AD 67-25-05

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AD Number:
67-25-05
Document Type:
AD Final Rules
Docket Number:
Unknown
Subject Heading:
Airworthiness Directives; MCDONNELL DOUGLAS DC-8 and DC-9 Series Airplanes
Subject:
Thrust Reverser Autothrottle System
Status:
Current
Citation:
(Federal Register: September 6, 1967)
Citation Publish Date:
09/06/1967
Effective Date:
09/06/1967
Make:
The Boeing Company
Model:
DC-8-11 | DC-8-12 | DC-8-21 | DC-8-31 | DC-8-32 | DC-8-33 | DC-8-41 | DC-8-42 | DC-8-43 | DC-8-51 | ...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Superseded AD: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Superseded By: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: 67-25-05
CITATION:   [Federal Register: September 6, 1967]

PAGE NUMBER:  

DOCKET NUMBER:   Unknown

AMENDMENT:   39-470

AD NUMBER:   67-25-05

SUBJECT HEADING:   Airworthiness Directives; MCDONNELL DOUGLAS DC-8 and DC-9 Series Airplanes

ACTION:  

SUMMARY:  

DATES:   Effective September 6, 1967.

ADDRESSES:  

FOR FURTHER INFORMATION CONTACT:  

SUPPLEMENTARY INFORMATION:  

REGULATORY TEXT:  
67-25-05 MCDONNELL DOUGLAS: Amdt. 39-470, Part 39, Federal Register September 6, 1967. Applies to Model DC-8 Series Airplanes listed in Douglas Aircraft Division Service Bulletin No. 76-26, Revision No. 2, dated October 12, 1967, and Model DC-9 Series Airplanes listed in Douglas Aircraft Division Service Bulletin No. 76-15 dated July 28, 1967.

Compliance required as indicated.

To ensure proper stowage of the thrust reverser (piggy-back) levers, and to prevent possible deployment of the thrust reversers in the event of an electrical malfunction in the autothrottle computer that causes inadvertent movement of the throttles to the mechanical stop position, accomplish the following:

1. Unless electrical deactivation of the autothrottle system has already been accomplished in accordance with Paragraph (1) of AD 67-20-03, before further flight, deactivate the autothrottle system by pulling the autothrottle computer/amplifier circuit breaker and securing the circuit breaker in the open position.

2. Unless already accomplished in accordance with Paragraph (2) of AD 67-20-03, before further flight, install a placard on the throttle pedestal in clear view of the pilot stating "autothrottle inoperative".

3. Reactivation of the autothrottle system and removal of the placard specified in Paragraph 2 of this AD may be accomplished immediately following the installation of a spring on each throttle lever assembly in accordance with Douglas Aircraft Division Service Bulletin No. 76-26 dated July 31, 1967, or later FAA-approved revision (in the case of Model DC-8 Series Airplanes) or Douglas Aircraft Division Service Bulletin No. 76-15 dated July 28, 1967, or later FAA-approved revision (in the case of Model DC-9 Series Airplanes).

This supersedes Amendment 39-436 (issued telegraphically on June 10, 1967, and later published in 32 F.R. 8890), AD 67-20-03.

This Amendment effective September 6, 1967.


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