[Federal Register Volume 71, Number 23 (Friday, February 3, 2006)]
[Proposed Rules]
[Pages 5796-5799]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: E6-1470]


 ========================================================================
 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.
 
 ========================================================================
 

  Federal Register / Vol. 71, No. 23 / Friday, February 3, 2006 / 
Proposed Rules  

[[Page 5796]]



DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2005-23334; Directorate Identifier 2005-CE-53-AD]
RIN 2120-AA64


Airworthiness Directives; General Machine--Diecron, Inc. Actuator 
Nut Assembly for the Right Main Landing Gear

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

ACTION: Notice of proposed rulemaking (NPRM).

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

SUMMARY: The FAA proposes to adopt a new airworthiness directive (AD) 
for General Machine--Diecron, Inc. (GMD) actuator nut assembly, part 
number (P/N) GMD115-810029-17 and P/N GMD115-810029-23, that are 
installed on certain airplanes. This proposed AD would require you to 
determine by maintenance records check and/or inspection whether any 
actuator nut assembly, P/N GMD115-810029-17 or P/N GMD115-810029-23, is 
installed on the right main landing gear (MLG) actuator, and, if 
installed, would require you to replace it with a new actuator nut 
assembly, P/N GMD115-810029-23B or FAA-approved equivalent P/N. This 
proposed AD results from several reports of failures of the actuator 
nut assembly, P/N GMD115-810029-17 and P/N GMD115-810029-23. We are 
issuing this proposed AD to prevent failure of the actuator nut 
assembly for the right MLG actuator, which could result in failure of 
the MLG. This failure could prevent the extension or retraction of the 
MLG.

DATES: We must receive comments on this proposed AD by April 3, 2006.

ADDRESSES: Use one of the following addresses to comment on this 
proposed AD:
     DOT Docket Web site: Go to http://dms.dot.gov and follow 
the instructions for sending your comments electronically.
     Government-wide rulemaking Web site: Go to http://www.regulations.gov and follow the instructions for sending your 
comments electronically.
     Mail: Docket Management Facility; U.S. Department of 
Transportation, 400 Seventh Street, SW., Nassif Building, Room PL-401, 
Washington, DC 20590-0001.
     Fax: 1-202-493-2251.
     Hand Delivery: Room PL-401 on the plaza level of the 
Nassif Building, 400 Seventh Street, SW., Washington, DC, between 9 
a.m. and 5 p.m., Monday through Friday, except Federal holidays.
    Contact General Machine--Diecron, Inc., 3131 U.S. Highway 41, 
Griffin, Georgia 30224, telephone: (770) 228-6200; facsimile: (770) 
228-6299, for the service information identified in this proposed AD.
    You may examine the comments on this proposed AD in the AD docket 
on the Internet at http://dms.dot.gov.

FOR FURTHER INFORMATION CONTACT: Don Buckley, Aerospace Engineer, 
Airframe and Propulsion Branch, ACE-117A, FAA, Atlanta Aircraft 
Certification Office, One Crown Center, 1895 Phoenix Boulevard, Suite 
450, Atlanta, Georgia 30337-2748, telephone (770) 703-6086; fax (770) 
703-6097.

SUPPLEMENTARY INFORMATION: 

Comments Invited

How do I comment on this proposed AD?

    We invite you to send any written relevant data, views, or 
arguments regarding this proposal. Send your comments to an address 
listed under ADDRESSES. Include the docket number, ``FAA-2005-23334; 
Directorate Identifier 2005-CE-53-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://dms.dot.gov, including any personal information you provide. We will 
also post a report summarizing each substantive verbal contact with FAA 
personnel concerning this proposed rulemaking. Using the search 
function of the DOT docket Web site, anyone can find and read the 
comments received into any of our dockets, including the name of the 
individual who sent the comment (or signed the comment on behalf of an 
association, business, labor union, etc.). You may review the DOT's 
complete Privacy Act Statement in the Federal Register published on 
April 11, 2000 (65 FR 19477-78) or you may visit http://dms.dot.gov.

Examining the Dockets

Where can I go to view the docket information?

    You may examine the docket that contains the proposal, any comments 
received and any final disposition on the Internet at http://dms.dot.gov, or in person at the DOT Docket Offices between 9 a.m. and 
5 p.m., Monday through Friday, except Federal holidays. The Docket 
Office (telephone 1-800-647-5227) is located on the plaza level of the 
Department of Transportation NASSIF Building at the street address 
stated in ADDRESSES. Comments will be available in the AD docket 
shortly after the Docket Management Facility receives them.

Discussion

What events have caused this proposed AD?

    The FAA has received several reports of failure of the actuator nut 
assembly, part numbers (P/N) GMD115-810029-17 and P/N GMD115-810029-23, 
for the right main landing gear (MLG) actuator in airplanes not 
equipped with a hydraulic MLG or modified to a hydraulic MLG. One 
failure resulted in the MLG not extending and a ``gear-up'' landing.
    Investigation found the separation of the threaded nut insert in 
the P/N GMD115-810029-17 and P/N GMD115-810029-23 MLG actuator nut 
assembly. The insert has internal and external threads. The external 
threads of the insert screw into a threaded steel tube to complete the 
actuator nut assembly. The internal threads of the insert interface 
with the Actuator Screw in the Raytheon MLG Actuator. Rotation of the 
MLG Actuator Screw in the right MLG Actuator transmits load to the 
insert which tends to unscrew the insert from the GMD Actuator Nut 
Assembly during the extension cycle of the MLG. If the insert separates 
(unscrews) from the threaded steel tube, it can prevent the

[[Page 5797]]

actuator from extending or retracting the MLG to the locked position. 
The separation of the insert only occurs in the right MLG actuator.

What is the potential impact if FAA took no action?

    This condition, if not corrected, could prevent the extension or 
retraction of the MLG.

Relevant Service Information

Is there service information that applies to this subject?

    We have reviewed General Machine Diecron, Inc. Service Bulletin GM-
D 32-30-01/102505, dated November 21, 2005.

What are the provisions of this service information?

    The service information describes procedures for:
     Determining by maintenance records check and/or inspection 
whether any actuator nut assembly, P/N GMD115-810029-17 or P/N GMD115-
810029-23, is installed on the right MLG actuator; and
     If any actuator nut assembly, P/N GMD115-810029-17 or P/N 
GMD115-810029-23, is installed, replacing it with a new P/N GMD115-
810029-23B actuator nut assembly.

FAA's Determination and Requirements of the Proposed AD

Why have we determined AD action is necessary and what would this 
proposed AD require?

    We are proposing this AD to address an unsafe condition that we 
determined is likely to exist or develop on other products of this same 
type design. The proposed AD would require you to determine by 
maintenance records check and/or inspection whether any actuator nut 
assembly, P/N GMD115-810029-17 or P/N GMD115-810029-23, is installed on 
the right MLG actuator, and, if installed, would require you to replace 
it with a new actuator nut assembly, P/N GMD115-810029-23B or FAA-
approved equivalent P/N. The proposed AD would require you to use the 
service information described previously to perform these actions.

Differences Between the Proposed AD and Service Information

Are there differences between the requirements of this AD and what is 
contained in the service information?

    If any actuator nut assembly, P/N GMD115-810029-17 or P/N GMD115-
810029-23, is installed on the right MLG actuator, this AD would 
require you to replace it with a new actuator nut assembly, P/N GMD115-
810029-23B or FAA-equivalent P/N. The requirements of the proposed AD, 
if adopted as a final rule, would take precedence over the provisions 
in the service information.

Costs of Compliance

How many airplanes would this proposed AD impact?

    We estimate that this proposed AD affects 1,629 airplanes in the 
U.S. registry.

What would be the cost impact of this proposed AD on owners/operators 
of the affected airplanes?

    We estimate the following costs to do this proposed maintenance 
records check and/or inspection to determine whether any actuator nut 
assembly, P/N GMD115-810029-17 or P/N GMD115-810029-23, is installed on 
the right MLG actuator:

----------------------------------------------------------------------------------------------------------------
                                                                      Total cost Per      Total cost on U.S.
               Labor cost                         Parts cost             airplane              operators
----------------------------------------------------------------------------------------------------------------
1 work hour x $65 = $65.................  Not Applicable............            $65   1,629 x $65 = $105,885
----------------------------------------------------------------------------------------------------------------

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

------------------------------------------------------------------------
                                                             Total cost
                 Labor cost                    Parts cost   per airplane
------------------------------------------------------------------------
4 work hours x $65 = $260...................        $1,700        $1,960
------------------------------------------------------------------------

Authority for This Rulemaking

What authority does FAA have for issuing this rulemaking action?

    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

Would this proposed AD impact various entities?

    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.

[[Page 5798]]

    We prepared a regulatory evaluation of the estimated costs to 
comply with this proposed AD. See the ADDRESSES section for a location 
to examine the regulatory evaluation.

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 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 
airworthiness directive:

General Machine--Diecron, Inc.: Docket No. FAA-2005-23334; 
Directorate Identifier 2005-CE-53-AD.

When Is the Last Date I Can Submit Comments on This Proposed AD?

    (a) The Federal Aviation Administration (FAA) must receive 
comments on this airworthiness directive (AD) action by April 3, 
2006.

What Other ADs Are Affected by This Action?

    (b) None.

What Airplanes Are Affected by This AD?

    (c) This AD affects any actuator nut assembly, part number (P/N) 
GMD115-810029-17 or P/N GMD115-810029-23, for the right main landing 
gear (MLG) actuator installed on, but not limited to, the following 
aircraft that are certificated in any category and not equipped with 
a hydraulic MLG or modified to a hydraulic MLG.

------------------------------------------------------------------------
            Models                            Serial Nos.
------------------------------------------------------------------------
(1) F90......................  LA-2 through LA-225 (except aircraft that
                                incorporate Beech Kit No. 90-8011).
(2) 99, 99A, A99, and B99....  U-1 through U-49 and U51 through U164
                                (except aircraft that incorporate Beech
                                Kit No. 99-8010-1 or factory installed
                                hydraulic landing gear).
(3) 100 and A100.............  B-1 through B-94, B-100 through B-204,
                                and B-206 through B-247.
(4) B100.....................  BE-1 through BE-137.
(5) 200......................  BB-2, BB-6 through BB-733, BB-735 through
                                BB-792, BB-794 through BB-828, BB-830
                                through BB-853, BB-872, BB-873, BB-892,
                                BB-893, and BB-912 (except aircraft that
                                incorporate Beech Kit No. 101-8018).
(6) B200.....................  BB-734, BB-793, BB-829, BB-854 through BB-
                                870, BB-874 through BB-891, BB-894, BB-
                                896 through BB-911, and BB-913 through
                                BB-1157, BB-1159 through BB-1166, and BB-
                                1168 through BB-1192 (except aircraft
                                that incorporate Beech Kit No. 101-
                                8018).
(7) 200T and B200T...........  BT-1 through BT-30 (except aircraft that
                                incorporate Beech Kit No. 101-8018).
(8) 200C and B200C...........  BL-1 through BL-72 (except aircraft that
                                incorporate Beech Kit No. 101-8018).
(9) 200CT and B200CT.........  BN-1 through BN-4 (except aircraft that
                                incorporate Beech Kit No. 101-8018).
(10) A200CT (FWC-12D)........  FG-1 and FG-2 (except aircraft that
                                incorporate Beech Kit No. 101-8018).
------------------------------------------------------------------------

What Is the Unsafe Condition Presented in This AD?

    (d) This AD results from several reports of failures of the 
actuator nut assembly, P/N GMD115-810029-17 and P/N GMD115-810029-
23, on the right MLG actuator. The actions specified in this AD are 
intended to prevent failure of the actuator nut assembly for the 
right MLG actuator, which could result in failure of the MLG. This 
failure could prevent the extension or retraction of the MLG.

What Must I Do To Address This Problem?

