Airworthiness Directives; De Havilland Aircraft of Canada Limited (Type Certificate Previously Held by Bombardier, Inc.) Airplanes, 16008-16011 [2020-05762]

Download as PDF 16008 Proposed Rules Federal Register Vol. 85, No. 55 Friday, March 20, 2020 This section of the FEDERAL REGISTER contains notices to the public of the proposed issuance of rules and regulations. The purpose of these notices is to give interested persons an opportunity to participate in the rule making prior to the adoption of the final rules. DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2020–0200; Product Identifier 2019–NM–185–AD] RIN 2120–AA64 Airworthiness Directives; De Havilland Aircraft of Canada Limited (Type Certificate Previously Held by Bombardier, Inc.) Airplanes Federal Aviation Administration (FAA), DOT. ACTION: Notice of proposed rulemaking (NPRM). AGENCY: SUMMARY: The FAA proposes to supersede Airworthiness Directive (AD) 2015–14–01, which applies to certain Bombardier, Inc., Model DHC–8–400 series airplanes. AD 2015–14–01 requires a detailed inspection for loose bolts on the aft translating door crank assembly, and removal and reinstallation of the bolts. Since AD 2015–14–01 was issued, the FAA received a report that additional airplanes may be subject to the unsafe condition. In addition, the design of the translating door crank handle has been improved. This proposed AD would retain the inspections of AD 2015–14– 01 and add airplanes to the applicability. For all airplanes, this proposed AD would also require a modification of the door crank handle, which would terminate the inspections. The FAA is proposing this AD to address the unsafe condition on these products. The FAA must receive comments on this proposed AD by May 4, 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. jbell on DSKJLSW7X2PROD with PROPOSALS DATES: VerDate Sep<11>2014 17:34 Mar 19, 2020 Jkt 250001 • 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 De Havilland Aircraft of Canada Limited, Q-Series Technical Help Desk, 123 Garratt Boulevard, Toronto, Ontario M3K 1Y5, Canada; telephone 416–375–4000; fax 416–375–4539; email thd@ dehavilland.com; internet https:// dehavilland.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–2020– 0200; 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: Darren Gassetto, Aerospace Engineer, Mechanical Systems and Administrative Services Section, FAA, New York ACO Branch, 1600 Stewart Avenue, Suite 410, Westbury, NY 11590; telephone 516–228–7323; 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 the ADDRESSES section. Include ‘‘Docket No. FAA–2020–0200; Product Identifier 2019–NM–185–AD’’ at the beginning of your comments. The FAA specifically invites comments on the overall regulatory, economic, environmental, and energy aspects of this proposed AD. The FAA will PO 00000 Frm 00001 Fmt 4702 Sfmt 4702 consider all comments received by the closing date and may amend this proposed AD based on 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 proposed AD. Discussion The FAA issued AD 2015–14–01, Amendment 39–18199 (80 FR 38615, July 7, 2015) (‘‘AD 2015–14–01’’), for certain Bombardier, Inc., Model DHC– 8–400 series airplanes. AD 2015–14–01 requires a detailed inspection for loose bolts on the aft translating door crank assembly, and removal and reinstallation of the bolts. AD 2015–14– 01 resulted from a report of loose bolts that are intended to secure the translating door crank assembly to the outside handle shaft. The FAA issued AD 2015–14–01 to prevent loose bolts from falling out. If both bolts become loose or fall out after the door is closed and locked, the door cannot be opened from inside or outside, which could impede evacuation in the event of an emergency. Actions Since AD 2015–14–01 was Issued Since AD 2015–14–01 was issued, the FAA received a report that loose bolts were found on airplane serial numbers that were outside the applicability range. Further, the manufacturer reclassified the forward baggage door on some airplanes as an emergency exit, which is not subject to AD 2015–14–01. The FAA also received a report that the manufacturer