83 FR 10411 - Airworthiness Directives; Airbus Airplanes
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration Federal Register Volume 83, Issue 47 (March 9, 2018)
Federal Aviation Administration
Federal Register Volume 83, Issue 47 (March 9, 2018)
| Page Range | 10411-10415 | |
| FR Document | 2018-04727 |
[Federal Register Volume 83, Number 47 (Friday, March 9, 2018)] [Proposed Rules] [Pages 10411-10415] From the Federal Register Online [www.thefederalregister.org] [FR Doc No: 2018-04727] ----------------------------------------------------------------------- DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA-2018-0165; Product Identifier 2017-NM-122-AD] RIN 2120-AA64 Airworthiness Directives; Airbus Airplanes AGENCY: Federal Aviation Administration (FAA), DOT. ACTION: Notice of proposed rulemaking (NPRM). ----------------------------------------------------------------------- SUMMARY: We propose to adopt a new airworthiness directive (AD) for all Airbus Model A318-111 and -112 airplanes, Model A319-111, -112, -113, - 114, and -115 airplanes, Model A320-211, -212, -214, and -216 airplanes, and Model A321-111, -112, -211, -212, and -213 airplanes. This proposed AD was prompted by a report of a production quality deficiency on the [[Page 10412]] inner retainer installed on link assemblies of the aft engine mount, which could result in failure of the retainer. This proposed AD would require modifying and re-identifying the aft engine mount assemblies. We are proposing this AD to address the unsafe condition on these products. DATES: We must receive comments on this proposed AD by April 23, 2018. 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 http://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 Airbus service information identified in this NPRM, contact Airbus, Airworthiness Office--EIAS, 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex, France; telephone +33 5 61 93 36 96; fax +33 5 61 93 44 51; email [email protected]; internet http://www.airbus.com. For Goodrich Aerospace service information identified in this NPRM, contact Goodrich Corporation, Aerostructures, 850 Lagoon Drive, Chula Vista, CA 91910-2098; phone: 619-691-2719; email: [email protected]; internet: http://www.goodrich.com/TechPubs. 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 http://www.regulations.gov by searching for and locating Docket No. FAA-2018- 0165; or in person at the Docket Management Facility between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. The AD docket contains this NPRM, the regulatory evaluation, any comments received, and other information. The street address for the Docket Operations office (telephone 800-647-5527) is in the ADDRESSES section. 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. SUPPLEMENTARY INFORMATION: Comments Invited We invite 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-2018-0165; Product Identifier 2017-NM-122-AD'' at the beginning of your comments. We specifically invite comments on the overall regulatory, economic, environmental, and energy aspects of this NPRM. We will consider all comments received by the closing date and may amend this NPRM based on those comments. We will post all comments we receive, without change, to http://www.regulations.gov, including any personal information you provide. We will also post a report summarizing each substantive verbal contact we receive about this NPRM. Discussion The European Aviation Safety Agency (EASA), which is the Technical Agent for the Member States of the European Union, has issued EASA Airworthiness Directive 2017-0251, dated December 15, 2017 (referred to after this as the Mandatory Continuing Airworthiness Information, or ``the MCAI''), to correct an unsafe condition for all Airbus Model A318-111 and -112 airplanes, Model A319-111, -112, -113, -114, and -115 airplanes, Model A320-211, -212, -214, and -216 airplanes, and Model A321-111, -112, -211, -212, and -213 airplanes. The MCAI states: During in-service inspections, several aft engine mount inner retainers, fitted on aeroplanes equipped with CFM56-5A/5B engines, were found broken. Investigation identified that the main cause of crack initiation was the vibration dynamic effect that affects the retainers, and that the ``dull'' surface finish pitting is an aggravating factor when compared with the ``bright'' surface finishing. This condition, if not detected and corrected, could lead to in- flight loss of an aft engine mount link, possibly resulting in damage to the aeroplane and/or injury to persons on the ground. To address this potential unsafe condition, Airbus issued Alert Operators Transmission (AOT) A71N001-12 (later revised) and EASA issued AD 2013-0050 [which corresponds to FAA AD 2014-14-06, Amendment 39-17901 (79 FR 42655, July 23, 2014)], later superseded by EASA AD 2015-0021 [which corresponds to FAA AD 2016-14-09, Amendment 39-18590 (81 FR 44989, July 12, 2016) (``AD 2016-14- 09'')], requiring repetitive detailed inspections (DET) of all aft engine mount inner retainers and, depending on findings, their replacement. After EASA AD 2015-0021 was issued, a production quality deficiency was identified by Airbus and Goodrich Aerostructures, the engine mount retainer manufacturer, on the inner retainer, Part Number (P/N) 238-0252-505, installed in the three link assemblies of the engine mount fitted on CFM56-5A/5B engines. Airbus issued AOT A71N011-15 and Service Bulletin (SB) A320-71-1070, providing a list of affected parts and applicable corrective actions. Consequently, EASA issued AD 2016-0010 (later revised), retaining the requirements of EASA AD 2015-0021, which was superseded, and in addition requiring the identification and replacement of all non-conforming aft engine mount inner retainers [EASA AD 2016-0010 R1 corresponds to FAA AD 2017-04-10, Amendment 39-18805 (82 FR 11791, February 27, 2017) (``AD 2017-04-10'')]. After that [EASA] AD was issued, a new engine mount retainer was developed by Goodrich Aerostructures to improve the retainer efficiency. For retrofit purposes, Goodrich Aerostructures issued SB RA32071-164, and Airbus issued SB A320-71-1071, providing instructions to modify and re-identify the engine mount assemblies as instructed in the Goodrich Aerostructures SB. Subsequently, it was observed that, on aeroplanes equipped with certain engines fitted with a Turbine Rear Frame (TRF) with 4 lugs configuration, the installation of the new engine mount retainers can lead to interference, and Goodrich Aerostructures revised SB RA32071-164, providing instructions not to install the new engine retainers on affected engines. Airbus SB A320-71-1071 is expected to be revised accordingly. For engines fitted with a TRF with 4 lugs, a new installation (potentially requiring different engine mount retainers) is being developed by Goodrich Aerospace and Airbus. Consequently, EASA issued AD 2017-0138, retaining the requirements of EASA AD 2016-0010R1, which was superseded, and, except for aeroplanes equipped with engines fitted with a TRF with 4 lugs configuration, requiring modification and identification of aft engine mount assemblies as terminating action for the repetitive inspections of the retainers. That [EASA] AD also included additional instructions applicable to installation of engines fitted with a TRF with 4 lugs configuration. Since EASA AD 2017-0138 was issued, it was determined that installation of new engine mount assemblies must not be allowed for some specific engine configurations, and that installation of Goodrich Aerostructures SB RA32071-164 alone can be referred to, in order to accomplish the terminating action as required by that [EASA] AD. For the reason described above, this [EASA] AD retains the requirements of EASA AD 2017-0138, which is superseded, adds reference to Goodrich Aerostructures SB RA32071-164 * * *, and introduces new requirement for aeroplanes equipped with engines fitted with a TRF with 4 lugs configuration. [[Page 10413]] This NPRM would not supersede AD 2017-04-10. Rather, we have determined that a stand-alone AD would be more appropriate to address the changes in the MCAI. This NPRM would require modifying and re- identifying the aft engine mount assemblies. Accomplishment of the proposed actions would then terminate the repetitive detailed inspections required by paragraph (l) of AD 2016-14-09, and serve as a method of compliance for the requirements of paragraph (g) of AD 2017- 04-10. You may examine the MCAI in the AD docket on the internet at http://www.regulations.gov by searching for and locating Docket No. FAA-2018-0165. Related Service Information Under 1 CFR Part 51 Airbus has issued Service Bulletin A320-71-1071, dated November 8, 2016. Goodrich Aerostructures has issued Service Bulletin RA32071-164, Revision 1, dated July 19, 2017. The service information describes procedures for modifying and re-identifying the aft engine mount retainer assembly. These documents are distinct since they apply to different airplane models in different configurations. This service information is reasonably available because the interested parties have access to it through their normal course of business or by the means identified in the ADDRESSES section. FAA's Determination and Requirements of This Proposed AD This product has been approved by the aviation authority of another country, and is approved for operation in the United States. Pursuant to our bilateral agreement with the State of Design Authority, we have been notified of the unsafe condition described in the MCAI and service information referenced above. We are proposing this AD because we evaluated all pertinent information and determined an unsafe condition exists and is likely to exist or develop on other products of these same type designs. Costs of Compliance We estimate that this proposed AD affects 500 airplanes of U.S. registry. We estimate the following costs to comply with this proposed AD: Estimated Costs ---------------------------------------------------------------------------------------------------------------- Cost per Cost on U.S. Action Labor cost Parts cost product operators ---------------------------------------------------------------------------------------------------------------- Modification and re-identification. 20 work-hours x $85 per $3,152 $4,852 $2,426,000 hour = $1,700. ---------------------------------------------------------------------------------------------------------------- Authority for This Rulemaking Title 49 of the United States Code specifies the FAA's authority to issue rules on aviation safety. Subtitle I, section 106, describes the authority of the FAA Administrator. ``Subtitle VII: Aviation Programs,'' describes in more detail the scope of the Agency's authority. We are issuing this rulemaking under the authority described in ``Subtitle VII, Part A, Subpart III, Section 44701: General requirements.'' Under that section, Congress charges the FAA with promoting safe flight of civil aircraft in air commerce by prescribing regulations for practices, methods, and procedures the Administrator finds necessary for safety in air commerce. This regulation is within the scope of that authority because it addresses an unsafe condition that is likely to exist or develop on products identified in this rulemaking action. This 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 to the Director of the System Oversight Division. Regulatory Findings We 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. Is not a ``significant rule'' under the DOT Regulatory Policies and Procedures (44 FR 11034, February 26, 1979); 3. Will not affect intrastate aviation in Alaska; and 4. Will not have a significant economic impact, positive or negative, on a substantial number of small entities under the criteria of the Regulatory Flexibility Act. List of Subjects in 14 CFR Part 39 Air transportation, Aircraft, Aviation safety, Incorporation by reference, Safety. 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): Airbus: Docket No. FAA-2018-0165; Product Identifier 2017-NM-122-AD. (a) Comments Due Date We must receive comments by April 23, 2018. (b) Affected ADs This AD affects AD 2016-14-09, Amendment 39-18590 (81 FR 44989, July 12, 2016) (``AD 2016-14-09''); and AD 2017-04-10, Amendment 39- 18805 (82 FR 11791, February 27, 2017) (``AD 2017-04-10''). (c) Applicability This AD applies to the Airbus airplanes identified in paragraphs (c)(1) through (c)(4) of this AD, certificated in any category, all manufacturer serial numbers. (1) Model A318-111 and -112 airplanes. (2) Model A319-111, -112, -113, -114, and -115 airplanes. (3) Model A320-211, -212, -214, and -216 airplanes. (4) Model A321-111, -112, -211, -212, and -213 airplanes. (d) Subject Air Transport Association (ATA) of America Code 71, Powerplant. [[Page 10414]] (e) Reason This AD was prompted by a report of a production quality deficiency on the inner retainer installed on link assemblies of the aft engine mount, which could result in failure of the retainer. We are issuing this AD to address non-conforming retainers of the aft engine mount. This condition could result in loss of the locking feature of the nuts of the inner and outer pins; loss of the pins will result in the aft mount engine link no longer being secured to the aft engine mount, possibly resulting in damage to the airplane. (f) Compliance Comply with this AD within the compliance times specified, unless already done. (g) Definitions (1) For the purpose of this AD: A Group 1 airplane has an aft engine mount assembly installed, having a part number (P/N) identified as ``Old P/N'' in figure 1 to paragraphs (g), (h), (i), (j), (k), and (l) of this AD. A Group 2 airplane does not have any aft engine mount assembly installed having a part number identified as ``Old P/N'' in figure 1 to paragraphs (g), (h), (i), (j), (k), and (l) of this AD. (2) For the purpose of this AD, a 4-lugs engine is a CFM56-5A1, CFM56-5A3, CFM56-5A4, CFM56-5A4/F, CFM56-5A5, or CFM56-5A5/F engine, fitted with a turbine rear frame (TRF) having a part number as identified in figure 2 to paragraph (g) of this AD. Figure 1 to Paragraphs (g), (h), (i), (j), (k), and (l) of this AD--Part Re-Identification ------------------------------------------------------------------------ Old P/N New P/N ------------------------------------------------------------------------ 238-0230-11............................ 238M0230-11 238-0230-15............................ 238M0230-15 238-0230-5............................. 238M0230-5 642-2300-3............................. 642-2300-11 ------------------------------------------------------------------------ Figure 2 to Paragraph (g) of This AD--TRF With 4-Lugs Configuration ------------------------------------------------------------------------ Part No. ------------------------------------------------------------------------- 336-031-615-0 336-031-617-0 336-031-618-0 336-031-621-0 336-031-650-0 336-031-651-0 336-031-652-0 336-031-653-0 336-031-660-0 336-031-661-0 336-031-662-0 336-031-663-0 336-031-670-0 336-031-671-0 336-031-672-0 336-031-673-0 336-031-640-0 336-031-642-0 ------------------------------------------------------------------------ (h) Modification For Group 1 airplanes: Within 48 months after the effective date of this AD, except for 4-lugs engines, modify the aft engine mount assembly, having a part number identified as ``Old P/N'' in figure 1 to paragraphs (g), (h), (i), (j), (k), and (l) of this AD, and re- identify it with the corresponding part number identified as ``New P/N'' in figure 1 to paragraphs (g), (h), (i), (j), (k), and (l) of this AD, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A320-71-1071, dated November 8, 2016; or Goodrich Aerostructures Service Bulletin RA32071-164, Revision 1, dated July 19, 2017. (i) Other Acceptable Method of Compliance Replacement on an airplane of each aft engine mount assembly, identified as ``Old P/N'' in figure 1 to paragraphs (g), (h), (i), (j), (k), and (l) of this AD, with a corresponding aft engine mount assembly, identified as ``New P/N'' in figure 1 to paragraphs (g), (h), (i), (j), (k), and (l) of this AD, is an acceptable method to comply with the requirements of paragraph (h) of this AD for that airplane. (j) Identification of Certain Airplanes That Do Not Have Affected Parts An airplane on which Airbus modification 158435 has been embodied in production and on which it can be positively determined that no aft engine mount assembly, identified as ``Old P/N'' in figure 1 to paragraphs (g), (h), (i), (j), (k), and (l) of this AD, is installed, is considered a Group 2 airplane. A review of airplane maintenance records is acceptable to make this determination, if it can be conclusively determined that no aft engine mount assembly identified as ``Old P/N'' in figure 1 to paragraphs (g), (h), (i), (j), (k), and (l) of this AD is installed. Group 2 airplanes are not affected by the requirements of paragraph (h) of this AD. (k) Parts Installation Prohibition (1) For Group 1 airplanes: Do not install an aft engine mount assembly identified as ``Old P/N'' in figure 1 to paragraphs (g), (h), (i), (j), (k), and (l) of this AD on any airplane after modification of the airplane as required by paragraph (h) of this AD, or after any replacement specified in paragraph (i) of this AD. (2) For Group 2 airplanes: As of the effective date of this AD, do not install an aft engine mount assembly identified as ``Old P/ N'' in figure 1 to paragraphs (g), (h), (i), (j), (k), and (l) of this AD on any airplane. (3) For airplanes equipped with a 4-lugs engine (left-hand (LH) or right-hand (RH) side): As of the effective date of this AD, do not modify any aft engine mount assembly identified as ``Old P/N'' in figure 1 to paragraphs (g), (h), (i), (j), (k), and (l) of this AD, as required by paragraph (h) of this AD, and do not install on an affected engine pylon (LH or RH) any aft engine mount assembly identified as ``New P/N'' in figure 1 to paragraphs (g), (h), (i), (j), (k), and (l) of this AD. (l) 4-Lugs Engine Installation (1) From the effective date of this AD, it is allowed to install or reinstall a 4-lugs engine on an airplane (LH or RH) provided that the airplane is equipped with an aft engine mount assembly identified as ``Old P/N'' in figure 1 to paragraphs (g), (h), (i), (j), (k), and (l) of this AD on the affected engine pylon (LH or RH). (2) For airplanes equipped with a 4-lugs engine (LH or RH), and on which, prior to the effective date of this AD, an aft engine mount assembly identified as ``New P/N'' in figure 1 to paragraphs (g), (h), (i), (j), (k), and (l) of this AD has been installed on the affected engine pylon (LH or RH), or on which the aft engine part assembly has been modified as specified in paragraph (h) of this AD: Within 30 days after the effective date of this AD, obtain repair instructions using a method approved by the Manager, International Section, Transport Standards Branch, FAA; or the European Aviation Safety Agency (EASA); or Airbus's EASA Design Organization Approval (DOA), and accomplish those instructions accordingly. If approved by the DOA, the approval must include the DOA-authorized signature. (m) Terminating Action and Method of Compliance (1) Modification of an airplane as required by paragraph (h) of this AD, or as specified in paragraph (i) of this AD, constitutes terminating action for the repetitive detailed inspections required by paragraph (l) of AD 2016-14-09 for that airplane. (2) Modification of an airplane as required by paragraph (h) of this AD, or as specified in paragraph (i) of this AD, is a method of compliance with the requirements of paragraph (g) of AD 2017-04-10 for that airplane. (n) 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 (p)(2) of this AD. Information may be emailed to: [email protected]. 