CAP 562 Civil Aircraft Airworthiness Information and Procedures

APPENDIX 1-2 The Consignment by Air of Aircraft Spares as Cargo which

meet the Criteria Of 'Dangerous Goods'

1 Introduction

This appendix supersedes Airworthiness Notice No. 12 Appendix 59 Issue 1 dated 23

October 1998. This Appendix highlights the dangers associated with the improper air
transport of aircraft spares and replacement items, meeting the criteria of 'Dangerous
Goods'.

2 Background

Dangerous Goods are defined as articles or substances which are capable of posing
a risk to health, safety, property or the environment when transported by air and
which are classified according to the ICAO's Technical Instructions for the Safe
Transport of Dangerous Goods by Air. Personnel may be more familiar with the field
document produced by IATA, the Dangerous Goods Regulations. These reflect the
Technical Instructions and as such are a comprehensive set of rules to ensure the
perfectly safe practice of transporting dangerous goods.

3 Airworthiness and Operational Considerations

3.1 Aircraft components are installed in accordance with prescribed airworthiness

specifications such that they do not present a hazard to the aircraft or its occupants.
However, this safeguard may not apply to such items if they are removed and shipped
as cargo. This was graphically demonstrated by an accident in 1996 in which 110
passengers and crew were killed. This accident occurred following an intense in-flight
cargo hold fire caused by the improper carriage as cargo of a number of chemical
oxygen generators. These generators had previously been safely installed in aircraft
passenger service units (PSUs) but had been removed and shipped in a manner such
that they presented an extreme danger when transported as cargo. As a result of this
accident, chemical oxygen generators are now forbidden for carriage on passenger
aircraft as cargo and may only be carried on a cargo aircraft subject to, amongst other
things, very stringent packing requirements which are specified in the Technical
Instructions.
3.2 With the extensive publicity surrounding this accident and the subsequent remedial
actions, the dangers associated with chemical oxygen generators are now relatively
well known, although incidents involving these items continue to be reported.
However, apart from chemical oxygen generators, which are also found in Personal
Breathing Equipment (PBE), it is essential to be alert to the possibility that dangerous
goods can also be found in various other types of aircraft spares e.g. compressed
gases (fire extinguishers, oxygen cylinders, life saving appliances), explosives (engine
fire extinguishers, flares), flammable liquids (fuel line components, paint), etc., all of
which, when sent as spares, may only be transported as cargo in accordance with the
provisions of the Technical Instructions.
3.3 Anyone consigning dangerous goods for carriage by air has a responsibility under the
Air Navigation (Dangerous Goods) Regulations, to ensure that any dangerous goods
are prepared for carriage in accordance with the Technical Instructions. It is also a
requirement of the Technical Instructions that all staff with duties associated with
dangerous goods receive training commensurate with their responsibilities. Any
failure to comply with the requirements of the Air Navigation (Dangerous Goods)

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CAP 562 Civil Aircraft Airworthiness Information and Procedures

Regulations is a criminal offence, the penalty for which reflects the potentially very
serious consequence of any breach.
3.4 In summary, aircraft spares and replacement items (i.e. components and equipment)
meeting the criteria of dangerous goods, may only be transported by air as cargo in
accordance with the ICAO Technical Instructions (or IATA Dangerous Goods
Regulations). It is imperative that all personnel with responsibilities either directly or
indirectly associated with the transport of these items are aware of this fact. It is also
essential that measures are put in place to ensure that dangerous goods can never
be offered for air transport when not fully meeting the requirements.

APPENDIX 1-3 Foreign Object Damage to Aircraft and Engines

1 Introduction

This Appendix supersedes Airworthiness Notice No. 12 Appendix 68, Issue 2, dated
28 September 2005.

2 Background

2.1 The CAA continues to receive reports of damage to aircraft and engines caused by
foreign objects (FOD). Foreign object damage presents a serious airworthiness threat
to any aircraft not to mention the economic impact on the operator. In extreme cases,
FOD can lead to an accident and loss of life. FOD damage to airframes and engines
can be extremely expensive to rectify and may result in the aircraft being removed
from revenue service for significant periods of time. There are numerous reports on
record of FOD damage to engines (in particular rotating assemblies), nose and main
landing gear assemblies and aircraft structure.
2.2 Recent audits of airports, including a 10-month study at one major UK international
airport, have revealed that a continuing threat exists from varying amounts of FOD
present on aircraft maintenance areas and airport-manoeuvring areas, including
stands, aircraft taxiways and runways. The study showed the aircraft themselves as
the main cause of FOD on the runway and this poses the highest immediate risk.
Here, parts of aircraft become detached or tools and equipment, inadvertently left in
the aircraft fall out during take off or landing. The largest item found on a runway was
a wheel chock but metal panels and honeycomb structure were also amongst the
larger items. The FOD found on taxiways and stands came mainly from airport
vehicles and the equipment they tow such as baggage trolleys, steps, cargo
equipment etc. The size and shape of some of this FOD makes it likely to cause tyre
damage and subsequent tyre burst. The cleaning of aircraft cabins and the transfer of
waste from cabin to airside rubbish containers is also seen to be a common source
of FOD in the stand areas. Other typical FOD consists of such items as oil cans,
spanners, pliers, engineers torches, suitcase items (both internal and external),
mobile radios, aircraft catering equipment, cutlery, landing gear ground lock pins,
thrust reverser lock-out pins and broken parts of ground servicing equipment/
vehicles.
2.3 Smaller items could be ingested by an engine. In many cases, FOD damage to engine
rotating assemblies has led to vibration leading to air turn-backs, diversions and
subsequent engine replacement. Boroscope inspections of engines following reports
of engine surging very often reveal internal damage to the engine – such damage can
of course be very expensive to repair. Typically, damage to the aircraft can range from

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damage to horizontal stabilizer leading edges to pressure hull penetration by objects

thrown up from the runway, to varying degrees of damage to landing gear assemblies
and main-planes. It is not unusual for tyre treads (nose and main) to detach as a result
of FOD damage during take-off and landing causing damage to the fuselage, wings,
trailing edge flaps, lift dumpers, engine intakes and compressors. Tyre tread
detachment often occurs within several takeoffs / landings of an earlier penetration
of the tread by an item of FOD. It is known that in some cases aircraft have been lost
due to FOD damage to tyre assemblies and has lead to significant loss of life.

3 Operator, Maintenance and Ground Handling Organisation

Recommended Best Practice
3.1 Aircraft operators should not allow their aircraft to be positioned onto arrival/
departure stands unless satisfied that the stand is clean and free from FOD.
Operators should consider the implementation of procedures whereby its staff or
contracted ground handling personnel check parking stand cleanliness standards prior
to aircraft arrival on stand and again following its departure from stand prior to being
occupied by the next aircraft.
3.2 Aircraft operators should ensure that the topic of FOD is placed as a standing agenda
item on all airport users committee meetings that it attends and internal airline safety
meetings as necessary in order that the topic is adequately covered and remains
visible at all times. It is suggested that operators may wish to nominate an individual
with responsibility for the implementation of the airline’s policy in this area.
3.3 Aircraft operators and maintenance organisations should implement procedures that
would preclude tools, inspection equipment or other service items being left in the
aircraft installations following routine or unscheduled maintenance (e.g. undercarriage
bays, engine intakes) and/or at the airport areas where the work took place.
3.4 Airport authorities and maintenance organisations should ensure that adequate
cleaning/sweeping programmes are in place for those aircraft ramp and maintenance
areas under their control. Airport authorities and maintenance organisations should
provide sufficient numbers of strategically positioned FOD bins that should be readily
visible and placarded as to their use.
3.5 Aircraft operators, maintenance and ground handling organisations should include
FOD in their induction and continuation training programmes. For example, the
practice of putting chocks and other loose equipment on aircraft tugs in positions
from where it can fall unnoticed should be discouraged.
3.6 Aircraft operators and maintenance organisations should consider the inclusion of
FOD into their ramp area audits ensuring that where problems exist that the persons
responsible are notified without delay. Where FOD is a persistent problem and no
effort is made to rectify the problem, consideration should be given to reporting
matters to the CAA’s Aerodrome Standards Department.
3.7 Aircraft operators should ensure that contracted aircraft cleaning and ground handling
organisations are made aware of its policies regarding the prevention of FOD during
cabin cleaning and ground handling operations. This should include the condition of
vehicles and the quality of repairs made to them.
3.8 Some aircraft types are permitted to back off the stand using high power reverse
thrust settings. Operators of such types are reminded that these operations can be
susceptible to FOD. Operators carrying out such operations should ensure that they
are only carried out in accordance with manufacturer’s recommendations and from
clean, contamination free ramp areas.
REMEMBER THE ONLY ACCEPTABLE FOD IS NO FOD!

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APPENDIX 4–1 Ambiguous Information

1 Introduction

This Appendix supersedes Airworthiness Notice No. 12 Appendix No. 25 Issue 1

dated 22 January 1979 which was originally issued as a result of ambiguities in
maintenance documents.

2 Background

2.1 During an investigation into an accident, it became apparent that some information
contained in the maintenance documents for the aircraft was in fact ambiguous and
had led to confusion in the minds of the staff concerned.
2.2 Whilst care is taken by all concerned, it is not always possible to avoid error or
ambiguity, and in consequence, instructions may occasionally be found to be
inaccurate or not clear as to their meaning.

3 Airworthiness Considerations

EASA Part 145.45 (c) and AMC 145.A.45 (c) require that a Part 145 approved
organisation has procedures in their Maintenance Organisation Exposition detailing
how any maintenance data errors and ambiguities should be reported to the author of
the data. A record of these communications should be kept until the error or
ambiguity has been addressed by the author of such data. Any person or organisation
not subject to the Part-145 regulation who identifies ambiguities or errors in approved
documents of any kind (Maintenance Schedules, Flight Manuals, etc.) should inform
the organisation responsible for the publication of the source data so that any
uncertainties which could affect airworthiness can be corrected.

APPENDIX 4–2 The Use and Interpretation of Unfamiliar Units

1 Introduction

This Appendix supersedes Airworthiness Notice No. 12 Appendix No. 28 Issue 1

dated 2 October 1981.

2 Background

CAA publications have for some years included units from the SI system alongside
the previous Imperial Units.

3 Airworthiness Considerations

3.1 The use of SI Units (Système International) within the United Kingdom is dealt with
in a publication 'Changing to the Metric System' issued by the National Physical
Laboratory and obtainable from The Stationery Office, and in BSI 5775, obtainable
from the British Standards Institute.

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3.2 The names of the various units, the symbols used for them, and the methods to be
used for presentation of those symbols in technical documents, are dealt with in both
documents.
3.3 The correct understanding of technical information and instructions can depend upon
the symbols used and their method of presentation. Hence, it is important that where
safety may depend on the correct interpretation of symbols, product support
departments and others involved in the dissemination of safety documents should
consider whether any doubt could exist. Where this is the case, potentially
ambiguous notation should be explained and illustrated by examples, where
appropriate.
3.4 Where the users of such documents are in any doubt, they should make a careful
check using reference documents such as those mentioned in paragraph 2.
3.5 In one case, a degree of uncertainty evidently arose when an area was expressed
using the symbol 'mm2' to express the concept of a square millimetre. This usage is
similar to that, in Imperial Units, of 'in2' to represent square inches (or 'sq in').
3.6 Figure 1 illustrates the unit of area of one square inch, or 1 in2 (cross-hatched). An area
of two square inches is shown, occupying twice the area. A two inch square, i.e. a
square of sides 2 inches, clearly occupies four times the area or 4 in2.

Figure 1

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3.7 Figure 2 similarly illustrates the unit of area of one square millimetre, or 1 mm2, and
as an example, an area of 50 square millimetres (i.e. 50 mm2, in that case a rectangle
5 mm by 10 mm). Once again this is quite different from the area of a 50 mm square,
which is 50 times greater.

Figure 2

3.8 This Appendix is issued for information and action by all concerned. Reference should
also be made to CAAIP Leaflet 11–22, Appendix 4–1 Ambiguous Information.

APPENDIX 4-3 Responsibilities of Engineers who carry out and Certify

Maintenance on Aircraft

1 Introduction

This Appendix supersedes Airworthiness Notice No. 12 Appendix 52 Issue 1 dated 19

July 1996 which was issued as a result of an enquiry into a serious incident which
occurred to an aircraft on the first flight following maintenance being carried out.

2 Background

The CAA wishes to remind Licensed Aircraft Maintenance Engineers and Authorised
Certifying Staff employed by Part-145 Approved Maintenance Organisations of their
responsibilities when issuing Certificates of Release to Service after maintenance.

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3 Certification Responsibilities

CAP 562 Leaflet 15-2 specifies the certification responsibilities for Type Rated
Licensed Aircraft Maintenance Engineers in relation to Articles 14 and 16 of the Air
Navigation Order 2005 (as amended). Paragraph 1.7 includes the following
information relative to the certification of maintenance:
‘A Certificate of Release to Service shall only be issued for a particular overhaul,
repair, replacement, modification, mandatory inspection or scheduled maintenance
inspection when the signatory is (signatories are) satisfied that the work has been
properly carried out and accurately recorded, having due regard to the use of:
a) up-to-date instructions including manuals, drawings, specifications, CAA
mandatory modifications/inspections and company procedures,
b) recommended tooling and test equipment which is currently calibrated where
applicable, and
c) a working environment appropriate to the work being carried out.’

4 Part-145 requirements apply to Authorised Certifying Staff employed by Part-145

Approved Maintenance Organisations who should be fully conversant with their
content, particularly the following extracts from the requirements which are pertinent
when carrying out and certifying maintenance:
4.1 Part 145.A.40 Equipment, tools and material
(See AMC 145.A.40)
a) The Part-145 approved maintenance organisation must have the necessary
equipment, tools and material to perform the approved scope of work.
NOTE: The associated AMC 145.A.40 (a) states 'Once the applicant for approval has
determined the intended scope of approval for consideration by the competent
authority, it will be necessary to show that all tools and equipment as specified in
the maintenance data can be made available when needed. All such tools and
equipment that require to be controlled in terms of servicing or calibration by virtue
of being necessary to measure specified dimensions and torque figures etc, should
be clearly identified and listed in a control register including any personal tools and
equipment that the organisation agrees can be used.'
4.2 Part 145.A.45 Airworthiness data
(See AMC 145.A.45)
a) The Part-145 approved maintenance organisation must be in receipt of all
necessary airworthiness data from the CAA, the aircraft/aircraft component design
organisation and any other approved design organisation, as appropriate to support
the work performed.
NOTE: AMC 145.A.30(e) Personnel Requirements. Paragraph 3 states 'To assist in the
assessment of competence, job descriptions are recommended for each job role in
the organisation. Basically, the assessment should establish that ....... -
d. Supervisors are able to ensure that all required maintenance tasks are carried out
and where not completed or where it is evident that a particular maintenance task
cannot be carried out to the maintenance data then such problems will be reported
to the 145.A.30(c) person for appropriate action. In addition, for those supervisors
who also carry out maintenance tasks, that they understand such tasks should not
be undertaken when incompatible with their management responsibilities.'

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4.3 Part 145.A.50 Certification of maintenance

(See AMC 145.A.50)
a) A certificate of release to service must be issued by appropriately authorised staff
on behalf of the Part-145 approved maintenance organisation when satisfied that
all required maintenance has been properly carried out by the Part-145 approved
maintenance organisation in accordance with the procedures specified in the Part
145.A.70 maintenance organisation exposition
4.4 Part 145.A.65 Safety and quality policy, Maintenance procedures and quality
system (See AMC 145.A.65)
a) The Part-145 approved maintenance organisation must establish procedures
acceptable to the CAA to ensure good maintenance practices and compliance with
all relevant requirements in this Part-145 such that aircraft and aircraft components
may be released to service in accordance with Part 145.A.50. Part 145.A.65
Paragraph (b)2 states 'The maintenance procedures established or to be
established by the organisation under this paragraph shall cover all aspects of
carrying out the maintenance activity, including the provision and control of
specialised services and lay down the standards to which the organisation intends
to work.'

5 The CAA consider that:

a) the responsibilities defined in both CAP 562 Leaflet 15-2 and Part-145 are
fundamentally equivalent and require work to be carried out to specified
maintenance instructions using recommended tooling and, when working in
approved maintenance organisations, in accordance with established procedures.
b) it is important to adhere to publications which provide instructions for continued
airworthiness together with company procedures which lay down the standards
for work carried out by Licensed Aircraft Maintenance Engineers, Authorised
Certifying Staff and Approved Maintenance Organisations. The privileges of
Licensed Aircraft Maintenance Engineers and Authorised Certifying Staff do not
include authority to deviate from such instructions or procedures.

APPENDIX 4-4 CAA Approval and Continued Airworthiness of the L-3

Communications Model F-800 Digital Flight Data Recorder
(Previously issued as AN 12, Appendix 63)

1 The CAA has been made aware that the Federal Aviation Administration (FAA) has
cancelled the Technical Standard Order (TSO) Authorisation for the L-3
Communications (Formerly known as LORAL Data Systems and Fairchild Aviation
Recorders, Sarasota, Florida 34232 USA) Digital Flight Data Recorder Model F-800.
This followed reports of several performance problems related to this type of
magnetic tape recorder. Some of these problems have caused difficulties for air
accident investigators when replays are conducted. The CAA has conducted its own
review of the service experience of the Model F-800 and has drawn similar
conclusions to those of the FAA.

2 As a result, the CAA declared the BCAR Equipment Approval Number AR 515
obsolescent. This means that the L-3 Communications Model F-800 Digital Flight
Data Recorder may not be newly installed on any UK registered aircraft for the
purposes of compliance with any mandatory carriage requirement. (Mandatory
carriage requirements are specified in the UK Air Navigation Order 2005 (as

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CAP 562 Civil Aircraft Airworthiness Information and Procedures

amended), or the Joint Aviation Requirements JAR-OPS, as appropriate.) However,

where already installed in a UK registered aircraft, the Model F-800 may continue to
be used, serviced and repaired, as necessary, until such time as the aircraft operator
chooses to replace it with another model of flight data recorder. In such cases the
Model F-800 installation will still be accepted as being compliant with the mandatory
carriage requirements.

3 Following the FAA TSO approval cancellation, L-3 Communications no longer

manufacture the Model F-800 but they are still providing continued airworthiness
support and are continuing to manufacture spares. However, in their Field Service
Bulletin No. F800 DFR FSB033, dated 1 April 2000, L-3 Communications have
announced that the magnetic tape supply used to manufacture the F800 DFR reel and
tape assemblies is being depleted. There is a finite and very limited supply of the DFR
tape.

4 The CAA recommends that aircraft operators and maintenance organisations take
these, and any other relevant obsolescence issues into account when reviewing their
flight recorder maintenance schedules. Maintainers should ensure that approved
replacement parts are acquired to meet future demand.

5 In addition, it should be noted that solid state Flight Data Recorder (FDR) technology
meeting the standards listed below has become widely available. One of the
advantages of this technology is that solid state equipment can be designed to be
operated under an on-condition maintenance regime.
• EUROCAE ED55
• EUROCAE ED112
• FAA TSO C124a
• JAA TSO C124a
• EASA ETSO C124a*
• EASA ETSO 2c124b (which supersedes *).

APPENDIX 4-5 Retention of Records – Post Incident and Accident

Investigations

1 Introduction

This Appendix supersedes Airworthiness Notice No. 12 Appendix 61, Issue 4, dated
29 September 2006.

2 During a number of recent accident investigations, the retention of aircraft/engine

records was found to be inadequate and incomplete. Considerable difficulty was
experienced during these investigations in tracing the full details of the maintenance
and repair action taken during the most recent history of the aircraft.

3 Aircraft operators, owners and maintenance organisations are reminded of their

responsibility to retain adequate, complete and detailed maintenance, repair and
modification records as specified in the following paragraphs for the periods listed
according to the relevant requirements.

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4 The requirements for retention of aircraft continuing airworthiness records (necessary

for demonstrating the adequacy of continuing airworthiness arrangements) for EASA
aircraft operated for both Commercial Air Transport and Non-Commercial Air
Transport are identified in EASA Part-M, M.A.305 and M.A.306.

5 For non-EASA aircraft, it is the responsibility of the operator to retain the records for
the period specified in the Air Navigation Order 2005 (as amended) (currently two
years after the aircraft has been destroyed or has been permanently withdrawn from
use).

6 EASA Part-145 approved maintenance organisations need to retain a copy of all

detailed maintenance records for two years from the date the aircraft or component
was released from the Part-145 organisation (Part-145.A.55). This assumes, however,
that the Part-145 organisation has provided the operator with copies of all of the
relevant documentation for their records (such as work packs and work sheets etc.).
Where reference to a work pack is made in a Certificate for Release to Service, this
information then forms a part of the permanent records of that aircraft. If the Part-
145 organisation is contracted to keep records on behalf of the Operator then the
retention period will be two years after the aircraft has been destroyed or has been
permanently withdrawn from use as required by EASA Part-M.A. 305 and M.A. 306.

7 The requirements for retention of records for all other aircraft registered in the United
Kingdom are defined in the Air Navigation Order 2005 (as amended). Article 22
requires the Operator of the aircraft to keep Aircraft, Engine and Propeller Log Books,
and ANO Article 15 requires a Technical Log where applicable. The Log Books must
include particulars as specified in ANO Schedule 6, for example:
• Particulars of all maintenance work carried out on the aircraft or its equipment; and
• Particulars of any overhauls, repairs, replacements and modifications relating to
the aircraft or its equipment.
It should be noted that for some aircraft types, where there are components that have
assigned overhaul, service life or ultimate life limits the use of individual log cards for
the components are often used. These form part of an aircraft's records. The
retention period is the same as that specified in the Air Navigation Order 2005 (as
amended) or Part M as appropriate unless the cards have been returned with the
component to an overhaul facility.
Also note that any document, such as a work pack, which is incorporated by a cross-
reference entered in a log book, shall be part of the log book and it is the duty of the
Operator to retain the above records. Every log book shall be preserved by the
Operator of the aircraft until two years after the aircraft has been destroyed or has
been permanently withdrawn from use.

8 For Part-M, Subpart F approved Maintenance Organisations (associated with EASA

aircraft of 5700 kg and below, and single-engine helicopters) the records retention
period is currently three years from the date of release of the aircraft/components.

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Aircraft, Engine, Propeller and Component Records Retention: Summary

of Requirements

Minimum Records
Applicable Entity Requirement Reference
Retention Period

Part-145 Approved Part-145.55 At least 2 years from aircraft

Maintenance Organisation or component release date.
All details of maintenance
work necessary for If Part-145 Approved
issuance of certificate of Maintenance Organisation
release to service is contracted to retain
records by Operator, then
requirements for Part-
M.A.305 and M.A 306
apply, i.e. at least 2 years
after the aircraft or
component has been
permanently withdrawn
from service.

Part-M, Subpart F Part-M, M.A.614 At least 3 years from aircraft

Maintenance Organisation or aircraft/component
for EASA aircraft < or = Records necessary to prove release dates.
5700 kg, and single-engine all requirements have been
helicopters. met for issuance of
certificate of release to
service.

Owner/Operator of EASA Part-M, M.A.305 At least 2 years after the

Aircraft aircraft or component has
Continuing Airworthiness been permanently
Records withdrawn from service.

Part-M, M.A.306 At least 3 years after the

date of last entry
Technical Log (Where
applicable)

Operator of Non-EASA ANO Article 22 At least 2 years after the

aircraft (Annex II aircraft) aircraft or component has
Log Books (Aircraft, engine been permanently
and propeller) including withdrawn from service.
details of all maintenance,
overhauls, repairs,
replacements and
modifications carried out.

ANO Article 15 At least 2 years after the

aircraft or component has
Technical Log (Where been permanently
applicable) withdrawn from service.

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APPENDIX 5–1 Aged Components – Permit To Fly Aircraft

1 Introduction
This Appendix supersedes Airworthiness Notice No. 12 Appendix No. 34 Issue 2
dated 10 December 1986 which was issued following the investigation involving two
fatal accidents.

2 Background
A split diaphragm in the fuel pump of a Hercules engine and a corroded capsule of a
Gipsy Queen engine resulted in over-rich operation, both of which led to fatal
accidents. Power loss in another Hercules engine was probably caused by failure of
the insulation in a magneto. In each case extended calendar time between overhauls
and low utilisation may have been factors contributing to the deterioration.

3 Airworthiness Considerations
These are just three examples of malfunctions associated with the deterioration of
aged components in aircraft which are not maintained to an approved Maintenance
Schedule.
3.1 It is recommended, therefore, that components including materials where
deterioration due to age may occur, be inspected periodically. If signs of ageing,
hardening, or deterioration of rubber components, insulation materials, or corrosion
of metallic components are found, such components should be assessed and
renewed as necessary.
3.2 Original servicing schedules and procedures should be used wherever available with
due regard to the low utilisation of the aircraft. Operators are advised to consider
additional periodic inspections for all components and equipment which may be
affected by calendar time deterioration.

APPENDIX 5-2 Planning and Recording of non-scheduled Maintenance Tasks

1 Introduction

This Appendix supersedes Airworthiness Notice No. 12 Appendix No. 53 Issue 2

dated 30 September 1996 which was issued as a result of an enquiry into a serious
incident where incorrect and incomplete documentation was cited as a contributory
factor.

2 Background

The CAA wishes to remind all Operators, Certifying Engineers and Part-145 Approved
Maintenance Organisations of the need to prepare complete documentation prior to
the work being accomplished which clearly and accurately defines the non-scheduled
maintenance task(s) to be undertaken.

3 Airworthiness Considerations

Non-scheduled maintenance tasks can arise from scheduled maintenance

inspections or from defects recorded on operational aircraft. Non-scheduled

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maintenance tasks require a certificate of release to service be issued when all

maintenance relating to the task(s) has been completed.

4 Part 145.A.50(a), Certification of Maintenance, specifies 'A certificate of release to

service shall be issued by appropriately authorised staff on behalf of the organisation
when it has been verified that all maintenance ordered has been properly carried out
by the organisation in accordance with the procedures specified in 145.A.70 ...' It
therefore follows that the documents recording a non-scheduled maintenance task
must contain sufficient detail to enable the Certifying Engineer to determine that it
has been properly carried out by the organisation to enable him to issue a certificate
of release to service.

5 Maintenance tasks on aircraft vary in complexity and task cards raised for scheduled
maintenance reflect the level of complexity of the specific task. Control of these
complex tasks by maintenance personnel at shop floor level is normally simplified by
breaking each task down into a number of discrete steps with the provision for
appropriately authorised staff to sign/stamp when each step is completed. It is equally
important that non-scheduled maintenance tasks are similarly broken down into steps
to provide a detailed record of maintenance which is to be carried out and certified on
completion of each step or group of steps as they occur. Engineers are reminded of
the need for a full and comprehensive hand-over of work outstanding at shift changes.
NOTE: The CAA endorses the use of stage sheets which is good maintenance
practice as it enables personnel to record work to be carried out and provide
a record of the accomplishment of that work. Human factors studies in
engineering repeatedly show that the use of properly prepared stage sheets
when carrying out tasks considerably reduces the opportunity for
maintenance errors occurring.

APPENDIX 9–1 Ground Handling of Transport Aircraft

1 Introduction

This Appendix supersedes Airworthiness Notice No. 12 Appendix No. 18 Issue 1

dated 25 March 1977 which was originally issued to alert operators to the possibility
of a nose undercarriage failure in older types of aircraft during towing or push-back.

2 Background

There have been a number of occurrences involving nose undercarriage failure in the
older types of transport aircraft. These failures can be attributed, at least in part, to
loads induced during towing or push-back. Such loads have, in a number of cases,
resulted in the initiation of fatigue cracking, leading to subsequent failure under
operational loads.

3 Operating Considerations

3.1 Aircraft manufacturers specify suitable ground handling equipment, compatible with
the aircraft type, designed to avoid overloading, e.g. employing shear pins, which fail
at predetermined loads. However, it is possible to induce overloading by rapid
acceleration or braking, especially when employing large, powerful tractors to move

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the smaller types of aircraft. Furthermore, certain manoeuvres now commonly

employed, such as 'push-back' were not anticipated in the design of some older
aircraft.
3.2 Operators, especially those of the older types of aircraft, should ensure that the
correct ground handling equipment is always employed, that it is regularly and
adequately maintained, and that particular care is taken when using large powerful
tractors. Operators should also check with the manufacturer that their ground
handling procedures are compatible with the aircraft design.

APPENDIX 9-2 Aircraft Towing and Limitations

1 Introduction
1.1 This Appendix supersedes Airworthiness Notice No. 12, Appendix 70, Issue 1, dated
29 March 2006.

2 The CAA has been made aware of an incident in which an aircraft sustained structural
damage to the nose landing gear to fuselage mounting structure. It is believed that a
causal factor in this incident was that ground movement of the aircraft had been
undertaken using a hydraulically powered "towbarless" tug and not ensuring that this
was accomplished in accordance with the appropriate aircraft manufacturers'
instructions.

3 Aircraft manufacturers are required, in accordance with type Certification

Specifications, to publish Servicing Information. This servicing information must
contain, amongst other things, equipment required for servicing and towing
instructions and limitations.

4 Operators/owners and their maintenance and ground service providers are obliged to
comply with all the applicable aircraft manufacturers' instructions in order to ensure
the continued airworthiness of their aircraft.

5 By publication of this Appendix to Leaflet 11-22 the CAA would like to remind all
operators/owners that when their aircraft is towed by either themselves or a third
party they take the necessary steps to make sure the above obligations and practices
are adhered to.

APPENDIX 10-1 Control of the Use of Pitot Head and Static Vent Blanking
Covers
(Previously issued as AN 12, Appendix 57)

1 A serious incident involving a large commercial air transport aircraft occurred due to
the loss of half the primary reference flight instruments readings during take-off. The
reason for the loss was that pitot head blanking covers had not been removed before
flight.

2 The aircraft had been subjected to an overnight stop during which time all four of the
pitot head blanking covers were installed.

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3 The engineering and flight crew pre-departure check resulted in two of the four pitot
head covers being removed. The remaining two were missed, and not removed.

4 The pre-departure check was carried out at night and in rain, thus weather and
darkness contributed to the incident.

5 Good maintenance practices dictate that the installation of blanks or covers requires
a clear, unambiguous entry in the Technical Log that the aircraft is no longer airworthy
as a result of that installation. This practice would assist line maintenance personnel
in ensuring the removal of such items before aircraft acceptance by the flight crew.

6 Hence procedures should be instituted by operators and maintenance organisations

to control the installation and removal of blanking covers for pitot and static probes.
6.1 Open entries should be made, at the time of installation of such blanking cover(s), in
the Technical Log, identifying which blanking cover(s) have been installed.
6.2 Upon removal of the blanking cover(s) the open entry in the Technical Log should be
appropriately annotated and certified.
6.3 Emphasising the use of ‘temporary’ blanking covers, such as masking tape on
operational aircraft is not acceptable as it can also result in the type of incident
described herein.

7 The reliance of warning or attention getting 'flags' attached to blanks or covers is not,
in itself, sufficient to insure their identification and removal before flight. This is
especially true when completing aircraft pre-departure checks in darkness or adverse
weather conditions.
NOTE: Operators should consider application of similar practises in respect of other
commonly used blanking or locking devices such as landing gear locking pins, intake
blanks, external control locks etc.

APPENDIX 11–1 Aircraft Markings and Placards

1 Introduction

This Appendix supersedes Airworthiness Notice No. 12 Appendix No. 45 Issue 1

dated 12 November 1990 which was originally issued to highlight the importance of
the legibility and position of markings and placards.

2 Background

Resulting from an enquiry into an accident, the CAA wishes to draw attention to the
importance of the correct positioning and legibility of aircraft markings and placards,
especially those relating to emergency situations.

3 Maintenance Considerations

3.1 Operators and maintenance organisations are reminded that all placards, markings,
operating instructions, especially those which pertain to emergency equipment and
exits, should be inspected periodically to ensure legibility, complement and location.

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3.2 The Light Aircraft Maintenance Schedule (LAMS) requires the inspection of placards
in Section 7 at Check A, 50 hour, 150 hour and Annual check periods. Where other
maintenance schedules do not refer to this subject, action should be taken to revise
the schedule as appropriate.

APPENDIX 12–1 Fluids Used in Aircraft

1 Introduction

This Appendix supersedes Airworthiness Notice No. 12 Appendix No. 5 Issue 2 dated
1 April 1985 which was originally issued to warn of the possibility of accidents
occurring as a result of incorrect fluids being used.

2 Background

Aircraft are replenished with many fluids during their operation. Accidents and
incidents continue to draw attention to the need to avoid the use of incorrect fluids.

3 Airworthiness Considerations

3.1 In addition to the obvious risks associated with damage to systems and failure to
function if they are filled with the incorrect fluids, there is a risk that the damage may
not become apparent until the aircraft is in flight with possible catastrophic results.
Use of incorrect fluids may result from:
a) Incorrectly establishing the fluid required.
b) Incorrect identification of the fluid available.
3.2 Identifying fluids
3.2.1 To avoid incorrectly establishing the fluid required, the following should be observed:
a) Filling points are required to be clearly marked to indicate the fluid to be used and
these markings should be maintained in a legible condition.
b) Where it is critical that the fluid to be used is to a particular specification(s), the
marking may either indicate the specification(s) or provide sufficient information to
permit servicing staff to determine which specification is applicable. Where neither
is indicated, operators should ensure that the servicing staff, whether their own or
an agent’s, follow a procedure that will ensure that the required specification is
correctly established.
3.2.2 To avoid incorrect identification of the fluid available, the following should be
observed:
a) Containers and dispensing apparatus should be clearly marked with the identity of
the fluid.
b) If a 'used' container has to be re-used to contain a fluid other than that
corresponding to the original identification, then the identification should be
removed or permanently obscured and the identification of the new fluid should be
clearly marked on the container.
c) Fluids should only be obtained from sources whose integrity in respect of the
contents of a container is beyond doubt.

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3.3 Additional hazards apply when servicing fluids are carried on board aircraft and used
to replenish systems when transiting overseas stations. Where foreign handling
agents are used, language problems may compound potential problems. Operators
should ensure that:
a) Ideally all fluids are in sealed manufacturer’s cans.
b) Purpose-designed stowages are provided for each fluid type, arranged where
possible, to give physical separation between different types.
c) The stowages are clearly identified as to the contents and that these markings
correspond to those on the aircraft filler points.
d) Procedures on use and replacement are contained in an appropriate Company
manual.
e) Scheduled checks are made to check the identity and stowage of on-board fluids.

APPENDIX 12–3 Helicopter Gear Boxes Oil Level Sightglasses

1 Introduction

This Appendix supersedes Airworthiness Notice No. 12 Appendix No. 43 Issue 1

dated 16 March 1990 which was originally issued following incidents caused by the
misreading of oil levels in gearboxes.

2 Background

Several incidents and an accident have occurred after stained oil level sightglasses
gave the impression that transmission gearboxes were full, when they were in fact
empty. This problem is particularly prevalent when synthetic oil is used.

3 Maintenance Considerations

Operators are reminded that sightglasses should be closely inspected for staining,
regularly, and if readability is impaired they should be cleaned.

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APPENDIX 12-4 Ice Falls From Aircraft

1 Introduction

This Appendix supersedes Airworthiness Notice No. 12 Appendix 66, Issue 1, dated
23 October 2003 which was issued to highlight the problems which arose from
leaking aircraft potable water and toilet systems.

2 Background

2.1 In recent years, the CAA has received numerous reports regarding damage to
property caused by blue or clear ice falling from aircraft. During the six year period
1997 – 2002, over 200 ice fall reports within the UK were received by the CAA and
whilst in the majority of cases it was not possible to identify the offending aircraft it
is known that the ice in most of these cases emanated from toilet system servicing
points on the aircraft.
2.2 On several occasions, where an accurate incident time and location have been
provided, ATC radar replays have been able to identify a specific aircraft responsible
for the ice fall and follow up investigations have been able to identify an aircraft defect
responsible for the ice build-up. Reports received by the CAA show that ice falls from
aircraft occur throughout the year, mainly during descent and in the majority of cases
affect properties located under approach paths into the UK’s major airports. On those
days when higher ambient temperatures exist at lower levels the ice may well melt,
reaching the ground as slush or fluid.
2.3 The majority of ice accumulations recovered following such incidents are reported as
being blue or clear in colour – the blue ice emanating from leaking toilet system
servicing points, whereas the clear ice in the majority of cases is believed to come
from leaking water system servicing or overflow points. In one incident where
significant damage was caused to the roof of a house it was found that the
responsible aircraft’s water tank overflow valve was stuck open.
2.4 Damage to property has ranged from significant damage to house roofs,
conservatories, greenhouses, garages and other buildings to cracked car
windscreens. Reported sizes of ice range from “pellet” or “melon” size up to the size
of a “bag of cement”. Whilst there are reports of people on the ground having been
struck by falling ice and suffering minor injury, to date there have been no known
fatalities.
2.5 Quite apart from the potential for falling ice to damage property and cause a hazard
to people, ice detaching from an aircraft can present a serious airworthiness threat.
There are several cases on record of extensive damage being caused to mainplanes,
stabilizers and engines by ice detaching from leaking toilet system servicing points.
2.6 Several aircraft have over the years suffered engine detachment during flight due to
being struck by ice accumulating at leaking toilet system servicing points. In one case,
a large commercial air transport aircraft had a long history of the forward toilet not
flushing due to the toilet system repeatedly losing its fluid charge. Eventually, the No.
3 engine detached during cruise at 35,000 ft after being hit by a large piece of ice that
became detached from the forward toilet system servicing panel. Damage to engine
intakes and compressor sections is not uncommon.
2.7 Toilet system fluid readily promotes corrosion and if allowed to leak past toilet system
servicing panel sealing arrangements can be forced by the airflow into difficult to

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access structures (e.g. lap joints) and may well eventually result in the need for
expensive repairs to pressure hull boundary structures.
2.8 Aircraft operators should be aware that during ramp audits of aircraft by the CAA and
indeed by overseas regulatory authorities, any evidence of leakage/staining at toilet
and water system servicing points may well result in the aircraft being delayed whilst
investigations are carried out. Cases are on record where aircraft with no leaks but
with previous staining not removed have been delayed for investigation during such
audits.
2.9 It should be noted that what might appear to be a small seep/leak on the ground past
toilet system servicing point seals will be significantly greater when the aircraft is
pressurised.
REMEMBER
THE ONLY ACCEPTABLE LEAK IS NO LEAK!!

3 OPERATOR, MAINTENANCE AND GROUND HANDLING ORGANISATION

RESPONSIBILITIES

3.1 Whilst toilet and water system details vary between aircraft types, the operating
concepts and philosophies are of course similar and operators, maintenance and
ground handling organisations should bear the following points in mind.
• Operators must ensure that personnel employed by contracted ground handling
companies who provide toilet and water system servicing to the aircraft are fully
aware of the reasons for and potential hazards associated with blue/clear ice.
Ground handling personnel should be provided with instruction in Aircraft
Maintenance Manual procedures for toilet and water system servicing.
Continuation training programmes should ensure that these aspects are revisited
as and when required. Ground handling personnel should be advised of the need
to report leakage, damage or any servicing difficulties to maintenance personnel
for corrective action.
• Reports of inoperative toilet flush and water systems especially where the fluid
charge is being lost should be investigated and rectified without delay.
• Galley and toilet sinks that refuse to drain in flight are often an indication of a failed
drain mast heater and therefore another possible source of ice accumulation.
• Operators should ensure that the aircraft maintenance programme contains all the
manufacturer’s recommendations for the maintenance of such systems.
• Operator and maintenance organisation quality departments should include
inspection of toilet and water system servicing points for evidence of leakage and
satisfactory condition of sealing arrangements in aircraft audit programmes.
• Where leaks are found prior to flight and cannot be rectified, the system should be
drained and the toilet placarded INOPERATIVE – reference should be made to the
aircraft’s MEL.
• Where dents/damage to engine intake lips, compressor blades, stabilizer leading
edges etc. are seen with no readily apparent reason for such damage,
consideration should be given to the damage having been caused by the
detachment of ice from toilet or water system servicing points forward of the
damaged area.

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• Where blue streaking/staining from toilet servicing panels is evident with nil
apparent leaks, consideration should be given to the possibility of inadequate
servicing procedures having been used.
• Whilst obviously all Airworthiness Directives applicable to such systems must be
complied with all non mandatory service bulletins and modifications should be
carefully assessed for application to such systems.
• Toilet and water system servicing point sealing arrangements must be maintained
serviceable at all times and should receive the same level of attention as afforded
to any other aircraft system.
• Leakage from otherwise fully serviceable toilet systems has on occasions been
caused by items such as soap dispensers and disposable nappies being placed in
toilets and becoming lodged under the toilet dump valve assembly. Placards
located adjacent to the toilet showing prohibited items should be maintained
legible at all times.
• Toilet systems servicing panel areas should be kept clean and free of staining to
assist in the early detection of leaks. Following any leak rectification, maintenance
personnel should ensure that any staining/contamination is removed otherwise
any future leaks may well go undetected. Operators should consider the
implementation of a cleaning programme for toilet servicing panel areas to assist
the prompt detection of leaks.
REMEMBER
THE ONLY ACCEPTABLE LEAK IS NO LEAK!

APPENDIX 20–1 Soft Metal Shims

1 Introduction

This Appendix supersedes Airworthiness Notice No. 12 Appendix No. 1 Issue 1 dated
1 March 1973 which was originally issued to warn operators of the possible failure of
a power control bracket fitting to the elevator.

2 Background

An investigation into the failure of a power control bracket fitting to an elevator

revealed that soft metal shims were embodied between the bracket and the elevator,
apparently for assembly alignment and adjustment. Small diameter special tapered
bolts were embodied in shear and set bolts in tension, but the effect of these was
quickly lost after tightening due to setting or extrusion of the soft metal shims.

3 Airworthiness Considerations

In this type of assembly it is important that the initial torque loading at manufacture
should be maintained throughout the life of the assembly. This object was defeated
by the use of soft metal shims and thus a design feature which had been proved by
experience to be undesirable, was repeated and created a serious hazard.

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APPENDIX 20–2 Crowded Ball Races

1 Introduction

This Appendix supersedes Airworthiness Notice No. 12 Appendix No. 2 Issue 1 dated
1 March 1973 which was originally issued to warn of the possibility of a control shaft
becoming completely jammed.

2 Airworthiness Considerations

2.1 Crowded ball races have no cage, and the balls are placed in position by forcing them
through assembly slots in the inner and outer races. Only a small amount of
interference between the ball and the slot is possible during assembly, with the result
that excessive wear (which can be caused by rusting or faulty manufacture) can leave
the balls free to re-enter the assembly slot. The inner race can then become locked
to the outer race and, in addition, loose balls may drop out and possibly create a
further hazard.
2.2 Cases have arisen with such bearings in which the clearances became sufficiently
large for a ball to move from its proper track into the assembly slot and yet not escape
completely because of the configuration of the bearing on the shaft. In this position,
the ball completely jammed the control shaft on which it was used.
2.3 Among many ways of preventing this kind of hazard is the use of shaped washers
alongside the bearing to prevent the balls moving sideways far enough to re-enter the
slot.

APPENDIX 20–3 Unauthorised Alteration of Parts

1 Introduction

This Appendix supersedes Airworthiness Notice No. 12 Appendix No. 11 Issue 1

dated 7 November 1973 which was originally issued to alert operators of accidents
occurring as a result of unauthorised alterations to parts.

2 Background

Fatal accidents to UK registered civil aircraft have occurred after, and at least in one
instance, as a result of, the unauthorised alteration of parts in such a way as to enable
their incorrect assembly and functioning.

3 Airworthiness Considerations

3.1 No part which could affect the safety of an aircraft may be altered other than in
accordance with drawings or instructions from the manufacturer or an appropriately
approved organisation.
3.2 In the assembly of all parts, but particularly when any change which could affect
interchangeability has been made, care must be taken to ensure that the correct part
for the particular purpose is fitted, that it is fitted correctly, the right way round, and

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if a working part, that it and the system of which it is part, works in the correct sense
and throughout the correct range.
3.3 No alteration may be made to nullify a feature provided to prevent wrong assembly.

APPENDIX 20–4 Maintenance and Re-installation of Pipes and Cable Looms

For the purpose of this Appendix, the term pipe is intended to cover small bore
flexible or rigid pipes carrying fluid at either positive or negative pressure
relevant to ambient and typically supported by 'P' clips or 'B' nuts.

1 Introduction

This Appendix supersedes Airworthiness Notice No. 12 Appendix No. 42 Issue 1

dated 16 March 1990 which was issued following a number of incidents which
occurred due to poor or incorrect routing of pipes and cable looms.

2 Background

2.1 A number of incidents have been reported in which the failure of pipes and cable
looms has occurred due to poor or incorrect routing, incorrect or absent structural
attachments and in the case of rigid pipes, corrosion and chafing at 'P' clips and 'B'
nut locations.
2.2 Manufacturers’ recommended maintenance requirements and standard practices
have always stressed the need to conduct adequate inspections of pipes and cable
looms in areas of poor and limited access during scheduled maintenance inspections
and non-scheduled maintenance. However, it is felt appropriate to re-emphasise the
need to conduct satisfactory inspections and re-installations of pipes and cable looms
following maintenance activities.

3 Airworthiness Considerations

3.1 Maintenance organisations and maintenance personnel must be alert to the need to
ensure the satisfactory condition of all pipes and cable looms with regard to chafing,
correct routing and adequate structural attachment, following scheduled
maintenance inspections, non-scheduled maintenance and the installation of
approved modifications. Attention should also be paid to the re-installation of pipes
and cable looms in accordance with the manufacturer’s original installation.
3.2 When inspecting pipes, care should also be taken to ensure that no corrosion exists
under 'P' clips and 'B' nuts. Particular attention should be paid to pipes located in
areas of adverse environmental exposure such as wheel bays, wing trailing edges and
undercarriages.
3.3 For additional information related to cable looms see CAAIP Leaflet 11-22 Appendix
24–3 and for Stainless Steel pipes see CAAIP Leaflet 11-22 Appendix 70–3.

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APPENDIX 20–5 Hazards of Damage Caused by Arc Burns

1 Introduction

This Appendix supersedes Airworthiness Notice No. 12 Appendix No. 29 Issue 1

dated 1 April 1983 which was originally issued following a fatigue failure of a titanium
alloy fan blade initiated by damage remaining from an arc burn.

2 Background

2.1 An engine’s titanium alloy fan blade failed in fatigue that had emanated from an area
of local blending on the blade leading edge. The failed airfoil may have been contained
initially by the fan containment casing but the imposed impact and rotor unbalance
loads caused damage such that together with aerodynamic loads, there were
consecutive separations in-flight of the nose-cowl assembly and of the fan
containment casing which then damaged the airframe and another engine.
2.2 The blending is believed to have met the acceptable standards for removing visible
damage, but had been applied to remove a burned area which had been caused by a
high energy electrical arc contacting the blade’s leading edge. Subsequent laboratory
examination of the failed blade’s microstructure indicated that the blending operation
had not removed all of the arc burn’s heat affected area, one remaining portion of
which became the origin of a fatigue crack.
2.3 There have been other cases of fan blade failure from arc burns. In addition, a failure
of a helicopter rotor blade has been attributed to an arc burn which had occurred
during an anodising process in manufacture.
2.4 The accidental occurrence of electrical arcs produces localised melting and rapid
subsequent cooling of materials, thereby causing a local degradation of material
properties, which may then lead to cracking (cracks for evaluation of fatigue crack
growth in test specimens are often 'started' by means of low voltage short duration
electrical arcs used to introduce a flaw in the material).
2.5 An arc burn may be evidenced by a small circular or semi-circular heat-affected area
on the surface which may contain shallow pitting, re-melting or cracking. Usually a
dark blue oxide discoloration is associated with the heat-affected area (paint protected
materials are not immune, and paint burns could be indicative of arc burn damage in
the component).
2.6 Most manufacturers provide detailed instructions for the rectification of the large
scale arc burn damage caused by lightning strikes, but they may not all adequately
cover the possibility and hazards of arc burns from electrical equipment used during
maintenance and overhaul.

3 Airworthiness Considerations

3.1 Minimise the possibility of arc burns by proper maintenance of all electrical equipment
used in the vicinity of aircraft/engine components.
3.2 If any electrical equipment, including its leads, is found to be faulty or has blown a
fuse, inspect carefully for evidence of arc burns on any item which the equipment has
been near.

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3.3 Do not regard arc burns as 'normal' damage in determining the actions to remove the
damaged area – in the absence of any published specific instructions regarding
removal of arc burn damage, obtain advice from the manufacturer or reject the part.

APPENDIX 20–6 Hydraulic Fluid Contamination

1 Introduction

This Appendix supersedes Airworthiness Notice No. 12 Appendix No. 33 Issue 2

dated 10 December 1986 which was originally issued to warn helicopter operators of
the effects of chlorine contamination of hydraulic fluid.

2 Background

2.1 A shut off valve, integral with a flying control actuator, jammed due to internal
corrosion and could not function correctly causing an accident to a large helicopter.
The corrosion had been induced by chlorine contamination of the hydraulic fluid.
2.2 Whilst manufacturers’ publications and accepted maintenance practices have always
stressed the need for scrupulous cleanliness when dealing with hydraulic
components, there has been little emphasis on the potential hazards which may
result from the vulnerability of both phosphate ester and mineral based hydraulic
fluids to contamination by cleaning solvents or water.

3 Airworthiness Considerations

3.1 Cleaning fluids in general contain, or are based on, chlorinated solvents. These
solvents, or their residues, can combine with excessive amounts of water, which are
often found in hydraulic systems, to form hydrochloric acid. This acid will attack
internal metallic surfaces in a system, particularly ferrous materials, and produce rust-
like corrosion. Such corrosion is virtually impossible to stop and component overhaul
and thorough system decontamination is usually necessary to restore the system to
a serviceable condition.
3.2 Residual contamination by chlorinated solvents during hydraulic system maintenance
or component overhaul must be prevented. When chlorinated solvents are used, care
should be taken to ensure that all surfaces, including connectors associated with
hydraulic test rigs of ground power supply sources, are free from such residual
solvent before assembly or connection to the aircraft system.
3.3 All overhaul agencies and maintenance personnel must be alert to this significant but
obscure hazard and are advised to review their maintenance procedures to ensure
that chlorinated solvents cannot get into hydraulic systems or components.
3.4 In some fluids, an excess of water, even in the absence of chlorine contamination,
may result in a build-up of acidity, or the formation of gelatinous deposits which can
clog filter elements and small passageways, therefore, hydraulic fluid in aircraft
systems and test rigs should be periodically checked for total acidity and water
content to ensure these parameters remain within the appropriate aircraft
manufacturer’s recommended limits.

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APPENDIX 22–1 Auto-pilots on Light Aircraft

1 Introduction

This Appendix supersedes Airworthiness Notice No. 12 Appendix No. 9 Issue 1 dated
7 November 1973 which was issued following an incident where the aileron control
of a light aircraft jammed.

2 Background

The aileron controls of a light aircraft recently jammed in flight; the pilot managed to
maintain control by means of the rudder. The incident was caused by the corrosion
and seizure of a bearing which supported the output drive gear of an auto-pilot roll
servo motor. A slipping clutch associated with this gear had also seized. There was
no weak link in the drive between the servo motor and the aileron control system.

3 Airworthiness Considerations

3.1 The type of auto-pilot involved in the incident is installed in many light aircraft, and the
use of a slipping clutch to protect the aircraft against excess servo motor torque, or a
jammed servo motor, is a feature common to other types of light aircraft auto-pilots.
It must be realised that such a slipping clutch does not provide protection against
jamming where seizures occur in the drive between the clutch and the flying control
system.
3.2 In the operating instructions for the aircraft involved in the incident, the pilot is advised
to check the system prior to each flight to ensure that the clutch can be slipped.
Wherever practicable a similar check should be made by pilots of all light aircraft fitted
with auto-pilots in which slipping clutches are incorporated.
3.3 Any auto-pilot servo motor (including bearings and attachments) which is connected
so as to be part of the Flying Control Installation, must be subjected to the same
maintenance checks as those called up in the Maintenance Schedule for the Flying
Control Installation.
3.4 At all times the manufacturers’ recommendations for operating and maintaining the
autopilot must be adhered to.

APPENDIX 24–1 Electrical Power Supplies – Light Aircraft Care and

Maintenance

1 Introduction

This Appendix supersedes Airworthiness Notice No. 12 Appendix No. 21 Issue 2

dated 18 August 1989 which was originally issued following incidents involving a total
loss of electrical power on light aircraft.

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2 Background

Investigations into incidents involving total loss of electrical power supplies on light
aircraft have shown that insufficient care was taken in the maintenance of the major
components of the electrical system.

3 Airworthiness Considerations

3.1 A single fault, or a single fault plus a dormant fault, may cause the loss of electrical
supplies. For example:
a) If the battery becomes disconnected from a generation system using 'commercial'
type alternators, instability may occur with the subsequent loss of the output of
both alternators and result in the total loss of electrical power.
b) In a twin-engined aircraft, a slack drive belt may operate quite adequately when
both generators/alternators (generator) are sharing the load, but may slip should
the other generator fail, with the resultant loss of output from both and leaving the
electrical system demands dependent on the battery. On a single-engined aircraft,
the belt may slip with increasing electrical load on the system, with similar results.
c) Faults in the load-sharing system may effect both generators, possibly to such an
extent as to result in the loss of output from them both.
3.2 While there are obviously many other faults which may result in generation system
failures, these examples are quoted since they have occurred a number of times in
service.
3.3 Should both generators fail and difficulty be experienced in re-setting, it may be
possible to re-set one of them by reducing the electrical load to a minimum. Having
re-set one, it is advisable not to attempt to re-set the other, since this may cause
permanent loss of the output of both.
3.4 The attention of Owners and Operators is drawn to the necessity for ensuring that
the following items are checked periodically:
a) The battery and its control relay must be correctly installed and the battery
terminals must be free from corrosion and correctly tightened.
b) Voltage settings and load-sharing adjustment (where applicable) must be correct.
c) All cable connections must be secure with locking devices in place and with end
fittings showing no signs of fatigue fracture or corrosion. Earth connections are
equally as important as the positive connections.
d) Drive belts for generators must be checked to ensure that they are in good
condition and correctly tensioned.
3.5 It is recommended that these checks should be carried out approximately every 50
flying hours or six months, whichever is the sooner. The appropriate Maintenance
Schedules should be reviewed and, where necessary, adjusted to take these
recommendations into account.
3.6 The operation of the appropriate indicators and failure warning devices should be
checked daily or during the pre-flight drill.
3.7 Whilst the CAA considers that the situation should be contained by the diligent
application of maintenance procedures, owners and operators may, nevertheless,
wish to consider modifications to improve the reliability of their own particular aircraft
by, for example, the introduction of an emergency battery to act as a power source
for vital services should the main electrical system fail. Such batteries have already
been introduced on certain aircraft, and installation information is available.

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APPENDIX 24–3 Electrical Cable Failure

1 Introduction

This Appendix supersedes Airworthiness Notice No. 12 Appendix No. 32 Issue 2

dated 10 December 1986 which was originally issued following incidents in which
damage to the insulation of electrical cables was the cause of an electrical system
failure.

