Airworthiness directives › 98-22-16
AD 98-22-16 Airworthiness Directives; Robinson Helicopter Company (RHC) Model R44 Helicopters
Makes named: robinson. Models named: R44. Read the applicability below — it usually turns on serial or part numbers too.
Applicability*9
Model R44 helicopters, serial numbers (S/N) 0002 through 0486, with main rotor blades, part number (P/N) C016-1, installed, 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 (f) 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 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 a main rotor blade and subsequent loss of control of the helicopter, accomplish the following: (a) Within the next 5 hours time-in-service (TIS), perform a dye-penetrant inspection of the main rotor blade skin around both inboard trim tab alignment rivets as follows, referring to Figure 1. BILLING CODE 4910-13-U [[Page 62934]] [GRAPHIC] [TIFF OMITTED] TR10NO98.000 BILLING CODE 4910-13-C [[Page 62935]] (1) Remove all paint around both rivets, exposing an area of approximately 3/4'' in diameter, at the inboard trim tab on the top and bottom of each main rotor blade (4 places per main rotor blade). Use 180 grit or finer abrasive paper, followed by 600 grit or finer paper to eliminate course sanding marks. Sand only in a spanwise direction. Do not use chemical paint strippers. (2) Inspect the main rotor blade skin around the rivets on the upper and lower surfaces (4 locations) using a dye-penetrant inspection method. Note 2: Chordwise cracks in the paint up to 2 inches long which are located along either inboard or outboard edge of the trim tab are acceptable. (b) Clean the sanded areas prepared in accordance with paragraph (a) of this AD with 111-Trichloroethane or methyl ethyl ketone (MEK) and then apply clear lacquer to seal the unpainted areas. Note 3: Do not bend the inboard main rotor blade tabs from their present position or utilize them for any subsequent main rotor blade tracking adjustment. (c) Thereafter, prior to the first flight of each day, or at intervals not to exceed 5 hours TIS, whichever occurs first, using a 5-power or higher magnifying glass, visually inspect both upper and lower main rotor blade skin surfaces around the inboard trim tab rivets (4 locations) for cracks. (d) If a crack is found, replace the main rotor blade with an airworthy main rotor blade before further flight. (e) Prior to further flight after November 15, 1998, install a set of main rotor blades, main rotor blade P/N C016-2. This constitutes terminating action for the inspections required by this AD. Note 4: Robinson Helicopter Company R44 Service Bulletin SB-27B, Revision B, and Robinson Helicopter Company Service Bulletin SB-28, both dated June 18, 1998, pertain to the subject of this AD. (f) An alternative method of compliance or adjustment of the compliance time that provides an acceptable level of safety may be used when approved by the Manager, Los Angeles Aircraft Certification Office, FAA. Operators shall submit their requests through an FAA Principal Maintenance Inspector, who may concur or comment and then send it to the Manager, Los Angeles Aircraft Certification Office. Note 5: Information concerning the existence of approved alternative methods of compliance with this AD, if any, may be obtained from the Los Angeles Aircraft Certification Office. (g) Special flight permits will not be issued. (h) This amendment becomes effective on November 10, 1998, to all persons except those persons to whom it was made immediately effective by Priority Letter AD 98-22-16, issued October 22, 1998, which contained the requirements of this amendment. Issued in Fort Worth, Texas, on November 1, 1998. Eric Bries, Acting Manager, Rotorcraft Directorate, Aircraft Certification Service. [FR Doc. 98-30046 Filed 11-9-98; 8:45 am] BILLING CODE 4910-13-U
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The directive text above is reproduced from the Federal Register, a work of the United States government and in the public domain. The separation into applicability, compliance and required actions is TrackAD's.*1