64534 Federal Register / Vol. 69, No. 214 / Friday, November 5, 2004 / Proposed Rules 

Modification of Thermal Insulation and 

Fuselage Drainage Systems 

(f) Within 22 months after the effective 

date of this AD, modify the thermal 

insulation system of applicable fuselage 

frames and modify the fuselage drainage 

system, by doing all actions in the 

Accomplishment Instructions of the 

applicable service bulletins specified in 

Table 1 of this AD.

TABLE 1.—RELEVANT SERVICE BULLETINS

For Airbus models Modify the thermal insulation according to Airbus Service Bulletin 

And modify the fuselage drainage system according to Airbus Service Bulletin 

A300 B2 and B4 series ..................................... A300–21–0116, Revision 02, dated June 13, 

2003.

A300–53–0201, Revision 04, dated May 2, 

2003. 

A300 B4–600, B4–600R, and F4–600R series; 

A300 C4–605R Variant F (collectively called 

A300–600).

A300–21–6025, Revision 01, dated June 13, 

2003.

A300–53–6008, Revision 05, dated July 15, 

2004. 

A310 series ........................................................ A310–21–2041, Revision 02, dated June 13, 

2003.

A310–53–2027, Revision 04, dated July 15, 

2004. 

Modifications Accomplished According to 

Previous Issues of Service Bulletins 

(g) Modifications accomplished before the 

effective date of this AD according to Airbus 

Service Bulletin A300–53–6008, Revision 03, 

dated November 6, 1990, or Revision 04, 

dated April 28, 2003 (for Model A300 B4–

600, B4–600R, and F4–600R series airplanes; 

and A300 C4–605R Variant F airplanes 

(collectively called A300–600)); or Airbus 

Service Bulletin A310–53–2027, Revision 02, 

dated November 6, 1990, or Revision 03, 

dated May 2, 2003 (for Model A310 series 

airplanes); are considered acceptable for 

compliance with the corresponding action 

specified in this AD. 

Maintenance Program Revision 

(h) Within 90 days after doing the actions 

required by paragraph (f) of this AD, or 

within 90 days after the effective date of this 

AD, whichever is later: Incorporate into the 

FAA-approved maintenance inspection 

program repetitive detailed inspections for 

corrosion or cracking of fuselage structure 

from FR 38.2 to 39, and at FR 54, as 

applicable, as described in Airbus 

Maintenance Planning Document Task 

Numbers 538295–0603–01 (for Airbus Model 

A300 B2 and B4 series airplanes), and 

541531–01–1 and 531533–01–1 (for Airbus 

Model A300 B4–600, B4–600R, and F4–600R 

series airplanes, and A300 C4–605R Variant 

F airplanes (collectively called A300–600); 

and Model A310 series airplanes). Then, 

thereafter, comply with the applicable 

requirements.

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 

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.’’

Alternative Methods of Compliance 

(AMOCs) 

(i) 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. 

Related Information 

(j) French airworthiness directive 2003–

317(B), dated August 20, 2003, also addresses 

the subject of this AD.

Issued in Renton, Washington, on October 

26, 2004. 

Ali Bahrami, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service.

[FR Doc. 04–24722 Filed 11–4–04; 8:45 am] 

BILLING CODE 4910–13–P

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration 

14 CFR Part 39

[Docket No. FAA–2004–19533; Directorate 

Identifier 2004–NM–31–AD] 

RIN 2120–AA64

Airworthiness Directives; Boeing 

Model 737–300, –400, and –500 Series 

Airplanes

AGENCY: Federal Aviation 

Administration (FAA), DOT.

ACTION: Notice of proposed rulemaking 

(NPRM). 

SUMMARY: The FAA proposes to adopt a 

new airworthiness directive (AD) for 

certain Boeing Model 737–300, –400, 

and –500 series airplanes. This 

proposed AD would require repetitive 

inspections for cracking of the crown 

area of the fuselage skin, and corrective 

actions, if necessary. This proposed AD 

is prompted by a 737 fuselage structure 

test and fatigue analysis that indicate 

fuselage skin cracking could occur 

between 21,000 and 42,000 total flight 

cycles. We are proposing this AD to 

detect and correct fatigue cracking of the 

fuselage skin, which could cause the 

fuselage skin to fracture and fail, and 

could result in rapid decompression of 

the airplane.

DATES: We must receive comments on 

this proposed AD by December 20, 

2004.

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. 

• By 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–2004–

19533; the directorate identifier for this 

docket is 2004–NM–31–AD.

FOR FURTHER INFORMATION CONTACT:

Technical Information: Sue Lucier, 

Aerospace Engineer, Airframe Branch, 

ANM–120S, FAA, Seattle Aircraft 

Certification Office, 1601 Lind Avenue, 

SW., Renton, Washington 98055–4056; 

telephone (425) 917–6438; fax (425) 

917–6590. 

Plain Language Information: Marcia 

Walters, marcia.walters@faa.gov.

SUPPLEMENTARY INFORMATION:

Federal Register / Vol. 69, No. 214 / Friday, November 5, 2004 / Proposed Rules 64535

Docket Management System (DMS) 

The FAA has implemented new 

procedures for maintaining AD dockets 

electronically. As of May 17, 2004, new 

AD actions are posted on DMS and 

assigned a docket number. We track 

each action and assign a corresponding 

directorate identifier. The DMS AD 

docket number is in the form ‘‘Docket 

No. FAA–2004–99999.’’ The Transport 

Airplane Directorate identifier is in the 

form ‘‘Directorate Identifier 2004–NM–

999–AD.’’ Each DMS AD docket also 

lists the directorate identifier (‘‘Old 

Docket Number’’) as a cross-reference 

for searching purposes.

Comments Invited 

We invite you to submit any written 

relevant data, views, or arguments 

regarding this proposed AD. Send your 

comments to an address listed under 

ADDRESSES. Include ‘‘Docket No. FAA–

2004–19533; Directorate Identifier 

2004–NM–31–AD’’ in the subject line 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 submitted 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.

We are reviewing the writing style we 

currently use in regulatory documents. 

We are interested in your comments on 

whether the style of this document is 

clear, and your suggestions to improve 

the clarity of our communications that 

affect you. You can get more 

information about plain language at 

http://www.faa.gov/language and http://

www.plainlanguage.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 DMS 

receives them. 

Discussion 

We have received the results of a 737 

fuselage structure test and fatigue 

analysis conducted by the airplane 

manufacturer. The results indicate that 

fatigue cracking is expected to occur 

between body station (BS) 360 and BS 

1016 common to the chem-milled step 

of the upper skin above the S–4 and S–

10 lap joints, when the airplane 

accumulates between 21,000 to 42,000 

total flight cycles. This kind of cracking 

is caused by fatigue from high bending 

stresses at the edge of the chem-milled 

step. This condition, if not detected and 

corrected, could cause the fuselage skin 

to fracture and fail, and could result in 

rapid decompression of the airplane. 

Other Related Rulemaking 

On August 26, 2004, we issued AD 

2004–18–06, amendment 39–13784 (69 

FR 54206, September 8, 2004), 

applicable to certain Boeing Model 737–

200, –200C, –300, –400, and –500 series 

airplanes, which requires repetitive 

inspections to find fatigue cracking of 

certain upper and lower skin panels of 

the fuselage, and follow-on and 

corrective actions, if necessary. That AD 

was prompted by reports indicating that 

cracks were found along the edges of the 

chem-milled pockets in the upper skin 

at stringer S–12, and above the S–4, S–

10, and S–14 lap joints, on several 

Boeing Model 737 series airplanes. The 

actions required by that AD are 

intended to find and fix fatigue cracking 

of the skin panels, which could result in 

sudden fracture and failure of the skin 

panels of the fuselage, and consequent 

rapid decompression of the airplane. AD 

2004–18–06 does not affect the 

requirements of this AD. 

Relevant Service Information 

We have reviewed Boeing Special 

Attention Service Bulletin 737–53–

1234, dated June 13, 2002, which 

describes doing repetitive external 

detailed and eddy current inspections 

for cracking of the crown area of the 

fuselage skin just above the S–4 and S–

14 lap joints from station 360 to station 

1016, and doing either the permanent 

repair or a time-limited repair. Doing 

either repair ends the repetitive 

inspections for the repaired area. The 

service bulletin specifies that the 

inspections are not necessary in certain 

areas and to contact Boeing if certain 

repairs are found. 

The permanent repair, which is 

subject to certain limitations, consists of 

the following related investigative and 

corrective actions: 

1. Doing eddy current inspections of 

the fuselage skin for cracking; 

2. Doing detailed inspections of the 

fastener holes common to the lower 

row/remaining rows of fasteners in the 

lap joint for cracking; 

3. Doing general visual, detailed, and 

eddy current inspections of the skin and 

lap joint for cracking, corrosion, or 

disbonding; 

4. Contacting Boeing for repair if any 

cracking, corrosion, or disbonding is 

found or if Hi-locks, lockbolts, or bolts 

are installed in the area of a crack; and 

5. Reporting any cracking to Boeing. 

The time-limited repair, which is 

subject to certain limitations, consists of 

the following related investigative and 

corrective actions: 

1. Doing external detailed inspections 

of the skin in each adjacent bay in the 

area of chem-milled step for cracks; 

2. Doing external detailed inspections 

of the skin and lap joint in the area of 

the repair for corrosion or disbonding; 

and 

3. Contacting Boeing for repair if any 

cracking, corrosion, or disbonding is 

found. 

If the time-limited repair is done, the 

service bulletin describes doing these 

related investigative and corrective 

actions at times varying from 3,000 

flight cycles to 10,000 flight cycles after 

the time-limited repair is done:

1. Doing repetitive general visual 

inspections for loose or missing 

fasteners; 

2. Replacing missing or loose 

fasteners with new fasteners; 

3. Doing one-time inspections of the 

skin and lap joint of the repaired area 

for cracking or corrosion (includes 

doing a general visual inspection of the 

lap joint for corrosion and eddy current 

inspections of the skin and the skin 

under the tear strap for cracking); 

4. Contacting Boeing for repair if any 

cracking or corrosion is found; and 

5. Doing a permanent modification of 

the time-limited repair (includes doing 

detailed inspections of the fastener 

holes for cracking, doing a detailed 

inspection of the skin for corrosion or 

disbonded doublers; and contacting 

Boeing for any applicable repair). Doing 

a permanent modification ends the need 

for the repetitive general visual 

inspections for the repaired area only. 

The service bulletin recommends the 

following approximate compliance 

times for the initial detailed and eddy 

64536 Federal Register / Vol. 69, No. 214 / Friday, November 5, 2004 / Proposed Rules 

current inspections: Within 21,000 to 

42,000 total flight cycles, depending on 

the applicable site of the fuselage skin; 

or within 4,500 cycles after release of 

this service bulletin; whichever is later. 

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. Therefore, we are 

proposing this AD, which would require 

repetitive inspections for cracking of the 

crown area of the fuselage skin, and 

permanent or time-limited repair if 

necessary. The proposed AD would 

require you to use the service 

information described previously to 

perform these actions, except as 

discussed under ‘‘Differences Between 

the Proposed AD and the Service 

Bulletin.’’

Differences Between the Proposed AD 

and the Service Bulletin 

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 type 

certification basis of the airplane, and 

that have been approved by a Boeing 

Company Designated Engineering 

Representative who has been authorized 

by the FAA to make such findings. 

You should note that, although the 

service bulletin describes procedures for 

reporting information to the 

manufacturer, this proposed AD would 

not require those actions. We do not 

need this information. 

Interim Action 

This is considered to be interim 

action until final action is identified, at 

which time we may consider further 

rulemaking. 

Costs of Compliance 

There are about 579 airplanes of the 

affected design in the worldwide fleet. 

The following table provides the 

estimated costs for U.S. operators to 

comply with this proposed AD.

ESTIMATED COSTS

Action Work hours Average labor 

rate per hour 

Cost per

airplane, per

inspection 

cycle 

Number of 

U.S.-registered 

airplanes 

Fleet cost, per 

inspection 

cycle 

Inspections ........................................................................... 94 $65 $6,110 175 $1,069,250

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 adding 

the following new airworthiness 

directive (AD):

Boeing: Docket No. FAA–2004–19533; 

Directorate Identifier 2004–NM–31–AD. 

Comments Due Date 

(a) The Federal Aviation Administration 

(FAA) must receive comments on this AD 

action by December 20, 2004. 

Affected ADs 

(b) None. 

Applicability: (c) This AD applies to 

Boeing Model 737–300, –400, and –500 series 

airplanes, certificated in any category; as 

listed in Boeing Special Attention Service 

Bulletin 737–53–1234, dated June 13, 2002. 

Unsafe Condition 

(d) This AD was prompted by a 737 

fuselage structure test and fatigue analysis 

that indicate fuselage skin cracking could 

occur between 21,000 and 42,000 total flight 

cycles. We are issuing this AD to detect and 

correct fatigue cracking of the fuselage skin, 

which could cause the fuselage skin to 

fracture and fail, and could result in rapid 

decompression 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. 

Service Bulletin References 

(f) The term ‘‘service bulletin,’’ as used in 

this AD, means Boeing Special Attention 

Service Bulletin 737–53–1234, dated June 13, 

2002. 

Initial and Repetitive Inspections 

(g) At the later of the times specified in 

paragraphs (g)(1) and (g)(2) of this AD, 

perform detailed and eddy current 

inspections for cracking of the crown area of 

the fuselage skin in accordance with Part 1, 

including the ‘‘Note,’’ of the Work 

Instructions of the service bulletin, except as 

provided by paragraph (j) of this AD. 

(1) Before the accumulation of the 

applicable total flight cycles specified in the 

‘‘Threshold’’ column of Table 1 of Figure 1 

of the service bulletin. 

(2) Within 4,500 flight cycles after the 

effective date of this AD. 

(h) Repeat either the detailed or eddy 

current inspections specified in paragraph (g) 

of this AD at the applicable intervals 

specified in paragraph (h)(1) or (h)(2) of this 

AD until paragraph (i)(1) or (i)(2) of this AD 

has been done, as applicable. 

(1) Repeat the detailed inspections 

thereafter at intervals not to exceed 1,200 

flight cycles. 

(2) Repeat the eddy current inspections 

thereafter at intervals not to exceed 3,000 

flight cycles. 

Permanent or Time-Limited Repair 

(i) If any cracking is found during any 

inspection required by paragraph (g) or (h) of 

this AD, do the actions specified in 

paragraph (i)(1) or (i)(2) of this AD in 

accordance with the service bulletin, except 

as provided by paragraphs (j) and (k) of this 

AD. 

Federal Register / Vol. 69, No. 214 / Friday, November 5, 2004 / Proposed Rules 64537

(1) Before further flight, do a permanent 

repair (including related investigative actions 

and applicable corrective actions) in 

accordance with Part 2, including the 

‘‘Note,’’ of the Work Instructions of the 

service bulletin. Doing a permanent repair 

ends the repetitive inspections required by 

paragraph (h) of this AD for the repaired area 

only. 

(2) Do the actions specified in paragraphs 

(i)(2)(i) and (i)(2)(ii) of this AD at the time 

specified in the applicable paragraph. Doing 

a time-limited repair ends the repetitive 

inspections required by paragraph (h) of this 

AD for the repaired area only. 

(i) Before further flight, do a time-limited 

repair (including related investigative actions 

and applicable corrective actions) in 

accordance with Part 3, including the 

‘‘Note,’’ of the Work Instructions of the 

service bulletin. 

(ii) At the times specified in Figure 8 of the 

service bulletin, do the related investigative 

and corrective actions in accordance with 

Part 3, including the ‘‘Note,’’ of the Work 

Instructions of the service bulletin. 

Contact the FAA 

(j) Where the service bulletin specifies to 

contact Boeing for appropriateaction: Before 

further flight, repair per a method approved 

by the Manager, Seattle Aircraft Certification 

Office (ACO), FAA; or per data meeting the 

type certification basis of the airplane 

approved by a Boeing Company Designated 

Engineering Representative who has been 

authorized by the Manager, Seattle ACO, to 

make such findings. For a repair method to 

be approved, the approval must specifically 

reference this AD. 

No Reporting 

(k) Although the service bulletin specifies 

reporting certain information to Boeing, this 

AD does not require that action. 

Alternative Methods of Compliance 

(AMOCs) 

(l) The Manager, Seattle ACO, FAA, has the 

authority to approve AMOCs for this AD, if 

requested using the procedures found in 14 

CFR 39.19.

Issued in Renton, Washington, on October 

26, 2004. 

Ali Bahrami, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service.

[FR Doc. 04–24721 Filed 11–4–04; 8:45 am] 

BILLING CODE 4910–13–P

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration 

14 CFR Part 39

[Docket No. FAA–2004–19532; Directorate 

Identifier 2004–NM–87–AD] 

RIN 2120–AA64

Airworthiness Directives; Boeing 

Model 747–100, 747–100B, 747–200B, 

747–300, 747–400, 747–400D, 747SR, 

and 747SP Series Airplanes

AGENCY: Federal Aviation 

Administration (FAA), 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, 747–300, 747–400, 

747–400D, 747SR, and 747SP series 

airplanes. This proposed AD would 

require replacing or modifying the 

control panels for the galley cart lift and 

modifying related electrical cable 

assemblies, as applicable. This proposed 

AD is prompted by reports of injuries to 

catering personnel and flight attendants 

who were loading or unloading galley 

carts on one deck when the galley cart 

lift unexpectedly moved when it was 

activated from the other deck. We are 

proposing this AD to ensure that the 

galley cart lift can be sent only from the 

deck on which it is in use, which will 

prevent unexpected movement of the 

cart lift that could result in possible 

injury to catering personnel or flight 

attendants.

DATES: We must receive comments on 

this proposed AD by December 20, 

2004.

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. 

• By 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–2004–

19532; the directorate identifier for this 

docket is 2004–NM–87–AD.

FOR FURTHER INFORMATION CONTACT: 

Technical Information: Donald Wren, 

Aerospace Engineer, Cabin Safety and 

Environmental Systems Branch, ANM–

150S, FAA, Seattle Aircraft Certification 

Office, 1601 Lind Avenue, SW., Renton, 

Washington 98055–4056; telephone 

(425) 917–6451; fax (425) 917–6590. 

Plain Language Information: Marcia 

Walters, marcia.walters@faa.gov.

SUPPLEMENTARY INFORMATION: 

Docket Management System (DMS) 

The FAA has implemented new 

procedures for maintaining AD dockets 

electronically. As of May 17, 2004, new 

AD actions are posted on DMS and 

assigned a docket number. We track 

each action and assign a corresponding 

directorate identifier. The DMS AD 

docket number is in the form ‘‘Docket 

No. FAA–2004–99999.’’ The Transport 

Airplane Directorate identifier is in the 

form ‘‘Directorate Identifier 2004–NM–

999–AD.’’ Each DMS AD docket also 

lists the directorate identifier (‘‘Old 

Docket Number’’) as a cross-reference 

for searching purposes. 

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–

2004–19532; Directorate Identifier 

2004–NM–87–AD’’ in the subject line 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 submitted 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