Airworthiness Directives; Sicma Aero Seat; Third Occupant Seat Assemblies, 133 Series, 75411-75413 [E6-21186]

Download as PDF Federal Register / Vol. 71, No. 241 / Friday, December 15, 2006 / Rules and Regulations Effective Date (a) This AD becomes effective January 19, 2007. Affected ADs (b) None. Applicability (c) This AD applies Bombardier Model DHC–8–400, DHC–8–401, and DHC–8–402 airplanes, certificated in any category; serial numbers 4001 and 4003 and subsequent. Unsafe Condition (d) This AD results from reports of incidents of airspeed mismatch between the pilot, co-pilot, and standby airspeed indications caused by contamination in the pitot static system. We are issuing this AD to prevent erroneous/misleading altitude and airspeed information from a contaminated pitot static system to the flightcrew, which could reduce the ability of the flightcrew to maintain the safe flight and landing of the airplane. cprice-sewell on PROD1PC66 with RULES 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. Initial and Repetitive Cleaning and Inspection of the Pitot Static Drain Holes (f) Within 30 days after the effective date of this AD, do paragraphs (f)(1) and (f)(2) of this AD. Thereafter, repeat the actions in paragraphs (f)(1) and (f)(2) of this AD at intervals not to exceed 70 flight hours. (1) Clean the drain holes of all the pitot static probes in accordance with a method approved by the Manager, New York Aircraft Certification Office (ACO), FAA. Paragraph 4.B., Procedure 2, subparagraphs (1) through (3) of Bombardier Task 20–00–40–170–801 in the Bombardier Dash 8 Q400 Aircraft Maintenance Manual (AMM), PSM 1–84–2, Part 2, is one approved method for accomplishing the requirements of this paragraph. (2) Before further flight after cleaning the drain holes of the pitot static probes, as specified in paragraph (f)(1) of this AD, do a general visual inspection of the drain holes of all the pitot static probes for blockages, in accordance with a method approved by the Manager, New York ACO. Paragraph 4.A., Procedure 1, of Bombardier Task 20–00–40– 170–801 in the Bombardier Dash 8 Q400 AMM, PSM 1–84–2, Part 2, is one approved method for accomplishing the requirements of this paragraph. Note 1: For the purposes of this AD, a general visual inspection is: ‘‘A visual examination of an interior or exterior area, installation, or assembly to detect obvious damage, failure, or irregularity. This level of inspection is made from within touching distance unless otherwise specified. A mirror may be necessary to ensure visual access to all surfaces in the inspection area. This level of inspection is made under normally available lighting conditions such as daylight, hangar lighting, flashlight, or droplight and may require removal or opening of access panels or doors. Stands, VerDate Aug<31>2005 14:57 Dec 14, 2006 Jkt 211001 ladders, or platforms may be required to gain proximity to the area being checked.’’ (g) If any blockage is found in the drain hole of any pitot static probe during the inspection required in paragraph (f)(2) of this AD, before further flight, repeat the cleaning and inspection specified in paragraphs (f)(1) and (f)(2) of this AD on the affected pitot static probe. Cleaning of the Pitot Static Lines (h) Within 30 days after the effective date of this AD, clean the pitot lines of the pitot static system in accordance with a method approved by the Manager, New York ACO. Bombardier Task 34–11–00–170–801 in the Bombardier Dash 8 Q400 AMM, PSM 1–84– 2, Part 2, is one approved method for accomplishing the actions required by this paragraph. Thereafter, repeat the cleaning of the pitot lines at intervals not to exceed 600 flight hours. Alternative Methods of Compliance (AMOCs) (i)(1) The Manager, New York 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. Related Information (j) Canadian airworthiness directive CF– 2005–15, dated May 18, 2005, also addresses the subject of this AD. Material Incorporated by Reference (k) None. Issued in Renton, Washington, on December 7, 2006. Michael J. Kaszycki, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. E6–21267 Filed 12–14–06; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2005–22959; Directorate Identifier 2005–NE–40–AD; Amendment 39– 14856; AD 2006–25–15] RIN 2120–AA64 Airworthiness Directives; Sicma Aero Seat; Third Occupant Seat Assemblies, 133 Series Federal Aviation Administration (FAA), Department of Transportation (DOT). ACTION: Final rule. AGENCY: SUMMARY: The FAA is adopting a new airworthiness directive (AD) for Sicma PO 00000 Frm 00005 Fmt 4700 Sfmt 4700 75411 Aero Seat third occupant seat assemblies, 133 series. This AD requires visually inspecting the installation of the two headrest bushings and installing Mecanindus pins to secure the bushings. This AD results from Sicma’s determination that missing or incorrectly secured bushings could loosen and cause disengagement of the headrest from the seat during a highenergy stop of the airplane, possibly injuring the seat occupant. We are issuing this AD to prevent disengagement of the headrest from the seat during a high-energy stop of the airplane that could injure the seat occupant. DATES: This AD becomes effective January 19, 2007. The Director of the Federal Register approved the incorporation by reference of certain publications listed in the regulations as of January 19, 2007. ADDRESSES: You can get the service information identified in this AD from Sicma Aero Seat, 7 Rue Lucien Coupet, 36100 Issoudun, France, telephone: (33) 54 03 39 39; fax: (33) 54 03 15 16. You may examine the AD docket on the Internet at https://dms.dot.gov or in Room PL–401 on the plaza level of the Nassif Building, 400 Seventh Street, SW., Washington, DC. FOR FURTHER INFORMATION CONTACT: Jeffrey Lee, Aerospace Engineer, Boston Aircraft Certification Office, FAA, Engine and Propeller Directorate, FAA, 12 New England Executive Park, Burlington, MA 01803; telephone (781) 238–7161; fax (781) 238–7170. SUPPLEMENTARY INFORMATION: The FAA proposed to amend 14 CFR part 39 with a proposed AD. The proposed AD applies to Sicma Aero Seat third occupant seat assemblies, 133 series. We published the proposed AD in the Federal Register on March 1, 2006 (71 FR 10453). That action proposed to require visually inspecting the installation of the two headrest bushings and installing Mecanindus pins to secure the bushings. Examining the AD Docket You may examine the docket that contains the AD, any comments received, and any final disposition in person at the Docket Management Facility Docket Office between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. The Docket Office (telephone (800) 647–5227) is located on the plaza level of the Department of Transportation Nassif Building at the street address stated in ADDRESSES. Comments will be available in the AD docket shortly after the DMS receives them. E:\FR\FM\15DER1.SGM 15DER1 75412 Federal Register / Vol. 71, No. 241 / Friday, December 15, 2006 / Rules and Regulations Comments We provided the public the opportunity to participate in the development of this AD. We have considered the comments received. economic burden on any operator nor increase the scope of the AD. Costs of Compliance Request To Change Compliance Requirement Air Transport Association and Northwest Airlines request that the compliance requirement of ‘‘within 30 days’’ be changed to ‘‘within 90 days’’. This will allow AD compliance in conjunction with operators’ current ACheck interval. We agree and changed the AD to ‘‘within 90 days’’. Labor Time Information Does Not Match the Sicma Aero Seat Service Bulletin Air Transport Association and Northwest Airlines state that the estimated labor time information in the proposed AD does not match the manpower estimate in Sicma Aero Seat Service Bulletin (SB) No. 133–25–006, dated May 12, 1999. We agree that the AD estimate for doing the work needs to match the SB. We changed the labor time in the AD to 0.17 work-hour (10 minutes) per seat. Seat Part Numbers Do Not Match Air Transport Association and Northwest Airlines state that the seat part numbers (P/Ns) in the proposed AD do not match those in Sicma Aero Seat SB No. 133–25–006, dated May 12, 1999. We partially agree. We corrected the P/Ns to 1330622–070, 1330622– 070–1, 1330622–070–2, 1330622–100, and 1330622V100–1 in the AD. These are the same listed P/Ns affected as those identified by the Direction Generale de L’Aviation Civile, which is the airworthiness authority of France. Question on Serial Numbers Air Transport Association and Northwest Airlines question why the serial numbers (SNs) in the proposed AD are specific, whereas there are no specific SNs listed in the SB. We listed the same SNs as those identified by the Direction Generale de L’Aviation Civile, which is the airworthiness authority for France. They correctly identified the SNs affected, in their AD No. 2000– 042(AB). We did not change the AD. cprice-sewell on PROD1PC66 