Federal Register / Vol. 70, No. 193 / Thursday, October 6, 2005 / Rules and Regulations 58295 

‘‘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): 

2005–20–22 BAE Systems (Operations) 

Limited (Formerly British Aerospace 

Regional Aircraft): Amendment 39–

14318. Docket No. FAA–2005–22583; 

Directorate Identifier 2002–NM–303–AD. 

Effective Date 

(a) This AD becomes effective October 21, 

2005. 

Affected ADs 

(b) None. 

Applicability 

(c) This AD applies to all BAE Systems 

(Operations) Limited Model ATP airplanes, 

certificated in any category. 

Unsafe Condition 

(d) This AD results from information 

indicating the potential for environmental 

damage of the fuselage and wing structure. 

We are issuing this AD to detect and correct 

such damage, including corrosion, in the 

fuselage and wing structure, which could 

result in cracking and consequent reduced 

structural integrity of the fuselage and wing 

structure. 

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. 

Repetitive Inspections and Corrective 

Actions 

(f) Within 18 months after the effective 

date of this AD, perform detailed inspections 

for environmental damage, including but not 

limited to corrosion, of the fuselage and wing 

structure and any applicable corrective 

action in accordance with the 

Accomplishment Instructions of BAE 

Systems (Operations) Limited Service 

Bulletin ATP–51–001, dated August 14, 

2002, except as provided by paragraph (g) of 

this AD. Any applicable corrective actions 

must be accomplished before further flight. 

Thereafter, repeat these inspections at 

intervals not to exceed those specified in the 

ATP Maintenance Review Board Report and 

the Maintenance Planning Document, as 

applicable, in accordance with the service 

bulletin. 

Note 1: For the purposes of this AD, a 

detailed inspection is: ‘‘An intensive 

examination of a specific item, installation, 

or assembly to detect damage, failure, or 

irregularity. Available lighting is normally 

supplemented with a direct source of good 

lighting at an intensity deemed appropriate. 

Inspection aids such as mirror, magnifying 

lenses, etc., may be necessary. Surface 

cleaning and elaborate procedures may be 

required.’’

Exception to Service Bulletin Instructions 

(g) If damage is found that is outside the 

limits specified in the structural repair 

manual, as referenced in BAE Systems 

(Operations) Limited Service Bulletin ATP–

51–001, dated August 14, 2002, and the 

service bulletin specifies reporting the details 

of the damage to In-Service Engineering and 

asking for repair instructions: Before further 

flight, repair the damage in accordance with 

a method approved by either the Manager, 

International Branch, ANM–116, Transport 

Airplane Directorate, FAA; or the Civil 

Aviation Authority (or its delegated agent). 

No Reporting 

(h) Although British Aerospace ATP 

Service Bulletin ATP–51–001, dated August 

14, 2002, specifies reporting inspection 

results to the manufacturer, this AD does not 

require that action. 

Alternative Methods of Compliance 

(AMOCs) 

(i)(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 

(j) None. 

Material Incorporated by Reference 

(k) You must use BAE Systems 

(Operations) Limited Service Bulletin ATP–

51–001, dated August 14, 2002, 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 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/cfr/ibr-locations.html. 

Issued in Renton, Washington, on 

September 26, 2005. 

Ali Bahrami, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 05–19833 Filed 10–5–05; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2005–22586; Directorate 

Identifier 2002–NM–258–AD; Amendment 

39–14315; AD 2005–20–19] 

RIN 2120–AA64 

Airworthiness Directives; BAE 

Systems (Operations) Limited Model 

ATP Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

58296 Federal Register / Vol. 70, No. 193 / Thursday, October 6, 2005 / Rules and Regulations 

ACTION: Final rule; request for 

comments. 

SUMMARY: The FAA is adopting a new 

airworthiness directive (AD) for all BAE 

Systems (Operations) Limited Model 

ATP airplanes. This AD requires onetime inspections for corrosion of the 

engine sub-frame tubes in zone 1 and of 

the engine attachment struts in zone 5, 

and corrective action if necessary. This 

AD results from reports of reduced 

thickness in localized areas of the 

engine sub-frame tubes due to corrosion, 

and reports that corrosion may also exist 

in the engine attachment struts in zone 

5. We are issuing this AD to prevent 

failure of the engine sub-frame tubes or 

the engine attachment struts, which 

could result in separation of an engine 

from the airplane. 

DATES: This AD becomes effective 

October 21, 2005. 

The Director of the Federal Register 

approved the incorporation by reference 

of certain publications listed in the AD 

as of October 21, 2005. 

We must receive comments on this 

AD by December 5, 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. 

• 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 British Aerospace Regional 

Aircraft American Support, 13850 

Mclearen Road, Herndon, Virginia 

20171, for service information identified 

in this AD. 

FOR FURTHER INFORMATION CONTACT: 

Todd Thompson, Aerospace Engineer, 

International Branch, ANM–116, FAA, 

Transport Airplane Directorate, 1601 

Lind Avenue, SW., Renton, Washington 

98055–4056; telephone (425) 227–1175; 

fax (425) 227–1149. 

