Airworthiness Directives; Bombardier Model DHC-8-400 Series Airplanes, 39244-39247 [E6-10912]

Download as PDF 39244 Federal Register / Vol. 71, No. 133 / Wednesday, July 12, 2006 / Proposed Rules it is determined that this proposal would not have federalism implications under Executive Order 13132. For the reasons discussed above, I certify that this 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) if promulgated, 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. A copy of the draft regulatory evaluation prepared for this action is contained in the Rules Docket. A copy of it may be obtained by contacting the Rules Docket at the location provided under the caption ADDRESSES. List of Subjects in 14 CFR Part 39 Air transportation, Aircraft, Aviation safety, Safety. The Proposed Amendment Accordingly, pursuant to the authority delegated to me by the Administrator, the Federal Aviation Administration proposes to amend part 39 of the Federal Aviation Regulations (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] wwhite on PROD1PC61 with PROPOSALS 2. Section 39.13 is amended by adding the following new airworthiness directive: Gulfstream Aerospace Corporation: Docket 96–NM–143–AD. Applicability: All Model G–159 airplanes, certificated in any category. Compliance: Required as indicated, unless accomplished previously. To detect and correct corrosion and cracking of the spot-welded skins of the lower wing plank splices and certain structural assemblies, which could result in reduced controllability of the airplane, accomplish the following: Note 1: A note in the Accomplishment Instructions of the Gulfstream customer bulletin instructs operators to contact Gulfstream if any difficulty is encountered in accomplishing the customer bulletin. However, any deviation from the instructions provided in the customer bulletin must be approved as an alternative method of compliance (AMOC) under paragraph (h) of this AD. Non-Destructive Testing Inspections of the Fuselage, Empennage, and Flight Controls (a) Within 9 months after the effective date of this AD, perform a non-destructive test VerDate Aug<31>2005 18:09 Jul 11, 2006 Jkt 208001 (NDT) to detect corrosion of the skins of the elevators, ailerons, rudder and rudder trim tab, flaps, aft lower fuselage, and vertical and horizontal stabilizers; in accordance with the Accomplishment Instructions of Gulfstream GI Customer Bulletin (CB) 337B, including Appendix A, dated August 17, 2005. The corrosion criteria must be determined by the Manager, Atlanta Aircraft Certification Office (ACO), FAA. Gulfstream Tool ST905–377 is also an acceptable method of determining the corrosion criteria. (1) If no corrosion or cracking is detected, repeat the inspection thereafter at intervals not to exceed 18 months. (2) If any corrosion is detected that meets the criteria of ‘‘light’’ or ‘‘mild’’ corrosion, repeat the NDT inspections of that component thereafter at intervals not to exceed 12 months. (3) If any corrosion is detected that meets the criteria of ‘‘moderate’’ corrosion: Within 9 months after the initial inspection, repeat the NDT inspection of that component, and within 18 months since the initial inspection, repair or replace the component with a serviceable component in accordance with the CB. (4) If any corrosion is detected that meets the criteria of ‘‘severe’’ corrosion, before further flight, replace the component with a serviceable component in accordance with the CB. Existing Repairs (b) If any existing repairs are found during the inspections required by paragraph (a) of this AD, before further flight, ensure that the repairs are in accordance with a method approved by the Manager, Atlanta ACO. Inspections of the Lower Wing Plank (c) Except as provided in paragraph (f) of this AD: Within 9 months after the effective date of this AD, perform NDT inspections to detect corrosion and cracking of the lower wing plank splices, in accordance with the Accomplishment Instructions of Gulfstream GI CB 337B, including Appendix A, dated August 17, 2005. (1) If no corrosion or cracking is detected, repeat the NDT inspection at intervals not to exceed 18 months. (2) If any corrosion or cracking is detected, before further flight, perform all applicable investigative actions and corrective actions in accordance with the customer bulletin. Repair Removal Threshold (d) For repairs specified in Appendix A of Gulfstream GI CB 337B, dated August 17, 2005: Within 144 months after the date of the repair installation, remove the repaired component and replace it with a new or serviceable component, in accordance with Gulfstream GI CB 337B, including Appendix A, dated August 17, 2005. Prior Blending in the Riser Areas (e) If, during the performance of the inspections required by paragraph (c) or (f) of this AD, the inspection reveals that prior blending has been performed on the riser areas: Before further flight, perform an eddy current or fluorescent penetrant inspection, as applicable, to evaluate the blending, and accomplish appropriate corrective actions, in PO 00000 Frm 00010 Fmt 4702 Sfmt 4702 accordance with the Accomplishment Instructions of Gulfstream GI CB 337B, including Appendix A, dated August 17, 2005. If any blend-out is outside the limits specified in the CB, before further flight, repair in a manner approved by the Manager, Atlanta ACO. For Airplanes With New Lower Wing Planks (f) For airplanes with new lower wing planks: Within 144 months after replacement of the lower wing planks with new lower wing planks, or within 9 months after the effective date of this AD, whichever occurs later, perform all of the actions, including any other related investigative actions and corrective actions, specified in paragraph (c) of this AD. Reporting Requirement (g) Within 30 days of performing the inspections required by this AD: Submit a report of inspection findings (both positive and negative) to Gulfstream Aerospace Corporation; Attention: Technical Operations—Structures Group, Dept. 893, Mail Station D–25, 500 Gulfstream Road, Savannah, Georgia 31408. Information collection requirements contained in this regulation have been approved by the Office of Management and Budget (OMB) under the provisions of the Paperwork Reduction Act of 1980 (44 U.S.C. 3501 et seq.) and have been assigned OMB Control Number 2120–0056. Alternative Methods of Compliance (h)(1) The Manager, Atlanta ACO, has the authority to approve AMOCs for this AD, if requested in accordance with the procedures found in 14 CFR 39.19. (2) Before using any AMOC approved in accordance with § 39.19 on any airplane to which the AMOC applies, notify the appropriate principal inspector in the FAA Flight Standards Certificate Holding District Office. Issued in Renton, Washington, on June 30, 2006. Kalene C. Yanamura, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. E6–10911 Filed 7–11–06; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2006–25328; Directorate Identifier 2006–NM–130–AD] RIN 2120–AA64 Airworthiness Directives; Bombardier Model DHC–8–400 Series Airplanes Federal Aviation Administration (FAA), Department of Transportation (DOT). ACTION: Notice of proposed rulemaking (NPRM). AGENCY: E:\FR\FM\12JYP1.SGM 12JYP1 Federal Register / Vol. 71, No. 133 / Wednesday, July 12, 2006 / Proposed Rules SUMMARY: The FAA proposes to adopt a new airworthiness directive (AD) for certain Bombardier Model DHC–8–400 series airplanes. This proposed AD would require inspecting for fouling and chafing damage of the outboard brake control cable of the main landing gear, replacing the control cable if necessary, reworking the control cable cover, and, if applicable, manufacturing/installing an offset plate on the control cable cover. This proposed AD is prompted by a review of brake control cable operation conducted by the manufacturer. We are proposing this AD to prevent abrasion and wear of the outboard brake control cable, which could lead to cable separation and reduced control of airplane braking. DATES: We must receive comments on this proposed AD by August 11, 2006. 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. • 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. Contact Bombardier, Inc., Bombardier Regional Aircraft Division, 123 Garratt Boulevard, Downsview, Ontario M3K 1Y5, Canada, for service information identified in this proposed AD. FOR FURTHER INFORMATION CONTACT: Ezra Sasson, Aerospace Engineer, Systems and Flight Test Branch, ANE–172, FAA, New York Aircraft Certification Office, 1600 Stewart Avenue, suite 410, Westbury, New York 11590; telephone (516) 228–7320; fax (516) 794–5531. SUPPLEMENTARY INFORMATION: Comments Invited wwhite on PROD1PC61 with PROPOSALS We invite you to submit any relevant written data, views, or arguments regarding this proposed AD. Send your comments to an address listed in the VerDate Aug<31>2005 18:09 Jul 11, 2006 Jkt 208001 section. Include the docket number ‘‘FAA–2006–25328; Directorate Identifier 2006–NM–130–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 received 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 that 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 may review the DOT’s complete Privacy Act Statement in the Federal Register published on April 11, 2000 (65 FR 19477–78), or you may visit https:// dms.dot.gov. ADDRESSES Examining the Docket You may 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 Docket Management System 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–8–400 series airplanes. TCCA advises that a review conducted by the manufacturer revealed that the outboard brake control cable can become fouled on two fasteners on the pilot’s bulkhead cover assembly. This condition, if not corrected, could result in abrasion and wear of the outboard brake control cable, which could lead to cable separation and reduced control of airplane braking. PO 00000 Frm 00011 Fmt 4702 Sfmt 4702 39245 Relevant Service Information Bombardier has issued Service Bulletin 84–53–37, Revision ‘C,’ dated December 5, 2005. The service bulletin describes procedures for inspecting for fouling and chafing damage of the main landing gear outboard brake control cable, replacing the control cable if necessary, reworking the control cable cover, and, if not already installed, manufacturing/installing an offset plate on the control cable cover. 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–2006–05, dated March 31, 2006, 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 airplanes of this type design that are certificated for operation in the United States. Therefore, we are proposing this AD, which would require accomplishing the actions specified in the service information described previously, except as discussed under ‘‘Clarification of Inspection Terminology.’’ Clarification of Inspection Terminology The service bulletin specifies a ‘‘visual inspection;’’ however, this proposed AD would require a ‘‘general visual inspection.’’ We have included the definition of a general visual inspection in a note in the proposed AD. Costs of Compliance The following table provides the estimated costs for U.S. operators to comply with this proposed AD, at an average labor rate of $80 per work hour. E:\FR\FM\12JYP1.SGM 12JYP1 39246 Federal Register / Vol. 71, No. 133 / Wednesday, July 12, 2006 / Proposed Rules ESTIMATED COSTS Work hours Action Inspect brake cable ....................................................................................... Rework cable cover ...................................................................................... Manufacture/ install offset plate, as applicable ............................................. 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. wwhite on PROD1PC61 with PROPOSALS 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 and placed it in the AD docket. See the ADDRESSES section for a location to examine the regulatory evaluation. VerDate Aug<31>2005 18:09 Jul 11, 2006 Jkt 208001 1 3 3 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. [Amended] 2. The Federal Aviation Administration (FAA) amends § 39.13 by adding the following new airworthiness directive (AD): Bombardier, Inc. (Formerly de Havilland, Inc.): Docket No. FAA–2006–25328; Directorate Identifier 2006–NM–130–AD. Comments Due Date (a) The FAA must receive comments on this AD action by August 11, 2006. Affected ADs (b) None. Applicability (c) This AD applies to Bombardier Model DHC–8–400 series airplanes, certificated in any category; having serial numbers 4003, 4004, 4006, 4008 through 4064 inclusive, 4072, and 4073. Unsafe Condition (d) This AD results from a review of brake control cable operation conducted by the manufacturer. We are issuing this AD to prevent abrasion and wear of the outboard brake control cable, which could lead to cable separation and reduced control of airplane braking. 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. Inspection of Control Cable (f) Within 12 months after the effective date of this AD, perform a general visual inspection for fouling and chafing damage of the outboard brake control cable of the main landing gear, in accordance with the Accomplishment Instructions of Bombardier PO 00000 Frm 00012 Fmt 4702 Sfmt 4702 Number of U.S.registered airplanes Fleet cost $80 240 440 17 .................. 17 .................. Up to 17 ........ $1,360. 4,080. Up to $7,480. N/A N/A 200 List of Subjects in 14 CFR Part 39 Air transportation, Aircraft, Aviation safety, Safety. § 39.13 Cost per airplane Parts Service Bulletin 84–53–37, Revision ‘‘C,’’ dated December 5, 2005. Note 1: For the purposes of this AD, a general visual inspection is: ‘‘A visual examination of an interior or exterior area, installation, or assembly to detect obvious damage, failure, or irregularity. This level of inspection is made from within touching distance unless otherwise specified. A mirror may be necessary to ensure visual access to all surfaces in the inspection area. This level of inspection is made under normally available lighting conditions such as daylight, hangar lighting, flashlight, or droplight and may require removal or opening of access panels or doors. Stands, ladders, or platforms may be required to gain proximity to the area being checked.’’ Control Cable Cover Rework Only (g) If no fouling or damage is found during the inspection required by paragraph (f) of this AD: Within 24 months after the accomplishment date of the inspection, rework the control cable cover and, as applicable, manufacture/install the offset plate assembly; in accordance with the Accomplishment Instructions of Bombardier Service Bulletin 84–53–37, Revision ‘‘C,’’ dated December 5, 2005. Cable Replacement and Control Cable Cover Rework (h) If any fouling or damage is found during the inspection required by paragraph (f) of this AD: Before further flight, replace the control cable with a new control cable, rework the control cable cover and, if not already installed, manufacture/install the offset plate assembly; in accordance with the Accomplishment Instructions of Bombardier Service Bulletin 84–53–37, Revision ‘‘C,’’ dated December 5, 2005. Actions Accomplished According to Previous Issue of Service Bulletin (i) Actions accomplished before the effective date of this AD in accordance with Bombardier Service Bulletin 84–53–37, Revision ‘‘A,’’ dated October 17, 2005; or Revision ‘‘B,’’ dated November 24, 2005; are considered acceptable for compliance with the corresponding actions specified in this AD. Alternative Methods of Compliance (AMOCs) (j)(1) The Manager, New York Aircraft Certification Office (ACO), FAA, has the authority to approve AMOCs for this AD, if requested in accordance with the procedures found in 14 CFR 39.19. (2) Before using any AMOC approved in accordance with § 39.19 on any airplane to E:\FR\FM\12JYP1.SGM 12JYP1 Federal Register / Vol. 71, No. 133 / Wednesday, July 12, 2006 / Proposed Rules which the AMOC applies, notify the appropriate principal inspector in the FAA Flight Standards Certificate Holding District Office. Related Information (k) Canadian airworthiness directive CF– 2006–05, dated March 31, 2006, also addresses the subject of this AD. Issued in Renton, Washington, on July 3, 2006. Kalene C. Yanamura, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. E6–10912 Filed 7–11–06; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 71 [Docket No. FAA–2006–25069; Airspace Docket No. 06–AWP–9] Proposed Modification of Class E Airspace; Honolulu International Airport, HI Federal Aviation Administration (FAA), DOT. ACTION: Notice of proposed rulemaking. wwhite on PROD1PC61 with PROPOSALS AGENCY: SUMMARY: This notice proposes to modify the Class E airspace area at Honolulu International Airport, HI. The establishment of an Area Navigation (RNAV) Required Navigation Performance (RNP) Instrument Approach Procedures (IAP) to Runway (RWY) 08L and 26L at Honolulu International Airport, Honolulu, HI has made this proposal necessary. Additional controlled airspace extending upward from 700 feet or more above the surface of the earth is needed to contain aircraft executing the RNAV (RNP) IAP to RWY 08L/26L at Honolulu International Airport. The intended effect of this proposal is to provide adequate controlled airspace for Instrument Flight Rules (IFR) operations at Honolulu International Airport, Honolulu, HI. DATES: Comments must be received on or before August 28, 2006. ADDRESSES: Send comments on this proposal to the Docket Management System, U.S. Department of Transportation, Room Plaza 401, 400 Seventh Street, SW., Washington, DC 20590–0001. You must identify the docket number FAA–2006–25069/ Airspace Docket No. 06–AWP–9 at the beginning of your comments. You may also submit comments on the Internet at https://dms.dot.gov. You may review the public docket containing the proposal, VerDate Aug<31>2005 18:09 Jul 11, 2006 Jkt 208001 any comments received, and any final dispositions in