AD 77-07-01

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AD Number:
77-07-01
Document Type:
AD Final Rules
Docket Number:
Unknown
Subject Heading:
Airworthiness Directives; 77-07-01 Hughes Model 269 series Helicopters
Subject:
Clutch Actuator
Status:
Current
Citation:
This information is not available.
Citation Publish Date:
Effective Date:
04/04/1977
Make:
Schweizer Aircraft Corporation
Model:
269A | 269A-1 | 269B | 269C
Product Type:
Aircraft
Product Subtype:
Rotorcraft
Affected AD:
Superseded AD:
Affected By:
Superseded By:
Service/Office:
Office of Primary Responsibility:
CFR Part Reference:
Part 39
Comments:
Updated RGL applicability to match AD applicability; CAR C-11-185
AIRWORTHINESS DIRECTIVES FINAL RULES: 77-07-01
CITATION:   This information is not available.

PAGE NUMBER:  

DOCKET NUMBER:   Unknown

AMENDMENT:   39-2859

AD NUMBER:   77-07-01

SUBJECT HEADING:   Airworthiness Directives; 77-07-01 Hughes Model 269 series Helicopters

ACTION:  

SUMMARY:  

DATES:   Effective April 4, 1977.

ADDRESSES:  

FOR FURTHER INFORMATION CONTACT:  

SUPPLEMENTARY INFORMATION:  

REGULATORY TEXT:  
77-07-01 HUGHES HELICOPTERS: Amendment 39-2859. Applies to Hughes Model 269 series helicopters certificated in all categories, incorporating belt drive clutch linear actuator assemblies (hereinafter referred to as the "clutch actuator") P/N's DL1020-M81C (12V), DL1020-MS82C (24V), DL1020M48, and 269A4564.

Compliance required as indicated, unless already accomplished.

To detect possible cracks in belt drive clutch aluminum actuating shaft and actuator attachment fixed end fittings which can cause separation of the actuator attachment resulting in declutching of the main rotor, accomplish the following:

(a) Within 10 days after the effective date of this AD, prior to the first flight each day, conduct a visual check of the clutch actuator in accordance with the procedures described in Part II of Hughes Service Information Notice N-141.1 dated March 8, 1977, or later FAA approved revision. If any indication of cracks, corrosion or deformation is observed, perform a dye penetrant inspection of the suspect areas per Part III of above referenced service notice. Before further flight, replace any defective clutch actuator with a serviceable unit.

(b) The daily visual check required by paragraph (a) of this AD may be performed by the pilot.

(c) Within the next 100 hours time in service after the effective date of this AD, and at intervals not to exceed 100 hours time in service thereafter, perform a dye penetrant inspection of the clutch actuator per Part III of Hughes Service Information Notice N-141.1 dated March 8, 1977, or later FAA-approved revision. Before further flight, replace any defective clutch actuator with a serviceable part.

(d) When the clutch actuator is modified to, or replaced with, an actuator incorporating the stainless steel parts as described in Part I of Hughes Service Information Notice N-141.1, dated March 8, 1977, or later FAA approved revision, the visual checks required by paragraph (a) and the dye penetrant inspection required by paragraph (c) may be discontinued.

(e) Equivalent checks, inspections and modification procedures for the clutch actuator 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 helicopters to a base for accomplishment of the 100 hour inspections required by paragraph (c) of this AD.

(g) Record the daily visual check required by this AD in the rotorcraft maintenance record in accordance with FAR 91.173.

This amendment becomes effective April 4, 1977.

FOOTER: