[Federal Register Volume 67, Number 231 (Monday, December 2, 2002)]
[Proposed Rules]
[Pages 71505-71507]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 02-30346]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 2001-NM-18-AD]
RIN 2120-AA64


Airworthiness Directives; Raytheon Model Hawker 800XP and 800 
(Including Variant U-125A) 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 
800XP and 800 (including variant U-125A) airplanes. This proposal would 
require a one-time inspection to identify the bolts installed at 
certain locations in the wing or fuselage, and corrective actions if 
necessary. This action is necessary to prevent failure of certain 
attachment bolts due to manufacturing discrepancies, which could result 
in reduced structural integrity of the airplane, and loss of system 
function for flaps, controls, and landing gear. This action is intended 
to address the identified unsafe condition.

DATES: Comments must be received by January 16, 2003.

ADDRESSES: Submit comments in triplicate to the Federal Aviation 
Administration (FAA), Transport Airplane Directorate, ANM-114, 
Attention: Rules Docket No. 2001-NM-18-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: 
[email protected]. Comments sent via fax or the Internet must 
contain ``Docket No. 2001-NM-18-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, 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: David Ostrodka, Senior Aerospace 
Engineer, Airframe Branch, ACE-118W, FAA, Wichita Aircraft 
Certification Office, 1801 Airport Road, Room 100, Mid-Continent 
Airport, Wichita, Kansas 67209; telephone (316) 946-4129; 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:
    [sbull] 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.
    [sbull] For each issue, state what specific change to the proposed 
AD is being requested.
    [sbull] 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 2001-NM-18-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.

[[Page 71506]]

2001-NM-18-AD, 1601 Lind Avenue, SW., Renton, Washington 98055-4056.

Discussion

    The FAA has received a report of broken bolts found in the wing and 
fuselage of certain Hawker Model 800XP and 800 (including variant U-
125A) airplanes. Investigation revealed inadequate control of the heat 
treat process during manufacture of the subject bolts. This resulted in 
an increased sensitivity to hydrogen embrittlement when electro-
deposited cadmium plating was applied to the bolts. A bolt that incurs 
damage (hydrogen embrittlement) during manufacture will break in a 
short time after installation because of the bolt's installation 
preload. Intact (nonbroken) bolts currently installed on affected 
airplanes are considered adequate to carry the design loads. However, 
broken bolts could result in reduced structural integrity of the 
airplane, and the loss of the systems for flaps, controls, and landing 
gear.

Explanation of Relevant Service Information

    The FAA has reviewed and approved Raytheon Service Bulletins SB 51-
3408, dated October 2000, and SB 51-3426, Revision 1, dated November 
2001 (for Model Hawker 800XP airplanes); and SB 51-3421, Revision 1, 
dated November 2001 (for Model Hawker 800 (including variant U-125A) 
airplanes). The service bulletins describe procedures for a one-time 
inspection to identify any Ravenstone Jackson DHS bolts installed at 
certain locations in the wing and fuselage, a one-time ultrasonic 
inspection of those bolts to detect breakage, and replacement of any 
broken bolt with an acceptable new bolt identified in the service 
bulletins. Accomplishment of the actions specified in the applicable 
service bulletins is intended to adequately address the identified 
unsafe condition.

Explanation of Requirements of Proposed Rule

    Since an unsafe condition has been identified that is likely to 
exist or develop on other products of this same type design, the 
proposed AD would require accomplishment of the actions specified in 
the applicable service bulletins described previously. The proposed AD 
would also require that operators report inspection findings of broken 
bolts to the FAA.

Cost Impact

    There are approximately 104 airplanes of the affected design in the 
worldwide fleet. The FAA estimates that 76 airplanes of U.S. registry 
would be affected by this proposed AD, that it would take approximately 
44 or 600 work hours per airplane (depending on configuration) to 
accomplish the proposed inspection, 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 $2,640 or $36,000 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 proposed AD were not adopted. However, the FAA has 
been advised that the actions specified in this proposed AD have 
already been accomplished on a number of airplanes that are subject to 
this AD. Therefore, the future economic cost impact of this rule on 
U.S. operators is expected to be reduced. 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. The manufacturer may cover the cost of 
replacement parts associated with this proposed AD, subject to warranty 
conditions. Manufacturer warranty remedies may also be available for 
labor costs associated with this proposed AD. As a result, the costs 
attributable to the proposed AD may be less than stated above.

Regulatory Impact

    The regulations proposed herein would not have a substantial direct 
effect 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, 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 2001-NM-18-AD.

    Applicability: Model Hawker 800XP and 800 (including variant U-
125A) airplanes, certificated in any category, serial numbers 258287 
through 258390, excluding the following serial numbers:

258289
258291
258292
258293
258294
258295
258301
258303
258310
258312
258313
258315
258321
258336
258343

    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 (e) 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 failure of certain attachment bolts due to 
manufacturing discrepancies,

[[Page 71507]]

which could result in reduced structural integrity of the airplane, 
and loss of system function for flaps, controls, and landing gear, 
accomplish the following:

Inspection for Ravenstone Jackson Bolts

    (a) Perform a general visual inspection to identify the type of 
bolts installed at specified locations of the wing and fuselage, in 
accordance with paragraphs (a)(1), (a)(2), (a)(3), (a)(4), and 
(a)(5), as applicable, of this AD.

    Note 2: For the purposes of this AD, a general visual inspection 
is defined as: ``A visual examination of an interior or exterior 
area, installation, or assembly to detect obvious damage, failure, 
or irregularity. This level of inspection is made from within 
touching distance unless otherwise specified. A mirror may be 
necessary to enhance visual access to all exposed surfaces in the 
inspection area. This level of inspection is made under normally 
available lighting conditions such as daylight, hangar lighting, 
flashlight, or droplight and may require removal or opening of 
access panels or doors. Stands, ladders, or platforms may be 
required to gain proximity to the area being checked.''

    (1) For Model Hawker 800XP airplanes identified in the 
effectivity of Raytheon Service Bulletin SB 51-3408, dated October 
2000: Inspect within 12 months after the effective date of this AD 
in accordance with the service bulletin.
    (2) For Model Hawker 800XP airplanes identified in the 
effectivity of Raytheon Service Bulletin SB 51-3426, Revision 1, 
dated November 2001: Inspect within 18 months after the effective 
date of this AD in accordance with the service bulletin. Inspection 
before the effective date of this AD in accordance with Raytheon 
Service Bulletin SB 51-3426, dated December 2000, is acceptable for 
compliance with the inspection requirements only for those locations 
identified in the original service bulletin; this AD requires 
inspections at additional locations in accordance with Revision 1 of 
the service bulletin.
    (3) For Model Hawker 800 (including variant U-125A) airplanes 
identified as Group A airplanes in Raytheon Service Bulletin SB 51-
3421, Revision 1, dated November 2001: Inspect within 12 months 
after the effective date of this AD in accordance with the service 
bulletin. Inspection before the effective date of this AD in 
accordance with Raytheon Service Bulletin SB 51-3421, dated December 
2000, is acceptable for compliance with this inspection requirement 
for Group A airplanes.
    (4) For Model Hawker 800 (including variant U-125A) airplanes 
identified as Group B airplanes in Raytheon Service Bulletin SB 51-
3421, Revision 1, dated November 2001: Inspect within 18 months 
after the effective date of this AD in accordance with the service 
bulletin. Inspection before the effective date of this AD in 
accordance with Raytheon Service Bulletin SB 51-3421, dated December 
2000, is acceptable for compliance with the inspection requirement 
only for those locations identified in the original service 
bulletin; this AD requires inspections at additional locations in 
accordance with Revision 1 of the service bulletin.
    (5) For Model Hawker 800 (including variant U-125A) airplanes 
identified as Group C airplanes in Raytheon Service Bulletin SB 51-
3421, Revision 1, dated November 2001: Inspect within 12 months 
after the effective date of this AD in accordance with the service 
bulletin. Inspection before the effective date of this AD in 
accordance with Raytheon Service Bulletin SB 51-3421, dated December 
2000, is acceptable for compliance with the inspection requirement 
only for those locations identified in the original service 
bulletin; this AD requires inspections at additional locations in 
accordance with Revision 1 of the service bulletin.

Inspection for Broken Bolts

    (b) For any discrepant bolt (any Ravenstone Jackson DHS bolt or 
any bolt that cannot be identified) found during the inspection 
required by paragraph (a) of this AD: Before further flight 
following detection of the discrepant bolt, perform an ultrasonic 
inspection to determine if the bolt is broken, in accordance with 
the applicable service bulletin identified in paragraph (a) of this 
AD. Replace any broken bolt with a new bolt before further flight, 
in accordance with the applicable service bulletin.

Reporting Requirement

    (c) If any broken bolt is found during the inspection specified 
in paragraph (b) of this AD: Send an inspection report at the 
applicable time specified in paragraph (c)(1) or (c)(2) of this AD 
to the Manager, Wichita Aircraft Certification Office (ACO), 1801 
Airport Road, Room 100, Mid-Continent Airport, Wichita, Kansas 
67209; fax (316) 946-4407. The report must include the inspection 
results, a description of all discrepancies found, and the airplane 
serial number. Information collection requirements contained in this 
AD have been approved by the Office of Management and Budget (OMB) 
under the provisions of the Paperwork Reduction Act of 1980 (44 
U.S.C. 3501 et seq.) and have been assigned OMB Control Number 2120-
0056.
    (1) For airplanes on which the inspection is accomplished after 
the effective date of this AD: Submit the report within 30 days 
after performing the inspection required by paragraph (a) of this 
AD.
    (2) For airplanes on which the inspection has been accomplished 
prior to the effective date of this AD: Submit the report within 90 
days after the effective date of this AD.

Part Installation

    (d) As of the effective date of this AD, no person may install 
on any airplane a Ravenstone Jackson DHS bolt having a batch number 
identified in paragraph 3.B. of Raytheon Service Bulletin SB 51-
3426, Revision 1, dated November 2001; paragraph 3.A. Raytheon 
Service Bulletin SB 51-3421, Revision 1, dated November 2001; or 
paragraph 2.B. of Raytheon Service Bulletin SB 51-3408, dated 
October 2000.

Alternative Methods of Compliance

    (e) 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 ACO. 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

    (f) 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 November 22, 2002.
Ali Bahrami,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 02-30346 Filed 11-29-02; 8:45 am]
BILLING CODE 4910-13-P