Airworthiness Directives; Bombardier, Inc., Airplanes, 27503-27506 [2019-12351]

Download as PDF 27503 Rules and Regulations Federal Register Vol. 84, No. 114 Thursday, June 13, 2019 This section of the FEDERAL REGISTER contains regulatory documents having general applicability and legal effect, most of which are keyed to and codified in the Code of Federal Regulations, which is published under 50 titles pursuant to 44 U.S.C. 1510. The Code of Federal Regulations is sold by the Superintendent of Documents. Examining the AD Docket DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2019–0024; Product Identifier 2018–NM–138–AD; Amendment 39–19640; AD 2019–10–01] RIN 2120–AA64 Airworthiness Directives; Bombardier, Inc., Airplanes Federal Aviation Administration (FAA), Department of Transportation (DOT). ACTION: Final rule. AGENCY: We are adopting a new airworthiness directive (AD) for certain Bombardier, Inc., Model CL–600–2A12 (601) airplanes. This AD was prompted by a report of damage to the antirotation tab on a main landing gear (MLG) side brace fitting due to the installation of an incorrect side brace fitting shaft. This AD requires an inspection of the MLG side brace fitting for damage, a verification of the side brace fitting shaft part number, and replacement of the side brace fitting shaft if necessary. It also requires the installation of an anti-rotation bracket. We are issuing this AD to address the unsafe condition on these products. DATES: This AD is effective July 18, 2019. The Director of the Federal Register approved the incorporation by reference of a certain publication listed in this AD as of July 18, 2019. ADDRESSES: For service information identified in this final rule, contact Bombardier, Inc., 200 Coˆte-Vertu Road West, Dorval, Que´bec H4S 2A3, Canada; North America toll-free telephone 1– 866–538–1247 or direct-dial telephone 1–514–855–2999; email ac.yul@ aero.bombardier.com; internet https:// www.bombardier.com. You may view this service information at the FAA, Transport Standards Branch, 2200 khammond on DSKBBV9HB2PROD with RULES SUMMARY: VerDate Sep<11>2014 16:11 Jun 12, 2019 Jkt 247001 South 216th St., Des Moines, WA. For information on the availability of this material at the FAA, call 206–231–3195. It is also available on the internet at https://www.regulations.gov by searching for and locating Docket No. FAA–2019– 0024. You may examine the AD docket on the internet at https:// www.regulations.gov by searching for and locating Docket No. FAA–2019– 0024; or in person at Docket Operations between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. The AD docket contains this final rule, the regulatory evaluation, any comments received, and other information. The address for Docket Operations (phone: 800–647–5527) is 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: Aziz Ahmed, Aerospace Engineer, FAA, New York ACO Branch, 1600 Stewart Avenue, Suite 410, Westbury, New York 11590; telephone: 516–287–7329; fax: 516–794–5531; email: Aziz.Ahmed@ faa.gov. SUPPLEMENTARY INFORMATION: Discussion We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR part 39 by adding an AD that would apply to certain Bombardier, Inc., Model CL–600–2A12 (601) airplanes. The NPRM published in the Federal Register on February 28, 2019 (84 FR 6705). The NPRM was prompted by a report of damage to the anti-rotation tab on an MLG side brace fitting due to the installation of an incorrect side brace fitting shaft. The NPRM proposed to require an inspection of the MLG side brace fitting for damage, a verification of the side brace fitting shaft part number, and replacement of the side brace fitting shaft if necessary. It also proposed to require the installation of an antirotation bracket. We are issuing this AD to address premature cracking of the MLG side brace fitting. This condition, if not corrected, could lead to the collapse of the MLG, resulting in structural damage to the wing spar and fuel tank. PO 00000 Frm 00001 Fmt 4700 Sfmt 4700 Transport Canada Civil Aviation (TCCA), which is the aviation authority for Canada, has issued Canadian AD CF–2018–19, dated July 20, 2018 (referred to after this as the Mandatory Continuing Airworthiness Information, or ‘‘the MCAI’’), to correct an unsafe condition for certain Bombardier, Inc., Model CL–600–2A12 (601) airplanes. The MCAI states: There has been a report of damage to the anti-rotation tab on a Main Landing Gear (MLG) Side Brace fitting. Investigation of the report revealed that a Challenger model CL600 MLG Side Brace shaft had been installed on a Challenger model CL601 Side Brace fitting. Due to the difference in size, this will result in changes to the way the load is transferred between the shaft and the MLG Side Brace fitting and may result in premature cracking of the MLG Side Brace fitting. This condition, if not corrected, could lead to the collapse of the MLG resulting in structural damage to the wing spar and fuel tank. This [Canadian] AD mandates an inspection of the MLG Side Brace fitting and shaft to verify that the correct shaft part number (P/N) is installed and the fitting is not damaged [damage includes cracking, scratches, gouges, corrosion, defects, and incorrect inner diameter tolerance]. If the Challenger CL600 shaft is installed, this AD mandates replacement with the correct Challenger model CL601 part. If the correct P/N is found installed, this [Canadian] AD also mandates the installation of a bracket to prevent the incorrect part from being installed in the future. You may examine the MCAI in the AD docket on the internet at https:// www.regulations.gov by searching for and locating Docket No. FAA–2019– 0024. Comments We gave the public the opportunity to participate in developing this final rule. We received no comments on the NPRM or on the determination of the cost to the public. Conclusion We reviewed the relevant data and determined that air safety and the public interest require adopting this final rule as proposed, except for minor editorial changes. We have determined that these minor changes: • Are consistent with the intent that was proposed in the NPRM for addressing the unsafe condition; and • Do not add any additional burden upon the public than was already proposed in the NPRM. E:\FR\FM\13JNR1.SGM 13JNR1 27504 Federal Register / Vol. 84, No. 114 / Thursday, June 13, 2019 / Rules and Regulations Related Service Information Under 1 CFR Part 51 and side brace fitting shaft, installing a replacement side brace fitting shaft if necessary, and installing an antirotation bracket. This service information is reasonably available because the interested parties have access to it through their normal Bombardier has issued Service Bulletin 601–0624, Revision 02, dated January 29, 2018. This service information describes procedures for inspecting the MLG side brace fitting course of business or by the means identified in the ADDRESSES section. Costs of Compliance We estimate that this AD affects 9 airplanes of U.S. registry. We estimate the following costs to comply with this AD: ESTIMATED COSTS FOR REQUIRED ACTIONS Labor cost Parts cost Cost per product Cost on U.S. operators 4 work-hours × $85 per hour = $340 .......................................................................................... $397 $737 $6,633 We estimate the following costs to do any necessary on-condition actions that would be required based on the results of any required actions. We have no way of determining the number of aircraft that might need these on-condition actions: khammond on DSKBBV9HB2PROD with RULES ESTIMATED COSTS OF ON-CONDITION ACTIONS Labor cost Parts cost Cost per product 8 work-hours × $85 per hour = $680 ...................................................................................................................... $7,989 $8,669 Authority for This Rulemaking Regulatory Findings Title 49 of the United States Code specifies the FAA’s authority to issue rules on aviation safety. Subtitle I, section 106, describes the authority of the FAA Administrator. Subtitle VII: Aviation Programs, describes in more detail the scope of the Agency’s authority. We are issuing this rulemaking under the authority described in Subtitle VII, Part A, Subpart III, Section 44701: ‘‘General requirements.’’ Under that section, Congress charges the FAA with promoting safe flight of civil aircraft in air commerce by prescribing regulations for practices, methods, and procedures the Administrator finds necessary for safety in air commerce. This regulation is within the scope of that authority because it addresses an unsafe condition that is likely to exist or develop on products identified in this rulemaking action. This AD is issued in accordance with authority delegated by the Executive Director, Aircraft Certification Service, as authorized by FAA Order 8000.51C. In accordance with that order, issuance of ADs is normally a function of the Compliance and Airworthiness Division, but during this transition period, the Executive Director has delegated the authority to issue ADs applicable to transport category airplanes and associated appliances to the Director of the System Oversight Division. 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. VerDate Sep<11>2014 16:11 Jun 12, 2019 Jkt 247001 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: PO 00000 Frm 00002 Fmt 4700 Sfmt 4700 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 adding the following new airworthiness directive (AD): ■ 2019–10–01 Bombardier, Inc.: Amendment 39–19640; Docket No. FAA–2019–0024; Product Identifier 2018–NM–138–AD. (a) Effective Date This AD is effective July 18, 2019. (b) Affected ADs None. (c) Applicability This AD applies to Bombardier, Inc., Model CL–600–2A12 (601) airplanes, certificated in any category, serial numbers (S/N) 3001 through 3009 inclusive and 3011 through 3029 inclusive. (d) Subject Air Transport Association (ATA) of America Code 57, Wings. (e) Reason This AD was prompted by a report of damage to the anti-rotation tab on a main landing gear (MLG) side brace fitting due to the installation of an incorrect side brace fitting shaft. We are issuing this AD to address premature cracking of the MLG side brace fitting. This condition, if not corrected, could lead to the collapse of the MLG, resulting in structural damage to the wing spar and fuel tank. E:\FR\FM\13JNR1.SGM 13JNR1 Federal Register / Vol. 84, No. 114 / Thursday, June 13, 2019 / Rules and Regulations (f) Compliance Comply with this AD within the compliance times specified, unless already done. (g) Inspection for Damage and Identification of the Side Brace Fitting Shaft Part Number Within 400 flight cycles or 12 months, whichever occurs first, after the effective date of this AD, do the actions specified in paragraphs (g)(1) and (g)(2) of this AD. (1) Identify the part number of the installed side brace fitting shaft. (2) Do a detailed visual inspection (DVI) of the side brace fitting for signs of damage, including cracking and gouges, in accordance with paragraph 2.B. of the Accomplishment Instructions of Bombardier Service Bulletin 601–0624, Revision 02, dated January 29, 2018. khammond on DSKBBV9HB2PROD with RULES (h) Installation of Anti-Rotation Bracket (1) For airplanes on which a side brace fitting shaft having P/N 600–10237–3 is installed and the actions required by paragraph (g) of this AD are done on or after the effective date of this AD: Before further flight, modify the MLG side brace fitting by installing the anti-rotation bracket in accordance with paragraph 2.C. of the Accomplishment Instructions of Bombardier Service Bulletin 601–0624, Revision 02, dated January 29, 2018. (2) For airplanes on which a side brace fitting shaft having P/N 600–10237–3 is installed and the actions required by paragraph (g) of this AD were done before the effective date of this AD: Within 6 months after the effective date of this AD, modify the MLG side brace fitting by installing the antirotation bracket in accordance with paragraph 2.C. of the Accomplishment Instructions of Bombardier Service Bulletin 601–0624, Revision 02, dated January 29, 2018. (i) Replacement of the Side Brace Fitting Shaft and Installation of the Anti-Rotation Bracket (1) For airplanes on which a side brace fitting shaft having P/N 600–10237–1 or 600– 10237–5 is installed and damage is found during the DVI of the side brace fitting: Before further flight, do a DVI of the antirotation tab and side brace fitting aft bushing for cracking, scratches, gouges, corrosion, and inner diameter tolerance, and a special detailed inspection (SDI) of the side brace fitting aft bore for cracks and defects; perform applicable repairs; replace the side brace fitting shaft with a side brace fitting shaft having P/N 600–10237–3; and install the anti-rotation bracket in accordance with paragraph 2.D. of the Accomplishment Instructions of Bombardier Service Bulletin 601–0624, Revision 02, dated January 29, 2018. (2) For airplanes on which a side brace fitting shaft having P/N 600–10237–1 or 600– 10237–5 is installed and no damage is found during the DVI of the side brace fitting: Within 300 flight cycles or 12 months, whichever occurs first, after the inspection required by paragraph (g)(2) of this AD, do a DVI of the anti-rotation tab and side brace fitting aft bushing for cracking, scratches, VerDate Sep<11>2014 16:11 Jun 12, 2019 Jkt 247001 gouges, corrosion, and inner diameter tolerance, and an SDI of the side brace fitting aft bore for cracks and defects; perform applicable repairs; replace the side brace fitting shaft with a side brace fitting shaft having P/N 600–10237–3; and install the anti-rotation bracket in accordance with paragraph 2.D. of the Accomplishment Instructions of Bombardier Service Bulletin 601–0624, Revision 02, dated January 29, 2018. (j) Exceptions to Service Information Where Bombardier Service Bulletin 601– 0624, Revision 02, dated January 29, 2018, specifies contacting Bombardier’s Customer Support Engineering for repair instructions: This AD requires doing the repair before further flight using a method approved in accordance with the procedures specified in paragraph (l)(2) of this AD. (k) Credit for Previous Actions (1) For an airplane on which a side brace fitting shaft having P/N 600–10237–3 is installed: This paragraph provides credit for actions required by paragraphs (g) and (h) of this AD, if those actions were performed before the effective date of this AD using Bombardier Service Bulletin 601–0624, dated October 1, 2012; or Bombardier Service Bulletin 601–0624, Revision 01, dated March 29, 2017. (2) 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 601–0624, dated October 1, 2012; or Bombardier Service Bulletin 601– 0624, Revision 01, dated March 29, 2017, provided that the side brace fitting shaft was identified as having P/N 600–10237–3 and within 6 months after the effective date of this AD, the MLG side brace fitting is modified by installing the anti-rotation bracket in accordance with paragraph 2.C. of the Accomplishment Instructions of Bombardier Service Bulletin 601–0624, Revision 02, dated January 29, 2018. (3) This paragraph provides credit for actions required by paragraphs (g) and (i) of this AD, if those actions were performed before the effective date of this AD using Bombardier Service Bulletin 601–0624, Revision 01, dated March 29, 2017, provided that any side brace fitting shaft having P/N 600–10237–1 or P/N 600–10237–5 was identified and replaced with a side brace fitting shaft having P/N 600–10237–3, and the anti-rotation bracket was installed in accordance with paragraph 2.D. of the Accomplishment Instructions of Bombardier Service Bulletin 601–0624, Revision 01, dated March 29, 2017. (l) 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 PO 00000 Frm 00003 Fmt 4700 Sfmt 4700 27505 to the manager of the certification office, send it to ATTN: Program Manager, Continuing Operational Safety, FAA, New York ACO Branch, 1600 Stewart Avenue, Suite 410, Westbury, NY 11590; telephone 516–228–7300; fax 516–794–5531. Before using any approved AMOC, notify your appropriate principal inspector, or lacking a principal inspector, the manager of the local flight standards district office/certificate holding district office. (2) Contacting the Manufacturer: For any requirement in this AD to obtain corrective actions from a manufacturer, the action must be accomplished using a method approved by the Manager, New York ACO Branch, FAA; or Transport Canada Civil Aviation (TCCA); or Bombardier, Inc.’s TCCA Design Approval Organization (DAO). If approved by the DAO, the approval must include the DAO-authorized signature. (m) Related Information (1) Refer to Mandatory Continuing Airworthiness Information (MCAI) Canadian AD CF–2018–19, dated July 20, 2018, for related information. This MCAI may be found in the AD docket on the internet at https://www.regulations.gov by searching for and locating Docket No. FAA–2019–0024. (2) For more information about this AD, contact Aziz Ahmed, Aerospace Engineer, FAA, New York ACO Branch, 1600 Stewart Avenue, Suite 410, Westbury, New York 11590; telephone: 516–287–7329; fax: 516– 794–5531; email: Aziz.Ahmed@faa.gov. (3) Service information identified in this AD that is not incorporated by reference is available at the addresses specified in paragraphs (n)(3) and (n)(4) of this AD. (n) 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 601–0624, Revision 02, dated January 29, 2018. (ii) [Reserved] (3) For service information identified in this AD, contact Bombardier, Inc., 200 CoˆteVertu Road West, Dorval, Que´bec H4S 2A3, Canada; North America toll-free telephone: 1–866–538–1247 or direct-dial telephone: 1– 514–855–2999; email: ac.yul@ aero.bombardier.com; internet: https:// www.bombardier.com. (4) You may view this service information at the FAA, Transport Standards Branch, 2200 South 216th St., Des Moines, WA. For information on the availability of this material at the FAA, call 206–231–3195. (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: https:// www.archives.gov/federal-register/cfr/ibrlocations.html. E:\FR\FM\13JNR1.SGM 13JNR1 27506 Federal Register / Vol. 84, No. 114 / Thursday, June 13, 2019 / Rules and Regulations Issued in Des Moines, Washington, on May 29, 2019. Michael Kaszycki, Acting Director, System Oversight Division, Aircraft Certification Service. [FR Doc. 2019–12351 Filed 6–12–19; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2019–0405; Product Identifier 2019–NM–003–AD; Amendment 39–19647; AD 2019–11–01] RIN 2120–AA64 Airworthiness Directives; Airbus SAS Airplanes Federal Aviation Administration (FAA), DOT. ACTION: Final rule; request for comments. AGENCY: We are superseding Airworthiness Directive (AD) 2018–25– 12, which applied to certain Airbus SAS Model A350–941 airplanes. AD 2018– 25–12 required modifying the vertical tail plane (VTP) tension bolts connection by adding sealant and protective treatment to the head of the connection, at the barrel nut cavities, and in the surrounding area. Since we issued AD 2018–25–12, it was determined that the instructions for certain airplanes are unclear for proper accomplishment of the required modification. This AD, for certain airplanes, requires accomplishing a revised modification and, for certain other airplanes, retains the modification required by AD 2018–25–12, as specified in an European Aviation Safety Agency (EASA) AD, which will be incorporated by reference. We are issuing this AD to address the unsafe condition on these products. DATES: This AD becomes effective June 28, 2019. The Director of the Federal Register approved the incorporation by reference of a certain publication listed in this AD as of June 28, 2019. We must receive comments on this AD by July 29, 2019. ADDRESSES: You may send comments, using the procedures found in 14 CFR 11.43 and 11.45, by any of the following methods: • Federal eRulemaking Portal: Go to https://www.regulations.gov. Follow the instructions for submitting comments. • Fax: 202–493–2251. • Mail: U.S. Department of Transportation, Docket Operations, khammond on DSKBBV9HB2PROD with RULES SUMMARY: VerDate Sep<11>2014 16:11 Jun 12, 2019 Jkt 247001 M–30, West Building Ground Floor, Room W12–140, 1200 New Jersey Avenue SE, Washington, DC 20590. • Hand Delivery: U.S. Department of Transportation, Docket Operations, M–30, West Building Ground Floor, Room W12–140, 1200 New Jersey Avenue SE, Washington, DC 20590, between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. For the material incorporated by reference (IBR) in this AD, contact the EASA, at Konrad-Adenauer-Ufer 3, 50668 Cologne, Germany; telephone +49 221 89990 1000; email: ADs@ easa.europa.eu; internet: www.easa.europa.eu. You may find this IBR material on the EASA website at https://ad.easa.europa.eu. You may view this IBR material at the FAA, Transport Standards Branch, 2200 South 216th St., Des Moines, WA. For information on the availability of this material at the FAA, call 206–231–3195. It is also available in the AD docket on the internet at https:// www.regulations.gov. Examining the AD Docket You may examine the AD docket on the internet at https:// www.regulations.gov by searching for and locating Docket No. FAA–2019– 0405; or in person at Docket Operations 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 street address for Docket Operations (phone: 800–647–5527) is listed above. Comments will be available in the AD docket shortly after receipt. FOR FURTHER INFORMATION CONTACT: Kathleen Arrigotti, Aerospace Engineer, International Section, Transport Standards Branch, FAA, 2200 South 216th St., Des Moines, WA 98198; telephone and fax 206–231–3218. SUPPLEMENTARY INFORMATION: Discussion We issued AD 2018–25–12, Amendment 39–19523 (83 FR 64230, December 14, 2018) (‘‘AD 2018–25– 12’’), which applied to certain Airbus SAS Model A350–941 airplanes. AD 2018–25–12 required modifying the VTP tension bolts connection by adding sealant and protective treatment to the head of the connection, at the barrel nut cavities, and in the surrounding area. AD 2018–25–12 resulted from a determination that certain holes for the VTP tension bolts connection are not properly protected against corrosion. We issued AD 2018–25–12 to address corrosion of the VTP tension bolts PO 00000 Frm 00004 Fmt 4700 Sfmt 4700 connection, which could reduce the structural integrity of the VTP, and could ultimately lead to reduced controllability of the airplane. Actions Since AD 2018–25–12 Was Issued Since we issued AD 2018–25–12, it was determined that the instructions for certain airplanes (Group 2 airplanes as identified in the EASA AD identified below), are unclear for proper accomplishment of the required modification. The EASA, which is the Technical Agent for the Member States of the European Union, has issued EASA AD 2018–0290, dated December 21, 2018 (‘‘EASA AD 2018–0290’’) (also referred to as the Mandatory Continuing Airworthiness Information, or ‘‘the MCAI’’), to correct an unsafe condition for certain Airbus SAS Model A350–941 airplanes. The MCAI states: It was identified that the section 19 holes for the Vertical Tail Plane (VTP) tension bolts connection are not properly protected against corrosion. This condition, if not corrected, could reduce the structural integrity of the VTP. To address this unsafe condition, Airbus developed production mod 108307 and mod 110696 to improve protection against corrosion, and issued the SB [service bulletin] to provide in-service modification instructions. Consequently, EASA issued AD 2018–0045 [which corresponds to FAA 2018–25–12] to require a modification by adding sealant and protective treatment to the head of the section 19 VTP tension bolts connection, at the barrel nut cavities and in the surrounding area. Since that [EASA] AD was issued, it was identified that the instructions for Group 2 aeroplanes, as identified in the SB, were not clear enough for proper accomplishment. Consequently, Airbus published Revision 01 of the SB to clarify those instructions for Group 2 aeroplanes. For the reasons described above, this [EASA] AD retains the requirements of EASA AD 2018–0045, which is superseded, and requires, for Group 2 aeroplanes, accomplishment of the modification in accordance with the instructions of Revision 01 of the SB. You may examine the MCAI in the AD docket on the internet at https:// www.regulations.gov by searching for and locating Docket No. FAA–2019– 0405. Explanation of Retained Requirements Although this AD does not explicitly restate the requirements of AD 2018– 25–12, this AD retains certain requirements of AD 2018–25–12 with clarified instructions. Those requirements are referenced in EASA AD 2018–0290, which, in turn, is referenced in paragraph (g) of this AD. E:\FR\FM\13JNR1.SGM 13JNR1

Agencies

[Federal Register Volume 84, Number 114 (Thursday, June 13, 2019)]
[Rules and Regulations]
[Pages 27503-27506]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2019-12351]



========================================================================
Rules and Regulations
                                                Federal Register
________________________________________________________________________

This section of the FEDERAL REGISTER contains regulatory documents 
having general applicability and legal effect, most of which are keyed 
to and codified in the Code of Federal Regulations, which is published 
under 50 titles pursuant to 44 U.S.C. 1510.

The Code of Federal Regulations is sold by the Superintendent of Documents. 

========================================================================


Federal Register / Vol. 84, No. 114 / Thursday, June 13, 2019 / Rules 
and Regulations

[[Page 27503]]



DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2019-0024; Product Identifier 2018-NM-138-AD; Amendment 
39-19640; AD 2019-10-01]
RIN 2120-AA64


Airworthiness Directives; Bombardier, Inc., Airplanes

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

ACTION: Final rule.

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

SUMMARY: We are adopting a new airworthiness directive (AD) for certain 
Bombardier, Inc., Model CL-600-2A12 (601) airplanes. This AD was 
prompted by a report of damage to the anti-rotation tab on a main 
landing gear (MLG) side brace fitting due to the installation of an 
incorrect side brace fitting shaft. This AD requires an inspection of 
the MLG side brace fitting for damage, a verification of the side brace 
fitting shaft part number, and replacement of the side brace fitting 
shaft if necessary. It also requires the installation of an anti-
rotation bracket. We are issuing this AD to address the unsafe 
condition on these products.

DATES: This AD is effective July 18, 2019.
    The Director of the Federal Register approved the incorporation by 
reference of a certain publication listed in this AD as of July 18, 
2019.

ADDRESSES: For service information identified in this final rule, 
contact Bombardier, Inc., 200 C[ocirc]te-Vertu Road West, Dorval, 
Qu[eacute]bec H4S 2A3, Canada; North America toll-free telephone 1-866-
538-1247 or direct-dial telephone 1-514-855-2999; email 
[email protected]; internet https://www.bombardier.com. You may 
view this service information at the FAA, Transport Standards Branch, 
2200 South 216th St., Des Moines, WA. For information on the 
availability of this material at the FAA, call 206-231-3195. It is also 
available on the internet at https://www.regulations.gov by searching 
for and locating Docket No. FAA-2019-0024.

Examining the AD Docket

    You may examine the AD docket on the internet at https://www.regulations.gov by searching for and locating Docket No. FAA-2019-
0024; or in person at Docket Operations between 9 a.m. and 5 p.m., 
Monday through Friday, except Federal holidays. The AD docket contains 
this final rule, the regulatory evaluation, any comments received, and 
other information. The address for Docket Operations (phone: 800-647-
5527) is 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: Aziz Ahmed, Aerospace Engineer, FAA, 
New York ACO Branch, 1600 Stewart Avenue, Suite 410, Westbury, New York 
11590; telephone: 516-287-7329; fax: 516-794-5531; email: 
[email protected].

SUPPLEMENTARY INFORMATION: 

Discussion

    We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR 
part 39 by adding an AD that would apply to certain Bombardier, Inc., 
Model CL-600-2A12 (601) airplanes. The NPRM published in the Federal 
Register on February 28, 2019 (84 FR 6705). The NPRM was prompted by a 
report of damage to the anti-rotation tab on an MLG side brace fitting 
due to the installation of an incorrect side brace fitting shaft. The 
NPRM proposed to require an inspection of the MLG side brace fitting 
for damage, a verification of the side brace fitting shaft part number, 
and replacement of the side brace fitting shaft if necessary. It also 
proposed to require the installation of an anti-rotation bracket.
    We are issuing this AD to address premature cracking of the MLG 
side brace fitting. This condition, if not corrected, could lead to the 
collapse of the MLG, resulting in structural damage to the wing spar 
and fuel tank.
    Transport Canada Civil Aviation (TCCA), which is the aviation 
authority for Canada, has issued Canadian AD CF-2018-19, dated July 20, 
2018 (referred to after this as the Mandatory Continuing Airworthiness 
Information, or ``the MCAI''), to correct an unsafe condition for 
certain Bombardier, Inc., Model CL-600-2A12 (601) airplanes. The MCAI 
states:

    There has been a report of damage to the anti-rotation tab on a 
Main Landing Gear (MLG) Side Brace fitting. Investigation of the 
report revealed that a Challenger model CL600 MLG Side Brace shaft 
had been installed on a Challenger model CL601 Side Brace fitting. 
Due to the difference in size, this will result in changes to the 
way the load is transferred between the shaft and the MLG Side Brace 
fitting and may result in premature cracking of the MLG Side Brace 
fitting. This condition, if not corrected, could lead to the 
collapse of the MLG resulting in structural damage to the wing spar 
and fuel tank.
    This [Canadian] AD mandates an inspection of the MLG Side Brace 
fitting and shaft to verify that the correct shaft part number (P/N) 
is installed and the fitting is not damaged [damage includes 
cracking, scratches, gouges, corrosion, defects, and incorrect inner 
diameter tolerance]. If the Challenger CL600 shaft is installed, 
this AD mandates replacement with the correct Challenger model CL601 
part. If the correct P/N is found installed, this [Canadian] AD also 
mandates the installation of a bracket to prevent the incorrect part 
from being installed in the future.

    You may examine the MCAI in the AD docket on the internet at https://www.regulations.gov by searching for and locating Docket No. FAA-2019-
0024.

Comments

    We gave the public the opportunity to participate in developing 
this final rule. We received no comments on the NPRM or on the 
determination of the cost to the public.

Conclusion

    We reviewed the relevant data and determined that air safety and 
the public interest require adopting this final rule as proposed, 
except for minor editorial changes. We have determined that these minor 
changes:
     Are consistent with the intent that was proposed in the 
NPRM for addressing the unsafe condition; and
     Do not add any additional burden upon the public than was 
already proposed in the NPRM.

[[Page 27504]]

Related Service Information Under 1 CFR Part 51

    Bombardier has issued Service Bulletin 601-0624, Revision 02, dated 
January 29, 2018. This service information describes procedures for 
inspecting the MLG side brace fitting and side brace fitting shaft, 
installing a replacement side brace fitting shaft if necessary, and 
installing an anti-rotation bracket.
    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 9 airplanes of U.S. registry. We 
estimate the following costs to comply with this AD:

                                      Estimated Costs for Required Actions
----------------------------------------------------------------------------------------------------------------
                                                                                    Cost per       Cost on U.S.
                          Labor cost                              Parts cost        product         operators
----------------------------------------------------------------------------------------------------------------
4 work-hours x $85 per hour = $340...........................            $397             $737           $6,633
----------------------------------------------------------------------------------------------------------------

    We estimate the following costs to do any necessary on-condition 
actions that would be required based on the results of any required 
actions. We have no way of determining the number of aircraft that 
might need these on-condition actions:

                 Estimated Costs of On-Condition Actions
------------------------------------------------------------------------
                                                             Cost per
              Labor cost                   Parts cost        product
------------------------------------------------------------------------
8 work-hours x $85 per hour = $680....          $7,989           $8,669
------------------------------------------------------------------------

Authority for This Rulemaking

    Title 49 of the United States Code specifies the FAA's authority to 
issue rules on aviation safety. Subtitle I, section 106, describes the 
authority of the FAA Administrator. Subtitle VII: Aviation Programs, 
describes in more detail the scope of the Agency's authority.
    We are issuing this rulemaking under the authority described in 
Subtitle VII, Part A, Subpart III, Section 44701: ``General 
requirements.'' Under that section, Congress charges the FAA with 
promoting safe flight of civil aircraft in air commerce by prescribing 
regulations for practices, methods, and procedures the Administrator 
finds necessary for safety in air commerce. This regulation is within 
the scope of that authority because it addresses an unsafe condition 
that is likely to exist or develop on products identified in this 
rulemaking action.
    This AD is issued in accordance with authority delegated by the 
Executive Director, Aircraft Certification Service, as authorized by 
FAA Order 8000.51C. In accordance with that order, issuance of ADs is 
normally a function of the Compliance and Airworthiness Division, but 
during this transition period, the Executive Director has delegated the 
authority to issue ADs applicable to transport category airplanes and 
associated appliances to the Director of the System Oversight Division.

Regulatory Findings

    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 adding the following new airworthiness 
directive (AD):

2019-10-01 Bombardier, Inc.: Amendment 39-19640; Docket No. FAA-
2019-0024; Product Identifier 2018-NM-138-AD.

(a) Effective Date

    This AD is effective July 18, 2019.

(b) Affected ADs

    None.

(c) Applicability

    This AD applies to Bombardier, Inc., Model CL-600-2A12 (601) 
airplanes, certificated in any category, serial numbers (S/N) 3001 
through 3009 inclusive and 3011 through 3029 inclusive.

(d) Subject

    Air Transport Association (ATA) of America Code 57, Wings.

(e) Reason

    This AD was prompted by a report of damage to the anti-rotation 
tab on a main landing gear (MLG) side brace fitting due to the 
installation of an incorrect side brace fitting shaft. We are 
issuing this AD to address premature cracking of the MLG side brace 
fitting. This condition, if not corrected, could lead to the 
collapse of the MLG, resulting in structural damage to the wing spar 
and fuel tank.

[[Page 27505]]

(f) Compliance

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

(g) Inspection for Damage and Identification of the Side Brace Fitting 
Shaft Part Number

    Within 400 flight cycles or 12 months, whichever occurs first, 
after the effective date of this AD, do the actions specified in 
paragraphs (g)(1) and (g)(2) of this AD.
    (1) Identify the part number of the installed side brace fitting 
shaft.
    (2) Do a detailed visual inspection (DVI) of the side brace 
fitting for signs of damage, including cracking and gouges, in 
accordance with paragraph 2.B. of the Accomplishment Instructions of 
Bombardier Service Bulletin 601-0624, Revision 02, dated January 29, 
2018.

(h) Installation of Anti-Rotation Bracket

    (1) For airplanes on which a side brace fitting shaft having P/N 
600-10237-3 is installed and the actions required by paragraph (g) 
of this AD are done on or after the effective date of this AD: 
Before further flight, modify the MLG side brace fitting by 
installing the anti-rotation bracket in accordance with paragraph 
2.C. of the Accomplishment Instructions of Bombardier Service 
Bulletin 601-0624, Revision 02, dated January 29, 2018.
    (2) For airplanes on which a side brace fitting shaft having P/N 
600-10237-3 is installed and the actions required by paragraph (g) 
of this AD were done before the effective date of this AD: Within 6 
months after the effective date of this AD, modify the MLG side 
brace fitting by installing the anti-rotation bracket in accordance 
with paragraph 2.C. of the Accomplishment Instructions of Bombardier 
Service Bulletin 601-0624, Revision 02, dated January 29, 2018.

(i) Replacement of the Side Brace Fitting Shaft and Installation of the 
Anti-Rotation Bracket

    (1) For airplanes on which a side brace fitting shaft having P/N 
600-10237-1 or 600-10237-5 is installed and damage is found during 
the DVI of the side brace fitting: Before further flight, do a DVI 
of the anti-rotation tab and side brace fitting aft bushing for 
cracking, scratches, gouges, corrosion, and inner diameter 
tolerance, and a special detailed inspection (SDI) of the side brace 
fitting aft bore for cracks and defects; perform applicable repairs; 
replace the side brace fitting shaft with a side brace fitting shaft 
having P/N 600-10237-3; and install the anti-rotation bracket in 
accordance with paragraph 2.D. of the Accomplishment Instructions of 
Bombardier Service Bulletin 601-0624, Revision 02, dated January 29, 
2018.
    (2) For airplanes on which a side brace fitting shaft having P/N 
600-10237-1 or 600-10237-5 is installed and no damage is found 
during the DVI of the side brace fitting: Within 300 flight cycles 
or 12 months, whichever occurs first, after the inspection required 
by paragraph (g)(2) of this AD, do a DVI of the anti-rotation tab 
and side brace fitting aft bushing for cracking, scratches, gouges, 
corrosion, and inner diameter tolerance, and an SDI of the side 
brace fitting aft bore for cracks and defects; perform applicable 
repairs; replace the side brace fitting shaft with a side brace 
fitting shaft having P/N 600-10237-3; and install the anti-rotation 
bracket in accordance with paragraph 2.D. of the Accomplishment 
Instructions of Bombardier Service Bulletin 601-0624, Revision 02, 
dated January 29, 2018.

(j) Exceptions to Service Information

    Where Bombardier Service Bulletin 601-0624, Revision 02, dated 
January 29, 2018, specifies contacting Bombardier's Customer Support 
Engineering for repair instructions: This AD requires doing the 
repair before further flight using a method approved in accordance 
with the procedures specified in paragraph (l)(2) of this AD.

(k) Credit for Previous Actions

    (1) For an airplane on which a side brace fitting shaft having 
P/N 600-10237-3 is installed: This paragraph provides credit for 
actions required by paragraphs (g) and (h) of this AD, if those 
actions were performed before the effective date of this AD using 
Bombardier Service Bulletin 601-0624, dated October 1, 2012; or 
Bombardier Service Bulletin 601-0624, Revision 01, dated March 29, 
2017.
    (2) 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 601-
0624, dated October 1, 2012; or Bombardier Service Bulletin 601-
0624, Revision 01, dated March 29, 2017, provided that the side 
brace fitting shaft was identified as having P/N 600-10237-3 and 
within 6 months after the effective date of this AD, the MLG side 
brace fitting is modified by installing the anti-rotation bracket in 
accordance with paragraph 2.C. of the Accomplishment Instructions of 
Bombardier Service Bulletin 601-0624, Revision 02, dated January 29, 
2018.
    (3) This paragraph provides credit for actions required by 
paragraphs (g) and (i) of this AD, if those actions were performed 
before the effective date of this AD using Bombardier Service 
Bulletin 601-0624, Revision 01, dated March 29, 2017, provided that 
any side brace fitting shaft having P/N 600-10237-1 or P/N 600-
10237-5 was identified and replaced with a side brace fitting shaft 
having P/N 600-10237-3, and the anti-rotation bracket was installed 
in accordance with paragraph 2.D. of the Accomplishment Instructions 
of Bombardier Service Bulletin 601-0624, Revision 01, dated March 
29, 2017.

(l) Other FAA AD Provisions

    The following provisions also apply to this AD:
    (1) Alternative Methods of Compliance (AMOCs): The Manager, New 
York ACO Branch, FAA, has the authority to approve AMOCs for this 
AD, if requested using the procedures found in 14 CFR 39.19. In 
accordance with 14 CFR 39.19, send your request to your principal 
inspector or local Flight Standards District Office, as appropriate. 
If sending information directly to the manager of the certification 
office, send it to ATTN: Program Manager, Continuing Operational 
Safety, FAA, New York ACO Branch, 1600 Stewart Avenue, Suite 410, 
Westbury, NY 11590; telephone 516-228-7300; fax 516-794-5531. Before 
using any approved AMOC, notify your appropriate principal 
inspector, or lacking a principal inspector, the manager of the 
local flight standards district office/certificate holding district 
office.
    (2) Contacting the Manufacturer: For any requirement in this AD 
to obtain corrective actions from a manufacturer, the action must be 
accomplished using a method approved by the Manager, New York ACO 
Branch, FAA; or Transport Canada Civil Aviation (TCCA); or 
Bombardier, Inc.'s TCCA Design Approval Organization (DAO). If 
approved by the DAO, the approval must include the DAO-authorized 
signature.

(m) Related Information

    (1) Refer to Mandatory Continuing Airworthiness Information 
(MCAI) Canadian AD CF-2018-19, dated July 20, 2018, for related 
information. This MCAI may be found in the AD docket on the internet 
at https://www.regulations.gov by searching for and locating Docket 
No. FAA-2019-0024.
    (2) For more information about this AD, contact Aziz Ahmed, 
Aerospace Engineer, FAA, New York ACO Branch, 1600 Stewart Avenue, 
Suite 410, Westbury, New York 11590; telephone: 516-287-7329; fax: 
516-794-5531; email: [email protected].
    (3) Service information identified in this AD that is not 
incorporated by reference is available at the addresses specified in 
paragraphs (n)(3) and (n)(4) of this AD.

(n) 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 601-0624, Revision 02, dated 
January 29, 2018.
    (ii) [Reserved]
    (3) For service information identified in this AD, contact 
Bombardier, Inc., 200 C[ocirc]te-Vertu Road West, Dorval, 
Qu[eacute]bec H4S 2A3, Canada; North America toll-free telephone: 1-
866-538-1247 or direct-dial telephone: 1-514-855-2999; email: 
[email protected]; internet: https://www.bombardier.com.
    (4) You may view this service information at the FAA, Transport 
Standards Branch, 2200 South 216th St., Des Moines, WA. For 
information on the availability of this material at the FAA, call 
206-231-3195.
    (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: https://www.archives.gov/federal-register/cfr/ibr-locations.html.


[[Page 27506]]


    Issued in Des Moines, Washington, on May 29, 2019.
Michael Kaszycki,
Acting Director, System Oversight Division, Aircraft Certification 
Service.
[FR Doc. 2019-12351 Filed 6-12-19; 8:45 am]
 BILLING CODE 4910-13-P
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