42952 Federal Register / Vol. 62, No. 154 / Monday, August 11, 1997 / Proposed Rules

Explanation of Relevant Service

Information

Fokker has issued Service Bulletin

SBF100–32–099, dated June 14, 1996,

which describes procedures for

replacement of the fusible pin in the

upper torque link of the MLG with an

improved pin. (This service bulletin

references Menasco Service Bulletin

41050–32–6, dated March 15, 1995, as

an additional source of service

information for accomplishment of the

replacement.) The RLD classified the

Fokker service bulletin as mandatory

and issued Dutch airworthiness

directive BLA 1996–074 (A), dated June

28, 1996, in order to assure the

continued airworthiness of these

airplanes in the Netherlands.

FAA’s Conclusions

These airplane models are

manufactured in the Netherlands and

are type certificated for operation in the

United States under the provisions of

section 21.29 of the Federal Aviation

Regulations (14 CFR 21.29) and the

applicable bilateral airworthiness

agreement. Pursuant to this bilateral

airworthiness agreement, the RLD has

kept the FAA informed of the situation

described above. The FAA has

examined the findings of the RLD,

reviewed all available information, and

determined that AD action is necessary

for products of this type design that are

certificated for operation in the United

States.

Explanation of Requirements of

Proposed Rule

Since an unsafe condition has been

identified that is likely to exist or

develop on other airplanes of the same

type design registered in the United

States, the proposed AD would require

accomplishment of the actions specified

in the Fokker service bulletin described

previously.

Cost Impact

The FAA estimates that 10 airplanes

of U.S. registry would be affected by this

proposed AD, that it would take

approximately 14 work hours per

airplane to accomplish the proposed

actions, and that the average labor rate

is $60 per work hour. Required parts

would be supplied by the manufacturer

at no cost to the operators. Based on

these figures, the cost impact of the

proposed AD on U.S. operators is

estimated to be $8,400, or $840 per

airplane.

The cost impact figure discussed

above is based on assumptions that no

operator has yet accomplished any of

the proposed requirements of this AD

action, and that no operator would

accomplish those actions in the future if

this AD were not adopted.

Regulatory Impact

The regulations proposed herein

would 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

proposal would not have sufficient

federalism implications to warrant the

preparation of a Federalism Assessment.

For the reasons discussed above, I

certify that this proposed regulation (1)

is not a ‘‘significant regulatory action’’

under Executive Order 12866; (2) is not

a ‘‘significant rule’’ under the DOT

Regulatory Policies and Procedures (44

FR 11034, February 26, 1979); and (3) if

promulgated, 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 draft

regulatory 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, Safety.

The Proposed Amendment

Accordingly, pursuant to the

authority delegated to me by the

Administrator, the Federal Aviation

Administration proposes to amend 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:

Fokker: Docket 97–NM–165–5-AD.

Applicability: Model F28 Mark 0100 and

0070 series airplanes, equipped with

Menasco Aerospace Ltd. main landing gears

having part number (P/N) 41050, including

the fusible upper torque link pin having P/

N 41223–1; certificated in any category.

Note 1: This AD applies to each airplane

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 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 as indicated, unless

accomplished previously.

To prevent reduced structural integrity and

potential collapse of the main landing gear,

accomplish the following:

(a) Within one year after the effective date

of this AD, replace any main landing gear

upper torque link fusible pin having P/N

41223–1 with a pin having P/N 41223–3, in

accordance with Fokker Service Bulletin

SBF100–32–099, dated June 14, 1996.

(b) As of the effective date of this AD, no

person shall install a main landing gear

upper torque link fusible pin having P/N

41223–1 on any airplane.

(c) 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,

Standardization Branch, ANM–113, 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, Standardization

Branch, ANM–113.

Note 2: Information concerning the

existence of approved alternative methods of

compliance with this AD, if any, may be

obtained from the Standardization Branch,

ANM–113.

(d) 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.

Issued in Renton, Washington, on August

5, 1997.

John J. Hickey,

Acting Manager, Transport Airplane

Directorate, Aircraft Certification Service.

[FR Doc. 97–21097 Filed 8–8–97; 8:45 am]

BILLING CODE 4910–13–U

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 97–NM–166–AD]

RIN 2120–AA64

Airworthiness Directives; Israel

Aircraft Industries (IAI), Ltd., Model

1121, 1121A, 1121B, 1123, 1124, and

1124A Series Airplanes

AGENCY: Federal Aviation

Administration, DOT.
Federal Register / Vol. 62, No. 154 / Monday, August 11, 1997 / Proposed Rules 42953

ACTION: Notice of proposed rulemaking

(NPRM).

SUMMARY: This document proposes the

adoption of a new airworthiness

directive (AD) that is applicable to all

IAI, Ltd., Model 1121, 1121A, 1121B,

1123, 1124, and 1124A series airplanes.

This proposal would require repetitive

inspections of the trim actuator of the

horizontal stabilizer to verify jackscrew

integrity and to detect excessive wear of

the tie rod, and replacement of the

actuator or tie rod, if necessary. This

proposal is prompted by issuance of

mandatory continued airworthiness

information by a foreign civil

airworthiness authority. The actions

specified by the proposed AD are

intended to ensure that the trim actuator

of the horizontal stabilizer operates

properly; failure of the actuator to

operate properly could result in reduced

controllability of the airplane.

DATES: Comments must be received by

September 22, 1997.

ADDRESSES: Submit comments in

triplicate to the Federal Aviation

Administration (FAA), Transport

Airplane Directorate, ANM–103,

Attention: Rules Docket No. 97–NM–

166–AD, 1601 Lind Avenue, SW.,

Renton, Washington 98055–4056.

Comments may be inspected at this

location between 9:00 a.m. and 3:00

p.m., Monday through Friday, except

Federal holidays.

The service information referenced in

the proposed rule may be obtained from

Technical Publications, Astra Jet

Corporation, 77 McCullough Drive,

Suite 11, New Castle, Delaware 19720.

This information may be examined at

the FAA, Transport Airplane

Directorate, 1601 Lind Avenue, SW.,

Renton, Washington.

FOR FURTHER INFORMATION CONTACT: Tim

Dulin, Aerospace Engineer,

Standardization Branch, ANM–113,

FAA, Transport Airplane Directorate,

1601 Lind Avenue, SW., Renton,

Washington 98055–4056; telephone

(425) 227–2141; fax (425) 227–1149.

SUPPLEMENTARY INFORMATION:

Comments Invited

Interested persons are invited to

participate in the making of the

proposed 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 above. All communications

received on or before the closing date

for comments, specified above, will be

considered before taking action on the

proposed rule. The proposals contained

in this notice may be changed in light

of the comments received.

Comments are specifically invited on

the overall regulatory, economic,

environmental, and energy aspects of

the proposed 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

summarizing each FAA-public contact

concerned with the substance of this

proposal will be filed in the rules

docket.

Commenters wishing the FAA to

acknowledge receipt of their comments

submitted in response to this notice

must submit a self-addressed, stamped

postcard on which the following

statement is made: ‘‘Comments to

Docket Number 97-NM–166-AD.’’ The

postcard will be date stamped and

returned to the commenter.

Availability of NPRMs

Any person may obtain a copy of this

NPRM by submitting a request to the

FAA, Transport Airplane Directorate,

ANM–103, Attention: Rules Docket No.

97-NM–166-AD, 1601 Lind Avenue,

SW., Renton, Washington 98055–4056.

Discussion

The Civil Aviation Administration of

Israel (CAAI), which is the

airworthiness authority for Israel,

notified the FAA that an unsafe

condition may exist on all Israel Aircraft

Industries (IAI), Ltd., Model 1121,

1121A, 1121B, 1123, 1124, and 1124A

series airplanes. The CAAI advises that,

during an inspection, an operator found

one sheared actuator jackscrew of the

horizontal stabilizer on an airplane,

which caused the rod end to separate

from the jackscrew. This condition, if

not corrected, could result in failure of

the actuator to operate properly, and

consequent reduced controllability of

the airplane.

Explanation of Relevant Service

Information

The manufacturer has issued

Commodore Jet Service Bulletin SB

1121–27–023, dated August 14, 1996

(for Model 1121, 1121A, and 1121B

series airplanes), Westwind Service

Bulletin SB 1123–27–046, dated August

14, 1996 (for Model 1123 series

airplanes), and Westwind Service

Bulletin 1124–27–133, dated August 14,

1996 (for Model 1124 and 1124A series

airplanes). These service bulletins

describe procedures for repetitive

inspections of the trim actuator of the

horizontal stabilizer to verify jackscrew

integrity and to detect excessive wear of

the tie rod, and replacement of the

actuator or tie rod, if necessary. The

CAAI classified these service bulletins

as mandatory and issued Israeli

airworthiness directive 96–92, dated

September 1, 1996, in order to assure

the continued airworthiness of these

airplanes in Israel.

FAA’s Conclusions

These airplane models are

manufactured in Israel and are type

certificated for operation in the United

States under the provisions of section

21.29 of the Federal Aviation

Regulations (14 CFR 21.29) and the

applicable bilateral airworthiness

agreement. Pursuant to this bilateral

airworthiness agreement, the CAAI has

kept the FAA informed of the situation

described above. The FAA has

examined the findings of the CAAI,

reviewed all available information, and

determined that AD action is necessary

for products of this type design that are

certificated for operation in the United

States.

Explanation of Requirements of

Proposed Rule

Since an unsafe condition has been

identified that is likely to exist or

develop on other airplanes of the same

type design registered in the United

States, the proposed AD would require

accomplishment of the actions specified

in the applicable service bulletin

described previously.

Cost Impact

The FAA estimates that 292 airplanes

of U.S. registry would be affected by this

proposed AD, that it would take

approximately 4 work hours per

airplane to accomplish the proposed

actions, and that the average labor rate

is $60 per work hour. Based on these

figures, the cost impact of the proposed

AD on U.S. operators is estimated to be

$70,080, or $240 per airplane.

The cost impact figure discussed

above is based on assumptions that no

operator has yet accomplished any of

the proposed requirements of this AD

action, and that no operator would

accomplish those actions in the future if

this AD were not adopted.

Regulatory Impact

The regulations proposed herein

would 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

proposal would not have sufficient
42954 Federal Register / Vol. 62, No. 154 / Monday, August 11, 1997 / Proposed Rules

federalism implications to warrant the

preparation of a Federalism Assessment.

For the reasons discussed above, I

certify that this proposed regulation (1)

is not a ‘‘significant regulatory action’’

under Executive Order 12866; (2) is not

a ‘‘significant rule’’ under the DOT

Regulatory Policies and Procedures (44

FR 11034, February 26, 1979); and (3) if

promulgated, 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 draft

regulatory 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, Safety.

The Proposed Amendment

Accordingly, pursuant to the

authority delegated to me by the

Administrator, the Federal Aviation

Administration proposes to amend 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:

Israel Aircraft Industries (IAI), LTD.: Docket

97–NM–166–AD.

Applicability: All Model 1121, 1121A,

1121B, 1123, 1124, and 1124A 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) 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 ensure that the trim actuator of the

horizontal stabilizer operates properly;

failure of the actuator to operate properly

could result in reduced controllability of the

airplane, accomplish the following:

(a) Perform an inspection of the trim

actuator of the horizontal stabilizer to verify

jackscrew integrity and to detect excessive

wear of the tie rod, in accordance with

Commodore Jet Service Bulletin SB 1121–27–

023, dated August 14, 1996 (for Model 1121,

1121A, and 1121B series airplanes),

Westwind Service Bulletin SB 1123–27–046,

dated August 14, 1996 (for Model 1123 series

airplanes), or Westwind Service Bulletin

1124–27–133, dated August 14, 1996 (for

Model 1124 and 1124A series airplanes), as

applicable; at the times specified in

paragraph (a)(1) or (a)(2) of this AD, as

applicable.

