Airworthiness Directives; Eurocopter France Helicopters, 59298-59303 [2013-23434]

Download as PDF 59298 Federal Register / Vol. 78, No. 187 / Thursday, September 26, 2013 / Proposed Rules identified in paragraphs (g)(1), (g)(2), and (g)(3) of this AD. (1) For airplanes on which Airbus Modification 53368 (back-up speed scale) has been embodied in production or Airbus Service Bulletin A330–34–3213, Airbus Service Bulletin A340–34–4213, or Airbus Service Bulletin A340–34–5060, as applicable, has been embodied in service: Within 3 months after December 14, 2010 (the effective date of AD 2010–23–12, Amendment 39–16501 (75 FR 68698, November 9, 2010)). (2) For airplanes on which Airbus Modification 53368 (back-up speed scale) has not been embodied in production and Airbus Service Bulletin A330–34–3213, Airbus Service Bulletin A340–34–4213, or Airbus Service Bulletin A340–34–5060, as applicable, has not been embodied in service: Within 15 months after December 14, 2010 (the effective date of AD 2010–23–12, Amendment 39–16501 (75 FR 68698, November 9, 2010)). (i) New Replacement of AoA Probes For airplanes on which an AoA probe having P/N C16291AA or C16291AB, with a serial number identified in Thales Service Bulletin C16291A–34–007, Revision 04, dated October 11, 2012, is installed, except as provided by paragraph (k) of this AD: Within 6 months after the effective date of this AD, replace any AoA probe having P/N C16291AA or C16291AB with a serviceable AoA probe, in accordance with the Accomplishment Instructions of the applicable service information identified in paragraphs (g)(1), (g)(2), and (g)(3) of this AD. A review of airplane maintenance records that demonstrates that the affected AoA probe has passed the inspection, in accordance with the Accomplishment Instructions of Thales Service Bulletin C16291A–34–007, Revision 04, dated October 11, 2012, is acceptable for compliance with the requirements of this paragraph. emcdonald on DSK67QTVN1PROD with PROPOSALS (j) Exception to AD Requirements Airplanes on which Airbus Modification 58555 (installation of AoA sensors with P/N C16291AB) or Airbus Modification 46921 (installation of AoA sensors with P/N 0861ED) has been embodied in production are not affected by the requirements in paragraphs (g), (h) and (i) of this AD, provided that no AoA sensor has been replaced since first flight. (k) Parts Installation Limitations (1) For airplanes on which an AoA sensor having part number (P/N) C16291AA is installed: As of December 14, 2010 (the effective date of AD 2010–23–12, Amendment 39–16501 (75 FR 68698, November 9, 2010)) and until the effective date of this AD, no person may install, on any airplane, a Thales Avionics AoA probe having P/N C16291AA and a serial number identified in Thales Service Bulletin C16291A–34–007, Revision 01, dated December 3, 2009, unless the AoA is fitted with an inspection label stating that Thales Service Bulletin C16291A–34–007, has been accomplished. VerDate Mar<15>2010 18:01 Sep 25, 2013 Jkt 229001 (2) As of the effective date of this AD, no person may install, on any airplane, a Thales Avionics AoA probe having P/N C16291AA or P/N C16291AB and a serial number identified in Thales Service Bulletin C16291A–34–007, Revision 04, dated October 11, 2012, unless the AoA is fitted with an inspection label stating that Thales Service Bulletin C16291A–34–007, has been accomplished. (l) 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, Washington 98057– 3356; telephone (425) 227–1138; fax (425) 227–1149. Information may be emailed to: 9ANM-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) Airworthy Product: For any requirement in this AD to obtain corrective actions from a manufacturer or other source, use these actions if they are FAA-approved. Corrective actions are considered FAA-approved if they are approved by the State of Design Authority (or their delegated agent). You are required to assure the product is airworthy before it is returned to service. (m) Related Information (1) Refer to Mandatory Continuing Airworthiness Information Airworthiness Directive 2013–0068, dated March 15, 2013, for related information, which can be found in the AD docket on the internet at http:// www.regulations.gov. (2) For Airbus 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. (3) For Thales Avionics service information identified in this proposed AD, contact Thales—Aerospace Division, 105, avenue du General Eisenhower—BP 63647, 31036 Toulouse Cedex 1, France; telephone +33 (0)5 61 19 65 00; fax +33 (0)5 61 19 66 00; Internet http://www.thalesgroup.com/ aerospace. (4) You may review copies of the referenced service information at the FAA, Transport Airplane Directorate, 1601 Lind Avenue SW., Renton, Washington. For PO 00000 Frm 00010 Fmt 4702 Sfmt 4702 information on the availability of this material at the FAA, call 425–227–1221. Issued in Renton, Washington, on September 17, 2013. Ross Landes, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 2013–23443 Filed 9–25–13; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2011–1158; Directorate Identifier 2010–SW–018–AD] RIN 2120–AA64 Airworthiness Directives; Eurocopter France Helicopters Federal Aviation Administration (FAA), DOT. ACTION: Notice of proposed rulemaking (NPRM). AGENCY: We propose