Airworthiness Directives; Gulfstream Model G-159 Airplanes, 70868-70870 [E6-20620]

Download as PDF 70868 Federal Register / Vol. 71, No. 235 / Thursday, December 7, 2006 / Rules and Regulations of this AD: Perform the initial inspection required by paragraph (i) of this AD within 1,000 landings after the effective date of this AD. Additional Inspections (k) For airplanes on which the inspections specified in paragraphs (f)(2), (f)(4), (h)(2), and (h)(4) of this AD are accomplished after the effective date of this AD: Where this AD requires an eddy current inspection for cracks, do a detailed inspection for corrosion at the same time as the eddy current inspection for cracks, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A300–53–0218, Revision 03, dated August 3, 2006. (l) For airplanes on which the inspections specified in paragraphs (f)(2) and (h)(2) of this AD are accomplished after the effective date of this AD: If any crack is found during any inspection required by paragraph (f)(2) or (h)(2), before further flight, do an X-ray inspection for cracking of the rim area of the rear pressure bulkhead in the area of STGR 21 LH and RH in accordance with the Accomplishment Instructions of Airbus Service Bulletin A300–53–0218, Revision 03, dated August 3, 2006. New Repetitive Inspections (m) For airplanes on which a repair has been done in accordance with Airbus Service Bulletin A300–53–218, Revision 1, dated July 28, 1989; Airbus Service Bulletin A300–53– 0218, Revision 02, dated May 10, 2005; or Revision 03, dated August 3, 2006; before the effective date of this AD: At the later of the times specified in paragraphs (m)(1) and (m)(2) of this AD, do the inspections specified in paragraphs (h), (k), and (l) of this AD. Repeat the inspections specified in paragraphs (h), (k), and (l) of this AD thereafter at the applicable times specified in paragraph (h) of this AD. (1) Within the times specified in paragraph (h) of this AD. (2) Within 2,000 landings after the effective date of this AD. Corrective Actions for Cracking and Corrosion and Repetitive Inspections (n) If cracking or corrosion is found during any inspection required by paragraph (f), (h), (k), (l) or (m) of this AD, repair prior to further flight, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A300–53–218, Revision 1, dated July 28, 1989; or Airbus Service Bulletin A300–53–0218, Revision 03, dated August 3, 2006. As of the effective date of this AD, do the repair in accordance with the Accomplishment Instructions of Airbus Service Bulletin A300–53–0218, Revision 03, dated August 3, 2006; except where the service bulletin specifies to contact the manufacturer to repair certain conditions, this AD requires repairing those conditions using a method approved by either the Manager, International Branch, ANM–116, Transport Airplane Directorate, FAA; or the European Aviation Safety Agency (EASA) (or its delegated agent). As of the effective date of this AD, repeat the inspections specified in paragraphs (h), (k), and (l) of this AD thereafter at the applicable times specified in paragraph (h) of this AD. Actions Accomplished According to Previous Issue of Service Bulletin (o) Actions accomplished before the effective date of this AD in accordance with Airbus Service Bulletin A300–53–0218, Revision 02, dated May 10, 2005, are considered acceptable for compliance with the corresponding actions specified in this AD. Alternative Methods of Compliance (AMOCs) (p)(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) Before using any AMOC approved in accordance with § 39.19 on any airplane to which the AMOC applies, notify the appropriate principal inspector in the FAA Flight Standards Certificate Holding District Office. (3) AMOCs approved previously in accordance with AD 90–03–08 are not approved as AMOCs with this AD. Related Information (q) French airworthiness directive F–2005– 093 R1, dated August 3, 2005, also addresses the subject of this AD. Material Incorporated by Reference (r) You must use Airbus Service Bulletin A300–53–218, Revision 1, dated July 28, 1989; and Airbus Service Bulletin A300–53– 0218, Revision 03, dated August 3, 2006; as applicable; to perform the actions that are required by this AD, unless the AD specifies otherwise. Airbus Service Bulletin A300–53– 218, Revision 1, dated July 28, 1989, contains the following effective pages: Page Nos. Revision level shown on page Date shown on page 1–4, 7, 8, 16, 19–25 ............................................................... 