person in the Docket Office between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. The Docket Office (telephone 1–800–647–5527) is on the plaza level of the Department of Transportation NASSIF Building at the above address. An informal docket may also be examined during normal business hours at the Office of the Regional Western Terminal Operations, Federal Aviation Administration, at 15000 Aviation Boulevard, Lawndale, California 90261, telephone number (310) 725–6502. SUPPLEMENTARY INFORMATION: Comments Invited Interested parties are invited to participate in this proposed rulemaking by submitting such written data, views, or arguments, as they may desire. Comments that provide the factual basis supporting the views and suggestions presented are particularly helpful in developing reasoned regulatory decisions on the proposal. Comments are specifically invited on the overall regulatory, aeronautical, economic, environmental, and energy-related aspects of the proposal. Communications should identify both docket numbers and be submitted in triplicate to the address listed above. Commenters wishing the FAA to acknowledge receipt of their comments on this notice must submit with the comments a self-addressed, stamped postcard on which the following statement is made: ‘‘Comments to Docket No. FAA–2006–25069/Airspace Docket No. 06–AWP–9.’’ The postcard will be date/time stamped and returned to the commenter. All communications received before the specified closing date for comments will be considered before taking action on the proposed rule. The proposal contained in this notice may be changed in light of the comments received. A report summarizing each substantive public contact with FAA personnel concerned with this rulemaking will be filed in the docket. Availability of NPRM’s An electronic copy of this document may be downloaded through the Internet at https://dms.dot.gov. Recently published rulemaking documents can also be accessed through the FAA’s Web page at https://www.faa.gov. or the Superintendent of Document’s Web page at https://www.access.gpo.gov/nara. Additionally, any person may obtain a copy of this notice by submitting a request to the Federal Aviation Administration, Office of Air Traffic PO 00000 Frm 00013 Fmt 4702 Sfmt 4702 39247 Airspace Management, ATA–400, 800 Independence Avenue, SW., Washington, DC 20591, or by calling (202) 267–8783. Communications must identify both document numbers for this notice. Persons interested in being placed on a mailing list for future NPRM’s should contact the FAA’s Office of Rulemaking, (202) 267–9677, to request a copy of Advisory Circular No. 11–2A, Notice of Proposed Rulemaking Distribution System, which describes the application procedures. The Proposal The FAA is considering an amendment to 14 CFR part 71 by modifying the Class E airspace area at Honolulu International Airport, Honolulu, HI. The establishment of a RNAV (RNP) IAP to RWY 08L/26L at Honolulu International Airport has made this proposal necessary. Additional controlled airspace extending upward from 700 feet above the surface is needed to contain aircraft executing the RNAV (RNP) IAP to RWY 08L/26L at Honolulu International Airport has made this proposal necessary. The intended effect of this proposal is to provide adequate controlled airspace for aircraft executing the RNAV (RNP) IAP to RWY 08L/26L Honolulu International Airport, HI. Class E airspace designations are published in paragraph 6005 of FAA Order 7400.9N dated September 1, 2005, and effective September 15, 2005, which is incorporated by reference in 14 CFR 71.1. The Class E airspace designation listed in this document would be published subsequently in this Order. The FAA has determined that this proposed regulation only involves an established body of technical regulations for which frequent and routine amendments are necessary to keep them operationally current. Therefore, this proposed regulation—(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) does not warrant preparation of a regulatory evaluation as the anticipated impact is so minimal. Since this is a routine matter that will affect air traffic procedures and air navigation, it is certified that this proposed rule would not have a significant economic impact on a substantial number of small entities under the criteria of the Regulatory Flexibility Act. List of Subjects in 14 CFR Part 71 Airspace, Incorporation by reference, Navigation (air). E:\FR\FM\12JYP1.SGM 12JYP1

Agencies

[Federal Register Volume 71, Number 133 (Wednesday, July 12, 2006)]
[Proposed Rules]
[Pages 39244-39247]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: E6-10912]


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

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2006-25328; Directorate Identifier 2006-NM-130-AD]
RIN 2120-AA64


Airworthiness Directives; Bombardier Model DHC-8-400 Series 
Airplanes

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

ACTION: Notice of proposed rulemaking (NPRM).

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

[[Page 39245]]

SUMMARY: The FAA proposes to adopt a new airworthiness directive (AD) 
for certain Bombardier Model DHC-8-400 series airplanes. This proposed 
AD would require inspecting for fouling and chafing damage of the 
outboard brake control cable of the main landing gear, replacing the 
control cable if necessary, reworking the control cable cover, and, if 
applicable, manufacturing/installing an offset plate on the control 
cable cover. This proposed AD is prompted by a review of brake control 
cable operation conducted by the manufacturer. We are proposing this AD 
to prevent abrasion and wear of the outboard brake control cable, which 
could lead to cable separation and reduced control of airplane braking.

DATES: We must receive comments on this proposed AD by August 11, 2006.

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.
     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.
    Contact Bombardier, Inc., Bombardier Regional Aircraft Division, 
123 Garratt Boulevard, Downsview, Ontario M3K 1Y5, Canada, for service 
information identified in this proposed AD.

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

SUPPLEMENTARY INFORMATION: 

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 in the ADDRESSES section. Include the docket number ``FAA-2006-
25328; Directorate Identifier 2006-NM-130-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 received 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 
that 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 may review the DOT's complete Privacy Act Statement in the 
Federal Register published on April 11, 2000 (65 FR 19477-78), or you 
may visit https://dms.dot.gov.

Examining the Docket

    You may 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 Docket Management System 
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-8-400 series airplanes. TCCA advises that 
a review conducted by the manufacturer revealed that the outboard brake 
control cable can become fouled on two fasteners on the pilot's 
bulkhead cover assembly. This condition, if not corrected, could result 
in abrasion and wear of the outboard brake control cable, which could 
lead to cable separation and reduced control of airplane braking.

Relevant Service Information

    Bombardier has issued Service Bulletin 84-53-37, Revision `C,' 
dated December 5, 2005. The service bulletin describes procedures for 
inspecting for fouling and chafing damage of the main landing gear 
outboard brake control cable, replacing the control cable if necessary, 
reworking the control cable cover, and, if not already installed, 
manufacturing/installing an offset plate on the control cable cover. 
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-
2006-05, dated March 31, 2006, 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 airplanes of this type design that are certificated for 
operation in the United States.
    Therefore, we are proposing this AD, which would require 
accomplishing the actions specified in the service information 
described previously, except as discussed under ``Clarification of 
Inspection Terminology.''

Clarification of Inspection Terminology

    The service bulletin specifies a ``visual inspection;'' however, 
this proposed AD would require a ``general visual inspection.'' We have 
included the definition of a general visual inspection in a note in the 
proposed AD.

Costs of Compliance

    The following table provides the estimated costs for U.S. operators 
to comply with this proposed AD, at an average labor rate of $80 per 
work hour.

[[Page 39246]]



                                                 Estimated Costs
----------------------------------------------------------------------------------------------------------------
                                      Work                Cost per     Number of U.S.-
              Action                 hours      Parts     airplane   registered airplanes        Fleet cost
----------------------------------------------------------------------------------------------------------------
Inspect brake cable..............          1        N/A        $80  17...................  $1,360.
Rework cable cover...............          3        N/A        240  17...................  4,080.
Manufacture/ install offset                3        200        440  Up to 17.............  Up to $7,480.
 plate, as applicable.
----------------------------------------------------------------------------------------------------------------

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

Bombardier, Inc. (Formerly de Havilland, Inc.): Docket No. FAA-2006-
25328; Directorate Identifier 2006-NM-130-AD.

