[Federal Register Volume 66, Number 108 (Tuesday, June 5, 2001)]
[Proposed Rules]
[Pages 30107-30109]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 01-14044]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 2000-NM-373-AD]
RIN 2120-AA64


Airworthiness Directives; 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

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 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. This proposed AD would require an inspection for cracking or 
corrosion of the cylinder head lugs of the main landing gear (MLG) 
actuator and follow-on/corrective actions. This proposed AD is prompted 
by reports of attachment lugs cracking at the actuator cylinder head. 
This action is necessary to prevent separation of the cylinder head 
lugs, which could prevent the MLG from extending and result in a 
partial gear-up landing. This action is intended to address the 
identified unsafe condition.

DATES: Comments must be received by July 20, 2001.

ADDRESSES: Submit comments in triplicate to the Federal Aviation 
Administration (FAA), Transport Airplane Directorate, ANM-114, 
Attention: Rules Docket No. 2000-NM-373-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: 
<a href="/cdn-cgi/l/email-protection#556c78343b38783b252738363a3838303b21153334347b323a23"><span class="__cf_email__" data-cfemail="5b62763a353676352b2936383436363e352f1b3d3a3a753c342d">[email protected]</span></a>. Comments sent via fax or the Internet must 
contain ``Docket No. 2000-NM-373-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, Wichita, Kansas.

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:

[[Page 30108]]

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:
    <bullet> 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.
    <bullet> For each issue, state what specific change to the proposed 
AD is being requested.
    <bullet> 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 2000-NM-373-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. 2000-NM-373-AD, 1601 Lind Avenue, SW., Renton, Washington 
98055-4056.

Discussion

    The FAA has received reports of cracking of the cylinder head lugs 
of the main landing gear (MLG) actuator. Such cracking of the cylinder 
heads could result in separation of the cylinder head lugs, which could 
prevent the MLG from extending. This condition, if not corrected, could 
result in a partial gear-up landing.

Explanation of Relevant Service Information

    The FAA has reviewed and approved Raytheon Service Bulletin (SB) 
32-3391, dated August 2000. The service bulletin describes procedures 
for performing a one-time eddy current inspection to detect cracking or 
corrosion of the cylinder head lugs of the MLG and follow-on/corrective 
actions. The follow-on/corrective actions include ``vibro-etching'' the 
MLG actuator data plate, painting a blue stripe on the actuator 
cylinder head, and replacing bushings; applying corrosion protection to 
the lug bores; and replacing the actuator with a new or overhauled 
actuator or replacement of the actuator cylinder head with a new 
cylinder head, as applicable.

Additional Source of Service Information

    The Raytheon service bulletin references Precision Hydraulics 
Cylinder Maintenance Manual 32-30-1105 for additional service 
information regarding the replacement of the actuator cylinder head 
with a new cylinder head.

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 doing the actions specified in the Raytheon 
service bulletin described previously. The actions would be required to 
be accomplished in accordance with the Raytheon service bulletin 
described previously.

Cost Impact

    There are approximately 1,000 airplanes of the affected design in 
the worldwide fleet. The FAA estimates that this proposed AD would 
affect 650 airplanes of U.S. registry. The proposed inspection would 
take approximately 20 work hours per airplane, at an average labor rate 
of $60 per work hour. Based on these figures, we estimate the cost of 
the proposed AD on U.S. operators 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 proposed requirements of 
this AD action, and that no operator would accomplish those actions in 
the future if this proposed 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 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 2000-NM-373-AD.

    Applicability: 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, as listed in Raytheon 
Service Bulletin SB 32-3391, dated August 2000; 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

[[Page 30109]]

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, do the following:

Inspection

    (a) Perform an eddy current inspection of the actuator cylinder 
head lugs for cracking or corrosion per Raytheon Service Bulletin SB 
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 SB 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 SB 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.

    Note 2: Raytheon Service Bulletin SB 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 
Secs. 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 May 30, 2001.
Vi L. Lipski,
Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 01-14044 Filed 6-4-01; 8:45 am]
BILLING CODE 4910-13-P


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