SUPPLEMENTARY INFORMATION: 

Discussion 

The Civil Aviation Authority (CAA), 

which is the airworthiness authority for 

the United Kingdom, notified us that an 

unsafe condition may exist on all BAE 

Systems (Operations) Limited Model 

ATP airplanes. The CAA advises that 

there have been reports indicating 

reduced thickness in localized areas of 

the engine sub-frame tubes due to 

corrosion. Such corrosion may also exist 

in the engine attachment struts in zone 

5. This condition, if not corrected, could 

result in failure of the engine sub-frame 

tubes or the engine attachment struts, 

and consequent separation of an engine 

from the airplane. 

Relevant Service Information 

BAE Systems (Operations) Limited 

has issued Service Bulletins ATP–54–18 

and ATP–54–19, both dated March 2, 

2001. Service Bulletin ATP–54–18 

describes procedures for performing an 

X-ray (radiographic) inspection for 

corrosion of the engine sub-frame tubes 

in Zone 1, and doing corrective action 

if necessary. Service Bulletin ATP–54–

19 describes procedures for performing 

an X-ray (radiographic) inspection for 

corrosion of the engine attachment 

struts in Zone 5, and doing corrective 

action if necessary. If corrosion is found, 

the service bulletins specify that the 

corrective action is installing a 

serviceable component, or contacting 

the manufacturer for instructions on 

repairing corroded components. 

Accomplishing the actions specified 

in the service information is intended to 

adequately address the unsafe 

condition. The CAA mandated the 

service information and issued British 

airworthiness directives 006–03–2001 

(mandating Service Bulletin ATP–54–

18) and 007–03–2001 (mandating 

Service Bulletin ATP–54–19) to ensure 

the continued airworthiness of these 

airplanes in the United Kingdom. 

FAA’s Determination and Requirements 

of This AD 

This airplane model is manufactured 

in the United Kingdom and is 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 CAA has 

kept the FAA informed of the situation 

described above. We have examined the 

CAA’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 

prevent failure of the engine sub-frame 

tubes or the engine attachment struts, 

which could result in separation of an 

engine from the airplane. This AD 

requires accomplishing the actions 

specified in the service information 

described previously, except as 

discussed under ‘‘Differences Among 

the AD, British Airworthiness 

Directives, and Service Bulletins.’’

Differences Among the AD, British 

Airworthiness Directives, and Service 

Bulletins 

British airworthiness directives 006–

03–2001 and 007–03–2001 specify that 

compliance is required no later than 

August 31, 2002. We do not use 

calendar dates to establish compliance 

times in our ADs. In developing an 

appropriate compliance time for this 

AD, we considered the CAA’s and the 

manufacturer’s recommendations, and 

the degree of urgency associated with 

the subject unsafe condition. In light of 

these factors, we find that a compliance 

time of 180 days after the effective date 

of this AD represents an appropriate 

interval of time for affected airplanes to 

continue to operate without 

compromising safety. This difference 

has been coordinated with the CAA. 

The service bulletins specify that, in 

lieu of replacing a corroded component 

with a serviceable component, operators 

may contact the manufacturer for 

information on the ‘‘serviceability’’ of 

corroded components. If any corrosion 

is found, this AD requires, before further 

flight, replacing the corroded 

component with a serviceable 

component, or repairing the corroded 

component using a method that we or 

the CAA (or its delegated agent) 

approve. In light of the type of repair 

that would be required to address the 

unsafe condition, and consistent with 

existing bilateral airworthiness 

agreements, we have determined that, 

for this AD, a repair we or the CAA 

approve would be acceptable for 

compliance with the repair provision of 

this AD. 

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, 

the required actions would take about 7 

work hours per airplane, at an average 

labor rate of $65 per work hour. Based 

on these figures, the estimated cost of 

the AD would be $455 per airplane. 

Federal Register / Vol. 70, No. 193 / Thursday, October 6, 2005 / Rules and Regulations 58297 

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. 

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–2005–22586; Directorate Identifier 

2002–NM–258–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): 

2005–20–19 BAE Systems (Operations) 

Limited (Formerly British Aerospace 

Regional Aircraft): Amendment 39–

14315. Docket No. FAA–2005–22586; 

Directorate Identifier 2002–NM–258–AD. 

Effective Date 

(a) This AD becomes effective October 21, 

2005. 

Affected ADs 

(b) None. 

Applicability 

(c) This AD applies to all BAE Systems 

(Operations) Limited Model ATP airplanes, 

certificated in any category. 

Unsafe Condition 

(d) This AD results from reports of reduced 

thickness in localized areas of the engine 

sub-frame tubes due to corrosion, and reports 

that corrosion may also exist in the engine 

attachment struts in zone 5. The FAA is 

issuing this AD to prevent failure of the 

engine sub-frame tubes or the engine 

attachment struts, which could result in 

separation of an engine from 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. 