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, International Section, Transport Standards Branch, FAA; or EASA; or Airbus's EASA DOA. If approved by the DOA, the approval must include the DOA- authorized signature. (3) Required for Compliance (RC): If any service information contains procedures or tests that are identified as RC, those procedures and tests must be done to comply [[Page 10415]] 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. (o) Special Flight Permits Special flight permits, as described in Section 21.197 and Section 21.199 of the Federal Aviation Regulations (14 CFR 21.197 and 21.199), are not allowed. (p) Related Information (1) Refer to Mandatory Continuing Airworthiness Information (MCAI) EASA Airworthiness Directive 2017-0251 dated December 15, 2017, for related information. This MCAI may be found in the AD docket on the internet at http://www.regulations.gov by searching for and locating Docket No. FAA-2018-0165. (2) For more information about this AD, 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. (3) For Airbus service information identified in this AD, contact Airbus, Airworthiness Office--EIAS, 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex, France; telephone +33 5 61 93 36 96; fax +33 5 61 93 44 51; email [email protected]; internet http://www.airbus.com. (4) For Goodrich Aerospace service information identified in this AD, contact Goodrich Corporation, Aerostructures, 850 Lagoon Drive, Chula Vista, CA 91910-2098; phone: 619-691-2719; email: [email protected]; internet: http://www.goodrich.com/TechPubs. 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 Renton, Washington, on March 5, 2018. Michael Kaszycki, Acting Director, System Oversight Division, Aircraft Certification Service. [FR Doc. 2018-04727 Filed 3-8-18; 8:45 am] BILLING CODE 4910-13-P
![Federal Register / Vol. 83, No. 47 / Friday, March 9, 2018 / Proposed Rules 10411
paragraph (g) of this AD and all applicable applicable, terminates the requirements of actions from a manufacturer, the action must
corrective actions required by paragraph (h) paragraphs (h), (i), and (j) of this AD. be accomplished using a method approved
of this AD, check the bolt preload, and do all by the Manager, New York ACO Branch,
(n) Parts Installation Prohibition FAA; or Transport Canada Civil Aviation
applicable corrective actions, in accordance
with paragraph 3.B., ‘‘Procedure,’’ of the After modification of an airplane as (TCCA); or Bombardier, Inc.’s TCCA Design
Accomplishment Instructions of Bombardier required by paragraphs (l) and (m) of this AD, Approval Organization (DAO). If approved by
Alert Service Bulletin A84–55–04, Revision no person may install a DSC228 series barrel the DAO, the approval must include the
C, dated May 3, 2016. Do all applicable nut at the horizontal-stabilizer-to-vertical- DAO-authorized signature.
corrective actions before further flight. stabilizer attachment joint on the modified
airplane. (r) Related Information
Accomplishment of the actions required by
paragraphs (l) and (m) of this AD, as (1) Refer to Mandatory Continuing
(o) Terminating Actions Airworthiness Information (MCAI) TCCA
applicable, terminates the requirements of
Accomplishment of the actions required by Airworthiness Directive CF–2015–13R1,
this paragraph.
paragraphs (l) and (m) of this AD, as dated June 26, 2017, for related information.
(j) Retained Repetitive Inspection Interval, applicable, terminates the requirements of This MCAI may be found in the AD docket
With New Terminating Action paragraphs (h), (i), and (j) of this AD. on the internet at http://www.regulations.gov
This paragraph restates the requirements of (p) Credit for Previous Actions by searching for and locating Docket No.
paragraph (j) of AD 2016–24–03, with new FAA–2018–0160.
(1) This paragraph provides credit for (2) For more information about this AD,
terminating action. Repeat the inspection and actions required by paragraphs (g)(1), (g)(2),
preload check required by paragraphs (g) and contact Aziz Ahmed, Aerospace Engineer,
(h)(1), (h)(1)(i), (h)(1)(ii), (h)(2), (h)(3), (h)(4), Airframe and Mechanical Systems Section,
(i) of this AD at intervals not to exceed 3,600 (i), and (k) of this AD, if those actions were
flight hours or 18 months, whichever occurs FAA, New York ACO Branch, 1600 Stewart
performed before the effective date of this AD Avenue, Suite 410, Westbury, NY 11590;
first, except as provided by paragraph (k) of using the service information identified in
this AD. Accomplishment of the actions telephone 516–228–7329; fax 516–794–5531.
paragraphs (p)(1)(i) through (p)(1)(iii) of this (3) For service information identified in
required by paragraphs (l) and (m) of this AD, AD.
as applicable, terminates the requirements of this AD, contact Bombardier, Inc., Q-Series
(i) Bombardier Alert Service Bulletin A84– Technical Help Desk, 123 Garratt Boulevard,
this paragraph. 55–04, dated May 21, 2015, which is not Toronto, Ontario M3K 1Y5, Canada;
(k) Retained Optional Barrel Nut incorporated by reference in this AD. telephone 416–375–4000; fax 416–375–4539;
Replacement, With New Service Information (ii) Bombardier Alert Service Bulletin A84– email thd.qseries@aero.bombardier.com;
55–04, Revision A, dated June 2, 2015, which internet http://www.bombardier.com. You
This paragraph restates the provisions of is not incorporated by reference in this AD.
paragraph (k) of AD 2016–24–03, with new may view this service information at the
(iii) Bombardier Alert Service Bulletin FAA, Transport Standards Branch, 2200
service information. Inspection and A84–55–04, Revision B, dated July 30, 2015,
replacement of all barrel nuts at the South 216th St., Des Moines, WA. For
which is not incorporated by reference in this information on the availability of this
horizontal-stabilizer-to-vertical-stabilizer AD.
attachment joints, in accordance with material at the FAA, call 206–231–3195.
(2) This paragraph provides credit for
paragraph 3.B., ‘‘Procedure,’’ of the actions required by paragraphs (h)(1), Issued in Renton, Washington, on March 2,
Accomplishment Instructions of Bombardier (h)(1)(i), (h)(1)(ii), (h)(2), and (k) of this AD, 2018.
Service Bulletin 84–55–08, Revision A, dated if those actions were performed before the Michael Kaszycki,
August 2, 2017, extends the next inspection effective date of this AD using the service
required by paragraph (j) of this AD to within Acting Director, System Oversight Division,
information identified in paragraphs (p)(2)(i) Aircraft Certification Service.
6,000 flight hours or 36 months, whichever and (p)(2)(ii) of this AD.
occurs first, after accomplishing the (i) Bombardier Service Bulletin 84–55–08, [FR Doc. 2018–04720 Filed 3–8–18; 8:45 am]
replacement. dated January 27, 2017, which is not BILLING CODE 4910–13–P
(l) New Requirement of This AD: Sealing incorporated by reference in this AD.
Disk Installation (ii) Bombardier Alert Service Bulletin A84–
55–04, Revision C, dated May 3, 2016, which DEPARTMENT OF TRANSPORTATION
Within 8,000 flight hours or 48 months, was incorporated by reference in AD 2016–
whichever occurs first, after the effective date 24–03. Federal Aviation Administration
of this AD, install a sealing disk at the mid-
spar location of the vertical stabilizer in (q) Other FAA AD Provisions
accordance with paragraph 3.B., 14 CFR Part 39
(1) Alternative Methods of Compliance
‘‘Procedure,’’ of the Accomplishment (AMOCs): The Manager, New York ACO [Docket No. FAA–2018–0165; Product
Instructions of Bombardier Service Bulletin Branch, FAA, has the authority to approve Identifier 2017–NM–122–AD]
84–55–06, dated January 31, 2017. AMOCs for this AD, if requested using the
Accomplishment of the actions required by procedures found in 14 CFR 39.19. In RIN 2120–AA64
paragraphs (l) and (m) of this AD, as accordance with 14 CFR 39.19, send your
applicable, terminates the requirements of request to your principal inspector or local Airworthiness Directives; Airbus
paragraphs (h), (i), and (j) of this AD. Flight Standards District Office, as Airplanes
appropriate. If sending information directly
(m) New Requirement of This AD:
to the manager of the certification office, AGENCY: Federal Aviation
Replacement of DSC228 Series Barrel Nuts send it to ATTN: Program Manager, Administration (FAA), DOT.
For Bombardier, Inc., Model DHC–8–400, Continuing Operational Safety, FAA, New ACTION: Notice of proposed rulemaking
–401 and –402 airplanes, serial numbers York ACO Branch, 1600 Stewart Avenue, (NPRM).
4001 through 4524 inclusive: Within 8,000 Suite 410, Westbury, NY 11590; telephone
flight hours or 48 months, whichever occurs 516–228–7300; fax 516–794–5531. SUMMARY: We propose to adopt a new
first, after the effective date of this AD, (i) Before using any approved AMOC, airworthiness directive (AD) for all
replace all DSC228 series barrel nuts at the notify your appropriate principal inspector,
amozie on DSK30RV082PROD with PROPOSALS
Airbus Model A318–111 and –112
horizontal-stabilizer-to-vertical-stabilizer or lacking a principal inspector, the manager airplanes, Model A319–111, –112, –113,
attachment joints with B0203073 series barrel of the local flight standards district office/ –114, and –115 airplanes, Model A320–
nuts in accordance with paragraph 3.B., certificate holding district office.
‘‘Procedure,’’ of the Accomplishment (ii) AMOCs approved previously for AD 211, –212, –214, and –216 airplanes,
Instructions of Bombardier Service Bulletin 2016–24–03 are approved as AMOCs for the and Model A321–111, –112, –211, –212,
84–55–08, Revision A, dated August 2, 2017. corresponding provisions of this AD. and –213 airplanes. This proposed AD
Accomplishment of the actions required by (2) Contacting the Manufacturer: For any was prompted by a report of a
paragraphs (l) and (m) of this AD, as requirement in this AD to obtain corrective production quality deficiency on the
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![10412 Federal Register / Vol. 83, No. 47 / Friday, March 9, 2018 / Proposed Rules
inner retainer installed on link International Section, Transport engine mount inner retainers and, depending
assemblies of the aft engine mount, Standards Branch, FAA, 2200 South on findings, their replacement.
which could result in failure of the 216th St., Des Moines, WA 98198; After EASA AD 2015–0021 was issued, a
production quality deficiency was identified
retainer. This proposed AD would telephone and fax 206–231–3223. by Airbus and Goodrich Aerostructures, the
require modifying and re-identifying the SUPPLEMENTARY INFORMATION: engine mount retainer manufacturer, on the
aft engine mount assemblies. We are inner retainer, Part Number (P/N) 238–0252–
proposing this AD to address the unsafe Comments Invited
505, installed in the three link assemblies of
condition on these products. We invite you to send any written the engine mount fitted on CFM56–5A/5B
DATES: We must receive comments on relevant data, views, or arguments about engines. Airbus issued AOT A71N011–15
this proposed AD by April 23, 2018. this proposal. Send your comments to and Service Bulletin (SB) A320–71–1070,
an address listed under the ADDRESSES providing a list of affected parts and
ADDRESSES: You may send comments, applicable corrective actions.
using the procedures found in 14 CFR section. Include ‘‘Docket No. FAA–
Consequently, EASA issued AD 2016–0010
11.43 and 11.45, by any of the following 2018–0165; Product Identifier 2017– (later revised), retaining the requirements of
methods: NM–122–AD’’ at the beginning of your EASA AD 2015–0021, which was
• Federal eRulemaking Portal: Go to comments. We specifically invite superseded, and in addition requiring the
http://www.regulations.gov. Follow the comments on the overall regulatory, identification and replacement of all non-
instructions for submitting comments. economic, environmental, and energy conforming aft engine mount inner retainers
aspects of this NPRM. We will consider [EASA AD 2016–0010 R1 corresponds to
• Fax: 202–493–2251. FAA AD 2017–04–10, Amendment 39–18805
• Mail: U.S. Department of all comments received by the closing
date and may amend this NPRM based (82 FR 11791, February 27, 2017) (‘‘AD 2017–
Transportation, Docket Operations, 04–10’’)].
M–30, West Building Ground Floor, on those comments.
