AD 90-04-07

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AD Number:
90-04-07
Document Type:
AD Final Rules
Docket Number:
Unknown
Subject Heading:
COMMANDER (GULFSTREAM AEROSPACE, ROCKWELL) Models 112, 112B, 112TC, 112TCA, 114 and 114A Airplanes
Subject:
Wing Spars
Status:
Current
Citation:
This information is not available.
Citation Publish Date:
Effective Date:
03/09/1990
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Superseded AD: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Superseded By: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: 90-04-07
CITATION:   This information is not available.

PAGE NUMBER:  

DOCKET NUMBER:   Unknown

AMENDMENT:   39-6501

AD NUMBER:   90-04-07

SUBJECT HEADING:   COMMANDER (GULFSTREAM AEROSPACE, ROCKWELL) Models 112, 112B, 112TC, 112TCA, 114 and 114A Airplanes

ACTION:  

SUMMARY:  

DATES:   Effective March 9, 1990.

ADDRESSES:  

FOR FURTHER INFORMATION CONTACT:  

SUPPLEMENTARY INFORMATION:  

REGULATORY TEXT:  
90-04-07 COMMANDER (GULFSTREAM AEROSPACE, ROCKWELL): Amendment 39-6501.

Applicability: Models 112 and 112B [Serial Numbers (S/N) 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 in the body of the AD unless already accomplished.

To prevent failure of the forward wing spar in the area of the main landing gear side brace fitting attachment, accomplish the following:

(a) Within the next 100 hours time-in-service (TIS), after the effective date of this AD, inspect the left and right forward wing spars in the area of the main landing gear side brace fitting in accordance with the instructions specified in Part I of Gulfstream Aerospace Service Bulletin (SB) Nos. SB-112-71C or SB-114-22C both dated November 1988 as applicable.

(1) If cracks are found in the left or right forward wing spar as noted in paragraph 8d, Part I, of the above referenced service instructions, prior to further flight repair in accordance with Part II of Gulfstream Aerospace SB Nos. SB-112-71C or SB-114-22C both dated November 1988, as applicable.

(2) If cracks are found in the left or right forward wing spar as noted in paragraph 8a, Part I, of the above referenced service instructions, prior to further flight repair in accordance with Part IV of Gulfstream Aerospace SB Nos. SB-112-71C or SB-114-22C, both dated November 1988, as applicable.

(3) If cracks are found in the left or right forward wing spar as noted in paragraph 8b or 8e, Part I of the above referenced service instructions, prior to further flight repair in accordance with Part V of Gulfstream Aerospace SB Nos. SB-112-71C or SB-114-22C, both dated November 1988, as applicable.

(4) If cracks are found in the left or right forward wing spar, as noted in paragraph 8c, Part I of the above referenced service instructions, prior to further flight modify the airplane in accordance with instructions obtained from the Manager, Airplane Certification Office, FAA, at the address listed in paragraph (e) of this AD.

(5) If no cracks are found, reinspect the spars thereafter at intervals not to exceed 100 hours' TIS, and within the next 300 hours' TIS, modify the airplane in accordance with the instructions in Part II of Gulfstream Aerospace SB-112-71C or SB-114-22C, both dated November 1988 as applicable. The repetitive inspection may be discontinued once the airplane is so modified.

(b) If the airplane has been modified either in accordance with Part II of Gulfstream Aerospace SB No. SB-112-71, or Part II of SB No. SB-112-71A or Part II or Part V of SB No. SB-112-71B, repeat the inspections specified in paragraph (a) of this AD at intervals not to exceed 100 hours' TIS after the initial inspection, and within the next 300 hours' TIS modify the airplane in accordance with the instructions in Part III of Gulfstream Aerospace SB No. SB-112-71C. The repetitive inspections may be discontinued once the airplane is so modified.

(c) If the airplane has been modified either in accordance with Part II of Gulfstream Aerospace SB-114-22, Part II of SB-114-22A, or Part II or Part V of SB-114-22B, repeat the inspection specified in paragraph (a) of this AD at intervals not to exceed 100 hours TIS after the initial inspection and within the next 300 hours TIS, modify the airplane in accordance with the instructions in Part III of Gulfstream Aerospace SB No. SB-114-22C. The repetitive inspection may be discontinued once the airplane is so modified.

(d) Airplanes may be flown in accordance with FAR 21.197 to a location where the repair can be performed, provided the following conditions are met:

(1) Existing cracks have not propagated together (in the event there are cracks above each bracket attachment bolts) and the cracks have not propagated beyond the limits in the service bulletin (as noted in paragraph 8c, Part I of Accomplishment Instructions of Gulfstream Aerospace Service Bulletin Nos. SB-112-71C or SB-114-22C both dated November 1988, as applicable).

(2) The landing gear side brace and bracket are firmly attached such that proper extension and retraction of the gear will occur.

(3) Pilot only on board.

(4) Day VFR only, avoiding all rough weather possible, and with no intentional abrupt maneuvers.

(e) An alternate method of compliance or adjustment of the initial or repetitive compliance times, which provides an equivalent level of safety, may be approved by the Manager, Airplane Certification Office, ASW-150, FAA, Southwest Region, Fort Worth, Texas 76193-0150; Telephone (817) 624-5150.

NOTE: The request should be forwarded through an FAA Maintenance Inspector, who may add comments and send it to the Manager, Airplane Certification Office, Southwest Region.

All persons affected by this directive may obtain copies of the documents referred to herein upon request to Commander Aircraft Company, 7200 N.W. 63rd Street, Hangar 8, Wiley Post Airport, Bethany, Oklahoma 73008; or may examine these documents at the FAA, Office of the Assistant Chief Counsel, Room 1558, 601 East 12th Street, Kansas City, Missouri 64106.

This AD supersedes AD 87-14-03, Amendment 39-5671 (52 FR 26472).

This amendment (39-6501, AD 90-04-07) becomes effective on March 9, 1990.

FOOTER: