Federal Register / Vol. 65, No. 233 / Monday, December 4, 2000 / Rules and Regulations 75603

provides an acceptable level of safety may be

used if approved by the Manager, 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.

(2) Alternative methods of compliance,

approved previously in accordance with AD

98–22–07, amendment 39–10854, are

approved as alternative methods of

compliance with paragraph (a) of this AD.

Note 3: Information concerning the

existence of approved alternative methods of

compliance with this AD, if any, may be

obtained from the Manager, International

Branch, ANM–116.

Special Flight Permits

(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 airplane to

a location where the requirements of this AD

can be accomplished.

Incorporation by Reference

(f) Except as provided by paragraph (b) of

this AD, the AFM revisions shall be done in

accordance with Dornier 328 All Operators

Telefax AOT–328–27–016, dated July 31,

1998; or Dornier 328 All Operators Telefax

AOT–328–27–016, Revision 1, dated October

28, 1998. The modification shall be done in

accordance with Dornier 328 Service Bulletin

SB–328–27–293, dated November 10, 1999.

(1) The incorporation by reference of

Dornier 328 All Operators Telefax AOT–328–

27–016, Revision 1, dated October 28, 1998;

and Dornier 328 Service Bulletin SB–328–

27–293, dated November 10, 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

Dornier 328 All Operators Telefax AOT–328–

27–016, dated July 31, 1998, was approved

previously by the Director of the Federal

Register as of November 12, 1998 (63 FR

57244, October 27, 1998).

(3) Copies may be obtained from

FAIRCHILD DORNIER, DORNIER Luftfahrt

GmbH, P.O. Box 1103, D–82230 Wessling,

Germany. 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 4: The subject of this AD is addressed

in German airworthiness directive 1998–359/

3, dated April 6, 2000.

Effective Date

(g) This amendment becomes effective on

January 8, 2001.

Issued in Renton, Washington, on

November 20, 2000.

Donald L. Riggin,

Acting Manager, Transport Airplane

Directorate, Aircraft Certification Service.

[FR Doc. 00–30120 Filed 12–1–00; 8:45 am]

BILLING CODE 4910–13–P

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 99–NM–381–AD; Amendment

39–12009; AD 2000–24–02]

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

A319, A320, and A321 series airplanes,

that currently requires repetitive

inspections to detect wear of the

inboard flap trunnions, and to detect

wear or debonding of the protective

half-shells; and corrective actions, if

necessary. This amendment requires

accomplishment of the previously

optional terminating action. 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 chafing and resultant wear

damage on the inboard flap drive

trunnions or on the protective halfshells, which could result in failure of

the trunnion primary load path; this

would adversely affect the fatigue life of

the secondary load path and could lead

to loss of the flap.

DATES: Effective January 8, 2001.

The incorporation by reference of

certain publications, as listed in the

regulations, is approved by the Director

of the Federal Register as of January 8,

2001.

The incorporation by reference of

certain other publications, as listed in

the regulations, was approved

previously by the Director of the Federal

Register as of September 27, 1999 (64 FR

45868, August 23, 1999).

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

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 99–17–11,

amendment 39–11259 (64 FR 45868,

August 23, 1999), which is applicable to

certain Airbus Model A319, A320, and

A321 series airplanes, was published in

the Federal Register on September 20,

2000 (65 FR 56814). The action

proposed to continue to require

repetitive inspections to detect wear of

the inboard flap trunnions, and to detect

wear or debonding of the protective

half-shells; and corrective actions, if

necessary. The action also proposed to

require accomplishment of the

previously optional terminating action.

Comments

Interested persons have been afforded

an opportunity to participate in the

making of this amendment. No

comments were submitted in response

to the proposal or the FAA’s

determination of the cost to the public.

Conclusion

The FAA has determined that air

safety and the public interest require the

adoption of the rule as proposed.

Cost Impact

There are approximately 132

airplanes of U.S. registry that will be

affected by this AD.

The actions that are currently

required by AD 99–17–11, and retained

in this AD, take approximately 1 work

hour per airplane to accomplish, at an

average labor rate of $60 per work hour.

Based on these figures, the cost impact

of the currently required actions on U.S.

operators is approximately $7,920, or

$60 per airplane, per inspection cycle.

The new actions that are required in

this AD will take approximately 14

work hours per airplane to accomplish,

at an average labor rate of $60 per work

hour. Required parts will be provided

by the manufacturer at no cost to the

operators. Based on these figures, the

cost impact of the new requirements of

this AD on U.S. operators is estimated

to be $110,880, or $840 per airplane.

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. The cost impact

figures discussed in AD rulemaking

actions represent only the time

necessary to perform the specific actions

75604 Federal Register / Vol. 65, No. 233 / Monday, December 4, 2000 / Rules and Regulations

actually required by the AD. These

figures typically do not include

incidental costs, such as the time

required to gain access and close up,

planning time, or time necessitated by

other administrative actions.

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 39–11259 (64 FR

45868, August 23, 1999), and by adding

a new airworthiness directive (AD),

amendment 39–12009, to read as

follows:

2000–24–02 Airbus Industrie: Amendment

39–12009. Docket 99–NM–381–AD.

Supersedes AD 99–17–11, Amendment

39–11259.

Applicability: Model A319, A320, and

A321 series airplanes; certificated in any

category; except airplanes on which Airbus

Modification 26495 (reference Airbus Service

Bulletin A320–27–1117) 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)(1) 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 chafing and resultant wear

damage on the inboard flap drive trunnions

or on the protective half-shells, which could

result in failure of the trunnion primary load

path, adversely affect the fatigue life of the

secondary load path, and lead to loss of the

flap, accomplish the following:

Restatement of Certain Requirements of AD

99–17–11

Inspections

(a) For airplanes on which a protective

half-shell has been installed over area 1 of

the left or right inboard flap trunnion:

Perform a detailed visual inspection of the

protective half-shell (area 1) to detect wear or

debonding, and perform a detailed visual

inspection of the trunnion (area 2) to detect

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

(a)(2), or (a)(3) of this AD, as applicable; in

accordance with Airbus Service Bulletin

A320–27–1108, Revision 01, dated July 15,

1997, Revision 02, dated April 17, 1998, or

Revision 03, dated June 25, 1999.

(1) For Model A319 and Model A320 series

airplanes on which Airbus Modification

22841 has been installed: Inspect prior to the

accumulation of 2,500 flight hours after the

incorporation of the modification, or within

500 flight hours after September 27, 1999 (the

effective date of AD 99–17–11, amendment

39–11259), whichever occurs later.

(2) For Model A321 series airplanes on

which Airbus Modification 23926 has been

installed, or on which the repair specified in

Airbus Service Bulletin A320–27–1097,

dated October 5, 1996, or Revision 01, dated

July 15, 1997, has been accomplished; and

for Model A320 series airplanes on which the

repair specified in Airbus Service Bulletin

A320–27–1066, Revision 3, dated October 30,

1996, or Revision 4, dated July 15, 1997, has

been accomplished: Inspect prior to the

accumulation of 5,000 flight hours after

incorporation of the repair or modification,

or within 500 flight hours after September 27,

1999, whichever occurs later.

(3) For Airbus Model A320 series airplanes

on which Airbus Modification 22881 (Airbus

Service Bulletin A320–27–1050) has been

accomplished, and on which Airbus

Modification 22841 has not been

accomplished: Inspect within 500 flight

hours after the effective date of this new AD.

Note 2: Paragraph (a)(3) of AD 99–17–11

has been revised to correct the description of

airplanes affected by that paragraph. Since

such a revision could result in additional

airplanes being affected, the compliance time

has been restarted from the effective date of

this AD to allow additional time to

accomplish the actions required by that

paragraph.

