AD 73-19-10 - Airworthiness Directives; Grumman Models G-164A and G-164B

Type	Manufacturer	Model	Details
aircraft	Allied Ag Cat Productions, Inc.	G-164A	Airworthiness Directives; Grumman Models G-164A and G-164B
aircraft	Allied Ag Cat Productions, Inc.	G-164B	Airworthiness Directives; Grumman Models G-164A and G-164B
aircraft	Allied Ag Cat Productions, Inc.	G-164B-15T	Airworthiness Directives; Grumman Models G-164A and G-164B
aircraft	Allied Ag Cat Productions, Inc.	G-164B-20T	Airworthiness Directives; Grumman Models G-164A and G-164B
aircraft	Allied Ag Cat Productions, Inc.	G-164B-34T	Airworthiness Directives; Grumman Models G-164A and G-164B
aircraft	Allied Ag Cat Productions, Inc.	G-164B (with 73 inch wing gap)	Airworthiness Directives; Grumman Models G-164A and G-164B

Unsafe Condition

Looseness, wear, or corrosion of the bolts attaching the Elevator Control Horn, P/N A 1841-3, to the left and right side elevators, P/N A1201-5A and A1201-4A, could result in loss of elevator control.

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Required Actions

Inspect bolts for standard torque rating, corrosion, and looseness within 25 hours in service or two weeks (whichever comes first), unless done in last 75 hours. Thereafter, repeat inspections every 100 hours or 60 days. Remove and inspect worn bolts; replace worn or corroded bolts with specified parts. Replace bolts every 1000 hours or one year. Discontinue inspections after installing Service Note No. 23 or equivalent.

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Compliance Time

Within the next 25 hours in service or two weeks, whichever occurs first, unless already accomplished within the last 75 hours in service

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Affected Aircraft

Grumman Models G-164A (S/N 1 through 1659A) and G-164B (S/N 1B through 56B), and all G-164A/B aircraft without elevator control horn modifications per Gulfstream American Service Note No. 23 or FAA-approved equivalent.

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Federal Register Abstract

Elevator Control Horn

Applicability Source Text

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AD Final Rules - DRS_73-19-10.html
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AD Number:
73-19-10
Document Type:
AD Final Rules
Docket Number:
Unknown
Subject Heading:
Airworthiness Directives; Grumman Models G-164A and G-164B
Subject:
Elevator Control Horn
Status:
Current
Citation:
This information is not available.
Citation Publish Date:
Effective Date:
08/29/1979
Make:
Allied Ag Cat Productions, Inc.
Model:
G-164A | G-164B | G-164B-15T | G-164B-20T | G-164B-34T | G-164B (with 73 inch wing gap)
Product Type:
Aircraft
Product Subtype:
Small Airplane
Affected AD:
Superseded AD:
Affected By:
Superseded By:
Service/Office:
Office of Primary Responsibility:
CFR Part Reference:
Part 39
Comments:
AIRWORTHINESS DIRECTIVES FINAL RULES: 73-19-10
CITATION: This information is not available.

PAGE NUMBER:

DOCKET NUMBER: Unknown

AMENDMENT: 39-3544

AD NUMBER: 73-19-10

SUBJECT HEADING: Airworthiness Directives; Grumman Models G-164A and G-164B

ACTION:

SUMMARY:

DATES: Effective August 29, 1979.

ADDRESSES:

FOR FURTHER INFORMATION CONTACT:

SUPPLEMENTARY INFORMATION:

REGULATORY TEXT: 73-19-10 GRUMMAN AIRCRAFT: Amendment 39-1719 as amended by Amendments 39-1757 and 39-1828 is further amended by Amendment 39-3544. Applies to G-164A S/N's 1 through 1659A and G-164B S/N's 1B through 56B certificated in all categories and all G-164A and G-164B aircraft in which the elevator control horn assembly and torque tube end fittings have not been modified per Gulfstream American Service Note No. 23 or FAA-approved equivalent.

Compliance required as indicated.

1. Within the next 25 hours in service or two weeks, whichever occurs first, unless already accomplished within the last 75 hours in service, inspect the bolts attaching the Elevator Control Horn, P/N A 1841-3, to the left and right side elevator, P/N A1201-5A and A1201-4A respectively, for a standard (ref. AC 43.13-1 Chg. 7) torque rating and for corrosion and thereafter at intervals not to exceed 100 hours in service or 60 days, whichever occurs first.

2. If any looseness is detected, the bolts must be removed and inspected for wear.

3. Replace any worn or corroded bolts with bolts of the same part number or NAS 1304-12 bolts or an equivalent as approved by the Chief, Engineering and Manufacturing Branch, FAA Eastern Region, except that the aircraft may be flown in accordance with FAR 21.197.

4. The bolts referenced in paragraph 3, must be replaced at intervals not exceeding 1000 hours in service or one year, whichever occurs first.

5. Upon submission of substantiating data by an owner or operator through an FAA Maintenance Inspector, the Chief, Engineering and Manufacturing Branch, FAA Eastern Region, may adjust the inspection intervals specified in this AD.

6. The repetitive inspection intervals required by paragraph 1 may be discontinued upon accomplishment of the modification in Grumman Gulfstream Service Note No. 23 dated 8/1/76, or an FAA-approved equivalent.

7. Any equivalent parts or alterations must be approved by the Chief, Engineering and Manufacturing Branch, FAA, Eastern Region.

(Grumman American Aviation Corporation AgCat Service Bulletin No. 51 pertains to this subject.)

Amendment 39-1719 was effective September 21, 1973.

Amendment 39-1757 was effective December 20, 1973.

Amendment 39-1828 was effective May 6, 1974.

This Amendment 39-3544 is effective August 29, 1979.

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