FAA 

Aviation Safety 

DATE: August 6, 2015 

AD#: 2015-16-51 

EMERGENCY 

AIRWORTHINESS DIRECTIVE 

www.faa.gov/aircraft/safety/alerts/ 

This emergency airworthiness directive (EAD) 2015-16-51 is being sent to owners and 

operators of Bell Helicopter Textron Canada Limited (Bell) Model 429 helicopters. 

Background 

This EAD was prompted by several reports of 

This condition, if not corrected, could result in 

helicopter. 

Transport 

16, dated July 2, 9 helicopters. Transport 

Canada advises link spherical bearings have 

experienced early ons, bearings were found worn beyond limits 

during pre-flight axial play that was easily detectable. In one case, 

the spherical rotor pitch link, resulting in damage to the tail rotor 

blade pitch horn another case, the spherical bearing had been inspected and found 

acceptable during inspection; about "1 hour air time" later, it was found worn beyond 

limits during a pre-flight inspection. 

FAA's Determination 

This helicopter has been approved by the aviation authority of Canada and is approved for 

operation in the United States. Pursuant to our bilateral agreement with Canada, Transport Canada, its 

technical representative, has notified us ofthe unsafe condition described in its EAD. We are issuing 

this EAD because we evaluated all information provided by Transport Canada and determined the 

unsafe condition exists and is likely to exist or develop on other helicopters of the same type design. 

Related Service Information 

Bell has issued Alert Service Bulletin 429-15-16, dated February 18, 2015 (ASB). The ASB 

applies to Bell Model429 helicopters, SIN 57001 and subsequent, which have accumulated more 

than 50 hours. The ASB specifies the following actions: 

• Inspecting both inboard and outboard tail rotor pitch link assemblies for axial and radial play; 

• If abnormal wear or bearing play is detected, removing the affected tail rotor pitch link and 

performing a dimensional check of both axial and radial play; and 

• Replacing any tail rotor pitch link assembly 429-012-112-10 I or -103 or pitch link bearing 

429-312-107-103 that exceeds the allowable limits. 
EAD Requirements 

This EAD requires, before further flight, and thereafter at intervals not to exceed 50 hours 

time-in-service (TIS), inspecting each inboard and outboard tail rotor pitch link assembly for axial or 

radial bearing play. If there is axial or radial bearing play, removing the tail rotor pitch link and 

performing a dimensional inspection for wear are required. If there is wear that exceeds the allowable 

limits, replacing the tail rotor pitch link assembly is required. 

Differences between this EAD and the Transport Canada EAD 

The Transport Canada EAD requires the inspection of the inboard and 

pitch link assembly for wear or axial or radial bearing play to be done 

EAD requires the inspection before further flight. 

Interim Action 

consider further ru 

tail rotor 

TIS, and this 

the FAA's authority to issue rules on aviation 

authority ofthe FAA Administrator. "Subtitle VII, 

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 44 70 I, 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 rulel!laking action. 

Adoption of the Emergency Airworthiness Directive (EAD) 

We are issuing this EAD under 49 U.S.C. Sections 106(g), 40113, and 44701 according to the 

authority delegated to me by the Administrator. 

2015-16-51 Bell Helicopter Textron Canada Limited: Directorate Identifier 2015-SW-23-AD. 

(a) Applicability 

This EAD applies to Model 429 helicopters that have 50 or more hours time-in-service (TIS), 

with a pitch link assembly part number 429-012-112-101 or -103 installed, certificated in any 

category. 

(b) Unsafe Condition 

This EAD defines the unsafe condition as a worn pitch link. This condition, if not detected 

and corrected, could result in pitch link failure and subsequent loss of control of the helicopter. 

(c) Effective Date 

This EAD is effective upon receipt. 

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(d) Compliance 

You are responsible for performing each action required by this EAD within the specified 

compliance time unless it has already been accomplished prior to that time. 

(e) Required Actions 

Before further flight and thereafter at intervals not to exceed 50 hours TIS, inspect each 

inboard and outboard tail rotor pitch link assembly for axial or radial bearing play. If there is axial or 

radial bearing play, remove the tail rotor pitch link and perform a dimensional inspection for wear. If 

there is wear that exceeds the allowable limits, replace the tail rotor pitch link assembly. 

(f) Alternative Methods of Compliance (AMOCs) 

(1) The Manager, Safety Management Group, FAA, 

Send your proposal to: David Hatfield, Aviation 

Rotorcraft Directorate, FAA, 1 0 1 0 I Hill wood 

222-5I10; email9-ASW-FTW 

(g) 

or under I4 CFR 

lacking a principal 

or certificate holding district office, 

anAMOC. 

contact: David Hatfield, Aviation Safety Engineer, Safety 

Management Group, Directorate, FAA, I 0 I 0 1 Hill wood Pkwy, Fort Worth, TX 7 6177; 

telephone (8I7) 222-5II 0; email david.hatfield@faa.gov. 

(2) Bell Helicopter Alert Service Bulletin 429-15-16, dated February 18, 2015, which is not 

incorporated by reference, contains additional information about the subject of this EAD. For a copy 

ofthe ASB, contact: Bell Helicopter Textron Canada Limited, I2,800 Rue de l'Avenir, Mirabel, 

Quebec J7JlR4; telephone (450) 437-2862 or (800) 363-8023; fax (450) 433-0272; or at 

http://www.bellcustomer.com/files/. 

(3) The subject of this EAD is addressed in Transport Canada AD No. CF -20 I5-I6, dated 

July 2, 2015. 

(h) Subject 

Air Transport Association of America (A TA) Tracking Code: 6720 Tail Rotor Control 

System. 

Issued in Fort Worth, Texas, on August 6, 20I5. 

Larry M. Kelly, 

Acting Manager, Rotorcraft Directorate, 

Aircraft Certification Service. 

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