16070 Federal Register / Vol. 62, No. 65 / Friday, April 4, 1997 / Rules and Regulations

U.S. operators is estimated to be $1,500,

or $60 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.

Regulatory Impact

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:

97–07–08 Jetstream Aircraft Limited:

Amendment 39–9982. Docket 96–NM–131–

AD.

Applicability: Model 4101 airplanes, as

listed in Jetstream Service Bulletin J41–11–

014, dated January 18, 1996; certificated in

any category.

Note 1: This AD applies to each airplane

identified in the preceding applicability

provision, regardless of whether it has been

otherwise 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 failure of the front bulkhead of

the aft main baggage bay and the doors of the

aft right stowage compartment during

emergency landing dynamic conditions,

which consequently could result in injury to

passengers and flight crew and hinder

evacuation of the airplane through the exit

adjacent to the bulkhead, accomplish the

following:

(a) For all airplanes: Within 30 days after

the effective date of this AD, replace the

weight limitation placards in the aft main

baggage bay and aft right stowage

compartment with new placards indicating

lower maximum weight limitations, in

accordance with Jetstream Service Bulletin

J41–11–014, dated January 18, 1996.

(b) For airplanes having constructor

numbers 41041 through 41043 inclusive,

41045, 41055, 41058, 41059, 41063, and

41064: Within 30 days after the effective date

of this AD, after accomplishment of the

requirements of paragraph (a) of this AD,

revise the FAA-approved Airplane Flight

Manual by removing Amendment P25, in

accordance with Jetstream Service Bulletin

J41–11–014, dated January 18, 1996.

(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

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 Jetstream Service Bulletin J41–11–014,

dated January 18, 1996. 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.

(f) This amendment becomes effective on

May 9, 1997.

Issued in Renton, Washington, on March

26, 1997.

Darrell M. Pederson,

Acting Manager, Transport Airplane

Directorate, Aircraft Certification Service.

[FR Doc. 97–8265 Filed 4–3–97; 8:45 am]

BILLING CODE 4910–13–U

14 CFR Part 39

[Docket No. 96–NM–101–AD; Amendment

39–9983; AD 97–07–09]

RIN 2120–AA64

Airworthiness Directives; Airbus Model

A300 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 series airplanes, that requires

repetitive checks and testing of certain

equipment that regulates the flow of fuel

from wing tank 2A to the number 2

engine. This amendment also requires

replacement of this equipment with

equipment that has been designed to

prevent incorrect installation; this

replacement is considered to be

terminating action for the repetitive

equipment checks and tests. This

amendment is prompted by reports

indicating that the incorrect installation

of this equipment has caused the flight

crew to shut off, rather than open,

certain valves that regulate the flow of

fuel from between this tank and engine.

The actions specified by this AD are

intended to detect and rectify incorrect

installations, which could result in the

flight crew inadvertently shutting off the

flow of fuel to the engine, and

consequent engine failure during flight.

DATES: Effective May 9, 1997.

The incorporation by reference of

certain publications listed in the

regulations is approved by the Director

of the Federal Register as of May 9,

1997.

ADDRESSES: The service information

referenced in this AD may be obtained

from Airbus Industrie, 1 Rond Point

Maurice Bellonte, 31707 Blagnac Cedex,
Federal Register / Vol. 62, No. 65 / Friday, April 4, 1997 / Rules and Regulations 16071

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: Tim

Backman, Aerospace Engineer,

Standardization Branch, ANM–113,

FAA, Transport Airplane Directorate,

1601 Lind Avenue, SW., Renton,

Washington 98055–4056; telephone

(206) 227–2797; fax (206) 227–1149.

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 Airbus

Model A300 series airplanes was

published in the Federal Register on

January 13, 1997 (62 FR 1695). That

action proposed to require repetitive

checks of the control knobs on isolation

valve and crossfeed valve control unit

5QB; and repetitive tests of this control

unit. As terminating action for these

repetitive checks and tests, that action

also proposed to require that operators

replace these knobs and this control

unit with knobs and a control unit that

have been modified.

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 advises that it does

not operate the affected Airbus series

aircraft and, therefore, is not affected by

this rule.

Conclusion

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.

Cost Impact

The FAA estimates that 13 Airbus

Model A300 airplanes of U.S. registry

will be affected by this AD.

It will take approximately 1 work

hour per airplane to accomplish each

required check and test cycle, at an

average labor rate of $60 per work hour.

Based on these figures, the cost impact

of the required check and test on U.S.

operators is estimated to be $780, or $60

per airplane, per check/test cyle.

It will take approximately 1 work

hour per airplane to accomplish the

required replacement of the control

knobs and control unit, at an average

labor rate of $60 per work hour.

Required parts will cost approximately

$1,043 per airplane. Based on these

figures, the cost impact of the required

replacement on U.S. operators is

estimated to be $14,339, or $1,103 per

airplane.

The cost impact figures discussed

above are 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.

Regulatory Impact

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:

97–07–09 Airbus Industrie: Amendment 39–

9983. Docket 96–NM–101–AD.

Applicability: Model A300 series airplanes,

as listed in the Airbus service documents

referenced in paragraphs (a), (b), and (c) of

this AD; certificated in any category.

Note 1: This AD applies to each airplane

identified in the preceding applicability

provision, regardless of whether it has been

otherwise 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 (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 the flight crew from

inadvertently shutting off the flow of fuel

from wing tank 2A to the number 2 engine,

due to the incorrect installation of the

isolation valve and crossfeed valve control

unit 5QB, and the consequent failure of the

engine, accomplish the following:

(a) For airplanes listed in Airbus A300 All

Operator Telex (AOT) 28–03, dated June 6,

1991: Within 30 days after the effective date

of this AD, perform a check and functional

test of the control knob configurations for the

isolation valve and crossfeed valve control

unit 5QB, in accordance with Airbus AOT

28–03, dated June 6, 1991.

(1) Repeat the check and test thereafter at

intervals not to exceed 500 hours time-inservice, and prior to further flight after any

maintenance action is performed on the

control unit.

(2) Any unit that does not successfully pass

the check/functional test, must be repaired or

otherwise rectified prior to further flight, in

accordance with the AOT.

(b) For airplanes listed in Airbus

Service Bulletin A300–28–055, Revision

3, dated December 19, 1991, as

amended by Service Bulletin Change

Notice 3.A., dated March 16, 1992:

Within 2 years after the effective date of

this AD, replace the crossfeed and isolation

valve control unit 5QB with a modified unit,

in accordance Airbus Service Bulletin A300–

28–055, Revision 3, dated December 19,

1991, as amended by Service Bulletin Change

Notice 3.A.

Note 2: Airbus Service Bulletin A300–28–

055, Revision 3, references L’e ́quipment et La

Construction Electrique (ECE) Service

Bulletins 28–195 and 28–196, both dated

August 31, 1983, as additional sources of

procedural information for replacement of

the control unit.

(c) For airplanes listed in Airbus

Service Bulletin A300–28–0061,
16072 Federal Register / Vol. 62, No. 65 / Friday, April 4, 1997 / Rules and Regulations

Revision 1, dated March 14, 1992:

Within 2 years after the effective date of

this AD, replace the control knobs on

the crossfeed and isolation valve control

unit 5QB with new knobs, in

accordance with Airbus Service Bulletin

A300–28–0061, Revision 1, dated March

14, 1992.

Note 3: Airbus Service Bulletin A300–28–

0061, Revision 1, references ECE Service

Bulletins 28–191, dated July 26, 1982, and

28–228, dated November 1, 1991, as

additional sources of procedural information

for replacement of the control knobs.

(d) Accomplishment of both of the

replacements specified in paragraphs (b) and

(c) of this AD constitutes terminating action

for the repetitive checks and tests required by

paragraph (a) of this AD.

(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,

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 4: Information concerning the

existence of approved alternative methods of

compliance with this AD, if any, may be

obtained from the Standardization Branch,

ANM–113.

(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 airplane to

a location where the requirements of this AD

can be accomplished.

(g) The actions shall be done in accordance

with the following Airbus service documents,

which contain the specified list of effective

pages:

Service bulletin referenced and date Page No. Revision level

shown on page

Date shown on

page

Airbus All Operator Telex (AOT) 28–03, June 6, 1991 ........................................... 1–3 ............................ ...................... June 6, 1991

Airbus Service Bulletin A300–28–055, Revision 3, December 19, 1991 ................ 1,4 ............................. 3 ....................... Dec. 19, 1991.

2, 3, 5, 6 .................... 2 ....................... Sept. 19, 1991.

7, 9, 10, 13 ................ Original ............. Oct. 16, 1983.

8, 11, 12 .................... 1 ....................... July 2, 1991.

Airbus Service Bulletin A300–28–055, Change Notice 3.A., March 16, 1992 ........ 1–2 ............................ ...................... Mar. 16, 1992

Airbus Service Bulletin A300–28–0061, Revision 1, March 14, 1992 ..................... 1 ................................ 1 ....................... Mar. 14, 1992.

2–7 ............................ Original ............. Jan. 23, 1992.

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 Airbus Industrie, 1 Rond Point Maurice

Bellonte, 31707 Blagnac Cedex, France.

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.

(h) This amendment becomes effective on

May 9, 1997.

Issued in Renton, Washington, on March

26, 1997.

S.R. Miller,

Acting Manager, Transport Airplane

Directorate, Aircraft Certification Service.

[FR Doc. 97–8266 Filed 4–3–97; 8:45 am]

BILLING CODE 4910–13–U

14 CFR Part 39

[Docket No. 96–SW–17-AD;

Amendment 39–9980; AD 97–07–06]

RIN 2120–AA64

Airworthiness Directives; Bell

Helicopter Textron, Inc. Model 412

Helicopters

AGENCY: Federal Aviation

Administration, DOT.

ACTION: Final rule.

SUMMARY: This amendment supersedes

an existing priority letter airworthiness

directive (AD), applicable to Bell

Helicopter Textron, Inc. Model 412

helicopters, that currently requires a

daily inspection of certain swashplate

support assemblies. It also requires a

reduction in VNE, and installation of

appropriate airspeed indicator markings

and a placard. This amendment requires

the same actions required by the

existing priority letter AD, but restricts

the applicability to the Model 412

helicopters with a certain steel main

rotor control swashplate support

assembly (steel swashplate support

assembly) installed. This amendment

also allows the installation of an

improved main rotor control swashplate

assembly that terminates the

requirements of this AD. This

amendment is prompted by reported

cracking and in-service failures of

certain steel swashplate support

assemblies. The actions specified by this

AD are intended to prevent failure of the

steel swashplate support assembly that

could result in loss of main rotor control

and subsequent loss of control of the

helicopter.

DATES: Effective May 9, 1997.

The incorporation by reference of

certain publications listed in the

regulations is approved by the Director

of the Federal Register as of May 9,

1997.

ADDRESSES: The service information

referenced in this AD may be obtained

from Bell Helicopter Textron, Inc., P.O.

Box 482, Fort Worth, Texas 76101. This

information may be examined at the

FAA, Office of the Assistant Chief

Counsel, 2601 Meacham Blvd., Room

663, Fort Worth, Texas, or at the Office

of the Federal Register, 800 North

Capitol Street, NW., suite 700,

Washington, DC.

FOR FURTHER INFORMATION CONTACT: Mr.

Charles Harrison, Aerospace Engineer,

Federal Aviation Administration,

Southwest Region, Rotorcraft

Certification Office, ASW–170, Fort

Worth, Texas 76193–0170, telephone

(817) 222–5447, FAX (817) 222–5959.

SUPPLEMENTARY INFORMATION: A

proposal to amend part 39 of the Federal

Aviation Regulations (14 CFR part 39)

by superseding priority letter AD 92–

03–13, issued January 31, 1992, which

is applicable to Bell Helicopter Textron,

Inc. Model 412 helicopters, was

published in the Federal Register on

October 25, 1996 (61 FR 55231). That

action proposed to require a daily

inspection of certain steel main rotor

control swashplate support assemblies,

a reduction in VNE, and installation of

appropriate airspeed markings and a

placard. It also proposed an optional

installation of an improved steel main

rotor control swashplate support

assembly or an aluminum swashplate

support assembly, that, when installed,

constitutes a terminating action for the

requirements of this AD.

Interested persons have been afforded

an opportunity to participate in the

making of this amendment. No

comments were received on the

proposal or the FAA’s determination of

the cost to the public. The FAA has

determined that air safety and the

public interest require the adoption of

the rule with one change—a reference to

a specific part of a service bulletin was

added for clarification. The FAA has

determined that this change will neither

increase the economic burden on any