Source: https://regulations.justia.com/regulations/fedreg/2014/08/18/2014-19524.html
Timestamp: 2020-08-09 18:14:57
Document Index: 548458862

Matched Legal Cases: ['art 39', 'art 39', 'art 39', 'ART 39', 'art 39', '§ 39', '§ 39', 'art 119', 'art 91', 'art 275']

Airworthiness Directives; Airbus Helicopters Deutschland GmbH (Previously Eurocopter Deutschland GmbH) (Airbus Helicopters) Helicopters, 48707-48709 [2014-19524] :: Federal Aviation Administration :: Department Of Transportation :: Regulation Tracker :: Justia
Justia Regulation Tracker Department Of Transportation Federal Aviation Administration Airworthiness Directives; Airbus Helicopters Deutschland GmbH (Previously Eurocopter Deutschland GmbH) (Airbus Helicopters) Helicopters, 48707-48709 [2014-19524]
Airworthiness Directives; Airbus Helicopters Deutschland GmbH (Previously Eurocopter Deutschland GmbH) (Airbus Helicopters) Helicopters, 48707-48709 [2014-19524]
Download as PDF Federal Register / Vol. 79, No. 159 / Monday, August 18, 2014 / Proposed Rules DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2014–0577; Directorate Identifier 2013–SW–042–AD] RIN 2120–AA64 Airworthiness Directives; Airbus Helicopters Deutschland GmbH (Previously Eurocopter Deutschland GmbH) (Airbus Helicopters) Helicopters Federal Aviation Administration (FAA), DOT. ACTION: Notice of proposed rulemaking (NPRM). AGENCY: We propose to adopt a new airworthiness directive (AD) for Airbus Helicopters Model EC135P1, EC135T1, EC135P2, EC135T2, EC135P2+, EC135T2+, and MBB–BK 117 C–2 helicopters. This proposed AD would require inspecting certain washers for movement and making appropriate repairs if the washers move. This proposed AD is prompted by play found between the Smart Electro Mechanical Actuator (SEMA) and the control rod during installation work on a helicopter. The proposed actions are intended to prevent loss of concerned control axis and subsequent loss of control of the helicopter. SUMMARY: We must receive comments on this proposed AD by October 17, 2014. ADDRESSES: You may send comments by any of the following methods: • Federal eRulemaking Docket: Go to http://www.regulations.gov. Follow the online instructions for sending your comments electronically. • Fax: 202–493–2251. • Mail: Send comments to the U.S. Department of Transportation, Docket Operations, M–30, West Building Ground Floor, Room W12–140, 1200 New Jersey Avenue SE., Washington, DC 20590–0001. • Hand Delivery: Deliver to the ‘‘Mail’’ address between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. DATES: tkelley on DSK3SPTVN1PROD with PROPOSALS 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 proposed AD, the European Aviation Safety Agency (EASA) AD, the economic evaluation, any comments received, and other VerDate Mar<15>2010 16:52 Aug 15, 2014 Jkt 232001 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 proposed AD, contact Airbus Helicopters, Inc., 2701 N. Forum Drive, Grand Prairie, TX 75052; telephone (972) 641–0000 or (800) 232–0323; fax (972) 641–3775; or at http:// www.airbushelicopters.com/techpub. You may review the referenced service information at the FAA, Office of the Regional Counsel, Southwest Region, 2601 Meacham Blvd., Room 663, Fort Worth, Texas 76137. FOR FURTHER INFORMATION CONTACT: Matt Wilbanks, Aviation Safety Engineer, Regulations and Policy Group, Rotorcraft Directorate, FAA, 2601 Meacham Blvd., Fort Worth, Texas 76137; telephone (817) 222–5110; email matt.wilbanks@faa.gov. SUPPLEMENTARY INFORMATION: Comments Invited 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 might result from adopting the proposals in this document. The most helpful comments reference a specific portion of the proposal, 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 only one time. We will file in the docket all comments that we receive, as well as a report summarizing each substantive public contact with FAA personnel concerning this proposed rulemaking. Before acting on this proposal, we will consider all comments we receive on or before the closing date for comments. We will consider comments filed after the comment period has closed if it is possible to do so without incurring