Federal Register / Vol. 70, No. 196 / Wednesday, October 12, 2005 / Rules and Regulations 59233 

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): 

2005–20–34 BAE Systems (Operations) 

Limited (Formerly British Aerospace 

Regional Aircraft): Amendment 39–

14331. Docket No. FAA–2005–22625; 

Directorate Identifier 2003–NM–213–AD. 

Effective Date 

(a) This AD becomes effective October 27, 

2005. 

Affected ADs 

(b) None. 

Applicability 

(c) This AD applies to BAE Systems 

(Operations) Limited Model HS 748 series 2A 

and series 2B airplanes, certificated in any 

category, with batteries installed in the 

nosecone. 

Unsafe Condition 

(d) This AD results from an accident in 

which the nose landing leg, together with the 

pintle webs, detached from the airplane. As 

a result, the battery earth return cables were 

severed from their earth posts. We are issuing 

this AD to prevent loss of safety critical 

services including fuel shut-off and nacelle 

fire extinguishing services. 

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. 

Battery Earth Post Relocation 

(f) Within 120 days after the effective date 

of this AD, relocate the battery earth posts, 

in accordance with the Accomplishment 

Instructions of BAE Systems (Operations) 

Limited Service Bulletin HS748–24–131, 

Revision 1, dated June 16, 2003. 

Alternative Methods of Compliance 

(AMOCs) 

(g)(1) The Manager, International Branch, 

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. 

(2) Before using any AMOC approved in 

accordance with 14 CFR 39.19 on any 

airplane to which the AMOC applies, notify 

the appropriate principal inspector in the 

FAA Flight Standards Certificate Holding 

District Office. 

Related Information 

(h) British airworthiness directive 006–01–

003 also addresses the subject of this AD. 

Material Incorporated by Reference 

(i) You must use BAE Systems (Operations) 

Limited Service Bulletin HS748–24–131, 

Revision 1, dated June 16, 2003, to perform 

the actions that are required by this AD, 

unless the AD specifies otherwise. BAE 

Systems (Operations) Limited Service 

Bulletin HS748–24–131, Revision 1, dated 

June 16, 2003, contains the following 

effective pages: 

Page number Revision level 

shown on page 

Date shown on 

page 

1–12, 14 ........................................................................................................................................................ 1 ....................... June 16, 2003. 

13 .................................................................................................................................................................. Original ............. January 20, 2003. 

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 British 

Aerospace Regional Aircraft American 

Support, 13850 Mclearen Road, Herndon, 

Virginia 20171, 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/code_of_federal_regulations/ 

ibr_locations.html. 

Issued in Renton, Washington, on 

September 28, 2005. 

Kalene C. Yanamura, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 05–20068 Filed 10–11–05; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2005–22614; Directorate 

Identifier 2005–NM–035–AD; Amendment 

39–14324; AD 2005–20–27] 

RIN 2120–AA64 

Airworthiness Directives; Airbus Model 

A340–211, –212, –311, and –312 

Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Final rule; request for 

comments. 

SUMMARY: The FAA is adopting a new 

airworthiness directive (AD) for certain 

Airbus Model A340–211, –212, –311, 

and –312 airplanes. This AD requires an 

initial rotating probe inspection and 

initial and repetitive ultrasonic 

inspections for discrepancies of the first 

fastener hole of the horizontal flange of 

the keel beam on previously modified 

airplanes, installation of new fasteners, 

and corrective action if necessary. This 

AD results from a report that certain 

inspections done before accomplishing 

the modification of the lower keel beam 

fitting and forward lower shell 

connection, revealed cracking that was 

outside the modification limits specified 

in the service bulletin; the cracking was 

repaired by installing a titanium 

doubler. We are issuing this AD to find 

and fix discrepancies of the fastener 

holes of the horizontal flange of the keel 

beam, which could result in reduced 

structural integrity of the fuselage. 

DATES: This AD becomes effective 

October 27, 2005. 

The Director of the Federal Register 

approved the incorporation by reference 

of certain publications listed in the AD 

as of October 27, 2005. 

We must receive comments on this 

AD by December 12, 2005. 

ADDRESSES: Use one of the following 

addresses to submit comments on this 

AD. 

• DOT Docket Web site: Go to http:// 

dms.dot.gov and follow the instructions 

for sending your comments 

electronically. 

• Government-wide rulemaking web 

site: Go to http://www.regulations.gov 

and follow the instructions for sending 

your comments electronically. 

• Mail: Docket Management Facility; 

U.S. Department of Transportation, 400 

Seventh Street SW., Nassif Building, 

room PL–401, Washington, DC 20590. 

• Fax: (202) 493–2251. 

59234 Federal Register / Vol. 70, No. 196 / Wednesday, October 12, 2005 / Rules and Regulations 

• Hand Delivery: room PL–401 on the 

plaza level of the Nassif Building, 400 

Seventh Street SW., Washington, DC, 

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

through Friday, except Federal holidays. 

Contact Airbus, 1 Rond Point Maurice 

Bellonte, 31707 Blagnac Cedex, France, 

for service information identified in this 

AD. 

FOR FURTHER INFORMATION CONTACT: Tim 

Backman, Aerospace Engineer, 

International Branch, ANM–116, FAA, 

Transport Airplane Directorate, 1601 

Lind Avenue, SW., Renton, Washington 

98055–4056; telephone (425) 227–2797; 

fax (425) 227–1149. 

SUPPLEMENTARY INFORMATION: 

Discussion 

The Direction Ge ́ne ́rale de l’Aviation 

Civile (DGAC), which is the 

airworthiness authority for France, 

notified us that an unsafe condition may 

exist on certain Airbus Model A340–

211, –212, –311, and –312 airplanes. 

The DGAC advises that certain 

inspections done before accomplishing 

the modification specified in Airbus 

Service Bulletin A340–57–4036 (Airbus 

Modification 43577), Revision 05, dated 

March 14, 2000, revealed cracking that 

was outside the modification limits 

specified in that service bulletin. The 

cracking was repaired by installing a 

titanium doubler using certain repair 

drawings. Subsequently, a detailed 

structural analysis was done on the 

repaired airplanes. It was determined by 

the manufacturer that a specific 

inspection program is necessary for the 

repaired airplanes in order to maintain 

structural integrity. Cracking of the 

fastener holes of the horizontal flange of 

the keel beam could result in reduced 

structural integrity of the fuselage. 

Relevant Service Information 

Airbus has issued Service Bulletin 

A340–57–4087, dated November 21, 

2003. The service bulletin describes 

procedures for an initial rotating probe 

inspection and initial and repetitive 

ultrasonic inspections for discrepancies 

(cracking, out-of-tolerance fastener 

holes, and fastener damage) of the first 

fastener hole of the horizontal flange of 

the keel beam. If no cracking is found 

during the rotating probe inspection, the 

service bulletin describes procedures for 

installation of a new fastener and 

determining if the fastener hole is outof-tolerance. The corrective action for 

any out-of-tolerance hole includes 

reaming any out-of-tolerance fastener 

holes to oversize and installing 

oversized fasteners. The service bulletin 

also describes procedures for repetitive 

follow-on ultrasonic inspections for 

cracking, and contacting Airbus for 

repair instructions if cracking is found. 

Accomplishing the actions specified in 

the service information is intended to 

adequately address the unsafe 

condition. The DGAC mandated the 

service information and issued French 

airworthiness directive F–2005–007, 

dated January 5, 2005, to ensure the 

continued airworthiness of these 

airplanes in France. 

The service bulletin also specifies to 

contact the manufacturer for disposition 

of certain repair conditions and report 

inspection findings to the manufacturer. 

The service bulletin refers to Airbus 

Service Bulletin A340–57–4036, 

Revision 05, dated March 14, 2000, as 

the source of service information for 

accomplishing Airbus Modification 

43577. The modification was previously 

accomplished on all airplanes affected 

by this AD. 

FAA’s Determination and Requirements 

of This AD 

These airplane models are 

manufactured in France and are type 

certificated for operation in the United 

States under the provisions of section 

21.29 of the Federal Aviation 

Regulations (14 CFR 21.29) and the 

applicable bilateral airworthiness 

agreement. Pursuant to this bilateral 

airworthiness agreement, the DGAC has 

kept the FAA informed of the situation 

described above. We have examined the 

DGAC’s findings, evaluated all pertinent 

information, and determined that we 

need to issue an AD for products of this 

type design that are certificated for 

operation in the United States. 

Therefore, we are issuing this AD to 

find and fix discrepancies of the 

fastener holes of the horizontal flange of 

the keel beam, which could result in 

reduced structural integrity of the 

fuselage. This AD requires 

accomplishing the actions specified in 

Service Bulletin A340–57–4087, 

described previously, except as 

discussed under ‘‘Difference Between 

this AD, the French Airworthiness 

Directive, and Service Bulletin A340–

57–4087.’’

Difference Between This AD, the French 

Airworthiness Directive, and Service 

Bulletin A340–57–4087 

The French airworthiness directive 

and the service bulletin specify 

contacting the manufacturer for 

disposition of certain repair conditions; 

this AD requires the repair of those 

conditions to be accomplished per a 

method approved by either the FAA or 

the DGAC (or its delegated agent). In 

light of the type of repair that would be 

required to address the identified unsafe 

condition, and in consonance with 

existing bilateral airworthiness 

agreements, the FAA has determined 

that, for this AD, a repair approved by 

either the FAA or the DGAC (or its 

delegated agent) would be acceptable for 

compliance with this AD. 

Although the French airworthiness 

directive allows for use of the 

procedures specified in Airbus 

Technical Disposition F57D03012810 or 

582.0651/2002 for accomplishing the 

first rotating probe inspection, this AD 

does not allow for those documents to 

be used. This difference has been 

coordinated with the DGAC. 

Clarification of Compliance Time 

The service bulletin and French 

airworthiness directive do not provide a 

compliance time for the initial 

ultrasonic inspection if no cracking is 

found during the rotating probe 

inspection; however, this AD requires 

that the inspection be done within 1,480 

flight cycles or 7,400 flight hours after 

accomplishing the one-time rotating 

probe inspection. 

Costs of Compliance 

None of the airplanes affected by this 

action are on the U.S. Register. All 

airplanes affected by this AD are 

currently operated by non-U.S. 

operators under foreign registry; 

therefore, they are not directly affected 

by this AD action. However, we 

consider this AD necessary to ensure 

that the unsafe condition is addressed if 

any affected airplane is imported and 

placed on the U.S. Register in the future. 

If an affected airplane is imported and 

placed on the U.S. Register in the future, 

it would take between 3 and 8 work 

hours per airplane for the initial 

inspections and about 2 work hours per 

airplane for each repetitive inspection, 

at an average labor rate of $65 per work 

hour. Two kits would be required for 

installing the new fasteners after 

discarding the removed fasteners. Parts 

cost is $190 for each kit. Based on these 

figures, the estimated cost of the initial 

actions would be between $575 and 

$900 per airplane; and the estimated 

cost of the repeat inspection is 

estimated to be $130 per airplane, per 

inspection cycle. 

FAA’s Determination of the Effective 

Date 

No airplane affected by this AD is 

currently on the U.S. Register. 

Therefore, providing notice and 

opportunity for public comment is 

unnecessary before this AD is issued, 

and this AD may be made effective in 

less than 30 days after it is published in 

the Federal Register. 

