Airworthiness Directives; Bombardier Model CL-600-2B19 (Regional Jet Series 100 & 440) Airplanes, 55315-55321 [05-18794]

Download as PDF Federal Register / Vol. 70, No. 182 / Wednesday, September 21, 2005 / Proposed Rules DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2005–22481; Directorate Identifier 2004–NM–176–AD] RIN 2120–AA64 Airworthiness Directives; Bombardier Model CL–600–2B19 (Regional Jet Series 100 & 440) Airplanes Federal Aviation Administration (FAA), Department of Transportation (DOT). ACTION: Notice of proposed rulemaking (NPRM). AGENCY: The FAA proposes to supersede an existing airworthiness directive (AD) that applies to certain Bombardier Model CL–600–2B19 (Regional Jet Series 100 & 440) airplanes. The existing AD currently requires revising the Airplane Flight Manual (AFM) to provide the flightcrew with revised procedures for checking the flap system. The existing AD also requires revising the maintenance program to provide procedures for checking the flap system, and performing follow-on actions, if necessary. This proposed AD would require installing new flap actuators, a new or retrofitted air data computer, a new skew detection system, and new airspeed limitation placards; and revising the AFM to include revised maximum allowable speeds for flight with the flaps extended, and a new skew detection system/crosswindrelated limitation for take-off flap selection. This proposed AD is prompted by a number of cases of flap system failure that resulted in a twisted outboard flap panel. We are proposing this AD to prevent an unannunciated failure of the flap system, which could result in a flap asymmetry and consequent reduced controllability of the airplane. DATES: We must receive comments on this proposed AD by October 21, 2005. ADDRESSES: Use one of the following addresses to submit comments on this proposed AD. • DOT Docket Web site: Go to https://dms.dot.gov and follow the instructions for sending your comments electronically. • Government-wide rulemaking Web site: Go to https://www.regulations.gov and follow the instructions for sending your comments electronically. • Mail: Docket Management Facility; U.S. Department of Transportation, 400 Seventh Street SW., Nassif Building, room PL–401, Washington, DC 20590. SUMMARY: VerDate Aug<31>2005 14:37 Sep 20, 2005 Jkt 205001 • Fax: (202) 493–2251. • Hand Delivery: Room PL–401 on the plaza level of the Nassif Building, 400 Seventh Street SW., Washington, DC, between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. For service information identified in this proposed AD, contact Bombardier, Inc., Canadair, Aerospace Group, P.O. Box 6087, Station Centre-ville, Montreal, Quebec H3C 3G9, Canada. You can examine the contents of this AD docket on the Internet at https:// dms.dot.gov, or in person at the Docket Management Facility, U.S. Department of Transportation, 400 Seventh Street SW., room PL–401, on the plaza level of the Nassif Building, Washington, DC. This docket number is FAA–2005– 22481; the directorate identifier for this docket is 2004–NM–176–AD. FOR FURTHER INFORMATION CONTACT: Daniel Parrillo, Aerospace Engineer, Systems and Flight Test Branch, ANE– 172, FAA, New York Aircraft Certification Office, 1600 Stewart Avenue, Suite 410, Westbury, New York 11590; telephone (516) 228–7305; fax (516) 794–5531. SUPPLEMENTARY INFORMATION: Comments Invited We invite you to submit any relevant written data, views, or arguments regarding this proposed AD. Send your comments to an address listed under ADDRESSES. Include ‘‘Docket No. FAA– 2005–22481; Directorate Identifier 2004–NM–176–AD’’ at the beginning of your comments. We specifically invite comments on the overall regulatory, economic, environmental, and energy aspects of the proposed AD. We will consider all comments received by the closing date and may amend the proposed AD in light of those comments. We will post all comments we receive, without change, to https:// dms.dot.gov, including any personal information you provide. We will also post a report summarizing each substantive verbal contact with FAA personnel concerning this proposed AD. Using the search function of our docket Web site, anyone can find and read the comments in any of our dockets, including the name of the individual who sent the comment (or signed the comment on behalf of an association, business, labor union, etc.). You can review the DOT’s complete Privacy Act Statement in the Federal Register published on April 11, 2000 (65 FR 19477–78), or you can visit https:// dms.dot.gov. PO 00000 Frm 00008 Fmt 4702 Sfmt 4702 55315 Examining the Docket You can examine the AD docket on the Internet at https://dms.dot.gov, or in person at the Docket Management Facility office between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. The Docket Management Facility office (telephone (800) 647–5227) is located on the plaza level of the Nassif Building at the DOT street address stated in the ADDRESSES section. Comments will be available in the AD docket shortly after the Docket Management System (DMS) receives them. Discussion On September 17, 1998, we issued AD 98–20–01, amendment 39–10767 (63 FR 49661, September 17, 1998), for certain Bombardier Model CL–600–2B19 (Regional Jet Series 100) series airplanes. That AD requires revising the airplane flight manual (AFM) to provide the flight crew with revised procedures for checking the flap system. That AD also requires revising the maintenance program to provide procedures for checking the flap system, and performing follow-on actions, if necessary. That AD was prompted by issuance of mandatory continuing airworthiness information by a civil airworthiness authority of another country. We issued that AD to prevent an unannunciated failure of the flap system, which could result in a flap asymmetry, and consequent reduced controllability of the airplane. Actions Since Existing AD Was Issued A number of flap systems had failed and caused twisted outboard flap panels before we issued AD 98–20–01. An internal fault within the number 3 flap actuator (the inboard actuator on the outboard flap) caused the failures. In one case, a twisted flap was not detected before take-off, while in other cases the twisted flap occurred on deployment of the flaps for landing. In all cases the airplane was controllable and landed successfully. Several other cases have occurred while the airplanes were on the ground. Since we issued AD 98–20–01, Transport Canada Civil Aviation (TCCA) has issued its applicable revised airworthiness directive, CF–1998–14R4, dated June 1, 2004 (AD 98–20–01 refers to CF–1998–14, dated July 6, 1998). The revision to airworthiness directive CF– 1998–14 changes the text of the revisions to the airplane flight manual (AFM) that were mandated by TCCA and that we also mandated in AD 98– 20–01. In addition, the revision to airworthiness directive CF–1998–14 E:\FR\FM\21SEP1.SGM 21SEP1 55316 Federal Register / Vol. 70, No. 182 / Wednesday, September 21, 2005 / Proposed Rules also mandates the following: installing new airspeed limitation placards and decals; doing certain maintenance actions following a ‘‘FLAPS FAIL’’ caution message, including replacing both actuators if necessary; establishing a ‘‘health check’’ program for the number 3 flap actuator which includes incorporating Canadair Temporary Revision (TR) RJ/71 into the Canadair Regional Jet AFM (to reflect the airspeed limitations); installing new flap actuators, a new or retrofitted air data computer (ADC), and a new skew detection system (SDS) for the outboard flaps; and revising the Limitations section of the Canadair Regional Jet AFM to include the information specified in Canadair TR RJ/128, to include revised maximum allowable speeds for flight with the flaps extended (VFE), and a new SDS/crosswind-related limitation for take-off flap selection. In addition, in the preamble to AD 98–20–01 we specified that we considered the requirements ‘‘interim action’’ and that the manufacturer was developing a modification to address the unsafe condition. That AD explained that we may consider further rulemaking if a final action is identified. The final action has now been identified, and we have determined that further rulemaking is indeed necessary; this proposed AD follows from that determination. Relevant Service Information Bombardier (Canadair) has issued TR RJ/128, dated November 28, 2003, to the Canadair Regional Jet AFM, CSP A–102. This TR includes revised VFE values, and a new SDS/crosswind-related limitation for take-off flap selection. Bombardier (Canadair) has also issued the service bulletins identified in the following table, for Bombardier Model CL–600–2B19 (Regional Jet Series 100 & 440) airplanes having serial numbers 7003 through 7903 inclusive as identified in each service bulletin. BOMBARDIER (CANADAIR) SERVICE BULLETINS Bombardier Service Bulletin Revision Date Procedure 601R–11–080 ............................... 601R–27–111 ............................... 601R–27–114, including Appendix A. 601R–27–115 ............................... 601R–27–116 ............................... 601R–34–128 ............................... Original ...... Original ...... B ................ November 28, 2003 ....... March 6, 2000 ................ December 4, 2003 ......... D ................ B ................ B ................ March 18, 2004 .............. February 2, 2004 ........... September 7, 2001 ........ Install new airspeed limitation placards. Remove decal. Replace #3 inboard and #4 outboard flap actuators for the outboard flaps. Install electrical provisions for the SDS. Install and activate the SDS. Install the air data computer (ADC) containing software with reduced flap overspeed. Accomplishing the actions specified in the service information is intended to adequately address the unsafe condition. TCCA mandated the service information, and issued Canadian airworthiness directive CF–1998–14R4, dated June 1, 2004, to ensure the continued airworthiness of these airplanes in Canada. FAA’s Determination and Requirements of the Proposed AD These airplane models are manufactured in Canada and are type certificated for operation in the United States under the provisions of section 21.29 of the Federal Aviation Regulations (14 CFR 21.29) and the applicable bilateral airworthiness agreement. Pursuant to this bilateral airworthiness agreement, TCCA has kept the FAA informed of the situation described above. We have examined TCCA’s findings, evaluated all pertinent information, and determined that AD action is necessary for airplanes of this type design that are certificated for operation in the United States. This proposed AD would supersede AD 98–20–01. This proposed AD would retain the requirements of the existing AD. This proposed AD also would require installing new flap actuators, a new or retrofitted air data computer, a new skew detection system, and new airspeed limitation placards; and revising the AFM to include revised VerDate Aug<31>2005 14:37 Sep 20, 2005 Jkt 205001 maximum allowable speeds for flight with the flaps extended, and a new skew detection system/crosswindrelated limitation for take-off flap selection. Doing the new proposed actions would terminate the requirements of the existing AD. Difference Between the Proposed AD and the Canadian Airworthiness Directive The Canadian airworthiness directive includes several actions that are not included in this proposed AD: incorporating revised AFM procedures for checking the flap system; installing new airspeed limitation placards and decals; doing certain maintenance actions following a ‘‘FLAPS FAIL’’ caution message, including replacing both actuators if necessary; establishing a ‘‘health check’’ program for the number 3 flap actuator; and incorporating TR RJ/71 into the AFM (to reflect the airspeed limitations). We have determined that these actions were mandated by TCCA as interim actions until a final action was developed by the manufacturer. We find that the revision to the AFM that was previously mandated by AD 98–20–01 provides an adequate level of safety without our mandating the interim actions specified in the Canadian airworthiness directive. Mandating these interim actions would add an additional cost burden to operators without improving safety. PO 00000 Frm 00009 Fmt 4702 Sfmt 4702 This difference has been coordinated with TCCA. Changes to Existing AD This proposed AD would retain all requirements of AD 98–20–01. Since AD 98–20–01 was issued, the AD format has been revised, and certain paragraphs have been rearranged. As a result, the corresponding paragraph identifiers have changed in this proposed AD, as listed in the following table: REVISED PARAGRAPH IDENTIFIERS Requirement in AD 98–20–01 Paragraph (a) ............ Paragraph (b) ............ Corresponding requirement in this proposed AD Paragraph (f). Paragraph (g). In addition, Note 2 from the existing AD has been changed to Note 1. The information from Note 1 in AD 98–20– 01 has been incorporated into paragraph (l) of this proposed AD. Explanation of Change to Applicability We have revised the applicability to reflect the model designations as published in the most recent type certificate data sheets. Costs of Compliance The following table provides the estimated costs for U.S. operators to comply with this proposed AD. For all actions the average labor rate is $65 and E:\FR\FM\21SEP1.SGM 21SEP1 Federal Register / Vol. 70, No. 182 / Wednesday, September 21, 2005 / Proposed Rules 55317 the number of U.S.-registered airplanes is 651. ESTIMATED COSTS Work hours Action Revise the AFM (required by AD 98–20–01) ................................................................. Revise the maintenance (required by AD 98–20–01) .................................................... Install ADC (new proposed action) ................................................................................. Install #3 and #4 flap actuators (new proposed action) ................................................. Install skew detection system (new proposed action) .................................................... Install new airspeed limitation placards (new proposed action) ..................................... Revise the AFM (new proposed 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. See the ADDRESSES section for a location to examine the regulatory evaluation. VerDate Aug<31>2005 14:37 Sep 20, 2005 Jkt 205001 1 1 1 18 147 1 1 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 removing amendment 39–10767 (63 FR 49661, September 17, 1998) and adding the following new airworthiness directive (AD): Bombardier, Inc. (Formerly Canadair): Docket No. FAA–2005–22481; Directorate Identifier 2004–NM–176–AD. Comments Due Date (a) The Federal Aviation Administration must receive comments on this AD action by October 21, 2005. Affected ADs (b) This AD supersedes AD 98–20–01. Applicability (c) This AD applies to Bombardier Model CL–600–2B19 (Regional Jet Series 100 & 400) airplanes, certificated in any category, serial numbers 7003 through 7903 inclusive. Unsafe Condition (d) This AD was prompted by a number of cases of flap system failure that resulted in a twisted outboard flap panel. We are issuing this AD to prevent an unannunciated failure of the flap system, which could result in a flap asymmetry and consequent reduced controllability of the airplane. Compliance (e) You are responsible for having the actions required by this AD performed within the compliance times specified, unless the actions have already been done. PO 00000 Frm 00010 Fmt 4702 Sfmt 4702 Parts N/A ................... N/A ................... No Charge ........ No Charge ........ No Charge ........ No Charge ........ N/A .................... Cost per airlane $65 65 65 1,170 9,555 65 65 Fleet cost $42,315 42,315 42,315 761,670 6,220,305 42,315 42,315 Restatement of the Requirements of AD 98– 20–01 Note 1: Bombardier Service Letter RJ–SL– 27–002A, dated April 8, 1998, and Service Letter RJ–SL–27–037, dated July 2, 1998, may provide operators with additional information concerning the actions required by this AD. However, accomplishment of the procedures specified in these service letters should not be considered to be an acceptable method of compliance with the requirements of this AD. (f) Within 10 days after October 2, 1998 (the effective date of AD 98–20–01), accomplish the requirements of paragraphs (f)(1), (f)(2), and (f)(3) of this AD. (1) Revise the Limitations Section of the FAA-approved airplane flight manual (AFM) to include the following procedures and Figures 1 and 2 of this AD. After accomplishing the actions in paragraphs (h) and (i) of this AD, remove the revisions required by this paragraph of this AD from the AFM. ‘‘Air Operator Actions IMPORTANT: If the outboard flap position is outside the ‘GO’ range, as shown in figure 2., further flight is prohibited until required maintenance actions have been accomplished. 1. Touch-and-go landings for the purposes of training must be accomplished using a flap setting of 20 degrees for the entire procedure. 2. (a) Take-off flaps must be set prior to departure, and (b) An external visual check must be accomplished to detect any twisting, skewing, or abnormal deformation of the flaps, using the information given in Figures 1 and 2. Note 1: If the outboard flap position is outside the ‘GO’ range as shown in figure 2., further flight is prohibited until required maintenance actions have been accomplished. Note 2: This visual check must be accomplished either by a member of the flight crew or by maintenance personnel, and the results reported directly to the pilot-incommand prior to take-off. 3. If any additional change to the flap position is necessary, prior to take-off, accomplish the visual check specified by the preceding paragraph 2. (b).’’ (2) Revise the Normal Procedures Section of the FAA-approved AFM to include the following procedures: E:\FR\FM\21SEP1.SGM 21SEP1 Federal Register / Vol. 70, No. 182 / Wednesday, September 21, 2005 / Proposed Rules ‘‘To minimize a possible flap twist in flight when operating flaps, operate the flap selector sequentially, stopping at each setting (i.e., 0 degrees, 8 degrees if applicable, 20 degrees, 30 degrees, 45 degrees; or operate the flap selector in reverse order), and waiting for the flaps to reach each position before selecting the next setting. Monitor the control wheel for abnormal control wheel angles during each transition in flap position. Note: This procedure is not applicable during a go-around or during any emergency aircraft handling procedure where prompt flap retraction is required. In these cases, follow the applicable AFM procedures.’’ (3) Revise the Abnormal Procedures Section of the FAA-approved AFM to include the following procedures. VerDate Aug<31>2005 14:37 Sep 20, 2005 Jkt 205001 ‘‘If abnormal aileron control wheel angles develop during flap operation with the autopilot on, or if the aircraft rolls without pilot input with the autopilot off (with or without a ‘FLAPS FAIL’ caution message), perform the following actions: 1. If flaps are being extended, immediately return the flaps to the previously selected position (e.g., for flaps selected from 8 degrees to 20 degrees, re-select 8 degrees). 2. If flaps are being retracted, the flap selector should remain in the currently selected position (e.g., for flaps selected from 20 degrees to 8 degrees, leave selector at 8 degrees). 3. Do not attempt to operate the flaps any further. 4. If the flaps are engaged, disconnect the autopilot. PO 00000 Frm 00011 Fmt 4702 Sfmt 4725 Note: When disconnecting the autopilot, anticipate an out-of-trim situation and hold the aileron control wheel in its current position. 5. For landing, perform the ‘Flaps Failure’ procedure for the following conditions: (a) If an abnormal aileron control wheel angle to the left develops, do not land if a crosswind from the left is greater than 20 knots. (b) If an abnormal aileron control wheel angle to the right develops, do not land if a crosswind from the right is greater than 20 knots. 6. After landing, do not attempt to retract the flaps. Record the event in the Aircraft Maintenance Log Book and notify the person responsible for maintenance.’’ BILLING CODE 4910–13–P E:\FR\FM\21SEP1.SGM 21SEP1 EP21SE05.020</GPH> 55318 Federal Register / Vol. 70, No. 182 / Wednesday, September 21, 2005 / Proposed Rules 55319 VerDate Aug<31>2005 14:37 Sep 20, 2005 Jkt 205001 PO 00000 Frm 00012 Fmt 4702 Sfmt 4702 E:\FR\FM\21SEP1.SGM 21SEP1 EP21SE05.021</GPH> BILLING CODE 4910–13—C 55320 Federal Register / Vol. 70, No. 182 / Wednesday, September 21, 2005 / Proposed Rules (g) Within 10 days after October 2, 1998, revise the FAA-approved maintenance program to include the following procedures and Figures 1 and 2 of this AD: ‘‘Maintenance Procedure Whenever a ‘FLAPS FAIL’ caution message occurs, carry out the following procedures after landing: Note: These procedures are to be accomplished by maintenance personnel only. 1. Check that there have been no other ‘FLAPS FAIL’ caution messages reported within the previous 72 hours. If a previous message has been reported, prior to further flight, perform the actions required in the following Maintenance Action section. If no previous ‘FLAPS FAIL’ caution message has been reported, continue with the following: 2. Carry out an external visual check of each outboard flap for evidence of twisting, skewing, or abnormal deformation. (Reference Figures 1 and 2.) 3. If there is no evidence of twisting, skewing, or abnormal deformation, proceed as follows: (a) Reset the flap system ONLY ONCE by cycling circuit breakers CB1–F4 and CB2–F4. (b) If the system does not reset (i.e., the ‘FLAPS FAIL’ caution message is still posted), prior to further flight, perform the actions required in the following Maintenance Action section. (c) If the system resets, cycle the flaps to 45 degrees and back to 0 degrees. Continued flap operation for up to a maximum of 72 hours is then permitted as long as no additional ‘FLAPS FAIL’ caution message is indicated. (d) If an additional ‘FLAPS FAIL’ caution message occurs within the period of 72 hours, as specified above, prior to further flight, perform the actions required in the following Maintenance Action section. (e) Within 72 hours, even if no further ‘FLAPS FAIL’ messages have been indicated, perform the actions required in the following Maintenance Action section. 4. If there is evidence of twisting, skewing, or abnormal deformation, PRIOR TO FURTHER FLIGHT, perform the actions required in the following Maintenance Action section. Maintenance Action Whenever the outboard flap position indicator is outside the ‘GO’ range as shown in Figure 2, or whenever directed to do so by the Maintenance Procedure above, perform the following procedures: A. Interrogate the flap electronic control unit (FECU) per Fault Isolation Manual, Section 27–50–00, ‘Flaps Fault Isolation,’ and rectify as applicable. B. Visually check each flap for evidence of twisting, skewing, or abnormal deformation. 1. If there is no evidence of twisting, skewing, or abnormal deformation, manually isolate any jammed, disconnected, or dragging component; and rectify all discrepant conditions. 2. If there is evidence of twisting, skewing, or abnormal deformation, replace both actuators and any discrepant flap panel with new or serviceable components. In addition, VerDate Aug<31>2005 14:37 Sep 20, 2005 Jkt 205001 inspect flexible shaft(s) inboard of the most outboard actuator removed for discrepancies, and replace any discrepant flexible shaft with a new or serviceable flexible shaft. Note: An acceptable procedure for testing the flap drive breakaway input torque is detailed in Aircraft Maintenance Manual Temporary Revision 27–203, Task 27–53–00– 750–802, dated July 17, 1998. C. Within 3 days after identifying a flap panel twist or logging a ‘FLAPS FAIL’ caution message, notify Bombardier Aerospace, via the Canadair Regional Jet Action Center, of all findings and actions taken.’’ New Requirements of the AD Install New Flap Actuators (h) Within 12 months after the effective date of this AD: Install new Number 3 and Number 4 flap actuators in accordance with the Accomplishment Instructions of Bombardier Service Bulletin 601R–27–114, Revision B, dated December 4, 2003. The actions in paragraph (h) of this AD must be accomplished prior to or concurrently with the actions in paragraph (i) of this AD. Install Skew Detection System (SDS) and Air Data Computer (i) Within 30 months after the effective date of this AD, but after the actions required by paragraph (h) of this AD have been accomplished: install the SDS in accordance with paragraphs (i)(1), (i)(2), (i)(3), (i)(4), and (i)(5) of this AD. These actions must be accomplished in the order stated in this paragraph. Accomplishing the actions in paragraphs (h) and (i) of this AD terminates the requirements of paragraphs (f) and (g) of this AD, and the AFM revisions required by those paragraphs may be removed from the AFM. (1) Install the electrical provisions for the SDS in accordance with the Accomplishment Instructions of Bombardier Service Bulletin 601R–27–115, Revision D, dated March 18, 2004. (2) Install and activate the SDS in accordance with the Accomplishment Instructions of Bombardier Service Bulletin 601R–27–116, Revision B, dated February 2, 2004; and install a new or retrofitted air data computer (ADC) in accordance with the Accomplishment Instructions of Bombardier Service Bulletin 601R–34–128, Revision B, dated September 7, 2001. (3) Install new airspeed limitation placards in accordance with the Accomplishment Instructions of Bombardier Service Bulletin 601R–11–080, dated November 28, 2003. (4) Revise the Limitations section of the AFM to include the information specified in Canadair Temporary Revision (TR) RJ/128, dated November 28, 2003, to Canadair Regional Jet AFM, CSP A–102, to include revised VFE values, and a new SDS and crosswind-related limitation for take-off flap selection. Note 2: The action in paragraph (i)(4) of this AD may be accomplished by inserting a copy of Canadair TR RJ/128 in the AFM. When this temporary revision has been incorporated into the general revisions of the AFM, the general revisions may be inserted PO 00000 Frm 00013 Fmt 4702 Sfmt 4702 in the AFM, provided the information contained in the general revision is identical to that specified in Canadair Temporary Revision RJ/128. (5) For airplanes on which decals stating ‘‘Visually inspect flaps prior to departure’’ have been installed in production or in accordance with an alternative method of compliance (AMOC) granted by the FAA: After the installation required by paragraph (h)(1), (i)(1), (i)(2), (i)(3), and (i)(4) of this AD, remove the decals in accordance with Part A of Bombardier Service Bulletin 601R–27–111, dated March 6, 2000. Note 3: This AD requires revisions to certain operator maintenance documents to include new inspections. Compliance with these inspections is required by 14 CFR 91.403(c). For airplanes that have been previously modified, altered, or repaired in the areas addressed by these inspections, the operator may not be able to accomplish the inspections described in the revisions. In this situation, to comply with 14 CFR 91.403(c), the operator must request approval for an AMOC according to paragraph (1) of this AD. The request should include a description of changes to the required inspections that will ensure the continued damage tolerance of the affected structure. The FAA has provided guidance for this determination in Advisory Circular (AC) 25–1529. Actions Accomplished in Accordance With Previous Revisions of Service Bulletins (j) Actions accomplished before the effective date of this AD according to the service bulletins identified in paragraphs (j)(1) and (j)(2) of this AD, are considered acceptable for compliance with the corresponding action specified in paragraphs (h) and (i) of this AD. (1) For the action in paragraph (h) of this AD: Bombardier Service Bulletin 601R–27– 114, dated March 22, 2002; or Revision A, dated November 6, 2002. (2) For the actions in paragraph (i) of this AD: Bombardier Service Bulletin 601R–27– 116, dated July 23, 2003; or Revision A, dated September 10, 2003. Parts Installation (k)(1) As of 12 months after the effective date of this AD, no person may install on any airplane a flap actuator with part numbers (P/ Ns) 601R93103–5, –6, –7, –8, –9, –10, –11, –12, –17, and –18 (Vendor P/Ns 853D100 –7, –8, –9, –10, –11, –12, –13, –14, –17 and –18). (2) As of 12 months after the effective date of this AD, no person may install on any airplane a flap actuator with P/Ns 601R93104–5, –6, –7, –8, –9 and –10 (Vendor P/Ns 854D100–7, –8, –9, –10, –11 and –12). (3) As of 30 months after the effective date of this AD, no person may install on any airplane an ADC with P/Ns 822–0372–140 and –143. AMOCs (l)(1) The Manager, New York ACO, FAA, has the authority to approve AMOCs for this AD, if requested in accordance with the procedures found in 14 CFR 39.19. (2) AMOCs approved previously according to AD 98–20–01, are approved as AMOCs for the corresponding provisions of this AD. E:\FR\FM\21SEP1.SGM 21SEP1 Federal Register / Vol. 70, No. 182 / Wednesday, September 21, 2005 / Proposed Rules Related Information (m) Canadian airworthiness directive CF– 1998–14R4, dated June 1, 2004, also addresses the subject of this AD. Issued in Renton, Washington, on September 8, 2005. Kalene C. Yanamura, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 05–18794 Filed 9–20–05; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2005–22471; Directorate Identifier 2005–NM–142–AD] RIN 2120–AA64 Airworthiness Directives; Boeing Model 757 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 757 airplanes. This proposed AD would require repetitive measurements of the freeplay of each of the three power control units (PCUs) that move the rudder; repetitive lubrication of rudder components; and corrective actions if necessary. This proposed AD results from a report of freeplay-induced vibration of the rudder. We are proposing this AD to prevent excessive vibration of the airframe during flight, which could result in divergent flutter and loss of control of the airplane. DATES: We must receive comments on this proposed AD by November 7, 2005. ADDRESSES: Use one of the following addresses to submit comments on this proposed AD. • DOT Docket Web site: Go to https://dms.dot.gov and follow the instructions for sending your comments electronically. • Government-wide rulemaking Web site: Go to https://www.regulations.gov and follow the instructions for sending your comments electronically. • Mail: Docket Management Facility, U.S. Department of Transportation, 400 Seventh Street SW., Nassif Building, room PL–401, Washington, DC 20590. • Fax: (202) 493–2251. • Hand Delivery: Room PL–401 on the plaza level of the Nassif Building, 400 Seventh Street SW., Washington, VerDate Aug<31>2005 14:37 Sep 20, 2005 Jkt 205001 55321 DC, between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. Contact Boeing Commercial Airplanes, P.O. Box 3707, Seattle, Washington 98124–2207, for the service information identified in this proposed AD. FOR FURTHER INFORMATION CONTACT: Dennis Stremick, Aerospace Engineer, Airframe Branch, ANM–120S, FAA, Seattle Aircraft Certification Office, 1601 Lind Avenue, SW., Renton, Washington 98055–4056; telephone (425) 917–6450; fax (425) 917–6590. SUPPLEMENTARY INFORMATION: airplane. Excessive corrosion and wear of components and/or interfaces allows excessive freeplay movement of the control surfaces and can cause excessive vibration of the airframe during flight. The point of transition from vibration to divergent flutter is unknown. When divergent flutter occurs, the amplitude of each cycle or oscillation is larger than the last one and the surface can quickly reach its structural limits. This condition, if not corrected, could result in loss of control of the airplane. Comments Invited We invite you to submit any relevant written data, views, or arguments regarding this proposed AD. Include the docket number ‘‘FAA–2005–22471; Directorate Identifier 2005–NM–142– AD’’ at the beginning of your comments. We specifically invite comments on the overall regulatory, economic, environmental, and energy aspects of the proposed AD. We will consider all comments received by the closing date and may amend the proposed AD in light of those comments. We will post all comments we receive, without change, to https:// dms.dot.gov, including any personal information you provide. We will also post a report summarizing each substantive verbal contact with FAA personnel concerning this proposed AD. Using the search function of that web site, anyone can find and read the comments in any of our dockets, including the name of the individual who sent the comment (or signed the comment on behalf of an association, business, labor union, etc.). You may review DOT’s complete Privacy Act Statement in the Federal Register published on April 11, 2000 (65 FR 19477–78), or you may visit https:// dms.dot.gov. We have reviewed Boeing Special Attention Service Bulletin 757–27– 0148, dated June 16, 2005 (for Model 757–200, –200CB, and –200PF series airplanes); and Boeing Special Attention Service Bulletin 757–27–0149, dated June 16, 2005 (for Model 757–300 series airplanes). The service bulletins describe procedures for measuring the freeplay for each of the three power control units (PCUs) that move the rudder. If the freeplay exceeds certain specified limits, the service bulletins describe procedures for doing applicable related investigative and corrective actions. These related investigative and corrective actions include doing a general visual inspection for wear of the affected components such as the rudder hinges, reaction link, reaction link bearings, hanger link, rod end bearings, and rudder hinge bolts, bearings, and bushings; and repairing or replacing the affected part if necessary. The corrective actions also include repeating the freeplay measurement and any related investigative and corrective actions until the maximum rudder freeplay is within acceptable limits. The service bulletins also describe procedures for repetitive lubrication of the rudder hinge, rudder PCU bearings, PCU reaction links, hanger links, and rod end bearings. The service bulletins note that if the freeplay measurement and a lubrication cycle are due at the same time, the freeplay measurement must be satisfactory before the lubrication is done. Accomplishing the actions specified in the service information is intended to adequately address the unsafe condition. Examining the Docket You may examine the AD docket on the Internet at https://dms.dot.gov, or in person at the Docket Management Facility office between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. The Docket Management Facility office (telephone (800) 647–5227) is located on the plaza level of the Nassif Building at the DOT street address stated in the ADDRESSES section. Comments will be available in the AD docket shortly after the Docket Management System receives them. Discussion We have received a report of freeplayinduced flutter of the rudder during flight on a Boeing Model 757–200 series PO 00000 Frm 00014 Fmt 4702 Sfmt 4702 Relevant Service Information FAA’s Determination and Requirements of the Proposed AD We have evaluated all pertinent information and identified an unsafe condition that is likely to exist or develop on other airplanes of this same type design. For this reason, we are proposing this AD, which would require accomplishing the actions specified in E:\FR\FM\21SEP1.SGM 21SEP1

