Federal Register / Vol. 64, No. 144 /Wednesday, July 28, 1999 /Rules and Regulations 40743

may be subject to criminal and

administrative sanctions.

(5) The administrative fee for limited

coverage will be waived if you request

it and you qualify as a limited resource

farmer.

(6) The administrative fee for

additional coverage is not subject to any

limits and may not be waived.

* * * * *

15. Production Included in

Determining Indemnities.

* * * * *

(d) The amount of an indemnity that

may be determined under the applicable

provisions of your crop policy may be

reduced by an amount, determined in

accordance with the Crop Provisions or

Special Provisions, to reflect out-ofpocket expenses that were not incurred

by you as a result of not planting, caring

for, or harvesting the crop. Indemnities

paid for acreage prevented from being

planted will be based on a reduced

guarantee as provided for in the crop

policy and will not be further reduced

to reflect expenses not incurred.

* * * * *

Signed in Washington, DC, on July 20,

1999.

Kenneth D. Ackerman,

Manager, Federal Crop Insurance

Corporation.

[FR Doc. 99–19013 Filed 7–27–99; 8:45 am]

BILLING CODE 3410–08–P

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 98–NM–62–AD; Amendment

39–11236; AD 99–16–01]

RIN 2120–AA64

Airworthiness Directives; Airbus

Industrie Model A300–600 Series

Airplanes

AGENCY: Federal Aviation

Administration, DOT.

ACTION: Final rule.

SUMMARY: This amendment supersedes

an existing airworthiness directive (AD),

applicable to certain Airbus Industrie

Model A300–600 series airplanes, that

currently requires repetitive high

frequency eddy current inspections to

detect cracks in bolt holes where parts

of the main landing gear are attached to

the rear spar, and repair, if necessary.

This amendment requires repetitive

ultrasonic inspections to detect cracking

in certain bolt holes of the rear spar, and

repair, if necessary. 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 detect and correct cracking

of the rear spar of the wing, which could

result in reduced structural integrity of

the airplane.

DATES: Effective September 1, 1999.

The incorporation by reference of

Airbus Industrie Service Bulletin A300–

57–6017, Revision 3, dated November

19, 1997, as listed in the regulations is

approved by the Director of the Federal

Register as of September 1, 1999.

The incorporation by reference of

Airbus Industrie Service Bulletin A300–

57–6017, Revision 1 (includes

Appendix 1), dated July 25, 1994, as

listed in the regulations was approved

previously by the Director of the Federal

Register as of November 9, 1995 (60 FR

52618, October 10, 1995).

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 95–20–02,

amendment 39–9380 (60 FR 52618,

October 10, 1995), which is applicable

to certain Airbus Industrie Model A300–

600 series airplanes, was published in

the Federal Register on April 23, 1999

(64 FR 19942). The action proposed to

require repetitive ultrasonic inspections

to detect cracking in certain bolt holes

of the rear spar, and repair, if necessary.

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 54 airplanes

of U.S. registry that will be affected by

this AD.

The new inspections that are required

by this AD will take approximately 226

work hours per airplane to accomplish,

at an average labor rate of $60 per work

hour. Based on these figures, the cost

impact of the new requirements of this

AD on U.S. operators is estimated to be

$732,240, or $13,560 per airplane, per

inspection cycle.

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:
40744 Federal Register / Vol. 64, No. 144 /Wednesday, July 28, 1999 /Rules and Regulations

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 39–9380 (60 FR

52618, October 10, 1995), and by adding

a new airworthiness directive (AD),

amendment 39–11236, to read as

follows:

99–16–01 Airbus Industrie: Amendment

39–11236. Docket 98–NM–62–AD.

Supersedes AD 95–20–02, Amendment

39–9380.

Applicability: Model A300–600 series

airplanes, having manufacturer’s serial

numbers (MSN) 252 through 553 inclusive,

certificated in any category; except those

airplanes on which Airbus Industrie

Production Modification No. 07601 has been

accomplished prior to delivery.

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 (h) 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 rear

spar of the wing, which could result in

reduced structural integrity of the airplane,

accomplish the following:

Restatement of Requirements of AD 95–20–

02:

Note 2: Accomplishment of the inspections

and repair of cracking in accordance with

Airbus Industrie Service Bulletin A300–57–

6017, dated November 22, 1993, prior to

November 9, 1995 (the effective date of AD

95–20–02, amendment 39–9380), is

acceptable for compliance with the

applicable action specified in this

amendment.

(a) Perform a high frequency eddy current

(HFEC) rototest inspection to detect cracks in

certain bolt holes where the main landing

gear (MLG) forward pick-up fitting and MLG

rib 5 aft are attached to the rear spar, in

accordance with Airbus Industrie Service

Bulletin A300–57–6017, Revision 1 (includes

Appendix 1), dated July 25, 1994.

Note 3: This service bulletin also

references Airbus Industrie Service Bulletin

A300–57–6020, dated November 22, 1993, as

an additional source of service information.

(1) For airplanes that have accumulated

17,300 total landings or less as of November

9, 1995: Inspect prior to the accumulation of

17,300 total landings, or within 1,500

landings after November 9, 1995, whichever

occurs later.

(2) For airplanes that have accumulated

17,301 or more total landings, but less than

19,300 total landings as of November 9, 1995:

Inspect within 1,500 landings after November

9, 1995.

(3) For airplanes that have accumulated

19,300 or more total landings as of November

9, 1995: Inspect within 750 landings after

November 9, 1995.

(b) If no crack is found during the

inspection required by paragraph (a) of this

AD, repeat that inspection thereafter at the

time specified in either paragraph (b)(1) or

(b)(2) of this AD, as applicable.

(1) For airplanes on which Airbus Industrie

Modification 07716 (as described in Airbus

Industrie Service Bulletin A300–57–6020)

has not been accomplished, inspect at the

time specified in paragraph (b)(1)(i) or

(b)(1)(ii) of this AD, as applicable.

(i) For airplanes having MSN 465 through

553 inclusive: Repeat the inspection at

intervals not to exceed 13,000 landings, until

the inspection required by paragraph

(d)(2)(i)(A) has been accomplished.

(ii) For airplanes having MSN 252 through

464 inclusive: Repeat the inspection at

intervals not to exceed 8,400 landings, until

the inspection required by paragraph

(d)(2)(i)(B) has been accomplished.

(2) For airplanes on which Airbus Industrie

Modification 07716 has been accomplished,

inspect at the time specified in either

paragraph (b)(2)(i) or (b)(2)(ii) of this AD, as

applicable.

(i) For airplanes having MSN 465 through

553 inclusive: Repeat the inspection at

intervals not to exceed 11,800 landings, until

the inspection required by paragraph

(d)(2)(ii)(A) has been accomplished.

(ii) For airplanes having MSN 252 through

464 inclusive: Repeat the inspection within

10,700 landings following the initial

inspection required by paragraph (a) of this

AD, and thereafter at intervals not to exceed

7,500 landings, until the inspection required

by paragraph (d)(2)(ii)(B) has been

accomplished.

(c) If any crack is found during the

inspection required by either paragraph (a) or

(b) of this AD, prior to further flight,

accomplish the requirements of either

paragraph (c)(1) or (c)(2) of this AD, as

applicable.

(1) For airplanes on which Airbus Industrie

Modification 07716 has not been

accomplished: Oversize the bolt hole by 1/32

inch and repeat the HFEC inspection

required by paragraph (a) of this AD, in

accordance with Airbus Industrie Service

Bulletin 300–57–6017, Revision 1, dated July

25, 1994. After accomplishing the oversizing

and HFEC inspection, repeat the inspection

as required by paragraph (b) of this AD at the

applicable schedule specified in that

paragraph, until the inspection required by

paragraph (d)(2)(ii)(A) has been

accomplished.

Note 4: For the purposes of this AD,

airplanes that are repaired in accordance

with Airbus Industrie Service Bulletin 300–

57–6017, Revision 1, are considered to be

subject to repetitive inspections at the same

interval as those airplanes on which Airbus

Industrie Modification 07716 has been

accomplished.

(i) If no cracking is detected, install the

second oversize bolt in accordance with the

service bulletin.

(ii) If any cracking is detected, repair in

accordance with a method approved by the

Manager, International Branch, ANM–116,

FAA, Transport Airplane Directorate.

(2) For airplanes on which Airbus Industrie

Modification 07716 has been accomplished:

Repair in accordance with a method

approved by the Manager, International

Branch, ANM–116. After repair, repeat the

inspections as required by paragraph (b) of

this AD at the applicable schedule specified

in that paragraph, until the inspection

required by paragraph (d)(2)(ii)(B) has been

accomplished.

New Requirements of This AD

New Initial and Repetitive Inspections

(d) Perform an ultrasonic inspection to

detect cracks in certain bolt holes where the

MLG forward pick-up fitting and MLG rib 5

aft are attached to the rear spar, in

accordance with Airbus Industrie Service

Bulletin A300–57–6017, Revision 3, dated

November 19, 1997; at the time specified in

paragraph (d)(1) or (d)(2) of this AD, as

applicable.

Note 5: Inspections accomplished prior to

the effective date of this AD in accordance

with Airbus Industrie Service Bulletin A300–

57–6017, Revision 2, dated January 14, 1997,

are considered acceptable for compliance

with paragraph (d) of this AD.

(1) For airplanes not inspected prior to the

effective date of this AD in accordance with

Airbus Industrie Service Bulletin A300–57–

6017, dated November 22, 1993, or Revision

1 (includes Appendix 1), dated July 25, 1994:

Inspect at the time specified in paragraph

(d)(1)(i), (d)(1)(ii), or (d)(1)(iii) of this AD, as

applicable. Accomplishment of this

inspection terminates the requirements of

paragraph (a) of this AD.

(i) For airplanes that have accumulated

17,300 total landings or fewer as of the

effective date of this AD: Inspect prior to the

accumulation of 17,300 total landings, or

within 1,500 landings after the effective date

of this AD, whichever occurs later.

(ii) For airplanes that have accumulated

17,301 total landings or more but fewer than

19,300 total landings as of the effective date

of this AD: Inspect within 1,500 landings

after the effective date of this AD.

(iii) For airplanes that have accumulated

19,300 total landings or more as of the

effective date of this AD: Inspect within 750

landings after the effective date of this AD.

(2) For airplanes on which an HFEC

inspection was performed prior to the

effective date of this AD in accordance with

paragraph (a) of AD 95–20–02, or in

accordance with Airbus Industrie Service

Bulletin A300–57–6017, dated November 22,

1993: Inspect at the time specified in

paragraph (d)(2)(i) or (d)(2)(ii), as applicable.

(i) If no cracking was detected during any

HFEC inspection accomplished prior to the

effective date of this AD, and if Airbus
Federal Register / Vol. 64, No. 144 /Wednesday, July 28, 1999 /Rules and Regulations 40745

Industrie Modification 07716 has not been

accomplished: Inspect at the time specified

in paragraph (d)(2)(i)(A) or (d)(2)(i)(B) of this

AD, as applicable.

(A) For airplanes having MSN 465 through

553 inclusive: Inspect within 13,000 landings

after the most recent HFEC inspection, and

thereafter at intervals not to exceed 8,900

landings. Accomplishment of this inspection

constitutes terminating action for the

repetitive inspection requirement of

paragraph (b)(1)(i) of this AD.

(B) For airplanes having MSN 252 through

464 inclusive: Inspect within 8,400 landings

after the most recent HFEC inspection, and

thereafter at intervals not to exceed 5,500

landings. Accomplishment of this inspection

constitutes terminating action for the

repetitive inspection requirement of

paragraph (b)(1)(ii) of this AD.

(ii) If any cracking was detected during any

HFEC inspection performed prior to the

effective date of this AD, regardless of the

method of repair, or if Airbus Industrie

Modification 07716 has been accomplished:

Inspect at the time specified in paragraph

(d)(2)(ii)(A) or (d)(2)(ii)(B) of this AD, as

applicable.

(A) For airplanes having MSN 465 through

553 inclusive: Inspect within 11,800 landings

after the most recent HFEC inspection, and

thereafter at intervals not to exceed 8,200

landings. Accomplishment of this inspection

constitutes terminating action for the

repetitive inspection requirement of

paragraph (c)(1) or (c)(2) of this AD, as

applicable.

(B) For airplanes having MSN 252 through

464 inclusive: Inspect within 10,700 landings

after the initial inspection in accordance with

paragraph (a) of AD 95–20–02, or within

7,500 landings after the most recent HFEC

inspection, whichever occurs later, and

thereafter at intervals not to exceed 4,900

landings. Accomplishment of this inspection

constitutes terminating action for the

repetitive inspection requirement of

paragraph (c)(1) or (c)(2) of this AD, as

applicable.

(e) If no cracking is detected during the

ultrasonic inspection required by paragraph

(d)(1) of this AD, repeat that inspection

thereafter at the time specified in paragraph

(e)(1) or (e)(2) of this AD, as applicable.

(1) For airplanes having MSN 465 through

553 inclusive: Repeat the inspection at

intervals not to exceed 8,900 landings.

(2) For airplanes having MSN 232 through

464 inclusive: Repeat the inspection at

intervals not to exceed 5,500 landings.

Repair

(f) If any cracking is detected during any

inspection performed in accordance with

paragraph (d) or (e) of this AD: Prior to

further flight, repair in accordance with a

method approved by the Manager,

International Branch, ANM–116; or the

Direction Ge ́ne ́rale de l’Aviation Civile (or its

delegated agent).

Terminating Action

(g) Accomplishment of Airbus Industrie

Modification 11440 (Airbus Industrie Service

Bulletin A300–57–6073, dated September 30,

1997) constitutes terminating action for the

repetitive inspection requirements of

paragraphs (d) and (e) of this AD, as

applicable.

Alternative Methods of Compliance

(h) 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 6: Information concerning the

existence of approved alternative methods of

compliance with this AD, if any, may be

obtained from the International Branch,

ANM–116.

Special Flight Permits

(i) 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.

Incorporation by Reference

(j) Except as provided by paragraphs

(c)(1)(ii), (c)(2), (f), and (g) of this AD, the

actions shall be done in accordance with

Airbus Industrie Service Bulletin A300–57-

6017, Revision 1 (includes Appendix 1),

dated July 25, 1994, and Airbus Industrie

Service Bulletin A300–57–6017, Revision 3,

dated November 19, 1997. The incorporation

by reference of Airbus Industrie Service

Bulletin A300–57–6017, Revision 3, dated

November 19, 1997 is approved by the

Director of the Federal Register in accordance

with 5 U.S.C. 552(a) and 1 CFR part 51. The

incorporation by reference of Airbus

Industrie Service Bulletin A300–57–6017,

Revision 1 (includes Appendix 1), dated July

25, 1994, was approved previously by the

Director of the Federal Register as of

November 9, 1995 (60 FR 52618, October 10,

1995). 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 7: The subject of this AD is addressed

in French airworthiness directive 94–031–

155(B)R1, dated May 7, 1997.

(k) This amendment becomes effective on

September 1, 1999.

Issued in Renton, Washington, on July 21,

1999.

D. L. Riggin,

Acting Manager, Transport Airplane

Directorate, Aircraft Certification Service.

[FR Doc. 99–19155 Filed 7–27–99; 8:45 am]

BILLING CODE 4910–13–P

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 71

[Airspace Docket No. 99–AWP–8]

Correction of Class D Airspace,

Bullhead City, AZ

AGENCY: Federal Aviation

Administration (FAA), DOT.

ACTION: Direct final rule; request for

comments.

SUMMARY: This action will correct the

Class D airspace ceiling at Laughlin/

Bullhead International Airport,

Bullhead City, AZ.

EFFECTIVE DATE: 0901 UTC September 9,

1999. Comment date: Comments for

inclusion in the Rules Docket must be

received on or before August 27, 1999.

ADDRESSES: Send comments on the

direct final rule in triplicate to: Federal

Aviation Administration, Attn:

Manager, Airspace Branch, AWP–520,

Docket No. 99–AWP–8, Air Traffic

Division, P.O. Box 92007, Worldway

Postal Center, Los Angeles, California

90009.

The official docket may be examined

in the Office of the Assistant Chief

Counsel, Western-Pacific Region,

Federal Aviation Administration, Room

6007, 15000 Aviation Boulevard,

Lawndale, California 90261.

An informal docket may also be

examined during normal business hours

at the Office of the Manager, Airspace

Branch, Air Traffic Division at the above

address.

FOR FURTHER INFORMATION CONTACT:

Larry Tonish, Air Traffic Division,

Airspace Specialist, AWP–520.1,

Western-Pacific Region, Federal

Aviation Administration, 15000

Aviation Boulevard, Lawndale,

California 90261, telephone (310) 725–

6539.

SUPPLEMENTARY INFORMATION: The

intended effect of this action is to

correct the Class D airspace area ceiling

associated with Laughlin/Bullhead

International Airport. On January 4,

1996, the Class D airspace ceiling of

Laughlin/Bullhead International Airport

was published and chartered in error as

2,500 feet Above Ground Level (AGL).

FAA Order 7400.9F requires all

altitudes to be published in feet above

Mean Sea Level (MSL). The corrected

altitude of 3200 feet MSL will not

change the boundaries or volume of

Class D airspace area associated with

Laughlin/Bullhead International Airport

but will only correct the ceiling of

existing Class D airspace area from an