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.

64516 Federal Register / Vol. 69, No. 214 / Friday, November 5, 2004 / Proposed Rules 

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–

2004–19539; Directorate Identifier 

2004–NM–06–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 reports indicating 

that operators of two Boeing Model 737–

700 series airplanes and one Model 

737–300 series airplane were unable to 

refuel the airplanes automatically due to 

tripped circuit breakers that couldn’t be 

reset. The operators discovered 

evidence of chafed wiring due to 

rubbing of wires against sharp edges and 

components behind the P15 refuel 

panel, and signs of arcing to the back of 

the P15 refuel panel and adjacent wing 

structure. This condition, if not 

corrected, could lead to arcing and fire 

with consequent airplane damage and 

injury to refueling personnel. 

Relevant Service Information 

We have reviewed Boeing Special 

Attention Service Bulletin 737–28–

1193, dated April 24, 2003 (for Model 

737–100, –200, –200C, –300, –400, and 

–500 series airplanes). The service 

bulletin describes procedures for 

performing a visual inspection of the 

wires in wire bundle W0024 to 

connector D04578P on the back of the 

P15 refuel panel for discrepancies, 

which would include chafed or burned 

wires, signs of arcing to the back of the 

P15 refuel panel and adjacent wing 

structure, and loose or untied wires and 

excessive wire loops. The service 

bulletin also describes procedures for 

corrective and related investigative 

actions if any discrepancy is found. 

Corrective actions include tying and 

rerouting wires and wire bundle away 

from sharp edges and components 

behind the P15 refuel panel; repairing or 

replacing any chafed or burned wires; 

and installing Teflon sleeves around the 

wires as needed for additional 

protection against chafing. The related 

investigative action includes measuring 

the electrical bonding resistance to the 

P15 panel and performing an 

operational test of the refuel quantity 

indicators and valve position lights. 

We have also reviewed Boeing Special 

Attention Service Bulletin 737–28–

1200, dated July 10, 2003 (for Model 

737–600, –700, –700C, –800, and –900 

series airplanes). For Group 1 and 

Group 2 airplanes, the service bulletin 

describes procedures for a detailed 

inspection for discrepancies of the 

clamp and T-bolt assembly on the wing 

thermal anti-ice (TAI) duct near the P15 

refuel panel. For Group 2 airplanes 

only, the service bulletin also describes 

a detailed inspection of the wires in 

wire bundle W0024 to connector 

D04578P on the back of the P15 refuel 

panel for discrepancies such as 

inadequate clearance between wires and 

sharp edges, chafed or burned wires, or 

signs of arcing to the back of the P15 

refuel panel and adjacent wing 

structure. This service bulletin also 

describes procedures for corrective and 

related investigative actions, which 

include repositioning of the clamp and 

T-bolt assembly on the TAI duct and 

performing a leak check of the TAI duct; 

and, as applicable, repairing or 

replacing any chafed or burned wires; 

measuring the electrical bonding 

resistance to the P15 refuel panel; and 

performing a functional test of the refuel 

quantity indicators, refuel valve 

switches, and valve position lights. 

Accomplishment of the actions 

specified in the service bulletins 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, 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 actions 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 

Referenced Service Bulletins.’’

Differences Between the Proposed AD 

and Referenced Service Bulletins 

Boeing Special Attention Service 

Bulletin 737–28–1200, dated July 10, 

2003, specifies a compliance time of 24 

months from the release date of the 

service bulletin; while Special Attention 

Service Bulletin 737–28–1193, dated 

April 24, 2003, specifies a compliance 

time of 18 months from the release date 

of the service bulletin. We have 

determined that the unsafe condition is 

sufficiently hazardous that a compliance 

time of 18 months after the effective 

date of this proposed AD is appropriate 

for all affected airplanes. This difference 

has been coordinated with Boeing. 

Although Boeing Special Attention 

Service Bulletin 737–28–1193, dated 

April 24, 2003, specifies a ‘‘visual 

check,’’ this proposed AD would require 

a ‘‘detailed inspection.’’ We have 

included Note 1 in this proposed AD to 

define that inspection. 

Costs of Compliance 

This proposed AD would affect about 

1,653 airplanes of U.S. registry and 

4,254 airplanes worldwide. The 

proposed inspections would take about 

3 work hours per airplane, at an average 

labor rate of $65 per work hour. Based 

Federal Register / Vol. 69, No. 214 / Friday, November 5, 2004 / Proposed Rules 64517

on these figures, the estimated cost of 

the proposed AD for U.S. operators is 

$322,335, or $195 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.

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–2004–19539; 

Directorate Identifier 2004–NM–06–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 the Boeing airplanes 

listed in Table 1 of this AD, certificated in 

any category:

TABLE 1.—APPLICABILITY

Airplane Line numbers 

Model 737–100, –200, –200C, –300, –400, and –500 series airplanes ........................................................ 1 through 3132 inclusive. 

Model 737–600, –700, –700C, –800, and –900 series airplanes .................................................................. 0001 through 1240 inclusive. 

Unsafe Condition 

(d) This AD was 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 issuing 

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. 

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 and Corrective Actions 

(f) Within 18 months after the effective 

date of this AD, perform the following 

actions as applicable: 

(1) For Model 737–100, –200, –200C, –300, 

–400, and –500 series airplanes: Perform a 

one-time detailed inspection of the wires in 

wire bundle W0024 to connector D04578P on 

the back of the P15 refuel panel for 

discrepancies, and do any applicable 

corrective and related investigative actions 

before further flight, in accordance with the 

Accomplishment Instructions of Boeing 

Special Attention Service Bulletin 737–28–

1193, dated April 24, 2003. 

(2) For Model 737–600, –700, –700C, –800, 

and –900 series airplanes: Perform all 

applicable actions listed in paragraphs 

(f)(2)(i) and (f)(2)(ii) of this AD in accordance 

with the Accomplishment Instructions of 

Boeing Special Attention Service Bulletin 

737–28–1200, dated July 10, 2003. 

(i) For Group 1 and Group 2 airplanes as 

defined in Service Bulletin 737–28–1200: 

Perform a one-time detailed inspection for 

discrepancies of the clamp and T-bolt 

assembly on the wing thermal anti-ice duct 

near the P15 refuel panel and do any 

applicable corrective actions before further 

flight. 

(ii) For Group 2 airplanes only: Perform a 

one-time detailed inspection for 

discrepancies of the wires in wire bundle 

W0024 to connector D04578P on the back of 

the P15 refuel panel and do any applicable 

corrective actions before further flight.

Note 1: For the purposes of this AD, a 

detailed inspection is: ‘‘An intensive visual 

examination of a specific structural area, 

system, installation, or assembly to detect 

damage, failure, or irregularity. Available 

lighting is normally supplemented with a 

direct source of good lighting at intensity 

deemed appropriate by the inspector. 

Inspection aids such as mirror, magnifying 

lenses, etc., may be used. Surface cleaning 

and elaborate access 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 

26, 2004. 

Ali Bahrami, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service.

[FR Doc. 04–24727 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–2004–19538; Directorate 

Identifier 2003–NM–99–AD] 

RIN 2120–AA64

Airworthiness Directives; Boeing 

Model 747 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) for certain Boeing Model 

747 series airplanes. That AD currently 

requires inspections to detect cracks in 

the front spar pressure bulkhead chord, 

and repair, if necessary. This proposed 

AD would require repetitive high 

frequency eddy current (HFEC) 

inspections of the body station (BS) 

1000 bulkhead chord for cracks, 

repetitive detailed inspections of the 

bathtub fittings, if installed, for cracks, 

and corrective action, if necessary. 

Accomplishment of new inspections 

would end the inspections of the 

existing AD. This proposed AD would 

also revise the applicability of the 

existing AD to include additional