Federal Register / Vol. 65, No. 233 / Monday, December 4, 2000 / Rules and Regulations 75599

Actions Compliance times Procedures

(2) If a misrouting has

been recorded or found

during this inspection, install replacement rudder

control cables in accordance with the following:

(i) Apply corrosion preventive compounds, as necessary, to provide corrosion protection.

(ii) Install rudder control cables

(iii) Adjust rudder control

cables to correct tension

and adjust control surface

travel.

(iv) Perform an operational

checkout of the flight control system to ensure

proper operation of installed rudder control cables, pulley brackets,

guard pins and attaching

hardware.

Before further flight after the inspection. Accomplish this action in accordance with the ACCOMPLISHMENT INSTRUCTIONS paragraph of

Raytheon Mandatory Service Bulletin SB 27–3265,

Issued: January 2000, and the applicable airplane

Maintenance Manual or Shop Manual.

(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, Wichita Aircraft

Certification Office (ACO), approves your

alternative. Submit your request through an

FAA Principal Maintenance Inspector, who

may add comments and then send it to the

Manager, Wichita ACO.

Note: 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 Paul C. DeVore,

Aerospace Engineer, Wichita Aircraft

Certification Office, FAA, 1801 Airport Road,

Mid-Continent Airport, Wichita, Kansas

67209; telephone: (316) 946–4142; facsimile:

(316) 946–4407.

(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

Raytheon Mandatory Service Bulletin SB 27–

3265, Issued: January 2000. 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

Raytheon Aircraft Company, P.O. Box 85,

Wichita, KS 67201–0085; or on the Internet

at http://www.raytheon.com/rac/servinfo/27–

3265.pdf. This file is in Adobe Portable

Document Format. The Acrobat Reader is

available at http://www.adobe.com/>. 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.

Issued in Kansas City, Missouri, on

November 20, 2000.

Marvin R. Nuss,

Acting Manager, Small Airplane Directorate,

Aircraft Certification Service.

[FR Doc. 00–30318 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–CE–16–AD; Amendment

39–12012; AD 2000–24–05]

RIN 2120–AA64

Airworthiness Directives; Vulcanair

S.p.A. Models P 68 ‘‘OBSERVER’’, P68

‘‘OBSERVER 2’’, and P68TC

‘‘OBSERVER’’ Airplanes

AGENCY: Federal Aviation

Administration, DOT.

ACTION: Final rule.

SUMMARY: This amendment adopts a

new airworthiness directive (AD) that

applies to certain Vulcanair S.p.A.

(Vulcanair) Models P 68 ‘‘OBSERVER’’,

P68 ‘‘OBSERVER 2’’, and P68TC

‘‘OBSERVER’’ airplanes. This AD

requires you to inspect the nose landing

gear (NLG) upper strut for evidence of

cracking (cracks or crack beginnings),

and replace the NLG upper strut if you

find evidence of cracking. This AD is

the result of mandatory continuing

airworthiness information (MCAI)

issued by the airworthiness authority for

Italy. The actions specified by this AD

are intended to prevent failure of the

NLG upper strut caused by cracking in

the area of the seeger retaining ring

groove, which could result in loss of

control of the airplane.

DATES: This AD becomes effective on

January 5, 2001.

The Director of the Federal Register

approved the incorporation by reference

of certain publications listed in the

regulations as of January 5, 2001.

ADDRESSES: You may get the service

information referenced in this AD from

Vulcanair S.p.A., Via G. Poscoli, 7,

80026 Casoria (Naples), Italy; telephone:

+39–081–5918111; facsimile: +39–081–

5918172. You may examine this

information at the Federal Aviation

Administration (FAA), Central Region,

Office of the Regional Counsel,

Attention: Rules Docket No. 2000–CE–

16–AD, 901 Locust, Room 506, Kansas

City, Missouri 64106; or at the Office of

the Federal Register, 800 North Capitol

Street, NW, suite 700, Washington, DC.

75600 Federal Register / Vol. 65, No. 233 / Monday, December 4, 2000 / Rules and Regulations

FOR FURTHER INFORMATION 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.

