AD 86-22-05

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AD Number:
86-22-05
Document Type:
AD Final Rules
Docket Number:
Unknown
Subject Heading:
Airworthiness Directives; Gates Learjet Model 23, 24, 25, 28, 29, 35, 36 and 55 Series Airplanes
Subject:
Flap Sector Mounting Brackets Inspection
Status:
Current
Citation:
This information is not available.
Citation Publish Date:
Effective Date:
11/10/1986
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Superseded AD: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Superseded By: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:
Updated RGL applicability to match AD applicability; CAR C-11-185
AIRWORTHINESS DIRECTIVES FINAL RULES: 86-22-05
CITATION:   This information is not available.

PAGE NUMBER:  

DOCKET NUMBER:   Unknown

AMENDMENT:   39-5448

AD NUMBER:   86-22-05

SUBJECT HEADING:   Airworthiness Directives; Gates Learjet Model 23, 24, 25, 28, 29, 35, 36 and 55 Series Airplanes

ACTION:  

SUMMARY:  

DATES:   Effective November 10, 1986.

ADDRESSES:  

FOR FURTHER INFORMATION CONTACT:  

SUPPLEMENTARY INFORMATION:  

REGULATORY TEXT:  
86-22-05 GATES LEARJET: Amendment 39-5448. Applies to the following Gates Learjet series airplanes, models/serial number listed below, certificated in any category.

MODEL	SERIAL NUMBER
23	003 thru 089 (if equipped with dual flap actuators)
23	090 thru 099
24	100 thru 357
25	003 thru 373
28	001 thru 005
29	001 thru 004
35	002 thru 545, 589 thru 598
36	001 thru 053, and 055
55	001 thru 121

Compliance required as indicated, unless previously accomplished.

To prevent impairment of flap operation, an asymmetric flap condition, false gear warning horn signals, or incorrect biasing of the stall warning system, due to flap sector upper mount bracket failures, accomplish the following:

A. Within the next 50 hours time-in-service after the effective date of this AD, inspect the flap sector upper mounting brackets for cracks, in accordance with instructions in Gates Learjet Corporation Airplane Modification Kit (AMK) 86-4 or 55-86-2, as applicable.

1. If cracks are found in either the left-hand or right-hand flap sector upper mounting brackets (Figure I of AMK), prior to further flight, replace both brackets and install stiffeners in accordance with the applicable AMK.

2. If cracks are not found in the flap sector upper mounting brackets, replace the brackets and install stiffeners in accordance with the applicable AMK within 100 hours time-in-service after the effective date of this AD.

B. If both flap sector upper mounting brackets have been previously replaced with steel brackets, compliance with this AD is not required.

C. Special flight permits may be issued in accordance with FAR 21.197 and 21.199 to operate airplanes to a base in order to comply with the requirements of this AD.

D. Alternate means of compliance with this AD, which provides an acceptable level of safety, may be used when approved by the Manager, Wichita Aircraft Certification Office, FAA, Central Region.

All persons affected by this directive who have not already received the appropriate service documents from the manufacturer may obtain copies upon request to Gates Learjet Corporation, P.O. Box 7707, Wichita, Kansas 67277. These documents may be examined at FAA, Northwest Mountain Region, 17900 Pacific Highway South, Seattle, Washington, or FAA, Central Region, Wichita Aircraft Certification Office, 1801 Airport Road, Room 100, Wichita, Kansas.

This supersedes AD 84-20-06, Amendment 39-4908.

This amendment becomes effective November 10, 1986.

FOOTER: