Airworthiness Directives; Bell Helicopter Textron Canada Helicopters, 18970-18973 [2012-7542]

Download as PDF 18970 Federal Register / Vol. 77, No. 61 / Thursday, March 29, 2012 / Proposed Rules Proposed AD Requirements This proposed AD would require, for S–76C model helicopters with serial numbers 760506 and 760607 through 760812, within 6 months after the effective date of the proposed AD, installing an improved throttle stop and a wider trigger on each ECL as specified in the ASB. Differences Between This Proposed AD and the Service Information The Sikorsky ASB requires installation of the modifications on or before March 7, 2012. The proposed AD requires installation within 6 months after the effective date of the AD. Costs of Compliance We estimate that this proposed AD would affect 52 helicopters of U.S. Registry. We estimate that operators may incur the following costs in order to comply with this AD. To replace the engine control lever stop and trigger assemblies will require 2 work-hours at an average labor cost of $85 per hour. Required parts will cost about $939. Based upon these costs, we estimate a total cost of $1,109 per helicopter and a total cost of $57,668 for the entire U.S. operator fleet. Authority for This Rulemaking mstockstill on DSK4VPTVN1PROD with PROPOSALS 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 VerDate Mar<15>2010 17:03 Mar 28, 2012 Jkt 226001 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: (e) 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, Aerospace Engineer, FAA, Boston Aircraft Certification Office, Engine and Propeller Directorate, 12 New England Executive Park, Burlington, MA 01803; telephone (781) 238–7190; email kirk.gustafson@faa.gov. (2) For operations conducted under a Part 119 operating certificate or under 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. (f) Subject Joint Aircraft Service Component (JASC) Code: 7600: Engine Controls. Issued in Fort Worth, Texas, on March 20, 2012. Kim Smith, Manager, Rotorcraft Directorate, Aircraft Certification Service. [FR Doc. 2012–7541 Filed 3–28–12; 8:45 am] PART 39—AIRWORTHINESS DIRECTIVES BILLING CODE 4910–13–P 1. The authority citation for part 39 continues to read as follows: Authority: 49 U.S.C. 106(g), 40113, 44701. § 39.13 lever and perform a throttle position check as specified in the Accomplishment Instructions, Sections 3.A and 3.B, of Sikorsky Alert Service Bulletin No. 76–76– 6A Revision A, dated May 18, 2011. [Amended] DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 2. The FAA amends § 39.13 by adding the following new Airworthiness Directive (AD): 14 CFR Part 39 Sikorsky Aircraft Corporation: Docket No. FAA–2012–0340; Directorate Identifier 2011–SW–073–AD. RIN 2120–AA64 (a) Applicability This AD applies to Sikorsky Aircraft Corporation (Sikorsky) Model S–76C helicopters, serial numbers 760506 and 760607 through 760812, certificated in any category. (b) Unsafe Condition This AD defines the unsafe condition as unintended movement of the engine control levers due to an external force to the windshield or canopy. This condition could result in significantly reduced engine power, unrecoverable loss of main rotor speed, and subsequent loss of control of the helicopter. (c) Compliance You are responsible for performing each action required by this AD within the specified compliance time unless accomplished previously. (d) Required Action Within 6 months, replace the throttle stop and trigger assembly on each engine control PO 00000 Frm 00008 Fmt 4702 Sfmt 4702 [Docket No. FAA–2012–0337; Directorate Identifier 2010–SW–090–AD] Airworthiness Directives; Bell Helicopter Textron Canada Helicopters Federal Aviation Administration (FAA), DOT. ACTION: Notice of proposed rulemaking (NPRM). AGENCY: We propose to adopt a new airworthiness directive (AD) for the Bell Helicopter Textron Canada Limited (BHTC) Model 407 helicopters. This proposed AD is prompted by a review of the tailboom-attachment installation, which revealed that the torque value of the bolts specified in the BHTC Model 407 Maintenance Manual and applied during manufacturing was incorrect and exceeded the torque range recommended for the bolts. This proposed AD would require you to replace tailboom-attachment hardware (attachment hardware), and perform initial and recurring determinations of SUMMARY: E:\FR\FM\29MRP1.SGM 29MRP1 mstockstill on DSK4VPTVN1PROD with PROPOSALS Federal Register / Vol. 77, No. 61 / Thursday, March 29, 2012 / Proposed Rules the torque on the nuts of the tailboomattachment bolts (bolts) at all four attachment locations. The actions required by this proposed AD are intended to prevent an over-torque of a bolt, bolt failure, loss of the tailboom, and subsequent loss of control of the helicopter. DATES: We must receive comments on this proposed AD by May 29, 2012. 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 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 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 copies of 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: Sharon Miles, Aerospace Engineer, FAA, Regulations and Policy Group, 2601 Meacham Blvd., Fort Worth, Texas 76137; telephone: (817) 222–5122; fax: (817) 222–5961; email: sharon.y.miles@ 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 VerDate Mar<15>2010 17:03 Mar 28, 2012 Jkt 226001 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, which is the aviation authority for Canada, has issued AD No. CF–2010–33, dated September 30, 2010 (AD CF–2010–33), to correct an unsafe condition for the BHTC Model 407 helicopter, serial numbers (S/Ns) 53000 through 53990. Transport Canada advises that a review of the tailboom-attachment installation determined that the torque value of the bolts specified in the BHTC Model 407 Maintenance Manual and applied during manufacturing exceeded the torque range recommended for the bolts. Transport Canada states that this situation, if not corrected, could lead to a bolt failure, detachment of the tailboom, and subsequent loss of control of the helicopter. 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, Transport Canada, its technical representative, has notified us of the unsafe condition described in its AD. FAA’s Determination We are proposing this AD because we evaluated all known relevant information and determined that an unsafe condition exists and is likely to exist or develop on other products of the same type design. Related Service Information BHTC has issued Alert Service Bulletin No. 407–10–93, Revision A, dated August 30, 2010 (ASB), which PO 00000 Frm 00009 Fmt 4702 Sfmt 4702 18971 specifies installing new attachment hardware with a reduced torque value. This ASB specifies performing a torque check of the newly installed bolts and nuts every one to five flight hours until torque stabilizes at all locations, and thereafter at intervals not to exceed 300 flight hours. Transport Canada classified this ASB as mandatory and issued AD CF–2010–33 to ensure the continued airworthiness of these helicopters. Proposed AD Requirements This proposed AD would require for helicopters with 7000 hours or less time-in-service (TIS), at the next 600 hours scheduled inspection, or 90 days, whichever comes first; and for helicopters with more than 7000 hours TIS, within 150 hours TIS or 90 days, whichever comes first, the following actions: • Remove the left upper bolt, washers, and nut. Install a new bolt, part number (P/N) NAS627–30; washers, P/N 140–007–29S25E6 and P/N NAS1149G0732P; and new nut, P/N 42FLW–720. Repeat this action for the opposite right upper attachment hardware. • Remove the left lower bolt, washers, and nut. Install a new bolt, P/N NAS626–26; washer, P/N 140–007– 25S22E6, washer(s), P/N NAS1149G0663P; and new nut, P/N 42FLW–624. Repeat this action for the opposite right lower attachment hardware. • After installation of the new attachment hardware, at intervals of not less than 1 hour TIS but not exceeding 5 hours TIS, determine the torque of each nut until torque stabilizes at each attachment location. Thereafter, determine the torque of each nut at recurring intervals not to exceed 300 hours TIS. If the proper torque has not been retained since the last torquing, remove and inspect the tailboom assembly for damage, corrosion, improper assembly, and condition. If the tailboom assembly is airworthy, replace the attachment hardware and determine that the torque has stabilized at each attachment location. Replace any unairworthy tailboom assembly with an airworthy tailboom assembly before further flight. Differences Between This Proposed AD and the Transport Canada AD The differences between this proposed AD and the Transport Canada AD are as follows: • This proposed AD uses the term ‘‘hours time-in-service’’ to describe compliance times, and the Transport Canada AD uses the term ‘‘air time’’; E:\FR\FM\29MRP1.SGM 29MRP1 18972 Federal Register / Vol. 77, No. 61 / Thursday, March 29, 2012 / Proposed Rules • For helicopters with 7000 hours or less TIS, the Transport Canada AD requires accomplishing the actions in the AD at the next scheduled 600-hour inspection or by December 31, 2010, whichever occurs first. This proposed AD requires accomplishing the actions at the next scheduled 600-hour inspection or 90 days, whichever occurs first. • This proposed AD uses the term ‘‘determine the torque’’ when referring to the torque on a nut, and the Transport Canada AD uses the term ‘‘perform a torque check.’’ mstockstill on DSK4VPTVN1PROD with PROPOSALS Costs of Compliance We estimate that this proposed AD would affect 552 helicopters of U.S. registry. We estimate it would take about 2.0 work-hours per helicopter to replace the hardware and 1.0 work-hour per helicopter to determine the recurring torque value at an average labor rate of $85 per work hour. Required parts would cost about $498 per helicopter. Based on these figures, we estimate for the first year the total cost per helicopter to be $923, and the total cost impact on U.S. operators to be $509,496. This estimated total cost assumes attachment hardware will be replaced on all affected helicopters, the torque will be considered stabilized after determining the torque value once, and the 300-hour TIS recurring torque determination will be accomplished twice a year. 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 VerDate Mar<15>2010 17:03 Mar 28, 2012 Jkt 226001 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 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 adding the following new Airworthiness Directive (AD): Bell Helicopter Textron Canada (BHTC): Docket No. FAA–2012–0337; Directorate Identifier 2010–SW–090–AD. (a) Applicability BHTC Model 407 helicopters, serial numbers 53000 through 53990, certificated in any category. (b) Unsafe Condition This proposed AD defines the unsafe condition as an incorrect torque value of the tailboom attachment bolt (bolt) specified in the BHTC Model 407 Maintenance Manual and applied during manufacturing, which exceeds the torque range recommended for the bolts. This condition could result in an over-torque of the bolt, bolt failure, loss of the tailboom, and subsequent loss of control of the helicopter. (c) Compliance You are responsible for performing each action required by this AD within the PO 00000 Frm 00010 Fmt 4702 Sfmt 4702 specified compliance time unless accomplished previously. (d) Required Actions (1) For helicopters with 7000 hours or less time-in-service (TIS), at the next 600 hours scheduled inspection, or 90 days, whichever comes first; and for helicopters with more than 7000 hours TIS, within 150 hours TIS or 90 days, whichever comes first, replace the tailboom-attachment hardware (attachment hardware) as follows: (i) Remove the left upper bolt, washers, and nut. (ii) Install a new bolt, part number (P/N) NAS627–30; washer, P/N 140–007– 29S25E6; washer(s), P/N NAS1149G0732P; and new nut, P/N 42FLW–720 in accordance with paragraphs 2.a) through paragraph 3.e) of the ‘‘Accomplishment Instructions: Replacement of tailboom attachment bolts and nuts’’ section and Figure 2 in the BHTC Alert Service Bulletin No. 407–10–93, Revision A, dated August 30, 2010 (ASB). (iii) Remove the opposite right upper bolt, washers, and nut, and accomplish the requirements in paragraph (d)(1)(ii) of this AD. (iv) Remove the left lower bolt, washers, and nut. (v) Install a new bolt, (P/N) NAS626–26; washer, P/N 140–007–25S22E6; washer(s), P/N NAS1149G0663P; and new nut, P/N 42FLW–624 in accordance with paragraphs 6.a) through 7.e) of the ‘‘Accomplishment Instructions: Replacement of tailboom attachment bolts and nuts’’ section and Figure 2 in the ASB. (vi) Remove the right lower bolt, washers, and nut, and accomplish the requirements in paragraph (d)(1)(v) of this AD. (2) After installation of the new attachment hardware, at intervals of not less than 1 hour TIS but not exceeding 5 hours TIS, determine the torque of each nut until the torque stabilizes at each attachment location, referring to Figure 2 of the ASB. Apply the minimum specified torque of the range, plus the minimum acceptable tare torque of 14 inch/lbs (1.58 Nm) for the upper nuts, and 9.5 inch/lbs (1.07 Nm) for the lower nuts. (3) At intervals not to exceed 300 hours TIS, determine the torque of each of the four attachment nuts, referring to Figure 2 of the ASB. Apply the minimum specified torque of the range plus the minimum acceptable tare torque of 14 inch/lbs (1.58 Nm) for the upper nuts, and 9.5 inch/lbs (1.07 Nm) for the lower nuts. If the proper torque has not been retained since the last torque determination, remove and inspect the tailboom assembly for damage, corrosion, improper assembly, and condition. If the tailboom assembly is airworthy, replace the attachment hardware in accordance with the requirements in paragraphs (d)(1)(i) through (d)(1)(vi) and determine that the torque has stabilized in accordance with paragraph (2) of this AD. Replace any unairworthy tailboom assembly with an airworthy tailboom assembly. (e) Alternative Methods of Compliance (AMOC) (1) The Manager, Safety Management Group, FAA, may approve AMOCs for this AD. Send your proposal to: Sharon Miles, E:\FR\FM\29MRP1.SGM 29MRP1 Federal Register / Vol. 77, No. 61 / Thursday, March 29, 2012 / Proposed Rules 2601 Meacham Blvd., Fort Worth, Texas 76137; telephone: (817) 222–5122; fax: 817– 222–5961; email: sharon.y.miles@faa.gov. (2) For operations conducted under a Part 119 operating certificate or under 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. (f) Additional Information The subject of this AD is addressed in the Transport Canada Civil Aviation (TCCA) AD CF–2010–33, dated September 30, 2010. (g) Subject Joint Aircraft Service Component (JASC) Code: 5302, Rotorcraft tailboom. Issued in Fort Worth, Texas, on March 21, 2012. Kim Smith, Manager, Rotorcraft Directorate, Aircraft Certification Service. [FR Doc. 2012–7542 Filed 3–28–12; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF LABOR Occupational Safety and Health Administration 29 CFR Parts 1910, 1915, 1917, 1926, and 1928 [Docket Nos. OSHA–2010–0058, OSHA– 2010–0059] RIN 1218–AC51 Reinforced Concrete in Construction, and Preventing Backover Injuries and Fatalities Occupational Safety and Health Administration (OSHA), Labor. ACTION: Request for information (RFI). AGENCY: OSHA is aware of employee safety risks in two areas, reinforcing operations in concrete work (construction only) and fatal backovers by vehicles and equipment (all industries), and is requesting information from the public on these risks. This RFI requests information that will assist the Agency in determining what steps, if any, it can take to prevent injuries and fatalities in these two areas. DATES: Submit comments and other information by June 27, 2012. All submissions must bear a postmark or provide other evidence of the submission date. ADDRESSES: Submit comments and additional materials using any of the following methods (submissions relating to Reinforced Concrete in Construction to Docket No. OSHA–2010–0058, and submissions relating to Preventing mstockstill on DSK4VPTVN1PROD with PROPOSALS SUMMARY: VerDate Mar<15>2010 17:03 Mar 28, 2012 Jkt 226001 Backover Injuries and Fatalities to Docket No. OSHA–2010–0059): Electronically. Submit comments and attachments electronically at http:// www.regulations.gov, which is the Federal eRulemaking Portal. Follow the instructions online for making electronic submissions. Facsimile. Commenters may fax submissions, including attachments, that are no longer than 10 pages in length to the OSHA Docket Office at (202) 693–1648; OSHA does not require hard copies of these documents. Commenters must submit lengthy attachments that supplement these documents (e.g., studies, journal articles) to the OSHA Docket Office, Technical Data Center, Room N–2625, U.S. Department of Labor, 200 Constitution Ave., NW., Washington, DC 20210. These attachments must clearly identify the commenter’s name, date, subject, and docket number (i.e., for Reinforced Concrete in Construction, OSHA–2010–0058, and for Preventing Backover Injuries and Fatalities, OSHA– 2010–0059) so the Agency can attach them to the appropriate comments. Regular mail, express delivery, hand (courier) delivery, or messenger service. Submit a copy of comments and any additional material (e.g., studies, journal articles) to the OSHA Docket Office, Docket No. OSHA–2010–0058 (for Reinforced Concrete in Construction), Technical Data Center, Room N–2625, U.S. Department of Labor, 200 Constitution Avenue NW., Washington, DC 20210; telephone (202) 693–2350 (TDY number: (877) 889–5627). For submissions relating to Preventing Backover Injuries and Fatalities, please identify the docket number as OSHA– 2010–0059. Note that security procedures may result in significant delays in receiving comments and other written materials by regular mail. Contact the OSHA Docket Office for information about security procedures concerning delivery of materials by express delivery, hand delivery, or messenger service. The hours of operation for the OSHA Docket Office are 8:15 a.m.–4:45 p.m., e.t. Instructions. All submissions must include the Agency name and the OSHA docket number for this rulemaking; i.e., for Reinforced Concrete in Construction, Docket No. OSHA–2010–0058, and for Preventing Backover Injuries and Fatalities, Docket No. OSHA–2010– 0059. The Agency places all submissions, including any personal information provided, in the public docket without change; this information will be available online at http:// www.regulations.gov. Therefore, the Agency cautions commenters about PO 00000 Frm 00011 Fmt 4702 Sfmt 4702 18973 submitting information they do not want made available to the public, or submitting comments that contain personal information (either about themselves or others) such as Social Security numbers, birth dates, and medical data. Docket. To read or download submissions or other material in the docket, go to http:// www.regulations.gov, or to the OSHA Docket Office at the address above. While the Agency lists all documents in the docket in the http:// www.regulations.gov index, some information (e.g., copyrighted material) is not publicly available to read or download through this Web site. All submissions, including copyrighted material, are available for inspection and copying at the OSHA Docket Office. Contact the OSHA Docket Office for assistance in locating docket submissions. FOR FURTHER INFORMATION CONTACT: Information regarding this Request for Information is available from the following sources: Press inquiries. Contact Frank Meilinger, Director, OSHA Office of Communications, Room N–3647, U.S. Department of Labor, 200 Constitution Avenue NW., Washington, DC 20210; telephone: (202) 693–1999. General and technical information. Contact Blake Skogland, Office of Construction Standards and Guidance, OSHA Directorate of Construction, Room N–3468, U.S. Department of Labor, 200 Constitution Avenue NW., Washington, DC 20210; telephone: (202) 693–2020; fax: (202) 693–1689. Copies of this Federal Register notice. Electronic copies are available at http://www.regulations.gov. This Federal Register notice, as well as news releases and other relevant information, also are available at OSHA’s Web page at http://www.osha.gov. Table of Contents of This RFI Exhibits Referenced in this RFI Reinforced Concrete in Construction, Docket No. OSHA–2010–0058 Preventing Backover Injuries and Fatalities, Docket No. OSHA–2010–0059 Authority and Signature SUPPLEMENTARY INFORMATION: Exhibits Referenced in This RFI Documents referenced by OSHA in this request for information, other than OSHA standards and Federal Register notices, are in Docket Nos. OSHA– 2010–0058 (Reinforced Concrete in Construction) and OSHA–2010–0059 (Preventing Backover Injuries and Fatalities). The dockets are available at http://www.regulations.gov, the Federal E:\FR\FM\29MRP1.SGM 29MRP1

