Airworthiness Directives; Bombardier Model DHC-8-102, -103, and -106 Airplanes and Model DHC-8-200 and DHC-8-300 Series Airplanes, 13683-13685 [E7-5217]

Download as PDF Federal Register / Vol. 72, No. 56 / Friday, March 23, 2007 / Rules and Regulations investigation, this AD does not include those requirements. Applicability (c) This AD applies to all Airbus Model A318, A319, A320, and A321 airplanes, certificated in any category. Unsafe Condition (d) This AD results from reports of slow operation of the main landing gear (MLG) door opening/closing sequence due to a defective actuator. We are issuing this AD to detect and correct defective actuators of the MLG door, which could result in slow operation of the MLG door and consequent non-extension of the MLG during an emergency freefall operation. 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. sroberts on PROD1PC70 with RULES Repetitive Inspections/Replacement (f) At the time specified in paragraph (f)(1) or (f)(2) of this AD, as applicable: Do a general visual inspection of the operation of the MLG door opening sequence to determine if a defective actuator is installed by doing all the applicable actions, including replacing the door actuator, as applicable, specified in the Accomplishment Instructions of Airbus Service Bulletin A320– 32–1309, Revision 01, dated June 19, 2006. Do all applicable replacements before further flight. Repeat the inspection thereafter at intervals not to exceed 900 flight cycles. Accomplishing the actions before the effective date of this AD in accordance with Airbus Service Bulletin A320–32–1309, dated March 7, 2006, is acceptable for compliance with the corresponding requirements in this paragraph. (1) For airplanes on which a record of the total number of flight cycles on the MLG door actuator is available: Before the accumulation of 3,000 total flight cycles on the MLG door actuator, or within 800 flight cycles after the effective date of this AD, whichever is later. (2) For airplanes on which a record of the total number of flight cycles on the MLG door actuator is not available: Within 800 flight cycles after the effective date of this AD. 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 enhance visual access to all exposed 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, ladders, or platforms may be required to gain proximity to the area being checked.’’ No Reporting/Parts Return Required (g) Although the Accomplishment Instructions of Airbus Service Bulletin A320– 32–1309, Revision 01, dated June 19, 2006, specify submitting certain information to the manufacturer and sending defective actuators back to the component manufacturer for VerDate Aug<31>2005 18:36 Mar 22, 2007 Jkt 211001 Alternative Methods of Compliance (AMOCs) (h)(1) The Manager, International Branch, ANM–116, Transport Airplane Directorate, FAA, 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 (i) European Aviation Safety Agency airworthiness directive 2006–0112, dated May 15, 2006, also addresses the subject of this AD. Material Incorporated by Reference (j) You must use Airbus Service Bulletin A320–32–1309, Revision 01, dated June 19, 2006, to perform the actions that are required by this AD, unless the AD specifies otherwise. The Director of the Federal Register approved the incorporation by reference of this document 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 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 March 13, 2007. Ali Bahrami, Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. E7–5221 Filed 3–22–07; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2006–26725; Directorate Identifier 2006–NM–161–AD; Amendment 39–15000; AD 2007–06–19] RIN 2120–AA64 Airworthiness Directives; Bombardier Model DHC–8–102, –103, and –106 Airplanes and Model DHC–8–200 and DHC–8–300 Series Airplanes Federal Aviation Administration (FAA), Department of Transportation (DOT). ACTION: Final rule. AGENCY: PO 00000 Frm 00013 Fmt 4700 Sfmt 4700 13683 SUMMARY: The FAA is adopting a new airworthiness directive (AD) for certain Bombardier Model DHC–8–102, –103, and –106 airplanes and Model DHC–8– 200 and DHC–8–300 series airplanes. This AD requires modifying the main landing gear (MLG) and nose landing gear (NLG) handle assemblies for alternate release and the MLG retaining plate. This AD also requires doing a related investigative action and corrective action if necessary. This AD results from reports of broken or damaged MLG and NLG alternate release cables caused by rubbing and fraying at the cable-to-handle interface. We are issuing this AD to prevent breakage of the MLG and NLG alternate release cables, which, if the normal gear extension fails, could result in the inability to extend the MLG or NLG and consequent collapse of the landing gear during ground maneuvers or upon landing. DATES: This AD becomes effective April 27, 2007. The Director of the Federal Register approved the