(b) For airplanes on which no protective

half-shell is installed over area 1 of the left

or right inboard flap trunnion: Within 500

flight hours after September 27, 1999,

perform a detailed visual inspection of areas

1 and 2 of the inboard flap trunnion to detect

wear on the trunnion, in accordance with

Airbus Service Bulletin A320–27–1066,

Revision 4, dated July 15, 1997 (for Model

A320 series airplanes); or A320–27–1097,

Revision 01, dated July 15, 1997, or Revision

02, dated June 25, 1999 (for Model A321

series airplanes).

Corrective Actions

(c) Except as provided by paragraph (d) of

this AD: Following the accomplishment of

any inspection required by either paragraph

(a) or (b) of this AD, perform the follow-on

repetitive inspections and/or corrective

actions, as applicable, in accordance with

Airbus Service Bulletin A320–27–1066,

Revision 4, dated July 15, 1997 (for Model

A320 series airplanes); A320–27–1097,

Revision 01, dated July 15, 1997, or Revision

02, dated June 25, 1999 (for Model A321

series airplanes); or A320–27–1108, Revision

01, dated July 15, 1997, Revision 02, dated

April 17, 1998, or Revision 03, dated June 25,

1999 (for Model A319, A320, and A321 series

airplanes); as applicable; at the compliance

times specified in the applicable service

bulletin.

(d) If the applicable service bulletin

specifies to contact Airbus for an appropriate

action, prior to further flight, repair in

accordance with a method approved by

either the Manager, International Branch,

ANM–116, FAA, Transport Airplane

Directorate, or the Direction Generale de

l’Aviation Civile (or its delegated agent).

New Requirements of this AD

Service Bulletin Revisions

(e) As of the effective date of this new AD,

the following service bulletin revisions must

be used for accomplishment of the applicable

actions required by paragraphs (a), (b), and

(c) of this AD:

(1) Airbus Service Bulletin A320–27–1108,

Revision 04, dated November 22, 1999.

(2) Airbus Service Bulletin A320–27–1066,

Revision 5, dated June 25, 1999.

Terminating Modification

(f) Within 18 months after the effective

date of this AD, modify the sliding panel

driving mechanism of the flap drive

trunnions, in accordance with Airbus Service

Bulletin A320–27–1117, Revision 02, dated

January 18, 2000. This modification

constitutes terminating action for the

repetitive inspections required by this AD.

Note 3: Accomplishment of the

modification required by paragraph (f) of this

Federal Register / Vol. 65, No. 233 / Monday, December 4, 2000 / Rules and Regulations 75605

AD prior to the effective date of this AD in

accordance with Airbus Service Bulletin

A320–27–1117, dated July 31, 1997, or

Revision 01, dated June 25, 1999, is

acceptable for compliance with that

paragraph.

Alternative Methods of Compliance

(g)(1) 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 requests through an appropriate

FAA Principal Maintenance Inspector, who

may add comments and then send it to the

Manager, International Branch, ANM–116.

(2) Alternative methods of compliance,

approved previously in accordance with AD

99–17–11, amendment 39–11259, are

approved as alternative methods of

compliance with this AD.

Note 4: 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) Except as required by paragraph (d) of

this AD, the actions shall be done in

accordance with Airbus Service Bulletin

A320–27–1108, Revision 01, dated July 15,

1997; Airbus Service Bulletin A320–27–1108,

Revision 02, dated April 17, 1998; Airbus

Service Bulletin A320–27–1108; Revision 03,

dated June 25, 1999; Airbus Service Bulletin

A320–27–1066, Revision 4, dated July 15,

1997; Airbus Service Bulletin A320–27–1097,

Revision 01, dated July 15, 1997; Airbus

Service Bulletin A320–27–1097, Revision 02,

dated June 25, 1999; Airbus Service Bulletin

A320–27–1108, Revision 04, dated November

22, 1999; Airbus Service Bulletin A320–27–

1066, Revision 5, dated June 25, 1999; and

Airbus Service Bulletin A320–27–1117,

Revision 02, dated January 18, 2000; as

applicable.

