658 Federal Register / Vol. 63, No. 4 / Wednesday, January 7, 1998 / Rules and Regulations

April 20, 1998, and this rule needs to be

in effect by February so containers can

be ordered in time for harvest and

shipment; and (4) this rule provides a

60-day comment period and any

comments received will be considered

prior to finalization of this rule.

List of Subjects in 7 CFR Part 925

Grapes, Marketing agreements and

orders, Reporting and recordkeeping

requirements.

For the reasons set forth in the

preamble, 7 CFR part 925 is amended to

read as follows:

PART 925—GRAPES GROWN IN A

DESIGNATED AREA OF

SOUTHEASTERN CALIFORNIA

1. The authority citation for 7 CFR

part 925 continues to read as follows:

Authority: 7 U.S.C. 601–674.

2. In part 925, the words ‘‘California

Administrative Code (Title 3)’’ are

removed and the words ‘‘Title 3:

California Code of Regulations’’ are

added in their place everywhere they

appear.

3. In § 925.304:

(A) Paragraph (b)(1) introductory text

is amended by removing the number

‘‘1380.19(14)’’ and adding in its place

the phrase ‘‘1380.14, and 1380.19(n)’’,

and

(B) Paragraphs (b)(1)(i) through (vii)

are removed and paragraphs (b)(1)(viii)

and (ix) are redesignated as paragraphs

(b)(1)(ii) and (b)(1)(iii) and a new

paragraph (b)(1)(i) is added to read as

follows:

§ 925.304 California Desert Grape

Regulation 6.

* * * * *

(b) * * *

(1) * * *

(i)

CONTAINER DESCRIPTIONS IN INCHES

Container Depth Width Length

28 Sawdust Pack ........................................................... 73⁄4 (inside) ........................ 1415⁄16 (inside) ................... 185⁄8 (inside).

38J Polystyrene Lug ....................................................... 63⁄4 (inside) ........................ 121⁄2 (inside) ...................... 153⁄8 (inside).

38K Standard Grape ...................................................... 41⁄2 to 81⁄2 (inside) ............. 131⁄2 to 141⁄2 (outside) ....... 165⁄8 to 171⁄2 (outside).

38Q Polystyrene Lug ...................................................... 61⁄4 to 81⁄4 (inside) ............. 111⁄4 (inside) ...................... 181⁄8 (inside).

38R Grape Lug ............................................................... 4 to 7 (inside) .................... 153⁄4 to 16 (outside) ........... 1911⁄16 to 20 (outside).

38S Grape Lug ............................................................... 5 to 9 (inside) .................... 1111⁄16 to 12 (outside) ....... 1911⁄16 to 20 (outside).

38T Grape Lug ............................................................... 51⁄2 to 71⁄2 (inside) ............. 131⁄8 to 1315⁄16 (outside) .... 155⁄16 to 16 (outside).

38U Grape Lug ............................................................... 63⁄16 to 7 (inside) ............... 1311⁄16 (outside) ................. 201⁄2 (outside).

38 V Grape Lug .............................................................. 5 3⁄4 (inside) ....................... 14 (outside) ........................ 16 (outside).

* * * * *

Dated: December 30, 1997.

Sharon Bomer Lauritsen,

Acting Deputy Administrator, Fruit and

Vegetable Programs.

[FR Doc. 98–284 Filed 1–6–98; 8:45 am]

BILLING CODE 3410–02–P

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 97–NM–333–AD; Amendment

39–10272; AD 98–01–09]

RIN 2120–AA64

Airworthiness Directives; Airbus Model

A300–600 and A310 Series Airplanes

AGENCY: Federal Aviation

Administration, DOT.

ACTION: Final rule; request for

comments.

SUMMARY: This amendment adopts a

new airworthiness directive (AD) that is

applicable to certain Airbus Model

A300–600 and A310 series airplanes.

This action requires revising the

Airplane Flight Manual (AFM) to

instruct the flightcrew to crosscheck

certain primary power setting

parameters of the Thrust Control

Computer (TCC) against tables of these

values; and apply corrective action, if

necessary. This amendment also

provides for optional terminating action

for the AFM revision. This amendment

is prompted by issuance of mandatory

continuing airworthiness information by

a foreign civil airworthiness authority.

The actions specified in this AD are

intended to ensure that the flightcrew is

provided with procedures for

crosschecking and correcting certain

primary power setting parameters of the

TCC; incorrect parameters could result

in insufficient thrust being applied

during takeoff.

DATES: Effective January 22, 1998.

The incorporation by reference of

certain publications listed in the

regulations is approved by the Director

of the Federal Register as of January 22,

1998.

Comments for inclusion in the Rules

Docket must be received on or before

February 6, 1998.

ADDRESSES: Submit comments in

triplicate to the Federal Aviation

Administration (FAA), Transport

Airplane Directorate, ANM–114,

Attention: Rules Docket No. 97–NM–

333–AD, 1601 Lind Avenue, SW.,

Renton, Washington 98055–4056.

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 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.

FOR FURTHER INFORMATION CONTACT:

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: 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 A310 and A300–

600 series airplanes. The DGAC advises

that, in three instances, incorrect

primary power setting parameters [N1

rotor speed or engine pressure ratio

(EPR)] have been observed on airplanes

in service. These incorrect parameters

have been attributed to inaccurate data

computations by the Thrust Control

Computer (TCC), due to electrical power

transients occurring during the engine

startup sequence. Incorrect primary

power setting parameters in the TCC, if

not corrected, could result in

insufficient thrust being applied during

takeoff.

Explanation of Relevant Service

Information

Airbus has issued A300–600 Flight

Manual Temporary Revisions 4.03.00/18

and 4.03.00/19; and A310 Flight Manual

Temporary Revisions 4.03.00/20 and
Federal Register / Vol. 63, No. 4 / Wednesday, January 7, 1998 / Rules and Regulations 659

4.03.00/21; all dated November 4, 1996.

These temporary revisions describe

procedures for crosschecking the

primary power setting parameters (N1 or

EPR) of the TCC against tables of these

values given in the Airplane Flight

Manual (AFM); and resetting the TCC, if

necessary.

Airbus also has issued service

bulletins which describe procedures for

modification of the TCC on certain

airplanes, to prevent its sensitivity to

electrical power transients.

Accomplishment of the modification

eliminates the need for the AFM

limitation. The modification of the TCC

varies depending on the airplane model

and engine configuration, as specified in

each Airbus service bulletin below:

• 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;

and

• A300–22–6017, dated September 2,

1991.

The DGAC classified these AFM

temporary revisions and service

bulletins as mandatory and issued

French airworthiness directive 97–110–

218(B), dated May 7, 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 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 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, this AD is being issued to ensure

that the flightcrew is provided with

procedures for crosschecking and

correcting certain primary power setting

parameters of the TCC; incorrect

parameters could result in insufficient

thrust being applied during takeoff. This

AD requires revising the Limitations

Section of the FAA-approved AFM by

incorporating the previously described

temporary AFM revisions, as applicable.

This AD also provides for optional

terminating action for the AFM

revisions.

Interim Action

This AD is considered to be interim

action. While the French airworthiness

directive also requires modification of

the TCC on certain A310 and A300–600

series airplanes, in accordance with the

previously described service bulletins,

this AD provides for optional

modification of the TCC. The FAA is

currently considering requiring

modification of the TCC. However, the

planned compliance time is sufficiently

long so that notice and opportunity for

prior public comment will be

practicable.

Determination of Rule’s Effective Date

Since a situation exists that requires

the immediate adoption of this

regulation, it is found that notice and

opportunity for prior public comment

hereon are impracticable, and that good

cause exists for making this amendment

effective in less than 30 days.

Comments Invited

Although this action is in the form of

a final rule that involves requirements

affecting flight safety and, thus, was not

preceded by notice and an opportunity

for public comment, comments are

invited on this rule. Interested persons

are invited to comment on this 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

under the caption ADDRESSES. All

communications received on or before

the closing date for comments will be

considered, and this rule may be

amended in light of the comments

received. Factual information that

supports the commenter’s ideas and

suggestions is extremely helpful in

evaluating the effectiveness of the AD

action and determining whether

additional rulemaking action would be

needed.

Comments are specifically invited on

the overall regulatory, economic,

environmental, and energy aspects of

the rule that might suggest a need to

modify the 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 that

summarizes each FAA-public contact

concerned with the substance of this AD

will be filed in the Rules Docket.

Commenters wishing the FAA to

acknowledge receipt of their comments

submitted in response to this rule must

submit a self-addressed, stamped

postcard on which the following

statement is made: ‘‘Comments to

Docket Number 97–NM–333–AD.’’ The

postcard will be date stamped and

returned to the commenter.

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.

The FAA has determined that this

regulation is an emergency regulation

that must be issued immediately to

correct an unsafe condition in aircraft,

and that it is not a ‘‘significant

regulatory action’’ under Executive

Order 12866. It has been determined

further that this action involves an

emergency regulation under DOT

Regulatory Policies and Procedures (44

FR 11034, February 26, 1979). If it is

determined that this emergency

regulation otherwise would be

significant under DOT Regulatory

Policies and Procedures, a final

regulatory evaluation will be prepared

and placed in the Rules Docket. A copy

of it, if filed, 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.
660 Federal Register / Vol. 63, No. 4 / Wednesday, January 7, 1998 / Rules and Regulations

§ 39.13 [Amended]

2. Section 39.13 is amended by

adding the following new airworthiness

directive:

98–01–09 Airbus Industrie: Amendment 39–

10272. Docket 97–NM–333–AD.

Applicability: Model A310 and A300–600

series airplanes equipped with General

Electric CF6–80C2 engines on which Airbus

Modification 7174, 7588, or 8246 has not

been accomplished; and Model A310 and

A300–600 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 ensure that the flightcrew is provided

with procedures for crosschecking and

correcting certain primary power setting

parameters of the Thrust Control Computer

(TCC),accomplish the following:

(a) Within 15 days after the effective date

of this AD, 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

in the AFM, provided the information

contained in the general revision is identical

to that specified in the applicable temporary

revision cited in paragraph (a).

(b) Accomplishment of modification of the

TCC in accordance with the applicable

Airbus service bulletins specified below

constitutes terminating action for the

requirement of paragraph (a) of this AD:

• 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;

• A300–22–6017, dated September 2,

1991.

After the modification has been

accomplished, the Temporary AFM 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 AFM revision 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 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 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

January 22, 1998.

Issued in Renton, Washington, on

December 29, 1997.

Darrell M. Pederson,

Acting Manager, Transport Airplane

Directorate, Aircraft Certification Service.

[FR Doc. 98–115 Filed 1–6–98; 8:45 am]

BILLING CODE 4910–13–U

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 61

[Docket No. 28095; SFAR No. 73–1]

RIN 2120–AG47

Robinson R–22/R–44 Special Training

And Experience Requirements

AGENCY: Federal Aviation

Administration (FAA), Department of

Transportation (DOT).

ACTION: Final rule.

SUMMARY: This final rule extends the

expiration date of Special Federal

Aviation Regulation (SFAR) 73, and

amends the special training and

experience requirements for pilots

operating the Robinson R–22 or R–44

helicopters in order to maintain the safe

operation of Robinson helicopters. It

also requires special training and

experience requirements for certified

flight instructors conducting student

instruction or flight reviews. The

purpose of this action is to maintain

awareness of and training for the

potential hazards of particular flight

operations needed for the continued

safe operation of Robinson helicopters.

EFFECTIVE DATE: December 31, 1997.

FOR FURTHER INFORMATION CONTACT:

Robert J. O’Haver, Operations Branch,

AFS–820, General Aviation and

Commercial Division, 800

Independence Avenue, SW.,

Washington, DC 20591; telephone: (202)

267–7031.

SUPPLEMENTARY INFORMATION:

Availability of Final Rule

This document may be downloaded

from the FAA regulations section of the

FedWorld electronic bulletin board

(telephone: 703–321–3339), the Federal

Register’s electronic bulletin board

(telephone: 202–512–1661), or the

FAA’s Aviation Rulemaking Advisory

Committee Bulletin Board (telephone:

800–322–2722 or 202–267–5948).

Internet users may access the FAA’s

web page at http://www.faa.gov or the

Federal Register’s web page at http://

www.access.gpo.gov/suldocs to

download recently published

rulemaking documents.

Any person may obtain a copy of this

final rule by submitting a request to the

Federal Aviation Administration, Office

of Rulemaking, ARM–1, 800

Independence Avenue, SW.,

Washington, DC 20591, or by calling

(202) 267–9677. Communications must

reference the amendment number of this

final rule.