Federal Register / Vol. 70, No. 162 / Tuesday, August 23, 2005 / Proposed Rules 49215

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 Federal Aviation 

Administration (FAA) amends § 39.13 

by adding the following new 

airworthiness directive (AD):

Airbus: Docket No. FAA–2005–22170; 

Directorate Identifier 2005–NM–073–AD. 

Comments Due Date 

(a) The FAA must receive comments on 

this AD action by September 22, 2005. 

Affected ADs 

(b) None. 

Applicability 

(c) This AD applies to Airbus Model A320–

111, –211, –212, and –231 airplanes, 

certificated in any category, that have not 

received Airbus Modification 21088 or 21999 

in production; and airplanes that have 

received Airbus Modification 21088 in 

production and have manufacturer’s serial 

number 91 to 113 inclusive and 140 to 189 

inclusive. 

Unsafe Condition 

(d) This AD results from fuel systems 

reviews conducted by the manufacturer. We 

are issuing this AD to prevent chafing of the 

fuel pump cables, which could result in 

electrical arcing and possible ignition of fuel 

vapors and consequent explosion of the fuel 

tank. 

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 Modification of Fuel Pump 

Access Holes 

(f) Within 58 months after the effective 

date of this AD, perform the actions required 

by paragraph (f)(1) or (f)(2) of this AD, as 

applicable. 

(1) For airplanes that have not received 

Airbus Modification 21088 or 21999 in 

production: Modify the cables and access 

holes to the inner tank fuel pumps, in 

accordance with the Accomplishment 

Instructions of Airbus Service Bulletin A320–

28–1008, Revision 1, dated April 10, 1989. 

(2) For airplanes that have received Airbus 

Modification 21088 in production and have 

manufacturer’s serial number 91 to 113 

inclusive and 140 to 189 inclusive: Perform 

a general visual inspection for the correct 

radius of the fuel pump access holes and 

modify the access holes, if necessary, in 

accordance with the Accomplishment 

Instructions of Airbus Service Bulletin A320–

28–1054, dated August 23, 1993. Do any 

applicable repairs before further flight.

Note 1: For the purposes of this AD, a 

general visual inspection is: ‘‘A visual 

examination of an interior or exterior area, 

installation, or assembly to detect obvious 

damage, failure, or irregularity. This level of 

inspection is made from within touching 

distance unless otherwise specified. A mirror 

may be necessary to ensure visual access to 

all surfaces in the inspection area. This level 

of inspection is made under normally 

available lighting conditions such as 

daylight, hangar lighting, flashlight, or 

droplight and may require removal or 

opening of access panels or doors. Stands, 

ladders, or platforms may be required to gain 

proximity to the area being checked.’’

No Reporting Requirement 

(g) Although Airbus Service Bulletin 

A320–28–1054, dated August 23, 1993, 

describes procedures for reporting inspection 

findings to Airbus, this AD does not require 

such a report. 

Alternative Methods of Compliance 

(AMOCs) 

(h) 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 

(i) French airworthiness directive F–2005–

031, dated February 16, 2005, also addresses 

the subject of this AD.

Issued in Renton, Washington, on August 

11, 2005. 

Kalene C. Yanamura, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service.

[FR Doc. 05–16753 Filed 8–22–05; 8:45 am] 

BILLING CODE 4910–13–U

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. 2000–NE–42–AD] 

RIN 2120–AA64 

Airworthiness Directives; General 

Electric Company CF34 Series 

Turbofan Engines

AGENCY: Federal Aviation 

Administration (FAA), DOT.

ACTION: Notice of proposed rulemaking 

(NPRM). 

SUMMARY: The FAA proposes to 

supersede an existing airworthiness 

directive (AD) for General Electric 

Company (GE) CF34–1A, –3A, –3A1, 

–3A2, –3B, and –3B1 turbofan engines. 

That AD currently requires a onetime 

inspection, and if necessary replacing 

certain fan disks for electrical arc-out 

indications. That AD also reduces the 

life limit of certain fan disks. This 

proposed AD would require the same 

actions and adds one disk part number 

(P/N) and serial number (SN) to the 

affected fan disks. This proposed AD 

results from an error in the first part 

number and serial number listed in 

Table 1 of the original AD. We are 

proposing this AD to prevent rupture of 

the fan disk due to cracks that initiate 

at an electrical arc-out, which could 

result in an uncontained failure of the 

engine.

DATES: We must receive any comments 

on this proposed AD by October 24, 

2005.

ADDRESSES: Use one of the following 

addresses to comment on this proposed 

AD: 

• By mail: Federal Aviation 

Administration (FAA), New England 

Region, Office of the Regional Counsel, 

Attention: Rules Docket No. 2000–NE–

42–AD, 12 New England Executive Park, 

Burlington, MA 01803–5299. 

• By fax: (781) 238–7055. 

• By e-mail: 9-aneadcomment@faa.gov. 

You can get the service information 

identified in this proposed AD from GE 

Aircraft Engines, 1000 Western Avenue, 

Lynn, MA 01910; Attention: CF34 

Product Support Engineering, Mail 

Zone: 34017; telephone (781) 594–6323; 

fax (781) 594–0600. 

You may examine the AD docket at 

the FAA, New England Region, Office of 

the Regional Counsel, 12 New England 

Executive Park, Burlington, MA.

FOR FURTHER INFORMATION CONTACT:

Eugene Triozzi, Aerospace Engineer, 

Engine Certification Office, FAA, Engine 

and Propeller Directorate, 12 New 

England Executive Park, Burlington, MA 

01803–5299; telephone 781–238–7148; 

fax 781–238–7199.

SUPPLEMENTARY INFORMATION: 

Comments Invited 

We invite you to send any written 

relevant data, views, or arguments 

regarding this proposal. Send your 

comments to an address listed under 

ADDRESSES. Include ‘‘AD Docket No. 

2000–NE–42–AD’’ in the subject line of 

your comments. If you want us to 

acknowledge receipt of your mailed 

comments, send us a self-addressed, 

stamped postcard with the docket 

number written on it; we will datestamp your postcard and mail it back to 

49216 Federal Register / Vol. 70, No. 162 / Tuesday, August 23, 2005 / Proposed Rules 

you. We specifically invite comments 

on the overall regulatory, economic, 

environmental, and energy aspects of 

the proposed AD. If a person contacts us 

verbally, and that contact relates to a 

substantive part of this proposed AD, 

we will summarize the contact and 

place the summary in the docket. We 

will consider all comments received by 

the closing date and may amend the 

proposed AD in light of those 

comments. 

Examining the AD Docket 

You may examine the AD Docket 

(including any comments and service 

information), by appointment, between 

8 a.m. and 4:30 p.m., Monday through 

Friday, except Federal holidays. See 

ADDRESSES for the location. 

Discussion 

On May 7, 2001, the FAA issued AD 

2001–10–13, Amendment 39–12229 (66 

FR 27017, May 16, 2001). That AD 

requires a onetime inspection, and if 

necessary replacing certain fan disks for 

electrical arc-out indications. That AD 

also reduces the life limit of certain fan 

disks. That AD resulted from a report of 

a crack that was found during a visual 

inspection as part of routine engine 

maintenance. That condition, if not 

corrected, could result in rupture of the 

fan disk due to cracks that initiate at an 

electrical arc-out, which could result in 

an uncontained failure of the engine. 

Actions Since AD 2001–10–13 Was 

Issued 

Since we issued that AD, we 

discovered that the first fan disk part 

number and the first fan disk serial 

number listed in Table 1, Fan Disks that 

Require Removal Based on Blended 

Callouts are incorrect. This proposed 

AD would correct those numbers. In all 

other respects, the proposed AD remains 

the same as AD 2001–10–03. 

Relevant Service Information 

We have reviewed and approved the 

technical contents of GE Aircraft 

Engines (GEAE) Alert Service Bulletin 

(ASB) CF34–BJ 72–A0088, Revision 1, 

dated October 30, 2000; and ASB CF34–

AL 72–A0103, dated August 4, 2000. 

These ASB’s provide procedures for 

inspections of certain disks for electrical 

arc-out indications, and if necessary, 

replacement of the disk with a 

serviceable disk.

Differences Between the Proposed AD 

and the Service Information 

Although fan disk part number (P/N) 

5922T01G02 is not specified by ASB 

CF34–BJ 72–A0088, Revision 1, dated 

October 30, 2000, fan disk P/N 

5922T01G02 is subject to the 

requirements specified in this AD. 

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 products of this same 

type design. We are proposing this AD, 

which would require requires an 

inspection of fan disks, P/N’s 

5921T18G01, 5921T18G09, 

5921T18G10, 5921T54G01, 

5922T01G02, 5922T01G04, 

5922T01G05, 6020T62G04, 

6020T62G05, 6078T00G01, 

6078T57G01, 6078T57G02, 

6078T57G03, 6078T57G04, 

6078T57G05, and 6078T57G06, for 

electrical arc-out indications and, if 

necessary, replacement of the fan disk 

with a serviceable disk. This AD would 

also require replacing certain fan disks 

with blended callouts and listed by

P/N and serial number (SN) in this AD 

before achieving a new reduced life 

limit. The proposed AD would require 

that you do these actions using the 

service information described 

previously. 

Costs of Compliance 

We estimate that one General Electric 

Company (GE) CF34–1A, –3A, –3A1, 

–3A2, –3B, and –3B1 turbofan engine of 

U.S. registry would be affected by this 

proposed AD. We also estimate that it 

would take approximately six work 

hours per engine to perform the 

proposed actions, and that the average 

labor rate is $65 per work hour. 

Required parts would cost 

approximately $140,000 per engine. 

Based on these figures, we estimate the 

total cost of the proposed AD to U.S. 

operators to be $140,390. 

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. Would 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 summary of the costs 

to comply with this proposal and placed 

it in the AD Docket. You may get a copy 

of this summary by sending a request to 

us at the address listed under 

ADDRESSES. Include ‘‘AD Docket No. 

2000–NE–42–AD’’ in your request.

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 Federal Aviation Administration 

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 

removing Amendment 39–12229 FR 

27017, May 16, 2001, and by adding a 

new airworthiness directive to read as 

follows:

General Electric Company: Docket No. 2000–

NE–42–AD. 

Comments Due Date 

(a) The Federal Aviation Administration 

(FAA) must receive comments on this 

airworthiness directive (AD) action by 

October 24, 2005. 

Affected ADs 

(b) This AD supersedes AD 2001–10–03, 

Amendment 39–12229. 

Applicability 

(c) This AD applies to General Electric 

Company (GE) CF34–1A, –3A, –3A1, –3A2, 

–3B, and –3B1 turbofan engines. These 

engines are installed on, but not limited to, 

Bombardier, Inc. Canadair airplane models 

CL–600–2A12, –2B16, and –2B19. 

Unsafe Condition 

(d) This AD results from a report of a crack 

that was found during a visual inspection as 

part of routine engine maintenance. We are 

issuing this AD to prevent rupture of the fan 

disk due to cracks that initiate at an electrical 

arc-out, which could result in an 

uncontained failure of the engine, 

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. 

Removal of Certain Fan Disks From Service 

(f) On disk P/N’s 5921T18G01, 

5921T18G09, 5921T18G10, 5921T54G01, 

Federal Register / Vol. 70, No. 162 / Tuesday, August 23, 2005 / Proposed Rules 49217

5922T01G02, 5922T01G04, 5922T01G05, 

6020T62G04, 6020T62G05, 6078T00G01, 

6078T57G01, 6078T57G02, 6078T57G03, 

6078T57G04, 6078T57G05, and 6078T57G06, 

that are listed by P/N and serial number (SN) 

in the following Table 1 of this AD and that 

have less than 8,000 cycles-since-new (CSN) 

on the effective date of this AD, replace fan 

disk P/N’s before accumulating 8,000 CSN:

TABLE 1.—FAN DISKS THAT REQUIRE

REMOVAL BASED ON BLENDED

CALLOUTS

Disk part No. Disk serial 

No. 

6078T57G02 .......................... GAT6306N 

6078T00G01 .......................... GAT3860G 

6078T57G02 .......................... GAT1924L 

5922T01G04 .......................... GAT9599G 

6078T57G04 .......................... GEE05831 

TABLE 1.—FAN DISKS THAT REQUIRE

REMOVAL BASED ON BLENDED

CALLOUTS—Continued

Disk part No. Disk serial 

No. 

6078T57G04 .......................... GEE06612 

6078T57G04 .......................... GEE06618 

6078T57G04 .......................... GEE06974 

6078T57G04 .......................... GEE06980 

6078T57G05 .......................... GEE143FY 

6078T57G05 .......................... GEE1453G 

6078T57G05 .......................... GEE14452 

6078T57G05 .......................... GEE145NA 

6078T57G04 .......................... GEE08086 

6078T57G04 .......................... GEE09287 

6078T57G04 .......................... GEE09337 

6078T57G05 .......................... GEE12720 

6078T57G05 .......................... GEE14214 

6078T57G05 .......................... GEE142YT 

6078T57G05 .......................... GEE146GT 

(g) For disks with SN’s listed in Table 1 of 

this AD that have 8,000 CSN or greater on the 

effective date of this AD, replace the disk 

within 30 days after the effective date of this 

AD. 

Inspection of All Other Fan Disks 

(h) Inspect all other fan disks, P/N’s 

5921T18G01, 5921T18G09, 5921T18G10, 

5921T54G01, 5922T01G02, 5922T01G04, 

5922T01G05, 6020T62G04, 6020T62G05, 

6078T00G01, 6078T57G01, 6078T57G02, 

6078T57G03, 6078T57G04, 6078T57G05, and 

6078T57G06 in accordance with paragraphs 

3.A.(1) through 3.E.(2) of the 

Accomplishment Instructions of Alert 

Service Bulletin (ASB) CF34–BJ 72–A0088, 

Revision 1, dated October 30, 2000 or 

paragraphs 3.A.(1) through 3.A.(2)(f) of the 

Accomplishment Instructions of ASB CF34–

AL 72–A0103, dated August 4, 2000. Use the 

compliance times specified in the following 

Table 2:

TABLE 2.—FAN DISK INSPECTION COMPLIANCE TIMES

Fan disk operating CSN Inspect by 

(1) Fewer than 8,000 CSN or the effective date of this AD .................... Before accumulating 8,000 CSN or by the next hot section inspection 

after the effective date of this AD, whichever occurs earlier. 

(2) 8,000 CSN or greater on the effective date of this AD ...................... Within 120 days after the effective date of this AD. 

Definitions 

(i) For the purposes of this AD, the 

following definitions apply: 

(1) A serviceable fan disk is defined as a 

fan disk that has been inspected as specified 

in paragraph (h) of this AD and is not listed 

in Table 1 of this AD. 

(2) Cycles-since-new for fan disk P/N’s 

5922T01G04 or 5922T01G05 is defined as 

total cycles accrued since new as P/N 

6078T57G02 or 6078T57G03, added to total 

cycles accrued after modification from P/N 

6078T57G02 or 6078T57G03. 

Alternative Methods of Compliance 

(j) The Manager, Engine Certification 

Office, has the authority to approve 

alternative methods of compliance for this 

AD if requested using the procedures found 

in 14 CFR 39.19.Special Flight Permits 

Related Information 

(k) None.

Issued in Burlington, Massachusetts, on 

August 17, 2005. 

Richard Noll, 

Acting Manager, Engine and Propeller 

Directorate, Aircraft Certification Service.

[FR Doc. 05–16709 Filed 8–22–05; 8:45 am] 

BILLING CODE 4910–13–P

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2005–20712; Directorate 

Identifier 2005–CE–15–AD] 

RIN 2120–AA64 

Airworthiness Directives; Raytheon 

Aircraft Company, Model 390, Premier 

1 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 Raytheon Aircraft Company 

(Raytheon), Model 390, Premier 1 

airplanes. For certain airplanes, this 

proposed AD would require you (unless 

already done) to replace the plastic 

cover over the air conditioning motor 

module with a metallic cover and 

modify the air conditioning compressor 

motor module electromagnetic 

interference-radio frequency 

interference (EMI–RFI) filter located 

under the cover and reidentify the 

module part number. For all airplanes, 

the proposed AD would limit future 

installations of the cover for the air 

conditioner and the air conditioning 

compressor motor module. This 

proposed AD results from reports that 

the plastic cover over the air 

conditioning motor module was found 

melted or burned and that the 

overheating of the EMI–RFI filter 

assembly located under the cover 

caused this damage. We are issuing this 

proposed AD to prevent the melting or 

burning of the plastic cover. The 

burning of the plastic cover could result 

in a fire.

DATES: We must receive any comments 

on this proposed AD by October 21, 

2005.

ADDRESSES: Use one of the following 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–

001. 

• Fax: 1–202–493–2251. 

• 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. 

To get the service information 

identified in this proposed AD, contact 

Raytheon Aircraft Company, PO Box 85,