UNITED STATES ENVIRONMENTAL PROTECTION AGENCY

WASHINGTON, D.C.  20460

	OFFICE OF PREVENTION, PESTICIDE

	AND TOXIC SUBSTANCES

  SEQ CHAPTER \h \r 1 MEMORANDUM

Date:  03-MAR-2010

SUBJECT:	Difenoconazole.  The Need for Additional Independent Laboratory
Validation (ILV) Information for the Livestock Enforcement Method REM
147.07.

PC Code:  128847	DP Barcodes:  D374898

Decision Nos.:  403560	Registration Nos.:	NA

Petition Nos.:  PP#8F7482 and PP#6F7115	Regulatory Action:	NA

Risk Assessment Type:  NA	Case No.: NA

TXR No.:  NA	CAS No.:  119446-68-3

MRID No.:  None	40 CFR:  180.475

	Ver.Apr.08

FROM:	Bonnie Cropp-Kohlligian, Environmental Scientist

		Risk Assessment Branch 4

		Health Effects Division (7509P)  SEQ CHAPTER \h \r 1

THROUGH:	Susan V. Hummel, Chemist/Senior Scientist

		Risk Assessment Branch 4

		Health Effects Division (7509P)

TO:		Rosemary Kearns/Tony Kish (RM 22)

		Fungicide Branch

		Registration Division (7505P)

Executive Summary

In previous residue chemistry reviews (DP# 340379, 8/9/07, W. Wassell
and M. Sahafeyan and, most recently, DP#361054 and DP#362648, 9/17/09,
B. Cropp-Kohlligian), HED has required additional information concerning
the ILV study (MRID 46950221) conducted for the livestock enforcement
method REM 147.07.  HED has concluded that this information is not
needed based on the method validation conducted by the Analytical
Chemistry Branch (ACB memo from C. Stafford, ACB Project # B07-26, dated
10/29/07) which found that the ILV study data submitted for method REM
147.07 (MRID 46950221) are acceptable and indicate that the method
performance is reproducible.  No additional information concerning the
ILV study (MRID 46950221) for the livestock enforcement method, REM
147.07, is required.

References

DP#:	340379

Subject:	PP#6F7115; Difenoconazole.  Petition for Establishment of
Tolerances on Fruiting Vegetables, Pome Fruit, Sugar Beets, Tuberous and
Corm Vegetables, and Imported Papaya.  Summary of Analytical Chemistry
and Residue Data.

From:	W. Wassell/M. Sahafeyan

To:	D. Rosenblatt/S. Brothers

Dated:	8/9/07

MRIDs:	46950215-46950237

DP#:	None (ACB memo)

Subject:	  SEQ CHAPTER \h \r 1 Review of Proposed Tolerance Enforcement
Method for Difenoconazole.  ACB Project # B07-26.

From:	C. Stafford

To:	D. Vogel

Dated:	10/29/07

MRIDs:	46950219-46950221

  SEQ CHAPTER \h \r 1 DP#s:		D361054 and D362648

Subject:	PP#8F7482; Difenoconazole.  Application for Amended Section 3
Registration to Add Uses on Bulb Vegetables, Brassica Leafy Vegetables,
Cucurbit Vegetables, Citrus Fruits, Grapes, Pistachios, and Tree Nuts.
Submission of Residue Analytical Methods Data in Response to DP#340379.
Summary of Analytical Chemistry and Residue Data.

From:		B. Cropp-Kohlligian

To:		R. Kearns/T. Kish

Dated:		17-SEP-2009

MRIDs:	47648604 and 47648605 and 47586101-47586107

Page   PAGE  1  of   NUMPAGES  2


[Federal Register Volume 79, Number 162 (Thursday, August 21, 2014)]
[Rules and Regulations]
[Pages 49445-49449]
[FR Doc No: 2014-19525]

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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2014-0034; Directorate Identifier 2013-SW-006-AD;
Amendment 39-17948; AD 2014-16-24]
RIN 2120-AA64

Airworthiness Directives; Airbus Helicopters Deutschland GmbH
(Previously Eurocopter Deutschland GbmH) (Airbus Helicopters)
Helicopters

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Final rule.

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

SUMMARY: We are superseding Airworthiness Directive (AD) 2012-10-53 for
Eurocopter Deutschland GmbH (ECD) (now Airbus Helicopters) Model
EC135P1, EC135P2, EC135P2+, EC135T1, EC135T2, and EC135T2+ helicopters.
AD 2012-10-53 required, before further flight and at specified
intervals, checking and inspecting the upper and lower main rotor hub
(MRH) shaft flanges for a crack, and inspecting the lower hub-shaft
flange bolt attachment areas for a crack. Since we issued AD 2012-10-
53, it has been determined that it is safe to increase the visual
inspection intervals of the MRH shaft flanges from 10 hours time-in-
service (TIS) to 50 hours TIS and remove the inspection of the lower
MRH shaft flange bolt attachment areas. This new AD continues to
require checking and inspecting the upper and lower MRH shaft flanges
for a crack. These actions are intended to detect a crack on the MRH
shaft flange, which if not corrected, could result in failure of the
MRH and subsequent loss of control of the helicopter.

DATES: This AD is effective September 25, 2014.
    The Director of the Federal Register approved the incorporation by
reference of a certain publication listed in this AD as of September
25, 2014.

ADDRESSES: For service information identified in this AD, contact
Airbus Helicopters, Inc., 2701 N. Forum Drive, Grand Prairie, Texas
75052; telephone<PHONE_NUMBER> or<PHONE_NUMBER>; fax<PHONE_NUMBER>;
or at http://www.airbushelicopters.com/techpub. You may view this
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 at http://www.regulations.gov by searching for and locating Docket No. FAA-2014-
0034; or in person at the Docket Management Facility between 9 a.m. and
5 p.m., Monday through Friday, except Federal holidays. The AD docket
contains this AD, the European Aviation Safety Agency (EASA) AD, any
incorporated-by-reference information, the economic evaluation, any
comments received, and other information. The address for the Docket
Office (phone:<PHONE_NUMBER>) is Document Management Facility, U.S.
Department of Transportation, Docket Operations, M-30, West Building
Ground Floor, Room W12-140, 1200 New Jersey Avenue SE., Washington, DC
20590.

FOR FURTHER INFORMATION CONTACT: Gary Roach, Aviation Safety Engineer,
Regulations and Policy Group, Rotorcraft Directorate, FAA, 2601 Meacham
Blvd., Fort Worth, Texas 76137; telephone<PHONE_NUMBER>; email
<EMAIL_ADDRESS>
SUPPLEMENTARY INFORMATION:

Discussion

    On May 18, 2012, we issued Emergency AD 2012-10-53, which
superseded Emergency AD 2012-10-51. Emergency AD 2012-10-53 was
published in the Federal Register as a Final rule; request for comments
on November 20, 2012, at 77 FR 69558. AD 2012-10-53 required a
repetitive pilot check of the lower MRH shaft flange for a crack, a
repetitive inspection of the upper and lower MRH shaft flanges and bolt
attachment areas for a crack, and replacing the MRH shaft if there is a
crack. AD 2012-10-53 was prompted by three reported incidents of
cracking on the lower hub-shaft flanges of EC135 model helicopters.
    After we issued AD 2012-10-53, Eurocopter revised Alert Service
Bulletin (ASB) No. EC135-62A-029, now at Revision 7, dated October 22,
2012, which contains the procedures for the repetitive pilot checks and
inspections. The inspection interval for the visual inspection of the
MRH shaft flanges was increased to 50 flight hours based on results
from full scale component testing. The note regarding the preflight
check states that the time between two preflight checks must not exceed
6 flight hours, and clarifies that one flight may comprise of multiple
take-offs and landings and a flight starts when the helicopter takes
off and ends when the helicopter is on the ground with the engines shut
off. Eurocopter also removed the visual inspection of

the blade bolt attachment areas from the ASB.
    EASA also revised its AD, now at EASA AD 2012-0085R5, dated October
30, 2012, to correct this unsafe condition. EASA advises that based on
results of the further full scale component testing, it has been
determined that the interval for the repetitive visual inspections of
the upper and lower hub shaft flanges can be extended to 50 flight
hours. EASA AD No. 2012-0085R5 also references ECD ASB No. EC135-62A-
029, Revision 7, dated October 22, 2012, for related information. EASA
considers AD 2012-0085R5 to be interim AD action and further AD action
may follow.
    On January 16, 2014, we issued a notice of proposed rulemaking
(NPRM) to amend 14 CFR part 39 to supersede AD 2012-10-53. The NPRM
published in the Federal Register on January 31, 2014 (79 FR 5325). The
NPRM proposed to continue to require the repetitive visual pilot check
and inspection of the upper and lower MRH shaft flanges, as well as the
replacement requirements of AD 2012-10-53. An owner/operator (pilot)
may perform the required visual check and must enter compliance with
the applicable paragraph of the AD into the helicopter maintenance
records in accordance with 14 CFR 43.9(a)(1) through (4) and
91.417(a)(2)(v). A pilot may perform this check because it involves
only looking at the visible area of the MRH shaft flanges and can be
performed equally well by a pilot or a mechanic. This check is an
exception to our standard maintenance regulations. Further, the NPRM
proposed to increase the repetitive visual inspection interval for MRH
shafts with 400 hours or more TIS from 10 hours TIS to 50 hours TIS.
Any alternative method of compliance (AMOC) previously approved in
accordance with AD 2012-10-53 would continue to be considered approved
as an AMOC for the corresponding requirements in this AD.
    Since we issued the NPRM, Eurocopter Deutschland GmbH changed its
name to Airbus Helicopters Deutschland GmbH. This AD reflects that
change and updates the contact information to obtain service
documentation.

Comments

    We gave the public the opportunity to participate in developing
this AD, but we did not receive any comments on the NPRM (79 FR 5325,
January 31, 2014).

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
the EASA ADs. We are issuing this AD because we evaluated all
information provided by EASA and determined the unsafe condition exists
and is likely to exist or develop on other helicopters of these same
type designs and that air safety and the public interest require
adopting the AD requirements as proposed except for the name change
previously described and a minor editorial change to meet current
publishing requirements. The reference to ``the applicability of this
AD'' in paragraph (f)(3) of this AD has been changed to reference
``paragraph (a) of this AD.'' These changes are consistent with the
intent of the proposals in the NPRM (79 FR 5325, January 31, 2014) and
will not increase the economic burden on any operator.

Differences Between This AD and the EASA AD

    EASA considers its AD action to be an interim action; we do not
consider this AD to be an interim AD action because the requirements
for the applicable part-numbered MRH shafts are not expected to change.
The EASA AD requires you to report the findings and send the removed
MRH to ECD (now Airbus Helicopters), while this AD does not. The EASA
AD requires the initial visual check within 3 days, while this AD
requires the initial visual check before further flight. The EASA AD
does not specify affected MRH shaft part numbers; this AD does because
the FAA anticipates Airbus Helicopters will produce new part-numbered
MRH shafts without the same unsafe condition.

Related Service Information

    We reviewed Eurocopter ASB No. EC135-62A-029, Revision 7, dated
October 22, 2012, which describes procedures for preflight checking the
visible area of the upper and lower MRH shaft flanges and performing a
repetitive visual inspection of the upper and lower MRH shaft for
cracks. EASA classified this ASB as mandatory and issued AD No. 2012-
0085R5 to ensure the continued airworthiness of these helicopters.

Costs of Compliance

    We estimate that this AD affects 244 helicopters of U.S. Registry.
We estimate inspecting the MRH shaft flanges requires 2.5 work-hours at
an average labor rate of $85 per work-hour, for a total cost per
helicopter of $212 and a total cost to U.S. operators of $51,728 per
inspection cycle. Replacing an MRH shaft requires about 8 work-hours
and required parts cost $55,715, for a total cost per helicopter of
$56,395.

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 have determined that this AD will not have federalism
implications under Executive Order 13132. This AD will not have a
substantial direct effect on the States, on the relationship between
the national government and the States, or on the distribution of power
and responsibilities among the various levels of government.
    For the reasons discussed above, I certify that this AD:
    (1) Is not a ``significant regulatory action'' under Executive
Order 12866,
    (2) Is not a ``significant rule'' under DOT Regulatory Policies and
Procedures (44 FR 11034, February 26, 1979),
    (3) Will not affect intrastate aviation in Alaska to the extent
that it justifies making a regulatory distinction, and
    (4) Will not have a significant economic impact, positive or
negative, on a substantial number of small entities under the criteria
of the Regulatory Flexibility Act.

List of Subjects in 14 CFR Part 39

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

Adoption of the Amendment

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

PART 39--AIRWORTHINESS DIRECTIVES

0
1. The authority citation for part 39 continues to read as follows:

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

Sec.  39.13  [Amended]

0
2. The FAA amends Sec.  39.13 by removing Airworthiness Directive (AD)
2012-10-53 (77 FR 69558, November 20, 2012), and adding the following
new AD:

2014-16-24 Airbus Helicopters Deutschland GmbH (Previously
Eurocopter Deutschland GmbH) Helicopters: Amendment 39-17948; Docket
No. FAA-2014-0034; Directorate Identifier 2013-SW-006-AD.

(a) Applicability

    This AD applies to Model EC135P1, EC135P2, EC135P2+, EC135T1,
EC135T2, and EC135T2+ helicopters, with a main rotor hub (MRH)
shaft, part number (P/N) L623M1006101, L623M1206101, L623M1006102,
L623M1206102, L623M1006103, or L623M1206103 installed, certificated
in any category.

(b) Unsafe Condition

    This AD defines the unsafe condition as a crack in the MRH shaft
flange, which could result in failure of the MRH and subsequent loss
of control of the helicopter.

(c) Affected ADs

    This AD supersedes AD 2012-10-53, Amendment 39-17254 (77 FR
69558, November 20, 2012).

(d) Effective Date

    This AD becomes effective September 25, 2014.

(e) 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.

(f) Required Actions

    (1) Before further flight, and thereafter at intervals not to
exceed 6 hours time-in-service (TIS), check the MRH shaft lower
flange and the visible area of the MRH shaft upper flange for a
crack. Figures 1 and 2 to Paragraph (f)(1) of this AD are examples
of cracks that have been discovered in the MRH shaft lower flange.
The actions required by this paragraph may be performed by the
owner/operator (pilot) holding at least a private pilot certificate,
and must be entered into the aircraft records showing compliance
with this AD in accordance with 14 CFR 43.9 (a)(1) through (4) and
14 CFR 91.417(a)(2)(v). The record must be maintained as required by
14 CFR 91.417, 121.380, or 135.439.

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[GRAPHIC] [TIFF OMITTED] TR21AU14.003

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    (2) For MRH shafts with 400 or more hours TIS, within 50 hours
TIS, and thereafter at intervals not to exceed 50 hours TIS:
    (i) Remove the rotor-hub cap.
    (ii) Clean the upper and lower MRH shaft flange as depicted in
Figure 2 of Eurocopter Alert Service Bulletin No. EC135-62A-029,
Revision 7, dated October 22, 2012, and visually inspect for a
crack.
    (3) If there is a crack in the upper or lower MRH shaft flange,
before further flight, replace that MRH shaft with an airworthy MRH
shaft. Replacing the MRH shaft with an MRH shaft having a P/N listed
in paragraph (a) of this AD does not constitute terminating action
for the requirements of this AD.

(g) Alternative Methods of Compliance (AMOCs)

    (1) The Manager, Safety Management Group, FAA, may approve AMOCs
for this AD. Send your proposal to: Gary Roach,

Aviation Safety Engineer, Regulations and Policy Group, Rotorcraft
Directorate, FAA, 2601 Meacham Blvd., Fort Worth, Texas 76137;
telephone<PHONE_NUMBER>; email<EMAIL_ADDRESS>    (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.
    (3) Any AMOC approved previously in accordance with AD No. 2012-
10-53, Amendment 39-17254 (77 FR 69558, November 20, 2012), is
approved as an AMOC for the corresponding requirements in paragraph
(f) of this AD.

(h) Additional Information

    The subject of this AD is addressed in European Aviation Safety
Agency (EASA) AD No. 2012-0085R5, dated October 30, 2012. You may
view the EASA AD on the Internet at http://www.regulations.gov in
Docket No. FAA-2014-0034.

(i) Subject

    Joint Aircraft Service Component (JASC) Code: 6220, Main Rotor
Head.

(j) 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 No. EC135-62A-029,
Revision 7, dated October 22, 2012, excluding Figure 1.
    (ii) Reserved.
    (3) For Eurocopter service information identified in this AD,
contact Airbus Helicopters, Inc., 2701 N. Forum Drive, Grand
Prairie, Texas 75052; telephone<PHONE_NUMBER> or<PHONE_NUMBER>;
fax<PHONE_NUMBER>; or at http://www.airbushelicopters.com/techpub.
    (4) You may view this service information at FAA, Office of the
Regional Counsel, Southwest Region, 2601 Meacham Blvd., Room 663,
Fort Worth, Texas 76137. For information on the availability of this
material at the FAA, call<PHONE_NUMBER>.
    (5) You may view this service information that is incorporated
by reference at the National Archives and Records Administration
(NARA). For information on the availability of this material at
NARA, call<PHONE_NUMBER>, or go to: http://www.archives.gov/federal-register/cfr/ibr-locations.html.

    Issued in Fort Worth, Texas, on August 8, 2014.
Lance T. Gant,
Acting Directorate Manager, Rotorcraft Directorate, Aircraft
Certification Service.
[FR Doc. 2014-19525 Filed 8-20-14; 8:45 am]
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