Federal Register / Vol. 69, No. 4 / Wednesday, January 7, 2004 / Proposed Rules 897

$14,300, or $260 per airplane. For 

airplanes on which damage is found, the 

cost impact of the proposed replacement 

on U.S. operators is estimated to be 

$42,900, or $780 per airplane. 

The cost impact figure discussed 

above is based on assumptions that no 

operator has yet accomplished any of 

the proposed requirements of this AD 

action, and that no operator would 

accomplish those actions in the future if 

this AD were not adopted. The cost 

impact figures discussed in AD 

rulemaking actions represent only the 

time necessary to perform the specific 

actions actually required by the AD. 

These figures typically do not include 

incidental costs, such as the time 

required to gain access and close up, 

planning time, or time necessitated by 

other administrative actions. 

Regulatory Impact 

The regulations proposed herein 

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. Therefore, 

it is determined that this proposal 

would not have federalism implications 

under Executive Order 13132. 

For the reasons discussed above, I 

certify that this 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) if 

promulgated, 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. A copy of the draft 

regulatory evaluation prepared for this 

action is contained in the Rules Docket. 

A copy of it may be obtained by 

contacting the Rules Docket at the 

location provided under the caption 

ADDRESSES.

List of Subjects in 14 CFR Part 39 

Air transportation, Aircraft, Aviation 

safety, Safety.

The Proposed Amendment 

Accordingly, pursuant to the 

authority delegated to me by the 

Administrator, the Federal Aviation 

Administration proposes to amend part 

39 of the Federal Aviation Regulations 

(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. Section 39.13 is amended by 

adding the following new airworthiness 

directive:

Gulfstream Aerospace LP (Formerly Israel 

Aircraft Industries, Ltd.): Docket 2002–

NM–236–AD. 

Applicability: Model Astra SPX and 1125 

Westwind Astra series airplanes, serial 

numbers 004 through 141 inclusive; 

certificated in any category. 

Compliance: Required as indicated, unless 

accomplished previously. 

To prevent chafing of the starter generator 

cable, which could result in electrical arcing 

in the vicinity of a fuel line, and possible fire 

or explosion, accomplish the following: 

Service Bulletin Reference 

(a) The following information pertains to 

the service bulletin referenced in this AD: 

(1) The term ‘‘service bulletin,’’ as used in 

this AD, means the Accomplishment 

Instructions of Gulfstream Service Bulletin 

100–54–252, dated April 24, 2002. 

(2) Although the service bulletin 

referenced in this AD specifies to submit 

certain information to the manufacturer, this 

AD does not include such a requirement. 

Initial and Repetitive Inspections 

(b) Within 250 flight hours after the 

effective date of this AD, perform a detailed 

inspection of the starter generator electrical 

cables of both engines to detect damage, per 

the service bulletin.

Note 1: For the purposes of this AD, a 

detailed inspection is defined as: ‘‘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.’’

Follow-on Action if No Damage Is Found 

(c) If no damage is found during any 

inspection required by paragraph (b) of this 

AD: Before further flight, measure the 

insulation resistance between the starter 

generator cable and firewall support in 

accordance with the service bulletin. 

(1) If the measured resistance is less than 

20 Megaohms: Before further flight, replace 

the electrical cables and cable support per 

paragraph (d) of this AD. 

(2) If the measured resistance is greater 

than or equal to 20 Megaohms, repeat the 

inspection required by paragraph (b) of this 

AD at intervals not to exceed 250 flight 

hours, including the follow-on measurement 

in paragraph (c), as applicable, until the 

applicable replacement required by 

paragraph (d) or (e) of this AD is 

accomplished. 

Replacement if Any Damage Is Found 

(d) If any damage is found during any 

inspection required by paragraph (b), or if the 

insulation resistance as required to be 

measured by paragraph (c) of this AD is less 

than 20 megaohms: Before further flight, 

replace the electrical cables and cable 

support per Part C of the service bulletin. 

This replacement terminates the repetitive 

inspections required by paragraph (b) and the 

measurement required by paragraph (c) of 

this AD, for that affected engine. 

Replacement if No Damage is Found 

(e) If no damage is found during any 

inspection required by paragraph (b) or if the 

insulation resistance as required to be 

measured by paragraph (c) of this AD is 

greater than or equal to 20 megaohms: Within 

5 years after the effective date of this AD, or 

at the next engine removal, whichever comes 

first, replace the cable support per Part B of 

the service bulletin. This replacement 

terminates the repetitive inspections required 

by paragraph (b) and the measurement 

required by paragraph (c) of this AD, for that 

affected engine. 

Alternative Methods of Compliance 

(f) In accordance with 14 CFR 39.19, the 

Manager, International Branch, ANM–116, 

FAA, Transport Airplane Directorate, is 

authorized to approve alternative methods of 

compliance for this AD.

Note 2: The subject of this AD is addressed 

in Israeli airworthiness directive 54–02–06–

12, dated July 4, 2002.

Issued in Renton, Washington, on 

December 31, 2003. 

Michael J. Kaszycki, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service.

[FR Doc. 04–271 Filed 1–6–04; 8:45 am] 

BILLING CODE 4910–13–P

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. 2002–NM–289–AD] 

RIN 2120–AA64 

Airworthiness Directives; Boeing 

Model 737–100, –200, and –200C Series 

Airplanes

AGENCY: Federal Aviation 

Administration, DOT.

ACTION: Notice of proposed rulemaking 

(NPRM). 

SUMMARY: This document proposes the 

adoption of a new airworthiness 

directive (AD) that is applicable to all 

Boeing Model 737–100, –200, and 

–200C series airplanes. This proposal 

would require repetitive inspections to 

detect discrepancies of certain fuselage 

skin panels located just aft of the wheel 

well, and repair if necessary. The 

actions specified by the proposed AD 

are intended to detect and correct 

898 Federal Register / Vol. 69, No. 4 / Wednesday, January 7, 2004 / Proposed Rules 

fatigue cracking of the skin panels, 

which could cause rapid decompression 

of the airplane. This action is intended 

to address the identified unsafe 

condition.

DATES: Comments must be received by 

February 23, 2004.

ADDRESSES: Submit comments in 

triplicate to the Federal Aviation 

Administration (FAA), Transport 

Airplane Directorate, ANM–114, 

Attention: Rules Docket No. 2002–NM–

289–AD, 1601 Lind Avenue, SW., 

Renton, Washington 98055–4056. 

Comments may be inspected at this 

location between 9 a.m. and 3 p.m., 

Monday through Friday, except Federal 

holidays. 

The service information referenced in 

the proposed rule may be obtained from 

Boeing Commercial Airplane Group, 

P.O. Box 3707, Seattle, Washington 

98124–2207. This information may be 

examined at the FAA, Transport 

Airplane Directorate, 1601 Lind 

Avenue, SW., Renton, Washington.

FOR FURTHER INFORMATION CONTACT:

Suzanne Lucier, Aerospace Engineer, 

Airframe Branch, ANM–120S, FAA, 

Seattle Aircraft Certification Office, 

1601 Lind Avenue, SW., Renton, 

Washington 98055–4056; telephone 

(425) 917–6438; fax (425) 917–6590.

SUPPLEMENTARY INFORMATION: 

Comments Invited 

Interested persons are invited to 

participate in the making of the 

proposed rule by submitting such 

written data, views, or arguments as 

they may desire. Communications shall 

identify the Rules Docket number and 

be submitted in triplicate to the address 

specified above. All communications 

received on or before the closing date 

for comments, specified above, will be 

considered before taking action on the 

proposed rule. The proposals contained 

in this notice may be changed in light 

of the comments received. 

Comments are specifically invited on 

the overall regulatory, economic, 

environmental, and energy aspects of 

the proposed rule. All comments 

submitted will be available, both before 

and after the closing date for comments, 

in the Rules Docket for examination by 

interested persons. A report 

summarizing each FAA-public contact 

concerned with the substance of this 

proposal will be filed in the Rules 

Docket. 

Commenters wishing the FAA to 

acknowledge receipt of their comments 

submitted in response to this notice 

must submit a self-addressed, stamped 

postcard on which the following 

statement is made: ‘‘Comments to 

Docket Number 2002–NM–289–AD.’’

The postcard will be date stamped and 

returned to the commenter. 

Availability of NPRMs 

Any person may obtain a copy of this 

NPRM by submitting a request to the 

FAA, Transport Airplane Directorate, 

ANM–114, Attention: Rules Docket No. 

2002–NM–289–AD, 1601 Lind Avenue, 

SW., Renton, Washington 98055–4056.

Discussion 

The FAA has received reports of 

fatigue cracking of the skins and 

doublers located aft of the wing, 

between body station (BS) 727 and BS 

1016, and between body stringers 14 

and 25, on numerous Boeing Model 

737–100, –200, and –200C series 

airplanes. On some airplanes, 

reinforcing angles had been installed on 

the skin doublers; however, cracking 

was detected on both modified and 

unmodified airplanes. The cracking has 

been attributed to fatigue from a 

combination of shear stresses due to 

repeated wrinkling of the skin, and the 

skin chem-milled pockets configuration. 

Such fatigue cracking, if not corrected, 

could cause rapid decompression of the 

airplane. 

Related Rulemaking 

AD 90–06–02, amendment 39–6489 

(55 FR 8372, March 7, 1990), requires 

numerous modifications to aging Model 

737 series airplanes. That AD requires, 

among other things, accomplishment of 

the preventive modification specified in 

Boeing Service Bulletin 737–53–1065, 

Revision 1, dated October 12, 1989, of 

certain fuselage skin panels in the 

subject area. 

Since AD 90–06–02 was issued, the 

FAA has received reports indicating that 

several airplanes developed fatigue 

cracking in the fuselage skin panels 

even after the skin panels had been 

modified or repaired in accordance with 

that AD. While the cause of this postmodification or post-repair skin 

cracking has not yet been determined, it 

is evident that the previous 

modifications or repairs may not have 

adequately addressed the original 

fatigue cracking problem. 

Explanation of Relevant Service 

Information 

The FAA has reviewed and approved 

Boeing Service Bulletin 737–53–1065, 

Revision 2, dated April 19, 2001, 

including Evaluation Form. This service 

bulletin describes procedures for 

various actions on 42 different groups of 

airplanes, based on airplane 

configuration differences. The service 

bulletin includes procedures in different 

areas of the airplane for: 

• A subsurface eddy current or 

magnetic optical imaging inspection on 

the exterior skin to detect skin cracking 

or other damage in zones 1 and 3; 

• An internal HFEC inspection, if 

cracking is detected during the eddy 

current or magnetic optical imaging 

inspection, to detect cracking along the 

edge of the tearstrap and disbonding of 

the bonded doubler; 

• A blind fastener repair, which 

would extend the interval for the next 

HFEC inspection; 

• A general visual inspection of the 

exterior side of the skin in Zone 2; 

• Repair of cracking; 

• Removal of wrinkles from the skin 

to allow the repair to be done; 

• Reinspecting unrepaired areas at 

regular intervals; and 

• Installation of reinforcing angles, 

which would extend the interval for the 

next inspection.

Accomplishment of the actions 

specified in the service bulletin is 

intended to adequately address the 

identified unsafe condition. 

Explanation of Requirements of 

Proposed Rule 

Since an unsafe condition has been 

identified that is likely to exist or 

develop on other products of this same 

type design, the proposed AD would 

require repetitive inspections to detect 

discrepancies of certain fuselage skin 

panels located just aft of the wheel well, 

and repair if necessary. The purpose of 

these inspections is to detect fatigue 

cracking of the skin panels, which could 

cause rapid decompression of the 

airplane. The proposed inspections are 

to be accomplished in accordance with 

the service bulletin, except as discussed 

below.

Differences Between the Service 

Bulletin and the Proposed AD 

Although the service bulletin 

specifies that the manufacturer may be 

contacted for disposition of certain 

repair conditions, this proposed AD 

would require the repair of those 

conditions to be accomplished in 

accordance with a method approved by 

the FAA, or in accordance with data 

meeting the type certification basis of 

the airplane approved by a Boeing 

Company Designated Engineering 

Representative who has been authorized 

by the FAA to make such findings. 

Although the service bulletin 

recommends that operators report 

certain crack findings, this AD would 

not require such a report. 

Federal Register / Vol. 69, No. 4 / Wednesday, January 7, 2004 / Proposed Rules 899

Interim Action 

This is considered to be interim 

action. The manufacturer has advised 

that it is developing an improved 

preventive modification intended to 

address the identified unsafe condition 

for unmodified skin areas. After this 

modification is developed, approved, 

and available, the FAA may consider 

additional rulemaking. 

Cost Impact 

There are approximately 1,000 

airplanes of the affected design in the 

worldwide fleet. The FAA estimates that 

390 airplanes of U.S. registry would be 

affected by this proposed AD. 

It would take approximately 47 to 88 

work hours per airplane (depending on 

configuration) to accomplish the 

proposed inspections, at an average 

labor rate of $65 per work hour. Based 

on these figures, the cost impact of the 

inspections proposed by this AD is 

estimated to be $3,055 to $5,720 per 

airplane, per inspection cycle. 

The cost impact figures discussed 

above are based on assumptions that no 

operator has yet accomplished any of 

the proposed requirements of this AD 

action, and that no operator would 

accomplish those actions in the future if 

this proposed AD were not adopted. The 

cost impact figures discussed in AD 

rulemaking actions represent only the 

time necessary to perform the specific 

actions actually required by the AD. 

These figures typically do not include 

incidental costs, such as the time 

required to gain access and close up, 

planning time, or time necessitated by 

other administrative actions. 

Regulatory Impact 

The regulations proposed herein 

would not have substantial direct effects 

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. Therefore, 

in accordance with Executive Order 

12612, it is determined that this 

proposal would not have sufficient 

federalism implications to warrant the 

preparation of a Federalism Assessment. 

For the reasons discussed above, I 

certify that this 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) if 

promulgated, 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. A copy of the draft 

regulatory evaluation prepared for this 

action is contained in the Rules Docket. 

A copy of it may be obtained by 

contacting the Rules Docket at the 

location provided under the caption 

ADDRESSES.

List of Subjects in 14 CFR Part 39 

Air transportation, Aircraft, Aviation 

safety, Safety.

The Proposed Amendment 

Accordingly, pursuant to the 

authority delegated to me by the 

Administrator, the Federal Aviation 

Administration proposes to amend part 

39 of the Federal Aviation Regulations 

(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. Section 39.13 is amended by 

adding the following new airworthiness 

directive:

Boeing: Docket 2002–NM–289–AD.

Applicability: All Model 737–100, –200, 

and –200C series airplanes; certificated in 

any category. 

Compliance: Required as indicated, unless 

accomplished previously. 

To detect and correct fatigue cracking of 

the skin panels, which could cause rapid 

decompression of the airplane, accomplish 

the following: 

Repetitive Inspections: Unmodified Skin 

Areas 

(a) For fuselage skin panel areas that have 

not been modified with stiffening angles: 

Before the airplane accumulates 16,000 total 

flight cycles, or within 4,500 flight cycles 

after the effective date of this AD, whichever 

occurs later, inspect the unmodified fuselage 

side skins just aft of the main wheelwell, and 

perform all follow-on actions, in accordance 

with Part I of the Accomplishment 

Instructions of Boeing Service Bulletin 737–

53–1065, Revision 2, dated April 19, 2001. If 

no cracking, loose fasteners, disbonding, or 

damage is found: Repeat the inspection at the 

time specified in paragraph 1.E., of the 

service bulletin, as applicable, except as 

provided by paragraph (d) of this AD. 

Repetitive Inspections: Modified Skin Areas 

(b) For fuselage skin panel areas that have 

been modified with stiffening angles in 

accordance with Boeing Service Bulletin 

737–53–1065, dated April 19, 2001: Within 

16,000 flight cycles after the modification, or 

within 4,500 flight cycles after the effective 

date of this AD, whichever occurs later, 

inspect the modified areas as specified in 

accordance with Part I of Boeing Service 

Bulletin 737–53–1065, Revision 2, dated 

April 19, 2001. Repeat the inspection at the 

time specified in paragraph 1.E., of the 

service bulletin, as applicable, except as 

provided by paragraph (d) of this AD. If any 

cracks, loose fasteners, disbonding, or 

damage is found: Repair before further flight 

in accordance with the requirements of 

paragraph (d) of this AD. 

Terminating Action for Inspections of 

Modified Skin Areas 

(c) For fuselage skin panel areas that have 

been modified with stiffening angles in 

accordance with Boeing Service Bulletin 

737–53–1065, dated April 19, 2001: At the 

later of the times specified by paragraphs 

(c)(1) and (c)(2) of this AD: Perform a 

subsurface eddy current or magneto optical 

imaging inspection to detect subsurface skin 

cracks along the edge of the bonded doubler, 

in accordance with Figure 10 of Boeing 

Service Bulletin 737–53–1065, Revision 2, 

dated April 19, 2001. If any cracks are found, 

repair before further flight in accordance 

with paragraph (d) of this AD. 

Accomplishment of this inspection and all 

applicable corrective actions terminates the 

repetitive inspections required by paragraph 

(b) of this AD for the modified areas. 

(1) Inspect within 24,500, but not fewer 

than 20,000, flight cycles after the 

modification of the skin. 

(2) Inspect within 4,500 flight cycles after 

the effective date of this AD. 

Repair: Modified and Unmodified Skin 

Areas 

(d) If any cracking is detected during any 

inspection required by this AD: Do the 

actions specified by paragraph (d)(1) or (d)(2) 

of this AD before further flight. Do the 

actions in accordance with Boeing Service 

Bulletin 737–53–1065, Revision 2, dated 

April 19, 2001, except as required by 

paragraph (e) of this AD.

(1) Do a time-limited repair (including a 

detailed inspection of the skin in the area of 

the repair to detect corrosion and doubler 

disbonding) in accordance with Part III of the 

Accomplishment Instructions of the service 

bulletin. 

(i) After the time-limited repair has been 

accomplished: At intervals not to exceed 

3,000 flight cycles, perform an external 

general visual inspection of the repair to 

detect loose or missing fasteners, in 

accordance with Part III of the 

Accomplishment Instructions of the service 

bulletin, until the actions specified in 

paragraph (d)(1)(v) of this AD have been 

accomplished. 

(ii) After the time-limited repair has been 

accomplished: At intervals not to exceed 

4,500 flight cycles, perform an internal 

inspection of the repair to detect cracking or 

doubler disbonding using general visual and 

high-frequency eddy current methods, in 

accordance with Figure 11 of the service 

bulletin, until the actions specified in 

paragraph (d)(1)(v) of this AD have been 

accomplished. 

(iii) If any cracking is found during any 

inspection required by paragraph (d)(1) of 

this AD: Repair before further flight in 

accordance with paragraph (e) of this AD. 

(iv) If any disbonding is found during any 

inspection required by paragraph (d)(1) of 

this AD: Repair before further flight in 

900 Federal Register / Vol. 69, No. 4 / Wednesday, January 7, 2004 / Proposed Rules 

accordance with Part II of the service 

bulletin. 

(v) Within 10,000 flight cycles after 

accomplishment of the time-limited repair: 

Make the repair permanent in accordance 

with Part III of the Accomplishment 

Instructions of the service bulletin. 

Permanent repair of an area terminates the 

repetitive inspections specified in this AD for 

that repaired area only. 

(2) Do a permanent repair (including an 

inspection using external subsurface eddy 

current or magneto optical imaging methods 

to detect cracks at the chem-milled step in 

each adjacent bay of the fuselage skin, a 

detailed inspection of the skin in the area of 

the repair for corrosion and doubler 

disbonding, and applicable corrective action) 

of the cracked area, in accordance with Part 

II of the Accomplishment Instructions of the 

service bulletin. Permanent repair of an area 

terminates the repetitive inspections 

specified in this AD for that repaired area 

only. 

Exceptions to Service Bulletin Procedures 

(e) During any inspection required by this 

AD, if any discrepancy (including cracking) 

is detected for which the service bulletin 

specifies to contact Boeing for appropriation 

action: Before further flight, repair in 

accordance with a method approved by the 

Manager, Seattle ACO; or in accordance with 

data meeting the type certification basis of 

the airplane approved by a Boeing Company 

Designated Engineering Representative who 

has been authorized by the Manager, Seattle 

ACO, to make such findings. For a repair 

method to be approved, as required by this 

paragraph, the approval letter must 

specifically refer to this AD. 

(f) Although Boeing Service Bulletin 737–

53–1065, Revision 2, dated April 19, 2001, 

recommends that cracks found in Zone 2 be 

reported to Boeing, this AD does not require 

such a report. 

Alternative Methods of Compliance 

(g)(1) In accordance with 14 CFR 39.19, the 

Manager, Seattle ACO, FAA, is authorized to 

approve alternative methods of compliance 

(AMOCs) for this AD. 

(2) An AMOC that provides an acceptable 

level of safety may be used for any repair 

required by this AD, if it is approved by a 

Boeing Company Designated Engineering 

Representative who has been authorized by 

the Manager, Seattle ACO, to make such 

findings.

Issued in Renton, Washington, on 

December 30, 2003. 

Michael J. Kaszycki, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service.

[FR Doc. 04–272 Filed 1–6–04; 8:45 am] 

BILLING CODE 4910–13–P

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. 2001–NM–226–AD] 

RIN 2120–AA64 

Airworthiness Directives; McDonnell 

Douglas MD–90–30 Airplanes

AGENCY: Federal Aviation 

Administration, DOT.

ACTION: Notice of proposed rulemaking 

(NPRM). 

SUMMARY: This document proposes the 

adoption of a new airworthiness 

directive (AD) that is applicable to 

certain McDonnell Douglas Model MD–

90–30 airplanes. For some airplanes, the 

proposal would require replacing one 3-

phase limiter block assembly, 6 current 

limiters, and hardware for 9 electrical 

cables with new parts. For other 

airplanes, this proposal would require 

inspecting 6 current limiters and 3 spare 

current limiters and replacing any 

defective current limiters with new 

current limiters. These actions are 

necessary to prevent overheating of the 

terminal studs on the 3-phase limiter 

blocks and associated current limiters, 

which could cause a fire in the airplane. 

This action is intended to address the 

identified unsafe condition.

DATES: Comments must be received by 

February 23, 2004.

ADDRESSES: Submit comments in 

triplicate to the Federal Aviation 

Administration (FAA), Transport 

Airplane Directorate, ANM–114, 

Attention: Rules Docket No. 2001–NM–

226–AD, 1601 Lind Avenue, SW., 

Renton, Washington 98055–4056. 

Comments may be inspected at this 

location between 9 a.m. and 3 p.m., 

Monday through Friday, except Federal 

holidays. Comments may be submitted 

via fax to (425) 227–1232. Comments 

may also be sent via the Internet using 

the following address: 9-anmnprmcomment@faa.gov. Comments sent 

via fax or the Internet must contain 

‘‘Docket No. 2001–NM–226–AD in the 

subject line and need not be submitted 

in triplicate. Comments sent via the 

Internet as attached electronic files must 

be formatted in Microsoft Word 97 for 

Windows or ASCII text. 

The service information referenced in 

the proposed rule may be obtained from 

Boeing Commercial Aircraft Group, 

Long Beach Division, 3855 Lakewood 

Boulevard, Long Beach, California 

90846, Attention: Data and Service 

Management, Dept. C1–L5A (D800–

0024). This information may be 

examined at the FAA, Transport 

Airplane Directorate, 1601 Lind 

Avenue, SW., Renton, Washington or at 

the FAA, Los Angeles Aircraft 

Certification Office, 3960 Paramount 

Boulevard, Lakewood, California.

FOR FURTHER INFORMATION CONTACT:

George Mabuni, Aerospace Engineer, 

Systems and Equipment Branch, ANM–

130L, FAA, Los Angeles Aircraft 

Certification Office, 3960 Paramount 

Boulevard, Lakewood, California 

90712–4137; telephone (562) 627–5341; 

fax (562) 627–5210.

SUPPLEMENTARY INFORMATION: 

Comments Invited 

Interested persons are invited to 

participate in the making of the 

proposed rule by submitting such 

written data, views, or arguments as 

they may desire. Communications shall 

identify the Rules Docket number and 

be submitted in triplicate to the address 

specified above. All communications 

received on or before the closing date 

for comments, specified above, will be 

considered before taking action on the 

proposed rule. The proposals contained 

in this action may be changed in light 

of the comments received. 

Submit comments using the following 

format: 

• Organize comments issue-by-issue. 

For example, discuss a request to 

change the compliance time and a 

request to change the service bulletin 

reference as two separate issues.

• For each issue, state what specific 

change to the proposed AD is being 

requested. 

• Include justification (e.g., reasons or 

data) for each request. 

Comments are specifically invited on 

the overall regulatory, economic, 

environmental, and energy aspects of 

the proposed rule. All comments 

submitted will be available, both before 

and after the closing date for comments, 

in the Rules Docket for examination by 

interested persons. A report 

summarizing each FAA-public contact 

concerned with the substance of this 

proposal will be filed in the Rules 

Docket. 

Commenters wishing the FAA to 

acknowledge receipt of their comments 

submitted in response to this action 

must submit a self-addressed, stamped 

postcard on which the following 

statement is made: ‘‘Comments to 

Docket Number 2001–NM–226–AD.’’

The postcard will be date stamped and 

returned to the commenter. 

Availability of NPRMs 

Any person may obtain a copy of this 

NPRM by submitting a request to the