45900 Federal Register / Vol. 73, No. 153 / Thursday, August 7, 2008 / Proposed Rules 

(2) Install a tie-wrap through the lower 

bolts of the stabilizer control unit, in 

accordance with the Accomplishment 

Instructions of Fokker Service Bulletin 

SBF100–27–091, dated August 31, 2007. 

FAA AD Differences 

Note: This AD differs from the MCAI and/ 

or service information as follows: No 

differences. 

Other FAA AD Provisions 

(g) The following provisions also apply to 

this AD: 

(1) Alternative Methods of Compliance 

(AMOCs): The Manager, International 

Branch, ANM–116, 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: Tom Rodriguez, 

Aerospace Engineer, International Branch, 

ANM–116, FAA, Transport Airplane 

Directorate, 1601 Lind Avenue, SW., Renton, 

WA 98057–3356; telephone (425) 227–1137; 

fax (425) 227–1149. 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. 

(2) Airworthy Product: For any 

requirement in this AD to obtain corrective 

actions from a manufacturer or other source, 

use these actions if they are FAA-approved. 

Corrective actions are considered FAAapproved if they are approved by the State 

of Design Authority (or their delegated 

agent). You are required to assure the product 

is airworthy before it is returned to service. 

(3) Reporting Requirements: For any 

reporting requirement in this AD, under the 

provisions of the Paperwork Reduction Act, 

the Office of Management and Budget (OMB) 

has approved the information collection 

requirements and has assigned OMB Control 

Number 2120–0056. 

Related Information 

(h) Refer to MCAI European Aviation 

Safety Agency Airworthiness Directive 2007–

0287, dated November 15, 2007, and Fokker 

Service Bulletin SBF100–27–091, dated 

August 31, 2007, for related information. 

Issued in Renton, Washington, on July 29, 

2008. 

Ali Bahrami, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. E8–18225 Filed 8–6–08; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2008–0854; Directorate 

Identifier 2008–CE–050–AD] 

RIN 2120–AA64 

Airworthiness Directives; Allied Ag Cat 

Productions, Inc. G–164 Series 

Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Notice of proposed rulemaking 

(NPRM). 

SUMMARY: We propose to supersede 

Airworthiness Directive (AD) 78–08–09, 

which applies to certain Allied Ag Cat 

Productions, Inc. (formerly GrummanAmerican) Models G–164, G–164A, and 

G–164B airplanes. AD 78–08–09 

currently requires repetitively 

inspecting the interior and the exterior 

of the main tubular spar of the rudder 

assembly for corrosion, taking necessary 

corrective action if corrosion is found, 

and applying corrosion protection. 

Since we issued AD 78–08–09, the 

rudder main tubular spar failed on a 

later production airplane. Consequently, 

this proposed AD would retain the 

actions required in AD 78–08–09 and 

expand the applicability to include all 

G–164 series airplanes. We are 

proposing this AD to detect and correct 

corrosion in the rudder main tubular 

spar, which could result in failure of the 

weld to the main spar tube. This failure 

could lead to loss of directional control. 

DATES: We must receive comments on 

this proposed AD by October 6, 2008. 

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 Grumman 

American Aviation Corporation, P.O. 

Box 2206, Savannah, Georgia 31402; 

telephone: (912) 964–3000. 

FOR FURTHER INFORMATION CONTACT: 

Andy McAnaul, Aerospace Engineer, 

ASW–150, FAA San Antonio MIDO–43, 

10100 Reunion Place, Suite 650, San 

Antonio, Texas 78216, phone: (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–2008–0854; Directorate 

Identifier 2008–CE–050–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 

Excessive corrosion on the main 

tubular spar, part number A1203–11, of 

the rudder assembly resulting from 

moisture accumulating in the lower 

internal cavity on Allied Ag Cat 

Productions, Inc. (formerly GrummanAmerican) Models G–164, G–164A, and 

G–164B airplanes caused us to issue AD 

78–08–09, Amendment 39–3191. AD 

78–08–09 currently requires the 

following on certain Models G–164, 

G–164A, and G–164B airplanes: 

• Repetitively inspecting the rudder 

main tubular spar for corrosion; 

• Repairing any corrosion found; and 

• Applying corrosion protection. 

AD 78–08–09 applies only to early 

production Allied Ag Cat airplanes. In 

March 2008, the rudder main tubular 

spar failed on a Model G164B airplane, 

serial number 586B (not affected by AD 

78–08–09). The spar failed where the 

lower fitting is welded to the main tube. 

Investigation revealed that the failure 

was a result of severe internal corrosion 

caused by moisture trapped in the lower 

internal cavity of the spar tube. 

AD 78–08–09 does not establish a way 

to identify affected rudders. It is a 

common practice to repair agricultural 

airplanes with repaired or used 

serviceable parts from other sources, or 

using removed parts from other 

airplanes. Based on the lack of 

traceability, rudders affected by AD 78–

08–09 are potentially being installed on 


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Federal Register / Vol. 73, No. 153 / Thursday, August 7, 2008 / Proposed Rules 45901 

Allied Ag Cat model airplanes not 

affected by AD 78–08–09. Also, many 

rudders have been modified to ‘‘tall’’

rudders by supplemental type certificate 

(STC), or replaced with aftermarket 

rudders, which all have the same 

corrosion susceptible design as the 

original earlier production rudders. 

This condition, if not detected and 

corrected, could result in failure of the 

rudder main spar tubular spar. This 

failure could lead to loss of directional 

control. 

Relevant Service Information 

We have reviewed Grumman 

American Aviation Corporation Ag-Cat 

Service Bulletin No. 61, dated June 6, 

1977. 

The service information specifies: 

• Repetitively inspecting the main 

tubular spar for corrosion; 

• Repairing any corrosion found; and 

• Applying corrosion protection. 

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 78–08–09 with a new AD 

that would retain the actions required in 

AD 78–08–09 and expand the 

applicability to include all G–164 series 

airplanes. 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 2,700 airplanes in the U.S. 

registry. 

We estimate the following costs to do 

the proposed inspections: 

Labor cost Parts cost Total cost per 

airplane 

Total cost on 

U.S. operators 

4 work-hours × $80 per hour = $320 ........................... Not applicable ............................................................... $320 $864,000 

We have no way of determining the 

cost of repairs or parts replacement or 

the number of airplanes that may 

require repair or part replacement based 

on the result of the proposed 

inspections. 

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. 

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, 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) 

78–08–09, Amendment 39–3191, and 

adding the following new AD: 

Allied Ag Cat Productions, Inc.: Docket No. 

FAA–2008–0854; Directorate Identifier 

2008–CE–050–AD. 

Comments Due Date 

(a) We must receive comments on this 

airworthiness directive (AD) action by 

October 6, 2008. 

Affected ADs 

(b) This AD supersedes AD 78–08–09, 

Amendment 39–3191. 

Applicability 

(c) This AD applies to the following 

airplane models, all serial numbers, that are 

certificated in any category: 

Models 

G–164, G–164A, G–164B, G–164B with 73′′, G–164B–15T, G–164B–34T, G–164B–20T, G–164C, G–164D, and G–164D with 73′′ wing gap. 


rmajette on PRODPC74 with PROPOSALS
45902 Federal Register / Vol. 73, No. 153 / Thursday, August 7, 2008 / Proposed Rules 

Unsafe Condition 

(d) This AD results from a report of the 

rudder main tubular spar failing on a later 

production airplane. We are issuing this AD 

to detect and correct corrosion in the rudder 

main tubular spar, which could result in 

failure of the weld to the main spar tube. 

This failure could lead to loss of directional 

control. 

Compliance 

(e) To address this problem, you must do 

the following, unless already done: 

Actions Compliance Procedures 

(1) Drill an access hole and do a borescope 

visual inspection of the lower end internal 

cavity of the rudder main spar tube for corrosion and do a visual inspection of the exterior of the rudder main spar tube for corrosion.

(i) For airplanes previously affected by AD 

78–08–09: Initially inspect within the next 60 

months after the last inspection required in 

AD 78–08–09 or within the next 30 days 

after the effective date of this AD, whichever occurs later. Repetitively inspect thereafter at intervals not to exceed 60 calendar 

months.

Following Steps 1 through 3 of Grumman 

American Aviation Corporation Ag-Cat Service Bulletin No. 61, dated June 6, 1977. 

(ii) For airplanes not previously affected by AD 

78–08–09: Initially inspect within the next 30 

days after the effective date of this AD. Repetitively inspect thereafter at intervals not 

to exceed 60 calendar months.

(2) If corrosion is found during any inspection 

required in paragraph (e)(1) of this AD, repair in accordance with Advisory Circular 

43.13–1B or equivalent, or replace the damaged part(s).

Before further flight after any inspection in 

which corrosion is found.

As specified in Steps 5 and 6 of Grumman 

American Aviation Corporation Ag-Cat Service Bulletin No. 61, dated June 6, 1977. Following Advisory Circular 43.13–1B or equivalent, and an FAA-approved procedure. The 

appropriate maintenance manual contains 

these procedures. 

(3) After each inspection and repair or replacement required in this AD, corrosion protect 

the spar tube internal cavity by filling with 

warm, raw linseed oil, Paralketone, or CRC3 

(LPS Heavy Duty Rust Inhibitor Type 3), or 

suitable equivalent protector for alloy steel, 

and allow to drain. Seal access hole with 

Scotch caulking compound, or suitable silicone based sealant, or equivalent.

Before further flight after any inspection required in paragraph (e)(1) of this AD and 

after any repair or replacement required in 

paragraph (e)(2) of this AD.

As specified in Step 4 of Grumman American 

Aviation Corporation Ag-Cat Service Bulletin 

No. 61, dated June 6, 1977. 

(4) Verify rigging check of the rudder ................ Before further flight after any inspection required in paragraph (e)(1) of this AD and 

after any repair or replacement required in 

paragraph (e)(2) of this AD.

Following an FAA-approved procedure. The 

appropriate maintenance manual contains 

these procedures. 

(5) Only install a rudder that has been inspected as specified in paragraph (e)(1) of 

this AD, is free of corrosion, and has had the 

corrosion protection applied and sealed as 

specified in paragraph (e)(3) of this AD.

As of the next 30 days after the effective date 

of this AD.

Not applicable. 

Alternative Methods of Compliance 

(AMOCs) 

(f) The Manager, Fort Worth Airplane 

Certification Office, 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 Place, 

Suite 650, San Antonio, Texas 78216, phone: 

(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. 

(g) AMOCs approved for AD 78–08–09 are 

not approved for this AD. 

Related Information 

(h) To get copies of the service information 

referenced in this AD, contact Grumman 

American Aviation Corporation, P.O. Box 

2206, Savannah, Georgia 31402. 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 August 

1, 2008. 

James E. Jackson, 

Acting Manager, Small Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. E8–18228 Filed 8–6–08; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2007–27268; Directorate 

Identifier 2007–CE–025–AD] 

RIN 2120–AA64 

Airworthiness Directives; Cessna 

Aircraft Company (Type Certificate 

Previously Held by Columbia Aircraft 

Manufacturing) Models LC40–550FG, 

LC41–550FG, and LC42–550FG 

Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Notice of proposed rulemaking 

(NPRM). 

SUMMARY: We propose to revise 

Airworthiness Directive (AD) 2007–07–


rmajette on PRODPC74 with PROPOSALS