[Federal Register Volume 61, Number 105 (Thursday, May 30, 1996)]
[Proposed Rules]
[Pages 27028-27030]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 96-13497]



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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 95-NM-166-AD]
RIN 2120-AA64


Airworthiness Directives; Beech (Raytheon) Model BAe 125 Series 
1000A and Model Hawker 1000 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 series 1000A and Model Hawker 1000 airplanes. This proposal would 
require a one-time inspection for correct sleeve lengths, an inspection 
to detect discrepancies of the elevator pulley assembly, and correction 
of any discrepancy. This proposal is prompted by reports indicating 
that some aircraft have been fitted with an elevator pulley that was 
assembled incorrectly during manufacture. The actions specified by the 
proposed AD are intended to prevent reduced structural integrity of the 
elevator control circuit due to failure of one or more outer lugs or 
malfunction of the elevator pulley assembly as a result of incorrect 
assembly of the pulley.

DATES: Comments must be received by July 8, 1996.

ADDRESSES: Submit comments in triplicate to the Federal Aviation 
Administration (FAA), Transport Airplane Directorate, ANM-103, 
Attention: Rules Docket No. 95-NM-166-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: 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-166-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-166-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

[[Page 27029]]

the FAA that an unsafe condition may exist on certain Beech (Raytheon) 
Model BAe 125 series 1000A and Model Hawker 1000 airplanes. The CAA 
advises that it has received reports indicating that some aircraft have 
been fitted with an elevator pulley that was assembled incorrectly 
during manufacture. Failure of one or more outer lugs or malfunction of 
the elevator pulley assembly, if not corrected, could result in reduced 
structural integrity of the elevator control circuit.

Explanation of Relevant Service Information

    The manufacturer has issued Hawker Service Bulletin SB 27-161, 
Revision 1, dated July 29, 1994, which describes procedures for a one-
time inspection for correct sleeve lengths, and a one-time visual 
inspection to detect discrepancies of the elevator pulley assembly. The 
CAA classified this service bulletin as mandatory in order to assure 
the continued airworthiness of these airplanes in the United Kingdom.

FAA's Conclusions

    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.

Explanation of Requirements of Proposed Rule

    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 inspection for correct sleeve 
lengths, a one-time visual inspection to detect discrepancies of the 
elevator pulley assembly, and correction of any discrepancy. The 
inspections would be required to be accomplished in accordance with the 
service bulletin described previously. Correction of discrepancies 
would be required to be accomplished in accordance with a method 
approved by the FAA.

Cost Impact

    The FAA estimates that 40 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 
$2,400, 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 action, and that no operator would accomplish those actions 
in the future if this AD were not adopted.

Regulatory Impact

    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 Company (Formerly DeHavilland; Hawker Siddeley; 
British Aerospace, PLC; Raytheon Corporate Jets, Inc.): Docket 95-
NM-166-AD.

    Applicability: Model BAe 125 series 1000A and Model Hawker 1000 
airplanes; as listed in Hawker Service Bulletin SB 27-161, Revision 
1, dated July 29, 1994; 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.

    Note 2: Beech (Raytheon) Model BAe 125 series 1000B airplanes 
are similar in design to the airplanes that are subject to the 
requirements of this AD and, therefore, also may be subject to the 
unsafe condition addressed by this AD. However, as of the effective 
date of this AD, those models are not type certificated for 
operation in the United States. Airworthiness authorities of 
countries in which Model BAe 125 series 1000B series airplanes are 
approved for operation should consider adopting corrective action, 
applicable to those models, that is similar to the corrective action 
required by this AD.

    Compliance: Required as indicated, unless accomplished 
previously.
    To prevent reduced structural integrity of the elevator control 
circuit, accomplish the following:
    (a) Within 6 months after the effective date of this AD: Perform 
a one-time inspection for correct sleeve lengths, and a one-time 
visual inspection to detect discrepancies of the elevator pulley 
assembly, in accordance with Hawker Service Bulletin SB 27-161, 
Revision 1, dated July 29, 1994.
    (1) If no discrepancy is found, no further action is required by 
this AD.
    (2) If any discrepancy is found, prior to further flight, 
correct the discrepancy 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, 
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.


[[Page 27030]]


    Note 3: 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 May 22, 1996.
John J. Hickey,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 96-13497 Filed 5-29-96; 8:45 am]
BILLING CODE 4910-13-U