[Federal Register: June 28, 2011 (Volume 76, Number 124)]
[Proposed Rules]
[Page 37684-37686]
[DOCID:fr28jn11-27]

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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2011-0687; Directorate Identifier 2011-CE-017-AD]
RIN 2120-AA64

Airworthiness Directives; Diamond Aircraft Industries GmbH Model
(Diamond) DA 40 Airplanes Equipped With Certain Cabin Air Conditioning
Systems

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Notice of proposed rulemaking (NPRM).

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SUMMARY: We propose to adopt a new airworthiness directive (AD) for the
products listed above. This proposed AD would require deactivation and
removal of the vapor cycle system (VCS) installed per STC SA03674AT
held by Premier Aircraft Services (originally held by DER Services)
following DER Services Master Document List MDL-2006-020-1, Revision C,
dated February 3, 2009; Revision D, dated April 22, 2009; Revision E,
dated May 12, 2010; or Revision F, dated July 6, 2010. This proposed AD
would also require revision to the airplane weight and balance. This
proposed AD was prompted by reports of damage around the VCS compressor
mounting areas found during maintenance inspections. We are proposing
this AD to remove the VCS mount, which could result in the air
conditioner compressor

disconnecting in the engine compartment. This condition could result in
engine stoppage or additional damage to the engine.

DATES: We must receive comments on this proposed AD by August 12, 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: Deliver to Mail address above between 9
a.m. and 5 p.m., Monday through Friday, except Federal holidays.
    For service information identified in this proposed AD, contact
Premier Aircraft Service, 5540 NW. 23 Avenue Hangar 14, Ft. Lauderdale,
FL 33309, telephone:<PHONE_NUMBER>; fax:<PHONE_NUMBER>; Internet:
http://www.flypas.com. You may review copies of the referenced service
information at the FAA, Small Airplane Directorate, 901 Locust St.,
Kansas City, Missouri 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 proposed 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: Hal Horsburgh, Aerospace Engineer,
FAA, Atlanta Aircraft Certification Office, 1701 Columbia Avenue,
College Park, Georgia 30337; telephone:<PHONE_NUMBER>; fax: (404) 474-
5606; e-mail<EMAIL_ADDRESS>
SUPPLEMENTARY INFORMATION:

Comments Invited

    We invite you to send any written relevant data, views, or
arguments about this proposal. Send your comments to an address listed
under the ADDRESSES section. Include ``Docket No. FAA-2011-0687,
Directorate Identifier 2011-CE-017-AD'' at the beginning of your
comments. We specifically invite comments on the overall regulatory,
economic, environmental, and energy aspects of this proposed AD. We
will consider all comments received by the closing date and may amend
this proposed AD because of those comments.
    We will post all comments we receive, without change, to 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 proposed AD.

Discussion

    We received reports of damage found during maintenance inspections
of the Diamond Model DA 40 airplanes equipped with a VCS installed per
Premier Aircraft Service STC SA03674AT held by Premier Aircraft
Services (originally held by DER Services) following DER Services
Master Document List MDL-2006-020-1, Revision C, dated February 3,
2009; Revision D, dated April 22, 2009; Revision E, dated May 12, 2010;
or Revision F, dated July 6, 2010. The damage included excessive wear
in the VCS compressor mounting holes, mounting brackets, and the
mounting bolt, and denting was found around the mounting bracket and
compressor due to unintended relative motion. We are proposing this AD
to remove the VCS mount, which could result in the air conditioner
compressor disconnecting in the engine compartment. This condition
could result in engine stoppage or additional damage to the engine.

Relevant Service Information

    We reviewed Premier Aircraft Service Work Instruction PAS-WI-MSB-
40-2011-001, dated March 4, 2011; and Premier Aircraft Service
Mandatory Service Bulletin No. PAS-MSB-40-2011-001, dated March 4,
2011. The service information describes procedures for deactivation of
the VCS Compressor and associated mounting hardware and the removal of
the VCS installed per Premier Aircraft Service STC SA03674AT.

FAA's Determination

    We are proposing 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.

Proposed AD Requirements

    This proposed AD would require deactivation of the VCS Compressor
and removal of the VCS and the associated mounting hardware, except as
discussed under ``Differences Between the Proposed AD and the Service
Information.''

Differences Between the Proposed AD and the Service Information

    The service information requires compliance prior to flight after
effectivity of the service information. The service information also
includes a reporting requirement.
    This proposed AD requires a compliance time of within the next 100
hours time-in-service after installation of the STC or 30 days after
the effective date of this proposed AD, whichever occurs later. We are
not including the reporting requirement.

Costs of Compliance

    We estimate that this proposed AD affects 11 airplanes of U.S.
registry.
    We estimate the following costs to comply with this proposed AD:

                                                 Estimated Costs
----------------------------------------------------------------------------------------------------------------
                                                                                Cost per      Cost on U.S.
              Action                      Labor cost             Parts cost           product        operators
----------------------------------------------------------------------------------------------------------------
Remove the VCS compressor,          3 work-hours x $85     Not applicable.......            $255          $2,805
 deactivate system, and revise       per hour = $255
 weight and balance.
----------------------------------------------------------------------------------------------------------------

Authority for This Rulemaking

    Title 49 of the United States Code specifies the FAA's authority to
issue rules on aviation safety. Subtitle I, section 106, describes the
authority of the FAA Administrator. Subtitle VII: Aviation Programs,
describes in more detail the scope of the Agency's authority.
    We are issuing this rulemaking under the authority described in
Subtitle VII,

Part A, Subpart III, Section 44701: ``General requirements.'' Under
that section, Congress charges the FAA with promoting safe flight of
civil aircraft in air commerce by prescribing regulations for
practices, methods, and procedures the Administrator finds necessary
for safety in air commerce. This regulation is within the scope of that
authority because it addresses an unsafe condition that is likely to
exist or develop on products identified in this rulemaking action.

Regulatory Findings

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

The Proposed Amendment

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

PART 39--AIRWORTHINESS DIRECTIVES

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

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

Sec.  39.13  [Amended]

    2. The FAA amends Sec.  39.13 by adding the following new
airworthiness directive (AD):

Diamond Aircraft Industries GmbH Model (Diamond) DA 40 Airplanes
Equipped With Certain Cabin Air Conditioning Systems: Docket No.
FAA-2011-0687; Directorate Identifier 2011-CE-017-AD.

Comments Due Date

    (a) We must receive comments by August 12, 2011.

Affected ADs

    (b) None.

Applicability

    (c) This AD applies to Diamond Aircraft Industries GmbH Model DA
40 airplanes, all serial numbers that:
    (1) Are equipped with vapor cycle system (VCS) cabin air
conditioning systems installed per Premier Aircraft Services
Supplemental Type Certificate (STC) SA03674AT following DER Services
Master Document List MDL-2006-020-1, Revision C, dated February 3,
2009; Revision D, dated April 22, 2009; Revision E, dated May 12,
2010; or Revision F, dated July 6, 2010; and
    (2) Are certificated in any category.

Subject

    (d) Joint Aircraft System Component (JASC) Code 2150, Cabin
Cooling System.

Unsafe Condition

    (e) This AD was prompted by reports of damage around the VCS
compressor mounting area found during maintenance inspections. We
are proposing this AD to remove the VCS compressor and mount, as a
result of excessive wear, which could result in the air conditioner
compressor disconnecting in the engine compartment. This condition
could result in engine stoppage or additional damage to the engine.

Compliance

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

Required Actions

    (g) Within the next 100 hours time-in-service after installation
of the VCS installed per STC SA03674AT held by Premier Aircraft
Services (originally held by DER Services) following DER Services
Master Document List MDL-2006-020-1, Revision C, dated February 3,
2009; Revision D, dated April 22, 2009; Revision E, dated May 12,
2010; or Revision F, dated July 6, 2010, or within 30 days after the
effective date of this AD, whichever occurs later, do the following
actions following Premier Aircraft Service Work Instruction PAS-WI-
MSB-40-2011-001, dated March 4, 2011; and Premier Aircraft Service
Mandatory Service Bulletin No. PAS-MSB-40-2011-001, dated March 4,
2011:
    (1) Deactivate the VCS system.
    (2) Pull and collar the compressor breaker and place a placard
above the breaker stating ``INOP.''
    (3) Remove the VCS compressor and associated mounting hardware.
    (4) Revise the airplane weight and balance.

Special Flight Permit

    (h) The compressor drive belt must be cut and removed before the
airplane may be moved for one ferry flight to an approved repair
facility to comply with the remainder of this proposed AD.

Alternative Methods of Compliance (AMOCs)

    (i)(1) The Manager, Atlanta 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 appropriate
principal inspector, or lacking a principal inspector, the manager
of the local flight standards district office/certificate holding
district office.

Related Information

    (j) For more information about this AD, contact Hal Horsburgh,
Aerospace Engineer, FAA, Atlanta ACO, 1701 Columbia Avenue, College
Park, Georgia 30337; telephone:<PHONE_NUMBER>; fax:<PHONE_NUMBER>;
e-mail<EMAIL_ADDRESS>    (k) For service information identified in this AD, contact
Premier Aircraft Service, 5540 NW. 23 Avenue Hangar 14, Ft.
Lauderdale, FL 33309, telephone:<PHONE_NUMBER>; fax: (954) 334-
1489; Internet: http://www.flypas.com. You may review copies of the
referenced service information at the FAA, Small Airplane
Directorate, 901 Locust, Kansas City, MO 64106. For information on
the availability of this material at the FAA, call<PHONE_NUMBER>.

    Issued in Kansas City, Missouri, on June 22, 2011.
John Colomy,
Acting Manager, Small Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 2011-16137 Filed 6-27-11; 8:45 am]
BILLING CODE 4910-13-P


[Federal Register Volume 79, Number 98 (Wednesday, May 21, 2014)]
[Rules and Regulations]
[Pages 29100-29101]
[FR Doc No: 2014-11802]

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DEPARTMENT OF HOMELAND SECURITY

Coast Guard

33 CFR Part 165

[Docket No. USCG-2014-0173]

Safety Zone; Red, White, and Tahoe Blue Fireworks, Incline
Village, NV

AGENCY: Coast Guard, DHS.

ACTION: Notice of enforcement of regulation.

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SUMMARY: The Coast Guard will enforce the safety zone for the Red,
White, and Tahoe Blue Fireworks display in the Captain of the Port, San
Francisco area of responsibility during the dates and times noted
below. This action is necessary to protect life and property of the
maritime public from the hazards associated with the fireworks display.
During the enforcement period, unauthorized persons or vessels are
prohibited from entering into, transiting through, or anchoring in the
safety zone, unless authorized by the Patrol Commander (PATCOM).

DATES: The regulations in 33 CFR 165.1191, Table 1, Item number 19,
will be enforced from 7 a.m. on June 29, 2014 through 10:45 p.m. on
July 4, 2014.

FOR FURTHER INFORMATION CONTACT: If you have questions on this notice,
call or email Lieutenant Junior Grade Joshua Dykman, Sector San
Francisco Waterways Safety Division, U.S. Coast Guard; telephone 415-
399-3585, email<EMAIL_ADDRESS>
SUPPLEMENTARY INFORMATION: The Coast Guard will enforce a safety zone
in navigable waters around and under the fireworks barges within a
radius of 100 feet during the loading, transit, and arrival of the
fireworks barges to the display location and until the start of the
fireworks display. From 7 a.m. on June 29, 2014 until 8 p.m. on July 4,
2014 the fireworks barges will be loaded off of Incline Beach, near
Incline Village, NV at approximate position 39[deg]14'21'' N,
119[deg]56'51'' W (NAD 83). From 8 p.m. to 9 p.m. on July 4, 2014 the
loaded barges will transit from Incline Beach to the launch site off of
Incline Village, NV at approximate position 39[deg]14'14'' N,
119[deg]56'56'' W (NAD 83) where it will remain until the commencement
of the fireworks display. Upon the commencement of the 30 minute
fireworks display, scheduled to take place between 9 p.m. and 10 p.m.
on July 4, 2014, the safety zone will increase in size to encompass the
navigable waters around and under the fireworks barges within a radius
1,000 feet at approximate position 39[deg]14'14'' N, 119[deg]56'56'' W
(NAD 83) for the Red, White, and Tahoe Blue Fireworks, Incline Village,
NV in 33 CFR 165.1191, Table 1, Item number 19. This safety zone will
be in effect from 7 a.m. on June 29, 2014 until 10:45 p.m. on July 4,
2014.
    Under the provisions of 33 CFR 165.1191, unauthorized persons or
vessels are prohibited from entering into, transiting through, or
anchoring in the safety zone during all applicable effective dates and
times, unless authorized to do so by the PATCOM. Additionally, each
person who receives notice of a lawful order or direction issued by an
official patrol vessel shall obey the order or direction. The PATCOM is
empowered to forbid entry into and control the regulated area. The
PATCOM shall be designated by the Commander, Coast Guard Sector San
Francisco. The PATCOM may, upon request, allow the transit of
commercial vessels through regulated areas when it is safe to do so.
    This notice is issued under authority of 33 CFR 165.1191 and 5
U.S.C. 552(a). In addition to this notice in the Federal Register, the
Coast Guard will provide the maritime community with extensive advance
notification of the safety zone and its enforcement period via the
Local Notice to Mariners.
    If the Captain of the Port determines that the regulated area need
not be enforced for the full duration stated in this notice, a
Broadcast Notice to Mariners may be used to grant general permission to
enter the regulated area.

    Dated: April 29, 2014.
Gregory G. Stump,
Captain, U.S. Coast Guard, Captain of the Port San Francisco.
[FR Doc. 2014-11802 Filed 5-20-14; 8:45 am]
BILLING CODE 9110-04-P


[Federal Register Volume 80, Number 153 (Monday, August 10, 2015)]
[Proposed Rules]
[Pages 47871-47874]
[FR Doc No: 2015-19323]

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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2015-3300; Directorate Identifier 2015-CE-024-AD]
RIN 2120-AA64

Airworthiness Directives; Fiberglas-Technik Rudolf Lindner GmbH &
Co. KG Gliders

AGENCY: Federal Aviation Administration (FAA), Department of
Transportation (DOT).

ACTION: Notice of proposed rulemaking (NPRM).

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SUMMARY: We propose to adopt a new airworthiness directive (AD) for
Fiberglas-Technik Rudolf Lindner GmbH & Co. KG Model G103 TWIN ASTIR,
G103 TWIN II, and G103A TWIN II ACRO gliders. This proposed AD results
from mandatory continuing airworthiness information (MCAI) originated
by an aviation authority of another country to identify and correct an
unsafe condition on an aviation product. The MCAI describes the unsafe
condition as a broken bell-crank installed in the air brake control
system. We are issuing this proposed AD to require actions to address
the unsafe condition on these products.

DATES: We must receive comments on this proposed AD by September 24,
2015.

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 proposed AD, contact
Fiberglas-Technik Rudolf Lindner GmbH & Co.KG, Steige 3, D-88487
Walpertshofen, Germany; phone: ++49

(0) 7353/22 43; fax: ++49 (0) 7353/30 96; email<EMAIL_ADDRESS>
internet: http://www.ltb-lindner.com/. You may review this referenced
service information at the FAA, Small Airplane Directorate, 901 Locust,
Kansas City, Missouri 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 by searching for and locating Docket No. FAA-2015-
3300; 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 proposed AD, the regulatory evaluation, any comments
received, and other information. The street address for the Docket
Office (telephone<PHONE_NUMBER>) is in the ADDRESSES section. Comments
will be available in the AD docket shortly after receipt.

FOR FURTHER INFORMATION CONTACT: Jim Rutherford, Aerospace Engineer,
FAA, Small Airplane Directorate, 901 Locust, Room 301, Kansas City,
Missouri 64106; telephone:<PHONE_NUMBER>; fax:<PHONE_NUMBER>; email:
<EMAIL_ADDRESS>
SUPPLEMENTARY INFORMATION:

Comments Invited

    We invite you to send any written relevant data, views, or
arguments about this proposed AD. Send your comments to an address
listed under the ADDRESSES section. Include ``Docket No. FAA-2015-3300;
Directorate Identifier 2015-CE-024-AD'' at the beginning of your
comments. We specifically invite comments on the overall regulatory,
economic, environmental, and energy aspects of this proposed AD. We
will consider all comments received by the closing date and may amend
this proposed AD because of those comments.
    We will post all comments we receive, without change, to http://regulations.gov, including any personal information you provide. We
will also post a report summarizing each substantive verbal contact we
receive about this proposed AD.

Discussion

    The European Aviation Safety Agency (EASA), which is the Technical
Agent for the Member States of the European Community, has issued EASA
AD No.: 2015-0116, dated June 24, 2015 (referred to after this as ``the
MCAI''), to correct an unsafe condition for the specified products. The
MCAI states:

    A report was received concerning a broken bell-crank, installed
in the air brake control circuit approximately 1.4 m outside the
wing root rib of a GROB G 103 Twin II sailplane. Preliminary
investigation results revealed additional cases of cracks on the
same part, installed in the air brake control systems of the early
Twin II type design.
    The same bell-cranks are also installed at the same location in
the control systems of other models belonging to the same type
design (see list of affected models under Applicability).
    This condition, if not detected and corrected, could lead to
failure of the air brake system, possibly resulting in reduced
control of the sailplane.
    To address this potential unsafe condition, Fiberglas-Technik
issued Technische Mitteilung (TM)/Service Bulletin (SB) TM-G08/SB-
G08 (one document) and Anweisung (A)/Instructions (I) A/I-G08 (one
document) to provide instructions for a check of the air brake
locking forces, the inspection of the bell-crank and, if cracks are
found, replacement of the bell-crank.
    Additionally, TM-G07/SB-G07 (one document) and A/I-G07 (one
document) provide instructions for the installation of inspection
openings in the wing of GROB G 103 TWIN II and G 103 A TWIN II ACRO
sailplanes to facilitate the inspection of the bell-crank. (For the
TWIN ASTIR and TWIN ASTIR TRAINER sailplanes, such an opening is
required by LBA AD 92-190/2 (GROB SB 315- 45/2.) This installation
is optional for sailplanes not exceeding the original intended life
limit.
    For the reason described above, this AD requires a check of the
air brake locking forces, an inspection for cracks in the air brake
control unit and, if cracks are found, replacement of the affected
flight control system parts. This AD is a temporary measure and
further AD action may follow.

    You may examine the MCAI on the Internet at http://www.regulations.gov by searching for and locating Docket No. FAA-2015-
3300.

Related Service Information Under 1 CFR Part 51

    Fiberglas-Technik Rudolf Lindner GmbH & Co. KG has issued
Fiberglas-Technik Rudolf Lindner Technische Mitteilung (English
translation: Service Bulletin), (TM-G08)/(SB-G08), Ausgabe (English
translation: Edition) April 24, 2015; and Fiberglas-Technik Rudolf
Lindner Anweisung (English translation: Instructions), (A/I-G08),
Ausgabe (English translation: Edition) April 24, 2015. The service
information describes procedures for inspecting the air brake locking
forces; inspecting the bell-crank; and, if cracks are found during the
inspections, replacing the bell-crank. 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 of this NPRM.

Interim Action

    We consider this AD interim action. The design approval holder is
working toward a terminating action for the inspections. We may take
further AD action in the future.

FAA's Determination and Requirements of the Proposed AD

    This product has been approved by the aviation authority of another
country, and is approved for operation in the United States. Pursuant
to our bilateral agreement with this State of Design Authority, they
have notified us of the unsafe condition described in the MCAI and
service information referenced above. We are proposing this AD because
we evaluated all information and determined the unsafe condition exists
and is likely to exist or develop on other products of the same type
design.

Costs of Compliance

    We estimate that this proposed AD will affect 106 products of U.S.
registry. We also estimate that it would take about 2 work-hours per
product to comply with the basic requirements of this proposed AD. The
average labor rate is $85 per work-hour.
    Based on these figures, we estimate the cost of the proposed AD on
U.S. operators to be $18,020, or $170 per product.
    In addition, we estimate that any necessary follow-on actions would
be as follows:
     Replacement of bell-crank would take about 5 work-hours
per product. Required parts would cost about $566 for a total of $991
per product.
     Installation of optional inspection openings would take
about 15 work-hours per product. Required parts would cost about $1,004
for a total of $2,279 per product.
    We have no way of determining the number of products that may need
these actions.

Paperwork Reduction Act

    A federal agency may not conduct or sponsor, and a person is not
required to respond to, nor shall a person be subject to penalty for
failure to comply with a collection of information subject to the
requirements of the Paperwork Reduction Act unless that collection of
information displays a current valid OMB control number. The control
number for the collection of information required by this AD is 2120-
0056. The paperwork cost associated with this AD has been detailed in
the Costs of Compliance section of this document and includes time for
reviewing instructions, as well as completing and

reviewing the collection of information. Therefore, all reporting
associated with this AD is mandatory. Comments concerning the accuracy
of this burden and suggestions for reducing the burden should be
directed to the FAA at 800 Independence Ave. SW., Washington, DC 20591.
ATTN: Information Collection Clearance Officer, AES-200.

Authority for This Rulemaking

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

Regulatory Findings

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

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 AD:

Fiberglas-Technik Rudolf Lindner GmbH & Co. KG: Docket No. FAA-2015-
3300; Directorate Identifier 2015-CE-024-AD.

(a) Comments Due Date

    We must receive comments by September 24, 2015.

(b) Affected ADs

    None.

(c) Applicability

    This AD applies to Fiberglas-Technik Rudolf Lindner GmbH & Co.
KG Model G103 TWIN ASTIR, G103 TWIN II, and G103A TWIN II ACRO
gliders, all manufacturer serial numbers, certificated in any
category.

(d) Subject

    Air Transport Association of America (ATA) Code 27: Flight
Controls.

(e) Reason

    This AD was prompted by mandatory continuing airworthiness
information (MCAI) originated by an aviation authority of another
country to identify and correct an unsafe condition on an aviation
product. The MCAI describes the unsafe condition as a broken bell-
crank installed in the air brake control system. We are issuing this
AD to detect and correct a broken bell-crank which could lead to
failure of the air brake system, possibly resulting in reduced
control.

(f) Actions and Compliance

    Unless already done, do the following actions:
    (1) Within 30 days after the effective date of this AD and
repetitively thereafter at intervals not to exceed 12 months,
inspect the locking forces of the air brake control unit, and, if
any discrepancy is found, before further flight, correct the locking
forces. Do the inspection and correction of any discrepancy
following the instructions of Fiberglas-Technik Rudolf Lindner
Technische Mitteilung (English translation: Service Bulletin), (TM-
G08)/(SB-G08), Ausgabe (English translation: Edition) April 24,
2015; and Fiberglas-Technik Rudolf Lindner Anweisung (English
translation: Instructions), (A/I-G08), Ausgabe (English translation:
Edition) April 24, 2015.

    Note 1 to paragraph (f)(1) of this AD:  This service information
contains German to English translation. The European Aviation Safety
Agency (EASA) used the English translation in referencing the
document. For enforceability purposes, we will refer to the
Fiberglas-Technik Rudolf Lindner service information as it appears
on the document.

    (2) Within 60 days after the effective date of this AD, inspect
the bell-crank installed in the air brake control system, and, if
any cracks are found, before further flight, replace the bell-crank
with a serviceable part. Do the inspection and replacement following
the instructions of Fiberglas-Technik Rudolf Lindner Technische
Mitteilung (English translation: Service Bulletin), (TM-G08)/(SB-
G08), Ausgabe (English translation: Edition) April 24, 2015; and
Fiberglas-Technik Rudolf Lindner Anweisung (English translation:
Instructions), (A/I-G08), Ausgabe (English translation: Edition)
April 24, 2015.

    Note 2 to paragraph (f)(1) of this AD:  In the lower wing
surface inspection, openings near the bell-crank may be installed to
simplify the inspection and make a possible replacement of the bell-
crank possible. This optional installation is described in GROB Luft
Und Raumfahrt Service Bulletin 315-45/2, dated December 21, 1995;
and Fiberglas-Technik Rudolf Lindner Technische Mitteilung (English
translation: Service Bulletin), (TM-G07)/(SB-G07), Ausgabe (English
translation: Edition) April 24, 2015.

    (3) Within 30 days after replacing a bell-crank as required by
paragraph (f)(2) of this AD, report the inspection results of the
removed bell-crank to Fiberglas-Technik Rudolf Lindner GmbH & Co.
KG. You may find contact information for Fiberglas-Technik Rudolf
Lindner GmbH & Co. KG in paragraph (h) of this AD.

(g) Other FAA AD Provisions

    The following provisions also apply to this AD:
    (1) Alternative Methods of Compliance (AMOCs): The Manager,
Standards Office, FAA, has the authority to approve AMOCs for this
AD, if requested using the procedures found in 14 CFR 39.19. Send
information to ATTN: Jim Rutherford, Aerospace Engineer, FAA, Small
Airplane Directorate, 901 Locust, Room 301, Kansas City, Missouri
64106; telephone:<PHONE_NUMBER>; fax:<PHONE_NUMBER>; email:
<EMAIL_ADDRESS>Before using any approved AMOC on any
airplane to which the AMOC applies, notify your appropriate
principal inspector (PI) in the FAA Flight Standards District Office
(FSDO), or lacking a PI, your local FSDO.
    (2) Airworthy Product: For any requirement in this AD to obtain
corrective actions from a manufacturer or other source, use these
actions if they are FAA-approved. Corrective actions are considered
FAA-approved if they are approved by the State of Design Authority
(or their delegated agent). You are required to assure the product
is airworthy before it is returned to service.
    (3) Reporting Requirements: For any reporting requirement in
this AD, a federal agency may not conduct or sponsor, and a person
is not required to respond to, nor shall a person be subject to a
penalty for failure to comply with a collection of information
subject to the requirements of the Paperwork Reduction Act unless
that collection of information displays a current valid OMB Control
Number. The OMB Control Number for this information

collection is 2120-0056. Public reporting for this collection of
information is estimated to be approximately 5 minutes per response,
including the time for reviewing instructions, completing and
reviewing the collection of information. All responses to this
collection of information are mandatory. Comments concerning the
accuracy of this burden and suggestions for reducing the burden
should be directed to the FAA at: 800 Independence Ave. SW.,
Washington, DC 20591, Attn: Information Collection Clearance
Officer, AES-200.

(h) Related Information

    Refer to MCAI EASA AD No.: 2015-0116, dated June 24, 2015; GROB
Luft Und Raumfahrt Service Bulletin 315-45/2, dated December 21,
1995; and Fiberglas-Technik Rudolf Lindner Technische Mitteilung
(English translation: Service Bulletin), (TM-G07)/(SB-G07), Ausgabe
(English translation: Edition) April 24, 2015, for related
information. You may examine the MCAI on the Internet at http://www.regulations.gov by searching for and locating Docket No. FAA-
2015-3300. For service information related to this AD, contact
Fiberglas-Technik Rudolf Lindner GmbH & Co. KG, Steige 3, D-88487
Walpertshofen, Germany; phone: ++49 (0) 7353/22 43; fax: ++49 (0)
7353/30 96; email<EMAIL_ADDRESS>internet: http://www.ltb-lindner.com/. You may review this referenced service information at
the FAA, Small Airplane Directorate, 901 Locust, Kansas City,
Missouri 64106. For information on the availability of this material
at the FAA, call<PHONE_NUMBER>.

    Issued in Kansas City, Missouri, on July 31, 2015.
Earl Lawrence,
Manager, Small Airplane Directorate, Aircraft Certification Service.
[FR Doc. 2015-19323 Filed 8-7-15; 8:45 am]
 BILLING CODE 4910-13-P