Airworthiness Directives; M7 Aerospace LP SA226 and SA227 Series Airplanes, 21171-21176 [E7-8163]
Download as PDF
<![CDATA[
Federal Register / Vol. 72, No. 82 / Monday, April 30, 2007 / Proposed Rules
2006; are considered acceptable for
compliance with the corresponding action
specified in this AD.
Alternative Methods of Compliance
(AMOCs)
(h)(1) The Manager, Los Angeles Aircraft
Certification Office (ACO), FAA, has the
authority to approve AMOCs for this AD, if
requested in accordance with the procedures
found in 14 CFR 39.19.
(2) Before using any AMOC approved in
accordance with § 39.19 on any airplane to
which the AMOC applies, notify the
appropriate principal inspector in the FAA
Flight Standards Certificate Holding District
Office.
Issued in Renton, Washington, on April 23,
2007.
Stephen P. Boyd,
Acting Manager, Transport Airplane
Directorate, Aircraft Certification Service.
[FR Doc. E7–8176 Filed 4–27–07; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2006–25927; Directorate
Identifier 2006–CE–52–AD]
RIN 2120–AA64
Airworthiness Directives; M7
Aerospace LP SA226 and SA227 Series
Airplanes
Federal Aviation
Administration (FAA), Department of
Transportation (DOT).
ACTION: Notice of proposed rulemaking
(NPRM).
jlentini on PROD1PC65 with PROPOSAL
AGENCY:
SUMMARY: We propose to supersede
Airworthiness Directive (AD) 98–19–15
R1 and AD 2000–03–17, which apply to
M7 Aerospace LP SA226 and SA227
series airplanes equipped with certain
pitch trim actuators. AD 98–19–15 R1
currently requires you to incorporate
changes into the Limitations Section of
the FAA-approved Airplane Flight
Manual (AFM) if certain part number
(P/N) pitch trim actuators are installed.
AD 2000–03–17 requires repetitive
inspections and repetitive replacements
of the pitch trim actuator. The repetitive
inspection and repetitive replacement
times vary depending on the
combination of airplane model and
pitch trim actuator P/N installed. We are
proposing this AD because we have
determined that reliance on critical
repetitive inspections on aging
commuter-class airplanes carries an
unnecessary safety risk when a design
change exists that could eliminate or, in
certain instances, reduce the number of
VerDate Aug<31>2005
16:35 Apr 27, 2007
Jkt 211001
those critical inspections. Consequently,
this proposed AD would retain all of the
actions of the previously referenced
ADs, place life limits on certain P/N
pitch trim actuators, and require the
replacement of certain P/N pitch trim
actuators with one of an improved
design. Once installed, the improved
design pitch trim actuator would
terminate the AFM limitations in this
proposed AD and reduce the repetitive
inspection and repetitive replacement
requirements. We are proposing this AD
to detect excessive freeplay or rod
slippage in the pitch trim actuator,
which, if not detected and corrected,
could result in pitch trim actuator
failure. We are also proposing this AD
to lessen the severity of pitch upset if a
pitch trim actuator mechanical failure
occurs. These conditions could lead to
possible loss of control.
DATES: We must receive comments on
this proposed AD by June 29, 2007.
ADDRESSES: Use one of the following
addresses to comment on this proposed
AD:
• DOT Docket web site: Go to
https://dms.dot.gov and follow the
instructions for sending your comments
electronically.
• Mail: Docket Management Facility;
U.S. Department of Transportation, 400
Seventh Street, SW., Nassif Building,
Room PL–401, Washington, DC 20590–
0001.
• Fax: (202) 493–2251.
• Hand Delivery: Room PL–401 on
the plaza level of the Nassif Building,
400 Seventh Street, SW., Washington,
DC, between 9 a.m. and 5 p.m., Monday
through Friday, except Federal holidays.
• Federal eRulemaking Portal: Go to
https://www.regulations.gov. Follow the
instructions for submitting comments.
For service information identified in
this proposed AD, contact M7
Aerospace LP, P.O. Box 790490, San
Antonio, Texas 78279–0490; telephone:
(210) 824–9421, extension 7294.
FOR FURTHER INFORMATION CONTACT:
Werner Koch, Aerospace Engineer, 2601
Meacham Blvd, Fort Worth, Texas
76137–4298; telephone: (817) 222–5133;
fax: (817) 222–5960.
SUPPLEMENTARY INFORMATION:
Comments Invited
We invite you to send any written
relevant data, views, or arguments
regarding this proposed AD. Send your
comments to an address listed under the
ADDRESSES section. Include the docket
number ‘‘FAA–2006–25927; Directorate
Identifier 2006–CE–52–AD’’ at the
beginning of your comments. We
specifically invite comments on the
overall regulatory, economic,
PO 00000
Frm 00047
Fmt 4702
Sfmt 4702
21171
environmental, and energy aspects of
the proposed AD. We will consider all
comments received by the closing date
and may amend the proposed AD in
light of those comments.
We will post all comments we
receive, without change, to https://
dms.dot.gov, including any personal
information you provide. We will also
post a report summarizing each
substantive verbal contact we receive
concerning this proposed AD.
Discussion
History of AD Actions
Failure of a Barber-Coleman pitch
trim actuator, which allowed the
horizontal stabilizer to move to a full
aircraft nose up position on an M7
Aerospace LP Model SA227 airplane,
caused us to issue AD 98–19–15 R1,
Amendment 39–11507 (65 FR 1540,
January 11, 2000). AD 98–19–15 R1
currently requires you to revise the
Limitations Section of the FAAapproved AFM to limit the maximum
indicated airspeed and increase the
minimum crew size if a Barber-Coleman
pitch trim actuator P/N 27–19008–001,
P/N 27–19008–002, P/N 27–19008–004,
or P/N 27–19008–005 is installed.
To avoid the above limitations, AD
98–19–15 R1 allows installation of a
Barber-Coleman P/N 27–19008–006,
Barber Coleman P/N 27–19008–007,
Simmonds-Precision P/N DL5040M5,
Simmonds-Precision P/N DL5040M6, or
Simmonds-Precision P/N DL5040M8
pitch trim actuator. All airplane models
are eligible for any of these installations.
The applicable service bulletin depends
on the airplane model and pitch trim
actuator.
The FAA also issued AD 2000–03–17,
Amendment 39–11576 (65 FR 8037,
February 17, 2000), to establish
inspection and replacement intervals for
the pitch trim actuators. Inspection
times and replacement times vary
depending on the model of the airplane
and the P/N of the pitch trim actuator
installed.
Events Since Previous AD Actions
Since we issued ADs 98–19–15 R1
and 2000–03–17, the FAA has
determined that the actions fall within
the FAA’s aging commuter-class aircraft
policy, which briefly states that reliance
on critical repetitive inspections carries
an unnecessary safety risk when a
design change exists that could
eliminate or, in certain instances,
reduce the number of those critical
inspections. We also determined that
the number of repetitive replacements
could be reduced in these AD actions
E:\FR\FM\30APP1.SGM
30APP1
21172
Federal Register / Vol. 72, No. 82 / Monday, April 30, 2007 / Proposed Rules
because of pitch trim actuator design
changes.
The FAA has identified installation of
Barber-Coleman P/N 27–19008–006,
Barber-Coleman P/N 27–19008–007, or
Simmonds-Precision P/N DL5040M8
pitch trim actuators on all SA226 and
SA227 series airplanes or installation of
Simmonds-Precision P/N DL5040M6
pitch trim actuators on all SA226 and
SA227 series airplanes (except Models
SA227-CC and SA227-DC) will
significantly reduce the number of
repetitive inspections and repetitive
replacements currently required by AD
2000–03–17.
Relevant Service Information
We have reviewed the following
Fairchild Aircraft service information:
• Fairchild Aircraft SA226 Series
Service Letter (SL) 226–SL–005,
Revised: August 3, 1999;
• Fairchild Aircraft SA227 Series SL
227–SL–011, Revised August 3, 1999;
• Fairchild Aircraft SA227 Series SL
CC7–SL–028, Issued: August 12, 1999;
• Fairchild Aircraft SA226 Series SL
226–SL–014, Revised: February 1, 1999;
• Fairchild Aircraft SA227 Series SL
227–SL–031, Revised: February 1, 1999;
and
• Fairchild Aircraft SA227 Series SL
CC7–SL–021, Revised: February 1, 1999.
The service information describes
procedures for inspecting the various
pitch trim actuators that can be installed
in SA226 and SA227 series airplanes.
This service information is currently
referenced in the existing ADs.
FAA’s Determination and Requirements
of the Proposed AD
We are proposing this AD because we
evaluated all information and
determined the unsafe condition
described previously is likely to exist or
develop on other products of the same
type design. This proposed AD would
supersede AD 98–19–15 R1 and AD
2000–03–17 with a new AD that would
retain all of the actions of the previously
referenced ADs, but limit the part
numbers of the pitch trim actuators that
can be used for replacement. This
proposed AD would also place a life
limit on Barber-Coleman P/N 27–19008–
001, Barber-Coleman P/N 27–19008–
002, Barber-Coleman P/N 27–19008–
004, and Barber-Coleman P/N 27–
19008–005 pitch trim actuators. This
proposed AD would require you to use
the service information described
previously to perform these actions.
Costs of Compliance
We estimate that this proposed AD
would affect 307 airplanes in the U.S.
registry.
This proposed AD requires pitch trim
actuators to either be inspected or
overhauled. We have no way of
determining the number of airplanes
that may need the inspection or
overhaul. We have presented the fleet
cost as the lowest cost based on all
airplanes needing the inspection and
the highest cost based on all airplanes
needing the overhaul. The actual fleet
cost will be somewhere between the
lowest and highest fleet cost presented.
We estimate the following costs to do
the proposed inspection or overhaul:
Labor cost
Parts cost
4 work-hours × $80 per hour = $320 ......................................................................................................
4 work-hours × $80 per hour = $320 ......................................................................................................
We estimate the following costs to do
any necessary replacements that would
be required based on the results of the
proposed inspection or proposed
mandatory replacement. We have no
way of determining the number of
Total cost
per airplane
None
$9,000
$320
9,320
Total cost
on U.S.
operators
$98,240
2,861,240
airplanes that may need this
replacement:
Parts cost
Total cost
per airplane
4 work-hours × $80 per hour = $320 ..............................................................................................................................
jlentini on PROD1PC65 with PROPOSAL
Labor cost
$64,000
$64,320
The replacement estimate is based on
replacing the pitch trim actuator with a
new Simmonds-Precision P/N
DL5040M8 pitch trim actuator. If the
pitch trim actuator is replaced with a
different P/N FAA-approved pitch trim
actuator or a zero-timed FAA-approved
pitch trim actuator the cost to the
owner/operator could be less.
The estimated costs represented in the
above actions include the costs
associated with AD 98–19–15 R1, AD
2000–03–17, and the costs of this
proposed AD. The added cost impact
this AD imposes upon an owner/
operator over that already required by
AD 98–19–15 R1 and AD 2000–03–17 is
the eventual replacement of the pitch
trim actuator if the airplane currently
has a Barber-Coleman P/N 27–19008–
001, P/N 27–19008–002, P/N 27–19008–
004, or P/N 27–19008–005 installed.
VerDate Aug<31>2005
16:35 Apr 27, 2007
Jkt 211001
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
PO 00000
Frm 00048
Fmt 4702
Sfmt 4702
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); and
E:\FR\FM\30APP1.SGM
30APP1
Federal Register / Vol. 72, No. 82 / Monday, April 30, 2007 / Proposed Rules
3. 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.
We prepared a regulatory evaluation
of the estimated costs to comply with
this proposed AD and placed it in the
AD docket.
Examining the AD Docket
You may examine the AD docket that
contains the proposed AD, the
regulatory evaluation, any comments
received, and other information on the
Internet at https://dms.dot.gov; or in
person at the Docket Management
Facility between 9 a.m. and 5 p.m.,
Monday through Friday, except Federal
holidays. The Docket Office (telephone
(800) 647–5227) is located at the street
address stated in the ADDRESSES section.
Comments will be available in the AD
docket shortly after receipt.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation
safety, Safety.
The Proposed Amendment
Accordingly, under the authority
delegated to me by the Administrator,
the FAA proposes to amend 14 CFR part
39 as follows:
PART 39—AIRWORTHINESS
DIRECTIVES
1. The authority citation for part 39
continues to read as follows:
Authority: 49 U.S.C. 106(g), 40113, 44701.
§ 39.13
[Amended]
2. The FAA amends § 39.13 by
removing Airworthiness Directive (AD)
98–19–15 R1, Amendment 39–11507 (65
FR 1540, January 11, 2000), and AD
2000–03–17, Amendment 39–11576 (65
FR 8037, February 17, 2000); and by
adding the following new AD:
M7 Aerospace LP (Type Certificate No.
A5SW, A8SW, and A18SW formerly
held by Fairchild Aircraft
Incorporated): Docket No. FAA–2006–
25927; Directorate Identifier 2006–CE–
52–AD.
jlentini on PROD1PC65 with PROPOSAL
Comments Due Date
(a) We must receive comments on this
airworthiness directive (AD) action by June
29, 2007.
Affected ADs
(b) This AD supersedes the following ADs:
(1) AD 98–19–15 R1, Amendment 39–
11507; and
(2) AD 2000–03–17, Amendment 39–
11576.
VerDate Aug<31>2005
16:35 Apr 27, 2007
Jkt 211001
Applicability
(c) This AD applies to all Models 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–PC, and SA227–TT airplanes, all
serial numbers, that:
(1) are certificated in any category; and
(2) are equipped with pitch trim actuator
Barber-Coleman part number (P/N) 27–
19008–001, Barber-Coleman P/N 27–19008–
002, Barber-Coleman P/N 27–19008–004,
Barber-Coleman P/N 27–19008–005, BarberColeman P/N 27–19008–006, Barber-Coleman
P/N 27–19008–007, Simmonds-Precision P/N
DL5040M5, Simmonds-Precision P/N
DL5040M6, or Simmonds-Precision P/N
DL5040M8.
Unsafe Condition
(d) This AD results from reports of
mechanical failure of the pitch trim actuator
causing the horizontal stabilizer to move to
full aircraft nose up. We are proposing this
AD to detect excessive freeplay or rod
slippage in the pitch trim actuator, which, if
not detected and corrected, could result in
pitch trim actuator failure. We are also
proposing this AD to lessen the severity of
pitch upset if a pitch trim actuator
mechanical failure occurs. These conditions
could lead to possible loss of control. In
addition, we are proposing this AD to
eliminate the use of certain pitch trim
actuators that require frequent critical
inspections or replacements.
Compliance
(e) To address this problem, you must do
the following, unless already done:
(1) For airplanes with a Barber-Coleman
pitch trim actuator, P/N 27–19008–001, P/N
27–19008–002, P/N 27–19008–004, or P/N
27–19008–005: Before further flight after
September 25, 1998 (the effective date of AD
98–19–15), incorporate the text in paragraphs
(e)(1)(i) and (e)(1)(ii) of this AD into the
Limitations Section of the FAA-approved
Airplane Flight Manual (AFM). The owner/
operator holding at least a private pilot
certificate as authorized by section 43.7 of
the Federal Aviation Regulations (14 CFR
43.7) may insert the information specified in
paragraphs (e)(1)(i) and (e)(1)(ii) of this AD
into the AFM Limitations Section. This may
be done by inserting a copy of this AD into
the AFM. Make an entry into the aircraft
records showing compliance with this
portion of the AD in accordance with section
43.9 of the Federal Aviation Regulations (14
CFR 43.9).
(i) ‘‘Limit the maximum indicated airspeed
to maneuvering airspeed (Va) as shown in the
appropriate airplane flight manual (AFM)’’;
and
(ii) ‘‘The minimum crew required is two
pilots.’’
Note 1: Fairchild Service Letter 226–SL–
017, Fairchild Service Letter 227–SL–033,
and Fairchild Service Letter CC7–SL–023, all
FAA Approved: August 26, 1998; Revised:
September 2, 1998, address the subject matter
of this AD.
PO 00000
Frm 00049
Fmt 4702
Sfmt 4702
21173
Note 2: The before further flight
compliance time of paragraph (e)(1) of this
AD is retained from AD 98–19–15 R1.
Note 3: Installation of any FAA-approved
pitch trim actuator other than the BarberColeman P/N 27–19008–001, P/N 27–19008–
002, P/N 27–19008–004, or P/N 27–19008–
005 terminates the requirements of paragraph
(e)(1) of this AD.
(2) For all airplanes: Do the following
initial inspection or overhaul and repetitive
inspection or overhaul at the times specified
in the table in paragraph (4) of this AD:
(i) For airplanes equipped with a
Simmonds-Precision pitch trim actuator P/N
DL5040M5, P/N DL5040M6, or P/N
DL5040M8: Measure the freeplay of the pitch
trim actuator and inspect the pitch trim
actuator for rod slippage using the
INSTRUCTIONS section of Fairchild Aircraft
SA226 Series Service Letter (SL) 226–SL–005
or Fairchild Aircraft SA227 Series SL 227–
SL–011, both Revised: August 3, 1999; or
Fairchild Aircraft SA227 Series Service
Letter CC7–SL–028, Issued: August 12, 1999,
as applicable.
(ii) For airplanes equipped with BarberColeman pitch trim actuators, P/N 27–19008–
001, P/N 27–19008–002, P/N 27–19008–004,
or P/N 27–19008–005: Do a functional
inspection of the pitch trim actuator using
the INSTRUCTIONS section of Fairchild
Aircraft SA226 Series SL 226–SL–014,
Fairchild Aircraft SA227 Series SL 227–SL–
031, or Fairchild Aircraft SA227 Series SL
CC7–SL–021; all Revised: February 1, 1999;
as applicable.
Note 4: The actions in paragraphs (e)(2)(i)
and (e)(2)(ii) of this AD are the same as the
actions in AD 2000–03–17. The only
difference between this AD and AD 2000–03–
17 is the addition of life limits to BarberColeman pitch trim actuators P/N 27–19008–
001, P/N 27–19008–002, P/N 27–19008–004,
or P/N 27–19008–005.
(iii) For airplanes equipped with BarberColeman pitch trim actuators, P/N 27–19008–
006 or P/N 27–19008–007: Overhaul the pitch
trim actuator following the applicable
maintenance manual.
(3) For all airplanes: Before further flight
replace the pitch trim actuator following the
applicable maintenance manual when any of
the following occurs:
(i) The pitch trim actuator is inspected
following paragraphs (e)(2)(i) and (e)(2)(ii) of
this AD and the freeplay limitations are
exceeded, rod slippage is found, or a ratching
sound occurs, as specified in the applicable
service letters; or
(ii) The installed pitch trim actuator
reaches its repetitive replacement time as
specified in the table in paragraph (e)(4) of
this AD.
(4) The table below presents the pitch trim
actuators that could be installed and the
compliance times for the initial inspections
or overhaul, repetitive inspections or
overhaul, and repetitive replacements
required by this AD:
E:\FR\FM\30APP1.SGM
30APP1
21174
Federal Register / Vol. 72, No. 82 / Monday, April 30, 2007 / Proposed Rules
TABLE—INSPECTION/OVERHAUL AND REPLACEMENT REQUIREMENTS FOR PITCH TRIM ACTUATORS.
Initial inspection or overhaul
Repetitive inspection or overhaul
Repetitive replacement
(i) For all affected airplane models
(except for the Models SA227–
CC and SA227–DC) that have
an original Simmonds-Precision
pitch
trim
actuator,
P/N
DL5040M5, installed.
Inspect
following
paragraph
(e)(2)(i) of this AD before accumulating 3,000 hours time-inservice (TIS) on the pitch trim
actuator or within 50 hours TIS
after April 17, 1995 (the effective date of AD 93–15–02 R1),
whichever occurs later.
Inspect
following
paragraph
(e)(2)(i) of this AD before accumulating 250 hours TIS after
the initial inspection and repetitively thereafter at intervals not
to exceed 250 hours TIS until
accumulating the hours TIS
specified in the paragraph
(e)(4)(i) Repetitive Replacement
column of this AD.
(ii) For all affected airplane models
(except for the Models SA227–
CC and SA227–DC) that have a
replacement
Simmonds-Precision pitch trim actuator, P/N
DL5040M5, installed.
Inspect
following
paragraph
(e)(2)(i) of this AD before accumulating 5,000 hours TIS on
the pitch trim actuator or within
50 hours TIS after April 17,
1995 (the effective date of AD
93–15–02 R1), whichever occurs later.
Inspect
following
paragraph
(e)(2)(i) of this AD before accumulating 300 hours TIS after
the initial inspection and repetitively thereafter at intervals not
to exceed 300 hours TIS until
accumulating the hours TIS
specified in the paragraph
(e)(4)(ii) Repetitive Replacement column of this AD.
(iii) For all affected airplane models (except for the Models
SA227–CC and SA227–DC) that
have a replacement SimmondsPrecision pitch trim actuator, P/N
DL5040M6, installed. This part
can be new, modified from a P/
N DL5040M5 pitch trim actuator,
or overhauled and zero-timed.
Inspect
following
paragraph
(e)(2)(i) of this AD before accumulating 7,500 hours TIS on
the pitch trim actuator or within
50 hours TIS after April 17,
1995 (the effective date of AD
93–15–02 R1), whichever occurs later.
Inspect
following
paragraph
(e)(2)(i) of this AD before accumulating 300 hours TIS after
the initial inspection and repetitively thereafter at intervals not
to exceed 300 hours TIS until
accumulating the hours TIS
specified in the paragraph
(e)(4)(iii) Repetitive Replacement column of this AD.
(iv) For all affected airplane models (except for the Models
SA227–CC and SA227–DC) that
have a replacement SimmondsPrecision pitch trim actuator, P/N
DL5040M5, installed that was
overhauled
and
zero-timed
where both nut assemblies, P/N
AA56142, were replaced with
new assemblies during overhaul.
jlentini on PROD1PC65 with PROPOSAL
Condition
Inspect
following
paragraph
(e)(2)(i) of this AD before accumulating 5,000 hours TIS on
the pitch trim actuator or within
50 hours TIS after April 17,
1995 (the effective date of AD
93–15–02 R1), whichever occurs later.
Inspect
following
paragraph
(e)(2)(i) of this AD before accumulating 300 hours TIS after
the initial inspection and repetitively thereafter at intervals not
to exceed 300 hours TIS until
accumulating the hours TIS
specified in the paragraph
(e)(4)(iv) Repetitive Replacement column of this AD.
(v) For all affected airplane models
(except for the Models SA227–
CC and SA227–DC) that have a
replacement
Simmonds-Precision P/N DL5040M5 pitch trim
actuator installed that was overhauled and zero-timed where
both
nut
assemblies,
P/N
AA56142, were not replaced
with new assemblies during
overhaul.
Inspect
following
paragraph
(e)(2)(i) of this AD before accumulating 3,000 hours TIS on
the pitch trim actuator or within
50 hours TIS after April 17,
1995 (the effective date of AD
93–15–02 R1), whichever occurs later.
Inspect
following
paragraph
(e)(2)(i) of this AD before accumulating 250 hours TIS after
the initial inspection and repetitively thereafter at intervals not
to exceed 250 hours TIS until
accumulating the hours TIS
specified in the paragraph
(e)(4)(v) Repetitive Replacement column of this AD.
Replace the pitch trim actuator
with a Simmonds-Precision P/N
DL5040M6,
Simmonds-Precision P/N DL5040M8, BarberColeman P/N 27–19008–006,
Barber-Coleman
P/N
27–
19008–007, or an FAA-approved equivalent pitch trim actuator
before
accumulating
5,000 hours TIS on the pitch
trim actuator, 500 hours TIS
after the initial inspection, or
within 30 days after the effective date of this AD, whichever
occurs later.
Replace the pitch trim actuator
with a Simmonds-Precision P/N
DL5040M6,
Simmonds-Precision P/N DL5040M8, BarberColeman P/N 27–19008–006,
Barber-Coleman
P/N
27–
19008–007, or an FAA-approved equivalent pitch trim actuator
before
accumulating
6,500 hours TIS on the pitch
trim actuator or within 30 days
after the effective date of this
AD, whichever occurs later.
Replace the pitch trim actuator
with a Simmonds-Precision P/N
DL5040M6,
Simmonds-Precision P/N DL5040M8, BarberColeman P/N 27–19008–006,
Barber-Coleman
P/N
27–
19008–007, or an FAA-approved equivalent pitch trim actuator
before
accumulating
9,900 hours TIS on the pitch
trim actuator or within 30 days
after the effective date of this
AD, whichever occurs later.
Replace the pitch trim actuator
with a Simmonds-Precision P/N
DL5040M6,
Simmonds-Precision P/N DL5040M8, BarberColeman P/N 27–19008–006,
Barber-Coleman
P/N
27–
19008–007, or an FAA-approved equivalent pitch trim actuator
before
accumulating
6,500 hours TIS on the pitch
trim actuator or within 30 days
after the effective date of this
AD, whichever occurs later.
Replace the pitch trim actuator
with a Simmonds-Precision P/N
DL5040M6,
Simmonds-Precision P/N DL5040M8, BarberColeman P/N 27–19008–006,
Barber-Coleman
P/N
27–
19008–007, or an FAA-approved equivalent pitch trim actuator
before
accumulating
5,000 hours TIS on the pitch
trim actuator or within 30 days
after the effective date of this
AD, whichever occurs later.
VerDate Aug<31>2005
16:35 Apr 27, 2007
Jkt 211001
PO 00000
Frm 00050
Fmt 4702
Sfmt 4702
E:\FR\FM\30APP1.SGM
30APP1
Federal Register / Vol. 72, No. 82 / Monday, April 30, 2007 / Proposed Rules
21175
TABLE—INSPECTION/OVERHAUL AND REPLACEMENT REQUIREMENTS FOR PITCH TRIM ACTUATORS.—Continued
Initial inspection or overhaul
Repetitive inspection or overhaul
Repetitive replacement
(vi) For all affected airplane models (except for the Models
SA227–CC and SA227–DC) that
have a newly fabricated or overhauled and zero-timed BarberColman pitch trim actuator, P/N
27–19008–001, P/N 27–19008–
002, P/N 27–19008–004, or P/N
27–19008–005.
Inspect
following
paragraph
(e)(2)(ii) of this AD before accumulating 500 hours total TIS on
the pitch trim actuator or within
50 hours TIS after December 1,
1997 (the effective date of AD
97–23–01), whichever occurs
later.
Inspect
following
paragraph
(e)(2)(ii) of this AD before accumulating 300 hours TIS after
the initial inspection and repetitively thereafter at intervals not
to exceed 300 hours TIS until
accumulating the hours TIS
specified in the paragraph
(e)(4)(vi) Repetitive Replacement column of this AD.
(vii) For the Models SA227–CC
and SA227–DC that have a
Simmonds-Precision pitch trim
actuator, P/N DL5040M5 or P/N
DL5040M6, installed.
None .............................................
None .............................................
(viii) For the Models SA227–CC
and SA227–DC that have a
newly fabricated or over-hauled
and zero-timed Barber-Colman
pitch trim actuator, P/N 27–
19008–001, P/N 27–19008–002,
P/N 27–19008–004, or P/N 27–
19008–005.
Inspect
following
paragraph
(e)(2)(ii) of this AD before accumulating 500 hours total TIS on
the pitch trim actuator or within
50 hours TIS after December 1,
1997 (the effective date of AD
97–23–01), whichever occurs
later.
Inspect
following
paragraph
(e)(2)(ii) of this AD before accumulating 300 hours TIS after
the initial inspection and repetitively thereafter at intervals not
to exceed 300 hours TIS until
accumulating the hours TIS
specified in the paragraph
(e)(4)(viii) Repetitive Replacement column of this AD.
(ix) For all affected airplanes with
a Simmonds-Precision pitch trim
actuator, P/N DL5040M8, installed.
Inspect
following
paragraph
(e)(2)(i) of this AD before accumulating 7,500 hours TIS on
the pitch trim actuator or within
the next 50 hours TIS after
April 10, 2000 (the effective
date of AD 2000–03–17),
whichever occurs later.
Inspect
following
paragraph
(e)(2)(i) of this AD before accumulating 300 hours TIS after
the initial inspection and repetitively thereafter at intervals not
to exceed 300 hours TIS until
accumulating the hours TIS
specified in paragraph (e)(4)(ix)
Repetitive Replacement column
of this AD.
(x) For all affected airplanes with a
Barber-Colman P/N 27–19008–
006 or 27–19008–007 pitch trim
actuator installed.
jlentini on PROD1PC65 with PROPOSAL
Condition
Overhaul following paragraph
(e)(2)(iii) of this AD before accumulating 2,000 hours TIS on
the pitch trim actuator.
Overhaul following paragraph
(e)(2)(iii) of this AD before accumulating 2,000 hours TIS on
the pitch trim actuator.
Replace the pitch trim actuator
with a Simmonds-Precision P/N
DL5040M6,
Simmonds-Precision P/N DL5040M8, BarberColeman P/N 27–19008–006,
Barber-Coleman
P/N
27–
19008–007, or an FAA-approved equivalent pitch trim actuator
before
accumulating
5,000 hours TIS on the pitch
trim actuator or within 30 days
after the effective date of this
AD, whichever occurs later.
Replace the pitch trim actuator
with a Simmonds-Precision
pitch
trim
actuator
P/N
DL5040M8, a Barber-Coleman
P/N 27–19008–006 or P/N 27–
19008–007, or an FAA-approved equivalent before accumulating 1,500 hours TIS on
the pitch trim actuator or within
30 days after the effective date
of this AD, whichever occurs
later.
Replace the pitch trim actuator
with a Simmonds-Precision P/N
DL5040M8, Barber-Coleman P/
N 27–19008–006, Barber-Coleman P/N 27–19008–007, or an
FAA-approved equivalent pitch
trim actuator before accumulating 5,000 hours TIS on the
pitch trim actuator or within 30
days after the effective date of
this AD, whichever occurs later.
Replace the pitch trim actuator
with a Simmonds-Precision
pitch
trim
actuator
P/N
DL5040M8, a Barber-Coleman
P/N 27–19008–006 or P/N 27–
19008–007, or an FAA-approved equivalent before accumulating 9,900 hours TIS on
the pitch trim actuator or within
30 days after the effective date
of this AD, whichever occurs
later.
No replacement requirements.
(5) For all airplane models except Models
SA227–CC and SA227–DC: As of the effective
date of this AD, do not install as a
replacement any of the following pitch trim
actuators or FAA-approved equivalent P/N:
(i) Barber-Colman P/N 27–19008–001;
(ii) Barber-Colman P/N 27–19008–002;
(iii) Barber-Colman P/N 27–19008–004;
(iv) Barber-Colman P/N 27–19008–005; or
(v) Simmonds-Precision P/N DL5040M5.
(6) For all airplane Models SA227–CC and
SA227–DC: As of the effective date of this
AD, do not install as a replacement any of the
following pitch trim actuators or FAAapproved equivalent P/N:
(i) Barber-Colman P/N 27–19008–001;
(ii) Barber-Colman P/N 27–19008–002;
VerDate Aug<31>2005
16:35 Apr 27, 2007
Jkt 211001
(iii) Barber-Colman P/N 27–19008–004;
(iv) Barber-Colman P/N 27–19008–005;
(v) Simmonds-Precision P/N DL5040M5; or
(vi) Simmonds-Precision P/N DL5040M6.
Alternative Methods of Compliance
(AMOCs)
(f) The Manager, Fort Worth Airplane
Certification Office (ACO), FAA, ATTN:
Werner Koch, Aerospace Engineer, 2601
Meacham Blvd, Fort Worth, Texas 76137–
4298, has the authority to approve AMOCs
for this AD, if requested using the procedures
found in 14 CFR 39.19. Before using any
approved AMOC on any airplane to which
the AMOC applies, notify your appropriate
principal inspector (PI) in the FAA Flight
PO 00000
Frm 00051
Fmt 4702
Sfmt 4702
Standards District Office (FSDO), or lacking
a PI, your local FSDO.
Related Information
(g) To get copies of the service information
referenced in this AD, contact M7 Aerospace
LP, 10823 N. E. Entrance, San Antonio, Texas
78216. To view the AD docket, go to the
Docket Management Facility; U.S.
Department of Transportation, 400 Seventh
Street, SW., Nassif Building, Room PL–401,
Washington, DC, or on the Internet at https://
dms.dot.gov. The docket number is Docket
No. FAA–2006–25927; Directorate Identifier
2006–CE–52–AD.
E:\FR\FM\30APP1.SGM
30APP1
21176
Federal Register / Vol. 72, No. 82 / Monday, April 30, 2007 / Proposed Rules
Issued in Kansas City, Missouri, on April
20, 2007.
Charles L. Smalley,
Acting Manager, Small Airplane Directorate,
Aircraft Certification Service.
[FR Doc. E7–8163 Filed 4–27–07; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF THE INTERIOR
Office of Surface Mining Reclamation
and Enforcement
30 CFR Part 935
[OH–252–FOR]
Ohio Regulatory Program
Office of Surface Mining
Reclamation and Enforcement (OSM),
Interior.
ACTION: Proposed rule; public comment
period and opportunity for public
hearing on proposed amendment.
jlentini on PROD1PC65 with PROPOSAL
AGENCY:
SUMMARY: We (OSM) are announcing
receipt of a proposed amendment to the
Ohio regulatory program (the ‘‘Ohio
program’’) under the Surface Mining
Control and Reclamation Act of 1977
(SMCRA or the Act). Ohio proposes to
revise the Ohio Revised Code (ORC)
regarding changes to the State’s
alternate bonding system (bond pool),
funding for its regulatory and
abandoned mine land programs and its
bond pool, permitting procedures for
determining the potential that proposed
mine sites may or may not produce
acid-mine drainage, and authorizes rulemaking if Ohio becomes covered by a
State programmatic general permit
issued by the U.S. Army Corps of
Engineers for the discharge of dredged
or fill material into waters of the United
States by coal mining operations. The
amendment is primarily intended to
satisfy a program condition codified in
the Federal regulations. This
amendment replaces the State’s bond
pool amendment that the State
previously submitted and that OSM
announced, and requested public
comments on, in the Federal Register
dated February 13, 2006 (71 FR 7480).
This document gives the times and
locations that the Ohio program and
proposed amendment to that program
are available for your inspection, the
comment period during which you may
submit written comments on the
amendment, and the procedures that we
will follow for the public hearing, if one
is requested.
DATES: We will accept written
comments on this amendment until 4
p.m. (local time), May 30, 2007. If
VerDate Aug<31>2005
16:35 Apr 27, 2007
Jkt 211001
requested, we will hold a public hearing
on the amendment on May 25, 2007. We
will accept requests to speak at a
hearing until 4 p.m., local time, on May
15, 2007.
ADDRESSES: You may submit comments,
identified by OH–252–FOR, by any of
the following methods:
• E-mail: grieger@osmre.gov. Include
OH–252–FOR in the subject line of the
message;
• Mail/Hand Delivery: Mr. George
Rieger, Chief, Pittsburgh Field Division,
Office of Surface Mining Reclamation
and Enforcement, 4605 Morse Road,
Room 102, Columbus, OH 43230.
Telephone: 614–416–2238.
• Federal eRulemaking Portal: https://
www.regulations.gov. Follow the
instructions for submitting comments.
Instructions: All submissions received
must include the agency docket number
for this rulemaking. For detailed
instructions on submitting comments
and additional information on the
rulemaking process, see the ‘‘Public
Comment Procedures’’ heading in the
SUPPLEMENTARY INFORMATION section of
this document. You may also request to
speak at a public hearing by any of the
methods listed above or by contacting
the individual listed under FOR FURTHER
INFORMATION CONTACT.
Docket: You may review copies of the
Ohio program, this amendment, a listing
of any scheduled public hearings, and
all written comments received in
response to this document at the
addresses listed below during normal
business hours, Monday through Friday,
excluding holidays. You may also
receive one free copy of this amendment
by contacting OSM’s Pittsburgh Field
Division listed below:
Mr. George Rieger, Chief, Pittsburgh
Field Division, Office of Surface
Mining Reclamation and Enforcement
4605 Morse Road, Room 102,
Columbus, OH 43230 614–416–2238.
E-mail: grieger@osmre.gov.
Mr. Scott Kell, Acting Chief, Division of
Mineral Resources Management, Ohio
Department of Natural Resources,
2045 Morse Road, Bldg. H–2,
Columbus, Ohio 43229, Telephone:
(614) 265–6633.
FOR FURTHER INFORMATION CONTACT: Mr.
George Rieger, Chief, Pittsburgh Field
Division, Telephone: (717) 782–4849,
extension 11; or 614–416–2238; or 412–
937–2153. E-mail: grieger@osmre.gov.
SUPPLEMENTARY INFORMATION:
I. Background on the Ohio Program
II. Description of the Proposed Amendment
III. Public Comment Procedures
IV. Procedural Determinations
PO 00000
Frm 00052
Fmt 4702
Sfmt 4702
I. Background on the Ohio Program
Section 503(a) of the Act permits a
State to assume primacy for the
regulation of surface coal mining and
reclamation operations on non-Federal
and non-Indian lands within its borders
by demonstrating that its program
includes, among other things, ‘‘a State
law which provides for the regulation of
surface coal mining and reclamation
operations in accordance with the
requirements of the Act * * * and rules
and regulations consistent with
regulations issued by the Secretary
pursuant to the Act.’’ See 30 U.S.C.
1253(a)(1) and (7). On the basis of these
criteria, the Secretary of the Interior
conditionally approved the Ohio
program on August 16, 1982. You can
find background information on the
Ohio program, including the Secretary’s
findings, the disposition of comments,
and conditions of approval of the Ohio
program in the August 16, 1982, Federal
Register (47 FR 34687). You can also
find later actions concerning Ohio’s
program and program amendments at 30
CFR 935.11, 935.15, and 935.16.
II. Description of the Proposed
Amendment
By letter dated March 6, 2007, Ohio
sent us a proposed amendment to its
program (Administrative Record
Number OH–2185–28) under SMCRA
(30 U.S.C. 1201 et seq.). In its letter,
Ohio stated that in December of 2006,
the Ohio legislature passed House Bill
443, which is intended to address many
of the issues of concern relative to
Ohio’s bond pool. Ohio proposes to
revise the Ohio Revised Code (ORC)
regarding changes to the State’s
alternate bonding system (bond pool),
funding for its regulatory and
abandoned mine land programs and its
bond pool, permitting procedures for
determining the potential that proposed
mine sites may or may not produce
acid-mine drainage, and authorizes rulemaking if Ohio becomes covered by a
State programmatic general permit
issued by the U.S. Army Corps of
Engineers for the discharge of dredged
or fill material into waters of the United
States by coal mining operations.
The amendment is intended to satisfy
a program condition codified in the
Federal regulations at 30 CFR 935.11(h),
and is in response to OSM’s letter of
May 4, 2005, issued under provisions of
30 CFR 733.12(b). The program
condition provides that Ohio must
submit a program amendment that
demonstrates how the alternative
bonding system will assure timely
reclamation at the site of all operations
for which bond has been forfeited.
E:\FR\FM\30APP1.SGM
30APP1
]]>Agencies
[Federal Register Volume 72, Number 82 (Monday, April 30, 2007)]
[Proposed Rules]
[Pages 21171-21176]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: E7-8163]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2006-25927; Directorate Identifier 2006-CE-52-AD]
RIN 2120-AA64
Airworthiness Directives; M7 Aerospace LP SA226 and SA227 Series
Airplanes
AGENCY: Federal Aviation Administration (FAA), Department of
Transportation (DOT).
ACTION: Notice of proposed rulemaking (NPRM).
-----------------------------------------------------------------------
SUMMARY: We propose to supersede Airworthiness Directive (AD) 98-19-15
R1 and AD 2000-03-17, which apply to M7 Aerospace LP SA226 and SA227
series airplanes equipped with certain pitch trim actuators. AD 98-19-
15 R1 currently requires you to incorporate changes into the
Limitations Section of the FAA-approved Airplane Flight Manual (AFM) if
certain part number (P/N) pitch trim actuators are installed. AD 2000-
03-17 requires repetitive inspections and repetitive replacements of
the pitch trim actuator. The repetitive inspection and repetitive
replacement times vary depending on the combination of airplane model
and pitch trim actuator P/N installed. We are proposing this AD because
we have determined that reliance on critical repetitive inspections on
aging commuter-class airplanes carries an unnecessary safety risk when
a design change exists that could eliminate or, in certain instances,
reduce the number of those critical inspections. Consequently, this
proposed AD would retain all of the actions of the previously
referenced ADs, place life limits on certain P/N pitch trim actuators,
and require the replacement of certain P/N pitch trim actuators with
one of an improved design. Once installed, the improved design pitch
trim actuator would terminate the AFM limitations in this proposed AD
and reduce the repetitive inspection and repetitive replacement
requirements. We are proposing this AD to detect excessive freeplay or
rod slippage in the pitch trim actuator, which, if not detected and
corrected, could result in pitch trim actuator failure. We are also
proposing this AD to lessen the severity of pitch upset if a pitch trim
actuator mechanical failure occurs. These conditions could lead to
possible loss of control.
DATES: We must receive comments on this proposed AD by June 29, 2007.
ADDRESSES: Use one of the following addresses to comment on this
proposed AD:
DOT Docket web site: Go to https://dms.dot.gov and follow
the instructions for sending your comments electronically.
Mail: Docket Management Facility; U.S. Department of
Transportation, 400 Seventh Street, SW., Nassif Building, Room PL-401,
Washington, DC 20590-0001.
Fax: (202) 493-2251.
Hand Delivery: Room PL-401 on the plaza level of the
Nassif Building, 400 Seventh Street, SW., Washington, DC, between 9
a.m. and 5 p.m., Monday through Friday, except Federal holidays.
Federal eRulemaking Portal: Go to https://
www.regulations.gov. Follow the instructions for submitting comments.
For service information identified in this proposed AD, contact M7
Aerospace LP, P.O. Box 790490, San Antonio, Texas 78279-0490;
telephone: (210) 824-9421, extension 7294.
FOR FURTHER INFORMATION CONTACT: Werner Koch, Aerospace Engineer, 2601
Meacham Blvd, Fort Worth, Texas 76137-4298; telephone: (817) 222-5133;
fax: (817) 222-5960.
SUPPLEMENTARY INFORMATION:
Comments Invited
We invite you to send any written relevant data, views, or
arguments regarding this proposed AD. Send your comments to an address
listed under the ADDRESSES section. Include the docket number ``FAA-
2006-25927; Directorate Identifier 2006-CE-52-AD'' at the beginning of
your comments. We specifically invite comments on the overall
regulatory, economic, environmental, and energy aspects of the proposed
AD. We will consider all comments received by the closing date and may
amend the proposed AD in light of those comments.
We will post all comments we receive, without change, to https://
dms.dot.gov, including any personal information you provide. We will
also post a report summarizing each substantive verbal contact we
receive concerning this proposed AD.
Discussion
History of AD Actions
Failure of a Barber-Coleman pitch trim actuator, which allowed the
horizontal stabilizer to move to a full aircraft nose up position on an
M7 Aerospace LP Model SA227 airplane, caused us to issue AD 98-19-15
R1, Amendment 39-11507 (65 FR 1540, January 11, 2000). AD 98-19-15 R1
currently requires you to revise the Limitations Section of the FAA-
approved AFM to limit the maximum indicated airspeed and increase the
minimum crew size if a Barber-Coleman pitch trim actuator P/N 27-19008-
001, P/N 27-19008-002, P/N 27-19008-004, or P/N 27-19008-005 is
installed.
To avoid the above limitations, AD 98-19-15 R1 allows installation
of a Barber-Coleman P/N 27-19008-006, Barber Coleman P/N 27-19008-007,
Simmonds-Precision P/N DL5040M5, Simmonds-Precision P/N DL5040M6, or
Simmonds-Precision P/N DL5040M8 pitch trim actuator. All airplane
models are eligible for any of these installations. The applicable
service bulletin depends on the airplane model and pitch trim actuator.
The FAA also issued AD 2000-03-17, Amendment 39-11576 (65 FR 8037,
February 17, 2000), to establish inspection and replacement intervals
for the pitch trim actuators. Inspection times and replacement times
vary depending on the model of the airplane and the P/N of the pitch
trim actuator installed.
Events Since Previous AD Actions
Since we issued ADs 98-19-15 R1 and 2000-03-17, the FAA has
determined that the actions fall within the FAA's aging commuter-class
aircraft policy, which briefly states that reliance on critical
repetitive inspections carries an unnecessary safety risk when a design
change exists that could eliminate or, in certain instances, reduce the
number of those critical inspections. We also determined that the
number of repetitive replacements could be reduced in these AD actions
[[Page 21172]]
because of pitch trim actuator design changes.
The FAA has identified installation of Barber-Coleman P/N 27-19008-
006, Barber-Coleman P/N 27-19008-007, or Simmonds-Precision P/N
DL5040M8 pitch trim actuators on all SA226 and SA227 series airplanes
or installation of Simmonds-Precision P/N DL5040M6 pitch trim actuators
on all SA226 and SA227 series airplanes (except Models SA227-CC and
SA227-DC) will significantly reduce the number of repetitive
inspections and repetitive replacements currently required by AD 2000-
03-17.
Relevant Service Information
We have reviewed the following Fairchild Aircraft service
information:
Fairchild Aircraft SA226 Series Service Letter (SL) 226-
SL-005, Revised: August 3, 1999;
Fairchild Aircraft SA227 Series SL 227-SL-011, Revised
August 3, 1999;
Fairchild Aircraft SA227 Series SL CC7-SL-028, Issued:
August 12, 1999;
Fairchild Aircraft SA226 Series SL 226-SL-014, Revised:
February 1, 1999;
Fairchild Aircraft SA227 Series SL 227-SL-031, Revised:
February 1, 1999; and
Fairchild Aircraft SA227 Series SL CC7-SL-021, Revised:
February 1, 1999.
The service information describes procedures for inspecting the
various pitch trim actuators that can be installed in SA226 and SA227
series airplanes. This service information is currently referenced in
the existing ADs.
FAA's Determination and Requirements of the Proposed AD
We are proposing this AD because we evaluated all information and
determined the unsafe condition described previously is likely to exist
or develop on other products of the same type design. This proposed AD
would supersede AD 98-19-15 R1 and AD 2000-03-17 with a new AD that
would retain all of the actions of the previously referenced ADs, but
limit the part numbers of the pitch trim actuators that can be used for
replacement. This proposed AD would also place a life limit on Barber-
Coleman P/N 27-19008-001, Barber-Coleman P/N 27-19008-002, Barber-
Coleman P/N 27-19008-004, and Barber-Coleman P/N 27-19008-005 pitch
trim actuators. This proposed AD would require you to use the service
information described previously to perform these actions.
Costs of Compliance
We estimate that this proposed AD would affect 307 airplanes in the
U.S. registry.
This proposed AD requires pitch trim actuators to either be
inspected or overhauled. We have no way of determining the number of
airplanes that may need the inspection or overhaul. We have presented
the fleet cost as the lowest cost based on all airplanes needing the
inspection and the highest cost based on all airplanes needing the
overhaul. The actual fleet cost will be somewhere between the lowest
and highest fleet cost presented.
We estimate the following costs to do the proposed inspection or
overhaul:
------------------------------------------------------------------------
Total cost Total cost
Labor cost Parts cost per on U.S.
airplane operators
------------------------------------------------------------------------
4 work-hours x $80 per hour = None $320 $98,240
$320............................
4 work-hours x $80 per hour = $9,000 9,320 2,861,240
$320............................
------------------------------------------------------------------------
We estimate the following costs to do any necessary replacements
that would be required based on the results of the proposed inspection
or proposed mandatory replacement. We have no way of determining the
number of airplanes that may need this replacement:
------------------------------------------------------------------------
Total cost
Labor cost Parts cost per airplane
------------------------------------------------------------------------
4 work-hours x $80 per hour = $320.......... $64,000 $64,320
------------------------------------------------------------------------
The replacement estimate is based on replacing the pitch trim
actuator with a new Simmonds-Precision P/N DL5040M8 pitch trim
actuator. If the pitch trim actuator is replaced with a different P/N
FAA-approved pitch trim actuator or a zero-timed FAA-approved pitch
trim actuator the cost to the owner/operator could be less.
The estimated costs represented in the above actions include the
costs associated with AD 98-19-15 R1, AD 2000-03-17, and the costs of
this proposed AD. The added cost impact this AD imposes upon an owner/
operator over that already required by AD 98-19-15 R1 and AD 2000-03-17
is the eventual replacement of the pitch trim actuator if the airplane
currently has a Barber-Coleman P/N 27-19008-001, P/N 27-19008-002, P/N
27-19008-004, or P/N 27-19008-005 installed.
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); and
[[Page 21173]]
3. 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.
We prepared a regulatory evaluation of the estimated costs to
comply with this proposed AD and placed it in the AD docket.
Examining the AD Docket
You may examine the AD docket that contains the proposed AD, the
regulatory evaluation, any comments received, and other information on
the Internet at https://dms.dot.gov; or in person at the Docket
Management Facility between 9 a.m. and 5 p.m., Monday through Friday,
except Federal holidays. The Docket Office (telephone (800) 647-5227)
is located at the street address stated in the ADDRESSES section.
Comments will be available in the AD docket shortly after receipt.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation safety, 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.
Sec. 39.13 [Amended]
2. The FAA amends Sec. 39.13 by removing Airworthiness Directive
(AD) 98-19-15 R1, Amendment 39-11507 (65 FR 1540, January 11, 2000),
and AD 2000-03-17, Amendment 39-11576 (65 FR 8037, February 17, 2000);
and by adding the following new AD:
M7 Aerospace LP (Type Certificate No. A5SW, A8SW, and A18SW formerly
held by Fairchild Aircraft Incorporated): Docket No. FAA-2006-25927;
Directorate Identifier 2006-CE-52-AD.
Comments Due Date
(a) We must receive comments on this airworthiness directive
(AD) action by June 29, 2007.
Affected ADs
(b) This AD supersedes the following ADs:
(1) AD 98-19-15 R1, Amendment 39-11507; and
(2) AD 2000-03-17, Amendment 39-11576.
Applicability
(c) This AD applies to all Models 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-PC, and SA227-TT airplanes, all serial
numbers, that:
(1) are certificated in any category; and
(2) are equipped with pitch trim actuator Barber-Coleman part
number (P/N) 27-19008-001, Barber-Coleman P/N 27-19008-002, Barber-
Coleman P/N 27-19008-004, Barber-Coleman P/N 27-19008-005, Barber-
Coleman P/N 27-19008-006, Barber-Coleman P/N 27-19008-007, Simmonds-
Precision P/N DL5040M5, Simmonds-Precision P/N DL5040M6, or
Simmonds-Precision P/N DL5040M8.
Unsafe Condition
(d) This AD results from reports of mechanical failure of the
pitch trim actuator causing the horizontal stabilizer to move to
full aircraft nose up. We are proposing this AD to detect excessive
freeplay or rod slippage in the pitch trim actuator, which, if not
detected and corrected, could result in pitch trim actuator failure.
We are also proposing this AD to lessen the severity of pitch upset
if a pitch trim actuator mechanical failure occurs. These conditions
could lead to possible loss of control. In addition, we are
proposing this AD to eliminate the use of certain pitch trim
actuators that require frequent critical inspections or
replacements.
Compliance
(e) To address this problem, you must do the following, unless
already done:
(1) For airplanes with a Barber-Coleman pitch trim actuator, P/N
27-19008-001, P/N 27-19008-002, P/N 27-19008-004, or P/N 27-19008-
005: Before further flight after September 25, 1998 (the effective
date of AD 98-19-15), incorporate the text in paragraphs (e)(1)(i)
and (e)(1)(ii) of this AD into the Limitations Section of the FAA-
approved Airplane Flight Manual (AFM). The owner/operator holding at
least a private pilot certificate as authorized by section 43.7 of
the Federal Aviation Regulations (14 CFR 43.7) may insert the
information specified in paragraphs (e)(1)(i) and (e)(1)(ii) of this
AD into the AFM Limitations Section. This may be done by inserting a
copy of this AD into the AFM. Make an entry into the aircraft
records showing compliance with this portion of the AD in accordance
with section 43.9 of the Federal Aviation Regulations (14 CFR 43.9).
(i) ``Limit the maximum indicated airspeed to maneuvering
airspeed (Va) as shown in the appropriate airplane flight manual
(AFM)''; and
(ii) ``The minimum crew required is two pilots.''
Note 1: Fairchild Service Letter 226-SL-017, Fairchild Service
Letter 227-SL-033, and Fairchild Service Letter CC7-SL-023, all FAA
Approved: August 26, 1998; Revised: September 2, 1998, address the
subject matter of this AD.
Note 2: The before further flight compliance time of paragraph
(e)(1) of this AD is retained from AD 98-19-15 R1.
Note 3: Installation of any FAA-approved pitch trim actuator
other than the Barber-Coleman P/N 27-19008-001, P/N 27-19008-002, P/
N 27-19008-004, or P/N 27-19008-005 terminates the requirements of
paragraph (e)(1) of this AD.
(2) For all airplanes: Do the following initial inspection or
overhaul and repetitive inspection or overhaul at the times
specified in the table in paragraph (4) of this AD:
(i) For airplanes equipped with a Simmonds-Precision pitch trim
actuator P/N DL5040M5, P/N DL5040M6, or P/N DL5040M8: Measure the
freeplay of the pitch trim actuator and inspect the pitch trim
actuator for rod slippage using the INSTRUCTIONS section of
Fairchild Aircraft SA226 Series Service Letter (SL) 226-SL-005 or
Fairchild Aircraft SA227 Series SL 227-SL-011, both Revised: August
3, 1999; or Fairchild Aircraft SA227 Series Service Letter CC7-SL-
028, Issued: August 12, 1999, as applicable.
(ii) For airplanes equipped with Barber-Coleman pitch trim
actuators, P/N 27-19008-001, P/N 27-19008-002, P/N 27-19008-004, or
P/N 27-19008-005: Do a functional inspection of the pitch trim
actuator using the INSTRUCTIONS section of Fairchild Aircraft SA226
Series SL 226-SL-014, Fairchild Aircraft SA227 Series SL 227-SL-031,
or Fairchild Aircraft SA227 Series SL CC7-SL-021; all Revised:
February 1, 1999; as applicable.
Note 4: The actions in paragraphs (e)(2)(i) and (e)(2)(ii) of
this AD are the same as the actions in AD 2000-03-17. The only
difference between this AD and AD 2000-03-17 is the addition of life
limits to Barber-Coleman pitch trim actuators P/N 27-19008-001, P/N
27-19008-002, P/N 27-19008-004, or P/N 27-19008-005.
(iii) For airplanes equipped with Barber-Coleman pitch trim
actuators, P/N 27-19008-006 or P/N 27-19008-007: Overhaul the pitch
trim actuator following the applicable maintenance manual.
(3) For all airplanes: Before further flight replace the pitch
trim actuator following the applicable maintenance manual when any
of the following occurs:
(i) The pitch trim actuator is inspected following paragraphs
(e)(2)(i) and (e)(2)(ii) of this AD and the freeplay limitations are
exceeded, rod slippage is found, or a ratching sound occurs, as
specified in the applicable service letters; or
(ii) The installed pitch trim actuator reaches its repetitive
replacement time as specified in the table in paragraph (e)(4) of
this AD.
(4) The table below presents the pitch trim actuators that could
be installed and the compliance times for the initial inspections or
overhaul, repetitive inspections or overhaul, and repetitive
replacements required by this AD:
[[Page 21174]]
Table--Inspection/Overhaul and Replacement Requirements for Pitch Trim Actuators.
----------------------------------------------------------------------------------------------------------------
Initial inspection or Repetitive inspection
Condition overhaul or overhaul Repetitive replacement
----------------------------------------------------------------------------------------------------------------
(i) For all affected airplane models Inspect following Inspect following Replace the pitch trim
(except for the Models SA227-CC and paragraph (e)(2)(i) of paragraph (e)(2)(i) of actuator with a
SA227-DC) that have an original this AD before this AD before Simmonds-Precision P/N
Simmonds-Precision pitch trim accumulating 3,000 accumulating 250 hours DL5040M6, Simmonds-
actuator, P/N DL5040M5, installed. hours time-in-service TIS after the initial Precision P/N
(TIS) on the pitch inspection and DL5040M8, Barber-
trim actuator or repetitively Coleman P/N 27-19008-
within 50 hours TIS thereafter at 006, Barber-Coleman P/
after April 17, 1995 intervals not to N 27-19008-007, or an
(the effective date of exceed 250 hours TIS FAA-approved
AD 93-15-02 R1), until accumulating the equivalent pitch trim
whichever occurs later. hours TIS specified in actuator before
the paragraph accumulating 5,000
(e)(4)(i) Repetitive hours TIS on the pitch
Replacement column of trim actuator, 500
this AD. hours TIS after the
initial inspection, or
within 30 days after
the effective date of
this AD, whichever
occurs later.
(ii) For all affected airplane models Inspect following Inspect following Replace the pitch trim
(except for the Models SA227-CC and paragraph (e)(2)(i) of paragraph (e)(2)(i) of actuator with a
SA227-DC) that have a replacement this AD before this AD before Simmonds-Precision P/N
Simmonds-Precision pitch trim accumulating 5,000 accumulating 300 hours DL5040M6, Simmonds-
actuator, P/N DL5040M5, installed. hours TIS on the pitch TIS after the initial Precision P/N
trim actuator or inspection and DL5040M8, Barber-
within 50 hours TIS repetitively Coleman P/N 27-19008-
after April 17, 1995 thereafter at 006, Barber-Coleman P/
(the effective date of intervals not to N 27-19008-007, or an
AD 93-15-02 R1), exceed 300 hours TIS FAA-approved
whichever occurs later. until accumulating the equivalent pitch trim
hours TIS specified in actuator before
the paragraph accumulating 6,500
(e)(4)(ii) Repetitive hours TIS on the pitch
Replacement column of trim actuator or
this AD. within 30 days after
the effective date of
this AD, whichever
occurs later.
(iii) For all affected airplane Inspect following Inspect following Replace the pitch trim
models (except for the Models SA227- paragraph (e)(2)(i) of paragraph (e)(2)(i) of actuator with a
CC and SA227-DC) that have a this AD before this AD before Simmonds-Precision P/N
replacement Simmonds-Precision pitch accumulating 7,500 accumulating 300 hours DL5040M6, Simmonds-
trim actuator, P/N DL5040M6, hours TIS on the pitch TIS after the initial Precision P/N
installed. This part can be new, trim actuator or inspection and DL5040M8, Barber-
modified from a P/N DL5040M5 pitch within 50 hours TIS repetitively Coleman P/N 27-19008-
trim actuator, or overhauled and after April 17, 1995 thereafter at 006, Barber-Coleman P/
zero-timed. (the effective date of intervals not to N 27-19008-007, or an
AD 93-15-02 R1), exceed 300 hours TIS FAA-approved
whichever occurs later. until accumulating the equivalent pitch trim
hours TIS specified in actuator before
the paragraph accumulating 9,900
(e)(4)(iii) Repetitive hours TIS on the pitch
Replacement column of trim actuator or
this AD. within 30 days after
the effective date of
this AD, whichever
occurs later.
(iv) For all affected airplane models Inspect following Inspect following Replace the pitch trim
(except for the Models SA227-CC and paragraph (e)(2)(i) of paragraph (e)(2)(i) of actuator with a
SA227-DC) that have a replacement this AD before this AD before Simmonds-Precision P/N
Simmonds-Precision pitch trim accumulating 5,000 accumulating 300 hours DL5040M6, Simmonds-
actuator, P/N DL5040M5, installed hours TIS on the pitch TIS after the initial Precision P/N
that was overhauled and zero-timed trim actuator or inspection and DL5040M8, Barber-
where both nut assemblies, P/N within 50 hours TIS repetitively Coleman P/N 27-19008-
AA56142, were replaced with new after April 17, 1995 thereafter at 006, Barber-Coleman P/
assemblies during overhaul. (the effective date of intervals not to N 27-19008-007, or an
AD 93-15-02 R1), exceed 300 hours TIS FAA-approved
whichever occurs later. until accumulating the equivalent pitch trim
hours TIS specified in actuator before
the paragraph accumulating 6,500
(e)(4)(iv) Repetitive hours TIS on the pitch
Replacement column of trim actuator or
this AD. within 30 days after
the effective date of
this AD, whichever
occurs later.
(v) For all affected airplane models Inspect following Inspect following Replace the pitch trim
(except for the Models SA227-CC and paragraph (e)(2)(i) of paragraph (e)(2)(i) of actuator with a
SA227-DC) that have a replacement this AD before this AD before Simmonds-Precision P/N
Simmonds-Precision P/N DL5040M5 accumulating 3,000 accumulating 250 hours DL5040M6, Simmonds-
pitch trim actuator installed that hours TIS on the pitch TIS after the initial Precision P/N
was overhauled and zero-timed where trim actuator or inspection and DL5040M8, Barber-
both nut assemblies, P/N AA56142, within 50 hours TIS repetitively Coleman P/N 27-19008-
were not replaced with new after April 17, 1995 thereafter at 006, Barber-Coleman P/
assemblies during overhaul. (the effective date of intervals not to N 27-19008-007, or an
AD 93-15-02 R1), exceed 250 hours TIS FAA-approved
whichever occurs later. until accumulating the equivalent pitch trim
hours TIS specified in actuator before
the paragraph accumulating 5,000
(e)(4)(v) Repetitive hours TIS on the pitch
Replacement column of trim actuator or
this AD. within 30 days after
the effective date of
this AD, whichever
occurs later.
[[Page 21175]]
(vi) For all affected airplane models Inspect following Inspect following Replace the pitch trim
(except for the Models SA227-CC and paragraph (e)(2)(ii) paragraph (e)(2)(ii) actuator with a
SA227-DC) that have a newly of this AD before of this AD before Simmonds-Precision P/N
fabricated or over-hauled and zero- accumulating 500 hours accumulating 300 hours DL5040M6, Simmonds-
timed Barber-Colman pitch trim total TIS on the pitch TIS after the initial Precision P/N
actuator, P/N 27-19008-001, P/N 27- trim actuator or inspection and DL5040M8, Barber-
19008-002, P/N 27-19008-004, or P/N within 50 hours TIS repetitively Coleman P/N 27-19008-
27-19008-005. after December 1, 1997 thereafter at 006, Barber-Coleman P/
(the effective date of intervals not to N 27-19008-007, or an
AD 97-23-01), exceed 300 hours TIS FAA-approved
whichever occurs later. until accumulating the equivalent pitch trim
hours TIS specified in actuator before
the paragraph accumulating 5,000
(e)(4)(vi) Repetitive hours TIS on the pitch
Replacement column of trim actuator or
this AD. within 30 days after
the effective date of
this AD, whichever
occurs later.
(vii) For the Models SA227-CC and None................... None................... Replace the pitch trim
SA227-DC that have a Simmonds- actuator with a
Precision pitch trim actuator, P/N Simmonds-Precision
DL5040M5 or P/N DL5040M6, installed. pitch trim actuator P/
N DL5040M8, a Barber-
Coleman P/N 27-19008-
006 or P/N 27-19008-
007, or an FAA-
approved equivalent
before accumulating
1,500 hours TIS on the
pitch trim actuator or
within 30 days after
the effective date of
this AD, whichever
occurs later.
(viii) For the Models SA227-CC and Inspect following Inspect following Replace the pitch trim
SA227-DC that have a newly paragraph (e)(2)(ii) paragraph (e)(2)(ii) actuator with a
fabricated or over-hauled and zero- of this AD before of this AD before Simmonds-Precision P/N
timed Barber-Colman pitch trim accumulating 500 hours accumulating 300 hours DL5040M8, Barber-
actuator, P/N 27-19008-001, P/N 27- total TIS on the pitch TIS after the initial Coleman P/N 27-19008-
19008-002, P/N 27-19008-004, or P/N trim actuator or inspection and 006, Barber-Coleman P/
27-19008-005. within 50 hours TIS repetitively N 27-19008-007, or an
after December 1, 1997 thereafter at FAA-approved
(the effective date of intervals not to equivalent pitch trim
AD 97-23-01), exceed 300 hours TIS actuator before
whichever occurs later. until accumulating the accumulating 5,000
hours TIS specified in hours TIS on the pitch
the paragraph trim actuator or
(e)(4)(viii) within 30 days after
Repetitive Replacement the effective date of
column of this AD. this AD, whichever
occurs later.
(ix) For all affected airplanes with Inspect following Inspect following Replace the pitch trim
a Simmonds-Precision pitch trim paragraph (e)(2)(i) of paragraph (e)(2)(i) of actuator with a
actuator, P/N DL5040M8, installed. this AD before this AD before Simmonds-Precision
accumulating 7,500 accumulating 300 hours pitch trim actuator P/
hours TIS on the pitch TIS after the initial N DL5040M8, a Barber-
trim actuator or inspection and Coleman P/N 27-19008-
within the next 50 repetitively 006 or P/N 27-19008-
hours TIS after April thereafter at 007, or an FAA-
10, 2000 (the intervals not to approved equivalent
effective date of AD exceed 300 hours TIS before accumulating
2000-03-17), whichever until accumulating the 9,900 hours TIS on the
occurs later. hours TIS specified in pitch trim actuator or
paragraph (e)(4)(ix) within 30 days after
Repetitive Replacement the effective date of
column of this AD. this AD, whichever
occurs later.
(x) For all affected airplanes with a Overhaul following Overhaul following No replacement
Barber-Colman P/N 27-19008-006 or 27- paragraph (e)(2)(iii) paragraph (e)(2)(iii) requirements.
19008-007 pitch trim actuator of this AD before of this AD before
installed. accumulating 2,000 accumulating 2,000
hours TIS on the pitch hours TIS on the pitch
trim actuator. trim actuator.
----------------------------------------------------------------------------------------------------------------
(5) For all airplane models except Models SA227-CC and SA227-DC:
As of the effective date of this AD, do not install as a replacement
any of the following pitch trim actuators or FAA-approved equivalent
P/N:
(i) Barber-Colman P/N 27-19008-001;
(ii) Barber-Colman P/N 27-19008-002;
(iii) Barber-Colman P/N 27-19008-004;
(iv) Barber-Colman P/N 27-19008-005; or
(v) Simmonds-Precision P/N DL5040M5.
(6) For all airplane Models SA227-CC and SA227-DC: As of the
effective date of this AD, do not install as a replacement any of
the following pitch trim actuators or FAA-approved equivalent P/N:
(i) Barber-Colman P/N 27-19008-001;
(ii) Barber-Colman P/N 27-19008-002;
(iii) Barber-Colman P/N 27-19008-004;
(iv) Barber-Colman P/N 27-19008-005;
(v) Simmonds-Precision P/N DL5040M5; or
(vi) Simmonds-Precision P/N DL5040M6.
Alternative Methods of Compliance (AMOCs)
(f) The Manager, Fort Worth Airplane Certification Office (ACO),
FAA, ATTN: Werner Koch, Aerospace Engineer, 2601 Meacham Blvd, Fort
Worth, Texas 76137-4298, has the authority to approve AMOCs for this
AD, if requested using the procedures found in 14 CFR 39.19. Before
using any approved AMOC on any airplane to which the AMOC applies,
notify your appropriate principal inspector (PI) in the FAA Flight
Standards District Office (FSDO), or lacking a PI, your local FSDO.
Related Information
(g) To get copies of the service information referenced in this
AD, contact M7 Aerospace LP, 10823 N. E. Entrance, San Antonio,
Texas 78216. To view the AD docket, go to the Docket Management
Facility; U.S. Department of Transportation, 400 Seventh Street,
SW., Nassif Building, Room PL-401, Washington, DC, or on the
Internet at https://dms.dot.gov. The docket number is Docket No. FAA-
2006-25927; Directorate Identifier 2006-CE-52-AD.
[[Page 21176]]
Issued in Kansas City, Missouri, on April 20, 2007.
Charles L. Smalley,
Acting Manager, Small Airplane Directorate, Aircraft Certification
Service.
[FR Doc. E7-8163 Filed 4-27-07; 8:45 am]
BILLING CODE 4910-13-P
