Federal Register / Vol. 74, No. 82 / Thursday, April 30, 2009 / Proposed Rules 19905 

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 

proposed AD would not have federalism 

implications under Executive Order 

13132. This proposed AD would 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 proposed AD: 

1. Is not a ‘‘significant regulatory 

action’’ under Executive Order 12866; 

2. Is not a ‘‘significant rule’’ under the 

DOT Regulatory Policies and Procedures 

(44 FR 11034, February 26, 1979); and 

3. Would 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 proposed AD. You may get a copy 

of this summary at the address listed 

under ADDRESSES. 

List of Subjects in 14 CFR Part 39 

Air transportation, Aircraft, Aviation 

safety, Safety. 

The Proposed Amendment 

Under the authority delegated to me 

by the Administrator, the Federal 

Aviation Administration proposes to 

amend 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 airworthiness 

directive: 

International Aero Engines: Docket No. 

FAA–2007–29060; Directorate Identifier 

2007–NE–34–AD. 

Comments Due Date 

(a) The Federal Aviation Administration 

(FAA) must receive comments on this 

airworthiness directive (AD) action by June 

29, 2009. 

Affected ADs 

(b) None. 

Applicability 

(c) This AD applies to International Aero 

Engines (IAE) V2500–A1, V2527E–A5, 

V2527M–A5, V2528–D5, V2530–A5, and 

V2533–A5 turbofan engines with high 

pressure (HP) compressor stage 3–8 drums, 

part numbers (P/Ns) 6A5467, 6A6473, and 

6A7401, installed. These engines are 

installed on, but not limited to, Airbus A319, 

A320, and A321 series airplanes and Boeing 

MD–90 airplanes. 

Unsafe Condition 

(d) This AD results from reports of 

fractured vortex reducers found at shop 

visits. We are issuing this AD to inspect for 

cracks in the vortex reducer. Cracks in the 

vortex reducer could cause an uncontained 

failure of the HP compressor stage 3–8 drum, 

which could result in damage to 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. 

Onetime Fluorescent Penetrant Inspection 

(f) Fluorescent penetrant inspect the vortex 

reducer for cracks when the HPC stage 3–8 

drum has between 3,000 and 13,500 cycles 

since new (CSN) if all of the following 

conditions also apply: 

(1) The HPC stage 3–8 drum has ever 

operated in an engine at the V2527E–A5, 

V2527M–A5, V2528–D5, V2530–A5 thrust 

ratings, 

(2) The vortex reducer had cycles 

accumulated on it when mated with the HPC 

stage 3–8 drum, and 

(3) The HPC stage 3–8 drum had fewer 

than 3,000 CSN when mated to the vortex 

reducer. 

(g) If the vortex reducer is cracked, remove 

both the vortex reducer and the HPC stage 3– 

8 drum from service. 

(h) After the effective date of this AD, do 

not return to service any HPC stage 3–8 drum 

that was removed as specified in paragraph 

(g) of this AD. 

Alternative Methods of Compliance 

(i) The Manager, Engine Certification 

Office, has the authority to approve 

alternative methods of compliance for this 

AD if requested using the procedures found 

in 14 CFR 39.19. 

Related Information 

(j) Contact Kevin Dickert, Aerospace 

Engineer, Engine Certification Office, FAA, 

Engine & Propeller Directorate, 12 New 

England Executive Park, Burlington, MA 

01803; e-mail: kevin_dickert@faa.gov; 

telephone (781) 238–7117; fax (781) 238– 

7199, for more information about this AD. 

Issued in Burlington, Massachusetts, on 

April 27, 2009. 

Peter A. White, 

Assistant Manager, Engine and Propeller 

Directorate, Aircraft Certification Service. 

[FR Doc. E9–9965 Filed 4–29–09; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2009–0398; Directorate 

Identifier 2008–NM–193–AD] 

RIN 2120–AA64 

Airworthiness Directives; BAE 

Systems (Operations) Limited Model 

BAe 146 and Avro 146–RJ Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Notice of proposed rulemaking 

(NPRM). 

SUMMARY: We propose to adopt a new 

airworthiness directive (AD) for the 

products listed above. This proposed 

AD results from mandatory continuing 

airworthiness information (MCAI) 

originated by an aviation authority of 

another country to identify and correct 

an unsafe condition on an aviation 

product. The MCAI describes the unsafe 

condition as: 

There have been a number of incidents 

where wing-to-fuselage or MLG [main 

landing gear] door fairing panels have 

detached from the aircraft during flight. 

Subsequent inspection revealed the loss of 

the fairing panels to be due to failure of 

certain steel grommets * * *. A detaching 

panel could strike the aircraft during flight, 

causing damage. In addition, a detaching 

panel could become attached to the structure 

or control surfaces, resulting in reduced 

control of the aircraft. 

The proposed AD would require 

actions that are intended to address the 

unsafe condition described in the MCAI. 

DATES: We must receive comments on 

this proposed AD by June 1, 2009. 

ADDRESSES: You may send comments by 

any of the following methods: 

• Federal eRulemaking Portal: Go to 

http://www.regulations.gov. Follow the 

instructions for submitting comments. 

• Fax: (202) 493–2251. 

• Mail: U.S. Department of 

Transportation, Docket Operations, M– 

30, West Building Ground Floor, Room 

W12–140, 1200 New Jersey Avenue, SE., 

Washington, DC 20590. 

• Hand Delivery: U.S. Department of 

Transportation, Docket Operations, M– 

30, West Building Ground Floor, Room 

W12–40, 1200 New Jersey Avenue, SE., 

19906 Federal Register / Vol. 74, No. 82 / Thursday, April 30, 2009 / Proposed Rules 

Washington, DC, between 9 a.m. and 5 

p.m., Monday through Friday, except 

Federal holidays. 

For service information identified in 

this proposed AD, contact BAE Systems 

Regional Aircraft, 13850 McLearen 

Road, Herndon, Virginia 20171; 

telephone 703–736–1080; e-mail 

raebusiness@baesystems.com; Internet 

http://www.baesystems.com/Businesses/ 

RegionalAircraft/index.htm. You may 

review copies of the referenced service 

information at the FAA, Transport 

Airplane Directorate, 1601 Lind 

Avenue, SW., Renton, Washington. For 

information on the availability of this 

material at the FAA, call 425–227–1221 

or 425–227–1152. 

Examining the AD Docket 

You may examine the AD docket on 

the Internet at http:// 

www.regulations.gov; or in person at the 

Docket Operations office between 9 a.m. 

and 5 p.m., Monday through Friday, 

except Federal holidays. The AD docket 

contains this proposed AD, the 

regulatory evaluation, any comments 

received, and other information. The 

street address for the Docket Operations 

office (telephone (800) 647–5527) is in 

the ADDRESSES section. Comments will 

be available in the AD docket shortly 

after receipt. 

FOR FURTHER INFORMATION CONTACT: 

Todd Thompson, Aerospace Engineer, 

International Branch, ANM–116, 

Transport Airplane Directorate, FAA, 

1601 Lind Avenue, SW., Renton, 

Washington 98057–3356; telephone 

(425) 227–1175; fax (425) 227–1149. 

SUPPLEMENTARY INFORMATION: 

Comments Invited 

We invite you to send any written 

relevant data, views, or arguments about 

this proposed AD. Send your comments 

to an address listed under the 

ADDRESSES section. Include ‘‘Docket No. 

FAA–2009–0398; Directorate Identifier 

2008–NM–193–AD’’ at the beginning of 

your comments. We specifically invite 

comments on the overall regulatory, 

economic, environmental, and energy 

aspects of this proposed AD. We will 

consider all comments received by the 

closing date and may amend this 

proposed AD based on those comments. 

We will post all comments we 

receive, without change, to http:// 

www.regulations.gov, including any 

personal information you provide. We 

will also post a report summarizing each 

substantive verbal contact we receive 

about this proposed AD. 

Discussion 

The European Aviation Safety Agency 

(EASA), which is the Technical Agent 

for the Member States of the European 

Community, has issued EASA 

Airworthiness Directive 2008–0180, 

dated September 30, 2008 (referred to 

after this as ‘‘the MCAI’’), to correct an 

unsafe condition for the specified 

products. The MCAI states: 

There have been a number of incidents 

where wing-to-fuselage or MLG [main 

landing gear] door fairing panels have 

detached from the aircraft during flight. 

Subsequent inspection revealed the loss of 

the fairing panels to be due to failure of 

certain steel grommets, (P/N) [part number] 

SL5183 and HC535H0312, through which the 

attachment bolts are inserted. These failures 

may have been caused by improper 

installation of the grommets or damage 

resulting from maintenance procedures 

relating to paint stripping and repainting, 

allowing air loads to pull the panel through 

the grommet. A detaching panel could strike 

the aircraft during flight, causing damage. In 

addition, a detaching panel could become 

attached to the structure or control surfaces, 

resulting in reduced control of the aircraft. 

Following the application of BAE Systems 

(Operations) Ltd ISB 53–202 at Revision 1 to 

the first few, it has been discovered that 

removal of existing grommets P/N SL5183 

and HC535H0312 may result in localised 

damage to the aluminum foil membrane 

attached to the inner surface of some fairing 

panels. BAE Systems (Operations) Ltd has 

therefore issued additional instructions in 

All Operators Message (AOM) 08–015V, 

including bonding checks and detailed 

procedures for applying an electroconductive paste at each SL5185 grommet 

location in order to bridge any gap between 

grommet and the inner aluminum foil. The 

next revision of BAE Systems (Operations) 

Ltd ISB 53–202 will include the technical 

content of AOM 08–015V. 

For the reasons described above, this EASA 

AD requires repetitive inspections of the 

wing-to-fuselage & MLG door fairing panel 

grommets and, when damage is detected, the 

accomplishment of corrective actions. 

Corrective actions include replacing 

damaged grommets with new P/N 

SL5185 grommets; or doing a temporary 

repair, which delays the replacement. 

You may obtain further information by 

examining the MCAI in the AD docket. 

Relevant Service Information 

BAE Systems (Operations) Limited 

has issued Inspection Service Bulletin 

ISB.53–202, Revision 3, dated December 

10, 2008. The actions described in the 

service information are intended to 

correct the unsafe condition identified 

in the MCAI. 

FAA’s Determination and Requirements 

of This Proposed AD 

This product has been approved by 

the aviation authority of another 

country, and is approved for operation 

in the United States. Pursuant to our 

bilateral agreement with the State of 

Design Authority, we have been notified 

of the unsafe condition described in the 

MCAI and service information 

referenced above. We are proposing this 

AD because we evaluated all pertinent 

information and determined an unsafe 

condition exists and is likely to exist or 

develop on other products of the same 

type design. 

Differences Between This AD and the 

MCAI or Service Information 

We have reviewed the MCAI and 

related service information and, in 

general, agree with their substance. But 

we might have found it necessary to use 

different words from those in the MCAI 

to ensure the AD is clear for U.S. 

operators and is enforceable. In making 

these changes, we do not intend to differ 

substantively from the information 

provided in the MCAI and related 

service information. 

We might also have proposed 

different actions in this AD from those 

in the MCAI in order to follow FAA 

policies. Any such differences are 

highlighted in a NOTE within the 

proposed AD. 

Costs of Compliance 

Based on the service information, we 

estimate that this proposed AD would 

affect about 1 product of U.S. registry. 

We also estimate that it would take 

about 14 work hours per product to 

comply with the basic requirements of 

this proposed AD. The average labor 

rate is $80 per work-hour. Based on 

these figures, we estimate the cost of the 

proposed AD on U.S. operators to be 

$1,120. 

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. 

Federal Register / Vol. 74, No. 82 / Thursday, April 30, 2009 / Proposed Rules 19907 

Regulatory Findings 

We determined that this proposed AD 

would not have federalism implications 

under Executive Order 13132. This 

proposed AD would not have a 

substantial direct effect on the States, on 

the relationship between the national 

Government and the States, or on the 

distribution of power and 

responsibilities among the various 

levels of government. 

For the reasons discussed above, I 

certify this proposed 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 proposed AD and placed it in the 

AD docket. 

List of Subjects in 14 CFR Part 39 

Air transportation, Aircraft, Aviation 

safety, Incorporation by reference, 

Safety. 

The Proposed Amendment 

Accordingly, under the authority 

delegated to me by the Administrator, 

the FAA proposes to amend 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: 

BAE Systems (Operations) Limited 

(Formerly British Aerospace Regional 

Aircraft): Docket No. FAA–2009–0398; 

Directorate Identifier 2008–NM–193–AD. 

