Commonwealth legislation

AD/F28/59 Amdt 1 - Emergency Lighting

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legislative instrument

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This Airworthiness Directive requires all Fokker F28‑1000/2000/3000/4000 aeroplanes to have a three‑position emergency lighting switch (OFF/ON/ARMED) that resists accidental movement and to verify emergency lights operate when the AC generators fail, when switched on in the cockpit, and at the flight attendant station. Operators must either fit dedicated emergency‑lighting batteries or modify control circuitry so power switches to dedicated batteries before the aircraft battery drops below a measured minimum. The regulator sets the compliance deadline; operators pay for modifications and testing.

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AD/F28/59 Amdt 1 - Emergency Lighting

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

SCHEDULE OF AIRWORTHINESS DIRECTIVES

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Fokker F28 Series Aeroplanes

AD/F28/59

Amdt 1

Emergency Lighting 8/89

Applicability: All model F28-1000, 2000, 3000 and 4000 Series aeroplanes.

Requirement: 1. Ensure that a three position emergency lighting switch (ie OFF, ON and ARMED), which incorporates a means to ensure against inadvertent operation from the ON or ARMED positions is installed in the cockpit.

Note: Fokker SB F28/33-26 and F28/33/35 refers.

2. Verify that the emergency lighting system will illuminate:

(a) upon loss of normal electrical power (ie upon loss of AC generator power) when armed in the cockpit

(b) when turned on in the cockpit; and

(c) when turned on at the flight attendant station.

3. Accomplish one of the following:

(a) Modify the emergency lighting system so that when armed, and upon loss of normal electrical power, the emergency lighting system is powered by its own dedicated battery packs ; or

(b) Determine, by illumination measurement, the minimum aircraft battery voltage necessary to provide the required emergency lighting illumination levels. Modify the emergency lighting control circuitry to ensure that when armed and upon loss of normal aircraft power, the emergency lighting system power source is switched from the aircraft battery to the emergency lighting system dedicated battery packs PRIOR to the aircraft battery falling below this minimum voltage.

Note 1: For the purpose of this Directive, the emergency lighting system is considered to consist of the emergency lights, the evacuation lights, and where required the floor proximity escape path lighting.

Note 2: Normal electrical power is considered to be AC generator power. Note 3: Fokker S B F28/33/35 and FAA AD 88-25-07 refer.

Compliance: Prior to 23 February 1990.

Background: The FAA and Fokker have advised that early configuration F28 aircraft may not have a three position switch of the type required, and also that certain elements of the emergency lighting system may not illuminate automatically if normal aircraft power is lost. This condition could result in failure of the emergency lights to operate when required in an emergency.

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

SCHEDULE OF AIRWORTHINESS DIRECTIVES

Amendment 1 to this Directive is issued to clarify Requirement 2.

Source text

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

1 AD/F28/59 Amdt 1 - Emergency Lighting

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

SCHEDULE OF AIRWORTHINESS DIRECTIVES

Fokker F28 Series Aeroplanes

AD/F28/59

Amdt 1

Emergency Lighting 8/89

Applicability: All model F28-1000, 2000, 3000 and 4000 Series aeroplanes.

Note: Fokker SB F28/33-26 and F28/33/35 refers.

2. Verify that the emergency lighting system will illuminate:

(a) upon loss of normal electrical power (ie upon loss of AC generator power) when armed in the cockpit

(b) when turned on in the cockpit; and

(c) when turned on at the flight attendant station.

3. Accomplish one of the following:

(a) Modify the emergency lighting system so that when armed, and upon loss of normal electrical power, the emergency lighting system is powered by its own dedicated battery packs ; or

(b) Determine, by illumination measurement, the minimum aircraft battery voltage necessary to provide the required emergency lighting illumination levels. Modify the emergency lighting control circuitry to ensure that when armed and upon loss of normal aircraft power, the emergency lighting system power source is switched from the aircraft battery to the emergency lighting system dedicated battery packs PRIOR to the aircraft battery falling below this minimum voltage.

Note 2: Normal electrical power is considered to be AC generator power. Note 3: Fokker S B F28/33/35 and FAA AD 88-25-07 refer.

Compliance: Prior to 23 February 1990.

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

SCHEDULE OF AIRWORTHINESS DIRECTIVES