Federal Register / Vol. 65, No. 220 / Tuesday, November 14, 2000 / Rules and Regulations 68069

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 (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 as indicated, unless

accomplished previously.

To prevent failure of the outboard flap

idler hinge fitting due to fatigue cracking,

which could result in a deflected flap that

may cause an asymmetric lift and consequent

reduced controllability and structural

integrity of the airplane, accomplish the

following:

Measurement

(a) Before the accumulation of 24,000 total

landings, or within 90 days after the effective

date of this AD, whichever occurs later,

measure the diameter of the hole counterbore

of the outboard idler hinge fitting of the left

and right wing flap, per Boeing Alert Service

Bulletin DC9–57A218, including Appendix,

dated September 20, 2000.

Acceptable Measurement of 0.875 (7⁄8) Inch:

Installation of Certain Parts

(1) If the diameter of any hole counterbore

is 0.875 (7⁄8) inch, before further flight, install

a new nut, plain washer, and PLI washer, per

the service bulletin.

Unacceptable Measurement of 1.125 (11⁄8)

Inches: Repetitive Inspections and

Corrective Actions, If Necessary

(2) If the diameter of any hole counterbore

is 1.125 (11⁄8) inches, before further flight, do

a high frequency eddy current inspection

(HFEC) to detect cracks at the flap idler hinge

fitting, per the service bulletin.

(i) Condition 1. If no crack is detected,

before further flight, install a new nut, plain

washer, and PLI washer, per the service

bulletin. Repeat the HFEC inspection every

1,000 landings until the replacement

specified in paragraph (a)(2)(ii) has been

done.

(ii) Condition 2. If any crack is detected,

before further flight, replace the flap idler

hinge fitting with a new like part, per the

service bulletin. Within 24,000 landings after

accomplishment of the replacement, do the

HFEC inspection required by paragraph (a)(2)

of this AD.

Alternative Methods of Compliance

(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, Los

Angeles Aircraft Certification Office (ACO),

FAA. Operators shall submit their requests

through an appropriate FAA Principal

Maintenance Inspector, who may add

comments and then send it to the Manager,

Los Angeles ACO.

Note 2: Information concerning the

existence of approved alternative methods of

compliance with this AD, if any, may be

obtained from the Los Angeles ACO.

Special Flight Permits

(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 airplane to

a location where the requirements of this AD

can be accomplished.

Incorporation by Reference

(d) The actions shall be done in accordance

with Boeing Alert Service Bulletin DC9–

57A218, including Appendix, dated

September 20, 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 Boeing Commercial Aircraft

Group, Long Beach Division, 3855 Lakewood

Boulevard, Long Beach, California 90846,

Attention: Technical Publications Business

Administration, Dept. C1–L51 (2–60). Copies

may be inspected at the FAA, Transport

Airplane Directorate, 1601 Lind Avenue,

SW., Renton, Washington; or at the FAA, Los

Angeles Aircraft Certification Office, 3960

Paramount Boulevard, Lakewood, California;

or at the Office of the Federal Register, 800

North Capitol Street, NW., suite 700,

Washington, DC.

Effective Date

(e) This amendment becomes effective on

November 29, 2000.

Issued in Renton, Washington, on

November 1, 2000.

Donald L. Riggin,

Acting Manager, Transport Airplane

Directorate, Aircraft Certification Service.

[FR Doc. 00–28480 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–46–AD; Amendment

39–11970; AD 2000–22–22]

RIN 2120–AA64

Airworthiness Directives; Raytheon

Model Hawker 800XP and Hawker 800

(U–125A) Series Airplanes

AGENCY: Federal Aviation

Administration, DOT.

ACTION: Final rule.

SUMMARY: This amendment adopts a

new airworthiness directive (AD),

applicable to certain Raytheon Model

Hawker 800XP and Hawker 800 (U–

125A) series airplanes, that requires

inspection of the wire bundle to relay

‘‘KT’’ on panel ‘‘JA’’ for correct routing,

adequate clearance from the fuel crossfeed valve operating lever, and the

presence of chafing; this amendment

also requires corrective action, if

necessary. The actions specified by this

AD are intended to detect and correct

chafing of the wire bundle exiting panel

‘‘JA’’ due to insufficient clearance from

the fuel cross-feed valve operating lever.

Such chafing of the wire bundle could

result in a fire in the area of the fuel

system in a confined space. 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.

ADDRESSES: The service information

referenced in this AD may be obtained

from Raytheon Aircraft Company, 9709

East Central, Wichita, Kansas 67206.

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 FAA,

Wichita Aircraft Certification Office,

1801 Airport Road, Room 100, MidContinent Airport, Wichita, Kansas; or

at the Office of the Federal Register, 800

North Capitol Street, NW., suite 700,

Washington, DC.

FOR FURTHER INFORMATION CONTACT:

Philip Petty, Aerospace Engineer,

Systems and Propulsion Branch, ACE–

116W, FAA, Wichita Aircraft

Certification Office, 1801 Airport Road,

Room 100, Mid-Continent Airport,

Wichita, Kansas 67209; telephone (316)

946–4139; fax (316) 946–4407.

SUPPLEMENTARY INFORMATION: A

proposal to amend part 39 of the Federal

Aviation Regulations (14 CFR part 39) to

include an airworthiness directive (AD)

that is applicable to certain Model

Hawker 800XP and Hawker 800 (U–

125A) series airplanes was published in

the Federal Register on August 8, 2000

(65 FR 48404). That action proposed to

require inspection of the wire bundle to

relay ‘‘KT’’ on panel ‘‘JA’’ for correct

routing, adequate clearance from the

fuel cross-feed valve operating lever,

and the presence of chafing. That action

also proposed to require corrective

action, if necessary.

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.

68070 Federal Register / Vol. 65, No. 220 / Tuesday, November 14, 2000 / Rules and Regulations

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 148

airplanes of the affected design in the

worldwide fleet. The FAA estimates that

60 airplanes of U.S. registry will be

affected by this required AD, that it will

take approximately 1 work hour per

airplane to accomplish the required

inspection, and that the average labor

rate is $60 per work hour. Based on

these figures, the cost impact of the

inspection required by this AD on U.S.

operators is estimated to be $3,600, or

$60 per airplane.

No estimate is provided for the cost

impact of repairing the wire bundle or

modifying the routing of the wire

bundle or ensuring adequate clearance

between the wire bundle and the fuel

cross-feed valve operating lever because

these costs will depend on the extent of

the repairs or modifications required.

The cost impact figure discussed

above is 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

adding the following new airworthiness

directive:

2000–22–22 Raytheon Aircraft Company:

Amendment 39–11970. Docket 2000–

NM–46–AD.

Applicability: Model Hawker 800XP series

airplanes, as listed in Raytheon Service

Bulletin SB 24–3212, dated August 1999; and

Hawker 800 (U–125A) series airplanes, as

listed in Raytheon Service Bulletin SB 24–

3213, dated February 2000; 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) 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 chafing of the wire

bundle exiting panel ‘‘JA’’ due to insufficient

clearance from the fuel cross-feed valve

operating lever, which could result in a fire

in the area of the fuel system in a confined

space, accomplish the following:

Inspection and Corrective Actions

(a) Within 50 flight hours or 6 months after

the effective date of this AD, whichever

comes first, conduct a one-time detailed

visual inspection of the panel ‘‘JA’’ wire

bundle in accordance with the

Accomplishment Instructions of Raytheon

Aircraft Service Bulletin SB 24–3212, dated

August 1999 (for Model 800XP series

airplanes); or SB 24–3213, Revision 1, dated

February 2000 (for Model 800 (U–125A)

series airplanes; as applicable.

(1) Ensure that the wire bundle is routed

correctly, in accordance with Figure 1 of the

applicable service bulletin.

(2) Ensure that a minimum clearance of

0.25-inch exists between the wire bundle

from relay ‘‘KT’’ and the fuel cross-feed valve

operating lever throughout its range of travel.

Note 2: For the purposes of this AD, a

detailed visual inspection is defined as: ‘‘An

intensive visual examination of a specific

structural area, system, installation, or

assembly to detect damage, failure, or

irregularity. Available lighting is normally

supplemented with a direct source of good

lighting at intensity deemed appropriate by

the inspector. Inspection aids such as mirror,

magnifying lenses, etc., may be used. Surface

cleaning and elaborate access procedures

may be required.’’

(b) If the wire bundle is routed correctly

and sufficient clearance exists, no further

action is required by this AD.

(c) If the wire bundle is not routed

correctly or if sufficient clearance does not

exist, prior to further flight, perform a

detailed visual inspection of the wire bundle

to relay ‘‘KT’’ for chafing, in accordance with

the Accomplishment Instructions of

Raytheon Aircraft Service Bulletin SB 24–

3212, dated August 1999 (for Model 800XP

series airplanes); or SB 24–3213, Revision 1,

dated February 2000 (for Model 800 (U–

125A) series airplanes); as applicable.

(1) If no chafing is detected, prior to further

flight, ensure that the wire bundle is routed

correctly and ensure that a minimum

clearance of 0.25-inch exists between the

wire bundle and the fuel cross-feed valve

operating valve throughout its range of travel,

in accordance with the applicable service

bulletin.

(2) If any chafing is detected, prior to

further flight, repair the chafed wire, ensure

that the wire bundle is routed correctly and

ensure that a minimum clearance of 0.25-

inch exists between the wire bundle and the

fuel cross-feed valve operating valve

throughout its range of travel, in accordance

with the applicable service bulletin.

Alternative Methods of Compliance

(d) 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, Wichita

Aircraft Certification Office (ACO), FAA.

Operators shall submit their requests through

an appropriate FAA Principal Maintenance

Inspector, who may add comments and then

send it to the Manager, Wichita ACO.

Note 3: Information concerning the

existence of approved alternative methods of

compliance with this AD, if any, may be

obtained from the Wichita ACO.

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

Federal Register / Vol. 65, No. 220 / Tuesday, November 14, 2000 / Rules and Regulations 68071

a location where the requirements of this AD

can be accomplished.

Incorporation by Reference

(f) The actions shall be done in accordance

with Raytheon Aircraft Service Bulletin SB

24–3212, dated August 1999; or Raytheon

Aircraft Service Bulletin SB 24–3213,

Revision 1, dated February 2000; as

applicable. 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 Raytheon Aircraft Company, 9709 East

Central, Wichita, Kansas 67206. Copies may

be inspected at the FAA, Transport Airplane

Directorate, 1601 Lind Avenue, SW., Renton,

Washington; or at the FAA, Wichita Aircraft

Certification Office, 1801 Airport Road,

Room 100, Mid-Continent Airport, Wichita,

Kansas; or at the Office of the Federal

Register, 800 North Capitol Street, NW., suite

700, Washington, DC.

Effective Date

(g) This amendment becomes effective on

December 19, 2000.

Issued in Renton, Washington, on

November 1, 2000.

Donald L. Riggin,

Acting Manager, Transport Airplane

Directorate, Aircraft Certification Service.

[FR Doc. 00–28479 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–SW–14–AD; Amendment

39–11967; AD 2000–22–19]

RIN 2120–AA64

Airworthiness Directives; Eurocopter

France Model SA330F, G, and J

Helicopters

AGENCY: Federal Aviation

Administration, DOT.

ACTION: Final rule.

SUMMARY: This amendment supersedes

an existing airworthiness directive (AD)

that applies to Eurocopter France Model

SA330F, G, and J helicopters and

requires inspecting the tail rotor blade

(blade) skin for cracks and replacing, as

necessary, the blade. This amendment

requires skin bonding and eddy current

inspections of the blade skin for cracks

and would reference a more recent

service bulletin (SB). This amendment

is prompted by improved inspection

methods and by the manufacturer

revising the SB referenced in the current

AD. The actions specified by this AD are

intended to prevent fatigue cracking of

a blade, failure of a blade, and

subsequent loss of control of the

helicopter.

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.

ADDRESSES: The service information

referenced in this AD may be obtained

from American Eurocopter Corporation,

2701 Forum Drive, Grand Prairie, Texas

75053–4005, telephone (972) 641–3460,

fax (972) 641–3527. This information

may be examined 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.

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: A

proposal to amend part 39 of the Federal

Aviation Regulations (14 CFR part 39)

by superseding AD 80–12–04,

Amendment 39–3790 (45 FR 37180,

June 2, 1980), which applies to

Eurocopter France Model SA330F, G,

and J helicopters, was published in the

Federal Register on August 10, 2000 (65

FR 48936). That action proposed to

require skin bonding and eddy current

inspections of the blade skin for cracks

and referenced a more recent SB.

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 4 helicopters

of U.S. registry will be affected by this

AD, that it will take approximately 1.5

work hours per helicopter to accomplish

the required actions, and that the

average labor rate is $60 per work hour.

Based on these figures, the total cost

impact of the AD on U.S. operators is

estimated to be $360.

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 39–3790 (45 FR

37180, June 2, 1980), and by adding a

new airworthiness directive (AD),

Amendment 39–11967, to read as

follows:

2000–22–19 Eurocopter France:

Amendment 39–11967. Docket No. 2000-

SW–14–AD. Supersedes AD 80–12–04,

Amendment 39–3790, Docket No. 20384.

Applicability: Model SA330F, G, and J

helicopters with a tail rotor blade (blade),

part number (P/N) 330A12–0000-(all dash

numbers), 330A12–0000-(all dash numbers),

330A12–0006-(all dash numbers), 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.