Federal Register / Vol. 76, No. 3 / Wednesday, January 5, 2011 / Rules and Regulations 441 

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 

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 FAAapproved 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: A federal 

agency may not conduct or sponsor, and a 

person is not required to respond to, nor 

shall a person be subject to a penalty for 

failure to comply with a collection of 

information subject to the requirements of 

the Paperwork Reduction Act unless that 

collection of information displays a current 

valid OMB Control Number. The OMB 

Control Number for this information 

collection is 2120–0056. Public reporting for 

this collection of information is estimated to 

be approximately 5 minutes per response, 

including the time for reviewing instructions, 

completing and reviewing the collection of 

information. All responses to this collection 

of information are mandatory. Comments 

concerning the accuracy of this burden and 

suggestions for reducing the burden should 

be directed to the FAA at: 800 Independence 

Ave., SW., Washington, DC 20591, Attn: 

Information Collection Clearance Officer, 

AES–200. 

Related Information 

(i) Refer to MCAI Brazilian Airworthiness 

Directives 2007–08–01, effective September 

27, 2007, and 2009–08–03, effective August 

20, 2009; Sections A2.5.2, Fuel System 

Limitation Items, and A2.4, Critical Design 

Configuration Control Limitation (CDCCL), of 

Appendix 2 of EMBRAER Legacy BJ— 

Maintenance Planning Guide MPG–1483, 

Revision 5, dated March 22, 2007; and the 

Parker CMMs listed in table 2 of this AD; for 

related information. 

Material Incorporated by Reference 

(j) You must use the applicable service 

information contained in table 3 of this AD 

to do the actions required by this AD, unless 

the AD specifies otherwise. 

TABLE 3—ALL MATERIAL INCORPORATED BY REFERENCE

Document Revision Date 

Parker Component Maintenance Manual With Illustrated Parts List 28–41–69 ............................. 2 ................................ March 13, 2009. 

Parker Component Maintenance Manual With Illustrated Parts List 28–41–66 ............................. 1 ................................ March 13, 2009. 

Parker Component Maintenance Manual With Illustrated Parts List 28-41-90 ............................... Original ...................... April 3, 2009. 

Sections A2.5.2, Fuel System Limitation Items, and A2.4, Critical Design Configuration Control 

Limitation (CDCCL), of Appendix 2 of EMBRAER Legacy BJ—Maintenance Planning Guide 

MPG–1483.

5 ................................ March 22, 2007. 

(Parker Component Maintenance Manual 

With Illustrated Parts List 28–41–69, 

Revision 2, dated March 13, 2009, contains 

an incorrect date on page 105; the correct 

date is March 13, 2009.) 

(1) The Director of the Federal Register 

approved the incorporation by reference of 

the service information contained in table 4 

of this AD under 5 U.S.C. 552(a) and 1 CFR 

part 51. 

TABLE 4—NEW MATERIAL INCORPORATED BY REFERENCE

Document Revision Date 

Parker Component Maintenance Manual With Illustrated Parts List 28–41–69 ............................. 2 ................................ March 13, 2009. 

Parker Component Maintenance Manual With Illustrated Parts List 28–41–66 ............................. 1 ................................ March 13, 2009. 

Parker Component Maintenance Manual With Illustrated Parts List 28-41-90 ............................... Original ...................... April 3, 2009. 

(2) The Director of the Federal Register 

previously approved the incorporation by 

reference of Sections A2.5.2, Fuel System 

Limitation Items, and A2.4, Critical Design 

Configuration Control Limitation (CDCCL), of 

Appendix 2 of EMBRAER Legacy BJ— 

Maintenance Planning Guide MPG–1483, 

Revision 5, dated March 22, 2007, on July 30, 

2008 (73 FR 35908, June 25, 2008). 

(3) For EMBRAER 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. For Parker service 

information identified in this AD, contact 

Parker Hannifin Corporation, Aerospace 

Group, Electronic Systems Division, 300 

Marcus Boulevard, Smithtown, New York 

11787; telephone 631–231–3737; e-mail 

csoengineering@parker.com; Internet http:// 

www.parker.com. 

(4) 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. 

(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 

December 17, 2010. 

Ali Bahrami, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 2010–32998 Filed 1–4–11; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2010–1278; Directorate 

Identifier 2010–NM–260–AD; Amendment 

39–16567; AD 2011–01–13] 

RIN 2120–AA64 

Airworthiness Directives; Airbus Model 

A300 B4–600, B4–600R, and F4–600R 

Series Airplanes, and Model C4–605R 

Variant F Airplanes (Collectively Called 

A300–600 Series Airplanes) 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Final rule; request for 

comments. 

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442 Federal Register / Vol. 76, No. 3 / Wednesday, January 5, 2011 / Rules and Regulations 

SUMMARY: We are adopting a new 

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 a routine maintenance check on an 

A300–600 aeroplane, the operator found the 

pitch uncoupling unit installed at an 

incorrect location. The pitch uncoupling unit 

was inverted with the rod assembly. 

After a complete inspection of all A300– 

600 aeroplanes of its fleet, the operator 

identified the same incorrect installation on 

another aeroplane. 

* * * * * 

This condition, if not detected and 

corrected, in combination with particular 

failure modes, could lead to loss of control 

of the aeroplane during the takeoff phase. 

* * * * * 

This AD requires actions that are 

intended to address the unsafe 

condition described in the MCAI. 

DATES: This AD becomes effective 

January 20, 2011. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication listed in the AD 

as of January 20, 2011. 

We must receive comments on this 

AD by February 22, 2011. 

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: 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. 

SUPPLEMENTARY INFORMATION: 

Discussion 

The European Aviation Safety Agency 

(EASA), which is the Technical Agent 

for the Member States of the European 

Community, has issued EASA 

Emergency Airworthiness Directive 

2010–0239–E, dated November 19, 2010 

[Corrected November 23, 2010] (referred 

to after this as ‘‘the MCAI’’), to correct 

an unsafe condition for the specified 

products. The MCAI states: 

During a routine maintenance check on an 

A300–600 aeroplane, the operator found the 

pitch uncoupling unit installed at an 

incorrect location. The pitch uncoupling unit 

was inverted with the rod assembly. 

After a complete inspection of all A300– 

600 aeroplanes of its fleet, the operator 

identified the same incorrect installation on 

another aeroplane. 

Had this routine maintenance check, which 

was accomplished for other purposes, not 

been carried out, the incorrect installation 

could only have been detected during the 

accomplishment of the pitch uncoupling 

functional test. 

Note: Another maintenance task, the pitch 

uncoupling operational test, scheduled at 

intervals not to exceed 2,000 FH or 36 

months, whichever occurs first (MPD task 

273100–01–1), only validates the condition 

of the pitch uncoupling solenoid. 

This condition, if not detected and 

corrected, in combination with particular 

failure modes, could lead to loss of control 

of the aeroplane during the takeoff phase. 

For the reason described above, this AD 

requires a one time visual inspection, to 

detect any incorrect installation of the pitch 

uncoupling unit,and, depending on findings, 

to take corrective actions. 

This [EASA] AD was republished to correct 

the compliance time. 

Corrective actions include removing 

and re-installing the pitch uncoupling 

unit and rod assembly at the correction 

location and doing a functional test to 

verify correct operation. You may obtain 

further information by examining the 

MCAI in the AD docket. 

Relevant Service Information 

Airbus has issued A300–600 All 

Operators Telex 27A6068, Revision 01, 

dated November 18, 2010. 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. 

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 

An unsafe condition exists that 

requires the immediate adoption of this 

AD. The FAA has found that the risk to 

the flying public justifies waiving notice 

and comment prior to adoption of this 

rule because a pitch uncoupling unit 

was found to be installed at an incorrect 

location. The pitch uncoupling unit was 

inverted with the rod assembly. This 

condition, if not detected and corrected, 

in combination with other failure 

modes, could lead to loss of control of 

the airplane during the take-off phase. 

Therefore, we determined that notice 

and opportunity for public comment 

before issuing this AD are impracticable 

and that good cause exists for making 

this amendment effective in fewer than 

30 days. 

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–2010–1278; 

Directorate Identifier 2010–NM–260– 

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Federal Register / Vol. 76, No. 3 / Wednesday, January 5, 2011 / Rules and Regulations 443 

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 adding 

the following new AD: 

2011–01–13 Airbus: Amendment 39–16567. 

Docket No. FAA–2010–1278; Directorate 

Identifier 2010–NM–260–AD. 

Effective Date 

(a) This airworthiness directive (AD) 

becomes effective January 20, 2011. 

Affected ADs 

(b) None. 

Applicability 

(c) This AD applies to Airbus Model A300 

B4–601, B4–603, B4–620, B4–622, B4–605R, 

B4–622R, F4–605R, F4–622R, and C4–605R 

Variant F airplanes, certificated in any 

category, all serial numbers, except for 

airplanes on which the pitch uncoupling 

functional test has already been performed in 

service since new. 

Note 1: The pitch uncoupling functional 

test is described in Section 3.D.(2) of task 27– 

31–00, Page Block 501 of Airbus A300–600 

Aircraft Maintenance Manual (AMM) 

[Maintenance Planning Document (MPD) task 

273100–02–1]. 

Subject 

(d) Air Transport Association (ATA) of 

America Code 27: Flight Controls. 

Reason 

(e) The mandatory continued airworthiness 

information (MCAI) states: 

During a routine maintenance check on an 

A300–600 aeroplane, the operator found the 

pitch uncoupling unit installed at an 

incorrect location. The pitch uncoupling unit 

was inverted with the rod assembly. 

After a complete inspection of all A300– 

600 aeroplanes of its fleet, the operator 

identified the same incorrect installation on 

another aeroplane. 

* * * * * 

This condition, if not detected and 

corrected, in combination with particular 

failure modes, could lead to loss of control 

of the aeroplane during the takeoff phase. 

* * * * * 

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. 

Inspection, Re-Installation, and Functional 

Test 

(g) Within 30 days after the effective date 

of this AD, do a general visual inspection for 

correct location of the pitch uncoupling unit, 

in accordance with paragraph 4.2 of Airbus 

A300–600 All Operators Telex (AOT) 

27A6068, Revision 01, dated November 18, 

2010. If the pitch uncoupling unit is found 

inverted with the rod assembly, before 

further flight, remove and re-install the 

uncoupling unit and the rod assembly at 

their correct locations and do a functional 

test of the pitch uncoupling unit to verify 

correct operation, in accordance with 

paragraph 4.2 of Airbus A300–600 AOT 

27A6068, Revision 01, dated November 18, 

2010. 

FAA AD Differences 

Note 2: 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: 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. Information 

may be e-mailed to: 9-ANM-116-AMOCREQUESTS@faa.gov. 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 FAAapproved 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: A federal 

agency may not conduct or sponsor, and a 

person is not required to respond to, nor 

shall a person be subject to a penalty for 

failure to comply with a collection of 

information subject to the requirements of 

the Paperwork Reduction Act unless that 

collection of information displays a current 

valid OMB Control Number. The OMB 

Control Number for this information 

collection is 2120–0056. Public reporting for 

this collection of information is estimated to 

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444 Federal Register / Vol. 76, No. 3 / Wednesday, January 5, 2011 / Rules and Regulations 

be approximately 5 minutes per response, 

including the time for reviewing instructions, 

completing and reviewing the collection of 

information. All responses to this collection 

of information are mandatory. Comments 

concerning the accuracy of this burden and 

suggestions for reducing the burden should 

be directed to the FAA at: 800 Independence 

Ave., SW., Washington, DC 20591, Attn: 

Information Collection Clearance Officer, 

AES–200. 

Related Information 

(i) Refer to MCAI European Aviation Safety 

Agency Emergency Airworthiness Directive 

2010–0239–E, dated November 19, 2010 

[Corrected November 23, 2010]; and Airbus 

A300–600 AOT 27A6068, Revision 01, dated 

November 18, 2010; for related information. 

Material Incorporated by Reference 

(j) You must use Airbus A300–600 All 

Operators Telex 27A6068, Revision 01, dated 

November 18, 2010, 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 Airbus SAS—EAW 

(Airworthiness Office), 1 Rond Point Maurice 

Bellonte, 31707 Blagnac Cedex, France; 

telephone +33 5 61 93 36 96; fax +33 5 61 

93 44 51; e-mail: account.airwortheas@airbus.com; Internet http:// 

www.airbus.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. 

(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 

December 22, 2010. 

Jeffrey E. Duven, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2010–32995 Filed 1–4–11; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2010–1023 Directorate 

Identifier 2010–CE–055–AD; Amendment 

39–16557; AD 2011–01–04] 

RIN 2120–AA64 

Airworthiness Directives; Empresa 

Brasileira de Aeronautica S.A. 

(EMBRAER) Model EMB–500 Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Final rule. 

SUMMARY: We are adopting a new 

airworthiness directive (AD) for the 

products listed above. This AD results 

from mandatory continuing 

airworthiness information (MCAI) 

issued 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: 

It has been detected a short circuit in 

harness W101 due to its interference with the 

main door mechanism. Further analysis of 

the affected region has also revealed the 

possibility of chafing between the same 

harness and the oxygen tubing. The chafing 

of the wiring harness against the oxygen 

tubing could lead to a short circuit of the 

wiring harness and a subsequent fire in the 

airplane. 

Since this condition may occur in other 

airplanes of the same type and affects flight 

safety, a corrective action is required. Thus, 

sufficient reason exists to request compliance 

with this AD in the indicated time limit. 

We are issuing this AD to require 

actions to correct the unsafe condition 

on these products. 

DATES: This AD becomes effective 

February 9, 2011. 

On February 9, 2011, the Director of 

the Federal Register approved the 

incorporation by reference of certain 

publications listed in this AD. 

ADDRESSES: You may examine the AD 

docket on the Internet at http:// 

www.regulations.gov or in person at 

Document Management Facility, U.S. 

Department of Transportation, Docket 

Operations, M–30, West Building 

Ground Floor, Room W12–140, 1200 

New Jersey Avenue, SE., Washington, 

DC 20590. 

For service information identified in 

this AD, contact EMBRAER Empresa 

Brasileira de Aerona ́utica S.A., Phenom 

Maintenance Support, Av. Brig. Farina 

Lima, 2170, Sao Jose dos Campos—SP, 

CEP: 12227–901—PO Box: 38/2, 

BRASIL, telephone: ++55 12 3927–5383; 

fax: ++55 12 3927–2610; E-mail: 

reliability.executive@embraer.com.br; 

Internet: http://www.embraer.com.br. 

You may review copies of the 

referenced service information at the 

FAA, Small Airplane Directorate, 901 

Locust, Kansas City, Missouri 64106. 

For information on the availability of 

this material at the FAA, call 816–329– 

4148. 

FOR FURTHER INFORMATION CONTACT: Jim 

Rutherford, Aerospace Engineer, FAA, 

Small Airplane Directorate, 901 Locust, 

Room 301, Kansas City, Missouri 64106; 

telephone: (816) 329–4165; fax: (816) 

329–4090. 

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 October 15, 2010 (75 FR 

63422). That NPRM proposed to correct 

an unsafe condition for the specified 

products. The MCAI states: 

It has been detected a short circuit in 

harness W101 due to its interference with the 

main door mechanism. Further analysis of 

the affected region has also revealed the 

possibility of chafing between the same 

harness and the oxygen tubing. The chafing 

of the wiring harness against the oxygen 

tubing could lead to a short circuit of the 

wiring harness and a subsequent fire in the 

airplane. 

Since this condition may occur in other 

airplanes of the same type and affects flight 

safety, a corrective action is required. Thus, 

sufficient reason exists to request compliance 

with this AD in the indicated time limit. 

The MCAI requires installing clamps to 

the W101 wiring harness. 

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 

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 

WReier-Aviles on DSKGBLS3C1PROD with RULES