[Federal Register Volume 67, Number 169 (Friday, August 30, 2002)]
[Proposed Rules]
[Pages 55742-55744]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 02-22178]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 2002-NM-15-AD]
RIN 2120-AA64


Airworthiness Directives; Raytheon Model DH.125, HS.125, and 
BH.125 Series Airplanes; Model BAe.125 Series 800A, 800A (C-29A), 800A 
(U-125), 800B, 1000A, and 1000B Airplanes; and Model Hawker 800, 800 
(U-125A), 1000, and 800XP Airplanes

AGENCY: Federal Aviation Administration, DOT.

ACTION: Notice of proposed rulemaking (NPRM).

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SUMMARY: This document proposes the supersedure of an existing 
airworthiness directive (AD); applicable to certain Raytheon Model 
DH.125, HS.125, BH.125, and BAe.125 (U-125 and C-29A) series airplanes; 
and Model Hawker 800, Hawker 800 (U-125A), Hawker 800XP, and Hawker 
1000 airplanes; that currently 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 action proposes to 
expand the applicability of the existing AD to add an airplane model 
and further clarify the applicability; and, for certain airplanes, to 
clarify the compliance time of the inspection requirements. The actions 
specified by the proposed 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: Comments must be received by October 15, 2002.

ADDRESSES: Submit comments in triplicate to the Federal Aviation 
Administration (FAA), Transport Airplane Directorate, ANM-114, 
Attention: Rules Docket No. 2002-NM-15-AD, 1601 Lind Avenue, SW., 
Renton, Washington 98055-4056. Comments may be inspected at this 
location between 9 a.m. and 3 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: 
[email protected]. Comments sent via fax or the Internet must 
contain ``Docket No. 2002-NM-15-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: Technical Information: 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.
    Other Information: Sandi Carli, Airworthiness Directive Technical 
Editor/Writer; telephone (425) 687-4242, fax (425) 227-1232. Questions 
or comments may also be sent via the Internet using the following 
address: [email protected]. Questions or comments sent via the 
Internet as attached electronic files must be formatted in Microsoft 
Word 97 for Windows or ASCII text.

SUPPLEMENTARY INFORMATION:

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:
     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.
     For each issue, state what specific change to the proposed 
AD is being requested.
     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

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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 2002-NM-15-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. 2002-NM-15-AD, 1601 Lind Avenue, SW., Renton, Washington 
98055-4056.

Discussion

    On January 18, 2002, the FAA issued AD 2001-17-26 R1, amendment 39-
12619 (67 FR 4171, January 29, 2002), applicable to certain Raytheon 
Model DH.125, HS.125, BH.125, and BAe.125 (U-125 and C-29A) series 
airplanes; and Model Hawker 800, Hawker 800 (U-125A), Hawker 800XP, and 
Hawker 1000 airplanes; to require an inspection for cracking or 
corrosion of the cylinder head lugs of the main landing gear (MLG) 
actuator and follow-on/corrective actions. The requirements of that 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.

Actions Since Issuance of Previous Rule

    Since the issuance of that AD, the FAA has determined that the 
applicability should be expanded to be consistent with the effectivity 
specified in Raytheon Service Bulletin 32-3391, dated August 2000 
(which is referenced as the appropriate source of service information 
for that AD), and revised to identify model designations as published 
in the most recent type certificate data sheet for the affected models. 
In addition, we have determined that the compliance time for the 
inspection requirements in that AD needs to be clarified in paragraph 
(b) of the final rule. Therefore, we have determined that further 
rulemaking is necessary, and this proposed AD follows from that 
determination.

Explanation of Requirements of Proposed AD

    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 supersede AD 2001-17-26 R1 to continue to require an 
inspection for cracking or corrosion of the cylinder head lugs of the 
MLG actuator, and follow-on/corrective actions. The proposed AD also 
would expand and clarify the applicability of the existing AD per the 
referenced service bulletin and type certificate data sheet, and, for 
certain airplanes, clarify the compliance time for the inspection 
requirements in paragraph (b)(3) of this AD. This proposed AD is 
intended to prevent separation of the cylinder head lugs, which could 
prevent the MLG from extending and result in a partial gear-up landing.

Explanation of Changes to AD 2001-17-26 R1

    This proposed AD differs from AD 2001-17-26 R1 in that the 
applicability includes all of the airplane models cited in the 
effectivity of the referenced service bulletin. This change was 
necessary to include Model BAe.125 Series 800B airplanes, because that 
model was not specified in the applicability of AD 2001-17-26 R1. The 
change also clarifies model designations per the most recent type 
certificate data sheet.
    We have further clarified the applicability of this proposed AD to 
specify airplane models ``as listed in Raytheon Service Bulletin 32-
3391, dated August 2000.'' This change is necessary because the 
effectivity of the service bulletin also specifies that accomplishment 
of the service bulletin is not necessary for airplanes installed with 
an MLG actuator having part numbers ``AIR48502-5 and AIR48503-5, or 
DOIW00839-1 and DOIW00839-2.''
    We also have clarified the compliance time for the inspection 
requirements in paragraphs (b), (b)(3)(i), and (b)(3)(ii) of this AD 
for Model BAe.125 series 800B airplanes, because an actuator cylinder 
head could have been in service for more than 7 years and have 4,001 or 
more total landings as of the effective date of this AD.

