Airworthiness Directives; M7 Aerospace LLC Airplanes, 34326-34330 [2015-14698]
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Federal Register / Vol. 80, No. 115 / Tuesday, June 16, 2015 / Proposed Rules
in the levels of production necessary for
Board membership for each unit.
Section 1220.201(d) of the Order
provides that at the end of each 3-year
period, the Secretary must review the
volume of production of each unit and
adjust the boundaries of any unit and
the number of Board members from
each such unit as necessary to conform
with the criteria set forth in
§ 1220.201(e): (1) To the extent
practicable, States with annual average
soybean production of less than
3,000,000 bushels shall be grouped into
geographically contiguous units, each of
which has a combined production level
equal to or greater than 3,000,000
bushels, and each such group shall be
entitled to at least one member on the
Board; (2) units with at least 3,000,000
bushels, but fewer than 15,000,000
bushels shall be entitled to one board
member; (3) units with 15,000,000
bushels or more but fewer than
70,000,000 bushels shall be entitled to
two Board members; (4) units with
70,000,000 bushels or more but fewer
than 200,000,000 bushels shall be
entitled to three Board members; and (5)
units with 200,000,000 bushels or more
shall be entitled to four Board members.
The Board was last reapportioned in
2012. The total Board membership
increased from 69 to 70 members, with
Mississippi gaining one additional
member. The final rule was published
in the Federal Register (74 FR 27467) on
January 2, 2013. This change was
effective with the 2013 appointments.
Currently, the Board has 70 members
representing 31 geographical units. This
membership is based on average
production levels for the years 2007–
2011 (excluding crops in years that
production was the highest and that
production was the lowest) as reported
by USDA’s National Agricultural
Statistics Service (NASS).
This proposed rule would increase
total membership on the Board from 70
to 73. Production data for years 2010–
2014 (excluding the crops in years in
which production was the highest and
in which production was the lowest)
was gathered from NASS. This change
would not affect the number of
geographical units. The NASS
information combines the production
from the Western and Eastern Regions
into one production data without
distinguishing between the two regions.
The NASS data does not support a
change in membership for either region.
As such, this proposed rule would leave
the membership of both regions
unchanged with one member each.
This proposed rule would adjust
representation on the Board as follows:
Current
representation
Proposed
representation
3
0
2
State
4
1
3
Missouri ....................................................................................................................................................................
New Jersey ..............................................................................................................................................................
Wisconsin .................................................................................................................................................................
Board adjustments as proposed by
this rulemaking would become effective,
if adopted, with the 2016 appointment
process.
List of Subjects in 7 CFR Part 1220
Administrative practice and
procedure, Advertising, Agricultural
research, Marketing agreements,
Soybeans and soybean products,
Reporting and recordkeeping
requirements.
For the reasons set forth in the
preamble, it is proposed that title 7, part
1220 be amended as follows:
PART 1220–SOYBEAN PROMOTION,
RESEARCH, AND CONSUMER
INFORMATION
1. The authority citation for 7 CFR
part 1220 continues to read as follows:
■
Authority: 7 U.S.C. 6301–6311 and 7
U.S.C. 7401.
2. In § 1220.201, paragraph (a), the
table is revised to read as follows:
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■
§ 1220.201
Membership of board.
(a) * * *
Unit
Number of
members
Illinois ....................................
Iowa ......................................
Minnesota .............................
Indiana ..................................
Nebraska ..............................
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4
4
4
4
4
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Number of
members
Unit
Ohio ......................................
Missouri ................................
Arkansas ...............................
South Dakota ........................
Kansas ..................................
Michigan ...............................
North Dakota ........................
Mississippi ............................
Wisconsin .............................
Louisiana ..............................
Tennessee ............................
North Carolina ......................
Kentucky ...............................
Pennsylvania ........................
Virginia ..................................
Maryland ...............................
Georgia .................................
South Carolina ......................
Alabama ................................
Delaware ...............................
Texas ....................................
Oklahoma .............................
New York ..............................
New Jersey ...........................
Eastern Region
(Massachusetts, Connecticut, Florida,
Rhode Island,
Vermont, New Hampshire, Maine, West
Virginia, District of Columbia, and Puerto
Rico ............................
Western Region
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Number of
members
Unit
4
4
3
3
3
3
3
3
3
2
2
2
2
2
2
2
2
1
1
1
1
1
1
1
(Montana, Wyoming,
Colorado, New Mexico, Idaho, Utah, Arizona, Washington, Oregon, Nevada, California, Hawaii, and
Alaska) .......................
*
*
*
*
*
Dated: June 11, 2015.
Rex A. Barnes,
Associate Administrator, Agricultural
Marketing Service.
[FR Doc. 2015–14708 Filed 6–15–15; 8:45 am]
BILLING CODE 3410–02–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2015–2207; Directorate
Identifier 2015–CE–003–AD]
RIN 2120–AA64
Airworthiness Directives; M7
Aerospace LLC Airplanes
Federal Aviation
Administration (FAA), DOT.
ACTION: Notice of proposed rulemaking
(NPRM).
AGENCY:
1
1
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Federal Register / Vol. 80, No. 115 / Tuesday, June 16, 2015 / Proposed Rules
We propose to supersede
Airworthiness Directive (AD) 97–02–02,
which applies to 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
currently requires 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. Since we issued AD 97–02–
02, an operator experienced a 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. This proposed
AD would prevent loss of pitch control,
which if not corrected, could result in
loss of airplane control. We are
proposing this AD to correct the unsafe
condition on these products.
DATES: We must receive comments on
this proposed AD by July 31, 2015.
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: Deliver to Mail
address above between 9 a.m. and 5
p.m., Monday through Friday, except
Federal holidays.
For service information identified in
this proposed AD, contact 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.
asabaliauskas on DSK5VPTVN1PROD with PROPOSALS
SUMMARY:
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–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
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contains this proposed AD, the
regulatory evaluation, any comments
received, and other information. The
street address for the Docket Office
(phone: 800–647–5527) is in the
ADDRESSES section. Comments will be
available in the AD docket shortly after
receipt.
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:
Comments Invited
We invite you to send any written
relevant data, views, or arguments about
this proposed AD. Send your comments
to an address listed under the
ADDRESSES section. Include ‘‘Docket No.
FAA–2015–2207; Directorate Identifier
2015–CE–003–AD at the beginning of
your comments. We specifically invite
comments on the overall regulatory,
economic, environmental, and energy
aspects of this proposed AD. We will
consider all comments received by the
closing date and may amend this
proposed AD because of those
comments.
We will post all comments we
receive, without change, to https://
www.regulations.gov, including any
personal information you provide. We
will also post a report summarizing each
substantive verbal contact we receive
about this proposed AD.
Discussion
On January 6, 1997, we issued AD 97–
02–02, Amendment 39–9886 (62 FR
2552, January 17, 1997), (‘‘AD 97–02–
02’’), for 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.
AD 97–02–02 requires applying torque
to check the security of the control
column pitch bearing attaching nuts,
inspecting for any looseness or
movement of the bearing assembly, and
inspecting the elevator control rod end
bearing retainer/dust seals for creasing.
If any of these problems are evident,
replace these parts, as well as install a
new bolt and washer to the elevator
control rod end bearing assembly at the
walking beam connection. AD 97–02–02
resulted from reports of Fairchild SA227
series airplanes losing pitch control inflight. We issued AD 97–02–02 to
prevent loss of pitch control, which if
not corrected, could result in loss of
airplane control.
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Actions Since AD 97–02–02 Was Issued
Since we issued AD 97–02–02, an
operator experienced 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 time in service (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 within 35,000 hours TIS that is
in the supplemental inspections
document (SID). Issue of the new
service information, the revised IPC,
and this proposed AD will eliminate the
conflicts between AD 97–02–02, the
service information, the IPC, the ALS,
and the SID.
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
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Federal Register / Vol. 80, No. 115 / Tuesday, June 16, 2015 / Proposed Rules
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 the NPRM.
FAA’s Determination
We are proposing this AD because we
evaluated all the relevant information
and determined the unsafe condition
described previously is likely to exist or
develop in other products of the same
type design.
Proposed AD Requirements
This proposed AD would retain none
of the requirements of AD 97–02–02.
This proposed AD would require
inspecting for movement and correct
torque of the elevator control pivot
bearing, inspecting the elevator control
rod for damage, and replacing parts as
necessary. This proposed AD would
also require a 10,000-hour TIS repetitive
replacement of the control column pivot
bearing and require replacement of the
control column pivot bearing with the
improved design within 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.
Costs of Compliance
We estimate that this proposed AD
affects 360 airplanes of U.S. registry.
We estimate the following costs to
comply with this proposed 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
Authority for This Rulemaking
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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
proposed AD would not have federalism
implications under Executive Order
13132. This proposed AD would not
have a substantial direct effect on the
States, on the relationship between the
national Government and the States, or
on the distribution of power and
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responsibilities among the various
levels of government.
For the reasons discussed above, I
certify that the proposed regulation:
(1) Is not a ‘‘significant regulatory
action’’ under Executive Order 12866,
(2) Is not a ‘‘significant rule’’ under
the DOT Regulatory Policies and
Procedures (44 FR 11034, February 26,
1979),
(3) Will not affect intrastate aviation
in Alaska, and
(4) Will not have a significant
economic impact, positive or negative,
on a substantial number of small entities
under the criteria of the Regulatory
Flexibility Act.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation
safety, Incorporation by reference,
Safety.
The Proposed Amendment
Accordingly, under the authority
delegated to me by the Administrator,
the FAA proposes to amend 14 CFR part
39 as follows:
PART 39—AIRWORTHINESS
DIRECTIVES
1. The authority citation for part 39
continues to read as follows:
■
Authority: 49 U.S.C. 106(g), 40113, 44701.
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§ 39.13
[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:
■
M7 Aerospace: Docket No. FAA–2015–2207;
Directorate Identifier 2015–CE–003–AD.
(a) Comments Due Date
The FAA must receive comments on this
AD action by July 31, 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
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Federal Register / Vol. 80, No. 115 / Tuesday, June 16, 2015 / Proposed Rules
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.
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(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 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 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
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(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 pargraph (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 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 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 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
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34329
replaced within the last 10,000 hours TIS
before 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 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
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
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
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 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.
E:\FR\FM\16JNP1.SGM
16JNP1
34330
Federal Register / Vol. 80, No. 115 / Tuesday, June 16, 2015 / Proposed Rules
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 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 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.
asabaliauskas on DSK5VPTVN1PROD with PROPOSALS
(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.
(2) 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.
Issued in Kansas City, Missouri, on June 9,
2015.
Earl Lawrence,
Manager, Small Airplane Directorate, Aircraft
Certification Service.
[FR Doc. 2015–14698 Filed 6–15–15; 8:45 am]
BILLING CODE 4910–13–P
VerDate Sep<11>2014
16:44 Jun 15, 2015
Jkt 235001
DEPARTMENT OF TRANSPORTATION
Examining the AD Docket
Federal Aviation Administration
You may examine the AD docket on
the Internet at https://
www.regulations.gov by searching for
and locating Docket No. FAA–2015–
2134; or in person at the Docket
Management Facility between 9 a.m.
and 5 p.m., Monday through Friday,
except Federal holidays. The AD docket
contains this proposed AD, the
regulatory evaluation, any comments
received, and other information. The
street address for the Docket Office
(phone: 800–647–5527) is in the
ADDRESSES section. Comments will be
available in the AD docket shortly after
receipt.
FOR FURTHER INFORMATION CONTACT:
David Enns, Aerospace Engineer,
Wichita Aircraft Certification Office,
FAA, 1801 S. Airport Road, Room 100,
Wichita, Kansas 67209; phone: (316)
946–4147; fax: (316) 946–4107; email:
david.enns@faa.gov.
SUPPLEMENTARY INFORMATION:
14 CFR Part 39
[Docket No. FAA–2015–2134; Directorate
Identifier 2015–CE–012–AD]
RIN 2120–AA64
Airworthiness Directives; B/E
Aerospace Protective Breathing
Equipment Part Number 119003–11
Federal Aviation
Administration (FAA), DOT.
ACTION: Notice of proposed rulemaking
(NPRM).
AGENCY:
We propose to adopt a new
airworthiness directive (AD) for certain
B/E Aerospace protective breathing
equipment (PBE) that is installed on
airplanes. This proposed AD was
prompted by reports of a compromise in
the vacuum seal of the pouch that
contains the PBE. This proposed AD
would require inspecting the PBE to
determine if the pouch has the proper
vacuum seal. We are proposing this AD
to correct the unsafe condition on these
products.
DATES: We must receive comments on
this proposed AD by July 31, 2015.
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: Deliver to Mail
address above between 9 a.m. and 5
p.m., Monday through Friday, except
Federal holidays.
For service information identified in
this proposed AD, contact B/E
Aerospace, Inc., Commercial Aircraft
Products Group, 10800 Pflumm Road,
Lenexa, Kansas 66215; telephone: (913)
338–9800; fax: (913) 338–8419; Internet:
www.beaerospace.com. You may review
this referenced service information at
the FAA, Small Airplane Directorate,
901 Locust, Kansas City, Missouri
64106. For information on the
availability of this material at the FAA,
call (816) 329–4148. It is also available
on the Internet at https://
www.regulations.gov by searching for
and locating Docket No. FAA–2015–
2134.
SUMMARY:
PO 00000
Frm 00006
Fmt 4702
Sfmt 4702
Comments Invited
We invite you to send any written
relevant data, views, or arguments about
this proposal. Send your comments to
an address listed under the ADDRESSES
section. Include ‘‘Docket No. FAA–
2015–2134; Directorate Identifier 2015–
CE–012–AD’’ at the beginning of your
comments. We specifically invite
comments on the overall regulatory,
economic, environmental, and energy
aspects of this proposed AD. We will
consider all comments received by the
closing date and may amend this
proposed AD because of those
comments.
We will post all comments we
receive, without change, to https://
www.regulations.gov, including any
personal information you provide. We
will also post a report summarizing each
substantive verbal contact we receive
about this proposed AD.
Discussion
We received a report of B/E Aerospace
protective breathing equipment (PBE),
part number 119003–11, catching fire
when activated by a crew member
during taxi aboard an Emirates Airline
airplane.
Following the PBE fire event and
during the initial investigation, it was
determined that a number of pouches
containing the PBE that were installed
in various airplanes had a compromised
vacuum seal. A compromised seal in the
pouch of a PBE results in degradation
and possible contamination of the
chemicals that provide oxygen during
use.
E:\FR\FM\16JNP1.SGM
16JNP1
]]>Agencies
[Federal Register Volume 80, Number 115 (Tuesday, June 16, 2015)]
[Proposed Rules]
[Pages 34326-34330]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2015-14698]
=======================================================================
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2015-2207; Directorate Identifier 2015-CE-003-AD]
RIN 2120-AA64
Airworthiness Directives; M7 Aerospace LLC Airplanes
AGENCY: Federal Aviation Administration (FAA), DOT.
ACTION: Notice of proposed rulemaking (NPRM).
-----------------------------------------------------------------------
[[Page 34327]]
SUMMARY: We propose to supersede Airworthiness Directive (AD) 97-02-02,
which applies to 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
currently requires 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. Since we issued AD 97-02-02, an
operator experienced a 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. This proposed AD would prevent
loss of pitch control, which if not corrected, could result in loss of
airplane control. We are proposing this AD to correct the unsafe
condition on these products.
DATES: We must receive comments on this proposed AD by July 31, 2015.
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: Deliver to Mail address above between 9
a.m. and 5 p.m., Monday through Friday, except Federal holidays.
For service information identified in this proposed AD, contact 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.
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-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 proposed AD, the regulatory evaluation, any comments
received, and other information. The street address for the Docket
Office (phone: 800-647-5527) is in the ADDRESSES section. Comments will
be available in the AD docket shortly after receipt.
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:
Comments Invited
We invite you to send any written relevant data, views, or
arguments about this proposed AD. Send your comments to an address
listed under the ADDRESSES section. Include ``Docket No. FAA-2015-2207;
Directorate Identifier 2015-CE-003-AD at the beginning of your
comments. We specifically invite comments on the overall regulatory,
economic, environmental, and energy aspects of this proposed AD. We
will consider all comments received by the closing date and may amend
this proposed AD because of those comments.
We will post all comments we receive, without change, to https://www.regulations.gov, including any personal information you provide. We
will also post a report summarizing each substantive verbal contact we
receive about this proposed AD.
Discussion
On January 6, 1997, we issued AD 97-02-02, Amendment 39-9886 (62 FR
2552, January 17, 1997), (``AD 97-02-02''), for 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. AD 97-02-02 requires applying torque to
check the security of the control column pitch bearing attaching nuts,
inspecting for any looseness or movement of the bearing assembly, and
inspecting the elevator control rod end bearing retainer/dust seals for
creasing. If any of these problems are evident, replace these parts, as
well as install a new bolt and washer to the elevator control rod end
bearing assembly at the walking beam connection. AD 97-02-02 resulted
from reports of Fairchild SA227 series airplanes losing pitch control
in-flight. We issued AD 97-02-02 to prevent loss of pitch control,
which if not corrected, could result in loss of airplane control.
Actions Since AD 97-02-02 Was Issued
Since we issued AD 97-02-02, an operator experienced 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 time in service (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 within 35,000 hours TIS that is in the supplemental
inspections document (SID). Issue of the new service information, the
revised IPC, and this proposed AD will eliminate the conflicts between
AD 97-02-02, the service information, the IPC, the ALS, and the SID.
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
[[Page 34328]]
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 the NPRM.
FAA's Determination
We are proposing this AD because we evaluated all the relevant
information and determined the unsafe condition described previously is
likely to exist or develop in other products of the same type design.
Proposed AD Requirements
This proposed AD would retain none of the requirements of AD 97-02-
02. This proposed AD would require inspecting for movement and correct
torque of the elevator control pivot bearing, inspecting the elevator
control rod for damage, and replacing parts as necessary. This proposed
AD would also require a 10,000-hour TIS repetitive replacement of the
control column pivot bearing and require replacement of the control
column pivot bearing with the improved design within 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.
Costs of Compliance
We estimate that this proposed AD affects 360 airplanes of U.S.
registry.
We estimate the following costs to comply with this proposed AD:
Estimated Costs
----------------------------------------------------------------------------------------------------------------
Cost per Cost on U.S.
Action Labor cost Parts cost product operators
----------------------------------------------------------------------------------------------------------------
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 20 work-hours x 2,450...................... 4,150 1,494,000
pivot bearing replacement. $85 per hour =
$1,700.
Elevator rod end bolt 4 work-hours x $85 10......................... 350 126,000
replacement. 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 proposed AD would not have federalism
implications under Executive Order 13132. This proposed AD would not
have a substantial direct effect on the States, on the relationship
between the national Government and the States, or on the distribution
of power and responsibilities among the various levels of government.
For the reasons discussed above, I certify that the proposed
regulation:
(1) Is not a ``significant regulatory action'' under Executive
Order 12866,
(2) Is not a ``significant rule'' under the DOT Regulatory Policies
and Procedures (44 FR 11034, February 26, 1979),
(3) Will not affect intrastate aviation in Alaska, and
(4) Will not have a significant economic impact, positive or
negative, on a substantial number of small entities under the criteria
of the Regulatory Flexibility Act.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation safety, Incorporation by
reference, Safety.
The Proposed Amendment
Accordingly, under the authority delegated to me by the
Administrator, the FAA proposes to amend 14 CFR part 39 as follows:
PART 39--AIRWORTHINESS DIRECTIVES
0
1. The authority citation for part 39 continues to read as follows:
Authority: 49 U.S.C. 106(g), 40113, 44701.
Sec. 39.13 [Amended]
0
2. The FAA amends Sec. 39.13 by removing Airworthiness Directive (AD)
97-02-02, Amendment 39-9886 (62 FR 2552, January 17, 1997), and adding
the following new AD:
M7 Aerospace: Docket No. FAA-2015-2207; Directorate Identifier 2015-
CE-003-AD.
(a) Comments Due Date
The FAA must receive comments on this AD action by July 31,
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
[[Page 34329]]
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 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
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 pargraph (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 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 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 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 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
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 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 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 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 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.
[[Page 34330]]
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 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 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.
(2) 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.
Issued in Kansas City, Missouri, on June 9, 2015.
Earl Lawrence,
Manager, Small Airplane Directorate, Aircraft Certification Service.
[FR Doc. 2015-14698 Filed 6-15-15; 8:45 am]
BILLING CODE 4910-13-P
