81 FR 26121 - Airworthiness Directives; Bombardier, Inc. Airplanes
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration Federal Register Volume 81, Issue 84 (May 2, 2016)
Federal Aviation Administration
Federal Register Volume 81, Issue 84 (May 2, 2016)
| Page Range | 26121-26124 | |
| FR Document | 2016-08959 |
[Federal Register Volume 81, Number 84 (Monday, May 2, 2016)] [Rules and Regulations] [Pages 26121-26124] From the Federal Register Online [www.thefederalregister.org] [FR Doc No: 2016-08959] ----------------------------------------------------------------------- DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA-2015-3988; Directorate Identifier 2015-NM-005-AD; Amendment 39-18491; AD 2016-08-15] RIN 2120-AA64 Airworthiness Directives; Bombardier, Inc. Airplanes AGENCY: Federal Aviation Administration (FAA), Department of Transportation (DOT). ACTION: Final rule. ----------------------------------------------------------------------- SUMMARY: We are superseding Airworthiness Directive (AD) 2014-17-51 for certain Bombardier, Inc. Model CL-600-2B16 airplanes. AD 2014-17-51 required inspecting the inboard flap fasteners of the hinge-box forward fitting at Wing Station (WS) 76.50 and WS 127.25 to determine the orientation and condition of the fasteners, as applicable, and replacement or repetitive inspections of the fasteners if necessary. AD 2014-17-51 also provided for optional terminating action for the requirements of that AD. This new AD requires accomplishment of the previously optional terminating action. This AD was prompted by a determination that that additional action is necessary. We are issuing this AD to detect and correct incorrectly oriented or fractured fasteners, that could result in premature failure of the fasteners attaching the inboard flap hinge-box forward fitting; failure of the fasteners could lead to the detachment of the flap hinge box and the flap surface, and consequent loss of control of the airplane. DATES: This AD is effective June 6, 2016. The Director of the Federal Register approved the incorporation by reference of certain publications listed in this AD as of June 6, 2016. The Director of the Federal Register approved the incorporation by reference of certain other publications listed in this AD as of November 12, 2014 (79 FR 64088, October 28, 2014). The Director of the Federal Register approved the incorporation by reference of certain other publications listed in this AD as of March 6, 2014 (79 FR 9389, February 19, 2014). ADDRESSES: For service information identified in this final rule, contact Bombardier, Inc., 400 C[ocirc]te-Vertu Road West, Dorval, Qu[eacute]bec H4S 1Y9, Canada; telephone 514-855-5000; fax 514-855- 7401; email [email protected]; Internet http://www.bombardier.com. You may view this referenced service information at the FAA, Transport Airplane Directorate, 1601 Lind Avenue SW., Renton, WA. For information on the availability of this material at the FAA, call 425-227-1221. It is also available on the Internet at http://www.regulations.gov by searching for and locating Docket No. FAA-2015- 3988. Examining the AD Docket You may examine the AD docket on the Internet at http://www.regulations.gov by searching for and locating Docket No. FAA-2015- 3988; 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 Docket 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: Aziz Ahmed, Aerospace Engineer, Propulsion and Services Branch, ANE-173, FAA, New York Aircraft Certification Office (ACO), 1600 Stewart Avenue, Suite 410, Westbury, NY 11590; telephone 516-228-7329; fax 516-794-5531. SUPPLEMENTARY INFORMATION: Discussion We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR part 39 to supersede AD 2014-17-51, Amendment 39-17999 (79 FR 64088, October 28, 2014) (``AD 2014-17-51''). AD 2014-17-51 applied to certain Bombardier, Inc. Model CL-600-2B16 airplanes. The NPRM published in the Federal Register on October 19, 2015 (80 FR 63141) (``the NPRM''). Transport Canada Civil Aviation (TCCA), which is the aviation authority for Canada, has issued Canadian Airworthiness Directive CF- 2014-27R1, dated August 29, 2014 (referred to after this as the Mandatory Continuing Airworthiness Information, or ``the MCAI''), to correct an unsafe condition for certain Bombardier, Inc. Model CL-600- 2B16 airplanes. The MCAI states: There have been three in-service reports on 604 Variant aeroplanes of a fractured fastener head on the inboard flap hinge- box forward fitting at Wing Station (WS) 76.50, found during a routine maintenance inspection. Investigation revealed that the installation of these fasteners on the inboard flap hinge-box forward fittings at WS 76.50 and WS 127.25, on both wings, does not conform to the engineering drawings. Incorrect installation may result in premature failure of the fasteners attaching the inboard flap hinge-box forward fitting. Failure of the fasteners could lead to the detachment of the flap hinge box and consequently the detachment of the flap surface. The loss of a flap surface could adversely affect the continued safe operation of the aeroplane. The original issue of [Canadian] AD CF-2013-39 [http://www.regulations.gov/#!documentDetail;D=FAA-2014-0054-0002] [which corresponds to FAA AD 2014-03-17, Amendment 39-17754 (79 FR 9389, February 19, 2014)] mandated a detailed visual inspection (DVI) of each inboard flap hinge-box forward fitting, on both wings, and rectification as required. Incorrectly oriented fasteners require repetitive inspections until the terminating action is accomplished. After the issuance of [Canadian] AD CF-2013-39, there has been one reported incident on a 604 Variant aeroplane where four fasteners were found fractured on the same flap hinge-box forward fitting. The investigation determined that the fasteners were incorrectly installed. The original issue of this [Canadian] AD was issued to reduce the initial and repetitive inspection intervals previously mandated in [Canadian] AD CF-2013-39, and to impose replacement of the incorrectly oriented fasteners within 24 months. The CL-600-1A11, - 2A12 and -2B16 (601-3A/-3R Variant) aeroplanes are addressed through [Canadian] AD CF-2013-39R1. Revision 1 of this [Canadian] AD is issued to clarify the requirements for the initial and repetitive inspections. You may examine the MCAI in the AD docket on the Internet at http://www.regulations.gov by searching for and locating Docket No. FAA-2015- 3988. Comments We gave the public the opportunity to participate in developing this AD. We received no comments on the NPRM or on the determination of the cost to the public. Change to Paragraph (k) of This AD Paragraph (k) of the NPRM specified to do the replacement on ``both'' wings. However, the replacement only needs to be done on the affected wing on which incorrectly oriented fasteners were found but none were found to be fractured. We have revised paragraph (k) of this AD to specify accomplishing the replacement on the affected wings. We [[Page 26122]] have coordinated this change with TCCA. Conclusion We reviewed the relevant data and determined that air safety and the public interest require adopting this AD with the change described previously and minor editorial changes. We have determined that these minor changes:Are consistent with the intent that was proposed in the NPRM for correcting the unsafe condition; and Do not add any additional burden upon the public than was already proposed in the NPRM. We also determined that these changes will not increase the economic burden on any operator or increase the scope of this AD. Related Service Information Under 1 CFR Part 51 Bombardier has issued Alert Service Bulletins: A604-57-006, Revision 04, dated November 12, 2014, including Appendices 1 and 2, dated September 26, 2013; and A605-57-004, Revision 04, dated November 12, 2014, including Appendices 1 and 2, dated September 26, 2013. The service information describes repetitive detailed visual inspections of each inboard flap fastener of the hinge-box forward fitting at WS 76.50 and WS 127.25, on both wings, and, if necessary, replacement of the fasteners. This service information is reasonably available because the interested parties have access to it through their normal course of business or by the means identified in the ADDRESSES section. Costs of Compliance We estimate that this AD affects 285 airplanes of U.S. registry. The actions required by AD 2014-17-51, and retained in this AD take about 1 work-hour per product, at an average labor rate of $85 per work-hour. Required parts cost about $0 per product. Based on these figures, the estimated cost of the actions that are required by AD 2014-17-51 is $85 per product. We also estimate that it will take about 58 work-hours per product to comply with the basic requirements of this AD. The average labor rate is $85 per work-hour. Required parts cost about $753 per product. Based on these figures, we estimate the cost of this AD on U.S. operators to be $1,619,655, or $5,683 per product. In addition, we estimate that any necessary follow-on actions will take about 58 work-hours and require parts costing $753, for a cost of $5,683 per product. We have no way of determining the number of aircraft that might need this action. According to the manufacturer, some of the costs of this AD may be covered under warranty, thereby reducing the cost impact on affected individuals. We do not control warranty coverage for affected individuals. As a result, we have included all costs in our cost estimate. 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 that 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); 3. Will not affect intrastate aviation in Alaska; and 4. 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. 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 Airworthiness Directive (AD) 2014-17-51, Amendment 39-17999 (79 FR 64088, October 28, 2014), and adding the following new AD: 2016-08-15 Bombardier, Inc.: Amendment 39-18491. Docket No. FAA- 2015-3988; Directorate Identifier 2015-NM-005-AD. (a) Effective Date This AD is effective June 6, 2016. (b) Affected ADs (1) This AD replaces AD 2014-17-51, Amendment 39-17999 (79 FR 64088, October 28, 2014) (``AD 2014-17-51''). (2) This AD affects AD 2014-03-17, Amendment 39-17754 (79 FR 9389, February 19, 2014) (``AD 2014-03-17''), only for the airplanes identified in paragraph (c) of this AD. (c) Applicability This AD applies to Bombardier, Inc. Model CL-600-2B16 airplanes, certificated in any category, serial numbers 5301 through 5665 inclusive, and 5701 through 5920 inclusive. (d) Subject Air Transport Association (ATA) of America Code 57, Wings. (e) Reason This AD was prompted by reports of fractured fastener heads on the inboard flap hinge-box forward fitting at Wing Station (WS) 76.50 due to incorrect installation. We are issuing this AD to detect and correct incorrectly oriented or fractured fasteners, that could result in premature failure of the fasteners attaching the inboard flap hinge-box forward fitting; failure of the fasteners could lead to the detachment of the flap hinge box and the flap surface, and consequent loss of control of the airplane. (f) Compliance Comply with this AD within the compliance times specified, unless already done. (g) Retained Inspection, With New Service Information: Airplanes Not Previously Inspected This paragraph restates the requirements of paragraph (g) of AD 2014-17-51, with new service information. For airplanes on which the actions required by AD 2014-03-17 have not been done as of November 12, 2014 (the effective date of AD 2014-17-51): Within 10 [[Page 26123]] flight cycles after November 12, 2014, or within 100 flight cycles after March 6, 2014 (the effective date of AD 2014-03-17), whichever occurs first, do a detailed visual inspection of each inboard flap fastener of the hinge-box forward fitting at WS 76.50 and WS 127.25, on both wings, to determine if the fasteners are correctly oriented and intact (non-fractured, with intact fastener head). Do the inspection in accordance with the Accomplishment Instructions of Bombardier Alert Service Bulletin A604-57-006, Revision 01, dated September 26, 2013, including Appendices 1 and 2, dated September 26, 2013, Revision 02, dated January 22, 2014, including Appendices 1 and 2, dated September 26, 2013, or Revision 04, dated November 12, 2014, including Appendices 1 and 2, dated September 26, 2013 (for serial numbers 5301 through 5665 inclusive); or Bombardier Alert Service Bulletin A605-57-004, Revision 01, dated September 26, 2013, including Appendices 1 and 2, dated September 26, 2013, Revision 02, dated January 22, 2014, including Appendices 1 and 2, dated September 26, 2013, or Revision 04, dated November 12, 2014, including Appendices 1 and 2, dated September 26, 2013 (for serial numbers 5701 through 5920 inclusive). As of the effective date of this AD, only use Bombardier Alert Service Bulletin A604-57-006, Revision 04, dated November 12, 2014, including Appendices 1 and 2, dated September 26, 2013; or Bombardier Alert Service Bulletin A605- 57-004, Revision 04, dated November 12, 2014, including Appendices 1 and 2, dated September 26, 2013; as applicable; for the actions required by this paragraph. (1) If all fasteners are found intact and correctly oriented, no further action is required by this AD. (2) If any fastener is found fractured: Before further flight, remove and replace all forward and aft fasteners at WS 76.50 and WS 127.25, regardless of condition or orientation, on both wings, in accordance with the Accomplishment Instructions of the applicable service information identified in paragraph (g) of this AD. As of the effective date of this AD, only use Bombardier Alert Service Bulletin A604-57-006, Revision 04, dated November 12, 2014, including Appendices 1 and 2, dated September 26, 2013; or Bombardier Alert Service Bulletin A605-57-004, Revision 04, dated November 12, 2014, including Appendices 1 and 2, dated September 26, 2013; as applicable; for the actions required by this paragraph. After replacement of all fasteners as required by this paragraph of this AD, no further action is required by this AD. (3) If any incorrectly oriented but intact fastener is found, and no fractured fastener is found, repeat the inspection required by paragraph (g) of this AD thereafter at intervals not to exceed 10 flight cycles, until the requirements of paragraph (i)(1) or (k) of this AD have been done. (h) Retained Actions, With New Service Information: Airplanes Previously Inspected, Having Incorrectly Oriented Fastener(s) This paragraph restates the requirements of paragraph (h) of AD 2014-17-51, with new service information. For airplanes on which an inspection required by paragraph (g) or (j) of AD 2014-03-17 has been done as of November 12, 2014 (the effective date of AD 2014-17- 51), and on which any incorrectly oriented fastener, but no fractured fastener, was found: Except as provided by paragraph (i)(3) of this AD, do a detailed visual inspection of all inboard flap fasteners of the hinge-box forward fitting at WS 76.50 and WS 127.25, on both wings, to determine if the fasteners are intact (non-fractured, with intact fastener head). Inspect within 10 flight cycles after November 12, 2014, or within 100 flight cycles after the most recent inspection done as required by AD 2014-03-17, whichever occurs first. Inspect in accordance with the Accomplishment Instructions of the applicable service information identified in paragraph (g) of this AD. As of the effective date of this AD, only use Bombardier Alert Service Bulletin A604-57-006, Revision 04, dated November 12, 2014, including Appendices 1 and 2, dated September 26, 2013; or Bombardier Alert Service Bulletin A605- 57-004, Revision 04, dated November 12, 2014, including Appendices 1 and 2, dated September 26, 2013; as applicable; for the actions required by this paragraph. (1) If all fasteners are found intact, repeat the inspection thereafter at intervals not to exceed 10 flight cycles, until the requirements of paragraph (i)(1) or (k) of this AD have been done. (2) If any fastener is found fractured: Before further flight, remove and replace all forward and aft fasteners at WS 76.50 and WS 127.25, regardless of condition or orientation, on both wings, in accordance with the Accomplishment Instructions of the applicable service information identified in paragraph (g) of this AD. As of the effective date of this AD, only use Bombardier Alert Service Bulletin A604-57-006, Revision 04, dated November 12, 2014, including Appendices 1 and 2, dated September 26, 2013; or Bombardier Alert Service Bulletin A605-57-004, Revision 04, dated November 12, 2014, including Appendices 1 and 2, dated September 26, 2013; as applicable; for the actions required by this paragraph. After replacement of all fasteners as required by this paragraph, no further action is required by this AD. (i) Retained Terminating Action, With New Service Information This paragraph restates the terminating action specified in paragraph (i) of AD 2014-17-51), with new service information. (1) Replacement of all forward and aft fasteners at WS 76.50 and WS 127.25, on both wings, in accordance with the Accomplishment Instructions of the applicable service information identified in paragraph (g) of this AD, terminates the requirements of this AD. As of the effective date of this AD, only use Bombardier Alert Service Bulletin A604-57-006, Revision 04, dated November 12, 2014, including Appendices 1 and 2, dated September 26, 2013; or Bombardier Alert Service Bulletin A605-57-004, Revision 04, dated November 12, 2014, including Appendices 1 and 2, dated September 26, 2013; as applicable; for the actions specified in this paragraph. (2) Accomplishment of the applicable requirements of this AD constitutes terminating action for the requirements of AD 2014-03-17 for that airplane only. (3) Replacement of all fractured and incorrectly oriented fasteners before November 12, 2014 (the effective date of AD 2014- 17-51), as provided by paragraph (i) or (k) of AD 2014-03-17, is acceptable for compliance with the requirements of this AD. (j) Retained Special Flight Permit Prohibition This paragraph restates the requirements of paragraph (j) of AD 2014-17-51. Special flight permits to operate the airplane to a location where the airplane can be repaired in accordance with 14 CFR 21.197 and 21.199 are not allowed. (k) New Requirement of This AD: Post-Inspection Fastener Replacement For airplanes on which incorrectly oriented fasteners were found during any inspection required by paragraph (g), (g)(3), (h), or (h)(1) of this AD, but none were found to be fractured: Within 24 months after the effective date of this AD, remove and replace all forward and aft fasteners at WS 76.50 and WS 127.25, regardless of condition or orientation, on affected wings, in accordance with the Accomplishment Instructions of Bombardier Alert Service Bulletin A604-57-006, Revision 04, dated November 12, 2014, including Appendices 1 and 2, dated September 26, 2013 (for serial numbers 5301 through 5665 inclusive); or Bombardier Alert Service Bulletin A605-57-004, Revision 04, dated November 12, 2014, including Appendices 1 and 2, dated September 26, 2013 (for serial numbers 5701 through 5920 inclusive). Accomplishing the requirements of this paragraph terminates the requirements of this AD. (l) Credit for Previous Actions (1) This paragraph provides credit for actions required by paragraphs (g), (h), and (i)(1) of this AD, if those actions were performed before the effective date of this AD using the applicable service information identified in paragraphs (l)(1)(i) and (l)(1)(ii) of this AD, which are not incorporated by reference in this AD. (i) Bombardier Alert Service Bulletin A604-57-006, Revision 03, dated August 19, 2014, including Appendices 1 and 2, dated September 26, 2013. (ii) Bombardier Alert Service Bulletin A605-57-004, Revision 03, dated August 19, 2014, including Appendices 1 and 2, dated September 26, 2013. (2) This paragraph provides credit for actions required by paragraph (k) of this AD, if those actions were done before the effective date of this AD using the applicable service information identified in paragraphs (l)(2)(i) through (l)(2)(iv) of this AD. (i) Bombardier Alert Service Bulletin A604-57-006, Revision 01, dated September 26, 2013, including Appendices 1 and 2, dated September 26, 2013, which is incorporated by reference in AD 2014- 03-17. (ii) Bombardier Alert Service Bulletin A604-57-006, Revision 02, dated January 22, 2014, including Appendices 1 and 2, dated [[Page 26124]] September 26, 2013, which was incorporated by reference in AD 2014- 17-51. (iii) Bombardier Alert Service Bulletin A605-57-004, Revision 01, dated September 26, 2013, including Appendices 1 and 2, dated September 26, 2013, which is incorporated by reference in AD 2014- 03-17. (iv) Bombardier Alert Service Bulletin A604-57-004, Revision 02, dated January 22, 2014, including Appendices 1 and 2, dated September 26, 2013, which was incorporated by reference in AD 2014- 17-51. (m) Other FAA AD Provisions The following provisions also apply to this AD: (1) Alternative Methods of Compliance (AMOCs): The Manager, New York Aircraft Certification Office (ACO), 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, NY 11590; telephone 516-228-7300; fax 516-794-5531. (i) 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. (ii) AMOCs previously approved for AD 2014-17-51 are acceptable for the corresponding requirements of this AD. (2) Contacting the Manufacturer: As of the effective date of this AD, for any requirement in this AD to obtain corrective actions from a manufacturer, the action must be accomplished using a method approved by the Manager, New York ACO, ANE-170, Engine and Propeller Directorate, FAA; or Transport Canada Civil Aviation (TCCA); or Bombardier, Inc.'s TCCA Design Approval Organization (DAO). If approved by the DAO, the approval must include the DAO-authorized signature. (n) Related Information (1) Refer to Mandatory Continuing Airworthiness Information (MCAI) Canadian Emergency Airworthiness Directive CF-2014-27R1, dated August 29, 2014, for related information. This MCAI may be found in the AD docket on the Internet at http://www.regulations.gov by searching for and locating Docket No. FAA-2015-3988. (2) Service information identified in this AD that is not incorporated by reference is available at the addresses specified in paragraphs (o)(6) and (o)(7) of this AD. (o) Material Incorporated by Reference (1) The Director of the Federal Register approved the incorporation by reference (IBR) of the service information listed in this paragraph under 5 U.S.C. 552(a) and 1 CFR part 51. (2) You must use this service information as applicable to do the actions required by this AD, unless this AD specifies otherwise. (3) The following service information was approved for IBR on June 6, 2016. (i) Bombardier Alert Service Bulletin A604-57-006, Revision 04, dated November 12, 2014, including Appendices 1 and 2, dated September 26, 2013. (ii) Bombardier Alert Service Bulletin A605-57-004, Revision 04, dated November 12, 2014, including Appendices 1 and 2, dated September 26, 2013. (4) The following service information was approved for IBR on November 12, 2014 (79 FR 64088, October 28, 2014). (i) Bombardier Alert Service Bulletin A604-57-006, Revision 02, dated January 22, 2014, including Appendices 1 and 2, dated September 26, 2013. (ii) Bombardier Alert Service Bulletin A605-57-004, Revision 02, dated January 22, 2014, including Appendices 1 and 2, dated September 26, 2013. (5) The following service information was approved for IBR on March 6, 2014 (79 FR 9389, February 19, 2014). (i) Bombardier Alert Service Bulletin A604-57-006, Revision 01, dated September 26, 2013, including Appendices 1 and 2, dated September 26, 2013. (ii) Bombardier Alert Service Bulletin A605-57-004, Revision 01, dated September 26, 2013, including Appendices 1 and 2, dated September 26, 2013. (6) For service information identified in this AD, contact Bombardier, Inc., 400 C[ocirc]te Vertu Road West, Dorval, Qu[eacute]bec H4S 1Y9, Canada; telephone 514-855-5000; fax 514-855- 7401; email [email protected]; Internet http://www.bombardier.com. (7) You may view this service information at the FAA, Transport Airplane Directorate, 1601 Lind Avenue SW., Renton, WA. For information on the availability of this material at the FAA, call 425-227-1221. (8) You may view this 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/cfr/ibr-locations.html. Issued in Renton, Washington, on April 8, 2016. Michael Kaszycki, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 2016-08959 Filed 4-29-16; 8:45 am] BILLING CODE 4910-13-P
![Federal Register / Vol. 81, No. 84 / Monday, May 2, 2016 / Rules and Regulations 26121
Issued in Renton, Washington, on April 13, this AD as of March 6, 2014 (79 FR for certain Bombardier, Inc. Model CL–
2016. 9389, February 19, 2014). 600–2B16 airplanes. The MCAI states:
Victor Wicklund, ADDRESSES: For service information There have been three in-service reports on
Acting Manager, Transport Airplane identified in this final rule, contact 604 Variant aeroplanes of a fractured fastener
Directorate, Aircraft Certification Service. Bombardier, Inc., 400 Côte-Vertu Road head on the inboard flap hinge-box forward
[FR Doc. 2016–09119 Filed 4–29–16; 8:45 am] West, Dorval, Québec H4S 1Y9, Canada; fitting at Wing Station (WS) 76.50, found
BILLING CODE 4910–13–P telephone 514–855–5000; fax 514–855– during a routine maintenance inspection.
Investigation revealed that the installation of
7401; email thd.crj@aero.
these fasteners on the inboard flap hinge-box
bombardier.com; Internet http:// forward fittings at WS 76.50 and WS 127.25,
DEPARTMENT OF TRANSPORTATION www.bombardier.com. You may view on both wings, does not conform to the
this referenced service information at engineering drawings. Incorrect installation
Federal Aviation Administration the FAA, Transport Airplane may result in premature failure of the
Directorate, 1601 Lind Avenue SW., fasteners attaching the inboard flap hinge-box
14 CFR Part 39 Renton, WA. For information on the forward fitting. Failure of the fasteners could
availability of this material at the FAA, lead to the detachment of the flap hinge box
[Docket No. FAA–2015–3988; Directorate
and consequently the detachment of the flap
Identifier 2015–NM–005–AD; Amendment call 425–227–1221. It is also available
surface. The loss of a flap surface could
39–18491; AD 2016–08–15] on the Internet at http:// adversely affect the continued safe operation
www.regulations.gov by searching for of the aeroplane.
RIN 2120–AA64
and locating Docket No. FAA–2015– The original issue of [Canadian] AD CF–
Airworthiness Directives; Bombardier, 3988. 2013–39 [http://www.regulations.gov/
Inc. Airplanes #!documentDetail;D=FAA-2014-0054-0002]
Examining the AD Docket [which corresponds to FAA AD 2014–03–17,
AGENCY: Federal Aviation You may examine the AD docket on Amendment 39–17754 (79 FR 9389, February
Administration (FAA), Department of the Internet at http:// 19, 2014)] mandated a detailed visual
www.regulations.gov by searching for inspection (DVI) of each inboard flap hinge-
Transportation (DOT).
box forward fitting, on both wings, and
ACTION: Final rule. and locating Docket No. FAA–2015– rectification as required. Incorrectly oriented
3988; or in person at the Docket fasteners require repetitive inspections until
SUMMARY: We are superseding Management Facility between 9 a.m. the terminating action is accomplished.
Airworthiness Directive (AD) 2014–17– and 5 p.m., Monday through Friday, After the issuance of [Canadian] AD CF–
51 for certain Bombardier, Inc. Model except Federal holidays. The AD docket 2013–39, there has been one reported
CL–600–2B16 airplanes. AD 2014–17– contains this AD, the regulatory incident on a 604 Variant aeroplane where
51 required inspecting the inboard flap evaluation, any comments received, and four fasteners were found fractured on the
fasteners of the hinge-box forward other information. The address for the same flap hinge-box forward fitting. The
investigation determined that the fasteners
fitting at Wing Station (WS) 76.50 and Docket Office (telephone 800–647–5527) were incorrectly installed.
WS 127.25 to determine the orientation is Docket Management Facility, U.S. The original issue of this [Canadian] AD
and condition of the fasteners, as Department of Transportation, Docket was issued to reduce the initial and repetitive
applicable, and replacement or Operations, M–30, West Building inspection intervals previously mandated in
repetitive inspections of the fasteners if Ground Floor, Room W12–140, 1200 [Canadian] AD CF–2013–39, and to impose
necessary. AD 2014–17–51 also New Jersey Avenue SE., Washington, replacement of the incorrectly oriented
provided for optional terminating action DC 20590. fasteners within 24 months. The CL–600–
for the requirements of that AD. This 1A11, –2A12 and –2B16 (601–3A/–3R
FOR FURTHER INFORMATION CONTACT: Aziz
new AD requires accomplishment of the Variant) aeroplanes are addressed through
Ahmed, Aerospace Engineer, Propulsion [Canadian] AD CF–2013–39R1.
previously optional terminating action. and Services Branch, ANE–173, FAA, Revision 1 of this [Canadian] AD is issued
This AD was prompted by a New York Aircraft Certification Office to clarify the requirements for the initial and
determination that that additional (ACO), 1600 Stewart Avenue, Suite 410, repetitive inspections.
action is necessary. We are issuing this Westbury, NY 11590; telephone 516–
AD to detect and correct incorrectly You may examine the MCAI in the
228–7329; fax 516–794–5531. AD docket on the Internet at http://
oriented or fractured fasteners, that SUPPLEMENTARY INFORMATION:
could result in premature failure of the www.regulations.gov by searching for
fasteners attaching the inboard flap Discussion and locating Docket No. FAA–2015–
hinge-box forward fitting; failure of the 3988.
We issued a notice of proposed
fasteners could lead to the detachment rulemaking (NPRM) to amend 14 CFR Comments
of the flap hinge box and the flap part 39 to supersede AD 2014–17–51, We gave the public the opportunity to
surface, and consequent loss of control Amendment 39–17999 (79 FR 64088, participate in developing this AD. We
of the airplane. October 28, 2014) (‘‘AD 2014–17–51’’). received no comments on the NPRM or
DATES: This AD is effective June 6, 2016. AD 2014–17–51 applied to certain on the determination of the cost to the
The Director of the Federal Register Bombardier, Inc. Model CL–600–2B16 public.
approved the incorporation by reference airplanes. The NPRM published in the
of certain publications listed in this AD Federal Register on October 19, 2015 Change to Paragraph (k) of This AD
as of June 6, 2016. (80 FR 63141) (‘‘the NPRM’’). Paragraph (k) of the NPRM specified
The Director of the Federal Register Transport Canada Civil Aviation to do the replacement on ‘‘both’’ wings.
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approved the incorporation by reference (TCCA), which is the aviation authority However, the replacement only needs to
of certain other publications listed in for Canada, has issued Canadian be done on the affected wing on which
this AD as of November 12, 2014 (79 FR Airworthiness Directive CF–2014–27R1, incorrectly oriented fasteners were
64088, October 28, 2014). dated August 29, 2014 (referred to after found but none were found to be
The Director of the Federal Register this as the Mandatory Continuing fractured. We have revised paragraph (k)
approved the incorporation by reference Airworthiness Information, or ‘‘the of this AD to specify accomplishing the
of certain other publications listed in MCAI’’), to correct an unsafe condition replacement on the affected wings. We
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have coordinated this change with costing $753, for a cost of $5,683 per Adoption of the Amendment
TCCA. product. We have no way of Accordingly, under the authority
determining the number of aircraft that delegated to me by the Administrator,
Conclusion
might need this action. the FAA amends 14 CFR part 39 as
We reviewed the relevant data and According to the manufacturer, some follows:
determined that air safety and the of the costs of this AD may be covered
public interest require adopting this AD under warranty, thereby reducing the PART 39—AIRWORTHINESS
with the change described previously cost impact on affected individuals. We DIRECTIVES
and minor editorial changes. We have do not control warranty coverage for
determined that these minor changes: affected individuals. As a result, we ■ 1. The authority citation for part 39
• Are consistent with the intent that have included all costs in our cost continues to read as follows:
was proposed in the NPRM for estimate. Authority: 49 U.S.C. 106(g), 40113, 44701.
correcting the unsafe condition; and
• Do not add any additional burden Authority for This Rulemaking § 39.13 [Amended]
upon the public than was already Title 49 of the United States Code ■ 2. The FAA amends § 39.13 by
proposed in the NPRM. specifies the FAA’s authority to issue removing Airworthiness Directive (AD)
We also determined that these 2014–17–51, Amendment 39–17999 (79
rules on aviation safety. Subtitle I,
changes will not increase the economic FR 64088, October 28, 2014), and
section 106, describes the authority of
burden on any operator or increase the adding the following new AD:
the FAA Administrator. ‘‘Subtitle VII:
scope of this AD.
Aviation Programs,’’ describes in more 2016–08–15 Bombardier, Inc.: Amendment
Related Service Information Under 1 detail the scope of the Agency’s 39–18491. Docket No. FAA–2015–3988;
CFR Part 51 authority. Directorate Identifier 2015–NM–005–AD.
Bombardier has issued Alert Service We are issuing this rulemaking under (a) Effective Date
Bulletins: the authority described in ‘‘Subtitle VII, This AD is effective June 6, 2016.
• A604–57–006, Revision 04, dated Part A, Subpart III, Section 44701:
General requirements.’’ Under that (b) Affected ADs
November 12, 2014, including
Appendices 1 and 2, dated September section, Congress charges the FAA with (1) This AD replaces AD 2014–17–51,
26, 2013; and promoting safe flight of civil aircraft in Amendment 39–17999 (79 FR 64088, October
28, 2014) (‘‘AD 2014–17–51’’).
• A605–57–004, Revision 04, dated air commerce by prescribing regulations
for practices, methods, and procedures (2) This AD affects AD 2014–03–17,
November 12, 2014, including Amendment 39–17754 (79 FR 9389, February
Appendices 1 and 2, dated September the Administrator finds necessary for
19, 2014) (‘‘AD 2014–03–17’’), only for the
26, 2013. safety in air commerce. This regulation airplanes identified in paragraph (c) of this
The service information describes is within the scope of that authority AD.
repetitive detailed visual inspections of because it addresses an unsafe condition
that is likely to exist or develop on (c) Applicability
each inboard flap fastener of the hinge-
box forward fitting at WS 76.50 and WS products identified in this rulemaking This AD applies to Bombardier, Inc. Model
127.25, on both wings, and, if necessary, action. CL–600–2B16 airplanes, certificated in any
category, serial numbers 5301 through 5665
replacement of the fasteners. This Regulatory Findings inclusive, and 5701 through 5920 inclusive.
