Federal Register / Vol. 63, No. 147 / Friday, July 31, 1998 /Rules and Regulations 40811

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 98–NM–80–AD; Amendment

39–10685; AD 98–16–09]

RIN 2120–AA64

Airworthiness Directives; Airbus Model

A300, A310, and A300–600 Series

Airplanes

AGENCY: Federal Aviation

Administration, DOT.

ACTION: Final rule.

SUMMARY: This amendment adopts a

new airworthiness directive (AD),

applicable to certain Airbus Model

A300, A310, and A300–600 series

airplanes, that requires a one-time

operational test of the fire shut-off

valves (FSOV’s) to determine if the

FSOV’s are functioning correctly, and

replacement of failed parts with new or

serviceable parts. This amendment is

prompted by issuance of mandatory

continuing airworthiness information by

a foreign civil airworthiness authority.

The actions specified by this AD are

intended to prevent failure of the

FSOV’s to close, which could result in

failure of the engine fire shut-off system,

and consequent inability to extinguish

an engine fire.

DATES: Effective September 4, 1998.

The incorporation by reference of

certain publications listed in the

regulations is approved by the Director

of Federal Register as of September 4,

1998.

ADDRESSES: The service information

referenced in this AD may be obtained

from Airbus Industrie, 1 Rond Point

Maurice Bellonte, 31707 Blagnac Cedex,

France. This information may be

examined at the Federal Aviation

Administration (FAA), Transport

Airplane Directorate, Rule Docket, 1601

Lind Avenue, SW., Renton, Washington;

or at the Office of the Federal Register,

800 North Capitol Street, NW., suite

700, Washington, DC.

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 (415) 227–2110;

fax (425) 227–1149.

SUPPLEMENTARY INFORMATION: A

proposal to amend part 39 of the Federal

Aviation Regulations (14 CFR part 39) to

include an airworthiness directive (AD)

that is applicable to certain Airbus

Model A300, A310, and A300–600

series airplanes was published in the

Federal Register on April 6, 1998 (63 FR

16716). That action proposed to require

a one-time operational test of the fire

shut-off valves (FSOV’s) to determine if

the FSOV’s are functioning correctly,

and replacement of failed parts with

new or serviceable parts.

Comments

Interested persons have been afforded

an opportunity to participate in the

making of this amendment. Due

consideration has been given to the

comments received.

Two commenters express no objection

to the proposed rule. However, both

request that the applicability of the

proposed AD be revised to expressly

identify affected part numbers of the fire

shut-off valves, rather than referencing

information contained in Airbus All

Operator Telex (AOT) 29–22, dated

November 24, 1997. The commenters

state that such a change will prevent

confusion by removing any ambiguity as

to which airplanes are affected by this

proposed AD. The FAA concurs that the

applicability can be revised to specify

those airplanes having an affected part

number installed. Because the

referenced AOT provides this same

information, there is no change in the

airplanes that would be affected by the

proposed AD. The final rule has been

revised accordingly.

Conclusion

After careful review of the available

data, including the comments noted

above, the FAA has determined that air

safety and the public interest require the

adoption of the rule with the change

previously described. The FAA has

determined that this change will neither

increase the economic burden on any

operator nor increase the scope of the

AD.

Cost Impact

The FAA estimates that 103 airplanes

of U.S. registry will be affected by this

AD, that it will take approximately 1

work hour per airplane to accomplish

the required test, and that the average

labor rate is $60 per work hour. Based

on these figures, the cost impact of the

AD on U.S. operators is estimated to be

$6,180, or $60 per airplane.

The cost impact figure discussed

above is based on assumptions that no

operator has yet accomplished any of

the 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 adopted herein will

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 final rule does

not have sufficient federalism

implications to warrant the preparation

of a Federalism Assessment.

For the reasons discussed above, I

certify that this action (1) is not a

‘‘significant regulatory action’’ under

Executive Order 12866; (2) is not a

‘’significant rule’’ under DOT

Regulatory Policies and Procedures (44

FR 11034, February 26, 1979); and (3)

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 final evaluation has

been prepared for this action and it is

contained in the Rules Docket. A copy

of it may be obtained from the Rules

Docket at the location provided under

the caption ADDRESSES.

List of Subjects in 14 CFR Part 39

Air transportation, Aircraft, Aviation

safety, Incorporation by reference,

Safety.

Adoption of the Amendment

Accordingly, pursuant to the

authority delegated to me by the

Administrator, the Federal Aviation

Administration amends 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:

98–16–09 Airbus Industrie: Amendment

39–10685. Docket 98–NM–80–AD.

Applicability: Model A300, A310, and

A300–600 series airplanes; on which any fire

shut-off valve (FSOV) having part number (P/

N) B38LC37XX or B38LC50XX (where XX is

05, 06, 07, 08, 09, or 10) is installed;

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
40812 Federal Register / Vol. 63, No. 147 / Friday, July 31, 1998 /Rules and Regulations

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 failure of the FSOV’s to close,

which would result in failure of the engine

fire shut-off system, and consequently

inability to extinguish an engine fire,

accomplish the following:

(a) Within 500 flight hours after the

effective date of this AD, perform a one-time

operational test of the 4 fire shut-off valves

(FSOV’s) on the airplane, in accordance with

Airbus All Operator Telex (AOT) 29–22,

dated November 24, 1997. If any FSOV fails

the test, prior to further flight, replace the

failed FSOV or actuator, as applicable, with

a new or serviceable FSOV or actuator, as

applicable, in accordance with AOT 29–22.

