58300 Federal Register / Vol. 70, No. 193 / Thursday, October 6, 2005 / Rules and Regulations 

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 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 AD and placed it in the AD docket. 

See the ADDRESSES section for a location 

to examine the regulatory evaluation. 

List of Subjects in 14 CFR Part 39 

Air transportation, Aircraft, Aviation 

safety, Incorporation by reference, 

Safety. 

Adoption of the Amendment 

■ Accordingly, under the authority 

delegated to me by the Administrator, 

the FAA amends 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 Federal Aviation 

Administration (FAA) amends § 39.13 

by adding the following new 

airworthiness directive (AD): 

2005–20–20 Airbus: Amendment 39–

14316. Docket No. FAA–2005–22587; 

Directorate Identifier 2003–NM–266–AD. 

Effective Date 

(a) This AD becomes effective October 21, 

2005. 

Affected ADs 

(b) None. 

Applicability 

(c) This AD applies to Airbus Model A330–

301, –321, –322, –341, and –342 airplanes; 

Model A340–211, –212, and –213 airplanes; 

and Model A340–311, –312, and –313 

airplanes; certificated in any category; as 

identified in Airbus Service Bulletin A330–

32–3167, dated August 12, 2003; and Airbus 

Service Bulletin A340–32–4206, dated 

August 12, 2003; as applicable. 

Unsafe Condition 

(d) This AD results from reports of tie bolts 

that were broken or missing from the main 

landing gear (MLG) wheel assembly; in some 

cases the wheels have ruptured and caused 

damage to other equipment in the adjacent 

area. We are issuing this AD to prevent 

damage to the wheel assembly and 

equipment in the area adjacent to the MLG 

and center landing gear (CLG), which could 

result in a decrease in braking function and 

possible runway over-run. 

Compliance 

(e) You are responsible for having the 

actions required by this AD performed within 

the compliance times specified, unless the 

actions have already been done. 

Modification and Reidentification 

(f) Within 12 months after the effective 

date of this AD, modify the MLG and CLG, 

as applicable, by installing lockplates on the 

wheel assembly. Do all actions in accordance 

with the Accomplishment Instructions of 

Airbus Service Bulletin A330–32–3167, 

dated August 12, 2003; or A340–32–4206, 

dated August, 12, 2003; as applicable. 

Note 1: The service bulletins referenced in 

paragraph (f) of this AD refer to GoodrichMessier Service Bulletin 3–1509–32–5, dated 

August 12, 2003; as an additional source of 

service information for installing the 

lockplates. 

Alternative Methods of Compliance 

(AMOCs) 

(g)(1) The Manager, International Branch, 

ANM–116, Transport Airplane Directorate, 

FAA, has the authority to approve AMOCs 

for this AD, if requested in accordance with 

the procedures found in 14 CFR 39.19. 

(2) Before using any AMOC approved in 

accordance with § 39.19 on any airplane to 

which the AMOC applies, notify the 

appropriate principal inspector in the FAA 

Flight Standards Certificate Holding District 

Office. 

Related Information 

(h) French airworthiness directives 2003–

392(B) and 2003–393(B), both dated October 

29, 2003, also address the subject of this AD. 

Material Incorporated by Reference 

(i) You must use Airbus Service Bulletin 

A330–32–3167, dated August 12, 2003; or 

Airbus Service Bulletin A340–32–4206, 

dated August 12, 2003; as applicable; to 

perform the actions that are required by this 

AD, unless the AD specifies otherwise. The 

Director of the Federal Register approved the 

incorporation by reference of these 

documents in accordance with 5 U.S.C. 

552(a) and 1 CFR part 51. Contact Airbus, 1 

Rond Point Maurice Bellonte, 31707 Blagnac 

Cedex, France, for a copy of this service 

information. You may review copies at the 

Docket Management Facility, U.S. 

Department of Transportation, 400 Seventh 

Street SW., room PL–401, Nassif Building, 

Washington, DC; on the Internet at http:// 

dms.dot.gov; or at the National Archives and 

Records Administration (NARA). For 

information on the availability of this 

material at the NARA, call (202) 741–6030, 

or go to http://www.archives.gov/

federal_register/code_of_federal_regulations/

ibr_locations.html. 

Issued in Renton, Washington, on 

September 26, 2005. 

Ali Bahrami, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 05–19830 Filed 10–5–05; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2005–22588; Directorate 

Identifier 2005–NM–096–AD; Amendment 

39–14317; AD 2005–20–21] 

RIN 2120–AA64 

Airworthiness Directives; Fokker 

Model F27 Mark 050 Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Final rule; request for 

comments. 

SUMMARY: The FAA is adopting a new 

airworthiness directive (AD) for certain 

Fokker Model F27 Mark 050 airplanes. 

This AD requires repetitive visual 

checks for oil leaks of both engines 

between the spinner and the engine 

cowling, and directly behind the heated 

intake lip of the engine; repetitive 

inspections for oil leaks at the feathering 

pump on both engines; and corrective 

actions if necessary. This AD results 

from reports of oil leakage at the engine 

feathering pump. We are issuing this AD 

to prevent oil loss from the feathering 

pump, which could cause the engine to 

shut down in flight. 

DATES: This AD becomes effective 

October 21, 2005. 

The Director of the Federal Register 

approved the incorporation by reference 

of certain publications listed in the AD 

as of October 21, 2005. 

We must receive comments on this 

AD by December 5, 2005. 

ADDRESSES: Use one of the following 

addresses to submit comments on this 

AD. 

• DOT Docket Web site: Go to 

http://dms.dot.gov and follow the 

instructions for sending your comments 

electronically. 

• Government-Wide Rulemaking Web 

Site: Go to http://www.regulations.gov 

and follow the instructions for sending 

your comments electronically. 

• Mail: Docket Management Facility; 

U.S. Department of Transportation, 400 

Seventh Street SW., Nassif Building, 

room PL–401, Washington, DC 20590. 

• Fax: (202) 493–2251. 

Federal Register / Vol. 70, No. 193 / Thursday, October 6, 2005 / Rules and Regulations 58301 

• Hand Delivery: Room PL–401 on 

the plaza level of the Nassif Building, 

400 Seventh Street SW., Washington, 

DC, between 9 a.m. and 5 p.m., Monday 

through Friday, except Federal holidays. 

Contact Fokker Services B.V., P.O. 

Box 231, 2150 AE Nieuw-Vennep, the 

Netherlands, for service information 

identified in this AD. 

FOR FURTHER INFORMATION CONTACT: Tom 

Rodriguez, Aerospace Engineer, 

International Branch, ANM–116, FAA, 

Transport Airplane Directorate, 1601 

Lind Avenue, SW., Renton, Washington 

98055–4056; telephone (425) 227–1137; 

fax (425) 227–1149. 

SUPPLEMENTARY INFORMATION: 

Discussion 

The Civil Aviation Authority—The 

Netherlands (CAA–NL), which is the 

airworthiness authority for the 

Netherlands, notified us that an unsafe 

condition may exist on certain Fokker 

Model F27 Mark 050 airplanes. The 

CAA–NL advises that a number of inflight engine shut-downs have been 

reported on Fokker Model F27 Mark 050 

airplanes. The shut-downs were caused 

by oil leakage at the engine feathering 

pump, which resulted from a damaged 

seal on one of the bobbins between the 

feathering pump and the engine 

reduction gearbox. The CAA–NL 

mandated several actions to prevent 

recurrence of the leakage. Since those 

actions were mandated, several 

operators have found oil leaks at the 

feathering pumps. Most of these leaks 

were discovered during pre-flight or 

overnight checks. Investigators have not 

identified the cause of the new leaks. 

Oil loss from the feathering pump, if not 

corrected, could cause the engine to 

shut down in flight. 

Relevant Service Information 

Fokker Services B.V. has issued All 

Operator Message (AOM) AOF50.037 

(Ref TS04.57535), dated November 2, 

2004. The AOM describes procedures 

for doing an external visual inspection 

for oil leaks before each take-off. The 

inspections are to be done in two 

specific areas of both engines: Between 

the spinner and the engine cowling, and 

directly behind the heated intake lip of 

the engine. The AOM states that either 

the flightcrew or the maintenance crew 

can perform this inspection. If any leak 

is found, the AOM specifies that further 

inspections are necessary before further 

flight, in accordance with the Fokker 

service bulletin described below. The 

AOM also states that operators should 

report cases of oil leakage and send 

failed O-rings to Fokker Services. 

Fokker Services B.V. has also issued 

Service Bulletin SBF50–61–023, dated 

November 3, 2004. The service bulletin 

describes procedures for repetitive 

detailed inspections for oil leaks at the 

feathering pump on both engines. If any 

leak is found, the service bulletin 

provides procedures for the corrective 

actions of replacing the O-rings of the 

feathering pump bobbins and the 

mounting pad gasket (if installed) with 

new parts. 

The CAA–NL mandated the service 

information and issued Dutch 

airworthiness directive 2004–129, dated 

November 3, 2004, to ensure the 

continued airworthiness of these 

airplanes in the Netherlands. 

FAA’s Determination and Requirements 

of This AD 

This airplane model is manufactured 

in the Netherlands and is type 

certificated for operation in the United 

States under the provisions of section 

21.29 of the Federal Aviation 

Regulations (14 CFR 21.29) and the 

applicable bilateral airworthiness 

agreement. Pursuant to this bilateral 

airworthiness agreement, the CAA–NL 

has kept the FAA informed of the 

situation described above. We have 

examined the CAA–NL’s findings, 

evaluated all pertinent information, and 

determined that we need to issue an AD 

for products of this type design that are 

certificated for operation in the United 

States. 

Therefore, we are issuing this AD to 

prevent oil loss from the feathering 

pump, which could cause the engine to 

shut down in flight. This AD requires 

accomplishing the actions specified in 

the service information described 

previously. 

Interim Action 

We consider this AD interim action. If 

final action is later identified, we may 

consider further rulemaking then. 

Clarification of Inspections 

Although the Dutch airworthiness 

directive specifies visually inspecting 

for oil leaks, this AD refers to that 

inspection as a ‘‘visual check.’’ We have 

determined that pilots may properly 

perform these visual checks because the 

checks do not require tools, precision 

measuring equipment, training, or pilot 

logbook endorsements, or the use of or 

reference to technical data that are not 

contained in the body of the AD. 

Costs of Compliance 

None of the airplanes affected by this 

action are on the U.S. Register. All 

airplanes affected by this AD are 

currently operated by non-U.S. 

operators under foreign registry; 

therefore, they are not directly affected 

by this AD action. However, we 

consider this AD necessary to ensure 

that the unsafe condition is addressed if 

any affected airplane is imported and 

placed on the U.S. Register in the future. 

The following table provides the 

estimated costs to comply with this AD 

for any affected airplane that might be 

imported and placed on the U.S. 

Register in the future. 

ESTIMATED COSTS

Action Work 

hours 

Average 

labor rate 

per hour 

Cost per airplane 

Pre-flight check, per cycle ........................................................................................................ 1 $65 $65, per cycle. 

Detailed inspection, per inspection cycle ................................................................................. 1 65 65, per inspection cycle. 

Changes to 14 CFR Part 39/Effect on the 

AD Relating to Special Flight Permits 

On July 10, 2002, we issued a new 

version of 14 CFR part 39 (67 FR 47997, 

July 22, 2002), which governs the FAA’s 

airworthiness directives system. The 

regulation now includes material that 

relates to altered products, special flight 

permits, and alternative methods of 

compliance (AMOC). This material is 

included in part 39, except that the 

office authorized to approve AMOCs is 

identified in each individual AD. 

However, as amended, part 39 provides 

for the FAA to add special requirements 

for operating an airplane to a repair 

facility to do the work required by an 

airworthiness directive. For purposes of 

this AD, we have determined that such 

a special flight permit is prohibited. 

58302 Federal Register / Vol. 70, No. 193 / Thursday, October 6, 2005 / Rules and Regulations 

FAA’s Determination of the Effective 

Date 

No airplane affected by this AD is 

currently on the U.S. Register. 

Therefore, providing notice and 

opportunity for public comment is 

unnecessary before this AD is issued, 

and this AD may be made effective in 

less than 30 days after it is published in 

the Federal Register. 

Comments Invited 

This AD is a final rule that involves 

requirements that affect flight safety and 

was not preceded by notice and an 

opportunity for public comment; 

however, we invite you to submit any 

relevant written data, views, or 

arguments regarding this AD. Send your 

comments to an address listed in the 

ADDRESSES section. Include ‘‘Docket No. 

FAA–2005–22588; Directorate Identifier 

2005–NM–096–AD’’ at the beginning of 

your comments. We specifically invite 

comments on the overall regulatory, 

economic, environmental, and energy 

aspects of the AD that might suggest a 

need to modify it. 

We will post all comments we 

receive, without change, to http:// 

dms.dot.gov, including any personal 

information you provide. We will also 

post a report summarizing each 

substantive verbal contact with FAA 

personnel concerning this AD. Using the 

search function of that Web site, anyone 

can find and read the comments in any 

of our dockets, including the name of 

the individual who sent the comment 

(or signed the comment on behalf of an 

association, business, labor union, etc.). 

You may review the DOT’s complete 

Privacy Act Statement in the Federal 

Register published on April 11, 2000 

(65 FR 19477–78), or you may visit 

http://dms.dot.gov. 

Examining the Docket 

You may examine the AD docket on 

the Internet at http://dms.dot.gov, or in 

person at the Docket Management 

Facility office between 9 a.m. and 5 

p.m., Monday through Friday, except 

Federal holidays. The Docket 

Management Facility office (telephone 

(800) 647–5227) is located on the plaza 

level of the Nassif Building at the DOT 

street address stated in the ADDRESSES

section. Comments will be available in 

the AD docket shortly after the Docket 

Management System receives them. 

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 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 the 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 AD and placed it in the AD docket. 

See the ADDRESSES section for a location 

to examine the regulatory evaluation. 

List of Subjects in 14 CFR Part 39 

Air transportation, Aircraft, Aviation 

safety, Incorporation by reference, 

Safety. 

Adoption of the Amendment 

■ Accordingly, under the authority 

delegated to me by the Administrator, 

the FAA amends 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 Federal Aviation 

Administration (FAA) amends § 39.13 

by adding the following new 

airworthiness directive (AD): 

2005–20–21 Fokker Services B.V.: 

Amendment 39–14317. Docket No. 

FAA–2005–22588; Directorate Identifier 

2005–NM–096–AD. 

Effective Date 

(a) This AD becomes effective October 21, 

2005. 

Affected ADs 

(b) None. 

Applicability 

(c) This AD applies to Fokker Model F27 

Mark 050 airplanes, certificated in any 

category, as identified in Fokker Service 

Bulletin SBF50–61–023, dated November 3, 

2004. 

Unsafe Condition 

(d) This AD results from reports of oil 

leakage at the engine feathering pump. We 

are issuing this AD to prevent oil loss from 

the feathering pump, which could cause the 

engine to shut down in flight. 

Compliance 

(e) You are responsible for having the 

actions required by this AD performed within 

the compliance times specified, unless the 

actions have already been done. 

Pre-Flight Checks 

(f) Before the next flight after the effective 

date of this AD: Do a visual check for oil 

leaks between the spinner and the engine 

cowling, and from directly behind the heated 

intake lip, of both engines, in accordance 

with Fokker All Operator Message (AOM) 

AOF50.037 (Ref TS04.57535), dated 

November 2, 2004. Repeat the visual check 

thereafter before each flight. If any leak is 

found, before further flight, do the action in 

paragraph (g) of this AD. 

Repetitive Detailed Inspections 

(g) Except as required by paragraph (f) of 

this AD, at the applicable time in paragraph 

(g)(1) or (g)(2) of this AD: Do a detailed 

inspection for oil leaks at the feathering 

pump on both engines and do any applicable 

corrective action before further flight. Do all 

actions in accordance with the 

Accomplishment Instructions of Fokker 

Service Bulletin SBF50–61–023, dated 

November 3, 2004. Repeat the detailed 

inspection thereafter at the applicable 

interval in paragraph (g)(1) or (g)(2) of this 

AD. 

(1) For airplanes identified in paragraph 

1.A. ‘‘Effectivity,’’ sub-paragraph (1) of the 

service bulletin: Do the first inspection before 

the next flight after the effective date of this 

AD, and repeat the inspection thereafter 

before each flight. 

(2) For airplanes identified in paragraph 

1.A. ‘‘Effectivity,’’ sub-paragraph (2) of the 

service bulletin: Do the first inspection 

within 32 flight hours after the effective date 

of this AD, and repeat the inspection 

thereafter at intervals not to exceed 32 flight 

hours. 

Note 1: For the purposes of this AD, a 

detailed inspection is: ‘‘An intensive 

examination of a specific item, installation, 

or assembly to detect damage, failure, or 

irregularity. Available lighting is normally 

Federal Register / Vol. 70, No. 193 / Thursday, October 6, 2005 / Rules and Regulations 58303 

supplemented with a direct source of good 

lighting at an intensity deemed appropriate. 

Inspection aids such as mirror, magnifying 

lenses, etc., may be necessary. Surface 

cleaning and elaborate procedures may be 

required.’’

No Reporting Requirement 

(h) Although Fokker AOM AOF50.037 (Ref 

TS04.57535), dated November 2, 2004, 

specifies that operators should report cases of 

oil leakage and send failed O-rings to Fokker 

Services B.V., this AD does not include that 

requirement. 

Special Flight Permit 

(i) Special flight permits (14 CFR 21.197 

and 21.199) are not allowed. 

Alternative Methods of Compliance 

(AMOCs) 

(j)(1) The Manager, International Branch, 

ANM–116, Transport Airplane Directorate, 

FAA, has the authority to approve AMOCs 

for this AD, if requested in accordance with 

the procedures found in 14 CFR 39.19. 

(2) Before using any AMOC approved in 

accordance with § 39.19 on any airplane to 

which the AMOC applies, notify the 

appropriate principal inspector in the FAA 

Flight Standards Certificate Holding District 

Office. 

Related Information 

(k) Dutch airworthiness directive 2004–

129, dated November 3, 2004, also addresses 

the subject of this AD. 

Material Incorporated by Reference 

(l) You must use Fokker All Operator 

Message AOF50.037 (Ref TS04.57535), dated 

November 2, 2004; and Fokker Service 

Bulletin SBF50–61–023, dated November 3, 

2004; as applicable, to perform the actions 

that are required by this AD, unless the AD 

specifies otherwise. (Only page 1 of Fokker 

All Operator Message AOF50.037 (Ref 

TS04.57535), contains the issue date of the 

document; no other page of the document 

contains this information.) The Director of 

the Federal Register approved the 

incorporation by reference of these 

documents in accordance with 5 U.S.C. 

552(a) and 1 CFR part 51. Contact Fokker 

Services B.V., P.O. Box 231, 2150 AE NieuwVennep, the Netherlands, for a copy of this 

service information. You may review copies 

at the Docket Management Facility, U.S. 

Department of Transportation, 400 Seventh 

Street SW., room PL–401, Nassif Building, 

Washington, DC; on the Internet at http:// 

dms.dot.gov; or at the National Archives and 

Records Administration (NARA). For 

information on the availability of this 

material at the NARA, call (202) 741–6030, 

or go to http://www.archives.gov/ 

federal_register/code_of_federal_regulations/ 

ibr_locations.html. 

Issued in Renton, Washington, on 

September 26, 2005. 

Ali Bahrami, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 05–19829 Filed 10–5–05; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2005–22032; Directorate 

Identifier 2005–NM–049–AD; Amendment 

39–14308; AD 2005–20–14] 

RIN 2120–AA64 

Airworthiness Directives; Airbus Model 

A300 B4–620, A310–304, A310–324, 

and A310–325 Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Final rule. 

SUMMARY: The FAA is adopting a new 

airworthiness directive (AD) for certain 

Airbus Model A300 B4–620, A310–304, 

A310–324, and A310–325 airplanes. 

This AD requires installing fused 

adaptors between the external wiring 

harness and the in-tank wiring at the 

connectors on the fuel tank wall of the 

auxiliary center tank (ACT). This AD 

results from fuel system reviews 

conducted by the manufacturer. We are 

issuing this AD to prevent an ignition 

source in the ACT, which, in 

combination with flammable fuel 

vapors, could result in a fuel tank 

explosion and consequent loss of the 

airplane. 

DATES: This AD becomes effective 

November 10, 2005. 

The Director of the Federal Register 

approved the incorporation by reference 

of certain publications listed in the AD 

as of November 10, 2005. 

ADDRESSES: You may examine the AD 

docket on the Internet at http:// 

dms.dot.gov or in person at the Docket 

Management Facility, U.S. Department 

of Transportation, 400 Seventh Street 

SW., Nassif Building, room PL–401, 

Washington, DC. 

Contact Airbus, 1 Rond Point Maurice 

Bellonte, 31707 Blagnac Cedex, France, 

for service information identified in this 

AD. 

FOR FURTHER INFORMATION CONTACT: Tim 

Backman, Aerospace Engineer, 

International Branch, ANM–116, FAA, 

Transport Airplane Directorate, 1601 

Lind Avenue, SW., Renton, Washington 

98055–4056; telephone (425) 227–2797; 

fax (425) 227–1149. 

SUPPLEMENTARY INFORMATION: 

Examining the Docket 

You may examine the airworthiness 

directive (AD) docket on the Internet at 

http://dms.dot.gov or in person at the 

Docket Management Facility office 

between 9 a.m. and 5 p.m., Monday 

through Friday, except Federal holidays. 

The Docket Management Facility office 

(telephone (800) 647–5227) is located on 

the plaza level of the Nassif Building at 

the street address stated in the 

ADDRESSES section. 

Discussion 

The FAA issued a notice of proposed 

rulemaking (NPRM) to amend 14 CFR 

part 39 to include an AD that would 

apply to certain Airbus Model A300 B4–

620, A310–304, A310–324, and A310–

325 airplanes. That NPRM was 

published in the Federal Register on 

August 8, 2005 (70 FR 45587). That 

NPRM proposed to require installing 

fused adaptors between the external 

wiring harness and the in-tank wiring at 

the connectors on the fuel tank wall of 

the auxiliary center tank (ACT). 

Comments 

We provided the public the 

opportunity to participate in the 

development of this AD. We received no 

comments on the NPRM or on the 

determination of the cost to the public. 

Clarification of Alternative Method of 

Compliance (AMOC) Paragraph 

We have revised this AD to clarify the 

appropriate procedure for notifying the 

principal inspector before using any 

approved AMOC on any airplane to 

which the AMOC applies. 

Conclusion 

We have carefully reviewed the 

available data and determined that air 

safety and the public interest require 

adopting the AD with the change 

described previously. We have 

determined that this change will neither 

increase the economic burden on any 

operator nor increase the scope of the 

AD. 

Costs of Compliance 

This AD affects about 2 airplanes of 

U.S. registry. The actions take about 52 

work hours per airplane, at an average 

labor rate of $65 per work hour. 

Required parts cost about $5,410 per 

ACT (up to two ACTs per airplane). 

Based on these figures, the estimated 

cost of the AD for U.S. operators is 

$8,790 per ACT, per airplane. 

Currently, there are no Model A300 

B4–620 airplanes of U.S. registry with 

one or more ACTs. However, if an 

affected airplane is imported and placed 

on the U.S. Register in the future, the 

required actions would take about 52 

work hours, at an average labor rate of 

$65 per work hour. Required parts 

would cost about $10,730 per ACT, per 

airplane. Based on these figures, we