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

------------------------------------------------------------------------
           Actions                 Compliance            Procedures
------------------------------------------------------------------------
(1) Maintenance Records       Within the next 50    No special
 Check:                        hours time-in-        procedures
                               service (TIS) or 30   necessary to check
                               calendar days after   the maintenance
                               the effective date    records.
                               of this AD,
                               whichever occurs
                               first, unless
                               already done.
(i) Check the maintenance
 records to determine
 whether the following
 replacements have been
 made:.
(A) Actuator nut assembly
 (part number (P/N) GMD115-
 810029-17) for the right
 main landing gear (MLG)
 actuator; and.
(B) Actuator nut assembly (P/
 N) GMD115-810029-23 for the
 right main landing gear
 (MLG) actuator.
(ii) The owner/operator
 holding at least a private
 pilot certificate as
 authorized by section 43.7
 of the Federal Aviation
 Regulations (14 CFR 43.7)
 may make this check. You
 must make an entry into the
 aircraft records that shows
 compliance with this
 portion of the AD in
 accordance with section
 43.9 of the Federal
 Aviation Regulations (14
 CFR 43.9).
(2) If you find as a result   Within the next 50    Follow General
 of the check required by      hours time-in-        Machine Diecron,
 paragraph (e)(1)(i) of this   service (TIS) or 30   Inc. Service
 AD that there is no record    calendar days after   Bulletin GM-D 32-30-
 of the specified assembly     the effective date    01/102505, dated
 replacement then inspect      of this AD,           November 21, 2005.
 for any:                      whichever occurs
                               first, unless
                               already done.

[[Page 5799]]

 
(i) Actuator nut assembly,
 (P/N) GMD115-810029-17, for
 the right main landing gear
 (MLG) actuator; and
(ii) Actuator nut assembly,
 (P/N) GMD115-810029-23, for
 the right main landing gear
 (MLG) actuator.
(iii) You may choose to do
 the inspection without
 doing the maintenance
 records check.
(3) If during the inspection  Before further        Follow General
 required by paragraph         flight after the      Machine Diecron,
 (e)(2) of this AD, you find   inspection required   Inc. Service
 any actuator nut assembly,    by paragraph (e)(2)   Bulletin GM-D 32-30-
 (P/N) GMD115-810029-17 or     of this AD.           01/102505, dated
 (P/N) GMD115-810029-23, for                         November 21, 2005.
 the right MLG actuator,
 replace the specific
 assembly with a new
 actuator nut assembly, (P/
 N) GMD115-810029-23B or FAA-
 approved equivalent (P/N).
(4) Do not install any        As of the effective   Not Applicable.
 actuator nut assembly, (P/    date of this AD.
 N) GMD115-810029-17 or (P/
 N) GMD115-810029-23, for
 the right MLG actuator.
------------------------------------------------------------------------

May I Request an Alternative Method of Compliance?

    (f) The Manager, Atlanta Aircraft Certification Office (ACO), 
FAA, has the authority to approve alternative methods of compliance 
for this AD, if requested using the procedures found in 14 CFR 
39.19.
    (g) For information on any already approved alternative methods 
of compliance or for information pertaining to this AD, contact Don 
Buckley, Aerospace Engineer, Airframe and Propulsion Branch, ACE-
117A, FAA, Atlanta ACO, One Crown Center, 1895 Phoenix Boulevard, 
Suite 450, Atlanta, Georgia 30337-2748, telephone (770) 703-6086; 
fax (770) 703-6097.

May I Get Copies of the Documents Referenced in This AD?

    (h) To get copies of the documents referenced in this AD, 
contact General Machine--Diecron, Inc., 3131 U.S. Highway 41, 
Griffin, Georgia 30224, telephone: (770) 228-6200; facsimile: (770) 
228-6299. To view the AD docket, go to the Docket Management 
Facility; U.S. Department of Transportation, 400 Seventh Street, 
SW., Nassif Building, Room PL-401, Washington, DC, or on the 
Internet at http://dms.dot.gov. The docket number is Docket No. FAA-
2005-23334; Directorate Identifier 2005-CE-53-AD.

    Issued in Kansas City, Missouri, on January 30, 2006.
John R. Colomy,
Acting Manager, Small Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. E6-1470 Filed 2-2-06; 8:45 am]
BILLING CODE 4910-13-P