32016 Federal Register / Vol. 65, No. 99 / Monday, May 22, 2000 / Rules and Regulations

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:

AD 2000–10–09 Eurocopter France:

Amendment 39–11733. Docket No. 99–

SW–36–AD.

Applicability: Model AS350B, BA, B1, B2,

B3, D, and AS355E, F, F1, F2, and N

helicopters, with Crouzet single-pole circuit

breaker, part numbers (P/N) 84 400 028, and

P/N 84 400 031 through P/N 84 400 036,

installed as part of any optional installations,

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 loss of electrical power to the

emergency flotation gear or other optional

installations and subsequent loss of the

helicopter emergency flotation capability,

accomplish the following:

(a) On or before 200 hours time-in-service

or within the next 3 calendar months,

whichever occurs first:

(1) For Model AS350B, BA, B1, B2, B3, and

D helicopters, inspect and if inoperable,

replace the Crouzet single-pole circuit

breakers installed in the flotation gear unit

assembly and other optional installations for

electrical continuity in accordance with

section 2.B. of the Accomplishment

Instructions contained in Eurocopter France

Service Bulletin (SB) No. 01.00.47, dated

November 10, 1998, except disregard the

compliance times stated in paragraph 2.B.2)

of the SB.

(2) For Model AS355E, F, F1, F2, and N

helicopters, inspect and if inoperable, replace

the Crouzet single-pole circuit breakers

installed in the flotation gear unit assembly

and other optional installations for electrical

continuity in accordance with section 2.B. of

the Accomplishment Instructions contained

in SB No. 01.00.44, dated November 10,

1998, except disregard the compliance times

stated in paragraph 2.B.2) of the SB.

(b) On or before July 1, 2000, replace all

Crouzet single-pole circuit breakers in

accordance with section 2.B. of the

Accomplishment Instructions of the

applicable SB.

(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, Regulations

Group, Rotorcraft Directorate, FAA.

Operators shall submit their requests through

an 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.

(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 and modification shall

be done in accordance with section 2.B. of

the Accomplishment Instructions contained

in Eurocopter France Service Bulletin No.

01.00.44 or No. 01.00.47, both dated

November 10, 1998. 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.

(f) This amendment becomes effective on

June 26, 2000.

Note 3: The subject of this AD is addressed

in Direction Generale De L’Aviation Civile

(France) AD 98–510–055(A) for the Model AS

355 helicopters and AD 98–511–074(A) for

the Model AS 350 helicopters. Both DGAC

AD’s are dated December 16, 1998.

Issued in Fort Worth, Texas, on May 9,

2000.

Henry A. Armstrong,

Manager, Rotorcraft Directorate, Aircraft

Certification Service.

[FR Doc. 00–12352 Filed 5–19–00; 8:45 am]

BILLING CODE 4910–13–P

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 99–SW–39–AD; Amendment

39–11734; AD 2000–10–10]

RIN 2120–AA64

Airworthiness Directives; Eurocopter

France Model AS–350B, BA, B1, B2,

and D, and Model AS–355E, F, F1, F2,

and N Helicopters

AGENCY: Federal Aviation

Administration, DOT.

ACTION: Final rule.

SUMMARY: This amendment supersedes

an existing airworthiness directive (AD)

that applies to Eurocopter France Model

AS–350B, BA, B1, B2, and D, and Model

AS–355E, F, F1, F2, and N helicopters

and requires inspecting the main

gearbox suspension bi-directional crossbeam (cross-beam) for cracks, and

replacing the cross-beam if a crack is

found. This amendment requires the

same inspections as the existing AD, but

adds the time intervals for performing

repetitive dye-penetrant inspections on

cross-beams with 5,000 or more hours

time-in-service (TIS). This amendment

is prompted by the discovery that time

intervals for performing the required

dye-penetrant inspections are not

included in the existing AD. The actions

specified by this AD are intended to

prevent failure of the cross-beam that

could lead to rotation of the main

gearbox, resulting in severe vibrations

and a subsequent forced landing.

DATES: Effective June 26, 2000.

The incorporation by reference of

certain publications listed in the

regulations was previously approved by

the Director of the Federal Register as of

August 3, 1998 (63 FR 35128, June 29,

1998).

ADDRESSES: The service information

referenced in this AD may be obtained

from American Eurocopter Corporation,

2701 Forum Drive, Grand Prairie, Texas

75053–4005, telephone (972) 641–3460,

fax (972) 641–3527. 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

Federal Register / Vol. 65, No. 99 / Monday, May 22, 2000 / Rules and Regulations 32017

of the Federal Register, 800 North

Capitol Street, NW., suite 700,

Washington, DC.

FOR FURTHER INFORMATION CONTACT: Jim

Grigg, Aviation Safety Engineer, FAA,

Rotorcraft Directorate, ASW–111, 2601

Meacham Blvd., Fort Worth, Texas

76137, telephone (817) 222–5490, fax

(817) 222–5961.

SUPPLEMENTARY INFORMATION: A

proposal to amend part 39 of the Federal

Aviation Regulations (14 CFR part 39)

by superseding AD 98–14–01,

Amendment 39–10635 (63 FR 35128,

June 29, 1998), which applies to

Eurocopter France Model AS–350B, BA,

B1, B2, and D, and Model AS–355E, F,

F1, F2, and N helicopters, was

published in the Federal Register on

February 11, 2000 (65 FR 6927). That

action proposed to require, at specified

time intervals or cycles, repetitive visual

and dye-penetrant inspections of the

cross-beam for cracks and replacing, if

necessary, the cross-beam with an

airworthy cross-beam.

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 454

helicopters of U.S. registry will be

affected by this AD. It will take

approximately 0.5 work hour per

helicopter to accomplish each visual

inspection, with an estimated average of

150 visual inspections per helicopter; 3

work hours per helicopter to accomplish

a dye-penetrant inspection, with an

estimated average of 3 dye-penetrant

inspections per helicopter; and 6 work

hours per helicopter to replace the

cross-beam, if necessary. The average

labor rate is $60 per work hour. Parts

will cost approximately $6,000 per

cross-beam. Based on these figures, the

total cost impact of the AD on U.S.

operators is estimated to be $5,175,600

to perform 150 visual inspections and

an average of 3 dye-penetrant

inspections per helicopter and to

replace the cross-beam on all 454

helicopters.

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 39–10635 (63 FR

35128), and by adding a new

airworthiness directive (AD),

Amendment 39–11734, to read as

follows:

AD 2000–10–10 Eurocopter France:

Amendment 39–11734. Docket No. 99–

SW–39–AD. Supersedes AD 98–14–01,

Amendment 39–10635, Docket No. 97–

SW–25–AD.

Applicability: Model AS–350B, BA, B1, B2,

and D, and Model AS–355E, F, F1, F2, and

N helicopters, with main gearbox suspension

bi-directional cross-beam (cross-beam), part

number (P/N) 350A38–1018—all dash

numbers, installed, 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 (e) 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 failure of the cross-beam that

could lead to rotation of the main gearbox,

resulting in severe vibrations and a

subsequent forced landing, accomplish the

following:

(a) For cross-beams having 2,000 or more

hours time-in-service (TIS) or 10,000 or more

operating cycles, whichever occurs first:

Note 2: The Master Service

Recommendations and the flight log contain

accepted procedures that are used to

determine the cumulative operating cycles on

the rotorcraft.

(1) Within 30 hours TIS, and thereafter at

intervals not to exceed 30 hours TIS or 150

operating cycles, whichever occurs first,

visually inspect the cross-beam for cracks in

accordance with paragraph 2.B.1) of

Eurocopter France Service Bulletin No.

05.00.28, applicable to Model AS–350

helicopters, or Eurocopter France Service

Bulletin No. 05.00.29, applicable to Model

AS–355 helicopters, both dated May 26,

1997.

(2) If a crack is found, remove the crossbeam and replace it with an airworthy crossbeam.

(b) For cross-beams having 5,000 or more

hours TIS:

(1) In addition to continuing the repetitive

inspections of paragraph (a)(1), before further

flight, and thereafter at intervals not to

exceed 550 hours TIS or 2,750 operating

cycles, whichever occurs first, perform a dyepenetrant inspection in accordance with

paragraph 2.B.2) of Eurocopter France

Service Bulletin No. 05.00.28, applicable to

Model AS–350 helicopters, or Eurocopter

Service Bulletin No. 05.00.29, applicable to

Model AS–355 helicopters, both dated May

26, 1996.

(2) If a crack is found, remove the crossbeam and replace it with an airworthy crossbeam.

(c) Prior to installing any replacement

cross-beams, regardless of TIS or operating

cycles, inspect the replacement cross-beam in

accordance with paragraph (b)(1) of this AD.

(d) Modifying the helicopter in accordance

with paragraph 2.B of the Accomplishment

Instructions in Eurocopter Service Bulletin

No. 63.00.07, applicable to Model AS–350B,

BA, B1, B2, and D helicopters, or Eurocopter

Service Bulletin No. 63.00.13, applicable to

Model AS–355E, F, F1, F2, and N

helicopters, both dated April 7, 1997,

constitutes terminating action for the

requirements of this AD.

32018 Federal Register / Vol. 65, No. 99 / Monday, May 22, 2000 / Rules and Regulations

(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, Regulations

Group, Rotorcraft Directorate, FAA.

Operators shall submit their requests through

an FAA Principal Maintenance Inspector,

who may concur or comment and then send

it to the Manager, Regulations Group.

Note 3: Information concerning the

existence of approved alternative methods of

compliance with this AD, if any, may be

obtained from the Regulations Group.

(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 helicopter

to a location where the requirements of this

AD can be accomplished.

(g) The inspections and replacements, if

necessary, shall be done in accordance with

Eurocopter France Service Bulletin No.

05.00.28, applicable to Model AS–350

helicopters, and Eurocopter France Service

Bulletin No. 05.00.29, applicable to Model

AS–355 helicopters, both dated May 26,

1997. The incorporation by reference of those

documents was previously approved by the

Director of the Federal Register in accordance

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

August 3, 1998 (63 FR 35128, June 29, 1998).

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.

(h) This amendment becomes effective on

June 26, 2000.

Note 4: The subject of this AD is addressed

in Direction Generale De L’Aviation Civile

(France) AD 96–156–071(B)R1 and AD 96–

155–053(B)R1, both dated June 4, 1997.

Issued in Fort Worth, Texas, on May 11,

2000.

Eric Bries,

Acting Manager, Rotorcraft Directorate,

Aircraft Certification Service.

[FR Doc. 00–12575 Filed 5–19–00; 8:45 am]

BILLING CODE 4910–13–U

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 99–SW–86–AD; Amendment

39–11737; AD 2000–10–13]

RIN 2120–AA64

Airworthiness Directives; Eurocopter

France Model SA–365N, SA–365N1,

AS–365N2 and AS–365N3 Helicopters

AGENCY: Federal Aviation

Administration, DOT.

ACTION: Final rule; request for

comments.

SUMMARY: This amendment adopts a

new airworthiness directive (AD)

applicable to Eurocopter France Model

SA–365N, SA–365N1, AS–365N2 and

AS–365N3 helicopters. This action

requires inspecting the installation of

each window panel on the enlarged

sliding door (door). If any window panel

is installed on the outside of the door,

this AD requires installing and sealing

the window panel on the inside. This

amendment is prompted by the loss of

a window panel in flight that was

incorrectly sealed with the window

installed on the outside of the door.

This condition, if not corrected, could

result in loss of a window panel in

flight. The actions specified in this AD

are intended to prevent loss of a

window panel, impact with a main rotor

blade, and subsequent loss of control of

the helicopter.

DATES: Effective June 6. 2000.

Comments for inclusion in the Rules

Docket must be received on or before

July 21, 2000.

ADDRESSES: Submit comments in

triplicate to the Federal Aviation

Administration (FAA), Office of the

Regional Counsel, Southwest Region,

Attention: Rules Docket No. 99–SW–86–

AD, 2601 Meacham Blvd., Room 663,

Fort Worth, Texas 76137. You may also

send comments electronically to the

Rules Docket at the following address:

9-asw-adcomments@faa.gov.

FOR FURTHER INFORMATION CONTACT: Jim

Grigg, Aviation Safety Engineer, FAA,

Rotorcraft Directorate, Regulations

Group, Fort Worth, Texas 76193–0111,

telephone (817) 222–5490, fax (817)

222–5961.

SUPPLEMENTARY INFORMATION: The

Direction Generale De L’Aviation Civile

(DGAC), the airworthiness authority for

France, notified the FAA that an unsafe

condition may exist on Eurocopter

France Model SA–365N, SA–365N1,

AS–365N2 and AS–365N3 helicopters.

The DGAC advises of the need to

visually inspect each window for

correct mounting to prevent loss of a

window in flight, impact with a main

rotor blade, and subsequent loss of

control of the helicopter. Eurocopter France has issued Telex

Information No. 00097, dated November

9, 1999 (Telex). The Telex advises of the

loss of a window panel in flight due to

the window panel being sealed and

positioned on the outside of the door.

The Telex specifies visually inspecting

the installation of each window panel

and resuming flight if the window

panels are inside the door. If the

window panels are outside the door, the

Telex specifies repositioning and

resealing the window panels inside the

door. The DGAC classified this Telex as

mandatory and issued AD 1999–459–

049(A), dated December 1, 1999, to

ensure the continued airworthiness of

these helicopters in France.

These helicopter 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 these type designs that

are certificated for operation in the

United States.

Since an unsafe condition has been

identified that is likely to exist or

develop on other Eurocopter France

Model SA–365N, SA–365N1, AS–365N2

and AS–365N3 helicopters of the same

type designs registered in the United

States, this AD is being issued to

prevent loss of a window panel, impact

with a main rotor blade, and subsequent

loss of control of the helicopter. This

AD requires visually inspecting each

window panel for correct installation on

the door. If the window panel is

installed properly, no further action is

required by this AD. If any window

panel is installed outside the door, this

AD also requires, before further flight,

removing, installing inside the door,

and resealing the window panel. The

short compliance time involved is

required because the previously

described critical unsafe condition can

adversely affect the structural integrity

of the helicopter. Therefore, visually

inspecting each window panel for

correct installation on the door is

required within 10 hours time-in-service

and this AD must be issued

immediately.