SUPPLEMENTARY INFORMATION:

Discussion

What events have caused this AD?

The Ente Nazionale per l’Aviazione

Civile (ENAC), which is the

airworthiness authority for Italy,

recently notified FAA that an unsafe

condition may exist on certain

Vulcanair Models P 68 ‘‘OBSERVER’’,

P68 ‘‘OBSERVER 2’’, and P68TC

‘‘OBSERVER’’ airplanes. The ENAC

reports three instances of cracking of the

nose landing gear (NLG) upper strut,

part number 4.4173–1, in the area of the

seeger retaining ring groove.

Investigation of these instances reveals

a work defect found during surface

finishing within the groove. The groove

is then susceptible to cracks after a hard

landing.

What are the consequences if the

condition is not corrected? Such

cracking, if not detected and corrected,

could result in failure of the NLG upper

strut, which could result in loss of

control of the airplane.

Has FAA taken any action to this

point? We issued a proposal to amend

part 39 of the Federal Aviation

Regulations (14 CFR part 39) to include

an AD that would apply to certain

Vulcanair Models P 68 ‘‘OBSERVER’’,

P68 ‘‘OBSERVER 2’’, and P68TC

‘‘OBSERVER’’ airplanes. This proposal

was published in the Federal Register

as a notice of proposed rulemaking

(NPRM) on September 22, 2000 (65 FR

57296). The NPRM proposed to require

you to inspect the NLG upper strut for

evidence of cracking (cracks or crack

beginnings), and replace the NLG upper

strut if you find evidence of cracking.

Was the public invited to comment?

Interested persons were afforded an

opportunity to participate in the making

of this amendment. No comments were

received on the proposed rule or the

FAA’s determination of the cost to the

public.

The FAA’s Determination

What is FAA’s final determination on

this issue? After careful review of all

available information related to the

subject presented above, we have

determined that air safety and the

public interest require the adoption of

the rule as proposed except for minor

editorial corrections. We determined

that these minor corrections:

—will not change the meaning of the

AD; and

—will not add any additional burden

upon the public than was already

proposed.

Cost Impact

How many airplanes does this AD

impact? We estimate that this AD affects

15 airplanes in the U.S. registry.

What is the cost impact of this AD on

owners/operators of the affected

airplanes? We estimate the following

costs to accomplish the inspection:

Labor cost Parts cost Total cost per airplane Total cost on U.S.

airplane operators

10 workhours × $60 per hour =

$600.

No parts required for the inspection.$600 per airplane ......................... $600 × 15 = $9,000.

We estimate the following costs to accomplish any necessary replacements that will be required based on the results

of the inspection. We have no way of determining the number of airplanes that may need such replacement:

Labor cost Parts cost Total cost per airplane

10 workhours × $60 per hour = $600 ............... $600 per airplane. ............................................ $1,200 per airplane

Regulatory Impact

Does this AD impact various entities?

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.

Does this AD involve a significant rule

or regulatory action? 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 copy of the final

evaluation prepared for this action is

contained in the Rules Docket. A copy

of it may be obtained by contacting 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, under 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. FAA amends § 39.13 by adding a

new AD to read as follows:

2000–24–05 Vulcanair S.P.A. (Partenavia

Costruzioni Aeronauticas S.p.A

previously held Type Certificate A31EU):

Amendment 39–12012; Docket No.

2000–CE–16–AD.

(a) What airplanes are affected by this AD?

This AD affects Models P 68 ‘‘OBSERVER’’,

P68 ‘‘OBSERVER 2’’, and P68TC

‘‘OBSERVER’’ airplanes, all serial numbers

up to and including 400, that are certificated

in any category.

(b) Who must comply with this AD?

Anyone who wishes to operate any of the

above airplanes must comply with this AD.

(c) What problem does this AD address?

The actions specified by this AD are intended

to prevent failure of the nose landing gear

(NLG) upper strut caused by cracking in the

area of the seeger retaining ring groove,

which could result in loss of control of the

airplane.

(d) What actions must I accomplish to

address this problem? To address this

problem, you must accomplish the following:

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.