Document ID: FAA-2008-1312-0001
Agency: faa
Document Type: Rule
Title: Airworthiness Directives; Hawker Beechcraft Corporation Models 1900, 1900C, and 1900D Airplanes
Posted Date: 2008-12-15T05:00Z

[Federal Register: December 15, 2008 (Volume 73, Number 241)]
[Proposed Rules]               
[Page 75977-75979]
From the Federal Register Online via GPO Access [wais.access.gpo.gov]
[DOCID:fr15de08-18]                         

========================================================================
Proposed Rules
                                                Federal Register
________________________________________________________________________

This section of the FEDERAL REGISTER contains notices to the public of 
the proposed issuance of rules and regulations. The purpose of these 
notices is to give interested persons an opportunity to participate in 
the rule making prior to the adoption of the final rules.

========================================================================

[[Page 75977]]

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2008-1312; Directorate Identifier 2008-CE-065-AD]
RIN 2120-AA64

 
Airworthiness Directives; Hawker Beechcraft Corporation Models 
1900, 1900C, and 1900D Airplanes

AGENCY: Federal Aviation Administration (FAA), Department of 
Transportation (DOT).

ACTION: Notice of proposed rulemaking (NPRM).

-----------------------------------------------------------------------

SUMMARY: We propose to adopt a new airworthiness directive (AD) for 
certain Hawker Beechcraft Corporation (HBC) Models 1900, 1900C, and 
1900D airplanes. This proposed AD would require a one-time visual 
inspection and repetitive ultrasonic inspections of the left and right 
main landing gear (MLG) actuators for leaking and/or cracks with 
replacement of the actuator if leaking and/or cracks are found. This 
proposed AD results from reports of leaking and cracked actuators. We 
are proposing this AD to detect and correct leaking and cracks in the 
MLG actuators, which could result in loss of hydraulic fluid. This 
condition could lead to an inability to extend or lock down the landing 
gear, which could result in a gear up landing or a gear collapse on 
landing.

DATES: We must receive comments on this proposed AD by February 13, 
2009.

ADDRESSES: Use one of the following addresses to comment on this 
proposed AD:
     Federal eRulemaking Portal: Go to http://
www.regulations.gov. Follow the instructions for submitting comments.
     Fax: (202) 493-2251.
     Mail: U.S. Department of Transportation, Docket 
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New 
Jersey Avenue, SE., Washington, DC 20590.
     Hand Delivery: U.S. Department of Transportation, Docket 
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New 
Jersey Avenue, SE., Washington, DC 20590, between 9 a.m. and 5 p.m., 
Monday through Friday, except Federal holidays.
    For service information identified in this proposed AD, contact 
Hawker Beechcraft Corporation, P.O. Box 85, Wichita, Kansas 67201-0085; 
telephone: (800) 429-5372 or (316) 676-3140; Internet: http://
pubs.hawkerbeechcraft.com.

FOR FURTHER INFORMATION CONTACT: Don Ristow, Aerospace Engineer, 1801 
Airport Road, Room 100, Wichita, Kansas 67209; telephone: (316) 946-
4120; fax: (316) 946-4107.

SUPPLEMENTARY INFORMATION:

Comments Invited

    We invite you to send any written relevant data, views, or 
arguments regarding this proposed AD. Send your comments to an address 
listed under the ADDRESSES section. Include the docket number, ``FAA-
2008-1312; Directorate Identifier 2008-CE-065-AD'' at the beginning of 
your comments. We specifically invite comments on the overall 
regulatory, economic, environmental, and energy aspects of the proposed 
AD. We will consider all comments received by the closing date and may 
amend the proposed AD in light of those comments.
    We will post all comments we receive, without change, to http://
www.regulations.gov, including any personal information you provide. We 
will also post a report summarizing each substantive verbal contact we 
receive concerning this proposed AD.

Discussion

    We have received information that two HBC 1900 series airplanes' 
MLG actuators have been found with fatigue cracks in the end cap, which 
resulted in hydraulic fluid leakage. This condition, along with an 
inoperative liquid level sensor, was found on another airplane that 
landed with all landing gear up. There have been a total of 6 reports 
of leaking actuators and 13 reports of cracked actuators.
    This condition, if not corrected, could result in leaking and 
cracks in the MLG actuators, which may cause loss of hydraulic fluid. 
Loss of hydraulic fluid could lead to an inability to extend or lock 
down the landing gear, which could result in a gear up landing or a 
gear collapse on landing.

Relevant Service Information

    We have reviewed Hawker Beechcraft Mandatory Service Bulletin SB 
32-3870, dated April 2008.
    The service information describes procedures for doing the 
following:
     One-time visual inspection and repetitive ultrasonic 
inspections of the MLG actuators;
     Replacement of the actuator if leaking and/or cracks are 
found; and
     Reporting the size and location of cracks to HBC if any 
are found during the inspections.

FAA's Determination and Requirements of the Proposed AD

    We are proposing this AD because we evaluated all information and 
determined the unsafe condition described previously is likely to exist 
or develop on other products of the same type design. This proposed AD 
would require a one-time visual inspection of the left and right main 
landing gear (MLG) actuators and repetitive ultrasonic inspections of 
the left and right MLG actuators for leaking and/or cracks with 
replacement of the actuator if leaking and/or cracks are found.

Costs of Compliance

    We estimate that this proposed AD would affect 300 airplanes in the 
U.S. registry.
    The ultrasonic inspection includes the time allowed for removing 
and reinstalling the actuator. We estimate the following costs to do 
the proposed inspections:

----------------------------------------------------------------------------------------------------------------
                                                                                  Total cost per   Total cost on
                  Labor cost                               Parts cost                airplane     U.S. operators
----------------------------------------------------------------------------------------------------------------
Visual Inspection: .5 work-hour x $80 per hour  Not applicable..................             $40         $12,000
 = $40.

[[Page 75978]]

Ultrasonic Inspection: 6 work hours x $80 per   Not applicable..................             480         144,000
 hour = $480 (If the mechanic does not remove
 the actuator for the ultrasonic inspection,
 the labor cost will be less.).
----------------------------------------------------------------------------------------------------------------

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

------------------------------------------------------------------------
                                                          Total cost per
            Labor cost                  Parts cost           airplane
------------------------------------------------------------------------
6 work hours x $80 per hour =      $4,600 per actuator.          $5,080
 $480 (If the mechanic removes
 the actuator for the ultrasonic
 inspection, then the labor cost
 will be less.).
------------------------------------------------------------------------

Authority for This Rulemaking

    Title 49 of the United States Code specifies the FAA's authority to 
issue rules on aviation safety. Subtitle I, Section 106, describes the 
authority of the FAA Administrator. Subtitle VII, Aviation Programs, 
describes in more detail the scope of the Agency's authority.
    We are issuing this rulemaking under the authority described in 
Subtitle VII, Part A, Subpart III, Section 44701, ``General 
requirements.'' Under that section, Congress charges the FAA with 
promoting safe flight of civil aircraft in air commerce by prescribing 
regulations for practices, methods, and procedures the Administrator 
finds necessary for safety in air commerce. This regulation is within 
the scope of that authority because it addresses an unsafe condition 
that is likely to exist or develop on products identified in this 
rulemaking action.

Regulatory Findings

    We have determined that this proposed AD would not have federalism 
implications under Executive Order 13132. This proposed AD 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.
    For the reasons discussed above, I certify that the 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. 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.
    We prepared a regulatory evaluation of the estimated costs to 
comply with this proposed AD and placed it in the AD docket.

Examining the AD Docket

    You may examine the AD docket that contains the proposed AD, the 
regulatory evaluation, any comments received, and other information on 
the Internet at http://www.regulations.gov; or in person at the Docket 
Management Facility between 9 a.m. and 5 p.m., Monday through Friday, 
except Federal holidays. The Docket Office (telephone (800) 647-5527) 
is located at the street address stated in the ADDRESSES section. 
Comments will be available in the AD docket shortly after receipt.

List of Subjects in 14 CFR Part 39

    Air transportation, Aircraft, Aviation safety, Incorporation by 
reference, Safety.

The Proposed Amendment

    Accordingly, under the authority delegated to me by the 
Administrator, the FAA proposes to amend 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. The FAA amends Sec.  39.13 by adding the following new AD:

Hawker Beechcraft Corporation: Docket No. FAA-2008-1312; Directorate 
Identifier 2008-CE-065-AD.

Comments Due Date

    (a) We must receive comments on this airworthiness directive 
(AD) action by February 13, 2009.

Affected ADs

    (b) None.

Applicability

    (c) This AD applies to the following airplane models and serial 
numbers that are certificated in any category and equipped with a 
part number (P/N) 114-380041-11, 114-380041-13, or 114-380041-15 
main landing gear (MLG) actuator:

------------------------------------------------------------------------
                 Models                            Serial Nos.
------------------------------------------------------------------------
(1) 1900...............................  UA-3.
(2) 1900C..............................  UB-1 through UB-74, UC-1
                                          through UC-174, and UD-1
                                          through UD-6.
(3) 1900D..............................  UE-1 through UE-439.
------------------------------------------------------------------------

Unsafe Condition

    (d) This AD results from reports of leaking and cracked 
actuators. We are issuing this AD to detect and correct leaking and 
cracks in the MLG actuators, which could result in loss of hydraulic 
fluid. This condition could lead to an inability to extend or lock 
down the landing gear, which could result in a gear up landing or a 
gear collapse on landing.