Agencies

[Federal Register Volume 77, Number 61 (Thursday, March 29, 2012)]
[Proposed Rules]
[Pages 18970-18973]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 2012-7542]


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

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2012-0337; Directorate Identifier 2010-SW-090-AD]
RIN 2120-AA64


Airworthiness Directives; Bell Helicopter Textron Canada 
Helicopters

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Notice of proposed rulemaking (NPRM).

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

SUMMARY: We propose to adopt a new airworthiness directive (AD) for the 
Bell Helicopter Textron Canada Limited (BHTC) Model 407 helicopters. 
This proposed AD is prompted by a review of the tailboom-attachment 
installation, which revealed that the torque value of the bolts 
specified in the BHTC Model 407 Maintenance Manual and applied during 
manufacturing was incorrect and exceeded the torque range recommended 
for the bolts. This proposed AD would require you to replace tailboom-
attachment hardware (attachment hardware), and perform initial and 
recurring determinations of

[[Page 18971]]

the torque on the nuts of the tailboom-attachment bolts (bolts) at all 
four attachment locations. The actions required by this proposed AD are 
intended to prevent an over-torque of a bolt, bolt failure, loss of the 
tailboom, and subsequent loss of control of the helicopter.

DATES: We must receive comments on this proposed AD by May 29, 2012.

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 
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 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 copies of 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: Sharon Miles, Aerospace Engineer, FAA, 
Regulations and Policy Group, 2601 Meacham Blvd., Fort Worth, Texas 
76137; telephone: (817) 222-5122; fax: (817) 222-5961; email: 
sharon.y.miles@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, which is the aviation authority for Canada, has 
issued AD No. CF-2010-33, dated September 30, 2010 (AD CF-2010-33), to 
correct an unsafe condition for the BHTC Model 407 helicopter, serial 
numbers (S/Ns) 53000 through 53990. Transport Canada advises that a 
review of the tailboom-attachment installation determined that the 
torque value of the bolts specified in the BHTC Model 407 Maintenance 
Manual and applied during manufacturing exceeded the torque range 
recommended for the bolts. Transport Canada states that this situation, 
if not corrected, could lead to a bolt failure, detachment of the 
tailboom, and subsequent loss of control of the helicopter.
    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, Transport Canada, its technical 
representative, has notified us of the unsafe condition described in 
its AD.

