Federal Register / Vol. 72, No. 43 / Tuesday, March 6, 2007 / Proposed Rules 9877 

submitting information or transacting 

business electronically to the maximum 

extent possible. 

The AMS is committed to complying 

with the E-Government Act, to promote 

the use of the Internet and other 

information technologies to provide 

increased opportunities for citizen 

access to Government information and 

services, and for other purposes. 

E. General Notice of Public Rulemaking 

This proposed rule reflects 

recommendations submitted to the 

Secretary by the NOSB for the 

continuation of 166 exemptions and 

prohibitions contained on the National 

List of Allowed and Prohibited 

Substances. This proposed rule also 

reflects recommendations by the NOSB 

to discontinue 3 exemptions contained 

on the National List. A 60-day period for 

interested persons to comment on this 

rule is provided. 

List of Subjects in 7 CFR Part 205 

Administrative practice and 

procedure, Agriculture, Animals, 

Archives and records, Imports, Labeling, 

Organically produced products, Plants, 

Reporting and recordkeeping 

requirements, Seals and insignia, Soil 

conservation. 

For the reasons set forth in the 

preamble, 7 CFR part 205, Subpart G is 

proposed to be amended as follows: 

PART 205—NATIONAL ORGANIC 

PROGRAM 

1. The authority citation for 7 CFR 

part 205 continues to read as follows: 

Authority: 7 U.S.C. 6501–6522. 

2. Section 205.603 is revised to read 

as follows: 

§ 205.603 Synthetic substances allowed 

for use in organic livestock production. 

In accordance with restrictions 

specified in this section the following 

synthetic substances may be used in 

organic livestock production: 

(a) As disinfectants, sanitizer, and 

medical treatments as applicable. 

(1) Alcohols. 

(i) Ethanol—disinfectant and sanitizer 

only, prohibited as a feed additive. 

(ii) Isopropanol—disinfectant only. 

(2) Aspirin—approved for health care 

use to reduce inflammation. 

(3) Biologics—Vaccines. 

(4) Chlorhexidine—Allowed for 

surgical procedures conducted by a 

veterinarian. Allowed for use as a teat 

dip when alternative germicidal agents 

and/or physical barriers have lost their 

effectiveness. 

(5) Chlorine materials—disinfecting 

and sanitizing facilities and equipment. 

Residual chlorine levels in the water 

shall not exceed the maximum residual 

disinfectant limit under the Safe 

Drinking Water Act. 

(i) Calcium hypochlorite. 

(ii) Chlorine dioxide. 

(iii) Sodium hypochlorite. 

(6) Electrolytes—without antibiotics. 

(7) Glucose. 

(8) Glycerine—Allowed as a livestock 

teat dip, must be produced through the 

hydrolysis of fats or oils. 

(9) Hydrogen peroxide. 

(10) Iodine. 

(11) Magnesium sulfate. 

(12) Oxytocin—use in postparturition 

therapeutic applications. 

(13) Paraciticides. Ivermectin—

prohibited in slaughter stock, allowed in 

emergency treatment for dairy and 

breeder stock when organic system 

plan-approved preventive management 

does not prevent infestation. Milk or 

milk products from a treated animal 

cannot be labeled as provided for in 

subpart D of this part for 90 days 

following treatment. In breeder stock, 

treatment cannot occur during the last 

third of gestation if the progeny will be 

sold as organic and must not be used 

during the lactation period for breeding 

stock. 

(14) Phosphoric acid—allowed as an 

equipment cleaner, Provided, That, no 

direct contact with organically managed 

livestock or land occurs. 

(b) As topical treatment, external 

parasiticide or local anesthetic as 

applicable. (1) Copper sulfate. 

(2) Iodine. 

(3) Lidocaine—as a local anesthetic. 

Use requires a withdrawal period of 90 

days after administering to livestock 

intended for slaughter and 7 days after 

administering to dairy animals. 

(4) Lime, hydrated—as an external 

pest control, not permitted to cauterize 

physical alterations or deodorize animal 

wastes. 

(5) Mineral oil—for topical use and as 

a lubricant. 

(6) Procaine—as a local anesthetic, 

use requires a withdrawal period of 90 

days after administering to livestock 

intended for slaughter and 7 days after 

administering to dairy animals. 

(c) As feed supplements. None. 

(d) As feed additives. 

(1) DL-Methionine, DL-Methioninehydroxy analog, and DL-Methioninehydroxy analog calcium—for use only 

in organic poultry production until 

October 21, 2008. 

(2) Trace minerals, used for 

enrichment or fortification when FDA 

approved. 

(3) Vitamins, used for enrichment or 

fortification when FDA approved. 

(e) As synthetic inert ingredients as 

classified by the Environmental 

Protection Agency (EPA), for use with 

nonsynthetic substances or a synthetic 

substances listed in this section and 

used as an active pesticide ingredient in 

accordance with any limitations on the 

use of such substances. 

(1) EPA List 4—Inerts of Minimal 

Concern. 

(2) [Reserved] 

(f) through (z) [Reserved] 

§ 205.605 [Amended] 

3. In § 205.605, the substance ‘‘colors, 

nonsynthetic sources only’’ is removed 

from paragraph (a) and the substance 

‘‘Potassium tartrate made from tartaric 

acid’’ is removed from paragraph (b). 

Dated: February 28, 2007. 

Lloyd C. Day, 

Administrator, Agricultural Marketing 

Service. 

[FR Doc. E7–3829 Filed 3–5–07; 8:45 am] 

BILLING CODE 3410–02–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2007–27359; Directorate 

Identifier 2006–NM–042–AD] 

RIN 2120–AA64 

Airworthiness Directives; Boeing 

Model 747–100, 747–100B, 747–200B, 

747–200C, 747–200F, 747–300, 747SR, 

and 747SP 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 

certain Boeing Model 747–100, 747–

100B, 747–200B, 747–200C, 747–200F, 

747–300, 747SR, and 747SP series 

airplanes. This proposed AD would 

require repetitive high frequency eddy 

current inspections for cracks of the 

fuselage skin at stringer 5 left and right 

between stations 340 and 350, and 

corrective actions if necessary. This 

proposed AD results from reports of 

fatigue cracks in the fuselage skin near 

stringer 5 between stations 340 and 350. 

We are proposing this AD to detect and 

correct fatigue cracking of the fuselage 

skin near stringer 5. Cracks in this area 

could join together and result in inflight depressurization of the airplane. 

DATES: We must receive comments on 

this proposed AD by April 20, 2007. 


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9878 Federal Register / Vol. 72, No. 43 / Tuesday, March 6, 2007 / Proposed Rules 

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 Boeing Commercial 

Airplanes, P.O. Box 3707, Seattle, 

Washington 98124–2207, for the service 

information identified in this proposed 

AD. 

FOR FURTHER INFORMATION CONTACT: Ivan 

Li, Aerospace Engineer, Airframe 

Branch, ANM–120S, FAA, Seattle 

Aircraft Certification Office, 1601 Lind 

Avenue, SW., Renton, Washington 

98057–3356; 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 in the 

ADDRESSES section. Include the docket 

number ‘‘FAA–2007–27359; Directorate 

Identifier 2006–NM–042–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 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 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. 

Discussion 

We have received a report indicating 

that, during inspections on certain 

Boeing Model 747 airplanes, four 

operators found fatigue cracks in the 

fuselage skin at stringer 5, between 

stations 340 and 350. The airplanes had 

flown 18,000 to 20,000 total flight 

cycles. The cracks that were found 

ranged in length from a single crack of 

0.25 inch to multiple cracks that were 

equivalent to a 10-inch long crack. Skin 

cracks in this area could join together 

and result in in-flight depressurization 

of the airplane. 

Other Relevant Rulemaking 

On January 16, 1990, we issued AD 

90–06–06, amendment 39–6490 (55 FR 

8374, March 7, 1990), for certain Boeing 

Model 747 series airplanes. That AD 

requires the incorporation of certain 

structural modifications (reference 

Boeing Service Bulletin 747–53–2272, 

Revision 12, dated December 22, 1988, 

identified in Boeing Document No. D6–

35999). We issued that AD to prevent 

structural failure of the affected 

airplanes. One of the required 

modifications of AD 90–06–06 ends the 

repetitive inspections of certain 

structures that would also be required 

by this proposed AD. 

On April 1, 2005, we issued AD 2005–

08–01, amendment 39–14053 (70 FR 

18290, April 11, 2005), for certain 

Boeing Model 747 series airplanes. That 

AD requires repetitive inspections; 

repetitive external detailed inspections 

for cracks or loose or missing fasteners 

of certain body skin on the left and right 

sides of the airplane; an internal 

detailed inspection for cracking of 

certain left- and right-side frames and 

adjacent skin; repetitive high-frequency 

eddy current (HFEC) inspections of 

certain body frames between certain 

body stations; and repairs if necessary. 

We issued that AD to detect and correct 

fatigue cracks in the body frames, skin, 

and other internal structures in fuselage 

section 41, which could lead to rapid 

decompression and loss of the structural 

integrity of the airplane. Paragraph (s) of 

AD 2005–08–01 refers to Boeing Service 

Bulletin 747–53–2272, dated January 12, 

1987, and any revision through Revision 

18, dated May 16, 2002, as the 

appropriate source of service 

information for accomplishing the 

terminating action described in that AD. 

That terminating action ends the 

repetitive inspections of certain 

structures that would also be required 

by this proposed AD. 

Relevant Service Information 

We have reviewed Boeing Alert 

Service Bulletin 747–53A2542, dated 

February 16, 2006 (referred to hereafter 

as ‘‘the alert service bulletin’’). For 

airplanes that do not have external skin 

doublers installed around the left- and 

right-side Number 3 flight deck 

windows in accordance with Boeing 

Service Bulletin 747–53–2272, the alert 

service bulletin describes procedures for 

repetitive HFEC inspections for cracks 

of the external surface of the fuselage 

skin at stringer 5 left and right, between 

stations 340 and 350. The alert service 

bulletin specifies that the HFEC 

inspections be done at the compliance 

times specified in the following table. 

COMPLIANCE TIMES FOR HFEC INSPECTIONS

Airplane group Airplane condition Initial compliance time 

(whichever occurs later) 

Repetitive interval 

(not to exceed) 

Group 1 ............. Fewer than 16,000 total flight cycles.Before accumulating 16,000 total flight cycles or within 2,000 

flight cycles 1.

4,000 flight cycles. 

16,000 or more total flight cycles Before accumulating 18,000 total flight cycles or within 250 flight 

cycles 1.

None. 

Group 2 ............. Fewer than 20,000 total flight 

cycle.

Before accumulating 20,000 total flight cycles or within 2,000 

flight cycles 1.

4,000 flight cycles. 


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Federal Register / Vol. 72, No. 43 / Tuesday, March 6, 2007 / Proposed Rules 9879 

COMPLIANCE TIMES FOR HFEC INSPECTIONS—Continued 

Airplane group Airplane condition Initial compliance time 

(whichever occurs later) 

Repetitive interval 

(not to exceed) 

20,000 or more total flight cycles Before accumulating 22,000 total flight cycles or within 250 flight 

cycles 1.

None. 

1After the date on the alert service bulletin. 

The alert service bulletin also 

describes corrective actions to be done 

if any crack is found. If the total length 

of all cracks found is less than 1.0 inch, 

corrective actions include stop drilling 

the crack or cracks; and, either installing 

external skin doublers around the 

Number 3 flight deck window, or 

installing a temporary external 

structural repair manual (SRM) skin 

repair. If the total length of all cracks 

found is 1.0 inch or longer, corrective 

actions include trimming the cracked 

area of skin and installing a filler; and, 

either installing external skin doublers 

around the Number 3 flight deck 

window and installing a tripler, or 

installing a temporary external SRM 

skin repair. The alert service bulletin 

specifies that the corrective actions 

should be done before further flight. The 

alert service bulletin refers to Boeing 

Service Bulletin 747–53–2272 (currently 

at Revision 18, dated May 16, 2002) as 

an additional source of service 

information for installing the external 

skin doublers around the left- and rightside Number 3 flight deck windows. 

For Group 2 airplanes only: The alert 

service bulletin describes installing 

external skin doublers around the leftand right-side Number 3 flight deck 

windows before accumulating 24,000 

total flight cycles or within 250 flight 

cycles after the effective date of the alert 

service bulletin, whichever occurs later. 

This constitutes terminating action for 

the repetitive HFEC inspections 

specified in this NPRM. 

For Group 1 airplanes only: AD 90–

06–06 requires installation of external 

skin doublers around the Number 3 

flight deck windows in accordance with 

Boeing Service Bulletin 747–53–2272, 

Revision 12, dated December 22, 1988, 

at or before 20,000 total flight cycles. 

This constitutes terminating action for 

the repetitive HFEC inspections 

specified in this NPRM. 

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 

We have evaluated all pertinent 

information and identified an unsafe 

condition that is likely to exist or 

develop on other airplanes of this same 

type design. For this reason, we are 

proposing this AD, which would require 

accomplishing the actions specified in 

the service information described 

previously, except as discussed under 

‘‘Difference Between the Proposed AD 

and Alert Service Bulletin.’’

Difference Between the Proposed AD 

and Alert Service Bulletin 

The alert service bulletin specifies to 

contact the manufacturer for 

instructions on how to repair certain 

conditions, but this proposed AD would 

require repairing 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 Commercial Airplanes 

Delegation Option Authorization 

Organization whom we have authorized 

to make those findings. 

Clarification of Reporting 

Although the alert service bulletin 

discusses reporting inspection results, 

the Accomplishment Instructions of the 

alert service bulletin do not specify 

sending such a report to Boeing. This 

proposed AD would not require such 

reporting. 

Costs of Compliance 

There are about 281 airplanes of the 

affected design in the worldwide fleet. 

This proposed AD would affect about 92 

airplanes of U.S. registry. The proposed 

inspection would take about 4 work 

hours per airplane, at an average labor 

rate of $80 per work hour. Based on 

these figures, the estimated cost of the 

proposed inspection for U.S. operators 

is $29,440, or $320 per airplane, per 

inspection cycle. 

For Group 2 airplanes (about 4 of U.S. 

registry), the mandatory terminating 

action for the repetitive inspections 

would take about 1,240 work hours, at 

an average labor rate of $80 per work 

hour. The manufacturer states that it 

will supply required parts to the 

operators at no cost. Based on these 

figures, the estimated cost of the 

terminating action for U.S. operators is 

$396,800, or $99,200 per airplane. 

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. 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. 


cprice-sewell on PROD1PC67 with PROPOSALS
9880 Federal Register / Vol. 72, No. 43 / Tuesday, March 6, 2007 / Proposed Rules 

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 Federal Aviation 

Administration (FAA) amends § 39.13 

by adding the following new 

airworthiness directive (AD): 

Boeing: Docket No. FAA–2007–27359; 

Directorate Identifier 2006–NM–042–AD. 

Comments Due Date 

(a) The FAA must receive comments on 

this AD action by April 20, 2007. 

Affected ADs 

(b) AD 90–06–06, amendment 39–6490, 

paragraph A., requires installation of external 

skin doublers in the area near the flight deck 

windows for Group 1 airplanes, which ends 

the repetitive high-frequency eddy current 

(HFEC) inspections required by this AD only 

for those airplanes. Installing external skin 

doublers as required by paragraph (g) of this 

AD ends certain repetitive inspections of the 

fuselage skin required by paragraph (f) of AD 

2005–08–01, amendment 39–14053, only for 

the area near the flight deck windows 

modified by the external skin doublers. 

Applicability 

(c) This AD applies to Boeing Model 747–

100, 747–100B, 747–200B, 747–200C, 747–

200F, 747–300, 747SR, and 747SP series 

airplanes, certificated in any category; as 

identified in Boeing Alert Service Bulletin 

747–53A2542, dated February 16, 2006. 

Unsafe Condition 

(d) This AD results from reports of fatigue 

cracks in the fuselage skin near stringer 5 

between body stations 340 and 350. We are 

issuing this AD to detect and correct fatigue 

cracking of the fuselage skin near stringer 5. 

Cracks in this area could join together and 

result in in-flight depressurization 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. 

Inspections and Corrective Actions 

(f) For any airplane that has not had 

external skin doublers installed around the 

left- or right-side Number 3 flight deck 

window in accordance with Boeing Service 

Bulletin 747–53–2272, Revision 18, dated 

May 16, 2002, or an earlier revision: Do the 

applicable actions described in paragraphs 

(f)(1) and (f)(2) of this AD. Do all the actions 

in and in accordance with the 

Accomplishment Instructions of Boeing Alert 

Service Bulletin 747–53A2542, dated 

February 16, 2006. Do the actions at the 

compliance times specified in paragraph 1.E., 

‘‘Compliance,’’ of Boeing Alert Service 

Bulletin 747–53A2542, dated February 16, 

2006, on the side(s) of the airplane on which 

the doubler installation has not been done; 

except where the service bulletin specifies 

compliance times after the date on the 

service bulletin, this AD requires compliance 

times after the effective date of this AD. 

Installing external skin doublers around the 

left- or right-side Number 3 flight deck 

windows in accordance with Boeing Service 

Bulletin 747–53–2272, Revision 18, or an 

earlier revision; ends the repetitive HFEC 

inspections required by this paragraph on the 

side of the airplane on which the doubler is 

installed. After the effective date of this AD, 

only Boeing Service Bulletin 747–53–2272, 

Revision 18, may be used to install the 

external skin doublers around the left- and 

right-side Number 3 flight deck windows. 

(1) Do a HFEC inspection for cracks of the 

fuselage skin at stringer 5, between body 

stations 340 and 350; and do all applicable 

corrective actions before further flight. 

(2) Repeat the HFEC inspection thereafter 

at the applicable interval specified in 

paragraph 1.E. of Boeing Alert Service 

Bulletin 747–53A2542. 

Terminating Action 

(g) For Group 2 airplanes only: Before 

accumulating 24,000 total flight cycles, or 

within 250 flight cycles after the effective 

date of the AD, whichever occurs later, 

install external skin doublers around the leftand right-side Number 3 flight deck 

windows; in accordance with Boeing Service 

Bulletin 747–53–2272, Revision 17, dated 

November 18, 1999; or Revision 18, dated 

May 16, 2002. After the effective date of this 

AD, only Boeing Service Bulletin 747–53–

2272, Revision 18, may be used to 

accomplish the doubler installation around 

the left- and right-side Number 3 flight deck 

windows. Accomplishing this action ends 

the repetitive inspections required by 

paragraph (f) of this AD. 

Alternative Methods of Compliance 

(AMOCs) 

(h)(1) The Manager, Seattle Aircraft 

Certification Office (ACO), 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. 

(3) 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 

Commercial Airplanes 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. 

Issued in Renton, Washington, on February 

23, 2007. 

Ali Bahrami, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. E7–3842 Filed 3–5–07; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2006–25658; Directorate 

Identifier 2006–NM–054–AD] 

RIN 2120–AA64 

Airworthiness Directives; Airbus Model 

A318, A319, A320, and A321 Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Supplemental notice of 

proposed rulemaking (NPRM); 

reopening of comment period. 

SUMMARY: The FAA is revising an earlier 

NPRM for an airworthiness directive 

(AD) that applies to certain Airbus 

Model A318, A319, A320, and A321 

airplanes. The original NPRM would 

have superseded an existing AD that 

currently requires repetitive detailed 

inspections of the inboard flap 

trunnions for any wear marks and of the 

sliding panels for any cracking at the 

long edges, and corrective actions if 

necessary. The original NPRM proposed 

to add airplanes to the applicability in 

the existing AD and change the 

inspection type. The original NPRM 

resulted from a determination that 

certain airplanes must be included in 

the applicability of the AD, and that the 

inspection type must be revised. This 

new action revises the original NPRM 

by including airplanes that were 

inadvertently excluded from the 

applicability. We are proposing this 

supplemental NPRM to detect and 

correct wear of the inboard flap 

trunnions, which could lead to loss of 

flap surface control and consequently 

result in the flap detaching from the 

airplane. A detached flap could result in 

damage to the tail of the airplane. 

DATES: We must receive comments on 

this supplemental NPRM by April 2, 

2007. 

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. 


cprice-sewell on PROD1PC67 with PROPOSALS