Airworthiness Directives; Airbus Airplanes, 3346-3348 [2016-00944]

Download as PDF 3346 Federal Register / Vol. 81, No. 13 / Thursday, January 21, 2016 / Proposed Rules vanning takeoffs/departures as a method to turn aircraft: Prohibited. (f) Credit for Actions Previously Completed Incorporating the changes contained in Kaman K–1200 RFM, Revision 5, dated April 14, 2015, before the effective date of this AD is considered acceptable for compliance with the corresponding actions specified in paragraph (e) of this AD. (g) Alternative Methods of Compliance (AMOC) (1) The Manager, Boston Aircraft Certification Office, FAA, may approve AMOCs for this AD. Send your proposal to: Kirk Gustafson, Aviation Safety Engineer, Boston Aircraft Certification Office, Engine & Propeller Directorate, FAA, 12 New England Executive Park, Burlington, Massachusetts 01803; telephone (781) 238–7190; email kirk.gustafson@faa.gov. (2) For operations conducted under a 14 CFR part 119 operating certificate or under 14 CFR part 91, subpart K, we suggest that you notify your principal inspector, or lacking a principal inspector, the manager of the local flight standards district office or certificate holding district office before operating any aircraft complying with this AD through an AMOC. (h) Subject Joint Aircraft Service Component (JASC) Code: 6710, Main Rotor Control. Issued in Fort Worth, Texas, on January 12, 2016. Lance T. Gant, Manager, Rotorcraft Directorate, Aircraft Certification Service. [FR Doc. 2016–00947 Filed 1–20–16; 8:45 am] BILLING CODE 4910–13–P 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 Federal Aviation Administration (FAA), DOT. ACTION: Notice of proposed rulemaking (NPRM). AGENCY: 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 jstallworth on DSK7TPTVN1PROD with PROPOSALS SUMMARY: VerDate Sep<11>2014 15:09 Jan 20, 2016 Jkt 238001 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 airworthiness.A330–A340@airbus.com; 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. PO 00000 Frm 00006 Fmt 4702 Sfmt 4702 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 E:\FR\FM\21JAP1.SGM 21JAP1 Federal Register / Vol. 81, No. 13 / Thursday, January 21, 2016 / Proposed Rules jstallworth on DSK7TPTVN1PROD with PROPOSALS 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: 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. 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 reinstallation, 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 Related Service Information Under 1 CFR Part 51 VerDate Sep<11>2014 15:09 Jan 20, 2016 Jkt 238001 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. 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. PO 00000 Frm 00007 Fmt 4702 Sfmt 4702 3347 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 1. The authority citation for part 39 continues to read as follows: ■ Authority: 49 U.S.C. 106(g), 40113, 44701. E:\FR\FM\21JAP1.SGM 21JAP1 3348 § 39.13 Federal Register / Vol. 81, No. 13 / Thursday, January 21, 2016 / Proposed Rules [Amended] 2. The FAA amends § 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. jstallworth on DSK7TPTVN1PROD with PROPOSALS (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 VerDate Sep<11>2014 15:09 Jan 20, 2016 Jkt 238001 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: 9-ANM-116AMOC-REQUESTS@faa.gov. Before using any approved AMOC, notify your appropriate principal inspector, or lacking a principal inspector, the manager of the local flight standards district office/certificate holding district office. 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 PO 00000 Frm 00008 Fmt 4702 Sfmt 4702 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 airworthiness.A330-A340@airbus.com; 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 DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2016–0460; Directorate Identifier 2015–NM–078–AD] RIN 2120–AA64 Airworthiness Directives; Beechcraft Corporation (Type Certificate Previously Held by Hawker Beechcraft Corporation; Raytheon Aircraft Company) Airplanes Federal Aviation Administration (FAA), DOT. ACTION: Notice of proposed rulemaking (NPRM). AGENCY: We propose to adopt a new airworthiness directive (AD) for certain Beechcraft Corporation Model BAe.125 series 1000A and 1000B airplanes and Model Hawker 1000 airplanes. This proposed AD was prompted by reports of inadvertent stowage of the thrust reversers, which can result in high forward engine thrust even though the throttle is commanding reverse thrust. This proposed AD would require installing kits that include relays, associated wiring, and a thrust reverser fail annunciator. We are proposing this AD to prevent inadvertent stowage of the thrust reversers, which could cause a runway overrun during a rejected takeoff or landing, and consequent structural failure and possible injury to occupants. DATES: We must receive comments on this proposed AD by March 7, 2016. ADDRESSES: You may send comments, using the procedures found in 14 CFR SUMMARY: E:\FR\FM\21JAP1.SGM 21JAP1

Agencies

[Federal Register Volume 81, Number 13 (Thursday, January 21, 2016)]
[Proposed Rules]
[Pages 3346-3348]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2016-00944]


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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 airworthiness.A330-A340@airbus.com; 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: 9-ANM-116-AMOC-REQUESTS@faa.gov. Before using any 
approved AMOC, notify your appropriate principal inspector, or 
lacking a principal inspector, the manager of the local flight 
standards district office/certificate holding district office. 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 airworthiness.A330-A340@airbus.com; 
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