[Federal Register Volume 74, Number 150 (Thursday, August 6, 2009)]
[Proposed Rules]
[Pages 39243-39247]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: E9-18815]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2009-0707; Directorate Identifier 2009-CE-035-AD]
RIN 2120-AA64


Airworthiness Directives; Air Tractor, Inc. Models AT-802 and AT-
802A Airplanes

AGENCY: Federal Aviation Administration (FAA), Department of 
Transportation (DOT).

ACTION: Notice of proposed rulemaking (NPRM).

-----------------------------------------------------------------------

SUMMARY: We propose to supersede Airworthiness Directive (AD) 2006-08-
09, which applies to all Air Tractor, Inc. (Air Tractor) Models AT-802 
and AT-802A airplanes. AD 2006-08-09 currently requires you to 
repetitively inspect (using the eddy current method) the two outboard 
fastener holes in both of the wing main spar lower caps at the center 
splice joint for cracks and repair or replace any cracked spar cap. 
Since we issued AD 2006-08-09, we have determined we need to clarify 
the applicability of Models AT-802 and AT-802A airplanes affected 
serial number (SN) ranges. Additionally, we propose to add an option of 
modifying the wing main spar lower caps to extend the safe life limit 
on the affected airplanes. Consequently, this proposed AD would keep 
the actions of AD 2006-08-09, clarify the applicability of Models AT-
802 and AT-802A affected SN ranges, and add a modification option to 
extend the safe life limit. We are proposing this AD to detect and 
correct cracks in the wing main spar lower cap at the center splice 
joint, which could result in failure of the spar cap and lead to wing 
separation and loss of control of the airplane.

DATES: We must receive comments on this proposed AD by September 21, 
2009.

ADDRESSES: Use one of the following addresses to comment on this 
proposed AD:
    <bullet> Federal eRulemaking Portal: Go to http://www.regulations.gov. Follow the instructions for submitting comments.
    <bullet> Fax: (202) 493-2251.
    <bullet> Mail: U.S. Department of Transportation, Docket 
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New 
Jersey Avenue, SE., Washington, DC 20590.
    <bullet> Hand Delivery: U.S. Department of Transportation, Docket 
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New 
Jersey Avenue, SE., Washington, DC 20590, between 9 a.m. and 5 p.m., 
Monday through Friday, except Federal holidays.
    For service information identified in this proposed AD, contact Air 
Tractor, Inc., P.O. Box 485, Olney, Texas 76374; telephone: (940) 564-
5616; fax: (940) 564-5612; e-mail: <a href="/cdn-cgi/l/email-protection#35545c4758545c5975545c4741475456415a471b565a58"><span class="__cf_email__" data-cfemail="2a4b4358474b43466a4b43585e584b495e455804494547">[email protected]</span></a>; Internet: 
http://www.airtractor.com.

FOR FURTHER INFORMATION CONTACT: Andy McAnaul, Aerospace Engineer, ASW-
150, FAA San Antonio MIDO-43, 10100 Reunion Pl., Ste. 650, San Antonio, 
Texas 78216; telephone: (210) 308-3365; fax: (210) 308-3370.

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-
2009-0707; Directorate Identifier 2009-CE-035-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://www.regulations.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

    Since 2000, we have issued several airworthiness directives (ADs) 
related to the wing spar inspection and safe life on Air Tractor AT-
400, AT-500, AT-600, and AT-800 series airplanes.
    In 2001, we issued AD 2001-10-04, Amendment 39-12230 (66 FR 27014, 
May 16, 2001) to lower the safe life for the wing lower spar cap on Air 
Tractor AT-400, AT-500, and AT-800 series airplanes. This AD allowed 
for inspection (using eddy current methods) of the wing lower spar cap 
for airplanes that were at or over the lower safe life and for which 
parts were not available. Later that same year we revised that AD to 
remove AT-800 series airplanes from the applicability that were 
equipped with the factory-supplied computerized fire gate (part number 
80540) and engaged in full-time firefighting.
    In 2002, we issued AD 2002-11-05, Amendment 39-12766 (67 FR 37967, 
May 31, 2002) to further reduce the safe life for certain AT-400 series 
airplanes and certain AT-500 series airplanes that either incorporate 
or have incorporated Marburger winglets.
    After receiving reports of fatigue cracking found on three Model 
AT-802A airplanes that were below the reduced safe life established in 
AD 2002-11-05, we issued AD 2006-08-09, Amendment 39-14565 (71 FR 
27784, May 12, 2006). AD 2006-08-09 currently requires the following on 
Air Tractor Models AT-802 and AT-802A airplanes:
    <bullet> Repetitively inspecting (using the eddy current method) 
the two outboard fastener holes in both of the wing main spar lower 
caps at the center splice joint for cracks; and
    <bullet> Repairing or replacing any cracked spar cap.
    Since we issued AD 2006-08-09, we have determined we need to 
clarify the applicability of Models AT-802 and AT-802A airplanes 
affected SN ranges. The manufacturer, Air Tractor, shared a common SN 
range for the Models AT-802 and AT-802A. Sometimes service information 
listed only one of the models with a starting or ending SN within an SN 
range, depending on which model was produced with that specific SN, 
even though the service information applied to both models.
    Additionally, we propose to add an option of modifying the wing 
main spar

[[Page 39244]]

lower caps to extend the safe life limit on the affected airplanes.
    This condition, if not corrected, could result in failure of the 
spar cap and lead to wing separation and loss of control of the 
airplane.

Relevant Service Information

    We have reviewed the following Snow Engineering Co. service 
information:
    <bullet> Process Specification <greek-i>197, page 1, revised June 
4, 2002; pages 2 through 4, dated February 23, 2001; and page 5, dated 
May 3, 2002;
    <bullet> Process Specification <greek-i>204, Rev. C, dated November 
16, 2004;
    <bullet> Service Letter <greek-i>215, page 5, titled ``802 Spar 
Inspection Holes and Vent Tube Mod,'' dated November 19, 2003;
    <bullet> Service Letter <greek-i>240, dated September 30, 2004;
    <bullet> Service Letter <greek-i>244, dated April 25, 2005;
    <bullet> Drawing Number 20975, Sheet 2, Rev. A, dated September 1, 
2004;
    <bullet> Drawing Number 20975, Sheet 3, dated January 6, 2005; and
    <bullet> Drawing Number 20995, Sheet 2, Rev. C., dated September 
28, 2004.
    The service information describes procedures for:
    <bullet> Repetitively inspecting (using the eddy current method) 
the two outboard fastener holes in both of the wing main spar lower 
caps at the center splice joint for cracks; and
    <bullet> Repairing or replacing any cracked spar cap.

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 2006-08-09 with a new AD that would incorporate the 
actions in the previously-referenced service information. This proposed 
AD would require you to use the service information described 
previously to perform these actions.

Differences Between This Proposed AD and the Service Information

    Sometimes service information lists only one of the models with a 
starting or ending SN within an SN range, depending on which of those 
models was produced with that SN, even though the service information 
applies to both models. The requirements of this proposed AD, if 
adopted as a final rule, would take precedence over the provisions in 
the service information.

Costs of Compliance

    We estimate that this proposed AD would affect 187 airplanes in the 
U.S. registry.
    We estimate the following costs to do the proposed inspection:

----------------------------------------------------------------------------------------------------------------
                                                                                            Total cost on U.S.
              Labor cost                      Parts cost        Total cost per airplane         operators
----------------------------------------------------------------------------------------------------------------
$500 to $800.........................  Not applicable.........  $500 to $800...........  $93,500 to $149,600.
----------------------------------------------------------------------------------------------------------------

     We estimate the following costs to do any necessary repairs for 
two spars that may be required based on the results of the proposed 
inspection or the modification as an option. We have no way of 
determining the number of airplanes that may need this repair:

------------------------------------------------------------------------
                                                              Total cost
                                                 Parts cost  (two spars)
            Labor cost (two spars)              (two spars)      per
                                                               airplane
------------------------------------------------------------------------
225 work-hours x $80 per hour = $18,000.......       $7,500      $25,500
------------------------------------------------------------------------

     We estimate the following costs to do any necessary spar cap 
replacement (two spars) that would be required based on the results of 
the proposed inspection. We have no way of determining the number of 
airplanes that may need this replacement:

------------------------------------------------------------------------
                                                              Total cost
                                                 Parts cost  (two spars)
            Labor cost (two spars)              (two spars)      per
                                                               airplane
------------------------------------------------------------------------
495 work-hours x $80 per hour = $39,600.......      $39,100      $78,700
------------------------------------------------------------------------

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
    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.

[[Page 39245]]

    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://www.regulations.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) 647-5527) 
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, Incorporation by 
reference, Safety.

The Proposed Amendment

    Accordingly, under the authority delegated to me by the 
Administrator, the FAA proposes to amend 14 CFR part 39 as follows:

PART 39--AIRWORTHINESS DIRECTIVES

    1. The authority citation for part 39 continues to read as follows:

    Authority:  49 U.S.C. 106(g), 40113, 44701.


Sec.  39.13  [Amended]

    2. The FAA amends Sec.  39.13 by removing Airworthiness Directive 
(AD) 2006-08-09, Amendment 39-14565 (71 FR 27784, May 12, 2006), and 
adding the following new AD:

Air Tractor, Inc.: Docket No. FAA-2009-0707; Directorate Identifier 
2009-CE-035-AD.

Comments Due Date

    (a) We must receive comments on this airworthiness directive 
(AD) action by September 21, 2009.

Affected ADs

    (b) This AD supersedes AD 2006-08-09, Amendment 39-14565.

Applicability

    (c) This AD affects Model AT-802 and AT-802A airplanes, all 
serial numbers (SNs) beginning with -0001, that are:
    (1) Certificated in any category;
    (2) Engaged in agricultural dispersal operations, including 
those airplanes that have been converted from fire fighting to 
agricultural dispersal or airplanes that convert between fire 
fighting and agricultural dispersal;
    (3) Not equipped with the factory-supplied computerized fire 
gate (part number (P/N) 80540); and
    (4) Not engaged in only full-time fire fighting.

Unsafe Condition

    (d) This AD results from our determination that we need to 
clarify the applicability of Models AT-802 and AT-802A airplanes 
affected serial number (SN) ranges. Additionally, we are adding an 
option to modify the wing main spar lower caps to extend the safe 
life limit on the affected airplanes. We are issuing this AD to 
detect and correct cracks in the wing main spar lower cap at the 
center splice joint, which could result in failure of the spar cap 
and lead to wing separation and loss of control of the airplane.

Compliance

    (e) For Models AT-802 and AT-802A airplanes, SNs -0001 through -
0091, do the following actions, unless already done, using the wing 
main spar lower cap hours time-in-service (TIS) schedule found in 
Table 1 of this AD to do the initial and repetitive inspections:
    (1) Install access cover plates following Snow Engineering Co. 
Service Letter <greek-i>215, page 5, titled ``802 Spar Inspection 
Holes and Vent Tube Mod,'' dated November 19, 2003.
    (2) Eddy current inspect for cracks the center splice joint 
outboard two fastener holes in both the right and left wing main 
spar lower caps following Snow Engineering Co. Process Specification 
<greek-i>197, page 1, revised June 4, 2002; pages 2 through 4, dated 
February 23, 2001; and page 5, dated May 3, 2002.

                                            Table 1--Inspection Times
----------------------------------------------------------------------------------------------------------------
                                                                             Repetitively inspect  thereafter at
              SNs                     Condition         Initially inspect          intervals  not to exceed
----------------------------------------------------------------------------------------------------------------
(i) AT-802 and AT-802A, SNs -    As manufactured...  Upon accumulating       850 hours TIS.
 0001 through -0091.                                  1,700 hours TIS after
                                                      April 21, 2006 (the
                                                      effective date of AD
                                                      2006-08-09) or within
                                                      the next 50 hours TIS
                                                      after April 21, 2006
                                                      (the effective date
                                                      of AD 2006-08-09),
                                                      whichever occurs
                                                      later.
(ii) AT-802 and AT-802A, serial  Modified with       If performing the       1,700 hours TIS.
 numbers SNs -0001 through -      cold[dash]worked    cold[dash]working
 0091.                            fastener holes      procedure in Service
                                  following Service   Letter <greek-i>244,
                                  Letter <greek-      dated April 25, 2005,
                                  i>244, dated        it includes the
                                  April 25, 2005.     initial eddy current
                                                      inspection.
----------------------------------------------------------------------------------------------------------------

     (f) One of the following must do the eddy current inspections 
required in paragraph (e)(2) of this AD:
    (1) A level 2 or 3 inspector certified in eddy current 
inspection using the guidelines established by the American Society 
for Nondestructive Testing or MIL-STD-410; or
    (2) A person authorized to perform AD work and who has completed 
and passed the Air Tractor, Inc. training course on eddy current 
inspection on wing lower spar caps.
    (g) If cracks are found during any inspection required in 
paragraph (e)(2) of this AD, repair or replace any cracked spar cap 
before further flight after the inspection in which cracks are 
found. For repair or replacement, do whichever of the following that 
applies:
    (1) For cracks that can be repaired by incorporating the 
modification specified in paragraph (j) of this AD, do the actions 
following the procedures in paragraph (j) of this AD before further 
flight after the inspection in which cracks are found.
    (2) For cracks that cannot be repaired by incorporating the 
modification specified in paragraph (j) of this AD, replace the 
lower spar caps and associated parts listed following the procedures 
identified in paragraph (h) of this AD before further flight after 
the inspection in which cracks are found.
    (h) For all AT-802 and AT-802A airplanes, replace the wing main 
spar lower caps, the center joint splice blocks and hardware, the 
wing attach angles and hardware, and install the steel web splice 
plate (P/N 21106-1 for SNs -0001 through -0091, and P/N 20094-2 for 
all SNs beginning with -0092). Do the replacement upon accumulating 
the safe life hours TIS on the wing main spar lower caps as listed 
in Table 2 of this AD or within 50 hours TIS after April 21, 2006 
(the effective date of AD 2006-08-09), whichever occurs later. For 
SNs -0001 through -0091, you may extend the safe life hours TIS of 
the wing main spar lower caps to 8,000 hours TIS before doing the 
replacement if you modified your wing as specified in paragraph (j) 
of this AD.
    (1) Use the following service information for replacement:
    (i) For airplane Models AT-802 and AT-802A, SNs -0001 through -
0091, follow

[[Page 39246]]

Snow Engineering Co. Drawing Number 20975, Sheet 3, dated January 6, 
2005; and Process Specification <greek-i>204, Rev. C, dated November 
16, 2004.
    (ii) For airplane Models AT-802 and AT-802A, SNs beginning with 
-0092, follow Drawing Number 20975, Sheet 2, Rev. A, dated September 
1, 2004; and Process Specification <greek-i>204, Rev. C, dated 
November 16, 2004.
    (2) The following presents the safe life and replacement times 
as required in paragraph (h) of this AD:

                                    Table 2--Safe Life and Replacement Times
----------------------------------------------------------------------------------------------------------------
                      SNs                                         Wing spar lower cap safe life
----------------------------------------------------------------------------------------------------------------
AT-802-0001 through AT-802-0059...............  4,132 hours TIS.
AT-802-0060 through AT-802-0091...............  4,188 hours TIS.
All beginning with AT-802-0092................  8,163 hours TIS.
AT-802A-0001 through AT-802A-0059.............  4,969 hours TIS.
AT-802A-0060 through AT-802A-0091.............  4,531 hours TIS.
All beginning with AT-802A-0092...............  8,648 hours TIS.
----------------------------------------------------------------------------------------------------------------

     (i) After replacing the wing main spar lower caps and hardware, 
installing the web splice plate, and cold working the fastener holes 
by following Snow Engineering Co. Drawing Number 20975, Sheet 3, 
dated January 6, 2005 (SNs -0001 through -0091); or Sheet 2, Rev. A, 
dated September 1, 2004 (all SNs beginning with -0092); and Process 
Specification <greek-i>204, Rev. C, dated November 16, 2004, the new 
safe life for the wing main spar lower caps is as follows:

                              Table 3--New Safe Life for Wing Main Spar Lower Caps
----------------------------------------------------------------------------------------------------------------
                      SNs                                         Wing spar lower cap safe life
----------------------------------------------------------------------------------------------------------------
All beginning with AT-802-0001................  8,163 hours TIS.
All beginning with AT-802A-0001...............  8,648 hours TIS.
----------------------------------------------------------------------------------------------------------------

     (j) For Models AT-802 and AT-802A airplanes, SNs -0001 through 
-0091, in lieu of replacing the wing main spar lower cap at the safe 
life hours TIS listed in Table 2 in paragraph (h) of this AD, you 
may extend the safe life of the wing main spar lower caps by doing 
the following actions. Between 3,200 hours TIS and the safe life 
hours TIS for your airplane currently listed in Table 2 of this AD, 
do the following, unless already done:
    (1) Modify the wing by installing P/N 20997-2 web plate and P/N 
20985-1 and 20985-2 extended 8-bolt splice blocks following Snow 
Engineering Co. Drawing 20995, Sheet 2, Rev. C, dated September 28, 
2004.
    (2) Cold-work the outboard two fastener holes in both the left 
and right hand lower spar caps at the center splice following Snow 
Engineering Co. Service Letter <greek-i>240, dated September 30, 
2004.
    (3) Do an eddy current inspection of the wing center splice 
joint outboard two fastener holes in both the right and left wing 
main spar lower caps for cracks at the time of modification 
following Snow Engineering Co. Process Specification <greek-i>197, 
page 1, revised June 4, 2002; pages 2 through 4, dated February 23, 
2001; and page 5, dated May 3, 2002.
    (4) If, before the effective date of this AD, an airplane has 
already been modified following paragraph (j)(1) of this AD but did 
not receive cold working in the outboard two fastener holes in both 
the left and right hand lower spar caps following paragraph (j)(2) 
of this AD, do the following:
    (i) Initially do an eddy current inspection within the next 
2,400 hours TIS after the modification, using the procedure in 
paragraph (j)(3) of this AD, and repetitively thereafter at 
intervals not to exceed every 1,200 hours TIS until the wing spar 
lower cap reaches 8,000-hour TIS safe life.
    (ii) At any time after the modification, you may do the cold 
working in the outboard two fastener holes in both the left and 
right hand lower spar caps following paragraph (j)(2) of this AD to 
terminate the repetitive eddy current inspections required in 
paragraph (j)(4)(i) of this AD.
    (5) If you have modified your airplane following paragraph 
(j)(1) of this AD prior to 3,200 hours TIS, you must do the 
following to reach the extended 8,000-hour TIS safe life:
    (i) If you did not cold work in the outboard two fastener holes 
in both the left and right hand lower spar caps following paragraph 
(j)(2) of this AD, you must do the repetitive eddy current 
inspections following paragraph (j)(4)(i) of this AD until you 
accumulate 4,800 hours TIS after the modification on the wing spar 
lower cap. Upon accumulation of 4,800 hours TIS after the 
modification on the wing spar lower cap, do the repetitive eddy 
current inspections at intervals not to exceed every 600 hours TIS 
until you reach the extended safe life of 8,000-hour TIS.
    (ii) If you did cold work the outboard two fastener holes in 
both the left and right hand lower spar caps following paragraph 
(j)(2) of this AD, upon accumulation of 4,800 hours TIS after the 
modification on the wing spar lower cap do the repetitive eddy 
current inspections at intervals not to exceed every 600 hours TIS 
until you reach the 8,000-hour TIS safe life.
    (6) For the initial and repetitive eddy current inspections 
required in paragraphs (j)(3), (j)(4)(i), (j)(5)(i) and (j)(5)(ii) 
of this AD, follow the instructions as specified in Snow Engineering 
Co. Process Specification <greek-i>197, page 1, revised June 4, 
2002; pages 2 through 4, dated February 23, 2001; and page 5, dated 
May 3, 2002. For any cracks found, follow the instructions for 
repair or replacement as specified in paragraph (g) of this AD.
    (k) If any cracks are found as a result of any inspection 
required in paragraphs (e)(2), (j)(3), (j)4)(i), (j)(5)(i), and 
(j)(5)(ii) of this AD, report any cracks you find within 10 days 
after the cracks are found or within 10 days after April 21, 2006 
(the effective date of AD 2006-08-09), whichever occurs later.
    (1) Include in your report the aircraft SN, aircraft hours TIS, 
wing spar cap hours TIS, crack location and size, corrective action 
taken, and a point of contact name and phone number. Send your 
report to Andrew McAnaul, Aerospace Engineer, ASW-150 (c/o MIDO-43), 
10100 Reunion Place, Suite 650, San Antonio, Texas 78216; telephone: 
(210) 308-3365; facsimile: (210) 308-3370.
    (2) The Office of Management and Budget (OMB) approved the 
information collection requirements contained in this regulation 
under the provisions of the Paperwork Reduction Act and assigned OMB 
Control Number 2120-0056.

Special Permit Flight

    (l) Under 14 CFR part 39.23, we are allowing special flight 
permits for the purpose of compliance with this AD under the 
following conditions:
    (1) Only operate in day visual flight rules (VFR).
    (2) Ensure that the hopper is empty.
    (3) Limit airspeed to 135 miles per hour (mph) indicated 
airspeed (IAS).
    (4) Avoid any unnecessary g-forces.
    (5) Avoid areas of turbulence.
    (6) Plan the flight to follow the most direct route.

Alternative Methods of Compliance (AMOCs)

    (m) The Manager, Fort Worth Airplane Certification Office, ASW-
150, FAA, has the authority to approve AMOCs for this AD, if 
requested using the procedures found in 14

[[Page 39247]]

CFR 39.19. Send information to ATTN: Andy McAnaul, Aerospace 
Engineer, ASW-150, FAA San Antonio MIDO-43, 10100 Reunion Pl., Ste. 
650, San Antonio, Texas 78216; telephone: (210) 308-3365; fax: (210) 
308-3370. 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.
    (n) AMOCs approved for AD 2006-08-09 are not approved for this 
AD.

Related Information

    (o) To get copies of the service information referenced in this 
AD, contact Air Tractor, Inc., P.O. Box 485, Olney, Texas 76374; 
telephone: (940) 564-5616; fax: (940) 564-5612; e-mail: 
<a href="/cdn-cgi/l/email-protection#96f7ffe4fbf7fffad6f7ffe4e2e4f7f5e2f9e4b8f5f9fb"><span class="__cf_email__" data-cfemail="b8d9d1cad5d9d1d4f8d9d1cacccad9dbccd7ca96dbd7d5">[email protected]</span></a>; Internet: www.airtractor.com. 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://www.regulations.gov.

    Issued in Kansas City, Missouri, on July 31, 2009.
James E. Jackson,
Acting Manager, Small Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. E9-18815 Filed 8-5-09; 8:45 am]
BILLING CODE 4910-13-P


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