Airworthiness Directives; Bell Helicopter Textron Canada Model 427 Helicopters, 12098-12100 [E9-6225]

Download as PDF 12098 Federal Register / Vol. 74, No. 54 / Monday, March 23, 2009 / Proposed Rules manufacturer of the cargo hook. The lever is a component of the cargo hook, P/N 528– 010–01. This lever is a critical structural component of the cargo hook, and a crack could result in inadvertent loss of the cargo hook load. DEPARTMENT OF TRANSPORTATION Actions and Compliance (e) Before each cargo hook operation, visually inspect the cargo hook lever, P/N 232–028–00, for any crack. Use a 10-power or higher magnifying glass and inspect in the area depicted in Figures 1 and 2 of the following Agusta Alert Bollettino Tecnico (ABT), all dated June 6, 2007: (1) ABT No. 109EP–78 for Model A109E helicopters; (2) ABT No. 109S–12 for Model A109S helicopters; or (3) ABT No. 119–21 for Model A119 helicopters. (f) If a crack is found in the lever, do not use the cargo hook until the entire cargo hook is replaced with an airworthy cargo hook with an uncracked lever. [Docket No. FAA–2009–0227; Directorate Identifier 2007–SW–65–AD] Differences Between the FAA AD and the MCAI AD (g) This AD differs from the MCAI AD in that we: (1) Exclude the August 31, 2007 compliance date because that date has passed; (2) Exclude the Model A109LUH from the applicability and do not reference Agusta ABT No. 109L–006 because the Model A109LUH helicopter is not on the U.S. type certificate, H7EU; (3) Add the Model AW119MKII to the applicability; (4) Require the use of a 10-power or higher magnifying glass to accomplish the visual inspections; and (5) Exclude the kit installation P/N, relying instead on the cargo hook and lever P/N. Other Information (h) Alternative Methods of Compliance (AMOCs): The Manager, Safety Management Group, FAA, has the authority to approve AMOCs for this AD, if requested using the procedures found in 14 CFR 39.19. Send information to Attn: John Strasburger, Aviation Safety Engineer, Regulations and Policy Group, Rotorcraft Directorate, FAA, 2601 Meacham Blvd., Fort Worth, TX 76137; telephone (817) 222–5167; fax (817) 222– 5961. dwashington3 on PROD1PC60 with PROPOSALS Related Information (i) EASA Emergency AD No. 2007–0160–E, dated June 7, 2007, contains related information. Air Transport Association of America (ATA) Tracking Code (j) Air Transport Association of America (ATA) Code 2550: Cargo Compartments. Issued in Fort Worth, Texas on March 4, 2009. Jerald E. Strentz, Acting Manager, Rotorcraft Directorate, Aircraft Certification Service. [FR Doc. E9–6224 Filed 3–20–09; 8:45 am] BILLING CODE 4910–13–P VerDate Nov<24>2008 15:23 Mar 20, 2009 Jkt 217001 Federal Aviation Administration 14 CFR Part 39 RIN 2120–AA64 Airworthiness Directives; Bell Helicopter Textron Canada Model 427 Helicopters 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 427 helicopters. This proposed AD results from mandatory continuing airworthiness information (MCAI) originated by the aviation authority of Canada to identify and correct an unsafe condition on an aviation product. Transport Canada, the aviation authority of Canada, with which we have a bilateral agreement, states that it has been determined that the existing hardware connecting the vertical fin to the tail rotor gearbox needs to be upgraded, to prevent the vertical fin from becoming loose. BHTC has received reports of loose vertical fins discovered during inspections. Investigation revealed that the current vertical fin attachment hardware may not provide adequate clamp-up. If not corrected, the vertical fin could become loose and cause vibration, which could lead to subsequent loss of control of the helicopter. The proposed AD would require actions that are intended to address this unsafe condition. DATES: We must receive comments on this proposed AD by April 22, 2009. ADDRESSES: You may send comments by any of the following methods: • Federal eRulemaking Portal: Go to https://www.regulations.gov. Follow the instructions for submitting comments. • Fax: 202–493–2251. • Mail: U.S. Department of Transportation, Docket Operations, M– 30, West Building Ground Floor, Room W12–140, 1200 New Jersey Avenue, SE., Washington, DC 20590. • Hand Delivery: U.S. Department of Transportation, Docket Operations, M– 30, West Building Ground Floor, Room W12–140, 1200 New Jersey Avenue, SE., Washington, DC 20590, between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. You may get the service information identified in this proposed AD from Bell PO 00000 Frm 00005 Fmt 4702 Sfmt 4702 Helicopter Textron Canada, 12,800 Rue de l’Avenir, Mirabel, Quebec J7J1R4, telephone (450) 437–2862 or (800) 363– 8023, fax (450) 433–0272, or at https:// www.bellcustomer.com/files/. Examining