55230 Federal Register / Vol. 70, No. 182 / Wednesday, September 21, 2005 / Rules and Regulations 

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 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. 

We prepared a regulatory evaluation 

of the estimated costs to comply with 

this AD and placed it in the AD docket. 

See the ADDRESSES section for a location 

to examine the regulatory evaluation. 

List of Subjects in 14 CFR Part 39 

Aircraft, Air transportation, 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 Federal Aviation 

Administration (FAA) amends § 39.13 

by adding the following new 

airworthiness directive (AD): 

2005–19–14 Airbus: Amendment 39–14279. 

Docket No. FAA–2005–21189; 

Directorate Identifier 2005–NM–055–AD. 

Effective Date 

(a) This AD becomes effective October 26, 

2005. 

Affected ADs 

(b) None. 

Applicability 

(c) This AD applies to Airbus Model A318–

111 and –112 airplanes; A319–111, –112, 

–113, –114, –115, –131, –132, and –133 

airplanes; A320–111, –211, –212, –214, –231, 

–232, and –233 airplanes; and A321–111, 

–112, –131, –211 and –231 airplanes; 

certificated in any category; except airplanes 

that have received Airbus Modification 

31892 in production. 

Unsafe Condition 

(d) This AD was prompted by results of 

fuel system reviews conducted by the 

manufacturer. We are issuing this AD to 

prevent electrical arcing in the center fuel 

tank due to inadequate bonding, which could 

result in an explosion of the center fuel tank 

and consequent loss of the airplane. 

Compliance 

(e) 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 and Related Investigative and 

Corrective Actions 

(f) Within 58 months after the effective 

date of this AD: Modify the electrical 

bonding of all structures and systems 

installed inside the center fuel tank by 

accomplishing all of the actions in 

accordance with the Accomplishment 

Instructions of Airbus Service Bulletin A320–

28–1104, Revision 01, dated December 8, 

2004. 

Actions Accomplished According to 

Previous Issue of Service Bulletin 

(g) Actions done before the effective date 

of this AD in accordance with Airbus Service 

Bulletin A320–28–1104, dated December 2, 

2003, are acceptable for compliance with the 

corresponding requirements of paragraph (f) 

of this AD. 

Alternative Methods of Compliance 

(AMOCs) 

(h) The Manager, ANM–116, Transport 

Airplane Directorate, FAA, has the authority 

to approve AMOCs for this AD, if requested 

in accordance with the procedures found in 

14 CFR 39.19. 

Related Information 

(i) French airworthiness directive F–2005–

028, dated February 16, 2005, also addresses 

the subject of this AD. 

Material Incorporated by Reference 

(j) You must use Airbus Service Bulletin 

A320–28–1104, Revision 01, dated December 

8, 2004, to perform the actions that are 

required by this AD, unless the AD specifies 

otherwise. The Director of the Federal 

Register approved the incorporation by 

reference of this document in accordance 

with 5 U.S.C. 552(a) and 1 CFR part 51. 

Contact Airbus, 1 Rond Point Maurice 

Bellonte, 31707 Blagnac Cedex, France, for a 

copy of this service information. You may 

review copies at the Docket Management 

Facility, U.S. Department of Transportation, 

400 Seventh Street, SW., Room PL–401, 

Nassif Building, Washington, DC; on the 

Internet at http://dms.dot.gov; or at the 

National Archives and Records 

Administration (NARA). For information on 

the availability of this material at the NARA, 

call (202) 741–6030, or go to http:// 

www.archives.gov/federal-register/cfr/ibrlocations.html. 

Issued in Renton, Washington, on 

September 9, 2005. 

Ali Bahrami, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 05–18518 Filed 9–20–05; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2005–21087; Directorate 

Identifier 2005–NM–019–AD; Amendment 

39–14280; AD 2005–19–15] 

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: The FAA is superseding an 

existing airworthiness directive (AD), 

which applies to all BAE Systems 

(Operations) Limited (Jetstream) Model 

4101 airplanes. That AD currently 

requires operators to determine the 

number of flight cycles accumulated on 

each component of the main landing 

gear (MLG) and the nose landing gear 

(NLG), and to replace each component 

that reaches its life limit with a 

serviceable component. The existing AD 

also requires operators to revise the 

Airworthiness Limitations section (ALS) 

of the Instructions for Continued 

Airworthiness in the aircraft 

maintenance manual to reflect the new 

life limits. This new AD requires 

revising the ALS to incorporate 

extended and more restrictive life limits 

for structurally significant items. This 

AD is prompted by engineering analysis 

of fleet operations which resulted in 

more restrictive life limits. We are 

issuing this AD to prevent failure of 

certain structurally significant items, 

including the MLG and the NLG, which 

could result in reduced structural 

integrity of the airplane. 

