[Federal Register Volume 61, Number 49 (Tuesday, March 12, 1996)]
[Proposed Rules]
[Pages 9958-9960]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 96-5857]



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[[Page 9959]]


DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 95-NM-180-AD]


Airworthiness Directives; Beech (Raytheon) Model BAe 125-1000A 
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 Beech (Raytheon) Model BAe 
125-1000A and Model Hawker 1000 series airplanes. This proposal would 
require a one-time inspection for adequate clearances between, and 
damage to, the flap cables and turnbuckles, airbrakes cables and 
turnbuckles, and all other flight control cables and turnbuckles at 
keel subframe 15A; and various follow-on actions, if necessary. This 
proposal is prompted by reports of chafing due to insufficient 
clearance between the flaps turnbuckle and the subframe, and between 
the airbrakes cable and the subframe. The actions specified by the 
proposed AD are intended to prevent such chafing, which could result in 
damage to the flaps turnbuckle and the airbrakes cable, and subsequent 
fraying or seizing of the flight control cables. These conditions, if 
not corrected, could result in restriction or loss of the flight 
controls.

DATES: Comments must be received by April 22, 1996.

ADDRESSES: Submit comments in triplicate to the Federal Aviation 
Administration (FAA), Transport Airplane Directorate, ANM-103, 
Attention: Rules Docket No. 95-NM-180-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 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.

FOR FURTHER INFORMATION CONTACT: Tim Backman, Aerospace Engineer, 
Standardization Branch, ANM-113, FAA, Transport Airplane Directorate, 
1601 Lind Avenue, SW., Renton, Washington 98055-4056; telephone (206) 
227-2797; 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-180-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-180-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 (Raytheon) Model BAe 125-
1000A and Model Hawker 1000 series airplanes. The CAA advises that it 
received reports of chafing of the flaps turnbuckle and the airbrakes 
cable at keel subframe 15A. The cause of this chafing has been 
attributed to insufficient clearance between the flap turnbuckle and 
the subframe, and between the airbrakes cable and the subframe. Such 
insufficient clearance and resultant chafing could result in damage to 
the flap cables and/or turnbuckles and the airbrakes cable, and 
subsequent fraying or seizing of the flight control cables. These 
conditions, if not corrected, could result in restriction or loss of 
the flight controls.
    Raytheon Corporate Jets has issued Hawker Service Bulletin SB.27-
168, dated July 17, 1995, which describes procedures for a one-time 
visual inspection for adequate clearances and/or damage of the flap 
cables and turnbuckles, airbrakes cables and turnbuckles, and all other 
flight control cables and turnbuckles at keel subframe 15A (left- and 
right-hand side); and various follow-on actions, if necessary. (These 
follow-on actions include modification, repair, and replacement of 
damaged cables.) The CAA classified this service bulletin as mandatory 
in order to assure the continued airworthiness of these airplanes in 
the United Kingdom.
    These airplane models are manufactured in the United Kingdom and 
are 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 type design, the 
proposed AD would require a one-time visual inspection for adequate 
clearances between, and/or damage to, the flap cables and turnbuckles, 
airbrakes cables and turnbuckles, and all other flight control cables 
and turnbuckles at keel subframe 15A (left- and right-hand side); and 
various follow-on actions, if necessary. The actions would be required 
to be accomplished in accordance with the service bulletin described 
previously.
    The FAA estimates that 25 airplanes of U.S. registry would be 
affected by this proposed AD, that it would take approximately 1 work 
hour 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 
$1,500, or $60 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

[[Page 9960]]
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 U.S.C. 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-180-AD.

    Applicability: Model BAe 125-1000A and Model Hawker 1000 series 
airplanes, as listed in Hawker Service Bulletin SB.27-168, dated 
July 17, 1995; 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 request approval for an 
alternative method of compliance in accordance with paragraph (b) 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 restriction or loss of the flight controls due to 
insufficient clearance and resultant chafing and damage to the flaps 
cable and/or turnbuckle and the airbrakes cable, accomplish the 
following:
    (a) Within 6 months after the effective date of this AD: Perform 
a one-time detailed visual inspection for adequate working 
clearances and for damage of the flap, airbrakes, and other flight 
control cables and turnbuckles with the structure at keel subframe 
15A (left- and right-hand sides) specified in Hawker Service 
Bulletin SB.27-168, dated July 17, 1995. Perform the inspection in 
accordance with that service bulletin. The detailed visual 
inspection for working clearances shall be conducted for each 
affected flight control through its full range of travel.
    (1) If all clearances are within the limits specified in the 
service bulletin, and no damage is found: No further action is 
required by this AD.
    (2) If the clearance for the flaps controls is outside the 
limits specified in the service bulletin: Prior to further flight, 
accomplish Modification SB 27-168-253705B in accordance with the 
service bulletin.
    (3) If the clearance for the airbrakes controls is outside the 
limits specified in the service bulletin: Prior to further flight, 
repair in accordance with the service bulletin.
    (4) If any cable is found to be damaged, and the damage exceeds 
the limits defined in Chapter 20-10-31 of the Airplane Maintenance 
Manual: Prior to further flight, replace the damaged cable with a 
new cable in accordance with the service bulletin.
    (5) If any turnbuckle, keel subframe, or polythene strip is 
found to be damaged: Prior to further flight, repair in accordance 
with a method approved by the Manager, Standardization Branch, ANM-
113, FAA, Transport Airplane Directorate.
    (b) 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. 
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.

    (c) 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 March 6, 1996.
Darrell M. Pederson,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 96-5857 Filed 3-11-96; 8:45 am]
BILLING CODE 4910-13-U