FAA Aviation Safety 

## EMERGENCY AIRWORTHINESS DIRECTIVE www.faa.gov/aircraft/safety/alerts/



### DATE: August 19, 2014 AD#: 2014-17-51 Emergency Airworthiness Directive (AD) 2014-17-51 is sent to owners and operators of Bombardier, Inc. Model CL-600-2816 airplanes. 

### Background Transport Canada Civil Aviation (TCCA), which is the aviation authority for Canada, has issued Canadian Emergency Airworthiness Directive CF-2014-27, dated August 15, 2014 (referred to after this as the Mandatory Continuing Airworthiness Information, or "the MCAI"), to correct an unsafe condition on certain Model CL-600-2B 16 airplanes. The MCAI states: There have been three in-service reports on 604 Variant aeroplanes ofa fractured fastener head on the inboard flap hinge-box forward fitting at Wing Station (WS) 76.50, found during a routine maintenance inspection. Investigation revealed that the installation ofthese fasteners on the inboard flap hinge-box forward fittings at WS 76.50 and WS 127.25, on both wings, does not conform to the engineering drawings. Incorrect installation may result in premature failure ofthe fasteners attaching the inboard flap hinge-box forward fitting. Failure ofthe fasteners could lead to the detachment ofthe flap hinge box and consequently the detachment ofthe flap surface. The loss ofa flap surface could adversely affect the continued safe operation ofthe aeroplane.
The original issue ofAD CF-2013-39 [dated December 6, 2013] [which corresponds to FAA AD 2014-03-17, Amendment 39-17754 (79 FR 9389, February 19, 2014)] mandated a detailed visual inspection (DVI) ofeach inboard flap hinge-box forward fitting, on both wings, and rectification as required

. Incorrectly oriented fasteners require repetitive inspections until the terminating action is accomplished.
After the issuance ofAD CF-2013-39, there has been one reported incident on a 604 Variant aeroplane where four fasteners were found fractured on the same flap hinge-box forward fitting. The investigation determined that the fasteners were incorrectly installed. This [Canadian] AD is issued to reduce the initial and repetitive inspection intervals previously mandated in AD CF-2013-39, and to impose replacement ofthe incorrectly oriented fasteners within 24 months. The CL-600-1A11, -2A12 and -2B16 (601-3A/-3R Variant) aeroplanes are addressed through AD CF-2013-39R1 [dated August 15 , 2014]. 

### Relevant Service Information
We reviewed the following service information:

1• Bombardier Alert Service Bulletin A604-57-006, Revision 01 , dated September 26, 2013 , including Appendices 1 and 2, dated September 26, 2013.

• Bombardier Alert Service Bulletin A604-57-006, Revision 02, dated January 22, 2014, including Appendices 1 and 2, dated September 26, 2013.

• Bombardier Alert Service Bulletin A605-57-004, Revision 01 , dated September 26, 2013 , including Appendices 1 and 2, dated September 26, 2013.

• Bombardier Alert Service Bulletin A605-57-004, Revision 02, dated January 22, 2014, including Appendices 1 and 2, dated September 26, 2013.
The actions described in this service information are intended to correct the unsafe condition identified in the MCAI.
Revision 02 ofthe service information instructs operators to contact Bombardier for repair procedures for certain configurations; paragraph (k)(2) ofthis AD addresses this issue. 

### FAA's Determination and AD Requirements
This product has been approved by the aviation authority ofanother country, and is approved for operation in the United States. Pursuant to our bilateral agreement with the State ofDesign Authority, we have been notified ofthe unsafe condition described in the MCAI and service information referenced above. We are issuing this AD because we evaluated all pertinent information and determined the unsafe condition exists and is likely to exist or develop on other products ofthe same type design. Accomplishment ofthe requirements ofthis AD constitutes terminating action for the requirements ofAD 2014-03-17, Amendment 39-17754 (79 FR 9389, February 19, 2014), for the airplanes identified in paragraph (c) ofthis AD.
FAA AD 2014-03-17, Amendment 39-17754 (79 FR 9389, February 19, 2014), corresponds to Canadian AD CF-2013-39, dated December 6, 2013. FAA AD 2014-03-17 applies to Bombardier, Inc. Model CL-600-1A11 (CL-600), CL-600-2A12 (CL-601), and CL-600-2B16 (CL-601-3A, CL-601-3R, and CL-604 Variants) airplanes. Because ofthe urgency ofthis unsafe condition for the CL-604 Variant airplanes, we have determined that it is necessary to issue an emergency AD, only for CL-604 Variant airplanes, to reduce the compliance times for the inspection required by AD 2014-03-17. 

### Explanation ofApplicability
This AD applies to Bombardier, Inc. Model CL-600-2B 16 airplanes with certain serial numbers. The CL-605 is a marketing designation for the Challenger CL-600-2B 16, CL-604 Variant, with Modsums 604DX10000, 604DX20000, and 604DX30000 incorporated, beginning with serial numbers 5701 and subsequent. All CL-604 and CL-605 airplanes are type certified as CL-600-2B16 airplanes. Therefore this AD applies to all CL-600-2B16 models in the specified serial-number range. 

### Differences Between This AD and the MCAI/Service Information Canadian Airworthiness Directive CF-2014-27 , dated August 15, 2014, specifies to replace all forward and aft fasteners at WS 76.50 and 127

.25 within 24 months, ifany incorrectly installed fasteners are found. We are considering requiring this replacement, which would terminate the actions required by this AD

. However, the planned compliance time for the replacement would allow

2enough time to provide notice and opportunity for prior public comment on the merits ofthe replacement. Although the service information identified previously specifies that operators may contact the manufacturer for disposition ofcertain repair conditions, this AD requires operators to repair those conditions in accordance with a method approved by the FAA, or the TCCA, or Bombardier, Inc.'s TCCA Design Approval Organization (DAO). Authority for this Rulemaking
Title 49 ofthe United States Code specifies the FAA's authority to issue rules on aviation safety. Subtitle I, Section 106, describes the authority ofthe FAA Administrator. Subtitle VII, Aviation Programs, describes in more detail the scope ofthe 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 ofcivil 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 ofthat authority because it addresses an unsafe condition that is likely to exist or develop on products identified in this rulemaking action. Presentation ofthe Actual AD
We are issuing this AD under 49 U.S.C. Section 44701 according to the authority delegated to me by the Administrator. 2014-17-51 Bombardier, Inc.: Directorate Identifier 2014-NM-167-AD. (a) Effective Date
This Emergency AD is effective upon receipt. (b) Affected ADs
The requirements ofthis AD terminate the requirements ofAD 2014-03-17 , Amendment 39-17754 (79 FR 9389, February 19, 2014), only for the airplanes identified in paragraph (c) ofthis AD. (c) Applicability
This AD applies to Bombardier, Inc. Model CL-600-2B 16 airplanes, certificated in any category, serial numbers 5301 through 5665 inclusive, and 5701 through 5920 inclusive. (d) Subject
Air Transport Association (ATA) ofAmerica Code 57, Wings. (e) Unsafe Condition
This AD was prompted by reports offractured fastener heads on the inboard flap hinge-box forward fitting at Wing Station (WS) 76.50 due to incorrect installation. We are issuing this AD to detect and correct incorrectly oriented or fractured fasteners , which could result in premature failure ofthe fasteners attaching the inboard flap hinge-box forward fitting. Failure ofthe fasteners could

3lead to the detachment ofthe flap hinge box and the flap surface, and consequent loss ofcontrol of the airplane. (f) Compliance Comply with this AD within the compliance times specified, unless already done. (g) Inspection: Airplanes Not Previously Inspected
For airplanes on which the actions required by AD 2014-03-17, Amendment 39-17754 (79 FR 9389, February 19, 2014), have not been done as ofreceipt ofthis AD: Within 10 flight cycles after receipt ofthis AD, or within 100 flight cycles after March 6, 2014 (the effective date ofAD 2014-03-17, Amendment 39-1 7754 (79 FR 93 89, February 19, 2014)), whichever occurs first: Do a detailed visual inspection ofeach inboard flap fastener ofthe hinge-box forward fitting at WS 76.50 and WS 127.25, on both wings, to determine ifthe fasteners are correctly oriented and intact (nonfractured, with intact fastener head). Do the inspection in accordance with the Accomplishment Instructions ofBombardier Alert Service Bulletin A604-57-006, Revision 01, dated September 26, 2013, including Appendices 1 and 2, dated September 26, 2013, or Revision 02, dated January 22, 2014, including Appendices 1 and 2, dated September 26, 2013 (for serial numbers 5301 through 5665 inclusive); or Bombardier Alert Service Bulletin A605-57-004, Revision 01, dated September 26, 2013, including Appendices 1 and 2, dated September 26, 2013, or Revision 02, dated January 22, 2014, including Appendices 1 and 2, dated September 26, 2013 (for serial numbers 5701 through 5920 inclusive). (1) Ifall fasteners are found intact and correctly oriented, no further action is required by this AD. (2) Ifany fastener is found fractured: Before further flight, remove and replace all forward and aft fasteners at WS 76.50 and WS 127.25, regardless ofcondition or orientation, on both wings, in accordance with the Accomplishment Instructions ofBombardier Alert Service Bulletin A604-57-006, Revision 01, dated September 26, 2013, including Appendices 1 and 2, dated September 26, 2013, or Revision 02, dated January 22, 2014, including Appendices 1 and 2, dated September 26, 2013 (for serial numbers 5301 through 5665 inclusive); or Bombardier Alert Service Bulletin A605-57-004, Revision 01, dated September 26, 2013, including Appendices 1 and 2, dated September 26, 2013, or Revision 02, dated January 22, 2014, including Appendices 1 and 2, dated September 26, 2013 (for serial numbers 5701 through 5920 inclusive). After replacement ofall fasteners as required by paragraph (g)(2) ofthis AD, no further action is required by this AD. (3) Ifany incorrectly oriented but intact fastener is found, and no fractured fastener is found, repeat the inspection required by paragraph (g) ofthis AD thereafter at intervals not to exceed 1 0 flight cycles, until the requirements ofparagraph (i)(1) ofthis AD have been done. (h) Airplanes Previously Inspected, With Incorrectly Oriented Fastener(s) For airplanes on which an inspection required by paragraph (g) or (j) ofAD 2014-03-17, Amendment 39-17754 (79 FR 9389, February 19, 2014), has been done as ofreceipt ofthis AD, and on which any incorrectly oriented fastener, but no fractured fastener, was found: Except as provided by paragraph (i)(3) ofthis AD, do a detailed visual inspection ofall inboard flap fasteners ofthe hinge-box forward fitting at WS 76.50 and WS 127.25, on both wings, to determine ifthe fasteners are intact (non-fractured, with intact fastener head). Inspect within 10 flight cycles after receipt ofthis AD, or within 100 flight cycles after the most recent inspection done as required by AD 2014-03-17, whichever occurs first. Inspect in accordance with the Accomplishment Instructions ofBombardier

4Alert Service Bulletin A604-57-006, Revision 01 , dated September 26, 2013 , including Appendices 1 and 2, dated September 26, 2013 , or Revision 02, dated January 22, 2014, including Appendices 1 and 2, dated September 26, 2013 (for serial numbers 5301 through 5665 inclusive); or Bombardier Alert Service Bulletin A605-57-004, Revision 01 , dated September 26, 2013 , including Appendices 1 and 2, dated September 26, 2013 , or Revision 02, dated January 22, 2014, including Appendices 1 and 2, dated September 26, 2013 (for serial numbers 5701 through 5920 inclusive)

. (1) Ifall fasteners are found intact, repeat the inspection thereafter at intervals not to exceed 10 flight cycles, until the requirements ofparagraph (i)(1) ofthis AD have been done

. (2) Ifany fastener is found fractured: Before further flight, remove and replace all forward and aft fasteners at WS 76.50 and WS 127.25 , regardless ofcondition or orientation, on both wings, in accordance with the Accomplishment Instructions ofBombardier Alert Service Bulletin A604-57-006, Revision 01 , dated September 26, 2013 , including Appendices 1 and 2, dated September 26, 2013 , or Revision 02, dated January 22, 2014, including Appendices 1 and 2, dated September 26,2013 (for serial numbers 5301 through 5665 inclusive); or Bombardier Alert Service Bulletin A605-57-004, Revision 01 , dated September 26, 2013 , including Appendices 1 and 2, dated September 26, 2013 , or Revision 02, dated January 22, 2014, including Appendices 1 and 2, dated September 26, 2013 (for serial numbers 5701 through 5920 inclusive). After replacement ofall fasteners as required by paragraph (h)(2) ofthis AD, no further action is required by this AD. (i) Terminating Action (1) Replacement ofall forward and aft fasteners at WS 76.50 and WS 127.25 , on both wings, in accordance with the Accomplishment Instructions ofBombardier Alert Service Bulletin A604-57-006, Revision 01 , dated September 26, 2013 , including Appendices 1 and 2, dated September 26, 2013 , or Revision 02, dated January 22, 2014, including Appendices 1 and 2, dated September 26, 2013 (for serial numbers 5301 through 5665 inclusive); or Bombardier Alert Service Bulletin A605-57-004, Revision 01, dated September 26, 2013 , including Appendices 1 and 2, dated September 26, 2013, or Revision 02, dated January 22, 2014, including Appendices 1 and 2, dated September 26, 2013 (for serial numbers 5701 through 5920 inclusive) ; terminates the requirements of this AD. (2) Accomplishment ofthe applicable requirements ofthis AD constitutes terminating action for the requirements ofAD 2014-03-17, Amendment 39-17754 (79 FR 9389, February 19, 2014), for that airplane only. (3) Replacement, before receipt ofthis AD, ofall fractured and incorrectly oriented fasteners , as provided by paragraph (i) or (k) ofAD 2014-03-17 , Amendment 39-17754 (79 FR 9389, February 19, 2014), is acceptable for compliance with the requirements ofthis AD. (j) Special Flight Permit Special flight permits to operate the airplane to a location where the airplane can be repaired in accordance with sections 21.197 and 21

. 199 ofthe Federal Aviation Regulations ( 14 CFR 21

. 197 and 21.199) are not allowed. (k) Other FAA Provisions (1) Alternative Methods ofCompliance (AMOCs): The Manager, New York Aircraft Certification Office, ANE-170, FAA, has the authority to approve AMOCs for this AD, ifrequested using the procedures found in 14 CFR 39.19. In accordance with 14 CFR 39.19, send your request to your principal inspector or local Flight Standards District Office, as appropriate. If sending


### 5information directly to the ACO, send it to ATTN: Program Manager, Continuing Operational Safety, FAA, New York ACO, 1600 Stewart Avenue, Suite 410, Westbury, NY 11590; telephone 516-228-7300; fax 516-794-5531. Before using any approved AMOC, notify your appropriate principal inspector, or lacking a principal inspector, the manager ofthe local flight standards district office/certificate holding district office. The AMOC approval letter must specifically reference this AD. (2) Contacting the Manufacturer: For any requirement in this AD to obtain corrective actions from a manufacturer, the action must be accomplished using a method approved by the Manager, New York Aircraft Certification Office, ANE-170, FAA; or the TCCA; or Bombardier, Inc.'s TCCA Design Approval Organization (DAO). Ifapproved by the DAO, the approval must include the DAO-authorized signature. (I) Related Information (1) For further information about this AD, contact: Aziz Ahmed, Aerospace Engineer, Propulsion and Services Branch, ANE-173, FAA, New York Aircraft Certification Office (ACO), 1600 Stewart Avenue, Suite 410, Westbury, NY 11590; telephone 516-228-7329; fax 516-794-5531. (2) For copies ofthe service information referenced in this AD, contact Bombardier, Inc., 400 Cote-Vertu Road West, Dorval, Quebec H4S 1 Y9, Canada; telephone 514-855-5000; fax 514-855-7401; email thd.crj @aero.bombardier.com; Internet http://www.bombardier.com. You may view this referenced service information at the FAA, Transport Airplane Directorate, 1601 Lind Avenue SW., Renton, WA.

Issued in Renton, Washington, on August 19, 2014.



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ev Acting Manager, Transport Airplane Directorate, Aircraft Certification Service.

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