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TABLE 2—CREDIT SERVICE INFORMATION

Airbus AOT— Revision— Dated— 

A300–55A6047 ............................................................ Original ........................................................................ May 11, 2009. 

A300–55A6047 ............................................................ 01 ................................................................................ July 8, 2009. 

A310–55A2048 ............................................................ Original ........................................................................ May 11, 2009. 

A310–55A2048 ............................................................ 01 ................................................................................ July 8, 2009. 

(k) For rudders on which temporary 

restoration with resin or permanent vacuum 

loss hole restoration has been done in 

accordance with the applicable service 

bulletin in Table 2 of this AD, as required in 

paragraph (g)(9) or (h)(9) of this AD, before 

the effective date of this AD: Within 4,500 

flight cycles from the restoration date, do an 

ultrasonic inspection for defects, including 

debonding of the reinforced area, in 

accordance with Airbus AOT A310–55A2048 

or AOT A300–55A6047, both Revision 02, 

both dated October 12, 2009, as applicable. 

If any defect is found, before further flight, 

contact Airbus for repair instructions and do 

the repair. 

(l) After the effective date of this AD, no 

person may install any rudder listed in Table 

1 of this AD on any airplane, unless the 

rudder has been inspected and all applicable 

corrective actions have been done in 

accordance with paragraph (g) or (h) of this 

AD. 

FAA AD Differences 

Note 1: This AD differs from the MCAI 

and/or service information as follows: No 

differences. 

Other FAA AD Provisions 

(m) The following provisions also apply to 

this AD: 

(1) Alternative Methods of Compliance 

(AMOCs): The Manager, International 

Branch, ANM–116, 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: 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. 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. 

The AMOC approval letter must specifically 

reference this AD. 

(2) Airworthy Product: For any requirement 

in this AD to obtain corrective actions from 

a manufacturer or other source, use these 

actions if they are FAA-approved. Corrective 

actions are considered FAA-approved if they 

are approved by the State of Design Authority 

(or their delegated agent). You are required 

to assure the product is airworthy before it 

is returned to service. 

(3) Reporting Requirements: For any 

reporting requirement in this AD, under the 

provisions of the Paperwork Reduction Act 

(44 U.S.C. 3501 et seq.), the Office of 

Management and Budget (OMB) has 

approved the information collection 

requirements and has assigned OMB Control 

Number 2120–0056. 

Related Information 

(n) Refer to MCAI European Aviation 

Safety Agency (EASA) Airworthiness 

Directive 2010–0002, dated January 5, 2010; 

and Airbus AOT A310–55A2048, Revision 

02, dated October 12, 2009, or Airbus AOT 

A300–55A6047, Revision 02, dated October 

12, 2009; for related information. 

Issued in Renton, Washington, on March 

25, 2010. 

Ali Bahrami, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 2010–7459 Filed 4–1–10; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2010–0279; Directorate 

Identifier 2009–NM–148–AD] 

RIN 2120–AA64 

Airworthiness Directives; Airbus Model 

A318, A319, A320, and A321 Series 

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: Surface defects were 

visually detected on the rudder of one 

A319 and one A321 in-service 

aeroplane. Investigation has determined 

that the defects reported on both 

rudders corresponded to areas that had 

been reworked in production. The 

investigation confirmed that the defects 

were a result of de-bonding between the 

skin and honeycomb core. An extended 

de-bonding, if not detected and 

corrected, may degrade the structural 

integrity of the rudder. The loss of the 

rudder leads to degradation of the 

handling qualities and reduces the 

controllability of the aeroplane. 

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 May 17, 2010. 

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, 

Airworthiness Office—EAS, 1 Rond 

Point Maurice Bellonte, 31707 Blagnac 

Cedex, France; fax +33 5 61 93 44 51; 

e-mail: account.airwortheas@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. 


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FOR FURTHER INFORMATION CONTACT: Tim 

Dulin, Aerospace Engineer, 

International Branch, ANM–116, 

Transport Airplane Directorate, FAA, 

1601 Lind Avenue, SW., Renton, 

Washington 98057–3356; telephone 

(425) 227–2141; 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–2010–0279; Directorate Identifier 

2009–NM–148–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 have lengthened the 30-day 

comment period for proposed ADs that 

address MCAI originated by aviation 

authorities of other countries to provide 

adequate time for interested parties to 

submit comments. The comment period 

for these proposed ADs is now typically 

45 days, which is consistent with the 

comment period for domestic transport 

ADs. 

