Airworthiness Directives; Eurocopter Deutschland GmbH Helicopters, 37777-37779 [2012-15325]

Download as PDF Federal Register / Vol. 77, No. 122 / Monday, June 25, 2012 / Rules and Regulations 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: Todd Thompson, Aerospace Engineer, International Branch, ANM–116, Transport Airplane Directorate, FAA 1601 Lind Avenue SW., Renton, Washington 98057–3356; telephone (425) 227–1175; fax (425) 227– 1149. Information may be emailed to: 9-ANM-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. Issued in Renton, Washington, on June 7, 2012. Michael Kaszycki, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. (j) Related Information SUMMARY: Refer to MCAI European Aviation Safety Agency Airworthiness Directive 2011–0065, dated April 7, 2011; and BAE Systems (Operations) Limited Modification Service Bulletin SB.26–077–36250A.B, Revision 4, dated January 7, 2011; for related information. erowe on DSK2VPTVN1PROD with RULES (k) 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) BAE Systems (Operations) Limited Modification Service Bulletin SB.26–077– 36250A.B, Revision 4, dated January 7, 2011. (3) For BAE Systems (Operations) Limited service information identified in this AD, contact BAE Systems (Operations) Limited, Customer Information Department, Prestwick International Airport, Ayrshire, KA9 2RW, Scotland, United Kingdom; telephone +44 1292 675207; fax +44 1292 675704; email RApublications@baesystems.com; Internet http://www.baesystems.com/Businesses/ RegionalAircraft/index.htm. (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. VerDate Mar<15>2010 14:43 Jun 22, 2012 Jkt 226001 [FR Doc. 2012–14729 Filed 6–22–12; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2012–0659; Directorate Identifier 2011–SW–061–AD; Amendment 39–17101; AD 2012–12–21] RIN 2120–AA64 Airworthiness Directives; Eurocopter Deutschland GmbH Helicopters Federal Aviation Administration (FAA), DOT. ACTION: Final rule; request for comments. AGENCY: We are superseding an existing airworthiness directive (AD) for all Eurocopter Deutschland GmbH (ECD) Model MBB–BK 117 C–2 helicopters. That AD currently requires revising the ‘‘Emergency and Malfunction Procedures’’ and ‘‘Performance Data’’ sections of the Rotorcraft Flight Manual (RFM) by inserting three temporary pages into the RFM to alert pilots to monitor the power display when a generator is deactivated and provides procedures to prevent failure of the remaining generator. Before we issued that AD, the manufacturer developed a procedure to modify the two ‘‘After Junction Boxes’’ by removing a diode from each box, which provides terminating action for our AD requirements. These actions are intended to require implementing this terminating action to prevent an electrical power system failure and subsequent loss of control of the helicopter and revising the RFM accordingly, by removing the temporary pages inserted to comply with the superseded AD. DATES: This AD becomes effective July 10, 2012. The Director of the Federal Register approved the incorporation by reference of certain documents listed in this AD as of July 10, 2012. We must receive comments on this AD by August 24, 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. PO 00000 Frm 00027 Fmt 4700 Sfmt 4700 37777 • 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 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 American Eurocopter Corporation, 2701 N. Forum Drive, Grand Prairie, TX 75052, telephone (972) 641–0000 or (800) 232–0323, fax (972) 641–3775, or at http:// www.eurocopter.com/techpub. You may review a copy of the 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: George Schwab, Aviation Safety Engineer, FAA, Rotorcraft Directorate, Safety Management Group, 2601 Meacham Blvd., Fort Worth, TX 76137, telephone (817) 222–5110, email: george.schwab@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 E:\FR\FM\25JNR1.SGM 25JNR1 37778 Federal Register / Vol. 77, No. 122 / Monday, June 25, 2012 / Rules and Regulations 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. erowe on DSK2VPTVN1PROD with RULES Discussion On September 29, 2011, we issued AD 2011–21–13 (76 FR 68299, November 4, 2011), for all ECD model MBB–BK 117 C–2 helicopters. Our AD 2011–21–13 was based on European Aviation Safety Agency (EASA) Emergency AD No. 2010–0268–E, dated December 21, 2010 (EAD 2010–0268–E), requiring the introduction of additional RFM procedures to monitor the electrical power display generator amperes (GEN AMPS) on the Vehicle and Engine Multifunction Display (VEMD) during switching of the generator. EASA advised that some ECD MBB–BK117 C–2 helicopters detected an excessive current flow when one generator was deactivated. This situation, if not detected and corrected, could lead to failure of the generator, likely resulting in loss of electrical power and inducing loss of systems that are necessary for safe flight. To address this unsafe condition, AD 2011–21–13 requires revising the ‘‘Emergency and Malfunction Procedures’’ and the ‘‘Performance Data’’ sections of the RFM by inserting three temporary pages from ECD Alert Service Bulletin (ASB) No. ASB MBB BK117 C–2–24A–008, dated December 20, 2010 (MBB BK117 C–2– 24A–008). Those pages require operators to insert pages into the RFM, which provide that pilots visually monitor the power display GEN AMPS on the VEMD for too high of a current when a generator is shut down, such as during the ENGINE POWER CHECK. These revised RFM provisions provide for switching off the two main electrical buses on the overhead panel to prevent the operating generator from being damaged when the other generator is shut down. We issued AD 2011–21–13 to prevent failure of a generator, which could result in loss of electrical power, loss of systems necessary for flight safety, and subsequent loss of control of the helicopter. Actions Since Existing AD Was Issued Before we issued AD 2011–21–13 (76 FR 68299, November 4, 2011), EASA, which is the Technical Agent for the Member States of the European Union, issued EASA AD No. 2011–0162, dated August 30, 2011 (AD 2011–0162). In AD 2011–0162, EASA states that ECD has developed a modification to prevent the VerDate Mar<15>2010 14:43 Jun 22, 2012 Jkt 226001 possibility of too high current flow when a generator is deactivated, and updated the RFM procedures accordingly. This EASA AD requires the RFM changes introduced by EAD 2010– 0268–E to be removed. The EASA AD also requires modification of the Generator Relay left-hand and righthand After Junction Boxes by removing diodes, CR10007 and CR10008, respectively, on ECD MBB–BK117 C–2 helicopters, serial numbers 9004 through 9500. Through this AD action, the FAA is requiring this same modification to the After Junction Boxes in helicopters registered in the United States and removal of the same pages from the RFM that were introduced by AD 2011–21–13. FAA’s Determination These helicopters have been approved by the aviation authority of the Federal Republic of Germany (FRG) and are approved for operation in the United States. Pursuant to our bilateral agreement with the FRG, EASA, their technical representative, has notified us of the unsafe condition described in the EASA AD. We are issuing this AD because we evaluated all information provided by EASA and determined the unsafe condition is likely to exist or develop on other helicopters of the same type design. Related Service Information We reviewed ECD ASB MBB BK117 C–2–24A–008, Revision 1, dated August 29, 2011. The ASB describes procedures for removing two diodes on the generator relays in the After Junction Boxes. EASA classified this ASB as mandatory and issued AD 2011–0162 to ensure the continued airworthiness of these helicopters. AD Requirements This AD requires, within 30 days, removing temporary pages from the RFM that were inserted for AD 2011– 21–13. This AD also requires modifying Generator Relay left-hand and righthand After Junction Boxes by removing diodes, CR10007 and CR10008. Differences Between This AD and the EASA AD The EASA AD requires compliance by September 6, 2011; the FAA requires compliance within 30 days from the effective date of the AD. Costs of Compliance We estimate that this AD affects 232 helicopters of U.S. Registry. We estimate that operators may incur the following costs in order to comply with this AD. Removing the diodes from the after PO 00000 Frm 00028 Fmt 4700 Sfmt 4700 junction boxes will require 2 work hours at an average labor cost of $85 per hour and incorporating the changes into the RFM will require .5 work hour for a total cost per operator of $213 and a cost to the entire U.S. fleet of $49,416. FAA’s Justification and Determination of the Effective Date Providing an opportunity for public comments prior to adopting these AD requirements would delay implementing the safety actions needed to correct this known unsafe condition. 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 within 30 days. 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 contrary to the public interest 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; E:\FR\FM\25JNR1.SGM 25JNR1 Federal Register / Vol. 77, No. 122 / Monday, June 25, 2012 / Rules and Regulations 2. Is not a ‘‘significant rule’’ under the 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. 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 proposes to amend 14 CFR part 39 as follows: PART 39—AIRWORTHINESS DIRECTIVES 1. The authority citation for part 39 continues to read as follows: ■ Authority: 49 U.S.C. 106(g), 40113, 44701. § 39.13 [Amended] 2. The FAA amends § 39.13 by removing Amendment 39–16836 (76 FR 68299, November 4, 2011), and adding the following new airworthiness directive (AD): ■ (i) ‘‘Emergency and Malfunction Procedures’’: pages 3–3 and 3–4, and (ii) ‘‘Performance Data’’: page 5–7. (2) Remove diodes CR10007 and CR10008 from the generator relays in the left-hand and right-hand After Junction Boxes, respectively, in accordance with the Accomplishment Instructions, paragraphs 3.B.2.(a) through 3.B.2.(d), and as depicted in Figures 1 and 2, of Eurocopter Alert Service Bulletin ASB MBB BK117 C–2–24A–008 Revision 1, dated August 29, 2011. (3) Test the DC Power system for proper operation. (4) Do not install an After Junction Box on any helicopter, unless the After Junction Box has been modified in accordance with the requirements of this AD. (f) Alternative Methods of Compliance (AMOCs) (1) The Manager, Safety Management Group, FAA, may approve AMOCs for this AD. Send your proposal to: George Schwab, Aviation Safety Engineer, FAA, Rotorcraft Directorate, Safety Management Group, 2601 Meacham Blvd., Fort Worth, TX 76137, telephone (817) 222–5114, email: george.schwab@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 AD through an AMOC. (g) Additional Information The subject of this AD is addressed in the European Aviation Safety Agency AD No. 2011–0162, dated August 30, 2011. 2012–12–21 Eurocopter Deutschland GMBH: Amendment 39–17101; Docket No. FAA–2012–0659; Directorate Identifier 2011–SW–061–AD. (h) Subject Joint Aircraft Service Component (JASC) Code: 2435: Starter Generator. (a) Applicability This AD applies to Model MBB–BK 117 C–2 helicopters, certificated in any category. (i) Material Incorporated by Reference (1) The Director of the Federal Register approved the incorporation by reference (IBR) of the service information listed in this paragraph under 5 U.S.C. 552(a) and 1 CFR part 51. (2) You must use this service information as applicable to do the actions required by this AD, unless the AD specifies otherwise. (i) Eurocopter Alert Service Bulletin ASB MBB BK117 C–2–24A–008 Revision 1, dated August 29, 2011. (ii) Reserved. (3) For Eurocopter service information identified in this AD, contact American Eurocopter Corporation, 2701 N. Forum Drive, Grand Prairie, TX 75052, telephone (972) 641–0000 or (800) 232–0323, fax (972) 641–3775, or at http://www.eurocopter.com/ techpub. (4) You may view this service information at the FAA, Office of the Regional Counsel, Southwest Region, 2601 Meacham Blvd., Room 663, Fort Worth, Texas 76137. (5) You may also view this service information at the National Archives and Records Administration (NARA). For information on the availability of this material at NARA, call (202) 741–6030, or go (b) Unsafe Condition This AD defines the unsafe condition as excessively high reverse current flow when switching off a generator during flight, which could make the remaining generator fail and result in a complete electrical power system failure and subsequent loss of control of the helicopter. erowe on DSK2VPTVN1PROD with RULES (c) Other Affected ADs This AD supersedes AD 2011–21–13, Amendment 39–16836 (76 FR 68299, November 4, 2011). (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 Action Within 30 days: (1) Remove the specified temporary pages from the following sections of the rotorcraft flight manual (RFM) RFM BK 117 C–2: VerDate Mar<15>2010 14:43 Jun 22, 2012 Jkt 226001 PO 00000 Frm 00029 Fmt 4700 Sfmt 4700 37779 to: http://www.archives.gov/federal_register/ code_of_federal_regulations/ ibr_locations.html. Issued in Fort Worth, Texas, on June 14, 2012. Lance T. Gant, Acting Manager, Rotorcraft Directorate, Aircraft Certification Service. [FR Doc. 2012–15325 Filed 6–22–12; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2012–0013; Directorate Identifier 2010–SW–043–AD; Amendment 39–17090; AD 2012–12–10] RIN 2120–AA64 Airworthiness Directives; Agusta S.p.A. Helicopters Federal Aviation Administration (FAA), DOT. ACTION: Final rule. AGENCY: We are adopting a new airworthiness directive (AD) for Agusta S.p.A. (Agusta) Model AB139 and AW139 helicopters with a certain generator control unit (GCU), to require replacing each affected GCU with an airworthy GCU. This AD was prompted by laboratory tests which revealed a potential fault in the overvoltage protection on a certain part-numbered GCU. The actions are intended to prevent failure of the overvoltage protection of the GCU, degraded performance of the electrical power generation and distribution systems, a fire, and subsequent loss of control of the helicopter. DATES: This AD is effective July 30, 2012. The Director of the Federal Register approved the incorporation by reference of a certain publication listed in this AD as of July 30, 2012. ADDRESSES: For service information identified in this AD, contact Agusta Westland, Customer Support & Services, Via Per Tornavento 15, 21019 Somma Lombardo (VA) Italy, ATTN: Giovanni Cecchelli; telephone 39–0331–711133; fax 39 0331 711180; or at http:// www.agustawestland.com/technicalbullettins. You may review a copy of the referenced service information at the FAA, Office of the Regional Counsel, Southwest Region, 2601 Meacham Blvd., Room 663, Fort Worth, Texas 76137. Examining the AD Docket: You may examine the AD docket on the Internet SUMMARY: E:\FR\FM\25JNR1.SGM 25JNR1

Agencies

[Federal Register Volume 77, Number 122 (Monday, June 25, 2012)]
[Rules and Regulations]
[Pages 37777-37779]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 2012-15325]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2012-0659; Directorate Identifier 2011-SW-061-AD; 
Amendment 39-17101; AD 2012-12-21]
RIN 2120-AA64


Airworthiness Directives; Eurocopter Deutschland GmbH Helicopters

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Final rule; request for comments.

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

SUMMARY: We are superseding an existing airworthiness directive (AD) 
for all Eurocopter Deutschland GmbH (ECD) Model MBB-BK 117 C-2 
helicopters. That AD currently requires revising the ``Emergency and 
Malfunction Procedures'' and ``Performance Data'' sections of the 
Rotorcraft Flight Manual (RFM) by inserting three temporary pages into 
the RFM to alert pilots to monitor the power display when a generator 
is deactivated and provides procedures to prevent failure of the 
remaining generator. Before we issued that AD, the manufacturer 
developed a procedure to modify the two ``After Junction Boxes'' by 
removing a diode from each box, which provides terminating action for 
our AD requirements. These actions are intended to require implementing 
this terminating action to prevent an electrical power system failure 
and subsequent loss of control of the helicopter and revising the RFM 
accordingly, by removing the temporary pages inserted to comply with 
the superseded AD.

DATES: This AD becomes effective July 10, 2012.
    The Director of the Federal Register approved the incorporation by 
reference of certain documents listed in this AD as of July 10, 2012.
    We must receive comments on this AD by August 24, 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 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 American 
Eurocopter Corporation, 2701 N. Forum Drive, Grand Prairie, TX 75052, 
telephone (972) 641-0000 or (800) 232-0323, fax (972) 641-3775, or at 
http://www.eurocopter.com/techpub. You may review a copy of the 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: George Schwab, Aviation Safety 
Engineer, FAA, Rotorcraft Directorate, Safety Management Group, 2601 
Meacham Blvd., Fort Worth, TX 76137, telephone (817) 222-5110, email: 
george.schwab@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

