30122 Federal Register / Vol. 63, No. 106 /Wednesday, June 3, 1998 /Rules and Regulations

(a) Within 6 months after the effective date

of this AD, replace the existing nitrogen

cylinder assembly on the ditching dams with

a new nitrogen cylinder assembly that

incorporates an improved valve assembly

(reference de Havilland Modification 8/

3154), in accordance with Bombardier

Service Bulletin S.B. 8–25–122, dated

October 10, 1997.

(b) As of the effective date of this AD, no

person shall install on any airplane any

nitrogen cylinder assembly having part

number 410870(BSC) or 410870–1.

(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, 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.

(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 replacement shall be done in

accordance with Bombardier Service Bulletin

S.B. 8–25–122, dated October 10, 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

Bombardier Inc., Bombardier Regional

Aircraft Division, Garratt Boulevard,

Downsview, Ontario M3K 1Y5, 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.

Note 3: The subject of this AD is addressed

in Canadian airworthiness directive CF–97–

21, dated November 13, 1997.

(f) This amendment becomes effective on

July 8, 1998.

Issued in Renton, Washington, on May 22,

1998.

Darrell M. Pederson,

Acting Manager, Transport Airplane

Directorate, Aircraft Certification Service.

[FR Doc. 98–14222 Filed 6–2–98; 8:45 am]

BILLING CODE 4910–13–U

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 97–ANE–60–AD; Amendment

39–10557, AD 98–11–32]

RIN 2120–AA64

Airworthiness Directives; Allison

Engine Company AE 3007A and AE

3007C Series Turbofan Engines

AGENCY: Federal Aviation

Administration, DOT.

ACTION: Final rule; request for

comments.

SUMMARY: This amendment adopts a

new airworthiness directive (AD) that is

applicable to Allison Engine Company

AE 3007A and AE 3007C series turbofan

engines. This action supersedes priority

letter AD 98–02–09, that currently

requires certain checks of the center

sump magnetic chip collector plug for

paste. Engines found with paste are

required to be removed from service.

This action references revisions of the

applicable Alert Service Bulletins (ASB)

providing clarifications of check

procedures. This amendment is

prompted by a change in the part

number applicability, a change in the

check interval, and the publication of

these revised ASBs. The actions

specified by this AD are intended to

prevent No. 4 bearing failure due to

excessive bearing wear, which can

result in an inflight engine shutdown.

DATES: Effective June 18, 1998.

The incorporation by reference of

certain publications listed in the

regulations is approved by the Director

of the Federal Register as of June 18,

1998.

Comments for inclusion in the Rules

Docket must be received on or before

August 3, 1998.

ADDRESSES: Submit comments in

triplicate to the Federal Aviation

Administration (FAA), New England

Region, Office of the Regional Counsel,

Attention: Rules Docket No. 97–ANE–

60–AD, 12 New England Executive Park,

Burlington, MA 01803–5299. Comments

may also be sent via the Internet using

the following address: ‘‘9-adengineprop@faa.dot.gov’’. Comments

sent via the Internet must contain the

docket number in the subject line.

The service information referenced in

this AD may be obtained from Allison

Engine Company, P.O. Box 420, Speed

Code U–15, Indianapolis, IN 46206–

0420; telephone (317) 230–6674. This

information may be examined at the

FAA, New England Region, Office of the

Regional Counsel, 12 New England

Executive Park, Burlington, MA; or at

the Office of the Federal Register, 800

North Capitol Street, NW., suite 700,

Washington, DC.

FOR FURTHER INFORMATION CONTACT: Kyri

Zaroyiannis, Aerospace Engineer,

Chicago Aircraft Certification Office,

FAA, Small Airplane Directorate, 2300

East Devon Avenue, Des Plaines, IL

60018; telephone (847) 294–7836, fax

(847) 294–7834.

SUPPLEMENTARY INFORMATION: On

January 16, 1998, the Federal Aviation

Administration (FAA) issued priority

letter airworthiness directive (AD) 98–

02–09, applicable to Allison Engine

Company AE 3007A and AE 3007C

series turbofan engines, which requires

each calendar day, for Allison Engine

Company AE 3007A series engines, and

every three calendar days, or prior to the

next flight, whichever occurs later, for

Allison Engine Company AE 3007C

series engines, alternating between the

left hand and right hand engines, checks

of the center sump magnetic chip

collector plug. After checking the center

sump magnetic chip collector plug , that

AD requires, if paste is found, collecting

paste, examining the O-ring for damage,

cleaning the plug once during the first

check only and not subsequently,

performing an engine ground run-up

and again examining the plug for paste.

If paste is found on this second

examination or subsequent

examinations, the engine must be

removed from service. There have been

five inflight engine shutdowns

associated with these bearing failures

since December 1, 1997, on Allison

Engine Company AE 3007A and AE

3007C series turbofan engines, which

occurred with total time in service since

new (TSN) ranging from 36 to 1,284

hours. The investigation revealed that

the No. 4 bearings deteriorate due to

manufacturing anomalies, which lead to

excessive bearing wear. Analysis of

failed bearings and service history has

narrowed the unsafe condition to one

particular bearing part number. That

condition, if not corrected, could result

in No. 4 bearing failure due to excessive

bearing wear, which can result in an

inflight engine shutdown.

Since the issuance of that priority

letter AD, Allison Engine Company has

issued Alert Service Bulletin (ASB) No.

AE 3007A–A–79–014, Revision 4, dated

April 14, 1998, and ASB No. AE 3007C–

A–79–018, Revision 3, dated April 21,

1998, which provide clarifications of

check procedures. In addition, this final

rule has added oil leak checks after each

magnetic chip detector inspection, in

order to minimize the possibility of
Federal Register / Vol. 63, No. 106 /Wednesday, June 3, 1998 /Rules and Regulations 30123

maintenance-induced errors. Also, this

final rule adds a terminating action

which eliminates the requirement for

repetitive magnetic chip detector

inspections by installing an improved

No. 4 main engine bearing.

Since an unsafe condition has been

identified that is likely to exist or

develop on other engines of this same

type design, this AD supersedes priority

letter AD 98–02–09 to reference

revisions of the applicable Allison

Engine Company ASBs providing

clarifications of check procedures,

change the part number applicability,

and change the check interval. The

actions are required to be accomplished

in accordance with the ASBs described

previously.

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 should 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 notice

must submit a self-addressed, stamped

postcard on which the following

statement is made: ‘‘Comments to

Docket Number 97–ANE–60–AD.’’ The

postcard will be date stamped and

returned to the commenter.

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 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:

98–11–32 Allison Engine Company:

Amendment 39–10557. Docket No. 97–

ANE–60–AD. Supersedes AD 98–02–09.

Applicability: Allison Engine Company AE

3007A and AE 3007C series turbofan engines

with No. 4 bearing, Part Number (P/N)

23062504, installed on but not limited to

EMBRAER EMB–145 and Cessna 750 series

aircraft.

Note 1: This airworthiness directive (AD)

applies to each engine 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 engines 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 (e)

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 No. 4 bearing failure due to

excessive bearing wear, which can result in

an inflight engine shutdown, accomplish the

following:

(a) For Allison Engine Company AE 3007A

series engines, within 8 flight hours after the

effective date of this AD, accomplish the

following in accordance with Allison Engine

Company Alert Service Bulletin (ASB) No.

AE 3007A–A–79–014, Revision 4, dated

April 14, 1998.

(1) Remove the center sump magnetic chip

collector plug (non-indicating) on each

engine and examine it for paste.

Note 2: Paste is a mixture of very fine

metallic particles and oil or soft carbon.

(2) If no paste is found, reinstall the center

sump magnetic chip collector, perform an oil

leak check, and thereafter inspect both

engines at intervals not to exceed 8 flight

hours.

(3) If paste is found, accomplish the

following prior to further flight:

(i) Remove the engine from service if paste

was previously found on the same engine

during any previous checks performed in

accordance with this AD, otherwise continue

with the following procedure:

(ii) Collect the paste on a clean white

paper. Cover the sample with clear tape and

retain it for analysis.

(iii) Examine the O-ring for damage and

replace as necessary.

(iv) Clean the center sump magnetic chip

collector plug.

(v) Reinstall the center sump magnetic chip

collector plug.

(vi) Perform a ground run-up of the engine

as follows:

(A) Ground Idle for 5 minutes.

(B) Maximum Takeoff for 2 minutes.

(C) 50% N1 (Fan speed) for 5 minutes.

(D) Ground Idle for 3 minutes.

(E) Stop the engine.

(vii) Re-examine the center sump magnetic

chip collector plug for paste. If paste is

found, remove the engine from service. If no

paste is found, thereafter inspect in

accordance with paragraph (a)(2) of this AD.

(viii) Send any removed paste to a

laboratory or facility capable of analysis with

a scanning electron microscope and an

energy dispersive x-ray microanalyzer for

analysis.

Note 3: Two laboratories capable of

performing this analysis are:
30124 Federal Register / Vol. 63, No. 106 /Wednesday, June 3, 1998 /Rules and Regulations

Aviation Laboratories, 910 Maria Street,

Kenner, LA 70062, 504–469–6751

or

Spectro Oil Analysis, Palace Gate, High

Street, Oldham, Hook, Hampshire, RG 291

NP, United Kingdom.

Send documentation referencing this AD or

ASB along with the sample.

(ix) Send the results of the analysis to

Allison as follows: Manager, AE Customer

Support, Large Commercial Engines, fax

(317) 230–4010.

(x) An engine found with paste either after

the engine ground run-up or during

subsequent checks performed in accordance

with this AD may not be operated again

without the approval of the Manager, Chicago

Aircraft Certification Office.

(b) For Allison AE 3007C series engines,

within 8 flight hours after the effective date

of this AD, accomplish the following in

accordance with Allison Engine ASB No. AE

3007C–A–79–018, Revision 3, dated April 21,

1998:

(1) Remove the center sump magnetic chip

collector plug (non-indicating) on each

engine and examine it for paste. (See Note 2)

(2) If no paste is found, reinstall the center

sump magnetic chip collector, perform an oil

leak check, and thereafter inspect both

engines at intervals not to exceed 8 flight

hours.

(3) If paste is found, accomplish the

following prior to further flight:

(i) Remove the engine from service if paste

was previously found on the same engine

during any previous checks performed in

accordance with this AD.

(ii) Collect the paste on a clean white

paper. Cover the sample with clear tape and

retain it for analysis.

(iii) Examine the O-ring for damage and

replace as necessary.

(iv) Clean the center sump magnetic chip

collector plug.

(v) Reinstall the center sump magnetic chip

collector plug.

(vi) Perform a ground run-up of the engine

as follows:

(A) Ground Idle for 5 minutes.

(B) Maximum Takeoff for 2 minutes.

(C) 50% N1 (Fan speed) for 5 minutes.

(D) Ground Idle for 3 minutes.

(E) Stop the engine.

(vii) Re-examine the center sump magnetic

chip collector plug for paste. If paste is

found, remove the engine from service. If no

paste is found, thereafter inspect in

accordance with paragraph (b)(2) of this AD.

(viii) Send any removed paste to a

laboratory or facility capable of analysis with

a scanning electron microscope and an

energy dispersive x-ray microanalyzer for

analysis. Send documentation referencing

this AD or ASB along with the sample. (See

Note 3)

(ix) Send the results of the analysis to

Allison as follows: Manager, AE Customer

Support, Large Commercial Engines, fax

(317) 230–4010.

(x) An engine found with paste either after

the engine ground run-up or during

subsequent checks performed in accordance

with this AD may not be operated again

without the approval of the Manager, Chicago

Aircraft Certification Office.

(c) For Allison Engine Company AE 3007A

series and AE 3007C series engines, remove

from service No. 4 main engine bearings,

P/N 23062504, at the next engine shop visit,

and replace with serviceable parts.

Installation of an improved No. 4 main

engine bearing constitutes terminating action

to the repetitive magnetic chip detector

checks required by paragraphs (a) and (b) of

this AD.

(d) For the purpose of this AD, the

following definitions apply:

(1) A serviceable part is defined as any No.

4 main engine bearing P/N other than

23062504.

(2) A shop visit is defined as any

maintenance action resulting in the

separation of any major engine flange.

(e) 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, Chicago

Aircraft Certification Office. Operators shall

submit their requests through an appropriate

FAA Principal Maintenance Inspector, who

may add comments and then send it to the

Manager, Chicago Aircraft Certification

Office.

Note 4: Information concerning the

existence of approved alternative methods of

compliance with this airworthiness directive,

if any, may be obtained from the Chicago

Aircraft Certification Office.

(f) 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 aircraft to

a location where the check requirements of

this AD can be accomplished.

(g) The actions required by this AD shall

be accomplished in accordance with the

following Allison Engine Company ASBs:

Document No. Page Revision Date

AE 3007A–A–79–014 ...................................................................................................................................... 1–7 4 April 14, 1998.

Total Pages: 7.

AE 3007C–A–79–018 ...................................................................................................................................... 1–6 3 April 21, 1998.

Total Pages: 6.

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 Allison Engine Company, P.O. Box 420,

Speed Code U–15, Indianapolis, IN 46206–

0420; telephone (317) 230–6674. Copies may

be inspected at the FAA, New England

Region, Office of the Regional Counsel, 12

New England Executive Park, Burlington,

MA; or at the Office of the Federal Register,

800 North Capitol Street, NW., suite 700,

Washington, DC.

(h) This amendment supersedes priority

letter AD 98–02–09, issued January 16, 1998.

(i) This amendment becomes effective on

June 18, 1998.

Issued in Burlington, Massachusetts, on

May 22, 1998.

Thomas A. Boudreau,

Acting Manager, Engine and Propeller

Directorate, Aircraft Certification Service.

[FR Doc. 98–14339 Filed 6–2–98; 8:45 am]

BILLING CODE 4910–13–U

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 98–NM–22–AD; Amendment

39–10410; AD 98–12–05]

RIN 2120–AA64

Airworthiness Directives; Airbus Model

A320–111 Series Airplanes

AGENCY: Federal Aviation

Administration, DOT.

ACTION: Direct final rule; confirmation of

effective date.

SUMMARY: This amendment adopts a

new airworthiness directive (AD) that is

applicable to certain Airbus Model

A320–111 series airplanes. This

amendment requires repetitive

inspections to detect cracking around

the attachment holes for the access

panels in the lower skin of the wing;

and repair, if necessary. This

amendment is prompted by issuance of

mandatory continuing airworthiness

information by a foreign civil

airworthiness authority. The actions

specified in this AD are intended to

detect and correct such cracking, which

could result in reduced structural

integrity of the airplane.

EFFECTIVE DATE: The direct final rule

published at 63 FR 13508 is effective on

June 18, 1998.

FOR FURTHER INFORMATION CONTACT:

Norman B. Martenson, Manager,

International Branch, ANM–116, FAA,

Transport Airplane Directorate, 1601

Lind Avenue, SW., Renton, Washington

98055–4056; telephone (425) 227–2110;

fax (425) 227–1149.

SUPPLEMENTARY INFORMATION: The FAA

published this direct final rule with

request for comments in the Federal