This section of the FEDERAL REGISTER

contains notices to the public of the proposed

issuance of rules and regulations. The

purpose of these notices is to give interested

persons an opportunity to participate in the

rule making prior to the adoption of the final

rules.

Proposed Rules Federal Register

41737

Vol. 63, No. 150

Wednesday, August 5, 1998

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 98–NM–108–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.

ACTION: Notice of proposed rulemaking

(NPRM).

SUMMARY: This document proposes the

supersedure of an existing airworthiness

directive (AD), applicable to all IAI,

Ltd., Model 1121, 1121A, 1121B, 1123,

1124, and 1124A series airplanes, that

currently requires 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. That AD also

provides for optional terminating action

for the repetitive inspections. This

action would require accomplishment of

the previously optional terminating

action. This proposal is prompted by

issuance of mandatory continuing

airworthiness information by a foreign

civil airworthiness authority. The

actions specified by the proposed AD

are intended to prevent failure of the

trim actuator of the horizontal stabilizer

due to failure of the jackscrews, which

could result in reduced controllability

of the airplane.

DATES: Comments must be received by

September 4, 1998.

ADDRESSES: Submit comments in

triplicate to the Federal Aviation

Administration (FAA), Transport

Airplane Directorate, ANM–114,

Attention: Rules Docket No. 98–NM–

108–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

Galaxy Aerospace Corporation, One

Galaxy Way, Fort Worth Alliance

Airport, Fort Worth, Texas 76177. This

information may be examined at the

FAA, Transport Airplane Directorate,

1601 Lind Avenue, SW., Renton,

Washington.

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:

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 98–NM–108–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–114, Attention: Rules Docket No.

98–NM–108–AD, 1601 Lind Avenue,

SW., Renton, Washington 98055–4056.

Discussion

On February 24, 1998, the FAA issued

AD 98–05–09, amendment 39–10370 (63

FR 11106, March 6, 1998), applicable to

all Israel Aircraft Industries (IAI), Ltd.,

Model 1121, 1121A, 1121B, 1123, 1124,

and 1124A series airplanes, to 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. That action was prompted by

a report indicating 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. The requirements of

that 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.

Actions Since Issuance of Previous Rule

When AD 98–05–09 was issued, it

contained a provision for an optional

replacement of the trim actuator of the

horizontal stabilizer with a modified

trim actuator with modified jackscrew

assemblies, which, if accomplished,

would constitute terminating action for

the required repetitive inspections.

Moreover, in AD 98–05–09, the FAA

indicated that the inspections required

by that AD are to be performed as

interim action, and that it was

considering further rulemaking to

require replacement of the trim actuator

of the horizontal stabilizer. This action

proposes such a requirement, to be

accomplished in accordance with

Commodore Jet Service Bulletin SB

1121–27–025, dated December 22, 1997

(for Model 1121, 1121A, and 1121B

series airplanes); Westwind Service

Bulletin SB 1123–27–047, dated

September 1, 1997 (for Model 1123

series airplanes); or Westwind Service

Bulletin 1124–27–136, dated September

1, 1997 (for Model 1124 and 1124A

series airplanes). These service bulletins

were described previously in AD 98–

05–09.

The FAA’s determination to require

accomplishment of the terminating

modification is based on the fact that

the repetitive inspections currently

required by AD 98–05–09 only detect
41738 Federal Register / Vol. 63, No. 150 /Wednesday, August 5, 1998 / Proposed Rules

failures of the jackscrew, rather than

detecting reduced structural integrity of

these parts. That is, the inspections

cannot determine whether cracking

exists that may result in future

structural failure of the horizontal

stabilizer jackscrews. In order to

adequately detect such cracking, a nondestructive test (NDT) inspection

method would be required. However,

use of any NDT inspection method

would necessitate removal and

disassembly of the horizontal stabilizer

in order to gain access to the jackscrews

for such inspection, which would entail

considerable work hours. Additionally,

such inspections would be required to

be accomplished on a repetitive basis.

Therefore, the FAA has determined

that long-term continued operational

safety will be better assured by

replacement of the trim actuator with a

trim actuator having a modified

jackscrew assembly to remove the

source of the problem, rather than by

repetitive inspections. The proposed

replacement requirement is also in

consonance with actions taken by the

Civil Aviation Administration of Israel

(CAAI), which is the airworthiness

authority for Israel. (The CAAI issued

Israeli airworthiness directive 27–97–

09–02 on September 4, 1997, which

requires replacement of the trim

actuator with a modified trim actuator,

in order to assure the 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

supersede AD 98–05–09 to continue to

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. In addition, the proposed AD

would require the eventual replacement

of the trim actuator of the horizontal

stabilizer with a modified trim actuator

with modified jackscrew assemblies,

which would terminate the repetitive

inspection requirements.

The FAA notes that Israeli

airworthiness directive 27–97–09–02,

dated September 4, 1997, includes a

note that references the revised

Instructions for Continued

Airworthiness for inspection

requirements, overhaul requirements,

and service life limitations of the

modified trim actuator and its modified

jackscrew assemblies and other parts.

The FAA is considering further

rulemaking to mandate compliance with

the new inspections and life limitations

requirements.

Cost Impact

There are approximately 295

airplanes of U.S. registry that would be

affected by this proposed AD.

The inspections that are currently

required by AD 98–05–09 take

approximately 4 work hours per

airplane to accomplish, at an average

labor rate of $60 per work hour. Based

on these figures, the cost impact of the

currently required actions on U.S.

operators is estimated to be $70,800, or

$240 per airplane, per inspection cycle.

The new replacement that is proposed

by this AD action would take

approximately 4 work hours per

airplane to accomplish, at an average

labor rate of $60 per work hour.

Required parts would cost

approximately $49,500 per airplane.

Based on these figures, the cost impact

of the replacement proposed by this AD

on U.S. operators is estimated to be

$14,673,300, or $49,740 per airplane.

The cost impact figures discussed

above are based on assumptions that no

operator has yet accomplished any of

the current or 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

removing amendment 39–10370 (63 FR

11106, arch 6, 1998), and by adding a

new airworthiness directive (AD), to

read as follows:

Israel Aircraft Industries (IAI), Ltd.: Docket

98–NM–108–AD. Supersedes AD 98–05–

09, Amendment 39–10370.

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 prevent failure of the trim actuator of

the horizontal stabilizer due to failure of the
Federal Register / Vol. 63, No. 150 /Wednesday, August 5, 1998 / Proposed Rules 41739

jackscrews, which could result in reduced

controllability of the airplane, accomplish

the following:

Restatement of Requirements of Paragraphs

(a) and (b) of AD 98–05–09

(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, or Revision 1,

dated May 28, 1997 (for Model 1121, 1121A,

and 1121B series airplanes); Westwind

Service Bulletin SB 1123–27–046, dated

August 14, 1996, or Revision 1, dated May

28, 1997 (for Model 1123 series airplanes); or

Westwind Service Bulletin SB 1124–27–133,

dated August 14, 1996, or Revision 1, dated

May 28, 1997 (for Model 1124 and 1124A

series airplanes); as applicable; at the time

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 April 10,

1998 (the effective date of AD 98–05–09,

amendment 39–10370): Inspect within 50

flight hours after April 10, 1998. 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 April 10, 1998: Inspect at the

time 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 April 10, 1998. 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 April 10, 1998. 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, or Revision 1, dated May 28, 1997 (for

Model 1121, 1121A, and 1121B series

airplanes); Westwind Service Bulletin SB

1123–27–046, dated August 14, 1996, or

Revision 1, dated May 28, 1997 (for Model

1123 series airplanes); or Westwind Service

Bulletin 1124–27–133, dated August 14,

1996, or Revision 1, dated May 28, 1997 (for

Model 1124 and 1124A series airplanes); as

applicable.

New Requirements of this AD

(c) Within 18 months after the effective

date of this AD, replace the trim actuator of

the horizontal stabilizer with a modified trim

actuator with modified jackscrew assemblies

(part number 21164–362 and –363 for Model

1121, 1121A, and 1121B series airplanes; part

number 21164–360 and –361 for Model 1123

series airplanes; or part number 21164–360

and –361 for Model 1124 and 1124A series

airplanes), in accordance with Commodore

Jet Service Bulletin SB 1121–27–025, dated

December 22, 1997 (for Model 1121, 1121A,

and 1121B series airplanes); Westwind

Service Bulletin SB 1123–27–047, dated

September 1, 1997 (for Model 1123 series

airplanes); or Westwind Service Bulletin SB

1124–27–136, dated September 1, 1997 (for

Model 1124 and 1124A series airplanes); as

applicable. Accomplishment of this

replacement terminates the repetitive

inspections required by 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,

International Branch, ANM–116, 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, International Branch,

ANM–116.

Note 2: Information concerning the

existence of approved alternative methods of

compliance with this AD, if any, may be

obtained from the Manager, International

Branch, ANM–116.

(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.

Note 3: The subject of this AD is addressed

in Israeli airworthiness directive 27–97–09–

02, dated September 4, 1997.

Issued in Renton, Washington, on July 29,

1998.

D. L. Riggin,

Acting Manager, Transport Airplane

Directorate, Aircraft Certification Service.

[FR Doc. 98–20835 Filed 8–4–98; 8:45 am]

BILLING CODE 4910–13–U

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 97–NM–53–AD]

RIN 2120–AA64

Airworthiness Directives; Boeing

Model 767 Series Airplanes

AGENCY: Federal Aviation

Administration, DOT.

ACTION: Notice of proposed rulemaking

(NPRM).

SUMMARY: This document proposes the

adoption of a new airworthiness

directive (AD) that is applicable to

certain Boeing Model 767 series

airplanes. This proposal would require

a detailed visual inspection to detect

corrosion inside the forward trunnion

joint of the main landing gear (MLG);

follow-on actions; and repair, if

necessary. The proposal also provides

for optional terminating action for the

repetitive inspections. This proposal is

prompted by reports of corrosion at the

forward trunnion thrust face, tabs, and

the internal threads of the forward

trunnion of the MLG due to moisture in

the forward trunnion joint. The actions

specified by the proposed AD are

intended to prevent corrosion of the

forward trunnion joint, which could

lead to a stress corrosion fracture of the

forward trunnion and possible

consequent collapse of the MLG.

DATES: Comments must be received by

September 21, 1998.

ADDRESSES: Submit comments in

triplicate to the Federal Aviation

Administration (FAA), Transport

Airplane Directorate, ANM–114,

Attention: Rules Docket No. 97–NM–

53–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

Boeing Commercial Airplane Group,

P.O. Box 3707, Seattle, Washington

98124–2207. This information may be

examined at the FAA, Transport

Airplane Directorate, 1601 Lind

Avenue, SW., Renton, Washington.

FOR FURTHER INFORMATION CONTACT:

James G. Rehrl, Aerospace Engineer,

Airframe Branch, ANM–120S, FAA,

Seattle Aircraft Certification Office,

1601 Lind Avenue, SW., Renton,

Washington; telephone (425) 227–2783;

fax (425) 227–1181.

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