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

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 Ageˆncia 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. 

mstockstill on DSKH9S0YB1PROD with PROPOSALS

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 disabled 

equipment 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: 

mstockstill on DSKH9S0YB1PROD with PROPOSALS

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

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 

mstockstill on DSKH9S0YB1PROD with PROPOSALS