| AD Number | 71-23-02 | Status | Active |
| Effective Date | November 26, 1971 | Issue Date | Not specified |
| Docket Number | Unknown | Amendment | 39-1328 |
| Product Type | ["Aircraft"] | Product Subtype | ["Large Airplane"] |
| CFR Part | --- - Part 39 | CFR Section | N/A |
| Citation | This information is not available. | ||
| Manufacturer(s) | Gulfstream Aerospace Corporation |
| Model(s) | G-159 |
71-23-02 GRUMMAN: Amdt. 39-1328. Applies to all Model G-159 airplanes.
Compliance required as indicated.
To detect cracking in the wing to fuselage attachment fittings at butt line 9 of Grumman Model G-159 airplanes, accomplish the following:
a. Within six months time in service after the effective date of this AD, unless already accomplished, inspect the wing to fuselage attachment fittings, P/Ns 159WM10064 and 159WM10065 (P/N 159WM10223 assembly), and P/N 159WM10045 at butt line 9 left and right, wing front beam for cracks, deformation, gaps or improper shimming in accordance with Grumman Gulfstream I Aircraft Service Change No. 190, dated June 28, 1971, or later FAA approved revision or in a manner approved by the Chief, Engineering and Manufacturing Branch, FAA Southern Region.
b. If cracks, deformation, gaps or improper shimming are found when conducting the inspection required by paragraph a., within 100 hours time in service after detection correct in accordance with Aircraft Service Change 190 or in a manner approved by the Chief, Engineering and Manufacturing Branch, FAA Southern Region.
c. Upon request of the operator, an FAA maintenance inspector, subject to prior approval of the Chief, Engineering and Manufacturing Branch, FAA Southern Region, may adjust the inspection time to coincide with inspections for wing corrosion required by AD 67-04- 01.
This amendment becomes effective November 26, 1971.