82 FR 42024 - Airworthiness Directives; Viking Air Limited (Type Certificate Previously Held by Bombardier, Inc.; Canadair Limited) Airplanes
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration Federal Register Volume 82, Issue 171 (September 6, 2017)
Federal Aviation Administration
Federal Register Volume 82, Issue 171 (September 6, 2017)
| Page Range | 42024-42029 | |
| FR Document | 2017-17838 |
[Federal Register Volume 82, Number 171 (Wednesday, September 6, 2017)] [Rules and Regulations] [Pages 42024-42029] From the Federal Register Online [www.thefederalregister.org] [FR Doc No: 2017-17838] ----------------------------------------------------------------------- DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA-2017-0474; Product Identifier 2016-NM-096-AD; Amendment 39-19007; AD 2017-17-17] RIN 2120-AA64 Airworthiness Directives; Viking Air Limited (Type Certificate Previously Held by Bombardier, Inc.; Canadair Limited) Airplanes AGENCY: Federal Aviation Administration (FAA), Department of Transportation (DOT). ACTION: Final rule. ----------------------------------------------------------------------- SUMMARY: We are superseding Airworthiness Directive (AD) 2011-03-08, which applied to certain Bombardier, Inc., Model CL-215-1A10 (CL-215), CL-215-6B11 (CL-215T Variant), and CL-215-6B11 (CL-415 Variant) airplanes. AD 2011-03-08 required an inspection to determine the number of flight cycles accumulated by certain accumulators installed on the airplane, and repetitive inspections of the accumulators for cracks, and replacement if necessary. This AD retains those inspections and the accumulator replacement if necessary, and adds a new terminating action to address the identified unsafe condition. This AD was prompted by the development of a terminating action for the repetitive inspections. We are issuing this AD to address the unsafe condition on these products. DATES: This AD is effective October 11, 2017. The Director of the Federal Register approved the incorporation by reference of certain publications listed in this AD as of October 11, 2017. The Director of the Federal Register approved the incorporation by reference of certain other publications listed in this AD as of March 14, 2011 (76 FR 6536, February 7, 2011). ADDRESSES: For service information identified in this final rule, contact Viking Air Limited, 1959 de Havilland Way, Sidney, British Columbia V8L 5V5, Canada; telephone +1-250-656-7227; fax +1-250-656- 0673; email [email protected]; Internet http://www.vikingair.com. You may view this referenced service information at the FAA, Transport Standards Branch, 1601 Lind Avenue SW., Renton, WA. For information on the availability of this material at the FAA, call 425-227-1221. It is also available on the Internet at http://www.regulations.gov by searching for and locating Docket No. FAA-2017- 0474. 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-2017- 0474; or in person at the Docket Management Facility between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. The AD docket contains this AD, the regulatory evaluation, any comments received, and other information. The address for the Docket Office (telephone 800- 647-5527) is Docket Management Facility, U.S. Department of Transportation, Docket Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New Jersey Avenue SE., Washington, DC 20590. FOR FURTHER INFORMATION CONTACT: Cesar A. Gomez, Aerospace Engineer, Airframe and Mechanical Systems Section, FAA, New York ACO Branch, 1600 Stewart Avenue, Suite 410, Westbury, NY 11590; telephone 516-228-7318; fax 516-794-5531. SUPPLEMENTARY INFORMATION: Discussion We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR part 39 to supersede AD 2011-03-08, Amendment 39-16592 (76 FR 6536, February 7, 2011) (``AD 2011-03-08''). AD 2011-03-08 applied to certain Bombardier, Inc., Model CL-215-1A10 (CL-215), CL-215-6B11 (CL-215T Variant), and CL-215-6B11 (CL-415 Variant) airplanes. The NPRM published in the Federal Register on May 18, 2017 (82 FR 22766). The NPRM was prompted by the development of a terminating action (relocation of the affected accumulators, and incorporation of new airworthiness limitations), which addresses the unsafe condition. The NPRM proposed to continue to require an inspection to determine the number of flight cycles accumulated by applicable accumulators (i.e., brake, aileron, elevator, and rudder accumulators) installed on the airplane, repetitive ultrasonic inspections of the accumulators for cracks, and [[Page 42025]] replacement of any accumulator in which a crack is detected. The NPRM also proposed to require a new terminating action for the repetitive inspections. We are issuing this AD to prevent failure of the screw cap or end cap of certain accumulators, which could result in impact damage to various components, potentially resulting in fuel spillage, uncommanded flap movement, or loss of aileron control. Transport Canada Civil Aviation (TCCA), which is the aviation authority for Canada, has issued Canadian Airworthiness Directive CF- 2009-42R2, dated May 30, 2016 (referred to after this as the Mandatory Continuing Airworthiness Information, or ''the MCAI''), to correct an unsafe condition for certain Viking Air Limited Model CL-215-1A10 (CL- 215), CL-215-6B11 (CL-215T Variant), and CL-215-6B11 (CL-415 Variant) airplanes. The MCAI states: Seven cases of on-ground hydraulic accumulator screw cap or end cap failure have been experienced on CL-600-2B19 (CRJ) aeroplane, resulting in loss of the associated hydraulic system and high-energy impact damage to adjacent systems and structure. To date, the lowest number of flight cycles accumulated at the time of failure has been 6991. Although there have been no failures to date on any CL-215-1A10 (CL-215) or CL-215-6B11 (CL-215T and CL-415) aeroplane, similar accumulators, Part Number (P/N) 08-8423-010 (MS28700-3), to those installed on the CL-600-2B19, are installed on the aeroplane models listed in the Applicability section of this [Canadian] AD. A detailed analysis of the systems and structure in the potential line of trajectory of a failed screw cap/end cap for each accumulator has been conducted. It has identified that the worst- case scenarios would be impact damage to various components, potentially resulting in fuel spillage, uncommanded flap movement, or loss of aileron control. This [Canadian] AD mandates repetitive [ultrasonic] inspections of the accumulators for cracks and replacement of any accumulator in which a crack is detected. Revision 1 of this [Canadian] AD clarified the text of the [Canadian] AD, including the P/N of the affected accumulators. This revision provides the terminating action [relocation of affected accumulators and incorporation of new airworthiness limitations] to this [Canadian] AD. It also modifies the applicability range for the CL-215-1A10 (CL-215); the CL-215 is out of production and the last aeroplane produced was serial number 1125. 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-2017- 0474. Comments We gave the public the opportunity to participate in developing this AD. We received no comments on the NPRM or on the determination of the cost to the public. Explanation of Changes Made to This Final Rule We have revised this final rule to identify the legal name of the manufacturer as published in the most recent type certificate data sheet for the affected airplane models. In the proposed AD, we inadvertently listed the wrong publication dates for service information in two places. Table 4 to paragraph (o) of the proposed AD referred to Bombardier Service Bulletin 215-4470, Revision 1, dated December 13, 2013. We have corrected the publication date for this document to June 27, 2014, in this AD. Additionally, paragraph (r)(1)(iii) of the proposed AD referred to Bombardier Service Bulletin 215-3158, dated March 28, 2012. We have corrected the publication date for this document to March 21, 2012, in this AD. Conclusion We reviewed the available data and determined that air safety and the public interest require adopting this AD with the changes described previously and minor editorial changes. We have determined that these changes:Are consistent with the intent that was proposed in the NPRM for correcting the unsafe condition; and Do not add any additional burden upon the public than was already proposed in the NPRM. Related Service Information Under 1 CFR Part 51 Bombardier, Inc., has issued the following service information: Bombardier Service Bulletin 215-552, Revision 2, dated June 18, 2015. This service information describes procedures to relocate the aileron hydraulic accumulator aft of its current location. Bombardier Service Bulletin 215-3158, Revision 2, dated April 15, 2014; and Bombardier Service Bulletin 215-4423, Revision 5, dated March 17, 2016. This service information describes procedures to relocate the aileron, elevator, and rudder hydraulic accumulators aft and outboard of their current locations. These documents are distinct since they apply to different airplane models. Bombardier Service Bulletin 215-557, Revision 1, dated June 27, 2014; Bombardier Service Bulletin 215-3182, Revision 1, dated June 27, 2014; and Bombardier Service Bulletin 215-4470, Revision 1, dated June 27, 2014. This service information describes procedures to establish the number of flight hours for each accumulator and determine if it has been used on another type of aircraft. These documents are distinct since they apply to different airplane models. Bombardier Temporary Revision 5-56, dated December 13, 2013; Bombardier Temporary Revision 295/7, dated December 13, 2013; Bombardier Temporary Revision LLC-1, dated December 13, 2013; and Bombardier Temporary Revision LLC-3, dated December 13, 2013. This service information provides a 10,000-hour accumulator life limitation for certain accumulators. These documents are distinct since they apply to different airplane models. This service information is reasonably available because the interested parties have access to it through their normal course of business or by the means identified in the ADDRESSES section. Costs of Compliance We estimate that this AD affects 7 airplanes of U.S. registry. We estimate the following costs to comply with this AD: Estimated Costs ---------------------------------------------------------------------------------------------------------------- Cost per Cost on U.S. Action Labor cost Parts cost product operators ---------------------------------------------------------------------------------------------------------------- Ultrasonic inspection (retained action 7 work-hours x $85 per $0 $595 $4,165 from AD 2011-03-08). hour = $595. Relocation, determination of 56 work-hours x $85 per 0 4,760 33,320 accumulator hours and usage, and hour = $4,760. maintenance or inspection program revision (new action). ---------------------------------------------------------------------------------------------------------------- [[Page 42026]] We estimate the following costs to do any necessary replacement that would be required based on the results of the inspection. We have no way of determining the number of aircraft that might need this replacement. On-Condition Costs ---------------------------------------------------------------------------------------------------------------- Cost per Action Labor cost Parts cost product ---------------------------------------------------------------------------------------------------------------- Replacement of cracked part (retained action 6 work-hours x $85 per hour = $4,055 $4,565 from AD 2011-03-08). $510. ---------------------------------------------------------------------------------------------------------------- According to the manufacturer, some of the costs of this AD may be covered under warranty, thereby reducing the cost impact on affected individuals. We do not control warranty coverage for affected individuals. As a result, we have included all costs in our cost estimate. Authority for This Rulemaking Title 49 of the United States Code specifies the FAA's authority to issue rules on aviation safety. Subtitle I, section 106, describes the authority of the FAA Administrator. ``Subtitle VII: Aviation Programs,'' describes in more detail the scope of the Agency's authority. We are issuing this rulemaking under the authority described in ``Subtitle VII, Part A, Subpart III, Section 44701: General requirements.'' Under that section, Congress charges the FAA with promoting safe flight of civil aircraft in air commerce by prescribing regulations for practices, methods, and procedures the Administrator finds necessary for safety in air commerce. This regulation is within the scope of that authority because it addresses an unsafe condition that is likely to exist or develop on products identified in this rulemaking action. This AD is issued in accordance with authority delegated by the Executive Director, Aircraft Certification Service, as authorized by FAA Order 8000.51C. In accordance with that order, issuance of ADs is normally a function of the Compliance and Airworthiness Division, but during this transition period, the Executive Director has delegated the authority to issue ADs applicable to transport category airplanes to the Director of the System Oversight Division. Regulatory Findings We determined that this AD will not have federalism implications under Executive Order 13132. This AD will not have a substantial direct effect on the States, on the relationship between the national government and the States, or on the distribution of power and responsibilities among the various levels of government. For the reasons discussed above, I certify that this AD: 1. Is not a ``significant regulatory action'' under Executive Order 12866; 2. Is not a ``significant rule'' under the DOT Regulatory Policies and Procedures (44 FR 11034, February 26, 1979); 3. Will not affect intrastate aviation in Alaska; and 4. Will not have a significant economic impact, positive or negative, on a substantial number of small entities under the criteria of the Regulatory Flexibility Act. List of Subjects in 14 CFR Part 39 Air transportation, Aircraft, Aviation safety, Incorporation by reference, Safety. Adoption of the Amendment Accordingly, under the authority delegated to me by the Administrator, the FAA amends 14 CFR part 39 as follows: PART 39--AIRWORTHINESS DIRECTIVES 0 1. The authority citation for part 39 continues to read as follows: Authority: 49 U.S.C. 106(g), 40113, 44701. Sec. 39.13 [Amended] 0 2. The FAA amends Sec. 39.13 by removing Airworthiness Directive (AD) 2011-03-08, Amendment 39-16592 (76 FR 6536, February 7, 2011), and adding the following new AD: 2017-17-17 Viking Air Limited (Type Certificate Previously Held by Bombardier, Inc.; Canadair Limited): Amendment 39-19007; Docket No. FAA-2017-0474; Product Identifier 2016-NM-096-AD. (a) Effective Date This AD is effective October 11, 2017. (b) Affected ADs This AD replaces AD 2011-03-08, Amendment 39-16592 (76 FR 6536, February 7, 2011) (``AD 2011-03-08''). (c) Applicability This AD applies to Viking Air Limited (Type Certificate previously held by Bombardier, Inc.; Canadair Limited) airplanes, certificated in