Airworthiness Directives; Bombardier Model DHC-8-100, DHC-8-200, and DHC-8-300 Series Airplanes, 30959-30961 [E7-10670]

Download as PDF 30959 Federal Register / Vol. 72, No. 107 / Tuesday, June 5, 2007 / Rules and Regulations Issued in Burlington, Massachusetts, on May 24, 2007. Francis A. Favara, Manager, Engine and Propeller Directorate, Aircraft Certification Service. [FR Doc. E7–10588 Filed 6–4–07; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2007–27713; Directorate Identifier 2006–NM–240–AD; Amendment 39–15079; AD 2007–12–01] RIN 2120–AA64 Airworthiness Directives; Bombardier Model DHC–8–100, DHC–8–200, and DHC–8–300 Series Airplanes Federal Aviation Administration (FAA), Department of Transportation (DOT). ACTION: Final rule. AGENCY: The FAA is adopting a new airworthiness directive (AD) for certain Bombardier Model DHC–8–100, DHC– 8–200, and DHC–8–300 series airplanes. This AD requires, for certain airplanes, modification of the upper bearing of the main landing gear (MLG) shock strut. This AD also requires, for certain airplanes, revising the de Havilland DHC–8 Maintenance Program Manual to include the MLG shock strut servicing task. This AD results from reports of over-extension of the MLG shock strut piston, which allows the torque links to go over-center and rest on the piston. We are issuing this AD to prevent loss in shock absorption during touchdown and failure of the shock strut housing, which could result in a subsequent loss of directional control. SUMMARY: This AD becomes effective July 10, 2007. The Director of the Federal Register approved the incorporation by reference of certain publications listed in the AD as of July 10, 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: Mazdak Hobbi, 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) 228–7330; fax (516) 794–5531. SUPPLEMENTARY INFORMATION: March 29, 2007 (72 FR 14721). That NPRM proposed to require, for certain airplanes, modification of the upper bearing of the main landing gear (MLG) shock strut. That NPRM proposed to also require, for certain airplanes, revising the de Havilland DHC–8 Maintenance Program Manual to include the MLG shock strut servicing task. 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. 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. DATES: Discussion The FAA issued a notice of proposed rulemaking (NPRM) to amend 14 CFR part 39 to include an AD that would apply to certain Bombardier Model DHC–8–100, DHC–8–200, and DHC–8– 300 series airplanes. That NPRM was published in the Federal Register on 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. Clarification of Part Number We have revised paragraph (i)(2) of this final rule to correct a typographical error, which resulted in an incorrect part number. Paragraph (i)(2) should have read ‘‘* * * 10129–5 or 10129– 553.’’ Clarification of Alternative Method of Compliance (AMOC) Paragraph Conclusion We have carefully reviewed the available data 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 The following table provides the estimated costs for U.S. operators to comply with this AD. ESTIMATED COSTS Action Work hours cprice-sewell on PROD1PC71 with RULES Modification ........................................................ Manual Revision ................................................ 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. VerDate Aug<31>2005 15:27 Jun 04, 2007 Jkt 211001 Average labor rate per hour 4 1 $80 80 Parts $274 0 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 PO 00000 Frm 00005 Fmt 4700 Sfmt 4700 Number of U.S.registered airplanes Cost per airplane $594 80 Up to 135 ......... 135 ................... Fleet cost Up to $80,190. $10,800. 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. E:\FR\FM\05JNR1.SGM 05JNR1 30960 Federal Register / Vol. 72, No. 107 / Tuesday, June 5, 2007 / Rules and Regulations 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 Accordingly, under the authority delegated to me by the Administrator, the FAA amends 14 CFR part 39 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 2007–12–01 Bombardier, Inc. (Formerly de Havilland, Inc.): Amendment 39–15079. Docket No. FAA–2007–27713; Directorate Identifier 2006–NM–240–AD. Effective Date (a) This AD becomes effective July 10, 2007. Affected ADs (b) None. Applicability (c) This AD applies to Bombardier Model DHC–8–101, –102, –103, –106, –201, –202, –301, –311, –314, and –315 airplanes, certificated in any category; serial numbers 003 through 618 inclusive. Unsafe Condition (d) This AD results from reports of overextension of the main landing gear (MLG) shock strut piston, which allows the torque links to go over-center and rest on the piston. We are issuing this AD to prevent loss in shock absorption during touchdown and failure of the shock strut housing, which could result in a subsequent loss of directional control. 