Airworthiness Directives; GA 8 Airvan (Pty) Ltd Airplanes, 46900-46902 [2018-19889]
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Federal Register / Vol. 83, No. 180 / Monday, September 17, 2018 / Proposed Rules
(ii) Reserved.
DEPARTMENT OF TRANSPORTATION
(h) Definition
For the purpose of this AD, an ‘‘engine
shop visit’’ is the induction of an engine into
the shop for maintenance involving the
separation of pairs of major mating engine
flanges, or any removal of the RGB assembly.
(1) The Manager, ECO 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 the attention of the person
identified in paragraph (j)(1) of this AD. You
may email your request to: ANE-AD-AMOC@
faa.gov.
(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.
(j) Related Information
(1) For more information about this AD,
contact Barbara Caufield, Aerospace
Engineer, ECO Branch, FAA, 1200 District
Avenue, Burlington, MA 01803; phone: 781–
238–7146; fax: 781–238–7199; email:
barbara.caufield@faa.gov.
(2) Refer to Transport Canada AD CF–
2015–01R1, dated November 18, 2016, for
more information. You may examine the
Transport Canada AD in the AD docket on
the internet at https://www.regulations.gov by
searching for and locating it in Docket No.
FAA–2018–0739.
(3) For service information identified in
this AD, contact Pratt & Whitney Canada
Corp., 1000 Marie-Victorin, Longueuil,
Quebec, Canada J4G 1A1; phone: 800–268–
8000; fax: 450–647–2888; website: https://
www.pwc.ca. You may view this service
information at the FAA, Engine & Propeller
Standards Branch, 1200 District Avenue,
Burlington, MA 01803. For information on
the availability of this material at the FAA,
call 781–238–7759.
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[FR Doc. 2018–19862 Filed 9–14–18; 8:45 am]
BILLING CODE 4910–13–P
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14 CFR Part 39
[Docket No. FAA–2018–0771; Product
Identifier 2018–CE–029–AD]
RIN 2120–AA64
(i) Alternative Methods of Compliance
(AMOCs)
Issued in Burlington, Massachusetts, on
September 7, 2018.
Robert J. Ganley,
Manager, Engine & Propeller Standards
Branch, Aircraft Certification Service.
Federal Aviation Administration
Airworthiness Directives; GA 8 Airvan
(Pty) Ltd Airplanes
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 GA 8
Airvan (Pty) Ltd Models GA8 and GA8–
TC320 airplanes. 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 certain wing strut fittings
manufactured with incorrect grain
orientation, which has an unknown
effect on fatigue related concerns. 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 November 1, 2018.
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 GA 8 Airvan
(Pty) Ltd, c/o GippsAero Pty Ltd, Attn:
Technical Services, P.O. Box 881,
Morwell Victoria 3840, Australia;
telephone: +61 03 5172 1200; fax: +61
03 5172 1201; email: aircraft.techpubs@
mahindraaerospace.com. You may
review this referenced service
information at the FAA, Policy and
Innovation Division, 901 Locust, Kansas
City, Missouri 64106. For information
on the availability of this material at the
FAA, call (816) 329–4148.
SUMMARY:
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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–2018–
0771; 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 proposed
AD, the regulatory evaluation, any
comments received, and other
information. The street address for
Docket Operations (telephone (800)
647–5527) is in the ADDRESSES section.
Comments will be available in the AD
docket shortly after receipt.
FOR FURTHER INFORMATION CONTACT:
Doug Rudolph, Aerospace Engineer,
FAA, Small Airplane Standards Branch,
901 Locust, Room 301, Kansas City,
Missouri 64106; telephone: (816) 329–
4059; fax: (816) 329–4090; email:
doug.rudolph@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–2018–0771; Product Identifier
2018–CE–029–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 Civil Aviation Safety Authority
(CASA), which is the aviation authority
for Australia, has issued AD No. AD/
GA8/9, Amendment 1, dated May 29,
2018 (referred to after this as ‘‘the
MCAI’’), to correct an unsafe condition
for the specified products. The MCAI
states:
Amendment 1 of this [CASA] AD is issued
to amend the replacement times as Service
Bulletin GA8–2017–174 Issue 2 changed the
mandatory replacement times for part
number GA8–570026–035 strut from 6000
hours time in service or 3 calendar years to
9000 hours time in service or 5 calendar
years, whichever occurs first.
A manufacturing quality escape has
resulted in wing strut fittings in the effective
serial number range to be manufactured with
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Federal Register / Vol. 83, No. 180 / Monday, September 17, 2018 / Proposed Rules
incorrect grain orientation. The fatigue
implications of the incorrect grain are not
well understood. Therefore, CASA has
mandated a conservative factored fatigue life
limit based on the known fleet data of the
affected aircraft. CASA will continue to
gather data for the purposes of managing the
fleet removal of these fittings from service.
You may examine the MCAI on the
internet at https://www.regulations.gov
by searching for and locating Docket No.
FAA–2018–0771.
Related Service Information Under 1
CFR Part 51
GippsAero has issued Service Bulletin
SB–GA8–2017–174, Issue 2, dated May
23, 2018. The service information
describes procedures for wing strut and
strut fitting inspection and replacement.
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 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.
daltland on DSKBBV9HB2PROD with PROPOSALS
Costs of Compliance
We estimate that this proposed AD
would affect 50 airplanes of U.S.
registry. The average labor rate is $85
per work-hour.
We estimate that it would take about
8 work-hours and $200 for parts to do
the initial inspections of this proposed
AD, for a cost of $880 per airplane and
$44,000 for the U.S. operator fleet. We
estimate that it would take about 5
work-hours and $200 for parts to do the
repetitive inspections, for a cost of $625
per airplane and $31,250 for the U.S.
operator fleet per inspection cycle.
In addition, we estimate that
replacing the struts and strut fittings
would take about 10 work-hours and
require parts costing $7,000, for a cost
of $7,850 per airplane and $392,500 for
the U.S. operator fleet.
Reporting the inspection findings
would require about 1 work-hour, for a
cost of $85 per airplane and $4,250 for
the U.S. operator fleet per inspection
cycle.
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According to the manufacturer, some
of the costs of this proposed 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.
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 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 currently 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 1 hour per response,
including the time for reviewing
instructions, searching existing data
sources, gathering and maintaining the
data needed, completing and reviewing
the collection of information. All
responses to this collection of
information are mandatory as required
by this AD; the nature and extent of
confidentiality to be provided, if any.
Send comments regarding this burden
estimate or any other aspect of this
collection of information, including
suggestions for reducing this burden to:
Information Collection Clearance
Officer, Federal Aviation
Administration, 10101 Hillwood
Parkway, Fort Worth, TX 76177–1524.
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.
This AD is issued in accordance with
authority delegated by the Executive
Director, Aircraft Certification Service,
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46901
as authorized by FAA Order 8000.51C.
In accordance with that order, issuance
of ADs is normally a function of the
Compliance and Airworthiness
Division, but during this transition
period, the Executive Director has
delegated the authority to issue ADs
applicable to small airplanes, gliders,
balloons, airships, domestic business jet
transport airplanes, and associated
appliances to the Director of the Policy
and Innovation Division.
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 airworthiness
directive (AD):
■
GA 8 Airvan (Pty) Ltd: Docket No. FAA–
2018–0771; Product Identifier 2018–CE–
029–AD.
(a) Comments Due Date
We must receive comments by November
1, 2018.
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Federal Register / Vol. 83, No. 180 / Monday, September 17, 2018 / Proposed Rules
(b) Affected ADs
None.
(c) Applicability
This AD applies to GA 8 Airvan (Pty) Ltd
Models GA8 and GA8–TC320 airplanes,
certificated in any category, with a strut or
strut fitting installed that has a part number
and serial number listed in table 1 of
GippsAero Service Bulletin SB–GA8–2017–
174, Issue 2, dated May 23, 2018 (GippsAero
SB–GA8–2017–174, Issue 2).
(d) Subject
Air Transport Association of America
(ATA) Code 57: Wings.
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(e) Reason
This AD was prompted by mandatory
continuing airworthiness information (MCAI)
issued by the aviation authority of another
country to identify and correct an unsafe
condition on an aviation product. The MCAI
describes the unsafe condition as certain
wing strut fittings manufactured with
incorrect grain orientation, which has an
unknown effect on fatigue-related concerns.
We are issuing this AD to detect and address
fatigue-related damage to the wing strut
fittings, which could lead to failure of the
wing with consequent loss of control of the
airplane.
(f) Actions and Compliance
Unless already done, do the following
actions in paragraphs (f)(1) through (6) of this
AD:
(1) Within 3 months after the effective date
of this AD or within 100 hours time-inservice (TIS) after the effective date of this
AD, whichever occurs first, with the wing
struts removed, visually inspect each forward
and aft wing strut fitting and fuselage
attachment point for cracks, corrosion, and
damage. If a crack, corrosion, or damage is
found during the inspection, before further
flight, do the applicable corrective actions
(check torque, restore surface protection,
rework areas with fouling, and replace any
part with a crack, corrosion, or damage).
Follow the procedures in Parts C1, C2, and
D or E, as applicable, in the Accomplishment
Instructions in GippsAero SB–GA8–2017–
174, Issue 2.
(2) Within 3 months after the effective date
of this AD or within 100 hours TIS after the
effective date of this AD, whichever occurs
first, and thereafter at intervals not to exceed
100 hours TIS, visually inspect each strut
and strut fitting for cracks, corrosion, and
damage. If a crack, corrosion, or damage is
found during any of the inspections, before
further flight, do the applicable corrective
actions (check torque, restore surface
protection, and replace any part with a crack,
corrosion, or damage). Follow the procedures
in Parts B and D or E, as applicable, in the
Accomplishment Instructions of GippsAero
SB–GA8–2017–174, Issue 2.
(3) Within 1,000 hours TIS after doing the
inspections required in paragraph (f)(1) of
this AD and thereafter at intervals not to
exceed 1,000 hours TIS, with the wing struts
installed, visually inspect each forward and
aft wing strut, strut fitting, and strut fitting
lug hole for cracks, corrosion, and damage. If
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Jkt 244001
a crack, corrosion, or damage is found during
any of the inspections, before further flight,
do the applicable corrective actions (do
additional inspections, replace hardware,
and replace any part with a crack, corrosion,
or damage). Follow the procedures in Parts
C3 and D or E, as applicable, in the
Accomplishment Instructions of GippsAero
SB–GA8–2017–174, Issue 2.
(4) To use an eddy current or fluorescent
liquid penetrant inspection method instead
of a visual inspection for the requirements in
paragraphs (f)(1) of this AD, the Manager,
Small Airplane Standards Branch, FAA must
approve your inspection method, and the
Manager’s approval letter must specifically
refer to this AD. Send your approval request
to the contact information found in
paragraph (g)(1) of this AD.
(5) Remove from service each part listed in
Parts D and E of table 3 on or before the part
exceeds its specified replacement time and
replace with an airworthy part. On the
effective date of this AD, any part listed in
table 3 of GippsAero SB–GA8–2017–174,
Issue 2, that has exceeded its replacement
time, within 100 hours TIS after the effective
date of this AD or within 12 months after the
effective date of this AD, whichever occurs
first, remove the part from service and
replace with an airworthy part. Follow the
replacement procedures in Part D or Part E,
as applicable, in the Accomplishment
Instructions of GippsAero SB–GA8–2017–
174, Issue 2.
(6) Within 24 hours after each inspection
required in paragraphs (f)(1) and (2) of this
AD, submit a report of the inspection results,
even if no damage is found, to the Civil
Aviation Safety Authority (CASA) and GA 8
Airvan (Pty) Ltd. Use the Document
Compliance Notice of GippsAero SB–GA8–
2017–174, Issue 2, and include in the report
the total hours TIS on the airplane and the
type of operation. You may use the contact
information found in paragraph (h) of this
AD to contact GA 8 Airvan (Pty) Ltd. To
contact CASA, use the online CASA Defect
Reporting Service at the following internet
address: https://drs.casa.gov.au/.
(g) Other FAA AD Provisions
The following provisions also apply to this
AD:
(1) Alternative Methods of Compliance
(AMOCs): The Manager, Small Airplane
Standards Branch, 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: Doug Rudolph,
Aerospace Engineer, FAA, Small Airplane
Standards Branch, 901 Locust, Room 301,
Kansas City, Missouri 64106; telephone:
(816) 329–4059; fax: (816) 329–4090; email:
doug.rudolph@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) Contacting the Manufacturer: For any
requirement in this AD to obtain corrective
actions from a manufacturer, the action must
instead be accomplished using a method
approved by the Manager, Small Airplane
Standards Branch, FAA; or CASA.
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(3) Reporting Requirements: 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 currently
valid OMB Control Number. The OMB
Control Number for this information
collection is 2120–0731. Public reporting for
this collection of information is estimated to
be approximately 1 hour per response,
including the time for reviewing instructions,
searching existing data sources, gathering
and maintaining the data needed, completing
and reviewing the collection of information.
All responses to this collection of
information are voluntary; the nature and
extent of confidentiality to be provided, if
any. Send comments regarding this burden
estimate or any other aspect of this collection
of information, including suggestions for
reducing this burden to: Information
Collection Clearance Officer, Federal
Aviation Administration, 10101 Hillwood
Parkway, Fort Worth, TX 76177–1524.
(h) Related Information
Refer to MCAI issued by CASA, AD No.
AD/GA8/9, Amendment 1, dated May 29,
2018. You may examine the MCAI on the
internet at https://www.regulations.gov by
searching for and locating Docket No. FAA–
2018–0771. For service information related to
this AD, contact GA 8 Airvan (Pty) Ltd, c/o
GippsAero Pty Ltd, Attn: Technical Services,
P.O. Box 881, Morwell Victoria 3840,
Australia; telephone: +61 03 5172 1200; fax:
+61 03 5172 1201; email: aircraft.techpubs@
mahindraaerospace.com. You may review
this referenced service information at the
FAA, Policy and Innovation Division, 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 August
31, 2018.
Melvin J. Johnson,
Deputy Director, Policy & Innovation Division,
Aircraft Certification Service.
[FR Doc. 2018–19889 Filed 9–14–18; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2018–0793; Product
Identifier 2018–NM–057–AD]
RIN 2120–AA64
Airworthiness Directives; The Boeing
Company Airplanes
Federal Aviation
Administration (FAA), DOT.
ACTION: Notice of proposed rulemaking
(NPRM).
AGENCY:
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]]>Agencies
[Federal Register Volume 83, Number 180 (Monday, September 17, 2018)]
[Proposed Rules]
[Pages 46900-46902]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2018-19889]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2018-0771; Product Identifier 2018-CE-029-AD]
RIN 2120-AA64
Airworthiness Directives; GA 8 Airvan (Pty) Ltd Airplanes
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 GA
8 Airvan (Pty) Ltd Models GA8 and GA8-TC320 airplanes. 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 certain wing strut fittings manufactured with
incorrect grain orientation, which has an unknown effect on fatigue
related concerns. 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 November 1,
2018.
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 GA
8 Airvan (Pty) Ltd, c/o GippsAero Pty Ltd, Attn: Technical Services,
P.O. Box 881, Morwell Victoria 3840, Australia; telephone: +61 03 5172
1200; fax: +61 03 5172 1201; email:
[email protected]. You may review this referenced
service information at the FAA, Policy and Innovation Division, 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-2018-
0771; 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 proposed AD, the regulatory evaluation, any comments received, and
other information. The street address for Docket Operations (telephone
(800) 647-5527) is in the ADDRESSES section. Comments will be available
in the AD docket shortly after receipt.
FOR FURTHER INFORMATION CONTACT: Doug Rudolph, Aerospace Engineer, FAA,
Small Airplane Standards Branch, 901 Locust, Room 301, Kansas City,
Missouri 64106; telephone: (816) 329-4059; fax: (816) 329-4090; email:
[email protected].
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-2018-0771;
Product Identifier 2018-CE-029-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 Civil Aviation Safety Authority (CASA), which is the aviation
authority for Australia, has issued AD No. AD/GA8/9, Amendment 1, dated
May 29, 2018 (referred to after this as ``the MCAI''), to correct an
unsafe condition for the specified products. The MCAI states:
Amendment 1 of this [CASA] AD is issued to amend the replacement
times as Service Bulletin GA8-2017-174 Issue 2 changed the mandatory
replacement times for part number GA8-570026-035 strut from 6000
hours time in service or 3 calendar years to 9000 hours time in
service or 5 calendar years, whichever occurs first.
A manufacturing quality escape has resulted in wing strut
fittings in the effective serial number range to be manufactured
with
[[Page 46901]]
incorrect grain orientation. The fatigue implications of the
incorrect grain are not well understood. Therefore, CASA has
mandated a conservative factored fatigue life limit based on the
known fleet data of the affected aircraft. CASA will continue to
gather data for the purposes of managing the fleet removal of these
fittings from service.
You may examine the MCAI on the internet at https://www.regulations.gov
by searching for and locating Docket No. FAA-2018-0771.
Related Service Information Under 1 CFR Part 51
GippsAero has issued Service Bulletin SB-GA8-2017-174, Issue 2,
dated May 23, 2018. The service information describes procedures for
wing strut and strut fitting inspection and replacement. 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 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 would affect 50 airplanes of U.S.
registry. The average labor rate is $85 per work-hour.
We estimate that it would take about 8 work-hours and $200 for
parts to do the initial inspections of this proposed AD, for a cost of
$880 per airplane and $44,000 for the U.S. operator fleet. We estimate
that it would take about 5 work-hours and $200 for parts to do the
repetitive inspections, for a cost of $625 per airplane and $31,250 for
the U.S. operator fleet per inspection cycle.
In addition, we estimate that replacing the struts and strut
fittings would take about 10 work-hours and require parts costing
$7,000, for a cost of $7,850 per airplane and $392,500 for the U.S.
operator fleet.
Reporting the inspection findings would require about 1 work-hour,
for a cost of $85 per airplane and $4,250 for the U.S. operator fleet
per inspection cycle.
According to the manufacturer, some of the costs of this proposed
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.
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 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 currently 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 1 hour per response, including the time for reviewing
instructions, searching existing data sources, gathering and
maintaining the data needed, completing and reviewing the collection of
information. All responses to this collection of information are
mandatory as required by this AD; the nature and extent of
confidentiality to be provided, if any. Send comments regarding this
burden estimate or any other aspect of this collection of information,
including suggestions for reducing this burden to: Information
Collection Clearance Officer, Federal Aviation Administration, 10101
Hillwood Parkway, Fort Worth, TX 76177-1524.
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.
This AD is issued in accordance with authority delegated by the
Executive Director, Aircraft Certification Service, as authorized by
FAA Order 8000.51C. In accordance with that order, issuance of ADs is
normally a function of the Compliance and Airworthiness Division, but
during this transition period, the Executive Director has delegated the
authority to issue ADs applicable to small airplanes, gliders,
balloons, airships, domestic business jet transport airplanes, and
associated appliances to the Director of the Policy and Innovation
Division.
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 airworthiness
directive (AD):
GA 8 Airvan (Pty) Ltd: Docket No. FAA-2018-0771; Product Identifier
2018-CE-029-AD.
(a) Comments Due Date
We must receive comments by November 1, 2018.
[[Page 46902]]
(b) Affected ADs
None.
(c) Applicability
This AD applies to GA 8 Airvan (Pty) Ltd Models GA8 and GA8-
TC320 airplanes, certificated in any category, with a strut or strut
fitting installed that has a part number and serial number listed in
table 1 of GippsAero Service Bulletin SB-GA8-2017-174, Issue 2,
dated May 23, 2018 (GippsAero SB-GA8-2017-174, Issue 2).
(d) Subject
Air Transport Association of America (ATA) Code 57: Wings.
(e) Reason
This AD was prompted by mandatory continuing airworthiness
information (MCAI) issued by the aviation authority of another
country to identify and correct an unsafe condition on an aviation
product. The MCAI describes the unsafe condition as certain wing
strut fittings manufactured with incorrect grain orientation, which
has an unknown effect on fatigue-related concerns. We are issuing
this AD to detect and address fatigue-related damage to the wing
strut fittings, which could lead to failure of the wing with
consequent loss of control of the airplane.
(f) Actions and Compliance
Unless already done, do the following actions in paragraphs
(f)(1) through (6) of this AD:
(1) Within 3 months after the effective date of this AD or
within 100 hours time-in-service (TIS) after the effective date of
this AD, whichever occurs first, with the wing struts removed,
visually inspect each forward and aft wing strut fitting and
fuselage attachment point for cracks, corrosion, and damage. If a
crack, corrosion, or damage is found during the inspection, before
further flight, do the applicable corrective actions (check torque,
restore surface protection, rework areas with fouling, and replace
any part with a crack, corrosion, or damage). Follow the procedures
in Parts C1, C2, and D or E, as applicable, in the Accomplishment
Instructions in GippsAero SB-GA8-2017-174, Issue 2.
(2) Within 3 months after the effective date of this AD or
within 100 hours TIS after the effective date of this AD, whichever
occurs first, and thereafter at intervals not to exceed 100 hours
TIS, visually inspect each strut and strut fitting for cracks,
corrosion, and damage. If a crack, corrosion, or damage is found
during any of the inspections, before further flight, do the
applicable corrective actions (check torque, restore surface
protection, and replace any part with a crack, corrosion, or
damage). Follow the procedures in Parts B and D or E, as applicable,
in the Accomplishment Instructions of GippsAero SB-GA8-2017-174,
Issue 2.
(3) Within 1,000 hours TIS after doing the inspections required
in paragraph (f)(1) of this AD and thereafter at intervals not to
exceed 1,000 hours TIS, with the wing struts installed, visually
inspect each forward and aft wing strut, strut fitting, and strut
fitting lug hole for cracks, corrosion, and damage. If a crack,
corrosion, or damage is found during any of the inspections, before
further flight, do the applicable corrective actions (do additional
inspections, replace hardware, and replace any part with a crack,
corrosion, or damage). Follow the procedures in Parts C3 and D or E,
as applicable, in the Accomplishment Instructions of GippsAero SB-
GA8-2017-174, Issue 2.
(4) To use an eddy current or fluorescent liquid penetrant
inspection method instead of a visual inspection for the
requirements in paragraphs (f)(1) of this AD, the Manager, Small
Airplane Standards Branch, FAA must approve your inspection method,
and the Manager's approval letter must specifically refer to this
AD. Send your approval request to the contact information found in
paragraph (g)(1) of this AD.
(5) Remove from service each part listed in Parts D and E of
table 3 on or before the part exceeds its specified replacement time
and replace with an airworthy part. On the effective date of this
AD, any part listed in table 3 of GippsAero SB-GA8-2017-174, Issue
2, that has exceeded its replacement time, within 100 hours TIS
after the effective date of this AD or within 12 months after the
effective date of this AD, whichever occurs first, remove the part
from service and replace with an airworthy part. Follow the
replacement procedures in Part D or Part E, as applicable, in the
Accomplishment Instructions of GippsAero SB-GA8-2017-174, Issue 2.
(6) Within 24 hours after each inspection required in paragraphs
(f)(1) and (2) of this AD, submit a report of the inspection
results, even if no damage is found, to the Civil Aviation Safety
Authority (CASA) and GA 8 Airvan (Pty) Ltd. Use the Document
Compliance Notice of GippsAero SB-GA8-2017-174, Issue 2, and include
in the report the total hours TIS on the airplane and the type of
operation. You may use the contact information found in paragraph
(h) of this AD to contact GA 8 Airvan (Pty) Ltd. To contact CASA,
use the online CASA Defect Reporting Service at the following
internet address: https://drs.casa.gov.au/.
(g) Other FAA AD Provisions
The following provisions also apply to this AD:
(1) Alternative Methods of Compliance (AMOCs): The Manager,
Small Airplane Standards Branch, 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: Doug Rudolph, Aerospace Engineer,
FAA, Small Airplane Standards Branch, 901 Locust, Room 301, Kansas
City, Missouri 64106; telephone: (816) 329-4059; fax: (816) 329-
4090; email: [email protected]. 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) Contacting the Manufacturer: For any requirement in this AD
to obtain corrective actions from a manufacturer, the action must
instead be accomplished using a method approved by the Manager,
Small Airplane Standards Branch, FAA; or CASA.
(3) Reporting Requirements: 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 currently valid OMB Control Number. The OMB Control
Number for this information collection is 2120-0731. Public
reporting for this collection of information is estimated to be
approximately 1 hour per response, including the time for reviewing
instructions, searching existing data sources, gathering and
maintaining the data needed, completing and reviewing the collection
of information. All responses to this collection of information are
voluntary; the nature and extent of confidentiality to be provided,
if any. Send comments regarding this burden estimate or any other
aspect of this collection of information, including suggestions for
reducing this burden to: Information Collection Clearance Officer,
Federal Aviation Administration, 10101 Hillwood Parkway, Fort Worth,
TX 76177-1524.
(h) Related Information
Refer to MCAI issued by CASA, AD No. AD/GA8/9, Amendment 1,
dated May 29, 2018. You may examine the MCAI on the internet at
https://www.regulations.gov by searching for and locating Docket No.
FAA-2018-0771. For service information related to this AD, contact
GA 8 Airvan (Pty) Ltd, c/o GippsAero Pty Ltd, Attn: Technical
Services, P.O. Box 881, Morwell Victoria 3840, Australia; telephone:
+61 03 5172 1200; fax: +61 03 5172 1201; email:
[email protected]. You may review this
referenced service information at the FAA, Policy and Innovation
Division, 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 August 31, 2018.
Melvin J. Johnson,
Deputy Director, Policy & Innovation Division, Aircraft Certification
Service.
[FR Doc. 2018-19889 Filed 9-14-18; 8:45 am]
BILLING CODE 4910-13-P
