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[Federal Register: October 21, 2010 (Volume 75, Number 203)]
[Proposed Rules]               
[Page 64960-64963]
From the Federal Register Online via GPO Access [wais.access.gpo.gov]
[DOCID:fr21oc10-12]                         

========================================================================
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 64960]]

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2010-1039; Directorate Identifier 2010-NM-002-AD]
RIN 2120-AA64

 
Airworthiness Directives; Bombardier, Inc. Model CL-600-2B19 
(Regional Jet Series 100 & 440) Airplanes

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Notice of proposed rulemaking (NPRM).

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

SUMMARY: We propose to adopt a new airworthiness directive (AD) for the 
products listed above that would supersede an existing AD. This 
proposed AD results from mandatory continuing airworthiness information 
(MCAI) originated by an aviation authority of another country to 
identify and correct an unsafe condition on an aviation product. The 
MCAI describes the unsafe condition as:

    There has been numerous reported failures of the Regional Jet 
engine TCGB [throttle control gearbox] P/Ns: 2100140-003, 2100140-
005 & 2100140-007. Some of these failures have resulted in in-flight 
engine shutdowns. Post incident investigations revealed that 
excessive wear within the engine TCGB could alter the rigging 
position or cause the throttle to jam. With the rigging position 
altered, movement of the throttle lever towards the idle position 
can result in throttle moving too close to the fuel shut-off 
position, which potentially, can cause the engine to flame out.
* * * * *
The proposed AD would require actions that are intended to address the 
unsafe condition described in the MCAI.

DATES: We must receive comments on this proposed AD by December 6, 
2010.

ADDRESSES: You may send comments by any of the following methods:
     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 W12-40, 1200 New 
Jersey Avenue, SE., Washington, DC, between 9 a.m. and 5 p.m., Monday 
through Friday, except Federal holidays.
    For service information identified in this proposed AD, contact 
Bombardier, Inc., 400 C[ocirc]te-Vertu Road West, Dorval, Qu[eacute]bec 
H4S 1Y9, Canada; telephone 514-855-5000; fax 514-855-7401; e-mail 
thd.crj@aero.bombardier.com; Internet http://www.bombardier.com. You 
may review copies of the referenced service information at the FAA, 
Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton, 
Washington. For information on the availability of this material at the 
FAA, call 425-227-1221.

Examining the AD Docket

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

FOR FURTHER INFORMATION CONTACT: Rocco Viselli, Senior Aviation Safety 
Engineer, Avionic & Flight Test Branch, ANE-172, FAA, New York Aircraft 
Certification Office, 1600 Stewart Avenue, Suite 410, Westbury, New 
York 11590; telephone (516) 228-7331; fax (516) 794-5531.

SUPPLEMENTARY INFORMATION: 

Comments Invited

    We invite you to send any written relevant data, views, or 
arguments about this proposed AD. Send your comments to an address 
listed under the ADDRESSES section. Include ``Docket No. FAA-2010-1039; 
Directorate Identifier 2010-NM-002-AD'' at the beginning of your 
comments. We specifically invite comments on the overall regulatory, 
economic, environmental, and energy aspects of this proposed AD. We 
will consider all comments received by the closing date and may amend 
this proposed AD based on 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 about this proposed AD.

Discussion

    On March 8, 2005, we issued AD 2005-06-04, Amendment 39-14012 (70 
FR 12963, March 17, 2005). That AD required actions intended to address 
an unsafe condition on the products listed above.
    Since we issued AD 2005-06-04, the inspection for the throttle 
control gearbox (TCGB) required by that AD has been transcribed in a 
new certification maintenance requirement (CMR) task. This NPRM 
proposes to mandate the incorporation of the new CMR task into the CL-
600-2B19 maintenance requirements manual (MRM) as introduced by the MRM 
temporary revision 2A-47. Transport Canada Civil Aviation, which is the 
aviation authority for Canada, has issued Canadian Airworthiness 
Directive CF-2004-01R2, dated September 29, 2009 (referred to after 
this as ``the MCAI''), to correct an unsafe condition for the specified 
products. The MCAI states:

    There has been numerous reported failures of the Regional Jet 
engine TCGB P/Ns: 2100140-003, 2100140-005 & 2100140-007. Some of 
these failures have resulted in in-flight engine shutdowns. Post 
incident investigations revealed that excessive wear within the 
engine TCGB could alter the rigging position or cause the throttle 
to jam. With the rigging position altered, movement of the throttle 
lever towards the idle position can result in throttle moving too 
close to the fuel shut-off position, which potentially, can cause 
the engine to flame out.
    Bombardier issued Service Bulletin (SB) 601R-76-019 dated 21 
August 2003, to introduce an inspection of, and if required, 
replacement of the throttle control gearbox with a serviceable unit. 
AD CF-2004-01 was originally issued to mandate the subject 
inspection requirement as per SB 601R-76-019 and subsequent 
revisions.
    The subject TCGB inspection requirements mandated as per the 
earlier versions of this AD, are now transcribed in a new 
Certification Maintenance Requirement (CMR) task. This revision is 
issued to

[[Page 64961]]

mandate the incorporation of the new CMR task into the CL-600-2B19 
Maintenance Requirements Manual (MRM), as introduced by the MRM 
Temporary Revision (TR) 2A-47.

    You may obtain further information by examining the MCAI in the AD 
docket.

Relevant Service Information

    Bombardier has issued Service Bulletin 601R-76-019, Revision B, 
dated February 16, 2005; and Service Bulletin 601R-76-019, Revision C, 
dated July 5, 2007. Bombardier has also issued Temporary Revision 2A-
47, dated May 27, 2009, to Appendix A--Certification Maintenance 
Requirements, of Part 2 of the Bombardier CL-600-2B19 Maintenance 
Requirements Manual. The actions described in this service information 
are intended to correct the unsafe condition identified in the MCAI.

FAA's Determination and Requirements of This Proposed AD

    This product has been approved by the aviation authority of another 
country, and is approved for operation in the United States. Pursuant 
to our bilateral agreement with the State of Design Authority, we have 
been notified of the unsafe condition described in the MCAI and service 
information referenced above. We are proposing this AD because we 
evaluated all pertinent information and determined an unsafe condition 
exists and is likely to exist or develop on other products of the same 
type design.

Differences Between This AD and the MCAI or Service Information

    We have reviewed the MCAI and related service information and, in 
general, agree with their substance. But we might have found it 
necessary to use different words from those in the MCAI to ensure the 
AD is clear for U.S. operators and is enforceable. In making these 
changes, we do not intend to differ substantively from the information 
provided in the MCAI and related service information.
    We might also have proposed different actions in this AD from those 
in the MCAI in order to follow FAA policies. Any such differences are 
highlighted in a NOTE within the proposed AD.

Costs of Compliance

    Based on the service information, we estimate that this proposed AD 
would affect about 638 products of U.S. registry.
    The actions that are required by AD 2005-06-04 and retained in this 
proposed AD take about 7 work-hours per product. The average labor rate 
is $85 per work-hour. Based on these figures, we estimate the cost of 
the requirements retained in this proposed AD on U.S. operators to be 
$379,610, or $595 per product
    We estimate that it would take about 1 work-hour per product to 
comply with the new basic requirements of this proposed AD. The average 
labor rate is $85 per work-hour. Based on these figures, we estimate 
the cost of the new basic requirements in this proposed AD on U.S. 
operators to be $54,230, or $85 per product.

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 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 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. 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.

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 removing Amendment 39-14012 (70 FR 
12963, March 17, 2005) and adding the following new AD:

Bombardier, Inc.: Docket No. FAA-2010-1039; Directorate Identifier 
2010-NM-002-AD.

Comments Due Date

    (a) We must receive comments by December 6, 2010.

Affected ADs

    (b) The AD supersedes AD 2005-06-04, Amendment 39-14012.

Applicability

    (c) This AD applies to Bombardier, Inc. Model CL-600-2B19 
(Regional Jet Series 100 & 440) airplanes, certificated in any 
category, having an engine throttle control gearbox (TCGB) with part 
number 2100140-003, 2100140-005, or 2100140-007 installed.

    Note 1:  This AD requires revisions to certain operator 
maintenance documents to include new inspections. Compliance with 
these inspections is required by 14 CFR 91.403(c). For airplanes 
that have been previously modified, altered, or repaired in the 
areas addressed by these inspections, the operator may not be able 
to accomplish the inspections described in the revisions. In this 
situation, to comply with 14 CFR 91.403(c), the operator must 
request approval for an alternative method of compliance according 
to paragraph (m)(1) of this AD. The request should include a 
description of changes to the required inspections that will ensure 
the continued operational safety of the airplane.

Subject

    (d) Air Transport Association (ATA) of America Code 76: Engine 
Controls.

Reason

    (e) The mandatory continuing airworthiness information (MCAI) 
states:
    There has been numerous reported failures of the Regional Jet 
engine TCGB P/Ns: 2100140-003, 2100140-005 & 2100140-007. Some of 
these failures have resulted in in-flight engine shutdowns. Post 
incident investigations revealed that excessive wear within the 
engine TCGB could alter the rigging position or cause the throttle 
to jam.

[[Page 64962]]

With the rigging position altered, movement of the throttle lever 
towards the idle position can result in throttle moving too close to 
the fuel shut-off position, which potentially, can cause the engine 
to flame out.
    Bombardier issued Service Bulletin (SB) 601R-76-019 dated 21 
August 2003, to introduce an inspection of, and if required, 
replacement of the throttle control gearbox with a serviceable unit. 
AD CF-2004-01 was originally issued to mandate the subject 
inspection requirement as per SB 601R-76-019 and subsequent 
revisions.
    The subject TCGB inspection requirements mandated as per the 
earlier versions of this AD, are now transcribed in a new 
Certification Maintenance Requirement (CMR) task. This revision is 
issued to mandate the incorporation of the new CMR task into the CL-
600-2B19 Maintenance Requirements Manual (MRM), as introduced by the 
MRM Temporary Revision (TR) 2A-47.

Compliance

    (f) You are responsible for having the actions required by this 
AD performed within the compliance times specified, unless the 
actions have already been done.

Restatement of Requirements of AD 2005-06-04, With New Service 
Information

Inspection

    (g) For airplanes having serial numbers (S/Ns) 7003 through 7067 
inclusive, and 7069 and subsequent: At the applicable time specified 
in paragraph (g)(1) or (g)(2) of this AD, do a detailed inspection 
for wear of the left and right engine throttle control gearboxes 
having part number (P/N) 2100140-005 or 2100140-007 by doing all the 
actions per Part A, paragraphs A., B., and C.(1) through C.(4), of 
the Accomplishment Instructions of Bombardier Service Bulletin 601R-
76-019, dated August 21, 2003; Revision `A,' dated February 19, 
2004; Revision B, dated February 16, 2005; or Revision C, dated July 
5, 2007. If the wear value is the same as that specified in Part A, 
paragraph B.(8), of the Accomplishment Instructions of Bombardier 
Service Bulletin 601R-76-019, dated August 21, 2003; Revision `A,' 
dated February 19, 2004; Revision B, dated February 16, 2005; or 
Revision C, dated July 5, 2007: Repeat the inspection thereafter at 
intervals not to exceed 1,000 flight hours. As of the effective date 
of this AD, only Bombardier Service Bulletin 601R-76-019, Revision 
C, dated July 5, 2007, may be used. Doing the inspection required by 
paragraph (k) of this AD terminates the requirement in this 
paragraph.
    (1) For airplanes having S/Ns 7003 through 7067 inclusive and 
7069 through 7999 inclusive: Within 1,000 flight hours or 90 days 
after March 25, 2004 (the effective date of AD 2004-05-12), 
whichever is later.
    (2) For airplanes having S/Ns 8000 and subsequent: Within 1,000 
flight hours or 90 days after April 1, 2005 (the effective date of 
AD 2005-06-04), whichever is later.

    Note 2:  For the purposes of this AD, a detailed inspection is: 
``An intensive visual examination of a specific structural area, 
system, installation, or assembly to detect damage, failure, or 
irregularity. Available lighting is normally supplemented with a 
direct source of good lighting at an intensity deemed appropriate by 
the inspector. Inspection aids such as mirror, magnifying lenses, 
etc., may be used. Surface cleaning and elaborate access procedures 
may be required.''

Corrective Action

    (h) If the wear value found during any inspection required by 
paragraph (g) of this AD is not the same as that specified in Part 
A, paragraph B.(8), of the Accomplishment Instructions of Bombardier 
Service Bulletin 601R-76-019, dated August 21, 2003; Revision `A,' 
dated February 19, 2004; Revision B, dated February 16, 2005; or 
Revision C, dated July 5, 2007: Do the applicable actions required 
by paragraph (h)(1), (h)(2), or (h)(3) of this AD, at the time 
specified, per the Accomplishment Instructions of Bombardier Service 
Bulletin 601R-76-019, dated August 21, 2003; Revision `A,' dated 
February 19, 2004; Revision B, dated February 16, 2005; or Revision 
C, dated July 5, 2007. Repeat the inspection required by paragraph 
(g) of this AD thereafter at intervals not to exceed 1,000 flight 
hours. As the effective date of this AD, only Bombardier Service 
Bulletin 601R-76-019, Revision C, dated July 5, 2007, may be used. 
Doing the inspection required by paragraph (k) of this AD terminates 
the inspection requirements of this paragraph.
    (1) If the wear value on one or both of the gearboxes is the 
same as that specified in Part A, paragraph B.(5), of the 
Accomplishment Instructions of Bombardier Service Bulletin 601R-76-
019, dated August 21, 2003; Revision `A,' dated February 19, 2004; 
Revision B, dated February 16, 2005; or Revision C, dated July 5, 
2007: Before further flight, replace the affected gearbox with a new 
or serviceable gearbox, by doing all the actions per Part B, 
paragraphs D. through F.(7) of the Accomplishment Instructions of 
Bombardier Service Bulletin 601R-76-019, dated August 21, 2003; 
Revision `A,' dated February 19, 2004; Revision B, dated February 
16, 2005; or Revision C, dated July 5, 2007. As the effective date 
of this AD, only Bombardier Service Bulletin 601R-76-019, Revision 
C, dated July 5, 2007, may be used.
    (2) If the wear value on both the left and right gearboxes is 
the same as that specified in Part A, paragraph B.(6), of Bombardier 
Service Bulletin 601R-76-019, dated August 21, 2003; Revision `A,' 
dated February 19, 2004; Revision B, dated February 16, 2005; or 
Revision C, dated July 5, 2007: Before further flight, replace the 
gearbox having the higher wear value with a new or serviceable 
gearbox, by doing all the actions per Part B, paragraphs D. through 
F.(7), of the Accomplishment Instructions of Bombardier Service 
Bulletin 601R-76-019, dated August 21, 2003; Revision `A,' dated 
February 19, 2004; Revision B, dated February 16, 2005; or Revision 
C, dated July 5, 2007. Within 1,000 flight hours after doing the 
replacement, replace the other gearbox. As the effective date of 
this AD, only Bombardier Service Bulletin 601R-76-019, Revision C, 
dated July 5, 2007, may be used.
    (3) If the wear value on only one gearbox is the same as that 
specified in Part A, paragraph B.(7), and the wear value on the 
other gearbox is the same as that specified in Part A, paragraph 
B.(8), of the Accomplishment Instructions of Bombardier Service 
Bulletin 601R-76-019, dated August 21, 2003; Revision `A,' dated 
February 19, 2004; Revision B, dated February 16, 2005; or Revision 
C, dated July 5, 2007: Within 1,000 flight hours after the 
inspection, replace the gearbox with the wear value that is the same 
as that specified in Part A, paragraph B.(7), with a new or 
serviceable gearbox. Do the replacement by doing all the actions per 
Part B, paragraphs D. through F.(7), of the Accomplishment 
Instructions of Bombardier Service Bulletin 601R-76-019, dated 
August 21, 2003; Revision `A,' dated February 19, 2004; Revision B, 
dated February 16, 2005; or Revision C, dated July 5, 2007. As the 
effective date of this AD, only Bombardier Service Bulletin 601R-76-
019, Revision C, dated July 5, 2007, may be used.

Additional Guidance

    Note 3:  Bombardier Service Bulletin 601R-76-019, dated August 
21, 2003; Revision `A,' dated February 19, 2004; Revision B, dated 
February 16, 2005; or Revision C, dated July 5, 2007; reference 
Trans Digm, Inc., AeroControlex Group, Service Bulletin 2100140-007-
76-04, dated July 22, 2003, as an additional source of guidance for 
accomplishment of the inspections and replacement.

Reporting Requirement

    (i) At the applicable time specified in paragraph (i)(1) or 
(i)(2) of this AD, submit a report of gearbox wear to Bombardier 
Aerospace, In-Service Engineering (Engine Group); fax (514) 855-
7708. The report must include the airplane serial number, the number 
of flight hours on the airplane, and the number of flight hours on 
each gearbox (if different than the number of flight hours on the 
airplane). Under the provisions of the Paperwork Reduction Act of 
1980 (44 U.S.C. 3501 et seq.), the Office of Management and Budget 
(OMB) has approved the information collection requirements contained 
in this AD and has assigned OMB Control Number 2120-0056.
    (1) For Bombardier Model CL-600-2B19 (Regional Jet Series 100 & 
440) airplanes, serial numbers 7003 through 7067 inclusive, and 7069 
through 7999 inclusive: Submit a report within 10 days after doing 
the inspection required by paragraph (g) of this AD, or within 10 
days after March 25, 2004, whichever is later.
    (2) For Bombardier Model CL-600-2B19 (Regional Jet Series 100 & 
440) airplanes, serial numbers 8000 and subsequent: Submit a report 
within 10 days after doing the inspection required by paragraph (g) 
of this AD, or within 10 days after April 1, 2005 (the effective 
date of AD 2005-06-04), whichever is later.

New Requirements of This AD

Actions

    (j) For all airplanes: Within 30 days as the effective date of 
this AD, revise the Airworthiness Limitations (AWL) section of the 
Instructions for Continued Airworthiness to include the information 
in Bombardier

[[Page 64963]]

Temporary Revision 2A-47, dated May 27, 2009, to Appendix A--
Certification Maintenance Requirements, of Part 2 of the Bombardier 
CL-600-2B19 Maintenance Requirements Manual.

    Note 4: The actions required by paragraph (j) of this AD may be 
done by inserting a copy of Bombardier Temporary Revision 2A-47, 
dated May 27, 2009, into the AWL section of Appendix A--
Certification Maintenance Requirements, of Part 2 of the Bombardier 
CL-600-2B19 Maintenance Requirements Manual. When this temporary 
revision has been included in the limitation section of the general 
revisions of the document, the general revisions may be inserted in 
the document, provided the relevant information in the general 
revision is identical to that in Bombardier Temporary Revision 2A-
47, dated May 27, 2009.

    (k) For the task identified in Bombardier Temporary Revision 2A-
47, dated May 27, 2009, do the initial inspection within 1,000 
flight hours after the effective date of this AD. Doing the initial 
inspection required by this paragraph terminates the requirements of 
paragraph (g) of this AD and the inspection requirements of 
paragraph (h) of this AD.
    (l) Thereafter, except as provided by paragraph (m) of this AD, 
no alternative intervals may be approved for the task indentified in 
Bombardier Temporary Revision 2A-47, dated May 27, 2009, which 
requires a special detailed inspection of the throttle control 
gearbox for gear and rack teeth wear.

FAA AD Differences

    Note 5:  This AD differs from the MCAI and/or service 
information as follows: No differences.

Other FAA AD Provisions

    (m) The following provisions also apply to this AD:
    (1) Alternative Methods of Compliance (AMOCs): The Manager, New 
York Aircraft Certification Office (ACO), ANE-170, 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: Program 
Manager, Continuing Operational Safety, FAA, New York ACO, 1600 
Stewart Avenue, Suite 410, Westbury, New York 11590; telephone 516-
228-7300; fax 516-794-5531. Before using any approved AMOC on any 
airplane to which the AMOC applies, notify your principal 
maintenance inspector (PMI) or principal avionics inspector (PAI), 
as appropriate, or lacking a principal inspector, your local Flight 
Standards District Office. The AMOC approval letter must 
specifically reference this AD.
    (2) Airworthy Product: For any requirement in this AD to obtain 
corrective actions from a manufacturer or other source, use these 
actions if they are FAA-approved. Corrective actions are considered 
FAA-approved if they are approved by the State of Design Authority 
(or their delegated agent). You are required to assure the product 
is airworthy before it is returned to service.
    (3) Reporting Requirements: For any reporting requirement in 
this AD, under the provisions of the Paperwork Reduction Act (44 
U.S.C. 3501 et seq.), the Office of Management and Budget (OMB) has 
approved the information collection requirements and has assigned 
OMB Control Number 2120-0056.

Related Information

    (n) Refer to MCAI Canadian Airworthiness Directive CF-2004-01R2, 
dated September 29, 2009; Bombardier Service Bulletin 601R-76-019, 
Revision C, dated July 5, 2007; and Bombardier Temporary Revision 
2A-47, dated May 27, 2009, to Appendix A--Certification Maintenance 
Requirements, of Part 2 of the Bombardier CL-600-2B19 Maintenance 
Requirements Manual; for related information.

    Issued in Renton, Washington, on October 13, 2010.
John Piccola,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 2010-26550 Filed 10-20-10; 8:45 am]
BILLING CODE 4910-13-P
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