[Federal Register Volume 60, Number 140 (Friday, July 21, 1995)]
[Proposed Rules]
[Pages 37606-37608]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 95-18030]



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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 95-NM-42-AD]


Airworthiness Directives; Raytheon Corporate Jets Model Hawker 
1000 and BAe 125-1000A 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 Raytheon Model Hawker 1000 
and BAe 125-1000A series airplanes. This proposal would require an 
inspection to detect damage to an electrical cable loom (wire bundle). 
This proposal would also require tying back the loom with a cable tie 
to the cable loom support bracket, and repair, if necessary. This 
proposal is prompted by a report indicating that damage had occurred to 
the electrical cable loom. The actions specified by the proposed AD are 
intended to prevent incorrect fault displays in the cockpit and 
possible electrical systems failures, as a result of damage to the 
electrical cable loom.

DATES: Comments must be received by August 31, 1995.

ADDRESSES: Submit comments in triplicate to the Federal Aviation 
Administration (FAA), Transport Airplane Directorate, ANM-103, 
Attention: Rules Docket No. 95-NM-42-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 Corporate Jets, Inc., Customer Support 
Department, Adams Field, P.O. Box 3356, Little Rock, Arkansas 72203. 
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-42-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-52-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 Raytheon Model Hawker 1000 and 
BAe 125-1000A series airplanes. The CAA advises that it has received a 
report of chafing damage to a certain electrical cable loom (wire 
bundle) behind the right-hand throttle box cover. Investigation has 
revealed that the chafing damage was caused by the flap selector spring 
strut when it was moved to the ``lift dump'' position. This condition, 
if not corrected, could result in incorrect fault displays in the 
cockpit and possible failure of the electrical systems.
    Raytheon has issued Service Bulletin SB 24-313, dated December 19, 
1994, which describes procedures for a one-time detailed visual 
inspection to detect chafing damage of the electrical cable loom 
located behind the right-hand throttle box cover. The service bulletin 
also describes verifying that the arrangement of the cable loom is 
correct, and provides procedures for tying back the loom with a cable 
tie to the cable loom support bracket, if no damaged cable is found. 
The CAA classified this service bulletin as mandatory in order to 
assure the continued airworthiness of these airplanes in the United 
Kingdom.
    This airplane model is manufactured in the United Kingdom 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 type design registered 
in the United States, the proposed AD would require a one-time detailed 
visual inspection to detect chafing damage of a certain electrical 
cable loom located behind the right-hand throttle box cover. The 
proposed AD would also require tying back the loom with a cable tie to 
the cable loom support bracket, if no damaged cable is found. The 
actions would be required to be accomplished in accordance with the 
service bulletin described previously. If any cable loom is damaged, 
the repair actions would be required to be accomplished in accordance 
with a method approved by the FAA.
    As a result of recent communications with the Air Transport 
Association (ATA) of America, the FAA has learned that, in general, 
some operators may misunderstand the legal effect of AD's on airplanes 
that are identified in the applicability provision of the AD, but that 
have been altered or repaired in the area addressed by the AD. The FAA 
points out that all airplanes identified in the applicability provision 
of an AD are legally subject to the AD. If an airplane has been altered 
or repaired in the affected area in such a way as to affect compliance 
with the AD, the owner or operator is required to obtain FAA approval 
for an alternative method of compliance with the AD, in accordance with 
the paragraph of each AD that

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provides for such approvals. A note has been included in this notice to 
clarify this long-standing requirement.
    The FAA estimates that 19 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 
total cost impact of the proposed AD on U.S. operators is estimated to 
be $1,140, or $60 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 U.S.C. App. 1354(a), 1421 and 1423; 49 U.S.C. 
106(g); and 14 CFR 11.89.


Sec. 39.13  [Amended]

    2. Section 39.13 is amended by adding the following new 
airworthiness directive:

Raytheon Corporate Jets, Inc. (Formerly de Havilland; Hawker 
Siddeley; British Aerospace, plc): Docket 95-NM-42-AD.

    Applicability: Model Hawker 1000 and BAe 125-1000A series 
airplanes; as listed in Raytheon Service Bulletin SB 24-313, dated 
December 19, 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 use the authority 
provided in paragraph (b) 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 incorrect fault displays in the cockpit and possible 
electrical systems failures, accomplish the following:
    (a) Within 6 months after the effective date of this AD, perform 
a detailed visual inspection to detect chafing damage of the 
electrical cable loom (wire bundle) behind the right-hand throttle 
box cover, and perform continuity and insulation checks and system 
functional tests, in accordance with Raytheon Service Bulletin SB 
24-313, dated December 19, 1994.
    (1) If no damage is found, prior to further flight, verify that 
the arrangement of the cable loom is correct and, using a cable tie, 
tie back the loom to the cable loom support bracket, in accordance 
with the service bulletin.
    (2) If any damage is found, prior to further flight, repair the 
damaged loom, 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.

    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 July 17, 1995.
James V. Devany,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 95-18030 Filed 7-20-95; 8:45 am]
BILLING CODE 4910-13-U