Airworthiness Directives; Bombardier Model DHC-8-102, -03, -106, -201, -202, -301, -311, and -315 Airplanes, 16182-16185 [05-6253]

Download as PDF 16182 Federal Register / Vol. 70, No. 60 / Wednesday, March 30, 2005 / Proposed Rules 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 proposed AD would not have federalism implications under Executive Order 13132. This proposed AD would 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 the proposed regulation: 1. Is not a ‘‘significant regulatory action’’ under Executive Order 12866; 2. Is not a ‘‘significant rule’’ under the 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 proposed 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, Safety. The Proposed Amendment Accordingly, under the authority delegated to me by the Administrator, the FAA proposes to amend 14 CFR part 39 as follows: PART 39—AIRWORTHINESS DIRECTIVES 1. The authority citation for part 39 continues to read as follows: 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): Empresa Brasileira de Aeronautica S.A. (EMBRAER): Docket No. FAA–2005– VerDate jul<14>2003 14:59 Mar 29, 2005 Jkt 205001 20728; Directorate Identifier 2005–NM– 003–AD. Comments Due Date (a) The Federal Aviation Administration must receive comments on this AD action by April 29, 2005. Affected ADs (b) None. Applicability (c) This AD applies to Model EMB–145 and –135 series airplanes; certificated in any category; as identified in EMBRAER Service Bulletin 145–27–0106, Revision 01 (for Model EMB–145 and EMB–135 series airplanes, except for EMB–135BJ series airplanes), and EMBRAER Service Bulletin 145LEG–27–0016, Revision 01 (for Model EMB–135BJ series airplanes); both dated August 30, 2004. Unsafe Condition (d) This AD was prompted by reports of loss of the pitch trim system due to a simultaneous failure of both channels of the horizontal stabilizer control unit (HSCU). We are issuing this AD to prevent loss of pitch trim and reduced controllability of the airplane. 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. Replacement (f) Within 18 months or 4,000 flight hours after the effective date of this AD, whichever occurs first, replace the HSCU with a modified and reidentified or new, improved HSCU, part number 362100–1013, by doing all the actions specified in the Accomplishment Instructions of EMBRAER Service Bulletin 145–27–0106, Revision 01; or EMBRAER Service Bulletin 145LEG–27– 0016, Revision 01; both dated August 30, 2004; as applicable. Related AD (g) For airplanes identified in paragraph 1.C (1) of EMBRAER Service Bulletins 145– 27–0106, Revision 01, and 145LEG–27–0016, Revision 01, both dated August 30, 2004: Prior to or concurrently with the actions required by paragraph (f) of this AD, replace the HSCU with a new HSCU with improved features, and having a new part number, in accordance with EMBRAER Service Bulletins 145LEG–27–0002, Revision 01, dated April 15, 2003, or 145–27–0084, Revision 04, dated October 21, 2003, as applicable. These actions are currently required by AD 2004– 25–21, amendment 39–13909 (69 FR 76605, December 22, 2004). Actions Accomplished Per Previous Issue of Service Bulletin (h) Actions accomplished before the effective date of this AD in accordance with EMBRAER Service Bulletin 145–27–0106, and EMBRAER Service Bulletin 145LEG–27– 0016; both dated August 4, 2004; are considered acceptable for compliance with the applicable action in this AD. PO 00000 Frm 00022 Fmt 4702 Sfmt 4702 Alternative Methods of Compliance (AMOCs) (i) 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. Related Information (j) Brazilian airworthiness directive 2004– 11–01, dated November 28, 2004, also addresses the subject of this AD. Issued in Renton, Washington, on March 18, 2005. Ali Bahrami, Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 05–6252 Filed 3–29–05; 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] RIN 2120–AA64 Airworthiness Directives; Bombardier Model DHC–8–102, –03, –106, –201, –202, –301, –311, and –315 Airplanes Federal Aviation Administration (FAA), Department of Transportation (DOT). ACTION: Notice of proposed rulemaking (NPRM). AGENCY: SUMMARY: The FAA proposes to adopt a new airworthiness directive (AD) for certain Bombardier Model DHC–8–102, –103, –106, –201, –202, –301, –311 and –315 airplanes. This proposed AD would 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. This proposed 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 proposing 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: We must receive comments on this proposed AD by April 29, 2005. ADDRESSES: Use one of the following addresses to submit comments on this proposed AD. E:\FR\FM\30MRP1.SGM 30MRP1 Federal Register / Vol. 70, No. 60 / Wednesday, March 30, 2005 / Proposed Rules • DOT Docket Web site: Go to https://dms.dot.gov and follow the instructions for sending your comments electronically. • Government-wide rulemaking Web site: Go to https://www.regulations.gov and follow the instructions for sending your comments electronically. • Mail: Docket Management Facility, U.S. Department of Transportation, 400 Seventh Street SW., Nassif Building, room PL–401, Washington, DC 20590. • By fax: (202) 493–2251. • Hand Delivery: Room PL–401 on the plaza level of the Nassif Building, 400 Seventh Street SW., Washington, DC, between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. For service information identified in this proposed AD, contact Bombardier, Inc., Bombardier Regional Aircraft Division, 123 Garratt Boulevard, Downsview, Ontario M3K 1Y5, Canada. You can examine the contents of this AD docket on the Internet at https:// dms.dot.gov, or in person at the Docket Management Facility, U.S. Department of Transportation, 400 Seventh Street SW., room PL–401, on the plaza level of the Nassif Building, 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: Comments Invited We invite you to submit any relevant written data, views, or arguments regarding this proposed AD. Send your comments to an address listed under ADDRESSES. Include ‘‘Docket No. FAA– 2005–20756; Directorate Identifier 2004–NM–52–AD at the beginning of your comments. We specifically invite comments on the overall regulatory, economic, environmental, and energy aspects of the proposed AD. We will consider all comments submitted by the closing date and may amend the proposed AD in light of those comments. We will post all comments we receive, without change, to https:// dms.dot.gov, including any personal information you provide. We will also post a report summarizing each substantive verbal contact with FAA personnel concerning this proposed AD. Using the search function of our docket Web site, anyone can find and read the comments in any of our dockets, VerDate jul<14>2003 14:59 Mar 29, 2005 Jkt 205001 including the name of the individual who sent the comment (or signed the comment on behalf of an association, business, labor union, etc.). You can review the DOT’s complete Privacy Act Statement in the Federal Register published on April 11, 2000 (65 FR 19477–78), or you can visit https:// dms.dot.gov. Examining the Docket You can examine the AD docket on the Internet at https://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 DOT street address stated in the ADDRESSES section. Comments will be available in the AD docket shortly after the DMS receives them. Discussion Transport Canada Civil Aviation (TCCA), which is the airworthiness authority for Canada, notified us that an unsafe condition may exist on certain Bombardier Model DHC–8–102, –103, –106, –201, –202, –301, –311, and –315 airplanes. TCCA advises that there have been two instances during which the Numbers 1 and 2 hydraulic systems power was lost due to a hydraulic leak downstream of one of the brake shuttle valves. Investigation revealed that a minor leak in one of the brake units allowed the Number 2 hydraulic system fluid to deplete. In addition, the shuttle valve internal garter spring had also failed. This failure allowed the Number 1 hydraulic system fluid to also deplete through the same brake unit. This condition, if not corrected, could result in loss of hydraulic power from both hydraulic systems, which could lead to reduced controllability of the airplane. An additional incident has been reported of a brake seizure and subsequent wheel assembly fire while the airplane was taxiing. An investigation revealed that hydraulic pressure remained applied to the brake unit even after brake release. It was determined that the dislodging of the 10-micron filter in the brake shuttle valve had blocked the valve port and prevented hydraulic fluid flow from the brake. Brake failure could result in the loss of directional control on the ground and consequent departure from the runway during landing. Relevant Service Information Bombardier Inc. has issued Service Bulletin S.B. 8–29–36, Revision ‘‘B,’’ dated January 6, 2003, that describes PO 00000 Frm 00023 Fmt 4702 Sfmt 4702 16183 procedures for installing check valves in the Numbers 1 and 2 hydraulic systems by incorporating Modsum 8Q101320. Bombardier has also issued S.B. 8–29– 37, Revision ‘‘A,’’ dated September 19, 2003, that provides instructions for incorporating Modsum 8Q101316 to remove the filter assemblies and internal garter spring, and S.B. 8–29–39, dated July 14, 2003, that includes instructions for incorporating Modsum 8Q101422 to remove the filter assemblies. Accomplishing the actions specified in the service information is intended to adequately address the unsafe condition. TCCA mandated the service information and issued Canadian airworthiness directive CF– 2004–02, dated February 9, 2004, to ensure the continued airworthiness of these airplanes in Canada. FAA’s Determination and Requirements of the Proposed AD These airplane models are manufactured in Canada and are type certificated for operation in the United States under the provisions of section 21.29 of the Federal Aviation Regulations (14 CFR 21.29) and the applicable bilateral airworthiness agreement. Pursuant to this bilateral airworthiness agreement, TCCA has kept the FAA informed of the situation described above. We have examined TCCA’s findings, evaluated all pertinent information, and determined that we need to issue an AD for products of this type design that are certificated for operation in the United States. Therefore, we are proposing this AD, which would require installation of check valves in Numbers 1 and 2 hydraulic systems, removal of filters from the brake shuttle valves and removal of the internal garter spring from the brake shuttle valves. The proposed AD would require you to use the service information described previously to perform these actions, except as discussed under ‘‘Differences Between the Proposed AD and Canadian Airworthiness Directive.’’ Differences Between the Proposed AD and Canadian Airworthiness Directive Although the Canadian airworthiness directive recommends, for airplanes that removed the filters from the brake shuttle valve, removal of the internal garter spring at the next overhaul of each brake shuttle valve, we have determined that a specific compliance time is needed. In developing appropriate compliance times for this proposed AD, we considered not only the manufacturer’s recommendation, but also the degree of urgency associated with addressing the subject E:\FR\FM\30MRP1.SGM 30MRP1 16184 Federal Register / Vol. 70, No. 60 / Wednesday, March 30, 2005 / Proposed Rules unsafe condition, and the average utilization of the affected fleet. Considering these factors, we find that after removing the filters, a compliance time of 40,000 flight hours for the removal of the internal garter spring is warranted. We have coordinated this issue with TCCA. Costs of Compliance The following table provides the estimated costs for U.S. operators to comply with this proposed AD: ESTIMATED COSTS Action Work hours 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 proposed AD would not have federalism implications under Executive Order 13132. This proposed AD would 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 the proposed regulation: 1. Is not a ‘‘significant regulatory action’’ under Executive Order 12866; 2. Is not a ‘‘significant rule’’ under the 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 proposed AD. See the ADDRESSES Jkt 205001 Number of U.S.-registered airplanes Average fleet cost $65 $279–$405 $444–$600 179 $79,476–$107,400 3 The FAA’s authority to issue rules regarding aviation safety is found in Title 49 of the United States Code. 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. This rulemaking is promulgated 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 proposed AD. 14:59 Mar 29, 2005 Cost per airplane Parts 3 Authority for This Rulemaking VerDate jul<14>2003 Average labor rate per hour 65 252–1,360 447–1,555 179 80,013–278,345 section for a location to examine the regulatory evaluation. List of Subjects in 14 CFR Part 39 Air transportation, Aircraft, Aviation safety, Safety. The Proposed Amendment Accordingly, under the authority delegated to me by the Administrator, the FAA proposes to amend 14 CFR part 39 as follows: PART 39—AIRWORTHINESS DIRECTIVES 1. The authority citation for part 39 continues to read as follows: 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): Bombardier, Inc. (Formerly de Havilland, Inc.): Docket No. FAA–2005–20756; Directorate Identifier 2004–NM–52–AD. Comments Due Date (a) The Federal Aviation Administration must receive comments on this AD action by April 29, 2005. Affected ADs (b) None. Applicability (c) This AD applies to Bombardier Model DHC–8–102, –103, –106, –201, –202, –301, –311, and –315, certificated in any category; serial numbers 003 through 593 inclusive. Unsafe Condition (d) 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 proposing 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. PO 00000 Frm 00024 Fmt 4702 Sfmt 4702 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 S.B. 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 S.B. 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 S.B. 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 S.B. 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 S.B. 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. Actions Accomplished According to Previous Issues of Service Bulletins (h) Installations accomplished before the effective date of this AD according to Bombardier Service Bulletin S.B. 8–29–36, E:\FR\FM\30MRP1.SGM 30MRP1 Federal Register / Vol. 70, No. 60 / Wednesday, March 30, 2005 / Proposed Rules 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 S.B. 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. Issued in Renton, Washington, on March 22, 2005. Ali Bahrami, Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 05–6253 Filed 3–29–05; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2005–20757; Directorate Identifier 2004–NM–192–AD] RIN 2120–AA64 Airworthiness Directives; BAE Systems (Operations) Limited Model BAe 146 and Avro 146–RJ Series Airplanes Federal Aviation Administration (FAA), Department of Transportation (DOT). ACTION: Notice of proposed rulemaking (NPRM). AGENCY: SUMMARY: The FAA proposes to adopt a new airworthiness directive (AD) for certain BAE Systems (Operations) Limited Model BAe 146 and Avro 146– RJ series airplanes. This proposed AD would require modifying the auxiliary power unit (APU) exhaust duct in the environmental control system (ECS) bay; installing new, improved insulation on this APU exhaust duct; and replacing the existing drain pipe with a new exhaust drain pipe blank. This proposed AD is prompted by a determination that the temperature of the skin of the APU exhaust duct in the ECS bay is higher than the certificated maximum VerDate jul<14>2003 14:59 Mar 29, 2005 Jkt 205001 temperature for this area. We are proposing this AD to prevent the potential for ignition of fuel or hydraulic fluid, which could leak from pipes running through the ECS bay. Ignition of these flammable fluids could result in a fire in the ECS bay. DATES: We must receive comments on this proposed AD by April 29, 2005. ADDRESSES: Use one of the following addresses to submit comments on this proposed AD. • DOT Docket Web site: Go to https://dms.dot.gov and follow the instructions for sending your comments electronically. • Government-wide rulemaking web site: Go to https://www.regulations.gov and follow the instructions for sending your comments electronically. • Mail: Docket Management Facility, U.S. Department of Transportation, 400 Seventh Street SW., Nassif Building, room PL–401, Washington, DC 20590. • By fax: (202) 493–2251. • Hand Delivery: Room PL–401 on the plaza level of the Nassif Building, 400 Seventh Street SW., Washington, DC, between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. For service information identified in this proposed AD, contact British Aerospace Regional Aircraft American Support, 13850 Mclearen Road, Herndon, Virginia 20171. You can examine the contents of this AD docket on the Internet at https:// dms.dot.gov, or in person at the Docket Management Facility, U.S. Department of Transportation, 400 Seventh Street SW., room PL–401, on the plaza level of the Nassif Building, Washington, DC. This docket number is FAA–2005– 20757; the directorate identifier for this docket is 2004–NM–192–AD. FOR FURTHER INFORMATION CONTACT: Dan Rodina, Aerospace Engineer, International Branch, ANM–116, FAA, Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton, Washington 98055–4056; telephone (425) 227–2125; fax (425) 227–1149. SUPPLEMENTARY INFORMATION: Comments Invited We invite you to submit any relevant written data, views, or arguments regarding this proposed AD. Send your comments to an address listed under ADDRESSES. Include ‘‘Docket No. FAA– 2005–20757; Directorate Identifier 2004–NM–192–AD’’ at the beginning of your comments. We specifically invite comments on the overall regulatory, economic, environmental, and energy aspects of the proposed AD. We will consider all comments submitted by the closing date and may amend the PO 00000 Frm 00025 Fmt 4702 Sfmt 4702 16185 proposed AD in light of those comments. We will post all comments we receive, without change, to https:// dms.dot.gov, including any personal information you provide. We will also post a report summarizing each substantive verbal contact with FAA personnel concerning this proposed AD. Using the search function of our docket Web site, anyone can find and read the comments in any of our dockets, including the name of the individual who sent the comment (or signed the comment on behalf of an association, business, labor union, etc.). You can review the DOT’s complete Privacy Act Statement in the Federal Register published on April 11, 2000 (65 FR 19477–78), or you can visit https:// dms.dot.gov. Examining the Docket You can examine the AD docket on the Internet at https://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 DOT street address stated in the ADDRESSES section. Comments will be available in the AD docket shortly after the DMS receives them. Discussion The Civil Aviation Authority (CAA), which is the airworthiness authority for the United Kingdom, notified us that an unsafe condition may exist on certain BAE Systems (Operations) Limited Model BAe 146 and Avro 146–RJ series airplanes. The CAA advises that it has determined that the temperature of the skin of the auxiliary power unit (APU) exhaust duct in the environmental control system (ECS) bay is higher than the certificated maximum temperature for this area. The ECS bay is not a designated fire zone; therefore, there is no fire detection or suppression system. Also, ventilation airflow around the APU exhaust duct is low. Pipes carrying fuel and hydraulic fluid run through the ECS bay. Should these pipes leak flammable fluids, the excessive temperature of the APU exhaust duct skin could present an ignition source. This condition, if not corrected, could result in a fire in the ECS bay. Relevant Service Information BAE Systems (Operations) Limited has issued Modification Service Bulletin SB.49–072–36244A, dated October 11, 2004. The service bulletin describes procedures for modifying the APU E:\FR\FM\30MRP1.SGM 30MRP1

Agencies

[Federal Register Volume 70, Number 60 (Wednesday, March 30, 2005)]
[Proposed Rules]
[Pages 16182-16185]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 05-6253]


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

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2005-20756; Directorate Identifier 2004-NM-52-AD]
RIN 2120-AA64


Airworthiness Directives; Bombardier Model DHC-8-102, -03, -106, 
-201, -202, -301, -311, and -315 Airplanes

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

ACTION: Notice of proposed rulemaking (NPRM).

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

SUMMARY: The FAA proposes to adopt a new airworthiness directive (AD) 
for certain Bombardier Model DHC-8-102, -103, -106, -201, -202, -301, -
311 and -315 airplanes. This proposed AD would 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. This proposed 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 proposing 
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: We must receive comments on this proposed AD by April 29, 2005.

ADDRESSES: Use one of the following addresses to submit comments on 
this proposed AD.

[[Page 16183]]

     DOT Docket Web site: Go to https://dms.dot.gov and follow 
the instructions for sending your comments electronically.
     Government-wide rulemaking Web site: Go to https://
www.regulations.gov and follow the instructions for sending your 
comments electronically.
     Mail: Docket Management Facility, U.S. Department of 
Transportation, 400 Seventh Street SW., Nassif Building, room PL-401, 
Washington, DC 20590.
     By fax: (202) 493-2251.
     Hand Delivery: Room PL-401 on the plaza level of the 
Nassif Building, 400 Seventh Street SW., Washington, DC, between 9 a.m. 
and 5 p.m., Monday through Friday, except Federal holidays.
    For service information identified in this proposed AD, contact 
Bombardier, Inc., Bombardier Regional Aircraft Division, 123 Garratt 
Boulevard, Downsview, Ontario M3K 1Y5, Canada.
    You can examine the contents of this AD docket on the Internet at 
https://dms.dot.gov, or in person at the Docket Management Facility, 
U.S. Department of Transportation, 400 Seventh Street SW., room PL-401, 
on the plaza level of the Nassif Building, 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:

Comments Invited

    We invite you to submit any relevant written data, views, or 
arguments regarding this proposed AD. Send your comments to an address 
listed under ADDRESSES. Include ``Docket No. FAA-2005-20756; 
Directorate Identifier 2004-NM-52-AD at the beginning of your comments. 
We specifically invite comments on the overall regulatory, economic, 
environmental, and energy aspects of the proposed AD. We will consider 
all comments submitted by the closing date and may amend the proposed 
AD in light of those comments.
    We will post all comments we receive, without change, to https://
dms.dot.gov, including any personal information you provide. We will 
also post a report summarizing each substantive verbal contact with FAA 
personnel concerning this proposed AD. Using the search function of our 
docket Web site, anyone can find and read the comments in any of our 
dockets, including the name of the individual who sent the comment (or 
signed the comment on behalf of an association, business, labor union, 
etc.). You can review the DOT's complete Privacy Act Statement in the 
Federal Register published on April 11, 2000 (65 FR 19477-78), or you 
can visit https://dms.dot.gov.

Examining the Docket

    You can examine the AD docket on the Internet at https://
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 DOT 
street address stated in the ADDRESSES section. Comments will be 
available in the AD docket shortly after the DMS receives them.

Discussion

    Transport Canada Civil Aviation (TCCA), which is the airworthiness 
authority for Canada, notified us that an unsafe condition may exist on 
certain Bombardier Model DHC-8-102, -103, -106, -201, -202, -301, -311, 
and -315 airplanes. TCCA advises that there have been two instances 
during which the Numbers 1 and 2 hydraulic systems power was lost due 
to a hydraulic leak downstream of one of the brake shuttle valves. 
Investigation revealed that a minor leak in one of the brake units 
allowed the Number 2 hydraulic system fluid to deplete. In addition, 
the shuttle valve internal garter spring had also failed. This failure 
allowed the Number 1 hydraulic system fluid to also deplete through the 
same brake unit. This condition, if not corrected, could result in loss 
of hydraulic power from both hydraulic systems, which could lead to 
reduced controllability of the airplane.
    An additional incident has been reported of a brake seizure and 
subsequent wheel assembly fire while the airplane was taxiing. An 
investigation revealed that hydraulic pressure remained applied to the 
brake unit even after brake release. It was determined that the 
dislodging of the 10-micron filter in the brake shuttle valve had 
blocked the valve port and prevented hydraulic fluid flow from the 
brake. Brake failure could result in the loss of directional control on 
the ground and consequent departure from the runway during landing.

Relevant Service Information

    Bombardier Inc. has issued Service Bulletin S.B. 8-29-36, Revision 
``B,'' dated January 6, 2003, that describes procedures for installing 
check valves in the Numbers 1 and 2 hydraulic systems by incorporating 
Modsum 8Q101320. Bombardier has also issued S.B. 8-29-37, Revision 
``A,'' dated September 19, 2003, that provides instructions for 
incorporating Modsum 8Q101316 to remove the filter assemblies and 
internal garter spring, and S.B. 8-29-39, dated July 14, 2003, that 
includes instructions for incorporating Modsum 8Q101422 to remove the 
filter assemblies. Accomplishing the actions specified in the service 
information is intended to adequately address the unsafe condition. 
TCCA mandated the service information and issued Canadian airworthiness 
directive CF-2004-02, dated February 9, 2004, to ensure the continued 
airworthiness of these airplanes in Canada.

FAA's Determination and Requirements of the Proposed AD

    These airplane models are manufactured in Canada and are type 
certificated for operation in the United States under the provisions of 
section 21.29 of the Federal Aviation Regulations (14 CFR 21.29) and 
the applicable bilateral airworthiness agreement. Pursuant to this 
bilateral airworthiness agreement, TCCA has kept the FAA informed of 
the situation described above. We have examined TCCA's findings, 
evaluated all pertinent information, and determined that we need to 
issue an AD for products of this type design that are certificated for 
operation in the United States.
    Therefore, we are proposing this AD, which would require 
installation of check valves in Numbers 1 and 2 hydraulic systems, 
removal of filters from the brake shuttle valves and removal of the 
internal garter spring from the brake shuttle valves. The proposed AD 
would require you to use the service information described previously 
to perform these actions, except as discussed under ``Differences 
Between the Proposed AD and Canadian Airworthiness Directive.''

Differences Between the Proposed AD and Canadian Airworthiness 
Directive

    Although the Canadian airworthiness directive recommends, for 
airplanes that removed the filters from the brake shuttle valve, 
removal of the internal garter spring at the next overhaul of each 
brake shuttle valve, we have determined that a specific compliance time 
is needed. In developing appropriate compliance times for this proposed 
AD, we considered not only the manufacturer's recommendation, but also 
the degree of urgency associated with addressing the subject

[[Page 16184]]

unsafe condition, and the average utilization of the affected fleet. 
Considering these factors, we find that after removing the filters, a 
compliance time of 40,000 flight hours for the removal of the internal 
garter spring is warranted. We have coordinated this issue with TCCA.

Costs of Compliance

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

                                                                     Estimated Costs
--------------------------------------------------------------------------------------------------------------------------------------------------------
                                                                                                                     Number of
                                                                            Average                    Cost per        U.S.-
                          Action                            Work hours    labor rate       Parts       airplane     registered      Average fleet cost
                                                                           per hour                                  airplanes
--------------------------------------------------------------------------------------------------------------------------------------------------------
Installation of check valves in Numbers 1 and 2 hydraulic             3           $65     $279-$405     $444-$600           179         $79,476-$107,400
 systems.................................................
Removal of filters and internal garter springs from brake             3            65     252-1,360     447-1,555           179           80,013-278,345
 shuttle valves..........................................
--------------------------------------------------------------------------------------------------------------------------------------------------------

Authority for This Rulemaking

    The FAA's authority to issue rules regarding aviation safety is 
found in Title 49 of the United States Code. 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.
    This rulemaking is promulgated 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 
proposed AD.

Regulatory Findings

    We have determined that this proposed AD would not have federalism 
implications under Executive Order 13132. This proposed AD would 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 the proposed 
regulation:
    1. Is not a ``significant regulatory action'' under Executive Order 
12866;
    2. Is not a ``significant rule'' under the 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 proposed 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, Safety.

The Proposed Amendment

    Accordingly, under the authority delegated to me by the 
Administrator, the FAA proposes to amend 14 CFR part 39 as follows:

PART 39--AIRWORTHINESS DIRECTIVES

    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]

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

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

Comments Due Date

    (a) The Federal Aviation Administration must receive comments on 
this AD action by April 29, 2005.

Affected ADs

    (b) None.

Applicability

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

Unsafe Condition

    (d) 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 proposing 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 S.B. 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 S.B. 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 S.B. 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 S.B. 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 S.B. 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.

Actions Accomplished According to Previous Issues of Service Bulletins

    (h) Installations accomplished before the effective date of this 
AD according to Bombardier Service Bulletin S.B. 8-29-36,

[[Page 16185]]

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 S.B. 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.

    Issued in Renton, Washington, on March 22, 2005.
Ali Bahrami,
Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 05-6253 Filed 3-29-05; 8:45 am]
BILLING CODE 4910-13-P
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