(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.

(d) The actions shall be done in accordance

with Airbus All Operator Telex (AOT) 29–22,

dated November 24, 1997. This incorporation

by reference was approved by the Director of

the Federal Register in accordance with 5

U.S.C. 552(a) and 1 CFR part 51. Copies may

be obtained from Airbus Industrie, 1 Rond

Point Maurice Bellonte, 31707 Blagnac

Cedex, France. Copies may be inspected at

the FAA, Transport Airplane Directorate,

1601 Lind Avenue, SW., Renton,

Washington; or at the Office of the Federal

Register, 800 North Capitol Street, NW., suite

700, Washington, DC.

Note 3: The subject of this AD is addressed

in French airworthiness directive 97–384–

241(B)R1, dated January 14, 1998.

(e) This amendment becomes effective on

September 4, 1998.

Issued in Renton, Washington, on July 24,

1998.

S.R. Miller,

Acting Manager, Transport Airplane

Directorate, Aircraft Certification Service.

[FR Doc. 98–20432 Filed 7–30–98; 8:45 am]

BILLING CODE 4910–13–U

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 96–NM–42–AD; Amendment

39–10680; AD 98–16–05]

RIN 2120–AA64

Airworthiness Directives; Airbus Model

A300–600 Series Airplanes

AGENCY: Federal Aviation

Administration, DOT.

ACTION: Final rule.

SUMMARY: This amendment adopts a

new airworthiness directive (AD),

applicable to all Airbus Model A300–

600 series airplanes, that requires

inspections of the areas behind the scuff

plates below the passenger/crew doors

and bulk cargo door to detect cracks and

corrosion, and repair, if necessary. This

amendment also requires inspections to

detect cracking of the holes of the corner

doublers, the fail-safe ring, and the door

frames of the door structures; and

repair, if necessary. In addition, this

amendment provides for optional

terminating action for certain

inspections. This amendment is

prompted by reports indicating that

corrosion was found behind the scuff

plates at exit and cargo doors, and

fatigue cracks originated from certain

fastener holes located in adjacent

structure. The actions specified by this

AD are intended to detect and correct

such corrosion and fatigue cracking,

which could result in reduced structural

integrity of the door surroundings.

DATES: Effective September 4, 1998.

The incorporation by reference of

certain publications listed in the

regulations is approved by the Director

of the Federal Register as of September

4, 1998.

ADDRESSES: The service information

referenced in this AD may be obtained

from Airbus Industrie, 1 Rond Point

Maurice Bellonte, 31707 Blagnac Cedex,

France. This information may be

examined at the Federal Aviation

Administration (FAA), Transport

Airplane Directorate, Rules Docket,

1601 Lind Avenue, SW., Renton,

Washington; or at the Office of the

Federal Register, 800 North Capitol

Street, NW., suite 700, Washington, DC.

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: A

proposal to amend part 39 of the Federal

Aviation Regulations (14 CFR part 39) to

include an airworthiness directive (AD)

that is applicable to all Airbus Model

A300–600 series airplanes was

published in the Federal Register on

January 29, 1997 (62 FR 4211). That

action proposed to require inspections

of the lower door surrounding structure

to detect cracks and corrosion, and

repair, if necessary. That action also

proposed to require inspections to

detect cracking of the holes of the corner

doublers, the fail-safe ring, and the door

frames of the door structures; and

repair, if necessary. In addition, that

action proposed to provide for optional

terminating action for certain

inspections.

Comments

Interested persons have been afforded

an opportunity to participate in the

making of this amendment. Due

consideration has been given to the

comments received.

Clarification of Terminology

One commenter expresses no

objection to the proposed rule, but

requests that certain terminology in the

proposed AD be changed for the sake of

clarity. The commenter states that the

title is not complete, since it refers only

to inspections of the lower door

structure, while inspection of the upper

door corners is also required. The FAA

concurs. The FAA infers that the

commenter is referring to the Summary

section of the proposed AD, which

states that ‘‘this proposal would require

inspections of the lower door

surrounding structure.’’ However, in all

other sections of the proposed AD, the

area to be inspected is described as ‘‘the

areas behind the scuff plates below the

passenger/crew doors and bulk cargo

door,’’ in accordance with procedures

described in Airbus Service Bulletin

A300–53–6011, Revision 3, dated

February 4, 1991. To avoid confusion

regarding the area to be inspected for

cracks and corrosion, the Summary

section of the final rule has been

changed to correspond to the

terminology used elsewhere throughout

the AD.

The same commenter requests that

paragraphs (b) and (d) of the proposed

AD be changed to refer to the ‘‘fail-safe

ring and corner strap,’’ rather than the

existing terminology of ‘‘fail-safe ring

and corner doubler.’’ The commenter

states that the term ‘‘corner strap’’ is

used in Airbus Service Bulletin A300–

53–6022, dated February 4, 1991, and in

other maintenance documents, rather

than ‘‘corner doubler.’’ The FAA does