Airworthiness Directives; Eurocopter Deutschland Model EC135 Helicopters, 27956-27958 [2011-11882]

Download as PDF 27956 Federal Register / Vol. 76, No. 93 / Friday, May 13, 2011 / Proposed Rules Related Information (j) MCAI AD No. 2006–0362–E, dated November 30, 2006, contains related information. Joint Aircraft System/Component (JASC) Code (k) The Joint Aircraft System/Component (JASC) Code is 5311: Main Rotor Head. Issued in Fort Worth, Texas, on April 28, 2011. Scott A. Horn, Acting Manager, Rotorcraft Directorate, Aircraft Certification Service. [FR Doc. 2011–11878 Filed 5–12–11; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2011–0453; Directorate Identifier 2008–SW–16–AD] RIN 2120–AA64 Airworthiness Directives; Eurocopter Deutschland Model EC135 Helicopters Federal Aviation Administration (FAA), DOT. ACTION: Notice of proposed rulemaking (NPRM). AGENCY: We propose to adopt a new airworthiness directive (AD) for Eurocopter Deutschland (ECD) Model EC135 helicopters. This proposed AD results from a mandatory continuing airworthiness information (MCAI) AD issued by the aviation authority of the Federal Republic of Germany, with which we have a bilateral agreement, to identify and correct an unsafe condition. The MCAI AD states that in the past, the FADEC FAIL caution light illuminated on a few EC135 T1 helicopters. They state that this was caused by a discrepancy in the parameters which were generated within the fuel main metering unit and transmitted to the FADEC. This discrepancy led to the display of the FADEC FAIL caution light and ‘‘freezing’’ of the fuel main metering valve at its position resulting in loss of the automatic engine control in the affected system. With the EASA AD, a synchronization procedure for pilots, which was already used in the past, is being re-introduced, which prevents the parameter discrepancy arising and thus sustains the automatic engine control. The proposed AD actions are intended to prevent failure of the FADEC to automatically meter fuel, indicated by a FADEC FAIL cockpit WReier-Aviles on DSKGBLS3C1PROD with PROPOSALS SUMMARY: VerDate Mar<15>2010 15:16 May 12, 2011 Jkt 223001 caution light, and subsequent loss of control of the helicopter. DATES: We must receive comments on this proposed AD by June 13, 2011. ADDRESSES: You may send comments by any of the following methods: • Federal eRulemaking Portal: Go to https://www.regulations.gov. Follow the instructions for submitting comments. • Fax: 202–493–2251. • Mail: U.S. Department of Transportation, Docket Operations, M–30, West Building Ground Floor, Room W12–140, 1200 New Jersey Avenue, SE., Washington, DC 20590. • Hand Delivery: U.S. Department of Transportation, Docket Operations, M–30, West Building Ground Floor, Room W12–140, 1200 New Jersey Avenue, SE., Washington, DC 20590, between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. You may get the service information identified in this proposed AD from American Eurocopter Corporation, 2701 Forum Drive, Grand Prairie, Texas 75053–4005, telephone (972) 641–3460, fax (972) 641–3527. Examining the AD Docket: You may examine the AD docket on the Internet at https://www.regulations.gov, or in person at the Docket Operations office between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. The AD docket contains this proposed AD, the economic evaluation, any comments received, and other information. The street address for the Docket Operations office (telephone (800) 647–5527) is in the ADDRESSES section. Comments will be available in the AD docket shortly after receipt. FOR FURTHER INFORMATION CONTACT: Eric Haight, Aviation Safety Engineer, FAA, Rotorcraft Directorate, Regulations and Guidance Group, Fort Worth, Texas 76137, telephone (817) 222–5204, fax (817) 222–5961. SUPPLEMENTARY INFORMATION: Comments Invited We invite you to send any written relevant data, views, or arguments about this proposed AD. Send your comments to an address listed under the ADDRESSES section. Include ‘‘Docket No. FAA–2011–0453; Directorate Identifier 2008–SW–16–AD’’ at the beginning of your comments. We specifically invite comments on the overall regulatory, economic, environmental, and energy aspects of this proposed AD. We will consider all comments received by the closing date and may amend this proposed AD based on those comments. We will post all comments we receive, without change, to https:// www.regulations.gov, including any PO 00000 Frm 00038 Fmt 4702 Sfmt 4702 personal information you provide. We will also post a report summarizing each substantive verbal contact we receive about this proposed AD. Discussion Luftfahrt-Bundesamt, which is the aviation authority for the Federal Republic of Germany, has issued AD No. 2002–333, dated September 16, 2002, to correct an unsafe condition for this German-certificated product. The MCAI AD states that in the past, the FADEC FAIL caution