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

[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.

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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

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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