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
Federal Register / Vol. 73, No. 181 / Wednesday, September 17, 2008 / Proposed Rules 53771 

2008–NM–008–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 because of 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 

On December 21, 2006, we issued AD 

2006–26–12, amendment 39–14870 (72 

FR 256, January 4, 2007), for certain 

Airbus Model A330, A340–200, and 

A340–300 series airplanes. That AD 

superseded AD 2005–06–08, 

amendment 39–14016 (70 FR 13345, 

March 21, 2005) and requires repetitive 

inspections of a certain bracket that 

attaches the flight deck instrument 

panel to the airplane structure; 

replacement of the bracket with a new, 

improved bracket; and related 

investigative and corrective actions if 

necessary. That AD further requires 

replacement of the existing bracket with 

a titanium-reinforced bracket, which 

would end the repetitive inspections. 

AD 2006–26–12 resulted from a report 

of cracking damage found on certain 

brackets that were replaced per the 

requirements of AD 2005–06–08. We 

issued AD 2006–26–12 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. 

Actions Since Existing AD Was Issued 

Since we issued AD 2006–26–12, we 

have received a report that incorrect 

torque values could damage the bracket. 

These incorrect torque values were 

included in Airbus Service Bulletins 

A330–25–3249 and A340–25–4245, both 

dated May 3, 2005. We referred to those 

service bulletins in AD 2006–26–12 as 

the appropriate sources of service 

information for replacing the existing 

bracket with a titanium-reinforced 

bracket. Airbus has now revised these 

service bulletins (both Revision 01, both 

dated July 10, 2007) to include the 

correct torque values. 

The European Aviation Safety Agency 

(EASA) mandated the service 

information and issued EASA 

airworthiness directives 2007–0281 and 

2007–0282, both dated November 6, 

2007, to ensure the continued 

airworthiness of these airplanes in the 

European Union. 

Relevant Service Information 

As stated above, Airbus has issued 

Mandatory Service Bulletins A330–25– 

3249 and A340–25–4245, both Revision 

01, and both dated July 10, 2007. The 

procedures in Revision 01 of the service 

bulletins are essentially the same as the 

procedures in the original issue. 

However, Revision 01 of the service 

bulletins specifies new procedures for 

airplanes on which the bracket has been 

replaced in accordance with the 

procedures specified in the original 

issue. The new procedures are removing 

the fasteners of the titanium-reinforced 

bracket and, if a fastener is broken, 

doing a detailed inspection for cracking 

of the horizontal beam. If any crack is 

found, the service bulletins specify the 

corrective action of contacting Airbus 

for repair procedures. If no crack is 

found, the service bulletins specify the 

corrective action of installing new 

fasteners on the bracket. 

FAA’s Determination and Requirements 

of the Proposed AD 

These airplanes 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 EASA has kept the FAA informed of 

the situation described above. We have 

examined the EASA’s findings, 

evaluated all pertinent information, and 

determined that AD action is necessary 

for airplanes of this type design that are 

certificated for operation in the United 

States. 

This proposed AD would supersede 

AD 2006–26–12 and would retain the 

requirements of the existing AD. This 

proposed AD would also require 

accomplishing the actions specified in 

Airbus Mandatory Service Bulletins 

A330–25–3249 and A340–25–4245, both 

Revision 01, and both dated July 10, 

2007, as discussed under ‘‘Difference 

Between the Proposed AD and the 

EASA Airworthiness Directives.’’ 

Difference Between the Proposed AD 

and the EASA Airworthiness Directives 

The EASA airworthiness directives 

specify contacting Airbus for 

instructions on how to repair certain 

conditions. This proposed AD requires 

repairing those conditions using a 

method that we or the EASA 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 proposed 

AD, a repair we or the EASA (or its 

delegated agent) approve would be 

acceptable for compliance with this 

proposed AD. 

Costs of Compliance 

The following table provides the 

estimated costs for U.S. operators to 

comply with this proposed AD. This 

proposed AD would affect about 24 

Model A330 series airplanes of U.S. 

registry. There are currently no affected 

Model A340–200 and –300 series 

airplanes of U.S. registry. However, if 

one of these airplanes is imported and 

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

these cost estimates would also apply to 

those airplanes. 

ESTIMATED COSTS

Action Work hours Average labor 

rate per hour Parts Cost per airplane Fleet cost 

Inspections (required by AD 

2006–26–12).

1 $80 $0 $80, per inspection cycle ...... $1,920, per inspection cycle. 

Replacement and investigative actions (required by 

AD 2006–26–12).

9 80 330 $1,050 ................................... $25,200. 

One-time inspection (new 

proposed action).

