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 of a 

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 of these 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 of the fasteners attaching the 

inboard flap hinge-box forward fitting. Failure of the fasteners could lead 

to the detachment of the flap hinge box and consequently the detachment 

of the flap surface. The loss of a flap surface could adversely affect the 

continued safe operation of the aeroplane. 

The original issue of AD 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) of each 

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 of AD 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 of the 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: 

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• 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 of the service information instructs operators to contact Bombardier for repair 

procedures for certain configurations; paragraph (k)(2) of this AD addresses this issue. 

FAA's Determination and AD Requirements 

This product has been approved by the aviation authority of another country, and is approved 

for operation in the United States. Pursuant to our bilateral agreement with the State of Design 

Authority, we have been notified of the unsafe condition described in the MCAI and service 

information referenced above. We are 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 of the 

same type design. 

Accomplishment of the requirements of this AD constitutes terminating action for the 

requirements of AD 2014-03-17, Amendment 39-17754 (79 FR 9389, February 19, 2014), for the 

airplanes identified in paragraph (c) of this 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 of the urgency of this 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 of Applicability 

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, if any 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 

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enough time to provide notice and opportunity for prior public comment on the merits of the 

replacement. 

Although the service information identified previously specifies that operators may contact 

the manufacturer for disposition of certain 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 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 ofthat authority because it addresses an unsafe condition that is likely 

to exist or develop on products identified in this rulemaking action. 

Presentation of the 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 of this AD terminate the requirements of AD 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) of America Code 57, Wings. 

(e) Unsafe Condition 

This AD was prompted by reports of fractured 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 

of the fasteners attaching the inboard flap hinge-box forward fitting. Failure of the fasteners could 

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lead to the detachment of the flap hinge box and the flap surface, and consequent loss of control 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 of this AD, or within 100 flight cycles after March 6, 2014 (the effective date of AD 

2014-03-17, Amendment 3 9-1 77 54 (79 FR 93 89, February 19, 2014) ), whichever occurs first: Do a 

detailed visual inspection of each inboard flap fastener of the 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 of Bombardier 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) If all fasteners are found intact and correctly oriented, no further action is required by this 

AD. 

(2) If any fastener is found fractured: Before further flight, remove and replace all forward 

and aft fasteners at WS 76.50 and WS 127.25, regardless of condition or orientation, on both wings, 

in accordance with the Accomplishment Instructions of Bombardier 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 of all 

fasteners as required by paragraph (g)(2) of this AD, no further action is required by this AD. 

(3) If any incorrectly oriented but intact fastener is found, and no fractured fastener is found, 

repeat the inspection required by paragraph (g) of this AD thereafter at intervals not to exceed 1 0 

flight cycles, until the requirements of paragraph (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) of AD 2014-03-17, 

Amendment 39-17754 (79 FR 9389, February 19, 2014), has been done as of receipt ofthis AD, and 

on which any incorrectly oriented fastener, but no fractured fastener, was found: Except as provided 

by paragraph (i)(3) of this AD, do a detailed visual inspection of all inboard flap fasteners ofthe 

hinge-box forward fitting at WS 76.50 and WS 127.25, on both wings, to determine if the fasteners 

are intact (non-fractured, with intact fastener head). Inspect within 10 flight cycles after receipt of this 

AD, or within 100 flight cycles after the most recent inspection done as required by AD 2014-03-1 7, 

whichever occurs first. Inspect in accordance with the Accomplishment Instructions of Bombardier 

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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) If all fasteners are found intact, repeat the inspection thereafter at intervals not to exceed 

10 flight cycles, until the requirements of paragraph (i)(1) of this AD have been done. 

(2) If any fastener is found fractured: Before further flight, remove and replace all forward 

and aft fasteners at WS 76.50 and WS 127.25, regardless of condition or orientation, on both wings, 

in accordance with the Accomplishment Instructions of Bombardier 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 of all 

fasteners as required by paragraph (h)(2) of this AD, no further action is required by this AD. 

(i) Terminating Action 

(1) Replacement of all forward and aft fasteners at WS 76.50 and WS 127.25, on both wings, 

in accordance with the Accomplishment Instructions of Bombardier 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 of this AD constitutes terminating action 

for the requirements of AD 2014-03-17, Amendment 39-17754 (79 FR 9389, February 19, 2014), for 

that airplane only. 

(3) Replacement, before receipt of this AD, of all fractured and incorrectly oriented fasteners, 

as provided by paragraph (i) or (k) of AD 2014-03-17, Amendment 39-17754 (79 FR 9389, 

February 19, 2014), is acceptable for compliance with the requirements of this 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 of the Federal Aviation Regulations ( 14 CFR 21 .197 

and 21.199) are not allowed. 

(k) Other FAA Provisions 

(1) Alternative Methods of Compliance (AMOCs): The Manager, New York Aircraft 

Certification Office, ANE-170, FAA, has the authority to approve AMOCs for this AD, if requested 

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 

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information 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 of the 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). If approved 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 of the 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 

514-85 5-7 401; 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. 

--- ------

ev 

Acting Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

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