[Federal Register Volume 76, Number 214 (Friday, November 4, 2011)]
[Rules and Regulations]
[Pages 68299-68301]
[FR Doc No: 2011-27776]

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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2011-1075; Directorate Identifier 2011-SW-011-AD;
Amendment 39-16836; AD 2011-21-13]
RIN 2120-AA64

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

AGENCY: Federal Aviation Administration, DOT.

ACTION: Final rule; request for comments.

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SUMMARY: This amendment adopts a new airworthiness directive (AD) for
ECD Model MBB-BK 117 C-2 helicopters. This action requires revising the
Rotorcraft Flight Manual (RFM) by inserting certain temporary pages
into the Emergency and Performance Data sections of the RFM to alert
the operators to monitor the power display when a generator is
deactivated and provides appropriate actions. This amendment is
prompted by reports of too high a current flow when one generator is
deactivated. The actions specified in this AD are intended to prevent
failure of the remaining generator when one generator is deactivated,
loss of electrical power, loss of systems necessary for flight safety,
and subsequent loss of control of the helicopter.

DATES: Effective November 21, 2011.
    The incorporation by reference of certain publications listed in
the regulations is approved by the Director of the Federal Register as
of November 21, 2011.
    Comments for inclusion in the Rules Docket must be received on or
before January 3, 2012.

ADDRESSES: Use one of the following addresses to submit comments on
this AD:
     Federal eRulemaking Portal: Go to http://www.regulations.gov. Follow the instructions for submitting comments.
     Fax:<PHONE_NUMBER>.
     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 AD from
American Eurocopter Corporation, 2701 Forum Drive, Grand Prairie, TX
75053-4005, telephone<PHONE_NUMBER>, fax<PHONE_NUMBER>, or at http://www.eurocopter.com.
    Examining the Docket: You may examine the docket that contains the
AD, any comments, and other information 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 Docket Operations office (telephone<PHONE_NUMBER>) 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.

FOR FURTHER INFORMATION CONTACT: George Schwab, Aviation Safety
Engineer, FAA, Rotorcraft Directorate, Safety Management Group, 2601
Meacham Blvd., Fort Worth, Texas 76137, telephone<PHONE_NUMBER>, fax
(817) 222-5961.

SUPPLEMENTARY INFORMATION:

Discussion

    The European Aviation Safety Agency (EASA), which is the Technical
Agent for the Member States of the European Union, has issued EASA AD
No. 2010-0268-E, dated December 21, 2010, to correct an unsafe
condition for the ECD Model MBB-BK 117 C-2 helicopters. EASA advises of
reports that on some helicopters a too high current flow was detected
when one generator was deactivated (for example, during the ENGINE
POWER CHECK). EASA also advises that 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. Therefore, the EASA AD requires additional
RFM procedures to include visual monitoring of the electrical power
display during switching of a generator. Also, EASA advises that their
AD is an interim measure pending the development of a final solution
that will prevent this particular mode of generator failure.

Related Service Information

    ECD has issued Alert Service Bulletin ASB MBB BK117 C-2-24A-008,
dated December 20, 2010 (ASB). The ASB specifies inserting certain
pages from the ASB into the RFM to alert operators to visually monitor
the power display generator amperes (GEN AMPS) on the Vehicle and
Engine Multifunction

Display (VEMD) for too high a current flow when a generator has been
deactivated; for example, during the ENGINE POWER CHECK. In such a
situation, the revised RFM provides instructions for switching off the
two main electrical buses (BUS TIEs) on the overhead panel to prevent
the operating generator from being damaged. The ASB states that failure
of the generator could result in subsequent loss of electrical power
and loss of systems. EASA classified this ASB as mandatory and issued
AD No. 2010-0268-E, dated December 21, 2010, to ensure the continued
airworthiness of these helicopters.

FAA's Evaluation and Unsafe Condition Determination

    These helicopters have been approved by the aviation authority of
the Federal Republic of Germany and are approved for operation in the
United States. Pursuant to our bilateral agreement with the Federal
Republic of Germany, 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 exists and is likely to exist or
develop on other helicopters of this same type design.

FAA's Determination and Requirements of This AD

    This unsafe condition is likely to exist or develop on other
helicopters of the same type design. This amendment adopts a new AD for
ECD Model MBB-BK 117 C-2 helicopters. This action requires revising the
Emergency Procedures and Performance Data sections of the RFM BK117 C-2
by copying or cutting out the temporary pages 7, 8, and 11 of the ASB
and inserting the pages into RFM BK 117 C-2. This amendment is prompted
by reports of too high a current flow when one generator is
deactivated. The actions specified in this AD are intended to revise
the RFM by inserting temporary pages into the Emergency Procedures and
Performance Data sections. The revisions to the RFM are intended to
alert pilots to visually monitor the power display GEN AMPS on the VEMD
when a generator is deactivated to detect too high a current flow and
to switch off the two BUS TIEs on the overhead panel to prevent the
operating generator from being damaged. Accomplish the actions by
copying or cutting out pages 7, 8, and 11 of the ASB described
previously and inserting them into the Emergency Procedures and
Performance Data sections of the RFM.
    The short compliance time involved is required because the
previously described critical unsafe condition can adversely affect the
controllability or structural integrity of the helicopter. Therefore,
revising the Emergency and Performance Data sections of the RFM is
required before further flight, and this AD must be issued immediately.
    Since a situation exists that requires the immediate adoption of
this regulation, it is found that notice and opportunity for prior
public comment hereon are impracticable, and that good cause exists for
making this amendment effective in less than 30 days.

Costs of Compliance

    We estimate that this AD will affect about 232 helicopters of U.S.
registry. We also estimate that it will take a minimal amount of time
to copy and insert the pages into the RFM. Therefore, the cost of the
AD will be minimal.

Comments Invited

    This AD is a final rule that involves requirements that affect
flight safety and was not preceded by notice and an opportunity for
public comment; however, we invite you to submit any written data,
views, or arguments regarding this AD. Send your comments to an address
listed under ADDRESSES. Include ``Docket No. FAA-2011-1075; Directorate
Identifier 2011-SW-011-AD'' at the beginning of your comments. We
specifically invite comments on the overall regulatory, economic,
environmental, and energy aspects of the AD. We will consider all
comments received by the closing date and may amend the AD in light of
those comments.
    We will post all comments we receive, without change, to http://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 AD. 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 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).

Regulatory Findings

    We have determined that this AD will not have federalism
implications under Executive Order 13132. This AD will not have a
substantial direct effect on the States, on the relationship between
the national Government and the States, or on the distribution of power
and responsibilities among the various levels of government.
    For the reasons discussed above, I certify that the regulation:
    1. Is not a ``significant regulatory action'' under Executive Order
12866;
    2. Is not a ``significant rule'' under the DOT Regulatory Policies
and Procedures (44 FR 11034, February 26, 1979);
    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.

Authority for This Rulemaking

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

List of Subjects in 14 CFR Part 39

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

Adoption of the Amendment

    Accordingly, pursuant to the authority delegated to me by the
Administrator, the Federal Aviation Administration amends part 39 of
the Federal Aviation Regulations (14 CFR part 39) as follows:

PART 39--AIRWORTHINESS DIRECTIVES

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

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

Sec.  39.13  [Amended]

0
2. Section 39.13 is amended by adding a new airworthiness directive to
read as follows:

2011-21-13 EUROCOPTER DEUTSCHLAND GmbH (ECD):

Amendment 39-16836; Docket No. FAA-2011-1075; Directorate Identifier
2011-SW-011-AD.

    Applicability: Model MBB-BK 117 C-2 helicopters, certificated in
any category.
    Compliance: Before further flight, unless accomplished
previously.
    To prevent failure of a generator, loss of electrical power,
loss of systems necessary for flight safety, and subsequent loss of
control of the helicopter, do the following:
    (a) Revise the ``Emergency and Malfunction Procedures'' and the
``Performance Data'' sections of the Rotorcraft Flight Manual (RFM)
BK117 C-2 by copying or cutting out temporary pages 7, 8, and 11
(RFM pages 3-3 and 3-3a for ``Emergency and Malfunction Procedures''
and page 5-7 for ``Performance Data'') of ECD Alert Service Bulletin
No. ASB MBB BK117 C-2-24A-008, dated December 20, 2010, and
inserting the pages into RFM BK 117 C-2.
    (b) To request a different method of compliance or a different
compliance time for this AD, follow the procedures in 14 CFR 39.19.
Contact the Manager, Safety Management Group, ATTN: George Schwab,
Aviation Safety Engineer, FAA, Rotorcraft Directorate, 2601 Meacham
Blvd., Fort Worth, Texas 76137, telephone<PHONE_NUMBER>, fax (817)
222-5961, for information about previously approved alternative
methods of compliance.
    (c) The Joint Aircraft System/Component (JASC) Code is 2435:
Starter-Generator, 2437: DC Indicating System, and 2430: DC
Generator System.
    (d) Revise the Emergency Procedures and Performance Data
sections of RFM BK 117 C-2 by inserting the specified portions of
ECD Alert Service Bulletin No. ASB MBB BK117 C-2-24A-008, dated
December 20, 2010, into the RFM. The Director of the Federal
Register approved this incorporation by reference in accordance with
5 U.S.C. 552(a) and 1 CFR part 51. Copies may be obtained from
American Eurocopter Corporation, 2701 Forum Drive, Grand Prairie, TX
75053-4005, telephone<PHONE_NUMBER>, fax<PHONE_NUMBER>, or at
http://www.eurocopter.com. Copies may be inspected at the FAA,
Office of the Regional Counsel, Southwest Region, 2601 Meacham
Blvd., Room 663, Fort Worth, Texas, or at the National Archives and
Records Administration (NARA). For information on the availability
of this material at NARA, call<PHONE_NUMBER>, or go to: http://www.archives.gov/federal_register/code_of_federal_regulations/ibr_locations.html.
    (e) This amendment becomes effective on November 21, 2011.

    Note: The subject of this AD is addressed in The European
Aviation Safety Agency (the Federal Republic of Germany) AD No.
2010-0268-E, dated December 21, 2010.

    Issued in Fort Worth, Texas, on September 29, 2011.
Kim Smith,
Manager, Rotorcraft Directorate, Aircraft Certification Service.
[FR Doc. 2011-27776 Filed 11-3-11; 8:45 am]
BILLING CODE 4910-13-P


[Federal Register Volume 75, Number 241 (Thursday, December 16, 2010)]
[Rules and Regulations]
[Pages 78596-78599]
[FR Doc No: 2010-31438]

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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2010-1242; Directorate Identifier 2010-CE-062-AD;
Amendment 39-16542; AD 2010-26-03]
RIN 2120-AA64

Airworthiness Directives; Hawker Beechcraft Corporation Models
B200, B200GT, B300, and B300C Airplanes

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Final rule; request for comments.

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

SUMMARY: We are superseding an existing airworthiness directive (AD)
for the products listed above. That AD currently requires fabricating
and installing a placard incorporating information that limits
operation when there is known or forecast icing and requires replacing
a section of the pneumatic supply tube for the tail deice system with a
new tube of a different material. This AD requires fabricating and
installing a placard incorporating information that limits operation
when there is known or forecast icing and requires replacing the entire
length of the pneumatic supply tube for the tail deice system with a
new tube of a different material. This AD was prompted by reports of
two failures of the pneumatic supply tube for the tail deice system
outside the area covered by AD 2008-07-10. We are issuing this AD to
prevent collapsed pneumatic supply tubes, which could result in failure
of the tail deice boots to operate. This failure could lead to loss of
control in icing conditions.

DATES: This AD is effective December 20, 2010.
    The Director of the Federal Register approved the incorporation by
reference of a certain publication listed in the AD as of December 20,
2010.
    We must receive any comments on this AD by January 31, 2011.

ADDRESSES: You may send comments by any of the following methods:
     Federal eRulemaking Portal: Go to http://www.regulations.gov. Follow the instructions for submitting comments.
     Fax:<PHONE_NUMBER>.
     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.
    For service information identified in this AD, contact Hawker
Beechcraft Corporation, P.O. Box 85, Wichita, Kansas 67201-0085;
telephone:<PHONE_NUMBER> or<PHONE_NUMBER>; Internet:
www.hawkerbeechcraft.com. You may review copies of the referenced
service information at the FAA, Small Airplane Directorate, 901 Locust
St., Kansas City, MO 64106. For information on the availability of this
material at the FAA, call<PHONE_NUMBER>.

Examining the AD Docket

    You may examine the AD docket on the Internet at http://www.regulations.gov; 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 regulatory evaluation,
any comments received, and other information. The street address for
the Docket Office (phone:<PHONE_NUMBER>) is in the ADDRESSES section.
Comments will be available in the AD docket shortly after receipt.

FOR FURTHER INFORMATION CONTACT: Don Ristow, Aerospace Engineer,
Wichita Aircraft Certification Office, 1801 Airport Road, Room 100,
Wichita, Kansas 67209; telephone:<PHONE_NUMBER>; fax:<PHONE_NUMBER>;
e-mail<EMAIL_ADDRESS>
SUPPLEMENTARY INFORMATION:

Discussion

    On March 27, 2008, we issued AD 2008-07-10, Amendment 39-15451 (73
FR 18706, April 7, 2008), for certain Hawker Beechcraft Corporation
Models B200, B200GT, B300, and B300C airplanes. That AD requires
fabricating and installing a placard incorporating

information that limits operation when there is known or forecast icing
and requires replacing a section of the pneumatic supply tube for the
tail deice system with a new tube of a different material. That AD
resulted from reports of collapsed tail deice boot pneumatic supply
tubes. We issued that AD to prevent collapsed pneumatic supply tubes,
which could result in failure of the tail deice boots to operate. This
failure could lead to loss of control in icing conditions.

Actions Since AD Was Issued

    Since we issued AD 2008-07-10, we received reports of two failures
of the pneumatic supply tube for the tail deice system outside the area
covered by AD 2008-07-10 on an affected Model B300 airplane and on an
affected Model B300C airplane.

Relevant Service Information

    We reviewed Hawker Beechcraft Mandatory Service Bulletin SB 30-
3889, Rev. 1, dated October 2010. The service information describes
procedures for replacing the entire length of the pneumatic supply tube
for the tail deice system with a new tube of a different material.

FAA's Determination

    We are issuing this AD because we evaluated all the relevant
information and determined the unsafe condition described previously is
likely to exist or develop in other products of the same type design.

AD Requirements

    This AD requires accomplishing the actions specified in the service
information described previously.

FAA's Justification and Determination of the Effective Date

    An unsafe condition exists that requires the immediate adoption of
this AD. The FAA has found that the risk to the flying public justifies
waiving notice and comment prior to adoption of this rule because this
condition could result in failure of the tail deice boots to operate.
This failure could lead to loss of control in icing conditions.
Therefore, we find that notice and opportunity for prior public comment
are impracticable and that good cause exists for making this amendment
effective in less than 30 days.

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 before it becomes effective. However, we invite
you to send any written data, views, or arguments about this AD. Send
your comments to an address listed under the ADDRESSES section. Include
the docket number FAA-2010-1242 and directorate identifier 2010-CE-062-
AD at the beginning of your comments. We specifically invite comments
on the overall regulatory, economic, environmental, and energy aspects
of this AD. We will consider all comments received by the closing date
and may amend this AD because of those comments.
    We will post all comments we receive, without change, to http://www.regulations.gov, including any personal information you provide. We
will also post a report summarizing each substantive verbal contact we
receive about this AD.

Costs of Compliance

    We estimate that this AD affects 90 airplanes of U.S. registry.
    We estimate the following costs to comply with this AD:

                                                 Estimated Costs
----------------------------------------------------------------------------------------------------------------
                                                                                Cost per      Cost on U.S.
              Action                      Labor Cost             Parts cost           product        operators
----------------------------------------------------------------------------------------------------------------
Fabricate placard (retained action  1 work-hour x $85 per  Not applicable.......             $85          $7,650
 from AD 2008-07-10).                hour = $85.
Replace entire length of the        15 work-hours x $85    $100.................          $1,375        $123,750
 pneumatic supply tube for the       per hour = $1,275.
 tail de-ice system.
----------------------------------------------------------------------------------------------------------------

    According to the manufacturer, some of the costs of this AD may be
covered under warranty, thereby reducing the cost impact on affected
individuals. We do not control warranty coverage for affected
individuals. As a result, we have included all costs in our cost
estimate.

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

    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, 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

0
Accordingly, under the authority delegated to me by the Administrator,
the FAA amends part 39 of the Federal Aviation Regulations (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)
2008-07-10, Amendment 39-15451 (73 FR 18706, April 7, 2008) and adding
the following new AD:

2010-26-03 Hawker Beechcraft Corporation: Amendment 39-16542; Docket
No. FAA-2010-1242; Directorate Identifier 2010-CE-062-AD.

Effective Date

    (a) This AD is effective December 20, 2010.

Affected ADs

    (b) This supersedes AD 2008-07-10; Amendment 39-15451.

Applicability

    (c) This AD applies to the following Hawker Beechcraft
Corporation airplanes that are certificated in any category:

          Table 1--Affected Airplane Models and Serial Numbers
------------------------------------------------------------------------
                 Model                           Serial numbers
------------------------------------------------------------------------
B200..................................  BB-1926, BB-1978, and BB-1988
                                         through BB-2000.
B200GT................................  BY-1 through BY-26.
B300..................................  FL-427, FL-493, and FL-500
                                         through FL-573.
B300C (C-12W).........................  FM-14 through FM-18.
------------------------------------------------------------------------

Subject

    (d) Joint Aircraft System Component (JASC)/Air Transport
Association (ATA) of America Code 30, Ice and Rain Protection.

Unsafe Condition

    (e) This AD was prompted by reports of failures of the pneumatic
supply tube for the tail deice system outside the area covered by AD
2008-07-10. We are issuing this AD to prevent collapsed pneumatic
supply tubes, which could result in failure of the tail deice boots
to operate. This failure could lead to loss of control in icing
conditions.

Compliance

    (f) Comply with this AD within the compliance times specified,
unless already done.

                    Table 2--Requirements of This AD
------------------------------------------------------------------------
           Actions                 Compliance            Procedures
------------------------------------------------------------------------
(1) Fabricate a placard       Before further        Not applicable.
 (using at least 1/            flight in known or
 8[dash]inch letters) with     forecast icing
 the following words and       conditions or
 install the placard on the    within the next 3
 instrument panel within the   days after December
 pilot's clear view: ``THIS    20, 2010 (the
 AIRPLANE IS PROHIBITED FROM   effective of this
 FLIGHT IN KNOWN OR FORECAST   AD), whichever
 ICING.''                      occurs first.
(2) For Model B200 and Model  Before further        Follow the
 B200GT airplanes: Replace     flight in known or    Accomplishment
 the pneumatic supply tubing   forecast icing        Instructions in
 from the rear spar at         conditions, within    Hawker Beechcraft
 Fuselage Station (FS)         25 hours time-in-     Mandatory Service
 227.00 to the aft pressure    service (TIS) after   Bulletin SB 30-
 bulkhead at FS 347.750 with   December 20, 2010     3889, Rev 1, dated
 Hytrel tubing part number     (the effective date   October 2010.
 (P/N) 131823VH10D-1210; and   of this AD), or
 for Model B300 and Model      within 3 months
 B300C airplanes: Replace      after December 20,
 pneumatic supply tubing       2010 (the effective
 from the rear spar at FS      date of this AD),
 241.40 to the aft pressure    whichever occurs
 bulkhead at FS 381.750 with   first.
 Hytrel tubing P/N
 131823VH10D-1406. The
 replacement of tail deice
 boot pneumatic supply tubes
 required by paragraph
 (f)(2) of this AD is
 terminating action for the
 placard required by
 paragraph (f)(1) of this AD.
(3) Remove the placard        Before further        Not applicable.
 required by paragraph         flight after the
 (f)(1) of this AD.            replacement of tail
                               deice boot
                               pneumatic supply
                               tubes required by
                               paragraph (f)(2) of
                               this AD.
------------------------------------------------------------------------

Credit for Actions Accomplished in Accordance With Previous Service
Information

    (g) If Hawker Beechcraft Mandatory Service Bulletin SB 30-3889,
Issued: March 2008, has already been complied with, you may splice
new Hytrel tubing on the existing Hytrel tubing in the aft
evaporator bay area before further flight in known or forecast icing
conditions, within 25 hours TIS after December 20, 2010 (the
effective date of this AD), or within 3 months after December 20,
2010 (the effective date of this AD), whichever occurs first.

Alternative Methods of Compliance (AMOCs)

    (h)(1) The Manager, Wichita Aircraft Certification Office (ACO),
FAA, has the authority to approve AMOCs for this AD, if requested
using the procedures found in 14 CFR 39.19. 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 manager of the ACO, send it to the
attention of the person identified in the Related Information
section of this AD.
    (2) Before using any approved AMOC, notify your Principal
Maintenance Inspector or Principal Avionics Inspector, as
appropriate, or lacking a principal inspector, your local Flight
Standards District Office.

Related Information

    (i) For more information about this AD, contact Don Ristow,
Aerospace Engineer, Wichita ACO, 1801 Airport Road, Room 100,
Wichita, Kansas 67209; telephone:<PHONE_NUMBER>; fax: (316) 946-
4107; email<EMAIL_ADDRESS>
Material Incorporated by Reference

    (j) You must use Hawker Beechcraft Mandatory Service Bulletin SB
30-3889, Rev. 1, dated October 2010, to do the actions required by
this AD, unless the AD specifies otherwise.
    (1) The Director of the Federal Register approved the
incorporation by reference of this service information under 5
U.S.C. 552(a) and 1 CFR part 51.
    (2) For service information identified in this AD, contact
Hawker Beechcraft Corporation, P.O. Box 85, Wichita, Kansas 67201-
0085; telephone:<PHONE_NUMBER> or<PHONE_NUMBER>; Internet: http://www.hawkerbeechcraft.com.
    (3) You may review copies of the service information at the FAA,
Small Airplane Directorate, 901 Locust St., Kansas City, MO 64106.
For information on the availability of this material at the FAA,
call<PHONE_NUMBER>.

    (4) 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<PHONE_NUMBER>, or go to http://www.archives.gov/federal_register/code_of_federal_regulations/ibr_locations.html.

    Issued in Kansas City, Missouri, on December 9, 2010.
John Colomy,
Acting Manager, Small Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 2010-31438 Filed 12-15-10; 8:45 am]
BILLING CODE 4910-13-P


[Federal Register Volume 86, Number 74 (Tuesday, April 20, 2021)]
[Proposed Rules]
[Pages 20461-20465]
[FR Doc No: 2021-08053]

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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2021-0309; Project Identifier MCAI-2020-00918-T]
RIN 2120-AA64

Airworthiness Directives; MHI RJ Aviation ULC (Type Certificate
Previously Held by Bombardier, Inc.) Airplanes

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Notice of proposed rulemaking (NPRM).

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

SUMMARY: The FAA proposes to adopt a new airworthiness directive (AD)
for MHI RJ Aviation ULC Model CL-600-2C10 (Regional Jet Series 700, 701
& 702), CL-600-2C11 (Regional Jet Series 550), CL-600-2D15 (Regional
Jet Series 705), CL-600-2D24 (Regional Jet Series 900), and CL-600-2E25
(Regional Jet Series 1000) airplanes. This proposed AD was prompted by
reports and a design review indicating that there could be possible
corrosion on the main landing gear (MLG) outer cylinder at the
interface with the gland nut on the shock strut installation and on the
forward and aft trunnion pins in the MLG dressed shock strut assembly.
This proposed AD would require detailed inspections for corrosion on
the MLG outer cylinder assemblies, certain MLG dressed shock strut
assemblies, and the MLG outer cylinder at the gland nut threads, thread
relief groove, and chamfer; a detailed inspection for the presence of
corrosion-inhibiting compound (CIC) on the MLG forward and aft trunnion
pins and grease adapter assemblies; applicable corrective actions;
application of primer, paint, and CIC as applicable; re-identification
of certain part numbers; and marking of the MOD STATUS field of the
nameplate of certain parts. The FAA is proposing this AD to address the
unsafe condition on these products.

DATES: The FAA must receive comments on this proposed AD by June 4,
2021.

ADDRESSES: You may send comments, using the procedures found in 14 CFR
11.43 and 11.45, by any of the following methods:
     Federal eRulemaking Portal: Go to https://www.regulations.gov. Follow the instructions for submitting comments.
     Fax:<PHONE_NUMBER>.
     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: Deliver to Mail address above between 9
a.m. and 5 p.m., Monday through Friday, except Federal holidays.
    For Bombardier service information identified in this NPRM, contact
MHI RJ Aviation ULC, 12655 Henri-Fabre Blvd., Mirabel, Qu[eacute]bec
J7N 1E1 Canada; Widebody Customer Response Center North America toll-
free telephone +1-844-272-2720 or direct-dial telephone +1-514-855-
8500; fax +1-514-855-8501; email<EMAIL_ADDRESS>internet https://eservices.aero.bombardier.com.
    You may view this service information at the FAA, Airworthiness
Products Section, Operational Safety Branch, 2200 South 216th St., Des
Moines, WA. For information on the availability of this material at the
FAA, call<PHONE_NUMBER>.

Examining the AD Docket

    You may examine the AD docket on the internet at https://www.regulations.gov by searching for and locating Docket No. FAA-2021-
0309; or in person at Docket Operations between 9 a.m. and 5 p.m.,
Monday through Friday, except Federal holidays. The AD docket contains
this NPRM, any comments received, and other information. The street
address for Docket Operations is listed above.

FOR FURTHER INFORMATION CONTACT: Darren Gassetto, Aerospace Engineer,
Mechanical Systems and Administrative Services Section, FAA, New York
ACO Branch, 1600 Stewart Avenue, Suite 410, Westbury, NY 11590;
telephone<PHONE_NUMBER>; fax<PHONE_NUMBER>; email<EMAIL_ADDRESS>
SUPPLEMENTARY INFORMATION:

Comments Invited

    The FAA invites you to send any written relevant data, views, or
arguments about this proposal. Send your comments to an address listed
under ADDRESSES. Include ``Docket No. FAA-2021-0309; Project Identifier
MCAI-2020-00918-T'' at the beginning of your comments. The most helpful
comments reference a specific portion of the proposal, explain the
reason for any recommended change, and include supporting data. The FAA
will consider all comments received by the closing date and may amend
the proposal because of those comments.
    Except for Confidential Business Information (CBI) as described in
the following paragraph, and other information as described in 14 CFR
11.35, the FAA will post all comments received, without change, to
https://www.regulations.gov, including any personal information you
provide. The agency will also post a report summarizing each
substantive verbal contact received about this proposed AD.

Confidential Business Information

    CBI is commercial or financial information that is both customarily
and actually treated as private by its owner. Under the Freedom of
Information Act (FOIA) (5 U.S.C. 552), CBI is exempt from public
disclosure. If your comments responsive to this NPRM contain commercial
or financial information that is customarily treated as private, that
you actually treat as private, and that is relevant or responsive to
this NPRM, it is important that you clearly designate the submitted
comments as CBI. Please mark each page of your submission containing
CBI as ``PROPIN.'' The FAA will treat such marked submissions as
confidential under the FOIA, and they will not be placed in the public
docket of this NPRM. Submissions containing CBI should be sent to
Darren Gassetto, Aerospace Engineer, Mechanical Systems and
Administrative Services Section, FAA, New York ACO Branch, 1600 Stewart
Avenue, Suite 410, Westbury, NY 11590; telephone<PHONE_NUMBER>; fax 516-
794-5531; email<EMAIL_ADDRESS>Any commentary that the FAA
receives which is not specifically designated as CBI will be placed in
the public docket for this rulemaking.

Background

    Transport Canada Civil Aviation (TCCA), which is the aviation
authority for Canada, has issued TCCA AD CF-2019-17R1, dated June 18,
2020 (referred to after this as the Mandatory Continuing Airworthiness
Information, or ``the MCAI''), to correct an unsafe condition for MHI
RJ Aviation ULC (type certificate previously held by Bombardier, Inc.)
Model CL-600-2C10 (Regional Jet Series 700, 701 & 702) airplanes, Model
CL-600-2C11 (Regional Jet Series 550) airplanes, Model CL-600-2D15
(Regional Jet Series 705) airplanes, CL-600-2D24 (Regional Jet Series
900) airplanes, and Model CL-600-2E25 (Regional Jet Series 1000)
airplanes. You may examine the MCAI in the AD docket on the internet at
https://www.regulations.gov by searching for and locating Docket No.
FAA-2021-0309.
    This proposed AD was prompted by reports and a design review
indicating that there could be corrosion on the MLG outer cylinder
assemblies and certain MLG dressed shock strut assemblies; primer was
not correctly applied at the gland nut thread relief groove and chamfer
areas on certain MLG outer cylinders during production; and CIC was
inadvertently removed from certain MLG forward and aft trunnion pins
and grease adapter assemblies during maintenance. The FAA is proposing
this AD to address undetected corrosion on the MLG forward and aft
trunnion pins, and the gland nut interface on certain MLG outer
cylinders, which could result in an MLG collapse. See the MCAI for
additional background information.

Related Service Information Under 1 CFR Part 51

    Bombardier has issued the following service information.
     Service Bulletin 670BA-32-024, Revision C, dated February
11, 2015, which describes procedures for a detailed visual inspection
of the MLG outer cylinder assemblies and dressed shock strut assemblies
for corrosion of the outer cylinder gland nut thread interface and
relief area, and corrective actions including repair and corrosion
removal.
     Service Bulletin 670BA-32-034, Revision B, dated December
21, 2018, which describes procedures for a detailed visual inspection
of the inside diameter of the MLG trunnion pins for discrepancies
including the condition of paint and CIC and evidence of corrosion, and
corrective actions including replacement and rework of the trunnion
pins as applicable.
     Service Bulletin 670BA-32-039, dated February 29, 2012,
which describes procedures for inspections of the inner diameter of the
MLG forward and aft trunnion pins for discrepancies including corrosion
and inadequate CIC, and corrective actions including application of CIC
and replacement of corroded forward and aft trunnion pins with
serviceable parts.
     Service Bulletin 670BA-32-052, dated February 9, 2015,
which describes procedures for a detailed visual inspection of the
gland nut thread relief groove and chamfer surface for the condition of
the protective coating and

for discrepancies including evidence of corrosion or rework at the
gland nut thread relief groove and chamfer surface of the MLG shock
strut outer cylinder assemblies, and corrective actions including
corrosion removal.
    This service information is reasonably available because the
interested parties have access to it through their normal course of
business or by the means identified in the ADDRESSES section.

FAA's Determination

    This product has been approved by the aviation authority of another
country, and is approved for operation in the United States. Pursuant
to the FAA's bilateral agreement with the State of Design Authority,
the FAA has been notified of the unsafe condition described in the MCAI
and service information referenced above. The FAA is proposing this AD
because the FAA evaluated all the relevant information and determined
the unsafe condition described previously is likely to exist or develop
on other products of the same type design.

Proposed Requirements of This NPRM

    This proposed AD would require accomplishing the actions specified
in the service information described previously, except as discussed
under ``Differences Between this Proposed AD and the MCAI or Service
Information.''

Differences Between This Proposed AD and the MCAI or Service
Information

    Although certain service information specifies to return damaged
MLG trunnion pins to Goodrich Landing Gear, that action would not be
required by this proposed AD.

Costs of Compliance

    The FAA estimates that this proposed AD affects 562 airplanes of
U.S. registry. The FAA estimates the following costs to comply with
this proposed AD:

                                      Estimated Costs for Required Actions
----------------------------------------------------------------------------------------------------------------
              Labor cost                      Parts cost            Cost per product      Cost on U.S. operators
----------------------------------------------------------------------------------------------------------------
Up to 100 work-hours x $85 per hour =  Up to $36,604..........  Up to $45,104..........  Up to $25,348,448.
 Up to $8,500.
----------------------------------------------------------------------------------------------------------------

    According to the manufacturer, some or all of the costs of this
proposed AD may be covered under warranty, thereby reducing the cost
impact on affected operators. The FAA does not control warranty
coverage for affected operators. As a result, the FAA has included all
known costs in our cost estimate.

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.
    The FAA is 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

    The FAA 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) Would not affect intrastate aviation in Alaska, and
    (3) Would 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.

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

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 adding the following new airworthiness
directive:

MHI RJ Aviation ULC (Type Certificate Previously Held by Bombardier,
Inc.): Docket No. FAA-2021-0309; Project Identifier MCAI-2020-00918-
T.

(a) Comments Due Date

    The FAA must receive comments on this airworthiness directive
(AD) by June 4, 2021.

(b) Affected ADs

    None.

(c) Applicability

    This AD applies to the MHI RJ Aviation ULC (type certificate
previously held by Bombardier, Inc.) airplanes, certificated in any
category, specified in paragraphs (c)(1) through (3) of this AD.
    (1) Model CL-600-2C10 (Regional Jet Series 700, 701 & 702) and
Model CL-600-2C11 (Regional Jet Series 550) airplanes, serial
numbers 10002 and subsequent.
    (2) Model CL-600-2D15 (Regional Jet Series 705) airplanes and
CL-600-2D24 (Regional Jet Series 900) airplanes, serial numbers
15001 and subsequent.
    (3) Model CL-600-2E25 (Regional Jet Series 1000) airplanes,
serial numbers 19001 and subsequent.

(d) Subject

    Air Transport Association (ATA) of America Code 32, Landing
Gear.

(e) Reason

    This AD was prompted by reports and a design review indicating
that there could be corrosion on the main landing gear (MLG) outer
cylinder assemblies at the interface with the gland nut on the shock
strut installation and on the forward and aft trunnion pins in the
MLG dressed shock strut assemblies; primer was not correctly applied
at the gland nut thread relief groove and chamfer areas on certain
MLG outer cylinders during production; and corrosion-inhibiting
compound (CIC) could have inadvertently been removed from certain
MLG forward and aft trunnion pins and grease adapter assemblies
during maintenance. The FAA is issuing this AD to address undetected
corrosion on the MLG forward and aft trunnion pins, and the gland
nut interface on certain MLG outer cylinders, which could result in
an MLG collapse.

(f) Compliance

    Comply with this AD within the compliance times specified,
unless already done.

(g) Inspection and Application of Corrosion Protection for MLG Outer
Cylinder Assemblies and Certain MLG Dressed Shock Strut Assemblies

    For airplanes identified in paragraphs (c)(1) and (2) of this AD
with MLG outer cylinder assemblies and MLG dressed shock strut
assemblies having part numbers and serial numbers specified in the
effectivity tables in Section 1.A.(1) of Bombardier Service Bulletin
670BA-32-024, Revision C, dated February 11, 2015 (Bombardier
Service Bulletin 670BA-32-024, Revision C): At the applicable time
specified in paragraph (g)(1) or (2) of this AD, do a detailed
visual inspection for corrosion and all other required actions
specified in, and in accordance with, Section 2., Part A, of the
Accomplishment Instructions of Bombardier Service Bulletin 670BA-32-
024, Revision C.
    (1) For MLG assemblies that have accumulated 12,500 total flight
hours or less, and have been in service for 72 months or less from
entry into service or the last overhaul date: Within 6,500 flight
hours or 36 months, whichever comes first, after the effective date
of this AD.
    (2) For MLG assemblies that have accumulated more than 12,500
total flight hours, or have been in service for more than 72 months
from entry into service or the last overhaul date: Within 3,500
flight hours or 24 months, whichever occurs first, after the
effective date of this AD.

