[Federal Register Volume 60, Number 74 (Tuesday, April 18, 1995)]
[Rules and Regulations]
[Pages 19350-19351]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 95-8830]



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DEPARTMENT OF TRANSPORTATION
14 CFR Part 39

[Docket No. 94-NM-220-AD; Amendment 39-9195; AD 95-08-06]


Airworthiness Directives; Raytheon Corporate Jets Models DH/BH/
HS/BAe 125-1A to -700A Series Airplanes; BAe 125-800A Airplanes; and 
Hawker 800 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 certain Raytheon Corporate Jets Models DH/BH/HS/BAe 125-
1A to -700A series, BAe 125-800A, and Hawker 800 series airplanes, that 
requires replacement of the existing standby static inverter with an 
inverter that incorporates a circuit board assembly sealed with a 
conformal coating. This amendment is prompted by reports of failure of 
the standby static inverter caused by electrical shorting from moisture 
condensing on the printed circuit boards (PCB), due to aberrations in 
the PCB conformal coating. The actions specified by this AD are 
intended to prevent malfunction of the standby static inverter due to 
exposure to moisture caused by inadequate insulation coating of the 
circuit board assembly. Malfunction or failure of the standby static 
inverter, when its use is necessary, could result in the loss of 
electric power for certain equipment critical to safety of flight.

DATES: Effective May 18, 1995.
    The incorporation by reference of certain publications listed in 
the regulations is approved by the Director of the Federal Register as 
of May 18, 1995.

ADDRESSES: The service information referenced in this AD may be 
obtained from Raytheon Corporate Jets, Inc., 3 Bishops Square, St. 
Albans Road West, Hatfield, Hertfordshire AL109NE, United Kingdom. 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: William Schroeder, Aerospace Engineer, 
Standardization Branch, ANM-113, FAA, Transport Airplane Directorate, 
1601 Lind Avenue, SW., Renton, Washington 98055-4056; telephone (206) 
227-2148; fax (206) 227-1320.

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 certain Raytheon Corporate Jets 
Models DH/BH/HS/BAe 125-1A to -700A series airplanes, BAe 125-800A 
airplanes, and Hawker 800 airplanes was published in the Federal 
Register on January 18, 1995 (60 FR 3592). That action proposed to 
require replacement of the existing standby static inverters with a 
printed circuit board assembly that is properly sealed with a conformal 
coating.
    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.
    For clarification purposes, the FAA has revised the references to 
the DH/BH/HS/BAe 125 models throughout this rule to add the model 
designator ``A'' to the series numbers. Models DH/BH/HS/BAe 125-1A 
through -700A are the models that are type certificated for operation 
in the United States and, accordingly, affected by this AD action.
     After careful review of the available data, the FAA has 
determined that air safety and the public interest require the adoption 
of the rule with the clarifying change previously described. The FAA 
has determined that this change will neither increase the economic 
burden on any operator nor increase the scope of the AD.
    The FAA estimates that 450 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 actions, and that the average labor 
rate is $60 per work hour. Required parts will cost approximately $410 
per airplane. Based on these figures, the total cost impact of the AD 
on U.S. operators is estimated to be $292,500, or $650 per airplane.
    The total cost impact figure discussed above is based on 
assumptions that no operator has yet accomplished any of 
[[Page 19351]] the requirements of this AD action, and that no operator 
would accomplish those actions in the future if this AD were not 
adopted.
    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. App. 1354(a), 1421 and 1423; 49 U.S.C. 
106(g); and 14 CFR 11.89.


Sec. 39.13  [Amended]

    2. Section 39.13 is amended by adding the following new 
airworthiness directive:

95-08-06  Raytheon Corporate Jets, Inc. (Formerly de Havilland; 
Hawker Siddeley; British Aerospace, plc): Amendment 39-9195. Docket 
94-NM-220-AD.

    Applicability: Model DH/BH/HS/BAe 125-1A to -700A series 
airplanes, inclusive, on which Modification 252740 has been 
installed; Model BAe 125-800A airplanes having constructor's numbers 
prior to number 258248; and Hawker 800 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 use the authority 
provided in paragraph (b) to request approval from the FAA. This 
approval may address either no action, if the current configuration 
eliminates the unsafe condition; or different actions necessary to 
address the unsafe condition described in this AD. Such a request 
should include an assessment of the effect of the changed 
configuration on the unsafe condition addressed by this AD. In no 
case does the presence of any modification, alteration, or repair 
remove any airplane from the applicability of this AD.

    Compliance: Required as indicated, unless accomplished 
previously.
    To prevent an electrical short in the standby static inverter 
due to the printed circuit boards being exposed to condensed 
moisture, accomplish the following: -
    (a) Within 5 months of the effective date of this AD, remove the 
existing standby static inverter (type PC 250) and replace it with a 
Mod C Marathon/Flitetronics Inverter (type PC 250), in accordance 
with Raytheon Corporate Jets Hawker Service Bulletin SB.24-308-
7673A, Revision 1, dated July 11, 1994.
    (b) 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, FAA, 
Transport Airplane Directorate, ANM-113. 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.

    (c) 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.
    (d) The replacement shall be done in accordance with Raytheon 
Corporate Jets Hawker Service Bulletin SB.24-308-7673A, Revision 1, 
dated July 11, 1994. 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 Raytheon 
Corporate Jets, Inc., 3 Bishops Square, St. Albans Road West, 
Hatfield, Hertfordshire, AL109NE, United Kingdom. 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.
    (e) This amendment becomes effective on May 18, 1995.

    Issued in Renton, Washington, on April 5, 1995.
S.R. Miller,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 95-8830 Filed 4-17-95; 8:45 am]
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