[Federal Register Volume 63, Number 44 (Friday, March 6, 1998)]
[Rules and Regulations]
[Pages 11106-11108]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 98-5348]
[[Page 11106]]
=======================================================================
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. 97-NM-166-AD; Amendment 39-10370; AD 98-05-09]
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.
-----------------------------------------------------------------------
SUMMARY: This amendment adopts a new airworthiness directive (AD),
applicable to all IAI, Ltd., Model 1121, 1121A, 1121B, 1123, 1124, and
1124A series airplanes, that 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. This amendment is prompted by
issuance of mandatory continued airworthiness information by a foreign
civil airworthiness authority. The actions specified by this 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: Effective April 10, 1998.
The incorporation by reference of certain publications listed in
the regulations is approved by the Director of the Federal Register as
of April 10, 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) to include an airworthiness
directive (AD) that is applicable to all IAI, Ltd., Model 1121, 1121A,
1121B, 1123, 1124, and 1124A series airplanes was published in the
Federal Register on August 11, 1997 (62 FR 42952). That action proposed
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.
Interested persons have been afforded an opportunity to participate
in the making of this amendment. Due consideration has been given to
the comments received.
Requests to Mandate Modifications
One commenter requests that the FAA not issue this AD, but instead
issue an AD to require replacement of the trim actuator of the
horizontal stabilizer. This commenter notes that a modification to the
jackscrew threads has been identified, which will reduce stress
concentration at the thread root and would eliminate the need to
conduct the inspections of the jackscrews. The commenter further notes
that, since the issuance of the proposed rule, Galaxy Aerospace
Corporation has issued Westwind Service Bulletins SB 1123-27-047 (for
Model 1123 series airplanes) and SB 1124-27-136 (for Model 1124 and
1124A series airplanes), both dated September 1, 1997. The commenter
also notes that Galaxy Aerospace Corporation is scheduled to issue
Commodore Jet Service Bulletin SB 1121-27-025 (for Model 1121, 1121A,
and 1121B series airplanes) in December 1997. These three service
bulletins describe procedures for replacement of the trim actuators of
the horizontal stabilizer with modified trim actuators containing
jackscrews with modified threads. The commenter considers that
accomplishment of these service bulletins provides a more effective
means to resolve the safety of flight issues.
The FAA concurs partially with the commenter's request. Since the
issuance of the proposed rule, Galaxy Aerospace Corporation has issued
Service Bulletin SB 1121-27-025, dated December 22, 1997. The FAA
agrees that replacement of the trim actuator of the horizontal
stabilizer with a modified trim actuator in accordance with the
procedures described in the three service bulletins referenced
previously provides a more effective means to prevent failure of the
trim actuator jackscrews and would eliminate the need for the
repetitive inspections required by this AD. Therefore, the final rule
has been revised to include the replacement of the trim actuator as an
optional terminating action.
However, the FAA does not agree that this AD, which would require
inspections, should be withdrawn. Rather, the FAA considers that,
consistent with the actions taken by the Civil Aviation Administration
of Israel (CAAI), and due to the urgency of the problem, the
inspections must be performed as an interim action to ensure safe
operation. Although the replacement of the trim actuator is provided as
an optional terminating action in this final rule, the FAA is
considering further rulemaking to require replacement of the trim
actuator on all affected airplanes. The FAA notes that Israeli
airworthiness directive 27-97-09-02 was issued on September 4, 1997.
That airworthiness directive requires replacement of the trim actuator
with a modified trim actuator in accordance with the service bulletins
defined above, and specifies that the replacement of the trim actuator
is terminating action for the repetitive inspections required by
Israeli airworthiness directive 96-92 dated September 1, 1996, which is
the Israeli airworthiness directive addressed by this AD.
Request To Not Mandate Modifications
One commenter supports the requirement of the proposed AD to
perform repetitive inspections of the jack screws and tie rods of the
trim actuator of the horizontal stabilizer. However, this commenter
(and several others) object to any plans to mandate replacement of the
trim actuators. The commenter notes that it is only aware of one
cracked eye bolt that was found during inspections of the trim
actuators. The commenter also notes that some of the modified trim
actuators were obtained from non-operable aircraft in salvage yards,
and that it believes that the trim actuator could be rebuilt to meet
the specifications for much less cost than the price quoted in the
service bulletins. The commenter considers that the replacement of the
trim actuators is driven by money issues and not safety issues. Other
commenters consider the replacement too costly. Another commenter notes
that both broken jack screws were found on airplanes operated by the
same flight department, and that this may not be a fleet-wide problem.
The FAA points out that this AD does not mandate replacement of the
trim actuators of the horizontal stabilizer, but rather now provides
for optional terminating action to replace the trim actuators. However,
as stated above, the FAA is considering further rulemaking
[[Page 11107]]
to require replacement of the trim actuators on all affected airplanes.
The FAA will consider the remarks submitted by these commenters, and
will determine whether other options are available to address the
identified unsafe conditions. In addition, under the provisions of
paragraph (e) of this final rule, the FAA may approve requests for
approval of an alternative method of compliance for the requirements of
this AD, if data are submitted to substantiate that accomplishment of
such actions would provide an acceptable level of safety.
Request To Include Later Revisions of the Service Information
One commenter requests that the AD be revised to include an option
to inspect the jackscrews of the trim actuator in accordance with
Revision 1 of the service bulletins referenced in the proposed AD. The
commenter notes that the service bulletins referenced in the proposed
AD have been revised to permit use of alternative sealants during
reassembly following inspection.
The FAA concurs with the commenter's request, and has revised this
final rule to include an option to comply with Revision 1 of the
service bulletins.
Request To Change Name and Address of Service Information Source
One commenter requests that the AD be revised to change the name
and address where service information can be obtained. The commenter
notes that Astra Jet Corporation no longer provides support for these
aircraft, and that all references to Astra Jet Corporation should be
changed to ``Galaxy Aerospace Corporation.'' The commenter further
notes that, effective October 13, 1997, the new address for customer
service and product support for IAI products is: Galaxy Aerospace
Corporation, One Galaxy Way, Fort Worth Alliance Airport, Fort Worth,
Texas 76177. The FAA concurs, and has revised this final rule
accordingly.
Conclusion
After careful review of the available data, including the comments
noted above, the FAA has determined that air safety and the public
interest require the adoption of the rule with the changes previously
described. The FAA has determined that these changes will neither
increase the economic burden on any operator nor increase the scope of
the AD.
Cost Impact
The FAA estimates that 292 airplanes of U.S. registry will be
affected by this AD, that it will take approximately 4 work hours per
airplane to accomplish the required inspection, and that the average
labor rate is $60 per work hour. Based on these figures, the cost
impact of the inspection required by this 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 requirements of this AD
action, and that no operator would accomplish those actions in the
future if this AD were not adopted.
Should an operator elect to accomplish the optional terminating
action rather than continue the repetitive inspections, it would take
approximately 4 work hours per airplane to accomplish the replacement,
at an average labor rate of $60 per work hour. Required parts would
cost approximately $44,350 per airplane. Based on these figures, the
cost impact of this optional terminating action is estimated to be
$44,590 per airplane.
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 adding the following new
airworthiness directive:
98-05-09 Israel Aircraft Industries (IAI), Ltd.: Amendment 39-
10370. 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 (e) 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, 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, 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; 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 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
[[Page 11108]]
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, 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.
(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) Replacement of the trim actuator of the horizontal
stabilizer with a modified trim actuator with modified jackscrew
assemblies 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 1124-27-136, dated September 1, 1997 (for
Model 1124 and 1124A series airplanes), as applicable; constitutes
terminating action for the requirements of this AD.
(e) 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 International Branch, ANM-116.
(f) 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.
(g) The actions shall be done in accordance with the following
service bulletins, which contain the specified effective pages:
----------------------------------------------------------------------------------------------------------------
Page number
Service bulletin referenced and shown on Revision level shown on page Date shown on page
date page
----------------------------------------------------------------------------------------------------------------
Westwind, SB 1124-27-133, August 1-6 Original......................... Aug. 14, 1996.
14, 1996.
Westwind, SB 1124-27-133, Revision 1-4 1................................ May 28, 1997.
1, May 28, 1997.
5, 6 Original......................... Aug. 14, 1996.
Westwind, SB 1123-27-046, August 1-6 Original......................... Aug. 14, 1996.
14, 1996.
Westwind, SB 1124-27-046, Revision 1-4 1................................ May 28, 1997.
1, May 28, 1997.
5, 6 Original......................... Aug. 14, 1996.
Westwind, SB 1124-27-136, September 1-3 Original......................... Sept. 1, 1997.
1, 1997.
Westwind, SB 1123-27-047, September 1-3 Original......................... Sept. 1, 1997.
1, 1997.
Commodore Jet, SB 1121-27-025, 1-3 Original......................... Dec. 22, 1997.
December 22, 1997.
Commodore Jet, SB 1121-27-023, 1-6 Original......................... Aug. 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......................... Aug. 14, 1996.
----------------------------------------------------------------------------------------------------------------
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 3: The subject of this AD is addressed in Israeli
airworthiness directive 96-92, dated September 1, 1996.
(h) This amendment becomes effective on April 10, 1998.
Issued in Renton, Washington, on February 24, 1998.
Darrell M. Pederson,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 98-5348 Filed 3-5-98; 8:45 am]
BILLING CODE 4910-13-U
