Airworthiness Directives; BAE Systems (Operations) Limited (Jetstream) Model 4101 Airplanes, 67817-67820 [E8-27161]

Download as PDF Federal Register / Vol. 73, No. 222 / Monday, November 17, 2008 / Proposed Rules Boeing: Docket No. FAA–2008–1213; Directorate Identifier 2007–NM–092–AD. Comments Due Date (a) The FAA must receive comments on this AD action by January 2, 2009. Affected ADs (b) This AD supersedes AD 2005–20–03. Applicability (c) This AD applies to Model 737–100, –200, –200C, –300, –400, and –500 series airplanes, certificated in any category, as identified in Boeing Alert Service Bulletin 737–53A1204, Revision 1, dated March 26, 2007. Unsafe Condition (d) This AD results from reports of fatigue cracks. We are issuing this AD to detect and correct fatigue cracking of the intercostals on the forward and aft sides of the forward entry door, which could result in loss of the forward entry door and rapid decompression of the airplane. Compliance (e) You are responsible for having the actions required by this AD performed within the compliance times specified, unless the actions have already been done. Initial Compliance Time (f) For all Model 737–100, –200, –200C, –300, –400, and –500 series airplanes: Before the accumulation of 15,000 total flight cycles, or within 4,500 flight cycles after November 1, 2005 (the effective date of AD 2005–20– 03), whichever occurs later: Do the inspections required by paragraphs (h) and (i) of this AD. (g) For all Model 737–200C series airplanes: Before the accumulation of 15,000 total flight cycles, or within 4,500 flight cycles after the effective date of this AD, whichever occurs later: Do the inspection required by paragraph (j) of this AD. jlentini on PROD1PC65 with PROPOSALS Initial Inspection for Passenger Configuration Airplanes (h) For Group 1 passenger airplanes identified in Boeing Alert Service Bulletin 737–53A1204, Revision 1, dated March 26, 2007: Perform a detailed inspection for cracking of the intercostal web, attachment clips, and stringer splice channels; and a high frequency eddy current inspection for cracking of the stringer splice channels located forward and aft of the forward entry door; and do all applicable corrective actions before further flight; in accordance with Parts 1 and 2 of the Work Instructions of Boeing Special Attention Service Bulletin 737–53– 1204, dated June 19, 2003; or Boeing Alert Service Bulletin 737–53A1204, Revision 1, dated March 26, 2007. After the effective date of this AD, only Revision 1 may be used. Initial Inspection for Cargo Configuration Airplanes (Forward of the Forward Entry Door) (i) For Group 2 cargo airplanes identified in Boeing Alert Service Bulletin 737– 53A1204, Revision 1, dated March 26, 2007: Perform a detailed inspection for cracking of the intercostal webs and attachment clips VerDate Aug<31>2005 17:49 Nov 14, 2008 Jkt 217001 located forward of the forward entry door; and do all applicable corrective actions before further flight; in accordance with Part 3 of the Work Instructions of Boeing Special Attention Service Bulletin 737–53–1204, dated June 19, 2003, or Boeing Alert Service Bulletin 737–53A1204, Revision 1, dated March 26, 2007. After the effective date of this AD, only Revision 1 may be used. Initial Inspection for Cargo Configuration Airplanes (Aft of the Forward Entry Door) (j) For Group 2 cargo airplanes identified in Boeing Alert Service Bulletin 737– 53A1204, Revision 1, dated March 26, 2007: Perform a detailed inspection for cracking of the intercostal webs and attachment clips located aft of the forward entry door; and do all applicable corrective actions before further flight; in accordance with Part 4 of the Work Instructions of Boeing Special Attention Service Bulletin 737–53–1204, dated June 19, 2003; or Boeing Alert Service Bulletin 737–53A1204, Revision 1, dated March 26, 2007. After the effective date of this AD, only Revision 1 may be used. Repeat Inspections (k) Repeat the inspections required by paragraphs (h), (i), and (j) of this AD thereafter at intervals not to exceed 6,000 flight cycles after the previous inspection, or within 3,000 flight cycles after the effective date of this AD, whichever occurs later. Exceptions (l) Do the actions required by this AD by accomplishing all the applicable actions specified in the Accomplishment Instructions of the Boeing Special Attention Service Bulletin 737–53–1204, dated June 19, 2003; or Boeing Alert Service Bulletin 737– 53A1204, Revision 1, dated March 26, 2007; (‘‘the service bulletins’’) except as provided by paragraphs (l)(1) and (l)(2) of this AD. After the effective date of this AD, only Revision 1 may be used (1) Where the service bulletins specify to contact Boeing for repair instructions: Before further flight, repair using a method approved in accordance with the procedures specified in paragraph (m) of this AD. (2) Where the service bulletins specify a compliance time relative to the date of a service bulletin, this AD requires compliance relative to the effective date of this AD. Where the service bulletins specify a compliance time relative to the date of the initial release of the service bulletin, this AD requires compliance relative to the effective date of AD 2005–20–03 (November 1, 2005). Alternative Methods of Compliance (AMOCs) (m)(1) The Manager, Seattle Aircraft Certification Office (ACO), FAA, ATTN: Howard Hall, Aerospace Engineer, Airframe Branch, ANM–120S, FAA, Seattle ACO, 1601 Lind Avenue, SW., Renton, Washington 98057–3356; telephone (425) 917–6430; fax (425) 917–6590; has the authority to approve AMOCs for this AD, if requested using 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 PO 00000 Frm 00005 Fmt 4702 Sfmt 4702 67817 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. (3) An AMOC that provides an acceptable level of safety may be used for any repair required by this AD, if it is approved by an Authorized Representative for the Boeing Commercial Airplanes Delegation Option Authorization Organization who has been authorized by the Manager, Seattle ACO, to make those findings. For a repair method to be approved, the repair must meet the certification basis of the airplane, and the approval must specifically refer to this AD. (4) AMOCs approved previously in accordance with AD 2005–20–03 are approved as AMOCs for the corresponding provisions of this AD, provided the repetitive inspection intervals (if any) do not exceed 6,000 flight cycles. (5) AMOCs approved previously in accordance with AD 2005–20–03 are not approved as AMOCs for the provisions of paragraph (j) or (k) of this AD. Issued in Renton, Washington, on November 6, 2008. Stephen P. Boyd, Assistant Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. E8–27163 Filed 11–14–08; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2008–1214; Directorate Identifier 2007–NM–259–AD] RIN 2120–AA64 Airworthiness Directives; BAE Systems (Operations) Limited (Jetstream) Model 4101 Airplanes Federal Aviation Administration (FAA), Department of Transportation (DOT). ACTION: Notice of proposed rulemaking (NPRM). AGENCY: SUMMARY: The FAA proposes to supersede an existing airworthiness directive (AD) that applies to all BAE Systems (Operations) Limited (Jetstream) Model 4101 airplanes. The existing AD currently requires operators to determine the number of flight cycles accumulated on each component of the main landing gear (MLG) and the nose landing gear (NLG), and to replace each component that reaches its life limit with a serviceable component. The existing AD also requires operators to revise the Airworthiness Limitations (AWL) section of the Instructions for Continued Airworthiness (ICA) in the aircraft maintenance manual to reflect E:\FR\FM\17NOP1.SGM 17NOP1 67818 Federal Register / Vol. 73, No. 222 / Monday, November 17, 2008 / Proposed Rules the new life limits for structurally significant items. This proposed AD would require a new revision of the AWL section of the ICA to incorporate revised life limits for structurally significant items, operational and functional tests of certain systems, and instructions to retain critical ignition source prevention features during configuration changes. This proposed AD results from mandatory continuing airworthiness information (MCAI) originated by an aviation authority of another country. We are proposing this AD to prevent failure of certain structurally significant items, including the MLG and the NLG, which could result in reduced structural integrity of the airplane; and to prevent fuel vapor ignition sources, which could result in fuel tank explosion and consequent loss of the airplane. DATES: We must receive comments on this proposed AD by December 17, 2008. 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 BAE Systems Regional Aircraft, 13850 McLearen Road, Herndon, Virginia 20171; telephone 703–736–1080; e-mail raebusiness@baesystems.com; Internet https://www.baesystems.com/Businesses/ RegionalAircraft/index.htm. ADDRESSES: jlentini on PROD1PC65 with PROPOSALS 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. VerDate Aug<31>2005 17:49 Nov 14, 2008 Jkt 217001 FOR FURTHER INFORMATION CONTACT: Todd Thompson, Aerospace Engineer, International Branch, ANM–116, Transport Airplane Directorate, FAA, 1601 Lind Avenue, SW., Renton, Washington 98057–3356; telephone (425) 227–1175; fax (425) 227–1149. 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–2008–1214; Directorate Identifier 2007–NM–259–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 On September 9, 2005, we issued AD 2005–19–15, amendment 39–14280 (70 FR 55230, September 21, 2005), for all BAE Systems (Operations) Limited (Jetstream) Model 4101 airplanes. That AD requires operators to determine the number of flight cycles accumulated on each component of the main landing gear (MLG) and the nose landing gear (NLG), and to replace each component that reaches its life limit with a serviceable component. The existing AD also requires operators to revise the Airworthiness Limitations (AWL) section of the Instructions for Continued Airworthiness in the aircraft maintenance manual to reflect the new life limits for structurally significant items. That AD resulted from engineering analysis of fleet operations which resulted in more restrictive life limits. We issued that AD to prevent failure of certain structurally significant items, including the MLG and the NLG, which could result in reduced structural integrity of the airplane. Actions Since Existing AD Was Issued Since we issued AD 2005–19–15, the European Aviation Safety Agency (EASA), which is the airworthiness authority for the European Union, advises that BAE System (Operations) Limited has issued revised Airworthiness Limitations, Certification PO 00000 Frm 00006 Fmt 4702 Sfmt 4702 Maintenance Requirements, and Critical Design Configuration Control Limitations (CDCCL). The revisions were based on assessments of fuel tank wiring installations. These assessments revealed that fuel vapor ignition sources may remain undetected. Fuel vapor ignition sources, if not corrected, could result in fuel tank explosion and consequent loss of the airplane. Relevant Service Information BAE Systems (Operations) Limited has issued Chapters 05–10–10, ‘‘Airworthiness Limitations,’’ 05–10–20, ‘‘Certification Maintenance Requirements,’’ and 05–10–30, ‘‘Critical Design Configuration Control Limitations (CDCCL)—Fuel System’’ of BAE Systems (Operations) Limited Jetstream Series 4100 AMM, Revision 29, dated February 15, 2008. Chapter 05–10–10 revises life limits for structurally significant items. Chapter 05–10–20 includes operational and functional tests of certain systems (e.g., air conditioning, electrical power, fire protection, and flight controls) and the maximum permitted time between those tests to maintain the certificated airworthiness standard of the airplanes. Chapter 05–10–30 includes CDCCLs that provide instructions to retain critical ignition source prevention features during configuration changes that may be caused by modification, repair, or maintenance actions. Accomplishing the actions specified in the service information is intended to adequately address the unsafe condition. The EASA mandated the service information and issued airworthiness directive 2008–0094, dated May 16, 2008 (referred to after this as ‘‘the MCAI’’), to ensure the continued airworthiness of these airplanes in the European Union. FAA’s Determination and Requirements of the Proposed AD This product has been approved by the aviation authority of another country, and is approved for operation in the United States. Pursuant to our bilateral agreement with the State of Design Authority, we have been notified of the unsafe condition described in the MCAI and service information referenced above. We are proposing this AD because we evaluated all pertinent information and determined an unsafe condition exists and is likely to exist or develop on other products of the same type design. This proposed AD would supersede AD 2005–19–15 and would continue to require revising the AWL section of the Instructions for Continued Airworthiness in the AMM to reflect the E:\FR\FM\17NOP1.SGM 17NOP1 67819 Federal Register / Vol. 73, No. 222 / Monday, November 17, 2008 / Proposed Rules new life limits structurally significant items. This proposed AD would also require revising the AWL section of the Instructions for Continued Airworthiness by incorporating the instructions specified in certain chapters of the service information described previously. Change to Existing AD This proposed AD would retain only certain requirements of AD 2005–19–15. As a result, the corresponding paragraph identifiers have changed in this proposed AD, as listed in the following table: Costs of Compliance The following table provides the estimated costs for U.S. operators to comply with this proposed AD. REVISED PARAGRAPH IDENTIFIER Requirement in AD 2005–19–15 paragraph (l) ............. Corresponding requirement in this proposed AD paragraph (f). ESTIMATED COSTS Action AWL revision (required by AD 2005–19–15) ....................... AWL revision (new proposed action) ................................... jlentini on PROD1PC65 with PROPOSALS 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 VerDate Aug<31>2005 17:49 Nov 14, 2008 Average labor rate per hour Work hour Jkt 217001 1 1 Cost per airplane $80 80 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, Incorporation by reference, 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 $80 80 Number of U.S.registered airplanes Fleet cost 3 3 $240 240 Applicability (c) This AD applies to all BAE Systems (Operations) Limited Model Jetstream 4101 airplanes, certificated in any category. Unsafe Condition (d) This AD results from mandatory continuing airworthiness information (MCAI) originated by an aviation authority of another country. We are issuing this AD to prevent failure of certain structurally significant items, including the main landing gear (MLG) and the nose landing gear (NLG), which could result in reduced structural integrity of the airplane; and to prevent fuel vapor ignition sources, which could result in fuel tank explosion and consequent loss of the airplane. Compliance (e) You are responsible for having the actions required by this AD performed within the compliance times specified, unless the actions have already been done. Certain Requirement of AD 2005–19–15 BAE Systems (Operations) Limited (Formerly British Aerospace Regional Aircraft): Docket No. FAA–2008–1214; Directorate Identifier 2007–NM–259–AD. Revise Aircraft Maintenance Manual (AMM) (f) Within 30 days after October 26, 2005 (the effective date of AD 2005–19–15): Revise the Airworthiness Limitations (AWL) section of the Instructions for Continued Airworthiness of the BAE Systems (Operations) Limited J41 AMM to include the life limits of the components listed in Chapter 05–10–10, Airworthiness Limitations—Description and Operation Section, Revision 23, dated February 15, 2005, of the AMM. This may be accomplished by inserting a copy into the AWL section of the Instructions for Continued Airworthiness. Thereafter, except as provided in paragraph (i) of this AD, no alternative replacement times may be approved for any affected component. Comments Due Date New Requirements of This AD 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 39–14280 (70 FR 55230, September 21, 2005) and adding the following new airworthiness directive (AD): (a) The FAA must receive comments on this AD action by December 17, 2008. Affected ADs (b) This AD supersedes AD 2005–19–15. PO 00000 Frm 00007 Fmt 4702 Sfmt 4702 Revise AWL Section of Instructions for Continued Airworthiness (g) Within 90 days after the effective date of this AD: Revise the AWL section of the E:\FR\FM\17NOP1.SGM 17NOP1 67820 Federal Register / Vol. 73, No. 222 / Monday, November 17, 2008 / Proposed Rules Instructions for Continued Airworthiness by incorporating the instructions of Chapters 05–10–10, ‘‘Airworthiness Limitations,’’ 05– 10–20, ‘‘Certification Maintenance Requirements,’’ and 05–10–30, ‘‘Critical Design Configuration Control Limitations (CDCCL)—Fuel System’’ of BAE Systems (Operations) Limited Jetstream Series 4100 AMM, Revision 29, dated February 15, 2008 (hereafter ‘‘the service information’’). Thereafter, except as provided in paragraph (i) of this AD, no alternative replacement times or inspection intervals may be approved for any affected component. The revised Chapter 05–10–10 replaces the corresponding chapter specified in paragraph (f) of this AD. (h) Where paragraph 2.A.(2) of the service information specifies that certain landing gear units ‘‘must be removed 31st March 2008,’’ this AD requires compliance within 60 days after the effective date of this AD. Alternative Methods of Compliance (AMOCs) (i) The Manager, International Branch, ANM–116, FAA, has the authority to approve AMOCs for this AD, if requested using the procedures found in 14 CFR 39.19. Send information to ATTN: Todd Thompson, Aerospace Engineer, International Branch, ANM–116, Transport Airplane Directorate, FAA, 1601 Lind Avenue, SW., Renton, Washington 98057–3356; telephone (425) 227–1175; fax (425) 227–1149. 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 (j) European Aviation Safety Agency (EASA) airworthiness directive 2008–0094, dated May 16, 2008, also addresses the subject of this AD. Issued in Renton, Washington, on November 6, 2008. Stephen P. Boyd, Assistant Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. E8–27161 Filed 11–14–08; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2008–1216; Directorate Identifier 2008–NM–111–AD] jlentini on PROD1PC65 with PROPOSALS RIN 2120–AA64 Airworthiness Directives; Bombardier Model CL–600–1A11 (CL–600), CL– 600–2A12 (CL–601), and CL–600–2B16 (CL–601–3A, CL–601–3R, and CL–604) Airplanes Federal Aviation Administration (FAA), DOT. AGENCY: VerDate Aug<31>2005 17:49 Nov 14, 2008 Jkt 217001 Notice of proposed rulemaking (NPRM). ACTION: SUMMARY: We propose to adopt a new airworthiness directive (AD) for the products listed above. This proposed AD results from mandatory continuing airworthiness information (MCAI) originated by an aviation authority of another country to identify and correct an unsafe condition on an aviation product. The MCAI describes the unsafe condition as: * * * [S]everal cases of wing anti-ice piccolo duct failure reported on CL–600– 2B19 (CRJ) aircraft. Although there have been no failures reported on Challenger aircraft, similar ducts are installed on the above Challenger models. * * * * * Cracking of the wing anti-ice piccolo ducts could result in air leakage, with an adverse effect on the anti-ice air distribution pattern and a possible unannunciated insufficient heat condition. * * * The unsafe condition is anti-ice system air leakage with a possible adverse effect on the anti-ice air distribution pattern and anti-ice capability without annunciation to the flightcrew, and consequent reduced controllability of the airplane. The proposed AD would require actions that are intended to address the unsafe condition described in the MCAI. DATES: We must receive comments on this proposed AD by December 17, 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 W12–40, 1200 New Jersey Avenue, SE., Washington, DC, between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. Examining the AD Docket You may examine the AD docket on the Internet at https:// www.regulations.gov; or in person at the Docket Operations office 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 Operations office (telephone (800) 647–5527) is in PO 00000 Frm 00008 Fmt 4702 Sfmt 4702 the ADDRESSES section. Comments will be available in the AD docket shortly after receipt. FOR FURTHER INFORMATION CONTACT: Dan Parrillo, 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) 228–7305; 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–2008–1216; Directorate Identifier 2008–NM–111–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 based on 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 Transport Canada Civil Aviation (TCCA), which is the aviation authority for Canada, has issued Canadian Airworthiness Directive CF–2008–18, dated May 9, 2008 (referred to after this as ‘‘the MCAI’’), to correct an unsafe condition for the specified products. The MCAI states: There have been several cases of wing antiice piccolo duct failure reported on CL–600– 2B19 (CRJ) aircraft. Although there have been no failures reported on Challenger aircraft, similar ducts are installed on the above Challenger models [CL–600–1A11, CL–600– 2A12, and CL–600–2B16]. Upon investigation, it has been determined that ducts manufactured since June 2000, and installed since 1 August 2000, are susceptible to cracking due to the process used to drill the holes in the ducts. These ducts were installed on CL–600–2B16 aircraft, serial numbers 5469 through 5635 in production, but may also have been installed as replacements on CL–600–1A11, CL–600– 2A12 and other CL–600–2B16 aircraft. Cracking of the wing anti-ice piccolo ducts could result in air leakage, with an adverse effect on the anti-ice air distribution pattern and a possible unannunciated insufficient heat condition. As a result, the airplane flight manual (AFM) instructions have been revised to provide proper annunciation of an insufficient heat condition, utilizing existing messages and indications, with instructions, to the pilot, to leave icing conditions if E:\FR\FM\17NOP1.SGM 17NOP1

Agencies

[Federal Register Volume 73, Number 222 (Monday, November 17, 2008)]
[Proposed Rules]
[Pages 67817-67820]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: E8-27161]


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

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2008-1214; Directorate Identifier 2007-NM-259-AD]
RIN 2120-AA64


Airworthiness Directives; BAE Systems (Operations) Limited 
(Jetstream) Model 4101 Airplanes

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

ACTION: Notice of proposed rulemaking (NPRM).

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

SUMMARY: The FAA proposes to supersede an existing airworthiness 
directive (AD) that applies to all BAE Systems (Operations) Limited 
(Jetstream) Model 4101 airplanes. The existing AD currently requires 
operators to determine the number of flight cycles accumulated on each 
component of the main landing gear (MLG) and the nose landing gear 
(NLG), and to replace each component that reaches its life limit with a 
serviceable component. The existing AD also requires operators to 
revise the Airworthiness Limitations (AWL) section of the Instructions 
for Continued Airworthiness (ICA) in the aircraft maintenance manual to 
reflect

[[Page 67818]]

the new life limits for structurally significant items. This proposed 
AD would require a new revision of the AWL section of the ICA to 
incorporate revised life limits for structurally significant items, 
operational and functional tests of certain systems, and instructions 
to retain critical ignition source prevention features during 
configuration changes. This proposed AD results from mandatory 
continuing airworthiness information (MCAI) originated by an aviation 
authority of another country. We are proposing this AD to prevent 
failure of certain structurally significant items, including the MLG 
and the NLG, which could result in reduced structural integrity of the 
airplane; and to prevent fuel vapor ignition sources, which could 
result in fuel tank explosion and consequent loss of the airplane.

DATES: We must receive comments on this proposed AD by December 17, 
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 BAE Systems 
Regional Aircraft, 13850 McLearen Road, Herndon, Virginia 20171; 
telephone 703-736-1080; e-mail raebusiness@baesystems.com; Internet 
https://www.baesystems.com/Businesses/RegionalAircraft/index.htm.

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: Todd Thompson, Aerospace Engineer, 
International Branch, ANM-116, Transport Airplane Directorate, FAA, 
1601 Lind Avenue, SW., Renton, Washington 98057-3356; telephone (425) 
227-1175; fax (425) 227-1149.

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-2008-1214; 
Directorate Identifier 2007-NM-259-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

    On September 9, 2005, we issued AD 2005-19-15, amendment 39-14280 
(70 FR 55230, September 21, 2005), for all BAE Systems (Operations) 
Limited (Jetstream) Model 4101 airplanes. That AD requires operators to 
determine the number of flight cycles accumulated on each component of 
the main landing gear (MLG) and the nose landing gear (NLG), and to 
replace each component that reaches its life limit with a serviceable 
component. The existing AD also requires operators to revise the 
Airworthiness Limitations (AWL) section of the Instructions for 
Continued Airworthiness in the aircraft maintenance manual to reflect 
the new life limits for structurally significant items. That AD 
resulted from engineering analysis of fleet operations which resulted 
in more restrictive life limits. We issued that AD to prevent failure 
of certain structurally significant items, including the MLG and the 
NLG, which could result in reduced structural integrity of the 
airplane.

Actions Since Existing AD Was Issued

    Since we issued AD 2005-19-15, the European Aviation Safety Agency 
(EASA), which is the airworthiness authority for the European Union, 
advises that BAE System (Operations) Limited has issued revised 
Airworthiness Limitations, Certification Maintenance Requirements, and 
Critical Design Configuration Control Limitations (CDCCL). The 
revisions were based on assessments of fuel tank wiring installations. 
These assessments revealed that fuel vapor ignition sources may remain 
undetected. Fuel vapor ignition sources, if not corrected, could result 
in fuel tank explosion and consequent loss of the airplane.

Relevant Service Information

    BAE Systems (Operations) Limited has issued Chapters 05-10-10, 
``Airworthiness Limitations,'' 05-10-20, ``Certification Maintenance 
Requirements,'' and 05-10-30, ``Critical Design Configuration Control 
Limitations (CDCCL)--Fuel System'' of BAE Systems (Operations) Limited 
Jetstream Series 4100 AMM, Revision 29, dated February 15, 2008. 
Chapter 05-10-10 revises life limits for structurally significant 
items. Chapter 05-10-20 includes operational and functional tests of 
certain systems (e.g., air conditioning, electrical power, fire 
protection, and flight controls) and the maximum permitted time between 
those tests to maintain the certificated airworthiness standard of the 
airplanes. Chapter 05-10-30 includes CDCCLs that provide instructions 
to retain critical ignition source prevention features during 
configuration changes that may be caused by modification, repair, or 
maintenance actions.
    Accomplishing the actions specified in the service information is 
intended to adequately address the unsafe condition. The EASA mandated 
the service information and issued airworthiness directive 2008-0094, 
dated May 16, 2008 (referred to after this as ``the MCAI''), to ensure 
the continued airworthiness of these airplanes in the European Union.

FAA's Determination and Requirements of the Proposed AD

    This product has been approved by the aviation authority of another 
country, and is approved for operation in the United States. Pursuant 
to our bilateral agreement with the State of Design Authority, we have 
been notified of the unsafe condition described in the MCAI and service 
information referenced above. We are proposing this AD because we 
evaluated all pertinent information and determined an unsafe condition 
exists and is likely to exist or develop on other products of the same 
type design.
    This proposed AD would supersede AD 2005-19-15 and would continue 
to require revising the AWL section of the Instructions for Continued 
Airworthiness in the AMM to reflect the

[[Page 67819]]

new life limits structurally significant items. This proposed AD would 
also require revising the AWL section of the Instructions for Continued 
Airworthiness by incorporating the instructions specified in certain 
chapters of the service information described previously.

Change to Existing AD

    This proposed AD would retain only certain requirements of AD 2005-
19-15. As a result, the corresponding paragraph identifiers have 
changed in this proposed AD, as listed in the following table:

                      Revised Paragraph Identifier
------------------------------------------------------------------------
                                             Corresponding  requirement
       Requirement in AD 2005-19-15             in this  proposed AD
------------------------------------------------------------------------
paragraph (l).............................  paragraph (f).
------------------------------------------------------------------------

Costs of Compliance

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

                                                 Estimated Costs
----------------------------------------------------------------------------------------------------------------
                                                                                  Number of U.S.-
             Action                  Work hour     Average labor     Cost per        registered     Fleet cost
                                                   rate per hour     airplane        airplanes
----------------------------------------------------------------------------------------------------------------
AWL revision (required by AD                   1             $80             $80               3            $240
 2005-19-15)....................
AWL revision (new proposed                     1              80              80               3             240
 action)........................
----------------------------------------------------------------------------------------------------------------

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, Incorporation by 
reference, 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 39-14280 (70 FR 55230, September 21, 2005) and 
adding the following new airworthiness directive (AD):

BAE Systems (Operations) Limited (Formerly British Aerospace 
Regional Aircraft): Docket No. FAA-2008-1214; Directorate Identifier 
2007-NM-259-AD.

Comments Due Date

    (a) The FAA must receive comments on this AD action by December 
17, 2008.

Affected ADs

    (b) This AD supersedes AD 2005-19-15.

Applicability

    (c) This AD applies to all BAE Systems (Operations) Limited 
Model Jetstream 4101 airplanes, certificated in any category.

Unsafe Condition

    (d) This AD results from mandatory continuing airworthiness 
information (MCAI) originated by an aviation authority of another 
country. We are issuing this AD to prevent failure of certain 
structurally significant items, including the main landing gear 
(MLG) and the nose landing gear (NLG), which could result in reduced 
structural integrity of the airplane; and to prevent fuel vapor 
ignition sources, which could result in fuel tank explosion and 
consequent loss of the airplane.

Compliance

    (e) You are responsible for having the actions required by this 
AD performed within the compliance times specified, unless the 
actions have already been done.

Certain Requirement of AD 2005-19-15

Revise Aircraft Maintenance Manual (AMM)

    (f) Within 30 days after October 26, 2005 (the effective date of 
AD 2005-19-15): Revise the Airworthiness Limitations (AWL) section 
of the Instructions for Continued Airworthiness of the BAE Systems 
(Operations) Limited J41 AMM to include the life limits of the 
components listed in Chapter 05-10-10, Airworthiness Limitations--
Description and Operation Section, Revision 23, dated February 15, 
2005, of the AMM. This may be accomplished by inserting a copy into 
the AWL section of the Instructions for Continued Airworthiness. 
Thereafter, except as provided in paragraph (i) of this AD, no 
alternative replacement times may be approved for any affected 
component.

New Requirements of This AD

Revise AWL Section of Instructions for Continued Airworthiness

    (g) Within 90 days after the effective date of this AD: Revise 
the AWL section of the

[[Page 67820]]

Instructions for Continued Airworthiness by incorporating the 
instructions of Chapters 05-10-10, ``Airworthiness Limitations,'' 
05-10-20, ``Certification Maintenance Requirements,'' and 05-10-30, 
``Critical Design Configuration Control Limitations (CDCCL)--Fuel 
System'' of BAE Systems (Operations) Limited Jetstream Series 4100 
AMM, Revision 29, dated February 15, 2008 (hereafter ``the service 
information''). Thereafter, except as provided in paragraph (i) of 
this AD, no alternative replacement times or inspection intervals 
may be approved for any affected component. The revised Chapter 05-
10-10 replaces the corresponding chapter specified in paragraph (f) 
of this AD.
    (h) Where paragraph 2.A.(2) of the service information specifies 
that certain landing gear units ``must be removed 31st March 2008,'' 
this AD requires compliance within 60 days after the effective date 
of this AD.

Alternative Methods of Compliance (AMOCs)

    (i) The Manager, International Branch, ANM-116, FAA, has the 
authority to approve AMOCs for this AD, if requested using the 
procedures found in 14 CFR 39.19. Send information to ATTN: Todd 
Thompson, Aerospace Engineer, International Branch, ANM-116, 
Transport Airplane Directorate, FAA, 1601 Lind Avenue, SW., Renton, 
Washington 98057-3356; telephone (425) 227-1175; fax (425) 227-1149. 
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

    (j) European Aviation Safety Agency (EASA) airworthiness 
directive 2008-0094, dated May 16, 2008, also addresses the subject 
of this AD.

    Issued in Renton, Washington, on November 6, 2008.
Stephen P. Boyd,
Assistant Manager, Transport Airplane Directorate, Aircraft 
Certification Service.
[FR Doc. E8-27161 Filed 11-14-08; 8:45 am]
BILLING CODE 4910-13-P
This site is protected by reCAPTCHA and the Google Privacy Policy and Terms of Service apply.