any category, as identified in paragraphs (c)(1) through (c)(3) of this AD. (1) Model CL-215-1A10 (CL-215) airplanes, serial numbers 1001 through 1125 inclusive. (2) Model CL-215-6B11 (CL-215T Variant) airplanes, serial numbers 1056 through 1125 inclusive. (3) Model CL-215-6B11 (CL-415 Variant) airplanes, serial numbers 2001 through 2990 inclusive. (d) Subject Air Transport Association (ATA) of America Code 29, Hydraulic power. (e) Reason This AD was prompted by reports of on-ground hydraulic accumulator screw cap or end cap failure resulting in a loss of the associated hydraulic system and high-energy impact damage to adjacent systems and structure. We are issuing this AD to prevent failure of the screw cap or end cap, which could result in impact damage to various components, potentially resulting in fuel spillage, uncommanded flap movement, or loss of aileron control. (f) Compliance Comply with this AD within the compliance times specified, unless already done. (g) Retained Inspection To Determine Flight Cycles, With No Changes This paragraph restates the requirements of paragraph (g) of AD 2011-03-08, with no changes. Within 50 flight hours after March 14, 2011 (the effective date of AD 2011-03-08), inspect to determine the number of flight cycles accumulated by each of the applicable accumulators (i.e., brake, aileron, elevator, and rudder accumulators) having part number 08-8423-010 (MS28700-3) installed on the airplane. A review of airplane maintenance records is acceptable in lieu of this inspection if the number of flight cycles accumulated can be conclusively determined from that review. (h) Retained Initial Ultrasonic Inspection for Model CL-215-1A10 (CL- 215) and CL-215-6B11 (CL-215T Variant) Airplanes, With No Changes This paragraph restates the requirements of paragraph (h) of AD 2011-03-08, with no changes. For Model CL-215-1A10 (CL-215) and CL- 215-6B11 (CL-215T Variant) airplanes: Do an ultrasonic inspection for cracking of the accumulator at the applicable time specified in paragraph (h)(1) or (h)(2) of this AD, in accordance with Part B of the Accomplishment Instructions of the [[Page 42027]] applicable service bulletin listed in table 1 to paragraphs (h), (i), and (k) of this AD. Table 1 to Paragraphs (h), (i), and (k) of This AD--Service Bulletins ------------------------------------------------------------------------ Use bombardier service For model-- bulletin-- ------------------------------------------------------------------------ CL-215-1A10 (CL-215)...................... 215-541, Revision 1, dated March 12, 2010. CL-215-6B11 (CL-215T Variant)............. 215-3155, Revision 1, dated March 12, 2010. CL-215-6B11 (CL-415 Variant).............. 215-4414, Revision 1, dated March 12, 2010. ------------------------------------------------------------------------ (1) For any accumulator on which the inspection required by paragraph (g) of this AD shows an accumulation of more than 875 total flight cycles, or on which it is not possible to determine the number of total accumulated flight cycles, do the inspection within 125 flight cycles after March 14, 2011 (the effective date of AD 2011-03-08). (2) For any accumulator on which the inspection required by paragraph (g) of this AD shows an accumulation of 875 total flight cycles or fewer, do the inspection before the accumulation of 1,000 flight cycles on the accumulator. (i) Retained Initial Ultrasonic Inspection for Model CL-215-6B11 (CL- 415 Variant) Airplanes, With No Changes This paragraph restates the requirements of paragraph (i) of AD 2011-03-08, with no changes. For Model CL-215-6B11 (CL-415 Variant) airplanes, do an ultrasonic inspection for cracking of the accumulator at the applicable time specified in paragraph (i)(1) or (i)(2) of this AD, in accordance with Part B of the Accomplishment Instructions of the applicable service bulletin listed in table 1 to paragraphs (h), (i), and (k) of this AD. (1) For any accumulator on which the inspection required by paragraph (g) of this AD shows an accumulation of more than 750 flight cycles, or on which it is not possible to determine the number of total accumulated flight cycles, do the inspection within 250 flight cycles after March 14, 2011 (the effective date of AD 2011-03-08). (2) For any accumulator on which the inspection required by paragraph (g) of this AD shows an accumulation of 750 total flight cycles or fewer, do the inspection before the accumulation of 1,000 flight cycles on the accumulator. (j) Retained Repetitive Inspections, With New Terminating Action This paragraph restates the requirements of paragraph (j) of AD 2011-03-08, with new terminating action. If no cracking is found during any inspection required by paragraph (h) or (i) of this AD, repeat the inspection thereafter at intervals not to exceed 750 flight cycles until the actions required by paragraphs (n), (o), and (p) of this AD have been done. (k) Retained Replacement of Cracked Accumulators and Repetitive Inspections, With New Terminating Action This paragraph restates the requirements of paragraph (k) of AD 2011-03-08, with new terminating action. If any cracking is found during any inspection required by paragraph (h) or (i) of this AD, before further flight, replace the accumulator with a serviceable accumulator, in accordance with Part B of the Accomplishment Instructions of the applicable service bulletin listed in table 1 to paragraphs (h), (i), and (k) of this AD. Doing the replacement does not end the inspection requirements of paragraphs (h) and (i) of this AD. Repeat the inspections required by paragraph (h) or (i) of this AD, as applicable, at intervals not to exceed 750 flight cycles until the actions required by paragraphs (n), (o), and (p) of this AD have been done. (l) Retained Parts Installation Limitation, With No Changes This paragraph restates the parts installation limitation in paragraph (l) of AD 2011-03-08, with no changes. As of March 14, 2011 (the effective date of AD 2011-03-08), no person may install an accumulator, part number 08-8423-010 (MS28700-3), on any airplane unless the accumulator has been inspected in accordance with the requirements of paragraph (h) or (i) of this AD. (m) Retained Credit for Previous Actions, With No Changes This paragraph restates the credit provided in paragraph (m) of AD 2011-03-08, with no changes. Inspections accomplished before March 14, 2011 (the effective date of AD 2011-03-08), in accordance with the applicable service bulletin listed in table 2 to paragraph (m) of this AD are considered acceptable for compliance with the corresponding action specified in paragraph (h), (i), (j), or (k) of this AD. Table 2 to Paragraph (m) of This AD--Credit Service Bulletins ------------------------------------------------------------------------ Use Bombardier Service For model-- Bulletin-- ------------------------------------------------------------------------ CL-215-1A10 (CL-215)...................... 215-541, dated July 9, 2009. CL-215-6B11 (CL-215T Variant)............. 215-3155, dated July 9, 2009. CL-600-6B11 (CL-415 Variant).............. 