Airworthiness Directives; Bombardier, Inc., Airplanes, 43829-43832 [2017-19660]

Download as PDF sradovich on DSKBBY8HB2PROD with RULES Federal Register / Vol. 82, No. 181 / Wednesday, September 20, 2017 / Rules and Regulations conditions or 5 minutes each under AEO conditions in any one flight, for a maximum accumulated usage of 20 minutes in any one flight. Each flight where the ‘‘Rated TOTHAT’’ is used must be followed by mandatory inspection and maintenance actions.’’ (iii) As required by § 33.5(b), Operating instructions, include a note stating that ‘‘the engine thrust control system automatically resets the thrust on the operating engine to the ‘‘Rated TOTHAT’’ level when one engine fails during takeoff at specified altitudes and temperatures, and the ‘‘Rated TOTHAT’’ is available by manual selection when all engines are operational during takeoff at specified altitudes and temperatures.’’ (d) Section 33.28, Engine Control Systems. The engine must incorporate a means, or a provision for a means, for automatic availability and automatic control of the ‘‘Rated TOTHAT’’ under OEI conditions and must permit manual activation of the ‘‘Rated TOTHAT’’ under AEO conditions. (e) Section 33.29, Instrument connection. The engine must: (1) Have means, or provisions for means, to alert the pilot when the ‘‘Rated TOTHAT’’ is in use, when the event begins and when the time interval expires. (2) Have means, or provision for means, which cannot be reset in flight, to: (i) Automatically record each use and duration of the ‘‘Rated TOTHAT’’, and (ii) Alert maintenance personnel that the engine has been operated at the ‘‘Rated TOTHAT’’ and permit retrieval of recorded data. (3) Have means, or provision for means, to enable routine verification of the proper operation of the means in paragraph 2(e)(1) and (e)(2) of these special conditions. (f) Section 33.85(b), Calibration tests. The applicant must base the calibration test on the thrust check at the end of the endurance test required by § 33.87 of these special conditions. (g) Section 33.87, Endurance test. (1) In addition to the applicable requirements of § 33.87(a): (i) The § 33.87 endurance test must be modified as follows: (A) Modify the 30 minute test cycle at the rated takeoff thrust in § 33.87(b)(2)(ii) to run one minute at rated takeoff thrust, followed by five minutes at the ‘‘Rated TOTHAT’’, followed by the rated takeoff thrust for the remaining twenty-four minutes. (B) The modified 30 minute period described above in paragraph VerDate Sep<11>2014 17:10 Sep 19, 2017 Jkt 241001 2(g)(1)(i)(A) must be repeated ten times in cycles 16 through 25 of the § 33.87 endurance test. (2) After completion of the tests required by § 33.87(b), as modified in paragraph 2(g)(1)(i) above, and without intervening disassembly, except as needed to replace those parts described as consumables in the ICA, the applicant must conduct the following test sequence for a total time of not less than 120 minutes: (i) Ten minutes at ‘‘Rated TOTHAT’’. (ii) Eighty-eight minutes at rated maximum continuous thrust. (iii) One minute at 50 percent of rated takeoff thrust. (iv) Ten minutes at ‘‘Rated TOTHAT’’. (v) Ten minutes at rated maximum continuous thrust. (vi) One minute at flight idle. (3) The test sequence of §§ 33.87(b)(1) through (b)(6) of these special conditions must be run continuously. If a stop occurs during these tests, the interrupted sequence must be repeated unless the applicant shows that the severity of the test would not be reduced if the current tests were continued. (4) Where the engine characteristics are such that acceleration to the ‘‘Rated TOTHAT’’ results in a transient over temperature in excess of the steady-state temperature limit identified in paragraph 2(c)(1)(iii) of these special conditions, the transient gas over temperature must be applied to each acceleration to the ‘‘Rated TOTHAT’’ of the test sequence in paragraph 2(g)(2) of these special conditions. (h) Section 33.93, Teardown inspection. The applicant must perform the teardown inspection required by § 33.93(a), after completing the endurance test prescribed by § 33.87 of these special conditions. (i) Section 33.201, Design and test requirements for Early ETOPS eligibility. In addition to the requirements of § 33.201(c)(1), the simulated ETOPS mission cyclic endurance test must include two cycles of 10 minute duration, each at the ‘‘Rated TOTHAT’’; one before the last diversion cycle and one at the end of the ETOPS test. Issued in Burlington, Massachusetts on August 23, 2017. Karen M. Grant Acting Manager, Engine and Propeller Standards Branch, Aircraft Certification Service. [FR