DATES: This AD becomes effective 

October 26, 2005. 

Federal Register / Vol. 70, No. 182 / Wednesday, September 21, 2005 / Rules and Regulations 55231 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication listed in the AD 

as of October 26, 2005. 

On August 3, 2004 (69 FR 38816, June 

29, 2004), the Director of the Federal 

Register approved the incorporation by 

reference of BAE Systems (Operations) 

Limited Service Bulletin J41–05–001, 

Revision 2, dated March 15, 2002; BAE 

Systems (Operations) Limited Service 

Bulletin J41–05–001, Revision 3, dated 

January 9, 2004; and BAE Systems 

(Operations) Limited Service Bulletin 

J41–32–078, dated April 12, 2002. 

ADDRESSES: For service information 

identified in this AD, contact British 

Aerospace Regional Aircraft American 

Support, 13850 Mclearen Road, 

Herndon, Virginia 20171. 

Docket: The AD docket contains the 

proposed AD, comments, and any final 

disposition. You can examine the AD 

docket on the Internet at http:// 

dms.dot.gov, or in person at the Docket 

Management Facility office between 9 

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

Friday, except Federal holidays. The 

Docket Management Facility office 

(telephone (800) 647–5227) is located on 

the plaza level of the Nassif Building at 

the U.S. Department of Transportation, 

400 Seventh Street SW., room PL–401, 

Washington, DC. This docket number is 

FAA–2005–21087; the directorate 

identifier for this docket is 2005–NM–

019–AD. 

FOR FURTHER INFORMATION CONTACT: Dan 

Rodina, Aerospace Engineer, 

International Branch, ANM–116, FAA, 

Transport Airplane Directorate, 1601 

Lind Avenue, SW., Renton, Washington 

98055–4056; telephone (425) 227–2125; 

fax (425) 227–1149. 

SUPPLEMENTARY INFORMATION: The FAA 

proposed to amend part 39 of the 

Federal Aviation Regulations (14 CFR 

part 39) with an AD to supersede AD 

2004–13–07, amendment 39–13689 (69 

FR 38816, June 29, 2004). The existing 

AD applies to all BAE Systems 

(Operations) Limited (Jetstream) Model 

4101 airplanes. The proposed AD was 

published in the Federal Register on 

May 2, 2005 (70 FR 22615), to continue 

to require operators to determine the 

number of flight cycles accumulated on 

each component of the main landing 

gear (MLG) and nose landing gear 

(NLG), and to replace each component 

that reaches its life limit with a 

serviceable component. That action also 

proposed to require operators to revise 

the Airworthiness Limitations section 

(ALS) of the Instructions for Continued 

Airworthiness in the airplane 

maintenance manual (AMM) to 

incorporate extended and more 

restrictive life limits for structurally 

significant items. 

Comments 

We provided the public the 

opportunity to participate in the 

development of this AD. We have 

considered the comment that has been 

submitted on the proposed AD. The 

commenter supports the proposed AD. 

Explanation of Change to Applicability 

We have revised the applicability of 

the proposed AD to identify model 

designations as published in the most 

recent type certificate data sheet for the 

affected models. 

Explanation of Editorial Changes 

We have corrected the date of 

Revision 3 of BAE Systems (Operations) 

Limited Service Bulletin J41–05–001 in 

paragraph (f) of this AD, and the British 

airworthiness directive reference in 

paragraph (n) of this AD. 

Conclusion 

We have carefully reviewed the 

available data, including the comment 

that has been received, and determined 

that air safety and the public interest 

require adopting the AD with the 

changes described previously. We have 

determined that these changes will 

neither increase the economic burden 

on any operator nor increase the scope 

of the AD. 

Costs of Compliance 

This AD will affect about 57 airplanes 

of U.S. registry. 

For the actions that are required by 

AD 2004–13–07, and retained in this 

AD, it will take approximately 1 work 

hour per airplane to accomplish the 

required determination of the number of 

flight cycles, and 1 work hour per 

airplane to accomplish the required 

revision of the AMM. The average labor 

rate is $65 per work hour. Based on 

these figures, the estimated cost of the 

currently required actions for U.S. 

operators is $7,410, or $130 per 

airplane. 

The new revision of the AMM will 

take about 1 work hour per airplane, at 

an average labor rate of $65 per work 

hour. Based on these figures, the 

estimated cost of the new AMM revision 

specified in this AD for U.S. operators 

is $3,705, or $65 per airplane. 

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 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. 

We prepared a regulatory evaluation 

of the estimated costs to comply with 

this AD. See the ADDRESSES section for 

a location to examine the regulatory 

evaluation. 

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 

removing amendment 39–13689 (69 FR 

38816, June 29, 2004) and by adding the 

following new airworthiness directive 

(AD): 

55232 Federal Register / Vol. 70, No. 182 / Wednesday, September 21, 2005 / Rules and Regulations 

2005–19–15 BAE Systems (Operations) 

Limited (Formerly British Aerospace 

Regional Aircraft): Amendment 39–

14280. Docket No. FAA–2005–21087; 

Directorate Identifier 2005–NM–019–AD. 

Effective Date 

(a) This AD becomes effective October 26, 

2005. 

Affected ADs 

(b) This AD supersedes AD 2004–13–07. 

Applicability 

(c) This AD applies to all BAE Systems 

(Operations) Limited Model Jetstream 4101 

airplanes, certificated in any category. 

Note 1: This AD requires revisions to 

certain operator maintenance documents to 

include new inspections. Compliance with 

these inspections is required by 14 CFR 

91.403(c). For airplanes that have been 

previously modified, altered, or repaired in 

the areas addressed by these inspections, the 

operator may not be able to accomplish the 

inspections described in the revisions. In this 

situation, to comply with 14 CFR 91.403(c), 

the operator must request approval for an 

alternative method of compliance according 

to paragraph (m) of this AD. The request 

should include a description of changes to 

the required inspections that will ensure the 

continued damage tolerance of the affected 

structure. The FAA has provided guidance 

for this determination in Advisory Circular 

(AC) 25–1529. 

Unsafe Condition 

(d) This AD was prompted by engineering 

analysis of fleet operations which resulted in 

more restrictive life limits. We are issuing 

this AD to prevent failure of certain 

structurally significant items, including the 

main landing gear and the nose landing gear, 

which could result in reduced structural 

integrity of the airplane. 

Compliance 

(e) You are responsible for having the 

actions required by this AD performed within 

the compliance times specified, unless the 

actions have already been done. 

Restatement of Requirements of AD 2004–

13–07 

Determine Flight Cycles for Components 

(f) Within 90 days after August 3, 2004 (the 

effective date of AD 2004–13–07): Determine 

the number of flight cycles accumulated on 

each landing gear component listed in Table 

1 and Table 2 of the Accomplishment 

Instructions of BAE Systems (Operations) 

Limited Service Bulletin J41–32–078, dated 

April 12, 2002. If there are no records or 

incomplete records for any component, 

establish the number of flight cycles in 

accordance with the Accomplishment 

Instructions of BAE Systems (Operations) 

Limited Service Bulletin J41–05–001, 

Revision 2, dated March 15, 2002; or 

Revision 3, dated January 9, 2004. 

Note 2: BAE Systems (Operations) Limited 

Service Bulletin J41–32–078 refers to BAE 

Systems (Operations) J41 Service Information 

Leaflet 32–15, Issue 1, dated February 15, 

2002, as an additional source of service 

information for establishing the life limits of 

landing gear components and for tracking the 

accumulated life of each component. 

Replace Components 

(g) Except as provided by paragraph (h) of 

this AD, within 60 days after establishing the 

flight cycles per paragraph (f) of this AD: 

Replace any landing gear component that has 

reached the life limit determined by 

paragraph (f) of this AD, with a serviceable 

component per a method approved by either 

the Manager, International Branch, ANM–

116, Transport Airplane Directorate, FAA; or 

the Civil Aviation Authority (CAA) (or its 

delegated agent). Doing the actions in chapter 

32 of the Jetstream 4100 airplane 

maintenance manual (AMM) is one approved 

method. Thereafter, replace any component 

that reaches its life limit prior to the 

accumulation of the applicable number of 

flight cycles shown in Table 1 and Table 2 

of the Accomplishment Instructions of BAE 

Systems (Operations) Limited Service 

Bulletin J41–32–078, dated April 12, 2002. 

(h) Any component for which the total 

accumulated life cycles has not been 

established, or that has exceeded its life 

limit, but has not yet been replaced per 

paragraph (g) of this AD, must be replaced 

within 72 months after August 3, 2004, in 

accordance with BAE Systems (Operations) 

Limited Service Bulletin J41–32–078, dated 

April 12, 2002. 

Revise AMM 

(i) Within 30 days after August 3, 2004: 

Revise the Airworthiness Limitations section 

(ALS) of the Instructions for Continued 

Airworthiness of the Jetstream 4100 AMM to 

include the life limits of the components 

listed in Table 1 and Table 2 of the 

Accomplishment Instructions of BAE 

Systems (Operations) Limited Service 

Bulletin J41–32–078, dated April 12, 2002. 

This may be accomplished by inserting a 

copy of the service bulletin into the ALS of 

the Instructions for Continued Airworthiness 

until such time as a revision is issued. 

Thereafter, except as provided in paragraphs 

(m) and (l) of this AD, no alternative 

replacement times may be approved for any 

affected component. Once the AMM revision 

required by paragraph (l) of this AD is 

accomplished, the AMM revision required by 

this paragraph must be removed from the 

AMM. 

Parts Installation 

(j) As of August 3, 2004, no landing gear 

unit may be installed on any airplane unless 

the accumulated flight cycles of all 

components of that landing gear have been 

established per paragraph (f) of this AD, and 

any component that has exceeded its life 

limit has been replaced per paragraph (g) of 

this AD. 

Actions Accomplished Per Previous Issue of 

Service Bulletin 

(k) Calculations of total accumulated flight 

cycles accomplished per BAE Systems 

(Operations) Limited Service Bulletin J41–

05–001, Revision 1, dated April 10, 2001; or 

BAE Systems (Operations) Limited Service 

Bulletin J41–05–001, Revision 2, dated 

March 15, 2002; are considered acceptable 

for compliance with the corresponding action 

specified in this AD. 

New Requirements of This AD 

Revise AMM 

(l) Within 30 days after the effective date 

of this AD: Revise the ALS of the Instructions 

for Continued Airworthiness of the BAE 

Systems (Operations) Limited J41 AMM to 

include the life limits of the components 

listed in Chapter 05–10–10, Airworthiness 

Limitations—Description and Operation 

Section, Revision 23, dated February 15, 

2005, of the AMM. This may be 

accomplished by inserting a copy into the 

ALS of the Instructions for Continued 

Airworthiness. Thereafter, except as 

provided in paragraph (m) of this AD, no 

alternative replacement times may be 

approved for any affected component. Once 

this AMM revision is included, the AMM 

revision required by paragraph (i) of this AD 

must be removed from the AMM. 

Alternative Methods of Compliance (AMOCs) 

(m) The Manager, International Branch, 

ANM–116, has the authority to approve 

AMOCs for this AD, if requested in 

accordance with the procedures found in 14 

CFR 39.19. 

Related Information 

(n) British airworthiness directive G–2005–

0005, dated February 3, 2005, also addresses 

the subject of this AD. 

Material Incorporated by Reference 

(o) Unless otherwise specified in this AD, 

the actions shall be done in accordance with 

the service information listed in Table 1 of 

this AD. 

TABLE 1.—MATERIAL INCORPORATED BY REFERENCE

Service Information Revision level Date 

BAE Systems (Operations) Limited J41 Airplane Maintenance Manual ............ Revision 23 .......................................... February 15, 2005. 

BAE Systems (Operations) Limited Service Bulletin J41–05–001 ..................... Revision 2 ............................................ March 15, 2002. 

BAE Systems (Operations) Limited Service Bulletin J41–05–001 ..................... Revision 3 ............................................ January 9, 2004. 

BAE Systems (Operations) Limited Service Bulletin J41–32–078 ..................... Original ................................................. April 12, 2002. 

Federal Register / Vol. 70, No. 182 / Wednesday, September 21, 2005 / Rules and Regulations 55233 

(1) The Director of the Federal Register 

approves the incorporation by reference of 

Chapter 05–10–10 of the BAE Systems 

(Operations) Limited J41 Airplane 

Maintenance Manual, Revision 23, dated 

February 15, 2005, in accordance with 5 

U.S.C. 552(a) and 1 CFR part 51. 

(2) On August 3, 2004 (69 FR 38816, June 

29, 2004), the Director of the Federal Register 

approved the incorporation by reference of 

BAE Systems (Operations) Limited Service 

Bulletin J41–05–001, Revision 2, dated 

March 15, 2002; BAE Systems (Operations) 

Limited Service Bulletin J41–05–001, 

Revision 3, dated January 9, 2004; and BAE 

Systems (Operations) Limited Service 

Bulletin J41–32–078, dated April 12, 2002. 

(3) To get copies of the service information, 

contact British Aerospace Regional Aircraft 

American Support, 13850 Mclearen Road, 

Herndon, Virginia 20171. You may review 

copies at the Docket Management Facility, 

U.S. Department of Transportation, 400 

Seventh Street SW., room PL–401, Nassif 

Building, Washington, DC; on the Internet at 

http://dms.dot.gov; or at the National 

Archives and Records Administration 

(NARA). For information on the availability 

of this material at the 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 

September 9, 2005. 

Kalene C. Yanamura, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 05–18519 Filed 9–20–05; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2005–21861; Directorate 

Identifier 2005–NM–093–AD; Amendment 

39–14281; AD 2005–19–16] 

RIN 2120–AA64 

Airworthiness Directives; Airbus Model 

A320–111 Airplanes and Model A320–

200 Series Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Final rule. 

SUMMARY: The FAA is adopting a new 

airworthiness directive (AD) for certain 

Airbus Model A320–111 airplanes and 

Model A320–200 series airplanes. This 

AD requires installing a bonding strip 

between each of the two water scavenge 

jet pumps of the center fuel tank and the 

rear spar in section 21. This AD results 

from the results of fuel system reviews 

conducted by the manufacturer. We are 

issuing this AD to prevent an ignition 

source for fuel vapor in the wing, which 

could result in fire or explosion in the 

center wing fuel tank. 

DATES: This AD becomes effective 

October 26, 2005. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication listed in the AD 

as of October 26, 2005. 

ADDRESSES: You may examine the AD 

docket on the Internet at http:// 

dms.dot.gov or in person at the Docket 

Management Facility, U.S. Department 

of Transportation, 400 Seventh Street 

SW., Nassif Building, Room PL–401, 

Washington, DC. 

Contact Airbus, 1 Rond Point Maurice 

Bellonte, 31707 Blagnac Cedex, France, 

for service information identified in this 

AD. 

FOR FURTHER INFORMATION CONTACT: Dan 

Rodina, Aerospace Engineer, 

International Branch, ANM–116, FAA, 

Transport Airplane Directorate, 1601 

Lind Avenue, SW., Renton, Washington 

98055–4056; telephone (425) 227–2125; 

fax (425) 227–1149. 

SUPPLEMENTARY INFORMATION:

Examining the Docket 

You may examine the airworthiness 

directive (AD) docket on the Internet at 

http://dms.dot.gov or in person at the 

Docket Management Facility office 

between 9 a.m. and 5 p.m., Monday 

through Friday, except Federal holidays. 

The Docket Management Facility office 

(telephone (800) 647–5227) is located on 

the plaza level of the Nassif Building at 

the street address stated in the 

ADDRESSES section. 

Discussion 

The FAA issued a notice of proposed 

rulemaking (NPRM) to amend 14 CFR 

part 39 to include an AD that would 

apply to certain Airbus Model A320–

111 airplanes and Model A320–200 

series airplanes. That NPRM was 

published in the Federal Register on 

July 19, 2005 (70 FR 41350). That NPRM 

proposed to require installing a bonding 

strip between each of the two water 

scavenge jet pumps of the center fuel 

tank and the rear spar in section 21. 

Comments 

We provided the public the 

opportunity to participate in the 

development of this AD. We have 

considered the comment received. The 

commenter supports the NPRM. 

Conclusion 

We have carefully reviewed the 

available data, including the comment 

received, and determined that air safety 

and the public interest require adopting 

the AD as proposed. 

Costs of Compliance 

This AD will affect about 371 

airplanes of U.S. registry. The actions 

will take about 1 work hour per 

airplane, at an average labor rate of $65 

per work hour. The manufacturer will 

supply required parts at no charge. 

Based on these figures, the estimated 

cost of the AD for U.S. operators is 

$24,115, or $65 per airplane. 

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 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. 

We prepared a regulatory evaluation 

of the estimated costs to comply with 

this AD and placed it in the AD docket. 

See the ADDRESSES section for a location 

to examine the regulatory evaluation. 

List of Subjects in 14 CFR Part 39 

Air transportation, Aircraft, Aviation 

safety, Incorporation by reference, 

Safety.