Federal Register / Vol. 62, No. 240 / Monday, December 15, 1997 / Rules and Regulations 65601

Docket Number 97–NM–259–AD.’’ The

postcard will be date stamped and

returned to the commenter.

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.

The FAA has determined that this

regulation is an emergency regulation

that must be issued immediately to

correct an unsafe condition in aircraft,

and that it is not a ‘‘significant

regulatory action’’ under Executive

Order 12866. It has been determined

further that this action involves an

emergency regulation under DOT

Regulatory Policies and Procedures (44

FR 11034, February 26, 1979). If it is

determined that this emergency

regulation otherwise would be

significant under DOT Regulatory

Policies and Procedures, a final

regulatory evaluation will be prepared

and placed in the Rules Docket. A copy

of it, if filed, 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, 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:

97–26–04 Boeing: Amendment 39–10247.

Docket 97–NM–259–AD.

Applicability: All Model 737–100, –200,

–300, –400, and –500 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 request approval for an

alternative method of compliance in

accordance with paragraph (d) 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 defective ailerons installed on an

airplane, which could result in in-flight

separation of an aileron from the airplane

and consequent reduced controllability of the

airplane, accomplish the following:

(a) Within 60 days after the effective date

of this AD, perform a one-time visual

inspection to determine if an aileron repaired

by Tramco Inc. (doing business as

BFGoodrich Aerospace, Repair Station

HN6R593N) having any of the following

serial numbers is installed on the airplane:

Affected Serial Numbers

BN23

BN49

BN56

BN59

BN167

BN180

BN206

BN236

162

237

(b) If any aileron is found with an affected

serial number identified in paragraph (a) of

this AD, accomplish paragraphs (b)(1) and

(b)(2) of this AD.

(1) Prior to further flight, remove the

defective aileron, and replace it with a new

or serviceable aileron. And

(2) Within 10 days after accomplishing the

inspection required by paragraph (a) of this

AD, submit a report of any findings of

ailerons specified in paragraph (a) of this AD

to the Manager, FAA, Transport Airplane

Directorate, Seattle Aircraft Certification

Office (ACO), 1601 Lind Avenue, SW.,

Renton, Washington 98055–4056; telephone

(425) 227–2028; fax (425) 227–1181.

Information collection requirements

contained in this regulation have been

approved by the Office of Management and

Budget (OMB) under the provisions of the

Paperwork Reduction Act of 1980 (44 U.S.C.

3501 et seq.) and have been assigned OMB

Control Number 2120–0056.

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

person shall install on any airplane an

aileron having any serial number identified

in paragraph (a) of this AD.

(d) 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, Seattle

ACO. Operators shall submit their requests

through an appropriate FAA Principal

Maintenance Inspector, who may add

comments and then send it to the Manager,

Seattle ACO.

Note 2: Information concerning the

existence of approved alternative methods of

compliance with this AD, if any, may be

obtained from the Seattle ACO.

(e) 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.

(f) This amendment becomes effective on

December 30, 1997.

Issued in Renton, Washington, on

December 9, 1997.

John J. Hickey,

Acting Manager, Transport Airplane

Directorate, Aircraft Certification Service.

[FR Doc. 97–32609 Filed 12–12–97; 8:45 am]

BILLING CODE 4910–13–U

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 97–NM–183–AD; Amendment

39–10242; AD 97–25–17]

RIN 2120–AA64

Airworthiness Directives; Airbus Model

A320 and A321 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 and A321 series airplanes, that

requires a revision to the Airplane

Flight Manual (AFM) to include

procedures for the flightcrew to follow

in the event of radio altimeter height

malfunction. This amendment also

requires replacement of certain radio

altimeter antennas with improved

antennas, at which time the AFM

revision will no longer be required. 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

prevent output of erroneous radio

altimeter height information to the

flightcrew and autopilot, which could

result in reduced ability of the

flightcrew to cope with adverse

operating conditions.

DATES: Effective January 20, 1998.

The incorporation by reference of

certain publications listed in the

regulations is approved by the Director

of the Federal Register as of January 20,

1998.

ADDRESSES: The service information

referenced in this AD may be obtained
65602 Federal Register / Vol. 62, No. 240 / Monday, December 15, 1997 / Rules and Regulations

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:

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 A320 and A321 series airplanes

was published in the Federal Register

on October 1, 1997 (62 FR 51383). That

action proposed to require a revision to

the Airplane Flight Manual (AFM) to

include procedures for the flightcrew to

follow in the event of radio altimeter

height malfunction. That action also

proposed to require replacement of

certain radio altimeter antennas with

improved antennas, at which time the

AFM revision would no longer be

required.

Comments

Interested persons have been afforded

an opportunity to participate in the

making of this amendment. Due

consideration has been given to the two

comments received.

Both commenters support the

proposed rule.

Service Information Date

One commenter, Airbus, points out

that Airbus A319/320/321 Flight

Manual Temporary Revision (TR)

2.05.00/13 was approved by the

Direction Ge ́ne ́rale de l’Aviation Civile

(DGAC), which is the airworthiness

authority for France, on October 18,

1996. (Paragraph (a) of the proposal

indicates that the TR is undated.) The

FAA has revised paragraph (a) of this

final rule to specify the date provided

by Airbus.

Conclusion

After careful review of the available

data, including the comments 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.

Cost Impact

The FAA estimates that 50 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 AFM revision, and 1 work

hour per airplane to accomplish the

antenna replacement, at an average

labor rate of $60 per work hour.

Required parts will be provided by the

manufacturer at no cost to operators.

Based on these figures, the cost impact

of the AD on U.S. operators is estimated

to be $6,000, or $120 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:

97–25–17 Airbus Industrie: Amendment

39–10242. Docket 97–NM–183–AD.

Applicability: Model A320 and A321 series

airplanes equipped with Collins radio

altimeter antennas having part number (P/N)

622–8701–002 and a serial number below

2014, 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 (d) 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 output of erroneous radio

altimeter height information to the flightcrew

and autopilot, due to inadequate antenna

solder connections, which could result in

reduced ability of the flightcrew to cope with

adverse operating conditions, accomplish the

following:

(a) Within 10 days after the effective date

of this AD, revise the Limitations Section of

the FAA-approved Airplane Flight Manual

(AFM) by incorporating Airbus A319/320/

321 Flight Manual Temporary Revision (TR)

2.05.00/13, dated October 18, 1996, into the

AFM to provide procedures for the flightcrew

to follow in the event of radio altimeter

malfunction.

(b) Within 6 months after the effective date

of this AD, replace any COLLINS radio

altimeter antenna having P/N 622–8701–002,

a serial number below 2014, and white paint

on the inner side of the C-sink hole with a

new antenna having the same P/N that is

fitted with metallic C-sink inserts in its

attaching holes; in accordance with Airbus

All Operators Telex (AOT) 34–03, dated

February 20, 1996. Accomplishment of the

actions specified in this paragraph

constitutes terminating action for the AFM

revision required by paragraph (a) of this AD.

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

person shall install a COLLINS radio

altimeter antenna having P/N 622–8701–002

and a serial number below 2014, unless the

antenna is fitted with metallic C-sink inserts

in its attaching holes.

(d) An alternative method of compliance or

adjustment of the compliance time that
Federal Register / Vol. 62, No. 240 / Monday, December 15, 1997 / Rules and Regulations 65603

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.

(e) 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.

(f) The actions shall be done in accordance

with Airbus A319/320/321 Flight Manual

Temporary Revision (TR) 2.05.00/13, dated

October 18, 1996; and Airbus All Operators

Telex (AOT) 34–03, dated February 20, 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 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 (CN) 96–

172–084(B), dated August 28, 1996.

(g) This amendment becomes effective on

January 20, 1998.

Issued in Renton, Washington, on

December 5, 1997.

John J. Hickey,

Acting Manager, Transport Airplane

Directorate, Aircraft Certification Service.

[FR Doc. 97–32430 Filed 12–12–97; 8:45 am]

BILLING CODE 4910–13–U

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 97–NM–146–AD; Amendment

39–10241; AD 97–25–16]

RIN 2120–AA64

Airworthiness Directives; British

Aerospace (Jetstream) Model 4101

Airplanes

AGENCY: Federal Aviation

Administration, DOT.

ACTION: Final rule.

SUMMARY: This amendment adopts a

new airworthiness directive (AD),

applicable to certain British Aerospace

(Jetstream) Model 4101 airplanes, that

requires a one-time inspection of the

tailplane (horizontal stabilizer) leading

edges and surrounding area for

discrepancies, 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 prevent separation of the

horizontal stabilizer from the fin, which

could lead to reduced controllability of

the airplane.

DATES: Effective January 20, 1998.

The incorporation by reference of

certain publications listed in the

regulations is approved by the Director

of the Federal Register as of January 20,

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:

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 (Jetstream) Model 4101

airplanes was published in the Federal

Register on October 1, 1997 (62 FR

51386). That action proposed to require

a one-time inspection of the tailplane

(horizontal stabilizer) leading edges and

surrounding area for discrepancies, and

corrective action, if necessary.

Comments

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.

Conclusion

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 57 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 cost impact

of the AD on U.S. operators is estimated

to be $3,420, 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.