[Federal Register Volume 65, Number 118 (Monday, June 19, 2000)]
[Proposed Rules]
[Pages 37922-37924]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 00-15420]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 99-NM-376-AD]
RIN 2120-AA64


Airworthiness Directives; Raytheon Model DH.125, Model HS.125, 
Model BH.125, Model BAe125 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: Notice of proposed rulemaking (NPRM).

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SUMMARY: This document proposes the adoption of a new 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 1000 series airplanes. This 
proposal would require leak checks and inspections for corrosion of the 
pitot/static and stall vent drain valves, and replacement of certain 
components, if necessary. This proposal is prompted by reports of 
plugged or taped drain valves as well as consequent corrosion of 
certain drain valves. The actions specified by the proposed AD are 
intended to prevent erroneous altimeter and airspeed indications due to 
plugged or taped pitot/static and stall vent drain valves.

DATES: Comments must be received by August 3, 2000.

ADDRESSES: Submit comments in triplicate to the Federal Aviation 
Administration (FAA), Transport Airplane Directorate, ANM-114, 
Attention: Rules Docket No. 99-NM-376-AD, 1601 Lind Avenue, SW., 
Renton, Washington 98055-4056. Comments may be inspected at this 
location between 9 a.m. and 3 p.m., Monday through Friday, except 
Federal holidays.
    The service information referenced in the proposed rule 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 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.

FOR FURTHER INFORMATION CONTACT: Paul DeVore, Aerospace Engineer, 
Systems and Propulsion Branch, ACE-116W, FAA, Small Airplane 
Directorate, Wichita, Kansas 672029; telephone (316) 946-4142; fax 
(316) 946-4407.

SUPPLEMENTARY INFORMATION:

Comments Invited

    Interested persons are invited to participate in the making of the 
proposed rule by submitting such written data, views, or arguments as 
they may desire. Communications shall identify the Rules Docket number 
and be submitted in triplicate to the address specified above. All 
communications received on or before the closing date for comments, 
specified above, will be considered before taking action on the 
proposed rule. The proposals contained in this notice may be changed in 
light of the comments received.
    Comments are specifically invited on the overall regulatory, 
economic, environmental, and energy aspects of the proposed rule. All 
comments submitted will be available, both before and after the closing 
date for comments, in the Rules Docket for examination by interested 
persons. A report summarizing each FAA-public contact concerned with 
the substance of this proposal will be filed in the Rules Docket.
    Commenters wishing the FAA to acknowledge receipt of their comments 
submitted in response to this notice must submit a self-addressed, 
stamped postcard on which the following statement is made: ``Comments 
to Docket Number 99-NM-376-AD.'' The postcard will be date stamped and 
returned to the commenter.

Availability of NPRMs

    Any person may obtain a copy of this NPRM by submitting a request 
to the FAA, Transport Airplane Directorate, ANM-114, Attention: Rules 
Docket No. 99-NM-376-AD, 1601 Lind Avenue, SW., Renton, Washington 
98055-4056.

Discussion

    The FAA has received reports of plugged or taped pitot/static and 
stall vent drain valves. The reports indicate that corrosion also was 
detected in some valves. This condition, if not corrected, could result 
in erroneous altimeter and airspeed indications.

Explanation of Relevant Service Information

    The FAA has reviewed and approved Raytheon Aircraft Service 
Bulletin SB 34-3207, dated August 1999, which describes procedures for 
performing repetitive leak checks of the pitot/static

[[Page 37923]]

and stall vent drain valves and inspections for corrosion of the drain 
valve system, and corrective actions, such as replacement of certain 
components of the drain valve system. That service bulletin also 
references the following two service bulletins as additional sources of 
service information.
    Raytheon Aircraft Service Bulletin SB 34-3223, dated August 1999, 
describes the application of a temporary seal for the pitot/static and 
stall vent drain valves.
    Raytheon Aircraft Service Bulletin SB 34-3282, dated August 1999, 
describes the installation of a new insert for the pitot/static and 
stall vent drain valves that will provide a positive seal of the 
valves. If accomplished on all drain valves, the modification would 
eliminate the need for the repetitive leak checks described in SB 34-
3207.

Explanation of Requirements of Proposed Rule

    Since an unsafe condition has been identified that is likely to 
exist or develop on other products of this same type design, the 
proposed AD would require leak checks of the pitot/static and stall 
vent drain valve systems and corrective actions, if necessary. The 
proposed AD would provide an optional action to apply a temporary seal 
of the drain valve for certain drain valves that are operative but that 
are leaking. The actions would be required to be accomplished in 
accordance with the service bulletins described previously. The 
proposed AD also would provide an optional terminating action for the 
proposed repetitive inspections that involves installing a new insert 
for the drain valve system.

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 
would be affected by this proposed AD, that it would take approximately 
4 work hours per airplane to accomplish the proposed actions, and that 
the average labor rate is $60 per work hour. Based on these figures, 
the cost impact of the proposed 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 proposed requirements of 
this AD action, and that no operator would accomplish those actions in 
the future if this AD were not adopted.
    Should an operator accomplish the optional modification to the 
drain valve system, it would take approximately 1 work hour per 
airplane to accomplish, at an average labor rate of $60 per work hour. 
Based on these figures, the cost impact of the optional modification is 
estimated to be $60 per airplane.

Regulatory Impact

    The regulations proposed herein would 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 proposal would not have federalism implications 
under Executive Order 13132.
    For the reasons discussed above, I certify that this proposed 
regulation (1) is not a ``significant regulatory action'' under 
Executive Order 12866; (2) is not a ``significant rule'' under the DOT 
Regulatory Policies and Procedures (44 FR 11034, February 26, 1979); 
and (3) if promulgated, 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 copy of the draft 
regulatory evaluation prepared for this action is contained in the 
Rules Docket. A copy of it may be obtained by contacting the Rules 
Docket at the location provided under the caption ADDRESSES.

List of Subjects in 14 CFR Part 39

    Air transportation, Aircraft, Aviation safety, Safety.

The Proposed Amendment

    Accordingly, pursuant to the authority delegated to me by the 
Administrator, the Federal Aviation Administration proposes to amend 
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:

Raytheon Aircraft Co. (Formerly Beech): 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 
modified, altered, or repaired in the area subject to the 
requirements of this AD. For airplanes that have been otherwise 
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

    (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 paragraphs (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 the modification on ALL drain 
valves consititutes 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

[[Page 37924]]

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.

    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 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 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 
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.


    Issued in Renton, Washington, on June 13, 2000.
Donald L. Riggin,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 00-15420 Filed 6-16-00; 8:45 am]
BILLING CODE 4910-13-U