[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