expense or delay. We may change this proposal in light of the comments we receive. Discussion EASA, which is the Technical Agent for the Member States of the European Union, issued EASA AD No. 2013–0176, dated August 7, 2013, to correct an unsafe condition for Eurocopter Deutschland GmbH Model EC 135 P1 (CDS), EC 135 P1 (CPDS), EC 135 P2+, EC 135 P2 (CPDS), EC 135 T1 (CDS), EC PO 00000 Frm 00015 Fmt 4702 Sfmt 4702 48707 135 T1 (CPDS), EC 135 T2+, EC 135 T2 (CPDS), EC 635 P2+, EC 635 T1 (CPDS), EC 635 T2+, and MBB–BK 117 C–2 helicopters. EASA advises that during installation work on a helicopter, it was discovered that it was not possible to install attachment hardware on a threaded blind borehole between the SEMA and the control rod without play. According to EASA, the loose attachment hardware was caused by an ‘‘unfavourable adding of the tolerances’’ of the individual attachment hardware elements. EASA states that as a result, the screw pushed against the bottom of the threaded blind borehole on the SEMA, and no clamping force could be achieved on the screw head. EASA advises that this condition, if not detected and corrected, could lead to loss of the concerned control axis, possibly resulting in loss of helicopter control. For these reasons, EASA AD No. 2013–0176 requires a one-time inspection of the affected SEMA attachment hardware to detect improper connection and play and, depending on the findings, replacement of the affected hardware. Since the issuance of EASA AD No. 2013–0176, Eurocopter Deutschland GmbH has changed its name to Airbus Helicopters Deutschland GmbH. FAA’s Determination These helicopters have been approved by the aviation authority of Germany and are approved for operation in the United States. Pursuant to our bilateral agreement with Germany, EASA, its technical representative, has notified us of the unsafe condition described in its AD. We are proposing this AD because we evaluated all known relevant information and determined that an unsafe condition is likely to exist or develop on other products of the same type design. Related Service Information Eurocopter reported in Alert Service Bulletins (ASBs) EC135–22A–015, Revision 1, dated January 28, 2013, and MBB BK117 C–2–22A–009, Revision 1, dated August 3, 2009, that it was discovered during the installation work on a helicopter that it was not possible to establish attachment hardware on a threaded blind borehole between the SEMA and the control rod without play. The ASBs state that ‘‘unfavourable adding of the tolerances’’ of the individual attachment hardware elements caused the screw to push against the bottom of the threaded blind borehole on the SEMA, preventing any clamping force on the screw head. The ASBs call for inspecting the SEMA attachment hardware connected to their E:\FR\FM\18AUP1.SGM 18AUP1 48708 Federal Register / Vol. 79, No. 159 / Monday, August 18, 2014 / Proposed Rules respective control rods for play and making the proper adjustments to eliminate any play. Proposed AD Requirements This proposed AD would require, within 50 hours time-in-service, inspecting whether the washers can be moved in the attachment hardware that connects the SEMA and the control rod of the longitudinal, lateral, and yaw actuators. For Model MBB BK117 C–2 helicopters, this inspection is only for the hardware connecting the YawSEMA and the Yaw-SEMA control rod. If none of the washers can be moved, then no further action is needed. If a washer can be moved, then this proposed AD would require replacing the four screws, installing two additional washers, and torquetightening the screws to 5–6 Nm. Differences Between This Proposed AD and the EASA AD The EASA AD applies to Eurocopter Model EC635P2+, EC635T1 and EC635T2+ helicopters. The proposed AD does not apply to these model helicopters because they have no FAA type certificate. tkelley on DSK3SPTVN1PROD with PROPOSALS Costs of Compliance We estimate that this proposed AD would affect 385 helicopters of U.S. Registry and that labor costs average $85 per work-hour. Based on these estimates, we expect the following costs: • Inspecting for movement of the washers would require 1.5 work hours for a labor cost of $128 per helicopter and $49,280 for the U.S. fleet. • Replacing the screws and related work would require an additional 0.5 work-hours for a labor cost of $43. Screws would cost $4 each while washers would cost $10 each. We estimate the cost would be $79 per repair. 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 proposed VerDate Mar<15>2010 16:52 Aug 15, 2014 Jkt 232001 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, 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); 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 proposed 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. 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 airworthiness directive (AD): ■ Airbus Helicopters Deutschland GmbH (Previously Eurocopter Deutschland GmbH) (Airbus Helicopters) Helicopters: Docket No. FAA–2014–0577; Directorate Identifier 2013–SW–042–AD. (a) Applicability This AD applies to Airbus Helicopters Model EC135P1, EC135T1, EC135P2, EC135T2, EC135P2+, EC135T2+, and MBB– BK 117 C–2 helicopters, certificated in any category. PO 00000 Frm 00016 Fmt 4702 Sfmt 4702 (b) Unsafe Condition This AD defines the unsafe condition as loose attachment hardware between the Smart Electro Mechanical Actuator (SEMA) and a control rod. This condition could result in loss of the control axis and subsequent loss of control of the helicopter. (c) Comments Due Date We must receive comments by October 17, 2014. (d) Compliance You are responsible for performing each action required by this AD within the specified compliance time unless it has already been accomplished prior to that time. (e) Required Actions (1) Within 50 hours time in service (TIS), for Model EC135P1, EC135T1, EC135P2, EC135T2, EC135P2+, and EC135T2+ helicopters, do the following: (i) Using Figure 1 and Figure 2 of Eurocopter Alert Service Bulletin EC135– 22A–015, Revision 1, dated January 28, 2013 (ASB EC135–22A–015) as reference, inspect the attachment hardware between the SEMA and the longitudinal actuator control rod to determine whether any of the washers can be moved. (A) If no washer can be moved, no further action is needed. (B) If a washer can be moved, replace the four screws and install two additional washers, part number (P/N) EN2139–05016, to connect the SEMA with the control rod. Torque-tighten each screw to 5–6 Nm. (ii) Using Figure 1 and Figure 2 of ASB EC135–22A–015 as reference, inspect the attachment hardware between the SEMA and the lateral actuator control rod to determine whether any of the washers can be moved. (A) If no washer can be moved, no further action is needed. (B) If a washer can be moved, replace the four screws and install two additional washers, P/N EN2139–05016, to connect the SEMA with the control rod. Torque-tighten each screw to 5–6 Nm. (iii) Using Figure 1, Figure 3, and Figure 4 of ASB EC135–22A–015 as reference, inspect the attachment hardware between the SEMA and the yaw actuator control rod to determine whether any of the washers can be moved. (A) If no washer can be moved, no further action is needed. (B) If a washer can be moved, replace the four screws and install two additional washers, P/N EN2139–05016, to connect the SEMA with the control rod. Torque-tighten each screw to 5–6 Nm. (2) Within 50 hours TIS, for Model MBB BK117 C–2 helicopters, using Figure 1 of Eurocopter Alert Service Bulletin MBB BK117 C–2–22A–009, Revision 1, dated August 3, 2009, as reference, inspect the attachment hardware between the YawSEMA and the Yaw-SEMA control rod to determine whether any of the washers can be moved. (i) If no washer can be moved, no further action is needed. (ii) If a washer can be moved, replace the four screws and install two additional E:\FR\FM\18AUP1.SGM 18AUP1 Federal Register / Vol. 79, No. 159 / Monday, August 18, 2014 / Proposed Rules washers, P/N EN2139–05016, to connect the SEMA with the control rod. Torque-tighten each screw to 5–6 Nm and apply polyurethane lacquer onto the attachment hardware. (f) Alternative Methods of Compliance (AMOCs) (1) The Manager, Safety Management Group, FAA, may approve AMOCs for this AD. Send your proposal to: Matt Wilbanks, Aviation Safety Engineer, Regulations and Policy Group, Rotorcraft Directorate, FAA, 2601 Meacham Blvd., Fort Worth, Texas 76137; telephone (817) 222–5110; email matt.wilbanks@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 (EASA) AD No. 2013–0176, dated August 7, 2013. You may view the EASA AD on the Internet at http://www.regulations.gov in Docket No. FAA–2014–0577. (i) Subject Joint Aircraft Service Component (JASC) Code: 2213, Flight Controller. Issued in Fort Worth, Texas, on August 8, 2014. Lance T. Gant, Acting Directorate Manager, Rotorcraft Directorate, Aircraft Certification Service. [FR Doc. 2014–19524 Filed 8–15–14; 8:45 am] BILLING CODE 4910–13–P SECURITIES AND EXCHANGE COMMISSION 17 CFR Part 275 [Release No. IA–3893; File No. S7–23–07] RIN 3235–AL56 Securities and Exchange Commission. ACTION: Proposed rule. AGENCY: The Securities and Exchange Commission is proposing to amend rule 206(3)–3T under the Investment Advisers Act of 1940, a temporary rule that establishes an alternative means for investment advisers that are registered with the Commission as broker-dealers to meet the requirements of section 206(3) of the Investment Advisers Act when they act in a principal capacity in transactions with certain of their advisory clients. The amendment would tkelley on DSK3SPTVN1PROD with PROPOSALS SUMMARY: 16:52 Aug 15, 2014 Comments must be received on or before September 17, 2014. DATES: Comments may be submitted by any of the following methods: ADDRESSES: Electronic Comments • Use the Commission’s Internet comment form (http://www.sec.gov/ rules/proposed.shtml); or • Send an email to rule-comments@ sec.gov. Please include File Number S7– 23–07 on the subject line; or • Use the Federal eRulemaking Portal (http://www.regulations.gov). Follow the instructions for submitting comments. Paper Comments • Send paper comments to Secretary, Securities and Exchange Commission, 100 F Street NE., Washington, DC 20549–1090. All submissions should refer to File Number S7–23–07. This file number should be included on the subject line if email is used. To help us process and review your comments more efficiently, please use only one method. The Commission will post all comments on the Commission’s Internet Web site (http://www.sec.gov/rules/ proposed.shtml). Comments are also available for Web site viewing and printing in the Commission’s Public Reference Room, 100 F Street NE., Washington, DC 20549, on official business days between the hours of 10:00 a.m. and 3:00 p.m. All comments received will be posted without change; we do not edit personal identifying information from submissions. You should submit only information that you wish to make available publicly. FOR FURTHER INFORMATION CONTACT: Temporary Rule Regarding Principal Trades With Certain Advisory Clients VerDate Mar<15>2010 extend the date on which rule 206(3)– 3T will sunset from December 31, 2014 to December 31, 2016. Jkt 232001 Melissa S. Gainor, Senior Counsel, Sarah A. Buescher, Branch Chief, or Daniel S. Kahl, Assistant Director, at (202) 551–6787 or IArules@sec.gov, Investment Adviser Regulation Office, Division of Investment Management, U.S. Securities and Exchange Commission, 100 F Street NE., Washington, DC 20549–8549. The Securities and Exchange Commission is proposing an amendment to temporary rule 206(3)–3T [17 CFR 275.206(3)–3T] under the Investment Advisers Act of 1940 [15 U.S.C. 80b] that would extend the date on which the rule will sunset from December 31, 2014 to December 31, 2016. SUPPLEMENTARY INFORMATION: PO 00000 Frm 00017 Fmt 4702 Sfmt 4702 48709 I. Background On September 24, 2007, we adopted, on an interim final basis, rule 206(3)– 3T, a temporary rule under the Investment Advisers Act of 1940 (the ‘‘Advisers Act’’) that provides an alternative means for investment advisers that are registered with us as broker-dealers to meet the requirements of section 206(3) of the Advisers Act when they act in a principal capacity in transactions with certain of their advisory clients.1 The purpose of the rule was to permit broker-dealers to sell to their advisory clients, in the wake of Financial Planning Association v. SEC (the ‘‘FPA Decision’’),2 certain securities held in the proprietary accounts of their firms that might not be available on an agency basis—or might be available on an agency basis only on less attractive terms 3—while protecting clients from conflicts of interest as a result of such transactions.4 As initially adopted on an interim final basis, rule 206(3)–3T was set to sunset on December 31, 2009. In December 2009, however, we adopted rule 206(3)–3T as a final rule in the same form in which it was adopted on an interim final basis in 2007, except that we extended the rule’s sunset date by one year to December 31, 2010.5 We 1 Rule 206(3)–3T [17 CFR 275.206(3)–3T]. All references to rule 206(3)–3T and the various sections thereof in this release are to 17 CFR 275.206(3)–3T and its corresponding sections. See also Temporary Rule Regarding Principal Trades with Certain Advisory Clients, Investment Advisers Act Release No. 2653 (Sep. 24, 2007) [72 FR 55022 (Sep. 28, 2007)] (‘‘2007 Principal Trade Rule Release’’). 2 482 F.3d 481 (D.C. Cir. 2007). In the FPA Decision, handed down on March 30, 2007, the Court of Appeals for the DC Circuit vacated (subject to a subsequent stay until October 1, 2007) rule 202(a)(11)–1 under the Advisers Act. Rule 202(a)(11)–1 provided, among other things, that feebased brokerage accounts were not advisory accounts and were thus not subject to the Advisers Act. For further discussion of fee-based brokerage accounts, see 2007 Principal Trade Rule Release, Section I. 3 See 2007 Principal Trade Rule Release at nn.19– 20 and Section VI.C. 4 As a consequence of the FPA Decision, brokerdealers offering fee-based brokerage accounts with an advisory component became subject to the Advisers Act with respect to those accounts, and the client relationship became fully subject to the Advisers Act. These broker-dealers—to the extent they wanted to continue to offer fee-based accounts and met the requirements for registration—had to: Register as investment advisers, if they had not done so already; act as fiduciaries with respect to those clients; disclose all material conflicts of interest; and otherwise fully comply with the Advisers Act, including the restrictions on principal trading contained in section 206(3) of the Act. See 2007 Principal Trade Rule Release, Section I. 5 See Temporary Rule Regarding Principal Trades with Certain Advisory Clients, Investment Advisers Act Release No. 2965 (Dec. 23, 2009) [74 FR 69009 E:\FR\FM\18AUP1.SGM Continued 18AUP1
[Pages 48707-48709]
[FR Doc No: 2014-19524]
[[Page 48707]]
[Docket No. FAA-2014-0577; Directorate Identifier 2013-SW-042-AD]
(Previously Eurocopter Deutschland GmbH) (Airbus Helicopters)
Airbus Helicopters Model EC135P1, EC135T1, EC135P2, EC135T2, EC135P2+,
EC135T2+, and MBB-BK 117 C-2 helicopters. This proposed AD would
require inspecting certain washers for movement and making appropriate
repairs if the washers move. This proposed AD is prompted by play found
between the Smart Electro Mechanical Actuator (SEMA) and the control
rod during installation work on a helicopter. The proposed actions are
intended to prevent loss of concerned control axis and subsequent loss
of control of the helicopter.
DATES: We must receive comments on this proposed AD by October 17,
Federal eRulemaking Docket: Go to http://www.regulations.gov. Follow the online instructions for sending your
Mail: Send comments to the U.S. Department of
Room W12-140, 1200 New Jersey Avenue SE., Washington, DC 20590-0001.
Hand Delivery: Deliver to the ``Mail'' address between 9
You may examine the AD docket on the Internet at http://www.regulations.gov or in person at the Docket Operations Office
holidays. The AD docket contains this proposed AD, the European
Aviation Safety Agency (EASA) AD, the economic evaluation, any comments
Operations Office (telephone 800-647-5527) is in the ADDRESSES section.
Comments will be available in the AD docket shortly after receipt.
Airbus Helicopters, Inc., 2701 N. Forum Drive, Grand Prairie, TX 75052;
telephone (972) 641-0000 or (800) 232-0323; fax (972) 641-3775; or at
http://www.airbushelicopters.com/techpub. You may review the referenced
Southwest Region, 2601 Meacham Blvd., Room 663, Fort Worth, Texas
76137.
FOR FURTHER INFORMATION CONTACT: Matt Wilbanks, Aviation Safety
Engineer, Regulations and Policy Group, Rotorcraft Directorate, FAA,
2601 Meacham Blvd., Fort Worth, Texas 76137; telephone (817) 222-5110;
email matt.wilbanks@faa.gov.
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 might
result from adopting the proposals in this document. The most helpful
comments reference a specific portion of the proposal, 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 only one time.
We will file in the docket all comments that we receive, as well as
a report summarizing each substantive public contact with FAA personnel
concerning this proposed rulemaking. Before acting on this proposal, we
will consider all comments we receive on or before the closing date for
comments. We will consider comments filed after the comment period has
closed if it is possible to do so without incurring expense or delay.
We may change this proposal in light of the comments we receive.
EASA, which is the Technical Agent for the Member States of the
European Union, issued EASA AD No. 2013-0176, dated August 7, 2013, to
correct an unsafe condition for Eurocopter Deutschland GmbH Model EC
135 P1 (CDS), EC 135 P1 (CPDS), EC 135 P2+, EC 135 P2 (CPDS), EC 135 T1
(CDS), EC 135 T1 (CPDS), EC 135 T2+, EC 135 T2 (CPDS), EC 635 P2+, EC
635 T1 (CPDS), EC 635 T2+, and MBB-BK 117 C-2 helicopters. EASA advises
that during installation work on a helicopter, it was discovered that
it was not possible to install attachment hardware on a threaded blind
borehole between the SEMA and the control rod without play. According
to EASA, the loose attachment hardware was caused by an ``unfavourable
adding of the tolerances'' of the individual attachment hardware
elements. EASA states that as a result, the screw pushed against the
bottom of the threaded blind borehole on the SEMA, and no clamping
force could be achieved on the screw head. EASA advises that this
condition, if not detected and corrected, could lead to loss of the
concerned control axis, possibly resulting in loss of helicopter
control. For these reasons, EASA AD No. 2013-0176 requires a one-time
inspection of the affected SEMA attachment hardware to detect improper
connection and play and, depending on the findings, replacement of the
affected hardware.
Since the issuance of EASA AD No. 2013-0176, Eurocopter Deutschland
GmbH has changed its name to Airbus Helicopters Deutschland GmbH.
These helicopters have been approved by the aviation authority of
Germany and are approved for operation in the United States. Pursuant
to our bilateral agreement with Germany, EASA, its technical
representative, has notified us of the unsafe condition described in
its AD. We are proposing this AD because we evaluated all known
relevant information and determined that an unsafe condition is likely
to exist or develop on other products of the same type design.
Eurocopter reported in Alert Service Bulletins (ASBs) EC135-22A-
015, Revision 1, dated January 28, 2013, and MBB BK117 C-2-22A-009,
Revision 1, dated August 3, 2009, that it was discovered during the
installation work on a helicopter that it was not possible to establish
attachment hardware on a threaded blind borehole between the SEMA and
the control rod without play. The ASBs state that ``unfavourable adding
of the tolerances'' of the individual attachment hardware elements
caused the screw to push against the bottom of the threaded blind
borehole on the SEMA, preventing any clamping force on the screw head.
The ASBs call for inspecting the SEMA attachment hardware connected to
[[Page 48708]]
respective control rods for play and making the proper adjustments to
eliminate any play.
This proposed AD would require, within 50 hours time-in-service,
inspecting whether the washers can be moved in the attachment hardware
that connects the SEMA and the control rod of the longitudinal,
lateral, and yaw actuators. For Model MBB BK117 C-2 helicopters, this
inspection is only for the hardware connecting the Yaw-SEMA and the
Yaw-SEMA control rod. If none of the washers can be moved, then no
further action is needed. If a washer can be moved, then this proposed
AD would require replacing the four screws, installing two additional
washers, and torque-tightening the screws to 5-6 Nm.
The EASA AD applies to Eurocopter Model EC635P2+, EC635T1 and
EC635T2+ helicopters. The proposed AD does not apply to these model
helicopters because they have no FAA type certificate.
We estimate that this proposed AD would affect 385 helicopters of
U.S. Registry and that labor costs average $85 per work-hour. Based on
these estimates, we expect the following costs:
Inspecting for movement of the washers would require 1.5
work hours for a labor cost of $128 per helicopter and $49,280 for the
Replacing the screws and related work would require an
additional 0.5 work-hours for a labor cost of $43. Screws would cost $4
each while washers would cost $10 each. We estimate the cost would be
$79 per repair.
finds necessary for safety in air commerce. This proposed 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.
3. Will not affect intrastate aviation in Alaska to the extent that
it justifies making a regulatory distinction; and
with this proposed AD and placed it in the AD docket.
Airbus Helicopters Deutschland GmbH (Previously Eurocopter
Deutschland GmbH) (Airbus Helicopters) Helicopters: Docket No. FAA-
2014-0577; Directorate Identifier 2013-SW-042-AD.
This AD applies to Airbus Helicopters Model EC135P1, EC135T1,
EC135P2, EC135T2, EC135P2+, EC135T2+, and MBB-BK 117 C-2
This AD defines the unsafe condition as loose attachment
hardware between the Smart Electro Mechanical Actuator (SEMA) and a
control rod. This condition could result in loss of the control axis
We must receive comments by October 17, 2014.
(1) Within 50 hours time in service (TIS), for Model EC135P1,
EC135T1, EC135P2, EC135T2, EC135P2+, and EC135T2+ helicopters, do
(i) Using Figure 1 and Figure 2 of Eurocopter Alert Service
Bulletin EC135-22A-015, Revision 1, dated January 28, 2013 (ASB
EC135-22A-015) as reference, inspect the attachment hardware between
the SEMA and the longitudinal actuator control rod to determine
whether any of the washers can be moved.
(A) If no washer can be moved, no further action is needed.
(B) If a washer can be moved, replace the four screws and
install two additional washers, part number (P/N) EN2139-05016, to
connect the SEMA with the control rod. Torque-tighten each screw to
5-6 Nm.
(ii) Using Figure 1 and Figure 2 of ASB EC135-22A-015 as
reference, inspect the attachment hardware between the SEMA and the
lateral actuator control rod to determine whether any of the washers
install two additional washers, P/N EN2139-05016, to connect the
SEMA with the control rod. Torque-tighten each screw to 5-6 Nm.
(iii) Using Figure 1, Figure 3, and Figure 4 of ASB EC135-22A-
015 as reference, inspect the attachment hardware between the SEMA
and the yaw actuator control rod to determine whether any of the
washers can be moved.
(2) Within 50 hours TIS, for Model MBB BK117 C-2 helicopters,
using Figure 1 of Eurocopter Alert Service Bulletin MBB BK117 C-2-
22A-009, Revision 1, dated August 3, 2009, as reference, inspect the
attachment hardware between the Yaw-SEMA and the Yaw-SEMA control
rod to determine whether any of the washers can be moved.
(i) If no washer can be moved, no further action is needed.
(ii) If a washer can be moved, replace the four screws and
install two additional
[[Page 48709]]
washers, P/N EN2139-05016, to connect the SEMA with the control rod.
Torque-tighten each screw to 5-6 Nm and apply polyurethane lacquer
onto the attachment hardware.
(1) The Manager, Safety Management Group, FAA, may approve AMOCs
for this AD. Send your proposal to: Matt Wilbanks, Aviation Safety
2601 Meacham Blvd., Fort Worth, Texas 76137; telephone (817) 222-
5110; email matt.wilbanks@faa.gov.
The subject of this AD is addressed in the European Aviation
Safety Agency (EASA) AD No. 2013-0176, dated August 7, 2013. You may
view the EASA AD on the Internet at http://www.regulations.gov in
Docket No. FAA-2014-0577.
Joint Aircraft Service Component (JASC) Code: 2213, Flight
Issued in Fort Worth, Texas, on August 8, 2014.
Acting Directorate Manager, Rotorcraft Directorate, Aircraft
[FR Doc. 2014-19524 Filed 8-15-14; 8:45 am]