Federal Register / Vol. 70, No. 169 / Thursday, September 1, 2005 / Proposed Rules 52043 

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 and placed it in the 

AD docket. 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 Federal Aviation 

Administration (FAA) amends § 39.13 

by adding the following new 

airworthiness directive (AD): 

Saab Aircraft AB: Docket No. FAA–2005–

22255; Directorate Identifier 2005–NM–

106–AD. 

Comments Due Date 

(a) The FAA must receive comments on 

this AD action by October 3, 2005. 

Affected ADs 

(b) None. 

Applicability 

(c) This AD applies to SAAB Model SAAB 

2000 airplanes, certificated in any category, 

serial numbers –004 through –063 inclusive. 

Unsafe Condition 

(d) This AD results from reports of in-flight 

engine shutdown caused by uncommanded 

operation of the feather pump of the 

propeller. We are issuing this AD to prevent 

uncommanded feathering of the propeller, 

which could result in the shutdown of an 

engine during flight 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. 

Modification 

(f) Within 12 months after the effective 

date of this AD, modify the manual featherand-unfeather system of the propellers by 

doing all actions specified in the 

Accomplishment Instructions of Saab Service 

Bulletin 2000–61–006, Revision 01, dated 

February 17, 2005. 

Actions Accomplished Previously 

(g) A modification accomplished before the 

effective date of this AD in accordance with 

Saab Service Bulletin 2000–61–006, dated 

December 20, 2004, is acceptable for 

compliance with paragraph (f) of this AD. 

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) Swedish airworthiness directive 1–198, 

dated February 14, 2005, also addresses the 

subject of this AD. 

Issued in Renton, Washington, on August 

24, 2005. 

Ali Bahrami, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 05–17404 Filed 8–31–05; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2004–18648; Directorate 

Identifier 2004–NE–26–AD] 

RIN 2120–AA64 

Airworthiness Directives; General 

Electric Company CF34–1A, –3A, –3A1, 

–3A2, –3B, and –3B1 Series Turbofan 

Engines 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Notice of proposed rulemaking 

(NPRM). 

SUMMARY: The FAA proposes to 

supersede an existing airworthiness 

directive (AD) that was issued for 

General Electric Company (GE) CF34–

3A1 and –3B1 series turbofan engines 

with certain part numbers (P/Ns) and 

serial numbers (SNs) of stage 5 low 

pressure turbine (LPT) disks and stage 6 

LPT disks. These engines are installed 

in Bombardier Canadair CL600–2B19 

Regional Jet (RJ) airplanes. This 

proposed AD would add SNs to the 

affected disk population for RJ 

airplanes. This proposed AD would also 

add GE CF34–1 and –3 series turbofan 

engines with certain P/Ns and SNs of 

stage 5 LPT disks and stage 6 LPT disks, 

to the applicability section. These 

engines are installed in Bombardier 

Canadair models CL–600–2A12 (CL–

601), CL–600–2B16 (CL–601–3A), (CL–

601–3R), and (CL–604) Business Jet (BJ) 

airplanes. This proposed AD would 

require initial and repetitive visual and 

eddy current inspections (ECI) of the 

affected disk population. This proposed 

AD would also allow replacement of 

those disks as optional terminating 

action to the repetitive inspections. 

Also, this proposed AD would require 

eventual replacement of the affected 

disks as terminating action to the 

repetitive inspections. This proposed 

AD results from the discovery of 

additional suspect stage 5 LPT disks and 

stage 6 LPT disks. These disks could fail 

due to low-cycle fatigue cracking that 

may start at the site of an electrical arcout on the disk. We are proposing this 

AD to prevent low-cycle-fatigue (LCF) 

failure of stage 5 LPT disks and stage 6 

LPT disks, which could lead to 

uncontained engine failure. 

DATES: We must receive any comments 

on this proposed AD by October 31, 

2005. 

ADDRESSES: Use one of the following 

addresses to comment 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–

0001. 

• 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. 

Contact 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, for the service information 

identified in this proposed AD. 

FOR FURTHER INFORMATION CONTACT: Tara 

Fitzgerald, Aerospace Engineer, Engine 

Certification Office, FAA, Engine and 

Propeller Directorate, 12 New England 

Executive Park, Burlington, MA 01803–

5299; telephone (781) 238–7130; 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 ‘‘Docket No. FAA–

52044 Federal Register / Vol. 70, No. 169 / Thursday, September 1, 2005 / Proposed Rules 

2004–18648; Directorate Identifier 

2004–NE–26–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 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 the Docket 

Management System (DMS) 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 the 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. 

Examining the AD Docket 

You may examine the docket that 

contains the proposal, any comments 

received and any final disposition in 

person at the DMS Docket Offices 

between 9 a.m. and 5 p.m., Monday 

through Friday, except Federal holidays. 

The Docket Office (telephone (800) 647–

5227) is located on the plaza level of the 

Department of Transportation Nassif 

Building at the street address stated in 

ADDRESSES. Comments will be available 

in the AD docket shortly after the DMS 

receives them. 

Discussion 

On August 9, 2004, the FAA issued 

AD 2004–15–03R1, Amendment 39–

13773 (69 FR 50299, August 16, 2004). 

That AD requires initial and repetitive 

visual inspections and ECIs of certain 

SNs of stage 5 LPT disks, P/N 

6078T92P01, and certain SNs of stage 6 

LPT disks, P/N 6078T89P01, installed in 

GE CF34–3A1 and –3B1 series turbofan 

engines that power certain Bombardier 

Canadair RJ airplanes. That AD also 

allows replacement of those SN disks as 

an optional terminating action to the 

repetitive inspections. Also, that AD 

requires replacement of certain stage 5 

and stage 6 LPT disks. That AD was the 

result of an LCF failure of a stage 5 LPT 

disk that occurred during factory 

testing. GE performed a metallurgical 

evaluation of the disk. The evaluation 

showed that the origin of the LCF failure 

was a disk crack caused by inadvertent 

contact with electrochemical etch 

probes. These probes were used to 

match-mark components during engine 

assembly. GE’s evaluation concluded 

that the probe contact caused damage 

known as electrical arc-out. Electrical 

arc-out damage can lead to crack 

initiation and subsequent LCF failure of 

the disk. That AD also resulted from the 

discovery that an incorrect part number 

for stage 6 LPT disks was published in 

the existing AD and recognition of the 

need to allow credit for actions 

completed per previous releases of GE 

Alert Service Bulletin (ASB) No. CF34–

AL S/B 72–A0173. That electrical arcout damage condition, if not corrected, 

could result in LCF failure of stage 5 

LPT disks and stage 6 LPT disks, and 

lead to uncontained engine failure. 

Actions Since AD 2004–15–03R1 Was 

Issued 

Since we issued AD 2004–15–03R1, 

GE identified additional suspect stage 5 

LPT disks, P/Ns 4922T16P01, 

5024T53P01, 5024T53P02, and 

6078T92P01, and stage 6 LPT disks, P/ 

Ns 4922T17P01, 5023T45P03, 

5023T45P04, and 6078T89P01, that 

might have the same arc-out indications. 

These disks are installed in GE CF34–

1A, –3A, –3A1, –3A2, –3B, and –3B1 

series turbofan engines that power 

Bombardier Canadair BJ and RJ 

airplanes. GE has issued ASBs to 

address these additional suspect disks. 

Relevant Service Information 

We have reviewed and approved the 

technical contents of GE ASB No. CF34–

AL S/B 72–A0173, Revision 05, dated 

May 24, 2005, and GE ASB No. CF34–

BJ S/B 72–A0148, Revision 02, dated 

May 24, 2005. These SBs identify the 

suspect disks by serial number, and 

describe procedures for initial and 

repetitive visual inspections and ECIs 

and eventual replacement of those 

disks. 

Differences Between the Proposed AD 

and the Manufacturer’s Service 

Information 

GE ASB No. CF34–AL S/B 72–A0173, 

Revision 05, dated May 24, 2005, and 

GE ASB No. CF34–BJ S/B 72–A0148, 

Revision 02, dated May 24, 2005, 

require visually inspecting for electrical 

arc out indications around the match 

marks on stage 3 disk arms and stage 4 

disk arms. This proposed AD would not 

mandate these inspections, as the stage 

3 disks and stage 4 disks are not part of 

the suspect population. 

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. For that reason, we are 

proposing this AD, which would require 

initial and repetitive visual inspections 

and ECIs of suspect disks and eventual 

replacement of those disks. The 

proposed AD would require that you do 

these actions using the service 

information described previously. 

Costs of Compliance 

There are about 973 GE CF34–3A1 

and –3B1 series turbofan engines 

installed in Bombardier Canadair RJ 

airplanes in the worldwide fleet and 683 

of those engines are installed on 

airplanes of U.S. registry. We estimate 

that 355 of those engines would be 

affected by this proposed AD. There are 

about 970 CF34–1A, –3A, –3A1, –3A2, 

and –3B series turbofan engines 

installed in Bombardier Canadair BJ 

airplanes in the worldwide fleet and 690 

of those engines are installed on 

airplanes of U.S. registry. We estimate 

that 249 of those engines would be 

affected by this proposed AD. We also 

estimate that it would take about 70 

work hours per engine to perform the 

proposed disk inspections when the 

LPT module is exposed in the shop, and 

about 94 work hours per engine to 

perform the proposed disk inspections 

when the LPT module is forced offwing. We also estimate that the average 

labor rate is $65 per work hour. Prorated 

stage 5 LPT disks would cost about 

$42,650 (RJ), and $71,083 (BJ) per 

engine and prorated stage 6 LPT disks 

would cost about $30,110 (RJ) and 

$50,183 (BJ) per engine. We also 

estimate that about 24 stage 5 LPT disks 

and about 24 stage 6 LPT disks would 

be found with the arc-out condition and 

require replacement. Based on these 

figures, we estimate the total cost of the 

proposed AD to U.S. operators to be 

$14,409,772. 

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 

Federal Register / Vol. 70, No. 169 / Thursday, September 1, 2005 / Proposed Rules 52045 

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 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 

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 13773 (69 FR 

50299, August 16, 2004) and by adding 

a new airworthiness directive, 

Amendment 39–XXXXX, to read as 

follows: 

General Electric Company: Docket No. FAA–

2004–18648; Directorate Identifier 2004–

NE–26–AD. 

Comments Due Date 

(a) The Federal Aviation Administration 

(FAA) must receive comments on this 

airworthiness directive (AD) action by 

October 31, 2005. 

Affected ADs 

(b) This AD supersedes AD 2004–15–03R1, 

Amendment 39–13773. 

Applicability 

(c) This AD applies to the following two 

groups of engine models: 

(1) General Electric Company (GE) CF34–

3A1 and –3B1 series turbofan engines with 

stage 5 low pressure turbine (LPT) disks, part 

number (P/N) 6078T92P01 or stage 6 LPT 

disks P/N 6078T89P01, or both, with serial 

numbers (SNs) listed in Figure 3 or Figure 4 

of GE Alert Service Bulletin (ASB) No. CF34–

AL S/B 72–A0173, Revision 05, dated May 

24, 2005. These engines are installed on 

Bombardier Canadair CL600–2B19 Regional 

Jet (RJ) airplanes. 

(2) GE CF34–1A, –3A, –3A1, –3A2, and 

–3B series turbofan engines with stage 5 LPT 

disks P/N 4922T16P01, 5024T53P01, 

5024T53P02, or 6078T92P01 or stage 6 LPT 

disks P/Ns 4922T17P01, 5023T45P03, 

5023T45P04, or 6078T89P01, or both, with 

SNs listed in Figure 3 or Figure 4 of GE ASB 

No. CF34–BJ S/B 72–A0148, Revision 02, 

dated May 24, 2005. These engines are 

installed on Bombardier Canadair Models 

CL–600–2A12 (CL–601), CL–600–2B16 (CL–

601–3A), (CL–601–3R), and (CL–604) 

Business Jet (BJ) airplanes. 

Unsafe Condition 

(d) This AD results from the discovery of 

an additional population of suspect stage 5 

LPT disks and stage 6 LPT disks that could 

fail due to low-cycle fatigue cracking that 

may start at the site of an electrical arc-out 

on the disk. 

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. 

Initial Inspection or Replacement 

(f) Using the compliance schedule in Table 

1 of this AD, do the following: 

(1) For engines installed in Bombardier 

Canadair RJ airplanes, if a stage 5 LPT disk 

or stage 6 LPT disk listed in Figure 3 of GE 

ASB No. CF34–AL S/B 72–A0173, Revision 

05, dated May 24, 2005 or listed in any 

previous issue of ASB No. CF34–AL S/B 72–

A0173 did not complete a visual inspection 

and eddy current inspection (ECI) using 

paragraphs 3.C.(1) through 3.D.(2) and 

paragraphs 3.E. through 3.E.(6) of the 

Accomplishment Instructions of that SB 

before June 1, 2005, then replace that disk at 

the next piece-part exposure. 

TABLE 1.—COMPLIANCE SCHEDULE

On the effective date of this AD, if the disk has: Then perform the actions defined in paragraph (f) of this AD at next 

piece-part exposure, not to exceed the accumulation of: 

(i) 14,750 or more cycles-since-new (CSN) and has not been fluorescent penetrant inspected (FPI) at an earlier piece-part exposure.An additional 250 cycles-in-service (CIS) after the effective date of this 

AD 

(ii) 14,750 or more CSN and has been FPI at an earlier piece-part exposure..An additional 500 CIS after the effective date of this AD 

(iii) 14,500 or more CSN but fewer than 14,750 CSN ............................. An additional 500 CIS after the effective date of this AD. 

(iv) 14,250 or more CSN but fewer than 14,500 CSN ............................. An additional 750 CIS after the effective date of this AD. 

(v) 13,000 or more CSN but fewer than 14,250 CSN ............................. An additional 1,000 CIS after the effective date of this AD. 

(vi) 2,500 or more CSN but fewer than 13,000 CSN ............................... An additional 4,000 CIS after the effective date of this AD, or 14,000 

CSN, whichever comes first. 

(vii) Fewer than 2,500 cycles-since-new (CSN) ....................................... 6,500 CSN. 

(2) For engines installed in Bombardier 

Canadair BJ airplanes, perform an initial 

visual inspection and ECI of stage 5 LPT 

disks and stage 6 LPT disks listed in Figure 

3 of GE ASB No. CF34–BJ S/B 72–A0148, 

Revision 02, dated May 24, 2005, before 

January 1, 2010. Use paragraphs 3.C.(1) 

through 3.D.(2) and paragraphs 3.E. through 

3.E.(6) of Accomplishment Instructions of GE 

ASB No. CF34–BJ S/B 72–A0148, Revision 

02, dated May 24, 2005 to do the inspections. 

Repetitive Inspections 

(g) For engines installed in Bombardier 

Canadair RJ airplanes with stage 5 LPT disks 

and stage 6 LPT disks listed in Figure 3 of 

GE ASB No. CF34–AL S/B 72–A0173, 

Revision 05, dated May 24, 2005, that were 

initially visually inspected and ECI’ed before 

June 1, 2005, do the following: 

(1) Perform repetitive visual inspections 

and ECIs within every 3,100 cycles-sincelast-inspection (CSLI), until the life limit of 

the disk is reached. 

(2) Use paragraphs 3.C.(1) through 3.D.(2) 

and paragraphs 3.E. through 3.E.(6) of 

Accomplishment Instructions of GE ASB No. 

CF34–AL S/B 72–A0173, Revision 05, dated 

May 24, 2005 to do the inspections. 

(h) For engines installed in Bombardier 

Canadair BJ airplanes, with stage 5 LPT disks 

and stage 6 LPT disks initially inspected as 

specified in paragraph (f)(2) of this AD, do 

the following: 

(1) Perform repetitive visual inspections 

and ECIs within every 3,100 

CSLI, until the life limit of the disk is 

reached. 

(2) Use paragraphs 3.C.(1) through 3.D.(2) 

and paragraphs 3.E. through 3.E.(6) of 

Accomplishment Instructions of GE ASB No. 

CF34–BJ S/B 72–A0148, Revision 02, dated 

May 24, 2005, to do the inspections. 

Disks That Pass Inspection 

(i) Reinstall disks that pass the inspections 

in paragraphs (f), (g), and (h) of this AD into 

the same LPT module from which they were 

removed. 

LPT Stage 5 and Stage 6 Disk Removal 

(j) Remove any disk from service if there 

is an arc-out found on that disk. 

(k) At the next piece-part exposure for 

engines installed in Bombardier Canadair RJ 

airplanes, remove from service stage 5 LPT 

disks and stage 6 LPT disks listed in Figure 

4 of GE ASB No. CF34–AL S/B 72–A0173, 

Revision 05, dated May 24, 2005. 

(l) At the next piece-part exposure for 

engines installed in Bombardier Canadair BJ 

52046 Federal Register / Vol. 70, No. 169 / Thursday, September 1, 2005 / Proposed Rules 

airplanes, remove from service stage 5 LPT 

disks and stage 6 LPT disks listed in Figure 

4 of GE ASB No. CF34–BJ S/B 72–A0148 

Revision 02, dated May 24, 2005. 

Optional Terminating Action 

(m) Replacement of an affected stage 5 LPT 

disk or affected stage 6 LPT disk, with a disk 

not listed in Figure 3 or Figure 4 of GE ASB 

No. CF34–AL S/B 72–A0173 Revision 05, 

dated May 24, 2005 or not listed in Figure 

3 or Figure 4 of GE ASB No. CF34–BJ S/B 72–

A0148, Revision 02, dated May 24, 2005 is 

terminating action to the repetitive 

inspections and removals required by this 

AD for that disk. 

Terminating Action 

(n) As terminating action to the repetitive 

inspections and removals in this AD, replace 

all disks by January 1, 2013 that are listed in 

Figure 3 and Figure 4 of GE ASB No. CF34–

AL S/B 72–A0173, Revision 05, dated May 

24, 2005, and that are listed in Figure 3 and 

Figure 4 of GE ASB No. CF34-BJ 72–A0148, 

Revision 02, dated May 24, 2005. 

Actions Completed Per Previous Releases of 

Alert Service Bulletins 

(o) Actions completed before the effective 

date of this AD using GE ASB No. CF34–AL 

S/B 72–A0173, dated April 2, 2004; or 

Revision 01, dated May 20, 2004; or Revision 

02, dated June 22, 2004; or Revision 03, dated 

July 20, 2004; or Revision 04, dated February 

7, 2005; or GE ASB No. CF34–BJ S/B 72–

A0148, dated September 2, 2004; or Revision 

01, dated March 10, 2005, are considered 

acceptable for compliance with the 

corresponding action in this AD. 

Serviceable LPT Disk Definition 

(p) For the purpose of this AD, a 

serviceable LPT disk is a disk not listed in 

Figure 3 or Figure 4 of GE ASB No. CF34–

AL S/B 72–A0173 Revision 05, dated May 24, 

2005, or Figure 3 or Figure 4 of GE ASB No. 

CF34–BJ 72–A0148, Revision 02, dated May 

24, 2005. 

Piece-Part Exposure Definitions 

(q) For the purpose of this AD, the 

definition of piece part exposure for the stage 

5 LPT disk is when the disk is separated from 

the forward and aft bolted joints. 

(r) For the purpose of this AD, the 

definition of piece part exposure for the stage 

6 LPT disk is when the disk is separated from 

the forward bolted joint. 

Replacement Engine or Replacement LPT 

Module Definition 

(s) For the purpose of this AD, the 

definition of a replacement engine or 

replacement LPT module is an engine or LPT 

module that does not have installed any of 

the suspect disks listed in Figure 3 or Figure 

4 of GE ASB No. CF34–AL S/B 72–A0173 

Revision 05, dated May 24, 2005, or Figure 

3 or Figure 4 of GE ASB No. CF34–BJ 72–

A0148, Revision 02, dated May 24, 2005. 

Alternative Methods of Compliance 

(t) 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. 

Related Information 

(u) GE ASB No. CF34–AL S/B 72–A0178 

and ASB No. CF34–BJ S/B 72–A0152 contain 

the information necessary to identify and 

inspect the suspect disks that are the subject 

of this AD. 

Issued in Burlington, Massachusetts, on 

August 26, 2005. 

Jay J. Pardee, 

Manager, Engine and Propeller Directorate, 

Aircraft Certification Service. 

[FR Doc. 05–17400 Filed 8–31–05; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2005–22254; Directorate 

Identifier 2005–NM–001–AD] 

RIN 2120–AA64 

Airworthiness Directives; McDonnell 

Douglas Model DC–9–10, DC–9–20, 

DC–9–30, DC–9–40, and DC–9–50 

Series Airplanes; McDonnell Douglas 

Model DC–9–81 (MD–81), DC–9–82 

(MD–82), DC–9–83 (MD–83), and DC–9–

87 (MD–87) Airplanes; McDonnell 

Douglas Model MD–88 Airplanes; 

McDonnell Douglas Model MD–90–30 

Airplanes; and McDonnell Douglas 

Model 717–200 Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Notice of proposed rulemaking 

(NPRM). 

SUMMARY: The FAA proposes to adopt a 

new airworthiness directive (AD) for 

certain McDonnell Douglas transport 

category airplanes. This proposed AD 

would require an inspection to 

determine the part number of the upper 

and lower stop pad support fittings of 

all the lower cargo doors, repetitive 

inspections of all early configuration 

stop pad support fittings, and corrective 

action if necessary. This proposed AD 

would also provide an optional 

terminating action for the repetitive 

inspections. This proposed AD is 

prompted by a report of cracks found in 

the area of the upper and lower stop pad 

support fittings of the cargo door pan on 

numerous airplanes. We are proposing 

this AD to prevent cracks in the cargo 

door pan, which could result in the 

inability to fully pressurize an airplane 

and possible rapid decompression of the 

airplane. 

DATES: We must receive comments on 

this proposed AD by October 17, 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, Long Beach 

Division, 3855 Lakewood Boulevard, 

Long Beach, California 90846, 

Attention: Data and Service 

Management, Dept. C1–L5A (D800–

0024). 

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–2005–

22254; the directorate identifier for this 

docket is 2005–NM–001–AD. 

FOR FURTHER INFORMATION CONTACT: 

Maureen Moreland, Aerospace 

Engineer, Airframe Branch, ANM–120L, 

FAA, Los Angeles Aircraft Certification 

Office, 3960 Paramount Boulevard, 

Lakewood, California 90712–4137; 

telephone (562) 627–5238; fax (562) 

627–5210. 

SUPPLEMENTARY INFORMATION: 

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–

2005–22254; Directorate Identifier 

2005–NM–001–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