Airworthiness Directives; GROB Aircraft AG Gliders, 5456-5458 [2017-00658]
Download as PDF
5456
Federal Register / Vol. 82, No. 11 / Wednesday, January 18, 2017 / Proposed Rules
(a) Comments Due Date
We must receive comments by March 6,
2017.
884B–17, 892–17, 892B–17, and 895–17
turbofan engines.
damage to the engine, and damage to the
airplane.
(d) Subject
(f) Compliance
(b) Affected ADs
This AD supersedes AD 2012–04–01,
Amendment 39–16956 (77 FR 10355,
February 22, 2012).
Joint Aircraft System Component (JASC)
Code 7200, Engine (Turbine/Turboprop).
Comply with this AD within the
compliance times specified, unless already
done.
(1) After the effective date of this AD,
remove from service the parts listed in Table
1 to paragraph (f) of this AD before exceeding
the new life limit indicated:
(e) Unsafe Condition
(c) Applicability
This AD applies to all Rolls-Royce plc (RR)
RR RB211–Trent 875–17, 877–17, 884–17,
This AD was prompted by RR revising the
life limits of certain critical engine rotating
parts. We are issuing this AD to prevent the
failure of critical engine rotating parts,
TABLE 1 TO PARAGRAPH (f)—REDUCED PART LIVES
Part nomenclature
Part No.
Intermediate Pressure (IP) Compressor Rotor Shaft ..................................................................
IP Compressor Rotor Shaft .........................................................................................................
High-Pressure Compressor (HPC) Stage 1 to 4 Rotor Discs Shaft ...........................................
HPC Stage 1 to 4 Rotor Discs Shaft ...........................................................................................
HPC Stage 1 to 4 Rotor Discs Shaft ...........................................................................................
HPC Stage 1 to 4 Rotor Discs Shaft ...........................................................................................
HPC Stage 1 to 4 Rotor Discs Shaft ...........................................................................................
HPC Stage 5 and 6 Discs and Cone ..........................................................................................
HPC Stage 5 and 6 Discs and Cone ..........................................................................................
IP Turbine Rotor Disc ..................................................................................................................
IP Turbine Rotor Disc ..................................................................................................................
(2) Reserved.
DEPARTMENT OF TRANSPORTATION
(g) Installation Prohibition
After the effective date of this AD, do not
install any IP turbine discs, P/N FK33083,
into any engine.
Federal Aviation Administration
14 CFR Part 39
(h) Alternative Methods of Compliance
(AMOCs)
[Docket No. FAA–2017–0019; Directorate
Identifier 2016–CE–038–AD]
The Manager, Engine Certification Office,
FAA, may approve AMOCs for this AD. Use
the procedures found in 14 CFR 39.19 to
make your request. You may email your
request to: ANE-AD-AMOC@faa.gov.
RIN 2120–AA64
(i) Related Information
mstockstill on DSK3G9T082PROD with PROPOSALS
(1) For more information about this AD,
contact Robert Green, Aerospace Engineer,
Engine Certification Office, FAA, Engine &
Propeller Directorate, 1200 District Avenue,
Burlington, MA 01803; phone: 781–238–
7754; fax: 781–238–7199; email:
robert.green@faa.gov.
(2) Refer to MCAI European Aviation
Safety Agency, AD 2016–0223, dated
November 8, 2016, for more information. You
may examine the MCAI in the AD docket on
the Internet at https://www.regulations.gov by
searching for and locating it in Docket No.
FAA–2010–0755.
Issued in Burlington, Massachusetts, on
January 11, 2017.
Colleen M. D’Alessandro,
Manager, Engine & Propeller Directorate,
Aircraft Certification Service.
[FR Doc. 2017–00890 Filed 1–17–17; 8:45 am]
BILLING CODE 4910–13–P
VerDate Sep<11>2014
16:51 Jan 17, 2017
Jkt 241001
Airworthiness Directives; GROB
Aircraft AG Gliders
Federal Aviation
Administration (FAA), Department of
Transportation (DOT).
ACTION: Notice of proposed rulemaking
(NPRM).
AGENCY:
We propose to adopt a new
airworthiness directive (AD) for GROB
Aircraft AG Models GROB G 109 and
GROB G 109B 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 broken pivots of the tail
wheel mounting bracket resulting from
corrosion and damage due to wear. 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 March 6, 2017.
ADDRESSES: You may send comments by
any of the following methods:
SUMMARY:
PO 00000
Frm 00026
Fmt 4702
Sfmt 4702
FK24100
FK24496
FK24009
FK26167
FK32580
FW11590
FW61622
FK25230
FK27899
FK21117
FK33083
Life in
standard
duty cycles
12,500
8,860
4,560
5,580
5,580
8,550
8,550
5,000
5,000
11,610
0
Life in cycles
using the
HEAVY profile
11,500
8,180
4,460
5,280
5,280
6,850
6,850
5,000
5,000
10,400
0
• Federal eRulemaking Portal: Go to
https://www.regulations.gov. Follow the
instructions for submitting comments.
• Fax: (202) 493–2251.
• Mail: U.S. Department of
Transportation, Docket Operations, M–
30, West Building Ground Floor, Room
W12–140, 1200 New Jersey Avenue SE.,
Washington, DC 20590.
• Hand Delivery: U.S. Department of
Transportation, Docket Operations, M–
30, West Building Ground Floor, Room
W12–140, 1200 New Jersey Avenue SE.,
Washington, DC 20590, between 9 a.m.
and 5 p.m., Monday through Friday,
except Federal holidays.
For service information identified in
this proposed AD, contact GROB
Aircraft AG, Product Support,
Lettenbachstrasse 9, D–86874
Tussenhausen-Mattsies, Germany,
telephone: + 49 (0) 8268–998–105; fax:
+ 49 (0) 8268–998–200; email:
productsupport@grob-aircraft.com;
Internet: grob-aircraft.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 (816) 329–4148.
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–2017–
0019; or in person at the Docket
Management Facility between 9 a.m.
E:\FR\FM\18JAP1.SGM
18JAP1
Federal Register / Vol. 82, No. 11 / Wednesday, January 18, 2017 / Proposed Rules
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 (800) 647–5527) 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: (816) 329–4165; fax: (816)
329–4090; email: jim.rutherford@
faa.gov.
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–2017–0019; Directorate Identifier
2016–CE–038–AD’’ at the beginning of
your comments. We specifically invite
comments on the overall regulatory,
economic, environmental, and energy
aspects of this proposed AD. We will
consider all comments received by the
closing date and may amend this
proposed AD because of those
comments.
We will post all comments we
receive, without change, to https://
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.
mstockstill on DSK3G9T082PROD with PROPOSALS
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.:
2016–0228, dated November 14, 2016
(referred to after this as ‘‘the MCAI’’), to
correct an unsafe condition for the
specified products. The MCAI states:
Occurrences were reported of broken
pivots of the tail wheel mounting bracket.
Subsequent investigation attributed these
events to corrosion and damage due to wear.
This condition, if not detected and
corrected, could lead to loss of rudder
control, resulting in reduced control of the
powered sailplane.
To address this potentially unsafe
condition, Grob Aircraft AG issued
Mandatory Service Bulletin (MSB) 817–70
(hereafter referred to as ‘the MSB’ in this AD)
to provide inspection and repair instructions.
For the reasons described above, this AD
requires repetitive inspections of the tail
wheel mounting bracket and, depending on
findings, accomplishment of applicable
corrective action(s).
VerDate Sep<11>2014
16:51 Jan 17, 2017
Jkt 241001
You may examine the MCAI on the
Internet at https://www.regulations.gov
by searching for and locating Docket No.
FAA–2017–0019.
Related Service Information Under 1
CFR Part 51
GROB Aircraft AG has issued Service
Bulletin No. MSB817–70, dated
September 28, 2016, and GROB Aircraft
AG Repair Instruction RI 817–015, dated
September 16, 2016. In combination,
this service information describes
procedures for inspection of the tail
mounting bracket and instructions for
any necessary repair. 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.
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 57 products of U.S. registry.
We also estimate that it would take
about 3 work-hours per product to
comply with the basic requirements of
this proposed AD. The average labor
rate is $85 per work-hour. Required
parts would cost about $50 per product.
Based on these figures, we estimate
the cost of the proposed AD on U.S.
operators to be $17,385, or $305 per
product.
In addition, we estimate that any
necessary follow-on actions would take
about 5 work-hours and require parts
costing $100, for a cost of $525 per
product. We have no way of
determining the number of products
that may need these actions.
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.
PO 00000
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Fmt 4702
Sfmt 4702
5457
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.
§ 39.13
[Amended]
2. The FAA amends § 39.13 by adding
the following new AD:
■
GROB Aircraft AG: Docket No. FAA–2017–
0019; Directorate Identifier 2016–CE–
038–AD.
E:\FR\FM\18JAP1.SGM
18JAP1
5458
Federal Register / Vol. 82, No. 11 / Wednesday, January 18, 2017 / Proposed Rules
(a) Comments Due Date
We must receive comments by March 6,
2017.
(b) Affected ADs
None.
(c) Applicability
This AD applies to GROB Aircraft AG
Models GROB G 109 and GROB G 109B
gliders, all serial numbers, certificated in any
category.
(d) Subject
Air Transport Association of America
(ATA) Code 32: Landing Gear.
(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 broken
pivots of the tail wheel mounting bracket
resulting from corrosion and damage due to
wear. We are issuing this proposed AD to
detect and correct if necessary any corrosion
or damage to the tail wheel mounting
bracket, which could cause loss of rudder
control and result in reduced control.
mstockstill on DSK3G9T082PROD with PROPOSALS
(f) Actions and Compliance
Unless already done, do the following
actions:
(1) Within the next 3 months after the
effective date of this AD or 100 hours timein-service (TIS) after the effective date of this
AD, whichever occurs first, and repetitively
thereafter at intervals not to exceed every 100
hours TIS or 12 months, whichever occurs
first, inspect the tail wheel mounting bracket
following the Accomplishment Instructions
in section 1.8 of GROB Aircraft AG Service
Bulletin (SB) No. MSB817–70, dated
September 28, 2016.
(2) If any damage is found during any
inspection required in paragraph (f)(1) of this
AD, before further flight, repair following
GROB Aircraft AG Repair Instruction RI 817–
015, dated September 16, 2016.
Note 1 to paragraph (f)(2) of this AD: The
bolt in Figure 1, Pos. 10 of GROB Aircraft AG
Repair Instruction RI 817–015, dated
September 16, 2016, is welded into place
onto the steel base plate. Therefore, in order
to facilitate the removal of the bolt, the
welding seams may be carefully ground off
using caution to not damage the steel base
plate, instead of completely cutting off the
bolt head.
(3) Repairs made as required by paragraph
(f)(2) of this AD do not qualify as terminating
action for the repetitive inspections required
in paragraph (f)(1) 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,
VerDate Sep<11>2014
16:51 Jan 17, 2017
Jkt 241001
Room 301, Kansas City, Missouri 64106;
telephone: (816) 329–4165; fax: (816) 329–
4090; email: jim.rutherford@faa.gov. 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.
(h) Related Information
Refer to MCAI European Aviation Safety
Agency (EASA) AD No.: 2016–0228, dated
November 14, 2016, for related information.
You may examine the MCAI on the Internet
at https://www.regulations.gov by searching
for and locating Docket No. FAA–2017–0019.
For service information related to this AD,
contact GROB Aircraft AG, Product Support,
Lettenbachstrasse 9, D–86874 TussenhausenMattsies, Germany, telephone: + 49 (0) 8268–
998–105; fax: + 49 (0) 8268–998–200; email:
productsupport@grob-aircraft.com; Internet:
grob-aircraft.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 (816) 329–4148.
Issued in Kansas City, Missouri, on January
6, 2017.
Melvin Johnson,
Acting Manager, Small Airplane Directorate,
Aircraft Certification Service.
[FR Doc. 2017–00658 Filed 1–17–17; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF HOUSING AND
URBAN DEVELOPMENT
24 CFR Parts 982 and 983
[Docket No. FR–5976–N–03]
Housing Opportunity Through
Modernization Act of 2016:
Implementation of Various Section 8
Voucher Provisions
Office of the Assistant
Secretary for Public and Indian
Housing, HUD.
ACTION: Implementation and request for
comment.
AGENCY:
On July 29, 2016, President
Obama signed into law the Housing
Opportunity Through Modernization
Act of 2016 (HOTMA). Several of the
statutory amendments made by HOTMA
affect the Project-Based Voucher (PBV)
program or the Housing Choice Voucher
(HCV) program. HOTMA also gave HUD
the authority to implement many of
SUMMARY:
PO 00000
Frm 00028
Fmt 4702
Sfmt 4702
those changes by notice, and those
statutory changes are not effective until
HUD issues that notice. This document
serves as the implementation notice for
several of the provisions of HOTMA that
impact the HCV and PBV programs, and
seeks additional public input on both
the implementing requirements in this
document and future changes to these
programs.
Effective date: April 18, 2017.
Comment due date: March 20, 2017.
ADDRESSES: Interested persons are
invited to submit comments regarding
this document. All communications
must refer to the above docket number
and title. There are two methods for
submitting public comments.
1. Submission of Comments by Mail.
Comments may be submitted by mail to
the Regulations Division, Office of
General Counsel, Department of
Housing and Urban Development, 451
7th Street SW., Room 10276,
Washington, DC 20410–0500.
2. Electronic Submission of
Comments. Interested persons may
submit comments electronically through
the Federal eRulemaking Portal at
www.regulations.gov. HUD strongly
encourages commenters to submit
comments electronically. Electronic
submission of comments allows the
commenter maximum time to prepare
and submit a comment, ensures timely
receipt by HUD, and enables HUD to
make comments immediately available
to the public. Comments submitted
electronically through the
www.regulations.gov Web site can be
viewed by other commenters and
interested members of the public.
Commenters should follow the
instructions provided on that site to
submit comments electronically.
No Facsimile Comments. Facsimile
(fax) comments are not acceptable.
Public Inspection of Public
Comments. All properly submitted
comments and communications
submitted to HUD will be available for
public inspection and copying between
8 a.m. and 5 p.m., weekdays, at the
above address. Due to security measures
at the HUD Headquarters building, an
advance appointment to review the
public comments must be scheduled by
calling the Regulations Division at 202–
708–3055 (this is not a toll-free
number). Individuals with speech or
hearing impairments may access this
number via TTY by calling the Federal
Relay Service at 800–877–8339 (this is
a toll-free number). Copies of all
comments submitted are available for
inspection and downloading at
www.regulations.gov.
DATES:
E:\FR\FM\18JAP1.SGM
18JAP1
Agencies
[Federal Register Volume 82, Number 11 (Wednesday, January 18, 2017)]
[Proposed Rules]
[Pages 5456-5458]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2017-00658]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2017-0019; Directorate Identifier 2016-CE-038-AD]
RIN 2120-AA64
Airworthiness Directives; GROB Aircraft AG Gliders
AGENCY: Federal Aviation Administration (FAA), Department of
Transportation (DOT).
ACTION: Notice of proposed rulemaking (NPRM).
-----------------------------------------------------------------------
SUMMARY: We propose to adopt a new airworthiness directive (AD) for
GROB Aircraft AG Models GROB G 109 and GROB G 109B 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 broken pivots of the tail wheel
mounting bracket resulting from corrosion and damage due to wear. 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 March 6, 2017.
ADDRESSES: You may send comments by any of the following methods:
Federal eRulemaking Portal: Go to https://www.regulations.gov. Follow the instructions for submitting comments.
Fax: (202) 493-2251.
Mail: U.S. Department of Transportation, Docket
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New
Jersey Avenue SE., Washington, DC 20590.
Hand Delivery: U.S. Department of Transportation, Docket
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New
Jersey Avenue SE., Washington, DC 20590, between 9 a.m. and 5 p.m.,
Monday through Friday, except Federal holidays.
For service information identified in this proposed AD, contact
GROB Aircraft AG, Product Support, Lettenbachstrasse 9, D-86874
Tussenhausen-Mattsies, Germany, telephone: + 49 (0) 8268-998-105; fax:
+ 49 (0) 8268-998-200; email: aircraft.com">productsupport@grob-aircraft.com;
Internet: grob-aircraft.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 (816) 329-4148.
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-2017-
0019; or in person at the Docket Management Facility between 9 a.m.
[[Page 5457]]
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 (800) 647-5527) 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: (816) 329-4165; fax: (816) 329-4090; email:
jim.rutherford@faa.gov.
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-2017-0019;
Directorate Identifier 2016-CE-038-AD'' at the beginning of your
comments. We specifically invite comments on the overall regulatory,
economic, environmental, and energy aspects of this proposed AD. We
will consider all comments received by the closing date and may amend
this proposed AD because of those comments.
We will post all comments we receive, without change, to https://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.: 2016-0228, dated November 14, 2016 (referred to after this as
``the MCAI''), to correct an unsafe condition for the specified
products. The MCAI states:
Occurrences were reported of broken pivots of the tail wheel
mounting bracket. Subsequent investigation attributed these events
to corrosion and damage due to wear.
This condition, if not detected and corrected, could lead to
loss of rudder control, resulting in reduced control of the powered
sailplane.
To address this potentially unsafe condition, Grob Aircraft AG
issued Mandatory Service Bulletin (MSB) 817-70 (hereafter referred
to as `the MSB' in this AD) to provide inspection and repair
instructions.
For the reasons described above, this AD requires repetitive
inspections of the tail wheel mounting bracket and, depending on
findings, accomplishment of applicable corrective action(s).
You may examine the MCAI on the Internet at https://www.regulations.gov by searching for and locating Docket No. FAA-2017-
0019.
Related Service Information Under 1 CFR Part 51
GROB Aircraft AG has issued Service Bulletin No. MSB817-70, dated
September 28, 2016, and GROB Aircraft AG Repair Instruction RI 817-015,
dated September 16, 2016. In combination, this service information
describes procedures for inspection of the tail mounting bracket and
instructions for any necessary repair. 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.
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 57 products of U.S.
registry. We also estimate that it would take about 3 work-hours per
product to comply with the basic requirements of this proposed AD. The
average labor rate is $85 per work-hour. Required parts would cost
about $50 per product.
Based on these figures, we estimate the cost of the proposed AD on
U.S. operators to be $17,385, or $305 per product.
In addition, we estimate that any necessary follow-on actions would
take about 5 work-hours and require parts costing $100, for a cost of
$525 per product. We have no way of determining the number of products
that may need these actions.
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:
GROB Aircraft AG: Docket No. FAA-2017-0019; Directorate Identifier
2016-CE-038-AD.
[[Page 5458]]
(a) Comments Due Date
We must receive comments by March 6, 2017.
(b) Affected ADs
None.
(c) Applicability
This AD applies to GROB Aircraft AG Models GROB G 109 and GROB G
109B gliders, all serial numbers, certificated in any category.
(d) Subject
Air Transport Association of America (ATA) Code 32: Landing
Gear.
(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 broken pivots of
the tail wheel mounting bracket resulting from corrosion and damage
due to wear. We are issuing this proposed AD to detect and correct
if necessary any corrosion or damage to the tail wheel mounting
bracket, which could cause loss of rudder control and result in
reduced control.
(f) Actions and Compliance
Unless already done, do the following actions:
(1) Within the next 3 months after the effective date of this AD
or 100 hours time-in-service (TIS) after the effective date of this
AD, whichever occurs first, and repetitively thereafter at intervals
not to exceed every 100 hours TIS or 12 months, whichever occurs
first, inspect the tail wheel mounting bracket following the
Accomplishment Instructions in section 1.8 of GROB Aircraft AG
Service Bulletin (SB) No. MSB817-70, dated September 28, 2016.
(2) If any damage is found during any inspection required in
paragraph (f)(1) of this AD, before further flight, repair following
GROB Aircraft AG Repair Instruction RI 817-015, dated September 16,
2016.
Note 1 to paragraph (f)(2) of this AD: The bolt in Figure 1,
Pos. 10 of GROB Aircraft AG Repair Instruction RI 817-015, dated
September 16, 2016, is welded into place onto the steel base plate.
Therefore, in order to facilitate the removal of the bolt, the
welding seams may be carefully ground off using caution to not
damage the steel base plate, instead of completely cutting off the
bolt head.
(3) Repairs made as required by paragraph (f)(2) of this AD do
not qualify as terminating action for the repetitive inspections
required in paragraph (f)(1) 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: (816) 329-4165; fax: (816) 329-4090; email:
jim.rutherford@faa.gov. 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.
(h) Related Information
Refer to MCAI European Aviation Safety Agency (EASA) AD No.:
2016-0228, dated November 14, 2016, for related information. You may
examine the MCAI on the Internet at https://www.regulations.gov by
searching for and locating Docket No. FAA-2017-0019. For service
information related to this AD, contact GROB Aircraft AG, Product
Support, Lettenbachstrasse 9, D-86874 Tussenhausen-Mattsies,
Germany, telephone: + 49 (0) 8268-998-105; fax: + 49 (0) 8268-998-
200; email: aircraft.com">productsupport@grob-aircraft.com; Internet: grob-
aircraft.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 (816) 329-4148.
Issued in Kansas City, Missouri, on January 6, 2017.
Melvin Johnson,
Acting Manager, Small Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 2017-00658 Filed 1-17-17; 8:45 am]
BILLING CODE 4910-13-P