Federal Register / Vol. 62, No. 227 / Tuesday, November 25, 1997 / Proposed Rules 62721

(2) A statement verifying that all known

cases/indications of leakage or failed leak

tests are included in the submitted material;

(3) The type of valve (make, model,

manufacturer, vendor part number, and serial

number);

(4) The period of time covered by the data;

(5) The current FAA leak test interval;

(6) Whether or not seals have been

replaced between the seal replacement

intervals required by this AD;

(7) Whether or not a service panel drain

valve is installed downstream of an in-line

drain valve, Kaiser Electroprecision part

number series 2651–278: Data on a service

panel valve installed downstream of an inline drain valve will not be considered as an

indicator of the reliability of the service

panel drain valve because the in-line valve

prevents potential leakage from reaching the

service panel drain valve.

(8) Whether or not leakage has been

detected between leak test intervals required

by this AD, and the reason for leakage (i.e.,

worn seals, foreign materials on sealing

surface, scratched or damaged sealing surface

on valve, etc.);

(9) Whether or not any cleaning, repairs, or

seal changes were performed on the valve

prior to conducting the leak test. [If such

activities have been accomplished prior to

conducting the periodic leak test, that leak

test shall be recorded as a ‘‘failure’’ for

purposes of the data required for this request

submission. The exception to this is the

normally-scheduled seal change in

accordance with paragraph (b)(1) of this AD.

Performing this scheduled seal change prior

to a leak test will not cause that leak test to

be recorded as a failure. Debris removal of

major blockages done as part of normal

maintenance for previous flights is also

allowable and will not cause a leak test to be

recorded as a failure. Minor debris removal

that is not commonly removed during the

normal ground maintenance test should not

be removed prior to the leak test.]

Note 7: Requests for approval of revised

leak test intervals may be submitted in any

format, provided the data give the same level

of assurance specified in paragraph (c) above.

Results of an Environmental Quality Analysis

(EQA) examination and leak test on a

randomly selected high-flight-hour valve,

with seals that have not been replaced during

a period of use at least as long as the desired

interval, may be considered a valuable

supplement to the service history data,

reducing the amount of service data that

would otherwise be required.

Note 8: For the purposes of expediting

resolution of requests for revisions to the leak

test intervals, the FAA suggests that the

requester summarize the raw data; group the

data gathered from different airplanes (of the

same model) and drain systems with the

same kind of valve; and provide a

recommendation from pertinent industry

group(s) and/or the manufacturer specifying

an appropriate revised leak test interval.

Note 9: In cases where changes are made

to a valve design approved for an extended

leak test interval such that a new valve dash

number or part number is established for the

valve, the FAA may not require extensive

service history data to approve the new valve

to the same leak test interval as the previous

valve design. Similarity of design, the nature

of the design changes, the nature and amount

of testing, and like factors will be considered

by the FAA to determine the appropriate data

requirements and leak test interval for a new

or revised valve based upon an existing

design.

(d) For all airplanes: Unless already

accomplished, within 5,000 flight hours after

the effective date of this AD, perform the

actions specified in paragraph (d)(1), (d)(2),

or (d)(3) of this AD:

(1) Install an FAA-approved lever/lock cap

on the flush/fill lines for all lavatories. Or

(2) Install a vacuum break, Monogram part

number series 3765–190, or Shaw Aero

Devises part number series 301–0009–01, in

the flush/fill lines for all lavatories. Or

(3) Install a flush/fill ball valve Kaiser

Electroprecision part number series 0062–

0009 on the flush/fill lines for all lavatories.

(e) For any affected airplane acquired after

the effective date of this AD: Before any

operator places into service any airplane

subject to the requirements of this AD, a

schedule for the accomplishment of the leak

tests required by this AD shall be established

in accordance with either paragraph (e)(1) or

(e)(2) of this AD, as applicable. After each

leak test has been performed once, each

subsequent leak test must be performed in

accordance with the new operator’s schedule,

in accordance with either paragraph (a) or (b)

of this AD as applicable.

(1) For airplanes previously maintained in

accordance with this AD, the first leak test

to be performed by the new operator must be

accomplished in accordance with the

previous operator’s schedule or with the new

operator’s schedule, whichever would result

in the earlier accomplishment date for that

leak test.

(2) For airplanes that have not been

previously maintained in accordance with

this AD, the first leak test to be performed by

the new operator must be accomplished prior

to further flight, or in accordance with a

schedule approved by the FAA PMI, but

within a period not to exceed 200 flight

hours.

(f) Alternative method(s) of compliance

with this AD:

(1) 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, FAA, Transport Airplane Directorate.

Operators shall submit their requests through

an appropriate FAA PMI, who may add

comments and then send it to the Manager,

Seattle ACO.

(2) Alternative methods of compliance

previously approved for AD 89–11–03, which

permit a 4,500-flight hour interval between

leak tests of the forward waste drain system

for those operators installing the

modifications specified in Boeing Service

Bulletin 737–38–1026, Revision 2, dated May

4, 1995, or Boeing Service Bulletin 737–38–

1031, Revision 1, dated April 20, 1995, and

later FAA-approved revisions, are considered

acceptable alternative methods of compliance

with the requirements of only paragraph

(a)(2) of this AD. For those operators, the

other requirements of this AD are still

required to be accomplished. All other

alternative methods of compliance approved

for AD 89–11–03 are terminated and are no

longer in effect.

Note 10: Information concerning the

existence of approved alternative methods of

compliance with this AD, if any, may be

obtained from the Seattle ACO.

Note 11: For any valve that is not eligible

for the extended leak test intervals of this

AD: To be eligible for the extended leak test

intervals specified in paragraph (b) of this

AD, the service history data of the valve must

be submitted to the Manager, Seattle ACO,

FAA, Transport Airplane Directorate, with a

request for an alternative method of

compliance. The request should include an

analysis of known failure modes for the

valve, if it is an existing design, and known

failure modes of similar valves, with an

explanation of how design features will

preclude these failure modes, results of

qualification tests, and approximately 25,000

flight hours or 25,000 flight cycles of service

history data which include a winter season,

collected in accordance with the

requirements of paragraph (c) above, or a

similar program. One of the factors that the

FAA will consider in approving alternative

valve designs is whether the valve meets

Boeing Specification S417T105 or 10–62213.

However, meeting the Boeing specification is

not a prerequisite for approval of alternative

valve designs.

(g) 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.

Issued in Renton, Washington, on

November 18, 1997.

James V. Devany,

Acting Manager, Transport Airplane

Directorate, Aircraft Certification Service.

[FR Doc. 97–30855 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–148–AD]

RIN 2120–AA64

Airworthiness Directives; Airbus Model

A320 and A321 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 A320 and A321

series airplanes. This proposal would

require replacement of the fuel pump

strainers with improved strainers. This
62722 Federal Register / Vol. 62, No. 227 / Tuesday, November 25, 1997 / Proposed Rules

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 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.

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–

148–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–148–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–148–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,

notified the FAA that an unsafe

condition may exist on certain Airbus

Model A320 and A321 series airplanes.

The DGAC advises that it has received

reports of low fuel pressure during taxi,

takeoff, and climb. Investigation

revealed that the low fuel pressure was

caused by the build-up of ice on the fuel

pump strainer during extended cold

soak conditions or extreme cold weather

operations. This condition, if not

corrected, could result in low fuel

pressure, and consequent shutdown of

the engine during critical phases of

flight.

Explanation of Relevant Service

Information

Airbus has issued Service Bulletin

A320–28–1044, Revision 10, dated

November 5, 1996, which describes

procedures for replacement of the 8

mesh strainers of the fuel pump with 4

mesh strainers. These new strainers

have a larger mesh to prevent the buildup of ice, and have protective cowlstrainers to prevent the entry of debris.

Accomplishment of the actions

specified in the service bulletin is

intended to adequately address the

identified unsafe condition. The DGAC

classified this service bulletin as

mandatory and issued French

airworthiness directive 96–170–082(B),

dated August 28, 1996, 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 bulletin described

previously.

Cost Impact

The FAA estimates that 132 Airbus

Model A320 and A321 series airplanes

of U.S. registry would be affected by this

proposed AD, that it would take

approximately 13 work hours per

airplane to accomplish the proposed

actions, and that the average labor rate

is $60 per work hour. Required parts

would be supplied by the manufacturer

at no cost to the operators. Based on

these figures, the cost impact of the

proposed AD on U.S. operators is

estimated to be $102,960, or $780 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.
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,