Consigne de Navigabilité sur les ROBINSON R44 & R44 II !
Posted: Sat 11 Sep, 2021 11:57
Consigne de Navigabilité, imminente débutant le 22 septembre, 2021. Sur les ‘’Pales de Rotor de queue installé sur les Robinson R44 & R44 II, applicable sur les Numéro de Pièce (Part Number (P/N)) : C029-3, ayant les numéros de série (with serial number (S/N)) : 9410 à 9909 inclusivement.
Voir la partie ici-bas en Anglais
AIRWORTHINESS DIRECTIVE http://www.faa.gov/aircraft/safety/alerts/" onclick="window.open(this.href);return false; http://www.gpoaccess.gov/fr/advanced.html" onclick="window.open(this.href);return false;
AIRWORTHINESS DIRECTIVE: 2021-19-08
2021-19-08 Robinson Helicopter Company: Amendment 39-21726; Docket No. FAA-2021-0727; Project Identifier AD-2021-00835-R.
(a) Effective Date This airworthiness directive (AD) is effective September 22, 2021.
(b) Affected ADs None.
(c) Applicability Robinson Helicopter Company Model R44 and R44 II helicopters, certificated in any category, with a tail rotor blade (blade) part number (P/N) C029-3 with serial number (S/N) 9410 through 9909 inclusive, installed.
(d) Subject Joint Aircraft System Component (JASC) Code: 6410, Tail Rotor Blades.
(e) Unsafe Condition This AD was prompted by reports of cracked blades. The FAA is issuing this AD to detect and prevent cracks in the affected blades. The unsafe condition, if not addressed, could result in reduced controllability and subsequent loss of control of the helicopter.
(f) Compliance Comply with this AD within the compliance times specified, unless already done.
(g) Required Actions (1) Before further flight and thereafter before each flight, check each blade at the leading edge for a crack. This action may be performed by the owner/operator (pilot) holding at least a private pilot certificate and must be entered into the aircraft records showing compliance with this AD in accordance with 14 CFR 43.9(a)(1) through (4) and 14 CFR 91.417(a)(2)
(v). The record must be maintained as required by 14 CFR 91.417, 121.380, or 135.439. (2) If there is any crack, before further flight, remove the blade from service. (3) As of the effective date of this AD, do not install a blade identified in paragraph (c) of this AD on any helicopter. (4) Within three months after the effective date of this AD, remove from service any blade identified in paragraph (c) of this AD.
Les informations suivantes ont été récemment publiées sur le site Web des Consignes de navigabilité de Transport Canada : Le sujet et l’applicabilité sont alimentés à partir du document original. Les informations provenant de sources étrangères ne sont pas soumises à la Loi sur les langues officielles, il n’y a donc pas de traduction disponible.
Numéro : US2021-19-08
Sujet : ATA 64 - TAIL ROTOR BLADES - DETECT AND PREVENT CRACKS IN THE AFFECTED BLADES
Applicabilité : Robinson Helicopter Company Model R44 and R44 II helicopters
Lien : https://wwwapps.tc.gc.ca/saf-sec-sur/2/ ... -19-08.PDF" onclick="window.open(this.href);return false;
Voir la partie ici-bas en Anglais
AIRWORTHINESS DIRECTIVE http://www.faa.gov/aircraft/safety/alerts/" onclick="window.open(this.href);return false; http://www.gpoaccess.gov/fr/advanced.html" onclick="window.open(this.href);return false;
AIRWORTHINESS DIRECTIVE: 2021-19-08
2021-19-08 Robinson Helicopter Company: Amendment 39-21726; Docket No. FAA-2021-0727; Project Identifier AD-2021-00835-R.
(a) Effective Date This airworthiness directive (AD) is effective September 22, 2021.
(b) Affected ADs None.
(c) Applicability Robinson Helicopter Company Model R44 and R44 II helicopters, certificated in any category, with a tail rotor blade (blade) part number (P/N) C029-3 with serial number (S/N) 9410 through 9909 inclusive, installed.
(d) Subject Joint Aircraft System Component (JASC) Code: 6410, Tail Rotor Blades.
(e) Unsafe Condition This AD was prompted by reports of cracked blades. The FAA is issuing this AD to detect and prevent cracks in the affected blades. The unsafe condition, if not addressed, could result in reduced controllability and subsequent loss of control of the helicopter.
(f) Compliance Comply with this AD within the compliance times specified, unless already done.
(g) Required Actions (1) Before further flight and thereafter before each flight, check each blade at the leading edge for a crack. This action may be performed by the owner/operator (pilot) holding at least a private pilot certificate and must be entered into the aircraft records showing compliance with this AD in accordance with 14 CFR 43.9(a)(1) through (4) and 14 CFR 91.417(a)(2)
(v). The record must be maintained as required by 14 CFR 91.417, 121.380, or 135.439. (2) If there is any crack, before further flight, remove the blade from service. (3) As of the effective date of this AD, do not install a blade identified in paragraph (c) of this AD on any helicopter. (4) Within three months after the effective date of this AD, remove from service any blade identified in paragraph (c) of this AD.
Les informations suivantes ont été récemment publiées sur le site Web des Consignes de navigabilité de Transport Canada : Le sujet et l’applicabilité sont alimentés à partir du document original. Les informations provenant de sources étrangères ne sont pas soumises à la Loi sur les langues officielles, il n’y a donc pas de traduction disponible.
Numéro : US2021-19-08
Sujet : ATA 64 - TAIL ROTOR BLADES - DETECT AND PREVENT CRACKS IN THE AFFECTED BLADES
Applicabilité : Robinson Helicopter Company Model R44 and R44 II helicopters
Lien : https://wwwapps.tc.gc.ca/saf-sec-sur/2/ ... -19-08.PDF" onclick="window.open(this.href);return false;
je dis ça de même.... 
Mon tiroir à souvenirs s'est ouvert du mauvais bord.