[Federal Register Volume 66, Number 31 (Wednesday, February 14, 2001)]
[Proposed Rules]
[Pages 10236-10238]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 01-3675]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 2000-NM-212-AD]
RIN 2120-AA64


Airworthiness Directives; Raytheon Model BAe.125 Series 800A (C-
29A and U-125 Military), 1000A, and 1000B Airplanes; Hawker 800 (U-125A 
Military) Airplanes; and Hawker 800XP and 1000 Series Airplanes.

AGENCY: Federal Aviation Administration, DOT.

ACTION: Supplemental notice of proposed rulemaking; reopening of 
comment period.

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SUMMARY: This document revises an earlier proposed airworthiness 
directive (AD), applicable to certain Raytheon Model BAe.125, Hawker 
800 (U-125A military) and Hawker 800XP series airplanes that would have 
required removal of existing clamps, bedding tapes, and rubber 
connecting sleeves at the ends of the turbine air discharge duct and 
the water separator, and replacement of the clamps and rubber 
connecting sleeves with new, improved components. This new action 
revises the proposed rule by adding airplanes to the applicability; 
and, for certain airplanes, adding a new requirement to remove aluminum 
bedding strips that are installed under the existing clamps. The 
actions specified by this new proposed AD are intended to prevent the 
turbine air discharge duct or water separator outlet duct from 
disconnecting from the cold air unit turbine or from the water 
separator, resulting in the loss of air supply to maintain adequate 
cabin pressure. Loss of adequate cabin pressure at high altitude would 
require emergency procedures, such as use of oxygen, auxiliary 
pressurization, or emergency descent.

DATES: Comments must be received by March 12, 2001.

ADDRESSES: Submit comments in triplicate to the Federal Aviation 
Administration (FAA), Transport Airplane Directorate, ANM-114, 
Attention: Rules Docket No. 2000-NM-212-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. Comments may be submitted via fax to (425) 227-1232. 
Comments may also be sent via the Internet using the following address: 
<a href="/cdn-cgi/l/email-protection#2e17034f404303405e5c434d4143434b405a6e484f4f00494158"><span class="__cf_email__" data-cfemail="c3faeea2adaeeeadb3b1aea0acaeaea6adb783a5a2a2eda4acb5">[email protected]</span></a>. Comments

[[Page 10237]]

sent via fax or the Internet must contain ``Docket No. 2000-NM-212-AD'' 
in the subject line and need not be submitted in triplicate. Comments 
sent via the Internet as attached electronic files must be formatted in 
Microsoft Word 97 for Windows or ASCII text.
    The service information referenced in the proposed rule may be 
obtained from Raytheon Aircraft Company, Manager, Service Engineering, 
Product Support Department (62), 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; or at the FAA, 
Wichita Aircraft Certification Office, 1801 Airport Road, Room 100, 
Mid-Continent Airport, Wichita, Kansas.

FOR FURTHER INFORMATION CONTACT: Paul C. DeVore, Aerospace Engineer, 
Systems and Propulsion Branch, ACE-116W, FAA, Wichita Aircraft 
Certification Office, 1801 Airport Road, Room 100, Mid-Continent 
Airport, Wichita, Kansas 67209; telephone (316) 946-4142; fax (316) 
946-4407.

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 action may be changed in 
light of the comments received.
    Submit comments using the following format:
    <bullet> Organize comments issue-by-issue. For example, discuss a 
request to change the compliance time and a request to change the 
service bulletin reference as two separate issues.
    <bullet> For each issue, state what specific change to the proposed 
AD is being requested.
    <bullet> Include justification (e.g., reasons or data) for each 
request.
    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 action must submit a self-addressed, 
stamped postcard on which the following statement is made: ``Comments 
to Docket Number 2000-NM-212-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-114, Attention: Rules 
Docket No. 2000-NM-212-AD, 1601 Lind Avenue, SW., Renton, Washington 
98055-4056.

Discussion

    A proposal to amend part 39 of the Federal Aviation Regulations (14 
CFR part 39) to add an airworthiness directive (AD), applicable to 
certain Raytheon Model BAe.125, Hawker 800 (U-125A), and Hawker 800XP 
series airplanes, was published as a notice of proposed rulemaking 
(NPRM) in the Federal Register on August 14, 2000 (65 FR 49523). That 
NPRM would have required removal of existing clamps, bedding tapes, and 
rubber connecting sleeves at the ends of the turbine air discharge duct 
and the water separator, and replacement of the clamps and rubber 
connecting sleeves with new, improved components.

Actions Since Issuance of Previous Proposal

    Since the issuance of that NPRM, the FAA has received reports 
indicating that aluminum bedding strips may inhibit proper torquing of 
the clamp. Such improper torquing of the clamp may allow separation of 
the turbine air discharge duct or water separator outlet duct from the 
cold air unit turbine or from the water separator, which could result 
in the loss of air supply to maintain adequate cabin pressure. Loss of 
adequate cabin pressure at high altitude would require emergency 
procedures, such as use of oxygen, auxiliary pressurization, or 
emergency descent.

Issuance of a New Service Bulletin

    The FAA has reviewed and approved Raytheon Service Bulletin SB 21-
3414, Revision 1, dated July 2000, that describes procedures for 
removing certain aluminum bedding strips on the air conditioning duct 
sleeves attached to both ends of the turbine air discharge duct and at 
the outlet end of the water separator. That service bulletin also 
specifies additional airplane models to the effectivity specified in 
Raytheon Service Bulletin SB 21-3377, Revision 1, dated July 2000, 
which was specified as the appropriate service information in the 
original NPRM.

Conclusion

    Since this change expands the scope of the originally proposed 
rule, the FAA has determined that it is necessary to reopen the comment 
period to provide additional opportunity for public comment.

