Federal Register / Vol. 62, No. 227 / Tuesday, November 25, 1997 / Proposed Rules 62723

A copy of it may be obtained by

contacting 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.

The Proposed Amendment

Accordingly, pursuant to the

authority delegated to me by the

Administrator, the Federal Aviation

Administration proposes to amend 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:

Airbus Industrie: Docket 97–NM–148–AD.

Applicability: Model A320 and A321 series

airplanes; as listed in Airbus Service Bulletin

A320–28–1044, Revision 10, dated November

5, 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 (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 blockage of fuel by the buildup of ice crystals, which could result in low

fuel pressure, and consequent shutdown of

the engine during critical phases of flight,

accomplish the following:

(a) Within 24 months after the effective

date of this AD, replace the 8 mesh strainers

of each fuel pump with 4 mesh strainers, in

accordance with Airbus Service Bulletin

A320–28–1044, Revision 10, dated November

5, 1996.

(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.

Note 3: The subject of this AD is addressed

in French airworthiness directive 96–170–

082(B), dated August 28, 1996.

Issued in Renton, Washington, on

November 18, 1997.

James V. Devany,

Acting Manager, Transport Airplane

Directorate, Aircraft Certification Service.

[FR Doc. 97–30856 Filed 11–24–97; 8:45 am]

BILLING CODE 4910–13–U

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 97–NM–178–AD]

RIN 2120–AA64

Airworthiness Directives; Airbus Model

A300 and A300–600 Series Airplanes

AGENCY: Federal Aviation

Administration, DOT.

ACTION: Notice of proposed rulemaking

(NPRM).

SUMMARY: This document proposes the

adoption of a new airworthiness

directive (AD) that is applicable to

certain Airbus Model A300 and A300–

600 series airplanes. This proposal

would require inspections to detect

cracks in Gear Rib 5 of the main landing

gear (MLG) attachment fittings at the

lower flange, and repair, if necessary.

This proposal is prompted by issuance

of mandatory continuing airworthiness

information by a foreign civil

airworthiness authority. The actions

specified by the proposed AD are

intended to detect and correct fatigue

cracking of the MLG attachment fittings,

which could result in reduced structural

integrity of the airplane.

DATES: Comments must be received by

December 26, 1997.

ADDRESSES: Submit comments in

triplicate to the Federal Aviation

Administration (FAA), Transport

Airplane Directorate, ANM–103,

Attention: Rules Docket No. 97–NM–

178–AD, 1601 Lind Avenue, SW.,

Renton, Washington 98055–4056.

Comments may be inspected at this

location between 9:00 a.m. and 3:00

p.m., Monday through Friday, except

Federal holidays.

The service information referenced in

the proposed rule may be obtained from

Airbus Industrie, 1 Rond Point Maurice

Bellonte, 31707 Blagnac Cedex, France.

This information may be examined at

the FAA, Transport Airplane

Directorate, 1601 Lind Avenue, SW.,

Renton, Washington.

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:

Comments Invited

Interested persons are invited to

participate in the making of the

proposed rule by submitting such

written data, views, or arguments as

they may desire. Communications shall

identify the Rules Docket number and

be submitted in triplicate to the address

specified above. All communications

received on or before the closing date

for comments, specified above, will be

considered before taking action on the

proposed rule. The proposals contained

in this notice may be changed in light

of the comments received.

Comments are specifically invited on

the overall regulatory, economic,

environmental, and energy aspects of

the proposed rule. All comments

submitted will be available, both before

and after the closing date for comments,

in the Rules Docket for examination by

interested persons. A report

summarizing each FAA-public contact

concerned with the substance of this

proposal will be filed in the Rules

Docket.

Commenters wishing the FAA to

acknowledge receipt of their comments

submitted in response to this notice

must submit a self-addressed, stamped

postcard on which the following

statement is made: ‘‘Comments to

Docket Number 97–NM–178–AD.’’ The

postcard will be date stamped and

returned to the commenter.

Availability of NPRMs

Any person may obtain a copy of this

NPRM by submitting a request to the

FAA, Transport Airplane Directorate,

ANM–103, Attention: Rules Docket No.

97–NM–178–AD, 1601 Lind Avenue,

SW., Renton, Washington 98055–4056.

Discussion

The Direction Ge ́ne ́rale de l’Aviation

Civile (DGAC), which is the

airworthiness authority for France,
62724 Federal Register / Vol. 62, No. 227 / Tuesday, November 25, 1997 / Proposed Rules

notified the FAA that an unsafe

condition may exist on certain Airbus

Model A300 and A300–600 series

airplanes. The DGAC advises that, on

two in-service airplanes, fatigue

cracking has been detected on Gear Rib

5 of the main landing gear attachment

fitting at the lower flange. Such fatigue

cracking, if not detected and corrected

in a timely manner, could result in

reduced structural integrity of the

airplane.

Explanation of Relevant Service

Information

Airbus has issued Service Bulletins

A300–57A6087 (for Model A300–600

series airplanes) and A300–57A0234

(for Model A300 series airplanes), both

dated August 5, 1997. These service

bulletins describe procedures for

detailed visual and high frequency eddy

current inspections to detect cracks in

Gear Rib 5 of the main landing gear

attachment fittings at the lower flange.

The DGAC classified these service

bulletins as mandatory and issued

French airworthiness directive (CN) 97–

274–230(B), dated September 24, 1997,

in order to assure the continued

airworthiness of these airplanes in

France.

FAA’s Conclusions

These airplane models are

manufactured in France and are type

certificated for operation in the United

States under the provisions of section

21.29 of the Federal Aviation

Regulations (14 CFR 21.29) and the

applicable bilateral airworthiness

agreement. Pursuant to this bilateral

airworthiness agreement, the DGAC has

kept the FAA informed of the situation

described above. The FAA has

examined the findings of the DGAC,

reviewed all available information, and

determined that AD action is necessary

for products of this type design that are

certificated for operation in the United

States.

Explanation of Requirements of

Proposed Rule

Since an unsafe condition has been

identified that is likely to exist or

develop on other airplanes of the same

type design registered in the United

States, the proposed AD would require

accomplishment of the actions specified

in the service bulletins described

previously, except as discussed below.

Differences Between the Proposed AD

and the Related Service Bulletins

The service bulletins described

previously specify that appropriate

corrective action may be obtained by

contacting the manufacturer, Airbus,

directly. However, this proposed AD

would requires that any such repair be

accomplished in accordance with a

method approved by the FAA.

Cost Impact

The FAA estimates that 67 airplanes

of U.S. registry would be affected by this

proposed AD, that it would take

approximately 6 work hours per

airplane to accomplish the proposed

actions, and that the average labor rate

is $60 per work hour. Based on these

figures, the cost impact of the proposed

AD on U.S. operators is estimated to be

$24,120, or $360 per airplane.

The cost impact figure discussed

above is based on assumptions that no

operator has yet accomplished any of

the proposed 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 proposed herein

would 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

proposal would not have sufficient

federalism implications to warrant the

preparation of a Federalism Assessment.

For the reasons discussed above, I

certify that this proposed regulation (1)

is not a ‘‘significant regulatory action’’

under Executive Order 12866; (2) is not

a ‘‘significant rule’’ under the DOT

Regulatory Policies and Procedures (44

FR 11034, February 26, 1979); and (3) if

promulgated, 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 copy of the draft

regulatory evaluation prepared for this

action is contained in the Rules Docket.

A copy of it may be obtained by

contacting 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.

The Proposed Amendment

Accordingly, pursuant to the

authority delegated to me by the

Administrator, the Federal Aviation

Administration proposes to amend 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:

Airbus Industrie: Docket 97–NM–178–AD.

Applicability: Model A300–600 series

airplanes, as listed in Airbus Service Bulletin

A300–57A6087, dated August 5, 1997; and

Model A300 series airplanes, as listed in

Airbus Service Bulletin A300–57A0234,

dated August 5, 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

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 detect and correct cracks in Gear Rib 5

of the main landing gear attachment fittings

at the lower flange, which could result in

reduced structural integrity of the airplane,

accomplish the following:

(a) For Model A300 series airplanes that

have accumulated more than 27,000 flight

cycles as of the effective date of this AD:

Except as provided by paragraph (b) of this

AD, within 40 flight cycles after the effective

date of this AD, perform a detailed visual

inspection to detect cracks in Gear Rib 5 of

the main landing gear attachment fittings at

the lower flange, in accordance with Airbus

Service Bulletin A300–57A0234, dated

August 5, 1997. Thereafter, repeat the

inspection at intervals not to exceed 40 flight

cycles, until the actions required by

paragraph (b) are accomplished.

(b) For all airplanes: Perform a detailed

visual and a high frequency eddy current

inspection to detect cracks in Gear Rib 5 of

the main landing gear attachment fittings at

the lower flange, in accordance with Airbus

Service Bulletin A300–57A6087 (for Model

A300–600 series airplanes) or A300–57A0234

(for Model A300 series airplanes), both dated

August 5, 1997; as applicable; at the time

specified in paragraph (b)(1) or (b)(2) of this

AD, as applicable. Accomplishment of the

inspection required by this paragraph

terminates the inspections required by

paragraph (a) of this AD.

(1) For airplanes that have accumulated

20,000 or more total flight cycles as of the

effective date of this AD: Inspect within 500
Federal Register / Vol. 62, No. 227 / Tuesday, November 25, 1997 / Proposed Rules 62725

flight cycles after the effective date of this

AD.

(2) For airplanes that have accumulated

less than 20,000 total flight cycles as of the

effective date of this AD: Inspect prior to the

accumulation of 18,000 total flight cycles, or

within 1,500 flight cycles after the effective

date of this AD, whichever occurs later.

(c) If any crack is detected during any

inspection required by this AD, prior to

further flight, repair in accordance with a

method approved by the Manager,

International Branch, ANM–116, FAA,

Transport Airplane Directorate.

(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,

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 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 §§ 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.

Note 3: The subject of this AD is addressed

in French airworthiness directive (CN) 97–

274–230(B), dated September 24, 1997.

Issued in Renton, Washington, on

November 18, 1997.

Stewart R. Miller,

Acting Manager, Transport Airplane

Directorate, Aircraft Certification Service.

[FR Doc. 97–30858 Filed 11–24–97; 8:45 am]

BILLING CODE 4910–13–U

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 97–CE–78–AD]

RIN 2120–AA64

Airworthiness Directives; AeromotIndustria Mecanico Metalurgica Ltda.

Models AMT–100 and AMT–200

Powered Gliders

AGENCY: Federal Aviation

Administration, DOT.

ACTION: Notice of proposed rulemaking

(NPRM).

SUMMARY: This document proposes to

adopt a new airworthiness directive

(AD) that would apply to certain

Aeromot-Industria Mecanico

Metalurgica Ltda. (Aeromot) Models

AMT–100 and AMT–200 powered

gliders. The proposed action would

require replacing all main landing gear

attaching nuts and bolts with ones of

improved design. The proposed AD is

the result of mandatory continued

airworthiness information (MCAI)

issued by the airworthiness authority for

Brazil. The actions specified by the

proposed AD are intended to prevent

failure of the main landing gear, which

could cause loss of control of the

sailplane during landing operations.

DATES: Comments must be received on

or before December 26, 1997.

ADDRESSES: Submit comments in

triplicate to the Federal Aviation

Administration (FAA), Central Region,

Office of the Regional Counsel,

Attention: Rules Docket No. 97–CE–78–

AD, Room 1558, 601 E. 12th Street,

Kansas City, Missouri 64106. Comments

may be inspected at this location

between 8 a.m. and 4 p.m., Monday

through Friday, holidays excepted.

Service information that applies to the

proposed AD may be obtained from

Grupo Aeromot, Aeromot-Industria

Mecanico Metalurgica Ltda., Av. das

Industries-1210, Bairro Anchieta, Caixa

Postal 8031, 90200-Porto Alegre-RS,

Brazil. This information also may be

examined at the Rules Docket at the

address above.

FOR FURTHER INFORMATION CONTACT:

Curtis Jackson, Aerospace Engineer,

Atlanta Aircraft Certification Office,

One Crown Center, 1895 Phoenix Blvd.,

suite 450, Atlanta, Georgia 30349;

telephone (770) 703–6083; facsimile

(770) 703–6097.

SUPPLEMENTARY INFORMATION:

Comments Invited

Interested persons are invited to

participate in the making of the

proposed rule by submitting such

written data, views, or arguments as

they may desire. Communications

should identify the Rules Docket

number and be submitted in triplicate to

the address specified above. All

communications received on or before

the closing date for comments, specified

above, will be considered before taking

action on the proposed rule. The

proposals contained in this notice may

be changed in light of the comments

received.

Comments are specifically invited on

the overall regulatory, economic,

environmental, and energy aspects of

the proposed rule. All comments

submitted will be available, both before

and after the closing date for comments,

in the Rules Docket for examination by

interested persons. A report that

summarizes each FAA-public contact

concerned with the substance of this

proposal will be filed in the Rules

Docket.

Commenters wishing the FAA to

acknowledge receipt of their comments

submitted in response to this notice

must submit a self-addressed, stamped

postcard on which the following

statement is made: ‘‘Comments to

Docket No. 9–CE–78–AD.’’ The postcard

will be date stamped and returned to the

commenter.

Availability of NPRMs

Any person may obtain a copy of this

NPRM by submitting a request to the

FAA, Central Region, Office of the

Regional Counsel, Attention: Rules

Docket No. 97–CE–78–AD, Room 1558,

601 E. 12th Street, Kansas City, Missouri

64106.

Discussion

The Centro Tecnico Aeroespacial

(CTA), which is the airworthiness

authority for Brazil, recently notified the

FAA that an unsafe condition may exist

on certain Aeromot Models AMT–100

and AMT–200 powered gliders. The

CTA reports that the main landing gear

on two powered gliders failed. The

failure is the result of hard landings

shearing the attaching bolts and causing

collapse of the main landing gear. After

further investigation, the manufacturer

has determined that these bolts (part

numbers (P/N) TH 6x30 PL11) and nuts

(P/N 6PA–108) may have intergranular

defects and the design is not adequate

to withstand a very hard landing. These

conditions, if not corrected, could result

in loss of the main landing gear during

landing operations.

Relevant Service Information

Aeromot has issued Service Bulletin

(SB) No. SB–200–32–044, Issue Date

August 18, 1997, which specifies

procedures for removing the original

attaching bolts and nuts, and installing

attaching bolts and nuts of an improved

design.

The CTA classified these service

bulletins as mandatory and issued

Brazilian AD 97–09–06, dated August

14, 1997, in order to assure the

continued airworthiness of these

airplanes in Brazil.

The FAA’s Determination

This airplane model is manufactured

in Brazil and is type certificated for

operation in the United States under the

provisions of section 21.29 of the

Federal Aviation Regulations (14 CFR

21.29) and the applicable bilateral

airworthiness agreement. Pursuant to

this bilateral airworthiness agreement,

the CTA has kept the FAA informed of

the situation described above. The FAA