68072 Federal Register / Vol. 65, No. 220 / Tuesday, November 14, 2000 / Rules and Regulations

Compliance: Required as indicated, unless

accomplished previously.

To prevent fatigue cracking of a blade,

failure of a blade, and subsequent loss of

control of the helicopter, accomplish the

following:

(a) Within 30 hours time-in-service (TIS),

and thereafter at intervals not to exceed 15

hours TIS for blades equipped with deicing

systems or 30 hours TIS for blades without

deicing systems, conduct skin bonding and

eddy current inspections on each affected

blade for skin bonding and a crack. Inspect

in accordance with paragraph 1.C of

Aerospatiale Service Bulletin 05.71R4, dated

December 18, 1990. Replace any blade failing

the skin bonding inspection or eddy current

inspection before further flight.

(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 2: 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) The inspection shall be done in

accordance with paragraph 1.C of

Aerospatiale Service Bulletin 05.71R4, dated

December 18, 1990. 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.

(e) This amendment becomes effective on

December 19, 2000.

Issued in Fort Worth, Texas, on October 30,

2000.

Mark R. Schilling,

Manager, Rotorcraft Directorate, Aircraft

Certification Service.

[FR Doc. 00–28722 Filed 11–13–00; 8:45 am]

BILLING CODE 4910–13–P

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 2000–NM–315–AD; Amendment

39–11972; AD 2000–23–02]

RIN 2120–AA64

Airworthiness Directives; Bombardier

Model CL–600–2B16 (CL–604) Series

Airplanes

AGENCY: Federal Aviation

Administration, DOT.

ACTION: Final rule; request for

comments.

SUMMARY: This amendment adopts a

new airworthiness directive (AD) that is

applicable to certain Bombardier Model

CL–600–2B16 (CL–604) series airplanes.

This action requires, among other

actions, a general visual inspection to

detect gaps between the vane bracket(s)

and the adjacent skin; corrective

actions, if necessary; and replacement of

the six flap vane actuator beams with

new beams. This action is necessary to

detect and correct corrosion of the

inboard flap actuator beam assembly

and gaps between the vane brackets and

adjacent skin, which could compromise

the structural integrity of the flap

systems and reduce the controllability

of the airplane in the event that a flap

vane actuator or a flap vane bracket fails

during flight. This action is intended to

address the identified unsafe condition.

DATES: Effective November 29, 2000.

The incorporation by reference of

certain publications listed in the

regulations is approved by the Director

of the Federal Register as of November

29, 2000.

Comments for inclusion in the Rules

Docket must be received on or before

December 14, 2000.

ADDRESSES: Submit comments in

triplicate to the Federal Aviation

Administration (FAA), Transport

Airplane Directorate, ANM–114,

Attention: Rules Docket No. 2000–NM–

315–AD, 1601 Lind Avenue, SW.,

Renton, Washington 98055–4056.

Comments may be inspected at this

location between 9:00 a.m. and 3:00

p.m., Monday through Friday, except

Federal holidays. Comments may be

submitted via fax to (425) 227–1232.

Comments may also be sent via the

Internet using the following address: 9-

anm-iarcomment@faa.gov. Comments

sent via the Internet must contain

‘‘Docket No. 2000–NM–315–AD’’ in the

subject line and need not be submitted

in triplicate. Comments sent via fax or

the Internet as attached electronic files

must be formatted in Microsoft Word 97

for Windows or ASCII text.

The service information referenced in

this AD may be obtained from

Bombardier, Inc., Canadair, Aerospace

Group, P.O. Box 6087, Station A,

Montreal, Quebec H3C 3G9, Canada.

This information may be examined at

the FAA, Transport Airplane

Directorate, 1601 Lind Avenue, SW.,

Renton, Washington; or at the FAA,

New York Aircraft Certification Office,

10 Fifth Street, Third Floor, Valley

Stream, New York; or at the Office of the

Federal Register, 800 North Capitol

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

FOR FURTHER INFORMATION CONTACT:

Serge Napoleon, Aerospace Engineer,

Airframe and Propulsion Branch, ANE–

171, FAA, New York Aircraft

Certification Office, 10 Fifth Street,

Third Floor, Valley Stream, New York;

telephone (516) 256–7512; fax (516)

568–2716.

SUPPLEMENTARY INFORMATION: Transport

Canada Civil Aviation (TCCA), which is

the airworthiness authority for Canada,

recently notified the FAA that an unsafe

condition may exist on certain

Bombardier Model CL–600–2B16 (CL–

604) series airplanes. TCCA advises that

it has received a report that, during a

visual inspection of the flap systems,

corrosion was found in the inboard flap

actuator beam assembly, part number

(P/N) 600–14250–25, as well as gaps

between the vane brackets, P/N’s 600–

14306–1 and –2, and adjacent skin. Both

of these discrepancies have been

attributed to deficiencies in the

manufacturing process. These

conditions, if not corrected, could

compromise the structural integrity of

the flap systems and could reduce the

controllability of the airplane in the

event that a flap vane actuator or a flap

vane bracket fails during flight.

Explanation of Relevant Service

Information

Bombardier has issued Alert Service

Bulletin A604–27–006, dated April 18,

2000. The service bulletin describes

procedures for a general visual

inspection to detect gaps between the

vane bracket(s) and the adjacent skin;

corrective actions, if necessary;

replacement of the six flap vane actuator

beams with new beams; and returning

certain parts to the airplane

manufacturer. The corrective actions

involve performing a non-destructive

inspection to detect cracks of the vane

brackets; replacing any cracked vane

bracket with a new vane bracket;

eliminating the gap by filling the gap

with liquid shim or installing a solid

shim, as applicable; and repairing the

Federal Register / Vol. 65, No. 220 / Tuesday, November 14, 2000 / Rules and Regulations 68073

gap. Accomplishment of the action

specified in the service bulletin is

intended to adequately address the

identified unsafe condition. The TCCA

classified this service bulletin as

mandatory and issued Canadian

airworthiness directive CF–2000–18,

dated July 11, 2000, in order to assure

the continued airworthiness of these

airplanes in Canada.

FAA’s Conclusions

This airplane model is manufactured

in Canada and is 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 TCCA has kept the FAA informed of

the situation described above. The FAA

has examined the findings of the TCCA,

reviewed all available information, and

determined that AD action is necessary

for products of this type design that are

certificated for operation in the United

States.

Explanation of Requirements of Rule

Since an unsafe condition has been

identified that is likely to exist or

develop on other airplanes of the same

type design registered in the United

States, this AD is being issued to detect

and correct corrosion of the inboard flap

actuator beam assembly and gaps

between the vane brackets and adjacent

skin, which could compromise the

structural integrity of the flap systems

and could reduce the controllability of

the airplane in the event that a flap vane

actuator or a flap vane bracket fails

during flight. This AD requires

accomplishment of the action specified

in the service bulletin described

previously, except as discussed below.

This AD also requires operators to

return certain parts and submit a data

report of those parts to the airplane

manufacturer. The FAA finds that these

actions are necessary to determine if

further rulemaking is needed.

Differences Between Proposed Rule and

Service Bulletin

Operators should note that, although

the service bulletin specifies that the

manufacturer may be contacted for

disposition of certain repair conditions,

this proposal would require the repair of

those conditions to be accomplished in

accordance with a method approved by

either the FAA, or the TCCA (or its

delegated agent). In light of the type of

repair that would be required to address

the identified unsafe condition, and in

consonance with existing bilateral

airworthiness agreements, the FAA has

determined that, for this proposed AD,

a repair approved by either the FAA or

the TCCA would be acceptable for

compliance with this proposed AD.

Interim Action

This is considered to be interim

action until final action is identified, at

which time the FAA may consider

further rulemaking.

Determination of Rule’s Effective Date

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.

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 shall 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.

Submit comments using the following

format:

• Organize comments issue-by-issue.

For example, discuss a request to

change the compliance time and a

request to change the service bulletin

reference as two separate issues.

• For each issue, state what specific

change to the AD is being requested.

• Include justification (e.g., reasons or

data) for each request.

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 comments

submitted in response to this rule must

submit a self-addressed, stamped

postcard on which the following

statement is made: ‘‘Comments to

Docket Number 2000–NM–315–AD.’’

The postcard will be date stamped and

returned to the commenter.

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.

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, 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:

2000–23–02 Bombardier Inc. (Formerly

Canadair): Amendment 39–11972.

Docket 2000–NM–315–AD.

68074 Federal Register / Vol. 65, No. 220 / Tuesday, November 14, 2000 / Rules and Regulations

Applicability: Model CL–600–2B16 (CL–

604) series airplanes, serial numbers 5301

through 5374 inclusive, 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

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 detect and correct corrosion of the

inboard flap actuator beam assembly and

gaps between the vane brackets and adjacent

skin, which could compromise the structural

integrity of the flap systems and reduce the

controllability of the airplane in the event

that a flap vane actuator or a flap vane

bracket fails during flight, accomplish the

following:

General Visual Inspection

(a) Do a general visual inspection to detect

gaps between the vane bracket(s), part

number (P/N) 600–14306–1 and –2, and the

adjacent skin, per paragraph ‘‘2.

Accomplishment Instructions,’’ of

Bombardier Alert Service Bulletin A604–27–

006, dated April 18, 2000; at the time

specified in paragraph (a)(1), (a)(2), or (a)(3)

of this AD, as applicable.

(1) For airplanes having serial numbers

5301 through 5334 inclusive: Within 30 days

after the effective date of this AD.

(2) For airplanes having serial numbers

5335 through 5354 inclusive: Within 90 days

after the effective date of this AD.

(3) For airplanes having serial numbers

5355 through 5374 inclusive: Within 180

days after the effective date of this AD.

