[Federal Register Volume 60, Number 243 (Tuesday, December 19, 1995)]
[Proposed Rules]
[Pages 65254-65256]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 95-30748]



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DEPARTMENT OF TRANSPORTATION
14 CFR Part 39

[Docket No. 95-NM-141-AD]


Airworthiness Directives; Beech Model BAe 125-1000A and 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 all Beech Model BAe 125-1000A and 
Hawker 1000 series airplanes. This proposal would require a detailed 
visual inspection to detect chafing damage to the hydraulic pipes 
adjacent to the 

[[Page 65255]]
hydraulic module, and various follow-on actions. This proposal is 
prompted by reports of chafing damage between hydraulic pipes at three 
locations in the rear equipment bay adjacent to the hydraulic module. 
The actions specified by the proposed AD are intended to prevent such 
chafing damage to the hydraulic pipe and subsequent hydraulic fluid 
leakage; this condition may lead to failure of essential airplane 
systems.

DATES: Comments must be received by January 25, 1996.

ADDRESSES: Submit comments in triplicate to the Federal Aviation 
Administration (FAA), Transport Airplane Directorate, ANM-103, 
Attention: Rules Docket No. 95-NM-141-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 Beech Aircraft Corporation, 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-141-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-141-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 all Beech Model BAe 125-1000A and Hawker 
1000 series airplanes. The CAA advises that it has received several 
reports of chafing damage between hydraulic pipes at three locations in 
the rear equipment bay adjacent to the hydraulic module. Investigation 
revealed the cause of such chafing damage has been attributed to the 
vibratory movement of the hydraulic pipes and their close proximity to 
other pipe runs, adjacent equipment, and structure in the rear 
equipment bay. These conditions, if not corrected, could result in 
chafing damage to the hydraulic pipe and subsequent hydraulic fluid 
leakage; this condition may lead to failure of essential airplane 
systems.
    The manufacturer has issued Hawker Service Bulletin SB.29-95, dated 
March 24, 1995, which describes procedures for:
    1. Performing a detailed visual inspection to detect chafing damage 
to the hydraulic pipes located aft of frame 21 and adjacent to the 
hydraulic module;
    2. Performing a visual inspection to determine if adequate 
clearance exists between the pipes, and with other equipment or 
structure, if no chafing damage is detected;
    3. Adjusting the pipe connections and/or clipping, if the clearance 
is inadequate;
    4. Replacing the pipes with new pipes, if any chafing is detected 
beyond certain limits; and
    5. Performing a pressure test, if any chafing damage is detected 
within certain limits, and replacement of the pipe with a new pipe, if 
necessary.
    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, the 
proposed AD would require a detailed visual inspection to detect 
chafing damage to the hydraulic pipes located aft of frame 21 and 
adjacent to the hydraulic module, and various follow-on actions (i.e., 
visual inspection, adjustment, replacement, pressure test). The actions 
would be required to be accomplished in accordance with the service 
bulletin described previously. If any chafing damage to other equipment 
or structure is found, repair would be required to be accomplished in 
accordance with a method approved by the FAA.
    The FAA estimates that 27 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 
$1,620, 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.
    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. 

[[Page 65256]]

    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), 40101, 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-141-AD.

    Applicability: All Model BAe 125-1000A and Hawker 1000 series 
airplanes, 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 chafing damage to the hydraulic pipe and subsequent 
hydraulic fluid leakage; this condition may lead to failure of 
essential airplane systems; accomplish the following:
    (a) Within 3 months after the effective date of this AD, perform 
a detailed visual inspection to detect chafing damage to the 
hydraulic pipes located aft of frame 21 and adjacent to the 
hydraulic module, in accordance with Hawker Service Bulletin SB.29-
95, dated March 24, 1995.
    (1) If no chafing damage is detected, prior to further flight, 
perform a visual inspection to determine if adequate clearance 
exists between the intersecting pipe runs, and between pipes and 
adjacent equipment or structure, in accordance with the service 
bulletin.
    (i) If the clearance is adequate, no further action is required 
by this AD.
    (ii) If the clearance is inadequate, prior to further flight, 
adjust the pipe connections and/or clipping in accordance with the 
service bulletin.
    (iii) If any chafing damage to other equipment or structure is 
found, prior to further flight, repair it in accordance with a 
method approved by the Manager, Standardization Branch, ANM-113, 
FAA, Transport Airplane Directorate.
    (2) If any chafing damage is detected and it is beyond the 
limits specified in paragraph 2.B.(4) of the service bulletin, prior 
to further flight, replace the damaged pipe with a new pipe in 
accordance with the service bulletin.
    (3) If any chafing damage is detected within the limits 
specified in paragraph 2.B.(4) of the service bulletin, prior to 
further flight, perform a pressure test or replace the damaged pipe 
with a new pipe in accordance with the service bulletin.
    (i) If the pipes are satisfactory, no further action is required 
by this AD.
    (ii) If any pipe leaks and/or if any distortion occurs in or 
around the area of chafing damage, prior to further flight, replace 
the pipe with a new pipe in accordance with the service bulletin.
    (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 December 13, 1995.
Darrell M. Pederson,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 95-30748 Filed 12-18-95; 8:45 am]
BILLING CODE 4910-13-U