45898 Federal Register / Vol. 73, No. 153 / Thursday, August 7, 2008 / Proposed Rules 

Terminating Action for AWLs Revision 

(k) Incorporating AWL No. 28–AWL–22 

into the AWLs section of the ICA in 

accordance with paragraph (g)(3) of AD 

2008–10–11, amendment 39–15517, 

terminates the action in paragraph (h) of this 

AD. 

Alternative Methods of Compliance 

(AMOCs) 

(l)(1) The Manager, Seattle ACO, FAA, 

ATTN: Jen Pei, Aerospace Engineer, Systems 

and Equipment Branch, ANM–130S, FAA, 

Seattle ACO, 1601 Lind Avenue, SW., 

Renton, Washington 98057–3356; telephone 

(425) 917–6409; fax (425) 917–6590; has the 

authority to approve AMOCs for this AD, if 

requested using the procedures found in 14 

CFR 39.19. 

(2) To request a different method of 

compliance or a different compliance time 

for this AD, follow the procedures in 14 CFR 

39.19. Before using any approved AMOC on 

any airplane to which the AMOC applies, 

notify your appropriate principal inspector 

(PI) in the FAA Flight Standards District 

Office (FSDO), or lacking a PI, your local 

FSDO. 

Issued in Renton, Washington, on July 29, 

2008. 

Ali Bahrami, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. E8–18222 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–2008–0850; Directorate 

Identifier 2007–NM–342–AD] 

RIN 2120–AA64 

Airworthiness Directives; Fokker 

Model F.28 Mark 0100 Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Notice of proposed rulemaking 

(NPRM). 

SUMMARY: We propose to adopt a new 

airworthiness directive (AD) for the 

products listed above that would 

supersede an existing AD. This 

proposed AD results from mandatory 

continuing airworthiness information 

(MCAI) originated by an aviation 

authority of another country to identify 

and correct an unsafe condition on an 

aviation product. The MCAI describes 

the unsafe condition as: 

* * * * * 

During recent inspections it was found that 

some * * * bolts, that connect the horizontal 

stabilizer control unit actuator with the doglinks, were broken. This condition, if not 

corrected, could lead to [the loss of the flight 

control input connection to the horizontal 

stabilizer and consequent] partial loss of 

control of the aircraft. 

* * * * * 

The proposed AD would require actions 

that are intended to address the unsafe 

condition described in the MCAI. 

DATES: We must receive comments on 

this proposed AD by September 8, 2008. 

ADDRESSES: You may send comments by 

any of the following methods: 

• 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 

W12–40, 1200 New Jersey Avenue, SE., 

Washington, DC, between 9 a.m. and 5 

p.m., Monday through Friday, except 

Federal holidays. 

Examining the AD Docket 

You may examine the AD docket on 

the Internet at http:// 

www.regulations.gov; or in person at the 

Docket Operations office between 9 a.m. 

and 5 p.m., Monday through Friday, 

except Federal holidays. The AD docket 

contains this proposed AD, the 

regulatory evaluation, any comments 

received, and other information. The 

street address for the Docket Operations 

office (telephone (800) 647–5527) is in 

the ADDRESSES section. Comments will 

be available in the AD docket shortly 

after receipt. 

FOR FURTHER INFORMATION CONTACT: 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. 

SUPPLEMENTARY INFORMATION: 

Comments Invited 

We invite you to send any written 

relevant data, views, or arguments about 

this proposed AD. Send your comments 

to an address listed under the 

ADDRESSES section. Include ‘‘Docket No. 

FAA–2008–0850; Directorate Identifier 

2007–NM–342–AD’’ at the beginning of 

your comments. We specifically invite 

comments on the overall regulatory, 

economic, environmental, and energy 

aspects of this proposed AD. We will 

consider all comments received by the 

closing date and may amend this 

proposed AD based on 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 

about this proposed AD. 

Discussion 

On June 13, 1997, we issued AD 97–

13–05, Amendment 39–10051 (62 FR 

34617, June 27, 1997). That AD required 

actions intended to address an unsafe 

condition on the products listed above. 

Since we issued AD 97–13–05, we 

received reports of inspection results 

indicating that the bolt that connects the 

horizontal stabilizer control unit 

actuator with the dog-links was broken 

(one on the nut side, and one on the 

head side). When the bolts fails at the 

nut end, the remaining part of the bolt 

cannot drop out of the connection due 

to the limited amount of space available 

between the bolt head and plate, and the 

affected connection is still able to carry 

the system loads. However, if the head 

side of the bolt fails, then the bolt may 

drop out of the connection. 

The European Aviation Safety Agency 

(EASA), which is the Technical Agent 

for the Member States of the European 

Community, has issued EASA 

Airworthiness Directive 2007–0287, 

dated November 15, 2007 (referred to 

after this as ‘‘the MCAI’’), to correct an 

unsafe condition for the specified 

products. The MCAI states: 

In January 1996, Fokker issued Service 

Bulletin (SB) SBF–100–27–069 (referencing 

Menasco, now Goodrich, SB 23100–27–19) to 

introduce an inspection of bolt Part Number 

(P/N) 23233–1 for cracks after the 

examination of a failed bolt. This Service 

Bulletin was made mandatory by CAA–NL 

(Civil Aviation Authority—the Netherlands) 

with the issuance of AD BLA 1996–006 (A) 

[reference corresponding FAA AD 97–13–05]. 

Additionally the same SB introduced a lower 

torque value for these bolts. 

During recent inspections it was found that 

some of these bolts, that connect the 

horizontal stabilizer control unit actuator 

with the dog-links, were broken. This 

condition, if not corrected, could lead to [the 

loss of the flight control input connection to 

the horizontal stabilizer and consequent] 

partial loss of control of the aircraft. 

Since an unsafe condition has been 

identified that continues to exist or develop 

on other aircraft of the same type design, this 

Airworthiness Directive supersedes CAA–NL 

AD 1996–006 and requires an integrity check 

by a re-torque in accordance with SBF–100–

27–091 and the installation of a tie-wrap 

through the bolt, which will act as a retainer 

for the bolt and nut. The key function for this 

tie-wrap is to keep the bolt in place in the 

event the bolt head fails. 

The corrective action includes 

replacing any failed bolt (i.e., broken or 


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Federal Register / Vol. 73, No. 153 / Thursday, August 7, 2008 / Proposed Rules 45899 

loose bolt) with a serviceable bolt. This 

proposed AD also expands the 

applicability of AD 97–13–05. You may 

obtain further information by examining 

the MCAI in the AD docket. 

Relevant Service Information 

Fokker Services B.V. has issued 

Fokker Service Bulletin SBF–100–27–

091, dated August 31, 2007. The actions 

described in this service information are 

intended to correct the unsafe condition 

identified in the MCAI. 

FAA’s Determination and Requirements 

of This Proposed AD 

This product has been approved by 

the aviation authority of another 

country, and is approved for operation 

in the United States. Pursuant to our 

bilateral agreement with the State of 

Design Authority, we have been notified 

of the unsafe condition described in the 

MCAI and service information 

referenced above. We are proposing this 

AD because we evaluated all pertinent 

information and determined an unsafe 

condition exists and is likely to exist or 

develop on other products of the same 

type design. 

Differences Between This AD and the 

MCAI or Service Information 

We have reviewed the MCAI and 

related service information and, in 

general, agree with their substance. But 

we might have found it necessary to use 

different words from those in the MCAI 

to ensure the AD is clear for U.S. 

operators and is enforceable. In making 

these changes, we do not intend to differ 

substantively from the information 

provided in the MCAI and related 

service information. 

We might also have proposed 

different actions in this AD from those 

in the MCAI in order to follow FAA 

policies. Any such differences are 

highlighted in a Note within the 

proposed AD. 

Costs of Compliance 

Based on the service information, we 

estimate that this proposed AD would 

affect about 9 products of U.S. registry. 

We also estimate that it would take 

about 3 work-hours per product to 

comply with the basic requirements of 

this proposed AD. The average labor 

rate is $80 per work-hour. Based on 

these figures, we estimate the cost of the 

proposed AD on U.S. operators to be 

$2,160, or $240 per product. 

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 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 this 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. 

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 Amendment 39–10051 (62 FR 

34617, June 27, 1997) and adding the 

following new AD: 

Fokker Services B.V.: Docket No. FAA–

2008–0850; Directorate Identifier 2007–

NM–342–AD. 

Comments Due Date 

(a) We must receive comments by 

September 8, 2008. 

Affected ADs 

(b) The proposed AD supersedes AD 97–

13–05, Amendment 39–10051. 

Applicability 

(c) This AD applies to Fokker Model F.28 

Mark 0100 airplanes, certificated in any 

category, all serial numbers. 

Subject 

(d) Air Transport Association (ATA) of 

America Code 27: Flight Controls. 

Reason 

(e) The mandatory continuing 

airworthiness information (MCAI) states: 

In January 1996, Fokker issued Service 

Bulletin (SB) SBF–100–27–069 (referencing 

Menasco, now Goodrich, SB 23100–27–19) to 

introduce an inspection of bolt Part Number 

(P/N) 23233–1 for cracks after the 

examination of a failed bolt. This Service 

Bulletin was made mandatory by CAA–NL 

(Civil Aviation Authority—the Netherlands) 

with the issuance of AD BLA 1996–006 (A) 

[reference corresponding FAA AD 97–13–05]. 

Additionally the same SB introduced a lower 

torque value for these bolts. 

During recent inspections it was found that 

some of these bolts, that connect the 

horizontal stabilizer control unit actuator 

with the dog-links, were broken. This 

condition, if not corrected, could lead to [the 

loss of the flight control input connection to 

the horizontal stabilizer and consequent] 

partial loss of control of the aircraft. 

Since an unsafe condition has been 

identified that continues to exist or develop 

on other aircraft of the same type design, this 

Airworthiness Directive [European Aviation 

Safety Agency (EASA) Airworthiness 

Directive 2007–0287, dated November 15, 

2007] supersedes CAA–NL AD 1996–006 and 

requires an integrity check by a re-torque in 

accordance with SBF100–27–091 and the 

installation of a tie wrap through the bolt, 

which will act as a retainer for the bolt and 

nut. The key function for this tie-wrap is to 

keep the bolt in place in the event the bolt 

head fails. 

The corrective action includes replacing any 

failed bolt (i.e., broken or loose bolt) with a 

serviceable bolt. 

Actions and Compliance 

(f) Unless already done, within 6 months 

after the effective date of this AD, do the 

following actions. 

(1) Perform a one-time inspection (integrity 

check) for failure of the lower bolts of the 

stabilizer control unit dog-links, in 

accordance with the Accomplishment 

Instructions of Fokker Service Bulletin 

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

failed bolt is found, before further flight, 

replace the bolt with a serviceable bolt in 

accordance with the Accomplishment 

Instructions of the service bulletin. 


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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 


rmajette on PRODPC74 with PROPOSALS