Cost Impact

    There are approximately 270 Model BAe.125 series 800A (C-29A and U-
125 military), 1000A, and 1000B airplanes, Hawker 800 (U-125A military) 
airplanes, and Hawker 800XP and 1000 series airplanes of the affected 
design in the worldwide fleet.
    The FAA estimates that 154 airplanes of U.S. registry would be 
affected by paragraph (a) of this proposed AD. We estimate that the 
actions required by paragraph (a) of this AD would take approximately 8 
work hours per airplane to accomplish, and that the average labor rate 
is $60 per work hour. Required parts would cost approximately $492 per 
airplane. Based on these figures, the cost impact of the proposed AD on 
U.S. operators is estimated to be $149,688, or $972 per airplane.
    The FAA estimates that an additional 36 airplanes of U.S. registry 
would be affected by paragraph (b) of this proposed AD. We estimate 
that the actions required by paragraph (b) of this AD would take 
approximately 2 hours per airplane to accomplish the proposed actions, 
and that the average labor rate is $60 per work hour. There is no cost 
for required parts. Based on these figures, the cost impact of 
paragraph (b) of the proposed AD on U.S. operators is estimated to be 
$4,320, or $120 per airplane.
    The cost impact figures discussed above are 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 cost impact figures 
discussed in AD rulemaking actions represent only the time necessary to 
perform the specific actions actually required by the AD. These figures 
typically do not include incidental costs, such as the time required to 
gain access and close up, planning time, or time necessitated by other 
administrative actions.

Regulatory Impact

    The regulations proposed herein would not have a substantial direct 
effect on the States, on the relationship

[[Page 10238]]

between the national Government and the States, or on the distribution 
of power and responsibilities among the various levels of government. 
Therefore, it is determined that this proposal would not have 
federalism implications under Executive Order 13132.
    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:

Raytheon Aircraft Company:  Docket 2000-NM-212-AD.

    Applicability: Model BAe.125 series 800A (C-29A and U-125 
military), 1000A, and 1000B airplanes, Hawker 800 (U-125A military) 
airplanes; up to and including serial number 258406; and Hawker 
800XP series airplanes, up to and including serial number 258483 and 
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 request approval for an 
alternative method of compliance in accordance with paragraph (d) 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 the turbine air discharge duct or water separator 
outlet duct from disconnecting from the cold air unit turbine or 
from the water separator, resulting in the loss of air supply to 
maintain adequate cabin pressure, accomplish the following:

Replacement

    (a) For Model BAe.125 series 800A (C-29A and U-125 military) 
series airplanes, Hawker 800 (U-125A military) airplanes up to and 
including serial number 258406, and Hawker 800XP series airplanes up 
to and including serial number 258459: Remove the clamps, bedding 
tapes, and rubber connecting sleeves at the ends of the air turbine 
discharge duct and the water separator, and replace the clamps and 
rubber connecting sleeves with new, improved components, in 
accordance with the Accomplishment Instructions of Raytheon Service 
Bulletin SB 21-3377, Revision 1, dated July 2000, at the earliest of 
the times specified in paragraphs (a)(1), (a)(2), and (a)(3) of this 
AD.
    (1) Prior to any extended over-water operation.
    (2) Within the next 300 hours time-in-service after the 
effective date of this AD.
    (3) Within the next six months after the effective date of this 
AD.

    Note 2: An extended over-water operation is defined in 14 CFR 
1.1 as `` * * * an operation over water at a horizontal distance of 
more than 50 nautical miles from the nearest shoreline. * * * ''

    (b) For Model Hawker 800XP series airplanes having serial 
numbers 258460 through 258483, Model BAe.125 series 1000A/1000B 
airplanes, and Hawker 1000 series airplanes: Remove the aluminum 
bedding strips from the air conditioning duct sleeves attached to 
both ends of the turbine air discharge duct and at the outlet end of 
the water separator, in accordance with the Accomplishment 
Instructions of Raytheon Service Bulletin SB 21-3414, Revision 1, 
dated July 2000, at the earliest of the times specified in 
paragraphs (b)(1), (b)(2), and (b)(3) of this AD.
    (1) Prior to any extended over-water operation.
    (2) Within the next 300 hours time-in-service after the 
effective date of this AD.
    (3) Within the next six months after the effective date of this 
AD.

Actions Accomplished Previously and Terminating Actions

    (c) For certain airplanes, actions described in the original 
issuance of Raytheon Service Bulletin SB 21-3377, may have been 
accomplished prior to the effective date of this AD. On those 
airplanes, those actions are not required to be repeated, as allowed 
by the phrase, ``unless accomplished previously.'' However, any 
action described in Raytheon Service Bulletin SB 21-3377, Revision 
1, dated July 2000, or Raytheon Service Bulletin SB 21-3414, 
Revision 1, dated July 2000, that has not been accomplished on those 
airplanes must be accomplished in accordance with this AD. 
Accomplishment of the actions specified in both Raytheon Service 
Bulletin SB 21-3377, Revision 1, dated July 2000, and Raytheon 
Service Bulletin SB 21-3414, Revision 1, dated July 2000, is 
considered to be terminating action for the requirements of this AD.

Alternative Methods of Compliance

    (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, Wichita Aircraft Certification 
Office (ACO), FAA. Operators shall submit their requests through an 
appropriate FAA Principal Maintenance Inspector, who may add 
comments and then send it to the Manager, Wichita ACO.

    Note 3: Information concerning the existence of approved 
alternative methods of compliance with this AD, if any, may be 
obtained from the Wichita ACO.

Special Flight Permits

    (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 7, 2001.
Donald L. Riggin,
Acting Manager,, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 01-3675 Filed 2-13-01; 8:45 am]
BILLING CODE 4910-13-P


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