[Federal Register Volume 66, Number 168 (Wednesday, August 29, 2001)]
[Rules and Regulations]
[Pages 45575-45577]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 01-21491]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 2000-NM-373-AD; Amendment 39-12417; AD 2001-17-26]
RIN 2120-AA64


Airworthiness Directives; Raytheon Model DH.125, HS.125, BH.125, 
and BAe. 125 (U-125 and C-29A) Series Airplanes; Model Hawker 800, 
Hawker 800 (U-125A), Hawker 800XP, and Hawker 1000 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 DH.125, HS.125, BH.125, and BAe. 
125 (U-125 and C-29A) series airplanes; Model Hawker 800, Hawker 800 
(U-125A), Hawker 800XP, and Hawker 1000 airplanes, that requires an 
inspection for cracking or corrosion of the cylinder head lugs of the 
main landing gear (MLG) actuator and follow-on/corrective actions. This 
amendment is prompted by reports of attachment lugs cracking at the 
actuator cylinder head. The actions specified by this AD are intended 
to prevent separation of the cylinder head lugs, which could prevent 
the MLG from extending and result in a partial gear-up landing.

DATES: Effective October 3, 2001.
    The incorporation by reference of certain publications listed in 
the regulations is approved by the Director of the Federal Register as 
of October 3, 2001.

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 
Federal

[[Page 45576]]

Aviation Administration (FAA), Transport Airplane Directorate, Rules 
Docket, 1601 Lind Avenue, SW., Renton, Washington; or at the FAA, 
Wichita Aircraft Certification Office, 1801 Airport Road, Room 100, 
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 Model DH.125, 
HS.125, BH.125, and BAe 125 (U-125 and C-29A) series airplanes, and 
Hawker 800, Hawker 800 (U-125A), Hawker 800XP, and Hawker 1000 
airplanes was published in the Federal Register on June 5, 2001 (66 FR 
30107). That action proposed to require an inspection to detect 
cracking or corrosion of the cylinder head lugs of the main landing 
gear (MLG) and follow-on/corrective actions.

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 1,000 airplanes of the affected design in 
the worldwide fleet. The FAA estimates that 650 airplanes of U.S. 
registry will be affected by this AD, that it will take approximately 
20 work hours 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 
$780,000, or $1,200 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.

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:

2001-17-26  Raytheon Aircraft Company: Amendment 39-12417. Docket 
2000-NM-373-AD.

    Applicability: Model DH.125, HS.125, BH.125, and BAe. 125 (U-125 
and C-29A) series airplanes; Model Hawker 800, Hawker 800 (U-125A), 
Hawker 800XP, and Hawker 1000 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 separation of the cylinder head lugs, which could 
prevent the main landing gear (MLG) from extending and result in a 
partial gear-up landing, accomplish the following:

Inspection

    (a) Perform an eddy current inspection of the actuator cylinder 
head lugs for cracking or corrosion per Raytheon Service Bulletin 
32-3391, dated August 2000, at the time specified in paragraph 
(a)(1), (a)(2), (a)(3), or (a)(4) of this AD, as applicable.
    (1) For actuator cylinder heads that have 3,000 or less total 
landings as of the effective date of this AD: Perform the eddy 
current inspection within 24 months after the effective date of this 
AD.
    (2) For actuator cylinder heads that have 3,001 to 4,000 total 
landings as of the effective date of this AD: Perform the eddy 
current inspection within 6 months after the effective date of this 
AD.
    (3) For actuator cylinder heads that have been in service for 
more than 7 years as of the effective date of this AD: Perform the 
eddy current inspection within 6 months of the effective date of 
this AD.
    (4) For actuator cylinder heads that have 4,001 or more total 
landings as of the effective date of this AD: Perform the eddy 
current inspection within 10 landings after the effective date of 
this AD.

If No Cracking or Corrosion

    (b) If no cracking or corrosion is found during the inspection 
required by paragraph (a) of this AD, before further flight, 
accomplish the follow-on actions (e.g., ``vibro-etching'' the MLG 
actuator data plate, painting a blue stripe on the actuator cylinder 
head to indicate \1/32\ inch oversize bushings, replacing bushings, 
and applying corrosion protection to the lug bores), per Raytheon 
Service Bulletin 32-3391, dated August 2000.

If Any Cracking or Corrosion

    (c) If any cracking or corrosion is found during the inspection 
required by paragraph (a) of this AD, before further flight, 
accomplish either of the actions specified in paragraph (c)(1) or 
(c)(2) of this AD, per Raytheon Service Bulletin 32-3391, dated 
August 2000.
    (1) Replace the actuator of the MLG with a new or serviceable 
actuator, or
    (2) Replace the actuator cylinder head with a new cylinder head.


[[Page 45577]]


    Note 2: Raytheon Service Bulletin 32-3391, dated August 2000, 
references Precision Hydraulics Cylinder Maintenance Manual (CMM) 
32-30-1105 as an additional source of service information.

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 Permit

    (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.

Incorporation by Reference

    (f) The actions shall be done in accordance with Raytheon 
Service Bulletin 32-3391, dated August 2000. 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, 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 October 3, 2001.

    Issued in Renton, Washington, on August 20, 2001.
Vi L. Lipski,
Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 01-21491 Filed 8-28-01; 8:45 am]
BILLING CODE 4910-13-P