[Federal Register Volume 68, Number 58 (Wednesday, March 26, 2003)]
[Rules and Regulations]
[Pages 14530-14532]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 03-6966]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 2001-NM-18-AD; Amendment 39-13093; AD 2003-06-06]
RIN 2120-AA64


Airworthiness Directives; Raytheon Model Hawker 800XP and 800 
(Including Variant U-125A) Airplanes

AGENCY: Federal Aviation Administration, DOT.

ACTION: Final rule.

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SUMMARY: This amendment adopts a new airworthiness directive (AD), 
applicable to certain Raytheon Model Hawker 800XP and 800 (including 
variant U-125A) airplanes, that requires a one-time inspection to 
identify the bolts installed at certain locations in the wing or 
fuselage, and corrective actions if necessary. The actions specified by 
this AD are intended 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: Effective April 30, 2003.
    The incorporation by reference of certain publications listed in 
the regulations is approved by the Director of the Federal Register as 
of April 30, 2003.

ADDRESSES: The service information referenced in this AD 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; or at 
the Office of the Federal Register, 800 North Capitol Street, NW., 
suite 700, Washington, DC.

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: A proposal to amend part 39 of the Federal 
Aviation Regulations (14 CFR part 39) to include an airworthiness 
directive (AD) that is applicable to certain Raytheon Model Hawker 
800XP and 800 (including variant U-125A) airplanes was published in the 
Federal Register on December 2, 2002 (67 FR 71505). That action 
proposed to require a one-time inspection to identify the bolts 
installed at certain locations in the wing or fuselage, and corrective 
actions if necessary.

Comments

    Interested persons have been afforded an opportunity to participate 
in the making of this amendment. No comments were submitted in response 
to the proposal or the FAA's determination of the cost to the public.

Explanation of Editorial Changes

    In the notice of proposed rulemaking (NPRM) we stated that, for 
Model

[[Page 14531]]

Hawker 800 (including variant U-125A) airplanes, the proposed actions 
should be accomplished in accordance with Raytheon Service Bulletin SB 
51-3421, Revision 1, dated November 2001. Both Revision 1 and the 
original issue of that service bulletin reference Appendix 1, dated 
December 2000, as an additional source of service information for 
performing the actions required by this final rule. Therefore, we have 
changed the service bulletin citation throughout this final rule to 
include Appendix 1.
    We also stated in the NPRM that the proposed actions were to be 
accomplished per Raytheon Service Bulletins SB 51-3408, dated October 
2000; and SB 51-3426, Revision 1, dated November 2001. However, SB 51-
3408, SB 51-3426, and SB 51-3421 have an attached form titled Service 
Bulletin/Kit Drawing Report Fax. Throughout this final rule the 
citations for these service bulletins have been changed to exclude the 
form. Although this final rule does include a reporting requirement, it 
does not require that this form be completed by operators and submitted 
to the airplane manufacturer.

Conclusion

    After careful review of the available data, we have determined that 
air safety and the public interest require the adoption of the rule 
with the changes previously described. We have determined that these 
changes will neither increase the economic burden on any operator nor 
increase the scope of the AD.

Cost Impact

    There are approximately 104 airplanes of the affected design in the 
worldwide fleet. We estimate that 76 airplanes of U.S. registry will be 
affected by this AD, that it will take approximately 44 or 600 work 
hours per airplane (depending on configuration) to accomplish the 
required inspection, and that the average labor rate is $60 per work 
hour. Based on these figures, the cost impact of this 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 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. The manufacturer may cover the cost of 
replacement parts associated with this AD, subject to warranty 
conditions. Manufacturer warranty remedies may also be available for 
labor costs associated with this AD. As a result, the costs 
attributable to the AD may be less than stated above.

Regulatory Impact

    The regulations adopted herein will 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 final rule does not have federalism 
implications under Executive Order 13132.
    For the reasons discussed above, I certify that this action (1) is 
not a ``significant regulatory action'' under Executive Order 12866; 
(2) is not a ``significant rule'' under DOT Regulatory Policies and 
Procedures (44 FR 11034, February 26, 1979); and (3) 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 final evaluation has been prepared for this action 
and it is contained in the Rules Docket. A copy of it may be obtained 
from the Rules Docket at the location provided under the caption 
ADDRESSES.

List of Subjects in 14 CFR Part 39

    Air transportation, Aircraft, Aviation safety, Incorporation by 
reference, Safety.

Adoption of the Amendment

    Accordingly, pursuant to the authority delegated to me by the 
Administrator, the Federal Aviation Administration amends 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:

2003-06-06 Raytheon Aircraft Company: Amendment 39-13093. 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, 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, excluding Service Bulletin/Kit Drawing Report Fax: 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, excluding Service Bulletin/Kit Drawing Report 
Fax: 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, excluding Service 
Bulletin/Kit Drawing Report Fax, is acceptable for compliance with 
the inspection requirements

[[Page 14532]]

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, including Appendix 1, dated 
December 2000, excluding Service Bulletin/Kit Drawing Report Fax: 
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, including Appendix 1, dated December 2000, 
excluding Service Bulletin/Kit Drawing Report Fax, 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, including Appendix 1, dated 
December 2000, excluding Service Bulletin/Kit Drawing Report Fax: 
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, including Appendix 1, dated December 2000, 
excluding Service Bulletin/Kit Drawing Report Fax, 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, including Appendix 1, dated 
December 2000, excluding Service Bulletin/Kit Drawing Report Fax: 
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, including Appendix 1, dated December 2000, 
excluding Service Bulletin/Kit Drawing Report Fax, 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.

Incorporation by Reference

    (g) Unless otherwise specified in this AD, the actions shall be 
done in accordance with Raytheon Service Bulletin SB 51-3408, dated 
October 2000, excluding Service Bulletin/Kit Drawing Report Fax; 
Raytheon Service Bulletin SB 51-3426, Revision 1, dated November 
2001, excluding Service Bulletin/Kit Drawing Report Fax; or Raytheon 
Service Bulletin SB 51-3421, Revision 1, dated November 2001, 
including Appendix 1, dated December 2000, and excluding Service 
Bulletin/Kit Drawing Report Fax; as applicable. Raytheon Service 
Bulletin SB 51-3421, Revision 1, contains the following list of 
effective pages:

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                                  Revision level
           Page No.               shown on page     Date shown  on page
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1, 3, 37, 49-51...............  1................  November 2001.
2, 4-36, 38-48, 52-171........  Original.........  December 2000.
                                Appendix 1.......
1-11..........................  Original.........  December 2000.
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This incorporation by reference was approved by the Director of the 
Federal Register in accordance with 5 U.S.C. 552(a) and 1 CFR part 
51. Copies may be obtained from Raytheon Aircraft Company, 
Department 62, P.O. Box 85, Wichita, Kansas 67201-0085. Copies may 
be inspected 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; or at the Office of the Federal Register, 
800 North Capitol Street, NW., suite 700, Washington, DC.

Effective Date

    (h) This amendment becomes effective on April 30, 2003.

    Issued in Renton, Washington, on March 18, 2003.
Michael J. Kaszycki,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 03-6966 Filed 3-25-03; 8:45 am]
BILLING CODE 4910-13-P