FAA's Determination

    We are proposing this AD because we evaluated all known relevant 
information and determined that an unsafe condition exists and is 
likely to exist or develop on other products of the same type design.

Related Service Information

    BHTC has issued Alert Service Bulletin No. 407-10-93, Revision A, 
dated August 30, 2010 (ASB), which specifies installing new attachment 
hardware with a reduced torque value. This ASB specifies performing a 
torque check of the newly installed bolts and nuts every one to five 
flight hours until torque stabilizes at all locations, and thereafter 
at intervals not to exceed 300 flight hours. Transport Canada 
classified this ASB as mandatory and issued AD CF-2010-33 to ensure the 
continued airworthiness of these helicopters.

Proposed AD Requirements

    This proposed AD would require for helicopters with 7000 hours or 
less time-in-service (TIS), at the next 600 hours scheduled inspection, 
or 90 days, whichever comes first; and for helicopters with more than 
7000 hours TIS, within 150 hours TIS or 90 days, whichever comes first, 
the following actions:
     Remove the left upper bolt, washers, and nut. Install a 
new bolt, part number (P/N) NAS627-30; washers, P/N 140-007-29S25E6 and 
P/N NAS1149G0732P; and new nut, P/N 42FLW-720. Repeat this action for 
the opposite right upper attachment hardware.
     Remove the left lower bolt, washers, and nut. Install a 
new bolt, P/N NAS626-26; washer, P/N 140-007-25S22E6, washer(s), P/N 
NAS1149G0663P; and new nut, P/N 42FLW-624. Repeat this action for the 
opposite right lower attachment hardware.
     After installation of the new attachment hardware, at 
intervals of not less than 1 hour TIS but not exceeding 5 hours TIS, 
determine the torque of each nut until torque stabilizes at each 
attachment location. Thereafter, determine the torque of each nut at 
recurring intervals not to exceed 300 hours TIS. If the proper torque 
has not been retained since the last torquing, remove and inspect the 
tailboom assembly for damage, corrosion, improper assembly, and 
condition. If the tailboom assembly is airworthy, replace the 
attachment hardware and determine that the torque has stabilized at 
each attachment location. Replace any unairworthy tailboom assembly 
with an airworthy tailboom assembly before further flight.

Differences Between This Proposed AD and the Transport Canada AD

    The differences between this proposed AD and the Transport Canada 
AD are as follows:
     This proposed AD uses the term ``hours time-in-service'' 
to describe compliance times, and the Transport Canada AD uses the term 
``air time'';

[[Page 18972]]

     For helicopters with 7000 hours or less TIS, the Transport 
Canada AD requires accomplishing the actions in the AD at the next 
scheduled 600-hour inspection or by December 31, 2010, whichever occurs 
first. This proposed AD requires accomplishing the actions at the next 
scheduled 600-hour inspection or 90 days, whichever occurs first.
     This proposed AD uses the term ``determine the torque'' 
when referring to the torque on a nut, and the Transport Canada AD uses 
the term ``perform a torque check.''

Costs of Compliance

    We estimate that this proposed AD would affect 552 helicopters of 
U.S. registry. We estimate it would take about 2.0 work-hours per 
helicopter to replace the hardware and 1.0 work-hour per helicopter to 
determine the recurring torque value at an average labor rate of $85 
per work hour. Required parts would cost about $498 per helicopter. 
Based on these figures, we estimate for the first year the total cost 
per helicopter to be $923, and the total cost impact on U.S. operators 
to be $509,496. This estimated total cost assumes attachment hardware 
will be replaced on all affected helicopters, the torque will be 
considered stabilized after determining the torque value once, and the 
300-hour TIS recurring torque determination will be accomplished twice 
a year.

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

    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]

    2. The FAA amends Sec.  39.13 by adding the following new 
Airworthiness Directive (AD):

Bell Helicopter Textron Canada (BHTC): Docket No. FAA-2012-0337; 
Directorate Identifier 2010-SW-090-AD.

(a) Applicability

    BHTC Model 407 helicopters, serial numbers 53000 through 53990, 
certificated in any category.

(b) Unsafe Condition

    This proposed AD defines the unsafe condition as an incorrect 
torque value of the tailboom attachment bolt (bolt) specified in the 
BHTC Model 407 Maintenance Manual and applied during manufacturing, 
which exceeds the torque range recommended for the bolts. This 
condition could result in an over-torque of the bolt, bolt failure, 
loss of the tailboom, and subsequent loss of control of the 
helicopter.

(c) Compliance

    You are responsible for performing each action required by this 
AD within the specified compliance time unless accomplished 
previously.

(d) Required Actions

    (1) For helicopters with 7000 hours or less time-in-service 
(TIS), at the next 600 hours scheduled inspection, or 90 days, 
whichever comes first; and for helicopters with more than 7000 hours 
TIS, within 150 hours TIS or 90 days, whichever comes first, replace 
the tailboom-attachment hardware (attachment hardware) as follows:
    (i) Remove the left upper bolt, washers, and nut.
    (ii) Install a new bolt, part number (P/N) NAS627-30; washer, P/
N 140-007-29S25E6; washer(s), P/N NAS1149G0732P; and new nut, P/N 
42FLW-720 in accordance with paragraphs 2.a) through paragraph 3.e) 
of the ``Accomplishment Instructions: Replacement of tailboom 
attachment bolts and nuts'' section and Figure 2 in the BHTC Alert 
Service Bulletin No. 407-10-93, Revision A, dated August 30, 2010 
(ASB).
    (iii) Remove the opposite right upper bolt, washers, and nut, 
and accomplish the requirements in paragraph (d)(1)(ii) of this AD.
    (iv) Remove the left lower bolt, washers, and nut.
    (v) Install a new bolt, (P/N) NAS626-26; washer, P/N 140-007-
25S22E6; washer(s), P/N NAS1149G0663P; and new nut, P/N 42FLW-624 in 
accordance with paragraphs 6.a) through 7.e) of the ``Accomplishment 
Instructions: Replacement of tailboom attachment bolts and nuts'' 
section and Figure 2 in the ASB.
    (vi) Remove the right lower bolt, washers, and nut, and 
accomplish the requirements in paragraph (d)(1)(v) of this AD.
    (2) After installation of the new attachment hardware, at 
intervals of not less than 1 hour TIS but not exceeding 5 hours TIS, 
determine the torque of each nut until the torque stabilizes at each 
attachment location, referring to Figure 2 of the ASB. Apply the 
minimum specified torque of the range, plus the minimum acceptable 
tare torque of 14 inch/lbs (1.58 Nm) for the upper nuts, and 9.5 
inch/lbs (1.07 Nm) for the lower nuts.
    (3) At intervals not to exceed 300 hours TIS, determine the 
torque of each of the four attachment nuts, referring to Figure 2 of 
the ASB. Apply the minimum specified torque of the range plus the 
minimum acceptable tare torque of 14 inch/lbs (1.58 Nm) for the 
upper nuts, and 9.5 inch/lbs (1.07 Nm) for the lower nuts. If the 
proper torque has not been retained since the last torque 
determination, remove and inspect the tailboom assembly for damage, 
corrosion, improper assembly, and condition. If the tailboom 
assembly is airworthy, replace the attachment hardware in accordance 
with the requirements in paragraphs (d)(1)(i) through (d)(1)(vi) and 
determine that the torque has stabilized in accordance with 
paragraph (2) of this AD. Replace any unairworthy tailboom assembly 
with an airworthy tailboom assembly.

(e) Alternative Methods of Compliance (AMOC)

    (1) The Manager, Safety Management Group, FAA, may approve AMOCs 
for this AD. Send your proposal to: Sharon Miles,

[[Page 18973]]

2601 Meacham Blvd., Fort Worth, Texas 76137; telephone: (817) 222-
5122; fax: 817-222-5961; email: sharon.y.miles@faa.gov.
    (2) For operations conducted under a Part 119 operating 
certificate or under 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.

(f) Additional Information

    The subject of this AD is addressed in the Transport Canada 
Civil Aviation (TCCA) AD CF-2010-33, dated September 30, 2010.

 (g) Subject

    Joint Aircraft Service Component (JASC) Code: 5302, Rotorcraft 
tailboom.

    Issued in Fort Worth, Texas, on March 21, 2012.
Kim Smith,
Manager, Rotorcraft Directorate, Aircraft Certification Service.

[FR Doc. 2012-7542 Filed 3-28-12; 8:45 am]
BILLING CODE 4910-13-P