2 Background

In a well-documented occurrence, damage to the insulation of electrical cables,

caused by defective circuit identification printing, was a contributory factor to a
significant aircraft electrical system fault in flight. The incorrect application of hot
stamp printing resulted in excessive penetration of insulation and a group of individual
cable damage sites coincided physically in a loom. Fluid from a leaking toilet waste
system contaminated the cables in the damaged area and severe electrical arcing
occurred which was of sufficient intensity to rupture the damaged cables and also
others in close proximity.

3 Airworthiness Considerations

3.1 Study of the pertinent factors has indicated that in addition to avoiding damage to
cables during installation, modification or repair activity, there is a need for vigilance
in the following areas:
a) Fluid contamination of electrical equipment is obviously to be avoided but it is
particularly necessary to appreciate that certain contaminants, notably that from
toilet waste systems (which is saline) and fluids which contain sugar, such as
sweetened drinks, can induce electrical tracking of degraded electrical cables and
unsealed electrical components.
b) Cable looms are particularly vulnerable to liquid contamination because they can
provide a drainage path. Care should be taken to route cables away from known
areas of possible leakage but, should contamination occur, cable looms must be
thoroughly cleaned and dried and any unsealed electrical items removed to
workshops for examination.
c) In areas where it is not possible to provide segregation between electrical cables
and pipes which carry fluid, it is good design practice to keep pipe joints to an
unavoidable minimum. The fitment of drip shields or drained enclosures to joints
in liquid waste systems is recommended.
d) The CAA will pay additional attention to the quality control of hot stamp printing
applied by cable users and will expect to see appropriate testing of cables after
printing. The preferred method of ensuring that the insulation of printed cable has
not been degraded is to employ a High Voltage Test using one of the systems
defined in British Standard BS 3G 230: 2000 Test 16. Continuous testing is not
required provided an adequate sample is tested whenever any machine setting is
altered, including changes of alpha numeric characters.
e) It is important to note that hot stamp printing may only be applied onto cable types
and sizes which have been certified as capable of accepting such marking. Cable
manufacturers whose products have approval under BCAR Section A, Chapter
A/B4–8 procedures are able to give appropriate guidance on a Declaration of
Design and Performance (DDP) and they will be able to advise on suitable test and
inspection methods.

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3.2 It has been further reported that certain types of widely-used cable insulation are
susceptible to 'arc track' when seriously abused in service. The failure detailed in
paragraph 2 related to a wet 'arc tracking' condition and designers of installations
should be aware that, in addition to the factors noted in paragraph 3.1, it is
recommended that cable selection should include evaluation of 'wet-arc tracking'
characteristics. BS 3G 230: 2000 defines test conditions for aircraft electrical cables
and Test 42 provides a test regime which facilitates comparison between cable types.
Cable manufacturers are evaluating their existing products using Test 42 criteria and
in consequence some new cable manufactures have been developed.
3.3 A further failure mode which has been established by laboratory testing and widely
canvassed, is that of 'dry-arc tracking', which is a secondary failure condition resulting
from the short circuiting of cables. The primary aim of the testing was to explore
'battle damage' failure but it may be postulated that cable to cable abrasion or other
'cut-through' faults can permit intense local heating at power levels which are well
within the short term no-trip characteristic of the associated electrical protection. In
such conditions some insulation materials can form a conducting char and if this
extends to cables not involved in the original fault, a 'cascade' failure may develop.
The CAA and other agencies are seeking to establish if this failure mechanism has any
relevance to civil aircraft beyond placing further emphasis on the need for good
design, installation and maintenance of electrical interconnect systems.
Personnel engaged in servicing of aircraft are reminded that the discovery of a
potentially hazardous failure condition during maintenance or fault finding may well
justify the raising of a Mandatory Occurrence Report (MOR). In the context of this
Appendix, any disruptive failure of electrical cables would warrant such a report.
Physical evidence should be retained for investigation.

APPENDIX 24–4 Thermal Circuit Breakers

1 Introduction

This Appendix supersedes Airworthiness Notice No. 12 Appendix No. 40 Issue 1

dated 16 September 1988 which was originally issued to clarify the role of electrical
thermal circuit breakers.

2 Background

There would appear to be some misunderstanding of the intended role of electrical

thermal circuit breakers, which is reflected in the selection, maintenance and in-flight
use of such devices. This Appendix relates to push button operated single pole and
three pole units but does not embrace the simple thermal devices which are not
capable of being manually switched (such units are occasionally fitted to light aircraft).

3 Airworthiness Considerations

3.1 The basic function of a thermal circuit breaker (CB) is to detect an electrical overload
condition which is, for rating and calibration purposes, assumed to be a constant
current. The first point to note, therefore, is that electrical faults may be of a form
which do not represent an overload to a given CB and that faults seldom present a
constant value of current for a continuous time. The CB can only be expected to
isolate faults which will overload the circuit and therefore any protection which is

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afforded to a consuming equipment, such as a motor, is often a matter of chance.

Where consumer equipment requires protection against an internal fault or functional
overload, then an appropriate form of current or temperature sensing protection
needs to be incorporated as an integral part of the design.
3.2 Distribution faults of a 'splashing' nature, which cause intermittent currents of high
instantaneous value, will also be undetected by a thermal CB unless the integral sum
of the fault currents does constitute an overload within the relevant trip
characteristics. It follows that, where other constraints permit, the current rating of
CBs should be selected at the lowest value consistent with the avoidance of nuisance
trips caused by, for example, high ambient temperatures within the CB enclosure.
Such derating of detection below the nominal level appropriate for a given cable size
will afford a greater possibility of fault protection for fault conditions which do not
conform to the idealised overload failure pattern as represented by circuit breaker
characteristic curves.

4 Operational Use

4.1 In-flight operational use of CBs will usually involve the action of resetting a circuit
breaker which has tripped because of an electrical overload or fault. Clearly the re-
establishment of electrical power to a circuit which is at fault does involve, however
slight, an element of risk. Accordingly, flight crews should be advised not to attempt
to reset CBs in flight for other than essential services and, even then, only when there
is no clearly associated condition of smoke or fumes. A second reset should not be
attempted.
4.2 Cabin crew should be advised that CBs associated with domestic services should not
be reset in flight because, by definition, the circuits involved are mostly within the
passenger areas and the inconvenience caused by the loss of service would not
justify any possible distress occasioned by 'electrical smells'.
4.3 A Technical Log entry should be made whenever any circuit breaker trips when the
aircraft is in operation and a thorough investigation should subsequently be
undertaken, including a visual inspection of the appropriate cable harnesses wherever
possible (see CAAIP Leaflet 11–22 Appendix 24–3).

5 Maintenance Considerations

5.1 It has become apparent that the progressive development of the Maintenance
Review Board determining scheduled maintenance has led to a significant erosion of
maintenance checks of circuit breakers. Users are reminded that there is a continuing
duty to monitor the performance of equipment and that items such as circuit breakers
which are largely passive in nature should be assessed for dormant faults.
5.2 As a minimum and where Maintenance Schedules do not require a high level of
checking, all CBs which are not regularly exercised by mechanical switching should
be checked for correct mechanical operation by performing two manual switching
cycles at periods of not more than two years. The necessary action should be taken
to revise Maintenance Schedules as appropriate.
5.3 Where aircraft maintenance organisations are required to undertake scheduled
calibration checks of circuit breakers, corresponding reliability data should be
gathered. Simple pass/fail criteria is not sufficient for circuit breakers, or indeed any
other equipment, where an analysis can make a significant contribution to reliability
and airworthiness.

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5.4 When installing CBs, any units which have not been supplied directly from an
Approved source or have been stored for two years or more, should be checked for
correct mechanical and, ideally, electrical operation before fitment to an aircraft.

APPENDIX 24–5 Battery Terminal Failure – GA Aircraft

1 Introduction

This Appendix supersedes Airworthiness Notice No. 12 Appendix No. 44 Issue 1

dated 12 November 1990 which was originally issued following incidents of loose,
melted or detached battery terminals on GA aircraft.

2 Background

There have been a number of reported incidents of loose, melted or detached

terminals of batteries in service on GA aircraft. In one particular case, a light twin-
engined aircraft experienced a fire in the nose compartment, on the ground, whilst
attempting to start an engine. The fire resulted from ignition of hydrogen gas (emitted
from the battery) caused by arcing of a loose battery terminal. Upon examination after
the incident, the positive battery terminal had become completely detached with the
top of the battery badly deformed as a result of the fire.

3 Design Considerations

3.1 Following this incident, the CAA issued a letter to Operators (LTO No. 795) giving
details of the dangers associated with loose battery terminals.
3.2 The terminals are basically square headed brass bolts, tinned and fluxed and placed
with thread uppermost in a lead casting assembly. Cables are held on to the terminal
post by a wing nut so as to maintain contact between the cable terminal pad and the
battery terminal post.
3.3 The FAA conducted their own investigation with the manufacturers of the batteries
and a General Aviation Airworthiness Alert No. AC 43–16 was issued. This alert
recommended certain actions as preventative maintenance which is supported by the
CAA and are outlined below:
a) Ensure that before installing any battery into an aircraft, it is the correct model for
the installation.
b) Inspect the battery terminal and stud. If it is at all loose or deformed, it should not
be installed.
c) Ensure that the battery cable terminal is clean and free from corrosion, oxidation
and contamination.
d) Ensure that the battery cable terminal fits correctly on the terminal.
e) Ensure the battery terminal post wing nut is correctly tightened (it should not be
possible to move the terminal lug by hand).
CAUTION: Do not overtighten the terminal post wing nut. Overtightening may
result in deformation of the terminal post material which will eventually result
in the terminal becoming loose in service.

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3.4 Personnel are reminded that the discovery of a potentially hazardous failure condition
during maintenance or fault finding may well justify the raising of a Mandatory
Occurrence Report (MOR). In the context of this appendix, any broken or detached
battery terminals discovered would warrant such a report. Physical evidence should
be retained for investigation.
3.5 CAAIP Leaflet 11–22 Appendix 24–1 also deals with battery terminals.

APPENDIX 24-6 Lithium Batteries

(Previously issued as AN 12, Appendix 39)

1 Introduction

1.1 The development of primary cells employing Lithium in combination with other
materials has resulted in the availability of batteries with energy densities which are
very significantly higher than those which have previously been achieved. In-service
experience and the results of safety tests carried out to Lithium batteries has shown
that there is a potential for hazard. It is therefore necessary for users to consider the
possible hazardous consequences of abuse or failure of such devices and this
Appendix considers the safeguards which should be observed.
1.2 Lithium sulphur dioxide cells have been available for aircraft use for many years but
early experience showed the risk of disruptive failure if batteries did not incorporate
adequate protective devices. In the USA Technical Standard Order C97 was produced
and this has represented an acceptable standard for Lithium Sulphur Dioxide cells, but
because other Lithium based systems have now been developed, TSO C97 has
naturally become outdated. In 1984 the CAA sought the assistance of the BSI in
preparing a British Standard to cover all known systems which was published as
British Standard G239; this standard has now been updated and re-issued as 2G 239.
Since initial publication of this Appendix, advances in Lithium technology have
resulted in Secondary (rechargeable) Lithium batteries becoming available. At present
no appropriate standard is available covering the use of these batteries on aircraft. The
CAA have again sought BSI assistance in formulating a standard similar to 2G 239 for
secondary Lithium batteries. It is the policy of the CAA to continue to implement BS
2G 239 and, in the absence of a specific standard for secondary Lithium batteries,
implement the safety requirements defined in BS 2G 239.
NOTE: EASA has published ETSO-C97 which is equivalent to the FAA TSO-C97.

2 Intending users of Lithium batteries, as defined in paragraph 3, are advised that the
CAA will seek positive assurances regarding the design and build standard of such
batteries. The following guidelines should, therefore, be observed:
2.1 The specification for the battery should embrace all the relevant requirements of BS
2G 239.
2.2 The procuring design authority should invoke BCAR Chapter A3-3 requirements for
the approval of a Controlled Item and a Declaration of Design and Performance to the
format given in BS 2G 239 should be obtained in all cases. This will normally involve
a supplier who holds an appropriate approval to BCAR Chapter A8-1 as a Group A1
Company, or EASA Part 21 subpart G, Production Approval (as appropriate).
2.3 Due regard should be taken of the possibility that some types of cell may fail such that
gases will be vented. Such failure is usually associated with accidental electrical
charging, the puncturing of cells, or the application of heat. It follows that Lithium
batteries should not be installed in proximity to passengers or flight crew if any of
these conditions can be foreseen.

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2.4 The CAA and EASA have approved suitable organisations for the design and
manufacture of Lithium batteries. The assembly of batteries by unapproved
organisations is not acceptable unless the user can, under the terms of his own
approval, demonstrate that such batteries do satisfy the requirements of BS 2G 239.
Continuing control of the design standard and production quality of such items should
be maintained.
2.5 Where Lithium batteries have been installed in aircraft prior to the issue of this
Appendix evidence should be sought that such batteries were approved to TSO C97
or that the safety requirements of BS 2G 239 are met. Should such assurance not be
available, as a minimum, evidence of safe operation under the abusive failure
conditions which are relevant to individual installations should be sought.
2.6 When batteries are removed from aircraft at the end of life, it is in the interest of
safety that the disposal procedures given in BS 2G 239 be followed.

3 For the purpose of this Appendix a single cell fitted in aircraft as a Line Replaceable
Unit (LRU) may be taken as representing a battery and thus be eligible for Accessory
Approval (BCAR Chapter A3-3). However, small button cells which are hard wired
within equipment may be considered as a component part of the equipment (as
defined in CAAIP Leaflet 9-3) and be approved within the overall type test. Such cells
should be fully assessed by equipment designers, who should be aware of the
precautions which need be taken to avoid abusive failures and be able to demonstrate
that the effects of failure have been considered. They may, therefore, seek a
Declaration of Design and Performance from the cell manufacturer as supportive
evidence.

4 Overhaul manuals for equipment containing Lithium batteries or cells should include
cautionary notes and refer to the methods of disposal given in BS 2G 239. Attention
should be drawn to the corrosive nature of any chemical contamination which may
result from disruptive failure, with appropriate advice on cleaning methods.
5 Attention is also drawn to Guidance Note GS43 entitled 'Lithium Batteries' which is
published for the Health and Safety Executive by HMSO.

APPENDIX 24-7 MIL-W-22759/16, 17, 18 and 19 Aircraft Electrical Wire

1 Introduction

This Appendix supersedes Airworthiness Notice No. 12, Appendix 64, Issue 3, dated
28 September 2005.

2 Background
Electrical wires meeting the MIL-W-22759/16,17,18 and 19 specifications have a
single non-cross linked ETFE extruded insulation.
Although not generally recommended by large aircraft manufacturers, this type of
wire construction is and continues to be in widespread use within the aircraft
industry. The acceptability of this wire type is referenced in a number of industry and
regulatory documents, e.g. FAA AC 43.13-1B, FAA Policy Memorandum Ref No.PS-
ACE100-2004-10023 and SAE AS50881.
Although this wire can be suitable for a wide range of applications it is recognised that
there are a number of performance limitations with this type of wire construction that
should be reviewed before the wire can be assessed as suitable for use in a specific
application.

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3 Limitations

The following are known performance limitations:

The insulation of this wire type can lose its mechanical properties (begin to melt)
when the wire is subjected to high fault currents or is influenced by an external heat
source.
The single extrusion insulation provides limited protection against the propagation of
insulation surface damage through to the conductor. Cracks and nicks can readily
propagate through to the conductor.
Generally, modern approved airframe wires have two or more insulation layers
specifically to provide stress relief protection against the propagation of insulation
surface damage through to the conductor.
Non-crosslinked ETFE insulation may not meet expected abrasion or cut-through
performance levels, e.g. EN3475-503.
Although the flammability test method described in MIL-W-22759/16,17,18,19
provides a good assessment of the flame characteristics of this wire, the test method
does not exactly correlate to the 60° flame test in the Certification Specifications (e.g.
CS 25), which is necessary to show compliance.

4 Discussion

Aircraft equipment should always be assessed for its suitability for use (fit for
purpose) and compliance with the relevant certification requirements. The use of this
type of wire is not automatically acceptable for the reasons stated above. Particular
care must therefore be taken when selecting this wire type to ensure that it meets all
installation and regulatory requirements and is fit for its intended application.

5 Requirement

Users of MIL-W-22759/16,17,18,19 wire and similar wire constructions shall

determine the following specific data and information for each application of the wire
to demonstrate compliance with the applicable airworthiness requirements:
The installation of the wire shall be assessed as appropriate to its intended application
and environment. The proximity of external heat sources shall be considered in
particular.
When selecting wires that are different to the existing manufacturer’s installed
wiring, the performance characteristics of the existing wiring and the new wiring shall
be compared and any differences shall be determined as acceptable.
The wire must be kept within acceptable operating parameters that accommodates
the circuit protection levels, as well as environmental and circuit heating. (Note: it is
undesirable to allow a temperature rise due to electrical heating of more than 40°C
above ambient).
The installation design shall mitigate the abrasion hazard to the cable insulation. It
shall also be established that the cable is compatible with other wire constructions in
the same bundle.
It shall be shown that the wire type to be used meets, as a minimum, the appropriate
airworthiness fire test requirements (e.g. CS 25.869 (a)(4), Appendix F Part 1(a) (3),
CS 23.1359 (c) Appendix F, CS 27.1365(c), CS 29.1359(c) etc.)

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The design assessment of the wire selection shall establish any maintenance or
inspection procedures with appropriate intervals to ensure the continued
airworthiness of the wire insulation, as appropriate.

APPENDIX 25–1 Single Lock Airframe Seat and Furnishing Attachments

1 Introduction

This Appendix supersedes Airworthiness Notice No. 12 Appendix No. 37 Issue 1

dated 6 November 1987 which was issued following an accident in which passenger
seats had become detached from the floor.

2 Background

Investigations into an aircraft accident revealed that some of the passenger seats had
detached at the floor attachment points, resulting in injury and fatalities of
passengers. The fittings used, in this particular case, were of a claw and locking collar
device on the seat legs mating with mushroom headed studs on the cabin floor. The
fitting part number was D1416–2 manufactured by General Logistics in America.
Normally the seat leg fitting and collar have an inter-connected secondary locking
device. On the seats in question, the seat leg fitting was of an early design that did
not have the secondary locking device. It is believed that impact forces allowed the
locking collar to be driven out of engagement allowing the claw to disengage from the
floor attachment, thus releasing the seats.

3 Airworthiness Considerations

3.1 All aircraft should have their seats and other items of furnishings (e.g. Galleys)
inspected for this type of fitting. Where such fittings are found, they should be
replaced with a style of attachment fitting which requires positive manual actions to
release it. If it is intended that the claw and mushroom head type be retained, then
they should be of a type possessing a minimum of four groups of holding claws plus
two interconnected locking devices. The second locking device must be of a type that
requires a positive physical action to operate it before the primary claw locking collar
can be moved.
3.2 All future designs for furnishings should use fittings similar to those described in
paragraph 3.1 above.

APPENDIX 25–2 Stowage and Accessibility of Lifejackets

1 Introduction

This Appendix supersedes Airworthiness Notice No. 12 Appendix No. 27 Issue 1

dated 2 October 1981 which was originally issued as a result of an incident where
passengers had difficulties in retrieving lifejackets.

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2 Background

An enquiry into an accident to a UK passenger transport aircraft revealed that some

passengers experienced difficulty in obtaining the valise containing the lifejacket
(hereinafter referred to as the 'valise') which was stowed underneath their seat.
Subsequent investigation showed that because the stowage pouch in which the
valise was retained was not positioned close to the front edge of the seat pan,
difficulty arose for some passengers in locating and releasing the valise.

3 Maintenance Checks

3.1 Attention of operators and manufacturers is drawn to the need for careful
interpretation of the requirements for accessibility of safety equipment* as they
relate to the occupants of aircraft, and particularly passengers, having ready and easy
access to the valise during all phases of the flight. These requirements apply not only
to the initial certification of the aeroplane type but also to modifications to seats,
seating arrangements, and equipment stowage arrangements.
3.2 Interpretation of the requirement for ease of accessibility will in most installations,
necessitate the valises, when stowed under seats, being located near to the front
edge of the seat pan, arranged so as to allow the occupant of the seat readily to
remove the valise from the stowage pouch, which may be a two handed operation,
in the shortest possible time. The method for removing the valise from the stowage
pouch should not, therefore, necessitate any extensive body movement by a seated
passenger with safety belt fastened. Furthermore, the possibility of the valise being
ejected or falling from its stowage pouch onto the cabin floor either during normal
operation or in an emergency should be minimal.
* EASA Certification Specification (CS) 25.1411.

APPENDIX 25-5 Seat Belts in Light Aircraft - Orientation of Stitched Joints

1 Introduction

This Appendix supersedes Airworthiness Notice No. 12, Appendix 62, Issue 1 dated
29 October 2001 which was issued as a result of a fatal accident.
2 An investigation into a fatal accident involving a light aircraft concluded that the seat
belt failed during a forced landing. The orientation of the stitched joint on the harness
and its interaction with a hard object, probably a trouser belt buckle, was cited as the
probable cause of the failure.

3 Background

A high proportion of light aircraft seat belts have the release box, tongue and overlap
stitching positioned so that they fall well to the side or behind the occupant’s body
when installed and adjusted. These belts are considered satisfactory and are
excluded from this notice. Care should be taken to ensure that any overlapped joints
do fall behind the body on all occasions allowing for all reasonable variations of
adjustment of the seat belt to accommodate a full range of adult human body height
and girth.

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4 Where the Original Equipment Manufacturer (OEM) provides instructions on the

installation of their seat belts / harnesses, these should be followed.
5 In the absence of OEM instructions, the CAA would advise using the following best
practice.
5.1 During routine maintenance and inspection by owners, the Popular Flying
Association, the British Microlight Aircraft Association, licensed aircraft maintenance
engineers and approved maintenance organisations, the joint between harness
webbing and metal components (release boxes, tongues and adjusters) should be
checked.
5.2 Where the webbing reversed overlapped and stitched sections are orientated
towards the body, if practical, the joint orientation should be reversed.

Incorrect Correct

APPENDIX 25-6 Emergency Escape Provisions – Doors and Escape Slides

1 Introduction

This Appendix supersedes Airworthiness Notice No. 12, Appendix 16, Issue 3, dated
18 March 2003.

2 During several emergency evacuations, difficulty has been experienced in opening

aircraft doors and in deploying the associated inflatable escape slides. Subsequent
investigations have shown that the difficulties were due to various reasons such as
incorrect rigging of door assist mechanisms, incorrect packing of the inflatable,
incorrect installation, safety pins being left in, ageing/wear of items, design
shortcomings, fitment of incorrect parts. In a significant proportion of cases however,
no reason for failure could be determined.

3 Current maintenance requirements include regular inspection, inflation checks and

overhaul of the escape slide assembly. However, this may not give an indication of
faults or deterioration that could result in the evacuation system not being available
for its intended purpose. It is considered therefore, that slides should be tested on
the aircraft by opening the doors with the slides armed and a check made to ensure
that they deploy and inflate correctly as expected in an emergency evacuation. It is
appreciated that this alone will not guarantee correct future operation of all slides on
any particular aircraft, but it will provide a level of confidence on the reliability of slide
and door operation.

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4 For all aircraft fitted with inflatable escape slides which are automatically deployed by
the opening of emergency exits, slides must be deployed as part of a slide
deployment programme on the aircraft by the automatic release and inflation of the
slide in accordance with paragraph 4.1 or 4.2 of this Leaflet. It is recommended that
when feasible the slide deployment should be carried out by cabin crew, in order to
better replicate the emergency condition.
4.1 Every slide on the aircraft should be deployed when it becomes due for overhaul in
accordance with the manufacturer's recommended intervals. This period should not
exceed 36 months.
4.2 Operators can develop a slide deployment sampling programme, with the agreement
of the CAA as part of the Approved Maintenance Programme. This programme must
ensure that, on each aircraft type, a sample of at least 10 or 10%, whichever is the
greater, of all the exits in the fleet, will have been deployed within an elapsed period
of not more than two years. The sampling programme must ensure a reasonably
uniform distribution of the exits on that aircraft type. Inadvertent slide deployments
should not be included in the slide deployment sampling programme but should still
be investigated if the slide fails to deploy correctly.

5 Details of the operators slide deployment programme should be included in the

Approved Maintenance Programme or Schedule.

6 Every operator should define it’s own pass / fail criteria which should be accepted by
the local Regional Office. The pass / fail criteria should be based on any
recommendations made by the aircraft or slide manufacturer and would be expected
to include at least the following as failures:
• Failure of the automatic deployment system (i.e. manual inflation required);
• Failure of the door to fully open;
• Door assist failure (if fitted);
• Failure to fully inflate;
• Failure to fully inflate within 10 seconds (unless otherwise specified by the
manufacturer). Timing is from when the door is initially actuated until the slide is
deployed in a useable state;
• Complete failure of slide lights to illuminate
All the above failures must be reported to the authority using the mandatory
occurrence reporting (MOR) scheme and to the aircraft type certificate holder.

7 To assist in the slide deployment failure investigation, unless otherwise agreed by the
CAA, all slide deployments must be recorded by video or other similar means and
copies of failed deployments should be held for a minimum of one year or until any
MOR or investigation into the failure has been closed. A copy should be made
available to the CAA on request.

8 All slide deployment failures must be investigated to determine the cause of failure
and action taken to prevent similar occurrences. The type certificate holder and
escape slide manufacturer should be kept informed of failure investigations and
provide assistance where possible. If there are either high levels of slide failures or
slide failure causes cannot be determined it may be necessary, in conjunction with
the CAA to carry out further deployment tests, increase the paragraph 4.2 sampling
size or remove MEL alleviation until a satisfactory level of reliability is achieved.

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9 For each deployment test the door / slide position, slide part number, pass or fail
result, date of manufacture of the slide, failure mode and failure cause should be
recorded. Operators should forward a summary of slide deployment testing at regular
intervals for each aircraft type to the appropriate CAA Regional Office. This summary
should include the following information: Number of aircraft in fleet, number of
deployments carried out and overall pass rate for fleet.

10 Due to the complexity and safety critical nature of escape slide systems it is
recommended that Maintenance Organisations involved in the installation,
maintenance and overhaul of escape slides should implement duplicate or
independent inspections on critical tasks i.e. slide installation, firing mechanism
connections, girt bar installation and rigging, door assist deactivation / slide safety pin
removal. Consideration should also be given to the training and competence of
personnel involved with the packing, installation, inspection and overhaul of escape
slides.

11 Operators should review all escape slide continued airworthiness instructions from
the type certificate holder and escape slide manufacturer including service bulletins
and service letters and consider embodiment where there may be improvements in
escape slide reliability.
When an Operator changes maintenance providers i.e. slide overhauler or aircraft
maintenance organisation it must review the slide deployment programme to monitor
the affects of such changes on the fleet escape slide reliability.

APPENDIX 26-1 Fire Hazards

1 Introduction

This Appendix supersedes Airworthiness Notice No. 12 Appendix 60 Issue 1 dated 18

March 1999.

2 Background

The collection of debris, dust and discarded catering materials found in various areas
of aircraft has, in a number of cases, created conditions which have resulted in the
outbreak of fire or the production of sufficient fumes for an emergency to be declared.

3 Airworthiness and Operational Considerations

3.1 Recently reported flight deck incidents have been attributed to:
a) the collection of dust around the flight crew foot warmers which subsequently
ignited when a high temperature setting was selected;
b) fumes produced by shorted electrical equipment as the result of metal objects
falling onto connections (as many as 7 metal cutlery knives have been found
behind a glare shield).
3.1.1 Fumes have also been produced when equipment cooling systems have collected
sufficient dust and lint to drastically reduce the airflow. This has on a number of
occasions resulted in the smell of burning and/or smoke and emergency in-flight
action having to be taken.

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3.2 Collection of debris in other areas also provides the potential for various electrical
sources to ignite combustible materials. Areas such as the void beneath toilet
shrouds, behind light fittings and behind sidewall-to-floor panels in the passenger
cabin are all places where flammable materials can accumulate. Such accumulations
pose an obvious fire risk where electrical equipment and wiring carries sufficient
current to create sparks.
3.3 Modern interior carpeting often produces large quantities of lint which finds its way
into equipment cooling filters and toilet smoke detector sampling tubes often
resulting in a reduction in performance or complete failure.
3.4 The design of most aircraft is such that large objects cannot fall into sensitive areas,
but the omission of gap fillers, seals, electrical terminal shielding and insulating boots
during maintenance can create conditions that may initiate a fire.
3.5 Maintenance personnel should ensure that design standards of sealing are restored
after equipment and panels are refitted and that all loose objects are removed prior to
closure.
3.6 Maintenance Organisations and Operators should ensure that cleaning programmes
are designed to address the removal of clogging and combustible materials at regular
intervals.
3.7 Quality sampling programmes should address cleanliness standards of aircraft
interiors, particularly flight deck areas. Flight crew should be reminded of the dangers
of placing any loose objects (including catering) on flight deck glare-shields and
pedestals.

APPENDIX 27–2 Flap Systems on General Aviation Aircraft

1 Introduction

This Appendix supersedes Airworthiness Notice No. 12 Appendix No. 19 Issue 1

dated 31 August 1977 which was issued following occurrences of sudden
asymmetric flap retraction.

2 Background

Incidents in which aircraft have experienced a sudden asymmetric flap retraction have
occurred in the UK. Two of these incidents, one of which resulted in a fatal accident,
involved different types of aircraft of United States origin and were caused by
malfunctioning of a single 'down' limit microswitch. Subsequent mechanical failures
in the flap operating mechanism resulted from repeated high loading when the flap
drive system reached the mechanical limits of its travel. Other incidents have been
reported in which asymmetric flap retractions have resulted solely from mechanical
failure of the flap drive system, e.g. operating cables or flexible drive assemblies.

3 Airworthiness Considerations

3.1 During functional checks, it is recommended that particular attention should be paid
to the correct operation of all microswitches which affect the travel limits of the flaps
and to the condition of all visible elements of the operating mechanism. The Light
Aircraft Maintenance Schedule has been amended to require a check based on these
recommendations.

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3.2 Where the 'up' and 'down' limits of flap travel are governed by the operation of single
microswitches and one of these microswitches is found to be faulty, the operating
mechanisms should be checked for any evidence of static overloading.
3.3 Where a modification to introduce an additional microswitch is available, it is strongly
recommended that it should be embodied.

APPENDIX 27-3 Control and use of Rigging Pins

1 Introduction

This Appendix supersedes Airworthiness Notice No. 12 Appendix 55 Issue 1 dated 7

November 1997 which was issued as a result of a serious incident involving a large
commercial air transport aircraft due to an unofficial rigging pin being left in the aileron
control system following maintenance.

2 Background

Whilst carrying out full and free control movement checks prior to take-off, the first
officer felt a restriction in the aileron controls. The aircraft captain confirmed there
was a restriction and the aircraft returned to the stand where it was found that a bolt,
(instead of the correct rigging pin) was installed in the control wheel rigging pin hole
at the base of the Captain’s control column.

3 Airworthiness and Certification Considerations

3.1 Subsequent investigations revealed that due to the non-availability of the correct
rigging pin, (with an attached ‘attention getting’ red disc/flag), a bolt obtained from a
free issue dispensing area was used as an alternative. The correct rigging pin, with a
red disc/flag attached, would have been clearly visible at the base of the control
column. The bolt used as an alternative was not only difficult to see but effectively
camouflaged by two similar and adjacent bolts.
3.2 All aircraft maintenance engineers, and in particular those holding certification
responsibilities, are reminded of the need for vigilance when working on control
systems and in particular during rigging operations when rigging pins are being used.
In order to minimize hazards associated with rigging pins and to prevent future
occurrences the following points should be noted:
3.3 Control of Rigging Pins
3.3.1 All rigging pins should be subjected to a form of control in order that their
whereabouts can be established. A tool store procedure which could include visual
cues in the form of shadow boards is one possibility.
3.3.2 All rigging pins should be subjected to serviceability checks prior to use, with
particular emphasis being placed on the secure attachment of ‘attention getting’
flags/discs.
3.3.3 The installation and removal of rigging pins should be controlled by the use of
worksheets, or stage sheets (CAAIP Leaflet 11-22 Appendix 5-2 refers).

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3.3.4 For maintenance in accordance with Part-145 requirements, AMC145.40(a) states

that tools and equipment as specified in the maintenance data should be made
available when needed.
NOTE: Part M AMC M.A.402(a) stipulates similar requirements.
3.4 Use of Rigging Pins
3.4.1 Only rigging pins having adequate ‘attention getting’ devices attached should be
used.
3.4.2 Where any maintenance task necessitates installation of a rigging pin(s), an open
entry should be made, to this effect, in the controlling Stage Sheet, Technical Log or
Additional Work Sheet at the time of its installation.
3.4.3 Upon completion of the maintenance task the rigging pin(s) should be removed and
the open entry in the Stage Sheet, Technical Log or Additional Work Sheet
appropriately annotated and certified.
3.4.4 Upon completion of any control system rigging operations, full and free movement
checks should be carried out as a matter of practice thus providing the final
opportunity to locate that forgotten rigging pin.
NOTE: The reader’s attention is drawn to CAAIP Leaflet 2-13 Control Systems
which contains additional information concerning the use of control system
rigging pins.

APPENDIX 27-4 Control Cable End Fittings

1 Introduction

This Appendix supersedes Airworthiness Notice No. 12, Appendix 65, Issue 1 dated
18 March 2003 which was issued as a result of information received from the FAA.

2 Background

In November 2001 the CAA received information from the FAA of a NTSB
investigation of control cable end fittings. The NTSB has investigated the failure of
flight control cable end fittings on six aircraft. Four of the failures occurred in-flight,
although not leading to serious accident or loss of life.

3 Additional end fittings from some of the incident aircraft as well as from four other
aircraft were examined and found cracked. Most of the end fittings had fractured or
cracked in a transverse manner through the shaft on the threaded end of the fitting
close to the spanner/wrench flats. A few showed evidence of cracking in the swaged
portion of the fitting.

4 The NTSB investigation identified a number of common features to the failures and
cracking of the end fittings:
• The material of manufacture of the fittings was a free machining stainless steel
grade containing selenium and a high sulphur content.
• The fittings surfaces were generally corrosion pitted. Where locking wire was
wrapped around the fitting it was noted that the pits had a higher density beneath
the wire.
• The predominant fracture mode was stress corrosion cracking, initiated at
corrosion pits.

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5 Stress corrosion cracking only occurs under specific environmental conditions, in sus-
ceptible materials when tensile stresses are induced in the material. The end fittings
examined were all taken from light aircraft which had been in service for at least 20
years, however the specific environmental conditions that caused the corrosion have
not been identified. Although, not all stainless steel end fittings are considered sus-
ceptible, it is not possible to identify the grade of stainless steel used for a fitting by
inspection.

6 The initial indication of degradation would be surface pitting of the steel. As the attack
progresses surface breaking cracks will become evident, and possibly staining and
discolouration of the steel.

7 It is recommended that all control cable end fittings are inspected for degradation
when access allows.

APPENDIX 31–1 Altimeters In Aircraft

1 Introduction

This Appendix supersedes Airworthiness Notice No. 12 Appendix No. 23 Issue 2

dated 6 November 1987 which was originally issued following incidents whereby
altimeter pressure scales had become detached from altimeter pointers.

2 Background

2.1 Instances have occurred in flight whereby altimeter pressure setting scales have
become detached from altimeter pointers when the pilot was attempting to set an
appropriate QNH. This has resulted in large indicated altimeter errors.
2.2 Subsequent investigation has revealed that satisfactory operation of the altimeter
depends on the barometric adjustment control knob being attached to the spindle so
that no fore or aft play exists between the knob and instrument bezel. If such play
exists, forward or rearward pressure on the knob may disengage the barometric
adjustment scale from the altimeter pointer.
2.3 A number of altimeters of US manufacture are known to be prone to this particular
defect. Included amongst these are the following:
Aero Mechanism 8040, 8140, 8141, 8142, 8503 Series
Kollsman Altimeters,
Narco AR 800 Series,
Bendix 3252013 Series, and
United Instrument Altimeters.

3 Maintenance Considerations

3.1 The Federal Aviation Administration have issued Airworthiness Directive 86–05–02
which is applicable to a range of part numbers of United Instruments Altimeters that
do not have encoding capabilities and were manufactured after 1 February 1985. The
affected instruments were discovered to have a deficient locking clamp which
resulted in a possible de-synchronisation of the barometric adjusting knob and altitude
pointers.

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NOTE: The CAA previously published Additional Airworthiness Directive (AAD) 006-02-87
which was cancelled on 28 September 2003.
3.2 It is strongly advised that before each flight the following checks are made:
a) That rotation of the barometric adjustment control knob results in a movement of
both the pressure setting scale and the altimeter pointers, and that forward and
rearward pressure on the knob during rotation does not disengage the barometric
adjustment scale from the altimeter pointers.
b) That the relevant altimeter pointer reading is compatible with the setting on the
barometric adjustment scale.

APPENDIX 31-2 Vertical Speed Indicators on Imported Aircraft

(Previously issued as AN 53)

1 Introduction

1.1 A recent incident on an imported light aircraft has shown the possible danger of the
presentation of false information to the pilot due to reversed indication by the vertical
speed indicator during a fast rate of descent.
1.2 United Kingdom approved instruments and instruments complying with EASA ETSO-
C8d, JAA JSTO Specification C8d, or the United States TSO Specifications C8d or
C8e, are fitted with stops to prevent such occurrences. It is not known whether other
instruments, particularly those likely to be installed in imported aircraft of less than
5700 kg (12 500 lb) maximum weight, are similarly equipped.

2 Action

2.1 Before issue of the Airworthiness Certificate and subsequent reviews for continued
airworthiness of an imported aircraft, it shall be established whether the vertical
speed indicator is fitted with limit stops. This may be done by test or reference to the
manufacturer.
2.2 If stops are not fitted, either the vertical speed indicator shall be replaced by an
instrument that has stops, or alternatively the placard defined in paragraph 3 shall be
fitted.

3 Placard

3.1 The following placard shall be fitted adjacent to a vertical speed indicator not fitted
with stops:
‘This indicator is not fitted with limit stops and a rate of change of altitude in excess
of the maximum calibration will cause indication in the reverse sense.’
3.2 The placard may, as a temporary measure, be typewritten on white card, but shall be
replaced by a more permanent placard as soon as possible.

4 Record

A record of the action taken to comply with paragraph 2 above shall be made in the
aircraft log book, quoting the serial number of the instrument.

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APPENDIX 32–1 Brake And Anti-skid Systems

1 Introduction

This Appendix supersedes Airworthiness Notice No. 12 Appendix No. 8 Issue 2 dated
8 October 1974 which was originally issued to alert operators of the possibility of
malfunction of anti-skid protection.

2 Background

Instances have occurred in which wheel brake systems incorporating antiskid

protection have not functioned in a fully effective manner. Subsequently, in most
instances, a fault has been discovered in the braking system which has prevented the
brakes from operating efficiently on all wheels. Loss of efficiency can result from a
variety of causes, e.g. incorrect assembly or failure of components in either an
electrical or hydro/mechanical anti-skid system. In one instance, a cross connection
of units in combination with a dormant fault contributed to an accident.

3 Airworthiness Considerations

3.1 Experience has shown that dormant faults which reduce the maximum energy
absorption capability of the brakes can exist without being detected during normal
energy stops. These only become apparent when the full effectiveness of the brakes
is called into use, such as during a rejected take-off. In order, therefore, to guard
against such troubles, it will be necessary to institute checks, at agreed periodic
intervals and also after any disturbance or replacement of the brake or parts of the
anti-skid system, to ensure that:
a) the operation of each anti-skid sensor controls the brake on the wheel with which
it is associated and
b) the operation of the whole braking system, including any anti-skid facility, is normal
and satisfactory
3.2 If functional checks carried out in accordance with the relevant Maintenance Manuals
would not achieve the objectives stated in 3.1 a) and b), the aircraft manufacturer
should be consulted in order to agree suitable amendments to the Manuals to include
tests which will verify the functional integrity of the system.
3.3 Operators having Maintenance Schedules/Programmes approved by the CAA should
review these Schedules/Programmes, and if necessary, forward suitable
amendments which will ensure that functional checks prescribed in the Schedule will
cover the particular matters stated in 3.1 a) and b) and that any necessary cross
references to the Maintenance Manual are amended or added.
3.4 In the event of difficulty in obtaining agreement with manufacturers, the CAA’s
Survey Department should be consulted.

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APPENDIX 32–2 Tyre Maintenance And Reliability

1 Introduction

This Appendix supersedes Airworthiness Notice No. 12 Appendix No. 24 Issue 1

dated 26 May 1978 which was originally issued following a series of accidents and
incidents caused by tyre failure.

2 Background

2.1 Multiple tyre failures have become more significant with the growth in aircraft size
and weight and have resulted in serious accidents and incidents. Inadequate
maintenance of tyres directly affects their performance and reliability. This is
particularly so for the high pressure and/or high speed rating tyres, i.e. marked in
excess of 160 mph, used on multi-wheel landing gear.
2.2 A marked reduction or loss of inflation of one tyre can, through over-deflection, result
in the failure of other tyres on the same axle, or in a marked reduction in its own ability
to carry the increased load after another tyre failure. The risk of such failures is likely
to be greater during take-off when wheel loads and/or speeds are highest or during
extended taxiing. Braking performance may also be affected to the extent that
stopping distances are increased or the remaining effective brakes are over-heated.
Tyre and wheel debris may damage hydraulic and anti-skid systems. One large aircraft
was completely destroyed by fire and other serious fires have occurred. In some
accidents, aircraft have left the runway during rejected take-offs associated with tyre
problems during the take-off run.

3 Airworthiness Considerations

3.1 Adequate inflation pressure levels and leakage checks are necessary if adequate tyre
performance is to be achieved. The maximum permissible inflation pressure
improves a tyre’s capability to sustain abnormal loads. Tyre pressures should be
accurately checked on at least a daily basis, visual inspection is totally inadequate.
Tyres should be inspected for external condition at every available opportunity bearing
in mind that fitted stationary tyres cannot be entirely inspected.
3.2 Tyre removal criteria should be adhered to, and particular attention should be paid to
tyres which have been over-deflected or underinflated or subjected to excessive
brake heat. Wear limits and damage criteria can be found in tyre manufacturers’
manuals and it should also be noted that very wet operational conditions could cause
aquaplaning during landing.
3.3 The possibility of tyre carcass and tread failures which may damage structure,
systems and engines and thus jeopardise safety, can be directly reduced by timely
attention to, and adequate maintenance of, tyre and wheel assemblies.

4 Change of Tyre Specification

A recent survey of a Yak aircraft established that an American manufactured tyre had
been fitted of a different size and ply rating to that recommended within the Parts
catalogue. It should be noted that such changes to original specification must be
supported by an approved modification.

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5 Additional Information

Additional information can be found within CAAIP Leaflet 5-7 Tyres, and for specific
tyre brands, most tyre manufacturers now publish information on their websites,
detailing information on tyre care and general servicing instructions for aircraft tyres
and tubes. The instructions are generally applicable, unless superseded by an
individual aircraft maintenance manual, technical order or Airworthiness Directive.
Examples include:
http://www.dunlopaircrafttyres.com/tyrecare/index.htm
http://www.goodyearaviation.com/tirecare.html
http://www.airmichelin.com/databook.html
http://ap.bridgestone.co.jp/candm/candm.html

APPENDIX 33–1 Bonding Of Strobe Lights

1 Introduction

This Appendix supersedes Airworthiness Notice No. 12 Appendix No. 13 Issue 1

dated 27 January 1975 which was originally issued following an explosion and fire in
a light aircraft prior to take-off.

2 Background

2.1 An incident of an explosion followed by a fire occurred on an American light aircraft,

prior to take-off. This was caused by the ignition of spilt fuel by an electrical spark at
an incorrectly bonded strobe light fitting. Following this incident Emergency
Airworthiness Directive 74–20–11, covering Beech aircraft, was issued by the FAA.
This was further superseded by AD 74-24-03. Since this hazard could develop during
service on any aircraft to which strobe lights are fitted, the attention of owners and
operators is drawn to the need to ensure that such strobe light units are correctly
bonded, as outlined in paragraphs 3.1 – 3.3.
2.2 The recommendations of paragraph 3 are applicable to strobe lights which are fitted
either during the initial build of the aircraft, or by subsequent modification action.

3 Airworthiness Considerations

3.1 For all aircraft, it is recommended that all strobe lights installed in areas which may be
subjected to either spilt or vented fuel, or to high concentrations of fuel vapour (such
as the wing tips or lower fuselage) should be inspected to ensure that a positive bond,
not greater than 0·05 ohms resistance, is provided between the airframe and light
housing. The inspection and any necessary rectification action should be carried out
as soon as is practical, but in any event not later than the next schedule airframe
maintenance inspection.
3.2 Wherever practical the bond should be a short, flexible, metal strap, attached
between the light housing and the aircraft local structure, and with clean metal-to-
metal contacts. After completion, the bonding attachments and surrounding areas
should be adequately protected against corrosion.

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3.3 Where the form of bonding described in paragraph 3.2 is impractical, a good metal-to-
metal contact between the light housing and the aircraft structure must be ensured.
This contact area must be clean and free from paint, dirt or corrosion.

APPENDIX 34–1 Maintenance of Radio Navigation Equipment Course and

Alarm Signal Current Limits

1 Introduction

This Appendix supersedes Airworthiness Notice No. 12 Appendix No. 12 Issue 2

dated 22 August 1974 which was originally issued following an accident caused by an
aircraft’s signal current settings on the ILS Localiser and Glide Path systems being set
too high.

2 Background

Following an aircraft accident it is understood that investigation of the ILS Localiser

and Glide Path systems revealed that the signal current settings were set too high.
This could result both in the course indicator being over-sensitive and in the flag
warnings failing to appear in fault conditions.

3 Airworthiness Considerations

3.1 Engineers must ensure that the instructions contained in the relevant maintenance/
overhaul manuals are complied with, particularly those applicable to course deviation
and alarm current settings.
3.2 Prior to installation in an aircraft, engineers must ensure that the current settings of
units are compatible with the particular aircraft system.
3.3 Any adjustment found necessary must only be carried out in a workshop where the
necessary test equipment and maintenance/overhaul manuals are available and by
persons appropriately approved.
3.4 Most ramp test equipment, whilst capable of checking alarm circuits for some gross
failures, is inadequate for checking their operation in other important cases. In
particular, it will not reveal whether current settings are such as to prejudice proper
flag operation. The CAA is discussing with manufacturers the possibility of modifying
such equipment, e.g. by making provision for the interruption of the tone sources so
as to enable a check of the operation of alarm circuits of the installation to be made,
and the outcome of these discussions would be the subject of manufacturers
bulletins.
3.5 It is good practice, which the CAA will expect operators and maintenance
organisations to implement, that all units incorporating adjustments for variable loads,
whether in aircraft or held as spares, have a label indicating the loads for which the
unit has been adjusted, fixed in a prominent position on the front of the unit. Aircraft
using such units should have a similar label fixed to the unit mounting.

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APPENDIX 34-2 MODE “S” Transponder ICAO 24-bit Aircraft Addresses

1 Introduction

This Appendix supersedes Airworthiness Notice No. 12, Appendix 67, Issue 4, dated
21 March 2005.

2 CAA have become aware of incorrect 24-bit addresses being installed/hard wired on
individual aircraft. This has happened not only on first installation of a Mode S
transponder but also when a modification has been made or following a change of
State of Registration. Incorrect installation, such as setting the address to all zeros or
inadvertent duplication of an address, can pose a risk to flight safety. In particular, the
airborne collision avoidance system (ACAS) operates on the assumption that only a
single, and therefore unique 24-bit aircraft address exists per airframe. The
performance of ACAS can be seriously degraded and in some cases disabled if an
incorrect or duplicate address is installed on an aircraft.

3 ICAO has recognised that the present management methodology of aircraft 24-bit
addresses presents a genuine safety hazard that needs to be addressed and suitably
mitigated in any system that is to make use of the Mode S address. CAA have issued
AIC 94/2004 (yellow 151) dated 14 October 2004 in order to make the operating
community aware of this issue. This Appendix to Leaflet 11-22 is published to make
the maintenance community similarly aware as it affects them.

4 In order to ensure that the 24-bit Mode S address is installed correctly at the time of
initial CAA certificate of airworthiness issue, as well as throughout the in-service life
of the aircraft and at the time it leaves the UK register, the following should be
accomplished:
a) A positive check that the correct Mode S address is assigned for each transponder
installed on the aircraft.
b) The correct Mode S address is periodically confirmed and recorded for each
transponder installed on the aircraft, via a field test set at an appropriate
maintenance opportunity (not to exceed a 2 year periodicity). This task should be
incorporated into the Approved Maintenance Schedule or Programme.
NOTE: Contact details to obtain an allocated ICAO 24-bit address may be obtained from
the Mode S homepage on the Directorate of Airspace Policy website via
www.caa.co.uk.
c) Ensure whenever the aircraft is subject to modification that the Mode S address
has not been changed.
d) The UK assigned Mode S address is removed when the aircraft leaves the UK
register.

5 Operators are requested to review their documented procedures and update them,
as appropriate, to ensure the above points are addressed. These procedures should
also include a method to record that the applicable actions have been accomplished.

6 Reference should also be made to CAAIP Leaflet 11-22 Appendix 34-3 which contains
advice on testing criteria for Transponders.
NOTE: With the introduction of Mode S Elementary and Enhanced Surveillance
functionality, within the transponder, it is envisaged that additional testing of the
transponder will be required on a periodic basis (not to exceed 2 years). Notification
of revised testing requirements will be included in a future issue of CAAIP Leaflet
11-22 Appendix 34-3.

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APPENDIX 34-3 ATC Transponders and Traffic Alert and Collision Avoidance
Systems (TCAS) Ground Testing

1 Introduction

This Appendix supersedes Airworthiness Notice No. 12 Appendix 69, Issue 1, dated
28 September 2005.
This Leaflet is to provide general guidance material to aircraft maintenance
organisations and maintenance personnel relating to ATC Transponder and Traffic
Alert and Collision Avoidance Systems (TCAS). It includes information on the TCAS
system together with precautions to be considered when ground testing ATC
Transponders in order to minimise the possibility of causing nuisance advisory
warnings on TCAS equipped aircraft.
NOTE: In Europe TCAS is often referred to as Airborne Collision Avoidance System (ACAS).

2 General

A number of aircraft operating within airspace regulated by the United Kingdom are
now equipped with TCAS. This equipment provides flight deck crew with an
independent back-up to visual search and the ATC system by alerting them to
potential collision hazards. In the case of the more sophisticated systems which
predominate in number, the equipment provides advice to the flight deck crew on
how best to manoeuvre so that adequate separation may be maintained or achieved
between potentially conflicting aircraft.

3 System Description and Operation – TCAS II

3.1 TCAS comprises a dedicated computer unit with associated aerials. Visual and voice
advisories are provided for the flight deck crew.
3.2 The TCAS computer requires the presence of a mode S transponder which provides
a data link between TCAS equipped aircraft. Sensor inputs to TCAS include radio
height and pressure altitude.
3.3 TCAS can provide two distinct forms of advisory information to the flight deck crew,
Traffic Advisory (TA), and Resolution Advisory (RA).
a) Traffic Advisory (TA), is aural and visual information provided in the cockpit to
advise the flight deck crew as to the position of a potential threat aircraft.
b) Resolution Advisory (RA), is aural and visual information provided in the cockpit to
advise the flight deck crew that a particular manoeuvre should, or should not, be
performed to maintain safe separation from a threat aircraft.
NOTE: Resolution Advisories can not be produced if a potential threat aircraft does not
provide altitude information.
3.4 TCAS equipped aircraft operate by interrogating the mode S or mode A/C
transponders in proximate aircraft. The replies from mode S and mode C
transponders are tracked in range, bearing and altitude. This data is passed on to the
system logic for TA and RA processing and display.
3.5 Mode A/C transponders which are not equipped with an altitude encoder or when the
altitude reporting is switched off, reply with no data in the altitude field, therefore, the
TCAS will track in range and bearing only. This information is passed to the collision
avoidance logic for TA detection and display.

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4 Testing Considerations

4.1 Recognising that airborne TCAS aircraft operate by interrogating operational

transponders, it is apparent that they will elicit replies from transponder equipped
aircraft on the ground if they are in range and the equipment switched on.
4.2 This, therefore, presents the possibility that a ground operated transponder may
trigger a nuisance advisory on a TCAS equipped aircraft operating in the close vicinity.
If the ground target is providing altitude data the TCAS logic should declare the aircraft
to be on the ground and ought not to generate an advisory.
4.3 If no altitude data is provided the TCAS will generate a TA if the threat criteria are met.
If the ground is providing altitude data other than surface altitude, as may happen with
a defective altitude encoder, or if a test pressure is being applied to the altitude
encoder, the TCAS may generate both a TA and a RA if the threat criteria are met.
4.4 Maintenance organisations and personnel who are involved in the ground testing of
transponders and TCAS equipment are requested to establish procedures and take
precautions to ensure that the risks of causing nuisance advisories are recognised and
kept to a minimum.
4.5 It is considered that nuisance advisories may be caused to any TCAS equipped aircraft
flying in the vicinity of transponders which are being tested, this may also include
aircraft passing overhead at medium altitudes. The problem may be more noticeable
where ground testing of transponders takes place at airfields located beneath
Terminal Control Areas or in the vicinity of Control Areas and Zones where air traffic
movements are likely to be numerous.
4.6 The following advice is provided to minimise the possibility of causing nuisance
advisories to TCAS equipped aircraft when ground testing transponders and/or TCAS:
a) When not required ensure that transponders are selected to ‘OFF’ or ‘Standby’.
b) For transponders under test, when equipped for altitude reporting, set the control
unit to ‘Mode A/C’ and select Altitude Reporting ‘ON’.
c) Where possible, carry out testing inside a hangar to take advantage of any
shielding properties it may provide.
d) Always use the antenna transmission absorption covers when these are provided
with the test set.
e) When testing mode C operation which require the altitude to be increased, radiate
directly into the ramp test set via the prescribed attenuator.
f) In between test parameters, select the transponder to the standby mode.
g) The simulation of TCAS operation by the radiation from an antenna located on, or
remotely based from a workshop, is not permitted.
NOTES: 1) The FAA have advised their staff of operational problems resulting in nuisance
advisories caused by ground based transponders installed on hangars for the
purpose of testing TCAS installations. Maintenance organisations are reminded
that all UK aeronautical radio stations are required to be licensed by the
Department of Trade and Industry and the CAA.
2) Air Traffic Control Units may be advised when testing is to be carried out if it is
considered that there is a possibility of nuisance advisories being caused by the
activity due to its proximity to operational runways.

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APPENDIX 35–1 Oxygen Fire Risk

1 Introduction

This Appendix supersedes Airworthiness Notice No. 12 Appendix No. 3 Issue 1 dated
1 March 1973 which was originally issued to warn operators of the damage which can
be caused when fire is fed by the aircraft’s oxygen system.

2 Background

2.1 Serious fire damage to aircraft has been caused where fires (which would probably
otherwise have been insignificant) have been fed by oxygen from the aircraft’s piped
oxygen system. In some cases an oxygen leak contributed to the outbreak of fire, in
others the oxygen was liberated by the fire which as a result then became much more
severe.
2.2 Although the increased flammability and heat of combustion of many materials in the
presence of oxygen is well known, it appears that due regard for this fact is not always
paid in the design of aircraft, particularly in the consideration of minor modifications
after original manufacture.

3 Airworthiness Considerations

Precautions should be taken to ensure that an oxygen leak will not create a fire hazard
where none previously existed and that a minor overheat or an electrical fire condition
cannot damage the oxygen system, thus promoting far more serious consequences.
Therefore, leak checks should be carried out after any disturbance of an oxygen
system.

APPENDIX 35–2 Passenger And Crew Oxygen Systems

1 Introduction

This Appendix supersedes Airworthiness Notice No. 12 Appendix No. 50 Issue 1

dated 16 March 1993 which was originally issued following an increasing number of
incidents in which the passenger/crew oxygen systems failed.

2 Background

2.1 The CAA has noted an increasing number of occurrences relating to failures of
passenger/crew oxygen systems. In a significant proportion of the cases reported,
the failures were attributed to installation errors following maintenance, operation or
test. These occurrences were mostly in connection with, but not confined to,
passengers/crew oxygen automatic drop out systems.
2.2 Due to the nature of the design of the automatic drop out systems, an installation
error may lay dormant and undetected until the system is used (possibly in an
emergency). Faulty installation has, on a number of occasions, subsequently led to a
functional failure of part or all of a system, leading to an obvious lowering of safety
levels. On a number of occasions, it has been reported that supply pipes have been
crushed and rendered inoperative by faulty installation.

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3 Maintenance Considerations

3.1 Operators should ensure that staff who may need to maintain, test or re-install
oxygen systems, especially the more elaborate passenger/crew oxygen drop out
systems, are adequately trained for the task and are retrained as necessary to ensure
retention of their competency levels.
3.2 Operators should ensure that maintenance schedules adequately address the need
to assess the functional integrity of these otherwise mostly dormant systems.
Additionally, test and installation instructions to maintenance staff and crew
members (where necessary) should be reviewed to ensure that such instructions are
adequate and unambiguous. The instructions should emphasise the need to ensure
that following functional testing or maintenance, all functional inhibiting devices are
removed.
3.3 In the case of portable oxygen systems in particular, care should be taken to ensure
that not only is the bottle addressed during routine maintenance and check (contents
and pressure testing etc.) but the condition of masks and piping should be
continuously monitored during service, possibly by cabin staff as well as maintenance
staff. Consideration should be given to invoking pre-flight checks by cabin staff where
appropriate.

APPENDIX 51–2 Primary Structural Fasteners Made in H-11 Steel

1 Introduction

This Appendix supersedes Airworthiness Notice No. 12 Appendix No. 35 Issue 1

dated 10 December 1986 which was issued following an abnormally high failure rate
of H-11 steel bolts.

2 Background

An abnormally high failure rate in service of H–11 steel bolts has been reported from
the USA. Such failures are mainly caused by stress corrosion. H–11 is a 5% chromium
molybdenum tool steel to specifications such as BS 4659; BH–11; DTD 5222; AMS
6488; AISI H–11 Modified. It is heat-treatable to tensile strength above 1400Mpa
(over 200,000 lbf/in2) with good strength retention at high temperature. Typical
applications are specialised bolts in engine, nacelle, flap track and undercarriage
mounting structures and H–11 is also offered as a material in some standard ranges
of fasteners.

3 Airworthiness Considerations

3.1 Aircraft manufacturers are asked to review their current and projected designs and
take any necessary action to avoid the use of H–11 fasteners wherever practicable,
particularly in locations where any fastener is:
a) in a tension application,
b) a single load path,
c) exposed to phosphate-ester hydraulic fluid above 120°C (250°F),
d) exposed to exhaust gases,
e) subject to weathering.

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3.2 When failures have occurred in service, the remaining H–11 fasteners should be
replaced by a fleet campaign rather than on an attrition basis. The aircraft
manufacturer should be consulted regarding replacement fasteners of a suitable
alternative material.
3.3 Owners and operators are asked to review their aircraft fleets in respect of such
fasteners to ensure:
a) adequate maintenance of corrosion protection schemes,
b) implementation of manufacturer’s SB on the subject,
c) correct torque tightening (without over-torque) of such fasteners on re-installation.

APPENDIX 51–3 Corrosion Inhibiting (Temporary Protective) Compounds

1 Introduction

This Appendix supersedes Airworthiness Notice No. 12 Appendix No. 46 Issue 1

dated 18 March 1991 which was originally issued following a review of corrosion
inhibiting compounds.

2 Background

In conjunction with the international activity on ageing aircraft, the CAA has been
reviewing the nature of corrosion inhibiting (temporary protective) compounds and
their use in the transport aircraft operating industry.

3 Design Considerations

3.1 Overall it has become clear that operators may be using such compounds that are
different from those recommended or approved by the manufacturer of the aircraft
they operate. Operators are reminded that in such circumstances it is their
responsibility to ascertain, and technically justify, the fitness for purpose of the
compound they use in their particular applications. Furthermore, adequate
procedures should be in place to ensure that the material procured consistently
meets its specification.
3.2 On this latter point a local authority trading standards department has advised the
CAA that in recent years one product of intermediate viscosity has been supplied to
the industry with its viscosity clearly above specification maxima.
3.3 One consequence of too high viscosity is the lack of penetrating capability which
could lead to areas of structure, particularly mating surfaces, remaining unprotected.
Operators are advised to check that their stocks of such material are of the
appropriate viscosity. Should they believe that they have used such non-conforming
materials on an aircraft, the area of application should be cleaned and reprotected
with appropriate conforming material, at the next maintenance opportunity.

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APPENDIX 51–4 Lock-Bolt Failures

1 Introduction

This Appendix supersedes Airworthiness Notice No. 12 Appendix No. 26 Issue 1

dated 15 January 1981 which was originally issued as a result of problems
encountered with lock bolts.

2 Background

2.1 An airframe manufacturer has experienced a problem whilst inserting steel swage
locking pins (lock-bolts).
2.2 When auto setting ¼” dia. lock-bolts (U.S.A. NAS 1468) in a rear wing spar assembly
some failures of the lock-bolt occurred on the first locking ring groove instead of at
the break groove. Other ¼” dia. lock-bolts removed from the same assembly were
found to be 'necked' with cracking evident in the first locking ring groove. This
cracking is not visible without removing the bolt but may result ultimately in the loss
of the locking collar.
2.3 Subsequent investigations revealed that defective lock-bolts have a carburised
surface with a hardness above the upper limit of the U.S.A. Procurement
Specification (NAS 1413).

3 Airworthiness Considerations

Manufacturers using this type of fastener are recommended to check that their
stocks are within specification, with particular reference to hardness values. Owners
and Operators of aircraft are advised to check such fasteners for security of collar on
an opportunity basis.

APPENDIX 51–5 Control of Precision Cutting Tools

1 Introduction

This Appendix supersedes Airworthiness Notice No. 12 Appendix No. 49 Issue 1

dated 9 November 1992 which was originally issued following incidents during
airframe manufacture which highlighted the ease with which incorrect countersink
angles and knife edge holes may be cut when adequate controls are not in place.

2 Background

In the latest incident, a series of 90° countersinks were cut when 100° was specified.
This was not revealed during fastener installation or the subsequent inspection of the
fasteners, as the countersinks were covered by the fastener heads.

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3 Design Considerations

3.1 Manufacturers and maintenance organisations are reminded of the need to ensure
that adequate procedures are in place to control the issue and use of precision cutting
tools and the installation of correct fasteners.
3.2 Incorrectly cut countersinks can cause a severe decrease in the strength of a joint
leading to a serious reduction in airworthiness and to the need for costly repair or
replacement.

APPENDIX 51-6 Self-locking Fasteners

1 Introduction

This Appendix supersedes Airworthiness Notice No.12 Appendix No. 17 Issue 3

dated 16 March 1998.

2 Background

A recent incident investigation concluded that the cause was the loss of a number of
bolts, used to secure a helicopter tail rotor drive shaft fairing, and that the bolts were
lost because the self-locking function of the associated stiffnuts had become
ineffective.

3 Airworthiness Considerations

Previous issues of Airworthiness Notice No. 12 Appendix 17 highlighted that there

have been a number of incidents concerning the use of self-locking fasteners in
helicopter control systems. These incidents arose when self-locking fasteners on
control system linkages had become detached, allowing the control system to
separate. The scope of this Appendix 51-6 has now been broadened to further
emphasise that the hazards associated with self-locking fasteners used in control
systems are also applicable to aircraft access panels on both rotary and fixed wing
aircraft.
The disturbance of fasteners to facilitate maintenance tasks may result in degradation
of the effectiveness of the friction component. Where the aircraft manufacturer
permits the re-use of self-locking fasteners, maintenance personnel are reminded
that careful attention must be given to their security, and the effectiveness of the self-
locking function.
In every case the aircraft manufacturers’ guidance should be adhered to in relation to
the use and re-use of self-locking fasteners. Such fasteners must not be re-used
unless the user is satisfied that the self-locking characteristics have not deteriorated
to a point where there is an ineffective friction element. Where no guidance is
available from the aircraft manufacturer, it is recommended that the guidance given
in CAAIP (CAP 562) Leaflet 2-5 paragraph 8, including the advice not to re-use certain
fasteners, should be followed.

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APPENDIX 51-7 Foreign Objects and Loose Articles – Danger of Jamming

1 Introduction

This Appendix shows information previously published in Airworthiness Notice No. 12

Appendix 7 Issue 6 dated 2 April 2004.

2 Background

Jamming of aircraft flight control systems by foreign objects and loose articles such
as those identified below continues to be a major threat to aircraft safety. Approved
Organisations, Aircraft Owners and Licensed Aircraft Engineers must remain alert to
the hazards of entrapment of such items and ensure that adequate precautions are
taken to prevent items falling into or being left in critical areas. Good design, high
standards of cleanliness and the implementation of standard practices can reduce the
risks of such incidents. However the awareness of personnel involved in all aspects
of aircraft operation is one of the most important elements in preventing such
potentially dangerous incidents.

3 Manufacturing, Airworthiness and Operational Considerations

3.1 As the presence of foreign objects and loose articles can cause jamming or restriction
of engine and flight control systems, organisations involved in the manufacture,
operation and maintenance of aircraft, should establish standard practices to address
foreign object and loose article control. Such practices should require personnel to
check that all equipment, tools, rags or any loose objects/articles, which could impede
the free movement and safe operation of a system(s), have been removed and that
the system(s) and installation in the work area are clean and unobstructed.
3.2 In particular maintenance personnel are the front line of defence against such
problems. As such they should remain vigilant of the need to remove foreign objects
and loose articles during and after any scheduled or non-scheduled maintenance.
Consideration should also be given to the potential to introduce loose articles into
control systems from adjoining structure e.g. loose or incorrectly torqued fasteners.
While a structure may remain safe with one fastener missing, the aircraft safety may
be severely compromised if that fastener jams a control system.
NOTE: The Duplicate Inspection is intended to ensure the correct operation and
assembly of controls, it will not prevent loose articles or foreign objects from
becoming a hazard to their continued safe operation.
3.3 Some of the reported incidents:
• Throttle movement found to be stiff due to a broken plastic spoon, lodged
between throttle levers and adjacent components in throttle pedestal.
• A bolt lodged between a flying control hydraulic-booster jack and its chassis.
• Hydraulic fluid top-up cans and meal trays fouling primary control runs.
• A spare control rod left in a fin by the manufacturer, causing intermittent jamming
of rudder and not found during twelve months of operation.
• A nut left on a control chain adjacent to the sprocket, causing the chain to fail and
jamming one flap surface.

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• A ring spanner which had remained undiscovered for two and a half years in a wing
bay which had been opened several times for control systems inspection.
• An incorrectly fitted screw on a fin leading edge which rolled across the top of the
fin and jammed the elevator during the take-off climb.
• A rudder pedal control jammed during taxi checks due to a coat hanger in a
footwell.
• The AAIB investigation of an accident involving a jammed elevator, found
numerous foreign objects which potentially may have restricted control system
movement.
• An AAIB investigation of a fatal accident to a light aeroplane, revealed a small
screwdriver had jammed the elevators such that they could not be moved beyond
neutral in a nose-up direction.

APPENDIX 56-1 Aircraft Windshields and Transparencies

1 Introduction

This Appendix supersedes Airworthiness Notice No. 12 Appendix 54 Issue 1 dated 7

November 1997 which was issued as a result of a General Aviation accident review.

2 Background

The CAA wishes to draw attention to the importance of maintaining the visibility of
windshields and transparencies to ensure that a clear and undistorted view is
provided for flight crew.

3 Operational and Airworthiness Considerations

Operators and maintenance organisations are reminded that the optical standard and
the standard of cleanliness of cockpit windshields and transparencies can have a
direct effect on the flying of the aircraft especially in conditions of poor visibility. A
hazy screen blurs the details, reduces black to grey and dims outlines. Dirt or slight
scratching scatters the light and may make it impossible for the pilot to see against
the sun.
Section 7 of the Light Aircraft Maintenance Schedule (LAMS) requires the inspection
of windscreens at Check A intervals, with a further inspection of all windows at 50
hour, 150 hour and Annual check periods. Where other maintenance schedules do not
refer to this subject, action should be taken to revise the schedule as appropriate.

APPENDIX 70–3 Effects of Chloride Based Materials on Stainless Steel and

Titanium

1 Introduction

This Appendix supersedes Airworthiness Notice No. 12 Appendix No. 41 Issue 1

dated 18 August 1989 which was issued following premature failure of stainless steel
pipes.

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2 Background

2.1 Premature failure of stainless steel pipes has occurred in engines due to the
unauthorised applications of chloride based materials, such as Neoprene tube and
glass fibre tape, used as wrappings to protect pipes from chafing against adjacent
parts. Whilst the desire to minimise wear due to fretting is quite reasonable, the need
to ensure that the correct materials are used cannot be over-emphasised.
2.2 Chloride based materials break down with heat (temperatures above 150°C) to
produce corrosive salts which will attack stainless steel and titanium components,
resulting in premature failure.
2.3 It is possible that smears of chloride material may be left on components which have
been touched by PVC (Plasticised Polyvinyl Chloride) sheeting while covered over by,
or packed in, such material.

3 Airworthiness Considerations

Operators and Maintenance Organisations are reminded of the need to refer to the
approved publications and use only the equipment and materials specified therein.

APPENDIX 72–1 Air Intake Filters

1 Introduction

This Appendix supersedes Airworthiness Notice No. 12 Appendix No. 31 Issue 1

dated 1 April 1985 which was issued following a series of forced-landings involving
piston-engined aircraft attributable to collapsed air intake filters.

2 Background

2.1 Forced-landings have occurred involving piston-engined aircraft which were directly
attributable to collapsed air intake filters obstructing the carburettor. In one case only
a fortunate combination of circumstances enabled the pilot to avoid a potentially
serious accident.
2.2 Investigation suggests that the maintenance applied to the air intake filters on piston-
engined light aircraft may not always be adequate. The LAMS Schedules concern
themselves with the cleanliness and condition of air intake filters, but under the
definition of 'inspect', imply that this can be done in situ and as viewed externally.
Individually approved maintenance schedules are generally similar in this respect.

3 Airworthiness Considerations

3.1 In practice it is apparent that for a typical air intake filter installation:
a) Visual inspection of the downstream face is usually not possible in situ. It is this
face which may show the first signs of collapse.
b) Varying degrees of dismantling may be necessary to gain access to it.
c) In nearly all cases it must be removed for cleaning.
d) Methods of cleaning vary and some methods may not be effective for all types of
filter.

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3.2 When completing scheduled maintenance inspections, engineers and pilots who may
accomplish 50-hour checks on Private Category aircraft maintained to the LAMS
Schedules must be satisfied that air intake filters are clean and fully serviceable. If
visual inspection of both faces of the filter is not readily possible, consideration must
be given to gaining access sufficiently often to ensure continued serviceability.
Reference should be made to the manufacturers instructructions whenever air filter
inspections are carried out.

APPENDIX 76–1 Single Path Control Systems

1 Introduction

This Appendix supersedes Airworthiness Notice No. 12 Appendix No. 20 Issue 1

dated 31 August 1977 which was originally issued following an incident which
occurred as a result of failure of a carburettor mixture indicator.

2 Background

An incident which could easily have been a serious accident occurred because the
single strand inner core of a flexible push pull mixture control failed at the mixture
control lever on the carburettor and the lever subsequently vibrated into the lean
position, resulting in a loss of engine power during take-off.

3 Design Considerations

Designers embodying such controls should consider the consequence of failure and
the practicability of mitigating any serious effect by the provision of a friction device
or by spring biasing the part to be operated by such a control to the safest position.

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Leaflet 11-23 Microbiological Contamination of Fuel Tanks

of Turbine Engined Aircraft

(Previously Issued as Airworthiness Notice No. 21)

1 Introduction

This leaflet supersedes Airworthiness Notice No. 21 Issue 3 dated 15 May 1970
which was issued following reports of contamination of fuel tanks.

2 Background

2.1 Reports have been received that aircraft regularly operating in climatic conditions
such as those prevailing between the latitudes 30° North and 30° South, have been
contaminated in the fuel tanks by fungus. Another aircraft, regularly operating from
the United Kingdom, was found to have localised areas of heavy growth when
inspected after standing in a heated hangar for two months with fuel in the tanks. It
is considered that the storage conditions were a contributory factor.
2.2 In one case contamination was found during an investigation into the cause of erratic
fuel contents indication, when white crusty deposits and brown stains were seen on
the probes. Further examination revealed the presence of brown/black slimes
adhering to horizontal upward facing surfaces within the tanks. Examination by the
Commonwealth Mycological Institute, Kew, confirmed that this substance was a
fungal growth of the type Cladesporium Resinae.

3 Effects of Contamination

3.1 The problems associated with microbiological growths have been known for some
years and research into their behaviour has been conducted throughout the world. In
the case of Cladesporium Resinae, the spores of the fungus can exist in a dormant
state in kerosene fuels in most parts of the world. These will only develop when in
contact with water in fuel at temperatures such as those reached when the aircraft
or storage tanks are exposed to a warm ambient temperature such as radiation from
the sun for long periods in a tropical or sub-tropical environment, or prolonged periods
in a heated hangar. If developing fungus forms on water not drained off and which
adheres to the tank surfaces, the fungus is able to absorb water later introduced with
fuel or condensing following a cold soak.
3.2 Where fungus has formed there is a probability that corrosion will occur. Corrosion
has been found where fungus had formed on the bottom tank skin, on the chordal
support member in the wing root and on fuel pipes within the tank. In some cases
aircraft have been sufficiently affected to necessitate replacement of some
component parts.
3.3 The fungus itself, if dislodged by fuel during refuelling, can obstruct fuel filters.

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4 Inspection

4.1 Operators uplifting fuel or operating regularly in areas having high normal ambient
temperatures and high humidity or where fungus development is known to have been
encountered, are advised to scrutinise tank areas for signs of fungus whenever
access is gained for any purpose. It is further recommended that, for aircraft operating
under these conditions, Maintenance Schedules should be amended to include a
visual internal tank check at periods prescribed by the aircraft manufacturer. It is also
important, whenever fuel tanks are inspected, to ensure that all passage ways
between rib cleats, etc. are not obstructed, so that a drainage path for water is
maintained at all times. If the aircraft has been standing in a heated hangar for a
prolonged period the fuel in the tanks should be treated with biocide (see paragraph
5).
4.2 If contents gauges give suspect indications, immediate consideration should be given
to the possibility that tank probes may be contaminated with water and/or fungus and
appropriate inspections should be carried out.
4.3 Whenever fuel filters are checked, they should be closely examined for the presence
of slimes of any colour.
4.4 The need to prevent water collection by good maintenance practices and control of
fuel supplies is emphasised. A high degree of protection can be maintained by strict
adherence to water drain checks before and after refuelling and again, if the aircraft
has been standing for any length of time, before the next flight. Fuel quality control
checks should be rigorously applied.

5 Treatment

5.1 If fungus is discovered, the fuel system should be cleaned as soon as possible by a
method approved by the aircraft manufacturer and the engine manufacturer. It must
be appreciated that if the fungus is allowed to develop, cleansing and rectification
could become a major operation involving grounding the aircraft for a long period.
5.2 It is strongly recommended that when aircraft operate in an area where fungal growth
can be encountered, or where there is any possibility of temperatures in the fuel tanks
frequently rising above 25°C, a fungicide additive should be used in the fuel as
approved by the aircraft manufacturer and the engine manufacturer. The frequency of
treatment and the dilutions prescribed by the aircraft manufacturer and the engine
manufacturer must be adhered to. Introduction of an unapproved fungicide or
inhibitor may jeopardise the safe operation of the aircraft.

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Leaflet 11-24 Use of Standard Parts in Aircraft and Aircraft

Restoration Projects

1 Introduction

This Leaflet has been raised to provide guidance on the use of standard parts in
aircraft restoration projects and their subsequent maintenance. This Leaflet should be
read in conjunction with the relevant aircraft manuals, manufacturers instructions,
British Civil Airworthiness Requirements (BCAR) and CAP 562 Leaflet 11-45.

2 Background

2.1 BCAR Chapter A4–8 prescribes procedures for the Design Approval of Aircraft
Equipment and Accessories. In particular paragraph 3 refers to Standard Parts with a
statement that BCAR A4–8 need not be followed for Aircraft General Spares (AGS)
and other standard parts complying with National or International specifications or
standards recognised by the CAA.
NOTE: This is intended to cover minor items complying with AGS, SBAC, BSI or
similar standards, where these are limited to manufacturing drawings from
which the approved Organisation can assess the items as suitable for the
intended application.
2.2 From time to time, whilst carrying out aircraft restoration projects usually associated
with vintage aircraft, the standard parts, or AGS of the original design standard are no
longer available. To enable the project(s) to be concluded successfully, there are
methods and procedures required to be followed by the restorer(s) for the use of
alternative parts of AGS.

3 Critical/Non Critical Nature

3.1 In the context of this Leaflet the term 'Critical Nature' is used to describe any bolted
joint or attachment where stress levels are high and where inadequate assembly
techniques or inappropriate fasteners could result in fatigue or catastrophic failure of
the structure. Examples of critical nature joints are:
a) Spar or wing attachment joints
b) Fin/tailplane attachment joints
c) Engine/strut mounting structure
d) Flying control systems or surface attachments
3.2 In the context of this Leaflet the term 'Non Critical Nature' is used to describe any
attachment or fastener of ancillary structure or fairings which are not critical to the
airworthiness of the aircraft or structure. Examples of fasteners or attachments of a
non critical nature are not exhaustive but could be associated with:
a) Fairings
b) Cabin interior furnishing
c) Panel attachment

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4 Alternative Parts

4.1 Standard Parts – Critical Nature Standard Parts which are replaced by those of
equal or improved specification with regard to dimensional tolerances and material
properties, can only be embodied by modification procedure in accordance with the
requirements of BCAR A/B2–5, or be in accordance with the product support
publications of the aircraft Type Certificate holder or Type Design (See CAP 562
Leaflet 1-14).
4.2 Standard Parts – Non Critical Nature Where the manufacturer’s airworthiness
data permits, it is acceptable to replace original standard parts used in areas of a non
critical nature with items of equal or improved specification with regard to
dimensional tolerances and material properties, without the need for CAA
involvement. In all other instances the requirements of BCAR A/B2–5 are applicable.

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Leaflet 11-25 Compact Disc – Read Only Memory (CD-ROM)

Technical Library

(Formerly entitled “Airworthiness Data Supplied and Held in Electronic

Format”)

1 Introduction

1.1 The availability of information as digital libraries providing information, guidance and
Airworthiness data in electronic format is now widespread throughout the aviation
industry. Airworthiness data (e.g. (EC) Regulation 2042/2003, Annex II, Part 145,
145.45) published in this format potentially offers the user simplified search and
access functions when compared with Airworthiness data produced in the more
traditional formats. Increasingly the CAA is being asked if it is permissible to accept
commercially produced electronic libraries as an alternative to the more traditional
'hard copy' or Microform (Microfiche) manuals.
1.2 Commercial library systems provide a useful service in consolidating all related
information into digital format with regular updating by electronic means. Users
therefore have the benefit of a comprehensive information source without the
difficulty of incorporating frequent amendments.
1.3 The purpose of this Leaflet is to provide guidance on the acceptance of Airworthiness
data provided in electronic format. When promulgated by either the appropriate Type
Certificate holder, Design Organisation or Airworthiness Authority, in any format, it is
referred to as 'Primary Source'. When promulgated by a third party it is referred to as
'Secondary Source'.
1.4 It should be borne in mind that, in respect of CAA Approval, firstly, access to the
Airworthiness data is required by the requirement for gaining and maintaining that
approval. Secondly, the CAA must be satisfied that the person (or organisation) which
the CAA has licensed or approved to make reports is qualified to do so, and remains
so. The need for that person or organisation to have access to the up to date
appropriate Airworthiness data is therefore essential.

2 Use of Primary Source Airworthiness Data

Primary Source material need not necessarily be in hard copy format as the use of
computer recorded Airworthiness data is now recognised in many areas of the law.
Hence there appears to be no reason for not accepting it in aviation. The source of
information rather than its format will, therefore, be the CAA’s primary concern.

3 Use of Secondary Source Airworthiness Data

3.1 In all cases, an organisation choosing to use Secondary Source Airworthiness data will
be responsible for ensuring that the source of the Airworthiness data will provide a
level of accuracy equal to that provided by Primary Source Airworthiness data.
Furthermore, the revision frequency will need to be such that it reflects that of the
Primary Source Airworthiness data. In entering into an arrangement based on
Secondary Source Airworthiness data, users will need to determine that the
organisation providing the Airworthiness data is legally entitled to do so.

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3.2 When selecting a supplier, consideration should be given to any particular

Airworthiness limitations which may be applicable to UK registered aircraft.
NOTE: This is particularly true of suppliers who have initially produced the
Airworthiness data to market in foreign countries whose Airworthiness
Authority may impose airworthiness limitations different to those of the
CAA.
3.3 Persons or Organisations wishing to make use of such library services should also
consider the publishers stated limitations and waivers. These will often contain
statements such as – 'It is at all times the sole responsibility of the user to interpret
and assess the validity of the information provided by the library'. Furthermore, it is
to be remembered that the majority of the manufacturer and regulatory information
contained in these libraries was not originally designed for electronic delivery.
Therefore, users should be aware that variances in spelling, ATA indexing, and
conventions may impact the effectiveness of searches and usage. Where any doubt
exists the user should refer to the Primary Source Airworthiness data.

4 Procedural Control Considerations

4.1 Any person (or organisation) using Airworthiness data is responsible to satisfy himself
that it has been supplied by an appropriate competent person and is in a form which
is acceptable to the originator of the Primary Source material. Organisation
procedures should be such that it can be demonstrated that the Airworthiness data is
both up to date and available at all times when needed.
4.2 The library controls necessary for more traditional forms of Airworthiness data are in
many cases equally applicable to that supplied in electronic format. However,
organisations in choosing to use Airworthiness data provided in electronic format
should take into account the following additional aspects:
a) It is normal industry practice to provide amendments to Airworthiness data in
electronic format by issuing replacement media; these amendments are often
supplied at frequent intervals.
b) Organisations should implement procedures which ensure that access is only
allowed to current versions of electronic data. Where it is considered that there is
a need to have available superseded electronic data, an archive system should be
implemented.
c) Airworthiness data, including associated temporary revisions and the ability to read
the Airworthiness data, should be provided in close proximity to where the work is
to be undertaken. Where printing facilities are provided, such printed material
should be automatically annotated by the software to clearly identify the source of
the Airworthiness data and its edition date.
d) The number of terminals is sufficient in relation to the volume of work to be
undertaken. Suitable arrangements should also be made to ensure that in the
event of a system failure, an alternative means of providing the Airworthiness data
is available.
e) The operating system selected should not allow the unauthorised alteration of the
Airworthiness data it displays.
f) A contract with a supplier or suppliers, should be established to maintain both the
necessary hardware and software needed to access electronic Airworthiness data,
reflecting the working patterns of the user. The contract should provide for the
support of the system which reflects the working patterns of the users.

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CAP 562 Civil Aircraft Airworthiness Information and Procedures

g) Training as appropriate on the use of the software and hardware is to be provided

to all potential users. In addition 'User Instructions' should be available at all times,
at all terminals.
h) Revision frequency in particular must be such as to ensure that users are aware of
current mandatory requirements.
i) The library subscriber is expected to be in possession of confirmation that a
contract, or agreement, exists between the publisher and the manufacturer for the
continuing supply of manufacturers information for the specific aircraft type.
NOTE: Further information on electronic Libraries may be found in:
BSi Code of Practice .... PD0008
FAA AC 120-78
ATA Specification 2100

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Leaflet 11-26 Passenger Service and In-Flight

Entertainment (IFE) Systems

This Leaflet is superseded and cancelled by JAA Administrative and Guidance Material,
Section One: General, Part 3: Temporary Guidance leaflets, Leaflet No. 17 Passenger Service
and In-Flight Entertainment (IFE) Systems, and by CAAIP Leaflet 5-12, Continuing
Airworthiness and Safety Standards of Passenger Service and In-Flight Entertainment
Systems.

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Leaflet 11-27 Disposition of Scrap Aircraft Parts and

Materials

(Previously issued as AN 96)

1 Purpose

The purpose of this Leaflet is to provide information and guidance to persons involved
in the maintenance, sale, or disposal of aircraft parts. It provides additional guidance
material and should be read, where applicable, with the requirements of Part-
145.A.42 paragraph (d) and Part-M.A Subparts C, D and E, to prevent scrap aircraft
parts and materials from being sold or acquired as serviceable parts and materials.

2 Introduction

It is common practice for owners of aircraft parts to dispose of scrap parts and
materials by selling, discarding, or transferring such items. In some instances, these
items have reappeared for sale in the active parts inventories of the aviation
community. Misrepresentation of the status of parts and material and the practice of
making such items appear serviceable could result in the use of non conforming parts
and materials.

3 Types of Parts and Materials that may be Misrepresented

Persons disposing of scrap aircraft parts and materials should consider the possibility
of such parts and materials being misrepresented and sold as serviceable at a later
date. Caution should be exercised to ensure that the following types of parts and
materials are disposed of in a controlled manner that does not allow them to be
returned to service:
a) Parts with non-repairable defects, whether visible or not to the naked eye;
b) Parts that are not within the specifications set forth by the approved design, and
cannot be brought into conformance with applicable specifications;
c) Parts and materials for which further processing or rework cannot make them
eligible for certification under a recognised released system;
d) Parts subjected to unacceptable modification or rework that is irreversible;
e) Life-limited parts that have reached or exceeded their life limits, or have missing
or incomplete records;
f) Parts that cannot be returned to an airworthy condition due to exposure to extreme
forces or heat;
g) Principal Structural Elements (PSE) removed from a high-cycle aircraft for which
conformity cannot be accomplished by complying with the mandatory
requirements applicable to ageing aircraft.

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CAP 562 Civil Aircraft Airworthiness Information and Procedures

4 Methods to Prevent Misrepresentation of Scrap Parts and Materials

4.1 Persons disposing of scrap aircraft parts and materials should, when appropriate,
mutilate those parts and materials prior to release. Mutilation should be accomplished
in such a manner that the parts become unusable for their original intended use, nor
should they be able to be reworked or camouflaged to provide the appearance of
being serviceable, such as by re-plating, shortening and re-threading long bolts,
welding, straightening, machining, cleaning, polishing, or repainting.
4.1.1 Mutilation may be accomplished by one or a combination of the following procedures,
but is not limited to:
a) Grinding;
b) Burning;
c) Removal of a major lug or other integral feature;
d) Permanent distortion of parts;
e) Cutting a hole with cutting torch or saw;
f) Melting;
g) Sawing into many small pieces.
4.1.2 The following procedures are examples of mutilation that are often less successful
because they may not be consistently effective:
a) Stamping (such as a stamped 'R' on a part);
b) Spraying with paint;
c) Hammer marks;
d) Identification by tag or markings;
e) Drilling small holes;
f) Sawing in two pieces. Persons who rework scrap parts and materials may be
skilled technicians and attempt to restore parts cut in two pieces in such a manner
that the mutilation proves difficult to detect.
4.2 With regards to persons disposing of scrap aircraft parts and materials for legitimate
non-flight uses, such as training and education aids, research and development, or for
non-aviation applications. In such instances, mutilation is not appropriate and the
following methods should be used to prevent misrepresentation:
a) Permanently marking or stamping the parts, subparts, and material as ‘NOT
SERVICEABLE’. (Ink stamping is not an acceptable method);
b) Removing original part number identification;
c) Removing data plate identification;
d) Maintaining a tracking or accountability system, by serial number or other
individualised data, to record transferred scrap aircraft parts and materials; and
e) Including written instructions concerning disposition and disposal of such parts
and materials in any agreement or contract transferring such parts and materials.
NOTE: Scrap or expired life-limited parts and materials should not be passed on to any
person or organisation who may end up placing the parts and materials back in actual
use, due to the criticality of parts and material failure and the potential safety threat.

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CAP 562 Civil Aircraft Airworthiness Information and Procedures

4.3 Organisations handling scrap or expired life-limited aircraft parts and materials should
establish a quarantine store area in which to segregate such items from active
serviceable inventories and to prevent unauthorised access. Caution should be
exercised to ensure that these parts and materials receive the disposition specified in
this Leaflet.
4.4 Manufacturers producing approved aircraft parts should consider maintaining records
of serial numbers for 'retired' life-limited or other critical parts. In such cases, the
owner who mutilates applicable parts is encouraged to provide the original
manufacturer with the data plate and/or serial number and final disposition of the part.

5 Method to identify misrepresented parts

All purchasers of aircraft parts and materials should ensure that misrepresented scrap
parts and materials are not received into active inventory. The following are examples
of conditions to be alert for when receiving parts:
a) Parts showing signs of rework which were purchased as ‘new’;
b) Used parts showing signs of unapproved or inappropriate repair;
c) Parts with poor workmanship or signs of rework in the area of the part data plate,
number or serial number inscription;
d) Used parts lacking verifiable documentation of history and approval;
e) Parts with prices ‘too good to be true’;
f) Questionable part numbers, fraudulent or suspicious Technical Standard Order or
FAA-Parts Manufacturer Approval markings and/or re-identification, stamp-overs
or vibro-etching on the data plate;
g) Parts delivered with photocopied or missing EASA Form 1 or other acceptable
maintenance release documentation;
h) Parts with a finish that is inconsistent with industry standards (e.g. discoloration,
inconsistencies, resurfacing);
i) Parts purchased as new but with release documentation reflecting a status other
than new;
j) Parts with poor documentation exhibiting incomplete or inconsistent part identity
information;
k) Intact ‘scrap’ unsalvageable parts offered in bulk weight for prices higher than for
mutilated parts with identical weight and content.
NOTE: Suspected Unapproved Parts Notification can be found on FAA Internet address:
www.faa.gov/avr/sups.htm and Special Airworthiness Information Bulletins can be
found on FAA Internet address: www.faa.gov/certification/aircraft/av-info/AD/
saibs.asp
An approved organisation or LAME who receives suspect parts should report to the
CAA as detailed in paragraph 6 of CAP 562 Leaflet 1-6.

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Leaflet 11-28 Return to Service of Aircraft Items Recovered

from Aircraft Involved in Accidents/Incidents

(Previously issued as AN 97)

NOTE: For the purpose of this Leaflet the term 'items' includes all components, parts,
engines and accessories.

1 Introduction

1.1 This Leaflet reviews the factors involved in establishing the acceptability of aircraft
items recovered from aircraft involved in accidents/incidents, and states the
conditions to be met before such items may be returned to service.
1.2 This Leaflet applies to aircraft designated as falling under Annex II to Regulation EC
216/2008. These are known as non-EASA aircraft and come under the regulatory
control of the Civil Aviation Authority and are issued with National Certificates of
Airworthiness and Permits to Fly. It does not apply to EASA type certificated aircraft,
which are covered by requirements defined in Part 145 and Part M.
1.3 The Civil Aviation Authority has evidence that some aircraft items, (including highly
stressed rotating parts) have been released to service after having been recovered
from aircraft involved in accidents/incidents even though the accident circumstances
may have caused damage or changed characteristics from those of the type design.
Since such items may not manifest any visual evidence of damage, distortion or
changed characteristics, a serious airworthiness hazard could result from their use
without special precautions being taken as detailed in this Leaflet.
NOTE: The subject of this Leaflet was first promulgated to industry by a CAA Letter to
Operators Number 461 (revised to LTO 461/A on the 18 December 1981), following
informal consultation with industry and with aviation insurers.

2 Establishing Origin of Recovered Items

2.1 When an aircraft has been involved in an accident/incident, the title to the salvage
may pass from the insured owner to other persons (e.g. aircraft insurers) and this
salvage may be offered for sale either complete or as separate aircraft items in an 'as
is - where is' condition. While some items may be totally unaffected by the accident/
incident which caused the aircraft to be declared as salvage, it is essential to obtain
clear evidence that this is the case. If such evidence cannot be obtained, the item may
not be returned to service.
2.2 All such items must therefore be subject to competent assessment and inspection in
the light of adequate knowledge of the circumstances of the accident, subsequent
storage and transport conditions, and with evidence of previous operational history
obtained from valid airworthiness records, before overhaul and re-installation can be
considered.
2.3 In particular, if a crash load is sufficient to take any part above its proof strength,
residual strains may remain which could reduce the effective strength of the item or
otherwise impair its functioning. Loads higher than this may of course crack the item,
with an even more dangerous potential. Further, a reduction in strength may be
caused by virtue of the change of a material’s characteristics following overheat from

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CAP 562 Civil Aircraft Airworthiness Information and Procedures

a fire. It is therefore of the utmost importance to establish that the item is neither
cracked, distorted nor overheated. The degree of distortion may be difficult to assess
if the precise original dimensions are not known, in which case there is no option but
to reject the item. Any suggestion of overheating would be cause for a laboratory
investigation into significant change of material properties.
2.4 The standard procedures appropriate to items removed for overhaul following normal
service life may not therefore be sufficient for items from salvaged aircraft. If the
information in the Manufacturer’s Manual, or other technical publications, is
insufficient to deal with the considerations detailed above then the manufacturer
must be consulted for guidance. If the manufacturer provides the additional
information, and the item can be shown to meet this, then it may be returned to
service.
2.5 Where a difficulty exists in classifying the airworthiness significance of an aircraft
item recovered after an accident/incident, the question should be referred to the CAA
Airworthiness Division, Survey Department, for advice. The CAA will require full
details of the circumstances of the accident/incident before a response is made to the
enquiry.
2.6 It should be noted that UK licensed engineers or CAA Approved Organisations cannot
inspect components or assess the implications of impact damage or fatigue without
the involvement of the manufacturer or a CAA Approved Design Organisation if the
existing approved data for the aircraft type does not provide appropriate and specific
inspections. The component can only be released in accordance with approved data,
reference BCAR Section A6-2 and CAP 562 Leaflet No. 15-2.

3 Information obtained from Aviation Insurers

3.1 Aviation insurers and other persons who obtain title to salvage parts may supply to
salvage purchasers the details of the accident/incident leading to the aircraft, or
aircraft item, being declared as salvage. It is also common practice for aviation
insurers to pass over the airworthiness records to the salvage purchaser. Whilst such
information and records are an essential part of the assessment, where return to
service is being considered, they are not a guarantee that the item is acceptable for
re-installation.
3.2 Some aviation insurers have agreed to co-operate with the CAA’s attempt to prevent
items being returned to service if their airworthiness cannot be confidently confirmed.
They have agreed to supply details of the occurrence, and to identify the party to
whom the salvage has been sold, to the Airworthiness Division, Application and
Approvals Department. This information may be relevant when CAA advice is sought
under paragraph 2.5 of this Leaflet, but does not excuse the enquirer from furnishing
the information required by that paragraph.

4 Supplementary Information

4.1 Attention is drawn to CAP 562 Leaflets 1-6 and 11-45 which also deal with the
safeguards necessary for users obtaining aircraft parts in the open market, particularly
in relation to the release documentation and evidence of previous history.

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CAP 562 Civil Aircraft Airworthiness Information and Procedures

Leaflet 11-30 Portable Battery Powered Megaphones

(Previously issued as AIL/0045. This leaflet has not been technically revised but is
scheduled to be reviewed in the near future.)

1 Purpose

The purpose of this Leaflet is to provide guidance in the form of a specification to an

operator who has to install portable megaphones in order to comply with the Air
Navigation Order.

2 References

Air Navigation Order

3 Introduction

The Air Navigation Order has been amended to require that all UK registered aircraft
used for the purpose of Public Transport, having a seating capacity for 60 or more
passengers will be required to carry a complement of Portable Battery-Powered
Megaphones for use by the crew should an emergency arise.
This Leaflet presents an acceptable means of compliance with the ANO, in the form
of a specification which states minimum characteristics and other necessary features
and additionally covers associated installational aspects.
It is intended after gaining experience of its application to embody the material into a
CAA specification. This specification is intended for guidance to an Operator who may
wish to install a commercially available megaphone. Appendices to the specification
state recommendations on methods of meeting the specification requirements.
The Federal Aviation Regulations also prescribe in FAR Part 121.309(f) the carriage of
portable battery-powered megaphones, but no Specification similar to that proposed
by this Paper has been issued by the FAA.

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Appendix A

1 Specification for Portable Battery-Powered Megaphones

Intended for use in emergency conditions in Civil Transport Aircraft.

2 Basic Requirements

Portable megaphones to comply with this Specification should have the following
characteristics:
a) Intelligibility
Under normal ground conditions in the cabin, messages spoken into the
megaphone should be intelligible to at least 90% of the occupants in the
passenger cabin in the aircraft in which it is expected to operate. See paragraph m)
and Annex 1.
b) Acoustic Power
As a criterion it can be taken that when the megaphone is used in open country
where a reasonably quiet sound background exists it should be capable of
providing intelligible speech at a distance of 100 metres. See Annex 1.
c) Power Supply
They should have a self-contained power supply. This should not be interpreted to
exclude connection, when not in use, to the aircraft power supply system.
d) Design Standard
The design of the megaphone and its power supply arrangements should be such
that the likelihood of satisfactory operation when needed is high.
e) Environmental Resistance
The megaphone should be shown to be suitable for withstanding the
environmental conditions which it will experience in the aircraft. It should be so
installed as to minimise any adverse effects from the environment.
f) Mounting in Aircraft
It should be so installed and retained that it will withstand the emergency
accelerations specified in British Civil Airworthiness Requirements Chapter D3-8
paragraph 2 without breaking loose or having its performance impaired.
g) Compass Interference
Should powerful magnets be incorporated in the device, it must be so installed that
it does not interfere with any magnetic compass in the aircraft beyond the limits
stated in the British Civil Airworthiness Requirements Chapter D6-8.
h) Acoustic Operational Characteristics
The microphone should be such as to render the system satisfactorily resistant to
the risk of feedback howl. The microphone should also be not unduly critical
regarding the distance between it and the mouth of the person speaking.
Consideration should be given to making this appropriate distance neutral and self-
evident to the user.

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CAP 562 Civil Aircraft Airworthiness Information and Procedures

i) Controls
The number of controls should be minimal, of a type which are self-evident and are
easily operable by a crew member even under conditions of stress. The control of
volume by the user of the megaphone should preferably be by switch setting
although continuous control could be considered. Two levels should be
incorporated which can be pre-set on checking a particular installation, one for use
inside and one for use outside the aircraft.
j) General Design
The megaphone should be so designed that inadvertent operation is unlikely.
k) Portability
A suitable means of carrying (such as a harness) should be provided.
l) Battery Checking
Arrangements should be made in the maintenance schedule for the checking of
the battery. Labels should be attached to the exterior to render battery
replacement times easily identifiable.
m) Tests
It is necessary to test the megaphone for intelligibility. This should preferably be
done in the environments in which it is intended to be used. An alternative test is
indicated in Annex 1.
n) User Instructions
The megaphone should incorporate simple but effective instructions for its use, on
its outside. These should cover switching on and off, volume control and proper
use of the microphone.

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CAP 562 Civil Aircraft Airworthiness Information and Procedures

Annex 1

1 Test for Intelligibility and Acoustic Power

The acoustic conditions in aircraft interiors vary considerably and according to the
aircraft design, the number of passengers who may be expected to hear a particular
message will vary in accordance with the internal arrangements of the aircraft and the
corresponding crew training.
Ideally each type of megaphone should be tested in the cabin environment in which
it is liable to be used. Volunteers should be used to simulate the passenger
complement. A number of messages should be broadcast containing occasional
unexpected words and the volunteers invited to write them down. A 90% correct
recording would be regarded as acceptable.
However, it is recognized that the assembly of people required for such a test is
expensive and may only be warranted when there are special unknowns.
Experiments have shown that there is a reasonable correlation between the
performance of a megaphone in the highly absorbent acoustic environment of an
aircraft and its ability to be heard at a distance in a quiet open-air environment. It has
been established that the megaphones found satisfactory in typical aircraft cabins
were all capable of good intelligibility at ranges of 100 metres in the open air.
The open-air test should be conducted in an area where the acoustic environment is
reasonably quiet. If it were felt that ‘reasonably quiet’ is in need of a more formal
definition the suggested level would be that the ambient noise should not be greater
than 40 dBA. Not less than three observers, spaced apart but all at 100 metres
distance from the megaphone should be asked to record appropriate messages. It
might well be desirable to use more than one speaker to eliminate the effects of
exceptional voice characteristics or lack of training in microphone usage. Again a 90%
correct recording would be acceptable having regard to the redundancy provided in a
situation by the natural repetition tendency of a speaker in a crisis – particularly if
trained to do so.

2 Proof of Suitable Enviromental Resistance

Since the portable megaphone does not function continuously, the cost of testing in
a simulated environment is considered unwarranted. On completion of a satisfactory
intelligibility test, the equipment should be installed in the aircraft with its proper
retaining arrangements and then checked for functioning at appropriate intervals (e.g.
three months). Completion of a year’s flying with proper functioning at three-monthly
intervals would be regarded as suitable confirmation that the chosen megaphone was
resistant to the effects of temperature, vibration and humidity encountered on that
installation. However, extension of overhaul periods would depend on the trust that
can be placed on the battery.

3 The Battery

It could well be that the megaphone would be most satisfactory if it incorporated re-
chargeable cells in its battery. These could be trickle-charged from a detachable lead
connected to the aircraft supply. From what is known, successive checks might easily
establish an effective time between overhauls of several years of such a combination.

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CAP 562 Civil Aircraft Airworthiness Information and Procedures

However, most of the readily available specimens incorporate simple batteries

containing zinc-carbon or similar dry-cells. These have the great advantage of
cheapness and so there is little discouragement of frequent replacement. It is felt
essential that only cells date-coded by the manufacturer should be used. The battery
should then be tested under load at three-monthly periods. Such tests will enable the
build up of useful experience and a realistic replacement time to be deduced. Account
should be taken of the temperature conditions in which the aircraft operates. It is
particularly important to examine the battery and casing, and the connectors, for
corrosion. On an aircraft with good control of the cabin air-conditioning system, a
reasonable replacement time of six months, or even a year, might be established. It
may well be that shorter periods will be necessary, however.
Experience has shown that the spring type pressure contacts commonly used for
batteries comprised of unit cells (e.g. AA or HP7 size) are not satisfactory. This is
particularly so with alkaline cells, usually installed to achieve a greater replacement life
than the recommended three months limitation for zinc carbon cells. It is
recommended that cells should be assembled, preferably by the battery
manufacturer, into a proper battery pack which can be incorporated with highly
reliable screw-on connectors.
The maintenance organisation of the airline should keep records of the dates of
manufacture, installation and testing of the particular cells which they use.
It is possible to obtain more sophisticated primary cells such as the manganese-
alkaline or mercury types which could have a longer life. However, whichever cell is
chosen, the Airworthiness Division of the CAA finds that there is no substitute for the
standard procedure of periodical functional testing. Thus the intervals between tests
can only be extended cautiously.
Where longer life type cells are incorporated, even when confidence on the longer life
has been established by sample discharge tests, it is useful and conventional to
conduct a terminal voltage test on the batteries on interim maintenance. It is pointed
out that when fairly high impedance volt meters are used (e.g. AVO) the reading is
useless for assessing battery state if the battery is not suitably loaded. Thus while
making such a measurement the tester could either operate the megaphone
(shouting loudly into it) at the same time, or impose a resistive load so adjusted as to
create a current drain of say 300 mA. Cells showing less than 1.1 volts under this
condition should be rejected.

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CAP 562 Civil Aircraft Airworthiness Information and Procedures

Leaflet 11-31 Radio Apparatus for use in Aircraft for other

than Flight Operational Purposes

(Previously issued as AIL/0167)

PURPOSE: This Leaflet provides information and guidance concerning the approval and
installation of Radio equipment for use in aircraft for other than Flight
Operational Purposes.

The Leaflet is only applicable to those aircraft that are excluded from EASA
under Annex II of EC Regulation No. 216/2008 and others excluded through
being in service with the military, customs, police or similar services (under
Article I of the regulation). For all other aircraft whose Type Certificates have
been transferred to EASA, minor and major change procedures of Part-21 to
EC Regulation No. 1702/2003, Subparts D and E apply. For the remainder of
this Leaflet, no further reference will be made to Part-21 procedures.

REFERENCES: Air Navigation: The Order and the Regulations, CAP 393.
British Civil Airworthiness Requirements (BCAR), Sections A, B and R.
EASA Certification Specifications: CS-23, CS-25, CS-27, CS-29 and CS-ETSO.
Ofcom.
Radio Frequency Allocations, (see website: http://www.radio.gov.uk/).

CAAIP Leaflet 9-8, ’Use of Electrically Powered Medical Equipment on

Aircraft’.
JAA Administrative and Guidance Material, Section One: General, Part
Three, Temporary Guidance Leaflet: Leaflet No. 17: Passenger Service and
In- Flight Entertainment (IFE) Systems.
JAA Administrative and Guidance Material, Section Four: Operations, Part
Three, Temporary Guidance Leaflet (JAR-OPS) No. 29.
EC Regulation No. 216/2008.

CANCELLATION:This Leaflet supersedes and cancels AIL/0167 dated 29 October 2004.

1 Introduction

The Air Navigation Order requires all radio equipment carried on UK registered civil
aircraft to be of a type approved by the CAA or EASA. This Leaflet provides guidance
on the approval procedures to be followed to gain CAA approval of radio equipment
that is to be used for purposes other than normal flight operations. Typically, such
equipment includes radio transceivers for work involving surveillance, survey, marine
communications, emergency services operations, passenger communications, and
trials.
This Leaflet is updated to: amend EASA Regulation ‘1592/2002’ to ‘216/2008’;
convert references to AILs to CAP 562 Leaflets; and explain the use of the DAP 1902
Form in lieu of the AD 968 Form.

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CAP 562 Civil Aircraft Airworthiness Information and Procedures

2 Approval Categories

BCAR Section R and Volume 2 of CAP 208 (now obsolescent – CAP 562 General
Information Section, Airworthiness Publications refers) lists five approval categories
which have the following designations:
Approval number prefixed by – WR, VC, LAI, LAII or LAIII.
Within BCARs other approval categories exist which have been applied to radio, they
are:
Approval number prefixed by – Q, MISC, SA or G.
Non flight operational radios must be approved either in one of the latter categories
or through the procedures described in section 4 of this Leaflet.
NOTE: The EASA CS-ETSO (formerly JAR-TSO) system is not currently applicable to
non-flight operational radios.

3 Approval Considerations

3.1 The approval considers that the radio equipment should function as intended but no
’credit’ is given for the performance capability of the system. Substantiation is
required to demonstrate that the equipment and its installation shall not affect the
safety of persons or the safe operation of the aircraft and shall not interfere with other
radio users.
3.2 Article 20(5)(a) of the United Kingdom Air Navigation Order 2005 (as amended)
(contained in CAP 393) states ’All radio and radio navigation equipment installed in an
aircraft registered in the United Kingdom, or carried on such an aircraft for use in
connection with the aircraft shall be of a type approved by the CAA in relation to the
purpose for which it is to be used…..’ .
3.3 Radio equipment are generally common user, non-aircraft specific items which are
CAA approved under a unique radio approval reference.
3.4 The following criteria shall be complied with and the appropriate evidence submitted
with the approval application:
a) The radio frequency or frequencies used by airborne transmitters shall comply with
the frequency allocations for Aeronautical Mobile use as referenced in the UK table
of Radio Frequency allocations, or have specific agreement from Ofcom.
b) The Radio Operators Licence required for the operation of the equipment shall not
preclude airborne use and it is the responsibility of the aircraft owner/operator to
complete the radio licence application form DAP 1902 (ACT1 1001) and return to
the Radio Licensing section of the Directorate of Airspace Policy at the address
below:
Radio Licensing Section
Directorate of Airspace Policy
K6 Gate 6
CAA House
45-49 Kingsway
London WC2B 6TE
Tel. 0207 453 6555
Fax. 0207 453 6556
E-mail radio.licensing@caa.co.uk
NOTE: The Form DAP 1902 replaces the Form AD 968 which is no longer used.

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CAP 562 Civil Aircraft Airworthiness Information and Procedures

c) The CAA may continue to approve these radios where it is determined that they
are to be installed in an Annex II aircraft or aircraft excluded from EASA under
Article I of EC Regulation No. 216/2008.
Organisations applying for CAA approval for such radio apparatus shall provide
adequate declarations and reports together with appropriate technical information;
including statements of transmitter frequency range, spurious radiation, output
power, frequency tolerance and modulation characteristics and evidence of radio
regulatory approval, e.g. Department of Trade and Industry (DTI), Federal
Communication Commission (FCC), BCAR Section A, Chapters A4-8 and A4-10,
BCAR Section B, Chapters B4-8 and B4-10 refer.
d) The method of use and installation shall be approved by the CAA in accordance
with BCAR Section A, Chapters A2-5 and A3-11,BCAR Section B, Chapters B2-5
and B3-11, and Section R, Chapter 4 in order to ensure that the use of this category
of radio apparatus shall not adversely affect the safe operation of the aircraft in
which it is installed.
i) The organisation undertaking the design of the installation shall ensure that
adequate Electromagnetic Compatibility (EMC) tests are performed. These
tests should be performed with the aircraft engines running, and with all
required electrical and avionic equipment which can be operated on the ground
in operation. The installed radio equipment shall be operated over a range of
frequencies throughout the operating band such as to establish that the level of
radio and electrical interference is such as not to reduce the performance of any
aircraft required system below a level compatible with the characteristic
performance of the system. Systems that could be susceptible to interference
include FADECs, engine computers, cockpit displays, required communication
and navigation equipment and autopilot/flight director systems.
These tests shall be agreed with the Civil Aviation Authority.
ii) Where it is not practical to perform ground tests (for example, on aircraft with
engines controlled by FADEC), it may be necessary to perform a flight test.
Such tests shall also be agreed with the Civil Aviation Authority.
e) Where safety is dependent on particular crew actions, a Flight Manual supplement
must be provided to represent the limitations and procedures required for safe
operation.
f) The electrical load analysis shall be amended to show that the non-flight
operational loads do not compromise the busbar loading, generator ratings and
battery duration.

4 Approved Organisation

4.1 Where a CAA or EASA approved design organisation has a recognised special need
to install and/or use radio equipment that is not normally designated for civil aircraft
use then this section applies.
4.2 This Leaflet is not eligible for use by organisations that do not hold an EASA design
approval or, while still applicable, CAA design approvals.
4.3 This is not applicable to equipment operated within the civil aeronautical radio
frequency bands.

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CAP 562 Civil Aircraft Airworthiness Information and Procedures

4.4 Non-flight operational radios may be approved under Component procedures as

defined in BCAR Section A, Chapter A4-8, paragraph 5.3 or BCAR Section B, Chapter
B4-8, paragraph 5.3.
4.5 The following criteria shall be complied with:
a) Paragraphs 3.4 a), b), d), e) and f).
b) A tabular list of equipment is to be maintained by the design organisation and/or
operator. The information contained in the table should be that shown in Table 1a
and 1b.
c) The list of equipment should be available for inspection by the CAA on a regular
basis.
d) Adequate declarations and reports together with appropriate technical information
should be available for inspection.
e) The equipment installed, including the operational constraints for an approved
installation, must be recorded on the modification control document. Approval for
the equipment only applies to that modification.
f) The purpose and application of the equipment should be defined for the
operational area and environment.
g) Monitoring and protection systems should be presented for approval with the
equipment.
NOTE: For the purposes of this Leaflet an approved organisation is only that
recognised under EASA Part 21, Subpart J, or BCAR Section A8-21.

30 September 2008 Part 11 Leaflet 11-31 Page 4

 Issue: Date:
CAP 562

AIRCRAFT EQUIPMENT APPROVAL

30 September 2008
NON-FLIGHT OPERATIONAL RADIO EQUIPMENT

TABLE 1a

Organisation:
EASA/CAA Approval No:

EQUIPMENT EQUIPMENT EQUIPMENT TYPE OPERATING

ITEM DDP NO. OUTPUT POWER
MANUFACTURER DESCRIPTION NO. FREQUENCY RANGE
1
2
3
4
5
6
7
8
9
10
11
12

Distribution: CAA, Ofcom

Part 11 Leaflet 11-31 Page 5

Civil Aircraft Airworthiness Information and Procedures
 Issue: Date:
CAP 562

AIRCRAFT EQUIPMENT APPROVAL

30 September 2008
NON-FLIGHT OPERATIONAL RADIO EQUIPMENT

TABLE 1b

Organisation:
EASA/CAA Approval No:

AIRCRAFT AIRCRAFT OPERATIONAL APPROVAL EXPIRY

ITEM AUTHORISED REMARKS
REGISTRATION TYPE CONSTRAINT STATUS DATE
1
2
3
4
5
6
7
8
9
10
11
12

Distribution: CAA, Ofcom

Part 11 Leaflet 11-31 Page 6

Civil Aircraft Airworthiness Information and Procedures
CAP 562 Civil Aircraft Airworthiness Information and Procedures

Leaflet 11-35 Radio Altimeters and AVADs for Helicopters

(Previously issued as AIL/0114)

PURPOSE: This Leaflet provides information and guidance concerning the installation of
Radio Altimeter activated audio voice alerting device/systems (AVAD).

REFERENCES: ANO Schedule 4 Scale EE

JAR OPS 3.660

1 Introduction

1.1 To meet the requirements of JAR OPS 3.660 and Schedule 4 Scale EE of the ANO,
certain helicopters will need to be equipped with a Radio Altimeter and display
indicator providing a voice and visual warning of descent below a pre-set height above
surface level. This Leaflet provides guidance material on complying with these
requirements.
1.2 Whilst most current Radio Altimeters include a height warning light, this is not
considered sufficient for alerting a pilot to an inadvertent descent as his attention may
be directed away from the indicator at the critical time. It is for this reason that an
audio low height warning is considered necessary. An aural tone on its own is not
considered to be acceptable. The warning must be distinguishable from other
warnings and should therefore be a clear and concise voice message.

2 Requirement and Background

Since 1 February 1986, an audio warning has been required, operating at a pre-set
height and a visual warning at a pilot selectable decision height. This is mandatory
when flying for more than a total of 3 minutes over water in any flight.
NOTE: The requirements for the audio warning were introduced into BCAR Section G by
CAA Paper G815.

3 Warning Format

3.1 In order to gain acceptance, the audio warning requires certain characteristics. They
are:
a) The warning should be unique (voice).
b) It should not be inhibited by any other audio warnings.
c) The urgency of the warning should be adequate to gain attention but not such as
to cause undue annoyance during deliberate descents through the datum height.

30 September 2008 Part 11 Leaflet 11-35 Page 1

CAP 562 Civil Aircraft Airworthiness Information and Procedures

3.2 Research activity has indicated that the characteristics above can be satisfactorily met
if the warning format incorporates the following features:
a) A unique tone should precede the voice message. A further tone after the voice
may enhance uniqueness and attention-getting without causing undue annoyance.
b) The perceived urgency of the tone and voice should be moderately urgent.
c) The message should be compact as opposed to lengthy, provided the meaning is
not compromised, e.g. ’One fifty feet’ as opposed to ’One hundred and fifty feet’.
d) An information message is preferable (e.g. ’One hundred feet’). Messages such as
’Low height’ do not convey the correct impression during deliberate descents
through the datum height.
e) Command messages (e.g. ’Pull up, Pull up’ are not acceptable unless they relate
specifically to height monitoring (e.g. ’Check height’).
f) The volume of the warning should be adequate and not variable below an
acceptable minimum value.
3.3 Every effort should be made to prevent spurious warnings.

4 Altitude Trigger

4.1 The height at which the audio warning is triggered by the radio altimeter should be
such as to provide adequate warning for the pilot to take corrective action. It is
envisaged that most installations will adopt a height in the range of 100 – 160 ft. It will
not be permissible for the datum to be altered in flight.
4.2 The pre-set height should not be set such that it will coincide with commonly used
instrument approach minima (i.e. 200 ft). Once triggered, the message must sound
within 0.5 seconds.
4.3 The voice warning should be triggered only whilst descending through the pre-set
height and be inhibited whilst ascending.

5 Approval Considerations

5.1 All Radio Altimeters shall be CAA or EASA approved in accordance with BCAR Section
A Chapter A4-10, and conform to either CAP 208 Vol. 1, Pt. 13, EUROCAE ED-30,
EASA ETSO-2087, FAA TSO C87 or RTCA DO 155.
5.2 All automatic voice alerting devices (AVAD) shall be CAA or EASA approved in
accordance with either the Accessory Procedure or Component Procedure of BCAR
Section A, Chapter A4-8 (non-EASA aircraft) or EASA Part 21 (EASA aircraft) as
applicable.

6 Installation Aspects

6.1 The airframe installation shall be approved under the modification procedures of
BCAR Chapter A2-5 (non-EASA aircraft) or EASA Part 21 (EASA aircraft) as applicable.
6.2 A single Radio Altimeter indicator is permissible provided it is usable by both pilots.
6.3 Radio Altimeters with digital only displays will not be acceptable.
6.4 A suitable ‘DH’ amber light is acceptable as satisfying the ANO requirement for a
’Visual Warning’.

30 September 2008 Part 11 Leaflet 11-35 Page 2

CAP 562 Civil Aircraft Airworthiness Information and Procedures

Leaflet 11-36 Certification and Installation of TCAS 1

Equipment and Other Similar Non-Mandatory
Collision Avoidance Systems1

(Previously issued as AIL/0186. Although this Leaflet has not been technically changed,
it has been updated and should be read in its entirety.)

PURPOSE: This Leaflet provides guidance for the certification and installation of TCAS 1
type equipment. A Flight Manual/Pilot’s Operating Handbook (POH)
supplement template is provided in Appendix 1 which, when completed,
should be submitted to the Flight Manuals and MMEL Unit, Aviation House,
Gatwick for approval. Guidance on ground and flight testing is given together
with modification classification guidelines.

REFERENCES: JAR-21 Certification Procedures for Aircraft, and Related Products & Parts
JAR-23 Normal, Utility, Aerobatic and Commuter Category Aeroplanes
JAR-27 Small Rotorcraft
JAR 29 Large Rotocraft
JAR-TSO Joint Technical Standard Order (JTSO C147 - pending issue)
FAA TSO C147
Air Navigation Order 2005 (CAP 393)
BCAR Sections A8-1, A8-2, A8-8 and A8-9
AIC 37/2006 (Yellow 199)
BCAR Section K
BCAR Section G
CAA CAP 761 - Operation of IFF/SSR Interrogators in the UK - Planning
Principles and Procedures
CAP 747 - Mandatory Requirements for Airworthiness, Generic
Requirements (GRs) Nos. 4 and 6
CAP 562 - CAAIP Leaflet 11-37

1 Introduction

This Leaflet is issued in response to the increasing demand for non-mandatory Traffic
Collision Avoidance System installations (TCAS 1 and TAS types).
These types of systems provide 'Traffic Alerts' (TA), including approximate bearing
and range information. Unlike ACAS II (TCAS II Version 7), TCAS 1 does not provide
Resolution Advisories (in the form of vertical guidance to the pilot). The BF Goodrich,
Skywatch System is similar in operation to TCAS 1 and for the purposes of this Leaflet
it may be considered a TCAS 1 type system.

1. Excludes passive Collision Avoidance Systems that do not transmit signals in order to interrogate nearby SSR trans-
ponders, and ACAS II systems (carriage of ACAS II is mandatory for certain aircraft). The term Traffic Advisory Sys-
tem (TAS) may also be used to describe TCAS 1 'type' systems.

31 August 2006 Part 11 Leaflet 11-36 Page 1

CAP 562 Civil Aircraft Airworthiness Information and Procedures

The guidance provided in this Leaflet is intended to assist the design organisation,
maintenance organisation and aircraft operators to determine the certification
considerations required to demonstrate compliance with the applicable airworthiness
requirements. This Leaflet also provides some guidance on the installation
considerations.

2 Airworthiness Approval

When assessing the installation of TCAS 1 installations the following needs to be

considered:
2.1 Equipment Approval Issues
TCAS 1 type systems are not required to be installed on an aircraft to meet any
airspace or operational requirement. These systems do, however, transmit and
receive radio signals and therefore the equipment must be CAA approved or have a
JTSO authorisation, before installation on an aircraft.
2.2 Power Supply Considerations
The equipment should not be connected to the aircraft's emergency or battery
supported busbar.
2.3 Performance Considerations
Good bonding and positioning of the TCAS 1 antenna(s) is essential to ensure correct
operation of the system, and non interference to other aircraft systems.
The performance demonstration needs to include appropriate ground testing and
possible flight evaluation. The ground test should demonstrate correct bearing and
range of targets in each quadrant. An EMC (Electromagnetic Compatibility) test
should be performed to ensure that the installed system does not affect existing
aircraft systems. A flight evaluation is at the discretion of the installer, and may be
conducted using targets of opportunity to confirm the correct operation of the
system.
2.4 Flight Manual/Pilot’s Operating Handbook (POH)
The modification will require a Flight Manual/Pilots Operating Handbook (POH)
Supplement which will need to address, at least, the following:
Limitations:
Navigation must not be predicated on the use of the TCAS 1 display.
Normal Procedures:
If a 'Traffic Alert' (TA) is received, the pilot should not initiate a manoeuvre based on
the display alone, without first visually acquiring the target .
Emergency Procedures:
None
Abnormal Procedures:
None
Performance:
None
A Flight Manual/Pilot’s Operating Handbook (POH) Supplement template for a
'typical' TCAS 1 type installation is contained in Appendix 1 to this Leaflet.

31 August 2006 Part 11 Leaflet 11-36 Page 2

CAP 562 Civil Aircraft Airworthiness Information and Procedures

The Design Organisation should submit the Flight Manual/Pilot’s Operating Handbook
(POH) Supplement, as detailed in Appendix 1, duly completed, to the Flight Manuals
and MMEL Unit, Aviation House, Gatwick for approval.
Guidance on the compilation of a Flight Manual/Pilot’s Operating Handbook (POH)
supplement is provided in Appendix 2 to this Leaflet.
2.5 Electrical Load Analysis
The installation of TCAS 1 will affect the Electrical Load Analysis, and may affect
compliance with CAP 747 GR Nos. 4 and 6. Continued compliance with these GRs
will therefore need to be demonstrated.
2.6 Structural Analysis
A structural analysis of the installation, including the TCAS antenna(s) and their
mountings must be conducted.

3 Classification of Modification

A TCAS 1 type installation may be classified as MINOR provided the following

conditions are satisfied:
a) The company applying for the modification holds an 'E2' CAA Design Approval and
their scope of approval supports this type of work (see Note 1)
b) The Flight Manual/Pilot’s Operating Handbook (POH) Supplement requires no
additional limitations, other than those listed in the Flight Manual/Pilot’s Operating
Handbook (POH) Supplement template given in Appendix 1.
c) There is no effect to the existing instruments on the Flight Deck, by installation of
the Traffic Display. For example, if the Traffic Display displaces another
instrument, causing an overall change to the flight deck, an assessment of the
flight deck will be required by Flight Department. Also, if the Traffic Display is
located outboard of the main instrument panel by means of a bracket, or if it is
located on the glare shield, a Flight Department assessment may be required.
d) Interfacing of TCAS 1 with existing onboard sensors does not introduce possible
failures to existing aircraft systems. An assessment may be required if existing
systems are affected. Example: failure (signal grounded) of an altitude input to
TCAS 1. If this input also supplies altitude information to other aircraft systems, a
failure introduced by TCAS 1 could affect existing aircraft systems. (Pilot’s display
of barometric height could be affected, transponder output of Mode C Altitude
could be affected).
e) TCAS 1 aurals do not inhibit any other aurals.
NOTE: The time taken to assess the modification documents provided by a non 'E2'
CAA Design Approved Organisation is likely to exceed one hour of a
Surveyor’s time, therefore a minor classification is not appropriate.

4 Approval to Operate an IFF/SSR Interrogator

All TCAS 1 or TAS systems that transmit interrogation signals on 1030 MHz require a
separate approval to operate from the National IFF/SSR Committee. Operators should
obtain such an approval prior to commencing installation and flight trials. Applicants
should note that although there is currently no charge, TCAS 1 approvals can take up
to 4 months to process. Further details can be found in AIC 37/2006 (Yellow 199),

31 March 2009 Part 11 Leaflet 11-36 Page 3

CAP 562 Civil Aircraft Airworthiness Information and Procedures

TCAS I Systems Approvals Policy, and in CAP 761, Operation of IFF/ISSR

Interrogators in the UK: Planning Principles and Procedures. Enquiries and
applications for approval should be submitted to:
NISC Secretariat
K6 G6
CAA House
45-59 Kingsway
London WC2B 6TE
Tel. 020 7453 6536
E-mail: nisc@dap.caa.co.uk
For Airworthiness certification aspects, further information may be obtained from:
Engineering Department
Aviation House
Gatwick Airport South
West Sussex
RH6 0YR
Tel. 01293 57 3132
For Flight Manual/Pilot’s Operating Handbook (POH) and MMEL aspects, further
information may be obtained from:
Flight Manuals and MMEL Unit
Aircraft Certification Department
Aviation House
Gatwick Airport South
West Sussex
RH6 0YR.
Tel. 01293 57 3187 or 01293 57 3189.

31 March 2009 Part 11 Leaflet 11-36 Page 4

CAP 562 Civil Aircraft Airworthiness Information and Procedures

Appendix 1

TEMPLATE FOR TCAS 1

FLIGHT MANUAL SUPPLEMENT/PILOT'S OPERATING HANDBOOK (POH)

<<Aircraft Type>> Flight Manual (or POH as appropriate) Reference <<XXXX>>

<<Company Name>>
FLIGHT MANUAL/PILOT’S OPERATING HANDBOOK (POH) SUPPLEMENT
<<x>> ISSUE <<y>>

Registration Mark:..................... Serial Number ...........................

TCAS 1
Modification Number <<XXXX>>
ADDITIONAL LIMITATIONS AND INFORMATION FOR CERTIFICATION

The limitations and information contained herein either supplement or, in

the case of conflict, override those in the Flight Manual/Pilot’s Operating
Handbook (POH).

LIMITATIONS
Navigation must not be predicated on the use of the (insert name of TCAS 1 type
system) display.
If a 'Traffic Alert' (insert aural message here, for example 'Traffic, Traffic') is received,
the pilot should not initiate a manoeuvre based on the display alone, without first
visually acquiring the target.
NORMAL PROCEDURES
The normal procedures specified in the Basic Flight Manual remain applicable.
EMERGENCY PROCEDURES
None
ABNORMAL PROCEDURES
None
PERFORMANCE
None

To be inserted in the Flight Manual/Pilot’s Operating Handbook (POH) and

the record sheet amended accordingly.
Page 1 of CAA Approval Date:

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CAP 562 Civil Aircraft Airworthiness Information and Procedures

Appendix 2

NOTES ON THE PRODUCTION OF FLIGHT MANUAL / PILOT’S OPERATING

HANDBOOK (POH) SUPPLEMENT

a) The supplement should be written to fit the size and style of the Flight Manual/Pilot’s
Operating Handbook (POH) supplied by the aircraft manufacturer and to which it
refers, preferably without resorting to photo-reduction.
b) A company logo can be included if desired.
c) The supplement must be uniquely identifiable within the referenced Flight Manual/
Pilot’s Operating Handbook (POH).
d) A log of supplements should already be provided in the front of the manual/handbook.
This log should be amended to reflect the additional supplement. Where no log of
supplements exists, the design organisation/installer will provide one.
e) Aircraft identification (Registration etc.) will be added to the copy which goes in the
aircraft copy of the Flight Manual/Pilot’s Operating Handbook (POH). Where several
aircraft on the same Flight Manual/Pilot’s Operating Handbook (POH) document have
the same equipment, copies of the same Flight Manual/Pilot's Operating Handbook
Supplement may be issued to each aircraft and annotated with the aircraft's
identification accordingly.
f) If a supplement is submitted for approval for a specific aircraft registration and/or
serial number, the supplement will only be approved for that particular aircraft.
g) Any information contained in the system users manual that addresses: the system's
Limitations, Normal Procedures, Emergency Procedures, Abnormal Procedures and/
or Performance, should be detailed in the Flight Manual/Pilot’s Operating Handbook
(POH). Provision of this information in the Flight Manual/Pilot’s Operating Handbook
(POH) by referencing the system's users manual should also be carried out with the
guidance contained in AC 25.1581-1 & AMJ 25.1581.
h) When approved, one copy of the supplement should be placed, as appropriate in the
aircraft's Flight Manual/Pilot's Operating Handbook.

31 August 2006 Part 11 Leaflet 11-36 Appendix 2 Page 1

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CAP 562 Civil Aircraft Airworthiness Information and Procedures

Leaflet 11-37 Structural Attachment of Aerials

(Previously issued as AIL/0025)

PURPOSE: This Leaflet provides information on the procedure to be adopted when

fitting aerials to aeroplanes and helicopters.

REFERENCES: BCAR/JAR/FAR/CS Design and Construction Codes

Several instances have been reported of aircraft skin cracking as a result of

inadequate reinforcement of structure following the fitting of blade type aerials. In
one instance the cracking extended to include frame, stringer and doubler.
Installers must ensure when fitting aerials that adequate structural strength is
provided. Where airframe manufacturer’s modification schemes are not utilized, the
extent of the structural substantiation necessary, should be discussed with the
appropriate Regional Office Surveyor.
It should be noted that the aerials of different manufacturers vary in design and that
together with the different aerial locations on the aircraft, varying mounting
techniques will be required to ensure adequate structural strength is achieved.

31 August 2006 Part 11 Leaflet 11-37 Page 1

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CAP 562 Civil Aircraft Airworthiness Information and Procedures

Leaflet 11-38 A Simplified Means of Approval for Airframe

Structural Repairs Design

(Previously issued as AIL/0180)

PURPOSE: To provide information on the procedures acceptable to the CAA for approval
for airframe structural repair design on aircraft operating under CAA
Regulatory Approval (i.e. Annex II to EU Regulation (EC) No. 216/2008.

REFERENCES: BCAR Section A and B Chapter 5-3 paragraph 2.1

BCAR A and B Chapter 6-7 paragraph 2.1.1
CAP 562 Leaflet 1-1, Appendix 2

1 Introduction

A revised and simplified means of repair design approval has been developed
following a review of the procedures within the Airworthiness Division. The
procedure places more reliance on repair approval granted by foreign regulatory
authorities and does not necessitate a change to any requirement. For the purposes
of this document, 'foreign' means non-UK.

2 Background

There are currently two chapters within BCAR A and B that define the CAA's
requirements on repair design approval to aircraft.
a) BCAR Section A and B Chapter 5-3 paragraph 2.1 allows manuals containing
information necessary for the repair of aircraft, such as the Structural Repair
Manual (SRM), to be certified and published under the authority of the appropriate
Approved UK Type Design Organisation (TDO) or in the case of foreign TDOs,
under the local regulatory process. Repairs in the SRM, therefore, do not need to
be approved directly by the CAA, nor do amendments to the SRM. There has been
no change to this procedure.
b) BCAR Section A and B Chapter 6-7 paragraph 2.1.1 requires that repairs shall
be carried out in accordance with .... ’the approved Manuals, drawings and
schedules related thereto, and any other documents required or recognised by
the CAA.’ In this context ’approved’ means certified by the UK TDO, or in the case
of foreign TDOs, under the local regulatory process.
The change to the CAA's procedure is in the interpretation of the bold text above.

3 Revised Procedure

It is now the intention that, for repairs designed by the TDO, a document approved
under the local regulatory process is considered by the CAA as ’...documents.....
recognised by the CAA.’

31 March 2009 Part 11 Leaflet 11-38 Page 1

CAP 562 Civil Aircraft Airworthiness Information and Procedures

Repairs designed by foreign and domestic TDOs need to be considered separately:

• Repairs of Foreign TDO origin. Where the repair has been designed by the
foreign TDO responsible for the type, documentation for the repair approved under
the local regulatory process (e.g. on behalf of the FAA by the US TDO Designated
Engineering Representative (DER) using the FAA Form 8110-3) will be considered
as a recognised document in accordance with BCAR B6-7, paragraph 2.1.1.
• Other foreign repairs. Where the repair has been designed by a foreign
organisation that is not the TDO for the type and has been approved under the local
regulatory process, it will need to be investigated by the CAA. However,
appropriate credit will be given for the domestic certification in the CAA validation
process. STC holders fall under this category.
• Repairs of UK TDO origin. As the CAA is the local regulatory authority, all repairs
may be processed under the normal BCAR Section A procedures. However, as an
alternative, if the UK TDO wishes to avoid the potential delay associated with
seeking CAA approval of each repair, repairs may be associated with the SRM.
Such associated repairs may be certified under the authority of the TDO (see BCAR
A5-3 paragraph 2), providing the TDO's Terms of Approval permit the design of
repairs and there are applicable procedures referenced in the Company's
Exposition. Note that these associated repairs must be subject to the same
airworthiness controls as the SRM.
• Other UK repairs. For UK Approved Design Organisations who are not TDO, and
who are taking full design responsibility for the repair, the current procedures of
BCAR A2-5 still apply.

4 General Points

Apart from the normal auditing of the UK TDO, the CAA reserves the right to directly
investigate any repair from the TDO (UK or foreign) in exceptional circumstances.
Examples of this might be:
• if survey of an aircraft raises questions about a repair's suitability;
• if the repair is novel or very extensive;
• if the repair is found to conflict with the applicable CAA requirements.
Repairs may be approved and aircraft released to service while awaiting any required
damage tolerance evaluation. Up to a 12 month period for evaluation to be completed
and for incorporation into the Aircraft Maintenance Schedule (AMS) is acceptable.
There must be a procedure for any resulting inspections to be placed in the AMS.
Under normal circumstances aircraft would not be released into service without the
requisite approval documentation being in place. This would include documents such
as 8110-3 or Repair Assessment Sheet (RAS), but not a 'No Technical Objection'
(NTO).
A statement of 'No Technical Objection' from the TDO does not constitute approval
of a repair, although this may be necessary supporting documentation for repair
approval.

5 Repairs to Aircraft Operating under EASA Design Control

Reference should be made to CAP 562 Leaflet 1-1, Appendix 2 - Acceptable Data for
use by Part-145 Organisations.

31 March 2009 Part 11 Leaflet 11-38 Page 2

CAP 562 Civil Aircraft Airworthiness Information and Procedures

Leaflet 11-39 Propellers Approved for use on Civil Aircraft

Manufactured in the United Kingdom

(Previously issued as AN 4)
1 Propellers listed in the attached Appendix are approved for use on civil aircraft
manufactured in the United Kingdom with Certificates of Airworthiness issued by the
Civil Aviation Authority. In addition, for those aircraft types which have a current Civil
Aviation Authority Type Certificate Data Sheet (TCDS), that TCDS should be consulted
for details of approved propellers. For aircraft designated as EASA aircraft in CAP 747,
the EASA TCDS, if issued, should be consulted.
NOTE: Propellers listed in this Leaflet also include those which have been approved for
aircraft certificated in the Special Category only, and it would therefore be wrong to
assume that the aircraft listed against a propeller type will automatically qualify for
certification in other Categories with that propeller fitted.
2 For convenience, propellers are listed under types of engines, but each propeller is
approved only for the specific engine-airframe combination shown.
3 Propellers manufactured after the date of this Leaflet to the same drawing numbers
as those given in the attached list may, in addition, bear certain issue numbers. These
issue numbers are used mainly to indicate minor modifications which do not affect
safety, but in some cases the intention is to indicate changes in pitch or diameter. In
addition, propellers manufactured by other appropriately approved organisations are
accepted, provided it is shown that manufacture is in accordance with the relevant
drawing requirements.
3.1 Where an issue number has been used to indicate a minor modification and the pitch
and diameter remain the same as against the drawing number shown in this list, it
may be assumed that the propeller is approved.
3.2 Where an issue number has been used to indicate a change in pitch or diameter and
either of these differ from the figures given in the attached list, the propeller is not
approved unless it actually appears in this list.
4 Before fitting a variable-pitch propeller it is essential to ensure that the basic pitch-
range setting conforms with the latest setting approved for the particular engine-
airframe combination.
5 The pitch quoted is that measured at the radius defined by the manufacturer. Usually
this is at 70% or 71% of radius, although in some cases it is at 75%.
6 On 28 September 2003, responsibility for approval of new engine/propeller
combinations for non-Annex II aircraft passed to EASA. The EASA website
www.easa.eu.int should be consulted for information concerning any approvals
issued for these aircraft after this date. If it is desired to use an unapproved propeller,
application for approval should be made in accordance with the procedure prescribed
in Chapter A4-4 of British Civil Airworthiness Requirements, for Annex II aircraft, or to
EASA for non-Annex II aircraft.
7 For propellers approved for imported aircraft of foreign origin, reference should be
made to the appropriate publications issued by the Airworthiness Authority
concerned, or the relevant manufacturer. Information may also be obtained from the
Civil Aviation Authority, Safety Regulation Group.

31 March 2009 Part 11 Leaflet 11-39 Page 1

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CAP 562 Civil Aircraft Airworthiness Information and Procedures

Appendix 1

(Previously issued as AN 4, Appendix 1)

Drawing No. Diam. Pitch Aircraft

(ft) (ft)

ARDEM X
Z3405 .. .. .. .. .. . 4.75 2.45 Turbulent, Nipper 3
Z3407 .. .. .. .. .. . 4.75 2.7 Turbulent
HR1201 .. .. .. .. .. . 4.75 2.45 Turbulent, Nipper 3
ASTAZOU XIIH and H1
FH 76-2-07 . .. .. .. .. . 8.2 VP Skyvan Mk. 2
CHEETAH 15, 17 and 27
CR30/242/1 .. .. .. .. . 8.25 VP Avro 19
CR30/242/4 .. .. .. .. . 8.25 VP Avro 19
CHEETAH 19
61271A/X3 . .. .. .. .. . 7.50 7.10 Anson
A66365 . . .. .. .. .. . 7.50 7.10 Anson
CIRRUS MAJOR 2
A66290/XI . .. .. .. .. . 7.00 4.58 Cygnet
LA520 . . . .. .. .. .. . 6.67 4.59 Cygnet
Z974/1 .. .. .. .. .. . 6.23 5.26 M.18
CIRRUS MAJOR 3
A66290/X1 . .. .. .. .. . 7.00 4.58 Messenger
A66290/X6 . .. .. .. .. . 7.00 4.98 M.18
A66670/X1 . .. .. .. .. . 6.75 4.82 Messenger
A66697/X6 . .. .. .. .. . 6.75 4.97 Auster J.5.G, Auster J.5.K, Messenger
A66697/X7 . .. .. .. .. . 6.75 4.50 Auster J.5.G
A66940/X1 . .. .. .. .. . 6.00 6.66 Aries
B67869/X1 . .. .. .. .. . 6.96 4.58 Messenger
B67921/X1 . .. .. .. .. . 6.67 4.50 Auster J.5.G, Messenger
B67941/X1 . .. .. .. .. . 6.67 4.97 Auster J.5.G, J.5.K
B67971/X1 . .. .. .. .. . 6.50 4.99 Auster J.5.G
C67975/X1 . .. .. .. .. . 6.92 4.58 Messenger
C67999/X1 . .. .. .. .. . 6.83 4.76 Messenger 2A
HR669 .. .. .. .. .. . 6.84 3.53 Messenger
LA520 .. .. .. .. .. . 6.67 4.59 Cygnet
Z3756 .. .. .. .. .. . 6.30 5.15 Messenger
Z6013 .. .. .. .. .. . 6.67 4.51 Blackburn B2, Messenger
Z6014 .. .. .. .. .. . 6.67 4.70 Messenger

30 September 2008 Part 11 Leaflet 11-39 Appendix 1 Page 1

CAP 562 Civil Aircraft Airworthiness Information and Procedures

Drawing No. Diam. Pitch Aircraft

(ft) (ft)
CIRRUS MINOR I
A66580/X6 . . . .. .. .. . 6.00 4.28 Auster 5.J.4, Taylorcraft 'C' and 'D'
B67936/X2 . . . .. .. .. . 5.92 4.28 Taylorcraft 'D'
C66897/X3 . . . .. .. .. . 5.88 4.28 Taylorcraft 'D'
H020-178-120L . .. .. .. . 5. 83 3.9 Auster 5.J.4
H020-183-105L . .. .. .. . 6.00 3.44 Auster 5.J.4
LA505 .. .. .. .. .. . 5.87 3.38 Auster 5.J.4, B.A. Swallow 2, Taylorcraft
'C' and 'D'
LA544 .. .. .. .. .. . 5.88 4.15 Mosscraft M.A.2
LA617 .. .. .. .. .. . 6.65 2.75 Taylorcraft 'D'
N209 . .. .. .. .. .. . 5.87 3.38 B.A. Swallow 2
Z5701 .. .. .. .. .. . 5.50 4.78 Taylorcraft 'D'
Z8020 .. .. .. .. .. . 5.87 4.27 B.A. Swallow 2, Taylorcraft 'D'
Z8022 .. .. .. .. .. . 6.00 3.62 Auster 5.J.4, Taylorcraft 'C' and 'D', B.A.
Swallow 2
CIRRUS MINOR II & IIA
A66580/X1 . . . .. .. .. . 6.00 4.61 Auster 5.J.1
A66580/X2 . . . .. .. .. . 6.00 4.52 Auster 5.J.1
A66619/X1 . . . .. .. .. . 5.75 5.22 Gemini
A66619/X2 . . . .. .. .. . 5.75 5.09 Gemini
A66619/X4 . . . .. .. .. . 5.75 4.93 Gemini
A66619/X6 . . . .. .. .. . 5.75 4.79 Auster 5.J.1, Gemini
A66859/X2 . . . .. .. .. . 5.50 5.46 Gemini
A66929 . . . . .. .. .. . 5.75 5.22 Gemini
B66883/X1 . . . .. .. .. . 5.86 4.52 Auster 5.J.1
B67858/X2 . . . .. .. .. . 5.75 4.79 Auster 5.J.1
B67859/X1 . . . .. .. .. . 5.87 4.60 Auster 5.J.1
B67992/X1 . . . .. .. .. . 5.73 4.74 Auster 5.J.1
B67933/X1 . . . .. .. .. . 5.73 4.78 Auster 5.J.1
B67936/X1 . . . .. .. .. . 5.92 4.52 Auster 5.J.1
B67943/X1 . . . .. .. .. . 5.73 4.74 Auster 5.J.1
B67944/X1 . . . .. .. .. . 5.75 4.74 Auster 5.J.1
B67987/X1 . . . .. .. .. . 5.67 4.74 Auster 5.J.1
B67990/X1 . . . .. .. .. . 5.92 4.52 Auster 5.J.1
C66631/X1 . . . .. .. .. . 5.75 4.66 Auster 5.J.1
C66897/X1 . . . .. .. .. . 5.88 4.52 Auster 5.J.1
C66897/X2 . . . .. .. .. . 5.88 4.84 Auster 5.J.1
C66897/X3 . . . .. .. .. . 5.88 4.28 Auster 5.J.1
C66914/X1 . . . .. .. .. . 5.67 5.22 Gemini
C66934/X1 . . . .. .. .. . 5.83 4.52 Auster 5.J.1
C67891/X1 . . . .. .. .. . 5.94 4.52 Auster 5.J.1
FP400/2A-1 and -2 .. .. .. . 5.42 5.07 Gemini, Auster 5.J.1
HR702 .. .. .. .. .. . 5.75 3.97 Auster 5.J.1
HR702/2 . . . . .. .. .. . 5.75 4.11 Auster 5.J.1
HR724 .. .. .. .. .. . 5.42 5.07 Gemini
HR1241 . . . . .. .. .. . 6.00 4.04 Auster 5.J.1

30 September 2008 Part 11 Leaflet 11-39 Appendix 1 Page 2

CAP 562 Civil Aircraft Airworthiness Information and Procedures

Drawing No. Diam. Pitch Aircraft

(ft) (ft)
CIRRUS MINOR II & IIA (continued)
H020-178-120L . .. .. .. . 5.83 3.9 Auster 5.J.1
H020-183-105L . .. .. .. . 6.00 3.44 Auster 5.J.1
Z5435 .. .. .. .. .. . 5.50 4.65 Gemini
Z5641 . . . . . .. .. .. . 6.00 4.04 Auster 5.J.1
Z5642 .. .. .. .. .. . 6.00 4.04 Auster 5.J.1
Z5646 .. .. .. .. .. . 6.00 4.04 Auster 5.J.1
Z5647 .. .. .. .. .. . 6.00 4.04 Auster 5.J.1
Z5701 .. .. .. .. .. . 5.50 4.78 Auster 5.J.1, Gemini
Z5702 .. .. .. .. .. . 5.50 4.78 Gemini
Z5704 .. .. .. .. .. . 5.50 5.06 Gemini
Z5705 .. .. .. .. .. . 5.25 5.02 Gemini
Z5801 .. .. .. .. .. . 5.64 3.83 Auster 5.J.1
CONTINENTAL C75
1188/3 .. .. .. .. .. . 6.33 3.48 Auster 5.J.2
1188/4 .. .. .. .. .. . 6.33 3.29 Auster 5.J.2
1188/5 .. .. .. .. .. . 6.00 3.29 Auster 5.J.2
Z5750 .. .. .. .. .. . 5.75 3.97 Auster 5.J.2
Z5751 .. .. .. .. .. . 6.00 3.22 Auster 5.J.2
CONTINENTAL C125
FP422 .. .. .. .. .. . 5.67 5.65 Gemini
FP422/2 .. .. .. .. .. . 5.67 5.33 Gemini
HR728 .. .. .. .. .. . 5.67 5.33 Gemini
CONTINENTAL O-200
F-H2/LC14-183 110 7R .. .. . 6.00 3.6 Linnet
HR1211 . . . . . . .. .. . 5.75 3.2 Auster J.4, Condor
HR1212 . . . . . . .. .. . 5.75 3.2 Auster J.4, Condor
Z5792 .. .. .. .. .. . 5.75 3.97 Linnet
Z5793 .. .. .. .. .. . 5.75 3.2 Auster J.4, Condor
R. R. CONTINENTAL O-200A
1A101/DCM-69-52 .. .. .. . 5.75 4.33 Linnet
1A105/SCM/7053 .. .. .. . 6.84 4.42 Beagle B121
D11/28/7C . . . .. .. .. . 5.76 4.13 Auster J.4
Z5723 .. .. .. .. .. . 5.1 4.78 Linnet
Z5794 .. .. .. .. .. . 5.75 3.7 Linnet
HR1211 . . . . .. .. .. . 5.75 3.2 Auster J.4, Condor
HR1212 . . . . .. .. .. . 5.75 3.2 Auster J.4, Condor
R. R. CONTINENTAL O-240A
HR1631 . . .. .. .. .. . 5.83 4.16 Condor
HR1633 . . .. .. .. .. . 5.83 4.00 Condor
1C172/EM . .. .. .. .. . 6.00 4.08 Condor

30 September 2008 Part 11 Leaflet 11-39 Appendix 1 Page 3

CAP 562 Civil Aircraft Airworthiness Information and Procedures

Drawing No. Diam. Pitch Aircraft

(ft) (ft)
CONTINENTAL GIO-470
2AF36C68/100 RFM-10 . . .. . 7.50 VP Beagle B.206Y
R. R. CONTINENTAL GIO-470
2AF36C68/100 RFM-10 to -12 . . . 7.50 VP Beagle B.206 Series 1
CONTINENTAL GTSIO-520-C
3AF34C86/90LF .. .. .. . 7.5 VP Beagle B206 Series 2
HC-A3VF/2/V8833 .. .. .. . 7.37 VP Beagle B206 Series 2
DART 514
CR201/4-30-4/20 .. .. .. . 12.00 VP HS 748 Series 1
DART 531 and 531U
CR212/4-30-4/22 .. .. .. . 12.00 VP HS 748 Series 2
DART 532, 532-2S and 532-2L
CR212/4-30-4/22 .. .. .. . 12.00 VP HS 748 Series 2A
DART 532-2L, 532-2S, 533-2, 534-2, 535-2 and 536-2T
CR212/4-30-4/22 .. .. .. . 12.00 VP HS 748 Series 2 and 2A
DART 533-2
CR212/4-30-4/22 .. .. .. . 12.00 VP HS 748 Series 1
DART 534-2, 535-2 and 536-2
CR212/4-30-4/22 .. .. .. . 12.00 VP HS 748 Series 2B
CR251/4-30-4/49 .. .. .. . 12.00 VP HS 748 Series 2B
GIPSY 1
DH5180/5 . .. .. .. .. . 6.33 5.08 DH.60G
GIPSY 2
DH5180/14 .. .. .. .. . 6.33 5.00 DH.60G
GIPSY 3
67104A/X2 . .. .. .. .. . 7.00 5.10 DH.80A
67104A/X12 .. .. .. .. . 7.00 5.18 DH.80A
DH5212/D . .. .. .. .. . 6.17 5.42 DH.80A
DH5218/C . .. .. .. .. . 6.50 5.16 DH.80A
E860/1 .. .. .. .. .. . 6.87 4.26 Blackburn B2
LA520 .. .. .. .. .. . 6.67 4.59 DH.80A
LA543 .. .. .. .. .. . 7.00 4.00 Blackburn B2
GIPSY MAJOR (AUSTER 3)
DH5220/P25 .. .. .. .. . 6.33 4.58 Auster 3
LA596 .. .. .. .. .. . 6.50 5.00 Auster 5.c
61187A/X11 .. .. .. .. . 6.75 5.18 Hawk Trainer

31 March 2009 Part 11 Leaflet 11-39 Appendix 1 Page 4

CAP 562 Civil Aircraft Airworthiness Information and Procedures

Drawing No. Diam. Pitch Aircraft

(ft) (ft)
GIPSY MAJOR 1
5232/A/1. . . .. .. .. .. . 6.50 5.10 DH.83
61187A/X1 . .. .. .. .. . 6.75 5.50 Hawk Trainer, Whitney Straight
61187A/X9 . .. .. .. .. . 6.75 5.24 Falcon, Monarch
61326A/X1. .. .. .. .. . 6.17 5.92 DH.85, Whitney Straight
61326A/X2 . .. .. .. .. . 6.17 5.56 Whitney Straight
61326A/X4 . .. .. .. .. . 6.17 6.58 DH.85
61326A/X8 . .. .. .. .. . 6.17 6.01 DH.85, Whitney Straight, DH.87B
61326A/X9 . .. .. .. .. . 6.17 5.72 Monarch, Whitney Straight
61326A/X10 .. .. .. .. . 6.17 5.85 Whitney Straight
61414A/X2 . .. .. .. .. . 6.58 5.65 DH.85
67104A/X2 . .. .. .. .. . 7.00 5.10 DH.80A, DH.83, DH.85
67104A/X3 . .. .. .. .. . 7.00 4.95 DH.87B
67104A/X4 . .. .. .. .. . 7.00 4.77 DH.82A, DH.83, DH.85, DH.87B
67104A/X6 . .. .. .. .. . 7.00 5.33 DH.80A, DH.83, DH.85
67104A/X7 . .. .. .. .. . 7.00 4.71 DH.87B
67104A/X10 .. .. .. .. . 7.00 4.60 DH.82A, DH.83, DH.85, DH.87B
67104A/X11 .. .. .. .. . 7.00 5.52 DH.85
67104A/X12 .. .. .. .. . 7.00 5.18 DH.85, DH.87B, DH.82A
67104A/X13 .. .. .. .. . 7.00 5.40 DH.85
67104A/X14 .. .. .. .. . 7.00 4.52 DH.82A, DH.83, DH.85
67104A/X15 .. .. .. .. . 7.00 5.01 DH.85
67575A/X1 . .. .. .. .. . 7.00 4.71 DH.82A
84723A/X1 . .. .. .. .. . 7.00 4.84 DH.82A, DH.87B
94103A/X17 .. .. .. .. . 6.75 4.80 Falcon
A66016/X4 . .. .. .. .. . 7.00 4.58 DH.82A
A66696/X1 . .. .. .. .. . 6.75 4.83 Auster 5.J.1.B; J.1.N; 5.J.5; J.5.B; J.5.F;
J.5.Q; 5D; 3
A66696/X3 . .. .. .. .. . 6.75 4.67 Auster 5.J.1.B; 5.J.5; J.1.N; J.5.B
A66753/X1 . .. .. .. .. . 6.75 5.01 Auster J.1.N, DH.82A
A66772/X2 . .. .. .. .. . 6.50 5.00 Auster J.5.B
A66860/X1 . .. .. .. .. . 6.50 5.66 Auster 5.C
A66911/X3 . .. .. .. .. . 6.00 5.77 Hawk Trainer
A66938/X2 . .. .. .. .. . 7.50 3.52 DH.82A, Jackaroo
A104940/X2 .. .. .. .. . 7.42 3.52 DH.82A, Jackaroo
A104940/X3 .. .. .. .. . 7.42 3.70 DH.82A
A104941/X2 .. .. .. .. . 7.34 3.56 Jackaroo
A104942/X2 .. .. .. .. . 7.25 3.59 Jackaroo
A104943/X2 .. .. .. .. . 7.17 3.75 Jackaroo
A104943/X3 .. .. .. .. . 7.17 3.62 DH.82A, Jackaroo
A104944/X2 .. .. .. .. . 7.09 3.62 Jackaroo
A104945/X2 .. .. .. .. . 7.00 3.60 Jackaroo
B66131/X1 . .. .. .. .. . 5.92 5.92 Monarch
B66143/X1 . .. .. .. .. . 6.74 5.49 DH.85, DH.87B
B66143/X2 . .. .. .. .. . 6.74 4.69 DH.82A
B66980/X1 . .. .. .. .. . 6.58 5.24 Falcon, Monarch
B67926/X1 . .. .. .. .. . 6.42 4.80 Auster 5.J.5; 5.J.1.B; J.5.B

30 September 2008 Part 11 Leaflet 11-39 Appendix 1 Page 5

CAP 562 Civil Aircraft Airworthiness Information and Procedures

Drawing No. Diam. Pitch Aircraft

(ft) (ft)
GIPSY MAJOR 1 (continued)
B67927/X2 . .. .. .. .. . 6.92 4.60 DH.87B
B67940/X1 . .. .. .. .. . 6.57 3.83 Auster 5D
B67995A/XI .. .. .. .. . 6.33 5.12 Auster J.5.F
B104952/X1 .. .. .. .. . 6.92 4.07 Jackaroo
B104952/X2 .. .. .. .. . 6.92 3.95 Jackaroo
B104956/X1 .. .. .. .. . 6.30 5.12 Auster 5.J.1.B; J.1.N; 5.J.5; J.5.B; J.5.F;
J.5.Q; 5D; 3
B104977/X1 .. .. .. .. . 6.37 5.12 Auster J.5.F
BA211/2 . . .. .. .. .. . 6.18 5.41 Whitney Straight
C66969/X1 . .. .. .. .. . 5.92 4.50 DH.82A, DH.87B
C67887/X1 . .. .. .. .. . 6.63 4.83 Auster 5.J.1.B; J.1.N; 5.J.5; J.5.B; J.5.F;
J.5.Q; 5D; 3
C67927/X1 . .. .. .. .. . 6.92 5.18 DH.87B
DH5180/14/21 .. .. .. .. . 6.33 5.00 Auster 5D
DH5200/M . .. .. .. .. . 6.33 4.50 Auster J.1.N; J.1.B; J.5
DH5208/C/2 .. .. .. .. . 6.33 4.92 DH.80A
DH5212/A . .. .. .. .. . 6.17 5.25 DH.90A
DH5212/C . .. .. .. .. . 6.17 5.17 DH.84
DH5212/D . .. .. .. .. . 6.17 5.42 Whitney Straight, DH.80A, DH.82A,
DH.84, DH.90A
DH5212/G . . . .. .. .. . 6.17 5.14 DH.84
DH5218/B . . . .. .. .. . 6.50 5.10 DH.80A, DH.82A, DH.84
DH5218/BX/10 . . .. .. .. . 6.50 5.10 DH.83
DH5220/B . . . .. .. .. . 6.33 5.08 DH.82A
DH5220/G . . . .. .. .. . 6.33 4.58 DH.82A, DH.83
DH5220/H . . . .. .. .. . 6.33 4.92 Auster J.1.N., DH.82A, DH.83, DH.84
DH5220/L . . . .. .. .. . 6.33 4.75 DH.82A, Auster 5D, 5.J.5., 5.J.1.B
DH5220/M . . . .. .. .. . 6.33 4.50 DH.82A, Auster 5D, 5.J.1.B, 5.J.5, J.1.N
DH5220/P . . . .. .. .. . 6.33 4.58 Auster 3; 5.D; 5.J.1.B; 5.J.5; J.1.N; J.5B;
DH.60G; DH.82A; DH.87B
DH5220/B (Poncelet) . .. .. . 6.33 5.08 DH82A
DH5220/G (Poncelet) . .. .. . 6.33 4.58 DH82A
DH5220/H (Poncelet) . .. .. . 6.33 4.92 DH82A
DH5220/L (Poncelet) . .. .. . 6.33 4.75 DH82A
DH5220/M (Poncelet). .. .. . 6.33 4.50 DH82A
DH5220/P (Poncelet) . .. .. . 6.33 4.58 DH82A
DH5228A . . . . . . .. .. . 6.00 5.25 DH.84
DH5228/B . . . . . .. .. . 6.00 5.12 DH.84
DH5230/H. . . . . . .. .. . 6.33 4.92 Auster J.1.N
DH5232/A. . . . . . .. .. . 6.50 5.10 DH.80A, DH.82A, DH.83, DH.84, DH.85
DH5232/B . . . . . .. .. . 6.50 5.30 DH.82A, DH.83, DH.84, DH.85
DH5234/A . . . . . .. .. . 6.75 5.08 DH.80A, DH.82A, DH.85
DH5234/B . . . . . .. .. . 6.75 4.95 DH.80A, DH.82A, DH.85, DH.87B
DH5234/D . . . . . .. .. . 6.75 4.80 DH.80A, DH.85, DH.87, DH.87B,
Messenger
DH5234/E . .. .. .. .. . 6.75 4.50 DH.85, DH.87A, DH.87B
DH5234/H . .. .. .. .. . 6.75 4.30 DH.87B

30 September 2008 Part 11 Leaflet 11-39 Appendix 1 Page 6

CAP 562 Civil Aircraft Airworthiness Information and Procedures

Drawing No. Diam. Pitch Aircraft

(ft) (ft)
GIPSY MAJOR 1 (continued)
DH5234/J . . . . . .. .. . 6.75 4.40 DH.85, DH.87B, DH.82A
DH5250/B . . . . . .. .. . 6.33 5.17 DH.80A, DH.90A, Auster J.1.N
HR671 .. .. .. .. .. . 6.84 3.53 DH.82A, Jackaroo
HO21-198B-140L . . .. .. . 6.49 4.59 Auster J1N, DH.82A
HO21-198B-140LK . . .. .. . 6.49 4.59 DH.82A
HO21-207S-155LK . . .. .. . 6.79 5.08 DH.87B
HO21-208B-108L . . .. .. . 6.82 3.54 DH.82A
HO21LM-198B-140L . .. .. . 6.49 4.59 DH.82A
HO21LM-207S-155LK .. .. . 6.79 5.08 DH.82A
LA506/3 . . . . . . .. .. . 6.50 4.35 DH.82A
LA510 .. .. .. .. .. . 6.50 5.36 Monarch, Whitney Straight, DH.85
LA520 .. .. .. .. .. . 6.67 4.59 DH.90A
LA523 .. .. .. .. .. . 6.50 5.16 Auster J.1.N
LA543 .. .. .. .. .. . 7.00 4.00 Blackburn B2
LA550 .. .. .. .. .. . 6.67 5.05 Hawk Trainer
LA550/1 . . . . . . .. .. . 6.67 5.05 DH.85
LA594/2 . . . . . . .. .. . 6.50 4.35 DH.82A
LA596 .. .. .. .. .. . 6.50 5.00 DH.82A, DH.84, DH.85, Hawk Trainer,
Messenger, Whitney Straight
LA596/3 . . .. .. .. .. . 6.50 5.36 DH.87B
LA604 .. .. .. .. .. . 6.50 4.58 DH.82A, DH.84, DH.87B
LA604/AM . .. .. .. .. . 6.50 4.51 Auster J.1.N
LA623/2 . . .. .. .. .. . 6.84 3.53 Mercury
OP60/B . . .. .. .. .. . 6.16 5.42 Hawk Trainer, Whitney Straight, Falcon
Z970 . . . .. .. .. .. . 6.23 5.72 Hawk Trainer
Z970-2 .. .. .. .. .. . 6.38 6.23 Falcon
Z971 . . . .. .. .. .. . 6.23 5.26 DH.82A, Monarch, Whitney Straight
Z973 . . . .. .. .. .. . 6.23 5.50 DH.80A, DH.82A, DH.90A, Falcon, Hawk
Trainer, Monarch, Whitney Straight,
Auster J.1.N
Z978 . . . .. .. .. .. . 5.85 5.50 DH.82A, Auster J.1.N
Z1510 .. .. .. .. .. . 6.36 5.20 DH.84
Z2010 .. .. .. .. .. . 6.50 5.65 Falcon
Z3101 .. .. .. .. .. . 6.42 5.22 DH.90A
Z3104 .. .. .. .. .. . 6.50 5.42 DH.90A
Z5890 .. .. .. .. .. . 6.50 4.49 Auster 3; 5.D; 5.J.1.B; 5.J.5
Z8010 .. .. .. .. .. . 6.84 3.53 DH.82A, Jackaroo
Z8014 .. .. .. .. .. . 6.84 3.53 Auster J.5.B, Auster J.1.N, Auster 3G
ZD5220/1 . . .. .. .. .. . 6.33 4.83 DH.82A
871 . . . . .. .. .. .. . 6.50 3.05 DH.82A
1993 . . . .. .. .. .. . 6.04 4.18 DH.82A
94103A/X13 .. .. .. .. . 6.75 4.92 Chipmunk

30 September 2008 Part 11 Leaflet 11-39 Appendix 1 Page 7

CAP 562 Civil Aircraft Airworthiness Information and Procedures

Drawing No. Diam. Pitch Aircraft

(ft) (ft)
GIPSY MAJOR 1C
61326A/X9 . . . . . . . . . . 6.17 5.72 Monarch
66875/X4 . . . . . . . . . . . 6.50 5.84 Gemini
67104A/X7 . . . . . . . . . . 7.00 4.71 DH.87B
A66696/X1 . . . . . . . . . . 6.75 4.83 Auster J.5.F
A66753/X1 . . . . . . . . . . 6.75 5.01 Leopard Moth
A66875/X4 . . . . . . . . . . 6.50 5.84 DH.82A
A66938/X3 . . . . . . . . . . 7.50 3.70 Jackaroo
A104940/X3 . . . . . . . . . 7.42 3.70 Jackaroo
B66143/X2 . . . . . . . . . . 6.74 4.69 DH.82A
B104951/X2 . . . . . . . . . 6.75 5.02 DH.82A
B104952/X1 . . . . . . . . . 6.92 4.07 Jackaroo
DH5220/H (Invincible Airscrews Pty.) 6.33 4.92 DH82A
DH5220/M . . . . . . . . . . 6.33 4.50 Auster J.1.N
DH5220/P . . . . . . . . . . 6.33 4.58 Auster J.1.N, DH.82A, DH.83
DH5220/P (Poncelet) . . . . . . 6.33 4.58 DH82A
DH5234/D . . . . . . . . . . 6.75 4.80 DH.85, DH.87B
HO21-198B-140L . . . . . . . 6.49 4.95 DH.82A
HO21-198B-140LK . . . . . . . 6.49 4.59 DH.82A
LA596 . . . . . . . . . . . 6.50 5.00 Hawk Trainer, DH.87B
LA604 . . . . . . . . . . . 6.50 4.58 DH.82A
Z973 . . . . . . . . . . . . 6.23 5.50 Gemini, Hawk Trainer
Z5620/2 . . . . . . . . . . . 6.50 4.33 Messenger
Z8010 . . . . . . . . . . . 6.84 3.53 DH.82A, Jackaroo
GIPSY MAJOR 1D
67104A/X10 .. .. .. .. . 7.0 4.60 DH.87B
A66696/X1 . .. .. .. .. . 6.75 4.83 Messenger
DH5234/J . .. .. .. .. . 6.75 4.40 DH.87B
HR671 .. .. .. .. .. . 6.84 3.53 Messenger
LA596 .. .. .. .. .. . 6.50 5.00 Messenger
LA604 .. .. .. .. .. . 6.50 4.58 Messenger
Z971 . . . .. .. .. .. . 6.23 5.26 Messenger
Z973 . . . .. .. .. .. . 6.23 5.50 DH.90A
Z5620/2 . . .. .. .. .. . 6.50 4.33 Messenger
Z5623 .. .. .. .. .. . 6.50 4.30 Messenger
Z8010 .. .. .. .. .. . 6.84 3.53 Messenger
GIPSY MAJOR 1F
1993 . . . . .. .. .. .. . 6.04 4.18 DH82A
61326A/X8 . .. .. .. .. . 6.17 6.01 DH87B
67104A/X10 .. .. .. .. . 7.00 4.60 DH82A, DH87B
67104A/X12 .. .. .. .. . 7.00 5.18 DH82A, DH87B
67104A/X14 .. .. .. .. . 7.00 4.52 DH82A
67104A/X3 . .. .. .. .. . 7.00 4.95 DH87B
67104A/X4 . .. .. .. .. . 7.00 4.77 DH82A, DH87B
67104A/X7 . .. .. .. .. . 7.00 4.71 DH87B

30 September 2008 Part 11 Leaflet 11-39 Appendix 1 Page 8

CAP 562 Civil Aircraft Airworthiness Information and Procedures

Drawing No. Diam. Pitch Aircraft

(ft) (ft)
GIPSY MAJOR 1F (continued)
67575A/X1 . . . . . .. .. . 7.00 4.71 DH82A
84723A/X1 . . . . . .. .. . 7.00 4.84 DH82A, DH87B
871 . . . . . . . . .. .. . 6.50 3.05 DH82A
A104940/X2 . . . . .. .. . 7.42 3.52 DH82A
A104940/X3 . . . . .. .. . 7.42 3.70 DH82A
A104943/X3 . . . . .. .. . 7.17 3.62 DH82A
A66016/X4 . . . . . .. .. . 7.00 4.58 DH82A
A66753/X1 . . . . . .. .. . 6.75 5.01 DH82A
A66938/X2 . . . . . .. .. . 7.50 3.52 DH82A
B66143/X1 . . . . . .. .. . 6.74 5.49 DH87B
B66143/X2 . . . . . .. .. . 6.74 4.69 DH82A
B67927/X2 . . . . . .. .. . 6.92 4.60 DH87B
C66969/X1 . . . . . .. .. . 5.92 4.50 DH82A, DH87B
C67927/X1 . . . . . .. .. . 6.92 5.18 DH87B
DH5212/D. . . . . . .. .. . 6.17 5.42 DH82A
DH5218/B. . . . . . .. .. . 6.50 5.10 DH82A
DH5220/B. . . . . . .. .. . 6.33 5.08 DH82A
DH5220/G. . . . . . .. .. . 6.33 4.58 DH82A
DH5220/H. . . . . . .. .. . 6.33 4.92 DH82A
DH5220/L . . . . . . .. .. . 6.33 4.75 DH82A
DH5220/M . . . . . .. .. . 6.33 4.50 DH82A
DH5220/P . . . . . . .. .. . 6.33 4.58 DH82A, DH87B
DH5220/B (Poncelet) . .. .. . 6.33 5.08 DH82A
DH5220/G (Poncelet) . .. .. . 6.33 4.58 DH82A
DH5220/H (Poncelet) . .. .. . 6.33 4.92 DH82A
DH5220/L (Poncelet) . .. .. . 6.33 4.75 DH82A
DH5220/M (Poncelet). .. .. . 6.33 4.50 DH82A
DH5220/P (Poncelet) . .. .. . 6.33 4.58 DH82A
DH5232/A. . . . . . .. .. . 6.50 5.10 DH82A
DH5232/B. . . . . . .. .. . 6.50 5.30 DH82A
DH5234/A. . . . . . .. .. . 6.75 5.08 DH82A
DH5234/B. . . . . . .. .. . 6.75 4.95 DH82A, DH87B
DH5234/D. . . . . . .. .. . 6.75 4.80 DH87B
DH5234/E . . . . . . .. .. . 6.75 4.50 DH87B
DH5234/H. . . . . . .. .. . 6.75 4.30 DH87B
DH5234/J . . . . . . .. .. . 6.75 4.40 DH82A, DH87B
HO21-198B-140L . . .. .. . 6.49 4.59 DH82A
HO21-198B-140LK . . .. .. . 6.49 4.59 DH82A
HO21-207S-155LK . . .. .. . 6.79 5.08 DH87B
HO21-208B-108L . . .. .. . 6.82 3.54 DH82A
HO21LM-198B-140L . .. .. . 6.49 4.59 DH82A
HO21LM-207S-155LK .. .. . 6.79 5.08 DH82A
HR671 .. .. .. .. .. . 6.84 3.53 DH82A
LA506/3 . . . . . . .. .. . 6.50 4.35 DH82A
LA594/2 . . . . . . .. .. . 6.50 4.35 DH82A
LA596 . . . . . . . .. .. . 6.50 5.00 DH82A

30 September 2008 Part 11 Leaflet 11-39 Appendix 1 Page 9

CAP 562 Civil Aircraft Airworthiness Information and Procedures

Drawing No. Diam. Pitch Aircraft

(ft) (ft)
GIPSY MAJOR 1F (continued)
LA596/3 .. .. .. .. .. . 6.50 5.36 DH87B
LA604 . .. .. .. .. .. . 6.50 4.58 DH82A, DH87B
Z8010 . .. .. .. .. .. . 6.84 3.53 DH82A
Z971 . . .. .. .. .. .. . 6.23 5.26 DH82A
Z973 . . .. .. .. .. .. . 6.23 5.50 DH82A
Z978 . . .. .. .. .. .. . 5.85 5.50 DH82A
ZD5220/1 .. .. .. .. .. . 6.33 4.83 DH82A
GIPSY MAJOR 1H
A66875/X4 . . . . . . . . . . 6.50 5.84 DH82A
B66143/X2 . . . . . . . . . . 6.74 4.69 DH82A
B104951/X2 . . . . . . . . . 6.75 5.02 DH82A
DH5220/H (Invincible Airscrews Pty.) 6.33 4.92 DH82A
DH5220/P . . . . . . . . . . . 6.33 4.58 DH82A
DH5220/P (Poncelet) . . . . . . 6.33 4.58 DH82A
HO21-198B-140L . . . . . . . 6.49 4.59 DH82A
HO21-198B-140LK . . . . . . . 6.49 4.59 DH82A
LA604 . . . . . . . . . . . . 6.50 4.58 DH82A
Z8010 . . . . . . . . . . . . 6.84 3.53 DH82A
GIPSY MAJOR 1J
A104940/X2 .. .. .. .. . 7.42 3.52 DH.82A
DH5212D . . .. .. .. .. . 6.17 5.42 Hawk Trainer
HR671 .. .. .. .. .. . 6.84 3.53 DH.82A
LA604 .. .. .. .. .. . 6.50 4.58 DH.82A, Hawk Trainer
Z973 . . . .. .. .. .. . 6.23 5.50 Hawk Trainer
Z8010 .. .. .. .. .. . 6.84 3.53 DH.82A
GIPSY MAJOR 10 Mks. 1-1, 1-3, 1-7
A66578/X1 . .. .. .. .. . 6.75 4.64 DH.85
A66661/X2 . .. .. .. .. . 6.75 5.01 Chipmunk
A66661/X3 . .. .. .. .. . 6.75 4.71 Chipmunk
A66661/X4 . .. .. .. .. . 6.75 4.75 Auster 6A
A66696/X1 . .. .. .. .. . 6.75 4.83 Auster J.1.N, DH.82A, Beagle, A61
Series 2
A66696/X1/3 .. .. .. .. . 6.33 4.67 Beagle A61 Series 2
A66696/X3 . .. .. .. .. . 6.75 4.67 Auster J.5.L, Auster J.5.P, Chrislea Super
Ace, Auster A61, DH.85, Auster 6A,
Beagle A61 Series 2
A66696/X6 . .. .. .. .. . 6.75 4.19 Auster J.5.P
A66753/X1 . .. .. .. .. . 6.75 5.01 Chipmunk
A66875/X1 . .. .. .. .. . 6.50 5.72 Gemini
A66875/X3 . .. .. .. .. . 6.50 6.02 Gemini
A66875/X4 . .. .. .. .. . 6.50 5.84 Gemini
A66875/X7 . .. .. .. .. . 6.50 6.22 Gemini
A66938/X2 . .. .. .. .. . 7.50 3.52 Auster 6A
A66938/X3 . .. .. .. .. . 7.50 3.70 Auster 6A

30 September 2008 Part 11 Leaflet 11-39 Appendix 1 Page 10

CAP 562 Civil Aircraft Airworthiness Information and Procedures

Drawing No. Diam. Pitch Aircraft

(ft) (ft)
GIPSY MAJOR 10 Mks. 1-1, 1-3, 1-7 (continued)
A67960/X1 . .. .. .. .. . 6.75 4.67 Auster J.5.P, Beagle A61 Series 2
A94103A/X11 .. .. .. .. . 6.75 5.34 Chipmunk
B67934/X1 . .. .. .. .. . 6.62 4.71 Chipmunk
B67935/X1 . .. .. .. .. . 6.75 5.01 Chipmunk
DH5232/AR/5 .. .. .. .. . 6.50 5.10 DH.82A
DH5234-B . .. .. .. .. . 6.75 4.95 Beagle A61
HR671 .. .. .. .. .. . 6.84 3.53 Chrislea Super Ace
HR708 .. .. .. .. .. . 6.33 4.33 Chrislea Super Ace
LA596 .. .. .. .. .. . 6.50 5.00 Gemini
Z971 . . . .. .. .. .. . 6.23 5.26 Messenger
Z973 . . . .. .. .. .. . 6.23 5.50 Gemini, Hawk
Z1510 .. .. .. .. .. . 6.36 5.20 Desford Trainer
Z5623/1 . . .. .. .. .. . 6.50 4.30 Messenger, Chrislea Super Ace
Z5672 .. .. .. .. .. . 6.25 4.44 Messenger, Chrislea Super Ace
Z5780 .. .. .. .. .. . 6.50 4.05 Messenger, Chrislea Super Ace
Z8010 .. .. .. .. .. . 6.84 3.53 Messenger, Chrislea Super Ace
Z8014 .. .. .. .. .. . 6.84 3.53 Auster 6A, Beagle Auster A61, Beagle
A61 Series 2
GIPSY MAJOR 10 Mks. 1-1A, 1-3A, 1-7A, Mk. 2, 2-1
A66753/X1 . .. .. .. .. . 6.75 5.01 Auster J.1.N, Chipmunk, DH.85, Gemini
3C
A66904/X1 . .. .. .. .. . 6.50 5.24 Chipmunk, Desford/Bobsleigh
A67925/X2 . .. .. .. .. . 6.75 4.02 Chipmunk
A67925/X3 . .. .. .. .. . 6.75 4.67 Auster 6A, Beagle A61, Auster J.5.P,
J.5.R, J.5.L
A67960/X1 . .. .. .. .. . 6.75 4.67 Auster J.5.L, J.5.P, J.5.R, Auster 6A,
Beagle A.61
A67960/X2 . . . . . .. .. . 6.75 4.19 Auster J.5.P, Auster J.5.R
A67889 . . . . . . .. .. . 6.75 5.01 Chipmunk
B104972 . . . . . . .. .. . 6.47 5.01 Chipmunk
B104973 . . . . . . .. .. . 6.30 5.36 Chipmunk
B67871/X1 . . . . . .. .. . 6.58 5.01 Chipmunk
D67972/X1 . . . . . .. .. . 6.50 5.84 Chipmunk, Gemini
D67972/X2 . . . . . .. .. . 6.50 5.20 Gemini
D67972/X5 . . . . . .. .. . 6.50 5.72 Chipmunk, Falcon, Gemini
D67989/X2 . . . . . .. .. . 6.75 4.67 Auster J.5.L
D67996/X1 . . . . . .. .. . 6.76 3.88 Chipmunk
D104967/X1 . . . . .. .. . 6.75 5.01 Chipmunk
HO21-198B-140L . . .. .. . 6.49 4.59 Chipmunk
HO21-198B-140LK . . .. .. . 6.49 4.59 DH.82A
HO21-208B-108L . . .. .. . 6.82 3.54 Chipmunk
HO21HM-198B-140L . .. .. . 6.49 4.59 Chipmunk
HO21HM-198B-140LK .. .. . 6.49 4.59 Chipmunk
HR864 .. .. .. .. .. . 6.50 4.58 Messenger, DH.87B
Z976 . . . . . . . .. .. . 6.23 5.50 Falcon, Gemini

30 September 2008 Part 11 Leaflet 11-39 Appendix 1 Page 11

CAP 562 Civil Aircraft Airworthiness Information and Procedures

Drawing No. Diam. Pitch Aircraft

(ft) (ft)
GIPSY MINOR
DH5258/A . .. .. .. .. . 5.88 3.96 DH.94
DH5258/E . .. .. .. .. . 5.88 4.19 DH.94
DH5258/J . .. .. .. .. . 5.88 4.03 DH.94
DH5258/K . .. .. .. .. . 5.88 4.00 DH.94
HR1312 . . .. .. .. .. . 5.88 4.03 DH.94
GIPSY QUEEN 3
61186A/X4 . .. .. .. .. . 7.00 6.48 DH.89, DH.89A
61186A/X6 . .. .. .. .. . 7.00 6.33 DH.89, DH.89A
61186A/X9 . .. .. .. .. . 7.00 5.94 DH.89, DH.89A
61186A/X12 .. .. .. .. . 7.00 6.41 DH.89, DH.89A
A66327/X2 . .. .. .. .. . 6.75 5.90 DH.89, DH.89A
A67967/X2 . .. .. .. .. . 7.00 6.65 DH.89, DH.89A
A67967/X3 . .. .. .. .. . 7.00 6.46 DH.89, DH.89A
A67967/X5 . .. .. .. .. . 7.00 5.45 DH.89, DH.89A
B66936/X1 . .. .. .. .. . 6.83 5.94 DH.89, DH.89A
B66937/X1 . .. .. .. .. . 6.83 5.94 DH.89, DH.89A
B67982/X1 . .. .. .. .. . 6.42 6.25 DH.89, DH.89A
GIPSY QUEEN 30-2
PD70/212/1/2 . . .. .. .. . 7.50 VP Prentice
GIPSY QUEEN 30-3 and 30 Mk. 2
PD136/212/1/2 . . .. .. .. . 7.00 VP DH.114
PD170/212/1/2 . . .. .. .. . 7.00 VP DH.114
PD175/212/1/2 . . .. .. .. . 7.00 VP DH.114
PD190/212/1 . . .. .. .. . 7.00 VP DH.114
GIPSY QUEEN 70-3 and 70-4
PD116/312/1 to /7 inc. .. .. . 7.50 VP DH.104
PD143/312/1 to /7 inc. .. .. . 7.50 VP DH.104
GIPSY QUEEN 70 Mk. 2
PD143/312/1 to /7 inc. .. .. . 7.50 VP DH.104
GIPSY QUEEN 70 Mk. 3
PD143/312/1 to /7 inc .. .. . 7.50 VP DH.104

30 September 2008 Part 11 Leaflet 11-39 Appendix 1 Page 12

CAP 562 Civil Aircraft Airworthiness Information and Procedures

Drawing No. Diam. Pitch Aircraft

(ft) (ft)
GIPSY SIX 1
61025A/X2 . .. .. .. .. . 7.00 6.47 DH.86, DH.89, DH.89A
61052A/X3 . .. .. .. .. . 7.00 6.29 DH.89, DH.89A
61052A/X5 . .. .. .. .. . 7.00 6.03 DH.89, DH.89A
61186A/X2 . .. .. .. .. . 7.00 6.66 DH.86, DH.86B, DH.89, DH.89A
61186A/X3 . .. .. .. .. . 7.00 6.56 DH.86, DH.86B, DH.89, DH.89A
61186A/X4 . .. .. .. .. . 7.00 6.48 DH.89A, DH.89
61186A/X5 . .. .. .. .. . 7.00 6.39 DH.89A, DH.89
61186A/X6 . .. .. .. .. . 7.00 6.33 DH.86, DH.86B, DH.89, DH.89A
61186A/X7 . .. .. .. .. . 7.00 6.28 DH.89, DH.89A
61186A/X9 . .. .. .. .. . 7.00 5.94 DH.89A
61186A/X12 .. .. .. .. . 7.00 6.41 DH.89A
61189A/X1 . .. .. .. .. . 7.00 7.11 Hawk
61189A/X5 . .. .. .. .. . 7.00 6.96 Hawk
61189A/X7 . .. .. .. .. . 7.00 6.84 Hawk
61189A/X8 . .. .. .. .. . 7.00 7.29 Hawk
61375A/X1 . .. .. .. .. . 7.00 6.76 Gull
61375A/X2 . .. .. .. .. . 7.00 7.03 Hawk
A66327/X2 . .. .. .. .. . 6.75 5.90 DH.89A
A67967/X2 . .. .. .. .. . 7.00 6.65 DH.89
A67967/X5 . .. .. .. .. . 7.00 5.45 DH.89A
B66128/X1 . .. .. .. .. . 7.00 6.75 DH.89, DH.89A
B66942/X1 . .. .. .. .. . 6.67 6.62 Hawk
C66026/X1 . .. .. .. .. . 6.75 6.81 DH.89, DH.89A
C66093/X1 . .. .. .. .. . 6.75 6.66 DH.86B, DH.89, DH.89A
DH5238/F . .. .. .. .. . 6.75 6.30 DH.86, DH.89, DH.89A
DH5238/G . .. .. .. .. . 6.75 6.40 DH.86, DH.89, DH.89A, Heck
DH5238/H . .. .. .. .. . 6.75 6.40 DH.89, DH.89A
DH5238/J . .. .. .. .. . 6.75 6.20 DH.89, DH.89A
DH5244/A . .. .. .. .. . 6.75 6.40 DH.89, DH.89A
DH5244/B . .. .. .. .. . 6.75 6.30 DH.89, DH.89A
DH5246/B . .. .. .. .. . 6.75 6.20 DH.86, DH.89, DH.89A
Z1800 .. .. .. .. .. . 6.92 6.20 Hawk
Z2192 .. .. .. .. .. . 6.75 6.18 DH.89, DH.89A
Z2682/1 . . .. .. .. .. . 6.72 6.20 DH.86, DH.89, DH.89A
Z2682/7 . . .. .. .. .. . 6.56 6.18 DH.89, DH.89A
Z2687 .. .. .. .. .. . 6.56 6.43 DH.86, DH.86B
Z2688 .. .. .. .. .. . 6.56 6.29 DH.89, DH.89A
Z2689 .. .. .. .. .. . 6.56 6.50 DH.86, DH.86B
GIPSY SIX 2
PD30/211/1 .. .. .. .. . 7.00 VP Proctor 1, 2, 3, 4, 5
PD154/211/1 .. .. .. .. . 6.75 VP Mew Gull
PD209/211/1 .. .. .. .. . 7.00 VP Mew Gull

30 September 2008 Part 11 Leaflet 11-39 Appendix 1 Page 13

CAP 562 Civil Aircraft Airworthiness Information and Procedures

Drawing No. Diam. Pitch Aircraft

(ft) (ft)
LEONIDES 501, 502, 503 and 504
CR162/3-20-3/5 or /5P .. .. . 9.00 VP President
PD158/313/1 . . . . .. .. . 9.00 VP Prince
PD159/313/1 . . . . .. .. . 9.00 VP Prince
PD184/313/1 . . . . .. .. . 9.00 VP Beaver
PD232/313/1 and /2 . . .. .. . 9.00 VP Prince, President
LEONIDES 503/8, 504/8 and 514/8
PD205/323/1 .. .. .. .. . 11.00 VP Twin Pioneer
LEONIDES 514/5A
CR143/3-20-3/2 . .. .. .. . 9.00 VP President 2A
LEONIDES 531/8B
PD237/323/1 .. .. .. .. . 11.00 VP Twin Pioneer
LYCOMING GO-480-B
Blade 9333C-3 . . . . .. .. . 7.50 VP E.P.9
Hub HC82x20-1B . . .. .. . 7.50 VP E.P.9
P1033/G4-AD-0691236 .. .. . 7.75 VP E.P.9
LYCOMING GO-480 G1A6
Blade 9333C-3 . . . . .. .. . 7.50 VP E.P.9
Hub HC83x20-1B . . .. .. . 7.50 VP E.P.9
P1033/G4-AD-0691236 .. .. . 7.75 VP E.P.9
LYCOMING O-235-C1
M76/AM-2-48 . . .. .. .. . 6.16 4.00 Auster D4
Z5960 .. .. .. .. .. . 6.50 3.06 Auster D4
LYCOMING O-290-3 and 0-290-C
1A. 170. LL. 7647 .. .. .. . 6.33 3.92 Auster 5
FP420 .. .. .. .. .. . 6.25 4.18 Auster 4 and 5
HO-30-190-112 . . .. .. .. . 6.23 3.67 Auster 4 and 5
HR1231 . . . . .. .. .. . 6.50 3.48 Auster 4 and 5
Z5594 .. .. .. .. .. . 6.00 3.67 Auster 4 and 5
Z5600 .. .. .. .. .. . 6.50 3.48 Auster 4 and 5
Z5602 .. .. .. .. .. . 6.50 3.19 Auster 4 and 5
LYCOMING O-320-A2B
M74DMS-0-60 . . .. .. .. . 7.16 5.00 B121 Series 2
74DM6S5-0-60 . .. .. .. . 7.16 5.00 B121 Series 2
LYCOMING O-320-B
1A/175/GM 8052 .. .. .. . 6.66 4.33 Auster D5

31 March 2009 Part 11 Leaflet 11-39 Appendix 1 Page 14

CAP 562 Civil Aircraft Airworthiness Information and Procedures

Drawing No. Diam. Pitch Aircraft

(ft) (ft)
LYCOMING O-320-B2B
M74DM56 . . . .. .. .. . 6.02 4.08 Auster J5V
1A200/FAM-8043 .. .. .. . 6.66 3.58 Auster D6
1A200/FAM-8046 .. .. .. . 6.66 3.83 Auster J5V, Auster D5
LYCOMING O-320-D2C
M74DMS-0-62 . . .. .. .. . 7.16 5.16 B121 Series 3
74DM6S5-0-62 . .. .. .. . 7.16 5.16 B121 Series 3
LYCOMING O-360-A1A
2D36C14/78KM-4 .. .. .. . 6.17 VP Auster J.1.U, Auster D6, Beagle A.109
LYCOMING O-360-A2A
1A200/FA-8240 . .. .. .. . 6.83 3.33 Auster D5
1A200/FA-8243 . .. .. .. . 6.83 3.58 Auster D5, Auster D6, Auster J.1.U
1A200/FA-8250 . .. .. .. . 6.83 4.16 Auster D5, Auster D6, Auster J.1.U
NIAGARA 3
Z5740 .. .. .. .. .. . 6.50 8.26 Comper Swift

TPE 331-2
HCB3TN-5C/T10282HB . . .. . 8.5 VP Skyvan 3
HCB3TN-5E/T10282HB . . .. . 8.5 VP Skyvan 3
HCB4TN-5C/T10282HB-4P .. . 8.25 VP Skyvan 3A
HCB3TN-5E/T10232HB . . .. . 8.5 VP Skyvan 100-81
TYNE 515-101W
PD244/476/2 .. .. .. .. . 16 VP Belfast SC5
WALTER MIKRON 2
A66049/1X1 .. .. .. .. . 4.75 3.59 Tipsy Trainer
A66167/X4 . .. .. .. .. . 5.50 3.44 Tipsy B, Tipsy Trainer
A66167/X5 . .. .. .. .. . 5.50 3.90 Tipsy B
B66592/X1 . .. .. .. .. . 5.25 3.56 Tipsy Trainer
LA511 .. .. .. .. .. . 5.05 3.92 Tipsy Trainer
LA553/2 . . .. .. .. .. . 5.35 3.22 Tipsy Trainer

30 September 2008 Part 11 Leaflet 11-39 Appendix 1 Page 15

INTENTIONALLY LEFT BLANK
CAP 562 Civil Aircraft Airworthiness Information and Procedures

Leaflet 11-40 Acceptance of Ex-UK Government

Gipsy Major 8 Engines and Fixed Pitch Fairey
Reed Metal Propellers

(Previously issued as AIL/0177)

PURPOSE: This Leaflet provides information on the acceptance of ex-UK Government

Gipsy Major 8 engines and Fairey Reed metal propellers for installation on UK
registered DH Chipmunk aircraft.

REFERENCES: Rolls-Royce Technical News Sheet TNS GE No. 27 dated 24 October 1974.
CAP 562 Leaflet 11-39
CAP 562 Leaflet 11-48
CAP 747 Generic Requirement (GR) No. 24.

The following information is additional to that given in the above references:

1) In order for military engines/propellers to be used in aircraft with a UK Certificate of
Airworthiness, acceptance by the CAA is normally required in accordance with CAP
562 Leaflet 11-48. However, this process can be waived for the subject engines/
propellers provided the following information is supplied prior to acceptance of an
engine or propeller:
a) Statement of serviceability from the UK military body from which the engine/
propeller was obtained.
b) Statement of the engine/propeller build standard from the UK military body or from
a CAA approved overhaul organisation, in order to verify that all modifications
embodied are CAA approved and that all CAA mandatory modifications have been
embodied.
c) Statement from the UK military body or from a CAA approved overhaul
organisation that all engine/propeller repairs are CAA approved.
d) Engine log book. It must be verified that all mandatory inspections have been
complied with.
2) Rolls-Royce TNS GE No. 27 states that the civilian TBO for the Gipsy Major 8 Mk 2 is
1500 hours. This TBO can be exceeded subject to meeting the requirements of CAP
747 GR No. 24. It should be noted however, that paragraph 3.1.1 c) of this GR states:
’The engine must have been operated in an aircraft registered in the United Kingdom
for a period of at least 200 hours immediately prior to completion of the engine
manufacturer’s overhaul period recommendation’.
For the subject engines, the requirement of this paragraph can be waived. This allows
engines with a TSO up to 2250 hours (this being the MOD overhaul period limitation)
to be accepted by the CAA subject to all other requirements of CAP 747 GR No. 24
(including any applicable calendar life limitations) and Section 1 of this Leaflet being
satisfied.

1 All Gipsy Major 8 modifications up to and including 4037 have CAA approval.
For engines incorporating modifications later than modification 4037,
application shall be made to the CAA preferably through the Type Certificate

31 March 2009 Part 11 Leaflet 11-40 Page 1

CAP 562 Civil Aircraft Airworthiness Information and Procedures

holder for approval or confirmation of civil approval of the modification(s). This

may involve the applicant being charged for the investigation.

2 Propellers approved for use on the civil Chipmunk aircraft are stated in CAP 562
Leaflet 11-39.

NOTE: This Leaflet is applicable to UK Government engines, whether obtained

directly from the UK Government or from another source.

31 March 2009 Part 11 Leaflet 11-40 Page 2

CAP 562 Civil Aircraft Airworthiness Information and Procedures

Leaflet 11-41 Acceptance of Ex-UK Government Lycoming IO

360-A1B6 Engines and Variable Pitch
Propellers

(Previously issued as AIL/0181)

PURPOSE: This Leaflet provides information on the acceptance of ex-UK Government

Lycoming engines and Hartzell propellers for installation on UK registered
Bulldog aircraft.

REFERENCES: Textron Lycoming Service Instruction No 1009AT

CAP 562 Leaflet 11-48
CAP 747 Generic Requirement (GR) No. 24

The following information is additional to that given in the above references:

1 Acceptance onto UK Register

In order for military engines/propellers to be used in aircraft with a UK Certificate of

Airworthiness, acceptance by the CAA is normally required in accordance with CAP
562 Leaflet 11-48. However, this process can be waived for the subject engines/
propellers provided the following information is established by the owner's/operator's
Part 145 maintenance organisation or an appropriately type rated CAA Licensed
Aircraft Engineer, prior to acceptance of an engine or propeller:
a) Serviceability, based on an appropriate statement from the UK military body from
which the engine / propeller was obtained.
b) Engine/propeller build standard based on an appropriate statement from the UK
military body or from a CAA approved overhaul organisation, in order to verify that
all CAA mandatory modifications and inspections have been accomplished.
c) All engine/propeller repairs are CAA approved based on an appropriate statement
from the UK military body or from a CAA approved overhaul organisation.
d) Engine and propeller log books issued.
e) Civil identification plates are fitted.

2 Engine TBO Recommendations

Textron Lycoming Service Instruction No 1009AT states that the recommended TBO
for the IO 360-A1B6 engine is 2000 hours. Paragraph 10 states that ’Some engines in
the field have been altered to incorporate an inverted oil system in order to perform
aerobatic manoeuvres. Whenever this modification is done to an engine, the TBO of
the engine must be determined in the same manner listed for AEIO engines of the
same model series’.
It could be considered therefore that the manufacturer's recommended TBO for the
engine is reduced to 1400 hours. However, the aerobatic capability of the Bulldog
aircraft is limited by the airframe, and is not increased by the fitment of the inverted
oil system. It has therefore been decided that a TBO of 1800 hours should be
established, which is consistent with the TBO applicable in military service.

31 March 2009 Part 11 Leaflet 11-41 Page 1

CAP 562 Civil Aircraft Airworthiness Information and Procedures

This TBO may be subject to extension under CAP 747 GR No. 24. However, it should
be noted that paragraph 3.1.1 c) of the GR states:
’The engine must have been operated in an aircraft registered in the United Kingdom
for a period of at least 200 hours immediately prior to completion of the engine
manufacturer's overhaul period recommendation’.
Since the subject engines have clearly been operated and maintained in the United
Kingdom the above requirement for 200 hours to be completed on the UK register
can be waived. This allows engines with a TSO up to 1800 hours (this being the
military TBO limitation) to be accepted for TBO extension subject to all other
requirements of CAP 747 GR No. 24 and Section 1 of this Leaflet being satisfied.

3 Propeller TBO Recommendations

For the propeller, the TBOs should be as per the manufacturer's instruction for
propellers of this type when fitted to aerobatic aircraft.

4 Timing of TBO

The next TBO for both engine and propeller should be timed from the last overhaul in
military service.
NOTE: This Leaflet is applicable to ex-UK Government engines whether obtained
directly from the UK Government or from another source. If the engines have
been operated since being obtained from the UK Government, and are to be
registered for use in Public Transport Category, then the Leaflet does not
apply.

31 March 2009 Part 11 Leaflet 11-41 Page 2

CAP 562 Civil Aircraft Airworthiness Information and Procedures

Leaflet 11-42 Restoration, Airworthiness Control and

Maintenance of Aircraft of Ex-military Origin
under a BCAR Chapter A8-20 Approval

(Previously issued as AIL/0170)

PURPOSE: This information is issued for the guidance of applicants seeking an approval
under BCAR A8-20 and CAA staff when they are investigating such an
approval.

BCAR A8-20 contains the requirements for making submissions to the CAA
for the grant of initial approval and the maintenance of ex-Military aircraft
above 2730kg. The other requirements of BCAR sections A and B remain
applicable, in particular chapters A3-7/B3-7.

REFERENCES: BCAR Chapters A3-7, B3-7, A8-20, CAP 632, AIL 0165.

1 Introduction

1.1 An organisation approved under BCAR A8-20 may according to the scope of its
approval, make a submission to the CAA for initial approval of an ex-military aircraft,
perform maintenance, repair, defect rectification, inspection and modification of an
aircraft and its related components, including complete rebuild or restoration of the
aircraft, and make a recommendation for the issue or renewal of a Permit to Fly.
1.2 This Leaflet should be read in conjunction with BCAR A8-20. This Leaflet is issued
primarily to give guidance for those organisations that are applying for approval under
BCAR A8-20. The guidance is provided in two separate appendices to this Leaflet.
Appendix 1 corresponds with paragraph 1.2.1 of BCAR A8-20 (E4 approval) covering
design related aspects of ex-military aircraft. Appendix 2 relates to those
organisations requiring approval for recommending the renewal of a Permit to Fly
under paragraph 1.2.2 of BCAR A8-20 (M5 approval).
1.3 The information provided in the Appendices of this document is intended to provide
guidance on the interpretation of the requirements and procedures required of the
organisation in order to obtain approval for ex-military aircraft.
1.4 The organisation must be defined in an exposition and this must contain adequate
control procedures for review and approval of the aircraft in question. The types of
aircraft to which the approval relates will be defined in the exposition of the
organisation by means of capability lists. These lists will be subject to the agreement
of the CAA and the exposition must contain adequate control procedures for review
and approval of these lists.
1.5 Organisations holding an approval under paragraph 1.2.1 (E4) or paragraph 1.2.2 (M5),
if applying for an extension for the other associated approval, will be required to meet
the criteria of the other approval and amend the existing exposition.

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Appendix 1

BCAR CHAPTER A8-20 EX-MILITARY AIRCRAFT

DESIGN ASPECTS - E4 APPROVAL

1 Introduction

1.1 This Appendix provides guidance on the organisational requirements and

responsibilities for organisations requiring to hold an E4 approval in accordance with
paragraph 1.2.1 of BCAR A8-20. This approval is required for organisations to
recommend that the CAA make initial issue of a Permit to Fly for an ex-military aircraft.

2 Personnel

2.1 The organisation should nominate the key design and/or engineering staff who are to
support its operation. These staff should be employed under a formal agreement
between the organisation and the staff member concerned with details of their terms
of reference as senior members of the organisation provided within the exposition.
2.2 The organisation should have a staff member - see A8-20 3.2(b) - who should be a
senior engineer and who will be the nominated contact with the CAA Design Liaison
Surveyor and who will gather, co-ordinate and submit evidence required to the CAA
in order to establish the standard of particular aircraft (see A8-20 3.2(c)). This person
should have adequate qualifications and experience appropriate to the category of
aircraft concerned.
2.3 Additional part time staff may be used to supplement the company resources where
necessary, providing that there are in existence suitable control procedures within the
organisation exposition. A form of agreement should be raised which gives detailed
terms of reference in writing to each such person. Such arrangements may be
required in order that the organisation is able to draw upon sufficiently qualified and
experienced personnel to cover specific design aspects such as the research needed
to establish the design standard of particular aircraft (see A8-20 3.2(c)), or structural
substantiation (or check stress signatory) of a repair or material substitution.
2.4 CAA Forms AD458 declaring relevant qualifications and experience for persons
nominated under the A8-20 approval should be submitted to the CAA Airworthiness
Division, Organisations Section at Gatwick.
2.5 The Exposition will include charts showing chains of responsibility and signatories for
documents to be submitted to the CAA.
2.6 The Exposition of organisations approved to cover Complex aircraft will include copies
of the formal agreements with each external organisation providing support of the
Complex aircraft and its systems and equipment.

3 Procedures

3.1 Two ex-military aircraft ostensibly of identical type may be of significantly differing
design/build standards and fatigue states and for this reason the CAA does not
consider that it is generally possible to accept one aircraft as series to another.
Because of this each aircraft requires an individual investigation culminating in issue

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CAP 562 Civil Aircraft Airworthiness Information and Procedures

of an Airworthiness Approval Note specific to it, for approval and initial issue of a
Permit to Fly. However, cross referencing to previous AANs for the same type is
acceptable in areas where the design/build standard is identical.
3.2 The basis upon which ex-military aircraft may qualify for issue of a Permit is referred
in BCAR A3-7/B3-7 paragraph 3.1(d) and the Appendix 1 to BCAR A3-7/B3-7 lists the
evidence required to substantiate applications for Permits on this basis. The A8-20 E4
organisation responsible for gathering the evidence necessary for substantiation of
submissions to the CAA is responsible for maintaining documentary records covering
these submissions. Particular aspects covered by the organisations procedures
covering the following may need to be covered in the exposition:
3.2.1 Initial Application to CAA and Establishment of Aircraft Complexity Grouping.
The organisation should make initial application to the CAA for approval of the aircraft
early in the process (Form CA3). The applicant should also propose and obtain CAA
agreement of the grouping (see paragraph 1.2.1 of BCAR A8-20) of the particular
aircraft early in the process. The proposal should contain sufficient information on the
design features of the type to justify the recommendation.
3.2.2 Establishment of Safety Record (BCAR A3-7/B3-7 Appendix 1 paragraph 2.1)
Investigation of Intermediate and Complex aircraft of a specific type which the CAA
have not yet accepted will commence with a demonstration that the aircraft type has
a safety record in service acceptable to the CAA for its intended use. Combat losses
or those directly attributable to peculiarly military operational causes such as low level
training may be discounted but a review employing such judgements should be made
by appropriately qualified personnel. The organisations procedures should include
presentation of the safety record (total loss and fatal accidents per million flying hours)
to the CAA for acceptance prior to commencement of the main investigation of
design and build standard. Such presentations to be made by the nominated
personnel accepted by the CAA for the purpose.
NOTE: It may be possible to establish that particular aircraft were hazardous in
specific operational circumstances, or that particular modifications rendered
the aircraft hazardous. In this event, it may be that application of particular
limitations may render the aircraft type acceptable to the CAA. In the case of
complex aircraft, in most cases, the CAA will require that such submissions
are supported by the manufacturer.
3.2.3 Continued Airworthiness Support/Information
The more complex the aircraft, the more necessary it will be to have adequate
technical/design expertise of the type in order to maintain the level of continued
airworthiness support. For organisations supporting only Simple or Intermediate
types, it may not be possible to retain permanent staff of adequate capability to cover
initial approval of a given aircraft. In these cases adequate arrangements should exist
to cover initial approval and continued support of each aircraft.
Complex aircraft will require permanent support covering each aspect, and may
require additional specialist support covering aspects such as powered flying control
systems, variable geometry intakes and nozzles, reaction control systems, digital
(computer) controlled systems. Some types may only be considered supportable by
the armed forces who operated them or by the manufacturer. The Exposition of
organisations approved to cover Complex aircraft should include procedures for the
necessary interface with the manufacturers providing support for the aircraft and of
its critical equipment, and/or an acceptable Military Authority. The nature and depth
of such procedures will be subject to the agreement of the CAA.

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In all cases where the type continues to be actively supported by the manufacturer
(i.e. examples of the type are still in operational service), arrangement should be made
with the manufacturer to provide copies of all continued airworthiness information
(i.e. SBs, STIs etc.) to the organisation.
3.2.4 Establishment of Conformity to Type Design Standard (BCAR A3-7/B3-7
Appendix 1 paragraph 2.2)
The organisation will have a procedure to establish that the individual aircraft
conforms to the type Design Standard to which the established safety record is
related. This involves ensuring that any modifications necessary to maintain the
standard of airworthiness are determined and incorporated. This includes obtaining
lists (in the English language) of Manufacturers (and/or the Military Engineering
Authority's, Military Operators) modifications which were considered essential for
airworthiness, and reviewing the aircraft and its accompanying paperwork to
ascertain that each such modification is embodied. The Exposition will show that the
signatory in respect of BCAR A8-20 3.2(c) will compile a statement against each such
modification showing embodiment or acceptable alternative.
This may also include RAF Special Technical Instructions (STIs), Service Instructions
(SIs) etc. Compliance with Mandatory Permit Directives promulgated by CAA for the
type is also required.
The following aspects will be covered as part of establishing conformity to Design
Standard:
a) Fatigue State
The organisation will:
i) research and identify fatigue critical components, their lives and accounting
procedures;
ii) check that all such components are identifiably within these limits and this is
supported by documentary evidence covering the full life of the aircraft;
iii) obtain CAA agreement for procedures as applied to civil operation of the aircraft
(role factors etc.)
NOTE: Statements for submission to the CAA should be signed by nominated
personnel (BCAR A8-20 paragraph 3.2(c)).
b) Identification of Limitations
The organisation will identify and record normal operating limitations appropriate
to the aircraft and to observe any limitations that the CAA may determine having
regard to the safety of third parties and occupants during intended operations of
the aircraft.
NOTE: Limitations should normally be supported by copies of published
documentation. Examples of circumstances where more restrictive
limitations may be applied (subject to agreement of the CAA) are:
i) where flight test has identified an unsafe part of the envelope to be avoided;
ii) where the equipment fit renders more restrictive limits appropriate, for instance
restriction of maximum altitude as a consequence of lack of oxygen system;
iii) where the operator chooses to operate an engine within published limitations
in order to conserve engine condition.
NOTE: Specialist Equipment such as Ejector Seats and Drop Tanks should be
subject to particular investigation.

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CAP 562 Civil Aircraft Airworthiness Information and Procedures

c) Published Information
The organisation will obtain copies (English language) of all documentation
necessary in order to operate and maintain the aircraft. This will normally include
Aircrew Manual or Pilots Notes, and schedules and manuals covering airframe,
engine and propeller overhaul, maintenance and repair. Any specialist systems
should be covered adequately.
3.2.5 Modifications made by the A8-20 E4 Organisation
In general the normal CAA procedure as detailed in BCAR A2-5/B2-5 will apply. The
E4 approval granted under BCAR A8-20 approval does not confer approval of any
activity to design or seek approval for Major Modifications on this class of aircraft.
Minor modifications to aircraft or components are required to be submitted either to
the local CAA Regional Office, along with technical justification, to substantiate such
change or alternatively be submitted via a suitably CAA approved design organisation.
Significant changes to the aircraft in terms of powerplant changes, propeller type,
alternative material specifications or equipment changes (to ensure that the aircraft is
equipped to a standard acceptable to the CAA for the intended purpose) may be the
subject of major modification action, but all such applications should be discussed
with the CAA. If the E4 approved company wishes to undertake such work they
should make application for CAA Approval under A8-8(E1) and/or A8-2(A2), but
approval may require additional personnel with specialist qualifications and
experience.
While the aircraft should conform as closely as possible to the Type Design Standard
in respect of which the safety record has been accepted, it is recognised that the
operating organisation may wish to embody modifications in order to simplify
operation of the aircraft (such as replacement of non-standard oxygen supply
connectors with NATO standard connectors). The A8-20 E4 organisation's Exposition
will include a procedure whereby such modifications are identified, defined, and
submitted to the CAA for approval (these may form part of a submission for initial
approval of an aircraft). Such modifications are to be adequately defined on
modification sheets to include drawings, circuit diagrams and changes to Pilots Notes
showing effect on limitations and operation, and justification.

NOTE: 1 In the event that the initial basis of acceptance of an aircraft into service
is not known in detail, the justification for approval of such a modifica-
tion is subject to agreement of the CAA (e.g. compliance with a appro-
priate parts of a design code such as BCAR Section K, JAR-23 etc.).
2 Material substitution during manufacture of replacement parts (in
accordance with paragraph 8 of Appendix 2 to this Leaflet) or any
repairs not identifiably made in accordance with manufacturers repair
manuals constitute modifications which must be properly approved.

Major Modifications to Complex aircraft should be accepted in writing by the

manufacturer supporting the aircraft prior to CAA approval.
3.2.6 Compilation of Draft Airworthiness Approval Note (AAN)
The organisation will have a procedure to submit a draft AAN for CAA acceptance in
order to summarise the results of investigations as above prior to issue of the Permit
to Test. Although the AAN will continue to be produced and signed by the CAA, in
order to minimise administration involved, the applicant (E4 organisation) is expected
to provide a draft which will summarise all the aspects covered above and culminate

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in a recommendation (signed by nominated signatory) that the CAA issue the Permit
to Fly. AIL 0165 provides detailed guidance on the content of AANs.
The applicant's procedures should provide for submission of the draft AAN to the CAA
and arrangement of the CAA survey of the aircraft to occur prior to flight test.

NOTE: 1 The CAA will on request provide examples of AANs.

2 Maintenance schedules, where they differ from published schedules
are subject to the agreement of the CAA Regional Office. A mainte-
nance schedule should be agreed prior to issue of a Permit to Fly.

3.2.7 Flight Test Arrangements

The organisation will have a procedure covering conduct of the necessary flight
testing of the aircraft as required by the CAA. The test schedule and the pilot should
be accepted by the CAA and a draft AAN (see 3.2.6 above) accepted by the CAA prior
to test.

4 Exposition

4.1 The Exposition should be kept as simple as possible, appropriate to the size of the
organisation to be approved. Full quality functions are not required but may be
accepted if already in place.
4.2 The Exposition should contain a capability list. This list may include blanket coverage
for aircraft in the Simple or Intermediate categories (see paragraph 1.2.1 of BCAR A8-
20), but will be on a type-by-type basis for Complex aircraft.
4.3 The Exposition should have a BCAR approval certified statement signed by the
accountable manager as follows:
This Exposition defines the Organisation and Procedures upon which Civil Aviation
Authority Approval AI/....../.... is based. These procedures are approved by the
undersigned and must be adhered to as applicable when the Organisation is
performing the functions relating to which the approval is granted.
It is accepted that the Organisation's procedures do not over-ride the necessity for
compliance with the Air Navigation Order, British Civil Airworthiness
Requirements or other requirements published by the Civil Aviation Authority from
time to time.
The Company will ensure, prior to undertaking any overhaul, repair, modification,
test or inspection, that all Manuals, Service Bulletins, Modification Standards,
Mandatory Documentation, Special Tools (including test equipment) and any
necessary training required by the Manufacturer or Civil Aviation Authority are
obtained.
HEAPWARBIRD LTD
signed
Accountable Manager.

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Appendix 2

BCAR CHAPTER A8-20 EX-MILITARY AIRCRAFT

MAINTENANCE ASPECTS - M5 APPROVAL

1 Introduction

This Appendix provides guidance on the organisational requirements and

responsibilities for organisations requiring to hold a Group M5 approval in accordance
with paragraph 1.2.2 of BCAR A8-20. This approval is required for organisations to
maintain and recommend that the Authority renew a Permit to Fly for an ex-military
aircraft.

2 Personnel and Staff

2.1 The organisation should nominate the key engineering staff who are to support its
operation. These staff should be employed under a formal agreement between the
organisation and the staff member concerned with details of their terms of reference
as senior members of the organisation provided within the exposition.
2.2 The organisation should have a minimum of one staff member who is nominated as
a senior engineer who holds CAA licences without type ratings appropriate to the
aircraft to be maintained. Where this cannot be satisfied in the case of established
organisations, well known to the Regional Office, an unlicensed person with long
association with the CAA may be acceptable.
2.3 Additional part time staff may be used to provide additional resources providing there
are in existence suitable control procedures within the organisation exposition. A
form of agreement should be raised which gives detailed terms of reference in writing
to the volunteer.
2.4 CAA Forms AD458 Biographical Details for persons nominated under the A8-20
approval should be submitted to the regional office.

3 Organisation Personnel Authorisations

3.1 A nominated senior person as required under BCAR A8-20 paragraph 3.2(b) will be
accepted by the CAA to grant personnel authorisations under the organisation's
approval, appropriate to the staff who are to carry out nominated functions and
activities whilst contracted to or in the employ of the organisation.
3.2 A limited number of full authorisations may be granted, on a restricted basis, for
issuing a flight release certificate after scheduled maintenance or defect rectification.
In respect of aircraft nominated under A8-20 paragraph 1.2.1 as Complex, the
signatory of the Flight Release Certificate (see BCAR A3-7 appendix 2) would be a
suitably qualified person with appropriate practical experience, gained whilst
employed by either the manufacturer or an acceptable Military Authority.
3.3 Authorisations may be granted for specific functions as are seen to be necessary to
support operations either at the main base or away from that base. e.g. taxiing,
ground runs, pre-flight checks etc.
3.4 Records of authorisations given shall be kept and issued to the persons involved.

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4 Inspection and Certification

The organisation should ensure that all maintenance and defect rectification is
recorded and certified by the appropriate staff with details of the necessary action
taken. The procedure should be in a form acceptable to the CAA and take due account
of any flight record system required by CAP 632 for the operation that is supported.
It is expected that the normal aviation practices for the documenting of maintenance
checks and recording defects with subsequent rectification will satisfy this
requirement.
Maintenance check sheets should provide information of the amendment status of
the maintenance programme when work is certified. A work records control system
should be established to show the status of completion of work at any time and be
readily capable of review.

5 Maintenance Programmes

5.1 The compilation of maintenance programmes and the associated schedules should
where possible be based upon the original aircraft type documentation and should
reflect both the original servicing elements and any additional requirements of the
CAA. This should take into account any known service experience such as NDI
programmes and supplementary inspections and be adjusted to suit the aircraft
utilisation rate. The need to change the periods from flying hours or cycles to calendar
based periods should be considered and agreed by the CAA. Part of the maintenance
schedule should contain life limitation listings and reflect any component overhaul or
life limitations, fatigue limits or other significant data.
5.2 In some instances major structural inspections are not included in the military service
notes, this should be taken into account when compiling the programme of
maintenance. Where possible the original manufacturer should be consulted if doubt
exists regarding the adequacy of the structural programme, or the CAA Aircraft
Certification Department.
5.3 The maintenance schedules for the aircraft should also take into consideration the
general requirements of the LAMS schedule; e.g. compass swings, radio checks etc.

6 Spares Procurement

6.1 All the required spare parts and components procured for this type of aircraft should,
wherever possible, be obtained from original sources or through known and reputable
distributors.
6.2 Where items are obtained via Military, or other related sources these items should be
inspected and evaluated with regard to physical condition, life details, completeness
of records, modification status and compatibility to aircraft serial by the organisation
purchasing the item. Acceptance of the item following such inspection should be
assessed and recorded by a certifying engineer prior to fitment. This procedure
should be reflected in the associated exposition.
6.3 During the conditional assessment of components consideration must also be given
to the need to carry out an internal examination to assess the effects of age and
corrosion. It may be necessary to carry out a strip investigation, partial or full, if the
component's condition cannot be readily assessed by other means, e.g. boroscope,
NDT, etc.

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6.4 Structural components, forging and castings should be visually inspected for
condition and damage and consideration given to utilising NDT techniques to assist
such an inspection, whenever possible the manufacturers advice should be sought.
6.5 Engines, propellers and gearboxes should be overhauled prior to their initial fitment
to the aircraft except where the item's service history and current status is known and
documented. The overhaul should be carried out by an organisation approved for the
purpose or by a company as agreed within the terms of the A8-20 organisation's
exposition.
6.6 AGS and Standard Parts. Standard aircraft hardware such as fasteners, e.g. nuts and
bolts, should be purchased from normal aviation sources. These should conform to
the specified part number in the manufacturer's maintenance information. Where this
information differs from the current specifications for those items in civil use,
acceptance via a certificate of conformity showing equivalence will suffice.
6.7 Where items are no longer manufactured or available from known sources, caution
should be exercised on the acceptance of items unless their serviceability can readily
be determined by inspection and/or overhaul. The use of alternative parts in the
overhaul or maintenance of aircraft or components is only permitted when supported
by the agreement of the manufacturer or an approved Design Organisation, through
modification action, or where agreed in individual circumstances with the CAA
Regional Office.

7 Arrangements for Maintenance of Specialised Equipment

7.1 The arrangements for the maintenance and overhaul of items and systems as detailed
in paragraphs 3.2. and 3.4 of A8-20 Supplement No. 1 should be defined in the
organisation's exposition. Where the organisation does not hold the capability itself
to satisfy this requirement, suitable letters of agreement with appropriately approved
organisations should be held detailing the provisions made to cover all such
undertakings.

8 Component Manufacture

8.1 With regard to the manufacture of components, the A8-20 approval is not intended to
replace the requirements of a BCAR A8-2 Group A2 Supplier Approval. Manufacture
of non critical parts may be permitted subject to the organisation having the
necessary drawings and facilities, equipment, etc. where the part is intended to be
produced only for an aircraft supported by the approved organisation.
8.2 Major structural items should be manufactured under the control of a BCAR A8-2
company to the required specifications and original drawings, unless agreed
otherwise in advance by the local CAA Regional Office. Any deviation in material
specification, heat treatment or manufacturing process will need to be supported by
technical justification and a prepared case should be submitted in the form of
individual requests to the CAA Regional Office.
8.3 Manufacture to pattern is normally prohibited, however specific items may be agreed
by the CAA Regional Office in conjunction with Aircraft Certification Department.

9 Modifications

9.1 The normal CAA procedure as detailed in BCAR A2-5/B2-5 will apply. The E4 approval
granted under BCAR A8-20 does not confer approval of any activity to design or
approve modifications on this class of aircraft. Minor modifications to aircraft or

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CAP 562 Civil Aircraft Airworthiness Information and Procedures

components are required to be submitted either to the local CAA Regional Office,
along with technical justification, to substantiate such a change or alternatively be
submitted via a suitably CAA approved design organisation.
9.2 Significant changes to the aircraft in terms of powerplant changes, propeller type,
alternative material specifications or equipment changes may be the subject of major
modification action, but all such applications should be discussed with the CAA
Regional Office concerned in the first instance.

10 Secondary Site Control

10.1 Where the organisation intends to conduct activities at sites other than the main site
of the approval but remaining under the control of the basic approved organisation,
the additional geographical locations will be considered as secondary sites for
approval purposes. The secondary sites should be environmentally suitable for the
needs of the operations to be carried out and defined in the exposition. Short term
agreements for secondary sites may be arranged by letter with the local CAA
Regional Office and may be subject to any special conditions that are deemed
necessary.
10.2 The term secondary site is not intended to include activities associated with line
support of the aircraft during normal operations. Repairs or scheduled maintenance
away from base may require to be reflected in a short term agreement as above.

11 Recommendations for the Renewal or Validation of Permits to Fly

11.1 The Permit to Fly will be a non-expiring document that requires an associated
Certificate of Validity. These documents will be contained in a wallet.
11.2 The validation will be predicated upon an inspection report prepared by an
organisation approved for the purpose (A8-20), and a recommendation made on Form
AD202P.
11.3 Following an annual inspection, the approved organisation will submit the following
documentation to the CAA:
a) AD200 application for renewal;
b) Statutory fee;
c) Flight Test (if applicable - see 11.8);
d) AD202P recommendation.
11.4 The documentation listed in 11.3 should be sent to the CAA at the following address:
Applications and Approvals Department
Civil Aviation Authority
Safety Regulation Group
Aviation House
West Sussex RH6 OYR
11.5 Subject to the submitted documentation being acceptable, a Certificate of Validity will
be returned, valid for a twelve month period. The Certificate should be placed in the
'pocket' of the Permit to Fly wallet.
11.6 The validation process may be anticipated by a maximum period of thirty one days
without loss of the twelve month consecutive validity period. If the anticipation period
is more than thirty one days the Certificate of Validity will be limited to one year and

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CAP 562 Civil Aircraft Airworthiness Information and Procedures

thirty one days following the recommendation date. If the validity certificate has
expired, the validity certificate will be dated from the date of receipt by the CAA and
expire one year from the recommendation date.
11.7 If the Certificate of Validity has expired and a flight test is required, it will first be
necessary to submit the AD200 application together with the statutory fee in order
that the CAA may issue a Permit to Fly for test purposes. Following completion of the
test, the flight test report and the AD202P should be submitted as in 11.3.
11.8 The Flight Test period has been extended to three years but must be completed for
the first issue of the non-expiring Permit to Fly. The next flight test due date will be
stated on the Certificate of Validity.
NOTE: AD202P pads will be supplied by the CAA.

12 Exposition

12.1 The Exposition should be kept as simple as possible appropriate to the size of the
organisation to be approved. Full quality functions are not required but may be
accepted if already in place.
12.2 The exposition should state the level of basic approval granted in the terms of one or
more of the following:
a) Maintenance of airframes and engines;
b) Overhaul of engines;
c) Restoration of airframes and associated systems;
d) Component Overhaul.
12.3 The Exposition should contain a capability list. This list may include blanket coverage
for one or more Groups (see paragraph 1.2.2 of BCAR A8-20) but will specify
individual aircraft types for those classified as Complex in accordance with paragraph
1.2.1(c) of BCAR A8-20.
12.4 The Exposition should have a BCAR approval certified statement signed by the
accountable manager as follows:
This Exposition defines the Organisation and Procedures upon which Civil Aviation
Authority Approval AI/ ---/--- is based.
These procedures are approved by the undersigned and must be adhered to as
applicable when orders qualifying for release under the Approval are being
progressed.
It is accepted that the Organisation's procedures do not over-ride the necessity
for compliance with the Air Navigation Order, British Civil Airworthiness
Requirements or other requirements published by the Civil Aviation Authority from
time to time.
The Company will ensure, prior to undertaking any overhaul, repair, modification,
test or inspection, that all Manuals, Service Bulletins, Modification Standards,
Mandatory Documentation, Special Tools (including test equipment) and any
necessary training required by the Manufacturer or Civil Aviation Authority are
obtained.
HEAPWARBIRD LTD
signed
Accountable Manager.

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Leaflet 11-43 Approval of Maintenance Schedules For

Aircraft Above 2730 kg MTWA not Operated
for Commercial Air Transport

(Previously issued as AIL/0171. This leaflet has been revised and should be read in its
entirety.)

PURPOSE: This Leaflet is intended to provide guidance material for the compilation of a
maintenance schedule for aircraft within the above group.

REFERENCES: CAA Standard Maintenance Practice No. 19.

1 Introduction

1.1 The CAA is changing the current Certificate of Airworthiness (C of A) renewal process
which has historically required CAA technical staff involvement at the renewal
interval. One aspect of this change is that CAA Approved Maintenance Schedules are
required for aircraft within this scheme. A principal benefit will be the flexibility of
renewing C of As without disrupting the aircraft operation and minimising CAA
technical staff effort.
1.2 Where the aircraft maintenance schedule is approved by the CAA a recommendation
to renew the C of A can be made to CAA by an organisation approved under BCAR
A8-3 Supplement No.2. As of 1st April 1995, all aircraft within this group will be
required to be maintained to a CAA Approved Maintenance Schedule.
1.3 In order to ensure that the Approval process is as simple as possible the procedures
assume the use of the manufacturers schedule (as amended), and Standard
Maintenance Practice No. 19 (including Appendices A, B and C).

2 Maintenance Schedule Approval Procedure

2.1 A copy of Standard Maintenance Practice No. 19 is available in CAP 562 - CAAIP Part
14 as Leaflet 14-19 and may be copied for use.
2.2 The SMP is formatted with space for details to be added. It can however, be produced
and formatted on a word processor providing the intent is not changed. This
document will identify the manufacturer's schedule reference and revision status. It
must also contain information regarding the aircraft type, serial no., and the
registration mark. The CAA will record the aircraft registrations and schedule
references. Anticipated annual utilisation is to be stated to enable the operator/
contracted maintenance organisation to assess the maintenance periods against the
manufacturer's predicted utilisation.
2.3 The SMP 19 contains three Appendices:

Appendix A Which should be completed to address supplementary maintenance

requirements. This should list, Equipment Manufacturer's Mainte-
nance Requirements, and Life Limits not covered by the Airframe
Manufacturer's maintenance programme.

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Appendix B Which should be completed to address Maintenance Tasks arising

from SBs, SLs and other service information as required by the
Operator.
Appendix C Which gives guidance on permitted variations to Maintenance peri-
ods.

2.4 When SMP 19 has been completed two copies should be submitted to the CAA
Survey Department Regional Office with a copy of the manufacturer's schedule. The
Regional Office will assess the submission and will advise if the manufacturer's
schedule is acceptable. Approval of this submission will be signified by the issue of
Form AD271, and the allocation of a CAA Approval Reference.
2.5 The operator must instigate a formal method of amendment. Any proposed changes
to the AD271 or SMP19 shall be submitted to the CAA Survey Department Regional
Office for approval. Amendments to the manufacturer's programme must be
incorporated and advised to the CAA Regional Office, without the need for individual
CAA approval.
NOTE: Amendments may be in the form of Service Bulletins issued by the
manufacturer prior to full revision of the maintenance programme.

3 Alternative to Manufacturer's Schedule

3.1 It is not the CAA's intention to promote the use of an Alternative to the Manufacturers
schedule. However, if the operator or his contracted maintenance organisation
wishes to use an alternative schedule, than a detailed submission should be made to
the CAA setting out the justification for such an alternative and this should be
accompanied by suitable substantiation for the revised scheduled maintenance tasks.
A fee may be charged for this process.
3.2 The schedule with the completed SMP 19 should be sent to the CAA Survey
Department Regional Office. Once the schedule has been reviewed any comments
raised will be communicated to the applicant for corrective action to be taken. When
all outstanding items have been addressed, approval will be signified by issue of
AD271, and the allocation of a CAA Approval Reference.

4 Alignment Check

Where the aircraft is transferred from one schedule to another, an alignment or

bridging check will be required. The extent of the check should be decided by the
operator/contracted maintenance organisation following a review of the maintenance
carried out to date, but will as a minimum, need to ensure that the requirements of
the new schedule have been met.

5 Maintenance Certification

The organisation contracted to carry out maintenance of the aircraft will enter the
details of the maintenance carried out in the appropriate Aircraft Log Books and
indicate the reference number of the schedule used. This reference number will be
shown on the Approval Document AD271. At the time of C of A renewal an annual
check in the form of a Maintenance Review is to be carried out. A statement to this
effect must be made in the Aircraft Log Book. (Details of this annual check can be
found in SMP 19.)

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Leaflet 11-44 Applications for the Approval of CAA

Supplemental Type Certificates

(Previously issued as AIL/0189)

PURPOSE: To advise applicants of the information they will have to provide in support
of an application for the approval by the CAA of a Supplemental Type
Certificate (non-EASA) for an aircraft, engine or propeller as defined by Annex
II.
REFERENCES: Regulation (EC) No 216/2008 of 20 February 2008 including amendments, on
Common Rules in the field of Civil Aviation and establishing a European
Aviation Safety Agency.
Regulation (EC) No 1702/2003 of 24 September 2003, including
amendments, Implementing Rules for Airworthiness and Environmental
Certification of Aircraft and Related Products, Parts and Appliances, as well
as for the Certification of Design and Production Organisations.
EASA Website: www.easa.europa.eu
CAA Scheme of Charges, Official Record Series 5
Part 21.101; Changed Product Rule

1 Introduction

This Leaflet is for Annex II aircraft only and does not apply to any product under the
authority of EASA as defined by Regulation 216/2008. Mutual recognition is not
automatically achieved within EASA Member states for STCs to Annex II products.
This Leaflet is to inform owners, operators, designers and modifiers of aircraft of the
CAA procedures for the approval of Supplemental Type Certificates (STC). The
Leaflet has particular emphasis on the information which the applicant will be
expected to provide to the CAA. The procedure to be followed is similar to that
required by EASA under Regulation 1702/2003 however it must be noted that EASA
has developed their own procedure for STC applications that can be found on the
EASA website.
The EASA STC Procedures classify STCs from a procedural point of view into
Significant and Non-Significant. A Significant 1 STC is defined as "a major design
change, which necessitates a change to the Type Certification basis referenced in the
TCDS for the Product". A Non-Significant STC is any other STC.
It is important to note that these STC Procedures are an alternative and not a
replacement for the Airworthiness Approval Note (AAN) Procedures.

2 Application

Application for issue of an STC to an Annex II Product may be made to the CAA by:
a) A UK applicant;
b) A non-UK applicant for an STC to be validated.
NOTE: This is conditional on the applicant being subject to the jurisdiction of an
Authority, which has entered into, or is prepared to enter into an
Arrangement with the UK.
Application must be made on the relevant CAA Form No STC01 (Appendix 1), to
Applications and Approvals Department together with the appropriate fee.

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3 Classification

At time of application, the applicant must propose the category of the STC with
appropriate justification. This justification will be reviewed in accordance with the
criteria defined in Part 21.101 at the discretion of the CAA.

4 Registration

When the application has been accepted, the Project will be issued with a CAA STC
Project Number taken from the CAA STC Project Number register. The register for
aircraft and engines/propellers is maintained by Applications and Approvals
Department.
The STC Project Number will be used as the CAA charging number as well as the
reference for the department file and all correspondence during the Project.
The STC Project Number will be in the form PNxxxxx and will not be the same as the
STC Number.

5 Design Investigation

5.1 CAA Team

The CAA will identify a team having regard to the Product, the applicant, the
complexity of the Project, and the anticipated length of the Project. The Team Leader
will normally be from either Aircraft Certification Department or Engineering
Department and will be responsible for the management of the STC Project.
The Team Leader will advise the applicant of the Team membership, which may
comprise representatives from within the Airworthiness Division (including Survey
Department) and Flight Operations Division.
5.2 Design Organisation Approval
The Applicant will be required to hold a Design Organisation Approval recognised by
the CAA. The Team Leader will be responsible for ensuring that the terms of the
applicant's Approval, as applicable are observed during the certification exercise. The
Team will determine if the Terms of Approval are sufficient to cover the scope of the
STC. If necessary the Applicant may be required to apply to the CAA to update the
Terms of Approval in order to include the new STC.
5.3 Information Exchange
When the CAA is validating an STC from a non-UK applicant the Team Leader is
responsible for ensuring appropriate information exchange links with the Authority of
the State of Design.
The applicant will advise the Team Leader of any arrangement with the Type
Certificate Holder. This information is requested on the Application Form.
5.4 Certification Basis
For a Non-Significant STC the Certification Basis is that referenced in the applicable
CAA Type Certificate Data Sheet for the Product.
For a Significant STC the Certification Basis will be agreed between the Team and the
Applicant.

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5.5 Demonstration of Compliance

STC Definition Document
The applicant should provide a STC Definition Document (or equivalent
documentation) to the Team. This document provides a summary of the change,
including a description of the change and reference to supporting drawings, diagrams
and schematics, as well as a reference to compliance and service documentation. An
example of a template for such a document is at Appendix 2 together with guidance
on how it should be completed.
Where the CAA STC is a validation of a Major change from a non-UK applicant an
alternative summary document specified by the certificating Authority can be
accepted as long as it provides the equivalent information.
Certification Plan
The Team Leader will request the applicant to submit a certification plan, which
describes the means by which compliance with the requirements of the Certification
Basis affected by the change will be demonstrated, including any tests, together with
the projected time-scales. Appendix 3 provides guidance on the information which
should be provided by the applicant.
The plan will be reviewed by the Team for acceptability. The Team will discuss means
of compliance with the applicant as necessary to ensure mutual understanding. The
applicant will be required to set up a process to allow the status of each item in the
certification plan to be tracked and recorded throughout the programme.
Compliance Record
The applicant will provide certification reports to the Team, which will formally record
compliance with each applicable requirement. Team Members will be allocated the
task of reviewing and accepting the reports by the Team Leader, having regard to
their speciality and experience. Following a review of their decisions, the applicable
compliance sheet will be closed, with a reference to any supporting reports, raised in
issue, and circulated by the applicant. CAA Management involvement will be
necessary where the proposed demonstration of compliance is controversial or
where the applicant and Team are unable to agree.
Closed compliance sheets will be entered in the Compliance Record Document. An
index of certification reports will be maintained by the applicant. The index should be
regularly updated to show the CAA approval status. Copies of the certification plan
and the report index will be retained by the CAA.
Witnessing of Tests and Physical Inspections
The test programme will be reviewed by the Team Leader who will determine with
the Team which tests are to be witnessed, and physical inspections made. Team
Members will be allocated specific tests and inspections. The applicant will be
advised of this information in order that the Team Members concerned may be
advised of test/inspection dates in good time.
Flight Testing
The UK Air Navigation Order (ANO) 2005 (as amended) Article 8 specifies the
circumstances under which an aircraft may fly. When an aircraft is modified its
Certificate of Airworthiness or Permit to Fly is rendered invalid until such time as the
modification is approved by the CAA (ANO 2005 (as amended) Article 10). It follows
therefore that an aircraft, which has modifications embodied which are not approved
by the CAA may not fly except under specific flight testing provisions granted by the
CAA.

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The normal mechanism for the authorisation of exploratory test flights is for the
organisation that proposes to conduct the flying to obtain a "permit to fly for test
purposes" approval. Where it is necessary to conduct flight trials to establish
compliance with the approval basis, and by implication to provide the evidence
necessary to approve the modification, the permit must be in force throughout the
trials.
Where there is already evidence of satisfactory flight characteristics, such as prior
certification by the State of Design (for STC validations), or in the case of a
modification it can reasonably be concluded that there will be no detrimental effect,
flight testing may not necessarily be required for approval of the design. If
nevertheless it is considered necessary to fly the aircraft in order to confirm correct
functioning or performance, that flight will normally be carried out after approval of the
STC.
Certification Meetings
The Team Leader will review progress with the applicant on a regular basis. If
meetings are required the applicant shall issue minutes. The minutes will be
circulated to Team Members as appropriate.
Documentation and Manuals
The applicant will provide supplements to manuals or documents required by the
applicable requirements for approval by the Team.
Accomplishment instructions (e.g. Service Bulletins) will be prepared by the applicant
and distributed as approved data. Approval of the instructions will be granted by the
Team or through the applicant's design approval privilege when held.

6 Responsibilities of the Applicant

It is the responsibility of the applicant to define and record all activities leading to the
issue of the STC. The applicant must determine the requirements that are applicable,
and obtain the agreement of the CAA to the approval basis. The applicant must be
satisfied that compliance with all of the applicable requirements has been
demonstrated and that evidence of compliance, including assumptions and methods
used, is recorded and retained. It is the responsibility of the applicant to provide to
the CAA the information needed to complete the approval.
Efficient progression of the approval will be heavily dependent upon the timely
submission of information, that is both complete and of good quality. Where the CAA
has to make requests for clarification, correction or additional data this will inevitably
delay the process and increase the staff hours expended by the CAA, in turn leading
to higher charges. Where incomplete or poor quality information is submitted, the
CAA may suspend the approval process and require the applicant to re-submit using
an Approved Organisation having greater expertise and ability to complete the task.
The applicant should advise the CAA at the time of application of the proposed
programme timescale, and of the proposed means of compliance with the approval
basis. In this respect applicants are requested to note that the CAA commonly has
no advance notice of the applications it receives and has to manage its finite
resources to meet the diverse demands of the many and various applicants. Efficient
management of resources is only possible if the timescale for each approval is
reasonable, and allows for the inevitable multi-tasking of CAA staff.

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7 STC Issue

After the Team has been satisfied by the compliance demonstration, the applicant will
submit the final issue of the STC Definition Document and a final Compliance
Checklist with a Declaration of Compliance to the Team Leader. These will be held
on the CAA file. The Team Leader will then sign a Final Statement of Compliance.
The CAA STC will then be issued to the applicant (Appendix 4).

8 Post STC Activities

Amendments to STCs are only allowed by the STC holder. The change will need to
be classified Major/ Minor, and if major will follow a similar procedure as for the initial
STC. A Significant change to an STC will require a new STC. The principles laid out
in Part 21 will be followed where possible. The involvement of the Team will depend
on the level of change.

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CAP 562 Civil Aircraft Airworthiness Information and Procedures

Appendix 1 CAA Application Form

Civil Aviation Authority

United Kingdom
APPLICATION FOR SUPPLEMENTAL TYPE CERTIFICATE
This form should be completed and forwarded together with the appropriate fee, as notified in
the Current CAA Airworthiness Scheme of Charges, to: Civil Aviation Authority, Airworthiness
Division, Application and Approvals Department, Aviation House, Gatwick Airport South, West
Sussex RH6 0YR.

Applicant: Tel No:

Address: Fax No:

E-Mail:

Post Code:

Aircraft/Product Type:

TCDS Ref:

Location of aircraft for inspection: Applicant Modification No:

Proposed Classification: Design Organisation:

Significant/Non-Significant
CAA Approval Ref:
Justification:
Production Organisation:

CAA Approval Ref:

STC Title:

Requested Date for STC Issue:

Flight Manual Affected (delete as applicable): Arrangement with TC Holder (delete as

applicable):
Yes/No Yes/No

I hereby declare that the above particulars are true in every respect. I agree to pay any further
charges in connection with this application, which may be notified by the CAA, including costs
subsequently incurred by the CAA for work carried out on post-certification activities.I understand
and accept that the STC, when issued, will be published in databases accessible to the public.

Signature: Name: Date:

Position:

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Reserved for CAA use only

£ ACP Number Action Project No.

Received by Surveyor Date

Date Regional Office Initials

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CAP 562 Civil Aircraft Airworthiness Information and Procedures

Appendix 2 STC Definition Document

Applicant Document Ref:

Issue: Date:

CAA Design Approval Ref: Page 1 of

CAA Project Ref:

CAA UK
SUPPLEMENTAL TYPE CERTIFICATE
SIGNIFICANT NON-SIGNIFICANT
DEFINITION DOCUMENT
Delete as appropriate

Product Modified:

STC Title/Description:

CAA Production Approval Ref:

Certification Basis:

Requirements Affected:

Compliance Plan Ref:

Compliance Record Ref:

Drawing List:

Manuals Affected/ Flight Manual

Supplement Ref:
Airworthiness Limitations

Maintenance Manual

Maintenance Schedule

Electrical Load Analysis

MMEL

Weight & Balance Manual

Accomplishment Instructions Ref:

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CAP 562 Civil Aircraft Airworthiness Information and Procedures

Guidance Notes for Compiling STC Definition Document.

Applicant Company name of applicant for STC.

Document Reference Applicant internal reference number for STC Definition Document
that could be used as referenced data on the STC when issued.
CAA Design Approval Applicant's Design Approval reference.
Reference
CAA Project Number The CAA Project reference number will be supplied by CAA. This
will be the internal CAA tracking number pending the granting of
the CAA STC.
Significant /Non- Delete as appropriate. STCs are classified from a procedural point
Significant of view into Significant and Non-Significant. A Significant STC is a
major design change that necessitates a change to the
Certification Basis of the basic Product, as referenced in its Type
Certificate Data Sheet. A Non-Significant STC is any other STC.
Product Modified The Product changed by the STC. The full Type/Variant designation
should be given.
STC Title/Description Title of STC. This should include a brief description of the STC to
clearly summarise the physical changes to the Product.
CAA Production The applicant should identify the production organisation(s) that
Approval Reference will receive approved data and assistance in order to permit
production of airworthy parts eligible for installation as part of the
STC.
Certification Basis Reference should be included to a document presenting the
Certification Basis of the Product being changed, generally the
Type Certificate Data Sheet. The Certification Basis identifies the
applicable standards against which the applicant must show the
proposed change complies.
Requirements Reference is required to all those requirements of the Certification
Affected Basis, including environmental requirements i.e. noise and
emissions, affected by the change and for which a compliance
statement is required to be included in the Compliance Record.

In addition, design requirements that must be complied with in

order that operational requirements can be satisfied should be
included e.g. JAA TGLs for BRNAV, EGPWS, RVSM and any
specific design requirements relating to equipment required by
operational rules such as JAR-OPS.
Compliance Plan Reference to the compliance plan should be included. The plan
Reference itself should provide at least the following for each compliance
subject:
• Affected Requirement (CS, BCAR etc.) and its amendment level;
• Means of Compliance, e.g. calculation, test, design review,
inspection etc.
Any specific flight testing provisions required to be granted by
CAA, reference BCAR A8-9, should be noted in the plan.

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CAP 562 Civil Aircraft Airworthiness Information and Procedures

Compliance Record Reference to the compliance record (which itself should include
Reference reference to all compliance reports) should be included.
Drawing List This must include all drawings introduced by the change. Where
there is a significant number of drawings, reference to a Master
Drawing List is acceptable, as long as this provides a ready
reference to all the other drawings.
Manuals Affected All manuals affected should be indicated by inclusion of a
reference to the required supplement/amendment.
Accomplishment Reference to the accomplishment instructions document provided
Instructions to installers of the STC should be included.

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Appendix 3 Guidance for Compilation of Certification

Documents

The following should be used as an aid when determining the content of the Certification
document(s) required by the STC procedures. The applicant should agree the specific project
documentation with the CAA.
Applicants may decide whether to compile one or more documents which contain this
information. As the project progresses the document(s) will be maintained jointly by the
applicant.

Applicant’s Certification Name and contact details of key personnel involved in

Personnel programme, e.g. programme manager, technical and
airworthiness staff, and design signatories with their
specialisation accepted by CAA.
Description of This should include a system/configuration definition with
Modification associated drawings, diagrams, and schematics to summarise
the physical change to the aircraft.
Liaison with Production The applicant should identify the production organisation(s) that
will receive approved data and assistance in order to permit
production of airworthy parts eligible for installation as part of
the STC.

This should also include, as necessary, details of the parts

approval status and a conformity inspection plan.
Operator Focal Point Name and contact details of the operator’s representative(s).
Aircraft and Location Details of the aircraft and its location for inspection/certification
purposes.
Foreign Aviation Details of any foreign aviation authority involved in the STC
Authority approval process.
Arrangement with Type Details of any arrangement entered into with the Type Certificate
Certificate Holder Holder in support of the STC application where applicable.
Certification Schedule A schedule of certification activities that will be agreed between
the CAA and the applicant and maintained by the applicant
through the programme.
Certification Basis The Certification Basis identifies the applicable standards to
which the applicant must show compliance. It also includes the
need for special conditions, exemptions, and equivalent safety
findings, if any. An issues list should be included to highlight for
resolution those special requirements and other areas that may
be significant, even though they may not warrant a special
condition, exemption, or equivalent safety finding. Reference
should also be made to the applicable CAA design requirements
for the issue of a Certificate of Airworthiness.

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CAP 562 Civil Aircraft Airworthiness Information and Procedures

Operational Identification of the design requirements that must be complied

Requirements with in order that operational requirements can be satisfied. For
example: JAA TGLs for BRNAV, EGPWS, RVSM and any specific
design requirements relating to equipment required by
operational rules such as JAR-OPS.
Environmental The applicable noise and emissions requirements.
Requirements
Compliance Matrix/ A table listing for each affected part of the aircraft:
Check List a) the compliance subject;
b) the applicable requirement (BCAR etc.) and its amendment
level;
c) the method of compliance, e.g. calculation, test, design
review, inspection etc.
Test Requirements Details of the various tests identified in paragraph 12 above (e.g.
laboratory, ground, flight etc.) together with planned test
locations, approval of test facilities, and dates. This section
should contain any requirements for the planning, preparation,
and conduct of flight testing. The applicant should identify the
need for any specific flight testing provisions to be granted by
CAA.
Compliance Documents A list of the compliance documents that will be produced
including the document/ drawing reference number, title,
applicable requirement, and proposed submittal date where
applicable.
Manuals Specification, or reference to a document specifying, changes to
documents and placarding. Commonly this may include:
a) Flight Manual;
b) Maintenance Manual;
c) Airworthiness Limitations;
d) Maintenance Schedule;
e) Electrical Load Analysis;
f) MMEL;
g) Weight and Balance Schedule;
h) Type Certificate Data Sheet(s).
Instructions for A statement of, or reference to documents defining, any
Continued inspections or other actions required to maintain airworthiness
Airworthiness in-service.

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Appendix 4 Example Supplemental Type Certificate

United Kingdom
Civil Aviation Authority
SUPPLEMENTAL TYPE CERTIFICATE
[STC No]
Pursuant to the National Regulations for the time being in force and subject to the conditions
and limitations specified below, the CAA-UK in accordance with its National Procedures,
hereby certifies to:
[Applicant]
[Address of the Applicant[
[CAA design approval reference, if applicable]
that the change in the Type Design to the following product, as specified herein, meets the
appropriate [applicable code] requirements.

Basic Product Type Certificate Number:

Type:
Variant:

STC Title:
STC Definition Document:
Flight Manual Supplement: , or later approved revision.
Airworthiness Limitation Supplement(s):

Conditions and Limitations:

• Compatibility of this installation with previously installed equipment must be
determined by the installer.
• Subject to compliance with the provisions in force at time of issue, this Certificate and
associated data shall remain valid until surrendered, withdrawn or otherwise
terminated.
• If transfer of this Certificate is requested, the Certificate will be reissued.

Date of application: ………………..

Date of issue: ………………..
Date of re-issue: ………………… Signed………...............................
(Insert signatory’s name)
For the United Kingdom CAA

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Leaflet 11-45 The Rebuilding and Restoration of Aircraft

(Previously issued as AN 11)

1 Introduction

The CAA has been made aware that additional guidance is necessary for those
engaged in the rebuilding or long term restoration of aircraft, to alert them to the
airworthiness requirements and the monitoring of such projects by the Civil Aviation
Authority Regional Offices.

2 Applicability

This Leaflet is applicable to aircraft that have previously held a UK/EASA Certificate of
Airworthiness or Permit to Fly.

3 Definition

3.1 Restoration is a generic term that may include any one or combination of overhaul,
repair, inspection, modification or replacement activity, which is to be performed on
an aircraft where the UK Certificate of Airworthiness or Permit to Fly has lapsed for
some years. Such an aircraft is likely to require extensive dismantling and inspection
to determine the extent of work needed to restore it to an airworthy standard.
3.2 Aircraft rebuild projects include the return to an airworthy condition of any aircraft
where the UK Certificate of Airworthiness or Permit to Fly has ceased to be in force
due, for example, to accident or incident damage, the use of major parts from other
aircraft of the same type, significant corrosion or major overhaul.

4 Background

4.1 From time to time the CAA is not made aware of major restoration or rebuild projects
until they have reached the final stages of completion. This means that the necessary
CAA stage inspections or surveys have not been carried out.
4.2 In many restoration cases the necessary repairs, including the production of parts no
longer available from the original manufacturer, have not used approved data such as
the original manufacturer's repair manual or design drawings, and have been outside
the scope of the certification privileges of the Licensed Engineer. A number of rebuild
projects have used structural components and major assemblies where the
provenance and traceability of the parts fitted has been questionable.
4.3 For aircraft which held Certificates of Airworthiness, all replacement parts must either
conform to the part number specified by the manufacturer for the particular aircraft
type, model and serial number, or be approved under modification procedures in
accordance with BCARs or EASA Regulations, as applicable. All replacement parts
from whatever source must be serviceable and accompanied by appropriate
documentation.
4.4 In the cases described in paragraphs 1 and 2 there have been delays in the CAA
approval of the project and subsequent issue of the Certificate of Airworthiness or
Permit to Fly and in some cases dismantling has been required to enable inspections
to take place which could have been avoided by regular contact between the
Licensed Engineer (or owners) and CAA Regional Offices.

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CAP 562 Civil Aircraft Airworthiness Information and Procedures

5 Requirements

5.1 The attention of Certifying Engineers concerned with major rebuilding projects or the
long term restoration of aircraft is directed to the relevant chapters of BCAR Section
A/B, EU Regulations 1702/2002 and 2042/2003, as applicable. Reference should be
made to the table below to assure compliance with the relevant regulations.

Non EASA EASA

Requirement
Aircraft Aircraft

It must be shown that the aircraft conforms to type BCAR A/B3-2 Part 21.A.181
design and any repairs and changes conform to Paragraph 1.3 and 21.A.183
appropriate data.

The aircraft must be constructed under the supervision BCAR A3-2 Part 145.A.42
of an organisation approved by the CAA for the Paragraph 4 and M.A.501
purpose. The restorer or rebuilder must show proof
that the major components proposed for use on the
restored or rebuilt aircraft are original, i.e. were
manufactured by or for the organisation who obtained
the first Certificate of Airworthiness or Type Certificate
for the aircraft or that they are an approved alternative.
Failure to provide sufficient proof will result in the
aircraft being refused either a Certificate of
Airworthiness or a Permit to Fly.

A Certificate of Release to Service shall only be issued BCAR A/B6-2 ANO 2005 (as
for overhaul, repair, replacement, modification or Paragraph 8 amended)
inspection when the signatory is satisfied that the and ANO 2005 Article 16, 17,
work has been properly carried out having due regard (as amended) Part 145.A.50
to the use of manuals, drawings, specifications and the Article 16 or 17 or M.A.801,
use of calibrated tooling. as applicable as applicable

In the case of structural repairs to aircraft, where the BCAR A/B6-7 Part 21
repairs are of a major nature or not covered in a Paragraph 2 Sub Part M
particular Repair Manual, the Approved Organisation or
the appropriately licensed maintenance engineer
concerned, must be able to demonstrate all repairs are
appropriately approved.

All modifications/ changes, except those which are BCAR A/B2-5 Part 21
agreed by the CAA to be of such a nature that Paragraph 2.1.4 Sub Part D
airworthiness is not affected, shall be approved.

Aircraft with Permits to Fly

All of the above references apply to aircraft with Certificates of Airworthiness.
For aircraft holding Permits to Fly, the CAA needs to be satisfied that similar
standards have been achieved, including, as far as possible, reference to
original drawings and data. This should include compliance with the
Airworthiness Approval Note for the particular aircraft being restored (these
aircraft are not accepted by the CAA as series aircraft).

6 Procedures

6.1 In the case of a rebuilding or restoration project expected to exceed fifteen months
duration, the local CAA Regional Office (see CAAIP General Information, Contact
Details for UK Regional Office addresses) must be advised of the project at the

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CAP 562 Civil Aircraft Airworthiness Information and Procedures

earliest opportunity. This will allow for a preliminary assessment by a Regional Office
Surveyor of the extent of the restoration work required and initial acceptance of the
applicant's proposals regarding sourcing of parts and components to be used in the
restoration.
6.2 Normally, if the Regional Office Surveyor decides that the restoration or rebuilding
project is of such a magnitude that regular inspections will be necessary, a Special
Survey will be needed. Alternatively, it may be necessary, by virtue of the extent of
the rebuild or restoration required, that a major modification will be needed instead of
a Special Survey to record and approve the proposed repairs or replacements. If this
is the case the Regional Office Surveyor will advise the potential applicant
accordingly.
6.3 An application for a Special Survey should be made by the owner to Applications and
Approvals Department at Aviation House, Gatwick (see CAAIP General Information,
Contact Details).
6.4 Following acceptance by CAA of an application for a Special Survey it will not be
necessary to make an application for the subsequent issue of a Certificate of
Airworthiness or the renewal of the Permit to Fly, as the case may be, until the final
stages of completion unless a modification / change which has not previously been
approved is to be embodied on the aircraft. In some cases it may be that following a
Special Survey no recommendation can be made by the Regional Office Surveyor for
the renewal of the Certificate of Airworthiness or Permit to Fly. In these cases the
applicant will be advised of the reasons why the aircraft could not attain certification
and any Certificate of Airworthiness or Permit to Fly fee already paid will be refunded.
The cost of the Special Survey will, however, still have to be met by the applicant.

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CAP 562 Civil Aircraft Airworthiness Information and Procedures

Leaflet 11-46 Acceptance Standards for Imported Aircraft

for which a UK National Certificate of
Airworthiness is Sought

(Previously issued as AN 18)

1 Introduction

This Leaflet has been revised to advise of the implementation of changes that have
been made to the requirements for BCAR A8-8, Group E3 Approvals.

2 Requirements

2.1 BCAR Sections A and B, Sub-sections A3-2 and B3-2, specify the requirements for the
issue of Certificates of Airworthiness. These sub-sections have been revised for
aircraft with a maximum take off weight above 15 000 kg to require a report to be
submitted by an appropriate design organisation, certifying that the airworthiness
standard of the aircraft conforms to, or differs in a defined manner from, a standard
approved by the CAA for the issue of a Certificate of Airworthiness for that type. For
the purposes of this Leaflet, an appropriate design organisation is an organisation
approved in accordance with BCAR A8-8 Group E3 or it may be the Type Certificate
holder if considered acceptable.
NOTE: In the case where the issue of a Certificate of Airworthiness is to be completed
outside the United Kingdom at a place where an Organisation is not specifically
approved to provide reports for the purpose, the overseas Organisation shall be one
that is acceptable to the CAA.
2.2 For other aircraft with a maximum take off weight below 15 000 kg, a suitably
approved maintenance organisation, or, subject to CAA agreement, appropriately
licensed aircraft maintenance engineers for aircraft types not listed in paragraph 17 of
CAP 562 Leaflet 15-3 may be used. However, the use of the services of an E3
approved organisation is recommended, particularly where the work to establish
compliance is significant.
2.3 BCAR Section A, Sub-section A8 details the various organisation approvals. The
requirements for design organisation approvals under Sub-section A8-8 have been
amended to enable an E3 Design Organisation to provide reports and to certify that a
particular aircraft conforms to, or differs in a defined manner from, a standard
approved by the CAA for the issue of a Certificate of Airworthiness for that aircraft
type. Previously the E3 approval was limited to the provision of reports and
certification of compliance with design standards only. The amendment addresses all
of the airworthiness standards associated with issue of a Certificate of Airworthiness
and applicable operational requirements. Consequently an E3 Design Organisation
will now be required to have suitable procedures and arrangements for the inspection
of aircraft to establish compliance with the documented airworthiness standard.
2.4 The BCAR Chapter A8-8 requirement contains an appendix that gives guidance on the
format and content of the report to be provided by the E3 Design Organisation.
NOTE: Organisations should note that for EASA Aircraft Types, the introduction of the non-
expiring C of A in accordance with Part 21 Sub-part H and Part M Sub-part I was
introduced on 28 September 2007. Following this date, the requirement for an E-3

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CAP 562 Civil Aircraft Airworthiness Information and Procedures

approval and associated report ceased for EASA aircraft. Following 28 September
2007, organisations bringing EASA aircraft onto the register of an EASA member
state, including the UK, are required to provide an Airworthiness Review in
accordance with Part M, M.A.710. This review may in reality be presented in a
similar format to an existing E-3 Report, but it must comply with the categories and
requirements laid down under M.A.710.

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CAP 562 Civil Aircraft Airworthiness Information and Procedures

Leaflet 11-47 Overhauls, Modifications, Repairs and

Replacements to Aircraft not Exceeding
2730 kg with a National Certificate of
Airworthiness in the Special Category

(Previously issued as AN 32)

1 There have been a number of accidents to aircraft in the above Category on which it
was subsequently established that work had been done which was such that, under
Article 10 of the Air Navigation Order 2005 (as amended), the Certificate of
Airworthiness may have ceased to be in force.
2 Article 10 (a) of the Air Navigation Order 2005 (as amended), provides that a Certificate
of Airworthiness issued in respect of an aircraft shall cease to be in force if the aircraft,
or such of its equipment as is necessary for the airworthiness of the aircraft, is
overhauled, repaired or modified, or if any part of the aircraft or of such equipment is
removed or is replaced, otherwise than in a manner and with material of a type
approved by the Authority either generally or in relation to a class of aircraft or to the
particular aircraft.
3 Although Articles 16(5) and 16(6) of the Order specifically excludes certain Special
Category aircraft from the requirements for the issue of Certificates of Release to
Service, the provisions of Article 10 apply to all aircraft without exception. Any person,
therefore, who intends to undertake work on an aircraft covered by this Leaflet should
only do so when he is in possession of adequate knowledge of the tasks involved, has
access to the necessary facilities and the relevant maintenance, overhaul or repair
manuals, and uses parts or materials which are known to satisfy CAA requirements.
If any doubt exists as to whether these conditions are met, the person concerned
should seek advice from a CAA approved organisation or a licensed aircraft
maintenance engineer.
It is emphasised that a person who flies an aircraft when the Certificate of
Airworthiness has ceased to be in force by virtue of Article 10 of the Air Navigation
Order 2005 (as amended), may render himself liable to prosecution for contravention
of Article 8 of the Order and there may be other serious consequences.

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CAP 562 Civil Aircraft Airworthiness Information and Procedures

Leaflet 11-48 The Process for Acceptance of Used Engines,

Engine Modules, Auxiliary Power Units (APUs)
and Propellers for Use on NON-EASA Aircraft
Requiring a UK Certificate of Airworthiness

(Previously issued as AN 16)

1 Introduction

1.1 For the purposes of this Leaflet, engines, engine modules, APUs, and propellers are
hereafter referred to as Powerplants.
1.2 Article 10 of the Air Navigation Order 2005 states that a Certificate of Airworthiness
shall cease to be in force if the aircraft is overhauled, repaired or modified otherwise
than in a manner and with material of a type approved by the CAA.
1.3 Similarly, for non Commercial Air Transport, Article 16(10) (a) requires that a
Certificate of Release to Service (CRS) be issued when an aircraft has been
overhauled, repaired, modified or maintained in a manner and with material of a type
approved by the CAA.
1.4 For aircraft which are subject to regulation by EASA under Regulation (EC) 216/2008,
Part M Subpart E, M.A.501 and associated AMC/GM material detail how
components, including Powerplants, from non-EASA approved sources are to be
assessed. Those requirements must be followed for acceptance of such Powerplants
for these aircraft and this Leaflet is not applicable.
1.5 For Powerplants to be used on aircraft that are not subject to regulation by EASA and
are obtained from sources not under the direct airworthiness control of the CAA, this
Leaflet defines a procedure which owners/operators must follow in order to meet the
requirements of Article 10 or Article 16(10) of the Air Navigation Order 2005 (as
amended). The procedure described below is only applicable to Powerplants for “non-
EASA” aircraft as defined in CAP 747 Mandatory Requirements for Airworthiness.
1.6 Instructions are also included regarding both pool and lease/loan/power-by-the-hour
arrangements and the alignment of maintenance programmes to be used on “non-
EASA” aircraft.

2 General Requirements

It must be established by the owner’s/operator’s approved maintenance organisation

or an appropriately type rated Licensed Aircraft Engineer, as appropriate, that:
a) the Powerplant is of a type approved by the CAA;
b) civil identification plates are fitted;
c) log books or their equivalent, as appropriate, are issued;
d) original or certified true copies of any relevant documents (e.g. confirming
modification standard, test results, etc.) arising from construction or previous Hot
Section Inspection (H.S.I.)/Refurbishment/Overhaul/Performance Restoration are
provided with the CRS;
e) the Powerplant is in compliance with all applicable Airworthiness Directives of the
State of Design and the CAA;

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CAP 562 Civil Aircraft Airworthiness Information and Procedures

NOTE: In the case of a Pool Powerplant only the Airworthiness Directives of the State of
Design are required as a minimum (see paragraph 8).
f) any period of storage has been in accordance with the manufacturer’s
recommendations and that the Powerplant has not become unserviceable due to
operational abuse, damage or the removal of components;
g) the hours and cycles accrued of any life limited parts are clearly defined;
h) all modifications and repairs embodied in the Powerplant have been approved by
the Type Certificating Authority of the Powerplant or the CAA.

3 Alignment of Maintenance Programmes

Powerplant types which in the UK operator’s maintenance programme are subject to

fixed H.S.I/Refurbishment/Overhaul/Performance Restoration intervals must have
the time remaining to these intervals agreed by the CAA when the previous
operator’s maintenance programme does not specify the same shop visit
requirements or intervals.

4 Powerplants with an EASA, JAA, FAA or Transport Canada Authorised

Release Document

4.1 Powerplants which meet the requirements of Paragraph 2 of this Leaflet and have not
been operated since the last H.S.I/Refurbishment/Overhaul/Performance Restoration
are acceptable for use if received with an Authorised Release Document as defined
in a), b), c) or d):
a) an EASA form 1;
b) a JAA Form 1 issued by a JAR-145 Maintenance Organisation listed in the JAA
publication 'JAR-145 Listed Organisations';
c) an FAA Form 8130-3 from an EASA aproved FAR-145 Repair Station listed in EASA
Foreign Part-145 organisations located in the United States;
d) a Transport Canada Form 24-0078 from an EASA approved Transport Canada
Approved AM573 Maintenance Organisation listed in EASA Foreign Part-145
organisations located in Canada.
4.2 If the Powerplant satisfies all of the requirements of paragraphs 2 and 4.1 of this
Leaflet, then the following statement, signed by the person issuing the CRS, must be
entered into the appropriate log book:
‘Part........... S/N............ has been accepted under procedures complying with
CAAIP Leaflet 11-48, paragraphs 2 and 4.’

5 Powerplants Operated Under the Airworthiness Control of the EASA,

JAA, FAA or Transport Canada since Last H.S.I./Refurbishment/
Overhaul/Performance Restoration

5.1 Powerplants which meet the requirements of paragraph 2 and the Authorised
Release Document requirements of paragraph 4 of this Leaflet, but which have been
operated since last H.S.I./Refurbishment/Overhaul/Performance Restoration, will be
acceptable for use provided that:

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CAP 562 Civil Aircraft Airworthiness Information and Procedures

a) a serviceability statement is obtained from the previous operator declaring any

restrictions in hours or cycles relating to inspection, lubrication, replacement or
overhaul as necessary to maintain the airworthiness of the Powerplant;
b) all defects have been rectified, or recorded;
c) the Powerplant has been maintained to an EASA, JAA, FAA or Transport Canada
approved maintenance programme.
5.2 If the Powerplant satisfies all of the requirements in paragraphs 2 and 5.1 of this
Leaflet, then the following statement, signed by the person issuing the CRS, must be
entered into the appropriate log book:
‘Part.............. S/N............... has been accepted under procedures complying
with CAAIP Leaflet 11-48, paragraphs 2 and 5.’

6 Powerplants from Other Sources or those Requiring Further

Substantiation

6.1 This paragraph applies when any of the following circumstances exist:
a) it is not possible to satisfactorily confirm the origin, traceability or serviceability of
the Powerplant;
b) the Powerplant is obtained without an EASA, JAA, FAA or Transport Canada
Authorised Release Document (as described in paragraph 4 of this Leaflet);
c) the Powerplant has not been under the airworthiness control of EASA, JAA, FAA
or Transport Canada operator since the last H.S.I./Refurbishment/Overhaul/
Performance Restoration;
d) the Powerplant does not meet all of the requirements of Section 2.
NOTE: Owners and operators are advised to review the requirements of paragraphs 6.2 and
6.4 of this Leaflet prior to entering into a commercial agreement to purchase a
Powerplant.
6.2 The owner’s or operator’s maintenance organisation or an appropriately type rated
maintenance Licensed Aircraft Engineer, as appropriate, must demonstrate to the
satisfaction of the CAA the Powerplant’s acceptability, taking into account the
following:
a) the details of any unapproved modifications and repairs which have been
embodied in the Powerplant;
b) confirmation that military Powerplants which are similar to a civil equivalent have
been modified to comply with civil requirements in conjunction with the
manufacturer in each particular case, unless agreed otherwise with the CAA;
c) confirmation that the last H.S.I./Refurbishment/Overhaul/Performance Restoration
was undertaken to a specification, and by an organisation or person, acceptable to
the CAA;
d) a statement certifying serviceability (i.e. an Authorised Release Document or
equivalent), issued by either the last H.S.I./Refurbishment/Overhaul/Performance
Restoration organisation or the previous operator’s maintenance organisation, as
appropriate. This organisation must be appropriately authorised by its national
airworthiness authority to make such a statement. Alternatively, a statement
certifying serviceability issued by the appropriate national airworthiness authority
may be acceptable.

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CAP 562 Civil Aircraft Airworthiness Information and Procedures

6.3 If the CAA accepts the Powerplant, the following statement, signed by a CAA
Surveyor, must be entered into the appropriate log book:
‘Part........... S/N............... has been accepted by the CAA in accordance with
CAAIP Leaflet 11-48, paragraphs 2 and 6.2.’
6.4 If the serviceability cannot be adequately established then the Powerplant must be
dismantled and inspected.
A suitably approved maintenance organisation or an appropriately type rated Licensed
Aircraft Maintenance Engineer must dismantle and inspect the Powerplant. The
manufacturer’s recommendations must be used as the basis of the workscope for
this activity, which must be sufficient to determine if either of the declarations below
can be made. Rectification action must be taken where necessary.
If it cannot be established that the records are accurate and complete, all life limited
parts must be scrapped. In addition, the applicant must make reference to the CAA
for a decision on whether any other parts should be scrapped in the absence of
satisfactory records.
6.5 If serviceability is established one of the following statements, signed by the
maintenance organisation or the appropriately type rated Licensed Aircraft
Maintenance Engineer, as applicable, must be entered into the appropriate log book,
either:
‘Part.......... S/N........... has been examined in accordance with CAAIP Leaflet
11-48, paragraph 6.4, and no evidence of operational abuse, inadequate
maintenance or unsuitable storage has been revealed.’
or
‘Part....... S/N......... has been examined in accordance with CAAIP Leaflet 11-48,
paragraph 6.4, and appropriate action has been taken to restore serviceability.’

7 Lease/Loan/Power-by-the-Hour Powerplants

7.1 When a Powerplant is obtained on a long-term lease, loan or power-by-the-hour

arrangement from a supplier who is either (a) the original manufacturer, or (b) an
EASA, JAA, FAA or Transport Canada approved maintenance organisation or repair
station defined in paragraph 4 of this Leaflet, then the operator must confirm that:
a) the Powerplant complies with the requirements of paragraph 2;
b) the supplier has issued a serviceability statement declaring any restrictions in
hours or cycles relating to inspection, lubrication, replacement or overhaul as
necessary to maintain the airworthiness of the Powerplant;
c) the Powerplant has been maintained to either the manufacturer’s maintenance
programme, or an EASA, JAA, FAA or Transport Canada approved maintenance
programme;
d) all defects have been rectified or recorded.
7.2 The following statement, signed by the person issuing the CRS for the Powerplant,
must be entered into the appropriate log book:
‘Part.......... S/N............ has been accepted under procedures complying with
CAAIP Leaflet 11-48, paragraph 7.’

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CAP 562 Civil Aircraft Airworthiness Information and Procedures

8 Pool Powerplant

8.1 A ‘Pool’ Powerplant, interchanged between certain operators on a temporary basis

(limited to a maximum of 200 hours), is permitted provided:
a) the conditions relating to airworthiness which apply to the pooling agreement are
laid down in advance by the operator, agreed by CAA and lodged permanently in
the operator’s Maintenance Management Exposition. These conditions require
consideration of not only the history of the Powerplant but also the acceptability of
the source of the H.S.I./Refurbishment/Repair/Overhaul/Performance Restoration
where this is other than by the pool partner.
b) the Powerplant is in compliance with all applicable Airworthiness Directives of the
State of Design.
c) the UK operator obtains from the previous operator a signed statement certifying
the Powerplant is airworthy when released on loan, declaring any restrictions in
cycles or hours, etc., relating to inspection, lubrication, replacement, or overhaul
as necessary to maintain the airworthiness of the Powerplant during the period of
loan.
8.2 The following statement, signed by the person issuing the CRS for the Powerplant,
must be entered into the appropriate log book:
‘Part......... S/N............ has been accepted under procedures complying with
CAAIP Leaflet 11-48, paragraph 8.’

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CAP 562 Civil Aircraft Airworthiness Information and Procedures

Leaflet 11-49 Changes Affecting Design and Production

Organisations

(Previously issued as AN 21)

1 Purpose

1.1 To provide information to Design and Production Organisations regarding changes

caused by the European Regulations that came into force on 28 September 2003,
particularly:
• requirements for organisation approvals for design and production activities not
subject to European Regulation (EC) No. 216/2008; and
• flight-testing required by Part-21.

2 Applicability

2.1 Design and Production Organisations.

2.2 Organisations required to conduct flight tests required by Part-21.

3 Introduction

3.1 The European Aviation Safety Agency (EASA) as established in European Regulation
(EC) No. 216/2008 commenced operation on 28 September 2003 and at the same
time European Commission Regulation (EC) No. 1702/2003, laying down
implementing rules for the airworthiness and certification of aircraft, entered into
force. These regulations and implementing rules have affected the organisation
approval requirements for design and production organisations currently approved to
BCAR Sub-Section A8.
NOTES: 1) For the purposes of this Leaflet, aircraft that are required to comply with
Regulation (EC) No. 216/2008 are specified as “EASA Aircraft”.
2) For the purposes of this Leaflet, aircraft that are not required to comply with
Regulation (EC) No. 216/2008 are specified as “Non-EASA Aircraft”.
3) Lists of EASA and Non-EASA aircraft can be found in CAP 747.

4 Effectivity

This Leaflet is effective from 28 September 2004.

5 Requirements

5.1 Design – EASA aircraft

All design changes, repair design and initial design associated with EASA aircraft must
be in accordance with Part-21 and approved either by EASA or by an appropriately
approved Part-21 Subpart J design organisation.
NOTE: Even if an aircraft is being used as a 'state aircraft' and is therefore not the
responsibility of EASA, a design change to that aircraft could still be approved
through the EASA system. If the design change is a series modification and
applicable to aircraft covered by the TC it is not state specific and could be accepted
as an EASA design change. Alternatively, the design change could be defined as
aircraft specific which would make it applicable to the 'state aircraft' only and would
allow it to be approved under the national system as below.

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CAP 562 Civil Aircraft Airworthiness Information and Procedures

5.2 Design – Non-EASA aircraft

Design changes, repair design and initial design not eligible for approval under Part-21
are a national responsibility and are approved by the CAA, an appropriately approved
BCAR design organisation or a Part-21 approved design organisation with an
appropriate supplement to their EASA approval issued by the CAA. A Part-21 DOA
requiring the ability to perform design activity in accordance with the national system,
rather than to Part-21, can apply to the CAA for this supplement.
Examples of design not eligible for approval under Part-21 are:
a) Annex II aircraft design changes or repair design; and
b) Modification of an aircraft with an EASA TC but used for state purposes (e.g.
police) where the design change is not certifiable as an EASA design change. If a
design change to a state aircraft can be approved through Part-21, as described
above, it is advisable to do this as any design change or repair not approved under
Part-21 precludes the issuance of an EASA Certificate of Airworthiness for the
affected aircraft. If at a later date the aircraft is not used for state purposes all non-
EASA design changes will need removal or approving under the EASA system
before the EASA Certificate of Airworthiness could be granted.
5.3 Production – EASA aircraft
Production against EASA approved design data needs to be in accordance with
Part-21 and may be released on an EASA Form 1 by a Subpart G approved production
organisation (POA) or an organisation working in accordance with Subpart F. Release
on a JAA Form One has not been appropriate in the UK since 28 September 2005.
5.4 Production – Non-EASA aircraft
If the design data has been approved under the CAA national system and not under
the EASA system then release on an EASA Form 1 is not appropriate. An organisation
with an appropriate BCAR approval or a Part-21 POA with an appropriate CAA
supplement can release on a CAA Approved Certificate as described in Appendix 1 to
this Leaflet. Release on a JAA Form One has not been appropriate in the UK since
28 September 2005.
5.5 Information on the future requirements for organisation approvals for design
and production activities on Non-EASA aircraft
Organisations whose activity is only related to Non-EASA aircraft may continue to use
their BCAR Section A8 approvals. The CAA has replaced these national requirements
with a set of common requirements based upon Part-21. These requirements are
published as BCAR Chapter A8-21 and have been developed with industry support.
5.6 Flight testing required by Part-21
NOTES: 1) For EASA aircraft the CAA were responsible for making the findings associated
with the issue of a Permit to Fly until 28 March 2007 in accordance with
Regulation (EC) No. 1702/2003 Article 2, paragraph 11.
EU regulation 375/2007 was published on the 4 April 2007 and introduced EASA
requirements for flight testing into Part-21. CAP 562 Leaflet 1-15 provides
guidance on the new rules and the associated processes for application, approval
and issue of EASA Permits to Fly.
2) For Non-EASA aircraft the requirements of BCAR Chapter A3-8 (A Conditions)
and Chapter A3-9 (B Conditions) are still applicable and an organisation approval
in accordance with BCAR Chapter A8-9 is required as necessary.

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CAP 562 Civil Aircraft Airworthiness Information and Procedures

Appendix 1

(Previously issued as AN 21 Appendix 1)

1United Kingdom
Civil Aviation Authority
UK CAA 3 Form Tracking Number

APPROVED CERTIFICATE

4 Approved Organisation Name and Address 5 Work Order / Contract /

Invoice

6 Item 7 Description 8 Part No. 9 Eligibility* 10 Qty 11 Serial No 12 Status/Work

/ Batch No

13 Remarks

This certificate has been issued under national rule provisions

14 19
Certifies that, unless otherwise specified in block Certifies that unless otherwise specified in block 13
13, the items identified above were manufactured the work identified in block 12 and described in
in conformity to: block 13 was accomplished in accordance with the
… approved design data and are in a condition for airworthiness requirements of the UK and in
safe operation respect to that work the items are considered ready
for release to service
… non-approved design data specified in block 13
15 Authorised Signature 16 Approval No. 20 Authorised Signature 21 Approval No.

17 Name 18 Date (dd/mmm/yyyy) 22 Name 23 Date (dd/mmm/yyyy)

* Installer must cross-check eligibility with applicable technical data

USER/INSTALLER RESPONSIBILITIES

NOTES: 1. It is important to understand that the existence of the document alone does not automatically constitute authority to
install the part/component/assembly.

2. Where the user/installer works in accordance with the national regulations of another airworthiness authority it is
essential that the user/installer ensure that his/her airworthiness authority accepts parts/components/assemblies from
the UK CAA.

3. Statement 14 and 19 do not constitute installation certification. In all cases the aircraft maintenance record shall contain
an installation certification issued in accordance with the national regulations by the user/installer before the aircraft may
be flown.

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CAP 562 Civil Aircraft Airworthiness Information and Procedures

APPROVED CERTIFICATE
COMPLETION INSTRUCTIONS
These instructions relate only to the use of the UK CAA Approved Certificate for manufacturing
purposes.

1 Purpose and Scope

The primary purpose of the certificate is to release products, parts and appliances
(hereafter referred to as 'item(s)') as identified in Blocks 7 through 11 as applicable
after manufacture, or to release maintenance work carried out on items under the
approval of the CAA.
The Certificate serves as an official certificate for the delivery of items from the
manufacturer to users. The Certificate is not, however, a delivery or shipping note.
It may only be issued by organisations certificated by the CAA, within the scope of
such an approval. Aircraft are not to be released using the Certificate. Products, Parts
or Appliances for aircraft that are the responsibility of the European Aviation Safety
Agency (EASA) are NOT to be released using the Certificate.
A mixture of 'New' and 'Used' items is not permitted on the same Certificate.
A mixture of items certified in conformity with 'approved data' and to 'non-approved
data' is not permitted on the same Certificate, and consequently only one box in Block
14 can be ticked.

2 General

The Certificate must comply with the format attached including block numbers and
the location of each Block. The size of each Block may however be varied to suit the
individual application, but not to the extent that would make the Certificate
unrecognisable. The overall size of the Certificate may be significantly increased or
decreased so long as the Certificate remains recognisable and legible. The Certificate
must be in 'Portrait' rather than 'Landscape' to help differentiate it from the EASA
Form 1. If in doubt consult the CAA.
Please note that the user responsibility statements can be placed on either the
reverse or front of this Certificate.
All printing must be clear and legible to permit easy reading and be in English.
The Certificate may either be pre-printed or computer generated but in either case the
printing of lines and characters must be clear and legible. Pre-printed wording is
permitted in accordance with the attached model but no other certification
statements are permitted.
The details entered onto the Certificate must be in English and permit easy reading,
and may be entered by hand, using block letters, or by a machine or computer.
Abbreviations must be restricted to a minimum.
The space remaining on the reverse side of the Certificate may be used by the
originator for any additional information but must not include any certification
statement.
The original Certificate must accompany the items and correlation must be
established between the Certificate and the item(s). A copy of the Certificate must be
retained by the organisation that manufactured the item. Where the Certificate format
and the data is entirely computer generated, subject to acceptance by the CAA, it is
permissible to retain the Certificate format and data on a secure database.

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CAP 562 Civil Aircraft Airworthiness Information and Procedures

There is no restriction in the number of copies of the Certificate sent to the customer
or retained by the originator.
The Certificate that accompanies the item may be attached to the item by being
placed in an envelope for durability.

3 Completion of the Approved Certificate by the Originator

Except as otherwise stated, there must be an entry in all Blocks to make the
document a valid certificate.

Block 1 Pre-printed 'United Kingdom Civil Aviation Authority'.

Block 2 Pre-printed 'UK CAA Approved Certificate'.

Block 3 A unique number must be pre-printed in this Block for Certificate control and
traceability purposes except that in the case of a computer generated
document, the unique number need not be pre-printed where the computer
is programmed to produce the number.

Block 4 The information in this Block needs to satisfy two objectives:

1 to relate the Certificate to an organisation approval, for the purposes of

verifying authenticity and authority of the Certificate;

2 to provide a ready means of rapidly identifying the place of manufacture

and release, to facilitate traceability and communication in the event of
problems or queries.

Therefore, the name entered in the box is that of the organisation approval
holder who is responsible for making the final determination of conformity
or airworthiness, and whose Approval Reference Number is quoted in Block
16. The name must be entered in exactly the same form as appears in the
Approval Certificate held by the organisation.

The address(es) entered in Block 4 will assist in the identification of the

approval holder and in identifying the place of release.

If the place of manufacture and release is one of the organisation addresses

listed on the Approval Certificate, then that is the only address needed in
this Block.

If the place of manufacture and release is a location which is NOT listed in

the Approval Certificate then two addresses are required. The first address
will be the address of the approval holder (as listed in the Approval
Certificate) and a second address entered to identify the place of
manufacture and release.

This Block may be pre-printed. Logo of the production approval holder, etc.,
is permitted if it can be contained within the Block.

Block 5 The purpose is to reference work order/contract/invoice or any other internal

organisational process such that a fast traceability system can be
established. The use of the Block for such traceability is mandatory in the
absence of item Serial Numbers or batch numbers in Block 11. When not
used, state N/A.

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CAP 562 Civil Aircraft Airworthiness Information and Procedures

Block 6 The Block is provided for the convenience of the organisation issuing the
Certificate to permit easy cross-reference to the 'Remarks' Block 13 by the
use of line item numbers. Block 6 must be completed where there is more
than one line item.

Where a number of items are to be released on the Certificate, it is

permissible to use a separate listing cross-referring Certificate and list to
each other.

Block 7 The name or description of the item must be given. Preference must be
given to use of the Illustrated Parts Catalogue (IPC) designation.

Block 8 State the Part Number. Preference must be given to use of the IPC number
designation.

Block 9 Used to indicate the type-approved applications for which the released items
are eligible for installation, based on information provided by the design
approval holder. The following entries are permitted:

a) At least one specific or series aircraft, propeller, or engine model as

identified by the design approval holder. In case of engine or propeller
release, state the aircraft approved applications, or, if application is not
specific, state 'type-certificated engine/propeller'.
b) 'None', to be used only when it is known that the items do not yet have a
type-approved application, for example: pending type-certificate, for test
only, pending approved data. If this category is used, then appropriate
explanatory information must be provided in Block 13 and new items may
only be released for Conformity purposes.
c) 'Various' if known to be eligible for installation on multiple products,
according to a procedure approved by the CAA.

In the case of multiple applications it is acceptable for this Block to contain

cross reference to an attached document which lists such applications.

Any information in Block 9 does not constitute authority to fit the item to a
particular aircraft, engine or propeller. The User/Installer must confirm via
documents such as the Parts Catalogue, Service Bulletins, etc., that the
item is eligible for the particular installation.

Any information in Block 9 does not necessarily mean that the product, parts
or appliances are only eligible for installation on the listed model(s). Nor does
it guarantee that the product, parts or appliances are eligible for installation
on all entries in Block 9. Eligibility may be affected by modification or
configuration changes.

Where a part is identified by the design holder in accordance with officially

recognised Standards, then the part is considered a Standard Part and
release with an Approved Certificate is not necessary. However where a
production approval holder releases a standard part with an Approved
Certificate then it must be able to demonstrate that it is in control of the
manufacture of that part.

Block 10 State the quantity of items being released.

Block 11 State the Serial Number (or Batch Number) of the item if applicable. If not
applicable, state 'N/A'.

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CAP 562 Civil Aircraft Airworthiness Information and Procedures

Block 12 Enter one or a combination of appropriate standard words from the following
table. The table lists, in quotes, the standard words permitted for use when
releasing new items prior to entry into service, i.e. the items have not been
previously used in operational service. It also details the circumstances and
conditions under which they may be used. In all cases the certification rules
relating to Block 14 apply, the appropriate box is to be marked, and Block 15
is to be signed.

TABLE OF STANDARD WORDS FOR NEW PARTS

1 'MANUFACTURED'

a) The production of a new item in conformity with the applicable design

data, or

b) re-certification by the original manufacturer after rectification work on an

item, previously released under paragraph 1(a), which has been found to
be unserviceable prior to entry into service, e.g., defective, in need of
inspection or test, or shelf life expired. Details of the original release and
the rectification work are to be entered in Block 13, or re-certification of
new items from conformity purpose to airworthiness purpose at the time
of approval of the applicable design data, provided that the items
conform to the approved design data. An explanation of the basis of
release and details of the original release are to be entered in Block 13.

2 'INSPECTED'/'TESTED'

The examination of a previously released new item:

a) to establish conformity with the applicable design data, or

b) in accordance with a customer-specified standard or specification, details

of which are to be entered in Block 13, or

c) to establish serviceability and condition for safe operation prior to re-

release as a spare, where the item has been obtained with an EASA
Form 1 or Approved Certificate. An explanation of the basis of release
and details of the original release are to be entered in Block 13.

3 'MODIFIED'

The alteration, by the original manufacturer, of a previously released item

prior to entry into service. Details of the alteration and the original release
are to be entered in Block 13.

The above statements must be supported by reference to the approved

data/manual/specification. Such information shall be identified in either Block
12 or 13.

Block 13 It is necessary to state any information in this Block, either directly or by

reference to supporting documentation, that identifies particular data or
limitations relating to the item being released that are necessary for the
User/Installer to make the final airworthiness determination of the item. The
information must be clear, complete, and provided in a form and manner
which is adequate for the purpose of making such a determination.

Each statement must be clearly identified as to which item it relates.

If there is no statement, state 'None'.

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CAP 562 Civil Aircraft Airworthiness Information and Procedures

Block 13 Examples of conditions which would necessitate statements in Block 13 are:

(cont) • when the certificate is used for conformity purposes the following
statement must be entered at the beginning of Block 13:
'ONLY FOR CONFORMITY, NOT ELIGIBLE FOR INSTALLATION ON IN-
SERVICE TYPE-CERTIFICATED AIRCRAFT / ENGINE / PROPELLER';
• when the design data is not approved by the CAA, then the competent
authority of the third country responsible for the approval of the design
data must be identified and the following statement must be entered
together with a reference identifying the approval:
'DESIGN DATA APPROVED BY <identify the responsible competent
authority of a third country and the approval reference>';
• re-certification of new items from conformity purpose to airworthiness
purpose at the time of approval of the applicable design data, provided
that the items conform to the approved design data.

Provided that no change in design has occurred during the design data
approval process, the manufacturer may state that the design data has been
approved and that provided the specific component is still in the condition it
was when it was shipped to the user/installer, the component is now eligible
to be installed. The manufacturer must make this statement on a second
Approved Certificate where in addition to any other necessary remarks,
appropriate explanatory information must be provided. The following
wording must be used: 'RE-CERTIFICATION OF NEW PARTS FROM
CONFORMITY TO AIRWORTHINESS: THIS DOCUMENT ONLY CERTIFIES
THE APPROVAL OF THE DESIGN DATA TO WHICH THIS ITEM WAS
(THESE ITEMS WERE) MANUFACTURED, BUT DOES NOT COVER
CONFORMITY/CONDITION AFTER RELEASE OF THE INITIAL APPROVED
CERTIFICATE REF……..'
Approved Certificate (both for 'Conformity purposes' and for 'Airworthiness
purposes') must be generated by the same organisation, i.e. the original
manufacturer or prime manufacturer, whichever raised the original Approved
Certificate for Conformity purposes.

• For complete engines and propellers the applicable type-certificate, or

equivalent, must be referenced.
• For complete engines, a statement of compliance with the applicable
emissions requirements current at the date of manufacture of the engine.
• Usage restriction for repaired items.
• Modification standard.
• Alternative approved items supplied.
• Concessions applicable.
• Non-compliance with certification specifications.
• Details of repair work carried out or reference to a document where this
is stated.
• Compliance with, or non-compliance with Airworthiness Directives or
Service Bulletins.
• Information on life limited items.
• Condition of items or reference to a document detailing this information.
• Manufacturing date or cure date.
• Shelf life data.
• Shortages
• Time Since New (TSN), Time Since Overhaul (TSO), etc.
• Re-certification of previously released ‘new’ items.

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CAP 562 Civil Aircraft Airworthiness Information and Procedures

Block 14 This Block may only be used to indicate the status of new items.
The main purpose of the Certificate is to release items for airworthiness
purposes, which means conformity with approved design data and in
condition for safe operation.

This airworthiness certification is valid in the UK.

The certificate may also be used as a Conformity Certificate when items

conform to applicable design data which are not approved for a reason which
is stated in Block 13 (e.g., pending type-certificate, for test only, pending
approved data).

In this case the following additional statement must be entered at the

beginning of Block 13 itself and not in a separate document: 'ONLY FOR
CONFORMITY, NOT ELIGIBLE FOR INSTALLATION ON IN-SERVICE TYPE-
CERTIFICATED AIRCRAFT/ENGINE/PROPELLER'.

Mixtures of items released for Airworthiness and for Conformity purposes

are not permitted in the same certificate. Also refer to the notes for
completion of Block 9.

Block 15 The hand-written normal signature of a person who has written authority
from an approved production organisation to make Certifications in respect
of new items. Use of a stamp instead of a signature is not permitted, but the
authorised person may add a stamp impression to his or her signature to aid
recognition. Subject to the agreement of the CAA in any particular case,
computer-generated signatures are permitted if it can be demonstrated that
an equivalent level of control, traceability and accountability exists.

Block 16 State the full authorisation reference given by the CAA to the organisation
releasing the new items.

Block 17 The name of the person signing Block 15, printed, typed, or written in a
legible form.

Block 18 The date on which Block 15 is signed, in the format day/month/year. The
month must be stated in letters (sufficient letters must be used so there can
be no ambiguity as to the month intended).

Block 19 Not used and strike out for release of new items.

Block 20 Not used and strike out for release of new items.

Block 21 Not used and strike out for release of new items.

Block 22 Not used and strike out for release of new items.

Block 23 Not used and strike out for release of new items.

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CAP 562 Civil Aircraft Airworthiness Information and Procedures

Leaflet 11-50 Maintenance Error Management Systems

(Previously issued as AN 71)

1 Introduction

1.1 In January 2003, JAR 145 amendment 5 (subsequently incorporated into EASA
Part-145) introduced paragraph 145.A.60 – Occurrence Reporting, to require
organisations to “establish an internal occurrence reporting system…to enable the
collection and evaluation of such reports, [which have resulted, or may result, in an
unsafe condition]. This procedure shall identify adverse trends, corrective actions
taken or to be taken by the organisation to address deficiencies and include evaluation
of all known relevant information relating to such occurrences and a method to
circulate the information as necessary." CAA seeks to provide an environment in
which such errors may be openly investigated in order that the contributing factors
and root causes of maintenance errors can be addressed using a system that would
complement, not supplant, the two current systems for reporting maintenance errors
(MORS and CHIRP).
NOTE: Square brackets [ ] denote CAA insertion.
1.2 Mandatory Occurrence Reporting (MOR) scheme exists in order that significant
safety issues are brought to the notice of the CAA. However, the MORs scheme is
not intended to collect and monitor the normal flow of day-to-day defects/incidents
etc. which, in remaining an industry responsibility (CAP 382 Mandatory Occurrence
Reporting System, paragraph 5.4.5), forms an important part of the overall operational
safety task. This Leaflet concerns, primarily, those events which fall below the MOR
criteria but which, nevertheless, are important for an organisation to understand and
control. However, the principles described in this Leaflet may also be applied by an
organisation to their own internal investigation of incidents meeting the MOR criteria
NOTE: Organisations will still be required to report MORs to the CAA.
1.3 The Confidential Human Factors Incident Reporting Programme (CHIRP) scheme
provides an alternate reporting mechanism for individuals who want to report safety
concerns and incidents confidentially. However CHIRP should not be considered as
an alternative to implementing a Maintenance Error Management System (MEMS)
scheme. MEMS and CHIRP perform different functions albeit acting towards the
same ultimate aim, i.e. improved flight safety.
1.4 Maintenance errors with serious consequences such as accidents or incidents are
routinely investigated by organisations, Air Accident Investigation Branch or CAA.
Other operationally significant events (e.g. technical delays, cancellations, etc.) may
not be legally required to be reported externally but are frequently investigated by
organisations albeit too often only to apportion responsibility for the event, rather than
to determine cause. Below these levels are events without operational significance
which may rarely be investigated (e.g. the omission of an oil filler cap which, by
chance, is noticed and corrected before flight). In order to gain a better understanding
of the problems and factors which contribute to errors it is necessary to investigate
these and operationally significant events before they possibly contribute to or cause
an incident or accident in the future.
1.5 It is important to examine not just what happened, but why it happened, in order to
determine the root causes and problems.

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CAP 562 Civil Aircraft Airworthiness Information and Procedures

2 Maintenance Error Management System

2.1 AN 71 Issue 1 (2000) set out CAA policy on MEMS and, prior to the requirements
introduced by JAR 145.60 and Part 145.A.60, encouraged maintenance organisations,
in particular those maintaining large commercial air transport aircraft, to adopt MEMS
concepts. Subsequently, the JAA Maintenance Human Factors Working Group
incorporated very similar guidance into their report published in May 2001
(reproduced in CAP 716 issue 2, 18/12/2003), with the key elements being
incorporated into EASA Part 145.A.60(b) and AMC 145.A.60(b). Both key, and more
detailed, elements are described below, in particular the importance of a 'just culture'
for the successful functioning of a MEMS.
2.2 Prevailing industry best practice has shown that a MEMS should contain the following
elements:
• Clearly identified aims and objectives
• Demonstrable corporate commitment with responsibilities for the MEMS clearly
defined
• Corporate encouragement of uninhibited reporting and participation by individuals
• Disciplinary policies and boundaries identified and published
• An event investigation process
• The events that will trigger error investigations identified and published
• Investigators selected and trained
• MEMS education for staff, and training where necessary
• Appropriate action based on investigation findings
• Feedback of results to workforce
• Analysis of the collective data showing contributing factor trends and frequencies.
2.3 The aim of the scheme is to identify the factors contributing to incidents, and to make
the system resistant to similar errors. Whilst not essential to the success of a MEMS,
it is recommended that for large organisations a computerised database be used for
storage and analysis of MEMS data. This would enable the full potential of such a
system to be utilised in managing errors.
2.4 For the purpose of this Leaflet a maintenance error is considered to have occurred
when the maintenance system, including the human element, fails to perform in the
manner expected in order to achieve its safety objectives. The human element
includes technicians, engineers, planners, managers, store-keepers – in fact any
person contributing to the maintenance process. The foregoing definition differs from
that of a human error as it demands consideration of the system failings (e.g.
inadequate staffing, organisational factors, tooling availability, ambiguous manuals
etc.) as well as the error committed by a person.

3 CAA Assurances

3.1 It is recognised that the success of a MEMS programme is dependent on full and free
investigation without fear of action by the CAA. Accordingly, the CAA gives the
following assurances:
3.1.1 The CAA will be checking, as part of its approval audit process, that the organisation’s
internal occurrence reporting and investigation process is functioning as described in
the procedures approved by the CAA and in line with the objectives of the programme

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CAP 562 Civil Aircraft Airworthiness Information and Procedures

as explained in CAP 716 Issue 2. The CAA audit may involve the review of
disidentified MEMS investigations such that the foregoing can be satisfied. However,
the CAA makes the following assurances that it will:
a) subject to b) not disclose the name of the person submitting the MEMS report, nor
of a person to whom it relates, nor pass on a MEMS report to a third party, unless
required to do so by law or unless the person(s) concerned authorises such
disclosure.
b) take all reasonable steps possible to avoid disclosing the identity of the reporter or
of those individuals involved in the occurrence, should any follow-up action arising
from a MEMS report be taken.
c) not, as its policy, institute criminal proceedings in respect of unpremeditated or
inadvertent breaches of the law or requirements which come to its attention only
because they have been reported under the MEMS scheme, except in cases
involving dereliction of duty amounting to gross negligence or recklessness. Such
an assurance is similar to that provided under the MOR scheme.
3.2 As examples of what the CAA might require, as evidence that an organisation has a
working MEMS programme in accordance with Part 145.A.60(b), a surveyor may ask
to see the following documents and evidence, and in order to satisfy himself, he may
wish to speak to individual members of staff at any level within the organisation:
a) A copy of the company’s safety and disciplinary policy and determine that staff are
aware of this policy, and believe that it will be, and has been, applied fairly.
b) The procedure describing the company's process for reporting and investigating
incidents and errors, and the types of occurrences that would normally be
investigated.
c) Evidence that occurrences meeting the criteria detailed above have been reported,
and to assure himself that occurrences are not frequently going unreported.
d) Evidence that occurrences meeting the criteria detailed above have been
investigated, and to assure himself that occurrences are being, and have been,
fairly investigated. It is hoped that an organisation would cooperate with a surveyor
in putting him in touch with individuals who have been party to investigations, but
only with the agreement of the individuals concerned.
e) Within a large company, evidence that MEMS investigators had received
appropriate training.
f) Evidence that the organisation had acted, or was acting, upon results of MEMS
investigations, based on risk assessment. This may mean that no action had been
taken if a risk assessment has deemed that the causes were unlikely, in isolation
or in combination, to result in a hazardous event in the future. A surveyor would
expect to see evidence of action(s) to prevent root causes, and/or to mitigate the
effects of error where appropriate.
g) Evidence of feedback to the workforce, on both occurrences and their
investigation, and remedial action taken, would also be expected.
3.3 For a small organisation, the surveyor would expect evidence as described above, but
on a less structured basis.
3.4 If an organisation has no evidence to offer in the form of reported and investigated
occurrences, the surveyor may wish to talk to staff to assure himself that there have
been no such occurrences, as opposed to occurrences going unreported and
uninvestigated. The surveyor would respect staff confidences in seeking such
evidence.

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CAP 562 Civil Aircraft Airworthiness Information and Procedures

4 MEMS Code of Practice

4.1 The CAA encourages organisations to adopt the following code of practice regarding
a MEMS:
4.1.1 Where an occurrence reported via MEMS indicates an unpremeditated or inadvertent
lapse by an employee, as described below, the CAA would expect the employer to
act reasonably, agreeing that free and full reporting is the primary aim in order to
establish why the event happened by studying the contributory factors that led to the
incident, and that every effort should be made to avoid action that may inhibit
reporting.
4.1.2 In the context of error management it is considered that an unpremeditated or
inadvertent lapse should not incur any punitive action, but a breach of professionalism
may do so. As a guideline, individuals should not attract punitive action unless:
a) the act was intended to cause deliberate harm or damage.
b) the person concerned does not have a constructive attitude towards complying
with safe operating procedures.
c) the person concerned knowingly violated procedures that were readily available,
workable, intelligible and correct.
d) the person concerned has been involved previously in similar lapses.
e) the person concerned has attempted to hide their lapse or part in a mishap.
f) the act was the result of a substantial disregard for safety.
“Substantial disregard”, for this purpose, means:
• In the case of a certification authorisation holder (e.g. licensed engineer or
Certifying Staff) the act or failure to act was a substantial deviation from the
degree of care, judgement and responsibility reasonably expected of such a
person.
• In the case of a person holding no maintenance certification responsibility, the
act or failure to act was a substantial deviation from the degree of care and
diligence expected of a reasonable person in those circumstances.
The degree of culpability would vary depending on any mitigating circumstances that
are identified as a result of the MEMS investigation. It follows that any action taken
by the organisation would also be on a sliding scale varying from corrective measures
such as retraining through to dismissal of the individual.
4.1.3 In the case of incidents investigated via a MEMS, irrespective of whether or not such
incidents were brought to the knowledge of the CAA, the CAA expects an
organisation to address the problems which contributed to these incidents. The
organisation should, where possible, implement appropriate measures to prevent the
problem from re-occurring, or alternatively monitor future occurrences, according to
the degree of risk and likelihood of re-occurrence. A supporting database is useful in
these circumstances in helping to assess the frequency of occurrence and any
associated trends.
4.1.4 The CAA would expect that identified safety issues would be acted upon. If the CAA
becomes aware, by whatever means, that a significant safety problem existed and
was not being addressed, it reserves the right to take appropriate action.
NOTE: The statement by an organisation that an incident is undergoing, or has undergone,
a MEMS investigation, without any additional information provided to explain why
the incident occurred, would not normally be an adequate basis for an MOR closure.

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CAP 562 Civil Aircraft Airworthiness Information and Procedures

4.1.5 Organisations are encouraged to share their MEMS results with the CAA and with
other maintenance organisations. It is hoped that by sharing such data the CAA and
industry can jointly develop a better understanding of maintenance error causation
and develop more focused human factors strategies. However, it is appreciated that
some information in a MEMS may be considered sensitive to the organisation
affected, and may need to be dis-identified before being shared with other
organisations.
4.1.6 To support the sharing of MEMS results between organisations, members of the
UKOTG (UK Operators Technical Group) and EIMG (European Independent
Maintenance Group) in conjunction with the CAA and CHIRP have established a
MEMS Review Board and a shared dis-identified database. The Board’s role is to
facilitate, develop and guide this process. The CAA encourages UK maintenance
organisations to participate in the programme and join the MEMS Group. Further
details about the MEMS Review Board and how to join the MEMS Group can be
found at the following website: http://www.chirp-mems.co.uk/MEMS/Index.htm

5 Further Information

5.1 More detailed guidance information, including where to obtain free MEMS software,
is included in CAP 716 Issue 2.
5.2 Maintenance Organisations requiring further information or advice on how to
establish a Maintenance Error Management System should contact their CAA Survey
Department local Regional Office;
or:
Survey Department,
Chief Surveyor’s Office,
CAA
Aviation House
Gatwick Airport South
West Sussex
RH6 0YR
Tel: 01293 573366
Fax: 01293 573984

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CAP 562 Civil Aircraft Airworthiness Information and Procedures

Leaflet 11-51 CAA Use of Confidential Information

(Previously issued as AN 65)

1 Introduction

1.1 The Air Navigation Order places a duty on the CAA to consider:
a) the design, construction, workmanship and materials of aircraft and their
associated equipment; and
b) the results of flying trials and such other tests as are necessary;
when it is satisfying itself that aircraft registered in the UK are fit to fly. In carrying out
this duty the CAA, as it is empowered to do, makes extensive use of reports
furnished to it by appropriately qualified persons.
1.2 Such reports may come in various forms and have a range of purposes. They may
provide a physical description of anything from a complete aeroplane to a small item
of equipment. They may specify performance or present test results. They may
demonstrate that certain design or manufacturing standards are met.

2 CAA’s Use of Such Information

2.1 However it is presented, the CAA’s interest in such information stems from its need
to be satisfied that a given aircraft or aircraft type is fit to fly. Once satisfied, if the CAA
is subsequently presented with another aircraft (or item of equipment or operating
proposal etc.) which it knows to be identical in nature it cannot and should not ignore
this state of knowledge and insist that the person seeking approval goes through the
whole process of satisfying the CAA again.
2.2 The CAA is aware that there may be commercial implications to the policy described
in paragraph 2.1, in that second or subsequent applications for a given approval may
derive substantial benefit from the evidence provided when the first application was
cleared. Technical data are frequently submitted with notes purporting to place
restrictions on their use and it is possible that undue significance may be attached to
such notes. One purpose of this Leaflet is, therefore, to make it clear that when an
aircraft or item of equipment has once been shown fit for a particular purpose, the
fact has been established: the CAA does not need to demand repetitive evidence
from a later applicant for an identical certification and will not ask for it. The onus is,
of course, upon such an applicant to demonstrate that the relevant circumstances are
identical.
2.3 If safety depends on the way in which an aircraft (or item of equipment etc.) is used,
the CAA may have considered and approved certain proposed operating limitations,
or it may have required evidence that established operating procedures are
acceptable; if so, it may require similar material to be provided by subsequent
operators seeking a similar clearance. This is, however, a separate matter.

3 Confidentiality of Proprietary Information

3.1 It is no contradiction of the principles in paragraph 2, to state that subject to the

specific provisions in the Civil Aviation Act, the CAA totally accepts prohibitions placed
by the owners of information on its disclosures to third parties. Thus, if an aircraft
requires modification in order to satisfy a design requirement, no details of a

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CAP 562 Civil Aircraft Airworthiness Information and Procedures

proprietary modification would be passed on by the CAA to a third party without the
express permission of its owners. Nor, if an operation depended upon certain
proprietary Flight Manual limitations or data, would such information be passed on.
3.2 Having stated this, if the CAA were presented with details of a modification (or Flight
Manual amendment etc.) which was identified as being identical to one which from
prior experience it knew would satisfy an airworthiness requirement, such a
modification would have to be considered acceptable. Where this involves a light
aircraft type of which there exist or are likely to be numerous operators, the CAA may,
for efficiency, issue a CAA Supplement to the Flight Manual or Pilot’s Operating
Handbook, based on data or information supplied by a manufacturer or an Applicant.
As with the situation described in paragraph 2, the CAA can have no justification for
requiring further evidence once it has been established that its requirements can be
satisfied in a particular way. The onus is, of course, still upon such an applicant to
demonstrate that the relevant circumstances are identical.

4 Evidence of Identicality

4.1 To establish that a component, item of equipment, complete aircraft, or operating

condition is identical to one already approved may not be a simple matter. Design
criteria, manufacturing processes, quality control, systems safety assessments,
flying qualities and performance, etc., may all be involved and have to be considered.
4.2 In view of this, the CAA will invariably require applicants who request certification on
the basis of identicality to provide evidence that this claim is supported by the original
applicant (manufacturer, operator, etc.) against whose certification comparison is
being made. In the absence of such confirmation, the CAA will normally require
substantiating data to be developed and presented to justify certification in its own
right.

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CAP 562 Civil Aircraft Airworthiness Information and Procedures

Part 12 Specifications

Leaflet 12-1 Aerospace Specifications

1 Introduction

1.1 Materials used in aircraft parts affected by airworthiness requirements should

conform to approved material specifications. For this purpose, in addition to
specifications specifically approved by the CAA (see paragraph 5), British Standard
Specifications in the Aerospace Series, issued by the British Standards Institution
(BSI) are accepted as approved, and are obtainable from:
British Standards Institution
Standard Enquiries
389 Chiswick High Road
LONDON, W4 4AL
Telephone: (0208) 996 9000
1.2 Unless otherwise stated, reference to any specification referred to in this publication
implies the latest issue including any amendments.

2 DTD Specifications are prepared by the:

Materials and Structures Department

Royal Aircraft Establishment
FARNBOROUGH

3 DTD and DEF Specifications are published by and obtainable from:

TSO (The Stationery Office)

(Mail and Telephone orders only)
P O Box 276
LONDON SW8 5DT
Telephone: (0207) 622 3316

4 Defence Standards are published by and obtainable from:

Directorate of Standardisation
Stan 13
Ministry of Defence
Montrose House
187 George Street
GLASGOW G1 1YU

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CAP 562 Civil Aircraft Airworthiness Information and Procedures

5 Specifications Approved by the CAA

5.1 Specifications prepared for a material by an Approved Design Organisation where the
material is to be used in a part designed within the terms of the design approval
should be submitted in duplicate for approval to the:
Civil Aviation Authority
Safety Regulation Group
Aviation House
Gatwick Airport
WEST SUSSEX RH6 0YR
5.2 A specification submitted for approval should, according to the material concerned,
include such of the following information as appropriate:
a) An identity or reference number, issue number and date.
b) A title describing the material.
c) The quality and/or chemical composition of the material.
d) The mechanical and/or physical properties of the material.
e) The method of determining the mechanical and/or physical properties of the
material.
f) Particulars of defects which render the material unsuitable.
g) Particulars of heat treatment and/or other manufacturing processes.
h) A table of manufacturing tolerances.
i) Particulars of such markings which will ensure identification of the material.
5.2.1 A specification will be approved if the CAA accept that the material complies with
such a specification having the essential properties assumed by the design in the
associated technical investigation.

6 CAA Airworthiness Specifications

The following specifications are available from the CAA web site at www.caa.co.uk
under the Publications section. Paper copies are available from the CAA’s printers
whose details are given on the inside cover of this publication.

No. 1 Safety Belts Issue 6 12 March 2004

No. 2 Inflatable Liferafts Issue 2 1 November 1985

No. 5 Inflatable Lifejackets Issue 2 23 November 1979

No. 6 Escape Chutes Issue 2 21 June 1956
No. 7 Break-in Points Issue 2 8 August 1962

No. 9 Child’s Flotation Cot Issue 1 9 April 1957

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No. 10 Flight Data Recorder Systems Issue 1 1 May 1974

No. 10A Flight Data Recorder for Aeroplane
Accidents Investigation Issue 1 1 June 1990
No. 11 Cockpit Voice Recorder Systems Issue 3 13 August 1983
No. 12 Underwater Sonar Location Devices
Approval, Installation and Maintenance Issue 1 1 May 1974

No. 14 Ground Proximity Warning Systems Issue 2 September 1976

No. 15 Public Address Systems Issue 1 27 January 1989
No. 16 Automatically Deployable Emergency
Locator Transmitters for Helicopters Issue 2 1 December 1991
No. 17 Wheels and Wheel Brake Assemblies
Minimum Performance Standards Issue 1 18 September 1986
No. 18 Flight Data Recorder for Helicopter
Accidents Investigation Issue 1 1 June 1990
No. 19 Helicopter Crew Members Immersion
Suits Issue 1 15 April 1991
No. 20 Passenger Protective Breathing
Equipment (PPBE) – Smoke Hoods Issue 1 9 May 1988
No. 21 Helicopter Public Address Systems Issue 1 23 March 1998
No. 22 Global Positioning Systems (GPS) for Use
in Rotorcraft for En-route Navigation Issue 1 25 April 2005

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Part 14 Standard Maintenance Practices

Leaflet 14-0 Standard Maintenance Practices – Introduction

1 Introduction

1.1 Standard Maintenance Practices (SMPs) contained within this part are produced by
the Survey Department in consultation, where necessary, with other Sections of the
CAA. They are intended to give guidance and information to originators of
maintenance schedules submitted for Approval and the holders of Approved
Maintenance Schedules, in respect of the minimum maintenance requirements
acceptable to the CAA for the subjects addressed.
1.2 Holders of Approved Maintenance Schedules should review and update their
schedules, using the normal 'B' amendment procedure, to comply with applicable
SMPs.

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Leaflet 14-9 Standard Clauses for Insertion in Maintenance

Schedule Introductory Pages

The purpose of this Standard Maintenance Practice is to ensure that the introductory
pages of Maintenance Schedules are reasonably consistent and, where applicable,
include the following items. Minor variation in the wording is acceptable providing that
the intention remains clear.

1 Annual Utilisation and Maintenance Review

1.1 In the preparation of this Maintenance Schedule Reference ....... to meet the
requirements of the Air Navigation Order (ANO) and British Civil Airworthiness
Requirements (BCAR), the recommendations made by the constructors and
manufacturers have been evaluated and, where appropriate, have been incorporated.
It is agreed that it is a duty of the Operator or his contracted Maintenance
Organisation that subsequent maintenance recommendations, including
airworthiness information promulgated in Service Bulletins, Service Letters, etc.,
issued by the constructors and manufacturers, should be evaluated and, where
appropriate, should be incorporated in this Schedule by approved amendment
procedures.
1.2 The periods/frequencies of the maintenance tasks in this Schedule are generally
based on an anticipated annual utilisation of ..... flying hours and large variations in the
annual utilisation of individual aircraft could invalidate the effectiveness of certain
tasks. If the annual utilisation varies by more than 25% from that anticipated, the
Operator accepts that he, or his contracted maintenance organisation, must review
the maintenance tasks and periods with a view to making any necessary adjustments.
1.3 In addition to variations in utilisation, the data contained in this Schedule will be
reviewed at least annually by the Operator, or his contracted Maintenance
Organisation, to ensure that the detailed requirements continue to be valid in the light
of operating experience.

2 Maintenance Schedule Applicability

This Maintenance Schedule is applicable only to the following aircraft:

Registration Type Serial No.

NOTE: Any changes in aircraft applicability must have prior approval by the CAA.

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3 Flying Times

All periods in this Schedule quoted in 'hours flying' are to be calculated and recorded
on a 'Take-Off to Touch-Down' basis.

4 Maintenance Schedule Approved as Alternative to CAA/LAMS/FW or

CAA/LAMS/H

Maintenance Schedules for aircraft not exceeding 2730 kg MTWA are additionally
required to include the Certification requirements contained in CAP 520 Light Aircraft
Maintenance.

5 Certification of Maintenance

Attention is drawn to the necessity of ensuring that the appropriate Certification of

Maintenance is completed. The requirements are specified in the CAA Approval
Document and Endorsements relating to this Schedule.

6 Permitted Variations to Maintenance Periods

The periods prescribed by this Schedule may be varied subject to the conditions and
limits contained in Appendix A to this SMP.

7 Airworthiness Directives and Manufacturer’s Service Information

7.1 European Commission Regulation (EC) No. 2042/2003 Annex I requires Operators to
institute a system for the assessment of continuing airworthiness information. This
information will originate from the Responsible Authority of the State of Manufacture
in the form of Airworthiness Directives (or documents of comparable intent) and from
the manufacturer in the form of Service Bulletins, Letters, Information Leaflets, etc.
resulting from In-Service experience.
7.2 Compliance with the mandatory requirements of the Responsible Authority of the
country of origin must be achieved unless this requirement is varied by the CAA.
7.3 Continuing Airworthiness and other Service Information must be continuously
evaluated by the Operator or the contracted Maintenance Organisation and, where
necessary, appropriate action must be taken to amend the Maintenance Schedule.

8 Fatigue Lives and Mandatory Life Limitations

8.1 Structural 'fatigue' lives published by the manufacturer or by the CAA are mandatory
for aircraft on the UK register (see also BCAR Section A and B). In the case of foreign
products the CAA may vary the lives published by the manufacturer or itself publish
a life, normally as a CAA Additional Airworthiness Directive.
8.2 All other life limitations classified as mandatory by the manufacturer must also be
observed unless varied by the CAA.

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9 Maintenance Practices and Procedures

The practices and procedures necessary to accomplish the requirements of this

Schedule, or work resulting from its application, should be, as a minimum, to the
standards recommended in:
a) relevant Maintenance, Overhaul and Repair Manuals and where applicable
b) Civil Aircraft Airworthiness Information and Procedures.

10 All Vital Points and Control Systems

10.1 Whenever inspections are made or work is undertaken on vital points in flying or
engine control systems, a detailed investigation must be made on completion of the
task to ensure that all tools, rags or any other loose articles which could impede the
free movement and safe operation of the system(s) have been removed and that the
system(s) and installation in the work area are clean and unobstructed.
10.2 If, as a result of the application of this Schedule, any part of either the main or any
associated system is dismantled, adjusted, repaired or renewed, that part of the
system(s) which has been disturbed shall be subjected to a duplicate inspection, with
free movement, range, direction and tension checks and shall be certified in
accordance with British Civil Airworthiness Requirements, Section A Chapter A6–2 or
Section B Chapter B6–2 (A5–3).

11 Fuel System Contamination Checks

The following check must be made to establish that fuel systems are free from
contamination:
Fuel system water drain checks are to be carried out at periods not exceeding 24
hours elapsed time and in accordance with Company instruction.
NOTE: The operator must be satisfied with the quality of all fuel taken on board his
aircraft, particularly in respect of water contamination and monitor the
supplier’s quality performance.

12 Portable Valise Type Liferafts

At the appropriate Overhaul Period ten percent of all liferafts installed in fleets using
system bottle and release mechanism are to be inflated and tested. Ensure that
deployment and inflation is satisfactory.

13 Area or Zonal Inspection

Where the term 'AREA' or 'ZONAL' is used in this Schedule, this is to be interpreted
to mean that a general visual inspection is made for general condition, security and
leaks in the structure, systems and components and their installation in the specified
zone or area. The inspection must be of sufficient depth to establish that any
significant deterioration is identified and rectified to ensure that the general quality/
condition of the zone/area is satisfactory until the next higher inspection becomes
due.

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14 Inspection Standards

14.1 Unless otherwise stated, all inspection requirements are to be applied without
removing an item from the aircraft or dismantling the item, group or sub-assembly
unless dismantling is considered essential in order to ensure airworthiness. Where
dismantling is required by this Schedule, this is stated against the item concerned.
14.2 All significant terms and abbreviations used within this Schedule to define each
maintenance task are defined in accordance with the Type Certificate holder’s
definitions, current JAR, CAA BCAR definitions or, in the absence of formal
definitions, those quoted in World Airlines Technical Operations Glossary.
14.3 The inspection standards applied to individual task inspections must meet the
requirements of the Type Certificate holder’s recommended standards and practices.
In the absence of specific manufacturers guidance, refer to this CAP 562 (Civil Aircraft
Airworthiness Information and Procedures) or FAA AC 43–13–1A Aircraft Inspection
and Repair or other approved data, as appropriate.

15 Condition Monitored Maintenance/Reliability Programme

The method of data collection, analysis, corrective actions and reporting specified for
the implementation of this programme is prescribed in the current Document ........
'CMM/Reliability Programme', which constitutes part of this Approved Maintenance
Schedule.

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Appendix A

PERMITTED VARIATIONS TO MAINTENANCE PERIODS

1

1 The Operator or their contracted Maintenance Organisation, may vary the periods
prescribed by this Schedule provided that such variations are within the limits of sub-
paragraphs a) to e) of this Appendix A.

2 Variations shall be permitted only when the periods prescribed by this Schedule (or
documents in support of this Schedule) cannot be complied with due to
circumstances which could not reasonably have been foreseen by the Operator or by
the contracted Maintenance Organisation.

3 The decision to vary any of the prescribed periods shall be taken only by the Chief
Inspector/Quality Manager or person of equivalent status on behalf of the Operator or
the contracted Maintenance Organisation. Particulars of every variation so made shall
be entered in the appropriate Log Book(s).

a) Items Controlled by Flying Hours

Period Involved Maximum Variation of the Prescribed Period
i) 5000 flying hours or less 10%
ii) More than 5000 flying hours 500 flying hours
b) Items Controlled by Calendar Time
Period Involved Maximum Variation of the Prescribed Period
i) 1 year or less 10% or 1 month,
whichever is the lesser
ii) More than 1 year but not 2 months
exceeding 3 years
iii) More than 3 years 3 months
c) Items Controlled by Landing/Cycles
Period Involved Maximum Variation of the Prescribed Period
i) 500 landings/cycles or less 10% or 25
landings/cycles,
whichever is the lesser
ii) More than 500 landings/cycles 10% or 500
landings/cycles,
whichever is the lesser

d) Items Controlled by More Than One Limit. For items controlled by more than
one limit, e.g. items controlled by flying hours and calendar time or flying hours and
landings/cycles, the more restricted limit shall be applied.

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e) Items Already Subject to CAA Trial Extension Programme. For an item

already subject to an agreed CAA trial extension programme, the trial period may
be varied by a maximum of 50 flying hours only provided that such a variation is
not specifically excluded by the agreed trial extension programme.

NOTE The variations permitted above do not apply to:

a) Those components for which an ultimate (scrap) or retirement life has
been prescribed (e.g. primary structure of components with limited
fatigue lives and high energy rotating parts or which containment is
not provided). Details concerning all items of this nature are included
in the manufacturer’s documents or manuals.
b) Those periods included in the Maintenance Schedule which have been
classified as mandatory by the CAA (see CAP 747 - Mandatory
Requirements for Airworthiness).
c) The Annual Inspection periods for Schedules submitted as alternatives
to Schedules Reference CAA/LAMS/FW or CAA/LAMS/H.

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Leaflet 14-14 Cockpit Voice Recorder System Fairchild

A100 Series

1 Introduction

1.1 This SMP establishes minimum requirements relating to maintenance tasks and their
intervals for the Fairchild A100 Series Cockpit Voice Recorder (CVR) System. These
requirements take account of the Component Maintenance Manual 23–70–01, latest
issue. Account is also taken of the lack of failure detection within the system other
than that provided by the limited pre-flight test facility.
1.2 The maintenance intervals stated in this SMP are based on elapsed calendar time.
These intervals should be interpreted as the maximum permissible periods between
the maintenance tasks specified. Operators may submit Maintenance Schedules
based on flight hours provided that fleet operating statistics show that the calendar
time limits are unlikely to be exceeded.
1.3 Operators will need to review the results of their CVR sampling programme (see
paragraph 8) and, where shown to be necessary, reduce maintenance intervals until
an acceptable level of serviceability has been re-established. Such a review should be
made annually and a report should be sent to the CAA.

Maximum
Item Equipment Task Interpretation
Interval

1 Cockpit Voice Operational check Daily Confirm serviceability using TEST

Recorder (pre-flight function on CVR controller (flight
System post-flight) crew check).

2 Check/Functional Not Inspect installation. Confirm, by

Test exceeding 6 means of the CVR controller
months monitor jack, proper recording on
elapsed time each voice channel from area
microphone(s), receiver audio,
sidetone, interphone, public
address (if recorded) and boom
microphone (including 'hot mike'
function, i.e. interphone OFF).
Confirm proper functioning of the
inhibit logic for bulk erase.

3 Functional Test Not Confirm proper recording of data.

(helicopters only) exceeding 12
months
elapsed time

4 Cockpit Voice Check Not Remove CVR for inspection,

Recorder exceeding 24 cleaning of erase/recording heads
months and tape transport mechanism,
elapsed time replacement of worn parts,
weighing of Thermopack
insulation assembly and test as
required by the Component
Maintenance Manual.

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Maximum
Item Equipment Task Interpretation
Interval

NOTES:
1) Before cleaning is attempted,
the quality of the recording
already on the tape should be
evaluated. Where indicated by
the evaluation, appropriate
maintenance should be
performed on the aircraft from
which the CVR was removed.

2) The Component Maintenance

Manual lists various items
which may need to be
replaced between 7000 and
9000 equipment operating
hours.

5 Ditching Check/Functional Not Confirm proper sensor function.

Sensor Test exceeding 24 Test may be performed in situ if
(Helicopters) months practical.
elapsed time

6 Crash sensor Check/Functional As stated by Comply with the instructions

(where fitted) Test the vendor issued by the vendor.

7 Underwater Check/Functional As stated by Comply with the instructions

Locator Test the vendor issued by the vendor.
Beacon

8 Cockpit Voice Sample check * in As agreed Remove CVR immediately after

Recorder accordance with between flight. Replay and evaluate quality
System criteria and operator and of in-flight recording.
procedures CAA
agreed with CAA

* NOTES: (1) The objective of this sample check is to confirm the adequacy of
maintenance and to detect any deterioration of recording quality, e.g.
due to vibration, electrical interference, acoustic noise or intermittent
defects.

(2) Operators will need to submit, to the CAA, proposals for their CVR
sampling programme. Account will need to be taken of route
structure, number of aircraft in the fleet type, and their annual
utilisation. See also paragraph 1.3.

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Leaflet 14-15 Maintenance and Inspection of Crew

Harnesses and Passenger Seat Belts (Metal to
Metal Attachment)

1 Introduction

1.1 The following information may be used to establish a consistent CAA policy
appertaining to the maintenance of seat belts and harnesses.
1.2 In the absence of manufacturer’s recommendations the following conditions must be
satisfied by an operator deciding to adopt the 'on-condition' philosophy in preference
to load testing:
a) A detailed visual inspection including the seat attachments for security of
installation and integrity of fittings. Check for signs of distress, wear or biochemical
staining at intervals not exceeding 6 months.
b) Whenever seat belts or harnesses are removed for repair or re-conditioning, the
requirements of CAA’s Specification No. 1 – Safety Belts – as an example must be
observed. (See Attachment.)
The CAA will accept the following values, depicted in the table below, as an
acceptable sample of the work completed in respect of the maintenance of safety
belts and harnesses:

Requirement Sample

i) Application of design ultimate 1% of batch or at least one assembly

load subsequent to repair of seat whichever is the greater.
belt/harness assembly.
ii) Following the application of the
load defined in paragraph (i), the
seat belt/harness assembly shall
be subjected to the requirement
of paragraph 5.4.1 of CAA
Specification No. 1 in order to
establish the buckle release load
which shall not exceed 20 lbf.

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Attachment to Leaflet 14-15

United Kingdom
Civil Aviation Authority
Specification No. 1
Issue 6
12 March 2004
Safety Belts

1 Introduction

1.1 Although this Specification was written originally for aeroplanes, a safety belt
designed to this Specification is also acceptable to the CAA for use in a Rotorcraft.

2 Applicability

2.1 Safety belts shall comply with this Specification or with such other Specifications as
the CAA may approve. Alternative Specifications, submitted for approval, shall
provide at least the same amount of protection. FAA TSO C.22(f) is considered to be
an acceptable specification provided that compliance with paragraphs 3.8, 4.2, 5.3,
5.4, 5.5 and 5.6 of this Specification is also demonstrated.
2.2 FAA TSO-C22g or JTSO-C22g qualified safety belts are considered acceptable for
installation with no further consideration of the requirements of this Specification.
2.3 The installation of safety belts shall be done in accordance with the certification
requirements for the aircraft.

3 Form

3.1 The belts shall be individual to a single occupant and shall be suitable in every respect
for installation in an aeroplane for the purpose of restraining the wearer, without
causing significant injury, against the ultimate inertia forces prescribed.
3.2 The correct method of using the belt shall be rapid and obvious.
3.3 Parts, made of metal or similar unyielding material, which come into contact with the
wearer, shall be well rounded where necessary.
NOTE: Consideration should be given to the fact that the wearer does not remain in the
normal sitting position during the application of the higher accelerations.
3.4 No part of a safety belt shall pass between the wearer’s legs or shall appreciably
restrict the movement of the wearer’s limbs.
3.5 The belt shall, when correctly adjusted to the wearer, remain in position irrespective
of variation of load.
3.6 Those parts of the belt which under the prescribed accelerations restrain, and are in
contact with the wearer, shall be not less than 50 mm (2 in.) wide.
NOTE: However for belts not needing TSO approval an approved military belt 44 mm
(1·75 in) minimum width which is otherwise acceptable will not be rejected by the
CAA.

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CAP 562 Civil Aircraft Airworthiness Information and Procedures

3.7 Those parts defined in paragraph 3.6 shall be such that the whole of the minimum
width specified is effective in transmitting load from the parts to the wearer.
3.8 When correctly installed, the belt, when worn, shall lie across the groin of the wearer.
The belt when so worn shall lie in a plane which is approximately at 45° to the plane
of the longitudinal and lateral axes of the aeroplane.
3.9 Throughout this Specification, a belt is regarded as being divisible into various
members (e.g. left strap, right strap, release mechanism, etc.) which are liable to be
detached from each other for purposes of storage or replacement. It is further
envisaged that more than one firm may be concerned in the manufacture of the
completed belt; for example, a release box may be made by a different firm from that
responsible for the webbing parts.

4 Strength

4.1 The certified strength of a belt is determined by the tests of paragraph 7.

NOTES: 1) The certified strength required of each member will depend upon the
manner in which the belt is installed in the aeroplane and upon the
emergency alighting accelerations appropriate to the particular aeroplane.

2) The emergency alighting accelerations for a particular aeroplane type into

which the belt is to be fitted may be determined in consultation with the
aeroplane manufacturer. Alternatively the belt may be made sufficiently
strong for it to be suitable in any aeroplane type. It is emphasised that
greater strength will permit the belt to be certified as being capable of giving
greater restraint, and this greater restraint may be of value in crash
conditions.

4.2 The strength of belts with self-aligning and fittings, fitted in a normal forward-facing
installation, however, may be designed for the loads prescribed in paragraph 4.3. The
loads of paragraph 4.3 may not be used and the installation shall be conservatively
represented in the tests as required by paragraph 7 if:
a) When restraining an occupant, the vertical projection of the angle between any strap
(at its attachment point) and the fore and aft axis of the aircraft exceeds 15° , or, if
the end fittings are not self-aligning,
or
b) The installation is not a forward facing seat installation.
4.3 For unit value of forward g the basis of certified strength required of a member is 670
N/g (150 lbf/g), this load shall be multiplied by the prescribed forward g for the
aeroplane type. Safety belt attachment fittings shall have an additional strength factor
of 1·33.

5 Means of Adjusting, Fastening and Releasing

5.1 The belt adjustment shall be either in the buckle or adjacent to it. The adjustment
provided in this way shall be such as to suit all persons likely to use the belt. A
separate action shall not be necessary to lock the means of adjustment.
NOTE: The load required to vary the adjustment, i.e. tighten or loosen the belt, should not
exceed 134 N (30 lbf) and the design should be such that it is easy to operate.

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CAP 562 Civil Aircraft Airworthiness Information and Procedures

5.2 The means of fastening and releasing shall be rapid and obvious and shall be of the
metal to metal positive latching type. The design shall be such that the possibility of
the means of locking, releasing or adjustment being jammed by loose clothing or by
twisting of the belt, is extremely remote. The fastening means shall be designed to
preclude incorrect latching by the wearer.
NOTE: Instructions may be marked on the belt to facilitate its use. However, the action
should not be such as to demand instructions.
5.3 The wearer, shall be able to release the belt with either hand, regardless of aircraft
orientation in an otherwise survivable accident without undue difficulty.
5.4 The force required to effect release from the belt shall be assessed when, after the
belt has been subjected to a load as near as practical to the ultimate load (see
paragraph 7.2.2), it is under a residual load of 1112 N (250 lbf).
5.4.1 Where a conventional lever operated release mechanism is used (i.e. one which can
be grasped with all the fingers of one hand) the load to effect release under the
conditions defined in paragraph 5.4 shall not exceed 90 N (20 lbf).
NOTE: In addition to the requirements of 5.4.2 it is also recommended that the minimum
release load should not be less than 22.5N (5 lbf).
5.4.2 To avoid inadvertent release there shall be a free movement of the lever and the belt
shall remain fastened until the lever attains an angle of not less than 70° or not more
than 95° to its position at rest. The lever shall be spring loaded to the position it
normally assumes when the belt is fastened.
NOTE: Release at a lever angle of less than 70° may be acceptable where the design is such
that it can be demonstrated that the lever is unlikely to be caught and moved by
clothing.
5.5 Where means of release other than by a conventional lever are employed the
functional characteristics and release loads of such means shall be agreed with the
CAA.
5.6 Where the positive locking action of the buckle is dependent upon a spring element,
no single failure shall cause or permit the belt to release, unless an adequate fatigue
life has been established.

NOTES: 1) A total of 100,000 cycles may be assumed as equal to 10 years of life.

2) It is recommended that the fastening and releasing mechanism should not

embody parts which need to be manufactured and maintained to close
tolerances for their satisfactory functioning.

5.7 The means of fastening shall be such that the responsible crew member will be able
to see at a glance whether the belt is securely fastened or not.
5.8 Extension pieces shall be identified as to the type of belt with which they are to be
used. Extension pieces shall be designed and tested to the same standards as are
established for belts submitted in compliance with this Specification.

6 Materials and Processes

This paragraph 6 is applicable only to parts which contribute to strength, and to parts
which are functionally important.
6.1 Only materials to a suitable approved specification1, or obtained from a source
approved by the CAA, shall be used.

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CAP 562 Civil Aircraft Airworthiness Information and Procedures

6.2 Fittings shall be made of metal or of materials that have been demonstrated to be
equally satisfactory for their intended function.
6.3 Materials which may deteriorate in service or materials the properties of which may
be significantly affected by ambient conditions (e.g. leather) shall not be used.
6.4 Where such processes as soldering, brazing, welding and casting are used, suitable
factors and safeguards acceptable to the CAA shall be employed. Primary load
carrying castings shall comply with the requirements for critical castings.
6.5 The choice of materials and of protective treatments for those parts which cannot
readily be inspected shall be such as to minimise the risk of corrosion or deterioration.
6.6 Materials shall be flame resistant to the appropriate standard defined in the
certification basis of the aircraft.

7 Tests

7.1 General
Each member shall be tested in a manner which is agreed by the CAA to represent
adequately the conditions of the installation. Accurate representation may be
necessary for cases where unusual geometry or eccentricity of loading could affect
the ultimate load or the functioning of the means of release. Tests shall be arranged
so that the friction effects in the test apparatus do not significantly relieve the stress
in any member under test.
The load in a member shall be taken as the load applied to the end nearest to the point
of attachment to the airframe or seat.
7.2 Prototype Belts
7.2.1 Each member shall be tested to the ultimate load: the member will be accepted if
each part supports the load required of it without significant slipping of any adjusting
mechanisms it may include.
NOTE: If, at the point during this test when one half of the certified strength is reached, an
inspection is made of those members utilising webbing or similar material in a load-
bearing capacity, it may be possible to obtain some confirmation whether or not it
will be possible to carry out the production test of 7.3.2.1 without damage to
otherwise satisfactory series belts.
7.2.1.1 The load to be applied shall be that of paragraph 4.3 multiplied by a factor of 1·2.
Where significantly new designs are being tested the CAA may require more than one
specimen to be tested.
7.2.2 Compliance with the requirements of paragraph 5.4 shall be demonstrated by tests
in which the release mechanism is first loaded by means of the members normally
assembled to it, to as near as is practical to the ultimate load of the belt (in no case to
less than its certified strength). The load shall then be reduced to not less than that
prescribed in paragraph 5.4, and the release mechanism operated. The force required
to operate it shall be assessed and shall be such that it can be applied without
difficulty by a wearer of the belt. This test shall be made for each combination of loads
liable to be critical.

1. British Standards Specifications issued by the British Standards Institution and D.T.D. Specifications obtainable from
HMSO are approved. Other specifications will be approved by the CAA if, in its opinion, materials accepted as complying
with these Specifications have the essential properties assumed in the technical investigation associated with the design
approval.

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CAP 562 Civil Aircraft Airworthiness Information and Procedures

7.3 Series Belts

7.3.1 General
Series belts shall be checked for consistency with that of the prototype by means of
the tests prescribed in paragraph 7.3.2.
NOTE: These tests may be modified, in consultation with the CAA, having regard to the
particular design and to the results of tests made in accordance with paragraph 7.2.
Where experience gained with the production of the particular design shows such
test to be unnecessary, the CAA may agree to waive the test requirements of
paragraphs 7.3.2.1 and 7.3.2.2 provided that an adequate sample of each production
batch is tested in accordance with paragraph 7.3.2.3.
7.3.2 Schedule of Tests
7.3.2.1 Each member, in which webbing or similar material is used in a load-bearing capacity,
shall be loaded to not less than one-half of its certified strength. Under these
conditions no sign of incipient failure shall be exhibited.
7.3.2.2 Each member incorporating a release mechanism shall be loaded to not less than one-
half of its certified strength. The load may then be reduced to not less than that
appropriate to the item, as prescribed in paragraph 5.4 and the release shall be
operated. Under these conditions the effort required for release shall be comparable
to that agreed by the CAA, in the light of tests carried out in accordance with
paragraph 7.2.2.
7.3.2.3 The ultimate strength as prescribed in paragraph 7.2.1.1 shall be verified by tests to
destruction on samples taken at random by the manufacturer, the percentage of parts
so tested being decided by the manufacturer, subject to any minimum which may be
prescribed by the CAA.
7.4 Reconditioned Belts. Reconditioned belts shall be subjected to tests similar to
those prescribed in paragraphs 7.3.2.1 and 7.3.2.2, or, in agreement with the CAA,
7.3.2.3 on a sampling basis.

