82 FR 49146 - Airworthiness Directives; Airbus Airplanes
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration Federal Register Volume 82, Issue 204 (October 24, 2017)
Federal Aviation Administration
Federal Register Volume 82, Issue 204 (October 24, 2017)
| Page Range | 49146-49149 | |
| FR Document | 2017-23014 |
[Federal Register Volume 82, Number 204 (Tuesday, October 24, 2017)] [Proposed Rules] [Pages 49146-49149] From the Federal Register Online [www.thefederalregister.org] [FR Doc No: 2017-23014] ----------------------------------------------------------------------- DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA-2017-1020; Product Identifier 2017-NM-114-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 review of maintenance instructions for a blend repair of the snout diameter of the main beam assembly of the forward engine mount that would create an excessive gap between the bearing mono-ball and the snout. This proposed AD would require modifying the main beam assembly of the forward engine mount. We are proposing this AD to address the unsafe condition on these products. DATES: We must receive comments on this proposed AD by December 8, 2017. 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 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. You may view this service information at the FAA, Transport Standards Branch, 1601 Lind Avenue SW., Renton, WA. For information on the availability of this material at the FAA, call 425- 227-1221. 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-2017- 1020; 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, 1601 Lind Avenue SW., Renton, WA 98057-3356; telephone 425-227-1405; fax 425-227- 1149. 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-2017-1020; Product Identifier 2017-NM-114-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 AD 2017-0132, dated July 27, 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, [[Page 49147]] -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: A review of maintenance instructions revealed that the Goodrich Aerospace CFM56-5B, Forward Engine Mount Component Maintenance Manual (CMM) 71-21-08, revision (rev.) 1 up to 46 (inclusive), repair 10 (Blend Repair-Beam Assembly Snout Diameter), provides instructions to blend the wear on the forward engine mount assembly, Part Number (P/N) 642-2000-9, 642-2000-13, or 642-2000-25, creating an excessive gap between the bearing mono-ball and the snout of the forward engine mount main beam assembly, P/N 642-2006-501, or P/N 642-2006-503. This condition, if not detected and corrected, could lead to in- flight failure of a forward engine mount and consequent detachment of an engine, possibly resulting in reduced control of the aeroplane and injury to persons on the ground. To address this potential unsafe condition, Airbus issued Service Bulletin (SB) A320-71-1065 and SB A320-71-1066, and Goodrich Aerospace issued SB RA32071-159, providing instructions for an in- shop inspection(s) for the main beam snout and, depending on findings, applicable corrective action(s) and re-identification. For the reason described above, this [EASA] AD requires replacement of the affected forward engine mount main beam assemblies. As the same main beam assemblies are certified for CFM56-5A engine installation, this [EASA] AD also applies to aeroplanes with that engine. Required actions include modifying the main beam assembly of the forward engine mount. The modification includes repairing, replacing, or reworking the main beam assembly. 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-2017-1020. Related Service Information Under 1 CFR Part 51 Airbus has issued Service Bulletin A320-71-1065, Revision 01, dated July 28, 2017. This service information describes procedures for modifying the main beam assembly of the forward engine mount. The modification includes, among other things, repair or replacement of the main beam assembly. Airbus has also issued Service Bulletin A320-71-1066, dated December 1, 2016. This service information describes procedures for modifying the main beam assembly of the forward engine mount. The modification includes, among other things, rework of the main beam assembly. 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 on U.S. Action Labor cost Parts cost Cost per product operators ---------------------------------------------------------------------------------------------------------------- Modification..................... Up to 76 work-hours $778 Up to $7,238....... Up to $3,619,000. x $85 per hour = $6,460. ---------------------------------------------------------------------------------------------------------------- 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. [[Page 49148]] Sec. 39.13 [Amended] 0 2. The FAA amends Sec. 39.13 by adding the following new airworthiness directive (AD): Airbus: Docket No. FAA-2017-1020; Product Identifier 2017-NM-114-AD. (a) Comments Due Date We must receive comments by December 8, 2017. (b) Affected ADs None. (c) Applicability This AD applies to 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; certificated in any category. (d) Subject Air Transport Association (ATA) of America Code 71, Powerplant. (e) Reason This AD was prompted by a review of maintenance instructions for a blend repair of the diameter of the snout of the main beam assembly of the forward engine mount that would create an excessive gap between the bearing mono-ball and the snout. We are issuing this AD to prevent in-flight failure of a forward engine mount, and consequent detachment of an engine, which could result in reduced controllability of the airplane. (f) Compliance Comply with this AD within the compliance times specified, unless already done. (g) Definition of Affected Parts For the purposes of this AD: An ``affected main beam'' is any main beam assembly of the forward engine mount, part number (P/N) 642-2006-501 or P/N 642-2006-503, identified in paragraph (g)(1) or (g)(2) of this AD. (1) Any part for which no maintenance records are available to confirm the part has never been repaired. (2) Any part that was repaired as specified in the instructions of Goodrich Aerospace component maintenance manual (CMM) 71-21-08, Revision 1 through 46, repair 10, except for parts identified in paragraphs (g)(2)(i), (g)(2)(ii), and (g)(2)(iii) of this AD. (i) Any part on which a qualifying inspection identified in paragraph (h) of this AD has been done and there were no findings (the inspection was passed). (ii) Any part on which a qualifying inspection identified in paragraph (h) of this AD has been done and that part has been repaired as specified in the instructions of Goodrich Aerospace Service Bulletin RA32071-159. (iii) Any part that has been repaired in accordance with other instructions 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). (h) Definition of Qualifying Inspection For the purposes of this AD: ``A qualifying inspection'' is an inspection done as specified in the instructions of Goodrich Aerospace Service Bulletin RA32071-159; or for CFM56-5B engines, an inspection done as specified in the instructions of Goodrich Aerospace CMM 71-21-08, Revision 47, repair 10; or for CFM56-5A engines, an inspection done as specified in the instructions of Goodrich Aerospace CMM 71-21-06, Revision 59, repair 21. (i) Definition of Airplane Groups For the purposes of this AD: ``Group 1 airplanes'' are airplanes on which an affected main beam has been installed as of the effective date of this AD. ``Group 2 airplanes'' are airplanes on which an affected main beam has not been installed as of the effective date of this AD; this includes airplanes with an original certificate of airworthiness or original export certificate of airworthiness that was issued after the effective date of this AD. (j) Modification of Affected Main Beam Assemblies For Group 1 airplanes as identified in paragraph (i) of this AD: At the earliest of the compliance times specified in paragraphs (j)(1), (j)(2), and (j)(3) of this AD, modify each affected main beam identified in paragraph (g) of this AD, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A320-71-1065, Revision 01, dated July 28, 2017; and Airbus Service Bulletin A320- 71-1066, dated December 1, 2016; as applicable, except as required by paragraph (k) of this AD. (1) Within 48 months after the effective date of this AD. (2) Within 10,000 flight cycles after the effective date of this AD. (3) Within 15,000 flight hours after the effective date of this AD. (k) Exception to Service Information Where Airbus Service Bulletin A320-71-1065, Revision 01, dated July 28, 2017, specifies to contact a manufacturer for appropriate action, and specifies that action as ``RC'' (Required for Compliance): Before further flight, accomplish corrective actions in accordance with the procedures specified in paragraph (n)(2) of this AD. (l) Credit for Previous Actions This paragraph provides credit for the actions required by paragraph (j) of this AD involving Airbus Service Bulletin A320-71- 1065, Revision 01, dated July 28, 2017, if those actions were performed before the effective date of this AD using Airbus Service Bulletin A320-71-1065, dated December 1, 2016. (m) Parts Installation Prohibition As of the effective date of this AD, no person may install an affected main beam identified in paragraph (g) of this AD or a forward engine mount assembly equipped with an affected main beam identified in paragraph (g) of this AD, on any 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 manager of the International Section, send it to the attention of the person identified in paragraph (o)(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): Except as required by paragraph (k) of this AD: If any service information contains procedures or tests that are identified as RC, those procedures and tests must be done to comply with this AD; any procedures or tests that are not identified as RC are recommended. Those procedures and tests that are not identified as RC may be deviated from using accepted methods in accordance with the operator's maintenance or inspection program without obtaining approval of an AMOC, provided the procedures and tests identified as RC can be done and the airplane can be put back in an airworthy condition. Any substitutions or changes to procedures or tests identified as RC require approval of an AMOC. (o) Related Information (1) Refer to Mandatory Continuing Airworthiness Information (MCAI) EASA AD 2017-0132, dated July 27, 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-2017-1020. (2) For more information about this AD, contact Sanjay Ralhan, Aerospace Engineer, International Section, Transport Standards Branch, FAA, 1601 Lind Avenue SW., Renton, WA 98057-3356; telephone 425-227-1405; fax 425-227-1149. (3) For 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. You may view this service information at the FAA, Transport Standards Branch, 1601 Lind Avenue SW., Renton, WA. For information on the availability of this material at the FAA, call 425-227-1221. [[Page 49149]] Issued in Renton, Washington, on October 17, 2017. Jeffrey E. Duven, Director, System Oversight Division, Aircraft Certification Service. [FR Doc. 2017-23014 Filed 10-23-17; 8:45 am] BILLING CODE 4910-13-P
![49146 Federal Register / Vol. 82, No. 204 / Tuesday, October 24, 2017 / Proposed Rules
Bulletin 32–JA981042 Rev 9, dated July 11, Issued in Kansas City, Missouri, on Cedex, France; telephone: +33 5 61 93
2017. October 12, 2017. 36 96; fax: +33 5 61 93 44 51; email:
(3) For all affected airplane models: Before Melvin J. Johnson, account.airworth-eas@airbus.com;
further flight after the effective date of this Internet: http://www.airbus.com. You
Acting Deputy Director, Policy & Innovation
AD, revise the FAA-approved maintenance
program (instructions for continued
Division, Aircraft Certification Service. may view this service information at the
airworthiness) on the basis of which the [FR Doc. 2017–22708 Filed 10–23–17; 8:45 am] FAA, Transport Standards Branch, 1601
operator or the owner ensures the continuing BILLING CODE 4910–13–P Lind Avenue SW., Renton, WA. For
airworthiness of each operated airplane, as information on the availability of this
applicable to the airplane model, by material at the FAA, call 425–227–1221.
