[Federal Register Volume 65, Number 7 (Tuesday, January 11, 2000)]
[Rules and Regulations]
[Pages 1538-1540]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 00-375]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 99-NM-80-AD; Amendment 39-11499; AD 2000-01-02]
RIN 2120-AA64


Airworthiness Directives; Raytheon Model BAe.125 Series 1000A and 
1000B Airplanes and 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 all Raytheon Model BAe.125 series 1000A and 1000B 
airplanes and Model Hawker 1000 series airplanes, that requires an 
inspection to determine the integrity of the duct connection on both 
ends of the turbine air discharge duct in the air conditioning system; 
an inspection to measure the bead height on the ends of the turbine air 
discharge duct; and corrective actions, if necessary. This amendment is 
prompted by reports indicating that the turbine air discharge duct 
disconnected from the cold air unit (CAU) or water separator due to 
insufficient bead height on the ends of the turbine air discharge duct. 
The actions specified by this AD are intended to prevent such 
disconnection from the CAU or water separator, which could result in 
cabin depressurization.

DATES: Effective February 15, 2000.
    The incorporation by reference of certain publications listed in 
the regulations is approved by the Director of the Federal Register as 
of February 15, 2000.

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, 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: Paul C. DeVore, Aerospace Engineer, 
Systems and Propulsion Branch, ACE-116W, FAA, Small Airplane 
Directorate, Wichita Aircraft Certification Office, 1801 Airport Road, 
Room 100, Mid-Continent Airport, Wichita, Kansas

[[Page 1539]]

67209; telephone (316) 946-4142; 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 all Raytheon Model BAe.125 series 
1000A and 1000B airplanes and Model Hawker 1000 series airplanes was 
published in the Federal Register on October 14, 1999 (64 FR 55638). 
That action proposed to require an inspection to determine the 
integrity of the duct connection on both ends of the turbine air 
discharge duct in the air conditioning system; an inspection to measure 
the bead height on the ends of the turbine air discharge duct; 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 52 airplanes of the affected design in the 
worldwide fleet. The FAA estimates that 35 airplanes of U.S. registry 
will be affected by this AD, that it will take approximately 9 work 
hours per airplane to accomplish the required actions, 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 $18,900, or 
$540 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 a substantial direct 
effect 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, it 
is determined that this final rule does not have federalism 
implications under Executive Order 13132.
    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:

2000-01-02 Raytheon Aircraft Company (Formerly Beech): Amendment 39-
11499. Docket 99-NM-80-AD.

    Applicability: All Model BAe.125 series 1000A and 1000B 
airplanes and Model Hawker 1000 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 (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 the turbine air discharge duct in the air 
conditioning system from disconnecting from the CAU or water 
separator in flight, which could result in cabin depressurization, 
accomplish the following:

Inspections

    (a) Within 25 flight hours after the effective date of this AD, 
perform a general visual inspection to determine the integrity of 
the duct connections (i.e., ensure that the duct and securing clamps 
are in place, the sleeve is central to the joint gap, and the clamps 
are clear of the duct bead) on both ends of the turbine air 
discharge duct in accordance with Raytheon Service Bulletin SB 21-
3108, dated November 1998. If any discrepancy is detected, prior to 
further flight, adjust the clamps in accordance with the service 
bulletin.

    Note 2: For the purposes of this AD, a general visual inspection 
is defined as: ``A visual examination of an interior or exterior 
area, installation, or assembly to detect obvious damage, failure, 
or irregularity. This level of inspection is made under normally 
available lighting conditions such as daylight, hangar lighting, 
flashlight, or drop-light, and may require removal or opening of 
access panels or doors. Stands, ladders, or platforms may be 
required to gain proximity to the area being checked.''

    (b) Within 300 flight hours or 6 months after the effective date 
of this AD, whichever occurs first, perform a one-time detailed 
inspection to measure the bead height on the ends of the turbine air 
discharge duct in accordance with Raytheon Service Bulletin SB 21-
3108, dated November 1998. If the bead height does not conform to 
the dimension shown in the service bulletin, prior to further 
flight, either rework the duct or replace the duct with a new duct, 
in accordance with the service bulletin.

    Note 3: For the purposes of this AD, a detailed 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.''

Spares

    (c) As of the effective date of this AD, no person shall install 
a turbine air discharge duct, part number 25-9VF425-1A, on any 
airplane, unless that duct has been inspected in accordance with 
Part II of Raytheon Service Bulletin SB 21-3108, dated November 
1998.

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 Aircraft Certification 
Office (ACO), FAA, Small 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, Wichita ACO.

    Note 4: Information concerning the existence of approved 
alternative methods of compliance with this AD, if any, may be 
obtained from the Wichita ACO.

[[Page 1540]]

Special Flight Permits

    (e) Special flight permits may be issued in accordance with 
Secs. 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) The actions shall be done in accordance with Raytheon 
Service Bulletin SB 21-3108, dated November 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 February 15, 2000.

    Issued in Renton, Washington, on January 3, 2000.
Donald L. Riggin,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 00-375 Filed 1-10-00; 8:45 am]
BILLING CODE 4910-13-U