17988 Federal Register / Vol. 60, No. 68 / Monday, April 10, 1995 / Rules and Regulations

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. App. 1354(a), 1421

and 1423; 49 U.S.C. 106(g); and 14 CFR

11.89.

§ 39.13 [Amended] –

2. Section 39.13 is amended by

adding the following new airworthiness

directive:

95–08–02 Jetstream Aircraft Limited:

Amendment 39–9191. Docket 94–NM–

170–AD.

Applicability: Model 4101 airplanes;

constructors numbers 41005 through 41015

inclusive, 41019 through 41024 inclusive,

41028, and 41029; 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 use the authority

provided in paragraph (b) to request approval

from the FAA. This approval may address

either no action, if the current configuration

eliminates the unsafe condition; or different

actions necessary to address the unsafe

condition described in this AD. Such a

request should include an assessment of the

effect of the changed configuration on the

unsafe condition addressed by this AD. In no

case does the presence of any modification,

alteration, or repair remove any airplane from

the applicability of this AD.

Compliance: Required as indicated, unless

accomplished previously.

To prevent the loss of the main system

hydraulics, accomplish the following:

(a) Within 4 months after the effective date

of this AD, install new case drain pipes and

an additional fairlead support for the

hydraulics case drain line in the rear spar

area of the engine/nacelle in accordance with

Jetstream Service Bulletin J41–29–005,

Revision 1, dated August 12, 1994; or

Revision 2, dated August 30, 1994.

(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, FAA, Transport

Airplane Directorate, 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.

(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 installation shall be done in

accordance with the following Jetstream

service bulletins, as applicable, which

contain the specified effective pages:

Service bulletin referenced and date– Page No.

Revision

level shown

on page

Date shown on

page

J41–29–005– .................................................................................................................................. 1, 4– 2 .................. Aug. 30, 1994.

Revision 2

August 30, 1994 ............................................................................................................................. 2, 3, 5–12– 1 .................. Aug. 12, 1994.

J41–29–005– .................................................................................................................................. 1–12– 1– ................ Aug. 12, 1994.

Revision 1

August 12, 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 Jetstream Aircraft, Inc., P.O. Box 16029,

Dulles International Airport, Washington, DC

20041–6029. 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

May 10, 1995.

Issued in Renton, Washington, on March

31, 1995.

Darrell M. Pederson,

Acting Manager, Transport Airplane

Directorate, Aircraft Certification Service.

[FR Doc. 95–8445 Filed 4–7–95; 8:45 am]

BILLING CODE 4910–13–U

14 CFR Part 39

[Docket No. 94–NM–169–AD; Amendment

39–9190; AD 95–08–01]

Airworthiness Directives; Jetstream

Model 4101 Airplanes

AGENCY: Federal Aviation

Administration, DOT.

ACTION: Final rule.

SUMMARY: This amendment adopts a

new airworthiness directive (AD),

applicable to certain Jetstream Model

4101 airplanes, that requires

modification of the spoiler system. This

amendment is prompted by reports of

fatigue failures of the tee fittings of the

spoiler bleed nipples. The actions

specified by this AD are intended to

ensure that the tee fittings do not fail,

and subsequently lead to loss of the

main system hydraulics.

DATES: Effective May 10, 1995.

The incorporation by reference of

certain publications listed in the

regulations is approved by the Director

of the Federal Register as of May 10,

1995.

ADDRESSES: The service information

referenced in this AD may be obtained

from Jetstream Aircraft, Inc., P.O. Box

16029, Dulles International Airport,

Washington, DC 20041–6029. 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: Sam

Grober, Aerospace Engineer,

Standardization Branch, ANM–113,

FAA, Transport Airplane Directorate,

1601 Lind Avenue, SW., Renton,

Washington 98055–4056; telephone

(206) 227–1187; fax (206) 227–1320.
Federal Register / Vol. 60, No. 68 / Monday, April 10, 1995 / Rules and Regulations 17989

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 Jetstream

Model 4101 airplanes was published in

the Federal Register on December 16,

1994 (59 FR 64873). That action

proposed to require modification of the

spoiler system.

Interested persons have been afforded

an opportunity to participate in the

making of this amendment. No

comments were submitted in response

to the proposal or the FAA’s

determination of the cost to the public.

After careful review of the available

data, the FAA has determined that air

safety and the public interest require the

adoption of the rule as proposed.

The FAA estimates that 14 airplanes

of U.S. registry will be affected by this

AD, that it will take approximately 7

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 the operators.

Based on these figures, the total cost

impact of the AD on U.S. operators is

estimated to be $5,880, or $420 per

airplane.

The total 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. App. 1354(a), 1421

and 1423; 49 U.S.C. 106(g); and 14 CFR

11.89.

§ 39.13 [Amended]

2. Section 39.13 is amended by

adding the following new airworthiness

directive:

95–08–01 Jetstream Aircraft Limited:

Amendment 39–9190. Docket 94–NM–

169–AD.

