59148 Federal Register / Vol. 69, No. 191 / Monday, October 4, 2004 / Proposed Rules 

Relevant Service Information 

Gulfstream Aerospace LP has issued 

Alert Service Bulletin 1125–32A–233, 

Revision 1, dated August 1, 2003. The 

service bulletin describes procedures for 

adjusting the ground contact switches of 

the MLG. Accomplishing the actions 

specified in the service information is 

intended to adequately address the 

unsafe condition. The CAAI mandated 

the service information and issued 

Israeli airworthiness directive 32–03–

08–05, dated September 4, 2003, to 

ensure the continued airworthiness of 

these airplanes in Israel.

FAA’s Determination and Requirements 

of the Proposed AD 

These airplane models are 

manufactured in Israel and are type 

certificated for operation in the United 

States under the provisions of section 

21.29 of the Federal Aviation 

Regulations (14 CFR 21.29) and the 

applicable bilateral airworthiness 

agreement. Pursuant to this bilateral 

airworthiness agreement, the CAAI has 

kept the FAA informed of the situation 

described above. We have examined the 

CAAI’s findings, evaluated all pertinent 

information, and determined that AD 

action is necessary for products of this 

type design that are certificated for 

operation in the United States. 

Therefore, we are proposing this AD, 

which would require adjusting the 

ground contact switches of the MLG. 

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 

Bulletin.’’

Difference Between the Proposed AD 

and the Service Bulletin 

Operators should note that, although 

the Accomplishment Instructions of the 

referenced service bulletin describe 

procedures for submitting a service 

reply card, this proposed AD would not 

require that action. We do not need this 

information from operators. 

Costs of Compliance 

This proposed AD would affect about 

106 airplanes of U.S. registry. The 

proposed actions would take about 3 

work hours per airplane, at an average 

labor rate of $65 per work hour. Based 

on these figures, the estimated cost of 

the proposed AD for U.S. operators is 

$20,670, 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):

Gulfstream Aerospace LP (Formerly Israel 

Aircraft Industries, Ltd.): Docket No. 

FAA–2004–19138; Directorate Identifier 

2004–NM–102–AD. 

Comments Due Date 

(a) The Federal Aviation Administration 

must receive comments on this AD action by 

November 3, 2004. 

Affected ADs 

(b) None. 

Applicability 

(c) This AD applies to Gulfstream 

Aerospace LP Model Gulfstream 100 

airplanes; and Model Astra SPX and 1125 

Westwind Astra series airplanes; serial 

numbers 004 through 127 inclusive; 

certificated in any category. 

Unsafe Condition 

(d) This AD was prompted by two 

occurrences of uncommanded deployments 

of the ground airbrakes during descent. We 

are issuing this AD to prevent a false 

‘‘Ground’’ position signal, which could result 

in deployment of the ground airbrakes and 

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. 

Corrective Action 

(f) Within 250 flight hours after the 

effective date of this AD, adjust the ground 

contact switches of the left and right main 

landing gear, in accordance with the 

Accomplishment Instructions of Gulfstream 

Alert Service Bulletin 1125–32A–233, 

Revision 1, dated August 1, 2003. Although 

the service bulletin referenced in this AD 

specifies to submit certain information to the 

manufacturer, this AD does not include that 

requirement. 

Alternative Methods of Compliance 

(AMOCs) 

(g) 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 

(h) Israeli airworthiness directive 32–03–

08–05, dated September 4, 2003, also 

addresses the subject of this AD.

Issued in Renton, Washington, on 

September 15, 2004. 

Ali Bahrami, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service.

[FR Doc. 04–22193 Filed 10–1–04; 8:45 am] 

BILLING CODE 4910–13–P

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2004–19157; Directorate 

Identifier 2004–NE–30–AD] 

RIN 2120–AA64 

Airworthiness Directives; Rolls-Royce 

Deutschland (RRD) (Formerly RollsRoyce plc) Tay 650–15 Series Turbofan 

Engines

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 RRD Tay 650–15 series turbofan 

engines. This proposed AD would 

require inspection of the high pressure 

compressor (HPC) shaft and high 

pressure turbine (HPT) shaft for spline 

flank wear. This proposed AD results 

from a number of occurrences of 

excessive HPC shaft and HPT shaft 

Federal Register / Vol. 69, No. 191 / Monday, October 4, 2004 / Proposed Rules 59149

spline flank wear discovered during onwing and in-shop inspections. We are 

proposing this AD to prevent spline 

disengagement resulting in an 

overspeed event, which could lead to an 

uncontained engine failure and possible 

damage to the airplane.

DATES: We must receive any comments 

on this proposed AD by December 3, 

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–

001. 

• 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. 

You can get the service information 

identified in this proposed AD from 

Rolls-Royce Deutschland Ltd & Co KG, 

Eschenweg 11, D–15827 Dahlewitz, 

Germany; telephone 49 (0) 33–7086–

1768; fax 49 (0) 33–7086–3356. 

You may examine the comments on 

this proposed AD in the AD docket on 

the Internet at http://dms.dot.gov.

FOR FURTHER INFORMATION CONTACT: Ian 

Dargin, Aerospace Engineer, Engine 

Certification Office, FAA, Engine and 

Propeller Directorate, 12 New England 

Executive Park, Burlington, MA 01803–

5299; telephone (781) 238–7178; fax 

(781) 238–7199.

SUPPLEMENTARY INFORMATION: 

Docket Management System (DMS) 

We have implemented new 

procedures for maintaining AD dockets 

electronically. As of May 17, 2004, we 

post new AD actions on the DMS and 

assign a DMS docket number. We track 

each action and assign a corresponding 

Directorate identifier. The DMS docket 

No. is in the form ‘‘Docket No. FAA–

200X–XXXXX.’’ Each DMS 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 proposal. Send your 

comments to an address listed under 

ADDRESSES. Include ‘‘Docket No. FAA–

2004–19157; Directorate Identifier 

2004–NE–30–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 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.

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 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 

The Civil Aviation Authority (CAA), 

which is the airworthiness authority for 

the United Kingdom, recently notified 

us that an unsafe condition might exist 

on certain RRD Tay 650–15 series 

turbofan engines. The CAA advises that 

the spline flanks on the HPC shaft and 

HPT shaft may be developing excessive 

wear. The amount of wear is directly 

related to the amount of relative 

movement between the HPC and an 

immobilized HPT. You can detect wear 

by inspecting the engine to determine 

the amount of relative movement 

between the HPC and an immobilized 

HPT. On-wing and in-shop inspections 

found excessive spline flank wear on 

HPC shafts and HPT shafts that 

incorporated Service Bulletin (SB) No. 

TAY–72–1327 (hard coated abutment 

face) and HPC shafts and HPT shafts 

that did not incorporate SB No. TAY–

72–1327. 

Relevant Service Information 

We have reviewed and approved the 

technical contents of RRD SB No. TAY–

72–1485, Revision 2, dated March 21, 

2003 that describes procedures for 

inspecting the flanks on the HPC shaft 

and HPT shaft for wear. The CAA 

classified the initial Rolls-Royce plc 

(RR) SB as mandatory and issued 

airworthiness directive CAA 001–01–

2002, dated January 11, 2002 in order to 

ensure the airworthiness of these RR 

engines in the United Kingdom. 

Subsequently, the certification 

responsibility was transferred to RRD 

and Revision 1 and Revision 2 were 

reclassified to ‘‘Recommended’’ by the 

Luftfahrt-Bundesamt (LBA), which is 

the aviation authority for Germany. 

Differences Between This Proposed AD 

and the Manufacturer’s Service 

Information 

The RRD SB No. TAY–72–1485, 

Revision 2, dated March 21, 2003 

specifies compliance times based on the 

date of receipt of the SB. We have 

mandated compliance times based on 

the effective date of this proposed AD. 

At initial inspection, if the HPC shaft 

or HPT shaft has accumulated 3,000 

flight cycles or more, RRD SB No. TAY–

72–1485, dated January 11, 2002, 

specifies compliance within 12 months. 

At initial inspection, if the HPC shaft or 

HPT shaft has accumulated 3,000 flight 

cycles or more, we specify compliance 

within six months from the effective 

date of the final rule.

