the actions specified in 

paragraph (f)(1) of this AD, this AD prohibits 

installation of the part as of the effective date 

of this AD. 

Other FAA AD Provisions 

(g) 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: Dan Rodina, 

Aerospace Engineer, International Branch, 

ANM–116, Transport Airplane Directorate, 

FAA, 1601 Lind Avenue, SW., Renton, 

Washington 98057–3356; telephone (425) 

227–2125; 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. 

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 

(h) Refer to MCAI EASA Airworthiness 

Directive 2009–0171, dated August 5, 2009; 

and the service bulletins identified in Table 

2 of this AD; for related information. 

Issued in Renton, Washington, on February 

17, 2010. 

Stephen P. Boyd, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2010–3817 Filed 2–24–10; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2010–0132; Directorate 

Identifier 2009–NM–096–AD] 

RIN 2120–AA64 

Airworthiness Directives; The Boeing 

Company Model 747–100, –200B, and 

–200F Series Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Notice of proposed rulemaking 

(NPRM). 

SUMMARY: The FAA proposes to 

supersede an existing airworthiness 

directive (AD) that applies to certain 

Model 747–100, 747–200B, and –200F 

series airplanes. The existing AD 

currently requires inspections to detect 

cracking in the upper row of fasteners 

holes of the skin lap joints in the 

fuselage lower lobe, and repair, if 

necessary. This proposed AD would 

reduce the maximum interval of the 

post-modification inspections. This 

proposed AD results from reports of 

fatigue cracking on modified airplanes. 

We are proposing this AD to detect and 

correct fatigue cracking in the 

longitudinal lap joints of the fuselage 

lower lobe, which could lead to the 

rapid decompression of the airplane and 

the inability of the structure to carry 

fail-safe loads. 

DATES: We must receive comments on 

this proposed AD by April 12, 2010. 

ADDRESSES: You may send comments by 

any of the following methods: 


sroberts on DSKD5P82C1PROD with PROPOSALS
Federal Register / Vol. 75, No. 37 / Thursday, February 25, 2010 / Proposed Rules 8555 

• 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 

W12–140, 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 proposed AD, contact Boeing 

Commercial Airplanes, Attention: Data 

& Services Management, P.O. Box 3707, 

MC 2H–65, Seattle, Washington 98124– 

2207; telephone 206–544–5000, 

extension 1; fax 206–766–5680; e-mail 

me.boecom@boeing.com; Internet 

https://www.myboeingfleet.com. You 

may review copies of the referenced 

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. 

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 proposed 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: Ivan 

Li, Aerospace Engineer, Airframe 

Branch, ANM–120S, FAA, Seattle 

Aircraft Certification Office, 1601 Lind 

Avenue, SW., Renton, Washington 

98057–3356; telephone (425) 917–6437; 

fax (425) 917–6590. 

SUPPLEMENTARY INFORMATION: 

Comments Invited 

We invite you to send any written 

relevant data, views, or arguments about 

this proposed AD. Send your comments 

to an address listed under the 

ADDRESSES section. Include ‘‘Docket No. 

FAA–2010–0132; Directorate Identifier 

2009–NM–096–AD’’ at the beginning of 

your comments. We specifically invite 

comments on the overall regulatory, 

economic, environmental, and energy 

aspects of this proposed AD. We will 

consider all comments received by the 

closing date and may amend this 

proposed 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 proposed AD. 

Discussion 

On August 4, 1994, we issued AD 94– 

17–01, Amendment 39–8996 (59 FR 

41653, August 15, 1994), for certain 

Model 747 series airplanes. That AD 

requires inspections to detect cracking 

in the upper row of fastener holes of the 

skin lap joints in the fuselage lower 

lobe, and repair if necessary. That AD 

resulted from reports of incidents 

involving fatigue cracking and corrosion 

of transport category airplanes that are 

approaching or have exceeded their 

design life goal. We issued that AD to 

prevent separation of fuselage skin and 

rapid loss of pressure in the airplane. 

Actions Since Existing AD Was Issued 

Since we issued AD 94–17–01, Boeing 

has performed a fleet-wide evaluation of 

the skin panel lap joints for widespread 

fatigue damage (WFD) and determined 

that the post-modification inspection 

interval of AD 94–17–01 needs to be 

reduced. In addition, lap joints where 

the upper (overlapping) skin thickness 

at the upper row of fasteners is 0.071 

inch or less need to be further modified 

to preclude WFD. WFD of the lap joints 

can link up and result in large skin 

cracks, and possible rapid in-flight 

decompression of the airplane. 

Relevant Service Information 

AD 94–17–01 referred to Boeing 

Service Bulletin 747–53A2267, Revision 

3, dated March 26, 1992, as the 

appropriate source of service 

information. Boeing has since issued 

Alert Service Bulletin 747–53A2267, 

Revision 4, dated March 26, 2009. This 

service bulletin reduces the repetitive 

interval for the post-modification 

inspections and references a structural 

modification for lap joints where the 

upper (overlapping) skin thickness at 

the upper row of fasteners is 0.071 inch 

or less. 

Related Rulemaking 

We are considering issuing related 

rulemaking to address the identified 

unsafe condition. We are in the process 

of issuing an AD that will refer to 

Revision 1 of Boeing Alert Service 

Bulletin 747–53A2463, and is related to 

this issue. That AD will require further 

modification of all the affected lap joints 

with an upper skin thickness of 0.071 

inch or less. 

FAA’s Determination and Requirements 

of the Proposed AD 

We have evaluated all pertinent 

information and identified an unsafe 

condition that is likely to develop on 

other airplanes of the same type design. 

For this reason, we are proposing this 

AD, which would supersede AD 94–17– 

01. This AD would retain the 

requirements of that AD using the 

revised service information, and reduce 

the maximum interval of the postmodification inspections from 3,000 

flight cycles to 1,000 flight cycles. 

Differences Between the Proposed AD 

and Service Bulletin 

Boeing Alert Service Bulletin 747– 

53A2267, Revision 4, dated March 26, 

2009, specifies to contact the 

manufacturer for instructions on how to 

repair certain conditions, but this 

proposed AD would require repairing 

those conditions in one of the following 

ways: 

• Using a method that we approve; or 

• Using data that meet the 

certification basis of the airplane, and 

that have been approved by the Boeing 

Commercial Airplanes Organization 

Designation Authorization that we have 

authorized to make those findings. 

Changes to Existing AD 

This proposed AD would retain the 

requirements of AD 94–17–01. Since AD 

94–17–01 was issued, the AD format has 

been revised, and certain paragraphs 

have been rearranged. As a result, the 

corresponding paragraph identifiers 

have changed in this proposed AD, as 

listed in the following table: 

REVISED PARAGRAPH IDENTIFIERS

Requirement in 

AD 94–17–01 

Corresponding 

requirement in this 

proposed AD 

Paragraph (a) Paragraph (g). 

Paragraph (b) Paragraph (h). 

Paragraph (c) Paragraph (i). 

This proposed AD identifies the legal 

name of the manufacturer as published 

in the most recent type certificate data 

sheet for the affected airplane models. 

Costs of Compliance 

There are about 23 airplanes of the 

affected design in the worldwide fleet. 

The following table provides the 

estimated costs for U.S. operators to 

comply with this proposed AD. 


sroberts on DSKD5P82C1PROD with PROPOSALS
8556 Federal Register / Vol. 75, No. 37 / Thursday, February 25, 2010 / Proposed Rules 

ESTIMATED COSTS

Action Work hours 

Average 

labor rate 

per hour 

Parts Cost per airplane 

Number of 

U.S. 

-registered 

airplanes 

Fleet cost 

Inspection (required by AD 

94–17–01).

244 $85 $0 $20,740 per inspection 

cycle.

7 $145,180 per inspection 

cycle. 

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 

proposed AD would not have federalism 

implications under Executive Order 

13132. This proposed AD would 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 proposed 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 proposed 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. 

The Proposed Amendment 

Accordingly, under the authority 

delegated to me by the Administrator, 

the FAA proposes to amend 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 39–8996 (59 FR 

41653, August 15, 1994) and adding the 

following new AD: 

The Boeing Company: Docket No. FAA– 

2010–0132; Directorate Identifier 2009– 

NM–096–AD. 