to revise airworthiness directive (AD) 2011–22– 05 for Eurocopter France (Eurocopter) Model AS350B, B1, B2, B3, BA, C, D, D1, AS355E, F, F1, F2, N, and NP helicopters with certain tail rotor pitch control rods installed. AD 2011–22–05 currently requires, before the first flight of each day, checking the tail rotor (T/ R) pitch control rod (control rod) outboard spherical bearing (bearing) for play. If play exists, AD 2011–22–05 requires measuring the bearing’s radial and axial play. Since we issued AD 2011–22–05, we have determined that we can safely extend the compliance time to perform the initial and recurring checks for bearing play. The proposed actions are intended to prevent failure of a control rod, loss of T/R control, and subsequent loss of control of the helicopter. DATES: We must receive comments on this proposed AD by November 25, 2013. ADDRESSES: You may send comments by any of the following methods: • Federal eRulemaking Docket: Go to http://www.regulations.gov. Follow the online instructions for sending your comments electronically. • Fax: 202–493–2251. • Mail: Send comments to the U.S. Department of Transportation, Docket Operations, M–30, West Building Ground Floor, Room W12–140, 1200 New Jersey Avenue SE., Washington, DC 20590–0001. • Hand Delivery: Deliver to the ‘‘Mail’’ address between 9 a.m. and 5 SUMMARY: E:\FR\FM\26SEP1.SGM 26SEP1 Federal Register / Vol. 78, No. 187 / Thursday, September 26, 2013 / Proposed Rules p.m., Monday through Friday, except Federal holidays. proposal in light of the comments we receive. Examining the AD Docket Discussion On October 12, 2011, we issued AD 2011–22–05, Amendment 39–16847 (76 FR 70046, November 10, 2011) for Eurocopter Model AS350B, B1, B2, B3, BA, C, D, D1, AS355E, F, F1, F2, N, and NP helicopters with certain T/R control rods installed. AD 2011–22–05 requires the following actions: • Before the first flight of each day, checking the control rod bearing for play on the helicopter, by observation and feel, by slightly moving the TR blade in the flapping axis while monitoring the bearing for movement. • If the Teflon cloth is coming out of its position within the bearing or if there is discoloration or scoring, replacing the control rod assembly before further flight. • If play is detected, having a mechanic remove the control rod from the helicopter, and using a dial indicator, measuring the control rod bearing wear. If the radial play exceeds 0.008 inch or axial play exceeds 0.016 inch, replacing the control rod with an airworthy control rod before further flight. • Thereafter, at intervals not to exceed 30 hours time-in-service (TIS), repeating the requirement to remove the control rod and measuring the bearing for wear using a dial indicator. AD 2011–22–05 was prompted by the issuance of AD No. 2010–0006, dated January 7, 2010, by the European Aviation Safety Agency (EASA), which is the Technical Agent for the Member States of the European Union. The EASA AD was issued to correct an unsafe condition for certain Eurocopter helicopters. EASA advised that a pilot of a Eurocopter Model AS350 helicopter felt slight vibrations in the pedal unit in flight. A few minutes later, the vibration level increased and the pilot carried out a precautionary autorotation landing. After landing, it was discovered that one TR pitch-change link was damaged, the tailboom cone was missing, and there was an impact mark on the tailboom. Further investigation revealed the affected TR pitch-change link showed extensive wear on the ball-joint. EASA advised that this condition, if not detected and corrected, could lead to loss of the anti-torque function and possible loss of control of the helicopter. You may examine the AD docket on the Internet at http:// www.regulations.gov or in person at the Docket Operations Office between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. The AD docket contains this proposed AD, the foreign authority’s AD, the economic 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 service information identified in this proposed AD, contact American Eurocopter Corporation, 2701 N. Forum Drive, Grand Prairie, TX 75052; telephone (972) 641–0000 or (800) 232– 0323; fax (972) 641–3775; or at http:// www.eurocopter.com/techpub. You may review service information at the FAA, Office of the Regional Counsel, Southwest Region, 2601 Meacham Blvd., Room 663, Fort Worth, Texas 76137. FOR FURTHER INFORMATION CONTACT: Robert Grant, Aviation Safety Engineer, Safety Management Group, FAA, 2601 Meacham Blvd., Fort Worth, Texas 76137; telephone (817) 222–5110; email robert.grant@faa.gov. SUPPLEMENTARY INFORMATION: emcdonald on DSK67QTVN1PROD with PROPOSALS Comments Invited We invite you to participate in this rulemaking by submitting written comments, data, or views. We also invite comments relating to the economic, environmental, energy, or federalism impacts that might result from adopting the proposals in this document. The most helpful comments reference a specific portion of the proposal, explain the reason for any recommended change, and include supporting data. To ensure the docket does not contain duplicate comments, commenters should send only one copy of written comments, or if comments are filed electronically, commenters should submit only one time. We will file in the docket all comments that we receive, as well as a report summarizing each substantive public contact with FAA personnel concerning this proposed rulemaking. Before acting on this proposal, we will consider all comments we receive on or before the closing date for comments. We will consider comments filed after the comment period has closed if it is possible to do so without incurring expense or delay. We may change this VerDate Mar<15>2010 18:01 Sep 25, 2013 Jkt 229001 Actions Since AD 2011–22–05 Was Issued Since we issued AD 2011–22–05 (76 FR 70046, November 10, 2011), we have determined that we can safely extend the compliance time for the initial PO 00000 Frm 00011 Fmt 4702 Sfmt 4702 59299 bearing play check and the interval for recurring checks to 30 hours TIS. We also received several requests for alternative methods of compliance regarding the bearing play check, and as a result this proposed AD would clarify the requirements of that check. We removed a previous requirement that if the Teflon cloth is coming out of its normal position within the bearing, or if there is discoloration or scoring on the bearing, that the control rod be replaced with an airworthy rod before further flight. FAA’s Determination These helicopters have been approved by the aviation authority of France and are approved for operation in the United States. Pursuant to our bilateral agreement with France, EASA, its technical representative, has notified us of the unsafe condition described in its AD. We are proposing this AD because we evaluated all known relevant information and determined that an unsafe condition is likely to exist or develop on other products of the same type design. Related Service Information Eurocopter has issued Alert Service Bulletin (ASB) No. 05.00.60 for the Model AS350 series helicopters, and ASB No. 05.00.56 for the Model AS355 series helicopters, both dated December 9, 2009. These ASBs specify performing an initial and recurring check for play in the pitch-change links. If axial play in the ball-joint is detectable, the ASBs specify removing the pitch-change link and measuring the bearing wear using a dial indicator. EASA classified these ASBs as mandatory and issued EASA AD No. 2010–0006 to ensure the continued airworthiness of these helicopters. Proposed AD Requirements This proposed AD would clarify the requirements of AD 2011–22–05, extend the compliance time for the bearing play checks to 30 hours TIS, and remove the requirement to replace the control rod if the Teflon cloth is out of position or if there is discoloration or scoring on the bearing. Costs of Compliance We estimate that this proposed AD would affect 936 helicopters of U.S. Registry and that labor costs will average $85 a work-hour. We estimate, per helicopter, it will take minimal work-hours to do the check, 1 workhour to measure the bearing play, and 1 work-hour to replace 1 control rod. The average labor rate is $85 per workhour. Required parts will cost about E:\FR\FM\26SEP1.SGM 26SEP1 59300 Federal Register / Vol. 78, No. 187 / Thursday, September 26, 2013 / Proposed Rules $1,724 to replace a control rod per helicopter. Based on these figures, we estimate the cost of this AD on U.S. operators is minimal for the check. Measuring the bearing play, if needed, would cost $85 per helicopter, and replacing 1 control rod would cost $1,809 per helicopter. 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. emcdonald on DSK67QTVN1PROD with PROPOSALS 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, I certify this proposed regulation: 1. Is not a ‘‘significant regulatory action’’ under Executive Order 12866; VerDate Mar<15>2010 18:01 Sep 25, 2013 Jkt 229001 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 to the extent that it justifies making a regulatory distinction; 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. We prepared an economic evaluation of the estimated costs to comply with this proposed AD and placed it in the AD docket. 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: (P/N) 350A33–2100–00, –01, –02, –03, –04; P/N 350A33–2121–00, –01, –02; P/N 350A33–2143–00; or P/N 350A33–2145–00 or –01, installed; certificated in any category. (b) Unsafe Condition This AD defines the unsafe condition as excessive play in the control rod. This condition could result in failure of a T/R control rod, loss of T/R control, and subsequent loss of control of the helicopter. (c) Affected ADs This AD revises AD 2011–22–05 (76 FR 70046, November 10, 2011), Amendment 39– 16847, Docket No. FAA–2011–1158, Directorate Identifier 2010–SW–018–AD. (d) Comments Due Date We must receive comments by November 25, 2013. (e) Compliance You are responsible for performing each action required by this AD within the specified compliance time unless it has already been accomplished prior to that time. (f) Required Actions PART 39—AIRWORTHINESS DIRECTIVES 1. The authority citation for part 39 continues to read as follows: ■ Authority: 49 U.S.C. 106(g), 40113, 44701. § 39.13 [Amended] 2. The FAA amends § 39.13 by removing Airworthiness Directive (AD) 2011–22–05, Amendment 39l16847 (76 FR 70046, November 10, 2011), and adding the following new AD: ■ Eurocopter France: Docket No. FAA–2011– 1158; Directorate Identifier 2010–SW– 018–AD. (a) Applicability This AD applies to Eurocopter France (Eurocopter) Model AS350B, B1, B2, B3, BA, C, D, D1; and Model AS355E, F, F1, F2, N, and NP helicopters; with tail rotor (T/R) pitch control rod (control rod), part number PO 00000 Frm 00012 Fmt 4702 Sfmt 4702 (1) Within 30 hours time-in-service (TIS) and, if no bearing play is detected, thereafter at intervals not to exceed 30 hours TIS, place the T/R pedals in the neutral position. If the helicopter is fitted with a T/R load compensator, discharge the accumulator as described in the rotorcraft flight manual. Check the control rod bearing (bearing) for play on the helicopter, by observation and feel, by slightly moving the T/R blade in the flapping axis while monitoring the bearing for movement. See the following Figure 1 to Paragraph (f) of this AD. The actions required by this paragraph of may be performed by the owner/operator (pilot) holding at least a private pilot certificate, and must be entered into the helicopter maintenance records showing compliance with this AD in accordance with 14 CFR 43.9(a)(1)–(4) and 14 CFR 91.417(a)(2)(v). The record must be maintained as required by 14 CFR 91.417, 121.380, or 135.439. BILLING CODE 4910–13–P E:\FR\FM\26SEP1.SGM 26SEP1 Federal Register / Vol. 78, No. 187 / Thursday, September 26, 2013 / Proposed Rules VerDate Mar<15>2010 18:01 Sep 25, 2013 Jkt 229001 helicopter, and using a dial indicator, measure the bearing wear according to the PO 00000 Frm 00013 Fmt 4702 Sfmt 4702 following and as shown in Figures 2 and 3 to Paragraph (f) of this AD: E:\FR\FM\26SEP1.SGM 26SEP1 EP26SE13.009</GPH> emcdonald on DSK67QTVN1PROD with PROPOSALS (2) If a pilot or mechanic detects play in the bearing, before the next flight, a mechanic must remove the control rod from the 59301 VerDate Mar<15>2010 Federal Register / Vol. 78, No. 187 / Thursday, September 26, 2013 / Proposed Rules 18:01 Sep 25, 2013 Jkt 229001 PO 00000 Frm 00014 Fmt 4702 Sfmt 4725 E:\FR\FM\26SEP1.SGM 26SEP1 EP26SE13.010</GPH> emcdonald on DSK67QTVN1PROD with PROPOSALS 59302 Federal Register / Vol. 78, No. 187 / Thursday, September 26, 2013 / Proposed Rules (i) Remove the control rod from the helicopter. (ii) Mount the control rod in a vise as shown in Figure 2 to Paragraph (f) of this AD. (iii) Using a dial indicator, take axial play readings by moving the spherical bearing in the direction F (up and down) as shown in Figure 2 to Paragraph (f) of this AD. (iv) Install a bolt through the bearing and secure it with a washer and nut to provide a clamping surface when the bearing is clamped in a vise. (v) Mount the control rod and bearing in a vise as shown in Figure 3 to Paragraph (f) of this AD. (vi) Using a dial indicator, take radial play measurements by moving the control rod in the direction F as shown in Figure 3 to Paragraph (f) of this AD. (vii) Record the hours of operation on each control rod. (viii) If the radial play exceeds 0.008 inch or axial play exceeds 0.016 inch, replace the control rod with an airworthy control rod before further flight. (ix) If the radial and axial play are within limits, reinstall the control rod. (x) Thereafter, at intervals not to exceed 30 hours TIS, remove the control rod and measure the bearing play with a dial indicator in accordance with paragraph (f)(2) of this AD. VerDate Mar<15>2010 18:01 Sep 25, 2013 Jkt 229001 (g) Alternative Methods of Compliance (AMOCs) (1) The Manager, Safety Management Group, FAA, may approve AMOCs for this AD. Send your proposal to: Robert Grant, Aviation Safety Engineer, Safety Management Group, FAA, 2601 Meacham Blvd., Fort Worth, Texas 76137; telephone (817) 222– 5110; email robert.grant@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. (3) An AMOC approved previously in accordance with Airworthiness Directive No. 2011–22–05, Amendment 39–16847 (76 FR 70046, November 10, 2011), is approved as an AMOC for the corresponding requirements in paragraph (f)(2) of this AD. (h) Additional Information (1) Eurocopter Alert Service Bulletin (ASB) No. 05.00.60 and ASB No. 05.00.56, both dated December 9, 2009, which are not incorporated by reference, contain additional information about the subject of this AD. For service information identified in this AD, contact American Eurocopter Corporation, PO 00000 Frm 00015 Fmt 4702 Sfmt 9990 2701 N. Forum Drive, Grand Prairie, TX 75052; telephone (972) 641–0000 or (800) 232–0323; fax (972) 641–3775; or at http:// www.eurocopter.com/techpub. You may review a copy of the service information at the FAA, Office of the Regional Counsel, Southwest Region, 2601 Meacham Blvd., Room 663, Fort Worth, Texas 76137. (2) The subject of this AD is addressed in the European Aviation Safety Agency (EASA) AD No. 2010–0006, dated January 7, 2010. You may view the EASA AD on the Internet at http://www.regulations.gov in Docket No. FAA–2011–1158. (i) Subject Joint Aircraft Service Component (JASC) Code: 6720, Tail rotor control system. Issued in Fort Worth, Texas, on September 17, 2013. Gwendolynne O’Connell, Acting Directorate Manager, Rotorcraft Directorate, Aircraft Certification Service. [FR Doc. 2013–23434 Filed 9–25–13; 8:45 am] BILLING CODE 4910–13–P E:\FR\FM\26SEP1.SGM 26SEP1 EP26SE13.011</GPH> emcdonald on DSK67QTVN1PROD with PROPOSALS BILLING CODE 4910–13–C 59303

Agencies

[Federal Register Volume 78, Number 187 (Thursday, September 26, 2013)]
[Proposed Rules]
[Pages 59298-59303]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 2013-23434]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2011-1158; Directorate Identifier 2010-SW-018-AD]
RIN 2120-AA64


Airworthiness Directives; Eurocopter France Helicopters

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Notice of proposed rulemaking (NPRM).

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SUMMARY: We propose to revise airworthiness directive (AD) 2011-22-05 
for Eurocopter France (Eurocopter) Model AS350B, B1, B2, B3, BA, C, D, 
D1, AS355E, F, F1, F2, N, and NP helicopters with certain tail rotor 
pitch control rods installed. AD 2011-22-05 currently requires, before 
the first flight of each day, checking the tail rotor (T/R) pitch 
control rod (control rod) outboard spherical bearing (bearing) for 
play. If play exists, AD 2011-22-05 requires measuring the bearing's 
radial and axial play. Since we issued AD 2011-22-05, we have 
determined that we can safely extend the compliance time to perform the 
initial and recurring checks for bearing play. The proposed actions are 
intended to prevent failure of a control rod, loss of T/R control, and 
subsequent loss of control of the helicopter.

DATES: We must receive comments on this proposed AD by November 25, 
2013.

ADDRESSES: You may send comments by any of the following methods:
     Federal eRulemaking Docket: Go to http://www.regulations.gov. Follow the online instructions for sending your 
comments electronically.
     Fax: 202-493-2251.
     Mail: Send comments to the U.S. Department of 
Transportation, Docket Operations, M-30, West Building Ground Floor, 
Room W12-140, 1200 New Jersey Avenue SE., Washington, DC 20590-0001.
     Hand Delivery: Deliver to the ``Mail'' address between 9 
a.m. and 5

[[Page 59299]]

p.m., Monday through Friday, except Federal holidays.

