Airworthiness Directives; Bell Helicopter Textron Canada, 44147-44149 [2014-17925]

Download as PDF Federal Register / Vol. 79, No. 146 / Wednesday, July 30, 2014 / Proposed Rules no further action is required by this paragraph. (2) If the resistance value is greater than 10 milliOhms at the left-hand or right-hand wing, before further flight, do a general visual inspection for corrosion of the component interface and adjacent area, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A320–57–1152, dated June 14, 2010. If any corrosion is found during the inspection, before further flight, repair the gravity fill fuel adaptor, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A320– 57–1152, dated June 14, 2010; except where Airbus Service Bulletin A320–57–1152, dated June 14, 2010, specifies to contact Airbus, before further flight, repair 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. (h) New Requirement of This AD: Maintenance Check/Electrical Bonding Test and Corrective Action if Necessary For airplanes other than those identified in paragraph (g) of this AD: Within 24 months after the effective date of this AD, determine whether a corrosion repair has been done on an overwing refueling aperture, whereby a primer coating has been applied on the mating surface of the aperture flange. A maintenance records check is acceptable to make this determination, provided those records can conclusively determine whether a primer coat was applied. (1) If it is determined that a primer coating was applied on the mating surface of the aperture flange; or if a determination cannot be made, or the outcome is inconclusive: Within 24 months after the effective date of this AD do the electrical bonding test specified in paragraph (g) of this AD, and before further flight, all applicable actions specified in paragraph (g)(2) of this AD. (2) If it is determined that a corrosion repair has not been done, and a primer coating has not been applied on the mating surface of the aperture flange since first entry into service, no further action is required by this paragraph. pmangrum on DSK3VPTVN1PROD with PROPOSALS (i) Corrosion Repair Provision As of the effective date of this AD, any corrosion repair done on an overwing refueling aperture on any airplane must be compliant with the repair requirements of paragraph (g)(2) of this AD. (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: VerDate Mar<15>2010 14:57 Jul 29, 2014 Jkt 232001 Sanjay Ralhan, Aerospace Engineer, International Branch, ANM–116, Transport Airplane Directorate, FAA, 1601 Lind Avenue SW., Renton, WA 98057–3356; telephone (425) 227–1405; fax (425) 227– 1149. Information may be emailed to: 9ANM-116-AMOC-REQUESTS@faa.gov. (i) 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. (ii) AMOCs approved previously for AD 2012–09–07, Amendment 39–17042 (77 FR 28238, May 14, 2012), are approved as AMOCs for the corresponding provisions of this AD. (2) Contacting the Manufacturer: For any requirement in this AD to obtain corrective actions from a manufacturer, the action must be accomplished using a method approved by the Manager, International 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 2013–0277R1, dated December 4, 2013, 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–2014–0484. (2) For service information identified in this AD, contact Airbus, Airworthiness Office—EAS, 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex, France; telephone +33 5 61 93 36 96; fax +33 5 61 93 44 51; email account.airworth-eas@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 July 13, 2014. Jeffrey E. Duven, Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 2014–17930 Filed 7–29–14; 8:45 am] BILLING CODE 4910–13–P PO 00000 Frm 00006 Fmt 4702 Sfmt 4702 44147 DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2014–0499; Directorate Identifier 2013–SW–061–AD] RIN 2120–AA64 Airworthiness Directives; Bell Helicopter Textron Canada Federal Aviation Administration (FAA), DOT. ACTION: Notice of proposed rulemaking (NPRM). AGENCY: We propose to adopt a new airworthiness directive (AD) for Bell Helicopter Textron Canada (BHTC) Model 430 helicopters to require inspecting the tail rotor control tube assembly (control tube) and either repairing or replacing the control tube. This proposed AD is prompted by two reports of failure of the control tube bonded clevis. The proposed actions are intended to prevent failure of a control tube bonded clevis, which could lead to failure of the control tube and subsequent loss of helicopter control. DATES: We must receive comments on this proposed AD by September 29, 2014. 