Cost Impact

    There are approximately 1,000 airplanes of the affected design in 
the worldwide fleet. We estimate that 650 airplanes of U.S. registry 
would be affected by this proposed AD.
    The actions that are currently required by AD 2001-17-26 R1, and 
retained in this proposed AD, take approximately 20 work hours per 
airplane to accomplish, at an average labor rate of $60 per work hour. 
Based on these figures, the cost impact of the currently required 
actions on U.S. operators is estimated to be $780,000, or $1,200 per 
airplane.
    This proposed AD does not add any new actions or requirements, and 
only revises the applicability of the AD by adding an airplane model, 
clarifying the model designations, and clarifying the compliance time 
for the inspection requirements for certain airplanes. Therefore, the 
estimated cost impact for this proposed AD is unchanged from the 
existing AD.
    The cost impact figure discussed above is based on assumptions that 
no operator has yet accomplished any of the current or proposed 
requirements of this AD action, and that no operator would accomplish 
those actions in the future if this AD were not adopted. However, for 
affected airplanes within the period under the warranty agreement, the 
FAA has been advised that the manufacturer has committed previously to 
its customers that it will bear the cost of replacement parts. The FAA 
also has been advised that manufacturer warranty remedies are available 
for labor costs associated with accomplishing the actions required by 
this proposed AD. Therefore, the future economic cost impact of this AD 
may be less than the cost impact figure indicated above. 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

[[Page 55744]]

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 removing amendment 39-12619 (67 FR 
4171, January 29, 2002), and by adding a new airworthiness directive 
(AD), to read as follows:

Raytheon Aircraft Company: Docket 2002-NM-15-AD. Supersedes AD 2001-
17-26 R1, Amendment 39-12619.

    Applicability: Model DH.125, HS.125, and BH.125 series 
airplanes; Model BAe.125 series 800A, 800A (C-29A), 800A (U-125), 
800B, 1000A, and 1000B airplanes; and Model Hawker 800, 800 (U-
125A), 1000, and 800XP airplanes; as listed in Raytheon Service 
Bulletin 32-3391, dated August 2000.

    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 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:

Restatement of Certain Requirements of AD 2001-17-26 R1

Inspection

    (a) For Model DH.125, HS.125, and BH.125 series airplanes; 
BAe.125 series 800A, 800A (C-19A), 800A (U-125A), 1000A, and 1000B 
airplanes; and Model Hawker 800, 800 (U-125A), 800XP, and 1000 
airplanes: 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 October 3, 2001 (the effective date of AD 2001-17-26 
R1, amendment 39-12619): Perform the eddy current inspection within 
24 months after October 3, 2001.
    (2) For actuator cylinder heads that have 3,001 to 4,000 total 
landings as of October 3, 2001: Perform the eddy current inspection 
within 6 months after October 3, 2001.
    (3) For actuator cylinder heads that have been in service for 
more than 7 years as of October 3, 2001: Perform the eddy current 
inspection within 6 months after October 3, 2001.
    (4) For actuator cylinder heads that have 4,001 or more total 
landings as of October 3, 2001: Perform the eddy current inspection 
within 10 landings after October 3, 2001.

New Requirements of This AD

    (b) For Model BAe.125 series 800B airplanes: 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 (b)(1), (b)(2), or (b)(3) 
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 or that have 4,001 or more total landings as of 
the effective date of this AD: Perform the eddy current inspection 
at the earlier of the times specified in paragraph (b)(3)(i) or 
(b)(3)(ii) of this AD:
    (i) Within 6 months after the effective date of this AD; or
    (ii) Within 10 landings after the effective date of this AD.

If No Cracking or Corrosion

    (c) If no cracking or corrosion is found during the inspection 
required by paragraph (a) or (b) of this AD, before further flight, 
accomplish 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

    (d) If any cracking or corrosion is found during the inspection 
required by paragraph (a) or (b) of this AD, before further flight, 
accomplish either of the actions specified in paragraph (d)(1) or 
(d)(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.

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

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 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

    (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.

    Issued in Renton, Washington, on August 26, 2002.
Vi L. Lipski,
Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 02-22178 Filed 8-29-02; 8:45 am]
BILLING CODE 4910-13-P