19684 Federal Register / Vol. 63, No. 76 /Tuesday, April 21, 1998 / Proposed Rules

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:

British Aerospace Airbus Limited (Formerly

British Aerospace Commercial Aircraft

Limited, British Aerospace Aircraft

Group): Docket 98–NM–51–AD.

Applicability: All Model BAC 1–11 200

and 400 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 (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 detect and correct cracking in the

trunnion fittings of the nose landing gear

(NLG), which could lead to collapse of the

NLG during takeoff and landing, and possible

injury to the flight crew and passengers,

accomplish the following:

(a) Perform a detailed visual inspection for

cracking on the left- and right-hand trunnion

fittings of the NLG, in the area of the

trunnion cap attachment holes, in accordance

with British Aerospace Alert Service Bulletin

53–A–PM6035, Revision 1, dated March 7,

1996; at the time specified in paragraph (a)(1)

or (a)(2) of this AD, as applicable.

(1) For airplanes on which British

Aerospace Modification PM5308 has not

been accomplished: Perform the inspection

within 6 years after the effective date of this

AD, or within 11 years after the last

inspection accomplished in accordance with

the alert service bulletin, whichever occurs

later. Repeat the inspection thereafter at

intervals not to exceed 11 years.

(2) For airplanes on which British

Aerospace Modification PM5308 has been

accomplished: Perform the inspection within

30 months after the effective date of this AD,

or within 5 years after the last inspection

accomplished in accordance with the alert

service bulletin, whichever occurs later.

Repeat the inspection thereafter at intervals

not to exceed 6 years.

(b) If any crack is found during any

inspection required by paragraph (a) of this

AD, prior to further flight, repair the crack in

accordance with a method approved by the

Manager, International Branch, ANM–116,

FAA, Transport Airplane Directorate.

(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. 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.

(d) 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 the British airworthiness directive 004–

03–96, dated April 26, 1996.

Issued in Renton, Washington, on April 15,

1998.

Darrell M. Pederson,

Acting Manager, Transport Airplane

Directorate, Aircraft Certification Service.

[FR Doc. 98–10475 Filed 4–20–98; 8:45 am]

BILLING CODE 4910–13–U

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 98–NM–81–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 all

Model A300–600 series airplanes. This

proposal would require a one-time

inspection for cracking of the gantry

lower flanges in the main landing gear

(MLG) bay area; 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 cracking

of the gantry lower flanges in the MLG

bay area, which could result in

decompression of the airplane.

DATES: Comments must be received by

May 21, 1998.

ADDRESSES: Submit comments in

triplicate to the Federal Aviation

Administration (FAA), Transport

Airplane Directorate, ANM–114,

Attention: Rules Docket No. 98–NM–

81–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–81–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
Federal Register / Vol. 63, No. 76 /Tuesday, April 21, 1998 / Proposed Rules 19685

FAA, Transport Airplane Directorate,

ANM–114, Attention: Rules Docket No.

98–NM–81–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 A300 and all Model A300–600

series airplanes. The DGAC advises that,

during an inspection on a Model A300–

600 series airplane, cracks were found at

20,600 flight cycles between left-hand

frames 51 and 52 on the gantry (frame

support structure) lower flange 4 in the

main landing gear (MLG) bay area. In

addition, the DGAC advises that, during

an inspection on a Model A300–600

series airplane, cracks were found at

16,800 flight cycles between right-hand

frames 50B, 51A, and 52A and at lefthand frame 50B on the gantry lower

flange 5. Such cracking, if not corrected,

could result in decompression of the

airplane.

The cause of the cracking in this area

is still under investigation. However,

the gantry lower flanges on certain

Model A300 series airplanes are

identical in design to those on Model

A300–600 series airplanes; therefore,

both models may be subject to the same

unsafe condition.

Explanation of Relevant Service

Information

Airbus has issued All Operators Telex

(AOT) 53–11, dated October 13, 1997,

which describes procedures for a onetime ultrasonic inspection for cracking

of the gantry lower flanges in the MLG

bay area. This AOT also describes

procedures for repair of cracks. The

repair involves stop drilling of cracks as

a temporary repair, or installing a

doubler on the gantry lower flange to

reinforce the area. The DGAC classified

this AOT as mandatory and issued

French airworthiness directive 97–372–

236(B), dated December 3, 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 § 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 AOT described previously, except

as discussed below.

Interim Action

This is considered to be interim

action until final action is identified, at

which time the FAA may consider

further rulemaking.

Differences Between Proposed Rule and

Service Information

Operators should note that, unlike the

procedures described in Airbus AOT

53–11, dated October 13, 1997, this

proposed AD would not permit further

flight if cracks are detected in the gantry

lower flanges in the MLG bay area. The

FAA has determined that, because of the

safety implications and consequences

associated with such cracking, any

subject gantry lower flange that is found

to be cracked must be repaired or

modified prior to further flight.

Cost Impact

The FAA estimates that 67 airplanes

of U.S. registry would be affected by this

proposed AD. It would take

approximately 4 work hours per

airplane to accomplish the proposed

inspection, at an average labor rate of

$60 per work hour. Based on this figure,

the cost impact of the proposed AD on

U.S. operators is estimated to be

$16,080, or $240 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 98–NM–81–AD.

Applicability: Model A300 series airplanes

on which Airbus Modification 3474 has been

accomplished, and all Model 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

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 detect and correct cracking of the gantry

lower flanges in the main landing gear (MLG)

bay area, which could result in
19686 Federal Register / Vol. 63, No. 76 /Tuesday, April 21, 1998 / Proposed Rules

decompression of the airplane, accomplish

the following:

(a) Prior to the accumulation of 16,300 total

flight cycles, or within 500 flight cycles after

the effective date of this AD, whichever

occurs later, perform a one-time ultrasonic

inspection for cracking of the gantry lower

flanges in the MLG bay area, in accordance

with Airbus All Operators Telex (AOT) 53–

11, dated October 13, 1997.

(1) If any cracking is detected, prior to

further flight, repair in accordance with the

AOT.

(2) If no cracking is detected, no further

action is required by this AD.

(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 97–372–

236(B), dated December 3, 1997.

Issued in Renton, Washington, on April 15,

1998.

Darrell M. Pederson,

Acting Manager, Transport Airplane

Directorate, Aircraft Certification Service.

[FR Doc. 98–10488 Filed 4–20–98; 8:45 am]

BILLING CODE 4910–13–U

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 98–NM–100–AD]

RIN 2120–AA64

Airworthiness Directives; Saab Model

SAAB SF340A and SAAB 340B 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 Saab Model SAAB SF340A and

SAAB 340B series airplanes. This

proposal would require repetitive,

detailed visual inspections of the

windshield wiper assembly for

discrepant conditions, 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 failure of the

windshield wiper assembly, which

could result in loss of visibility, damage

to the propeller(s), or penetration of the

fuselage skin and consequent

depressurization of the airplane.

DATES: Comments must be received by

May 21, 1998.

ADDRESSES: Submit comments in

triplicate to the Federal Aviation

Administration (FAA), Transport

Airplane Directorate, ANM–114,

Attention: Rules Docket No. 98–NM–

100–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

Saab Aircraft AB, SAAB Aircraft

Product Support, S–581.88, Linko ̈ping,

Sweden. 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–100–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–100–AD, 1601 Lind Avenue,

SW., Renton, Washington 98055–4056.

Discussion

The Luftfartsverket (LFV), which is

the airworthiness authority for Sweden,

notified the FAA that an unsafe

condition may exist on certain Saab

Model SAAB SF340A and SAAB 340B

series airplanes. The LFV advises that it

has received reports indicating that a

windshield wiper blade separated from

the wiper arm at the attachment point,

which consists of two rivets that

connect the wiper blade and arm tip to

the wiper arm. On one airplane, the

wiper blade struck and damaged a

propeller and was thrown into the side

of the airplane. The cause of the

detachment of the blade has been

attributed to the failure of the two rivets.

Such failure could result in loss of

visibility, damage to the propeller(s), or

penetration of the fuselage skin and

consequent depressurization of the

airplane.

Explanation of Relevant Service

Information

The manufacturer has issued SAAB

Service Bulletin 340–30–081, dated

November 14, 1997, including

Attachment 1, Revision 1, dated

September 14, 1997, which describes

procedures for a one-time, detailed

visual inspection of the windshield

wiper assembly for discrepant

conditions (corrosion; excessive wear;

missing, loose, or broken parts;

improper alignment; and insecure

attachment), and corrective actions, if

necessary. The corrective actions

include repairing the arm tip assembly

or replacing it with a new or serviceable

part, if necessary. Accomplishment of

the actions specified in the service

bulletin is intended to adequately

address the identified unsafe condition.

The LFV classified this service bulletin

as mandatory and issued Swedish

airworthiness directive 1–115R1, dated