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 p.m., Monday through Friday, except Federal holidays. SUMMARY: 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 Bell E:\FR\FM\30JYP1.SGM 30JYP1 44148 Federal Register / Vol. 79, No. 146 / Wednesday, July 30, 2014 / Proposed Rules Helicopter Textron Canada Limited, 12,800 Rue de l’Avenir, Mirabel, Quebec J7J1R4; telephone (450) 437–2862 or (800) 363–8023; fax (450) 433–0272; or at http://www.bellcustomer.com/files/. You may review the referenced 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: Matt Fuller, Senior Aviation Safety Engineer, Safety Management Group, Rotorcraft Directorate, FAA, 2601 Meacham Blvd., Fort Worth, Texas 76137; telephone (817) 222–5110; email matthew.fuller@ faa.gov. SUPPLEMENTARY INFORMATION: pmangrum on DSK3VPTVN1PROD 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 proposal in light of the comments we receive. Discussion Transport Canada Civil Aviation (TCCA), which is the aviation authority for Canada, has issued Canadian AD No. CF–2013–30, dated October 7, 2013, to correct an unsafe condition for BHTC Model 430 helicopters with control tube part number (P/N) 430–001–007–101. TCCA advises of two cases concerning failures of the control tube bonded clevis caused by cracking from control tube oscillation. TCCA states that this situation, if not corrected, could result in the loss of control of the helicopter. TCCA AD No. CF–2013–30 consequently requires a one-time VerDate Mar<15>2010 14:57 Jul 29, 2014 Jkt 232001 inspection of the control tube for damage and contacting BHTC for evaluation of the control tube if the damage exceeds allowable limits. If the tube is not damaged, the damage is within allowable limits, or BHTC Engineering determines the control tube can be returned to service, TCCA AD No. CF–2013–30 requires modifying the tube according to BHTC’s service information. TCCA AD No. CF–2013–30 also requires replacing control tubes, P/N 430–001–007–101, with control tube, P/N 430–001–007–105, no later than 12 months from the effective date of its AD. • Within 250 hours TIS after the effective date of this AD, replacing each control tube, P/N 430–001–007–101, with control tube, P/N 430–001–007– 105. FAA’s Determination These helicopters have been approved by the aviation authority of Canada and are approved for operation in the United States. Pursuant to our bilateral agreement with Canada, TCCA, 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. We estimate that this proposed AD would affect 5 helicopters of U.S. Registry and that labor costs average $85 a work hour. Based on these estimates, expect the following costs: • The cost of inspecting the control tube would be minimal. • Repairing the control tube would require 2 work-hours for a labor cost of $170. • Replacing control tube, P/N 430– 001–007–101, with control tube, P/N 430–001–007–105, would require 3 work-hours for a labor cost of $255. Parts would cost $3,974 for a total cost per helicopter of $4,229. Related Service Information We reviewed Bell Helicopter Alert Service Bulletin No. 430–13–51, dated September 3, 2013 (ASB), which states that BHTC received two reports of control tube, P/N 430–001–007–101, failing because the clevis failed due to fatigue caused by control tube oscillation. The ASB specifies a onetime inspection of control tube assembly, P/N 430–001–007–101, to verify if the tube has chaffing damage. Bell Helicopter Technical Bulletin 430– 04–35, Revision B, dated March 20, 2009, recommends that control tube, P/N 430–001–007–101, be replaced with control tube, P/N 430–001–007–105, if damage exists. Proposed AD Requirements This proposed AD would require: • Within 50 hours time-in-service (TIS), visually inspecting each control tube for damage, damage to the clevis, and to determine whether the clevis is correctly bonded to the control tube. • If a control tube and clevis have no damage or damage within acceptable limits and the clevis is correctly bonded to the control tube, repairing the control tube by applying tape. • If the control tube or clevis is damaged beyond acceptable limits or if the clevis is not correctly bonded, replacing control tube, P/N 430–001– 007–101, with control tube, P/N 430– 001–007–105. PO 00000 Frm 00007 Fmt 4702 Sfmt 4702 Differences Between This Proposed AD and the TCCA AD The TCCA AD requires submitting sketches of a control tube damaged beyond defined limits to BHTC for evaluation. BHTC then determines if the control tube can be returned to service. We make no such requirement in this proposed AD. Costs of Compliance 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 E:\FR\FM\30JYP1.SGM 30JYP1 Federal Register / Vol. 79, No. 146 / Wednesday, July 30, 2014 / Proposed Rules 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 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. Amend § 39.13 by adding the following new airworthiness directive (AD): ■ Bell Helicopter Textron Canada: Docket No. FAA–2014–0499; Directorate Identifier 2013–SW–061–AD. pmangrum on DSK3VPTVN1PROD with PROPOSALS (a) Applicability This AD applies to Bell Helicopter Textron Canada (BHTC) Model 430 Helicopters, serial number 49001 through 49121, with control tube assembly (control tube), part number (P/N) 430–001–007–101, installed, certificated in any category. (b) Unsafe Condition This AD defines the unsafe condition as fatigue failure of a tail rotor control tube bonded clevis. This condition could result in failure of the tail rotor control tube and subsequent loss of helicopter control. (c) Comments Due Date We must receive comments by September 29, 2014. (d) 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. VerDate Mar<15>2010 14:57 Jul 29, 2014 Jkt 232001 (e) Required Actions (1) Within 50 hours time-in-service (TIS), visually inspect each control tube for any damage, for any damage to the clevis, and to determine whether the clevis is correctly bonded to the control tube. (i) If a control tube and clevis have no damage or damage within acceptable limits and the clevis is correctly bonded to the control tube, repair the control tube by applying tape in accordance the Accomplishment Instructions, Paragraph 5, of Bell Helicopter Alert Service Bulletin 430– 13–51, dated September 3, 2013. (ii) If the control tube or clevis is damaged beyond acceptable limits or if the clevis is not correctly bonded to the control tube, replace control tube, P/N 430–001–007–101, with control tube, P/N 430–001–007–105. (2) Within 250 hours TIS, replace each control tube, P/N 430–001–007–101, with control tube, P/N 430–001–007–105. (f) Alternative Methods of Compliance (AMOCs) (1) The Manager, Safety Management Group, FAA, may approve AMOCs for this AD. Send your proposal to: Matt Fuller, Senior Aviation Safety Engineer, Safety Management Group, Rotorcraft Directorate, FAA, 2601 Meacham Blvd., Fort Worth, Texas 76137; telephone (817) 222–5110; email matthew.fuller@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. (g) Additional Information (1) Bell Helicopter Technical Bulletin 430– 04–35, Revision B, dated March 20, 2009, which is not incorporated by reference, contains additional information about the subject of this AD. For service information, contact Bell Helicopter Textron Canada Limited, 12,800 Rue de l’Avenir, Mirabel, Quebec J7J1R4; telephone (450) 437–2862 or (800) 363–8023; fax (450) 433–0272; or at http://www.bellcustomer.com/files/. You may review the referenced 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 Transport Canada Civil Aviation (TCCA) AD No. CF–2013–30, dated October 7, 2013. You may view the TCCA AD on the Internet at http://www.regulations.gov in Docket No. FAA–2014–0499. (h) Subject Joint Aircraft Service Component (JASC) Code: 6720, Tail Rotor Control System. Issued in Fort Worth, Texas, on July 18, 2014. S. Frances Cox, Acting Directorate Manager, Rotorcraft Directorate, Aircraft Certification Service. [FR Doc. 2014–17925 Filed 7–29–14; 8:45 am] BILLING CODE 4910–13–P PO 00000 Frm 00008 Fmt 4702 Sfmt 4702 44149 DEPARTMENT OF THE INTERIOR Bureau of Indian Affairs [K00103 12/13 A3A10; 134D0102DR– DS5A300000–DR.5A311.IA000113] 25 CFR Part 83 RIN 1076–AF18 Federal Acknowledgment of American Indian Tribes Bureau of Indian Affairs, Interior. ACTION: Proposed rule; extension of comment period. AGENCY: On May 22, 2014, the Department of the Interior announced the availability of a proposed rule to revise regulations governing the process and criteria by which the Secretary acknowledges an Indian tribe. We have since received several requests for extension of the comment period and additional public hearings. This notice extends the comment deadline by 60 days and announces the addition of two more public hearings and two more tribal consultation sessions on the proposed rule. DATES: Comments on this rule must be received by September 30, 2014. See the SUPPLEMENTARY INFORMATION section of this notice for information on the public hearings and tribal consultations. ADDRESSES: You may submit comments by any of the following methods: • Federal rulemaking portal: http:// www.regulations.gov. The rule is listed under the agency name ‘‘Bureau of Indian Affairs.’’ The rule has been assigned Docket ID: BIA–2013–0007. • Email: consultation@bia.gov. Include the number 1076–AF18 in the subject line. • Mail or hand delivery: Elizabeth Appel, Office of Regulatory Affairs & Collaborative Action, U.S. Department of the Interior, 1849 C Street NW., MS 3642, Washington, DC 20240. Include the number 1076–AF18 on the envelope. Please note that we will not consider or include in the docket for this rulemaking comments received after the close of the comment period (see DATES) or comments sent to an address other than those listed above. FOR FURTHER INFORMATION CONTACT: Ms. Elizabeth Appel, Director, Office of Regulatory Affairs & Collaborative Action, (202) 273–4680; elizabeth.appel@bia.gov. SUPPLEMENTARY INFORMATION: On May 22, 2014, we announced the availability of a proposed rule to revise regulations governing the process and criteria by SUMMARY: E:\FR\FM\30JYP1.SGM 30JYP1

Agencies

[Federal Register Volume 79, Number 146 (Wednesday, July 30, 2014)]
[Proposed Rules]
[Pages 44147-44149]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 2014-17925]


-----------------------------------------------------------------------

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2014-0499; Directorate Identifier 2013-SW-061-AD]
RIN 2120-AA64


Airworthiness Directives; Bell Helicopter Textron Canada

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Notice of proposed rulemaking (NPRM).

-----------------------------------------------------------------------

SUMMARY: We propose to adopt a new airworthiness directive (AD) for 
Bell Helicopter Textron Canada (BHTC) Model 430 helicopters to require 
inspecting the tail rotor control tube assembly (control tube) and 
either repairing or replacing the control tube. This proposed AD is 
prompted by two reports of failure of the control tube bonded clevis. 
The proposed actions are intended to prevent failure of a control tube 
bonded clevis, which could lead to failure of the control tube and 
subsequent loss of helicopter control.

DATES: We must receive comments on this proposed AD by September 29, 
2014.

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 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 
Bell

[[Page 44148]]

Helicopter Textron Canada Limited, 12,800 Rue de l'Avenir, Mirabel, 
Quebec J7J1R4; telephone (450) 437-2862 or (800) 363-8023; fax (450) 
433-0272; or at http://www.bellcustomer.com/files/. You may review the 
referenced 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: Matt Fuller, Senior Aviation Safety 
Engineer, Safety Management Group, Rotorcraft Directorate, FAA, 2601 
Meacham Blvd., Fort Worth, Texas 76137; telephone (817) 222-5110; email 
matthew.fuller@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

    Transport Canada Civil Aviation (TCCA), which is the aviation 
authority for Canada, has issued Canadian AD No. CF-2013-30, dated 
October 7, 2013, to correct an unsafe condition for BHTC Model 430 
helicopters with control tube part number (P/N) 430-001-007-101. TCCA 
advises of two cases concerning failures of the control tube bonded 
clevis caused by cracking from control tube oscillation. TCCA states 
that this situation, if not corrected, could result in the loss of 
control of the helicopter. TCCA AD No. CF-2013-30 consequently requires 
a one-time inspection of the control tube for damage and contacting 
BHTC for evaluation of the control tube if the damage exceeds allowable 
limits. If the tube is not damaged, the damage is within allowable 
limits, or BHTC Engineering determines the control tube can be returned 
to service, TCCA AD No. CF-2013-30 requires modifying the tube 
according to BHTC's service information. TCCA AD No. CF-2013-30 also 
requires replacing control tubes, P/N 430-001-007-101, with control 
tube, P/N 430-001-007-105, no later than 12 months from the effective 
date of its AD.

FAA's Determination

    These helicopters have been approved by the aviation authority of 
Canada and are approved for operation in the United States. Pursuant to 
our bilateral agreement with Canada, TCCA, 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

    We reviewed Bell Helicopter Alert Service Bulletin No. 430-13-51, 
dated September 3, 2013 (ASB), which states that BHTC received two 
reports of control tube, P/N 430-001-007-101, failing because the 
clevis failed due to fatigue caused by control tube oscillation. The 
ASB specifies a one-time inspection of control tube assembly, P/N 430-
001-007-101, to verify if the tube has chaffing damage. Bell Helicopter 
Technical Bulletin 430-04-35, Revision B, dated March 20, 2009, 
recommends that control tube, P/N 430-001-007-101, be replaced with 
control tube, P/N 430-001-007-105, if damage exists.

Proposed AD Requirements

    This proposed AD would require:
     Within 50 hours time-in-service (TIS), visually inspecting 
each control tube for damage, damage to the clevis, and to determine 
whether the clevis is correctly bonded to the control tube.
     If a control tube and clevis have no damage or damage 
within acceptable limits and the clevis is correctly bonded to the 
control tube, repairing the control tube by applying tape.
     If the control tube or clevis is damaged beyond acceptable 
limits or if the clevis is not correctly bonded, replacing control 
tube, P/N 430-001-007-101, with control tube, P/N 430-001-007-105.
     Within 250 hours TIS after the effective date of this AD, 
replacing each control tube, P/N 430-001-007-101, with control tube, P/
N 430-001-007-105.

Differences Between This Proposed AD and the TCCA AD

    The TCCA AD requires submitting sketches of a control tube damaged 
beyond defined limits to BHTC for evaluation. BHTC then determines if 
the control tube can be returned to service. We make no such 
requirement in this proposed AD.

Costs of Compliance

    We estimate that this proposed AD would affect 5 helicopters of 
U.S. Registry and that labor costs average $85 a work hour. Based on 
these estimates, expect the following costs:
     The cost of inspecting the control tube would be minimal.
     Repairing the control tube would require 2 work-hours for 
a labor cost of $170.
     Replacing control tube, P/N 430-001-007-101, with control 
tube, P/N 430-001-007-105, would require 3 work-hours for a labor cost 
of $255. Parts would cost $3,974 for a total cost per helicopter of 
$4,229.

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

[[Page 44149]]

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. Amend Sec.  39.13 by adding the following new airworthiness 
directive (AD):

Bell Helicopter Textron Canada: Docket No. FAA-2014-0499; 
Directorate Identifier 2013-SW-061-AD.

(a) Applicability

    This AD applies to Bell Helicopter Textron Canada (BHTC) Model 
430 Helicopters, serial number 49001 through 49121, with control 
tube assembly (control tube), part number (P/N) 430-001-007-101, 
installed, certificated in any category.

(b) Unsafe Condition

    This AD defines the unsafe condition as fatigue failure of a 
tail rotor control tube bonded clevis. This condition could result 
in failure of the tail rotor control tube and subsequent loss of 
helicopter control.

(c) Comments Due Date

    We must receive comments by September 29, 2014.

(d) 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.

(e) Required Actions

    (1) Within 50 hours time-in-service (TIS), visually inspect each 
control tube for any damage, for any damage to the clevis, and to 
determine whether the clevis is correctly bonded to the control 
tube.
    (i) If a control tube and clevis have no damage or damage within 
acceptable limits and the clevis is correctly bonded to the control 
tube, repair the control tube by applying tape in accordance the 
Accomplishment Instructions, Paragraph 5, of Bell Helicopter Alert 
Service Bulletin 430-13-51, dated September 3, 2013.
    (ii) If the control tube or clevis is damaged beyond acceptable 
limits or if the clevis is not correctly bonded to the control tube, 
replace control tube, P/N 430-001-007-101, with control tube, P/N 
430-001-007-105.
    (2) Within 250 hours TIS, replace each control tube, P/N 430-
001-007-101, with control tube, P/N 430-001-007-105.

(f) Alternative Methods of Compliance (AMOCs)

    (1) The Manager, Safety Management Group, FAA, may approve AMOCs 
for this AD. Send your proposal to: Matt Fuller, Senior Aviation 
Safety Engineer, Safety Management Group, Rotorcraft Directorate, 
FAA, 2601 Meacham Blvd., Fort Worth, Texas 76137; telephone (817) 
222-5110; email matthew.fuller@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.

(g) Additional Information

    (1) Bell Helicopter Technical Bulletin 430-04-35, Revision B, 
dated March 20, 2009, which is not incorporated by reference, 
contains additional information about the subject of this AD. For 
service information, contact Bell Helicopter Textron Canada Limited, 
12,800 Rue de l'Avenir, Mirabel, Quebec J7J1R4; telephone (450) 437-
2862 or (800) 363-8023; fax (450) 433-0272; or at http://www.bellcustomer.com/files/. You may review the referenced 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 Transport Canada 
Civil Aviation (TCCA) AD No. CF-2013-30, dated October 7, 2013. You 
may view the TCCA AD on the Internet at http://www.regulations.gov 
in Docket No. FAA-2014-0499.

(h) Subject

    Joint Aircraft Service Component (JASC) Code: 6720, Tail Rotor 
Control System.

    Issued in Fort Worth, Texas, on July 18, 2014.
S. Frances Cox,
Acting Directorate Manager, Rotorcraft Directorate, Aircraft 
Certification Service.
[FR Doc. 2014-17925 Filed 7-29-14; 8:45 am]
BILLING CODE 4910-13-P