Airworthiness Directives; Bombardier, Inc., Airplanes, 68370-68374 [2019-25719]

Download as PDF 68370 Federal Register / Vol. 84, No. 241 / Monday, December 16, 2019 / Proposed Rules 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 (AD): ■ Airbus SAS: Docket No. FAA–2019–0977; Product Identifier 2019–NM–166–AD. (a) Comments Due Date The FAA must receive comments by January 30, 2020. (b) Affected ADs None. (c) Applicability This AD applies to all Airbus SAS airplanes specified in paragraphs (c)(1) through (3) of this AD, certificated in any category. (1) Model A319–131, –132, and –133 airplanes. (2) Model A320–231, –232, and –233 airplanes. (3) Model A321–131, –231, and –232 airplanes. (d) Subject Air Transport Association (ATA) of America Code 29, Hydraulic power. (e) Reason This AD was prompted by a report of rupture of a hydraulic reservoir air pressurization hose on an in-service airplane, leading to air leakage that was undetectable during normal operation, and found during subsequent zonal inspection. The FAA is issuing this AD to address this condition, which, if not detected and corrected, could lead to exposure of the wing structure to high temperatures (possibly above 200 degrees Celsius (392 degrees Fahrenheit)), possibly resulting in reduced structural integrity of the airplane. lotter on DSKBCFDHB2PROD with PROPOSALS (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 2019–0232, dated September 16, 2019 (‘‘EASA AD 2019– 0232’’). (h) Exceptions to EASA AD 2019–0232 (1) For purposes of determining compliance with the requirements of this AD: VerDate Sep<11>2014 22:14 Dec 13, 2019 Jkt 250001 Where EASA AD 2019–0232 refers to its effective date, this AD requires using the effective date of this AD. (2) The ‘‘Remarks’’ section of EASA AD 2019–0232 does not apply to this AD. (i) Other FAA AD Provisions The following provisions also apply to this AD: (1) Alternative Methods of Compliance (AMOCs): The Manager, International Section, Transport Standards 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 International Section, send it to the attention of the person identified in paragraph (j)(2) of this AD. Information may be emailed to: 9-ANM-116-AMOCREQUESTS@faa.gov. 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 instructions from a manufacturer, the instructions must be accomplished using a method approved by the Manager, International Section, Transport Standards Branch, FAA; or EASA; or Airbus SAS’s EASA Design Organization Approval (DOA). If approved by the DOA, the approval must include the DOAauthorized signature. (3) Required for Compliance (RC): For any service information referenced in EASA AD 2019–0232 that contains RC procedures and tests: Except as required by paragraph (i)(2) of this AD, RC procedures and tests must be done to comply with this AD; any procedures or tests that are not identified as RC are recommended. Those procedures and tests that are not identified as RC may be deviated from using accepted methods in accordance with the operator’s maintenance or inspection program without obtaining approval of an AMOC, provided the procedures and tests identified as RC can be done and the airplane can be put back in an airworthy condition. Any substitutions or changes to procedures or tests identified as RC require approval of an AMOC. (j) Related Information (1) For information about EASA AD 2019– 0232, contact the EASA, Konrad-AdenauerUfer 3, 50668 Cologne, Germany; telephone +49 221 89990 6017; 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, 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. This material may be found in the AD docket on the internet at https:// www.regulations.gov by searching for and locating Docket No. FAA–2019–0977. (2) For more information about this AD, contact Sanjay Ralhan, Aerospace Engineer, PO 00000 Frm 00021 Fmt 4702 Sfmt 4702 International Section, Transport Standards Branch, FAA, 2200 South 216th St., Des Moines, WA 98198; telephone and fax 206– 231–3223. Issued in Des Moines, Washington, on November 27, 2019. Michael Kaszycki, Acting Director, System Oversight Division, Aircraft Certification Service. [FR Doc. 2019–26674 Filed 12–13–19; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2019–0876; Product Identifier 2019–NM–070–AD] RIN 2120–AA64 Airworthiness Directives; Bombardier, Inc., Airplanes Federal Aviation Administration (FAA), DOT. ACTION: Notice of proposed rulemaking (NPRM). AGENCY: The FAA proposes to adopt a new airworthiness directive (AD) for certain Bombardier, Inc., Model BD– 700–1A10 and BD–700–1A11 airplanes. This proposed AD was prompted by a report that cracking was discovered in a channel within a structural support member for the rudder quadrant, rudder feel unit assembly, and environmental control system due to fatigue. This proposed AD would require repetitive inspections of the rudder quadrant box assembly for any cracking, and modification of the rudder quadrant box assembly. 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 January 30, 2020. 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., SUMMARY: E:\FR\FM\16DEP1.SGM 16DEP1 Federal Register / Vol. 84, No. 241 / Monday, December 16, 2019 / Proposed Rules 400 Coˆte-Vertu Road West, Dorval, Que´bec H4S 1Y9, Canada; telephone 514–855–5000; fax 514–855–7401; email thd.crj@aero.bombardier.com; 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. 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– 0876; 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, the regulatory evaluation, any comments received, and other information. The street address for Docket Operations is listed above. Comments will be available in the AD docket shortly after receipt. FOR FURTHER INFORMATION CONTACT: Andrea Jimenez, Aerospace Engineer, Airframe and Mechanical Systems Section, FAA, New York ACO Branch, 1600 Stewart Avenue, Suite 410, Westbury, NY 11590; telephone 516– 228–7330; fax 516–794–5531; email 9avs-nyaco-cos@faa.gov. SUPPLEMENTARY INFORMATION: Comments Invited lotter on DSKBCFDHB2PROD with PROPOSALS The FAA invites you to send any written relevant data, views, or arguments about this proposal. Send your comments to an address listed under the ADDRESSES section. Include ‘‘Docket No. FAA–2019–0876; Product Identifier 2019–NM–070–AD’’ at the beginning of your comments. The FAA specifically invites comments on the overall regulatory, economic, environmental, and energy aspects of this NPRM. The FAA will consider all comments received by the closing date and may amend this NPRM because of those comments. The FAA will post all comments received, without change, to https:// www.regulations.gov, including any personal information you provide. The FAA will also post a report summarizing each substantive verbal contact received about this NPRM. Discussion Transport Canada Civil Aviation (TCCA), which is the aviation authority for Canada, has issued Canadian VerDate Sep<11>2014 22:14 Dec 13, 2019 Jkt 250001 Airworthiness Directive CF–2019–11, dated March 22, 2019 (referred to after this as the Mandatory Continuing Airworthiness Information, or ‘‘the MCAI’’), to correct an unsafe condition for certain Bombardier, Inc., Model BD– 700–1A10 and BD–700–1A11 airplanes. 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– 0876. This proposed AD was prompted by a report that cracking was discovered in a channel within a structural support member for the rudder quadrant, rudder feel unit assembly, and environmental control system due to fatigue. The FAA is proposing this AD to address cracking in the rudder quadrant support structure, which can lead to progressive deterioration in the performance of the systems it supports, and could eventually lead to uncommanded rudder movement and bleed air leakage. See the MCAI for additional background information. Related Service Information Under 1 CFR Part 51 Bombardier has issued the following service information. • Bombardier Service Bulletin 700– 53–054, dated October 1, 2018. • Bombardier Service Bulletin 700– 53–5013, dated October 1, 2018. • Bombardier Service Bulletin 700– 53–6012, dated October 1, 2018. • Bombardier Service Bulletin 700– 1A11–53–029, dated October 1, 2018. This service information describes procedures for repetitive detailed visual inspections of the rudder quadrant box assembly for any cracking. These documents are distinct since they apply to different airplane models. Bombardier also issued the following service information: • Bombardier Service Bulletin 700– 53–052, dated October 1, 2018. • Bombardier Service Bulletin 700– 53–6010, dated October 1, 2018. • Bombardier Service Bulletin 700– 1A11–53–027, dated October 1, 2018. • Bombardier Service Bulletin 700– 53–5011, dated October 1, 2018. This service information describes procedures for modification of the rudder quadrant box assembly. The modification includes surface and bolthole eddy current inspections for cracking of the left-hand (LH) channel; a detailed visual inspection for cracking PO 00000 Frm 00022 Fmt 4702 Sfmt 4702 68371 of the forward and aft half ribs and bottom and top skins; replacement of the rudder quadrant box half ribs, air systems support fitting, and LH channel; and installation of new rudder quadrant box back-up fittings. These documents are distinct since they apply to different airplane models. This service information is reasonably available because the interested parties have access to it through their normal course of business or by the means identified in the ADDRESSES section. 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 a bilateral agreement with the State of Design Authority, the FAA has been notified of the unsafe condition described in the MCAI and service information referenced above. The FAA is proposing this AD because the agency 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 Requirements of This NPRM This proposed AD would require accomplishing the actions specified in the service information described previously, except as discussed under ‘‘Differences Between this Proposed AD and the MCAI or Service Information.’’ Differences Between This Proposed AD and the MCAI or Service Information Canadian Airworthiness Directive CF–2019–11, dated March 22, 2019, states that if any cracking is found during the repetitive detailed visual inspections of the rudder quadrant box assembly, the repair can be done within 100 flight cycles after the inspection. However, this AD requires that, for the LH channel, if the length of the crack exceeds the upper limit, the repair must be done before further flight. In addition, if the length of the crack for the LH channel is within the upper limit, the repair must be done within 50 flight cycles. These differences have been coordinated with TCCA. Costs of Compliance The FAA estimates that this proposed AD affects 123 airplanes of U.S. registry. The FAA estimates the following costs to comply with this proposed AD: E:\FR\FM\16DEP1.SGM 16DEP1 68372 Federal Register / Vol. 84, No. 241 / Monday, December 16, 2019 / Proposed Rules ESTIMATED COSTS FOR REQUIRED ACTIONS Cost per product Labor cost Parts cost 2 work-hours × $85 per hour = $170 per inspection cycle. $0 ............................................................................................................... The FAA estimates the following costs to do any necessary on-condition action that would be required based on the results of any required actions. The FAA has no way of determining the $170 per inspection cycle Cost on U.S. operators $20,910 per inspection cycle number of aircraft that might need this on-condition action: ESTIMATED COSTS OF ON-CONDITION ACTION Labor cost Parts cost Cost per product 46 work-hours × $85 per hour = $3,910 ................................................................................................................. $355 $4,265 lotter on DSKBCFDHB2PROD with PROPOSALS 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. This proposed 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 The FAA has 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 22:14 Dec 13, 2019 Jkt 250001 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. (c) Applicability This AD applies to Bombardier, Inc., Model BD–700–1A10 and BD–700–1A11 airplanes, certificated in any category, serial numbers 9001 through 9844 inclusive, and 9998. (d) Subject Air Transport Association (ATA) of America Code 53, Fuselage. The Proposed Amendment (e) Reason This AD was prompted by a report that cracking was discovered in a channel within a structural support member for the rudder quadrant, rudder feel unit assembly, and environmental control system due to fatigue. The FAA is issuing this AD to address cracking in the rudder quadrant support structure, which can lead to progressive deterioration in the performance of the systems it supports, and could eventually lead to uncommanded rudder movement and bleed air leakage. Accordingly, under the authority delegated to me by the Administrator, the FAA proposes to amend 14 CFR part 39 as follows: (f) Compliance Comply with this AD within the compliance times specified, unless already done. PART 39—AIRWORTHINESS DIRECTIVES (g) Initial and Repetitive Inspections For airplanes that have accumulated fewer than 2,900 total flight cycles as of the effective date of this AD, and that have not been modified as specified in paragraph (i) of this AD: At the applicable time specified in paragraph (g)(1) or (2) of this AD, do a detailed visual inspection for cracking of the rudder quadrant box assembly, in accordance with paragraph 2.B. of the Accomplishment Instructions of the applicable service bulletin specified in figure 1 to paragraph (g) of this AD. Repeat the inspection thereafter at intervals not to exceed 1,000 flight cycles. (1) For airplanes that have accumulated fewer than 2,000 total flight cycles as of the effective date of this AD: Inspect within 1,000 flight cycles after the effective date of this AD. (2) For airplanes that have accumulated 2,000 total flight cycles or more, but fewer than 2,900 total flight cycles, as of the effective date of this AD: Inspect within 100 List of Subjects in 14 CFR Part 39 Air transportation, Aircraft, Aviation safety, Incorporation by reference, Safety. 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): ■ Bombardier, Inc.: Docket No. FAA–2019– 0876; Product Identifier 2019–NM–070– AD. (a) Comments Due Date The FAA must receive comments by January 30, 2020. (b) Affected ADs None. PO 00000 Frm 00023 Fmt 4702 Sfmt 4702 E:\FR\FM\16DEP1.SGM 16DEP1 Federal Register / Vol. 84, No. 241 / Monday, December 16, 2019 / Proposed Rules 68373 flight cycles after the effective date of this AD. Figure 1 to paragraph (g) - Inspection Service Information BD- 700-1A10 airplanes having serial numbers 9002 through 9312 inclusive, 9314 through 9380 inclusive, and 9384 through 9429 inclusive Bombardier Service Bulletin 700-53-054, dated October 1, 2018 BD- 700-1A10 airplanes having serial numbers 9313, 9381, and 9432 through 9844 inclusive Bombardier Service Bulletin 700-53-6012, dated October 1, 2018 BD-700-lAl 1 airplanes having serial numbers 9127 through 9383 inclusive, 9389 through 9400 inclusive, 9404 through 9431 inclusive, and 9998 Bombardier Service Bulletin 700-lAl 1-53-029, dated October 1, 2018 BD-700-lAl 1 airplanes having serial numbers 9386, 9401, and 9445 through 9840 inclusive Bombardier Service Bulletin 700-53-5013, dated October 1, 2018 (h) Corrective Actions for Inspection Findings lotter on DSKBCFDHB2PROD with PROPOSALS If any cracking is found during the inspection specified in paragraph (g) of this AD, do the actions specified in paragraph (i) of this AD at the applicable time specified in paragraphs (h)(1) through (4) of this AD. (1) If any crack of 1.20 inch (30.48 mm) or longer is found on the forward (FWD) upper half rib: Do the actions within 100 flight cycles after discovery of the crack. (2) If any crack of 0.40 inch (10.16 mm) or longer is found on the AFT lower half rib, do the actions within 100 flight cycles after discovery of the crack. (3) If any crack is found on the left-hand (LH) channel that has grown from the air system’s support fitting aft fastener hole to the adjacent air systems support fitting fastener hole (which is 0.625 inch (15.88 mm) from hole edge to hole edge) or longer, do the actions before further flight. (4) If any crack is found on the LH channel that is less than 0.625 inch (15.88 mm) from VerDate Sep<11>2014 Service Information 22:14 Dec 13, 2019 Jkt 250001 hole edge to hole edge (which is the distance from the air system’s support fitting aft fastener hole to the adjacent air system’s support fitting fastener hole), do the actions within 50 flight cycles after discovery of the crack. (i) Modification of the Rudder Quadrant Box Assembly At the applicable time specified in paragraph (i)(1) or (2) of this AD, except as required by paragraph (h) of this AD: Modify the rudder quadrant box assembly. The modification includes surface and bolt-hole eddy current inspections for cracking of the left-hand channel; a detailed visual inspection for cracking of the forward and aft half ribs and bottom and top skins; applicable corrective actions; replacement of the rudder quadrant box half ribs, air systems support fitting, and LH channel; and installation of new rudder quadrant box back-up fittings. Do the modification and associated actions in accordance with PO 00000 Frm 00024 Fmt 4702 Sfmt 4702 paragraph 2.B., 2.C., and 2.D., of the Accomplishment Instructions of the applicable service bulletin specified in figure 2 to paragraph (i) of this AD; except, where the applicable service bulletin specifies to contact Bombardier for appropriate action, corrective actions must be done before further flight in accordance with the procedures specified in paragraph (l)(2) of this AD. (1) For airplanes that have accumulated 2,900 total flight cycles or fewer as of the effective date of this AD, do the required actions before the accumulation of 3,000 total flight cycles, or within 60 months after the effective date of this AD, whichever occurs first. (2) For airplanes that have accumulated more than 2,900 total flight cycles as of the effective date of this AD, do the required actions within 100 flight cycles or 12 months, whichever occurs first, after the effective date of this AD. E:\FR\FM\16DEP1.SGM 16DEP1 EP16DE19.076</GPH> Airplane Model 68374 Federal Register / Vol. 84, No. 241 / Monday, December 16, 2019 / Proposed Rules Figure 2 to paragraph (i) - Modification Service Information BD- 700-1A10 airplanes having serial numbers 9002 through 9312 inclusive, 9314 through 9380 inclusive, and 9384 through 9429 inclusive Bombardier Service Bulletin 700-53-052, dated October 1, 2018 BD- 700-1A10 airplanes having serial numbers 9313, 93 81, and 9432 through 9844 inclusive Bombardier Service Bulletin 700-53-6010, dated October 1, 2018. BD-700-lAl 1 airplanes having serial numbers 9127 through 9383 inclusive, 9389 through 9400 inclusive, 9404 through 9431 inclusive, and 9998 Bombardier Service Bulletin 700-lAl 1-53-027, dated October 1, 2018 BD-700-lAl 1 airplanes having serial numbers 9386, 9401, and 9445 through 9840 inclusive Bombardier Service Bulletin 700-53-5011, dated October 1, 2018 (j) Alternative Modification Airplanes that have been modified as specified by any modification identified in paragraph (j)(1) through (4) of this AD (which are not required by this AD), meet the requirements specified in paragraph (i) of this AD. (1) Bombardier Repair Modification R700T400669, Revision C, dated January 19, 2018, or Bombardier Repair Modification R700T400669, Revision G, dated May 30, 2018. (2) Bombardier In-Service Modification IS700–53–0024, Revision A, dated July 24, 2018. (3) Bombardier Service Request for Product Support Action (SRPSA) 000220372. (4) Bombardier Service Request for Product Support Action (SRPSA) 000271526. (k) Terminating Action for Repetitive Inspections Accomplishing the actions in paragraph (i) or (j) of this AD terminates all of the requirements in paragraph (g) of this AD. (l) Other FAA AD Provisions lotter on DSKBCFDHB2PROD with PROPOSALS Service Information 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 VerDate Sep<11>2014 22:14 Dec 13, 2019 Jkt 250001 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 Canada’s TCCA Design Approval Organization (DAO). If approved by the DAO, the approval must include the DAOauthorized signature. (m) Related Information (1) Refer to Mandatory Continuing Airworthiness Information (MCAI) Canadian Airworthiness Directive CF–2019–11, dated March 22, 2019, 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– 2019–0876. (2) For more information about this AD, contact Andrea Jimenez, Aerospace Engineer, Airframe and Mechanical Systems Section, FAA, New York ACO Branch, 1600 Stewart Avenue, Suite 410, Westbury, NY 11590; telephone 516–228–7330; fax 516–794–5531; email 9-avs-nyaco-cos@faa.gov. (3) For service information identified in this AD, contact Bombardier, Inc., 400 CoˆteVertu Road West, Dorval, Que´bec H4S 1Y9, Canada; telephone 514–855–5000; fax 514– 855–7401; email thd.crj@ aero.bombardier.com; 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. PO 00000 Frm 00025 Fmt 4702 Sfmt 4702 Issued in Des Moines, Washington, on November 21, 2019. Dorr Anderson, Acting Director, System Oversight Division, Aircraft Certification Service. [FR Doc. 2019–25719 Filed 12–13–19; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2019–0832; Product Identifier 2019–NE–28–AD] RIN 2120–AA64 Airworthiness Directives; International Aero Engines AG Turbofan Engines Federal Aviation Administration (FAA), DOT. ACTION: Notice of proposed rulemaking (NPRM). AGENCY: The FAA proposes to adopt a new airworthiness directive (AD) for International Aero Engines AG (IAE) V2500–A1, V2522–A5, V2524–A5, V2525–D5, V2527–A5, V2527E–A5, V2527M–A5, V2528–D5, V2530–A5, V2531–E5, and V2533–A5 turbofan engine models with a certain diffuser case assembly installed. This proposed AD was prompted by a report of a manufacturing quality escape that could impact the life of the diffuser case assembly. This proposed AD would require removal of the affected diffuser case assembly from service and replacement with a part eligible for installation. The FAA is proposing this SUMMARY: E:\FR\FM\16DEP1.SGM 16DEP1 EP16DE19.077</GPH> Airplane Model

Agencies

[Federal Register Volume 84, Number 241 (Monday, December 16, 2019)]
[Proposed Rules]
[Pages 68370-68374]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2019-25719]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2019-0876; Product Identifier 2019-NM-070-AD]
RIN 2120-AA64


Airworthiness Directives; Bombardier, Inc., Airplanes

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Notice of proposed rulemaking (NPRM).

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

SUMMARY: The FAA proposes to adopt a new airworthiness directive (AD) 
for certain Bombardier, Inc., Model BD-700-1A10 and BD-700-1A11 
airplanes. This proposed AD was prompted by a report that cracking was 
discovered in a channel within a structural support member for the 
rudder quadrant, rudder feel unit assembly, and environmental control 
system due to fatigue. This proposed AD would require repetitive 
inspections of the rudder quadrant box assembly for any cracking, and 
modification of the rudder quadrant box assembly. 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 January 30, 
2020.

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.,

[[Page 68371]]

400 C[ocirc]te-Vertu Road West, Dorval, Qu[eacute]bec H4S 1Y9, Canada; 
telephone 514-855-5000; fax 514-855-7401; 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.

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-
0876; 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, the regulatory evaluation, any comments received, and other 
information. The street address for Docket Operations is listed above. 
Comments will be available in the AD docket shortly after receipt.

FOR FURTHER INFORMATION CONTACT: Andrea Jimenez, Aerospace Engineer, 
Airframe and Mechanical Systems Section, FAA, New York ACO Branch, 1600 
Stewart Avenue, Suite 410, Westbury, NY 11590; telephone 516-228-7330; 
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 the ADDRESSES section. Include ``Docket No. FAA-2019-0876; 
Product Identifier 2019-NM-070-AD'' at the beginning of your comments. 
The FAA specifically invites comments on the overall regulatory, 
economic, environmental, and energy aspects of this NPRM. The FAA will 
consider all comments received by the closing date and may amend this 
NPRM because of those comments.
    The FAA will post all comments received, without change, to https://www.regulations.gov, including any personal information you provide. 
The FAA will also post a report summarizing each substantive verbal 
contact received about this NPRM.

Discussion

    Transport Canada Civil Aviation (TCCA), which is the aviation 
authority for Canada, has issued Canadian Airworthiness Directive CF-
2019-11, dated March 22, 2019 (referred to after this as the Mandatory 
Continuing Airworthiness Information, or ``the MCAI''), to correct an 
unsafe condition for certain Bombardier, Inc., Model BD-700-1A10 and 
BD-700-1A11 airplanes. 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-2019-0876.
    This proposed AD was prompted by a report that cracking was 
discovered in a channel within a structural support member for the 
rudder quadrant, rudder feel unit assembly, and environmental control 
system due to fatigue. The FAA is proposing this AD to address cracking 
in the rudder quadrant support structure, which can lead to progressive 
deterioration in the performance of the systems it supports, and could 
eventually lead to uncommanded rudder movement and bleed air leakage. 
See the MCAI for additional background information.

Related Service Information Under 1 CFR Part 51

    Bombardier has issued the following service information.
     Bombardier Service Bulletin 700-53-054, dated October 1, 
2018.
     Bombardier Service Bulletin 700-53-5013, dated October 1, 
2018.
     Bombardier Service Bulletin 700-53-6012, dated October 1, 
2018.
     Bombardier Service Bulletin 700-1A11-53-029, dated October 
1, 2018.
    This service information describes procedures for repetitive 
detailed visual inspections of the rudder quadrant box assembly for any 
cracking. These documents are distinct since they apply to different 
airplane models.
    Bombardier also issued the following service information:
     Bombardier Service Bulletin 700-53-052, dated October 1, 
2018.
     Bombardier Service Bulletin 700-53-6010, dated October 1, 
2018.
     Bombardier Service Bulletin 700-1A11-53-027, dated October 
1, 2018.
     Bombardier Service Bulletin 700-53-5011, dated October 1, 
2018.
    This service information describes procedures for modification of 
the rudder quadrant box assembly. The modification includes surface and 
bolt-hole eddy current inspections for cracking of the left-hand (LH) 
channel; a detailed visual inspection for cracking of the forward and 
aft half ribs and bottom and top skins; replacement of the rudder 
quadrant box half ribs, air systems support fitting, and LH channel; 
and installation of new rudder quadrant box back-up fittings. These 
documents are distinct since they apply to different airplane models.
    This service information is reasonably available because the 
interested parties have access to it through their normal course of 
business or by the means identified in the ADDRESSES section.

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 a bilateral agreement with the State of Design Authority, the FAA 
has been notified of the unsafe condition described in the MCAI and 
service information referenced above. The FAA is proposing this AD 
because the agency 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 Requirements of This NPRM

    This proposed AD would require accomplishing the actions specified 
in the service information described previously, except as discussed 
under ``Differences Between this Proposed AD and the MCAI or Service 
Information.''

Differences Between This Proposed AD and the MCAI or Service 
Information

    Canadian Airworthiness Directive CF-2019-11, dated March 22, 2019, 
states that if any cracking is found during the repetitive detailed 
visual inspections of the rudder quadrant box assembly, the repair can 
be done within 100 flight cycles after the inspection. However, this AD 
requires that, for the LH channel, if the length of the crack exceeds 
the upper limit, the repair must be done before further flight. In 
addition, if the length of the crack for the LH channel is within the 
upper limit, the repair must be done within 50 flight cycles. These 
differences have been coordinated with TCCA.

Costs of Compliance

    The FAA estimates that this proposed AD affects 123 airplanes of 
U.S. registry. The FAA estimates the following costs to comply with 
this proposed AD:

[[Page 68372]]



                                      Estimated Costs For Required Actions
----------------------------------------------------------------------------------------------------------------
                                                                                     Cost per      Cost on U.S.
                 Labor cost                               Parts cost                  product        operators
----------------------------------------------------------------------------------------------------------------
2 work-hours x $85 per hour = $170 per       $0.................................        $170 per     $20,910 per
 inspection cycle.                                                                    inspection      inspection
                                                                                           cycle           cycle
----------------------------------------------------------------------------------------------------------------

    The FAA estimates the following costs to do any necessary on-
condition action 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 this on-condition action:

                 Estimated Costs of On-Condition Action
------------------------------------------------------------------------
                                                             Cost per
              Labor cost                   Parts cost        product
------------------------------------------------------------------------
46 work-hours x $85 per hour = $3,910.            $355           $4,265
------------------------------------------------------------------------

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.
    This proposed 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

    The FAA has 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.

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 (AD):

Bombardier, Inc.: Docket No. FAA-2019-0876; Product Identifier 2019-
NM-070-AD.

(a) Comments Due Date

    The FAA must receive comments by January 30, 2020.

(b) Affected ADs

    None.

(c) Applicability

    This AD applies to Bombardier, Inc., Model BD-700-1A10 and BD-
700-1A11 airplanes, certificated in any category, serial numbers 
9001 through 9844 inclusive, and 9998.

(d) Subject

    Air Transport Association (ATA) of America Code 53, Fuselage.

(e) Reason

    This AD was prompted by a report that cracking was discovered in 
a channel within a structural support member for the rudder 
quadrant, rudder feel unit assembly, and environmental control 
system due to fatigue. The FAA is issuing this AD to address 
cracking in the rudder quadrant support structure, which can lead to 
progressive deterioration in the performance of the systems it 
supports, and could eventually lead to uncommanded rudder movement 
and bleed air leakage.

(f) Compliance

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

(g) Initial and Repetitive Inspections

    For airplanes that have accumulated fewer than 2,900 total 
flight cycles as of the effective date of this AD, and that have not 
been modified as specified in paragraph (i) of this AD: At the 
applicable time specified in paragraph (g)(1) or (2) of this AD, do 
a detailed visual inspection for cracking of the rudder quadrant box 
assembly, in accordance with paragraph 2.B. of the Accomplishment 
Instructions of the applicable service bulletin specified in figure 
1 to paragraph (g) of this AD. Repeat the inspection thereafter at 
intervals not to exceed 1,000 flight cycles.
    (1) For airplanes that have accumulated fewer than 2,000 total 
flight cycles as of the effective date of this AD: Inspect within 
1,000 flight cycles after the effective date of this AD.
    (2) For airplanes that have accumulated 2,000 total flight 
cycles or more, but fewer than 2,900 total flight cycles, as of the 
effective date of this AD: Inspect within 100

[[Page 68373]]

flight cycles after the effective date of this AD.
[GRAPHIC] [TIFF OMITTED] TP16DE19.076

