Airworthiness Directives; Bombardier, Inc. Model DHC-8 Airplanes, 38064-38066 [2010-15983]

Download as PDF 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 Federal Aviation Administration (FAA), DOT. ACTION: Notice of proposed rulemaking (NPRM). AGENCY: 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: WReier-Aviles on DSKGBLS3C1PROD with PROPOSALS 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 https://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– VerDate Mar<15>2010 15:20 Jun 30, 2010 Jkt 220001 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, ˆ Inc., 400 Cote-Vertu Road West, Dorval, ´ Quebec H4S 1Y9, Canada; telephone 514–855–5000; fax 514–855–7401; email thd.qseries@aero.bombardier.com; Internet https://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 https://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 PO 00000 Frm 00023 Fmt 4702 Sfmt 4702 comment period for domestic transport ADs. We will post all comments we receive, without change, to https:// 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. E:\FR\FM\01JYP1.SGM 01JYP1 Federal Register / Vol. 75, No. 126 / Thursday, July 1, 2010 / Proposed Rules 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 198 products of U.S. registry. We also estimate that it would take about 3 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 $815 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 $211,860, or $1,070 per product. WReier-Aviles on DSKGBLS3C1PROD with PROPOSALS Authority for This Rulemaking 15:20 Jun 30, 2010 Jkt 220001 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. 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. VerDate Mar<15>2010 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. § 39.13 [Amended] 2. The FAA amends § 39.13 by adding the following new AD: Bombardier, Inc.: Docket No. FAA–2010– 0643; Directorate Identifier 2010–NM– 030–AD. Comments Due Date (a) We must receive comments by August 16, 2010. Affected ADs (b) None. Applicability (c) This AD applies to the airplanes identified in paragraphs (c)(1) and (c)(2) of this AD, certificated in any category. (1) Bombardier, Inc. Model DHC–8–101, –102, –103, –106, –201, –202, –301, –311, and –315 airplanes, serial numbers 003 through 658 inclusive. (2) Bombardier, Inc. Model DHC–8–400, –401, –402 airplanes, serial numbers 4001, 4003, 4004, 4006, and 4008 through 4187 inclusive. PO 00000 Frm 00024 Fmt 4702 Sfmt 4702 38065 Subject (d) Air Transport Association (ATA) of America Code 32: Landing gear. Reason (e) The mandatory continuing airworthiness information (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. * * * 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) Within 6,000 flight hours or 36 months after the effective date of this AD, whichever comes first: Replace the latch assembly of the access panel for the alternate extension system for the landing gear with a modified latch assembly, in accordance with the Accomplishment Instructions of Bombardier Service Bulletin 8–32–166, Revision A, dated January 29, 2009 (for Model DHC–8–100, DHC–8–200, and DHC–8–300 series airplanes); or Bombardier Service Bulletin 84–32–57, Revision A, dated June 15, 2009 (for Model DHC–8–400 series airplanes). Actions Accomplished According to Previous Issue of Service Bulletin (h) Actions accomplished before the effective date of this AD according to Bombardier Service Bulletin 8–32–166, dated April 14, 2008; or Bombardier Service Bulletin 84–32–57, dated April 30, 2008; as applicable; are considered acceptable for compliance with the corresponding actions specified in this AD. FAA AD Differences Note 1: This AD differs from the MCAI and/or service information as follows: No differences. Other FAA AD Provisions (i) The following provisions also apply to this AD: (1) Alternative Methods of Compliance (AMOCs): The Manager, New York Aircraft Certification Office, ANE–170, 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: Program Manager, Continuing Operational Safety, FAA, New York ACO, 1600 Stewart Avenue, Suite 410, Westbury, New York, 11590; telephone 516–228–7300; fax 516– 794–5531. Before using any approved AMOC on any airplane to which the AMOC applies, notify your principal maintenance inspector E:\FR\FM\01JYP1.SGM 01JYP1 38066 Federal Register / Vol. 75, No. 126 / Thursday, July 1, 2010 / Proposed Rules (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 Canadian Airworthiness Directive CF–2009–46, dated December 14, 2009; Bombardier Service Bulletin 8–32–166, Revision A, dated January 29, 2009; and Bombardier Service Bulletin 84–32–57, Revision A, dated June 15, 2009; for related information. Issued in Renton, Washington, on June 23, 2010. Ali Bahrami, Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 2010–15983 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–2010–0646; Directorate Identifier 2009–NM–223–AD] RIN 2120–AA64 Airworthiness Directives; The Boeing Company Model 727, 727C, 727–100, 727–100C, 727–200, and 727–200F Series Airplanes WReier-Aviles on DSKGBLS3C1PROD with PROPOSALS AGENCY: Federal Aviation Administration (FAA), DOT. ACTION: Notice of proposed rulemaking (NPRM). SUMMARY: We propose to adopt a new airworthiness directive (AD) for all Model 727, 727C, 727–100, 727–100C, 727–200, and 727–200F series airplanes. This proposed AD would require repetitive detailed inspections of the aft pressure bulkhead web for cracking, and repair if necessary. For certain airplanes, this proposed AD also would provide for an optional preventative modification of the aft pressure bulkhead web, which would terminate VerDate Mar<15>2010 15:20 Jun 30, 2010 Jkt 220001 certain repetitive detailed inspections. This proposed AD results from reports of cracks in the aft pressure bulkhead web. We are proposing this AD to detect and correct cracking in the aft pressure bulkhead web, which could adversely affect the structural integrity of the airplane, resulting in difficulty maintaining cabin pressurization or rapid decompression of the airplane. 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 https://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 proposed AD, contact Boeing Commercial Airplanes, Attention: Data & Services Management, P.O. Box 3707, MC 2H–65, Seattle, Washington 98124– 2207; telephone 206–544–5000, extension 1; fax 206–766–5680; e-mail me.boecom@boeing.com; Internet https://www.myboeingfleet.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 https:// 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: Berhane Alazar, Aerospace Engineer, Airframe Branch, ANM–120S, FAA, Seattle Aircraft Certification Office, 1601 Lind Avenue, SW., Renton, Washington 98057–3356; telephone (425) 917–6577; fax (425) 917–6590. PO 00000 Frm 00025 Fmt 4702 Sfmt 4702 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–2010–0646; Directorate Identifier 2009–NM–223–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 https:// 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 We have received 13 reports of cracks in the aft pressure bulkhead web ranging from 0.75 inch to 11.8 inches in length at the buttock line 61, between water line (WL) 220 and WL 228. The cracks originated at the hydraulic line support brackets, which were installed in production after airplane line number 1136, or in accordance with Boeing Service Bulletin 727–29–0057. The cracks were found in airplanes that had accumulated between 14,939 total flight hours and 39,369 total flight hours, and between 10,685 total flight cycles and 29,357 total flight cycles. The cracking is attributed to fatigue of the aft pressure bulkhead web due to vibrations from the number 1 engine hydraulic pump line, in addition to normal pressurization cycles. Material analysis revealed multiple crack initiation sites and no evidence of corrosion. This condition, if not corrected, could result in difficulty maintaining cabin pressurization or rapid decompression of the airplane. Relevant Service Information We have reviewed Boeing Special Attention Service Bulletin 727–53– 0232, dated September 23, 2009. This service bulletin describes procedures for initial and repetitive detailed inspections of the aft pressure bulkhead web for any cracking around the hydraulic line support bracket, and repair of any crack found. For certain airplanes, this service bulletin describes procedures for installing an optional preventative modification if no cracking is found during the detailed inspections. The preventative modification includes doing high frequency eddy current E:\FR\FM\01JYP1.SGM 01JYP1

Agencies

[Federal Register Volume 75, Number 126 (Thursday, July 1, 2010)]
[Proposed Rules]
[Pages 38064-38066]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 2010-15983]


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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 https://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 C[ocirc]te-Vertu Road West, Dorval, Qu[eacute]bec 
H4S 1Y9, Canada; telephone 514-855-5000; fax 514-855-7401; e-mail 
thd.qseries@aero.bombardier.com; Internet https://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 https://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 https://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.

[[Page 38065]]

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 198 products of U.S. registry. We also estimate that 
it would take about 3 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 $815 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 $211,860, or $1,070 per product.

Authority for This Rulemaking

    Title 49 of the United States Code specifies the FAA's authority to 
issue rules on aviation safety. Subtitle I, section 106, describes the 
authority of the FAA Administrator. ``Subtitle VII: Aviation 
Programs,'' describes in more detail the scope of the Agency's 
authority.
    We are issuing this rulemaking under the authority described in 
``Subtitle VII, Part A, Subpart III, Section 44701: General 
requirements.'' Under that section, Congress charges the FAA with 
promoting safe flight of civil aircraft in air commerce by prescribing 
regulations for practices, methods, and procedures the Administrator 
finds necessary for safety in air commerce. This regulation is within 
the scope of that authority because it addresses an unsafe condition 
that is likely to exist or develop on products identified in this 
rulemaking action.

