Airworthiness Directives; Bombardier Inc. Model DHC-8-102, -103, -106, -201, -202, -301, -311, and -315 Airplanes; Equipped With Certain Cockpit Door Installations, 33173-33176 [2011-14091]

Download as PDF 33173 Proposed Rules Federal Register Vol. 76, No. 110 Wednesday, June 8, 2011 This section of the FEDERAL REGISTER contains notices to the public of the proposed issuance of rules and regulations. The purpose of these notices is to give interested persons an opportunity to participate in the rule making prior to the adoption of the final rules. NUCLEAR REGULATORY COMMISSION 10 CFR Part 35 [NRC–2008–0071 and NRC–2008–0175] RIN 3150–AI26, 3150–AI63 Medical Use Regulations Nuclear Regulatory Commission. ACTION: Availability of preliminary draft rule language and notice of public workshops; correction. AGENCY: This document corrects another document that was published in the Federal Register on May 20, 2011 (76 FR 29171). That document announces plans to hold public workshops to solicit comments on certain issues under consideration to amend the medical use regulations, provides the date of the first of the two public workshops, and notices the availability of preliminary draft rule language concerning the U.S. Nuclear Regulatory Commission’s (NRC) proposed amendments to the medical use regulations. This document is necessary to correct a Regulatory Identifier Number (RIN) that appears in the heading, and to add additional information regarding the availability of the preliminary draft rule language. FOR FURTHER INFORMATION CONTACT: Cindy Bladey, Chief, Rules, Announcements, and Directives Branch, Office of Administration, Nuclear Regulatory Commission, Washington, DC 20555–0001, e-mail: Cindy.Bladey@nrc.gov, telephone: 301– 492–3667. SUPPLEMENTARY INFORMATION: At the top of the first column of Page 29171 of Federal Register document 2011–12048, published on May 20, 2011 (76 FR 29171), in the heading of the document, ‘‘RIN 3150–AI28’’ is corrected to read ‘‘RIN 3150–AI26’’. Also, in the ‘‘Background Information’’ section, at the top of the first column of Page 29176 of the same document, before the last paragraph of the jlentini on DSK4TPTVN1PROD with PROPOSALS SUMMARY: VerDate Mar<15>2010 17:24 Jun 07, 2011 Jkt 223001 document, add the following three paragraphs: The NRC is making a preliminary version of this draft rule language available to inform stakeholders of the current status of this proposed rulemaking. The NRC is inviting stakeholders to comment on the preliminary draft rule language. The preliminary draft rule language may be subject to significant revisions during the rulemaking process prior to publication for formal comment as a proposed rule. Public input at this stage will help inform the development of the proposed rule. The NRC will review and consider any comments received; however, the NRC will not formally respond to any comments received at this prerulemaking stage. As appropriate, the Statement of Considerations for the proposed rule may briefly discuss any substantive changes made to the proposed rule language as a result of comments received on this preliminary version. Stakeholders will also have an additional opportunity to comment on the rule language when it is published as a proposed rule in accordance with the provisions of the Administrative Procedures Act. The NRC will respond to such comments in the Statement of Considerations for the final rule. The NRC may post updates to the preliminary proposed rule language on the Federal rulemaking Web site under Docket ID NRC–2008–0175. Regulations.gov allows members of the public to set-up e-mail alerts so that they may be notified when documents are added to a docket. Users are notified via e-mail at an e-mail address provided at the time of registration for the notification. Directions for signing up for the e-mail alerts can be found at https://www.regulations.gov. To do so, navigate to a docket folder you are interested in and then click the ‘‘Sign up for E-mail Alerts’’ link. Dated at Rockville, Maryland, this 3rd day of June, 2011. For the Nuclear Regulatory Commission. Leslie Terry, Acting Chief, Rules, Announcements, and Directives Branch, Division of Administrative Services, Office of Administration. [FR Doc. 2011–14060 Filed 6–7–11; 8:45 am] BILLING CODE 7590–01–P PO 00000 Frm 00001 Fmt 4702 Sfmt 4702 DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2011–0479; Directorate Identifier 2010–NM–154–AD] RIN 2120–AA64 Airworthiness Directives; Bombardier Inc. Model DHC–8–102, –103, –106, –201, –202, –301, –311, and –315 Airplanes; Equipped With Certain Cockpit Door Installations Federal Aviation Administration (FAA), DOT. ACTION: Notice of proposed rulemaking (NPRM). AGENCY: We propose to adopt a new airworthiness directive (AD) for the products listed above that would supersede an existing AD. 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: SUMMARY: During structural testing of the cockpit door, it was observed that the door lower hinge block rotated which resulted in disengagement of the mating hinge pin and excessive door deflection. The lower hinge block rotated because it was attached to its support structure with only one attachment bolt, which prevented it from reacting to any moment force. This condition, if not corrected could result in breakage and uncontrolled release of the cockpit door under certain decompression situations. After incorporation of Modsum 8Q900267 * * *, an operator reported a failure to complete the cockpit door removal function test. This condition, if not corrected, could result in the inability to remove the cockpit door for emergency egress. * * * 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 July 25, 2011. 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 E:\FR\FM\08JNP1.SGM 08JNP1 33174 Federal Register / Vol. 76, No. 110 / Wednesday, June 8, 2011 / Proposed Rules 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., Q–Series Technical Help Desk, 123 Garratt Boulevard, Toronto, Ontario M3K 1Y5, Canada; telephone 416–375– 4000; fax 416–375–4539; 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: Andreas Rambalakos, Aerospace Engineer, Airframe and Mechanical Systems Branch, ANE–171, FAA, New York Aircraft Certification Office, 1600 Stewart Avenue, Suite 410, Westbury, New York 11590; telephone (516) 228– 7345; fax (516) 794–5531. SUPPLEMENTARY INFORMATION: jlentini on DSK4TPTVN1PROD with PROPOSALS 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–2011–0479; Directorate Identifier 2010–NM–154–AD’’ at the beginning of your comments. We specifically invite comments on the overall regulatory, economic, environmental, and energy aspects of this proposed AD. We will consider all comments received by the closing date and may amend this proposed AD based on those comments. We will post all comments we receive, without change, to https:// www.regulations.gov, including any VerDate Mar<15>2010 17:24 Jun 07, 2011 Jkt 223001 personal information you provide. We will also post a report summarizing each substantive verbal contact we receive about this proposed AD. Discussion On June 5, 2006, we issued AD 2006– 12–16, Amendment 39–14642 (71 FR 34006, June 13, 2006). That AD required actions intended to address an unsafe condition on the products listed above. Since we issued AD 2006–12–16, an operator reported a failure to complete the cockpit door removal function test. This condition, if not corrected, could result in the inability to remove the cockpit door for emergency egress. The Transport Canada Civil Aviation (TCCA), which is the aviation authority for Canada, has issued Canadian Airworthiness Directive CF–2005–34R1, dated August 15, 2007 (referred to after this as ‘‘the MCAI’’), to correct an unsafe condition for the specified products. The MCAI states: During structural testing of the cockpit door, it was observed that the door lower hinge block rotated which resulted in disengagement of the mating hinge pin and excessive door deflection. The lower hinge block rotated because it was attached to its support structure with only one attachment bolt, which prevented it from reacting to any moment force. This condition, if not corrected could result in breakage and uncontrolled release of the cockpit door under certain decompression situations. After incorporation of Modsum 8Q900267 * * *, an operator reported a failure to complete the cockpit door removal function test. This condition, if not corrected, could result in the inability to remove the cockpit door for emergency egress. Therefore, * * * this [Canadian] directive is issued to require rework of the cockpit door striker plate and replacement of the latch block for the affected aircraft serial numbers. * * * You may obtain further information by examining the MCAI in the AD docket. Relevant Service Information Bombardier Inc. has issued Service Bulletins 8–52–58, Revision A, dated November 17, 2006; and 8–52–61, dated October 20, 2006. The actions described in this service information are intended to correct the unsafe condition identified in the MCAI. Change to Table 3 of the Existing AD We have revised Table 3 of the existing AD to remove reference to Bombardier Series 100/300 Modification Summary (Modsums) 8Q200015, 8Q420101, and 8Q420143 in the column labeled ‘‘One approved method for doing these actions.’’ However, we have approved De Havilland Aircraft of Canada, Limited, Modification 8/2337 as an additional source of guidance for PO 00000 Frm 00002 Fmt 4702 Sfmt 4702 reworking the cockpit door emergency release. We have approved De Havilland Aircraft of Canada, Limited, Modification 8/3339 as an additional source of guidance for installing a new label regarding the alternate release of the door. We have also approved Bombardier Series 100/300 Modsum 8Q200015 as an additional source of guidance for installing the cockpit door. Operators may contact the Manager, New York Aircraft Certification Office, ANE–170, for information regarding the use of Bombardier Series 100/300 Modsum 8Q200015 for installing the cockpit door, as required by paragraph (h) of this AD. We have not included Bombardier Series 100/300 Modsums 8Q420101 and 8Q420143 in this AD because they are optional installations of the emergency locator transmitter and blow-out panel on the cockpit door and were done during production. 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 17 products of U.S. registry. The actions that are required by AD 2006–12–16 and retained in this proposed AD take between 3 and 6 work-hours per product, depending on E:\FR\FM\08JNP1.SGM 08JNP1 Federal Register / Vol. 76, No. 110 / Wednesday, June 8, 2011 / Proposed Rules the airplane configuration, at an average labor rate of $85 per work hour. Required parts cost about $2,000 per product. Based on these figures, the estimated cost of the currently required actions is between $2,255 and $2,510 per product. We estimate that it would take about 3 work-hours per product to comply with the new basic requirements of this proposed AD. The average labor rate is $85 per work-hour. Required parts would cost about $2,000 per product. Where the service information lists required parts costs that are covered under warranty, we have assumed that there will be no charge for these costs. As we do not control warranty coverage for affected parties, some parties may incur costs higher than estimated here. Based on these figures, we estimate the cost of the proposed AD on U.S. operators to be $38,335, or $2,255 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 33175 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. installation part numbers (P/Ns) identified in Table 1 of this AD. List of Subjects in 14 CFR Part 39 Air transportation, Aircraft, Aviation safety, Incorporation by reference, Safety. Reason 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 removing Amendment 39–14642 (71 FR 34006, June 13, 2006) and adding the following new AD: Bombardier Inc.: Docket No. FAA–2011– 0479; Directorate Identifier 2010–NM–154– AD. Comments Due Date (a) We must receive comments by July 25, 2011. Affected ADs (b) This AD supersedes AD 2006–12–16, Amendment 39–14642. Applicability (c) This AD applies to Bombardier Model DHC–8–102, –103, –106, –201, –202, –301, –311, and –315 airplanes, certificated in any category; serial numbers (S/Ns) 003 through 557 inclusive; equipped with cockpit door TABLE 1—COCKPIT DOOR INSTALLATIONS AFFECTED BY THIS AD P/N 82510074 ....... 82510294 ....... 82510310 ....... 8Z4597 ........... H85250010 .... 82510700 ....... 82510704 ....... Dash number(s) All All –001 –001 All All All except –502 and –503 Subject (d) Air Transport Association (ATA) of America Code 52: Doors. (e) The mandatory continuing airworthiness information (MCAI) states: During structural testing of the cockpit door, it was observed that the door lower hinge block rotated which resulted in disengagement of the mating hinge pin and excessive door deflection. The lower hinge block rotated because it was attached to its support structure with only one attachment bolt, which prevented it from reacting to any moment force. This condition, if not corrected could result in breakage and uncontrolled release of the cockpit door under certain decompression situations. After incorporation of Modsum 8Q900267 * * * an operator reported a failure to complete the cockpit door removal function test. This condition, if not corrected, could result in the inability to remove the cockpit door for emergency egress. * * * 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. Restatement of Requirements of AD 2006– 12–16, With New Service Information Modification (g) Within 24 months after July 18, 2006 (the effective date of AD 2006–12–16), modify the cockpit door from a single-point attachment to a two-point attachment in accordance with the Accomplishment Instructions of the applicable service bulletin in Table 2 of this AD. For airplane serial numbers 452, 464, 490, 506, and 508 through 557 inclusive: After the effective date of this AD, use Bombardier Service Bulletin 8–52– 58, Revision A, dated November 17, 2006. jlentini on DSK4TPTVN1PROD with PROPOSALS TABLE 2—BOMBARDIER SERVICE BULLETINS FOR MODIFICATION REQUIRED BY PARAGRAPH (G) OF THIS AD Use this Bombardier Service Bulletin— For airplane serial numbers— 8–52–54, Revision A, dated November 5, 2004 ...................................... 003 through 451 inclusive, 453 through 463 inclusive, 465 through 489 inclusive, 491 through 505 inclusive, and 507. 452, 464, 490, 506, and 508 through 557 inclusive. 8–52–58, dated May 12, 2004, or Revision A, dated November 17, 2006. VerDate Mar<15>2010 17:24 Jun 07, 2011 Jkt 223001 PO 00000 Frm 00003 Fmt 4702 Sfmt 4702 E:\FR\FM\08JNP1.SGM 08JNP1 33176 Federal Register / Vol. 76, No. 110 / Wednesday, June 8, 2011 / Proposed Rules Note 1: Bombardier Service Bulletin 8–52– 54 refers to Bombardier Series 100/300 Modification Summary (Modsum) 8Q100859 as an additional source of guidance for installing a hinge pin with a two-point attachment. Bombardier Service Bulletin 8– 52–58 refers to Bombardier Series 100/300 Modsum 8Q900267 as an additional source of guidance for reworking and installing the cockpit door, and reworking the lower hinge attachment to provide a downward-facing pin with a two-point attachment. Prior/Concurrent Requirements (h) Prior to or concurrently with the modification in paragraph (g) of this AD, do the applicable actions specified in Table 3 of this AD, according to a method approved by either the Manager, New York Aircraft Certification (ACO), FAA; or Transport Canada Civil Aviation (TCCA) (or its delegated agent). TABLE 3—BOMBARDIER SERVICE BULLETINS FOR REQUIREMENTS OF PARAGRAPH (H) OF THIS AD For airplanes affected by Bombardier Service Bulletin— That have these serial numbers— 8–52–54, Revision A, dated November 5, 2004 003 through 407 inclusive, 409 through 412 inclusive, and 414 through 433 inclusive. .......................................................................... 8–52–58, dated May 12, 2004 ........................... Note 2: Bombardier Service Bulletin 8–52– 54, Revision A, dated November 5, 2004, refers to De Havilland Aircraft of Canada, Limited, Modification 8/2337 as an additional source of guidance for reworking the cockpit door emergency release; and Modification 8/3339 as additional source of guidance for installing a new label regarding alternate release of the door, on airplanes having serial numbers 003 through 407 inclusive, 409 through 412 inclusive, and 414 through 433 inclusive. Note 3: Bombardier Service Bulletin 8–52– 58, dated May 12, 2004; and Revision A, dated November 17, 2006; refer to Bombardier Modsum 8Q200015, as an additional source of guidance for installing the cockpit door, on airplanes having serial numbers 452, 464, 490, 506, and 508 through 557 inclusive. Actions Done In Accordance With Previous Revision of Service Bulletin (i) Actions done before July 18, 2006, in accordance with Bombardier Service Bulletin 8–52–54, dated May 12, 2004, are acceptable for compliance with the corresponding requirements in paragraph (g) of this AD. jlentini on DSK4TPTVN1PROD with PROPOSALS New Requirements of This AD (j) For airplanes having S/N 452, 464, 490, 506, and 508 through 557 inclusive, and on which the requirements in paragraph (g) of this AD have been done as of the effective date of this AD: Within 12 months after the effective date of this AD rework the cockpit door striker plate and replace the latch block, in accordance with the Accomplishment Instructions of Bombardier Service Bulletin 8–52–61, dated October 20, 2006. (k) For airplanes having S/Ns 452, 464, 490, 506, and 508 through 557 inclusive, and on which the requirements in paragraph (g) of this AD have not been done as of the effective date of this AD: Prior to or concurrently with doing the modification required in paragraph (g) of this AD, rework the cockpit door striker plate and replace the latch block, in accordance with the Accomplishment Instructions of Bombardier Service Bulletin 8–52–61, dated October 20, 2006. VerDate Mar<15>2010 17:24 Jun 07, 2011 Jkt 223001 452, 464, 490, 506, and 508 through 557 inclusive. FAA AD Differences Note 4: This AD differs from the MCAI and/or service information as follows: No differences. Do these actions— Rework the cockpit door emergency release. Install a new label regarding alternate release of the door. Install the cockpit door. Issued in Renton, Washington, on May 27, 2011. Ali Bahrami, Manager, Transport Airplane Directorate, Aircraft Certification Service. Other FAA AD Provisions [FR Doc. 2011–14091 Filed 6–7–11; 8:45 am] (l) 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. In accordance with 14 CFR 39.19, send your request to your principal inspector or local Flight Standards District Office, as appropriate. If sending information directly to the ACO, send it 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, notify your appropriate principal inspector, or lacking a principal inspector, the manager of the local flight standards district office/ certificate holding 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. BILLING CODE 4910–13–P Related Information (m) Refer to MCAI Canadian Airworthiness Directive CF–2005–34R1, dated August 15, 2007; Bombardier Service Bulletin 8–52–54, Revision A, dated November 5, 2004; Bombardier Service Bulletin 8–52–58, Revision A, dated November 17, 2006; and Bombardier Service Bulletin 8–52–61, dated October 20, 2006; for related information. PO 00000 Frm 00004 Fmt 4702 Sfmt 4702 DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2011–0478; Directorate Identifier 2010–NM–138–AD] RIN 2120–AA64 Airworthiness Directives; Airbus Model A300 B4–103, B4–203, and B4–2C Airplanes Federal Aviation Administration (FAA), DOT. ACTION: Notice of proposed rulemaking (NPRM). AGENCY: We propose to adopt a new airworthiness directive (AD) for the products listed above that would supersede an existing AD. 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: SUMMARY: One operator reported a failure of the MLG [main landing gear] retraction actuator sliding rod. This incident occurred at a number of operating flight cycles lower than the limit value imposed by the MLG manufacturer. This condition, if not detected and corrected, results in undampened extension of the MLG, leading to higher than usual loads on the MLG attachment. Higher loads E:\FR\FM\08JNP1.SGM 08JNP1

Agencies

[Federal Register Volume 76, Number 110 (Wednesday, June 8, 2011)]
[Proposed Rules]
[Pages 33173-33176]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 2011-14091]


=======================================================================
-----------------------------------------------------------------------

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2011-0479; Directorate Identifier 2010-NM-154-AD]
RIN 2120-AA64


Airworthiness Directives; Bombardier Inc. Model DHC-8-102, -103, 
-106, -201, -202, -301, -311, and -315 Airplanes; Equipped With Certain 
Cockpit Door Installations

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 that would supersede an existing AD. 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:

    During structural testing of the cockpit door, it was observed 
that the door lower hinge block rotated which resulted in 
disengagement of the mating hinge pin and excessive door deflection. 
The lower hinge block rotated because it was attached to its support 
structure with only one attachment bolt, which prevented it from 
reacting to any moment force. This condition, if not corrected could 
result in breakage and uncontrolled release of the cockpit door 
under certain decompression situations.
    After incorporation of Modsum 8Q900267 * * *, an operator 
reported a failure to complete the cockpit door removal function 
test. This condition, if not corrected, could result in the 
inability to remove the cockpit door for emergency egress. * * *

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 July 25, 2011.

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

[[Page 33174]]

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., Q-Series Technical Help Desk, 123 Garratt Boulevard, 
Toronto, Ontario M3K 1Y5, Canada; telephone 416-375-4000; fax 416-375-
4539; 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: Andreas Rambalakos, Aerospace 
Engineer, Airframe and Mechanical Systems Branch, ANE-171, FAA, New 
York Aircraft Certification Office, 1600 Stewart Avenue, Suite 410, 
Westbury, New York 11590; telephone (516) 228-7345; 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-2011-0479; 
Directorate Identifier 2010-NM-154-AD'' at the beginning of your 
comments. We specifically invite comments on the overall regulatory, 
economic, environmental, and energy aspects of this proposed AD. We 
will consider all comments received by the closing date and may amend 
this proposed AD based on those comments.
    We will post all comments we receive, without change, to 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

    On June 5, 2006, we issued AD 2006-12-16, Amendment 39-14642 (71 FR 
34006, June 13, 2006). That AD required actions intended to address an 
unsafe condition on the products listed above.
    Since we issued AD 2006-12-16, an operator reported a failure to 
complete the cockpit door removal function test. This condition, if not 
corrected, could result in the inability to remove the cockpit door for 
emergency egress. The Transport Canada Civil Aviation (TCCA), which is 
the aviation authority for Canada, has issued Canadian Airworthiness 
Directive CF-2005-34R1, dated August 15, 2007 (referred to after this 
as ``the MCAI''), to correct an unsafe condition for the specified 
products. The MCAI states:

    During structural testing of the cockpit door, it was observed 
that the door lower hinge block rotated which resulted in 
disengagement of the mating hinge pin and excessive door deflection. 
The lower hinge block rotated because it was attached to its support 
structure with only one attachment bolt, which prevented it from 
reacting to any moment force. This condition, if not corrected could 
result in breakage and uncontrolled release of the cockpit door 
under certain decompression situations.
    After incorporation of Modsum 8Q900267 * * *, an operator 
reported a failure to complete the cockpit door removal function 
test. This condition, if not corrected, could result in the 
inability to remove the cockpit door for emergency egress. 
Therefore, * * * this [Canadian] directive is issued to require 
rework of the cockpit door striker plate and replacement of the 
latch block for the affected aircraft serial numbers. * * *

You may obtain further information by examining the MCAI in the AD 
docket.

Relevant Service Information

    Bombardier Inc. has issued Service Bulletins 8-52-58, Revision A, 
dated November 17, 2006; and 8-52-61, dated October 20, 2006. The 
actions described in this service information are intended to correct 
the unsafe condition identified in the MCAI.

Change to Table 3 of the Existing AD

    We have revised Table 3 of the existing AD to remove reference to 
Bombardier Series 100/300 Modification Summary (Modsums) 8Q200015, 
8Q420101, and 8Q420143 in the column labeled ``One approved method for 
doing these actions.'' However, we have approved De Havilland Aircraft 
of Canada, Limited, Modification 8/2337 as an additional source of 
guidance for reworking the cockpit door emergency release. We have 
approved De Havilland Aircraft of Canada, Limited, Modification 8/3339 
as an additional source of guidance for installing a new label 
regarding the alternate release of the door. We have also approved 
Bombardier Series 100/300 Modsum 8Q200015 as an additional source of 
guidance for installing the cockpit door. Operators may contact the 
Manager, New York Aircraft Certification Office, ANE-170, for 
information regarding the use of Bombardier Series 100/300 Modsum 
8Q200015 for installing the cockpit door, as required by paragraph (h) 
of this AD. We have not included Bombardier Series 100/300 Modsums 
8Q420101 and 8Q420143 in this AD because they are optional 
installations of the emergency locator transmitter and blow-out panel 
on the cockpit door and were done during production.

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 17 products of U.S. registry.
    The actions that are required by AD 2006-12-16 and retained in this 
proposed AD take between 3 and 6 work-hours per product, depending on

[[Page 33175]]

the airplane configuration, at an average labor rate of $85 per work 
hour. Required parts cost about $2,000 per product. Based on these 
figures, the estimated cost of the currently required actions is 
between $2,255 and $2,510 per product.
    We estimate that it would take about 3 work-hours per product to 
comply with the new basic requirements of this proposed AD. The average 
labor rate is $85 per work-hour. Required parts would cost about $2,000 
per product. Where the service information lists required parts costs 
that are covered under warranty, we have assumed that there will be no 
charge for these costs. As we do not control warranty coverage for 
affected parties, some parties may incur costs higher than estimated 
here. Based on these figures, we estimate the cost of the proposed AD 
on U.S. operators to be $38,335, or $2,255 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 removing Amendment 39-14642 (71 FR 
34006, June 13, 2006) and adding the following new AD:

Bombardier Inc.: Docket No. FAA-2011-0479; Directorate Identifier 
2010-NM-154-AD.