(1) The incorporation by reference of

Airbus Service Bulletin A320–27–1108,

Revision 04, dated November 22, 1999;

Airbus Service Bulletin A320–27–1066,

Revision 5, dated June 25, 1999; and Airbus

Service Bulletin A320–27–1117, Revision 02,

dated January 18, 2000, 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

Airbus Service Bulletin A320–27–1108,

Revision 01, dated July 15, 1997; Airbus

Service Bulletin A320–27–1108, Revision 02,

dated April 17, 1998; Airbus Service Bulletin

A320–27–1108; Revision 03, dated June 25,

1999; Airbus Service Bulletin A320–27–1066,

Revision 4, dated July 15, 1997; Airbus

Service Bulletin A320–27–1097, Revision 01,

dated July 15, 1997; and Airbus Service

Bulletin A320–27–1097, Revision 02, dated

June 25, 1999, was approved previously by

the Director of the Federal Register as of

September 27, 1999 (64 FR 45868, August 23,

1999).

(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 5: The subject of this AD is addressed

in French airworthiness directive 1996–271–

092(B) R3, dated August 11, 1999.

Effective Date

(j) This amendment becomes effective on

January 8, 2001.

Issued in Renton, Washington, on

November 20, 2000.

Donald L. Riggin,

Acting Manager, Transport Airplane

Directorate, Aircraft Certification Service.

[FR Doc. 00–30119 Filed 12–1–00; 8:45 am]

BILLING CODE 4910–13–P

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 2000–NM–368–AD; Amendment

39–12008; AD 2000–24–01]

RIN 2120–AA64

Airworthiness Directives; Bombardier

Model CL–600–1A11 (CL–600), CL–

600–2A12 (CL–601), and CL–600–2B16

(CL–601–3A, CL–601–3R, and 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–600–1A11 (CL–600), CL–600–2A12

(CL–601), and CL–600–2B16 (CL–601–

3A, CL–601–3R, and CL–604) series

airplanes. This action requires

installation of protection shields in the

wheel bay of the main landing gear

(MLG). This action is necessary to

prevent water, ice or slush

accumulation on the aileron quadrants

and/or control cable pulleys in the

wheel bay of the MLG during ground

roll. Such water, ice or slush

accumulation could subsequently freeze

during the climb to cruise altitude and

cause stiffness in the aileron controls,

which could result in reduced

controllability of the airplane. This

action is intended to address the

identified unsafe condition.

DATES: Effective December 19, 2000.

The incorporation by reference of

certain publications listed in the

regulations is approved by the Director

of the Federal Register as of December

19, 2000.

Comments for inclusion in the Rules

Docket must be received on or before

January 3, 2001.

ADDRESSES: Submit comments in

triplicate to the Federal Aviation

Administration (FAA), Transport

Airplane Directorate, ANM–114,

Attention: Rules Docket No. 2000–NM–

368–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–368–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 Centreville, 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

11581; or at the Office of the Federal

Register, 800 North Capitol Street, NW.,

suite 700, Washington, DC.

FOR FURTHER INFORMATION CONTACT: Dan

Parillo, Aerospace Engineer, Systems

and Flight Test Branch, ANE–172, FAA,

New York Aircraft Certification Office,

10 Fifth Street, Third Floor, Valley

Stream, New York; telephone (516) 256–

7505; fax (516) 568–2716.

SUPPLEMENTARY INFORMATION: Transport

Canada Civil Aviation, which is the

airworthiness authority for Canada,

notified the FAA that an unsafe

condition may exist on certain

Bombardier Model CL–600–1A11 (CL–

600), CL–600–2A12 (CL–601), and CL–

600–2B16 (CL–601–3A, CL–601–3R, and

CL–604) series airplanes. TCCA advises

that it has received several reports of

stiffness in the aileron controls

following takeoff from a wet or snow/

slush covered runway. The cause of the

stiffness has been attributed apparently

to water, ice or slush accumulation on