66734 Federal Register / Vol. 66, No. 248 / Thursday, December 27, 2001 / Rules and Regulations

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 final evaluation has

been prepared for this action and it is

contained in the Rules Docket. A copy

of it may be obtained from the Rules

Docket at the location provided under

the caption ADDRESSES.

List of Subjects in 14 CFR Part 39

Air transportation, Aircraft, Aviation

safety, Incorporation by reference,

Safety.

Adoption of the Amendment

Accordingly, pursuant to the

authority delegated to me by the

Administrator, the Federal Aviation

Administration amends 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:

2001–26–08 Airbus: Amendment 39–12572.

Docket 2000–NM–247–AD.

Applicability: All Model A300 B2 series

airplanes and Model A300 B4–2C, B4–103,

and B4–203 series airplanes, certificated in

any category.

Note 1: This AD applies to each airplane

identified in the preceding applicability

provision, regardless of whether it has been

modified, altered, or repaired in the area

subject to the requirements of this AD. For

airplanes that have been modified, altered, or

repaired so that the performance of the

requirements of this AD is affected, the

owner/operator must request approval for an

alternative method of compliance in

accordance with paragraph (d) of this AD.

The request should include an assessment of

the effect of the modification, alteration, or

repair on the unsafe condition addressed by

this AD; and, if the unsafe condition has not

been eliminated, the request should include

specific proposed actions to address it.

Compliance: Required as indicated, unless

accomplished previously.

To detect and correct fatigue cracking of

certain repairs of the fuselage between frame

10 and frame 80, which could result in

reduced structural integrity of the airplane,

accomplish the following:

Identification of Repairs

(a) Before 10,000 total landings, or before

2,500 landings after the effective date of this

AD, whichever occurs later: Identify the

types and areas of repairs on the airplane

between frame 10 and frame 80, as specified

in Airbus Service Bulletin A300–53–0313,

Revision 01, dated April 27, 1999. Do the

actions per the Accomplishment Instructions

of the service bulletin. If none of the repairs

specified in the service bulletin are found, no

additional action is needed under this AD.

Follow-On Actions

(b) If, during the inspection, any repair is

found that meets the criteria specified in

Airbus Service Bulletin A300–53–0313,

Revision 01, dated April 27, 1999: Do either

an eddy current or ultrasonic inspection,

depending on the type of repair found, to

detect cracking of the applicable area

identified in Flow Chart 1, Figure 1, Sheet 1,

of the service bulletin. Do the inspection at

the time and in the manner specified in the

service bulletin. Based on the results of the

inspection, take the actions shown in the

following table:

TABLE 1.—FOLLOW-ON ACTIONS

If the following is found: Then— Per this schedule:

(1) No cracking ....................................... Repeat the inspection ............................................................ At least every 2,500 landings.

(2) Any cracking ...................................... Replace the repair per a method approved by either the

Manager, International Branch, ANM–116, FAA, Transport Airplane Directorate, or the Direction Ge ́ne ́rale de

l’Aviation Civile (DGAC) (or its delegated agent).

Before further flight.

Terminating Action

(c) Replacement of a repair that is specified

in Airbus Service Bulletin A300–53–0313,

Revision 01, dated April 27, 1999, per a

method approved by either the Manager,

International Branch, ANM–116, or the

DGAC (or its delegated agent), terminates the

requirements of this AD.

Alternative Methods of Compliance

(d) An alternative method of compliance or

adjustment of the compliance time that

provides an acceptable level of safety may be

used if approved by the Manager,

International Branch, ANM–116. Operators

shall submit their requests through an

appropriate FAA Principal Maintenance

Inspector, who may add comments and then

send it to the Manager, International Branch,

ANM–116.

Note 2: Information concerning the

existence of approved alternative methods of

compliance with this AD, if any, may be

obtained from the International Branch,

ANM–116.

Special Flight Permits

(e) Special flight permits may be issued in

accordance with sections 21.197 and 21.199

of the Federal Aviation Regulations (14 CFR

21.197 and 21.199) to operate the airplane to

a location where the requirements of this AD

can be accomplished.

Incorporation by Reference

(f) Except as provided in Table 1 and

paragraph (c) of this AD, the actions shall be

done in accordance with Airbus Service

Bulletin A300–53–0313, Revision 01, dated

April 27, 1999. This incorporation by

reference was approved by the Director of the

Federal Register in accordance with 5 U.S.C.

552(a) and 1 CFR part 51. Copies may be

obtained from Airbus Industrie, 1 Rond Point

Maurice Bellonte, 31707 Blagnac Cedex,

France. Copies may be inspected at the FAA,

Transport Airplane Directorate, 1601 Lind

Avenue, SW., Renton, Washington; or at the

Office of the Federal Register, 800 North

Capitol Street, NW., suite 700, Washington,

DC.

Note 3: The subject of this AD is addressed

in French airworthiness directive 2000–261–

312(B), dated June 28, 2000.

Effective Date

(g) This amendment becomes effective on

January 31, 2002.

Issued in Renton, Washington, on

December 14, 2001.

Kalene C. Yanamura,

Acting Manager, Transport Airplane

Directorate, Aircraft Certification Service.

[FR Doc. 01–31428 Filed 12–26–01; 8:45 am]

BILLING CODE 4910–13–P

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 2000–NM–351–AD; Amendment

39–12573; AD 2001–26–09]

RIN 2120–AA64

Airworthiness Directives; Boeing

Model 767–200 Series Airplanes

AGENCY: Federal Aviation

Administration, DOT.

ACTION: Final rule.

SUMMARY: This amendment adopts a

new airworthiness directive (AD),

applicable to certain Boeing Model 767–

Federal Register / Vol. 66, No. 248 / Thursday, December 27, 2001 / Rules and Regulations 66735

200 series airplanes, that requires a onetime inspection of the water line heater

tape where it passes close to the duct

assemblies of the air distribution system

for the flight compartment to detect

damage, and follow-on actions. This

amendment also requires eventual

replacement of certain duct assemblies

or foam insulation on those duct

assemblies with new duct assemblies or

improved foam insulation. This action

is necessary to prevent ignition of foam

insulation on the air distribution ducts,

which could result in a fire in the

airplane. This action is intended to

address the identified unsafe condition.

DATES: Effective January 31, 2002.

The incorporation by reference of

certain publications listed in the

regulations is approved by the Director

of the Federal Register as of January 31,

2002.

ADDRESSES: The service information

referenced in this AD may be obtained

from Boeing Commercial Airplane

Group, P.O. Box 3707, Seattle,

Washington 98124–2207. This

information may be examined at the

Federal Aviation Administration (FAA),

Transport Airplane Directorate, Rules

Docket, 1601 Lind Avenue, SW.,

Renton, Washington; or at the Office of

the Federal Register, 800 North Capitol

Street, NW., Suite 700, Washington, DC.

FOR FURTHER INFORMATION CONTACT: Don

Eiford, Aerospace Engineer, Systems

and Equipment Branch, ANM–130S,

FAA, Seattle Aircraft Certification

Office, 1601 Lind Avenue, SW., Renton,

Washington 98055–4056; telephone

(425) 227–2788; fax (425) 227–1181.

SUPPLEMENTARY INFORMATION: A

proposal to amend part 39 of the Federal

Aviation Regulations (14 CFR part 39) to

include an airworthiness directive (AD)

that is applicable to certain Boeing

Model 767–200 series airplanes was

published in the Federal Register on

May 14, 2001 (66 FR 24306). That action

proposed to require replacement of

certain duct assemblies of the air

distribution system for the flight

compartment with new duct assemblies

with improved insulation, and followon actions.

Comments

Interested persons have been afforded

an opportunity to participate in the

making of this amendment. Due

consideration has been given to the

comments received.

Two commenters concur with the

proposed rule.

Change Paragraph (a)

Three commenters ask that paragraph

(a) of the proposed rule be changed, as

follows:

One commenter states that the

proposed AD is similar to AD 2000–26–

05, amendment 39–12055 (65 FR 82898,

December 29, 2000). That AD requires

modification of the environmental

control system ducts for Model 737,

747, 757, and 767 series airplanes

within 6 years after the effective date of

the AD. The commenter asks that the

compliance time in this proposed AD be

changed to allow 18 months for

verification of proper clearance between

the water line heater tape and the duct

assemblies of the air distribution system

for the flight compartment, and 6 years

for duct insulation replacement, similar

to the compliance time allowed by AD

2000–26–05.

The second commenter asks that the

compliance time be changed to specify

doing the one-time general visual

inspection of the water line heater tape,

as specified in paragraph (a)(2) of the

proposed rule, within 18 months, and

then the replacement of the duct

assemblies, as specified in paragraph

(a)(1) of the proposed rule, within 6

years. The commenter states that, since

the burned duct was ignited by an

overheated water line heater tape routed

too close to a duct assembly, this

sequence of actions would ensure an

equivalent level of safety, while

providing operators the opportunity to

replace the duct assemblies at an

aircraft’s heavy maintenance visit.

The third commenter, Air Transport

Association, states that the original

equipment manufacturer is developing a

service bulletin which will allow

replacement of the BMS 8–39 foam

insulation on the ducts of the air

distribution system for the flight

compartment with BMS 8–300 foam.

Inclusion of this option in the AD

would minimize any need for the

replacement of the duct assemblies as

the means for installing the new

insulation material. The commenter

adds that requiring inspection and

corrective action to ensure proper

clearance between the duct and heater

tape within 18 months after the effective

date of the AD is prudent. The

commenter states that once these

actions are satisfactorily completed, an

acceptable level of safety would be

attained, and safe operations could be

continued. The commenter also

recommends issuing a supplemental

notice of proposed rulemaking to

address the revised instructions

specified above.

We concur with the commenters.

Since the issuance of the proposed rule

the FAA has reviewed and approved

Boeing Alert Service Bulletin 767–

21A0154, Revision 1, dated August 9,

2001. The service bulletin adds an

option to replace the existing BMS 8–39

foam insulation on the ducts of the air

distribution system for the flight

compartment with BMS 8–300

polyimide foam insulation, and

recommends inspection of the water

line heater tape within 18 months.

Therefore, per the revised bulletin and

the above comments, the FAA agrees to

require either replacement of the duct

assemblies or the foam insulation, and

to extend the compliance time for that

replacement. Revision 1 also has been

added as the source of service

information for accomplishment of the

required actions, and a new Note 3 has

been added to give credit for previous

accomplishment of certain actions per

Boeing Alert Service Bulletin 767–

21A0154, dated March 16, 2000 (which

was listed as the source of service

information for accomplishment of the

actions specified in the proposed rule).

This new requirement gives operators

the option of either replacement of the

duct assemblies or the foam insulation,

and does not add any additional work.

Therefore, issuing a supplemental

notice of proposed rulemaking is not

necessary.

Paragraph (a) of the final rule has

been changed to require an 18-month

compliance time for the one-time

general visual inspection of the water

line heater tape for damage, and followon actions; and a new paragraph (b) has

been added to expand the compliance

time to 6 years for either replacement of

the duct assemblies or replacement of

the existing BMS 8–39 foam insulation

on the ducts with BMS 8–300 polyimide

foam insulation. The Summary section

in this final rule also has been revised

accordingly.

Change Preamble in Proposed Rule

One commenter expands on the

language in the Discussion section in

the preamble of the proposed rule by

stating that the foam insulation was

compliant with flammability regulations

at the time of airplane delivery. The

FAA infers that the commenter wants

this information added to the final rule.

We acknowledge that certain

information in that section could be

changed for clarification purposes.

However, since that section of the

proposed rule does not appear in the

final rule, no change to the final rule is

necessary in this regard.

66736 Federal Register / Vol. 66, No. 248 / Thursday, December 27, 2001 / Rules and Regulations

Conclusion

After careful review of the available

data, including the comments noted

above, the FAA has determined that air

safety and the public interest require the

adoption of the rule with the changes

previously described. The FAA has

determined that these changes will

neither increase the economic burden

on any operator nor increase the scope

of the AD.

Cost Impact

There are approximately 81 airplanes

of the affected design in the worldwide

fleet. The FAA estimates that 52

airplanes of U.S. registry will be affected

by this AD, that it will take

approximately 1 work hour per airplane

to do the general visual inspection, at an

average labor rate of $60 per work hour.

Based on these figures, the cost impact

of the inspection required by this AD on

U.S. operators is estimated to be $3,120,

or $60 per airplane.

The replacement of the duct

assemblies is one option for compliance

with this AD action and will take

approximately 2 work hours to

accomplish, at an average labor rate of

$60 per work hour. Required parts will

cost a maximum of $7,285 per airplane.

Based on these figures, the cost impact

of the replacement of the duct

assemblies required by this AD is

estimated to be $7,405 per airplane.

In lieu of replacement of the duct

assemblies, this AD provides for

replacement of the foam insulation on

the ducts. It will take approximately 3

work hours to accomplish, at an average

labor rate of $60 per work hour. Based

on these figures, the cost impact of the

replacement of the foam insulation

required by this AD is estimated to be

$180 per airplane.

The cost impact figures discussed

above are based on assumptions that no

operator has yet accomplished any of

the 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 adopted herein will

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 final rule does not

have federalism implications under

Executive Order 13132.

For the reasons discussed above, I

certify that this action (1) is not a

‘‘significant regulatory action’’ under

Executive Order 12866; (2) is not a

‘‘significant rule’’ under 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. A final evaluation has

been prepared for this action and it is

contained in the Rules Docket. A copy

of it may be obtained from the Rules

Docket at the location provided under

the caption ADDRESSES.

List of Subjects in 14 CFR Part 39

Air transportation, Aircraft, Aviation

safety, Incorporation by reference,

Safety.

Adoption of the Amendment

Accordingly, pursuant to the

authority delegated to me by the

Administrator, the Federal Aviation

Administration amends 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:

2001–26–09 Boeing: Amendment 39–12573.

Docket 2000–NM–351–AD.

Applicability: Model 767–200 series

airplanes, as listed in Boeing Alert Service

Bulletin 767–21A0154, dated March 16,

2000; certificated in any category.

Note 1: This AD applies to each airplane

identified in the preceding applicability

provision, regardless of whether it has been

modified, altered, or repaired in the area

subject to the requirements of this AD. For

airplanes that have been modified, altered, or

repaired so that the performance of the

requirements of this AD is affected, the

owner/operator must request approval for an

alternative method of compliance in

accordance with paragraph (c) of this AD.

The request should include an assessment of

the effect of the modification, alteration, or

repair on the unsafe condition addressed by

this AD; and, if the unsafe condition has not

been eliminated, the request should include

specific proposed actions to address it.

Compliance: Required as indicated, unless

accomplished previously.

To prevent ignition of foam insulation on

the air distribution ducts, which could result

in a fire in the airplane, accomplish the

following:

Inspection and Follow-on Actions

(a) Within 18 months after the effective

date of this AD: Do a one-time general visual

inspection of the water line heater tape

where it passes close to the duct assemblies

of the air distribution system for the flight

compartment to detect damage; including

wear, chafing, pinching, discoloration,

localized burn marks, etc; per the

Accomplishment Instructions of Boeing Alert

Service Bulletin 767–21A0154, Revision 1,

dated August 9, 2001.

(1) If no damage is detected, before further

flight, measure the clearance between the

duct assemblies and the water line heater

tape. If clearance is less than 0.25 inch,

before further flight, re-route the heater tape

per the service bulletin.

(2) If any damage is detected, before further

flight, replace the heater tape with new

heater tape, per the service bulletin. When

installing the new tape, make sure that

clearance between the water line heater tape

and the duct assemblies is a minimum of

0.25 inch.

Note 2: For the purposes of this AD, a

general visual inspection is defined as: ‘‘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 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.’’

Replacement

(b) Within 6 years after the effective date

of this AD, do the actions specified in

paragraph (b)(1) or (b)(2) of this AD, per the

Accomplishment Instructions of Boeing Alert

Service Bulletin 767–21A0154, Revision 1,

dated August 9, 2001. Before further flight

after doing the applicable action, do a general

visual inspection to make sure that clearance

between the water line heater tape and the

duct assemblies is a minimum of 0.25 inch.

If clearance is less than 0.25 inch, before

further flight, re-route the heater tape per the

service bulletin.

(1) Replace the duct assemblies of the air

distribution system for the flight

compartment (which are located under the

main deck) with new duct assemblies having

fiberglass insulation; or

(2) Replace the existing BMS 8–39 foam

insulation on the ducts of the air distribution

system for the flight compartment (which are

located under the main deck) with BMS 8–

300 polyimide foam insulation.

Note 3: Inspection, replacement and

follow-on actions done before the effective

date of this AD per Boeing Alert Service

Bulletin 767–21A0154, dated March 16,

2000, are considered acceptable for

Federal Register / Vol. 66, No. 248 / Thursday, December 27, 2001 / Rules and Regulations 66737

compliance with the applicable actions

specified in paragraphs (a) and (b) of this AD.

Alternative Methods of Compliance

(c) An alternative method of compliance or

adjustment of the compliance time that

provides an acceptable level of safety may be

used if approved by the Manager, Seattle

Aircraft Certification Office (ACO), FAA.

Operators shall submit their requests through

an appropriate FAA Principal Maintenance

Inspector, who may add comments and then

send it to the Manager, Seattle ACO.

Note 4: Information concerning the

existence of approved alternative methods of

compliance with this AD, if any, may be

obtained from the Seattle ACO.

Special Flight Permits

(d) Special flight permits may be issued in

accordance with sections 21.197 and 21.199

of the Federal Aviation Regulations (14 CFR

21.197 and 21.199) to operate the airplane to

a location where the requirements of this AD

can be accomplished.

Incorporation by Reference

(e) The actions shall be done in accordance

with Boeing Alert Service Bulletin 767–

21A0154, Revision 1, including Appendix A,

dated August 9, 2001. This incorporation by

reference was approved by the Director of the

Federal Register in accordance with 5 U.S.C.

552(a) and 1 CFR part 51. Copies may be

obtained from Boeing Commercial Airplane

Group, P.O. Box 3707, Seattle, Washington

98124–2207. Copies may be inspected at the

FAA, Transport Airplane Directorate, 1601

Lind Avenue, SW., Renton, Washington; or at

the Office of the Federal Register, 800 North

Capitol Street, NW., suite 700, Washington,

DC.

Effective Date

(f) This amendment becomes effective on

January 31, 2002.

Issued in Renton, Washington, on

December 14, 2001.

Kalene C. Yanamura,

Acting Manager, Transport Airplane

Directorate, Aircraft Certification Service.

[FR Doc. 01–31429 Filed 12–26–01; 8:45 am]

BILLING CODE 4910–13–P

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 2001–NM–361–AD; Amendment

39–12571; AD 2001–26–07]

RIN 2120–AA64

Airworthiness Directives; Gulfstream

Model G–IV Series Airplanes

AGENCY: Federal Aviation

Administration, DOT.

ACTION: Final rule; request for

comments.

SUMMARY: This amendment adopts a

new airworthiness directive (AD) that is

applicable to certain Gulfstream Model

G–IV series airplanes. This action

requires an inspection of the electrical

connections for the fire extinguisher

bottles; an inspection after any

subsequent maintenance affecting the

fire extinguisher bottles; and corrective

action, if necessary. This action is

prompted by a report indicating that the

electrical connections for the fire

extinguisher bottle squibs had been

improperly installed either during

manufacturing or during subsequent

maintenance. This action is necessary to

prevent fire extinguishing agent from

being discharged into the wrong

location, which could result in failure to

extinguish an in-flight fire on an

affected engine and jeopardize operation

of the opposite engine.

DATES: Effective January 11, 2002.

The incorporation by reference of

certain publications listed in the

regulations is approved by the Director

of the Federal Register as of January 11,

2002.

Comments for inclusion in the Rules

Docket must be received on or before

January 28, 2002.

ADDRESSES: Submit comments in

triplicate to the Federal Aviation

Administration (FAA), Transport

Airplane Directorate, ANM–114,

Attention: Rules Docket No. 2001–NM–

361–AD, 1601 Lind Avenue, SW.,

Renton, Washington 98055–4056.

Comments may be inspected at this

location between 9:00 a.m. and 3:00

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-

anm-iarcomment@faa.gov. Comments

sent via the Internet must contain

‘‘Docket No. 2001–NM–361–AD’’ in the

subject line and need not be submitted

in triplicate. Comments sent via fax or

the Internet as attached electronic files

must be formatted in Microsoft Word 97

for Windows or ASCII text.

The service information referenced in

this AD may be obtained from

Gulfstream Aerospace Corporation, P.O.

Box 2206, M/S D–10, Savannah, Georgia

31402–9980. This information may be

examined at the FAA, Transport

Airplane Directorate, 1601 Lind

Avenue, SW., Renton, Washington; or at

the FAA, Atlanta Aircraft Certification

Office, One Crown Center, 1895 Phoenix

Boulevard, suite 450, Atlanta, Georgia

30349; or at the Office of the Federal

Register, 800 North Capitol Street, NW.,

suite 700, Washington, DC.

FOR FURTHER INFORMATION CONTACT: John

J. Philbin, Aerospace Engineer, Systems

and Flight Test Branch, ACE–116A,

FAA, Atlanta Aircraft Certification

Office, One Crown Center, 1895 Phoenix

Boulevard, suite 450, Atlanta, Georgia

30349; telephone (770) 703–6072; fax

(770) 703–6097.

SUPPLEMENTARY INFORMATION: The FAA

has received a report that, during an

inspection of a Gulfstream Model G–IV

series airplane, the electrical

connections for the left and right fire

extinguisher bottle squibs were found to

be improperly installed. The improper

installation occurred either during

manufacturing or during subsequent

maintenance affecting the fire

extinguisher bottles. The manufacturer

states that a contributing factor for

improper connection of the fire

extinguisher bottle is the potential for

the identification labels to migrate up

the wiring harness, which increases the

possibility for a technician to connect

the wiring to incorrect terminals. This

condition, if not corrected, could cause

fire extinguishing agent to be discharged

into the wrong location, which could

result in failure to extinguish an inflight fire on an affected engine and

jeopardize operation of the opposite

engine.

FAA Determination

The FAA has determined that

issuance of this AD, applicable to

Gulfstream Model G–IV series airplanes,

serial numbers 1253 through 1464

inclusive, is necessary because of the

potential for improper connection of the

electrical connections, as described

previously. The FAA adds that wire

marking tags often have been found

much farther from the terminal ends

than intended by the design, and it is

uncertain when the discrepancies in tag

installation began during production.

However, the FAA has been notified

by the manufacturer that the identified

unsafe condition has been addressed on

Model G–IV series airplanes, serial

numbers 1465 and subsequent, by a

clarification in the build instructions.

Therefore, it is unnecessary to include

those airplanes in the applicability of

this AD.

Explanation of Relevant Service

Information

The FAA has reviewed and approved

Gulfstream GIV Alert Customer Bulletin

No. 30, dated November 2, 2001, which

describes procedures for an inspection

of the electrical connections for the

engine fire extinguisher bottles; and

corrective action, if necessary.