6502 Federal Register / Vol. 62, No. 29 / Wednesday, February 12, 1997 / Proposed Rules

Issued in Renton, Washington, on February

5, 1997.

Darrell M. Pederson,

Acting Manager, Transport Airplane

Directorate, Aircraft Certification Service.

[FR Doc. 97–3433 Filed 2–11–97; 8:45 am]

BILLING CODE 4910–13–U

14 CFR Part 39

[Docket No. 96–NM–252–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

supersedure of an existing airworthiness

directive (AD), applicable to all Airbus

Model A320 series airplanes, that

currently requires revising the

Limitations Section of the FAAapproved Airplane Flight Manual

(AFM) to instruct the flight crew to

maintain a flap setting of ‘‘Configuration

Full’’ (CONF FULL) during landing.

That AD was prompted by a report of

severe control difficulties which

occurred on approach with the flaps

locked in CONF FULL and the landing

gear down. This action would add a

requirement for installation of a new,

improved flight warning computer

(FWC), which, when accomplished,

would constitute terminating action for

the AFM limitation. This action also

would revise the applicability of the

existing AD to include additional

airplanes that are subject to the

addressed unsafe condition. The actions

specified by the proposed AD are

intended to prevent reduced

controllability of the airplane during

approach when the flaps are locked in

CONF FULL.

DATES: Comments must be received by

March 24, 1997.

ADDRESSES: Submit comments in

triplicate to the Federal Aviation

Administration (FAA), Transport

Airplane Directorate, ANM–103,

Attention: Rules Docket No. 96-NM–

252-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:

Charles Huber, Aerospace Engineer,

Standardization Branch, ANM–113,

FAA, Transport Airplane Directorate,

1601 Lind Avenue, SW., Renton,

Washington 98055–4056; telephone

(206) 227–2589; fax (206) 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 96-NM–252-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.

96–NM–252–AD, 1601 Lind Avenue,

SW., Renton, Washington 98055–4056.

Discussion

On September 15, 1994, the FAA

issued AD 94–20–02, amendment 39–

9030 (59 FR 48563, September 22,

1994), applicable to all Airbus Model

A320 series airplanes, to require

revising the Limitations Section of the

FAA-approved Airplane Flight Manual

(AFM) to advise the flight crew to

maintain ‘‘Configuration Full’’ (CONF

FULL) during landing approaches. That

action was prompted by a report of

severe control difficulties which

occurred on approach with the flaps

locked in CONF FULL and the landing

gear down. The requirements of that AD

are intended to prevent severely

reduced controllability of the airplane

during approach.

In the preamble to AD 94–20–02, the

FAA indicated that the actions required

by that AD were considered ‘‘interim

action’’ and that further rulemaking

action was being considered. The FAA

now has determined that further

rulemaking is indeed necessary, and

this proposed AD follows from that

determination.

Actions Since Issuance of Previous Rule

Since the issuance of AD 94–20–02,

the FAA has determined that Airbus

Model A321 series airplanes may be

subject to the same unsafe condition

addressed by AD 94–20–02. Since the

FWC installed on those airplanes is

similar in design to those installed on

Model A320 series airplanes, the same

problems encountered on the Model

A320 could potentially occur on the

Model A321 as well.

Additionally, since issuance of AD

94–20–02, Airbus has developed an

improved flight warning computer

(FWC) that positively addresses the

control difficulties addressed by AD 94–

20–02. Installation of the FWC will

ensure adequate controllability of the

airplane during approach with the flaps

locked in CONF FULL and the landing

gear down.

Explanation of Relevant Service

Information

Airbus has issued Service Bulletin

A320–31–1080, Revision 01, dated July

12, 1996, which describes procedures

for installation of a new, improved FWC

that defines a new standard common to

Airbus Model A320 and A321 series

airplanes. Among other actions, the

service bulletin describes modifications

that correct certain FWC parts and that

implement predictive windshear

function capability. The Direction

Ge ́ne ́rale de l’Aviation Civile (DGAC),

which is the airworthiness authority for

France, classified this service bulletin as

mandatory and issued French

airworthiness directive 96–079–079(B),

dated April 10, 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
Federal Register / Vol. 62, No. 29 / Wednesday, February 12, 1997 / Proposed Rules 6503

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 94–20–02. It would

continue to require revising the AFM of

Model A320 series airplanes to instruct

the flight crew to maintain CONF FULL

during landing approaches for Airbus

Model A320 series airplanes.

This proposal also would require the

same AFM revision for Airbus Model

A321 series airplanes.

Additionally, this proposal would

require installation of a new, improved

FWC on all airplanes as terminating

action for the AFM limitations. The

previously required AFM revision must

be removed after the new, improved

FWC has been installed. The installation

would be required to be accomplished

in accordance with the service bulletin

described previously.

Cost Impact

There are approximately 109 Airbus

Model A320 series airplanes of U.S.

registry that would be affected by this

proposed AD.

The actions that are currently

required by AD 94–20–02 (revision of

the AFM) take 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 actions currently required on U.S.

operators is estimated to be $6,540, or

$60 per airplane.

The new actions that are proposed in

this AD action (installation of new,

improved FWC) would take

approximately 3 work hours per

airplane to accomplish, at an average

labor rate of $60 per work hour.

Required parts would be provided to

operators by the manufacturer at no

cost. Based on these figures, the cost

impact of the proposed requirements on

U.S. operators of Model A320 series

airplanes is estimated to be $19,620, or

$180 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.

None of the Model A321 series

airplanes affected by this proposed

action are on the U.S. Register. All of

those airplanes that are included in the

applicability of this proposal currently

are operated by non-U.S. operators

under foreign registry; therefore, they

are not directly affected by this

proposed AD action. However, the FAA

considers that inclusion of those

airplanes in the applicability of this

proposed rule is necessary to ensure

that the unsafe condition is addressed in

the event that any of these airplanes are

imported and placed on the U.S.

Register in the future.

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 39–9030 (59 FR

48563, September 22, 1994), and by

adding a new airworthiness directive

(AD), to read as follows:

Airbus Industrie: Docket 96–NM–252–AD.

Supersedes AD 94–20–02, Amendment 39–

9030.

Applicability: Model A320 and A321 series

airplanes, on which Airbus Modification

24612 or Airbus Service Bulletin A320–31–

1080 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 otherwise

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 severely reduced controllability

of the airplane during approach, accomplish

the following:

(a) At the applicable time specified in

either paragraph (a)(1) or (a)(2) of this AD,

revise the Limitations Section of the FAAapproved Airplane Flight Manual (AFM) to

include the information specified in Airbus

A320/A321 Flight Manual Temporary

Revision 9.99.99/20, dated June 14, 1994.

Note 2: This may be accomplished by

inserting a copy of Airbus A320/A321 Flight

Manual Temporary Revision 9.99.99/20,

dated June 14, 1994, in the AFM. When this

temporary revision has been incorporated in

the general revisions of the AFM, the general

revisions may be inserted in the AFM,

provided the information contained in the

general revisions is identical to that specified

in Temporary Revision 9.99.99/20.

(1) For Model A320 series airplanes: Revise

the AFM within 10 days after October 7, 1994

(the effective date of AD 94–20–02,

amendment 39–9030).

(2) For Model A321 series airplanes: Revise

the AFM within 10 days after the effective

date of this AD.

(b) Within 6 months after the effective date

of this AD, install a new, improved flight

warning computer (FWC) in accordance with

Airbus Service Bulletin A320–31–1080,

Revision 01, dated July 12, 1996. Prior to
6504 Federal Register / Vol. 62, No. 29 / Wednesday, February 12, 1997 / Proposed Rules

further flight after accomplishing this

installation, remove the AFM revision

required by paragraphs (a) of this AD.

(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, Manager,

Standardization Branch, ANM–113, FAA,

Transport Airplane Directorate. Operators

shall submit their requests through an

appropriate FAA Principal Operations

Inspector, who may add comments and then

send it to the Manager, Standardization

Branch, ANM–113.

Note 3: Information concerning the

existence of approved alternative methods of

compliance with this AD, if any, may be

obtained from the Standardization Branch,

ANM–113.

(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.

Issued in Renton, Washington, on February

5, 1997.

Darrell M. Pederson,

Acting Manager, Transport Airplane

Directorate, Aircraft Certification Service.

[FR Doc. 97–3434 Filed 2–11–97; 8:45 am]

BILLING CODE 4910–13–U

14 CFR Part 39

[Docket No. 96–NM–180–AD]

RIN 2120–AA64

Airworthiness Directives; Raytheon

Model BAe 125–1000A and Model

Hawker 1000 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

Raytheon Model BAe 125–1000A and

Model Hawker 1000 series airplanes.

This proposal would require various

modifications to increase the size of

certain existing pressure venting areas

and to add additional venting areas.

This proposal is prompted by results of

a design review of the requirements for

certification of the cabin pressurization

system. The actions specified by the

proposed AD are intended to prevent

inadequate venting of cabin pressure in

the event of rapid decompression,

which could cause failure or

deformation of certain structural

members, and consequent reduced

controllability of the airplane.

DATES: Comments must be received by

March 24, 1997.

ADDRESSES: Submit comments in

triplicate to the Federal Aviation

Administration (FAA), Transport

Airplane Directorate, ANM–103,

Attention: Rules Docket No. 96–NM–

180–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

Raytheon Aircraft Company, Manager

Service Engineering, Hawker Customer

Support Department, P.O. Box 85,

Wichita, Kansas 67201–0085. This

information may be examined at the

FAA, Transport Airplane Directorate,

1601 Lind Avenue, SW., Renton,

Washington.

FOR FURTHER INFORMATION CONTACT:

William Schroeder, Aerospace Engineer,

Standardization Branch, ANM–113,

FAA, Transport Airplane Directorate,

1601 Lind Avenue, SW., Renton,

Washington 98055–4056; telephone

(206) 227–2148; fax (206) 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 Number96–NM–180–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.

96–NM–180–AD, 1601 Lind Avenue,

SW., Renton, Washington 98055–4056.

Discussion

The FAA has reviewed results of a

design review of requirements for

certification of the cabin pressurization

system on Raytheon Model BAe 125 and

Model Hawker 1000 series airplanes.

The Civil Aviation Authority (the

airworthiness authority for the United

Kingdom) and the manufacturer

(Raytheon) conducted the design

review, and determined that the existing

venting between certain structural

members is inadequate to provide rapid

equalization of the pressure differential

between the two sides of these members

when rapid decompression occurs on

one side of the member. Inadequate

venting of cabin pressure, if not

corrected, could cause failure or

deformation of certain structural

members, and consequent reduced

controllability of the airplane.

Explanation of Relevant Service

Information

The FAA has reviewed and approved

the following Raytheon Service

Bulletins:

1. Service Bulletin SB.21–151–

25A683C, dated July 12, 1994

(Modification 25A683C), which

describes procedures for installing a

pressure relief flap in the rear luggage

compartment of the bulkhead at frame

19. Installation of the pressure relief flap

will limit the pressure differential

across the rear luggage compartment in

the event of rapid decompression of the

airplane.

2. Service Bulletin SB.53–81–3661B,

dated February 25, 1994 (Modification

253661B), which describes procedures

to remove the fiberglass infill cover

located outboard of the floor panels

between frame 8 and frame 10B. This

service bulletin also describes

procedures to increase the existing size

of the lightening holes in the rail web

of the right-hand seat between frame

10B and frame 10D, and to add a third

hole to increase the vent area.

Additionally, the service bulletin

describes procedures for installation of

a new reinforcing plate for all three

lightening holes. Accomplishment of

this modification will ensure the

structural integrity of the fuselage in the

event of rapid decompression of the

airplane.

3. Service Bulletin SB.53–76–3627A,

dated February 25, 1994 (Modification