Federal Register / Vol. 63, No. 135 /Wednesday, July 15, 1998 /Rules and Regulations 38079

time visual inspection specified in paragraph

(a) of this AD is not required.

(d) As of the effective date of this AD, no

person shall install a pitot/static system on

any airplane, unless it has been modified in

accordance with EMBRAER Service Bulletin

145–34–0008, dated September 10, 1997.

(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, Atlanta

Aircraft Certification Office (ACO), FAA,

Small 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, Atlanta ACO.

Note 3: Information concerning the

existence of approved alternative methods of

compliance with this AD, if any, may be

obtained from the Atlanta ACO.

(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 EMBRAER service

bulletins, which contain the specified list of

effective pages:

Service bulletin referenced and date

Page number shown

on page

Revision level

shown on page Date shown on page

145–34–0010, Change 01, September 25, 1997 ................................................................ 1, 2 1 ..................... September 25, 1997.

3–9 Original ........... July 25, 1997.

145–34–0008, September 10, 1997 .................................................................................... 1–22 Original ........... September 10, 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 Empresa Brasileira de Aeronautica S.A.

(EMBRAER), P.O. Box 343—CEP 12.225, Sao

Jose dos Campos—SP, Brazil. Copies may be

inspected at the FAA, Transport Airplane

Directorate, 1601 Lind Avenue, SW., Renton,

Washington; or at the FAA, Small Airplane

Directorate, Atlanta Aircraft Certification

Office, One Crown Center, 1895 Phoenix

Boulevard, suite 450, Atlanta, Georgia; 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 Brazilian airworthiness directive 97–07–

12R1, dated November 3, 1997.

(h) This amendment becomes effective on

August 19, 1998.

Issued in Renton, Washington, on July 6,

1998.

John J. Hickey,

Acting Manager, Transport Airplane

Directorate, Aircraft Certification Service.

[FR Doc. 98–18470 Filed 7–14–98; 8:45 am]

BILLING CODE 4910–13–P

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 98–NM–87–AD; Amendment

39–10656; AD 98–15–05]

RIN 2120–AA64

Airworthiness Directives; British

Aerospace Model BAe 146–200A

Series Airplanes

AGENCY: Federal Aviation

Administration, DOT.

ACTION: Final rule.

SUMMARY: This amendment adopts a

new airworthiness directive (AD),

applicable to certain British Aerospace

Model BAe 146–200A series airplanes,

that requires a one-time inspection of

the gust damper of the elevator control

system to determine if the gust damper

is properly charged, and of the

horizontal stabilizer to detect cracking

of elevator hinge rib 1; and corrective

action, if necessary. This amendment is

prompted by the 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 elevator hinge rib 1 of the horizontal

stabilizer, which could occur if the gust

damper of the elevator control system

discharges and allows the elevator to

move freely in ground gust conditions.

Such cracking could result in damage to

the structural attachment of the elevator

to the horizontal stabilizer, and

consequent reduced controllability of

the airplane.

DATES: Effective August 19, 1998.

The incorporation by reference of

certain publications listed in the

regulations is approved by the Director

of the Federal Register as of August 19,

1998.

ADDRESSES: The service information

referenced in this AD may be obtained

from AI(R) American Support, Inc.,

13850 Mclearen Road, Herndon,

Virginia 20171. 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:

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 British

Aerospace Model BAe 146–200A series

airplanes was published in the Federal

Register on April 16, 1998 (63 FR

18852). That action proposed to require

a one-time inspection of the gust

damper of the elevator control system to

determine if the gust damper is properly

charged, and of the horizontal stabilizer

to detect cracking of elevator hinge rib

1; and corrective action, 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.

Request To Revise Cost Information

One commenter, the manufacturer,

advises that the cost information

provided in the proposed AD contains

an error. The commenter states that the

number of BAe 146–200A series

airplanes of U.S. registry that would be

affected by the AD is 5, rather than 19,

as stated in the proposed AD. The FAA

concurs with the commenter. The cost

impact information, below, has been

revised to reflect the correct number of

affected airplanes on the U.S. register.

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 with the change

described previously. The FAA has

determined that this change will neither

increase the economic burden on any

operator nor increase the scope of the

AD.

Cost Impact

The FAA estimates that 5 British

Aerospace Model BAe 146–200A series
38080 Federal Register / Vol. 63, No. 135 /Wednesday, July 15, 1998 /Rules and Regulations

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 inspections,

at an average labor rate of $60 per work

hour. Based on these figures, the cost

impact of the inspections required by

this AD on U.S. operators is estimated

to be $300, 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:

198–15–05 British Aerospace Regional

Aircraft (Formerly British Aerospace

Regional Aircraft Limited, Avro

International Aerospace Division; British

Aerospace, PLC; British Aerospace

Commercial Aircraft Limited):

Amendment 39–10656. Docket 98–NM–

87–AD.

Applicability: Model BAe 146–200A series

airplanes, as listed in British Aerospace

Service Bulletin SB.55–16, dated July 14,

1997; 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 detect and correct cracking of elevator

hinge rib 1 of the horizontal stabilizer, which

could result in damage to the structural

attachment of the elevator to the horizontal

stabilizer and consequent reduced

controllability of the airplane; accomplish

the following:

(a) Within 60 days after the effective date

of this AD, accomplish paragraphs (a)(1) and

(a)(2) of this AD, in accordance with British

Aerospace Service Bulletin SB.55–16, dated

July 14, 1997.

(1) Perform a visual inspection of the gust

damper of the elevator control system to

determine if the gust damper is properly

charged. If any gust damper is found to be

improperly charged, prior to further flight,

recharge the gust damper in accordance with

the service bulletin.

(2) Perform a detailed visual inspection,

using a borescope, to detect cracking of

elevator hinge rib 1, on the left and right side

of the airplane, in accordance with the

service bulletin. If any cracking is found,

prior to further flight, replace any cracked

hinge rib 1 with a new or serviceable part,

in accordance with a method approved by

either the Manager, International Branch,

ANM–116, FAA, Transport Airplane

Directorate; or procedures provided by the

manufacturer that are approved by the Civil

Aviation Authority.

(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 inspections and recharge shall be

done in accordance with British Aerospace

Service Bulletin SB.55–16, dated July 14,

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 AI(R) American Support, Inc., 13850

Mclearen Road, Herndon, Virginia 20171.

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 British airworthiness directive 010–07–97,

dated March 2, 1998.

(e) This amendment becomes effective on

August 19, 1998.

Issued in Renton, Washington, on July 7,

1998.

Darrell M. Pederson,

Acting Manager, Transport Airplane

Directorate, Aircraft Certification Service.

[FR Doc. 98–18651 Filed 7–14–98; 8:45 am]

BILLING CODE 4910–13–P

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 97–NM–197–AD; Amendment

39–10655; AD 98–15–04]

RIN 2120–AA64

Airworthiness Directives; Airbus Model

A320 Series Airplanes

AGENCY: Federal Aviation

Administration, DOT.

ACTION: Final rule.

SUMMARY: This amendment adopts a

new airworthiness directive (AD),

applicable to certain Airbus Model

A320 series airplanes, that requires

repetitive inspections for fatigue

cracking of the bottom flanges of the

longitudinal floor beams at frame 43;

and repair, if necessary. This

amendment also requires a one-time

inspection for fatigue cracking of the

fastener holes in the longitudinal floor

beams, and modification of the floor