81 FR 79381 - Airworthiness Directives; Bombardier, Inc. Airplanes
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration Federal Register Volume 81, Issue 219 (November 14, 2016)
Federal Aviation Administration
Federal Register Volume 81, Issue 219 (November 14, 2016)
| Page Range | 79381-79384 | |
| FR Document | 2016-25009 |
[Federal Register Volume 81, Number 219 (Monday, November 14, 2016)] [Rules and Regulations] [Pages 79381-79384] From the Federal Register Online [www.thefederalregister.org] [FR Doc No: 2016-25009] ======================================================================== Rules and Regulations Federal Register ________________________________________________________________________ This section of the FEDERAL REGISTER contains regulatory documents having general applicability and legal effect, most of which are keyed to and codified in the Code of Federal Regulations, which is published under 50 titles pursuant to 44 U.S.C. 1510. The Code of Federal Regulations is sold by the Superintendent of Documents. Prices of new books are listed in the first FEDERAL REGISTER issue of each week. ======================================================================== Federal Register / Vol. 81, No. 219 / Monday, November 14, 2016 / Rules and Regulations [[Page 79381]] DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA-2016-5593; Directorate Identifier 2015-NM-184-AD; Amendment 39-18687; AD 2016-21-06] 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) 2015-02-23, for certain Bombardier, Inc. Model CL-600-1A11 (CL-600), CL-600-2A12 (CL-601), and CL-600-2B16 (CL-601-3A and CL-601-3R Variants) airplanes. AD 2015-02-23 required repetitive inspections for fractured or incorrectly oriented fasteners on the inboard flap hinge-box forward fittings on both wings, and replacement of all fasteners if necessary. This new AD also requires replacement of the fasteners, which terminates the requirements of this AD. This AD was prompted by reports of incorrectly oriented fasteners. We are issuing this AD to prevent incorrectly oriented or fractured fasteners, which could result in detachment of the flap hinge-box and the flap surface, and consequent reduced controllability of the airplane. DATES: This AD is effective December 19, 2016. The Director of the Federal Register approved the incorporation by reference of certain publications listed in this AD as of February 18, 2015 (80 FR 5670, February 3, 2015). 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; Widebody Customer Response Center North America toll-free telephone: 1-866-538-1247 or direct-dial telephone: 1-514-855-2999; 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-2016-5593. 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-2016- 5593; 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, Airframe and Mechanical Systems Branch, ANE-171, 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 2015-02-23, Amendment 39-18092 (80 FR 5670, February 3, 2015) (``AD 2015-02-23''). AD 2015-02-23 applied to certain Bombardier, Inc. Model CL-600-1A11 (CL-600), CL-600-2A12 (CL-601), and CL-600-2B16 (CL-601-3A and CL-601-3R Variants) airplanes. AD 2015-02-23 corresponded to Canadian Emergency AD CF-2013-39R2, dated December 12, 2014 (referred to after this as the Mandatory Continuing Airworthiness Information, or ``the MCAI''). The MCAI was issued by Transport Canada Civil Aviation (TCCA), which is the aviation authority for Canada. The preamble to AD 2015-02-23 explained that we considered the requirements interim action and were considering further rulemaking. We have now determined that further rulemaking is indeed necessary and that, instead of continuing repetitive inspections, for airplanes which have any incorrectly oriented fastener, and no fractured or missing fastener, replacement of all forward and aft fasteners, regardless of condition or orientation, is necessary. This AD follows from that determination. The NPRM published in the Federal Register on April 20, 2016 (81 FR 23202). The NPRM was prompted by reports of incorrectly oriented fasteners. The NPRM proposed to continue to require repetitive inspections for fractured or incorrectly oriented fasteners on the inboard flap hinge-box forward fittings on both wings, and replacement of all fasteners if necessary. The NPRM also proposed to require replacement of the fasteners, which would terminate the requirements of this AD. We are issuing this AD to prevent incorrectly oriented or fractured fasteners, which could result in detachment of the flap hinge-box and the flap surface, and consequent reduced controllability of the airplane. 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. Conclusion We reviewed the available data and determined that air safety and the public interest require adopting this AD as proposed except for 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. [[Page 79382]] Related Service Information Under 1 CFR Part 51 Bombardier has issued Alert Service Bulletins A600-0763, Revision 02, dated December 9, 2014, including Appendixes 1 and 2, dated September 26, 2013; and A601-0627, Revision 02, dated December 9, 2014, including Appendixes 1 and 2, dated September 26, 2013. The service information describes procedures for repetitive inspections of the fasteners on the inboard flap hinge-box forward fittings on both wings, and replacement of fasteners. These documents are distinct since they apply to different airplane models. 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 120 airplanes of U.S. registry. The actions required by AD 2015-02-23, and retained in this AD, take about 1 work-hour per product, at an average labor rate of $85 per work-hour. Based on these figures, the estimated cost of the actions that are required by AD 2015-02-23 is $85 per product. We also estimate that it would take about 59 work-hours per product to comply with the basic requirements of this AD. The average labor rate is $85 per work-hour. We have received no definitive data that would enable us to provide cost estimates for the parts cost. Based on these figures, we estimate the cost of this AD on U.S. operators to be $601,800, or $5,015 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 available 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) 2015-02-23, Amendment 39-18092 (80 FR 5670, February 3, 2015), and adding the following new AD: 2016-21-06 Bombardier, Inc.: Amendment 39-18687; Docket No. FAA- 2016-5593; Directorate Identifier 2015-NM-184-AD. (a) Effective Date This AD is effective December 19, 2016. (b) Affected ADs This AD replaces AD 2015-02-23, Amendment 39-18092 (80 FR 5670, February 3, 2015) (``AD 2015-02-23''). This AD affects AD 2014-03- 17, Amendment 39-17754 (79 FR 9389, February 19, 2014) (``AD 2014- 03-17''). (c) Applicability This AD applies to the Bombardier, Inc. airplanes identified in paragraphs (c)(1), (c)(2), and (c)(3) of this AD, certificated in any category. (1) Bombardier, Inc. Model CL-600-1A11 (CL-600) airplanes, having serial numbers (S/Ns) 1004 through 1085 inclusive. (2) Bombardier, Inc. Model CL-600-2A12 (CL-601) airplanes, having S/Ns 3001 through 3066 inclusive. (3) Bombardier, Inc. Model CL-600-2B16 (CL-601-3A and CL-601-3R Variants) airplanes, having S/Ns 5001 through 5194 inclusive. (d) Subject Air Transport Association (ATA) of America Code 57, Wings. (e) Reason This AD was prompted by reports of incorrectly oriented fasteners. We are issuing this AD to prevent incorrectly oriented or fractured fasteners, which could result in detachment of the flap hinge-box and the flap surface, and consequent reduced controllability of the airplane. (f) Compliance Comply with this AD within the compliance times specified, unless already done. (g) Retained Inspection on Airplanes Not Previously Inspected, With No Changes This paragraph restates the requirements of paragraph (g) of AD 2015-02-23, with no changes. For airplanes that have not been inspected as required by paragraph (g) of AD 2014-03-17, as of February 18, 2015 (the effective date of AD 2015-02-23): Within 10 flight cycles after February 18, 2015, or 100 flight cycles after March 6, 2014 (the effective date of AD 2014-03-17), whichever occurs first, do a detailed visual inspection for incorrect orientation and any fractured or missing fastener heads of each inboard flap fastener of the hinge-box forward fitting at wing station (WS) 76.50 and WS 127.25, on both wings, in accordance with the Accomplishment Instructions of the applicable service information specified in paragraphs (g)(1) and (g)(2) of this AD. Accomplishing the inspection required by this paragraph terminates the requirements of paragraph (g) of AD 2014-03-17 for the inspected airplane only. (1) For Model CL-600-1A11 (CL-600) airplanes having S/Ns 1004 through 1085 inclusive: Bombardier Alert Service Bulletin A600-0763, Revision 02, dated December 9, 2014, including Appendixes 1 and 2, dated September 26, 2013. (2) For Model CL-600-2A12 (CL-601) airplanes having S/Ns 3001 through 3066 [[Page 79383]] inclusive, and Model CL-600-2B16 (CL-601-3A and CL-601-3R Variants) airplanes having S/Ns 5001 through 5194 inclusive: Bombardier Alert Service Bulletin A601-0627, Revision 02, dated December 9, 2014, including Appendixes 1 and 2, dated September 26, 2013. (h) Retained Corrective Actions for Paragraph (g) of This AD, With Revised Paragraph (h)(2) of This AD (1) This paragraph restates the requirements of paragraph (h)(1) of AD 2015-02-23, with no changes. If, during any inspection required by paragraph (g) of this AD, all fasteners are found correctly oriented and not fractured, and no fastener heads are missing (fasteners found intact): No further action is required by this AD. (2) This paragraph restates the requirements of paragraph (h)(2) of AD 2015-02-23, with revised references to replacement paragraphs. If, during any inspection required by paragraph (g) of this AD, any fastener is found incorrectly oriented but no fasteners are fractured or are missing a fastener head (fasteners found intact), repeat the inspection required by paragraph (g) of this AD thereafter at intervals not to exceed 10 flight cycles until the replacements specified in paragraphs (h)(3), (k), or (n) of this AD are accomplished. (3) This paragraph restates the requirements of paragraph (h)(3) of AD 2015-02-23, with no changes. If, during any inspection required by paragraph (g) of this AD, any fastener is found fractured or has a missing fastener head: Before further flight, remove and replace all forward and aft fasteners (regardless of orientation or condition) at WS 76.50 and WS 127.25, on both wings, in accordance with the Accomplishment Instructions of the applicable service information specified in paragraphs (h)(3)(i) and (h)(3)(ii) of this AD, except as required by paragraph (m) of this AD. After accomplishing the replacements required by this paragraph, no further action is required by this AD. (i) For Model CL-600-1A11 (CL-600) airplanes having S/Ns 1004 through 1085 inclusive: Bombardier Alert Service Bulletin A600-0763, Revision 02, dated December 9, 2014, including Appendixes 1 and 2, dated September 26, 2013. (ii) For Model CL-600-2A12 (CL-601) airplanes having S/Ns 3001 through 3066 inclusive, and Model CL-600-2B16 (CL-601-3A and CL-601- 3R Variants) airplanes having S/Ns 5001 through 5194 inclusive: Bombardier Alert Service Bulletin A601-0627, Revision 02, dated December 9, 2014, including Appendixes 1 and 2, dated September 26, 2013. (i) Retained Inspection for Airplanes Previously Inspected and Found To Have Incorrectly Oriented Fastener(s), With No Changes This paragraph restates the requirements of paragraph (i) of AD 2015-02-23, with no changes. For airplanes on which an inspection required by paragraph (g) or (j) of AD 2014-03-17, has been done as of the effective date of this AD, and on which any incorrectly oriented fastener was found but no fasteners were fractured (fasteners found intact): Except as provided by paragraph (l) of this AD, within 10 flight cycles after February 18, 2015 (the effective date of AD 2015-02-23), or within 100 flight cycles after accomplishing the most recent inspection required by AD 2014-03-17, whichever occurs first, do a detailed visual inspection for any fractured or missing fastener heads of each inboard flap fastener of the hinge-box forward fitting at WS 76.50 and WS 127.25, on both wings. Do the inspection in accordance with the Accomplishment Instructions of the applicable service information specified in paragraphs (i)(1) and (i)(2) of this AD. Accomplishing the inspection required by this paragraph terminates the requirements of paragraphs (g) and (j) of AD 2014-03-17 for the inspected airplane only. (1) For Model CL-600-1A11 (CL-600) airplanes having S/Ns 1004 through 1085 inclusive: Bombardier Alert Service Bulletin A600-0763, Revision 02, dated December 9, 2014, including Appendixes 1 and 2, dated September 26, 2013. (2) For Model CL-600-2A12 (CL-601) airplanes having S/Ns 3001 through 3066 inclusive, and Model CL-600-2B16 (CL-601-3A and CL-601- 3R Variants) airplanes having S/Ns 5001 through 5194 inclusive: Bombardier Alert Service Bulletin A601-0627, Revision 02, dated December 9, 2014, including Appendixes 1 and 2, dated September 26, 2013. (j) Retained Corrective Actions for Paragraph (i) of This AD, With Revised Reference to Additional, New Requirements (1) This paragraph restates the requirements of paragraph (j)(1) of AD 2015-02-23, with revised reference to additional, new requirements. If, during any inspection required by paragraph (i) of this AD, no fasteners are found fractured or have missing fastener heads (fasteners are intact), repeat the inspection required by paragraph (i) of this AD thereafter at intervals not to exceed 10 flight cycles until the replacement specified in paragraph (j)(2), (k), or (n) of this AD is accomplished. (2) This paragraph restates the requirements of paragraph (j)(2) of AD 2015-02-23, with no changes. If, during any inspection required by paragraph (i) of this AD, any fastener is found fractured or has a missing fastener head: Before further flight, remove and replace all forward and aft fasteners (regardless of orientation or condition) at WS 76.50 and WS 127.25, on both wings, in accordance with the Accomplishment Instructions of the applicable service information specified in paragraphs (j)(2)(i) and (j)(2)(ii) of this AD, except as required by paragraph (m) of this AD. After accomplishing the replacements required by this paragraph, no further action is required by this AD. (i) For Model CL-600-1A11 (CL-600) airplanes having S/Ns 1004 through 1085 inclusive: Bombardier Alert Service Bulletin A600-0763, Revision 02, dated December 9, 2014, including Appendixes 1 and 2, dated September 26, 2013. (ii) For Model CL-600-2A12 (CL-601) airplanes having S/Ns 3001 through 3066 inclusive, and Model CL-600-2B16 (CL-601-3A and CL-601- 3R Variants) airplanes having S/Ns 5001 through 5194 inclusive: Bombardier Alert Service Bulletin A601-0627, Revision 02, dated December 9, 2014, including Appendixes 1 and 2, dated September 26, 2013. (k) Retained Optional Terminating Action for Incorrectly Oriented Fasteners, With No Changes This paragraph restates the provisions of paragraph (k) of AD 2015-02-23, with no changes. Replacement of all forward and aft fasteners (regardless of orientation or condition) at WS 76.50 and WS 127.25, on both wings, terminates the requirements of this AD. The replacement must be done in accordance with the Accomplishment Instructions of the applicable service information specified in paragraphs (k)(1) and (k)(2) of this AD, except as provided by paragraph (m) of this AD. Doing the replacements specified in this paragraph terminates the requirements of paragraphs (g) and (j) of AD 2014-03-17, only for the airplane on which the replacement was done. (1) For Model CL-600-1A11 (CL-600) airplanes having S/Ns 1004 through 1085 inclusive: Bombardier Alert Service Bulletin A600-0763, Revision 02, dated December 9, 2014, including Appendixes 1 and 2, dated September 26, 2013. (2) For Model CL-600-2A12 (CL-601) airplanes having S/Ns 3001 through 3066 inclusive, and Model CL-600-2B16 (CL-601-3A and CL-601- 3R Variants) airplanes having S/Ns 5001 through 5194 inclusive: Bombardier Alert Service Bulletin A601-0627, Revision 02, dated December 9, 2014, including Appendixes 1 and 2, dated September 26, 2013. (l) Retained Exception for Previously Replaced Fasteners, With No Changes This paragraph restates the provisions of paragraph (l) of AD 2015-02-23, with no changes. Replacement of all fractured and incorrectly oriented forward and aft fasteners, as specified in paragraph (i) or (k) of AD 2014-03-17, if done before the effective date of this AD, is considered acceptable for compliance with the requirements of this AD. (m) Retained Exception to the Service Information, With No Changes This paragraph restates the requirements of paragraph (m) of AD 2015-02-23, with no changes. Where Bombardier Alert Service Bulletin A600-0763, Revision 02, dated December 9, 2014, including Appendixes 1 and 2, dated September 26, 2013; and Bombardier Alert Service Bulletin A601-0627, Revision 02, dated December 9, 2014, including Appendixes 1 and 2, dated September 26, 2013; specify to contact Bombardier for repair instructions, before further flight, repair using a method approved by the Manager, New York Aircraft Certification Office (ACO), FAA; or Transport Canada Civil Aviation (TCCA); or Bombardier's TCCA Design Approval Organization (DAO). [[Page 79384]] (n) New Requirement of This AD: Terminating Action For airplanes on which any incorrectly oriented fastener, and no fractured or missing fastener, was detected during any inspection required by paragraph (g), (h)(2), (i), and (j)(1) of this AD: Within 24 months after the effective date of this AD, replace all forward and aft fasteners, regardless of condition or orientation, at WS 76.50 and WS 127.25, on affected wings, in accordance with the Accomplishment Instructions of the applicable service information specified in paragraphs (k)(1) and (k)(2) of this AD, except as provided by paragraph (m) of this AD. Doing the replacements specified in this paragraph terminates the requirements of this AD. Doing the replacements specified in this paragraph terminates the requirements of paragraphs (g) and (j) of AD 2014-03-17, only for the airplane on which the replacement was done. (o) Credit for Previous Actions This paragraph restates the provisions of paragraph (n) of AD 2015-02-23, with new credit for paragraph (n) of this AD. This paragraph provides credit for actions required by paragraphs (g), (h), (i), and (n) of this AD, if those actions were performed before the effective date of this AD using the applicable service information identified in paragraphs (o)(1) through (o)(4) of this AD. (1) Bombardier Alert Service Bulletin A600-0763, including Appendixes 1 and 2, dated September 26, 2013, which was previously incorporated by reference on March 6, 2014 (79 FR 9389, February 19, 2014). (2) Bombardier Alert Service Bulletin A600-0763, Revision 01, dated February 26, 2014, including Appendixes 1 and 2, dated September 26, 2013, which is not incorporated by reference in this AD. (3) Bombardier Alert Service Bulletin A601-0627, including Appendixes 1 and 2, dated September 26, 2013, which was previously incorporated by reference on March 6, 2014 (79 FR 9389, February 19, 2014). (4) Bombardier Alert Service Bulletin A601-0627, Revision 01, dated February 26, 2014, including Appendixes 1 and 2, dated September 26, 2013, which is not incorporated by reference in this AD. (p) Other FAA AD Provisions The following provisions also apply to this AD: (1) Alternative Methods of Compliance (AMOCs): The Manager, New York 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. 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. (2) Contacting the Manufacturer: 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, FAA; or TCCA; or Bombardier, Inc.'s TCCA DAO. If approved by the DAO, the approval must include the DAO-authorized signature. (q) Related Information (1) Refer to Mandatory Continuing Airworthiness Information (MCAI) Canadian Emergency AD CF-2013-39R2, dated December 12, 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-2016-5593. (2) Service information identified in this AD that is not incorporated by reference is available at the addresses specified in paragraphs (r)(4) and (r)(5) of this AD. (r) 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 February 18, 2015 (80 FR 5670, February 3, 2015). (i) Bombardier Alert Service Bulletin A600-0763, Revision 02, dated December 9, 2014, including Appendixes 1 and 2, dated September 26, 2013. (ii) Bombardier Alert Service Bulletin A601-0627, Revision 02, dated December 9, 2014, including Appendixes 1 and 2, dated September 26, 2013. (4) For service information identified in this AD, contact Bombardier, Inc., 400 C[ocirc]te-Vertu Road West, Dorval, Qu[eacute]bec H4S 1Y9, Canada; Widebody Customer Response Center North America toll-free telephone: 1-866-538-1247 or direct-dial telephone: 1-514-855-2999; fax 514-855-7401; email: [email protected]; Internet: http://www.bombardier.com. (5) 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. (6) 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 October 7, 2016. Michael Kaszycki, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 2016-25009 Filed 11-10-16; 8:45 am] BILLING CODE 4910-13-P
![79381
Rules and Regulations Federal Register
Vol. 81, No. 219
Monday, November 14, 2016
This section of the FEDERAL REGISTER West, Dorval, Québec H4S 1Y9, Canada; Airworthiness Information, or ‘‘the
contains regulatory documents having general Widebody Customer Response Center MCAI’’). The MCAI was issued by
applicability and legal effect, most of which North America toll-free telephone: 1– Transport Canada Civil Aviation
are keyed to and codified in the Code of 866–538–1247 or direct-dial telephone: (TCCA), which is the aviation authority
Federal Regulations, which is published under 1–514–855–2999; fax 514–855–7401;
50 titles pursuant to 44 U.S.C. 1510. for Canada.
email: ac.yul@aero.bombardier.com; The preamble to AD 2015–02–23
The Code of Federal Regulations is sold by Internet: http://www.bombardier.com.
explained that we considered the
the Superintendent of Documents. Prices of You may view this referenced service
requirements interim action and were
new books are listed in the first FEDERAL information at the FAA, Transport
REGISTER issue of each week. considering further rulemaking. We
Airplane Directorate, 1601 Lind Avenue
SW., Renton, WA. For information on have now determined that further
the availability of this material at the rulemaking is indeed necessary and
DEPARTMENT OF TRANSPORTATION FAA, call 425–227–1221. It is also that, instead of continuing repetitive
available on the Internet at http:// inspections, for airplanes which have
Federal Aviation Administration www.regulations.gov by searching for any incorrectly oriented fastener, and no
and locating Docket No. FAA–2016– fractured or missing fastener,
14 CFR Part 39 5593. replacement of all forward and aft
[Docket No. FAA–2016–5593; Directorate fasteners, regardless of condition or
Identifier 2015–NM–184–AD; Amendment
Examining the AD Docket orientation, is necessary. This AD
39–18687; AD 2016–21–06] You may examine the AD docket on follows from that determination.
RIN 2120–AA64
the Internet at http:// The NPRM published in the Federal
www.regulations.gov by searching for Register on April 20, 2016 (81 FR
Airworthiness Directives; Bombardier, and locating Docket No. FAA–2016– 23202). The NPRM was prompted by
Inc. Airplanes 5593; or in person at the Docket reports of incorrectly oriented fasteners.
Management Facility between 9 a.m. The NPRM proposed to continue to
AGENCY: Federal Aviation and 5 p.m., Monday through Friday,
Administration (FAA), Department of require repetitive inspections for
except Federal holidays. The AD docket fractured or incorrectly oriented
Transportation (DOT). contains this AD, the regulatory fasteners on the inboard flap hinge-box
ACTION: Final rule. evaluation, any comments received, and forward fittings on both wings, and
other information. The address for the
SUMMARY: We are superseding replacement of all fasteners if necessary.
Docket Office (telephone: 800–647–
Airworthiness Directive (AD) 2015–02– The NPRM also proposed to require
5527) is Docket Management Facility,
23, for certain Bombardier, Inc. Model replacement of the fasteners, which
U.S. Department of Transportation,
CL–600–1A11 (CL–600), CL–600–2A12 would terminate the requirements of
Docket Operations, M–30, West
(CL–601), and CL–600–2B16 (CL–601– this AD. We are issuing this AD to
Building Ground Floor, Room W12–140,
3A and CL–601–3R Variants) airplanes. 1200 New Jersey Avenue SE., prevent incorrectly oriented or fractured
AD 2015–02–23 required repetitive Washington, DC 20590. fasteners, which could result in
inspections for fractured or incorrectly detachment of the flap hinge-box and
FOR FURTHER INFORMATION CONTACT: Aziz
oriented fasteners on the inboard flap the flap surface, and consequent
Ahmed, Aerospace Engineer, Airframe
hinge-box forward fittings on both reduced controllability of the airplane.
and Mechanical Systems Branch, ANE–
wings, and replacement of all fasteners 171, FAA, New York Aircraft Comments
if necessary. This new AD also requires Certification Office (ACO), 1600 Stewart
replacement of the fasteners, which Avenue, Suite 410, Westbury, NY We gave the public the opportunity to
terminates the requirements of this AD. 11590; telephone: 516–228–7329; fax: participate in developing this AD. We
This AD was prompted by reports of 516–794–5531. received no comments on the NPRM or
incorrectly oriented fasteners. We are on the determination of the cost to the
SUPPLEMENTARY INFORMATION:
issuing this AD to prevent incorrectly public.
oriented or fractured fasteners, which Discussion
could result in detachment of the flap Conclusion
We issued a notice of proposed
hinge-box and the flap surface, and rulemaking (NPRM) to amend 14 CFR
consequent reduced controllability of We reviewed the available data and
part 39 to supersede AD 2015–02–23, determined that air safety and the
the airplane. Amendment 39–18092 (80 FR 5670, public interest require adopting this AD
DATES: This AD is effective December February 3, 2015) (‘‘AD 2015–02–23’’). as proposed except for minor editorial
19, 2016. AD 2015–02–23 applied to certain changes. We have determined that these
The Director of the Federal Register Bombardier, Inc. Model CL–600–1A11 minor changes:
approved the incorporation by reference (CL–600), CL–600–2A12 (CL–601), and
• Are consistent with the intent that
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of certain publications listed in this AD CL–600–2B16 (CL–601–3A and CL–
as of February 18, 2015 (80 FR 5670, 601–3R Variants) airplanes. AD 2015– was proposed in the NPRM for
February 3, 2015). 02–23 corresponded to Canadian correcting the unsafe condition; and
ADDRESSES: For service information Emergency AD CF–2013–39R2, dated • Do not add any additional burden
identified in this final rule, contact December 12, 2014 (referred to after this upon the public than was already
Bombardier, Inc., 400 Côte-Vertu Road as the Mandatory Continuing proposed in the NPRM.
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![79382 Federal Register / Vol. 81, No. 219 / Monday, November 14, 2016 / Rules and Regulations
Related Service Information Under 1 We are issuing this rulemaking under (a) Effective Date
CFR Part 51 the authority described in ‘‘Subtitle VII, This AD is effective December 19, 2016.
Bombardier has issued Alert Service Part A, Subpart III, Section 44701:
(b) Affected ADs
Bulletins A600–0763, Revision 02, General requirements.’’ Under that
section, Congress charges the FAA with This AD replaces AD 2015–02–23,
dated December 9, 2014, including Amendment 39–18092 (80 FR 5670, February
Appendixes 1 and 2, dated September promoting safe flight of civil aircraft in 3, 2015) (‘‘AD 2015–02–23’’). This AD affects
26, 2013; and A601–0627, Revision 02, air commerce by prescribing regulations AD 2014–03–17, Amendment 39–17754 (79
dated December 9, 2014, including for practices, methods, and procedures FR 9389, February 19, 2014) (‘‘AD 2014–03–
Appendixes 1 and 2, dated September the Administrator finds necessary for 17’’).
26, 2013. The service information safety in air commerce. This regulation (c) Applicability
describes procedures for repetitive is within the scope of that authority
because it addresses an unsafe condition This AD applies to the Bombardier, Inc.
inspections of the fasteners on the airplanes identified in paragraphs (c)(1),
inboard flap hinge-box forward fittings that is likely to exist or develop on (c)(2), and (c)(3) of this AD, certificated in
on both wings, and replacement of products identified in this rulemaking any category.
fasteners. These documents are distinct action. (1) Bombardier, Inc. Model CL–600–1A11
since they apply to different airplane (CL–600) airplanes, having serial numbers (S/
Regulatory Findings Ns) 1004 through 1085 inclusive.
models. This service information is (2) Bombardier, Inc. Model CL–600–2A12
We determined that this AD will not
reasonably available because the (CL–601) airplanes, having S/Ns 3001
have federalism implications under
interested parties have access to it through 3066 inclusive.
Executive Order 13132. This AD will
through their normal course of business (3) Bombardier, Inc. Model CL–600–2B16
not have a substantial direct effect on
or by the means identified in the (CL–601–3A and CL–601–3R Variants)
the States, on the relationship between airplanes, having S/Ns 5001 through 5194
ADDRESSES section.
the national government and the States, inclusive.
Costs of Compliance or on the distribution of power and
(d) Subject
We estimate that this AD affects 120 responsibilities among the various
levels of government. Air Transport Association (ATA) of
airplanes of U.S. registry. America Code 57, Wings.
The actions required by AD 2015–02– For the reasons discussed above, I
23, and retained in this AD, take about certify that this AD: (e) Reason
1 work-hour per product, at an average 1. Is not a ‘‘significant regulatory This AD was prompted by reports of
labor rate of $85 per work-hour. Based action’’ under Executive Order 12866; incorrectly oriented fasteners. We are issuing
on these figures, the estimated cost of 2. Is not a ‘‘significant rule’’ under the this AD to prevent incorrectly oriented or
DOT Regulatory Policies and Procedures fractured fasteners, which could result in
the actions that are required by AD
(44 FR 11034, February 26, 1979); detachment of the flap hinge-box and the flap
2015–02–23 is $85 per product. surface, and consequent reduced
We also estimate that it would take 3. Will not affect intrastate aviation in controllability of the airplane.
about 59 work-hours per product to Alaska; and
comply with the basic requirements of 4. Will not have a significant (f) Compliance
this AD. The average labor rate is $85 economic impact, positive or negative, Comply with this AD within the
per work-hour. We have received no on a substantial number of small entities compliance times specified, unless already
under the criteria of the Regulatory done.
definitive data that would enable us to
provide cost estimates for the parts cost. Flexibility Act. (g) Retained Inspection on Airplanes Not
Based on these figures, we estimate the Previously Inspected, With No Changes
List of Subjects in 14 CFR Part 39
cost of this AD on U.S. operators to be This paragraph restates the requirements of
$601,800, or $5,015 per product. Air transportation, Aircraft, Aviation paragraph (g) of AD 2015–02–23, with no
In addition, we estimate that any safety, Incorporation by reference, changes. For airplanes that have not been
necessary follow-on actions will take Safety. inspected as required by paragraph (g) of AD
about 58 work-hours and require parts 2014–03–17, as of February 18, 2015 (the
Adoption of the Amendment effective date of AD 2015–02–23): Within 10
costing $753, for a cost of $5,683 per flight cycles after February 18, 2015, or 100
product. We have no way of Accordingly, under the authority
flight cycles after March 6, 2014 (the effective
determining the number of aircraft that delegated to me by the Administrator, date of AD 2014–03–17), whichever occurs
might need this action. the FAA amends 14 CFR part 39 as first, do a detailed visual inspection for
According to the manufacturer, some follows: incorrect orientation and any fractured or
of the costs of this AD may be covered missing fastener heads of each inboard flap
under warranty, thereby reducing the PART 39—AIRWORTHINESS fastener of the hinge-box forward fitting at
cost impact on affected individuals. We DIRECTIVES wing station (WS) 76.50 and WS 127.25, on
both wings, in accordance with the
do not control warranty coverage for
■ 1. The authority citation for part 39 Accomplishment Instructions of the
affected individuals. As a result, we applicable service information specified in
continues to read as follows:
have included all available costs in our paragraphs (g)(1) and (g)(2) of this AD.
cost estimate. Authority: 49 U.S.C. 106(g), 40113, 44701. Accomplishing the inspection required by
§ 39.13 [Amended] this paragraph terminates the requirements of
Authority for This Rulemaking paragraph (g) of AD 2014–03–17 for the
Title 49 of the United States Code ■ 2. The FAA amends § 39.13 by inspected airplane only.
specifies the FAA’s authority to issue removing Airworthiness Directive (AD) (1) For Model CL–600–1A11 (CL–600)
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rules on aviation safety. Subtitle I, 2015–02–23, Amendment 39–18092 (80 airplanes having S/Ns 1004 through 1085
FR 5670, February 3, 2015), and adding inclusive: Bombardier Alert Service Bulletin
section 106, describes the authority of A600–0763, Revision 02, dated December 9,
the FAA Administrator. ‘‘Subtitle VII: the following new AD: 2014, including Appendixes 1 and 2, dated
Aviation Programs,’’ describes in more 2016–21–06 Bombardier, Inc.: Amendment September 26, 2013.
detail the scope of the Agency’s 39–18687; Docket No. FAA–2016–5593; (2) For Model CL–600–2A12 (CL–601)
authority. Directorate Identifier 2015–NM–184–AD. airplanes having S/Ns 3001 through 3066
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![79384 Federal Register / Vol. 81, No. 219 / Monday, November 14, 2016 / Rules and Regulations
(n) New Requirement of This AD: flight standards district office/certificate DEPARTMENT OF TRANSPORTATION
Terminating Action holding district office.
For airplanes on which any incorrectly (2) Contacting the Manufacturer: For any Federal Aviation Administration
oriented fastener, and no fractured or missing requirement in this AD to obtain corrective
fastener, was detected during any inspection actions from a manufacturer, the action must 14 CFR Part 39
required by paragraph (g), (h)(2), (i), and (j)(1) be accomplished using a method approved
of this AD: Within 24 months after the by the Manager, New York ACO, ANE–170, [Docket No. FAA–2015–7527; Directorate
effective date of this AD, replace all forward FAA; or TCCA; or Bombardier, Inc.’s TCCA Identifier 2015–NM–094–AD; Amendment
and aft fasteners, regardless of condition or DAO. If approved by the DAO, the approval 39–18686; AD 2016–21–05]
orientation, at WS 76.50 and WS 127.25, on must include the DAO-authorized signature.
RIN 2120–AA64
affected wings, in accordance with the (q) Related Information
Accomplishment Instructions of the Airworthiness Directives; The Boeing
applicable service information specified in (1) Refer to Mandatory Continuing
paragraphs (k)(1) and (k)(2) of this AD, except Airworthiness Information (MCAI) Canadian Company Airplanes
as provided by paragraph (m) of this AD. Emergency AD CF–2013–39R2, dated
AGENCY: Federal Aviation
Doing the replacements specified in this December 12, 2014, for related information.
This MCAI may be found in the AD docket Administration (FAA), DOT.
paragraph terminates the requirements of this
AD. Doing the replacements specified in this on the Internet at http://www.regulations.gov ACTION: Final rule.
paragraph terminates the requirements of by searching for and locating Docket No.
paragraphs (g) and (j) of AD 2014–03–17, FAA–2016–5593. SUMMARY: We are adopting a new
only for the airplane on which the (2) Service information identified in this airworthiness directive (AD) for certain
replacement was done. AD that is not incorporated by reference is The Boeing Company Model 777–200,
(o) Credit for Previous Actions
available at the addresses specified in –200LR, –300, and –300ER series
paragraphs (r)(4) and (r)(5) of this AD. airplanes. This AD was prompted by a
This paragraph restates the provisions of report indicating that the manufacturer
paragraph (n) of AD 2015–02–23, with new (r) Material Incorporated by Reference
credit for paragraph (n) of this AD. This
discovered locations where the control
(1) The Director of the Federal Register
paragraph provides credit for actions approved the incorporation by reference components and wiring of the left and
required by paragraphs (g), (h), (i), and (n) of (IBR) of the service information listed in this right engine fuel spar valves do not have
this AD, if those actions were performed paragraph under 5 U.S.C. 552(a) and 1 CFR adequate physical separation to meet
before the effective date of this AD using the part 51. the redundant system separation
applicable service information identified in (2) You must use this service information requirements. This AD requires
paragraphs (o)(1) through (o)(4) of this AD. as applicable to do the actions required by modifying the wiring, and installing a
(1) Bombardier Alert Service Bulletin this AD, unless this AD specifies otherwise. new relay bracket and new location for
A600–0763, including Appendixes 1 and 2, (3) The following service information was
dated September 26, 2013, which was
the relay on the left and right engine
approved for IBR on February 18, 2015 (80 fuel spar valves. This AD also requires
previously incorporated by reference on FR 5670, February 3, 2015).
March 6, 2014 (79 FR 9389, February 19, an inspection to identify the part
(i) Bombardier Alert Service Bulletin
2014). A600–0763, Revision 02, dated December 9, number of the motor operated valve
(2) Bombardier Alert Service Bulletin 2014, including Appendixes 1 and 2, dated (MOV) actuators for the left and right
A600–0763, Revision 01, dated February 26, September 26, 2013. engine fuel spar valves; replacement of
2014, including Appendixes 1 and 2, dated (ii) Bombardier Alert Service Bulletin specified MOV actuators with new MOV
September 26, 2013, which is not A601–0627, Revision 02, dated December 9, actuators; certain bonding resistance
incorporated by reference in this AD. 2014, including Appendixes 1 and 2, dated measurements; and applicable
(3) Bombardier Alert Service Bulletin September 26, 2013.
A601–0627, including Appendixes 1 and 2,
corrective actions. We are issuing this
(4) For service information identified in AD to prevent loss of control of both the
dated September 26, 2013, which was this AD, contact Bombardier, Inc., 400 Côte-
previously incorporated by reference on left and right engine fuel spar valves
Vertu Road West, Dorval, Québec H4S 1Y9,
March 6, 2014 (79 FR 9389, February 19, during a single event, such as local wire
Canada; Widebody Customer Response
2014). Center North America toll-free telephone: 1– bundle damage or a wire bundle fire,
(4) Bombardier Alert Service Bulletin 866–538–1247 or direct-dial telephone: 1– which could cause both engines to shut
A601–0627, Revision 01, dated February 26, 514–855–2999; fax 514–855–7401; email: down or result in the inability to control
2014, including Appendixes 1 and 2, dated ac.yul@aero.bombardier.com; Internet: an engine fire.
September 26, 2013, which is not http://www.bombardier.com.
incorporated by reference in this AD. DATES: This AD is effective December
(5) You may view this service information 19, 2016.
(p) Other FAA AD Provisions at the FAA, Transport Airplane Directorate, The Director of the Federal Register
1601 Lind Avenue SW., Renton, WA. For
The following provisions also apply to this approved the incorporation by reference
AD: information on the availability of this
material at the FAA, call 425–227–1221.
of certain publications listed in this AD
(1) Alternative Methods of Compliance as of December 19, 2016.
(AMOCs): The Manager, New York ACO, (6) You may view this service information
that is incorporated by reference at the ADDRESSES: For service information
ANE–170, FAA, has the authority to approve
AMOCs for this AD, if requested using the National Archives and Records identified in this final rule, contact
procedures found in 14 CFR 39.19. In Administration (NARA). For information on Boeing Commercial Airplanes,
accordance with 14 CFR 39.19, send your the availability of this material at NARA, call Attention: Data & Services Management,
request to your principal inspector or local 202–741–6030, or go to: http:// P.O. Box 3707, MC 2H–65, Seattle, WA
Flight Standards District Office, as www.archives.gov/federal-register/cfr/ibr-
98124–2207; telephone 206–544–5000,
appropriate. If sending information directly locations.html.
extension 1; fax 206–766–5680; Internet
to the ACO, send it to ATTN: Program Issued in Renton, Washington, on October https://www.myboeingfleet.com. You
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Manager, Continuing Operational Safety, 7, 2016. may view this referenced service
FAA, New York ACO, 1600 Stewart Avenue, Michael Kaszycki,
Suite 410, Westbury, NY 11590; telephone: information at the FAA, Transport
Acting Manager, Transport Airplane Airplane Directorate, 1601 Lind Avenue
516–228–7300; fax: 516–794–5531. Before
Directorate, Aircraft Certification Service. SW., Renton, WA. For information on
using any approved AMOC, notify your
appropriate principal inspector, or lacking a [FR Doc. 2016–25009 Filed 11–10–16; 8:45 am] the availability of this material at the
principal inspector, the manager of the local BILLING CODE 4910–13–P FAA, call 425–227–1221. It is also
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Document Created: 2018-10-24 10:47:29
Document Modified: 2018-10-24 10:47:29
| 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 December 19, 2016. | |
| Contact | Aziz Ahmed, Aerospace Engineer, Airframe and Mechanical Systems Branch, ANE-171, 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 79381 | |
| RIN Number | 2120-AA64 | |
| CFR Associated | Air Transportation; Aircraft; Aviation Safety; Incorporation by Reference and Safety |
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