AD 2014-05-10 Airworthiness Directives; Airbus Helicopters (Type Certificate Previously Held by Eurocopter France) (Airbus Helicopters)

This AD supersedes AD No. 2012-25-04, Amendment 39-17285 (78 FR 24041, April 24, 2013).

(1) For Model AS350B3 helicopters with MOD 07 5601 installed: Note 1 to paragraph (f) of this AD: MOD 075601 is an integral part of a specific Model AS350B3 configuration, commercially identified as “AS350B3e” and is not fitted on Model AS350B3 helicopters of other configurations. (i) Before further flight: (A) Install a velocity never exceed (V NE ) placard that reads as follows on the instrument panel in full view of the pilot and co-pilot with 6-millimeter red letters on a white background: VNE LIMITED TO 100 KTS IAS. (B) Replace the IAS limit versus the flight altitude placard located inside the cabin on the center post with the placard as depicted in Figure 1 to paragraph (f) of this AD:       VNE POWER ON Hp (ft) IAS (kts) 0 100 2000 97 4000 94 6000 91 8000 88 10000 85 12000 82 14000 79 16000 76 18000 73 20000 70 22000 67 Valid for VNE POWER OFF Figure 1 to paragraph (f) (ii) Before further flight, revise the Rotorcraft Flight Manual (RFM) by inserting a copy of this AD into the RFM or by making pen and ink changes as follows: (A) Revise paragraph 2.3 of the RFM by inserting the following: VNE limited to 100 kts IAS. (B) Revise paragraph 2.6 of the RFM by inserting Figure 2 to paragraph (f) of this AD.       VNE POWER ON Hp (ft) IAS (kts) 0 100 2000 97 4000 94 6000 91 8000 88 10000 85 12000 82 14000 79 16000 76 18000 73 20000 70 22000 67 Valid for VNE POWER OFF Figure 2 to paragraph (f) (C) Add the following as paragraph 3.3.3 to the RFM: 3.3.3 IN-FLIGHT VIBRATIONS FELT IN THE PEDALS Symptom: IN-FLIGHT VIBRATIONS FELT IN THE PEDALS 1. CHECK PEDAL EFFECTIVENESS 2. SMOOTHLY REDUCE THE SPEED TO VY 3. AVOID SIDESLIP AS MUCH AS POSSIBLE LAND AS SOON AS POSSIBLE (iii) Before further flight, and thereafter after each flight, without exceeding 3 hours time-in-service (TIS) between two checks, visually check each bearing as follows: (A) Position both tail rotor blades horizontally. (B) Apply load (F) by hand, perpendicular to the pressure face of one tail rotor blade (a), as shown in Figure 3 to paragraph (f) of this AD, taking care not to reach the extreme position against the tail rotor hub. The load will deflect the tail rotor blade towards the tail boom. (C) While maintaining the load, check all the visible faces of the bearings (front and side faces) in area B of DETAIL A of Figure 3 to paragraph (f) of this AD for separation between the elastomer and metal parts, a crack in the elastomer, or an extrusion (see example in Figure 4 to paragraph (f) of this AD). A flashlight may be used to enhance the check. BILLING CODE 4910-13-P ER28MR14.036 ER28MR14.037 (D) Repeat paragraphs (f)(1)(iii)(A) through (f)(1)(iii)(C) of this AD on the other tail rotor blade. (E) Apply load (G) by hand perpendicular to the suction face of one tail rotor blade as shown in Figure 5 to paragraph (f) of this AD. The load will deflect the tail rotor blade away from the tail boom. ER28MR14.038 (F) While maintaining the load, check visible faces of Area C as shown in Figure 5 to paragraph (f) of this AD for any extrusion. A flashlight may be used to enhance the check. (G) Repeat paragraphs (f)(1)(iii)(E) and (f)(1)(iii)(F) of this AD on the other tail rotor blade. (iv) The actions required by paragraphs (f)(1)(iii)(A) through (f)(1)(iii)(G) of this AD 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)-(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. (v) If there is an extrusion on any bearing, before further flight, replace the four bearings with airworthy bearings. (vi) If there is a separation or a crack on the pressure side bearing, measure the separation or the crack. If the separation or crack is greater than 5 millimeters (.196 inches) as indicated by dimension “L” in Figure 6 to paragraph (f) of this AD, before further flight, replace the four bearings with airworthy bearings. ER28MR14.039 BILLING CODE 4910-13-C (vii) No later than after the last flight of the day, perform a one-time inspection by removing the bearings and inspecting for a separation, a crack, or an extrusion. This inspection is not a daily inspection. If there is a separation, crack, or extrusion, before further flight, replace the four bearings with airworthy bearings. (viii) Within 130 hours TIS: (A) Modify the chin weight support as described in the Accomplishment Instructions, paragraphs 3.B.2.a through 3.B.2.h, of Eurocopter Service Bulletin (SB) No. AS350-64.00.11, Revision 0, dated December 19, 2012. (B) Remove the additional chin weights, install blanks on the chin weights, replace bearings with more than 5 hours TIS, and re-identify the blade assembly as described in the Accomplishment Instructions, paragraph 3.B.2.a., of Eurocopter SB No. AS350-01.00.66, Revision 1, dated February 15, 2013 (SB AS350-01.00.66). (C) Modify and re-identify the rotating pitch-change spider assembly as described in the Accomplishment Instructions, paragraph 3.B.2.b., of SB AS350-01.00.66. (D) Install a load compensator as described in the Accomplishment Instructions, paragraph 3.B.3.b., of SB AS350-01.00.66. (E) Modify the electrical installation as described in the Accomplishment Instructions, section 3.B.4., of SB AS350-01.00.66. Note 2 to paragraph (f) of this AD: The manufacturer refers to the actions in paragraphs (f)(1)(viii)(B) through (f)(1)(viii)(E) of this AD as MOD 07 5606. (ix) After modification of a helicopter as required by paragraphs (f)(1)(viii)(A) through (f)(1)(viii)(E) of this AD, the actions of paragraph (f)(1)(iii) through (f)(1)(vii) of this AD are no longer required and the operating limitation placards and RFM procedures required by paragraphs (f)(1)(i) through (f)(1)(ii)(C) of this AD may be removed. (2) For Model AS350B, AS350BA, AS350B1, AS350B2, AS350C, AS350D, AS350D1, AS355E, AS355F, AS355F1, AS355F2, AS355N, AS355NP helicopters, and Model AS350B3 helicopters that do not have MOD 07 5601 installed: (i) No later than after the last flight of the day, and thereafter during each last flight of the day check, without exceeding 10 hours TIS between two checks, visually check each bearing as described in paragraphs (f)(1)(iii)(A) through (f)(1)(vi) of this AD. (ii) If there is an extrusion on any bearing, before further flight, replace the bearing with an airworthy bearing. (iii) If there is a separation or a crack on the bearing, measure the separation or the crack. If the separation or crack is greater than 5 mm (.196 inches) as indicated by dimension “L” and greater than 2 mm (.078 inches) as indicated by dimension “P” in Figure 3 of Eurocopter Emergency Alert Service Bulletin (EASB) No. 05.00.71 or No. 05.00.63, both Revision 2 and both dated December 19, 2012, as applicable to your model helicopter, before further flight, replace the bearing.

Actions accomplished before the effective date of this AD in accordance with Emergency AD No. 2012-21-51, dated October 19, 2012, or AD No. 2012-25-04, Amendment 39-17285 (78 FR 24041, April 24, 2013) are considered acceptable for compliance with the corresponding actions of this AD.

You are responsible for performing each action required by this AD within the specified compliance time unless it has already been accomplished prior to that time.

This AD defines the unsafe condition as severe vibrations due to failure of laminated half-bearings (bearings). This condition could result in failure of the tail rotor and subsequent loss of control of the helicopter.