Airworthiness Directives; Bell Helicopter Textron Canada Limited Model 206A and 206B Helicopters, 38527-38529 [E7-13607]

Download as PDF Federal Register / Vol. 72, No. 134 / Friday, July 13, 2007 / Proposed Rules DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2007–28690; Directorate Identifier 2006–SW–21–AD] RIN 2120–AA64 Airworthiness Directives; Bell Helicopter Textron Canada Limited Model 206A and 206B Helicopters Federal Aviation Administration, DOT. ACTION: Notice of proposed rulemaking (NPRM). AGENCY: SUMMARY: This document proposes adopting a new airworthiness directive (AD) for Bell Helicopter Textron Canada Limited (BHTC) Model 206A and 206B helicopters, serial numbers (S/N) 0004 through 3906, with two-piece vertical stabilizer (fin) supports (fin supports) installed. This proposal would require inserting a revision into the applicable maintenance manual, verifying the torque on the fin support attachment hardware, inspecting the fin support bracket and vertical fin for paint or gaps, and inspecting the fin support bracket for cracking, and if a crack is found, replacing the two-piece vertical fin support with a one-piece casting support. This proposal is prompted by an accident in which the fin supports failed. The actions specified by this proposed AD are intended to detect improper torque of the fin support attachment hardware, gaps between the fin support bracket and the doubler, painted mating surfaces of the fin supports, vertical fin, and vertical fin inserts (fin inserts), and cracking in the fin supports, to prevent the vertical fin from rotating into the tail rotor, separation of the tail rotor, and subsequent loss of control of the helicopter. Comments must be received on or before September 11, 2007. ADDRESSES: Use one of the following addresses to submit comments on this proposed AD: • DOT Docket Web site: Go to https:// dms.dot.gov and follow the instructions for sending your comments electronically; • Government-wide rulemaking Web site: Go to https://www.regulations.gov and follow the instructions for sending your comments electronically; • Mail: U.S. Department of Transportation, Docket Operations, M– 30, West Building Ground Floor, Room jlentini on PROD1PC65 with PROPOSALS DATES: VerDate Aug<31>2005 16:43 Jul 12, 2007 Jkt 211001 W12–140, 1200 New Jersey Avenue SE., Washington, DC 20590; • Hand Delivery: Deliver to the ‘‘Mail’’ address between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays; or • Fax: 202–493–2251. You may get the service information identified in this proposed AD from 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. You may examine the comments to this proposed AD in the AD docket on the Internet at https://dms.dot.gov. FOR FURTHER INFORMATION CONTACT: Sharon Miles, Aviation Safety Engineer, FAA, Rotorcraft Directorate, Regulations and Policy Group, Fort Worth, Texas 76193–0111, telephone (817) 222–5122, fax (817) 222–5961. SUPPLEMENTARY INFORMATION: Comments Invited We invite you to submit any written data, views, or arguments regarding this proposed AD. Send your comments to the address listed under the caption ADDRESSES. Include the docket number ‘‘FAA–2007–28690, Directorate Identifier 2006–SW–21–AD’’ at the beginning of your comments. We specifically invite comments on the overall regulatory, economic, environmental, and energy aspects of the proposed AD. We will consider all comments received by the closing date and may amend the proposed AD in light of those comments. We will post all comments we receive, without change, to https:// dms.dot.gov, including any personal information you provide. We will also post a report summarizing each substantive verbal contact with FAA personnel concerning this proposed rulemaking. Using the search function of our docket Web site, you can find and read the comments to any of our dockets, including the name of the individual who sent or signed the comment. You may review the DOT’s complete Privacy Act Statement in the Federal Register published on April 11, 2000 (65 FR 19477–78), or you may visit https://dms.dot.gov. Examining the Docket You may examine the docket that contains the proposed AD, any comments, and other information in person at the Docket Management System (DMS) Docket Office between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. The Docket Office (telephone 1–800–647– 5527) is located in Room W12–140 on PO 00000 Frm 00032 Fmt 4702 Sfmt 4702 38527 the ground floor of the West Building, 1200 New Jersey Avenue SE., Washington, DC. Comments will be available in the AD docket shortly after the DMS receives them. Discussion This document proposes adopting a new AD for BHTC Model 206A and 206B helicopters, S/N 0004 through 3906, with fin supports, part numbers (P/N) 206–031–417–003 or –007, or 206–031–418–001 or –005, installed. This proposal would require inserting a revision into the Scheduled Inspection section, chapter 5, of the applicable maintenance manual, implementing a recurring inspection at intervals not to exceed 100 hours time-in-service (TIS) or at each annual inspection, whichever occurs first, of the torque on the fin supports’ attachment hardware, and inspecting the fin support for damage. Inspecting for paint on the mating surfaces of the fin support bracket and vertical fin; inspecting the vertical fin attaching hardware for proper torque and the amount of gap between the vertical fin support bracket and the vertical fin doubler; inspecting the fin support bracket for cracking using a 10× or higher power magnifying glass; and if either the torque or gap is out of limits or paint is present, fluorescent penetrant inspecting the vertical fin support for cracking would also be required. If a crack is found, replacing the vertical fin support with a one-piece casting support, P/N 206–033–426–003, would be required. This proposal is prompted by an accident in which the fin supports failed, allowing the lower part of the fin to contact the tail rotor blades, which resulted in subsequent separation of the gearbox and tail rotor from the helicopter. The actions specified by this proposed AD are intended to detect improper torque of the fin support attachment hardware, gaps between the fin support bracket and the doubler, painted mating surfaces of the fin supports, vertical fin, and fin inserts, and cracking in the fin supports, to prevent the vertical fin from rotating into the tail rotor, separation of the tail rotor, and subsequent loss of control of the helicopter. Transport Canada, the airworthiness authority for Canada, notified the FAA that an unsafe condition may exist on BHTC Model 206A and 206B helicopters, S/N 004 through 3906, with fin supports, P/N 206–031–417–003 or –007, or 206–031–418–001 or –005, installed. Transport Canada advises that a one-time inspection of the vertical fin mating surfaces is required to ensure an appropriate surface finish. In addition, they advise that a recurring torque E:\FR\FM\13JYP1.SGM 13JYP1 jlentini on PROD1PC65 with PROPOSALS 38528 Federal Register / Vol. 72, No. 134 / Friday, July 13, 2007 / Proposed Rules check of the vertical fin attaching hardware is required to maintain the structural integrity of the joint. They also advise that the initial inspection be performed at the next scheduled 100 hour TIS or annual inspection, but within three (3) months in accordance with BHTC Alert Service Bulletin No. 206–06–107, dated April 26, 2006, or later revisions approved by Transport Canada. BHTC has issued Alert Service Bulletin No. 206–06–107, Revision A, dated June 15, 2006, which specifies a series of inspections of the two-piece fin supports, and also introduces revisions to Chapters 5 and 53 of the BHT–206A/ B Series Maintenance Manual. The revision to Chapter 5 introduces a recurring vertical fin attaching hardware torque check and inspecting the fin supports for damage, which are to be accomplished at the next scheduled 100 hour TIS or annual inspection. The revision to Chapter 53 updates the procedures for removal, installation, and inspection of the vertical fin. Transport Canada classified this alert service bulletin as mandatory and issued AD No. CF–2006–12, dated June 5, 2006, to ensure the continued airworthiness of these helicopters in Canada. These helicopter models are manufactured in Canada and are type certificated for operation in the United States under the provisions of 14 CFR 21.29 and the applicable bilateral agreement. Pursuant to the applicable bilateral agreement, Transport Canada has kept us informed of the situation described above. We have examined the findings of the Transport Canada, reviewed all available information, and determined that AD action is necessary for products of these type designs that are certificated for operation in the United States. This previously described unsafe condition is likely to exist or develop on other helicopters of the same type designs registered in the United States. Therefore, the proposed AD would require, at the next scheduled 100 hour TIS inspection, but no later than 90 days from the effective date of this AD, unless accomplished previously, and thereafter at intervals not to exceed 100 hours TIS or at each annual inspection, whichever occurs first, verifying the torque on the fin support attachment hardware. Inspecting the fin support bracket and vertical fin for paint or gaps, inspecting the fin support bracket for cracking using a 10x or higher power magnifying glass, and if needed, fluorescent penetrant inspecting for cracking would also be required, as well as replacing any two-piece fin support VerDate Aug<31>2005 17:25 Jul 12, 2007 Jkt 211001 on which a crack is found with a onepiece casting support. Inserting a revision into the applicable maintenance manual would also be required. The actions would be required to be accomplished by following the specified portions of the alert service bulletin described previously. We estimate that this proposed AD would affect 1,466 helicopters of U.S. registry and the proposed inspections would take approximately 4 work hours per helicopter at an average labor rate of $80 per work hour. If needed, replacing a fin support would take approximately 30 work hours. Required parts would cost approximately $3,260 for each fin support. Based on these figures, we estimate the total cost impact of the proposed AD on U.S. operators to be $3,300,820 for the fleet during the first year, assuming 7 inspections per helicopter are conducted, and assuming that replacing the fin support is required on 3 helicopters. 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 have determined that this proposed AD would not have federalism implications under Executive Order 13132. Additionally, this proposed AD would not have a substantial direct effect on the States, on the relationship between the national Government and the States, or on the distribution of power and responsibilities among the various levels of government. For the reasons discussed above, I certify that the 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); and 3. 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 a draft economic evaluation of the estimated costs to comply with this proposed AD. See the DMS to examine the draft economic evaluation. 1. The authority citation for part 39 continues to read as follows: 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 PO 00000 Frm 00033 Fmt 4702 Sfmt 4702 List of Subjects in 14 CFR Part 39 Air transportation, Aircraft, Aviation safety, Safety. The Proposed Amendment Accordingly, pursuant to the authority delegated to me by the Administrator, the Federal Aviation Administration proposes to amend part 39 of the Federal Aviation Regulations (14 CFR part 39) as follows: PART 39—AIRWORTHINESS DIRECTIVES Authority: 49 U.S.C. 106(g), 40113, 44701. § 39.13 [Amended] 2. Section 39.13 is amended by adding a new airworthiness directive to read as follows: Bell Helicopter Textron Canada Limited: Docket No. FAA–2007–28690; Directorate Identifier 2006–SW–21–AD. Applicability: Model 206A and 206B helicopters, serial numbers 0004 through 3906, with two-piece vertical stabilizer (fin) supports (fin supports), part number (P/N) 206–031–417–003 or –007, or P/N 206–031– 418–001 or –005, installed, certificated in any category. Compliance: Required at the next scheduled 100 hour time-in-service (TIS) inspection or annual inspection, but no later than 90 days after the effective date of this AD, unless accomplished previously, and thereafter at intervals not to exceed 100 hours TIS or at each annual inspection, whichever occurs first. To detect improper torque of the fin support attachment hardware, gaps between the fin support bracket and the doubler, painted mating surfaces of the fin supports, vertical fin, and vertical fin inserts (fin inserts), and cracks in the fin supports, to prevent the vertical fin from rotating into the tail rotor, separation of the tail rotor, and subsequent loss of control of the helicopter, accomplish the following: (a) Insert Revision 4 of BHT–206A/B– SERIES–MM into the appropriate section of the maintenance manual. (b) Determine the type and part number of the installed vertical fin by referring to the listing in step 2., Table 1, of the Accomplishment Instructions of Bell Helicopter Textron Alert Service Bulletin No. 206–06–107, Revision A, dated June 15, 2006 (ASB). E:\FR\FM\13JYP1.SGM 13JYP1 jlentini on PROD1PC65 with PROPOSALS Federal Register / Vol. 72, No. 134 / Friday, July 13, 2007 / Proposed Rules (c) For Type 1 and Type 3 vertical fins, inspect the vertical fin and fin support bracket for paint, and the vertical fin attaching hardware for proper torque, in accordance with steps 5. and 6. of the Accomplishment Instructions of the ASB. (d) For Type 2 vertical fins, inspect the vertical fin and fin support bracket for paint, the vertical fin attaching hardware for proper torque, and the amount of gap between the vertical fin support bracket and the vertical fin doubler in accordance with steps 5., 6., and 7. of the Accomplishment Instructions of the ASB. (e) If the inspections required by paragraphs (c) and (d) of this AD indicate that the torque and gap are within limits, and there is no paint present, visually inspect the vertical fin support bracket in the area of the vertical fin attaching hardware for a crack using a 10x or higher power magnifying glass. (1) If no crack is found, re-torque the vertical fin attaching hardware to between 75 and 95 in. lbs. (8.47 to 10.75 Nm). (2) If a crack is found, replace the twopiece vertical fin support bracket with a onepiece vertical fin casting support, P/N 206– 033–426–003. (f) Based on your finding in paragraphs (c) and (d) of this AD, if either the torque or gap is out of limits, or paint is present: (1) Remove the vertical fin. (2) Remove all the primer and paint coatings in the areas indicated in Figure I of the ASB. (3) Fluorescent penetrant inspect (FPI) the vertical fin support. (4) If a crack is found, replace the twopiece vertical fin support with a one-piece vertical fin casting support, P/N 206–033– 426–003. (5) If no crack is found, apply two coats of Polyamide Epoxy Primer on bare metal surfaces. (g) For Type 2 vertical fins only: (1) If incorrect washers (spacers) or no washers are installed, visually inspect the 4 vertical fin potted inserts as depicted in the vertical fin detail in Figure I of the ASB for any damage using a 10x or higher power magnifying glass. (2) If any of the 4 vertical fin potted inserts is damaged with no other damage to the surrounding areas, remove and replace the damaged potted insert with an airworthy potted insert. (3) After assuring that all 4 installed vertical fin potted inserts are undamaged, install the correct washers in accordance with step 9.d. of the Accomplishment Instructions of the ASB. (h) This AD revises the helicopter maintenance manual by adding an inspection of the torque on the vertical fin attaching hardware, and inspections of the vertical fin and vertical fin support, to the 100-hour TIS and annual scheduled inspections. (i) To request a different method of compliance or a different compliance time for this AD, follow the procedures in 14 CFR 39.19. Contact the Manager, Regulations and Policy Group, FAA, ATTN: Sharon Miles, Aviation Safety Engineer, FAA, Rotorcraft Directorate, Regulations and Policy Group, Fort Worth, Texas 76193–0111, telephone VerDate Aug<31>2005 17:25 Jul 12, 2007 Jkt 211001 (817) 222–5122, fax (817) 222–5961, for information about previously approved alternative methods of compliance. Note: The subject of this AD is addressed in Transport Canada (Canada) AD No. CF– 2006–12, dated June 5, 2006. Issued in Fort Worth, Texas, on July 3, 2007. David A. Downey, Manager, Rotorcraft Directorate, Aircraft Certification Service. [FR Doc. E7–13607 Filed 7–12–07; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2007–28691; Directorate Identifier 2006–SW–22–AD] RIN 2120–AA64 Airworthiness Directives; Eurocopter France Model AS355E, F, F1, F2, and N Helicopters Federal Aviation Administration, DOT. ACTION: Notice of proposed rulemaking (NPRM). AGENCY: SUMMARY: This document proposes superseding an existing airworthiness directive (AD) for the specified Eurocopter France (ECF) helicopters. That AD currently requires certain checks of the magnetic chip detector plug (chip detector) and the main gearbox (MGB) oil-sight glass, certain inspections of the lubrication pump (pump), and replacing the MGB and the pump with an airworthy MGB and pump, if necessary. Also, the AD requires that before an MGB or pump with any hours time-in-service (TIS) can be installed, it must meet the AD requirements. This action would retain those requirements but would add all serial-numbered pumps to the applicability. This proposal is prompted by additional cases of MGB lubrication pump deterioration and a further investigation that determined that all serial-numbered pumps might be affected. The actions specified by the proposed AD are intended to detect sludge on the chip detector and dark oil in the MGB, to prevent failure of the MGB pump, seizure of the MGB, loss of drive to an engine and main rotor, and subsequent loss of control of the helicopter. Comments must be received on or before September 11, 2007. DATES: PO 00000 Frm 00034 Fmt 4702 Sfmt 4702 38529 Use one of the following addresses to submit comments on this proposed AD: • DOT Docket Web site: Go to https://dms.dot.gov and follow the instructions for sending your comments electronically; • Government-wide rulemaking Web site: Go to https://www.regulations.gov and follow the instructions for sending your comments electronically; • Mail: U.S. Department of Transportation, Docket Operations, M– 30, West Building Ground Floor, Room W12–140, 1200 New Jersey Avenue, SE., Washington, DC 20590; • Hand Delivery: Deliver to Mail address above between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays; or • Fax: 202–493–2251. • You may get the service information identified in this proposed AD from American Eurocopter Corporation, 2701 Forum Drive, Grand Prairie, Texas 75053–4005, telephone (972) 641–3460, fax (972) 641–3527. You may examine the comments to this proposed AD in the AD docket on the Internet at https://dms.dot.gov. FOR FURTHER INFORMATION CONTACT: Ed Cuevas, Aviation Safety Engineer, FAA, Rotorcraft Directorate, Safety Management Group, Fort Worth, Texas 76193–0111, telephone (817) 222–5355, fax (817) 222–5961. SUPPLEMENTARY INFORMATION: ADDRESSES: Comments Invited We invite you to submit any written data, views, or arguments regarding this proposed AD. Send your comments to the address listed under the caption ADDRESSES. Include the docket number ‘‘FAA–2007–28691, Directorate Identifier 2006–SW–22–AD’’ at the beginning of your comments. We specifically invite comments on the overall regulatory, economic, environmental, and energy aspects of the proposed AD. We will consider all comments received by the closing date and may amend the proposed AD in light of those comments. We will post all comments we receive, without change, to https:// dms.dot.gov, including any personal information you provide. We will also post a report summarizing each substantive verbal contact with FAA personnel concerning this proposed rulemaking. Using the search function of our docket Web site, you can find and read the comments to any of our dockets, including the name of the individual who sent or signed the comment. You may review the DOT’s complete Privacy Act Statement in the E:\FR\FM\13JYP1.SGM 13JYP1