with RULES 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 with the changes described previously. We have determined that these changes will neither increase the VerDate Aug<31>2005 14:57 Dec 14, 2006 Jkt 211001 There are about 459 Sicma Aero Seat third occupant seat assemblies, 133 series, of the affected design installed on airplanes of U.S. registry. There are about 698 airplanes of U.S. registry that these seats can be installed on. We estimate that it will take about 0.17 work-hour per seat assembly to perform the actions, and that the average labor rate is $65 per work-hour. The Mecanindus pins cost $99.88 each, however, Sicma Aero Seat has advised us that they will supply the parts at no cost. Based on the labor rate to install the parts, the total cost of the AD to U.S. operators will be about $5,072. 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. We prepared a summary of the costs to comply with this AD and placed it in the AD Docket. You may get a copy of this summary at the address listed under ADDRESSES. 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 Federal Aviation Administration amends 14 CFR part 39 as follows: I PART 39—AIRWORTHINESS DIRECTIVES 1. The authority citation for part 39 continues to read as follows: I Authority: 49 U.S.C. 106(g), 40113, 44701. § 39.13 2. The FAA amends § 39.13 by adding the following new airworthiness directive: I 2006–25–15 Sicma Aero Seat: Amendment 39–14856. Docket No. FAA–2005–22959; Directorate Identifier 2005–NE–40–AD. Effective Date (a) This airworthiness directive (AD) becomes effective January 19, 2007. Affected ADs (b) None. Applicability (c) This AD applies to Sicma Aero Seat third occupant seat assemblies, 133 series, with the part numbers (P/Ns) and serial numbers (SNs) in the following Table 1: TABLE 1.—APPLICABLE SEAT ASSEMBLIES 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 this AD: (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. PO 00000 Frm 00006 Fmt 4700 Sfmt 4700 [Amended] Seat P/N 1330622–070 ....................... 1330622–070–1 ................... 1330622–070–2 ................... 1330622–100 ....................... 1330622V100–1 ................... Seat SN 1 1 1 1 1 through through through through through 212. 212. 6. 13. 16. These third occupant seats are installed on, but not limited to, Airbus A319, A320, and A321 series airplanes. Unsafe Condition (d) This AD results from Sicma’s determination that missing or incorrectly secured bushings could loosen and cause disengagement of the headrest from the seat during a high-energy stop of the airplane, possibly injuring the seat occupant. We are issuing this AD to prevent disengagement of the headrest from the seat during a highenergy stop of the airplane that could injure the seat occupant. E:\FR\FM\15DER1.SGM 15DER1 Federal Register / Vol. 71, No. 241 / Friday, December 15, 2006 / Rules and Regulations Compliance DEPARTMENT OF TRANSPORTATION (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. Installing Protective Fairings (f) Within 90 days after the effective date of this AD, visually check the installation of the two headrest bushings and install Mecanindus pins, P/N GPMECAE2–5x5, to secure the bushings. Use the instructions in paragraph 2 of Sicma Aero Seat Service Bulletin No. 133–25–006, dated May 12, 1999, to perform the visual inspection and install the pins. Alternative Methods of Compliance (g) The Manager, Boston Aircraft Certification Office, has the authority to approve alternative methods of compliance for this AD if requested using the procedures found in 14 CFR 39.19. Related Information (h) Direction Generale de L’Aviation Civile airworthiness directive 2000–042(AB), dated January 26, 2000, also addresses the subject of this AD. Material Incorporated by Reference (i) You must use Sicma Aero Seat Service Bulletin No. 133–25–006, dated May 12, 1999, to perform the actions required by this AD. The Director of the Federal Register approved the incorporation by reference of this service bulletin in accordance with 5 U.S.C. 552(a) and 1 CFR part 51. Contact Sicma Aero Seat, 7 Rue Lucien Coupet, 36100 Issoudun, France, telephone: (33) 54 03 39 39; fax: (33) 54 03 15 16, for a copy of this service information. You may review copies 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: https:// www.archives.gov/federal-register/cfr/ibrlocations.html. Issued in Burlington, Massachusetts, on December 7, 2006. Robert J. Ganley, Acting Manager, Engine and Propeller Directorate, Aircraft Certification Service. [FR Doc. E6–21186 Filed 12–14–06; 8:45 am] cprice-sewell on PROD1PC66 with RULES BILLING CODE 4910–13–P Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2006–25645; Directorate Identifier 2005–NM–201–AD; Amendment 39–14857; AD 2006–25–16] RIN 2120–AA64 Airworthiness Directives; Bombardier Model CL–600–1A11 (CL–600), CL– 600–2A12 (CL–601), and CL–600–2B16 (CL–601–3A and CL–601–3R) Airplanes Federal Aviation Administration (FAA), Department of Transportation (DOT). ACTION: Final rule. AGENCY: SUMMARY: The FAA is adopting a new airworthiness directive (AD) for all Bombardier Model CL–600–1A11 (CL– 600), CL–600–2A12 (CL–601), and CL– 600–2B16 (CL–601–3A and CL–601–3R) airplanes. This AD requires implementing a corrosion prevention and control program (CPCP) either by accomplishing specific tasks or by revising the maintenance inspection program to include a CPCP. This AD results from the determination that, as airplanes age, they are more likely to exhibit indications of corrosion. We are issuing this AD to prevent structural failure of the airplane due to corrosion. DATES: This AD becomes effective January 19, 2007. The Director of the Federal Register approved the incorporation by reference of certain publications listed in the AD as of January 19, 2007. ADDRESSES: You may examine the AD docket on the Internet at https:// dms.dot.gov or in person at the Docket Management Facility, U.S. Department of Transportation, 400 Seventh Street, SW., Nassif Building, Room PL–401, Washington, DC. Contact Bombardier, Inc., Canadair, Aerospace Group, P.O. Box 6087, Station Centre-ville, Montreal, Quebec H3C 3G9, Canada, for service information identified in this AD. FOR FURTHER INFORMATION CONTACT: Richard Beckwith, Aerospace Engineer, Airframe and Propulsion Branch, ANE– 171, FAA, New York Aircraft Certification Office, 1600 Stewart Avenue, suite 410, Westbury, New York 11590; telephone (516) 228–7302; fax (516) 794–5531. SUPPLEMENTARY INFORMATION: Examining the Docket You may examine the airworthiness directive (AD) docket on the Internet at https://dms.dot.gov or in person at the VerDate Aug<31>2005 14:57 Dec 14, 2006 Jkt 211001 PO 00000 Frm 00007 Fmt 4700 Sfmt 4700 75413 Docket Management Facility office between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. The Docket Management Facility office (telephone (800) 647–5227) is located on the plaza level of the Nassif Building at the street address stated in the ADDRESSES section. Discussion The FAA issued a notice of proposed rulemaking (NPRM) to amend 14 CFR part 39 to include an AD that would apply to all Bombardier Model CL–600– 1A11 (CL–600), CL–600–2A12 (CL–601), and CL–600–2B16 (CL–601–3A and CL– 601–3R) airplanes. That NPRM was published in the Federal Register on August 21, 2006 (71 FR 48487). That NPRM proposed to require implementing a corrosion prevention and control program (CPCP) either by accomplishing specific tasks or by revising the maintenance inspection program to include a CPCP. Comments We provided the public the opportunity to participate in the development of this AD. We have considered the comments received. Request To Change Incorporation of Certain Information The Modification and Replacement Parts Association (MARPA) states that, typically, airworthiness directives are based on service information originating with the type certificate holder or its suppliers. MARPA adds that manufacturer service documents are privately authored instruments generally having copyright protection against duplication and distribution. MARPA notes that when a service document is incorporated by reference into a public document, such as an airworthiness directive, it loses its private, protected status and becomes a public document. MARPA adds that if a service document is used as a mandatory element of compliance, it should not simply be referenced, but should be incorporated into the regulatory document; by definition, public laws must be public, which means they cannot rely upon private writings. MARPA adds that incorporated by reference service documents should be made available to the public by publication in the Docket Management System (DMS), keyed to the action that incorporates them. MARPA notes that the stated purpose of the incorporation by reference method is brevity, to keep from expanding the Federal Register needlessly by publishing documents already in the hands of the affected E:\FR\FM\15DER1.SGM 15DER1

Agencies

[Federal Register Volume 71, Number 241 (Friday, December 15, 2006)]
[Rules and Regulations]
[Pages 75411-75413]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: E6-21186]


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

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2005-22959; Directorate Identifier 2005-NE-40-AD; 
Amendment 39-14856; AD 2006-25-15]
RIN 2120-AA64


Airworthiness Directives; Sicma Aero Seat; Third Occupant Seat 
Assemblies, 133 Series

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

ACTION: Final rule.

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

SUMMARY: The FAA is adopting a new airworthiness directive (AD) for 
Sicma Aero Seat third occupant seat assemblies, 133 series. This AD 
requires visually inspecting the installation of the two headrest 
bushings and installing Mecanindus pins to secure the bushings. This AD 
results from Sicma's determination that missing or incorrectly secured 
bushings could loosen and cause disengagement of the headrest from the 
seat during a high-energy stop of the airplane, possibly injuring the 
seat occupant. We are issuing this AD to prevent disengagement of the 
headrest from the seat during a high-energy stop of the airplane that 
could injure the seat occupant.

DATES: This AD becomes effective January 19, 2007. The Director of the 
Federal Register approved the incorporation by reference of certain 
publications listed in the regulations as of January 19, 2007.

ADDRESSES: You can get the service information identified in this AD 
from Sicma Aero Seat, 7 Rue Lucien Coupet, 36100 Issoudun, France, 
telephone: (33) 54 03 39 39; fax: (33) 54 03 15 16.
    You may examine the AD docket on the Internet at https://dms.dot.gov 
or in Room PL-401 on the plaza level of the Nassif Building, 400 
Seventh Street, SW., Washington, DC.

FOR FURTHER INFORMATION CONTACT: Jeffrey Lee, Aerospace Engineer, 
Boston Aircraft Certification Office, FAA, Engine and Propeller 
Directorate, FAA, 12 New England Executive Park, Burlington, MA 01803; 
telephone (781) 238-7161; fax (781) 238-7170.

SUPPLEMENTARY INFORMATION: The FAA proposed to amend 14 CFR part 39 
with a proposed AD. The proposed AD applies to Sicma Aero Seat third 
occupant seat assemblies, 133 series. We published the proposed AD in 
the Federal Register on March 1, 2006 (71 FR 10453). That action 
proposed to require visually inspecting the installation of the two 
headrest bushings and installing Mecanindus pins to secure the 
bushings.

Examining the AD Docket

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

[[Page 75412]]

Comments

    We provided the public the opportunity to participate in the 
development of this AD. We have considered the comments received.

Request To Change Compliance Requirement

    Air Transport Association and Northwest Airlines request that the 
compliance requirement of ``within 30 days'' be changed to ``within 90 
days''. This will allow AD compliance in conjunction with operators' 
current A-Check interval. We agree and changed the AD to ``within 90 
days''.

Labor Time Information Does Not Match the Sicma Aero Seat Service 
Bulletin

    Air Transport Association and Northwest Airlines state that the 
estimated labor time information in the proposed AD does not match the 
manpower estimate in Sicma Aero Seat Service Bulletin (SB) No. 133-25-
006, dated May 12, 1999. We agree that the AD estimate for doing the 
work needs to match the SB. We changed the labor time in the AD to 0.17 
work-hour (10 minutes) per seat.

Seat Part Numbers Do Not Match

    Air Transport Association and Northwest Airlines state that the 
seat part numbers (P/Ns) in the proposed AD do not match those in Sicma 
Aero Seat SB No. 133-25-006, dated May 12, 1999. We partially agree. We 
corrected the P/Ns to 1330622-070, 1330622-070-1, 1330622-070-2, 
1330622-100, and 1330622V100-1 in the AD. These are the same listed P/
Ns affected as those identified by the Direction Generale de L'Aviation 
Civile, which is the airworthiness authority of France.

Question on Serial Numbers

    Air Transport Association and Northwest Airlines question why the 
serial numbers (SNs) in the proposed AD are specific, whereas there are 
no specific SNs listed in the SB. We listed the same SNs as those 
identified by the Direction Generale de L'Aviation Civile, which is the 
airworthiness authority for France. They correctly identified the SNs 
affected, in their AD No. 2000-042(AB). We did not change the AD.

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 with the changes described previously. 
We have determined that these changes will neither increase the 
economic burden on any operator nor increase the scope of the AD.

Costs of Compliance

    There are about 459 Sicma Aero Seat third occupant seat assemblies, 
133 series, of the affected design installed on airplanes of U.S. 
registry. There are about 698 airplanes of U.S. registry that these 
seats can be installed on. We estimate that it will take about 0.17 
work-hour per seat assembly to perform the actions, and that the 
average labor rate is $65 per work-hour. The Mecanindus pins cost 
$99.88 each, however, Sicma Aero Seat has advised us that they will 
supply the parts at no cost. Based on the labor rate to install the 
parts, the total cost of the AD to U.S. operators will be about $5,072.

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 this AD:
    (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.
    We prepared a summary of the costs to comply with this AD and 
placed it in the AD Docket. You may get a copy of this summary at the 
address listed under ADDRESSES.

List of Subjects in 14 CFR Part 39

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

Adoption of the Amendment

0
Accordingly, under the authority delegated to me by the Administrator, 
the Federal Aviation Administration amends 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. The FAA amends Sec.  39.13 by adding the following new airworthiness 
directive:

2006-25-15 Sicma Aero Seat: Amendment 39-14856. Docket No. FAA-2005-
22959; Directorate Identifier 2005-NE-40-AD.

Effective Date

    (a) This airworthiness directive (AD) becomes effective January 
19, 2007.

Affected ADs

    (b) None.

Applicability

    (c) This AD applies to Sicma Aero Seat third occupant seat 
assemblies, 133 series, with the part numbers (P/Ns) and serial 
numbers (SNs) in the following Table 1:

                  Table 1.--Applicable Seat Assemblies
------------------------------------------------------------------------
                Seat P/N                              Seat SN
------------------------------------------------------------------------
1330622-070.............................  1 through 212.
1330622-070-1...........................  1 through 212.
1330622-070-2...........................  1 through 6.
1330622-100.............................  1 through 13.
1330622V100-1...........................  1 through 16.
------------------------------------------------------------------------

    These third occupant seats are installed on, but not limited to, 
Airbus A319, A320, and A321 series airplanes.

Unsafe Condition

    (d) This AD results from Sicma's determination that missing or 
incorrectly secured bushings could loosen and cause disengagement of 
the headrest from the seat during a high-energy stop of the 
airplane, possibly injuring the seat occupant. We are issuing this 
AD to prevent disengagement of the headrest from the seat during a 
high-energy stop of the airplane that could injure the seat 
occupant.

[[Page 75413]]

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.

Installing Protective Fairings

    (f) Within 90 days after the effective date of this AD, visually 
check the installation of the two headrest bushings and install 
Mecanindus pins, P/N GPMECAE2-5x5, to secure the bushings. Use the 
instructions in paragraph 2 of Sicma Aero Seat Service Bulletin No. 
133-25-006, dated May 12, 1999, to perform the visual inspection and 
install the pins.

Alternative Methods of Compliance

    (g) The Manager, Boston Aircraft Certification Office, has the 
authority to approve alternative methods of compliance for this AD 
if requested using the procedures found in 14 CFR 39.19.

Related Information

    (h) Direction Generale de L'Aviation Civile airworthiness 
directive 2000-042(AB), dated January 26, 2000, also addresses the 
subject of this AD.

Material Incorporated by Reference

    (i) You must use Sicma Aero Seat Service Bulletin No. 133-25-
006, dated May 12, 1999, to perform the actions required by this AD. 
The Director of the Federal Register approved the incorporation by 
reference of this service bulletin in accordance with 5 U.S.C. 
552(a) and 1 CFR part 51. Contact Sicma Aero Seat, 7 Rue Lucien 
Coupet, 36100 Issoudun, France, telephone: (33) 54 03 39 39; fax: 
(33) 54 03 15 16, for a copy of this service information. You may 
review copies 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: https://www.archives.gov/federal-
register/cfr/ibr-locations.html.

    Issued in Burlington, Massachusetts, on December 7, 2006.
Robert J. Ganley,
Acting Manager, Engine and Propeller Directorate, Aircraft 
Certification Service.
[FR Doc. E6-21186 Filed 12-14-06; 8:45 am]
BILLING CODE 4910-13-P