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

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—C OMPLIANCE 

### T IMES FOR 

### R EPEAT 

### I NSPECTIONS

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 occ urs 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).


### 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.


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


### 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 Co ˆ te-Vertu Road West, Dorval, Que  ́ bec H4S 1Y9, Canada; telephone514–855–5000; 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.