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.

Federal Register / Vol. 65, No. 99 / Monday, May 22, 2000 / Rules and Regulations 32019

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.

The FAA estimates that 60 helicopters

will be affected by this AD, that it will

take approximately 0.25 work hour to

accomplish the inspection and that the

average labor rate is $60 per work hour.

Based on these figures and assuming 10

windows are affected at $10 each for the

seal and 1 hour to reinstall each

window, the total cost impact of the AD

on U.S. operators is estimated to be

$1,600.

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 should 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 mailed

comments submitted in response to this

rule must submit a self-addressed,

stamped postcard on which the

following statement is made:

‘‘Comments to Docket No. 99–SW–86–

AD.’’ The postcard will be date stamped

and returned to the commenter.

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.

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, 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:

AD 2000–10–13 Eurocopter France:

Amendment 39–11737. Docket No. 99–

SW–86–AD.

Applicability: Model SA–365N, SA–365N1,

AS–365N2, and AS–365N3 helicopters, with

enlarged sliding doors, part number (P/N)

365A82–1142–0051, 0054, 0153, or 0154,

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 (b) 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 10 hours

time-in-service (TIS), unless accomplished

previously.

To prevent loss of a window panel, impact

with a main rotor blade, and subsequent loss

of control of the helicopter, accomplish the

following:

(a) Visually inspect each window panel in

any enlarged sliding door (door) for correct

positioning on the inside of the door. See

Figure 1.

(1) If the window panel is installed on the

inside of the door, no further action is

required by this AD.

(2) If a window is installed on the outside,

before further flight, remove the window and

reinstall using a new seal.

Note 2: The following optional procedure

may be used to remove and reinstall a

window, however, any procedure that results

in the installation of a properly sealed

airworthy window panel on the inside of the

door is acceptable:

a. From inside the door, cut the seal (see

Figure 1, item 3). Push the window out and

remove remnants of the seal from the

window panel and door structure.

b. Remove all traces of the sealing

compound (see Figure 1, item 4) with methyl

ethyl ketone (MEK), acetone, or equivalent.

c. Thoroughly dust the grooves of a new

seal with talcum powder.

d. Fit the new seal to the window panel.

The joint will be located in the lower center

of the window panel. The clearance between

the seal and the window panel should not

exceed 0.04 inch.

e. Insert a 0.01-inch diameter cord (ripcord

works well) into the seal slot. Position the

cord such that the cord ends are on the top

center of the panel).

f. Press the window panel and seal

assembly against the door from the inside.

g. Gently pull outward on the cord ends,

allowing the outer edge of the seal to pull

over the door structure. Continue pulling

cord around the window panel until

complete.

h. Apply PR1222 sealant between the seal

and the door structure. Wipe off any excess

sealant.

Note 3: Eurocopter Telex No. 00097, dated

November 9, 1999, pertains to this AD.

BILLING CODE 4910–13–U

32020 Federal Register / Vol. 65, No. 99 / Monday, May 22, 2000 / Rules and Regulations

BILLING CODE 4910–13–C

Federal Register / Vol. 65, No. 99 / Monday, May 22, 2000 / Rules and Regulations 32021

(b) 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 4: Information concerning the

existence of approved alternative methods of

compliance with this AD, if any, may be

obtained from the Regulations Group.

(c) 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.

(d) This amendment becomes effective on

June 6, 2000.

Note 5: The subject of this AD is addressed

in The Direction Generale De L’Aviation

Civile (France) AD 1999–459–049(A), dated

December 1, 1999.

Issued in Fort Worth, Texas, on May 15,

2000.

Henry A. Armstrong,

Manager, Rotorcraft Directorate, Aircraft

Certification Service.

[FR Doc. 00–12817 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–43–AD; Amendment

39–11738; AD 2000–10–14]

RIN 2120–AA64

Airworthiness Directives; Bell

Helicopter Textron Canada (BHTC)

Model 222, 222B, 222U, and 230

Helicopters

AGENCY: Federal Aviation

Administration, DOT.

ACTION: Final rule.

SUMMARY: This amendment adopts a

new airworthiness directive (AD) for

BHTC Model 222, 222B, 222U, and 230

helicopters that requires inspecting each

flapping bearing to yoke attachment bolt

(bolt) and replacing each bolt that shows

thread damage, shank wear, or corrosion

pitting with an airworthy bolt. This

amendment is prompted by the

discovery of a fractured bolt during a

post-flight inspection. The actions

specified by this AD are intended to

prevent a fracture of a bolt, failure of the

bearing and yoke interface, and

subsequent loss of control of the

helicopter.

EFFECTIVE DATE: June 26, 2000.

FOR FURTHER INFORMATION CONTACT:

Sharon Miles, Aviation Safety Engineer,

FAA, Rotorcraft Directorate, Rotorcraft

Standards Staff, Fort Worth, Texas

76193–0111, telephone (817) 222–5122,

fax (817) 222–5961.

SUPPLEMENTARY INFORMATION: A

proposal to amend part 39 of the Federal

Aviation Regulations (14 CFR part 39) to

include an AD for BHTC Model 222,

222B, 222U, and 230 helicopters was

published in the Federal Register on

March 1, 2000 (65 FR 11006). That

action proposed to require inspecting

the bolts and replacing each bolt that

shows thread damage, shank wear, or

corrosion with an airworthy bolt.

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 101

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. Required parts

will cost approximately $20 per bolt.

Based on these figures, the total cost

impact of the AD on U.S. operators is

estimated to be $20,200.

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 FAA, Office of the

Regional Counsel, Southwest Region,

2601 Meacham Blvd., Room 663, Fort

Worth, Texas.

List of Subjects in 14 CFR Part 39

Air transportation, Aircraft, Aviation

safety, 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:

AD 2000–10–14 Bell Helicopter Textron

Canada: Amendment 39–11738. Docket

No. 99–SW–43–AD.

Applicability: Model 222 helicopters, serial

number (S/N) 47006 through 47089; Model

222B helicopters, S/N 47131 through 47156;

Model 222U helicopters, S/N 47501 through

47574; and Model 230 helicopters, S/N 23001

through 23038 inclusive, 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 (b) 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 150 hours

time-in-service, unless accomplished

previously.

To prevent the fracture of a flapping

bearing to yoke attachment bolt (bolt), failure

of the bearing and yoke interface, and

subsequent loss of control of the helicopter,

accomplish the following:

(a) Remove one bolt at a time and inspect

each bolt located as shown in Figure 1.

Note 2: For main rotor hubs installed on

rotorcraft, the bolts may be removed,

inspected, and installed one at a time.

Note 3: Bell Helicopter Textron Canada

Alert Service Bulletins 230–98–15, 222–98–

83, and 222U–98–54, all dated October 12,

1998, pertain to the subject of this AD.

(i) Clean each bolt with a cloth dampened

with methyl ethyl ketone, RHO SOLV756,

Desoto 110, or equivalent.