Comments Due Date 

(a) The FAA must receive comments on 

this AD action by April 12, 2010. 

Affected ADs 

(b) This AD supersedes AD 94–17–01, 

Amendment 39–8996. 

Applicability 

(c) This AD applies to The Boeing 

Company Model 747–100, 747–200B, and 

747–200F series airplanes, certificated in any 

category, as identified in Boeing Alert 

Service Bulletin 747–53A2267, Revision 4, 

dated March 26, 2009. 

Subject 

(d) Air Transport Association (ATA) of 

America Code 53: Fuselage. 

Unsafe Condition 

(e) This AD results from reports of fatigue 

cracking. The Federal Aviation 

Administration is issuing this AD to detect 

and correct fatigue cracking in the fuselage 

lower lobe longitudinal lap joints, which 

could lead to the rapid decompression of the 

airplane and the inability of the structure to 

carry fail-safe loads. 

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 94–17– 

01, with Revised Compliance Times for PostModification Inspection and Revised Service 

Information: 

Initial External High Frequency Eddy 

Current Inspection 

(g) Perform an external high frequency 

eddy current inspection to detect cracks in 

the upper row of fasteners in the modified 

lap joints in accordance with Boeing Service 

Bulletin 747–53A2267, Revision 3, dated 

March 26, 1992; or Revision 4, dated March 

26, 2009; at the time specified in paragraph 

(g)(1) or (g)(2) or (g)(3) of this AD, as 

applicable. As of the effective date of this 

AD, only Revision 4 may be used. 

(1) For airplanes on which the full 

modification required by AD 90–06–06, 

Amendment 39–6490, has been 

accomplished in accordance with Revision 2 

of Boeing Service Bulletin 747–53A2267, 

dated March 29, 1990; or Revision 3, dated 

March 26, 1992; or Revision 4, dated March 

26, 2009: Prior to the accumulation of 10,000 

flight cycles after accomplishment of the full 

modification. 

(2) For airplanes on which the full 

modification required by AD 90–06–06 has 

been accomplished in accordance with 

Boeing Service Bulletin 747–53A2267, dated 

March 28, 1986; or Revision 1, dated 

September 25, 1986: Prior to the 

accumulation of 7,000 flight cycles after 

accomplishment of the full modification. 

(3) For airplanes on which the optional 

modification has been accomplished in 

accordance with Boeing Service Bulletin 

747–53A2267, Revision 2, dated March 29, 

1990; or Revision 3, dated March 26, 1992; 

or Revision 4, dated March 26, 2009: Prior to 

the accumulation of 7,000 flight cycles after 

accomplishment of the optional 

modification. 

Repetitive External High Frequency Eddy 

Current Inspections 

(h) If no cracking is detected during the 

inspection required by paragraph (g) of this 

AD, repeat the inspection required by 

paragraph (g) of this AD at the earlier of the 

times specified in paragraphs (h)(1) and 

(h)(2) of this AD, and thereafter at intervals 

not to exceed 1,000 flight cycles. 

(1) Within 3,000 flight cycles after the last 

inspection required by paragraph (g) of this 

AD. 

(2) Within 1,000 flight cycles after the last 

inspection required by paragraph (g) of this 

AD or 500 flight cycles after the effective date 

of this AD, whichever occurs later. 

Repair 

(i) If any cracking is detected during any 

inspection required by paragraph (g) of this 


sroberts on DSKD5P82C1PROD with PROPOSALS
Federal Register / Vol. 75, No. 37 / Thursday, February 25, 2010 / Proposed Rules 8557 

AD, prior to further flight, repair in 

accordance with Section 53–30–03 of the 

Boeing 747 Structural Repair Manual (SRM); 

or Boeing Alert Service Bulletin 747– 

53A2267, Revision 4, dated March 26, 2009; 

except as required by paragraph (j) of this 

AD; and repeat the inspection required by 

paragraph (g) of this AD at the times 

specified in paragraph (i)(1) of this AD. After 

the effective date of this AD, use only Boeing 

Alert Service Bulletin 747–53A2267, 

Revision 4, dated March 26, 2009. 

