Federal Register / Vol. 65, No. 233 / Monday, December 4, 2000 / Rules and Regulations 75601

Action Compliance time Procedures

(1) Inspect, using magnetic particle methods, the NLG

upper strut, part number 4.4173–1 (or FAA-approved

equivalent part number), for evidence of cracking

(cracks or crack beginnings).

Within the next 200 hours time-in-service

(TIS) after January 5, 2001 (the effective date of this AD).

Do this inspection in accordance with the

ACCOMPLISHMENT INSTRUCTIONS

section of Vulcanair Service Bulletiin

No. 98, dated July 31, 1999.

(2) If there is evidence of cracking, replace the NLG

upper strut with a new NLG upper strut, part number

4.4173–1 (or FAA-approved equivalent part number).

Prior to further flight after the inspection

where evidence of cracking is found.

Use the procedures in the maintenance

manual.

(3) Do not install any NLG upper strut, part number

4.4173–1, unless it is new from the factory, or has

been inspected as required in paragraph (d)(1) of this

AD and is found to not have any evidence of cracking.

As of January 5, 2001 (the effective date

of this AD).

Not Applicable.

(e) Can I comply with this AD in any other

way? You may use an alternative method of

compliance or adjust the compliance time if:

(1) Your alternative method of compliance

provides an equivalent level of safety; and

(2) The Manager, Small Airplane

Directorate, approves your alternative.

Submit your request through an FAA

Principal Maintenance Inspector, who may

add comments and then send it to the

Manager, Small Airplane Directorate.

Note 1: This AD applies to each airplane

identified in paragraph (a) of this AD,

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 you have not

eliminated the unsafe condition, specific

actions you propose to address it.

(f) Where can I get information about any

already-approved alternative methods of

compliance? Contact Roman Gabrys,

Aerospace Engineer, FAA, Small Airplane

Directorate, 901 Locust, Room 301, Kansas

City, Missouri 64106; telephone: (816) 329–

4141; facsimile: (816) 329–4090.

(g) What if I need to fly the airplane to

another location to comply with this AD? The

FAA can issue a special flight permit under

sections 21.197 and 21.199 of the Federal

Aviation Regulations (14 CFR 21.197 and

21.199) to operate your airplane to a location

where you can accomplish the requirements

of this AD.

(h) Are any service bulletins incorporated

into this AD by reference? Actions required

by this AD must be done in accordance with

Vulcanair Service Bulletin No. 98, dated July

31, 1999. The Director of the Federal Register

approved this incorporation by reference

under 5 U.S.C. 552(a) and 1 CFR part 51. You

can get copies from Vulcanair S.p.A., Via G.

Poscoli, 7, 80026 Casoria (Naples), Italy. You

can look at copies at the FAA, Central

Region, Office of the Regional Counsel, 901

Locust, Room 506, Kansas City, Missouri, or

at the Office of the Federal Register, 800

North Capitol Street, NW, suite 700,

Washington, DC.

(i) When does this amendment become

effective? This amendment becomes effective

on January 5, 2001.

Note 2: The subject of this AD is addressed

in Italian AD 2000–004, dated January 10,

2000.

Issued in Kansas City, Missouri, on

November 20, 2000.

Marvin R. Nuss,

Acting Manager, Small Airplane Directorate,

Aircraft Certification Service.

[FR Doc. 00–30317 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–112–AD; Amendment

39–12010; AD 2000–24–03]

RIN 2120–AA64

Airworthiness Directives; Dornier

Model 328–100 Series Airplanes

AGENCY: Federal Aviation

Administration, DOT.

ACTION: Final rule.

SUMMARY: This amendment supersedes

an existing airworthiness directive (AD),

applicable to all Dornier Model 328–100

series airplanes, that currently requires

revising the Airplane Flight Manual

(AFM) to provide the flightcrew with

additional information regarding

procedures to ensure complete

pressurization of the hydraulic lines for

the flaps. This amendment requires

revising the existing AFM revision to

include a flap system test to be

performed prior to the first flight of the

day. This amendment also requires, for

certain airplanes, modification of the

flap actuators of the flight controls. The

actions specified by this AD are

intended to prevent an uncommanded

retraction of the flaps during takeoff,

which could result in an aborted takeoff

and consequent potential for runway

overrun.

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

Dornier 328 All Operators Telefax AOT–

328–27–016, dated July 31, 1998, as

listed in the regulations, was approved

previously by the Director of the Federal

Register as of November 12, 1998 (63 FR

57244, October 27, 1998).

ADDRESSES: The service information

referenced in this AD may be obtained

from FAIRCHILD DORNIER, DORNIER

Luftfahrt GmbH, P.O. Box 1103, D–

82230 Wessling, Germany. 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 98–22–07,

amendment 39–10854 (63 FR 57244,

October 27, 1998), which is applicable

to all Dornier Model 328–100 series

airplanes, was published in the Federal

Register on August 29, 2000 (65 FR

52365). The action proposed to continue

to require revising the Airplane Flight

Manual (AFM) to provide the flightcrew

with additional information regarding

procedures to ensure complete

pressurization of the hydraulic lines for

the flaps. The action also proposed to

require revising the existing AFM

revision to include a flap system test to

be performed prior to the first flight of

the day. Additionally, the action

proposed to add a requirement, for

certain airplanes, for modification of the

flap actuators of the flight controls.

75602 Federal Register / Vol. 65, No. 233 / Monday, December 4, 2000 / Rules and Regulations

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 52 airplanes

of U.S. registry that will be affected by

this AD.

The AFM revision that is currently

required by AD 98–22–07, and retained

in this AD, takes 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 $3,120, or

$60 per airplane.

The new AFM revision that is

required by this AD will 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 required

AFM revision on U.S. operators is

estimated to be $3,120, or $60 per

airplane.

The new modification that is required

by this AD will take approximately 4

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 required modification

on U.S. operators is estimated to be

$240 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

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 39–10854 (63 FR

57244, October 27, 1998), and by adding

a new airworthiness directive (AD),

amendment 39–12010, to read as

follows:

2000–24–03 Dornier Luftfahrt GMBH:

Amendment 39–12010. Docket 2000–

NM–112–AD. Supersedes AD 98–22–07,

Amendment 39–10854.

Applicability: All Model 328–100 series

airplanes, 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 (d)(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 an uncommanded retraction of

the flaps during takeoff, which could result

in an aborted takeoff and consequent

potential for runway overrun, accomplish the

following:

Restatement of Requirements of AD 98–22–

07

Airplane Flight Manual (AFM) Revision

(a) Within 14 days after November 12, 1998

(the effective date of AD 98–22–07,

amendment 39–10854), accomplish the

requirements of paragraphs (a)(1) and (a)(2)

of this AD.

(1) Revise the Normal Procedures Section

of the Dornier 328 FAA-approved AFM to

include the information specified in pages 6

and 7 of Dornier 328 All Operators Telefax

(AOT) AOT–328–27–016, dated July 31,

1998. This may be accomplished by inserting

a copy of pages 6 and 7 of the AOT into the

AFM.

(2) Revise the Abnormal Procedures

Section of the Dornier 328 FAA-approved

AFM to include the information specified in

page 4 of Dornier 328 AOT–328–27–016,

dated July 31, 1998. This may be

accomplished by inserting a copy of page 4

of the AOT into the AFM.

New Requirements of This AD

New AFM Revision

(b) For all airplanes: Within 3 days after

the effective date of this AD, revise the

Dornier 328 FAA-approved AFM as specified

in paragraphs (b)(1) and (b)(2) of this AD.

Concurrent with this AFM revision, remove

the AFM revisions required by paragraph (a)

of this AD from the AFM.

(1) Revise the Normal Procedures Section

to include the information specified in pages

4, 5, and 6 of Dornier 328 AOT–328–27–016,

Revision 1, dated October 28, 1998. This may

be accomplished by inserting a copy of pages

4, 5, and 6 of the AOT into the AFM.

(2) Revise the Abnormal Procedures

Section to include the information specified

in page 3 of Dornier 328 AOT–328–27–016,

Revision 1, dated October 28, 1998. This may

be accomplished by inserting a copy of page

3 of the AOT into the AFM.

Modification

(c) For airplanes with serial numbers 3005

through 3099 inclusive, 3101 through 3108

inclusive, and 3110 through 3119 inclusive:

Within 5 months after the effective date of

this AD, modify the flap actuators of the

flight controls, in accordance with Dornier

328 Service Bulletin SB–328–27–293, dated

November 10, 1999.

Note 2: The Dornier service bulletin

references Liebherr Aerospace Service

Bulletin 1048A–27–02, dated November 9,

1999, as an additional source of service

information for accomplishing the

modification of the flap actuators of the flight

controls.

Alternative Methods of Compliance

(d)(1) An alternative method of compliance

or adjustment of the compliance time that

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