Comments Due Date

    (a) The FAA must receive comments on this AD action by August 
11, 2006.

Affected ADs

    (b) None.

Applicability

    (c) This AD applies to Bombardier Model DHC-8-400 series 
airplanes, certificated in any category; having serial numbers 4003, 
4004, 4006, 4008 through 4064 inclusive, 4072, and 4073.

Unsafe Condition

    (d) This AD results from a review of brake control cable 
operation conducted by the manufacturer. We are issuing this AD to 
prevent abrasion and wear of the outboard brake control cable, which 
could lead to cable separation and reduced control of airplane 
braking.

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.

Inspection of Control Cable

    (f) Within 12 months after the effective date of this AD, 
perform a general visual inspection for fouling and chafing damage 
of the outboard brake control cable of the main landing gear, in 
accordance with the Accomplishment Instructions of Bombardier 
Service Bulletin 84-53-37, Revision ``C,'' dated December 5, 2005.

    Note 1: For the purposes of this AD, a general visual inspection 
is: ``A visual examination of an interior or exterior area, 
installation, or assembly to detect obvious damage, failure, or 
irregularity. This level of inspection is made from within touching 
distance unless otherwise specified. A mirror may be necessary to 
ensure visual access to all surfaces in the inspection area. This 
level of inspection is made under normally available lighting 
conditions such as daylight, hangar lighting, flashlight, or 
droplight and may require removal or opening of access panels or 
doors. Stands, ladders, or platforms may be required to gain 
proximity to the area being checked.''

Control Cable Cover Rework Only

    (g) If no fouling or damage is found during the inspection 
required by paragraph (f) of this AD: Within 24 months after the 
accomplishment date of the inspection, rework the control cable 
cover and, as applicable, manufacture/install the offset plate 
assembly; in accordance with the Accomplishment Instructions of 
Bombardier Service Bulletin 84-53-37, Revision ``C,'' dated December 
5, 2005.

Cable Replacement and Control Cable Cover Rework

    (h) If any fouling or damage is found during the inspection 
required by paragraph (f) of this AD: Before further flight, replace 
the control cable with a new control cable, rework the control cable 
cover and, if not already installed, manufacture/install the offset 
plate assembly; in accordance with the Accomplishment Instructions 
of Bombardier Service Bulletin 84-53-37, Revision ``C,'' dated 
December 5, 2005.

Actions Accomplished According to Previous Issue of Service Bulletin

    (i) Actions accomplished before the effective date of this AD in 
accordance with Bombardier Service Bulletin 84-53-37, Revision 
``A,'' dated October 17, 2005; or Revision ``B,'' dated November 24, 
2005; are considered acceptable for compliance with the 
corresponding actions specified in this AD.

Alternative Methods of Compliance (AMOCs)

    (j)(1) The Manager, New York Aircraft Certification Office 
(ACO), FAA, has the authority to approve AMOCs for this AD, if 
requested in accordance with the procedures found in 14 CFR 39.19.
    (2) Before using any AMOC approved in accordance with Sec.  
39.19 on any airplane to

[[Page 39247]]

which the AMOC applies, notify the appropriate principal inspector 
in the FAA Flight Standards Certificate Holding District Office.

Related Information

    (k) Canadian airworthiness directive CF-2006-05, dated March 31, 
2006, also addresses the subject of this AD.

    Issued in Renton, Washington, on July 3, 2006.
Kalene C. Yanamura,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
 [FR Doc. E6-10912 Filed 7-11-06; 8:45 am]
BILLING CODE 4910-13-P
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