AD 73-14-07

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AD Number:
73-14-07
Document Type:
AD Final Rules
Docket Number:
Unknown
Subject Heading:
Airworthiness Directives; GRUMMAN AMERICAN AVIATION CORPORATION (GAAC) Models G-159 and G-1159 Airplanes
Subject:
Interior Lining Attachments
Status:
Current
Citation:
This information is not available.
Citation Publish Date:
Effective Date:
09/30/1974
Make:
Gulfstream Aerospace Corporation
Model:
G-1159 | G-159
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Superseded AD: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Superseded By: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:
Updated RGL applicability to match AD applicability; CAR C-11-185
AIRWORTHINESS DIRECTIVES FINAL RULES: 73-14-07
CITATION:   This information is not available.

PAGE NUMBER:  

DOCKET NUMBER:   Unknown

AMENDMENT:   39-1970

AD NUMBER:   73-14-07

SUBJECT HEADING:   Airworthiness Directives; GRUMMAN AMERICAN AVIATION CORPORATION (GAAC) Models G-159 and G-1159 Airplanes

ACTION:  

SUMMARY:  

DATES:   Effective September 30, 1974.

ADDRESSES:  

FOR FURTHER INFORMATION CONTACT:  

SUPPLEMENTARY INFORMATION:  

REGULATORY TEXT:   73-14-07 GRUMMAN AMERICAN AVIATION CORPORATION (GAAC): Amendment 39-1684 as amended by Amendment 39-1970. Applies to all G-159 airplanes, and to G-1159 airplanes, Serial Numbers 1 through 129 and 775, certificated in all categories.

Compliance required as indicated.

To detect fuselage aft section pressure dome cracks and prevent further cracking, accomplish the following:

(a) Within 200 hours time in service after the effective date of this AD or 90 days, whichever is the sooner, unless already accomplished, permanently remove all interior lining attachments other than fabric, carpeting, etc., from the fuselage aft section pressure dome assembly, Part No. 1159B21372 (G-1159), Part No. 159B10252 (G-159) and inspect for cracks in accordance with GAAC Customer Bulletins 167 (G-1159) or 240 (G-159), dated June 18, 1973 or later FAA approved revisions placing emphasis on those areas as defined in paragraph (b).

(b) Mark the exact location on the dome and record the geometric configuration of items removed in accordance with paragraph (a), noting the location of any discontinuities, particularly in radially running attachment strips. The FAA would appreciate receiving sketches and descriptive data of both the attachment location and geometric configurations. Sketches and descriptive data may be sent to the Chief, Engineering and Manufacturing Branch, Southern Region, P. O. Box 20636, Atlanta, Georgia 30320.

(c) For aircraft found to have no attachments on the dome, no further action is required.

(d) For aircraft having attachments, reinspect for cracks at intervals not to exceed 400 landings (G-1159) or 4000 landings (G-159), since the last inspection, in accordance with GAAC Customer Bulletins 167 (G-1159) or 240 (G-159).

(e) Repair all cracks detected during the inspections conducted in accordance with (a) or (d). Repair in accordance with GAAC Customer Bulletins 167 (G-1159) or 240 (G-159), before further flight.

(f) For the purpose of complying with paragraph (d) of this AD, subject to acceptance by the assigned FAA Maintenance Inspector, the number of landings may be determined by dividing each airplane's hour's time in service by the operator's fleet average time from takeoff to landing for the airplane type.

(g) Airplanes having cracked domes may be flown to a base for repairs in accordance with FAR 21.197 either:

(1) Unpressurized, or

(2) With limited pressurization with the concurrence of the FAA, Chief, Engineering and Manufacturing Branch, Southern Region.

Amendment 39-1684 became effective July 16, 1973.

This Amendment 39-1970 becomes effective September 30, 1974.

FOOTER: