Federal Register / Vol. 63, No. 141 /Thursday, July 23, 1998 /Rules and Regulations 39489

stiffeners, and in the top two and bottom two

rows of the fasteners attaching the web to the

rib posts. This inspection area is located

between FSS 570 and FSS 636 and between

FSS 675 and FSS 684.

(e) If any discrepancy (i.e., cracking, fuel

leakage, broken fasteners) is detected during

any inspection required by this AD, prior to

further flight, repair in accordance with

paragraphs E. and H. (as applicable) of the

Accomplishment Instructions of Boeing

Service Bulletin 747–57A2266, Revision 3,

dated March 31, 1994; Boeing Service

Bulletin 747–57A2266, Revision 4, dated

November 3, 1994; or Boeing Alert Service

Bulletin 747–57A2266, Revision 5, dated

August 3, 1995. Thereafter, continue to

inspect the remaining fasteners in accordance

with paragraph (c) or (d) of this AD, as

applicable, until the terminating action

specified in paragraph (f) of this AD is

accomplished. If any crack is found that

cannot be removed by oversizing the fastener

hole, prior to further flight, repair it in

accordance with a method approved by the

Manager, Seattle Aircraft Certification Office

(ACO), FAA, Transport Airplane Directorate.

(f) Replacement of the fasteners in the webto-chords and of the fasteners in the web-tostiffeners and web-to-rib posts, as specified

in Boeing Service Bulletin 747–57A2266,

Revision 3, dated March 31, 1994; Revision

4, dated November 3, 1994; or Revision 5,

dated August 3, 1995; with oversized

fasteners on each wing spar in accordance

with the service bulletin constitutes

terminating action for the repetitive

inspections required by paragraphs (a), (b),

(c), (d), and (e) of this AD.

(g) 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,

Transport 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, Seattle ACO.

Note 2: Information concerning the

existence of approved alternative methods of

compliance with this AD, if any, may be

obtained from the Seattle ACO.

(h) 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.

(i) The actions shall be done in accordance

with Boeing Service Bulletin 747–57A2266,

Revision 3, dated March 31, 1994; Boeing

Service Bulletin 747–57A2266, Revision 4,

dated November 3, 1994; and Boeing Alert

Service Bulletin 747–57A2266, Revision 5,

dated August 3, 1995.

(1) The incorporation by reference of

Boeing Alert Service Bulletin 747–57A2266,

Revision 5, dated August 3, 1995, is

approved by the Director of the Federal

Register in accordance with 5 U.S.C. 552(a)

and 1 CFR part 51.

(2) The incorporation by reference of

Boeing Service Bulletin 747–57A2266,

Revision 3, dated March 31, 1994; and

Boeing Service Bulletin 747–57A2266,

Revision 4, dated November 3, 1994, was

approved previously by the Director of the

Federal Register as of March 23, 1995 (60 FR

9613, February 21, 1995).

(3) 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.

(j) This amendment becomes effective on

August 27, 1998.

Issued in Renton, Washington, on July 15,

1998.

Darrell M. Pederson,

Acting Manager, Transport Airplane

Directorate, Aircraft Certification Service.

[FR Doc. 98–19455 Filed 7–22–98; 8:45 am]

BILLING CODE 4910–13–P

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 98–ANE–35–AD; Amendment

39–10668; AD 98–15–17]

RIN 2120–AA64

Airworthiness Directives; General

Electric Company CF6–80A3 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 General Electric Company

CF6–80A3 series turbofan engines. This

action requires initial and repetitive onwing borescope inspections of the left

hand aft mount link assembly for cracks,

bearing migration, and bearing race

rotation, and, if necessary, replacement

with serviceable parts. This amendment

is prompted by a report of a fractured

left hand aft mount link discovered

during a scheduled engine removal. The

actions specified in this AD are

intended to prevent left hand aft mount

link failure, which can result in adverse

redistribution of the aft mount loads and

possible aft mount system failure.

DATES: Effective August 7, 1998.

The incorporation by reference of

certain publications listed in the

regulations is approved by the Director

of the Federal Register as of August 7,

1998.

Comments for inclusion in the Rules

Docket must be received on or before

September 21, 1998.

ADDRESSES: Submit comments in

triplicate to the Federal Aviation

Administration (FAA), New England

Region, Office of the Regional Counsel,

Attention: Rules Docket No. 98–ANE–

35–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 Rohr,

Inc., 850 Lagoon Dr., Chula Vista, CA

91910–2098; telephone (619–691–3102),

fax (619–498–7215). 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:

William S. Ricci, Aerospace Engineer,

Engine Certification Office, FAA, Engine

and Propeller Directorate, 12 New

England Executive Park, Burlington, MA

01803–5299; telephone (781) 238–7742,

fax (781) 238–7199.

SUPPLEMENTARY INFORMATION: The

Federal Aviation Administration (FAA)

has received a report of a fractured left

hand aft mount link discovered during

a scheduled engine removal of a General

Electric Company (GE) CF6–80A3 series

turbofan engine. Failure analysis

revealed a fatigue type fracture with no

metallurgical anomalies and no

geometric discrepancies in the area of

the crack origin. Over the course of the

investigation of the cracked left hand aft

mount link assembly and the review of

other link assemblies returned from

service, two conditions were noted that

individually could be considered benign

but when combined could result in

higher stress levels and the reduced

fatigue capability of link assemblies.

The first condition is the incorrect

orientation of the entry slots of the

spherical bearing assembly and the

second condition is high friction

between the bearing and the race

resulting from contamination between

faying bearing surfaces. This condition,

if not corrected, could result in left hand

aft mount link failure, which can result

in adverse redistribution of the aft

mount loads and possible aft mount

system failure.

On May 20, 1998, the Direction

Generale de L’Aviation Civile (DGAC),

the airworthiness authority of France,

issued AD 98–205–260(B), applicable to

Airbus A310 aircraft, addressing this

unsafe condition by requiring initial and

repetitive on-wing borescope

inspections of the left hand aft mount

link assembly for cracks, bearing
39490 Federal Register / Vol. 63, No. 141 /Thursday, July 23, 1998 /Rules and Regulations

migration, and bearing race rotation,

and, if necessary, replacement with

serviceable parts. On June 3, 1998, the

Transport Airplane Directorate (TAD) of

the FAA issued AD 98–12–24, also

applicable to Airbus A310 aircraft,

requiring a one-time on-wing borescope

inspection for cracks and bearing

migration. The Engine and Propeller

Directorate has consulted with the

DGAC and the TAD and has determined

that it is necessary to issue this AD

applicable to GE CF6–80A3 series

engines mandating repetitive borescope

inspections in order to assure the

continued airworthiness of the aft

mount links.

The FAA has reviewed and approved

the technical contents of Rohr Alert

Service Bulletin (ASB) No. CF6–80A3–

NAC–A71–060, dated January 30, 1998,

that describes procedures for borescope

inspections of the left hand aft mount

link for cracks, bearing migration, and

bearing race rotation.

Since an unsafe condition has been

identified that is likely to exist or

develop on other engines of the same

type design, this AD is being issued to

prevent left hand aft mount link failure.

This AD requires initial and repetitive

on-wing borescope inspections of the

left hand aft mount link assembly for

cracks, bearing migration, and bearing

race rotation, and, if necessary,

replacement with serviceable parts. The

investigation is ongoing, and further

rulemaking may be necessary that may

require additional piece-part

inspections or the installation of a

modified left hand aft mount link

assembly that would terminate the

repetitive inspections required by this

AD. The actions are required to be

accomplished in accordance with the

ASB 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 98–ANE–35–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:

98–15–17 General Electric Company:

Amendment 39–10668. Docket 98–ANE–

35–AD.

Applicability: General Electric Company

(GE) CF6–80A3 series turbofan engines,

installed on but not limited to Airbus A310

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 (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 left hand aft mount link failure,

accomplish the following:

(a) Perform initial and repetitive borescope

on-wing inspections of the left hand aft

mount link assembly for cracks, bearing

migration, and bearing race rotation

exceeding the limits specified in Rohr Alert

Service Bulletin (ASB) No. CF6–80A3–NAC–

A71–060, dated January 30, 1998, and, if

necessary, replace with serviceable parts, as

follows:

(1) Initially inspect within 50 cycles in

service (CIS) after the effective date of this

AD.

(2) Thereafter, reinspect at intervals not to

exceed 175 CIS since last inspection.

