53768 Federal Register / Vol. 73, No. 181 / Wednesday, September 17, 2008 / Proposed Rules 

FAA AD Differences 

Note: 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, Standards Office, 

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: Sarjapur Nagarajan, Aerospace 

Engineer, FAA, Small Airplane Directorate, 

901 Locust, Room 301, Kansas City, Missouri 

64106; telephone: (816) 329–4145; fax: (816) 

329–4090. Before using any approved AMOC 

on any airplane to which the AMOC applies, 

notify your appropriate principal inspector 

(PI) in the FAA Flight Standards District 

Office (FSDO), or lacking a PI, your local 

FSDO. 

(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 

(h) Refer to MCAI European Aviation 

Safety Agency (EASA) AD No. 2008–0139, 

dated July 24, 2008; Diamond Aircraft 

Industries GmbH Mandatory Service Bulletin 

No. MSB–42–058, dated May 21, 2008; and 

Diamond Aircraft Industries GmbH Work 

Instruction WI–MSB–42–058, dated March 

12, 2008, for related information. 

Issued in Kansas City, Missouri, on 

September 10, 2008. 

James E. Jackson, 

Acting Manager, Small Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. E8–21701 Filed 9–16–08; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2008–0979; Directorate 

Identifier 2008–NM–079–AD] 

RIN 2120–AA64 

Airworthiness Directives; Airbus Model 

A300–600 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: 

Further to initial qualification tests of the 

spoiler actuators currently installed in 

position No. 3 to 7 on A300–600 and A300– 

600ST aircraft fleet, a life limit [of 55,750 

flight hours] has been defined by the actuator 

manufacturer. Initially, this life limit had no 

repercussions, as it was situated well beyond 

the initial Design Service Goal (DSG) of the 

aircraft. However, due to the Extended 

Service Goal (ESG) activities, the spoiler 

actuator life limit can be reached in service, 

and therefore the spoiler actuators must be 

replaced before exceeding this limit. 

In order to mitigate the risk to have aircraft 

on which the three hydraulic circuits would 

be impacted by affected spoiler actuators, 

which could result in the loss of 

controllability of the aircraft, this 

Airworthiness Directive (AD) requires actions 

to ensure that at least the level of safety of 

one hydraulic circuit will be restored within 

an acceptable timeframe. 

* * * * * 

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 October 17, 2008. 

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. 

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–2008–0979; Directorate Identifier 

2008–NM–079–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 2008–0058, 

dated March 20, 2008 (referred to after 

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

condition for the specified products. 

The MCAI states: 

Further to initial qualification tests of the 

spoiler actuators currently installed in 

position No. 3 to 7 on A300–600 and A300– 

600ST aircraft fleet, a life limit [of 55,750 

flight hours] has been defined by the actuator 

manufacturer. Initially, this life limit had no 

repercussions, as it was situated well beyond 

the initial Design Service Goal (DSG) of the 

aircraft. However, due to the Extended 

Service Goal (ESG) activities, the spoiler 

actuator life limit can be reached in service, 

and therefore the spoiler actuators must be 

replaced before exceeding this limit. 

In order to mitigate the risk to have aircraft 

on which the three hydraulic circuits would 

be impacted by affected spoiler actuators, 

which could result in the loss of 

controllability of the aircraft, this 

Airworthiness Directive (AD) requires actions 

to ensure that at least the level of safety of 

one hydraulic circuit will be restored within 

an acceptable timeframe. 


pwalker on PROD1PC71 with PROPOSALS
Federal Register / Vol. 73, No. 181 / Wednesday, September 17, 2008 / Proposed Rules 53769 

EASA AD 2007–0245, issued on 05 

September 2007 as an interim action, is 

superseded by the present [EASA] AD. 

Corrective actions include replacing the 

spoiler actuator with a serviceable unit. 

You may obtain further information by 

examining the MCAI in the AD docket. 

Relevant Service Information 

Airbus has issued Service Bulletins 

A300–27–6060, including Appendix 01, 

dated February 18, 2008, and A300– 

27A6062, including Appendix 01, dated 

July 6, 2007. 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 135 products of U.S. 

registry. We also estimate that it would 

take about 8 work-hours per product to 

comply with the basic requirements of 

this proposed AD. The average labor 

rate is $80 per work-hour. Required 

parts would cost about $32,000 per 

product. Where the service information 

lists required parts costs that are 

covered under warranty, we have 

assumed that there will be no charge for 

these costs. As we do not control 

warranty coverage for affected parties, 

some parties may incur costs higher 

than estimated here. Based on these 

figures, we estimate the cost of the 

proposed AD on U.S. operators to be 

$4,406,400, or $32,640 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, 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: 

Airbus: Docket No. FAA–2008–0979; 

Directorate Identifier 2008–NM–079–AD. 

Comments Due Date 

(a) We must receive comments by October 

17, 2008. 

Affected ADs 

(b) None. 

Applicability 

(c) This AD applies to Airbus Model A300– 

600 airplanes, all serial numbers, certificated 

in any category; on which Smith spoiler 

actuators having part number (P/N) 

P376A0002–05, –06, –07, or –09, or P/N 

P725A0001–00 are installed. 

Subject 

(d) Air Transport Association (ATA) of 

America Code 27: Flight controls. 

Reason 

(e) The mandatory continuing 

airworthiness information (MCAI) states: 

Further to initial qualification tests of the 

spoiler actuators currently installed in 

position No. 3 to 7 on A300–600 and A300– 

600ST aircraft fleet, a life limit [of 55,750 

flight hours] has been defined by the actuator 

manufacturer. Initially, this life limit had no 

repercussions, as it was situated well beyond 

the initial Design Service Goal (DSG) of the 

aircraft. However, due to the Extended 

Service Goal (ESG) activities, the spoiler 

actuator life limit can be reached in service, 

and therefore the spoiler actuators must be 

replaced before exceeding this limit. 

In order to mitigate the risk to have aircraft 

on which the three hydraulic circuits would 

be impacted by affected spoiler actuators, 

which could result in the loss of 

controllability of the aircraft, this 

Airworthiness Directive (AD) requires actions 

to ensure that at least the level of safety of 

one hydraulic circuit will be restored within 

an acceptable timeframe. 

EASA AD 2007–0245, issued on 05 

September 2007 as an interim action, is 

superseded by the present [EASA] AD. 

Corrective actions include replacing the 

spoiler actuator with a serviceable unit. 

Actions and Compliance 

(f) Unless already done: Within 700 flight 

hours after the effective date of this AD, do 

the following actions. 

(1) Identify the total flight hours 

accumulated on each spoiler actuator at 

positions 3 through 7 on the left- and righthand sides of the airplane (FIN 22CP/23CP, 

24CP/25CP, 26CP/27CP, 60CP/61CP and 


pwalker on PROD1PC71 with PROPOSALS
53770 Federal Register / Vol. 73, No. 181 / Wednesday, September 17, 2008 / Proposed Rules 

62CP/63CP), in accordance with the 

Accomplishment Instructions of Airbus 

Service Bulletin A300–27A6062, dated July 

6, 2007. 

(2) For airplanes on which the status of any 

spoiler actuator is unknown (unknown 

number of accumulated flight hours, 

unknown date of manufacture and/or 

unknown serial number) the actuator must be 

considered as having exceeded 55,750 total 

flight hours. 

(3) For airplanes on which all three 

hydraulic circuits have a spoiler actuator that 

has accumulated or exceeds 55,000 total 

flight hours: Before the accumulation of 

55,750 total flight hours or within 700 flight 

hours after the effective date of this AD, 

whichever occurs later, on at least one 

hydraulic circuit, interchange the spoiler 

actuator with a serviceable unit from another 

hydraulic circuit, or replace the spoiler 

actuator with a serviceable unit, in 

accordance with the Accomplishment 

Instructions of Airbus Service Bulletin A300– 

27–6060, dated February 18, 2008. 

(4) For airplanes on which the actions 

required by paragraph (f)(1) of this AD, and, 

as applicable, paragraph (f)(3) of this AD 

have been accomplished, each airplane must 

continue to have at least one hydraulic 

circuit fitted with spoiler actuators that do 

not exceed 55,750 total flight hours. 

Note 1: For the purposes of this AD, a 

serviceable unit is a unit that has 

accumulated less than 55,750 flight hours. 

(5) The operator must not interchange or 

replace spoiler actuators on more than two 

hydraulic circuits at the same time. This will 

mitigate the risk of having a malfunction on 

the three hydraulic systems at the same time. 

FAA AD Differences 

Note 2: This AD differs from the MCAI 

and/or service information as follows: 

(1) This AD does not include the reporting 

requirement specified in paragraph (1) of the 

MCAI. The MCAI carried this requirement 

forward from European Aviation Safety 

Agency (EASA) Airworthiness Directive 

2007–0245, dated September 5, 2007. We 

previously determined that no action was 

required on our part regarding EASA AD 

2007–0245. 

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: 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 

appropriate principal inspector (PI) in the 

FAA Flight Standards District Office (FSDO), 

or lacking a PI, your local FSDO. 

(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, 

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 EASA Airworthiness 

Directive 2008–0058, dated March 20, 2008; 

and Airbus Service Bulletins A300–27–6060, 

dated February 18, 2008; and A300– 

27A6062, dated July 6, 2007; for related 

information. 

Issued in Renton, Washington, on 

September 9, 2008. 

Michael J. Kaszycki, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. E8–21724 Filed 9–16–08; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2008–0980; Directorate 

Identifier 2008–NM–008–AD] 

RIN 2120–AA64 

Airworthiness Directives; Airbus Model 

A330 Airplanes, and Model A340–200 

and A340–300 Series Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Notice of proposed rulemaking 

(NPRM). 

SUMMARY: The FAA proposes to 

supersede an existing airworthiness 

directive (AD) that applies to certain 

Airbus Model A330, A340–200, and 

A340–300 series airplanes. The existing 

AD currently requires repetitive 

inspections of a certain bracket that 

attaches the flight deck instrument 

panel to the airplane structure; related 

investigative and corrective actions if 

necessary; and replacement of the 

existing bracket with a titaniumreinforced bracket, which ends the 

repetitive inspections in the existing 

AD. This proposed AD would add 

requirements only for airplanes on 

which the existing bracket was replaced 

with a titanium-reinforced bracket in 

accordance with the existing AD. The 

additional requirement is a one-time 

inspection to determine if certain 

fasteners are broken or cracked, and 

corrective actions if necessary. This 

proposed AD results from a report that 

incorrect torque values could damage 

the bracket. We are proposing this AD 

to prevent a cracked bracket. Failure of 

this bracket, combined with failure of 

the horizontal beam, could result in 

collapse of the left part of the flight deck 

instrument panel, and consequent 

reduced controllability of the airplane. 

DATES: We must receive comments on 

this proposed AD by October 17, 2008. 

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 

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

Washington, DC 20590, between 9 a.m. 

and 5 p.m., Monday through Friday, 

except Federal holidays. 

For service information identified in 

this AD, contact Airbus, 1 Rond Point 

Maurice Bellonte, 31707 Blagnac Cedex, 

France. 

Examining the AD Docket 

You may examine the AD docket on 

the Internet at http:// 

www.regulations.gov; or in person at the 

Docket Management Facility 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 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 

this proposed AD. Send your comments 

to an address listed under the 

ADDRESSES section. Include ‘‘Docket No. 

FAA–2008–0980; Directorate Identifier 


pwalker on PROD1PC71 with PROPOSALS