215-4414, dated July 9, 2009. ------------------------------------------------------------------------ (n) New Relocation of Affected Accumulators Within 12 months after the effective date of this AD, relocate affected hydraulic accumulators, in accordance with the Accomplishment Instructions of the applicable Bombardier service bulletin specified in table 3 to paragraph (n) of this AD. Table 3 to Paragraph (n) of This AD--Service Information for Relocating Accumulators ------------------------------------------------------------------------ Affected Use Service Bulletin-- For model-- accumulators-- ------------------------------------------------------------------------ CL-215-1A10 (CL-215).......... Aileron, if Bombardier Service installed. Bulletin 215-552, Revision 2, dated June 18, 2015. CL-215-6B11 (CL-215T Variant). Aileron, rudder, Bombardier Service and elevator. Bulletin 215-3158, Revision 2, dated April 15, 2014. CL-215-6B11 (CL-415 Variant).. Aileron, rudder, Bombardier Service and elevator. Bulletin 215-4423, Revision 5, dated March 17, 2016. ------------------------------------------------------------------------ (o) New Establishment of Flight Hours on the Accumulator, Determination of Previous Use of the Accumulator, and Replacement if Necessary Within 12 months after the effective date of this AD, establish the number of flight hours for each accumulator, and determine whether any accumulator has been used in service on another type of airplane other than Model CL-215-1A10 (CL-215), CL-215-6B11 (CL-215T Variant), or CL-215-6B11 (CL-415 Variant), in accordance with the Accomplishment Instructions in the applicable Bombardier service bulletin specified in table 4 to paragraph (o) of this AD. If any accumulator is found that has been in service on another type of airplane other than Model CL-215-1A10 (CL-215), CL-215-6B11 (CL-215T Variant), or CL-215-6B11 (CL-415 Variant), replace the accumulator within 50 flight hours after determining an affected accumulator is installed. Table 4 to Paragraph (o) of This AD--Establishment of Number of Flight Hours on the Accumulator ------------------------------------------------------------------------ For model-- Use Service Bulletin-- ------------------------------------------------------------------------ CL-215-1A10 (CL-215)......... Bombardier Service Bulletin 215-557, Revision 1, dated June 27, 2014 (applicable to MS28700-3 accumulator). [[Page 42028]] CL-215-6B11 (CL-215T Variant) Bombardier Service Bulletin 215-3182, Revision 1, dated June 27, 2014. CL-215-6B11 (CL-415 Variant). Bombardier Service Bulletin 215-4470, Revision 1, dated June 27, 2014. ------------------------------------------------------------------------ (p) New Airworthiness Limitations Within 30 days after the effective date of this AD, revise the maintenance or inspection program, as applicable, to incorporate the 10,000-hour accumulator life limitation specified in the applicable Time Limits/Maintenance Checks (TLMC) Manual temporary revisions (TRs) listed in table 5 to paragraph (p) of this AD. The initial compliance time for accomplishing the replacement of the accumulator is within the limitation specified in the applicable TR specified in table 5 to paragraph (p) of this AD, or within 30 days after the effective date of this AD, whichever occurs later. Table 5 to Paragraph (p) of This AD--Airworthiness Limitations -------------------------------------------------------------------------------------------------------------------------------------------------------- For model-- Comply with Bombardier TLMC manual-- Bombardier TR No.-- Dated-- -------------------------------------------------------------------------------------------------------------------------------------------------------- CL-215-1A10 (CL-215)................ PSP 295............................... 295/7................................. December 13, 2013. CL-215-6B11 (CL-215T Variant)....... PSP 395............................... LLC-3................................. December 13, 2013. CL-215-6B11 (CL-215T Variant)....... PSP 395-1............................. LLC-1................................. December 13, 2013. CL-215-6B11 (CL-415 Variant)........ PSP 495............................... 5-56.................................. December 13, 2013. -------------------------------------------------------------------------------------------------------------------------------------------------------- (q) No Alternative Actions and Intervals After accomplishment of the revision required by paragraph (p) of this AD, no alternative actions (e.g., inspections) or intervals may be used unless the actions and intervals are approved as an alternative method of compliance (AMOC) in accordance with the procedures specified in paragraph (s)(1) of this AD. (r) Credit for Previous Actions (1) This paragraph provides credit for actions required by paragraph (n) of this AD, if those actions were performed before the effective date of this AD using any applicable service information specified in paragraphs (r)(1)(i) through (r)(1)(ix) of this AD. (i) Bombardier Service Bulletin 215-552, dated December 16, 2013. (ii) Bombardier Service Bulletin 215-552, Revision 1, dated September 12, 2014. (iii) Bombardier Service Bulletin 215-3158, dated March 21, 2012. (iv) Bombardier Service Bulletin 215-3158, Revision 1, dated December 16, 2013. (v) Bombardier Service Bulletin 215-4423, Revision NC, dated April 4, 2011. (vi) Bombardier Service Bulletin 215-4423, Revision 1, dated September 28, 2011. (vii) Bombardier Service Bulletin 215-4423, Revision 2, dated May 30, 2012. (viii) Bombardier Service Bulletin 215-4423, Revision 3, dated December 16, 2013. (ix) Bombardier Service Bulletin 215-4423, Revision 4, dated December 3, 2015. (2) This paragraph provides credit for actions required by paragraph (o) of this AD, if those actions were performed before the effective date of this AD using any applicable service information specified in paragraphs (r)(2)(i) through (r)(2)(iii) of this AD. (i) Bombardier Service Bulletin 215-557, Revision NC, dated December 13, 2013. (ii) Bombardier Service Bulletin 215-3182, Revision NC, dated December 13, 2013. (iii) Bombardier Service Bulletin 215-4470, Revision NC, dated December 13, 2013. (s) Other FAA AD Provisions The following provisions also apply to this AD: (1) Alternative Methods of Compliance (AMOCs): The Manager, New York ACO Branch, 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 manager of the certification office, send it to ATTN: Program Manager, Continuing Operational Safety, FAA, New York ACO Branch, 1600 Stewart Avenue, Suite 410, Westbury, NY 11590; telephone 516-228-7300; fax 516-794-5531. Before using any approved AMOC, notify your appropriate principal inspector, or lacking a principal inspector, the manager of the local flight standards district office/certificate holding district office. (2) Contacting the Manufacturer: For any requirement in this AD to obtain corrective actions from a manufacturer, the action must be accomplished using a method approved by the Manager, New York ACO Branch, FAA; or Transport Canada Civil Aviation (TCCA); or Viking Air Limited's TCCA Design Approval Organization (DAO). If approved by the DAO, the approval must include the DAO-authorized signature. (t) Related Information (1) Refer to Mandatory Continuing Airworthiness Information (MCAI) Canadian Airworthiness Directive CF-2009-42R2, dated May 30, 2016, 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-2017-0474. (2) For more information about this AD, contact Cesar A. Gomez, Aerospace Engineer, Airframe and Mechanical Systems Section, FAA, New York ACO Branch, 1600 Stewart Avenue, Suite 410, Westbury, NY 11590; telephone 516-228-7318; fax 516-794-5531. (3) Service information identified in this AD that is not incorporated by reference is available at the addresses specified in paragraphs (u)(5) and (u)(6) of this AD. (u) Material Incorporated by Reference (1) The Director of the Federal Register approved the incorporation by reference (IBR) of the service information listed in this paragraph