[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 

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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