Airworthiness Directives; Raytheon Model BAe.125 Series 800A, 800A (C-29A), 800A (U-125), and 800B Airplanes; Model BH.125 Series 400A Airplanes; Model DH.125 Series Airplanes; Model Hawker 800, 800 (U-125A), and 800XP Airplanes; and Model HS.125 Series F3B, F3B/RA, F400B, F403B, 1B, 1B-522, 1B/R-522, 1B/S-522, 3B, 3B/R, 3B/RA, 3B/RB, 3B/RC, 400B, 400B/1, 401B, 403A(C), and 403B Airplanes

[Federal Register Volume 68, Number 64 (Thursday, April 3, 2003)]
[Rules and Regulations]
[Pages 16205-16207]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 03-8064]


-----------------------------------------------------------------------

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 2002-NM-268-AD; Amendment 39-13103; AD 2003-07-07]
RIN 2120-AA64


Airworthiness Directives; Raytheon Model BAe.125 Series 800A, 
800A (C-29A), 800A (U-125), and 800B Airplanes; Model BH.125 Series 
400A Airplanes; Model DH.125 Series Airplanes; Model Hawker 800, 800 
(U-125A), and 800XP Airplanes; and Model HS.125 Series F3B, F3B/RA, 
F400B, F403B, 1B, 1B-522, 1B/R-522, 1B/S-522, 3B, 3B/R, 3B/RA, 3B/RB, 
3B/RC, 400B, 400B/1, 401B, 403A(C), and 403B Airplanes

AGENCY: Federal Aviation Administration, DOT.

ACTION: Final rule.

-----------------------------------------------------------------------

SUMMARY: This amendment adopts a new airworthiness directive (AD), 
applicable to certain Raytheon airplanes, that requires inspection of 
the main landing gear (MLG) wheels to determine the part numbers of the 
tie-bolt nuts, and replacement of nuts that have the incorrect part 
number with nuts that have the correct part number. The actions 
specified by this AD are intended to prevent separation of an MLG wheel 
due to loose or missing tie-bolts or tie-bolt nuts, with consequent 
damage to airplane structure or systems, decompression, loss of full 
braking ability, or injury to personnel on the ground. This action is 
intended to address the identified unsafe condition.

DATES: Effective May 8, 2003.
    The incorporation by reference of certain publications listed in 
the regulations is approved by the Director of the Federal Register as 
of May 8, 2003.

ADDRESSES: The service information referenced in this AD may be 
obtained from Raytheon Aircraft Company, Department 62, PO Box 85, 
Wichita, Kansas 67201-0085. This information may be examined at the 
Federal Aviation Administration (FAA), Transport Airplane Directorate, 
Rules Docket, 1601 Lind Avenue, SW., Renton, Washington; 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, Aerospace Engineer, 
Airframe Branch, ACE-118W, FAA, Wichita Aircraft Certification Office, 
1801 Airport Road, Room 100, 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 airplanes was 
published in the Federal Register on January 3, 2003 (68 FR 322). That 
action proposed to require inspection of the main landing gear (MLG) 
wheels to determine the part numbers of the tie-bolt nuts, and 
replacement of nuts that have the incorrect part number with nuts that 
have the correct part number.

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.

Conclusion

    The FAA has determined that air safety and the public interest 
require the adoption of the rule as proposed.

[[Page 16206]]

Cost Impact

    There are approximately 166 airplanes of the affected design in the 
worldwide fleet. The FAA estimates that 84 airplanes of U.S. registry 
will be affected by this AD, that it will take approximately 1 work 
hour per airplane to accomplish the required inspection, and that the 
average labor rate is $60 per work hour. Based on these figures, the 
cost impact of the AD on U.S. operators is estimated to be $5,040, or 
$60 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. Manufacturer warranty remedies may 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 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

0
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

0
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]

0
2. Section 39.13 is amended by adding the following new airworthiness 
directive:

2003-07-07 Raytheon Aircraft Company: Amendment 39-13103. Docket 
2002-NM-268-AD.

    Applicability: The following airplanes, certificated in any 
category:

          Table--Airplane Models, Serial Numbers, and Equipment
------------------------------------------------------------------------
             Model--                 Serial No.--       Equipped with--
------------------------------------------------------------------------
BAe.125 series 800A.............  All...............  none.
BAe.125 series 800A (C-29A).....  All...............  none.
BAe.125 series 800A (U-125).....  All...............  none.
BAe.125 series 800B.............  All...............  none.
BH.125 series 400A..............  All...............  none.
DH.125 series airplanes.........  All...............  none.
Hawker 800......................  All...............  none.
Hawker 800 (U-125A).............  Up to and           none.
                                   including serial
                                   numbers 258493.
Hawker 800XP....................  Up to and           Dunlop wheels part
                                   including serial    numbers AH51909,
                                   numbers 258581.     AH52075, AH52286,
                                                       AH52206, AHA1287,
                                                       AHA1606, or
                                                       AHA1814.
HS.125 series F3B...............  All...............  none.
HS.125 series F3B/RA............  All...............  none.
HS.125 series F400B.............  All...............  none.
HS.125 series F403B.............  All...............  none.
HS.125 series 1B................  All...............  none.
HS.125 series 1B-522............  All...............  none.
HS.125 series 1B/R-522..........  All...............  none.
HS.125 series 1B/S-522..........  All...............  none.
HS.125 series 3B................  All...............  none.
HS.125 series 3B/R..............  All...............  none.
HS.125 series 3B/RA.............  All...............  none.
HS.125 series 3B/RB.............  All...............  none.
HS.125 series 3B/RC.............  All...............  none.
HS.125 series 400B..............  All...............  none.
HS.125 series 400B/1............  All...............  none.
HS.125 series 401B..............  All...............  none.
HS.125 series 403A(C)...........  All...............  none.
HS.125 series 403B..............  All...............  none.
------------------------------------------------------------------------


    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

[[Page 16207]]

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 separation of a main landing gear (MLG) wheel due to 
loose or missing tie-bolts or tie-bolt nuts, with consequent damage 
to airplane structure or systems, decompression, loss of full 
braking ability, or injury to personnel on the ground, accomplish 
the following:

Inspection

    (a) Within 10 landings or 12 days after the effective date of 
this AD, whichever comes first, inspect the MLG wheels to determine 
the part numbers (P/Ns) of the tie-bolt nuts; per Raytheon Service 
Bulletin SB 32-3522, dated September 2002, excluding Service 
Bulletin/Kit Drawing Report Fax.

Replacement

    (b) If any tie-bolt nut having P/N NAS1804 is found installed 
during the inspection required by paragraph (a) of this AD, before 
further flight, replace the tie-bolt nut with a new nut having P/N 
FN22A524, (or with a new tie-bolt nut having a Dunlop P/N H5227C-
5CW, SN407C-054, or LH13318-5, which are P/Ns authorized by 
Raytheon); per Raytheon Service Bulletin SB 32-3522, dated September 
2002, excluding Service Bulletin/Kit Drawing Report Fax.

Parts Installation

    (c) As of the effective date of this AD, no person shall install 
any MLG wheel having a tie-bolt nut with P/N NAS1804, on any 
airplane.

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 2: 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 
Sec. Sec.  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

    (f) Unless otherwise provided by this AD, the actions shall be 
done per Raytheon Service Bulletin SB 32-3522, dated September 2002, 
excluding Service Bulletin/Kit Drawing Report Fax. 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, PO Box 85, Wichita, Kansas 67201-0085. Copies may be 
inspected at the FAA, Transport Airplane Directorate, 1601 Lind 
Avenue, SW., Renton, Washington; 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

    (g) This amendment becomes effective on May 8, 2003.

    Issued in Renton, Washington, on March 28, 2003.
Michael J. Kaszycki,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 03-8064 Filed 4-2-03; 8:45 am]
BILLING CODE 4910-13-P

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