
[Federal Register: June 23, 2010 (Volume 75, Number 120)]
[Rules and Regulations]               
[Page 35616-35619]
From the Federal Register Online via GPO Access [wais.access.gpo.gov]
[DOCID:fr23jn10-5]                         

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

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2009-0707; Directorate Identifier 2009-CE-035-AD; 
Amendment 39-16339; AD 2010-13-08]
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: Final rule.

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

SUMMARY: We are adopting a new airworthiness directive (AD) to 
supersede 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 serial numbers (SNs) of the Models AT-802 and AT-
802A airplanes affected by that AD. Additionally, we are adding an 
option of modifying the wing main spar lower caps to extend the safe 
life limit on the affected airplanes. Consequently, this AD would keep 
the actions of AD 2006-08-09, clarify the affected SNs, and add a 
modification option to extend the safe life limit. 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.

DATES: This AD becomes effective on July 28, 2010.
    As of April 21, 2006 (71 FR 19994, April 19, 2006) the Director of 
the Federal Register approved the incorporation by reference of Snow 
Engineering Co. Process Specification 197, page 1, revised 
June 4, 2002; pages 2 through 4, dated February 23, 2001; and page 5, 
dated May 3, 2002; Snow Engineering Co. Process Specification 
204, Rev. C, dated November 16, 2004; Snow Engineering Co. 
Service Letter 215, page 5, titled ``802 Spar Inspection Holes 
and Vent Tube Mod,'' dated November 19, 2003; Snow Engineering Co. 
Service Letter 240, dated September 30, 2004; Snow Engineering 
Co. Drawing Number 20975, Sheet 2, Rev. A, dated September 1, 2004; 
Snow Engineering Co. Drawing Number 20975, Sheet 3, dated January 6, 
2005; and Snow Engineering Co. Drawing 20995, Sheet 2, Rev. C, dated 
September 28, 2004, listed in this AD.

ADDRESSES: For service information identified in this AD, contact Air 
Tractor, Inc., P.O. Box 485, Olney, Texas 76374; telephone: (940) 564-
5616; fax: (940) 564-5612; E-mail: airmail@airtractor.com; Internet: 
http://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. The docket number is FAA-2009-0707; 
Directorate Identifier 2009-CE-035-AD.

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

SUPPLEMENTARY INFORMATION:

Discussion

    On July 31, 2009, 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 all Air Tractor Models AT-802 and AT-802A airplanes. 
This proposal was published in the Federal Register as a notice of 
proposed rulemaking (NPRM) on August 6, 2009 (74 FR 39243). The NPRM 
proposed to supersede AD 2006-08-09 to clarify the SNs of the Models 
AT-802 and AT-802A airplanes affected by that AD. Additionally, we 
proposed to add an option of modifying the wing main spar lower caps to 
extend the safe life limit on the affected airplanes.

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 187 airplanes in the U.S. 
registry.
    We estimate the following costs to do the inspection:

----------------------------------------------------------------------------------------------------------------
           Labor cost                Parts cost        Total cost per airplane      Total cost on U.S. 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 inspection 
or the modification as an option. We have no way of determining the 
number of airplanes that may need this repair:

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


[[Page 35617]]

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

------------------------------------------------------------------------
                                                            Total cost
         Labor cost (two spars)             Parts 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 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;
    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-2009-0707; Directorate Identifier 2009-CE-035-AD'' in your 
request.

List of Subjects in 14 CFR Part 39

    Air transportation, Aircraft, Aviation safety, Incorporation by 
reference, 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) 
2006-08-09, amendment 39-14565 (71 FR 27784, May 12, 2006), and adding 
the following new AD:

2010-13-08 Air Tractor, Inc.: Amendment 39-16339; Docket No. FAA-
2009-0707; Directorate Identifier 2009-CE-035-AD.

Effective Date

    (a) This AD becomes effective on July 28, 2010.

Affected ADs

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

Applicability

    (c) This AD affects Models 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 SNs of the Models AT-802 and AT-802A airplanes affected 
by AD 2006-08-09. 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 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 
197, page 1, revised June 4, 2002; pages 2 through 4, dated 
February 23, 2001; and page 5, dated May 3, 2002.

[[Page 35618]]



                                            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 1,700 hours TIS   850 hours TIS.
 0001 through -0091.                                    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 -0091.  cold[dash]worked     cold[dash]working procedure in
                                   fastener holes       Service Letter 244,
                                   following Service    dated April 25, 2005, it includes
                                   Letter 244, dated April   inspection.
                                   25, 2005.
----------------------------------------------------------------------------------------------------------------

     (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 Models AT-802 and AT-802A airplanes, SNs -0001 through -
0091, follow Drawing Number 20975, Sheet 3, dated January 6, 2005; 
and Snow Engineering Co. Process Specification 204, Rev. C, 
dated November 16, 2004.
    (ii) For Models AT-802 and AT-802A airplanes, SNs beginning with 
-0092, follow Snow Engineering Co. Drawing Number 20975, Sheet 2, 
Rev. A, dated September 1, 2004; and Snow Engineering Co. Process 
Specification 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 Snow Engineering 
Co. Drawing Number 20975, Sheet 2, Rev. A, dated September 1, 2004 
(all SNs beginning with -0092); and Snow Engineering Co. Process 
Specification 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 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 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 July 28, 2010 (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

[[Page 35619]]

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 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 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 Andy 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 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: 
airmail@airtractor.com; Internet: http://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.

Material Incorporated by Reference

    (p) You must use Snow Engineering Co. Process Specification 
197, page 1, revised June 4, 2002; pages 2 through 4, dated 
February 23, 2001; and page 5, dated May 3, 2002; Snow Engineering 
Co. Process Specification 204, Rev. C, dated November 16, 
2004; Snow Engineering Co. Service Letter 215, page 5, 
titled ``802 Spar Inspection Holes and Vent Tube Mod,'' dated 
November 19, 2003; Snow Engineering Co. Service Letter 240, 
dated September 30, 2004; Snow Engineering Co. Drawing Number 20975, 
Sheet 2, Rev. A, dated September 1, 2004; Snow Engineering Co. 
Drawing Number 20975, Sheet 3, dated January 6, 2005; and Snow 
Engineering Co. Drawing 20995, Sheet 2, Rev. C, dated September 28, 
2004, to do the actions required by this AD, unless the AD specifies 
otherwise.
    (1) On April 21, 2006 (71 FR 19994, April 19, 2006), the 
Director of the Federal Register approved the incorporation by 
reference of Snow Engineering Co. Process Specification 
197, page 1, revised June 4, 2002; pages 2 through 4, dated 
February 23, 2001; and page 5, dated May 3, 2002; Snow Engineering 
Co. Process Specification 204, Rev. C, dated November 16, 
2004; Snow Engineering Co. Service Letter 215, page 5, 
titled ``802 Spar Inspection Holes and Vent Tube Mod,'' dated 
November 19, 2003; Snow Engineering Co. Service Letter 240, 
dated September 30, 2004; Snow Engineering Co. Drawing Number 20975, 
Sheet 2, Rev. A, dated September 1, 2004; Snow Engineering Co. 
Drawing Number 20975, Sheet 3, dated January 6, 2005; and Snow 
Engineering Co. Drawing 20995, Sheet 2, Rev. C, dated September 28, 
2004, under 5 U.S.C. 552(a) and 1 CFR part 51.
    (2) For service information identified in this AD, contact Air 
Tractor, Inc., P.O. Box 485, Olney, Texas 76374; telephone: (940) 
564-5616; fax: (940) 564-5612; E-mail: airmail@airtractor.com; 
Internet: http://www.airtractor.com.
    (3) You may review copies of the service information 
incorporated by reference for this AD at the FAA, Central Region, 
Office of the Regional Counsel, 901 Locust, Kansas City, Missouri 
64106. For information on the availability of this material at the 
Central Region, call (816) 329-3768.
    (4) You may also review copies of the service information 
incorporated by reference for this AD 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.

    Issued in Kansas City, Missouri on June 15, 2010.
Sandra J. Campbell,
Acting Manager, Small Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 2010-14990 Filed 6-22-10; 8:45 am]
BILLING CODE 4910-13-P