5, 6, 9–15, 17, 18 ................................................................... Revision 1 .............................................................................. Original ................................................................................... July 28, 1989. February 20, 1989. sroberts on PROD1PC70 with RULES The Director of the Federal Register approved the incorporation by reference of these documents in accordance with 5 U.S.C. 552(a) and 1 CFR part 51. Contact Airbus, 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex, France, for a copy of this service information. You may review copies at the Docket Management Facility, U.S. Department of Transportation, 400 Seventh Street, SW., Room PL–401, Nassif Building, Washington, DC; on the Internet at https:// dms.dot.gov; or at the National Archives and Records Administration (NARA). For information on the availability of this material at the NARA, call (202) 741–6030, or go to https://www.archives.gov/ federal_register/code_of_federal_regulations/ ibr_locations.html. Issued in Renton, Washington, on November 20, 2006. Ali Bahrami, Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. E6–20616 Filed 12–6–06; 8:45 am] BILLING CODE 4910–13–P VerDate Aug<31>2005 20:43 Dec 06, 2006 Jkt 211001 DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. 96–NM–143–AD; Amendment 39–14843; AD 2006–25–02] RIN 2120–AA64 Airworthiness Directives; Gulfstream Model G–159 Airplanes AGENCY: Federal Aviation Administration, DOT. ACTION: Final rule. SUMMARY: This amendment adopts a new airworthiness directive (AD), applicable to all Gulfstream Model G–159 airplanes, that requires repetitive non-destructive testing inspections to detect corrosion of the skin of certain structural assemblies, and corrective action if necessary. This AD also PO 00000 Frm 00014 Fmt 4700 Sfmt 4700 requires x-ray and ultrasonic inspections to detect corrosion and cracking of the splicing of certain structural assemblies, and repair if necessary. The actions specified by this AD are intended to detect and correct corrosion and cracking of the lower wing plank splices and spot-welded skins of certain structural assemblies, which could result in reduced controllability of the airplane. This action is intended to address the identified unsafe condition. DATES: Effective January 11, 2007. The incorporation by reference of a certain publication listed in the regulations is approved by the Director of the Federal Register as of January 11, 2007. ADDRESSES: The service information referenced in this AD may be obtained from Gulfstream Aerospace Corporation, Technical Publications Dept., P.O. Box 2206, Savannah, Georgia 31402–2206. E:\FR\FM\07DER1.SGM 07DER1 Federal Register / Vol. 71, No. 235 / Thursday, December 7, 2006 / Rules and Regulations This information may be examined at the Federal Aviation Administration (FAA), Transport Airplane Directorate, Rules Docket, 1601 Lind Avenue, SW., Renton, Washington; or at the FAA, Atlanta Aircraft Certification Office, One Crown Center, 1895 Phoenix Boulevard, Suite 450, Atlanta, Georgia. FOR FURTHER INFORMATION CONTACT: Michael Cann, Aerospace Engineer, Airframe Branch, ACE–117A, FAA, Atlanta Aircraft Certification Office, One Crown Center, 1895 Phoenix Boulevard, suite 450, Atlanta, Georgia 30349; telephone (770) 703–6038; fax (770) 703–6097. SUPPLEMENTARY INFORMATION: A proposal to amend part 39 of the Federal Aviation Regulations (14 CFR part 39) to include an airworthiness directive (AD) that is applicable to all Gulfstream Model G–159 airplanes was published as a second supplemental notice of proposed rulemaking (NPRM) in the Federal Register on July 12, 2006 (71 FR 39242). That action proposed to require repetitive non-destructive testing inspections to detect corrosion of the skin of certain structural assemblies, and corrective action if necessary. That action also proposed to require x-ray and ultrasonic inspections to detect corrosion and cracking of the splicing of certain structural assemblies, and repair if necessary. Interested persons have been afforded an opportunity to participate in the making of this amendment. Due consideration has been given to the comments received. sroberts on PROD1PC70 with RULES Request To Incorporate by Reference Service Information One commenter, the