This section of the FEDERAL REGISTER

contains notices to the public of the proposed

issuance of rules and regulations. The

purpose of these notices is to give interested

persons an opportunity to participate in the

rule making prior to the adoption of the final

rules.

Proposed Rules Federal Register

30150

Vol. 63, No. 106

Wednesday, June 3, 1998

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 98–NM–128–AD]

RIN 2120–AA64

Airworthiness Directives; Airbus Model

A310 and A300–600 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 all Airbus

Model A310 and A300–600 series

airplanes, that currently requires a

revision of the Airplane Flight Manual

that warns the flightcrew of certain

consequences associated with

overriding the autopilot when it is in

the pitch control axis. It also requires

modification of certain flight control

computers, and a modification to the

autopilot. For certain airplanes, that AD

also requires repetitive operational

testing of the modified autopilot to

determine if the disconnect function

operates properly, and repair, if

necessary. This action would add a new

requirement to accomplish those

repetitive operational tests on other

airplanes. 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 an out-of-trim

condition between the trimmable

horizontal stabilizer and the elevator,

which could result in severely reduced

controllability of the airplane.

DATES: Comments must be received by

July 6, 1998.

ADDRESSES: Submit comments in

triplicate to the Federal Aviation

Administration (FAA), Transport

Airplane Directorate, ANM–114,

Attention: Rules Docket No. 98–NM–

128–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–128–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–128–AD, 1601 Lind Avenue,

SW., Renton, Washington 98055–4056.

Discussion

On August 25, 1997, the FAA issued

AD 97–18–09, amendment 39–10119 (62

FR 45710, August 29, 1997), applicable

to all Airbus Model A310 and A300–600

series airplanes, to require a revision to

the Airplane Flight Manual (AFM) that

warns the flightcrew of certain

consequences associated with

overriding the autopilot when it is in

the pitch control axis, modification of

certain flight control computers (FCC),

and modification of the autopilot, which

would enable the flightcrew to

disconnect the autopilot when direct

force is applied to the control column,

regardless of its mode and the altitude

of the airplane. That AD also requires

repetitive operational testing of the

modified autopilot to determine if the

disconnect function operates properly,

and repair, if necessary. That action was

prompted by the results of an FAA

review of the requirements of an earlier

AD. The requirements of that AD are

intended to prevent an out-of-trim

condition between the trimmable

horizontal stabilizer and the elevator,

which could result in severely reduced

controllability of the airplane.

Actions Since Issuance of Previous Rule

Since the issuance of AD 97–18–09,

the Direction Ge ́ne ́rale de l’Aviation

Civile (DGAC), which is the

airworthiness authority for France, has

issued French airworthiness directive

97–373–237(B), dated December 3,

1997, which specifies that Airbus Model

A310 and A300–600 series airplanes on

which the modification of the autopilot

(reference Airbus Modification 11454)

has been accomplished during

production should be subject to the

same repetitive operational tests

required to be performed on Airbus

Model A310 and A300–600 series

airplanes modified in accordance with

Airbus Service Bulletin A310–22–2044,

Revision 1, or A300–22–6032, Revision

1, both dated January 8, 1997 (which

were referenced by AD 97–18–09 as the

appropriate sources of service

information).

In light of the criticality of the unsafe

condition (an out-of-trim condition

between the trimmable horizontal

stabilizer and the elevator, which could
Federal Register / Vol. 63, No. 106 /Wednesday, June 3, 1998 / Proposed Rules 30151

severely reduce controllability of the

airplane), modification of the autopilot

alone may not provide the degree of

safety assurance necessary for the

transport airplane fleet. Therefore,

repetitive operational testing of the

modified autopilot to determine if the

disconnect function operates properly is

necessary to ensure long term continued

operational safety, whether the

modification was installed during

production or in accordance with AD

97–18–09.

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

supersede AD 97–18–09 to continue to

require a revision to the Limitations

Section of the AFM that warns the

flightcrew of certain consequences

associated with overriding the autopilot

when it is in the pitch control axis;

modification of certain FCC’s;

modification of the autopilot and

removal of the revision to the AFM once

the modification has been

accomplished; repetitive operational

testing of the modified autopilot to

determine if the disconnect function

operates properly; and repair, if

necessary.

This proposed AD would add a new

requirement for accomplishment of the

same repetitive operational tests on

Airbus Model A310 and A300–600

series airplanes that received the

modification to the autopilot during

production.

Cost Impact

There are approximately 94 airplanes

of U.S. registry that would be affected

by this proposed AD.

The AFM revision that was required

previously by AD 96–08–07 and

retained in this AD, 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 of certain FCC’s that

was required previously by AD 96–08–

07 and retained in this AD, takes

approximately 1 work hour per airplane

to accomplish, at an average labor rate

of $60 per work hour. Required parts

will be supplied by the manufacturer at

no cost to operators. Based on these

figures, the cost impact of the currently

required modification of FCC’s on U.S.

operators is estimated to be $5,640, or

$60 per airplane.

The modification of the autopilot that

was required previously by AD 97–18–

09 and retained in this AD, takes

approximately 25 work hours per

airplane to accomplish, at an average

labor rate of $60 per work hour.

Required parts cost approximately

$1,578 per airplane. Based on these

figures, the cost impact of the currently

required modification of the autopilot

on U.S. operators is estimated to be

$289,332, or $3,078 per airplane.

The operational test that was required

previously by AD 97–18–09 and

retained in this AD, takes approximately

7 work hours per airplane, per test

cycle, to accomplish, at an average labor

rate of $60 per work hour. Based on

these figures, the cost impact of the

currently required operational test

requirement on U.S. operators is

estimated to be $39,480, or $420 per

airplane, per test cycle.

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 39–10119 (62 FR

45710, August 29, 1997), and by adding

a new airworthiness directive (AD), to

read as follows:

Airbus Industrie: Docket 98–NM–128–AD.

Supersedes AD 97–18–09, Amendment

39–10119.

Applicability: All Model A310 and A300–

600 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 (f) 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 an out-of-trim condition

between the trimmable horizontal stabilizer

and the elevator, which could result in

severely reduced controllability of the

airplane, accomplish the following:
30152 Federal Register / Vol. 63, No. 106 /Wednesday, June 3, 1998 / Proposed Rules

RESTATEMENT OF ACTIONS REQUIRED

BY AD 96–08–07, AMENDMENT 39–9573

(a) Within 10 days after May 23, 1996 (the

effective date of AD 96–08–07, amendment

39–9573), revise the Limitations Section of

the FAA-approved Airplane Flight Manual

(AFM) to include the information contained

in paragraph (a)(1) or (a)(2) of this AD, as

applicable. This may be accomplished by

inserting a copy of this AD in the AFM. The

AFM limitation required by AD 94–21–07,

amendment 39–9049, may be removed

following accomplishment of the

requirements of this paragraph.

(1) For airplanes on which the flight

control computers (FCC) have not been

modified in accordance with the

requirements of paragraph (b) of this AD:

‘‘Overriding the autopilot (AP) in pitch

axis does not cancel the AP autotrim when

LAND TRACK mode [green LAND on both

Flight Mode Annunciators (FMA)] or GOAROUND mode is engaged. In these modes,

if the pilot counteracts the AP, the autotrim

will trim against pilot input. This could lead

to a severe out-of-trim situation in a critical

phase of flight.’’

(2) For airplanes on which the FCC’s have

been modified in accordance with the

requirements of paragraph (b) of this AD:

‘‘Overriding the autopilot (AP) in pitch

axis does not cancel the AP autotrim when

LAND TRACK mode (green LAND on both

FMA’s) is engaged, or GO-AROUND mode is

engaged below 400 feet radio altitude (RA).

In these modes, if the pilot counteracts the

AP, the autotrim will trim against pilot input.

This could lead to a severe out-of-trim

situation in a critical phase of flight.’’

RESTATEMENT OF ACTIONS REQUIRED

BY AD 94–21–07, AMENDMENT 39–9049

(b) For airplanes equipped with FCC’s

having either part number (P/N) B470ABM1

(for Model A310 series airplanes) or

B470AAM1 (for Model A300–600 series

airplanes): Within 60 days after November 2,

1994 (the effective date of AD 94–21–07,

amendment 39–9049), modify the FCC’s in

accordance with Airbus Service Bulletin

A310–22–2036, dated December 14, 1993 (for

Model A310 series airplanes), or Airbus

Service Bulletin A300–22–6021, Revision 1,

dated December 24, 1993 (for Model A300–

600 series airplanes), as applicable.

(c) As of November 2, 1994, no person

shall install a FCC having either P/N

B470ABM1 or B470AAM1 on any airplane.

RESTATEMENT OF ACTIONS REQUIRED

BY AD 97–18–09, AMENDMENT 39–10119

(d) For airplanes on which Modification

No. 11454 [reference Airbus Service Bulletin

A310–22–2044, Revision 1 (for Model A310

series airplanes) or Airbus Service Bulletin

A300–22–6032, Revision 1 (for Model A300–

600 series airplanes)] has not been installed:

Accomplish paragraphs (d)(1), (d)(2)(i), and

(d)(2)(ii) of this AD.

(1) Within 24 months after October 3, 1997

(the effective date of AD 97–18–09,

amendment 39–10119), modify the autopilot

in accordance with Airbus Service Bulletin

A310–22–2044, Revision 1, dated January 8,

1997 (for Model A310 series airplanes), or

Service Bulletin A300–22–6032, Revision 1,

dated January 8, 1997 (for Model A300–600

series airplanes), as applicable. The

requirements of paragraph (a) of AD 95–25–

09, amendment 39–9455, if applicable, must

be accomplished prior to or at the same time

the requirements of this paragraph are

accomplished.

(2) Prior to further flight following

accomplishment of paragraph (d)(1) of this

AD:

(i) Remove the AFM revisions required by

paragraph (a) of this AD; and

(ii) Perform an operational test of this

autopilot disconnect feature to determine

that it operates properly, in accordance with

Airbus Service Bulletin A310–22–2047,

dated July 16, 1996 (for Model A310 series

airplanes), or Service Bulletin A300–22–

6035, dated July 16, 1996 (for Model A300–

600 series airplanes), as applicable. If any

discrepancy is detected, prior to further

flight, repair it in accordance with the

applicable service bulletin. Repeat this test

thereafter at intervals not to exceed 18

months.

NEW ACTIONS REQUIRED BY THIS AD

(e) For airplanes on which Modification

No. 11454 was installed during production:

Within 18 months after the date of

manufacture of the airplane, or within 6

months after the effective date of this AD,

whichever occurs later, accomplish the

actions specified in paragraph (d)(2)(ii) of

this AD.

(f) 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.

(g) 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 97–373–

237(B), dated December 3, 1997.

Issued in Renton, Washington, on May 27,

1998.

Darrell M. Pederson,

Acting Manager, Transport Airplane

Directorate, Aircraft Certification Service.

[FR Doc. 98–14610 Filed 6–2–98; 8:45 am]

BILLING CODE 4910–13–U

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 97–NM–128–AD]

RIN 2120–AA64

Airworthiness Directives; British

Aerospace Model BAe 146 and Model

Avro 146–RJ 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 all

British Aerospace Model BAe 146 and

certain Model Avro 146–RJ series

airplanes. This proposal would require

a one-time inspection for ‘‘drill marks’’

and corrosion on the underside of the

wing top skin, and corrective actions, 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 prevent corrosion from

developing on the underside of the top

skin of the center wing, which could

result in reduced structural integrity of

the airplane.

DATES: Comments must be received by

July 6, 1998.

ADDRESSES: Submit comments in

triplicate to the Federal Aviation

Administration (FAA), Transport

Airplane Directorate, ANM–114,

Attention: Rules Docket No. 97–NM–

128–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

AI(R) American Support, Inc., 13850

Mclearen Road, Herndon, Virginia

20171. 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: