Airworthiness Directives; Bombardier Model CL-600-1A11 (CL-600), CL-600-2A12 (CL-601), and CL-600-2B16 (CL-601-3A, CL-601-3R, and CL-604) Airplanes Modified by Supplemental Type Certificate (STC) SA4900SW, 30621-30624 [05-10536]

Download as PDF Federal Register / Vol. 70, No. 102 / Friday, May 27, 2005 / Rules and Regulations this AD is installed, and that meets the criteria (close ream fasteners, external doubler, rub strip or wear plate installed) in flag note 1 of Figure 9 of Boeing Alert Service Bulletin 767–53A0078, Revision 4, dated September 26, 2002: After the initial inspection in paragraph (n) of this AD, repeat the open-hole HFEC inspection in Step 7 of Figure 10 of the service bulletin, at intervals not to exceed 12,000 flight cycles, or 72 months, whichever occurs first. The openhole HFEC inspections are required in addition to the surface inspections (HFEC, LFEC, and detailed visual inspections) required by paragraph (n) of this AD. Alternative Methods of Compliance (p)(1) In accordance with 14 CFR 39.19, the Manager, Seattle ACO, is authorized to approve alternative methods of compliance (AMOCs) for the corresponding provisions of this AD. (2) AMOCs approved previously per AD 2001–09–13, amendment 39–12220, are approved as AMOCs with the corresponding provisions of this AD. (3) An AMOC that provides an acceptable level of safety may be used for any repair required by this AD, if it is approved by an Authorized Representative for the Boeing Delegation Option Authorization Organization who has been authorized by the Manager, Seattle ACO, to make such findings. Material Incorporated by Reference (q) Unless otherwise specified in this AD, the actions must be done in accordance with Boeing Service Bulletin 767–53–0078, Revision 2, dated April 19, 2001; Boeing Alert Service Bulletin 767–53A0078, Revision 3, dated November 15, 2001; and Boeing Alert Service Bulletin 767–53A0078, Revision 4, dated September 26, 2002; as applicable. (1) The incorporation by reference of Boeing Alert Service Bulletin 767–53A0078, Revision 3, dated November 15, 2001; and Boeing Alert Service Bulletin 767–53A0078, Revision 4, dated September 26, 2002; is approved by the Director of the Federal Register, in accordance with 5 U.S.C. 552(a) and 1 CFR part 51. (2) The incorporation by reference of Boeing Service Bulletin 767–53–0078, Revision 2, dated April 19, 2001, was approved previously by the Director of the Federal Register as of May 24, 2001 (66 FR 23538, May 9, 2001). (3) To get copies of the service information, contact Boeing Commercial Airplanes, P.O. Box 3707, Seattle, Washington 98124–2207. You may view the AD docket at the Docket Management Facility, U.S. Department of Transportation, 400 Seventh Street SW., room PL–401, Nassif Building, Washington, DC. To review copies of the service information, go to the National Archives and Records Administration (NARA). For information on the availability of this material at NARA, call (202) 741–6030, or go to https://www.archives.gov/federal_register/ code_of_federal_regulations/ ibr_locations.html. VerDate jul<14>2003 19:56 May 26, 2005 Jkt 205001 Issued in Renton, Washington, on May 16, 2005. Michael J. Kaszycki, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 05–10433 Filed 5–26–05; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2005–21315; Directorate Identifier 2005–NM–090–AD; Amendment 39–14106; AD 2005–11–04] RIN 2120–AA64 Airworthiness Directives; Bombardier Model CL–600–1A11 (CL–600), CL– 600–2A12 (CL–601), and CL–600–2B16 (CL–601–3A, CL–601–3R, and CL–604) Airplanes Modified by Supplemental Type Certificate (STC) SA4900SW Federal Aviation Administration (FAA), Department of Transportation (DOT). ACTION: Final rule; request for comments. AGENCY: SUMMARY: The FAA is adopting a new airworthiness directive (AD) for certain Bombardier Model CL–600–1A11 (CL– 600), CL–600–2A12 (CL–601), and CL– 600–2B16 (CL–601–3A, CL–601–3R, and CL–604) airplanes modified by STC SA4900SW. This AD requires revising the airplane flight manual (AFM) to require repetitive visual checks of the microphone jack assemblies on both control columns to detect damage that may interfere with movement of the control column. This AD also requires modification of the microphone jack assembly, related investigative actions, and corrective actions if necessary, which allows the AFM revision to be removed from the AFM. This AD is prompted by a report of a rejected takeoff and subsequent runway overrun due to restricted movement of the co-pilot’s control column, which resulted in collapse of the nose landing gear and consequent damage of the forward fuselage. We are issuing this AD to prevent a damaged microphone jack assembly from interfering with movement of the control column, which could result in loss of control of the airplane. DATES: Effective May 27, 2005. The incorporation by reference of a certain publication listed in the AD is approved by the Director of the Federal Register as of May 27, 2005. We must receive comments on this AD by July 26, 2005. PO 00000 Frm 00017 Fmt 4700 Sfmt 4700 30621 Use one of the following addresses to submit comments on this AD. • DOT Docket Web site: Go to http:/ /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 AD, contact Raytheon Aircraft Company, P.O. Box 3356, Little Rock, Arkansas 72203; or 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– 21315; the directorate identifier for this docket is 2005–NM–090–AD. ADDRESSES: 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. John Hardie, Aerospace Engineer, Special Certification Office, ASW–190, 2601 Meacham Blvd., Fort Worth, Texas 76137–4298; telephone (817) 222–5194; fax (817) 222–5785. SUPPLEMENTARY INFORMATION: We have received a report indicating that a Bombardier Model CL–600–1A11 (CL– 600) airplane experienced a rejected take-off and subsequently overran the runway. The nose landing gear collapsed, and the forward fuselage was damaged as a result of the incident. The FOR FURTHER INFORMATION CONTACT: E:\FR\FM\27MYR1.SGM 27MYR1 30622 Federal Register / Vol. 70, No. 102 / Friday, May 27, 2005 / Rules and Regulations flightcrew reported that, when they attempted to take off, the control column would not move aft beyond the neutral position. Investigation revealed that the microphone jack assembly installed on the co-pilot’s control column was bent downward, which restricted the aft movement of the control column. This condition, if not corrected, could result in loss of control of the airplane. The microphone jack assembly on the affected airplane was installed incidental to Supplemental Type Certificate (STC) SA4900SW. Therefore, we find that all Bombardier Model CL– 600–1A11 (CL–600), CL–600–2A12 (CL– 601), and CL–600–2B16 (CL–601–3A, CL–601–3R, and CL–604) airplanes modified by that STC may be subject to the same unsafe condition. Relevant Service Information Raytheon has issued Service Bulletin SB 23–3727, dated May 2005. The service bulletin describes procedures for modifying the microphone jack assembly, and performing related investigative actions and corrective actions if necessary. The related investigative actions include performing a general visual inspection of the cover of the pilot’s and co-pilot’s control columns for cracking around the existing fastener holes for the microphone bracket assembly; a NonDestructive Test (NDT) of the microphone jack assembly for any damage, including cracks; and a measurement of the distance between existing fastener holes and the location of the new fastener holes. (The service bulletin specifies various alternatives for performing the NDT including dyepenetrant, ultrasonic, and eddy current methods.) The service bulletin specifies to contact Raytheon if any cracking or damage is found, or if the minimum distance between existing and new fastener holes is below a certain limit. Accomplishing the actions specified in the service information is intended to adequately address the unsafe condition. Bombardier Advisory Wire AW600– 00–2247, Revision 2, dated March 24, 2005, also addresses the subject of this AD. Section 3.0, Action, of the Advisory Wire recommends a repetitive inspection to ‘‘verify the security of the installation of the [microphone jack] receptacle.’’ The intent of this inspection is identical to that of the repetitive visual checks specified in the airplane flight manual (AFM) revision required by paragraph (f) of this AD. VerDate jul<14>2003 19:56 May 26, 2005 Jkt 205001 FAA’s Determination and Requirements of This AD These airplane models are manufactured in Canada and are type certificated for operation in the United States under the provisions of § 21.29 of the Federal Aviation Regulations (14 CFR 21.29) and the applicable bilateral airworthiness agreement. We have evaluated all pertinent information, and determined that we need to issue an AD for products of this type design that are modified by STC SA4900SW and certificated for operation in the United States. Therefore, we are issuing this AD to prevent a damaged microphone jack assembly from interfering with movement of the control column, which could result in loss of control of the airplane. This AD requires revising the AFM to require repetitive visual checks of the microphone jack assemblies on both control columns to detect damage that may interfere with movement of the control column. We have determined that the checks specified in the AFM revision must be performed by the flightcrew because of the possibility that damage to the microphone jack assembly may occur between the time an inspection is performed by maintenance personnel and the time the flightcrew enters the flight deck to prepare for the flight. (For example, a member of the flightcrew may inadvertently step on the microphone jack assembly, causing it to bend.) We have determined that it is possible for the flightcrew to perform the visual checks because the checks do not require tools, precision measuring equipment, training, or pilot logbook endorsements, or the use of or reference to technical data that are not contained in the body of the AD. This AD also requires accomplishing the actions specified in the service information described previously, except as discussed under ‘‘Differences Between the AD and Service Information,’’ after which the AFM revision may be removed from the AFM. Differences Between the AD and Service Information Although the Raytheon service bulletin specifies that operators may contact the manufacturer for disposition of certain repair conditions, this proposed AD would require operators to repair those conditions according to a method approved by the FAA. The Raytheon service bulletin recommends that the modification of the microphone jack assembly be accomplished before the next flight or within 15 days from receipt of the PO 00000 Frm 00018 Fmt 4700 Sfmt 4700 service bulletin, whichever is first. This AD specifies a compliance time for the modification of 15 flight hours or 15 days after the effective date of the AD, whichever is first. In developing an appropriate compliance time for this AD, we considered the manufacturer’s recommendation, the degree of urgency associated with the subject unsafe condition, and the average utilization of the affected fleet. We also considered the recommendation for repetitive inspections in Bombardier Advisory Wire AW600–00–2247, Revision 2. (These repetitive inspections are similar to the repetitive visual checks specified in the AFM revision required by this AD.) In light of all of these factors, we find that, for the modification, a compliance time of 15 flight hours or 15 days, whichever is earlier, represents an appropriate interval of time for affected airplanes to continue to operate without compromising safety, provided that the microphone jack assembly is checked for damage before every flight. We find that this compliance time should provide an opportunity for affected operators to accomplish the modification without unnecessarily grounding airplanes. This difference has been coordinated with Raytheon. Although the Accomplishment Instructions of the referenced service bulletin describe procedures for reporting accomplishment of the service bulletin, this AD does not require that action. We do not need this information from operators. Clarification of Service Bulletin Note The Raytheon service bulletin includes a note in the Accomplishment Instructions to inform operators to contact Raytheon ‘‘should any difficulty be encountered’’ in accomplishing the service bulletin. We have included Note 3 in this proposed AD to clarify that any deviation from the instructions provided in the service bulletin must be approved as an alternative method of compliance under paragraph (i) of this proposed AD. FAA’s Determination of the Effective Date An unsafe condition exists that requires the immediate adoption of this AD; therefore, providing notice and opportunity for public comment before the AD is issued is impracticable, and good cause exists to make this AD effective in less than 30 days. Comments Invited This AD is a final rule that involves requirements that affect flight safety and was not preceded by notice and an opportunity for public comment; E:\FR\FM\27MYR1.SGM 27MYR1 Federal Register / Vol. 70, No. 102 / Friday, May 27, 2005 / Rules and Regulations however, we invite you to submit any relevant written data, views, or arguments regarding this AD. Send your comments to an address listed under ADDRESSES. Include ‘‘Docket No. FAA– 2005–21315; Directorate Identifier 2005NM–090-AD’’ at the beginning of your comments. We specifically invite comments on the overall regulatory, economic, environmental, and energy aspects of the AD. We will consider all comments received by the closing date and may amend the 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 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. 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 AD will not have federalism implications under Executive Order 13132. This AD will 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 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 AD. See the ADDRESSES section for a location to examine the regulatory evaluation. 30623 List of Subjects in 14 CFR Part 39 Air transportation, Aircraft, Aviation safety, Incorporation by reference, Safety. Adoption of the Amendment Accordingly, under the authority delegated to me by the Administrator, the FAA amends 14 CFR part 39 as follows: I PART 39—AIRWORTHINESS DIRECTIVES 1. The authority citation for part 39 continues to read as follows: I Authority: 49 U.S.C. 106(g), 40113, 44701. § 39.13 [Amended] 2. The FAA amends § 39.13 by adding the following new airworthiness directive (AD): I 2005–11–04 Bombardier, Inc. (Formerly Canadair): Amendment 39–14106. Docket No. FAA–2005–21315; Directorate Identifier 2005-NM–090-AD. Effective Date (a) This AD becomes effective May 27, 2005. Affected ADs (b) None. Applicability (c) This AD applies to Bombardier Model CL–600–1A11 (CL–600), CL–600–2A12 (CL– 601), and CL–600–2B16 (CL–601–3A, CL– 601–3R, and CL–604) airplanes; certificated in any category; modified by STC SA4900SW; excluding serial number (S/N) 3025; and including but not limited to the serial numbers listed in Table 1 of this AD. TABLE 1.—KNOWN AFFECTED S/NS Model Known S/Ns CL–600–1A11 (CL–600) ........................................................................... CL–600–2A12 (CL–601) ........................................................................... CL–600–2B16 (CL–601–3A, CL–601–3R, and CL–604) ......................... 1054, 1059, 1069, 1071, 1080 3012, 3013, 3034, 3045, 3050, 3051, 3061, 3065 5012, 5046, 5060 Unsafe Condition Airplane Flight Manual (AFM) Revision (d) This AD was prompted by a report of a rejected take-off and subsequent runway overrun due to restricted movement of the control column, which resulted in collapse of the nose landing gear and consequent damage of the forward fuselage. The FAA is issuing this AD to prevent a damaged microphone jack assembly from interfering with movement of the control column, which could result in loss of control of the airplane. (f) Within 5 days after the effective date of this AD, revise the Limitations and Normal Procedures section of the AFM to contain the following information. This may be done by inserting a copy of this AD in the AFM. ‘‘Before every flight, perform a visual check of the microphone jack assembly on the pilot’s and co-pilot’s control column to detect damage that may interfere with movement of the control column, including downward bending of the receptacle. This check must be performed by the flightcrew. Any damage that may interfere with the movement of the control column must be repaired before further flight.’’ 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. VerDate jul<14>2003 19:56 May 26, 2005 Jkt 205001 PO 00000 Frm 00019 Fmt 4700 Sfmt 4700 Note 1: Bombardier Advisory Wire AW600–00–2247, Revision 2, dated March 24, 2005, provides additional information on damaged microphone jack assemblies and interference of damaged assemblies with movement of the control column. Modification (g) At the applicable compliance time specified in paragraph (g)(1) or (g)(2) of this AD, modify the microphone jack assembly and do all related investigative actions and applicable corrective actions, in accordance with the Accomplishment Instructions of Raytheon Service Bulletin SB 23–3727, dated May 2005, except as provided by paragraph (h) of this AD. Once this modification is complete, the AFM revision required by E:\FR\FM\27MYR1.SGM 27MYR1 30624 Federal Register / Vol. 70, No. 102 / Friday, May 27, 2005 / Rules and Regulations paragraph (f) of this AD may be removed from the AFM. Although the service bulletin specifies reporting accomplishment of the service bulletin to the manufacturer, this AD does not require that action. (1) If damage that may interfere with the movement of the control column is found during any visual check performed in accordance with the AFM revision required by paragraph (f) of this AD: Before further flight. (2) If no damage that may interfere with the movement of the control column is found during any visual check performed in accordance with the AFM revision required by paragraph (f) of this AD: Within 15 days or 15 flight hours after the effective date of this AD, whichever is first. Repairs (h) If any cracking is found during any inspection required by this AD, or if the distance between existing and new fastener holes is less than the limit specified in Raytheon Service Bulletin SB 23–3727, dated May 2005, and the service bulletin specifies contacting Raytheon for appropriate action: Before further flight, repair the cracking or do other applicable corrective actions according to a method approved by the Manager, Special Certification Office, ASW–190, FAA. For a repair or corrective action method to be approved by the Manager, Special Certification Office, as required by this paragraph, the Manager’s approval letter must specifically refer to this AD. Note 2: A note in the Accomplishment Instructions of the Raytheon service bulletin instructs operators to contact Raytheon if any difficulty is encountered in accomplishing the service bulletin. However, any deviation from the instructions provided in the service bulletin must be approved as an alternative method of compliance (AMOC) under paragraph (i) of this AD. AMOCs (i) The Manager, Special Certification Office, ASW–190, has the authority to approve AMOCs for this AD, if requested in accordance with the procedures found in 14 CFR 39.19. Related Information (j) Bombardier Advisory Wire AW600–00– 2247, Revision 2, dated March 24, 2005, addresses the subject of this AD. Material Incorporated by Reference (k) You must use Raytheon Service Bulletin SB 23–3727, dated May 2005, to perform the actions that are required by this AD, unless the AD specifies otherwise. The Director of the Federal Register approves the incorporation by reference of this document in accordance with 5 U.S.C. 552(a) and 1 CFR part 51. To get copies of the service information, contact Raytheon Aircraft Company, P.O. Box 3356, Little Rock, Arkansas 72203; or Bombardier, Inc., Canadair, Aerospace Group, P.O. Box 6087, Station Centre-ville, Montreal, Quebec H3C 3G9, Canada. To view the AD docket, go to the Docket Management Facility, U.S. Department of Transportation, 400 Seventh Street SW, room PL–401, Nassif Building, VerDate jul<14>2003 19:56 May 26, 2005 Jkt 205001 Washington, DC. To review copies of the service information, go to the National Archives and Records Administration (NARA). For information on the availability of this material at the NARA, call (202) 741– 6030, or go to https://www.archives.gov/ federal_register/code_of_federal_regulations/ ibr_locations.html. Issued in Renton, Washington, on May 20, 2005. Michael J. Kaszycki, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 05–10536 Filed 5–26–05; 8:45 am] Issued in Washington, DC, on May 20, 2005. Rebecca B. MacPherson, Assistant Chief Counsel, Regulations Division. [FR Doc. 05–10596 Filed 5–26–05; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 71 BILLING CODE 4910–13–P [Docket No. FAA–2005–20574; Airspace Docket No. 05–ACE–11] DEPARTMENT OF TRANSPORTATION Federal Aviation Administration Establishment of Class E2 Airspace; and Modification of Class E5 Airspace; Chillicothe, MO 14 CFR Part 65 AGENCY: [Docket No. FAA–2001–11133; Amdt. 65–45] RIN 2120–AH19 Certification of Aircraft and Airmen for the Operation of Light-Sport Aircraft; Correction Federal Aviation Administration (FAA), DOT. AGENCY: ACTION: Final rule; correction. SUMMARY: This document corrects information regarding the training course design for the repairman certificate (light-sport aircraft) discussed in the preamble of the final rule, ‘‘Certification of Aircraft and Airmen for the Operation of Light-Sport Aircraft,’’ published in the Federal Register of July 27, 2004. The regulatory text addressing this matter was correct and no correction to that text is required. The final rule published at 69 FR 44772 (July 27, 2004) was effective September 1, 2004. DATES: FOR FURTHER INFORMATION CONTACT: Michael W. Brown, Certification and General Aviation Operations Branch Manager (AFS–810), 202–267–8212. Correction In final rule FR Doc. 04–16577, beginning on page 44772 in the Federal Register of July 27, 2004, make the following correction to the preamble discussion of § 65.107 Repairman certificate (light-sport aircraft): Eligibility, privileges and limits: Federal Aviation Administration (FAA), DOT. ACTION: Final rule. SUMMARY: This rule establishes a Class E surface area at Chillicothe, MO. It also modifies the Class E airspace area extending upward from 700 feet above the surface at Chillicothe, MO. The effect of this rule is to provide appropriate controlled Class E airspace for aircraft department from and executing instrument approach procedures to Chillicothe Municipal Airport and to segregate aircraft using instrument approach procedures in instrument conditions from aircraft operating in visual conditions. DATES: Effective 0901 UTC, July 7, 2005. FOR FURTHER INFORMATION CONTACT: Brenda Mumper, Air Traffic Division, Airspace Branch, ACE–520A, DOT Regional Headquarters Building, Federal Aviation Administration, 901 Locust, Kansas City, MO 64106; telephone: (816) 329–2524. SUPPLEMENTARY INFORMATION: History On Tuesday, April 12, 2005, the FAA proposed to amend 14 CFR part 71 to establish a Class E surface area and to modify other Class E airspace at Chillicothe, MO (70 FR 19027). The proposal was to establish a Class E surface area at Chillicothe, MO. It was also to modify the Class E5 airspace area to bring it into compliance with FAA directives. Interested parties were invited to participate in this rulemaking proceeding by submitting written comments on the proposal to the FAA. No comments objecting to the proposal were received. On page 44849, in the third column, in the 22nd line, the words ‘‘performs a task The Rule This amendment to Part 71 of the with supervision’’ should have read, Federal Aviation Regulations (14 CFR ‘‘performs a task without supervision.’’ I PO 00000 Frm 00020 Fmt 4700 Sfmt 4700 E:\FR\FM\27MYR1.SGM 27MYR1

Agencies

[Federal Register Volume 70, Number 102 (Friday, May 27, 2005)]
[Rules and Regulations]
[Pages 30621-30624]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 05-10536]


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

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2005-21315; Directorate Identifier 2005-NM-090-AD; 
Amendment 39-14106; AD 2005-11-04]
RIN 2120-AA64


Airworthiness Directives; Bombardier Model CL-600-1A11 (CL-600), 
CL-600-2A12 (CL-601), and CL-600-2B16 (CL-601-3A, CL-601-3R, and CL-
604) Airplanes Modified by Supplemental Type Certificate (STC) SA4900SW

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

ACTION: Final rule; request for comments.

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

SUMMARY: The FAA is adopting a new airworthiness directive (AD) for 
certain Bombardier Model CL-600-1A11 (CL-600), CL-600-2A12 (CL-601), 
and CL-600-2B16 (CL-601-3A, CL-601-3R, and CL-604) airplanes modified 
by STC SA4900SW. This AD requires revising the airplane flight manual 
(AFM) to require repetitive visual checks of the microphone jack 
assemblies on both control columns to detect damage that may interfere 
with movement of the control column. This AD also requires modification 
of the microphone jack assembly, related investigative actions, and 
corrective actions if necessary, which allows the AFM revision to be 
removed from the AFM. This AD is prompted by a report of a rejected 
take-off and subsequent runway overrun due to restricted movement of 
the co-pilot's control column, which resulted in collapse of the nose 
landing gear and consequent damage of the forward fuselage. We are 
issuing this AD to prevent a damaged microphone jack assembly from 
interfering with movement of the control column, which could result in 
loss of control of the airplane.

DATES: Effective May 27, 2005.
    The incorporation by reference of a certain publication listed in 
the AD is approved by the Director of the Federal Register as of May 
27, 2005.
    We must receive comments on this AD by July 26, 2005.

ADDRESSES: Use one of the following addresses to submit comments on 
this 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 AD, contact Raytheon 
Aircraft Company, P.O. Box 3356, Little Rock, Arkansas 72203; or 
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-2005-21315; the directorate identifier for this docket is 
2005-NM-090-AD.

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.

FOR FURTHER INFORMATION CONTACT: John Hardie, Aerospace Engineer, 
Special Certification Office, ASW-190, 2601 Meacham Blvd., Fort Worth, 
Texas 76137-4298; telephone (817) 222-5194; fax (817) 222-5785.

SUPPLEMENTARY INFORMATION: We have received a report indicating that a 
Bombardier Model CL-600-1A11 (CL-600) airplane experienced a rejected 
take-off and subsequently overran the runway. The nose landing gear 
collapsed, and the forward fuselage was damaged as a result of the 
incident. The

[[Page 30622]]

flightcrew reported that, when they attempted to take off, the control 
column would not move aft beyond the neutral position. Investigation 
revealed that the microphone jack assembly installed on the co-pilot's 
control column was bent downward, which restricted the aft movement of 
the control column. This condition, if not corrected, could result in 
loss of control of the airplane.
    The microphone jack assembly on the affected airplane was installed 
incidental to Supplemental Type Certificate (STC) SA4900SW. Therefore, 
we find that all Bombardier Model CL-600-1A11 (CL-600), CL-600-2A12 
(CL-601), and CL-600-2B16 (CL-601-3A, CL-601-3R, and CL-604) airplanes 
modified by that STC may be subject to the same unsafe condition.

Relevant Service Information

    Raytheon has issued Service Bulletin SB 23-3727, dated May 2005. 
The service bulletin describes procedures for modifying the microphone 
jack assembly, and performing related investigative actions and 
corrective actions if necessary. The related investigative actions 
include performing a general visual inspection of the cover of the 
pilot's and co-pilot's control columns for cracking around the existing 
fastener holes for the microphone bracket assembly; a Non-Destructive 
Test (NDT) of the microphone jack assembly for any damage, including 
cracks; and a measurement of the distance between existing fastener 
holes and the location of the new fastener holes. (The service bulletin 
specifies various alternatives for performing the NDT including dye-
penetrant, ultrasonic, and eddy current methods.) The service bulletin 
specifies to contact Raytheon if any cracking or damage is found, or if 
the minimum distance between existing and new fastener holes is below a 
certain limit. Accomplishing the actions specified in the service 
information is intended to adequately address the unsafe condition.
    Bombardier Advisory Wire AW600-00-2247, Revision 2, dated March 24, 
2005, also addresses the subject of this AD. Section 3.0, Action, of 
the Advisory Wire recommends a repetitive inspection to ``verify the 
security of the installation of the [microphone jack] receptacle.'' The 
intent of this inspection is identical to that of the repetitive visual 
checks specified in the airplane flight manual (AFM) revision required 
by paragraph (f) of this AD.

FAA's Determination and Requirements of This AD

    These airplane models are manufactured in Canada and are type 
certificated for operation in the United States under the provisions of 
Sec.  21.29 of the Federal Aviation Regulations (14 CFR 21.29) and the 
applicable bilateral airworthiness agreement. We have evaluated all 
pertinent information, and determined that we need to issue an AD for 
products of this type design that are modified by STC SA4900SW and 
certificated for operation in the United States.
    Therefore, we are issuing this AD to prevent a damaged microphone 
jack assembly from interfering with movement of the control column, 
which could result in loss of control of the airplane. This AD requires 
revising the AFM to require repetitive visual checks of the microphone 
jack assemblies on both control columns to detect damage that may 
interfere with movement of the control column. We have determined that 
the checks specified in the AFM revision must be performed by the 
flightcrew because of the possibility that damage to the microphone 
jack assembly may occur between the time an inspection is performed by 
maintenance personnel and the time the flightcrew enters the flight 
deck to prepare for the flight. (For example, a member of the 
flightcrew may inadvertently step on the microphone jack assembly, 
causing it to bend.) We have determined that it is possible for the 
flightcrew to perform the visual checks because the checks do not 
require tools, precision measuring equipment, training, or pilot 
logbook endorsements, or the use of or reference to technical data that 
are not contained in the body of the AD.
    This AD also requires accomplishing the actions specified in the 
service information described previously, except as discussed under 
``Differences Between the AD and Service Information,'' after which the 
AFM revision may be removed from the AFM.

Differences Between the AD and Service Information

    Although the Raytheon service bulletin specifies that operators may 
contact the manufacturer for disposition of certain repair conditions, 
this proposed AD would require operators to repair those conditions 
according to a method approved by the FAA.
    The Raytheon service bulletin recommends that the modification of 
the microphone jack assembly be accomplished before the next flight or 
within 15 days from receipt of the service bulletin, whichever is 
first. This AD specifies a compliance time for the modification of 15 
flight hours or 15 days after the effective date of the AD, whichever 
is first. In developing an appropriate compliance time for this AD, we 
considered the manufacturer's recommendation, the degree of urgency 
associated with the subject unsafe condition, and the average 
utilization of the affected fleet. We also considered the 
recommendation for repetitive inspections in Bombardier Advisory Wire 
AW600-00-2247, Revision 2. (These repetitive inspections are similar to 
the repetitive visual checks specified in the AFM revision required by 
this AD.) In light of all of these factors, we find that, for the 
modification, a compliance time of 15 flight hours or 15 days, 
whichever is earlier, represents an appropriate interval of time for 
affected airplanes to continue to operate without compromising safety, 
provided that the microphone jack assembly is checked for damage before 
every flight. We find that this compliance time should provide an 
opportunity for affected operators to accomplish the modification 
without unnecessarily grounding airplanes. This difference has been 
coordinated with Raytheon.
    Although the Accomplishment Instructions of the referenced service 
bulletin describe procedures for reporting accomplishment of the 
service bulletin, this AD does not require that action. We do not need 
this information from operators.

Clarification of Service Bulletin Note

    The Raytheon service bulletin includes a note in the Accomplishment 
Instructions to inform operators to contact Raytheon ``should any 
difficulty be encountered'' in accomplishing the service bulletin. We 
have included Note 3 in this proposed AD to clarify that any deviation 
from the instructions provided in the service bulletin must be approved 
as an alternative method of compliance under paragraph (i) of this 
proposed AD.

FAA's Determination of the Effective Date

    An unsafe condition exists that requires the immediate adoption of 
this AD; therefore, providing notice and opportunity for public comment 
before the AD is issued is impracticable, and good cause exists to make 
this AD effective in less than 30 days.

Comments Invited

    This AD is a final rule that involves requirements that affect 
flight safety and was not preceded by notice and an opportunity for 
public comment;

[[Page 30623]]

however, we invite you to submit any relevant written data, views, or 
arguments regarding this AD. Send your comments to an address listed 
under ADDRESSES. Include ``Docket No. FAA-2005-21315; Directorate 
Identifier 2005-NM-090-AD'' at the beginning of your comments. We 
specifically invite comments on the overall regulatory, economic, 
environmental, and energy aspects of the AD. We will consider all 
comments received by the closing date and may amend the 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 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.

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 AD will not have federalism 
implications under Executive Order 13132. This AD will 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 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 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, Incorporation by 
reference, Safety.

Adoption of the Amendment

0
Accordingly, under the authority delegated to me by the Administrator, 
the FAA amends 14 CFR part 39 as follows:

PART 39--AIRWORTHINESS DIRECTIVES

0
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]

0
2. The FAA amends Sec.  39.13 by adding the following new airworthiness 
directive (AD):

2005-11-04 Bombardier, Inc. (Formerly Canadair): Amendment 39-14106. 
Docket No. FAA-2005-21315; Directorate Identifier 2005-NM-090-AD.

Effective Date

    (a) This AD becomes effective May 27, 2005.

Affected ADs

    (b) None.

Applicability

    (c) This AD applies to Bombardier Model CL-600-1A11 (CL-600), 
CL-600-2A12 (CL-601), and CL-600-2B16 (CL-601-3A, CL-601-3R, and CL-
604) airplanes; certificated in any category; modified by STC 
SA4900SW; excluding serial number (S/N) 3025; and including but not 
limited to the serial numbers listed in Table 1 of this AD.

                      Table 1.--Known Affected S/Ns
------------------------------------------------------------------------
                 Model                              Known S/Ns
------------------------------------------------------------------------
CL-600-1A11 (CL-600)...................  1054, 1059, 1069, 1071, 1080
CL-600-2A12 (CL-601)...................  3012, 3013, 3034, 3045, 3050,
                                          3051, 3061, 3065
CL-600-2B16 (CL-601-3A, CL-601-3R, and   5012, 5046, 5060
 CL-604).
------------------------------------------------------------------------

Unsafe Condition

    (d) This AD was prompted by a report of a rejected take-off and 
subsequent runway overrun due to restricted movement of the control 
column, which resulted in collapse of the nose landing gear and 
consequent damage of the forward fuselage. The FAA is issuing this 
AD to prevent a damaged microphone jack assembly from interfering 
with movement of the control column, which could result in loss of 
control 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.

Airplane Flight Manual (AFM) Revision

    (f) Within 5 days after the effective date of this AD, revise 
the Limitations and Normal Procedures section of the AFM to contain 
the following information. This may be done by inserting a copy of 
this AD in the AFM.

``Before every flight, perform a visual check of the microphone jack 
assembly on the pilot's and co-pilot's control column to detect 
damage that may interfere with movement of the control column, 
including downward bending of the receptacle. This check must be 
performed by the flightcrew. Any damage that may interfere with the 
movement of the control column must be repaired before further 
flight.''


    Note 1: Bombardier Advisory Wire AW600-00-2247, Revision 2, 
dated March 24, 2005, provides additional information on damaged 
microphone jack assemblies and interference of damaged assemblies 
with movement of the control column.

Modification

    (g) At the applicable compliance time specified in paragraph 
(g)(1) or (g)(2) of this AD, modify the microphone jack assembly and 
do all related investigative actions and applicable corrective 
actions, in accordance with the Accomplishment Instructions of 
Raytheon Service Bulletin SB 23-3727, dated May 2005, except as 
provided by paragraph (h) of this AD. Once this modification is 
complete, the AFM revision required by

[[Page 30624]]

paragraph (f) of this AD may be removed from the AFM. Although the 
service bulletin specifies reporting accomplishment of the service 
bulletin to the manufacturer, this AD does not require that action.
    (1) If damage that may interfere with the movement of the 
control column is found during any visual check performed in 
accordance with the AFM revision required by paragraph (f) of this 
AD: Before further flight.
    (2) If no damage that may interfere with the movement of the 
control column is found during any visual check performed in 
accordance with the AFM revision required by paragraph (f) of this 
AD: Within 15 days or 15 flight hours after the effective date of 
this AD, whichever is first.

Repairs

    (h) If any cracking is found during any inspection required by 
this AD, or if the distance between existing and new fastener holes 
is less than the limit specified in Raytheon Service Bulletin SB 23-
3727, dated May 2005, and the service bulletin specifies contacting 
Raytheon for appropriate action: Before further flight, repair the 
cracking or do other applicable corrective actions according to a 
method approved by the Manager, Special Certification Office, ASW-
190, FAA. For a repair or corrective action method to be approved by 
the Manager, Special Certification Office, as required by this 
paragraph, the Manager's approval letter must specifically refer to 
this AD.

    Note 2: A note in the Accomplishment Instructions of the 
Raytheon service bulletin instructs operators to contact Raytheon if 
any difficulty is encountered in accomplishing the service bulletin. 
However, any deviation from the instructions provided in the service 
bulletin must be approved as an alternative method of compliance 
(AMOC) under paragraph (i) of this AD.

AMOCs

    (i) The Manager, Special Certification Office, ASW-190, has the 
authority to approve AMOCs for this AD, if requested in accordance 
with the procedures found in 14 CFR 39.19.

Related Information

    (j) Bombardier Advisory Wire AW600-00-2247, Revision 2, dated 
March 24, 2005, addresses the subject of this AD.

Material Incorporated by Reference

    (k) You must use Raytheon Service Bulletin SB 23-3727, dated May 
2005, to perform the actions that are required by this AD, unless 
the AD specifies otherwise. The Director of the Federal Register 
approves the incorporation by reference of this document in 
accordance with 5 U.S.C. 552(a) and 1 CFR part 51. To get copies of 
the service information, contact Raytheon Aircraft Company, P.O. Box 
3356, Little Rock, Arkansas 72203; or Bombardier, Inc., Canadair, 
Aerospace Group, P.O. Box 6087, Station Centre-ville, Montreal, 
Quebec H3C 3G9, Canada. To view the AD docket, go to the Docket 
Management Facility, U.S. Department of Transportation, 400 Seventh 
Street SW, room PL-401, Nassif Building, Washington, DC. To review 
copies of the service information, go to the National Archives and 
Records Administration (NARA). For information on the availability 
of this material at the NARA, call (202) 741-6030, or go to https://
www.archives.gov/federal_register/code_of_federal_regulations/
ibr_locations.html.

    Issued in Renton, Washington, on May 20, 2005.
Michael J. Kaszycki,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 05-10536 Filed 5-26-05; 8:45 am]
BILLING CODE 4910-13-P
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