FAA’s Determination and Requirements 

of the Proposed AD 

This engine model, manufactured in 

Germany, is type-certificated for 

operation in the United States under the 

provisions of section 21.29 of the 

Federal Aviation Regulations (14 CFR 

21.29) and the applicable bilateral 

airworthiness agreement. In keeping 

with this bilateral airworthiness 

agreement, the CAA and LBA have kept 

us informed of the situation described 

above. We have examined the findings 

of the CAA and LBA, reviewed all 

available information, and determined 

that AD action is necessary for products 

59150 Federal Register / Vol. 69, No. 191 / Monday, October 4, 2004 / Proposed Rules 

of this type design that are certificated 

for operation in the United States. We 

are proposing this AD, which would 

require inspecting the spline flanks on 

the HPC shaft and HPT shaft for wear. 

The proposed AD would require you to 

use the service information described 

previously to perform these actions. 

Costs of Compliance 

There are about 390 RRD Tay 650–15 

series turbofan engines of the affected 

design in the worldwide fleet. We 

estimate that 172 engines installed on 

airplanes of U.S. registry would be 

affected by this proposed AD. We also 

estimate that it would take about 4 work 

hours per engine to perform the 

proposed actions, and that the average 

labor rate is $65 per work hour. Based 

on these figures, we estimate the total 

cost of the proposed AD to U.S. 

operators, per inspection cycle, to be 

$44,720. We also estimate, for the HPC 

shaft of 172 engines to be replaced at 

teardown, with a parts cost of 

approximately $13,862 per shaft, the 

total cost of the proposed AD to U.S. 

operators to be $2,384,264. 

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 at the address listed 

under ADDRESSES.

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 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 a new airworthiness directive 

(AD) to read as follows:

Roll-Royce Deutschland Ltd & Co KG (RRD) 

(Formerly Rolls-Royce plc): Docket No. 

FAA–2004–19157; Directorate Identifier 

2004–NE–30–AD. 

Comments Due Date 

(a) The FAA must receive comments on 

this AD action by December 3, 2004. 

Affected ADs 

(b) None. 

Applicability 

(c) This AD applies to RRD Tay 650–15 

series turbofan engines. These engines are 

installed on, but not limited to, Fokker F100 

airplanes. 

Unsafe Condition 

(d) This AD results from a number of 

occurrences of excessive high pressure 

compressor (HPC) and high pressure turbine 

(HPT) shaft spline wear and spline flank 

wear discovered during on-wing and in-shop 

inspections. We are issuing this AD to 

prevent spline disengagement resulting in an 

overspeed event, which could lead to an 

uncontained engine failure and possible 

damage to 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.

Initial Visual Inspection of the HPC Shaft 

and HPT Shaft Splines 

(f) Within the compliance times specified 

in Table 1 of this AD, perform initial 

inspections of the HPC shaft splines and HPT 

shaft splines of RRD Tay 650–15 series 

turbofan engines. Use paragraph 3.A. of 

Accomplishment Instructions of RRD Service 

Bulletin (SB) No. TAY–72–1485, Revision 2, 

dated March 21, 2003, to do the inspections. 

Calculate spline wear using Appendix 1, 

paragraph 4.K., of RRD SB No. TAY–72–

1485, Revision 2, dated March 21, 2003.

TABLE 1.—HPC SHAFT SPLINES AND HPT SHAFT SPLINES INSPECTION SCHEDULE

Current shaft life Action 

(1) If the HPC shaft or HPT shaft has accumulated 3,000 cycles-sincenew (CSN) or more on the effective date of this AD.Inspect HPC shaft splines and HPT shaft splines for wear within six 

months after the effective date of this AD, unless previously done. 

(2) If the HPC shaft or HPT shaft has accumulated fewer than 3,000 

CSN on the effective date of this AD.

Wait until the HPC shaft or HPT shaft has accumulated 3,000 flight cycles, then inspect the HPC shaft splines and HPT shaft splines for 

wear within 300 cycles-since-last visual inspection (CSLI) or remainder of 12 months from the effective date of this AD, whichever is 

greater. 

(g) Disposition the HPC shaft, HPT shaft, or 

engine as specified in Table 2 of this AD.

TABLE 2.—VISUAL INSPECTION CRITERIA

Inspection limits Disposition 

(1) If spline wear is 0.1 inch or greater .................................................... Remove engine from service within 50 cycles-since-last visual inspection CSLI). 

(2) If spline wear is greater than or equal to 0.06 inch but less than 0.1 

inch.

Remove engine from service within 500 CSLI. 

(3) If spline wear is greater than or equal to 0.03 inch but less than 

0.06 inch..

Inspect HPC shaft and HPT shaft using the intervals in paragraph 

(h)(1) of this AD. 

Federal Register / Vol. 69, No. 191 / Monday, October 4, 2004 / Proposed Rules 59151

TABLE 2.—VISUAL INSPECTION CRITERIA—Continued

Inspection limits Disposition 

(4) If spline wear is less than 0.03 inch ................................................... Inspect HPC shaft and HPT shaft using the intervals in paragraph 

(h)(2) of this AD. 

Repetitive Visual Inspection of the HPC 

Shaft and HPT Shaft Splines 

(h) Perform repetitive inspections of the 

HPC shaft splines and HPT shaft splines of 

RRD Tay 650–15 series turbofan engines. Use 

paragraph 3.A. of Accomplishment 

Instructions with Appendix 1 of RRD SB No. 

TAY–72–1485, Revision 2, dated March 21, 

2003, to do the inspections. Calculate spline 

wear using Appendix 1, paragraph 4.K., of 

RRD SB No. TAY–72–1485, Revision 2, dated 

March 21, 2003. 

(1) If wear measured in paragraph (f) of this 

AD was greater than or equal to 0.03 inch but 

less than 0.06 inch, repetitively inspect HPC 

shaft and HPT shaft within 1,000 cyclessince-last visual inspection (CSLI). 

(2) If wear measured in paragraph (f) of this 

AD was less than 0.03 inch, repetitively 

inspect HPC shaft and HPT shaft within 

5,500 CSLI. 

(i) Disposition the HPC shaft, HPT shaft, or 

engine as specified in Table 2 of this AD. 

Previous Credit 

(j) Previous credit is allowed for 

performing the initial inspections in 

paragraph (f) of this AD, that were done using 

the Accomplishment Instructions of one of 

the following, before the effective date of this 

AD: 

(1) SB No. TAY–72–1485, dated January 

11, 2002; 

(2) SB No. TAY–72–1485, Revision 1, 

dated January 29, 2003; and 

(3) SB No. TAY–72–1485, Revision 2, 

dated March 21, 2003. 

Material Incorporated by Reference 

(k) None. 

Related Information 

(l) Civil Aviation Authority (CAA) 

airworthiness directive 001–01–2002, dated 

January 11, 2002, also addresses the subject 

of this AD.

Issued in Burlington, Massachusetts, on 

September 24, 2004. 

Francis A. Favara, 

Acting Manager, Engine and Propeller 

Directorate, Aircraft Certification Service.

[FR Doc. 04–22192 Filed 10–1–04; 8:45 am] 

BILLING CODE 4910–13–P

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2004–19228; Directorate 

Identifier 2004–NM–77–AD] 

RIN 2120–AA64 

Airworthiness Directives; Boeing 

Model 707 Airplanes and Model 720 

and 720B 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 all 

Boeing Model 707 airplanes and Model 

720 and 720B series airplanes. This 

proposed AD would require repetitive 

inspections of the left and right support 

ribs for the main landing gear (MLG) 

trunnion, related investigative/

corrective actions if necessary, and 

other specified actions. This proposed 

AD is prompted by reports of in-service 

cracking of the support ribs for the MLG 

trunnion. We are proposing this AD to 

detect and correct corrosion and 

cracking of the support ribs for the MLG 

trunnion, which could result in collapse 

of the MLG.

DATES: We must receive comments on 

this proposed AD by November 18, 

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: Candice 

Gerretsen, Aerospace Engineer, 

Airframe Branch, ANM–120S, FAA, 

Seattle Aircraft Certification Office, 

1601 Lind Avenue, SW., Renton, 

Washington 98055–4056; telephone 

(425) 917–6428; 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–

2004–19228; Directorate Identifier 

2004–NM–77–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.