Airworthiness Directives; Bell Helicopter Textron Canada Limited Model 427 Helicopters, 13061-13063 [2011-4468]

Download as PDF Federal Register / Vol. 76, No. 47 / Thursday, March 10, 2011 / Rules and Regulations Applicability: Model 206A, 206B, 206L, 206L–1, 206L–3, 206L–4, 222, 222B, 222U, 230, 407, 427, and 430 helicopters, with a tail rotor blade (blade) having a part number and serial number, installed, as listed in the Rotor Blades Inc. (RBI) document attached to the ASB No. Revision 206–07–116 ........................................................................... 206L–07–148 ......................................................................... 222–07–106 ........................................................................... 222U–07–77 .......................................................................... 230–07–38 ............................................................................. 407–07–81 ............................................................................. 427–07–18 ............................................................................. 430–07–41 ............................................................................. Compliance: Before further flight, unless accomplished previously. To prevent loss of a blade tip weight, loss of a blade, and subsequent loss of control of the helicopter, do the following: (a) Replace any affected blade with an airworthy blade. An airworthy blade is one that has a part number and a serial number that is not listed in the RBI document attached to each ASB listed in the Applicability section of this AD. (b) 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, Safety Management Group, FAA, ATTN: Sharon Miles, Aviation Safety Engineer, Rotorcraft Directorate, Regulations and Policy Group, 2601 Meacham Blvd., Fort Worth, Texas 76137, telephone (817) 222–5122, fax (817) 222–5961, for information about previously approved alternative methods of compliance. (c) Special flight permits will not be issued. (d) The Joint Aircraft System/Component (JASC) Code is: 6410—Tail Rotor Blades. (e) Determine the affected part number and serial number by referring to the RBI document attached to the following Bell Helicopter Textron Alert Service Bulletins, all dated November 29, 2010: Alert Service Bulletin No. B B D D D B B D .............. .............. .............. .............. .............. .............. .............. .............. November November November November November November November November 29, 29, 29, 29, 29, 29, 29, 29, 2010 2010 2010 2010 2010 2010 2010 2010 code_of_federal_regulations/ ibr_locations.html. (f) This amendment becomes effective on March 25, 2011, to all persons except those persons to whom it was made immediately effective by Emergency AD 2010–26–51, issued December 8, 2010, which contained the requirements of this amendment. Note: The subject of this AD is addressed in Transport Canada (Canada) AD CF–2007– 21R1, dated November 30, 2010. Issued in Fort Worth, Texas, on January 14, 2011. Kim Smith, Manager, Rotorcraft Directorate, Aircraft Certification Service. [FR Doc. 2011–4465 Filed 3–9–11; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2010–0866; Directorate Identifier 2010–SW–065–AD; Amendment 39–16586; AD 2011–03–03] jdjones on DSK8KYBLC1PROD with RULES RIN 2120–AA64 Airworthiness Directives; Bell Helicopter Textron Canada Limited Model 427 Helicopters VerDate Mar<15>2010 14:45 Mar 09, 2011 Jkt 223001 Federal Aviation Administration (FAA), Department of Transportation (DOT). ACTION: Final rule. AGENCY: The Director of the Federal Register approved this incorporation by reference in accordance with 5 U.S.C. 552(a) and 1 CFR part 51. Copies may be obtained 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, or at https:// www.bellcustomer.com/files/. Copies may be inspected at the FAA, Office of the Regional Counsel, Southwest Region, 2601 Meacham Blvd., Room 663, Fort Worth, Texas or at the National Archives and Records Administration (NARA). For information on the availability of this material at NARA, call 202–741–6030, or go to: https:// www.archives.gov/federal_register/ We are adopting a new airworthiness directive (AD) for the products listed above. This AD results from mandatory continuing airworthiness information (MCAI) issued by an aviation authority of another country to identify and correct an unsafe condition on an aviation product. The MCAI describes the unsafe condition as: SUMMARY: Tail rotor driveshaft hanger bearing bracket part number (P/N) 427–044–223–101 has been found cracked due to fatigue. It has been determined that the fatigue cracking PO 00000 Frm 00003 Fmt 4700 following Bell Helicopter Textron Alert Service Bulletins (ASBs), certificated in any category: Date Revision 206–07–116 .............................. 206L–07–148 ............................ 222–07–106 .............................. 222U–07–77 ............................. 230–07–38 ................................ 407–07–81 ................................ 427–07–18 ................................ 430–07–41 ................................ B B D D D B B D Sfmt 4700 13061 Helicopter model .............................. .............................. .............................. .............................. .............................. .............................. .............................. .............................. 206A and 206B Series. 206L, L–1, L–3, and L–4. 222 and 222B. 222U. 230. 407. 427. 430. was initiated by a tooling mark left during manufacture. The existence of tooling marks on the bracket could lead to bracket failure, loss of tail rotor drive and, consequently, loss of control of the helicopter. We are issuing this AD to require actions to correct the unsafe condition on these products. DATES: This AD becomes effective April 14, 2011. On April 14, 2011, the Director of the Federal Register approved the incorporation by reference of certain publications listed in this AD. ADDRESSES: You may examine the AD docket on the Internet at https:// www.regulations.gov or in person at Document Management Facility, U.S. Department of Transportation, Docket Operations, M–30, West Building Ground Floor, Room W12–140, 1200 New Jersey Avenue, SE., Washington, DC 20590. For service information identified in this AD, contact Bell Helicopter Textron, Inc., P.O. Box 482, Fort Worth, TX 76101; telephone: (817) 280–2011; fax: (817) 280–2321; or at https:// www.bellhelicopter.com. 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, Rotorcraft Directorate, 2601 Meacham Blvd., Fort Worth, Texas 76137; telephone: (817) 222–5122; fax: (817) 222–5961. SUPPLEMENTARY INFORMATION: Discussion We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR part 39 to include an AD that would apply to the specified products. That NPRM was published in the Federal Register on August 30, 2010 (75 FR 52912). That NPRM proposed to correct an unsafe condition for the specified products. The MCAI states: E:\FR\FM\10MRR1.SGM 10MRR1 13062 Federal Register / Vol. 76, No. 47 / Thursday, March 10, 2011 / Rules and Regulations Tail rotor driveshaft hanger bearing bracket part number (P/N) 427–044–223–101 has been found cracked due to fatigue. It has been determined that the fatigue cracking was initiated by a tooling mark left during manufacture. The existence of tooling marks on the bracket could lead to bracket failure, loss of tail rotor drive and, consequently, loss of control of the helicopter. The MCAI requires you to rework the tail rotor driveshaft hanger bearing bracket. Comments We gave the public the opportunity to participate in developing this AD. We received no comments on the NPRM or on the determination of the cost to the public. Conclusion We reviewed the available data and determined that air safety and the public interest require adopting the AD as proposed. Differences Between This AD and the MCAI or Service Information We have reviewed the MCAI and related service information and, in general, agree with their substance. But we might have found it necessary to use different words from those in the MCAI to ensure the AD is clear for U.S. operators and is enforceable. In making these changes, we do not intend to differ substantively from the information provided in the MCAI and related service information. We might also have required different actions in this AD from those in the MCAI in order to follow FAA policies. Any such differences are highlighted in a Note within the AD. jdjones on DSK8KYBLC1PROD with RULES Costs of Compliance We estimate that this AD will affect 30 products of U.S. registry. We also estimate that it will take about 4 workhours per product to comply with the basic requirements of this AD. The average labor rate is $85 per work-hour. Based on these figures, we estimate the cost of this AD to the U.S. operators to be $10,200 or $340 per product. In addition, we estimate that any necessary follow-on actions would require parts costing $5,034, for a cost of $5,034 per product. We have no way of determining the number of products that may need these actions. 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 VerDate Mar<15>2010 14:45 Mar 09, 2011 Jkt 223001 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 AD will not have federalism implications under Executive Order 13132. This AD will 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 AD: (1) Is not a ‘‘significant regulatory action’’ under Executive Order 12866; (2) Is not a ‘‘significant rule’’ under 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 regulatory evaluation of the estimated costs to comply with this AD and placed it in the AD Docket. Examining the AD Docket 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 the NPRM, 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. List of Subjects in 14 CFR Part 39 Air transportation, Aircraft, Aviation safety, Incorporation by reference, Safety. Adoption of the Amendment Accordingly, under the authority delegated to me by the Administrator, PO 00000 Frm 00004 Fmt 4700 Sfmt 4700 the FAA amends 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 AD: ■ 2011–03–03 Bell Helicopter Textron Canada Limited: Amendment 39–16586; Docket No. FAA–2010–0866; Directorate Identifier 2010–SW–065–AD. Effective Date (a) This airworthiness directive (AD) becomes effective April 14, 2011. Affected ADs (b) None. Applicability (c) This AD applies to Bell Helicopter Textron Canada Limited Model 427 helicopters, all serial numbers (SNs), certificated in any category. Subject (d) Air Transport Association of America (ATA) Code 65: Tail Rotor Drive. Reason (e) The mandatory continuing airworthiness information (MCAI) states: Tail rotor driveshaft hanger bearing bracket part number (P/N) 427–044–223–101 has been found cracked due to fatigue. It has been determined that the fatigue cracking was initiated by a tooling mark left during manufacture. The existence of tooling marks on the bracket could lead to bracket failure, loss of tail rotor drive and, consequently, loss of control of the helicopter. The MCAI requires you to rework the tail rotor driveshaft hanger bearing bracket. Actions and Compliance (f) Unless already done, do the following actions: (1) Applicable to SNs 56001 through 56073, and 56077: Within 30 days after April 14, 2011 (the effective date of this AD), inspect both sides of the hanger bracket, P/N 427–044–223–101, for cracks following Bell Helicopter Alert Service Bulletin No. 427–09–29, REV A, dated November 17, 2009. (i) If no cracks are found during the inspection required by paragraph (f)(1) of this AD, before further flight, rework both sides of the hanger bracket, P/N 427–044–223–101, following Bell Helicopter Alert Service Bulletin No. 427–09–29, REV A, dated November 17, 2009. (ii) If cracks are found during the inspection required by paragraph (f)(1) of this AD, before further flight, replace the hanger bracket, P/N 427–044–223–101, with a new hanger bracket, P/N 427–044–223–101, that has been reworked following Bell Helicopter E:\FR\FM\10MRR1.SGM 10MRR1 Federal Register / Vol. 76, No. 47 / Thursday, March 10, 2011 / Rules and Regulations Alert Service Bulletin No. 427–09–29, REV A, dated November 17, 2009. (2) Applicable to all SNs: As of April 14, 2011 (the effective date of this AD), you may not install replacement tail rotor driveshaft hanger bracket, P/N 427–044–223–101, unless the bracket has been inspected and found free of cracks and has been reworked following Bell Helicopter Alert Service Bulletin No. 427–09–29, REV A, dated November 17, 2009. FAA AD Differences Note: This AD differs from the MCAI and/ or service information as follows: No differences. jdjones on DSK8KYBLC1PROD with RULES Other FAA AD Provisions (g) The following provisions also apply to this AD: (1) Alternative Methods of Compliance (AMOCs): The Manager, Standards Office, 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, Aerospace Engineer, FAA, Rotorcraft Directorate, 2601 Meacham Blvd., Fort Worth, Texas 76137; telephone: (817) 222–5122; fax: (817) 222–5961. Before using any approved AMOC on any airplane to which the AMOC applies, notify your appropriate principal inspector (PI) in the FAA Flight Standards District Office (FSDO), or lacking a PI, your local FSDO. (2) Airworthy Product: For any requirement in this AD to obtain corrective actions from a manufacturer or other source, use these actions if they are FAA-approved. Corrective actions are considered FAA-approved if they are approved by the State of Design Authority (or their delegated agent). You are required to assure the product is airworthy before it is returned to service. (3) Reporting Requirements: For any reporting requirement in this AD, a federal agency may not conduct or sponsor, and a person is not required to respond to, nor shall a person be subject to a penalty for failure to comply with a collection of information subject to the requirements of the Paperwork Reduction Act unless that collection of information displays a current valid OMB Control Number. The OMB Control Number for this information collection is 2120–0056. Public reporting for this collection of information is estimated to be approximately 5 minutes per response, including the time for reviewing instructions, completing and reviewing the collection of information. All responses to this collection of information are mandatory. Comments concerning the accuracy of this burden and suggestions for reducing the burden should be directed to the FAA at: 800 Independence Ave., SW., Washington, DC 20591, Attn: Information Collection Clearance Officer, AES–200. Related Information (h) Refer to MCAI Transport Canada AD No. CF–2010–17, dated June 2, 2010; and Bell Helicopter Alert Service Bulletin No. 427–09–29, REV A, dated November 17, 2009, for related information. VerDate Mar<15>2010 14:45 Mar 09, 2011 Jkt 223001 Material Incorporated by Reference (i) You must use Bell Helicopter Alert Service Bulletin No. 427–09–29, REV A, dated November 17, 2009, to do the actions required by this AD, unless the AD specifies otherwise. (1) The Director of the Federal Register approved the incorporation by reference of this service information under 5 U.S.C. 552(a) and 1 CFR part 51. (2) For service information identified in this AD, contact Bell Helicopter Textron, Inc., P.O. Box 482, Fort Worth, TX 76101; telephone: (817) 280–2011; fax: (817) 280– 2321; or at https://www.bellhelicopter.com. (3) 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 information on the availability of this material at the FAA, call 816–329–4148. (4) You may also review copies of the service information incorporated by reference for this AD at the National Archives and Records Administration (NARA). For information on the availability of this material at NARA, call (202) 741–6030, or go to: https://www.archives.gov/federal_register/ code_of_federal_regulations/ ibr_locations.html. Issued in Fort Worth, Texas, on January 13, 2011. Kim Smith, Manager, Rotorcraft Directorate, Aircraft Certification Service. [FR Doc. 2011–4468 Filed 3–9–11; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2010–0891; Directorate Identifier 2009–SW–055–AD; Amendment 39–16585, AD 2011–03–02] RIN 2120–AA64 Airworthiness Directives; EUROCOPTER FRANCE Model SA330F, SA330G, and SA330J Helicopters Federal Aviation Administration (FAA), Department of Transportation (DOT). ACTION: Final rule. AGENCY: We are adopting a new airworthiness directive (AD) for the products listed above. This AD results from mandatory continuing airworthiness information (MCAI) issued by an aviation authority of another country to identify and correct an unsafe condition on an aviation product. The MCAI describes the unsafe condition as: SUMMARY: PO 00000 Frm 00005 Fmt 4700 Sfmt 4700 13063 While adjusting the position of the pedal unit on a SA 330 helicopter, the copilot set the position beyond the end limit (‘‘tall pilot’’ position). This resulted in the separation of the pedal adjustment system and the pedals rocking forward. After investigation, it was determined that the Loctite bond on the ‘‘tall pilot’’ stop nut was damaged, most likely due to aging of the adhesive. The nut came loose and could no longer perform its stop function. The threaded rod of the adjustment system separated from the system. The separation of the adjustment system, if not corrected, could result in the loss of control of the pedal units, causing the helicopter to begin rotating. We are issuing this AD to require actions to correct the unsafe condition on these products. DATES: This AD becomes effective April 14, 2011. On April 14, 2011, the Director of the Federal Register approved the incorporation by reference of certain publications listed in this AD. FOR FURTHER INFORMATION CONTACT: Gary B. Roach, Aerospace Engineer, FAA, Rotorcraft Directorate, 2601 Meacham Blvd., Fort Worth, Texas 76137; telephone: (817) 222–5130; fax: (817) 222–5961. SUPPLEMENTARY INFORMATION: Discussion We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR part 39 to include an AD that would apply to the specified products. That NPRM was published in the Federal Register on September 13, 2010 (75 FR 55492). That NPRM proposed to correct an unsafe condition for the specified products. The MCAI states: While adjusting the position of the pedal unit on a SA 330 helicopter, the copilot set the position beyond the end limit (‘‘tall pilot’’ position). This resulted in the separation of the pedal adjustment system and the pedals rocking forward. After investigation, it was determined that the Loctite bond on the ‘‘tall pilot’’ stop nut was damaged, most likely due to aging of the adhesive. The nut came loose and could no longer perform its stop function. The threaded rod of the adjustment system separated from the system. The separation of the adjustment system, if not corrected, could result in the loss of control of the pedal units, causing the helicopter to begin rotating. For the reasons described above, this Emergency AD requires a one-time functional test and modification (MOD 330A779820.00) of the pedal unit adjustment system. Comments We gave the public the opportunity to participate in developing this AD. We received no comments on the NPRM or on the determination of the cost to the public. E:\FR\FM\10MRR1.SGM 10MRR1

Agencies

[Federal Register Volume 76, Number 47 (Thursday, March 10, 2011)]
[Rules and Regulations]
[Pages 13061-13063]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 2011-4468]


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

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2010-0866; Directorate Identifier 2010-SW-065-AD; 
Amendment 39-16586; AD 2011-03-03]
RIN 2120-AA64


Airworthiness Directives; Bell Helicopter Textron Canada Limited 
Model 427 Helicopters

AGENCY: Federal Aviation Administration (FAA), Department of 
Transportation (DOT).

ACTION: Final rule.

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

SUMMARY: We are adopting a new airworthiness directive (AD) for the 
products listed above. This AD results from mandatory continuing 
airworthiness information (MCAI) issued by an aviation authority of 
another country to identify and correct an unsafe condition on an 
aviation product. The MCAI describes the unsafe condition as:

    Tail rotor driveshaft hanger bearing bracket part number (P/N) 
427-044-223-101 has been found cracked due to fatigue. It has been 
determined that the fatigue cracking was initiated by a tooling mark 
left during manufacture.
    The existence of tooling marks on the bracket could lead to 
bracket failure, loss of tail rotor drive and, consequently, loss of 
control of the helicopter.

We are issuing this AD to require actions to correct the unsafe 
condition on these products.

DATES: This AD becomes effective April 14, 2011.
    On April 14, 2011, the Director of the Federal Register approved 
the incorporation by reference of certain publications listed in this 
AD.

ADDRESSES: You may examine the AD docket on the Internet at https://www.regulations.gov or in person at Document Management Facility, U.S. 
Department of Transportation, Docket Operations, M-30, West Building 
Ground Floor, Room W12-140, 1200 New Jersey Avenue, SE., Washington, DC 
20590.
    For service information identified in this AD, contact Bell 
Helicopter Textron, Inc., P.O. Box 482, Fort Worth, TX 76101; 
telephone: (817) 280-2011; fax: (817) 280-2321; or at https://www.bellhelicopter.com. 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, 
Rotorcraft Directorate, 2601 Meacham Blvd., Fort Worth, Texas 76137; 
telephone: (817) 222-5122; fax: (817) 222-5961.

SUPPLEMENTARY INFORMATION: 

Discussion

    We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR 
part 39 to include an AD that would apply to the specified products. 
That NPRM was published in the Federal Register on August 30, 2010 (75 
FR 52912). That NPRM proposed to correct an unsafe condition for the 
specified products. The MCAI states:


[[Page 13062]]


    Tail rotor driveshaft hanger bearing bracket part number (P/N) 
427-044-223-101 has been found cracked due to fatigue. It has been 
determined that the fatigue cracking was initiated by a tooling mark 
left during manufacture.
    The existence of tooling marks on the bracket could lead to 
bracket failure, loss of tail rotor drive and, consequently, loss of 
control of the helicopter.

    The MCAI requires you to rework the tail rotor driveshaft hanger 
bearing bracket.

Comments

    We gave the public the opportunity to participate in developing 
this AD. We received no comments on the NPRM or on the determination of 
the cost to the public.

Conclusion

    We reviewed the available data and determined that air safety and 
the public interest require adopting the AD as proposed.

Differences Between This AD and the MCAI or Service Information

    We have reviewed the MCAI and related service information and, in 
general, agree with their substance. But we might have found it 
necessary to use different words from those in the MCAI to ensure the 
AD is clear for U.S. operators and is enforceable. In making these 
changes, we do not intend to differ substantively from the information 
provided in the MCAI and related service information.
    We might also have required different actions in this AD from those 
in the MCAI in order to follow FAA policies. Any such differences are 
highlighted in a Note within the AD.

Costs of Compliance

    We estimate that this AD will affect 30 products of U.S. registry. 
We also estimate that it will take about 4 work-hours per product to 
comply with the basic requirements of this AD. The average labor rate 
is $85 per work-hour.
    Based on these figures, we estimate the cost of this AD to the U.S. 
operators to be $10,200 or $340 per product.
    In addition, we estimate that any necessary follow-on actions would 
require parts costing $5,034, for a cost of $5,034 per product. We have 
no way of determining the number of products that may need these 
actions.

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 AD will not have federalism implications 
under Executive Order 13132. This AD will 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 AD:
    (1) Is not a ``significant regulatory action'' under Executive 
Order 12866;
    (2) Is not a ``significant rule'' under 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 regulatory evaluation of the estimated costs to 
comply with this AD and placed it in the AD Docket.

Examining the AD Docket

    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 the NPRM, 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.

List of Subjects in 14 CFR Part 39

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

Adoption of the Amendment

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

PART 39--AIRWORTHINESS DIRECTIVES

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

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


Sec.  39.13  [Amended]

0
2. The FAA amends Sec.  39.13 by adding the following new AD:

2011-03-03 Bell Helicopter Textron Canada Limited: Amendment 39-
16586; Docket No. FAA-2010-0866; Directorate Identifier 2010-SW-065-
AD.

Effective Date

    (a) This airworthiness directive (AD) becomes effective April 
14, 2011.

Affected ADs

    (b) None.

Applicability

    (c) This AD applies to Bell Helicopter Textron Canada Limited 
Model 427 helicopters, all serial numbers (SNs), certificated in any 
category.

Subject

    (d) Air Transport Association of America (ATA) Code 65: Tail 
Rotor Drive.

Reason

    (e) The mandatory continuing airworthiness information (MCAI) 
states:
    Tail rotor driveshaft hanger bearing bracket part number (P/N) 
427-044-223-101 has been found cracked due to fatigue. It has been 
determined that the fatigue cracking was initiated by a tooling mark 
left during manufacture.
    The existence of tooling marks on the bracket could lead to 
bracket failure, loss of tail rotor drive and, consequently, loss of 
control of the helicopter.

The MCAI requires you to rework the tail rotor driveshaft hanger 
bearing bracket.

Actions and Compliance

    (f) Unless already done, do the following actions:
    (1) Applicable to SNs 56001 through 56073, and 56077: Within 30 
days after April 14, 2011 (the effective date of this AD), inspect 
both sides of the hanger bracket, P/N 427-044-223-101, for cracks 
following Bell Helicopter Alert Service Bulletin No. 427-09-29, REV 
A, dated November 17, 2009.
    (i) If no cracks are found during the inspection required by 
paragraph (f)(1) of this AD, before further flight, rework both 
sides of the hanger bracket, P/N 427-044-223-101, following Bell 
Helicopter Alert Service Bulletin No. 427-09-29, REV A, dated 
November 17, 2009.
    (ii) If cracks are found during the inspection required by 
paragraph (f)(1) of this AD, before further flight, replace the 
hanger bracket, P/N 427-044-223-101, with a new hanger bracket, P/N 
427-044-223-101, that has been reworked following Bell Helicopter

[[Page 13063]]

Alert Service Bulletin No. 427-09-29, REV A, dated November 17, 
2009.
    (2) Applicable to all SNs: As of April 14, 2011 (the effective 
date of this AD), you may not install replacement tail rotor 
driveshaft hanger bracket, P/N 427-044-223-101, unless the bracket 
has been inspected and found free of cracks and has been reworked 
following Bell Helicopter Alert Service Bulletin No. 427-09-29, REV 
A, dated November 17, 2009.

FAA AD Differences

    Note:  This AD differs from the MCAI and/or service information 
as follows: No differences.

Other FAA AD Provisions

    (g) The following provisions also apply to this AD:
    (1) Alternative Methods of Compliance (AMOCs): The Manager, 
Standards Office, 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, Aerospace Engineer, FAA, 
Rotorcraft Directorate, 2601 Meacham Blvd., Fort Worth, Texas 76137; 
telephone: (817) 222-5122; fax: (817) 222-5961. Before using any 
approved AMOC on any airplane to which the AMOC applies, notify your 
appropriate principal inspector (PI) in the FAA Flight Standards 
District Office (FSDO), or lacking a PI, your local FSDO.
    (2) Airworthy Product: For any requirement in this AD to obtain 
corrective actions from a manufacturer or other source, use these 
actions if they are FAA-approved. Corrective actions are considered 
FAA-approved if they are approved by the State of Design Authority 
(or their delegated agent). You are required to assure the product 
is airworthy before it is returned to service.
    (3) Reporting Requirements: For any reporting requirement in 
this AD, a federal agency may not conduct or sponsor, and a person 
is not required to respond to, nor shall a person be subject to a 
penalty for failure to comply with a collection of information 
subject to the requirements of the Paperwork Reduction Act unless 
that collection of information displays a current valid OMB Control 
Number. The OMB Control Number for this information collection is 
2120-0056. Public reporting for this collection of information is 
estimated to be approximately 5 minutes per response, including the 
time for reviewing instructions, completing and reviewing the 
collection of information. All responses to this collection of 
information are mandatory. Comments concerning the accuracy of this 
burden and suggestions for reducing the burden should be directed to 
the FAA at: 800 Independence Ave., SW., Washington, DC 20591, Attn: 
Information Collection Clearance Officer, AES-200.

Related Information

    (h) Refer to MCAI Transport Canada AD No. CF-2010-17, dated June 
2, 2010; and Bell Helicopter Alert Service Bulletin No. 427-09-29, 
REV A, dated November 17, 2009, for related information.

Material Incorporated by Reference

    (i) You must use Bell Helicopter Alert Service Bulletin No. 427-
09-29, REV A, dated November 17, 2009, to do the actions required by 
this AD, unless the AD specifies otherwise.
    (1) The Director of the Federal Register approved the 
incorporation by reference of this service information under 5 
U.S.C. 552(a) and 1 CFR part 51.
    (2) For service information identified in this AD, contact Bell 
Helicopter Textron, Inc., P.O. Box 482, Fort Worth, TX 76101; 
telephone: (817) 280-2011; fax: (817) 280-2321; or at https://www.bellhelicopter.com.
    (3) 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 information on 
the availability of this material at the FAA, call 816-329-4148.
    (4) You may also review copies of the service information 
incorporated by reference for this AD at the National Archives and 
Records Administration (NARA). For information on the availability 
of this material at NARA, call (202) 741-6030, or go to: https://www.archives.gov/federal_register/code_of_federal_regulations/ibr_locations.html.

    Issued in Fort Worth, Texas, on January 13, 2011.
Kim Smith,
Manager, Rotorcraft Directorate, Aircraft Certification Service.
[FR Doc. 2011-4468 Filed 3-9-11; 8:45 am]
BILLING CODE 4910-13-P
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