Federal Register / Vol. 65, No. 93 / Friday, May 12, 2000 / Rules and Regulations 30529

safety and the public interest require the

adoption of the rule with the changes

described previously. The FAA has

determined that these changes will

neither increase the economic burden

on any operator nor increase the scope

of the AD.

Economic Analysis

There are approximately 1,000

engines of the affected design in the

worldwide fleet. The FAA estimates that

102 engines installed on aircraft of US

registry will be affected by this AD. It

will take approximately 4 work hours

per engine to accomplish the required

actions. The average labor rate is $60

per work hour. Required parts will cost

approximately $160 per engine. Based

on these figures, the total cost impact of

the AD on US operators is estimated to

be $40,800.

Regulatory Impact

This rule does not have federalism

implications, as defined in Executive

Order 13132, because it does 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. Accordingly, the

FAA has not consulted with state

authorities prior to publication of this

rule.

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 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, 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:

2000–09–14 Rolls-Royce plc: Amendment

39–11723. Docket No. 2000–NE–04–AD.

Applicability: Rolls-Royce plc RB211–535

series turbofan engines, with radial drive

steady bearings with outer race serial number

(S/N) prefixes: DLJO, DLJP, DLOQ, DLSK,

and DMBA, installed. Affected engines are

those that have had a new bearing fitted at

overhaul, were new production engines, or

had a bearing changed in service between

July 26, 1998, and September 30, 1999. These

engines are installed on but not limited to

Boeing 757 series aircraft and Tupolev Tu204

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 (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; 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 radial drive steady bearing

failure, which could result in an in-flight

engine shutdown and smoke and fumes in

the cabin, accomplish the following:

Remove Suspect Bearings

(a) Remove from service radial drive steady

bearings identified in the applicability

paragraph of this AD and replace with

serviceable parts as follows:

(1) For engines that had the suspect radial

drive steady bearings installed during a shop

visit or on-wing, remove from service before

accumulating 1,700 hours time-in-service

(TIS) after the effective date of this AD, but

no later than September 30, 2000.

(2) For engines that had the suspect radial

drive steady bearings installed in factory

production, remove from service before

accumulating 2,720 hours TIS after the

effective date of this AD, but no later than

December 31, 2000.

Note 2: Rolls-Royce plc Mandatory Service

Bulletin No. RB.211–72–C930, dated

December 22, 1999, provides additional

information on identifying and replacing the

suspect bearings.

Do Not Install Suspect Bearings

(b) As of the effective date of this AD,

accomplish the following:

(1) Do not install radial drive steady

bearings from the five affected batches listed

in the applicability paragraph of this AD at

overhaul, in service, or at new production.

(2) If performing an engine change, do not

allow two engines that have bearings from

any of the five affected batches listed in the

applicability paragraph of this AD to be

installed on the same airplane.

Serviceable Parts

(3) For the purpose of this AD, serviceable

bearings are those which are not listed in the

applicability paragraph of this AD. Current

outer race S/N prefix DPSF or alphabetically

subsequent prefix is considered serviceable.

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, Engine

Certification Office (ECO). Operators shall

submit their request through an appropriate

FAA Principal Maintenance Inspector, who

may add comments and then send it to the

Manager, ECO.

Note 3: Information concerning the

existence of approved alternative methods of

compliance with this airworthiness directive,

if any, may be obtained from the ECO.

Ferry Flights

(d) Special flight permits may be issued in

accordance with §§ 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.

Effective Date

(e) This amendment becomes effective on

July 11, 2000.

Issued in Burlington, Massachusetts, on

May 5, 2000.

David A. Downey,

Assistant Manager, Engine and Propeller

Directorate, Aircraft Certification Service.

[FR Doc. 00–11862 Filed 5–11–00; 8:45 am]

BILLING CODE 4910–13–P

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 99–NM–253–AD; Amendment

39–11720; AD 2000–09–11]

RIN 2120–AA64

Airworthiness Directives; Fokker

Model F.28 Mark 0070 Series Airplanes

AGENCY: Federal Aviation

Administration, DOT.

ACTION: Final rule; request for

comments.

SUMMARY: This amendment adopts a

new airworthiness directive (AD),

applicable to certain Fokker Model F.28

30530 Federal Register / Vol. 65, No. 93 / Friday, May 12, 2000 / Rules and Regulations

Mark 0070 series airplanes. This action

requires a one-time inspection to detect

loose bolts attaching the gustlock

counter-bracket to the pulley on the

elevator tension regulator assembly, and

corrective action, 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

prevent restricted elevator movement

and consequent reduced controllability

of the airplane.

DATES: Effective May 30, 2000.

The incorporation by reference of

certain publications listed in the

regulations is approved by the Director

of the Federal Register as of May 30,

2000.

Comments for inclusion in the Rules

Docket must be received on or before

June 12, 2000.

ADDRESSES: Submit comments in

triplicate to the Federal Aviation

Administration (FAA), Transport

Airplane Directorate, ANM–114,

Attention: Rules Docket No. 99–NM–

253–AD, 1601 Lind Avenue, SW.,

Renton, Washington 98055–4056.

The service information referenced in

this AD may be obtained from Fokker

Services B.V., P.O. Box 231, 2150 AE

Nieuw-Vennep, the Netherlands. 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:

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

Rijksluchtvaartdienst (RLD), which is

the airworthiness authority for the

Netherlands, notified the FAA that an

unsafe condition may exist on certain

Fokker Model F.28 Mark 0070 series

airplanes. The RLD advises that, during

a routine landing of a Model F.28 Mark

0070 series airplane, the flight crew

could not move the control column to

its fully aft position. A subsequent

inspection revealed that one of the three

bolts attaching the gustlock counterbracket to a pulley on the elevator

tension regulator assembly became

loose. The bolt had moved outwards

slightly, obstructing the driving lever of

the elevator and thus restricting the

elevator deflection to 21 degrees

(airplane nose up) instead of the normal

25 degrees. This condition, if not

corrected, could result in reduced

controllability of the airplane.

Explanation of Relevant Service

Information

Fokker has issued Service Bulletin

SBF100–27–076, dated July 1, 1999,

which describes procedures for a onetime general visual inspection to detect

discrepancies, and corrective action, if

necessary. Discrepancies include

improper installation, loose bolts,

sealant damage or an insufficient

amount of sealant, and incorrect torque

values of the bolts or nuts. Corrective

actions include removing the sealant (if

present) from the bolt head and nut and

checking the torque value of the bolt

and nut; replacing any discrepant bolt,

washer, or nut with a new component;

ensuring specified torque values; and

applying sealant to the bolt head and

nut to prevent corrosion.

Accomplishment of the inspections

and corrective actions specified in the

service bulletin is intended to

adequately address the identified unsafe

condition. The RLD classified this

service bulletin as mandatory and

issued Dutch airworthiness directive

1999–094, dated July 30, 1999, in order

to assure the continued airworthiness of

these airplanes in the Netherlands.

FAA’s Conclusions

This airplane model is manufactured

in the Netherlands 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 RLD has

kept the FAA informed of the situation

described above. The FAA has

examined the findings of the RLD,

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 the

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 restricted elevator movement

and consequent reduced controllability

of the airplane. This AD requires

accomplishment of the actions specified

in the service bulletin described

previously, except as described below.

Differences Between the Proposed AD

and the Service Bulletin

Operators should note that, although

the effectivity listing in the Planning

Information of the service bulletin

specifies ‘‘Model F.28 Mark 0070/0100’’

series airplanes, the applicability

statement of this proposed AD specifies

only ‘‘Model F.28 Mark 0070 series

airplanes.’’ The FAA has determined

that none of the affected Model F.28

Mark 0100 series airplanes are currently

eligible for import into the United

States; therefore, no action is required

for those airplanes by this AD. In

addition, the FAA points out that only

two of the airplanes listed in the service

bulletin are included in this proposed

AD because only serial numbers 11565

and 11569 are eligible for import into

the United States; the other serial

numbers listed in the service bulletin

are not eligible for import into the

United States.

Cost Impact

None of the Model F.28 Mark 0070

series airplanes affected by this action

are on the U.S. Register. All airplanes

included in the applicability of this rule

currently are operated by non-U.S.

operators under foreign registry;

therefore, they are not directly affected

by this AD action. However, the FAA

considers that this rule is necessary to

ensure that the unsafe condition is

addressed in the event that any of these

subject airplanes are imported and

placed on the U.S. Register in the future.

Should an affected airplane be

imported and placed on the U.S.

Register in the future, it would require

approximately 1 work hour to

accomplish the required actions, at an

average labor rate of $60 per work hour.

Based on these figures, the cost impact

of this AD on U.S. operators is estimated

to be $60 per airplane.

Determination of Rule’s Effective Date

Since this AD action does not affect

any airplane that is currently on the

U.S. register, it has no adverse economic

impact and imposes no additional

burden on any person. Therefore, prior

notice and public procedures hereon are

unnecessary and the amendment may be

made effective in less than 30 days after

publication in the Federal Register.

Comments Invited

Although this action is in the form of

a final rule and was not preceded by

notice and 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

Federal Register / Vol. 65, No. 93 / Friday, May 12, 2000 / Rules and Regulations 30531

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 99–NM–253–AD.’’ The

postcard will be date stamped and

returned to the commenter.

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:

2000–09–11 Fokker Services B.V.:

Amendment 39–11720. Docket 99–NM–

253–AD.

Applicability: Model F.28 Mark 0070

airplanes, serial numbers 11565 and 11569;

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 restricted elevator movement

and consequent reduced controllability of the

airplane, accomplish the following:

Inspection

(a) Within 2 months after the effective date

of this AD, perform a one-time general visual

inspection of the elevator gustlock counterbracket of the elevator tension regulator

assembly to detect any discrepancy

(including improper installation, loose bolts,

sealant damage or an insufficient amount of

sealant, and incorrect torque values of the

bolts or nuts), in accordance with the

Accomplishment Instructions of Fokker

Service Bulletin SBF100–27–076, dated July

1, 1999.

(1) If no discrepancy is detected, no further

action is required by this AD.

(2) If any discrepancy is detected, prior to

further flight, accomplish the applicable

corrective actions [removing the sealant (if

present) from the bolt head and nut and

checking the torque value of the bolt and nut;

replacing any discrepant bolt, washer, or nut

with a new component; ensuring specified

torque values; and applying sealant to the

bolt head and nut to prevent corrosion], in

accordance with the service bulletin.

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.’’

Alternative Methods of Compliance

(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,

International Branch, ANM–116, 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, International Branch,

ANM–116.

Note 3: 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

(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.

Incorporation by Reference

(d) The actions shall be done in accordance

with Fokker Service Bulletin SBF100–27–

076, dated July 1, 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 Fokker Services B.V., P.O.

Box 231, 2150 AE Nieuw-Vennep, the

Netherlands. 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 4: The subject of this AD is addressed

in Dutch airworthiness directive 1999–094,

dated July 30, 1999.

(e) This amendment becomes effective on

May 30, 2000.

Issued in Renton, Washington, on May 3,

2000.

Vi L. Lipski,

Acting Manager, Transport Airplane

Directorate, Aircraft Certification Service.

[FR Doc. 00–11546 Filed 5–11–00; 8:45 am]

BILLING CODE 4910–13–U