[Federal Register Volume 63, Number 188 (Tuesday, September 29, 1998)]
[Rules and Regulations]
[Pages 51803-51805]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 98-25776]



[[Page 51803]]

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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 98-NM-108-AD; Amendment 39-10802; AD 98-20-35]
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: Final rule.

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SUMMARY: This amendment supersedes 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 amendment requires accomplishment of the previously 
optional terminating action. This amendment is prompted by issuance of 
mandatory continuing airworthiness information by a foreign civil 
airworthiness authority. The actions specified by this 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: Effective November 3, 1998.
    The incorporation by reference of certain publications was approved 
previously by the Director of the Federal Register as of April 10, 1998 
(63 FR 11106, March 6, 1998).

ADDRESSES: 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 Federal Aviation Administration (FAA), Transport 
Airplane Directorate, Rules Docket, 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: 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: A proposal to amend part 39 of the Federal 
Aviation Regulations (14 CFR part 39) by superseding AD 98-05-09, 
amendment 39-10370 (63 FR 11106, March 6, 1998), which is applicable to 
all IAI, Ltd., Model 1121, 1121A, 1121B, 1123, 1124, and 1124A series 
airplanes, was published in the Federal Register on August 5, 1998 (63 
FR 41737). The action proposed 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. The action also 
proposed to require accomplishment of a previously optional terminating 
action.

Comments

    Interested persons have been afforded an opportunity to participate 
in the making of this amendment. No comments were submitted in response 
to the proposal or the FAA's determination of the cost to the public.

Conclusion

    The FAA has determined that air safety and the public interest 
require the adoption of the rule as proposed.

Cost Impact

    There are approximately 295 airplanes of U.S. registry that will be 
affected by this 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 required by this AD action will take 
approximately 4 work hours per airplane to accomplish, at an average 
labor rate of $60 per work hour. Required parts will cost approximately 
$49,500 per airplane. Based on these figures, the cost impact of the 
replacement required 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 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 adopted herein will 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 final 
rule does not have sufficient federalism implications to warrant the 
preparation of a Federalism Assessment.
    For the reasons discussed above, I certify that this action (1) is 
not a ``significant regulatory action'' under Executive Order 12866; 
(2) is not a ``significant rule'' under DOT Regulatory Policies and 
Procedures (44 FR 11034, February 26, 1979); and (3) 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 final evaluation has been prepared for this action 
and it is contained in the Rules Docket. A copy of it 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:

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 removing amendment 39-10370 (63 FR 
11106, March 6, 1998), and by adding a new airworthiness directive 
(AD), amendment 39-10802, to read as follows:
98-20-35  Israel Aircraft Industries (IAI), Ltd.: Amendment 39-
10802. 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

[[Page 51804]]

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 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.
    (f) The actions shall be done in accordance with the following 
Westwind and Commodore Jet service bulletins, as applicable, which 
contain the specified effective pages:

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  Service bulletin referenced and
                date                         Page number shown on page               Revision level shown on page              Date shown on page
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Westwind, SB 1124-27-133, August     1-6.....................................  Original...............................  August 14, 1996.
 14, 1996.
Westwind, SB 1124-27-133, Revision   1-4.....................................  1......................................  May 28, 1997.
 1, May 28, 1997.                    5, 6....................................  Original...............................  August 14, 1996.
Westwind, SB 1123-27-046, August     1-6.....................................  Original...............................  August 14, 1996.
 14, 1996.
Westwind, SB 1124-27-046, Revision   1-4.....................................  1......................................  May 28, 1997.
 1, May 28, 1997.                    5, 6....................................  Original...............................  August 14, 1996.
Westwind, SB 1124-27-136, September  1-3.....................................  Original...............................  September 1, 1997.
 1, 1997.
Westwind, SB 1123-27-047, September  1-3.....................................  Original...............................  September 1, 1997.
 1, 1997.
Commodore Jet, SB 1121-27-025,       1-3.....................................  Original...............................  December 22, 1997.
 December 22, 1997.
Commodore Jet, SB 1121-27-023,       1-6.....................................  Original...............................  August 14, 1996.
 August 14, 1996.
Commodore Jet, SB 1121-27-023,       1-4.....................................  1......................................  May 28, 1997.
 Revision 1, May 28, 1997.           5, 6....................................  Original...............................  August 14, 1996.
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[[Page 51805]]

    The incorporation by reference was approved previously by the 
Director of the Federal Register as of April 10, 1998 (63 FR 11106, 
March 6, 1998). 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 3: The subject of this AD is addressed in Israeli 
airworthiness directive 27-97-09-02, dated September 4, 1997.

    (g) This amendment becomes effective on November 3, 1998.

    Issued in Renton, Washington, on September 21, 1998.

Darrell M. Pederson,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 98-25776 Filed 9-28-98; 8:45 am]
BILLING CODE 4910-13-U