Commonwealth legislation

AD/HU 369/109 - Tail Rotor Gearbox Attachment

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Commonwealth

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legislative instrument

Plain English Summary

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This Airworthiness Directive requires operators of MD Helicopters Models 369D, 369E, 369F and 369FF modified by Aerometals STC SH5055NM or SH4801NM to inspect tail‑rotor gearbox attachment bolts, replace non‑conforming bolts with P/N NAS1304‑26, torque to 100–110 in‑lbs, check thread protrusion in the aft tailboom and add a washer if needed, and carry out repeated torque checks every 2–10 flight hours until no bolt movement occurs.

CASA states the action corrects an unsafe condition; the direct costs and labour fall to aircraft owners/operators, who must perform hands‑on and recurring maintenance under the AD.

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AIRWORTHINESS DIRECTIVE

View image in the official source

AIRWORTHINESS DIRECTIVE

For the reasons set out in the background section, the CASA delegate whose signature appears below issues the following Airworthiness Directive (AD) under subregulation 39.1 (1) of CAR 1998. The AD requires that the action set out in the requirement section (being action that the delegate considers necessary to correct the unsafe condition) be taken in relation to the aircraft or aeronautical product mentioned in the applicability section: (a) in the circumstances mentioned in the requirement section; and (b) in accordance with the instructions set out in the requirement section; and (c) at the time mentioned in the compliance section.

View image in the official source

McDonnell Douglas (Hughes) and Kawasaki 369 Series Helicopters

AD/HU 369/109 Tail Rotor Gearbox Attachm

AD/HU 369/109 Tail Rotor Gearbox Attachment 10/2002

Applicability: MD Helicopters Inc. Model 369D, 369E, 369F, and 369FF helicopters, modified in accordance with Aerometals Supplemental Type Certificate (STC) SH5055NM or SH4801NM.

Requirement: 1. Initial Inspection and bolt replacement:

Carry out an inspection of the tail rotor gearbox attachment bolts to determine the part number.

b. If the part number cannot be determined or if the bolt is not P/N NAS1304- 26, replace the bolt with bolt, P/N NAS1304-26.
c. Torque the bolt to 100-110 in- lbs and apply slippage mark.

d. Remove the tailboom control rod and determine the number of threads protruding from each nutplate on the internal surface of the aft tailboom frame casing, P/N 369D23503, as shown in Figure 1 of this Directive. At least one thread must protrude. If more than four threads protrude, add an additional washer, P/N AN960D416, under the bolt head.

e. Torque the bolt to 100-110 in- lbs and re apply slippage mark.

2. Repetitive Inspection:

Re check the attachment bolts for correct torque and re-torque if necessary.

b. Re apply slippage mark if re-torque is required.

Note: FAA AD 2002-13-05 Amdt 39-12793 refers.

Figure 1 — Inspection Location

Figure 1 – Inspection Location

View image in the official source

Compliance: 1. Initial Inspection and bolt replacement:

Within 25 flight hours from the effective date of this Directive.

Source text

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

AIRWORTHINESS DIRECTIVE AIRWORTHINESS DIRECTIVE

AIRWORTHINESS DIRECTIVE

McDonnell Douglas (Hughes) and Kawasaki 369 Series Helicopters

AD/HU 369/109 Tail Rotor Gearbox Attachm AD/HU 369/109 Tail Rotor Gearbox Attachment 10/2002

AD/HU 369/109 Tail Rotor Gearbox Attachment 10/2002

Applicability: MD Helicopters Inc. Model 369D, 369E, 369F, and 369FF helicopters, modified in accordance with Aerometals Supplemental Type Certificate (STC) SH5055NM or SH4801NM.

Requirement: 1. Initial Inspection and bolt replacement:

Carry out an inspection of the tail rotor gearbox attachment bolts to determine the part number.

b. If the part number cannot be determined or if the bolt is not P/N NAS1304- 26, replace the bolt with bolt, P/N NAS1304-26.
c. Torque the bolt to 100-110 in- lbs and apply slippage mark.

d. Remove the tailboom control rod and determine the number of threads protruding from each nutplate on the internal surface of the aft tailboom frame casing, P/N 369D23503, as shown in Figure 1 of this Directive. At least one thread must protrude. If more than four threads protrude, add an additional washer, P/N AN960D416, under the bolt head.

e. Torque the bolt to 100-110 in- lbs and re apply slippage mark.

2. Repetitive Inspection: 2. Repetitive Inspection:

2. Repetitive Inspection:

Re check the attachment bolts for correct torque and re-torque if necessary.

b. Re apply slippage mark if re-torque is required.

Note: FAA AD 2002-13-05 Amdt 39-12793 refers.

Figure 1 — Inspection Location Figure 1 — Inspection Location

Figure 1 – Inspection Location

Compliance: 1. Initial Inspection and bolt replacement:

Within 25 flight hours from the effective date of this Directive.