80 FR 63141 - Airworthiness Directives; Bombardier, Inc. Airplanes
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration Federal Register Volume 80, Issue 201 (October 19, 2015)
Federal Aviation Administration
Federal Register Volume 80, Issue 201 (October 19, 2015)
| Page Range | 63141-63145 | |
| FR Document | 2015-26222 |
[Federal Register Volume 80, Number 201 (Monday, October 19, 2015)] [Proposed Rules] [Pages 63141-63145] From the Federal Register Online [www.thefederalregister.org] [FR Doc No: 2015-26222] ----------------------------------------------------------------------- DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA-2015-3988; Directorate Identifier 2015-NM-005-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) 2014-17- 51, for certain Bombardier, Inc. Model CL-600-2B16 airplanes. AD 2014- 17-51 currently requires inspecting the inboard flap fasteners of the hinge-box forward fitting at Wing Station (WS) 76.50 and WS 127.25 to determine the orientation and condition of the fasteners, as applicable, and replacement or repetitive inspections of the fasteners if necessary. AD 2014-17-51 also provides for optional terminating action for the requirements of that AD. Since we issued AD 2014-17-51, we have determined that additional action is necessary. This proposed AD would also require accomplishment of the previously optional terminating action. We are proposing this AD to detect and correct incorrectly oriented or fractured fasteners, which could result in premature failure of the fasteners attaching the inboard flap hinge-box forward fitting; failure of the fasteners could lead to the detachment of the flap hinge box and the flap surface, and consequent loss of control of the airplane. DATES: We must receive comments on this proposed AD by December 3, 2015. 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. [[Page 63142]] For service information identified in this proposed 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 thd.crj@aero.bombardier.com; 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-2015- 3988; or in person at the Docket Management Facility between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. The AD docket contains this 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, Propulsion and Services Branch, ANE-173, FAA, New York Aircraft Certification Office (ACO), 1600 Stewart Avenue, Suite 410, Westbury, NY 11590; telephone 516-228-7329; fax 516-794-5531. SUPPLEMENTARY INFORMATION: 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-2015-3988; Directorate Identifier 2015-NM-005-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 October 13, 2014, we issued AD 2014-17-51, Amendment 39-17999 (79 FR 64088, October 28, 2014). AD 2014-17-51 requires actions intended to address an unsafe condition on certain Bombardier, Inc. Model CL-600-2B16 airplanes. The preamble to AD 2014-17-51, Amendment 39-17999 (79 FR 64088, October 28, 2014), explains that we consider the requirements ``interim action'' and were considering further rulemaking. We now have determined that further rulemaking is indeed necessary, and this proposed AD follows from that determination. Transport Canada Civil Aviation (TCCA), which is the aviation authority for Canada, has issued Canadian Airworthiness Directive CF- 2014-27R1, dated August 29, 2014 (referred to after this as the Mandatory Continuing Airworthiness Information, or ``the MCAI''), to correct an unsafe condition for certain Bombardier, Inc. Model CL-600- 2B16 airplanes. The MCAI states: There have been three in-service reports on 604 Variant aeroplanes of a fractured fastener head on the inboard flap hinge- box forward fitting at Wing Station (WS) 76.50, found during a routine maintenance inspection. Investigation revealed that the installation of these fasteners on the inboard flap hinge-box forward fittings at WS 76.50 and WS 127.25, on both wings, does not conform to the engineering drawings. Incorrect installation may result in premature failure of the fasteners attaching the inboard flap hinge-box forward fitting. Failure of the fasteners could lead to the detachment of the flap hinge box and consequently the detachment of the flap surface. The loss of a flap surface could adversely affect the continued safe operation of the aeroplane. The original issue of [Canadian] AD CF-2013-39 [http://www.regulations.gov/#!documentDetail;D=FAA-2014-0054-0002] [which corresponds to FAA AD 2014-03-17, Amendment 39-17754 (79 FR 9389, February 19, 2014)] mandated a detailed visual inspection (DVI) of each inboard flap hinge-box forward fitting, on both wings, and rectification as required. Incorrectly oriented fasteners require repetitive inspections until the terminating action is accomplished. After the issuance of [Canadian] AD CF-2013-39, there has been one reported incident on a 604 Variant aeroplane where four fasteners were found fractured on the same flap hinge-box forward fitting. The investigation determined that the fasteners were incorrectly installed. The original issue of this [Canadian] AD was issued to reduce the initial and repetitive inspection intervals previously mandated in [Canadian] AD CF-2013-39, and to impose replacement of the incorrectly oriented fasteners within 24 months. The CL-600-1A11, - 2A12 and -2B16 (601-3A/-3R Variant) aeroplanes are addressed through [Canadian] AD CF-2013-39R1. Revision 1 of this [Canadian] AD is issued to clarify the requirements for the initial and repetitive inspections. You may examine the MCAI in the AD docket on the Internet at http://www.regulations.gov by searching for and locating Docket No. FAA-2015- 3988. Related Service Information Under 1 CFR Part 51 Bombardier has issued Alert Service Bulletins: A604-57-006, Revision 04, dated November 12, 2014, including Appendices 1 and 2, dated September 26, 2013, A605-57-004, Revision 04, dated November 12, 2014, including Appendices 1 and 2, dated September 26, 2013, and The service information describes detailed visual inspection of each inboard flap fastener of the hinge-box forward fitting at WS 76.50 and WS 127.25, on both wings, and, if necessary, replacement of the fasteners. This service information is reasonably available because the interested parties have access to it through their normal course of business or by the means identified in the ADDRESSES section of this NPRM. FAA's Determination and Requirements of This Proposed AD This product has been approved by the aviation authority of another country, and is approved for operation in the United States. Pursuant to our bilateral agreement with the State of Design Authority, we have been notified of the unsafe condition described in the MCAI and service information referenced above. We are proposing this AD because we evaluated all