has modified the design of the translating door crank handle to improve retention of the bolts. Transport Canada Civil Aviation (TCCA), which is the aviation authority for Canada, has issued Canadian AD CF–2014–08R1, dated July 30, 2019 (referred to after this as the Mandatory Continuing Airworthiness Information, or ‘‘the MCAI’’), to correct an unsafe condition for certain De Havilland Aircraft of Canada Limited (Type Certificate Previously Held by Bombardier, Inc.) Model DHC–8–400 series airplanes. You may examine the MCAI in the AD docket on the internet at https://www.regulations.gov by E:\FR\FM\20MRP1.SGM 20MRP1 16009 Federal Register / Vol. 85, No. 55 / Friday, March 20, 2020 / Proposed Rules distinct since they apply to different airplane configurations. De Havilland Aircraft of Canada Limited has also issued Bombardier Service Bulletin 84–52–96, dated February 26, 2019, which describes procedures for a detailed visual inspection of the translating door crank assembly for any loose bolts. De Havilland Aircraft of Canada Limited has also issued Modification Summary Package IS4Q5200101, Revision A, dated July 5, 2019, which describes a deviation to the actions specified in certain service information. This proposed AD would also require Bombardier Service Bulletin 84–52–75, Related Service Information Under 1 Revision A, dated July 11, 2013, which CFR part 51 the Director of the Federal Register De Havilland Aircraft of Canada Limited has issued the following service approved for incorporation by reference as of August 11, 2015 (80 FR 38615, July information. • Bombardier Service Bulletin 84–52– 7, 2015). This service information is reasonably 89, Revision A, dated January 29, 2018. • Bombardier Service Bulletin 84–52– available because the interested parties have access to it through their normal 92, Revision A, dated January 24, 2018. • Bombardier Service Bulletin 84–52– course of business or by the means identified in the ADDRESSES section. 94, Revision A, dated January 24, 2018. This service information describes FAA’s Determination procedures for modifying the door crank handle with an improved bolt retention This product has been approved by design on the type 1 emergency door, the aviation authority of another the aft entry door, and the aft service country, and is approved for operation door, as necessary. These documents are in the United States. Pursuant to a searching for and locating Docket No. FAA–2020–0200. This proposed AD was prompted by reports of loose bolts that are intended to secure the translating door crank assembly to the outside handle shaft, and of sealant missing from these bolts on another translating door. The FAA is issuing this AD to address the potential for both bolts to become loose or fall out after the door is closed and locked, which would prevent the door from being opened from inside or outside and impede evacuation in the event of an emergency. See the MCAI for additional background information. 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 retain the inspections of AD 2015–14–01. This proposed AD would require accomplishing the actions specified in the service information described previously. Explanation of Change to Manufacturer’s Name Specified in AD 2015–14–01 This NPRM identifies the manufacturer’s name as published in the most recent type certificate data sheet for the affected models. Costs of Compliance The FAA estimates that this proposed AD affects 59 airplanes of U.S. registry. The FAA estimates the following costs to comply with this proposed AD: jbell on DSKJLSW7X2PROD with PROPOSALS ESTIMATED COSTS FOR REQUIRED ACTIONS Labor cost Parts cost Cost per product Up to 13 work-hours × $85 per hour = $1,105 .................................................. Up to $677 ............. Up to $1,782 .......... Cost on U.S. operators Up to $105,138. Authority for This Rulemaking Regulatory Findings List of Subjects in 14 CFR Part 39 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. 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. Air transportation, Aircraft, Aviation safety, Incorporation by reference, Safety. VerDate Sep<11>2014 17:34 Mar 19, 2020 Jkt 250001 PO 00000 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 removing Airworthiness Directive (AD) 2015–14–01, Amendment 39–18199 (80 FR 38615, July 7, 2015), and adding the following new AD: ■ De Havilland Aircraft of Canada Limited (Type Certificate Previously Held by Frm 00002 Fmt 4702 Sfmt 4702 E:\FR\FM\20MRP1.SGM 20MRP1 16010 Federal Register / Vol. 85, No. 55 / Friday, March 20, 2020 / Proposed Rules Bombardier, Inc.) Airplanes: Docket No. FAA–2020–0200; Product Identifier 2019–NM–185–AD. (a) Comments Due Date The FAA must receive comments by May 4, 2020. (b) Affected ADs This AD replaces AD 2015–14–01, Amendment 39–18199 (80 FR 38615, July 7, 2015) (‘‘AD 2015–14–01’’). (c) Applicability This AD applies to De Havilland Aircraft of Canada Limited (Type Certificate Previously Held by Bombardier, Inc.) Model DHC–8–400, –401, and –402 airplanes, certificated in any category, serial numbers (S/Ns) 4001 through 4530 inclusive. (d) Subject Air Transport Association (ATA) of America Code 52, Doors. (e) Reason This proposed AD was prompted by reports of loose bolts that are intended to secure the translating door crank assembly to the outside handle shaft, and of sealant missing from these bolts on another translating door. The FAA is issuing this AD to address the potential for both bolts to become loose or fall out after the door is closed and locked, which would prevent the door from being opened from inside or outside and impede evacuation in the event of an emergency. jbell on DSKJLSW7X2PROD with PROPOSALS (f) Compliance Comply with this AD within the compliance times specified, unless already done. (g) Inspection and Corrective Actions for S/ Ns 4001 Through 4411 Inclusive For airplane S/Ns 4001 through 4411 inclusive: Within 600 flight hours or 100 days, whichever occurs first after August 11, 2015 (the effective date of AD 2015–14–01): Perform a detailed inspection for loose bolts of the aft translating door crank assembly, in accordance with paragraph 3.B., ‘‘Procedure,’’ of Part A—INSPECTION of the Accomplishment Instructions of Bombardier Service Bulletin 84–52–75, Revision A, dated July 11, 2013. (1) If the detailed inspection was done before the effective date of this AD and the corrective action was done in accordance with 3.B., ‘‘Procedure,’’ and steps 3.C.(4) and 3.C.(5) of paragraph 3.C., ‘‘Close Out,’’ of Part B—RECTIFICATION, of the Accomplishment Instructions of Bombardier Service Bulletin 84–52–75, dated July 27, 2012; or Bombardier Service Bulletin 84–52–75, Revision A, dated July 11, 2013: No further work is required by paragraph (g) of this AD. (2) If the detailed inspection is done on or after the effective date of this AD, and any loose bolt is found: Before further flight, do the modification in paragraph (i) of this AD. (h) Inspection and Modification for S/Ns 4412 Through 4491 Inclusive For airplane S/Ns 4412 through 4491 inclusive: Within 800 flight hours or 120 VerDate Sep<11>2014 17:34 Mar 19, 2020 Jkt 250001 days, whichever occurs first after the effective date of this AD, perform a detailed inspection for loose bolts of the translating door crank assembly, in accordance with paragraph 3.B., ‘‘Procedure,’’ of the Accomplishment Instructions of Bombardier Service Bulletin 84–52–96, dated February 26, 2019. (1) If any loose bolt is found, before further flight do the modification specified in paragraph (i) of this AD. (2) If no loose bolt is found, at the compliance time specified in paragraph (i) of this AD, do the modification specified in paragraph (i) of this AD. (i) Modification for S/Ns 4001 Through 4530 Inclusive For airplane S/Ns 4001 through 4530 inclusive: Except as required by paragraphs (g)(2) and (h)(1) of this AD, within 8,000 flight hours or 48 months, whichever occurs first after the effective date of this AD, modify the door crank handle with an improved bolt retention design on the type 1 emergency door, the aft entry door, and the aft service door, as applicable, in accordance with the Accomplishment Instructions of the applicable service information specified in paragraphs (i)(1) through (3) of this AD. (1) For the aft entry door: Bombardier Service Bulletin 84–52–89, Revision A, dated January 29, 2018. (2) For the aft service door: Bombardier Service Bulletin 84–52–92, Revision A, dated January 24, 2018. (3) For the type 1 emergency door: Bombardier Service Bulletin 84–52–94, Revision A, dated January 24, 2018. (j) Alternative Modification For airplanes with de Havilland Modification Summary Package 4Q459324 incorporated for the cargo combi configuration: Accomplishing the modification in paragraph (i) of this AD using Bombardier Service Bulletin 84–52–89, Revision A, dated January 29, 2018; and Bombardier Service Bulletin 84–52–92, Revision A, dated January 24, 2018; as applicable; in combination with de Havilland Modification Summary Package IS4Q5200101, Revision A, dated July 5, 2019, also meets the requirement specified in paragraph (i) of this AD for the aft entry and aft service doors. (k) Terminating Actions Accomplishing the action required by paragraph (i) of this AD terminates the requirements of paragraphs (g) and (h) of this AD. (l) Credit for Previous Actions (1) This paragraph provides credit for actions required by the introductory text to paragraph (g) of this AD, if those actions were performed before August 11, 2015 (the effective date of AD 2015–14–01) using Bombardier Service Bulletin 84–52–75, dated July 27, 2012, which is not incorporated by reference in this AD. (2) This paragraph provides credit for the modification of the applicable doors in paragraph (i) of this AD, if the modification was performed before the effective date of this AD using the applicable service PO 00000 Frm 00003 Fmt 4702 Sfmt 4702 information specified in paragraphs (l)(2)(i) through (iii) of this AD. (i) Bombardier Service Bulletin 84–52–89, dated April 13, 2017. (ii) Bombardier Service Bulletin 84–52–92, dated April 18, 2017. (iii) Bombardier Service Bulletin 84–52–94, dated April 13, 2017. (m) Other FAA AD Provisions (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 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 De Havilland Aircraft of Canada Limited’s TCCA Design Approval Organization (DAO). If approved by the DAO, the approval must include the DAOauthorized signature. (n) Related Information (1) Refer to Mandatory Continuing Airworthiness Information (MCAI) Canadian AD CF–2014–08R1, dated July 30, 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–2020–0200. (2) For more information about this AD, contact Darren Gassetto, Aerospace Engineer, Mechanical Systems and Administrative Services Section, FAA, New York ACO Branch, 1600 Stewart Avenue, Suite 410, Westbury, NY 11590; telephone 516–228– 7323; fax 516–794–5531; email 9-avs-nyacocos@faa.gov. (3) For service information identified in this AD, contact De Havilland Aircraft of Canada Limited, Q-Series Technical Help Desk, 123 Garratt Boulevard, Toronto, Ontario M3K 1Y5, Canada; telephone 416– 375–4000; fax 416–375–4539; email thd@ dehavilland.com; internet https:// dehavilland.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. E:\FR\FM\20MRP1.SGM 20MRP1 Federal Register / Vol. 85, No. 55 / Friday, March 20, 2020 / Proposed Rules Issued on March 13, 2020. Gaetano A. Sciortino, Deputy Director for Strategic Initiatives, Compliance & Airworthiness Division, Aircraft Certification Service. [FR Doc. 2020–05762 Filed 3–19–20; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2020–0201; Product Identifier 2020–NM–007–AD] RIN 2120–AA64 Airworthiness Directives; Airbus SAS Airplanes Federal Aviation Administration (FAA), DOT. ACTION: Notice of proposed rulemaking (NPRM). jbell on DSKJLSW7X2PROD with PROPOSALS AGENCY: SUMMARY: The FAA proposes to adopt a new airworthiness directive (AD) for certain Airbus SAS Model A318–111, –112, –121, and –122 airplanes; Model A319–111, –112, –113, –114, –115, –131, –132, and –133 airplanes; Model A320–211, –212, –214, –216, –231, –232, and –233 airplanes; and Model A321–111, –112, –131, –211, –212, –213, –231, and –232 airplanes. This proposed AD was prompted by reports of fatigue cracks on continuity fittings at the lower framing of the front windshield on airplanes on which a certain production modification has been embodied. Additional analysis showed that certain certification requirements for damage tolerance and fatigue are not met on airplanes in a certain post-production modification configuration. This proposed AD would require repetitive high frequency eddy current (HFEC) inspections of the central node windshield area for cracking, and applicable corrective actions if cracking is found, as specified in a European Union Aviation Safety Agency (EASA) AD, which will be incorporated by reference. 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 May 4, 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– VerDate Sep<11>2014 17:34 Mar 19, 2020 Jkt 250001 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 the material identified in this proposed AD that will be incorporated by reference (IBR), contact the EASA, Konrad-Adenauer-Ufer 3, 50668 Cologne, Germany; telephone +49 221 89990 1000; email ADs@easa.europa.eu; internet www.easa.europa.eu. You may find this IBR material on the EASA website at https://ad.easa.europa.eu. You may view this IBR material at the FAA, Transport Standards Branch, 2200 South 216th St., Des Moines, WA. For information on the availability of this material at the FAA, call 206–231–3195. It is also available in the AD docket on the internet at https:// www.regulations.gov by searching for and locating Docket No. FAA–2020– 0201. 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–2020– 0201; 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: Sanjay Ralhan, Aerospace Engineer, International Section, Transport Standards Branch, FAA, 2200 South 216th St., Des Moines, WA 98198; telephone and fax 206–231–3223; email sanjay.ralhan@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 the ADDRESSES section. Include ‘‘Docket No. FAA–2020–0201; Product Identifier 2020–NM–007–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 based on those comments. The FAA will post all comments, without change, to https:// PO 00000 Frm 00004 Fmt 4702 Sfmt 4702 16011 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 The EASA, which is the Technical Agent for the Member States of the European Union, has issued EASA AD 2020–0005, dated January 13, 2020 (‘‘EASA AD 2020–0005’’) (also referred to as the Mandatory Continuing Airworthiness Information, or ‘‘the MCAI’’), to correct an unsafe condition for certain Airbus SAS Model A318– 111, –112, –121, and –122 airplanes; Model A319–111, –112, –113, –114, –115, –131, –132, and –133 airplanes; Model A320–211, –212, –214, –215, –216, –231, –232, and –233 airplanes; and Model A321–111, –112, –131, –211, –212, –213, –231, and –232 airplanes. Model A320–215 airplanes are not certified by the FAA and are not included on the U.S. type certificate data sheet; this proposed AD therefore does not include those airplanes in the applicability. This proposed AD was prompted by reports of fatigue cracks on continuity fittings at the lower framing of the front windshield on airplanes on which Airbus Production Modification 22058 (which is included in Airbus Modification 21999) has been embodied. Additional analysis showed that certain certification requirements for damage tolerance and fatigue are not met on airplanes in a post-production Modification 22058 configuration. The FAA is proposing this AD to address this condition, which could lead to failure of the continuity fittings at the lower node of the windshield central frame, possibly resulting in decompression of the airplane and injury to occupants. See the MCAI for additional background information. Related IBR Material Under 1 CFR part 51 EASA AD 2020–0005 describes procedures for repetitive HFEC inspections of the central node windshield area for cracking, and applicable corrective actions if cracking is found. The corrective actions include modification or repair. This material 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 and Requirements of This Proposed AD This product has been approved by the aviation authority of another E:\FR\FM\20MRP1.SGM 20MRP1

