[Federal Register Volume 61, Number 28 (Friday, February 9, 1996)]
[Proposed Rules]
[Pages 4942-4944]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 96-2868]
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DEPARTMENT OF TRANSPORTATION
14 CFR Part 39
[Docket No. 95-NM-122-AD]
Airworthiness Directives; Beech Model BAe 125-800A and Model
Hawker 800 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 Beech Model BAe 125-800A
and Model Hawker 800 airplanes. This proposal would require
modification of the airframe structure in the lower area of the
fuselage aft of the wing rear spar. For certain airplanes, this
proposal would also require a functional test to determine if a
particular bolt fouls the flap control system. This proposal is
prompted by reports of restricted control of the aileron due to water
accumulation that froze in the area around an aileron pulley located in
the lower area of the fuselage aft of the wing rear spar. The actions
specified by the proposed AD are intended to prevent such water
accumulation, which could freeze and result in restricted control of
the ailerons; subsequently, this could reduce the pilot's ability to
initiate roll control during critical phases of flight.
DATES: Comments must be received by March 22, 1996.
ADDRESSES: Submit comments in triplicate to the Federal Aviation
Administration (FAA), Transport Airplane Directorate, ANM-103,
Attention: Rules Docket No. 95-NM-122-AD, 1601 Lind Avenue SW., Renton,
Washington 98055-4056. Comments may be inspected at this location
between 9:00 a.m. and 3:00 p.m., Monday through Friday, except Federal
holidays.
The service information referenced in the proposed rule may be
obtained from Raytheon Aircraft Co., Manger 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.
FOR FURTHER INFORMATION CONTACT: William Schroeder, Aerospace Engineer,
Standardization Branch, ANM-113, FAA, Transport Airplane Directorate,
1601 Lind Avenue SW., Renton, Washington 98055-4056; telephone (206)
227-2148; fax (206) 227-1149.
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 95-NM-122-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-103, Attention: Rules
Docket No. 95-NM-122-AD, 1601 Lind Avenue SW., Renton, Washington
98055-4056.
Discussion
The Civil Aviation Authority (CAA), which is the airworthiness
authority for the United Kingdom, recently notified the FAA that an
unsafe condition may exist on certain Beech Model BAe 125-800A and
Model Hawker 800 airplanes. The CAA advises that it has received
several reports of restricted control of the aileron. Investigation
revealed that potable water leaked from the potable water supply system
of the galley and lavatory and accumulated in the lower area of the
fuselage aft of the wing rear spar. This water then drained to and
accumulated in the area around an aileron pulley located in the subject
area, and eventually froze. These conditions, if not corrected, could
result in restricted control of the ailerons, and, subsequently, reduce
the pilot's ability to initiate roll control during critical phases of
flight.
The manufacturer has issued Hawker Service Bulletin SB.53-82-3566G,
dated March 1, 1995; Revision 1, dated March 14, 1995; Revision 2,
dated May 3, 1995; and Revision 3, December 14, 1995 (for certain
airplanes, excluding Model BAe 125-800A airplane having constructor's
No. 258186). The manufacturer has also issued Hawker Service Bulletin
SB.53-85-3566D, dated March 10, 1995, and Revision 1, dated May 23,
1995 (for Model BAe 125-800A airplane having constructor's number
258186). These service bulletins describe procedures for modification
of the airframe structure in the lower area of the fuselage aft of the
wing rear spar. The modification entails the following actions:
1. Installing new drain holes in the fairing skin assembly of the
main landing gear (MLG);
2. Plugging existing vent holes of the keel stringers;
3. Installing a new water barrier diaphragm between the forward
diaphragm assembly of the MLG and the aft diaphragm assembly;
4. Installing a blanking plate on the forward diaphragm assembly;
5. Removing existing drain valves from the fuselage keel skin;
6. Blanking off an existing drain valve hole using a new patch
plate;
7. Installing two new drain spouts, a drain hose, and an outlet
fairing; and
8. Performing a functional test to determine if a bolt fouls the
flap control system (Revision 3 of Service Bulletin SB.53-82-3566G
only).
Accomplishment of the modification will prevent any leaked fluids
from collecting around the aileron pulley, and will allow any water
build-up in the fuselage keel area to drain away. The CAA classified
these service bulletins as mandatory in order to assure the continued
airworthiness of these airplanes in the United Kingdom.
This airplane model is manufactured in CAA and is type certificated
for operation in the United States under the provisions of section
21.29 of the Federal Aviation Regulations (14 CFR 21.29) and the
applicable bilateral airworthiness agreement. Pursuant to this
bilateral airworthiness agreement, the CAA has kept the FAA informed of
the situation described above. The FAA has examined the findings of the
CAA, reviewed all available information, and determined that AD action
is necessary for products of this type design that are certificated for
operation in the United States.
Since an unsafe condition has been identified that is likely to
exist or develop on other airplanes of the same
[[Page 4944]]
type design, the proposed AD would require modification of the airframe
structure in the lower area of the fuselage aft of the wing rear spar.
For certain airplanes, the proposed AD would also require a functional
test to determine if a bolt fouls the flap control system. The actions
would be required to be accomplished in accordance with the service
bulletins described previously. If any fouls are detected, the repair
would be required to be accomplished in accordance with a method
approved by the FAA.
The FAA estimates that 163 airplanes of U.S. registry would be
affected by this proposed AD, that it would take approximately 25 work
hours per airplane to accomplish the proposed actions, and that the
average labor rate is $60 per work hour. Required parts would be
supplied by the manufacturer at no cost to the operators. Based on
these figures, the total cost impact of the proposed AD on U.S.
operators is estimated to be $244,500, or $1,500 per airplane.
The total 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.
The regulations proposed herein would 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
proposal would not have sufficient federalism implications to warrant
the preparation of a Federalism Assessment.
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 USC 106(g), 40113, 44701.
Sec. 39.13 [Amended]
2. Section 39.13 is amended by adding the following new
airworthiness directive:
Beech Aircraft Corporation. (Formerly DeHavilland; Hawker Siddeley;
British Aerospace, plc; Raytheon Corporate Jets, Inc.): Docket 95-
NM-122-AD.
Applicability: Model BAe 125-800A (including military variants
C-29A and U-125); and Model Hawker 800 airplanes, excluding
airplanes having constructor's numbers 258079 and 258213;
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 use the authority
provided in paragraph (d) of this AD to request approval from the
FAA. This approval may address either no action, if the current
configuration eliminates the unsafe condition; or different actions
necessary to address the unsafe condition described in this AD. Such
a request should include an assessment of the effect of the changed
configuration on the unsafe condition addressed by this AD. In no
case does the presence of any modification, alteration, or repair
remove any airplane from the applicability of this AD.
-Compliance: Required as indicated, unless accomplished
previously.
To prevent restricted control of the ailerons, which could
reduce the pilot's ability to initiate roll control during critical
phases of flight, accomplish the following:
(a) For all airplanes, except Model BAe 125-800A airplane having
constructor's number 258186: Within 6 months after the effective
date of this AD, modify (including functional test) the airframe
structure in the lower area of the fuselage aft of the wing rear
spar, in accordance with Hawker Service Bulletin SB.53-82-3566G,
Revision 3, December 14, 1995.
(b) For airplanes identified in paragraph (a) of this AD on
which Hawker Modification 253566G has been installed prior to the
effective date of this AD, in accordance with Hawker Service
Bulletin SB.53-82-3566G, dated March 1, 1995, Revision 1, dated
March 14, 1995, or Revision 2, dated May 3, 1995: Within 30 days
after the effective date of this AD, perform a functional test to
determine if a bolt fouls the flap control system, in accordance
with paragraph 2.A.(18) of the Accomplishment Instructions of Hawker
Service Bulletin SB.53-82-3566G, Revision 3, December 14, 1995. If
any foul is detected, prior to further flight, repair in accordance
with a method approved by the Manager, Standardization Branch, ANM-
113, Transport Airplane Directorate, FAA.
(c) For Model BAe 125-800A airplane having constructor's number
258186: Within 6 months after the effective date of this AD, modify
the airframe structure in the lower area of the fuselage aft of the
wing rear spar, in accordance with Hawker Service Bulletin SB.53-85-
3566D, dated March 10, 1995, or Revision 1, dated May 23, 1995.
(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, Standardization Branch, ANM-113,
FAA, Transport 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,
Standardization Branch, ANM-113.
Note 2: Information concerning the existence of approved
alternative methods of compliance with this AD, if any, may be
obtained from the Standardization Branch, ANM-113.
(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.
Issued in Renton, Washington, on February 5, 1996.
Darrell M. Pederson,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 96-2868 Filed 2-8-96; 8:45 am]
BILLING CODE 4910-13-U
