[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]
-----------------------------------------------------------------------
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.
-----------------------------------------------------------------------
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]
BILLING CODE 4910-13-U