Inspections 

(f) Within 180 days after the effective date 

of this AD, perform X-ray (radiographic) 

inspections for corrosion of the engine subframe tubes in Zone 1 and the engine 

attachment struts in Zone 5, in accordance 

with the Accomplishment Instructions of 

BAE Systems (Operations) Limited Service 

Bulletins ATP–54–18 and ATP–54–19, both 

dated March 2, 2001. Although the service 

bulletins referenced in this AD specify to 

submit inspection results to the 

manufacturer, this AD does not require that 

action. 

Corrective Action 

(g) If any corrosion is found during the 

inspections required by paragraph (f) of this 

AD: Before further flight, replace the 

corroded component with a serviceable 

component, in accordance with the 

Accomplishment Instructions of BAE 

Systems (Operations) Limited Service 

Bulletins ATP–54–18 and ATP–54–19, both 

dated March 2, 2001; or repair the corroded 

component in accordance with a method 

approved by either the Manager, 

International Branch, ANM–116, Transport 

Airplane Directorate, FAA; or the Civil 

Aviation Authority (or its delegated agent). 

Alternative Methods of Compliance 

(AMOCs) 

(h)(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 

58298 Federal Register / Vol. 70, No. 193 / Thursday, October 6, 2005 / Rules and Regulations 

FAA Flight Standards Certificate Holding 

District Office. 

Related Information 

(i) British airworthiness directives 006–03–

2001 and 007–03–2001 also address the 

subjects of this AD. 

Material Incorporated by Reference 

(j) You must use BAE Systems (Operations) 

Limited Service Bulletin ATP–54–18, dated 

March 2, 2001; and BAE Systems 

(Operations) Limited Service Bulletin ATP–

54–19, dated March 2, 2001; 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 these 

documents 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 26, 2005. 

Ali Bahrami, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 05–19832 Filed 10–5–05; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2005–22587; Directorate 

Identifier 2003–NM–266–AD; Amendment 

39–14316; AD 2005–20–20] 

RIN 2120–AA64 

Airworthiness Directives; Airbus Model 

A330–301, –321, –322, –341, and –342 

Airplanes; and Model A340–200 and 

A340–300 Series 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 A330–301, –321, –322, 

–341, and –342 airplanes; and Model 

A340–200 and A340–300 series 

airplanes. This AD requires installing 

lockplates on the main landing gear 

(MLG) and center landing gear (CLG) 

wheel assemblies, as applicable, to keep 

the tie bolts in position in the wheel 

assembly in the event of a tie bolt 

failure. This AD results from reports of 

tie bolts that were broken or missing 

from the MLG wheel assembly; in some 

cases the wheels have ruptured and 

caused damage to other equipment in 

the adjacent area. We are issuing this 

AD to prevent damage to the wheel 

assembly and equipment in the area 

adjacent to the MLG and CLG, which 

could result in a decrease in braking 

function and possible runway over-run. 

DATES: Effective October 21, 2005. 

The Director of the Federal Register 

approved the incorporation by reference 

of certain publications listed in the AD 

as of October 21, 2005. 

We must receive comments on this 

AD by December 5, 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. 

• 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 A330–

301, –321, –322, –341, and –342 

airplanes that are equipped with 

Messier-Goodrich main landing gear 

(MLG) wheel assemblies, part number 

(P/N) 3–1509–2; and Model A340–200 

and A340–300 series airplanes that are 

equipped with center landing gear 

(CLG) and MLG wheel assemblies, P/N 

3–1509–2. The DGAC advises that 

operators of Model A330 series 

airplanes fitted with the affected wheel 

assemblies reported tie bolts that were 

broken or missing from the MLG wheel 

assemblies. Investigations indicated that 

the tie bolts ruptured due to fatigue 

failure and subsequently migrated out of 

the tie bolt hole. As a consequence, in 

some cases the failed tie bolt caught on 

the brake unit and ruptured a wheel. 

This condition, if not corrected, could 

cause damage to the wheel assembly 

and equipment in the area adjacent to 

the MLG and CLG, which could result 

in a decrease in braking function and 

possible runway over-run. 

Relevant Service Information 

Airbus has issued Service Bulletin 

A330–32–3167, dated August 12, 2003 

(for Model A330–301, –321, –322, and 

–342 airplanes); and Service Bulletin 

A340–32–4206, dated August 12, 2003 

(for Model A340–211 and –212 

airplanes; and Model A340–300 series 

airplanes). The service bulletins 

describe procedures for modifying the 

MLG and CLG, as applicable, by 

installing lockplates on the wheel 

assembly to keep the tie bolts in 

position in the wheel assembly in the 

event of a tie bolt failure. 

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 directives 2003–392(B) 

and 2003–393(B), both dated October 

29, 2003, to ensure the continued 

airworthiness of these airplanes in 

France. 

The service bulletins refer to 

Goodrich-Messier Service Bulletin 3–

1509–32–5, dated August 12, 2003, as 

an additional source of service 

information for installing the lockplates. 

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.