light illuminated on a few EC135 T1 helicopters. They state that this was caused by a discrepancy in the parameters which were generated within the fuel main metering unit and transmitted to the FADEC. This discrepancy led to the display of the FADEC FAIL caution light and ‘‘freezing’’ of the fuel main metering valve at its position resulting in loss of the automatic engine control in the affected system. Despite measures undertaken by Turbomeca to eliminate this problem (software improvements TU19C, TU23C and TU45C), additional FADEC FAIL cases have occurred on EC 135 T1 helicopters for which no explanation has been found. Therefore, a discrepancy in the parameters similar to those in the past cannot be ruled out. With this proposed AD, a synchronization procedure for pilots, which was already used in the past, is being re-introduced, which prevents the parameter discrepancy arising and thus sustains the automatic engine control. To date, there is no terminating action to this required manual pilot synchronization procedure. You may obtain further information by examining the MCAI AD and the service information in the AD docket. Related Service Information ECD has issued Alert Service Bulletin No. EC135–71A–024, dated August 6, 2002 (ASB). The ASB contains copies of special information to be inserted into the Rotorcraft Flight Manual (RFM) for synchronizing fuel control components for sustaining automatic engine control. The ASB specifies making copies of the RFM pages contained in the ASB, cutting them out, and filing them in the RFM. The actions described in the MCAI AD are intended to correct the same unsafe condition as that identified in this service information. FAA’s Determination and Requirements of This Proposed AD This model 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 E:\FR\FM\13MYP1.SGM 13MYP1 Federal Register / Vol. 76, No. 93 / Friday, May 13, 2011 / Proposed Rules agreement with that State of Design Authority, we have been notified of the unsafe condition described in the MCAI AD and service information. We are proposing this AD because we evaluated all pertinent information and determined an unsafe condition exists and is likely to exist or develop on other products of the same type design. Differences Between This AD and the MCAI AD We use a 50-hour TIS compliance time rather than before further flight as used in the MCAI AD. Also, the MCAI AD states to follow the ASB and insert pages into the RFM. We did not follow the ASB, which requires the RFM information to be filed in the Section 4, Normal Procedures, of the RFM. To make compliance with the information mandatory, we are requiring that it be inserted into the Section 2, Limitations Section of the RFM. WReier-Aviles on DSKGBLS3C1PROD with PROPOSALS Costs of Compliance We estimate that this proposed AD would affect about 20 helicopters of U.S. registry. We also estimate that it would take about 1⁄2 work-hour to copy and insert the synchronization procedure into the RFM. The average labor rate is $85 per hour. We estimate the cost of the proposed AD on U.S. operators to be $850. 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 proposed AD would not have federalism implications under Executive Order 13132. This proposed AD would not have a substantial direct effect on the States, on the relationship between the national Government and the States, or on the VerDate Mar<15>2010 15:16 May 12, 2011 Jkt 223001 distribution of power and responsibilities among the various levels of government. For the reasons discussed above, I certify this proposed regulation: 1. Is not a ‘‘significant regulatory action’’ under Executive Order 12866; 2. Is not a ‘‘significant rule’’ under the DOT Regulatory Policies and Procedures (44 FR 11034, February 26, 1979); and 3. Will not have a significant economic impact, positive or negative, on a substantial number of small entities under the criteria of the Regulatory Flexibility Act. We prepared an economic evaluation of the estimated costs to comply with this proposed AD and placed it in the AD docket. List of Subjects in 14 CFR Part 39 Air transportation, Aircraft, Aviation safety, Safety. The Proposed Amendment Accordingly, under the authority delegated to me by the Administrator, the FAA proposes to amend 14 CFR part 39 as follows: PART 39—AIRWORTHINESS DIRECTIVES 1. The authority citation for part 39 continues to read as follows: Authority: 49 U.S.C. 106(g), 40113, 44701. § 39.13 [Amended] 2. The FAA amends § 39.13 by adding the following new AD: Eurocopter Deutschland: Docket No. FAA– 2011–0453; Directorate Identifier 2008– SW–16–AD. Comments Due Date (a) We must receive comments by June 13, 2011. Other Affected ADs (b) None. Applicability (c) This AD applies to Model EC135 helicopters with Turbomeca Arrius 2B or 2B1 engines installed, certificated in any category. Reason (d) The mandatory continuing airworthiness information (MCAI) AD states that in the past, the FADEC FAIL caution light illuminated on a few EC135 T1 helicopters. They state that this was caused by a discrepancy in the parameters which were generated within the fuel main metering unit and transmitted to the FADEC. This discrepancy led to the display of the FADEC FAIL caution light and ‘‘freezing’’ of the fuel main metering valve at its position resulting in loss of the automatic engine control in the affected system. A discrepancy in the parameters similar to those in the past cannot be ruled out. With this AD, a synchronization PO 00000 Frm 00039 Fmt 4702 Sfmt 4702 27957 procedure for pilots is being re-introduced, which prevents the parameter discrepancy arising and thus sustains the automatic engine control. Actions and Compliance (e) Within 50 hours time-in-service (TIS), unless already done, either insert the following procedure by making pen and ink changes to the Rotorcraft Flight Manual (RFM) or by inserting a copy of this AD into the Limitations Section of the RFM. ‘‘SPECIAL INFORMATION FOR OEI/ AUTOROTATION TRAINING AND APPROACH/LANDING PREPARATION In order to prevent a malfunction, which could lead to a FADEC FAIL indication, the following procedure is mandatory: The procedure shown below must be performed while in a steady flight condition and at a safe altitude: —Before initiation of every approach (with or without landing) —During training of OEI or Autorotation before every switch-over to IDLE CAUTION: DURING THE RESET PROCEDURE DESCRIBED IN THE FOLLOWING, NO INPUTS ARE TO BE MADE TO THE COLLECTIVE LEVER OR TO THE TWIST GRIP FOR MANUAL ENGINE CONTROL, SINCE THIS CAN LEAD TO AN INEFFECTIVE SYNCHRONIZATION. The reset procedure is identical for each of two systems and is to be applied for both engines, one after the other. Procedure 1. ENG MODE SEL switch—Set from NORM TO MAN After illumination of the ENG MANUAL caution: 2. ENG MODE SEL switch—Set from MAN to NORM: ENG MANUAL caution must go off Repeat procedure for second engine.’’ Differences Between This FAA AD and the MCAI AD (f) We use a 50-hour TIS compliance time rather than before further flight. Also, the MCAI AD states to follow the ASB and insert pages into the RFM. We did not follow the ASB, which requires the RFM information to be filed in the Section 4, Normal Procedures, of the RFM. To make compliance with the information mandatory, we are requiring that it be inserted into the Section 2, Limitations Section of the RFM. Other Information (g) Alternative Methods of Compliance (AMOCs): The Manager, Safety Management Group, Rotorcraft Directorate, FAA, ATTN: Eric Haight, Aviation Safety Engineer, Regulations and Guidance Group, 2601 Meacham Blvd., Fort Worth, Texas 76137, telephone (817) 222–5204, fax (817) 222– 5961, has the authority to approve AMOCs, if requested, for this AD using the procedures found in 14 CFR 39.19. Related Information (h) MCAI AD 2002–333, dated September 16, 2002, contains related information. Air Transport Association of America (ATA) Tracking Code (i) The ATA Code is 7600: Engine Controls. E:\FR\FM\13MYP1.SGM 13MYP1 27958 Federal Register / Vol. 76, No. 93 / Friday, May 13, 2011 / Proposed Rules Issued in Fort Worth, Texas on April 28, 2011. Scott A. Horn, Acting Manager, Rotorcraft Directorate, Aircraft Certification Service. [FR Doc. 2011–11882 Filed 5–12–11; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2011–0449; Directorate Identifier 2010–SW–021–AD] RIN 2120–AA64 Airworthiness Directives; Bell Helicopter Textron Canada (Bell) Model 206A, 206B, and 206B3 Helicopters Federal Aviation Administration (FAA) DOT. ACTION: Notice of proposed rulemaking (NPRM). AGENCY: We propose to adopt a new airworthiness directive (AD) for the specified Bell model helicopters. This proposed AD would require revising the Operating Limitations, Section 1, of the Rotorcraft Flight Manual (RFM) to add an operating limitation when a litter kit is installed. This proposed AD is prompted by the need for corresponding operating limitations prohibiting flight, including hover, with the litter doorpost removed when certain litter kits are installed. The actions specified by this proposed AD are intended to add an operating limitation when a litter kit is installed to prohibit flight with the doorpost removed to prevent loss of structural integrity of the fuselage. DATES: Comments must be received on or before July 12, 2011. ADDRESSES: Use one of the following addresses to submit comments on this proposed AD: • Federal eRulemaking Portal: Go to https://www.regulations.gov. Follow the instructions for submitting comments. • Fax: 202–493–2251. • Mail: U.S. Department of Transportation, Docket Operations, M–30, West Building Ground Floor, Room W12–140, 1200 New Jersey Avenue, SE., Washington, DC 20590. • Hand Delivery: U.S. Department of Transportation, Docket Operations, M–30, West Building Ground Floor, Room W12–140, 1200 New Jersey Avenue, SE., Washington, DC 20590, between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. You may get the service information identified in this proposed AD from Bell WReier-Aviles on DSKGBLS3C1PROD with PROPOSALS SUMMARY: VerDate Mar<15>2010 15:16 May 12, 2011 Jkt 223001 Helicopter Textron Canada Limited, 12,800 Rue de l’Avenir, Mirabel, Quebec J7J1R4, telephone (450) 437–2862 or (800) 363–8023, fax (450) 433–0272, or at https://www.bellcustomer.com/files/. You may examine the comments to this proposed AD in the AD docket on the Internet at https:// www.regulations.gov. FOR FURTHER INFORMATION CONTACT: Mark Wiley, Aviation Safety Engineer, FAA, Rotorcraft Directorate, Regulations and Guidance Group, 2601 Meacham Blvd., Fort Worth, Texas 76137, telephone (817) 222–5134, fax (817) 222–5961. SUPPLEMENTARY INFORMATION: Comments Invited We invite you to send any written relevant data, views, or arguments about this proposed AD. Send your comments to an address listed under the caption ADDRESSES. Include the Docket No. ‘‘FAA–2011–0449, Directorate Identifier 2010–SW–021–AD’’ at the beginning of your comments. We specifically invite comments on the overall regulatory, economic, environmental, and energy aspects of this proposed AD. We will consider all comments received by the closing date and may amend this proposed AD because of those comments. We will post all comments we receive, without change, to https:// www.regulations.gov, including any personal information you provide. We will also post a report summarizing each substantive verbal contact with FAA personnel concerning this proposed rulemaking. Using the search function of the docket Web site, you can find and read the comments to any of our dockets, including the name of the individual who sent or signed the comment. You may review the DOT’s complete Privacy Act Statement in the Federal Register published on April 11, 2000 (65 FR 19477–78). Examining the Docket You may examine the docket that contains the proposed AD, any comments, and other information in person at the Docket Operations office between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. The Docket Operations office (telephone (800) 647–5527) is located in Room W12–140 on the ground floor of the West Building at the street address stated in the ADDRESSES section. Comments will be available in the AD docket shortly after receipt. Discussion Bell reissued RFM Supplement (RFMS) BHT–206A–FMS–8 for the PO 00000 Frm 00040 Fmt 4702 Sfmt 4702 Model 206A, BHT–206B–FMS–8 for the Model 206B, and BHT–206B3–FMS–2 for the Model 206B3 helicopters, all dated December 30, 2009, approved by Transport Canada and the FAA. The revisions to the RFMS were reformatted to match the RFM and to add a ‘‘Type of Operation’’ paragraph to Section 1 of the ‘‘Operating Limitations,’’ which states: ‘‘Flight, including hover, with litter doorpost removed is not approved. Litter doorpost may be removed and reinstalled with rotor turning at flat pitch.’’ FAA’s Evaluation and Unsafe Condition Determination These helicopters have been approved by the aviation authority of Canada and are approved for operation in the United States. We are proposing this AD because we evaluated all information provided by Transport Canada and determined the unsafe condition exists and is likely to exist or develop on other helicopters of these same type designs. This proposed AD would require revising the RFM by inserting into the Operating Limitations, Section 1, of the RFM the following statement: ‘‘Flight, including hover, with litter doorpost removed is prohibited.’’ This revision may be made by pen and ink changes, inserting a copy of this AD into the RFM, or inserting a copy of the RFMS dealing with Litter Kits into the RFM as follows: For Model 206A helicopters— inserting RFMS BHT–206A–FMS–8, dated December 30, 2009, into RFM BHT–206A–FM–1, dated July 2, 2009; for Model 206B helicopters—inserting RFMS BHT–206B–FMS–8, dated December 30, 2009, into RFM BHT– 206B–FM–1, dated July 2, 2009; and for Model 206B3 helicopters—inserting RFMS BHT–206B3–FMS–2, dated December 30, 2009, into RFM BHT– 206B3–FM–1, dated March 24, 2010. This limitation is required to prevent loss of structural integrity of the helicopter fuselage. Costs of Compliance We estimate this proposed AD would affect 1,463 helicopters of U.S. registry. The cost to revise the operating limitations section of the RFM for each helicopter would be negligible, and there are no required parts. Regulatory Findings We have determined that this proposed AD would not have federalism implications under Executive Order 13132. Additionally, this proposed AD would not have a substantial direct effect on the States, on the relationship between the national Government and the States, or on the distribution of E:\FR\FM\13MYP1.SGM 13MYP1

Agencies

[Federal Register Volume 76, Number 93 (Friday, May 13, 2011)]
[Proposed Rules]
[Pages 27956-27958]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 2011-11882]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2011-0453; Directorate Identifier 2008-SW-16-AD]
RIN 2120-AA64


Airworthiness Directives; Eurocopter Deutschland Model EC135 
Helicopters

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Notice of proposed rulemaking (NPRM).

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

SUMMARY: We propose to adopt a new airworthiness directive (AD) for 
Eurocopter Deutschland (ECD) Model EC135 helicopters. This proposed AD 
results from a mandatory continuing airworthiness information (MCAI) AD 
issued by the aviation authority of the Federal Republic of Germany, 
with which we have a bilateral agreement, to identify and correct an 
unsafe condition. The MCAI AD states that in the past, the FADEC FAIL 
caution light illuminated on a few EC135 T1 helicopters. They state 
that this was caused by a discrepancy in the parameters which were 
generated within the fuel main metering unit and transmitted to the 
FADEC. This discrepancy led to the display of the FADEC FAIL caution 
light and ``freezing'' of the fuel main metering valve at its position 
resulting in loss of the automatic engine control in the affected 
system. With the EASA AD, a synchronization procedure for pilots, which 
was already used in the past, is being re-introduced, which prevents 
the parameter discrepancy arising and thus sustains the automatic 
engine control.
    The proposed AD actions are intended to prevent failure of the 
FADEC to automatically meter fuel, indicated by a FADEC FAIL cockpit 
caution light, and subsequent loss of control of the helicopter.

DATES: We must receive comments on this proposed AD by June 13, 2011.

ADDRESSES: You may send comments by any of the following methods:
     Federal eRulemaking Portal: Go to https://www.regulations.gov. Follow the instructions for submitting comments.
     Fax: 202-493-2251.
     Mail: U.S. Department of Transportation, Docket 
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New 
Jersey Avenue, SE., Washington, DC 20590.
     Hand Delivery: U.S. Department of Transportation, Docket 
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New 
Jersey Avenue, SE., Washington, DC 20590, between 9 a.m. and 5 p.m., 
Monday through Friday, except Federal holidays.
    You may get the service information identified in this proposed AD 
from American Eurocopter Corporation, 2701 Forum Drive, Grand Prairie, 
Texas 75053-4005, telephone (972) 641-3460, fax (972) 641-3527.
    Examining the AD Docket: You may examine the AD docket on the 
Internet at https://www.regulations.gov, or in person at the Docket 
Operations office between 9 a.m. and 5 p.m., Monday through Friday, 
except Federal holidays. The AD docket contains this proposed AD, the 
economic evaluation, any comments received, and other information. The 
street address for the Docket Operations office (telephone (800) 647-
5527) is in the ADDRESSES section. Comments will be available in the AD 
docket shortly after receipt.

FOR FURTHER INFORMATION CONTACT: Eric Haight, Aviation Safety Engineer, 
FAA, Rotorcraft Directorate, Regulations and Guidance Group, Fort 
Worth, Texas 76137, telephone (817) 222-5204, fax (817) 222-5961.

SUPPLEMENTARY INFORMATION:

Comments Invited

    We invite you to send any written relevant data, views, or 
arguments about this proposed AD. Send your comments to an address 
listed under the ADDRESSES section. Include ``Docket No. FAA-2011-0453; 
Directorate Identifier 2008-SW-16-AD'' at the beginning of your 
comments. We specifically invite comments on the overall regulatory, 
economic, environmental, and energy aspects of this proposed AD. We 
will consider all comments received by the closing date and may amend 
this proposed AD based on those comments.
    We will post all comments we receive, without change, to https://www.regulations.gov, including any personal information you provide. We 
will also post a report summarizing each substantive verbal contact we 
receive about this proposed AD.

Discussion

    Luftfahrt-Bundesamt, which is the aviation authority for the 
Federal Republic of Germany, has issued AD No. 2002-333, dated 
September 16, 2002, to correct an unsafe condition for this German-
certificated product. The MCAI AD states that in the past, the FADEC 
FAIL caution light illuminated on a few EC135 T1 helicopters. They 
state that this was caused by a discrepancy in the parameters which 
were generated within the fuel main metering unit and transmitted to 
the FADEC. This discrepancy led to the display of the FADEC FAIL 
caution light and ``freezing'' of the fuel main metering valve at its 
position resulting in loss of the automatic engine control in the 
affected system. Despite measures undertaken by Turbomeca to eliminate 
this problem (software improvements TU19C, TU23C and TU45C), additional 
FADEC FAIL cases have occurred on EC 135 T1 helicopters for which no 
explanation has been found. Therefore, a discrepancy in the parameters 
similar to those in the past cannot be ruled out. With this proposed 
AD, a synchronization procedure for pilots, which was already used in 
the past, is being re-introduced, which prevents the parameter 
discrepancy arising and thus sustains the automatic engine control. To 
date, there is no terminating action to this required manual pilot 
synchronization procedure.
    You may obtain further information by examining the MCAI AD and the 
service information in the AD docket.

Related Service Information

    ECD has issued Alert Service Bulletin No. EC135-71A-024, dated 
August 6, 2002 (ASB). The ASB contains copies of special information to 
be inserted into the Rotorcraft Flight Manual (RFM) for synchronizing 
fuel control components for sustaining automatic engine control. The 
ASB specifies making copies of the RFM pages contained in the ASB, 
cutting them out, and filing them in the RFM. The actions described in 
the MCAI AD are intended to correct the same unsafe condition as that 
identified in this service information.

FAA's Determination and Requirements of This Proposed AD

    This model 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

[[Page 27957]]

agreement with that State of Design Authority, we have been notified of 
the unsafe condition described in the MCAI AD and service information. 
We are proposing this AD because we evaluated all pertinent information 
and determined an unsafe condition exists and is likely to exist or 
develop on other products of the same type design.

Differences Between This AD and the MCAI AD

    We use a 50-hour TIS compliance time rather than before further 
flight as used in the MCAI AD. Also, the MCAI AD states to follow the 
ASB and insert pages into the RFM. We did not follow the ASB, which 
requires the RFM information to be filed in the Section 4, Normal 
Procedures, of the RFM. To make compliance with the information 
mandatory, we are requiring that it be inserted into the Section 2, 
Limitations Section of the RFM.

Costs of Compliance

    We estimate that this proposed AD would affect about 20 helicopters 
of U.S. registry. We also estimate that it would take about \1/2\ work-
hour to copy and insert the synchronization procedure into the RFM. The 
average labor rate is $85 per hour. We estimate the cost of the 
proposed AD on U.S. operators to be $850.

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 proposed AD would not have federalism 
implications under Executive Order 13132. This proposed AD would not 
have a substantial direct effect on the States, on the relationship 
between the national Government and the States, or on the distribution 
of power and responsibilities among the various levels of government.
    For the reasons discussed above, I certify this proposed 
regulation:
    1. Is not a ``significant regulatory action'' under Executive Order 
12866;
    2. Is not a ``significant rule'' under the DOT Regulatory Policies 
and Procedures (44 FR 11034, February 26, 1979); and
    3. Will not have a significant economic impact, positive or 
negative, on a substantial number of small entities under the criteria 
of the Regulatory Flexibility Act.
    We prepared an economic evaluation of the estimated costs to comply 
with this proposed AD and placed it in the AD docket.

List of Subjects in 14 CFR Part 39

    Air transportation, Aircraft, Aviation safety, Safety.

The Proposed Amendment

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

PART 39--AIRWORTHINESS DIRECTIVES

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

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


Sec.  39.13  [Amended]

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

Eurocopter Deutschland: Docket No. FAA-2011-0453; Directorate 
Identifier 2008-SW-16-AD.

Comments Due Date

    (a) We must receive comments by June 13, 2011.

Other Affected ADs

    (b) None.

Applicability

    (c) This AD applies to Model EC135 helicopters with Turbomeca 
Arrius 2B or 2B1 engines installed, certificated in any category.

Reason

    (d) The mandatory continuing airworthiness information (MCAI) AD 
states that in the past, the FADEC FAIL caution light illuminated on 
a few EC135 T1 helicopters. They state that this was caused by a 
discrepancy in the parameters which were generated within the fuel 
main metering unit and transmitted to the FADEC. This discrepancy 
led to the display of the FADEC FAIL caution light and ``freezing'' 
of the fuel main metering valve at its position resulting in loss of 
the automatic engine control in the affected system. A discrepancy 
in the parameters similar to those in the past cannot be ruled out. 
With this AD, a synchronization procedure for pilots is being re-
introduced, which prevents the parameter discrepancy arising and 
thus sustains the automatic engine control.

Actions and Compliance

    (e) Within 50 hours time-in-service (TIS), unless already done, 
either insert the following procedure by making pen and ink changes 
to the Rotorcraft Flight Manual (RFM) or by inserting a copy of this 
AD into the Limitations Section of the RFM.

    ``SPECIAL INFORMATION FOR OEI/AUTOROTATION TRAINING AND 
APPROACH/LANDING PREPARATION
    In order to prevent a malfunction, which could lead to a FADEC 
FAIL indication, the following procedure is mandatory:
    The procedure shown below must be performed while in a steady 
flight condition and at a safe altitude:

--Before initiation of every approach (with or without landing)
--During training of OEI or Autorotation before every switch-over to 
IDLE

    CAUTION: DURING THE RESET PROCEDURE DESCRIBED IN THE FOLLOWING, 
NO INPUTS ARE TO BE MADE TO THE COLLECTIVE LEVER OR TO THE TWIST 
GRIP FOR MANUAL ENGINE CONTROL, SINCE THIS CAN LEAD TO AN 
INEFFECTIVE SYNCHRONIZATION.
    The reset procedure is identical for each of two systems and is 
to be applied for both engines, one after the other.
    Procedure
    1. ENG MODE SEL switch--Set from NORM TO MAN
    After illumination of the ENG MANUAL caution:
    2. ENG MODE SEL switch--Set from MAN to NORM: ENG MANUAL caution 
must go off
    Repeat procedure for second engine.''

Differences Between This FAA AD and the MCAI AD

    (f) We use a 50-hour TIS compliance time rather than before 
further flight. Also, the MCAI AD states to follow the ASB and 
insert pages into the RFM. We did not follow the ASB, which requires 
the RFM information to be filed in the Section 4, Normal Procedures, 
of the RFM. To make compliance with the information mandatory, we 
are requiring that it be inserted into the Section 2, Limitations 
Section of the RFM.

Other Information

    (g) Alternative Methods of Compliance (AMOCs): The Manager, 
Safety Management Group, Rotorcraft Directorate, FAA, ATTN: Eric 
Haight, Aviation Safety Engineer, Regulations and Guidance Group, 
2601 Meacham Blvd., Fort Worth, Texas 76137, telephone (817) 222-
5204, fax (817) 222-5961, has the authority to approve AMOCs, if 
requested, for this AD using the procedures found in 14 CFR 39.19.

Related Information

    (h) MCAI AD 2002-333, dated September 16, 2002, contains related 
information.

Air Transport Association of America (ATA) Tracking Code

    (i) The ATA Code is 7600: Engine Controls.


[[Page 27958]]


    Issued in Fort Worth, Texas on April 28, 2011.
Scott A. Horn,
Acting Manager, Rotorcraft Directorate, Aircraft Certification Service.
[FR Doc. 2011-11882 Filed 5-12-11; 8:45 am]
BILLING CODE 4910-13-P