78-07-02 HAWKER SIDDELEY AVIATION, LTD: Amendment 39-3168. Applies to Model HS-125 Series 700A airplanes, S/N NA0201 through NA0210, certificated in all categories.
Compliance is required as indicated.
To detect cracking and possible failure of the attaching lugs of the tee pieces, P/N 25- 7PA41, that are mounted on the master refuel valve, accomplish the following:
(a) Within 10 days after the effective date of this AD, unless already accomplished, inspect the attachment lugs for cracking and the area of attachment to the main refuel valve for evidence of fuel leakage in accordance with Part A of the section entitled "Accomplishment Instructions" of Hawker Siddeley Aviation, Ltd. Alert Service Bulletin 28-A65, dated November 30, 1977 (service bulletin), or an FAA-approved equivalent.
(b) If during the inspection required by paragraph (a) of this AD, evidence of lug cracking or fuel leakage is found, before further flight, except that the airplane may be flown in accordance with FARs 21.197 and 21.199 to a base where the repairs can be performed, remove and destroy both tee pieces and replace with the improved parts, P/N 25-7PA125A, in accordance with Part B of the section entitled "Accomplishment Instructions" of the service bulletin, or an FAA-approved equivalent.
(c) If during the inspection required by paragraph (a) of this AD, no evidence of lug cracking or fuel leakage is found, continue to inspect the area in accordance with paragraph (a) of this AD, at intervals not to exceed three calendar months from the initial inspection, except that both tee pieces must be replaced in accordance with the installation instructions of paragraph (b) of this AD no later than August 1, 1978. Compliance with the repetitive inspection requirements of this paragraph may be terminated after the replacement required by this paragraph is accomplished.
This amendment becomes effective April 14, 1978.