AD 78-24-01 R1 ACTIVE

78-24-01 R1 ROLLS-ROYCE LIMITED: Amendment 39-3345 as amended by Amendment 39-4641. Applies to Rolls-Royce DART engines and all variants of those engines listed below which have Rolls-Royce DART Modification 1525 incorporated (covered in Rolls-Royce DART Service Bulletin Da 72-351), as installed on, but not necessarily limited to the airplanes listed below.

DART Engine
Airplane
506, 510, 525, 530
Vickers Viscount Model 744, 745D, 810
511, 514, 528, 532
Fairchild F-27 & FH-227 series and Fokker F-27 series
526
Armstrong Whitworth AW-650 series 1
527
Handley Page Herald Type 300
529
Grumman G-159 and Fairchild F-27 and FH-227 series
532
Hawker Siddeley 748 series 2
542
General Dynamics Model 240 with STC No. SA1054WE installed (or Model 600), General Dynamics Model 340/440 with STC No. SA1096WE installed (or Model 640), and Nihon YS-11 and YS-11A series.

Compliance is required as indicated, unless already accomplished.

1. Compliance for all affected DART engines except the Mk. 530 is based on an effective date of December 11, 1978.

2. Compliance for the DART Mk. 530 engines is based on an effective date of May 12, 1983.

To prevent restricted movement of the engine power lever or the high pressure fuel shut-off valve control lever caused by control box mounting bolt failure, accomplish the following:

(a) Within the next 100 hours engine time in service or one month after the effective date of this AD, whichever occurs first, inspect the engine control box mounting bolts for integrity as specified in paragraph 5 of Rolls-Royce Service Bulletin Da 76-A17, Revision 1, dated April 4, 1978 (hereinafter referred to as the service bulletin) or an FAA-approved equivalent.

(b) If, during an inspection required by this AD, a bolt head is found to be detached or missing, before further flight replace both mounting bolts either -

(1) With new bolts of the same part number in accordance with paragraph 6 of the Service Bulletin or an FAA-approved equivalent and continue to inspect the bolts in accordance with paragraph (a) of this AD at intervals not to exceed 400 hours engine time in service or 4 months, whichever occurs first; or

(2) Install control box mounting bolts, in accordance with Rolls-Royce Service Bulletin Da 76-16, dated April 18, 1978, or an FAA-approved equivalent.

(c) If a detached or missing bolt head is not found during the inspection required by paragraph (a) of this AD, continue to inspect the bolts in accordance with that paragraph at intervals not to exceed 400 hours engine time in service or 4 months, whichever occurs first.

(d) The inspections required by paragraphs (b)(1) and (c) of this AD may be discontinued upon the installation of control box mounting bolts in accordance with Rolls-Royce Service Bulletin Da 76-16, dated April 18, 1978, or an FAA-approved equivalent.

(e) Upon request of an operator, the Manager, Aircraft Certification Staff, FAA, Europe, Africa, and Middle East Office, c/o American Embassy, Brussels, Belgium, may adjust the inspection interval specified in paragraphs (b) and (c) of this AD provided that such requests are made through an FAA maintenance inspector and the request contains substantiating data to justify the request for that operator.

Amendment 39-3345 became effective December 11, 1978.

This Amendment 39-4641 becomes effective May 12, 1983.