39074 Federal Register / Vol. 65, No. 122 / Friday, June 23, 2000 / Rules and Regulations

interval specified in paragraph 2.D. of the

Accomplishment Instructions of Airbus

Industrie Service Bulletin A300–54–6011,

Revision 1, dated October 15, 1993.

New Requirements of This AD

Model A310 Series Airplanes

(c) For Model A310–221, –222, –322, –324,

and –325 series airplanes: Perform an

internal eddy current inspection to detect

cracks in the lower spar axis of the pylon

between ribs 9 and 10, in accordance with

Airbus Industrie Service Bulletin A310–54–

2016, dated November 12, 1991; or Revision

1, dated October 15, 1993; or Revision 02,

dated June 11, 1999; at the time specified in

paragraph (d) of this AD.

(1) If no crack is found, repeat the

inspection thereafter at intervals not to

exceed 2,500 landings.

(2) If any crack is found that is less than

or equal to 30 mm: Perform subsequent

inspections and repair in accordance with

the methods and times specified in the

service bulletin.

(3) If any crack is found that is greater than

30 mm, but less than 100 mm: Prior to the

accumulation of 250 landings after crack

discovery, repair in accordance with a

method approved by the Manager,

International Branch, ANM–116; or the

DGAC (or its delegated agent).

(4) If any crack is found that is greater than

or equal to 100 mm: Prior to further flight,

repair in accordance with a method approved

by the Manager, International Branch, ANM–

116; or the DGAC (or its delegated agent).

(5) Accomplishment of the modification

specified in Airbus Industrie Service Bulletin

A310–54–2022, dated October 15, 1993; or

Revision 01, dated March 16, 1999; increases

the threshold and repetitive interval of the

inspections required by paragraph (c) of this

AD to the threshold and interval specified in

paragraph 2.D. of the Accomplishment

Instructions of Airbus Industrie Service

Bulletin A310–54–2016, Revision 02, dated

June 11, 1999.

(d) Perform the initial inspection required

by paragraph (c) of this AD at the earlier of

the times specified by paragraphs (d)(1) and

(d)(2) of this AD.

(1) Prior to the accumulation of 25,000

total landings, or within 500 landings after

June 12, 1995, whichever occurs later.

(2) At the applicable time specified by

paragraph (d)(2)(i), (d)(2)(ii), or (d)(2)(iii) of

this AD.

(i) For airplanes that have accumulated

fewer than 10,000 landings as of the effective

date of this AD: Perform the inspection prior

to the accumulation of 3,800 total landings,

or within 1,500 landings after the effective

date of this AD, whichever occurs later.

(ii) For airplanes that have accumulated

10,000 total landings or more, but fewer than

20,000 total landings, as of the effective date

of this AD: Perform the inspection within

1,000 landings after the effective date of this

AD.

(iii) For airplanes that have accumulated

20,000 total landings or more as of the

effective date of this AD: Perform the

inspection within 500 landings after the

effective date of this AD.

Alternative Methods of Compliance

(e) 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.

Special Flight Permits

(f) 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.

Incorporation by Reference

(g) Except as provided by paragraphs (a)(3),

(a)(4), (b)(3), (b)(4), (c)(3), and (c)(4) of this

AD, the actions shall be done in accordance

with the following Airbus Industrie service

bulletins, as applicable.

Airbus Industrie Service

Bulletin No.

Revision

Level

Service Bulletin

Date

A300–54–071 ......................................................................... Original .................................................................................. November 12, 1991.

A300–54–071 ......................................................................... 1 ............................................................................................ October 15, 1993.

A300–54–0079 ....................................................................... Original .................................................................................. October 15, 1993.

A300–54–6011 ....................................................................... Original .................................................................................. November 12, 1991.

Change Notice O.A. A300–54–6011 ..................................... Original .................................................................................. July 10, 1992.

A300–54–6011 ....................................................................... 1 ............................................................................................ October 15, 1993.

A300–54–6019 ....................................................................... Original .................................................................................. October 15, 1993.

A310–54–2016 ....................................................................... Original .................................................................................. November 12, 1991.

A310–54–2016 ....................................................................... 1 ............................................................................................ October 15, 1993.

A310–54–2022 ....................................................................... Original .................................................................................. October 15, 1993.

A310–54–2022 ....................................................................... 01 .......................................................................................... March 16, 1999.

A310–54–2016 ....................................................................... 02 .......................................................................................... June 11, 1999.

(1) The incorporation by reference of

Airbus Industrie Service Bulletin

A310–54–2016, Revision 02, dated June 11,

1999; and A310–54–2022, Revision 1, dated

March 16, 1999, is approved by the Director

of the Federal Register in accordance with 5

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

(2) The incorporation by reference of the

remaining Airbus Industrie publications was

approved previously by the Director of the

Federal Register as of June 12, 1995 (60 FR

25604, May 12, 1995).

(3) 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 1999–237–

285(B), dated June 2, 1999.

(h) This amendment becomes effective on

July 28, 2000.

Issued in Renton, Washington, on June 9,

2000.

Donald L. Riggin,

Acting Manager, Transport Airplane

Directorate, Aircraft Certification Service.

[FR Doc. 00–15185 Filed 6–22–00; 8:45 am]

BILLING CODE 4910–13–U

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 99–SW–37–AD; Amendment

39–11787; AD 2000–12–09]

RIN 2120–AA64

Airworthiness Directives; Sikorsky

Aircraft Corporation (Sikorsky) Model

S–76A Helicopters

AGENCY: Federal Aviation

Administration, DOT.

ACTION: Final rule.

SUMMARY: This amendment adopts a

new airworthiness directive (AD) for

Federal Register / Vol. 65, No. 122 / Friday, June 23, 2000 / Rules and Regulations 39075

Sikorsky Model S–76A helicopters. This

AD requires inspecting the air

conditioning system at specified

intervals until installing a soft-start

assembly retrofit kit to prevent a

continuous flow of current through the

soft-start resistor. This amendment is

prompted by a report of overheating of

the soft-start assembly. The actions

specified by this AD are intended to

prevent overheating of the air

conditioning soft-start assembly,

damage in the lower tailcone, an

electrical fire, and subsequent loss of

control of the helicopter.

DATES: Effective July 28, 2000.

The incorporation by reference of

certain publications listed in the

regulations is approved by the Director

of the Federal Register as of July 28,

2000.

ADDRESSES: The service information

referenced in this AD may be obtained

from Sikorsky Aircraft Corporation,

Attn: Manager, Commercial Tech

Support, 6900 Main Street, P. O. Box

9729, Stratford, Connecticut 06497–

9129, phone (203) 386–7860, fax (203)

386–4703. This information may be

examined at the FAA, Office of the

Regional Counsel, Southwest Region,

2601 Meacham Blvd., Room 663, Fort

Worth, Texas; or at the Office of the

Federal Register, 800 North Capitol

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

FOR FURTHER INFORMATION CONTACT:

Terry Fahr, Aviation Safety Engineer,

Boston Aircraft Certification Office, 12

New England Executive Park,

Burlington, MA 01803, telephone (781)

238–7155, fax (781) 238–7199.

SUPPLEMENTARY INFORMATION: A

proposal to amend part 39 of the Federal

Aviation Regulations (14 CFR part 39) to

include an AD for Sikorsky Model S–

76A helicopters was published in the

Federal Register on March 22, 2000 (65

FR 15280). That action proposed to

require inspecting the soft-start

assembly at intervals not to exceed 25

hours time-in-service until installing a

soft-start assembly retrofit kit on the

Aero Aire Air Conditioning System in

120 calendar days to prevent a

continuous flow of current through the

soft-start resistor.

Interested persons have been afforded

an opportunity to participate in the

making of this amendment. No

comments were received on the

proposal or the FAA’s determination of

the cost to the public. The FAA has

determined that air safety and the

public interest require the adoption of

the rule as proposed.

The FAA estimates that 9 helicopters

of U.S. registry will be affected by this

AD, that it will take approximately 3

work hours per helicopter to accomplish

the required actions, and that the

average labor rate is $60 per work hour.

Aero Aire Service Bulletin No. 97002

states that the retrofit kit will be

provided at no charge. Based on these

figures, the total cost impact of the AD

on U.S. operators is estimated to be

$1,620.

The regulations adopted herein will

not have a substantial direct effect 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, it is

determined that this final rule does not

have federalism implications under

Executive Order 13132.

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 a new airworthiness directive to

read as follows:

2000–12–09 Sikorsky Aircraft Corporation:

Amendment 39–11787. Docket No. 99–

SW–37–AD.

Applicability: Model S–76A helicopters

with Aero Aire Air Conditioning System, part

number (P/N) S–76A–1–2, modified in

accordance with Supplemental Type

Certificate SH4680SW, certificated in any

category.

Note 1: This AD applies to each helicopter

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 helicopters 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 overheating of the air

conditioning soft-start control assembly,

damage in the lower tailcone, a fire, and

subsequent loss of control of the helicopter,

accomplish the following:

(a) Within 25 hours time-in-service (TIS)

and thereafter at intervals not to exceed 25

hours TIS, inspect the soft-start control

assembly in accordance with the

Accomplishment Instruction, Section III, of

Aero Aire Corporation Service Bulletin No.

970001, Revision A, dated September 18,

1997, except neither contact nor return of the

soft-start controller unit is required.

(b) Within 120 calendar days, install a soft

start assembly retrofit kit (kit), P/N 76SB001,

in accordance with the Accomplishment

Instructions, Section III, of Aero Aire

Corporation Service Bulletin 970002, dated

December 18, 1997. Installing the kit is

terminating action for the requirements of

this AD.

(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, Boston

Aircraft Certification Office, FAA. Operators

shall submit their requests through an FAA

Principal Maintenance Inspector, who may

concur or comment and then send it to the

Manager, Boston Aircraft Certification Office.

Note 2: Information concerning the

existence of approved alternative methods of

compliance with this AD, if any, may be

obtained from the Boston Aircraft

Certification Office.

(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 helicopter

to a location where the requirements of this

AD can be accomplished.

(e) The inspection shall be done in

accordance with the Accomplishment

Instruction, Section III, of Aero Aire

Corporation Service Bulletin No. 970001,

Revision A, dated September 18, 1997. The

modification shall be done in accordance

with the Accomplishment Instructions,

Section III, of Aero Aire Corporation Service

Bulletin 970002, dated December 18, 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 Sikorsky Aircraft Corporation, Attn:

Manager, Commercial Tech Support, 6900

39076 Federal Register / Vol. 65, No. 122 / Friday, June 23, 2000 / Rules and Regulations

Main Street, P. O. Box 9729, Stratford,

Connecticut 06497–9129, phone (203) 386–

7860, fax (203) 386–4703. Copies may be

inspected at the FAA, Office of the Regional

Counsel, Southwest Region, 2601 Meacham

Blvd., Room 663, Fort Worth, Texas; or at the

Office of the Federal Register, 800 North

Capitol Street, NW., suite 700, Washington,

DC.

(f) This amendment becomes effective on

July 28, 2000.

Issued in Fort Worth, Texas, on June 8,

2000.

Larry M. Kelly,

Acting Manager, Rotorcraft Directorate,

Aircraft Certification Service.

[FR Doc. 00–15309 Filed 6–22–00; 8:45 am]

BILLING CODE 4910–13–U

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 99–NM–330–AD; Amendment

39–11797; AD 2000–12–19]

RIN 2120–AA64

Airworthiness Directives; Boeing

Model 747 Series Airplanes

AGENCY: Federal Aviation

Administration, DOT.

ACTION: Final rule.

SUMMARY: This amendment adopts a

new airworthiness directive (AD),

applicable to certain Boeing Model 747

series airplanes, that requires repetitive

inspections of the aft pressure bulkhead

to detect cracking, and repair, if

necessary. This amendment is prompted

by a report of fatigue cracking found in

the upper half of the aft pressure

bulkhead. The actions specified by this

AD are intended to detect and correct

cracking in the aft pressure bulkhead,

which could result in rapid

decompression of the fuselage or

overpressurization of the tail section.

DATES: Effective July 28, 2000.

The incorporation by reference of

certain publications listed in the

regulations is approved by the Director

of the Federal Register as of July 28,

2000.

ADDRESSES: The service information

referenced in this AD may be obtained

from Boeing Commercial Airplane

Group, P.O. Box 3707, Seattle,

Washington 98124–2207. 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: Rick

Kawaguchi, Aerospace Engineer,

Airframe Branch, ANM–120S, FAA,

Transport Airplane Directorate, Seattle

Aircraft Certification Office, 1601 Lind

Avenue, SW., Renton, Washington

98055–4056; telephone (425) 227–1153;

fax (425) 227–1181.

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 Boeing

Model 747 series airplanes was

published in the Federal Register on

February 2, 2000 (65 FR 4900). That

action proposed to require repetitive

inspections of the aft pressure bulkhead

to detect cracking, and repair, if

necessary.

Comments

Interested persons have been afforded

an opportunity to participate in the

making of this amendment. Due

consideration has been given to the

single comment received.

The commenter supports the

proposed rule.

Conclusion

After careful review of the available

data, including the comment noted

above, the FAA has determined that air

safety and the public interest require the

adoption of the rule as proposed.

Cost Impact

There are approximately 552

airplanes of the affected design in the

worldwide fleet. The FAA estimates that

84 airplanes of U.S. registry will be

affected by this AD.

It will take approximately 7 work

hours per airplane to accomplish the

required detailed visual inspection, at

the average labor rate of $60 per work

hour. Based on these figures, the cost

impact of the required detailed visual

inspection on U.S. operators is

estimated to be $35,280, or $420 per

airplane, per inspection cycle.

It will take approximately 7 work

hours per airplane to accomplish the

required HFEC inspections, at the

average labor rate of $60 per work hour.

Based on these figures, the cost impact

of the required HFEC inspections on

U.S. operators is estimated to be

$35,280, or $420 per airplane, per

inspection cycle.

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 a substantial direct effect 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, it is

determined that this final rule does not

have federalism implications under

Executive Order 13132.

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:

2000–12–19 Boeing: Amendment 39–11797.

Docket 99–NM–330–AD.

Applicability: Model 747 series airplanes,

as listed in Boeing Alert Service Bulletin

747–53A2425, dated October 29, 1998;

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