| AD Number | 86-06-08 R1 | Status | Superseded |
| Effective Date | July 10, 1987 | Issue Date | Not specified |
| Docket Number | 86-ASW-10 | Amendment | 39-5626 |
| Product Type | ["Aircraft"] | Product Subtype | ["Rotorcraft"] |
| CFR Part | --- - Part 39 | CFR Section | N/A |
| Citation | This information is not available. | ||
| Manufacturer(s) | Bell Helicopter Textron Scotts-Bell 47 Inc Bell Helicopter Textron Continental Copters, Inc. Isenberg, Wilbur M. McCreary, Gifton Teryjon Aviation, Inc. |
| Model(s) | 47B 47B3 47D 47D1 47E 47G 47G-2 47G-2A 47G-2A-1 47G-3 47G-3B 47G-3B-1 47G-3B-2 47G-3B-2A 47G-4 47G-4A 47G-5 47G-5A 47H-1 47J 47J-2 47J-2A 47K OH-13H OH-13E OH-13E OH-13H Fast Kat I (U.S. Army OH-13S) |
| Superseded By | 2000-18-51 |
86-06-08 R1 BELL HELICOPTER TEXTRON, INC.: TEXAS HELICOPTER CORPORATION: HAWKEYE ROTOR AND WING: TERYJON AVIATION, INC.: CONTINENTAL COPTERS, INC.: Amendment 39-5260 as amended by Amendment 39- 5626. Applies to Model 47 series, U.S. Army Model OH-13E, U.S. Army Model OH-13H, and Model Fast Kat I (U.S. Army Model OH-13S) helicopters certified in any category equipped with main rotor blade grips, BHTI Part Numbers (P/N) 47-120-135-2, 47-120-135-3, 47-120-135-5, and 47-120-252-1; Main Rotor Grip Assembly BHTI P/N's 47-120-252-7 and 47-120-252-11; and Texas Helicopters, Inc., Parts Manufacturer Approval (PMA) P/N's 74-120-252-11 and 74- 120-135-5. (AD Docket No. 86-ASW-10).
Compliance is required as indicated, unless already accomplished.
To prevent failure of the main rotor blade grip, accomplish the following:
(a) Inspect main rotor blade grips having 1,175 hours or more time in service on the effective date of this AD within the next 25 hours time in service, and thereafter at intervals not to exceed 300 hours time in service in accordance with paragraph (c) of this AD.
(b) Inspect main rotor blade grips having less than 1,175 hours time in service prior to the accumulation of 1200 hours time in service and thereafter at intervals not to exceed 300 hours time in service in accordance with paragraph (c) of this AD.
(c) Perform a fluorescent dye penetrant inspection of the main rotor blade threads in accordance with Military Standard No. MIL-STD-6866, dated November 29, 1985. The penetrant inspection requirements of MIL-STD-6866 paragraph 4.3 are not required.
(d) Alternative inspections, modifications, or other actions which provide an equivalent level of safety may be used when approved by the Manager, Helicopter Certification Branch, Southwest Region, Federal Aviation Administration, P.O. Box 1689, Fort Worth, Texas 76101. Inspections performed in accordance with MIL-I-6866B through Amendment 3 provide an equivalent level of safety with paragraph (c) of this AD. The inspection requirements of paragraph 5.8 of MIL-I-6866B are not required.
(e) This AD does not alter the time in service life limit of the main rotor blade grips.
This procedure shall be done in accordance with Military Standard MIL-STD-6866, dated November 29, 1985. This incorporation by reference was approved by the Director of the Federal Register in accordance with 5 U.S.C. (a) and 1 CFR Part 51. Copies may be obtained upon request to the Commanding Officer, Naval Publications and Forms Center, 5801 Tabor Avenue, Philadelphia, Pennsylvania 19120, by referencing MIL-STD-6866 listed in D.O.D. Index of Specifications and Standards.
Copies may be inspected at the Office of Regional Counsel, FAA, 4400 Blue Mound Road, Fort Worth, Texas, or at the Office of the Federal Register, 1100 L Street, NW., Room 8401, Washington, D.C.
This amendment, 39-5626, becomes effective July 10, 1987.
This amendment amends Amendment 39-5260 (51 FR 11300), AD No. 86-06-08.