81 FR 23202 - Airworthiness Directives; Bombardier, Inc. Airplanes
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration Federal Register Volume 81, Issue 76 (April 20, 2016)
Federal Aviation Administration
Federal Register Volume 81, Issue 76 (April 20, 2016)
| Page Range | 23202-23206 | |
| FR Document | 2016-08960 |
[Federal Register Volume 81, Number 76 (Wednesday, April 20, 2016)] [Proposed Rules] [Pages 23202-23206] From the Federal Register Online [www.thefederalregister.org] [FR Doc No: 2016-08960] ----------------------------------------------------------------------- DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA-2016-5593; Directorate Identifier 2015-NM-184-AD] RIN 2120-AA64 Airworthiness Directives; Bombardier, Inc. Airplanes AGENCY: Federal Aviation Administration (FAA), DOT. ACTION: Notice of proposed rulemaking (NPRM). ----------------------------------------------------------------------- SUMMARY: We propose to supersede 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 currently requires 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 preamble to AD 2015-02-23 explains that we consider the requirements interim action and are considering further rulemaking. We now have determined that further rulemaking is indeed necessary, and that replacement of the fasteners is necessary. This proposed AD would require terminating action to replace the fasteners on the inboard flap hinge-box forward fittings on both wings. We are proposing this AD to detect and correct 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: We must receive comments on this proposed AD by June 6, 2016. ADDRESSES: You may send comments by any of the following methods:Federal eRulemaking Portal: Go to http://www.regulations.gov. Follow the instructions for submitting comments. Fax: 202-493-2251. Mail: U.S. Department of Transportation, Docket Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New Jersey Avenue SE., Washington, DC 20590. Hand Delivery: U.S. Department of Transportation, Docket Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New Jersey Avenue SE., Washington, DC, between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. For service information identified in this NPRM, 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. 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 proposed AD, the regulatory evaluation, any comments received, and other information. The street address for the Docket Operations office (telephone 800-647-5527) is in the ADDRESSES section. Comments will be available in the AD docket shortly after receipt. FOR FURTHER INFORMATION CONTACT: Aziz Ahmed, Aerospace Engineer, Airframe and Mechanical Systems Branch, ANE-171, FAA, New York Aircraft Certification Office, 1600 Stewart Avenue, Suite 410, Westbury, NY 11590; telephone 516-228-7329; fax 516-794-5531. SUPPLEMENTARY INFORMATION: [[Page 23203]] Comments Invited We invite you to send any written relevant data, views, or arguments about this proposed AD. Send your comments to an address listed under the ADDRESSES section. Include ``Docket No. FAA-2016-5593; Directorate Identifier 2015-NM-184-AD'' at the beginning of your comments. We specifically invite comments on the overall regulatory, economic, environmental, and energy aspects of this proposed AD. We will consider all comments received by the closing date and may amend this proposed AD based on those comments. We will post all comments we receive, without change, to http://www.regulations.gov, including any personal information you provide. We will also post a report summarizing each substantive verbal contact we receive about this proposed AD. Discussion On January 20, 2015, we issued AD 2015-02-23, Amendment 39-18092 (80 FR 5670, February 3, 2015) (``AD 2015-02-23''). AD 2015-02-23 requires actions intended to address an unsafe condition on 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 corresponds to Canadian Emergency Airworthiness Directive 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 explains that we consider the requirements interim action and are considering further rulemaking. We have now determined that further rulemaking is indeed necessary and that, instead of continuing repetitive inspections, replacement of the incorrectly oriented fasteners is necessary. This proposed AD follows from that determination. This proposed AD would require terminating action to replace the fasteners on the inboard flap hinge-box forward fittings on affected wings. The repetitive inspections can only detect if a fastener head has fractured and sheared off. For incorrectly oriented fasteners, it is not possible to detect whether a crack has already initiated and propagated. The fastener fracture speed is unpredictable due to the variability in the quality of the hole preparation prior to fastener installation and whether there was any misalignment in the installation of the fasteners. The failure of two fasteners could result in the loss of the flap attachment, causing flap asymmetry and consequent reduced controllability of the airplane. We are proposing this AD to detect and correct 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. Related Service Information Under 1 CFR Part 51 Bombardier has issued Alert Service Bulletins A600-0763, Revision 02, dated December 9, 2014, including Appendices 1 and 2, dated September 26, 2013; and A601-0627, Revision 02, dated December 9, 2014, including Appendices 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. 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. FAA's Determination and Requirements of This Proposed AD This product has been approved by the aviation authority of another country, and is approved for operation in the United States. Pursuant to our bilateral agreement with the State of Design Authority, we have been notified of the unsafe condition described in the MCAI and service information referenced above. We are proposing this AD because we evaluated all pertinent information and determined an unsafe condition exists and is likely to exist or develop on other products of the same type designs. Clarification of Intent of the MCAI Paragraph C. of Canadian Emergency AD CF-2013-39R2, dated December 12, 2014, specifies to do the replacement on ``both'' wings. We have clarified with TCCA that the intent of paragraph C. of Canadian Emergency AD CF-2013-39R2, dated December 12, 2014, is that for airplanes on which any incorrectly oriented fastener, and no fractured or missing fastener, was detected, 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. The replacement of all forward and aft fasteners, regardless of condition or orientation, at wing station (WS) 76.50 and WS 127.25, on the affected wings, constitutes terminating action. Fasteners that have cracks or fractures were already addressed by the requirements of AD 2015-02-13, which is restated in this proposed AD. Costs of Compliance We estimate that this proposed AD affects 120 airplanes of U.S. registry. The actions required by AD 2015-02-23, and retained in this proposed 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 proposed 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 proposed 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 proposed 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. [[Page 23204]] Regulatory Findings We determined that this proposed AD would not have federalism implications under Executive Order 13132. This proposed AD would not have a substantial direct effect on the States, on the relationship between the national Government and the States, or on the distribution of power and responsibilities among the various levels of government. For the reasons discussed above, I certify this proposed regulation: 1. Is not a ``significant regulatory action'' under Executive Order 12866; 2. Is not a ``significant rule'' under the DOT Regulatory Policies and Procedures (44 FR 11034, February 26, 1979); 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. The Proposed Amendment Accordingly, under the authority delegated to me by the Administrator, the FAA proposes to amend 14 CFR part 39 as follows: PART 39--AIRWORTHINESS DIRECTIVES 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: Bombardier, Inc.: Docket No. FAA-2016-5593; Directorate Identifier 2015-NM-184-AD. (a) Comments Due Date We must receive comments by June 6, 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 detect and correct 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 Appendices 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 Appendices 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 paragraph (h)(3), (k), or (n) of this AD is 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 Appendices 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 Appendices 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 [[Page 23205]] 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 Appendices 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 Appendices 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 Appendices 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 Appendices 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 Appendices 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 Appendices 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 Appendices 1 and 2, dated September 26, 2013; and Bombardier Alert Service Bulletin A601-0627, Revision 02, dated December 9, 2014, including Appendices 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). (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 Appendices 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 Appendices 1 and 2, dated September 26, 2013, which is not incorporated by reference in this AD. (3) Bombardier Alert Service Bulletin A601-0627, including Appendices 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 Appendices 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. The AMOC approval letter must specifically reference this AD. (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, Engine and Propeller Directorate, 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 Airworthiness Directive CF-2013-39R2, dated December 12, 2014, for related information. This MCAI may be [[Page 23206]] found in the AD docket on the Internet at http://www.regulations.gov by searching for and locating Docket No. FAA-2016-5593. (2) 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. 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. Issued in Renton, Washington, on April 8, 2016. Michael Kaszycki, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 2016-08960 Filed 4-19-16; 8:45 am] BILLING CODE 4910-13-P
![23202 Federal Register / Vol. 81, No. 76 / Wednesday, April 20, 2016 / Proposed Rules
(2) Replace the current electrical cable with the DOA, the approval must include the hinge-box forward fittings on both
the new standard one in accordance with the DOA-authorized signature. wings. We are proposing this AD to
Accomplishment Instructions of Airbus detect and correct incorrectly oriented
(l) Related Information
Service Bulletin A320–92–1052, dated or fractured fasteners, which could
December 5, 2007. During the replacement, (1) Refer to Mandatory Continuing
Airworthiness Information (MCAI) EASA result in detachment of the flap hinge-
ensure that the anti-chafing protection
specified in Airbus Service Bulletin A320– Airworthiness Directive 2014–0198, dated box and the flap surface, and
92–1049, as required by paragraph (h)(1) of September 5, 2014, for related information. consequent reduced controllability of
this AD, remains in place. This MCAI may be found in the AD docket the airplane.
on the Internet at http://www.regulations.gov DATES: We must receive comments on
(i) Additional Modification by searching for and locating Docket No.
FAA–2016–5591.
this proposed AD by June 6, 2016.
For airplanes on which the installation
(2) For service information identified in ADDRESSES: You may send comments by
specified in Airbus Service Bulletin A320–
24–1062, Revision 05, dated June 27, 2002, this AD, contact Airbus, Airworthiness any of the following methods:
has been done: Within 60 months after the Office—EIAS, 1 Rond Point Maurice • Federal eRulemaking Portal: Go to
effective date of this AD, install insulators Bellonte, 31707 Blagnac Cedex, France; http://www.regulations.gov. Follow the
and cable ties, in accordance with telephone +33 5 61 93 36 96; fax +33 5 61 instructions for submitting comments.
‘‘Modification—Additional Work (Introduced 93 44 51; email account.airworth-eas@ • Fax: 202–493–2251.
at Revision No. 06)’’ of the Accomplishment airbus.com; Internet http://www.airbus.com. • Mail: U.S. Department of
Instructions of Airbus Service Bulletin A320– You may view this service information at the
FAA, Transport Airplane Directorate, 1601
Transportation, Docket Operations, M–
24–1062, Revision 07, dated November 28, 30, West Building Ground Floor, Room
2011. Lind Avenue SW., Renton, WA. For
information on the availability of this W12–140, 1200 New Jersey Avenue SE.,
(j) Credit for Previous Actions material at the FAA, call 425–227–1221. Washington, DC 20590.
(1) This paragraph provides credit for • Hand Delivery: U.S. Department of
Issued in Renton, Washington, on April 4,
actions required by paragraphs (g) and (i) of 2016. Transportation, Docket Operations, M–
this AD, if those actions were performed Jeffrey E. Duven,
30, West Building Ground Floor, Room
before the effective date of this AD using W12–140, 1200 New Jersey Avenue SE.,
Airbus Service Bulletin A320–24–1062, Manager, Transport Airplane Directorate,
Aircraft Certification Service.
Washington, DC, between 9 a.m. and 5
Revision 06, dated June 26, 2007, which is p.m., Monday through Friday, except
not incorporated by reference in this AD. [FR Doc. 2016–08953 Filed 4–19–16; 8:45 am]
Federal holidays.
(2) This paragraph provides credit for BILLING CODE 4910–13–P
For service information identified in
actions required by paragraph (h) of this AD,
if those actions were performed before the
this NPRM, contact Bombardier, Inc.,
effective date of this AD using Airbus Service 400 Côte-Vertu Road West, Dorval,
DEPARTMENT OF TRANSPORTATION
Bulletin A320–92–1049, dated July 23, 2007, Québec H4S 1Y9, Canada; telephone
which is not incorporated by reference in this Federal Aviation Administration 514–855–5000; fax 514–855–7401; email
AD. thd.crj@aero.bombardier.com; Internet
(k) Other FAA AD Provisions 14 CFR Part 39 http://www.bombardier.com. You may
view this referenced service information
The following provisions also apply to this [Docket No. FAA–2016–5593; Directorate at the FAA, Transport Airplane
AD: Identifier 2015–NM–184–AD]
(1) Alternative Methods of Compliance
Directorate, 1601 Lind Avenue SW.,
(AMOCs): The Manager, International RIN 2120–AA64 Renton, WA. For information on the
Branch, ANM–116, Transport Airplane availability of this material at the FAA,
Directorate, FAA, has the authority to Airworthiness Directives; Bombardier, call 425–227–1221.
approve AMOCs for this AD, if requested Inc. Airplanes
using the procedures found in 14 CFR 39.19.
Examining the AD Docket
AGENCY: Federal Aviation
In accordance with 14 CFR 39.19, send your You may examine the AD docket on
request to your principal inspector or local Administration (FAA), DOT.
the Internet at http://
Flight Standards District Office, as ACTION: Notice of proposed rulemaking www.regulations.gov by searching for
appropriate. If sending information directly (NPRM). and locating Docket No. FAA–2016–
to the International Branch, send it to ATTN:
SUMMARY: We propose to supersede 5593; or in person at the Docket
Sanjay Ralhan, Aerospace Engineer,
International Branch, ANM–116, Transport Airworthiness Directive (AD) 2015–02– Management Facility between 9 a.m.
Airplane Directorate, FAA, 1601 Lind 23, for certain Bombardier, Inc. Model and 5 p.m., Monday through Friday,
Avenue SW., Renton, WA 98057–3356; CL–600–1A11 (CL–600), CL–600–2A12 except Federal holidays. The AD docket
telephone 425–227–1405; fax 425–227–1149. (CL–601), and CL–600–2B16 (CL–601– contains this proposed AD, the
Information may be emailed to: 9-ANM-116- 3A, and CL–601–3R Variants) airplanes. regulatory evaluation, any comments
AMOC-REQUESTS@faa.gov. Before using received, and other information. The
AD 2015–02–23 currently requires
any approved AMOC, notify your appropriate street address for the Docket Operations
principal inspector, or lacking a principal repetitive inspections for fractured or
incorrectly oriented fasteners on the office (telephone 800–647–5527) is in
inspector, the manager of the local flight
inboard flap hinge-box forward fittings the ADDRESSES section. Comments will
standards district office/certificate holding
district office. The AMOC approval letter on both wings, and replacement of all be available in the AD docket shortly
must specifically reference this AD. fasteners if necessary. The preamble to after receipt.
(2) Contacting the Manufacturer: As of the AD 2015–02–23 explains that we FOR FURTHER INFORMATION CONTACT: Aziz
Ahmed, Aerospace Engineer, Airframe
Lhorne on DSK5TPTVN1PROD with PROPOSALS
effective date of this AD, for any requirement consider the requirements interim
in this AD to obtain corrective actions from action and are considering further and Mechanical Systems Branch, ANE–
a manufacturer, the action must be 171, FAA, New York Aircraft
rulemaking. We now have determined
accomplished using a method approved by Certification Office, 1600 Stewart
the Manager, International Branch, ANM– that further rulemaking is indeed
116, Transport Airplane Directorate, FAA; or necessary, and that replacement of the Avenue, Suite 410, Westbury, NY
the European Aviation Safety Agency fasteners is necessary. This proposed 11590; telephone 516–228–7329; fax
(EASA); or Airbus’s EASA Design AD would require terminating action to 516–794–5531.
Organization Approval (DOA). If approved by replace the fasteners on the inboard flap SUPPLEMENTARY INFORMATION:
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![23204 Federal Register / Vol. 81, No. 76 / Wednesday, April 20, 2016 / Proposed Rules
Regulatory Findings (1) Bombardier, Inc. Model CL–600–1A11 and not fractured, and no fastener heads are
(CL–600) airplanes, having serial numbers (S/ missing (fasteners found intact): No further
We determined that this proposed AD Ns) 1004 through 1085 inclusive. action is required by this AD.
would not have federalism implications (2) Bombardier, Inc. Model CL–600–2A12 (2) This paragraph restates the
under Executive Order 13132. This (CL–601) airplanes, having S/Ns 3001 requirements of paragraph (h)(2) of AD 2015–
proposed AD would not have a through 3066 inclusive. 02–23, with revised references to
substantial direct effect on the States, on (3) Bombardier, Inc. Model CL–600–2B16 replacement paragraphs. If, during any
the relationship between the national (CL–601–3A and CL–601–3R Variants) inspection required by paragraph (g) of this
Government and the States, or on the airplanes, having S/Ns 5001 through 5194 AD, any fastener is found incorrectly
inclusive. oriented but no fasteners are fractured or are
distribution of power and missing a fastener head (fasteners found
responsibilities among the various (d) Subject intact), repeat the inspection required by
levels of government. Air Transport Association (ATA) of paragraph (g) of this AD thereafter at
For the reasons discussed above, I America Code 57, Wings. intervals not to exceed 10 flight cycles until
certify this proposed regulation: the replacements specified in paragraph
(e) Reason
1. Is not a ‘‘significant regulatory (h)(3), (k), or (n) of this AD is accomplished.
action’’ under Executive Order 12866; This AD was prompted by reports of (3) This paragraph restates the
2. Is not a ‘‘significant rule’’ under the incorrectly oriented fasteners. We are issuing requirements of paragraph (h)(3) of AD 2015–
DOT Regulatory Policies and Procedures this AD to detect and correct incorrectly 02–23, with no changes. If, during any
oriented or fractured fasteners, which could inspection required by paragraph (g) of this
(44 FR 11034, February 26, 1979); result in detachment of the flap hinge-box
3. Will not affect intrastate aviation in AD, any fastener is found fractured or has a
and the flap surface, and consequent reduced missing fastener head: Before further flight,
Alaska; and controllability of the airplane. remove and replace all forward and aft
4. Will not have a significant
(f) Compliance fasteners (regardless of orientation or
economic impact, positive or negative, condition) at WS 76.50 and WS 127.25, on
on a substantial number of small entities Comply with this AD within the
both wings, in accordance with the
under the criteria of the Regulatory compliance times specified, unless already
Accomplishment Instructions of the
Flexibility Act. done.
applicable service information specified in
(g) Retained Inspection on Airplanes Not paragraphs (h)(3)(i) and (h)(3)(ii) of this AD,
List of Subjects in 14 CFR Part 39 except as required by paragraph (m) of this
Previously Inspected, With No Changes
Air transportation, Aircraft, Aviation This paragraph restates the requirements of AD. After accomplishing the replacements
safety, Incorporation by reference, paragraph (g) of AD 2015–02–23, with no required by this paragraph, no further action
Safety. changes. For airplanes that have not been is required by this AD.
inspected as required by paragraph (g) of AD (i) For Model CL–600–1A11 (CL–600)
The Proposed Amendment 2014–03–17, as of February 18, 2015 (the airplanes having S/Ns 1004 through 1085
Accordingly, under the authority effective date of AD 2015–02–23): Within 10 inclusive: Bombardier Alert Service Bulletin
flight cycles after February 18, 2015, or 100 A600–0763, Revision 02, dated December 9,
delegated to me by the Administrator, 2014, including Appendices 1 and 2, dated
the FAA proposes to amend 14 CFR part flight cycles after March 6, 2014 (the effective
date of AD 2014–03–17), whichever occurs September 26, 2013.
39 as follows: (ii) For Model CL–600–2A12 (CL–601)
first, do a detailed visual inspection for
incorrect orientation and any fractured or airplanes having S/Ns 3001 through 3066
PART 39—AIRWORTHINESS inclusive, and Model CL–600–2B16 (CL–
missing fastener heads of each inboard flap
DIRECTIVES fastener of the hinge-box forward fitting at 601–3A and CL–601–3R Variants) airplanes
wing station (WS) 76.50 and WS 127.25, on having S/Ns 5001 through 5194 inclusive:
■ 1. The authority citation for part 39 both wings, in accordance with the Bombardier Alert Service Bulletin A601–
continues to read as follows: Accomplishment Instructions of the 0627, Revision 02, dated December 9, 2014,
Authority: 49 U.S.C. 106(g), 40113, 44701. applicable service information specified in including Appendices 1 and 2, dated
paragraphs (g)(1) and (g)(2) of this AD. September 26, 2013.
§ 39.13 [Amended] Accomplishing the inspection required by (i) Retained Inspection for Airplanes
■ 2. The FAA amends § 39.13 by this paragraph terminates the requirements of Previously Inspected and Found To Have
removing Airworthiness Directive (AD) paragraph (g) of AD 2014–03–17 for the Incorrectly Oriented Fastener(s), With No
2015–02–23, Amendment 39–18092 (80 inspected airplane only. Changes
(1) For Model CL–600–1A11 (CL–600)
FR 5670, February 3, 2015), and adding airplanes having S/Ns 1004 through 1085 This paragraph restates the requirements of
the following new AD: inclusive: Bombardier Alert Service Bulletin paragraph (i) of AD 2015–02–23, with no
Bombardier, Inc.: Docket No. FAA–2016– A600–0763, Revision 02, dated December 9, changes. For airplanes on which an
5593; Directorate Identifier 2015–NM– 2014, including Appendices 1 and 2, dated inspection required by paragraph (g) or (j) of
184–AD. September 26, 2013. AD 2014–03–17, has been done as of the
(2) For Model CL–600–2A12 (CL–601) effective date of this AD, and on which any
(a) Comments Due Date airplanes having S/Ns 3001 through 3066 incorrectly oriented fastener was found but
We must receive comments by June 6, inclusive, and Model CL–600–2B16 (CL– no fasteners were fractured (fasteners found
2016. 601–3A and CL–601–3R Variants) airplanes intact): Except as provided by paragraph (l)
having S/Ns 5001 through 5194 inclusive: of this AD, within 10 flight cycles after
(b) Affected ADs Bombardier Alert Service Bulletin A601– February 18, 2015 (the effective date of AD
This AD replaces AD 2015–02–23, 0627, Revision 02, dated December 9, 2014, 2015–02–23), or within 100 flight cycles after
Amendment 39–18092 (80 FR 5670, February including Appendices 1 and 2, dated accomplishing the most recent inspection
3, 2015) (‘‘AD 2015–02–23’’). This AD affects September 26, 2013. required by AD 2014–03–17, whichever
occurs first, do a detailed visual inspection
Lhorne on DSK5TPTVN1PROD with PROPOSALS
AD 2014–03–17, Amendment 39–17754 (79
(h) Retained Corrective Actions for for any fractured or missing fastener heads of
FR 9389, February 19, 2014) (‘‘AD 2014–03–
Paragraph (g) of This AD, With Revised each inboard flap fastener of the hinge-box
17’’).
Paragraph (h)(2) of This AD forward fitting at WS 76.50 and WS 127.25,
(c) Applicability (1) This paragraph restates the on both wings. Do the inspection in
This AD applies to the Bombardier, Inc. requirements of paragraph (h)(1) of AD 2015– accordance with the Accomplishment
airplanes identified in paragraphs (c)(1), 02–23, with no changes. If, during any Instructions of the applicable service
(c)(2), and (c)(3) of this AD, certificated in inspection required by paragraph (g) of this information specified in paragraphs (i)(1) and
any category. AD, all fasteners are found correctly oriented (i)(2) of this AD. Accomplishing the
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![23206 Federal Register / Vol. 81, No. 76 / Wednesday, April 20, 2016 / Proposed Rules
found in the AD docket on the Internet at • Fax: 202–493–2251. www.regulations.gov, including any
http://www.regulations.gov by searching for • Mail: U.S. Department of personal information you provide. We
and locating Docket No. FAA–2016–5593. Transportation, Docket Operations, M– will also post a report summarizing each
(2) For service information identified in 30, West Building Ground Floor, Room
this AD, contact Bombardier, Inc., 400 Côte-
substantive verbal contact we receive
Vertu Road West, Dorval, Québec H4S 1Y9,
W12–140, 1200 New Jersey Avenue SE., about this proposed AD.
Canada; telephone 514–855–5000; fax 514– Washington, DC 20590.
• Hand Delivery: U.S. Department of Discussion
855–7401; email thd.crj@
aero.bombardier.com; Internet http:// Transportation, Docket Operations, M– On April 20, 2011, we issued AD
www.bombardier.com. You may view this 30, West Building Ground Floor, Room
2011–10–01, Amendment 39–16682 (76
service information at the FAA, Transport W12–140, 1200 New Jersey Avenue SE.,
Airplane Directorate, 1601 Lind Avenue SW., FR 25535, May 5, 2011). AD 2011–10–
Washington, DC, between 9 a.m. and 5
Renton, WA. For information on the 01 requires actions intended to address
p.m., Monday through Friday, except
availability of this material at the FAA, call an unsafe condition on all Dassault
Federal holidays.
425–227–1221.
For service information identified in Aviation Model FALCON 7X airplanes.
Issued in Renton, Washington, on April 8, this NPRM, contact Dassault Falcon Jet Since we issued AD 2011–10–01, we
2016. Corporation, Teterboro Airport, P.O. received a revision of an ALI document,
Michael Kaszycki, Box 2000, South Hackensack, NJ 07606; Chapter 5–40–00, Airworthiness
Acting Manager, Transport Airplane telephone: 201–440–6700; Internet: Limitations, DGT 107838, Revision 4,
Directorate, Aircraft Certification Service. http://www.dassaultfalcon.com. You dated February 2, 2015, of the Dassault
[FR Doc. 2016–08960 Filed 4–19–16; 8:45 am] may view this referenced service Falcon 7X Maintenance Manual, which
BILLING CODE 4910–13–P information at the FAA, Transport introduces new and more restrictive
Airplane Directorate, 1601 Lind Avenue maintenance requirements and
SW., Renton, WA. For information on airworthiness limitations.
DEPARTMENT OF TRANSPORTATION the availability of this material at the The European Aviation Safety Agency
FAA, call 425–227–1221. (EASA), which is the Technical Agent
Federal Aviation Administration for the Member States of the European
Examining the AD Docket
Union, has issued EASA Airworthiness
14 CFR Part 39 You may examine the AD docket on Directive AD 2015–0095, dated May 29,
[Docket No. FAA–2016–5464; Directorate the Internet at http:// 2015 (referred to after this as the
Identifier 2015–NM–097–AD] www.regulations.gov by searching for Mandatory Continuing Airworthiness
and locating Docket No. FAA–2016– Information, or ‘‘the MCAI’’), to correct
RIN 2120–AA64 5464; or in person at the Docket an unsafe condition for all Dassault
Management Facility between 9 a.m. Aviation FALCON 7X airplanes. The
Airworthiness Directives; Dassault
and 5 p.m., Monday through Friday, MCAI states:
Aviation Airplanes
except Federal holidays. The AD docket
AGENCY: Federal Aviation contains this proposed AD, the The airworthiness limitations and
maintenance requirements for the FALCON
Administration (FAA), DOT. regulatory evaluation, any comments
7X type design are included in Dassault
ACTION: Notice of proposed rulemaking received, and other information. The Aviation FALCON 7X Aircraft Maintenance
(NPRM). street address for the Docket Operations Manual (AMM) chapter 5–40 and are
office (telephone 800–647–5527) is in approved by EASA. To ensure
SUMMARY: We propose to supersede the ADDRESSES section. Comments will accomplishment of the maintenance tasks,
Airworthiness Directive (AD) 2011–10– be available in the AD docket shortly and implementation of the airworthiness
01, for all Dassault Aviation Model after receipt. limitations, as specified in Dassault Aviation
FALCON 7X airplanes. AD 2011–10–01 FOR FURTHER INFORMATION CONTACT: Tom FALCON 7X AMM chapter 5–40 original
currently requires repetitive functional Rodriguez, Aerospace Engineer, issue, including temporary revision (TR) TR–
tests of the ram air turbine (RAT) heater International Branch, ANM–116, 01, EASA issued AD 2008–0221 [http://
and repair if necessary. Since we issued ad.easa.europa.eu/ad/2008-0221].
Transport Airplane Directorate, FAA,
AD 2011–10–01, we received a revision Since that [EASA] AD was issued, Dassault
1601 Lind Avenue SW., Renton, WA Aviation issued revision 4 of the FALCON 7X
of an airworthiness limitations items 98057–3356; telephone 425–227–1137;
(ALI) document, which introduces new AMM chapter 5–40, which introduces new
fax 425–227–1149. and more restrictive maintenance
and more restrictive maintenance SUPPLEMENTARY INFORMATION: requirements and/or airworthiness
requirements and airworthiness limitations.
limitations for airplane structures and Comments Invited Dassault Aviation AMM chapter 5–40
systems. This proposed AD would We invite you to send any written revision 4 contains, among others, the
require revising the maintenance or relevant data, views, or arguments about following changes:
inspection program to incorporate new this proposed AD. Send your comments —Fatigue and Damage tolerance
maintenance requirements and to an address listed under the airworthiness limitations,
airworthiness limitations. We are ADDRESSES section. Include ‘‘Docket No. —Miscellaneous Certification Maintenance
proposing this AD to prevent reduced FAA–2016–5464; Directorate Identifier Requirements and Airworthiness
structural integrity and reduced control 2015–NM–097–AD’’ at the beginning of Limitation Items,
of these airplanes due to the failure of your comments. We specifically invite —Periodic restoration of the DC generators
system components. (this action was required by EASA AD
Lhorne on DSK5TPTVN1PROD with PROPOSALS
comments on the overall regulatory,
DATES: We must receive comments on
2009–0254) [http://ad.easa.europa.eu/ad/
economic, environmental, and energy 2009-0254],
this proposed AD by June 6, 2016. aspects of this proposed AD. We will —Functional test of the Ram Air Turbine
ADDRESSES: You may send comments by consider all comments received by the heater (this action was required by EASA
any of the following methods: closing date and may amend this AD 2010–0033) [http://ad.easa.europa.eu/
• Federal eRulemaking Portal: Go to proposed AD based on those comments. ad/2010-0233] [which corresponds to FAA
http://www.regulations.gov. Follow the We will post all comments we AD 2011–10–01, Amendment 39–16682
instructions for submitting comments. receive, without change, to http:// (76 FR 25535, May 5, 2011)],
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Document Created: 2016-04-20 01:52:02
Document Modified: 2016-04-20 01:52:02
| 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 | Proposed Rules | |
| Action | Notice of proposed rulemaking (NPRM). | |
| Dates | We must receive comments on this proposed AD by June 6, 2016. | |
| Contact | Aziz Ahmed, Aerospace Engineer, Airframe and Mechanical Systems Branch, ANE-171, FAA, New York Aircraft Certification Office, 1600 Stewart Avenue, Suite 410, Westbury, NY 11590; telephone 516-228-7329; fax 516-794-5531. | |
| FR Citation | 81 FR 23202 | |
| RIN Number | 2120-AA64 | |
| CFR Associated | Air Transportation; Aircraft; Aviation Safety; Incorporation by Reference and Safety |
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