AD 88-05-06

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AD Number:
88-05-06
Document Type:
AD Final Rules
Docket Number:
Unknown
Subject Heading:
Airworthiness Directives; Gulfstream Model 112, 112B, 112TC, 112TCA, 114 and 114A Series Airplanes
Subject:
Inspect for Cracks
Status:
Current
Citation:
This information is not available.
Citation Publish Date:
Effective Date:
04/08/1988
Make:
Commander Aircraft Corporation
Model:
112 | 112B | 112TC | 112TCA | 114 | 114A
Product Type:
Aircraft
Product Subtype:
Small 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Superseded AD: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Superseded By: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: 88-05-06
CITATION:   This information is not available.

PAGE NUMBER:  

DOCKET NUMBER:   Unknown

AMENDMENT:   39-5864

AD NUMBER:   88-05-06

SUBJECT HEADING:   Airworthiness Directives; Gulfstream Model 112, 112B, 112TC, 112TCA, 114 and 114A Series Airplanes

ACTION:  

SUMMARY:  

DATES:   Effective April 8, 1988.

ADDRESSES:  

FOR FURTHER INFORMATION CONTACT:  

SUPPLEMENTARY INFORMATION:  

REGULATORY TEXT:  
88-05-06 GULFSTREAM AEROSPACE (ROCKWELL): Amendment 39-5864. Applies to Models 112 and 112B (S/N's 1 through 544 and 13000); 112TC and 112TCA (S/N's 13001 through 13309); and 114 and 114A (S/N's 14000 through 14540) airplanes certificated in any category.

Compliance: Required as indicated after the effective date of this AD, unless already accomplished.

To prevent failure of the vertical fin attachment fitting (P/N 43255-1) and the fuselage frame (P/N 43205- 1) in the area of F.S. 230.5, accomplish the following:

(a) Within the next 50 hours time-in-service (TIS), or upon the accumulation of 250 hours total TIS, whichever occurs later, inspect for cracks in fuselage frame (P/N 43205-1) and vertical fin attachment fitting (P/N 43255-1) in accordance with Part I of Gulfstream Aerospace Service Bulletin Nos. SB-112-72A or SB-114-23A, both dated August 31, 1987, as applicable.

(b) If cracks are found in the fuselage frame or vertical fin attachment fitting, prior to further flight repair in accordance with Part II of Gulfstream Aerospace Service Bulletin Nos. SB-112-72A or SB-114-23A, both dated August 31, 1987, as applicable.

(c) If no cracks are found, thereafter at intervals not to exceed 100 hours TIS accomplish the inspection as specified in paragraph (a) of this AD until the repair required by paragraph (b) of this AD is accomplished.

(d) The repetitive inspections specified in paragraph (c) of this AD may be discontinued when the airplane is modified as specified in paragraph (b) of this AD.

(e) The airplane may be flown in accordance with FAR 21.197 to a location where the repair can be performed.

(f) An equivalent method of compliance with this AD may be used if approved by the Manager, Airplane Certification Branch, DOT, FAA, Southwest Regional Office, Fort Worth, Texas 76193-0150, Telephone (817) 624-5150.

All persons affected by this directive may obtain copies of the documents referred to herein upon request to Gulfstream Aerospace Corporation, Wiley Post Airport, P.O. Box 22500, Oklahoma City, Oklahoma 73123; or may examine these documents at the FAA, Office of the Regional Counsel, Room 1558, 601 East 12th Street, Kansas City, Missouri 64106.

This amendment becomes effective on April 8, 1988.

FOOTER: