AD 75-15-03

AD Final Rules - DRS_75-15-03.html
Copy URL
Print/Save as PDF
Document Versions
 Feedback
Details
AD Number:
75-15-03
Document Type:
AD Final Rules
Docket Number:
Unknown
Subject Heading:
Airworthiness Directives; GRUMMAN AMERICAN AVIATION CORPORATION Model G-1159 Airplanes
Subject:
Operating Procedures
Status:
Current
Citation:
This information is not available.
Citation Publish Date:
Effective Date:
07/18/1975
Make:
Gulfstream Aerospace Corporation
Model:
G-1159
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Superseded AD: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Superseded By: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: 75-15-03
CITATION:   This information is not available.

PAGE NUMBER:  

DOCKET NUMBER:   Unknown

AMENDMENT:   39-2264

AD NUMBER:   75-15-03

SUBJECT HEADING:   Airworthiness Directives; GRUMMAN AMERICAN AVIATION CORPORATION Model G-1159 Airplanes

ACTION:  

SUMMARY:  

DATES:   Effective July 18, 1975.

ADDRESSES:  

FOR FURTHER INFORMATION CONTACT:  

SUPPLEMENTARY INFORMATION:  

REGULATORY TEXT:   75-15-03 GRUMMAN AMERICAN AVIATION CORPORATION: Amendment 39- 2264: Applies to Model G-1159 airplanes, Serial Number 1 through 164 and 775.

Compliance required as indicated:

(1) Flight Manual. The emergency procedure set forth in Section A is effective upon receipt of this AD and must be incorporated in the Grumman Gulfstream II ARM, unless previously incorporated by Grumman Interim Revision 16-5 dated July 2, 1975.

(2) Operating Limitation. The limitation set forth in Section B is effective upon receipt of this AD. It must be incorporated in the Grumman Gulfstream II AFM and remains effective until Grumman American Service Change 199 has been accomplished.

(3) Replacement of stall barrier filters. Compliance with the filter change outlined in Section C is required within two hundred (200) flight hours, or three months, after the effective date of this AD, whichever occurs first.

A. Emergency Procedures - Page 3-21 under Stall Barrier Malfunction, after item 5, add:
If the stick pusher actuates in flight and cannot be deactivated using the above procedures, it is probable that a hydraulic malfunction has occurred in the stall barrier system. In this event, it will be necessary to continue the flight with the stall barrier actuated. The following procedures are recommended:

1. Cruise.
With gear and flaps retracted, the airplane can be trimmed at airspeeds above approximately 200 knots. For maximum aircraft nose up trim, use the manual trim available beyond electric trim limit. The trim speed is reduced to a value below 200 knots when the flaps are extended.
The trim tab deflection necessary for a trimmed condition will increase drag and reduce range by a small but undetermined amount.

2. Approach and Landing.
a. The airplane CG may be adjusted as far aft as practicable, without exceeding the aft CG limit, by moving baggage and passengers rearward.

b. Burn off fuel as required for a maximum landing gross weight of 46,000 pounds.

c. With flaps 20 degrees, gear down, the airplane can be trimmed down to approximately 180 KIAS.

d. On final approach at 170 KIAS, lower gear and landing flaps and reduce speed to 165 KIAS. This will result in a stick force of approximately 12 lbs. pull. Maintain 165 KIAS on final approach. The approach at 165 kts. and 39 degrees flaps will result in an attitude with the nose lower than normal. All other check list procedures are unchanged.

e. At approximately 100 ft. above ground level slowly reduce the power to idle. The airplane should be flown onto the runway with a slight flare to assure that the nose wheel will not touch first. Plan to touch down at approximately 150 KIAS. Apply maximum reverse thrust and brake as necessary. Stick force during flare and touchdown will increase to about 30 lbs. Care should be taken not to flare high, thereby using more runway than necessary.

f. Due to the higher touchdown speed, the landing distances will be increased. The required runway length has not been determined, but landings have been made in less than 7,000 feet of runway by using maximum reverse thrust and light braking.

B. Limitations - Page 1-9. Under Stall Warning/Stall Barrier System add:
INTENTIONAL STALLS ARE PROHIBITED.

C. To prevent the stall barrier stick pusher from remaining energized after actuation, due to portions of the hydraulic filters becoming lodged in the stall barrier valves, accomplish the following: Replace the stall barrier hydraulic in-line filters and inspect and leak check the stall barrier valves and cylinder if the replaced filters are determined to be not intact upon removal, according to Grumman American Service Change 199, or in an equivalent manner approved by the Chief, Engineering and Manufacturing Branch, Southern Region, Atlanta, Georgia.

This amendment becomes effective July 18, 1975.

FOOTER: