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
Federal Register / Vol. 62, No. 174 / Tuesday, September 9, 1997 / Rules and Regulations 47363

requires initial functional testing of the

main entrance door and ‘‘speed’’ lock

system, cleaning, and lubrication of the

‘‘speed’’ lock and ‘‘G’’ lock systems of

the main entrance door, and repair, if

necessary. This AD also requires followon repetitive cleaning, lubrication, and

functional testing of the ‘‘speed’’ lock

and ‘‘G’’ lock systems of the main

entrance door. The initial functional test

of the main entrance door is required to

be accomplished in accordance with the

Jetstream Model 4101 Airplane

Maintenance Manual. Other actions are

required to be accomplished in

accordance with the service bulletin

described previously.

Interim Action

This action is considered to be

interim action until final action is

identified, at which time the FAA may

consider further rulemaking.

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–164–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:

97–19–02 British Aerospace Regional

Aircraft [Formerly Jetstream Aircraft

Limited, British Aerospace (Commercial

Aircraft) Limited]: Amendment 39–

10122. Docket 97–NM–164–AD.

Applicability: All Model Jetstream 4101

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 (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 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, accomplish the following:

(a) Within 30 days after the effective date

of this AD, perform a functional test to verify

proper operation of the main entrance door

(including the ‘‘G’’ lock system) and the

‘‘speed’’ lock system of the main entrance

door, in accordance with Section 52–10–05

of BAe Jetstream Series 4101 Maintenance

Manual (MM).

(1) If the ‘‘speed’’ lock and the ‘‘G’’ lock

function satisfactorily: Within 60 days after

the effective date of the AD, perform the

actions specified in paragraphs (a)(1)(i) and

(a)(1)(ii) of this AD.

(i) Clean (remove existing contaminents

and lubricant) and re-lubricate (with a dry

lubricant) the ‘‘speed’’ lock and main

entrance door ‘‘G’’ lock systems in

accordance with Jetstream Service Bulletin

J41–52–058, dated July 14, 1997. And,

(ii) Following accomplishment of

paragraph (a)(1)(i) of this AD, and prior to

further flight, repeat the functional test

specified in paragraph (a) of this AD.

(A) If the ‘‘G’’ lock and the ‘‘speed’’ lock

function satisfactorily in the functional test

required by paragraph (a)(1)(ii) of this AD,

accomplish the requirements of paragraph (b)

of this AD.

(B) If the ‘‘G’’ lock and the ‘‘speed’’ lock

do not function satisfactorily in the

functional test required by paragraph

(a)(1)(ii) of this AD: Prior to further flight,

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

accordance with a method approved by the

Manager, Standardization Branch, ANM–113,

FAA, Transport Airplane Directorate.

(2) If either the ‘‘speed’’ lock and/or the

‘‘G’’ lock do not function correctly: Prior to

further flight, perform the actions specified
47364 Federal Register / Vol. 62, No. 174 / Tuesday, September 9, 1997 / Rules and Regulations

in paragraphs (a)(2)(i) and (a)(2)(ii) of this

AD.

(i) Clean (remove existing contaminents

and lubricant) and re-lubricate (with a dry

lubricant) the main entrance door ‘‘speed’’

lock and ‘‘G’’ lock systems in accordance

with Jetstream Service Bulletin J41–52–058,

dated July 14, 1997. And,

(ii) Following accomplishment of

paragraph (a)(2)(i) of this AD, and prior to

further flight, repeat the functional test of the

main entrance door (including the ‘‘G’’ lock

system) and the ‘‘speed’’ lock system, in

accordance with the MM.

(A) If the ‘‘G’’ lock and speed lock function

satisfactorily in the functional test required

by paragraph (a)(2) of this AD, accomplish

the requirements of paragraph (b) of this AD.

(B) If the ‘‘G’’ lock and speed lock do not

function satisfactorily in the functional tests

required by paragraph (a)(2) of this AD: Prior

to further flight, repair the ‘‘G’’ lock and

speed lock in accordance with a method

approved by the Manager, Standardization

Branch, ANM–113.

(b) Perform the actions specified in

paragraphs (b)(1) and (b)(2) of this AD within

1,500 hours time-in-service following

accomplishment of the initial functional test

of the main entrance door required by

paragraph (a) of this AD. Repeat the actions

specified in paragraphs (b)(1) and (b)(2) of

this AD, thereafter, at intervals not to exceed

1,500 hours time-in-service.

(1) Clean (remove contaminents and dry

lubricant) and re-lubricate (with dry

lubricant) the main entrance door ‘‘speed’’

lock and ‘‘G’’ lock systems in accordance

with Jetstream Service Bulletin J41–52–058,

dated July 14, 1997.

(2) Following accomplishment of

paragraph (b)(1) of this AD and prior to

further flight, perform a functional test of the

main entrance door (including the ‘‘G’’ lock

system) and the ‘‘speed’’ lock system, in

accordance with the MM. If the ‘‘G’’ lock or

‘‘speed’’ lock system do not perform

satisfactorily: Prior to further flight, repair

the ‘‘G’’ lock or ‘‘speed’’ lock system in

accordance with a method approved by the

Manager, Standardization Branch, ANM–113.

(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,

Standardization Branch, ANM–113.

Operators shall submit their requests through

an appropriate FAA Principal Maintenance

Inspector, who may add comments and then

send it to the Manager, Standardization

Branch, ANM–113.

Note 2: Information concerning the

existence of approved alternative methods of

compliance with this AD, if any, may be

obtained from the Standardization Branch,

ANM–113.

(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) Certain actions shall be done in

accordance with Jetstream Service Bulletin

J41–52–058, dated July 14, 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 AI(R)

American Support, Inc., 13850 Mclearen

Road, Herndon, Virginia 20171. 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.

(f) This amendment becomes effective on

September 24, 1997.

Issued in Renton, Washington, on

September 3, 1997.

Darrell M. Pederson,

Acting Manager, Transport Airplane

Directorate, Aircraft Certification Service.

[FR Doc. 97–23861 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–168–AD; Amendment

39–10123; AD 97–19–03]

RIN 2120–AA64

Airworthiness Directives; Boeing

Model 737 Series Airplanes Equipped

With Manual

IPECO Captain and First Officer Seats

AGENCY: Federal Aviation

Administration, DOT.

ACTION: Final rule; request for

comments.

SUMMARY: This amendment supersedes

an existing airworthiness directive (AD),

applicable to certain Boeing Model 737

series airplanes, that currently requires

an inspection to determine whether the

bearings of the tracklock bracket

assemblies of the pilot and co-pilot seats

are secure, modification of loose

bearings, and marking of the seat

identification labels. This AD requires a

visual inspection to determine whether

the modification and marking of the

crew seats were accomplished; and, if

not, accomplishment of these actions,

which constitutes terminating action for

the requirements of this AD. This

amendment is prompted by a report

indicating that a first officer’s crew seat

on an in-service airplane failed to lock

horizontally. The actions specified in

this AD are intended to prevent the

captain and first officer crew seats from

sliding freely on the track, which could

result in uncommanded movement of

the seats and reduced controllability of

the airplane.

DATES: Effective September 24, 1997.

The incorporation by reference of

IPECO Service Bulletin A001–25–92,

Issue 1, dated June 2, 1997, as listed in

the regulations is approved by the

Director of the Federal Register as of

September 24, 1997.

The incorporation by reference of

IPECO Service Bulletin A001–25–74,

Issue 2, dated May 6, 1993, as listed in

the regulations, was approved

previously by the Director of the

Federal Register as of August 24, 1993

(58 FR 42192, August 9, 1993).

Comments for inclusion in the Rules

Docket must be received on or before

November 10, 1997.

ADDRESSES: Submit comments in

triplicate to the Federal Aviation

Administration (FAA), Transport

Airplane Directorate, ANM–103,

Attention: Rules Docket No. 97–NM–

168–AD, 1601 Lind Avenue, SW.,

Renton, Washington 98055–4056.

The service information referenced in

this AD may be obtained from IPECO,

Inc., 3882 Del Amo Boulevard, suite

604, Torrance, California 90503. 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:

Monica L. Nemecek, Aerospace

Engineer, Airframe Branch, ANM–120S;

FAA, Transport Airplane Directorate,

Seattle Aircraft Certification Office

(ACO), 1601 Lind Avenue, SW., Renton,

Washington; telephone (425) 227–2773;

fax (425) 227–1181.

SUPPLEMENTARY INFORMATION: On August

2, 1993, the FAA issued AD 93–15–08,

amendment 39–8654 (58 FR 42192,

August 9, 1993), applicable to certain

Boeing Model 737 airplanes, to require

an inspection to determine whether the

bearings of the tracklock bracket

assemblies of the pilot and co-pilot seats

are secure, modification of loose

bearings, and marking of the seat

identification label. [A correction of the

rule was published in the Federal

Register on September 14, 1993 (58 FR

47986).] That action was prompted by

reports of pilot seats failing to lock

horizontally due to the tracklock pin

bearing becoming detached from its

housing and wedged in the mechanism.

The actions required by that AD are

intended to prevent the pilot and copilot seats from sliding freely on the

track, which could lead to the inability

of the pilots to control the airplane.

Actions Since Issuance of Previous Rule

Since the issuance of AD 93–15–08

R1, the FAA has received a report

indicating that a first officer’s crew seat

on a Boeing Model 737 series airplane,