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 2009–0141, 

dated July 2, 2009 (referred to after this 

as ‘‘the MCAI’’), to correct an unsafe 

condition for the specified products. 

The MCAI states: 

Surface defects were visually detected on 

the rudder of one A319 and one A321 inservice aeroplane. 

Investigation has determined that the 

defects reported on both rudders 

corresponded to areas that had been 

reworked in production. The investigation 

confirmed that the defects were a result of 

de-bonding between the skin and honeycomb 

core. 

An extended de-bonding, if not detected 

and corrected, may degrade the structural 

integrity of the rudder. The loss of the rudder 

leads to degradation of the handling qualities 

and reduces the controllability of the 

aeroplane. 

This AD requires inspections of specific 

areas and, when necessary, the application of 

corrective actions for those rudders where 

production reworks have been identified. 

Inspections include vacuum loss 

inspections for de-bonding of the 

rudders in reinforced areas and other 

areas (splice/lower rib/upper edge/ 

leading edge/other specified locations), 

and elasticity laminate checks for debonding of the rudders in the trailing 

edge area and other areas (splice/lower 

rib/upper edge/leading edge/other 

specified locations). Corrective actions 

include contacting Airbus for further 

instruction and doing the repair. You 

may obtain further information by 

examining the MCAI in the AD docket. 

Relevant Service Information 

Airbus has issued All Operators Telex 

A320–55A1038, Revision 02, dated 

September 28, 2009. The actions 

described in this 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 155 products of U.S. 

registry. We also estimate that it would 

take about 11 work-hours per product to 

comply with the basic requirements of 

this proposed AD. The average labor 

rate is $85 per work-hour. Based on 

these figures, we estimate the cost of the 

proposed AD on U.S. operators to be 

$144,925, or $935 per product. 

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 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: 


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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: 

Airbus: Docket No. FAA–2010–0279; 

Directorate Identifier 2009–NM–148–AD. 

Comments Due Date 

(a) We must receive comments by May 17, 

2010. 

Affected ADs 

(b) None. 

Applicability 

(c) This AD applies to Airbus Model A318– 

111, –112, –121, and –122 airplanes; Model 

A319–111, –112, –113, –114, –115, –131, 

–132, and –133 airplanes; Model A320–111, 

–211, –212, –214, –231, –232, and –233 

airplanes; and Model A321–111, –112, –131, 

–211, –212, –213, –231, and –232 airplanes; 

certificated in any category, all manufacturer 

serial numbers (S/Ns), if equipped with 

carbon fiber reinforced plastic rudders 

having part numbers (P/Ns) and S/Ns as 

listed in Table 1 of this AD. 

BILLING CODE 4910–13–P 


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BILLING CODE 4910–13–C 

Note 1: Only rudder P/N D554 71000 010 

00 having affected rudder S/Ns TS–1069 and 

TS–1090 and rudder P/N D554 71000 012 00 

having affected rudder S/N TS–1227, have a 

core density of 24 kilogram (kg)/meters cubed 

(m3). 

Subject 

(d) Air Transport Association (ATA) of 

America Code 55: Stabilizers. 

Reason 

(e) The mandatory continuing 

airworthiness information (MCAI) states: 

Surface defects were visually detected on 

the rudder of one A319 and one A321 inservice aeroplane. 

Investigation has determined that the 

defects reported on both rudders 

corresponded to areas that had been 

reworked in production. The investigation 

confirmed that the defects were a result of 

de-bonding between the skin and honeycomb 

core. 

An extended de-bonding, if not detected 

and corrected, may degrade the structural 

integrity of the rudder. The loss of the rudder 

leads to degradation of the handling qualities 

and reduces the controllability of the 

aeroplane. 

This AD requires inspections of specific 

areas and, when necessary, the application of 

corrective actions for those rudders where 

production reworks have been identified. 

Inspections include vacuum loss 

inspections for de-bonding of the rudders in 

reinforced areas and other areas (splice/lower 

rib/upper edge/leading edge/other specified 

locations), and elasticity laminate checks for 

de-bonding of the rudders in the trailing edge 

area and other areas (splice/lower rib/upper 

edge/leading edge/other specified locations). 

Corrective actions include contacting Airbus 

for further instruction and doing the repair. 

Compliance 

(f) You are responsible for having the 

actions required by this AD performed within 

the compliance times specified, unless the 

actions have already been done. 

Actions 

(g) For rudders with a honeycomb core 

density of 24 kg/m3 (rudder P/N D554 71000 

010 00 having affected rudder S/Ns TS–1069 

and TS–1090 and rudder P/N D554 71000 

012 00 having affected rudder S/N TS–1227), 

do the actions specified in paragraphs (g)(1), 

(g)(2), (g)(3), and (g)(4) of this AD, in 

accordance with Airbus All Operators Telex 

(AOT) A320–55A1038, Revision 02, dated 

September 28, 2009, for the locations defined 

in the AOT. 

(1) Within 200 days after the effective date 

of this AD, perform a vacuum loss inspection 

on the rudder reinforced area. 

(2) Within 20 months after the effective 

date of this AD, perform an elasticity 

laminate checker inspection on the rudder 

trailing edge area. Repeat the inspection two 

times, at intervals not to exceed 4,500 flight 

cycles but not sooner than 4,000 flight cycles 

after the last inspection. 

(3) Within 200 days after the effective date 

of this AD, perform an elasticity laminate 

checker inspection of the other areas (splice/ 

lower rib/upper edge/leading edge/and other 

specified locations). Repeat the inspection at 

intervals not to exceed 1,500 flight cycles or 

200 days, whichever comes first. 

(4) Within 20 months after the effective 

date of this AD, perform a vacuum loss 

inspection of the other areas (splice/lower 

rib/upper edge/leading edge/other specified 

locations). Accomplishment of the action 

specified in paragraph (g)(4) of this AD 

terminates the requirements of paragraph 

(g)(3) of this AD. 

(h) For rudders that do not have a 

honeycomb core density of 24 kg/m3 (all 

rudders identified in Table 1 of this AD, 

except: Rudder P/N D554 71000 010 00 

having affected rudder S/Ns TS–1069 and 

TS–1090 and rudder P/N D554 71000 012 00 

having affected rudder S/N TS–1227), do the 

actions specified in paragraphs (h)(1), (h)(2), 

(h)(3), and (h)(4) of this AD, in accordance 

with Airbus AOT A320–55A1038, Revision 

02, dated September 28, 2009, for the 

locations defined in the AOT. For this AD, 

‘‘reference date’’ is defined as the effective 

date of this AD or the date when the rudder 

will accumulate 20,000 total flight cycles 

from its first installation on an airplane, 

whichever occurs later. 

(1) Within 200 days after the reference 

date, perform a vacuum loss inspection on 

the rudder reinforced area. 

(2) Within 20 months after the reference 

date, perform an elasticity laminate checker 

inspection on the rudder trailing edge area. 

Repeat the inspection two times at intervals 

not to exceed 4,500 flight cycles but not 

sooner than 4,000 flight cycles after the last 

inspection. 

(3) Within 200 days after the reference 

date, perform an elasticity laminate checker 

inspection of the other areas (splice/lower 

rib/upper edge/leading edge/other specified 

locations). Repeat the inspection at intervals 

not to exceed 1,500 flight cycles or 200 days, 

whichever comes first. 

(4) Within 20 months after the reference 

date, perform a vacuum loss inspection of the 

other areas (splice/lower rib/upper edge/ 

leading edge/other specified locations). 

Accomplishment of the actions specified in 

this paragraph terminates the requirements of 

paragraph (h)(3) of this AD. 

(i) In case of de-bonding found during any 

inspection required by paragraph (g) or (h) of 

this AD, before further flight, contact Airbus 

for further instructions and apply the 

associated instructions and corrective actions 

in accordance with the approved data 

provided. 

(j) At the applicable time specified in 

paragraph (j)(1) or (j)(2) of this AD, submit a 

report of the findings (both positive and 

negative), of each inspection required by 

paragraphs (g) and (h) of this AD. The report 

must include the inspection results, as 

specified in Airbus Technical Disposition 

TD/K4/S2/27086/2009, Issue E, dated 

September 17, 2009. For positive findings, 

submit the report to the Manager, Seer1/ 


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Seer2/Seer3 Customer Services; fax +33 (0)5 

61 93 28 73; e-mail 

region1.structurerepairsupport@airbus.com, 

region2.structurerepairsupport@airbus.com, 

or 

region3.structurerepairsupport@airbus.com. 

For negative findings, submit the report to 

Nicolas Seynaeve, Sees1, Customer Services; 

telephone +33 (0)5 61 93 34 38; fax +33 (0)5 

61 93 36 14; e-mail 

nicolas.seynaeve@airbus.com. 

(1) For any inspection done on or after the 

effective date of this AD: Submit the report 

within 30 days after the inspection. 

(2) For any inspection done before the 

effective date of this AD: Submit the report 

within 30 days after the effective date of this 

AD. 

(k) All rudders that have passed the 

inspection specified in paragraphs (g)(1), 

(g)(2), (g)(3), (g)(4), (h)(1), (h)(2), (h)(3), and 

(h)(4) of this AD, before the effective date of 

this AD in accordance with Airbus AOT 

A320–55A1038, dated April 22, 2009; AOT 

A320–55A1038, Revision 01, dated June 10, 

2009; or Airbus Technical Disposition TD/ 

K4/S2/27051/2009, Issue B, dated February 

25, 2009; are compliant with this AD for the 

areas inspected; except additional areas 

requiring inspection, as defined in Section 0, 

‘‘Reason for Revision,’’ of Airbus AOT A320– 

55A1038, Revision 02, dated September 28, 

2009, must be inspected as specified in 

paragraph (g) or (h) of this AD. For all areas, 

the repetitive inspections required by 

paragraph (g) or (h) of this AD remain 

applicable. 

(l) After the effective date of this AD, no 

rudder listed in Table 1 of this AD may be 

installed on any airplane, unless the rudder 

is in compliance with the requirements of 

this AD. 

FAA AD Differences 

Note 2: This AD differs from the MCAI 

and/or service information as follows: No 

differences. 

Other FAA AD Provisions 

(m) 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: Tim Dulin, 

Aerospace Engineer, International Branch, 

ANM–116, Transport Airplane Directorate, 

FAA, 1601 Lind Avenue, SW., Renton, 

Washington 98057–3356; telephone (425) 

227–2141; 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. 

The AMOC approval letter must specifically 

reference this AD. 

(2) Airworthy Product: For any requirement 

in this AD to obtain corrective actions from 

a manufacturer or other source, use these 

actions if they are FAA-approved. Corrective 

actions are considered FAA-approved if they 

are approved by the State of Design Authority 

(or their delegated agent). You are required 

to assure the product is airworthy before it 

is returned to service. 

(3) Reporting Requirements: For any 

reporting requirement in this AD, under the 

provisions of the Paperwork Reduction Act 

(44 U.S.C. 3501 et seq.), the Office of 

Management and Budget (OMB) has 

approved the information collection 

requirements and has assigned OMB Control 

Number 2120–0056. 

Related Information 

(n) Refer to MCAI European Aviation 

Safety Agency Airworthiness Directive 2009– 

0141, dated July 2, 2009; Airbus All 

Operators Telex A320–55A1038, Revision 02, 

dated September 28, 2009; and Airbus 

Technical Disposition TD/K4/S2/27086/ 

2009, Issue E, dated September 17, 2009; for 

related information. 

Issued in Renton, Washington, on March 

25, 2010. 

Ali Bahrami, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 2010–7461 Filed 4–1–10; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2010–0278; Directorate 

Identifier 2009–NM–255–AD] 

RIN 2120–AA64 

Airworthiness Directives; Airbus Model 

A330–223, –321, –322, and –323 

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: During accomplishment of 

Damage Tolerant—Airworthiness 

Limitation Item task 712106–01–01 from 

A330 ALS Part 2, an A330 operator 

found a Fluorescent Penetrant 

Inspection (FPI) indication in the head 

of the shank filet radius in one of the 

Pratt & Whitney (PW) forward (FWD) 

engine mount pylon bolts. Dual-bolt 

fractures could lead to inability for 

mount assembly to sustain loads which 

may lead to an engine mount failure and 

consequently to engine separation from 

the aeroplane during flight, which 

would constitute an unsafe condition. 

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 May 17, 2010. 

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— 

Airworthiness Office—EAL, 1 Rond 

Point Maurice Bellonte, 31707 Blagnac 

Cedex, France; telephone +33 5 61 93 36 

96; fax +33 5 61 93 45 80; e-mail 

airworthiness.A330–A340@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. 

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: 

Vladimir Ulyanov, Aerospace Engineer, 

International Branch, ANM–116, 

Transport Airplane Directorate, FAA, 

1601 Lind Avenue, SW., Renton, 

Washington 98057–3356; telephone 

(425) 227–1138; fax (425) 227–1149. 

SUPPLEMENTARY INFORMATION: 

Comments Invited 

We invite you to send any written 

relevant data, views, or arguments about 


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