75270 Federal Register / Vol. 69, No. 241 / Thursday, December 16, 2004 / Proposed Rules 

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 2000–26–04

Modification 

(f) Within 6 years after February 2, 2001 

(the effective date of AD 2000–26–04, 

amendment 39–12054), accomplish 

paragraphs (f)(1), (f)(2), and (f)(3) of this AD; 

in accordance with Boeing Service Bulletin 

747–25–3253, dated June 29, 2000, or 

Revision 3, dated September 4, 2003; 757–

25–0226, dated July 3, 2000, or Revision 3, 

dated September 2, 2004; 757–25–0228, 

dated July 3, 2000; 767–25–0290, dated June 

29, 2000, or Revision 4, dated October 28, 

2004; or 777–25–0164, dated June 29, 2000; 

as applicable; except as provided by 

paragraph (g) of this AD. For Model 757–200, 

–200CB, and –200PF series airplanes subject 

to Boeing Service Bulletin 757–25–0226: As 

of the effective date of this AD, only Revision 

3 of the service bulletin may be used. For 

Model 747 and 767 series airplanes: As of the 

effective date of this AD, only Boeing Service 

Bulletin 747–25–3253, Revision 3, or 767–

25–0290, Revision 4, as applicable, may be 

used. 

(1) Modify drip shields located on the 

flight deck by installing fire blocks. 

(2) Prior to further flight following 

accomplishment of paragraph (f)(1) of this 

AD, perform a functional test of any system 

disturbed by the modification, in accordance 

with the applicable service bulletin or the 

Airplane Maintenance Manual (AMM), as 

applicable. If any functional test fails, prior 

to further flight, isolate the fault, correct the 

discrepancy in accordance with the 

applicable AMM, and repeat the failed test 

until it is successfully accomplished. 

(3) Prior to further flight following the 

accomplishment of paragraphs (f)(1) and 

(f)(2) of this AD, install placards on all 

modified drip shields. 

(g) If any wires or equipment are installed 

on the outboard surface of the drip shield 

(that is, between the drip shield and the 

airplane structure), modify that area in 

accordance with a method approved by the 

Manager, Seattle Aircraft Certification Office 

(ACO), FAA. 

Optional Sampling (Certain Model 747 Series 

Airplanes) 

(h) For Model 747 series airplanes listed in 

Group 1 in Boeing Service Bulletin 747–25–

3253, Revision 3, dated September 4, 2003: 

In lieu of accomplishing paragraph (f) of this 

AD, within 6 years after February 2, 2001, 

collect samples of the insulation and 

adhesive of the drip shields, and submit the 

samples to the manufacturer for testing, in 

accordance with the Accomplishment 

Instructions of Boeing Service Bulletin 747–

25–3253, dated June 29, 2000, or Revision 3, 

dated September 4, 2003. After the effective 

date of this AD, only Revision 3 may be used.

(1) If the test on all samples is positive, no 

further action is required by this AD. 

(2) If the test on any sample is negative, 

accomplish paragraph (f) of this AD before 

the compliance time specified in that 

paragraph. 

New Requirements of This AD 

Model 757–200, –200CB –200PF Series 

Airplanes Previously Modified 

(i) For Model 757–200, –200CB, and 

–200PF series airplanes that were modified 

before the effective date of this AD in 

accordance with Boeing Service Bulletin 

757–25–0226, dated July 3, 2000: Within 6 

years after the effective date of this AD, 

modify drip shields located above windows 

number 2 and 3 on the flight deck by 

installing fire blocks, in accordance with the 

Accomplishment Instructions of Boeing 

Service Bulletin 757–25–0226, Revision 3, 

dated September 2, 2004; except as provided 

by paragraph (g) of this AD. After the 

modification, do the actions required by 

paragraph (f)(2) and (f)(3) of this AD as these 

actions apply to the drip shields modified in 

accordance with this paragraph. 

Previously Accomplished Actions 

(j) Modifying the drip shields before the 

effective date of this AD in accordance with 

the applicable service bulletin specified in 

paragraph (j)(1) or (j)(2) of this AD is 

acceptable for compliance with the 

corresponding requirements of paragraphs (f) 

and (i) of this AD, as applicable. 

(1) For Model 757–200, –200CB, and 

–200PF series airplanes: Boeing Service 

Bulletin 757–25–0226, Revision 2, dated 

October 31, 2002. 

(2) For Model 767 series airplanes: Boeing 

Service Bulletin 767–25–0290, Revision 3, 

dated June 26, 2003. 

Alternative Methods of Compliance (AMOCs) 

(k)(1) 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. 

(2) Except for Model 757–200, –200CB, and 

–200PF series airplanes listed in Boeing 

Service Bulletin 757–25–0226, Revision 3, 

dated September 2, 2004: Alternative 

methods of compliance, approved previously 

in accordance with AD 2000–26–04, 

amendment 39–12054, are approved as 

alternative methods of compliance with this 

AD.

Issued in Renton, Washington, on 

December 6, 2004. 

Ali Bahrami, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service.

[FR Doc. 04–27503 Filed 12–15–04; 8:45 am] 

BILLING CODE 4910–13–P

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2004–19866; Directorate 

Identifier 2004–NM–25–AD] 

RIN 2120–AA64 

Airworthiness Directives; Boeing 

Model 767–200, –300, and –300F 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 767–200, –300, 

and –300F series airplanes. This 

proposed AD would require verifying 

the part and serial numbers of certain 

main landing gear (MLG) bogie beam 

pivot pins; replacing those pivot pins 

with new or overhauled pivot pins if 

necessary; and ultimately replacing all 

pivot pins with new, improved pivot 

pins. This proposed AD is prompted by 

reports indicating that numerous 

fractures of the MLG bogie beam pivot 

pin have been found and that some 

pivot pins may have had improper 

rework during manufacture. We are 

proposing this AD to prevent fracture of 

the MLG bogie beam pivot pin, which 

could lead to possible loss of the MLG 

truck during takeoff or landing and 

consequent loss of control of the 

airplane.

DATES: We must receive comments on 

this proposed AD by January 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. 

• 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. 

Federal Register / Vol. 69, No. 241 / Thursday, December 16, 2004 / Proposed Rules 75271

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–

19866; the directorate identifier for this 

docket is 2004–NM–25–AD.

FOR FURTHER INFORMATION CONTACT: 

Technical information: Suzanne 

Masterson, Aerospace Engineer, 

Airframe Branch, ANM–120S, FAA, 

Seattle Aircraft Certification Office, 

1601 Lind Avenue, SW., Renton, 

Washington 98055–4056; telephone 

(425) 917–6441; 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 written 

relevant data, views, or arguments 

regarding this proposed AD. Send your 

comments to an address listed under 

ADDRESSES. Include ‘‘Docket No. FAA–

2004–19866; Directorate Identifier 

2004–NM–25–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 can 

review 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.

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 reports indicating 

that numerous fractures of the main 

landing gear (MLG) bogie beam pivot 

pin have been found on certain Boeing 

Model 767–200 and –300 series 

airplanes. In four cases, a portion of the 

pin and the uplock fitting departed the 

airplane. The airplane manufacturer 

determined that the fractures are 

probably due to cracks initiating in 

areas of heat damage and propagating 

due to fatigue. Also, one supplier of 

pivot pins to the airplane manufacturer 

has reported that some pivot pins may 

have had improper rework during 

manufacture, which could have caused 

heat damage, cracks, or other defects. 

Fracture of the pivot pin, if not 

corrected, could lead to possible loss of 

the MLG truck during takeoff or landing 

and consequent loss of control of the 

airplane. 

The MLG on certain Model 767–300F 

series airplanes is identical to that on 

the affected Model 767–200 and –300 

series airplanes. Therefore, certain 

Model 767–300F series airplanes may be 

subject to the same unsafe condition 

revealed on the Model 767–200 and 

–300 series airplanes. 

Relevant Service Information 

We have reviewed Boeing Alert 

Service Bulletin 767–32A0202, dated 

July 22, 2004. The service bulletin 

describes procedures for a check of the 

part numbers and serial numbers of 

certain MLG bogie beam pivot pins and 

replacing discrepant pivot pins with 

new pins or overhauled pins that 

include a chrome plate strip as part of 

the pin overhaul, and for reporting the 

inspection results and numbers of 

suspect pivot pins to Boeing. 

We have also reviewed Boeing Service 

Bulletin 767–32A0199, Revision 1, 

dated July 22, 2004. The service bulletin 

describes procedures for replacing the 

MLG bogie beam pivot pin with a new, 

improved pivot pin. The service bulletin 

specifies a compliance time for these 

actions of 6–10 years since the pivot pin 

was new or overhauled (depending 

upon airplane group), or 18 months after 

the original issue date of the service 

bulletin, whichever occurs later. 

Accomplishing the actions in Service 

Bulletin 767–32A0199, Revision 1, 

eliminates the need to do the actions in 

Service Bulletin 767–32A0202. 

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. Therefore, we are 

proposing this AD, which would require 

replacement of the MLG bogie beam 

pivot pin with a new, improved pivot 

pin. The proposed AD would require 

you to use the service information 

described previously to perform these 

actions, except as discussed under 

‘‘Difference Between the Proposed AD 

and Service Bulletins.’’ The proposed 

AD would also require sending the 

inspection results to the manufacturer. 

Difference Between the Proposed AD 

and Service Bulletins 

The referenced service bulletins 

specify compliance times relative to the 

date of the original issue of the service 

bulletins; however, this proposed AD 

would require compliance times relative 

to the effective date of the AD. 

Costs of Compliance 

This proposed AD would affect about 

374 airplanes of U.S. registry and 857 

airplanes worldwide.

The proposed inspection would take 

about 1 work hour per airplane, at an 

average labor rate of $65 per work hour. 

Based on these figures, the estimated 

cost of the proposed inspection for U.S. 

operators is $55,705, or $65 per 

airplane. 

75272 Federal Register / Vol. 69, No. 241 / Thursday, December 16, 2004 / Proposed Rules 

The proposed pin replacement would 

take about 12 work hours per airplane, 

at an average labor rate of $65 per work 

hour. Required parts would cost about 

$35,134 per airplane. Based on these 

figures, the estimated cost of the 

proposed pin replacement for U.S. 

operators is $13,431,836 or $35,914 per 

airplane. 

Authority for This Rulemaking 

The FAA’s authority to issue rules 

regarding aviation safety is found in 

Title 49 of the United States Code. 

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. 

This rulemaking is promulgated 

under the authority described in subtitle 

VII, part A, subpart III, section 44701, 

‘‘General requirements.’’ Under that 

section, the FAA is charged with 

promoting safety 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 

proposed AD. 

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–2004–19866; 

Directorate Identifier 2004–NM–25–AD. 

Comments Due Date 

(a) The Federal Aviation Administration 

(FAA) must receive comments on this AD 

action by January 31, 2005. 

Affected ADs 

(b) None. 

Applicability 

(c) This AD applies to Boeing Model 767–

200, –300, and –300F series airplanes, 

certificated in any category, as specified in 

Boeing Alert Service Bulletin 767–32A0202, 

and Boeing Alert Service Bulletin 767–

32A0199, Revision 1, both dated July 22, 

2004. 

Unsafe Condition 

(d) This AD was prompted by reports 

indicating that numerous fractures of the 

main landing gear (MLG) bogie beam pivot 

pin have been found and that some pivot 

pins may have had improper rework during 

manufacture. We are issuing this AD to 

prevent fracture of the MLG bogie beam pivot 

pin, which could lead to possible loss of the 

MLG truck during takeoff or landing and 

consequent loss of control 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. 

Pin Inspection, Short-Term Replacement, 

and Discrepancy Reporting 

(f) Within 6 months after the effective date 

of this AD, do an inspection of the part and 

serial numbers of the MLG bogie beam pivot 

pin in accordance with the Accomplishment 

Instructions of Boeing Alert Service Bulletin 

767–32A0202, dated July 22, 2004. 

(1) If the serial number of the pivot pin 

contains the letters ‘‘MA’’ or ‘‘MAM’’, no 

further action is required by this paragraph. 

(2) If any pivot pin has a part and serial 

number as listed in figure 1 of the service 

bulletin, prior to further flight, remove and 

overhaul the pivot pin, or replace it with a 

new pivot pin or an overhauled pivot pin 

that includes a chrome plate strip as part of 

the pin overhaul; in accordance with the 

service bulletin. 

(g) If any pivot pin has a part and serial 

number as listed in figure 1 of the service 

bulletin, submit a report of the inspection 

required by paragraph (f) of this AD to the 

Manager, Airline Support, Boeing 

Commercial Airplanes, P.O. Box 3707, 

Seattle, Washington 98124–2207, at the 

applicable time specified in paragraph (g)(1) 

or (g)(2) of this AD. The report must include 

the part and serial number of the pivot pin, 

a description of any discrepancies found, the 

airplane serial number, and the number of 

landings and flight hours on the airplane. 

Under the provisions of the Paperwork 

Reduction Act of 1980 (44 U.S.C. 3501 et 

seq.), the Office of Management and Budget 

(OMB) has approved the information 

collection requirements contained in this AD 

and has assigned OMB Control Number 

2120–0056. 

(1) If the inspection was done after the 

effective date of this AD: Submit the report 

within 30 days after the inspection. 

(2) If the inspection was done before the 

effective date of this AD: Submit the report 

within 30 days after the effective date of this 

AD. 

Final Pin Replacement 

(h) Replace any MLG bogie beam pivot pin 

having part number (P/N) 161T1145–2, –3, or 

–4, with a new, improved pivot pin having

P/N 161T1145–5, in accordance with the 

Accomplishment Instructions of Boeing Alert 

Service Bulletin 767–32A0199, Revision 1, 

dated July 22, 2004. Do the replacement 

within the applicable compliance times 

specified in paragraph 1.E., ‘‘Compliance,’’ of 

the service bulletin; except, where the service 

bulletin specifies a compliance time after the 

original issue date of the service bulletin, this 

AD specifies compliance time after the 

effective date of this AD. 

(i) Airplanes on which the replacement 

required by paragraph (h) of this AD is 

performed within the compliance time 

specified in paragraph (f) of this AD are not 

required to accomplish the inspection 

required by paragraph (f). 

Final Pin Replacement per Previous Issue of 

Service Bulletin 

(j) Replacing any pivot pin before the 

effective date of this AD in accordance with 

Boeing Alert Service Bulletin 767–32A0199, 

dated April 8, 2004, is considered acceptable 

for compliance with the corresponding action 

specified in this AD. 

Part Installation 

(k) As of the effective date of this AD, no 

person may install on any airplane a MLG 

bogie beam pivot pin having part number

(P/N) 161T1145–2, –3, or –4, except in 

accordance with paragraph (f)(2) of this AD. 

Alternative Methods of Compliance 

(AMOCs) 

(l)(1) The Manager, Seattle Aircraft 

Certification Office (ACO), FAA, has the 

authority to approve AMOCs for this AD, if 

requested using 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 a 

Boeing Company Designated Engineering 

Federal Register / Vol. 69, No. 241 / Thursday, December 16, 2004 / Proposed Rules 75273

Representative who has been authorized by 

the Manager, Seattle ACO, to make such 

findings.

Issued in Renton, Washington, on 

December 6, 2004. 

Ali Bahrami, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service.

[FR Doc. 04–27504 Filed 12–15–04; 8:45 am] 

BILLING CODE 4910–13–P

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2004–19863; Directorate 

Identifier 2003–NM–29–AD] 

RIN 2120–AA64 

Airworthiness Directives; Airbus Model 

A319, A320, and A321 Series Airplanes

AGENCY: Federal Aviation 

Administration (FAA), DOT.

ACTION: Notice of proposed rulemaking 

(NPRM). 

SUMMARY: The FAA proposes to 

supersede an existing airworthiness 

directive (AD) that applies to certain 

Airbus Model A319, A320, and A321 

series airplanes. The existing AD 

currently requires modification of the 

telescopic girt bar of the escape slide/

raft assembly, and follow-on actions. 

This proposed AD would mandate a 

new modification of the telescopic girt 

bar, which would terminate the 

repetitive functional tests required by 

the existing AD. This proposed AD 

would also expand the applicability of 

the existing AD. This proposed AD is 

prompted by development of a new, 

improved modification. We are 

proposing this AD to prevent failure of 

the escape slide/raft to deploy correctly, 

which could result in the slide being 

unusable during an emergency 

evacuation and consequent injury to 

passengers or airplane crewmembers.

DATES: We must receive comments on 

this proposed AD by January 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 Airbus, 1 

Rond Point Maurice Bellonte, 31707 

Blagnac Cedex, France. 

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.

FOR FURTHER INFORMATION CONTACT: 

Technical information: Tim Dulin, 

Aerospace Engineer, International 

Branch, ANM–116, FAA, Transport 

Airplane Directorate, 1601 Lind 

Avenue, SW., Renton, Washington 

98055–4056; telephone (425) 227–2141; 

fax (425) 227–1149. 

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–

2004–19863; Directorate Identifier 

2003–NM–29–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 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. 

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 

On August 9, 2001, the FAA issued 

AD 2001–16–14, amendment 39–12383 

(66 FR 42939, August 16, 2001). That 

AD applies to certain Airbus Model 

A319, A320, and A321 series airplanes, 

and requires modifying the telescopic 

girt bar of the escape slide/raft 

assembly, and follow-on actions. That 

AD was prompted by several reports of 

the telescopic girt bar of the slide/raft 

assembly detaching from the door sill 

fittings and preventing proper 

deployment of the emergency escape 

slide. The requirements of that AD are 

intended to prevent failure of the escape 

slide/raft to deploy correctly, which 

could result in the slide being unusable 

during an emergency evacuation and 

consequent injury to passengers or 

airplane crewmembers. 

Actions Since Existing AD Was Issued 

The preamble to AD 2001–16–14 

specified that we considered the 

requirements ‘‘interim action’’ and that 

the manufacturer was developing a new 

modification to address the unsafe