13620 Federal Register / Vol. 60, No. 49 / Tuesday, March 14, 1995 / Rules and Regulations

(third generation) fuse pin, no further action

is required by this AD.

(e) Installation of 15–5 corrosion resistant

steel (third generation) fuse pins in the

forward and aft positions of the upper link

on the inboard or outboard strut constitutes

terminating action for the requirements of

this AD.

(f) 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, 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, Manager, Seattle

ACO.

Note 5: Information concerning the

existence of approved alternative methods of

compliance with this AD, if any, may be

obtained from the Seattle ACO.

(g) 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.

(h) The replacement, inspections, and

installation shall be done in accordance with

Boeing Alert Service Bulletin 747–54A2166,

dated April 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 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.

(i) This amendment becomes effective on

April 13, 1995.

Issued in Renton, Washington, on March 3,

1995.

Darrell M. Pederson,

Acting Manager, Transport Airplane

Directorate, Aircraft Certification Service.

[FR Doc. 95–5781 Filed 3–13–95; 8:45 am]

BILLING CODE 4910–13–U

14 CFR Part 39

[Docket No. 94–NM–126–AD; Amendment

39–9168; AD 95–05–01]

Airworthiness Directives; British

Aerospace Model BAe 146–100A,

–200A, and –300A Series Airplanes

AGENCY: Federal Aviation

Administration, DOT.

ACTION: Final rule.

SUMMARY: This amendment adopts a

new airworthiness directive (AD),

applicable to all British Aerospace

Model BAe 146–100A, –200A, and

–300A series airplanes, that requires

conducting closed loop tests to

determine the setting of the

underfrequency trip level on suspect

generator control units (GCU), and

either the correction of discrepancies or

replacement of the GCU. This

amendment is prompted by several

malfunctions of in-service GCU’s due to

the effects of setting the underfrequency

trip level too high. The actions specified

by this AD are intended to correct

GCU’s that may have the

underfrequency level set too high,

which could result in the unwanted

shut down of an electrical generator;

this condition may lead to loss of all

generated electrical power on the

airplane when other generator faults or

failures occur.

DATES: Effective April 13, 1995.

The incorporation by reference of

certain publications listed in the

regulations is approved by the Director

of the Federal Register as of April 13,

1995.

ADDRESSES: The service information

referenced in this AD may be obtained

from British Aerospace Holdings, Inc.,

Avro International Aerospace Division,

P.O. Box 16039, Dulles International

Airport, Washington, DC 20041–6039.

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:

William Schroeder, Aerospace Engineer,

ANM–113, Standardization Branch,

FAA, Transport Airplane Directorate,

1601 Lind Avenue SW., Renton,

Washington 98055–4056; telephone

(206) 227–2148; 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 all British

Aerospace Model BAe 146–100A,

–200A, and –300A series airplanes was

published in the Federal Register on

November 16, 1994 (59 FR 59179). That

action proposed to require checking the

part and serial number on the data plate

of each GCU to identify discrepant

units, and conducting closed loop tests

on affected GCU’s to determine the

setting of the underfrequency trip level.

That action also proposed to require

either adjusting the underfrequency trip

level or replacing the discrepant GCU

with a serviceable unit, and conducting

post assembly testing.

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 43 airplanes

of U.S. registry will be affected by this

AD, that it will take approximately 1

work hour 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 $2,580, or $60 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
Federal Register / Vol. 60, No. 49 / Tuesday, March 14, 1995 / Rules and Regulations 13621

‘‘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:

95–05–01 British Aerospace Regional

Aircraft Limited, Avro International

Aerospace Division (Formerly British

Aerospace, plc; British Aerospace

Commercial Aircraft Limited):

Amendment 39–9168. Docket 94–NM–

126–AD.

Applicability: All Model British Aerospace

Model BAe 146–100A, –200A, and –300A

series airplanes, 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 correct generator control units (GCU)

that may have the under-frequency trip level

set too high, which could lead to the

unwanted shut down of an electrical

generator, accomplish the following:

(a) Within 6 months after the effective date

of this AD, check the part and serial number

on the data plate of each generator control

unit (GCU). If the part number is one of those

affected and the serial number is listed in

Addendum 1 of GEC-Marconi Service

Bulletin HGE 24–23, dated March 11, 1994,

prior to further flight, conduct a closed loop

test to determine the setting of the

underfrequency trip level, in accordance

with that service bulletin.

(1) If the level exceeds that specified in

GEC-Marconi Service Bulletin HGE 24–23,

dated March 11, 1994, prior to further flight,

adjust the level in accordance with that

service bulletin; or replace the GCU with a

serviceable unit, in accordance with Avro

Service Bulletin S.B. 24–103, dated March

24, 1994.

(2) Prior to further flight, after adjustment

or replacement of the GCU as required by

paragraph (a)(1) of this AD, conduct the post

assembly testing in accordance with Avro

Service Bulletin S.B. 24–103, dated March

24, 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, 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 closed loop test and adjustment

shall be done in accordance with GECMarconi Service Bulletin HGE 24–23, dated

March 11, 1994. The replacement and post

assembly test shall be done in accordance

with Avro Service Bulletin S.B. 24–103,

dated March 24, 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 British Aerospace Holding,

Inc., Avro International Aerospace Division,

P.O. Box 16039, Dulles International Airport,

Washington, DC 20041–6039. 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 13, 1995.

Issued in Renton, Washington, on February

27, 1995.

Darrell M. Pederson,

Acting Manager, Transport Airplane

Directorate, Aircraft Certification Service.

[FR Doc. 95–5246 Filed 3–13–95; 8:45 am]

BILLING CODE 4910–13–U

14 CFR Part 39

[Docket No. 94–NM–136–AD; Amendment

39–9169; AD 95–05–02]

Airworthiness Directives; Airbus Model

A300 B4–2C, B4–103, and B4–203

Series Airplanes; and Model A300–600

B4–620, B4–622, B4–603, and B4–601

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 and A300–600 series airplanes,

that requires modification of the fuel

tank jettison system. This amendment is

prompted by a quality survey which

revealed that the electrical bonding of

the fuel jettison system has insufficient

protection from a lightning strike. The

actions specified by this AD are

intended to prevent electrical arcing and

resultant fire in the event of a lightning

strike.

DATES: Effective April 13, 1995.

The incorporation by reference of

certain publications listed in the

regulations is approved by the Director

of the Federal Register as of April 13,

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 and A300–600 series