pertinent information and determined an unsafe condition exists and is likely to exist or develop on other products of the same type design. Costs of Compliance We estimate that this proposed AD affects 285 airplanes of U.S. registry. The actions required by AD 2014-17-51, Amendment 39-17999 (79 FR 64088, October 28, 2014), and retained in this proposed AD take about 1 work-hour per product, at an average labor rate of $85 per work-hour. Required parts cost about $0 per product. Based on these figures, the estimated cost of the actions that are required by AD 2014-17-51 is $85 per product. We also estimate that it would take about 58 work-hours per product to comply with the basic requirements of this proposed AD. The average labor rate is $85 per work-hour. Required parts would cost about $753 per product. Based on these figures, we estimate the cost of this proposed AD on U.S. operators to be $1,619,655, or $5,683 per product. [[Page 63143]] In addition, we estimate that any necessary follow-on actions would 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 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 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) 2014-17-51, Amendment 39-17999 (79 FR 64088, October 28, 2014), and adding the following new AD: Bombardier, Inc.: Docket No. FAA-2015-3988; Directorate Identifier 2015-NM-005-AD. (a) Comments Due Date We must receive comments by December 3, 2015. (b) Affected ADs (1) This AD replaces AD 2014-17-51, Amendment 39-17999 (79 FR 64088, October 28, 2014). (2) This AD affects AD 2014-03-17, Amendment 39-17754 (79 FR 9389, February 19, 2014), only for the airplanes identified in paragraph (c) of this AD. (c) Applicability This AD applies to Bombardier, Inc. Model CL-600-2B16 airplanes, certificated in any category, serial numbers 5301 through 5665 inclusive, and 5701 through 5920 inclusive. (d) Subject Air Transport Association (ATA) of America Code 57, Wings. (e) Reason This AD was prompted by reports of fractured fastener heads on the inboard flap hinge-box forward fitting at Wing Station (WS) 76.50 due to incorrect installation. We are issuing this AD to detect and correct incorrectly oriented or fractured fasteners, which could result in premature failure of the fasteners attaching the inboard flap hinge-box forward fitting; failure of the fasteners could lead to the detachment of the flap hinge box and the flap surface, and consequent loss of control of the airplane. (f) Compliance Comply with this AD within the compliance times specified, unless already done. (g) Retained Inspection, With New Service Information: Airplanes Not Previously Inspected This paragraph restates the requirements of paragraph (g) of AD 2014-17-51, Amendment 39-17999 (79 FR 64088, October 28, 2014), with new service information. For airplanes on which the actions required by AD 2014-03-17, Amendment 39-17754 (79 FR 9389, February 19, 2014), have not been done as of November 12, 2014 (the effective date of AD 2014-17-51): Within 10 flight cycles after November 12, 2014, or within 100 flight cycles after March 6, 2014 (the effective date of AD 2014-03-17, Amendment 39-17754 (79 FR 9389, February 19, 2014)), whichever occurs first, do a detailed visual inspection of each inboard flap fastener of the hinge-box forward fitting at WS 76.50 and WS 127.25, on both wings, to determine if the fasteners are correctly oriented and intact (non-fractured, with intact fastener head). Do the inspection in accordance with the Accomplishment Instructions of Bombardier Alert Service Bulletin A604-57-006, Revision 01, dated September 26, 2013, including Appendices 1 and 2, dated September 26, 2013, Revision 02, dated January 22, 2014, including Appendices 1 and 2, dated September 26, 2013, or Revision 04, dated November 12, 2014, including Appendices 1 and 2, dated September 26, 2013 (for serial numbers 5301 through 5665 inclusive); or Bombardier Alert Service Bulletin A605-57-004, Revision 01, dated September 26, 2013, including Appendices 1 and 2, dated September 26, 2013, Revision 02, dated January 22, 2014, including Appendices 1 and 2, dated September 26, 2013, or Revision 04, dated November 12, 2014, including Appendices 1 and 2, dated September 26, 2013 (for serial numbers 5701 through 5920 inclusive). As of the effective date of this AD, only use Bombardier Alert Service Bulletin A604-57-006, Revision 04, dated November 12, 2014, including Appendices 1 and 2, dated September 26, 2013; or Bombardier Alert Service Bulletin A605-57-004, Revision 04, dated November 12, 2014, including Appendices 1 and 2, dated September 26, 2013; as applicable; for the actions required by this paragraph. (1) If all fasteners are found intact and correctly oriented, no further action is required by this AD. (2) If any fastener is found fractured: Before further flight, remove and replace all forward and aft fasteners at WS 76.50 and WS 127.25, regardless of condition or orientation, on both wings, in accordance with the Accomplishment Instructions of the applicable service information identified in paragraph (g) of this AD. As of the effective date of this AD, only use Bombardier Alert Service Bulletin A604-57-006, Revision 04, dated November 12, 2014, including Appendices 1 and 2, dated September 26, 2013; or Bombardier Alert Service Bulletin A605-57-004, Revision 04, dated November 12, 2014, including Appendices 1 and 2, dated September 26, 2013; as applicable; for the actions required by this paragraph. After replacement of all fasteners as required by this paragraph of this AD, no further action is required by this AD. [[Page 63144]] (3) If any incorrectly oriented but intact fastener is found, and no fractured fastener is found, repeat the inspection required by paragraph (g) of this AD thereafter at intervals not to exceed 10 flight cycles, until the requirements of paragraph (i)(1) or (k) of this AD have been done. (h) Retained Actions, With New Service Information: Airplanes Previously Inspected, Having Incorrectly Oriented Fastener(s) This paragraph restates the requirements of paragraph (h) of AD 2014-17-51, Amendment 39-17999 (79 FR 64088, October 28, 2014), with new service information. For airplanes on which an inspection required by paragraph (g) or (j) of AD 2014-03-17, Amendment 39- 17754 (79 FR 9389, February 19, 2014), has been done as of November 12, 2014 (the effective date of AD 2014-17-51), and on which any incorrectly oriented fastener, but no fractured fastener, was found: Except as provided by paragraph (i)(3) of this AD, do a detailed visual inspection of all inboard flap fasteners of the hinge-box forward fitting at WS 76.50 and WS 127.25, on both wings, to determine if the fasteners are intact (non-fractured, with intact fastener head). Inspect within 10 flight cycles after November 12, 2014, or within 100 flight cycles after the most recent inspection done as required by AD 2014-03-17, whichever occurs first. Inspect in accordance with the Accomplishment Instructions of the applicable service information identified in paragraph (g) of this AD. As of the effective date of this AD, only use Bombardier Alert Service Bulletin A604-57-006, Revision 04, dated November 12, 2014, including Appendices 1 and 2, dated September 26, 2013; or Bombardier Alert Service Bulletin A605-57-004, Revision 04, dated November 12, 2014, including Appendices 1 and 2, dated September 26, 2013; as applicable; for the actions required by this paragraph. (1) If all fasteners are found intact, repeat the inspection thereafter at intervals not to exceed 10 flight cycles, until the requirements of paragraph (i)(1) or (k) of this AD have been done. (2) If any fastener is found fractured: Before further flight, remove and replace all forward and aft fasteners at WS 76.50 and WS 127.25, regardless of condition or orientation, on both wings, in accordance with the Accomplishment Instructions of the applicable service information identified in paragraph (g) of this AD. As of the effective date of this AD, only use Bombardier Alert Service Bulletin A604-57-006, Revision 04, dated November 12, 2014, including Appendices 1 and 2, dated September 26, 2013; or Bombardier Alert Service Bulletin A605-57-004, Revision 04, dated November 12, 2014, including Appendices 1 and 2, dated September 26, 2013; as applicable; for the actions required by this paragraph. After replacement of all fasteners as required by this paragraph, no further action is required by this AD. (i) Retained Terminating Action, With New Service Information This paragraph restates the terminating action specified in paragraph (i) of AD 2014-17-51, Amendment 39-17999 (79 FR 64088, October 28, 2014), with new service information. (1) Replacement of all forward and aft fasteners at WS 76.50 and WS 127.25, on both wings, in accordance with the Accomplishment Instructions of the applicable service information identified in paragraph (g) of this AD, terminates the requirements of this AD. As of the effective date of this AD, only use Bombardier Alert Service Bulletin A604-57-006, Revision 04, dated November 12, 2014, including Appendices 1 and 2, dated September 26, 2013; or Bombardier Alert Service Bulletin A605-57-004, Revision 04, dated November 12, 2014, including Appendices 1 and 2, dated September 26, 2013; as applicable; for the actions specified in this paragraph. (2) Accomplishment of the applicable requirements of this AD constitutes terminating action for the requirements of AD 2014-03- 17, Amendment 39-17754 (79 FR 9389, February 19, 2014), for that airplane only. (3) Replacement of all fractured and incorrectly oriented fasteners before November 12, 2014 (the effective date of AD 2014- 17-51, Amendment 39-17999 (79 FR 64088, October 28, 2014)), as provided by paragraph (i) or (k) of AD 2014-03-17, Amendment 39- 17754 (79 FR 9389, February 19, 2014), is acceptable for compliance with the requirements of this AD. (j) Retained Special Flight Permit Prohibition This paragraph restates the requirements of paragraph (j) of AD 2014-17-51, Amendment 39-17999 (79 FR 64088, October 28, 2014). Special flight permits to operate the airplane to a location where the airplane can be repaired in accordance with sections 21.197 and 21.199 of the Federal Aviation Regulations (14 CFR 21.197 and 21.199) are not allowed. (k) New Requirement of This AD: Post-Inspection Fastener Replacement For airplanes on which incorrectly oriented fasteners were found during any inspection required by paragraph (g), (g)(3), (h), or (h)(1) of this AD, but none were found to be fractured: Within 24 months after the effective date of this AD, remove and replace all forward and aft fasteners at WS 76.50 and WS 127.25, regardless of condition or orientation, on both wings, in accordance with the Accomplishment Instructions of Bombardier Alert Service Bulletin A604-57-006, Revision 04, dated November 12, 2014, including Appendices 1 and 2, dated September 26, 2013 (for serial numbers 5301 through 5665 inclusive); or Bombardier Alert Service Bulletin A605-57-004, Revision 04, dated November 12, 2014, including Appendices 1 and 2, dated September 26, 2013 (for serial numbers 5701 through 5920 inclusive). Accomplishing the requirements of this paragraph terminates the requirements of this AD. (l) Credit for Previous Actions (1) This paragraph provides credit for actions required by paragraphs (g), (h), and (i)(1) of this AD, if those actions were performed before the effective date of this AD using the applicable service information identified in paragraphs (l)(1)(i) and (l)(1)(ii) of this AD, which are not incorporated by reference in this AD. (i) Bombardier Alert Service Bulletin A604-57-006, Revision 03, dated August 19, 2014, including Appendices 1 and 2, dated September 26, 2013. (ii) Bombardier Alert Service Bulletin A605-57-004, Revision 03, dated August 19, 2014, including Appendices 1 and 2, dated September 26, 2013. (2) This paragraph provides credit for actions required by paragraph (k) of this AD, if those actions were done before the effective date of this AD using the applicable service information identified in paragraphs (l)(2)(i) through (l)(2)(iv) of this AD. (i) Bombardier Alert Service Bulletin A604-57-006, Revision 01, dated September 26, 2013, including Appendices 1 and 2, dated September 26, 2013, which is incorporated by reference in AD 2014- 03-17, Amendment 39-17754 (79 FR 9389, February 19, 2014). (ii) Bombardier Alert Service Bulletin A604-57-006, Revision 02, dated January 22, 2014, including Appendices 1 and 2, dated September 26, 2013, which is incorporated by reference in AD 2014- 17-51, Amendment 39-17999 (79 FR 64088, October 28, 2014). (iii) Bombardier Alert Service Bulletin A605-57-004, Revision 01, dated September 26, 2013, including Appendices 1 and 2, dated September 26, 2013, which is incorporated by reference in AD 2014- 03-17, Amendment 39-17754 (79 FR 9389, February 19, 2014). (iv) Bombardier Alert Service Bulletin A604-57-004, Revision 02, dated January 22, 2014, including Appendices 1 and 2, dated September 26, 2013, which is incorporated by reference in AD 2014- 17-51, Amendment 39-17999 (79 FR 64088, October 28, 2014). (m) Other FAA AD Provisions The following provisions also apply to this AD: (1) Alternative Methods of Compliance (AMOCs): The Manager, New York Aircraft Certification Office (ACO), ANE-170, FAA, has the authority to approve AMOCs for this AD, if requested using the procedures found in 14 CFR 39.19. In accordance with 14 CFR 39.19, send your request to your principal inspector or local Flight Standards District Office, as appropriate. If sending information directly to the ACO, send it to ATTN: Program Manager, Continuing Operational Safety, FAA, New York ACO, 1600 Stewart Avenue, Suite 410, Westbury, NY 11590; telephone 516-228-7300; fax 516-794-5531. (i) Before using any approved AMOC, notify your appropriate principal inspector, or lacking a principal inspector, the manager of the local flight standards district office/certificate holding district office. The AMOC approval letter must specifically reference this AD. (ii) AMOCs previously approved for AD 2014-17-51, Amendment 39- 17999 (79 FR 64088, October 28, 2014), are acceptable for the corresponding requirements of this AD. (2) Contacting the Manufacturer: As of the effective date of this AD, for any requirement in this AD to obtain corrective actions from [[Page 63145]] a manufacturer, the action must be accomplished using a method approved by the Manager, New York ACO, ANE-170, FAA; or Transport Canada Civil Aviation (TCCA); or Bombardier, Inc.'s TCCA Design Approval Organization (DAO). If approved by the DAO, the approval must include the DAO-authorized signature. (n) Related Information (1) Refer to Mandatory Continuing Airworthiness Information (MCAI) Canadian Emergency Airworthiness Directive CF-2014-27R1, dated August 29, 2014, for related information. This MCAI may be found in the AD docket on the Internet at http://www.regulations.gov by searching for and locating Docket No. FAA-2015-3988. (2) 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 thd.crj@aero.bombardier.com; 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 October 6, 2015. Jeffrey E. Duven, Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 2015-26222 Filed 10-16-15; 8:45 am] BILLING CODE 4910-13-P
![Federal Register / Vol. 80, No. 201 / Monday, October 19, 2015 / Proposed Rules 63141
TABLE 1 TO PARAGRAPH (i) OF THIS the local flight standards district office/ DEPARTMENT OF TRANSPORTATION
AD—REPLACEMENT COMPLIANCE certificate holding district office. The AMOC
approval letter must specifically reference Federal Aviation Administration
TIMES—Continued this AD.
(2) Contacting the Manufacturer: For any 14 CFR Part 39
Year of requirement in this AD to obtain corrective
Compliance time
manufacture actions from a manufacturer, the action must [Docket No. FAA–2015–3988; Directorate
be accomplished using a method approved Identifier 2015–NM–005–AD]
2009 .................. Before exceeding 10 years
by the Manager, International Branch, ANM–
since date of manufac-
116, Transport Airplane Directorate, FAA; or RIN 2120–AA64
ture of the passenger
the European Aviation Safety Agency
chemical oxygen gener-
(EASA); or Airbus’s EASA Design Airworthiness Directives; Bombardier,
ator.
Organization Approval (DOA). If approved by Inc. Airplanes
the DOA, the approval must include the
(j) Definition of Serviceable DOA-authorized signature. AGENCY: Federal Aviation
For the purpose of this AD, a serviceable (3) Reporting Requirements: A federal Administration (FAA), DOT.
unit is a passenger chemical oxygen agency may not conduct or sponsor, and a
ACTION: Notice of proposed rulemaking
generator having P/N 117042–XX with a person is not required to respond to, nor
manufacturing date not older than 10 years, shall a person be subject to a penalty for
(NPRM).
or any other approved part number, provided failure to comply with, a collection of
that the generator has not exceeded the life SUMMARY: We propose to supersede
information subject to the requirements of
limit established for that generator by the the Paperwork Reduction Act unless that
Airworthiness Directive (AD) 2014–17–
manufacturer. collection of information displays a current 51, for certain Bombardier, Inc. Model
valid OMB Control Number. The OMB CL–600–2B16 airplanes. AD 2014–17–
(k) Reporting
Control Number for this information 51 currently requires inspecting the
At the applicable time specified in collection is 2120–0056. Public reporting for inboard flap fasteners of the hinge-box
paragraph (k)(1) or (k)(2) of this AD, submit this collection of information is estimated to forward fitting at Wing Station (WS)
a report of the findings (both positive and be approximately 5 minutes per response, 76.50 and WS 127.25 to determine the
negative) of the inspection required by including the time for reviewing instructions,
paragraph (g) of this AD, in accordance with orientation and condition of the
completing and reviewing the collection of fasteners, as applicable, and
paragraph 7., ‘‘Reporting,’’ of Airbus AOT information. All responses to this collection
A35N006–14, dated December 10, 2014, replacement or repetitive inspections of
of information are mandatory. Comments
including Appendix 01. The report must concerning the accuracy of this burden and
the fasteners if necessary. AD 2014–17–
include the information specified in suggestions for reducing the burden should 51 also provides for optional
Appendix 1 of Airbus AOT A35N006–14, be directed to the FAA at: 800 Independence terminating action for the requirements
dated December 10, 2014. Ave. SW., Washington, DC 20591, Attn: of that AD. Since we issued AD 2014–
(1) If the inspection was done on or after Information Collection Clearance Officer, 17–51, we have determined that
the effective date of this AD: Submit the AES–200. additional action is necessary. This
report within 30 days after the inspection.
(2) If the inspection was done before the (n) Related Information proposed AD would also require
effective date of this AD: Submit the report accomplishment of the previously
(1) Refer to Mandatory Continuing
within 30 days after the effective date of this optional terminating action. We are
Airworthiness Information (MCAI) EASA
AD. Airworthiness Directive EASA AD 2015– proposing this AD to detect and correct
0117, dated June 24, 2015; corrected August incorrectly oriented or fractured
(l) Parts Installation Limitation
7, 2015, for related information. This MCAI fasteners, which could result in
As of the effective date of this AD, no premature failure of the fasteners
may be found in the AD docket on the
person may install a passenger chemical
Internet at http://www.regulations.gov by attaching the inboard flap hinge-box
oxygen generator, unless it is determined,
prior to installation, that the oxygen
searching for and locating Docket No. FAA– forward fitting; failure of the fasteners
2015–3989. could lead to the detachment of the flap
generator is a serviceable unit as specified in
paragraph (j) of this AD. (2) For Airbus service information hinge box and the flap surface, and
identified in this proposed AD, contact consequent loss of control of the
(m) Other FAA AD Provisions Airbus, Airworthiness Office—EIAS, 1 Rond
airplane.
The following provisions also apply to this Point Maurice Bellonte, 31707 Blagnac
AD: Cedex, France; telephone +33 5 61 93 36 96; DATES: We must receive comments on
(1) Alternative Methods of Compliance fax +33 5 61 93 44 51; email this proposed AD by December 3, 2015.
(AMOCs): The Manager, International account.airworth-eas@airbus.com; Internet
ADDRESSES: You may send comments by
Branch, ANM–116, Transport Airplane http://www.airbus.com. For BE service
identified in this proposed AD, contact B/E any of the following methods:
Directorate, FAA, has the authority to • Federal eRulemaking Portal: Go to
approve AMOCs for this AD, if requested Aerospace Inc., 10800 Pflumm Road, Lenexa,
KS 66215; telephone: 913–338–9800; fax: http://www.regulations.gov. Follow the
using the procedures found in 14 CFR 39.19.
In accordance with 14 CFR 39.19, send your 913–469–8419; Internet http:// instructions for submitting comments.
request to your principal inspector or local beaerospace.com/home/globalsupport. You • Fax: 202–493–2251.
Flight Standards District Office, as may view this service information at the • Mail: U.S. Department of
appropriate. If sending information directly FAA, Transport Airplane Directorate, 1601 Transportation, Docket Operations, M–
to the International Branch, send it to ATTN: Lind Avenue SW., Renton, WA. For 30, West Building Ground Floor, Room
asabaliauskas on DSK5VPTVN1PROD with PROPOSALS
Sanjay Ralhan, Aerospace Engineer, information on the availability of this
W12–140, 1200 New Jersey Avenue SE.,
International Branch, ANM–116, Transport material at the FAA, call 425–227–1221.
Washington, DC 20590.
Airplane Directorate, FAA, 1601 Lind Issued in Renton, Washington, on October • Hand Delivery: U.S. Department of
Avenue SW., Renton, WA 98057–3356; 6, 2015. Transportation, Docket Operations, M–
telephone: 425–227–1405; fax: 425–227– Jeffrey E. Duven,
1149. Information may be emailed to: 9- 30, West Building Ground Floor, Room
ANM-116-AMOC-REQUESTS@faa.gov. Manager, Transport Airplane Directorate, W12–140, 1200 New Jersey Avenue SE.,
Before using any approved AMOC, notify Aircraft Certification Service. Washington, DC, between 9 a.m. and 5
your appropriate principal inspector, or [FR Doc. 2015–26220 Filed 10–16–15; 8:45 am] p.m., Monday through Friday, except
lacking a principal inspector, the manager of BILLING CODE 4910–13–P Federal holidays.
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![63142 Federal Register / Vol. 80, No. 201 / Monday, October 19, 2015 / Proposed Rules
For service information identified in Bombardier, Inc. Model CL–600–2B16 and locating Docket No. FAA–2015–
this proposed AD, contact Bombardier, airplanes. 3988.
Inc., 400 Côte-Vertu Road West, Dorval, The preamble to AD 2014–17–51, Related Service Information Under 1
Québec H4S 1Y9, Canada; telephone Amendment 39–17999 (79 FR 64088, CFR Part 51
514–855–5000; fax 514–855–7401; email October 28, 2014), explains that we
thd.crj@aero.bombardier.com; Internet consider the requirements ‘‘interim Bombardier has issued Alert Service
http://www.bombardier.com. You may action’’ and were considering further Bulletins:
view this referenced service information rulemaking. We now have determined • A604–57–006, Revision 04, dated
at the FAA, Transport Airplane that further rulemaking is indeed November 12, 2014, including
Directorate, 1601 Lind Avenue SW., necessary, and this proposed AD Appendices 1 and 2, dated September
Renton, WA. For information on the follows from that determination. 26, 2013,
availability of this material at the FAA, Transport Canada Civil Aviation • A605–57–004, Revision 04, dated
call 425–227–1221. (TCCA), which is the aviation authority November 12, 2014, including
Examining the AD Docket for Canada, has issued Canadian Appendices 1 and 2, dated September
Airworthiness Directive CF–2014–27R1, 26, 2013, and
You may examine the AD docket on
dated August 29, 2014 (referred to after The service information describes
the Internet at http://
this as the Mandatory Continuing detailed visual inspection of each
www.regulations.gov by searching for
Airworthiness Information, or ‘‘the inboard flap fastener of the hinge-box
and locating Docket No. FAA–2015–
MCAI’’), to correct an unsafe condition forward fitting at WS 76.50 and WS
3988; or in person at the Docket
for certain Bombardier, Inc. Model CL– 127.25, on both wings, and, if necessary,
Management Facility between 9 a.m.
600–2B16 airplanes. The MCAI states: replacement of the fasteners. This
and 5 p.m., Monday through Friday,
There have been three in-service reports on service information is reasonably
except Federal holidays. The AD docket
contains this proposed AD, the 604 Variant aeroplanes of a fractured fastener available because the interested parties
regulatory evaluation, any comments head on the inboard flap hinge-box forward have access to it through their normal
received, and other information. The fitting at Wing Station (WS) 76.50, found course of business or by the means
during a routine maintenance inspection. identified in the ADDRESSES section of
street address for the Docket Operations Investigation revealed that the installation of
office (telephone 800–647–5527) is in this NPRM.
these fasteners on the inboard flap hinge-box
the ADDRESSES section. Comments will forward fittings at WS 76.50 and WS 127.25, FAA’s Determination and Requirements
be available in the AD docket shortly on both wings, does not conform to the of This Proposed AD
after receipt. engineering drawings. Incorrect installation
may result in premature failure of the This product has been approved by
FOR FURTHER INFORMATION CONTACT: Aziz
fasteners attaching the inboard flap hinge-box the aviation authority of another
Ahmed, Aerospace Engineer, Propulsion
forward fitting. Failure of the fasteners could country, and is approved for operation
and Services Branch, ANE–173, FAA,
lead to the detachment of the flap hinge box in the United States. Pursuant to our
New York Aircraft Certification Office and consequently the detachment of the flap bilateral agreement with the State of
(ACO), 1600 Stewart Avenue, Suite 410, surface. The loss of a flap surface could Design Authority, we have been notified
Westbury, NY 11590; telephone 516– adversely affect the continued safe operation of the unsafe condition described in the
228–7329; fax 516–794–5531. of the aeroplane. MCAI and service information
SUPPLEMENTARY INFORMATION: The original issue of [Canadian] AD CF–
2013–39 [http://www.regulations.gov/
referenced above. We are proposing this
Comments Invited #!documentDetail;D=FAA-2014-0054-0002] AD because we evaluated all pertinent
We invite you to send any written [which corresponds to FAA AD 2014–03–17, information and determined an unsafe
relevant data, views, or arguments about Amendment 39–17754 (79 FR 9389, February condition exists and is likely to exist or
this proposed AD. Send your comments 19, 2014)] mandated a detailed visual develop on other products of the same
inspection (DVI) of each inboard flap hinge- type design.
to an address listed under the
box forward fitting, on both wings, and
ADDRESSES section. Include ‘‘Docket No. rectification as required. Incorrectly oriented Costs of Compliance
FAA–2015–3988; Directorate Identifier fasteners require repetitive inspections until
2015–NM–005–AD’’ at the beginning of We estimate that this proposed AD
the terminating action is accomplished.
your comments. We specifically invite affects 285 airplanes of U.S. registry.
After the issuance of [Canadian] AD CF–
comments on the overall regulatory, 2013–39, there has been one reported The actions required by AD 2014–17–
economic, environmental, and energy incident on a 604 Variant aeroplane where 51, Amendment 39–17999 (79 FR
aspects of this proposed AD. We will four fasteners were found fractured on the 64088, October 28, 2014), and retained
consider all comments received by the same flap hinge-box forward fitting. The in this proposed AD take about 1 work-
investigation determined that the fasteners hour per product, at an average labor
closing date and may amend this
were incorrectly installed. rate of $85 per work-hour. Required
proposed AD based on those comments. The original issue of this [Canadian] AD
We will post all comments we parts cost about $0 per product. Based
was issued to reduce the initial and repetitive on these figures, the estimated cost of
receive, without change, to http:// inspection intervals previously mandated in
www.regulations.gov, including any [Canadian] AD CF–2013–39, and to impose
the actions that are required by AD
personal information you provide. We replacement of the incorrectly oriented 2014–17–51 is $85 per product.
will also post a report summarizing each fasteners within 24 months. The CL–600– We also estimate that it would take
asabaliauskas on DSK5VPTVN1PROD with PROPOSALS
substantive verbal contact we receive 1A11, –2A12 and –2B16 (601–3A/–3R about 58 work-hours per product to
about this proposed AD. Variant) aeroplanes are addressed through comply with the basic requirements of
[Canadian] AD CF–2013–39R1. this proposed AD. The average labor
Discussion Revision 1 of this [Canadian] AD is issued rate is $85 per work-hour. Required
On October 13, 2014, we issued AD to clarify the requirements for the initial and parts would cost about $753 per
repetitive inspections.
2014–17–51, Amendment 39–17999 (79 product. Based on these figures, we
FR 64088, October 28, 2014). AD 2014– You may examine the MCAI in the estimate the cost of this proposed AD on
17–51 requires actions intended to AD docket on the Internet at http:// U.S. operators to be $1,619,655, or
address an unsafe condition on certain www.regulations.gov by searching for $5,683 per product.
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![Federal Register / Vol. 80, No. 201 / Monday, October 19, 2015 / Proposed Rules 63143
In addition, we estimate that any List of Subjects in 14 CFR Part 39 (g) Retained Inspection, With New Service
necessary follow-on actions would take Information: Airplanes Not Previously
about 58 work-hours and require parts Air transportation, Aircraft, Aviation Inspected
costing $753, for a cost of $5,683 per safety, Incorporation by reference, This paragraph restates the requirements of
product. We have no way of Safety. paragraph (g) of AD 2014–17–51,
determining the number of aircraft that Amendment 39–17999 (79 FR 64088, October
The Proposed Amendment 28, 2014), with new service information. For
might need this action. airplanes on which the actions required by
According to the manufacturer, some Accordingly, under the authority AD 2014–03–17, Amendment 39–17754 (79
of the costs of this proposed AD may be delegated to me by the Administrator, FR 9389, February 19, 2014), have not been
covered under warranty, thereby the FAA proposes to amend 14 CFR part done as of November 12, 2014 (the effective
reducing the cost impact on affected 39 as follows: date of AD 2014–17–51): Within 10 flight
individuals. We do not control warranty cycles after November 12, 2014, or within
PART 39—AIRWORTHINESS 100 flight cycles after March 6, 2014 (the
coverage for affected individuals. As a effective date of AD 2014–03–17,
result, we have included all costs in our DIRECTIVES
Amendment 39–17754 (79 FR 9389, February
cost estimate. 19, 2014)), whichever occurs first, do a
■ 1. The authority citation for part 39 detailed visual inspection of each inboard
Authority for This Rulemaking continues to read as follows: flap fastener of the hinge-box forward fitting
Title 49 of the United States Code Authority: 49 U.S.C. 106(g), 40113, 44701. at WS 76.50 and WS 127.25, on both wings,
to determine if the fasteners are correctly
specifies the FAA’s authority to issue
§ 39.13 [Amended] oriented and intact (non-fractured, with
rules on aviation safety. Subtitle I, intact fastener head). Do the inspection in
section 106, describes the authority of ■ 2. The FAA amends § 39.13 by accordance with the Accomplishment
the FAA Administrator. ‘‘Subtitle VII: removing Airworthiness Directive (AD) Instructions of Bombardier Alert Service
Aviation Programs,’’ describes in more 2014–17–51, Amendment 39–17999 (79 Bulletin A604–57–006, Revision 01, dated
detail the scope of the Agency’s FR 64088, October 28, 2014), and September 26, 2013, including Appendices 1
authority. adding the following new AD: and 2, dated September 26, 2013, Revision
02, dated January 22, 2014, including
We are issuing this rulemaking under Bombardier, Inc.: Docket No. FAA–2015– Appendices 1 and 2, dated September 26,
the authority described in ‘‘Subtitle VII, 3988; Directorate Identifier 2015–NM– 2013, or Revision 04, dated November 12,
Part A, Subpart III, Section 44701: 005–AD. 2014, including Appendices 1 and 2, dated
General requirements.’’ Under that September 26, 2013 (for serial numbers 5301
(a) Comments Due Date through 5665 inclusive); or Bombardier Alert
section, Congress charges the FAA with
promoting safe flight of civil aircraft in We must receive comments by December 3, Service Bulletin A605–57–004, Revision 01,
air commerce by prescribing regulations 2015. dated September 26, 2013, including
Appendices 1 and 2, dated September 26,
for practices, methods, and procedures (b) Affected ADs 2013, Revision 02, dated January 22, 2014,
the Administrator finds necessary for including Appendices 1 and 2, dated
(1) This AD replaces AD 2014–17–51,
safety in air commerce. This regulation September 26, 2013, or Revision 04, dated
Amendment 39–17999 (79 FR 64088, October
is within the scope of that authority November 12, 2014, including Appendices 1
28, 2014).
because it addresses an unsafe condition (2) This AD affects AD 2014–03–17,
and 2, dated September 26, 2013 (for serial
that is likely to exist or develop on numbers 5701 through 5920 inclusive). As of
Amendment 39–17754 (79 FR 9389, February the effective date of this AD, only use
products identified in this rulemaking 19, 2014), only for the airplanes identified in
action. Bombardier Alert Service Bulletin A604–57–
paragraph (c) of this AD. 006, Revision 04, dated November 12, 2014,
Regulatory Findings (c) Applicability including Appendices 1 and 2, dated
September 26, 2013; or Bombardier Alert
We determined that this proposed AD This AD applies to Bombardier, Inc. Model Service Bulletin A605–57–004, Revision 04,
would not have federalism implications CL–600–2B16 airplanes, certificated in any dated November 12, 2014, including
under Executive Order 13132. This category, serial numbers 5301 through 5665 Appendices 1 and 2, dated September 26,
proposed AD would not have a inclusive, and 5701 through 5920 inclusive. 2013; as applicable; for the actions required
substantial direct effect on the States, on by this paragraph.
(d) Subject (1) If all fasteners are found intact and
the relationship between the national Air Transport Association (ATA) of correctly oriented, no further action is
Government and the States, or on the America Code 57, Wings. required by this AD.
distribution of power and (2) If any fastener is found fractured: Before
responsibilities among the various (e) Reason further flight, remove and replace all forward
levels of government. This AD was prompted by reports of and aft fasteners at WS 76.50 and WS 127.25,
For the reasons discussed above, I fractured fastener heads on the inboard flap regardless of condition or orientation, on
hinge-box forward fitting at Wing Station both wings, in accordance with the
certify this proposed regulation: Accomplishment Instructions of the
(WS) 76.50 due to incorrect installation. We
1. Is not a ‘‘significant regulatory are issuing this AD to detect and correct applicable service information identified in
action’’ under Executive Order 12866; incorrectly oriented or fractured fasteners,
paragraph (g) of this AD. As of the effective
2. Is not a ‘‘significant rule’’ under the date of this AD, only use Bombardier Alert
which could result in premature failure of
Service Bulletin A604–57–006, Revision 04,
asabaliauskas on DSK5VPTVN1PROD with PROPOSALS
DOT Regulatory Policies and Procedures the fasteners attaching the inboard flap dated November 12, 2014, including
(44 FR 11034, February 26, 1979); hinge-box forward fitting; failure of the Appendices 1 and 2, dated September 26,
3. Will not affect intrastate aviation in fasteners could lead to the detachment of the 2013; or Bombardier Alert Service Bulletin
Alaska; and flap hinge box and the flap surface, and A605–57–004, Revision 04, dated November
consequent loss of control of the airplane. 12, 2014, including Appendices 1 and 2,
4. Will not have a significant dated September 26, 2013; as applicable; for
economic impact, positive or negative, (f) Compliance
the actions required by this paragraph. After
on a substantial number of small entities Comply with this AD within the replacement of all fasteners as required by
under the criteria of the Regulatory compliance times specified, unless already this paragraph of this AD, no further action
Flexibility Act. done. is required by this AD.
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![Federal Register / Vol. 80, No. 201 / Monday, October 19, 2015 / Proposed Rules 63145
a manufacturer, the action must be modification (MOD) 0755B28 improved 76177; telephone (817) 222–5110; email
accomplished using a method approved by the dynamic behavior of the horizontal robert.grant@faa.gov.
the Manager, New York ACO, ANE–170, stabilizer such that AD actions are not SUPPLEMENTARY INFORMATION:
FAA; or Transport Canada Civil Aviation required. This proposed AD would
(TCCA); or Bombardier, Inc.’s TCCA Design Comments Invited
Approval Organization (DAO). If approved by
retain the requirements of AD 2010–23–
the DAO, the approval must include the 01 and revise the applicability to We invite you to participate in this
DAO-authorized signature. exclude helicopters with MOD 0755B28. rulemaking by submitting written
These proposed actions are intended to comments, data, or views. We also
(n) Related Information exclude certain helicopters from the invite comments relating to the
(1) Refer to Mandatory Continuing applicability and restrict the VNE on economic, environmental, energy, or
Airworthiness Information (MCAI) Canadian other helicopters to prevent failure of federalism impacts that might result
Emergency Airworthiness Directive CF– the horizontal stabilizer and subsequent from adopting the proposals in this
2014–27R1, dated August 29, 2014, for document. The most helpful comments
related information. This MCAI may be
loss of control of the helicopter.
DATES: We must receive comments on
reference a specific portion of the
found in the AD docket on the Internet at
http://www.regulations.gov by searching for this proposed AD by December 18, proposal, explain the reason for any
and locating Docket No. FAA–2015–3988. 2015. recommended change, and include
(2) For service information identified in supporting data. To ensure the docket
this AD, contact Bombardier, Inc., 400 Côte ADDRESSES: You may send comments by does not contain duplicate comments,
Vertu Road West, Dorval, Québec H4S 1Y9, any of the following methods: commenters should send only one copy
Canada; telephone 514–855–5000; fax 514 • Federal eRulemaking Docket: Go to of written comments, or if comments are
855–7401; email http://www.regulations.gov. Follow the filed electronically, commenters should
thd.crj@aero.bombardier.com; Internet http:// online instructions for sending your submit only one time.
www.bombardier.com. You may view this comments electronically. We will file in the docket all
service information at the FAA, Transport
Airplane Directorate, 1601 Lind Avenue SW., • Fax: 202–493–2251. comments that we receive, as well as a
• Mail: Send comments to the U.S. report summarizing each substantive
Renton, WA. For information on the
availability of this material at the FAA, call Department of Transportation, Docket public contact with FAA personnel
425–227–1221. Operations, M–30, West Building concerning this proposed rulemaking.
Ground Floor, Room W12–140, 1200 Before acting on this proposal, we will
Issued in Renton, Washington, on October
New Jersey Avenue SE., Washington, consider all comments we receive on or
6, 2015.
DC 20590–0001. before the closing date for comments.
Jeffrey E. Duven, We will consider comments filed after
Manager, Transport Airplane Directorate, • Hand Delivery: Deliver to the
‘‘Mail’’ address between 9 a.m. and 5 the comment period has closed if it is
Aircraft Certification Service. possible to do so without incurring
[FR Doc. 2015–26222 Filed 10–16–15; 8:45 am]
p.m., Monday through Friday, except
Federal holidays. expense or delay. We may change this
BILLING CODE 4910–13–P proposal in light of the comments we
Examining the AD Docket receive.
DEPARTMENT OF TRANSPORTATION You may examine the AD docket on Discussion
the Internet at http://
On October 15, 2010, we issued AD
Federal Aviation Administration www.regulations.gov in Docket No.
2010–23–02, Amendment 39–16491 (75
FAA–2015–4112; or in person at the
FR 68169, November 5, 2010) for
14 CFR Part 39 Docket Operations Office between 9
Eurocopter France (now Airbus
a.m. and 5 p.m., Monday through
[Docket No. FAA–2015–4112; Directorate Helicopters) Model SA–365N, SA–
Friday, except Federal holidays. The AD
Identifier 2014–SW–043–AD] 365N1, AS–365N2, and AS 365 N3
docket contains this proposed AD, the
helicopters. AD 2010–23–02 requires
RIN 2120–AA64 European Aviation Safety Agency
amending the Limitations section of the
(EASA) AD, the economic evaluation,
Airworthiness Directives; Airbus RFM to limit the VNE to 150 KIAS and
any comments received and other
Helicopters (previously Eurocopter to add a 1,500 ft/minute R/D limitation
information. The street address for the
France) beyond 140 KIAS and installing one or
Docket Operations Office (telephone
more placards on the cockpit instrument
AGENCY: Federal Aviation 800–647–5527) is in the ADDRESSES
panel in full view of the pilot and
Administration (FAA), DOT. section. Comments will be available in
copilot. AD 2010–23–01 was prompted
the AD docket shortly after receipt.
ACTION: Notice of proposed rulemaking by failures of the horizontal stabilizers
For service information identified in on then-recently delivered Model AS
(NPRM).
this proposed AD, contact Airbus 365 N3 helicopters due to a vibration
SUMMARY: We propose to supersede Helicopters, Inc., 2701 N. Forum Drive, phenomenon that may arise during the
airworthiness directive (AD) 2010–23– Grand Prairie, TX 75052; telephone descent flight phases at high speed
02 for Eurocopter France (now Airbus (972) 641–0000 or (800) 232–0323; fax regardless of the stabilizer installed.
Helicopters) Model SA–365N, SA– (972) 641–3775; or at http:// Those actions were intended to prevent
365N1, AS–365N2, and AS 365 N3 www.airbushelicopters.com/techpub. failure of the horizontal stabilizer and
asabaliauskas on DSK5VPTVN1PROD with PROPOSALS
helicopters. AD 2010–23–02 currently You may review service information at subsequent loss of control of the
requires amending the Limitations the FAA, Office of the Regional Counsel, helicopter.
section of the Rotorcraft Flight Manual Southwest Region, 10101 Hillwood
(RFM) to limit the never-exceed velocity Pkwy., Room 6N–321, Fort Worth, Actions Since AD 2010–23–02 Was
(VNE) to 150 Knots Indicated Air Speed Texas 76177. Issued
(KIAS) and to add a 1,500 ft/minute rate FOR FURTHER INFORMATION CONTACT: Since we issued AD 2010–23–01 (75
of descent (R/D) limitation beyond 140 Robert Grant, Aviation Safety Engineer, FR 68169, November 5, 2010),
KIAS. Since we issued AD 2010–23–02, Safety Management Group, FAA, 10101 Eurocopter France changed its name to
a design change designated as Hillwood Pkwy., Fort Worth, Texas Airbus Helicopters. EASA, which is the
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Document Created: 2015-12-15 08:35:51
Document Modified: 2015-12-15 08:35:51
| 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 December 3, 2015. | |
| Contact | Aziz Ahmed, Aerospace Engineer, Propulsion and Services Branch, ANE-173, FAA, New York Aircraft Certification Office (ACO), 1600 Stewart Avenue, Suite 410, Westbury, NY 11590; telephone 516-228-7329; fax 516-794-5531. | |
| FR Citation | 80 FR 63141 | |
| RIN Number | 2120-AA64 | |
| CFR Associated | Air Transportation; Aircraft; Aviation Safety; Incorporation by Reference and Safety |
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