AD 80-26-02

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AD Number:
80-26-02
Document Type:
AD Final Rules
Docket Number:
Unknown
Subject Heading:
Airworthiness Directives; Gates Model 23, 24, 25, 28 and 29 Series Airplanes
Subject:
AFCS/AFC-SS Pitch Function
Status:
Current
Citation:
This information is not available.
Citation Publish Date:
Effective Date:
01/15/1981
Make:
Learjet Inc.
Model:
23 | 24 | 24A | 24B | 24B-A | 24C | 24D | 24D-A | 24E | 24F | 24F-A | 25 | 25A | 25B | 25C | 25D | 2...Show more
Product Type:
Aircraft
Product Subtype:
Small/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Superseded AD: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Superseded By: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: 80-26-02
CITATION:   This information is not available.

PAGE NUMBER:  

DOCKET NUMBER:   Unknown

AMENDMENT:   39-4015

AD NUMBER:   80-26-02

SUBJECT HEADING:   Airworthiness Directives; Gates Model 23, 24, 25, 28 and 29 Series Airplanes

ACTION:  

SUMMARY:  

DATES:   Effective January 15, 1981.

ADDRESSES:  

FOR FURTHER INFORMATION CONTACT:  

SUPPLEMENTARY INFORMATION:  

REGULATORY TEXT:  
80-26-02 GATES LEARJET: Amendment 39-4015. Applies to 23, 24, 25, 28 and 29 series airplanes certificated in all categories.

COMPLIANCE: Required as indicated, unless previously accomplished in accordance with AD 80-22-10.

A) Before further flight:

1. Deactivate the pitch function of the FC-110 Automatic Flight Control System (AFCS) or Automatic Flight Control Stability System (AFC/SS), as indicated below, by pulling the AFCS Pitch DC Circuit Breaker to the off position, banding it to prevent use of this function and checking to assure this function is the only deactivated circuit or control:

SERIES	SERIAL NUMBERS	LOCATION
23	003 thru 014
015 thru 099	Pilot's Switch Panel
Pilot's Sub Panel
24	100 thru 139
(except 131, 132, & 134)
131, 132, & 134
140 thru 229

230 and up	Pilot's Sub Panel

Pilot's circuit breaker panel
Autopilot computer rack
(under pilot's seat)
Pilot's circuit breaker panel
25	003 thru 069
(except 032)
032
070 and up	Autopilot computer rack
(under pilot's seat)
Pilot's Sub Panel
Pilot's circuit breaker panel
28	001 and up	Pilot's circuit breaker panel
29	001 and up	Pilot's circuit breaker panel

2. Install a locally fabricated placard on or near the autopilot control head in clear view of the crew, using letters at least 3/32 inch high, which reads:

AUTOPILOT PITCH AXIS INOPERATIVE

OBSERVE APPROPRIATE AFM AIRSPEED LIMITATIONS
FOR INOPERATIVE AUTOPILOT
and operate the airplane in accordance with this placard.

3. Insert in the appropriate section of the existing Airplane Flight Manual (AFM) the FAA approved temporary Airplane Flight Manual Change dated October 22, 1980, pertaining to emergency procedures for pitch axis malfunction.

B) On or before April 1, 1981, accomplish all of the following at a Gates Learjet authorized service center holding appropriate FAA repair station ratings.

1. Visually inspect the elevator control system to assure that Pitch Axis Servo (D.C. Torquer), P/N 6600163-( ) is installed.

a) If installed, modify the airplane by incorporating autopilot pitch trim monitor test switch in accordance with Gates Learjet Airplane Modification Kit AMK 80- 16B, Change 2.

b) If not installed, modify the airplane by replacing the pitch servo actuator and capstan and incorporating autopilot pitch trim monitor test switch in accordance with Gates Learjet Airplane Modification Kits AMK 80-3, Change 4, and AMK 80-16B, Change 2, respectively.

2. Insert in the appropriate sections of the existing Airplane Flight Manual (AFM) the FAA approved temporary Airplane Flight Manual changes dated October 22, 1980, for autopilot trim monitor.

C) When paragraph B of this AD has been accomplished, the requirements of paragraphs A)1. and 2. of this AD are no longer applicable.

D) Airplanes may be flown in accordance with FAR 21.197 to a location where the requirements of this AD can be accomplished provided the autopilot is not operative during that flight.

E) Any equivalent method of compliance with this AD must be approved by the Chief, Aircraft Certification Program, FAA, Central Region, Room 238, Terminal Building No. 2299, Mid-Continent Airport, Wichita, Kansas 67209.

This AD supersedes AD 80-22-10.

This amendment becomes effective on January 15, 1981, to all persons except those to whom it has already been made effective by an airmail letter from the FAA dated December 11, 1980, and is identified as AD 80-26-02.

FOOTER: