Airworthiness directives › 98-18-11
AD 98-18-11 Airworthiness Directives; Schweizer Aircraft Corporation and Hughes Helicopters, Inc. Model 269A, 269A-1, 269B, 269C, 269D, and TH- 55A Helicopters
Makes named: schweizer. Models named: 269A, 269A-1, 269B, TH-55A, 269C, 269D. Read the applicability below — it usually turns on serial or part numbers too.
Applicability*9
Model 269A, 269A-1, 269B, and TH-55A helicopters with main rotor blades, part number (P/N) 269A1190-1, serial numbers (S/N) S0001 through S0012 installed; and Model 269C and 269D helicopters with main rotor blades, P/N 269A1185-1, S/N S222, S312, S313, S325 through S327, S339, S341, S343, S346, S347, S349 through S367, S369 through S377, S379 through S391, S393 through S395, S397, S399, S401 through S417, S419 through S424, S426 through S449, S451 through S507, S509 through S513, S516 through S527, S529 through S540, S542, S544 through S560, S562 through S584, S586 through S595, S597 though S611, S620 through S623, S625, S628, S633, S641 through S644, S646, S653, S658, S664, S665, and S667, 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 (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 case does the presence of any modification, alteration, or repair (except for the repair of the abrasion strip) remove any helicopter from the applicability of this AD.
Compliance
Required as indicated, unless accomplished previously. To prevent loss of the abrasion strip from a main rotor blade (blade) and subsequent loss of control of the helicopter, accomplish the following: (a) Within the next 50 hours time-in-service (TIS), or within 90 calendar days after the effective date of this AD, whichever is earlier, or prior to installing an affected replacement blade, and thereafter at intervals not to exceed 50 hours TIS from the date of the last inspection or replacement installation: (1) Visually inspect the adhesive bead around the perimeter of each abrasion strip for erosion, cracks, or blisters. (2) Visually inspect the bond line between each abrasion strip and each blade skin for voids, separation, or lifting of the abrasion strip. (3) Inspect each abrasion strip for debonding or hidden corrosion voids using a tap (ring) test as described in the applicable maintenance manual. [[Page 46647]] (b) If any deterioration of an abrasion strip adhesive bead is discovered, prior to further flight, restore the bead in accordance with the applicable maintenance manual. (c) If abrasion strip debonding, separation, or a hidden corrosion void is found or suspected, prior to further flight, remove the blade with the defective abrasion strip and replace it with an airworthy blade. (d) Repair of an affected blade's abrasion strip is considered a terminating action for the requirements of this AD. Identify the repaired blade with a white dot added adjacent to the blade S/N. (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, New York 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, New York Aircraft Certification Office. Note 2: Information concerning the existence of approved alternative methods of compliance with this AD, if any, may be obtained from the New York Aircraft Certification Office. (f) Special flight permits may be issued in accordance with sections 21.197 and 21.199 of the Federal Aviation Regulations (14 CFR 21.197 and 21.199) to operate the helicopter to a location where the requirements of this AD can be accomplished, provided the abrasion strip has not started to separate or debond from the main rotor blade. (g) This amendment becomes effective on October 7, 1998. Issued in Fort Worth, Texas, on August 21, 1998. Larry M. Kelly, Acting Manager, Rotorcraft Directorate, Aircraft Certification Service. [FR Doc. 98-23600 Filed 9-1-98; 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