Airworthiness Directives; Bombardier Model DHC-8-102, -103, -106, -201, -202, -301, -311, and -315 Airplanes, 32986-32988 [05-11054]

Download as PDF 32986 Federal Register / Vol. 70, No. 108 / Tuesday, June 7, 2005 / Rules and Regulations Repeat the inspections thereafter at intervals not to exceed 4,500 flight cycles. Doing the applicable actions in paragraph (h) or (j) of this AD terminates the repetitive inspections. (g) Where the service bulletin specified in paragraph (f) of this AD provides a threshold relative to the release date of the service bulletin, this AD requires compliance within the applicable threshold following the effective date of this AD, if the ‘‘total airplane flight cycles’’ or ‘‘total replaced door flight cycles’’ threshold has been exceeded. Corrective Actions (h) For airplanes on which cracking is found during any inspection required by paragraph (f) of this AD: Before further flight, do all of the applicable corrective actions specified in the Accomplishment Instructions of Boeing Special Attention Service Bulletin 727–52–0149, dated October 16, 2003. Repairing any affected area terminates the repetitive inspections required by paragraph (f) of this AD. Parts Installation (i) Any replacement No. 3 cargo door installed on any airplane after the effective date of this AD must be inspected or modified in accordance with either paragraph (i)(1) or (i)(2) of this AD, as applicable. (1) If the number of total flight cycles on the door can be positively determined: Do the actions required by paragraphs (f) and (h) of this AD, as applicable, or paragraph (j) of this AD. Do the actions at the times specified in Table 2 of paragraph 1.E., ‘‘Compliance,’’ of Boeing Special Attention Service Bulletin 727–52–0149, dated October 16, 2003. (2) If the number of total flight cycles on the door cannot be positively determined: Do the actions required by paragraphs (f) and (h) of this AD, as applicable, or paragraph (j) of this AD, before installing the door. Optional Terminating Action (j) Concurrently with doing the inspection required by paragraph (f) of this AD, if no cracking is found, doing the preventative modification specified in paragraph 3.B.2. of the Accomplishment Instructions of Boeing Special Attention Service Bulletin 727–52– 0149, dated October 16, 2003, terminates the repetitive inspections required by paragraph (f) of this AD. Alternative Methods of Compliance (AMOCs) (k)(1) The Manager, Seattle Aircraft Certification Office (ACO), FAA, has the authority to approve AMOCs for this AD, if requested using the procedures found in 14 CFR 39.19. (2) An AMOC that provides an acceptable level of safety may be used for any repair for cracking required by this AD, if it is approved by an Authorized Representative for the Boeing Delegated Option Authorization Organization who has been authorized by the Manager, Seattle ACO, to make such findings. For a repair method to be approved, the repair must meet the certification basis of the airplane, and the approval must specifically refer to this AD. VerDate jul<14>2003 16:06 Jun 06, 2005 Jkt 205001 Material Incorporated by Reference (l) You must use Boeing Special Attention Service Bulletin 727–52–0149, dated October 16, 2003, to perform the actions that are required by this AD, unless the AD specifies otherwise. The Director of the Federal Register approves the incorporation by reference of this document in accordance with 5 U.S.C. 552(a) and 1 CFR part 51. To get copies of the service information, contact Boeing Commercial Airplanes, P.O. Box 3707, Seattle, Washington 98124–2207. To view the AD docket, go to the Docket Management Facility, U.S. Department of Transportation, 400 Seventh Street SW., room PL–401, Nassif Building, Washington, DC. To review copies of the service information, go to 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/ code_of_federal_regulations/ ibr_locations.html. Issued in Renton, Washington, on May 26, 2005. Ali Bahrami, Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 05–11055 Filed 6–6–05; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2005–20756; Directorate Identifier 2004–NM–52–AD; Amendment 39– 14112; AD 2005–11–10] RIN 2120–AA64 Airworthiness Directives; Bombardier Model DHC–8–102, –103, –106, –201, –202, –301, –311, and –315 Airplanes Federal Aviation Administration (FAA), Department of Transportation (DOT). ACTION: Final rule. AGENCY: SUMMARY: The FAA is adopting a new airworthiness directive (AD) for certain Bombardier Model DHC–8–102, –103, –106, –201, –202, –301, –311 and –315 airplanes. This AD requires installation of check valves in Numbers 1 and 2 hydraulic systems, removal of the filters from the brake shuttle valves, and removal of the internal garter spring from the brake shuttle valves. This AD results from two instances of brake failure due to the loss of hydraulic fluid from both Numbers 1 and 2 hydraulic systems and one incident of brake failure due to filter blockage in the shuttle valve. We are issuing this AD to prevent the loss of hydraulic power from both hydraulic systems, which PO 00000 Frm 00010 Fmt 4700 Sfmt 4700 could lead to reduced controllability of the airplane, and to prevent brake failure, which could result in the loss of directional control on the ground and consequent departure from the runway during landing. DATES: This AD becomes effective July 12, 2005. The incorporation by reference of certain publications listed in the AD is approved by the Director of the Federal Register as of July 12, 2005. ADDRESSES: For service information identified in this AD, contact Bombardier, Inc., Bombardier Regional Aircraft Division, 123 Garratt Boulevard, Downsview, Ontario M3K 1Y5, Canada. Docket: The AD docket contains the proposed AD, comments, and any final disposition. You can examine the 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 U.S. Department of Transportation, 400 Seventh Street SW., room PL–401, Washington, DC. This docket number is FAA–2005–20756; the directorate identifier for this docket is 2004–NM– 52–AD. FOR FURTHER INFORMATION CONTACT: Ezra Sasson, 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) 228–7320; fax (516) 794–5531. SUPPLEMENTARY INFORMATION: The FAA proposed to amend 14 CFR part 39 with an AD for certain Bombardier Model DHC–8–102, –103, –106, –201, –202, –301, –311, and –315 airplanes. That action, published in the Federal Register on March 30, 2005 (70 FR 16182), proposed to require installation of check valves in Numbers 1 and 2 hydraulic systems, removal of the filters from the brake shuttle valves, and removal of the internal garter spring from the brake shuttle valves. Comments We provided the public the opportunity to participate in the development of this AD. No comments have been submitted on the proposed AD or on the determination of the cost to the public. Explanation of Editorial Change We have revised the Costs of Compliance section of this AD to correct a mathematical error. E:\FR\FM\07JNR1.SGM 07JNR1 Federal Register / Vol. 70, No. 108 / Tuesday, June 7, 2005 / Rules and Regulations Conclusion We have carefully reviewed the available data and determined that air safety and the public interest require adopting the AD as proposed. 32987 Costs of Compliance The following table provides the estimated costs for U.S. operators to comply with this AD: ESTIMATED COSTS Action Installation of check valves in Numbers 1 and 2 hydraulic systems .................................... Removal of filters and internal garter springs from brake shuttle valves .................................. 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. See the ADDRESSES section for Jkt 205001 Number of U.S.-registered airplanes Average fleet cost $65 $279–$405 $474–$600 179 $84,846–$107,400 3 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. 16:06 Jun 06, 2005 Cost per airplane Parts 3 Authority for This Rulemaking VerDate jul<14>2003 Average labor rate per hour Work hours 65 252–1,360 447–1,555 179 80,013–278,345 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 FAA amends § 39.13 by adding the following new airworthiness directive (AD): I 2005–11–10 Bombardier, Inc. (Formerly de Havilland, Inc.): Amendment 39–14112. Docket No. FAA–2005–20756; Directorate Identifier 2004–NM–52–AD. Effective Date (a) This AD becomes effective July 12, 2005. Affected ADs (b) None. Applicability (c) This AD applies to Bombardier Model DHC–8–102, –103, –106, –201, –202, –301, –311, and –315 airplanes, certificated in any category; serial numbers 003 through 593 inclusive. Unsafe Condition (d) This AD was prompted by two instances of brake failure due to the loss of hydraulic fluid from both Numbers 1 and 2 hydraulic systems and one incident of brake failure due to filter blockage in the shuttle valve. We are issuing this AD to prevent the loss of hydraulic power from both hydraulic systems, which could lead to reduced controllability of the airplane, and to prevent PO 00000 Frm 00011 Fmt 4700 Sfmt 4700 brake failure, which could result in the loss of directional control on the ground and consequent departure from the runway during 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. Installation of Check Valves in Numbers 1 and 2 Hydraulic Systems (f) Within 12 months after the effective date of this AD, install check valves in the Numbers 1 and 2 hydraulic return systems by incorporating Modsum 8Q101320 in accordance with the Accomplishment Instructions of Bombardier Service Bulletin 8–29–36, Revision ‘‘B,’’ dated January 6, 2003. Removal of Filters and Internal Garter Spring From the Brake Shuttle Valves (g) Within 12 months after the effective date of this AD, modify the brake shuttle valves, part number (P/N) 5084–1, by doing the actions in either paragraph (g)(1) or (g)(2) of this AD. The installation specified in paragraph (f) of this AD must be done prior to doing any actions in accordance with Bombardier Service Bulletin 8–29–37, Revision ‘‘A,’’ dated September 19, 2003 (Modsum 8Q101316), that are specified in paragraphs (g)(1) and (g)(2) of this AD. (1) Remove the filter assemblies by incorporating Modsum 8Q101422 in accordance with the Accomplishment Instructions of Bombardier Service Bulletin 8–29–39, dated July 14, 2003; and within 40,000 flight hours after removing the filter assemblies, remove the internal garter spring by incorporating Modsum 8Q101316 in accordance with the Accomplishment Instructions of Bombardier Service Bulletin 8–29–37, Revision ‘‘A,’’ dated September 19, 2003. (2) Remove the filter assemblies and internal garter spring by incorporating Modsum 8Q101316 in accordance with the Accomplishment Instructions of Bombardier Service Bulletin 8–29–37, Revision ‘‘A,’’ dated September 19, 2003. Note 1: You can mix shuttle valves that have incorporated either Modsum 8Q101316 or 8Q101422 on the same airplane. E:\FR\FM\07JNR1.SGM 07JNR1 32988 Federal Register / Vol. 70, No. 108 / Tuesday, June 7, 2005 / Rules and Regulations Actions Accomplished According to Previous Issues of Service Bulletins (h) Installations accomplished before the effective date of this AD according to Bombardier Service Bulletin 8–29–36, dated December 6, 2002; and Revision ‘‘A,’’ dated December 12, 2002, are considered acceptable for compliance with the corresponding installation specified in paragraph (f) of this AD. (i) Removals of the filters and internal garter springs accomplished before the effective date of this AD according to Bombardier Service Bulletin 8–29–37, dated July 15, 2003, are considered acceptable for compliance with the corresponding removals specified in paragraph (g) of this AD. Issued in Renton, Washington, on May 26, 2005. Ali Bahrami, Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 05–11054 Filed 6–6–05; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2005–20590; Directorate Identifier 2005–CE–13–AD; Amendment 39– 14110; AD 2005–11–08] Alternative Methods of Compliance (AMOCs) RIN 2120–AA64 (j) 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. Airworthiness Directives; GROB– WERKE Model G120A Airplanes Related Information (k) Canadian airworthiness directive CF– 2004–02, dated February 9, 2004, also addresses the subject of this AD. Material Incorporated by Reference (l) You must use the documents listed in Table 1 of this AD to perform the actions that are required by this AD, unless the AD specifies otherwise. The Director of the Federal Register approves the incorporation by reference of these documents in accordance with 5 U.S.C. 552(a) and 1 CFR part 51. To get copies of the service information, contact Bombardier, Inc., Bombardier Regional Aircraft Division, 123 Garratt Boulevard, Downsview, Ontario M3K 1Y5, Canada. To view the AD docket, go to the Docket Management Facility, U.S. Department of Transportation, 400 Seventh Street SW., room PL–401, Nassif Building, Washington, DC. To review copies of the service information, go to the National Archives and Records Administration (NARA). For information on the availability of this material at the NARA, call (202) 741– 6030, or go to http://www.archives.gov/ federal_register/code_of_federal_regulations/ ibr_locations.html. TABLE 1.—MATERIAL INCORPORATED BY REFERENCE Bombardier service bulletin Revision level Date 8–29–36 .... B ..................... 8–29–37 .... A ..................... 8–29–39 .... Original ........... January 6, 2003. September 19, 2003. July 14, 2003. VerDate jul<14>2003 16:06 Jun 06, 2005 Jkt 205001 Federal Aviation Administration (FAA), DOT. ACTION: Final rule. AGENCY: SUMMARY: The FAA adopts a new airworthiness directive (AD) for all GROB–WERKE (GROB) Model G120A airplanes. This AD requires you to replace the main landing gear front and rear spherical bearings with improved spherical bearings. This AD results from mandatory continuing airworthiness information (MCAI) issued by the airworthiness authority for Germany. We are issuing this AD to replace front and rear main landing gear bearings that are susceptible to damage when exposed to high axial loads, which could result in failure of the landing gear bearing. This failure could lead to loss of control on landing. DATES: This AD becomes effective on July 18, 2005. As of July 18, 2005, the Director of the Federal Register approved the incorporation by reference of certain publications listed in the regulation. ADDRESSES: To get the service information identified in this AD, contact GROB–WERKE, Burkart Grob e.K., Unternehmenbereich Luft-und Raumfahrt, Lettenbachstrasse 9, 86874 Tussenhausen-Mattsies, Germany; telephone: 011 49 8268 998 105; facsimile: 011 49 8268 998 200. To view the AD docket, go to the Docket Management Facility; U.S. Department of Transportation, 400 Seventh Street, SW., Nassif Building, Room PL–401, Washington, DC 20590– 001 or on the Internet at http:// dms.dot.gov. The docket number is FAA–2005–20590; Directorate Identifier 2005–CE–13–AD. FOR FURTHER INFORMATION CONTACT: Karl Schletzbaum, Aerospace Engineer, PO 00000 Frm 00012 Fmt 4700 Sfmt 4700 ACE–112, Small Airplane Directorate, 901 Locust, Room 301, Kansas City, Missouri 64106; telephone: 816–329– 4146; facsimile: 816–329–4090. SUPPLEMENTARY INFORMATION: Discussion What events have caused this AD? The Luftfahrt-Bundesamt (LBA), which is the airworthiness authority for Germany, recently notified FAA that an unsafe condition may exist on all GROB–WERKE (GROB) Model G120A airplanes. The LBA reports an incident of a damaged spherical bearing (part number (P/N) S20) installed in the main landing gear on one of the affected airplanes. Evidence showed that the bearing inner ring was shifted against the outer ring. This indicated that the bearing was exposed to high axial loads. Grob has an improved spherical bearing (P/N SSRC 20 C2) that can tolerate higher axial loads. What is the potential impact if FAA took no action? Main landing gear front and rear bearings that are susceptible to damage when exposed to high axial loads could result in failure of the landing gear bearing. This failure could lead to loss of control on landing. Has FAA taken any action to this point? We issued a proposal to amend part 39 of the Federal Aviation Regulations (14 CFR part 39) to include an AD that would apply to all GROB– WERKE (GROB) Model G120A airplanes. This proposal was published in the Federal Register as a notice of proposed rulemaking (NPRM) on April 1, 2005 (70 FR 16769). The NPRM proposed to require you to replace the main landing gear front and rear spherical bearings with improved spherical bearings. Comments Was the public invited to comment? We provided the public the opportunity to participate in developing this AD. We received no comments on the proposal or on the determination of the cost to the public. Conclusion What is FAA’s final determination on this issue? We have carefully reviewed the available data and determined that air safety and the public interest require adopting the AD as proposed except for minor editorial corrections. We have determined that these minor corrections: —Are consistent with the intent that was proposed in the NPRM for correcting the unsafe condition; and —Do not add any additional burden upon the public than was already proposed in the NPRM. E:\FR\FM\07JNR1.SGM 07JNR1

Agencies

[Federal Register Volume 70, Number 108 (Tuesday, June 7, 2005)]
[Rules and Regulations]
[Pages 32986-32988]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 05-11054]


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

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2005-20756; Directorate Identifier 2004-NM-52-AD; 
Amendment 39-14112; AD 2005-11-10]
RIN 2120-AA64


Airworthiness Directives; Bombardier Model DHC-8-102, -103, -106, 
-201, -202, -301, -311, and -315 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, -106, -201, -202, -301, -311 
and -315 airplanes. This AD requires installation of check valves in 
Numbers 1 and 2 hydraulic systems, removal of the filters from the 
brake shuttle valves, and removal of the internal garter spring from 
the brake shuttle valves. This AD results from two instances of brake 
failure due to the loss of hydraulic fluid from both Numbers 1 and 2 
hydraulic systems and one incident of brake failure due to filter 
blockage in the shuttle valve. We are issuing this AD to prevent the 
loss of hydraulic power from both hydraulic systems, which could lead 
to reduced controllability of the airplane, and to prevent brake 
failure, which could result in the loss of directional control on the 
ground and consequent departure from the runway during landing.

DATES: This AD becomes effective July 12, 2005.
    The incorporation by reference of certain publications listed in 
the AD is approved by the Director of the Federal Register as of July 
12, 2005.

ADDRESSES: For service information identified in this AD, contact 
Bombardier, Inc., Bombardier Regional Aircraft Division, 123 Garratt 
Boulevard, Downsview, Ontario M3K 1Y5, Canada.
    Docket: The AD docket contains the proposed AD, comments, and any 
final disposition. You can examine the 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 U.S. 
Department of Transportation, 400 Seventh Street SW., room PL-401, 
Washington, DC. This docket number is FAA-2005-20756; the directorate 
identifier for this docket is 2004-NM-52-AD.

FOR FURTHER INFORMATION CONTACT: Ezra Sasson, 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) 228-7320; fax (516) 794-5531.

SUPPLEMENTARY INFORMATION: The FAA proposed to amend 14 CFR part 39 
with an AD for certain Bombardier Model DHC-8-102, -103, -106, -201, -
202, -301, -311, and -315 airplanes. That action, published in the 
Federal Register on March 30, 2005 (70 FR 16182), proposed to require 
installation of check valves in Numbers 1 and 2 hydraulic systems, 
removal of the filters from the brake shuttle valves, and removal of 
the internal garter spring from the brake shuttle valves.

Comments

    We provided the public the opportunity to participate in the 
development of this AD. No comments have been submitted on the proposed 
AD or on the determination of the cost to the public.

Explanation of Editorial Change

    We have revised the Costs of Compliance section of this AD to 
correct a mathematical error.

[[Page 32987]]

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       Parts         Cost per       registered     Average fleet cost
                                                                     rate per hour                     airplane        airplanes
--------------------------------------------------------------------------------------------------------------------------------------------------------
Installation of check valves in Numbers 1 and 2                  3             $65       $279-$405       $474-$600             179      $84,846-$107,400
 hydraulic systems................................
Removal of filters and internal garter springs                   3              65       252-1,360       447-1,555             179        80,013-278,345
 from brake shuttle valves........................
--------------------------------------------------------------------------------------------------------------------------------------------------------

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. 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 FAA amends Sec.  39.13 by adding the following new airworthiness 
directive (AD):

2005-11-10 Bombardier, Inc. (Formerly de Havilland, Inc.): Amendment 
39-14112. Docket No. FAA-2005-20756; Directorate Identifier 2004-NM-
52-AD.

Effective Date

    (a) This AD becomes effective July 12, 2005.

Affected ADs

    (b) None.

Applicability

    (c) This AD applies to Bombardier Model DHC-8-102, -103, -106, -
201, -202, -301, -311, and -315 airplanes, certificated in any 
category; serial numbers 003 through 593 inclusive.

Unsafe Condition

    (d) This AD was prompted by two instances of brake failure due 
to the loss of hydraulic fluid from both Numbers 1 and 2 hydraulic 
systems and one incident of brake failure due to filter blockage in 
the shuttle valve. We are issuing this AD to prevent the loss of 
hydraulic power from both hydraulic systems, which could lead to 
reduced controllability of the airplane, and to prevent brake 
failure, which could result in the loss of directional control on 
the ground and consequent departure from the runway during 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.

Installation of Check Valves in Numbers 1 and 2 Hydraulic Systems

    (f) Within 12 months after the effective date of this AD, 
install check valves in the Numbers 1 and 2 hydraulic return systems 
by incorporating Modsum 8Q101320 in accordance with the 
Accomplishment Instructions of Bombardier Service Bulletin 8-29-36, 
Revision ``B,'' dated January 6, 2003.

Removal of Filters and Internal Garter Spring From the Brake Shuttle 
Valves

    (g) Within 12 months after the effective date of this AD, modify 
the brake shuttle valves, part number (P/N) 5084-1, by doing the 
actions in either paragraph (g)(1) or (g)(2) of this AD. The 
installation specified in paragraph (f) of this AD must be done 
prior to doing any actions in accordance with Bombardier Service 
Bulletin 8-29-37, Revision ``A,'' dated September 19, 2003 (Modsum 
8Q101316), that are specified in paragraphs (g)(1) and (g)(2) of 
this AD.
    (1) Remove the filter assemblies by incorporating Modsum 
8Q101422 in accordance with the Accomplishment Instructions of 
Bombardier Service Bulletin 8-29-39, dated July 14, 2003; and within 
40,000 flight hours after removing the filter assemblies, remove the 
internal garter spring by incorporating Modsum 8Q101316 in 
accordance with the Accomplishment Instructions of Bombardier 
Service Bulletin 8-29-37, Revision ``A,'' dated September 19, 2003.
    (2) Remove the filter assemblies and internal garter spring by 
incorporating Modsum 8Q101316 in accordance with the Accomplishment 
Instructions of Bombardier Service Bulletin 8-29-37, Revision ``A,'' 
dated September 19, 2003.

    Note 1: You can mix shuttle valves that have incorporated either 
Modsum 8Q101316 or 8Q101422 on the same airplane.


[[Page 32988]]



Actions Accomplished According to Previous Issues of Service Bulletins

    (h) Installations accomplished before the effective date of this 
AD according to Bombardier Service Bulletin 8-29-36, dated December 
6, 2002; and Revision ``A,'' dated December 12, 2002, are considered 
acceptable for compliance with the corresponding installation 
specified in paragraph (f) of this AD.
    (i) Removals of the filters and internal garter springs 
accomplished before the effective date of this AD according to 
Bombardier Service Bulletin 8-29-37, dated July 15, 2003, are 
considered acceptable for compliance with the corresponding removals 
specified in paragraph (g) of this AD.

Alternative Methods of Compliance (AMOCs)

    (j) 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.

Related Information

    (k) Canadian airworthiness directive CF-2004-02, dated February 
9, 2004, also addresses the subject of this AD.

Material Incorporated by Reference

    (l) You must use the documents listed in Table 1 of this AD to 
perform the actions that are required by this AD, unless the AD 
specifies otherwise. The Director of the Federal Register approves 
the incorporation by reference of these documents in accordance with 
5 U.S.C. 552(a) and 1 CFR part 51. To get copies of the service 
information, contact Bombardier, Inc., Bombardier Regional Aircraft 
Division, 123 Garratt Boulevard, Downsview, Ontario M3K 1Y5, Canada. 
To view the AD docket, go to the Docket Management Facility, U.S. 
Department of Transportation, 400 Seventh Street SW., room PL-401, 
Nassif Building, Washington, DC. To review copies of the service 
information, go to the National Archives and Records Administration 
(NARA). For information on the availability of this material at the 
NARA, call (202) 741-6030, or go to http://www.archives.gov/
federal_register/code_of_federal_regulations/ibr_
locations.html.

              Table 1.--Material Incorporated by Reference
------------------------------------------------------------------------
  Bombardier service
       bulletin             Revision level                Date
------------------------------------------------------------------------
8-29-36...............  B.....................  January 6, 2003.
8-29-37...............  A.....................  September 19, 2003.
8-29-39...............  Original..............  July 14, 2003.
------------------------------------------------------------------------


    Issued in Renton, Washington, on May 26, 2005.
Ali Bahrami,
Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 05-11054 Filed 6-6-05; 8:45 am]
BILLING CODE 4910-13-P