| AD Number | 78-25-04 | Status | Active |
| Effective Date | December 18, 1978 | Issue Date | Not specified |
| Docket Number | Unknown | Amendment | 39-3364 |
| Product Type | ["Aircraft"] | Product Subtype | ["Rotorcraft"] |
| CFR Part | --- - Part 39 | CFR Section | N/A |
| Citation | This information is not available. | ||
| Manufacturer(s) | Schweizer Aircraft Corporation |
| Model(s) | 269A 269A-1 269B 269C |
78-25-04 HUGHES HELICOPTERS: Amendment 39-3364. Applies to Hughes Model 269A, TH-55A, 269A-1, 269B and 269C helicopters equipped with part number 269A5103-9 pinion assemblies, Hughes Tool Company, Serial Nos. 001 through 5101, certificated in all categories.
Compliance required as indicated, unless already accomplished.
To detect and prevent fatigue crack propagation that could cause failure of the main transmission input pinion assembly, accomplish the following:
(a) Within the next 50 hours additional time in service or 60 calendar days, whichever occurs first after the effective date of this AD, perform a magnetic particle inspection of all input pinions Part No. 269A5103-9, serial nos. listed in Table A, for cracks in accordance with the instructions of paragraph (d), Hughes Service Information Notice N-151.2, dated November 7, 1978. Reinspect these input pinions in accordance with paragraph (d) of the S.I.N. between 450 and 500 total hours time in service, if,at the time of the initial inspection, the assembly had less than 250 hours total time in service.
TABLE A
269A5103-9 Pinion Assembly Serial Nos. Affected by Paragraph (a)
164783
254498
164784
254500
164786
254501
164787
254502
164789
254504
164790
254506
164791
254508
164792
254509
164794
254510
164795
254511
164796
254512
164798
254513
164800
254514
164801
254515
164802
254516
164803
254517
164805
254518
164806
254519
164807
254520
164809
254521
164811
254522
164813
254524
164814
254525
164815
254526
164816
254527
164817
254528
164818
254529
164819
254532
254533
254534
254535
254536
254537
(b) Within 100 hours additional time in service after the effective date of this AD, perform a magnetic particle inspection of all other input pinions, Part No. 269A5103-9, for cracks, in accordance with the instructions of paragraph (d), Hughes Service Information Notice N-151.2, dated November 7, 1978.
(c) Prior to the installation of pinion assembly Part No. 269A5103-9 on any helicopter listed in this AD inspect per paragraph (d) of Hughes Service Information Notice No. N-151.2. Pinion assemblies of serial numbers listed in table A of paragraph (a) of this AD, which have less than 250 hours total time in service at time of inspection, must be reinspected per paragraph (d) of the above referenced S.I.N. after accumulating a total of 450 hours time in service and before accumulating 500 hours total time in service.
(d) Any assembly exhibiting crack indications as a result of those inspections performed in paragraphs (a), (b) and (c), above, must be removed from service and marked in a conspicuous manner to prevent inadvertent return to service.
NOTE 1: The agency recommends that all unserviceable pinion assemblies be returned to Hughes Helicopters Warranty and Repair Department. Reference: Paragraph d.2, Hughes Service InformationNotice No. N-151.2.
NOTE 2: Hughes Service Information Notice N-151.2, dated November 7, 1978, is the only version of the notice suitable for compliance with this AD.
(e) Equivalent inspection procedures and repairs may be used when approved by the Chief, Aircraft Engineering Division, FAA Western Region.
(f) Special flight permits may be issued in accordance with FAR's 21.197 and 21.199 to operate aircraft to a base for the accomplishment of inspections required by this AD.
This amendment becomes effective December 18, 1978.