[Federal Register Volume 64, Number 218 (Friday, November 12, 1999)]
[Rules and Regulations]
[Pages 61482-61484]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 99-29053]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. 99-NM-156-AD; Amendment 39-11406; AD 99-23-10]
RIN 2120-AA64
Airworthiness Directives; Raytheon Model Hawker 1000 Series
Airplanes
AGENCY: Federal Aviation Administration, DOT.
ACTION: Final rule.
-----------------------------------------------------------------------
SUMMARY: This amendment adopts a new airworthiness directive (AD),
applicable to certain Raytheon Model Hawker 1000 series airplanes, that
requires a visual inspection of the PS wire bundle, shielded wires
going to fuel probe `G,' and any other wire or wire bundle for chafing
in the forward wing spar and forward ventral tank area; and corrective
actions, if necessary. This amendment is prompted by reports indicating
that, due to improper routing of a wire bundle, the wire bundle chafed
against the forward ventral tank transfer/crossfeed valve, which caused
an electrical short and resulted in failure of the landing light. The
actions specified by this AD are intended to prevent a short circuit
due to wire chafing, which can cause a fire in the ventral fuel tank
area.
DATES: Effective December 17, 1999.
The incorporation by reference of certain publications listed in
the regulations is approved by the Director of the Federal Register as
of December 17, 1999.
ADDRESSES: The service information referenced in this AD may be
obtained from Raytheon Aircraft Company, Manager Service Engineering,
Hawker Customer Support Department, P.O. Box 85, Wichita, Kansas 67201-
0085. 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 FAA, Transport
Airplane Directorate, 1601 Lind Avenue, SW., Renton, Washington; or at
the FAA, Small Airplane Directorate, Wichita Aircraft Certification
Office, 1801 Airport Road, Room 100, Mid-Continent Airport, Wichita,
Kansas; or at the Office of the Federal Register, 800 North Capitol
Street, NW., suite 700, Washington, DC.
FOR FURTHER INFORMATION CONTACT: Philip Petty, Aerospace Engineer,
Systems and Propulsion Branch, ACE-116W, FAA, Small Airplane
Directorate, Wichita Aircraft Certification Office,
[[Page 61483]]
1801 Airport Road, Room 100, Mid-Continent Airport, Wichita, Kansas
67209; telephone (316) 946-4139; fax (316) 946-4407.
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 Model Hawker 1000
series airplanes was published in the Federal Register on August 20,
1999 (64 FR 45485). That action proposed to require a visual inspection
of the PS wire bundle, shielded wires going to fuel probe `G,' and any
other wire or wire bundle for chafing in the forward wing spar and
forward ventral tank area; and corrective actions, if necessary.
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 91 airplanes of the affected design in the
worldwide fleet. The FAA estimates that 39 airplanes of U.S. registry
will be affected by this AD, that it will take approximately 1 work
hour per airplane to accomplish the actions, at an average labor rate
of $60 per work hour. Based on these figures, the cost impact of this
AD on U.S. operators is estimated to be $2,340, or $60 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.
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:
99-23-10 Raytheon Aircraft Company (Formerly Beech): Amendment 39-
11406. Docket 99-NM-156-AD.
Applicability: Model Hawker 1000 series airplanes, serial
numbers 258151, 258159, and 259003 through 259052 inclusive,
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 (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 a short circuit due to wire chafing, which can cause
a fire in the ventral fuel tank area, accomplish the following:
Inspection and Modification
(a) Within 50 flight hours after the effective date of this AD,
perform a detailed visual inspection of the PS wire bundle coming
from the bung `DF' for chafing against the front ventral tank
transfer/crossfeed actuator, in accordance with Raytheon Aircraft
Service Bulletin SB 24-3201, dated October 1998.
Note 2: For the purposes of this AD, a detailed visual
inspection is defined as: ``An intensive visual examination of a
specific structural area, system, installation, or assembly to
detect damage, failure, or irregularity. Available lighting is
normally supplemented with a direct source of good lighting at
intensity deemed appropriate by the inspector. Inspection aids such
as mirror, magnifying lenses, etc., may be used. Surface cleaning
and elaborate access procedures may be required.''
(1) If no chafing is found, prior to further flight, ensure a
minimum 0.25-inch clearance exists between the PS wire bundle and
valve actuator; and install spiral wrap, as necessary; in accordance
with the service bulletin.
(2) If any chafing is found on a 22, 20, 16, or 14 gauge (non-
shielded) wire, prior to further flight, repair chafed wire by
splicing the damaged section using MIL-S-81824/1 splices; ensure a
minimum 0.25-inch clearance exists between the wire bundle and valve
actuator; and install spiral wrap, as necessary; in accordance with
the service bulletin.
(3) If any chafing is found on a 10 gauge wire, replace the
entire wire with a new 10 gauge wire; ensure a minimum 0.25-inch
clearance exists between the wire bundle and valve actuator; and
install spiral wrap, as necessary; in accordance with the service
bulletin.
(b) Within 50 flight hours after the effective date of this AD,
perform a detailed visual inspection of the shielded wires going to
the fuel probe `G' for chafing against the wing transfer valve
actuator and mounting screws, in accordance with Raytheon Aircraft
Service Bulletin SB 24-3201, dated October 1998.
(1) If no chafing is found, prior to further flight, ensure a
minimum 0.25-inch clearance exists between the wire bundle and valve
actuator; and install spiral wrap, as necessary; in accordance with
the service bulletin.
(2) If any chafing is found, prior to further flight, replace
the entire shielded wire with a new shielded wire; ensure a minimum
0.25-inch clearance exists between the wire bundle and valve
actuator; and install spiral wrap, as necessary; in accordance with
the service bulletin.
(c) Within 50 flight hours after the effective date of this AD,
perform a borescope inspection of the entire forward wing spar/
forward ventral tank area for chafing of any other wire or wire
bundle; and install spiral wrap, as necessary; in accordance with
Raytheon Aircraft Service Bulletin SB 24-3201, dated October 1998.
(1) If no chafing is found, no further action is required by
this AD.
(2) If any chafed wire or wire bundle is found, prior to further
flight, repair in accordance with a method approved by the Manager,
Wichita Aircraft Certification Office (ACO), FAA, Small Airplane
Directorate. For a repair method to be approved by the Manager,
Wichita ACO, as required by this
[[Page 61484]]
paragraph, the Manager's approval letter must specifically reference
this AD.
Alternative Methods of Compliance
(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, Wichita ACO. Operators shall submit
their requests through an appropriate FAA Principal Maintenance
Inspector, who may add comments and then send it to the Manager,
Wichita ACO.
Note 3: Information concerning the existence of approved
alternative methods of compliance with this AD, if any, may be
obtained from the Wichita ACO.
Special Flight Permits
(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.
Incorporation by Reference
(f) Except as provided by paragraph (c)(2) of this AD, the
actions shall be done in accordance with Raytheon Aircraft Service
Bulletin SB 24-3201, dated October 1998. 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 Aircraft Company, Manager Service
Engineering, Hawker Customer Support Department, P.O. Box 85,
Wichita, Kansas 67201-0085. Copies may be inspected at the FAA,
Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton,
Washington; or at the FAA, Small Airplane Directorate, Wichita
Aircraft Certification Office, 1801 Airport Road, Room 100, Mid-
Continent Airport, Wichita, Kansas; or at the Office of the Federal
Register, 800 North Capitol Street, NW., suite 700, Washington, DC.
(g) This amendment becomes effective on December 17, 1999.
Issued in Renton, Washington, on November 1, 1999.
D.L. Riggin,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 99-29053 Filed 11-10-99; 8:45 am]
BILLING CODE 4910-13-P