(3) Prior to further flight, remove from

service any left hand aft mount link

discovered with cracks, bearing migration, or

bearing race rotation, exceeding the limits

specified in Rohr ASB No. CF6–80A3–NAC–

A71–060, dated January 30, 1998, and

replace with serviceable parts.

(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, Engine
Federal Register / Vol. 63, No. 141 /Thursday, July 23, 1998 /Rules and Regulations 39491

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, Engine Certification Office.

Note 2: Information concerning the

existence of approved alternative methods of

compliance with this airworthiness directive,

if any, may be obtained from the Engine

Certification Office.

(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 aircraft to

a location where the requirements of this AD

can be accomplished.

(d) The actions required by this AD shall

be done in accordance with the following

Rohr ASB:

Document No. Pages Date

CF6–80A3–

NAC–A71–

060.

1–10 January 30, 1998.

Total pages: 10.

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 Rohr, Inc., 850 Lagoon Dr., Chula Vista,

CA 91910–2098; telephone (619–691–3102),

fax (619–498–7215). 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.

(e) This amendment becomes effective on

August 7, 1998.

Issued in Burlington, Massachusetts, on

July 15, 1998.

Jay J. Pardee,

Manager, Engine and Propeller Directorate,

Aircraft Certification Service.

[FR Doc. 98–19485 Filed 7–22–98; 8:45 am]

BILLING CODE 4910–13–U

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 98–ANE–26–AD; Amendment

39–10667; AD 98–15–16]

RIN 2120–AA64

Airworthiness Directives; BombardierRotax GmbH 912 F Series

Reciprocating 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 Bombardier-Rotax GmbH

912 F series reciprocating engines. This

action requires installation of an

improved fuel pump and fuel supply

tube. This amendment is prompted by

reports of fuel leaks at the outlet port of

the fuel pump. The actions specified in

this AD are intended to prevent fuel

leaks from the fuel pump, which could

result in undetected loss of fuel in flight

or, an engine fire.

DATES: Effective August 7, 1998.

The incorporation by reference of

certain publications listed in the

regulations is approved by the Director

of the Federal Register as of August 7,

1998.

Comments for inclusion in the Rules

Docket must be received on or before

September 21, 1998.

ADDRESSES: Submit comments in

triplicate to the Federal Aviation

Administration (FAA), New England

Region, Office of the Regional Counsel,

Attention: Rules Docket No. 98–ANE–

26–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

Bombardier-Rotax GmbH, Welser

Strasse 32, A–4623 Gunskirchen,

Austria; telephone 7246–601–232, fax

7246–601–370. 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:

James Lawrence, Aerospace Engineer,

Engine Certification Office, FAA, Engine

and Propeller Directorate, 12 New

England Executive Park, Burlington, MA

01803–5299; telephone (781) 238–7176,

fax (781) 238–7199.

SUPPLEMENTARY INFORMATION: The

Austro Control GmbH (ACG), which is

the airworthiness authority for Austria,

recently notified the FAA that an unsafe

condition may exist on BombardierRotax GmbH 912 F series reciprocating

engines. The ACG advises that they

have received reports of fuel leaks at the

outlet port of the fuel pump. One

service difficulty report indicated that

up to approximately one half of the fuel

tank contents was lost in flight as a

result of a large crack forming at the

base of the fuel pump outlet port. This

was the second occurrence of fuel leak

on that particular engine. The

investigation revealed misalignment of

the rigid tube connecting the fuel

distribution manifold and fuel pump.

This condition, if not corrected, could

result in fuel leaks from the fuel pump,

which could result in undetected loss of

fuel in flight or, an engine fire.

Bombardier-Rotax GmbH has issued

Technical Bulletin (TB) No. 912–20 R1,

dated February 10, 1998, that specifies

procedures for installation of an

improved fuel pump and fuel supply

tube. The ACG classified this TB as

mandatory and issued AD 94/1 in order

to assure the airworthiness of these

engines in Austria.

This engine model is manufactured in

Austria 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. Pursuant to

this bilateral airworthiness agreement,

the ACG has kept the FAA informed of

the situation described above. The FAA

has examined the findings of the ACG,

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.

Since an unsafe condition has been

identified that is likely to exist or

develop on other engines of the same

type design registered in the United

States, the AD requires installation of an

improved fuel pump and fuel supply

tube. The actions would be required to

be accomplished in accordance with the

TB 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