(h) Corrective Actions for Inspection Findings

    If any cracking is found during the inspection specified in 
paragraph (g) of this AD, do the actions specified in paragraph (i) 
of this AD at the applicable time specified in paragraphs (h)(1) 
through (4) of this AD.
    (1) If any crack of 1.20 inch (30.48 mm) or longer is found on 
the forward (FWD) upper half rib: Do the actions within 100 flight 
cycles after discovery of the crack.
    (2) If any crack of 0.40 inch (10.16 mm) or longer is found on 
the AFT lower half rib, do the actions within 100 flight cycles 
after discovery of the crack.
    (3) If any crack is found on the left-hand (LH) channel that has 
grown from the air system's support fitting aft fastener hole to the 
adjacent air systems support fitting fastener hole (which is 0.625 
inch (15.88 mm) from hole edge to hole edge) or longer, do the 
actions before further flight.
    (4) If any crack is found on the LH channel that is less than 
0.625 inch (15.88 mm) from hole edge to hole edge (which is the 
distance from the air system's support fitting aft fastener hole to 
the adjacent air system's support fitting fastener hole), do the 
actions within 50 flight cycles after discovery of the crack.

(i) Modification of the Rudder Quadrant Box Assembly

    At the applicable time specified in paragraph (i)(1) or (2) of 
this AD, except as required by paragraph (h) of this AD: Modify the 
rudder quadrant box assembly. The modification includes surface and 
bolt-hole eddy current inspections for cracking of the left-hand 
channel; a detailed visual inspection for cracking of the forward 
and aft half ribs and bottom and top skins; applicable corrective 
actions; replacement of the rudder quadrant box half ribs, air 
systems support fitting, and LH channel; and installation of new 
rudder quadrant box back-up fittings. Do the modification and 
associated actions in accordance with paragraph 2.B., 2.C., and 
2.D., of the Accomplishment Instructions of the applicable service 
bulletin specified in figure 2 to paragraph (i) of this AD; except, 
where the applicable service bulletin specifies to contact 
Bombardier for appropriate action, corrective actions must be done 
before further flight in accordance with the procedures specified in 
paragraph (l)(2) of this AD.
    (1) For airplanes that have accumulated 2,900 total flight 
cycles or fewer as of the effective date of this AD, do the required 
actions before the accumulation of 3,000 total flight cycles, or 
within 60 months after the effective date of this AD, whichever 
occurs first.
    (2) For airplanes that have accumulated more than 2,900 total 
flight cycles as of the effective date of this AD, do the required 
actions within 100 flight cycles or 12 months, whichever occurs 
first, after the effective date of this AD.

[[Page 68374]]

[GRAPHIC] [TIFF OMITTED] TP16DE19.077

(j) Alternative Modification

    Airplanes that have been modified as specified by any 
modification identified in paragraph (j)(1) through (4) of this AD 
(which are not required by this AD), meet the requirements specified 
in paragraph (i) of this AD.
    (1) Bombardier Repair Modification R700T400669, Revision C, 
dated January 19, 2018, or Bombardier Repair Modification 
R700T400669, Revision G, dated May 30, 2018.
    (2) Bombardier In-Service Modification IS700-53-0024, Revision 
A, dated July 24, 2018.
    (3) Bombardier Service Request for Product Support Action 
(SRPSA) 000220372.
    (4) Bombardier Service Request for Product Support Action 
(SRPSA) 000271526.

(k) Terminating Action for Repetitive Inspections

    Accomplishing the actions in paragraph (i) or (j) of this AD 
terminates all of the requirements in paragraph (g) of this AD.

(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 Canada'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 Airworthiness Directive CF-2019-11, dated March 22, 
2019, 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-2019-0876.
    (2) For more information about this AD, contact Andrea Jimenez, 
Aerospace Engineer, Airframe and Mechanical Systems Section, FAA, 
New York ACO Branch, 1600 Stewart Avenue, Suite 410, Westbury, NY 
11590; telephone 516-228-7330; fax 516-794-5531; email [email protected].
    (3) For service information identified in this AD, contact 
Bombardier, Inc., 400 C[ocirc]te-Vertu Road West, Dorval, 
Qu[eacute]bec H4S 1Y9, Canada; telephone 514-855-5000; fax 514-855-
7401; 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.

    Issued in Des Moines, Washington, on November 21, 2019.
Dorr Anderson,
Acting Director, System Oversight Division, Aircraft Certification 
Service.
[FR Doc. 2019-25719 Filed 12-13-19; 8:45 am]
BILLING CODE 4910-13-P