[Federal Register Volume 65, Number 213 (Thursday, November 2, 2000)]
[Proposed Rules]
[Pages 65805-65808]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 00-28093]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 2000-CE-27-AD]
RIN 2120-AA64


Airworthiness Directives; Raytheon Aircraft Company Models 99, 
99A, 99A (FACH), A99A, B99, and C99 Airplanes

AGENCY: Federal Aviation Administration, DOT.

ACTION: Notice of proposed rulemaking (NPRM).

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SUMMARY: This document proposes to adopt a new airworthiness directive 
(AD) that would apply to certain Raytheon Aircraft Company (Raytheon) 
Models 99, 99A, 99A (FACH), A99A, B99, and C99 airplanes. The proposed 
AD would require you to inspect all main landing gear (MLG) hydraulic 
actuators to determine the end cap part number that is installed, and 
replace any actuator that has a part number 4A125C32 end cap. The 
proposed AD is the result of the potential for fatigue cracks to 
develop on the MLG hydraulic actuator end caps. The actions specified 
by this proposed AD are intended to eliminate existing and prevent 
future fatigue cracks in the MLG hydraulic actuator end caps. Such 
cracks could cause hydraulic fluid to leak and result in collapse of 
one or more gears with consequent aircraft damage and passenger injury.

DATES: The Federal Aviation Administration (FAA) must receive any 
comments on this rule on or before December 29, 2000.

ADDRESSES: Submit comments in triplicate to FAA, Central Region, Office 
of the Regional Counsel, Attention: Rules Docket No. 2000-CE-27-AD, 901 
Locust, Room 506, Kansas City, Missouri 64106. Comments may be 
inspected at this location between 8 a.m. and 4 p.m., Monday through 
Friday, holidays excepted.
    Service information that applies to the proposed AD may be obtained 
from the Raytheon Aircraft Company, PO Box 85, Wichita, Kansas 67201-
0085; telephone: (800) 625-7043 or (316) 676-4556. This information 
also may be examined at the Rules Docket at the address above.

FOR FURTHER INFORMATION CONTACT: Paul C. DeVore, Aerospace Engineer, 
Wichita Aircraft Certification Office, FAA, 1801 Airport Road, Mid-
Continent Airport, Wichita, Kansas 67209; telephone: (316) 946-4142; 
facsimile: (316) 946-4407.

SUPPLEMENTARY INFORMATION:

Comments Invited

    How do I comment on the proposed AD? The FAA invites comments on 
this proposed rule. You may submit whatever written data, views, or 
arguments you choose. You need to include the rule's docket number and 
submit your comments in triplicate to the address specified under the 
caption ADDRESSES. The FAA will consider all comments received on or 
before the closing date. We may amend the proposed rule in light of 
comments received. Factual information that supports your ideas and 
suggestions is extremely helpful in evaluating the effectiveness of the 
proposed AD action and determining whether we need to take additional 
rulemaking action.
    Are there any specific portions of the proposed AD I should pay 
attention to? The FAA specifically invites comments on the overall 
regulatory, economic, environmental, and energy aspects of the proposed 
rule that might suggest a need to modify the rule. You may examine all 
comments we receive before and after the closing date of the rule in 
the Rules Docket. We will file a report in the Rules Docket that 
summarizes each FAA contact with the public that concerns the 
substantive parts of the proposed AD.
    We are re-examining the writing style we currently use in 
regulatory documents, in response to the Presidential memorandum of 
June 1, 1998. That memorandum requires federal agencies to communicate 
more clearly with the public. We are interested in your comments on 
whether the style of this document is clearer, and any other 
suggestions you might have to improve the clarity of FAA communications 
that affect you. You can get more information about the Presidential 
memorandum and the plain language initiative at http://www.plainlanguage.gov.
    How can I be sure FAA receives my comment? If you want us to 
acknowledge the receipt of your comments, you must include a self-
addressed, stamped postcard. On the postcard, write ``Comments to 
Docket No. 2000-CE-27-AD.'' We will date stamp and mail the postcard 
back to you.

Discussion

    What events have caused this AD? The FAA has received a report of 
an incident on a Raytheon Model C99 airplane where a cracked main 
landing gear (MLG) hydraulic actuator end cap resulted in nose landing 
gear (NLG) collapse during landing. The cracked

[[Page 65806]]

end cap caused the hydraulic fluid to leak, which then prevented the 
landing gear from locking down. We have received several other reports 
of cracks in the MLG hydraulic actuator end caps on certain Raytheon 99 
series airplanes of a similar type design.
    The suspect MLG hydraulic actuator end caps are part number (P/N) 
4A125C32 end caps. These end caps were originally installed on P/N 99-
388001 series actuators. We have reports that these parts may also have 
been installed on the overhauled P/N 99-388008 series, although they 
are not approved for this configuration.
    The P/N 99-388001 and 99-388008 series actuators are installed on 
Raytheon Models 99, 99A, 99A (FACH), A99A, B99, and C99 airplanes.
    What are the consequences if the condition is not corrected? 
Cracked MLG hydraulic actuator end caps, if not eliminated and 
prevented from occurring in the future, could cause hydraulic fluid to 
leak and result in collapse of one or more gears with consequent 
aircraft damage and passenger injury.

Relevant Service Information

    Is there service information that applies to this subject? Raytheon 
has issued Mandatory Service Bulletin SB 2290, Rev. 1, Revised: August, 
1999.
    What are the provisions of this service bulletin? The service 
bulletin includes procedures for:
    <bullet> Inspecting all MLG hydraulic actuators to determine the 
end cap P/N that is installed; and
    <bullet> Replacing any MLG hydraulic actuator that has a P/N 
4A125C32 end cap.

The FAA's Determination and an Explanation of the Provisions of the 
Proposed AD

    What has FAA decided? After examining the circumstances and 
reviewing all available information related to the incidents described 
above, including the above-referenced service information, we have 
determined that:
    <bullet> The unsafe condition referenced in this document exists or 
could develop on other Raytheon Models 99, 99A, 99A (FACH), A99A, B99, 
and C99 airplanes of the same type design;
    <bullet> The actions specified in the previously-referenced service 
information should be accomplished on the affected airplanes; and
    <bullet> AD action should be taken in order to correct this unsafe 
condition.
    What would the proposed AD require? This proposed AD would require 
you to inspect all MLG hydraulic actuators to determine the end cap 
part number that is installed with replacement of any actuator that has 
a part number 4A125C32 end cap.

Cost Impact

    How many airplanes would the proposed AD impact? We estimate that 
the proposed AD would affect 139 airplanes in the U.S. registry.
    What would be the cost impact of the proposed AD on owners/
operators of the affected airplanes? We estimate the following costs to 
accomplish the proposed inspection:

----------------------------------------------------------------------------------------------------------------
                                                                                                  Total cost on
                  Labor cost                              Parts cost             Total cost per   U.S. airplane
                                                                                    airplane        operators
----------------------------------------------------------------------------------------------------------------
 2 workhours  x  $60 per hour = $120.........  No parts necessary to                  $120 per          $16,680
                                                accomplish the inspection.            airplane
----------------------------------------------------------------------------------------------------------------

    We estimate the following costs to accomplish any necessary 
replacements that would be required based on the results of the 
proposed inspection. We have no way of determining the number of 
airplanes that may need such replacement:

------------------------------------------------------------------------
                                                       Total cost per
         Labor cost                Parts cost             airplane
------------------------------------------------------------------------
 4 workhours  x  $60 per      $1,400 for each       $3,040 per airplane.
 hour = $240.                  actuator; each
                               airplane requires 2
                               for a total cost of
                               $2,800 per airplane.
------------------------------------------------------------------------

Regulatory Impact

    Would this proposed AD impact various entities? 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 
proposed rule would not have federalism implications under Executive 
Order 13132.
    Would this proposed AD involve a significant rule or regulatory 
action? 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) 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 has been placed 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, under the authority delegated to me by the 
Administrator, the Federal Aviation Administration proposes to amend 14 
CFR part 39 of the Federal Aviation Regulations 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. FAA amends Sec. 39.13 by adding a new airworthiness directive 
(AD) to read as follows:

Raytheon Aircraft Company: Docket No. 2000-CE-27-AD

    (a) What airplanes are affected by this AD? This AD affects the 
following airplane models and serial numbers that are certificated 
in any category:

[[Page 65807]]



------------------------------------------------------------------------
               Models                           Serial numbers
------------------------------------------------------------------------
 99, 99A, 99A (FACH), A99A, and B99   U-1 through U-49 and U51 through U-
C99................................   164.
                                     U-50 and U-165 through U-239.
------------------------------------------------------------------------

    (b) Who must comply with this AD? Anyone who wishes to operate 
any of the above airplanes must comply with this AD.
    (c) What problem does this AD address? The actions specified by 
this AD are intended to eliminate existing and prevent future 
fatigue cracks in the main landing gear (MLG) hydraulic actuator end 
caps. Such cracks could cause hydraulic fluid to leak and result in 
collapse of one or more gears with consequent aircraft damage and 
passenger injury.
    (d) What actions must I accomplish to address this problem? To 
address this problem, you must accomplish the following:

------------------------------------------------------------------------
           Action                Compliance time         Procedures
------------------------------------------------------------------------
(1) Inspect all MLG           Within the next 200   In accordance with
 hydraulic actuators to        hours time-in-        the Accomplishment
 determine what part number    service (TIS) after   Instructions
 (P/N) end caps are            the effective date    section of Raytheon
 installed.                    of this AD, unless    Mandatory Service
                               already               Bulletin SB 2290,
                               accomplished.         Rev. 1, Revised:
                                                     August, 1999.
 (2) If a P/N 4A211S1 (or     AD is complied with.  AD is complied with.
 FAA-approved equivalent
 part number) end cap is
 installed on both
 actuators, then no
 additional action is
 required by this AD.
(3) If a P/N 4A125C32 (or     Accomplish the        In accordance with
 FAA-approved equivalent       inspection prior to   Part I, steps (2)
 part number) end cap is       further flight        through (10) and
 installed on a P/N 99-        after the             Part II, of the
 388001 series actuator,       inspection required   Accomplishment
 accomplish the following.     by paragraph (d)(1)   Instructions
(i) Inspect, using             of this AD and        section of Raytheon
 fluorescent penetrant         thereafter at         Mandatory Service
 methods, each end cap for     intervals not to      Bulletin SB 2290,
 evidence of cracking;.        exceed 200 hours      Rev. 1, Revised:
(ii) Replace each actuator     TIS until the end     August, 1999.
 with an actuator that has a   caps are replaced.
 P/N 4A211SI (or FAA-          Accomplish the
 approved equivalent part      replacement prior
 number) end cap; and.         to further flight
(iii) This replacement may     after the
 be accomplished prior to      inspection where
 600 hours TIS, but must be    any evidence of
 replaced if evidence of       cracking is found
 cracking is found..           or within 600 hours
                               TIS after the
                               effective date of
                               this AD if no
                               evidence of
                               cracking is found.
(4) If a P/N 4A125C32 (or     Prior to further      In accordance with
 FAA-approved equivalent       flight after the      Part I, steps (2)
 part number) end cap is       inspection required   through (10) and
 installed on a P/N 99-        by this AD.           Part II, of the
 388008 series actuator,                             Accomplishment
 replace the actuator with                           Instructions
 an actuator that has a P/N                          section of Raytheon
 4A211SI (or FAA-approved                            Mandatory Service
 equivalent part number) end                         Bulletin SB 2290,
 cap.                                                Rev. 1, Revised:
                                                     August, 1999.
 (5) Do not install, on any   As of the effective   Not Applicable.
 affected airplane, a P/N 99-  date of this AD.
 388008 series actuator that
 incorporates an end cap
 that is not P/N 4A211S1 (or
 FAA-approved equivalent
 part number).
 (6) Do not install, on any   As of 600 hours TIS   Not Applicable.
 affected airplane, a P/N 99-  after the effective
 388001 series actuator that   date of this AD
 incorporates an end cap       provided the 200-
 that is not P/N 4A211SI (or   hour repetitive
 FAA-approved equivalent       inspections
 part number).                 required by this AD
                               are accomplished
                               and no evidence of
                               cracking is found.
                               If evidence of
                               cracking is found,
                               the actuator must
                               be immediately
                               replaced with one
                               that incorporates P/
                               N 4A211S1 (or FAA-
                               approved equivalent
                               part number).
------------------------------------------------------------------------

    (e) Can I comply with this AD in any other way? You may use an 
alternative method of compliance or adjust the compliance time if:
    (1) Your alternative method of compliance provides an equivalent 
level of safety; and
    (2) The Manager, Wichita Aircraft Certification Office (ACO), 
approves your alternative. Submit your request through an FAA 
Principal Maintenance Inspector, who may add comments and then send 
it to the Manager, Wichita ACO.

    Note: This AD applies to each airplane identified in paragraph 
(a) of this AD, 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 you have not eliminated the unsafe condition, specific 
actions you propose to address it.

    (f) Where can I get information about any already-approved 
alternative methods of compliance? Contact Paul C. DeVore, Aerospace 
Engineer, Wichita Aircraft Certification Office, FAA, 1801 Airport 
Road, Mid-Continent Airport, Wichita, Kansas 67209; telephone: (316) 
946-4142; facsimile: (316) 946-4407.
    (g) What if I need to fly the airplane to another location to 
comply with this AD? The FAA can issue a special flight permit under 
sections 21.197 and 21.199 of the Federal Aviation Regulations (14 
CFR 21.197 and 21.199) to operate your airplane to a location where 
you can accomplish the requirements of this AD.
    (h) How do I get copies of the documents referenced in this AD? 
You may obtain copies of the documents referenced in this AD from 
the Raytheon Aircraft Company, PO Box 85, Wichita, Kansas 67201-
0085; telephone: (800) 625-7043 or (316) 676-4556. You may examine 
these documents at FAA, Central Region, Office of the Regional 
Counsel, 901 Locust, Room 506, Kansas City, Missouri 64106.


[[Page 65808]]


    Issued in Kansas City, Missouri, on October 27, 2000.
James E. Jackson,
Acting Manager, Small Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 00-28093 Filed 11-1-00; 8:45 am]
BILLING CODE 4910-13-P