37272 Federal Register / Vol. 65, No. 115 / Wednesday, June 14, 2000 / Rules and Regulations

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:

2000–12–03 Eurocopter France:

Amendment 39–11781. Docket No. 99–

SW–82–AD.

Applicability: Model AS332L2 helicopters,

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 (d) 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 within 50 hours

time-in-service (TIS) or within 50 hours TIS

after accumulating 1,000 hours TIS on the

transmission flexible mounting plate (plate),

whichever occurs last, unless accomplished

previously.

To prevent cracking of the plate slats,

increased helicopter vibration, loss of

transmission mounting integrity, and

subsequent loss of control of the helicopter,

accomplish the following:

(a) Inspect for interference between the

plate, part number (P/N) 332A38–0106–00,

the forward shim, P/N 332A22307420, and

the aft shim (shim), P/N 332A22307020, in

accordance with paragraph 2.B.1 of the

Accomplishment Instructions in Eurocopter

AS 332 Service Bulletin No. 05.00.54, dated

July 8, 1999 (SB). If interference is found,

replace the shims and repair the plate in

accordance with paragraph 2.B.3 of the

Accomplishment Instructions in the SB

before further flight.

(b) Visually inspect the plate for a broken

slat. If a broken slat is found, replace the

plate and the shims with an airworthy plate

and shims in accordance with paragraph

2.B.3 of the SB before further flight. Replace

the plate with an airworthy plate if slat

damage beyond repair limits is found.

(c) Install Eurocopter France MOD 0725946

and Eurocopter France MOD 0726012 at the

next major inspection or when the

transmission is next removed, whichever

occurs first. Installation of both MOD’s is

considered a terminating action for the

requirements of this AD.

(d) 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, Regulations

Group, Rotorcraft Directorate, FAA.

Operators shall submit their requests through

a FAA Principal Maintenance Inspector, who

may concur or comment and then send it to

the Manager, Regulations Group.

Note 2: Information concerning the

existence of approved alternative methods of

compliance with this AD, if any, may be

obtained from the Regulations Group.

(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 helicopter

to a location where the requirements of this

AD can be accomplished.

(f) The inspections and modification shall

be done in accordance with paragraph 2.B.1

and 2.B.3 of the Accomplishment

Instructions in Eurocopter AS 332 Service

Bulletin No. 05.00.54, dated July 8, 1999.

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 American Eurocopter Corporation, 2701

Forum Drive, Grand Prairie, Texas 75053–

4005, telephone (972) 641–3460, fax (972)

641–3527. 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.

(g) This amendment becomes effective on

July 19, 2000.

Note 3: The subject of this AD is addressed

in Direction Generale De L’Aviation Civile

(France) AD No. 1999–329–015(A), dated

August 11, 1999.

Issued in Fort Worth, Texas, on June 5,

2000.

Eric Bries,

Acting Manager, Rotorcraft Directorate,

Aircraft Certification Service.

[FR Doc. 00–14790 Filed 6–13–00; 8:45 am]

BILLING CODE 4910–13–P

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 99–NM–95–AD; Amendment

39–11782; AD 2000–12–04]

RIN 2120–AA64

Airworthiness Directives; Airbus Model

A319, A320, and A321 Series Airplanes

AGENCY: Federal Aviation

Administration, DOT.

ACTION: Final rule.

SUMMARY: This amendment supersedes

an existing airworthiness directive (AD),

applicable to certain Airbus Model

A320 series airplanes, that currently

requires an initial inspection of fastener

holes on certain outer frames of the

fuselage to detect fatigue cracking, and

modification of the area by cold

expanding the holes and installing

oversized fasteners. This amendment

requires revising the applicability to

include additional airplanes; a high

frequency eddy current inspection to

detect fatigue cracking in the frames and

frame feet at fuselage frames FR37

through FR41; and follow-on actions.

This amendment also provides for an

optional terminating action for the

follow-on repetitive inspections. 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 fatigue cracking of the fuselage

frames and frame feet, and consequent

reduced structural integrity of the

fuselage.

DATES: Effective July 19, 2000.

The incorporation by reference of

certain publications listed in the

regulations is approved by the Director

of the Federal Register as of July 19,

2000.

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

Federal Register / Vol. 65, No. 115 / Wednesday, June 14, 2000 / Rules and Regulations 37273

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 97–11–01,

amendment 39–10030 (62 FR 28324,

May 23, 1997), which is applicable to

certain Airbus Model A320 series

airplanes, was published in the Federal

Register on April 5, 2000 (65 FR 17824).

The action proposed to require an HFEC

inspection to detect fatigue cracking in

the frames and frame feet of left and

right fuselage frames FR37 through

FR41; and follow-on actions. The action

proposed to revise the applicability to

include additional airplanes. The action

also proposed to allow for an optional

terminating action for the follow-on

repetitive inspections.

Comments Received

Interested persons have been afforded

an opportunity to participate in the

making of this amendment. Due

consideration has been given to the

comments received.

Support for the Proposal

One commenter concurs with the

content of the proposed AD. Another

commenter is not affected by the

proposed AD and thus has no objection

to its issuance.

Request To Allow Flight With Known

Cracks

One commenter, an operator, requests

that the proposed AD be revised to

allow continued service with cracks of

the frame footing or frame segment for

500 flight cycles, as allowed in Airbus

Service Bulletin A320–53–1141,

Revision 01, dated October 4, 1999. The

commenter states that the proposed AD

does not allow such relief, and this

added restriction may impact its

operations.

The FAA does not concur. It is the

FAA’s policy to require repair of known

cracks prior to further flight (the FAA

may make exceptions to this policy in

certain cases of unusual need). This

policy is based on the fact that such

damaged airplanes do not conform to

the FAA certificated type design and,

therefore, are not airworthy until a

properly approved repair is

incorporated. While the FAA recognizes

that repair deferrals may be necessary at

times, the FAA policy is intended to

minimize adverse human factors

relating to the lack of reliability of longterm repetitive inspections, which may

reduce the safety of the type certificated

design if such repair deferrals are

practiced routinely. Exceptions may be

made to this policy in certain cases, if

there is an unusual need for a temporary

deferral, such as legitimate difficulty in

acquiring parts to accomplish repairs.

However, since the FAA is not aware of

any unusual need for repair deferral in

regard to this AD, no change is made to

the final rule.

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 as proposed.

Cost Impact

There are approximately 198

airplanes of U.S. registry that will be

affected by this AD.

The new HFEC inspection that is

required by this new AD will take

approximately 2 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

requirements of this AD on U.S.

operators is estimated to be $23,760, or

$120 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.

Should an operator elect to

accomplish the optional terminating

action rather than continue the

repetitive inspections, it would take

between 297 and 316 work hours per

airplane to accomplish the inspection

and modification, at an average labor

rate of $60 per work hour. Required

parts would cost between $40 and

$5,290 per airplane. Based on these

figures, the cost impact of this optional

terminating action is estimated to be

between $17,860 and $24,250 per

airplane.

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

removing amendment 39–10030 (62 FR

28324, May 23, 1997), and by adding a

new airworthiness directive (AD),

amendment 39–11782, to read as

follows:

2000–12–04 Airbus Industrie: Amendment

39–11782. Docket 99–NM–95–AD.

Supersedes AD 97–11–01, Amendment

39–10030.

Applicability: Model A319, A320, and

A321 series airplanes, certificated in any

category; except those on which Airbus

Modification 25896, 25592, or 25593, or

Airbus Service Bulletin A320–53–1128,

Revision 01, dated October 4, 1999, has been

accomplished.

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 (g) 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 fatigue cracking of the fuselage

frames and frame feet, and consequent

reduced structural integrity of the fuselage,

accomplish the following:

37274 Federal Register / Vol. 65, No. 115 / Wednesday, June 14, 2000 / Rules and Regulations

Inspection

(a) Perform a high frequency eddy current

(HFEC) inspection to detect fatigue cracks in

the frames and frame feet at fuselage frames

FR37 through FR41, adjacent to stringer 23,

at the time specified in paragraph (a)(1),

(a)(2), or (a)(3), as applicable; in accordance

with Airbus Service Bulletin A320–53–1141,

Revision 01, dated October 4, 1999.

(1) For Configuration 01 airplanes, as

identified in Airbus Service Bulletin A320–

53–1141: Within 3,500 flight cycles after the

effective date of this AD.

(2) For Configuration 02 airplanes, as

identified in Airbus Service Bulletin A320–

53–1141: Within 16,000 flight cycles after

accomplishment of Airbus Service Bulletin

A320–53–1025, Revision 1, dated November

24, 1994, or within 3,500 flight cycles after

the effective date of this AD, whichever

occurs later.

(3) For Configurations 03, 04, and 05

airplanes, as identified in Airbus Service

Bulletin A320–53–1141: Prior to the

accumulation of 20,000 total flight cycles, or

within 3,500 flight cycles after the effective

date of this AD, whichever occurs later.

Repetitive Inspections or Corrective

Action(s)

(b) For Configuration 01 airplanes: If no

crack is detected during the HFEC inspection

required by paragraph (a) of this AD,

accomplish the action specified in either

paragraph (b)(1) or (b)(2) of this AD.

(1) Repeat the HFEC inspection required by

paragraph (a) of this AD thereafter at

intervals not to exceed 3,500 flight cycles

until accomplishment of paragraph (f) of this

AD. Or

(2) Prior to further flight, modify each

fastener hole of the outer frame flanges of left

and right fuselage frames FR37 through FR41,

adjacent to stringer 23, in accordance with

Airbus Service Bulletin A320–53–1141,

Revision 01, dated October 4, 1999. Within

16,000 flight cycles after accomplishment of

this modification, and thereafter at intervals

not to exceed 3,500 flight cycles, repeat the

HFEC inspection required by paragraph (a) of

this AD until accomplishment of paragraph

(f) of this AD.

Note 2: Airbus Service Bulletin A320–53–

1141, Revision 01, dated October 4, 1999,

references Airbus Service Bulletin A320–53–

1025, Revision 1, dated November 24, 1994,

as an additional source of information for

accomplishing the modification required by

paragraph (b)(2) of this AD.

Note 3: Accomplishment of the

modification in accordance with Airbus

Service Bulletin A320–53–1125, dated

August 5, 1994, prior to the effective date of

this AD, is considered acceptable for

compliance with the modification

requirements of paragraph (b)(2) of this AD.

(c) For Configurations 02, 03, 04, and 05

airplanes: If no crack is detected during the

inspection required by paragraph (a) of this

AD, repeat the HFEC inspection required by

paragraph (a) of this AD thereafter at

intervals not to exceed 3,500 flight cycles

until accomplishment of paragraph (f) of this

AD.

(d) If any crack less than 0.20 inches (5.0

mm) in length is detected during any HFEC

inspection required by this AD, prior to

further flight, accomplish the actions

specified in either paragraph (d)(1) or (d)(2)

of this AD.

(1) Repair in accordance with Airbus

Service Bulletin A320–53–1141, Revision 01,

dated October 4, 1999. Repeat the HFEC

inspection required by paragraph (a) of this

AD thereafter at intervals not to exceed 3,500

flight cycles. Or

(2) Accomplish the actions specified in

paragraph (f) of this AD.

(e) If any crack is 0.20 inches (5.0 mm) or

greater in length, or if more than one crack

per frame side is detected during any HFEC

inspection required by this AD, prior to

further flight, simultaneously accomplish the

actions specified in paragraphs (e)(1) and

(e)(2) of this AD.

(1) Replace the frame segment and/or frame

foot with a new frame segment or frame foot

in accordance with Airbus Service Bulletin

A320–53–1141, Revision 01, dated October 4,

1999. And

(2) Accomplish the actions specified in

paragraph (f) of this AD.

Optional Terminating Action

(f) Modification of the frames and frame

feet area at fuselage frames FR37 through

FR41 (including the rotating probe eddy

current inspection to detect cracks, fastener

hole repair, installation of doublers on each

frame, cold working of specified fastener

holes, installation of new fasteners in the

cold-worked holes, and installation of new

modified system brackets), as applicable, in

accordance with Airbus Service Bulletin

A320–53–1128, Revision 01, including

Appendix 01, dated October 4, 1999,

constitutes terminating action for the

requirements of this AD.

Note 4: Accomplishment of the

modification in accordance with Airbus

Service Bulletin A320–53–1128, including

Appendix 01, dated October 3, 1997, prior to

the effective date of this AD, is considered

acceptable for compliance with the

modification requirements of paragraph (f) of

this AD.

Alternative Methods of Compliance

(g) 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 5: 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

(h) 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

(i) The actions shall be done in accordance

with Airbus Service Bulletin A320–53–1141,

Revision 01, dated October 4, 1999. 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 6: The subject of this AD is addressed

in French airworthiness directive 98–509–

123(B), dated December 16, 1998.

(j) This amendment becomes effective on

July 19, 2000.

Issued in Renton, Washington, on June 6,

2000.

Donald L. Riggin,

Acting Manager, Transport Airplane

Directorate, Aircraft Certification Service.

[FR Doc. 00–14791 Filed 6–13–00; 8:45 am]

BILLING CODE 4910–13–P

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 2000–NM–06–AD; Amendment

39–11778; AD 2000–11–29]

RIN 2120–AA64

Airworthiness Directives; Fokker

Model F27 Mark 050, 100, 200, 300, 400,

500, 600, and 700 Series Airplanes; and

Model F28 Mark 0070, 0100, 1000, 2000,

3000, and 4000 Series Airplanes

AGENCY: Federal Aviation

Administration, DOT.

ACTION: Final rule.

SUMMARY: This amendment adopts a

new airworthiness directive (AD),

applicable to certain Fokker Model F27

Mark 050, 100, 200, 300, 400, 500, 600,

and 700 series airplanes, and Model F28

Mark 0070, 0100, 1000, 2000, 3000, and

4000 series airplanes, that requires a

one-time functional test to verify correct

installation of the shoulder harnesses of

the pilot’s and co-pilot’s seats and, if

necessary, replacement of the shoulder

harness assembly with a new or

serviceable shoulder harness assembly.

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

shoulder harness, which could result in

injury to the flight crew during