Comments Due Date 

(a) We must receive comments by June 1, 

2009. 

Affected ADs 

(b) None. 

Applicability 

(c) This AD applies to BAE Systems 

(Operations) Limited Model BAe 146–100A, 

–200A, and –300A series airplanes; and 

Model Avro 146–RJ70A, 146–RJ85A, and 

146–RJ100A airplanes; certificated in any 

category, all models, all serial numbers, that 

have embodied modification HCM00633E or 

HCM00934A. 

Subject 

(d) Air Transport Association (ATA) of 

America Code 53: Fuselage. 

Reason 

(e) The mandatory continuing 

airworthiness information (MCAI) states: 

There have been a number of incidents 

where wing-to-fuselage or MLG [main 

landing gear] door fairing panels have 

detached from the aircraft during flight. 

Subsequent inspection revealed the loss of 

the fairing panels to be due to failure of 

certain steel grommets, (P/N) [part number] 

SL5183 and HC535H0312, through which the 

attachment bolts are inserted. These failures 

may have been caused by improper 

installation of the grommets or damage 

resulting from maintenance procedures 

relating to paint stripping and repainting, 

allowing air loads to pull the panel through 

the grommet. A detaching panel could strike 

the aircraft during flight, causing damage. In 

addition, a detaching panel could become 

attached to the structure or control surfaces, 

resulting in reduced control of the aircraft. 

Following the application of BAE Systems 

(Operations) Ltd ISB 53–202 at Revision 1 to 

the first few, it has been discovered that 

removal of existing grommets P/N SL5183 

and HC535H0312 may result in localised 

damage to the aluminum foil membrane 

attached to the inner surface of some fairing 

panels. BAE Systems (Operations) Ltd has 

therefore issued additional instructions in 

All Operators Message (AOM) 08–015V, 

including bonding checks and detailed 

procedures for applying an electroconductive paste at each SL5185 grommet 

location in order to bridge any gap between 

grommet and the inner aluminum foil. The 

next revision of BAE Systems (Operations) 

Ltd ISB 53–202 will include the technical 

content of AOM 08–015V. 

For the reasons described above, this EASA 

AD requires repetitive inspections of the 

wing-to-fuselage & MLG door fairing panel 

grommets and, when damage is detected, the 

accomplishment of corrective actions. 

Corrective actions include replacing 

damaged grommets with new P/N SL5185 

grommets; or doing a temporary repair, 

which delays the replacement. 

Actions and Compliance 

(f) Unless already done, do the following 

actions. 

(1) Within 4,000 flight cycles or 24 months 

after the effective date of this AD, whichever 

occurs later, and thereafter at intervals not to 

exceed 8,000 flight cycles, conduct a visual 

inspection of the steel grommets on the 

fairing panels in accordance with paragraph 

2.C. of BAE Systems (Operations) Limited 

Inspection Service Bulletin ISB.53–202, 

Revision 3, dated December 10, 2008. 

(2) If damage is found during any 

inspection required by paragraph (f)(1) of this 

AD, before further flight, do the actions 

specified in paragraph (f)(2)(i) or (f)(2)(ii) of 

this AD. 

(i) Replace the grommets with new P/N 

SL5185 grommets in accordance with 

paragraph 2.C. of BAE Systems (Operations) 

Limited Inspection Service Bulletin ISB.53– 

202, Revision 3, dated December 10, 2008, 

and concurrently conduct a bonding 

inspection at each grommet location in 

accordance with paragraph 2.C. of BAE 

Systems (Operations) Limited Inspection 

Service Bulletin ISB.53–202, Revision 3, 

dated December 10, 2008. If unsatisfactory 

bonding is detected, before further flight, 

apply electro-conductive paste in accordance 

with Appendix 4 of BAE Systems 

(Operations) Limited Inspection Service 

Bulletin ISB.53–202, Revision 3, dated 

December 10, 2008. 

(ii) Do a temporary repair in accordance 

with Appendix 3 of the BAE Systems 

(Operations) Limited Inspection Service 

Bulletin ISB.53–202, Revision 3, dated 

December 10, 2008, or an approved BAE 

Systems (Operations) Limited temporary 

repair scheme. 

