[Federal Register Volume 66, Number 109 (Wednesday, June 6, 2001)]
[Rules and Regulations]
[Pages 30302-30305]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 01-13579]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 2000-CE-27-AD; Amendment 39-12245; AD 2001-11-04]
RIN 2120-AA64


Airworthiness Directives; Raytheon Aircraft Company Models 99, 
99A, 99A (FACH), A99, A99A, B99, and C99 Airplanes

AGENCY: Federal Aviation Administration, DOT.

ACTION: Final rule.

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SUMMARY: This amendment adopts a new airworthiness directive (AD) that 
applies to certain Raytheon Aircraft Company (Raytheon) Models 99, 99A, 
99A (FACH), A99, A99A, B99, and C99 airplanes. This AD requires 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. This AD is the result of the 
potential for fatigue cracks to develop on the MLG hydraulic actuator 
end caps. The actions specified by this 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: This AD becomes effective on July 23, 2001.
    The Director of the Federal Register approved the incorporation by 
reference of certain publications listed in the regulations as of July 
23, 2001.

ADDRESSES: You may get the service information 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 this 
information at the Federal Aviation Administration (FAA), Central 
Region, Office of the Regional Counsel, Attention: Rules Docket No. 
2000-CE-27-AD, 901 Locust, Room 506, Kansas City, Missouri 64106; or at 
the Office of the Federal Register, 800 North Capitol Street, NW., 
suite 700, Washington, DC.

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:

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 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.

[[Page 30303]]

    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), A99, 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.

Has FAA Taken Any Action to This Point?

    We issued a proposal to amend part 39 of the Federal Aviation 
Regulations (14 CFR part 39) to include an AD that would apply to 
certain Raytheon Models 99, 99A, 99A (FACH), A99A, B99, and C99 
airplanes. This proposal was published in the Federal Register as a 
notice of proposed rulemaking (NPRM) on November 2, 2000 (65 FR 65805). 
The NPRM proposed to 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.

Was the Public Invited To Comment?

    Interested persons were afforded an opportunity to participate in 
the making of this amendment. No comments were received on the proposed 
rule or the FAA's determination of the cost to the public.

Is There Any New Information Pertaining to This Subject?

    The FAA's intent is to not affect those airplanes with mechanical 
landing gear installed either at manufacture or through field approval. 
The way the NPRM is written would make the AD applicable to all 
affected airplane models. We are changing the AD to only apply to those 
airplanes that are equipped with hydraulic landing gear.
    We also realized that we inadvertently left off the Raytheon Beech 
Model A99 airplanes in the Applicability section of the NPRM. These 
airplanes were originally manufactured with mechanical landing gear, 
but could have hydraulic landing gear installed. Only 1 of these 
airplanes is currently on the U.S. Register and FAA has verified that 
this airplane does not have hydraulic landing gear. Therefore, adding 
the Beech Model A99 to the AD will not increase the burden upon the 
public over that already proposed in the NPRM.

FAA's Determination

What Is FAA's Final Determination on This Issue?

    After careful review of all available information related to the 
subject presented above, we have determined that air safety and the 
public interest require the adoption of the rule as proposed except for 
the changes described above and minor editorial corrections. We 
determined that these changes and minor corrections:

--Will not change the meaning of the AD; and
-Will not add any additional burden upon the public than was already 
proposed.

Cost Impact

How Many Airplanes Does This AD Impact?

    We estimate that this AD could affect 139 airplanes in the U.S. 
registry.

What Is the Cost Impact of This AD on Owners/Operators of the Affected 
Airplanes?

    We estimate the following costs to accomplish the inspection:

----------------------------------------------------------------------------------------------------------------
                                                              Total cost per
            Labor cost                    Parts cost             airplane          Total cost on U.S. operators
----------------------------------------------------------------------------------------------------------------
2 workhours  x  $60 per hour =      No parts necessary to  $120 per airplane...  $120  x  139 = $16,680.
 $120.                               accomplish the
                                     inspection.
----------------------------------------------------------------------------------------------------------------

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

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

Regulatory Impact

Does This AD Impact Various Entities?

    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.

Does This 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) 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 final 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, Incorporation by 
reference, Safety.

Adoption of the Amendment

    Accordingly, under 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:


[[Page 30304]]


    Authority: 49 U.S.C. 106(g), 40113, 44701.


Sec. 39.13  [Amended]

    2. FAA amends Sec. 39.13 by adding a new AD to read as follows:

2001-11-04  Raytheon Aircraft Company: Amendment 39-12245; 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 and are equipped with hydraulic landing gear:

----------------------------------------------------------------------------------------------------------------
                   Model                                                 Serial Nos.
----------------------------------------------------------------------------------------------------------------
99, 99A, 99A (FACH), A99, A99A, and B99....  U-1 through U-49 and U51 through U-164.
C99........................................  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:

------------------------------------------------------------------------
           Actions                 Compliance            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            July 23, 2001 (the    section of Raytheon
 installed.                    effective date of     Mandatory Service
                               this AD), unless      Bulletin SB 2290,
                               already               Rev. 1, Revised:
                               accomplished.         August, 1999.
------------------------------------------------------------------------
(2) If a P/N 4A211S1 (or FAA- AD is complied with.  AD is complied with.
 approved equivalent part
 number) end cap is
 installed on both
 actuators, then no
 additional action is
 required by this AD.
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(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 4A211S1 (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 July 23,
                               2001 (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
 4A211S1 (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 July 23, 2001,  Not Applicable.
 affected airplane, a P/N 99-  (the effective date
 388008 series actuator that   of this AD).
 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 July 23, 2001
 388001 series actuator that   (the effective date
 incorporates an end cap       of this AD)
 that is not P/N 4A211S1 (or   provided the 200-
 FAA-approved equivalent       hour repetitive
 part number).                 inspections
                               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

[[Page 30305]]

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) Are any service bulletins incorporated into this AD by 
reference? Actions required by this AD must be done in accordance 
with Raytheon Mandatory Service Bulletin SB 2290, Rev. 1, Revised: 
August, 1999. The Director of the Federal Register approved this 
incorporation by reference under 5 U.S.C. 552(a) and 1 CFR part 51. 
You can get copies from the Raytheon Aircraft Company, PO Box 85, 
Wichita, Kansas 67201-0085. You can look at copies at the FAA, 
Central Region, Office of the Regional Counsel, 901 Locust, Room 
506, Kansas City, Missouri, or at the Office of the Federal 
Register, 800 North Capitol Street, NW., suite 700, Washington, DC.
    (i) When does this amendment become effective? This amendment 
becomes effective on July 23, 2001.

    Issued in Kansas City, Missouri, on May 22, 2001.
Michael Gallagher,
Manager, Small Airplane Directorate, Aircraft Certification Service.
[FR Doc. 01-13579 Filed 6-5-01; 8:45 am]
BILLING CODE 4910-13-P