47360 Federal Register / Vol. 62, No. 174 / Tuesday, September 9, 1997 / Rules and Regulations

numbers 7003 through 7105 inclusive;

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 (b) 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 the direct current (DC) power

distribution system from short circuiting,

which could result in a burnt wire, smoke

entering the cockpit area, and consequent

passenger injury due to smoke inhalation,

accomplish the following:

(a) Within 600 hours time-in-service after

the effective date of this AD, perform a onetime inspection of the DC power distribution

system for reliability in accordance with

Canadair Regional Jet Alert Service Bulletin

S.B. A601R–24–056, Revision ‘A,’ dated July

9, 1996. Prior to further flight, correct or

repair any discrepant fuse holders and

associated electrical wiring, in accordance

with the service bulletin.

(b) 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, New York

Aircraft Certification Office (ACO), FAA,

Engine and Propeller Directorate. Operators

shall submit their requests through an

appropriate FAA Principal Maintenance

Inspector, who may add comments and then

send it to the Manager, New York ACO.

Note 2: Information concerning the

existence of approved alternative methods of

compliance with this AD, if any, may be

obtained from the New York ACO.

(c) 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.

(d) The inspection shall be done in

accordance with Canadair Regional Jet Alert

Service Bulletin S.B. A601R–24–056,

Revision ‘A,’ dated July 9, 1996. 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

Bombardier, Inc., Canadair Aerospace Group,

P.O. Box 6087, Station Centre-ville, Quebec

H3C 3G9, Canada. Copies may be inspected

at the FAA, Transport Airplane Directorate,

1601 Lind Avenue, SW., Renton,

Washington; or at the FAA, Engine and

Propeller Directorate, New York Aircraft

Certification Office, 10 Fifth Street, Third

Floor, Valley Stream, New York; or at the

Office of the Federal Register, 800 North

Capitol Street, NW., suite 700, Washington,

DC.

(e) This amendment becomes effective on

October 14, 1997.

Issued in Renton, Washington, on August

28, 1997.

Darrell M. Pederson,

Acting Manager, Transport Airplane

Directorate, Aircraft Certification Service.

[FR Doc. 97–23465 Filed 9–8–97; 8:45 am]

BILLING CODE 4910–13–U

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 97–NM–221–AD; Amendment

39–10124; AD 97–19–04]

RIN 2120–AA64

Airworthiness Directives; Empresa

Brasileira de Aeronautica S.A.

(EMBRAER) Model EMB–145 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 EMBRAER Model

EMB–145 series airplanes. This action

requires repetitive visual inspections to

detect cracks in the firewall of the

auxiliary power unit (APU), and repair,

if necessary. This AD also requires

installation of a visco-elastic damper

blanket on the firewall, which

constitutes terminating action for the

repetitive inspection requirements. This

amendment is prompted by reports

indicating that cracks were found in the

firewall of the APU due to vibration of

the firewall. The actions specified in

this AD are intended to prevent such

cracking, which could result in reduced

structural integrity of the fuselage and

empennage in the event that a fire

penetrates through the firewall of the

APU.

DATES: Effective September 24, 1997.

The incorporation by reference of

certain publications listed in the

regulations is approved by the Director

of the Federal Register as of September

24, 1997.

Comments for inclusion in the Rules

Docket must be received on or before

October 9, 1997.

ADDRESSES: Submit comments in

triplicate to the Federal Aviation

Administration (FAA), Transport

Airplane Directorate, ANM–103,

Attention: Rules Docket No. 97–NM–

221–AD, 1601 Lind Avenue, SW.,

Renton, Washington 98055–4056.

The service information referenced in

this AD may be obtained from Empresa

Brasileira de Aeronautica S.A.

(EMBRAER), P.O. Box 343—CEP 12.225,

Sao Jose dos Campos—SP, Brazil. This

information may be examined at the

FAA, Transport Airplane Directorate,

1601 Lind Avenue, SW., Renton,

Washington; or at the FAA, Small

Airplane Directorate, Atlanta Aircraft

Certification Office, 1895 Phoenix

Boulevard, Suite 450, Atlanta, Georgia;

or at the Office of the Federal Register,

800 North Capitol Street, NW., suite

700, Washington, DC.

FOR FURTHER INFORMATION CONTACT:

Curtis Jackson, Aerospace Engineer,

Airframe and Propulsion Branch, ACE–

117A, the FAA, Small Airplane

Directorate, Atlanta Aircraft

Certification Office, 1895 Phoenix

Boulevard, Suite 450, Atlanta, Georgia

30349; telephone (770) 703–6083; fax

(770) 703–6097.

SUPPLEMENTARY INFORMATION: The

Departamento de Aviacao Civil (DAC),

which is the airworthiness authority for

Brazil, recently notified the FAA that an

unsafe condition may exist on certain

EMBRAER Model EMB–145 series

airplanes. The CTA advises that it has

received reports indicating that, during

a routine inspection, cracks were found

in the firewall of the auxiliary power

unit (APU). In one incident, the crack

was 24 inches in length. The cause of

such cracking has been attributed to

vibration of the firewall in the location

where the recessed area of the shell is

spot welded to the firewall. Cracking in

the firewall of the APU, if not corrected,

could result in reduced structural

integrity of the fuselage and empennage

in the event that a fire penetrates

through the firewall of the APU.

Explanation of Relevant Service

Information

EMBRAER has issued Service Bulletin

145–53–0004, dated July 28, 1997,

which describes procedures for

repetitive visual inspections to detect

cracks in the firewall of the APU. The

service bulletin also describes

procedures for installation of a viscoelastic damper blanket on the firewall,

which eliminates the need for the

repetitive inspections. The DAC issued

Brazilian airworthiness directive NPR/

AD–97–145–02, dated July 30, 1997, in

order to assure the continued

airworthiness of these airplanes in

Brazil.

FAA’s Conclusions

This airplane model is manufactured

in Brazil and is type certificated for
Federal Register / Vol. 62, No. 174 / Tuesday, September 9, 1997 / Rules and Regulations 47361

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 DAC has kept the FAA informed of

the situation described above. The FAA

has examined the findings of the DAC,

reviewed all available information, and

determined that AD action is necessary

for products of this type design that are

certificated for operation in the United

States.

Explanation of Requirements of Rule

Since an unsafe condition has been

identified that is likely to exist or

develop on other airplanes of the same

type design registered in the United

States, this AD is being issued to

prevent cracking in the firewall of the

APU, which could result in reduced

structural integrity of the fuselage and

empenage in the event that a fire

penetrates through the firewall of the

APU. This AD requires repetitive visual

inspections to detect cracks in the

firewall of the APU, and repair, if

necessary. This AD also requires

installation of a visco-elastic damper

blanket on the firewall, which

constitutes terminating action for the

repetitive inspection requirements. The

inspections and installation are required

to be accomplished in accordance with

the service bulletin described

previously.

Differences Between the AD and the

Relevant Service Information

Operators should note that, although

the referenced service bulletin specifies

that the manufacturer must be contacted

for disposition of certain conditions,

this AD requires the repair of those

conditions to be accomplished in

accordance with a method approved by

the FAA.

Determination of Rule’s Effective Date

Since a situation exists that requires

the immediate adoption of this

regulation, it is found that notice and

opportunity for prior public comment

hereon are impracticable, and that good

cause exists for making this amendment

effective in less than 30 days.

Comments Invited

Although this action is in the form of

a final rule that involves requirements

affecting flight safety and, thus, was not

preceded by notice and an opportunity

for public comment, comments are

invited on this rule. Interested persons

are invited to comment on this 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

under the caption ADDRESSES. All

communications received on or before

the closing date for comments will be

considered, and this rule may be

amended in light of the comments

received. Factual information that

supports the commenter’s ideas and

suggestions is extremely helpful in

evaluating the effectiveness of the AD

action and determining whether

additional rulemaking action would be

needed.

Comments are specifically invited on

the overall regulatory, economic,

environmental, and energy aspects of

the rule that might suggest a need to

modify the 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 that

summarizes each FAA-public contact

concerned with the substance of this AD

will be filed in the Rules Docket.

Commenters wishing the FAA to

acknowledge receipt of their comments

submitted in response to this rule must

submit a self-addressed, stamped

postcard on which the following

statement is made: ‘‘Comments to

Docket Number 97–NM–221–AD.’’ The

postcard will be date stamped and

returned to the commenter.

Regulatory Impact

The regulations adopted herein will

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 final rule does

not have sufficient federalism

implications to warrant the preparation

of a Federalism Assessment.

The FAA has determined that this

regulation is an emergency regulation

that must be issued immediately to

correct an unsafe condition in aircraft,

and that it is not a ‘‘significant

regulatory action’’ under Executive

Order 12866. It has been determined

further that this action involves an

emergency regulation under DOT

Regulatory Policies and Procedures (44

FR 11034, February 26, 1979). If it is

determined that this emergency

regulation otherwise would be

significant under DOT Regulatory

Policies and Procedures, a final

regulatory evaluation will be prepared

and placed in the Rules Docket. A copy

of it, if filed, 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:

97–19–04 EMPRESA BRASILEIRA DE

AERONAUTICA S.A.: Amendment 39–

10124. Docket 97–NM–221–AD.

Applicability: Model EMB–145 series

airplanes, serial numbers 145004

through 145019 inclusive; certificated in

any category.

Note 1: This AD applies to each airplane

identified in the preceding applicability

provision, regardless of whether it has been

otherwise 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 cracking in the firewall of the

auxiliary power unit (APU), which could

result in reduced structural integrity of the

fuselage and empennage in the event that a

fire penetrates through the firewall of the

APU, accomplish the following:

(a) Within 50 flight hours after the effective

date of this AD, perform a visual inspection

to detect cracks in the firewall of the APU,

in accordance with EMBRAER Service

Bulletin 145–53–0004, dated July 28, 1997.

(1) If no crack is detected, repeat the visual

inspection thereafter at intervals not to

exceed 100 flight hours.

(2) If any crack is detected, prior to

operation of the APU, repair it in accordance

with a method approved by the Manager,

Atlanta Aircraft Certification Office (ACO),

FAA, Small Airplane Directorate.
47362 Federal Register / Vol. 62, No. 174 / Tuesday, September 9, 1997 / Rules and Regulations

(b) Within 200 flight hours after the

effective date of this AD, install the viscoelastic damper blanket on the firewall in

accordance with EMBRAER Service Bulletin

145–53–0004, dated July 28, 1997.

Accomplishment of the installation

constitutes terminating action for the

repetitive inspection requirements of this

AD.

(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, Atlanta

Aircraft Certification Office (ACO), FAA,

Small Airplane Directorate. Operators shall

submit their requests through an appropriate

FAA Principal Maintenance Inspector, who

may add comments and then send it to the

Manager, Atlanta ACO.

Note 2: Information concerning the

existence of approved alternative methods of

compliance with this AD, if any, may be

obtained from the Atlanta ACO.

(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.

(e) The inspection and installation shall be

done in accordance with EMBRAER Service

Bulletin 145–53–0004, dated July 28, 1997.

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 Empresa Brasileira de Aeronautica S.A.

(EMBRAER), P.O. Box 343—CEP 12.225, Sao

Jose dos Campos—SP, Brazil. Copies may be

inspected at the FAA, Transport Airplane

Directorate, 1601 Lind Avenue, SW., Renton,

Washington; or at the FAA, Small Airplane

Directorate, Atlanta Aircraft Certification

Office, 1895 Phoenix Boulevard, Suite 450,

Atlanta, Georgia; or at the Office of the

Federal Register, 800 North Capitol Street,

NW., suite 700, Washington, DC.

(f) This amendment becomes effective on

September 24, 1997.

Note 3: The subject of this AD is addressed

in Brazilian airworthiness directive NPR/

AD–97–145–02, dated July 30, 1997.

Issued in Renton, Washington, on

September 3, 1997.

Darrell M. Pederson,

Acting Manager, Transport Airplane

Directorate, Aircraft Certification Service.

[FR Doc. 97–23860 Filed 9–8–97; 8:45 am]

BILLING CODE 4910–13–P

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 97–NM–164–AD; Amendment

39–10122; AD 97–19–02]

RIN 2120–AA64

Airworthiness Directives; British

Aerospace (Jetstream) Model 4101

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 all British Aerospace

(Jetstream) Model 4101 airplanes. This

action requires repetitive functional

testing of the main entrance door,

cleaning and lubricating of the ‘‘speed’’

lock and ‘‘G’’ lock systems, and repair,

if necessary. This amendment is

prompted by reports of flight crews and

ground crews being unable to open the

main entrance door. The actions

specified in this AD are intended to

prevent inability of the main entrance

door to open, which could delay or

impede passengers exiting the airplane,

or rescue personnel from entering the

airplane during an emergency.

DATES: Effective September 24, 1997.

The incorporation by reference of

certain publications listed in the

regulations is approved by the Director

of the Federal Register as of September

24, 1997.

Comments for inclusion in the Rules

Docket must be received on or before

October 9, 1997.

ADDRESSES: Submit comments in

triplicate to the Federal Aviation

Administration (FAA), Transport

Airplane Directorate, ANM–103,

Attention: Rules Docket No. 97–NM–

164–AD, 1601 Lind Avenue, SW.,

Renton, Washington 98055–4056.

The service information referenced in

this AD may be obtained from AI(R)

American Support, Inc., 13850 Mclearen

Road, Herndon, Virginia 20171. This

information may be examined 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.

FOR FURTHER INFORMATION CONTACT:

William Schroeder, Aerospace Engineer,

Standardization Branch, ANM–113,

FAA, Transport Airplane Directorate,

1601 Lind Avenue, SW., Renton,

Washington 98055–4056; telephone

(425) 227–2148; fax (425) 227–1149.

SUPPLEMENTARY INFORMATION: The FAA

has received several reports indicating

that flight crews and/or ground crews

were unable to open the main entrance

door from either the inside or outside of

British Aerospace (Jetstream) Model

4101 airplanes. Investigation revealed

excessive friction in the main entrance

door ‘‘speed’’ lock and ‘‘G’’ lock systems

due to impurities (dirt) at mechanical

linkage points of movement in these

locking systems. Additionally, excessive

friction in the ‘‘speed’’ lock and ‘‘G’’

lock systems has been attributed to the

use of a certain type of lubricant

currently specified by the airplane

manufacturer. Such excessive friction, if

not corrected, could result in the main

entrance door being ‘‘stuck,’’ and

consequently, unable to be opened from

the inside or the outside of the airplane.

The FAA has reviewed the available

information and has determined that the

inability to open the main entrance door

during an emergency may cause delay

or impede passengers exiting the

airplane, or rescue personnel from

entering the airplane during an

emergency.

Explanation of Relevant Service

Information

Jetstream has issued Service Bulletin

J41–52–058, dated July 14, 1997, which

describes procedures for performing

repetitive functional checks of the main

entrance door, and cleaning and

lubricating of ‘‘speed’’ lock and ‘‘G’’

lock systems.

Accomplishment of these actions will

ensure that the ‘‘speed’’ lock and ‘‘G’’

lock systems will not prevent the main

entrance door from being opened when

the airplane is on the ground.

U.S. Type Certification of the Airplane

This airplane model is manufactured

in the United Kingdom and 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.

Explanation of Requirements of Rule

Since an unsafe condition has been

identified that is likely to exist or

develop on other airplanes of the same

type design registered in the United

States, this AD is being issued to

prevent excessive friction in the main

entrance door ‘‘speed’’ lock and ‘‘G’’

lock systems, which could prohibit the

door from being opened, and

consequently delay or impede

passengers when exiting the airplane, or

rescue personnel from entering the

airplane during an emergency. This AD