[Federal Register Volume 72, Number 82 (Monday, April 30, 2007)]
[Proposed Rules]
[Pages 21171-21176]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: E7-8163]


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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]
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).

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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:
    <bullet> DOT Docket web site: Go to http://dms.dot.gov and follow 
the instructions for sending your comments electronically.
    <bullet> Mail: Docket Management Facility; U.S. Department of 
Transportation, 400 Seventh Street, SW., Nassif Building, Room PL-401, 
Washington, DC 20590-0001.
    <bullet> Fax: (202) 493-2251.
    <bullet> 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.
    <bullet> Federal eRulemaking Portal: Go to http://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 http://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:
    <bullet> Fairchild Aircraft SA226 Series Service Letter (SL) 226-
SL-005, Revised: August 3, 1999;
    <bullet> Fairchild Aircraft SA227 Series SL 227-SL-011, Revised 
August 3, 1999;
    <bullet> Fairchild Aircraft SA227 Series SL CC7-SL-028, Issued: 
August 12, 1999;
    <bullet> Fairchild Aircraft SA226 Series SL 226-SL-014, Revised: 
February 1, 1999;
    <bullet> Fairchild Aircraft SA227 Series SL 227-SL-031, Revised: 
February 1, 1999; and
    <bullet> 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 http://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 http://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