[Federal Register Volume 65, Number 223 (Friday, November 17, 2000)]
[Rules and Regulations]
[Pages 69439-69441]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 00-29078]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 2000-NM-364-AD; Amendment 39-11985; AD 2000-23-13]
RIN 2120-AA64


Airworthiness Directives; Israel Aircraft Industries, Ltd., Model 
1121, 1121A, 1121B, 1123, 1124, and 1124A Series Airplanes

AGENCY: Federal Aviation Administration, DOT.

ACTION: Final rule; request for comments.

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SUMMARY: This amendment adopts a new airworthiness directive (AD) that 
is applicable to all Israel Aircraft Industries, Ltd., Model 1121, 
1121A, 1121B, 1123, 1124, and 1124A series airplanes. This action 
requires a one-time inspection, and corrective action if necessary, to 
ensure the proper installation of the tie rod through the dust shield 
and both jackscrew assemblies on the horizontal stabilizer trim 
actuator. This action is necessary to prevent jamming or disconnection 
of the horizontal stabilizer trim actuator, which could result in 
reduced pitch control of the airplane. This action is intended to 
address the identified unsafe condition.

DATES: Effective December 4, 2000.
    The incorporation by reference of certain publications listed in 
the regulations is approved by the Director of the Federal Register as 
of December 4, 2000.
    Comments for inclusion in the Rules Docket must be received on or 
before December 18, 2000.

ADDRESSES: Submit comments in triplicate to the Federal Aviation 
Administration (FAA), Transport Airplane Directorate, ANM-114, 
Attention: Rules Docket No. 2000-NM-364-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.
    Comments may be submitted via fax to (425) 227-1232. Comments may 
also be sent via the Internet using the following address: <a href="/cdn-cgi/l/email-protection#457c68242b28682c2437262a2828202b31052324246b222a33"><span class="__cf_email__" data-cfemail="efd6c28e8182c2868e9d8c8082828a819baf898e8ec1888099">[email protected]</span></a>. Comments sent via fax or the Internet must contain 
``Docket No. 2000-NM-364-AD'' in the subject line and need not be 
submitted in triplicate. Comments sent via the Internet as attached 
electronic files must be formatted in Microsoft Word 97 for Windows or 
ASCII text.
    The service information referenced in this AD 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; or at the Office of the Federal Register, 800 North Capitol 
Street, NW., suite 700, Washington, DC.

FOR FURTHER INFORMATION CONTACT: Tim Dulin, Aerospace Engineer, 
International Branch, ANM-116, FAA, 1601 Lind Avenue, SW., Renton, 
Washington 98055-4056; telephone (425) 227-2141; fax (425) 227-1149.

SUPPLEMENTARY INFORMATION: The Civil Aviation Administration of Israel 
(CAAI), which is the airworthiness authority for Israel, recently 
notified the FAA that an unsafe condition may exist on all Israel 
Aircraft Industries, Ltd., Model 1121, 1121A, 1121B, 1123, 1124, and 
1124A series airplanes. The CAAI advises that the horizontal stabilizer 
trim actuator can jam or disconnect due to incorrect installation, 
maintenance, or inspection. The CAAI reports one case of incorrect 
installation of the trim actuator tie rod and dust shield, which may 
have caused an accident. Jamming or disconnection of the actuator, if 
not corrected, could result in reduced pitch control of the airplane.

Explanation of Relevant Service Information

    Israel Aircraft Industries, Ltd., has issued the following alert 
service bulletins:

[[Page 69440]]



----------------------------------------------------------------------------------------------------------------
            Service bulletin                               Date                                Model
----------------------------------------------------------------------------------------------------------------
1121  Commodore Jet Alert Service         August 28, 2000.......................  1121 JET COMMANDER.
 Bulletin 1121-27A-028.
1123  Westwind Alert Service Bulletin     August 28, 2000.......................  1123 WESTWIND.
 1123-27A-053.
1124  Westwind Alert Service Bulletin     August 28, 2000.......................  1124 and 1124A WESTWIND.
 1124-27A-147.
----------------------------------------------------------------------------------------------------------------

These alert service bulletins describe procedures for a one-time visual 
inspection to determine whether the tie rod is installed correctly 
through the dust shield and both jackscrew assemblies on the horizontal 
stabilizer trim actuator. The inspection includes measuring the 
distance between the bottom of the dust shield and the housing of the 
horizontal stabilizer actuator. The CAAI classified these service 
bulletins as mandatory and issued Israeli airworthiness directive 27-
00-09-01, dated September 24, 2000, to ensure 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 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, this AD is being issued to prevent jamming or 
disconnection of the horizontal stabilizer trim actuator, which could 
result in reduced pitch control of the airplane. This AD requires 
accomplishment of the actions specified in the service bulletins 
described previously, except as discussed below.

Difference Between AD and Relevant Service Information

    Operators should note that, although the alert service bulletins 
specify that the manufacturer may be contacted for disposition of 
certain repair conditions, this AD requires the repair of those 
conditions to be accomplished in accordance with a method approved by 
the FAA or the CAAI. In light of the type of repair that would be 
required to address the identified unsafe condition, and in consonance 
with existing bilateral airworthiness agreements, the FAA has 
determined that, for this AD, a repair approved by either the FAA or 
the CAAI would be acceptable for compliance with this AD.

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.
    Submit comments using the following format:
    <bullet> Organize comments issue-by-issue. For example, discuss a 
request to change the compliance time and a request to change the 
service bulletin reference as two separate issues.
    <bullet> For each issue, state what specific change to the AD is 
being requested.
    <bullet> Include justification (e.g., reasons or data) for each 
request.
    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 No. 2000-NM-364-AD.''
    The postcard will be date stamped and returned to the commenter.

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.
    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:

[[Page 69441]]

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.


Sec. 39.13  [Amended]

    2. Section 39.13 is amended by adding the following new 
airworthiness directive:

2000-23-13 Israel Aircraft Industries, LTD.: Amendment 39-11985. 
Docket 2000-NM-364-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 (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 jamming or disconnection of the horizontal stabilizer 
trim actuator, which could result in reduced pitch control of the 
airplane, accomplish the following:

Inspection

    (a) Within 25 flight hours after the effective date of this AD: 
Perform a detailed visual inspection to determine whether the tie 
rod is installed correctly through the dust shield and both 
jackscrew assemblies of the horizontal stabilizer trim actuator. Do 
the inspection per Israel Aircraft Industries Alert Service 
Bulletins 1121-27A-028 (for 1121 JET COMMANDER series airplanes), 
1123-27A-053 (for 1123 WESTWIND series airplanes), or 1124-27A-147 
(for 1124 and 1124A WESTWIND series airplanes); all dated August 28, 
2000; as applicable.

    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.''

    (1) If both the tie rod and the dust shield are correctly 
assembled: No further action is required by this AD.
    (2) If either the tie rod or the dust shield is not correctly 
assembled: Prior to further flight, accomplish the actions specified 
by either paragraph (a)(2)(i) or (a)(2)(ii).
    (i) Replace the horizontal stabilizer trim actuator with a 
serviceable part in accordance with the airplane maintenance manual. 
Or
    (ii) Repair the horizontal stabilizer trim actuator in 
accordance with a method approved by the Manager, International 
Branch, ANM-116, FAA, Transport Airplane Directorate; or the Civil 
Aviation Administration of Israel (CAAI) (or its delegated agent). 
For a repair method to be approved by the Manager, International 
Branch, ANM-116, as required by this paragraph, the Manager's 
approval letter must specifically reference this AD.

Spares

    (b) As of the effective date of this AD, no person shall install 
a horizontal stabilizer trim actuator on any airplane, unless the 
actuator has been inspected and all applicable corrective actions 
have been performed in accordance with the requirements of this AD.

Alternative Methods of Compliance

    (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, International Branch, ANM-116. 
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 3: Information concerning the existence of approved 
alternative methods of compliance with this AD, if any, may be 
obtained from the International Branch, ANM-116.

Special Flight Permits

    (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.

Incorporation by Reference

    (e) Except as provided by paragraphs (a)(2)(i) and (a)(2)(ii) of 
this AD: The actions shall be done in accordance with the following 
alert service bulletins:

------------------------------------------------------------------------
          Service bulletin                           Date
------------------------------------------------------------------------
1121  Commodore Jet Alert Service     August 28, 2000.
 Bulletin 1121-27A-028.
1123  Westwind Alert Service          August 28, 2000.
 Bulletin 1123-27A-053.
1124  Westwind Alert Service          August 28, 2000.
 Bulletin 1124-27A-147.
------------------------------------------------------------------------

    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 Galaxy Aerospace Corporation, 
One Galaxy Way, Fort Worth Alliance Airport, Fort Worth, Texas 
76177. Copies may be inspected at the FAA, Transport Airplane 
Directorate, 1601 Lind Avenue, SW., Renton, Washington; or at the 
Office of the Federal Register, 800 North Capitol Street, NW., suite 
700, Washington, DC.

    Note 4: The subject of this AD is addressed in Israeli 
airworthiness directive 27-00-09-01, dated September 24, 2000.

Effective Date

    (f) This amendment becomes effective on December 4, 2000.

    Issued in Renton, Washington, on November 7, 2000.
Donald L. Riggin,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 00-29078 Filed 11-16-00; 8:45 am]
BILLING CODE 4910-13-U


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