Applicability: Model 4101 airplanes on

which Jetstream Modification JM41290B

(reference Jetstream Service Bulletin J41–29–

001) has not been installed, 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 use the authority

provided in paragraph (b) to request approval

from the FAA. This approval may address

either no action, if the current configuration

eliminates the unsafe condition; or different

actions necessary to address the unsafe

condition described in this AD. Such a

request should include an assessment of the

effect of the changed configuration on the

unsafe condition addressed by this AD. In no

case does the presence of any modification,

alteration, or repair remove any airplane from

the applicability of this AD.

Compliance: Required as indicated, unless

accomplished previously.

To prevent failure of the tee fittings and

subsequent loss of the main system

hydraulics, accomplish the following:

(a) Within 4 months after the effective date

of this AD, modify the spoiler system in

accordance with Jetstream Service Bulletin

J41–29–001, dated August 12, 1994, or

Revision 1, dated August 30, 1994.

(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, FAA, Transport

Airplane Directorate, 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.

(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 modification shall be done in

accordance with the following Jetstream

service bulletins, as applicable, which

contain the specified effective pages:

Service bulletin referenced and date Page No.

Revision

level shown

on page

Date shown on

page

J41–29–001 Original Issue, August 12, 1994 ................................................................................ 1–12 Original ........ Aug. 12, 1994.

J41–29–001 Revision 1, August 30, 1994 ..................................................................................... 1, 3 1 .................. Aug. 30, 1994.

2, 4–12 Original ........ Aug. 12, 1994.
17990 Federal Register / Vol. 60, No. 68 / Monday, April 10, 1995 / Rules and Regulations

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 Jetstream Aircraft, Inc., P.O. Box 16029,

Dulles International Airport, Washington, DC

20041–6029. 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

May 10, 1995.

Issued in Renton, Washington, on March

31, 1995.

Darrell M. Pederson,

Acting Manager, Transport Airplane

Directorate, Aircraft Certification Service.

[FR Doc. 95–8446 Filed 4–7–95; 8:45 am]

BILLING CODE 4910–13–U

14 CFR Part 39

[Docket No. 94–NM–192–AD; Amendment

39–9187; AD 95–07–05]

Airworthiness Directives; Airbus Model

A300–600 Series Airplanes

AGENCY: Federal Aviation

Administration, DOT.

ACTION: Final rule.

SUMMARY: This amendment adopts a

new airworthiness directive (AD),

applicable to certain Airbus Model

A300–600 series airplanes, that requires

repetitive ultrasonic inspections to

detect cracks in the bolt holes inboard

and outboard of rib 9 on the bottom

booms of the front and rear wing spars,

and repair, if necessary. This

amendment is prompted by the

discovery of fatigue cracks that

emanated from the bolt holes inboard

and outboard of rib 9 in the bottom

booms of the front and rear wing spars.

The actions specified by this AD are

intended to prevent reduced structural

integrity of a wing spar as a result of

fatigue cracks in the bolt holes.

DATES: Effective May 10, 1995.

The incorporation by reference of

certain publications listed in the

regulations is approved by the Director

of the Federal Register as of May 10,

1995.

ADDRESSES: The service information

referenced in this AD may be obtained

from Airbus Industrie, 1 Rond Point

Maurice Bellonte, 31707 Blagnac Cedex,

France. 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:

Stephen Slotte, Aerospace Engineer,

Standardization Branch, ANM–113,

FAA, Transport Airplane Directorate,

1601 Lind Avenue, SW., Renton,

Washington 98055–4056; telephone

(206) 227–2797; fax (206) 227–1320.

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 Airbus

Model A300–600 series airplanes was

published in the Federal Register on

December 15, 1994 (59 FR 64626). That

action proposed to require repetitive

ultrasonic inspections to detect cracks

in the bolt holes inboard and outboard

of rib 9 on the bottom booms of the front

and rear wing spars, and repair, if

necessary.

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.

As a result of recent communications

with the Air Transport Association

(ATA) of America, the FAA has learned

that, in general, some operators may

misunderstand the legal effect of AD’s

on airplanes that are identified in the

applicability provision of the AD, but

that have been altered or repaired in the

area addressed by the AD. The FAA

points out that all airplanes identified in

the applicability provision of an AD are

legally subject to the AD. If an airplane

has been altered or repaired in the

affected area in such a way as to affect

compliance with the AD, the owner or

operator is required to obtain FAA

approval for an alternative method of

compliance with the AD, in accordance

with the paragraph of each AD that

provides for such approvals. A note has

been added to this final rule to clarify

this long-standing requirement.

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 with the change

previously described. The FAA has

determined that this change will neither

increase the economic burden on any

operator nor increase the scope of the

AD.

The FAA estimates that 35 airplanes

of U.S. registry will be affected by this

AD, that it will take approximately 11

work hours per airplane to accomplish

the required actions, and that the

average labor rate is $60 per work hour.

Based on these figures, the total cost

impact of the AD on U.S. operators is

estimated to be $23,100, or $660 per

airplane.

The total 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. App. 1354(a), 1421

and 1423; 49 U.S.C. 106(g); and 14 CFR

11.89.

39.13 [Amended]

2. Section 39.13 is amended by

adding the following new airworthiness

directive:

95–07–05 Airbus Industrie: Amendment 39–

9187. Docket 94–NM–192–AD.

Applicability: Model A300–600 series

airplanes on which Airbus Modification