[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]


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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.

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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