AD 2003-07-07

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.

Final rule.

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 including serial numbers 258493.
none.
Hawker 800XP
Up to and including serial numbers 258581.
Dunlop wheels part numbers AH51909, 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 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 requestshould 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 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.

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.

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 aresult, 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

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.

39.13 [Amended]

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