Federal Register / Vol. 63, No. 75 / Monday, April 20, 1998 /Rules and Regulations 19391

The FAA’s Determination

After careful review of all available

information related to the subject

presented above, the FAA has

determined that air safety and the

public interest require the adoption of

the rule as proposed except for minor

editorial corrections. The FAA has

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

The FAA estimates that 40 airplanes

in the U.S. registry will be affected by

this AD, that it will take approximately

6 workhours per airplane to accomplish

this action, and that the average labor

rate is approximately $60 an hour. Parts

will be provided at no cost by the

manufacturer. Based on these figures,

the total cost impact of this AD on U.S.

operators is estimated to be $14,400 or

$360 per airplane.

Regulatory Impact

The regulations adopted herein will

not have substantial direct effects 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, in

accordance with Executive Order 12612,

it is determined that this final rule does

not have sufficient federalism

implications to warrant the preparation

of a Federalism Assessment.

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, 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

(AD) to read as follows:

98–08–26 Pilatus Aircraft Ltd.: Amendment

39–10475; Docket No. 97–CE–46–AD.

Applicability: Model PC–12 and PC–12/45

airplanes, serial numbers MSN 001 through

MSN 168, 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 (c) 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 within the next 100

hours time-in-service (TIS) after the effective

date of this AD, unless already accomplished.

To prevent electrical arcing in the fuel

tanks and detonation of the fuel-air mixture,

which can be created by poor electrical

bonding of fuel tank underwing access

panels, and could result in a fire on the

airplane, accomplish the following:

(a) Install aluminum bonding bushings

onto the screws for certain fuel tank

underwing access panels in accordance with

Part A and Part B of the Accomplishment

Instructions in Pilatus Service Bulletin No.

57–001, dated February 28, 1997.

(b) 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.

(c) An alternative method of compliance or

adjustment of the compliance time that

provides an equivalent level of safety may be

approved by the Manager, Small Airplane

Directorate, Aircraft Certification Service,

1201 Walnut, suite 900, Kansas City,

Missouri 64106. The request shall be

forwarded through an appropriate FAA

Maintenance Inspector, who may add

comments and then send it to the Manager,

Small Airplane Directorate.

Note 2: Information concerning the

existence of approved alternative methods of

compliance with this AD, if any, may be

obtained from the Small Airplane

Directorate.

(d) Questions or technical information

related to Pilatus Service Bulletin No. 57–

001, dated February 28, 1997, should be

directed to Pilatus Aircraft Ltd., CH–6370

Stans, Switzerland. This service information

may be examined at the FAA, Central Region,

Office of the Regional Counsel, Room 1558,

601 E. 12th Street, Kansas City, Missouri.

(e) The installations required by this AD

shall be done in accordance with Pilatus

Service Bulletin No. 57–001, dated February

28, 1997. 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 Pilatus Aircraft Ltd., CH–6370 Stans,

Switzerland. Copies may be inspected at the

FAA, Central Region, Office of the Regional

Counsel, Room 1558, 601 E. 12th Street,

Kansas City, Missouri, or at the Office of the

Federal Register, 800 North Capitol Street,

NW, suite 700, Washington, DC.

(f) This amendment becomes effective on

May 29, 1998.

Issued in Kansas City, Missouri, on April

9, 1998.

Michael Gallagher,

Manager, Small Airplane Directorate, Aircraft

Certification Service.

[FR Doc. 98–10176 Filed 4–17–98; 8:45 am]

BILLING CODE 4910–13–U

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 98–NM–114–AD; Amendment

39–10480; AD 98–09–01]

RIN 2120–AA64

Airworthiness Directives; Gulfstream

Model GV 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 Gulfstream Model

GV series airplanes. This action requires

inspections and functional tests of the

elevator Hardover Prevention System

(HOPS) to detect any miswiring of

electrical connectors, correction of any

discrepancy found, and eventual

modification of the HOPS wiring. This

amendment is prompted by reports of

incorrect matching of electrical

connectors to the hydraulic deactivation

valves of the elevator HOPS. The actions

specified in this AD are intended to

prevent the incorrect operation of the

elevator HOPS, which could result in

loss of control of the airplane.