Doc. 2017–19952 Filed 9–19–17; 8:45 am] BILLING CODE 4910–13–P PO 00000 Frm 00003 Fmt 4700 Sfmt 4700 43829 DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2017–0334; Product Identifier 2017–NM–008–AD; Amendment 39–19039; AD 2017–19–09] RIN 2120–AA64 Airworthiness Directives; Bombardier, Inc., Airplanes Federal Aviation Administration (FAA), Department of Transportation (DOT). ACTION: Final rule. AGENCY: We are superseding Airworthiness Directive (AD) 2014–25– 01, which applied to certain Bombardier, Inc., Model DHC–8–400 series airplanes. AD 2014–25–01 required modifying the nose landing gear (NLG) trailing arm and installing a new pivot pin retention mechanism. This AD instead requires modifying the NLG shock strut assembly. This AD was prompted by reports of discrepancies of a certain bolt at the pivot pin link, resulting in corrosion of the bolt. We are issuing this AD to address the unsafe condition on these products. DATES: This AD is effective October 24, 2017. The Director of the Federal Register approved the incorporation by reference of a certain publication listed in this AD as of October 24, 2017. ADDRESSES: For service information identified in this final rule, contact Bombardier, Inc., Q-Series Technical Help Desk, 123 Garratt Boulevard, Toronto, Ontario M3K 1Y5, Canada; telephone 416–375–4000; fax 416–375– 4539; email thd.qseries@ aero.bombardier.com; Internet http:// www.bombardier.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–2017–0334. SUMMARY: 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– 0334; 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 E:\FR\FM\20SER1.SGM 20SER1 43830 Federal Register / Vol. 82, No. 181 / Wednesday, September 20, 2017 / Rules and Regulations 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: Fabio Buttitta, Aerospace Engineer, Airframe and Mechanical Systems Section, FAA, New York ACO Branch, 1600 Stewart Avenue, Suite 410, Westbury, NY 11590; telephone 516– 228–7303; fax 516–794–5531. SUPPLEMENTARY INFORMATION: Discussion sradovich on DSKBBY8HB2PROD with RULES We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR part 39 to supersede AD 2014–25–01, Amendment 39–18042 (79 FR 73808, December 12, 2014) (‘‘AD 2014–25– 01’’). AD 2014–25–01 applied to certain Bombardier, Inc., Model DHC–8–400 series airplanes. The NPRM published in the Federal Register on May 9, 2017 (82 FR 21484). The NPRM was prompted by reports of discrepancies of a certain bolt at the pivot pin link, resulting in corrosion of the bolt. The NPRM proposed to require modifying the NLG shock strut assembly. We are issuing this AD to prevent failure of the pivot pin retention bolt, which could result in a loss of directional control or loss of an NLG tire during takeoff or landing. Transport Canada Civil Aviation (TCCA), which is the aviation authority for Canada, has issued Canadian Airworthiness Directive CF–2009–29R2, dated December 21, 2016 (referred to after this as the Mandatory Continuing Airworthiness Information, or ‘‘the MCAI’’), to correct an unsafe condition for certain Bombardier, Inc., Model DHC–8–400 series airplanes. The MCAI states: Two in-service incidents have been reported on DHC–8 Series 400 aircraft in which the nose landing gear (NLG) trailing arm pivot pin retention bolt (part number NAS6204–13D) was damaged. One incident involved the left hand NLG tire which ruptured on take-off. Investigation determined that the retention bolt failure was due to repeated contact of the castellated nut with the towing device including both the towbar and the towbarless rigs. The loss of the retention bolt allowed the pivot pin to migrate from its normal position and resulted in contact with and rupture of the tire. The loss of the pivot pin could compromise retention of the trailing arm and could result in a loss of directional control due to loss of nose wheel steering. The loss of an NLG tire or the loss of directional control could VerDate Sep<11>2014 17:10 Sep 19, 2017 Jkt 241001 adversely affect the aircraft during take-off or landing. To prevent the potential failure of the pivot pin retention bolt, Bombardier Aerospace has developed a modification which includes a new retention bolt, a reverse orientation of the retention bolt and a rework of the weight on wheel (WOW) proximity sensor cover to provide clearance for the re-oriented retention bolt. Since the original issue of this [Canadian] AD [which corresponds to AD 2010–13–04, Amendment 39–16335 (75 FR 35622, June 23, 2010)], there have been several reports of pivot pin retention bolts found missing or damaged. Additional investigation determined that the failures were caused by high contact stresses on the retention bolt due to excessive frictional torque on the pivot pin and an adverse tolerance condition at the retention bolt. Revision 1 of this [Canadian] AD mandated the installation of a new pivot pin retention mechanism. Since the issuance of Revision 1 of this [Canadian] AD, there have been reports of chrome peeling on special bolt part number 47205–1 at the pivot pin link resulting in corrosion of the bolt substrate layer. Revision 2 of this [Canadian] AD mandates the installation of new special bolt part number 47205–3 with additional processing for increased chrome plating adhesion on aeroplanes equipped with nose landing gear shock strut assembly part number 47100–19 or any assembly with Bombardier (BA) Service Bulletin (SB) 84–32–110 incorporated. In addition, Revision 2 of this [Canadian] AD mandates the installation of a new pivot pin retention mechanism that includes new special bolt part number 47205–3 on aeroplanes equipped with nose landing gear shock strut assembly part number 47100–9, 47100–11, 47100–13, 47100–15, or 47100–17 without BA SB 84– 32–110 incorporated. The corrective actions of Revision 2 of this [Canadian] AD cancel and replace the corrective actions of Revision 1 of this [Canadian] AD. 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– 0334. Comments We gave the public the opportunity to participate in developing this AD. The following presents the comments received on the NPRM and the FAA’s response to each comment. Support for the NPRM The Air Line Pilots Association, International concurred with the intent of the NPRM. Request To Exclude Setup and Closeout Sections Horizon Air asked that we revise paragraph (g) of the proposed AD to exclude the ‘‘Job Set-up’’ and ‘‘Close Out’’ sections of Bombardier Service PO 00000 Frm 00004 Fmt 4700 Sfmt 4700 Bulletin 84–32–145, Revision A, dated October 18, 2016. Horizon Air stated that incorporating those sections as a requirement of the AD restricts an operator’s ability to perform other maintenance in conjunction with incorporation of the referenced service information. We agree with the commenter’s request for the reason provided. We have revised paragraph (g) of this AD to require accomplishment of only paragraph 3.B., ‘‘Procedure’’ of the Accomplishment Instructions of Bombardier Service Bulletin 84–32–145, Revision A, dated October 18, 2016. Conclusion We reviewed the relevant data, considered the comments received, and determined that air safety and the public interest require adopting this AD with the change described previously and minor editorial changes. We have determined that these minor changes: • Are consistent with the intent that was proposed in the NPRM for correcting the unsafe condition; and • Do not add any additional burden upon the public than was already proposed in the NPRM. We also determined that these changes will not increase the economic burden on any operator or increase the scope of this AD. Related Service Information Under 1 CFR Part 51 Bombardier, Inc., has issued Bombardier Service Bulletin 84–32–145, Revision A, dated October 18, 2016. The service information describes procedures for modifying the NLG shock strut assembly by installing a new, improved pivot pin retention mechanism and a new retention bolt. 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 52 airplanes of U.S. registry. We also estimate that it takes about 2 work-hours per product to comply with the basic requirements of this AD. The average labor rate is $85 per work-hour. Required parts will cost about $0 per product. Based on these figures, we estimate the cost of this AD on U.S. operators to be $8,840, or $170 per product. Authority for This Rulemaking Title 49 of the United States Code specifies the FAA’s authority to issue rules on aviation safety. Subtitle I, E:\FR\FM\20SER1.SGM 20SER1 Federal Register / Vol. 82, No. 181 / Wednesday, September 20, 2017 / Rules and Regulations 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. sradovich on DSKBBY8HB2PROD with RULES 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: VerDate Sep<11>2014 17:10 Sep 19, 2017 Jkt 241001 PART 39—AIRWORTHINESS DIRECTIVES 1. The authority citation for part 39 continues to read as follows: ■ Authority: 49 U.S.C. 106(g), 40113, 44701. § 39.13 [Amended] 2. The FAA amends § 39.13 by removing Airworthiness Directive (AD) 2014–25–01, Amendment 39–18042 (79 FR 73808, December 12, 2014), and adding the following new AD: ■ 2017–19–09 Bombardier, Inc.: Amendment 39–19039; Docket No. FAA–2017–0334; Product Identifier 2017–NM–008–AD. (a) Effective Date This AD is effective October 