[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