AD/JT8D/35 Amdt 1 - Combustion Chamber Outer Case (Cth)

COMMONWEALTH OF AUSTRALIA (Civil Aviation Regulations 1998), PART 39 - 106 CIVIL AVIATION SAFETY AUTHORITY SCHEDULE OF AIRWORTHINESS DIRECTIVES

Pratt and Whitney Turbine Engines - JT8D Series

AD/JT8D/35 Amdt 1

Combustion Chamber Outer Case 1/99

Applicability: Pratt & Whitney JT8D-1, -1A, -1b, -7 ,-7A, -7B, -9, -11, -15, -15A, -17, -17A, -17R and -17AR turbofan engines, with combustion chamber outer case (CCOC) part numbers 490547, 5421555, 616315, 728829, 728829-001, 730413, 730413-001, 730414, 730414-001, 767197, 767279, or 767279-001 installed.

Requirement: For engines identified by serial number (S/N) in Table 1 of FAA AD 98-04-39, perform a one time borescope inspection of the CCOC rear flange in accordance with paragraph 2.A.(5) of Pratt and Whitney Alert Service Bulletin (ASB) No.A6202, Revision 1, dated 4 January, 1998.

Compliance: Unless previously accomplished:

1. For engines installed on McDonnell Douglas DC-9 series aircraft, inspect within 1,000 cycles in service (CIS) since the last ultrasonic inspection of the CCOC rear flange performed in accordance with AD AD/JT8D/22 Amdt 4 (FAA AD 96-23- 14), or within 100 CIS after the effective date of this AD, whichever occurs later.

2. For engines installed on Boeing 737 series aircraft, inspect within 1,500 CIS since the last ultrasonic inspection of the CCOC rear flange performed in accordance with AD/JT8D/22 Amdt 4 (FAA AD 96-23-14), or within 100 CIS after the effective date of this AD, whichever occurs later.

3. For engines installed on Boeing 727 series aircraft, inspect within 2,500 CIS since the last ultrasonic inspection of the CCOC rear flange performed in accordance with AD/JT8D/22 Amdt 4 (FAA AD 96-23-14), or within 100 CIS after the effective date of this AD, whichever occurs later.