[Federal Register Volume 62, Number 154 (Monday, August 11, 1997)]
[Proposed Rules]
[Pages 42952-42954]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 97-21098]


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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.


[[Page 42953]]


ACTION: Notice of proposed rulemaking (NPRM).

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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

[[Page 42954]]

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.


Sec. 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