2 80 0 $160 ...................................... Up to $3,840. 


pwalker on PROD1PC71 with PROPOSALS
53772 Federal Register / Vol. 73, No. 181 / Wednesday, September 17, 2008 / Proposed Rules 

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 

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 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. 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, 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 Federal Aviation 

Administration (FAA) amends § 39.13 

by removing amendment 39–14870 (72 

FR 256, January 4, 2007) and adding the 

following new airworthiness directive 

(AD): 

Airbus: Docket No. FAA–2008–0980; 

Directorate Identifier 2008–NM–008–AD. 

Comments Due Date 

(a) The FAA must receive comments on 

this AD action by October 17, 2008. 

Affected ADs 

(b) This AD supersedes AD 2006–26–12. 

Applicability 

(c) This AD applies to all Airbus Model 

A330 airplanes, and Model A340–200 and 

A340–300 series airplanes; certificated in any 

category; except those airplanes identified in 

paragraphs (c)(1), (c)(2) and (c)(3) of this AD. 

(1) Model A330 airplanes, and Model 

A340–200, and A340–300 series airplanes on 

which Airbus Modification 53446 has been 

incorporated in production. 

(2) Model A330 airplanes on which Airbus 

Service Bulletin A330–25–3249, Revision 01, 

dated July 10, 2007, has been embodied in 

service. 

(3) Model A340–200 and –300 series 

airplanes on which Airbus Service Bulletin 

A340–25–4245, Revision 01, dated July 10, 

2007, has been embodied in service. 

Unsafe Condition 

(d) This AD results from a report that 

incorrect torque values could damage a 

certain bracket that attaches the flight deck 

instrument panel to the airplane structure. 

We are issuing 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. 

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. 

Service Bulletin Reference 

(f) The term ‘‘service bulletin,’’ as used in 

this AD, means the Accomplishment 

Instructions of the service bulletins identified 

in paragraphs (f)(1), (f)(2), and (f)(3) of this 

AD, as applicable. 

(1) For the requirements of paragraphs (g), 

(h), and (i) of this AD: Airbus Service 

Bulletins A330–25–3227 and A340–25–4230, 

both Revision 01, both dated May 3, 2005. 

Accomplishment before February 8, 2007 

(the effective date of AD 2006–26–12) of 

Airbus Service Bulletins A330–25–3227 and 

A340–25–4230, both including Appendix 01, 

both dated June 17, 2004, as applicable, is an 

acceptable means of compliance for 

paragraphs (g), (h), and (i) of this AD. 

(2) For the requirements of paragraph (k) of 

this AD done before the effective date of this 

AD: Airbus Service Bulletins A330–25–3249 

and A340–25–4245, both dated May 3, 2005, 

as applicable. 

(3) For the requirements of paragraph (k) of 

this AD done after the effective date of this 

AD, and for the requirements of paragraph (l) 

of this AD: Airbus Mandatory Service 

Bulletins A330–25–3249 and A340–25–4245, 

both Revision 01, both dated July 10, 2007, 

as applicable. 

Restatement of the Requirements of AD 

2006–26–12 

Initial Inspection 

(g) At the applicable time specified in 

paragraph (g)(1) or (g)(2) of this AD, perform 

a detailed inspection of the bracket having 

part number (P/N) F2511012920000, which 

attaches the flight deck instrument panel to 

airplane structure, in accordance with the 

applicable service bulletin. 

(1) For Model A330 series airplanes: Prior 

to the accumulation of 16,500 total flight 

cycles, or within 60 days after April 25, 2005 

(the effective date of AD 2005–06–08, 

amendment 39–14016, which was 

superseded by AD 2006–26–12), whichever is 

later. 

(2) For Model A340–200 and –300 series 

airplanes: Prior to the accumulation of 9,700 

total flight cycles, or within 2,700 flight 

cycles after April 25, 2005, whichever is 

later. 

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.’’ 

No Cracking/Repetitive Inspections 

(h) If no crack is found during the initial 

inspection required by paragraph (g) of this 

AD: Repeat the inspection thereafter at the 

applicable interval specified in paragraph 

(h)(1) or (h)(2) of this AD, until the 

replacement specified in paragraph (k) of this 

AD has been accomplished. 

(1) For Model A330 series airplanes: 

Intervals not to exceed 13,800 flight cycles. 

(2) For Model A340–200 and –300 series 

airplanes: Intervals not to exceed 7,000 flight 

cycles. 

Crack Found/Replacement and Repetitive 

Inspections 

(i) If any crack is found during any 

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

this AD: Do the actions in paragraphs (i)(1) 

and (i)(2) of this AD, except as provided by 

paragraph (j) of this AD, until 

accomplishment of the replacement required 

by paragraph (k) of this AD. 

(1) Before further flight: Replace the 

cracked bracket with a new, improved 

bracket having P/N F2511012920095, in 

accordance with the service bulletin. 

