Airworthiness Directives; Bombardier, Inc., Airplanes, 31453-31456 [2021-12351]

Download as PDF Federal Register / Vol. 86, No. 112 / Monday, June 14, 2021 / Proposed Rules § 39.13 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. The FAA is issuing this rulemaking under the authority described in Subtitle VII, Part A, Subpart III, Section 44701: General requirements. Under that section, Congress charges the FAA with promoting safe flight of civil aircraft in air commerce by prescribing regulations for practices, methods, and procedures the Administrator finds necessary for safety in air commerce. This regulation is within the scope of that authority because it addresses an unsafe condition that is likely to exist or develop on products identified in this rulemaking action. Regulatory Findings The FAA determined that this proposed AD would not have federalism implications under Executive Order 13132. This proposed AD would not have a substantial direct effect on the States, on the relationship between the national Government and the States, or on the distribution of power and responsibilities among the various levels of government. For the reasons discussed above, I certify this proposed regulation: (1) Is not a ‘‘significant regulatory action’’ under Executive Order 12866, (2) Will not affect intrastate aviation in Alaska, and (3) 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. lotter on DSK11XQN23PROD with PROPOSALS1 The Proposed Amendment Accordingly, under the authority delegated to me by the Administrator, the FAA proposes to amend 14 CFR part 39 as follows: PART 39—AIRWORTHINESS DIRECTIVES 1. The authority citation for part 39 continues to read as follows: ■ Authority: 49 U.S.C. 106(g), 40113, 44701. VerDate Sep<11>2014 16:49 Jun 11, 2021 Jkt 253001 [Amended] 2. The FAA amends § 39.13 by adding the following new airworthiness directive: ■ Leonardo S.p.a.: Docket No. FAA–2021– 0461; Project Identifier MCAI–2021– 00156–R. (a) Comments Due Date The FAA must receive comments on this airworthiness directive (AD) by July 29, 2021. (b) Affected ADs None. (c) Applicability This AD applies to all Leonardo S.p.a. Model AB139 and AW139 helicopters, certificated in any category. (d) Subject Joint Aircraft System Component (JASC) Code 2400, Electrical Power System. (e) Unsafe Condition This AD was prompted by a report of a short circuit caused by chafing of the electrical wiring in the overhead panel. The FAA is issuing this AD to address a short circuit caused by chafing of the electrical wiring in the overhead panel, which could cause damaged electrical wiring, possible fire in the overhead panel, and loss of control of the helicopter. (f) Compliance Comply with this AD within the compliance times specified, unless already done. (g) Requirements Except as specified in paragraph (h) of this AD: Comply with all required actions and compliance times specified in, and in accordance with, European Union Aviation Safety Agency (EASA) AD 2021–0044, dated February 5, 2021 (EASA AD 2021–0044). (h) Exceptions to EASA AD 2021–0044 (1) Where EASA AD 2021–0044 refers to its effective date, this AD requires using the effective date of this AD. (2) The ‘‘Remarks’’ section of EASA AD 2021–0044 does not apply to this AD. (3) Where EASA AD 2021–0044 refers to flight hours (FH), this AD requires using hours time-in-service. (4) Where paragraphs (3) and (5) of EASA AD 2021–0044 refer to ‘‘any discrepancy,’’ for this AD, discrepancies include chafing of the cable harnesses or incorrect clearance between the anchor nuts/screws and the cable harnesses, incorrect length of the screws, inadequately bonded supports, and poor condition of the white protective tape. (i) No Reporting Requirement Although EASA AD 2021–0044 and the service information referenced in EASA AD 2021–0044 specify to submit certain information to the manufacturer, this AD does not include that requirement. (j) Special Flight Permit Special flight permits may be issued in accordance with 14 CFR 21.197 and 21.199 PO 00000 Frm 00003 Fmt 4702 Sfmt 4702 31453 to operate the helicopter to a location where the helicopter can be modified (if the operator elects to do so), provided the flight is straight, level, and avoids areas of known turbulence. (k) Alternative Methods of Compliance (AMOCs) (1) The Manager, International Validation 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 International Validation Branch, send it to the attention of the person identified in paragraph (l)(2) of this AD. Information may be emailed to: 9-AVS-AIR730-AMOC@faa.gov. (2) 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. (l) Related Information (1) For EASA AD 2021–0044, contact the EASA, Konrad-Adenauer-Ufer 3, 50668 Cologne, Germany; phone: +49 221 8999 000; email: ADs@easa.europa.eu; internet: www.easa.europa.eu. You may find this EASA AD on the EASA website at https:// ad.easa.europa.eu. You may view this material at the FAA, Office of the Regional Counsel, Southwest Region, 10101 Hillwood Pkwy., Room 6N–321, Fort Worth, TX 76177. For information on the availability of this material at the FAA, call 817–222–5110. This material may be found in the AD docket at https://www.regulations.gov by searching for and locating Docket No. FAA–2021–0461. (2) For more information about this AD, contact Jacob Fitch, Aerospace Engineer, COS Program Management Section, Operational Safety Branch, Compliance & Airworthiness Division, FAA, 10101 Hillwood Pkwy., Fort Worth, TX 76177; phone: (817) 222–4130; email: jacob.fitch@faa.gov. Issued on June 7, 2021. Ross Landes, Deputy Director for Regulatory Operations, Compliance & Airworthiness Division, Aircraft Certification Service. [FR Doc. 2021–12359 Filed 6–11–21; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2021–0462; Project Identifier MCAI–2020–01714–T] RIN 2120–AA64 Airworthiness Directives; Bombardier, Inc., Airplanes Federal Aviation Administration (FAA), DOT. AGENCY: E:\FR\FM\14JNP1.SGM 14JNP1 31454 Federal Register / Vol. 86, No. 112 / Monday, June 14, 2021 / Proposed Rules Notice of proposed rulemaking (NPRM). ACTION: The FAA proposes to adopt a new airworthiness directive (AD) for certain Bombardier, Inc., CL–600–2B16 (604 Variant) airplanes. This proposed AD was prompted by multiple reports of cracking of the main landing gear (MLG) shock strut lower pin. This proposed AD would require repetitive lubrication and repetitive detailed visual inspections (DVI) and non-destructive test (NDT) inspections of the MLG shock strut lower pins, and replacement if necessary. The FAA is proposing this AD to address the unsafe condition on these products. DATES: The FAA must receive comments on this proposed AD by July 29, 2021. 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, M–30, West Building Ground Floor, Room W12–140, 1200 New Jersey Avenue SE, Washington, DC 20590. • Hand Delivery: Deliver to Mail address above between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. For service information identified in this NPRM, 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, Airworthiness Products Section, Operational Safety Branch, 2200 South 216th St., Des Moines, WA. For information on the availability of this material at the FAA, call 206–231–3195. SUMMARY: lotter on DSK11XQN23PROD with PROPOSALS1 Examining the AD Docket You may examine the AD docket at https://www.regulations.gov by searching for and locating Docket No. FAA–2021–0462; 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 NPRM, any comments received, and other information. The street address for Docket Operations is listed above. FOR FURTHER INFORMATION CONTACT: Chirayu Gupta, Aerospace Engineer, Mechanical Systems and Administrative Services Section, FAA, New York ACO VerDate Sep<11>2014 16:49 Jun 11, 2021 Jkt 253001 Branch, 1600 Stewart Avenue, Suite 410, Westbury, NY 11590; telephone 516–228–7300; fax 516–794–5531; email 9-avs-nyaco-cos@faa.gov. SUPPLEMENTARY INFORMATION: Comments Invited The FAA invites you to send any written relevant data, views, or arguments about this proposal. Send your comments to an address listed under ADDRESSES. Include ‘‘Docket No. FAA–2021–0462; Project Identifier MCAI–2020–01714–T’’ at the beginning of your comments. The most helpful comments reference a specific portion of the proposal, explain the reason for any recommended change, and include supporting data. The FAA will consider all comments received by the closing date and may amend the proposal because of those comments. Except for Confidential Business Information (CBI) as described in the following paragraph, and other information as described in 14 CFR 11.35, the FAA will post all comments received, without change, to https:// www.regulations.gov, including any personal information you provide. The agency will also post a report summarizing each substantive verbal contact received about this NPRM. Confidential Business Information CBI is commercial or financial information that is both customarily and actually treated as private by its owner. Under the Freedom of Information Act (FOIA) (5 U.S.C. 552), CBI is exempt from public disclosure. If your comments responsive to this NPRM contain commercial or financial information that is customarily treated as private, that you actually treat as private, and that is relevant or responsive to this NPRM, it is important that you clearly designate the submitted comments as CBI. Please mark each page of your submission containing CBI as ‘‘PROPIN.’’ The FAA will treat such marked submissions as confidential under the FOIA, and they will not be placed in the public docket of this NPRM. Submissions containing CBI should be sent to Chirayu Gupta, Aerospace Engineer, Mechanical Systems and Administrative Services Section, FAA, New York ACO Branch, 1600 Stewart Avenue, Suite 410, Westbury, NY 11590; telephone 516– 228–7300; fax 516–794–5531; email 9avs-nyaco-cos@faa.gov. Any commentary that the FAA receives which is not specifically designated as CBI will be placed in the public docket for this rulemaking. PO 00000 Frm 00004 Fmt 4702 Sfmt 4702 Background Transport Canada Civil Aviation (TCCA), which is the aviation authority for Canada, has issued TCCA AD CF– 2020–54R1, dated December 23, 2020 (TCCA AD CF–2020–54R1) (also referred to after this as the Mandatory Continuing Airworthiness Information, or the MCAI), to correct an unsafe condition for certain Bombardier, Inc., CL–600–2B16 (604 Variant) airplanes. You may examine the MCAI in the AD docket at https://www.regulations.gov by searching for and locating Docket No. FAA–2021–0462. This proposed AD was prompted by multiple reports of cracking of the MLG shock strut lower pin part number (P/N) 19146–3. The subsequent investigation concluded that the friction torque when the shock strut is under compression loading, causes the pin anti-rotation tangs to become loaded beyond their load carrying capability. This overload condition can result in pin fracture originating at the base of the pin antirotation tang. Inadequate lubrication aggravates the condition. The FAA is proposing this AD to address cracking of the MLG shock strut lower pin. If not addressed, this condition could result in structural failure of one or both MLG. See the MCAI for additional background information. Related Service Information Under 1 CFR Part 51 Bombardier, Inc., has issued the following service information: • Service Bulletin 604–32–030, dated June 30, 2020. • Service Bulletin 605–32–007, dated June 30, 2020. • Service Bulletin 650–32–004, dated June 30, 2020. This service information describes procedures for lubricating, inspecting (DVI and NDT inspections for cracking and damage, including fracture of the MLG shock strut lower pin at the pin rotation tang location), and replacing the MLG shock strut lower pin. These documents are distinct since they apply to different airplane configurations. 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. FAA’s Determination This product has been approved by the aviation authority of another country, and is approved for operation in the United States. Pursuant to the FAA’s bilateral agreement with the State of Design Authority, the FAA has been notified of the unsafe condition E:\FR\FM\14JNP1.SGM 14JNP1 Federal Register / Vol. 86, No. 112 / Monday, June 14, 2021 / Proposed Rules described in the MCAI and service information referenced above. The FAA is proposing this AD because the FAA evaluated all the relevant information and determined the unsafe condition described previously is likely to exist or develop on other products of the same type design. Proposed AD Requirements in This NPRM This proposed AD would require accomplishing the actions specified in the service information already described. 31455 Costs of Compliance The FAA estimates that this AD, if adopted as proposed, would affect 433 airplanes of U.S. registry. The FAA estimates the following costs to comply with this proposed AD: ESTIMATED COSTS FOR REQUIRED ACTIONS Labor cost Parts cost Cost per product Cost on U.S. operators 7 work-hours × $85 per hour = $595 .......................................................................................... $0 $595 $257,635 The FAA estimates the following costs to do any necessary on-condition actions that would be required based on the results of any required actions. The FAA has no way of determining the number of aircraft that might need these on-condition actions: ESTIMATED COSTS OF ON-CONDITION ACTIONS Labor cost Parts cost Cost per product 6 work-hours × $85 per hour = $510 ...................................................................................................................... $2,435 $2,945 The FAA has included all known costs in its cost estimate. According to the manufacturer, however, some or all of the costs of this proposed AD may be covered under warranty, thereby reducing the cost impact on affected operators. lotter on DSK11XQN23PROD with PROPOSALS1 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. The FAA is issuing this rulemaking under the authority described in Subtitle VII, Part A, Subpart III, Section 44701: General requirements. Under that section, Congress charges the FAA with promoting safe flight of civil aircraft in air commerce by prescribing regulations for practices, methods, and procedures the Administrator finds necessary for safety in air commerce. This regulation is within the scope of that authority because it addresses an unsafe condition that is likely to exist or develop on products identified in this rulemaking action. Regulatory Findings The FAA determined that this proposed AD would not have federalism implications under Executive Order 13132. This proposed AD would not have a substantial direct effect on the States, on the relationship between the national Government and the States, or VerDate Sep<11>2014 16:49 Jun 11, 2021 Jkt 253001 on the distribution of power and responsibilities among the various levels of government. For the reasons discussed above, I certify this proposed regulation: (1) Is not a ‘‘significant regulatory action’’ under Executive Order 12866, (2) Would not affect intrastate aviation in Alaska, and (3) Would not have a significant economic impact, positive or negative, on a substantial number of small entities under the criteria of the Regulatory Flexibility Act. List of Subjects in 14 CFR Part 39 Air transportation, Aircraft, Aviation safety, Incorporation by reference, Safety. The Proposed Amendment Accordingly, under the authority delegated to me by the Administrator, the FAA proposes to amend 14 CFR part 39 as follows: PART 39—AIRWORTHINESS DIRECTIVES 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: ■ Bombardier, Inc.: Docket No. FAA–2021– 0462; Project Identifier MCAI–2020– 01714–T. PO 00000 Frm 00005 Fmt 4702 Sfmt 4702 (a) Comments Due Date The FAA must receive comments on this airworthiness directive (AD) by July 29, 2021. (b) Affected ADs None. (c) Applicability This AD applies to Bombardier, Inc., Model CL–600–2B16 (604 Variant) airplanes, serial numbers (S/N) 5301 through 5665 inclusive, 5701 through 5988 inclusive, and 6050 through 6999 inclusive, certificated in any category. (d) Subject Air Transport Association (ATA) of America Code 32, Landing gear. (e) Unsafe Condition This AD was prompted by multiple reports of cracking of the main landing gear (MLG) shock strut lower pin. The FAA is issuing this AD to address cracking of the MLG shock strut lower pin. If not addressed, this condition could result in structural failure of one or both MLG. (f) Compliance Comply with this AD within the compliance times specified, unless already done. (g) Repetitive Lubrication Within 200 flight hours (FH) or 12 months after the effective date of this AD, whichever occurs first, lubricate the left-hand (LH) and right-hand (RH) MLG shock strut lower pins having part number (P/N) 19146–3, in accordance with paragraph 2.B., ‘‘Part A,’’ of the Accomplishment Instructions of the applicable service bulletin, as specified in paragraphs (g)(1) through (3) of this AD. Repeat thereafter at intervals not to exceed 200 FH or 12 months, whichever occurs first. E:\FR\FM\14JNP1.SGM 14JNP1 31456 Federal Register / Vol. 86, No. 112 / Monday, June 14, 2021 / Proposed Rules (1) For airplanes having S/N 5301 through 5665 inclusive: Bombardier Service Bulletin 604–32–030, dated June 30, 2020. (2) For airplanes having S/N 5701 through 5988 inclusive: Bombardier Service Bulletin 605–32–007, dated June 30, 2020. (3) For airplanes having S/N 6050 through 6999 inclusive: Bombardier Service Bulletin 650–32–004, dated June 30, 2020. lotter on DSK11XQN23PROD with PROPOSALS1 (h) Repetitive Detailed Visual Inspections (DVI) At the applicable compliance time specified in paragraphs (h)(1) through (3) of this AD, perform the DVI for cracking and damage of the LH and RH MLG shock strut lower pins having part number (P/N) 19146– 3, in accordance with paragraph 2.C., ‘‘Part B,’’ of the Accomplishment Instructions of the applicable service bulletin, as specified in paragraphs (g)(1) through (3) of this AD. Repeat thereafter at intervals not to exceed 400 FH or 24 months, whichever occurs first. If the DVI coincides with a non-destructive testing (NDT) inspection required by paragraph (i) of this AD, the NDT inspection supersedes the DVI for that interval only. If the accumulated flight cycles (FC) of the MLG shock strut lower pin are not known, use the related MLG assembly accumulated FC to determine when to accomplish the actions required by this paragraph. (1) For airplanes with an original airworthiness certificate or original export certificate of airworthiness issued on or before the effective date of this AD and on which an MLG shock strut lower pin has accumulated fewer than 600 total FC on the pin as of the effective date of this AD: Before the accumulation of 750 total FC on the pin. (2) For airplanes with an original airworthiness certificate or original export certificate of airworthiness issued on or before the effective date of this AD and on which an MLG shock strut lower pin has accumulated 600 total FC or more on the pin as of the effective date of this AD: Within 150 FC after the effective date of this AD. (3) For airplanes with an original airworthiness certificate or original export certificate of airworthiness issued after the effective date of this AD: Before the accumulation of 750 total FC. (i) Repetitive NDT Inspection At the applicable compliance time specified in paragraphs (i)(1) through (4) of this AD: Perform the NDT for cracking and damage of the LH and RH MLG shock strut lower pins having P/N 19146–3, in accordance with paragraph 2.D., ‘‘Part C,’’ of the Accomplishment Instructions of the applicable service bulletin, as specified in paragraphs (g)(1) through (3) of this AD. Repeat thereafter at intervals not to exceed 900 FC. If the accumulated FC of the MLG shock strut lower pin is not known, use the related MLG assembly accumulated FC to determine when to accomplish the actions required by this paragraph. (1) For airplanes with an original airworthiness certificate or original export certificate of airworthiness issued on or before the effective date of this AD and on which an MLG shock strut lower pin has accumulated fewer than 1,200 total FC on the VerDate Sep<11>2014 16:49 Jun 11, 2021 Jkt 253001 pin as of the effective date of this AD: Before the accumulation of 1,500 total FC on the pin. (2) For airplanes with an original airworthiness certificate or original export certificate of airworthiness issued on or before the effective date of this AD and on which an MLG shock strut lower pin has accumulated 1,200 total FC or more but fewer than 2,000 total FC on the pin as of the effective date of this AD: Within 300 FC after the effective date of this AD, or before the accumulation of 2,200 total FC on the pin, whichever occurs first. (3) For airplanes with an original airworthiness certificate or original export certificate of airworthiness issued on or before the effective date of this AD and on which an MLG shock strut lower pin that has accumulated 2,000 total FC or more on the pin as of the effective date of this AD: Within 200 FC after the effective date of this AD. (4) For airplanes with an original airworthiness certificate or original export certificate of airworthiness issued after the effective date of this AD: Before the accumulation of 1,500 total FC. (j) Replacement If, during any inspection required by this AD, any crack or damage of the MLG shock strut lower pin is detected, before further flight, replace the affected MLG shock strut lower pin with a new part in accordance with paragraph 2.E., ‘‘Part D,’’ of the Accomplishment Instructions of the applicable service bulletin, as specified in paragraphs (g)(1) through (3) of this AD. (k) 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 responsible Flight Standards 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 responsible Flight Standards Office. (2) Contacting the Manufacturer: For any requirement in this AD to obtain instructions from a manufacturer, the instructions 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. (l) Related Information (1) Refer to Mandatory Continuing Airworthiness Information (MCAI) TCCA AD CF–2020–54R1, dated December 23, 2020, for related information. This MCAI may be PO 00000 Frm 00006 Fmt 4702 Sfmt 4702 found in the AD docket on the internet at https://www.regulations.gov by searching for and locating Docket No. FAA–2021–0462. (2) For more information about this AD, contact Chirayu Gupta, Aerospace Engineer, Mechanical Systems and Administrative Services Section, FAA, New York ACO Branch, 1600 Stewart Avenue, Suite 410, Westbury, NY 11590; telephone 516–228– 7300; fax 516–794–5531; email 9-avs-nyacocos@faa.gov. (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. You may view this service information at the FAA, Airworthiness Products Section, Operational Safety Branch, 2200 South 216th St., Des Moines, WA. For information on the availability of this material at the FAA, call 206–231–3195. Issued on June 8, 2021. Lance T. Gant, Director, Compliance & Airworthiness Division, Aircraft Certification Service. [FR Doc. 2021–12351 Filed 6–11–21; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF HOMELAND SECURITY Coast Guard 33 CFR Part 165 [Docket Number USCG–2021–0135] RIN 1625–AA00 Safety Zones; Fireworks Displays, Air Shows and Swim Events in Captain of the Port Long Island Sound Zone Coast Guard, DHS. Notice of proposed rulemaking. AGENCY: ACTION: The Coast Guard is proposing to add one safety zone for the Dolan Family Labor Day Fireworks event on Oyster Bay, NY, and remove six other annual recurring marine events in Coast Guard Sector Long Island Sound’s Captain of the Port Zone. This proposed rule is intended to expedite public information and to ensure the protection of the maritime public and event participants from the hazards associated with certain marine events. When enforced, the safety zones would restrict vessels from transiting the regulated area during annually recurring events. We invite your comments on this proposed rulemaking. DATES: Comments and related material must be received by the Coast Guard on or before July 14, 2021. SUMMARY: E:\FR\FM\14JNP1.SGM 14JNP1

Agencies

[Federal Register Volume 86, Number 112 (Monday, June 14, 2021)]
[Proposed Rules]
[Pages 31453-31456]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2021-12351]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2021-0462; Project Identifier MCAI-2020-01714-T]
RIN 2120-AA64


Airworthiness Directives; Bombardier, Inc., Airplanes

AGENCY: Federal Aviation Administration (FAA), DOT.

[[Page 31454]]


ACTION: Notice of proposed rulemaking (NPRM).

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SUMMARY: The FAA proposes to adopt a new airworthiness directive (AD) 
for certain Bombardier, Inc., CL-600-2B16 (604 Variant) airplanes. This 
proposed AD was prompted by multiple reports of cracking of the main 
landing gear (MLG) shock strut lower pin. This proposed AD would 
require repetitive lubrication and repetitive detailed visual 
inspections (DVI) and non-destructive test (NDT) inspections of the MLG 
shock strut lower pins, and replacement if necessary. The FAA is 
proposing this AD to address the unsafe condition on these products.

DATES: The FAA must receive comments on this proposed AD by July 29, 
2021.

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, M-30, West Building Ground Floor, Room W12-140, 1200 New 
Jersey Avenue SE, Washington, DC 20590.
     Hand Delivery: Deliver to Mail address above between 9 
a.m. and 5 p.m., Monday through Friday, except Federal holidays.
    For service information identified in this NPRM, 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, Airworthiness Products Section, Operational 
Safety Branch, 2200 South 216th St., Des Moines, WA. For information on 
the availability of this material at the FAA, call 206-231-3195.

Examining the AD Docket

    You may examine the AD docket at https://www.regulations.gov by 
searching for and locating Docket No. FAA-2021-0462; 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 NPRM, any comments 
received, and other information. The street address for Docket 
Operations is listed above.

FOR FURTHER INFORMATION CONTACT: Chirayu Gupta, Aerospace Engineer, 
Mechanical Systems and Administrative Services Section, FAA, New York 
ACO Branch, 1600 Stewart Avenue, Suite 410, Westbury, NY 11590; 
telephone 516-228-7300; fax 516-794-5531; email [email protected].

SUPPLEMENTARY INFORMATION:

Comments Invited

    The FAA invites you to send any written relevant data, views, or 
arguments about this proposal. Send your comments to an address listed 
under ADDRESSES. Include ``Docket No. FAA-2021-0462; Project Identifier 
MCAI-2020-01714-T'' at the beginning of your comments. The most helpful 
comments reference a specific portion of the proposal, explain the 
reason for any recommended change, and include supporting data. The FAA 
will consider all comments received by the closing date and may amend 
the proposal because of those comments.
    Except for Confidential Business Information (CBI) as described in 
the following paragraph, and other information as described in 14 CFR 
11.35, the FAA will post all comments received, without change, to 
https://www.regulations.gov, including any personal information you 
provide. The agency will also post a report summarizing each 
substantive verbal contact received about this NPRM.

Confidential Business Information

    CBI is commercial or financial information that is both customarily 
and actually treated as private by its owner. Under the Freedom of 
Information Act (FOIA) (5 U.S.C. 552), CBI is exempt from public 
disclosure. If your comments responsive to this NPRM contain commercial 
or financial information that is customarily treated as private, that 
you actually treat as private, and that is relevant or responsive to 
this NPRM, it is important that you clearly designate the submitted 
comments as CBI. Please mark each page of your submission containing 
CBI as ``PROPIN.'' The FAA will treat such marked submissions as 
confidential under the FOIA, and they will not be placed in the public 
docket of this NPRM. Submissions containing CBI should be sent to 
Chirayu Gupta, Aerospace Engineer, Mechanical Systems and 
Administrative Services Section, FAA, New York ACO Branch, 1600 Stewart 
Avenue, Suite 410, Westbury, NY 11590; telephone 516-228-7300; fax 516-
794-5531; email [email protected]. Any commentary that the FAA 
receives which is not specifically designated as CBI will be placed in 
the public docket for this rulemaking.

Background

    Transport Canada Civil Aviation (TCCA), which is the aviation 
authority for Canada, has issued TCCA AD CF-2020-54R1, dated December 
23, 2020 (TCCA AD CF-2020-54R1) (also referred to after this as the 
Mandatory Continuing Airworthiness Information, or the MCAI), to 
correct an unsafe condition for certain Bombardier, Inc., CL-600-2B16 
(604 Variant) airplanes. You may examine the MCAI in the AD docket at 
https://www.regulations.gov by searching for and locating Docket No. 
FAA-2021-0462.
    This proposed AD was prompted by multiple reports of cracking of 
the MLG shock strut lower pin part number (P/N) 19146-3. The subsequent 
investigation concluded that the friction torque when the shock strut 
is under compression loading, causes the pin anti-rotation tangs to 
become loaded beyond their load carrying capability. This overload 
condition can result in pin fracture originating at the base of the pin 
anti-rotation tang. Inadequate lubrication aggravates the condition. 
The FAA is proposing this AD to address cracking of the MLG shock strut 
lower pin. If not addressed, this condition could result in structural 
failure of one or both MLG. See the MCAI for additional background 
information.

Related Service Information Under 1 CFR Part 51

    Bombardier, Inc., has issued the following service information:
     Service Bulletin 604-32-030, dated June 30, 2020.
     Service Bulletin 605-32-007, dated June 30, 2020.
     Service Bulletin 650-32-004, dated June 30, 2020.
    This service information describes procedures for lubricating, 
inspecting (DVI and NDT inspections for cracking and damage, including 
fracture of the MLG shock strut lower pin at the pin rotation tang 
location), and replacing the MLG shock strut lower pin. These documents 
are distinct since they apply to different airplane configurations. 
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.

FAA's Determination

    This product has been approved by the aviation authority of another 
country, and is approved for operation in the United States. Pursuant 
to the FAA's bilateral agreement with the State of Design Authority, 
the FAA has been notified of the unsafe condition

[[Page 31455]]

described in the MCAI and service information referenced above. The FAA 
is proposing this AD because the FAA evaluated all the relevant 
information and determined the unsafe condition described previously is 
likely to exist or develop on other products of the same type design.

Proposed AD Requirements in This NPRM

    This proposed AD would require accomplishing the actions specified 
in the service information already described.

