### 8001 Federal Register / Vol. 75, No. 35 / Tuesday, February 23, 2010 / Proposed Rules

FAA AD Differences

Note 1: This AD differs from the MCAI and/or service information as follows:

Although EMBRAER Service Bulletins 145LEG–32–0032, Revision 02, dated February 17, 2009; and 145–32–0120, Revision 02, dated February 17, 2009; specify that no person may install on any airplane an LGEU having P/N 355–022–002 as of 30 months after the effective date of this AD, we have determined that no LGEU having P/N 355–022–002 with a S/N 1000 through 1999 inclusive may be installed as of 12 months after the effective date of this AD. Allowing installation of those serial numbers beyond 12 months would not address the identified unsafe condition and ensure an adequate level of safety. This difference has been coordinated with the Age ˆ ncia Nacional de
Aviac

 ̧ a  ̃ o Civil (ANAC).

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 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: 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 MCAI ANAC Airworthiness Directive 2009–01–01, effective January 8, 2009, as corrected by Brazilian Airworthiness Directive Errata, effective January 20, 2009; and Embraer Service Bulletins 145–32–0120, Revision 02, dated February 17, 2009; and 145LEG–32–0032, Revision 02, dated February 17, 2009; for related information. Issued in Renton, Washington, on February 16, 2010. Stephen P. Boyd, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service.
[FR Doc. 2010–3441 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–2010–0158; Directorate Identifier 2010–CE–006–AD]** 

**RIN 2120–AA64**

**Airworthiness Directives; Hawker Beechcraft Corporation (Type**  **Certificate No. A00010WI Previously Held by Raytheon Aircraft Company)**  **Model 390 Airplanes**

**AGENCY :**  Federal Aviation Administration (FAA), Department of Transportation (DOT).

**ACTION :**  Notice of proposed rulemaking (NPRM).

**SUMMARY :**  We propose to adopt a new airworthiness directive (AD) for certain Hawker Beechcraft Corporation Model 390 airplanes. This proposed AD would require you to inspect the essential bus lightning strike protection for proper installation of metal oxide varistor (MOV) and spark gap wiring. This proposed AD would also require you to rework the wiring as necessary to achieve the required lightning strike/ surge protection. This proposed AD results from a report that the wires to the MOV and spark gap were swapped. We are proposing this AD to detect and correct improper installation of the MOV and spark gap wiring, which could result in overload of the MOV in a lightning strike and allow electrical energy to continue to the essential bus and disable equipment that receives power from the essential bus. The disabled equipment could include the autopilot, anti-skid system, hydraulic indicator, spoiler system, pilot primary flight display, audio panel, or the #1 air data computer. This failure could lead to a significant increase in pilot workload during adverse operating conditions.

**DATES :**  We must receive comments on this proposed AD by April 9, 2010.

**ADDRESSES :**  Use one of the following addresses to comment on this proposed AD:

• 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 Hawker Beechcraft Corporation, 9709 East Central, Wichita, Kansas 67201; telephone: (316) 676–5034; fax: (316) 676–6614; Internet: https:// www.hawkerbeechcraft.com/ service

_support/pubs/.

**FOR FURTHER INFORMATION CONTACT :**  Kevin Schwemmer, Aerospace Engineer, FAA, Wichita Aircraft Certification Office (ACO), 1801 Airport Road, Room 100, Wichita, Kansas 67209; telephone:(316) 946–4174; fax: (316) 946–4107; email: kevin.schwemmer@faa.gov.

**SUPPLEMENTARY INFORMATION :** 
Comments Invited

We invite you to send any written relevant data, views, or arguments regarding this proposed AD. Send your comments to an address listed under the

**ADDRESSES** section. Include the docket number, ‘‘FAA–2010–0158; Directorate Identifier 2010–CE–006–AD ’’ at the beginning of your comments. We specifically invite comments on the overall regulatory, economic, environmental, and energy aspects of the proposed AD. We will consider all comments received by the closing date and may amend the proposed AD in light 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 concerning this proposed AD.

Discussion

We received a report that on a Hawker Beechcraft Corporation Model 390 airplane the wires to the MOV and spark gap were swapped. The swapped wires were discovered during an inspection following a lightning strike. The spark gap has a higher current carrying capability than the MOV and is designed to carry direct currents caused by a lightning strike. In the event of a lightning strike, the potential exists to overload the MOV and allow an electrical spike to pass through to the essential bus.


### 8002 Federal Register / Vol. 75, No. 35 / Tuesday, February 23, 2010 / Proposed Rules

This condition, if not corrected, could allow electrical energy to continue to the essential bus and disable equipment that receives power from the essential bus. The disabled equipment could include the autopilot, anti-skid system, hydraulic indicator, spoiler system, pilot primary flight display, audio panel, or the #1 air data computer. This failure could lead to a significant increase in pilot workload during adverse operating conditions.

Relevant Service Information

We have reviewed Hawker Beechcraft Mandatory Service Bulletin SB 24–3995, issued September 2009. The service information describes procedures for inspecting the essential bus lightning strike protection for proper installation of MOV and spark gap wiring. The service information also describes procedures for rework as necessary to achieve the required lightning strike/ surge protection. FAA’s Determination and Requirements of the Proposed AD

We are proposing this AD because we evaluated all information and determined the unsafe condition described previously is likely to exist or develop on other products of the same type design. This proposed AD would require you to inspect the essential bus lightning strike protection for proper installation of MOV and spark gap wiring. This proposed AD would also require you to rework the wiring as necessary to achieve the required lightning strike/surge protection.
Costs of Compliance

We estimate that this proposed AD would affect 170 airplanes in the U.S. registry.

We estimate the following costs to do the proposed inspection (includes any necessary follow-on action):

Labor cost Parts cost Total cost per airplane Total cost on U.S. operators

3 work-hours × $85 per hour = $255 .............................................................................. Not applicable ........... $255 $43,350

Warranty credit may be given to the extent specified in Hawker Beechcraft Mandatory Service Bulletin SB 24–3995, issued September 2009. 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. Examining the AD Docket

You may examine the AD docket that contains the proposed AD, the regulatory evaluation, any comments received, and other information 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 Docket Office (telephone (800) 647–5527) is located at the street address stated 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. 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 adding the following new AD:
Hawker Beechcraft Corporation (Type Certificate No. A00010WI Previously Held By Raytheon Aircraft Company): Docket No. FAA–2010–0158; Directorate Identifier 2010–CE–006–AD.

Comments Due Date

(a) We must receive comments on this airworthiness directive (AD) action by April 9, 2010.

Affected ADs

(b) None.
Applicability

(c) This AD applies to Model 390 airplanes, serial numbers RB–4 through RB–248, that are certificated in any category.
Subject

(d) Air Transport Association of America (ATA) Code 24: Electric Power.

Unsafe Condition

(e) This AD results from a report that the metal oxide varistor (MOV) and spark gap wiring of the essential bus lightning strike protection were swapped. We are issuing this AD to detect and correct improper installation of the MOV and spark gap wiring, which could result in overload of the MOV in a lightning strike and allow electrical energy to continue to the essential bus and disable equipment that receives power from the essential bus. The disabledequipment could include the autopilot, antiskid system, hydraulic indicator, spoiler system, pilot primary flight display, audio panel, or the #1 air data computer. This failure could lead to a significant increase in pilot workload during adverse operating conditions.
Compliance

(f) To address this problem, you must do the following, unless already done:


### 8003 Federal Register / Vol. 75, No. 35 / Tuesday, February 23, 2010 / Proposed Rules

Actions Compliance Procedures

(1) Inspect the essential bus lightning strike

protection for proper installation of MOV and spark gap wiring. Within the next 200 hours time-in-service after the effective date of this AD or within the next 12 months after the effective date of this AD, whichever occurs first. Follow Hawker Mandatory Service Bulletin SB 24–3995, issued September 2009.

(2) Where improper wiring installation is found,

rework the essential bus lightning strike wiring installation for the MOV and spark gap. Before further flight after the inspection in paragraph (f)(1) of this AD. Follow Hawker Mandatory Service Bulletin SB 24–3995, issued September 2009.

Alternative Methods of Compliance (AMOCs)

(g) The Manager, Wichita Aircraft Certification Office (ACO), 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: Kevin Schwemmer, Aerospace Engineer, FAA, Wichita Aircraft Certification Office (ACO), 1801 Airport Road, Room 100, Wichita, Kansas 67209; telephone: (316) 946–4174; fax: (316) 946–4107; e-mail: kevin.schwemmer@faa.gov. Before using any approved AMOC on any airplane to which the AMOC applies, notify your appropriate principal inspector (PI) in the FAA Flight Standards District Office (FSDO), or lacking a PI, your local FSDO.

Related Information

(h) To get copies of the service information referenced in this AD, contact Hawker Beechcraft Corporation, 9709 East Central, Wichita, Kansas 67201; telephone: (316) 676– 5034; fax: (316) 676–6614; Internet: https:// www.hawkerbeechcraft.com/service

_support/ pubs/. To view the AD docket, go to U.S. Department of Transportation, Docket Operations, M–30, West Building Ground Floor, Room W12–140, 1200 New Jersey Avenue, SE., Washington, DC 20590, or on the Internet at http://www.regulations.gov.

Issued in Kansas City, Missouri, on February 16, 2010. Kim Smith, Manager, Small Airplane Directorate, Aircraft Certification Service.
[FR Doc. 2010–3538 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–2010–0129; Directorate Identifier 2009–NM–245–AD]** 

**RIN 2120–AA64**

**Airworthiness Directives; Airbus A318, A319, A320, A321 Series 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: Several occurrences of loss of the AC [alternating current] BUS 1 have been reported which led in some instances to the loss of the AC ESS [essential] BUS and DC [direct current] ESS BUS and connected systems. The affected systems include multiple flight deck Display Units (Primary Flight Display, Navigation Display and Upper Electronic Centralised Aircraft Monitoring display). The loss of multiple display units, if not corrected expediently during a high workload period, potentially affects the capability of the flight crew and could contribute to a loss of situational awareness and consequent control of the aeroplane, which would constitute an unsafe condition.

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 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.

For service information identified in this proposed AD, contact Airbus, Airworthiness Office—EAS, 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.airworth-eas@airbus.com; Internet http://www.airbus.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 :**  Tim Dulin, Aerospace Engineer, International Branch, ANM–116, Transport Airplane Directorate, FAA, 1601 Lind Avenue, SW., Renton, Washington 98057–3356; telephone (425) 227–2141; 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

**ADDRESSES** section. Include ‘‘Docket No. FAA–2010–0129; Directorate Identifier 2009–NM–245–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 based on those comments.

We have lengthened the 30-day comment period for proposed ADs that address MCAI originated by aviation authorities of other countries to provide adequate time for interested parties to submit comments. The comment period for these proposed ADs is now typically 45 days, which is consistent with the comment period for domestic transport ADs.

We will post all comments we receive, without change, to http:// www.regulations.gov, including any