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. PART 39—AIRWORTHINESS DIRECTIVES Modification of the Upper Bearing (f) For Model DHC–8–311, –314, and –315 airplanes, serial numbers 202 through 516 inclusive, with MLG shock struts having any 1. The authority citation for part 39 continues to read as follows: I serial number DCL3501/90 through DCL3768/97 inclusive installed: Within 3,000 flight hours after the effective date of this AD, modify the upper bearing in each MLG (including doing inspections of the upper bearing and cylinder bore for wear and damage, and doing all applicable corrective actions) in accordance with the Accomplishment Instructions of Bombardier Service Bulletin 8–32–144, Revision ‘A,’ dated April 29, 2002, which includes Messier-Dowty Service Bulletin M–DT SBDHC8–32–82, Revision 1, dated July 5, 2001, except if wear exceeds the maximum diameter specified in the service bulletin for the cylinder bore or if damage is found on the cylinder bore, before further flight, repair using a method approved by either the Manager, International Branch, ANM–116, Transport Airplane Directorate, FAA; or Transport Canada Civil Aviation (TCCA) (or its delegated agent). Do all applicable corrective actions before further flight. Revision of the Maintenance Program Manual (g) For Model DHC–8–101, –102, –103, –106, –201, –202, –301, –311, –314, and –315 airplanes, serial numbers 003 through 614 inclusive: Within 30 days after the effective date of this AD, revise Part 1 of the applicable de Havilland DHC–8 Maintenance Program Manual by incorporating the applicable MLG shock strut servicing Task 3210/15 specified in Table 1 of this AD. Note 1: This may be done by inserting copies of the applicable task into the applicable maintenance program manual. When these tasks have been included in the general revisions of the applicable maintenance program manual, the general revisions may be inserted in the applicable maintenance program manual and the copy of the task may be removed from the maintenance program manual. TABLE 1.—TASKS To the de Havilland Program Support Manual (PSM)— Task— Dated— de Havilland Dash 8 Series 100 Maintenance Task Card 3210/15. de Havilland Dash 8 Series 200 Maintenance Task Card 3210/15. de Havilland Dash 8 Series 300 Maintenance Task Card 3210/15. June 22, 2005 .......................... 1–8–7 DHC–8–100 series airplanes. June 22, 2005 .......................... 1–82–7 DHC–8–200 series airplanes. November 29, 2005 ................. 1–83–7 DHC–8–300 series airplanes. cprice-sewell on PROD1PC71 with RULES Parts Installation (h) After the effective date of this AD, no person may install a part identified in paragraphs (h)(1) and (h)(2) of this AD, as a replacement during the repair or overhaul of any shock strut assembly, on any airplane. (1) Upper bearing, part number 10130–3 or 10130–551. (2) Damper ring, part number 10129–3 or 10129–551. VerDate Aug<31>2005 15:27 Jun 04, 2007 Jkt 211001 (i) After the effective date of this AD, only the parts identified in paragraphs (i)(1) and (i)(2) of this AD may be installed on any airplane as replacement upper bearings and damper rings during the repair or overhaul of any shock strut assembly, except as provided by paragraph (j) of this AD. (1) Upper bearing, part number 10130–5. (2) Damper ring, part number 10129–5 or 10129–553. PO 00000 Frm 00006 Fmt 4700 Sfmt 4700 For model— (j) After the effective date of this AD, only MLGs with a reworked, oversize cylinder bore (part number identified in the applicable component maintenance manual (CMM)) that have parts identified in paragraphs (j)(1), (j)(2), and (j)(3) of this AD used in accordance with the applicable CMM may be installed on any airplane. (1) Upper bearing, part number CRS85– 167–11. E:\FR\FM\05JNR1.SGM 05JNR1 Federal Register / Vol. 72, No. 107 / Tuesday, June 5, 2007 / Rules and Regulations (2) Damper ring, part number CRS85–167– 31 or CRS85–167–33. (3) Seal carrier, part number CRS85–167– 21. Credit for Actions Done Using Previous Service Information (k) Modifications accomplished before the effective date of this AD in accordance with Bombardier Service Bulletin 8–32–144, dated August 10, 1998, which includes MessierDowty Service Bulletin M–DT SBDHC8–32– 82, dated March 9, 1998, are considered acceptable for compliance with the corresponding actions specified in this AD. Alternative Methods of Compliance (AMOCs) accordance with the procedures found in 14 CFR 39.19. (2) To request a different method of compliance or a different compliance time for this AD, follow the procedures in 14 CFR 39.19. Before using any approved AMOC on any airplane to which the AMOC applies, notify your appropriate principal inspector (PI) in the FAA Flight Standards District Office (FSDO), or lacking a PI, your local FSDO. Related Information (m) Canadian airworthiness directive CF– 2006–14, dated June 14, 2006, also addresses the subject of this AD. Material Incorporated by Reference (l)(1) The Manager, New York Aircraft Certification Office, FAA, has the authority to approve AMOCs for this AD, if requested in (n) You must use Bombardier Service Bulletin 8–32–144, Revision ‘A,’ dated April 29, 2002, which includes Messier-Dowty 30961 Service Bulletin M–DT SBDHC8–32–82, Revision 1, dated July 5, 2001; and the task cards identified in Table 2 of this AD; 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 these documents 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. TABLE 2.—TASK CARDS INCORPORATED BY REFERENCE Task card— Dated— de Havilland Dash 8 Series 100 Maintenance Task Card 3210/15 ...................................................... de Havilland Dash 8 Series 200 Maintenance Task Card 3210/15 ...................................................... de Havilland Dash 8 Series 300 Maintenance Task Card 3210/15 ...................................................... June 22, 2005 ................. June 22, 2005 ................. November 29, 2005 ........ Issued in Renton, Washington, on May 25, 2007. Ali Bahrami, Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. E7–10670 Filed 6–4–07; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2007–26856; Directorate Identifier 2006–NM–125–AD; Amendment 39–15082; AD 2007–12–04] RIN 2120–AA64 Airworthiness Directives; Airbus Model A300 B4–600, B4–600R, and F4–600R Series Airplanes, and Model C4–605R Variant F Airplanes (Collectively Called A300–600 Series Airplanes) Federal Aviation Administration (FAA), Department of Transportation (DOT). ACTION: Final rule. cprice-sewell on PROD1PC71 with RULES AGENCY: SUMMARY: The FAA is superseding an existing airworthiness directive (AD) that applies to all Airbus Model A300– 600 series airplanes. That AD currently requires inspections of the lower door surrounding structure to detect cracks and corrosion; inspections to detect cracking of the holes of the corner VerDate Aug<31>2005 15:27 Jun 04, 2007 Jkt 211001 doublers, the fail-safe ring, and the door frames of the door structures; and repair if necessary. That AD also provides for optional terminating action for certain inspections. This new AD retains all requirements of the existing AD, mandates the previously optional terminating action, reduces the applicability of the existing AD, and adds repetitive inspections behind scuff plates for certain affected airplanes. This AD results from a determination that further rulemaking is necessary to improve the fatigue behavior of the cabin door surroundings. We are issuing this AD to prevent corrosion between the scuff plates at exit and cargo doors and fatigue cracks originating from certain fastener holes located in adjacent structure, which could result in reduced structural integrity of the door surroundings. DATES: This AD becomes effective July 10, 2007. The Director of the Federal Register approved the incorporation by reference of certain publications listed in the AD as of July 10, 2007. On September 4, 1998 (63 FR 40812, July 31, 1998), the Director of the Federal Register approved the incorporation by reference of certain other publications listed in the AD. 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 PO 00000 Frm 00007 Fmt 4700 Sfmt 4700 To the de Havilland program support manual— 1–8–7. 1–82–7. 1–83–7. 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: Tom Stafford, Aerospace Engineer, International Branch, ANM–116, FAA, Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton, Washington 98057–3356; telephone (425) 227–1622; fax (425) 227–1149. 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 supersedes AD 98–16–05, amendment 39–10680 (63 FR 40812, July 31, 1998). The existing AD applies to all Airbus Model A300–600 series airplanes. That E:\FR\FM\05JNR1.SGM 05JNR1

Agencies

[Federal Register Volume 72, Number 107 (Tuesday, June 5, 2007)]
[Rules and Regulations]
[Pages 30959-30961]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: E7-10670]


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

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2007-27713; Directorate Identifier 2006-NM-240-AD; 
Amendment 39-15079; AD 2007-12-01]
RIN 2120-AA64


Airworthiness Directives; Bombardier Model DHC-8-100, 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-8-100, DHC-8-200, and DHC-8-300 series 
airplanes. This AD requires, for certain airplanes, modification of the 
upper bearing of the main landing gear (MLG) shock strut. This AD also 
requires, for certain airplanes, revising the de Havilland DHC-8 
Maintenance Program Manual to include the MLG shock strut servicing 
task. This AD results from reports of over-extension of the MLG shock 
strut piston, which allows the torque links to go over-center and rest 
on the piston. We are issuing this AD to prevent loss in shock 
absorption during touchdown and failure of the shock strut housing, 
which could result in a subsequent loss of directional control.

DATES: This AD becomes effective July 10, 2007.
    The Director of the Federal Register approved the incorporation by 
reference of certain publications listed in the AD as of July 10, 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: Mazdak Hobbi, 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) 228-7330; 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 apply to certain Bombardier 
Model DHC-8-100, DHC-8-200, and DHC-8-300 series airplanes. That NPRM 
was published in the Federal Register on March 29, 2007 (72 FR 14721). 
That NPRM proposed to require, for certain airplanes, modification of 
the upper bearing of the main landing gear (MLG) shock strut. That NPRM 
proposed to also require, for certain airplanes, revising the de 
Havilland DHC-8 Maintenance Program Manual to include the MLG shock 
strut servicing task.

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.

Clarification of Part Number

    We have revised paragraph (i)(2) of this final rule to correct a 
typographical error, which resulted in an incorrect part number. 
Paragraph (i)(2) should have read ``* * * 10129-5 or 10129-553.''

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 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

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

                                                                     Estimated Costs
--------------------------------------------------------------------------------------------------------------------------------------------------------
                                                       Average
                Action                   Work hours   labor rate     Parts       Cost per     Number of U.S.-registered              Fleet cost
                                                       per hour                  airplane             airplanes
--------------------------------------------------------------------------------------------------------------------------------------------------------
Modification..........................            4          $80         $274         $594  Up to 135....................  Up to $80,190.
Manual Revision.......................            1           80            0           80  135..........................  $10,800.
--------------------------------------------------------------------------------------------------------------------------------------------------------

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.

[[Page 30960]]

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):

2007-12-01 Bombardier, Inc. (Formerly de Havilland, Inc.): Amendment 
39-15079. Docket No. FAA-2007-27713; Directorate Identifier 2006-NM-
240-AD.

Effective Date

    (a) This AD becomes effective July 10, 2007.

Affected ADs

    (b) None.

Applicability

    (c) This AD applies to Bombardier Model DHC-8-101, -102, -103, -
106, -201, -202, -301, -311, -314, and -315 airplanes, certificated 
in any category; serial numbers 003 through 618 inclusive.

Unsafe Condition

    (d) This AD results from reports of over-extension of the main 
landing gear (MLG) shock strut piston, which allows the torque links 
to go over-center and rest on the piston. We are issuing this AD to 
prevent loss in shock absorption during touchdown and failure of the 
shock strut housing, which could result in a subsequent loss of 
directional control.

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 of the Upper Bearing

    (f) For Model DHC-8-311, -314, and -315 airplanes, serial 
numbers 202 through 516 inclusive, with MLG shock struts having any 
serial number DCL3501/90 through DCL3768/97 inclusive installed: 
Within 3,000 flight hours after the effective date of this AD, 
modify the upper bearing in each MLG (including doing inspections of 
the upper bearing and cylinder bore for wear and damage, and doing 
all applicable corrective actions) in accordance with the 
Accomplishment Instructions of Bombardier Service Bulletin 8-32-144, 
Revision `A,' dated April 29, 2002, which includes Messier-Dowty 
Service Bulletin M-DT SBDHC8-32-82, Revision 1, dated July 5, 2001, 
except if wear exceeds the maximum diameter specified in the service 
bulletin for the cylinder bore or if damage is found on the cylinder 
bore, before further flight, repair using a method approved by 
either the Manager, International Branch, ANM-116, Transport 
Airplane Directorate, FAA; or Transport Canada Civil Aviation (TCCA) 
(or its delegated agent). Do all applicable corrective actions 
before further flight.

Revision of the Maintenance Program Manual

    (g) For Model DHC-8-101, -102, -103, -106, -201, -202, -301, -
311, -314, and -315 airplanes, serial numbers 003 through 614 
inclusive: Within 30 days after the effective date of this AD, 
revise Part 1 of the applicable de Havilland DHC-8 Maintenance 
Program Manual by incorporating the applicable MLG shock strut 
servicing Task 3210/15 specified in Table 1 of this AD.

    Note 1: This may be done by inserting copies of the applicable 
task into the applicable maintenance program manual. When these 
tasks have been included in the general revisions of the applicable 
maintenance program manual, the general revisions may be inserted in 
the applicable maintenance program manual and the copy of the task 
may be removed from the maintenance program manual.


                                                 Table 1.--Tasks
----------------------------------------------------------------------------------------------------------------
                                                                         To the de
                                                                         Havilland
                 Task--                             Dated--               Program             For model--
                                                                      Support Manual
                                                                          (PSM)--
----------------------------------------------------------------------------------------------------------------
de Havilland Dash 8 Series 100            June 22, 2005.............           1-8-7  DHC-8-100 series
 Maintenance Task Card 3210/15.                                                        airplanes.
de Havilland Dash 8 Series 200            June 22, 2005.............          1-82-7  DHC-8-200 series
 Maintenance Task Card 3210/15.                                                        airplanes.
de Havilland Dash 8 Series 300            November 29, 2005.........          1-83-7  DHC-8-300 series
 Maintenance Task Card 3210/15.                                                        airplanes.
----------------------------------------------------------------------------------------------------------------

Parts Installation

    (h) After the effective date of this AD, no person may install a 
part identified in paragraphs (h)(1) and (h)(2) of this AD, as a 
replacement during the repair or overhaul of any shock strut 
assembly, on any airplane.
    (1) Upper bearing, part number 10130-3 or 10130-551.
    (2) Damper ring, part number 10129-3 or 10129-551.
    (i) After the effective date of this AD, only the parts 
identified in paragraphs (i)(1) and (i)(2) of this AD may be 
installed on any airplane as replacement upper bearings and damper 
rings during the repair or overhaul of any shock strut assembly, 
except as provided by paragraph (j) of this AD.
    (1) Upper bearing, part number 10130-5.
    (2) Damper ring, part number 10129-5 or 10129-553.
    (j) After the effective date of this AD, only MLGs with a 
reworked, oversize cylinder bore (part number identified in the 
applicable component maintenance manual (CMM)) that have parts 
identified in paragraphs (j)(1), (j)(2), and (j)(3) of this AD used 
in accordance with the applicable CMM may be installed on any 
airplane.
    (1) Upper bearing, part number CRS85-167-11.

[[Page 30961]]

    (2) Damper ring, part number CRS85-167-31 or CRS85-167-33.
    (3) Seal carrier, part number CRS85-167-21.

Credit for Actions Done Using Previous Service Information

    (k) Modifications accomplished before the effective date of this 
AD in accordance with Bombardier Service Bulletin 8-32-144, dated 
August 10, 1998, which includes Messier-Dowty Service Bulletin M-DT 
SBDHC8-32-82, dated March 9, 1998, are considered acceptable for 
compliance with the corresponding actions specified in this AD.

Alternative Methods of Compliance (AMOCs)

    (l)(1) The Manager, New York Aircraft Certification Office, FAA, 
has the authority to approve AMOCs for this AD, if requested in 
accordance with the procedures found in 14 CFR 39.19.
    (2) To request a different method of compliance or a different 
compliance time for this AD, follow the procedures in 14 CFR 39.19. 
Before using any approved AMOC on any airplane to which the AMOC 
applies, notify your appropriate principal inspector (PI) in the FAA 
Flight Standards District Office (FSDO), or lacking a PI, your local 
FSDO.

Related Information

    (m) Canadian airworthiness directive CF-2006-14, dated June 14, 
2006, also addresses the subject of this AD.

Material Incorporated by Reference

    (n) You must use Bombardier Service Bulletin 8-32-144, Revision 
`A,' dated April 29, 2002, which includes Messier-Dowty Service 
Bulletin M-DT SBDHC8-32-82, Revision 1, dated July 5, 2001; and the 
task cards identified in Table 2 of this AD; 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 these documents 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.

             Table 2.--Task Cards Incorporated by Reference
------------------------------------------------------------------------
                                                             To the de
                                                             Havilland
            Task card--                    Dated--            program
                                                              support
                                                             manual--
------------------------------------------------------------------------
de Havilland Dash 8 Series 100      June 22, 2005.......          1-8-7.
 Maintenance Task Card 3210/15.
de Havilland Dash 8 Series 200      June 22, 2005.......         1-82-7.
 Maintenance Task Card 3210/15.
de Havilland Dash 8 Series 300      November 29, 2005...         1-83-7.
 Maintenance Task Card 3210/15.
------------------------------------------------------------------------


    Issued in Renton, Washington, on May 25, 2007.
Ali Bahrami,
Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. E7-10670 Filed 6-4-07; 8:45 am]
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