Federal Register / Vol. 75, No. 126 / Thursday, July 1, 2010 / Proposed Rules 38061 

low bolt torque, loose or rotating nuts, 

suspect integrity of the bolt/nut assembly, or 

gaps between the fitting and wing structure) 

is found, before further flight, do the actions 

specified in paragraphs (i)(1), (i)(2), (i)(3), 

(i)(4), and (i)(5) of this AD, in accordance 

with the Accomplishment Instructions of 

BAE Systems (Operations) Limited 

Inspection Service Bulletin ISB.57–033, 

Revision 9, dated October 10, 2006. 

(1) Do a detailed inspection of the sealant 

for cracks at and around all rear spar root 

joint attachment bolts. 

(2) Do a detailed inspection of the bolt for 

damage or evidence of the nut being 

tightened to the end of the thread. 

(3) Do a detailed inspection of the wear 

pattern on the seating surfaces of the bolt and 

nut to determine if the bolt and nut have 

been evenly seated on the structure. 

(4) Do a detailed inspection of the bolt hole 

and surrounding area for damage. 

(5) Do a detailed inspection to determine 

that the hole edge radius on the forward face 

of the rear spar meets the dimensions 

specified in Table 4 of the Accomplishment 

Instructions of BAE Systems (Operations) 

Limited Inspection Service Bulletin ISB.57– 

033, Revision 9, dated October 10, 2006. 

(j) If during any inspection required by 

paragraph (h) or (i) of this AD, any defects 

(e.g., evidence of fuel seepage, damaged bolts 

or low bolt torque, loose or rotating nuts, 

suspect integrity of the bolt/nut assembly, 

gaps between the fitting and wing structure, 

cracked sealant, bolt damage or evidence of 

the nut being tightened to the end of the 

thread, uneven seating of the bolt and nut, 

bolt hole and surrounding area damage, or 

hole edge radius out of dimensions specified 

in Table 4 of the Accomplishment 

Instructions of BAE Systems (Operations) 

Limited Inspection Service Bulletin ISB.57– 

033, Revision 9, dated October 10, 2006), is 

found, before further flight, do all applicable 

correction actions, which include either 

replacing the bolt or repairing the defect, in 

accordance with the Accomplishment 

Instructions of BAE Systems (Operations) 

Limited Inspection Service Bulletin ISB.57– 

033, Revision 9, dated October 10, 2006. 

(k) Repeat the inspections in paragraph (h) 

of this AD thereafter, at the applicable time 

specified in Table 1 of this AD, for each 

individual location. 

TABLE 1—COMPLIANCE TIMES FOR REPEAT INSPECTIONS

If the location has— Then repeat the inspection— 

A Hi-Lok bolt ............................................................................................. Within 4,000 flight cycles or 24 months, whichever occurs earlier, after 

doing the last inspection. 

A tension bolt that was not replaced during the inspections in paragraphs (h) and (i) of this AD and no defects were found.Within 8,000 flight cycles or 48 months, whichever occurs earlier, after 

doing the last inspection. 

A tension bolt that was replaced as required by paragraph (j) of this AD Within 4,000 flight cycles or 24 months, whichever occurs earlier after 

doing the replacement. 

A tension bolt that was not replaced and any defects were repaired as 

required by paragraph (j) of this AD.

Within 4,000 flight cycles or 24 months, whichever occurs earlier after 

doing the repair specified in paragraph (j) of this AD. 

FAA AD Differences 

Note 1: This AD differs from the MCAI 

and/or service information as follows: 

Although BAE Systems (Operations) Limited 

Inspection Service Bulletin ISB.57–033, 

Revision 9, dated October 10, 2006, allows 

additional time to rectify the defect for the 

corrective action depending on the condition, 

this AD requires rectifying the defect before 

further flight. 

Other FAA AD Provisions 

(l) 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. 

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 

(m) Refer to MCAI European Aviation 

Safety Agency Airworthiness Directive 2007– 

0270 R1, dated November 7, 2007; and BAE 

Systems (Operations) Limited Inspection 

Service Bulletin ISB.57–033, Revision 9, 

dated October 10, 2006; for related 

information. 

Issued in Renton, Washington, on June 23, 

2010. 

Ali Bahrami, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 2010–15981 Filed 6–30–10; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2010–0644; Directorate 

Identifier 2009–NM–204–AD] 

RIN 2120–AA64 

Airworthiness Directives; Airbus Model 

A300 B4–600 Series Airplanes; Model 

A300 B4–600R Series Airplanes; Model 

A300 C4–605R Variant F Airplanes; and 

Model A300 F4–600R 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: 

Within the framework of the A300–600 

aircraft Service Life Extension programme 

(42 500 FC [flight cycles]), it has been 

concluded that a reinforcement of the 

junction of frame bases at FR48, FR49 and 

FR51 to FR53 is necessary to enable the 

aircraft to reach the Extended Service Goal 

(ESG). 

WReier-Aviles on DSKGBLS3C1PROD with PROPOSALS

38062 Federal Register / Vol. 75, No. 126 / Thursday, July 1, 2010 / Proposed Rules 

* * * [Failure of the frame base], if not 

corrected, could affect the structural integrity 

of the fuselage. 

* * * * * 

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 August 16, 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– 

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. 

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–2010–0644; Directorate Identifier 

2009–NM–204–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 2009–0188, 

dated August 26, 2009 (referred to after 

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

condition for the specified products. 

The MCAI states: 

Within the framework of the A300–600 

aircraft Service Life Extension programme 

(42 500 FC [flight cycles]), it has been 

concluded that a reinforcement of the 

junction of frame bases at FR48, FR49 and 

FR51 to FR53 is necessary to enable the 

aircraft to reach the Extended Service Goal 

(ESG). 

* * * [Failure of the frame base], if not 

corrected, could affect the structural integrity 

of the fuselage. 

For the reasons described above, this AD 

requires the reinforcement of the affected 

junction of frame bases. 

Required actions include doing a 

dimensional measurement of the holes, 

and doing corrective actions if 

necessary; doing an eddy current 

inspection of the holes for cracking, and 

doing corrective actions if necessary; 

and doing cold expansion of the holes 

and installing fasteners. Corrective 

actions include contacting Airbus for 

repair instructions and doing the repair. 

You may obtain further information by 

examining the MCAI in the AD docket. 

Relevant Service Information 

Airbus has issued Mandatory Service 

Bulletin A300–53–6161, Revision 02, 

including Appendix 01, dated October 

16, 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 122 products of U.S. 

registry. We also estimate that it would 

take about 81 work-hours per product to 

comply with the basic requirements of 

this proposed AD. The average labor 

rate is $85 per work-hour. Required 

parts would cost about $12,300 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 

$2,340,570, or $19,185 per product. 

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Federal Register / Vol. 75, No. 126 / Thursday, July 1, 2010 / Proposed Rules 38063 

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: 

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–2010–0644; 

Directorate Identifier 2009–NM–204–AD. 

Comments Due Date 

(a) We must receive comments by August 

16, 2010. 

Affected ADs 

(b) None. 

Applicability 

(c) This AD applies to Airbus Model A300 

B4–601, B4–603, B4–620, B4–622, B4–605R, 

B4–622R; Model A300 C4–605R Variant F; 

Model F4–605R and F4–622R airplanes; 

certificated in any category; on which 

modification 12699 has not been completed. 

Subject 

(d) Air Transport Association (ATA) of 

America Code 53: Fuselage. 

Reason 

(e) The mandatory continuing 

airworthiness information (MCAI) states: 

Within the framework of the A300–600 

aircraft Service Life Extension programme 

(42 500 FC), it has been concluded that a 

reinforcement of the junction of frame bases 

at FR48, FR49 and FR51 to FR53 is necessary 

to enable the aircraft to reach the Extended 

Service Goal (ESG). 

* * * [Failure of the frame base], if not 

corrected, could affect the structural integrity 

of the fuselage. 

* * * * * 

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) Except for airplanes identified in 

paragraph (h) of this AD: At the time 

specified in paragraph (g)(1) or (g)(2) of this 

AD, as applicable, reinforce the junctions of 

frame bases FR48, FR49, FR51, FR52 and 

FR53, which includes doing a dimensional 

measurement of the holes, doing an eddy 

current inspection of the holes for cracking, 

doing a cold expansion of the holes, 

installing fasteners, and doing applicable 

corrective actions, in accordance with the 

Accomplishment Instructions of Airbus 

Mandatory Service Bulletin A300–53–6161, 

Revision 02, dated October 16, 2009. If 

cracking is found, before further flight, 

contact Airbus for repair instructions and do 

the repair. 

(1) For airplanes on which Airbus 

Modification No. 03986 has been 

accomplished as of the effective date of this 

AD: Before the accumulation of 37,600 total 

flight cycles. 

(2) For airplanes on which Airbus 

Modification No. 03986 has not been 

accomplished as of the effective date of this 

AD: Before the accumulation of 28,900 total 

flight cycles. 

(h) For airplanes modified prior to the 

effective date of this AD in accordance with 

the Accomplishment Instructions of Airbus 

Mandatory Service Bulletin A300–53–6161, 

dated February 13, 2009; or Revision 01, 

dated June 24, 2009: Within 10 days after the 

effective date of this AD, prior to doing any 

cold working process, determine if an eddy 

current inspection for cracking has been 

done, in accordance with the 

Accomplishment Instructions of Airbus 

Mandatory Service Bulletin A300–53–6161, 

Revision 02, dated October 16, 2009. If the 

eddy current inspection has not been done, 

or it cannot be proven that it has been done, 

before further flight, contact Airbus for 

instructions and accomplish those 

instructions. 

FAA AD Differences 

Note 1: This AD differs from the MCAI 

and/or service information as follows: No 

differences. 

Other FAA AD Provisions 

(i) 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 

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 

(j) Refer to MCAI European Aviation Safety 

Agency (EASA) Airworthiness Directive 

2009–0188, dated August 26, 2009; and 

Airbus Mandatory Service Bulletin A300–53– 

6161, Revision 02, dated October 16, 2009; 

for related information. 

WReier-Aviles on DSKGBLS3C1PROD with PROPOSALS

38064 Federal Register / Vol. 75, No. 126 / Thursday, July 1, 2010 / Proposed Rules 

Issued in Renton, Washington, on June 23, 

2010. 

Ali Bahrami, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 2010–15982 Filed 6–30–10; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2010–0643; Directorate 

Identifier 2010–NM–030–AD] 

RIN 2120–AA64 

Airworthiness Directives; Bombardier, 

Inc. Model DHC–8 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: 

The landing gear alternate extension 

system in the cockpit is accessible through an 

access panel located on the cockpit floor. 

There have been reports of failure of the 

access panel latch assembly as a consequence 

of repeated closure of the access panel 

involving the use of excessive force. Failure 

of the latch assembly can result in the access 

panel being jammed in the closed position, 

and require mechanical prying to open. 

An undetected or uncorrected latch failure 

condition in the access panel can prevent 

immediate access to the landing gear 

alternate extension system by the flight crew 

during an emergency. * * * 

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 August 16, 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 Bombardier, 

Inc., 400 Coˆte-Vertu Road West, Dorval, 

Que ́bec H4S 1Y9, Canada; telephone 

514–855–5000; fax 514–855–7401; email thd.qseries@aero.bombardier.com; 

Internet http://www.bombardier.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: 

Craig Yates, Aerospace Engineer, 

Airframe and Mechanical Systems 

Branch, ANE–171, New York Aircraft 

Certification Office, FAA, 1600 Stewart 

Avenue, Suite 410, Westbury, New York 

11590; telephone (516) 228–7355; 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. 

FAA–2010–0643; Directorate Identifier 

2010–NM–030–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 Transport Canada Civil Aviation 

(TCCA), which is the aviation authority 

for Canada, has issued Canadian 

Airworthiness Directive CF–2009–46, 

dated December 14, 2009 (referred to 

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

unsafe condition for the specified 

products. The MCAI states: 

The landing gear alternate extension 

system in the cockpit is accessible through an 

access panel located on the cockpit floor. 

There have been reports of failure of the 

access panel latch assembly as a consequence 

of repeated closure of the access panel 

involving the use of excessive force. Failure 

of the latch assembly can result in the access 

panel being jammed in the closed position, 

and require mechanical prying to open. 

An undetected or uncorrected latch failure 

condition in the access panel can prevent 

immediate access to the landing gear 

alternate extension system by the flight crew 

during an emergency. This Directive requires 

the replacement of the existing latch 

assembly with a stronger modified latch 

assembly. 

You may obtain further information by 

examining the MCAI in the AD docket. 

Relevant Service Information 

Bombardier, Inc. has issued Service 

Bulletin 8–32–166, Revision A, dated 

January 29, 2009; and Service Bulletin 

84–32–57, Revision A, dated June 15, 

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. 

WReier-Aviles on DSKGBLS3C1PROD with PROPOSALS