Airworthiness Directives; Boeing Vertol (Type Certificate Currently Held by Columbia Helicopters, Inc. (CHI)) and Kawasaki Heavy Industries, Limited Helicopters (Kawasaki), 42954-42956 [2012-17278]

Download as PDF 42954 Federal Register / Vol. 77, No. 141 / Monday, July 23, 2012 / Rules and Regulations accordance with the Accomplishment Instructions of Airbus Service Bulletin A320– 53–1218, Revision 01, including Appendices 01 and 02, dated June 17, 2010. If any cracking is found, before further flight, repair in accordance with the Accomplishment Instructions of Airbus Service Bulletin A320– 53–1218, Revision 01, including Appendices 01 and 02, dated June 17, 2010. (h) Reporting Submit a report of the findings of the inspection required by paragraph (g) of this AD to Airbus in accordance with Appendix 01 of Airbus Service Bulletin A320–53–1218, Revision 01, including Appendices 01 and 02, dated June 17, 2010, at the applicable time specified in paragraph (h)(1) or (h)(2) of this AD. (1) If the inspection was done on or after the effective date of this AD: Submit the report within 90 days after the inspection. (2) If the inspection was done before the effective date of this AD: Submit the report within 90 days after the effective date of this AD. mstockstill on DSK4VPTVN1PROD with RULES (i) Credit for Previous Actions This paragraph provides credit for inspections and replacements required by paragraph (g) of this AD, if those actions were performed before the effective date of this AD using Airbus Service Bulletin A320–53–1218, including Appendices 01 and 02, dated February 8, 2010. (j) Other FAA AD Provisions The following provisions also apply to this AD: (1) Alternative Methods of Compliance (AMOCs): The Manager, International Branch, ANM–116, FAA, has the authority to approve AMOCs for this AD, if requested using the procedures found in 14 CFR 39.19. In accordance with 14 CFR 39.19, send your request to your principal inspector or local Flight Standards District Office, as appropriate. If sending information directly to the International Branch, send it to ATTN: Sanjay Ralhan, Aerospace Engineer, International Branch, ANM–116, Transport Airplane Directorate, FAA, 1601 Lind Avenue SW., Renton, Washington 98057– 3356; phone: 425–227–1405; fax: 425–227– 1149. Information may be emailed to: 9ANM-116-AMOC-REQUESTS@faa.gov. Before using any approved AMOC, notify your appropriate principal inspector, or lacking a principal inspector, the manager of the local flight standards district office/ certificate holding district office. The AMOC approval letter must specifically reference this AD. (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: 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 VerDate Mar<15>2010 16:44 Jul 20, 2012 Jkt 226001 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. DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2012–0730; Directorate Identifier 2012–SW–048–AD; Amendment 39–17124; AD 2012–14–10] RIN 2120–AA64 Airworthiness Directives; Boeing Vertol (Type Certificate Currently Held by Columbia Helicopters, Inc. (CHI)) and Kawasaki Heavy Industries, Limited Helicopters (Kawasaki) (k) Related Information Refer to MCAI European Aviation Safety Agency Airworthiness Directive 2011– 0120R1, dated July 13, 2011; and Airbus Service Bulletin A320–53–1218, Revision 01, including Appendices 01 and 02, dated June 17, 2010; for related information. Federal Aviation Administration (FAA), Department of Transportation (DOT). ACTION: Final rule; request for comments. SUMMARY: (l) Material Incorporated by Reference (1) The Director of the Federal Register approved the incorporation by reference (IBR) of the following service information under 5 U.S.C. 552(a) and 1 CFR part 51. (2) You must use the following service information to do the actions required by this AD, unless the AD specifies otherwise. (i) Airbus Service Bulletin A320–53–1218, Revision 01, including Appendices 01 and 02, dated June 17, 2010. (3) For service information identified in this AD, contact Airbus, Airworthiness Office—EAS, 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex, France; telephone +33 5 61 93 36 96; fax +33 5 61 93 44 51; email account.airworth-eas@airbus.com; Internet http://www.airbus.com. (4) You may review copies of the 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. (5) You may also review copies of the service information that is incorporated by reference at the National Archives and Records Administration (NARA). For information on the availability of this material at an NARA facility, call 202–741– 6030, or go to http://www.archives.gov/ federal_register/code_of_federal_regulations/ ibr_locations.html. Issued in Renton, Washington, on July 5, 2012. Kalene C. Yanamura, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 2012–17389 Filed 7–20–12; 8:45 am] BILLING CODE 4910–13–P PO 00000 Frm 00006 Fmt 4700 Sfmt 4700 AGENCY: We are adopting a new airworthiness directive (AD) for CHI Model 107–II and Kawasaki Model KV107–II and KV107–IIA helicopters. This AD requires, before further flight, replacing certain upper collective pitch control yoke bolts. This AD is prompted by three failures of the affected bolts. These actions are intended to prevent failure of an upper collective pitch control yoke bolt (bolt), excessive vibration, migration of the shafts, and subsequent loss of control of the helicopter. This AD becomes effective August 7, 2012. We must receive comments on this AD by September 21, 2012. ADDRESSES: You may send comments by any of the following methods: • Federal eRulemaking Docket: Go to http://www.regulations.gov. Follow the online instructions for sending your comments electronically. • Fax: 202–493–2251. • Mail: Send comments to the U.S. Department of Transportation, Docket Operations, M–30, West Building Ground Floor, Room W12–140, 1200 New Jersey Avenue SE., Washington, DC 20590–0001. • Hand Delivery: Deliver to the ‘‘Mail’’ address between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. DATES: Examining the AD Docket You may examine the AD docket on the Internet at http:// www.regulations.gov or in person at the Docket Operations Office between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. The AD docket contains this AD, the economic evaluation, any comments received, and other information. The street address for E:\FR\FM\23JYR1.SGM 23JYR1 Federal Register / Vol. 77, No. 141 / Monday, July 23, 2012 / Rules and Regulations the Docket Operations Office (telephone 800–647–5527) is in the ADDRESSES section. Comments will be available in the AD docket shortly after receipt. For service information identified in this AD, contact Columbia Helicopters, Inc.; 14452 Arndt Road NE., Aurora, OR 97002; telephone (503) 678–1222; email ContactEngineering@colheli.com; or at www.ColHeli.com. You may review the referenced service information at the FAA, Office of the Regional Counsel, Southwest Region, 2601 Meacham Blvd., Room 663, Fort Worth, Texas 76137. FOR FURTHER INFORMATION CONTACT: Kathleen Arrigotti, Aviation Safety Engineer, Seattle Aircraft Certification Office, Transport Airplane Directorate, FAA, 1601 Lind Avenue SW., Renton, Washington 98057; telephone (425) 917–6426; email kathleen.arrigotti@faa.gov. SUPPLEMENTARY INFORMATION: mstockstill on DSK4VPTVN1PROD with RULES Comments Invited This AD is a final rule that involves requirements affecting flight safety, and we did not provide you with notice and an opportunity to provide your comments prior to it becoming effective. However, we invite you to participate in this rulemaking by submitting written comments, data, or views. We also invite comments relating to the economic, environmental, energy, or federalism impacts that resulted from adopting this AD. The most helpful comments reference a specific portion of the AD, explain the reason for any recommended change, and include supporting data. To ensure the docket does not contain duplicate comments, commenters should send only one copy of written comments, or if comments are filed electronically, commenters should submit them only one time. We will file in the docket all comments that we receive, as well as a report summarizing each substantive public contact with FAA personnel concerning this rulemaking during the comment period. We will consider all the comments we receive and may conduct additional rulemaking based on those comments. Discussion We are adopting a new AD for CHI Model 107–II and Kawasaki Model KV107–II and KV107–IIA helicopters. This AD requires replacing certain partnumbered bolts. The bolts are located in the forward and aft rotor upper collective pitch control assemblies. Upon failure, the yoke bolt head shears off, allowing shafts around the bolt to migrate out of place. If the shaft migrates fully out of place, the rotor VerDate Mar<15>2010 16:44 Jul 20, 2012 Jkt 226001 pitch cannot be controlled. This AD is prompted by multiple failures of the affected bolts at low flight hours. These actions are intended to prevent failure of a bolt, excessive vibration, migration of the shafts, and subsequent loss of control of the helicopter. FAA’s Determination We are issuing this AD because we evaluated all the relevant information and determined the unsafe condition described previously is likely to exist or develop in other helicopters of the same type designs. Related Service Information CHI issued Service Bulletin No. 107– 27–0005 (SB), Revision 0, dated April 26, 2012. The SB specifies replacing all bolts, part number (P/N) 107C2733–1 and P/N 107C2733–2, with bolts, P/N C07C2700–1. The SB also specifies modifying spare assemblies, daily inspections of the yoke bolt retaining nut, and recurring 35-hour inspections of the bolt. AD Requirements This AD requires, before further flight, replacing all affected bolts with airworthy bolts, P/N C07C2700–1, and torquing the nut to 450–500 in-lbs. This AD also prohibits installing washer P/N A02C3112–13 with bolt P/N C07C2700– 1, and installing bolt P/N 107C2733–1 and P/N 107C2733–2 on any helicopter. Differences Between This AD and the Service Information The CHI SB requires a repetitive daily inspection of the yoke bolt retaining nut, and a repetitive 35-hour inspection of the bolts after replacement. This AD does not require those inspections. The SB also specifies modifying spare assemblies. This AD does not address parts that are not installed. Costs of Compliance We estimate that this AD will affect 12 helicopters of U.S. Registry. We estimate that operators may incur the following costs in order to comply with this AD: Replacing the bolts will take 4 hours at an average labor rate of $85 per work hour. Required parts will cost $2,000. The total cost per helicopter is $2,340 and the total cost for the entire U.S. fleet is $28,080. FAA’s Justification and Determination of the Effective Date Providing an opportunity for public comments before adopting these AD requirements would delay implementing the safety actions needed to correct a previously described known critical unsafe condition, which can PO 00000 Frm 00007 Fmt 4700 Sfmt 4700 42955 adversely affect the structural integrity and controllability of the helicopter. Therefore, we find that the risk to the flying public justifies waiving notice and comment prior to the adoption of this rule because the required corrective actions must be accomplished before further flight. Since an unsafe condition exists that requires the immediate adoption of this AD, we determined that notice and opportunity for public comment before issuing this AD are impracticable and that good cause exists for making this amendment effective in less than 30 days. 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, I certify that 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); 3. Will not affect intrastate aviation in Alaska to the extent that it justifies making a regulatory distinction; and 4. Will not have a significant economic impact, positive or negative, on a substantial number of small entities under the criteria of the Regulatory Flexibility Act. E:\FR\FM\23JYR1.SGM 23JYR1 42956 Federal Register / Vol. 77, No. 141 / Monday, July 23, 2012 / Rules and Regulations We prepared an economic evaluation of the estimated costs to comply with this AD and placed it in the AD docket. List of Subjects in 14 CFR Part 39 Air transportation, Aircraft, Aviation safety, Incorporation by reference, Safety. 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 1. The authority citation for part 39 continues to read as follows: ■ Authority: 49 U.S.C. 106(g), 40113, 44701. § 39.13 [Amended] 2. The FAA amends § 39.13 by adding the following new airworthiness directive (AD): ■ 2012–14–10 Boeing Vertol (Type Certificate Currently Held by Columbia Helicopters, Inc.) and Kawasaki Heavy Industries, Limited Helicopters: Amendment 39–17124; Docket No. FAA–2012–0730; Directorate Identifier 2012–SW–048–AD. (a) Applicability This AD applies to Boeing Vertol (type certificate currently held by Columbia Helicopters, Inc. (CHI)) Model 107–II and Kawasaki Heavy Industries, Limited Model KV107–II and KV107–IIA helicopters with an upper collective pitch control assembly, part number (P/N) 107CK003–2 or 107CK002–2, installed, certificated in any category. (f) Alternative Methods of Compliance (AMOCs) (1) The Manager, Seattle Aircraft Certification Office, FAA, may approve AMOCs for this AD. Send your proposal to: Kathleen Arrigotti, Aviation Safety Engineer, Seattle Aircraft Certification Office, Transport Airplane Directorate, FAA, 1601 Lind Avenue SW., Renton, Washington 98057; telephone (425) 917–6426; email 9ANM-Seattle-ACO-AMOC-Requests@faa.gov. (2) For operations conducted under a 14 CFR part 119 operating certificate or under 14 CFR part 91, subpart K, we suggest that you notify your principal inspector, or lacking a principal inspector, the manager of the local flight standards district office or certificate holding district office, before operating any aircraft complying with this EAD through an AMOC. (g) Additional Information CHI Service Bulletin No. 107–27–0005 (SB), Revision 0, dated April 26, 2012, which is not incorporated by reference, contains additional information about the subject of this AD. For service information identified in this AD, contact Columbia Helicopters, Inc.; 14452 Arndt Road NE., Aurora, OR 97002; telephone (503) 678–1222; email ContactEngineering@colheli.com; or at www.ColHeli.com. You may review the referenced service information at the FAA, Office of the Regional Counsel, Southwest Region, 2601 Meacham Blvd., Room 663, Fort Worth, Texas 76137. (h) Subject Joint Aircraft Service Component (JASC) Code: 6230 Main Rotor Mast/Swashplate. Issued in Fort Worth, Texas, on July 5, 2012. Kim Smith, Manager, Rotorcraft Directorate, Aircraft Certification Service. [FR Doc. 2012–17278 Filed 7–20–12; 8:45 am] BILLING CODE 4910–13–P (b) Unsafe Condition This AD defines the unsafe condition as failure of an upper collective pitch control yoke bolt (bolt). This condition could result in excessive vibration, migration of the shafts, and subsequent loss of control of the helicopter. (c) Effective Date This AD becomes effective August 7, 2012. DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2012–0271; Directorate Identifier 2011–NM–196–AD; Amendment 39–17118; AD 2012–14–04] (d) Compliance RIN 2120–AA64 You are responsible for performing each action required by this AD within the specified compliance time unless it has already been accomplished prior to that time. Airworthiness Directives; Bombardier, Inc. Airplanes mstockstill on DSK4VPTVN1PROD with RULES (e) Required Actions Before further flight, replace bolts, P/N 107C2733–1 and P/N 107C2733–2, with airworthy bolts, P/N C07C2700–1. Torque each nut to 450–500 in-lbs. Do not install a washer, P/N A02C3112–13 with a bolt, P/N C07C2700–1. Do not install bolts, P/N 107C2733–1 and P/N 107C2733–2, on any helicopter. VerDate Mar<15>2010 16:44 Jul 20, 2012 Jkt 226001 Federal Aviation Administration (FAA), Department of Transportation (DOT). ACTION: Final rule. AGENCY: We are adopting a new airworthiness directive (AD) for certain Bombardier, Inc. Model DHC–8–100, DHC–8–200, and DHC–8–300 series airplanes. This AD was prompted by SUMMARY: PO 00000 Frm 00008 Fmt 4700 Sfmt 4700 reports of hydraulic accumulator screw cap or end cap failure. This AD requires replacing the affected parking brake accumulator. We are issuing this AD to prevent failure of the parking brake accumulator screw caps or end caps, which could result in loss of the number 2 hydraulic system and damage to airplane structures, and could potentially have an adverse effect on the controllability of the airplane. DATES: This AD becomes effective August 27, 2012. The Director of the Federal Register approved the incorporation by reference of certain publications listed in this AD as of August 27, 2012. ADDRESSES: You may examine the AD docket on the Internet at http://www. regulations.gov or in person at the U.S. Department of Transportation, Docket Operations, M–30, West Building Ground Floor, Room W12–140, 1200 New Jersey Avenue SE., Washington, DC. FOR FURTHER INFORMATION CONTACT: Cesar Gomez, Aerospace Engineer, Airframe and Mechanical Systems Branch, ANE–171, FAA, New York Aircraft Certification Office, 1600 Stewart Avenue, Suite 410, Westbury, New York 11590; telephone (516) 228– 7318; fax (516) 794–5531. 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 March 21, 2012 (77 FR 16488). That NPRM proposed to correct an unsafe condition for the specified products. The MCAI states: Seven cases of on-ground hydraulic accumulator screw cap or end cap failure have been experienced on CL–600–2B19 (CRJ) aeroplanes, resulting in loss of the associated hydraulic system and high-energy impact damage to adjacent systems and structure. To date, the lowest number of flight cycles accumulated at the time of failure has been 6991. Although there have been no failures to date on any DHC–8 aeroplanes, similar accumulators to those installed on the CL– 600–2B19, Part Numbers (P/N)0860162001 and 0860162002 (Parking Brake Accumulator), are installed on the aeroplanes listed in the Applicability section of this [TCCA] directive. A detailed analysis of the systems and structure in the potential line of trajectory of a failed screw cap/end cap for the accumulator has been conducted. It has identified that the worst-case scenarios would be the loss of number 2 hydraulic system, and damage to aeroplane structures. E:\FR\FM\23JYR1.SGM 23JYR1

Agencies

[Federal Register Volume 77, Number 141 (Monday, July 23, 2012)]
[Rules and Regulations]
[Pages 42954-42956]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 2012-17278]


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

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2012-0730; Directorate Identifier 2012-SW-048-AD; 
Amendment 39-17124; AD 2012-14-10]
RIN 2120-AA64


Airworthiness Directives; Boeing Vertol (Type Certificate 
Currently Held by Columbia Helicopters, Inc. (CHI)) and Kawasaki Heavy 
Industries, Limited Helicopters (Kawasaki)

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

ACTION: Final rule; request for comments.

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

SUMMARY: We are adopting a new airworthiness directive (AD) for CHI 
Model 107-II and Kawasaki Model KV107-II and KV107-IIA helicopters. 
This AD requires, before further flight, replacing certain upper 
collective pitch control yoke bolts. This AD is prompted by three 
failures of the affected bolts. These actions are intended to prevent 
failure of an upper collective pitch control yoke bolt (bolt), 
excessive vibration, migration of the shafts, and subsequent loss of 
control of the helicopter.

DATES: This AD becomes effective August 7, 2012.
    We must receive comments on this AD by September 21, 2012.

ADDRESSES: You may send comments by any of the following methods:
     Federal eRulemaking Docket: Go to http://www.regulations.gov. Follow the online instructions for sending your 
comments electronically.
     Fax: 202-493-2251.
     Mail: Send comments to the U.S. Department of 
Transportation, Docket Operations, M-30, West Building Ground Floor, 
Room W12-140, 1200 New Jersey Avenue SE., Washington, DC 20590-0001.
     Hand Delivery: Deliver to the ``Mail'' address between 9 
a.m. and 5 p.m., Monday through Friday, except Federal holidays.

Examining the AD Docket

    You may examine the AD docket on the Internet at http://www.regulations.gov or in person at the Docket Operations Office 
between 9 a.m. and 5 p.m., Monday through Friday, except Federal 
holidays. The AD docket contains this AD, the economic evaluation, any 
comments received, and other information. The street address for

[[Page 42955]]

the Docket Operations Office (telephone 800-647-5527) is in the 
ADDRESSES section. Comments will be available in the AD docket shortly 
after receipt.
    For service information identified in this AD, contact Columbia 
Helicopters, Inc.; 14452 Arndt Road NE., Aurora, OR 97002; telephone 
(503) 678-1222; email ContactEngineering@colheli.com; or at 
www.ColHeli.com. You may review the referenced service information at 
the FAA, Office of the Regional Counsel, Southwest Region, 2601 Meacham 
Blvd., Room 663, Fort Worth, Texas 76137.

FOR FURTHER INFORMATION CONTACT: Kathleen Arrigotti, Aviation Safety 
Engineer, Seattle Aircraft Certification Office, Transport Airplane 
Directorate, FAA, 1601 Lind Avenue SW., Renton, Washington 98057; 
telephone (425) 917-6426; email kathleen.arrigotti@faa.gov.

SUPPLEMENTARY INFORMATION:

Comments Invited

    This AD is a final rule that involves requirements affecting flight 
safety, and we did not provide you with notice and an opportunity to 
provide your comments prior to it becoming effective. However, we 
invite you to participate in this rulemaking by submitting written 
comments, data, or views. We also invite comments relating to the 
economic, environmental, energy, or federalism impacts that resulted 
from adopting this AD. The most helpful comments reference a specific 
portion of the AD, explain the reason for any recommended change, and 
include supporting data. To ensure the docket does not contain 
duplicate comments, commenters should send only one copy of written 
comments, or if comments are filed electronically, commenters should 
submit them only one time. We will file in the docket all comments that 
we receive, as well as a report summarizing each substantive public 
contact with FAA personnel concerning this rulemaking during the 
comment period. We will consider all the comments we receive and may 
conduct additional rulemaking based on those comments.

Discussion

    We are adopting a new AD for CHI Model 107-II and Kawasaki Model 
KV107-II and KV107-IIA helicopters. This AD requires replacing certain 
part-numbered bolts. The bolts are located in the forward and aft rotor 
upper collective pitch control assemblies. Upon failure, the yoke bolt 
head shears off, allowing shafts around the bolt to migrate out of 
place. If the shaft migrates fully out of place, the rotor pitch cannot 
be controlled. This AD is prompted by multiple failures of the affected 
bolts at low flight hours. These actions are intended to prevent 
failure of a bolt, excessive vibration, migration of the shafts, and 
subsequent loss of control of the helicopter.

FAA's Determination

    We are issuing this AD because we evaluated all the relevant 
information and determined the unsafe condition described previously is 
likely to exist or develop in other helicopters of the same type 
designs.

Related Service Information

    CHI issued Service Bulletin No. 107-27-0005 (SB), Revision 0, dated 
April 26, 2012. The SB specifies replacing all bolts, part number (P/N) 
107C2733-1 and P/N 107C2733-2, with bolts, P/N C07C2700-1. The SB also 
specifies modifying spare assemblies, daily inspections of the yoke 
bolt retaining nut, and recurring 35-hour inspections of the bolt.

AD Requirements

    This AD requires, before further flight, replacing all affected 
bolts with airworthy bolts, P/N C07C2700-1, and torquing the nut to 
450-500 in-lbs. This AD also prohibits installing washer P/N A02C3112-
13 with bolt P/N C07C2700-1, and installing bolt P/N 107C2733-1 and P/N 
107C2733-2 on any helicopter.

Differences Between This AD and the Service Information

    The CHI SB requires a repetitive daily inspection of the yoke bolt 
retaining nut, and a repetitive 35-hour inspection of the bolts after 
replacement. This AD does not require those inspections. The SB also 
specifies modifying spare assemblies. This AD does not address parts 
that are not installed.

Costs of Compliance

    We estimate that this AD will affect 12 helicopters of U.S. 
Registry. We estimate that operators may incur the following costs in 
order to comply with this AD: Replacing the bolts will take 4 hours at 
an average labor rate of $85 per work hour. Required parts will cost 
$2,000. The total cost per helicopter is $2,340 and the total cost for 
the entire U.S. fleet is $28,080.

FAA's Justification and Determination of the Effective Date

    Providing an opportunity for public comments before adopting these 
AD requirements would delay implementing the safety actions needed to 
correct a previously described known critical unsafe condition, which 
can adversely affect the structural integrity and controllability of 
the helicopter. Therefore, we find that the risk to the flying public 
justifies waiving notice and comment prior to the adoption of this rule 
because the required corrective actions must be accomplished before 
further flight.
    Since an unsafe condition exists that requires the immediate 
adoption of this AD, we determined that notice and opportunity for 
public comment before issuing this AD are impracticable and that good 
cause exists for making this amendment effective in less than 30 days.

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, I certify that 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);
    3. Will not affect intrastate aviation in Alaska to the extent that 
it justifies making a regulatory distinction; and
    4. Will not have a significant economic impact, positive or 
negative, on a substantial number of small entities under the criteria 
of the Regulatory Flexibility Act.

[[Page 42956]]

    We prepared an economic evaluation of the estimated costs to comply 
with this AD and placed it in the AD docket.

List of Subjects in 14 CFR Part 39

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

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 airworthiness 
directive (AD):

2012-14-10 Boeing Vertol (Type Certificate Currently Held by 
Columbia Helicopters, Inc.) and Kawasaki Heavy Industries, Limited 
Helicopters: Amendment 39-17124; Docket No. FAA-2012-0730; 
Directorate Identifier 2012-SW-048-AD.

(a) Applicability

    This AD applies to Boeing Vertol (type certificate currently 
held by Columbia Helicopters, Inc. (CHI)) Model 107-II and Kawasaki 
Heavy Industries, Limited Model KV107-II and KV107-IIA helicopters 
with an upper collective pitch control assembly, part number (P/N) 
107CK003-2 or 107CK002-2, installed, certificated in any category.

(b) Unsafe Condition

    This AD defines the unsafe condition as failure of an upper 
collective pitch control yoke bolt (bolt). This condition could 
result in excessive vibration, migration of the shafts, and 
subsequent loss of control of the helicopter.

(c) Effective Date

    This AD becomes effective August 7, 2012.

(d) Compliance

    You are responsible for performing each action required by this 
AD within the specified compliance time unless it has already been 
accomplished prior to that time.

(e) Required Actions

    Before further flight, replace bolts, P/N 107C2733-1 and P/N 
107C2733-2, with airworthy bolts, P/N C07C2700-1. Torque each nut to 
450-500 in-lbs. Do not install a washer, P/N A02C3112-13 with a 
bolt, P/N C07C2700-1. Do not install bolts, P/N 107C2733-1 and P/N 
107C2733-2, on any helicopter.

(f) Alternative Methods of Compliance (AMOCs)

    (1) The Manager, Seattle Aircraft Certification Office, FAA, may 
approve AMOCs for this AD. Send your proposal to: Kathleen 
Arrigotti, Aviation Safety Engineer, Seattle Aircraft Certification 
Office, Transport Airplane Directorate, FAA, 1601 Lind Avenue SW., 
Renton, Washington 98057; telephone (425) 917-6426; email 9-ANM-Seattle-ACO-AMOC-Requests@faa.gov.
    (2) For operations conducted under a 14 CFR part 119 operating 
certificate or under 14 CFR part 91, subpart K, we suggest that you 
notify your principal inspector, or lacking a principal inspector, 
the manager of the local flight standards district office or 
certificate holding district office, before operating any aircraft 
complying with this EAD through an AMOC.

(g) Additional Information

    CHI Service Bulletin No. 107-27-0005 (SB), Revision 0, dated 
April 26, 2012, which is not incorporated by reference, contains 
additional information about the subject of this AD. For service 
information identified in this AD, contact Columbia Helicopters, 
Inc.; 14452 Arndt Road NE., Aurora, OR 97002; telephone (503) 678-
1222; email ContactEngineering@colheli.com; or at www.ColHeli.com. 
You may review the referenced service information at the FAA, Office 
of the Regional Counsel, Southwest Region, 2601 Meacham Blvd., Room 
663, Fort Worth, Texas 76137.

(h) Subject

    Joint Aircraft Service Component (JASC) Code: 6230 Main Rotor 
Mast/Swashplate.

    Issued in Fort Worth, Texas, on July 5, 2012.
Kim Smith,
Manager, Rotorcraft Directorate, Aircraft Certification Service.
[FR Doc. 2012-17278 Filed 7-20-12; 8:45 am]
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