Modification and Replacement Parts Association (MARPA), requests that service documents deemed essential to the accomplishment of the proposed action be incorporated by reference into the regulatory instrument. The commenter states that once a service document is incorporated by reference into a public document such as an airworthiness directive (AD), it loses its private, protected status and becomes itself a public document. The commenter also states that there is concern that failure to incorporate essential service information could result in a court decision invalidating the AD. We do not agree that documents should be incorporated by reference during the NPRM phase of rulemaking. The Office of the Federal Register requires that documents that are necessary to accomplish the requirements of the AD be incorporated by reference during the final rule phase VerDate Aug<31>2005 20:43 Dec 06, 2006 Jkt 211001 of rulemaking. This final rule incorporates by reference the document necessary for the accomplishment of the requirements mandated by this AD. Further, we point out that while documents that are incorporated by reference do become public information, they do not lose their copyright protection. For that reason, we advise the public to contact the manufacturer to obtain copies of the referenced service information. No change is necessary to the AD in this regard. Request To Publish Appropriate Service Information The same commenter, MARPA, also requests that service information necessary to accomplish actions specified in ADs be published in the Docket Management System (DMS). We are currently in the process of reviewing issues surrounding the posting of service bulletins on the Department of Transportation’s DMS as part of an AD docket. Once we have thoroughly examined all aspects of this issue and have made a final determination, we will consider whether our current practice needs to be revised. No change is necessary to the AD in this regard. Conclusion We have carefully reviewed the available data, including the comments received, and determined that air safety and the public interest require adopting the AD as proposed in the second supplemental NPRM. Cost Impact There are approximately 52 airplanes of the affected design in the worldwide fleet. The FAA estimates that 25 airplanes of U.S. registry will be affected by this AD, that it will take approximately between 300 and 450 work hours per airplane, depending upon how many spot-welded skins have been replaced with bonded skin panels, to accomplish the required actions, and that the average labor rate is $80 per work hour. Based on these figures, the cost impact of this AD on U.S. operators is estimated to be between $600,000 and $900,000, or between $24,000 and $36,000 per airplane, per inspection cycle. The cost impact figures discussed above are based on assumptions that no operator has yet accomplished any of the proposed requirements of this AD action, and that no operator would accomplish those actions in the future if this AD were not adopted. The cost impact figures discussed in AD rulemaking actions represent only the time necessary to perform the specific PO 00000 Frm 00015 Fmt 4700 Sfmt 4700 70869 actions actually required by the AD. These figures typically do not include incidental costs, such as the time required to gain access and close up, planning time, or time necessitated by other administrative actions. Regulatory Impact The regulations adopted herein will not have a substantial direct effect on the States, on the relationship between the national Government and the States, or on the distribution of power and responsibilities among the various levels of government. Therefore, it is determined that this final rule does not have federalism implications under Executive Order 13132. For the reasons discussed above, I certify that this action (1) Is not a ‘‘significant regulatory action’’ under Executive Order 12866; (2) is not a ‘‘significant rule’’ under DOT Regulatory Policies and Procedures (44 FR 11034, February 26, 1979); and (3) will not have a significant economic impact, positive or negative, on a substantial number of small entities under the criteria of the Regulatory Flexibility Act. A final evaluation has been prepared for this action and it is contained in the Rules Docket. A copy of it may be obtained from the Rules Docket at the location provided under the caption ADDRESSES. List of Subjects in 14 CFR Part 39 Air transportation, Aircraft, Aviation safety, Incorporation by reference, Safety. Adoption of the Amendment Accordingly, pursuant to the authority delegated to me by the Administrator, the Federal Aviation Administration amends part 39 of the Federal Aviation Regulations (14 CFR part 39) as follows: n PART 39—AIRWORTHINESS DIRECTIVES 1. The authority citation for part 39 continues to read as follows: n Authority: 49 U.S.C. 106(g), 40113, 44701. § 39.13 [Amended] 2. Section 39.13 is amended by adding the following new airworthiness directive: n 2006–25–02 Gulfstream Aerospace Corporation: Amendment 39–14843. Docket 96–NM–143–AD. Applicability: All Model G–159 airplanes, certificated in any category. Compliance: Required as indicated, unless accomplished previously. To detect and correct corrosion and cracking of the lower wing plank splices and spot-welded skins of certain structural E:\FR\FM\07DER1.SGM 07DER1 70870 Federal Register / Vol. 71, No. 235 / Thursday, December 7, 2006 / Rules and Regulations assemblies, which could result in reduced controllability of the airplane, accomplish the following: Note 1: A note in the Accomplishment Instructions of the Gulfstream customer bulletin instructs operators to contact Gulfstream if any difficulty is encountered in accomplishing the customer bulletin. However, any deviation from the instructions provided in the customer bulletin must be approved as an alternative method of compliance (AMOC) under paragraph (h) of this AD. Non-Destructive Testing Inspections of the Fuselage, Empennage, and Flight Controls (a) Within 9 months after the effective date of this AD, perform a non-destructive test (NDT) to detect corrosion of the skins of the elevators, ailerons, rudder and rudder trim tab, flaps, aft lower fuselage, and vertical and horizontal stabilizers; in accordance with the Accomplishment Instructions of Gulfstream GI Customer Bulletin (CB) 337B, including Appendix A, dated August 17, 2005. The corrosion criteria must be determined by the Manager, Atlanta Aircraft Certification Office (ACO), FAA. Gulfstream Tool ST905–377 is also an acceptable method of determining the corrosion criteria. (1) If no corrosion or cracking is detected, repeat the inspection thereafter at intervals not to exceed 18 months. (2) If any corrosion is detected that meets the criteria of ‘‘light’’ or ‘‘mild’’ corrosion, repeat the NDT inspections of that component thereafter at intervals not to exceed 12 months. (3) If any corrosion is detected that meets the criteria of ‘‘moderate’’ corrosion: Within 9 months after the initial inspection, repeat the NDT inspection of that component, and within 18 months since the initial inspection, repair or replace the component with a serviceable component in accordance with the CB. (4) If any corrosion is detected that meets the criteria of ‘‘severe’’ corrosion, before further flight, replace the component with a serviceable component in accordance with the CB. Existing Repairs (b) If any existing repairs are found during the inspections required by paragraph (a) of this AD, before further flight, ensure that the repairs are in accordance with a method approved by the Manager, Atlanta ACO. sroberts on PROD1PC70 with RULES Inspections of the Lower Wing Plank (c) Except as provided in paragraph (f) of this AD: Within 9 months after the effective date of this AD, perform NDT inspections to detect corrosion and cracking of the lower wing plank splices, in accordance with the Accomplishment Instructions of Gulfstream GI CB 337B, including Appendix A, dated August 17, 2005. (1) If no corrosion or cracking is detected, repeat the NDT inspection at intervals not to exceed 18 months. (2) If any corrosion or cracking is detected, before further flight, perform all applicable investigative actions and corrective actions in accordance with the customer bulletin. VerDate Aug<31>2005 20:43 Dec 06, 2006 Jkt 211001 Repair Removal Threshold (d) For repairs specified in Appendix A of Gulfstream GI CB 337B, dated August 17, 2005: Within 144 months after the date of the repair installation, remove the repaired component and replace it with a new or serviceable component, in accordance with Gulfstream GI CB 337B, including Appendix A, dated August 17, 2005. Prior Blending in the Riser Areas (e) If, during the performance of the inspections required by paragraph (c) or (f) of this AD, the inspection reveals that prior blending has been performed on the riser areas: Before further flight, perform an eddy current or fluorescent penetrant inspection, as applicable, to evaluate the blending, and accomplish appropriate corrective actions, in accordance with the Accomplishment Instructions of Gulfstream GI CB 337B, including Appendix A, dated August 17, 2005. If any blend-out is outside the limits specified in the CB, before further flight, repair in a manner approved by the Manager, Atlanta ACO. For Airplanes with New Lower Wing Planks (f) For airplanes with new lower wing planks: Within 144 months after replacement of the lower wing planks with new lower wing planks, or within 9 months after the effective date of this AD, whichever occurs later, perform all of the actions, including all related investigative actions and corrective actions, specified in paragraph (c) of this AD. Reporting Requirement (g) Within 30 days of performing the inspections required by this AD: Submit a report of inspection findings (both positive and negative) to Gulfstream Aerospace Corporation; Attention: Technical Operations—Structures Group, Dept. 893, Mail Station D–25, 500 Gulfstream Road, Savannah, Georgia 31408. Information collection requirements contained in this regulation have been approved by the Office of Management and Budget (OMB) under the provisions of the Paperwork Reduction Act (44 U.S.C. 3501 et seq.) and have been assigned OMB Control Number 2120–0056. Alternative Methods of Compliance (h)(1) The Manager, Atlanta ACO, has the authority to approve AMOCs for this AD, if requested in accordance with the procedures found in 14 CFR 39.19. (2) Before using any AMOC approved in accordance with § 39.19 on any airplane to which the AMOC applies, notify the appropriate principal inspector in the FAA Flight Standards Certificate Holding District Office. Incorporation by Reference (i) Unless otherwise specified in this AD, the actions must be done in accordance with Gulfstream GI Customer Bulletin 337B, including Appendix A, dated August 17, 2005. This incorporation by reference was approved by the Director of the Federal Register in accordance with 5 U.S.C. 552(a) and 1 CFR part 51. To get copies of this service information, contact Gulfstream Aerospace Corporation, Technical PO 00000 Frm 00016 Fmt 4700 Sfmt 4700 Publications Dept., P.O. Box 2206, Savannah, Georgia 31402–2206. To inspect copies of this service information, go to the FAA, Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton, Washington; to FAA, Atlanta Aircraft Certification Office, One Crown Center, 1895 Phoenix Boulevard, suite 450, Atlanta, Georgia; or to the National Archives and Records Administration (NARA). For information on the availability of this material at the NARA, call (202) 741– 6030, or go to https://www.archives.gov/ federal_register/code_of_federal_regulations/ ibr_locations.html. Effective Date (j) This amendment becomes effective on January 11, 2007. Issued in Renton, Washington, on November 20, 2006. Ali Bahrami, Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. E6–20620 Filed 12–6–06; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF HEALTH AND HUMAN SERVICES Food and Drug Administration 21 CFR Part 2 [Docket No. 2006N–0416] RIN 0910–AF93 Use of Ozone-Depleting Substances; Removal of Essential Use Designations AGENCY: Food and Drug Administration, HHS. ACTION: Direct final rule. SUMMARY: The Food and Drug Administration (FDA) is amending its regulation on the use of ozone-depleting substances (ODSs) in pressurized containers to remove the essential use designations for beclomethasone, dexamethasone, fluticasone, bitolterol, salmeterol, ergotamine tartrate, and ipratropium bromide used in oral pressurized metered-dose inhalers (MDIs). Under the Clean Air Act, FDA, in consultation with the Environmental Protection Agency (EPA), is required to determine whether an FDA-regulated product that releases an ODS is essential. None of these products is currently being marketed, which provides grounds for removing their essential use designation. We are using direct final rulemaking for this action because the agency expects that there will be no significant adverse comment on the rule. In the proposed rule section in this issue of the Federal Register, we are concurrently proposing and soliciting comments on this rule. If E:\FR\FM\07DER1.SGM 07DER1

Agencies

[Federal Register Volume 71, Number 235 (Thursday, December 7, 2006)]
[Rules and Regulations]
[Pages 70868-70870]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: E6-20620]


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

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 96-NM-143-AD; Amendment 39-14843; AD 2006-25-02]
RIN 2120-AA64


Airworthiness Directives; Gulfstream Model G-159 Airplanes

AGENCY: Federal Aviation Administration, DOT.

ACTION: Final rule.

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

SUMMARY: This amendment adopts a new airworthiness directive (AD), 
applicable to all Gulfstream Model G-159 airplanes, that requires 
repetitive non-destructive testing inspections to detect corrosion of 
the skin of certain structural assemblies, and corrective action if 
necessary. This AD also requires x-ray and ultrasonic inspections to 
detect corrosion and cracking of the splicing of certain structural 
assemblies, and repair if necessary. The actions specified by this AD 
are intended to detect and correct corrosion and cracking of the lower 
wing plank splices and spot-welded skins of certain structural 
assemblies, which could result in reduced controllability of the 
airplane. This action is intended to address the identified unsafe 
condition.

DATES: Effective January 11, 2007.
    The incorporation by reference of a certain publication listed in 
the regulations is approved by the Director of the Federal Register as 
of January 11, 2007.

ADDRESSES: The service information referenced in this AD may be 
obtained from Gulfstream Aerospace Corporation, Technical Publications 
Dept., P.O. Box 2206, Savannah, Georgia 31402-2206.

[[Page 70869]]

This information may be examined at the Federal Aviation Administration 
(FAA), Transport Airplane Directorate, Rules Docket, 1601 Lind Avenue, 
SW., Renton, Washington; or at the FAA, Atlanta Aircraft Certification 
Office, One Crown Center, 1895 Phoenix Boulevard, Suite 450, Atlanta, 
Georgia.

FOR FURTHER INFORMATION CONTACT: Michael Cann, Aerospace Engineer, 
Airframe Branch, ACE-117A, FAA, Atlanta Aircraft Certification Office, 
One Crown Center, 1895 Phoenix Boulevard, suite 450, Atlanta, Georgia 
30349; telephone (770) 703-6038; fax (770) 703-6097.

SUPPLEMENTARY INFORMATION: A proposal to amend part 39 of the Federal 
Aviation Regulations (14 CFR part 39) to include an airworthiness 
directive (AD) that is applicable to all Gulfstream Model G-159 
airplanes was published as a second supplemental notice of proposed 
rulemaking (NPRM) in the Federal Register on July 12, 2006 (71 FR 
39242). That action proposed to require repetitive non-destructive 
testing inspections to detect corrosion of the skin of certain 
structural assemblies, and corrective action if necessary. That action 
also proposed to require x-ray and ultrasonic inspections to detect 
corrosion and cracking of the splicing of certain structural 
assemblies, and repair if necessary.
    Interested persons have been afforded an opportunity to participate 
in the making of this amendment. Due consideration has been given to 
the comments received.

Request To Incorporate by Reference Service Information

    One commenter, the Modification and Replacement Parts Association 
(MARPA), requests that service documents deemed essential to the 
accomplishment of the proposed action be incorporated by reference into 
the regulatory instrument. The commenter states that once a service 
document is incorporated by reference into a public document such as an 
airworthiness directive (AD), it loses its private, protected status 
and becomes itself a public document. The commenter also states that 
there is concern that failure to incorporate essential service 
information could result in a court decision invalidating the AD.
    We do not agree that documents should be incorporated by reference 
during the NPRM phase of rulemaking. The Office of the Federal Register 
requires that documents that are necessary to accomplish the 
requirements of the AD be incorporated by reference during the final 
rule phase of rulemaking. This final rule incorporates by reference the 
document necessary for the accomplishment of the requirements mandated 
by this AD. Further, we point out that while documents that are 
incorporated by reference do become public information, they do not 
lose their copyright protection. For that reason, we advise the public 
to contact the manufacturer to obtain copies of the referenced service 
information. No change is necessary to the AD in this regard.

Request To Publish Appropriate Service Information

    The same commenter, MARPA, also requests that service information 
necessary to accomplish actions specified in ADs be published in the 
Docket Management System (DMS).
    We are currently in the process of reviewing issues surrounding the 
posting of service bulletins on the Department of Transportation's DMS 
as part of an AD docket. Once we have thoroughly examined all aspects 
of this issue and have made a final determination, we will consider 
whether our current practice needs to be revised. No change is 
necessary to the AD in this regard.

Conclusion

    We have carefully reviewed the available data, including the 
comments received, and determined that air safety and the public 
interest require adopting the AD as proposed in the second supplemental 
NPRM.

Cost Impact

    There are approximately 52 airplanes of the affected design in the 
worldwide fleet. The FAA estimates that 25 airplanes of U.S. registry 
will be affected by this AD, that it will take approximately between 
300 and 450 work hours per airplane, depending upon how many spot-
welded skins have been replaced with bonded skin panels, to accomplish 
the required actions, and that the average labor rate is $80 per work 
hour. Based on these figures, the cost impact of this AD on U.S. 
operators is estimated to be between $600,000 and $900,000, or between 
$24,000 and $36,000 per airplane, per inspection cycle.
    The cost impact figures discussed above are based on assumptions 
that no operator has yet accomplished any of the proposed requirements 
of this AD action, and that no operator would accomplish those actions 
in the future if this AD were not adopted. The cost impact figures 
discussed in AD rulemaking actions represent only the time necessary to 
perform the specific actions actually required by the AD. These figures 
typically do not include incidental costs, such as the time required to 
gain access and close up, planning time, or time necessitated by other 
administrative actions.

Regulatory Impact

    The regulations adopted herein will not have a substantial direct 
effect on the States, on the relationship between the national 
Government and the States, or on the distribution of power and 
responsibilities among the various levels of government. Therefore, it 
is determined that this final rule does not have federalism 
implications under Executive Order 13132.
    For the reasons discussed above, I certify that this action (1) Is 
not a ``significant regulatory action'' under Executive Order 12866; 
(2) is not a ``significant rule'' under DOT Regulatory Policies and 
Procedures (44 FR 11034, February 26, 1979); and (3) will not have a 
significant economic impact, positive or negative, on a substantial 
number of small entities under the criteria of the Regulatory 
Flexibility Act. A final evaluation has been prepared for this action 
and it is contained in the Rules Docket. A copy of it may be obtained 
from the Rules Docket at the location provided under the caption 
ADDRESSES.

List of Subjects in 14 CFR Part 39

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

Adoption of the Amendment

0
Accordingly, pursuant to the authority delegated to me by the 
Administrator, the Federal Aviation Administration amends part 39 of 
the Federal Aviation Regulations (14 CFR part 39) as follows:

PART 39--AIRWORTHINESS DIRECTIVES

0
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]

0
2. Section 39.13 is amended by adding the following new airworthiness 
directive:

2006-25-02 Gulfstream Aerospace Corporation: Amendment 39-14843. 
Docket 96-NM-143-AD.

    Applicability: All Model G-159 airplanes, certificated in any 
category.
    Compliance: Required as indicated, unless accomplished 
previously.
    To detect and correct corrosion and cracking of the lower wing 
plank splices and spot-welded skins of certain structural

[[Page 70870]]

assemblies, which could result in reduced controllability of the 
airplane, accomplish the following:

    Note 1: A note in the Accomplishment Instructions of the 
Gulfstream customer bulletin instructs operators to contact 
Gulfstream if any difficulty is encountered in accomplishing the 
customer bulletin. However, any deviation from the instructions 
provided in the customer bulletin must be approved as an alternative 
method of compliance (AMOC) under paragraph (h) of this AD.

Non-Destructive Testing Inspections of the Fuselage, Empennage, and 
Flight Controls

    (a) Within 9 months after the effective date of this AD, perform 
a non-destructive test (NDT) to detect corrosion of the skins of the 
elevators, ailerons, rudder and rudder trim tab, flaps, aft lower 
fuselage, and vertical and horizontal stabilizers; in accordance 
with the Accomplishment Instructions of Gulfstream GI Customer 
Bulletin (CB) 337B, including Appendix A, dated August 17, 2005. The 
corrosion criteria must be determined by the Manager, Atlanta 
Aircraft Certification Office (ACO), FAA. Gulfstream Tool ST905-377 
is also an acceptable method of determining the corrosion criteria.
    (1) If no corrosion or cracking is detected, repeat the 
inspection thereafter at intervals not to exceed 18 months.
    (2) If any corrosion is detected that meets the criteria of 
``light'' or ``mild'' corrosion, repeat the NDT inspections of that 
component thereafter at intervals not to exceed 12 months.
    (3) If any corrosion is detected that meets the criteria of 
``moderate'' corrosion: Within 9 months after the initial 
inspection, repeat the NDT inspection of that component, and within 
18 months since the initial inspection, repair or replace the 
component with a serviceable component in accordance with the CB.
    (4) If any corrosion is detected that meets the criteria of 
``severe'' corrosion, before further flight, replace the component 
with a serviceable component in accordance with the CB.

Existing Repairs

    (b) If any existing repairs are found during the inspections 
required by paragraph (a) of this AD, before further flight, ensure 
that the repairs are in accordance with a method approved by the 
Manager, Atlanta ACO.