DATES: Effective May 5, 1998.

The incorporation by reference of

certain publications listed in the
19392 Federal Register / Vol. 63, No. 75 / Monday, April 20, 1998 /Rules and Regulations

regulations is approved by the Director

of the Federal Register as of May 5,

1998.

Comments for inclusion in the Rules

Docket must be received on or before

June 19, 1998.

ADDRESSES: Submit comments in

triplicate to the Federal Aviation

Administration (FAA), Transport

Airplane Directorate, ANM–114,

Attention: Rules Docket No. 98–NM–

114–AD, 1601 Lind Avenue, SW.,

Renton, Washington 98055–4056.

The service information referenced in

this AD may be obtained from

Gulfstream Aerospace Corporation, P.O.

Box 2206, M/S D–10, Savannah, Georgia

31402–9980. This information may be

examined at the FAA, Transport

Airplane Directorate, 1601 Lind

Avenue, SW., Renton, Washington; or at

the FAA, Small Airplane Directorate,

Atlanta Aircraft Certification Office,

One Crown Center, 1895 Phoenix

Boulevard, suite 450, Atlanta, Georgia;

or at the Office of the Federal Register,

800 North Capitol Street, NW., suite

700, Washington, DC.

FOR FURTHER INFORMATION CONTACT: Neil

Berryman, Aerospace Engineer, Systems

and Flight Test Branch, ACE–116A,

FAA, Small Airplane Directorate,

Atlanta Aircraft Certification Office,

One Crown Center, 1895 Phoenix

Boulevard, suite 450, Atlanta, Georgia

30337–2748; telephone (770) 703–6066;

fax (770) 703–6097.

SUPPLEMENTARY INFORMATION: The FAA

has received reports indicating that,

during recent inspections and

operational tests of the elevator

Hardover Prevention System (HOPS) on

certain Gulfstream Model GV series

airplanes, a configuration discrepancy

was identified in which certain

electrical connectors were incorrectly

connected to the hydraulic deactivation

valves of the elevator HOPS. The flight

control hydraulic servos on the

Gulfstream Model GV series airplane

incorporate two redundant actuator

pistons. The HOPS is designed to detect

a runaway (or hardover) condition in

either of these actuator pistons, and to

subsequently shut down the affected

side of the hydraulic servo. If the

elevator HOPS is wired incorrectly, the

system will shut down the wrong side

of the hydraulic servo although that

actuator is still operating properly. This

condition, if not corrected, would

prevent the correct operation of the

elevator HOPS, which could result in

loss of control of the airplane.

Explanation of Relevant Service

Information

The FAA has reviewed and approved

Gulfstream Aerospace Alert Customer

Bulletin No. 3, dated February 25, 1998,

which describes procedures for

performing a one-time inspection of the

elevator HOPS to detect any incorrect

wiring connections associated with the

HOPS hydraulic deactivation valves,

and corrective action, if necessary. The

alert customer bulletin also describes

procedures for a one-time functional test

to ensure correct operation of the

elevator HOPS.

In addition, the FAA has reviewed

and approved Gulfstream Aerospace GV

Customer Bulletin No. 4, dated March

31, 1998, which describes procedures

for modifying the electrical harness of

the hydraulic deactivation valves of the

left elevator HOPS, and installing

additional identification decals in order

to prevent future miswiring.

Accomplishment of the actions

specified in this customer bulletin

eliminates the need for the inspection

and functional test specified in

Gulfstream Alert Customer Bulletin No.

3.

Explanation of the Requirements of the

Rule

Since an unsafe condition has been

identified that is likely to exist or

develop on other airplanes of the same

type design, this AD is being issued to

prevent the incorrect operation of the

elevator HOPS, which could result in

loss of control of the airplane. This AD

requires accomplishment of the actions

specified in the customer bulletins

described previously, except as

discussed below.

Differences Between This Rule and

Customer Bulletin

Operators should note that Gulfstream

Aerospace Alert Customer Bulletin No.

3, dated February 25, 1998, describes a

one-time inspection and functional test

to verify proper electrical configuration

and operation of the elevator HOPS. The

FAA has determined that, because of the

safety implications and consequences

associated with energizing the incorrect

hydraulic deactivation valve of the

elevator HOPS, performance of the

inspection and functional test is

necessary following accomplishment of

any maintenance action associated with

the elevator HOPS, until the wiring

modifications described in Gulfstream

Aerospace GV Customer Bulletin No. 4,

dated March 31, 1998, are

accomplished.

Operators also should note that,

although Gulfstream Aerospace Alert

Customer Bulletin No. 3 specifies that

the manufacturer may be contacted if

technical assistance is required during

accomplishment of the functional test,

this AD requires that repair of any

discrepancies be accomplished in

accordance with a method approved by

the FAA.

Determination of Rule’s Effective Date

Since a situation exists that requires

the immediate adoption of this

regulation, it is found that notice and

opportunity for prior public comment

hereon are impracticable, and that good

cause exists for making this amendment

effective in less than 30 days.

Comments Invited

Although this action is in the form of

a final rule that involves requirements

affecting flight safety and, thus, was not

preceded by notice and an opportunity

for public comment, comments are

invited on this rule. Interested persons

are invited to comment on this rule by

submitting such written data, views, or

arguments as they may desire.

Communications shall identify the

Rules Docket number and be submitted

in triplicate to the address specified

under the caption ADDRESSES. All

communications received on or before

the closing date for comments will be

considered, and this rule may be

amended in light of the comments

received. Factual information that

supports the commenter’s ideas and

suggestions is extremely helpful in

evaluating the effectiveness of the AD

action and determining whether

additional rulemaking action would be

needed.

Comments are specifically invited on

the overall regulatory, economic,

environmental, and energy aspects of

the rule that might suggest a need to

modify the rule. All comments

submitted will be available, both before

and after the closing date for comments,

in the Rules Docket for examination by

interested persons. A report that

summarizes each FAA-public contact

concerned with the substance of this AD

will be filed in the Rules Docket.

Commenters wishing the FAA to

acknowledge receipt of their comments

submitted in response to this rule must

submit a self-addressed, stamped

postcard on which the following

statement is made: ‘‘Comments to

Docket Number 98–NM–114–AD.’’ The

postcard will be date stamped and

returned to the commenter.

Regulatory Impact

The regulations adopted herein will

not have substantial direct effects on the

States, on the relationship between the
Federal Register / Vol. 63, No. 75 / Monday, April 20, 1998 /Rules and Regulations 19393

national government and the States, or

on the distribution of power and

responsibilities among the various

levels of government. Therefore, in

accordance with Executive Order 12612,

it is determined that this final rule does

not have sufficient federalism

implications to warrant the preparation

of a Federalism Assessment.

The FAA has determined that this

regulation is an emergency regulation

that must be issued immediately to

correct an unsafe condition in aircraft,

and that it is not a ‘‘significant

regulatory action’’ under Executive

Order 12866. It has been determined

further that this action involves an

emergency regulation under DOT

Regulatory Policies and Procedures (44

FR 11034, February 26, 1979). If it is

determined that this emergency

regulation otherwise would be

significant under DOT Regulatory

Policies and Procedures, a final

regulatory evaluation will be prepared

and placed in the Rules Docket. A copy

of it, if filed, 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:

98–09–01 Gulfstream Aerospace

Corporation: Amendment 39–10480.

Docket 98–NM–114–AD.

Applicability: Model GV series airplanes,

serial numbers 501 and 504 through 540

inclusive, 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 prevent the incorrect operation of the

elevator Hardover Prevention System

(HOPS), which could result in loss of control

of the airplane, accomplish the following:

(a) Within 25 flight hours after the effective

date of this AD, accomplish the requirements

of paragraphs (a)(1) and (a)(2) of this AD, in

accordance with Gulfstream Aerospace Alert

Customer Bulletin No. 3, dated February 25,

1998.

(1) Perform a visual inspection to verify

correct wire connections to the forward and

aft hydraulic deactivation valve, left- and

right-hand sides, of the elevator HOPS. If any

connector is connected improperly, prior to

further flight, re-connect the wiring in

accordance with the alert customer bulletin.

And

(2) Perform a functional test to ensure

correct operation of the elevator HOPS. If any

discrepancy is found, prior to further flight,

repair in accordance with a method approved

by the Manager, Atlanta Aircraft Certification

Office (ACO), FAA, Small Airplane

Directorate.

(b) Thereafter, repeat the actions required

by paragraph (a) of this AD immediately

following accomplishment of any

maintenance actions on the elevator HOPS,

until the actions required by paragraph (c) of

the AD have been accomplished.

(c) Within 150 flight hours after the

effective date of this AD, modify the

electrical harness of the hydraulic

deactivation valves of the left elevator HOPS,

and install additional identification decals,

in accordance with Gulfstream Aerospace GV

Customer Bulletin No. 4, dated March 31,

1998. Accomplishment of the requirements

of this paragraph constitutes terminating

action for this AD.

(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, Atlanta

ACO. Operators shall submit their requests

through an appropriate FAA Principal

Maintenance Inspector, who may add

comments and then send it to the Manager,

Atlanta ACO.

Note 2: Information concerning the

existence of approved alternative methods of

compliance with this AD, if any, may be

obtained from the Atlanta ACO.

(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.

(f) The inspection and functional test shall

be done in accordance with Gulfstream

Aerospace Alert Customer Bulletin No. 3,

dated February 25, 1998. The modification

shall be done in accordance with Gulfstream

Aerospace GV Customer Bulletin No. 4, dated

March 31, 1998. 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 Gulfstream Aerospace

Corporation, P.O. Box 2206, M/S D–10,

Savannah, Georgia 31402–9980. Copies may

be inspected at the FAA, Transport Airplane

Directorate, 1601 Lind Avenue, SW., Renton,

Washington; or at the FAA, Small Airplane

Directorate, Atlanta Aircraft Certification

Office, One Crown Center, 1895 Phoenix

Boulevard, suite 450, Atlanta, Georgia; or at

the Office of the Federal Register, 800 North

Capitol Street, NW., suite 700, Washington,

DC.

(g) This amendment becomes effective on

May 5, 1998.

Issued in Renton, Washington, on April 13,

1998.

Darrell M. Pederson,

Acting Manager, Transport Airplane

Directorate, Aircraft Certification Service.

[FR Doc. 98–10276 Filed 4–17–98; 8:45 am]

BILLING CODE 4910–13–U

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 71

[Airspace Docket No. 98–AWP–2]

Modification of Class E Airspace;

Porterville, CA

AGENCY: Federal Aviation

Administration (FAA), DOT.

ACTION: Final rule.

SUMMARY: This action modifies the Class

E airspace area at Porterville, CA. The

establishment of a Global Positioning

System (GPS) Standard Instrument

Approach Procedure (SIAP) to Runway

(RWY) 12 and a GPS SIAP to RWY 30

at Porterville Municipal Airport has

made this action necessary. Additional

controlled airspace extending upward

from 700 feet or more above the surface

of the earth is needed to contain aircraft

executing the GPS RWY 12 SIAP and

GPS RWY 30 SIAP to Porterville

Municipal Airport. The intended effect

of this action is to provide adequate

controlled airspace for Instrument Flight

Rules (IFR) operations Porterville

Municipal Airport, Porterville, CA.

EFFECTIVE DATE: 0901 UTC August 13,

1998.

FOR FURTHER INFORMATION CONTACT:

Larry Tonish, Airspace Specialist,

Airspace Branch, AWP–520, Air Traffic

Division, Western-Pacific Region,

Federal Aviation Administration, 15000

Aviation Boulevard, Lawndale,

California 90261, telephone (310) 725–

6539.