(2) Repeat the inspection of the replaced 

bracket as required by paragraph (g) of this 

AD, at the time specified in paragraph (i)(2)(i) 

or (i)(2)(ii) of this AD. Then, do repetitive 

inspections or replace the bracket as 


pwalker on PROD1PC71 with PROPOSALS
Federal Register / Vol. 73, No. 181 / Wednesday, September 17, 2008 / Proposed Rules 53773 

specified in paragraph (h) or (i) of this AD, 

as applicable. 

(i) For Model A330 series airplanes: Within 

16,500 flight cycles after replacing the 

bracket. 

(ii) For Model A340–200 and –300 series 

airplanes: Within 9,700 flight cycles after 

replacing the bracket. 

(j) If both flanges of a bracket are found 

broken during any inspection required by 

this AD: Before further flight, replace the 

bracket as specified in paragraph (i) of this 

AD and perform any applicable related 

investigative and corrective actions (which 

may include inspections for damage to 

surrounding structure caused by the broken 

bracket, and corrective actions for any 

damage that is found), in accordance with a 

method approved by the Manager, 

International Branch, ANM–116, Transport 

Airplane Directorate, FAA; or the European 

Aviation Safety Agency (EASA) (or its 

delegated agent). 

Replacement of Brackets/Investigative and 

Corrective Actions 

(k) Except as required by paragraph (i)(1) 

of this AD: Within 72 months after February 

8, 2007 (the effective date of AD 2006–26– 

12), replace existing brackets having P/N 

F2511012920000 or P/N F2511012920095 

with titanium-reinforced brackets having P/N 

F2511305220096; and perform any related 

investigative and corrective actions (which 

may include detailed inspections for cracking 

of the bracket or damage to surrounding 

structure caused by a broken bracket, and 

applicable corrective actions for any damage 

that is found); in accordance with the 

applicable service bulletin. If any crack is 

found, before further flight, repair in 

accordance with the applicable service 

bulletin. Replacement of the affected bracket 

with a titanium-reinforced bracket having P/ 

N F2511305220096 ends the repetitive 

inspections required by paragraph (h) or (i) 

of this AD. Although the service bulletins 

specify to submit certain information to the 

manufacturer, this AD does not include that 

requirement. 

New Requirements of This AD 

One-Time Inspection 

(l) For airplanes on which the actions 

required by paragraph (k) of this AD have 

been accomplished before the effective date 

of this AD: At the applicable time in 

paragraph (l)(1) or (l)(2) of this AD, remove 

the fasteners of the titanium-reinforced 

bracket and, if a fastener is broken, do a 

detailed inspection for cracking of the 

horizontal beam. Do all applicable corrective 

actions before further flight. Do all actions in 

accordance with the applicable service 

bulletin. Where the applicable service 

bulletin specifies to contact Airbus, before 

further flight, repair in accordance with a 

method approved by the Manager, 

International Branch, ANM–116, Transport 

Airplane Directorate, FAA; or the EASA (or 

its delegated agent). 

(1) For Model A330 series airplanes: Prior 

to the accumulation of 16,500 total flight 

cycles, or within 20 months after the effective 

date of this AD, whichever occurs first. 

(2) For Model A340–200 and –300 series 

airplanes: Prior to the accumulation of 12,400 

total flight cycles, or within 20 months after 

the effective date of this AD, whichever 

occurs first. 

Alternative Methods of Compliance 

(AMOCs) 

(m)(1) 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: 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. 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) AMOCs approved previously in 

accordance with AD 2006–26–12 are 

approved as AMOCs for the corresponding 

provisions of this AD. 

Related Information 

(n) EASA airworthiness directives 2007– 

0281 and 2007–0282, both dated November 

6, 2007, also address the subject of this AD. 

Issued in Renton, Washington, on 

September 9, 2008. 

Michael J. Kaszycki, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. E8–21727 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–2008–0977; Directorate 

Identifier 2008–NM–124–AD] 

RIN 2120–AA64 

Airworthiness Directives; Bombardier 

Model CL–600–2B19 (Regional Jet 

Series 100 & 440) 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: 

Bombardier Aerospace has completed a 

system safety review of the CL–600–2B19 

aircraft fuel system against the new fuel tank 

safety standards * * *. 

The assessment showed that insufficient 

electrical bonding between the refuel/defuel 

shutoff valves and the aircraft structure could 

occur due to the presence of a nonconductive gasket (Gask-O-Seal). In addition, 

it was also determined that the presence of 

an anodic coating on the shutoff valve 

electrical conduit connection fitting could 

affect electrical bonding. The above 

conditions, if not corrected, could result in 

arcing and potential ignition source inside 

the fuel tank during lightning strikes and 

consequent fuel tank explosion. 

* * * * * 

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: 

Rocco Viselli, Aerospace Engineer, 

Airframe and Propulsion Branch, 

ANE–171, FAA, New York Aircraft 

Certification Office, 1600 Stewart 

Avenue, Suite 410, Westbury, New York 

11590; telephone (516) 228–7331; fax 

(516) 794–5531. 

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. 


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