(1) As of the effective date of this AD: If 

the repair specified in the Boeing 747 SRM 

does not include removing the lap joint and 

the upper row of countersunk fasteners, 

repeat the inspection required by paragraph 

(g) of this AD at the earlier of the times 

specified in paragraphs (i)(1)(i) and (i)(1)(ii) 

of this AD, and thereafter at intervals not to 

exceed 1,000 flight cycles. 

(i) Within 3,000 flight cycles after the last 

inspection required by paragraph (g) of this 

AD. 

(ii) Within 1,000 flight cycles after the last 

inspection required by paragraph (g) of this 

AD, or within 500 flight cycles after the 

effective date of this AD, whichever occurs 

later. 

(2) If the repair specified in the 747 SRM 

includes removing the lap joint and the 

upper row of countersunk fasteners, such 

repair constitutes terminating action for the 

inspection requirements of this AD. 

Exception to the Service Bulletin 

(j) If any cracking is found during any 

inspection required by this AD, and Boeing 

Alert Service Bulletin 747–53A2267, 

Revision 4, dated March 26, 2009, specifies 

contacting Boeing for appropriate action: 

Before further flight, repair the cracking 

using a method approved in accordance with 

the procedures specified in paragraph (k) of 

this AD. For a repair method to be approved 

by the Manager, Seattle ACO, as required by 

this paragraph, the Manager’s approval letter 

must specifically refer to this AD. 

Alternative Methods of Compliance 

(AMOCs) 

(k)(1) The Manager, Seattle Aircraft 

Certification Office, 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: Ivan Li, 

Aerospace Engineer, Airframe Branch, ANM– 

120S, FAA, Seattle Aircraft Certification 

Office, 1601 Lind Avenue, SW., Renton, 

Washington 98057–3356; telephone (425) 

917–6437; fax (425) 917–6590. Or, e-mail 

information to 9-ANM-Seattle-ACO-AMOCRequests@faa.gov. 

(2) To request a different method of 

compliance or a different compliance time 

for this AD, follow the procedures in 14 CFR 

39.19. 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. 

(3) An AMOC that provides an acceptable 

level of safety may be used for any repair 

required by this AD if it is approved by the 

Boeing Commercial Airplanes Organization 

Designation Authorization (ODA) that has 

been authorized by the Manager, Seattle 

ACO, to make those findings. For a repair 

method to be approved, the repair must meet 

the certification basis of the airplane, and the 

approval must specifically refer to this AD. 

(4) AMOCs approved previously in 

accordance with AD 94–17–01 are approved 

as AMOCs for the corresponding provisions 

of this AD. 

Issued in Renton, Washington, on February 

17, 2010. 

Stephen P. Boyd, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2010–3819 Filed 2–24–10; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2010–0170; Directorate 

Identifier 2009–NM–127–AD] 

RIN 2120–AA64 

Airworthiness Directives; Empresa 

Brasileira de Aeronautica S.A. 

(EMBRAER) Model EMB–135ER, 

–135KE, –135KL, and –135LR 

Airplanes; and EMBRAER Model EMB– 

145, –145ER, –145MR, –145LR, 

–145XR, –145MP, and –145EP 

Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Notice of proposed rulemaking 

(NPRM). 

SUMMARY: We propose to adopt a new 

airworthiness directive (AD) for the 

products listed above. This proposed 

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: 

Reassessment of the damage tolerance 

analysis resulted in threshold reduction for 

some Structure Significant Items (SSI) of the 

Maintenance Review Board Report (MRBR) 

Airworthiness Limitations Items (ALI). 

Failure to inspect these structural 

components, according to the new threshold, 

could prevent a timely detection of fatigue 

cracking. These cracks, if not properly 

addressed, could adversely affect the 

structural integrity of the airplane. 

* * * * * 

The proposed AD would require 

actions that are intended to address the 

unsafe condition described in the MCAI. 

DATES: We must receive comments on 

this proposed AD by April 12, 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. 

For service information identified in 

this proposed 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. 

You may review copies of the 

referenced 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. 

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 proposed 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: 

Comments Invited 

We invite you to send any written 

relevant data, views, or arguments about 

this proposed AD. Send your comments 

to an address listed under the 


sroberts on DSKD5P82C1PROD with PROPOSALS