under 5 U.S.C. 552(a) and 1 CFR part 51. (2) You must use this service information as applicable to do the actions required by this AD, unless this AD specifies otherwise. (3) The following service information was approved for IBR on October 11, 2017. (i) Bombardier Service Bulletin 215-552, Revision 2, dated June 18, 2015. (ii) Bombardier Service Bulletin 215-557, Revision 1, dated June 27, 2014. (iii) Bombardier Service Bulletin 215-3158, Revision 2, dated April 15, 2014. (iv) Bombardier Service Bulletin 215-3182, Revision 1, dated June 27, 2014. (v) Bombardier Service Bulletin 215-4423, Revision 5, dated March 17, 2016. (vi) Bombardier Service Bulletin 215-4470, Revision 1, dated June 27, 2014. (vii) Bombardier Temporary Revision 5-56, dated December 13, 2013. (viii) Bombardier Temporary Revision 295/7, dated December 13, 2013. (ix) Bombardier Temporary Revision LLC-1, dated December 13, 2013. (x) Bombardier Temporary Revision LLC-3, dated December 13, 2013. (4) The following service information was approved for IBR on March 14, 2011 (76 FR 6536, February 7, 2011). (i) Bombardier Service Bulletin 215-541, Revision 1, dated March 12, 2010. (ii) Bombardier Service Bulletin 215-3155, Revision 1, dated March 12, 2010. (iii) Bombardier Service Bulletin 215-4414, Revision 1, dated March 12, 2010. (5) For service information identified in this AD, contact Viking Air Limited, 1959 de [[Page 42029]] Havilland Way, Sidney, British Columbia V8L 5V5, Canada; telephone +1-250-656-7227; fax +1-250-656-0673; email [email protected]; Internet http://www.vikingair.com. (6) You may view this service information at the FAA, Transport Standards Branch, 1601 Lind Avenue SW., Renton, WA. For information on the availability of this material at the FAA, call 425-227-1221. (7) You may view this service information that is incorporated by reference at the National Archives and Records Administration (NARA). For information on the availability of this material at NARA, call 202-741-6030, or go to: http://www.archives.gov/federal-register/cfr/ibr-locations.html. Issued in Renton, Washington, on August 16, 2017. Jeffrey E. Duven, Director, System Oversight Division, Aircraft Certification Service. [FR Doc. 2017-17838 Filed 9-5-17; 8:45 am] BILLING CODE 4910-13-P
![42024 Federal Register / Vol. 82, No. 171 / Wednesday, September 6, 2017 / Rules and Regulations
AD 2016–04–01, effective April 4, 2016, for Issued in Renton, Washington, on July 28, technical.publications@vikingair.com;
related information. This MCAI may be 2017. Internet http://www.vikingair.com. You
found in the AD docket on the Internet at John P. Piccola, Jr., may view this referenced service
http://www.regulations.gov by searching for Acting Director, System Oversight Division, information at the FAA, Transport
and locating Docket No. FAA–2014–0008. Aircraft Certification Service. Standards Branch, 1601 Lind Avenue
(2) For more information about this AD,
contact Ana Martinez Hueto, Aerospace
[FR Doc. 2017–16667 Filed 9–5–17; 8:45 am] SW., Renton, WA. For information on
Engineer, International Section, Transport BILLING CODE 4910–13–P the availability of this material at the
Standards Branch, FAA, 1601 Lind Avenue FAA, call 425–227–1221. It is also
SW., Renton, WA 98057–3356; telephone available on the Internet at http://
425–227–1622; fax 425–227–1320. DEPARTMENT OF TRANSPORTATION www.regulations.gov by searching for
and locating Docket No. FAA–2017–
(m) Material Incorporated by Reference Federal Aviation Administration 0474.
(1) The Director of the Federal Register
approved the incorporation by reference 14 CFR Part 39 Examining the AD Docket
(IBR) of the service information listed in this You may examine the AD docket on
paragraph under 5 U.S.C. 552(a) and 1 CFR [Docket No. FAA–2017–0474; Product
part 51. Identifier 2016–NM–096–AD; Amendment the Internet at http://
(2) You must use this service information 39–19007; AD 2017–17–17] www.regulations.gov by searching for
as applicable to do the actions required by and locating Docket No. FAA–2017–
RIN 2120–AA64
this AD, unless this AD specifies otherwise. 0474; or in person at the Docket
(3) The following service information was Airworthiness Directives; Viking Air Management Facility between 9 a.m.
approved for IBR on October 11, 2017. Limited (Type Certificate Previously and 5 p.m., Monday through Friday,
(i) Appendix A, Airworthiness Limitations except Federal holidays. The AD docket
(AL), of the EMBRAER ERJ 190/195
Held by Bombardier, Inc.; Canadair
Limited) Airplanes contains this AD, the regulatory
Maintenance Review Board Report, MRB– evaluation, any comments received, and
1928, Revision 9, dated August 14, 2015. AGENCY: Federal Aviation other information. The address for the
(ii) Appendix A, Airworthiness Limitations
Administration (FAA), Department of Docket Office (telephone 800–647–5527)
(AL), of the EMBRAER Lineage 1000/1000E
Maintenance Planning Guide, MPG–2928, Transportation (DOT). is Docket Management Facility, U.S.
Revision 4, dated July 14, 2014. ACTION: Final rule. Department of Transportation, Docket
(iii) EMBRAER MPG—Temporary Revision Operations, M–30, West Building
4–2, dated February 13, 2015. SUMMARY: We are superseding Ground Floor, Room W12–140, 1200
(iv) EMBRAER MPG—Temporary Revision Airworthiness Directive (AD) 2011–03– New Jersey Avenue SE., Washington,
4–3, dated October 30, 2015. 08, which applied to certain DC 20590.
(v) EMBRAER MRB—Temporary Revision Bombardier, Inc., Model CL–215–1A10 FOR FURTHER INFORMATION CONTACT:
9–1, dated October 27, 2015. (CL–215), CL–215–6B11 (CL–215T
(vi) EMBRAER MRB—Temporary Revision
Cesar A. Gomez, Aerospace Engineer,
Variant), and CL–215–6B11 (CL–415 Airframe and Mechanical Systems
9–3, dated October 27, 2015. Variant) airplanes. AD 2011–03–08
(4) The following service information was Section, FAA, New York ACO Branch,
approved for IBR on January 14, 2013 (77 FR
required an inspection to determine the 1600 Stewart Avenue, Suite 410,
73270, December 10, 2012). number of flight cycles accumulated by Westbury, NY 11590; telephone 516–
(i) EMBRAER Temporary Revision (TR) 5– certain accumulators installed on the 228–7318; fax 516–794–5531.
1, dated February 11, 2011, to Part 2— airplane, and repetitive inspections of
SUPPLEMENTARY INFORMATION:
Airworthiness Limitation Inspections (ALI)— the accumulators for cracks, and
Structures, of Appendix A, Airworthiness replacement if necessary. This AD Discussion
Limitations (AL), of the EMBRAER 190 retains those inspections and the
Maintenance Review Board Report, MRB–
We issued a notice of proposed
accumulator replacement if necessary, rulemaking (NPRM) to amend 14 CFR
1928, Revision 5, dated November 11, 2010. and adds a new terminating action to
(ii) Appendix A, Airworthiness Limitation part 39 to supersede AD 2011–03–08,
address the identified unsafe condition. Amendment 39–16592 (76 FR 6536,
(AL), of the EMBRAER 190 Maintenance
This AD was prompted by the February 7, 2011) (‘‘AD 2011–03–08’’).
Review Board Report, MRB–1928, Revision 5,
dated November 11, 2010. development of a terminating action for AD 2011–03–08 applied to certain
(5) For service information identified in the repetitive inspections. We are Bombardier, Inc., Model CL–215–1A10
this AD, contact Embraer S.A., Technical issuing this AD to address the unsafe (CL–215), CL–215–6B11 (CL–215T
Publications Section (PC 060), Av. Brigadeiro condition on these products. Variant), and CL–215–6B11 (CL–415
Faria Lima, 2170—Putim—12227–901 São DATES: This AD is effective October 11, Variant) airplanes. The NPRM
Jose dos Campos—SP—BRASIL; telephone 2017.
+55 12 3927–5852 or +55 12 3309–0732; fax
published in the Federal Register on
The Director of the Federal Register May 18, 2017 (82 FR 22766). The NPRM
+55 12 3927–7546; email distrib@
embraer.com.br; Internet http://
approved the incorporation by reference was prompted by the development of a
www.flyembraer.com. of certain publications listed in this AD terminating action (relocation of the
(6) You may view this service information as of October 11, 2017. affected accumulators, and
at the FAA, Transport Standards Branch, The Director of the Federal Register incorporation of new airworthiness
1601 Lind Avenue SW., Renton, WA. For approved the incorporation by reference limitations), which addresses the unsafe
information on the availability of this of certain other publications listed in condition. The NPRM proposed to
material at the FAA, call 425–227–1221. this AD as of March 14, 2011 (76 FR continue to require an inspection to
(7) You may view this service information 6536, February 7, 2011).
nlaroche on DSKBBV9HB2PROD with RULES
determine the number of flight cycles
that is incorporated by reference at the
National Archives and Records
ADDRESSES: For service information accumulated by applicable
Administration (NARA). For information on identified in this final rule, contact accumulators (i.e., brake, aileron,
the availability of this material at NARA, call Viking Air Limited, 1959 de Havilland elevator, and rudder accumulators)
202–741–6030, or go to: http:// Way, Sidney, British Columbia V8L installed on the airplane, repetitive
www.archives.gov/federal-register/cfr/ibr- 5V5, Canada; telephone +1–250–656– ultrasonic inspections of the
locations.html. 7227; fax +1–250–656–0673; email acs- accumulators for cracks, and
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![Federal Register / Vol. 82, No. 171 / Wednesday, September 6, 2017 / Rules and Regulations 42025
replacement of any accumulator in limitations] to this [Canadian] AD. It also • Bombardier Service Bulletin 215–
which a crack is detected. The NPRM modifies the applicability range for the CL– 552, Revision 2, dated June 18, 2015.
also proposed to require a new 215–1A10 (CL–215); the CL–215 is out of
production and the last aeroplane produced
This service information describes
terminating action for the repetitive was serial number 1125. procedures to relocate the aileron
inspections. We are issuing this AD to hydraulic accumulator aft of its current
prevent failure of the screw cap or end You may examine the MCAI in the
location.
cap of certain accumulators, which AD docket on the Internet at http://
www.regulations.gov by searching for • Bombardier Service Bulletin 215–
could result in impact damage to
various components, potentially and locating Docket No. FAA–2017– 3158, Revision 2, dated April 15, 2014;
resulting in fuel spillage, uncommanded 0474. and Bombardier Service Bulletin 215–
flap movement, or loss of aileron 4423, Revision 5, dated March 17, 2016.
Comments
control. This service information describes
Transport Canada Civil Aviation We gave the public the opportunity to procedures to relocate the aileron,
(TCCA), which is the aviation authority participate in developing this AD. We elevator, and rudder hydraulic
for Canada, has issued Canadian received no comments on the NPRM or accumulators aft and outboard of their
Airworthiness Directive CF–2009–42R2, on the determination of the cost to the current locations. These documents are
public. distinct since they apply to different
dated May 30, 2016 (referred to after
this as the Mandatory Continuing Explanation of Changes Made to This airplane models.
Airworthiness Information, or ’’the Final Rule • Bombardier Service Bulletin 215–
MCAI’’), to correct an unsafe condition We have revised this final rule to 557, Revision 1, dated June 27, 2014;
for certain Viking Air Limited Model identify the legal name of the Bombardier Service Bulletin 215–3182,
CL–215–1A10 (CL–215), CL–215–6B11 manufacturer as published in the most Revision 1, dated June 27, 2014; and
(CL–215T Variant), and CL–215–6B11 recent type certificate data sheet for the Bombardier Service Bulletin 215–4470,
(CL–415 Variant) airplanes. The MCAI affected airplane models. Revision 1, dated June 27, 2014. This
states: In the proposed AD, we inadvertently service information describes
Seven cases of on-ground hydraulic listed the wrong publication dates for procedures to establish the number of
accumulator screw cap or end cap failure service information in two places. Table flight hours for each accumulator and
have been experienced on CL–600–2B19 4 to paragraph (o) of the proposed AD
(CRJ) aeroplane, resulting in loss of the
determine if it has been used on another
referred to Bombardier Service Bulletin type of aircraft. These documents are
associated hydraulic system and high-energy 215–4470, Revision 1, dated December
impact damage to adjacent systems and distinct since they apply to different
13, 2013. We have corrected the
structure. To date, the lowest number of airplane models.
flight cycles accumulated at the time of publication date for this document to
June 27, 2014, in this AD. Additionally, • Bombardier Temporary Revision 5–
failure has been 6991.
Although there have been no failures to paragraph (r)(1)(iii) of the proposed AD 56, dated December 13, 2013;
date on any CL–215–1A10 (CL–215) or CL– referred to Bombardier Service Bulletin Bombardier Temporary Revision 295/7,
215–6B11 (CL–215T and CL–415) aeroplane, 215–3158, dated March 28, 2012. We dated December 13, 2013; Bombardier
similar accumulators, Part Number (P/N) 08– have corrected the publication date for Temporary Revision LLC–1, dated
8423–010 (MS28700–3), to those installed on this document to March 21, 2012, in this December 13, 2013; and Bombardier
the CL–600–2B19, are installed on the AD. Temporary Revision LLC–3, dated
aeroplane models listed in the Applicability
section of this [Canadian] AD. Conclusion December 13, 2013. This service
A detailed analysis of the systems and information provides a 10,000-hour
structure in the potential line of trajectory of
We reviewed the available data and accumulator life limitation for certain
a failed screw cap/end cap for each determined that air safety and the accumulators. These documents are
accumulator has been conducted. It has public interest require adopting this AD distinct since they apply to different
identified that the worst-case scenarios with the changes described previously
airplane models.
would be impact damage to various and minor editorial changes. We have
components, potentially resulting in fuel determined that these changes: This service information is reasonably
spillage, uncommanded flap movement, or • Are consistent with the intent that available because the interested parties
loss of aileron control. was proposed in the NPRM for have access to it through their normal
This [Canadian] AD mandates repetitive correcting the unsafe condition; and course of business or by the means
[ultrasonic] inspections of the accumulators • Do not add any additional burden identified in the ADDRESSES section.
for cracks and replacement of any
accumulator in which a crack is detected.
upon the public than was already
proposed in the NPRM. Costs of Compliance
Revision 1 of this [Canadian] AD clarified
the text of the [Canadian] AD, including the Related Service Information Under 1 We estimate that this AD affects 7
P/N of the affected accumulators. CFR Part 51 airplanes of U.S. registry.
