AD 78-07-02
final rule
Applicability
| Type | Manufacturer | Model | Details |
|---|---|---|---|
| aircraft | Textron Aviation Inc. | HS.125 Series 700A | Airworthiness Directives; HAWKER SIDDELEY AVIATION, LTD Model HS-125 Series 700A Airplanes |
Unsafe Condition
Cracking of the attachment lugs of the tee pieces, P/N 25-7PA41, mounted on the master refuel valve, and possible fuel leakage at the area of attachment.
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Required Actions
Within 10 days after the effective date, inspect attachment lugs for cracking and fuel leakage per Hawker Siddeley Alert Service Bulletin 28-A65 Part A. If cracking or leakage found, replace tee pieces with P/N 25-7PA125A before further flight. If no issues found, repeat inspections every three calendar months until replacement by August 1, 1978.
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Compliance Time
Within 10 days after the effective date of this AD, unless already accomplished
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Affected Aircraft
HAWKER SIDDELEY AVIATION, LTD Model HS-125 Series 700A airplanes, S/N NA0201 through NA0210
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Federal Register Abstract
Attachment Lugs to Refuel Valve
Applicability Source Text
Show captured applicability text from the source AD
AD Final Rules - DRS_78-07-02.html Copy URL Print/Save as PDF Document Versions Feedback Details AD Number: 78-07-02 Document Type: AD Final Rules Docket Number: Unknown Subject Heading: Airworthiness Directives; HAWKER SIDDELEY AVIATION, LTD Model HS-125 Series 700A Airplanes Subject: Attachment Lugs to Refuel Valve Status: Current Citation: This information is not available. Citation Publish Date: Effective Date: 04/14/1978 Make: Textron Aviation Inc. Model: HS.125 Series 700A Product Type: Aircraft Product Subtype: Large Airplane Affected AD: Superseded AD: Affected By: Superseded By: Service/Office: Office of Primary Responsibility: CFR Part Reference: Part 39 Comments: AIRWORTHINESS DIRECTIVES FINAL RULES: 78-07-02 CITATION: This information is not available. PAGE NUMBER: DOCKET NUMBER: Unknown AMENDMENT: 39-3168 AD NUMBER: 78-07-02 SUBJECT HEADING: Airworthiness Directives; HAWKER SIDDELEY AVIATION, LTD Model HS-125 Series 700A Airplanes ACTION: SUMMARY: DATES: Effective April 14, 1978. ADDRESSES: FOR FURTHER INFORMATION CONTACT: SUPPLEMENTARY INFORMATION: REGULATORY TEXT: 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. FOOTER:
Document Text
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AD Final Rules - DRS_78-07-02.html Copy URL Print/Save as PDF Document Versions Feedback Details AD Number: 78-07-02 Document Type: AD Final Rules Docket Number: Unknown Subject Heading: Airworthiness Directives; HAWKER SIDDELEY AVIATION, LTD Model HS-125 Series 700A Airplanes Subject: Attachment Lugs to Refuel Valve Status: Current Citation: This information is not available. Citation Publish Date: Effective Date: 04/14/1978 Make: Textron Aviation Inc. Model: HS.125 Series 700A 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: AIRWORTHINESS DIRECTIVES FINAL RULES: 78-07-02 CITATION: This information is not available. PAGE NUMBER: DOCKET NUMBER: Unknown AMENDMENT: 39-3168 AD NUMBER: 78-07-02 SUBJECT HEADING: Airworthiness Directives; HAWKER SIDDELEY AVIATION, LTD Model HS-125 Series 700A Airplanes ACTION: SUMMARY: DATES: Effective April 14, 1978. ADDRESSES: FOR FURTHER INFORMATION CONTACT: SUPPLEMENTARY INFORMATION: REGULATORY TEXT: 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. FOOTER:
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