Airworthiness Directives; M7 Aerospace LLC Models Airplanes, 15982-15985 [2017-05857]
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Federal Register / Vol. 82, No. 61 / Friday, March 31, 2017 / Rules and Regulations
who is the subject of a record to impede
the investigation, to tamper with
witnesses or evidence, and to avoid
detection or apprehension. Amendment
of the records could interfere with
ongoing investigations and law
enforcement activities and would
impose an unreasonable administrative
burden by requiring investigations to be
continually reinvestigated. In addition,
permitting access and amendment to
such information could disclose
security-sensitive information that
could be detrimental to homeland
security.
(c) From subsection (e)(1) (Relevancy
and Necessity of Information) because
in the course of investigations into
potential violations of federal law, the
accuracy of information obtained or
introduced occasionally may be unclear,
or the information may not be strictly
relevant or necessary to a specific
investigation. In the interests of effective
law enforcement, it is appropriate to
retain all information that may aid in
establishing patterns of unlawful
activity.
(d) From subsection (e)(2) (Collection
of Information from Individuals)
because requiring that information be
collected from the subject of an
investigation would alert the subject to
the nature or existence of the
investigation, thereby interfering with
that investigation and related law
enforcement activities.
(e) From subsection (e)(3) (Notice to
Subjects) because providing such
detailed information could impede law
enforcement by compromising the
existence of a confidential investigation
or reveal the identity of witnesses or
confidential informants.
(f) From subsection (e)(5) (Collection
of Information) because with the
collection of information for law
enforcement purposes, it is impossible
to determine in advance what
information is accurate, relevant, timely,
and complete. Compliance with
subsection (e)(5) would preclude DHS
agents from using their investigative
training and exercise of good judgment
to both conduct and report on
investigations.
(g) From subsection (e)(8) (Notice on
Individuals) because compliance would
interfere with DHS’s ability to obtain,
serve, and issue subpoenas, warrants,
and other law enforcement mechanisms
that may be filed under seal and could
result in disclosure of investigative
techniques, procedures, and evidence.
(h) From subsection (g) (Civil
Remedies) to the extent that the system
is exempt from other specific
subsections of the Privacy Act.
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Dated: March 24, 2017.
Jonathan R. Cantor,
Acting Chief Privacy Officer, Department of
Homeland Security.
[FR Doc. 2017–06327 Filed 3–30–17; 8:45 am]
BILLING CODE 9110–04–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2016–9531; Directorate
Identifier 2015–CE–011–AD; Amendment
39–18839; AD 2017–07–01]
RIN 2120–AA64
Airworthiness Directives; M7
Aerospace LLC Models Airplanes
Federal Aviation
Administration (FAA), DOT.
ACTION: Final rule.
AGENCY:
We are adopting a new
airworthiness directive (AD) for certain
M7 Aerospace LLC Models SA226–T,
SA226–AT, SA226–T(B), SA226–TC,
SA227–AC (C–26A), SA227–AT,
SA227–BC (C–26A), SA227–CC, SA227–
DC (C–26B), and SA227–TT airplanes.
This AD was prompted by detachment
of the power lever linkage to the TPE331
engine propeller pitch control. This AD
requires repetitively inspecting the
propeller pitch control for proper
torque, with corrections as necessary
until required replacement or rework of
the PPC assembly to have a threaded
hole in the splined end of the
shouldered shaft and installation of a
secondary retention device is done. We
are issuing this AD to correct the unsafe
condition on these products.
DATES: This AD is effective May 5, 2017.
The Director of the Federal Register
approved the incorporation by reference
of certain publications listed in this AD
as of May 5, 2017.
ADDRESSES: For service information
identified in this final rule, contact M7
Aerospace LLC, 10823 NE Entrance
Road, San Antonio, Texas 78216; phone:
(210) 824–9421; fax: (210) 804–7766;
Internet: https://www.elbitsystemsus.com; email: MetroTech@
M7Aerospace.com; or Honeywell
International Inc. 111 S. 34th Street,
Phoenix, Arizona 85034–2802; phone:
(855) 808–6500; email:
AeroTechSupport@honeywell.com;
Internet: https://
aerospace.honeywell.com/en/services/
maintenance-and-monitoring. You may
view this referenced service information
at the FAA, Small Airplane Directorate,
901 Locust, Kansas City, Missouri
SUMMARY:
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64106. For information on the
availability of this material at the FAA,
call 816–329–4148. It is also available
on the internet at https://
www.regulations.gov by searching for
and locating Docket No. FAA–2016–
9531.
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–2016–
9531; or in person at the Docket
Management Facility between 9 a.m.
and 5 p.m., Monday through Friday,
except Federal holidays. The AD docket
contains this AD, the regulatory
evaluation, any comments received, and
other information. The address for the
Docket Office (phone: 800–647–5527) is
Document Management Facility, U.S.
Department of Transportation, Docket
Operations, M–30, West Building
Ground Floor, Room W12–140, 1200
New Jersey Avenue SE., Washington,
DC 20590.
FOR FURTHER INFORMATION CONTACT ONE
OF THE FOLLOWING:
• Justin Carter, ASW–142, Aerospace
Engineer, Fort Worth Airplane
Certification Office (ACO), FAA, 10101
Hillwood Parkway, Fort Worth, Texas
76177–1524; telephone: (817) 222–5146;
fax: (817) 222–5960; email:
justin.carter@faa.gov; or
• Kristin Bradley, ASW–143,
Aerospace Engineer, Fort Worth ACO,
FAA, 10101 Hillwood Parkway, Fort
Worth, Texas 76177–1524; telephone:
(817) 222–5485; fax: (817) 222–5960;
email: kristin.bradley@faa.gov.
SUPPLEMENTARY INFORMATION:
Discussion
We issued a notice of proposed
rulemaking (NPRM) to amend 14 CFR
part 39 by adding an AD that would
apply to certain M7 Aerospace LLC
Models SA226–T, SA226–AT, SA226–
T(B), SA226–TC, SA227–AC (C–26A),
SA227–AT, SA227–BC (C–26A),
SA227–CC, SA227–DC (C–26B), and
SA227–TT airplanes. The NPRM
published in the Federal Register on
December 28, 2016 (81 FR 95528). The
NPRM was prompted by reports of the
airplane power lever linkage detaching
from the TPE331 engine propeller pitch
control (PPC) shaft. In flight operations,
detachment may result in fuel flow to
the engine remaining constant
regardless of the power lever movement
by the pilot. The orientation of the
engine on certain M7 Aerospace
airplanes increases the vulnerability of
detachment. The PPC lever is an
airplane part and its detachment from
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the TPE311 has been the subject of
previous ADs on other airplane type
designs. The NPRM proposed to require
repetitive inspections of the PPC lever
with corrective action as necessary until
required replacement or rework of the
PPC assembly to have a threaded hole
in the splined end of the shouldered
shaft and installation of a secondary
retention feature for the airplane control
linkage interface is done. We are issuing
this AD to correct the unsafe condition
on these products.
Comments
We gave the public the opportunity to
participate in developing this AD. We
received no comments on the NPRM or
on the determination of the cost to the
public.
Conclusion
We reviewed the relevant data and
determined that air safety and the
public interest require adopting this AD
as proposed. We have determined that
these minor changes:
• Are consistent with the intent that
was proposed in the NPRM for
correcting the unsafe condition; and
• Do not add any additional burden
upon the public than was already
proposed in the NPRM.
Related Service Information Under 1
CFR Part 51
We reviewed M7 Aerospace LLC
SA226 Series Service Bulletin 226–76–
012, dated March 17, 2015; M7
Aerospace LLC SA227 Series Service
Bulletin 227–76–007, dated March 17,
2015; and M7 Aerospace LLC SA227
Series Commuter Category Service
Bulletin CC7–76–004, dated March 17,
2015; that, in combination with the
temporary revisions and service bulletin
listed below, describes the actions that
must be done for the applicable models
to comply with this AD.
We also reviewed M7 Aerospace
SA226 Series Maintenance Manual
Temporary Revision 71–02, dated
March 15, 2016; M7 Aerospace SA227
Series Maintenance Manual Temporary
Revision 71–03, dated March 15, 2016;
and M7 Aerospace SA227 Series
15983
Commuter Category Maintenance
Manual Temporary Revision 71–02,
dated March 15, 2016; that describes
procedures for installing the secondary
retention device on the PPC assembly
and doing a visual inspection of the PPC
lever for the applicable models.
We also reviewed Honeywell
International Inc. Service Bulletin
TPE331–72–2190, dated December 21,
2011, that describes procedures for
replacing or reworking the propeller
pitch control assembly, incorporating a
threaded hole in the splined end of the
shouldered shaft, and reassembling the
propeller pitch control assembly.
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 document.
Costs of Compliance
We estimate that this AD affects 360
airplanes of U.S. registry.
We estimate the following costs to
comply with this AD:
ESTIMATED COSTS
Action
Labor cost
Replacement or rework of the PPC assembly
Install secondary retention device ..................
Visual inspection of PPC lever .......................
19 work-hours × $85 per hour = $1,615 .......
1 work-hour × $85 per hour = $85 ................
.5 work-hour × $85 per hour = $42.50 ..........
$1,000 .............
10 ....................
Not applicable
We estimate the following costs to do
any necessary adjustments that would
be required based on the results of the
visual inspection. We have no way of
Cost per
product
Parts cost
$2,615
95
42.50
Cost on U.S.
operators
$941,400
34,200
15,300
determining the number of aircraft that
might need these adjustments:
ON-CONDITION COSTS
Action
Labor cost
Correct attachment of the PPC lever ...........................
.5 work-hour × $85 per hour = $42.50 ........................
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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
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safety in air commerce. This regulation
is within the scope of that authority
because it addresses an unsafe condition
that is likely to exist or develop on
products identified in this rulemaking
action.
Regulatory Findings
This AD will not have federalism
implications under Executive Order
13132. This AD will not have a
substantial direct effect on the States, on
the relationship between the national
government and the States, or on the
distribution of power and
responsibilities among the various
levels of government.
For the reasons discussed above, I
certify that this AD:
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Parts cost
Cost per
product
Not applicable
$42.50
(1) Is not a ‘‘significant regulatory
action’’ under Executive Order 12866,
(2) Is not a ‘‘significant rule’’ under
DOT Regulatory Policies and Procedures
(44 FR 11034, February 26, 1979),
(3) Will not affect intrastate aviation
in Alaska, and
(4) Will not have a significant
economic impact, positive or negative,
on a substantial number of small entities
under the criteria of the Regulatory
Flexibility Act.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation
safety, Incorporation by reference,
Safety.
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Federal Register / Vol. 82, No. 61 / Friday, March 31, 2017 / Rules and Regulations
Adoption of the Amendment
Accordingly, under the authority
delegated to me by the Administrator,
the FAA amends 14 CFR part 39 as
follows:
PART 39—AIRWORTHINESS
DIRECTIVES
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):
■
2017–07–01 M7 Aerospace LLC:
Amendment 39–18839; Docket No.
FAA–2016–9531; Directorate Identifier
2015–CE–011–AD.
(a) Effective Date
This AD is effective May 5, 2017.
(b) Affected ADs
None.
(c) Applicability
This AD applies to M7 Aerospace LLC
SA226–T, SA226–AT, SA226–T(B), SA226–
TC, SA227–AC (C–26A), SA227–AT, SA227–
BC (C–26A), SA227–CC, SA227–DC (C–26B),
and SA227–TT airplanes; all serial numbers,
certificated in any category.
(d) Subject
Joint Aircraft System Component (JASC)/
Air Transport Association (ATA) of America
Code 61, Propellers/Propulsors.
(e) Unsafe Condition
This AD was prompted by detachment of
the power lever linkage to the TPE331 engine
propeller pitch control (PPC). We are issuing
this AD to prevent detachment of the power
lever linkage to the TPE331 engine PPC,
which could result in uncommanded change
to the engine power settings with consequent
loss of control.
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(f) Compliance
Comply with this AD within the
compliance times specified, unless already
done.
(g) Applicable M7 Aerospace LLC Service
Bulletins
Use the applicable service bulletins as
listed in paragraph (g)(1), (2), or (3) of this
AD as reference to complete the actions in
paragraph (i)(1) or (2) of this AD:
(1) M7 Aerospace LLC SA226 Series
Service Bulletin 226–76–012, dated March
17, 2015;
(2) M7 Aerospace LLC SA227 Series
Service Bulletin 227–76–007, dated March
17, 2015; or
(3) M7Aerospace LLC SA227 Series
Commuter Category Service Bulletin CC7–
76–004, dated March 17, 2015.
(h) PPC Lever Installation
(1) Within 100 hours time-in-service (TIS)
after May 5, 2017 (the effective date of this
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AD) and repetitively thereafter at intervals
not to exceed 100 hours TIS, visually inspect
the PPC lever to assure the attachment is
properly installed following the applicable
service information listed in paragraph
(h)(1)(i), (ii), or (iii) of this AD, as applicable.
(i) For Models SA226 Series: M7 Aerospace
SA226 Series Maintenance Manual
Temporary Revision 71–02, dated March 15,
2016.
(ii) For Models SA227 Series: M7
Aerospace SA227 Series Maintenance
Manual Temporary Revision 71–03, dated
March 15, 2016.
(iii) For Models SA227 Series Commuter
Category: M7 Aerospace SA227 Series
Commuter Category Maintenance Manual
Temporary Revision 71–02, dated March 15,
2016.
(2) The rework/replacement required by
paragraph (i) of the AD and the installation
of the secondary retention device required in
paragraph (j) of this AD terminate the
repetitive visual inspections of the PPC lever
attachment required by paragraph (h)(1) of
this AD.
(i) Replace or Rework the Propeller Pitch
Assembly
Within the next 600 hours TIS after May
5, 2017 (the effective date of this AD) or
within the next 12 months after May 5, 2017
(the effective date of this AD), whichever
occurs first, do the actions in either
paragraph (i)(1) or (2) of this AD following
the Accomplishment Instructions in
Honeywell International Inc. Service Bulletin
TPE331–72–2190, dated December 21, 2011,
as referenced in the applicable service
information listed in paragraph (g)(1), (2), or
(3) this AD.
(1) Replace the PPC. Remove the PPC
assembly and replace with the applicable
new design PPC using the part numbers
listed in table 1 to paragraph (i)(1) of this AD.
TABLE 1 TO PARAGRAPH (i)(1) OF THIS
AD—PART NUMBER PPC ASSEMBLIES
Part No. PPC assembly to
remove
869130–11 ............................
869130–12 ............................
869130–13 ............................
869130–14 ............................
869130–16 ............................
869130–17 ............................
869130–18 ............................
869130–19 ............................
869130–30 ............................
895481–1 ..............................
895481–2 ..............................
895481–4 ..............................
895481–5 ..............................
895481–6 ..............................
895481–7 ..............................
895481–17 ............................
895481–18 ............................
895481–19 ............................
895481–20 ............................
895481–22 ............................
Part No. PPC
assembly to
install
70000295–11
70000295–12
70000295–13
70000295–14
70000295–16
70000295–17
70000295–18
70000295–19
70000295–30
70000298–1
70000298–2
70000298–4
70000298–5
70000298–6
70000298–7
70000298–17
70000298–18
70000298–19
70000298–20
70000298–22
(2) Rework the PPC assembly. Inspect the
splined end of the shouldered shaft for the
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presence and good condition of a threaded
hole, repairing or replacing the cam
assembly, and reworking the PPC assembly
as necessary.
(j) Secondary Retention Feature
(1) Before further flight after the
replacement or rework of the PPC assembly
required in paragraph (i)(1) or (2) of this AD,
install the secondary retention feature on the
PPC assembly following the applicable
service information listed in paragraph
(j)(1)(i), (ii), or (iii) of this AD.
(i) For Models SA226 Series: M7 Aerospace
SA226 Series Maintenance Manual
Temporary Revision 71–02, dated March 15,
2016.
(ii) For Models SA227 Series: M7
Aerospace SA227 Series Maintenance
Manual Temporary Revision 71–03, dated
March 15, 2016.
(iii) For Models SA227 Series Commuter
Category: M7 Aerospace SA227 Series
Commuter Category Maintenance Manual
Temporary Revision 71–02, dated March 15,
2016.
(2) The rework/replacement required by
paragraph (i) of this AD and the installation
of the secondary retention device required by
paragraph (j) of this AD terminate the
requirement for the repetitive inspections of
the PPC lever torque required in paragraph
(h) of this AD.
(k) Alternative Methods of Compliance
(AMOCs)
(1) The Manager, Fort Worth Airplane
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, mail it to the
attention of one of the people identified in
paragraph (l), Related Information, of this AD
or email the request to 9-asw-FWACO@
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.
(l) Related Information
For more information about this AD,
contact one of the following people:
(1) Justin Carter, ASW–142, Aerospace
Engineer, Fort Worth Airplane Certification
Office (ACO), FAA, 10101 Hillwood
Parkway, Fort Worth, Texas 76177–1524;
telephone: (817) 222–5146; fax: (817) 222–
5960; email: justin.carter@faa.gov; or
(2) Kristin Bradley, ASW–143, Aerospace
Engineer, Fort Worth ACO, FAA, 10101
Hillwood Parkway, Fort Worth, Texas 76177–
1524; telephone: (817) 222–5485; fax: (817)
222–5960; email: kristin.bradley@faa.gov.
(m) Material Incorporated by Reference
(1) The Director of the Federal Register
approved the incorporation by reference
(IBR) of the service information listed in this
paragraph under 5 U.S.C. 552(a) and 1 CFR
part 51.
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Federal Register / Vol. 82, No. 61 / Friday, March 31, 2017 / Rules and Regulations
(2) You must use this service information
as applicable to do the actions required by
this AD, unless the AD specifies otherwise.
(i) M7 Aerospace LLC SA226 Series
Service Bulletin 226–76–012, dated March
17, 2015.
(ii) M7 Aerospace LLC SA227 Series
Service Bulletin 227–76–007, dated March
17, 2015.
(iii) M7Aerospace LLC SA227 Series
Commuter Category Service Bulletin CC7–
76–004, dated March 17, 2015.
(iv) M7 Aerospace SA226 Series
Maintenance Manual Temporary Revision
71–02, dated March 15, 2016.
(v) M7 Aerospace SA227 Series
Maintenance Manual Temporary Revision
71–03, dated March 15, 2016.
(vi) M7 Aerospace SA227 Series Commuter
Category Maintenance Manual Temporary
Revision 71–02, dated March 15, 2016.
(vii) Honeywell International Inc. Service
Bulletin TPE331–72–2190, dated December
21, 2011.
(3) For service information identified in
this AD, contact M7 Aerospace LLC, 10823
NE Entrance Road, San Antonio, Texas
78216; phone: (210) 824–9421; fax: (210)
804–7766; Internet: https://www.elbitsystemsus.com; email: MetroTech@
M7Aerospace.com; or Honeywell
International Inc. 111 S. 34th Street, Phoenix,
Arizona 85034–2802; phone: (855) 808–6500;
email: AeroTechSupport@honeywell.com;
Internet: https://aerospace.honeywell.com/
en/services/maintenance-and-monitoring.
(4) You may view this service information
at 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.
(5) You may view this service information
that is incorporated by reference at the
National Archives and Records
Administration (NARA). For information on
the availability of this material at NARA, call
202–741–6030, or go to: https://
www.archives.gov/federal-register/cfr/ibrlocations.html.
Issued in Kansas City, Missouri on March
17, 2017.
William Schinstock,
Acting Manager, Small Airplane Directorate,
Aircraft Certification Service.
[FR Doc. 2017–05857 Filed 3–30–17; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
nlaroche on DSK30NT082PROD with RULES
14 CFR Part 39
[Docket No. FAA–2017–0245; Directorate
Identifier 2017–NM–023–AD; Amendment
39–18841; AD 2017–07–05]
RIN 2120–AA64
Airworthiness Directives; Airbus
Airplanes
Federal Aviation
Administration (FAA), DOT.
AGENCY:
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Jkt 241001
Final rule; request for
comments.
ACTION:
We are adopting a new
airworthiness directive (AD) for all
Airbus Model A330–243, –243F, –341,
–342, and –343 airplanes. This AD
requires an inspection to determine if
affected hydraulic pressure tube
assemblies are installed, and
replacement with serviceable hydraulic
pressure tube assemblies if necessary.
This AD also requires repetitive
replacements of serviceable hydraulic
pressure tube assemblies. This AD was
prompted by a determination that cracks
can develop on the ripple damper of the
hydraulic pressure tube assembly and
reports of failure of the ripple damper
of the hydraulic pressure tube assembly.
We are issuing this AD to address the
unsafe condition on these products.
DATES: This AD becomes effective April
17, 2017.
The Director of the Federal Register
approved the incorporation by reference
of a certain publication listed in this AD
as of April 17, 2017.
We must receive comments on this
AD by May 15, 2017.
ADDRESSES: You may send comments,
using the procedures found in 14 CFR
11.43 and 11.45, by any of the following
methods:
• Federal eRulemaking Portal: Go to
https://www.regulations.gov. Follow the
instructions for submitting comments.
• Fax: 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, between 9 a.m. and 5
p.m., Monday through Friday, except
Federal holidays.
For service information identified in
this final rule, contact Airbus SAS,
Airworthiness Office—EAL, 1 Rond
Point Maurice Bellonte, 31707 Blagnac
Cedex, France; telephone +33 5 61 93 36
96; fax +33 5 61 93 45 80; email
airworthiness.A330-A340@airbus.com;
Internet https://www.airbus.com. You
may view this referenced service
information at the FAA, Transport
Airplane Directorate, 1601 Lind Avenue
SW., Renton, WA. For information on
the availability of this material at the
FAA, call 425–227–1221. It is also
available on the Internet at https://
www.regulations.gov by searching for
and locating Docket No. FAA–2017–
0245.
SUMMARY:
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15985
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–
0245; or in person at the Docket
Operations office between 9 a.m. and 5
p.m., Monday through Friday, except
Federal holidays. The AD docket
contains this AD, the regulatory
evaluation, any comments received, and
other information. The street address for
the Docket Operations 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:
Vladimir Ulyanov, Aerospace Engineer,
International Branch, ANM–116,
Transport Airplane Directorate, FAA,
1601 Lind Avenue SW., Renton, WA
98057–3356; telephone 425–227–1138;
fax 425–227–1149.
SUPPLEMENTARY INFORMATION:
Discussion
The European Aviation Safety Agency
(EASA), which is the Technical Agent
for the Member States of the European
Union, has issued EASA Airworthiness
Directive 2017–0041, dated February 24,
2017; corrected February 28, 2017
(referred to after this as the Mandatory
Continuing Airworthiness Information,
or ‘‘the MCAI’’), to correct an unsafe
condition for all Airbus Model A330–
243, –243F, –341, –342, and –343
airplanes. The MCAI states:
Following introduction in-service of
Airbus modification (mod) 205242, a new
hydraulic pressure tube assembly Part
Number (P/N) AE711121–18 was installed,
one on each engine, with an integral ripple
damper. It was determined that, at a
relatively low number of cycles, cracks can
develop on the ripple damper weld of this
new hydraulic pressure tube, which could
lead to hydraulic leakage and consequent
loss of the green hydraulic system. Recently,
there has been a high rate of failure of the
affected dampers that, if continued, may
exceed the overall safety objective of the
certified design.
This condition, if not corrected, could, in
combination with other system failures,
result in reduced control of the aeroplane.
Prompted by these findings, Airbus issued
Alert Operators Transmission (AOT)
A71L012–16 Revision 01, to provide
instructions to replace the hydraulic pressure
tube assembly P/N AE711121–18 with an
improved assembly, P/N AE711121–18 Rev
A, equipped with a double-welded ripple
damper.
For the reasons described above, this
[EASA] AD requires [inspection for and]
replacement of each affected hydraulic
pressure tube assembly with a [serviceable]
tube assembly having the double welded
ripple damper installed. This [EASA] AD
also requires implementation of a life limit
E:\FR\FM\31MRR1.SGM
31MRR1
]]>Agencies
[Federal Register Volume 82, Number 61 (Friday, March 31, 2017)]
[Rules and Regulations]
[Pages 15982-15985]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2017-05857]
=======================================================================
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2016-9531; Directorate Identifier 2015-CE-011-AD;
Amendment 39-18839; AD 2017-07-01]
RIN 2120-AA64
Airworthiness Directives; M7 Aerospace LLC Models Airplanes
AGENCY: Federal Aviation Administration (FAA), DOT.
ACTION: Final rule.
-----------------------------------------------------------------------
SUMMARY: We are adopting a new airworthiness directive (AD) for certain
M7 Aerospace LLC Models SA226-T, SA226-AT, SA226-T(B), SA226-TC, SA227-
AC (C-26A), SA227-AT, SA227-BC (C-26A), SA227-CC, SA227-DC (C-26B), and
SA227-TT airplanes. This AD was prompted by detachment of the power
lever linkage to the TPE331 engine propeller pitch control. This AD
requires repetitively inspecting the propeller pitch control for proper
torque, with corrections as necessary until required replacement or
rework of the PPC assembly to have a threaded hole in the splined end
of the shouldered shaft and installation of a secondary retention
device is done. We are issuing this AD to correct the unsafe condition
on these products.
DATES: This AD is effective May 5, 2017.
The Director of the Federal Register approved the incorporation by
reference of certain publications listed in this AD as of May 5, 2017.
ADDRESSES: For service information identified in this final rule,
contact M7 Aerospace LLC, 10823 NE Entrance Road, San Antonio, Texas
78216; phone: (210) 824-9421; fax: (210) 804-7766; Internet: https://www.elbitsystems-us.com; email: MetroTech@M7Aerospace.com; or Honeywell
International Inc. 111 S. 34th Street, Phoenix, Arizona 85034-2802;
phone: (855) 808-6500; email: AeroTechSupport@honeywell.com; Internet:
https://aerospace.honeywell.com/en/services/maintenance-and-monitoring.
You may view 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. It is also available on the internet at https://www.regulations.gov by searching for and locating Docket No. FAA-2016-
9531.
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-2016-
9531; or in person at the Docket Management Facility between 9 a.m. and
5 p.m., Monday through Friday, except Federal holidays. The AD docket
contains this AD, the regulatory evaluation, any comments received, and
other information. The address for the Docket Office (phone: 800-647-
5527) is Document Management Facility, U.S. Department of
Transportation, Docket Operations, M-30, West Building Ground Floor,
Room W12-140, 1200 New Jersey Avenue SE., Washington, DC 20590.
FOR FURTHER INFORMATION CONTACT ONE OF THE FOLLOWING:
Justin Carter, ASW-142, Aerospace Engineer, Fort Worth
Airplane Certification Office (ACO), FAA, 10101 Hillwood Parkway, Fort
Worth, Texas 76177-1524; telephone: (817) 222-5146; fax: (817) 222-
5960; email: justin.carter@faa.gov; or
Kristin Bradley, ASW-143, Aerospace Engineer, Fort Worth
ACO, FAA, 10101 Hillwood Parkway, Fort Worth, Texas 76177-1524;
telephone: (817) 222-5485; fax: (817) 222-5960; email:
kristin.bradley@faa.gov.
SUPPLEMENTARY INFORMATION:
Discussion
We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR
part 39 by adding an AD that would apply to certain M7 Aerospace LLC
Models SA226-T, SA226-AT, SA226-T(B), SA226-TC, SA227-AC (C-26A),
SA227-AT, SA227-BC (C-26A), SA227-CC, SA227-DC (C-26B), and SA227-TT
airplanes. The NPRM published in the Federal Register on December 28,
2016 (81 FR 95528). The NPRM was prompted by reports of the airplane
power lever linkage detaching from the TPE331 engine propeller pitch
control (PPC) shaft. In flight operations, detachment may result in
fuel flow to the engine remaining constant regardless of the power
lever movement by the pilot. The orientation of the engine on certain
M7 Aerospace airplanes increases the vulnerability of detachment. The
PPC lever is an airplane part and its detachment from
[[Page 15983]]
the TPE311 has been the subject of previous ADs on other airplane type
designs. The NPRM proposed to require repetitive inspections of the PPC
lever with corrective action as necessary until required replacement or
rework of the PPC assembly to have a threaded hole in the splined end
of the shouldered shaft and installation of a secondary retention
feature for the airplane control linkage interface is done. We are
issuing this AD to correct the unsafe condition on these products.
Comments
We gave the public the opportunity to participate in developing
this AD. We received no comments on the NPRM or on the determination of
the cost to the public.
Conclusion
We reviewed the relevant data and determined that air safety and
the public interest require adopting this AD as proposed. We have
determined that these minor changes:
Are consistent with the intent that was proposed in the
NPRM for correcting the unsafe condition; and
Do not add any additional burden upon the public than was
already proposed in the NPRM.
Related Service Information Under 1 CFR Part 51
We reviewed M7 Aerospace LLC SA226 Series Service Bulletin 226-76-
012, dated March 17, 2015; M7 Aerospace LLC SA227 Series Service
Bulletin 227-76-007, dated March 17, 2015; and M7 Aerospace LLC SA227
Series Commuter Category Service Bulletin CC7-76-004, dated March 17,
2015; that, in combination with the temporary revisions and service
bulletin listed below, describes the actions that must be done for the
applicable models to comply with this AD.
We also reviewed M7 Aerospace SA226 Series Maintenance Manual
Temporary Revision 71-02, dated March 15, 2016; M7 Aerospace SA227
Series Maintenance Manual Temporary Revision 71-03, dated March 15,
2016; and M7 Aerospace SA227 Series Commuter Category Maintenance
Manual Temporary Revision 71-02, dated March 15, 2016; that describes
procedures for installing the secondary retention device on the PPC
assembly and doing a visual inspection of the PPC lever for the
applicable models.
We also reviewed Honeywell International Inc. Service Bulletin
TPE331-72-2190, dated December 21, 2011, that describes procedures for
replacing or reworking the propeller pitch control assembly,
incorporating a threaded hole in the splined end of the shouldered
shaft, and reassembling the propeller pitch control assembly.
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
document.
Costs of Compliance
We estimate that this AD affects 360 airplanes of U.S. registry.
We estimate the following costs to comply with this AD:
Estimated Costs
----------------------------------------------------------------------------------------------------------------
Cost per Cost on U.S.
Action Labor cost Parts cost product operators
----------------------------------------------------------------------------------------------------------------
Replacement or rework of the PPC 19 work-hours x $85 $1,000................. $2,615 $941,400
assembly. per hour = $1,615.
Install secondary retention 1 work-hour x $85 10..................... 95 34,200
device. per hour = $85.
Visual inspection of PPC lever... .5 work-hour x $85 Not applicable......... 42.50 15,300
per hour = $42.50.
----------------------------------------------------------------------------------------------------------------
We estimate the following costs to do any necessary adjustments
that would be required based on the results of the visual inspection.
We have no way of determining the number of aircraft that might need
these adjustments:
On-Condition Costs
----------------------------------------------------------------------------------------------------------------
Cost per
Action Labor cost Parts cost product
----------------------------------------------------------------------------------------------------------------
Correct attachment of the PPC lever.... .5 work-hour x $85 per Not applicable.............. $42.50
hour = $42.50.
----------------------------------------------------------------------------------------------------------------
Authority for This Rulemaking
Title 49 of the United States Code specifies the FAA's authority to
issue rules on aviation safety. Subtitle I, section 106, describes the
authority of the FAA Administrator. Subtitle VII: Aviation Programs,
describes in more detail the scope of the Agency's authority.
We are issuing this rulemaking under the authority described in
Subtitle VII, Part A, Subpart III, Section 44701: ``General
requirements.'' Under that section, Congress charges the FAA with
promoting safe flight of civil aircraft in air commerce by prescribing
regulations for practices, methods, and procedures the Administrator
finds necessary for safety in air commerce. This regulation is within
the scope of that authority because it addresses an unsafe condition
that is likely to exist or develop on products identified in this
rulemaking action.
Regulatory Findings
This AD will not have federalism implications under Executive Order
13132. This AD will not have a substantial direct effect on the States,
on the relationship between the national government and the States, or
on the distribution of power and responsibilities among the various
levels of government.
For the reasons discussed above, I certify that this AD:
(1) Is not a ``significant regulatory action'' under Executive
Order 12866,
(2) Is not a ``significant rule'' under DOT Regulatory Policies and
Procedures (44 FR 11034, February 26, 1979),
(3) Will not affect intrastate aviation in Alaska, and
(4) Will not have a significant economic impact, positive or
negative, on a substantial number of small entities under the criteria
of the Regulatory Flexibility Act.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation safety, Incorporation by
reference, Safety.
[[Page 15984]]
Adoption of the Amendment
Accordingly, under the authority delegated to me by the
Administrator, the FAA amends 14 CFR part 39 as follows:
PART 39--AIRWORTHINESS DIRECTIVES
0
1. The authority citation for part 39 continues to read as follows:
Authority: 49 U.S.C. 106(g), 40113, 44701.
Sec. 39.13 [Amended]
0
2. The FAA amends Sec. 39.13 by adding the following new airworthiness
directive (AD):
2017-07-01 M7 Aerospace LLC: Amendment 39-18839; Docket No. FAA-
2016-9531; Directorate Identifier 2015-CE-011-AD.
(a) Effective Date
This AD is effective May 5, 2017.
(b) Affected ADs
None.
(c) Applicability
This AD applies to M7 Aerospace LLC SA226-T, SA226-AT, SA226-
T(B), SA226-TC, SA227-AC (C-26A), SA227-AT, SA227-BC (C-26A), SA227-
CC, SA227-DC (C-26B), and SA227-TT airplanes; all serial numbers,
certificated in any category.
(d) Subject
Joint Aircraft System Component (JASC)/Air Transport Association
(ATA) of America Code 61, Propellers/Propulsors.
(e) Unsafe Condition
This AD was prompted by detachment of the power lever linkage to
the TPE331 engine propeller pitch control (PPC). We are issuing this
AD to prevent detachment of the power lever linkage to the TPE331
engine PPC, which could result in uncommanded change to the engine
power settings with consequent loss of control.
(f) Compliance
Comply with this AD within the compliance times specified,
unless already done.
(g) Applicable M7 Aerospace LLC Service Bulletins
Use the applicable service bulletins as listed in paragraph
(g)(1), (2), or (3) of this AD as reference to complete the actions
in paragraph (i)(1) or (2) of this AD:
(1) M7 Aerospace LLC SA226 Series Service Bulletin 226-76-012,
dated March 17, 2015;
(2) M7 Aerospace LLC SA227 Series Service Bulletin 227-76-007,
dated March 17, 2015; or
(3) M7Aerospace LLC SA227 Series Commuter Category Service
Bulletin CC7-76-004, dated March 17, 2015.
(h) PPC Lever Installation
(1) Within 100 hours time-in-service (TIS) after May 5, 2017
(the effective date of this AD) and repetitively thereafter at
intervals not to exceed 100 hours TIS, visually inspect the PPC
lever to assure the attachment is properly installed following the
applicable service information listed in paragraph (h)(1)(i), (ii),
or (iii) of this AD, as applicable.
(i) For Models SA226 Series: M7 Aerospace SA226 Series
Maintenance Manual Temporary Revision 71-02, dated March 15, 2016.
(ii) For Models SA227 Series: M7 Aerospace SA227 Series
Maintenance Manual Temporary Revision 71-03, dated March 15, 2016.
(iii) For Models SA227 Series Commuter Category: M7 Aerospace
SA227 Series Commuter Category Maintenance Manual Temporary Revision
71-02, dated March 15, 2016.
(2) The rework/replacement required by paragraph (i) of the AD
and the installation of the secondary retention device required in
paragraph (j) of this AD terminate the repetitive visual inspections
of the PPC lever attachment required by paragraph (h)(1) of this AD.
(i) Replace or Rework the Propeller Pitch Assembly
Within the next 600 hours TIS after May 5, 2017 (the effective
date of this AD) or within the next 12 months after May 5, 2017 (the
effective date of this AD), whichever occurs first, do the actions
in either paragraph (i)(1) or (2) of this AD following the
Accomplishment Instructions in Honeywell International Inc. Service
Bulletin TPE331-72-2190, dated December 21, 2011, as referenced in
the applicable service information listed in paragraph (g)(1), (2),
or (3) this AD.
(1) Replace the PPC. Remove the PPC assembly and replace with
the applicable new design PPC using the part numbers listed in table
1 to paragraph (i)(1) of this AD.
Table 1 to Paragraph (i)(1) of This AD--Part Number PPC Assemblies
------------------------------------------------------------------------
Part No. PPC
Part No. PPC assembly to remove assembly to
install
------------------------------------------------------------------------
869130-11............................................... 70000295-11
869130-12............................................... 70000295-12
869130-13............................................... 70000295-13
869130-14............................................... 70000295-14
869130-16............................................... 70000295-16
869130-17............................................... 70000295-17
869130-18............................................... 70000295-18
869130-19............................................... 70000295-19
869130-30............................................... 70000295-30
895481-1................................................ 70000298-1
895481-2................................................ 70000298-2
895481-4................................................ 70000298-4
895481-5................................................ 70000298-5
895481-6................................................ 70000298-6
895481-7................................................ 70000298-7
895481-17............................................... 70000298-17
895481-18............................................... 70000298-18
895481-19............................................... 70000298-19
895481-20............................................... 70000298-20
895481-22............................................... 70000298-22
------------------------------------------------------------------------
(2) Rework the PPC assembly. Inspect the splined end of the
shouldered shaft for the presence and good condition of a threaded
hole, repairing or replacing the cam assembly, and reworking the PPC
assembly as necessary.
(j) Secondary Retention Feature
(1) Before further flight after the replacement or rework of the
PPC assembly required in paragraph (i)(1) or (2) of this AD, install
the secondary retention feature on the PPC assembly following the
applicable service information listed in paragraph (j)(1)(i), (ii),
or (iii) of this AD.
(i) For Models SA226 Series: M7 Aerospace SA226 Series
Maintenance Manual Temporary Revision 71-02, dated March 15, 2016.
(ii) For Models SA227 Series: M7 Aerospace SA227 Series
Maintenance Manual Temporary Revision 71-03, dated March 15, 2016.
(iii) For Models SA227 Series Commuter Category: M7 Aerospace
SA227 Series Commuter Category Maintenance Manual Temporary Revision
71-02, dated March 15, 2016.
(2) The rework/replacement required by paragraph (i) of this AD
and the installation of the secondary retention device required by
paragraph (j) of this AD terminate the requirement for the
repetitive inspections of the PPC lever torque required in paragraph
(h) of this AD.
(k) Alternative Methods of Compliance (AMOCs)
(1) The Manager, Fort Worth Airplane 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, mail it to the
attention of one of the people identified in paragraph (l), Related
Information, of this AD or email the request to 9-asw-FWACO@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.
(l) Related Information
For more information about this AD, contact one of the following
people:
(1) Justin Carter, ASW-142, Aerospace Engineer, Fort Worth
Airplane Certification Office (ACO), FAA, 10101 Hillwood Parkway,
Fort Worth, Texas 76177-1524; telephone: (817) 222-5146; fax: (817)
222-5960; email: justin.carter@faa.gov; or
(2) Kristin Bradley, ASW-143, Aerospace Engineer, Fort Worth
ACO, FAA, 10101 Hillwood Parkway, Fort Worth, Texas 76177-1524;
telephone: (817) 222-5485; fax: (817) 222-5960; email:
kristin.bradley@faa.gov.
(m) Material Incorporated by Reference
(1) The Director of the Federal Register approved the
incorporation by reference (IBR) of the service information listed
in this paragraph under 5 U.S.C. 552(a) and 1 CFR part 51.
[[Page 15985]]
(2) You must use this service information as applicable to do
the actions required by this AD, unless the AD specifies otherwise.
(i) M7 Aerospace LLC SA226 Series Service Bulletin 226-76-012,
dated March 17, 2015.
(ii) M7 Aerospace LLC SA227 Series Service Bulletin 227-76-007,
dated March 17, 2015.
(iii) M7Aerospace LLC SA227 Series Commuter Category Service
Bulletin CC7-76-004, dated March 17, 2015.
(iv) M7 Aerospace SA226 Series Maintenance Manual Temporary
Revision 71-02, dated March 15, 2016.
(v) M7 Aerospace SA227 Series Maintenance Manual Temporary
Revision 71-03, dated March 15, 2016.
(vi) M7 Aerospace SA227 Series Commuter Category Maintenance
Manual Temporary Revision 71-02, dated March 15, 2016.
(vii) Honeywell International Inc. Service Bulletin TPE331-72-
2190, dated December 21, 2011.
(3) For service information identified in this AD, contact M7
Aerospace LLC, 10823 NE Entrance Road, San Antonio, Texas 78216;
phone: (210) 824-9421; fax: (210) 804-7766; Internet: https://www.elbitsystems-us.com; email: MetroTech@M7Aerospace.com; or
Honeywell International Inc. 111 S. 34th Street, Phoenix, Arizona
85034-2802; phone: (855) 808-6500; email:
AeroTechSupport@honeywell.com; Internet: https://aerospace.honeywell.com/en/services/maintenance-and-monitoring.
(4) You may view this service information at 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.
(5) You may view this service information that is incorporated
by reference at the National Archives and Records Administration
(NARA). For information on the availability of this material at
NARA, call 202-741-6030, or go to: https://www.archives.gov/federal-register/cfr/ibr-locations.html.
Issued in Kansas City, Missouri on March 17, 2017.
William Schinstock,
Acting Manager, Small Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 2017-05857 Filed 3-30-17; 8:45 am]
BILLING CODE 4910-13-P