Federal Register / Vol. 70, No. 196 / Wednesday, October 12, 2005 / Rules and Regulations 59235 

Comments Invited 

This AD is a final rule that involves 

requirements that affect flight safety and 

was not preceded by notice and an 

opportunity for public comment; 

however, we invite you to submit any 

relevant written data, views, or 

arguments regarding this AD. Send your 

comments to an address listed in the 

ADDRESSES section. Include ‘‘Docket No. 

FAA–2005–22614; Directorate Identifier 

2005–NM–035–AD’’ at the beginning of 

your comments. We specifically invite 

comments on the overall regulatory, 

economic, environmental, and energy 

aspects of the AD that might suggest a 

need to modify it. 

We will post all comments we 

receive, without change, to http:// 

dms.dot.gov, including any personal 

information you provide. We will also 

post a report summarizing each 

substantive verbal contact with FAA 

personnel concerning this AD. Using the 

search function of that web site, anyone 

can find and read the comments in any 

of our dockets, including the name of 

the individual who sent the comment 

(or signed the comment on behalf of an 

association, business, labor union, etc.). 

You may review the DOT’s complete 

Privacy Act Statement in the Federal 

Register published on April 11, 2000 

(65 FR 19477–78), or you may visit 

http://dms.dot.gov. 

Examining the Docket 

You may 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 DOT 

street address stated in the ADDRESSES

section. Comments will be available in 

the AD docket shortly after the Docket 

Management System receives them. 

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 the 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 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. 

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): 

2005–20–27 Airbus: Amendment 39–14324. 

Docket No. FAA–2005–22614; 

Directorate Identifier 2005–NM–035–AD. 

Effective Date 

(a) This AD becomes effective October 27, 

2005. 

Affected ADs 

(b) None. 

Applicability 

(c) This AD applies to Airbus Model A340–

211, –212, –311, and –312 airplanes, 

certificated in any category, serial numbers 

0006, 0007 (right-hand side only), 0008, 

0013, 0020, 0024 (left-hand side only), 0027 

through 0029 inclusive, 0031, 0033, 0035, 

0038 through 0040 inclusive, 0043, 0047, 

0049, and 0052. 

Unsafe Condition 

(d) This AD results from a report that 

certain inspections done before 

accomplishing the modification of the lower 

keel beam fitting and forward lower shell 

connection revealed cracking that was 

outside the modification limits specified in 

the service bulletin; the cracking was 

repaired by installing a titanium doubler. The 

FAA is issuing this AD to find and fix 

discrepancies of the fastener holes of the 

horizontal flange of the keel beam, which 

could result in reduced structural integrity of 

the fuselage. 

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. 

Note 1: Airbus Service Bulletin A340–57–

4087, dated November 21, 2003, cites Airbus 

Service Bulletin A340–57–4036, Revision 05, 

dated March 14, 2000, as the source of 

service information for accomplishing Airbus 

Modification 43577. 

Initial/Repetitive Nondestructive Test 

Inspections/Repair 

(f) Within 5,420 flight cycles or 26,200 

flight hours after accomplishing Airbus 

Modification 43577, whichever is first: 

Perform an initial rotating probe inspection 

for discrepancies of the first fastener hole of 

the horizontal flange of the keel beam by 

doing all the actions in accordance with the 

Accomplishment Instructions of Airbus 

Service Bulletin A340–57–4087, dated 

November 21, 2003. If no cracking is found, 

before further flight, inspect for correct 

fastener diameter tolerance; if the fastener 

diameter is out-of-tolerance, before further 

flight, ream to oversize the fastener holes and 

install oversize fasteners in accordance with 

the Accomplishment Instructions of the 

service bulletin. 

(g) If no cracking is found during any 

inspection required by paragraph (f) of this 

AD: Within 1,480 flight cycles or 7,400 flight 

hours, whichever is first, after accomplishing 

the inspection: Perform an initial ultrasonic 

inspection for discrepancies of the first 

fastener hole of the horizontal flange of the 

keel beam by doing all the actions in 

accordance with the Accomplishment 

Instructions of Airbus Service Bulletin A340–

57–4087, dated November 21, 2003. If no 

cracking is found, repeat the ultrasonic 

inspection thereafter at intervals not to 

exceed 1,480 flight cycles or 7,400 flight 

hours, whichever is first. 

Repair Per the FAA or the Direction 

Ge ́ne ́rale De L’Aviation Civile (DGAC) 

(h) If any cracking is found during any 

inspection required by this AD: Before 

59236 Federal Register / Vol. 70, No. 196 / Wednesday, October 12, 2005 / Rules and Regulations 

further flight, repair per a method approved 

by either the Manager, International Branch, 

ANM–116, Transport Airplane Directorate, 

FAA; or the DGAC (or its delegated agent). 

Within 1,480 flight cycles or 7,400 flight 

hours, whichever is first, after repair of any 

cracking, perform an ultrasonic inspection as 

required by paragraph (g) of this AD. Repeat 

the ultrasonic inspection thereafter at 

intervals not to exceed 1,480 flight cycles or 

7,400 flight hours, whichever is first. 

No Reporting Required 

(i) Although Airbus Service Bulletin A340–

57–4087, dated November 21, 2003, specifies 

submitting an inspection report to the 

manufacturer, this AD does not include that 

requirement. 

Alternative Methods of Compliance 

(AMOCs) 

(j)(1) 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. 

(2) Before using any AMOC approved in 

accordance with 14 CFR 39.19 on any 

airplane to which the AMOC applies, notify 

the appropriate principal inspector in the 

FAA Flight Standards Certificate Holding 

District Office. 

Related Information 

(k) French airworthiness directive F–2005–

007, dated January 5, 2005, also addresses the 

subject of this AD. 

Material Incorporated by Reference 

(l) You must use Airbus Service Bulletin 

A340–57–4087, including Appendix 01, 

dated November 21, 2003, 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 28, 2005. 

Kalene C. Yanamura, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 05–20073 Filed 10–11–05; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2005–21862; Directorate 

Identifier 2005–NM–091–AD; Amendment 

39–14333; AD 2005–20–36] 

RIN 2120–AA64 

Airworthiness Directives; Airbus Model 

A320–111 Airplanes; and Model A320–

200, A321–100, and A321–200 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, A321–100, and A321–

200 series airplanes. This AD requires 

installing a bonding lead between the 

low pressure valve and the adjacent 

pipe assembly in each wing. This AD 

results from 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 

adjacent wing fuel tank. 

DATES: This AD becomes effective 

November 16, 2005. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication listed in the AD 

as of November 16, 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, 

A321–100, and A321–200 series 

airplanes. That NPRM was published in 

the Federal Register on July 19, 2005 

(70 FR 41352). That NPRM proposed to 

require installing a bonding lead 

between the low pressure valve and the 

adjacent pipe assembly in each wing. 

Comments 

We provided the public the 

opportunity to participate in the 

development of this AD. We have 

considered the comment received. 

Request to Allow Credit for Use of 

Original Issue of Service Bulletin 

One commenter requests that we give 

credit for actions accomplished prior to 

the effective date of the AD using Airbus 

Service Bulletin A320–28–1055, dated 

July 12, 1993. The commenter contends 

that such credit is permitted by French 

airworthiness directive F–2005–058, 

dated April 13, 2005. 

We agree with this request. We have 

reviewed the original issue of the 

service bulletin and determined that no 

significant technical changes were made 

in the issuance of Airbus Service 

Bulletin A320–28–1055, Revision 1, 

dated March 8, 1994. Therefore, we 

have added new paragraph (g) to give 

credit as specified and re-identified 

existing paragraphs (g) and (h) to (h)(1) 

and (i) in this AD. 

Clarification of Alternative Method of 

Compliance (AMOC) Paragraph 

We have revised this action to clarify 

the appropriate procedure for notifying 

the principal inspector before using any 

approved AMOC on any airplane to 

which the AMOC applies. 

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 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 403 

airplanes of U.S. registry. The required