AD Amdt-39-10387

[Federal Register Volume 63, Number 49 (Friday, March 13, 1998)]
[Rules and Regulations]
[Pages 12403-12405]
From the Federal Register Online via the Government Publishing Office [<a href="http://www.gpo.gov">www.gpo.gov</a>]
[FR Doc No: 98-6332]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 97-NM-169-AD; Amendment 39-10387; AD 98-06-10]
RIN 2120-AA64


Airworthiness Directives; Israel Aircraft Industries, Ltd., Model 
1121, 1121A, 1121B, 1123, 1124, 1124A, 1125 Westwind Astra, and Astra 
SPX Series Airplanes

AGENCY: Federal Aviation Administration, DOT.

ACTION: Final rule.

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SUMMARY: This amendment adopts a new airworthiness directive (AD), 
applicable to all Israel Aircraft Industries, Ltd., Model 1121, 1121A, 
1121B, 1123, 1124, 1124A, 1125 Westwind Astra, and Astra SPX series 
airplanes, that requires repetitive functional tests for proper 
operation of hydraulic fuses installed in the brake system and 
emergency hydraulic indicating system; and replacement of any 
discrepant hydraulic fuse with a new, improved unit. This amendment is 
prompted by the 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 hydraulic 
fuse to operate properly, due to internal corrosion, in the event of an 
external leak downstream of the fuse, which could result in loss of 
hydraulic systems.

DATES: Effective April 17, 1998.
    The incorporation by reference of certain publications listed in 
the regulations is approved by the Director of the Federal Register as 
of April 17, 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 Israel Aircraft Industries, 
Ltd., Model 1121, 1121A, 1121B, 1123, 1124, 1124A, 1125 Westwind Astra, 
and Astra SPX series airplanes was published in the Federal Register on 
January 13, 1998 (63 FR 1930). That action proposed to require 
repetitive functional tests for proper operation of hydraulic fuses 
installed in the brake system and emergency hydraulic indicating 
system; and replacement of any discrepant hydraulic fuse with a new, 
improved unit.

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.

Interim Action

    This is considered to be interim action until final action is 
identified, at which time the FAA may consider further rulemaking.

[[Page 12404]]

Cost Impact

    The FAA estimates that 359 airplanes of U.S. registry will be 
affected by this AD, that it will take approximately 2 work hours per 
airplane to accomplish the required functional test, and that the 
average labor rate is $60 per work hour. Based on these figures, the 
cost impact of the AD on U.S. operators is estimated to be $43,080, or 
$120 per airplane, per functional test.
    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.

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:

98-06-10  Israel Aircraft Industries Ltd.: Amendment 39-10387. 
Docket 97-NM-169-AD.

    Applicability: All Model 1121, 1121A, 1121B, 1123, 1124, 1124A, 
1125 Westwind Astra, and Astra SPX 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 prevent failure of the hydraulic fuse to operate properly in 
the event of an external leak downstream of the fuse, which could 
result in loss of hydraulic systems, accomplish the following:
    (a) For Model 1121, 1121A, 1123, 1124, and 1124A series 
airplanes: Perform a functional test (by measuring fluid loss) for 
proper operation of the hydraulic fuses installed in the brake 
system and emergency hydraulic indicating system in accordance with 
Commodore Jet Service Bulletin 1121-29-022 (for Model 1121, 1121A, 
and 1121B series airplanes), Westwind Service Bulletin SB 1123-29-
045 (for Model 1123 series airplanes), or Westwind Service Bulletin 
SB 1124-29-132 (for Model 1124 and 1124A series airplanes); all 
dated September 11, 1996; as applicable; at the later of the times 
specified in paragraphs (a)(1) and (a)(2) of this AD. Thereafter, 
repeat the inspections at intervals not to exceed 1,200 flight hours 
or 3 years, whichever occurs first.
    (1) Within 250 flight hours or 1 year after the effective date 
of this AD, whichever occurs first. Or,
    (2) Prior to accumulation of 1,200 total flight hours, or within 
3 years since the date of manufacture, whichever occurs first.
    (b) For Model 1125 Westwind Astra and Astra SPX series 
airplanes: Perform a functional test (by measuring fluid loss) for 
proper operation of the hydraulic fuses installed in the brake 
system, in accordance with Astra Service Bulletin 1125-32-154, dated 
September 11, 1996, at the later of the times specified in 
paragraphs (b)(1) and (b)(2) of this AD. Thereafter, repeat the 
inspections at intervals not to exceed 1,000 flight hours or 3 
years, whichever occurs first.
    (1) Within 250 total flight hours or 1 year after the effective 
date of this AD, whichever occurs first. Or,
    (2) Prior to the accumulation of 1,000 total flight hours, or 
within 3 years since the date of manufacture, whichever occurs 
first.
    (c) If, during any inspection required by paragraph (a) or (b) 
of this AD, any discrepancy is found, prior to further flight, 
replace the fuse with a new, improved fuse (part number 713047 with 
suffix ``A'' after the serial number), in accordance with Commodore 
Jet Service Bulletin SB 1121-29-022 (for Model 1121, 1121A, and 
1121B series airplanes), Westwind Service Bulletin SB 1123-29-045 
(for Model 1123 series airplanes), Westwind Service Bulletin SB 
1124-29-132 (for Model 1124 and 1124A series airplanes), or Astra 
Service Bulletin SB 1125-32-154 (for Model 1125 Westwind Astra and 
Astra SPX series airplanes); all dated September 11, 1996; as 
applicable.

    Note 2: Replacement of the fuse in accordance with paragraph (c) 
of this AD does not constitute terminating action for the repetitive 
functional tests required by paragraphs (a) and (b) of this AD.

    (d) As of the effective date of this AD, no person shall install 
on any airplane a hydraulic fuse having part number 713047, unless 
it has a suffix ``A'' after the serial number.
    (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 3: 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 Commodore Jet 
Service Bulletin
SB 1121-29-022, dated September 11, 1996; Westwind Service Bulletin
SB 1123-29-045, dated September 11, 1996; Westwind Service Bulletin
SB 1124-29-132, dated September 11, 1996; and Astra Service Bulletin
SB 1125-32-154, dated September 11, 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 4: The subject of this AD is addressed in Israeli 
airworthiness directive 29-97-03-10, dated March 27, 1997.


[[Page 12405]]


    (h) This amendment becomes effective on April 17, 1998.

    Issued in Renton, Washington, on March 5, 1998.
Darrell M. Pederson,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 98-6332 Filed 3-12-98; 8:45 am]
BILLING CODE 4910-13-P