(3) For airplanes on which a temporary 

repair specified in paragraph (f)(2)(ii) of this 

AD has been done: Within 8,000 flight cycles 

after doing the temporary repair, replace any 

temporary repair grommets with new P/N 

SL5185 grommets in accordance with 

paragraph 2.C. of BAE Systems (Operations) 

Limited Inspection Service Bulletin ISB.53– 

202, Revision 3, dated December 10, 2008, 

and concurrently conduct a bonding 

inspection at each grommet location in 

accordance with paragraph 2.C. of BAE 

Systems (Operations) Limited Inspection 

Service Bulletin ISB.53–202, Revision 3, 

dated December 10, 2008. If unsatisfactory 

bonding is detected, before further flight, 

apply electro-conductive paste in accordance 

with Appendix 4 of BAE Systems 

(Operations) Limited Inspection Service 

Bulletin ISB.53–202, Revision 3, dated 

December 10, 2008. 

(4) For airplanes on which any new P/N 

SL5185 grommets have been installed 

without having a bonding inspection prior to 

the effective date of this AD: Before or during 

the next scheduled repetitive inspection in 

accordance with paragraph (f)(1) of this AD, 

conduct a bonding inspection in accordance 

with paragraph 2.C of BAE Systems 

(Operations) Limited Inspection Service 

Bulletin ISB.53–202, Revision 3, dated 

December 10, 2008. If unsatisfactory bonding 

is detected, before further flight, apply 

electro-conductive paste in accordance with 

Appendix 4 of BAE Systems (Operations) 

Limited Inspection Service Bulletin ISB.53– 

202, Revision 3, dated December 10, 2008. 

(5) Replacement of all existing grommets 

with new P/N SL5185 grommets on all 

panels, including the corresponding bonding 

inspections and the application of the 

electro-conductive paste as applicable, in 

accordance with BAE Systems (Operations) 

Limited Inspection Service Bulletin ISB.53– 

202, Revision 3, dated December 10, 2008, 

terminates the repetitive inspections required 

by paragraph (f)(1) of this AD. 

(6) Visual inspections, temporary repairs, 

and replacements of the grommets are also 

acceptable for compliance with the 

corresponding requirements of paragraphs 

(f)(1), (f)(2)(i), (f)(2)(ii), (f)(3), and (f)(5) of this 

AD if done before the effective date of this 

AD in accordance with BAE Systems 

(Operations) Limited Inspection Service 

Bulletin ISB.53–202, Revision 1, dated June 

4, 2008. 

19908 Federal Register / Vol. 74, No. 82 / Thursday, April 30, 2009 / Proposed Rules 

(7) Visual inspections, temporary repairs, 

replacements of the grommets, bonding 

inspections, and applications of conductive 

paste are also acceptable for compliance with 

the corresponding requirements of 

paragraphs (f)(1), (f)(2)(i), (f)(3), (f)(4), and 

(f)(5) of this AD if done before the effective 

date of this AD in accordance with BAE 

Systems (Operations) Limited Inspection 

Service Bulletin ISB.53–202, Revision 2, 

dated October 24, 2008. 

(8) Bonding inspections and applications 

of conductive paste are also acceptable for 

compliance with the corresponding 

requirement of paragraphs (f)(2)(i), (f)(3), 

(f)(4), and (f)(5) of this AD if done before the 

effective date of this AD in accordance with 

BAE Systems (Operations) Limited All 

Operator Message 08–015V, Issue 1, dated 

August 22, 2008. 

FAA AD Differences 

Note 1: 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 

principal maintenance inspector (PMI) or 

principal avionics inspector (PAI), as 

appropriate, or lacking a principal inspector, 

your local Flight Standards District Office. 

(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 ensure the product is airworthy before it 

is returned to service. 

(3) Reporting Requirements: For any 

reporting requirement in this AD, under the 

provisions of the Paperwork Reduction Act, 

the Office of Management and Budget (OMB) 

has approved the information collection 

requirements and has assigned OMB Control 

Number 2120–0056. 

Related Information 

(h) Refer to MCAI European Aviation 

Safety Agency Airworthiness Directive 2008– 

0180, dated September 30, 2008; and BAE 

Systems (Operations) Limited Inspection 

Service Bulletin ISB.53–202, Revision 3, 

dated December 10, 2008; for related 

information. 

Issued in Renton, Washington, on April 22, 

2009. 

Stephen P. Boyd, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. E9–9865 Filed 4–29–09; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2009–0397; Directorate 

Identifier 2008–NM–023–AD] 

RIN 2120–AA64 

Airworthiness Directives; Airbus Model 

A300 B2–1C, B2–203, B2K–3C, B4–103, 

B4–203, and B4–2C Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Notice of proposed rulemaking 

(NPRM). 

SUMMARY: We propose to adopt a new 

airworthiness directive (AD) for the 

products listed above. This proposed 

AD results from mandatory continuing 

airworthiness information (MCAI) 

originated by an aviation authority of 

another country to identify and correct 

an unsafe condition on an aviation 

product. The MCAI describes the unsafe 

condition as: 

An operator has reported the loss of a 

centre flap inner tab on an in-service A300 

aircraft. The centre flap inner tab detached 

during approach to an airport. A similar 

event was reported several years ago on a 

pre-mod 04770 aircraft. * * * 

* * * Investigations led by the 

manufacturer revealed that the centre hinge 

bracket developed a fatigue crack causing 

complete failure of the bracket. The tab 

rotated causing failure of the inboard link 

followed by the failure of the outboard link. 

[D]etachment of a centre flap inner tab 

* * * could be a potential risk to persons on 

[the] ground * * * . 

The proposed AD would require actions 

that are intended to address the unsafe 

condition described in the MCAI. 

DATES: We must receive comments on 

this proposed AD by June 1, 2009. 

ADDRESSES: You may send comments by 

any of the following methods: 

• Federal eRulemaking Portal: Go to 

http://www.regulations.gov. Follow the 

instructions for submitting comments. 

• Fax: (202) 493–2251. 

• Mail: U.S. Department of 

Transportation, Docket Operations, M– 

30, West Building Ground Floor, Room 

W12–140, 1200 New Jersey Avenue, SE., 

Washington, DC 20590. 

• Hand Delivery: U.S. Department of 

Transportation, Docket Operations, 

M–30, West Building Ground Floor, 

Room W12–40, 1200 New Jersey 

Avenue SE., Washington, DC, between 9 

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

Friday, except Federal holidays. 

For service information identified in 

this proposed AD, contact Airbus SAS— 

EAW (Airworthiness Office), 1 Rond 

Point Maurice Bellonte, 31707 Blagnac 

Cedex, France; telephone +33 5 61 93 36 

96; fax +33 5 61 93 44 51; e-mail 

account.airworth-eas@airbus.com; 

Internet http://www.airbus.com. You 

may review copies of the referenced 

service information at the FAA, 

Transport Airplane Directorate, 1601 

Lind Avenue, SW., Renton, Washington. 

For information on the availability of 

this material at the FAA, call 425–227– 

1221 or 425–227–1152. 

Examining the AD Docket 

You may examine the AD docket on 

the Internet at http:// 

www.regulations.gov; or in person at the 

Docket Operations office between 9 a.m. 

and 5 p.m., Monday through Friday, 

except Federal holidays. The AD docket 

contains this proposed AD, the 

regulatory evaluation, any comments 

received, and other information. The 

street address for the Docket Operations 

office (telephone (800) 647–5527) is in 

the ADDRESSES section. Comments will 

be available in the AD docket shortly 

after receipt. 

FOR FURTHER INFORMATION CONTACT: Dan 

Rodina, Aerospace Engineer, 

International Branch, ANM–116, 

Transport Airplane Directorate, FAA, 

1601 Lind Avenue, SW., Renton, 

Washington 98057–3356; telephone 

(425) 227–2125; fax (425) 227–1149. 

SUPPLEMENTARY INFORMATION: 

Comments Invited 

We invite you to send any written 

relevant data, views, or arguments about 

this proposed AD. Send your comments 

to an address listed under the 

ADDRESSES section. Include ‘‘Docket No. 

FAA–2009–0397; Directorate Identifier 

2008–NM–023–AD’’ at the beginning of 

your comments. We specifically invite 

comments on the overall regulatory, 

economic, environmental, and energy 

aspects of this proposed AD. We will 

consider all comments received by the 

closing date and may amend this 

proposed AD based on those comments. 

We will post all comments we 

receive, without change, to http:// 

www.regulations.gov, including any 

personal information you provide. We 

will also post a report summarizing each 

substantive verbal contact we receive 

about this proposed AD.