Federal Register / Vol. 63, No. 147 / Friday, July 31, 1998 /Rules and Regulations 40809

(d) As an alternative method of compliance

to the actions required by this AD, including

the actions in paragraphs (a), (b)(1), and

(b)(2), modify the fuel tank vent valve system

in accordance with the Accomplishment

Instructions section of Pilatus Service

Bulletin No. 28–005, dated May 4, 1998.

(e) 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.

(f) An alternative method of compliance or

adjustment of the compliance time that

provides an equivalent level of safety may be

approved by the Manager, Small Airplane

Directorate, FAA, 1201 Walnut, suite 900,

Kansas City, Missouri 64106.

(1) The request shall be forwarded through

an appropriate FAA Maintenance Inspector,

who may add comments and then send it to

the Manager, Small Airplane Directorate.

(2) Alternative methods of compliance

approved in accordance with AD 98–11–01

R1 (revised by this action), AD 98–11–01

(revised by AD 98–11–01 R1), and AD 97–

23–04 (superseded by AD 98–11–01) are

considered approved as alternative methods

of compliance for this AD.

Note 2: Information concerning the

existence of approved alternative methods of

compliance with this AD, if any, may be

obtained from the Small Airplane

Directorate.

(g) Questions or technical information to

the service information referenced in this

document should be directed to Pilatus

Aircraft Ltd., CH–6370 Stans, Switzerland.

This service information may be examined at

the FAA, Central Region, Office of the

Regional Counsel, Room 1558, 601 E. 12th

Street, Kansas City, Missouri 64106.

(h) The replacement required by this AD

shall be done in accordance with Pilatus

Service Bulletin No. 28–003, Revision 1,

dated September 30, 1997. The drilling

required by this AD shall be done in

accordance with Pilatus Service Bulletin No.

28–004, dated March 27, 1998. The

modification required by this AD shall be

done in accordance with Pilatus Service

Bulletin No. 28–005, dated May 4, 1998.

(1) The incorporation by reference of

Pilatus Service Bulletin No. 28–003, dated

September 30, 1997, was previously

approved by the Director of the Federal

Register as of December 1, 1997 (62 FR

59993, November 6, 1997).

(2) The incorporation by reference of

Pilatus Service Bulletin No. 28–004, dated

March 27, 1998, was previously approved by

the Director of the Federal Register as of June

7, 1998 (63 FR 27195, May 18, 1998).

(3) The incorporation by reference of

Pilatus Service Bulletin No. 28–005, dated

May 4, 1998, was previously approved by the

Director of the Federal Register as of

September 22, 1998 (63 FR 34565, June 25,

1998).

(4) Copies of these service bulletins may be

obtained from Pilatus Aircraft Ltd., CH–6370

Stans, Switzerland. Copies may be inspected

at the FAA, Central Region, Office of the

Regional Counsel, Room 1558, 601 E. 12th

Street, Kansas City, Missouri, 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 Swiss AD HB 97–432A, dated October 3,

1997; Swiss AD HB 98–086, dated March 31,

1998; and Swiss AD HB 98–126, dated May

15, 1998.

(i) This amendment revises AD 98–11–01

R1, amendment 39–10608; which revised AD

98–11–01, Amendment 39–10528; which

superseded AD 97–23–04, Amendment No.

39–10192.

(j) This amendment becomes effective on

September 22, 1998.

Issued in Kansas City, Missouri, on July 23,

1998.

Michael Gallagher,

Acting Manager, Small Airplane Directorate,

Aircraft Certification Service.

[FR Doc. 98–20439 Filed 7–30–98; 8:45 am]

BILLING CODE 4910–13–U

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 98–NM–19–AD; Amendment

39–10684; AD 98–16–08]

RIN 2120–AA64

Airworthiness Directives; Airbus Model

A300–600 and A310 Series Airplanes

AGENCY: Federal Aviation

Administration, DOT.

ACTION: Final rule.

SUMMARY: This amendment supersedes

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 amendment requires

accomplishment of the previously

optional terminating action. 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 incorrect primary power setting

parameters of the TCC, which could

result in insufficient thrust being

applied during takeoff.

DATES: Effective September 4, 1998.

The incorporation by reference of

certain publications as listed in the

regulations was approved previously by

the Director of the Federal Register as of

January 22, 1998 (63 FR 658, January 7,

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)

by superseding AD 98–01–09,

amendment 39–10272 (63 FR 658,

January 7, 1998), which is applicable to

certain Airbus Model A300–600 and

A310 series airplanes, was published in

the Federal Register on May 28, 1998

(63 FR 29146). The action proposed to

continue to require 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. The action also proposed to

require accomplishment of the

previously optional terminating action.

Comments

Interested persons have been afforded

an opportunity to participate in the

making of this amendment. No

comments were submitted in response

to the proposal or the FAA’s

determination of the cost to the public.

Conclusion

The FAA has determined that air

safety and the public interest require the

adoption of the rule as proposed.

Cost Impact

There are approximately 94 airplanes

of U.S. registry that will be affected by

this AD.

The AFM revision that is currently

required by AD 98–01–09, 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.
40810 Federal Register / Vol. 63, No. 147 / Friday, July 31, 1998 /Rules and Regulations

The modification that is required by

this new AD will take approximately 3

work hours per airplane to accomplish,

at an average labor rate of $60 per work

hour. Required parts will cost

approximately $4,300 per airplane.

Based on these figures, the cost impact

of the new requirements of the

modification required 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 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

removing amendment 39–10272 (63 FR

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

new airworthiness directive (AD),

amendment 39–10684, to read as

follows:

98–16–08 Airbus Industrie: Amendment

39–10684. 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

into 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

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.

(e) The actions shall be done in accordance

with Airbus A300–600 Flight Manual

Temporary Revision 4.03.00/18, dated

November 4, 1996; Airbus Model A300–600

Flight Manual Temporary Revision 4.03.00/

19, dated November 4, 1996; Airbus A310

Flight Manual Temporary Revision 4.03.00/

20, dated November 4, 1996; or Airbus A310

Flight Manual Temporary Revision 4.03.00/

21, dated November 4, 1996; as applicable.

The modification, if accomplished, shall be

done in accordance with Airbus Service

Bulletin A310–22–2025, dated April 18,

1989; Airbus Service Bulletin A310–22–2027,

dated June 8, 1990; Airbus Service Bulletin

A310–22–2031, dated September 2, 1991;

Airbus Service Bulletin A310–22–2035,

Revision 1, dated July 13, 1994; Airbus

Service Bulletin A300–22–6010, dated April

18, 1989; Airbus Service Bulletin A300–22–

6011, dated June 8, 1990; or Airbus Service

Bulletin A300–22–6017, dated September 2,

1991; as applicable. This incorporation by

reference was approved previously by the

Director of the Federal Register as of January

22, 1998 (63 FR 658, January 7, 1998).

Note 4: The subject of this AD is addressed

in French airworthiness directive 97–110–

218(B), dated May 7, 1997.

(f) 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. 98–20431 Filed 7–30–98; 8:45 am]

BILLING CODE 4910–13–U