Note 2: For the purposes of this AD, a

general visual inspection is defined as ‘‘A

visual examination of an interior or exterior

area, installation, or assembly to detect

obvious damage, failure, or irregularity. This

level of inspection is made under normally

available lighting conditions such as

daylight, hangar lighting, flashlight, or droplight, and may require removal or opening of

access panels or doors. Stands, ladders, or

platforms may be required to gain proximity

to the area being checked.’’

Corrective Actions if Any Gap Is Found

(b) If any gap is found during the general

visual inspection required by paragraph (a) of

this AD, before further flight, perform a nondestructive inspection to detect cracks of the

vane bracket, per paragraph ‘‘2.

Accomplishment Instructions,’’ of

Bombardier Alert Service Bulletin A604–27–

006, dated April 18, 2000.

(1) If any crack is detected, before further

flight, replace the cracked vane bracket with

a new vane bracket per the service bulletin.

(2) If no crack is detected and if the gap

is up to 0.100 inch (2.54 mm), eliminate the

gap by filling the gap with liquid shim or

installing a solid shim, as applicable, per the

service bulletin.

(3) If no crack is detected and if the gap

is more than 0.100 inch (2.54 mm), before

further flight, repair in accordance with a

method approved by the Manager, New York

Aircraft Certification Office (ACO), FAA; or

the Transport Canada Civil Aviation, (or its

delegated agent). For a repair method to be

approved by the Manager, New York ACO, as

required by this paragraph, the Manager’s

approval letter must specifically reference

this AD.

Replacement of Six Flap Vane Actuator

Beams

(c) Replace the six flap vane actuator

beams with new beams, per paragraph ‘‘2.

Accomplishment Instructions,’’ of

Bombardier Alert Service Bulletin A604–27–

006, dated April 18, 2000; at the time

specified in paragraph (a)(1), (a)(2), or (a)(3)

of this AD, as applicable.

(1) For airplanes having serial numbers

5301 through 5334 inclusive: Within 30 days

after the effective date of this AD.

(2) For airplanes having serial numbers

5335 through 5354 inclusive: Within 90 days

after the effective date of this AD.

(3) For airplanes having serial numbers

5355 through 5374 inclusive: Within 180

days after the effective date of this AD.

Return of Parts

(d) Within 30 days after doing the

replacement required by paragraph (c) of this

AD, forward any cracked vane bracket and

any two of the six removed flap vane actuator

assemblies to Bombardier, per paragraph ‘‘2.

Accomplishment Instructions,’’ of

Bombardier Alert Service Bulletin A604–27–

006, dated April 18, 2000. Data, such as the

station location of the flap actuator beam

assembly, the number of flight hours and

landings of the airplane at removal, must be

submitted along with the flap vane actuator

beam assemblies. Information collection

requirements contained in this regulation

have been approved by the Office of

Management and Budget (OMB) under the

provisions of the Paperwork Reduction Act of

1980 (44 U.S.C. 3501 et seq.) and have been

assigned OMB Control Number 2120–0056.

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, New York

ACO. Operators shall submit their requests

through an appropriate FAA Principal

Maintenance Inspector, who may add

comments and then send it to the Manager,

New York ACO.

Note 3: Information concerning the

existence of approved alternative methods of

compliance with this AD, if any, may be

obtained from the New York ACO.

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 in paragraph (b)(3)

of this AD, the actions shall be done in

accordance with Bombardier Alert Service

Bulletin A604–27–006, dated April 18, 2000.

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 Bombardier, Inc., Canadair, Aerospace

Group, P.O. Box 6087, Station A, Montreal,

Quebec H3C 3G9, Canada. Copies may be

inspected at the FAA, Transport Airplane

Directorate, 1601 Lind Avenue, SW., Renton,

Washington; or at the FAA, New York

Aircraft Certification Office, 10 Fifth Street,

Third Floor, Valley Stream, New York; or at

the Office of the Federal Register, 800 North

Capitol Street, NW., suite 700, Washington,

DC.

Note 4: The subject of this AD is addressed

in Canadian airworthiness directive CF–

2000–18, dated July 11, 2000.

Effective Date

(h) This amendment becomes effective on

November 29, 2000.

Issued in Renton, Washington, on

November 3, 2000.

Donald L. Riggin,

Acting Manager, Transport Airplane

Directorate, Aircraft Certification Service.

[FR Doc. 00–28830 Filed 11–13–00; 8:45 am]

BILLING CODE 4910–13–U

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 2000–NM–113–AD; Amendment

39–11975; AD 2000–23–05]

RIN 2120–AA64

Airworthiness Directives; British

Aerospace Model BAC 1–11 401/AK

and 410/AQ Airplanes

AGENCY: Federal Aviation

Administration, DOT.

ACTION: Final rule.

SUMMARY: This amendment adopts a

new airworthiness directive (AD),

applicable to all British Aerospace

Model BAC 1–11 401/AK and 410/AQ

airplanes, that requires replacement of

certain landing gear brake accumulators

with improved accumulators. The

actions specified by this AD are

intended to prevent loss of hydraulic

pressure and possible structural damage