the AD Docket: You may examine the AD docket on the Internet at https://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 FURTHER INFORMATION CONTACT: Sharon Miles, Aviation Safety Engineer, FAA, Rotorcraft Directorate, Regulations and Guidance Group, Fort Worth, Texas 76193–0111, telephone (817) 222–5122, fax (817) 222–5961. SUPPLEMENTARY INFORMATION: Comments Invited We invite you to send any written relevant data, views, or arguments about this proposed AD. Send your comments to an address listed under the ADDRESSES section. Include ‘‘Docket No. FAA–2009–0227; Directorate Identifier 2007–SW–65–AD’’ at the beginning of your comments. We specifically invite comments on the overall regulatory, economic, environmental, and energy aspects of this proposed AD. We will consider all comments received by the closing date and may amend this proposed AD based on those comments. We will post all comments we receive, without change, to https:// www.regulations.gov, including any personal information you provide. We will also post a report summarizing each substantive verbal contact we receive about this proposed AD. Discussion Transport Canada, which is the aviation authority for Canada, has issued an MCAI in the form of Canadian Airworthiness Directive CF–2007–22, dated September 14, 2007 (referred to after this as ‘‘the MCAI’’), to correct an unsafe condition for the specified products. Transport Canada states in the MCAI that it has been determined that the existing hardware connecting the vertical fin to the tail rotor gearbox need to be upgraded, to prevent the vertical fin from becoming loose. BHTC has received reports of loose vertical fins discovered during inspections. Investigation revealed that the current vertical fin attachment E:\FR\FM\23MRP1.SGM 23MRP1 Federal Register / Vol. 74, No. 54 / Monday, March 23, 2009 / Proposed Rules hardware may not provide adequate clamp-up. If not corrected, the vertical fin could become loose and cause vibration, which could lead to subsequent loss of control of the helicopter. You may obtain further information by examining the MCAI and service information in the AD docket. Relevant Service Information Bell Helicopter Textron has issued Alert Service Bulletin No. 427–06–15, dated December 14, 2006. The actions described in the MCAI are intended to correct the same unsafe condition as that identified in the service information. FAA’s Determination and Requirements of This Proposed AD This model helicopter has been approved by Transport Canada, which is the aviation authority of Canada, and is approved for operation in the United States. Pursuant to our bilateral agreement with this State of Design, we have been notified of the unsafe condition described in the MCAI. We are proposing this AD because we evaluated all pertinent information and determined an unsafe condition exists and is likely to exist or develop on other products of this same type design. Differences Between This AD and the MCAI We have reviewed the MCAI and related service information and, in general, agree with their substance. This AD differs from the MCAI as follows: • We do not require compliance ‘‘no later than November 27, 2007’’, because that date has passed. • We refer to the compliance time as ‘‘hours time-in-service’’ rather than ‘‘air time hours.’’ These differences are highlighted in the ‘‘Differences Between this AD and the MCAI’’ section in the AD. dwashington3 on PROD1PC60 with PROPOSALS Costs of Compliance We estimate that this proposed AD would affect about 17 products of U.S. registry. We also estimate that it would take about 2 work-hours per helicopter to remove and visually inspect the vertical fin and the tail rotor gearbox attachment legs and to re-install the vertical fin. The average labor rate is $80 per work-hour. Required parts would cost about $227 per helicopter. Based on these figures, we estimate the cost of the proposed AD on U.S. operators to be $6,579 for the fleet, or $387 per helicopter, to perform the inspections and remove and re-install the vertical fin. VerDate Nov<24>2008 15:23 Mar 20, 2009 Jkt 217001 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 helicopters identified in this rulemaking action. Regulatory Findings We determined that this proposed AD would not have federalism implications under Executive Order 13132. This proposed AD would not have a substantial direct effect on the States, on the relationship between the national Government and the States, or on the distribution of power and responsibilities among the various levels of government. For the reasons discussed above, I certify this proposed regulation: 1. Is not a ‘‘significant regulatory action’’ under Executive Order 12866; 2. Is not a ‘‘significant rule’’ under the DOT Regulatory Policies and Procedures (44 FR 11034, February 26, 1979); 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 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, 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. PO 00000 Frm 00006 Fmt 4702 Sfmt 4702 § 39.13 12099 [Amended] 2. The FAA amends § 39.13 by adding the following new AD: Bell Helicopter Textron Canada (BHTC): Docket No. FAA–2009–0227; Directorate Identifier 2007–SW–65–AD. Comments Due Date (a) We must receive comments by April 22, 2009. Other Affected ADs (b) None. Applicability (c) This AD applies to Model 427 helicopters, serial numbers 56001 through 56057, 58001, and 58002, certificated in any category. Reason (d) Transport Canada states in the mandatory continuing airworthiness information (MCAI) that it has been determined that the existing hardware connecting the vertical fin to the tail rotor gearbox need to be upgraded, to prevent the vertical fin from becoming loose. BHTC has received reports of loose vertical fins discovered during inspections. Investigation revealed that the current vertical fin attachment hardware may not provide adequate clamp-up. If not corrected, the vertical fin could become loose and cause vibration, which could lead to subsequent loss of control of the helicopter. Actions and Compliance (e) Within the next 150 hours time-inservice, unless already done, do the following: (1) Remove the vertical fin and visually inspect the inboard and outboard surfaces of the vertical fin where it attaches to the tail rotor gearbox support for a crack, an elongated bolt hole, fretting, distortion and corrosion. (2) Visually inspect the tail rotor gearbox support attachment legs for a crack, fretting and corrosion. (f) If a crack, elongated bolt hole, fretting, distortion or corrosion is detected, repair or replace the part with an airworthy part before further flight. (g) Reinstall the vertical fin. Differences Between This AD and the MCAI (h) This AD differs from the MCAI as follows: (1) We do not require compliance ‘‘no later than November 27, 2007’’, because that date has passed. (2) We refer to the compliance time as ‘‘hours time-in-service’’ rather than ‘‘air time hours.’’ Other Information (i) Alternative Methods of Compliance (AMOCs): The Manager, Safety Management Group, FAA, has the authority to approve AMOCs for this AD, if requested using the procedures found in 14 CFR 39.19. Send information to ATTN: Sharon Miles, Aviation Safety Engineer, FAA, Rotorcraft Directorate, Regulations and Guidance Group, Fort Worth, Texas 76193–0111, telephone (817) 222–5122, fax (817) 222–5961. E:\FR\FM\23MRP1.SGM 23MRP1 12100 Federal Register / Vol. 74, No. 54 / Monday, March 23, 2009 / Proposed Rules Federal Aviation Administration • Hand Delivery: U.S. Department of Transportation, Docket Operations, M– 30, West Building Ground Floor, Room W12–140, 1200 New Jersey Avenue, SE., Washington, DC 20590, between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. For service information identified in this AD, contact Boeing Commercial Airplanes, Attention: Data & Services Management, 3855 Lakewood Boulevard, MC D800–0019, Long Beach, California 90846–0001; telephone 206– 544–5000, extension 2; fax 206–766– 5683; e-mail dse.boecom@boeing.com; Internet https:// www.myboeingfleet.com. You may review copies of the referenced service information at the FAA, Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton, Washington. For information on the availability of this material at the FAA, call 425–227–1221 or 425–227–1152. 14 CFR Part 39 Examining the AD Docket [Docket No. FAA–2009–0160; Directorate Identifier 2008–NM–176–AD] You may examine the AD docket on the Internet at https:// www.regulations.gov; or in person at the Docket Management Facility between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. The AD docket contains this proposed AD, the regulatory evaluation, any comments received, and other information. The street address for the Docket Office (telephone 800–647–5527) is in the ADDRESSES section. Comments will be available in the AD docket shortly after receipt. FOR FURTHER INFORMATION CONTACT: Roger Durbin, Aerospace Engineer, Airframe Branch, ANM–120L, FAA, Los Angeles Aircraft Certification Office, 3960 Paramount Boulevard, Lakewood, California 90712–4137; telephone (562) 627–5233; fax (562) 627–5210. SUPPLEMENTARY INFORMATION: Related Information (j) Mandatory Continuing Airworthiness Information (MCAI) Transport Canada Airworthiness Directive CF–2007–22, dated September 14, 2007, and Bell Helicopter Textron Alert Service Bulletin No. 427–06– 15, dated December 14, 2006, contain related information. Subject (k) Air Transport Association of America (ATA) Code:5553, Vertical Stabilizer, Attach Fittings. Issued in Fort Worth, Texas, on March 4, 2009. Jerald E. Strentz, Acting Manager, Rotorcraft Directorate, Aircraft Certification Service. [FR Doc. E9–6225 Filed 3–20–09; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION RIN 2120–AA64 Airworthiness Directives; McDonnell Douglas Model MD–90–30 Airplanes dwashington3 on PROD1PC60 with PROPOSALS AGENCY: Federal Aviation Administration (FAA), DOT. ACTION: Notice of proposed rulemaking (NPRM). SUMMARY: We propose to adopt a new airworthiness directive (AD) for all McDonnell Douglas Model MD–90–30 airplanes. This proposed AD would require repetitive inspections for cracks of the upper aft skin panels on the horizontal stabilizer, and related investigative and corrective actions if necessary. This proposed AD results from a report of cracks found in the aft skin panels on the upper right side of the horizontal stabilizer at the aft inboard corner. We are proposing this AD to detect and correct cracks in the fail-safe structure that may not be able to sustain limit load, which could result in the loss of overall structural integrity of the horizontal stabilizer. DATES: We must receive comments on this proposed AD by May 7, 2009. ADDRESSES: You may send comments by any of the following methods: • Federal eRulemaking Portal: Go to https://www.regulations.gov. Follow the instructions for submitting comments. • Fax: 202–493–2251. • Mail: U.S. Department of Transportation, Docket Operations, M– 30, West Building Ground Floor, Room W12–140, 1200 New Jersey Avenue, SE., Washington, DC 20590. VerDate Nov<24>2008 15:23 Mar 20, 2009 Jkt 217001 Comments Invited We invite you to send any written relevant data, views, or arguments about this proposed AD. Send your comments to an address listed under the ADDRESSES section. Include ‘‘Docket No. FAA–2009–0160; Directorate Identifier 2008–NM–176–AD’’ at the beginning of your comments. We specifically invite comments on the overall regulatory, economic, environmental, and energy aspects of this proposed AD. We will consider all comments received by the closing date and may amend this proposed AD because of those comments. We will post all comments we receive, without change, to https:// www.regulations.gov, including any PO 00000 Frm 00007 Fmt 4702 Sfmt 4702 personal information you provide. We will also post a report summarizing each substantive verbal contact we receive about this proposed AD. Discussion We have received a report that one operator found two instances of a crack in the aft skin panel on the upper right side of the horizontal stabilizer at the aft inboard corner. The airplanes had accumulated 16,659 total flight cycles/ 31,403 total flight hours and 18,128 total flight cycles/33,959 total flight hours. The cause of the cracking on the aft skin panel on the upper right side of the horizontal stabilizer is suspected to be fatigue. This condition, if not detected and corrected, could result in cracks in the fail-safe structure that may not be able to sustain limit load, which could result in the loss of overall structural integrity of the horizontal stabilizer. Relevant Service Information We have reviewed Boeing Alert Service Bulletin MD90–55A012, dated September 23, 2008. The service bulletin describes procedures for repetitive eddy current inspections to detect cracks on the upper aft skin panels on the left and right sides of the horizontal stabilizer, and related investigative and corrective actions. The initial compliance time is 13,500 total flight cycles or 24 months after the effective date of this AD, whichever occurs later. The related investigative actions include repetitive eddy current inspections for cracks of the rear spar upper caps of the left and right sides of the horizontal stabilizer. The repetitive interval for the inspection is within 1,600 or 2,100 flight cycles, depending on the previous inspection method used. Corrective actions include, depending on crack findings and crack location, installing the upper aft skin panel splice of the horizontal stabilizer, and replacing the upper aft skin panel of the horizontal stabilizer. The service bulletin describes three options, depending on crack findings and crack location: • (Option 1) The service bulletin describes procedures for a high frequency eddy current inspection of the rear spar cap of the horizontal stabilizer and installation of the upper aft skin panel splice of the horizontal stabilizer before further flight, and an eddy current inspection on the upper aft skin panel of the horizontal stabilizer within 13,500 flight cycles after the installation. If the crack is on the rear spar cap of the horizontal stabilizer, the service bulletin specifies to contact E:\FR\FM\23MRP1.SGM 23MRP1

Agencies

[Federal Register Volume 74, Number 54 (Monday, March 23, 2009)]
[Proposed Rules]
[Pages 12098-12100]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: E9-6225]


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

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2009-0227; Directorate Identifier 2007-SW-65-AD]
RIN 2120-AA64


Airworthiness Directives; Bell Helicopter Textron Canada Model 
427 Helicopters

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 427 helicopters. This 
proposed AD results from mandatory continuing airworthiness information 
(MCAI) originated by the aviation authority of Canada to identify and 
correct an unsafe condition on an aviation product. Transport Canada, 
the aviation authority of Canada, with which we have a bilateral 
agreement, states that it has been determined that the existing 
hardware connecting the vertical fin to the tail rotor gearbox needs to 
be upgraded, to prevent the vertical fin from becoming loose.
    BHTC has received reports of loose vertical fins discovered during 
inspections. Investigation revealed that the current vertical fin 
attachment hardware may not provide adequate clamp-up. If not 
corrected, the vertical fin could become loose and cause vibration, 
which could lead to subsequent loss of control of the helicopter. The 
proposed AD would require actions that are intended to address this 
unsafe condition.

DATES: We must receive comments on this proposed AD by April 22, 2009.

ADDRESSES: You may send comments by any of the following methods:
     Federal eRulemaking Portal: Go to https://www.regulations.gov. Follow the instructions for submitting comments.
     Fax: 202-493-2251.
     Mail: U.S. Department of Transportation, Docket 
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New 
Jersey Avenue, SE., Washington, DC 20590.
     Hand Delivery: U.S. Department of Transportation, Docket 
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New 
Jersey Avenue, SE., Washington, DC 20590, between 9 a.m. and 5 p.m., 
Monday through Friday, except Federal holidays.
    You may get the service information identified in this proposed AD 
from Bell Helicopter Textron Canada, 12,800 Rue de l'Avenir, Mirabel, 
Quebec J7J1R4, telephone (450) 437-2862 or (800) 363-8023, fax (450) 
433-0272, or at https://www.bellcustomer.com/files/.
    Examining the AD Docket: You may examine the AD docket on the 
Internet at https://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 FURTHER INFORMATION CONTACT: Sharon Miles, Aviation Safety 
Engineer, FAA, Rotorcraft Directorate, Regulations and Guidance Group, 
Fort Worth, Texas 76193-0111, telephone (817) 222-5122, fax (817) 222-
5961.

SUPPLEMENTARY INFORMATION:

Comments Invited

    We invite you to send any written relevant data, views, or 
arguments about this proposed AD. Send your comments to an address 
listed under the ADDRESSES section. Include ``Docket No. FAA-2009-0227; 
Directorate Identifier 2007-SW-65-AD'' at the beginning of your 
comments. We specifically invite comments on the overall regulatory, 
economic, environmental, and energy aspects of this proposed AD. We 
will consider all comments received by the closing date and may amend 
this proposed AD based on those comments.
    We will post all comments we receive, without change, to https://www.regulations.gov, including any personal information you provide. We 
will also post a report summarizing each substantive verbal contact we 
receive about this proposed AD.

Discussion

    Transport Canada, which is the aviation authority for Canada, has 
issued an MCAI in the form of Canadian Airworthiness Directive CF-2007-
22, dated September 14, 2007 (referred to after this as ``the MCAI''), 
to correct an unsafe condition for the specified products. Transport 
Canada states in the MCAI that it has been determined that the existing 
hardware connecting the vertical fin to the tail rotor gearbox need to 
be upgraded, to prevent the vertical fin from becoming loose.
    BHTC has received reports of loose vertical fins discovered during 
inspections. Investigation revealed that the current vertical fin 
attachment

[[Page 12099]]

hardware may not provide adequate clamp-up. If not corrected, the 
vertical fin could become loose and cause vibration, which could lead 
to subsequent loss of control of the helicopter.
    You may obtain further information by examining the MCAI and 
service information in the AD docket.

Relevant Service Information

    Bell Helicopter Textron has issued Alert Service Bulletin No. 427-
06-15, dated December 14, 2006. The actions described in the MCAI are 
intended to correct the same unsafe condition as that identified in the 
service information.

FAA's Determination and Requirements of This Proposed AD

    This model helicopter has been approved by Transport Canada, which 
is the aviation authority of Canada, and is approved for operation in 
the United States. Pursuant to our bilateral agreement with this State 
of Design, we have been notified of the unsafe condition described in 
the MCAI. We are proposing this AD because we evaluated all pertinent 
information and determined an unsafe condition exists and is likely to 
exist or develop on other products of this same type design.

Differences Between This AD and the MCAI

    We have reviewed the MCAI and related service information and, in 
general, agree with their substance. This AD differs from the MCAI as 
follows:
     We do not require compliance ``no later than November 27, 
2007'', because that date has passed.
     We refer to the compliance time as ``hours time-in-
service'' rather than ``air time hours.''
    These differences are highlighted in the ``Differences Between this 
AD and the MCAI'' section in the AD.

Costs of Compliance

    We estimate that this proposed AD would affect about 17 products of 
U.S. registry. We also estimate that it would take about 2 work-hours 
per helicopter to remove and visually inspect the vertical fin and the 
tail rotor gearbox attachment legs and to re-install the vertical fin. 
The average labor rate is $80 per work-hour. Required parts would cost 
about $227 per helicopter. Based on these figures, we estimate the cost 
of the proposed AD on U.S. operators to be $6,579 for the fleet, or 
$387 per helicopter, to perform the inspections and remove and re-
install the vertical fin.

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 helicopters identified in this 
rulemaking action.

Regulatory Findings

    We determined that this proposed AD would not have federalism 
implications under Executive Order 13132. This proposed AD would not 
have a substantial direct effect on the States, on the relationship 
between the national Government and the States, or on the distribution 
of power and responsibilities among the various levels of government.
    For the reasons discussed above, I certify this proposed 
regulation:
    1. Is not a ``significant regulatory action'' under Executive Order 
12866;
    2. Is not a ``significant rule'' under the DOT Regulatory Policies 
and Procedures (44 FR 11034, February 26, 1979); 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 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, 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 AD:

Bell Helicopter Textron Canada (BHTC): Docket No. FAA-2009-0227; 
Directorate Identifier 2007-SW-65-AD.

Comments Due Date

    (a) We must receive comments by April 22, 2009.

Other Affected ADs

    (b) None.

Applicability

    (c) This AD applies to Model 427 helicopters, serial numbers 
56001 through 56057, 58001, and 58002, certificated in any category.

Reason

    (d) Transport Canada states in the mandatory continuing 
airworthiness information (MCAI) that it has been determined that 
the existing hardware connecting the vertical fin to the tail rotor 
gearbox need to be upgraded, to prevent the vertical fin from 
becoming loose. BHTC has received reports of loose vertical fins 
discovered during inspections. Investigation revealed that the 
current vertical fin attachment hardware may not provide adequate 
clamp-up. If not corrected, the vertical fin could become loose and 
cause vibration, which could lead to subsequent loss of control of 
the helicopter.

Actions and Compliance

    (e) Within the next 150 hours time-in-service, unless already 
done, do the following:
    (1) Remove the vertical fin and visually inspect the inboard and 
outboard surfaces of the vertical fin where it attaches to the tail 
rotor gearbox support for a crack, an elongated bolt hole, fretting, 
distortion and corrosion.
    (2) Visually inspect the tail rotor gearbox support attachment 
legs for a crack, fretting and corrosion.
    (f) If a crack, elongated bolt hole, fretting, distortion or 
corrosion is detected, repair or replace the part with an airworthy 
part before further flight.
    (g) Reinstall the vertical fin.

Differences Between This AD and the MCAI

    (h) This AD differs from the MCAI as follows:
    (1) We do not require compliance ``no later than November 27, 
2007'', because that date has passed.
    (2) We refer to the compliance time as ``hours time-in-service'' 
rather than ``air time hours.''

Other Information

    (i) Alternative Methods of Compliance (AMOCs): The Manager, 
Safety Management Group, FAA, has the authority to approve AMOCs for 
this AD, if requested using the procedures found in 14 CFR 39.19. 
Send information to ATTN: Sharon Miles, Aviation Safety Engineer, 
FAA, Rotorcraft Directorate, Regulations and Guidance Group, Fort 
Worth, Texas 76193-0111, telephone (817) 222-5122, fax (817) 222-
5961.

[[Page 12100]]

Related Information

    (j) Mandatory Continuing Airworthiness Information (MCAI) 
Transport Canada Airworthiness Directive CF-2007-22, dated September 
14, 2007, and Bell Helicopter Textron Alert Service Bulletin No. 
427-06-15, dated December 14, 2006, contain related information.

Subject

    (k) Air Transport Association of America (ATA) Code:5553, 
Vertical Stabilizer, Attach Fittings.

    Issued in Fort Worth, Texas, on March 4, 2009.
Jerald E. Strentz,
Acting Manager, Rotorcraft Directorate, Aircraft Certification Service.
[FR Doc. E9-6225 Filed 3-20-09; 8:45 am]
BILLING CODE 4910-13-P
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