Compliance

    (e) To address this problem, you must do the following, unless 
already done:

----------------------------------------------------------------------------------------------------------------
               Actions                             Compliance                            Procedures
----------------------------------------------------------------------------------------------------------------
(1) Do a one-time visual inspection   Within the next 50 hours time-in-     Follow Hawker Beechcraft Mandatory
 of the MLG actuator for cracks.       service after the effective date of   Service Bulletin SB 32-3870, dated
                                       this AD or within the next 30 days    April 2008.
                                       after the effective date of this
                                       AD, whichever occurs later.

[[Page 75979]]

(2) Do an ultrasonic inspection of    Initially within the next 600 cycles  Follow Hawker Beechcraft Mandatory
 the MLG actuator.                     after the effective date of this AD   Service Bulletin SB 32-3870, dated
                                       or within the next 3 months after     April 2008.
                                       the effective date of this AD,
                                       whichever occurs first.
                                       Repetitively thereafter inspect at
                                       intervals not to exceed every 1,200
                                       cycles since the last ultrasonic
                                       inspection.
(3) If cracks are found during any    Before further flight after the       Follow Hawker Beechcraft Mandatory
 inspection required in paragraph      inspection where the cracks are       Service Bulletin SB 32-3870, dated
 (e)(1) or (e)(2) of this AD,          found.                                April 2008.
 replace the MLG actuator with one
 of the following:
    (i) MLG actuator P/N 114-380041-
     15 (or FAA-approved equivalent
     P/N) that is new or has been
     inspected following paragraphs
     (e)(1) and (e)(2) of this AD
     and has been found to not have
     cracks; or
    (ii) MLG actuator P/N 114-380041-
     17 (or FAA-approved equivalent
     P/N). Installation of MLG
     actuator P/N 114-380041-17 (or
     FAA-approved equivalent P/N)
     terminates the inspection
     requirements of paragraphs
     (e)(1) and (e)(2) of this AD.
(4) Do not install any MLG actuator   As of 3 months after the effective    Not applicable.
 P/N 114-380041-11 or 114-380041-13.   date of this AD.
----------------------------------------------------------------------------------------------------------------

    Note: The compliance times of cycles in this AD may be 
calculated as hours time-in-service (TIS) by multiplying the number 
of hours TIS on the MLG actuator by 4 to come up with the number of 
cycles. For the purposes of this AD:
    1. 600 cycles equals 150 hours TIS; and
    2. 1,200 cycles equals 300 hours TIS.

    (f) If cracks are found during any inspection required in 
paragraphs (e)(1) or (e)(2) of this AD, report the size and location 
of the cracks to the type-certificate (TC) holder and send a copy of 
the report to the FAA.
    (i) For the TC holder: Send report to Hawker Beechcraft 
Corporation, P.O. Box 85, Wichita, Kansas 67201-0085.
    (ii) For the FAA: Send report to Don Ristow, Aerospace Engineer, 
Wichita ACO, 1801 Airport Road, Room 100, Wichita, Kansas 67209; e-
mail: donald.ristow@faa.gov.
    (iii) The Office of Management and Budget (OMB) approved the 
information collection requirements contained in this regulation 
under the provisions of the Paperwork Reduction Act of 1980 (44 
U.S.C. 3501 et seq.) and assigned OMB Control Number 2120-0056.

Alternative Methods of Compliance (AMOCs)

    (g) The Manager, Wichita Aircraft Certification Office (ACO), 
FAA, has the authority to approve AMOCs for this AD, if requested 
using the procedures found in 14 CFR 39.19. Send information to 
ATTN: Don Ristow, Aerospace Engineer, Wichita ACO, 1801 Airport 
Road, Room 100, Wichita, Kansas 67209; telephone: (316) 946-4120; 
fax: (316) 946-4107. Before using any approved AMOC on any airplane 
to which the AMOC applies, notify your appropriate principal 
inspector (PI) in the FAA Flight Standards District Office (FSDO), 
or lacking a PI, your local FSDO.

Related Information

    (h) To get copies of the service information referenced in this 
AD, contact Hawker Beechcraft Corporation, P.O. Box 85, Wichita, 
Kansas 67201-0085; telephone: (800) 429-5372 or (316) 676-3140; 
Internet: http://pubs.hawkerbeechcraft.com. To view the AD docket, 
go to U.S. Department of Transportation, Docket Operations, M-30, 
West Building Ground Floor, Room W12-140, 1200 New Jersey Avenue, 
SE., Washington, DC 20590, or on the Internet at http://
www.regulations.gov.

    Issued in Kansas City, Missouri, on December 8, 2008.
Kim Smith,
Manager, Small Airplane Directorate, Aircraft Certification Service.
[FR Doc. E8-29591 Filed 12-12-08; 8:45 am]

BILLING CODE 4910-13-P