Federal Register / Vol. 63, No. 122 /Thursday, June 25, 1998 /Rules and Regulations 34589

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:

98–13–36 SAAB Aircraft AB: Amendment

39–10627. Docket 96–NM–212–AD.

Applicability: Model SAAB SF340A series

airplanes, serial numbers –004 through –159,

inclusive; Model SAAB 340B series

airplanes, serial numbers –160 and

subsequent; and SAAB 2000 series airplanes,

serial numbers –005 and –007 through –009,

inclusive; equipped with a mechanical

elevator control system (MECS); 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 uncommanded movement of

the right-hand elevator trim-tab to a

maximum deflection position, which could

lead to structural overload of the horizontal

stabilizers at speeds above 180 knots, and

consequent reduced controllability of the

airplane, accomplish the following:

(a) Within 150 hours time-in-service after

the effective date of this AD, perform an

operational test of the pitch trim system that

moves the elevator trim-tab of the flight

control unit to ensure that the system

operates correctly, in accordance with Saab

Service Bulletins 340–27–079 (for Model

SAAB SF340A and SF340B series airplanes);

or 2000–27–018 (for Model SAAB 2000 series

airplanes); both dated December 22, 1995; as

applicable.

(1) If no discrepancy is found, repeat the

operational test of the pitch trim system

thereafter at intervals not to exceed 150 hours

time-in-service.

(2) If any discrepancy is found, prior to

further flight, accomplish repairs in

accordance with a method approved by

either the Manager, International Branch,

ANM–116, FAA, Transport Airplane

Directorate, or the Luftfartsverket (LFV), or

its delegated agent.

Note 2: Accomplishment of the repair

required by paragraph (a)(2) of this AD, in

accordance with Saab 340 Aircraft

Maintenance Manual 27–32–30, dated

January 1, 1998, is considered acceptable for

compliance with the applicable action

specified in this AD.

(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. 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.

(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 operational test shall be done in

accordance with Saab Service Bulletin 340–

27–079, dated December 22, 1995, or Saab

Service Bulletin 2000–27–018, dated

December 22, 1995, as applicable. This

incorporation by reference was previously

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 SAAB Aircraft AB, SAAB Aircraft

Product Support, S–581.88, Linko ̈ping,

Sweden. 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 Swedish airworthiness directive SAD No.

1–083, Revision 1, dated January 2, 1996.

(e) This amendment becomes effective on

July 30, 1998.

Issued in Renton, Washington, on June 17,

1998.

Darrell M. Pederson,

Acting Manager, Transport Airplane

Directorate, Aircraft Certification Service.

[FR Doc. 98–16697 Filed 6–24–98; 8:45 am]

BILLING CODE 4910–13–U

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 98–NM–81–AD; Amendment

39–10628; AD 98–13–37]

RIN 2120–AA64

Airworthiness Directives; Airbus Model

A300 and 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 and all Model A300–600 series

airplanes, that requires a one-time

inspection for cracking of the gantry

lower flanges in the main landing gear

(MLG) bay area; and repair, if necessary.

This amendment is prompted by

issuance of mandatory continuing

airworthiness information by a foreign

civil airworthiness authority. The

actions specified by this AD are

intended to detect and correct cracking

of the gantry lower flanges in the MLG

bay area, which could result in

decompression of the airplane.

DATES: Effective July 30, 1998.

The incorporation by reference of

certain publications listed in the

regulations is approved by the Director

of the Federal Register as of July 30,

1998.

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.
34590 Federal Register / Vol. 63, No. 122 /Thursday, June 25, 1998 /Rules and Regulations

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: 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 all Model A300–600

series airplanes series airplanes was

published in the Federal Register on

April 21, 1998 (63 FR 19684). That

action proposed to require a one-time

inspection for cracking of the gantry

lower flanges in the main landing gear

(MLG) bay area; and repair, if necessary.

Comments

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.

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.

Interim Action

This is considered to be interim

action until final action is identified, at

which time the FAA may consider

further rulemaking.

Cost Impact

The FAA estimates that 67 airplanes

of U.S. registry will be affected by this

AD. It will take approximately 4 work

hours per airplane to accomplish the

required inspection, at an average labor

rate of $60 per work hour. Based on this

figure, the cost impact of the inspection

required by this AD on U.S. operators is

estimated to be $16,080, or $240 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:

98–13–37 Airbus Industrie: Amendment

39–10628. Docket 98–NM–81–AD.

Applicability: Model A300 series airplanes

on which Airbus Modification 3474 has been

accomplished, and all Model A300–600

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

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 (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 detect and correct cracking of the gantry

lower flanges in the main landing gear (MLG)

bay area, which could result in

decompression of the airplane, accomplish

the following:

(a) Prior to the accumulation of 16,300 total

flight cycles, or within 500 flight cycles after

the effective date of this AD, whichever

occurs later, perform a one-time ultrasonic

inspection for cracking of the gantry lower

flanges in the MLG bay area, in accordance

with Airbus All Operators Telex (AOT) 53–

11, dated October 13, 1997.

(1) If any cracking is detected, prior to

further flight, repair in accordance with the

AOT.

(2) If no cracking is detected, no further

action is required by this AD.

(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 2: Information concerning the

existence of approved alternative methods of

compliance with this AD, if any, may be

obtained from the International Branch,

ANM–116.

(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 repair shall be done

in accordance with Airbus All Operators

Telex (AOT) 53–11, dated October 13, 1997.

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.

Note 3: The subject of this AD is addressed

in French airworthiness directive 97–372–

236(B), dated December 3, 1997.

(e) This amendment becomes effective on

July 30, 1998.

Issued in Renton, Washington, on June 17,

1998.

Darrell M. Pederson,

Acting Manager, Transport Airplane

Directorate, Aircraft Certification Service.

[FR Doc. 98–16699 Filed 6–24–98; 8:45 am]

BILLING CODE 4910–13–U