25, 2017. (b) Affected ADs This AD replaces AD 2014–25–01, Amendment 39–18042 (79 FR 73808, December 12, 2014). (c) Applicability This AD applies to Bombardier, Inc., Model DHC–8–400, –401, and –402 airplanes, certificated in any category, serial numbers 4001, 4003 through 4533 inclusive, and 4535, equipped with any nose landing gear (NLG) shock strut assembly having part number 47100–9, 47100–11, 47100–13, 47100–15, 47100–17, or 47100–19. (d) Subject Air Transport Association (ATA) of America Code 32, Landing Gear. (e) Reason This AD was prompted by reports of discrepancies of a certain bolt at the pivot pin link, resulting in corrosion of the bolt. We are issuing this AD to prevent failure of the pivot pin retention bolt, which could result in a loss of directional control or loss of an NLG tire during takeoff or landing. (f) Compliance Comply with this AD within the compliance times specified, unless already done. (g) Installation of Improved Pivot Pin Retention Mechanism and Bolt Within 6,000 flight hours or 36 months after the effective date of this AD, whichever occurs first: Install a new pivot pin retention mechanism to the NLG shock strut assembly, and replace the existing pivot pin retention bolt with a new bolt, in accordance with paragraph 3.B., ‘‘Procedure,’’ of the Accomplishment Instructions of Bombardier Service Bulletin 84–32–145, Revision A, dated October 18, 2016. (h) Credit for Previous Actions This paragraph provides credit for actions required by paragraph (g) of this AD, if those actions were performed before the effective date of this AD using Bombardier Service Bulletin 84–32–145, dated July 26, 2016. PO 00000 Frm 00005 Fmt 4700 Sfmt 4700 43831 (i) 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: As of the effective date of this AD, for any requirement in this AD to obtain corrective actions from a manufacturer, the action must be accomplished using a method approved by the Manager, New York ACO Branch, 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 DAOauthorized signature. (j) Related Information (1) Refer to Mandatory Continuing Airworthiness Information (MCAI) Canadian Airworthiness Directive CF–2009–29R2, dated December 21, 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–2017–0334. (2) For more information about this AD, contact Fabio Buttitta, Aerospace Engineer, Airframe and Mechanical Systems Section, FAA, New York ACO Branch, 1600 Stewart Avenue, Suite 410, Westbury, NY 11590; telephone 516–228–7303; 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 (k)(3) and (k)(4) of this AD. (k) 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. (i) Bombardier Service Bulletin 84–32–145, Revision A, dated October 18, 2016. (ii) Reserved. (3) For service information identified in this AD, contact Bombardier, Inc., Q-Series Technical Help Desk, 123 Garratt Boulevard, Toronto, Ontario M3K 1Y5, Canada; telephone 416–375–4000; fax 416–375–4539; email thd.qseries@aero.bombardier.com; Internet http://www.bombardier.com. (4) You may view this service information at the FAA, Transport Standards Branch, E:\FR\FM\20SER1.SGM 20SER1 43832 Federal Register / Vol. 82, No. 181 / Wednesday, September 20, 2017 / Rules and Regulations 1601 Lind Avenue SW., Renton, WA. For information on the availability of this material at the FAA, call 425–227–1221. (5) 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/ibrlocations.html. Issued in Renton, Washington, on September 7, 2017. Jeffrey E. Duven, Director, System Oversight Division, Aircraft Certification Service. [FR Doc. 2017–19660 Filed 9–19–17; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2017–0555; Product Identifier 2016–NM–183–AD; Amendment 39–19037; AD 2017–19–07] Examining the AD Docket RIN 2120–AA64 Airworthiness Directives; Airbus Defense and Space S.A. (Formerly Known as Construcciones Aeronauticas, S.A.) Airplanes Federal Aviation Administration (FAA), Department of Transportation (DOT). ACTION: Final rule. AGENCY: We are superseding Airworthiness Directive (AD) 2013–02– 12, which applied to all EADS CASA (now Airbus Defense and Space S.A.) Model CN–235, CN–235–100, CN–235– 200, and CN–235–300 airplanes. AD 2013–02–12 required a one-time inspection to identify the correct polarity for each pair of electrical connectors on each engine fire extinguisher cartridge, and repair if necessary. This AD continues to require identifying the correct polarity of each pair of electrical connectors of the affected engine fire extinguisher cartridge, and doing a repair if necessary. This AD also requires modifying the installation of the fire extinguisher circuit harnesses. This AD was prompted by reports of incorrect electrical polarity connections on engine fire extinguishing discharge cartridges. We are issuing this AD to address the unsafe condition on these products. sradovich on DSKBBY8HB2PROD with RULES SUMMARY: This AD is effective October 25, 2017. The Director of the Federal Register approved the incorporation by reference DATES: VerDate Sep<11>2014 17:10 Sep 19, 2017 Jkt 241001 of certain publications listed in this AD as of October 25, 2017. The Director of the Federal Register approved the incorporation by reference of a certain other publication listed in this AD as of March 8, 2013 (78 FR 7262, February 1, 2013). ADDRESSES: For service information identified in this final rule, contact Airbus Defense and Space Services/ Engineering Support, Avenida de ´ Aragon 404, 28022 Madrid, Spain; telephone +34 91 585 55 84; fax +34 91 585 31 27; email MTA.TechnicalService@airbus.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– 0555. You may examine the AD docket on the Internet at http:// www.regulations.gov by searching for and locating Docket No. FAA–2017– 0555; 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: Shahram Daneshmandi, Aerospace Engineer, International Section, Transport Standards Branch, FAA, 1601 Lind Avenue SW., Renton, WA 98057– 3356; telephone 425–227–1112; fax 425–227–1149. SUPPLEMENTARY INFORMATION: Discussion We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR part 39 to supersede AD 2013–02–12, Amendment 39–17333 (78 FR 7262, February 1, 2013) (‘‘AD 2013–02–12’’). AD 2013–02–12 applied to all EADS CASA (now Airbus Defense and Space S.A.) Model CN–235, CN–235–100, CN– 235–200, and CN–235–300 airplanes. The NPRM published in the Federal Register on June 16, 2017 (82 FR 27631). The NPRM was prompted by reports of incorrect electrical polarity connections PO 00000 Frm 00006 Fmt 4700 Sfmt 4700 on engine fire extinguishing discharge cartridges. The NPRM proposed to continue to require identifying the correct polarity of each pair of electrical connectors of the affected engine fire extinguisher cartridge, and doing a repair if necessary. The NPRM also proposed to require modifying the installation of the fire extinguisher circuit harnesses. We are issuing this AD to detect and correct incorrect polarity connections, which could prevent the actuation of the discharge cartridge in case of automatic fire detection or manual initiation during a potential engine fire, and could result in damage to the airplane and injury to passengers. The European Aviation Safety Agency (EASA), which is the Technical Agent for the Member States of the European Union, has issued EASA AD 2016–0201, dated October 11, 2016 (referred to after this as the Mandatory Continuing Airworthiness Information, or ‘‘the MCAI’’), to correct an unsafe condition for all Airbus Defense and Space S.A. Model CN–235, CN–235–100, CN–235– 200, and CN–235–300 airplanes. The MCAI states: Reports have been received of finding wrong electrical polarity connections of engine fire extinguishing discharge cartridges on CASA CN–235 aeroplanes. The results of the subsequent investigation showed that the incorrect discharge cartridge assembly was caused by production line errors. This condition, if not detected and corrected, could prevent the actuation of the discharge cartridge in case of automatic fire detection or manual initiation in case of engine fire, possibly resulting in damage to the aeroplane and injury to occupants. To address this potentially unsafe condition, EADS CASA (Airbus Military) developed instructions to identify erroneous wiring polarity installation and EASA issued AD 2012–0045 [which correlates to FAA AD 2013–02–12, Amendment 39–17333 (78 FR 7262, February 1, 2013)] to require a one-time inspection to verify proper electrical polarity of wiring of each engine fire extinguisher discharge cartridge and, depending on findings, corrective action. Since [EASA] AD 2012–0045 was issued, Airbus Defence and Space (D&S) developed modification of the installation of the fire extinguisher circuit harnesses, available for in-service installation through Service Bulletin (SB) SB–235–26–0005, which represents technical solution for an unsafe condition addressed by [EASA] AD 2012– 0045 for those aeroplanes. Embodiment of this modification introduces a design solution that avoids maintenance errors during (re)connecting of the affected fire extinguisher circuit harnesses after accomplishment of maintenance tasks or functional tests. For the reasons described above, this [EASA] AD retains the requirements of EASA AD 2012–0045, which is superseded and E:\FR\FM\20SER1.SGM 20SER1

Agencies

[Federal Register Volume 82, Number 181 (Wednesday, September 20, 2017)]
[Rules and Regulations]
[Pages 43829-43832]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2017-19660]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2017-0334; Product Identifier 2017-NM-008-AD; Amendment 
39-19039; AD 2017-19-09]
RIN 2120-AA64


Airworthiness Directives; Bombardier, Inc., Airplanes

AGENCY: Federal Aviation Administration (FAA), Department of 
Transportation (DOT).

ACTION: Final rule.

-----------------------------------------------------------------------

SUMMARY: We are superseding Airworthiness Directive (AD) 2014-25-01, 
which applied to certain Bombardier, Inc., Model DHC-8-400 series 
airplanes. AD 2014-25-01 required modifying the nose landing gear (NLG) 
trailing arm and installing a new pivot pin retention mechanism. This 
AD instead requires modifying the NLG shock strut assembly. This AD was 
prompted by reports of discrepancies of a certain bolt at the pivot pin 
link, resulting in corrosion of the bolt. We are issuing this AD to 
address the unsafe condition on these products.

DATES: This AD is effective October 24, 2017.
    The Director of the Federal Register approved the incorporation by 
reference of a certain publication listed in this AD as of October 24, 
2017.

ADDRESSES: For service information identified in this final rule, 
contact Bombardier, Inc., Q-Series Technical Help Desk, 123 Garratt 
Boulevard, Toronto, Ontario M3K 1Y5, Canada; telephone 416-375-4000; 
fax 416-375-4539; email thd.qseries@aero.bombardier.com; Internet 
http://www.bombardier.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-2017-0334.

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-
0334; 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

[[Page 43830]]

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: Fabio Buttitta, Aerospace Engineer, 
Airframe and Mechanical Systems Section, FAA, New York ACO Branch, 1600 
Stewart Avenue, Suite 410, Westbury, NY 11590; telephone 516-228-7303; 
fax 516-794-5531.

SUPPLEMENTARY INFORMATION: 

Discussion

    We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR 
part 39 to supersede AD 2014-25-01, Amendment 39-18042 (79 FR 73808, 
December 12, 2014) (``AD 2014-25-01''). AD 2014-25-01 applied to 
certain Bombardier, Inc., Model DHC-8-400 series airplanes. The NPRM 
published in the Federal Register on May 9, 2017 (82 FR 21484). The 
NPRM was prompted by reports of discrepancies of a certain bolt at the 
pivot pin link, resulting in corrosion of the bolt. The NPRM proposed 
to require modifying the NLG shock strut assembly. We are issuing this 
AD to prevent failure of the pivot pin retention bolt, which could 
result in a loss of directional control or loss of an NLG tire during 
takeoff or landing.
    Transport Canada Civil Aviation (TCCA), which is the aviation 
authority for Canada, has issued Canadian Airworthiness Directive CF-
2009-29R2, dated December 21, 2016 (referred to after this as the 
Mandatory Continuing Airworthiness Information, or ``the MCAI''), to 
correct an unsafe condition for certain Bombardier, Inc., Model DHC-8-
400 series airplanes. The MCAI states:

    Two in-service incidents have been reported on DHC-8 Series 400 
aircraft in which the nose landing gear (NLG) trailing arm pivot pin 
retention bolt (part number NAS6204-13D) was damaged. One incident 
involved the left hand NLG tire which ruptured on take-off. 
Investigation determined that the retention bolt failure was due to 
repeated contact of the castellated nut with the towing device 
including both the towbar and the towbarless rigs. The loss of the 
retention bolt allowed the pivot pin to migrate from its normal 
position and resulted in contact with and rupture of the tire. The 
loss of the pivot pin could compromise retention of the trailing arm 
and could result in a loss of directional control due to loss of 
nose wheel steering. The loss of an NLG tire or the loss of 
directional control could adversely affect the aircraft during take-
off or landing.
    To prevent the potential failure of the pivot pin retention 
bolt, Bombardier Aerospace has developed a modification which 
includes a new retention bolt, a reverse orientation of the 
retention bolt and a rework of the weight on wheel (WOW) proximity 
sensor cover to provide clearance for the re-oriented retention 
bolt.
    Since the original issue of this [Canadian] AD [which 
corresponds to AD 2010-13-04, Amendment 39-16335 (75 FR 35622, June 
23, 2010)], there have been several reports of pivot pin retention 
bolts found missing or damaged. Additional investigation determined 
that the failures were caused by high contact stresses on the 
retention bolt due to excessive frictional torque on the pivot pin 
and an adverse tolerance condition at the retention bolt.
    Revision 1 of this [Canadian] AD mandated the installation of a 
new pivot pin retention mechanism.
    Since the issuance of Revision 1 of this [Canadian] AD, there 
have been reports of chrome peeling on special bolt part number 
47205-1 at the pivot pin link resulting in corrosion of the bolt 
substrate layer.
    Revision 2 of this [Canadian] AD mandates the installation of 
new special bolt part number 47205-3 with additional processing for 
increased chrome plating adhesion on aeroplanes equipped with nose 
landing gear shock strut assembly part number 47100-19 or any 
assembly with Bombardier (BA) Service Bulletin (SB) 84-32-110 
incorporated. In addition, Revision 2 of this [Canadian] AD mandates 
the installation of a new pivot pin retention mechanism that 
includes new special bolt part number 47205-3 on aeroplanes equipped 
with nose landing gear shock strut assembly part number 47100-9, 
47100-11, 47100-13, 47100-15, or 47100-17 without BA SB 84-32-110 
incorporated. The corrective actions of Revision 2 of this 
[Canadian] AD cancel and replace the corrective actions of Revision 
1 of this [Canadian] AD.

    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-
0334.

Comments

    We gave the public the opportunity to participate in developing 
this AD. The following presents the comments received on the NPRM and 
the FAA's response to each comment.

Support for the NPRM

    The Air Line Pilots Association, International concurred with the 
intent of the NPRM.

Request To Exclude Setup and Closeout Sections

    Horizon Air asked that we revise paragraph (g) of the proposed AD 
to exclude the ``Job Set-up'' and ``Close Out'' sections of Bombardier 
Service Bulletin 84-32-145, Revision A, dated October 18, 2016. Horizon 
Air stated that incorporating those sections as a requirement of the AD 
restricts an operator's ability to perform other maintenance in 
conjunction with incorporation of the referenced service information.
    We agree with the commenter's request for the reason provided. We 
have revised paragraph (g) of this AD to require accomplishment of only 
paragraph 3.B., ``Procedure'' of the Accomplishment Instructions of 
Bombardier Service Bulletin 84-32-145, Revision A, dated October 18, 
2016.

Conclusion

    We reviewed the relevant data, considered the comments received, 
and determined that air safety and the public interest require adopting 
this AD with the change described previously and minor editorial 
changes. We have determined that these minor changes:
     Are consistent with the intent that was proposed in the 
NPRM for correcting the unsafe condition; and
     Do not add any additional burden upon the public than was 
already proposed in the NPRM.
    We also determined that these changes will not increase the 
economic burden on any operator or increase the scope of this AD.

Related Service Information Under 1 CFR Part 51

    Bombardier, Inc., has issued Bombardier Service Bulletin 84-32-145, 
Revision A, dated October 18, 2016. The service information describes 
procedures for modifying the NLG shock strut assembly by installing a 
new, improved pivot pin retention mechanism and a new retention bolt. 
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 52 airplanes of U.S. registry.
    We also estimate that it takes about 2 work-hours per product to 
comply with the basic requirements of this AD. The average labor rate 
is $85 per work-hour. Required parts will cost about $0 per product. 
Based on these figures, we estimate the cost of this AD on U.S. 
operators to be $8,840, or $170 per product.

