Federal Register / Vol. 65, No. 235 / Wednesday, December 6, 2000 / Rules and Regulations 76149

the airplane, and the use of composite

material in the airplane structure, the

immunity of critical avionics/

electronics and electrical systems to

HIRF must be established.

It is not possible to precisely define

the HIRF to which the airplane will be

exposed in service. There is also

uncertainty concerning the effectiveness

of airframe shielding for HIRF.

Furthermore, coupling of

electromagnetic energy to cockpitinstalled equipment through the cockpit

window apertures is undefined. Based

on surveys and analysis of existing HIRF

emitters, an adequate level of protection

exists when compliance with the HIRF

protection special condition is shown

with either paragraph 1. or,

alternatively, paragraph 2., below:

1. A minimum threat of 100 volts rms

per meter electric field strength from 10

KHz to 18 GHz.

a. The threat must be applied to the

system elements and their associated

wiring harnesses without the benefit of

airframe shielding.

b. Demonstration of this level of

protection is established through system

tests and analysis.

Or

2. A threat external to the airframe for

both of the following field strengths for

the frequency ranges indicated. Both

peak and average field strength

components from Table 1 are to be

demonstrated.

TABLE 1

Frequency

Field

Strength

(volts per

meter)

Peak Average

10 kHz—100 kHz ................. 50 50

100 kHz—500 kHz ............... 50 50

500 kHz—2 MHz .................. 50 50

2 MHz—30 MHz ................... 100 100

30 MHz—70 MHz ................. 50 50

70 MHz—100 MHz ............... 50 50

100 MHz—200 MHz ............. 100 100

200 MHz—400 MHz ............. 100 100

400 MHz—700 MHz ............. 700 50

700 MHz—1 GHz ................. 700 100

1 GHz—2 GHz ..................... 2000 200

2 GHz—4 GHz ..................... 3000 200

4 GHz—6 GHz ..................... 3000 200

6 GHz—8 GHz ..................... 1000 200

8 GHz—12 GHz ................... 3000 300

12 GHz—18 GHz ................. 2000 200

18 GHz—40 GHz ................. 600 200

The field strengths are expressed in terms of

peak of the root-mean-square (rms) over

the complete modulation period.

The threat levels identified in Table 1

are the result of an FAA review of

existing studies on the subject of HIRF,

in light of the ongoing work of the

Electromagnetic Effects Harmonization

Working Group of the Aviation

Rulemaking Advisory Committee.

Applicability

As discussed above, these special

conditions are applicable to the

Gulfstream Model G–1159, G–1159A,

and G–1159B series airplanes modified

by Duncan Aviation. Should Duncan

Aviation apply at a later date for a

supplemental type certificate to modify

any other model included on Type

Certificate No. A12EA to incorporate the

same novel or unusual design feature,

the special conditions would apply to

that model as well under the provisions

of § 21.101(a)(1).

Conclusion

This action affects only certain novel

or unusual design features on

Gulfstream Model G–1159, G–1159A,

and G–1159B airplanes modified by

Duncan Aviation. It is not a rule of

general applicability and affects only

the applicant who applied to the FAA

for approval of these features on the

airplane.

As stated previously, the substance of

these special conditions has been

subjected to the notice and comment

period in several prior instances and has

been derived without substantive

change from those previously issued. It

is unlikely that prior public comment

would result in a significant change

from the substance contained herein.

For this reason, and because a delay

would significantly affect the

certification of the airplane, which is

imminent, the FAA has determined that

prior public notice and comment are

unnecessary and impracticable, and

good cause exists for adopting these

special conditions upon issuance. The

FAA is requesting comments to allow

interested persons to submit views that

may not have been submitted in

response to the prior opportunities for

comment described above.

List of Subjects in 14 CFR Part 25

Aircraft, Aviation safety, Reporting

and recordkeeping requirements.

The authority citation for these

special conditions is as follows:

Authority: 49 U.S.C. 106(g), 40113, 44701,

44702, 44704.

The Special Conditions

Accordingly, pursuant to the

authority delegated to me by the

Administrator, the following special

conditions are issued as part of the type

certification basis for Gulfstream

Aerospace Model G–1159, G–1159A,

and G–1159B airplanes modified by

Duncan Aviation:

1. Protection From Unwanted Effects

of High-Intensity Radiated Fields

(HIRF). Each electrical and electronic

system that performs critical functions

must be designed and installed to

ensure that the operation and

operational capability of these systems

to perform critical functions are not

adversely affected when the airplane is

exposed to high intensity radiated

fields.

2. For the purpose of this special

condition, the following definition

applies: Critical Functions. Functions

whose failure would contribute to or

cause a failure condition that would

prevent the continued safe flight and

landing of the airplane.

Issued in Renton, Washington, on

November 29, 2000.

Ali Bahrami,

Acting Manager, Transport Airplane

Directorate, Aircraft Certification Service.

[FR Doc. 00–31085 Filed 12–5–00; 8:45 am]

BILLING CODE 4910–13–U

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 2000–SW–27–AD; Amendment

39–12028; AD 2000–24–21]

RIN 2120–AA64

Airworthiness Directives; Siam Hiller

Holdings, Inc. Model UH–12, UH–12A,

UH–12B, UH–12C, UH–12D, UH–12E,

UH–12E–L, UH–12L, and UH–12L4

Helicopters

AGENCY: Federal Aviation

Administration, DOT.

ACTION: Final rule.

SUMMARY: This amendment adopts a

new airworthiness directive (AD), for

Siam Hiller Holdings, Inc. (Hiller),

formerly Rogerson Hiller Corporation,

Model UH–12, UH–12A, UH–12B, UH–

12C, UH–12D, UH–12E, UH–12E–L,

UH–12L, and UH–12L4 helicopters, that

requires replacing all undrilled-shank

bolts at pivoting joints in the control

system linkage with drilled-shank bolts

and installing castellated nuts and cotter

pins. This amendment is prompted by

an accident caused by separation of the

control system linkage of a Model UH–

12E helicopter. The actions specified by

this AD are intended to prevent

separation of the control system

attachments at pivoting points and

subsequent loss of control of the

helicopter.

76150 Federal Register / Vol. 65, No. 235 / Wednesday, December 6, 2000 / Rules and Regulations

DATES: Effective January 10, 2001.

The incorporation by reference of

certain publications listed in the

regulations is approved by the Director

of the Federal Register as of January 10,

2001.

ADDRESSES: The service information

referenced in this AD may be obtained

from Hiller Aircraft Corporation, 3200

Imjin Road, Marina, California 93933–

5101, telephone (408) 384–4500, fax

(408) 384–3100. 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: Jon

Mowery, Aviation Safety Engineer,

FAA, Los Angeles Aircraft Certification

Office, Airframe Branch, 3960

Paramount Blvd., Lakewood, California

90712–4137, telephone (562) 627–5322,

fax (562) 627–5210.

SUPPLEMENTARY INFORMATION: A

proposal to amend part 39 of the Federal

Aviation Regulations (14 CFR part 39) to

include an airworthiness directive (AD)

for Hiller Model UH–12, UH–12A, UH–

12B, UH–12C, UH–12D, UH–12E, UH–

12E–L, UH–12L, and UH–12L4

helicopters was published in the

Federal Register on August 31, 2000 (65

FR 52958). That action proposed to

require replacing all undrilled-shank

bolts at the pivoting joints in the control

system linkage with drilled-shank bolts

and installing castellated nuts and cotter

pins.

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 500

helicopters of U.S. registry will be

affected by this AD, that it will take

approximately 24 work hours per

helicopter to accomplish the required

actions, and that the average labor rate

is $60 per work hour. Required parts

will cost approximately $150 per

helicopter. Based on these figures, the

total cost impact of the AD on U.S.

operators is estimated to be $795,000.

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 a new airworthiness directive to

read as follows:

2000–24–21 Siam Hiller Holdings, Inc.:

Amendment 39–12028. Docket No.

2000–SW–27–AD.

Applicability: Model UH–12, UH–12A,

UH–12B, UH–12C, UH–12D, UH–12E, UH–

12E–L, UH–12L, UH–12L4 helicopters,

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.

Compliance: Required at the next annual

inspection or within 12 months, whichever

occurs first, unless accomplished previously.

To prevent separation of the control system

attachments at pivoting points and

subsequent loss of control of the helicopter,

accomplish the following:

(a) Replace all undrilled-shank bolts at

pivoting joints in the control system linkage

with drilled-shank bolts, and install

castellated nuts and cotter pins in accordance

with Hiller Aircraft Corporation Service

Bulletin No. 10–4, Revision 2, dated

December 20, 1999.

(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, FAA.

Operators shall submit their requests through

an FAA Principal Maintenance Inspector,

who may concur or comment and then send

it to the Manager, Los Angeles Aircraft

Certification Office.

Note 2: Information concerning the

existence of approved alternative methods of

compliance with this AD, if any, may be

obtained from the Los Angeles Aircraft

Certification Office.

(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 installation of castellated nuts and

cotter pins shall be done in accordance with

Hiller Aircraft Corporation Service Bulletin

No. 10–4, Revision 2, dated December 20,

1999. 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 Hiller Aircraft Corporation, 3200 Imjin

Road, Marina, California 93933–5101,

telephone (408) 384–4500, fax (408) 384–

3100. 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

January 10, 2001.

Issued in Fort Worth, Texas, on November

14, 2000.

Michele M. Owsley,

Acting Manager, Rotorcraft Directorate,

Aircraft Certification Service.

[FR Doc. 00–30652 Filed 12–5–00; 8:45 am]

BILLING CODE 4910–13–U

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 71

[Airspace Docket No. 00–AWP–11]

Revision to the Legal Description of

the Laughlin/Bullhead International

Airport Class D Airspace Area, AZ

AGENCY: Federal Aviation

Administration (FAA) DOT.