[[Page 37778]]

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

    On September 29, 2011, we issued AD 2011-21-13 (76 FR 68299, 
November 4, 2011), for all ECD model MBB-BK 117 C-2 helicopters. Our AD 
2011-21-13 was based on European Aviation Safety Agency (EASA) 
Emergency AD No. 2010-0268-E, dated December 21, 2010 (EAD 2010-0268-
E), requiring the introduction of additional RFM procedures to monitor 
the electrical power display generator amperes (GEN AMPS) on the 
Vehicle and Engine Multifunction Display (VEMD) during switching of the 
generator. EASA advised that some ECD MBB-BK117 C-2 helicopters 
detected an excessive current flow when one generator was deactivated. 
This situation, if not detected and corrected, could lead to failure of 
the generator, likely resulting in loss of electrical power and 
inducing loss of systems that are necessary for safe flight. To address 
this unsafe condition, AD 2011-21-13 requires revising the ``Emergency 
and Malfunction Procedures'' and the ``Performance Data'' sections of 
the RFM by inserting three temporary pages from ECD Alert Service 
Bulletin (ASB) No. ASB MBB BK117 C-2-24A-008, dated December 20, 2010 
(MBB BK117 C-2-24A-008). Those pages require operators to insert pages 
into the RFM, which provide that pilots visually monitor the power 
display GEN AMPS on the VEMD for too high of a current when a generator 
is shut down, such as during the ENGINE POWER CHECK. These revised RFM 
provisions provide for switching off the two main electrical buses on 
the overhead panel to prevent the operating generator from being 
damaged when the other generator is shut down. We issued AD 2011-21-13 
to prevent failure of a generator, which could result in loss of 
electrical power, loss of systems necessary for flight safety, and 
subsequent loss of control of the helicopter.

Actions Since Existing AD Was Issued

    Before we issued AD 2011-21-13 (76 FR 68299, November 4, 2011), 
EASA, which is the Technical Agent for the Member States of the 
European Union, issued EASA AD No. 2011-0162, dated August 30, 2011 (AD 
2011-0162). In AD 2011-0162, EASA states that ECD has developed a 
modification to prevent the possibility of too high current flow when a 
generator is deactivated, and updated the RFM procedures accordingly. 
This EASA AD requires the RFM changes introduced by EAD 2010-0268-E to 
be removed. The EASA AD also requires modification of the Generator 
Relay left-hand and right-hand After Junction Boxes by removing diodes, 
CR10007 and CR10008, respectively, on ECD MBB-BK117 C-2 helicopters, 
serial numbers 9004 through 9500. Through this AD action, the FAA is 
requiring this same modification to the After Junction Boxes in 
helicopters registered in the United States and removal of the same 
pages from the RFM that were introduced by AD 2011-21-13.

FAA's Determination

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

Related Service Information

    We reviewed ECD ASB MBB BK117 C-2-24A-008, Revision 1, dated August 
29, 2011. The ASB describes procedures for removing two diodes on the 
generator relays in the After Junction Boxes. EASA classified this ASB 
as mandatory and issued AD 2011-0162 to ensure the continued 
airworthiness of these helicopters.

AD Requirements

    This AD requires, within 30 days, removing temporary pages from the 
RFM that were inserted for AD 2011-21-13. This AD also requires 
modifying Generator Relay left-hand and right-hand After Junction Boxes 
by removing diodes, CR10007 and CR10008.

Differences Between This AD and the EASA AD

    The EASA AD requires compliance by September 6, 2011; the FAA 
requires compliance within 30 days from the effective date of the AD.

Costs of Compliance

    We estimate that this AD affects 232 helicopters of U.S. Registry. 
We estimate that operators may incur the following costs in order to 
comply with this AD. Removing the diodes from the after junction boxes 
will require 2 work hours at an average labor cost of $85 per hour and 
incorporating the changes into the RFM will require .5 work hour for a 
total cost per operator of $213 and a cost to the entire U.S. fleet of 
$49,416.

FAA's Justification and Determination of the Effective Date

    Providing an opportunity for public comments prior to adopting 
these AD requirements would delay implementing the safety actions 
needed to correct this known unsafe condition. 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 within 30 days.
    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 contrary to 
the public interest 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;

[[Page 37779]]

    2. Is not a ``significant rule'' under the 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.
    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 proposes to amend 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 removing Amendment 39-16836 (76 FR 
68299, November 4, 2011), and adding the following new airworthiness 
directive (AD):

2012-12-21 Eurocopter Deutschland GMBH: Amendment 39-17101; Docket 
No. FAA-2012-0659; Directorate Identifier 2011-SW-061-AD.

(a) Applicability

    This AD applies to Model MBB-BK 117 C-2 helicopters, 
certificated in any category.

(b) Unsafe Condition

    This AD defines the unsafe condition as excessively high reverse 
current flow when switching off a generator during flight, which 
could make the remaining generator fail and result in a complete 
electrical power system failure and subsequent loss of control of 
the helicopter.

(c) Other Affected ADs

    This AD supersedes AD 2011-21-13, Amendment 39-16836 (76 FR 
68299, November 4, 2011).

(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 Action

    Within 30 days:
    (1) Remove the specified temporary pages from the following 
sections of the rotorcraft flight manual (RFM) RFM BK 117 C-2:
    (i) ``Emergency and Malfunction Procedures'': pages 3-3 and 3-4, 
and
    (ii) ``Performance Data'': page 5-7.
    (2) Remove diodes CR10007 and CR10008 from the generator relays 
in the left-hand and right-hand After Junction Boxes, respectively, 
in accordance with the Accomplishment Instructions, paragraphs 
3.B.2.(a) through 3.B.2.(d), and as depicted in Figures 1 and 2, of 
Eurocopter Alert Service Bulletin ASB MBB BK117 C-2-24A-008 Revision 
1, dated August 29, 2011.
    (3) Test the DC Power system for proper operation.
    (4) Do not install an After Junction Box on any helicopter, 
unless the After Junction Box has been modified in accordance with 
the requirements of this AD.

(f) Alternative Methods of Compliance (AMOCs)

    (1) The Manager, Safety Management Group, FAA, may approve AMOCs 
for this AD. Send your proposal to: George Schwab, Aviation Safety 
Engineer, FAA, Rotorcraft Directorate, Safety Management Group, 2601 
Meacham Blvd., Fort Worth, TX 76137, telephone (817) 222-5114, 
email: george.schwab@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 AD through an AMOC.

(g) Additional Information

    The subject of this AD is addressed in the European Aviation 
Safety Agency AD No. 2011-0162, dated August 30, 2011.

(h) Subject

    Joint Aircraft Service Component (JASC) Code: 2435: Starter 
Generator.

(i) Material Incorporated by Reference

    (1) The Director of the Federal Register approved the 
incorporation by reference (IBR) of the service information listed 
in this paragraph under 5 U.S.C. 552(a) and 1 CFR part 51.
    (2) You must use this service information as applicable to do 
the actions required by this AD, unless the AD specifies otherwise.
    (i) Eurocopter Alert Service Bulletin ASB MBB BK117 C-2-24A-008 
Revision 1, dated August 29, 2011.
    (ii) Reserved.
    (3) For Eurocopter service information identified in this AD, 
contact American Eurocopter Corporation, 2701 N. Forum Drive, Grand 
Prairie, TX 75052, telephone (972) 641-0000 or (800) 232-0323, fax 
(972) 641-3775, or at http://www.eurocopter.com/techpub.
    (4) You may view this service information at the FAA, Office of 
the Regional Counsel, Southwest Region, 2601 Meacham Blvd., Room 
663, Fort Worth, Texas 76137.
    (5) You may also view this service information 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: http://www.archives.gov/federal_register/code_of_federal_regulations/ibr_locations.html.

    Issued in Fort Worth, Texas, on June 14, 2012.
Lance T. Gant,
Acting Manager, Rotorcraft Directorate, Aircraft Certification Service.
[FR Doc. 2012-15325 Filed 6-22-12; 8:45 am]
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