[Federal Register Volume 65, Number 210 (Monday, October 30, 2000)]
[Rules and Regulations]
[Pages 64602-64604]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 00-27631]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 99-NM-376-AD; Amendment 39-11949; AD 2000-22-03]
RIN 2120-AA64


Airworthiness Directives; Raytheon Model DH.125, Model HS.125, 
Model BH.125, Model BAe.125 Series 800A (Including Major Variants C-29A 
and U1-25), Model Hawker 800, Model Hawker 800XP, 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 certain Raytheon Model DH.125, Model HS.125, Model 
BH.125, Model BAe.125 Series 800A, Model Hawker 800, Model Hawker 
800XP, and Model Hawker 1000 series airplanes, that requires leak 
checks and inspections for corrosion of the pitot/static and stall vent 
drain valves, and replacement of certain components, if necessary. This 
amendment is prompted by reports of plugged or taped drain valves as 
well as consequent corrosion of certain drain valves. The actions 
specified by this AD are intended to prevent erroneous altimeter and 
airspeed indications due to plugged or taped pitot/static and stall 
vent drain valves.

DATES: Effective December 4, 2000.
    The incorporation by reference of certain publications listed in 
the regulations is approved by the Director of the Federal Register as 
of December 4, 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, Wichita 
Aircraft Certification Office, 1801 Airport Road, Room 100, Mid-

[[Page 64603]]

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 DeVore, Aerospace Engineer, 
Systems and Propulsion Branch, ACE-116W, FAA, Wichita, Kansas 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 certain Raytheon Model DH.125, 
Model HS.125, Model BH.125, Model BAe.125 Series 800A, Model Hawker 
800, Model Hawker 800XP, and Model Hawker 100 series airplanes was 
published in the Federal Register on June 19, 2000 (65 FR 37922). That 
action proposed to require leak checks and inspections for corrosion of 
the pitot/static and stall vent drain valves, and replacement of 
certain components, 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 900 airplanes of the affected design in the 
worldwide fleet. The FAA estimates that 585 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. Based on these figures, the 
cost impact of the AD on U.S. operators is estimated to be $140,400, or 
$240 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. The cost impact figures discussed 
in AD rulemaking actions represent only the time necessary to perform 
the specific actions actually required by the AD. These figures 
typically do not include incidental costs, such as the time required to 
gain access and close up, planning time, or time necessitated by other 
administrative actions.

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:

2000-22-03 Raytheon Aircraft Co. (Formerly Beech): Amendment 39-
11949. Docket 99-NM-376-AD.

    Applicability: Model DH.125, Model HS.125, Model BH.125, Model 
BAe.125, Model Hawker 800, Model Hawker 800XP, and Model Hawker 1000 
series airplanes; as listed in Raytheon Aircraft Service Bulletin SB 
34-3207, dated August 1999; excluding those airplanes on which all 
pitot/static drain vent valves have been modified with an insert in 
accordance with Raytheon Aircraft Repair Design Office instructions; 
certificated in any category.

    Note 1: This AD applies to each airplane identified in the 
preceding applicability provision, regardless of whether it has been 
otherwise 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 (f) 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 erroneous altimeter and airspeed indications due to 
plugged or taped pitot/static and stall vent drain valves, 
accomplish the following:

Leak Tests

    (a) Within 300 hours time-in-service after the effective date of 
this AD: Drain the pitot/static and stall vent drain valves, and 
perform a leak test of the systems, in accordance with Raytheon 
Aircraft Service Bulletin SB 34-3207, dated August 1999. If all 
drain valves are operating correctly and the leak test is passed 
successfully, thereafter, repeat the leak test at intervals not to 
exceed 300 hours time-in-service.

Drain Valves Operative, Leak Test Failed

    (b) If all drain valves are operative, but any valve does not 
pass the leak test required by paragraph (a) of this AD: Prior to 
further flight, accomplish the actions specified in paragraph 
(b)(1), (b)(2), or (b)(3) of this AD.
    (1) Apply a temporary seal of the drain valve(s) in accordance 
with Raytheon Aircraft Service Bulletin SB 34-3223, dated August 
1999. Within 300 hours time-in-service after the accomplishment of 
the temporary seal, accomplish the requirements of paragraph (b)(2) 
or (b)(3) of this AD.
    (2) Replace the drain valve components with new or serviceable 
drain valve components in accordance with Raytheon Aircraft Service 
Bulletin SB 34-3207, dated August 1999, and perform the leak test 
specified in paragraph (a) of this AD. Thereafter, repeat the 
requirements of paragraph (a) of this AD at intervals not to exceed 
300 hours time-in-service.
    (3) Modify the drain valves in accordance with Raytheon Aircraft 
Service Bulletin SB 34-3282, dated August 1999. Thereafter, repeat 
the requirements of paragraph (a) of this AD at intervals not to 
exceed 300 hours time-in-service unless all the drain valves have 
been modified. Accomplishment of this modification on ALL drain 
valves constitutes terminating action for the requirement to perform 
repetitive leak tests.

Drain Valves Inoperative

    (c) If any drain valve is inoperative (e.g., plugged or taped), 
whether or not any leaking is detected: Prior to further flight, 
disassemble the valve and clean all obstructions in accordance with 
Raytheon Aircraft Service Bulletin SB 34-3207, dated August 1999, 
and perform a general visual inspection for corrosion of the drain 
valve.


[[Page 64604]]


    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 droplight, 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.''

    (d) If no corrosion of the drain valves is detected, prior to 
further flight, perform the actions specified in either paragraph 
(d)(1) or (d)(2) of this AD at the time specified.
    (1) Perform the leak test specified in paragraph (a) of this AD, 
and thereafter, repeat the leak test requirements at intervals not 
to exceed 300 hours time-in-service.
    (2) Prior to further flight, modify any inoperative valve in 
accordance with Raytheon Aircraft Service Bulletin SB 34-3282, dated 
August 1999. Thereafter, repeat the leak test requirements of 
paragraph (a) of this AD at intervals not to exceed 300 hours time-
in-service. Modification of ALL the drain valves constitutes 
terminating action for the requirement to perform repetitive leak 
tests.
    (e) If any drain valve is corroded, prior to further flight: 
Inspect the connecting tubing for corrosion and replace any corroded 
valve or tubing with a new or serviceable valve or tubing in 
accordance with Raytheon Aircraft Service Bulletin SB 34-3207, dated 
August 1999. Accomplish the actions of paragraph (e)(1) or (e)(2) of 
the AD at the time specified.
    (1) Prior to further flight, perform the leak test specified in 
paragraph (a) of this AD, and thereafter, repeat the leak test 
requirements of paragraph (a) of this AD at intervals not to exceed 
300 hours time-in-service.
    (2) Prior to further flight, modify any replaced drain valve in 
accordance with Raytheon Aircraft Service Bulletin SB 34-3282, dated 
August 1999. Thereafter, repeat the leak test requirements of 
paragraph (a) of this AD at intervals not to exceed 300 hours time-
in-service. Modification of ALL the drain valves constitutes 
terminating action for the requirement to perform repetitive leak 
tests.

Alternative Methods of Compliance

    (f) 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), ACE-116W, FAA. 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 Permit

    (g) 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

    (h) The actions shall be done in accordance with Raytheon 
Aircraft Service Bulletin SB 34-3207, dated August 1999; Raytheon 
Aircraft Service Bulletin SB 34-3223, dated August 1999; or Raytheon 
Aircraft Service Bulletin SB 34-3282, dated August 1999; as 
applicable. 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, 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.

Effective Date

    (i) This amendment becomes effective on December 4, 2000.


    Issued in Renton, Washington, on October 23, 2000.
Donald L. Riggin,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 00-27631 Filed 10-27-00; 8:45 am]
BILLING CODE 4910-13-U