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 


dwashington3 on PRODPC61 with RULES
Federal Register / Vol. 73, No. 151 / Tuesday, August 5, 2008 / Rules and Regulations 45349 

with skin wrinkles found at two of the 

external crack locations. We are issuing 

this AD to detect and correct wrinkles 

and cracks in certain external skin 

panels of Section 48, which could join 

together and result in reduced structural 

integrity of support structure for the 

vertical and horizontal stabilizers and 

inability of the airplane to sustain limit 

loads. 

DATES: This AD is 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: For service information 

identified in this AD, contact Boeing 

Commercial Airplanes, P.O. Box 3707, 

Seattle, Washington 98124–2207. 

Examining the AD Docket 

You may examine the AD docket on 

the Internet at http:// 

www.regulations.gov; or in person at the 

Docket Management Facility between 9 

a.m. and 5 p.m., Monday through 

Friday, except Federal holidays. The AD 

docket contains this AD, the regulatory 

evaluation, any comments received, and 

other information. The address for the 

Docket Office (telephone 800–647–5527) 

is the 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 FURTHER INFORMATION CONTACT: 

Duong Tran, Aerospace Engineer, 

Airframe Branch, ANM–120S, FAA, 

Seattle Aircraft Certification Office, 

1601 Lind Avenue, SW., Renton, 

Washington 98057–3356; telephone 

(425) 917–6452; fax (425) 917–6590. 

SUPPLEMENTARY INFORMATION: 

Discussion 

We issued a notice of proposed 

rulemaking (NPRM) to amend 14 CFR 

part 39 to include an airworthiness 

directive (AD) that would apply to 

certain Boeing Model 777–200 series 

airplanes. That NPRM was published in 

the Federal Register on May 7, 2008 (73 

FR 25599). That NPRM proposed to 

require 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. 

Comments 

We gave the public the opportunity to 

participate in developing this AD. We 

considered the comment received. 

Boeing concurs with the NPRM. 

Conclusion 

We reviewed the relevant data, 

considered the comments received, and 

determined that air safety and the 

public interest require adopting the AD 

as proposed. 

Costs of Compliance 

We estimate that the inspections in 

this AD affect 13 airplanes of U.S. 

registry. We also estimate that it takes 

about 15 work-hours per product to 

comply with this AD. The average labor 

rate is $80 per work-hour. Based on 

these figures, we estimate the cost of 

this AD to the U.S. operators to be 

$15,600, or $1,200 per product, per 

inspection cycle. 

Authority for This Rulemaking 

Title 49 of the United States Code 

specifies the FAA’s authority to issue 

rules on aviation safety. Subtitle I, 

section 106, describes the authority of 

the FAA Administrator. ‘‘Subtitle VII: 

Aviation Programs,’’ describes in more 

detail the scope of the Agency’s 

authority. 

We are issuing this rulemaking under 

the authority described in ‘‘Subtitle VII, 

Part A, Subpart III, Section 44701: 

General requirements.’’ Under that 

section, Congress charges the FAA with 

promoting safe flight of civil aircraft in 

air commerce by prescribing regulations 

for practices, methods, and procedures 

the Administrator finds necessary for 

safety in air commerce. This regulation 

is within the scope of that authority 

because it addresses an unsafe condition 

that is likely to exist or develop on 

products identified in this rulemaking 

action. 

Regulatory Findings 

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 that this AD: 

(1) Is not a ‘‘significant regulatory 

action’’ under Executive Order 12866, 

(2) Is not a ‘‘significant rule’’ under 

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. 

You can find our regulatory 

evaluation and the estimated costs of 

compliance 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: 

2008–16–12 Boeing: Amendment 39–15630. 

Docket No. FAA–2008–0520; Directorate 

Identifier 2008–NM–018–AD. 

Effective Date 

(a) This airworthiness directive (AD) is 

effective September 9, 2008. 

Affected ADs 

(b) None. 

Applicability 

(c) This AD applies to Boeing Model 

777–200 series airplanes, certificated in any 

category; as identified in Boeing Alert 

Service Bulletin 777–53A0051, dated 

November 8, 2007. 

Unsafe Condition 

(d) This AD results from a report of cracks 

found in the external skin on the left and 

right sides of the Section 48 fuselage panel 

on two airplanes with skin wrinkles found at 

two of the external crack locations. We are 

issuing this AD to detect and correct wrinkles 

and cracks in certain external skin panels of 

Section 48, which could join together and 

result in reduced structural integrity of 

support structure for the vertical and 

horizontal stabilizers and inability of the 

airplane to sustain limit loads. 

Compliance 

(e) Comply with this AD within the 

compliance times specified, unless already 

done. 

Repetitive Inspections/Investigative and 

Corrective Actions 

(f) At the applicable compliance times 

specified in paragraph 1.E., ‘‘Compliance’’ of 

Boeing Alert Service Bulletin 777–53A0051, 

dated November 8, 2007; except as provided 

by paragraph (g) of this AD: Do the applicable 

inspections for any wrinkle of the external 

skin and for cracking at the fuselage 

bulkhead shear tie end fastener locations at 

Stations 2195.75, 2221.65, and 2245.70 of the 

Section 48 panel of the fuselage, between 


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45350 Federal Register / Vol. 73, No. 151 / Tuesday, August 5, 2008 / Rules and Regulations 

stringers 5 and 10 on the left and right sides; 

and do all the applicable investigative and 

corrective actions; by doing all of the 

applicable actions in accordance with the 

Accomplishment Instructions of the service 

bulletin, except as provided by paragraph (h) 

of this AD. Do all applicable investigative 

and corrective actions before further flight. 

Repeat the applicable inspections thereafter 

at the applicable intervals specified in 

paragraph 1.E. of the service bulletin. 

Exception to Compliance Times 

(g) Where Boeing Alert Service Bulletin 

777–53A0051, dated November 8, 2007, 

specifies counting the compliance time from 

‘‘* * * the date on this service bulletin,’’ this 

AD requires counting the compliance time 

from the effective date of this AD. 

Exception to Corrective Actions 

(h) If any damage beyond the repair limits 

specified in Boeing Alert Service Bulletin 

777–53A0051, dated November 8, 2007, is 

found during any inspection required by this 

AD, and the service bulletin specifies to 

contact Boeing for appropriate action: Before 

further flight, repair the crack using a method 

approved in accordance with the procedures 

specified in paragraph (i) of this AD. 

Alternative Methods of Compliance 

(AMOCs) 

(i)(1) The Manager, Seattle Aircraft 

Certification Office (ACO), FAA, ATTN: 

Duong Tran, Aerospace Engineer, Airframe 

Branch, ANM–120S, FAA, 1601 Lind 

Avenue, SW., Renton, Washington 98057–

3356; telephone (425) 917–6452; fax (425) 

917–6590 has the authority to approve 

AMOCs for this AD, if requested using the 

procedures found in 14 CFR 39.19. 

(2) To request a different method of 

compliance or a different compliance time 

for this AD, follow the procedures in 14 CFR 

39.19. Before using any approved AMOC on 

any airplane to which the AMOC applies, 

notify your appropriate principal inspector 

(PI) in the FAA Flight Standards District 

Office (FSDO), or lacking a PI, your local 

FSDO. 

(3) An AMOC that provides an acceptable 

level of safety may be used for any repair 

required by this AD, if it is approved by an 

Authorized Representative for the Boeing 

Commercial Airplanes Delegation Option 

Authorization Organization who has been 

authorized by the Manager, Seattle ACO, to 

make those findings. For a repair method to 

be approved, the repair must meet the 

certification basis of the airplane. 

Material Incorporated by Reference 

(j) You must use Boeing Alert Service 

Bulletin 777–53A0051, dated November 8, 

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 Boeing Commercial 

Airplanes, P.O. Box 3707, Seattle, 

Washington 98124–2207. 

(3) You may review copies of the service 

information incorporated by reference 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/ 

code_of_federal_regulations/ 

ibr_locations.html. 

Issued in Renton, Washington, on July 23, 

2008. 

Ali Bahrami, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. E8–17749 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–2008–0413; Directorate 

Identifier 2008–NM–003–AD; Amendment 

39–15631; AD 2008–16–13] 

RIN 2120–AA64 

Airworthiness Directives; Boeing 

Model 737–600, –700, –700C, –800, 

–900, and –900ER Series Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule. 

SUMMARY: We are adopting a new 

airworthiness directive (AD) for certain 

Boeing Model 737–600, –700, –700C, 

–800, –900, and –900ER series 

airplanes. This AD requires replacing 

the pushrods for the left and right 

elevator tab control mechanisms with 

new, improved pushrods. This AD 

results from a report of a rod end 

fracture on a rudder power control unit 

(PCU) control rod, which is similar to 

the ones used for the elevator tab 

pushrods. Analysis revealed that the 

fractured rod end had an incorrect 

hardness, which had probably occurred 

during the manufacture of the control 

rod. We are issuing this AD to prevent 

fracture of the elevator tab pushrod 

ends, which could result in excessive 

in-flight vibrations of the elevator tab, 

possible loss of the elevator tab, and 

consequent loss of controllability of the 

airplane. 

DATES: This AD is 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: For service information 

identified in this AD, contact Boeing 

Commercial Airplanes, P.O. Box 3707, 

Seattle, Washington 98124–2207. 

Examining the AD Docket 

You may examine the AD docket on 

the Internet at http:// 

www.regulations.gov; or in person at the 

Docket Management Facility between 9 

a.m. and 5 p.m., Monday through 

Friday, except Federal holidays. The AD 

docket contains this AD, the regulatory 

evaluation, any comments received, and 

other information. The address for the 

Docket Office (telephone 800–647–5527) 

is the 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 FURTHER INFORMATION CONTACT: 

Tamara Anderson, Aerospace Engineer, 

Airframe Branch, ANM–120S, FAA, 

Seattle Aircraft Certification Office, 

1601 Lind Avenue, SW., Renton, 

Washington 98057–3356; telephone 

(425) 917–6421; fax (425) 917–6590. 

SUPPLEMENTARY INFORMATION: 

Discussion 

We issued a notice of proposed 

rulemaking (NPRM) to amend 14 CFR 

part 39 to include an airworthiness 

directive (AD) that would apply to 

certain Boeing Model 737–600, –700, 

–700C, –800, –900, and –900ER series 

airplanes. That NPRM was published in 

the Federal Register on April 24, 2008 

(73 FR 22090). That NPRM proposed to 

require replacing the pushrods for the 

left and right elevator tab control 

mechanisms with new, improved 

pushrods. 

Comments 

We gave the public the opportunity to 

participate in developing this AD. We 

considered the two comments received. 

Boeing concurs with the contents of the 

NPRM, and Continental Airlines has no 

issues with the NPRM. 

Conclusion 

We reviewed the relevant data, 

considered the comments received, and 

determined that air safety and the 

public interest require adopting the AD 

as proposed. 

Costs of Compliance 

We estimate that this AD affects 715 

airplanes of U.S. registry. We also 

estimate that it takes about 4 work-hours 

per product to comply with this AD. 

The average labor rate is $80 per workhour. Required parts cost about $8,036 

per product. Based on these figures, we 

estimate the cost of this AD to the U.S. 

operators to be $5,974,540, or $8,356 per 

product. 


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