Airworthiness Directives; Bombardier Inc. Model DHC-8-102, -103, -106, -201, -202, -301, -311, and -315 Airplanes; Equipped With Certain Cockpit Door Installations, 63169-63172 [2011-25770]

Download as PDF Federal Register / Vol. 76, No. 197 / Wednesday, October 12, 2011 / Rules and Regulations attention of the person identified in the Related Information section of this AD. (2) 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. Issued in Kansas City, Missouri, on October 3, 2011. Earl Lawrence, Manager, Small Airplane Directorate, Aircraft Certification Service. [FR Doc. 2011–26001 Filed 10–11–11; 8:45 am] BILLING CODE 4910–13–P (k) Related Information For more information about this AD, contact Hal Horsburgh, Aerospace Engineer, FAA, Atlanta ACO, 1701 Columbia Avenue, College Park, Georgia 30337; telephone: (404) 474–5553; fax: (404) 474–5606; e-mail: hal.horsburgh@faa.gov. WREIER-aviles on DSK7SPTVN1PROD with RULES (l) Material Incorporated by Reference (1) You must use the following service information to do the actions required by this AD, unless the AD specifies otherwise. The Director of the Federal Register approved the incorporation by reference (IBR) under 5 U.S.C. 552(a) and 1 CFR part 51 of the following service information on November 16, 2011: (i) Premier Aircraft Service Work Instruction PAS–WI–MSB–40–2011–001, dated March 4, 2011; and (ii) Premier Aircraft Service Mandatory Service Bulletin No. PAS–MSB–40–2011– 001, dated March 4, 2011. (2) If you accomplish the optional actions specified by this AD, you must use the following service information to perform those actions. The Director of the Federal Register approved the incorporation by reference (IBR) of the following service information on November 16, 2011: (i) Premier Aircraft Service Service Bulletin No. PAS–SB–40–2011–002, dated August 18, 2011; (ii) Seamech International Inc. Vapor Cycle Air Conditioning with Automatic Climate Control Instructions for Continued Airworthiness, ASI–772216A, Revision G, dated August 9, 2011; (iii) Seamech International Inc. Kit Compressor Mounting, Drawing SII 2216155, Revision D, dated July 21, 2011; (iv) DER Services Installation Instructions Engineering Order EO–2006–020–1, Revision F, dated August 18, 2011. (3) For service information identified in this AD, contact Premier Aircraft Service, 5540 NW 23 Avenue Hangar 14, Ft. Lauderdale, FL 33309, telephone: (954) 771– 0411; fax: (954) 334–1489; Internet: http:// www.flypas.com. (4) You may review copies of the referenced service information at the FAA, Small Airplane Directorate, 901 Locust, Kansas City, Missouri 64106. For information on the availability of this material at the FAA, call (816) 329–4148. (5) You may also review copies of the service information that is incorporated by reference at the National Archives and Records Administration (NARA). For information on the availability of this material at an NARA facility, call 202–741– 6030, or go to http://www.archives.gov/ federal_register/code_of_federal_regulations/ ibr_locations.html. VerDate Mar<15>2010 14:51 Oct 11, 2011 Jkt 226001 DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2011–0479; Directorate Identifier 2010–NM–154–AD; Amendment 39–16827; AD 2011–21–04] 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), Department of Transportation (DOT). ACTION: Final rule. AGENCY: We are superseding an existing airworthiness directive (AD) that applies to the products listed above. This 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. * * * We are issuing this AD to require actions to correct the unsafe condition on these products. DATES: This AD becomes effective November 16, 2011. The Director of the Federal Register approved the incorporation by reference of certain publications listed in this AD as of November 16, 2011. The Director of the Federal Register approved the incorporation by reference PO 00000 Frm 00021 Fmt 4700 Sfmt 4700 63169 of Bombardier Service Bulletin 8–52–54, Revision A, dated November 5, 2004, as of July, 18, 2006 (71 FR 34006, June 13, 2006). ADDRESSES: You may examine the AD docket on the Internet at http:// www.regulations.gov or in person at the U.S. Department of Transportation, Docket Operations, M–30, West Building Ground Floor, Room W12–140, 1200 New Jersey Avenue, SE., Washington, DC. 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: Discussion We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR part 39 to include an AD that would apply to the specified products. That NPRM was published in the Federal Register on June 8, 2011 (76 FR 33173), and proposed to supersede AD 2006– 12–16, Amendment 39–14642 (71 FR 34006, June 13, 2006). That NPRM proposed 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. Comments We gave the public the opportunity to participate in developing this AD. We considered the comment received. The commenter supports the NPRM (76 FR 33173, June 8, 2011). Conclusion We reviewed the available data, including the comment received, and E:\FR\FM\12OCR1.SGM 12OCR1 63170 Federal Register / Vol. 76, No. 197 / Wednesday, October 12, 2011 / Rules and Regulations determined that air safety and the public interest require adopting the AD as proposed. 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 required different actions in this AD from those in the MCAI in order to follow our FAA policies. Any such differences are highlighted in a NOTE within the AD. WREIER-aviles on DSK7SPTVN1PROD with RULES Costs of Compliance We estimate that this AD will affect about 17 products of U.S. registry. The actions that are required by AD 2006–12–16 (71 FR 34006, June 13, 2006) and retained in this AD take between 3 and 6 work-hours per product, 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 will take about 3 work-hours per product to comply with the new basic requirements of this AD. The average labor rate is $85 per workhour. Required parts will 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 parts. 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 this AD to the 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 VerDate Mar<15>2010 14:51 Oct 11, 2011 Jkt 226001 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 AD will not have federalism implications under Executive Order 13132. This AD will 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 AD: 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 AD and placed it in the AD docket. 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 the NPRM (76 FR 33173, June 8, 2011), 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. List of Subjects in 14 CFR Part 39 Air transportation, Aircraft, Aviation safety, Incorporation by reference, Safety. Adoption of the Amendment Accordingly, under the authority delegated to me by the Administrator, the FAA amends 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. Frm 00022 Fmt 4700 Sfmt 4700 [Amended] 2. The FAA amends § 39.13 by removing Amendment 39–14642 (71 FR 34006, June 13, 2006) and adding the following new AD: ■ 2011–21–04 Bombardier Inc.: Amendment 39–16827. Docket No. FAA–2011–0479; Directorate Identifier 2010–NM–154–AD. Effective Date (a) This airworthiness directive (AD) becomes effective November 16, 2011. Affected ADs (b) This AD supersedes AD 2006–12–16, Amendment 39–14642 (71 FR 34006, June 13, 2006). 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 ........................... 82510294 ........................... 82510310 ........................... 8Z4597 ............................... H85250010 ........................ 82510700 ........................... 82510704 ........................... All. All. –001. –001. All. All. 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 ■ PO 00000 § 39.13 (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. E:\FR\FM\12OCR1.SGM 12OCR1 Federal Register / Vol. 76, No. 197 / Wednesday, October 12, 2011 / Rules and Regulations Restatement of Requirements of AD 2006– 12–16 Amendment 39–14642 (71 FR 34006, June 13, 2006), With New Service Information Modification (g) Within 24 months after July 18, 2006 (the effective date of AD 2006–12–16 Amendment 39–14642 (71 FR 34006, June 13, 2006)), 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: 63171 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, 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. Note 1: Bombardier Service Bulletin 8–52– 54, Revision A, dated November 5, 2004, 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, dated May 12, 2004, or Revision A, dated November 17, 2006, 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, in accordance with 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— Do these actions— 8–52–54, Revision A, dated November 5, 2004 003 through 407 inclusive, 409 through 412 inclusive, and 414 through 433 inclusive. Rework the cockpit door emergency release. 8–52–58, dated May 12, 2004, or Revision A, dated November 17, 2006. 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. WREIER-aviles on DSK7SPTVN1PROD with RULES Note 3: Bombardier Service Bulletins 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 VerDate Mar<15>2010 14:51 Oct 11, 2011 Jkt 226001 452, 464, 490, 506, and 508 through 557 inclusive. Install a new label regarding alternate release of the door. Install the cockpit door. Other FAA AD Provisions 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. (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 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; 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. PO 00000 Frm 00023 Fmt 4700 Sfmt 4700 E:\FR\FM\12OCR1.SGM 12OCR1 63172 Federal Register / Vol. 76, No. 197 / Wednesday, October 12, 2011 / Rules and Regulations 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. Material Incorporated by Reference (n) You must use the following service information to do the applicable actions required by this AD, unless the AD specifies otherwise. The Director of the Federal Register approved the incorporation by reference (IBR) under 5 U.S.C. 552(a) and 1 CFR Part 51 of the following service information on the date specified: (1) Bombardier Service Bulletin 8–52–58, Revision A, dated November 17, 2006, approved for IBR November 16, 2011; (2) Bombardier Service Bulletin 8–52–61, dated October 20, 2006, approved for IBR November 16, 2011; (3) Bombardier Service Bulletin 8–52–54, Revision A, dated November 5, 2004, approved for IBR July 18, 2006 (71 FR 34006, June 13, 2006). (4) For service information identified in this 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 http://www.bombardier.com. (5) You may review copies of the 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. (6) You may also review copies of the service information that is incorporated by reference at the National Archives and Records Administration (NARA). For information on the availability of this material at NARA, call 202–741–6030, or go to: http://www.archives.gov/federal_register/ code_of_federal_regulations/ ibr_locations.html. [FR Doc. 2011–25770 Filed 10–11–11; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 WREIER-aviles on DSK7SPTVN1PROD with RULES [Docket No. FAA–2010–0033; Directorate Identifier 2009–NM–099–AD; Amendment 39–16737; AD 2011–14–02] RIN 2120–AA64 For service information identified in this AD, contact Boeing Commercial Airplanes, Attention: Data & Services Management, P.O. Box 3707, MC 2H–65, Seattle, Washington 98124– 2207; phone: 206–544–5000, extension 1; fax: 206–766–5680; e-mail: me.boecom@boeing.com; Internet: https://www.myboeingfleet.com. ADDRESSES: You may examine the AD docket on the Internet at http:// www.regulations.gov; or in person at the Docket Management Facility between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. The AD docket contains this AD, the regulatory evaluation, any comments received, and other information. The address for the Docket Office (telephone 800–647–5527) is the Document Management Facility, U.S. Department of Transportation, Docket Operations, M–30, West Building Ground Floor, Room W12–140, 1200 New Jersey Avenue, SE., Washington, DC 20590. FOR FURTHER INFORMATION CONTACT: Airworthiness Directives; The Boeing Company Model 767 Airplanes Federal Aviation Administration (FAA), Department of Transportation (DOT). ACTION: Final rule. AGENCY: 14:51 Oct 11, 2011 This AD becomes effective November 16, 2011. The Director of the Federal Register approved the incorporation by reference of certain publications listed in the AD as of November 16, 2011. DATES: Examining the AD Docket Issued in Renton, Washington, on September 23, 2011. Ali Bahrami, Manager, Transport Airplane Directorate, Aircraft Certification Service. VerDate Mar<15>2010 The FAA is superseding an existing airworthiness directive (AD) that applies to all Model 767 airplanes. The existing AD currently requires repetitive detailed and high frequency eddy current (HFEC) inspections of the station (STA) 1809.5 bulkhead for cracking, and corrective actions if necessary. This AD expands the inspection area to include the vertical inner chord at STA 1809.5. This AD results from reported fatigue cracking in the vertical inner chord and the forward outer chord while doing the detailed inspection of the horizontal inner chord at STA 1809.5. We are issuing this AD to detect and correct fatigue cracking in the bulkhead structure at STA 1809.5 and the vertical inner chord at STA 1809.5, which could result in failure of the bulkhead structure for carrying the flight loads of the horizontal stabilizer, and consequent loss of controllability of the airplane. SUMMARY: Jkt 226001 Berhane Alazar, Airframe Branch, ANM–120S, FAA, Seattle Aircraft Certification Office, 1601 Lind Avenue, SW., Renton, Washington 98057–3356; phone: 425–917–6577; fax: 425–917– 6590; e-mail: Berhane.Alazar@faa.gov. SUPPLEMENTARY INFORMATION: PO 00000 Frm 00024 Fmt 4700 Sfmt 4700 Discussion The FAA issued a notice of proposed rulemaking (NPRM) to amend 14 CFR part 39 to include an AD that supersedes AD 2006–24–04, Amendment 39–14833 (71 FR 68432, November 27, 2006). The existing AD applies to all Model 767 airplanes. That NPRM was published in the Federal Register on February 8, 2010 (75 FR 6154). That NPRM proposed to continue to require repetitive detailed and HFEC inspections of the STA 1809.5 bulkhead for cracking, and corrective actions if necessary. That NPRM also proposed to expand the inspection area to include the vertical inner chord at STA 1809.5. Comments We provided the public the opportunity to participate in the development of this AD. We have considered the comments that have been received on the NPRM (75 FR 6154, February 8, 2010). Support for the NPRM Continental Airlines (CAL) stated that it supports the intent of the NPRM (75 FR 6154, February 8, 2010). Request To Revise Paragraph (k)(1) of the NPRM Boeing requested that we revise the compliance time in paragraph (k)(1) of the NPRM (75 FR 6154, February 8, 2010) to state ‘‘whichever occurs later’’ rather than ‘‘whichever occurs first.’’ Boeing stated that a similar AD, AD 2006–24–04 (71 FR 68432, November 27, 2006) (the AD being superseded), provides a choice of the later of two compliance times. Boeing stated that changing the compliance time language in paragraph (k)(1) of the NPRM would make this AD consistent with AD 2006– 24–04. We agree with the request for the reasons provided by the commenter, and we have revised paragraph (k)(1) of this final rule accordingly. Request To Add Model 767–300BCF and 767–200SF Structural Repair Manuals (SRMs) To Clarify Terminating Action Boeing requested that we specify Model 767–300BCF and Model 767– 200SF SRMs in paragraphs (i) and (m) of the NPRM (75 FR 6154, February 8, 2010) to clarify the terminating action for converted Model 767–200 and –300 series airplanes. Boeing stated that some Model 767–300 airplanes have been converted to Model 767–300BCF airplanes, and some Model 767–200 airplanes have been converted to Model 767–200SF airplanes. Boeing stated that the Model 767–200SF and Model 767– E:\FR\FM\12OCR1.SGM 12OCR1

Agencies

[Federal Register Volume 76, Number 197 (Wednesday, October 12, 2011)]
[Rules and Regulations]
[Pages 63169-63172]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 2011-25770]


-----------------------------------------------------------------------

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2011-0479; Directorate Identifier 2010-NM-154-AD; 
Amendment 39-16827; AD 2011-21-04]
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), Department of 
Transportation (DOT).

ACTION: Final rule.

-----------------------------------------------------------------------

SUMMARY: We are superseding an existing airworthiness directive (AD) 
that applies to the products listed above. This 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. * * *

We are issuing this AD to require actions to correct the unsafe 
condition on these products.

DATES: This AD becomes effective November 16, 2011.
    The Director of the Federal Register approved the incorporation by 
reference of certain publications listed in this AD as of November 16, 
2011.
    The Director of the Federal Register approved the incorporation by 
reference of Bombardier Service Bulletin 8-52-54, Revision A, dated 
November 5, 2004, as of July, 18, 2006 (71 FR 34006, June 13, 2006).

ADDRESSES: You may examine the AD docket on the Internet at http://www.regulations.gov or in person at the U.S. Department of 
Transportation, Docket Operations, M-30, West Building Ground Floor, 
Room W12-140, 1200 New Jersey Avenue, SE., Washington, DC.

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:

Discussion

    We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR 
part 39 to include an AD that would apply to the specified products. 
That NPRM was published in the Federal Register on June 8, 2011 (76 FR 
33173), and proposed to supersede AD 2006-12-16, Amendment 39-14642 (71 
FR 34006, June 13, 2006). That NPRM proposed 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.

Comments

    We gave the public the opportunity to participate in developing 
this AD. We considered the comment received. The commenter supports the 
NPRM (76 FR 33173, June 8, 2011).

Conclusion

    We reviewed the available data, including the comment received, and

[[Page 63170]]

determined that air safety and the public interest require adopting the 
AD as proposed.

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 required different actions in this AD from those 
in the MCAI in order to follow our FAA policies. Any such differences 
are highlighted in a NOTE within the AD.

Costs of Compliance

    We estimate that this AD will affect about 17 products of U.S. 
registry.
    The actions that are required by AD 2006-12-16 (71 FR 34006, June 
13, 2006) and retained in this AD take between 3 and 6 work-hours per 
product, 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 will take about 3 work-hours per product to 
comply with the new basic requirements of this AD. The average labor 
rate is $85 per work-hour. Required parts will 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 parts. 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 this AD to the 
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 AD will not have federalism implications 
under Executive Order 13132. This AD will 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 AD:
    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 AD and placed it in the AD docket.

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 the NPRM (76 FR 33173, June 8, 2011), 
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.

List of Subjects in 14 CFR Part 39

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

Adoption of the Amendment

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

PART 39--AIRWORTHINESS DIRECTIVES

0
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]

0
2. The FAA amends Sec.  39.13 by removing Amendment 39-14642 (71 FR 
34006, June 13, 2006) and adding the following new AD:

2011-21-04 Bombardier Inc.: Amendment 39-16827. Docket No. FAA-2011-
0479; Directorate Identifier 2010-NM-154-AD.

Effective Date

    (a) This airworthiness directive (AD) becomes effective November 
16, 2011.

Affected ADs

    (b) This AD supersedes AD 2006-12-16, Amendment 39-14642 (71 FR 
34006, June 13, 2006).

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.

[[Page 63171]]

Restatement of Requirements of AD 2006-12-16 Amendment 39-14642 (71 FR 
34006, June 13, 2006), With New Service Information

Modification

    (g) Within 24 months after July 18, 2006 (the effective date of 
AD 2006-12-16 Amendment 39-14642 (71 FR 34006, June 13, 2006)), 
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.
------------------------------------------------------------------------


    Note 1:  Bombardier Service Bulletin 8-52-54, Revision A, dated 
November 5, 2004, 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, dated May 12, 2004, or Revision A, dated 
November 17, 2006, 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, in accordance with 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
 or Revision A, dated          and 508 through 557   door.
 November 17, 2006.            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 Bulletins 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;

[[Page 63172]]

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.

Material Incorporated by Reference

    (n) You must use the following service information to do the 
applicable actions required by this AD, unless the AD specifies 
otherwise. The Director of the Federal Register approved the 
incorporation by reference (IBR) under 5 U.S.C. 552(a) and 1 CFR 
Part 51 of the following service information on the date specified:
    (1) Bombardier Service Bulletin 8-52-58, Revision A, dated 
November 17, 2006, approved for IBR November 16, 2011;
    (2) Bombardier Service Bulletin 8-52-61, dated October 20, 2006, 
approved for IBR November 16, 2011;
    (3) Bombardier Service Bulletin 8-52-54, Revision A, dated 
November 5, 2004, approved for IBR July 18, 2006 (71 FR 34006, June 
13, 2006).
    (4) For service information identified in this 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 
http://www.bombardier.com.
    (5) You may review copies of the 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.
    (6) You may also review copies of the service information that 
is incorporated by reference at the National Archives and Records 
Administration (NARA). For information on the availability of this 
material at NARA, call 202-741-6030, or go to: http://www.archives.gov/federal_register/code_of_federal_regulations/ibr_locations.html.

    Issued in Renton, Washington, on September 23, 2011.
Ali Bahrami,
Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 2011-25770 Filed 10-11-11; 8:45 am]
BILLING CODE 4910-13-P