AD 67-22-03

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AD Number:
67-22-03
Document Type:
AD Final Rules
Docket Number:
Unknown
Subject Heading:
BOEING Model 727 Series Airplanes
Subject:
Main Gear Downlock Rod
Status:
Current
Citation:
This information is not available.
Citation Publish Date:
Effective Date:
07/24/1967
Make:
The Boeing Company
Model:
727-100 Series | 727-100C Series | 727-200 Series | 727-200F Series | 727 Series | 727C Series
Product Type:
Aircraft
Product Subtype:
Large 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Superseded AD: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Superseded By: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: 67-22-03
CITATION:   This information is not available.

PAGE NUMBER:  

DOCKET NUMBER:   Unknown

AMENDMENT:   39-445

AD NUMBER:   67-22-03

SUBJECT HEADING:   BOEING Model 727 Series Airplanes

ACTION:  

SUMMARY:  

DATES:   Effective July 24, 1967.

ADDRESSES:  

FOR FURTHER INFORMATION CONTACT:  

SUPPLEMENTARY INFORMATION:  

REGULATORY TEXT:  
67-22-03 BOEING: Amdt. No. 39-445, Part 39, Federal Register July 22, 1967. Applies to Model 727 Series Airplanes Listed in Boeing Service Bulletin No. 32-123(R-1 dated June 5, 1967).

Compliance required as indicated.

To detect visible wear and deformation of the main gear downlock rod and its attach bolts, to prevent wear and failure of the attach bolts caused by bolt rotation, and to prevent out-of- sequence operation of the door sequence valve following either rod failure or bolt failure, accomplish the following:

(a) For those airplanes having a main gear downlock rod assembly with 800 or more hours' time in service on the effective date of this AD, within the next 50 hours time in service, unless already accomplished within the previous 750 hours time in service, inspect each main gear downlock rod assembly for wear and deformation in accordance with Boeing telegraphic Service Bulletin No. 32-123 dated April 14, 1967, which is also repeated in the section entitled "I. PLANNING INFORMATION . . . C. DESCRIPTION . . . PART I . . ." of Boeing Service Bulletin 32-123(R-1 dated June 5, 1967).

(b) If wear or deformation is detected during the inspection conducted in accordance with Paragraph (a), unless already accomplished in accordance with Subparagraphs (1) or (2) of this Paragraph, replace the affected part(s) before further flight (except that the airplane may be flown with the gear down in accordance with FAR 21.197 to a base where the replacement or modification can be performed) by accomplishing (1) or (2) below:

(1) Replace the affected part(s) with a new part(s) of the same part number and comply with Subparagraph (2) of this Paragraph within 750 hours' time in service after this replacement; or

(2) Except as provided in this Subparagraph, modify the main gear downlock rod assembly(ies) incorporating the replacement part(s) in accordance with the section entitled "II. ACCOMPLISHMENT INSTRUCTIONS . . . PART II . . ." of Boeing Service Bulletin No. 32- 123(R-1 dated June 5, 1967) or later FAA-approved revision or by an equivalent method approved by the Chief, Aircraft Engineering Division, FAA Western Region. Replacement of the downlock rod must be accomplished by installing downlock rod P/N 69-33654-2 with metal-cal BAC27DLG14 installed or P/N 69-33654-3 with metal-cal BAC27DLG14 installed. Provisions of the Boeing Service Bulletin referenced herein applicable to modification of the downlock pushrod are not incorporated by reference in this AD and the modification of this assembly need not be accomplished hereunder.

(c) For all airplanes, within the next 800 hours' time in service after the effective date of this AD, unless already accomplished, modify each main gear downlock rod assembly in accordance with that section entitled "II. ACCOMPLISHMENT INSTRUCTIONS . . . PART II . . . " of Boeing Service Bulletin No. 32-123(R-1 dated June 5, 1967) and the main gear uplock assembly in accordance with that section entitled "II . ACCOMPLISHMENT INSTRUCTIONS . . . PART III . . ." of that Service Bulletin or later FAA-approved revision or by an equivalent method approved by the Chief, Aircraft Engineering Division, FAA Western Region. Replacement of the downlock rod must be accomplished by installing downlock rod P/N 69- 33654-2 with metal-cal BAC27DLG14 installed, or P/N 69-33654-3 with metal-cal BAC27DLG14 installed. Provisions of the Boeing Service Bulletin referenced herein applicable to a modification of the downlock pushrod are not incorporated by reference in this AD and the modification of this assembly need not be accomplished hereunder.

NOTE. - The absence of a requirement in Paragraphs (b) and (c) of this AD to modify the downlock pushrod assembly is not intended to discourage operators from incorporating this modification. It merely indicates that the FAA does not deem this modification necessary to correct the unsafe condition described in this AD.

(d) Operators who have not kept records of hours' time in service of individual main gear downlock rod assemblies shall substitute hours' time in service of the airplane in lieu thereof.

(e) Upon request of the operator, an FAA Maintenance Inspector, subject to prior approval of the Regional Director, FAA Western Region, may adjust the compliance times herein if the request contains substantiating data to justify the increase for the operator.

This amendment effective July 24, 1967.

FOOTER: