45346 Federal Register / Vol. 73, No. 151 / Tuesday, August 5, 2008 / Rules and Regulations 

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. 

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 the NPRM, 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. 

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: 

2008–16–08 Dassault Aviation: 

Amendment 39–15626. Docket No. 

FAA–2008–0557; Directorate Identifier 

2007–NM–364–AD. 

Effective Date 

(a) This airworthiness directive (AD) 

becomes effective September 9, 2008. 

Affected ADs 

(b) None. 

Applicability 

(c) This AD applies to Dassault Model 

Falcon 2000EX airplanes from serial number 

1 to 107 inclusive, certificated in any 

category; which have not been modified by 

Dassault Service Bulletin (SB) F2000EX–141. 

Subject 

(d) Air Transport Association (ATA) of 

America Code 24: Electrical Power. 

Reason 

(e) The mandatory continuing 

airworthiness information (MCAI) states: 

During approach, a Falcon 2000EX 

operator experienced a temporary loss of the 

4 Electronic Flight Instrumentation System 

(EFIS) display units followed by a 

consecutive restart of the avionics. During 

initial investigation, a loose connection on 

the DC load distribution system was 

discovered and determined to be the root 

cause of this event. However, further analysis 

pointed out that large electrical transients on 

the essential bus bar may possibly cause 

simultaneous and temporary power shortage 

on both sides of the electrical system. 

This Airworthiness Directive (AD) requires 

a wiring modification of the GCUs (Generator 

Control Units) to increase the electrical 

system robustness. This action is necessary to 

prevent a momentary loss of data on the EFIS 

screens, which could lead to the pilot’s loss 

of situational awareness during initial climb 

or approach/landing, and possibly result in 

reduced control of the airplane. This action 

is intended to address the identified unsafe 

condition. 

Actions and Compliance 

(f) Unless already done, do the following 

actions. 

(1) Within 13 months after the effective 

date of this AD, modify the GCU electrical 

wiring as instructed in the Accomplishment 

Instructions of Dassault Service Bulletin 

F2000EX–141, Revision 1, dated November 

26, 2007. 

(2) Actions done prior to the effective date 

of this AD according to Dassault Service 

Bulletin F2000EX–141, dated February 16, 

2007, are acceptable for compliance with the 

corresponding requirements of this AD. 

FAA AD Differences 

Note: This AD differs from the MCAI and/ 

or service information as follows: No 

differences. 

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: Tom Rodriguez, 

Aerospace Engineer, International Branch, 

ANM–116, Transport Airplane Directorate, 

FAA, 1601 Lind Avenue, SW., Renton, 

Washington 98057–3356; telephone (425) 

227–1137; fax (425) 227–1149. 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. 

(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, 

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 European Aviation 

Safety Agency Airworthiness Directive 2007–

0290, dated November 26, 2007; and Dassault 

Service Bulletin F2000EX–141, Revision 1, 

dated November 26, 2007; for related 

information. 

Material Incorporated by Reference 

(i) You must use Dassault Service Bulletin 

F2000EX–141, Revision 1, dated November 

26, 2007, 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 Dassault Falcon Jet, P.O. Box 

2000, South Hackensack, New Jersey 07606. 

(3) You may review copies at the FAA, 

Transport Airplane Directorate, 1601 Lind 

Avenue, SW., Renton, Washington; or 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/cfr/ibrlocations.html. 

Issued in Renton, Washington, on July 23, 

2008. 

Ali Bahrami, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. E8–17746 Filed 8–4–08; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2008–0541; Directorate 

Identifier 2008–NM–063–AD; Amendment 

39–15624; AD 2008–16–06] 

RIN 2120–AA64 

Airworthiness Directives; BAE 

Systems (Operations) Limited 

(Jetstream) Model 4101 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) 

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: 

Resulting from the assessment of fuel tank 

wiring installations required by SFAR 88 

(Special Federal Aviation Regulation 88) and 

equivalent JAA/EASA (Joint Aviation 


dwashington3 on PRODPC61 with RULES
Federal Register / Vol. 73, No. 151 / Tuesday, August 5, 2008 / Rules and Regulations 45347 

Authorities/European Aviation Safety 

Agency) policy, BAE Systems identified two 

features in the Jetstream 4100 where the need 

for design changes was apparent. * * * 

Insufficient or defective bonding in the fuel 

tank area, if not corrected, could lead to 

ignition of fuel vapours and subsequent fuel 

tank explosion. 

* * * * * 

We are issuing this AD to require 

actions to correct the unsafe condition 

on these products. 

DATES: This AD becomes effective 

September 9, 2008. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication listed in this AD 

as of September 9, 2008. 

ADDRESSES: You may examine the AD 

docket on the Internet at http:// 

www.regulations.gov or in person at the 

U.S. Department of Transportation, 

Docket Operations, M–30, West 

Building Ground Floor, Room W12–140, 

1200 New Jersey Avenue, SE., 

Washington, DC. 

FOR FURTHER INFORMATION CONTACT: 

Todd Thompson, Aerospace Engineer, 

International Branch, ANM–116, 

Transport Airplane Directorate, FAA, 

1601 Lind Avenue, SW., Renton, 

Washington 98057–3356; telephone 

(425) 227–1175; fax (425) 227–1149. 

SUPPLEMENTARY INFORMATION: 

Discussion 

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 May 13, 2008 (73 FR 27477). 

That NPRM proposed to correct an 

unsafe condition for the specified 

products. The MCAI states: 

Resulting from the assessment of fuel tank 

wiring installations required by SFAR 88 

(Special Federal Aviation Regulation 88) and 

equivalent JAA/EASA (Joint Aviation 

Authorities/European Aviation Safety 

Agency) policy, BAE Systems identified two 

features in the Jetstream 4100 where the need 

for design changes was apparent. One of 

these is addressed by Service Bulletin (SB) 

J41–28–013 which introduces additional 

bonding leads between pipes, structure and 

various components to improve the electrical 

bond paths within the fuel tank areas. This 

design change is identified by modification 

number JM41659. Additionally, SB J41–28–

013 provides instructions to inspect the 

existing bonding leads, to replace any 

defective leads and to examine all fuel 

system pipe runs in the wings to ensure 

appropriate clearances are maintained. 

Insufficient or defective bonding in the fuel 

tank area, if not corrected, could lead to 

ignition of fuel vapours and subsequent fuel 

tank explosion. 

For the reason stated above, this EASA 

Airworthiness Directive (AD) requires the 

installation of additional bonding leads, 

inspection [for defects] of existing bonding 

leads and [for clearance of] all fuel system 

pipe runs in the wings and follow-on 

corrective actions, as necessary. 

Corrective actions include replacing any 

defective bonding leads and adjusting 

clearances of the fuel system pipe runs. 

You may obtain further information by 

examining the MCAI in the AD docket. 

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 

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 our FAA 

policies. Any such differences are 

highlighted in a NOTE within the AD. 

Costs of Compliance 

We estimate that this AD will affect 

about 7 products of U.S. registry. We 

also estimate that it will take about 80 

work-hours per product to comply with 

the basic requirements of this AD. The 

average labor rate is $80 per work-hour. 

Required parts will cost about $1,700 

per product. Where the service 

information lists required parts costs 

that are covered under warranty, we 

have assumed that there will be no 

charge for these parts. As we do not 

control warranty coverage for affected 

parties, some parties may incur costs 

higher than estimated here. Based on 

these figures, we estimate the cost of 

this AD to the U.S. operators to be 

$56,700, or $8,100 per product. 

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. 

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 the NPRM, 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. 

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, 


dwashington3 on PRODPC61 with RULES
45348 Federal Register / Vol. 73, No. 151 / Tuesday, August 5, 2008 / Rules and Regulations 

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: 

2008–16–06 BAE Systems (Operations) 

Limited (Formerly British Aerospace 

Regional Aircraft): Amendment 39–

15624. Docket No. FAA–2008–0541; 

Directorate Identifier 2008–NM–063–AD. 

Effective Date 

(a) This airworthiness directive (AD) 

becomes effective September 9, 2008. 

Affected ADs 

(b) None. 

Applicability 

(c) This AD applies to all BAE Systems 

(Operations) Limited Model Jetstream 4101 

airplanes, certificated in any category, all 

serial numbers. 

Subject 

(d) Air Transport Association (ATA) of 

America Code 28: Fuel. 

Reason 

(e) The mandatory continuing 

airworthiness information (MCAI) states: 

Resulting from the assessment of fuel tank 

wiring installations required by SFAR 88 

(Special Federal Aviation Regulation 88) and 

equivalent JAA/EASA (Joint Aviation 

Authorities/European Aviation Safety 

Agency) policy, BAE Systems identified two 

features in the Jetstream 4100 where the need 

for design changes was apparent. One of 

these is addressed by Service Bulletin (SB) 

J41–28–013 which introduces additional 

bonding leads between pipes, structure and 

various components to improve the electrical 

bond paths within the fuel tank areas. This 

design change is identified by modification 

number JM41659. Additionally, SB J41–28–

013 provides instructions to inspect the 

existing bonding leads, to replace any 

defective leads and to examine all fuel 

system pipe runs in the wings to ensure 

appropriate clearances are maintained. 

Insufficient or defective bonding in the fuel 

tank area, if not corrected, could lead to 

ignition of fuel vapours and subsequent fuel 

tank explosion. 

For the reason stated above, this EASA 

Airworthiness Directive (AD) requires the 

installation of additional bonding leads, 

inspection [for defects] of existing bonding 

leads and [for clearance of] all fuel system 

pipe runs in the wings and follow-on 

corrective actions, as necessary. 

Corrective actions include replacing any 

defective bonding leads and adjusting 

clearances of the fuel system pipe runs. 

Actions and Compliance 

(f) Within 24 months after the effective 

date of this AD, unless already done, do the 

following actions. 

(1) Inspect the bonding leads between ribs 

1 and 9, and between ribs 16 and 19, in the 

left-hand (LH) and right-hand (RH) wings in 

accordance with paragraph 2.B.(2) of the 

Accomplishment Instructions of BAE 

Systems (Operations) Limited Service 

Bulletin J41–28–013, Revision 1, dated 

January 10, 2008; and, before next flight, 

replace all defective bonding leads with 

airworthy parts in accordance with the 

service bulletin. 

(2) Inspect all fuel system pipe runs inside 

the LH and RH wings in accordance with 

paragraph 2.B.(3) of the Accomplishment 

Instructions of BAE Systems (Operations) 

Limited Service Bulletin J41–28–013, 

Revision 1, dated January 10, 2008; and, if 

incorrect clearances are found, before next 

flight, adjust clearances in accordance with 

the service bulletin. 

(3) Install additional electrical bonding of 

components within the LH and RH wings in 

accordance with paragraphs 2.B.(4) to 

2.B.(15) of the Accomplishment Instructions 

of BAE Systems (Operations) Limited Service 

Bulletin J41–28–013, Revision 1, dated 

January 10, 2008. 

FAA AD Differences 

Note: This AD differs from the MCAI and/ 

or service information as follows: No 

differences. 

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: Todd Thompson, 

Aerospace Engineer, International Branch, 

ANM–116, Transport Airplane Directorate, 

FAA, 1601 Lind Avenue, SW., Renton, 

Washington 98057–3356; telephone (425) 

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

any approved AMOC on any airplane to 

which the AMOC applies, notify your 

appropriate principal inspector (PI) in the 

FAA Flight Standards District Office (FSDO), 

or lacking a PI, your local FSDO. 

(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, 

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 2008–0040, dated February 27, 

2008; and BAE Systems (Operations) Limited 

Service Bulletin J41–28–013, Revision 1, 

dated January 10, 2008; for related 

information. 

Material Incorporated by Reference 

(i) You must use BAE Systems (Operations) 

Limited Service Bulletin J41–28–013, 

Revision 1, dated January 10, 2008, 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 British Aerospace Regional 

Aircraft American Support, 13850 Mclearen 

Road, Herndon, Virginia 20171. 

(3) You may review copies at the FAA, 

Transport Airplane Directorate, 1601 Lind 

Avenue, SW., Renton, Washington; or 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/cfr/ibrlocations.html. 

Issued in Renton, Washington, on July 23, 

2008. 

Ali Bahrami, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. E8–17621 Filed 8–4–08; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2008–0520; Directorate 

Identifier 2008–NM–018–AD; Amendment 

39–15630; AD 2008–16–12] 

RIN 2120–AA64 

Airworthiness Directives; Boeing 

Model 777–200 Series Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule. 

SUMMARY: We are adopting a new 

airworthiness directive (AD) for certain 

Boeing Model 777–200 series airplanes. 

This AD requires repetitive inspections 

for any wrinkle in certain external skin 

panels, and for cracking at the fuselage 

bulkhead shear tie end fastener 

locations at certain stations of Section 

48 of the fuselage; and doing related 

investigative and corrective actions if 

necessary. This AD results from a report 

of cracks found in the external skin on 

the left and right sides of the Section 48 

panel of the fuselage on two airplanes 


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