Commonwealth legislation

AD/P68/13 Amdt 2 - Longitudinal Trim Indicator - Check and Modification

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Commonwealth

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legislative instrument

Plain English Summary

3/10 complexity

Requires operators of Partenavia P68/P68B aeroplanes whose longitudinal trim systems haven’t been modified to check the trim indicator before each flight and to fit specified modifications. The check sets the indicator to a zero position and verifies trim‑tab alignment; if misaligned, a new zero is established. Within 10 hours the approved replacement indicator or Partenavia SB No.41 modification must be installed; a transparent cover must be fitted within 100 hours. Operators bear compliance costs; pilots or licensed engineers may perform and certify checks.

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AD/P68/13 Amdt 2 - Longitudinal Trim Indicator - Check and Modification

COMMONWEALTH OF AUSTRALIA (Civil Aviation Regulations 1998), PART 39 - 105 CIVIL AVIATION SAFETY AUTHORITY

SCHEDULE OF AIRWORTHINESS DIRECTIVES

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Partenavia P68 Series Aeroplanes

AD/P68/13

Amdt 2

Longitudinal Trim Indicator - Check and Modification 7/79

Applicability: All models P68 and P68B aircraft with trim system and indicator not modified in accordance with schemes approved by the Secretary.

Requirement: 1. To check accuracy of longitudinal trim indicator until incorporation of Partenavia S/B No. 41.

(a) Set trim indicator to zero by rotating trim wheel.

(b) Position stabilator leading edge to zero reference point (rivet reference on fuselage left hand side) and check that trim tab is streamlined with stabilator. If this is the case, trim indicator is correct.

(c) If trim tab not streamlined with stabilator, maintaining leading edge to zero, rotate trim wheel until streamlined and consider this position of trim indicator as zero.

(d) Set take off trim with reference to new zero position.

(e) If reference rivet referred to in para. (b) above is not fitted consider zero reference point for stabilator to be 4.17 inches below upper longitudinal row of rivets.

2. Modify in accordance with Partenavia SB No. 41 and install trim indicator Type B P/N S.6041B or later equivalent.

3. Modify trim indicator by fitting an approved transparent cover or guard to prevent displacement of the pointer from the associated driving scroll.

Note: Registro Aeronautico Italiano AD No. 78-216/P68-19 refers to paras. 1 and 2 of this requirement.

Compliance: 1. Before each flight after 13 June 1979 until modified in accordance with paras. 2 and 3. For aircraft maintained in accordance with ANO 100.5.1, this Directive shall be entered on the maintenance release as maintenance required. The inspection may be performed by the pilot in command in which case certification is not required. In all other cases certification may be made on the maintenance release. This inspection may also be performed and certified by any Licensed Aircraft Maintenance Engineer.

2. Within 10 hours time in service after 13 June 1979.

3. Within 100 hours time in service after 13 June 1979.

Source text

Sourced from the Federal Register of Legislation (legislation.gov.au), CC BY 4.0.

1 AD/P68/13 Amdt 2 - Longitudinal Trim Indicator - Check and Modification