(h) Inspection of Certain Other MLG Dressed Shock Strut Assemblies and
Corrective Action

    For airplanes identified in paragraphs (c)(1) and (2) of this
AD, equipped with MLG dressed shock strut assemblies having part
numbers (P/Ns) 49000-25 through 49000-46 and P/Ns 49050-15 through
49050-22, on which the MLG active dynamic seal has been replaced
with the spare dynamic seal as specified in Bombardier CRJ700/705/
900/1000 Aircraft Maintenance Manual (AMM), CSP B-001, Task 32-11-
10-960-802, Revision 37, dated November 25, 2011, or earlier: At the
applicable time specified in paragraph (h)(1) or (2) of this AD, do
a detailed visual inspection of the MLG dressed shock strut
assemblies for corrosion, and all applicable corrective actions, in
accordance with Section 2., Part B, of the Accomplishment
Instructions of Bombardier Service Bulletin 670BA-32-024, Revision
C.
    (1) For MLG assemblies that have accumulated 12,500 total flight
hours or less, and have been in service for 72 months or less from
entry into service or the last overhaul date: Within 6,500 flight
hours or 36 months, whichever comes first, after the effective date
of this AD.
    (2) For MLG assemblies that have accumulated more than 12,500
total flight hours, or have been in service for more than 72 months
from entry into service or the last overhaul date: Within 3,500
flight hours or 24 months, whichever occurs first, after the
effective date of this AD.

(i) Inspection of MLG Outer Cylinder at the Gland Nut threads, Thread
Relief Groove, and Chamfer and Corrective Action

    For airplanes identified in paragraphs (c)(1) through (3) of
this AD equipped with MLG outer cylinder assemblies having part
numbers and serial numbers specified in Section 1.A., Effectivity,
of Bombardier Service Bulletin 670BA-32-052, dated February 9, 2015:
Within 6,500 flight hours or 36 months, whichever occurs first after
the effective date of this AD: Do a detailed visual inspection, of
the MLG shock strut outer cylinder assemblies and do all other
required actions specified in, and, in accordance with Section 2. of
the Accomplishment Instructions of Bombardier Service Bulletin
670BA-32-052, dated February 9, 2015.

(j) Inspection of Certain MLG Forward and Aft Trunnion Pins, and
Corrective Action

    For airplanes identified in paragraphs (c)(1) through (3) of
this AD equipped with MLG forward and aft trunnion pins and grease
adapter assemblies having part numbers and serial numbers specified
in Section 1.A., Effectivity, of Bombardier Service Bulletin 670BA-
32-034, Revision B, dated December 21, 2018: At the applicable time
specified in paragraph (j)(1) or (2) of this AD, do a detailed
visual inspection of the MLG forward and aft trunnion pins and do
all applicable corrective actions, in accordance with Section 2.B.
and paragraphs 2.C.(6) and (8) of the Accomplishment Instructions of
Bombardier Service Bulletin 670BA-32-034, Revision B, dated December
21, 2018.

    Note 1 to paragraph (j): The corrective action is applicable
only to MLG forward and aft trunnion pins having P/Ns 49101-9, -11,
and -13 reworked from P/Ns 49101-1, -5, and -7, as specified in the
procedures in Goodrich Service Bulletin 49101-32-47, any revision.
The corrective action is not applicable to MLG forward and aft
trunnion pins having P/Ns 49101-9, -11, and -13 that were installed
as original equipment or purchased from Goodrich Landing Gear.

    (1) For MLG forward and aft trunnion pins and grease adapter
assemblies that have not had the procedures specified in Goodrich
Service Bulletin 49101-32-47, any revision, incorporated, at the
applicable time specified in paragraph (j)(1)(i) or (ii) of this AD.
    (i) For MLG forward and aft trunnion pins that have accumulated
10,000 total flight hours or less, and have been in service 60
months or less from the entry into service or last overhaul date:
Within 6,500 flight hours or 36 months, whichever occurs first,
after the effective date of this AD.
    (ii) For MLG forward and aft trunnion pins that have accumulated
more than 10,000 total flight hours, or have been in service for
more than 60 months from entry into service or last overhaul date:
Within 3,000 flight hours or 24 months, whichever occurs first,
after the effective date of this AD.
    (2) For MLG forward and aft trunnion pins that have had the
procedures specified in Goodrich Service Bulletin 49101-32-47, any
revision, incorporated: Within 6,500 flight hours or 36 months,
whichever occurs first, after the effective date of this AD.

(k) Inspection of Certain Other MLG Trunnion Pins Having P/Ns 49101-9,
49101-11, and 49101-13, Maintained Using Certain Maintenance
Instructions

    For airplanes identified in paragraphs (c)(1) through (3) of
this AD equipped with MLG forward and aft trunnion pins having P/Ns
49101-9, 49101-11, and 49101-13 that were maintained in accordance
with the tasks identified in paragraphs (k)(1) through (4) of this
AD: Within 6,500 flight hours or 36 months after the effective date
of this AD, whichever occurs first, do a detailed visual inspection
of the MLG forward and aft trunnion pins, and do all applicable
corrective actions, in accordance with Section 2. of the
Accomplishment Instructions of Bombardier Service Bulletin 670BA-32-
039, dated February 29, 2012.
    (1) Bombardier CRJ700/705/900/1000 AMM, CSP B-001, Task 32-11-
05-400-801 A01, Revision 31, dated March 20, 2010, or earlier.
    (2) Bombardier CRJ700/705/900/1000 AMM, CSP B-001, Task 32-11-
05-400-801 A02, Revision 34, dated November 20, 2010, or earlier.
    (3) Bombardier CRJ700/705/900/1000 AMM, CSP B-001, Task 32-11-
05-400-804 A01, Revision 35, dated March 20, 2011, or earlier.
    (4) Bombardier CRJ700/705/900/1000 AMM, CSP B-001, Task 32-11-
05-400-805 A01, Revision 35, dated March 20, 2011, or earlier.

    Note 2 to paragraph (k): The corrective action described in this
paragraph is not applicable to MLG forward and aft trunnion pins
having P/Ns 49101-9, -11, and -13 reworked from P/Ns 49101-1, -5,
and -7 as specified in the procedures in Goodrich SB 49101-32-47,
any revision. The corrective action described in this paragraph is
applicable to MLG forward and aft trunnion pins having P/Ns 49101-9,
-11, and -13 installed as original equipment or purchased from
Goodrich Landing Gear.

(l) Credit for Previous Actions

    (1) This paragraph provides credit for actions required by
paragraph (g) of this AD, if those actions were performed before the
effective date of this AD using Section 2., Part A, of the
Accomplishment Instructions of Bombardier Service Bulletin 670BA-32-
024, Revision B, dated December 19, 2012.
    (2) This paragraph provides credit for actions required by
paragraph (h) of this AD if those actions were performed before the
effective date of this AD using Section 2., Part B, of the
Accomplishment Instructions of Bombardier Service Bulletin 670BA-32-
024, Revision B, dated December 19, 2012; or Bombardier CRJ700/705/
900/1000 Aircraft Maintenance Manual (AMM), CSP B-001, Task 32-11-
10-960-802, Revision 38, dated March 25, 2012.
    (3) This paragraph provides credit for actions required by
paragraph (j) of this AD if those actions were performed before the
effective date of this AD using Section 2.B. and paragraphs 2.C.(6)
and (8) of the Accomplishment Instructions of Bombardier Service
Bulletin 670BA-32-034, dated February 29, 2012; or Revision A, dated
August 17, 2012.

    (4) This paragraph provides credit for actions required by
paragraph (k) of this AD, if those actions were performed before the
effective date of this AD using the service information specified in
paragraphs (l)(4)(i) through (iv) of this AD.
    (i) Bombardier CRJ700/900/1000 Aircraft Maintenance Manual
(AMM), CSP B-001, Task 32-11-05-400-801 A01, Revision 38, dated
March 25, 2012.
    (ii) Bombardier CRJ700/900/1000 AMM, CSP B-001, Task 32-11-05-
400-801 A02, Revision 38, dated March 25, 2012.
    (iii) Bombardier CRJ700/900/1000 AMM, CSP B-001, Task 32-11-05-
400-804 A01, Revision 37, dated November 25, 2011, for actions
specified in Section 2.B.(1) of the Accomplishment Instructions of
Bombardier Service Bulletin 670BA-32-039, dated February 29, 2012.
    (iv) Bombardier CRJ700/900/1000 AMM, CSP B-001, Task 32-11-05-
400-805 A01, Revision 37, dated November 25, 2011, for actions
specified in Section 2.B.(2) of the Accomplishment Instructions of
Bombardier Service Bulletin 670BA-32-039, dated February 29, 2012.

(m) No Requirement for Return of Parts

    Although certain service information referenced in this AD
specifies to return damaged MLG trunnion pins to Goodrich Landing
Gear, this AD does not include that requirement.

(n) Other FAA AD Provisions

    The following provisions also apply to this AD:
    (1) Alternative Methods of Compliance (AMOCs): The Manager, New
York ACO Branch, FAA, has the authority to approve AMOCs for this
AD, if requested using the procedures found in 14 CFR 39.19. 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 manager of the certification
office, send it to ATTN: Program Manager, Continuing Operational
Safety, FAA, New York ACO Branch, 1600 Stewart Avenue, Suite 410,
Westbury, NY 11590; telephone<PHONE_NUMBER>; fax<PHONE_NUMBER>. 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.
    (2) Contacting the Manufacturer: For any requirement in this AD
to obtain instructions from a manufacturer, the instructions must be
accomplished using a method approved by the Manager, New York ACO
Branch, FAA; or Transport Canada Civil Aviation (TCCA); or MHI RJ
Aviation ULC's TCCA Design Approval Organization (DAO). If approved
by the DAO, the approval must include the DAO-authorized signature.

(o) Related Information

    (1) Refer to Mandatory Continuing Airworthiness Information
(MCAI) TCCA AD CF-2019-17R1, dated June 18, 2020, for related
information. This MCAI may be found in the AD docket on the internet
at https://www.regulations.gov by searching for and locating Docket
No. FAA-2021-0309.
    (2) For more information about this AD, contact Darren Gassetto,
Aerospace Engineer, Mechanical Systems and Administrative Services
Section, FAA, New York ACO Branch, 1600 Stewart Avenue, Suite 410,
Westbury, NY 11590; telephone<PHONE_NUMBER>; fax<PHONE_NUMBER>; email
<EMAIL_ADDRESS>    (3) For Bombardier service information identified in this AD,
contact MHI RJ Aviation ULC, 12655 Henri-Fabre Blvd., Mirabel,
Qu[eacute]bec J7N 1E1 Canada; Widebody Customer Response Center
North America toll-free telephone +1-844-272-2720 or direct-dial
telephone +1-514-855-8500; fax +1-514-855-8501; email
<EMAIL_ADDRESS>internet https://eservices.aero.bombardier.com.
You may view this service information at the FAA, Airworthiness
Products Section, Operational Safety Branch, 2200 South 216th St.,
Des Moines, WA. For information on the availability of this material
at the FAA, call<PHONE_NUMBER>.

    Issued on April 13, 2021.
Lance T. Gant,
Director, Compliance & Airworthiness Division, Aircraft Certification
Service.
[FR Doc. 2021-08053 Filed 4-19-21; 8:45 am]
BILLING CODE 4910-13-P


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	BMW

	Index	Type	TP	    TARF
	  1	 6	1	  -0.11983
	  2	 6	1	  -0.12275
	  3	 5	1	  -0.11373
	  4	 6	1	  -0.12365
	  5	 4	1	  -0.11263
	  6	 4	1	  -0.10616
	  7	 1	1	  -0.10131
	1000	 17	1	  -0.11896
	1001	 16	1	  -0.11373
	  1	 6	2	  -0.08466
	  2	 6	2	  -0.09069
	  3	 5	2	  -0.04944
	  4	 6	2	  -0.09225
	  5	 4	2	  -0.07823
	  6	 4	2	  -0.06887
	  7	 1	2	  -0.09501
	1000	 17	2	  -0.08484
	1001	 16	2	  -0.05415
	  1	 6	3	  -0.09752
	  2	 6	3	  -0.10367
	  3	 5	3	  -0.02654
	  4	 6	3	  -0.10482
	  5	 4	3	  -0.05572
	  6	 4	3	  -0.04370
	  7	 1	3	  -0.06064
	1000	 17	3	  -0.08564
	1001	 16	3	  -0.09355
	  1	 6	4	   0.25752
	  2	 6	4	   0.21901
	  3	 5	4	  -0.08892
	  4	 6	4	   0.21142
	  5	 4	4	  -0.00204
	  6	 4	4	   0.12484
	  7	 1	4	   0.17658
	1000	 17	4	   1.10540
	1001	 16	4	   0.79452
	  1	 6
	  2	 6
	  3	 5	5	   1.32015
	  4	 6
	  5	 4	5	   1.36883
	  6	 4	5	   1.51735
	  7	 1	5	   0.79620
	1000	 17
	1001	 16
	  1	 6
	  2	 6
	  3	 5
	  4	 6
	  5	 4
	  6	 4
	  7	 1
	1000	 17
	1001	 16

	Chrysler

	Index	Type	TP	    TARF
	  8	 13	1	  -0.11771
	  9	 16	1	  -0.11687
	 10	 9	1	  -0.11822
	 11	 8	1	  -0.11822
	 12	 7	1	  -0.10739
	 13	 12	1	  -0.11722
	 14	 4	1	  -0.11043
	 15	 3	1	  -0.11683
	 16	 13	1	  -0.11689
	 17	 5	1	  -0.11367
	 18	 5	1	  -0.11371
	 19	 3	1	  -0.11095
	 20	 4	1	  -0.11187
	 21	 2	1	  -0.11076
	 22	 13	1	  -0.12115
	 23	 8	1	  -0.11368
	 24	 4	1	  -0.11382
	 25	 1	1	  -0.10585
	1002	 13	1	  -0.11857
	1003	 10	1	  -0.12122
	1004	 11	1	  -0.11459
	1005	 17	1	  -0.10686
	1006	 13	1	  -0.11824
	1007	 10	1	  -0.11980
	1008	 16	1	  -0.11599
	1009	 12	1	  -0.11102
	1010	 9	1	  -0.11683
	1011	 8	1	  -0.11577
	1012	 7	1	  -0.10607
	1013	 12	1	  -0.11328
	1014	 16	1	  -0.11093
	1015	 12	1	  -0.10922
	  8	 13	2	  -0.07280
	  9	 16	2	  -0.03991
	 10	 9	2	  -0.04400
	 11	 8	2	  -0.05143
	 12	 7	2	  -0.06744
	 13	 12	2	  -0.02765
	 14	 4	2	  -0.07394
	 15	 3	2	  -0.08288
	 16	 13	2	  -0.07088
	 17	 5	2	  -0.04266
	 18	 5	2	  -0.04436
	 19	 3	2	  -0.07392
	 20	 4	2	  -0.08201
	 21	 2	2	  -0.08951
	 22	 13	2	  -0.07921
	 23	 8	2	  -0.03909
	 24	 4	2	  -0.08009
	 25	 1	2	  -0.09888
	1002	 13	2	  -0.08330
	1003	 10	2	  -0.07075
	1004	 11	2	  -0.07892
	1005	 17	2	  -0.05999
	1006	 13	2	  -0.08257
	1007	 10	2	  -0.06655
	1008	 16	2	  -0.05871
	1009	 12	2	  -0.02863
	1010	 9	2	  -0.05848
	1011	 8	2	  -0.06145
	1012	 7	2	  -0.07278
	1013	 12	2	  -0.03710
	1014	 16	2	  -0.04546
	1015	 12	2	  -0.02638
	  8	 13	3	  -0.03608
	  9	 16	3	  -0.08928
	 10	 9	3	  -0.05518
	 11	 8	3	  -0.04504
	 12	 7	3	  -0.05654
	 13	 12	3	  -0.06361
	 14	 4	3	  -0.05010
	 15	 3	3	  -0.07674
	 16	 13	3	  -0.03334
	 17	 5	3	  -0.01815
	 18	 5	3	  -0.02049
	 19	 3	3	  -0.06733
	 20	 4	3	  -0.06036
	 21	 2	3	  -0.06776
	 22	 13	3	  -0.04290
	 23	 8	3	  -0.03162
	 24	 4	3	  -0.05801
	 25	 1	3	  -0.06421
	1002	 13	3	  -0.05533
	1003	 10	3	  -0.08706
	1004	 11	3	  -0.04242
	1005	 17	3	  -0.06062
	1006	 13	3	  -0.05417
	1007	 10	3	  -0.08374
	1008	 16	3	  -0.09616
	1009	 12	3	  -0.06127
	1010	 9	3	  -0.06723
	1011	 8	3	  -0.05624
	1012	 7	3	  -0.06373
	1013	 12	3	  -0.06804
	1014	 16	3	  -0.08851
	1015	 12	3	  -0.05988
	  8	 13	4	  -0.02611
	  9	 16	4	   1.03014
	 10	 9	4	  -0.04967
	 11	 8	4	  -0.05264
	 12	 7	4	   1.21939
	 13	 12	4	   0.57054
	 14	 4	4	   0.05781
	 15	 3	4	   0.21619
	 16	 13	4	  -0.02308
	 17	 5	4	  -0.08443
	 18	 5	4	  -0.08560
	 19	 3	4	   0.26016
	 20	 4	4	  -0.04540
	 21	 2	4	   0.32278
	 22	 13	4	  -0.03922
	 23	 8	4	  -0.04061
	 24	 4	4	  -0.02863
	 25	 1	4	   0.16528
	1002	 13	4	  -0.04761
	1003	 10	4	   1.43620
	1004	 11	4	  -0.06884
	1005	 17	4	   1.60899
	1006	 13	4	  -0.04642
	1007	 10	4	   1.52448
	1008	 16	4	   0.74841
	1009	 12	4	   0.52203
	1010	 9	4	  -0.06290
	1011	 8	4	  -0.06245
	1012	 7	4	   0.99730
	1013	 12	4	   0.46832
	1014	 16	4	   0.88326
	1015	 12	4	   0.53385
	  8	 13	5	   2.40042
	  9	 16
	 10	 9	5	   1.11474
	 11	 8	5	   1.03614
	 12	 7	5	   0.35842
	 13	 12
	 14	 4	5	   1.43712
	 15	 3
	 16	 13	5	   2.45949
	 17	 5	5	   1.41798
	 18	 5	5	   1.39238
	 19	 3
	 20	 4	5	   1.32163
	 21	 2
	 22	 13	5	   2.12743
	 23	 8	5	   1.17471
	 24	 4	5	   1.33794
	 25	 1	5	   0.76605
	1002	 13	5	   1.79898
	1003	 10
	1004	 11
	1005	 17
	1006	 13	5	   1.82209
	1007	 10
	1008	 16
	1009	 12
	1010	 9	5	   0.85256
	1011	 8	5	   0.82266
	1012	 7	5	   0.28135
	1013	 12
	1014	 16
	1015	 12
	  8	 13
	  9	 16
	 10	 9
	 11	 8
	 12	 7
	 13	 12
	 14	 4
	 15	 3
	 16	 13
	 17	 5
	 18	 5
	 19	 3
	 20	 4
	 21	 2
	 22	 13
	 23	 8
	 24	 4
	 25	 1
	1002	 13
	1003	 10
	1004	 11
	1005	 17
	1006	 13
	1007	 10
	1008	 16
	1009	 12
	1010	 9
	1011	 8
	1012	 7
	1013	 12
	1014	 16
	1015	 12

	Ford

	Index	Type	TP	    TARF
	 26	 16	1	  -0.11813
	 27	 5	1	  -0.11454
	 28	 7	1	  -0.10636
	 29	 10	1	  -0.11961
	 30	 6	1	  -0.11940
	 31	 5	1	  -0.11289
	 32	 10	1	  -0.11949
	 33	 6	1	  -0.11821
	 34	 8	1	  -0.11614
	 35	 5	1	  -0.11382
	 36	 3	1	  -0.10945
	 37	 6	1	  -0.11173
	 38	 7	1	  -0.10807
	 39	 1	1	  -0.10482
	1016	 14	1	  -0.11794
	1017	 10	1	  -0.11925
	1018	 18	1	  -0.11470
	1019	 11	1	  -0.11372
	1020	 12	1	  -0.11220
	1021	 8	1	  -0.11855
	1022	 7	1	  -0.10816
	1023	 17	1	  -0.11986
	1024	 14	1	  -0.11789
	1025	 16	1	  -0.11570
	1026	 9	1	  -0.11880
	1027	 5	1	  -0.11228
	1028	 7	1	  -0.10227
	1029	 10	1	  -0.12471
	 26	 16	2	  -0.04841
	 27	 5	2	  -0.04501
	 28	 7	2	  -0.06130
	 29	 10	2	  -0.04675
	 30	 6	2	  -0.07938
	 31	 5	2	  -0.04537
	 32	 10	2	  -0.04853
	 33	 6	2	  -0.08051
	 34	 8	2	  -0.04547
	 35	 5	2	  -0.04787
	 36	 3	2	  -0.06916
	 37	 6	2	  -0.06789
	 38	 7	2	  -0.06386
	 39	 1	2	  -0.09612
	1016	 14	2	  -0.06816
	1017	 10	2	  -0.06478
	1018	 18	2	  -0.08213
	1019	 11	2	  -0.07674
	1020	 12	2	  -0.03270
	1021	 8	2	  -0.06915
	1022	 7	2	  -0.07403
	1023	 17	2	  -0.08637
	1024	 14	2	  -0.07016
	1025	 16	2	  -0.05918
	1026	 9	2	  -0.06436
	1027	 5	2	  -0.05500
	1028	 7	2	  -0.06319
	1029	 10	2	  -0.08106
	 26	 16	3	  -0.09427
	 27	 5	3	  -0.02099
	 28	 7	3	  -0.04931
	 29	 10	3	  -0.07023
	 30	 6	3	  -0.09301
	 31	 5	3	  -0.02174
	 32	 10	3	  -0.07183
	 33	 6	3	  -0.09668
	 34	 8	3	  -0.03882
	 35	 5	3	  -0.02478
	 36	 3	3	  -0.06187
	 37	 6	3	  -0.08572
	 38	 7	3	  -0.05205
	 39	 1	3	  -0.05961
	1016	 14	3	  -0.07555
	1017	 10	3	  -0.08236
	1018	 18	3	  -0.07733
	1019	 11	3	  -0.03934
	1020	 12	3	  -0.06421
	1021	 8	3	  -0.06449
	1022	 7	3	  -0.06488
	1023	 17	3	  -0.08712
	1024	 14	3	  -0.07736
	1025	 16	3	  -0.09641
	1026	 9	3	  -0.07254
	1027	 5	3	  -0.03511
	1028	 7	3	  -0.05275
	1029	 10	3	  -0.09512
	 26	 16	4	   0.94143
	 27	 5	4	  -0.08592
	 28	 7	4	   1.31902
	 29	 10	4	   2.12746
	 30	 6	4	   0.28901
	 31	 5	4	  -0.08630
	 32	 10	4	   2.08480
	 33	 6	4	   0.26359
	 34	 8	4	  -0.04669
	 35	 5	4	  -0.08789
	 36	 3	4	   0.28581
	 37	 6	4	   0.33755
	 38	 7	4	   1.28103
	 39	 1	4	   0.18140
	1016	 14	4	   1.48270
	1017	 10	4	   1.56116
	1018	 18
	1019	 11	4	  -0.06594
	1020	 12	4	   0.49946
	1021	 8	4	  -0.06998
	1022	 7	4	   0.98139
	1023	 17	4	   1.07538
	1024	 14	4	   1.44161
	1025	 16	4	   0.74366
	1026	 9	4	  -0.06850
	1027	 5	4	  -0.08871
	1028	 7	4	   1.14887
	1029	 10	4	   1.22240
	 26	 16
	 27	 5	5	   1.38553
	 28	 7	5	   0.39573
	 29	 10
	 30	 6
	 31	 5	5	   1.37680
	 32	 10
	 33	 6
	 34	 8	5	   1.10443
	 35	 5	5	   1.34189
	 36	 3
	 37	 6
	 38	 7	5	   0.38151
	 39	 1	5	   0.80480
	1016	 14
	1017	 10
	1018	 18
	1019	 11
	1020	 12
	1021	 8	5	   0.73594
	1022	 7	5	   0.27539
	1023	 17
	1024	 14
	1025	 16
	1026	 9	5	   0.78568
	1027	 5	5	   1.12391
	1028	 7	5	   0.33804
	1029	 10
	 26	 16
	 27	 5
	 28	 7
	 29	 10
	 30	 6
	 31	 5
	 32	 10
	 33	 6
	 34	 8
	 35	 5
	 36	 3
	 37	 6
	 38	 7
	 39	 1
	1016	 14
	1017	 10
	1018	 18
	1019	 11
	1020	 12
	1021	 8
	1022	 7
	1023	 17
	1024	 14
	1025	 16
	1026	 9
	1027	 5
	1028	 7
	1029	 10

	Subaru

	Index	Type	TP	    TARF
	 40	 5	1	  -0.11378
	 41	 7	1	  -0.10939
	 42	 5	1	  -0.11473
	 43	 3	1	  -0.11432
	 44	 4	1	  -0.11384
	 45	 1	1	  -0.11264
	1030	 16	1	  -0.11443
	1031	 5	1	  -0.11082
	1032	 7	1	  -0.10588
	 40	 5	2	  -0.04602
	 41	 7	2	  -0.06634
	 42	 5	2	  -0.05014
	 43	 3	2	  -0.07810
	 44	 4	2	  -0.08210
	 45	 1	2	  -0.10580
	1030	 16	2	  -0.05391
	1031	 5	2	  -0.05483
	1032	 7	2	  -0.06845
	 40	 5	3	  -0.02501
	 41	 7	3	  -0.05487
	 42	 5	3	  -0.03017
	 43	 3	3	  -0.07154
	 44	 4	3	  -0.06076
	 45	 1	3	  -0.07520
	1030	 16	3	  -0.09391
	1031	 5	3	  -0.03747
	1032	 7	3	  -0.05848
	 40	 5	4	  -0.08829
	 41	 7	4	   1.24212
	 42	 5	4	  -0.09114
	 43	 3	4	   0.24041
	 44	 4	4	  -0.05527
	 45	 1	4	   0.12692
	1030	 16	4	   0.78637
	1031	 5	4	  -0.08954
	1032	 7	4	   1.07005
	 40	 5	5	   1.33226
	 41	 7	5	   0.36693
	 42	 5	5	   1.27667
	 43	 3
	 44	 4	5	   1.30870
	 45	 1	5	   0.67435
	1030	 16
	1031	 5	5	   1.10695
	1032	 7	5	   0.30855
	 40	 5
	 41	 7
	 42	 5
	 43	 3
	 44	 4
	 45	 1
	1030	 16
	1031	 5
	1032	 7

	General Motors

	Index	Type	TP	    TARF
	 46	 16	1	  -0.11728
	 47	 12	1	  -0.10998
	 48	 5	1	  -0.11847
	 49	 7	1	  -0.11036
	 50	 4	1	  -0.10959
	 51	 3	1	  -0.11083
	 52	 13	1	  -0.11677
	 53	 6	1	  -0.11986
	 54	 12	1	  -0.11020
	 55	 5	1	  -0.11596
	 56	 13	1	  -0.11459
	 57	 6	1	  -0.11899
	 58	 12	1	  -0.10706
	 59	 5	1	  -0.11638
	 60	 3	1	  -0.11402
	 61	 6	1	  -0.11978
	 62	 12	1	  -0.10687
	 63	 4	1	  -0.11350
	 64	 2	1	  -0.10974
	 65	 4	1	  -0.10853
	 66	 1	1	  -0.10756
	1033	 13	1	  -0.11559
	1034	 12	1	  -0.11414
	1035	 7	1	  -0.11567
	1036	 7	1	  -0.11352
	1037	 17	1	  -0.11982
	1038	 13	1	  -0.11671
	1039	 16	1	  -0.11576
	1040	 12	1	  -0.10758
	1041	 7	1	  -0.11975
	1042	 12	1	  -0.11053
	1043	 5	1	  -0.11397
	1044	 13	1	  -0.11859
	1045	 12	1	  -0.11043
	 46	 16	2	  -0.04686
	 47	 12	2	  -0.00316
	 48	 5	2	  -0.06139
	 49	 7	2	  -0.06863
	 50	 4	2	  -0.07440
	 51	 3	2	  -0.07226
	 52	 13	2	  -0.07360
	 53	 6	2	  -0.08308
	 54	 12	2	  -0.00392
	 55	 5	2	  -0.05549
	 56	 13	2	  -0.06753
	 57	 6	2	  -0.07855
	 58	 12	2	   0.00188
	 59	 5	2	  -0.05670
	 60	 3	2	  -0.07957
	 61	 6	2	  -0.08460
	 62	 12	2	   0.00121
	 63	 4	2	  -0.08001
	 64	 2	2	  -0.08426
	 65	 4	2	  -0.07245
	 66	 1	2	  -0.09914
	1033	 13	2	  -0.07931
	1034	 12	2	  -0.03913
	1035	 7	2	  -0.08816
	1036	 7	2	  -0.08413
	1037	 17	2	  -0.08678
	1038	 13	2	  -0.08241
	1039	 16	2	  -0.05887
	1040	 12	2	  -0.01740
	1041	 7	2	  -0.09585
	1042	 12	2	  -0.03538
	1043	 5	2	  -0.06455
	1044	 13	2	  -0.08334
	1045	 12	2	  -0.02673
	 46	 16	3	  -0.09365
	 47	 12	3	  -0.04548
	 48	 5	3	  -0.04142
	 49	 7	3	  -0.05802
	 50	 4	3	  -0.05081
	 51	 3	3	  -0.06534
	 52	 13	3	  -0.03729
	 53	 6	3	  -0.09627
	 54	 12	3	  -0.04604
	 55	 5	3	  -0.03440
	 56	 13	3	  -0.02967
	 57	 6	3	  -0.09232
	 58	 12	3	  -0.04215
	 59	 5	3	  -0.03593
	 60	 3	3	  -0.07354
	 61	 6	3	  -0.09885
	 62	 12	3	  -0.04267
	 63	 4	3	  -0.05795
	 64	 2	3	  -0.06065
	 65	 4	3	  -0.04828
	 66	 1	3	  -0.06444
	1033	 13	3	  -0.04977
	1034	 12	3	  -0.06888
	1035	 7	3	  -0.08085
	1036	 7	3	  -0.07630
	1037	 17	3	  -0.08755
	1038	 13	3	  -0.05462
	1039	 16	3	  -0.09638
	1040	 12	3	  -0.05315
	1041	 7	3	  -0.08947
	1042	 12	3	  -0.06639
	1043	 5	3	  -0.04733
	1044	 13	3	  -0.05543
	1045	 12	3	  -0.05992
	 46	 16	4	   0.95200
	 47	 12	4	   0.71144
	 48	 5	4	  -0.09658
	 49	 7	4	   1.19534
	 50	 4	4	   0.05058
	 51	 3	4	   0.26956
	 52	 13	4	  -0.02730
	 53	 6	4	   0.26601
	 54	 12	4	   0.70781
	 55	 5	4	  -0.09286
	 56	 13	4	  -0.01896
	 57	 6	4	   0.29382
	 58	 12	4	   0.73876
	 59	 5	4	  -0.09366
	 60	 3	4	   0.23172
	 61	 6	4	   0.24653
	 62	 12	4	   0.73541
	 63	 4	4	  -0.02782
	 64	 2	4	   0.36123
	 65	 4	4	   0.07801
	 66	 1	4	   0.16423
	1033	 13	4	  -0.04164
	1034	 12	4	   0.46394
	1035	 7	4	   0.76173
	1036	 7	4	   0.82444
	1037	 17	4	   1.06639
	1038	 13	4	  -0.04674
	1039	 16	4	   0.74373
	1040	 12	4	   0.58752
	1041	 7	4	   0.64290
	1042	 12	4	   0.48329
	1043	 5	4	  -0.09499
	1044	 13	4	  -0.04765
	1045	 12	4	   0.53364
	 46	 16
	 47	 12
	 48	 5	5	   1.15189
	 49	 7	5	   0.34837
	 50	 4	5	   1.42863
	 51	 3
	 52	 13	5	   2.37709
	 53	 6
	 54	 12
	 55	 5	5	   1.23284
	 56	 13	5	   2.54146
	 57	 6
	 58	 12
	 59	 5	5	   1.21566
	 60	 3
	 61	 6
	 62	 12
	 63	 4	5	   1.33945
	 64	 2
	 65	 4	5	   1.46005
	 66	 1	5	   0.76406
	1033	 13	5	   1.91743
	1034	 12
	1035	 7	5	   0.19320
	1036	 7	5	   0.21666
	1037	 17
	1038	 13	5	   1.81666
	1039	 16
	1040	 12
	1041	 7	5	   0.14873
	1042	 12
	1043	 5	5	   0.98572
	1044	 13	5	   1.79872
	1045	 12
	 46	 16
	 47	 12
	 48	 5
	 49	 7
	 50	 4
	 51	 3
	 52	 13
	 53	 6
	 54	 12
	 55	 5
	 56	 13
	 57	 6
	 58	 12
	 59	 5
	 60	 3
	 61	 6
	 62	 12
	 63	 4
	 64	 2
	 65	 4
	 66	 1
	1033	 13
	1034	 12
	1035	 7
	1036	 7
	1037	 17
	1038	 13
	1039	 16
	1040	 12
	1041	 7
	1042	 12
	1043	 5
	1044	 13
	1045	 12

	Honda

	Index	Type	TP	    TARF
	 67	 7	1	  -0.10891
	 68	 5	1	  -0.11112
	 69	 3	1	  -0.11132
	 70	 2	1	  -0.09995
	 71	 1	1	  -0.10006
	1046	 7	1	  -0.11691
	1047	 16	1	  -0.11564
	1048	 5	1	  -0.11327
	1049	 7	1	  -0.10694
	1050	 16	1	  -0.11158
	 67	 7	2	  -0.06880
	 68	 5	2	  -0.04059
	 69	 3	2	  -0.07663
	 70	 2	2	  -0.07160
	 71	 1	2	  -0.09181
	1046	 7	2	  -0.09164
	1047	 16	2	  -0.05691
	1048	 5	2	  -0.06273
	1049	 7	2	  -0.07325
	1050	 16	2	  -0.04533
	 67	 7	3	  -0.05805
	 68	 5	3	  -0.01867
	 69	 3	3	  -0.07045
	 70	 2	3	  -0.04848
	 71	 1	3	  -0.05610
	1046	 7	3	  -0.08483
	1047	 16	3	  -0.09520
	1048	 5	3	  -0.04686
	1049	 7	3	  -0.06421
	1050	 16	3	  -0.08853
	 67	 7	4	   1.18534
	 68	 5	4	  -0.08359
	 69	 3	4	   0.24548
	 70	 2	4	   0.43421
	 71	 1	4	   0.19849
	1046	 7	4	   0.72272
	1047	 16	4	   0.76499
	1048	 5	4	  -0.09411
	1049	 7	4	   0.97946
	1050	 16	4	   0.88283
	 67	 7	5	   0.34569
	 68	 5	5	   1.44222
	 69	 3
	 70	 2
	 71	 1	5	   0.84726
	1046	 7	5	   0.17879
	1047	 16
	1048	 5	5	   1.00001
	1049	 7	5	   0.27466
	1050	 16
	 67	 7
	 68	 5
	 69	 3
	 70	 2
	 71	 1
	1046	 7
	1047	 16
	1048	 5
	1049	 7
	1050	 16

	Hyundai

	Index	Type	TP	    TARF
	 72	 16	1	  -0.11418
	 73	 5	1	  -0.11465
	 74	 7	1	  -0.11083
	 75	 5	1	  -0.11165
	 76	 3	1	  -0.11102
	 77	 2	1	  -0.10419
	 78	 4	1	  -0.11562
	 79	 1	1	  -0.10463
	1051	 16	1	  -0.11294
	1052	 5	1	  -0.11211
	1053	 16	1	  -0.11364
	 72	 16	2	  -0.03285
	 73	 5	2	  -0.04535
	 74	 7	2	  -0.06916
	 75	 5	2	  -0.03979
	 76	 3	2	  -0.07401
	 77	 2	2	  -0.07530
	 78	 4	2	  -0.08021
	 79	 1	2	  -0.09546
	1051	 16	2	  -0.04913
	1052	 5	2	  -0.05443
	1053	 16	2	  -0.04906
	 72	 16	3	  -0.08524
	 73	 5	3	  -0.02150
	 74	 7	3	  -0.05807
	 75	 5	3	  -0.01477
	 76	 3	3	  -0.06742
	 77	 2	3	  -0.04853
	 78	 4	3	  -0.05782
	 79	 1	3	  -0.05840
	1051	 16	3	  -0.09062
	1052	 5	3	  -0.03442
	1053	 16	3	  -0.09047
	 72	 16	4	   1.10140
	 73	 5	4	  -0.08612
	 74	 7	4	   1.19848
	 75	 5	4	  -0.08272
	 76	 3	4	   0.25978
	 77	 2	4	   0.42682
	 78	 4	4	  -0.02483
	 79	 1	4	   0.18542
	1051	 16	4	   0.84633
	1052	 5	4	  -0.08834
	1053	 16	4	   0.84871
	 72	 16
	 73	 5	5	   1.38093
	 74	 7	5	   0.35060
	 75	 5	5	   1.45527
	 76	 3
	 77	 2
	 78	 4	5	   1.34291
	 79	 1	5	   0.81469
	1051	 16
	1052	 5	5	   1.13190
	1053	 16
	 72	 16
	 73	 5
	 74	 7
	 75	 5
	 76	 3
	 77	 2
	 78	 4
	 79	 1
	1051	 16
	1052	 5
	1053	 16

	Tata

	Index	Type	TP	    TARF
	 80	 6	1	  -0.11682
	 81	 6	1	  -0.11787
	 82	 5	1	  -0.11615
	1054	 17	1	  -0.12122
	1055	 10	1	  -0.12206
	1056	 5	1	  -0.11534
	 80	 6	2	  -0.07882
	 81	 6	2	  -0.08086
	 82	 5	2	  -0.05452
	1054	 17	2	  -0.08996
	1055	 10	2	  -0.07723
	1056	 5	2	  -0.06796
	 80	 6	3	  -0.09269
	 81	 6	3	  -0.09439
	 82	 5	3	  -0.03284
	1054	 17	3	  -0.09066
	1055	 10	3	  -0.09364
	1056	 5	3	  -0.05119
	 80	 6	4	   0.29131
	 81	 6	4	   0.27939
	 82	 5	4	  -0.09209
	1054	 17	4	   1.00241
	1055	 10	4	   1.25468
	1056	 5	4	  -0.09703
	 80	 6
	 81	 6
	 82	 5	5	   1.25039
	1054	 17
	1055	 10
	1056	 5	5	   0.94181
	 80	 6
	 81	 6
	 82	 5
	1054	 17
	1055	 10
	1056	 5

	Kia

	Index	Type	TP	    TARF
	 83	 16	1	  -0.11826
	 84	 7	1	  -0.11101
	 85	 5	1	  -0.11160
	 86	 3	1	  -0.11009
	 87	 4	1	  -0.11253
	 88	 2	1	  -0.10653
	 89	 1	1	  -0.10192
	1057	 16	1	  -0.11392
	1058	 7	1	  -0.10841
	1059	 16	1	  -0.11364
	 83	 16	2	  -0.04513
	 84	 7	2	  -0.06942
	 85	 5	2	  -0.03725
	 86	 3	2	  -0.07040
	 87	 4	2	  -0.07364
	 88	 2	2	  -0.07898
	 89	 1	2	  -0.09226
	1057	 16	2	  -0.05030
	1058	 7	2	  -0.07338
	1059	 16	2	  -0.04906
	 83	 16	3	  -0.09234
	 84	 7	3	  -0.05834
	 85	 5	3	  -0.01154
	 86	 3	3	  -0.06318
	 87	 4	3	  -0.04920
	 88	 2	3	  -0.05338
	 89	 1	3	  -0.05331
	1057	 16	3	  -0.09120
	1058	 7	3	  -0.06401
	1059	 16	3	  -0.09047
	 83	 16	4	   0.97591
	 84	 7	4	   1.19428
	 85	 5	4	  -0.08100
	 86	 3	4	   0.27959
	 87	 4	4	   0.06862
	 88	 2	4	   0.40060
	 89	 1	4	   0.20323
	1057	 16	4	   0.83572
	1058	 7	4	   0.99347
	1059	 16	4	   0.84871
	 83	 16
	 84	 7	5	   0.34905
	 85	 5	5	   1.49316
	 86	 3
	 87	 4	5	   1.44927
	 88	 2
	 89	 1	5	   0.85739
	1057	 16
	1058	 7	5	   0.27991
	1059	 16
	 83	 16
	 84	 7
	 85	 5
	 86	 3
	 87	 4
	 88	 2
	 89	 1
	1057	 16
	1058	 7
	1059	 16

	Mazda

	Index	Type	TP	    TARF
	 90	 16	1	  -0.11813
	 91	 5	1	  -0.11473
	 92	 7	1	  -0.10973
	 93	 5	1	  -0.11417
	 94	 3	1	  -0.11236
	 95	 4	1	  -0.11517
	 96	 2	1	  -0.10875
	 97	 1	1	  -0.10933
	1060	 8	1	  -0.11901
	1061	 7	1	  -0.10684
	1062	 16	1	  -0.11386
	1063	 5	1	  -0.11245
	1064	 7	1	  -0.10736
	1065	 7	1	  -0.10381
	 90	 16	2	  -0.05016
	 91	 5	2	  -0.04900
	 92	 7	2	  -0.06864
	 93	 5	2	  -0.05022
	 94	 3	2	  -0.07639
	 95	 4	2	  -0.08707
	 96	 2	2	  -0.08412
	 97	 1	2	  -0.10300
	1060	 8	2	  -0.07037
	1061	 7	2	  -0.07150
	1062	 16	2	  -0.05531
	1063	 5	2	  -0.05828
	1064	 7	2	  -0.07265
	1065	 7	2	  -0.06589
	 90	 16	3	  -0.09639
	 91	 5	3	  -0.02621
	 92	 7	3	  -0.05768
	 93	 5	3	  -0.02758
	 94	 3	3	  -0.07000
	 95	 4	3	  -0.06697
	 96	 2	3	  -0.06046
	 97	 1	3	  -0.07084
	1060	 8	3	  -0.06571
	1061	 7	3	  -0.06209
	1062	 16	3	  -0.09497
	1063	 5	3	  -0.03942
	1064	 7	3	  -0.06334
	1065	 7	3	  -0.05576
	 90	 16	4	   0.90146
	 91	 5	4	  -0.08861
	 92	 7	4	   1.20373
	 93	 5	4	  -0.08935
	 94	 3	4	   0.24761
	 95	 4	4	  -0.11928
	 96	 2	4	   0.36220
	 97	 1	4	   0.14203
	1060	 8	4	  -0.07119
	1061	 7	4	   1.01988
	1062	 16	4	   0.76714
	1063	 5	4	  -0.09091
	1064	 7	4	   1.00261
	1065	 7	4	   1.10705
	 90	 16
	 91	 5	5	   1.32677
	 92	 7	5	   0.35258
	 93	 5	5	   1.30985
	 94	 3
	 95	 4	5	   1.23697
	 96	 2
	 97	 1	5	   0.71060
	1060	 8	5	   0.72202
	1061	 7	5	   0.28982
	1062	 16
	1063	 5	5	   1.07544
	1064	 7	5	   0.28333
	1065	 7	5	   0.32242
	 90	 16
	 91	 5
	 92	 7
	 93	 5
	 94	 3
	 95	 4
	 96	 2
	 97	 1
	1060	 8
	1061	 7
	1062	 16
	1063	 5
	1064	 7
	1065	 7

	Daimler

	Index	Type	TP	    TARF
	 98	 10	1	  -0.12756
	 99	 6	1	  -0.12315
	100	 5	1	  -0.11514
	101	 6	1	  -0.11263
	102	 5	1	  -0.11668
	103	 4	1	  -0.11410
	104	 6	1	  -0.12264
	105	 4	1	  -0.11511
	106	 1	1	  -0.08561
	1066	 17	1	  -0.11697
	1067	 14	1	  -0.12224
	1068	 16	1	  -0.11694
	 98	 10	2	  -0.07267
	 99	 6	2	  -0.09001
	100	 5	2	  -0.05152
	101	 6	2	  -0.07017
	102	 5	2	  -0.05314
	103	 4	2	  -0.07903
	104	 6	2	  -0.08906
	105	 4	2	  -0.08190
	106	 1	2	  -0.07782
	1066	 17	2	  -0.08027
	1067	 14	2	  -0.08006
	1068	 16	2	  -0.06278
	 98	 10	3	  -0.09240
	 99	 6	3	  -0.10196
	100	 5	3	  -0.02929
	101	 6	3	  -0.08549
	102	 5	3	  -0.03101
	103	 4	3	  -0.05658
	104	 6	3	  -0.10111
	105	 4	3	  -0.06037
	106	 1	3	  -0.03047
	1066	 17	3	  -0.08100
	1067	 14	3	  -0.08694
	1068	 16	3	  -0.09847
	 98	 10	4	   1.53146
	 99	 6	4	   0.22615
	100	 5	4	  -0.09019
	101	 6	4	   0.32861
	102	 5	4	  -0.09116
	103	 4	4	  -0.01272
	104	 6	4	   0.23208
	105	 4	4	  -0.05423
	106	 1	4	   0.28307
	1066	 17	4	   1.19236
	1067	 14	4	   1.21756
	1068	 16	4	   0.70719
	 98	 10
	 99	 6
	100	 5	5	   1.29165
	101	 6
	102	 5	5	   1.27033
	103	 4	5	   1.35631
	104	 6
	105	 4	5	   1.30890
	106	 1	5	   1.04884
	1066	 17
	1067	 14
	1068	 16
	 98	 10
	 99	 6
	100	 5
	101	 6
	102	 5
	103	 4
	104	 6
	105	 4
	106	 1
	1066	 17
	1067	 14
	1068	 16

	Mitsubishi

	Index	Type	TP	    TARF
	107	 5	1	  -0.11490
	108	 7	1	  -0.10998
	109	 5	1	  -0.11561
	110	 3	1	  -0.11402
	111	 4	1	  -0.11592
	112	 2	1	  -0.11375
	113	 1	1	  -0.10583
	1069	 16	1	  -0.11592
	1070	 5	1	  -0.11242
	1071	 7	1	  -0.10723
	107	 5	2	  -0.05238
	108	 7	2	  -0.07247
	109	 5	2	  -0.04792
	110	 3	2	  -0.07956
	111	 4	2	  -0.08119
	112	 2	2	  -0.09228
	113	 1	2	  -0.09886
	1069	 16	2	  -0.05590
	1070	 5	2	  -0.06074
	1071	 7	2	  -0.07526
	107	 5	3	  -0.03027
	108	 7	3	  -0.06221
	109	 5	3	  -0.02442
	110	 3	3	  -0.07342
	111	 4	3	  -0.05917
	112	 2	3	  -0.07136
	113	 1	3	  -0.06418
	1069	 16	3	  -0.09442
	1070	 5	3	  -0.04247
	1071	 7	3	  -0.06648
	107	 5	4	  -0.09074
	108	 7	4	   1.14145
	109	 5	4	  -0.08772
	110	 3	4	   0.23174
	111	 4	4	  -0.03854
	112	 2	4	   0.30334
	113	 1	4	   0.16540
	1069	 16	4	   0.77888
	1070	 5	4	  -0.09245
	1071	 7	4	   0.95939
	107	 5	5	   1.27970
	108	 7	5	   0.32925
	109	 5	5	   1.34586
	110	 3
	111	 4	5	   1.32761
	112	 2
	113	 1	5	   0.76661
	1069	 16
	1070	 5	5	   1.04173
	1071	 7	5	   0.26716
	107	 5
	108	 7
	109	 5
	110	 3
	111	 4
	112	 2
	113	 1
	1069	 16
	1070	 5
	1071	 7

	Nissan

	Index	Type	TP	    TARF
	114	 16	1	  -0.12053
	115	 7	1	  -0.10582
	116	 5	1	  -0.12235
	117	 6	1	  -0.12273
	118	 5	1	  -0.11589
	119	 3	1	  -0.10906
	120	 4	1	  -0.11444
	121	 2	1	  -0.10612
	122	 1	1	  -0.10540
	1072	 19	1	  -0.11939
	1073	 18	1	  -0.11500
	1074	 7	1	  -0.11269
	1075	 17	1	  -0.12204
	1076	 16	1	  -0.11747
	1077	 7	1	  -0.10566
	1078	 5	1	  -0.11831
	1079	 16	1	  -0.11327
	114	 16	2	  -0.05245
	115	 7	2	  -0.06623
	116	 5	2	  -0.06867
	117	 6	2	  -0.08859
	118	 5	2	  -0.05307
	119	 3	2	  -0.07388
	120	 4	2	  -0.08130
	121	 2	2	  -0.08358
	122	 1	2	  -0.09925
	1072	 19	2	  -0.08417
	1073	 18	2	  -0.08193
	1074	 7	2	  -0.08263
	1075	 17	2	  -0.08979
	1076	 16	2	  -0.06194
	1077	 7	2	  -0.07338
	1078	 5	2	  -0.07355
	1079	 16	2	  -0.04960
	114	 16	3	  -0.09657
	115	 7	3	  -0.05518
	116	 5	3	  -0.04994
	117	 6	3	  -0.10071
	118	 5	3	  -0.03091
	119	 3	3	  -0.06788
	120	 4	3	  -0.05961
	121	 2	3	  -0.05987
	122	 1	3	  -0.06478
	1072	 19	3	  -0.07954
	1073	 18	3	  -0.07722
	1074	 7	3	  -0.07457
	1075	 17	3	  -0.09047
	1076	 16	3	  -0.09797
	1077	 7	3	  -0.06440
	1078	 5	3	  -0.05781
	1079	 16	3	  -0.09086
	114	 16	4	   0.90137
	115	 7	4	   1.23811
	116	 5	4	  -0.10103
	117	 6	4	   0.23483
	118	 5	4	  -0.09134
	119	 3	4	   0.25741
	120	 4	4	  -0.04330
	121	 2	4	   0.36582
	122	 1	4	   0.16343
	1072	 19	4	   2.28194
	1073	 18
	1074	 7	4	   0.84774
	1075	 17	4	   1.00637
	1076	 16	4	   0.71629
	1077	 7	4	   0.98831
	1078	 5	4	  -0.10061
	1079	 16	4	   0.84184
	114	 16
	115	 7	5	   0.36545
	116	 5	5	   1.05519
	117	 6
	118	 5	5	   1.26835
	119	 3
	120	 4	5	   1.32212
	121	 2
	122	 1	5	   0.76246
	1072	 19
	1073	 18
	1074	 7	5	   0.22537
	1075	 17
	1076	 16
	1077	 7	5	   0.27797
	1078	 5	5	   0.86457
	1079	 16
	114	 16
	115	 7
	116	 5
	117	 6
	118	 5
	119	 3
	120	 4
	121	 2
	122	 1
	1072	 19
	1073	 18
	1074	 7
	1075	 17
	1076	 16
	1077	 7
	1078	 5
	1079	 16

	Porsche

	Index	Type	TP	    TARF
	123	 6	1	  -0.11914
	124	 4	1	  -0.11333
	1080	 17	1	  -0.11999
	1081	 10	1	  -0.12185
	1082	 16	1	  -0.11738
	123	 6	2	  -0.08364
	124	 4	2	  -0.07885
	1080	 17	2	  -0.08790
	1081	 10	2	  -0.07763
	1082	 16	2	  -0.06546
	123	 6	3	  -0.09970
	124	 4	3	  -0.05646
	1080	 17	3	  -0.09039
	1081	 10	3	  -0.09357
	1082	 16	3	  -0.10062
	123	 6	4	   0.25858
	124	 4	4	  -0.00656
	1080	 17	4	   1.01121
	1081	 10	4	   1.25290
	1082	 16	4	   0.66800
	123	 6
	124	 4	5	   1.36481
	1080	 17
	1081	 10
	1082	 16
	123	 6
	124	 4
	1080	 17
	1081	 10
	1082	 16

	Suzuki

	Index	Type	TP	    TARF
	125	 5	1	  -0.11610
	126	 1	1	  -0.11149
	1083	 16	1	  -0.11447
	1084	 5	1	  -0.11276
	125	 5	2	  -0.04914
	126	 1	2	  -0.10359
	1083	 16	2	  -0.05143
	1084	 5	2	  -0.05623
	125	 5	3	  -0.02596
	126	 1	3	  -0.07147
	1083	 16	3	  -0.09184
	1084	 5	3	  -0.03669
	125	 5	4	  -0.08853
	126	 1	4	   0.13986
	1083	 16	4	   0.82436
	1084	 5	4	  -0.08947
	125	 5	5	   1.32822
	126	 1	5	   0.70541
	1083	 16
	1084	 5	5	   1.10673
	125	 5
	126	 1
	1083	 16
	1084	 5

	Toyota

	Index	Type	TP	    TARF
	127	 16	1	  -0.11361
	128	 5	1	  -0.11003
	129	 7	1	  -0.10659
	130	 6	1	  -0.11571
	131	 5	1	  -0.11070
	132	 3	1	  -0.10785
	133	 6	1	  -0.11696
	134	 4	1	  -0.10842
	135	 2	1	  -0.08456
	136	 1	1	  -0.10221
	1085	 19	1	  -0.11765
	1086	 18	1	  -0.11161
	1087	 7	1	  -0.10882
	1088	 17	1	  -0.11997
	1089	 16	1	  -0.11065
	1090	 5	1	  -0.10804
	1091	 7	1	  -0.10600
	1092	 16	1	  -0.11052
	127	 16	2	  -0.03457
	128	 5	2	  -0.03676
	129	 7	2	  -0.06255
	130	 6	2	  -0.07661
	131	 5	2	  -0.04196
	132	 3	2	  -0.07053
	133	 6	2	  -0.07943
	134	 4	2	  -0.07181
	135	 2	2	  -0.05367
	136	 1	2	  -0.09453
	1085	 19	2	  -0.08186
	1086	 18	2	  -0.07245
	1087	 7	2	  -0.07525
	1088	 17	2	  -0.08631
	1089	 16	2	  -0.04316
	1090	 5	2	  -0.04685
	1091	 7	2	  -0.06999
	1092	 16	2	  -0.04160
	127	 16	3	  -0.08743
	128	 5	3	  -0.01124
	129	 7	3	  -0.05082
	130	 6	3	  -0.09088
	131	 5	3	  -0.01763
	132	 3	3	  -0.06564
	133	 6	3	  -0.09381
	134	 4	3	  -0.04745
	135	 2	3	  -0.03571
	136	 1	3	  -0.05723
	1085	 19	3	  -0.07709
	1086	 18	3	  -0.06693
	1087	 7	3	  -0.06633
	1088	 17	3	  -0.08707
	1089	 16	3	  -0.08834
	1090	 5	3	  -0.02554
	1091	 7	3	  -0.06038
	1092	 16	3	  -0.08624
	127	 16	4	   1.05022
	128	 5	4	  -0.08086
	129	 7	4	   1.29803
	130	 6	4	   0.30393
	131	 5	4	  -0.08421
	132	 3	4	   0.26709
	133	 6	4	   0.27833
	134	 4	4	   0.08788
	135	 2	4	   0.49191
	136	 1	4	   0.18972
	1085	 19	4	   2.37026
	1086	 18
	1087	 7	4	   0.96159
	1088	 17	4	   1.07611
	1089	 16	4	   0.87427
	1090	 5	4	  -0.08370
	1091	 7	4	   1.04345
	1092	 16	4	   0.92350
	127	 16
	128	 5	5	   1.49599
	129	 7	5	   0.38788
	130	 6
	131	 5	5	   1.42279
	132	 3
	133	 6
	134	 4	5	   1.47129
	135	 2
	136	 1	5	   0.82486
	1085	 19
	1086	 18
	1087	 7	5	   0.26798
	1088	 17
	1089	 16
	1090	 5	5	   1.23362
	1091	 7	5	   0.29860
	1092	 16
	127	 16
	128	 5
	129	 7
	130	 6
	131	 5
	132	 3
	133	 6
	134	 4
	135	 2
	136	 1
	1085	 19
	1086	 18
	1087	 7
	1088	 17
	1089	 16
	1090	 5
	1091	 7
	1092	 16

	Volkswagen

	Index	Type	TP	    TARF
	137	 13	1	  -0.13065
	138	 6	1	  -0.11973
	139	 5	1	  -0.10530
	140	 6	1	  -0.12631
	141	 5	1	  -0.11441
	142	 6	1	  -0.12516
	143	 4	1	  -0.10946
	144	 4	1	  -0.10823
	1093	 17	1	  -0.12144
	1094	 16	1	  -0.11793
	137	 13	2	  -0.10150
	138	 6	2	  -0.08544
	139	 5	2	  -0.02993
	140	 6	2	  -0.09751
	141	 5	2	  -0.05122
	142	 6	2	  -0.09522
	143	 4	2	  -0.07527
	144	 4	2	  -0.07017
	1093	 17	2	  -0.09116
	1094	 16	2	  -0.06704
	137	 13	3	  -0.07879
	138	 6	3	  -0.09813
	139	 5	3	  -0.00599
	140	 6	3	  -0.10884
	141	 5	3	  -0.02884
	142	 6	3	  -0.10725
	143	 4	3	  -0.05187
	144	 4	3	  -0.04532
	1093	 17	3	  -0.09184
	1094	 16	3	  -0.10148
	137	 13	4	  -0.07236
	138	 6	4	   0.25311
	139	 5	4	  -0.08059
	140	 6	4	   0.17774
	141	 5	4	  -0.09008
	142	 6	4	   0.19419
	143	 4	4	   0.03949
	144	 4	4	   0.11191
	1093	 17	4	   0.97671
	1094	 16	4	   0.65245
	137	 13	5	   1.48727
	138	 6
	139	 5	5	   1.49962
	140	 6
	141	 5	5	   1.29492
	142	 6
	143	 4	5	   1.41632
	144	 4	5	   1.49878
	1093	 17
	1094	 16
	137	 13
	138	 6
	139	 5
	140	 6
	141	 5
	142	 6
	143	 4
	144	 4
	1093	 17
	1094	 16