Comments Due Date

    (a) We must receive comments by July 25, 2011.

Affected ADs

    (b) This AD supersedes AD 2006-12-16, Amendment 39-14642.

Applicability

    (c) This AD applies to Bombardier Model DHC-8-102, -103, -106, -
201, -202, -301, -311, and -315 airplanes, certificated in any 
category; serial numbers (S/Ns) 003 through 557 inclusive; equipped 
with cockpit door installation part numbers (P/Ns) identified in 
Table 1 of this AD.

         Table 1--Cockpit Door Installations Affected by This AD
------------------------------------------------------------------------
                  P/N                             Dash number(s)
------------------------------------------------------------------------
82510074...............................  All
82510294...............................  All
82510310...............................  -001
8Z4597.................................  -001
H85250010..............................  All
82510700...............................  All
82510704...............................  All except -502 and -503
------------------------------------------------------------------------

Subject

    (d) Air Transport Association (ATA) of America Code 52: Doors.

Reason

    (e) The mandatory continuing airworthiness information (MCAI) 
states:
    During structural testing of the cockpit door, it was observed 
that the door lower hinge block rotated which resulted in 
disengagement of the mating hinge pin and excessive door deflection. 
The lower hinge block rotated because it was attached to its support 
structure with only one attachment bolt, which prevented it from 
reacting to any moment force. This condition, if not corrected could 
result in breakage and uncontrolled release of the cockpit door 
under certain decompression situations.
    After incorporation of Modsum 8Q900267 * * * an operator 
reported a failure to complete the cockpit door removal function 
test. This condition, if not corrected, could result in the 
inability to remove the cockpit door for emergency egress. * * *

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.

Restatement of Requirements of AD 2006-12-16, With New Service 
Information

Modification

    (g) Within 24 months after July 18, 2006 (the effective date of 
AD 2006-12-16), modify the cockpit door from a single-point 
attachment to a two-point attachment in accordance with the 
Accomplishment Instructions of the applicable service bulletin in 
Table 2 of this AD. For airplane serial numbers 452, 464, 490, 506, 
and 508 through 557 inclusive: After the effective date of this AD, 
use Bombardier Service Bulletin 8-52-58, Revision A, dated November 
17, 2006.

   Table 2--Bombardier Service Bulletins for Modification Required by
                        Paragraph (g) of this AD
------------------------------------------------------------------------
 Use this Bombardier Service Bulletin--   For airplane serial numbers--
------------------------------------------------------------------------
8-52-54, Revision A, dated November 5,   003 through 451 inclusive, 453
 2004.                                    through 463 inclusive, 465
                                          through 489 inclusive, 491
                                          through 505 inclusive, and
                                          507.
8-52-58, dated May 12, 2004, or          452, 464, 490, 506, and 508
 Revision A, dated November 17, 2006.     through 557 inclusive.
------------------------------------------------------------------------



[[Page 33176]]

    Note 1:  Bombardier Service Bulletin 8-52-54 refers to 
Bombardier Series 100/300 Modification Summary (Modsum) 8Q100859 as 
an additional source of guidance for installing a hinge pin with a 
two-point attachment. Bombardier Service Bulletin 8-52-58 refers to 
Bombardier Series 100/300 Modsum 8Q900267 as an additional source of 
guidance for reworking and installing the cockpit door, and 
reworking the lower hinge attachment to provide a downward-facing 
pin with a two-point attachment.

Prior/Concurrent Requirements

    (h) Prior to or concurrently with the modification in paragraph 
(g) of this AD, do the applicable actions specified in Table 3 of 
this AD, according to a method approved by either the Manager, New 
York Aircraft Certification (ACO), FAA; or Transport Canada Civil 
Aviation (TCCA) (or its delegated agent).

 Table 3--Bombardier Service Bulletins for Requirements of Paragraph (h)
                               of This AD
------------------------------------------------------------------------
  For airplanes affected by
Bombardier Service Bulletin--    That have these     Do these actions--
                                serial numbers--
------------------------------------------------------------------------
8-52-54, Revision A, dated    003 through 407       Rework the cockpit
 November 5, 2004.             inclusive, 409        door emergency
                               through 412           release.
                               inclusive, and 414
                               through 433
                               inclusive.
                              ....................  Install a new label
                                                     regarding alternate
                                                     release of the
                                                     door.
8-52-58, dated May 12, 2004.  452, 464, 490, 506,   Install the cockpit
                               and 508 through 557   door.
                               inclusive.
------------------------------------------------------------------------


    Note 2: Bombardier Service Bulletin 8-52-54, Revision A, dated 
November 5, 2004, refers to De Havilland Aircraft of Canada, 
Limited, Modification 8/2337 as an additional source of guidance for 
reworking the cockpit door emergency release; and Modification 8/
3339 as additional source of guidance for installing a new label 
regarding alternate release of the door, on airplanes having serial 
numbers 003 through 407 inclusive, 409 through 412 inclusive, and 
414 through 433 inclusive.


    Note 3:  Bombardier Service Bulletin 8-52-58, dated May 12, 
2004; and Revision A, dated November 17, 2006; refer to Bombardier 
Modsum 8Q200015, as an additional source of guidance for installing 
the cockpit door, on airplanes having serial numbers 452, 464, 490, 
506, and 508 through 557 inclusive.

Actions Done In Accordance With Previous Revision of Service 
Bulletin

    (i) Actions done before July 18, 2006, in accordance with 
Bombardier Service Bulletin 8-52-54, dated May 12, 2004, are 
acceptable for compliance with the corresponding requirements in 
paragraph (g) of this AD.

New Requirements of This AD

    (j) For airplanes having S/N 452, 464, 490, 506, and 508 through 
557 inclusive, and on which the requirements in paragraph (g) of 
this AD have been done as of the effective date of this AD: Within 
12 months after the effective date of this AD rework the cockpit 
door striker plate and replace the latch block, in accordance with 
the Accomplishment Instructions of Bombardier Service Bulletin 8-52-
61, dated October 20, 2006.
    (k) For airplanes having S/Ns 452, 464, 490, 506, and 508 
through 557 inclusive, and on which the requirements in paragraph 
(g) of this AD have not been done as of the effective date of this 
AD: Prior to or concurrently with doing the modification required in 
paragraph (g) of this AD, rework the cockpit door striker plate and 
replace the latch block, in accordance with the Accomplishment 
Instructions of Bombardier Service Bulletin 8-52-61, dated October 
20, 2006.

FAA AD Differences

    Note 4:  This AD differs from the MCAI and/or service 
information as follows: No differences.

Other FAA AD Provisions

    (l) 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. In accordance with 14 CFR 39.19, send your 
request to your principal inspector or local Flight Standards 
District Office, as appropriate. If sending information directly to 
the ACO, send it 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, notify your appropriate principal 
inspector, or lacking a principal inspector, the manager of the 
local flight standards district office/certificate holding 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.

Related Information

    (m) Refer to MCAI Canadian Airworthiness Directive CF-2005-34R1, 
dated August 15, 2007; Bombardier Service Bulletin 8-52-54, Revision 
A, dated November 5, 2004; Bombardier Service Bulletin 8-52-58, 
Revision A, dated November 17, 2006; and Bombardier Service Bulletin 
8-52-61, dated October 20, 2006; for related information.

    Issued in Renton, Washington, on May 27, 2011.
Ali Bahrami,
Manager, Transport Airplane Directorate, Aircraft Certification 
Service.

[FR Doc. 2011-14091 Filed 6-7-11; 8:45 am]
BILLING CODE 4910-13-P
This site is protected by reCAPTCHA and the Google Privacy Policy and Terms of Service apply.