Costs of Compliance

    The FAA estimates that this AD, if adopted as proposed, would 
affect 433 airplanes of U.S. registry. The FAA estimates the following 
costs to comply with this proposed AD:

                                      Estimated Costs for Required Actions
----------------------------------------------------------------------------------------------------------------
                                                                                    Cost per       Cost on U.S.
                          Labor cost                              Parts cost        product         operators
----------------------------------------------------------------------------------------------------------------
7 work-hours x $85 per hour = $595...........................              $0             $595         $257,635
----------------------------------------------------------------------------------------------------------------

    The FAA estimates the following costs to do any necessary on-
condition actions that would be required based on the results of any 
required actions. The FAA has 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
------------------------------------------------------------------------
6 work-hours x $85 per hour = $510....          $2,435           $2,945
------------------------------------------------------------------------

    The FAA has included all known costs in its cost estimate. 
According to the manufacturer, however, some or all of the costs of 
this proposed AD may be covered under warranty, thereby reducing the 
cost impact on affected operators.

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.
    The FAA is issuing this rulemaking under the authority described in 
Subtitle VII, Part A, Subpart III, Section 44701: General requirements. 
Under that section, Congress charges the FAA with promoting safe flight 
of civil aircraft in air commerce by prescribing regulations for 
practices, methods, and procedures the Administrator finds necessary 
for safety in air commerce. This regulation is within the scope of that 
authority because it addresses an unsafe condition that is likely to 
exist or develop on products identified in this rulemaking action.

Regulatory Findings

    The FAA determined that this proposed AD would not have federalism 
implications under Executive Order 13132. This proposed AD would not 
have a substantial direct effect on the States, on the relationship 
between the national Government and the States, or on the distribution 
of power and responsibilities among the various levels of government.
    For the reasons discussed above, I certify this proposed 
regulation:
    (1) Is not a ``significant regulatory action'' under Executive 
Order 12866,
    (2) Would not affect intrastate aviation in Alaska, and
    (3) Would not have a significant economic impact, positive or 
negative, on a substantial number of small entities under the criteria 
of the Regulatory Flexibility Act.

List of Subjects in 14 CFR Part 39

    Air transportation, Aircraft, Aviation safety, Incorporation by 
reference, Safety.

The Proposed Amendment

    Accordingly, under the authority delegated to me by the 
Administrator, the FAA proposes to amend 14 CFR part 39 as follows:

PART 39--AIRWORTHINESS DIRECTIVES

0
1. The authority citation for part 39 continues to read as follows:

    Authority:  49 U.S.C. 106(g), 40113, 44701.


Sec.  39.13  [Amended]

0
2. The FAA amends Sec.  39.13 by adding the following new airworthiness 
directive:

Bombardier, Inc.: Docket No. FAA-2021-0462; Project Identifier MCAI-
2020-01714-T.

(a) Comments Due Date

    The FAA must receive comments on this airworthiness directive 
(AD) by July 29, 2021.

(b) Affected ADs

    None.

(c) Applicability

    This AD applies to Bombardier, Inc., Model CL-600-2B16 (604 
Variant) airplanes, serial numbers (S/N) 5301 through 5665 
inclusive, 5701 through 5988 inclusive, and 6050 through 6999 
inclusive, certificated in any category.

 (d) Subject

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

(e) Unsafe Condition

    This AD was prompted by multiple reports of cracking of the main 
landing gear (MLG) shock strut lower pin. The FAA is issuing this AD 
to address cracking of the MLG shock strut lower pin. If not 
addressed, this condition could result in structural failure of one 
or both MLG.

(f) Compliance

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

(g) Repetitive Lubrication

    Within 200 flight hours (FH) or 12 months after the effective 
date of this AD, whichever occurs first, lubricate the left-hand 
(LH) and right-hand (RH) MLG shock strut lower pins having part 
number (P/N) 19146-3, in accordance with paragraph 2.B., ``Part A,'' 
of the Accomplishment Instructions of the applicable service 
bulletin, as specified in paragraphs (g)(1) through (3) of this AD. 
Repeat thereafter at intervals not to exceed 200 FH or 12 months, 
whichever occurs first.

[[Page 31456]]

    (1) For airplanes having S/N 5301 through 5665 inclusive: 
Bombardier Service Bulletin 604-32-030, dated June 30, 2020.
    (2) For airplanes having S/N 5701 through 5988 inclusive: 
Bombardier Service Bulletin 605-32-007, dated June 30, 2020.
    (3) For airplanes having S/N 6050 through 6999 inclusive: 
Bombardier Service Bulletin 650-32-004, dated June 30, 2020.

(h) Repetitive Detailed Visual Inspections (DVI)

    At the applicable compliance time specified in paragraphs (h)(1) 
through (3) of this AD, perform the DVI for cracking and damage of 
the LH and RH MLG shock strut lower pins having part number (P/N) 
19146-3, in accordance with paragraph 2.C., ``Part B,'' of the 
Accomplishment Instructions of the applicable service bulletin, as 
specified in paragraphs (g)(1) through (3) of this AD. Repeat 
thereafter at intervals not to exceed 400 FH or 24 months, whichever 
occurs first. If the DVI coincides with a non-destructive testing 
(NDT) inspection required by paragraph (i) of this AD, the NDT 
inspection supersedes the DVI for that interval only. If the 
accumulated flight cycles (FC) of the MLG shock strut lower pin are 
not known, use the related MLG assembly accumulated FC to determine 
when to accomplish the actions required by this paragraph.
    (1) For airplanes with an original airworthiness certificate or 
original export certificate of airworthiness issued on or before the 
effective date of this AD and on which an MLG shock strut lower pin 
has accumulated fewer than 600 total FC on the pin as of the 
effective date of this AD: Before the accumulation of 750 total FC 
on the pin.
    (2) For airplanes with an original airworthiness certificate or 
original export certificate of airworthiness issued on or before the 
effective date of this AD and on which an MLG shock strut lower pin 
has accumulated 600 total FC or more on the pin as of the effective 
date of this AD: Within 150 FC after the effective date of this AD.
    (3) For airplanes with an original airworthiness certificate or 
original export certificate of airworthiness issued after the 
effective date of this AD: Before the accumulation of 750 total FC.

 (i) Repetitive NDT Inspection

    At the applicable compliance time specified in paragraphs (i)(1) 
through (4) of this AD: Perform the NDT for cracking and damage of 
the LH and RH MLG shock strut lower pins having P/N 19146-3, in 
accordance with paragraph 2.D., ``Part C,'' of the Accomplishment 
Instructions of the applicable service bulletin, as specified in 
paragraphs (g)(1) through (3) of this AD. Repeat thereafter at 
intervals not to exceed 900 FC. If the accumulated FC of the MLG 
shock strut lower pin is not known, use the related MLG assembly 
accumulated FC to determine when to accomplish the actions required 
by this paragraph.
    (1) For airplanes with an original airworthiness certificate or 
original export certificate of airworthiness issued on or before the 
effective date of this AD and on which an MLG shock strut lower pin 
has accumulated fewer than 1,200 total FC on the pin as of the 
effective date of this AD: Before the accumulation of 1,500 total FC 
on the pin.
    (2) For airplanes with an original airworthiness certificate or 
original export certificate of airworthiness issued on or before the 
effective date of this AD and on which an MLG shock strut lower pin 
has accumulated 1,200 total FC or more but fewer than 2,000 total FC 
on the pin as of the effective date of this AD: Within 300 FC after 
the effective date of this AD, or before the accumulation of 2,200 
total FC on the pin, whichever occurs first.
    (3) For airplanes with an original airworthiness certificate or 
original export certificate of airworthiness issued on or before the 
effective date of this AD and on which an MLG shock strut lower pin 
that has accumulated 2,000 total FC or more on the pin as of the 
effective date of this AD: Within 200 FC after the effective date of 
this AD.
    (4) For airplanes with an original airworthiness certificate or 
original export certificate of airworthiness issued after the 
effective date of this AD: Before the accumulation of 1,500 total 
FC.

(j) Replacement

    If, during any inspection required by this AD, any crack or 
damage of the MLG shock strut lower pin is detected, before further 
flight, replace the affected MLG shock strut lower pin with a new 
part in accordance with paragraph 2.E., ``Part D,'' of the 
Accomplishment Instructions of the applicable service bulletin, as 
specified in paragraphs (g)(1) through (3) of this AD.

 (k) 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 responsible Flight Standards 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 
responsible Flight Standards Office.
    (2) Contacting the Manufacturer: For any requirement in this AD 
to obtain instructions from a manufacturer, the instructions 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.

(l) Related Information

    (1) Refer to Mandatory Continuing Airworthiness Information 
(MCAI) TCCA AD CF-2020-54R1, dated December 23, 2020, 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-2021-0462.
    (2) For more information about this AD, contact Chirayu Gupta, 
Aerospace Engineer, Mechanical Systems and Administrative Services 
Section, FAA, New York ACO Branch, 1600 Stewart Avenue, Suite 410, 
Westbury, NY 11590; telephone 516-228-7300; fax 516-794-5531; email 
[email protected].
    (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. You 
may view this service information at the FAA, Airworthiness Products 
Section, Operational Safety Branch, 2200 South 216th St., Des 
Moines, WA. For information on the availability of this material at 
the FAA, call 206-231-3195.

    Issued on June 8, 2021.
Lance T. Gant,
Director, Compliance & Airworthiness Division, Aircraft Certification 
Service.
[FR Doc. 2021-12351 Filed 6-11-21; 8:45 am]
BILLING CODE 4910-13-P