This revision provides the terminating
action [relocation of affected accumulators Bombardier, Inc., has issued the We estimate the following costs to
and incorporation of new airworthiness following service information: comply with this AD:
ESTIMATED COSTS
Cost per Cost on U.S.
Action Labor cost Parts cost product operators
nlaroche on DSKBBV9HB2PROD with RULES
Ultrasonic inspection (retained action from 7 work-hours × $85 per hour = $595 ............. $0 $595 $4,165
AD 2011–03–08).
Relocation, determination of accumulator 56 work-hours × $85 per hour = $4,760 ........ 0 4,760 33,320
hours and usage, and maintenance or in-
spection program revision (new action).
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![42026 Federal Register / Vol. 82, No. 171 / Wednesday, September 6, 2017 / Rules and Regulations
We estimate the following costs to do be required based on the results of the determining the number of aircraft that
any necessary replacement that would inspection. We have no way of might need this replacement.
ON-CONDITION COSTS
Cost per
Action Labor cost Parts cost product
Replacement of cracked part (retained action from AD 6 work-hours × $85 per hour = $510 ........................... $4,055 $4,565
2011–03–08).
According to the manufacturer, some For the reasons discussed above, I identified in paragraphs (c)(1) through (c)(3)
of the costs of this AD may be covered certify that this AD: of this AD.
under warranty, thereby reducing the 1. Is not a ‘‘significant regulatory (1) Model CL–215–1A10 (CL–215)
airplanes, serial numbers 1001 through 1125
cost impact on affected individuals. We action’’ under Executive Order 12866;
inclusive.
do not control warranty coverage for 2. Is not a ‘‘significant rule’’ under the (2) Model CL–215–6B11 (CL–215T Variant)
affected individuals. As a result, we DOT Regulatory Policies and Procedures airplanes, serial numbers 1056 through 1125
have included all costs in our cost (44 FR 11034, February 26, 1979); inclusive.
estimate. 3. Will not affect intrastate aviation in (3) Model CL–215–6B11 (CL–415 Variant)
Alaska; and airplanes, serial numbers 2001 through 2990
Authority for This Rulemaking inclusive.
4. Will not have a significant
Title 49 of the United States Code economic impact, positive or negative, (d) Subject
specifies the FAA’s authority to issue on a substantial number of small entities Air Transport Association (ATA) of
rules on aviation safety. Subtitle I, under the criteria of the Regulatory America Code 29, Hydraulic power.
section 106, describes the authority of Flexibility Act.
the FAA Administrator. ‘‘Subtitle VII: (e) Reason
Aviation Programs,’’ describes in more List of Subjects in 14 CFR Part 39 This AD was prompted by reports of on-
detail the scope of the Agency’s Air transportation, Aircraft, Aviation ground hydraulic accumulator screw cap or
authority. safety, Incorporation by reference, end cap failure resulting in a loss of the
We are issuing this rulemaking under Safety. associated hydraulic system and high-energy
impact damage to adjacent systems and
the authority described in ‘‘Subtitle VII, structure. We are issuing this AD to prevent
Adoption of the Amendment
Part A, Subpart III, Section 44701: failure of the screw cap or end cap, which
General requirements.’’ Under that Accordingly, under the authority could result in impact damage to various
section, Congress charges the FAA with delegated to me by the Administrator, components, potentially resulting in fuel
promoting safe flight of civil aircraft in the FAA amends 14 CFR part 39 as spillage, uncommanded flap movement, or
air commerce by prescribing regulations follows: loss of aileron control.
for practices, methods, and procedures (f) Compliance
the Administrator finds necessary for PART 39—AIRWORTHINESS
DIRECTIVES Comply with this AD within the
safety in air commerce. This regulation compliance times specified, unless already
is within the scope of that authority done.
■ 1. The authority citation for part 39
because it addresses an unsafe condition
continues to read as follows: (g) Retained Inspection To Determine Flight
that is likely to exist or develop on
Authority: 49 U.S.C. 106(g), 40113, 44701. Cycles, With No Changes
products identified in this rulemaking
action. This paragraph restates the requirements of
§ 39.13 [Amended] paragraph (g) of AD 2011–03–08, with no
This AD is issued in accordance with
■ 2. The FAA amends § 39.13 by changes. Within 50 flight hours after March
authority delegated by the Executive 14, 2011 (the effective date of AD 2011–03–
Director, Aircraft Certification Service, removing Airworthiness Directive (AD)
08), inspect to determine the number of flight
as authorized by FAA Order 8000.51C. 2011–03–08, Amendment 39–16592 (76 cycles accumulated by each of the applicable
In accordance with that order, issuance FR 6536, February 7, 2011), and adding accumulators (i.e., brake, aileron, elevator,
of ADs is normally a function of the the following new AD: and rudder accumulators) having part
Compliance and Airworthiness 2017–17–17 Viking Air Limited (Type number 08–8423–010 (MS28700–3) installed
Division, but during this transition Certificate Previously Held by on the airplane. A review of airplane
period, the Executive Director has Bombardier, Inc.; Canadair Limited): maintenance records is acceptable in lieu of
Amendment 39–19007; Docket No. this inspection if the number of flight cycles
delegated the authority to issue ADs
FAA–2017–0474; Product Identifier accumulated can be conclusively determined
applicable to transport category from that review.
airplanes to the Director of the System 2016–NM–096–AD.
Oversight Division. (a) Effective Date (h) Retained Initial Ultrasonic Inspection for
Model CL–215–1A10 (CL–215) and CL–215–
Regulatory Findings This AD is effective October 11, 2017. 6B11 (CL–215T Variant) Airplanes, With No
(b) Affected ADs Changes
We determined that this AD will not
have federalism implications under This AD replaces AD 2011–03–08, This paragraph restates the requirements of
paragraph (h) of AD 2011–03–08, with no
nlaroche on DSKBBV9HB2PROD with RULES
Executive Order 13132. This AD will Amendment 39–16592 (76 FR 6536, February
7, 2011) (‘‘AD 2011–03–08’’). changes. For Model CL–215–1A10 (CL–215)
not have a substantial direct effect on
and CL–215–6B11 (CL–215T Variant)
the States, on the relationship between (c) Applicability airplanes: Do an ultrasonic inspection for
the national government and the States, This AD applies to Viking Air Limited cracking of the accumulator at the applicable
or on the distribution of power and (Type Certificate previously held by time specified in paragraph (h)(1) or (h)(2) of
responsibilities among the various Bombardier, Inc.; Canadair Limited) this AD, in accordance with Part B of the
levels of government. airplanes, certificated in any category, as Accomplishment Instructions of the
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![Federal Register / Vol. 82, No. 171 / Wednesday, September 6, 2017 / Rules and Regulations 42029
Havilland Way, Sidney, British Columbia and locating Docket No. FAA–2017– replace a single long spacer, repetitive
V8L 5V5, Canada; telephone +1–250–656– 0638; or in person at Document inspections of the flap bell crank, and,
7227; fax +1–250–656–0673; email acs- Management Facility, U.S. Department depending on findings, replacement of the
technical.publications@vikingair.com; flap bell crank with an improved part.
of Transportation, Docket Operations, Installation of an improved flap bell crank
Internet http://www.vikingair.com.
(6) You may view this service information M–30, West Building Ground Floor, constitutes terminating action for the
at the FAA, Transport Standards Branch, Room W12–140, 1200 New Jersey repetitive inspections required by this
1601 Lind Avenue SW., Renton, WA. For Avenue SE., Washington, DC 20590. [EASA] AD.
information on the availability of this For service information identified in
The MCAI can be found in the AD
material at the FAA, call 425–227–1221. this AD, contact Diamond Aircraft
docket on the Internet at https://
(7) You may view this service information Industries GmbH, N.A. Otto-Stra+e 5,
that is incorporated by reference at the www.regulations.gov/
A–2700 Wiener Neustadt, Austria, document?D=FAA-2017-0638-0002.
National Archives and Records telephone: +43 2622 26700; fax: +43
Administration (NARA). For information on 2622 26780; email: office@diamond- Comments
the availability of this material at NARA, call
202–741–6030, or go to: http://
air.at; Internet: http:// We gave the public the opportunity to
www.archives.gov/federal-register/cfr/ibr- www.diamondaircraft.com. You may participate in developing this AD. We
locations.html. view this referenced service information received no comments on the NPRM or
at the FAA, Policy and Innovation on the determination of the cost to the
Issued in Renton, Washington, on August
16, 2017.
Division, 901 Locust, Kansas City, public.
Missouri 64106. For information on the
Jeffrey E. Duven, Conclusion
availability of this material at the FAA,
Director, System Oversight Division, Aircraft call (816) 329–4148. It is also available We reviewed the relevant data and
Certification Service.
on the Internet at http:// determined that air safety and the
[FR Doc. 2017–17838 Filed 9–5–17; 8:45 am]
www.regulations.gov by searching for public interest require adopting this AD
BILLING CODE 4910–13–P Docket No. FAA–2017–0638. as proposed except for minor editorial
FOR FURTHER INFORMATION CONTACT: changes. We have determined that these
Mike Kiesov, Aerospace Engineer, FAA, minor changes:
DEPARTMENT OF TRANSPORTATION • Are consistent with the intent that
Small Airplane Standards Branch, 901
Federal Aviation Administration Locust, Room 301, Kansas City, was proposed in the NPRM for
Missouri 64106; telephone: (816) 329– correcting the unsafe condition; and
4144; fax: (816) 329–4090; email: • Do not add any additional burden
14 CFR Part 39
mike.kiesov@faa.gov. upon the public than was already
[Docket No. FAA–2017–0638; Product
SUPPLEMENTARY INFORMATION:
proposed in the NPRM.
Identifier 2017–CE–018–AD; Amendment
39–19019; AD 2017–18–10] Discussion Related Service Information Under 1
CFR Part 51
RIN 2120–AA64 We issued a notice of proposed
rulemaking (NPRM) to amend 14 CFR We reviewed Diamond Aircraft
Airworthiness Directives; Diamond part 39 by adding an AD that would Industries GmbH Mandatory Service
Aircraft Industries GmbH Airplanes apply to certain Diamond Aircraft Bulletin MSB 42–126 MSB/42NG–066,
Industries GmbH Models DA 42, DA 42 dated March 27, 2017 (single
AGENCY: Federal Aviation document), and Work Instruction WI–
Administration (FAA), Department of M–NG, and DA 42 NG airplanes. The
NPRM was published in the Federal MSB 42–126/WI–MSB 42NG–066, dated
Transportation (DOT). March 27, 2017 (single document). In
ACTION: Final rule.
Register on June 23, 2017 (82 FR 28594).
The NPRM proposed to correct an combination, this service information
unsafe condition for the specified describes procedures for repetitively
SUMMARY: We are adopting a new
products and was based on mandatory inspecting the flap bell crank for cracks,
airworthiness directive (AD) for certain
continuing airworthiness information replacing the flap bell crank if cracks are
Diamond Aircraft Industries GmbH
(MCAI) originated by an aviation found, and modification of the flap
Models DA 42, DA 42 M–NG, and DA
authority of another country. The MCAI control system. This service information
42 NG airplanes. This AD results from
states: is reasonably available because the
mandatory continuing airworthiness
interested parties have access to it
information (MCAI) issued by an Cracks and deformation have been found through their normal course of business
aviation authority of another country to on the flap bell crank Part Number (P/N)
or by the means identified in the
identify and correct an unsafe condition D60–2757–11–00. Frequent high load
conditions have been identified as the root ADDRESSES section of this AD.
on an aviation product. The MCAI
describes the unsafe condition as crack cause. Costs of Compliance
formation on the flap bell crank, which This condition, if not detected and
corrected, could lead to failure of the flap We estimate that this AD will affect
could cause the flap bell crank to fail. 190 products of U.S. registry. We also
bell crank and consequent reduced control of
We are issuing this AD to require the aeroplane. estimate that it will take about 4 work-
actions to address the unsafe condition To address this potential unsafe condition, hours per product to comply with the
on these products. Diamond Aircraft Industries (DAI) issued initial inspection requirement of this
DATES: This AD is effective October 11, Mandatory Service Bulletin (MSB) 42–126/ AD. The average labor rate is $85 per
2017. MSB 42NG–066 and the corresponding Work work-hour.
Instruction (WI) MSB 42–126/WI–MSB
nlaroche on DSKBBV9HB2PROD with RULES
The Director of the Federal Register Based on these figures, we estimate
approved the incorporation by reference 42NG–066 (single document), hereafter
referred to as ‘the applicable MSB’ in this
the cost of the initial inspection
of certain publications listed in this AD requirement of this AD on U.S.
[EASA] AD, providing inspection and
as of October 11, 2017. modification instructions. operators to be $64,000, or $340 per
ADDRESSES: You may examine the AD For the reason described above, this product.
docket on the Internet at http:// [EASA] AD requires modification of the flap We also estimate that it will take
www.regulations.gov by searching for control system by installing two spacers to about 2 work-hours per product to
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Document Created: 2017-09-06 00:56:49
Document Modified: 2017-09-06 00:56:49
| Category | Regulatory Information | |
| Collection | Federal Register | |
| sudoc Class | AE 2.7: GS 4.107: AE 2.106: | |
| Publisher | Office of the Federal Register, National Archives and Records Administration | |
| Section | Rules and Regulations | |
| Action | Final rule. | |
| Dates | This AD is effective October 11, 2017. | |
| Contact | Cesar A. Gomez, Aerospace Engineer, Airframe and Mechanical Systems Section, FAA, New York ACO Branch, 1600 Stewart Avenue, Suite 410, Westbury, NY 11590; telephone 516-228-7318; fax 516-794-5531. | |
| FR Citation | 82 FR 42024 | |
| RIN Number | 2120-AA64 | |
| CFR Associated | Air Transportation; Aircraft; Aviation Safety; Incorporation by Reference and Safety |
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