incorporating the limitations described in DEPARTMENT OF TRANSPORTATION
BAE Systems British Aerospace Jetstream
Examining the AD Docket
Series 3100 and 3200 Service Bulletin 32– Federal Aviation Administration You may examine the AD docket on
JA981042 Rev 9, dated July 11, 2017, as the Internet at http://
applicable to the airplane model and 14 CFR Part 39 www.regulations.gov by searching for
depending on the airplane configuration. and locating Docket No. FAA–2017–
(4) For all airplanes: The compliance times [Docket No. FAA–2017–1020; Product
Identifier 2017–NM–114–AD] 1020; or in person at the Docket
in paragraphs (f)(1) and (2) of this AD are
presented in flight cycles (landings). If the
Management Facility between 9 a.m.
RIN 2120–AA64 and 5 p.m., Monday through Friday,
total flight cycles have not been kept,
multiply the total number of airplane hours except Federal holidays. The AD docket
Airworthiness Directives; Airbus contains this NPRM, the regulatory
time-in-service (TIS) by 0.75 to calculate the
cycles. For the purposes of this AD: Airplanes evaluation, any comments received, and
(i) 100 hours TIS × .75 = 75 cycles; and AGENCY: Federal Aviation other information. The street address for
(ii) 1,000 hours TIS × .75 = 750 cycles. Administration (FAA), DOT. the Docket Operations office (telephone
(g) Other FAA AD Provisions 800–647–5527) is in the ADDRESSES
ACTION: Notice of proposed rulemaking
section. Comments will be available in
The following provisions also apply to this (NPRM).
AD:
the AD docket shortly after receipt.
(1) Alternative Methods of Compliance SUMMARY: We propose to adopt a new FOR FURTHER INFORMATION CONTACT:
(AMOCs): The Manager, Small Airplane airworthiness directive (AD) for all Sanjay Ralhan, Aerospace Engineer,
Standards Branch, FAA, has the authority to Airbus Model A318–111 and –112 International Section, Transport
approve AMOCs for this AD, if requested airplanes; Model A319–111, –112, –113, Standards Branch, FAA, 1601 Lind
using the procedures found in 14 CFR 39.19. –114, and –115 airplanes; Model A320– Avenue SW., Renton, WA 98057–3356;
Send information to ATTN: Doug Rudolph, telephone 425–227–1405; fax 425–227–
211, –212, –214, and –216 airplanes;
Aerospace Engineer, FAA, Small Airplane 1149.
Standards Branch, 901 Locust, Room 301, and Model A321–111, –112, –211, –212,
Kansas City, Missouri 64106; telephone: and –213 airplanes. This proposed AD SUPPLEMENTARY INFORMATION:
(816) 329–4059; fax: (816) 329–4090; email: was prompted by a review of Comments Invited
doug.rudolph@faa.gov. Before using any maintenance instructions for a blend
approved AMOC on any airplane to which repair of the snout diameter of the main We invite you to send any written
the AMOC applies, notify your appropriate beam assembly of the forward engine relevant data, views, or arguments about
principal inspector (PI) in the FAA Flight mount that would create an excessive this proposal. Send your comments to
Standards District Office (FSDO), or lacking gap between the bearing mono-ball and an address listed under the ADDRESSES
a PI, your local FSDO. section. Include ‘‘Docket No. FAA–
the snout. This proposed AD would
(2) Contacting the Manufacturer: For any 2017–1020; Product Identifier 2017–
requirement in this AD to obtain corrective require modifying the main beam
assembly of the forward engine mount. NM–114–AD’’ at the beginning of your
actions from a manufacturer, the action must comments. We specifically invite
be accomplished using a method approved We are proposing this AD to address the
by the Manager, Small Airplane Standards unsafe condition on these products. comments on the overall regulatory,
Branch, FAA; or the European Aviation economic, environmental, and energy
DATES: We must receive comments on
Safety Agency (EASA). aspects of this NPRM. We will consider
this proposed AD by December 8, 2017.
all comments received by the closing
(h) Related Information ADDRESSES: You may send comments, date and may amend this NPRM based
(1) Refer to MCAI EASA AD 2017–0157, using the procedures found in 14 CFR on those comments.
dated August 25, 2017, and BAE Systems 11.43 and 11.45, by any of the following We will post all comments we
British Aerospace Jetstream Series 3100 and methods: receive, without change, to http://
3200 Service Bulletin 32–JA981042 Rev 9, • Federal eRulemaking Portal: Go to www.regulations.gov, including any
dated July 11, 2017, for related information. http://www.regulations.gov. Follow the
You may examine the MCAI on the Internet
personal information you provide. We
instructions for submitting comments. will also post a report summarizing each
at http://www.regulations.gov by searching
for and locating Docket No. FAA–2017–0993.
• Fax: 202–493–2251. substantive verbal contact we receive
For service information related to this AD, • Mail: U.S. Department of about this NPRM.
contact BAE Systems (Operations) Limited, Transportation, Docket Operations,
Customer Information Department, Prestwick M–30, West Building Ground Floor, Discussion
International Airport, Ayrshire, KA9 2RW, Room W12–140, 1200 New Jersey The European Aviation Safety Agency
Scotland, United Kingdom; telephone: +44 Avenue SE., Washington, DC 20590. (EASA), which is the Technical Agent
ethrower on DSK3G9T082PROD with PROPOSALS
1292 675207; fax: +44 1292 675704; email: • Hand Delivery: Deliver to Mail for the Member States of the European
RApublications@baesystems.com; Internet: address above between 9 a.m. and 5 Union, has issued EASA AD 2017–0132,
http://www.baesystems.com/Businesses/ p.m., Monday through Friday, except dated July 27, 2017 (referred to after this
RegionalAircraft/. You may review copies of
the referenced service information at the
Federal holidays. as the Mandatory Continuing
FAA, Policy and Innovation Division, 901 For service information identified in Airworthiness Information, or ‘‘the
Locust, Kansas City, Missouri 64106. For this NPRM, contact Airbus, MCAI’’), to correct an unsafe condition
information on the availability of this Airworthiness Office–EIAS, 1 Rond for all Airbus Model A318–111 and
material at the FAA, call (816) 329–4148. Point Maurice Bellonte, 31707 Blagnac –112 airplanes; Model A319–111, –112,
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![Federal Register / Vol. 82, No. 204 / Tuesday, October 24, 2017 / Proposed Rules 49147
–113, –114, and –115 airplanes; Model affected forward engine mount main beam modification includes, among other
A320–211, –212, –214, and –216 assemblies. As the same main beam things, rework of the main beam
airplanes; and Model A321–111, –112, assemblies are certified for CFM56–5A assembly.
–211, –212, and –213 airplanes. The engine installation, this [EASA] AD also
applies to aeroplanes with that engine. This service information is reasonably
MCAI states: available because the interested parties
A review of maintenance instructions Required actions include modifying have access to it through their normal
revealed that the Goodrich Aerospace the main beam assembly of the forward course of business or by the means
CFM56–5B, Forward Engine Mount engine mount. The modification identified in the ADDRESSES section.
Component Maintenance Manual (CMM) 71– includes repairing, replacing, or
21–08, revision (rev.) 1 up to 46 (inclusive), reworking the main beam assembly. You FAA’s Determination and Requirements
repair 10 (Blend Repair-Beam Assembly may examine the MCAI in the AD of This Proposed AD
Snout Diameter), provides instructions to docket on the Internet at http://
blend the wear on the forward engine mount This product has been approved by
assembly, Part Number (P/N) 642–2000–9,
www.regulations.gov by searching for
the aviation authority of another
642–2000–13, or 642–2000–25, creating an and locating Docket No. FAA–2017–
country, and is approved for operation
excessive gap between the bearing mono-ball 1020.
in the United States. Pursuant to our
and the snout of the forward engine mount
main beam assembly, P/N 642–2006–501, or
Related Service Information Under 1 bilateral agreement with the State of
P/N 642–2006–503. CFR Part 51 Design Authority, we have been notified
This condition, if not detected and Airbus has issued Service Bulletin of the unsafe condition described in the
corrected, could lead to in-flight failure of a A320–71–1065, Revision 01, dated July MCAI and service information
forward engine mount and consequent
28, 2017. This service information referenced above. We are proposing this
detachment of an engine, possibly resulting AD because we evaluated all pertinent
in reduced control of the aeroplane and describes procedures for modifying the
main beam assembly of the forward information and determined an unsafe
injury to persons on the ground. condition exists and is likely to exist or
To address this potential unsafe condition, engine mount. The modification
Airbus issued Service Bulletin (SB) A320– includes, among other things, repair or develop on other products of these same
71–1065 and SB A320–71–1066, and replacement of the main beam assembly. type designs.
Goodrich Aerospace issued SB RA32071– Airbus has also issued Service Costs of Compliance
159, providing instructions for an in-shop Bulletin A320–71–1066, dated
inspection(s) for the main beam snout and, We estimate that this proposed AD
depending on findings, applicable corrective December 1, 2016. This service
information describes procedures for affects 500 airplanes of U.S. registry.
action(s) and re-identification.
For the reason described above, this modifying the main beam assembly of We estimate the following costs to
[EASA] AD requires replacement of the the forward engine mount. The comply with this proposed AD:
ESTIMATED COSTS
Action Labor cost Parts cost Cost per product Cost on U.S. operators
Modification .................. Up to 76 work-hours × $85 per hour = $6,460 ... $778 Up to $7,238 ................ Up to $3,619,000.
Authority for This Rulemaking FAA Order 8000.51C. In accordance 3. Will not affect intrastate aviation in
with that order, issuance of ADs is Alaska; and
Title 49 of the United States Code
normally a function of the Compliance 4. Will not have a significant
specifies the FAA’s authority to issue
and Airworthiness Division, but during economic impact, positive or negative,
rules on aviation safety. Subtitle I,
this transition period, the Executive on a substantial number of small entities
section 106, describes the authority of
Director has delegated the authority to
the FAA Administrator. ‘‘Subtitle VII: under the criteria of the Regulatory
issue ADs applicable to transport
Aviation Programs,’’ describes in more Flexibility Act.
category airplanes to the Director of the
detail the scope of the Agency’s
System Oversight Division. List of Subjects in 14 CFR Part 39
authority.
We are issuing this rulemaking under Regulatory Findings Air transportation, Aircraft, Aviation
the authority described in ‘‘Subtitle VII, safety, Incorporation by reference,
We determined that this proposed AD
Part A, Subpart III, Section 44701: Safety.
would not have federalism implications
General requirements.’’ Under that
under Executive Order 13132. This The Proposed Amendment
section, Congress charges the FAA with
proposed AD would not have a
promoting safe flight of civil aircraft in
substantial direct effect on the States, on Accordingly, under the authority
air commerce by prescribing regulations
the relationship between the national delegated to me by the Administrator,
for practices, methods, and procedures
Government and the States, or on the the FAA proposes to amend 14 CFR part
the Administrator finds necessary for
distribution of power and 39 as follows:
safety in air commerce. This regulation
responsibilities among the various
is within the scope of that authority
levels of government. PART 39—AIRWORTHINESS
ethrower on DSK3G9T082PROD with PROPOSALS
because it addresses an unsafe condition
that is likely to exist or develop on For the reasons discussed above, I DIRECTIVES
products identified in this rulemaking certify this proposed regulation:
action. 1. Is not a ‘‘significant regulatory ■ 1. The authority citation for part 39
This proposed AD is issued in action’’ under Executive Order 12866; continues to read as follows:
accordance with authority delegated by 2. Is not a ‘‘significant rule’’ under the Authority: 49 U.S.C. 106(g), 40113, 44701.
the Executive Director, Aircraft DOT Regulatory Policies and Procedures
Certification Service, as authorized by (44 FR 11034, February 26, 1979);
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![49148 Federal Register / Vol. 82, No. 204 / Tuesday, October 24, 2017 / Proposed Rules
§ 39.13 [Amended] (h) Definition of Qualifying Inspection (n) Other FAA AD Provisions
■ 2. The FAA amends § 39.13 by adding For the purposes of this AD: ‘‘A qualifying The following provisions also apply to this
the following new airworthiness inspection’’ is an inspection done as AD:
directive (AD): specified in the instructions of Goodrich (1) Alternative Methods of Compliance
Aerospace Service Bulletin RA32071–159; or (AMOCs): The Manager, International
Airbus: Docket No. FAA–2017–1020; Product
for CFM56–5B engines, an inspection done as Section, Transport Standards Branch, FAA,
Identifier 2017–NM–114–AD.
specified in the instructions of Goodrich has the authority to approve AMOCs for this
(a) Comments Due Date Aerospace CMM 71–21–08, Revision 47, AD, if requested using the procedures found
We must receive comments by December 8, repair 10; or for CFM56–5A engines, an in 14 CFR 39.19. In accordance with 14 CFR
2017. inspection done as specified in the 39.19, send your request to your principal
instructions of Goodrich Aerospace CMM inspector or local Flight Standards District
(b) Affected ADs 71–21–06, Revision 59, repair 21. Office, as appropriate. If sending information
None. directly to the manager of the International
(i) Definition of Airplane Groups Section, send it to the attention of the person
(c) Applicability identified in paragraph (o)(2) of this AD.
For the purposes of this AD: ‘‘Group 1
This AD applies to all Airbus Model A318– airplanes’’ are airplanes on which an affected Information may be emailed to: 9-ANM-116-
111 and –112 airplanes; Model A319–111, main beam has been installed as of the AMOC-REQUESTS@faa.gov. Before using
–112, –113, –114, and –115 airplanes; Model effective date of this AD. ‘‘Group 2 airplanes’’ any approved AMOC, notify your appropriate
A320–211, –212, –214, and –216 airplanes; are airplanes on which an affected main principal inspector, or lacking a principal
and Model A321–111, –112, –211, –212, and beam has not been installed as of the inspector, the manager of the local flight
–213 airplanes; certificated in any category. effective date of this AD; this includes standards district office/certificate holding
(d) Subject airplanes with an original certificate of district office.
airworthiness or original export certificate of (2) Contacting the Manufacturer: For any
Air Transport Association (ATA) of requirement in this AD to obtain corrective
America Code 71, Powerplant. airworthiness that was issued after the
effective date of this AD. actions from a manufacturer, the action must
(e) Reason be accomplished using a method approved
(j) Modification of Affected Main Beam by the Manager, International Section,
This AD was prompted by a review of Assemblies Transport Standards Branch, FAA; or EASA;
maintenance instructions for a blend repair
For Group 1 airplanes as identified in or Airbus’s EASA DOA. If approved by the
of the diameter of the snout of the main beam
paragraph (i) of this AD: At the earliest of the DOA, the approval must include the DOA-
assembly of the forward engine mount that
would create an excessive gap between the compliance times specified in paragraphs authorized signature.
bearing mono-ball and the snout. We are (j)(1), (j)(2), and (j)(3) of this AD, modify each (3) Required for Compliance (RC): Except
issuing this AD to prevent in-flight failure of affected main beam identified in paragraph as required by paragraph (k) of this AD: If any
a forward engine mount, and consequent (g) of this AD, in accordance with the service information contains procedures or
detachment of an engine, which could result Accomplishment Instructions of Airbus tests that are identified as RC, those
in reduced controllability of the airplane. procedures and tests must be done to comply
Service Bulletin A320–71–1065, Revision 01,
with this AD; any procedures or tests that are
(f) Compliance dated July 28, 2017; and Airbus Service
not identified as RC are recommended. Those
Bulletin A320–71–1066, dated December 1,
Comply with this AD within the procedures and tests that are not identified
2016; as applicable, except as required by
compliance times specified, unless already as RC may be deviated from using accepted
paragraph (k) of this AD.
done. methods in accordance with the operator’s
(1) Within 48 months after the effective maintenance or inspection program without
(g) Definition of Affected Parts date of this AD. obtaining approval of an AMOC, provided
For the purposes of this AD: An ‘‘affected (2) Within 10,000 flight cycles after the the procedures and tests identified as RC can
main beam’’ is any main beam assembly of effective date of this AD. be done and the airplane can be put back in
the forward engine mount, part number (P/ (3) Within 15,000 flight hours after the an airworthy condition. Any substitutions or
N) 642–2006–501 or P/N 642–2006–503, effective date of this AD. changes to procedures or tests identified as
identified in paragraph (g)(1) or (g)(2) of this (k) Exception to Service Information RC require approval of an AMOC.
AD.
(1) Any part for which no maintenance Where Airbus Service Bulletin A320–71– (o) Related Information
records are available to confirm the part has 1065, Revision 01, dated July 28, 2017, (1) Refer to Mandatory Continuing
never been repaired. specifies to contact a manufacturer for Airworthiness Information (MCAI) EASA AD
(2) Any part that was repaired as specified appropriate action, and specifies that action 2017–0132, dated July 27, 2017, for related
in the instructions of Goodrich Aerospace as ‘‘RC’’ (Required for Compliance): Before information. This MCAI may be found in the
component maintenance manual (CMM) 71– further flight, accomplish corrective actions AD docket on the Internet at http://
21–08, Revision 1 through 46, repair 10, in accordance with the procedures specified www.regulations.gov by searching for and
except for parts identified in paragraphs in paragraph (n)(2) of this AD. locating Docket No. FAA–2017–1020.
(g)(2)(i), (g)(2)(ii), and (g)(2)(iii) of this AD. (2) For more information about this AD,
(l) Credit for Previous Actions
(i) Any part on which a qualifying contact Sanjay Ralhan, Aerospace Engineer,
inspection identified in paragraph (h) of this This paragraph provides credit for the International Section, Transport Standards
AD has been done and there were no findings actions required by paragraph (j) of this AD Branch, FAA, 1601 Lind Avenue SW.,
(the inspection was passed). involving Airbus Service Bulletin A320–71– Renton, WA 98057–3356; telephone 425–
(ii) Any part on which a qualifying 1065, Revision 01, dated July 28, 2017, if 227–1405; fax 425–227–1149.
inspection identified in paragraph (h) of this those actions were performed before the (3) For service information identified in
AD has been done and that part has been effective date of this AD using Airbus Service this AD, contact Airbus, Airworthiness
repaired as specified in the instructions of Bulletin A320–71–1065, dated December 1, Office–EIAS, 1 Rond Point Maurice Bellonte,
ethrower on DSK3G9T082PROD with PROPOSALS
Goodrich Aerospace Service Bulletin 2016. 31707 Blagnac Cedex, France; telephone: +33
RA32071–159. 5 61 93 36 96; fax: +33 5 61 93 44 51; email:
(m) Parts Installation Prohibition
(iii) Any part that has been repaired in account.airworth-eas@airbus.com; Internet:
accordance with other instructions approved As of the effective date of this AD, no http://www.airbus.com. You may view this
by the Manager, International Section, person may install an affected main beam service information at the FAA, Transport
Transport Standards Branch, FAA; or the identified in paragraph (g) of this AD or a Standards Branch, 1601 Lind Avenue SW.,
European Aviation Safety Agency (EASA); or forward engine mount assembly equipped Renton, WA. For information on the
Airbus’s EASA Design Organization with an affected main beam identified in availability of this material at the FAA, call
Approval (DOA). paragraph (g) of this AD, on any airplane. 425–227–1221.
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![Federal Register / Vol. 82, No. 204 / Tuesday, October 24, 2017 / Proposed Rules 49149
Issued in Renton, Washington, on October SW., Renton, WA. For information on tracks #6, #7 and #8 was found loose. In
17, 2017. the availability of this material at the some cases, a puncture was found in the fuel
Jeffrey E. Duven, FAA, call 425–227–1221. cap. The results of the technical
investigations concluded that the most
Director, System Oversight Division, Aircraft
Certification Service.
Examining the AD Docket probable reason for these events was
improper installation of the lock washers on
[FR Doc. 2017–23014 Filed 10–23–17; 8:45 am] You may examine the AD docket on
the screws during production or
BILLING CODE 4910–13–P
the Internet at http:// maintenance.
www.regulations.gov by searching for This condition, if not detected and
and locating Docket No. FAA–2017– corrected, could lead to structural damage to
DEPARTMENT OF TRANSPORTATION 0909; or in person at the Docket the wing front spar, and consequent fuel
Management Facility between 9 a.m. leakage, possibly resulting in an uncontrolled
Federal Aviation Administration and 5 p.m., Monday through Friday, fire.
except Federal holidays. The AD docket To address this potential unsafe condition,
14 CFR Part 39 contains this proposed AD, the Dassault issued [Service Bulletin] SB F900–
460 Revision 1, SB F900EX–508 Revision 3,
regulatory evaluation, any comments SB F2000–433 Revision 1, and SB F2000EX–
[Docket No. FAA–2017–0909; Product
Identifier 2017–NM–081–AD] received, and other information. The 386 Revision 3 (hereafter collectively referred
street address for the Docket Operations as ‘the applicable SB’ in this [EASA] AD), as
RIN 2120–AA64 office (telephone 800–647–5527) is in applicable to aeroplane type/model, to
the ADDRESSES section. Comments will provide inspection instructions.
Airworthiness Directives; Dassault be available in the AD docket shortly For the reasons described above, this
Aviation Airplanes after receipt. [EASA] AD requires a one-time [general
FOR FURTHER INFORMATION CONTACT: Tom visual] inspection of the slat tracks #6, #7
AGENCY: Federal Aviation
and #8 to verify the tightening torque of the
Administration (FAA), DOT. Rodriguez, Aerospace Engineer,
screw and proper lock washer installation
ACTION: Notice of proposed rulemaking International Section, Transport and, depending on findings, accomplishment
(NPRM). Standards Branch, FAA, 1601 Lind of applicable corrective action(s).
Avenue SW., Renton, WA 98057–3356;
SUMMARY: We propose to adopt a new telephone 425–227–1137; fax 425–227– Applicable corrective actions include
airworthiness directive (AD) for certain 1149. replacement, if necessary. You may
Dassault Aviation Model MYSTERE– examine the MCAI in the AD docket on
SUPPLEMENTARY INFORMATION:
FALCON 900, FALCON 900EX, the Internet at http://
Comments Invited www.regulations.gov by searching for
FALCON 2000, and FALCON 2000EX
airplanes. This proposed AD was We invite you to send any written and locating Docket No. FAA–2017–
prompted by reports of a loose screw on relevant data, views, or arguments about 0909.
certain slat mechanical stop assemblies, this proposal. Send your comments to Related Service Information Under 1
and punctures in certain fuel caps. This an address listed under the ADDRESSES CFR Part 51
proposed AD would require a one-time section. Include ‘‘Docket No. FAA–
2017–0909; Product Identifier 2017– Dassault Aviation has issued the
inspection, and corrective action if following service information.
necessary. We are proposing this AD to NM–081–AD’’ at the beginning of your
address the unsafe condition on these comments. We specifically invite • Dassault Service Bulletin F900–460,
products. comments on the overall regulatory, Revision 1, dated February 10, 2017
economic, environmental, and energy • Dassault Service Bulletin F900EX–
DATES: We must receive comments on aspects of this proposed AD. We will 508, Revision 3, dated February 10,
this proposed AD by December 8, 2017. consider all comments received by the 2017
ADDRESSES: You may send comments, closing date and may amend this • Dassault Service Bulletin F2000–433,
using the procedures found in 14 CFR proposed AD based on those comments. Revision 1, dated February 10, 2017
11.43 and 11.45, by any of the following We will post all comments we • Dassault Service Bulletin F2000EX–
methods: receive, without change, to http:// 386, Revision 3, dated February 10,
• Federal eRulemaking Portal: Go to www.regulations.gov, including any 2017
http://www.regulations.gov. Follow the personal information you provide. We This service information describes
instructions for submitting comments. will also post a report summarizing each procedures for doing a one-time general
• Fax: 202–493–2251. substantive verbal contact we receive visual inspection of the screw on the
• Mail: U.S. Department of about this proposed AD. affected slat tracks, and replacement if
Transportation, Docket Operations, necessary. These documents are distinct
M–30, West Building Ground Floor, Discussion
since they apply to different airplane
Room W12–140, 1200 New Jersey The European Aviation Safety Agency models. The service information is
Avenue SE., Washington, DC 20590. (EASA), which is the Technical Agent reasonably available because the
• Hand Delivery: Deliver to Mail for the Member States of the European interested parties have access to it
address above between 9 a.m. and 5 Union, has issued EASA Airworthiness through their normal course of business
p.m., Monday through Friday, except Directive 2017–0106, dated June 19, or by the means identified in the
Federal holidays. 2017 (referred to after this as the ADDRESSES section.
For service information identified in Mandatory Continuing Airworthiness
ethrower on DSK3G9T082PROD with PROPOSALS
this NPRM, contact Dassault Falcon Jet Information, or ‘‘the MCAI’’), to correct FAA’s Determination and Requirements
Corporation, Teterboro Airport, P.O. an unsafe condition for certain Dassault of This Proposed AD
Box 2000, South Hackensack, NJ 07606; Aviation Model MYSTERE–FALCON This product has been approved by
telephone 201–440–6700; Internet 900, FALCON 900EX, FALCON 2000, the aviation authority of another
http://www.dassaultfalcon.com. You and FALCON 2000EX airplanes. The country, and is approved for operation
may view this referenced service MCAI states: in the United States. Pursuant to our
information at the FAA, Transport On some aeroplanes in-service, the screw bilateral agreement with the State of
Standards Branch, 1601 Lind Avenue of the slat mechanical stop assembly on slat Design Authority, we have been notified
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Document Created: 2018-10-25 10:09:17
Document Modified: 2018-10-25 10:09:17
| 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 December 8, 2017. | |
| Contact | Sanjay Ralhan, Aerospace Engineer, International Section, Transport Standards Branch, FAA, 1601 Lind Avenue SW., Renton, WA 98057-3356; telephone 425-227-1405; fax 425-227- 1149. | |
| FR Citation | 82 FR 49146 | |
| RIN Number | 2120-AA64 | |
| CFR Associated | Air Transportation; Aircraft; Aviation Safety; Incorporation by Reference and Safety |
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