service information is reasonably
available because the interested parties We determined that this AD will not (d) Subject
have access to it through their normal have federalism implications under Air Transport Association (ATA) of
course of business or by the means Executive Order 13132. This AD will America Code 57, Wings.
identified in the ADDRESSES section. not have a substantial direct effect on (e) Reason
the States, on the relationship between
Costs of Compliance the national government and the States, This AD was prompted by reports of
fractured fastener heads on the inboard flap
We estimate that this AD affects 285 or on the distribution of power and hinge-box forward fitting at Wing Station
airplanes of U.S. registry. responsibilities among the various (WS) 76.50 due to incorrect installation. We
The actions required by AD 2014–17– levels of government. are issuing this AD to detect and correct
51, and retained in this AD take about For the reasons discussed above, I incorrectly oriented or fractured fasteners,
1 work-hour per product, at an average certify that this AD: that could result in premature failure of the
labor rate of $85 per work-hour. 1. Is not a ‘‘significant regulatory fasteners attaching the inboard flap hinge-box
Required parts cost about $0 per forward fitting; failure of the fasteners could
action’’ under Executive Order 12866; lead to the detachment of the flap hinge box
product. Based on these figures, the
estimated cost of the actions that are 2. Is not a ‘‘significant rule’’ under the and the flap surface, and consequent loss of
required by AD 2014–17–51 is $85 per DOT Regulatory Policies and Procedures control of the airplane.
product. (44 FR 11034, February 26, 1979);
(f) Compliance
We also estimate that it will take 3. Will not affect intrastate aviation in
Comply with this AD within the
about 58 work-hours per product to Alaska; and compliance times specified, unless already
comply with the basic requirements of 4. Will not have a significant done.
this AD. The average labor rate is $85 economic impact, positive or negative,
(g) Retained Inspection, With New Service
per work-hour. Required parts cost on a substantial number of small entities
Information: Airplanes Not Previously
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about $753 per product. Based on these under the criteria of the Regulatory Inspected
figures, we estimate the cost of this AD Flexibility Act.
This paragraph restates the requirements of
on U.S. operators to be $1,619,655, or List of Subjects in 14 CFR Part 39 paragraph (g) of AD 2014–17–51, with new
$5,683 per product. service information. For airplanes on which
In addition, we estimate that any Air transportation, Aircraft, Aviation the actions required by AD 2014–03–17 have
necessary follow-on actions will take safety, Incorporation by reference, not been done as of November 12, 2014 (the
about 58 work-hours and require parts Safety. effective date of AD 2014–17–51): Within 10
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![26124 Federal Register / Vol. 81, No. 84 / Monday, May 2, 2016 / Rules and Regulations
September 26, 2013, which was incorporated (3) The following service information was DEPARTMENT OF TRANSPORTATION
by reference in AD 2014–17–51. approved for IBR on June 6, 2016.
(iii) Bombardier Alert Service Bulletin (i) Bombardier Alert Service Bulletin Federal Aviation Administration
A605–57–004, Revision 01, dated September A604–57–006, Revision 04, dated November
26, 2013, including Appendices 1 and 2, 12, 2014, including Appendices 1 and 2, 14 CFR Part 39
dated September 26, 2013, which is dated September 26, 2013.
incorporated by reference in AD 2014–03–17. [Docket No. FAA–2015–1130; Directorate
(ii) Bombardier Alert Service Bulletin
(iv) Bombardier Alert Service Bulletin Identifier 2015–CE–008–AD; Amendment
A605–57–004, Revision 04, dated November 39–18492; AD 2015–09–04 R1]
A604–57–004, Revision 02, dated January 22,
2014, including Appendices 1 and 2, dated 12, 2014, including Appendices 1 and 2,
dated September 26, 2013. RIN 2120–AA64
September 26, 2013, which was incorporated
by reference in AD 2014–17–51. (4) The following service information was
approved for IBR on November 12, 2014 (79 Airworthiness Directives; DG
(m) Other FAA AD Provisions FR 64088, October 28, 2014). Flugzeugbau GmbH Gliders
The following provisions also apply to this (i) Bombardier Alert Service Bulletin
AD:
AGENCY: Federal Aviation
A604–57–006, Revision 02, dated January 22, Administration (FAA), Department of
(1) Alternative Methods of Compliance 2014, including Appendices 1 and 2, dated
(AMOCs): The Manager, New York Aircraft Transportation (DOT).
September 26, 2013.
Certification Office (ACO), ANE–170, FAA, ACTION: Final rule.
(ii) Bombardier Alert Service Bulletin
has the authority to approve AMOCs for this
AD, if requested using the procedures found A605–57–004, Revision 02, dated January 22, SUMMARY: We are revising Airworthiness
in 14 CFR 39.19. In accordance with 14 CFR 2014, including Appendices 1 and 2, dated Directive (AD) 2015–09–04 for DG
39.19, send your request to your principal September 26, 2013. Flugzeugbau GmbH Model DG–1000T
inspector or local Flight Standards District (5) The following service information was gliders equipped with a Solo
Office, as appropriate. If sending information approved for IBR on March 6, 2014 (79 FR Kleinmotoren Model 2350 C engine.
directly to the ACO, send it to ATTN: 9389, February 19, 2014).
Program Manager, Continuing Operational
This AD results from mandatory
(i) Bombardier Alert Service Bulletin
Safety, FAA, New York ACO, 1600 Stewart continuing airworthiness information
A604–57–006, Revision 01, dated September
Avenue, Suite 410, Westbury, NY 11590; (MCAI) issued by an aviation authority
26, 2013, including Appendices 1 and 2,
telephone 516–228–7300; fax 516–794–5531. of another country to identify and
dated September 26, 2013.
(i) Before using any approved AMOC, correct an unsafe condition on an
(ii) Bombardier Alert Service Bulletin
notify your appropriate principal inspector, aviation product. The MCAI describes
or lacking a principal inspector, the manager A605–57–004, Revision 01, dated September
26, 2013, including Appendices 1 and 2,
the unsafe condition as engine shaft
of the local flight standards district office/ failure and consequent propeller
certificate holding district office. The AMOC dated September 26, 2013.
(6) For service information identified in
detachment. We are issuing this AD to
approval letter must specifically reference
this AD. this AD, contact Bombardier, Inc., 400 Côte require actions to address the unsafe
(ii) AMOCs previously approved for AD Vertu Road West, Dorval, Québec H4S 1Y9, condition on these products.
2014–17–51 are acceptable for the Canada; telephone 514–855–5000; fax 514– DATES: This AD is effective June 6, 2016.
corresponding requirements of this AD. 855–7401; email thd.crj@ The Director of the Federal Register
(2) Contacting the Manufacturer: As of the aero.bombardier.com; Internet http:// approved the incorporation by reference
effective date of this AD, for any requirement www.bombardier.com. of certain publications listed in the AD
in this AD to obtain corrective actions from as of June 6, 2016.
(7) You may view this service information
a manufacturer, the action must be
at the FAA, Transport Airplane Directorate, The Director of the Federal Register
accomplished using a method approved by
the Manager, New York ACO, ANE–170, 1601 Lind Avenue SW., Renton, WA. For approved the incorporation by reference
Engine and Propeller Directorate, FAA; or information on the availability of this of a certain other publication listed in
Transport Canada Civil Aviation (TCCA); or material at the FAA, call 425–227–1221. this AD as of May 26, 2015 (80 FR
Bombardier, Inc.’s TCCA Design Approval (8) You may view this service information 25591, May 5, 2015).
Organization (DAO). If approved by the DAO, that is incorporated by reference at the ADDRESSES: You may examine the AD
the approval must include the DAO- National Archives and Records docket on the Internet at http://
authorized signature. Administration (NARA). For information on www.regulations.gov by searching for
(n) Related Information the availability of this material at NARA, call and locating Docket No. FAA–2015–
202–741–6030, or go to: http:// 1130; or in person at the Docket
(1) Refer to Mandatory Continuing
Airworthiness Information (MCAI) Canadian www.archives.gov/federal-register/cfr/ibr- Management Facility, U.S. Department
Emergency Airworthiness Directive CF– locations.html. of Transportation, Docket Operations,
2014–27R1, dated August 29, 2014, for Issued in Renton, Washington, on April 8, M–30, West Building Ground Floor,
related information. This MCAI may be 2016. Room W12–140, 1200 New Jersey
found in the AD docket on the Internet at Avenue SE., Washington, DC 20590.
http://www.regulations.gov by searching for Michael Kaszycki,
Acting Manager, Transport Airplane For service information identified in
and locating Docket No. FAA–2015–3988.
(2) Service information identified in this Directorate, Aircraft Certification Service. this AD, contact Solo Kleinmotoren
AD that is not incorporated by reference is [FR Doc. 2016–08959 Filed 4–29–16; 8:45 am]
GmbH, Postfach 600152, 71050
available at the addresses specified in Sindelfingen, Germany; telephone: +49
BILLING CODE 4910–13–P
paragraphs (o)(6) and (o)(7) of this AD. 7031 301–0; fax: +49 7031 301–136;
email: aircraft@solo-germany.com;
(o) Material Incorporated by Reference
Internet: http://aircraft.solo-online.com
mstockstill on DSK3G9T082PROD with RULES
(1) The Director of the Federal Register and DG Flugzeugbau GmbH, Otto
approved the incorporation by reference
Lilienthal Weg 2/Am Flugplatz, 76646
(IBR) of the service information listed in this
paragraph under 5 U.S.C. 552(a) and 1 CFR Bruchsal, Germany; telephone: +49 7251
part 51. 3020–0; fax: +49 7251 3020–200; email:
(2) You must use this service information wassenaar@dg-flugzeugbau.de; Internet:
as applicable to do the actions required by http://www.dg-flugzeugbau.de/
this AD, unless this AD specifies otherwise. index.php?id=1329. You may view this
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Document Created: 2016-04-30 13:35:36
Document Modified: 2016-04-30 13:35:36
| Category | Regulatory Information | |
| Collection | Federal Register | |
| sudoc Class | AE 2.7: GS 4.107: AE 2.106: | |
| Publisher | Office of the Federal Register, National Archives and Records Administration | |
| Section | Rules and Regulations | |
| Action | Final rule. | |
| Dates | This AD is effective June 6, 2016. | |
| Contact | Aziz Ahmed, Aerospace Engineer, Propulsion and Services Branch, ANE-173, FAA, New York Aircraft Certification Office (ACO), 1600 Stewart Avenue, Suite 410, Westbury, NY 11590; telephone 516-228-7329; fax 516-794-5531. | |
| FR Citation | 81 FR 26121 | |
| RIN Number | 2120-AA64 | |
| CFR Associated | Air Transportation; Aircraft; Aviation Safety; Incorporation by Reference and Safety |
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