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2008-10-08	EMPRESA BRASILEIRA DE AERONAUTICA S.A. (EMBRAER): Docket No. FAA-2008-0516; Directorate Identifier 2008-NM-026-AD; Amendment 39-15514.

EFFECTIVE DATE

(a) This AD becomes effective May 23, 2008.

AFFECTED ADS

(b) This AD supersedes AD 2005-26-15.

APPLICABILITY

(c) This AD  applies to EMBRAER  Model EMB-135BJ, -135ER,  -135KE, -135KL,
    and  -135LR airplanes;  and  Model  EMB-145, -145ER,  -145MR,  -145LR,
    -145XR, -145MP,  and -145EP  airplanes, certificated  in any category;
    serial numbers 145001 through 145189 inclusive, 145191 through  145362
    inclusive,  145364 through  145373 inclusive,  145375, 145377  through
    145411  inclusive,  145413 through  145424  inclusive, 145426  through
    145430  inclusive,  145434 through  145436  inclusive, 145440  through
    145445  inclusive,  145448,  145450,  and  145801;  equipped  with   a
    mechanical gust lock system.

UNSAFE CONDITION

(d) This AD results from  additional reports of failure of  the mechanical
    gust  lock  system  to  protect  the  elevator  control  surfaces  and
    components from  high wind  gusts. We  are issuing  this AD to prevent
    discrepancies in the  elevator control system,  which could result  in
    reduced control of the elevator and consequent reduced controllability
    of the airplane.

COMPLIANCE

(e) 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 THE  REQUIREMENTS OF  AD 2005-26-15  WITH CERTAIN  REVISED
COMPLIANCE TIMES/REQUIREMENTS

REPETITIVE INSPECTIONS

(f) Within 800 flight hours after February 3, 2006 (the effective date  of
    AD  2005-26-15),  do a  detailed  inspection of  the  elevator control
    system for any crack, rupture, or bend in any component, in accordance
    with the Accomplishment Instructions  of EMBRAER Service Bulletin  145
    -27-0087,  Change 03,  dated September  27, 2002.  Where this  service
    bulletin specifies  to return  discrepant parts  and report inspection
    results to the manufacturer, this  AD does not require these  actions.
    Repeat  the inspection  thereafter at  intervals not  to exceed  2,500
    flight hours or 15 months, whichever is first.

NOTE 1: For the purposes of this AD, a detailed inspection is defined  as:
"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 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."

REPLACEMENT OF DISCREPANT PARTS

(g) If  any discrepant  part is  found during  any inspection  required by
    paragraph  (f)  of  this  AD,  before  further  flight,  replace   the
    discrepant part with a new part, in accordance with the Accomplishment
    Instructions of EMBRAER Service Bulletin 145-27-0087, Change 03, dated
    September 27, 2002.

MODIFICATION

(h) At the applicable time specified  in paragraph (j) of this AD:  Modify
    the elevator gust lock by accomplishing paragraph (h)(1) or (h)(2)  of
    this AD, as applicable. Accomplishment of the modification  terminates
    the repetitive inspections required by paragraph (f) of this AD. Doing
    the actions  required by  paragraph (h)(1)  or (h)(2)  of this  AD, as
    applicable,  also  terminates  the  requirements  of  AD   2008-03-03,
    amendment 39-15352. This AD does not mandate installing new electrical
    grounding  for  the  gust  lock  system  actuator  at  the  horizontal
    stabilizer structure in accordance  with EMBRAER Service Bulletin  145
    -27-0075,  Revision 09,  dated November  8, 2006;  or EMBRAER  Service
    Bulletin 145-27-0086, Revision 05, dated November 8, 2006.

(1) For   airplanes  listed  in   EMBRAER  Service  Bulletin  145-27-0075,
    Revision 08, dated March 3, 2005: Do paragraph (h)(1)(i) or (h)(1)(ii)
    of this  AD, as  applicable, and  install a  new spring  cartridge and
    implement  new logic  for the  electromechanical gust  lock system  by
    doing all  actions in  section 3.D.  (Part IV)  of the  Accomplishment
    Instructions  of EMBRAER  Service Bulletin  145-27-0075, Revision  08,
    dated March 3, 2005; or Revision 09, dated November 8, 2006. After the
    effective date of this AD, Revision 09 of the service bulletin must be
    used. After accomplishing the actions in EMBRAER Service Bulletin  145
    -27-0101, as specified in  the Accomplishment Instructions of  EMBRAER
    Service Bulletin 145-27-0075, Revision 08 or Revision 09; the airplane
    flight manual (AFM) revision  required by AD 2002-26-51,  amendment 39
    -13008, may  be removed  from the  Limitations section  of the EMBRAER
    EMB-145 AFM. Accomplishing the actions specified in the Accomplishment
    Instructions of EMBRAER Service Bulletin 145-27-0102, as specified  by
    EMBRAER  Service Bulletin  145-27-0075, Revision  08  or  Revision 09,
    terminates  the  repetitive  inspections  required  by  AD 2005-24-11,
    amendment 39-14391.

(i) Replace the mechanical gust lock system with an electromechanical gust
    lock system,  and replace  the control  stand with  a reworked control
    stand, by doing  all the actions  (including a detailed  inspection to
    ensure that  certain parts  have been  removed previously  per EMBRAER
    Service Bulletin 145-27-0076) in and per section 3.A. (Part I) or 3.B.
    (Part  II),  as  applicable,  of  the  Accomplishment  Instructions of
    EMBRAER Service Bulletin 145-27-0075,  Revision 08 or Revision  09. If
    the  inspection  reveals  that certain  subject  parts  have not  been
    removed previously, before further flight, remove the subject parts in
    accordance with EMBRAER Service  Bulletin 145-27-0075, Revision 08  or
    Revision 09. Where Parts I  and II of the Accomplishment  Instructions
    of EMBRAER Service Bulletin  145-27-0075, Revision 08 or  Revision 09,
    specify to  remove and  "send the  control stand  to be  reworked in a
    workshop," replace the control stand with a control stand reworked  as
    specified  in  EMBRAER  Service Bulletin  145-27-0075, Revision  08 or
    Revision 09. After the effective date  of this AD, Revision 09 of  the
    service  bulletin  must  be  used for  the  actions  required  by this
    paragraph.

(ii) Replace  the  return spring  and spring  terminal  of  the gust  lock
     control lever with improved parts by doing all the actions in and per
     section 3.C. (Part III) of the Accomplishment Instructions of EMBRAER
     Service Bulletin 145-27-0075, Revision  08 or Revision 09.  After the
     effective date of this AD,  Revision 09 of the service  bulletin must
     be used.

NOTE 2:  Part IV  of the  Accomplishment Instructions  of EMBRAER  Service
Bulletins  145-27-0075, Revision  08 and  Revision 09,  refers to  EMBRAER
Service Bulletin 145-27-0101,  Revision 02, dated  December 27, 2004;  and
EMBRAER Service Bulletin 145-27-0102, Revision 02, dated January 20, 2005;
as additional sources of  instructions for accomplishing the  installation
of a  new spring  cartridge and  implementation of  the new  logic for the
electromechanical gust lock system.

(2) For airplanes listed in  EMBRAER Service Bulletin 145-27-0086,  Change
    04,  dated  March  21,  2005:  Do  paragraphs  (h)(2)(i),  (h)(2)(ii),
    (h)(2)(iii), and (h)(2)(iv) of this AD, as applicable.

(i) Rework the tail carbon box and the horizontal stabilizer by doing  all
    the actions  (including the  inspection for  delamination) in  and per
    section 3.A. (Part  I) of the  Accomplishment Instructions of  EMBRAER
    Service  Bulletin  145-27-0086,  Change  04;  or  Revision  05,  dated
    November 8, 2006. After the effective date of this AD, Revision 05  of
    the service bulletin must be  used. If any delamination is  found that
    is outside  the limits  specified in  EMBRAER Service  Bulletin 145-27
    -0086, Change 04 or Revision  05, before further flight, repair  per a
    method approved by either the Manager, International Branch,  ANM-116,
    Transport Airplane Directorate, FAA; the Departmento de Aviacao  Civil
    (or its delegated agent); or the Agência Nacional de Aviação Civil (or
    its delegated agent).

(ii) Install wiring and electrical components by doing all the actions  in
     and per section 3.B. (Part II) of the Accomplishment Instructions  of
     EMBRAER Service Bulletin 145-27-0086, Change 04 or Revision 05. After
     the effective date  of this AD,  Revision 05 of  the service bulletin
     must be used.

(iii) Install and activate the electromechanical gust lock system by doing
      all the  actions in  section 3.D.  (Part IV)  of the  Accomplishment
      Instructions of EMBRAER Service  Bulletin 145-27-0086, Change 04  or
      Revision 05.  Where Part  IV of  the Accomplishment  Instructions of
      EMBRAER  Service Bulletin  145-27-0086,  Change  04 or  Revision 05,
      specifies to remove and "send the control stand to be reworked in  a
      workshop," replace the control  stand with a control  stand reworked
      as  specified  in  Part  III  of  the  service  bulletin.  After the
      effective date of this AD, Revision 05 of the service bulletin  must
      be used.

(iv) Install  a  new spring  cartridge  and  implement new  logic for  the
     electromechanical gust lock system by doing all applicable actions in
     section 3.E. (Part V)  of the Accomplishment Instructions  of EMBRAER
     Service Bulletin  145-27-0086, Change  04 or  Revision 05.  After the
     effective date of this AD,  Revision 05 of the service  bulletin must
     be used. After accomplishing the actions in EMBRAER Service  Bulletin
     145-27-0101;  as  specified  in  the Accomplishment  Instructions  of
     EMBRAER Service Bulletin 145-27-0086,  Change 04 or Revision  05; the
     AFM revision required  by AD 2002-26-51,  amendment 39-13008, may  be
     removed  from the  Limitations section  of the  EMBRAER EMB-145  AFM.
     Accomplishing the actions in EMBRAER Service Bulletin 145-27-0102; as
     specified  in  the  Accomplishment  Instructions  of  EMBRAER Service
     Bulletin  145-27-0086,  Change  04  or  Revision  05;  terminates the
     repetitive  inspections  required  by  AD  2005-24-11,  amendment  39
     -14391.

NOTE 3: Part  V of  the  Accomplishment  Instructions  of  EMBRAER Service
Bulletin 145-27-0086, Change 04 and Revision 05, refers to EMBRAER Service
Bulletin 145-27-0101, Revision  02, dated December  27, 2004; and  EMBRAER
Service  Bulletin 145-27-0102,  Revision 02,  dated January  20, 2005;  as
additional sources of instructions for accomplishing the installation of a
new  spring  cartridge  and  implementation  of  the  new  logic  for  the
electromechanical gust lock system.

ACTIONS ACCOMPLISHED PREVIOUSLY

(i) Actions  accomplished before  February  3, 2006,  are  acceptable  for
    compliance  with  the  corresponding  requirements  of  this  AD,   as
    specified in paragraphs (i)(1), (i)(2), and (i)(3) of this AD.

(1) Modification of the elevator gust lock system before February 3, 2006,
    in accordance  with EMBRAER  Service Bulletin  145-27-0075, Change 06,
    dated  July  16, 2002,  is  acceptable for  compliance  with paragraph
    (h)(1) of this AD, provided that, within the compliance time specified
    in paragraph (h) of this AD,  a new spring cartridge is installed  and
    new logic for the electromechanical gust lock system is implemented in
    accordance  with  Part  IV of  EMBRAER  Service  Bulletin 145-27-0075,
    Revision 07, dated March 2, 2004, or Revision 08, dated March 3, 2005.

(2) Modification of the elevator gust lock system before February 3, 2006,
    in accordance with EMBRAER Service Bulletin 145-27-0075, Revision  07,
    dated  March 2, 2004,  is  acceptable  for  compliance  with paragraph
    (h)(1) of this AD.

(3) Modification of the elevator gust lock system before February 3, 2006,
    in accordance  with EMBRAER  Service Bulletin  145-27-0086, Change 02,
    dated  December 23,  2003;  or  EMBRAER Service  Bulletin 145-27-0086,
    Change 03,  dated April  14, 2004;  is acceptable  for compliance with
    paragraph (h)(2) of this AD.

REDUCED COMPLIANCE TIME FOR REQUIRED MODIFICATION

(j) For  airplanes on  which the  modification of  the elevator  gust lock
    system specified in paragraph (h) of  this AD has not been done  as of
    the effective date of this AD:  At the earlier of the times  specified
    in paragraphs  (j)(1) and  (j)(2) of  this AD,  accomplish the actions
    required by paragraph (h)(1) or (h)(2) of this AD, as applicable.

(1) Within 10,000 flight hours after February 3, 2006, or within 60 months
    after February 3, 2006, whichever occurs first.

(2) Within  90 days  after the  effective date  of this  AD, or 500 flight
    hours after the effective date of this AD, whichever occurs later.

ALTERNATIVE METHODS OF COMPLIANCE (AMOCS)

(k)(1) The Manager,  International Branch, ANM-116,  has the authority  to
       approve AMOCs  for this  AD, if  requested in  accordance with  the
       procedures found in 14 CFR 39.19.

(2) To request a different method of compliance or a different  compliance
    time for this AD, follow the procedures in 14 CFR 39.19. 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

(l) None.

MATERIAL INCORPORATED BY REFERENCE

(m) You must use the service information identified in Table 1 of this  AD
    to perform the  actions that are  required by this  AD, as applicable,
    unless the AD specifies otherwise.

              TABLE 1.--ALL MATERIAL INCORPORATED BY REFERENCE
    ______________________________________________________________________
    EMBRAER SERVICE BULLETIN      REVISION/CHANGE LEVEL       DATE
    ______________________________________________________________________
    145-27-0075                       Revision 08         March 3, 2005
    145-27-0075                       Revision 09        November 8, 2006
    145-27-0086                       Change 04           March 21, 2005
    145-27-0086                       Revision 05        November 8, 2006
    145-27-0087                       Change 03         September 27, 2002
    ______________________________________________________________________

(1) The  Director of  the Federal  Register approved  the incorporation by
    reference of the service information identified in Table 2 of this  AD
    in accordance with 5 U.S.C. 552(a) and 1 CFR part 51.

              TABLE 2.--NEW MATERIAL INCORPORATED BY REFERENCE
    ______________________________________________________________________
    EMBRAER SERVICE BULLETIN      REVISION/CHANGE LEVEL       DATE
    ______________________________________________________________________
    145-27-0075                       Revision 09         November 8, 2006
    145-27-0086                       Revision 05         November 8, 2006
    ______________________________________________________________________

(2) On February 3, 2006 (70 FR 77303, December 30, 2005), the Director  of
    the Federal Register  approved the incorporation  by reference of  the
    service information identified in Table 3 of this AD.

           TABLE 3.--MATERIAL PREVIOUSLY INCORPORATED BY REFERENCE
    ______________________________________________________________________
    EMBRAER SERVICE BULLETIN      REVISION/CHANGE LEVEL       DATE
    ______________________________________________________________________
         145-27-0075                  Revision 08         March 3, 2005
         145-27-0086                  Change 04           March 21, 2005
         145-27-0087                  Change 03         September 27, 2002
    ______________________________________________________________________

(3) Contact  Empresa Brasileira  de Aeronautica  S.A. (EMBRAER),  P.O. Box
    343, CEP 12.225, Sao Jose dos  Campos, SP, Brazil, for a copy  of this
    service  information.  You may  review  copies at  the  FAA, Transport
    Airplane Directorate, 1601 Lind Avenue, SW., Renton, Washington; or at
    the  National   Archives  and   Records  Administration   (NARA).  For
    information on  the availability  of this  material at  NARA, call 202
    -741-6030, or go to:
    http://www.archives.gov/ federal-register/cfr/ibr-locations.html.

Issued in  Renton, Washington,  on April  23, 2008.  Ali Bahrami, Manager,
Transport Airplane Directorate, Aircraft Certification Service.

FOR  FURTHER  INFORMATION  CONTACT:  Sanjay  Ralhan,  Aerospace  Engineer,
International Branch, ANM-116,  Transport Airplane Directorate,  FAA, 1601
Lind Avenue, SW., Renton, Washington 98057-3356; telephone (425) 227-1405;
fax (425) 227-1149.

PREAMBLE

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

ACTION: Final rule; request for comments.

SUMMARY: The FAA is superseding an existing airworthiness directive (AD) that applies to certain EMBRAER Model EMB-135 airplanes; and Model EMB-145, -145ER, -145MR, -145LR, -145XR, -145MP, and -145EP airplanes. The existing AD currently requires performing repetitive inspections for cracks, ruptures, or bends in certain components of the elevator control system; replacing discrepant components; and, for certain airplanes, installing a new spring cartridge and implementing new logic for the electromechanical gust lock system. The existing AD also requires eventual modification of the elevator gust lock system to replace the mechanical system with an electromechanical system, which terminates the repetitive inspections. This AD reduces the compliance time for doing the modification. This AD results from additional reports of failure of the mechanical gust lock system to protect the elevator control surfaces and components from high wind gusts. We are issuing this AD to prevent discrepancies in the elevator control system, which could result in reduced control of the elevator and consequent reduced controllability of the airplane.

DATES: This AD becomes effective May 23, 2008.

The Director of the Federal Register approved the incorporation by reference of certain publications listed in the AD as of May 23, 2008.

On February 3, 2006 (70 FR 77303, December 30, 2005), the Director of the Federal Register approved the incorporation by reference of certain other publications listed in this AD.

We must receive any comments on this AD by June 9, 2008.

DATES: This AD becomes effective May 23, 2008.

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 W12-140, 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 AD, contact Empresa Brasileira de Aeronautica S.A. (EMBRAER), P.O. Box 343, CEP 12.225, Sao Jose dos Campos, SP, Brazil.

Examining the AD Docket

You may examine the AD docket 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 AD docket contains this AD, the regulatory evaluation, any comments received, and other information. The street address for the Docket 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: Sanjay Ralhan, Aerospace Engineer, International Branch, ANM-116, Transport Airplane Directorate, FAA, 1601 Lind Avenue, SW., Renton, Washington 98057-3356; telephone (425) 227-1405; fax (425) 227-1149.

SUPPLEMENTARY INFORMATION:

Discussion

On December 13, 2005, we issued AD 2005-26-15, amendment 39-14436 (70 FR 77303, December 30, 2005), for certain EMBRAER Model EMB-135 airplanes; and Model EMB-145, -145ER, -145MR, -145LR, -145XR, -145MP, and -145EP airplanes. That AD requires performing repetitive inspections for cracks, ruptures, or bends in certain components of the elevator control system; replacing discrepant components; and, for certain airplanes, installing a new spring cartridge and implementing new logic for the electromechanical gust lock system. That AD also requires eventual modification of the elevator gust lock system to replace the mechanical system with an electromechanical system, which terminates the repetitive inspections. That AD resulted from reports that cracks were found in certain components of the elevator control system in the horizontal stabilizer area of several airplanes equipped with a mechanical gust lock system. Those cracks were attributed to damage from strong wind gusts on the ground. We issued that AD to prevent discrepancies in the elevator control system, which could result in reduced control of the elevator and consequent reduced controllability of the airplane.

Actions Since AD 2005-26-15 Was Issued

After we issued AD 2005-26-15, we received a report indicating that a Model EMB-145 airplane did not rotate in response to the command from the yoke during take-off, which resulted in a rejected take-off. The airplane was one of a small percentage of remaining airplanes in the U.S. fleet for which the mechanical elevator gust lock system had yet to be modified to an electromechanical elevator gust lock system, as required by AD 2005-26-15. The compliance time specified in AD 2005-26- 15 for accomplishment of the modification time is within 10,000 flight hours or 60 months after February 3, 2006 (the effective date of that AD), whichever is first.

In light of the report described previously, we determined that the repetitive inspections in AD 2005-26-15 were inadequate to ensure long- term continued operational safety. Consequently, on January 18, 2008, we issued AD 2008-03-03, amendment 39-15352 (73 FR 5426, January 30, 2008), for certain EMBRAER Model EMB-135 airplanes; and Model EMB-145, -145ER, -145MR, -145LR, -145XR, -145MP, and -145EP airplanes. That AD requires additional (interim) inspections to detect discrepancies of the components of the elevator control system, repetitive movements of the control column to observe the normal response of the elevators, repetitive inspections to detect discrepancies of the skin of the elevators, and applicable related investigative actions and corrective actions. AD 2008-03-03 also provides for an optional terminating action for the inspections and measurements; that optional terminating action is the same terminating action that is required by AD 2005-26-15.

In addition, AD 2008-03-03 requires that operators submit reports of any findings of damage or discrepancies found during any inspection required by the AD. As we explained in the preamble to AD 2008-03-03, we were considering superseding AD 2005-26-15 to reduce the compliance time for that modification based on the results of those inspections.

Since we issued AD 2008-03-03, we have received additional reports of in-service failures of the mechanical gust lock system to protect the control surfaces and components of the elevator control system from high wind gusts and jet blasts. Rapid uncommanded movement of the elevator control surface induces inertia loads in the elevator control system, which may result in systematic damage that could ultimately cause failure of the elevator control system and consequent reduced control of the airplane.

FAA's Conclusion

Based on these additional reports, and in light of the severity of the identified unsafe condition, we have determined that in order to further reduce the risk of potential damage of the elevator control system components, the terminating modification required by AD 2005-26- 15 must be done sooner than the compliance time specified in that AD. Accomplishment of the modification, as required by paragraph (h)(1) or (h)(2) of this AD, terminates the requirements of AD 2008-03-03, as well as the requirements of paragraph (f) of this AD.

Relevant Service Information

EMBRAER has issued Service Bulletin 145-27-0075, Revision 09, dated November 8, 2006; and Service Bulletin 145-27-0086, Revision 05, dated November 8, 2006. The procedures in these service bulletins are essentially the same as those in EMBRAER Service Bulletin 145-27-0075, Revision 06, dated July 16, 2002; and EMBRAER Service Bulletin 145-27-0086, Change 01, dated July 3, 2002; which we referred to in the proposed rules to AD 2005-26-15 as the appropriate sources of service information for doing the required modification. Accomplishing the actions specified in the service information is intended to adequately address the unsafe condition.

Differences Between the AD and the Service Information

Operators should note that this AD does not mandate installing new electrical grounding for the gust lock system actuator at the horizontal stabilizer structure, as provided in the new revisions of the service bulletins described previously.

Explanation of Brazilian Airworthiness Directive

The Departmento de Aviacao Civil (DAC), which is the former airworthiness authority for Brazil, mandated EMBRAER Service Bulletin 145-27-0075, Revision 06, and EMBRAER Service Bulletin 145-27-0086, Change 01, and further revisions approved by the DAC, by issuing Brazilian airworthiness directive 2002-01-01R3, effective November 8, 2002. The DAC issued that airworthiness directive to ensure the continued airworthiness of these airplanes in Brazil. We referred to Brazilian airworthiness directive 2002-01-01R3, effective November 8, 2002, in AD 2005-26-15 as a related source of information.

Since we issued AD 2005-26-15, the Agência Nacional de Aviação Civil (ANAC) has assumed responsibility for the airplane models subject to this AD. While it has not issued a new airworthiness directive related to this issue, we have coordinated the requirements of this AD with ANAC.

U.S. Type Certification of the Airplane

These airplane models are manufactured in Brazil and are type- certificated for operation in the United States under the provisions of section 21.29 of the Federal Aviation Regulations (14 CFR 21.29) and the applicable bilateral airworthiness agreement.

Change to Existing AD

This AD retains the requirements of AD 2005-26-15. Since AD 2005- 26-15 was issued, the AD format has been revised, and certain paragraphs have been rearranged. As a result, the corresponding paragraph identifiers have changed in this AD, as listed in the following table:

Revised Paragraph Identifiers

Requirement in AD 2005-26-15 Corresponding requirement in this AD

paragraph (a) paragraph (f)

paragraph (b) paragraph (g)

paragraph (c) paragraph (h)

paragraph (d) paragraph (i)

Paragraph (c)(2)(i) of AD 2005-26-15 (paragraph (h)(2)(i) of this AD) specifies making repairs using a method approved by either the FAA or the DAC (or its delegated agent). As we previously explained, the ANAC has assumed responsibility for the airplane model[s] subject to this AD. Therefore, we have revised paragraph (h)(2)(i) of this AD to specify making repairs using a method approved by the FAA, the DAC (or its delegated agent), or the ANAC (or its delegated agent).

FAA's Justification and Determination of the Effective Date

Based on the service reports since the release of AD 2005-26-15, we have determined that a shorter compliance time for the terminating action is necessary to address the unsafe condition and to ensure long- term continued operational safety in this case to detect any discrepancy before it represents a hazard to the airplane. Because of our requirement to promote safe flight of civil aircraft, and thus the critical need to ensure the proper functioning of the elevator control system and the short compliance time involved with this action, this AD must be issued immediately.

Because an unsafe condition exists that requires the immediate adoption of this AD, we find that notice and opportunity for prior public comment hereon are impracticable and that good cause exists for making this amendment effective in less that 30 days.

Comments Invited

This AD is a final rule that involves requirements affecting flight safety, and we did not provide you with notice and an opportunity to provide your comments before it becomes effective. However, we invite you to send any written data, views, or arguments about this AD. Send your comments to an address listed under the ADDRESSES section. Include "Docket No. FAA-2008-0516; Directorate Identifier 2008-NM-026-AD" at the beginning of your comments. We specifically invite comments on the overall regulatory, economic, environmental, and energy aspects of this AD. We will consider all comments received by the closing date and may amend this AD because 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 about this AD.

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 AD will not have federalism implications under Executive Order 13132. This AD 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.

For the reasons discussed above, I certify that the 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 AD and placed it in the AD docket. 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, Incorporation by reference, Safety.

Adoption of the Amendment

Accordingly, under the authority delegated to me by the Administrator, the FAA 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:

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

Sec. 39.13 [Amended]

2. The Federal Aviation Administration (FAA) amends Sec. 39.13 by removing amendment 39-14436 (70 FR 77303, December 30, 2005) and adding the following new AD: