82 FR 43829 - Airworthiness Directives; Bombardier, Inc., Airplanes
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration Federal Register Volume 82, Issue 181 (September 20, 2017)
Federal Aviation Administration
Federal Register Volume 82, Issue 181 (September 20, 2017)
| Page Range | 43829-43832 | |
| FR Document | 2017-19660 |
[Federal Register Volume 82, Number 181 (Wednesday, September 20, 2017)] [Rules and Regulations] [Pages 43829-43832] From the Federal Register Online [www.thefederalregister.org] [FR Doc No: 2017-19660] ----------------------------------------------------------------------- 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 [email protected]; 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 [email protected]; 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
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conditions or 5 minutes each under 2(g)(1)(i)(A) must be repeated ten times DEPARTMENT OF TRANSPORTATION
AEO conditions in any one flight, for a in cycles 16 through 25 of the § 33.87
maximum accumulated usage of 20 endurance test. Federal Aviation Administration
minutes in any one flight. Each flight (2) After completion of the tests
where the ‘‘Rated TOTHAT’’ is used required by § 33.87(b), as modified in 14 CFR Part 39
must be followed by mandatory paragraph 2(g)(1)(i) above, and without [Docket No. FAA–2017–0334; Product
inspection and maintenance actions.’’ intervening disassembly, except as Identifier 2017–NM–008–AD; Amendment
(iii) As required by § 33.5(b), needed to replace those parts described 39–19039; AD 2017–19–09]
Operating instructions, include a note as consumables in the ICA, the
stating that ‘‘the engine thrust control RIN 2120–AA64
applicant must conduct the following
system automatically resets the thrust test sequence for a total time of not less Airworthiness Directives; Bombardier,
on the operating engine to the ‘‘Rated than 120 minutes: Inc., Airplanes
TOTHAT’’ level when one engine fails (i) Ten minutes at ‘‘Rated TOTHAT’’.
during takeoff at specified altitudes and AGENCY: Federal Aviation
(ii) Eighty-eight minutes at rated
temperatures, and the ‘‘Rated TOTHAT’’ Administration (FAA), Department of
maximum continuous thrust.
is available by manual selection when Transportation (DOT).
all engines are operational during (iii) One minute at 50 percent of rated
ACTION: Final rule.
takeoff at specified altitudes and takeoff thrust.
temperatures.’’ (iv) Ten minutes at ‘‘Rated TOTHAT’’. SUMMARY: We are superseding
(d) Section 33.28, Engine Control (v) Ten minutes at rated maximum Airworthiness Directive (AD) 2014–25–
Systems. continuous thrust. 01, which applied to certain
The engine must incorporate a means, (vi) One minute at flight idle. Bombardier, Inc., Model DHC–8–400
or a provision for a means, for automatic (3) The test sequence of §§ 33.87(b)(1) series airplanes. AD 2014–25–01
availability and automatic control of the through (b)(6) of these special required modifying the nose landing
‘‘Rated TOTHAT’’ under OEI conditions conditions must be run continuously. If gear (NLG) trailing arm and installing a
and must permit manual activation of a stop occurs during these tests, the new pivot pin retention mechanism.
the ‘‘Rated TOTHAT’’ under AEO interrupted sequence must be repeated This AD instead requires modifying the
conditions. unless the applicant shows that the NLG shock strut assembly. This AD was
(e) Section 33.29, Instrument severity of the test would not be prompted by reports of discrepancies of
connection. reduced if the current tests were a certain bolt at the pivot pin link,
The engine must: continued. resulting in corrosion of the bolt. We are
(1) Have means, or provisions for issuing this AD to address the unsafe
means, to alert the pilot when the (4) Where the engine characteristics
are such that acceleration to the ‘‘Rated condition on these products.
‘‘Rated TOTHAT’’ is in use, when the DATES: This AD is effective October 24,
event begins and when the time interval TOTHAT’’ results in a transient over
temperature in excess of the steady-state 2017.
expires. The Director of the Federal Register
(2) Have means, or provision for temperature limit identified in
paragraph 2(c)(1)(iii) of these special approved the incorporation by reference
means, which cannot be reset in flight, of a certain publication listed in this AD
to: conditions, the transient gas over
temperature must be applied to each as of October 24, 2017.
(i) Automatically record each use and
duration of the ‘‘Rated TOTHAT’’, and acceleration to the ‘‘Rated TOTHAT’’ of ADDRESSES: For service information
(ii) Alert maintenance personnel that the test sequence in paragraph 2(g)(2) of identified in this final rule, contact
the engine has been operated at the these special conditions. Bombardier, Inc., Q-Series Technical
‘‘Rated TOTHAT’’ and permit retrieval (h) Section 33.93, Teardown Help Desk, 123 Garratt Boulevard,
of recorded data. inspection. Toronto, Ontario M3K 1Y5, Canada;
(3) Have means, or provision for The applicant must perform the telephone 416–375–4000; fax 416–375–
means, to enable routine verification of teardown inspection required by 4539; email thd.qseries@
the proper operation of the means in § 33.93(a), after completing the aero.bombardier.com; Internet http://
paragraph 2(e)(1) and (e)(2) of these endurance test prescribed by § 33.87 of www.bombardier.com. You may view
special conditions. these special conditions. this referenced service information at
(f) Section 33.85(b), Calibration tests. (i) Section 33.201, Design and test the FAA, Transport Standards Branch,
The applicant must base the requirements for Early ETOPS 1601 Lind Avenue SW., Renton, WA.
calibration test on the thrust check at eligibility. For information on the availability of
the end of the endurance test required this material at the FAA, call 425–227–
In addition to the requirements of
by § 33.87 of these special conditions. 1221. It is also available on the Internet
§ 33.201(c)(1), the simulated ETOPS
(g) Section 33.87, Endurance test. at http://www.regulations.gov by
mission cyclic endurance test must
(1) In addition to the applicable searching for and locating Docket No.
include two cycles of 10 minute
requirements of § 33.87(a): FAA–2017–0334.
duration, each at the ‘‘Rated TOTHAT’’;
(i) The § 33.87 endurance test must be
one before the last diversion cycle and Examining the AD Docket
modified as follows:
(A) Modify the 30 minute test cycle at one at the end of the ETOPS test. You may examine the AD docket on
the rated takeoff thrust in Issued in Burlington, Massachusetts on the Internet at http://
sradovich on DSKBBY8HB2PROD with RULES
§ 33.87(b)(2)(ii) to run one minute at August 23, 2017. www.regulations.gov by searching for
rated takeoff thrust, followed by five Karen M. Grant and locating Docket No. FAA–2017–
minutes at the ‘‘Rated TOTHAT’’, Acting Manager, Engine and Propeller 0334; or in person at the Docket
followed by the rated takeoff thrust for Standards Branch, Aircraft Certification Management Facility between 9 a.m.
the remaining twenty-four minutes. Service. and 5 p.m., Monday through Friday,
(B) The modified 30 minute period [FR Doc. 2017–19952 Filed 9–19–17; 8:45 am] except Federal holidays. The AD docket
described above in paragraph BILLING CODE 4910–13–P contains this AD, the regulatory
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![43830 Federal Register / Vol. 82, No. 181 / Wednesday, September 20, 2017 / Rules and Regulations
evaluation, any comments received, and adversely affect the aircraft during take-off or Bulletin 84–32–145, Revision A, dated
other information. The address for the landing. October 18, 2016. Horizon Air stated
Docket Office (telephone 800–647–5527) To prevent the potential failure of the pivot that incorporating those sections as a
is Docket Management Facility, U.S. pin retention bolt, Bombardier Aerospace has
requirement of the AD restricts an
developed a modification which includes a
Department of Transportation, Docket new retention bolt, a reverse orientation of operator’s ability to perform other
Operations, M–30, West Building the retention bolt and a rework of the weight maintenance in conjunction with
Ground Floor, Room W12–140, 1200 on wheel (WOW) proximity sensor cover to incorporation of the referenced service
New Jersey Avenue SE., Washington, provide clearance for the re-oriented information.
DC 20590. retention bolt. We agree with the commenter’s
FOR FURTHER INFORMATION CONTACT:
Since the original issue of this [Canadian] request for the reason provided. We
AD [which corresponds to AD 2010–13–04, have revised paragraph (g) of this AD to
Fabio Buttitta, Aerospace Engineer, Amendment 39–16335 (75 FR 35622, June
Airframe and Mechanical Systems require accomplishment of only
23, 2010)], there have been several reports of paragraph 3.B., ‘‘Procedure’’ of the
Section, FAA, New York ACO Branch, pivot pin retention bolts found missing or
1600 Stewart Avenue, Suite 410, Accomplishment Instructions of
damaged. Additional investigation
Westbury, NY 11590; telephone 516– determined that the failures were caused by Bombardier Service Bulletin 84–32–145,
228–7303; fax 516–794–5531. high contact stresses on the retention bolt Revision A, dated October 18, 2016.
due to excessive frictional torque on the Conclusion
SUPPLEMENTARY INFORMATION:
pivot pin and an adverse tolerance condition
Discussion at the retention bolt. We reviewed the relevant data,
Revision 1 of this [Canadian] AD mandated considered the comments received, and
We issued a notice of proposed the installation of a new pivot pin retention determined that air safety and the
rulemaking (NPRM) to amend 14 CFR mechanism. public interest require adopting this AD
part 39 to supersede AD 2014–25–01, Since the issuance of Revision 1 of this with the change described previously
Amendment 39–18042 (79 FR 73808, [Canadian] AD, there have been reports of and minor editorial changes. We have
December 12, 2014) (‘‘AD 2014–25– chrome peeling on special bolt part number
47205–1 at the pivot pin link resulting in
determined that these minor changes:
01’’). AD 2014–25–01 applied to certain
corrosion of the bolt substrate layer. • Are consistent with the intent that
Bombardier, Inc., Model DHC–8–400 Revision 2 of this [Canadian] AD mandates was proposed in the NPRM for
series airplanes. The NPRM published the installation of new special bolt part correcting the unsafe condition; and
in the Federal Register on May 9, 2017 number 47205–3 with additional processing • Do not add any additional burden
(82 FR 21484). The NPRM was for increased chrome plating adhesion on upon the public than was already
prompted by reports of discrepancies of aeroplanes equipped with nose landing gear proposed in the NPRM.
a certain bolt at the pivot pin link, shock strut assembly part number 47100–19 We also determined that these
resulting in corrosion of the bolt. The or any assembly with Bombardier (BA) changes will not increase the economic
NPRM proposed to require modifying Service Bulletin (SB) 84–32–110 burden on any operator or increase the
the NLG shock strut assembly. We are incorporated. In addition, Revision 2 of this
[Canadian] AD mandates the installation of a
scope of this AD.
issuing this AD to prevent failure of the new pivot pin retention mechanism that
pivot pin retention bolt, which could Related Service Information Under 1
includes new special bolt part number CFR Part 51
result in a loss of directional control or 47205–3 on aeroplanes equipped with nose
loss of an NLG tire during takeoff or landing gear shock strut assembly part Bombardier, Inc., has issued
landing. number 47100–9, 47100–11, 47100–13, Bombardier Service Bulletin 84–32–145,
Transport Canada Civil Aviation 47100–15, or 47100–17 without BA SB 84– Revision A, dated October 18, 2016. The
(TCCA), which is the aviation authority 32–110 incorporated. The corrective actions service information describes
for Canada, has issued Canadian of Revision 2 of this [Canadian] AD cancel procedures for modifying the NLG
and replace the corrective actions of Revision shock strut assembly by installing a
Airworthiness Directive CF–2009–29R2, 1 of this [Canadian] AD.
dated December 21, 2016 (referred to new, improved pivot pin retention
after this as the Mandatory Continuing You may examine the MCAI in the mechanism and a new retention bolt.
Airworthiness Information, or ‘‘the AD docket on the Internet at http:// This service information is reasonably
MCAI’’), to correct an unsafe condition www.regulations.gov by searching for available because the interested parties
for certain Bombardier, Inc., Model and locating Docket No. FAA–2017– have access to it through their normal
DHC–8–400 series airplanes. The MCAI 0334. course of business or by the means
states: identified in the ADDRESSES section.
Comments
Two in-service incidents have been
We gave the public the opportunity to Costs of Compliance
reported on DHC–8 Series 400 aircraft in
which the nose landing gear (NLG) trailing participate in developing this AD. The We estimate that this AD affects 52
arm pivot pin retention bolt (part number following presents the comments airplanes of U.S. registry.
NAS6204–13D) was damaged. One incident received on the NPRM and the FAA’s We also estimate that it takes about 2
involved the left hand NLG tire which response to each comment. work-hours per product to comply with
ruptured on take-off. Investigation the basic requirements of this AD. The
determined that the retention bolt failure was Support for the NPRM average labor rate is $85 per work-hour.
due to repeated contact of the castellated nut The Air Line Pilots Association, Required parts will cost about $0 per
with the towing device including both the International concurred with the intent product. Based on these figures, we
towbar and the towbarless rigs. The loss of of the NPRM. estimate the cost of this AD on U.S.
sradovich on DSKBBY8HB2PROD with RULES
the retention bolt allowed the pivot pin to
operators to be $8,840, or $170 per
migrate from its normal position and resulted Request To Exclude Setup and Closeout
in contact with and rupture of the tire. The product.
Sections
loss of the pivot pin could compromise Authority for This Rulemaking
retention of the trailing arm and could result Horizon Air asked that we revise
in a loss of directional control due to loss of paragraph (g) of the proposed AD to Title 49 of the United States Code
nose wheel steering. The loss of an NLG tire exclude the ‘‘Job Set-up’’ and ‘‘Close specifies the FAA’s authority to issue
or the loss of directional control could Out’’ sections of Bombardier Service rules on aviation safety. Subtitle I,
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section 106, describes the authority of PART 39—AIRWORTHINESS (i) Other FAA AD Provisions
the FAA Administrator. ‘‘Subtitle VII: DIRECTIVES The following provisions also apply to this
Aviation Programs,’’ describes in more AD:
detail the scope of the Agency’s ■ 1. The authority citation for part 39 (1) Alternative Methods of Compliance
authority. (AMOCs): The Manager, New York ACO
continues to read as follows: Branch, FAA, has the authority to approve
We are issuing this rulemaking under
the authority described in ‘‘Subtitle VII, Authority: 49 U.S.C. 106(g), 40113, 44701. AMOCs for this AD, if requested using the
procedures found in 14 CFR 39.19. In
Part A, Subpart III, Section 44701: § 39.13 [Amended] accordance with 14 CFR 39.19, send your
General requirements.’’ Under that request to your principal inspector or local
section, Congress charges the FAA with ■ 2. The FAA amends § 39.13 by Flight Standards District Office, as
promoting safe flight of civil aircraft in removing Airworthiness Directive (AD) appropriate. If sending information directly
air commerce by prescribing regulations 2014–25–01, Amendment 39–18042 (79 to the manager of the certification office,
for practices, methods, and procedures FR 73808, December 12, 2014), and send it to ATTN: Program Manager,
the Administrator finds necessary for Continuing Operational Safety, FAA, New
adding the following new AD:
safety in air commerce. This regulation York ACO Branch, 1600 Stewart Avenue,
2017–19–09 Bombardier, Inc.: Amendment Suite 410, Westbury, NY 11590; telephone
is within the scope of that authority 39–19039; Docket No. FAA–2017–0334; 516–228–7300; fax 516–794–5531. Before
because it addresses an unsafe condition Product Identifier 2017–NM–008–AD. using any approved AMOC, notify your
that is likely to exist or develop on appropriate principal inspector, or lacking a
products identified in this rulemaking (a) Effective Date principal inspector, the manager of the local
action. This AD is effective October 25, 2017. flight standards district office/certificate
This AD is issued in accordance with holding district office.
(b) Affected ADs (2) Contacting the Manufacturer: As of the
authority delegated by the Executive
Director, Aircraft Certification Service, This AD replaces AD 2014–25–01, effective date of this AD, for any requirement
Amendment 39–18042 (79 FR 73808, in this AD to obtain corrective actions from
as authorized by FAA Order 8000.51C. a manufacturer, the action must be
December 12, 2014).
In accordance with that order, issuance accomplished using a method approved by
of ADs is normally a function of the (c) Applicability the Manager, New York ACO Branch, FAA;
Compliance and Airworthiness This AD applies to Bombardier, Inc., or Transport Canada Civil Aviation (TCCA);
Division, but during this transition Model DHC–8–400, –401, and –402 or Bombardier, Inc.’s TCCA Design Approval
period, the Executive Director has airplanes, certificated in any category, serial Organization (DAO). If approved by the DAO,
delegated the authority to issue ADs numbers 4001, 4003 through 4533 inclusive, the approval must include the DAO-
applicable to transport category and 4535, equipped with any nose landing authorized signature.
airplanes to the Director of the System gear (NLG) shock strut assembly having part (j) Related Information
Oversight Division. number 47100–9, 47100–11, 47100–13,
(1) Refer to Mandatory Continuing
47100–15, 47100–17, or 47100–19.
Regulatory Findings Airworthiness Information (MCAI) Canadian
(d) Subject Airworthiness Directive CF–2009–29R2,
We determined that this AD will not dated December 21, 2016, for related
Air Transport Association (ATA) of
have federalism implications under information. This MCAI may be found in the
America Code 32, Landing Gear.
Executive Order 13132. This AD will AD docket on the Internet at http://
not have a substantial direct effect on (e) Reason www.regulations.gov by searching for and
the States, on the relationship between This AD was prompted by reports of locating Docket No. FAA–2017–0334.
the national government and the States, (2) For more information about this AD,
discrepancies of a certain bolt at the pivot
contact Fabio Buttitta, Aerospace Engineer,
or on the distribution of power and pin link, resulting in corrosion of the bolt.
Airframe and Mechanical Systems Section,
responsibilities among the various We are issuing this AD to prevent failure of
FAA, New York ACO Branch, 1600 Stewart
levels of government. the pivot pin retention bolt, which could Avenue, Suite 410, Westbury, NY 11590;
For the reasons discussed above, I result in a loss of directional control or loss telephone 516–228–7303; fax 516–794–5531.
certify that this AD: of an NLG tire during takeoff or landing. (3) Service information identified in this
1. Is not a ‘‘significant regulatory (f) Compliance AD that is not incorporated by reference is
action’’ under Executive Order 12866; available at the addresses specified in
Comply with this AD within the paragraphs (k)(3) and (k)(4) of this AD.
2. Is not a ‘‘significant rule’’ under the
compliance times specified, unless already
DOT Regulatory Policies and Procedures done. (k) Material Incorporated by Reference
(44 FR 11034, February 26, 1979);
(g) Installation of Improved Pivot Pin (1) The Director of the Federal Register
3. Will not affect intrastate aviation in
Retention Mechanism and Bolt approved the incorporation by reference
Alaska; and (IBR) of the service information listed in this
4. Will not have a significant Within 6,000 flight hours or 36 months paragraph under 5 U.S.C. 552(a) and 1 CFR
economic impact, positive or negative, after the effective date of this AD, whichever part 51.
on a substantial number of small entities occurs first: Install a new pivot pin retention (2) You must use this service information
under the criteria of the Regulatory mechanism to the NLG shock strut assembly, as applicable to do the actions required by
Flexibility Act. and replace the existing pivot pin retention this AD, unless this AD specifies otherwise.
bolt with a new bolt, in accordance with (i) Bombardier Service Bulletin 84–32–145,
List of Subjects in 14 CFR Part 39 paragraph 3.B., ‘‘Procedure,’’ of the Revision A, dated October 18, 2016.
Air transportation, Aircraft, Aviation Accomplishment Instructions of Bombardier (ii) Reserved.
safety, Incorporation by reference, Service Bulletin 84–32–145, Revision A, (3) For service information identified in
sradovich on DSKBBY8HB2PROD with RULES
dated October 18, 2016. this AD, contact Bombardier, Inc., Q-Series
Safety.
Technical Help Desk, 123 Garratt Boulevard,
(h) Credit for Previous Actions Toronto, Ontario M3K 1Y5, Canada;
Adoption of the Amendment
This paragraph provides credit for actions telephone 416–375–4000; fax 416–375–4539;
Accordingly, under the authority required by paragraph (g) of this AD, if those email thd.qseries@aero.bombardier.com;
delegated to me by the Administrator, actions were performed before the effective Internet http://www.bombardier.com.
the FAA amends 14 CFR part 39 as date of this AD using Bombardier Service (4) You may view this service information
follows: Bulletin 84–32–145, dated July 26, 2016. at the FAA, Transport Standards Branch,
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![43832 Federal Register / Vol. 82, No. 181 / Wednesday, September 20, 2017 / Rules and Regulations
1601 Lind Avenue SW., Renton, WA. For of certain publications listed in this AD on engine fire extinguishing discharge
information on the availability of this as of October 25, 2017. cartridges. The NPRM proposed to
material at the FAA, call 425–227–1221. The Director of the Federal Register continue to require identifying the
(5) You may view this service information approved the incorporation by reference correct polarity of each pair of electrical
that is incorporated by reference at the
National Archives and Records
of a certain other publication listed in connectors of the affected engine fire
Administration (NARA). For information on this AD as of March 8, 2013 (78 FR extinguisher cartridge, and doing a
the availability of this material at NARA, call 7262, February 1, 2013). repair if necessary. The NPRM also
202–741–6030, or go to: http:// ADDRESSES: For service information proposed to require modifying the
www.archives.gov/federal-register/cfr/ibr- identified in this final rule, contact installation of the fire extinguisher
locations.html. Airbus Defense and Space Services/ circuit harnesses. We are issuing this
Issued in Renton, Washington, on Engineering Support, Avenida de AD to detect and correct incorrect
September 7, 2017. Aragón 404, 28022 Madrid, Spain; polarity connections, which could
Jeffrey E. Duven, telephone +34 91 585 55 84; fax +34 91 prevent the actuation of the discharge
Director, System Oversight Division, Aircraft 585 31 27; email cartridge in case of automatic fire
Certification Service. MTA.TechnicalService@airbus.com. detection or manual initiation during a
[FR Doc. 2017–19660 Filed 9–19–17; 8:45 am] You may view this referenced service potential engine fire, and could result in
BILLING CODE 4910–13–P information at the FAA, Transport damage to the airplane and injury to
Standards Branch, 1601 Lind Avenue passengers.
SW., Renton, WA. For information on The European Aviation Safety Agency
DEPARTMENT OF TRANSPORTATION the availability of this material at the (EASA), which is the Technical Agent
FAA, call 425–227–1221. It is also for the Member States of the European
Federal Aviation Administration available on the Internet at http:// Union, has issued EASA AD 2016–0201,
www.regulations.gov by searching for dated October 11, 2016 (referred to after
14 CFR Part 39 and locating Docket No. FAA–2017– this as the Mandatory Continuing
0555. Airworthiness Information, or ‘‘the
[Docket No. FAA–2017–0555; Product
Identifier 2016–NM–183–AD; Amendment MCAI’’), to correct an unsafe condition
Examining the AD Docket for all Airbus Defense and Space S.A.
39–19037; AD 2017–19–07]
You may examine the AD docket on Model CN–235, CN–235–100, CN–235–
RIN 2120–AA64 the Internet at http:// 200, and CN–235–300 airplanes. The
www.regulations.gov by searching for MCAI states:
Airworthiness Directives; Airbus
and locating Docket No. FAA–2017– Reports have been received of finding
Defense and Space S.A. (Formerly
0555; or in person at the Docket wrong electrical polarity connections of
Known as Construcciones
Management Facility between 9 a.m. engine fire extinguishing discharge cartridges
Aeronauticas, S.A.) Airplanes
and 5 p.m., Monday through Friday, on CASA CN–235 aeroplanes. The results of
AGENCY: Federal Aviation except Federal holidays. The AD docket the subsequent investigation showed that the
Administration (FAA), Department of contains this AD, the regulatory incorrect discharge cartridge assembly was
Transportation (DOT). evaluation, any comments received, and caused by production line errors.
other information. The address for the This condition, if not detected and
ACTION: Final rule. corrected, could prevent the actuation of the
Docket Office (telephone 800–647–5527) discharge cartridge in case of automatic fire
SUMMARY: We are superseding is Docket Management Facility, U.S. detection or manual initiation in case of
Airworthiness Directive (AD) 2013–02– Department of Transportation, Docket engine fire, possibly resulting in damage to
12, which applied to all EADS CASA Operations, M–30, West Building the aeroplane and injury to occupants.
(now Airbus Defense and Space S.A.) Ground Floor, Room W12–140, 1200 To address this potentially unsafe
Model CN–235, CN–235–100, CN–235– New Jersey Avenue SE., Washington, condition, EADS CASA (Airbus Military)
200, and CN–235–300 airplanes. AD DC 20590. developed instructions to identify erroneous
2013–02–12 required a one-time wiring polarity installation and EASA issued
FOR FURTHER INFORMATION CONTACT:
inspection to identify the correct AD 2012–0045 [which correlates to FAA AD
Shahram Daneshmandi, Aerospace 2013–02–12, Amendment 39–17333 (78 FR
polarity for each pair of electrical Engineer, International Section, 7262, February 1, 2013)] to require a one-time
connectors on each engine fire Transport Standards Branch, FAA, 1601 inspection to verify proper electrical polarity
extinguisher cartridge, and repair if Lind Avenue SW., Renton, WA 98057– of wiring of each engine fire extinguisher
necessary. This AD continues to require 3356; telephone 425–227–1112; fax discharge cartridge and, depending on
identifying the correct polarity of each 425–227–1149. findings, corrective action.
pair of electrical connectors of the SUPPLEMENTARY INFORMATION:
Since [EASA] AD 2012–0045 was issued,
affected engine fire extinguisher Airbus Defence and Space (D&S) developed
cartridge, and doing a repair if Discussion modification of the installation of the fire
necessary. This AD also requires extinguisher circuit harnesses, available for
We issued a notice of proposed in-service installation through Service
modifying the installation of the fire rulemaking (NPRM) to amend 14 CFR Bulletin (SB) SB–235–26–0005, which
extinguisher circuit harnesses. This AD part 39 to supersede AD 2013–02–12, represents technical solution for an unsafe
was prompted by reports of incorrect Amendment 39–17333 (78 FR 7262, condition addressed by [EASA] AD 2012–
electrical polarity connections on February 1, 2013) (‘‘AD 2013–02–12’’). 0045 for those aeroplanes. Embodiment of
engine fire extinguishing discharge AD 2013–02–12 applied to all EADS this modification introduces a design
sradovich on DSKBBY8HB2PROD with RULES
cartridges. We are issuing this AD to CASA (now Airbus Defense and Space solution that avoids maintenance errors
address the unsafe condition on these S.A.) Model CN–235, CN–235–100, CN– during (re)connecting of the affected fire
products. extinguisher circuit harnesses after
235–200, and CN–235–300 airplanes. accomplishment of maintenance tasks or
DATES:This AD is effective October 25, The NPRM published in the Federal functional tests.
2017. Register on June 16, 2017 (82 FR 27631). For the reasons described above, this
The Director of the Federal Register The NPRM was prompted by reports of [EASA] AD retains the requirements of EASA
approved the incorporation by reference incorrect electrical polarity connections AD 2012–0045, which is superseded and
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Document Created: 2018-10-24 14:22:51
Document Modified: 2018-10-24 14:22:51
| Category | Regulatory Information | |
| Collection | Federal Register | |
| sudoc Class | AE 2.7: GS 4.107: AE 2.106: | |
| Publisher | Office of the Federal Register, National Archives and Records Administration | |
| Section | Rules and Regulations | |
| Action | Final rule. | |
| Dates | This AD is effective October 24, 2017. | |
| 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. | |
| FR Citation | 82 FR 43829 | |
| RIN Number | 2120-AA64 | |
| CFR Associated | Air Transportation; Aircraft; Aviation Safety; Incorporation by Reference and Safety |
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