Inspections of the Lower Wing Plank

    (c) Except as provided in paragraph (f) of this AD: Within 9 
months after the effective date of this AD, perform NDT inspections 
to detect corrosion and cracking of the lower wing plank splices, in 
accordance with the Accomplishment Instructions of Gulfstream GI CB 
337B, including Appendix A, dated August 17, 2005.
    (1) If no corrosion or cracking is detected, repeat the NDT 
inspection at intervals not to exceed 18 months.
    (2) If any corrosion or cracking is detected, before further 
flight, perform all applicable investigative actions and corrective 
actions in accordance with the customer bulletin.

Repair Removal Threshold

    (d) For repairs specified in Appendix A of Gulfstream GI CB 
337B, dated August 17, 2005: Within 144 months after the date of the 
repair installation, remove the repaired component and replace it 
with a new or serviceable component, in accordance with Gulfstream 
GI CB 337B, including Appendix A, dated August 17, 2005.

Prior Blending in the Riser Areas

    (e) If, during the performance of the inspections required by 
paragraph (c) or (f) of this AD, the inspection reveals that prior 
blending has been performed on the riser areas: Before further 
flight, perform an eddy current or fluorescent penetrant inspection, 
as applicable, to evaluate the blending, and accomplish appropriate 
corrective actions, in accordance with the Accomplishment 
Instructions of Gulfstream GI CB 337B, including Appendix A, dated 
August 17, 2005. If any blend-out is outside the limits specified in 
the CB, before further flight, repair in a manner approved by the 
Manager, Atlanta ACO.

For Airplanes with New Lower Wing Planks

    (f) For airplanes with new lower wing planks: Within 144 months 
after replacement of the lower wing planks with new lower wing 
planks, or within 9 months after the effective date of this AD, 
whichever occurs later, perform all of the actions, including all 
related investigative actions and corrective actions, specified in 
paragraph (c) of this AD.

Reporting Requirement

    (g) Within 30 days of performing the inspections required by 
this AD: Submit a report of inspection findings (both positive and 
negative) to Gulfstream Aerospace Corporation; Attention: Technical 
Operations--Structures Group, Dept. 893, Mail Station D-25, 500 
Gulfstream Road, Savannah, Georgia 31408. Information collection 
requirements contained in this regulation have been approved by the 
Office of Management and Budget (OMB) under the provisions of the 
Paperwork Reduction Act (44 U.S.C. 3501 et seq.) and have been 
assigned OMB Control Number 2120-0056.

Alternative Methods of Compliance

    (h)(1) The Manager, Atlanta ACO, has the authority to approve 
AMOCs for this AD, if requested in accordance with the procedures 
found in 14 CFR 39.19.
    (2) Before using any AMOC approved in accordance with Sec.  
39.19 on any airplane to which the AMOC applies, notify the 
appropriate principal inspector in the FAA Flight Standards 
Certificate Holding District Office.

Incorporation by Reference

    (i) Unless otherwise specified in this AD, the actions must be 
done in accordance with Gulfstream GI Customer Bulletin 337B, 
including Appendix A, dated August 17, 2005. This incorporation by 
reference was approved by the Director of the Federal Register in 
accordance with 5 U.S.C. 552(a) and 1 CFR part 51. To get copies of 
this service information, contact Gulfstream Aerospace Corporation, 
Technical Publications Dept., P.O. Box 2206, Savannah, Georgia 
31402-2206. To inspect copies of this service information, go to the 
FAA, Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton, 
Washington; to FAA, Atlanta Aircraft Certification Office, One Crown 
Center, 1895 Phoenix Boulevard, suite 450, Atlanta, Georgia; or to 
the National Archives and Records Administration (NARA). For 
information on the availability of this material at the NARA, call 
(202) 741-6030, or go to https://www.archives.gov/federal_register/
code_of_federal_regulations/ibr_locations.html.

Effective Date

    (j) This amendment becomes effective on January 11, 2007.

    Issued in Renton, Washington, on November 20, 2006.
Ali Bahrami,
Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
 [FR Doc. E6-20620 Filed 12-6-06; 8:45 am]
BILLING CODE 4910-13-P