Airworthiness Directives; M7 Aerospace LLC Airplanes, 58354-58357 [2015-24249]
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58354
Federal Register / Vol. 80, No. 188 / Tuesday, September 29, 2015 / Rules and Regulations
14 CFR part 91, subpart K, we suggest that
you notify your principal inspector, or
lacking a principal inspector, the manager of
the local flight standards district office or
certificate holding district office before
operating any aircraft complying with this
AD through an AMOC.
(h) Additional Information
(1) Airbus Helicopters Alert Service
Bulletin No. ASB BO105–10–125, Revision 3,
dated May 27, 2014, and Eurocopter Service
Bulletin B0105–10–126, Revision 1, dated
August 6, 2013, which are not incorporated
by reference, contain additional information
about the subject of this AD. For service
information identified in this AD, contact
Airbus Helicopters, 2701 N. Forum Drive,
Grand Prairie, TX 75052; telephone (972)
641–0000 or (800) 232–0323; fax (972) 641–
3775; or at https://
www.airbushelicopters.com/techpub.You
may review a copy of the service information
at the FAA, Office of the Regional Counsel,
Southwest Region, 10101 Hillwood Pkwy.,
Room 6N–321, Fort Worth, Texas 76177.
(2) The subject of this AD is addressed in
European Aviation Safety Agency (EASA) AD
2014–0230, dated October 21, 2014. You may
view the EASA AD on the Internet at https://
www.regulations.gov by searching for and
locating Docket No. FAA–2012–0503.
(i) Subject
Joint Aircraft Service Component (JASC)
Code: 6320 Main Gear Box.
Issued in Fort Worth, Texas, on September
17, 2015.
James A. Grigg,
Acting Manager, Rotorcraft Directorate,
Aircraft Certification Service.
[FR Doc. 2015–24256 Filed 9–28–15; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2015–2207; Directorate
Identifier 2015–CE–003–AD; Amendment
39–18272; AD 2015–19–10]
Examining the AD Docket
RIN 2120–AA64
Airworthiness Directives; M7
Aerospace LLC Airplanes
Federal Aviation
Administration (FAA), DOT.
ACTION: Final rule.
AGENCY:
We are superseding
Airworthiness Directive (AD) 97–02–02
for certain Models SA26–AT, SA26–T,
SA226–AT, SA226–T, 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. AD 97–02–02
required applying torque to the control
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SUMMARY:
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column pitch bearing attaching nuts,
inspecting the bearing assembly,
inspecting the elevator control rod end
bearing retainer/dust seals, and
replacing or installing new parts as
necessary. This new AD requires
inspecting for movement and correct
torque of the elevator control pivot
bearing, inspecting the elevator control
rod for damage and correct
configuration, and replacing parts as
necessary. This AD also requires a
10,000-hour time-in-service (TIS)
repetitive replacement of the control
column pivot bearing and elevator
control rod bolt and requires
replacement of the control column pivot
bearing with the improved design by
35,000 hours TIS. This AD was
prompted by loss of elevator control due
to failure of the bolt attaching the
elevator control rod to the elevator
walking beam under the cockpit floor.
We are issuing this AD to correct the
unsafe condition on these products.
DATES: This AD is effective November 3,
2015.
The Director of the Federal Register
approved the incorporation by reference
of certain publications listed in this AD
as of November 3, 2015.
ADDRESSES: 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. 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 Docket No. FAA–2015–
2207.
You may examine the AD docket on
the Internet at https://
www.regulations.govby searching for
and locating Docket No. FAA–2015–
2207; 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.
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FOR FURTHER INFORMATION CONTACT:
Andrew McAnaul, Aerospace Engineer,
FAA, ASW–143 (c/o San Antonio
MIDO), 10100 Reunion Place, Suite 650,
San Antonio, Texas 78216; phone: (210)
308–3365; fax: (210) 308–3370; email:
andrew.mcanaul@faa.gov.
SUPPLEMENTARY INFORMATION:
Discussion
We issued a notice of proposed
rulemaking (NPRM) to amend 14 CFR
part 39 to supersede AD 97–02–02,
Amendment 39–9886 (62 FR 2552,
January 17, 1997), (‘‘AD 97–02–02’’). AD
97–02–02 applied to certain M7
Aerospace LLC Models SA26–AT,
SA26–T, SA226–AT, SA226–T, 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
June 16, 2015 (80 FR 34326). The NPRM
was prompted by an operator
experiencing complete loss of elevator
control due to failure of the bolt
attaching the elevator control rod to the
elevator walking beam under the
cockpit floor. A follow-on inspection of
the operator’s fleet revealed a variety of
hardware installed. Some hardware
matched the illustrated parts catalog
(IPC), some matched the AD 97–02–02
configuration, and some matched
neither of those configurations.
When AD 97–02–02 was issued, the
IPC was never revised to match the
hardware configuration called out in AD
97–02–02 or in the service information
associated with that AD. Because of the
conflict between the AD and the IPC
configurations, an airplane that was in
compliance with the requirements of
AD 97–02–02 could have had an
incorrect hardware configuration
installed during routine maintenance
after complying with the AD. The IPC
has been updated and corrected by M7
Aerospace, LLC.
Also, since we issued AD 97–02–02,
the manufacturer developed an
improved design for the control column
pivot bearing and support structure that
terminates the repetitive torque check
and replacement of control column
pivot bearings.
The manufacturer also issued new
service information that adds the
10,000-hour TIS repetitive replacement
of the control column pivot bearing that
is in the airworthiness limitations
section (ALS) of the airplane
maintenance manual (AMM) and (if this
revision is mandated) requires the
replacement of the pivot bearing with
the improved design by 35,000 hours
TIS that is in the supplemental
inspections document (SID). Issuance of
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Federal Register / Vol. 80, No. 188 / Tuesday, September 29, 2015 / Rules and Regulations
the new service information, the revised
IPC, and this AD will eliminate the
conflicts between AD 97–02–02, the
service information, the IPC, the ALS,
and the SID.
The NPRM (80 FR 34326, June 16,
2015) proposed to require inspecting for
movement and correct torque of the
elevator control pivot bearing,
inspecting the elevator control rod for
damage and correct configuration, and
replacing parts as necessary. The NPRM
also proposed to require a 10,000-hour
TIS repetitive replacement of the control
column pivot bearing and elevator
control rod bolt and require replacement
of the control column pivot bearing with
the improved design by 35,000 hours
TIS. Replacing the original control
column pivot bearing with the improved
design terminates the requirement to
repetitively replace the original control
column pivot bearing every 10,000
hours. 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 (80
FR 34326, June 16, 2015) 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 except for minor editorial
changes. We have determined that these
minor changes:
• Are consistent with the intent that
was proposed in the NPRM (80 FR
34326, June 16, 2015) for correcting the
unsafe condition; and
• Do not add any additional burden
upon the public than was already
proposed in the NPRM (80 FR 34326,
June 16, 2015).
Relevant Service Information Under 1
CFR 51
We reviewed M7 Aerospace SA26
Series Service Bulletin No. 26–27–30–
046 R2, dated December 5, 2014;
Fairchild Aircraft SA26 Series Service
Bulletin No. 26–27–30–047, dated June
16, 1997; M7 Aerospace SA226 Series
Service Bulletin No. 226–27–060 R2,
dated December 5, 2014; Fairchild
Aerospace SA226 Series Service
Bulletin No. 226–27–061, dated June 16,
1997; M7 Aerospace SA227 Series
Service Bulletin, No. 227–27–041 R2,
dated December 5, 2014; Fairchild
Aircraft SA227 Series Service Bulletin
No. 227–27–042, dated June 16, 1997;
M7 Aerospace LLC SA227 Series
Commuter Category Service Bulletin No.
CC7–27–010 R2, dated December 5,
2014; and Fairchild Aircraft SA227
Series Commuter Category Service
Bulletin No. CC7–27–011, dated June
16, 1997. The service information
describes procedures for inspecting for
movement and correct torque of the
elevator control pivot bearing,
inspecting the elevator control rod for
damage, and replacing parts as
necessary. The service information also
adds a repetitive replacement of the
control column pivot bearings at 10,000
hours TIS and requires replacement of
the control column pivot bearing with
the improved design within 35,000
hours TIS. This 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 AD.
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
product
Cost on U.S.
operators
Action
Labor cost
Parts cost
Inspection of torque on the control column
pivot bearing.
Control column pivot bearing replacement ....
New designed control column pivot bearing
replacement.
Elevator rod end bolt replacement .................
2 work-hours × $85 per hour = $170 ............
Not applicable
$170
$61,200
8 work-hours × $85 per hour = $680 ............
20 work-hours × $85 per hour = $1,700 .......
$300 ................
$2,450 .............
980
4,150
352,800
1,494,000
4 work-hours × $85 per hour = $340 ............
$10 ..................
350
126,000
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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
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 have determined that this AD will
not have federalism implications under
Executive Order 13132. This AD will
not have a substantial direct effect on
the States, on the relationship between
the national government and the States,
or on the distribution of power and
responsibilities among the various
levels of government.
For the reasons discussed above, I
certify that 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,
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on a substantial number of small entities
under the criteria of the Regulatory
Flexibility Act.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation
safety, Incorporation by reference,
Safety.
Adoption of the Amendment
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.
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§ 39.13
Federal Register / Vol. 80, No. 188 / Tuesday, September 29, 2015 / Rules and Regulations
[Amended]
2. The FAA amends § 39.13 by
removing Airworthiness Directive (AD)
97–02–02, Amendment 39–9886 (62 FR
2552, January 17, 1997), and adding the
following new AD:
■
2015–19–10 M7 Aerospace: Amendment
39–18272; Docket No. FAA–2015–2207;
Directorate Identifier 2015–CE–003–AD.
(a) Effective Date
This AD is effective November 3, 2015.
(h) Control Column Pivot Bearing Revised
(Modified) Configuration
(b) Affected ADs
This AD supersedes AD 97–02–02,
Amendment 39–9886 (62 FR 2552, January
17, 1997).
(c) Applicability
This AD applies to M7 Aerospace LLC
Models SA26–AT, SA26–T, SA226–AT,
SA226–T, SA226–T(B), SA226–TC, SA227–
AC (C–26A), SA227–AT, SA227–BC (C–26A),
SA227–CC, SA227–DC (C–26B), SA227–TT,
all serial numbers, certificated in any
category.
(d) Subject
Joint Aircraft System Component (JASC)/
Air Transport Association (ATA) of America
Code 27, Flight Controls.
(e) Unsafe Condition
AD 97–02–02 (62 FR 2552, January 17,
1997) (‘‘AD 97–02–02’’) resulted from reports
of Fairchild SA227 series airplanes losing
pitch control in-flight. This supersedure was
prompted by an operator experiencing
complete loss of elevator control because of
failure of the bolt attaching the elevator
control rod to the elevator walking beam
under the cockpit floor. We are issuing this
AD to prevent loss of pitch control, which if
not corrected, could result in loss of airplane
control.
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(f) Compliance
Comply with this AD within the
compliance times specified, unless already
done. Models SA227–CC and SA227–DC,
serial numbers 892, 893, and 895 and up,
have the revised (modified) configuration.
Since those airplanes are already in
compliance, they do not have to do the
actions in paragraphs (h) or (i) of this AD,
including all subparagraphs. Those airplanes
must still do the actions required in
paragraph (j) of this AD, including all
subparagraphs.
(g) Credit for Actions Accomplished in
Accordance With Previous Service
Information
This AD allows credit for the control
column pivot bearing torque check and
initial replacement required in paragraph
(i)(2) of this AD and the elevator rod bolt
inspection and initial replacement required
in paragraphs (j)(1) and (j)(3)(i) of this AD, if
done before November 3, 2015 (the effective
date of this AD), following the procedures
specified in the Accomplishment
Instructions of the applicable service
information listed in paragraphs (g)(1)
through (g)(4) of this AD:
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(1) M7 Aerospace SA227 Commuter
Category Service Bulletin No. CC7–27–010,
original issue or revision 1.
(2) M7 Aerospace SA227 Series Service
Bulletin No. 227–27–041, original issue or
revision 1.
(3) M7 Aerospace SA226 Series Service
Bulletin No. 226–27–060, original issue or
revision 1.
(4) M7 Aerospace SA26 Series Service
Bulletin No. 26–27–30–046, original issue or
revision 1.
(1) On or before the airplane accumulates
a total of 35,000 hours time-in-service (TIS)
or within the next 1,000 hours TIS after
November 3, 2015 (the effective date of this
AD), whichever occurs later, you must revise
(modify) the control column pivot bearing
configuration with the improved design. Use
the applicable service information listed in
paragraphs (h)(1)(i) through (h)(1)(iv) of this
AD. Revising (modifying) the configuration of
the control column pivot bearing with the
improved design terminates the actions for
paragraph (i) of this AD, including all
subparagraphs, but you must still complete
the required actions in paragraph (j) of this
AD, including all subparagraphs.
(i) Fairchild Aircraft SA26 Series Service
Bulletin No. 26–27–30–047, dated June 16,
1997;
(ii) Fairchild Aircraft SA226 Series Service
Bulletin No. 226–27–061, dated June 16,
1997;
(iii) Fairchild Aircraft SA227 Series
Service Bulletin No. 227–27–042, dated June
16, 1997; or
(iv) Fairchild Aircraft SA227 Series
Commuter Category No. CC7–27–011, dated
June 16, 1997.
(2) You may at any time before 35,000
hours TIS revise (modify) the control column
pivot bearing configuration with the
improved design to terminate the repetitive
replacement of the original control column
pivot bearing using the applicable service
information listed in paragraphs (h)(1)(i)
through (h)(1)(iv) of this AD. This action
terminates the requirements of paragraph (i)
of this AD, including all subparagraphs, but
you must still complete the required actions
in paragraph (j) of this AD, including all
subparagraphs.
(i) Torque Check or Replacement of the
Control Column Pivot Bearing
(1) Use the service information, as
applicable, listed in paragraphs (i)(1)(i)
through (i)(1)(iv) of this AD to do a control
column pivot bearing torque check or
replacement at the applicable compliance
times in paragraph (i)(2) or (i)(3) of this AD,
including all subparagraphs:
(i) M7 Aerospace LLC SA26 Series Service
Bulletin No. 26–27–30–046 R2, dated
December 5, 2014;
(ii) M7 Aerospace LLC SA226 Series
Service Bulletin No. 226–27–060 R2, dated
December 5, 2014;
(iii) M7 Aerospace LLC SA227 Series
Service Bulletin No. 227–27–041 R2, dated
December 5, 2014; or
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(iv) M7 Aerospace LLC SA227 Series
Commuter Category Service Bulletin No.
CC7–27–010 R2, December 5, 2014.
(2) For airplanes where the control column
pivot bearing has been torque checked or
replaced within the last 10,000 hours TIS
before November 3, 2015 (the effective date
of this AD) using the applicable service
information listed in paragraph (g)(1) through
(g)(4) or (i)(1)(i) through (i)(1)(iv) of this AD,
do one of the following actions:
(i) Within the next 10,000 hours TIS after
the last control column pivot bearing
replacement or within the next 1,000 hours
TIS after November 3, 2015 (the effective date
of this AD), whichever occurs later, and
repetitively thereafter every 10,000 hours
TIS, replace the control column pivot bearing
following paragraph 2.B. of the
Accomplishment Instructions of the
applicable service information listed in
paragraphs (i)(1)(i) through (i)(1)(iv) of this
AD; or
(ii) Within the next 10,000 hours TIS after
the last control column pivot bearing
replacement or within the next 1,000 hours
TIS after November 3, 2015 (the effective date
of this AD), whichever occurs later, revise
(modify) the control column pivot bearing
configuration with the improved design
using the applicable service information
listed in paragraphs (h)(1)(i) through
(h)(1)(iv) of this AD. Revising (modifying) the
configuration of the control column pivot
bearing with the improved design terminates
the repetitive replacement of the original
control column pivot bearing. No other
actions are required for paragraph (i) of this
AD, including all subparagraphs, but you
must still complete the actions in paragraph
(j) of this AD, including all subparagraphs.
(3) For airplanes where the control column
pivot bearing has not been torque checked or
replaced within the last 10,000 hours TIS
before November 3, 2015 (the effective date
of this AD) using the applicable service
information listed in paragraphs (g)(1)
through (g)(4) or (i)(1)(i) through (i)(1)(iv) of
this AD, within the next 200 hours TIS after
November 3, 2015 (the effective date of this
AD), torque check the control column pivot
bearing following paragraph 2.A. of the
service information listed in paragraphs
(i)(1)(i) through (i)(1)(iv) of this AD.
(4) If nut movement occurs during the
torque check required in paragraph (i)(3) of
this AD, do one of the following actions:
(i) Before further flight and repetitively
thereafter at intervals not to exceed every
10,000 hours TIS, replace the control column
pivot bearing following paragraph 2.B. of the
Accomplishment Instructions of the
applicable service information listed in
paragraphs (i)(1)(i) through (i)(1)(iv) of this
AD; or
(ii) Before further flight, revise (modify) the
control column pivot bearing configuration
with the improved design using the
applicable service information listed in
paragraphs (h)(1)(i) through (h)(1)(iv) of this
AD. Revising (modifying) the configuration of
the control column pivot bearing with the
improved design terminates the repetitive
replacement of the original control column
pivot bearing. No other actions are required
for paragraph (i) of this AD, including all
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subparagraphs, but you must still complete
the actions in paragraph (j) of this AD,
including all subparagraphs.
(5) If no nut movement occurs during the
torque check required in paragraph (i)(3) of
this AD, do one of the following actions:
(i) Within the next 1,000 hours TIS after
November 3, 2015 (the effective date of this
AD), replace the control column pivot
bearing following paragraph 2.B. of the
Accomplishment Instructions of the
applicable service information listed in
paragraphs (i)(1)(i) through (i)(1)(iv) of this
AD; or
(ii) Within the next 1,000 hours TIS after
November 3, 2015 (the effective date of this
AD), revise (modify) the control column
pivot bearing configuration with the
improved design using the applicable service
information listed in paragraphs (h)(1)(i)
through (h)(1)(iv) of this AD. Revising
(modifying) the configuration of the control
column pivot bearing with the improved
design terminates the repetitive replacement
of the original control column pivot bearing.
(j) Inspect the Elevator Control Rod Ends
and Hardware
(1) Within the next 200 hours TIS after
November 3, 2015 (the effective date of this
AD), inspect the elevator control rod ends
and hardware for wear, creasing, or other
damage and verify the elevator rod bolt and
attachment hardware for correct
configuration following paragraph 2.D. of the
Accomplishment Instructions of the
applicable service information listed in
paragraphs (i)(1)(i) through (i)(1)(iv) of this
AD.
(2) If any damage is found during the
inspection required in paragraph (j)(1) of this
AD or the elevator rod bolt and attachment
hardware does not match the correct
configuration, before further flight, replace
the elevator rod bolt, rod ends, and
associated hardware following paragraph 2.D.
of the Accomplishment Instructions of the
applicable service information listed in
paragraphs (i)(1)(i) through (i)(1)(iv) of this
AD.
(3) Replace the elevator rod end bolt and
associated hardware following paragraph 2.D.
of the Accomplishment Instructions of the
applicable service information listed in
paragraphs (i)(1)(i) through (i)(1)(iv) of this
AD at whichever of the following compliance
times applies and repetitively thereafter at
intervals not to exceed 10,000 hours TIS:
(i) For airplanes where the elevator rod bolt
has been replaced: Within the next 10,000
hours TIS after the last elevator rod bolt
replacement or within the next 1,000 hours
TIS after November 3, 2015 (the effective date
of this AD), whichever occurs later; or
(ii) For airplanes where the elevator rod
bolt has never been replaced: Within the next
200 hours TIS after November 3, 2015 (the
effective date of this AD).
(k) Alternative Methods of Compliance
(AMOCs)
(1) The Manager, Fort Worth Airplane
Certification Office, 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
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58357
request to your principal inspector or local
Flight Standards District Office, as
appropriate. If sending information directly
to the manager of the ACO, send it to the
attention of the person identified in
paragraph (l)(1) of this AD.
(2) Before using any approved AMOC,
notify your appropriate principal inspector,
or lacking a principal inspector, the manager
of the local flight standards district office/
certificate holding district office.
Issued in Kansas City, Missouri, on
September 17, 2015.
Melvin Johnson,
Acting Manager, Small Airplane Directorate,
Aircraft Certification Service.
(l) Related Information
Federal Aviation Administration
(1) For more information about this AD,
contact Andrew McAnaul, Aerospace
Engineer, FAA, ASW–143 (c/o San Antonio
MIDO), 10100 Reunion Place, Suite 650, San
Antonio, Texas 78216; phone: (210) 308–
3365; fax: (210) 308–3370; email:
andrew.mcanaul@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.
(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 SA26 Series Service
Bulletin No. 26–27–30–046 R2, dated
December 5, 2014.
(ii) M7 Aerospace LLC SA226 Series
Service Bulletin No. 226–27–060 R2, dated
December 5, 2014.
(iii) M7 Aerospace LLC SA227 Series
Service Bulletin No. 227–27–041 R2, dated
December 5, 2014.
(iv) M7 Aerospace LLC SA227 Series
Commuter Category Service Bulletin No.
CC7–27–010 R2, December 5, 2014.
(v) Fairchild Aircraft SA26 Series Service
Bulletin No. 26–27–30–047, dated June 16,
1997.
(vi) Fairchild Aircraft SA226 Series Service
Bulletin No. 226–27–061, dated June 16,
1997.
(vii) Fairchild Aircraft SA227 Series
Service Bulletin No. 227–27–042, dated June
16, 1997.
(viii) Fairchild Aircraft SA227 Series
Commuter Category No. CC7–27–011, dated
June 16, 1997.
(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.
(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.
PO 00000
Frm 00023
Fmt 4700
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[FR Doc. 2015–24249 Filed 9–28–15; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
14 CFR Part 39
[Docket No. FAA–2014–0773; Directorate
Identifier 2014–NM–068–AD; Amendment
39–18271; AD 2015–19–09]
RIN 2120–AA64
Airworthiness Directives; The Boeing
Company Airplanes
Federal Aviation
Administration (FAA), DOT.
ACTION: Final rule.
AGENCY:
We are adopting a new
airworthiness directive (AD) for all The
Boeing Company Model 787–8
airplanes. This AD was prompted by
reports of a potential latent failure of the
fuel shutoff valve actuator circuitry,
which was not identified during
actuator development. This AD requires
replacing certain engine and auxiliary
power unit (APU) fuel shutoff valve
actuators with new actuators, and also
requires revising the maintenance or
inspection program to include a new
airworthiness limitation into the
Airworthiness Limitations Section
(ALS) of the Instructions for Continued
Airworthiness (ICA). We are issuing this
AD to detect and correct latent failures
of the fuel shutoff valve to the engine
and auxiliary power unit (APU), which
could result in the inability to shut off
fuel to the engine and APU and, in case
of certain fires, an uncontrollable fire
that could lead to structural failure.
DATES: This AD is effective November 3,
2015.
The Director of the Federal Register
approved the incorporation by reference
of a certain publication listed in this AD
as of November 3, 2015.
ADDRESSES: For service information
identified in this AD, contact Boeing
Commercial Airplanes, Attention: Data
& Services Management, P.O. Box 3707,
MC 2H–65, Seattle, WA 98124–2207;
telephone 206–544–5000, extension 1;
fax 206–766–5680; Internet https://
www.myboeingfleet.com. You may view
this referenced service information at
the FAA, Transport Airplane
Directorate, 1601 Lind Avenue SW.,
Renton, WA. For information on the
SUMMARY:
E:\FR\FM\29SER1.SGM
29SER1
]]>Agencies
[Federal Register Volume 80, Number 188 (Tuesday, September 29, 2015)]
[Rules and Regulations]
[Pages 58354-58357]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2015-24249]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2015-2207; Directorate Identifier 2015-CE-003-AD;
Amendment 39-18272; AD 2015-19-10]
RIN 2120-AA64
Airworthiness Directives; M7 Aerospace LLC Airplanes
AGENCY: Federal Aviation Administration (FAA), DOT.
ACTION: Final rule.
-----------------------------------------------------------------------
SUMMARY: We are superseding Airworthiness Directive (AD) 97-02-02 for
certain Models SA26-AT, SA26-T, SA226-AT, SA226-T, 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. AD 97-02-02 required applying torque
to the control column pitch bearing attaching nuts, inspecting the
bearing assembly, inspecting the elevator control rod end bearing
retainer/dust seals, and replacing or installing new parts as
necessary. This new AD requires inspecting for movement and correct
torque of the elevator control pivot bearing, inspecting the elevator
control rod for damage and correct configuration, and replacing parts
as necessary. This AD also requires a 10,000-hour time-in-service (TIS)
repetitive replacement of the control column pivot bearing and elevator
control rod bolt and requires replacement of the control column pivot
bearing with the improved design by 35,000 hours TIS. This AD was
prompted by loss of elevator control due to failure of the bolt
attaching the elevator control rod to the elevator walking beam under
the cockpit floor. We are issuing this AD to correct the unsafe
condition on these products.
DATES: This AD is effective November 3, 2015.
The Director of the Federal Register approved the incorporation by
reference of certain publications listed in this AD as of November 3,
2015.
ADDRESSES: 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. 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 Docket No.
FAA-2015-2207.
Examining the AD Docket
You may examine the AD docket on the Internet at https://www.regulations.govby searching for and locating Docket No. FAA-2015-
2207; 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: Andrew McAnaul, Aerospace Engineer,
FAA, ASW-143 (c/o San Antonio MIDO), 10100 Reunion Place, Suite 650,
San Antonio, Texas 78216; phone: (210) 308-3365; fax: (210) 308-3370;
email: andrew.mcanaul@faa.gov.
SUPPLEMENTARY INFORMATION:
Discussion
We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR
part 39 to supersede AD 97-02-02, Amendment 39-9886 (62 FR 2552,
January 17, 1997), (``AD 97-02-02''). AD 97-02-02 applied to certain M7
Aerospace LLC Models SA26-AT, SA26-T, SA226-AT, SA226-T, 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 June 16, 2015 (80 FR 34326). The NPRM was prompted
by an operator experiencing complete loss of elevator control due to
failure of the bolt attaching the elevator control rod to the elevator
walking beam under the cockpit floor. A follow-on inspection of the
operator's fleet revealed a variety of hardware installed. Some
hardware matched the illustrated parts catalog (IPC), some matched the
AD 97-02-02 configuration, and some matched neither of those
configurations.
When AD 97-02-02 was issued, the IPC was never revised to match the
hardware configuration called out in AD 97-02-02 or in the service
information associated with that AD. Because of the conflict between
the AD and the IPC configurations, an airplane that was in compliance
with the requirements of AD 97-02-02 could have had an incorrect
hardware configuration installed during routine maintenance after
complying with the AD. The IPC has been updated and corrected by M7
Aerospace, LLC.
Also, since we issued AD 97-02-02, the manufacturer developed an
improved design for the control column pivot bearing and support
structure that terminates the repetitive torque check and replacement
of control column pivot bearings.
The manufacturer also issued new service information that adds the
10,000-hour TIS repetitive replacement of the control column pivot
bearing that is in the airworthiness limitations section (ALS) of the
airplane maintenance manual (AMM) and (if this revision is mandated)
requires the replacement of the pivot bearing with the improved design
by 35,000 hours TIS that is in the supplemental inspections document
(SID). Issuance of
[[Page 58355]]
the new service information, the revised IPC, and this AD will
eliminate the conflicts between AD 97-02-02, the service information,
the IPC, the ALS, and the SID.
The NPRM (80 FR 34326, June 16, 2015) proposed to require
inspecting for movement and correct torque of the elevator control
pivot bearing, inspecting the elevator control rod for damage and
correct configuration, and replacing parts as necessary. The NPRM also
proposed to require a 10,000-hour TIS repetitive replacement of the
control column pivot bearing and elevator control rod bolt and require
replacement of the control column pivot bearing with the improved
design by 35,000 hours TIS. Replacing the original control column pivot
bearing with the improved design terminates the requirement to
repetitively replace the original control column pivot bearing every
10,000 hours. 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 (80 FR 34326, June 16,
2015) 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 except for
minor editorial changes. We have determined that these minor changes:
Are consistent with the intent that was proposed in the
NPRM (80 FR 34326, June 16, 2015) for correcting the unsafe condition;
and
Do not add any additional burden upon the public than was
already proposed in the NPRM (80 FR 34326, June 16, 2015).
Relevant Service Information Under 1 CFR 51
We reviewed M7 Aerospace SA26 Series Service Bulletin No. 26-27-30-
046 R2, dated December 5, 2014; Fairchild Aircraft SA26 Series Service
Bulletin No. 26-27-30-047, dated June 16, 1997; M7 Aerospace SA226
Series Service Bulletin No. 226-27-060 R2, dated December 5, 2014;
Fairchild Aerospace SA226 Series Service Bulletin No. 226-27-061, dated
June 16, 1997; M7 Aerospace SA227 Series Service Bulletin, No. 227-27-
041 R2, dated December 5, 2014; Fairchild Aircraft SA227 Series Service
Bulletin No. 227-27-042, dated June 16, 1997; M7 Aerospace LLC SA227
Series Commuter Category Service Bulletin No. CC7-27-010 R2, dated
December 5, 2014; and Fairchild Aircraft SA227 Series Commuter Category
Service Bulletin No. CC7-27-011, dated June 16, 1997. The service
information describes procedures for inspecting for movement and
correct torque of the elevator control pivot bearing, inspecting the
elevator control rod for damage, and replacing parts as necessary. The
service information also adds a repetitive replacement of the control
column pivot bearings at 10,000 hours TIS and requires replacement of
the control column pivot bearing with the improved design within 35,000
hours TIS. This 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
AD.
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
----------------------------------------------------------------------------------------------------------------
Inspection of torque on the 2 work-hours x $85 Not applicable......... $170 $61,200
control column pivot bearing. per hour = $170.
Control column pivot bearing 8 work-hours x $85 $300................... 980 352,800
replacement. per hour = $680.
New designed control column pivot 20 work-hours x $85 $2,450................. 4,150 1,494,000
bearing replacement. per hour = $1,700.
Elevator rod end bolt replacement 4 work-hours x $85 $10.................... 350 126,000
per hour = $340.
----------------------------------------------------------------------------------------------------------------
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 have determined that this AD will not have federalism
implications under Executive Order 13132. This AD will not have a
substantial direct effect on the States, on the relationship between
the national government and the States, or on the distribution of power
and responsibilities among the various levels of government.
For the reasons discussed above, I certify that this AD:
(1) Is not a ``significant regulatory action'' under Executive
Order 12866,
(2) Is not a ``significant rule'' under DOT Regulatory Policies and
Procedures (44 FR 11034, February 26, 1979),
(3) Will not affect intrastate aviation in Alaska, and
(4) Will not have a significant economic impact, positive or
negative, on a substantial number of small entities under the criteria
of the Regulatory Flexibility Act.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation safety, Incorporation by
reference, Safety.
Adoption of the Amendment
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.
[[Page 58356]]
Sec. 39.13 [Amended]
0
2. The FAA amends Sec. 39.13 by removing Airworthiness Directive (AD)
97-02-02, Amendment 39-9886 (62 FR 2552, January 17, 1997), and adding
the following new AD:
2015-19-10 M7 Aerospace: Amendment 39-18272; Docket No. FAA-2015-
2207; Directorate Identifier 2015-CE-003-AD.
(a) Effective Date
This AD is effective November 3, 2015.
(b) Affected ADs
This AD supersedes AD 97-02-02, Amendment 39-9886 (62 FR 2552,
January 17, 1997).
(c) Applicability
This AD applies to M7 Aerospace LLC Models SA26-AT, SA26-T,
SA226-AT, SA226-T, SA226-T(B), SA226-TC, SA227-AC (C-26A), SA227-AT,
SA227-BC (C-26A), SA227-CC, SA227-DC (C-26B), SA227-TT, all serial
numbers, certificated in any category.
(d) Subject
Joint Aircraft System Component (JASC)/Air Transport Association
(ATA) of America Code 27, Flight Controls.
(e) Unsafe Condition
AD 97-02-02 (62 FR 2552, January 17, 1997) (``AD 97-02-02'')
resulted from reports of Fairchild SA227 series airplanes losing
pitch control in-flight. This supersedure was prompted by an
operator experiencing complete loss of elevator control because of
failure of the bolt attaching the elevator control rod to the
elevator walking beam under the cockpit floor. We are issuing this
AD to prevent loss of pitch control, which if not corrected, could
result in loss of airplane control.
(f) Compliance
Comply with this AD within the compliance times specified,
unless already done. Models SA227-CC and SA227-DC, serial numbers
892, 893, and 895 and up, have the revised (modified) configuration.
Since those airplanes are already in compliance, they do not have to
do the actions in paragraphs (h) or (i) of this AD, including all
subparagraphs. Those airplanes must still do the actions required in
paragraph (j) of this AD, including all subparagraphs.
(g) Credit for Actions Accomplished in Accordance With Previous Service
Information
This AD allows credit for the control column pivot bearing
torque check and initial replacement required in paragraph (i)(2) of
this AD and the elevator rod bolt inspection and initial replacement
required in paragraphs (j)(1) and (j)(3)(i) of this AD, if done
before November 3, 2015 (the effective date of this AD), following
the procedures specified in the Accomplishment Instructions of the
applicable service information listed in paragraphs (g)(1) through
(g)(4) of this AD:
(1) M7 Aerospace SA227 Commuter Category Service Bulletin No.
CC7-27-010, original issue or revision 1.
(2) M7 Aerospace SA227 Series Service Bulletin No. 227-27-041,
original issue or revision 1.
(3) M7 Aerospace SA226 Series Service Bulletin No. 226-27-060,
original issue or revision 1.
(4) M7 Aerospace SA26 Series Service Bulletin No. 26-27-30-046,
original issue or revision 1.
(h) Control Column Pivot Bearing Revised (Modified) Configuration
(1) On or before the airplane accumulates a total of 35,000
hours time-in-service (TIS) or within the next 1,000 hours TIS after
November 3, 2015 (the effective date of this AD), whichever occurs
later, you must revise (modify) the control column pivot bearing
configuration with the improved design. Use the applicable service
information listed in paragraphs (h)(1)(i) through (h)(1)(iv) of
this AD. Revising (modifying) the configuration of the control
column pivot bearing with the improved design terminates the actions
for paragraph (i) of this AD, including all subparagraphs, but you
must still complete the required actions in paragraph (j) of this
AD, including all subparagraphs.
(i) Fairchild Aircraft SA26 Series Service Bulletin No. 26-27-
30-047, dated June 16, 1997;
(ii) Fairchild Aircraft SA226 Series Service Bulletin No. 226-
27-061, dated June 16, 1997;
(iii) Fairchild Aircraft SA227 Series Service Bulletin No. 227-
27-042, dated June 16, 1997; or
(iv) Fairchild Aircraft SA227 Series Commuter Category No. CC7-
27-011, dated June 16, 1997.
(2) You may at any time before 35,000 hours TIS revise (modify)
the control column pivot bearing configuration with the improved
design to terminate the repetitive replacement of the original
control column pivot bearing using the applicable service
information listed in paragraphs (h)(1)(i) through (h)(1)(iv) of
this AD. This action terminates the requirements of paragraph (i) of
this AD, including all subparagraphs, but you must still complete
the required actions in paragraph (j) of this AD, including all
subparagraphs.
(i) Torque Check or Replacement of the Control Column Pivot Bearing
(1) Use the service information, as applicable, listed in
paragraphs (i)(1)(i) through (i)(1)(iv) of this AD to do a control
column pivot bearing torque check or replacement at the applicable
compliance times in paragraph (i)(2) or (i)(3) of this AD, including
all subparagraphs:
(i) M7 Aerospace LLC SA26 Series Service Bulletin No. 26-27-30-
046 R2, dated December 5, 2014;
(ii) M7 Aerospace LLC SA226 Series Service Bulletin No. 226-27-
060 R2, dated December 5, 2014;
(iii) M7 Aerospace LLC SA227 Series Service Bulletin No. 227-27-
041 R2, dated December 5, 2014; or
(iv) M7 Aerospace LLC SA227 Series Commuter Category Service
Bulletin No. CC7-27-010 R2, December 5, 2014.
(2) For airplanes where the control column pivot bearing has
been torque checked or replaced within the last 10,000 hours TIS
before November 3, 2015 (the effective date of this AD) using the
applicable service information listed in paragraph (g)(1) through
(g)(4) or (i)(1)(i) through (i)(1)(iv) of this AD, do one of the
following actions:
(i) Within the next 10,000 hours TIS after the last control
column pivot bearing replacement or within the next 1,000 hours TIS
after November 3, 2015 (the effective date of this AD), whichever
occurs later, and repetitively thereafter every 10,000 hours TIS,
replace the control column pivot bearing following paragraph 2.B. of
the Accomplishment Instructions of the applicable service
information listed in paragraphs (i)(1)(i) through (i)(1)(iv) of
this AD; or
(ii) Within the next 10,000 hours TIS after the last control
column pivot bearing replacement or within the next 1,000 hours TIS
after November 3, 2015 (the effective date of this AD), whichever
occurs later, revise (modify) the control column pivot bearing
configuration with the improved design using the applicable service
information listed in paragraphs (h)(1)(i) through (h)(1)(iv) of
this AD. Revising (modifying) the configuration of the control
column pivot bearing with the improved design terminates the
repetitive replacement of the original control column pivot bearing.
No other actions are required for paragraph (i) of this AD,
including all subparagraphs, but you must still complete the actions
in paragraph (j) of this AD, including all subparagraphs.
(3) For airplanes where the control column pivot bearing has not
been torque checked or replaced within the last 10,000 hours TIS
before November 3, 2015 (the effective date of this AD) using the
applicable service information listed in paragraphs (g)(1) through
(g)(4) or (i)(1)(i) through (i)(1)(iv) of this AD, within the next
200 hours TIS after November 3, 2015 (the effective date of this
AD), torque check the control column pivot bearing following
paragraph 2.A. of the service information listed in paragraphs
(i)(1)(i) through (i)(1)(iv) of this AD.
(4) If nut movement occurs during the torque check required in
paragraph (i)(3) of this AD, do one of the following actions:
(i) Before further flight and repetitively thereafter at
intervals not to exceed every 10,000 hours TIS, replace the control
column pivot bearing following paragraph 2.B. of the Accomplishment
Instructions of the applicable service information listed in
paragraphs (i)(1)(i) through (i)(1)(iv) of this AD; or
(ii) Before further flight, revise (modify) the control column
pivot bearing configuration with the improved design using the
applicable service information listed in paragraphs (h)(1)(i)
through (h)(1)(iv) of this AD. Revising (modifying) the
configuration of the control column pivot bearing with the improved
design terminates the repetitive replacement of the original control
column pivot bearing. No other actions are required for paragraph
(i) of this AD, including all
[[Page 58357]]
subparagraphs, but you must still complete the actions in paragraph
(j) of this AD, including all subparagraphs.
(5) If no nut movement occurs during the torque check required
in paragraph (i)(3) of this AD, do one of the following actions:
(i) Within the next 1,000 hours TIS after November 3, 2015 (the
effective date of this AD), replace the control column pivot bearing
following paragraph 2.B. of the Accomplishment Instructions of the
applicable service information listed in paragraphs (i)(1)(i)
through (i)(1)(iv) of this AD; or
(ii) Within the next 1,000 hours TIS after November 3, 2015 (the
effective date of this AD), revise (modify) the control column pivot
bearing configuration with the improved design using the applicable
service information listed in paragraphs (h)(1)(i) through
(h)(1)(iv) of this AD. Revising (modifying) the configuration of the
control column pivot bearing with the improved design terminates the
repetitive replacement of the original control column pivot bearing.
(j) Inspect the Elevator Control Rod Ends and Hardware
(1) Within the next 200 hours TIS after November 3, 2015 (the
effective date of this AD), inspect the elevator control rod ends
and hardware for wear, creasing, or other damage and verify the
elevator rod bolt and attachment hardware for correct configuration
following paragraph 2.D. of the Accomplishment Instructions of the
applicable service information listed in paragraphs (i)(1)(i)
through (i)(1)(iv) of this AD.
(2) If any damage is found during the inspection required in
paragraph (j)(1) of this AD or the elevator rod bolt and attachment
hardware does not match the correct configuration, before further
flight, replace the elevator rod bolt, rod ends, and associated
hardware following paragraph 2.D. of the Accomplishment Instructions
of the applicable service information listed in paragraphs (i)(1)(i)
through (i)(1)(iv) of this AD.
(3) Replace the elevator rod end bolt and associated hardware
following paragraph 2.D. of the Accomplishment Instructions of the
applicable service information listed in paragraphs (i)(1)(i)
through (i)(1)(iv) of this AD at whichever of the following
compliance times applies and repetitively thereafter at intervals
not to exceed 10,000 hours TIS:
(i) For airplanes where the elevator rod bolt has been replaced:
Within the next 10,000 hours TIS after the last elevator rod bolt
replacement or within the next 1,000 hours TIS after November 3,
2015 (the effective date of this AD), whichever occurs later; or
(ii) For airplanes where the elevator rod bolt has never been
replaced: Within the next 200 hours TIS after November 3, 2015 (the
effective date of this AD).
(k) Alternative Methods of Compliance (AMOCs)
(1) The Manager, Fort Worth Airplane Certification Office, FAA,
has the authority to approve AMOCs for this AD, if requested using
the procedures found in 14 CFR 39.19. In accordance with 14 CFR
39.19, send your request to your principal inspector or local Flight
Standards District Office, as appropriate. If sending information
directly to the manager of the ACO, send it to the attention of the
person identified in paragraph (l)(1) of this AD.
(2) Before using any approved AMOC, notify your appropriate
principal inspector, or lacking a principal inspector, the manager
of the local flight standards district office/certificate holding
district office.
(l) Related Information
(1) For more information about this AD, contact Andrew McAnaul,
Aerospace Engineer, FAA, ASW-143 (c/o San Antonio MIDO), 10100
Reunion Place, Suite 650, San Antonio, Texas 78216; phone: (210)
308-3365; fax: (210) 308-3370; email: andrew.mcanaul@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.
(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 SA26 Series Service Bulletin No. 26-27-30-
046 R2, dated December 5, 2014.
(ii) M7 Aerospace LLC SA226 Series Service Bulletin No. 226-27-
060 R2, dated December 5, 2014.
(iii) M7 Aerospace LLC SA227 Series Service Bulletin No. 227-27-
041 R2, dated December 5, 2014.
(iv) M7 Aerospace LLC SA227 Series Commuter Category Service
Bulletin No. CC7-27-010 R2, December 5, 2014.
(v) Fairchild Aircraft SA26 Series Service Bulletin No. 26-27-
30-047, dated June 16, 1997.
(vi) Fairchild Aircraft SA226 Series Service Bulletin No. 226-
27-061, dated June 16, 1997.
(vii) Fairchild Aircraft SA227 Series Service Bulletin No. 227-
27-042, dated June 16, 1997.
(viii) Fairchild Aircraft SA227 Series Commuter Category No.
CC7-27-011, dated June 16, 1997.
(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.
(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 September 17, 2015.
Melvin Johnson,
Acting Manager, Small Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 2015-24249 Filed 9-28-15; 8:45 am]
BILLING CODE 4910-13-P