(1) For airplanes that have accumulated

6,000 or more total flight cycles or on which

the horizontal trim actuator has accumulated

2,000 or more flight cycles as of the effective

date of this AD: Inspect within 50 flight

hours after the effective date of this AD.

Repeat the inspection thereafter at intervals

not to exceed 300 flight hours (for Model

1121, 1121A, 1121B, and 1123 series

airplanes) or 400 flight hours (for Model 1124

and 1124A series airplanes), as applicable.

(2) For airplanes that have accumulated

less than 6,000 total flight cycles and on

which the horizontal trim actuator has

accumulated less than 2,000 total flight

cycles as of the effective date of this AD:

Inspect at the times specified in paragraph

(a)(2)(i) or (a)(2)(ii) of this AD, as applicable.

(i) For Model 1121, 1121A, 1121B,

and 1123 series airplanes: Inspect

within 300 flight hours after the

effective date of this AD. Repeat the

inspection thereafter at intervals not to

exceed 300 flight hours.

(ii) For Model 1124 and 1124A series

airplanes: Inspect within 400 flight

hours after the effective date of this AD.

Repeat the inspection thereafter at

intervals not to exceed 400 flight hours.

(b) If any discrepancy is found during

any inspection required by paragraph (a)

of this AD, prior to further flight,

replace the actuator or tie rod, as

applicable, in accordance with

Commodore Jet Service Bulletin SB

1121–27–023, dated August 14, 1996

(for Model 1121, 1121A, and 1121B

series airplanes), Westwind Service

Bulletin SB 1123–27–046, dated August

14, 1996 (for Model 1123 series

airplanes), or Westwind Service Bulletin

1124–27–133, dated August 14, 1996

(for Model 1124 and 1124A series

airplanes), as applicable.

(c) As of the effective date of this AD,

no horizontal stabilizer trim actuator

shall be installed on any airplane unless

that trim actuator has been inspected in

accordance with the requirements of

paragraph (a) of 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,

Standardization Branch, ANM–113,

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, Standardization Branch,

ANM–113.

Note 2: Information concerning the

existence of approved alternative methods of

compliance with this AD, if any, may be

obtained from the Standardization Branch,

ANM–113.

(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.

Issued in Renton, Washington, on August

5, 1997.

John J. Hickey,

Acting Manager, Transport Airplane

Directorate, Aircraft Certification Service.

[FR Doc. 97–21098 Filed 8–8–97; 8:45 am]

BILLING CODE 4910–13–U

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 71

[Airspace Docket No. 97–AWP–31]

Proposed Amendment to Class D

Airspace; Hayward, CA

AGENCY: Federal Aviation

Administration (FAA), DOT.

ACTION: Notice of proposed rulemaking.

SUMMARY: This notice proposes to

amend the Class D airspace area at

Hayward, CA. The development of a

Global Positioning System (GPS)

Standard Instrument Approach

Procedure (SIAP) to Runway (RWY) 28L

has made this amendment necessary.

The intended effect of this proposal is

to provide adequate controlled airspace

for Instrument Flight Rules (IFR)

operations at Hayward Air Terminal,

Hayward, CA.

DATES: Comments must be received on

or before September 10, 1997.

ADDRESSES: Send comments on the

proposal in triplicate to: Federal

Aviation Administration, Attn:

Manager, Airspace Branch, AWP–520,

Docket No. 97–AWP–31, Air Traffic

Division, P.O. Box 92007, Worldway

Postal Center, Los Angeles, California,

90009.

The official docket may be examined

in the Office of the Assistant Chief

Counsel, Western Pacific Region,

Federal Aviation Administration, Room