AIRWORTHINESS DIRECTIVE

CAA-AD-057/2002R1

Supersedes CAA-AD-057/2002

Date of issue: June 24, 2002

ENGINE - AUXILIARY POWER UNIT (APU) (ATA 49) - INSPECTION OF TURBINE

Applicability: HONEYWELL INTERNATIONAL, INC. (former AlliedSignal Aerospace, Garett Auxiliary Power Division) GTCP85 series auxiliary power units (APU's) with model numbers listed in:

- AlliedSignal Aerospace Service Bulletin (SB) No. GTCP85-49-6919, Revision 2, dated March 23, 1996, or SB No. GTCP85-49-7140, dated January 12,1996,

or

- AlliedSignal Aerospace Alert Service Bulletin (ASB) No. GTCP85-49-A6831 Revision 1, dated January 15, 1995, having a one-piece cast turbine rotor with part numbers (P/N) 3842072-1, -2, -3 and P/N 3604604-1, -2, -3, P/N 3606982-1, P/N 968095-1 through -8, P/N 3842350-1 and P/N 3842360-1.

These APU's are installed on but not limited to Boeing 707 series, 727 series and 737 series, Lockheed L382 series, McDonnell Douglas DC-8-70 and DC-9/MD-80 series and British Aerospace BAC1-11 series aircraft.

Effective date: August 08, 2002

Compliance: Required as indicated in DGAC AD 2002-201(B) R1.

Remarks: The compliance of this AD must be recorded in Aircraft Logbook, where applicable the requirements of this AD must be integrated into Aircraft Technical Documentation. Address inquiries concerning this AD to: Civil Aviation Authority, Airworthiness Division, Ruzyne Airport, 160 08 Prague 6, Czech Republic, tel.: 420 2 33320922, fax: 420 2 20562270.

Ing. Pavel MATOUŠEK

Director of Airworthiness Division

CAA CZ

DGAC AD No.: 2002-201(B) R1

HONEYWELL INTERNATIONAL INC.

GTCP85 series auxiliary power unit

Exhaust (ATA 49)

1. APPLICABILITY:

This Airworthiness Directive (AD) is applicable to HONEYWELL INTERNATIONAL, INC. (former AlliedSignal Aerospace, Garett Auxiliary Power Division) GTCP85 series auxiliary power units (APU's) with model numbers listed in:

- AlliedSignal Aerospace Service Bulletin (SB) No. GTCP85-49-6919, Revision 2, dated March 23, 1996, or SB No. GTCP85-49-7140, dated January 12,1996,

or

- AlliedSignal Aerospace Alert Service Bulletin (ASB) No. GTCP85-49-A6831 Revision 1, dated January 15, 1995, having a one-piece cast turbine rotor with part numbers (P/N) 3842072-1, -2, -3 and P/N 3604604-1, -2, -3, P/N 3606982-1, P/N 968095-1 through -8, P/N 3842350-1 and P/N 3842360-1.

These APU's are installed on but not limited to Boeing 707 series, 727 series and 737 series, Lockheed L382 series, McDonnell Douglas DC-8-70 and DC-9/MD-80 series and British Aerospace BAC1-11 series aircraft.

2. REASON:

To improve the retention of axial expulsion of fragments with high energy in case of turbine rupture.

This Revision 1 extends the limit date of compliance.

3. COMPLIANCE:

Accomplish the following, unless already accomplished:

(a) For flight-operable APU's, within twenty four 24 months after the effective date of this Airworthiness Directive (AD), install an exhaust centerbody in accordance with AlliedSignal Aerospace ASB No. GTCP85-49-A6831, Revision 1, dated January 15, 1995 or SB No. GTCP85-49-6919, Revision 2, dated March 23,1996, as applicable.

(b) For APU's that are ground-operable only, within thirty six 36 months after the effective date of this AD, install an exhaust centerbody in accordance with AlliedSignal Aerospace SB No. GTCP85-49-6919, Revision 1, dated January 15,1995.

(c) For APU's installed on a Boeing 737 or British Aerospace BAC 1-11 series aircraft, within twenty four 24 months after the effective date of this AD, install an exhaust centerbody in accordance with AlliedSignal Aerospace SB No. GTCP85-49-7140, dated January 12, 1996.

REF.: S.B. AlliedSignal Aerospace No. GTCP85-49-6831, Revision 1, dated January 15, 1995,

S.B. AlliedSignal Aerospace No. GTCP85-49-6919, Revision 2, dated March 23, 1996,

S.B. AlliedSignal Aerospace No. GTCP85-49-7140, dated January 12, 1996.

This Revision 1 replaces original AD 2002-201(B) dated April 17, 2002.

EFFECTIVE DATE:

Original AD and Revision 1: APRIL 27, 2002