AD 64-12-01

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AD Number:
64-12-01
Document Type:
AD Final Rules
Docket Number:
Unknown
Subject Heading:
BOEING Models 707 and 720 Series Aircraft
Subject:
Throttle Control System
Status:
Current
Citation:
This information is not available.
Citation Publish Date:
Effective Date:
08/05/1964
Make:
The Boeing Company
Model:
707-100 Long Body | 707-100B Long Body | 707-100B Short Body | 707-200 | 707-300 Series | 707-300B S...Show more
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Superseded AD: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Superseded By: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: 64-12-01
CITATION:   This information is not available.

PAGE NUMBER:  

DOCKET NUMBER:   Unknown

AMENDMENT:  

AD NUMBER:   64-12-01

SUBJECT HEADING:   BOEING Models 707 and 720 Series Aircraft

ACTION:  

SUMMARY:  

DATES:   Effective August 5, 1964.

ADDRESSES:  

FOR FURTHER INFORMATION CONTACT:  

SUPPLEMENTARY INFORMATION:  

REGULATORY TEXT:  
64-12-01 BOEING: Amdt. 733 Part 507 Federal Register May 23, 1964. Applies to All Models 707 and 720 Series Aircraft Equipped With Pratt & Whitney JT3D-1, -3 or -3B Engines.

Compliance required as indicated.

To prevent inadvertent inflight reversals caused by snap action closing of the throttles to the idle position accomplish the following:

(a) Within 500 hours' time in service after the effective date of this AD, unless already accomplished, rerig the throttle control system in accordance with the Boeing Maintenance Manual dated April 1964, or Boeing Service Letter 6-7161-4-6112 dated September 30, 1963.

(b) Within 2,500 hours' time in service after the effective date of this AD, unless already accomplished, accomplish the following:

(1) Inspect the strut mounted bracket in accordance with Service Bulletin No. 1659 (R-1) to determine what bracket assembly part number is installed on each airplane reverser installation.

(2) Modify the cam rocker arm, P/N 69-10814, in accordance with Boeing Service Bulletin No. 1931 or an FAA approved equivalent. This modification shall be accomplished prior to or concurrent with the thrust reverser directional control valve cam modification required in paragraph (b)(3). Installation of a modified cam with an unmodified cam rocker arm is prohibited because of operational incompatibility and subsequent possible interference.

(3) Modify the thrust reverser directional control valve cam assembly, P/N's 65- 18225-1, -2, -3 or 65-27438-3, in accordance with Boeing Service Bulletin No. 1931 or an FAA approved equivalent. Models 707 and 720 fan engine airplanes may have any one of or a combination of the thrust reverser directional control valve cam assembly part numbers listed above. Interchangeability of these directional control valve cam assemblies with strut mounted brackets and fan reverser followup cams are as follows:

(i) Cam assemblies P/N's 65-18225-2, -3, and 65-27438-3, all reworked in accordance with Service Bulletin No. 1931 must be used with bracket assembly P/N's 65-11882-2 or -4 or P/N 65-11882 reworked in accordance with Service Bulletin No. 1659(R-1).

(ii) Cam assembly P/N 65-18225-1 reworked in accordance with Service Bulletin No. 1931 must be used with bracket P/N's 65-11882, -2, or -4 or P/N 65-11882 reworked in accordance with Service Bulletin No. 1659(R-1).

(iii) Cam assemblies P/N 65-27438-3 reworked per Service Bulletin 1931 shall be used with fan reverser followup cams P/N's 65-27437-1 or 66-16560-1.

(iv) Cam assemblies P/N's 65-18225-1, -2 or -3 reworked per Service Bulletin 1931 shall be used with fan reverser followup cam P/N's 65-11826-3 or -7.

(c) Approval of any equivalent means shall be processed through the Aircraft Engineering Division, FAA Western Region, Los Angeles, California.

(Boeing Service Bulletins Nos. 1659(R-1) and 1931 cover this subject.)

This directive effective June 26, 1964.

Revised August 5, 1964.

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