Airworthiness Directives; Bombardier Model DHC-8-400 Series Airplanes, 36285-36288 [E8-14482]

Download as PDF 36285 Proposed Rules Federal Register Vol. 73, No. 124 Thursday, June 26, 2008 This section of the FEDERAL REGISTER contains notices to the public of the proposed issuance of rules and regulations. The purpose of these notices is to give interested persons an opportunity to participate in the rule making prior to the adoption of the final rules. DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2008–0356; Directorate Identifier 2008–NM–042–AD] RIN 2120–AA64 Airworthiness Directives; Bombardier Model DHC–8–400 Series Airplanes Federal Aviation Administration (FAA), Department of Transportation (DOT). ACTION: Supplemental notice of proposed rulemaking (NPRM); reopening of comment period. rfrederick on PROD1PC67 with PROPOSALS AGENCY: SUMMARY: The FAA is revising an earlier NPRM for an airworthiness directive (AD) that applies to certain Bombardier Model DHC–8–400 series airplanes. The original NPRM would have superseded an existing AD that currently requires inspecting all barrel nuts to determine if the barrel nuts have a certain marking, inspecting affected bolts to determine if the bolts are pre-loaded correctly, and replacing all hardware if the pre-load is incorrect. For airplanes on which the pre-load is correct, the existing AD requires doing repetitive visual inspections for cracking of the barrel nuts and cradles and replacing all hardware for all cracked barrel nuts. The existing AD also requires replacement of all hardware for certain affected barrel nuts that do not have cracking, which would end the repetitive inspections for those airplanes. The existing AD also provides an optional replacement for all affected barrel nuts. The original NPRM proposed to require replacement of all affected barrel nuts. The original NPRM resulted from reports of cracking in the barrel nuts at the four primary front spar wing-to-fuselage attachment joints. This new action revises the original NPRM by adding, for certain airplanes, application of a certain compound to the affected barrel nuts and bolts. We are proposing this supplemental NPRM VerDate Aug<31>2005 15:01 Jun 25, 2008 Jkt 214001 to detect and correct cracking of the barrel nuts at the wing front spar wingto-fuselage joints, which could result in reduced structural integrity of the wingto-fuselage attachments and consequent detachment of the wing. DATES: We must receive comments on this supplemental NPRM by July 21, 2008. ADDRESSES: You may send comments by any of the following methods: • Federal eRulemaking Portal: Go to https://www.regulations.gov. Follow the instructions for submitting comments. • Fax: 202–493–2251. • Mail: U.S. Department of Transportation, Docket Operations, M– 30, West Building Ground Floor, Room W12–140, 1200 New Jersey Avenue, SE., Washington, DC 20590. • Hand Delivery: U.S. Department of Transportation, Docket Operations, M– 30, West Building Ground Floor, Room W12–140, 1200 New Jersey Avenue, SE., Washington, DC 20590, between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. For service information identified in this AD, contact Bombardier, Inc., Bombardier Regional Aircraft Division, 123 Garratt Boulevard, Downsview, Ontario M3K 1Y5, Canada. Examining the AD Docket You may examine the AD docket on the Internet at https:// www.regulations.gov; or in person at the Docket Management Facility between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. The AD docket contains this proposed AD, the regulatory evaluation, any comments received, and other information. The street address for the Docket Office (telephone 800–647–5527) is in the ADDRESSES section. Comments will be available in the AD docket shortly after receipt. FOR FURTHER INFORMATION CONTACT: Pong Lee, 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) 228–7324; fax (516) 794–5531. SUPPLEMENTARY INFORMATION: Comments Invited We invite you to send any written relevant data, views, or arguments about this proposed AD. Send your comments to an address listed under the PO 00000 Frm 00001 Fmt 4702 Sfmt 4702 ADDRESSES section. Include ‘‘Docket No. FAA–2008–0356; Directorate Identifier 2008–NM–042–AD’’ at the beginning of your comments. We specifically invite comments on the overall regulatory, economic, environmental, and energy aspects of this proposed AD. We will consider all comments received by the closing date and may amend this proposed AD because of those comments. We will post all comments we receive, without change, to https:// www.regulations.gov, including any personal information you provide. We will also post a report summarizing each substantive verbal contact we receive about this proposed AD. Discussion The FAA issued a notice of proposed rulemaking (NPRM) (the ‘‘original NPRM’’) to amend 14 CFR part 39 to include an AD that supersedes AD 2008–04–02, amendment 39–15374 (73 FR 8187, February 13, 2008). The existing AD applies to certain Bombardier Model DHC–8–400 series airplanes. The original NPRM was published in the Federal Register on March 25, 2008 (73 FR 15682). The original NPRM proposed to retain the requirements of the existing AD and proposed to require replacement of all affected barrel nuts. Relevant Service Information Bombardier has issued Alert Service Bulletin A84–57–19, Revision B, dated March 6, 2008 (we referred to Bombardier Alert Service Bulletin A84– 57–19, Revision A, dated February 6, 2008, as the appropriate source of service information for doing the actions specified in the original NPRM). Revision B of the service bulletin contains the same actions as Revision A, except Revision B adds procedures to apply F13, Type 2 compound to the affected bolts and barrel nuts. Accomplishing the actions specified in the service information is intended to adequately address the unsafe condition. We have determined that for airplanes on which the affected bolts were replaced in accordance with Bombardier Alert Service Bulletin A84–57–19, dated February 1, 2008; or Revision A, dated February 6, 2008; operators must apply F13, Type 2 compound to the affected bolts and barrel nuts. We have added paragraph (l) to the supplemental NPRM E:\FR\FM\26JNP1.SGM 26JNP1 36286 Federal Register / Vol. 73, No. 124 / Thursday, June 26, 2008 / Proposed Rules to propose to require application of the compound for these airplanes. We have coordinated this action with Transport Canada Civil Aviation (TCCA), which is the aviation authority for Canada. TCCA issued Canadian airworthiness directive CF–2008–11R1, dated May 9, 2008, to ensure the continued airworthiness of these airplanes in Canada. We have also revised paragraphs (f), (f)(2), (g)(1)(ii), (g)(1)(iii), (g)(2)(ii), (g)(2)(iii), (g)(3)(ii), (g)(3)(iii), (g)(4), (g)(5), and (k) of the supplemental NPRM to refer to Bombardier Alert Service Bulletin A84–57–19, Revision B, dated March 6, 2008, as an appropriate source of service information for accomplishing the required actions. FAA’s Determination and Proposed Requirements of the Supplemental NPRM The changes discussed above expand the scope of the original NPRM; therefore, we have determined that it is necessary to reopen the comment period to provide additional opportunity for public comment on this supplemental NPRM. rfrederick on PROD1PC67 with PROPOSALS Costs of Compliance This proposed AD would affect about 48 airplanes of U.S. registry. The actions that are required by AD 2008–04–02 and retained in this proposed AD take about 3 work hours per airplane, at an average labor rate of $80 per work hour. Based on these figures, the estimated cost of the currently required actions is $11,520, or $240 per airplane, per inspection cycle. Replacement of the hardware of a barrel nut, if required, will take about 12 work hours per airplane, at an average labor rate of $80 per work hour. Required parts will cost about $800 per airplane. Based on these figures, we estimate the cost of a replacement to be $1,760 per barrel nut. Application of the compound, if required, will take about 4 work hours per airplane, at an average labor rate of $80 per work hour. Based on these figures, we estimate the cost of a replacement to be $320 per application. 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 VerDate Aug<31>2005 15:01 Jun 25, 2008 Jkt 214001 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 supplemental NPRM 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. § 39.13 [Amended] 2. The Federal Aviation Administration (FAA) amends § 39.13 by removing amendment 39–15374 (73 FR 8187, February 13, 2008) and adding the following new airworthiness directive (AD): Bombardier, Inc. (Formerly de Havilland, Inc.): Docket No. FAA–2008–0356; Directorate Identifier 2008–NM–042–AD. PO 00000 Frm 00002 Fmt 4702 Sfmt 4702 Comments Due Date (a) The FAA must receive comments on this AD action by July 21, 2008. Affected ADs (b) This AD supersedes AD 2008–04–02. Applicability (c) This AD applies to Bombardier Model DHC–8–400, DHC–8–401, and DHC–8–402 airplanes, certificated in any category; serial numbers 4001 and 4003 through 4176 inclusive. Unsafe Condition (d) This AD results from reports of cracking in the barrel nuts at the four primary front spar wing-to-fuselage attachment joints. We are issuing this AD to detect and correct cracking of the barrel nuts at the wing front spar wing-to-fuselage joints, which could result in reduced structural integrity of the wing-to-fuselage attachments and consequent detachment of the wing. 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. Restatement of Requirements of AD 2008– 04–02 With New Service Information Inspections and Corrective Actions (f) Within 50 flight hours after February 13, 2008 (the effective date of AD 2008–04–02), inspect all barrel nuts, part number DSC228– 16, to determine if the barrel nuts are identified with a marking of LH7940T SPS 01. Inspect in accordance with the Accomplishment Instructions of Bombardier Alert Service Bulletin A84–57–19, Revision A, dated February 6, 2008; or Revision B, dated March 6, 2008. As of the effective date of this AD, Bombardier Alert Service Bulletin A84–57–19, Revision B, dated March 6, 2008, must be used. (1) If no barrel nuts are identified with a marking of LH7940T SPS 01, no further actions are required by this paragraph. (2) If any barrel nut is found that is identified with a marking of LH7940T SPS 01, before further flight, inspect the inboard and outboard bolts to determine if the bolts are pre-loaded correctly. Inspect in accordance with the Accomplishment Instructions of Bombardier Alert Service Bulletin A84–57–19, Revision A, dated February 6, 2008; or Revision B, dated March 6, 2008. As of the effective date of this AD, Bombardier Alert Service Bulletin A84–57– 19, Revision B, dated March 6, 2008, must be used. (i) If the pre-load is incorrect (i.e., the ring can be rotated), before further flight, replace all hardware at that location in accordance with the Accomplishment Instructions of the alert service bulletin. (ii) If the pre-load is correct, before further flight, do a visual inspection for cracking of the barrel nuts and cradles in accordance with the Accomplishment Instructions of the alert service bulletin. (A) If no cracking of the barrel nut and cradle is found, do the applicable action required by paragraph (g) of this AD. E:\FR\FM\26JNP1.SGM 26JNP1 rfrederick on PROD1PC67 with PROPOSALS Federal Register / Vol. 73, No. 124 / Thursday, June 26, 2008 / Proposed Rules (B) If no cracking of the barrel nut is found and only cracking of the cradle is found, no action is required by this paragraph provided that the applicable corrective action specified in paragraph (g) of this AD is done. (C) If any cracking of the barrel nut is found, before next flight, replace all hardware only at that location in accordance with the Accomplishment Instructions of the alert service bulletin. (g) For any barrel nuts on which no cracking of the barrel nut was found during the inspection required by paragraph (f)(2)(ii) of this AD, do the applicable corrective action specified in paragraph (g)(1), (g)(2), (g)(3), (g)(4), or (g)(5) of this AD at the compliance time specified in the applicable paragraph. (1) If four barrel nuts having no cracking are found, do the actions specified in paragraphs (g)(1)(i), (g)(1)(ii), and (g)(1)(iii) of this AD. (i) Within 50 flight hours after doing the inspection required by paragraph (f)(2)(ii) of this AD, repeat the inspection specified in paragraph (f)(2) of this AD. Thereafter, repeat the inspection at intervals not to exceed 50 flight hours until the replacement specified in paragraph (g)(1)(ii) of this AD is done. (ii) Within 100 flight hours after doing the inspection required by paragraph (f)(2)(ii) of this AD, replace all hardware at the left-hand outboard location and the right-hand outboard location in accordance with the Accomplishment Instructions of Bombardier Alert Service Bulletin A84–57–19, Revision A, dated February 6, 2008; or Revision B, dated March 6, 2008. As of the effective date of this AD, Bombardier Alert Service Bulletin A84–57–19, Revision B, dated March 6, 2008, must be used. Replacing the barrel nuts on the outboard locations terminates the requirement to do the repetitive inspections specified in paragraph (g)(1)(i) of this AD. (iii) Within 100 flight hours after doing the replacement required by paragraph (g)(1)(ii) of this AD, repeat the inspection specified in paragraph (f)(2) of this AD for the remaining barrel nuts identified with a marking of LH7940T SPS 01. Thereafter, repeat the inspection at intervals not to exceed 100 flight hours until the replacement of all hardware at those locations is done. Do the inspection and replacement in accordance with the Accomplishment Instructions of Bombardier Alert Service Bulletin A84–57– 19, Revision A, dated February 6, 2008; or Revision B, dated March 6, 2008. As of the effective date of this AD, Bombardier Alert Service Bulletin A84–57–19, Revision B, dated March 6, 2008, must be used. (2) If three barrel nuts having no cracking are found, do the actions specified in paragraphs (g)(2)(i), (g)(2)(ii), and (g)(2)(iii) of this AD. (i) Within 50 flight hours after doing the inspection required by paragraph (f)(2)(ii) of this AD, repeat the inspection specified in paragraph (f)(2) of this AD. Thereafter, repeat the inspection at intervals not to exceed 50 flight hours until the replacement specified in paragraph (g)(2)(ii) of this AD is done. (ii) Within 100 flight hours after doing the inspection required by paragraph (f)(2)(ii) of this AD, replace all hardware for one affected barrel nut at the outboard location, on the VerDate Aug<31>2005 15:01 Jun 25, 2008 Jkt 214001 side with two affected barrel nuts, in accordance with the Accomplishment Instructions of Bombardier Alert Service Bulletin A84–57–19, Revision A, dated February 6, 2008; or Revision B, dated March 6, 2008. As of the effective date of this AD, Bombardier Alert Service Bulletin A84–57– 19, Revision B, dated March 6, 2008, must be used. Replacing the barrel nut on the outboard location terminates the requirement to do the repetitive inspections specified in paragraph (g)(2)(i) of this AD. (iii) Within 100 flight hours after doing the replacement required by paragraph (g)(2)(ii) of this AD, repeat the inspection specified in paragraph (f)(2) of this AD for the remaining barrel nuts identified with a marking of LH7940T SPS 01. Thereafter, repeat the inspection at intervals not to exceed 100 flight hours until the replacement of all hardware at those locations is done. Do the inspection and replacement in accordance with the Accomplishment Instructions of Bombardier Alert Service Bulletin A84–57– 19, Revision A, dated February 6, 2008; or Revision B, dated March 6, 2008. As of the effective date of this AD, Bombardier Alert Service Bulletin A84–57–19, Revision B, dated March 6, 2008, must be used. (3) If two barrel nuts having no cracking are found and both nuts are on the same side, do the actions specified in paragraphs (g)(3)(i), (g)(3)(ii), and (g)(3)(iii) of this AD. (i) Within 100 flight hours after doing the inspection required by paragraph (f)(2)(ii) of this AD, repeat the inspection specified in paragraph (f)(2) of this AD. Thereafter, repeat the inspection at intervals not to exceed 100 flight hours until the replacement specified in paragraph (g)(3)(ii) of this AD is done. (ii) Within 500 flight hours after doing the inspection required by paragraph (f)(2)(ii) of this AD, replace all hardware for one affected barrel nut at the outboard location that has two affected barrel nuts in accordance with the Accomplishment Instructions of Bombardier Alert Service Bulletin A84–57– 19, Revision A, dated February 6, 2008; or Revision B, dated March 6, 2008. As of the effective date of this AD, Bombardier Alert Service Bulletin A84–57–19, Revision B, dated March 6, 2008, must be used. Replacing the barrel nut on the outboard location terminates the requirement to do the repetitive inspections specified in paragraph (g)(3)(i) of this AD. (iii) Within 100 flight hours after doing the replacement required by paragraph (g)(3)(ii) of this AD, repeat the inspection specified in paragraph (f)(2) of this AD for the remaining barrel nut identified with a marking of LH7940T SPS 01. Thereafter, repeat the inspection at intervals not to exceed 100 flight hours until the replacement of all hardware at that location is done. Do the inspection and replacement in accordance with the Accomplishment Instructions of Bombardier Alert Service Bulletin A84–57– 19, Revision A, dated February 6, 2008; or Revision B, dated March 6, 2008. As of the effective date of this AD, Bombardier Alert Service Bulletin A84–57–19, Revision B, dated March 6, 2008, must be used. (4) If two barrel nuts having no cracking are found and are on opposite sides, within 100 flight hours after doing the inspection PO 00000 Frm 00003 Fmt 4702 Sfmt 4702 36287 required by paragraph (f)(2)(ii) of this AD, repeat the inspection specified in paragraph (f)(2) of this AD. Thereafter, repeat the inspection at intervals not to exceed 100 flight hours until the replacement of all hardware at those locations is done. Do the inspection and replacement in accordance with the Accomplishment Instructions of Bombardier Alert Service Bulletin A84–57– 19, Revision A, dated February 6, 2008; or Revision B, dated March 6, 2008. As of the effective date of this AD, Bombardier Alert Service Bulletin A84–57–19, Revision B, dated March 6, 2008, must be used. (5) If one barrel nut having no cracking is found, within 100 flight hours after doing the inspection required by paragraph (f)(2)(ii) of this AD, repeat the inspection specified in paragraph (f)(2) of this AD. Thereafter, repeat the inspection at intervals not to exceed 100 flight hours until the replacement of all hardware at that location is done. Do the inspection and replacement in accordance with the Accomplishment Instructions of Bombardier Alert Service Bulletin A84–57– 19, Revision A, dated February 6, 2008; or Revision B, dated March 6, 2008. As of the effective date of this AD, Bombardier Alert Service Bulletin A84–57–19, Revision B, dated March 6, 2008, must be used. Actions Accomplished According to Previous Issue of Alert Service Bulletin (h) Actions accomplished before February 13, 2008, in accordance with Bombardier Alert Service Bulletin A84–57–19, dated February 1, 2008, are acceptable for compliance with the corresponding actions specified in this AD. Actions Accomplished According to Bombardier Alert Service Bulletin A84–57– 18 (i) For airplanes on which the actions specified in Bombardier Alert Service Bulletin A84–57–18, dated January 16, 2008, were accomplished before February 13, 2008, and on which no barrel nuts were found that were identified with a marking of LH7940T SPS 01: No further action is required by this AD. Parts Installation (j) As of February 13, 2008, no person may install a barrel nut, part number DSC228–16, identified with a marking of LH7940T SPS 01, on any airplane. New Requirement of This AD Replacement of All Affected Barrel Nuts (k) For airplanes on which barrel nuts are inspected in accordance with paragraph (g)(1)(iii), (g)(2)(iii), (g)(3)(iii), (g)(4), or (g)(5) of this AD: Within 3,000 flight hours after the effective date of this AD, replace all hardware for all remaining barrel nuts, part number DSC228–16, identified with a marking of LH7940T SPS 01. Do the replacement in accordance with the Accomplishment Instructions of Bombardier Alert Service Bulletin A84–57–19, Revision B, dated March 6, 2008. Replacement of all hardware for all affected barrel nuts constitutes terminating action for the repetitive inspections of this AD. (l) For airplanes on which hardware for the barrel nut was replaced in accordance with E:\FR\FM\26JNP1.SGM 26JNP1 36288 Federal Register / Vol. 73, No. 124 / Thursday, June 26, 2008 / Proposed Rules Bombardier Alert Service Bulletin A84–57– 19, dated February 1, 2008; or Revision A, dated February 6, 2008: Within 3,000 flight hours after the effective date of this AD, apply F13, Type 2 corrosion inhibiting compound to the affected bolts and barrel nuts in accordance with the Accomplishment Instructions of Bombardier Alert Service Bulletin A84–57–19, Revision B, dated March 6, 2008; except if it can be conclusively determined from a review of airplane maintenance records that F13, Type 2 corrosion inhibiting compound was applied to the affected bolts and barrel nuts, then no further action is required by this paragraph. rfrederick on PROD1PC67 with PROPOSALS Special Flight Permit (m) Special flight permits, as described in Section 21.197 and Section 21.199 of the Federal Aviation Regulations (14 CFR 21.197 and 21.199), may be issued to operate the airplane to a location where the requirements of this AD can be accomplished, but concurrence by the Manager, New York Aircraft Certification Office, FAA, is required prior to issuance of the special flight permit. Before using any approved special flight permits, notify your appropriate principal inspector (PI) in the FAA Flight Standards District Office (FSDO), or lacking a PI, your local FSDO. Special flight permits may be permitted provided that the conditions specified in paragraphs (m)(1), (m)(2), (m)(3), (m)(4), and (m)(5) of this AD are met. (1) Both the right-hand side and left-hand side of the airplane must have at least one barrel nut that is not within the suspect batch (i.e., barrel nut is not identified with a marking of LH7940T SPS 01). The barrel nuts that are not within the suspect batch must be in good working condition (i.e., no cracking of the barrel nut). (2) No passengers and no cargo are onboard. (3) Airplane must operate in fair weather conditions with a low risk of turbulence. (4) Airplane must operate with reduced airspeed. For further information, contact Bombardier, Q Series 24 Hour Service Customer Response Center, at: Tel: 1–416– 375–4000; Fax: 1–416–375–4539; E-mail: thd.qseries@aero.bombardier.com. (5) All of the conditions specified in paragraphs (m)(1), (m)(2), (m)(3), and (m)(4) of this AD are on a case-by-case basis. Contact your appropriate principal inspector (PI) in the FAA Flight Standards District Office (FSDO), or lacking a PI, your local FSDO, for assistance. Alternative Methods of Compliance (AMOCs) (n)(1) The Manager, New York Aircraft Certification Office, FAA, has the authority to approve AMOCs for this AD, if requested in accordance with the procedures found in 14 CFR 39.19. (2) To request a different method of compliance or a different compliance time for this AD, follow the procedures in 14 CFR 39.19. Before using any approved AMOC on any airplane to which the AMOC applies, notify your appropriate principal inspector (PI) in the FAA Flight Standards District Office (FSDO), or lacking a PI, your local FSDO. VerDate Aug<31>2005 15:01 Jun 25, 2008 Jkt 214001 Related Information (o) Canadian airworthiness directive CF– 2008–11R1, dated May 9, 2008. Issued in Renton, Washington, on June 13, 2008. Ali Bahrami, Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. E8–14482 Filed 6–25–08; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2007–27715; Directorate Identifier 2006–NM–140–AD] RIN 2120–AA64 Airworthiness Directives; Airbus Model A330 and A340 Airplanes Federal Aviation Administration (FAA), Department of Transportation (DOT). ACTION: Supplemental notice of proposed rulemaking (NPRM); reopening of comment period. AGENCY: SUMMARY: The FAA is revising an earlier supplemental NPRM (SNPRM) for an airworthiness directive (AD) that applies to all Airbus Model A330–200, A330–300, A340–200, and A340–300 series airplanes; and Model A340–541 and A340–642 airplanes. The original NPRM would have superseded an existing AD that currently requires operators to revise the Airworthiness Limitations section (ALS) of the Instructions for Continued Airworthiness (ICA) to incorporate new information. This information includes, for all affected airplanes, decreased life limit values for certain components; and for Model A330–200 and –300 series airplanes, new inspections, compliance times, and new repetitive intervals to detect fatigue cracking, accidental damage, or corrosion in certain structures. The original NPRM proposed to revise the ALS, for all affected airplanes, by adding new Airworthiness Limitations Items (ALIs) to incorporate service life limits for certain items and inspections to detect fatigue cracking, accidental damage or corrosion in certain structures, in accordance with the revised ALS of the ICA. The original NPRM resulted from the issuance of new and more restrictive service life limits and structural inspections based on fatigue testing and in-service findings. The first supplemental NPRM revised the original NPRM by adding airplanes, adding new requirements, PO 00000 Frm 00004 Fmt 4702 Sfmt 4702 and including more restrictive compliance thresholds and intervals. This new action revises the first supplemental NPRM by adding a new weight variant configuration, and including more restrictive compliance thresholds and intervals. We are proposing this second supplemental NPRM to detect and correct fatigue cracking, accidental damage, or corrosion in principal structural elements, and to prevent failure of certain life-limited parts, which could result in reduced structural integrity of the airplane. DATES: We must receive comments on this supplemental NPRM by July 21, 2008. ADDRESSES: Use one of the following addresses to submit comments on this proposed AD. • DOT Docket Web site: Go to https://www.regulations.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: U.S. Department of Transportation, Docket Operations, M– 30, West Building Ground Floor, Room W12–140, 1200 New Jersey Avenue, SE., Washington, DC 20590. • Fax: (202) 493–2251. • Hand Delivery: Room W12–140 on the ground floor of the West Building, 1200 New Jersey Avenue, SE., Washington, DC, between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. Contact Airbus, 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex, France, for service information identified in this proposed AD. FOR FURTHER INFORMATION CONTACT: Tim Backman, Aerospace Engineer International Branch, ANM–116, FAA, International Branch, Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton, Washington 98055–4056; telephone (425) 227–2797; fax (425) 227–1149. SUPPLEMENTARY INFORMATION: Comments Invited We invite you to submit any relevant written data, views, or arguments regarding this proposal. Send your comments to an address listed in the ADDRESSES section. Include the docket number ‘‘Docket No. FAA–2007–27715; Directorate Identifier 2006–NM–140– AD’’ at the beginning of your comments. We specifically invite comments on the overall regulatory, economic, environmental, and energy aspects of this supplemental NPRM. We will E:\FR\FM\26JNP1.SGM 26JNP1

Agencies

[Federal Register Volume 73, Number 124 (Thursday, June 26, 2008)]
[Proposed Rules]
[Pages 36285-36288]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: E8-14482]


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Proposed Rules
                                                Federal Register
________________________________________________________________________

This section of the FEDERAL REGISTER contains notices to the public of 
the proposed issuance of rules and regulations. The purpose of these 
notices is to give interested persons an opportunity to participate in 
the rule making prior to the adoption of the final rules.

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Federal Register / Vol. 73, No. 124 / Thursday, June 26, 2008 / 
Proposed Rules

[[Page 36285]]



DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2008-0356; Directorate Identifier 2008-NM-042-AD]
RIN 2120-AA64


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

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

ACTION: Supplemental notice of proposed rulemaking (NPRM); reopening of 
comment period.

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

SUMMARY: The FAA is revising an earlier NPRM for an airworthiness 
directive (AD) that applies to certain Bombardier Model DHC-8-400 
series airplanes. The original NPRM would have superseded an existing 
AD that currently requires inspecting all barrel nuts to determine if 
the barrel nuts have a certain marking, inspecting affected bolts to 
determine if the bolts are pre-loaded correctly, and replacing all 
hardware if the pre-load is incorrect. For airplanes on which the pre-
load is correct, the existing AD requires doing repetitive visual 
inspections for cracking of the barrel nuts and cradles and replacing 
all hardware for all cracked barrel nuts. The existing AD also requires 
replacement of all hardware for certain affected barrel nuts that do 
not have cracking, which would end the repetitive inspections for those 
airplanes. The existing AD also provides an optional replacement for 
all affected barrel nuts. The original NPRM proposed to require 
replacement of all affected barrel nuts. The original NPRM resulted 
from reports of cracking in the barrel nuts at the four primary front 
spar wing-to-fuselage attachment joints. This new action revises the 
original NPRM by adding, for certain airplanes, application of a 
certain compound to the affected barrel nuts and bolts. We are 
proposing this supplemental NPRM to detect and correct cracking of the 
barrel nuts at the wing front spar wing-to-fuselage joints, which could 
result in reduced structural integrity of the wing-to-fuselage 
attachments and consequent detachment of the wing.

DATES: We must receive comments on this supplemental NPRM by July 21, 
2008.

ADDRESSES: You may send comments by any of the following methods:
     Federal eRulemaking Portal: Go to https://
www.regulations.gov. Follow the instructions for submitting comments.
     Fax: 202-493-2251.
     Mail: U.S. Department of Transportation, Docket 
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New 
Jersey Avenue, SE., Washington, DC 20590.
     Hand Delivery: U.S. Department of Transportation, Docket 
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New 
Jersey Avenue, SE., Washington, DC 20590, between 9 a.m. and 5 p.m., 
Monday through Friday, except Federal holidays.
    For service information identified in this AD, contact Bombardier, 
Inc., Bombardier Regional Aircraft Division, 123 Garratt Boulevard, 
Downsview, Ontario M3K 1Y5, Canada.

Examining the AD Docket

    You may examine the AD docket on the Internet at https://
www.regulations.gov; or in person at the Docket Management Facility 
between 9 a.m. and 5 p.m., Monday through Friday, except Federal 
holidays. The AD docket contains this proposed AD, the regulatory 
evaluation, any comments received, and other information. The street 
address for the Docket Office (telephone 800-647-5527) is in the 
ADDRESSES section. Comments will be available in the AD docket shortly 
after receipt.

FOR FURTHER INFORMATION CONTACT: Pong Lee, 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) 228-7324; fax (516) 794-5531.

SUPPLEMENTARY INFORMATION:

Comments Invited

    We invite you to send any written relevant data, views, or 
arguments about this proposed AD. Send your comments to an address 
listed under the ADDRESSES section. Include ``Docket No. FAA-2008-0356; 
Directorate Identifier 2008-NM-042-AD'' at the beginning of your 
comments. We specifically invite comments on the overall regulatory, 
economic, environmental, and energy aspects of this proposed AD. We 
will consider all comments received by the closing date and may amend 
this proposed AD because of those comments.
    We will post all comments we receive, without change, to https://
www.regulations.gov, including any personal information you provide. We 
will also post a report summarizing each substantive verbal contact we 
receive about this proposed AD.

Discussion

    The FAA issued a notice of proposed rulemaking (NPRM) (the 
``original NPRM'') to amend 14 CFR part 39 to include an AD that 
supersedes AD 2008-04-02, amendment 39-15374 (73 FR 8187, February 13, 
2008). The existing AD applies to certain Bombardier Model DHC-8-400 
series airplanes. The original NPRM was published in the Federal 
Register on March 25, 2008 (73 FR 15682). The original NPRM proposed to 
retain the requirements of the existing AD and proposed to require 
replacement of all affected barrel nuts.

Relevant Service Information

    Bombardier has issued Alert Service Bulletin A84-57-19, Revision B, 
dated March 6, 2008 (we referred to Bombardier Alert Service Bulletin 
A84-57-19, Revision A, dated February 6, 2008, as the appropriate 
source of service information for doing the actions specified in the 
original NPRM). Revision B of the service bulletin contains the same 
actions as Revision A, except Revision B adds procedures to apply F13, 
Type 2 compound to the affected bolts and barrel nuts. Accomplishing 
the actions specified in the service information is intended to 
adequately address the unsafe condition.
    We have determined that for airplanes on which the affected bolts 
were replaced in accordance with Bombardier Alert Service Bulletin A84-
57-19, dated February 1, 2008; or Revision A, dated February 6, 2008; 
operators must apply F13, Type 2 compound to the affected bolts and 
barrel nuts. We have added paragraph (l) to the supplemental NPRM

[[Page 36286]]

to propose to require application of the compound for these airplanes. 
We have coordinated this action with Transport Canada Civil Aviation 
(TCCA), which is the aviation authority for Canada. TCCA issued 
Canadian airworthiness directive CF-2008-11R1, dated May 9, 2008, to 
ensure the continued airworthiness of these airplanes in Canada.
    We have also revised paragraphs (f), (f)(2), (g)(1)(ii), 
(g)(1)(iii), (g)(2)(ii), (g)(2)(iii), (g)(3)(ii), (g)(3)(iii), (g)(4), 
(g)(5), and (k) of the supplemental NPRM to refer to Bombardier Alert 
Service Bulletin A84-57-19, Revision B, dated March 6, 2008, as an 
appropriate source of service information for accomplishing the 
required actions.

FAA's Determination and Proposed Requirements of the Supplemental NPRM

    The changes discussed above expand the scope of the original NPRM; 
therefore, we have determined that it is necessary to reopen the 
comment period to provide additional opportunity for public comment on 
this supplemental NPRM.

Costs of Compliance

    This proposed AD would affect about 48 airplanes of U.S. registry.
    The actions that are required by AD 2008-04-02 and retained in this 
proposed AD take about 3 work hours per airplane, at an average labor 
rate of $80 per work hour. Based on these figures, the estimated cost 
of the currently required actions is $11,520, or $240 per airplane, per 
inspection cycle.
    Replacement of the hardware of a barrel nut, if required, will take 
about 12 work hours per airplane, at an average labor rate of $80 per 
work hour. Required parts will cost about $800 per airplane. Based on 
these figures, we estimate the cost of a replacement to be $1,760 per 
barrel nut.
    Application of the compound, if required, will take about 4 work 
hours per airplane, at an average labor rate of $80 per work hour. 
Based on these figures, we estimate the cost of a replacement to be 
$320 per application.

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 supplemental NPRM 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 
removing amendment 39-15374 (73 FR 8187, February 13, 2008) and adding 
the following new airworthiness directive (AD):

Bombardier, Inc. (Formerly de Havilland, Inc.): Docket No. FAA-2008-
0356; Directorate Identifier 2008-NM-042-AD.

Comments Due Date

    (a) The FAA must receive comments on this AD action by July 21, 
2008.

Affected ADs

    (b) This AD supersedes AD 2008-04-02.

Applicability

    (c) This AD applies to Bombardier Model DHC-8-400, DHC-8-401, 
and DHC-8-402 airplanes, certificated in any category; serial 
numbers 4001 and 4003 through 4176 inclusive.

Unsafe Condition

    (d) This AD results from reports of cracking in the barrel nuts 
at the four primary front spar wing-to-fuselage attachment joints. 
We are issuing this AD to detect and correct cracking of the barrel 
nuts at the wing front spar wing-to-fuselage joints, which could 
result in reduced structural integrity of the wing-to-fuselage 
attachments and consequent detachment of the wing.

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.

Restatement of Requirements of AD 2008-04-02 With New Service 
Information

Inspections and Corrective Actions

    (f) Within 50 flight hours after February 13, 2008 (the 
effective date of AD 2008-04-02), inspect all barrel nuts, part 
number DSC228-16, to determine if the barrel nuts are identified 
with a marking of LH7940T SPS 01. Inspect in accordance with the 
Accomplishment Instructions of Bombardier Alert Service Bulletin 
A84-57-19, Revision A, dated February 6, 2008; or Revision B, dated 
March 6, 2008. As of the effective date of this AD, Bombardier Alert 
Service Bulletin A84-57-19, Revision B, dated March 6, 2008, must be 
used.
    (1) If no barrel nuts are identified with a marking of LH7940T 
SPS 01, no further actions are required by this paragraph.
    (2) If any barrel nut is found that is identified with a marking 
of LH7940T SPS 01, before further flight, inspect the inboard and 
outboard bolts to determine if the bolts are pre-loaded correctly. 
Inspect in accordance with the Accomplishment Instructions of 
Bombardier Alert Service Bulletin A84-57-19, Revision A, dated 
February 6, 2008; or Revision B, dated March 6, 2008. As of the 
effective date of this AD, Bombardier Alert Service Bulletin A84-57-
19, Revision B, dated March 6, 2008, must be used.
    (i) If the pre-load is incorrect (i.e., the ring can be 
rotated), before further flight, replace all hardware at that 
location in accordance with the Accomplishment Instructions of the 
alert service bulletin.
    (ii) If the pre-load is correct, before further flight, do a 
visual inspection for cracking of the barrel nuts and cradles in 
accordance with the Accomplishment Instructions of the alert service 
bulletin.
    (A) If no cracking of the barrel nut and cradle is found, do the 
applicable action required by paragraph (g) of this AD.

[[Page 36287]]

    (B) If no cracking of the barrel nut is found and only cracking 
of the cradle is found, no action is required by this paragraph 
provided that the applicable corrective action specified in 
paragraph (g) of this AD is done.
    (C) If any cracking of the barrel nut is found, before next 
flight, replace all hardware only at that location in accordance 
with the Accomplishment Instructions of the alert service bulletin.
    (g) For any barrel nuts on which no cracking of the barrel nut 
was found during the inspection required by paragraph (f)(2)(ii) of 
this AD, do the applicable corrective action specified in paragraph 
(g)(1), (g)(2), (g)(3), (g)(4), or (g)(5) of this AD at the 
compliance time specified in the applicable paragraph.
    (1) If four barrel nuts having no cracking are found, do the 
actions specified in paragraphs (g)(1)(i), (g)(1)(ii), and 
(g)(1)(iii) of this AD.
    (i) Within 50 flight hours after doing the inspection required 
by paragraph (f)(2)(ii) of this AD, repeat the inspection specified 
in paragraph (f)(2) of this AD. Thereafter, repeat the inspection at 
intervals not to exceed 50 flight hours until the replacement 
specified in paragraph (g)(1)(ii) of this AD is done.
    (ii) Within 100 flight hours after doing the inspection required 
by paragraph (f)(2)(ii) of this AD, replace all hardware at the 
left-hand outboard location and the right-hand outboard location in 
accordance with the Accomplishment Instructions of Bombardier Alert 
Service Bulletin A84-57-19, Revision A, dated February 6, 2008; or 
Revision B, dated March 6, 2008. As of the effective date of this 
AD, Bombardier Alert Service Bulletin A84-57-19, Revision B, dated 
March 6, 2008, must be used. Replacing the barrel nuts on the 
outboard locations terminates the requirement to do the repetitive 
inspections specified in paragraph (g)(1)(i) of this AD.
    (iii) Within 100 flight hours after doing the replacement 
required by paragraph (g)(1)(ii) of this AD, repeat the inspection 
specified in paragraph (f)(2) of this AD for the remaining barrel 
nuts identified with a marking of LH7940T SPS 01. Thereafter, repeat 
the inspection at intervals not to exceed 100 flight hours until the 
replacement of all hardware at those locations is done. Do the 
inspection and replacement in accordance with the Accomplishment 
Instructions of Bombardier Alert Service Bulletin A84-57-19, 
Revision A, dated February 6, 2008; or Revision B, dated March 6, 
2008. As of the effective date of this AD, Bombardier Alert Service 
Bulletin A84-57-19, Revision B, dated March 6, 2008, must be used.
    (2) If three barrel nuts having no cracking are found, do the 
actions specified in paragraphs (g)(2)(i), (g)(2)(ii), and 
(g)(2)(iii) of this AD.
    (i) Within 50 flight hours after doing the inspection required 
by paragraph (f)(2)(ii) of this AD, repeat the inspection specified 
in paragraph (f)(2) of this AD. Thereafter, repeat the inspection at 
intervals not to exceed 50 flight hours until the replacement 
specified in paragraph (g)(2)(ii) of this AD is done.
    (ii) Within 100 flight hours after doing the inspection required 
by paragraph (f)(2)(ii) of this AD, replace all hardware for one 
affected barrel nut at the outboard location, on the side with two 
affected barrel nuts, in accordance with the Accomplishment 
Instructions of Bombardier Alert Service Bulletin A84-57-19, 
Revision A, dated February 6, 2008; or Revision B, dated March 6, 
2008. As of the effective date of this AD, Bombardier Alert Service 
Bulletin A84-57-19, Revision B, dated March 6, 2008, must be used. 
Replacing the barrel nut on the outboard location terminates the 
requirement to do the repetitive inspections specified in paragraph 
(g)(2)(i) of this AD.
    (iii) Within 100 flight hours after doing the replacement 
required by paragraph (g)(2)(ii) of this AD, repeat the inspection 
specified in paragraph (f)(2) of this AD for the remaining barrel 
nuts identified with a marking of LH7940T SPS 01. Thereafter, repeat 
the inspection at intervals not to exceed 100 flight hours until the 
replacement of all hardware at those locations is done. Do the 
inspection and replacement in accordance with the Accomplishment 
Instructions of Bombardier Alert Service Bulletin A84-57-19, 
Revision A, dated February 6, 2008; or Revision B, dated March 6, 
2008. As of the effective date of this AD, Bombardier Alert Service 
Bulletin A84-57-19, Revision B, dated March 6, 2008, must be used.
    (3) If two barrel nuts having no cracking are found and both 
nuts are on the same side, do the actions specified in paragraphs 
(g)(3)(i), (g)(3)(ii), and (g)(3)(iii) of this AD.
    (i) Within 100 flight hours after doing the inspection required 
by paragraph (f)(2)(ii) of this AD, repeat the inspection specified 
in paragraph (f)(2) of this AD. Thereafter, repeat the inspection at 
intervals not to exceed 100 flight hours until the replacement 
specified in paragraph (g)(3)(ii) of this AD is done.
    (ii) Within 500 flight hours after doing the inspection required 
by paragraph (f)(2)(ii) of this AD, replace all hardware for one 
affected barrel nut at the outboard location that has two affected 
barrel nuts in accordance with the Accomplishment Instructions of 
Bombardier Alert Service Bulletin A84-57-19, Revision A, dated 
February 6, 2008; or Revision B, dated March 6, 2008. As of the 
effective date of this AD, Bombardier Alert Service Bulletin A84-57-
19, Revision B, dated March 6, 2008, must be used. Replacing the 
barrel nut on the outboard location terminates the requirement to do 
the repetitive inspections specified in paragraph (g)(3)(i) of this 
AD.
    (iii) Within 100 flight hours after doing the replacement 
required by paragraph (g)(3)(ii) of this AD, repeat the inspection 
specified in paragraph (f)(2) of this AD for the remaining barrel 
nut identified with a marking of LH7940T SPS 01. Thereafter, repeat 
the inspection at intervals not to exceed 100 flight hours until the 
replacement of all hardware at that location is done. Do the 
inspection and replacement in accordance with the Accomplishment 
Instructions of Bombardier Alert Service Bulletin A84-57-19, 
Revision A, dated February 6, 2008; or Revision B, dated March 6, 
2008. As of the effective date of this AD, Bombardier Alert Service 
Bulletin A84-57-19, Revision B, dated March 6, 2008, must be used.
    (4) If two barrel nuts having no cracking are found and are on 
opposite sides, within 100 flight hours after doing the inspection 
required by paragraph (f)(2)(ii) of this AD, repeat the inspection 
specified in paragraph (f)(2) of this AD. Thereafter, repeat the 
inspection at intervals not to exceed 100 flight hours until the 
replacement of all hardware at those locations is done. Do the 
inspection and replacement in accordance with the Accomplishment 
Instructions of Bombardier Alert Service Bulletin A84-57-19, 
Revision A, dated February 6, 2008; or Revision B, dated March 6, 
2008. As of the effective date of this AD, Bombardier Alert Service 
Bulletin A84-57-19, Revision B, dated March 6, 2008, must be used.
    (5) If one barrel nut having no cracking is found, within 100 
flight hours after doing the inspection required by paragraph 
(f)(2)(ii) of this AD, repeat the inspection specified in paragraph 
(f)(2) of this AD. Thereafter, repeat the inspection at intervals 
not to exceed 100 flight hours until the replacement of all hardware 
at that location is done. Do the inspection and replacement in 
accordance with the Accomplishment Instructions of Bombardier Alert 
Service Bulletin A84-57-19, Revision A, dated February 6, 2008; or 
Revision B, dated March 6, 2008. As of the effective date of this 
AD, Bombardier Alert Service Bulletin A84-57-19, Revision B, dated 
March 6, 2008, must be used.

Actions Accomplished According to Previous Issue of Alert Service 
Bulletin

    (h) Actions accomplished before February 13, 2008, in accordance 
with Bombardier Alert Service Bulletin A84-57-19, dated February 1, 
2008, are acceptable for compliance with the corresponding actions 
specified in this AD.

Actions Accomplished According to Bombardier Alert Service Bulletin 
A84-57-18

    (i) For airplanes on which the actions specified in Bombardier 
Alert Service Bulletin A84-57-18, dated January 16, 2008, were 
accomplished before February 13, 2008, and on which no barrel nuts 
were found that were identified with a marking of LH7940T SPS 01: No 
further action is required by this AD.

Parts Installation

    (j) As of February 13, 2008, no person may install a barrel nut, 
part number DSC228-16, identified with a marking of LH7940T SPS 01, 
on any airplane.

New Requirement of This AD

Replacement of All Affected Barrel Nuts

    (k) For airplanes on which barrel nuts are inspected in 
accordance with paragraph (g)(1)(iii), (g)(2)(iii), (g)(3)(iii), 
(g)(4), or (g)(5) of this AD: Within 3,000 flight hours after the 
effective date of this AD, replace all hardware for all remaining 
barrel nuts, part number DSC228-16, identified with a marking of 
LH7940T SPS 01. Do the replacement in accordance with the 
Accomplishment Instructions of Bombardier Alert Service Bulletin 
A84-57-19, Revision B, dated March 6, 2008. Replacement of all 
hardware for all affected barrel nuts constitutes terminating action 
for the repetitive inspections of this AD.
    (l) For airplanes on which hardware for the barrel nut was 
replaced in accordance with

[[Page 36288]]

Bombardier Alert Service Bulletin A84-57-19, dated February 1, 2008; 
or Revision A, dated February 6, 2008: Within 3,000 flight hours 
after the effective date of this AD, apply F13, Type 2 corrosion 
inhibiting compound to the affected bolts and barrel nuts in 
accordance with the Accomplishment Instructions of Bombardier Alert 
Service Bulletin A84-57-19, Revision B, dated March 6, 2008; except 
if it can be conclusively determined from a review of airplane 
maintenance records that F13, Type 2 corrosion inhibiting compound 
was applied to the affected bolts and barrel nuts, then no further 
action is required by this paragraph.

Special Flight Permit

    (m) Special flight permits, as described in Section 21.197 and 
Section 21.199 of the Federal Aviation Regulations (14 CFR 21.197 
and 21.199), may be issued to operate the airplane to a location 
where the requirements of this AD can be accomplished, but 
concurrence by the Manager, New York Aircraft Certification Office, 
FAA, is required prior to issuance of the special flight permit. 
Before using any approved special flight permits, notify your 
appropriate principal inspector (PI) in the FAA Flight Standards 
District Office (FSDO), or lacking a PI, your local FSDO. Special 
flight permits may be permitted provided that the conditions 
specified in paragraphs (m)(1), (m)(2), (m)(3), (m)(4), and (m)(5) 
of this AD are met.
    (1) Both the right-hand side and left-hand side of the airplane 
must have at least one barrel nut that is not within the suspect 
batch (i.e., barrel nut is not identified with a marking of LH7940T 
SPS 01). The barrel nuts that are not within the suspect batch must 
be in good working condition (i.e., no cracking of the barrel nut).
    (2) No passengers and no cargo are onboard.
    (3) Airplane must operate in fair weather conditions with a low 
risk of turbulence.
    (4) Airplane must operate with reduced airspeed. For further 
information, contact Bombardier, Q Series 24 Hour Service Customer 
Response Center, at: Tel: 1-416-375-4000; Fax: 1-416-375-4539; E-
mail: thd.qseries@aero.bombardier.com.
    (5) All of the conditions specified in paragraphs (m)(1), 
(m)(2), (m)(3), and (m)(4) of this AD are on a case-by-case basis. 
Contact your appropriate principal inspector (PI) in the FAA Flight 
Standards District Office (FSDO), or lacking a PI, your local FSDO, 
for assistance.

Alternative Methods of Compliance (AMOCs)

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

Related Information

    (o) Canadian airworthiness directive CF-2008-11R1, dated May 9, 
2008.

    Issued in Renton, Washington, on June 13, 2008.
Ali Bahrami,
Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. E8-14482 Filed 6-25-08; 8:45 am]
BILLING CODE 4910-13-P

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