Examining the AD Docket

    You may examine the AD docket on the Internet at http://www.regulations.gov or in person at the Docket Operations Office 
between 9 a.m. and 5 p.m., Monday through Friday, except Federal 
holidays. The AD docket contains this proposed AD, the foreign 
authority's AD, the economic 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 service information identified in this proposed AD, contact 
American Eurocopter Corporation, 2701 N. Forum Drive, Grand Prairie, TX 
75052; telephone (972) 641-0000 or (800) 232-0323; fax (972) 641-3775; 
or at http://www.eurocopter.com/techpub. You may review service 
information at the FAA, Office of the Regional Counsel, Southwest 
Region, 2601 Meacham Blvd., Room 663, Fort Worth, Texas 76137.

FOR FURTHER INFORMATION CONTACT: Robert Grant, Aviation Safety 
Engineer, Safety Management Group, FAA, 2601 Meacham Blvd., Fort Worth, 
Texas 76137; telephone (817) 222-5110; email robert.grant@faa.gov.

SUPPLEMENTARY INFORMATION:

Comments Invited

    We invite you to participate in this rulemaking by submitting 
written comments, data, or views. We also invite comments relating to 
the economic, environmental, energy, or federalism impacts that might 
result from adopting the proposals in this document. The most helpful 
comments reference a specific portion of the proposal, explain the 
reason for any recommended change, and include supporting data. To 
ensure the docket does not contain duplicate comments, commenters 
should send only one copy of written comments, or if comments are filed 
electronically, commenters should submit only one time.
    We will file in the docket all comments that we receive, as well as 
a report summarizing each substantive public contact with FAA personnel 
concerning this proposed rulemaking. Before acting on this proposal, we 
will consider all comments we receive on or before the closing date for 
comments. We will consider comments filed after the comment period has 
closed if it is possible to do so without incurring expense or delay. 
We may change this proposal in light of the comments we receive.

Discussion

    On October 12, 2011, we issued AD 2011-22-05, Amendment 39-16847 
(76 FR 70046, November 10, 2011) for Eurocopter Model AS350B, B1, B2, 
B3, BA, C, D, D1, AS355E, F, F1, F2, N, and NP helicopters with certain 
T/R control rods installed. AD 2011-22-05 requires the following 
actions:
     Before the first flight of each day, checking the control 
rod bearing for play on the helicopter, by observation and feel, by 
slightly moving the TR blade in the flapping axis while monitoring the 
bearing for movement.
     If the Teflon cloth is coming out of its position within 
the bearing or if there is discoloration or scoring, replacing the 
control rod assembly before further flight.
     If play is detected, having a mechanic remove the control 
rod from the helicopter, and using a dial indicator, measuring the 
control rod bearing wear. If the radial play exceeds 0.008 inch or 
axial play exceeds 0.016 inch, replacing the control rod with an 
airworthy control rod before further flight.
     Thereafter, at intervals not to exceed 30 hours time-in-
service (TIS), repeating the requirement to remove the control rod and 
measuring the bearing for wear using a dial indicator.
    AD 2011-22-05 was prompted by the issuance of AD No. 2010-0006, 
dated January 7, 2010, by the European Aviation Safety Agency (EASA), 
which is the Technical Agent for the Member States of the European 
Union. The EASA AD was issued to correct an unsafe condition for 
certain Eurocopter helicopters. EASA advised that a pilot of a 
Eurocopter Model AS350 helicopter felt slight vibrations in the pedal 
unit in flight. A few minutes later, the vibration level increased and 
the pilot carried out a precautionary autorotation landing. After 
landing, it was discovered that one TR pitch-change link was damaged, 
the tailboom cone was missing, and there was an impact mark on the 
tailboom. Further investigation revealed the affected TR pitch-change 
link showed extensive wear on the ball-joint. EASA advised that this 
condition, if not detected and corrected, could lead to loss of the 
anti-torque function and possible loss of control of the helicopter.

Actions Since AD 2011-22-05 Was Issued

    Since we issued AD 2011-22-05 (76 FR 70046, November 10, 2011), we 
have determined that we can safely extend the compliance time for the 
initial bearing play check and the interval for recurring checks to 30 
hours TIS. We also received several requests for alternative methods of 
compliance regarding the bearing play check, and as a result this 
proposed AD would clarify the requirements of that check. We removed a 
previous requirement that if the Teflon cloth is coming out of its 
normal position within the bearing, or if there is discoloration or 
scoring on the bearing, that the control rod be replaced with an 
airworthy rod before further flight.

FAA's Determination

    These helicopters have been approved by the aviation authority of 
France and are approved for operation in the United States. Pursuant to 
our bilateral agreement with France, EASA, its technical 
representative, has notified us of the unsafe condition described in 
its AD. We are proposing this AD because we evaluated all known 
relevant information and determined that an unsafe condition is likely 
to exist or develop on other products of the same type design.

Related Service Information

    Eurocopter has issued Alert Service Bulletin (ASB) No. 05.00.60 for 
the Model AS350 series helicopters, and ASB No. 05.00.56 for the Model 
AS355 series helicopters, both dated December 9, 2009. These ASBs 
specify performing an initial and recurring check for play in the 
pitch-change links. If axial play in the ball-joint is detectable, the 
ASBs specify removing the pitch-change link and measuring the bearing 
wear using a dial indicator. EASA classified these ASBs as mandatory 
and issued EASA AD No. 2010-0006 to ensure the continued airworthiness 
of these helicopters.

Proposed AD Requirements

    This proposed AD would clarify the requirements of AD 2011-22-05, 
extend the compliance time for the bearing play checks to 30 hours TIS, 
and remove the requirement to replace the control rod if the Teflon 
cloth is out of position or if there is discoloration or scoring on the 
bearing.

Costs of Compliance

    We estimate that this proposed AD would affect 936 helicopters of 
U.S. Registry and that labor costs will average $85 a work-hour. We 
estimate, per helicopter, it will take minimal work-hours to do the 
check, 1 work-hour to measure the bearing play, and 1 work-hour to 
replace 1 control rod. The average labor rate is $85 per work-hour. 
Required parts will cost about

[[Page 59300]]

$1,724 to replace a control rod per helicopter. Based on these figures, 
we estimate the cost of this AD on U.S. operators is minimal for the 
check. Measuring the bearing play, if needed, would cost $85 per 
helicopter, and replacing 1 control rod would cost $1,809 per 
helicopter.

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, 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 to the extent that 
it justifies making a regulatory distinction; 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.
    We prepared an economic evaluation of the estimated costs to comply 
with this proposed AD and placed it in the AD docket.

List of Subjects in 14 CFR Part 39

    Air transportation, Aircraft, Aviation safety, Incorporation by 
reference, Safety.

The Proposed Amendment

    Accordingly, under the authority delegated to me by the 
Administrator, the FAA proposes to amend 14 CFR part 39 as follows:

PART 39--AIRWORTHINESS DIRECTIVES

0
1. The authority citation for part 39 continues to read as follows:

    Authority:  49 U.S.C. 106(g), 40113, 44701.


Sec.  39.13  [Amended]

0
2. The FAA amends Sec.  39.13 by removing Airworthiness Directive (AD) 
2011-22-05, Amendment 39--16847 (76 FR 70046, November 10, 2011), and 
adding the following new AD:

Eurocopter France: Docket No. FAA-2011-1158; Directorate Identifier 
2010-SW-018-AD.

(a) Applicability

    This AD applies to Eurocopter France (Eurocopter) Model AS350B, 
B1, B2, B3, BA, C, D, D1; and Model AS355E, F, F1, F2, N, and NP 
helicopters; with tail rotor (T/R) pitch control rod (control rod), 
part number (P/N) 350A33-2100-00, -01, -02, -03, -04; P/N 350A33-
2121-00, -01, -02; P/N 350A33-2143-00; or P/N 350A33-2145-00 or -01, 
installed; certificated in any category.

(b) Unsafe Condition

    This AD defines the unsafe condition as excessive play in the 
control rod. This condition could result in failure of a T/R control 
rod, loss of T/R control, and subsequent loss of control of the 
helicopter.

(c) Affected ADs

    This AD revises AD 2011-22-05 (76 FR 70046, November 10, 2011), 
Amendment 39-16847, Docket No. FAA-2011-1158, Directorate Identifier 
2010-SW-018-AD.

(d) Comments Due Date

    We must receive comments by November 25, 2013.

(e) Compliance

    You are responsible for performing each action required by this 
AD within the specified compliance time unless it has already been 
accomplished prior to that time.

 (f) Required Actions

    (1) Within 30 hours time-in-service (TIS) and, if no bearing 
play is detected, thereafter at intervals not to exceed 30 hours 
TIS, place the T/R pedals in the neutral position. If the helicopter 
is fitted with a T/R load compensator, discharge the accumulator as 
described in the rotorcraft flight manual. Check the control rod 
bearing (bearing) for play on the helicopter, by observation and 
feel, by slightly moving the T/R blade in the flapping axis while 
monitoring the bearing for movement. See the following Figure 1 to 
Paragraph (f) of this AD. The actions required by this paragraph of 
may be performed by the owner/operator (pilot) holding at least a 
private pilot certificate, and must be entered into the helicopter 
maintenance records showing compliance with this AD in accordance 
with 14 CFR 43.9(a)(1)-(4) and 14 CFR 91.417(a)(2)(v). The record 
must be maintained as required by 14 CFR 91.417, 121.380, or 
135.439.
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    (2) If a pilot or mechanic detects play in the bearing, before 
the next flight, a mechanic must remove the control rod from the 
helicopter, and using a dial indicator, measure the bearing wear 
according to the following and as shown in Figures 2 and 3 to 
Paragraph (f) of this AD:

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[GRAPHIC] [TIFF OMITTED] TP26SE13.010


[[Page 59303]]


[GRAPHIC] [TIFF OMITTED] TP26SE13.011

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    (i) Remove the control rod from the helicopter.
    (ii) Mount the control rod in a vise as shown in Figure 2 to 
Paragraph (f) of this AD.
    (iii) Using a dial indicator, take axial play readings by moving 
the spherical bearing in the direction F (up and down) as shown in 
Figure 2 to Paragraph (f) of this AD.
    (iv) Install a bolt through the bearing and secure it with a 
washer and nut to provide a clamping surface when the bearing is 
clamped in a vise.
    (v) Mount the control rod and bearing in a vise as shown in 
Figure 3 to Paragraph (f) of this AD.
    (vi) Using a dial indicator, take radial play measurements by 
moving the control rod in the direction F as shown in Figure 3 to 
Paragraph (f) of this AD.
    (vii) Record the hours of operation on each control rod.
    (viii) If the radial play exceeds 0.008 inch or axial play 
exceeds 0.016 inch, replace the control rod with an airworthy 
control rod before further flight.
    (ix) If the radial and axial play are within limits, reinstall 
the control rod.
    (x) Thereafter, at intervals not to exceed 30 hours TIS, remove 
the control rod and measure the bearing play with a dial indicator 
in accordance with paragraph (f)(2) of this AD.

 (g) Alternative Methods of Compliance (AMOCs)

    (1) The Manager, Safety Management Group, FAA, may approve AMOCs 
for this AD. Send your proposal to: Robert Grant, Aviation Safety 
Engineer, Safety Management Group, FAA, 2601 Meacham Blvd., Fort 
Worth, Texas 76137; telephone (817) 222-5110; email 
robert.grant@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.
    (3) An AMOC approved previously in accordance with Airworthiness 
Directive No. 2011-22-05, Amendment 39-16847 (76 FR 70046, November 
10, 2011), is approved as an AMOC for the corresponding requirements 
in paragraph (f)(2) of this AD.

(h) Additional Information

    (1) Eurocopter Alert Service Bulletin (ASB) No. 05.00.60 and ASB 
No. 05.00.56, both dated December 9, 2009, which are not 
incorporated by reference, contain additional information about the 
subject of this AD. For service information identified in this AD, 
contact American Eurocopter Corporation, 2701 N. Forum Drive, Grand 
Prairie, TX 75052; telephone (972) 641-0000 or (800) 232-0323; fax 
(972) 641-3775; or at http://www.eurocopter.com/techpub. You may 
review a copy of the service information at the FAA, Office of the 
Regional Counsel, Southwest Region, 2601 Meacham Blvd., Room 663, 
Fort Worth, Texas 76137.
    (2) The subject of this AD is addressed in the European Aviation 
Safety Agency (EASA) AD No. 2010-0006, dated January 7, 2010. You 
may view the EASA AD on the Internet at http://www.regulations.gov 
in Docket No. FAA-2011-1158.

(i) Subject

    Joint Aircraft Service Component (JASC) Code: 6720, Tail rotor 
control system.


    Issued in Fort Worth, Texas, on September 17, 2013.
Gwendolynne O'Connell,
Acting Directorate Manager, Rotorcraft Directorate, Aircraft 
Certification Service.
[FR Doc. 2013-23434 Filed 9-25-13; 8:45 am]
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