Agencies

[Federal Register Volume 85, Number 55 (Friday, March 20, 2020)]
[Proposed Rules]
[Pages 16008-16011]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2020-05762]


========================================================================
Proposed Rules
                                                Federal Register
________________________________________________________________________

This section of the FEDERAL REGISTER contains notices to the public of 
the proposed issuance of rules and regulations. The purpose of these 
notices is to give interested persons an opportunity to participate in 
the rule making prior to the adoption of the final rules.

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


Federal Register / Vol. 85, No. 55 / Friday, March 20, 2020 / 
Proposed Rules

[[Page 16008]]



DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2020-0200; Product Identifier 2019-NM-185-AD]
RIN 2120-AA64


Airworthiness Directives; De Havilland Aircraft of Canada Limited 
(Type Certificate Previously Held by Bombardier, Inc.) Airplanes

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Notice of proposed rulemaking (NPRM).

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

SUMMARY: The FAA proposes to supersede Airworthiness Directive (AD) 
2015-14-01, which applies to certain Bombardier, Inc., Model DHC-8-400 
series airplanes. AD 2015-14-01 requires a detailed inspection for 
loose bolts on the aft translating door crank assembly, and removal and 
reinstallation of the bolts. Since AD 2015-14-01 was issued, the FAA 
received a report that additional airplanes may be subject to the 
unsafe condition. In addition, the design of the translating door crank 
handle has been improved. This proposed AD would retain the inspections 
of AD 2015-14-01 and add airplanes to the applicability. For all 
airplanes, this proposed AD would also require a modification of the 
door crank handle, which would terminate the inspections. 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 May 4, 
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 De 
Havilland Aircraft of Canada Limited, Q-Series Technical Help Desk, 123 
Garratt Boulevard, Toronto, Ontario M3K 1Y5, Canada; telephone 416-375-
4000; fax 416-375-4539; email [email protected]; internet https://dehavilland.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-2020-
0200; 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: Darren Gassetto, Aerospace Engineer, 
Mechanical Systems and Administrative Services Section, FAA, New York 
ACO Branch, 1600 Stewart Avenue, Suite 410, Westbury, NY 11590; 
telephone 516-228-7323; 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-2020-0200; 
Product Identifier 2019-NM-185-AD'' at the beginning of your comments. 
The FAA specifically invites comments on the overall regulatory, 
economic, environmental, and energy aspects of this proposed AD. The 
FAA will consider all comments received by the closing date and may 
amend this proposed AD based on 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 proposed AD.

Discussion

    The FAA issued AD 2015-14-01, Amendment 39-18199 (80 FR 38615, July 
7, 2015) (``AD 2015-14-01''), for certain Bombardier, Inc., Model DHC-
8-400 series airplanes. AD 2015-14-01 requires a detailed inspection 
for loose bolts on the aft translating door crank assembly, and removal 
and reinstallation of the bolts. AD 2015-14-01 resulted from a report 
of loose bolts that are intended to secure the translating door crank 
assembly to the outside handle shaft. The FAA issued AD 2015-14-01 to 
prevent loose bolts from falling out. If both bolts become loose or 
fall out after the door is closed and locked, the door cannot be opened 
from inside or outside, which could impede evacuation in the event of 
an emergency.

Actions Since AD 2015-14-01 was Issued

    Since AD 2015-14-01 was issued, the FAA received a report that 
loose bolts were found on airplane serial numbers that were outside the 
applicability range. Further, the manufacturer reclassified the forward 
baggage door on some airplanes as an emergency exit, which is not 
subject to AD 2015-14-01. The FAA also received a report that the 
manufacturer has modified the design of the translating door crank 
handle to improve retention of the bolts.
    Transport Canada Civil Aviation (TCCA), which is the aviation 
authority for Canada, has issued Canadian AD CF-2014-08R1, dated July 
30, 2019 (referred to after this as the Mandatory Continuing 
Airworthiness Information, or ``the MCAI''), to correct an unsafe 
condition for certain De Havilland Aircraft of Canada Limited (Type 
Certificate Previously Held by Bombardier, Inc.) Model DHC-8-400 series 
airplanes. You may examine the MCAI in the AD docket on the internet at 
https://www.regulations.gov by

[[Page 16009]]

searching for and locating Docket No. FAA-2020-0200.
    This proposed AD was prompted by reports of loose bolts that are 
intended to secure the translating door crank assembly to the outside 
handle shaft, and of sealant missing from these bolts on another 
translating door. The FAA is issuing this AD to address the potential 
for both bolts to become loose or fall out after the door is closed and 
locked, which would prevent the door from being opened from inside or 
outside and impede evacuation in the event of an emergency. See the 
MCAI for additional background information.

Related Service Information Under 1 CFR part 51

    De Havilland Aircraft of Canada Limited has issued the following 
service information.
     Bombardier Service Bulletin 84-52-89, Revision A, dated 
January 29, 2018.
     Bombardier Service Bulletin 84-52-92, Revision A, dated 
January 24, 2018.
     Bombardier Service Bulletin 84-52-94, Revision A, dated 
January 24, 2018.
    This service information describes procedures for modifying the 
door crank handle with an improved bolt retention design on the type 1 
emergency door, the aft entry door, and the aft service door, as 
necessary. These documents are distinct since they apply to different 
airplane configurations.
    De Havilland Aircraft of Canada Limited has also issued Bombardier 
Service Bulletin 84-52-96, dated February 26, 2019, which describes 
procedures for a detailed visual inspection of the translating door 
crank assembly for any loose bolts.
    De Havilland Aircraft of Canada Limited has also issued 
Modification Summary Package IS4Q5200101, Revision A, dated July 5, 
2019, which describes a deviation to the actions specified in certain 
service information.
    This proposed AD would also require Bombardier Service Bulletin 84-
52-75, Revision A, dated July 11, 2013, which the Director of the 
Federal Register approved for incorporation by reference as of August 
11, 2015 (80 FR 38615, July 7, 2015).
    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 retain the inspections of AD 2015-14-01. 
This proposed AD would require accomplishing the actions specified in 
the service information described previously.

Explanation of Change to Manufacturer's Name Specified in AD 2015-14-01

    This NPRM identifies the manufacturer's name as published in the 
most recent type certificate data sheet for the affected models.

Costs of Compliance

    The FAA estimates that this proposed AD affects 59 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
----------------------------------------------------------------------------------------------------------------
Up to 13 work[dash]hours x $85  Up to $677................  Up to $1,782.............  Up to $105,138.
 per hour = $1,105.
----------------------------------------------------------------------------------------------------------------

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.

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 removing Airworthiness Directive (AD) 
2015-14-01, Amendment 39-18199 (80 FR 38615, July 7, 2015), and adding 
the following new AD:

De Havilland Aircraft of Canada Limited (Type Certificate Previously 
Held by

[[Page 16010]]

Bombardier, Inc.) Airplanes: Docket No. FAA-2020-0200; Product 
Identifier 2019-NM-185-AD.

(a) Comments Due Date

    The FAA must receive comments by May 4, 2020.

(b) Affected ADs

    This AD replaces AD 2015-14-01, Amendment 39-18199 (80 FR 38615, 
July 7, 2015) (``AD 2015-14-01'').

(c) Applicability

    This AD applies to De Havilland Aircraft of Canada Limited (Type 
Certificate Previously Held by Bombardier, Inc.) Model DHC-8-400, -
401, and -402 airplanes, certificated in any category, serial 
numbers (S/Ns) 4001 through 4530 inclusive.

(d) Subject

    Air Transport Association (ATA) of America Code 52, Doors.

(e) Reason

    This proposed AD was prompted by reports of loose bolts that are 
intended to secure the translating door crank assembly to the 
outside handle shaft, and of sealant missing from these bolts on 
another translating door. The FAA is issuing this AD to address the 
potential for both bolts to become loose or fall out after the door 
is closed and locked, which would prevent the door from being opened 
from inside or outside and impede evacuation in the event of an 
emergency.

(f) Compliance

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

(g) Inspection and Corrective Actions for S/Ns 4001 Through 4411 
Inclusive

    For airplane S/Ns 4001 through 4411 inclusive: Within 600 flight 
hours or 100 days, whichever occurs first after August 11, 2015 (the 
effective date of AD 2015-14-01): Perform a detailed inspection for 
loose bolts of the aft translating door crank assembly, in 
accordance with paragraph 3.B., ``Procedure,'' of Part A--INSPECTION 
of the Accomplishment Instructions of Bombardier Service Bulletin 
84-52-75, Revision A, dated July 11, 2013.
    (1) If the detailed inspection was done before the effective 
date of this AD and the corrective action was done in accordance 
with 3.B., ``Procedure,'' and steps 3.C.(4) and 3.C.(5) of paragraph 
3.C., ``Close Out,'' of Part B--RECTIFICATION, of the Accomplishment 
Instructions of Bombardier Service Bulletin 84-52-75, dated July 27, 
2012; or Bombardier Service Bulletin 84-52-75, Revision A, dated 
July 11, 2013: No further work is required by paragraph (g) of this 
AD.
    (2) If the detailed inspection is done on or after the effective 
date of this AD, and any loose bolt is found: Before further flight, 
do the modification in paragraph (i) of this AD.

(h) Inspection and Modification for S/Ns 4412 Through 4491 Inclusive

    For airplane S/Ns 4412 through 4491 inclusive: Within 800 flight 
hours or 120 days, whichever occurs first after the effective date 
of this AD, perform a detailed inspection for loose bolts of the 
translating door crank assembly, in accordance with paragraph 3.B., 
``Procedure,'' of the Accomplishment Instructions of Bombardier 
Service Bulletin 84-52-96, dated February 26, 2019.
    (1) If any loose bolt is found, before further flight do the 
modification specified in paragraph (i) of this AD.
    (2) If no loose bolt is found, at the compliance time specified 
in paragraph (i) of this AD, do the modification specified in 
paragraph (i) of this AD.

(i) Modification for S/Ns 4001 Through 4530 Inclusive

    For airplane S/Ns 4001 through 4530 inclusive: Except as 
required by paragraphs (g)(2) and (h)(1) of this AD, within 8,000 
flight hours or 48 months, whichever occurs first after the 
effective date of this AD, modify the door crank handle with an 
improved bolt retention design on the type 1 emergency door, the aft 
entry door, and the aft service door, as applicable, in accordance 
with the Accomplishment Instructions of the applicable service 
information specified in paragraphs (i)(1) through (3) of this AD.
    (1) For the aft entry door: Bombardier Service Bulletin 84-52-
89, Revision A, dated January 29, 2018.
    (2) For the aft service door: Bombardier Service Bulletin 84-52-
92, Revision A, dated January 24, 2018.
    (3) For the type 1 emergency door: Bombardier Service Bulletin 
84-52-94, Revision A, dated January 24, 2018.

(j) Alternative Modification

    For airplanes with de Havilland Modification Summary Package 
4Q459324 incorporated for the cargo combi configuration: 
Accomplishing the modification in paragraph (i) of this AD using 
Bombardier Service Bulletin 84-52-89, Revision A, dated January 29, 
2018; and Bombardier Service Bulletin 84-52-92, Revision A, dated 
January 24, 2018; as applicable; in combination with de Havilland 
Modification Summary Package IS4Q5200101, Revision A, dated July 5, 
2019, also meets the requirement specified in paragraph (i) of this 
AD for the aft entry and aft service doors.

(k) Terminating Actions

    Accomplishing the action required by paragraph (i) of this AD 
terminates the requirements of paragraphs (g) and (h) of this AD.

(l) Credit for Previous Actions

    (1) This paragraph provides credit for actions required by the 
introductory text to paragraph (g) of this AD, if those actions were 
performed before August 11, 2015 (the effective date of AD 2015-14-
01) using Bombardier Service Bulletin 84-52-75, dated July 27, 2012, 
which is not incorporated by reference in this AD.
    (2) This paragraph provides credit for the modification of the 
applicable doors in paragraph (i) of this AD, if the modification 
was performed before the effective date of this AD using the 
applicable service information specified in paragraphs (l)(2)(i) 
through (iii) of this AD.
    (i) Bombardier Service Bulletin 84-52-89, dated April 13, 2017.
    (ii) Bombardier Service Bulletin 84-52-92, dated April 18, 2017.
    (iii) Bombardier Service Bulletin 84-52-94, dated April 13, 
2017.

(m) Other FAA AD Provisions

    (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 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 De 
Havilland Aircraft of Canada Limited's TCCA Design Approval 
Organization (DAO). If approved by the DAO, the approval must 
include the DAO-authorized signature.

(n) Related Information

    (1) Refer to Mandatory Continuing Airworthiness Information 
(MCAI) Canadian AD CF-2014-08R1, dated July 30, 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-2020-0200.
    (2) For more information about this AD, contact Darren Gassetto, 
Aerospace Engineer, Mechanical Systems and Administrative Services 
Section, FAA, New York ACO Branch, 1600 Stewart Avenue, Suite 410, 
Westbury, NY 11590; telephone 516-228-7323; fax 516-794-5531; email 
[email protected].
    (3) For service information identified in this AD, contact De 
Havilland Aircraft of Canada Limited, Q-Series Technical Help Desk, 
123 Garratt Boulevard, Toronto, Ontario M3K 1Y5, Canada; telephone 
416-375-4000; fax 416-375-4539; email [email protected]; internet 
https://dehavilland.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.


[[Page 16011]]


    Issued on March 13, 2020.
Gaetano A. Sciortino,
Deputy Director for Strategic Initiatives, Compliance & Airworthiness 
Division, Aircraft Certification Service.
[FR Doc. 2020-05762 Filed 3-19-20; 8:45 am]
 BILLING CODE 4910-13-P
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