29146 Federal Register / Vol. 63, No. 102 /Thursday, May 28, 1998 / Proposed Rules

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 98–NM–19–AD]

RIN 2120–AA64

Airworthiness Directives; Airbus Model

A300–600 and A310 Series Airplanes

AGENCY: Federal Aviation

Administration, DOT.

ACTION: Notice of proposed rulemaking

(NPRM).

SUMMARY: This document proposes the

supersedure of an existing airworthiness

directive (AD), applicable to certain

Airbus Model A300–600 and A310

series airplanes, that currently requires

revising the Airplane Flight Manual

(AFM) to instruct the flightcrew to

cross-check certain primary power

setting parameters of the Thrust Control

Computer (TCC) against tables of these

values; and apply corrective action, if

necessary. That AD also provides for

optional terminating action for the AFM

revisions. This proposed rule would

require accomplishment of the

previously optional terminating action.

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 prevent incorrect primary

power setting parameters of the TCC,

which could result in insufficient thrust

being applied during takeoff.

DATES: Comments must be received by

June 29, 1998.

ADDRESSES: Submit comments in

triplicate to the Federal Aviation

Administration (FAA), Transport

Airplane Directorate, ANM–114,

Attention: Rules Docket No. 98–NM–

19–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:

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:

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 98–NM–19–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–114, Attention: Rules Docket No.

98–NM–19–AD, 1601 Lind Avenue,

SW., Renton, Washington 98055–4056.

Discussion

On December 29, 1997, the FAA

issued AD 98–01–09, amendment 39–

10272 (63 FR 658, January 7, 1998),

applicable to certain Airbus Model

A300–600 and A310 series airplanes, to

require revising the Limitations Section

of the FAA-approved Airplane Flight

Manual (AFM) to instruct the flightcrew

to cross-check certain primary power

setting parameters of the Thrust Control

Computer (TCC) against tables of these

values; and apply corrective action, if

necessary. That AD also provides for an

optional terminating action for the AFM

revisions. That action was prompted by

issuance of mandatory continuing

airworthiness information by a foreign

civil airworthiness authority. The

requirements of that AD are intended to

ensure that the flightcrew is provided

with procedures for cross-checking and

correcting certain primary power setting

parameters of the TCC; incorrect

parameters could result in insufficient

thrust being applied during takeoff.

Actions Since Issuance of AD 98–01–09

In the preamble to AD 98–01–09, the

FAA specified that the actions required

by that AD were considered interim

action because French airworthiness

directive 97–110–218(B) dated May 7,

1997, required modification of the TCC

on A300–600 and A310 series airplanes,

while AD 98–01–09 provided for

optional modification of the TCC. The

FAA also indicated that it would

consider further rulemaking action since

the planned compliance time for that

action was sufficiently long so that

notice and opportunity for prior public

comment were practicable. This

proposed AD will require

accomplishment of the previously

optional modification.

Explanation of Relevant Service

Information

Airbus has issued the following

service bulletins:

• A310–22–2025, dated April 18,

1989;

• A310–22–2027, dated June 8, 1990;

• A310–22–2031, dated September 2,

1991;

• A310–22–2035, Revision 1, dated

July 13, 1994;

• A300–22–6010, dated April 18,

1989;

• A300–22–6011, dated June 8, 1990;

and

• A300–22–6017, dated September 2,

1991.

These service bulletins describe

procedures for modification of the TCC

to prevent sensitivity to electrical power

transients. Accomplishment of the

modification would eliminate the need

for the AFM limitation. The

modification of the TCC varies

depending on the airplane model and

engine configuration.

Accomplishment of the action

specified in the service bulletins is

intended to adequately address the

identified unsafe condition. The

Direction Genrale de l’Aviation Civile

(DGAC), which is the airworthiness

authority for France, classified these

service bulletins as mandatory and

issued French airworthiness directive

97–110–218(B), dated May 7, 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
Federal Register / Vol. 63, No. 102 /Thursday, May 28, 1998 / Proposed Rules 29147

certificated for operation in the United

States under the provisions of § 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 products of this same

type design, the proposed AD would

supersede AD 98–01–09 to continue to

require a revision to the Limitations

Section of the FAA-approved AFM, that

instructs the flightcrew to cross-check

certain primary power setting

parameters of the TCC. This proposed

AD also would add a requirement to

modify the TCC, which would terminate

the requirement for the AFM revision.

Cost Impact

The FAA estimates that 94 airplanes

of U.S. registry would be affected by this

proposed AD.

The AFM revision that is currently

required by AD 98–01–09 takes

approximately 1 work hour per airplane

to accomplish, at an average labor rate

of $60 per work hour. Based on these

figures, the cost impact of the currently

required AFM revision on U.S.

operators is estimated to be $5,640, or

$60 per airplane.

The modification that is proposed in

this AD action would take

approximately 3 work hours per

airplane to accomplish, at an average

labor rate of $60 per work hour.

Required parts would cost

approximately $4,300 per airplane.

Based on these figures, the cost impact

of the modification proposed by this AD

on U.S. operators is estimated to be

$421,120, or $4,480 per airplane.

The cost impact figures discussed

above are based on assumptions that no

operator has yet accomplished any of

the current or 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

removing amendment 39–10272 (63 FR

658, January 7, 1998), and by adding a

new airworthiness directive (AD), to

read as follows:

Airbus Industrie: Docket 98–NM–19–AD.

Supersedes AD 98–01–09, Amendment

39–10272.

Applicability: Model A300–600 and A310

series airplanes equipped with General

Electric CF6–80C2 engines on which Airbus

Modification 7174, 7588, or 8246 has not

been accomplished; and Model A300–600

and A310 series airplanes equipped with

Pratt & Whitney PW 4000 engines on which

Airbus Modification 7694 has not been

accomplished; 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 (c) 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 incorrect primary power setting

parameters of the Thrust Control Computer

(TCC), which could result in insufficient

thrust being applied during takeoff,

accomplish the following:

Restatement of Requirements of AD 98–01–

09

(a) Within 15 days after January 22, 1998

(the effective date of AD 98–01–09,

amendment 39–10272), revise the

Limitations Section of the FAA-approved

Airplane Flight Manual (AFM) by inserting a

copy of A300–600 or A310 Flight Manual

Temporary Revision 4.03.00/18, 4.03.00/19,

4.03.00/20, or 4.03.00/21, all dated November

4, 1996; as applicable; into the AFM.

Note 2: When the temporary revision

specified in paragraph (a) of this AD has been

incorporated into the general revisions of the

AFM, the general revisions may be inserted

in the AFM, provided the information

contained in the general revision is identical

to that specified in the applicable temporary

revision cited in paragraph (a).

New Requirements of this AD

(b) Within 15 months after the effective

date of this AD, modify the TCC in

accordance with the applicable Airbus

service bulletins specified below. (The

applicability of the service bulletins is

specified in the effectivity section of each

service bulletin.)

• A310–22–2025, dated April 18, 1989;

• A310–22–2027, dated June 8, 1990;

• A310–22–2031, dated September 2,

1991;

• A310–22–2035, Revision 1, dated July

13, 1994;

• A300–22–6010, dated April 18, 1989;

• A300–22–6011, dated June 8, 1990; or

• A300–22–6017, dated September 2,

1991.

Accomplishment of the modification of the

TCC constitutes terminating action for the

requirements of paragraph (a) of this AD.

After the modification has been

accomplished, the temporary revision may be

removed from the AFM.

(c) 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 3: Information concerning the

existence of approved alternative methods of

compliance with this AD, if any, may be
29148 Federal Register / Vol. 63, No. 102 /Thursday, May 28, 1998 / Proposed Rules

obtained from the International Branch,

ANM–116.

(d) 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 4: The subject of this AD is addressed

in French airworthiness directive 97–110–

218(B), dated May 7, 1997.

Issued in Renton, Washington, on May 20,

1998.

Darrell M. Pederson,

Acting Manager, Transport Airplane

Directorate, Aircraft Certification Service.

[FR Doc. 98–14036 Filed 5–27–98; 8:45 am]

BILLING CODE 4910–13–U

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 97–NM–187–AD]

RIN 2120–AA64

Airworthiness Directives; Dornier

Model 328 Series Airplanes Equipped

with Honeywell GP–300 Guidance and

Display Controller

AGENCY: Federal Aviation

Administration, DOT.

ACTION: Notice of proposed rulemaking

(NPRM).

SUMMARY: This document proposes the

supersedure of an existing airworthiness

directive (AD), applicable to certain

Dornier Model 328 series airplanes, that

currently requires modification of

certain Honeywell GP–300 guidance

and display controllers. That AD was

prompted by reports of smoke and

fumes emitting from the Honeywell GP–

300 guidance and display controller due

to a defective light bulb; and a report of

failure of the autopilot to disconnect

manually. The actions specified by that

AD are intended to prevent a defective

light bulb from causing a short circuit

that emits smoke and fumes into the

cockpit; or causing damage to the circuit

cards and various components, which

may lock the autopilot into the engaged

mode. Locking of the autopilot into the

engaged mode could lead to the

inability of the pilot to disconnect the

autopilot, which could result in reduced

controllability of the airplane. This

action would require verification of

proper installation of the modification,

and repair, if necessary.

DATES: Comments must be received by

June 29, 1998.

ADDRESSES: Submit comments in

triplicate to the Federal Aviation

Administration (FAA), Transport

Airplane Directorate, ANM–114,

Attention: Rules Docket No. 97–NM–

187–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

Honeywell, Inc., Attn: Customer

Support Materiel, P.O. Box 21111,

Phoenix, Arizona 85036. This

information may be examined at the

FAA, Transport Airplane Directorate,

1601 Lind Avenue, SW., Renton,

Washington; or at the FAA, Los Angeles

Aircraft Certification Office, 3960

Paramount Boulevard, Lakewood,

California 90712–4137; telephone (562)

627–5220; fax (562) 627–5210.

FOR FURTHER INFORMATION CONTACT: J.

Kirk Baker, Aerospace Engineer,

Systems and Equipment Branch, ANM–

130L, FAA, Los Angeles Aircraft

Certification Office, 3960 Paramount

Boulevard, Lakewood, California 90712;

telephone (562) 627–5345; fax (562)

627–5210.

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–187–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–114, Attention: Rules Docket No.

97–NM–187–AD, 1601 Lind Avenue,

SW., Renton, Washington 98055–4056.

Discussion

On May 31, 1996, the FAA issued AD

96–12–13, amendment 39–9656 (61 FR

29465, June 11, 1996), applicable to

certain Dornier Model 328 series

airplanes, to require modification of

certain Honeywell GP–300 guidance

and display controller. That action was

prompted by reports of smoke and

fumes emitting from the Honeywell GP–

300 guidance and display controller due

to a defective light bulb; and a report of

failure of the autopilot to disconnect

manually. The requirements of that AD

are intended to prevent a defective light

bulb from causing a short circuit that

emits smoke and fumes into the cockpit;

or causing damage to the circuit cards

and various components, which may

lock the autopilot into the engaged

mode. Locking of the autopilot into the

engaged mode could lead to the

inability of the pilot to disconnect the

autopilot, which could result in reduced

controllability of the airplane.

Actions Since Issuance of Previous Rule

Since the issuance of AD 96–12–13,

the Luftfahrt-Bundesamt (LBA), which

is the airworthiness authority for

Germany, has advised the FAA that the

service bulletin issued by Honeywell

and referenced in AD 96–12–13 has

been misinterpreted by personnel at

Honeywell service centers. The LBA

advises that, on an in-service airplane,

a miswired unit of the GP–300 control

panel was found, which caused the

panel to overheat and generate smoke.

In addition, two miswired units were

found during the manufacturing

process. Such miswired units would

prevent the overheat protection device

from functioning and could lead to

smoke and fumes in the cockpit.

Explanation of Relevant Service

Information

The FAA has reviewed and approved

Honeywell Service Bulletin 7015327–

22–4, dated March 31, 1997, which

describes procedures for verification of

proper installation of the modification

by re-testing the circuit card assemblies,

and repair, if necessary. The LBA

classified this service bulletin as

mandatory and issued German

airworthiness directive 96–239/2, dated

June 19, 1997, in order to assure the

continued airworthiness of these

airplanes in Germany.