Agencies

[Federal Register Volume 72, Number 134 (Friday, July 13, 2007)]
[Proposed Rules]
[Pages 38527-38529]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: E7-13607]



[[Page 38527]]

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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2007-28690; Directorate Identifier 2006-SW-21-AD]
RIN 2120-AA64


Airworthiness Directives; Bell Helicopter Textron Canada Limited 
Model 206A and 206B Helicopters

AGENCY: Federal Aviation Administration, DOT.

ACTION: Notice of proposed rulemaking (NPRM).

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

SUMMARY: This document proposes adopting a new airworthiness directive 
(AD) for Bell Helicopter Textron Canada Limited (BHTC) Model 206A and 
206B helicopters, serial numbers (S/N) 0004 through 3906, with two-
piece vertical stabilizer (fin) supports (fin supports) installed. This 
proposal would require inserting a revision into the applicable 
maintenance manual, verifying the torque on the fin support attachment 
hardware, inspecting the fin support bracket and vertical fin for paint 
or gaps, and inspecting the fin support bracket for cracking, and if a 
crack is found, replacing the two-piece vertical fin support with a 
one-piece casting support. This proposal is prompted by an accident in 
which the fin supports failed. The actions specified by this proposed 
AD are intended to detect improper torque of the fin support attachment 
hardware, gaps between the fin support bracket and the doubler, painted 
mating surfaces of the fin supports, vertical fin, and vertical fin 
inserts (fin inserts), and cracking in the fin supports, to prevent the 
vertical fin from rotating into the tail rotor, separation of the tail 
rotor, and subsequent loss of control of the helicopter.

DATES: Comments must be received on or before September 11, 2007.

ADDRESSES: Use one of the following addresses to submit comments on 
this proposed AD:
     DOT Docket Web site: Go to https://dms.dot.gov and follow 
the instructions for sending your comments electronically;
     Government-wide rulemaking Web site: Go to https://
www.regulations.gov and follow the instructions for sending your 
comments electronically;
     Mail: U.S. Department of Transportation, Docket 
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New 
Jersey Avenue SE., Washington, DC 20590;
     Hand Delivery: Deliver to the ``Mail'' address between 9 
a.m. and 5 p.m., Monday through Friday, except Federal holidays; or
     Fax: 202-493-2251.
    You may get the service information identified in this proposed AD 
from 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.
    You may examine the comments to this proposed AD in the AD docket 
on the Internet at https://dms.dot.gov.

FOR FURTHER INFORMATION CONTACT: Sharon Miles, Aviation Safety 
Engineer, FAA, Rotorcraft Directorate, Regulations and Policy Group, 
Fort Worth, Texas 76193-0111, telephone (817) 222-5122, fax (817) 222-
5961.

SUPPLEMENTARY INFORMATION: 

Comments Invited

    We invite you to submit any written data, views, or arguments 
regarding this proposed AD. Send your comments to the address listed 
under the caption ADDRESSES. Include the docket number ``FAA-2007-
28690, Directorate Identifier 2006-SW-21-AD'' at the beginning of your 
comments. We specifically invite comments on the overall regulatory, 
economic, environmental, and energy aspects of the proposed AD. We will 
consider all comments received by the closing date and may amend the 
proposed AD in light of those comments.
    We will post all comments we receive, without change, to https://
dms.dot.gov, including any personal information you provide. We will 
also post a report summarizing each substantive verbal contact with FAA 
personnel concerning this proposed rulemaking. Using the search 
function of our docket Web site, you can find and read the comments to 
any of our dockets, including the name of the individual who sent or 
signed the comment. You may review the DOT's complete Privacy Act 
Statement in the Federal Register published on April 11, 2000 (65 FR 
19477-78), or you may visit https://dms.dot.gov.

Examining the Docket

    You may examine the docket that contains the proposed AD, any 
comments, and other information in person at the Docket Management 
System (DMS) Docket Office between 9 a.m. and 5 p.m., Monday through 
Friday, except Federal holidays. The Docket Office (telephone 1-800-
647-5527) is located in Room W12-140 on the ground floor of the West 
Building, 1200 New Jersey Avenue SE., Washington, DC. Comments will be 
available in the AD docket shortly after the DMS receives them.

Discussion

    This document proposes adopting a new AD for BHTC Model 206A and 
206B helicopters, S/N 0004 through 3906, with fin supports, part 
numbers (P/N) 206-031-417-003 or -007, or 206-031-418-001 or -005, 
installed. This proposal would require inserting a revision into the 
Scheduled Inspection section, chapter 5, of the applicable maintenance 
manual, implementing a recurring inspection at intervals not to exceed 
100 hours time-in-service (TIS) or at each annual inspection, whichever 
occurs first, of the torque on the fin supports' attachment hardware, 
and inspecting the fin support for damage. Inspecting for paint on the 
mating surfaces of the fin support bracket and vertical fin; inspecting 
the vertical fin attaching hardware for proper torque and the amount of 
gap between the vertical fin support bracket and the vertical fin 
doubler; inspecting the fin support bracket for cracking using a 10x or 
higher power magnifying glass; and if either the torque or gap is out 
of limits or paint is present, fluorescent penetrant inspecting the 
vertical fin support for cracking would also be required. If a crack is 
found, replacing the vertical fin support with a one-piece casting 
support, P/N 206-033-426-003, would be required. This proposal is 
prompted by an accident in which the fin supports failed, allowing the 
lower part of the fin to contact the tail rotor blades, which resulted 
in subsequent separation of the gearbox and tail rotor from the 
helicopter. The actions specified by this proposed AD are intended to 
detect improper torque of the fin support attachment hardware, gaps 
between the fin support bracket and the doubler, painted mating 
surfaces of the fin supports, vertical fin, and fin inserts, and 
cracking in the fin supports, to prevent the vertical fin from rotating 
into the tail rotor, separation of the tail rotor, and subsequent loss 
of control of the helicopter.
    Transport Canada, the airworthiness authority for Canada, notified 
the FAA that an unsafe condition may exist on BHTC Model 206A and 206B 
helicopters, S/N 004 through 3906, with fin supports, P/N 206-031-417-
003 or -007, or 206-031-418-001 or -005, installed. Transport Canada 
advises that a one-time inspection of the vertical fin mating surfaces 
is required to ensure an appropriate surface finish. In addition, they 
advise that a recurring torque

[[Page 38528]]

check of the vertical fin attaching hardware is required to maintain 
the structural integrity of the joint. They also advise that the 
initial inspection be performed at the next scheduled 100 hour TIS or 
annual inspection, but within three (3) months in accordance with BHTC 
Alert Service Bulletin No. 206-06-107, dated April 26, 2006, or later 
revisions approved by Transport Canada.
    BHTC has issued Alert Service Bulletin No. 206-06-107, Revision A, 
dated June 15, 2006, which specifies a series of inspections of the 
two-piece fin supports, and also introduces revisions to Chapters 5 and 
53 of the BHT-206A/B Series Maintenance Manual. The revision to Chapter 
5 introduces a recurring vertical fin attaching hardware torque check 
and inspecting the fin supports for damage, which are to be 
accomplished at the next scheduled 100 hour TIS or annual inspection. 
The revision to Chapter 53 updates the procedures for removal, 
installation, and inspection of the vertical fin. Transport Canada 
classified this alert service bulletin as mandatory and issued AD No. 
CF-2006-12, dated June 5, 2006, to ensure the continued airworthiness 
of these helicopters in Canada.
    These helicopter models are manufactured in Canada and are type 
certificated for operation in the United States under the provisions of 
14 CFR 21.29 and the applicable bilateral agreement. Pursuant to the 
applicable bilateral agreement, Transport Canada has kept us informed 
of the situation described above. We have examined the findings of the 
Transport Canada, reviewed all available information, and determined 
that AD action is necessary for products of these type designs that are 
certificated for operation in the United States.
    This previously described unsafe condition is likely to exist or 
develop on other helicopters of the same type designs registered in the 
United States. Therefore, the proposed AD would require, at the next 
scheduled 100 hour TIS inspection, but no later than 90 days from the 
effective date of this AD, unless accomplished previously, and 
thereafter at intervals not to exceed 100 hours TIS or at each annual 
inspection, whichever occurs first, verifying the torque on the fin 
support attachment hardware. Inspecting the fin support bracket and 
vertical fin for paint or gaps, inspecting the fin support bracket for 
cracking using a 10x or higher power magnifying glass, and if needed, 
fluorescent penetrant inspecting for cracking would also be required, 
as well as replacing any two-piece fin support on which a crack is 
found with a one-piece casting support. Inserting a revision into the 
applicable maintenance manual would also be required. The actions would 
be required to be accomplished by following the specified portions of 
the alert service bulletin described previously.
    We estimate that this proposed AD would affect 1,466 helicopters of 
U.S. registry and the proposed inspections would take approximately 4 
work hours per helicopter at an average labor rate of $80 per work 
hour. If needed, replacing a fin support would take approximately 30 
work hours. Required parts would cost approximately $3,260 for each fin 
support. Based on these figures, we estimate the total cost impact of 
the proposed AD on U.S. operators to be $3,300,820 for the fleet during 
the first year, assuming 7 inspections per helicopter are conducted, 
and assuming that replacing the fin support is required on 3 
helicopters.

Regulatory Findings

    We have determined that this proposed AD would not have federalism 
implications under Executive Order 13132. Additionally, this proposed 
AD would not have a substantial direct effect on the States, on the 
relationship between the national Government and the States, or on the 
distribution of power and responsibilities among the various levels of 
government.
    For the reasons discussed above, I certify that the 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); and
    3. 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 a draft economic evaluation of the estimated costs to 
comply with this proposed AD. See the DMS to examine the draft economic 
evaluation.

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.

List of Subjects in 14 CFR Part 39

    Air transportation, Aircraft, Aviation safety, Safety.

The Proposed Amendment

    Accordingly, pursuant to the authority delegated to me by the 
Administrator, the Federal Aviation Administration proposes to amend 
part 39 of the Federal Aviation Regulations (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. Section 39.13 is amended by adding a new airworthiness directive 
to read as follows:

Bell Helicopter Textron Canada Limited: Docket No. FAA-2007-28690; 
Directorate Identifier 2006-SW-21-AD.
    Applicability: Model 206A and 206B helicopters, serial numbers 
0004 through 3906, with two-piece vertical stabilizer (fin) supports 
(fin supports), part number (P/N) 206-031-417-003 or -007, or P/N 
206-031-418-001 or -005, installed, certificated in any category.
    Compliance: Required at the next scheduled 100 hour time-in-
service (TIS) inspection or annual inspection, but no later than 90 
days after the effective date of this AD, unless accomplished 
previously, and thereafter at intervals not to exceed 100 hours TIS 
or at each annual inspection, whichever occurs first.
    To detect improper torque of the fin support attachment 
hardware, gaps between the fin support bracket and the doubler, 
painted mating surfaces of the fin supports, vertical fin, and 
vertical fin inserts (fin inserts), and cracks in the fin supports, 
to prevent the vertical fin from rotating into the tail rotor, 
separation of the tail rotor, and subsequent loss of control of the 
helicopter, accomplish the following:
    (a) Insert Revision 4 of BHT-206A/B-SERIES-MM into the 
appropriate section of the maintenance manual.
    (b) Determine the type and part number of the installed vertical 
fin by referring to the listing in step 2., Table 1, of the 
Accomplishment Instructions of Bell Helicopter Textron Alert Service 
Bulletin No. 206-06-107, Revision A, dated June 15, 2006 (ASB).

[[Page 38529]]

    (c) For Type 1 and Type 3 vertical fins, inspect the vertical 
fin and fin support bracket for paint, and the vertical fin 
attaching hardware for proper torque, in accordance with steps 5. 
and 6. of the Accomplishment Instructions of the ASB.
    (d) For Type 2 vertical fins, inspect the vertical fin and fin 
support bracket for paint, the vertical fin attaching hardware for 
proper torque, and the amount of gap between the vertical fin 
support bracket and the vertical fin doubler in accordance with 
steps 5., 6., and 7. of the Accomplishment Instructions of the ASB.
    (e) If the inspections required by paragraphs (c) and (d) of 
this AD indicate that the torque and gap are within limits, and 
there is no paint present, visually inspect the vertical fin support 
bracket in the area of the vertical fin attaching hardware for a 
crack using a 10x or higher power magnifying glass.
    (1) If no crack is found, re-torque the vertical fin attaching 
hardware to between 75 and 95 in. lbs. (8.47 to 10.75 Nm).
    (2) If a crack is found, replace the two-piece vertical fin 
support bracket with a one-piece vertical fin casting support, P/N 
206-033-426-003.
    (f) Based on your finding in paragraphs (c) and (d) of this AD, 
if either the torque or gap is out of limits, or paint is present:
    (1) Remove the vertical fin.
    (2) Remove all the primer and paint coatings in the areas 
indicated in Figure I of the ASB.
    (3) Fluorescent penetrant inspect (FPI) the vertical fin 
support.
    (4) If a crack is found, replace the two-piece vertical fin 
support with a one-piece vertical fin casting support, P/N 206-033-
426-003.
    (5) If no crack is found, apply two coats of Polyamide Epoxy 
Primer on bare metal surfaces.
    (g) For Type 2 vertical fins only:
    (1) If incorrect washers (spacers) or no washers are installed, 
visually inspect the 4 vertical fin potted inserts as depicted in 
the vertical fin detail in Figure I of the ASB for any damage using 
a 10x or higher power magnifying glass.
    (2) If any of the 4 vertical fin potted inserts is damaged with 
no other damage to the surrounding areas, remove and replace the 
damaged potted insert with an airworthy potted insert.
    (3) After assuring that all 4 installed vertical fin potted 
inserts are undamaged, install the correct washers in accordance 
with step 9.d. of the Accomplishment Instructions of the ASB.
    (h) This AD revises the helicopter maintenance manual by adding 
an inspection of the torque on the vertical fin attaching hardware, 
and inspections of the vertical fin and vertical fin support, to the 
100-hour TIS and annual scheduled inspections.
    (i) To request a different method of compliance or a different 
compliance time for this AD, follow the procedures in 14 CFR 39.19. 
Contact the Manager, Regulations and Policy Group, FAA, ATTN: Sharon 
Miles, Aviation Safety Engineer, FAA, Rotorcraft Directorate, 
Regulations and Policy Group, Fort Worth, Texas 76193-0111, 
telephone (817) 222-5122, fax (817) 222-5961, for information about 
previously approved alternative methods of compliance.

    Note: The subject of this AD is addressed in Transport Canada 
(Canada) AD No. CF-2006-12, dated June 5, 2006.


    Issued in Fort Worth, Texas, on July 3, 2007.
David A. Downey,
Manager, Rotorcraft Directorate, Aircraft Certification Service.
[FR Doc. E7-13607 Filed 7-12-07; 8:45 am]
BILLING CODE 4910-13-P

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