Federal Register / Vol. 69, No. 214 / Friday, November 5, 2004 / Proposed Rules 64513

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):

McDonnell Douglas: Docket No. FAA–2004–

19541; Directorate Identifier 2004–NM–

129–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 all 

McDonnell Douglas Model DC–8 airplanes, 

certificated in any category. 

Unsafe Condition 

(d) This AD was prompted by an accident 

involving a DC–8 airplane. The probable 

cause of the accident was a loss of pitch 

control resulting from the disconnection of 

the pushrod for the right elevator control tab. 

The pushrod dropped down and jammed in 

front of the control tab crank, causing a large 

deflection of the control tab. We are issuing 

this AD to minimize the possibility of a 

control tab offset. A control tab offset could 

cause elevator deflection, an elevator 

airplane-nose-up condition, and reduced 

controllability of the airplane. This AD was 

also prompted by a report that the elevator 

on a McDonnell Douglas Model DC–8 

airplane did not respond to command inputs 

from the flightcrew. We are also issuing this 

AD to minimize the possibility of a crank 

assembly failure when the assembly is 

exposed to abnormal load conditions. Failure 

of a crank assembly could result in a jammed 

elevator and consequent reduced 

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. 

Inspection of Pushrod Assemblies and Other 

Specified Actions 

(f) Within 24 months after the effective 

date of this AD: Do an inspection of the 

pushrod assemblies located in the left and 

right elevator control tabs to determine 

whether the assemblies are made of 

aluminum or steel. Replace any pushrod 

assembly made of aluminum with a new, 

improved pushrod assembly made of steel, or 

modify any existing steel pushrod assembly 

by replacing the aft end assembly with a new, 

improved aft end assembly, as applicable. Do 

the inspection, replacement or modification, 

and all other applicable specified actions by 

accomplishing all of the actions in the 

Accomplishment Instructions of Boeing Alert 

Service Bulletin DC8–27A281, dated June 2, 

2004. The replacement or modification and 

other applicable specified actions must be 

done before further flight. 

Inspection of Geared Tab Crank Assemblies 

and Other Specified Actions 

(g) Within 24 months after the effective 

date of this AD: Do an inspection of the 

inboard and outboard geared tab crank 

assemblies, located in the left and right 

elevators, to determine whether the 

assemblies are made of aluminum or steel. 

Replace any crank assembly made of 

aluminum with a new, improved crank 

assembly made of steel. Do the inspection, 

replacement, and other applicable specified 

actions by accomplishing all of the actions in 

the Accomplishment Instructions of Boeing 

Alert Service Bulletin DC8–27A280, dated 

June 2, 2004. The replacement and other 

applicable specified actions must be done 

before further flight. 

Alternative Methods of Compliance 

(AMOCs) 

(h) The Manager, Los Angeles Aircraft 

Certification Office, FAA, has the authority to 

approve AMOCs for this AD, if requested in 

accordance with 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. 04–24729 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–2004–19540; Directorate 

Identifier 2004–NM–110–AD] 

RIN 2120–AA64

Airworthiness Directives; Boeing 

Model 757 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 757 airplanes. 

This proposed AD would require 

inspections of certain wire bundles in 

the left and right engine-to-wing aft 

fairings for discrepancies, and other 

specified and corrective actions. This 

proposed AD is prompted by a report 

indicating that a circuit breaker for the 

fuel shutoff valve tripped due to a wire 

that chafed against the structure in the 

flammable leakage zone of the aft 

fairing, causing a short circuit. We are 

proposing this AD to prevent chafing 

between the wire bundle and the 

structure of the aft fairing, which could 

result in electrical arcing and 

subsequent ignition of flammable vapors 

and possible uncontrollable fire.

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 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: Thomas 

Thorson, Aerospace Engineer, 

Propulsion Branch, ANM–140S, FAA, 

Seattle Aircraft Certification Office, 

1601 Lind Avenue, SW., Renton, 

Washington 98055–4056; telephone 

(425) 917–6508; 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 

64514 Federal Register / Vol. 69, No. 214 / Friday, November 5, 2004 / Proposed Rules 

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–

2004–19540; Directorate Identifier 

2004–NM–110–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 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 a report indicating 

that a circuit breaker of the fuel shutoff 

valve tripped due to a wire that chafed 

against the structure in the flammable 

leakage zone of the aft fairing, causing 

a short circuit. This occurred on a 

Boeing Model 757–200 series airplane 

that had accumulated approximately 

10,900 total flight hours and 6,225 total 

flight cycles. Subsequent maintenance 

inspections of the remainder of the 

operator’s fleet revealed 9 out of 13 

airplanes had the same type of wire 

chafing. The causes of that chafing were 

missing or incorrectly installed wire 

sleeving, incorrect grommet installation, 

and incorrect wire clamp installation. 

The existing design allows contact 

between the wire bundle and the engine 

strut webs. Chafing between the wire 

bundle and the structure of the aft 

fairing could result in electrical arcing 

and subsequent ignition of flammable 

vapors and possible uncontrollable fire. 

The wire bundles of the fuel shutoff 

valves on Model 757–200PF, –200CB, 

and –300 series airplanes are identical 

to those on the affected Model 757–200 

series airplanes. Therefore, all of these 

models may be subject to the same 

unsafe condition. 

Relevant Service Information 

We have reviewed Boeing Alert 

Service Bulletins 757–28A0073 (for 

Model 757–200, –200CB, and –200PF 

series airplanes) and 757–28A0074 (For 

Model 757–300 series airplanes), both 

dated November 20, 2003. The service 

bulletins describe procedures for 

inspecting for discrepancies of the wire 

bundles (W5100 for the left engine strut; 

W5200 for the right engine strut) from 

power plant station (PP STA) 278 aft, to 

the rear spar of the wing in the left and 

right engine-to-wing aft fairings, and 

other specified and corrective actions. 

The discrepancies include chafing of the 

wire bundles, missing or chafed sleeves, 

and incorrect installation of the 

caterpillar grommet. The procedures for 

the other specified and corrective 

actions include: 

• Repairing any damage found, in 

addition to installing a new support 

bracket. 

• Inspecting for chafed or missing 

sleeves at PP STA 278, 290, and 301, 

and adding a new wrap-on sleeve if the 

sleeve is chafed or missing. 

• Inspecting the PP STA 278 and 301 

bulkheads to ensure correct installation 

of the caterpillar grommet, and cleaning 

the area and installing a new grommet 

if the grommet is missing or incorrectly 

installed; and 

• Re-routing the wire bundles. 

The service bulletins also describe 

procedures for a functional test of the 

engine fuel shutoff valves. 

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 

accomplishing the actions specified in 

the service information described 

previously. 

Clarification of Inspection Terminology 

In this proposed AD, the 

‘‘inspections’’ of the wire bundles, as 

specified in the Boeing service bulletins 

are referred to as ‘‘detailed inspections.’’

We have included the definition for a 

detailed inspection in a note in the 

proposed AD. 

Costs of Compliance 

This proposed AD would affect about 

613 airplanes worldwide and 335 

airplanes of U.S. registry. The proposed 

actions would take about 16 work hours 

per airplane, at an average labor rate of 

$65 per work hour. Required parts 

would cost about $560 per airplane. 

Based on these figures, the estimated 

cost of the proposed AD for U.S. 

operators is $536,000, or $1,600 per 

airplane. 

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.

Federal Register / Vol. 69, No. 214 / Friday, November 5, 2004 / Proposed Rules 64515

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–2004–19540; 

Directorate Identifier 2004–NM–110–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 Model 757–200, 

–200PF, –200CB, and –300 series airplanes; 

certificated in any category; as listed in 

Boeing Alert Service Bulletins 757–28A0073 

and 757–28A0074, both dated November 20, 

2003. 

Unsafe Condition 

(d) This AD was prompted by a report 

indicating that a circuit breaker for the fuel 

shutoff valve tripped due to a wire that 

chafed against the structure in the flammable 

leakage zone of the aft fairing, causing a short 

circuit. We are issuing this AD to prevent 

chafing between the wire bundle and the 

structure of the aft fairing, which could result 

in electrical arcing and subsequent ignition 

of flammable vapors and possible 

uncontrollable fire. 

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. 

One-Time Inspections/Investigative and 

Corrective Actions 

(f) Within 60 months after the effective 

date of this AD: Accomplish the detailed 

inspections for discrepancies of the wire 

bundles in the left and right engine-to-wing 

aft fairings, and other specified and 

corrective actions, as applicable, by doing all 

the actions in the Accomplishment 

Instructions of Boeing Alert Service Bulletin 

757–28A0073 (for Model 757–200, –200CB, 

and –200PF series airplanes) or 757–28A0074 

(for Model 757–300 series airplanes), both 

dated November 20, 2003; as applicable. Any 

corrective actions must be done before 

further flight and in accordance with the 

applicable service bulletin.

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) 

(g) 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.

Issued in Renton, Washington, on October 

27, 2004. 

Ali Bahrami, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service.

[FR Doc. 04–24728 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–2004–19539; Directorate 

Identifier 2004–NM–06–AD] 

RIN 2120–AA64

Airworthiness Directives; Boeing 

Model 737 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 airplanes. 

This proposed AD would require, for 

certain airplanes, a one-time detailed 

inspection for interference between a 

clamp assembly and the wires behind 

the P15 refuel panel, and corrective 

actions if necessary. For certain other 

airplanes, this proposed AD would 

require a one-time detailed inspection 

for discrepancies of the wires behind 

the P15 refuel panel; and corrective and 

related investigative actions if 

necessary. This proposed AD is 

prompted by evidence of chafed wiring 

behind the P15 refuel panel and arcing 

to the back of the P15 refuel panel and 

adjacent wing structure. We are 

proposing this AD to detect and correct 

chafing of the wiring behind the P15 

refuel panel, which could lead to arcing 

and fire with consequent airplane 

damage and injury to refueling 

personnel.

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–

19539; the directorate identifier for this 

docket is 2004–NM–06–AD.

FOR FURTHER INFORMATION CONTACT: 

Technical information: Sherry Vevea, 

Aerospace Engineer, Propulsion Branch, 

ANM–140S, FAA, Seattle Aircraft 

Certification Office, 1601 Lind Avenue, 

SW., Renton, Washington 98055–4056; 

telephone (425) 917–6514; 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.