Authority for This Rulemaking

    Title 49 of the United States Code specifies the FAA's authority to 
issue rules on aviation safety. Subtitle I,

[[Page 43831]]

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) 
2014-25-01, Amendment 39-18042 (79 FR 73808, December 12, 2014), and 
adding the following new AD:

2017-19-09 Bombardier, Inc.: Amendment 39-19039; Docket No. FAA-
2017-0334; Product Identifier 2017-NM-008-AD.

(a) Effective Date

    This AD is effective October 25, 2017.

(b) Affected ADs

    This AD replaces AD 2014-25-01, Amendment 39-18042 (79 FR 73808, 
December 12, 2014).

(c) Applicability

    This AD applies to Bombardier, Inc., Model DHC-8-400, -401, and 
-402 airplanes, certificated in any category, serial numbers 4001, 
4003 through 4533 inclusive, and 4535, equipped with any nose 
landing gear (NLG) shock strut assembly having part number 47100-9, 
47100-11, 47100-13, 47100-15, 47100-17, or 47100-19.

(d) Subject

    Air Transport Association (ATA) of America Code 32, Landing 
Gear.

(e) Reason

    This AD was prompted by reports of discrepancies of a certain 
bolt at the pivot pin link, resulting in corrosion of the bolt. We 
are issuing this AD to prevent failure of the pivot pin retention 
bolt, which could result in a loss of directional control or loss of 
an NLG tire during takeoff or landing.

(f) Compliance

    Comply with this AD within the compliance times specified, 
unless already done.

(g) Installation of Improved Pivot Pin Retention Mechanism and Bolt

    Within 6,000 flight hours or 36 months after the effective date 
of this AD, whichever occurs first: Install a new pivot pin 
retention mechanism to the NLG shock strut assembly, and replace the 
existing pivot pin retention bolt with a new bolt, in accordance 
with paragraph 3.B., ``Procedure,'' of the Accomplishment 
Instructions of Bombardier Service Bulletin 84-32-145, Revision A, 
dated October 18, 2016.

(h) Credit for Previous Actions

    This paragraph provides credit for actions required by paragraph 
(g) of this AD, if those actions were performed before the effective 
date of this AD using Bombardier Service Bulletin 84-32-145, dated 
July 26, 2016.

(i) 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: As of the effective date of 
this AD, for any requirement in this AD to obtain corrective actions 
from a manufacturer, the action must be accomplished using a method 
approved by the Manager, New York ACO Branch, 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.

(j) Related Information

    (1) Refer to Mandatory Continuing Airworthiness Information 
(MCAI) Canadian Airworthiness Directive CF-2009-29R2, dated December 
21, 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-2017-0334.
    (2) For more information about this AD, contact Fabio Buttitta, 
Aerospace Engineer, Airframe and Mechanical Systems Section, FAA, 
New York ACO Branch, 1600 Stewart Avenue, Suite 410, Westbury, NY 
11590; telephone 516-228-7303; 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 (k)(3) and (k)(4) of this AD.

(k) 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.
    (i) Bombardier Service Bulletin 84-32-145, Revision A, dated 
October 18, 2016.
    (ii) Reserved.
    (3) For service information identified in this AD, contact 
Bombardier, Inc., Q-Series Technical Help Desk, 123 Garratt 
Boulevard, Toronto, Ontario M3K 1Y5, Canada; telephone 416-375-4000; 
fax 416-375-4539; email thd.qseries@aero.bombardier.com; Internet 
http://www.bombardier.com.
    (4) You may view this service information at the FAA, Transport 
Standards Branch,

[[Page 43832]]

1601 Lind Avenue SW., Renton, WA. For information on the 
availability of this material at the FAA, call 425-227-1221.
    (5) 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 September 7, 2017.
Jeffrey E. Duven,
Director, System Oversight Division, Aircraft Certification Service.
[FR Doc. 2017-19660 Filed 9-19-17; 8:45 am]
BILLING CODE 4910-13-P