Regulatory Findings

    We determined that this proposed AD would not have federalism 
implications under Executive Order 13132. This proposed AD would not 
have a substantial direct effect on the States, on the relationship 
between the national Government and the States, or on the distribution 
of power and responsibilities among the various levels of government.
    For the reasons discussed above, I certify this proposed 
regulation:
    1. Is not a ``significant regulatory action'' under Executive Order 
12866;
    2. Is not a ``significant rule'' under the DOT Regulatory Policies 
and Procedures (44 FR 11034, February 26, 1979); and
    3. Will not have a significant economic impact, positive or 
negative, on a substantial number of small entities under the criteria 
of the Regulatory Flexibility Act.
    We prepared a regulatory evaluation of the estimated costs to 
comply with this proposed AD and placed it in the AD docket.

List of Subjects in 14 CFR Part 39

    Air transportation, Aircraft, Aviation safety, Incorporation by 
reference, Safety.

The Proposed Amendment

    Accordingly, under the authority delegated to me by the 
Administrator, the FAA proposes to amend 14 CFR part 39 as follows:

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.


Sec.  39.13  [Amended]

    2. The FAA amends Sec.  39.13 by adding the following new AD:

Bombardier, Inc.: Docket No. FAA-2010-0643; Directorate Identifier 
2010-NM-030-AD.

Comments Due Date

    (a) We must receive comments by August 16, 2010.

Affected ADs

    (b) None.

Applicability

    (c) This AD applies to the airplanes identified in paragraphs 
(c)(1) and (c)(2) of this AD, certificated in any category.
    (1) Bombardier, Inc. Model DHC-8-101, -102, -103, -106, -201, -
202, -301, -311, and -315 airplanes, serial numbers 003 through 658 
inclusive.
    (2) Bombardier, Inc. Model DHC-8-400, -401, -402 airplanes, 
serial numbers 4001, 4003, 4004, 4006, and 4008 through 4187 
inclusive.

Subject

    (d) Air Transport Association (ATA) of America Code 32: Landing 
gear.

Reason

    (e) The mandatory continuing airworthiness information (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. * 
* *

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) Within 6,000 flight hours or 36 months after the effective 
date of this AD, whichever comes first: Replace the latch assembly 
of the access panel for the alternate extension system for the 
landing gear with a modified latch assembly, in accordance with the 
Accomplishment Instructions of Bombardier Service Bulletin 8-32-166, 
Revision A, dated January 29, 2009 (for Model DHC-8-100, DHC-8-200, 
and DHC-8-300 series airplanes); or Bombardier Service Bulletin 84-
32-57, Revision A, dated June 15, 2009 (for Model DHC-8-400 series 
airplanes).

Actions Accomplished According to Previous Issue of Service Bulletin

    (h) Actions accomplished before the effective date of this AD 
according to Bombardier Service Bulletin 8-32-166, dated April 14, 
2008; or Bombardier Service Bulletin 84-32-57, dated April 30, 2008; 
as applicable; are considered acceptable for compliance with the 
corresponding actions specified in this AD.

FAA AD Differences

    Note 1:  This AD differs from the MCAI and/or service 
information as follows: No differences.

Other FAA AD Provisions

    (i) The following provisions also apply to this AD:
    (1) Alternative Methods of Compliance (AMOCs): The Manager, New 
York Aircraft Certification Office, ANE-170, 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: Program Manager, 
Continuing Operational Safety, FAA, New York ACO, 1600 Stewart 
Avenue, Suite 410, Westbury, New York, 11590; telephone 516-228-
7300; fax 516-794-5531. Before using any approved AMOC on any 
airplane to which the AMOC applies, notify your principal 
maintenance inspector

[[Page 38066]]

(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 Canadian Airworthiness Directive CF-2009-46, 
dated December 14, 2009; Bombardier Service Bulletin 8-32-166, 
Revision A, dated January 29, 2009; and Bombardier Service Bulletin 
84-32-57, Revision A, dated June 15, 2009; for related information.

    Issued in Renton, Washington, on June 23, 2010.
Ali Bahrami,
Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 2010-15983 Filed 6-30-10; 8:45 am]
BILLING CODE 4910-13-P
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