After that [EASA] AD was issued, a new
Room W12–140, 1200 New Jersey We will post all comments we engine mount retainer was developed by
Avenue SE, Washington, DC 20590. receive, without change, to http:// Goodrich Aerostructures to improve the
• Hand Delivery: Deliver to Mail www.regulations.gov, including any retainer efficiency. For retrofit purposes,
address above between 9 a.m. and 5 personal information you provide. We Goodrich Aerostructures issued SB
p.m., Monday through Friday, except will also post a report summarizing each RA32071–164, and Airbus issued SB A320–
Federal holidays. substantive verbal contact we receive 71–1071, providing instructions to modify
about this NPRM. and re-identify the engine mount assemblies
For Airbus service information as instructed in the Goodrich Aerostructures
identified in this NPRM, contact Airbus, Discussion SB. Subsequently, it was observed that, on
Airworthiness Office—EIAS, 1 Rond aeroplanes equipped with certain engines
The European Aviation Safety Agency
Point Maurice Bellonte, 31707 Blagnac fitted with a Turbine Rear Frame (TRF) with
(EASA), which is the Technical Agent
Cedex, France; telephone +33 5 61 93 36 4 lugs configuration, the installation of the
for the Member States of the European new engine mount retainers can lead to
96; fax +33 5 61 93 44 51; email
Union, has issued EASA Airworthiness interference, and Goodrich Aerostructures
account.airworth-eas@airbus.com;
Directive 2017–0251, dated December revised SB RA32071–164, providing
internet http://www.airbus.com.
15, 2017 (referred to after this as the instructions not to install the new engine
For Goodrich Aerospace service
Mandatory Continuing Airworthiness retainers on affected engines. Airbus SB
information identified in this NPRM, A320–71–1071 is expected to be revised
Information, or ‘‘the MCAI’’), to correct
contact Goodrich Corporation, accordingly. For engines fitted with a TRF
an unsafe condition for all Airbus
Aerostructures, 850 Lagoon Drive, Chula with 4 lugs, a new installation (potentially
Model A318–111 and –112 airplanes,
Vista, CA 91910–2098; phone: 619–691– requiring different engine mount retainers) is
Model A319–111, –112, –113, –114, and
2719; email: jan.lewis@goodrich.com; being developed by Goodrich Aerospace and
–115 airplanes, Model A320–211, –212, Airbus.
internet: http://www.goodrich.com/
–214, and –216 airplanes, and Model Consequently, EASA issued AD 2017–
TechPubs.
A321–111, –112, –211, –212, and –213 0138, retaining the requirements of EASA AD
You may view this service
airplanes. The MCAI states: 2016–0010R1, which was superseded, and,
information at the FAA, Transport
During in-service inspections, several aft except for aeroplanes equipped with engines
Standards Branch, 2200 South 216th St., fitted with a TRF with 4 lugs configuration,
Des Moines, WA. For information on the engine mount inner retainers, fitted on
aeroplanes equipped with CFM56–5A/5B requiring modification and identification of
availability of this material at the FAA, aft engine mount assemblies as terminating
engines, were found broken. Investigation
call 206–231–3195. identified that the main cause of crack action for the repetitive inspections of the
initiation was the vibration dynamic effect retainers. That [EASA] AD also included
Examining the AD Docket additional instructions applicable to
that affects the retainers, and that the ‘‘dull’’
You may examine the AD docket on surface finish pitting is an aggravating factor installation of engines fitted with a TRF with
the internet at http:// when compared with the ‘‘bright’’ surface 4 lugs configuration.
www.regulations.gov by searching for finishing. Since EASA AD 2017–0138 was issued, it
and locating Docket No. FAA–2018– This condition, if not detected and was determined that installation of new
corrected, could lead to in-flight loss of an aft engine mount assemblies must not be
0165; or in person at the Docket
engine mount link, possibly resulting in allowed for some specific engine
Management Facility between 9 a.m. configurations, and that installation of
damage to the aeroplane and/or injury to
and 5 p.m., Monday through Friday, persons on the ground. Goodrich Aerostructures SB RA32071–164
except Federal holidays. The AD docket To address this potential unsafe condition, alone can be referred to, in order to
contains this NPRM, the regulatory Airbus issued Alert Operators Transmission accomplish the terminating action as
evaluation, any comments received, and required by that [EASA] AD.
amozie on DSK30RV082PROD with PROPOSALS
(AOT) A71N001–12 (later revised) and EASA
other information. The street address for issued AD 2013–0050 [which corresponds to For the reason described above, this
the Docket Operations office (telephone FAA AD 2014–14–06, Amendment 39–17901 [EASA] AD retains the requirements of EASA
800–647–5527) is in the ADDRESSES (79 FR 42655, July 23, 2014)], later AD 2017–0138, which is superseded, adds
superseded by EASA AD 2015–0021 [which reference to Goodrich Aerostructures SB
section. Comments will be available in
corresponds to FAA AD 2016–14–09, RA32071–164 * * *, and introduces new
the AD docket shortly after receipt. Amendment 39–18590 (81 FR 44989, July 12, requirement for aeroplanes equipped with
FOR FURTHER INFORMATION CONTACT: 2016) (‘‘AD 2016–14–09’’)], requiring engines fitted with a TRF with 4 lugs
Sanjay Ralhan, Aerospace Engineer, repetitive detailed inspections (DET) of all aft configuration.
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![Federal Register / Vol. 83, No. 47 / Friday, March 9, 2018 / Proposed Rules 10413
This NPRM would not supersede AD Related Service Information Under 1 FAA’s Determination and Requirements
2017–04–10. Rather, we have CFR Part 51 of This Proposed AD
determined that a stand-alone AD This product has been approved by
would be more appropriate to address Airbus has issued Service Bulletin
A320–71–1071, dated November 8, the aviation authority of another
the changes in the MCAI. This NPRM country, and is approved for operation
would require modifying and re- 2016. Goodrich Aerostructures has
in the United States. Pursuant to our
identifying the aft engine mount issued Service Bulletin RA32071–164,
bilateral agreement with the State of
assemblies. Accomplishment of the Revision 1, dated July 19, 2017. The
Design Authority, we have been notified
proposed actions would then terminate service information describes of the unsafe condition described in the
the repetitive detailed inspections procedures for modifying and re- MCAI and service information
required by paragraph (l) of AD 2016– identifying the aft engine mount retainer referenced above. We are proposing this
14–09, and serve as a method of assembly. These documents are distinct AD because we evaluated all pertinent
compliance for the requirements of since they apply to different airplane information and determined an unsafe
paragraph (g) of AD 2017–04–10. You models in different configurations. condition exists and is likely to exist or
may examine the MCAI in the AD This service information is reasonably develop on other products of these same
docket on the internet at http:// available because the interested parties type designs.
www.regulations.gov by searching for have access to it through their normal Costs of Compliance
and locating Docket No. FAA–2018– course of business or by the means
0165. identified in the ADDRESSES section. We estimate that this proposed AD
affects 500 airplanes of U.S. registry.
We estimate the following costs to
comply with this proposed AD:
ESTIMATED COSTS
Cost per Cost on U.S.
Action Labor cost Parts cost product operators
Modification and re-identification .................... 20 work-hours × $85 per hour = $1,700 ........ $3,152 $4,852 $2,426,000
Authority for This Rulemaking Regulatory Findings PART 39—AIRWORTHINESS
Title 49 of the United States Code DIRECTIVES
We determined that this proposed AD
specifies the FAA’s authority to issue would not have federalism implications ■ 1. The authority citation for part 39
rules on aviation safety. Subtitle I, under Executive Order 13132. This continues to read as follows:
section 106, describes the authority of proposed AD would not have a
the FAA Administrator. ‘‘Subtitle VII: Authority: 49 U.S.C. 106(g), 40113, 44701.
substantial direct effect on the States, on
Aviation Programs,’’ describes in more the relationship between the national § 39.13 [Amended]
detail the scope of the Agency’s Government and the States, or on the ■ 2. The FAA amends § 39.13 by adding
authority. distribution of power and the following new airworthiness
We are issuing this rulemaking under responsibilities among the various directive (AD):
the authority described in ‘‘Subtitle VII, levels of government.
Part A, Subpart III, Section 44701: Airbus: Docket No. FAA–2018–0165; Product
For the reasons discussed above, I Identifier 2017–NM–122–AD.
General requirements.’’ Under that certify this proposed regulation:
section, Congress charges the FAA with (a) Comments Due Date
1. Is not a ‘‘significant regulatory
promoting safe flight of civil aircraft in We must receive comments by April 23,
action’’ under Executive Order 12866;
air commerce by prescribing regulations 2018.
for practices, methods, and procedures 2. Is not a ‘‘significant rule’’ under the
DOT Regulatory Policies and Procedures (b) Affected ADs
the Administrator finds necessary for
safety in air commerce. This regulation (44 FR 11034, February 26, 1979); This AD affects AD 2016–14–09,
3. Will not affect intrastate aviation in Amendment 39–18590 (81 FR 44989, July 12,
is within the scope of that authority 2016) (‘‘AD 2016–14–09’’); and AD 2017–04–
because it addresses an unsafe condition Alaska; and
10, Amendment 39–18805 (82 FR 11791,
that is likely to exist or develop on 4. Will not have a significant February 27, 2017) (‘‘AD 2017–04–10’’).
products identified in this rulemaking economic impact, positive or negative,
(c) Applicability
action. on a substantial number of small entities
This proposed AD is issued in under the criteria of the Regulatory This AD applies to the Airbus airplanes
Flexibility Act. identified in paragraphs (c)(1) through (c)(4)
accordance with authority delegated by of this AD, certificated in any category, all
the Executive Director, Aircraft List of Subjects in 14 CFR Part 39 manufacturer serial numbers.
Certification Service, as authorized by (1) Model A318–111 and –112 airplanes.
FAA Order 8000.51C. In accordance Air transportation, Aircraft, Aviation (2) Model A319–111, –112, –113, –114, and
amozie on DSK30RV082PROD with PROPOSALS
with that order, issuance of ADs is safety, Incorporation by reference, –115 airplanes.
normally a function of the Compliance Safety. (3) Model A320–211, –212, –214, and –216
and Airworthiness Division, but during airplanes.
The Proposed Amendment (4) Model A321–111, –112, –211, –212, and
this transition period, the Executive
–213 airplanes.
Director has delegated the authority to Accordingly, under the authority
issue ADs applicable to transport delegated to me by the Administrator, (d) Subject
category airplanes to the Director of the the FAA proposes to amend 14 CFR part Air Transport Association (ATA) of
System Oversight Division. 39 as follows: America Code 71, Powerplant.
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![Federal Register / Vol. 83, No. 47 / Friday, March 9, 2018 / Proposed Rules 10415
with this AD; any procedures or tests that are DEPARTMENT OF TRANSPORTATION Branch, 2200 South 216th St., Des
not identified as RC are recommended. Those Moines, WA. For information on the
procedures and tests that are not identified Federal Aviation Administration availability of this material at the FAA,
as RC may be deviated from using accepted call 206–231–3195.
methods in accordance with the operator’s 14 CFR Part 39
maintenance or inspection program without Examining the AD Docket
[Docket No. FAA–2018–0161; Product
obtaining approval of an AMOC, provided You may examine the AD docket on
Identifier 2017–NM–088–AD]
the procedures and tests identified as RC can the internet at http://
be done and the airplane can be put back in RIN 2120–AA64 www.regulations.gov by searching for
an airworthy condition. Any substitutions or and locating Docket No. FAA–2018–
changes to procedures or tests identified as Airworthiness Directives; Bombardier, 0161; or in person at the Docket
RC require approval of an AMOC. Inc., Airplanes Management Facility between 9 a.m.
AGENCY: Federal Aviation and 5 p.m., Monday through Friday,
(o) Special Flight Permits
Administration (FAA), DOT. except Federal holidays. The AD docket
Special flight permits, as described in contains this proposed AD, the
Section 21.197 and Section 21.199 of the ACTION: Notice of proposed rulemaking
regulatory evaluation, any comments
Federal Aviation Regulations (14 CFR 21.197 (NPRM). received, and other information. The
and 21.199), are not allowed. street address for the Docket Operations
SUMMARY: We propose to supersede
(p) Related Information Airworthiness Directive (AD) 2013–11– office (telephone 800–647–5527) is in
12, which applies to certain the ADDRESSES section. Comments will
(1) Refer to Mandatory Continuing
Bombardier, Inc., Model BD–100–1A10 be available in the AD docket shortly
Airworthiness Information (MCAI) EASA
airplanes. AD 2013–11–12 requires after receipt.
Airworthiness Directive 2017–0251 dated
December 15, 2017, for related information. inspecting for the correct serial number FOR FURTHER INFORMATION CONTACT:
This MCAI may be found in the AD docket of a certain hydraulic system Cesar Gomez, Aerospace Engineer,
on the internet at http://www.regulations.gov accumulator, and replacing affected Airframe and Mechanical Systems
by searching for and locating Docket No. hydraulic system accumulators with Section, FAA, New York ACO Branch,
FAA–2018–0165. new or serviceable accumulators. Since 1600 Stewart Avenue, Suite 410,
(2) For more information about this AD, we issued AD 2013–11–12, we have Westbury, NY 11590; telephone 516–
contact Sanjay Ralhan, Aerospace Engineer, determined that certain other hydraulic 228–7318; fax 516–794–5531.
International Section, Transport Standards system accumulators must be modified SUPPLEMENTARY INFORMATION:
Branch, FAA, 2200 South 216th St., Des or replaced and life limits must be Comments Invited
Moines, WA 98198; telephone and fax 206– added. This proposed AD would expand
231–3223. the applicability and require modifying We invite you to send any written
(3) For Airbus service information or replacing certain hydraulic brake relevant data, views, or arguments about
identified in this AD, contact Airbus, system accumulators. This proposed AD this proposal. Send your comments to
Airworthiness Office—EIAS, 1 Rond Point would also require revising the an address listed under the ADDRESSES
Maurice Bellonte, 31707 Blagnac Cedex, maintenance or inspection program to section. Include ‘‘Docket No. FAA–
France; telephone +33 5 61 93 36 96; fax +33 add life limits for the accumulators. We 2018–0161; Product Identifier 2017–
5 61 93 44 51; email account.airworth-eas@ are proposing this AD to address the NM–088–AD’’ at the beginning of your
airbus.com; internet http://www.airbus.com. unsafe condition on these products. comments. We specifically invite
(4) For Goodrich Aerospace service comments on the overall regulatory,
DATES: We must receive comments on
information identified in this AD, contact economic, environmental, and energy
this proposed AD by April 23, 2018. aspects of this proposed AD. We will
Goodrich Corporation, Aerostructures, 850
Lagoon Drive, Chula Vista, CA 91910–2098; ADDRESSES: You may send comments, consider all comments received by the
phone: 619–691–2719; email: jan.lewis@ using the procedures found in 14 CFR closing date and may amend this
goodrich.com; internet: http:// 11.43 and 11.45, by any of the following proposed AD based on those comments.
www.goodrich.com/TechPubs. You may view methods: We will post all comments we
this service information at the FAA, • Federal eRulemaking Portal: Go to receive, without change, to http://
Transport Standards Branch, 2200 South http://www.regulations.gov. Follow the www.regulations.gov, including any
216th St., Des Moines, WA. For information instructions for submitting comments. personal information you provide. We
on the availability of this material at the • Fax: 202–493–2251. will also post a report summarizing each
FAA, call 206–231–3195. • Mail: U.S. Department of substantive verbal contact we receive
Transportation, Docket Operations, M– about this proposed AD.
Issued in Renton, Washington, on March 5, 30, West Building Ground Floor, Room
2018. W12–140, 1200 New Jersey Avenue SE, Discussion
Michael Kaszycki, Washington, DC 20590. We issued AD 2013–11–12,
Acting Director, System Oversight Division, • Hand Delivery: Deliver to Mail Amendment 39–17472 (78 FR 33206,
Aircraft Certification Service. address above between 9 a.m. and 5 June 4, 2013) (‘‘AD 2013–11–12’’), for
[FR Doc. 2018–04727 Filed 3–8–18; 8:45 am] p.m., Monday through Friday, except certain Bombardier, Inc., Model BD–
BILLING CODE 4910–13–P Federal holidays. 100–1A10 airplanes. AD 2013–11–12
For service information identified in requires inspecting for the correct serial
amozie on DSK30RV082PROD with PROPOSALS
this NPRM, contact Bombardier, Inc., number of a certain hydraulic system
400 Côte-Vertu Road West, Dorval, accumulator, and replacing affected
Québec H4S 1Y9, Canada; telephone hydraulic system accumulators with
514–855–5000; fax 514–855–7401; email new or serviceable accumulators. AD
thd.crj@aero.bombardier.com; internet 2013–11–12 resulted from reports of
http://www.bombardier.com. You may failure of a screw cap or end cap of the
view this referenced service information hydraulic system accumulator while on
at the FAA, Transport Standards the ground, which resulted in loss of
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Document Created: 2018-03-09 03:48:47
Document Modified: 2018-03-09 03:48:47
| Category | Regulatory Information | |
| Collection | Federal Register | |
| sudoc Class | AE 2.7: GS 4.107: AE 2.106: | |
| Publisher | Office of the Federal Register, National Archives and Records Administration | |
| Section | Proposed Rules | |
| Action | Notice of proposed rulemaking (NPRM). | |
| Dates | We must receive comments on this proposed AD by April 23, 2018. | |
| 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. | |
| FR Citation | 83 FR 10411 | |
| RIN Number | 2120-AA64 | |
| CFR Associated | Air Transportation; Aircraft; Aviation Safety; Incorporation by Reference and Safety |
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