Airworthiness Directives; Eurocopter Deutschland GmbH Model MBB-BK 117 C-2 Helicopters, 66657-66659 [2010-26563]

Download as PDF Federal Register / Vol. 75, No. 209 / Friday, October 29, 2010 / Rules and Regulations § 39.13 [Amended] 2. The FAA amends § 39.13 by adding the following new AD: ■ 2010–22–09 Pilatus Aircraft Ltd.: Amendment 39–16488; Docket No. FAA–2010–0849; Directorate Identifier 2010–CE–043–AD. removed at any time during the life of the airplane, before further flight, do the actions specified in paragraphs 3.A.(2) through paragraph 3.E of Pilatus Aircraft Ltd. PC–7 Service Bulletin No. 57–015, Rev. No. 1, dated July 23, 2010. FAA AD Differences Effective Date (a) This airworthiness directive (AD) becomes effective December 3, 2010. Note: This AD differs from the MCAI and/ or service information as follows: No differences. Affected ADs (b) None. Other FAA AD Provisions Applicability (c) This AD applies to PILATUS Aircraft Ltd. Model PC–7 airplanes, manufacturer serial numbers (MSN) 101 through 618, certificated in any category. Subject (d) Air Transport Association of America (ATA) Code 57: Wings. WReier-Aviles on DSKGBLS3C1PROD with RULES Reason (e) The mandatory continuing airworthiness information (MCAI) states: This Airworthiness Directive (AD) is prompted due to an occurrence when an aircraft had a partial in-flight separation of the aileron outboard bearing support. The aileron outboard bearing supports are attached with two forward attachment bolts and two aft attachment bolts. The forward attachment bolts are approximately 3.2 mm (0.125 inch) longer than the aft attachment bolts. If the aileron outboard bearing supports have been removed, it is possible that during the reinstallation of the aileron outboard bearing supports, the attachment bolts can be installed in wrong positions. Bolts that are installed in wrong positions can damage the threads in the rear attachment anchor nuts. Such a condition, if left uncorrected, could lead to in-flight separation of the aileron outboard bearing support, and as a consequence, the loss or limited controllability of the aircraft. In order to correct and control the situation, this AD requires a one time inspection to verify that the bolts are installed in the correct positions and the threads of the anchor nuts are in good condition. The replacement of the attachment hardware is required if any damage on the anchor nut threads or a bolt at the wrong location is found. Actions and Compliance (f) Unless already done, do the following actions: (1) Within 1 month after December 3, 2010 (the effective date of this AD), check the airplane maintenance records to determine if the left and/or right aileron outboard bearing supports have been removed at any time during the life of the airplane. Do this check following paragraph 3.A. of Pilatus Aircraft Ltd. PC–7 Service Bulletin No. 57–015, Rev. No. 1, dated July 23, 2010. (2) If an entry is found during the airplane maintenance records check required in paragraph (f)(1) of this AD or it is unclear whether or not the left and/or right aileron outboard bearing supports have been VerDate Mar<15>2010 13:56 Oct 28, 2010 Jkt 223001 (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: Doug Rudolph, Aerospace Engineer, FAA, Small Airplane Directorate, 901 Locust, Room 301, Kansas City, Missouri 64106; telephone: (816) 329–4059; fax: (816) 329– 4090. 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. Special Flight Permit (h) Special flight permits will not be issued. Related Information (i) Refer to MCAI Federal Office of Civil Aviation (FOCA) AD HB–2010–010, dated July 29, 2010; and Pilatus Aircraft Ltd. PC– 7 Service Bulletin No. 57–015, Rev. No. 1, dated July 23, 2010, for related information. PO 00000 Frm 00015 Fmt 4700 Sfmt 4700 66657 Material Incorporated by Reference (j) You must use Pilatus Aircraft Ltd. PC– 7 Service Bulletin No. 57–015, Rev. No. 1, dated July 23, 2010, 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 Pilatus Aircraft Ltd., Customer Service Manager, CH–6371 STANS, Switzerland; telephone: +41 (0) 41 619 62 08; fax: +41 (0) 41 619 73 11; Internet: https://www.pilatus-aircraft.com. (3) You may review copies of the referenced service information at the FAA, Small Airplane Directorate, 901 Locust, Kansas City, Missouri 64106. 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 Kansas City, Missouri, on October 21, 2010. Christina L. Marsh, Acting Manager, Small Airplane Directorate, Aircraft Certification Service. [FR Doc. 2010–27214 Filed 10–28–10; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2010–0780; Directorate Identifier 2009–SW–68–AD; Amendment 39– 16486; AD 2010–22–07] RIN 2120–AA64 Airworthiness Directives; Eurocopter Deutschland GmbH Model MBB–BK 117 C–2 Helicopters Federal Aviation Administration, DOT. ACTION: Final rule. AGENCY: This amendment supersedes an existing airworthiness directive (AD) for the Eurocopter Deutschland GmbH (ECD) Model MBB BK 117 C–2 helicopters. This amendment results from a mandatory continuing airworthiness information (MCAI) AD issued by the European Aviation Safety Agency (EASA), which is the Technical Agent for the Member States of the European Community. The MCAI AD states there was an in-flight incident in which a dynamic weight broke off the SUMMARY: E:\FR\FM\29OCR1.SGM 29OCR1 66658 Federal Register / Vol. 75, No. 209 / Friday, October 29, 2010 / Rules and Regulations WReier-Aviles on DSKGBLS3C1PROD with RULES control lever leading to considerable vibrations. A visual inspection revealed that the threaded bolt of the control lever had broken off. The actions specified by this AD are intended to prevent separation of dynamic weights, severe vibration, and subsequent loss of control of the helicopter. DATES: Effective December 3, 2010. The incorporation by reference of certain publications listed in the regulations is approved by the Director of the Federal Register as of December 3, 2010. ADDRESSES: You may get the service information identified in this AD from American Eurocopter Corporation, 2701 Forum Drive, Grand Prairie, Texas 75053–4005, telephone (972) 641–3460, fax (972) 641–3527. Examining the Docket: You may examine the AD docket on the Internet at https://www.regulations.gov, or in person at the Docket Operations Office, West Building Ground Floor, Room W12–140, 1200 New Jersey Avenue, SE., Washington, DC, between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. FOR FURTHER INFORMATION CONTACT: DOT/FAA Southwest Region, Sharon Miles, ASW–111, Aviation Safety Engineer, Rotorcraft Directorate, Regulations and Policy Group, 2601 Meacham Blvd., ASW–111, Fort Worth, Texas 76137, telephone (817) 222–5122, fax (817) 222–5961. SUPPLEMENTARY INFORMATION: Discussion A proposal to amend 14 CFR Part 39 by superseding AD 2006–26–51, Amendment 39 14961 (72 FR 13679, March 23, 2007) for the specified ECD model helicopters was published in the Federal Register on August 11, 2010 (75 FR 48617). AD 2006–26–51 requires actions intended to address an unsafe condition on the Model MBB–BK 117 C–2 helicopters. Since we issued AD 2006–26–51, the manufacturer has modified the control lever and dynamic weights, which when installed on the helicopter will constitute terminating action for the requirements in AD 2006– 26–51. EASA, which is the technical agent for the Member States of the European Community, has issued EASA AD No. 2007–0237, dated August 31, 2007, to correct an unsafe condition for the Model MBB–BK 117 C–2 helicopters. The MCAI AD states: ‘‘EASA was informed by the manufacturer of an inflight incident in which a dynamic weight broke off the control lever subsequently leading to considerable vibrations. A visual inspection revealed VerDate Mar<15>2010 13:56 Oct 28, 2010 Jkt 223001 that the threaded bolt of the control lever had broken off.’’ You may obtain further information by examining the MCAI AD and service information in the AD docket. Related Service Information ECD has issued ECD Alert Service Bulletin MBB BK117 C–2–64A–002, Revision 2, dated August 6, 2007. The actions described in the MCAI AD are intended to correct the same unsafe condition as that identified in the service information. FAA’s Evaluation and Unsafe Condition Determination This helicopter has been approved by the aviation authority of the Federal Republic of Germany and is approved for operation in the United States. Pursuant to our bilateral agreement with the Federal Republic of Germany, EASA, their Technical Agent, has notified us of the unsafe condition described in the MCAI AD. We are issuing this AD because we evaluated all information provided by EASA and determined the unsafe condition exists and is likely to exist or develop on other helicopters of this same type design. Differences Between the AD and the MCAI AD We refer to flight hours as hours timein-service. We do not refer to a date of October 31, 2007, for replacing the levers because the date has passed. Comments Interested persons have been afforded an opportunity to participate in the making of this amendment. No comments were received on the proposal or the FAA’s determination of the cost to the public. We have determined that air safety and the public interest require the adoption of the rule as proposed. Cost of Compliance We estimate that this AD will affect 41 helicopters of U.S. registry. We also estimate that it will take about 20 workhours per helicopter to inspect and replace the tail rotor control lever. The average labor rate is $85 per work-hour, and required parts will cost about $10,316 per helicopter. Based on these figures, we estimate the total cost of this AD to U.S. operators to be $492,656, or $12,016 per helicopter, assuming the control lever is replaced on the entire fleet. not have a substantial direct effect on the States, on the relationship between the national Government and the States, or on the distribution of power and responsibilities among the various levels of government. For the reasons discussed above, I certify that the 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 AD and placed it in the AD docket. Authority for This Rulemaking Title 49 of the United States Code specifies the FAA’s authority to issue rules on aviation safety. Subtitle I, Section 106, describes the authority of the FAA Administrator. Subtitle VII, Aviation Programs, describes in more detail the scope of the Agency’s authority. We are issuing this rulemaking under the authority described in Subtitle VII, Part A, Subpart III, Section 44701, ‘‘General requirements.’’ Under that section, Congress charges the FAA with promoting safe flight of civil aircraft in air commerce by prescribing regulations for practices, methods, and procedures the Administrator finds necessary for safety in air commerce. This regulation is within the scope of that authority because it addresses an unsafe condition that is likely to exist or develop on products identified in this rulemaking action. List of Subjects in 14 CFR Part 39 Air transportation, Aircraft, Aviation safety, 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. Regulatory Findings § 39.13 We have determined that this AD will not have federalism implications under Executive Order 13132. This AD will ■ PO 00000 Frm 00016 Fmt 4700 Sfmt 4700 [Amended] 2. Section 39.13 is amended by removing Amendment 39 14961 (72 FR 13679, March 23, 2007), and by adding E:\FR\FM\29OCR1.SGM 29OCR1 Federal Register / Vol. 75, No. 209 / Friday, October 29, 2010 / Rules and Regulations a new airworthiness directive (AD), Amendment 39 16486, to read as follows: 2010–22–07 Eurocopter Deutschland GmbH: Amendment 39–16486; Docket No. FAA–2010–0780; Directorate Identifier 2009–SW–68–AD. Supersedes AD 2006–26–51, Amendment 39 14961, Docket No. FAA–2006–26721, Directorate Identifier 2006–SW–28–AD. Other Affected ADs (b) This AD supersedes AD 2006–26–51, Amendment 39–14961, Docket No. FAA 2006–26721, Directorate Identifier 2006–SW– 28–AD. Applicability (c) This AD applies to Model MBB–BK 117 C–2 helicopters with a tail rotor control lever B642M1009103, installed, certificated in any category. WReier-Aviles on DSKGBLS3C1PROD with RULES Reason (d) The mandatory continued airworthiness information (MCAI) AD states: ‘‘European Aviation Safety Agency (EASA) was informed by the manufacturer of an inflight incident in which a dynamic weight broke off the control lever subsequently leading to considerable vibrations. A visual inspection revealed that the threaded bolt of the control lever had broken off.’’ This AD requires actions that are intended to prevent separation of dynamic weights, severe vibration, and subsequent loss of control of the helicopter. Actions and Compliance (e) Before further flight, unless already done, mark the position of the weights, remove the split pins, remove the weights, and visually inspect the tail rotor control lever in the area around the split pin bore for score marks, notching, scratching, or a crack. Inspect by following the Accomplishment Instructions, paragraph 3.A.(1) through 3.A.(3) and Figure 1, of Eurocopter Alert Service Bulletin MBB BK 117 C–2–64A–002, Revision 2, dated August 6, 2007 (ASB). (1) If done previously, within the next 8 hours time-in-service (TIS) or before reaching 25 hours TIS after the last inspection, and thereafter at intervals not to exceed 8 hours TIS, repeat the visual inspection of the tail rotor control lever as required by paragraph (e) of this AD. (2) If you find a score mark, a notch, or a scratch that exceeds the maintenance manual limits, or find a crack, before further flight: (i) Replace the tail rotor control lever with an airworthy tail rotor control lever; and (ii) Reidentify the tail rotor head, head assembly, and drive system with the new part numbers by following the Accomplishment Instructions, paragraph 3.B.(1) through 3.B.(8) and 3.C.(1) through 3.C.(2), of the ASB. (f) Within 100 hours TIS, unless already done, replace the control levers and reidentify the tail rotor head, head assembly, and drive system with the new part numbers 13:56 Oct 28, 2010 Jkt 223001 Differences Between the FAA AD and the MCAI AD (h) We refer to flight hours as hours TIS. We do not refer to a date of October 31, 2007, for replacing the levers because the date has passed. Effective Date (a) This airworthiness directive (AD) becomes effective on December 3, 2010. VerDate Mar<15>2010 by following the Accomplishment Instructions, paragraph 3.B.(1) through 3.B.(8) and 3.C.(1) through 3.C.(2), of the ASB. (g) Replacing the control levers and reidentifying the part numbers is terminating action for the requirements of this AD. Other Information (i) Alternative Methods of Compliance (AMOCs): The Manager, Safety Management Group, ATTN: DOT/FAA Southwest Region, Sharon Miles, ASW–111, Aviation Safety Engineer, Rotorcraft Directorate, Regulations and Policy Group, 2601 Meacham Blvd., Fort Worth, Texas 76137, telephone (817) 222– 5122, fax (817) 222 5961, has the authority to approve AMOCs for this AD, if requested, using the procedures found in 14 CFR 39.19. (j) Special flight permits are prohibited. Related Information (k) MCAI EASA Airworthiness Directive No. 2006–0237, dated August 31, 2007, which supersedes EASA Emergency AD 2007–0189–E, dated July 12, 2007, contains related information. Joint Aircraft System/Component Code (l) The Joint Aircraft System/Component Code is 6400: Tail rotor system-control lever. Material Incorporated by Reference (m) The actions shall be done in accordance with the specified portions of Eurocopter Deutschland GmbH Alert Service Bulletin MBB BK117 C–2–64A–002, Revision 2, dated August 6, 2007. 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 American Eurocopter Corporation, 2701 Forum Drive, Grand Prairie, Texas 75053–4005, telephone (972) 641–3460, fax (972) 641–3527. 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/ code_of_federal_regulations/ ibr_locations.html. Issued in Fort Worth, Texas, on October 12, 2010. Kim Smith, Manager, Rotorcraft Directorate, Aircraft Certification Service. [FR Doc. 2010–26563 Filed 10–28–10; 8:45 am] BILLING CODE 4910–13–P PO 00000 Frm 00017 Fmt 4700 Sfmt 4700 66659 DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2010–0680; Directorate Identifier 2008–NM–195–AD; Amendment 39–16482; AD 2010–22–03] RIN 2120–AA64 Airworthiness Directives; Airbus Model A310 Series Airplanes 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) originated 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: Analysis performed in the frame of the Extended Service Goal has led Airbus to modify the inspection programme [modification of thresholds, intervals and associated configurations] which is currently ´ ´ required by DGAC (Direction Generale de l’Aviation Civile) France AD F–2005–001. This modified inspection programme is necessary to detect and prevent damage associated with a structural fatigue phenomenon of the rear spar internal angle and the tee fitting located in the centre wing box. This condition, if not corrected, could affect the structural integrity of the centre wing box. * * * * * The unsafe condition is reduced structural integrity of the wings. We are issuing this AD to require actions to correct the unsafe condition on these products. DATES: This AD becomes effective December 3, 2010. The Director of the Federal Register approved the incorporation by reference of certain publications listed in this AD as of December 3, 2010. ADDRESSES: You may examine the AD docket on the Internet at https:// 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: Dan Rodina, Aerospace Engineer, International Branch, ANM–116, FAA, Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton, Washington 98055–4056; telephone (425) 227–2125; fax (425) 227–1149. E:\FR\FM\29OCR1.SGM 29OCR1

Agencies

[Federal Register Volume 75, Number 209 (Friday, October 29, 2010)]
[Rules and Regulations]
[Pages 66657-66659]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 2010-26563]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2010-0780; Directorate Identifier 2009-SW-68-AD; 
Amendment 39-16486; AD 2010-22-07]
RIN 2120-AA64


Airworthiness Directives; Eurocopter Deutschland GmbH Model MBB-
BK 117 C-2 Helicopters

AGENCY: Federal Aviation Administration, DOT.

ACTION: Final rule.

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

SUMMARY: This amendment supersedes an existing airworthiness directive 
(AD) for the Eurocopter Deutschland GmbH (ECD) Model MBB BK 117 C-2 
helicopters. This amendment results from a mandatory continuing 
airworthiness information (MCAI) AD issued by the European Aviation 
Safety Agency (EASA), which is the Technical Agent for the Member 
States of the European Community. The MCAI AD states there was an in-
flight incident in which a dynamic weight broke off the

[[Page 66658]]

control lever leading to considerable vibrations. A visual inspection 
revealed that the threaded bolt of the control lever had broken off. 
The actions specified by this AD are intended to prevent separation of 
dynamic weights, severe vibration, and subsequent loss of control of 
the helicopter.

DATES: Effective December 3, 2010.
    The incorporation by reference of certain publications listed in 
the regulations is approved by the Director of the Federal Register as 
of December 3, 2010.

ADDRESSES: You may get the service information identified in this AD 
from American Eurocopter Corporation, 2701 Forum Drive, Grand Prairie, 
Texas 75053-4005, telephone (972) 641-3460, fax (972) 641-3527.
    Examining the Docket: You may examine the AD docket on the Internet 
at https://www.regulations.gov, or in person at the Docket Operations 
Office, West Building Ground Floor, Room W12-140, 1200 New Jersey 
Avenue, SE., Washington, DC, between 9 a.m. and 5 p.m., Monday through 
Friday, except Federal holidays.

FOR FURTHER INFORMATION CONTACT: DOT/FAA Southwest Region, Sharon 
Miles, ASW-111, Aviation Safety Engineer, Rotorcraft Directorate, 
Regulations and Policy Group, 2601 Meacham Blvd., ASW-111, Fort Worth, 
Texas 76137, telephone (817) 222-5122, fax (817) 222-5961.

SUPPLEMENTARY INFORMATION: 

Discussion

    A proposal to amend 14 CFR Part 39 by superseding AD 2006-26-51, 
Amendment 39 14961 (72 FR 13679, March 23, 2007) for the specified ECD 
model helicopters was published in the Federal Register on August 11, 
2010 (75 FR 48617). AD 2006-26-51 requires actions intended to address 
an unsafe condition on the Model MBB-BK 117 C-2 helicopters. Since we 
issued AD 2006-26-51, the manufacturer has modified the control lever 
and dynamic weights, which when installed on the helicopter will 
constitute terminating action for the requirements in AD 2006-26-51.
    EASA, which is the technical agent for the Member States of the 
European Community, has issued EASA AD No. 2007-0237, dated August 31, 
2007, to correct an unsafe condition for the Model MBB-BK 117 C-2 
helicopters. The MCAI AD states: ``EASA was informed by the 
manufacturer of an in-flight incident in which a dynamic weight broke 
off the control lever subsequently leading to considerable vibrations. 
A visual inspection revealed that the threaded bolt of the control 
lever had broken off.''
    You may obtain further information by examining the MCAI AD and 
service information in the AD docket.

Related Service Information

    ECD has issued ECD Alert Service Bulletin MBB BK117 C-2-64A-002, 
Revision 2, dated August 6, 2007. The actions described in the MCAI AD 
are intended to correct the same unsafe condition as that identified in 
the service information.

FAA's Evaluation and Unsafe Condition Determination

    This helicopter has been approved by the aviation authority of the 
Federal Republic of Germany and is approved for operation in the United 
States. Pursuant to our bilateral agreement with the Federal Republic 
of Germany, EASA, their Technical Agent, has notified us of the unsafe 
condition described in the MCAI AD. We are issuing this AD because we 
evaluated all information provided by EASA and determined the unsafe 
condition exists and is likely to exist or develop on other helicopters 
of this same type design.

Differences Between the AD and the MCAI AD

    We refer to flight hours as hours time-in-service. We do not refer 
to a date of October 31, 2007, for replacing the levers because the 
date has passed.

Comments

    Interested persons have been afforded an opportunity to participate 
in the making of this amendment. No comments were received on the 
proposal or the FAA's determination of the cost to the public. We have 
determined that air safety and the public interest require the adoption 
of the rule as proposed.

Cost of Compliance

    We estimate that this AD will affect 41 helicopters of U.S. 
registry. We also estimate that it will take about 20 work-hours per 
helicopter to inspect and replace the tail rotor control lever. The 
average labor rate is $85 per work-hour, and required parts will cost 
about $10,316 per helicopter. Based on these figures, we estimate the 
total cost of this AD to U.S. operators to be $492,656, or $12,016 per 
helicopter, assuming the control lever is replaced on the entire fleet.

Regulatory Findings

    We have 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 that the 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 AD and placed it in the AD docket.

Authority for This Rulemaking

    Title 49 of the United States Code specifies the FAA's authority to 
issue rules on aviation safety. Subtitle I, Section 106, describes the 
authority of the FAA Administrator. Subtitle VII, Aviation Programs, 
describes in more detail the scope of the Agency's authority.
    We are issuing this rulemaking under the authority described in 
Subtitle VII, Part A, Subpart III, Section 44701, ``General 
requirements.'' Under that section, Congress charges the FAA with 
promoting safe flight of civil aircraft in air commerce by prescribing 
regulations for practices, methods, and procedures the Administrator 
finds necessary for safety in air commerce. This regulation is within 
the scope of that authority because it addresses an unsafe condition 
that is likely to exist or develop on products identified in this 
rulemaking action.

List of Subjects in 14 CFR Part 39

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

Adoption of the Amendment

0
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. Section 39.13 is amended by removing Amendment 39 14961 (72 FR 
13679, March 23, 2007), and by adding

[[Page 66659]]

a new airworthiness directive (AD), Amendment 39 16486, to read as 
follows:

2010-22-07 Eurocopter Deutschland GmbH: Amendment 39-16486; Docket 
No. FAA-2010-0780; Directorate Identifier 2009-SW-68-AD. Supersedes 
AD 2006-26-51, Amendment 39 14961, Docket No. FAA-2006-26721, 
Directorate Identifier 2006-SW-28-AD.

Effective Date

    (a) This airworthiness directive (AD) becomes effective on 
December 3, 2010.

Other Affected ADs

    (b) This AD supersedes AD 2006-26-51, Amendment 39-14961, Docket 
No. FAA 2006-26721, Directorate Identifier 2006-SW-28-AD.

Applicability

    (c) This AD applies to Model MBB-BK 117 C-2 helicopters with a 
tail rotor control lever B642M1009103, installed, certificated in 
any category.

Reason

    (d) The mandatory continued airworthiness information (MCAI) AD 
states: ``European Aviation Safety Agency (EASA) was informed by the 
manufacturer of an in-flight incident in which a dynamic weight 
broke off the control lever subsequently leading to considerable 
vibrations. A visual inspection revealed that the threaded bolt of 
the control lever had broken off.'' This AD requires actions that 
are intended to prevent separation of dynamic weights, severe 
vibration, and subsequent loss of control of the helicopter.

Actions and Compliance

    (e) Before further flight, unless already done, mark the 
position of the weights, remove the split pins, remove the weights, 
and visually inspect the tail rotor control lever in the area around 
the split pin bore for score marks, notching, scratching, or a 
crack. Inspect by following the Accomplishment Instructions, 
paragraph 3.A.(1) through 3.A.(3) and Figure 1, of Eurocopter Alert 
Service Bulletin MBB BK 117 C-2-64A-002, Revision 2, dated August 6, 
2007 (ASB).
    (1) If done previously, within the next 8 hours time-in-service 
(TIS) or before reaching 25 hours TIS after the last inspection, and 
thereafter at intervals not to exceed 8 hours TIS, repeat the visual 
inspection of the tail rotor control lever as required by paragraph 
(e) of this AD.
    (2) If you find a score mark, a notch, or a scratch that exceeds 
the maintenance manual limits, or find a crack, before further 
flight:
    (i) Replace the tail rotor control lever with an airworthy tail 
rotor control lever; and
    (ii) Reidentify the tail rotor head, head assembly, and drive 
system with the new part numbers by following the Accomplishment 
Instructions, paragraph 3.B.(1) through 3.B.(8) and 3.C.(1) through 
3.C.(2), of the ASB.
    (f) Within 100 hours TIS, unless already done, replace the 
control levers and reidentify the tail rotor head, head assembly, 
and drive system with the new part numbers by following the 
Accomplishment Instructions, paragraph 3.B.(1) through 3.B.(8) and 
3.C.(1) through 3.C.(2), of the ASB.
    (g) Replacing the control levers and reidentifying the part 
numbers is terminating action for the requirements of this AD.

Differences Between the FAA AD and the MCAI AD

    (h) We refer to flight hours as hours TIS. We do not refer to a 
date of October 31, 2007, for replacing the levers because the date 
has passed.

Other Information

    (i) Alternative Methods of Compliance (AMOCs): The Manager, 
Safety Management Group, ATTN: DOT/FAA Southwest Region, Sharon 
Miles, ASW-111, Aviation Safety Engineer, Rotorcraft Directorate, 
Regulations and Policy Group, 2601 Meacham Blvd., Fort Worth, Texas 
76137, telephone (817) 222-5122, fax (817) 222 5961, has the 
authority to approve AMOCs for this AD, if requested, using the 
procedures found in 14 CFR 39.19.
    (j) Special flight permits are prohibited.

Related Information

    (k) MCAI EASA Airworthiness Directive No. 2006-0237, dated 
August 31, 2007, which supersedes EASA Emergency AD 2007-0189-E, 
dated July 12, 2007, contains related information.

Joint Aircraft System/Component Code

    (l) The Joint Aircraft System/Component Code is 6400: Tail rotor 
system-control lever.

Material Incorporated by Reference

    (m) The actions shall be done in accordance with the specified 
portions of Eurocopter Deutschland GmbH Alert Service Bulletin MBB 
BK117 C-2-64A-002, Revision 2, dated August 6, 2007. 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 American Eurocopter Corporation, 2701 Forum Drive, 
Grand Prairie, Texas 75053-4005, telephone (972) 641-3460, fax (972) 
641-3527. 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/code_of_federal_regulations/ibr_locations.html.

    Issued in Fort Worth, Texas, on October 12, 2010.
Kim Smith,
Manager, Rotorcraft Directorate, Aircraft Certification Service.
[FR Doc. 2010-26563 Filed 10-28-10; 8:45 am]
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