incorporation by reference of a certain publication listed in the AD as of April 27, 2007. ADDRESSES: You may examine the AD docket on the Internet at http:// 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., Bombardier Regional Aircraft Division, 123 Garratt Boulevard, Downsview, Ontario M3K 1Y5, Canada, for service information identified in this AD. FOR FURTHER INFORMATION CONTACT: Ezra Sasson, Aerospace Engineer, Systems and Flight Test Branch, ANE–172, FAA, New York Aircraft Certification Office, 1600 Stewart Avenue, Suite 410, Westbury, New York 11590; telephone (516) 228–7320; fax (516) 794–5531. SUPPLEMENTARY INFORMATION: Examining the Docket You may examine the airworthiness directive (AD) docket on the Internet at http://dms.dot.gov or in person at the 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 E:\FR\FM\23MRR1.SGM 23MRR1 13684 Federal Register / Vol. 72, No. 56 / Friday, March 23, 2007 / Rules and Regulations apply to certain Bombardier Model DHC–8–102, –103, and –106 airplanes and Model DHC–8–200 and DHC–8–300 series airplanes. That NPRM was published in the Federal Register on January 8, 2007 (72 FR 662). That NPRM proposed to require modifying the main landing gear (MLG) and nose landing gear handle assemblies for alternate release and the MLG retaining plate. That NPRM also proposed to require doing a related investigative action and corrective action if necessary. Comments We provided the public the opportunity to participate in the development of this AD. We received no comments on the NPRM or on the determination of the cost to the public. Conclusion We have carefully reviewed the available data and determined that air safety and the public interest require adopting the AD as proposed. Costs of Compliance The following table provides the estimated costs for U.S. operators to comply with this AD. ESTIMATED COSTS Action Work hours Average labor rate per hour Cost per airplane Number of U.S.-registered airplanes Fleet cost Modification .......................................................................... 5 $80 $400 164 $65,600 sroberts on PROD1PC70 with RULES 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 regulatory evaluation of the estimated costs to comply with VerDate Aug<31>2005 18:36 Mar 22, 2007 Jkt 211001 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 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 [Amended] 2. The Federal Aviation Administration (FAA) amends § 39.13 by adding the following new airworthiness directive (AD): I 2007–06–19 Bombardier, Inc. (Formerly de Havilland, Inc.): Amendment 39–15000. Docket No. FAA–2006–26725; Directorate Identifier 2006–NM–161–AD. Effective Date (a) This AD becomes effective April 27, 2007. Affected ADs (b) None. cable-to-handle interface. We are issuing this AD to prevent breakage of the MLG and NLG alternate release cables, which, if the normal gear extension fails, could result in the inability to extend the MLG or NLG and consequent collapse of the landing gear during ground maneuvers or upon landing. 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. Modification (f) Within 3,000 flight hours after the effective date of this AD, modify the MLG and NLG handle assemblies for alternate release and the MLG retaining plate, do the related investigative action, and the corrective action as applicable, by accomplishing all the applicable actions specified in the Accomplishment Instructions of Bombardier Service Bulletin 8–32–146, Revision ‘D,’ dated February 7, 2003. Do the corrective action, as applicable, before further flight. Actions Accomplished According to Previous Issue of Service Bulletin (g) Actions accomplished before the effective date of this AD in accordance with Bombardier Service Bulletin 8–32–146, dated September 10, 1999; Revision ‘A,’ dated January 17, 2001; Revision ‘B,’ dated June 25, 2001; or Revision ‘C,’ dated January 24, 2003; are considered acceptable for compliance with the corresponding action specified in this AD. Applicability (c) This AD applies to Bombardier Model DHC–8–102, DHC–8–103, and DHC–8–106 airplanes and Model DHC–8–200 and DHC– 8–300 series airplanes; certificated in any category; serial numbers 003 through 579 inclusive. Parts Installation (h) As of the effective date of this AD, no person may install any part specified in paragraphs (h)(1), (h)(2), and (h)(3) of this AD, on any airplane. (1) MLG handle assembly, part number (P/ N) 83260042. (2) NLG handle assembly, P/N 83260020. (3) MLG retaining plate, P/N 83260043. Unsafe Condition (d) This AD results from reports of broken or damaged main landing gear (MLG) and nose landing gear (NLG) alternate release cables caused by rubbing and fraying at the Alternative Methods of Compliance (AMOCs) (i)(1) The Manager, New York Aircraft Certification Office, FAA, has the authority to approve AMOCs for this AD, if requested in PO 00000 Frm 00014 Fmt 4700 Sfmt 4700 E:\FR\FM\23MRR1.SGM 23MRR1 Federal Register / Vol. 72, No. 56 / Friday, March 23, 2007 / Rules and Regulations 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– 2006–09, issued May 8, 2006, also addresses the subject of this AD. Material Incorporated by Reference (k) You must use Bombardier Service Bulletin 8–32–146, Revision ‘D,’ dated February 7, 2003, to perform the actions that are required by this AD, unless the AD specifies otherwise. The Director of the Federal Register approved the incorporation by reference of this document in accordance with 5 U.S.C. 552(a) and 1 CFR part 51. Contact Bombardier, Inc., Bombardier Regional Aircraft Division, 123 Garratt Boulevard, Downsview, Ontario M3K 1Y5, Canada, 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/ibrlocations.html. Issued in Renton, Washington, on March 13, 2007. Ali Bahrami, Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. E7–5217 Filed 3–22–07; 8:45 am] actuator fitting during maintenance. We are issuing this AD to prevent rupture of a rudder actuator fitting, which could result in reduced controllability of the airplane. This AD becomes effective April 27, 2007. The Director of the Federal Register approved the incorporation by reference of a certain publication listed in the AD as of April 27, 2007. ADDRESSES: You may examine the AD docket on the Internet at http:// 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 Airbus, 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex, France, for service information identified in this AD. FOR FURTHER INFORMATION CONTACT: Dan Rodina, Aerospace Engineer, International Branch, ANM–116, FAA, Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton, Washington 98057–3356; telephone (425) 227–2125; fax (425) 227–1149. SUPPLEMENTARY INFORMATION: DATES: Examining the Docket Federal Aviation Administration You may examine the airworthiness directive (AD) docket on the Internet at http://dms.dot.gov or in person at the 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. 14 CFR Part 39 Discussion BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION [Docket No. FAA–2006–26595; Directorate Identifier 2006–NM–208–AD; Amendment 39–14998; AD 2007–06–17] RIN 2120–AA64 Airworthiness Directives; Airbus Model A320 Series Airplanes Federal Aviation Administration (FAA), Department of Transportation (DOT). ACTION: Final rule. sroberts on PROD1PC70 with RULES AGENCY: SUMMARY: The FAA is adopting a new airworthiness directive (AD) for certain Airbus Model A320 series airplanes. This AD requires replacing the carbon fiber reinforced plastic (CFRP) actuator fittings of the rudder with aluminum actuator fittings and doing related investigative and corrective actions. This AD results from rupture of a CFRP VerDate Aug<31>2005 18:36 Mar 22, 2007 Jkt 211001 The FAA issued a notice of proposed rulemaking (NPRM) to amend 14 CFR part 39 to include an AD that would apply to certain Airbus Model A320 series airplanes. That NPRM was published in the Federal Register on December 15, 2006 (71 FR 75432). That NPRM proposed to require replacing the carbon fiber reinforced plastic (CFRP) actuator fittings of the rudder with aluminum actuator fittings and doing related investigative and corrective actions. Comments We provided the public the opportunity to participate in the development of this AD. We have considered the comments received. Support for the NPRM Airbus supports the NPRM. PO 00000 Frm 00015 Fmt 4700 Sfmt 4700 13685 Request To Revise Discussion Section In the Discussion section of the NPRM, we stated that investigation revealed that the CFRP actuator fittings cannot sustain limit loads resulting from ground gust conditions due to design of the fitting. Airbus requests that we revise that statement to clarify that the CFRP actuator fittings ‘‘on the rudder side’’ cannot sustain limit ‘‘compression’’ loads resulting from ground gust conditions due to design of the fitting. We agree with Airbus’ statement. However, we have not changed the AD in this regard, since the Discussion section is not retained in the final rule. Clarification of Alternative Method of Compliance (AMOC) Paragraph We have revised this action to clarify the appropriate procedure for notifying the principal inspector before using any approved AMOC on any airplane to which the AMOC applies. 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 change described previously. We have determined that this change will neither increase the economic burden on any operator nor increase the scope of the AD. Costs of Compliance This AD affects about 38 airplanes of U.S. registry. The required action takes about 100 work hours per airplane, at an average labor rate of $80 per work hour. Required parts cost about $6,310 per airplane. Based on these figures, the estimated cost of the AD for U.S. operators is $543,780, or $14,310 per airplane. 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 E:\FR\FM\23MRR1.SGM 23MRR1

Agencies

[Federal Register Volume 72, Number 56 (Friday, March 23, 2007)]
[Rules and Regulations]
[Pages 13683-13685]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: E7-5217]


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

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2006-26725; Directorate Identifier 2006-NM-161-AD; 
Amendment 39-15000; AD 2007-06-19]
RIN 2120-AA64


Airworthiness Directives; Bombardier Model DHC-8-102, -103, and -
106 Airplanes and Model DHC-8-200 and DHC-8-300 Series Airplanes

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

ACTION: Final rule.

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

SUMMARY: The FAA is adopting a new airworthiness directive (AD) for 
certain Bombardier Model DHC-8-102, -103, and -106 airplanes and Model 
DHC-8-200 and DHC-8-300 series airplanes. This AD requires modifying 
the main landing gear (MLG) and nose landing gear (NLG) handle 
assemblies for alternate release and the MLG retaining plate. This AD 
also requires doing a related investigative action and corrective 
action if necessary. This AD results from reports of broken or damaged 
MLG and NLG alternate release cables caused by rubbing and fraying at 
the cable-to-handle interface. We are issuing this AD to prevent 
breakage of the MLG and NLG alternate release cables, which, if the 
normal gear extension fails, could result in the inability to extend 
the MLG or NLG and consequent collapse of the landing gear during 
ground maneuvers or upon landing.

DATES: This AD becomes effective April 27, 2007.
    The Director of the Federal Register approved the incorporation by 
reference of a certain publication listed in the AD as of April 27, 
2007.

ADDRESSES: You may examine the AD docket on the Internet at http://
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., Bombardier Regional Aircraft Division, 
123 Garratt Boulevard, Downsview, Ontario M3K 1Y5, Canada, for service 
information identified in this AD.

FOR FURTHER INFORMATION CONTACT: Ezra Sasson, Aerospace Engineer, 
Systems and Flight Test Branch, ANE-172, FAA, New York Aircraft 
Certification Office, 1600 Stewart Avenue, Suite 410, Westbury, New 
York 11590; telephone (516) 228-7320; fax (516) 794-5531.

SUPPLEMENTARY INFORMATION: 

Examining the Docket

    You may examine the airworthiness directive (AD) docket on the 
Internet at http://dms.dot.gov or in person at the 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

[[Page 13684]]

apply to certain Bombardier Model DHC-8-102, -103, and -106 airplanes 
and Model DHC-8-200 and DHC-8-300 series airplanes. That NPRM was 
published in the Federal Register on January 8, 2007 (72 FR 662). That 
NPRM proposed to require modifying the main landing gear (MLG) and nose 
landing gear handle assemblies for alternate release and the MLG 
retaining plate. That NPRM also proposed to require doing a related 
investigative action and corrective action if necessary.

Comments

    We provided the public the opportunity to participate in the 
development of this AD. We received no comments on the NPRM or on the 
determination of the cost to the public.

Conclusion

    We have carefully reviewed the available data and determined that 
air safety and the public interest require adopting the AD as proposed.

Costs of Compliance

    The following table provides the estimated costs for U.S. operators 
to comply with this AD.

                                                                     Estimated Costs
--------------------------------------------------------------------------------------------------------------------------------------------------------
                                                                                                                        Number of U.S.-
                               Action                                   Work hours     Average labor       Cost per        registered       Fleet cost
                                                                                       rate per hour       airplane        airplanes
--------------------------------------------------------------------------------------------------------------------------------------------------------
Modification.......................................................               5              $80             $400              164          $65,600
--------------------------------------------------------------------------------------------------------------------------------------------------------

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 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

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

2007-06-19 Bombardier, Inc. (Formerly de Havilland, Inc.): Amendment 
39-15000. Docket No. FAA-2006-26725; Directorate Identifier 2006-NM-
161-AD.

Effective Date

    (a) This AD becomes effective April 27, 2007.

Affected ADs

    (b) None.

Applicability

    (c) This AD applies to Bombardier Model DHC-8-102, DHC-8-103, 
and DHC-8-106 airplanes and Model DHC-8-200 and DHC-8-300 series 
airplanes; certificated in any category; serial numbers 003 through 
579 inclusive.

Unsafe Condition

    (d) This AD results from reports of broken or damaged main 
landing gear (MLG) and nose landing gear (NLG) alternate release 
cables caused by rubbing and fraying at the cable-to-handle 
interface. We are issuing this AD to prevent breakage of the MLG and 
NLG alternate release cables, which, if the normal gear extension 
fails, could result in the inability to extend the MLG or NLG and 
consequent collapse of the landing gear during ground maneuvers or 
upon landing.

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.

Modification

    (f) Within 3,000 flight hours after the effective date of this 
AD, modify the MLG and NLG handle assemblies for alternate release 
and the MLG retaining plate, do the related investigative action, 
and the corrective action as applicable, by accomplishing all the 
applicable actions specified in the Accomplishment Instructions of 
Bombardier Service Bulletin 8-32-146, Revision `D,' dated February 
7, 2003. Do the corrective action, as applicable, before further 
flight.

Actions Accomplished According to Previous Issue of Service Bulletin

    (g) Actions accomplished before the effective date of this AD in 
accordance with Bombardier Service Bulletin 8-32-146, dated 
September 10, 1999; Revision `A,' dated January 17, 2001; Revision 
`B,' dated June 25, 2001; or Revision `C,' dated January 24, 2003; 
are considered acceptable for compliance with the corresponding 
action specified in this AD.

Parts Installation

    (h) As of the effective date of this AD, no person may install 
any part specified in paragraphs (h)(1), (h)(2), and (h)(3) of this 
AD, on any airplane.
    (1) MLG handle assembly, part number (P/N) 83260042.
    (2) NLG handle assembly, P/N 83260020.
    (3) MLG retaining plate, P/N 83260043.

Alternative Methods of Compliance (AMOCs)

    (i)(1) The Manager, New York Aircraft Certification Office, FAA, 
has the authority to approve AMOCs for this AD, if requested in

[[Page 13685]]

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.

Related Information

    (j) Canadian airworthiness directive CF-2006-09, issued May 8, 
2006, also addresses the subject of this AD.

Material Incorporated by Reference

    (k) You must use Bombardier Service Bulletin 8-32-146, Revision 
`D,' dated February 7, 2003, to perform the actions that are 
required by this AD, unless the AD specifies otherwise. The Director 
of the Federal Register approved the incorporation by reference of 
this document in accordance with 5 U.S.C. 552(a) and 1 CFR part 51. 
Contact Bombardier, Inc., Bombardier Regional Aircraft Division, 123 
Garratt Boulevard, Downsview, Ontario M3K 1Y5, Canada, 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 March 13, 2007.
Ali Bahrami,
Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. E7-5217 Filed 3-22-07; 8:45 am]
BILLING CODE 4910-13-P