Agencies

[Federal Register Volume 70, Number 182 (Wednesday, September 21, 2005)]
[Proposed Rules]
[Pages 55315-55321]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 05-18794]



[[Page 55315]]

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

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2005-22481; Directorate Identifier 2004-NM-176-AD]
RIN 2120-AA64


Airworthiness Directives; Bombardier Model CL-600-2B19 (Regional 
Jet Series 100 & 440) 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 certain Bombardier Model CL-600-2B19 
(Regional Jet Series 100 & 440) airplanes. The existing AD currently 
requires revising the Airplane Flight Manual (AFM) to provide the 
flightcrew with revised procedures for checking the flap system. The 
existing AD also requires revising the maintenance program to provide 
procedures for checking the flap system, and performing follow-on 
actions, if necessary. This proposed AD would require installing new 
flap actuators, a new or retrofitted air data computer, a new skew 
detection system, and new airspeed limitation placards; and revising 
the AFM to include revised maximum allowable speeds for flight with the 
flaps extended, and a new skew detection system/crosswind-related 
limitation for take-off flap selection. This proposed AD is prompted by 
a number of cases of flap system failure that resulted in a twisted 
outboard flap panel. We are proposing this AD to prevent an 
unannunciated failure of the flap system, which could result in a flap 
asymmetry and consequent reduced controllability of the airplane.

DATES: We must receive comments on this proposed AD by October 21, 
2005.

ADDRESSES: Use one of the following addresses to submit comments on 
this proposed AD.
     DOT Docket Web site: Go to https://dms.dot.gov and follow 
the instructions for sending your comments electronically.
     Government-wide rulemaking Web site: Go to https://
www.regulations.gov and follow the instructions for sending your 
comments electronically.
     Mail: Docket Management Facility; U.S. Department of 
Transportation, 400 Seventh Street SW., Nassif Building, room PL-401, 
Washington, DC 20590.
     Fax: (202) 493-2251.
     Hand Delivery: Room PL-401 on the plaza level of the 
Nassif Building, 400 Seventh Street SW., Washington, DC, between 9 a.m. 
and 5 p.m., Monday through Friday, except Federal holidays.
    For service information identified in this proposed AD, contact 
Bombardier, Inc., Canadair, Aerospace Group, P.O. Box 6087, Station 
Centre-ville, Montreal, Quebec H3C 3G9, Canada.
    You can examine the contents of this AD docket on the Internet at 
https://dms.dot.gov, or in person at the Docket Management Facility, 
U.S. Department of Transportation, 400 Seventh Street SW., room PL-401, 
on the plaza level of the Nassif Building, Washington, DC. This docket 
number is FAA-2005-22481; the directorate identifier for this docket is 
2004-NM-176-AD.

FOR FURTHER INFORMATION CONTACT: Daniel Parrillo, Aerospace Engineer, 
Systems and Flight Test Branch, ANE-172, FAA, New York Aircraft 
Certification Office, 1600 Stewart Avenue, Suite 410, Westbury, New 
York 11590; telephone (516) 228-7305; fax (516) 794-5531.

SUPPLEMENTARY INFORMATION:

Comments Invited

    We invite you to submit any relevant written data, views, or 
arguments regarding this proposed AD. Send your comments to an address 
listed under ADDRESSES. Include ``Docket No. FAA-2005-22481; 
Directorate Identifier 2004-NM-176-AD'' at the beginning of your 
comments. We specifically invite comments on the overall regulatory, 
economic, environmental, and energy aspects of the proposed AD. We will 
consider all comments received by the closing date and may amend the 
proposed AD in light of those comments.
    We will post all comments we receive, without change, to https://
dms.dot.gov, including any personal information you provide. We will 
also post a report summarizing each substantive verbal contact with FAA 
personnel concerning this proposed AD. Using the search function of our 
docket Web site, anyone can find and read the comments in any of our 
dockets, including the name of the individual who sent the comment (or 
signed the comment on behalf of an association, business, labor union, 
etc.). You can review the DOT's complete Privacy Act Statement in the 
Federal Register published on April 11, 2000 (65 FR 19477-78), or you 
can visit https://dms.dot.gov.

Examining the Docket

    You can examine the AD docket on the Internet at https://
dms.dot.gov, or in person at the Docket Management Facility office 
between 9 a.m. and 5 p.m., Monday through Friday, except Federal 
holidays. The Docket Management Facility office (telephone (800) 647-
5227) is located on the plaza level of the Nassif Building at the DOT 
street address stated in the ADDRESSES section. Comments will be 
available in the AD docket shortly after the Docket Management System 
(DMS) receives them.

Discussion

    On September 17, 1998, we issued AD 98-20-01, amendment 39-10767 
(63 FR 49661, September 17, 1998), for certain Bombardier Model CL-600-
2B19 (Regional Jet Series 100) series airplanes. That AD requires 
revising the airplane flight manual (AFM) to provide the flight crew 
with revised procedures for checking the flap system. That AD also 
requires revising the maintenance program to provide procedures for 
checking the flap system, and performing follow-on actions, if 
necessary. That AD was prompted by issuance of mandatory continuing 
airworthiness information by a civil airworthiness authority of another 
country. We issued that AD to prevent an unannunciated failure of the 
flap system, which could result in a flap asymmetry, and consequent 
reduced controllability of the airplane.

