Federal Register / Vol. 74, No. 150 / Thursday, August 6, 2009 / Proposed Rules 39243 

and novel aircraft can be evaluated, and 

the effects of aircraft configuration 

changes may be observed and measured. 

A Flying Qualities Demonstrator would 

enable the use of aircraft with modified 

flight controls to be used in the 

demonstration and development of 

flying qualities and flight controls. It is 

impractical to certificate these modified 

aircraft in compliance with the 

requirements of their standard category 

type certificate. Approval of these flight 

operations will be in compliance with 

the restricted category operating 

limitations specified in 14 CFR 91.313. 

How To Obtain Copies: 

You may get a copy of our proposal 

from the Internet at: http://www.faa.gov/ 

aircraft/draft_docs/. 

You may also request a copy from Mr. 

Graham Long. See the section entitled 

FOR FURTHER INFORMATION CONTACT for 

the complete address. 

Issued in Washington, DC, on July 24, 

2009. 

Susan J. M. Cabler, 

Assistant Manager, Aircraft Engineering 

Division, Aircraft Certification Service. 

[FR Doc. E9–18573 Filed 8–5–09; 8:45 am] 

BILLING CODE 4910–13–P 

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: 

• Federal eRulemaking Portal: Go to 

http://www.regulations.gov. Follow the 

instructions for submitting comments. 

• Fax: (202) 493–2251. 

• 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. 

• 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: 

airmail@airtractor.com; 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: 

• 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 

• 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 


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39244 Federal Register / Vol. 74, No. 150 / Thursday, August 6, 2009 / Proposed Rules 

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: 

• Process Specification #197, page 1, 

revised June 4, 2002; pages 2 through 4, 

dated February 23, 2001; and page 5, 

dated May 3, 2002; 

• Process Specification #204, Rev. C, 

dated November 16, 2004; 

• Service Letter #215, page 5, titled 

‘‘802 Spar Inspection Holes and Vent 

Tube Mod,’’ dated November 19, 2003; 

• Service Letter #240, dated 

September 30, 2004; 

• Service Letter #244, dated April 25, 

2005; 

• Drawing Number 20975, Sheet 2, 

Rev. A, dated September 1, 2004; 

• Drawing Number 20975, Sheet 3, 

dated January 6, 2005; and 

• Drawing Number 20995, Sheet 2, 

Rev. C., dated September 28, 2004. 

The service information describes 

procedures for: 

• 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 

• 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: 

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 proposed inspection or the 

modification as an option. We have no 

way of determining the number of 

airplanes that may need this repair: 

Labor cost (two spars) Parts cost 

(two spars) 

Total cost 

(two spars) 

per airplane 

225 work-hours × $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: 

Labor cost (two spars) Parts cost 

(two spars) 

Total cost 

(two spars) 

per airplane 

495 work-hours × $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. 


jlentini on DSKJ8SOYB1PROD with PROPOSALS
Federal Register / Vol. 74, No. 150 / Thursday, August 6, 2009 / Proposed Rules 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. 

§ 39.13 [Amended] 

2. The FAA amends § 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-inservice (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. 

TABLE 1—INSPECTION TIMES

SNs Condition Initially inspect 

Repetitively inspect 

thereafter at intervals 

not to exceed 

(i) AT–802 and AT–802A, SNs 

–0001 through –0091.

As manufactured ........................ Upon accumulating 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.

850 hours TIS. 

(ii) AT–802 and AT–802A, serial 

numbers SNs –0001 through 

–0091.

Modified with cold-worked fastener holes following Service 

Letter #244, dated April 25, 

2005.

If performing the cold-working procedure in 

Service Letter #244, dated April 25, 

2005, it includes the initial eddy current 

inspection.

1,700 hours TIS. 

(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 


jlentini on DSKJ8SOYB1PROD with PROPOSALS
39246 Federal Register / Vol. 74, No. 150 / Thursday, August 6, 2009 / Proposed Rules 

Snow Engineering Co. Drawing Number 

20975, Sheet 3, dated January 6, 2005; and 

Process Specification #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 #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 #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 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 #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 


jlentini on DSKJ8SOYB1PROD with PROPOSALS
Federal Register / Vol. 74, No. 150 / Thursday, August 6, 2009 / Proposed Rules 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: airmail@airtractor.com; 

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 

DEPARTMENT OF HOMELAND 

SECURITY 

Coast Guard 

33 CFR Part 165 

[Docket No. USCG–2009–0319] 

RIN 1625–AA00 

Safety Zone; Sea World December 

Fireworks, Mission Bay, San Diego, CA 

AGENCY: Coast Guard, DHS. 

ACTION: Notice of proposed rulemaking. 

SUMMARY: The Coast Guard proposes to 

establish a safety zone upon the 

navigable waters of Mission Bay near 

San Diego, California in support of the 

Sea World December Fireworks. This 

safety zone is necessary to provide for 

the safety of the participants, crew, 

spectators, participating vessels, and 

other users of the waterway. Persons 

and vessels are prohibited from entering 

into, transiting through, or anchoring 

within this safety zone unless 

authorized by the Captain of the Port, or 

his designated representative. 

DATES: Comments and related material 

must be received by the Coast Guard on 

or before September 8, 2009. 

ADDRESSES: You may submit comments 

identified by docket number USCG– 

2009–0319 using any one of the 

following methods: 

(1) Federal eRulemaking Portal: 

http://www.regulations.gov. 

(2) Fax: 202–493–2251. 

(3) Mail: Docket Management Facility 

(M–30), U.S. Department of 

Transportation, West Building Ground 

Floor, Room W12–140, 1200 New Jersey 

Avenue, SE., Washington, DC 20590– 

0001. 

(4) Hand delivery: Same as mail 

address above, between 9 a.m. and 5 

p.m., Monday through Friday, except 

Federal holidays. The telephone number 

is 202–366–9329. 

To avoid duplication, please use only 

one of these four methods. See the 

‘‘Public Participation and Request for 

Comments’’ portion of the 

SUPPLEMENTARY INFORMATION section 

below for instructions on submitting 

comments. 

FOR FURTHER INFORMATION CONTACT: If 

you have questions on this proposed 

rule, call or e-mail Petty Officer Shane 

Jackson, Waterways Management, U.S. 

Coast Guard Sector San Diego at 

telephone 619–278–7262, e-mail 

Shane.E.Jackson@uscg.mil. If you have 

questions on viewing or submitting 

material to the docket, call Renee V. 

Wright, Program Manager, Docket 

Operations, telephone 202–366–9826. 

SUPPLEMENTARY INFORMATION: 

Public Participation and Request for 

Comments 

We encourage you to participate in 

this rulemaking by submitting 

comments and related materials. All 

comments received will be posted 

without change to http:// 

www.regulations.gov and will include 

any personal information you have 

provided. 

Submitting Comments 

If you submit a comment, please 

include the docket number for this 

rulemaking (USCG–2009–0319), 

indicate the specific section of this 

document to which each comment 

applies, and provide a reason for each 

suggestion or recommendation. You 

may submit your comments and 

material online (via http:// 

www.regulations.gov) or by fax, mail, or 

hand delivery, but please use only one 

of these means. If you submit a 

comment online via http:// 

www.regulations.gov, it will be 

considered received by the Coast Guard 

when you successfully transmit the 

comment. If you fax, hand deliver, or 

mail your comment, it will be 

considered as having been received by 

the Coast Guard when it is received at 

the Docket Management Facility. We 

recommend that you include your name 

and a mailing address, an e-mail 

address, or a telephone number in the 

body of your document so that we can 

contact you if we have questions 

regarding your submission. 

To submit your comment online, go to 

http://www.regulations.gov, select the 

Advanced Docket Search option on the 

right side of the screen, insert ‘‘USCG– 

2009–0319’’ in the Docket ID box, press 

Enter, and then click on the balloon 

shape in the Actions column. If you 

submit your comments by mail or hand 

delivery, submit them in an unbound 

format, no larger than 81⁄2 by 11 inches, 

suitable for copying and electronic 

filing. If you submit comments by mail 

and would like to know that they 

reached the Facility, please enclose a 

stamped, self-addressed postcard or 

envelope. We will consider all 

comments and material received during 

the comment period and may change 

the rule based on your comments. 

Viewing Comments and Documents 

To view comments, as well as 

documents mentioned in this preamble 

as being available in the docket, go to 

http://www.regulations.gov, select the 

Advanced Docket Search option on the 

right side of the screen, insert USCG– 

2009–0319 in the Docket ID box, press 

Enter, and then click on the item in the 

Docket ID column. You may also visit 

the Docket Management Facility in 

Room W12–140 on the ground floor of 

the Department of Transportation West 

Building, 1200 New Jersey Avenue, SE., 

Washington, DC 20590, between 9 a.m. 

and 5 p.m., Monday through Friday, 

except Federal holidays. We have an 

agreement with the Department of 

Transportation to use the Docket 

Management Facility. 

Privacy Act 

Anyone can search the electronic 

form of comments received into any of 

our dockets by the name of the 

individual submitting the comment (or 

signing the comment, if submitted on 

behalf of an association, business, labor 

union, etc.). You may review a Privacy 

Act notice regarding our public dockets 

in the January 17, 2008 issue of the 

Federal Register (73 FR 3316). 

Public Meeting 

We do not now plan to hold a public 

meeting. But you may submit a request 

for one using one of the four methods 

specified under ADDRESSES. Please 

explain why you believe a public 

meeting would be beneficial. If we 

determine that one would aid this 

rulemaking, we will hold one at a time 


jlentini on DSKJ8SOYB1PROD with PROPOSALS