54668 Federal Register / Vol. 70, No. 179 / Friday, September 16, 2005 / Proposed Rules 

Egg white lysozyme (CAS # 9001–63–

2) 

* * * * * 

L-Malic acid (CAS # 97–67–6). 

* * * * * 

Microorganisms—any food grade 

bacteria, fungi, and other 

microorganism. 

* * * * * 

(b) * * * 

Activated charcoal (CAS #s 7440–44–

0; 64365–11–3)—only from vegetative 

sources; for use only as a filtering aid in 

handling agricultural products labeled 

‘‘made with organic (specified 

ingredients or food group(s));’’

prohibited in handling agricultural 

products labeled ‘‘organic.’’

* * * * * 

Ammonium hydroxide (CAS # 1336–

21–6)—for use only as a boiler water 

additive until October 21, 2005. 

Restricted to handling agricultural 

products labeled ‘‘made with organic 

(specified ingredients or food 

group(s));’’ prohibited in handling 

agricultural products labeled ‘‘organic.’’

* * * * * 

Cyclohexylamine (CAS # 108–91–8)—

for use only as a boiler water additive 

for packaging sterilization. Restricted to 

handling agricultural products labeled 

‘‘made with organic (specified 

ingredients or food group(s));’’

prohibited in handling agricultural 

products labeled ‘‘organic.’’

Diethylaminoethanol (CAS # 100–37–

8)—for use only as a boiler water 

additive for packaging sterilization. 

Restricted to handling agricultural 

products labeled ‘‘made with organic 

(specified ingredients or food 

group(s));’’ prohibited for use in 

handling agricultural products labeled 

‘‘organic.’’

* * * * * 

Octadecylamine (CAS # 124–30–1)—

for use only as a boiler water additive 

for packaging sterilization. Restricted to 

handling agricultural products labeled 

‘‘made with organic (specified 

ingredients or food group(s));’’

prohibited for use in handling 

agricultural products labeled ‘‘organic.’’

* * * * * 

Peracetic acid/Peroxyacetic acid (CAS 

# 79–21–0)—for use in wash and/or 

rinse water according to FDA 

limitations. For use as a sanitizer on 

food contact surfaces. Restricted to use 

in handling agricultural products 

labeled ‘‘made with organic (specified 

ingredients or food group(s));’’

prohibited in handling agricultural 

products labeled ‘‘organic.’’

* * * * * 

Sodium acid pyrophosphate (CAS # 

7758–16–9)—for use only as a leavening 

agent in agricultural products labeled 

‘‘made with organic (specified 

ingredients or food group(s));’’

prohibited in handling agricultural 

products labeled ‘‘organic.’’

* * * * * 

Tetrasodium pyrophosphate (CAS # 

7722–88–5)—for use only in meat 

analog products labeled ‘‘made with 

organic (specified ingredients or food 

group(s));’’ prohibited in handling 

agricultural products labeled ‘‘organic.’’

* * * * * 

4. In § 205.681, paragraph (d)(1) is 

revised to read as follows: 

§ 205.681 Appeals. 

* * * * * 

(d) * * * (1) Appeals to the 

Administrator must be filed in writing 

and addressed to: Administrator, USDA, 

AMS, c/o NOP Appeals Staff, Stop 0203, 

Room 3529–S, 1400 Independence 

Avenue, SW., Washington, DC 20250–

0203 

* * * * * 

Dated: September 12, 2005. 

Lloyd C. Day, 

Administrator, Agricultural Marketing 

Service. 

[FR Doc. 05–18381 Filed 9–15–05; 8:45 am] 

BILLING CODE 3410–02–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2005–22423; Directorate 

Identifier 2005–NM–068–AD] 

RIN 2120–AA64 

Airworthiness Directives; Boeing 

Model 747–200C and –200F Series 

Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Notice of proposed rulemaking 

(NPRM). 

SUMMARY: The FAA proposes to 

supersede an existing airworthiness 

directive (AD) that applies to certain 

Boeing Model 747–200C and –200F 

series airplanes. The existing AD 

currently requires repetitive inspections 

to find fatigue cracking in the upper 

chord of the upper deck floor beams, 

and repair if necessary. For certain 

airplanes, the existing AD also provides 

an optional repair/modification, which 

extends certain repetitive inspection 

intervals. This proposed AD would 

reduce the compliance time for all 

initial inspections and reduce the 

repetitive interval for a certain 

inspection. This proposed AD is 

prompted by new reports of cracks in 

the upper deck floor beams occurring at 

lower flight cycles. We are proposing 

this AD to find and fix cracking in 

certain upper deck floor beams. Such 

cracking could extend and sever floor 

beams at a floor panel attachment hole 

location and could result in rapid 

decompression and loss of 

controllability of the airplane. 

DATES: We must receive comments on 

this proposed AD by October 31, 2005. 

ADDRESSES: Use one of the following 

addresses to submit comments on this 

proposed 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. 

• 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. 

For service information identified in 

this proposed AD, contact Boeing 

Commercial Airplanes, P.O. Box 3707, 

Seattle, Washington 98124–2207. 

You can examine the contents of this 

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., room PL–401, on the plaza level of 

the Nassif Building, Washington, DC. 

This docket number is FAA–2005–

22423; the directorate identifier for this 

docket is 2005–NM–068–AD. 

FOR FURTHER INFORMATION CONTACT: Ivan 

Li, Aerospace Engineer, Airframe 

Branch, ANM–120S, FAA, Seattle 

Aircraft Certification Office, 1601 Lind 

Avenue, SW., Renton, Washington 

98055–4056; telephone (425) 917–6437; 

fax (425) 917–6590. 

SUPPLEMENTARY INFORMATION: 

Comments Invited 

We invite you to submit any relevant 

written data, views, or arguments 

regarding this proposed AD. Send your 

comments to an address listed under 

ADDRESSES. Include ‘‘Docket No. FAA–

2005–22423; Directorate Identifier 

2005–NM–068–AD’’ at the beginning of 

your comments. We specifically invite 

Federal Register / Vol. 70, No. 179 / Friday, September 16, 2005 / Proposed Rules 54669 

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:// 

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 proposed AD. 

Using the search function of our docket 

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 can 

review the DOT’s complete Privacy Act 

Statement in the Federal Register 

published on April 11, 2000 (65 FR 

19477–78), or you can visit http:// 

dms.dot.gov. 

Examining the Docket 

You can 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 (DMS) receives 

them. 

Discussion 

On January 29, 2004, we issued AD 

2004–03–11, amendment 39–13455 (69 

FR 5920, February 9, 2004), for certain 

Boeing Model 747–200C and –200F 

series airplanes. That AD requires 

repetitive inspections to find fatigue 

cracking in the upper chord of certain 

upper deck floor beams, and repair if 

necessary. For certain airplanes, that AD 

also provides an optional repair/ 

modification, which extends certain 

repetitive inspection intervals. That AD 

was prompted by a report of fatigue 

cracking of the station (STA) 340 upper 

deck floor beam. We issued that AD to 

find and fix cracking in certain upper 

deck floor beams. Such cracking could 

extend and sever floor beams at a floor 

panel attachment hole location and 

could result in rapid decompression and 

loss of controllability of the airplane. 

Actions Since Existing AD Was Issued 

Since we issued AD 2004–03–11, we 

have received new reports of cracks in 

the upper deck floor beams on several 

airplanes. The airplanes had 

accumulated between 19,580 and 23,561 

total flight cycles. In one case, the aft 

reinforcing strap of the upper chord of 

the floor beam at station 520 was found 

severed at 19,580 total flight cycles. 

Another airplane with 19,687 total flight 

cycles had significant cracks in the same 

area. The threshold for the initial 

inspection required by AD 2004–03–11 

is 22,000 total flight cycles. Therefore, 

we have determined that the initial 

inspections and a certain repetitive 

inspection required by that AD need to 

be done earlier to detect cracks in the 

upper deck floor beams in a timely 

manner. 

Relevant Service Information 

We have reviewed Revision 1 of 

Boeing Alert Service Bulletin 747–

53A2439, dated March 10, 2005. The 

inspections, repair, and optional repair/ 

modification described in Revision 1 are 

essentially identical to those in the 

original issue, which is referenced in 

AD 2004–03–11 as the appropriate 

source of service information for the 

required actions. Revision 1 reduces the 

compliance time for all initial 

inspections and reduces the repetitive 

inspection interval for surface high 

frequency eddy current (HFEC) 

inspection of the upper deck floor 

beams (header beams) at STAs 440 and 

520. The compliance time for 

accomplishing the inspection of 

repaired areas ranges between 5,000 and 

15,000 flight cycles depending on the 

diameter of the fastener hole. 

Accomplishing the actions specified in 

the service information is intended to 

adequately address the unsafe 

condition. 

FAA’s Determination and Requirements 

of the Proposed AD 

The unsafe condition described 

previously is likely to exist or develop 

on other airplanes of the same type 

design that may be registered in the U.S. 

at some time in the future. We are 

proposing to supersede AD 2004–03–11. 

This proposed AD would continue to 

require repetitive inspections to find 

fatigue cracking in the upper chord of 

the upper deck floor beams, and repair 

if necessary. This proposed AD would 

also continue to provide, for certain 

airplanes, an optional repair/ 

modification, which extends certain 

repetitive inspection intervals. This 

proposed AD would also reduce the 

compliance time for all initial 

inspections and reduce the repetitive 

interval for a certain inspection. The 

actions would be required to be 

accomplished in accordance with the 

service bulletin described previously, 

except as discussed under ‘‘Differences 

Between the Proposed AD and Service 

Bulletin.’’

Differences Between the Proposed AD 

and Service Bulletin 

The service bulletin provides the 

following information in Note 9 of the 

Accomplishment Instructions: ‘‘For the 

purposes of this service bulletin, do not 

count flight-cycles with a cabin pressure 

differential of 2.0 psi or less. However, 

any flight-cycle with momentary spikes 

in cabin pressure differential above 2.0 

psi must be included as a full-pressure 

flight-cycle.’’ We have determined that 

an adjustment of flight cycles due to a 

lower cabin differential pressure is not 

substantiated and will not be allowed 

for use in determining the flight cycle 

threshold for this proposed AD. 

The service bulletin specifies that you 

may contact the manufacturer for 

instructions on how to repair certain 

conditions, but this proposed AD would 

require you to repair those conditions in 

one of the following ways: 

• Using a method that we approve; or 

• Using data that meet the 

certification basis of the airplane, and 

that have been approved by an 

Authorized Representative for the 

Boeing Delegation Option Authorization 

Organization whom we have authorized 

to make those findings. 

Although the Accomplishment 

Instructions of the service bulletin 

describe procedures for submitting 

inspection results to Boeing, this 

proposed AD would not require that 

action. We do not need this information 

from operators. 

Change to Existing AD 

This proposed AD would retain 

certain requirements of AD 2004–03–11. 

Since AD 2004–03–11 was issued, the 

AD format has been revised, and certain 

paragraphs have been rearranged. As a 

result, the corresponding paragraph 

identifiers have changed in this 

proposed AD, as listed in the following 

table: 

REVISED PARAGRAPH IDENTIFIERS

Requirement in AD 

2004–03–11 

Corresponding 

requirement in 

this proposed AD 

Paragraph (a) ......... Paragraphs (f) and (g). 

Paragraph (b) ......... Paragraph (h). 

Costs of Compliance 

There are about 78 airplanes of the 

affected design in the worldwide fleet. 

This proposed AD would affect about 21 

airplanes of U.S. registry. 

54670 Federal Register / Vol. 70, No. 179 / Friday, September 16, 2005 / Proposed Rules 

The inspections that are required by 

AD 2004–03–11 and retained in this 

proposed AD take about 29 work hours 

per airplane, at an average labor rate of 

$65 per work hour. Based on these 

figures, the estimated cost of the 

currently required inspections for U.S. 

airplanes is $39,585, or $1,885 per 

airplane, per inspection cycle. 

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. 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, 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 39–13455 (69 FR 

5920, February 9, 2004) and adding the 

following new airworthiness directive 

(AD): 

Boeing: Docket No. FAA–2005–22423; 

Directorate Identifier 2005–NM–068–AD. 

Comments Due Date 

(a) The Federal Aviation Administration 

must receive comments on this AD action by 

October 31, 2005. 

Affected ADs 

(b) This AD supersedes AD 2004–03–11, 

amendment 39–13455. 

Applicability 

(c) This AD applies to Boeing Model 747–

200C and –200F series airplanes, certificated 

in any category, as listed in Boeing Alert 

Service Bulletin 747–53A2439, dated July 5, 

2001. 

Unsafe Condition 

(d) This AD was prompted by new reports 

of cracks in the upper deck floor beams 

occurring at lower flight cycles. We are 

issuing this AD to find and fix cracking in 

certain upper deck floor beams, which could 

extend and sever floor beams at a floor panel 

attachment hole location and could result in 

rapid decompression and loss of 

controllability of the airplane. 

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. 

Requirements of AD 2004–03–11 

Initial Compliance Time at a New Reduced 

Threshold 

(f) At the earliest of the times specified in 

paragraphs (f)(1) through (f)(3) of this AD, do 

the inspection required by paragraph (g) of 

this AD. 

(1) Before the accumulation of 22,000 total 

flight cycles, or within 1,000 flight cycles 

after March 15, 2004 (the effective date of AD 

2004–03–11), whichever occurs later. 

(2) For airplanes with 17,000 or more total 

flight cycles as of the effective date of this 

AD: Before the accumulation of 18,000 total 

flight cycles, or within 90 days after the 

effective date of this AD, whichever occurs 

later. 

(3) For airplanes with fewer than 17,000 

total flight cycles as of the effective date of 

this AD: Before the accumulation of 15,000 

total flight cycles, or within 1,000 flight 

cycles after the effective date of this AD, 

whichever occurs later. 

Inspections at Reduced Intervals for Certain 

Floor Beams and Repair 

(g) Do the applicable inspection to find 

fatigue cracking in the upper chord of the 

upper deck floor beams as specified in Part 

1 (Open-Hole High Frequency Eddy Current 

(HFEC) Inspection Method) or Part 2 (Surface 

HFEC Inspection Method) of the Work 

Instructions of Boeing Alert Service Bulletin 

747–53A2439, dated July 5, 2001. Do the 

inspections per the service bulletin. As of the 

effective date of this AD, the actions must be 

done per the Work Instructions of Boeing 

Alert Service Bulletin 747–53A2439, 

Revision 1, dated March 10, 2005. 

(1) If any crack is found, before further 

flight, repair per Part 3 (Upper Chord Repair) 

of the Work Instructions of the service 

bulletin; except where the service bulletin 

specifies to contact Boeing for appropriate 

action, before further flight, repair according 

to a method approved by the Manager, 

Seattle Aircraft Certification Office (ACO), 

FAA; or according to data meeting the 

certification basis of the airplane approved 

by an a Boeing Company Designated 

Engineering Representative (DER) or 

Authorized Representative for the Boeing 

Delegation Option Authorization 

Organization who has been authorized by the 

Manager, Seattle ACO, to make such 

findings. For a repair method to be approved 

by the Manager, Seattle ACO, as required by 

this paragraph, the Manager’s approval letter 

must specifically reference this AD. Do the 

applicable inspection of the repaired area per 

Part 1 of the Work Instructions of the service 

bulletin at the applicable time per Part 3 of 

the Work Instructions of the service bulletin, 

and repeat the applicable inspection at the 

applicable interval per Figure 1 of the service 

bulletin. As of the effective date of this AD, 

do the applicable inspection of the repaired 

area per Parts 1 and 6 of the Work 

Instructions of the service bulletin at the 

applicable time per Table 1 of Part 3 of the 

Work Instructions of the service bulletin, and 

repeat the applicable inspection thereafter at 

intervals not to exceed 3,000 flight cycles. 

(2) If no crack is found, repeat the 

applicable inspection per paragraph (g) of 

this AD at the applicable time specified in 

paragraphs (g)(2)(i) through (g)(2)(iii) of this 

AD. As an option, accomplishment of 

paragraph (h)(1) or (h)(2) of this AD, before 

further flight, extends the threshold for the 

initiation of the repetitive inspections 

required by this paragraph. 

(i) If the open-hole HFEC inspection 

method was used: Repeat that inspection at 

intervals not to exceed 3,000 flight cycles. 

(ii) If the surface HFEC inspection method 

was used at stations 340 through 420 

inclusive and station 500: Repeat that 

inspection at intervals not to exceed 750 

flight cycles. 

(iii) If the surface HFEC inspection method 

was used at stations 440 and 520: Repeat that 

inspection at the earlier of the times specified 

in paragraphs (g)(2)(iii)(A) and (g)(2)(iii)(B) of 

this AD, and thereafter at intervals not to 

exceed 250 flight cycles. 

Federal Register / Vol. 70, No. 179 / Friday, September 16, 2005 / Proposed Rules 54671 

(A) Within 750 flight cycles since the last 

surface HFEC inspection required by 

paragraph (g) of this AD. 

(B) Within 250 flight cycles after the 

effective date of this AD. 

Optional Repair/Modification 

(h) For airplanes on which the inspection 

required by paragraph (g) of this AD is done 

per Part 1 of the Work Instructions of Boeing 

Alert Service Bulletin 747–53A2439, dated 

July 5, 2001, or Revision 1, dated March 10, 

2005; and on which no cracking is found: 

Accomplishment of the actions specified in 

either paragraph (h)(1) or (h)(2) of this AD 

extends the threshold for the initiation of the 

repetitive inspections required by paragraph 

(g)(2) of this AD. For airplanes on which the 

inspection required by paragraph (g) of this 

AD is done per Part 2 of the Work 

Instructions of Boeing Alert Service Bulletin 

747–53A2439, dated July 5, 2001, or Revision 

1, dated March 10, 2005; and on which no 

cracking is found: Accomplishment of the 

actions specified in paragraph (h)(1) of this 

AD extends the threshold for the initiation of 

the repetitive inspections required by 

paragraph (g)(2) of this AD. 

(1) Do the applicable repair per Part 3 of 

the Work Instructions of the service bulletin. 

At the applicable time specified in Table 1 

of Part 3 of the Work Instructions of the 

service bulletin, do the applicable inspection 

of the repaired area per Part 1 of the Work 

Instructions of the service bulletin. Repeat 

the inspection thereafter within the 

applicable interval per Figure 1 of the service 

bulletin. As of the effective date of this AD, 

the actions must be done per Parts 1, 3, and 

6 of the Work Instructions of Boeing Alert 

Service Bulletin 747–53A2439, Revision 1, 

dated March 10, 2005, as applicable, and 

repeat the applicable inspection thereafter at 

intervals not to exceed 3,000 flight cycles. 

(2) Do the modification of the attachment 

hole of the floor panel per Figure 5 of the 

service bulletin. Within 10,000 flight cycles 

after accomplishment of the modification, do 

the inspection of the modified area per Part 

1 of the Work Instructions of the service 

bulletin. Repeat the inspection thereafter 

within the applicable interval per Figure 1 of 

the service bulletin. As of the effective date 

of this AD, the actions must be done per 

Figure 5 and Part 1 of the Work Instructions 

of Boeing Alert Service Bulletin 747–

53A2439, Revision 1, dated March 10, 2005, 

and repeat the inspection thereafter at 

intervals not to exceed 3,000 flight cycles. 

Determining the Number of Flight Cycles for 

Compliance Time 

(i) For the purposes of calculating the 

compliance threshold and repetitive intervals 

for actions required by paragraphs (f), (g), or 

(h) of this AD: As of the effective date of this 

AD, all flight cycles, including the number of 

flight cycles in which cabin differential 

pressure is at 2.0 pounds per square inch 

(psi) or less, must be counted when 

determining the number of flight cycles that 

have occurred on the airplane. 

No Reporting Requirement 

(j) Although the service bulletin referenced 

in this AD specifies to submit certain 

information to the manufacturer, this AD 

does not include that requirement. 

Alternative Methods of Compliance (AMOCs) 

(k)(1) The Manager, Seattle Aircraft 

Certification Office (SACO), FAA, has the 

authority to approve AMOCs for this AD, if 

requested in accordance with the procedures 

found in 14 CFR 39.19. 

(2) An AMOC that provides an acceptable 

level of safety may be used for any repair 

required by this AD, if it is approved by an 

Authorized Representative for the Boeing 

Delegation Option Authorization 

Organization who has been authorized by the 

Manager, Seattle ACO, to make those 

findings. For a repair method to be approved, 

the repair must meet the certification basis of 

the airplane, and the approval must 

specifically refer to this AD. 

(3) AMOCs approved previously according 

to AD 2004–03–11 are approved as AMOCs 

for the corresponding provisions of 

paragraphs (f) and (g) of this AD. 

Issued in Renton, Washington, on 

September 7, 2005. 

Kalene C. Yanamura, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 05–18403 Filed 9–15–05; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2005–22427; Directorate 

Identifier 2004–NM–263–AD] 

RIN 2120–AA64 

Airworthiness Directives; British 

Aerospace Model BAC 1–11 200 and 

400 Series Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Notice of proposed rulemaking 

(NPRM). 

SUMMARY: The FAA proposes to adopt a 

new airworthiness directive (AD) for all 

British Aerospace Model BAC 1–11 200 

and 400 series airplanes. This proposed 

AD would require revising the airplane 

flight manual (AFM) to contain 

applicable AFM amendments, which 

advise the flightcrew of information 

pertaining to safely operating the fuel 

system. The proposed AD would also 

require revising the FAA-approved 

maintenance program to include certain 

repetitive maintenance tasks intended to 

improve the safety of the fuel system. 

This proposed AD results from fuel 

system reviews conducted by the 

manufacturer. We are proposing this AD 

to prevent potential ignition sources 

inside the fuel system, which, in 

combination with flammable fuel 

vapors, could result in a fuel tank 

explosion and consequent loss of the 

airplane. 

DATES: We must receive comments on 

this proposed AD by October 17, 2005. 

ADDRESSES: Use one of the following 

addresses to submit comments on this 

proposed 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. 

• 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 British Aerospace, Service 

Support, Airbus Limited, P.O. Box 77, 

Bristol BS99 7AR, England, for service 

information identified in this proposed 

AD. 

FOR FURTHER INFORMATION CONTACT: 

Todd Thompson, Aerospace Engineer, 

International Branch, ANM–116, FAA, 

Transport Airplane Directorate, 1601 

Lind Avenue, SW., Renton, Washington 

98055–4056; telephone (425) 227–1175; 

fax (425) 227–1149. 

SUPPLEMENTARY INFORMATION: 

Comments Invited 

We invite you to submit any relevant 

written data, views, or arguments 

regarding this proposed AD. Include the 

docket number ‘‘Docket No. FAA–2005–

22427; Directorate Identifier 2004–NM–

263–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:// 

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 proposed AD. 

Using the search function of our docket 

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