Actions Since Existing AD Was Issued

    A number of flap systems had failed and caused twisted outboard 
flap panels before we issued AD 98-20-01. An internal fault within the 
number 3 flap actuator (the inboard actuator on the outboard flap) 
caused the failures. In one case, a twisted flap was not detected 
before take-off, while in other cases the twisted flap occurred on 
deployment of the flaps for landing. In all cases the airplane was 
controllable and landed successfully. Several other cases have occurred 
while the airplanes were on the ground.
    Since we issued AD 98-20-01, Transport Canada Civil Aviation (TCCA) 
has issued its applicable revised airworthiness directive, CF-1998-
14R4, dated June 1, 2004 (AD 98-20-01 refers to CF-1998-14, dated July 
6, 1998). The revision to airworthiness directive CF-1998-14 changes 
the text of the revisions to the airplane flight manual (AFM) that were 
mandated by TCCA and that we also mandated in AD 98-20-01. In addition, 
the revision to airworthiness directive CF-1998-14

[[Page 55316]]

also mandates the following: installing new airspeed limitation 
placards and decals; doing certain maintenance actions following a 
``FLAPS FAIL'' caution message, including replacing both actuators if 
necessary; establishing a ``health check'' program for the number 3 
flap actuator which includes incorporating Canadair Temporary Revision 
(TR) RJ/71 into the Canadair Regional Jet AFM (to reflect the airspeed 
limitations); installing new flap actuators, a new or retrofitted air 
data computer (ADC), and a new skew detection system (SDS) for the 
outboard flaps; and revising the Limitations section of the Canadair 
Regional Jet AFM to include the information specified in Canadair TR 
RJ/128, to include revised maximum allowable speeds for flight with the 
flaps extended (VFE), and a new SDS/crosswind-related 
limitation for take-off flap selection.
    In addition, in the preamble to AD 98-20-01 we specified that we 
considered the requirements ``interim action'' and that the 
manufacturer was developing a modification to address the unsafe 
condition. That AD explained that we may consider further rulemaking if 
a final action is identified. The final action has now been identified, 
and we have determined that further rulemaking is indeed necessary; 
this proposed AD follows from that determination.

Relevant Service Information

    Bombardier (Canadair) has issued TR RJ/128, dated November 28, 
2003, to the Canadair Regional Jet AFM, CSP A-102. This TR includes 
revised VFE values, and a new SDS/crosswind-related limitation for 
take-off flap selection.
    Bombardier (Canadair) has also issued the service bulletins 
identified in the following table, for Bombardier Model CL-600-2B19 
(Regional Jet Series 100 & 440) airplanes having serial numbers 7003 
through 7903 inclusive as identified in each service bulletin.

                                     Bombardier (Canadair) Service Bulletins
----------------------------------------------------------------------------------------------------------------
   Bombardier Service Bulletin         Revision                      Date                       Procedure
----------------------------------------------------------------------------------------------------------------
601R-11-080.....................  Original..........  November 28, 2003................  Install new airspeed
                                                                                          limitation placards.
601R-27-111.....................  Original..........  March 6, 2000....................  Remove decal.
601R-27-114, including Appendix   B.................  December 4, 2003.................  Replace 3
 A.                                                                                       inboard and 4
                                                                                          outboard flap
                                                                                          actuators for the
                                                                                          outboard flaps.
601R-27-115.....................  D.................  March 18, 2004...................  Install electrical
                                                                                          provisions for the
                                                                                          SDS.
601R-27-116.....................  B.................  February 2, 2004.................  Install and activate
                                                                                          the SDS.
601R-34-128.....................  B.................  September 7, 2001................  Install the air data
                                                                                          computer (ADC)
                                                                                          containing software
                                                                                          with reduced flap
                                                                                          overspeed.
----------------------------------------------------------------------------------------------------------------

    Accomplishing the actions specified in the service information is 
intended to adequately address the unsafe condition. TCCA mandated the 
service information, and issued Canadian airworthiness directive CF-
1998-14R4, dated June 1, 2004, to ensure the continued airworthiness of 
these airplanes in Canada.

FAA's Determination and Requirements of the Proposed AD

    These airplane models are manufactured in Canada and are type 
certificated for operation in the United States under the provisions of 
section 21.29 of the Federal Aviation Regulations (14 CFR 21.29) and 
the applicable bilateral airworthiness agreement. Pursuant to this 
bilateral airworthiness agreement, TCCA has kept the FAA informed of 
the situation described above. We have examined TCCA's findings, 
evaluated all pertinent information, and determined that AD action is 
necessary for airplanes of this type design that are certificated for 
operation in the United States.
    This proposed AD would supersede AD 98-20-01. This proposed AD 
would retain the requirements of the existing AD. This proposed AD also 
would require installing new flap actuators, a new or retrofitted air 
data computer, a new skew detection system, and new airspeed limitation 
placards; and revising the AFM to include revised maximum allowable 
speeds for flight with the flaps extended, and a new skew detection 
system/crosswind-related limitation for take-off flap selection. Doing 
the new proposed actions would terminate the requirements of the 
existing AD.

Difference Between the Proposed AD and the Canadian Airworthiness 
Directive

    The Canadian airworthiness directive includes several actions that 
are not included in this proposed AD: incorporating revised AFM 
procedures for checking the flap system; installing new airspeed 
limitation placards and decals; doing certain maintenance actions 
following a ``FLAPS FAIL'' caution message, including replacing both 
actuators if necessary; establishing a ``health check'' program for the 
number 3 flap actuator; and incorporating TR RJ/71 into the AFM (to 
reflect the airspeed limitations). We have determined that these 
actions were mandated by TCCA as interim actions until a final action 
was developed by the manufacturer. We find that the revision to the AFM 
that was previously mandated by AD 98-20-01 provides an adequate level 
of safety without our mandating the interim actions specified in the 
Canadian airworthiness directive. Mandating these interim actions would 
add an additional cost burden to operators without improving safety.
    This difference has been coordinated with TCCA.

Changes to Existing AD

    This proposed AD would retain all requirements of AD 98-20-01. 
Since AD 98-20-01 was issued, the AD format has been revised, and 
certain paragraphs have been rearranged. As a result, the corresponding 
paragraph identifiers have changed in this proposed AD, as listed in 
the following table:

                      Revised Paragraph Identifiers
------------------------------------------------------------------------
                                            Corresponding requirement in
        Requirement in AD 98-20-01                this proposed AD
------------------------------------------------------------------------
Paragraph (a).............................  Paragraph (f).
Paragraph (b).............................  Paragraph (g).
------------------------------------------------------------------------

    In addition, Note 2 from the existing AD has been changed to Note 
1. The information from Note 1 in AD 98-20-01 has been incorporated 
into paragraph (l) of this proposed AD.

Explanation of Change to Applicability

    We have revised the applicability to reflect the model designations 
as published in the most recent type certificate data sheets.

Costs of Compliance

    The following table provides the estimated costs for U.S. operators 
to comply with this proposed AD. For all actions the average labor rate 
is $65 and

[[Page 55317]]

the number of U.S.-registered airplanes is 651.

                                                 Estimated Costs
----------------------------------------------------------------------------------------------------------------
                                                                                           Cost per      Fleet
                  Action                   Work hours                Parts                  airlane      cost
----------------------------------------------------------------------------------------------------------------
Revise the AFM (required by AD 98-20-01).           1  N/A..............................         $65     $42,315
Revise the maintenance (required by AD 98-          1  N/A..............................          65      42,315
 20-01).
Install ADC (new proposed action)........           1  No Charge........................          65      42,315
Install 3 and 4 flap             18  No Charge........................       1,170     761,670
 actuators (new proposed action).
Install skew detection system (new                147  No Charge........................       9,555   6,220,305
 proposed action).
Install new airspeed limitation placards            1  No Charge........................          65      42,315
 (new proposed action).
Revise the AFM (new proposed action).....           1  N/A..............................          65      42,315
----------------------------------------------------------------------------------------------------------------

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. See the ADDRESSES section for a location 
to examine the regulatory evaluation.

List of Subjects in 14 CFR Part 39

    Air transportation, Aircraft, Aviation safety, Safety.

The Proposed Amendment

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

PART 39--AIRWORTHINESS DIRECTIVES

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

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


Sec.  39.13  [Amended]

    2. The FAA amends Sec.  39.13 by removing amendment 39-10767 (63 FR 
49661, September 17, 1998) and adding the following new airworthiness 
directive (AD):

Bombardier, Inc. (Formerly Canadair): Docket No. FAA-2005-22481; 
Directorate Identifier 2004-NM-176-AD.

Comments Due Date

    (a) The Federal Aviation Administration must receive comments on 
this AD action by October 21, 2005.

Affected ADs

    (b) This AD supersedes AD 98-20-01.

Applicability

    (c) This AD applies to Bombardier Model CL-600-2B19 (Regional 
Jet Series 100 & 400) airplanes, certificated in any category, 
serial numbers 7003 through 7903 inclusive.

Unsafe Condition

    (d) This AD was prompted by a number of cases of flap system 
failure that resulted in a twisted outboard flap panel. We are 
issuing this AD to prevent an unannunciated failure of the flap 
system, which could result in a flap asymmetry and consequent 
reduced controllability of the airplane.

Compliance

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

Restatement of the Requirements of AD 98-20-01

    Note 1: Bombardier Service Letter RJ-SL-27-002A, dated April 8, 
1998, and Service Letter RJ-SL-27-037, dated July 2, 1998, may 
provide operators with additional information concerning the actions 
required by this AD. However, accomplishment of the procedures 
specified in these service letters should not be considered to be an 
acceptable method of compliance with the requirements of this AD.

    (f) Within 10 days after October 2, 1998 (the effective date of 
AD 98-20-01), accomplish the requirements of paragraphs (f)(1), 
(f)(2), and (f)(3) of this AD.
    (1) Revise the Limitations Section of the FAA-approved airplane 
flight manual (AFM) to include the following procedures and Figures 
1 and 2 of this AD. After accomplishing the actions in paragraphs 
(h) and (i) of this AD, remove the revisions required by this 
paragraph of this AD from the AFM.
    ``Air Operator Actions
    IMPORTANT: If the outboard flap position is outside the `GO' 
range, as shown in figure 2., further flight is prohibited until 
required maintenance actions have been accomplished.
    1. Touch-and-go landings for the purposes of training must be 
accomplished using a flap setting of 20 degrees for the entire 
procedure.
    2. (a) Take-off flaps must be set prior to departure, and
    (b) An external visual check must be accomplished to detect any 
twisting, skewing, or abnormal deformation of the flaps, using the 
information given in Figures 1 and 2.

    Note 1: If the outboard flap position is outside the `GO' range 
as shown in figure 2., further flight is prohibited until required 
maintenance actions have been accomplished.


    Note 2: This visual check must be accomplished either by a 
member of the flight crew or by maintenance personnel, and the 
results reported directly to the pilot-in-command prior to take-off.

    3. If any additional change to the flap position is necessary, 
prior to take-off, accomplish the visual check specified by the 
preceding paragraph 2. (b).''
    (2) Revise the Normal Procedures Section of the FAA-approved AFM 
to include the following procedures:

[[Page 55318]]

    ``To minimize a possible flap twist in flight when operating 
flaps, operate the flap selector sequentially, stopping at each 
setting (i.e., 0 degrees, 8 degrees if applicable, 20 degrees, 30 
degrees, 45 degrees; or operate the flap selector in reverse order), 
and waiting for the flaps to reach each position before selecting 
the next setting. Monitor the control wheel for abnormal control 
wheel angles during each transition in flap position.

    Note: This procedure is not applicable during a go-around or 
during any emergency aircraft handling procedure where prompt flap 
retraction is required. In these cases, follow the applicable AFM 
procedures.''

    (3) Revise the Abnormal Procedures Section of the FAA-approved 
AFM to include the following procedures.
    ``If abnormal aileron control wheel angles develop during flap 
operation with the autopilot on, or if the aircraft rolls without 
pilot input with the autopilot off (with or without a `FLAPS FAIL' 
caution message), perform the following actions:
    1. If flaps are being extended, immediately return the flaps to 
the previously selected position (e.g., for flaps selected from 8 
degrees to 20 degrees, re-select 8 degrees).
    2. If flaps are being retracted, the flap selector should remain 
in the currently selected position (e.g., for flaps selected from 20 
degrees to 8 degrees, leave selector at 8 degrees).
    3. Do not attempt to operate the flaps any further.
    4. If the flaps are engaged, disconnect the autopilot.

    Note: When disconnecting the autopilot, anticipate an out-of-
trim situation and hold the aileron control wheel in its current 
position.

    5. For landing, perform the `Flaps Failure' procedure for the 
following conditions:
    (a) If an abnormal aileron control wheel angle to the left 
develops, do not land if a crosswind from the left is greater than 
20 knots.
    (b) If an abnormal aileron control wheel angle to the right 
develops, do not land if a crosswind from the right is greater than 
20 knots.
    6. After landing, do not attempt to retract the flaps. Record 
the event in the Aircraft Maintenance Log Book and notify the person 
responsible for maintenance.''

BILLING CODE 4910-13-P
[GRAPHIC] [TIFF OMITTED] TP21SE05.020


[[Page 55319]]


[GRAPHIC] [TIFF OMITTED] TP21SE05.021

BILLING CODE 4910-13--C

[[Page 55320]]

    (g) Within 10 days after October 2, 1998, revise the FAA-
approved maintenance program to include the following procedures and 
Figures 1 and 2 of this AD:

``Maintenance Procedure

    Whenever a `FLAPS FAIL' caution message occurs, carry out the 
following procedures after landing:

    Note: These procedures are to be accomplished by maintenance 
personnel only.

    1. Check that there have been no other `FLAPS FAIL' caution 
messages reported within the previous 72 hours. If a previous 
message has been reported, prior to further flight, perform the 
actions required in the following Maintenance Action section. If no 
previous `FLAPS FAIL' caution message has been reported, continue 
with the following:
    2. Carry out an external visual check of each outboard flap for 
evidence of twisting, skewing, or abnormal deformation. (Reference 
Figures 1 and 2.)
    3. If there is no evidence of twisting, skewing, or abnormal 
deformation, proceed as follows:
    (a) Reset the flap system ONLY ONCE by cycling circuit breakers 
CB1-F4 and CB2-F4.
    (b) If the system does not reset (i.e., the `FLAPS FAIL' caution 
message is still posted), prior to further flight, perform the 
actions required in the following Maintenance Action section.
    (c) If the system resets, cycle the flaps to 45 degrees and back 
to 0 degrees. Continued flap operation for up to a maximum of 72 
hours is then permitted as long as no additional `FLAPS FAIL' 
caution message is indicated.
    (d) If an additional `FLAPS FAIL' caution message occurs within 
the period of 72 hours, as specified above, prior to further flight, 
perform the actions required in the following Maintenance Action 
section.
    (e) Within 72 hours, even if no further `FLAPS FAIL' messages 
have been indicated, perform the actions required in the following 
Maintenance Action section.
    4. If there is evidence of twisting, skewing, or abnormal 
deformation, PRIOR TO FURTHER FLIGHT, perform the actions required 
in the following Maintenance Action section.

Maintenance Action

    Whenever the outboard flap position indicator is outside the 
`GO' range as shown in Figure 2, or whenever directed to do so by 
the Maintenance Procedure above, perform the following procedures:
    A. Interrogate the flap electronic control unit (FECU) per Fault 
Isolation Manual, Section 27-50-00, `Flaps Fault Isolation,' and 
rectify as applicable.
    B. Visually check each flap for evidence of twisting, skewing, 
or abnormal deformation.
    1. If there is no evidence of twisting, skewing, or abnormal 
deformation, manually isolate any jammed, disconnected, or dragging 
component; and rectify all discrepant conditions.
    2. If there is evidence of twisting, skewing, or abnormal 
deformation, replace both actuators and any discrepant flap panel 
with new or serviceable components. In addition, inspect flexible 
shaft(s) inboard of the most outboard actuator removed for 
discrepancies, and replace any discrepant flexible shaft with a new 
or serviceable flexible shaft.

    Note: An acceptable procedure for testing the flap drive 
breakaway input torque is detailed in Aircraft Maintenance Manual 
Temporary Revision 27-203, Task 27-53-00-750-802, dated July 17, 
1998.

    C. Within 3 days after identifying a flap panel twist or logging 
a `FLAPS FAIL' caution message, notify Bombardier Aerospace, via the 
Canadair Regional Jet Action Center, of all findings and actions 
taken.''

New Requirements of the AD

Install New Flap Actuators

    (h) Within 12 months after the effective date of this AD: 
Install new Number 3 and Number 4 flap actuators in accordance with 
the Accomplishment Instructions of Bombardier Service Bulletin 601R-
27-114, Revision B, dated December 4, 2003. The actions in paragraph 
(h) of this AD must be accomplished prior to or concurrently with 
the actions in paragraph (i) of this AD.

Install Skew Detection System (SDS) and Air Data Computer

    (i) Within 30 months after the effective date of this AD, but 
after the actions required by paragraph (h) of this AD have been 
accomplished: install the SDS in accordance with paragraphs (i)(1), 
(i)(2), (i)(3), (i)(4), and (i)(5) of this AD. These actions must be 
accomplished in the order stated in this paragraph. Accomplishing 
the actions in paragraphs (h) and (i) of this AD terminates the 
requirements of paragraphs (f) and (g) of this AD, and the AFM 
revisions required by those paragraphs may be removed from the AFM.
    (1) Install the electrical provisions for the SDS in accordance 
with the Accomplishment Instructions of Bombardier Service Bulletin 
601R-27-115, Revision D, dated March 18, 2004.
    (2) Install and activate the SDS in accordance with the 
Accomplishment Instructions of Bombardier Service Bulletin 601R-27-
116, Revision B, dated February 2, 2004; and install a new or 
retrofitted air data computer (ADC) in accordance with the 
Accomplishment Instructions of Bombardier Service Bulletin 601R-34-
128, Revision B, dated September 7, 2001.
    (3) Install new airspeed limitation placards in accordance with 
the Accomplishment Instructions of Bombardier Service Bulletin 601R-
11-080, dated November 28, 2003.
    (4) Revise the Limitations section of the AFM to include the 
information specified in Canadair Temporary Revision (TR) RJ/128, 
dated November 28, 2003, to Canadair Regional Jet AFM, CSP A-102, to 
include revised VFE values, and a new SDS and crosswind-
related limitation for take-off flap selection.

    Note 2: The action in paragraph (i)(4) of this AD may be 
accomplished by inserting a copy of Canadair TR RJ/128 in the AFM. 
When this temporary revision has been incorporated into the general 
revisions of the AFM, the general revisions may be inserted in the 
AFM, provided the information contained in the general revision is 
identical to that specified in Canadair Temporary Revision RJ/128.

    (5) For airplanes on which decals stating ``Visually inspect 
flaps prior to departure'' have been installed in production or in 
accordance with an alternative method of compliance (AMOC) granted 
by the FAA: After the installation required by paragraph (h)(1), 
(i)(1), (i)(2), (i)(3), and (i)(4) of this AD, remove the decals in 
accordance with Part A of Bombardier Service Bulletin 601R-27-111, 
dated March 6, 2000.

    Note 3: This AD requires revisions to certain operator 
maintenance documents to include new inspections. Compliance with 
these inspections is required by 14 CFR 91.403(c). For airplanes 
that have been previously modified, altered, or repaired in the 
areas addressed by these inspections, the operator may not be able 
to accomplish the inspections described in the revisions. In this 
situation, to comply with 14 CFR 91.403(c), the operator must 
request approval for an AMOC according to paragraph (1) of this AD. 
The request should include a description of changes to the required 
inspections that will ensure the continued damage tolerance of the 
affected structure. The FAA has provided guidance for this 
determination in Advisory Circular (AC) 25-1529.

Actions Accomplished in Accordance With Previous Revisions of 
Service Bulletins

    (j) Actions accomplished before the effective date of this AD 
according to the service bulletins identified in paragraphs (j)(1) 
and (j)(2) of this AD, are considered acceptable for compliance with 
the corresponding action specified in paragraphs (h) and (i) of this 
AD.
    (1) For the action in paragraph (h) of this AD: Bombardier 
Service Bulletin 601R-27-114, dated March 22, 2002; or Revision A, 
dated November 6, 2002.
    (2) For the actions in paragraph (i) of this AD: Bombardier 
Service Bulletin 601R-27-116, dated July 23, 2003; or Revision A, 
dated September 10, 2003.

Parts Installation

    (k)(1) As of 12 months after the effective date of this AD, no 
person may install on any airplane a flap actuator with part numbers 
(P/Ns) 601R93103-5, -6, -7, -8, -9, -10, -11, -12, -17, and -18 
(Vendor P/Ns 853D100 -7, -8, -9, -10, -11, -12, -13, -14, -17 and -
18).
    (2) As of 12 months after the effective date of this AD, no 
person may install on any airplane a flap actuator with P/Ns 
601R93104-5, -6, -7, -8, -9 and -10 (Vendor P/Ns 854D100-7, -8, -9, 
-10, -11 and -12).
    (3) As of 30 months after the effective date of this AD, no 
person may install on any airplane an ADC with P/Ns 822-0372-140 and 
-143.

AMOCs

    (l)(1) The Manager, New York ACO, FAA, has the authority to 
approve AMOCs for this AD, if requested in accordance with the 
procedures found in 14 CFR 39.19.
    (2) AMOCs approved previously according to AD 98-20-01, are 
approved as AMOCs for the corresponding provisions of this AD.

[[Page 55321]]

Related Information

    (m) Canadian airworthiness directive CF-1998-14R4, dated June 1, 
2004, also addresses the subject of this AD.

    Issued in Renton, Washington, on September 8, 2005.
Kalene C. Yanamura,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.

[FR Doc. 05-18794 Filed 9-20-05; 8:45 am]
BILLING CODE 4910-13-P
This site is protected by reCAPTCHA and the Google Privacy Policy and Terms of Service apply.