Airworthiness directives › 98-24-32
AD 98-24-32 Airworthiness Directives; Eurocopter France Model AS-365N2, SA- 360C, SA-365C, C1, C2, N, N1, and SA-366G1 Helicopters
Applicability*9
Model AS-365N2, SA-360C, SA-365C, C1, C2, N, N1, and SA-366G1, certificated in any category. Note 1: This AD applies to each helicopter identified in the preceding applicability provision, regardless of whether it has been modified, altered, or repaired in the area subject to the requirements of this AD. For helicopters that have been modified, altered, or repaired so that the performance of the requirements of this AD is affected, the owner/operator must use the authority provided in paragraph (e) to request approval from the FAA. This approval may address either no action, if the current configuration eliminates the unsafe condition, or different actions necessary to address the unsafe condition described in this AD. Such a request should include an assessment of the effect of the changed configuration on the unsafe condition addressed by this AD. In no [[Page 65550]] case does the presence of any modification, alteration, or repair remove any helicopter from the applicability of this AD.
Compliance
Required as indicated, unless accomplished previously To prevent failure of an attachment spring (spring), which could cause loss of the tail rotor hub fairing (fairing), damage to the tail rotor, and subsequent loss of control of the helicopter, accomplish the following: (a) Before further flight with fairing, part number (P/N) 360A33-1079-01, installed, that has modification 365A07-64B20 incorporated but is not marked with an ``X'' after the part number: (1) Remove the six fairing attachment bolts (bolts), then remove the fairing from the helicopter. (2) Inspect for broken springs, especially in the rounded sections at the rotor hub groove (Point A, Figure 1). BILLING CODE 4910-13-U [[Page 65551]] [GRAPHIC] [TIFF OMITTED] TR27NO98.000 BILLING CODE 4910-13-C [[Page 65552]] (3) If any broken springs are discovered, replace them with airworthy springs using the procedure specified in paragraph (b) of this AD. (4) Lubricate the threads with NATO 156 oil, then reinstall the six bolts, torqued to 0.4-0.5 m.daN (35.3-44.2 in.-lbs.). (5) Inspect for interference between the spring and the fairing (Point B, Figure 2), and replace any spring that exhibits such interference in accordance with the procedure specified in paragraph (b) of this AD. (6) Measure the outward axial protrusion (Dimension e, Figure 1), for each spring. If the protrusion dimension obtained from the measurement required by paragraph (a)(6) of this AD is less than 1mm (0.039-inches), or greater than 2.7mm (0.106 inches), either (i) replace the spring with an airworthy spring before further flight or, (ii) Inspect the out-of-tolerance spring(s) in accordance with paragraph (a)(2) before the first flight of each day until each spring is replaced with an airworthy spring. Any out-of-tolerance spring must be replaced with an airworthy spring within 25 hours time-in-service (TIS). (b) Replace a broken or out-of-tolerance spring as follows: (1) Remove the spring attachment rivet. (2) Temporarily install an airworthy spring, P/N 360A33-1078-01, and verify that the axial protrusion (Dimension e, Figure 1) is within tolerance and that no interference (see Figure 2) exists. (3) Permanently secure the new spring to the fairing with one ASN-A0078B402 rivet, coated with Mastinox 6856KD150-2, and installed with the rivet head on the outside of the fairing (see Figure 1). (4) Mark an ``X'' after the fairing part number using indelible ink after completing all inspections and spring replacements, as required. (c) Reinstall the fairing. (d) If one or more springs are replaced, rebalance the tail rotor head. (e) An alternative method of compliance or adjustment of the compliance time that provides an acceptable level of safety may be used if approved by the Manager, Rotorcraft Standards Staff, Rotorcraft Directorate, FAA. Operators shall submit their requests through an FAA Principal Maintenance Inspector, who may concur or comment and then send it to the Manager, Rotorcraft Standards Staff. Note 2: Information concerning the existence of approved alternative methods of compliance with this AD, if any, may be obtained from the Rotorcraft Standards Staff. (f) Special flight permits will not be issued. (g) This amendment becomes effective on December 14, 1998. Note 3: The subject of this AD is addressed in Direction Generale De L'Aviation Civile (France) AD 95-107-039(B)R1 and AD 95- 112-040(B), both dated June 7, 1995, and AD 95-108-018(B), dated May 24, 1995. Issued in Fort Worth, Texas, on November 19, 1998. Eric Bries, Acting Manager, Rotorcraft Directorate, Aircraft Certification Service. [FR Doc. 98-31589 Filed 11-25-98; 8:45 am] BILLING CODE 4910-13-U
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