14014 Federal Register / Vol. 61, No. 62 / Friday, March 29, 1996 / Rules and Regulations

series airplanes is estimated to be

$2,640, or $60 per airplane.

Should an operator of Model F28

Mark 0100 series airplanes be required

to accomplish the necessary bolt

replacement, it will take approximately

7 work hours per airplane to accomplish

the replacement, at an average labor rate

of $60 per work hour. Required parts

will cost approximately $100 per

airplane. Based on these figures, the cost

impact of any necessary replacement

action is estimated to be $520 per

airplane.

The cost impact figure discussed

above is based on assumptions that no

operator has yet accomplished any of

the requirements of this AD action, and

that no operator would accomplish

those actions in the future if this AD

were not adopted.

Currently there are no Fokker Model

F27 Mark 050 series airplanes on the

U.S. Register. However, should an

affected airplane be imported and

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

it will take approximately 1 work hour

per airplane to accomplish the required

inspection, at an average labor rate of

$60 per work hour. Based on these

figures, the impact of the required

inspection on operators of Model F27

Mark 050 series airplanes will be $60

per airplane.

Should an operator of Model F27

Mark 050 series airplanes be required to

accomplish the necessary bolt

replacement, it will take approximately

17 work hours per airplane to

accomplish the replacement, at an

average labor rate of $60 per work hour.

Required parts will cost approximately

$150 per airplane. Based on these

figures, the cost impact of any necessary

replacement action is estimated to be

$1,170 per airplane.

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.

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:

96–07–04 Fokker: Amendment 39–9553.

Docket 95–NM–70–AD.

Applicability: Model F27 Mark 050 series

airplanes having serial numbers 20247

through 20292 inclusive, and 20294 through

20297 inclusive; and Model F28 Mark 0100

series airplanes having serial numbers 11390

through 11479 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 electrical arcing and

subsequent loss of the associated electrical

system, which could result in the potential

for an electrical fire, accomplish the

following:

(a) Within 12 months after the effective

date of this AD, perform an inspection to

verify if adequate clearance exists between

the insulation screen and the two adjacent

terminal bolts in accordance with Fokker

Service Bulletin SBF100–20–001, dated

January 15, 1994 (for Model F28 Mark 0100

series airplanes), or Fokker Service Bulletin

SBF50–20–003, dated January 11, 1994 (for

Model F27 Mark 050 series airplanes), as

applicable.

(1) If adequate clearance is found, no

further action is required by this AD.

(2) If inadequate clearance is found, prior

to further flight, replace the circuit breaker

terminal bolts with new bolts in accordance

with the applicable 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,

Standardization Branch, ANM–113, 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, 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.

(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 and replacement shall

be done in accordance with Fokker Service

Bulletin SBF100–20–001, dated January 15,

1994, or Fokker Service Bulletin SBF50–20–

003, dated January 11, 1994, as applicable.

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 Aircraft USA, Inc., 1199 North

Fairfax Street, Alexandria, Virginia 22314.

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.

(e) This amendment becomes effective on

April 29, 1996.

Issued in Renton, Washington, on March

21, 1996.

Darrell M. Pederson,

Acting Manager, Transport Airplane

Directorate, Aircraft Certification Service.

[FR Doc. 96–7400 Filed 3–28–96; 8:45 am]

BILLING CODE 4910–13–P

14 CFR Part 39

[Docket No. 95–NM–86–AD; Amendment

39–9555; AD 96–07–06]

Airworthiness Directives; Fokker

Model F28 Mark 0100 Series Airplanes

AGENCY: Federal Aviation

Administration, DOT.

ACTION: Final rule.

SUMMARY: This amendment adopts a

new airworthiness directive (AD),

applicable to certain Fokker Model F28

Mark 0100 series airplanes, that requires
Federal Register / Vol. 61, No. 62 / Friday, March 29, 1996 / Rules and Regulations 14015

inspection(s) to verify that the position

indicator of the fuel balance transfer

valve (FBTV) is in the closed position,

and closing the FBTV, if necessary; and

deactivation of the fuel balance transfer

system (FBTS). This amendment is

prompted by a report that, under certain

failure conditions, the actuator of the

FBTV could remain in the open position

without a flight deck indication. The

actions specified by this AD are

intended to ensure that the FBTV is not

in the open position during flight,

which could lead to the reduction of

fuel supply to the engines during crossfeed operation and consequent engine

fuel starvation.

DATES: Effective April 29, 1996.

The incorporation by reference of

certain publications listed in the

regulations is approved by the Director

of the Federal Register as of April 29,

1996.

ADDRESSES: The service information

referenced in this AD may be obtained

from Fokker Aircraft USA, Inc., 1199

North Fairfax Street, Alexandria,

Virginia 22314. This information may be

examined at the Federal Aviation

Administration (FAA), Transport

Airplane Directorate, Rules Docket,

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: Tim

Dulin, Aerospace Engineer,

Standardization Branch, ANM–113,

FAA, Transport Airplane Directorate,

1601 Lind Avenue SW., Renton,

Washington 98055–4056; telephone

(206) 227–2141; fax (206) 227–1149.

SUPPLEMENTARY INFORMATION: A

proposal to amend part 39 of the Federal

Aviation Regulations (14 CFR part 39) to

include an airworthiness directive (AD)

that is applicable to certain Fokker

Model F28 Mark 0100 series airplanes

was published in the Federal Register

on December 11, 1995 (60 FR 63470).

That action proposed to require

inspection(s) to verify that the position

indicator of the fuel balance transfer

valve (FBTV) is in the closed position,

and closing the FBTV, if necessary; and

deactivation of the fuel balance transfer

system (FBTS).

Interested persons have been afforded

an opportunity to participate in the

making of this amendment. Due

consideration has been given to the

single comment received.

The commenter supports the

proposed rule.

After careful review of the available

data, including the comment noted

above, the FAA has determined that air

safety and the public interest require the

adoption of the rule as proposed.

The FAA estimates that 4 airplanes of

U.S. registry will be affected by this AD,

that it will take approximately 4 work

hours per airplane to accomplish the

required actions, and that the average

labor rate is $60 per work hour.

Required parts will cost approximately

$250 per airplane. Based on these

figures, the cost impact of the AD on

U.S. operators is estimated to be $1,960,

or $490 per airplane.

The cost impact figure discussed

above is based on assumptions that no

operator has yet accomplished any of

the requirements of this AD action, and

that no operator would accomplish

those actions in the future if this AD

were not adopted.

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.

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:

96–07–06 Fokker: Amendment 39–9555.

Docket 95–NM–86–AD.

Applicability: Model F28 Mark 0100 series

airplanes, as listed in Fokker Service Bulletin

SBF100–28–030, Revision 1, dated December

5, 1994; 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 the reduction of fuel supply to

the engines during cross-feed operation,

which could lead to engine fuel starvation,

accomplish the following:

(a) After the effective date of this AD,

whenever the fuel balance transfer system

(FBTS) is used during maintenance, prior to

further flight, perform an inspection to verify

that the position indicator of the fuel balance

transfer valve (FBTV) is in the closed

position, in accordance with Fokker Service

Bulletin SBF100–28–030, Revision 1, dated

December 5, 1994. The inspection

requirements of this paragraph must be

accomplished until the deactivation required

by paragraph (b) of this AD is accomplished.

(1) If the position indicator is in the closed

position, no further action is required by this

paragraph.

(2) If the position indicator is in the open

position, close the FBTV in accordance with

the service bulletin.

(b) Within 90 days after the effective date

of this AD, deactivate the FBTS in

accordance with either Part 2 or Part 3 of the

Accomplishment Instructions of Fokker

Service Bulletin SBF100–28–030, Revision 1,

dated December 5, 1994, as applicable.

Accomplishment of the deactivation

constitutes terminating action for the

repetitive inspection requirements of

paragraph (a) 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,

Standardization Branch, ANM–113, 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, Standardization

Branch, ANM–113.

Note 2: Information concerning the

existence of approved alternative methods of
14016 Federal Register / Vol. 61, No. 62 / Friday, March 29, 1996 / Rules and Regulations

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) The actions shall be done in accordance

with Fokker Service Bulletin SBF100–28–

030, Revision 1, dated December 5, 1994,

which contains the following list of effective

pages:

Page No.

Revision level

shown on

page

Date shown

on page

1–3, 5, 8, 10 . 1 ................... December 5,

1994.

4, 6, 7, 9 ....... Original ........ August 28,

1994.

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 Aircraft USA, Inc., 1199 North

Fairfax Street, Alexandria, Virginia 22314.

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

April 29, 1996.

Issued in Renton, Washington, on March

21, 1996.

Darrell M. Pederson,

Acting Manager, Transport Airplane

Directorate, Aircraft Certification Service.

[FR Doc. 96–7399 Filed 3–28–96; 8:45 am]

BILLING CODE 4910–13–P

14 CFR Part 39

[Docket No. 95–NM–136–AD; Amendment

39–9554; AD 96–07–05]

Airworthiness Directives; Dornier

Model 328–100 Series Airplanes

AGENCY: Federal Aviation

Administration, DOT.

ACTION: Final rule.

SUMMARY: This amendment adopts a

new airworthiness directive (AD),

applicable to certain Dornier Model

328–100 series airplanes, that requires

installation of a reinforcement doubler

on the rudder skin. This amendment is

prompted by the results of a design

review of this airplane model that

revealed inadequate structural strength

of the attachment fitting of the rudder

damper and of the adjacent structure.

The actions specified by this AD are

intended to prevent failure of the

attachment structure of the rudder

damper in the event of aerodynamic

gust loads, as the result of inadequate

structural strength of the subject

structure.

DATES: Effective April 29, 1996.

The incorporation by reference of

certain publications listed in the

regulations is approved by the Director

of the Federal Register as of April 29,

1996.

ADDRESSES: The service information

referenced in this AD may be obtained

from Dornier Luftfahrt GmbH, P.O. Box

1103, D–82230 Wessling, Germany. This

information may be examined at the

Federal Aviation Administration (FAA),

Transport Airplane Directorate, Rules

Docket, 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: Gary

Lium, Aerospace Engineer,

Standardization Branch, ANM–113,

FAA, Transport Airplane Directorate,

1601 Lind Avenue, SW., Renton,

Washington 98055–4056; telephone

(206) 227–1112; fax (206) 227–1149.

SUPPLEMENTARY INFORMATION: A

proposal to amend part 39 of the Federal

Aviation Regulations (14 CFR part 39) to

include an airworthiness directive (AD)

that is applicable to certain Dornier

Model 328–100 series airplanes was

published in the Federal Register on

January 3, 1996 (61 FR 133). That action

proposed to require installation of a

reinforcement doubler on the rudder

skin.

Interested persons have been afforded

an opportunity to participate in the

making of this amendment. Due

consideration has been given to the

single comment received.

The commenter supports the

proposed rule.

After careful review of the available

data, including the comment noted

above, the FAA has determined that air

safety and the public interest require the

adoption of the rule as proposed.

The FAA estimates that 12 airplanes

of U.S. registry will be affected by this

AD, that it will take approximately 2

work hours per airplane to accomplish

the required actions, and that the

average labor rate is $60 per work hour.

Required parts will be supplied by the

manufacturer at no cost to operators.

Based on these figures, the cost impact

of the AD on U.S. operators is estimated

to be $1,440, or $120 per airplane.

The cost impact figure discussed

above is based on assumptions that no

operator has yet accomplished any of

the requirements of this AD action, and

that no operator would accomplish

those actions in the future if this AD

were not adopted.

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.

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:

96–07–05 Dornier: Amendment 39–9554.

Docket 95–NM–136–AD.

Applicability: Model 328–100 series

airplanes, serial numbers 3005 through 3024

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