[Federal Register: August 3, 2007 (Volume 72, Number 149)]
[Rules and Regulations]
[Page 43139-43144]
From the Federal Register Online via GPO Access [wais.access.gpo.gov]
[DOCID:fr03au07-3]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2006-25927; Directorate Identifier 2006-CE-52-AD;
Amendment 39-15142; AD 2007-16-03]
RIN 2120-AA64
Airworthiness Directives; M7 Aerospace LP SA226 and SA227 Series
Airplanes
AGENCY: Federal Aviation Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule.
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SUMMARY: We are adopting a new airworthiness directive (AD) to
supersede 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. Since we issued
AD 98-19-15 R1 and AD 2000-03-17, 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 AD retains all of the actions
of the previously referenced ADs, places life limits on certain P/N
pitch trim actuators, and requires the replacement of certain P/N pitch
trim actuators with one of an improved design. Once installed, the
improved design pitch trim actuator will terminate the AFM limitations
in this AD and reduce the repetitive inspection and repetitive
replacement requirements. We are issuing 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 issuing 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: This AD becomes effective on September 7, 2007.
[[Page 43140]]
As of April 10, 2000 (65 FR 8037, February 17, 2000), the Director
of the Federal Register approved the incorporation by reference of the
following Fairchild Aircraft service information listed in this AD:
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.
ADDRESSES: For service information identified in this AD, contact M7
Aerospace LP, 10823 N.E. Entrance, San Antonio, Texas 78216.
To view the AD docket, go to U.S. Department of Transportation,
Docket Operations, M-30, West Building Ground Floor, Room W12-140, 1200
New Jersey Avenue, SE., Washington, DC 20590, or on the Internet at
http://dms.dot.gov. The docket number is FAA-2006-25927; Directorate
Identifier 2006-CE-52-AD.
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:
Discussion
On April 20, 2007, we issued a proposal to amend part 39 of the
Federal Aviation Regulations (14 CFR part 39) to include an AD that
would apply to M7 Aerospace LP SA226 and SA227 series airplanes
equipped with certain pitch trim actuators. This proposal was published
in the Federal Register as a notice of proposed rulemaking (NPRM) on
April 30, 2007 (72 FR 21171). The NPRM proposed to 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. The NPRM
also proposed placing a life limit on Barber-Coleman pitch trim
actuators P/N 27-19008-001, P/N 27-19008-002, P/N 27-19008-004, and P/N
27-19008-005. The NPRM proposed to require you to use the service
information described previously to perform these actions.
Comments
We provided the public the opportunity to participate in developing
this AD. We received no comments on the proposal or on the
determination of the cost to the public.
Conclusion
We have carefully reviewed the available data and determined that
air safety and the public interest require adopting the AD as proposed
except for minor editorial corrections. We have determined that these
minor corrections:
Are consistent with the intent that was proposed in the
NPRM for correcting the unsafe condition; and
Do not add any additional burden upon the public than was
already proposed in the NPRM.
Costs of Compliance
We estimate that this AD affects 307 airplanes in the U.S.
registry.
This AD requires pitch trim actuators to have a combination of
inspections, overhaul, and/or replacement. 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 have no way of determining the number of
airplanes needing replacement. (See below for airplane replacement
cost.)
We estimate the following costs to do the inspection or overhaul:
----------------------------------------------------------------------------------------------------------------
Total cost per Total cost on
Labor cost Parts cost airplane U.S. operators
----------------------------------------------------------------------------------------------------------------
For inspection: 4 work-hours x $80 per hour None............................... $320 $98,240
= $320.
For overhaul: 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 are required through the actions of this AD. 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 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 installed 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.
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 AD.
Regulatory Findings
We have determined that this AD will not have federalism
implications under Executive Order 13132. This AD will not have a
substantial direct effect on the States, on the relationship between
the national government and the States, or on the distribution of power
and responsibilities among the various levels of government.
For the reasons discussed above, I certify that this AD:
1. Is not a ``significant regulatory action'' under Executive Order
12866;
[[Page 43141]]
2. Is not a ``significant rule'' under the DOT Regulatory Policies
and Procedures (44 FR 11034, February 26, 1979); and
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 summary of the costs to comply with this AD (and
other information as included in the Regulatory Evaluation) and placed
it in the AD Docket. You may get a copy of this summary by sending a
request to us at the address listed under ADDRESSES. Include ``Docket
No. FAA-2006-25927; Directorate Identifier 2006-CE-52-AD'' in your
request.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation safety, Safety.
Adoption of the Amendment
0
Accordingly, under the authority delegated to me by the Administrator,
the Federal Aviation Administration amends part 39 of the Federal
Aviation Regulations (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)
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:
2007-16-03 M7 Aerospace LP (Type Certificate No. A5SW, A8SW, and
A18SW formerly held by Fairchild Aircraft Incorporated): Amendment
39-15142; Docket No. FAA-2006-25927; Directorate Identifier 2007-CE-
52-AD.
Effective Date
(a) This AD becomes effective on September 7, 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 issuing 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 issuing 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 issuing 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 actions at the times
specified in the initial inspection or overhaul column and the
repetitive inspection or overhaul column in table 1 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-Colman 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-Colman 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 ratcheting sound occurs, as
specified in the applicable service letters; or
(ii) The installed pitch trim actuator reaches its repetitive
replacement time as specified in table 1 in paragraph (e)(4) of this
AD.
(4) Table 1 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 43142]]
Table 1.--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
paragraph (e)(4)(i) accumulating 5,000
Repetitive Replacement hours TIS on the pitch
column of this AD. trim actuator, 500
hours TIS after the
initial inspection, or
within 30 days after
September 7, 2007 (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
paragraph (e)(4)(ii) accumulating 6,500
Repetitive Replacement hours TIS on the pitch
column of this AD. trim actuator or
within 30 days after
September 7, 2007 (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
paragraph (e)(4)(iii) accumulating 9,900
Repetitive Replacement hours TIS on the pitch
column of this AD. trim actuator or
within 30 days after
September 7, 2007 (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
paragraph (e)(4)(iv) accumulating 6,500
Repetitive Replacement hours TIS on the pitch
column of this AD. trim actuator or
within 30 days after
September 7, 2007 (the
effective date of this
AD), whichever occurs
later.
[[Page 43143]]
(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
paragraph (e)(4)(v) accumulating 5,000
Repetitive Replacement hours TIS on the pitch
column of this AD. trim actuator or
within 30 days after
September 7, 2007 (the
effective date of this
AD), whichever occurs
later.
(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 overhauled 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
paragraph (e)(4)(vi) accumulating 5,000
Repetitive Replacement hours TIS on the pitch
column of this AD. trim actuator or
within 30 days after
September 7, 2007 (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 P/N
DL5040M5 or P/N DL5040M6 installed. DL5040M8, Barber-
Coleman P/N 27-19008-
006 or P/N 27-19008-
007, or an FAA-
approved equivalent
pitch trim actuator
before accumulating
1,500 hours TIS on the
pitch trim actuator or
within 30 days after
September 7, 2007 (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 overhauled 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
paragraph (e)(4)(viii) trim actuator or
Repetitive Replacement within 30 days after
column of this AD. September 7, 2007 (the
effective date of 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 P/N
accumulating 7,500 accumulating 300 hours DL5040M8, Barber-
hours TIS on the pitch TIS after the initial Coleman P/N 27-19008-
trim actuator or inspection and 006 or P/N 27-19008-
within the next 50 repetitively 007, or an FAA-
hours TIS after April thereafter at approved equivalent
10, 2000 (the intervals not to pitch trim actuator
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 September 7, 2007 (the
column of this AD. effective date of 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.
----------------------------------------------------------------------------------------------------------------
[[Page 43144]]
(5) For all airplane models except Models SA227-CC and SA227-DC:
As of September 7, 2007 (the effective date of this AD), do not
install as a replacement any of the following pitch trim actuators
or FAA-approved equivalent P/Ns:
(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
September 7, 2007 (the effective date of this AD), do not install as
a replacement any of the following pitch trim actuators or FAA-
approved equivalent P/Ns:
(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.
Material Incorporated by Reference
(g) You must use the service information specified in table 2 of
this AD to do the actions required by this AD, unless the AD
specifies otherwise.
(1) On April 10, 2000 (65 FR 8037, February 17, 2000) the
Director of the Federal Register approved the incorporation by
reference of the service information listed in table 2 of this AD
under 5 U.S.C. 552(a) and 1 CFR part 51.
(2) For service information identified in this AD, contact M7
Aerospace LP, 10823 N. E. Entrance, San Antonio, Texas 78216.
(3) You may review copies at the FAA, Central Region, Office of
the Regional Counsel, 901 Locust, Kansas City, Missouri 64106; or at
the National Archives and Records Administration (NARA). For
information on the availability of this material at NARA, call 202-
741-6030, or go to: http://www.archives.gov/federal_register/code_of_federal_regulations/ibr_locations.html
.
Table 2.--Material Incorporated by Reference
------------------------------------------------------------------------
Service Letter (SL) Date
------------------------------------------------------------------------
Fairchild Aircraft SA226 Revised: August 3, 1999.
Series SL 226-SL-005.
Fairchild Aircraft SA227 Revised: August 3, 1999.
Series SL 227-SL-011.
Fairchild Aircraft SA227 Issued: August 12, 1999.
Series SL CC7-SL-028.
Fairchild Aircraft SA226 Revised: February 1, 1999.
Series SL 226-SL-014.
Fairchild Aircraft SA227 Revised: February 1, 1999.
Series SL 227-SL-031.
Fairchild Aircraft SA227 Revised: February 1, 1999.
Series SL CC7-SL-021.
------------------------------------------------------------------------
Issued in Kansas City, Missouri, on July 27, 2007.
James E. Jackson,
Acting Manager, Small Airplane Directorate, Aircraft Certification
Service.
[FR Doc. E7-15018 Filed 8-2-07; 8:45 am]
BILLING CODE 4910-13-P