Airworthiness Directives; Bombardier Model CL-600-2B19 (Regional Jet Series 100 & 440) Airplanes, 67870-67873 [E7-23339]

Download as PDF 67870 Federal Register / Vol. 72, No. 231 / Monday, December 3, 2007 / Proposed Rules 1. Is not a ‘‘significant regulatory action’’ under Executive Order 12866; 2. Is not a ‘‘significant rule’’ under the DOT Regulatory Policies and Procedures (44 FR 11034, February 26, 1979); and 3. Will not have a significant economic impact, positive or negative, on a substantial number of small entities under the criteria of the Regulatory Flexibility Act. We prepared a regulatory evaluation of the estimated costs to comply with this proposed AD and placed it in the AD docket. See the ADDRESSES section for a location to examine the regulatory evaluation. List of Subjects in 14 CFR Part 39 Air transportation, Aircraft, Aviation safety, Safety. The Proposed Amendment Accordingly, under the authority delegated to me by the Administrator, the FAA proposes to amend 14 CFR part 39 as follows: PART 39—AIRWORTHINESS DIRECTIVES 1. The authority citation for part 39 continues to read as follows: Authority: 49 U.S.C. 106(g), 40113, 44701. § 39.13 [Amended] 2. The Federal Aviation Administration (FAA) amends § 39.13 by adding the following new airworthiness directive (AD): Airbus: Docket No. FAA–2007–0266; Directorate Identifier 2007–NM–170–AD. Comments Due Date (a) The FAA must receive comments on this AD action by January 2, 2008. Affected ADs (b) None. yshivers on PROD1PC62 with PROPOSALS Applicability (c) This AD applies to Airbus Model A330– 200, A330–300, A340–200, and A340–300 series airplanes, certificated in any category; equipped with the air data inertial reference units (ADIRUs) identified in paragraphs (c)(1) and (c)(2) of this AD. (1) Honeywell ADIRUs having part numbers (P/Ns) HG2030AC0X (where X is any number between 0 and 9 inclusive) and P/Ns HG2030ADYY (where YY is any number between 00 and 10 inclusive). (2) Northrop Grumman (formerly Litton) ADIRUs having P/Ns 465020–030303ZZ (where ZZ is any number between 00 and 12 inclusive). Unsafe Condition (d) This AD results from data showing that the magnetic variation table installed in certain Honeywell and Northrop Grumman ADIRUs is obsolete at certain airports. We are issuing this AD to prevent the airplane from departing the runway during a CAT 2 or CAT VerDate Aug<31>2005 14:41 Nov 30, 2007 Jkt 214001 3 automatic landing or roll-out, due to differences between actual magnetic variation and the values in the ADIRU magnetic variation tables. 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. Temporary Revision (TR) References (f) The term ‘‘Temporary Revision,’’ as used in this AD, means the following TRs, as applicable: (1) For Model A330–200 and A330–300 series airplanes equipped with any Honeywell ADIRU identified in paragraph (c)(1) of this AD: Airbus TR 2.05.00/67, Issue 2, dated September 19, 2007, to the Airbus A330 Airplane Flight Manual (AFM); (2) For Model A330–200 and A330–300 series airplanes equipped with any Northrop Grumman ADIRU identified in paragraph (c)(2) of this AD: Airbus TR 2.05.00/68, dated March 31, 2006, to the Airbus A330 AFM; (3) For Model A340–200 and A340–300 series airplanes equipped with any Honeywell ADIRU identified in paragraph (c)(1) of this AD: Airbus TR 2.05.00/87, Issue 2, dated September 19, 2007, to the Airbus A340 AFM; (4) For Model A340–200 and A340–300 series airplanes equipped with any Northrop Grumman ADIRU identified in paragraph (c)(2) of this AD: Airbus TR 2.05.00/88, dated March 31, 2006, to the Airbus A340 AFM. Airplane Flight Manual (AFM) Revision (g) Within 14 days after the effective date of this AD, revise the Limitations Section of the Airbus A330 or A340 AFM, as applicable, to prohibit the flightcrew from performing CAT 2 and CAT 3 automatic landings and roll-outs at certain airports by incorporating the applicable Temporary Revision into the AFM. Operate the airplane according to the limitations in the applicable TR. (h) When the information in the applicable TR has been incorporated into the general revisions of the Airbus A330 or A340 AFM, as applicable, the general revisions may be inserted into the AFM, and the TR may be removed from the AFM. Optional Terminating Action (i) Replacing the ADIRUs with new, improved ADIRUs as specified in paragraph (i)(1), (i)(2), (i)(3), or (i)(4) of this AD terminates the AFM revision required by paragraph (g) of this AD. (1) For Model A330–200 and A330–300 series airplanes equipped with any Honeywell ADIRU identified in paragraph (c)(1) of this AD, doing the replacement in accordance with the Accomplishment Instructions of Airbus Service Bulletin A330– 34–3165, dated June 28, 2006; or Airbus Service Bulletin A330–34–3104, dated July 17, 2003. (2) For Model A330–200 and A330–300 series airplanes equipped with any Northrop Grumman ADIRU identified in paragraph (c)(2) of this AD, doing the replacement in accordance with the Accomplishment Instructions of Airbus Service Bulletin A330– 34–3132, dated December 16, 2003, or PO 00000 Frm 00007 Fmt 4702 Sfmt 4702 Revision 01, dated August 18, 2004; or Airbus Service Bulletin A330–34–3159, dated February 10, 2005. (3) For Model A340–200 and A340–300 series airplanes equipped with any Honeywell ADIRU identified in paragraph (c)(1) of this AD, doing the replacement in accordance with the Accomplishment Instructions of Airbus Service Bulletin A340– 34–4166, dated June 28, 2006; or Airbus Service Bulletin A340–34–4114, dated July 17, 2003. (4) For Model A340–200 and A340–300 series airplanes equipped with any Northrop Grumman ADIRU identified in paragraph (c)(2) of this AD, doing the replacement in accordance with the Accomplishment Instructions of Airbus Service Bulletin A340– 34–4141, dated December 16, 2003, or Revision 01, dated August 18, 2004; or Airbus Service Bulletin A340–34–4163, dated February 10, 2005. Alternative Methods of Compliance (AMOCs) (j)(1) The Manager, International Branch, ANM–116, 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 (k) European Aviation Safety Agency airworthiness directive 2006–0232, dated August 7, 2006, also addresses the subject of this AD. Issued in Renton, Washington, on November 23, 2007. Ali Bahrami, Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. E7–23338 Filed 11–30–07; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2007–0262; Directorate Identifier 2007–NM–247–AD] RIN 2120–AA64 Airworthiness Directives; Bombardier Model CL–600–2B19 (Regional Jet Series 100 & 440) Airplanes Federal Aviation Administration (FAA), DOT. ACTION: Notice of proposed rulemaking (NPRM). AGENCY: SUMMARY: We propose to adopt a new airworthiness directive (AD) for the E:\FR\FM\03DEP1.SGM 03DEP1 Federal Register / Vol. 72, No. 231 / Monday, December 3, 2007 / Proposed Rules 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: Bombardier Aerospace has completed a system safety review of the CL–600–2B19 aircraft fuel system * * *. The assessment showed that sealant has not been applied to bolts on the collector fuel tanks or the transfer ejector fuel pumps. Lack of sealant on the above-noted locations, if not corrected, could result in arcing and potential ignition source inside the fuel tank during lightning strikes and consequent fuel tank explosion. * * * 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 January 2, 2008. ADDRESSES: You may send comments by any of the following methods: • Federal eRulemaking Portal: Go to http://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. yshivers on PROD1PC62 with PROPOSALS Examining the AD Docket You may examine the AD docket on the Internet at http:// 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 the ADDRESSES section. Comments will be available in the AD docket shortly after receipt. FOR FURTHER INFORMATION CONTACT: Rocco Viselli, 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) 228–7331; fax (516) 794–5531. SUPPLEMENTARY INFORMATION: VerDate Aug<31>2005 14:41 Nov 30, 2007 Jkt 214001 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–2007–0262; Directorate Identifier 2007–NM–247–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 http:// 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–2007–17, dated September 4, 2007 (referred to after this as ‘‘the MCAI’’), to correct an unsafe condition for the specified products. The MCAI states: Bombardier Aerospace has completed a system safety review of the CL–600–2B19 aircraft fuel system against new fuel tank safety standards, introduced in Chapter 525 of the Airworthiness Manual through Notice of Proposed Amendment (NPA) 2002–043. The identified non-compliances were assessed using Transport Canada Policy Letter No. 525–001 to determine if mandatory corrective action is required. The assessment showed that sealant has not been applied to bolts on the collector fuel tanks or the transfer ejector fuel pumps. Lack of sealant on the above-noted locations, if not corrected, could result in arcing and potential ignition source inside the fuel tank during lightning strikes and consequent fuel tank explosion. To correct the unsafe condition, this directive mandates the application of sealant to the bolts that attach various fittings on the collector fuel tanks, [an inspection for a fillet seal and if necessary application of fillet seal] to the edges of the transfer ejector pumps and [an inspection for sealant and if necessary application of sealant] to the bolts that attach the transfer ejector pump to the transfer ejector pump casing. You may obtain further information by examining the MCAI in the AD docket. The FAA has examined the underlying safety issues involved in fuel tank explosions on several large transport airplanes, including the adequacy of existing regulations, the service history of airplanes subject to those regulations, and existing maintenance practices for fuel tank PO 00000 Frm 00008 Fmt 4702 Sfmt 4702 67871 systems. As a result of those findings, we issued a regulation titled ‘‘Transport Airplane Fuel Tank System Design Review, Flammability Reduction and Maintenance and Inspection Requirements’’ (66 FR 23086, May 7, 2001). In addition to new airworthiness standards for transport airplanes and new maintenance requirements, this rule included Special Federal Aviation Regulation No. 88 (‘‘SFAR 88,’’ Amendment 21–78, and subsequent Amendments 21–82 and 21–83). Among other actions, SFAR 88 requires certain type design (i.e., type certificate (TC) and supplemental type certificate (STC)) holders to substantiate that their fuel tank systems can prevent ignition sources in the fuel tanks. This requirement applies to type design holders for large turbine-powered transport airplanes and for subsequent modifications to those airplanes. It requires them to perform design reviews and to develop design changes and maintenance procedures if their designs do not meet the new fuel tank safety standards. As explained in the preamble to the rule, we intended to adopt airworthiness directives to mandate any changes found necessary to address unsafe conditions identified as a result of these reviews. In evaluating these design reviews, we have established four criteria intended to define the unsafe conditions associated with fuel tank systems that require corrective actions. The percentage of operating time during which fuel tanks are exposed to flammable conditions is one of these criteria. The other three criteria address the failure types under evaluation: single failures, single failures in combination with a latent condition(s), and in-service failure experience. For all four criteria, the evaluations included consideration of previous actions taken that may mitigate the need for further action. We have determined that the actions identified in this AD are necessary to reduce the potential of ignition sources inside fuel tanks, which, in combination with flammable fuel vapors, could result in fuel tank explosions and consequent loss of the airplane. Relevant Service Information Bombardier has issued Service Bulletins 601R–28–051 and 601R–28– 060, both Revision A, both dated March 30, 2005. The actions described in this service information are intended to correct the unsafe condition identified in the MCAI. E:\FR\FM\03DEP1.SGM 03DEP1 67872 Federal Register / Vol. 72, No. 231 / Monday, December 3, 2007 / Proposed Rules FAA’s Determination and Requirements of This 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. Differences Between This AD and the MCAI or Service Information We have reviewed the MCAI and related service information and, in general, agree with their substance. But we might have found it necessary to use different words from those in the MCAI to ensure the AD is clear for U.S. operators and is enforceable. In making these changes, we do not intend to differ substantively from the information provided in the MCAI and related service information. We might also have proposed different actions in this AD from those in the MCAI in order to follow FAA policies. Any such differences are highlighted in a NOTE within the proposed AD. Costs of Compliance Based on the service information, we estimate that this proposed AD would affect about 626 products of U.S. registry. We also estimate that it would take about 31 work-hours per product to comply with the basic requirements of this proposed AD. Required parts would cost a negligible amount per product. Where the service information lists required parts costs that are covered under warranty, we have assumed that there will be no charge for these costs. As we do not control warranty coverage for affected parties, some parties may incur costs higher than estimated here. The average labor rate is $80 per workhour. Based on these figures, we estimate the cost of the proposed AD on U.S. operators to be $1,552,480, or $2,480 per product. yshivers on PROD1PC62 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. VerDate Aug<31>2005 14:41 Nov 30, 2007 Jkt 214001 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. Comments Due Date (a) We must receive comments by January 2, 2008. Regulatory Findings Reason (e) The mandatory continuing airworthiness information (MCAI) states: Bombardier Aerospace has completed a system safety review of the CL–600–2B19 aircraft fuel system against new fuel tank safety standards, introduced in Chapter 525 of the Airworthiness Manual through Notice of Proposed Amendment (NPA) 2002–043. The identified non-compliances were assessed using Transport Canada Policy Letter No. 525–001 to determine if mandatory corrective action is required. The assessment showed that sealant has not been applied to bolts on the collector fuel tanks or the transfer ejector fuel pumps. Lack of sealant on the above-noted locations, if not corrected, could result in arcing and potential ignition source inside the fuel tank during lightning strikes and consequent fuel tank explosion. To correct the unsafe condition, this directive mandates the application of sealant to the bolts that attach various fittings on the collector fuel tanks, [an inspection for a fillet seal and if necessary application of fillet seal] to the edges of the transfer ejector pumps and [an inspection for sealant and if necessary application of sealant] to the bolts that attach the transfer ejector pump to the transfer ejector pump casing. We 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 this proposed regulation: 1. Is not a ‘‘significant regulatory action’’ under Executive Order 12866; 2. Is not a ‘‘significant rule’’ under the DOT Regulatory Policies and Procedures (44 FR 11034, February 26, 1979); and 3. 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. List of Subjects in 14 CFR Part 39 Air transportation, Aircraft, Aviation safety, Safety. The Proposed Amendment Accordingly, under the authority delegated to me by the Administrator, the FAA proposes to amend 14 CFR part 39 as follows: PART 39—AIRWORTHINESS DIRECTIVES 1. The authority citation for part 39 continues to read as follows: Authority: 49 U.S.C. 106(g), 40113, 44701. § 39.13 [Amended] 2. The FAA amends § 39.13 by adding the following new AD: Bombardier, INC. (Formerly Canadair): Docket No. FAA–2007–0262; Directorate Identifier 2007-NM–247-AD. PO 00000 Frm 00009 Fmt 4702 Sfmt 4702 Affected ADs (b) None. Applicability (c) This AD applies to Bombardier Model CL–600–2B19 (Regional Jet Series 100 & 440) airplanes, serial numbers 7003 through 7067 and 7069 through 7924; certificated in any category. Subject (d) Air Transport Association (ATA) of America Code 28: Fuel. Actions and Compliance (f) Unless already done, do the following actions. (1) Within 5,000 flight hours after the effective date of this AD: For airplanes with serial numbers 7003 through 7067 and 7069 through 7797, apply sealant to bolts on the collector fuel tanks according to the Accomplishment Instructions of Bombardier Service Bulletin 601R–28–051, Revision A, dated March 30, 2005. (2) Within 5,000 flight hours after the effective date of this AD: For airplanes with serial numbers 7003 through 7067 and 7069 through 7924, do a general visual inspection of the left and right transfer ejector pumps for the presence of a fillet seal on the edge of the pumps and sealant on the bolts, according to the Accomplishment Instructions of Bombardier Service Bulletin 601R–28–060, Revision A, dated March 30, 2005. (3) If during the inspection required by paragraph (f)(2) of this AD any fillet seal is found missing from the edge of the transfer ejector pump or sealant is found missing from any of the bolts, prior to further flight, E:\FR\FM\03DEP1.SGM 03DEP1 Federal Register / Vol. 72, No. 231 / Monday, December 3, 2007 / Proposed Rules apply fillet seal and sealant as applicable to the affected areas according to the Accomplishment Instructions of Bombardier Service Bulletin 601R–28–060, Revision A, dated March 30, 2005. (4) Application of sealant prior to the effective date of this AD according to Bombardier Service bulletin 601R–28–051, dated May 12, 2003, satisfies the requirements of paragraph (f)(1) of this AD. (5) Inspection and application of sealant and fillet seal prior to the effective date of this AD according to Bombardier Service Bulletin 601R–28–060, dated January 28, 2004, satisfy the corresponding requirements of paragraphs (f)(2) and (f)(3) of this AD. FAA AD Differences Note: This AD differs from the MCAI and/ or service information as follows: No Differences. Other FAA AD Provisions (g) The following provisions also apply to this AD: (1) Alternative Methods of Compliance (AMOCs): The Manager, New York Aircraft Certification Office, 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: Rocco Viselli, 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) 228–7331; fax (516) 794–5531. 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. (2) Airworthy Product: For any requirement in this AD to obtain corrective actions from a manufacturer or other source, use these actions if they are FAA-approved. Corrective actions are considered FAAapproved if they are approved by the State of Design Authority (or their delegated agent). You are required to assure the product is airworthy before it is returned to service. (3) Reporting Requirements: For any reporting requirement in this AD, under the provisions of the Paperwork Reduction Act, the Office of Management and Budget (OMB) has approved the information collection requirements and has assigned OMB Control Number 2120–0056. Related Information yshivers on PROD1PC62 with PROPOSALS (h) Refer to MCAI Canadian Airworthiness Directive CF–2007–17, dated September 4, 2007, and Bombardier Service Bulletins 601R–28–051 and 601R–28–060, both Revision A, both dated March 30, 2005, for related information. Issued in Renton, Washington, on November 23, 2007. Ali Bahrami, Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. E7–23339 Filed 11–30–07; 8:45 am] BILLING CODE 4910–13–P VerDate Aug<31>2005 14:41 Nov 30, 2007 Jkt 214001 DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2007–0265; Directorate Identifier 2007–NM–213–AD] RIN 2120–AA64 Airworthiness Directives; Boeing Model 727 Airplanes Federal Aviation Administration (FAA), Department of Transportation (DOT). ACTION: Notice of proposed rulemaking (NPRM). AGENCY: SUMMARY: The FAA proposes to adopt a new airworthiness directive (AD) for all Boeing Model 727 airplanes. This proposed AD would require repetitive inspections for any cracking of or damage to the left side and right side flight deck No. 2, No. 4, and No. 5 windows, as necessary, and corrective actions if necessary. This proposed AD results from reports of in-flight departure and separation of the flight deck windows. We are proposing this AD to detect and correct cracking in the vinyl interlayer or damage to the structural inner glass panes of the flight deck No. 2, No. 4, and No. 5 windows, which could result in loss of a window and rapid loss of cabin pressure. Loss of cabin pressure could cause crew communication difficulties or crew incapacitation. We must receive comments on this proposed AD by January 17, 2008. ADDRESSES: You may send comments by any of the following methods: • Federal eRulemaking Portal: Go to http://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 Boeing Commercial Airplanes, P.O. Box 3707, Seattle, Washington 98124–2207. DATES: Examining the AD Docket You may examine the AD docket on the Internet at http:// www.regulations.gov; or in person at the PO 00000 Frm 00010 Fmt 4702 Sfmt 4702 67873 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: Berhane Alazar, Aerospace Engineer, Airframe Branch, ANM–120S, FAA, Seattle Aircraft Certification Office, 1601 Lind Avenue, SW., Renton, Washington 98057–3356; telephone (425) 917–6577; fax (425) 917–6590. 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–2007–0265; Directorate Identifier 2007–NM–213–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 http:// 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 We have received one report of inflight departure of the flight deck No. 3 window, on a Boeing Model 747 series airplane, which resulted in rapid loss of cabin pressure and an emergency landing. That airplane had accumulated 36,131 total flight hours and 5,607 total flight cycles. We have also received two reports of in-flight separation of the left side flight deck No. 5 window, on two Boeing Model 737 series airplanes. One of the Model 737 series airplanes experienced cabin pressure loss at 12,500 feet due to separation of the forward, aft, and upper edges of the left side flight deck No. 5 window. That airplane had accumulated 25,673 total flight hours and 15,669 total flight cycles. The other Model 737 series airplane experienced a pressure leak at 29,000 feet due to partial separation of the upper aft corner of the left side flight deck No. 5 window. That airplane had E:\FR\FM\03DEP1.SGM 03DEP1

Agencies

[Federal Register Volume 72, Number 231 (Monday, December 3, 2007)]
[Proposed Rules]
[Pages 67870-67873]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: E7-23339]


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

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2007-0262; Directorate Identifier 2007-NM-247-AD]
RIN 2120-AA64


Airworthiness Directives; Bombardier Model CL-600-2B19 (Regional 
Jet Series 100 & 440) Airplanes

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Notice of proposed rulemaking (NPRM).

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

SUMMARY: We propose to adopt a new airworthiness directive (AD) for the

[[Page 67871]]

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:

    Bombardier Aerospace has completed a system safety review of the 
CL-600-2B19 aircraft fuel system * * *.
    The assessment showed that sealant has not been applied to bolts 
on the collector fuel tanks or the transfer ejector fuel pumps. Lack 
of sealant on the above-noted locations, if not corrected, could 
result in arcing and potential ignition source inside the fuel tank 
during lightning strikes and consequent fuel tank explosion. * * *

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 January 2, 2008.

ADDRESSES: You may send comments by any of the following methods:
     Federal eRulemaking Portal: Go to http://
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 http://
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 the ADDRESSES section. Comments will be available in the AD docket 
shortly after receipt.

FOR FURTHER INFORMATION CONTACT: Rocco Viselli, 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) 228-7331; 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-2007-0262; 
Directorate Identifier 2007-NM-247-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 http://
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-
2007-17, dated September 4, 2007 (referred to after this as ``the 
MCAI''), to correct an unsafe condition for the specified products. The 
MCAI states:

    Bombardier Aerospace has completed a system safety review of the 
CL-600-2B19 aircraft fuel system against new fuel tank safety 
standards, introduced in Chapter 525 of the Airworthiness Manual 
through Notice of Proposed Amendment (NPA) 2002-043. The identified 
non-compliances were assessed using Transport Canada Policy Letter 
No. 525-001 to determine if mandatory corrective action is required.
    The assessment showed that sealant has not been applied to bolts 
on the collector fuel tanks or the transfer ejector fuel pumps. Lack 
of sealant on the above-noted locations, if not corrected, could 
result in arcing and potential ignition source inside the fuel tank 
during lightning strikes and consequent fuel tank explosion. To 
correct the unsafe condition, this directive mandates the 
application of sealant to the bolts that attach various fittings on 
the collector fuel tanks, [an inspection for a fillet seal and if 
necessary application of fillet seal] to the edges of the transfer 
ejector pumps and [an inspection for sealant and if necessary 
application of sealant] to the bolts that attach the transfer 
ejector pump to the transfer ejector pump casing.

You may obtain further information by examining the MCAI in the AD 
docket.
    The FAA has examined the underlying safety issues involved in fuel 
tank explosions on several large transport airplanes, including the 
adequacy of existing regulations, the service history of airplanes 
subject to those regulations, and existing maintenance practices for 
fuel tank systems. As a result of those findings, we issued a 
regulation titled ``Transport Airplane Fuel Tank System Design Review, 
Flammability Reduction and Maintenance and Inspection Requirements'' 
(66 FR 23086, May 7, 2001). In addition to new airworthiness standards 
for transport airplanes and new maintenance requirements, this rule 
included Special Federal Aviation Regulation No. 88 (``SFAR 88,'' 
Amendment 21-78, and subsequent Amendments 21-82 and 21-83).
    Among other actions, SFAR 88 requires certain type design (i.e., 
type certificate (TC) and supplemental type certificate (STC)) holders 
to substantiate that their fuel tank systems can prevent ignition 
sources in the fuel tanks. This requirement applies to type design 
holders for large turbine-powered transport airplanes and for 
subsequent modifications to those airplanes. It requires them to 
perform design reviews and to develop design changes and maintenance 
procedures if their designs do not meet the new fuel tank safety 
standards. As explained in the preamble to the rule, we intended to 
adopt airworthiness directives to mandate any changes found necessary 
to address unsafe conditions identified as a result of these reviews.
    In evaluating these design reviews, we have established four 
criteria intended to define the unsafe conditions associated with fuel 
tank systems that require corrective actions. The percentage of 
operating time during which fuel tanks are exposed to flammable 
conditions is one of these criteria. The other three criteria address 
the failure types under evaluation: single failures, single failures in 
combination with a latent condition(s), and in-service failure 
experience. For all four criteria, the evaluations included 
consideration of previous actions taken that may mitigate the need for 
further action.
    We have determined that the actions identified in this AD are 
necessary to reduce the potential of ignition sources inside fuel 
tanks, which, in combination with flammable fuel vapors, could result 
in fuel tank explosions and consequent loss of the airplane.

Relevant Service Information

    Bombardier has issued Service Bulletins 601R-28-051 and 601R-28-
060, both Revision A, both dated March 30, 2005. The actions described 
in this service information are intended to correct the unsafe 
condition identified in the MCAI.

[[Page 67872]]

FAA's Determination and Requirements of This 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.

Differences Between This AD and the MCAI or Service Information

    We have reviewed the MCAI and related service information and, in 
general, agree with their substance. But we might have found it 
necessary to use different words from those in the MCAI to ensure the 
AD is clear for U.S. operators and is enforceable. In making these 
changes, we do not intend to differ substantively from the information 
provided in the MCAI and related service information.
    We might also have proposed different actions in this AD from those 
in the MCAI in order to follow FAA policies. Any such differences are 
highlighted in a NOTE within the proposed AD.

Costs of Compliance

    Based on the service information, we estimate that this proposed AD 
would affect about 626 products of U.S. registry. We also estimate that 
it would take about 31 work-hours per product to comply with the basic 
requirements of this proposed AD. Required parts would cost a 
negligible amount per product. Where the service information lists 
required parts costs that are covered under warranty, we have assumed 
that there will be no charge for these costs. As we do not control 
warranty coverage for affected parties, some parties may incur costs 
higher than estimated here. The average labor rate is $80 per work-
hour. Based on these figures, we estimate the cost of the proposed AD 
on U.S. operators to be $1,552,480, or $2,480 per product.

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 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 this proposed 
regulation:
    1. Is not a ``significant regulatory action'' under Executive Order 
12866;
    2. Is not a ``significant rule'' under the DOT Regulatory Policies 
and Procedures (44 FR 11034, February 26, 1979); and
    3. 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.

List of Subjects in 14 CFR Part 39

    Air transportation, Aircraft, Aviation safety, Safety.

The Proposed Amendment

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

PART 39--AIRWORTHINESS DIRECTIVES

    1. The authority citation for part 39 continues to read as follows:

    Authority: 49 U.S.C. 106(g), 40113, 44701.


Sec.  39.13  [Amended]

    2. The FAA amends Sec.  39.13 by adding the following new AD:

Bombardier, INC. (Formerly Canadair): Docket No. FAA-2007-0262; 
Directorate Identifier 2007-NM-247-AD.

Comments Due Date

    (a) We must receive comments by January 2, 2008.

Affected ADs

    (b) None.

Applicability

    (c) This AD applies to Bombardier Model CL-600-2B19 (Regional 
Jet Series 100 & 440) airplanes, serial numbers 7003 through 7067 
and 7069 through 7924; certificated in any category.

Subject

    (d) Air Transport Association (ATA) of America Code 28: Fuel.

Reason

    (e) The mandatory continuing airworthiness information (MCAI) 
states:
    Bombardier Aerospace has completed a system safety review of the 
CL-600-2B19 aircraft fuel system against new fuel tank safety 
standards, introduced in Chapter 525 of the Airworthiness Manual 
through Notice of Proposed Amendment (NPA) 2002-043. The identified 
non-compliances were assessed using Transport Canada Policy Letter 
No. 525-001 to determine if mandatory corrective action is required.
    The assessment showed that sealant has not been applied to bolts 
on the collector fuel tanks or the transfer ejector fuel pumps. Lack 
of sealant on the above-noted locations, if not corrected, could 
result in arcing and potential ignition source inside the fuel tank 
during lightning strikes and consequent fuel tank explosion. To 
correct the unsafe condition, this directive mandates the 
application of sealant to the bolts that attach various fittings on 
the collector fuel tanks, [an inspection for a fillet seal and if 
necessary application of fillet seal] to the edges of the transfer 
ejector pumps and [an inspection for sealant and if necessary 
application of sealant] to the bolts that attach the transfer 
ejector pump to the transfer ejector pump casing.

Actions and Compliance

    (f) Unless already done, do the following actions.
    (1) Within 5,000 flight hours after the effective date of this 
AD: For airplanes with serial numbers 7003 through 7067 and 7069 
through 7797, apply sealant to bolts on the collector fuel tanks 
according to the Accomplishment Instructions of Bombardier Service 
Bulletin 601R-28-051, Revision A, dated March 30, 2005.
    (2) Within 5,000 flight hours after the effective date of this 
AD: For airplanes with serial numbers 7003 through 7067 and 7069 
through 7924, do a general visual inspection of the left and right 
transfer ejector pumps for the presence of a fillet seal on the edge 
of the pumps and sealant on the bolts, according to the 
Accomplishment Instructions of Bombardier Service Bulletin 601R-28-
060, Revision A, dated March 30, 2005.
    (3) If during the inspection required by paragraph (f)(2) of 
this AD any fillet seal is found missing from the edge of the 
transfer ejector pump or sealant is found missing from any of the 
bolts, prior to further flight,

[[Page 67873]]

apply fillet seal and sealant as applicable to the affected areas 
according to the Accomplishment Instructions of Bombardier Service 
Bulletin 601R-28-060, Revision A, dated March 30, 2005.
    (4) Application of sealant prior to the effective date of this 
AD according to Bombardier Service bulletin 601R-28-051, dated May 
12, 2003, satisfies the requirements of paragraph (f)(1) of this AD.
    (5) Inspection and application of sealant and fillet seal prior 
to the effective date of this AD according to Bombardier Service 
Bulletin 601R-28-060, dated January 28, 2004, satisfy the 
corresponding requirements of paragraphs (f)(2) and (f)(3) of this 
AD.

FAA AD Differences

    Note: This AD differs from the MCAI and/or service information 
as follows: No Differences.

Other FAA AD Provisions

    (g) The following provisions also apply to this AD:
    (1) Alternative Methods of Compliance (AMOCs): The Manager, New 
York Aircraft Certification Office, 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: Rocco Viselli, 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) 228-7331; fax (516) 794-
5531. 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.
    (2) Airworthy Product: For any requirement in this AD to obtain 
corrective actions from a manufacturer or other source, use these 
actions if they are FAA-approved. Corrective actions are considered 
FAA-approved if they are approved by the State of Design Authority 
(or their delegated agent). You are required to assure the product 
is airworthy before it is returned to service.
    (3) Reporting Requirements: For any reporting requirement in 
this AD, under the provisions of the Paperwork Reduction Act, the 
Office of Management and Budget (OMB) has approved the information 
collection requirements and has assigned OMB Control Number 2120-
0056.

Related Information

    (h) Refer to MCAI Canadian Airworthiness Directive CF-2007-17, 
dated September 4, 2007, and Bombardier Service Bulletins 601R-28-
051 and 601R-28-060, both Revision A, both dated March 30, 2005, for 
related information.

    Issued in Renton, Washington, on November 23, 2007.
Ali Bahrami,
Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. E7-23339 Filed 11-30-07; 8:45 am]
BILLING CODE 4910-13-P