81 FR 3346 - Airworthiness Directives; Airbus Airplanes
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration Federal Register Volume 81, Issue 13 (January 21, 2016)
Federal Aviation Administration
Federal Register Volume 81, Issue 13 (January 21, 2016)
| Page Range | 3346-3348 | |
| FR Document | 2016-00944 |
[Federal Register Volume 81, Number 13 (Thursday, January 21, 2016)] [Proposed Rules] [Pages 3346-3348] From the Federal Register Online [www.thefederalregister.org] [FR Doc No: 2016-00944] ----------------------------------------------------------------------- DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA-2016-0459; Directorate Identifier 2015-NM-081-AD] RIN 2120-AA64 Airworthiness Directives; Airbus Airplanes AGENCY: Federal Aviation Administration (FAA), DOT. ACTION: Notice of proposed rulemaking (NPRM). ----------------------------------------------------------------------- SUMMARY: We propose to supersede Airworthiness Directive (AD) 2015-10- 03, for certain Airbus Model A330-200 and -300 series airplanes, and Model A340-200 and -300 series airplanes. AD 2015-10-03 currently requires a detailed inspection for visible chrome of each affected main landing gear (MLG) sidestay upper cardan pin, associated nuts, and retainer assembly; pin replacement if needed; measurement of cardan pin clearance dimensions (gap check); corrective actions if necessary; and a report of all findings. Since we issued AD 2015-10-03, further investigation concluded that the reported MLG sidestay upper cardan pin migration event had been caused by corrosion due to lack of jointing compound and inadequate sealant application during the MLG installation. This proposed AD would require a detailed inspection of the upper cardan pin and nut threads for any corrosion, pitting, or thread damage, and if necessary, replacement of the cardan pin and nut threads. This proposed AD would also revise the applicability to include additional airplane models. We are proposing this AD to detect and correct migration of the sidestay upper cardan pin, which could result in disconnection of the sidestay upper arm from the airplane structure, and could result in a landing gear collapse and consequent damage to the airplane and injury to occupants. DATES: We must receive comments on this proposed AD by March 7, 2016. ADDRESSES: You may send comments 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: U.S. Department of Transportation, Docket Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New Jersey Avenue SE., Washington, DC, between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. For service information identified in this proposed AD, contact Airbus SAS--Airworthiness Office--EAL, 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex, France; telephone +33 5 61 93 36 96; fax +33 5 61 93 45 80; email [email protected]; Internet http://www.airbus.com. You may view this referenced service information at the FAA, Transport Airplane Directorate, 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-2016- 0459; 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 proposed AD, 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: Vladimir Ulyanov, Aerospace Engineer, International Branch, ANM-116, Transport Airplane Directorate, FAA, 1601 Lind Avenue SW., Renton, WA 98057-3356; telephone 425-227-1138; fax 425-227-1149. SUPPLEMENTARY INFORMATION: Comments Invited We invite you to send any written relevant data, views, or arguments about this proposed AD. Send your comments to an address listed under the ADDRESSES section. Include ``Docket No. FAA-2016-0459; Directorate Identifier 2015-NM-081-AD'' at the beginning of your comments. We specifically invite comments on the overall regulatory, economic, environmental, and energy aspects of this proposed AD. We will consider all comments received by the closing date and may amend this proposed AD 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 proposed AD. Discussion On April 30, 2015, we issued AD 2015-10-03, Amendment 39-18158 (80 FR 30608, May 29, 2015). AD 2015-10-03 requires actions intended to address an unsafe condition on certain Airbus Model A330-200 and -300 series airplanes, and Model A340-200 and -300 series airplanes. Since we issued AD 2015-10-03, Amendment 39-18158 (80 FR 30608, May 29, 2015), further investigation concluded that the reported MLG sidestay upper cardan pin migration event had been caused by corrosion due to lack of jointing compound and inadequate sealant application during the MLG installation. Therefore, this issue affects any MLG that had an upper cardan pin replacement or reinstallation, regardless of MLG overhaul. Any corrosion on the upper cardan pin and nut threads would not have been detected during the currently required detailed inspection. The European Aviation Safety Agency (EASA), which is the Technical Agent [[Page 3347]] for the Member States of the European Union, has issued EASA Airworthiness Directive 2015-0079, dated May 7, 2015 (referred to after this as the Mandatory Continuing Airworthiness Information, or ``the MCAI''), to correct an unsafe condition for certain Airbus Model A330- 200 and -300 series airplanes, Model A340-200 and -300 series airplanes, and Model A340-541 and -642 airplanes. The MCAI states: An A330 aeroplane equipped with Basic MLG was rolling out after landing when it experienced a nose wheel steering fault (unrelated to the safety subject addressed by this AD), which resulted in the crew stopping the aeroplane on the taxiway after vacating the runway. The subsequent investigation revealed that the right-hand MLG sidestay upper cardan pin had migrated out of position. The sidestay upper cardan nut and retainer had detached from the upper cardan pin and were found, still bolted together, in the landing gear bay. Prompted by these findings, Airbus published Alert Operators Transmission (AOT) A32L003-14, providing inspection instructions and, as an interim solution, EASA issued AD 2014-0066 [which corresponds to FAA AD 2015-10-03, Amendment 39-18158 (80 FR 30608, May 29, 2015)] to require repetitive detailed inspections (DET) of the MLG upper cardan pin, nut and retainer. That AD also required accomplishment of a one-time gap check between wing rear spar fitting lugs and the bush flanges and, depending on findings, corrective action(s). The gap check (including corrections, as necessary) terminated the repetitive DET. Since that [EASA] AD was issued, further investigation concluded that the reported MLG sidestay upper cardan pin migration event had been caused by corrosion, due to lack of jointing compound and inadequate sealant application during MLG installation. Therefore, this issue affects any MLG that had an upper cardan pin replacement or re-installation, irrespective of MLG overhaul. Any corrosion on the upper cardan pin and nut threads would not have been detected during the previously required DET. This condition, if not detected and corrected, could lead to a complete migration of the sidestay upper cardan pin and a disconnection of the sidestay upper arm from the aeroplane structure, possibly resulting in MLG collapse with consequent damage to the aeroplane and injury to occupants. To address this potential unsafe condition, Airbus published Service Bulletin (SB) A330-32-3269, SB A340-32-4301 and SB A340-32- 5115 providing inspection instructions. In addition, to prevent any improper re-installation of an upper cardan pin on a MLG, Airbus amended the applicable Aircraft Maintenance Manual (AMM) on 01 October 2014. For the reasons described above, this [EASA] AD supersedes EASA [AD] 2014-0066 and requires a one-time DET of the MLG upper cardan pin and nut threads to check for corrosion or damage on the upper cardan pin and nut threads, and, depending on findings, replacement of the damaged part(s). As this unsafe condition could also develop on A330 freighters and A340-500/-600 aeroplanes, this [EASA] AD also applies to those aeroplanes. 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-2016- 0459. Related Service Information Under 1 CFR Part 51 Airbus has issued the following service information: Airbus Service Bulletin A330-32-3269, dated February 17, 2015. Airbus Service Bulletin A340-32-4301, dated February 17, 2015. Airbus Service Bulletin A340-32-5115, dated February 17, 2015. The service information describes procedures for a detailed inspection of the upper cardan pin and nut threads for any corrosion, pitting, or thread damage, and replacement of the cardan pin and nut threads. 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 95 airplanes of U.S. registry. We also estimate that it would take about 11 work-hours per product to comply with the basic requirements of this proposed AD. The average labor rate is $85 per work-hour. Based on these figures, we estimate the cost of this proposed AD on U.S. operators to be $88,825, or $935 per product. In addition, we estimate that any necessary follow-on actions would take about 12 work-hours and require parts costing $78,136, for a cost of $79,156 per product. We have no way of determining the number of aircraft that might need this action. 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. 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 3348]] Sec. 39.13 [Amended] 0 2. The FAA amends Sec. 39.13 by removing Airworthiness Directive (AD) 2015-10-03, Amendment 39-18158 (80 FR 30608, May 29, 2015), and adding the following new AD: Airbus: Docket No. FAA-2016-0459; Directorate Identifier 2015-NM- 081-AD. (a) Comments Due Date We must receive comments by March 7, 2016. (b) Affected ADs This AD replaces 2015-10-03, Amendment 39-18158 (80 FR 30608, May 29, 2015). (c) Applicability This AD applies to the airplanes, certificated in any category, identified in paragraphs (c)(1), (c)(2), and (c)(3) of this AD, except airplanes on which an upper cardan pin on a main landing gear (MLG) has never been replaced or reinstalled since first entry into service of the airplane. (1) Airbus Model A330-201, -202, -203, -223, -223F, -243, -243F, -301, -302, -303, -321, -322, -323, -341, -342, and -343 airplanes, all manufacturer serial numbers . (2) Airbus Model A340-211, -212, -213, -311, -312, and -313 airplanes, all manufacturer serial numbers. (3) Airbus Model A340-541 and -642 airplanes, all manufacturer serial numbers. (d) Subject Air Transport Association (ATA) of America Code 32, Landing Gear. (e) Reason This AD was prompted by a report that an MLG sidestay upper cardan pin migration event had been caused by corrosion due to lack of jointing compound and inadequate sealant application during the MLG installation. We are issuing this AD to detect and correct migration of the sidestay upper cardan pin, which could result in disconnection of the sidestay upper arm from the airplane structure, and could result in a landing gear collapse and consequent damage to the airplane and injury to occupants. (f) Compliance Comply with this AD within the compliance times specified, unless already done. (g) Definition For the purpose of this AD, an upper cardan pin on a MLG is affected if it has been installed as a replacement part, or reinstalled since first entry of the airplane into service, and if the installation was accomplished using the applicable airplane maintenance manual at a revision level prior to October 1, 2014. (h) Inspection and Replacement (1) For an affected upper cardan pin on an MLG: Before exceeding 96 months since its latest installation on an airplane, or within 12 months after the effective date of this AD, whichever occurs later, do a detailed inspection of the upper cardan pin and nut threads for any corrosion, pitting, or thread damage, in accordance with the Accomplishment Instructions of the applicable service information specified in paragraph (i) of this AD. (2) If, during the detailed inspection specified in paragraph (h)(1) of this AD, any corrosion, pitting, or thread damage is found, before further flight, replace the upper cardan pin and/or nut, as applicable, in accordance with the Accomplishment Instructions of the applicable service information specified in paragraph (i) of this AD. (i) Applicable Service Information Do the actions required by paragraph (h) of this AD in accordance with the Accomplishment Instructions of the applicable service information identified in paragraphs (i)(1), (i)(2), and (i)(3) of this AD. (1) Airbus Service Bulletin A330-32-3269, dated February 17, 2015 (for Airbus Model A330-201, -202, -203, -223, -223F, -243, - 243F, -301, -302, -303, -321, -322, -323, -341, -342, and -343 airplanes). (2) Airbus Service Bulletin A340-32-4301, dated February 17, 2015 (for Airbus Model A340-211, -212, -213, -311, -312, and -313 airplanes). (3) Airbus Service Bulletin A340-32-5115, dated February 17, 2015 (for Airbus Model A340-541 and -642 airplanes). (j) Other FAA AD Provisions The following provisions also apply to this AD: (1) Alternative Methods of Compliance (AMOCs): The Manager, International Branch, ANM-116, Transport Airplane Directorate, 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 Branch, send it to ATTN: Vladimir Ulyanov, Aerospace Engineer, International Branch, ANM 116, Transport Airplane Directorate, FAA, 1601 Lind Avenue SW., Renton, WA 98057-3356; telephone 425-227-1138; fax 425-227-1149. 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. The AMOC approval letter must specifically reference this AD. (2) Contacting the Manufacturer: As of the effective date of this AD, 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 Branch, ANM-116, Transport Airplane Directorate, FAA; or the European Aviation Safety Agency (EASA); or Airbus's EASA Design Organization Approval (DOA). If approved by the DOA, the approval must include the DOA-authorized signature. (k) Related Information (1) Refer to Mandatory Continuing Airworthiness Information (MCAI) EASA Airworthiness Directive 2015-0079, dated May 7, 2015, 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-2016-0459. (2) For service information identified in this AD, contact Airbus SAS--Airworthiness Office--EAL, 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex, France; telephone +33 5 61 93 36 96; fax +33 5 61 93 45 80; email [email protected]; Internet http://www.airbus.com. You may view this service information at the FAA, Transport Airplane Directorate, 1601 Lind Avenue SW., Renton, WA. For information on the availability of this material at the FAA, call 425-227-1221. Issued in Renton, Washington, on January 8, 2016. Jeffrey E. Duven, Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 2016-00944 Filed 1-20-16; 8:45 am] BILLING CODE 4910-13-P
![3346 Federal Register / Vol. 81, No. 13 / Thursday, January 21, 2016 / Proposed Rules
vanning takeoffs/departures as a method to cardan pin clearance dimensions (gap and 5 p.m., Monday through Friday,
turn aircraft: Prohibited. check); corrective actions if necessary; except Federal holidays. The AD docket
(f) Credit for Actions Previously Completed and a report of all findings. Since we contains this proposed AD, the
Incorporating the changes contained in
issued AD 2015–10–03, further regulatory evaluation, any comments
Kaman K–1200 RFM, Revision 5, dated April investigation concluded that the received, and other information. The
14, 2015, before the effective date of this AD reported MLG sidestay upper cardan pin street address for the Docket Operations
is considered acceptable for compliance with migration event had been caused by office (telephone 800–647–5527) is in
the corresponding actions specified in corrosion due to lack of jointing the ADDRESSES section. Comments will
paragraph (e) of this AD. compound and inadequate sealant be available in the AD docket shortly
(g) Alternative Methods of Compliance application during the MLG installation. after receipt.
(AMOC) This proposed AD would require a FOR FURTHER INFORMATION CONTACT:
(1) The Manager, Boston Aircraft
detailed inspection of the upper cardan Vladimir Ulyanov, Aerospace Engineer,
Certification Office, FAA, may approve pin and nut threads for any corrosion, International Branch, ANM–116,
AMOCs for this AD. Send your proposal to: pitting, or thread damage, and if Transport Airplane Directorate, FAA,
Kirk Gustafson, Aviation Safety Engineer, necessary, replacement of the cardan 1601 Lind Avenue SW., Renton, WA
Boston Aircraft Certification Office, Engine & pin and nut threads. This proposed AD 98057–3356; telephone 425–227–1138;
Propeller Directorate, FAA, 12 New England would also revise the applicability to fax 425–227–1149.
Executive Park, Burlington, Massachusetts include additional airplane models. We SUPPLEMENTARY INFORMATION:
01803; telephone (781) 238–7190; email are proposing this AD to detect and
kirk.gustafson@faa.gov. correct migration of the sidestay upper Comments Invited
(2) For operations conducted under a 14 We invite you to send any written
CFR part 119 operating certificate or under
cardan pin, which could result in
14 CFR part 91, subpart K, we suggest that disconnection of the sidestay upper arm relevant data, views, or arguments about
you notify your principal inspector, or from the airplane structure, and could this proposed AD. Send your comments
lacking a principal inspector, the manager of result in a landing gear collapse and to an address listed under the
the local flight standards district office or consequent damage to the airplane and ADDRESSES section. Include ‘‘Docket No.
certificate holding district office before injury to occupants. FAA–2016–0459; Directorate Identifier
operating any aircraft complying with this DATES: We must receive comments on 2015–NM–081–AD’’ at the beginning of
AD through an AMOC. your comments. We specifically invite
this proposed AD by March 7, 2016.
(h) Subject comments on the overall regulatory,
ADDRESSES: You may send comments by
economic, environmental, and energy
Joint Aircraft Service Component (JASC) any of the following methods: aspects of this proposed AD. We will
Code: 6710, Main Rotor Control. • Federal eRulemaking Portal: Go to consider all comments received by the
Issued in Fort Worth, Texas, on January 12, http://www.regulations.gov. Follow the closing date and may amend this
2016. instructions for submitting comments. proposed AD based on those comments.
Lance T. Gant, • Fax: 202–493–2251. We will post all comments we
Manager, Rotorcraft Directorate, Aircraft • Mail: U.S. Department of receive, without change, to http://
Certification Service. Transportation, Docket Operations, M– www.regulations.gov, including any
[FR Doc. 2016–00947 Filed 1–20–16; 8:45 am] 30, West Building Ground Floor, Room personal information you provide. We
BILLING CODE 4910–13–P
W12–140, 1200 New Jersey Avenue SE., will also post a report summarizing each
Washington, DC 20590. substantive verbal contact we receive
• Hand Delivery: U.S. Department of about this proposed AD.
DEPARTMENT OF TRANSPORTATION Transportation, Docket Operations, M–
30, West Building Ground Floor, Room Discussion
Federal Aviation Administration W12–140, 1200 New Jersey Avenue SE., On April 30, 2015, we issued AD
Washington, DC, between 9 a.m. and 5 2015–10–03, Amendment 39–18158 (80
14 CFR Part 39 p.m., Monday through Friday, except FR 30608, May 29, 2015). AD 2015–10–
Federal holidays. 03 requires actions intended to address
[Docket No. FAA–2016–0459; Directorate
Identifier 2015–NM–081–AD] For service information identified in an unsafe condition on certain Airbus
this proposed AD, contact Airbus SAS— Model A330–200 and –300 series
RIN 2120–AA64 Airworthiness Office—EAL, 1 Rond airplanes, and Model A340–200 and
Point Maurice Bellonte, 31707 Blagnac –300 series airplanes.
Airworthiness Directives; Airbus Cedex, France; telephone +33 5 61 93 36 Since we issued AD 2015–10–03,
Airplanes 96; fax +33 5 61 93 45 80; email Amendment 39–18158 (80 FR 30608,
AGENCY: Federal Aviation airworthiness.A330–A340@airbus.com; May 29, 2015), further investigation
Administration (FAA), DOT. Internet http://www.airbus.com. You concluded that the reported MLG
ACTION: Notice of proposed rulemaking may view this referenced service sidestay upper cardan pin migration
(NPRM). information at the FAA, Transport event had been caused by corrosion due
Airplane Directorate, 1601 Lind Avenue to lack of jointing compound and
SUMMARY: We propose to supersede SW., Renton, WA. For information on inadequate sealant application during
Airworthiness Directive (AD) 2015–10– the availability of this material at the the MLG installation. Therefore, this
03, for certain Airbus Model A330–200 FAA, call 425–227–1221. issue affects any MLG that had an upper
jstallworth on DSK7TPTVN1PROD with PROPOSALS
and –300 series airplanes, and Model cardan pin replacement or
A340–200 and –300 series airplanes. AD Examining the AD Docket
reinstallation, regardless of MLG
2015–10–03 currently requires a You may examine the AD docket on overhaul. Any corrosion on the upper
detailed inspection for visible chrome of the Internet at http:// cardan pin and nut threads would not
each affected main landing gear (MLG) www.regulations.gov by searching for have been detected during the currently
sidestay upper cardan pin, associated and locating Docket No. FAA–2016– required detailed inspection.
nuts, and retainer assembly; pin 0459; or in person at the Docket The European Aviation Safety Agency
replacement if needed; measurement of Management Facility between 9 a.m. (EASA), which is the Technical Agent
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![Federal Register / Vol. 81, No. 13 / Thursday, January 21, 2016 / Proposed Rules 3347
for the Member States of the European on findings, replacement of the damaged Authority for This Rulemaking
Union, has issued EASA Airworthiness part(s).
As this unsafe condition could also Title 49 of the United States Code
Directive 2015–0079, dated May 7, 2015 specifies the FAA’s authority to issue
develop on A330 freighters and A340–500/–
(referred to after this as the Mandatory rules on aviation safety. Subtitle I,
600 aeroplanes, this [EASA] AD also applies
Continuing Airworthiness Information, to those aeroplanes. section 106, describes the authority of
or ‘‘the MCAI’’), to correct an unsafe the FAA Administrator. ‘‘Subtitle VII:
condition for certain Airbus Model You may examine the MCAI in the
AD docket on the Internet at http:// Aviation Programs,’’ describes in more
A330–200 and –300 series airplanes, detail the scope of the Agency’s
Model A340–200 and –300 series www.regulations.gov by searching for
and locating Docket No. FAA–2016– authority.
airplanes, and Model A340–541 and We are issuing this rulemaking under
–642 airplanes. The MCAI states: 0459.
the authority described in ‘‘Subtitle VII,
An A330 aeroplane equipped with Basic Related Service Information Under 1 Part A, Subpart III, Section 44701:
MLG was rolling out after landing when it CFR Part 51 General requirements.’’ Under that
experienced a nose wheel steering fault section, Congress charges the FAA with
(unrelated to the safety subject addressed by Airbus has issued the following
service information: promoting safe flight of civil aircraft in
this AD), which resulted in the crew stopping
the aeroplane on the taxiway after vacating • Airbus Service Bulletin A330–32– air commerce by prescribing regulations
the runway. The subsequent investigation 3269, dated February 17, 2015. for practices, methods, and procedures
revealed that the right-hand MLG sidestay • Airbus Service Bulletin A340–32– the Administrator finds necessary for
upper cardan pin had migrated out of 4301, dated February 17, 2015. safety in air commerce. This regulation
position. The sidestay upper cardan nut and • Airbus Service Bulletin A340–32– is within the scope of that authority
retainer had detached from the upper cardan 5115, dated February 17, 2015. because it addresses an unsafe condition
pin and were found, still bolted together, in The service information describes that is likely to exist or develop on
the landing gear bay. procedures for a detailed inspection of products identified in this rulemaking
Prompted by these findings, Airbus action.
the upper cardan pin and nut threads
published Alert Operators Transmission
(AOT) A32L003–14, providing inspection for any corrosion, pitting, or thread Regulatory Findings
instructions and, as an interim solution, damage, and replacement of the cardan
EASA issued AD 2014–0066 [which pin and nut threads. This service We determined that this proposed AD
corresponds to FAA AD 2015–10–03, information is reasonably available would not have federalism implications
Amendment 39–18158 (80 FR 30608, May 29, because the interested parties have under Executive Order 13132. This
2015)] to require repetitive detailed access to it through their normal course proposed AD would not have a
inspections (DET) of the MLG upper cardan of business or by the means identified substantial direct effect on the States, on
pin, nut and retainer. That AD also required in the ADDRESSES section. the relationship between the national
accomplishment of a one-time gap check Government and the States, or on the
between wing rear spar fitting lugs and the FAA’s Determination and Requirements distribution of power and
bush flanges and, depending on findings, of this Proposed AD
corrective action(s). The gap check (including
responsibilities among the various
corrections, as necessary) terminated the This product has been approved by levels of government.
repetitive DET. the aviation authority of another For the reasons discussed above, I
Since that [EASA] AD was issued, further country, and is approved for operation certify this proposed regulation:
investigation concluded that the reported in the United States. Pursuant to our 1. Is not a ‘‘significant regulatory
MLG sidestay upper cardan pin migration bilateral agreement with the State of action’’ under Executive Order 12866;
event had been caused by corrosion, due to Design Authority, we have been notified 2. Is not a ‘‘significant rule’’ under the
lack of jointing compound and inadequate of the unsafe condition described in the DOT Regulatory Policies and Procedures
sealant application during MLG installation. MCAI and service information (44 FR 11034, February 26, 1979);
Therefore, this issue affects any MLG that
had an upper cardan pin replacement or re-
referenced above. We are proposing this 3. Will not affect intrastate aviation in
installation, irrespective of MLG overhaul. AD because we evaluated all pertinent Alaska; and
Any corrosion on the upper cardan pin and information and determined an unsafe 4. Will not have a significant
nut threads would not have been detected condition exists and is likely to exist or economic impact, positive or negative,
during the previously required DET. develop on other products of these same on a substantial number of small entities
This condition, if not detected and type designs. under the criteria of the Regulatory
corrected, could lead to a complete migration Flexibility Act.
of the sidestay upper cardan pin and a Costs of Compliance
disconnection of the sidestay upper arm from We estimate that this proposed AD List of Subjects in 14 CFR Part 39
the aeroplane structure, possibly resulting in affects 95 airplanes of U.S. registry.
MLG collapse with consequent damage to the
Air transportation, Aircraft, Aviation
We also estimate that it would take safety, Incorporation by reference,
aeroplane and injury to occupants.
To address this potential unsafe condition, about 11 work-hours per product to Safety.
Airbus published Service Bulletin (SB) comply with the basic requirements of
this proposed AD. The average labor The Proposed Amendment
A330–32–3269, SB A340–32–4301 and SB
A340–32–5115 providing inspection rate is $85 per work-hour. Based on Accordingly, under the authority
instructions. In addition, to prevent any these figures, we estimate the cost of delegated to me by the Administrator,
improper re-installation of an upper cardan this proposed AD on U.S. operators to the FAA proposes to amend 14 CFR part
jstallworth on DSK7TPTVN1PROD with PROPOSALS
pin on a MLG, Airbus amended the be $88,825, or $935 per product. 39 as follows:
applicable Aircraft Maintenance Manual In addition, we estimate that any
(AMM) on 01 October 2014. PART 39—AIRWORTHINESS
necessary follow-on actions would take
For the reasons described above, this DIRECTIVES
[EASA] AD supersedes EASA [AD] 2014– about 12 work-hours and require parts
0066 and requires a one-time DET of the costing $78,136, for a cost of $79,156
per product. We have no way of ■ 1. The authority citation for part 39
MLG upper cardan pin and nut threads to
check for corrosion or damage on the upper determining the number of aircraft that continues to read as follows:
cardan pin and nut threads, and, depending might need this action. Authority: 49 U.S.C. 106(g), 40113, 44701.
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![3348 Federal Register / Vol. 81, No. 13 / Thursday, January 21, 2016 / Proposed Rules
§ 39.13 [Amended] damage, in accordance with the MCAI may be found in the AD docket on the
■ 2. The FAA amends § 39.13 by Accomplishment Instructions of the Internet at http://www.regulations.gov by
removing Airworthiness Directive (AD) applicable service information specified in searching for and locating Docket No. FAA–
paragraph (i) of this AD. 2016–0459.
2015–10–03, Amendment 39–18158 (80 (2) If, during the detailed inspection (2) For service information identified in
FR 30608, May 29, 2015), and adding specified in paragraph (h)(1) of this AD, any this AD, contact Airbus SAS—Airworthiness
the following new AD: corrosion, pitting, or thread damage is found, Office—EAL, 1 Rond Point Maurice Bellonte,
Airbus: Docket No. FAA–2016–0459; before further flight, replace the upper cardan 31707 Blagnac Cedex, France; telephone +33
Directorate Identifier 2015–NM–081–AD. pin and/or nut, as applicable, in accordance 5 61 93 36 96; fax +33 5 61 93 45 80; email
with the Accomplishment Instructions of the airworthiness.A330-A340@airbus.com;
(a) Comments Due Date applicable service information specified in Internet http://www.airbus.com. You may
We must receive comments by March 7, paragraph (i) of this AD. view this service information at the FAA,
2016. (i) Applicable Service Information Transport Airplane Directorate, 1601 Lind
Avenue SW., Renton, WA. For information
(b) Affected ADs Do the actions required by paragraph (h) of on the availability of this material at the
This AD replaces 2015–10–03, Amendment this AD in accordance with the FAA, call 425–227–1221.
39–18158 (80 FR 30608, May 29, 2015). Accomplishment Instructions of the
applicable service information identified in Issued in Renton, Washington, on January
(c) Applicability paragraphs (i)(1), (i)(2), and (i)(3) of this AD. 8, 2016.
This AD applies to the airplanes, (1) Airbus Service Bulletin A330–32–3269, Jeffrey E. Duven,
certificated in any category, identified in dated February 17, 2015 (for Airbus Model Manager, Transport Airplane Directorate,
paragraphs (c)(1), (c)(2), and (c)(3) of this AD, A330–201, –202, –203, –223, –223F, –243, Aircraft Certification Service.
except airplanes on which an upper cardan –243F, –301, –302, –303, –321, –322, –323,
[FR Doc. 2016–00944 Filed 1–20–16; 8:45 am]
pin on a main landing gear (MLG) has never –341, –342, and –343 airplanes).
been replaced or reinstalled since first entry (2) Airbus Service Bulletin A340–32–4301, BILLING CODE 4910–13–P
into service of the airplane. dated February 17, 2015 (for Airbus Model
(1) Airbus Model A330–201, –202, –203, A340–211, –212, –213, –311, –312, and –313
–223, –223F, –243, –243F, –301, –302, –303, airplanes). DEPARTMENT OF TRANSPORTATION
–321, –322, –323, –341, –342, and –343 (3) Airbus Service Bulletin A340–32–5115,
airplanes, all manufacturer serial numbers . dated February 17, 2015 (for Airbus Model Federal Aviation Administration
(2) Airbus Model A340–211, –212, –213, A340–541 and –642 airplanes).
–311, –312, and –313 airplanes, all 14 CFR Part 39
(j) Other FAA AD Provisions
manufacturer serial numbers.
(3) Airbus Model A340–541 and –642 The following provisions also apply to this [Docket No. FAA–2016–0460; Directorate
airplanes, all manufacturer serial numbers. AD: Identifier 2015–NM–078–AD]
(1) Alternative Methods of Compliance
(d) Subject (AMOCs): The Manager, International RIN 2120–AA64
Air Transport Association (ATA) of Branch, ANM–116, Transport Airplane
America Code 32, Landing Gear. Directorate, FAA, has the authority to Airworthiness Directives; Beechcraft
approve AMOCs for this AD, if requested Corporation (Type Certificate
(e) Reason using the procedures found in 14 CFR 39.19. Previously Held by Hawker Beechcraft
This AD was prompted by a report that an In accordance with 14 CFR 39.19, send your Corporation; Raytheon Aircraft
MLG sidestay upper cardan pin migration request to your principal inspector or local Company) Airplanes
event had been caused by corrosion due to Flight Standards District Office, as
lack of jointing compound and inadequate appropriate. If sending information directly AGENCY: Federal Aviation
sealant application during the MLG to the International Branch, send it to ATTN: Administration (FAA), DOT.
installation. We are issuing this AD to detect Vladimir Ulyanov, Aerospace Engineer,
ACTION: Notice of proposed rulemaking
and correct migration of the sidestay upper International Branch, ANM 116, Transport
cardan pin, which could result in Airplane Directorate, FAA, 1601 Lind (NPRM).
disconnection of the sidestay upper arm from Avenue SW., Renton, WA 98057–3356;
the airplane structure, and could result in a telephone 425–227–1138; fax 425–227–1149. SUMMARY: We propose to adopt a new
landing gear collapse and consequent damage Information may be emailed to: 9-ANM-116- airworthiness directive (AD) for certain
to the airplane and injury to occupants. AMOC-REQUESTS@faa.gov. Before using Beechcraft Corporation Model BAe.125
any approved AMOC, notify your appropriate series 1000A and 1000B airplanes and
(f) Compliance principal inspector, or lacking a principal Model Hawker 1000 airplanes. This
Comply with this AD within the inspector, the manager of the local flight proposed AD was prompted by reports
compliance times specified, unless already standards district office/certificate holding of inadvertent stowage of the thrust
done. district office. The AMOC approval letter
must specifically reference this AD.
reversers, which can result in high
(g) Definition forward engine thrust even though the
(2) Contacting the Manufacturer: As of the
For the purpose of this AD, an upper effective date of this AD, for any requirement throttle is commanding reverse thrust.
cardan pin on a MLG is affected if it has been in this AD to obtain corrective actions from This proposed AD would require
installed as a replacement part, or reinstalled a manufacturer, the action must be installing kits that include relays,
since first entry of the airplane into service, accomplished using a method approved by associated wiring, and a thrust reverser
and if the installation was accomplished the Manager, International Branch, ANM– fail annunciator. We are proposing this
using the applicable airplane maintenance 116, Transport Airplane Directorate, FAA; or AD to prevent inadvertent stowage of
manual at a revision level prior to October 1, the European Aviation Safety Agency
2014. (EASA); or Airbus’s EASA Design
the thrust reversers, which could cause
jstallworth on DSK7TPTVN1PROD with PROPOSALS
Organization Approval (DOA). If approved by a runway overrun during a rejected
(h) Inspection and Replacement takeoff or landing, and consequent
the DOA, the approval must include the
(1) For an affected upper cardan pin on an DOA-authorized signature. structural failure and possible injury to
MLG: Before exceeding 96 months since its occupants.
latest installation on an airplane, or within (k) Related Information
DATES: We must receive comments on
12 months after the effective date of this AD, (1) Refer to Mandatory Continuing
whichever occurs later, do a detailed Airworthiness Information (MCAI) EASA this proposed AD by March 7, 2016.
inspection of the upper cardan pin and nut Airworthiness Directive 2015–0079, dated ADDRESSES: You may send comments,
threads for any corrosion, pitting, or thread May 7, 2015, for related information. This using the procedures found in 14 CFR
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Document Created: 2018-02-02 12:34:02
Document Modified: 2018-02-02 12:34:02
| 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 March 7, 2016. | |
| Contact | Vladimir Ulyanov, Aerospace Engineer, International Branch, ANM-116, Transport Airplane Directorate, FAA, 1601 Lind Avenue SW., Renton, WA 98057-3356; telephone 425-227-1138; fax 425-227-1149. | |
| FR Citation | 81 FR 3346 | |
| RIN Number | 2120-AA64 | |
| CFR Associated | Air Transportation; Aircraft; Aviation Safety; Incorporation by Reference and Safety |
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