AD 67-29-04
Applicability
| Type | Manufacturer | Model | Details |
|---|---|---|---|
| aircraft | Allied Ag Cat Productions, Inc. | G-164 | Airworthiness Directives; Grumman Model G-164 Aircraft |
| aircraft | Allied Ag Cat Productions, Inc. | G-164A | Airworthiness Directives; Grumman Model G-164 Aircraft |
| aircraft | Allied Ag Cat Productions, Inc. | G-164B | Airworthiness Directives; Grumman Model G-164 Aircraft |
| aircraft | Allied Ag Cat Productions, Inc. | G-164B-15T | Airworthiness Directives; Grumman Model G-164 Aircraft |
| aircraft | Allied Ag Cat Productions, Inc. | G-164B-20T | Airworthiness Directives; Grumman Model G-164 Aircraft |
| aircraft | Allied Ag Cat Productions, Inc. | G-164B-34T | Airworthiness Directives; Grumman Model G-164 Aircraft |
| aircraft | Allied Ag Cat Productions, Inc. | G-164B (with 73 inch wing gap) | Airworthiness Directives; Grumman Model G-164 Aircraft |
| aircraft | Allied Ag Cat Productions, Inc. | G-164C | Airworthiness Directives; Grumman Model G-164 Aircraft |
| aircraft | Allied Ag Cat Productions, Inc. | G-164D | Airworthiness Directives; Grumman Model G-164 Aircraft |
| aircraft | Allied Ag Cat Productions, Inc. | G-164D (with 73 inch wing gap) | Airworthiness Directives; Grumman Model G-164 Aircraft |
Unsafe Condition
Loose rivets attaching the rod ends of the elevator forward pushrod assembly (P/N A1847-1 and A1847-3) may lead to failure of the assembly.
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Required Actions
Visually inspect the fore and aft ends of the pushrod assemblies for loose rivets or elongated holes. If found, remove rivets and repair by reaming holes and installing specified bolts, washers, and nuts. Replace the assembly if holes exceed .251 inches. Discontinue inspections after repair or approved equivalent.
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Compliance Time
Within the next 50 hours' time in service (for aircraft with ≥250 hours on effective date) or before 300 hours' total time (for <250 hours), then every 100 hours' time in service thereafter.
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Affected Aircraft
Grumman Model G-164 aircraft, serial numbers 1 through 400, with elevator forward pushrod assemblies P/N A1847-1 (serials 1-100) or A1847-3 (serials 101-400).
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Federal Register Abstract
Elevator Forward Pushrod
Applicability Source Text
Show captured applicability text from the source AD
AD Final Rules - DRS_67-29-04.html Copy URL Print/Save as PDF Document Versions Feedback Details AD Number: 67-29-04 Document Type: AD Final Rules Docket Number: Unknown Subject Heading: Airworthiness Directives; Grumman Model G-164 Aircraft Subject: Elevator Forward Pushrod Status: Current Citation: This information is not available. Citation Publish Date: Effective Date: 10/27/1967 Make: Allied Ag Cat Productions, Inc. Model: G-164 | G-164A | G-164B | G-164B-15T | G-164B-20T | G-164B-34T | G-164B (with 73 inch wing gap) | G-...Show more 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: 67-29-04 CITATION: This information is not available. PAGE NUMBER: DOCKET NUMBER: Unknown AMENDMENT: 39-497 AD NUMBER: 67-29-04 SUBJECT HEADING: Airworthiness Directives; Grumman Model G-164 Aircraft ACTION: SUMMARY: DATES: Effective October 27, 1967. ADDRESSES: FOR FURTHER INFORMATION CONTACT: SUPPLEMENTARY INFORMATION: REGULATORY TEXT: 67-29-04 GRUMMAN: Amdt. 39-497 Part 39 Federal Register October 25, 1967. Applies to Type G-164 aircraft, Serial Numbers 1 through 400. Compliance required as indicated. Gulfstream G-164 type aircraft have experienced loose rivets which attach the rod ends of the elevator forward pushrod assembly. To detect loose rivets on the assembly, P/N A1847-1 (Aircraft Serial Numbers 1 through 100) and P/N A1847-3 (Aircraft Serial Numbers 101 through 400), accomplish the following: (a) For aircraft with 250 or more hours' total time in service on the effective date of this AD comply with paragraph (c) within the next 50 hours' time in service, and thereafter at intervals not to exceed 100 hours' time in service from the last inspection. (b) For aircraft with less than 250 hours' total time in service on the effective date of this AD comply with paragraph (c) before the accumulation of 300 hours' total time in service, and thereafter at intervals not to exceed 100 hours' time in service from the last inspection. (c) Visually inspect the fore and aft ends of the pushrod assemblies to determine if there are loose rivets or elongated holes. (d) If loose rivets or elongated holes are found during the inspection required in paragraphs (a) or (b), before further flight, remove rivets (4 places) and repair as follows: (1) Line ream original rivet holes .190 + .001 inch. (4 places) (2) Install AN3-13A bolt, AN960-10 washer (under nut), and AN365-1032 nut. (4 places) If holes have elongated in excess of .191 inches, repair as follows: (3) Line ream original rivet holes .250 + .001 inch. (4 places) (4) Install AN4-14A bolt, AN960-416 washer (under nut), and AN365-428 nut. (4 places) If holes have been elongated in excess of .251 inch then replace the assembly. (e) The repetitive inspection required by paragraphs (a) and (b) of this AD may be discontinued upon accomplishment of the repair specified in paragraph (d) or equivalent repair approved by the Chief, Engineering & Manufacturing Branch, FAA Eastern Region. (f) Upon request, with substantiating data submitted through an FAA maintenance inspector, compliance time may be increased by the Chief, Engineering & Manufacturing Branch, FAA Eastern Region. This amendment effective October 27, 1967. FOOTER:
Document Text
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AD Final Rules - DRS_67-29-04.html Copy URL Print/Save as PDF Document Versions Feedback Details AD Number: 67-29-04 Document Type: AD Final Rules Docket Number: Unknown Subject Heading: Airworthiness Directives; Grumman Model G-164 Aircraft Subject: Elevator Forward Pushrod Status: Current Citation: This information is not available. Citation Publish Date: Effective Date: 10/27/1967 Make: Allied Ag Cat Productions, Inc. Model: G-164 | G-164A | G-164B | G-164B-15T | G-164B-20T | G-164B-34T | G-164B (with 73 inch wing gap) | G-...Show more 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: 67-29-04 CITATION: This information is not available. PAGE NUMBER: DOCKET NUMBER: Unknown AMENDMENT: 39-497 AD NUMBER: 67-29-04 SUBJECT HEADING: Airworthiness Directives; Grumman Model G-164 Aircraft ACTION: SUMMARY: DATES: Effective October 27, 1967. ADDRESSES: FOR FURTHER INFORMATION CONTACT: SUPPLEMENTARY INFORMATION: REGULATORY TEXT: 67-29-04 GRUMMAN: Amdt. 39-497 Part 39 Federal Register October 25, 1967. Applies to Type G-164 aircraft, Serial Numbers 1 through 400. Compliance required as indicated. Gulfstream G-164 type aircraft have experienced loose rivets which attach the rod ends of the elevator forward pushrod assembly. To detect loose rivets on the assembly, P/N A1847-1 (Aircraft Serial Numbers 1 through 100) and P/N A1847-3 (Aircraft Serial Numbers 101 through 400), accomplish the following: (a) For aircraft with 250 or more hours' total time in service on the effective date of this AD comply with paragraph (c) within the next 50 hours' time in service, and thereafter at intervals not to exceed 100 hours' time in service from the last inspection. (b) For aircraft with less than 250 hours' total time in service on the effective date of this AD comply with paragraph (c) before the accumulation of 300 hours' total time in service, and thereafter at intervals not to exceed 100 hours' time in service from the last inspection. (c) Visually inspect the fore and aft ends of the pushrod assemblies to determine if there are loose rivets or elongated holes. (d) If loose rivets or elongated holes are found during the inspection required in paragraphs (a) or (b), before further flight, remove rivets (4 places) and repair as follows: (1) Line ream original rivet holes .190 + .001 inch. (4 places) (2) Install AN3-13A bolt, AN960-10 washer (under nut), and AN365-1032 nut. (4 places) If holes have elongated in excess of .191 inches, repair as follows: (3) Line ream original rivet holes .250 + .001 inch. (4 places) (4) Install AN4-14A bolt, AN960-416 washer (under nut), and AN365-428 nut. (4 places) If holes have been elongated in excess of .251 inch then replace the assembly. (e) The repetitive inspection required by paragraphs (a) and (b) of this AD may be discontinued upon accomplishment of the repair specified in paragraph (d) or equivalent repair approved by the Chief, Engineering & Manufacturing Branch, FAA Eastern Region. (f) Upon request, with substantiating data submitted through an FAA maintenance inspector, compliance time may be increased by the Chief, Engineering & Manufacturing Branch, FAA Eastern Region. This amendment effective October 27, 1967. FOOTER:
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Retrieved: Apr 8, 2026
Rights: U.S. Government Public Domain
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Related Airworthiness Directives
89-18-02 R1
final ruleAirworthiness Directives; SCHWEIZER (GRUMMAN) All Model G-164 Series Airplanes
Unsafe Condition: Failure of the forward and aft elevator control system push-pull rods and end fittings due to corrosion and cracks.
82-13-06
final ruleAirworthiness Directives; SCHWEIZER (GULFSTREAM AMERICAN-GRUMMAN) Models G-164B, G-164C, and G164D Airplanes
Unsafe Condition: Elongation of the aileron cable attach holes and dislodgement of P/N A1450-281 bushings from the aileron bellcrank.
73-19-10
final ruleAirworthiness 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.
78-23-11
final ruleAirworthiness Directives; GRUMMAN G-164 S/N's 1 thru 400, G-164A S/N's 401 and up, G-164B S/N's 01B and up, G-164C S/N's 01C and up, certificated in all categories.
Unsafe Condition: Aileron balance cables (P/N A1860-101 and A1860-401) may contain broken wires at the wing root pulley, which could result in loss of aileron control.