8 Compass Safe Distance

Where magnetic material is used the compass safe distance shall be not greater than
305 mm (12 in.) (i.e. the belt when at a distance of 305 mm (12 in.) from the compass
shall not affect the compass readings by more than 1° ). (See British Standard G.100
for further details.)

9 Marking
Each normally detachable member of a belt certified as complying with this
Specification shall be indelibly marked with:
• the manufacturer’s approved inspection mark,
• the part number and/or model number,
• the serial or batch number.

26 March 2004 Part 14 Leaflet 14-15 Attachment Page 5

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CAP 562 Civil Aircraft Airworthiness Information and Procedures

Leaflet 14-17 N15F210B Underwater Locating Beacon

1 This SMP has been raised to implement the results and recommendations of Dukane,
in respect of their N15F210B Underwater Locating Beacon.
2 Dukane’s ongoing reliability programme has identified a significant age related
reduction in the output of beacons that are greater than 12 years of age. The reduced
acoustic output will have a detrimental effect on being able to locate the beacon and
its associated flight recorder.
3 Action to be Taken

Underwater Locating Beacon: N15F210B

Serial Nos 1 thro 14500 Remove from service at the time of their
next battery change.

Any one or two letters before the Serial No. Manufactured after 1978 and are not
immediately affected.

Serial Nos 14500 thro C5500 to include all Receive one more battery change and then
Serial Nos with 5 digits and Serial Nos with be removed from service at the following
one letter plus 4 digits. battery change.

4 The N15F210B beacon, when removed from service can be returned to Dukane for
refurbishment and recertification.
5 A new DK100 beacon can be purchased from Dukane to replace each N15F210B
beacon removed from service.
6 Exclusions – Attached are two Appendices listing N15F210B Beacons by Serial
Numbers which were built prior to 1979 and from 1979 to 1983 which have since
been refurbished with the new potting material and are, therefore, not affected.

30 June 1992 Part 14 Leaflet 14-17 Page 1

CAP 562 Civil Aircraft Airworthiness Information and Procedures

Refurbished N15F210B Beacons – Prior to 1979

715 1304 2314 4086 6805 13266

717 1322 2334 4118 6983 13268
738 1343 2418 4168 7005 13280
804 1375 2488 4175 7073 13402
805 1401 2563 4187 7109 13509
844 1446 2566 4283 7130 13535
846 1496 2617 4292 7138 13559
847 1515 2626 4372 7158 13578
849 1526 2653 4373 7176 13582
858 1534 2747 4418 7347 13706
861 1566 2770 4423 7354 13718
878 1587 2873 4447 7357 13900
879 1595 2882 4453 7395 13932
887 1602 2908 4475 7821 14098
888 1607 2939 4640 8186 14448
892 1615 2957 4729 6174 14450
893 1620 2991 4759 8441
896 1627 3044 4787 8842
906 1634 3071 4813 9088
909 1698 3085 4629 10267
912 1703 3066 4877 10442
931 1730 3121 4885 10884
943 1754 3125 4896 10947
960 1771 3140 4910 10950
975 1779 3158 4973 10985
1005 1780 3169 5019 11096
1041 1807 3176 5029 11097
1043 1810 3185 5125 11130
1045 1816 3334 5147 11326
1082 1835 3367 5157 11343
1084 1861 3386 5277 11398
1086 1877 3390 5352 11421
1112 1878 3466 5449 11425
1135 1880 3522 5513 11433
1156 1888 3546 5594 11472
1169 1889 3557 5607 11473
1177 1893 3560 5610 11705
1187 1806 3570 5624 11707
1191 1910 3667 5811 11786
1210 1913 3727 5815 12177
1217 1926 3797 5849 12396
1223 1940 3806 6002 12423
1246 1944 3824 6064 12657
1249 1949 3840 6068 12763
1255 1954 3845 6402 12784
1257 1959 3647 6406 12892
1265 2060 3874 6506 12901
1278 2176 3893 6600 13112
1284 2179 3910 6655 13128
1297 2203 3935 6691 13170
1302 2261 4006 6756 13258

30 June 1992 Part 14 Leaflet 14-17 Page 2

CAP 562 Civil Aircraft Airworthiness Information and Procedures

Refurbished N15F210B Beacons – from 1979 to 1983

14721 22925 B9224 C5368

14926 22985 B9277
14998 23006 B9279
15002 23089 B9265
15019 23289 B9266
15204 23416 B9325
15249 23474 B9381
15337 23520 B9508
15651 23550 B9512
15719 23576 B9812
15754 23720 C0040
15923 23989 C0080
15930 24023 C0089
16073 24095 C0120
16226 24111 C0168
16231 24113 C0183
16356 24226 C0315
16448 24277 C1150
16662 24374 C1401
16763 24520 C1738
17065 24618 C1786
17280 24754 C1874
17376 24914 C1910
17734 25005 C1916
17856 25044 C1923
17863 B5670 C2281
18468 B5673 C2375
18506 B5834 C2393
18613 B7023 C2394
18614 B7048 C2395
18958 B7385 C3311
19008 B7739 C3373
19027 B7783 C3410
19068 B8077 C3499
19135 B8102 C3562
19354 B8169 C3593
19452 B8311 C3597
19480 B8367 C3604
19654 B8401 C3612
20113 B8402 C3616
20550 B8525 C3904
20742 B8623 C4046
20869 B8626 C4060
20980 B8948 C4109
21044 B9034 C4502
21371 B9051 C4564
21618 B9060 C4658
21682 B9061 C5168
22091 B9077 C5201
22198 B9100 C5212
22277 B9100 C5362

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CAP 562 Civil Aircraft Airworthiness Information and Procedures

Leaflet 14-19 Maintenance of Aircraft not Operated for

Commercial Air Transport

1 Introduction

1.1 The purpose of this Standard Maintenance Practice is to identify the maintenance
requirements for aircraft that are not operated for the purpose of commercial air
transport. The maintenance of the aircraft including its engines, propellers and
equipment (as applicable) shall be in accordance with the Type Certificate holder’s
inspection standards, recommended maintenance programme or schedule and the
requirements of this SMP where the manufacturer’s schedules may not encompass
the additional maintenance items covered by this SMP.
1.2 It is the responsibility of the operator to ensure that this document is completed and
submitted to the CAA Regional Office for approval.
1.3 The contents of this document shall not be amended without the approval of the Civil
Aviation Authority except where changes only affect Appendix B.

2 Maintenance Programme Reference

Manufacturer’s
Airframe Engine Propeller
manual reference
.......................... .......................... ..........................
Revision Status .......................... .......................... ..........................

NOTE: See also Appendix A for equipment etc.

2.1 Maintenance Schedule Applicability

Aircraft type Aircraft registration(s) Aircraft serial number(s)

...................................... ....................................... ......................................
...................................... ...................................... ......................................

3 Compliance Statement

The contents of this schedule and its associated appendices address the
manufacturer’s minimum maintenance requirements for the aircraft listed above.

Organisation/ ................... Person ................. Signature .................... Date ...............

Operator

CAA Use Only

CAA Schedule Approval Reference. MS/........................................ CAA Stamp

22 June 1998 Part 14 Leaflet 14-19 Page 1

CAP 562 Civil Aircraft Airworthiness Information and Procedures

4 Annual Utilisation and Maintenance Review

4.1 In order to meet the requirements of the Air Navigation Order (ANO), British Civil
Airworthiness Requirements (BCAR) and Joint Aviation Requirements (JAR) where
appropriate, the recommendations made by the manufacturers as amended, have
been evaluated and where appropriate are included. It is the duty of the operator or
his contracted maintenance organisation to ensure that subsequent maintenance
recommendations, including airworthiness information promulgated in Airworthiness
Directives, Service Bulletins, Service Letters, Maintenance Manuals, and other
regulatory material as issued by the State of Manufacture or the United Kingdom
CAA, are evaluated for applicability to this approved schedule.
4.2 Anticipated annual utilisation ................ (flying hours)/ ................. (flight cycles).
If the annual utilisation varies by more than 25% from that anticipated, the operator
accepts that he, or his contracted maintenance organisation, must review the
maintenance tasks and periods with a view to making any necessary adjustments.
NOTE: If the manufacturer produces a special utilisation (e.g. low utilisation) or a
schedule based on a specific annual utilisation then this must be used. If this
does not align with the anticipated annual utilisation stated above, then the
operator accepts that he, or his contracted maintenance organisation, must
review the maintenance tasks and periods with a view to making any
necessary adjustments.

5 Pre-Flight Inspections

These checks are to be carried out in accordance with the aircraft flight or operations
manual, or as specified in the manufacturer’s maintenance schedule.

6 Tyre Maintenance

Tyre reliability is dependant on regular checks being carried out. The pre-flight
inspection should include a check of the tyres for condition and correct inflation.
NOTE: For large transport aircraft with multi wheel installations see CAP 562 -
CAAIP Leaflet 11-22 Appendix 32-2.

7 Avionic Installations

7.1 In the absence of the aircraft manufacturer’s maintenance requirements for Radio
Navigation and Communication equipment, and Radar equipment, an appropriate
programme of maintenance shall be included.
7.2 Compass systems will require check swings at periods not exceeding;
i) for aircraft of 5700 kg MTWA or below, 2 years.
ii) for aircraft above 5700 kg MTWA, 3 years.
Where the aircraft system uses an inertial reference system which can be used to
cross check compass error in flight, this requirement may be varied subject to
approval by the CAA.

31 August 2006 Part 14 Leaflet 14-19 Page 2

CAP 562 Civil Aircraft Airworthiness Information and Procedures

8 CVR/FDR

Where required by the ANO as amended, or JAR–OPS as appropriate.

8.1 Maintain in accordance with the equipment manufacturer’s recommendations. In the
absence of any specific recommendation the CAA should be contacted for guidance
related to the specific installation.
8.2 The Operator shall in all cases comply with the requirements of the ANO 2005 (as
amended), Article 62(2)(b) by providing a data record for retention purposes every 12
months.

9 Battery Capacity Check

Routine capacity checks should be carried out in accordance with manufacturer’s

instructions and periods where specified; or the following periods shall apply.
Lead acid Battery – 3 months.
Ni-Cad Battery – 4 months.

10 Safety Equipment

Where the aircraft is required to carry safety equipment this should be checked for
serviceability at regular intervals. Overhaul and retirement periods are those specified
by the equipment manufacturer.

11 Modifications to Aircraft

11.1 Where equipment has been fitted to the aircraft after original manufacture, e.g.
autopilots, flight directors etc., the Supplementary Maintenance Appendix A, is
required to be amended to take into account the equipment manufacturer’s
requirements.
11.2 Where the aircraft structure has been modified from the original design standard, this
must be taken into account when assessing the maintenance requirements.

12 Fatigue Lives and Mandatory Life Limitations (Including Engines)

All fatigue lives and mandatory life limits published by the manufacturer or by the CAA
shall be complied with. In the case of foreign products, the CAA may vary the lives
published by the manufacturer or itself publish a life, normally as a CAA Additional
Airworthiness Directive.

13 Corrosion of Aircraft Structures

Where the manufacturer makes no specific reference to corrosion control

programmes, this should be taken into account when inspecting for condition. The
assessment may require adjustment of maintenance programme periods. The
application of corrosion inhibitors during maintenance may significantly improve the
durability of the airframe.

31 August 2006 Part 14 Leaflet 14-19 Page 3

CAP 562 Civil Aircraft Airworthiness Information and Procedures

14 Supplementary Maintenance Appendix

The attached Supplementary Maintenance Appendix A, should contain the equipment

manufacturer’s maintenance requirements, a list of reference material including
equipment manuals, service bulletins (SB), STCs, modifications etc. and any life
limitations.
The attached Supplementary Maintenance Appendix B, should contain Maintenance
Tasks arising from SBs, SLs, and other service information as required by the
operator.

15 Certification of Maintenance

15.1 The certificate of release to service for checks carried out in accordance with the
manufacturer’s programme, should cross refer to the CAA Maintenance Schedule
Approval reference number.
15.2 An annual review of the maintenance shall be completed. The review shall as a
minimum, include the following items:

1. Confirmation of mandatory modification, ADs and inspection status.

2. Audit of aircraft records.
3. Conformity with CAA approved maintenance schedule.
4. Conformity with CAA approved aircraft radio installation (AC968NR).
5. Review of outstanding deferred defects.
6. Evaluate the effectiveness of the maintenance schedule in addressing the
maintenance needs of the aircraft.
7. Review of aircraft and equipment life limits.

15.3 On successful completion of the annual review the following statement shall be made
in the Aircraft Log Book.
Annual review carried out in accordance with:
CAA APPROVED MAINTENANCE SCHEDULE REF: _____________________________
Signed: _____________________________ Approved Organisation Ref:___________
This certification shall be made in accordance with the requirements of the AD271,
Schedule Approval Document.

16 Permitted Variations to Maintenance Periods

The periods prescribed by the manufacturer may be varied subject to the conditions
and limits contained in Appendix C to this SMP.

17 Inspection Standards

17.1 Unless otherwise stated, all inspection requirements are to be applied without
removing an item from the aircraft or dismantling the item, group or sub-assembly

22 June 1998 Part 14 Leaflet 14-19 Page 4

CAP 562 Civil Aircraft Airworthiness Information and Procedures

unless dismantling is considered essential in order to ensure airworthiness. Where

dismantling is required by this Schedule, this is stated against the item concerned.
17.2 All significant terms and abbreviations used within this Programme to define each
maintenance task are defined in accordance with the Type Certificate holder’s
definitions, current JAR, CAA BCAR definitions or, in the absence of formal
definitions, those quoted in World Airlines Technical Operations Glossary.
17.3 The inspection standards applied to individual task inspections must meet the
requirements of the Type Certificate holder’s recommended standards and practices.
In the absence of specific manufacturers guidance, refer to CAA CAP 562 Civil Aircraft
Airworthiness Information and Procedures or FAA AC 43–13–1A Aircraft Inspection
and Repair or other approved data, as appropriate.

22 June 1998 Part 14 Leaflet 14-19 Page 5

 Supplementary Appendix A
(Equipment Manufacturer’s Maintenance Requirements, Life Limits not covered by the Manufacturer’s Maintenance
CAP 562

Programme as set out in SMP19 paragraph 2)

22 June 1998
DATE
SYSTEM DETAIL REFERENCE INFORMATION
ENTERED

Signature of person submitting page CAA Approval and Date

..................................................... .........................................

Part 14 Leaflet 14-19 Page 6

Civil Aircraft Airworthiness Information and Procedures
 Supplementary Appendix B
(Additional Maintenance Required by the Operator in the form of SBs, SLs and other Service Information)
CAP 562

22 June 1998
DATE
SYSTEM DETAIL REFERENCE INFORMATION
ENTERED

Signature of person submitting page

..................................................... .........................................

Part 14 Leaflet 14-19 Page 7

Civil Aircraft Airworthiness Information and Procedures
CAP 562 Civil Aircraft Airworthiness Information and Procedures

Supplementary Appendix C

Permitted Variations to Maintenance Periods

1 The operator or their contracted Maintenance Organisation, may vary the periods
prescribed by this Schedule provided that such variations are not included in the
manufacturer’s programme within the limits of sub-paragraphs 3 a) to d) of this
Appendix C.

2 Variations shall be permitted only when the periods prescribed by the manufacturer
cannot be complied with due to circumstances which could not reasonably have been
foreseen by the Operator or by the contracted Maintenance Organisation.

3 The decision to vary any of the prescribed periods with the exception of the Annual
Maintenance Review shall be taken only by the Chief Inspector/Quality Manager or
person of equivalent status acceptable as a signatory for the prescribed check, on
behalf of the Operator or the contracted Maintenance Organisation. Particulars of
every variation so made shall be entered in the appropriate Log Book(s).

a) Items Controlled by Flying Hours

Period Involved Maximum Variation of the Prescribed Period

(i) 5000 flying hours or less 10%

(ii) More than 5000 flying hours 500 flying hours

b) Items Controlled by Calendar Time

Period Involved Maximum Variation of the Prescribed Period

(i) 1 year or less 10% or 1 month, whichever is the lesser

(ii) More than 1 year but not 2 months
exceeding 3 years
(iii) More than 3 years 3 months

c) Items Controlled by Landing/Cycles

Period Involved Maximum Variation of the Prescribed Period

(i) 500 landings/cycles or less 10% or 25 landings/cycles, whichever is the

lesser
(ii) More than 500 landings/ 10% or 50 landings/cycles, whichever is the
cycles lesser

22 June 1998 Part 14 Leaflet 14-19 Page 8

CAP 562 Civil Aircraft Airworthiness Information and Procedures

d) Items Controlled by More Than One Limit. For items controlled by more than
one limit, e.g. items controlled by flying hours and calendar time or flying hours and
landings/cycles, the more restricted limit shall be applied.

NOTES: 1) CAP 747 - Mandatory Requirements for Airworthiness may override these
conditions .

2) The variations permitted do not apply to:

Those components for which an ultimate (scrap) or retirement life has been
prescribed (e.g. primary structure or components with limited fatigue lives
and high energy rotating parts of which containment is not provided).
Details concerning all items of this nature are included in the manufacturer’s
documents or manuals.

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CAP 562 Civil Aircraft Airworthiness Information and Procedures

Part 15 Maintenance Personnel Licensing

Leaflet 15-1 Aircraft Maintenance Engineers Licensing –

General Licensing Information

(Previously issued as AN 46)

1 General

1.1 Dates and venues of written examinations are shown in Appendix 1 of this Leaflet
which is correct at the time of publication. This and other detailed information on
licensing are published on the Personnel Licensing area of the CAA web site
www.srg.caa.co.uk. This site is updated frequently and engineers preparing to apply
for exams or licence issue/extension are strongly advised to view it for current
information on policy, procedures or exam schedules. Application forms may also be
downloaded from the site.
1.2 Additional information relating to Part-66 and the cessation of BCAR Section L has
been added to the Engineering Licensing part of the Personnel Licensing web site.
1.3 Following the UK CAA introduction of the Part-66 licence, the majority of BCAR
Section L licences require conversion by 28 September 2008 for certification on
aircraft of 5700 kg and below.
For information on conversion visit www.caa.co.uk/srg/licensing and then click on
engineer licensing and then 'making your application for Part-66'.
Existing JAR-66 licenses do not require conversion. If you do not convert your
BCAR Section L licence you will not be able to continue to issue a CRS after the
date above.
1.4 Upon conversion of a BCAR licence to a Part-66 licence, where protected rights do
not convert to a full Part-66 category or sub-category licence, limitations will be
applied. Part-66 limitations may be removed by completing the appropriate
conversion examinations, either before or after the conversion (refer to Section B of
the ELGD at www.caa.co.uk/ELGD).

2 EASA Commission Regulation (EC) No. 2042/2003 Including

Implementing Rules (IR) Part-66 and Part-147

2.1 The European Aviation Safety Agency (EASA) has commenced operations introducing
phased changes in respect of the licensing of aircraft maintenance engineers.
2.2 The UK CAA issued the first EASA Part-66 licence for aircraft above 5700 kg MTOM
on 1 June 2004 and the first EASA Part-66 licence to include aircraft above and below
5700 kg MTOM on 29 November 2004.
2.3 The holder of a JAR-66 AML will be deemed to be compliant with this Part and
certification privileges held under JAR-66 may continue to be exercised. Existing
JAR-66 licences held will be automatically converted to Part-66 licences at the next
licensing event. It is not necessary for existing JAR-66 licence holders to convert their
licence to Part-66.

31 March 2009 Part 15 Leaflet 15-1 Page 1

CAP 562 Civil Aircraft Airworthiness Information and Procedures

2.4 Part 145.A.30 (g), Part 145.A.30 (h)(1) and Part 145.A.30 (h)(2) will be implemented by
28 September 2008. Line maintenance certifying staff on aircraft below 5700 kg
MTOM, base maintenance certifying staff and B1, B2 support staff for multi engine
helicopters at or below 5700 kg MTOM and base maintenance certifying staff and B1,
B2 support staff for aircraft at or below 5700 kg MTOM are to be Part-66 qualified by
this date.
2.5 Maintenance certification for some aircraft categories e.g. Annex II aircraft and
airships will continue for the time being to be regulated by the UK CAA under National
Requirements of BCAR Section L.
NOTE: Annex II and State aircraft are aircraft that are not included under EC Regulation
216/2008 and therefore Part-145 and Part-M do not apply.

3 BCAR Section L Licence Renewal

3.1 EASA Part-66 licences now include aircraft both above and below 5700 kg. The CAA,
therefore, recommends that remaining BCAR Section L licence holders convert to
Part-66 without delay, even if the licence is not due for renewal. The appropriate
Form 19 (SRG1014) and Support Document (SRG/1020) can be downloaded from our
web site.
3.2 Applicants may still renew their BCAR Section L licences where a need can be
shown, e.g. for Annex II type aircraft ratings or airships.

4 The Engineers Licensing Guidance Document

4.1 The latest version of this document and all applicable updates are available on our
website www.caa.co.uk/ELGD.
4.2 The ELGD was designed to assist Aircraft Maintenance Engineers and those involved
with aircraft maintenance engineering by providing guidance on existing Aircraft
Maintenance Engineering licensing requirements.

5 Assessor Training Workshops

5.1 The workshop is designed for assessors, referees and quality personnel, primarily to
provide first-hand guidance in their role of supporting aircraft maintenance engineers
making application for licence issue and/or type ratings.
5.2 These individuals may be working within approved maintenance organisations, being
employed by, or in the case of the assessor nominated by, their organisation.
Assessors working independently within industry are directly approved by the UK
CAA as logbook assessors by submitting CAA Form SRG/1016 available at
www.caa.co.uk/SRG1016.
5.3 Depending on the individual’s role within industry, their responsibilities could include
assisting engineers to complete their logbooks, conducting practical experience
assessment following type training, or completion of application forms for both initial
licence issue and/or type ratings.
5.4 The training provides focused guidance for those individuals involved in the majority
of activities associated with licence applications, including the logbook validator,
logbook assessor and quality personnel, either new to the role of supporting
applications for a Part-66 licence or personnel requiring refreshment.

31 March 2009 Part 15 Leaflet 15-1 Page 2

CAP 562 Civil Aircraft Airworthiness Information and Procedures

5.5 The training covers:

• Part-66 licensing requirements;
• BCAR Section L and Part-66/-145/-147 interface issues;
• The AME’s Logbook;
• Practical experience assessment criteria;
• Application forms including supporting documentation;
• Protected Rights;
• Type ratings and removal of limitations.

6 Examination Venues and Dates

A list of written examination dates and venues is given in Appendix 1 to this Leaflet.

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CAP 562 Civil Aircraft Airworthiness Information and Procedures

Appendix 1 Engineer Licensing Examination Dates for 2009

All Engineer Licensing written examinations are held at the main Personnel Licensing
Department examination venues at Gatwick, Oxford, Manchester Britannia Airport Hotel,
Glasgow and Shuttleworth College. The venues can seat, in total, a minimum of 500
candidates per month. Venue details will be sent with each examination confirmation.
Arrangements for oral examinations remain unchanged and are conducted at the Regional
Offices.

Manchester
Shuttleworth
Gatwick Oxford Britannia Glasgow
College
Date Airport Hotel

April 09 14 14 14 14 14

May 09 11 11 11 8 11

June 09 5 5 5 8 5

July 09 10 10 10 10 10

Aug 09 7 7 7 7 7

Sept 09 11 11 11 11 11

Oct 09 9 9 9 9 9

Nov 09 6 6 6 6 6

Dec 09 11 11 11 11 11

Please note that published examination dates may be subject to alteration or cancellation.
The time between the closing date for applications and the examination sitting is two weeks.
Personnel Licensing Department will aim to send booking confirmations, venue details and
examination timetables to reach candidates within 2 days of the booking and in any case at
least 1 week prior to the sitting.
Bookings close ten clear working days prior to the examination date. However, exams at
Gatwick, Oxford and Manchester are usually fully booked 3-4 months in advance.
Please do not make any travel arrangements until your booking is confirmed in writing.

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CAP 562 Civil Aircraft Airworthiness Information and Procedures

Leaflet 15-2 Licensed Aircraft Maintenance Personnel –

Certification Responsibilities of Type
Rated/Authorised Personnel

(Previously issued as AN 3)

NOTE: This previously published information has not been amended at this time though it
should be noted that, due to the licensing requirements that will be in force after
September 2008, the UK CAA national licence and all supporting documentation will
undergo significant change at that time. Further information will be available on the
CAA website at www.caa.co.uk/pldwhatsnew from June 2008.
This Leaflet will be updated at the next amendment to include any new information
regarding future changes.

1 General The purpose of this Leaflet is to describe the certification responsibilities

of UK Licensed Aircraft Maintenance Personnel. Such personnel may be the holder of
an Aircraft Maintenance Engineer's Licence issued under BCAR Section L or an
Aircraft Maintenance Licence issued under Part-66 (a JAR-66 aircraft maintenance
licence is considered to be a Part-66 licence under Commission Regulation (EC) No.
2042/2003). The responsibilities apply when issuing certifications either as a Type
Rated Licence holder or as an engineer holding a certification authorisation. It also
describes the privileges of the various Type Rated Licences.
It should be noted that where the holder of a licence is performing maintenance
activities on an aircraft on which he or she is not appropriately licensed, i.e. acting as
a non-certifying engineer, they are still expected to act responsibly and carry out such
work in accordance with the procedures and standards identified in the following
paragraphs.
A National licence issued by the United Kingdom CAA does not confer any
certification privileges with respect to aircraft which are not registered in the United
Kingdom unless the licence holder is entitled to certify for such activities by way of
having the licence validated by the relevant Airworthiness Authority and/or is
authorised by a maintenance organisation approved by that Authority.
NOTES: 1) A BCAR Section L Licence Without Type Rating or a Part-66 Aircraft Maintenance
Licence does not confer any certification privileges on the holder in their own
right (except for that allowed under Part M.A.801(d)2). Such licences must be
used in conjunction with a certification authorisation.
2) In the context of this Leaflet, reference to an authorisation means an
authorisation issued by an EASA or a CAA Approved Maintenance Organisation
(under the requirements of BCARs or Part-145 or Part-M) to allow the holder to
issue certifications within the limitations shown on the authorisation.
3) As of 28 September 2008 certification of maintenance on non-commercial
transport aircraft using a Part-66 licence as authority is limited to items which are
not included in the list at Part-M Appendix VII.
1.1 a) The Certificate referred to under Article 14 of the Air Navigation Order 2005 (as
amended) is a Certificate of Maintenance Review to be issued following
completion of the review required by the Order. The Certificate referred to under
Article 16 of the Air Navigation Order 2005 (as amended) is a Certificate of Release
to Service to be issued on completion of maintenance of aircraft or components
not required to be maintained under Part-145 or Part-M.

31 March 2009 Part 15 Leaflet 15-2 Page 1

CAP 562 Civil Aircraft Airworthiness Information and Procedures

b) The Certificate referred to in Part-145, paragraph 145.A.50 is a Certificate of

Release to Service to be issued on completion of maintenance of aircraft or
components which are required to be maintained under the provisions of Part-145.
c) The certificate referred to in Part-M.A.801 is a Certificate of Release to Service to
be issued on completion of maintenance of aircraft or components which are
required to be maintained under the provisions of Part-M.
1.2 In connection with the issue of Certificates of Release to Service, the following
definitions apply:
a) Maintenance means any one or combination of overhaul, repair, inspection,
replacement, modification or defect rectification of an aircraft/aircraft component.
Regulation (EC) No. 2042/2003 extends this definition to include 'with the
exception of pre-flight inspection'.
b) Overhaul means the restoration of an aircraft/aircraft component by inspection
and replacement in conformity with an approved standard to extend the
operational life.
c) Repair means the restoration of an aircraft/aircraft component to a serviceable
condition in conformity with an approved standard.
d) Inspection means the examination of an aircraft/aircraft component to establish
conformity with an approved specification.
e) Replacement is any work operation which involves the removal and replacement
of the same part or the substitution of an approved alternative part.
f) Modification means the alteration of an aircraft/aircraft component in conformity
with an approved standard.
NOTES: 1) Defect rectification normally consists of an element of inspection and
troubleshooting followed by repair and replacement of the defective item.
2) Inspection includes:
i) Mandatory Inspection, an inspection made Mandatory by EASA, where the
inspection itself is the work (see CAP 747).
ii) Scheduled Maintenance Inspection, an inspection or maintenance including
tests required by the Approved Maintenance Schedule or Programme.

1.3 Although many terms in common usage describe the various aspects of aircraft
engineering, the meanings assigned to such terms are not always the same. For the
purpose of this Leaflet, in relation to airworthiness, the following definitions apply:
a) Condition – the physical state of an item.
b) Assembly – that items are fitted, assembled, attached, installed, connected,
secured or adjusted in the approved manner.
c) Functioning – operation in the approved manner achieving such performance,
range of movement and freedom of movement as may be specified.
The certifying engineer shall be responsible for the condition, assembly and
functioning of the aircraft or its components for maintenance that has been certified
under the privileges of a Type Rated Licence or an authorisation.
1.4 The certifying engineer shall be responsible for ensuring that work is performed and
recorded in a satisfactory manner taking into account the following:
a) Whenever work is carried out on an aircraft, it is the duty of all persons to whom
this Leaflet applies to ensure that the work, for which they are responsible,

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CAP 562 Civil Aircraft Airworthiness Information and Procedures

progresses in a managed and controlled manner. Where they are supported by

additional staff to carry out the work, consideration shall be given by them before
starting the work to the manpower resource available and the abilities of the staff
concerned. This is to ensure that the certifying engineer determines and exercises
an adequate degree of supervision over such staff.
b) In relation to work carried out on an aircraft, it is the duty of all persons to whom
this Leaflet applies to ensure that an adequate record of the work carried out is
maintained. This is particularly important where such work carries on beyond a
working period or shift, or is handed over from one person to another. The work
accomplished, particularly if only disassembly or disturbance of components or
aircraft systems, should be recorded as the work progresses or prior to
undertaking a disassociated task. In any event, records should be completed no
later than the end of the work period or shift of the individual undertaking the work.
Such records should include open entries to reflect the remaining actions
necessary to restore the aircraft to a serviceable condition prior to release. In the
case of complex tasks which are undertaken frequently, consideration should be
given to the use of pre-planned stage sheets to assist in the control, management
and recording of these tasks. Where such sheets are used, care must be taken to
ensure that they accurately reflect the current requirements and
recommendations of the manufacturer and that all key stages, inspections, or
replacements are recorded.
c) It is also the duty of all persons to whom this Leaflet applies to consider the effect
such work may have, directly or indirectly, on items which are the responsibility of
other such persons. In all cases where an overlap of responsibility between licence
categories occurs, the person primarily responsible for the item must involve all
other trade disciplines affected. Every person to whom this Leaflet applies must
therefore be conversant with all other relevant paragraphs of this Leaflet.
Certificates of Release to Service for each relevant trade category must be issued
by all persons concerned, each assuming responsibility of and certifying those
aspects of the work for which the licence/authorisation holder is entitled to
assume responsibility.
1.5 A Certificate of Release to Service shall only be issued on completion of maintenance
when the signatory is (signatories are) satisfied that the work has been properly
carried out and accurately recorded, having due regard to the use of:
a) up-to-date instructions and maintenance data (including manuals, drawings,
specifications, EASA Airworthiness Directives and Mandatory Requirements listed
in CAP 747, and, where applicable, company procedures);
b) recommended tooling and test equipment which is currently calibrated where
applicable;
c) a working environment appropriate to the work being carried out.
When issuing a Certificate of Release to Service for work performed by others, the
certifying engineer assumes responsibility. The certifying engineer must have
inspected a sufficiently representative sample of the work and the associated
documentation, and be satisfied with the competence of the persons who have
performed the work. For complex tasks this may require progressive inspections to
be carried out as the work proceeds. In the case of an aircraft or component where
welding a metallic part is considered essential to airworthiness, it is the responsibility
of the certifying engineer to establish that the welder is approved in accordance with
the requirements in BCAR Section A sub-section A8 for aircraft maintained under
national requirements.

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CAP 562 Civil Aircraft Airworthiness Information and Procedures

For aircraft maintained under Part-M Subpart F or Part-145 it is the responsibility of

the organisation to establish and control competencies in accordance with EC
Regulation 2042/2003.
NOTE: Licensed engineers certifying under the privileges of their licence may not deviate
from the manufacturer’s maintenance instruction or maintenance data, nor use
alternative parts, components or assemblies unless such deviation is supported by
the written agreement of the manufacturer, approved as a change or agreed by the
CAA. The local CAA Regional Office should be consulted in cases of difficulty.
Authorised engineers shall comply with all company procedures covering such
issues.
1.6 a) When the work involves the assembly or any disturbance of a vital point defined in
BCAR Section A, Chapter A5-3 or control system, the duplicate inspection required
must be completed and certified in accordance with BCAR Section A/B Chapter
A/B6-2 before the relevant Certificate of Release to Service is issued.
b) Part-M.A.402(a) requires that an independent inspection shall be carried out after
any flight safety sensitive maintenance task unless otherwise specified by
Part-145 or agreed by the competent authority.
c) The holder of a Type Rated Licence in Category 'A' and/or 'C' or Part-66 Category
B1 may make certification on aircraft (or their engines, as appropriate) below
5700 kg MTOM for Duplicate Inspections of minor adjustments to control systems
on other types within the Category in which the licence is type rated.
NOTE: A minor adjustment is considered to be a single point adjustment or reassembly of
a control.
1.7 The holder of an appropriately Type Rated BCAR Section L Aircraft Maintenance
Engineer’s Licence in Categories 'A', 'B', 'C' or 'D', or the holder of an aircraft Type
Authorisation equivalent to Section L Categories 'A' and/or 'C' or Part-66 Category B1,
may issue a Certificate of Release to Service to cover Non Destructive Inspections on
aircraft or components, within the privileges of the licence or authorisation held,
subject to the work being carried out as follows:
a) Inspection requiring the use of Field Kit for the Colour Contrast Dye Penetrant
technique may be carried out by persons either Type Rated or Type Authorised as
above or persons qualified in accordance with Generic Requirement (GR) No. 23 in
CAP 747.
b) Non Destructive Inspections requiring any other technique, including Fluorescent
Penetrant Dye, shall be carried out and signed for by persons appropriately
qualified in accordance with Generic Requirement (GR) No. 23 in CAP 747 prior to
the issue of the CRS by a licensed or authorised engineer.
1.8 Use of either a Type Rated Licence or an authorisation to issue a certification requires
that, in addition to the Licence or Authorisation being valid at the time of certification,
the holder has been engaged for periods totalling at least 6 months during the 24
months preceding the date of the certification on work affording experience
comparable with that required for the grant of the Licence/Authorisation.
1.9 A Type Rated Licensed Engineer may issue the Certificates identified below in
relation to aircraft for which the licence is Type Rated and in accordance with the
privileges detailed in the remaining paragraphs to this Leaflet. An authorised engineer
may only issue these certificates as permitted within the limits of the authorisation.
a) Certificate of Release to Service for aircraft not required to be maintained under
Part-M Subpart F or Part-145 – the holder of an appropriately Type Rated Licence
may issue Certificates of Release to Service subject to compliance with the
requirements of BCAR Section A/B, Chapter A/B6-2 and A/B6-7.

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CAP 562 Civil Aircraft Airworthiness Information and Procedures

b) Certificate of Maintenance Review – the holder of an appropriately Type Rated

Licence in at least two Categories (other than Category ’X’ Compasses) may issue
a Certificate of Maintenance Review subject to compliance with the requirements
of BCAR Section A/B, Chapter A/B6-2 and A/B6-7 and the Maintenance Schedule
Approval Document.
c) Certificates of Fitness for Flight – the holder of an appropriately Type Rated
Licence may issue Certificates of Fitness for Flight subject to compliance with the
requirements of BCAR Section A/B, Chapter A/B3-8.
d) Flight Release certificate - for aircraft not required to be maintained under Part-145.
The holder of a valid and appropriately type rated aircraft maintenance engineer's
licence granted under BCAR Section L or the holder of a Part-66 licence
appropriately endorsed for the aircraft type rendered valid in the United Kingdom,
may issue a Flight Release certificate under the terms of an EASA Permit to Fly.
1.10 The following licence categories may be used to allow the grant of an authorisation
within a Maintenance Organisation approved in accordance with EASA or CAA
requirements:
• A BCAR Section L LWTR (Licence Without Type Rating) providing that the
authorisation issued is within the scope of the licence held at 1st June 2001.
Applicable to aircraft of MTOM less than 5700 kg only.
• A BCAR Section L LWTR extended with the appropriate Type Rating. Applicable to
aircraft of MTOM less than 5700 kg only.
• A Part-66 Category A licence providing that the authorisation issued is in
compliance with AMC 145.A.30(g).
• A Part-66 Category B licence providing that the licence has been extended with the
appropriate type rating. No authorisation permitted against the basic Part-66
licence.
• A Part-66 Category C licence providing that the licence has been extended with the
appropriate type rating. No authorisation permitted against the basic Part-66
licence.
In addition to the foregoing paragraphs, when working within such Organisations, the
licensed engineer should be aware that he/she is part of a comprehensive
maintenance system. It is therefore important to realise that company procedures
may further define, or require specific actions, as to how certain issues are to be dealt
with and these procedures must be adhered to. It is also important to realise that
when working within an approved Maintenance Organisation and certifying under the
privileges of an authorisation the licensed engineer is not certifying under the
privileges of the licence.
NOTE: UK licence holders may work for and therefore be authorised to certify by
Maintenance Organisations which are not CAA approved. In such cases, validation
of a UK issued BCAR Section L licence or Part-66 licence may be required. In
addition, the holder of a licence may be required to satisfy specific company
requirements for authorisation. Such requirements may also introduce additional
National legislation and working practices which the licence holder should note and
comply with. Whilst certifying under such authorisations and in the absence of
specific guidance the principles and practices promulgated in this Leaflet should be
adhered to.

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CAP 562 Civil Aircraft Airworthiness Information and Procedures

2 BCAR Section L Aircraft Maintenance Engineer’s Licence – Type Rated in

Category 'A' – Aeroplanes

NOTES: 1) With the exception of certification of aircraft excluded from the requirements of
EC Regulation 216/2008 (Annex II and state aircraft as defined in article 1(2)
thereof), all persons issuing Certificates of Release to Service on aircraft below
5700 kg must comply with the provisions of EC Regulation 2042/2003 Article 7(d)
by way of derogation until 28 September 2008. For information on conversion
requirements refer to the ELGD booklet or visit our website at
www.srg.caa.co.uk
2) This paragraph must be read in conjunction with paragraph 1 of this Leaflet.
2.1 The holder of a BCAR Section L Category 'A' licence may issue Certificates of Release
to Service in respect of maintenance in relation to non-commercial air transport
aeroplanes (but not including engines) for which the licence is Type Rated.
2.2 In connection with the certification of maintenance the holder of a Type Rated
Licence in Category 'A' is responsible for all parts of the aeroplane subject to the
limitations detailed below (excluding those parts which are the responsibility of the
holder of a Type Rated Licence in Category 'C').
2.3 The holder of a Type Rated Licence in Category 'A' may issue Certificates of Release
to Service relating to maintenance (excluding overhaul) of parts of the aeroplane for
which the holder is responsible, providing that the work has not involved any of the
following:
a) Bolted joints requiring special techniques;
b) Complete riveted joints in primary structures;
c) Complete glued joints in primary structures;
d) Bonded assemblies in primary structures;
e) Composite material primary structures;
f) Welded and brazed joints, other than minor weld repairs carried out by an
Approved Welder, but excluding replacement of structural members or repairs to
flying control components;
g) Cotton, linen, polyester and glass fibre fabric covering of a complete fuselage or
aerofoil;
h) The disturbing of individual parts of units which are supplied as bench tested units,
except for the replacement or adjustment of items normally replaceable or
adjustable in service.
2.4 In connection with the maintenance of instrument, electrical, automatic pilot and radio
systems installed in aeroplanes (excluding overhaul or such systems as are
associated with the engine(s) and auxiliary power unit(s)) the holder of a Type Rated
Licence in Category 'A' is entitled to issue Certificates of Release to Service for
aircraft for which he holds a Type Rating, subject to the limitations detailed in sub-
paragraphs 2.4.1, 2.4.2, 2.4.3, 2.4.4 and 2.4.5.
NOTE: Where no limitations are shown, Certificates of Release to Service may be issued
for repair, replacement, modification, mandatory inspection or scheduled
maintenance inspection. In respect of the certification of scheduled maintenance
inspections, reference should also be made to the Maintenance Schedule Approval
Document which may require certification specifically by an engineer licensed in the
appropriate 'X' or 'R' Category. However, in the absence of such a requirement, the
holder of a Type Rated Licence in Category 'A' Aeroplanes assumes the
responsibility for establishing compliance with the maintenance schedule
requirements on the systems before issuing the Certificate of Release to Service.

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CAP 562 Civil Aircraft Airworthiness Information and Procedures

2.4.1 In respect of instrument systems in the aeroplane (excluding instrument systems

associated with the engine(s) and auxiliary power unit(s)):
a) If the aeroplane has an instrument system specified in sub-paragraph 8.1 of
CAP 562 Leaflet 15-3, Certificates of Release to Service may be issued.
b) If the aeroplane has an instrument system specified in sub-paragraphs 8.2 to 8.4
inclusive of CAP 562 Leaflet 15-3, Certificates of Release to Service may be issued
relating to replacements only, provided that functioning checks to prove
serviceability do not require the use of test apparatus.
c) If the aeroplane is specified in paragraph 10 of CAP 562 Leaflet 15-3, Certificates
of Release to Service may not be issued.
2.4.2 In respect of electrical systems in the aeroplane (excluding electrical systems
associated with the engine(s) and auxiliary power unit(s)):
a) If the aeroplane has an electrical system specified in sub-paragraph 9.1 of CAP 562
Leaflet 15-3, Certificates of Release to Service may be issued.
b) If the aeroplane has an electrical system specified in sub-paragraphs 9.2 to 9.4
inclusive of CAP 562 Leaflet 15-3, Certificates of Release to Service may be issued
relating to replacements only, provided that functioning checks to prove
serviceability do not require the use of test apparatus.
c) If the aeroplane is specified in paragraph 10 of CAP 562 Leaflet 15-3, Certificates
of Release to Service may not be issued.
2.4.3 In respect of automatic pilot systems in the aeroplane:
a) If the aeroplane has an automatic pilot system specified in sub-paragraph 13.1 of
CAP 562 Leaflet 15-3 installed, Certificates of Release to Service may be issued.
b) If the aeroplane has an automatic pilot system specified in sub-paragraph 13.2 of
CAP 562 Leaflet 15-3 installed, Certificates of Release to Service may be issued
relating to replacements only, provided that functioning checks to prove
serviceability do not require the use of test apparatus.
c) If the aeroplane has an automatic pilot system as specified in sub-paragraph 13.3
or the aeroplane is specified in paragraph 10 of CAP 562 Leaflet 15-3, Certificates
of Release to Service may not be issued.
2.4.4 Certificates of Release to Service may not be issued in respect of radio systems,
except that if the aeroplane has a MTOM not exceeding 2730 kg, certificates may be
issued in respect of the replacement of VHF communication equipment only.
2.4.5 Certificates of Release to Service may not be issued in respect of compass
compensation and adjustment unless the licence is endorsed to that effect.

3 BCAR Section L Aircraft Maintenance Engineer’s Licence – Type Rated in

Category 'B' – Aeroplanes or Rotorcraft

NOTE: This paragraph must be read in conjunction with paragraph 1 of this Leaflet.
3.1 The holder of a Section L Category ‘B’ licence may issue Certificates of Release to
Service in respect of overhaul, repair, replacement, modification and mandatory
inspection in relation to non-commercial air transport aeroplanes or rotorcraft (but not
including engines) for which the licence is Type Rated, subject to the limitations of
sub-paragraphs 3.2 and 3.3.

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CAP 562 Civil Aircraft Airworthiness Information and Procedures

3.2 Category 'B' – Aeroplanes

3.2.1 In connection with the certification of overhaul, repair, replacement, modification and
mandatory inspection, the holder of a Type Rated Licence in Category 'B' –
Aeroplanes is responsible for all parts of the aeroplane (provided that the work does
not involve the manufacturing of components or parts) excluding those parts which
are the responsibility of the holder of a Type Rated Licence in Category 'C' or 'D' and
subject to the same limitations as detailed in sub-paragraph 2.4 for Category 'A' and
excluding the overhaul of electrical, instrument or automatic pilot systems.
3.2.2 Notwithstanding the above, the holder of a Type Rated Licence in Category 'B' may
also issue Certificates of Release to Service relating to all aspects of overhaul, repair,
replacement, modification and mandatory inspection relating to items listed as a) to
e) below, except for those parts which form part of or are attached to the engine,
provided that the work does not involve the making of components or parts.
a) Engine mounting structures and cowlings;
b) Engine controls;
c) Engine fuel, oil and coolant systems;
d) Engine fire extinguishing systems;
e) Engine fluid de-icing systems.
3.3 Category 'B' – Rotorcraft
3.3.1 In connection with the certification of overhaul, repair, replacement, modification and
mandatory inspection the holder of a Type Rated Licence in Category ‘B’ – Rotorcraft
is responsible for all parts of the rotorcraft (provided that the work does not involve
the making of components or parts) excluding those parts which are the responsibility
of the holder of a Type Rated Licence in Category ‘D’ and subject to the same
limitations as detailed in sub-paragraph 6.5 for Category 'A' and 'C' Rotorcraft
excluding the overhaul of electrical, instrument, automatic pilot systems, main and tail
rotor blades.

4 BCAR Section L Aircraft Maintenance Engineer’s Licence – Type Rated in

Category 'C' – Engines

NOTE: This paragraph must be read in conjunction with paragraph 1 of this Leaflet.
4.1 The holder of a Section L Category 'C' licence may issue Certificates of Release to
Service in respect of maintenance in relation to non-commercial air transport engines
and auxiliary power units for which the licence is Type Rated.
4.2 In connection with the certification of maintenance (excluding overhaul) the holder of
a Type Rated Licence in Category 'C' is responsible for all parts of the engine(s), the
engine installation(s), auxiliary power unit(s), other propulsive device(s) and all
associated systems and devices which are concerned with their operation, subject to
the limitations detailed in sub-paragraphs 4.3, 4.4, 4.5 and 4.6 (excluding those parts
which are the responsibility of the holder of a Type Rated Licence in Category 'D').
4.3 The holder of a Type Rated Licence in Category 'C' may issue Certificates of Release
to Service relating to maintenance (excluding overhaul) of components or parts for
which the holder is responsible, providing that the work has not involved:
a) Dismantling of a piston engine other than to obtain access to the piston/cylinder
assemblies or the removal of the engine rear accessory cover to inspect and/or
replace oil pump assemblies where such work does not involve the removal and
refitment of internal gears;

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CAP 562 Civil Aircraft Airworthiness Information and Procedures

b) Dismantling of main casings or main rotating assemblies of a turbine engine,

except as detailed in sub-paragraph 4.4;
c) The removal or dismantling of reduction gears, except that, in the case of the BS
(DH) Gipsy Queen 70 engine, reduction gears may be removed for the purpose of
carrying out inspections after suspected shock loadings;
d) Propeller balancing, except for the certification of static balancing where required
by the maintenance manual and dynamic balancing on installed propellers using
electronic balancing equipment where permitted by the maintenance manual or
other approved airworthiness data. The work itself may have been carried out by
an LAE who has received suitable training on the balancing equipment to be used
and the associated procedures, or by an organisation approved for that purpose
and which has issued an Approved Test Certificate for the inspection;
e) Welded and brazed joints, other than minor weld repairs to exhaust units carried
out by an Approved Welder but excluding component replacement;
f) The disturbing of individual parts of units which are supplied as bench tested units,
except for the replacement or adjustment of items normally replaceable or
adjustable in service.
4.4 Where the maintenance manual for the particular engine provides instruction for the
task, replacement of main casings and/or rotating assemblies comprising the whole
or part of a particular rotating system will be permitted provided that removal from the
engine is achieved solely by disconnecting the flanges of main casings. In accordance
with the above principles, some engines have been assigned the following symbols,
~ or Ž in CAP 562 Leaflet 15-3. Dismantling of these engines is permissible, but is
limited to:
a) ~ – Removal/replacement of main casings, excluding those whose removal
results in concurrent removal of a rotating assembly from the engine. No
dismantling of main rotating assemblies is permitted.
b) Ž – Removal/replacement of main casings including those whose removal results
in concurrent removal of a rotating assembly from the engine, provided this is
accomplished solely by disconnecting at the casing flanges. No dismantling of
main rotating assemblies is permitted.
4.5 In connection with the maintenance of instrument, electrical and automatic pilot
systems installed in aeroplanes, the holder of a Type Rated Licence in Category 'C' is
entitled to issue Certificates of Release to Service in respect of such systems
associated with engine and auxiliary power unit installations for which the holder has
a Type Rating, subject to the limitations detailed in sub-paragraphs 4.5.1, 4.5.2 and
4.5.3.
NOTE: Where no limitations are shown, Certificates of Release to Service may be issued
for replacement, modification, repair, mandatory inspection or scheduled
maintenance inspection. In respect of the certification of scheduled maintenance
inspections reference should also be made to the Maintenance Schedule Approval
Document which may require certification specifically by an engineer licensed in the
appropriate ‘X’ Category. However, in the absence of such a requirement, the holder
of a Type Rated Licence in Category ‘C’ – Engines assumes the responsibility for
establishing compliance with the maintenance schedule requirements on the
systems before issuing the Certificate of Release to Service.
4.5.1 In respect of instrument systems associated with the engine(s) and auxiliary power
unit(s):

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CAP 562 Civil Aircraft Airworthiness Information and Procedures

a) If the engine is installed in an aeroplane which has an instrument system specified

in sub-paragraph 8.1 of CAP 562 Leaflet 15-3, Certificates of Release to Service
may be issued.
b) If the engine is installed in an aeroplane which has an instrument system specified
in sub-paragraphs 8.2 to 8.4 inclusive of CAP 562 Leaflet 15-3, Certificates of
Release to Service may be issued relating to replacements only, provided that
functioning checks to prove serviceability do not require the use of test apparatus.
c) If the engine is installed in an aeroplane specified in paragraph 10 of CAP 562
Leaflet 15-3, Certificates of Release to Service may not be issued.
4.5.2 In respect of electrical systems associated with the engine(s) and auxiliary power
unit(s):
a) If the engine is installed in an aeroplane which has an electrical system specified
in sub-paragraph 9.1 of CAP 562 Leaflet 15-3, Certificates of Release to Service
may be issued.
b) If the engine is installed in an aeroplane which has an electrical system specified
in sub-paragraphs 9.2 to 9.4 inclusive of CAP 562 Leaflet 15-3, Certificates of
Release to Service may be issued relating to replacements only, provided that
functioning checks to prove serviceability do not require the use of test apparatus.
c) If the engine is installed in an aeroplane specified in paragraph 10 of CAP 562
Leaflet 15-3, Certificates of Release to Service may not be issued.
4.5.3 In respect of automatic pilot systems associated with the engine(s):
a) If the aeroplane has an automatic pilot system specified in sub-paragraph 13.1 of
CAP 562 Leaflet 15-3 installed, Certificates of Release to Service may be issued.
b) If the aeroplane has an automatic pilot system specified in sub-paragraph 13.2 of
CAP 562 Leaflet 15-3 installed, Certificates of Release to Service may be issued
relating to replacements only, provided that functioning checks to prove
serviceability do not require the use of test apparatus.
c) If the aeroplane has an automatic pilot system as specified in sub-paragraph 13.3
or is specified in paragraph 10 of CAP 562 Leaflet 15-3, Certificates of Release to
Service may not be issued.

5 BCAR Section L Aircraft Maintenance Engineer’s Licence – Type Rated in

Category 'D' – Engines

NOTE: This paragraph must be read in conjunction with paragraph 1 of this Leaflet.
5.1 The holder of a Section L Category 'D' Licence may issue Certificates of Release to
Service in respect of non-commercial air transport engines for which the Licence is
Type Rated in respect of overhaul, repairs, replacements, modification and mandatory
inspection, subject to the limitations of sub-paragraphs 5.2 and 5.3.
5.2 In connection with overhaul, repair, replacement, modification and mandatory
inspection, the holder of a Type Rated Licence in Category 'D' is responsible for all
parts of the engine including functioning only insofar as test bed performance is
concerned. The certification of functioning insofar as an installed engine is concerned
must be made in conjunction with a holder of a Type Rated Licence in Category 'C'.
5.3 The holder of a Category 'D' Licence may issue Certificates of Release to Service
relating to all aspects of overhaul, repair, replacement, modification and mandatory
inspection of components and parts of the engine only (excluding overhaul, repair,

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CAP 562 Civil Aircraft Airworthiness Information and Procedures

replacement, modification and mandatory inspection of ignition apparatus, instrument

equipment and electrical equipment) provided that the work does not involve the
making of components or parts.
Commission Regulation (EC) 2042/2003 does not provide provision for aircraft
overhaul licences therefore; BCAR Section L category B and D licences do not
transfer to a Part-66 category B1 AML. The UK CAA is currently considering the
continuance and issue of National overhaul licences for certification purposes on
Commission Regulation (EC) 216/2008 Annex II aircraft types.
Although still under consideration, it is likely that new applicants for a National licence
for airframe overhaul work (BCAR Section L category B) will initially be required to
meet the criteria for a Part-66 AML.

6 BCAR Section L Aircraft Maintenance Engineer’s Licence – Type Rated in

Categories 'A' and 'C' – Rotorcraft

NOTES: 1) This paragraph must be read in conjunction with paragraph 1 of this Leaflet.
2) A Category 'A' and 'C' Rotorcraft Licence may not be used to certify for piston or
jet turbine engines installed in aeroplanes.
6.1 The holder of a Section L Categories 'A' and 'C' Rotorcraft Licence may issue
Certificates of Release to Service in respect of maintenance in relation to non-
commercial air transport rotorcraft and its engines for which the licence is Type
Rated.
6.2 In connection with the certification of maintenance the holder of a Type Rated
Licence in Categories 'A' and 'C' Rotorcraft is responsible for all parts of the rotorcraft
subject to the limitations detailed in sub-paragraphs 6.3, 6.4 and 6.5.
6.3 The holder of a Type Rated Licence in Category 'A' and 'C' Rotorcraft may issue
Certificates of Release to Service relating to maintenance (excluding overhaul) of
parts of the rotorcraft for which the holder is responsible, providing that the work has
not involved any of the following:
a) Bolted joints requiring special techniques;
b) Complete riveted joints in primary structures;
c) Complete glued joints in primary structures;
d) Bonded assemblies in primary structures;
e) Composite material primary structures;
f) Welded and brazed joints, other than minor weld repairs to aircraft structure or
exhaust units carried out by an Approved Welder but excluding structural or
component replacement;
g) Dismantling of a piston engine other than to obtain access to the piston/cylinder
assemblies or the removal of the engine rear accessory case cover to inspect
and/or replace oil pump assemblies where such work does not involve the removal
and refitment of internal gears;
h) Dismantling of main casings or main rotating assemblies of a turbine engine,
except as detailed in sub-paragraph 6.4;
i) Dismantling of gearbox casings, except that separation of casings to obtain access
for the purposes of internal inspections in accordance with the manufacturer’s
instruction is permitted;

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CAP 562 Civil Aircraft Airworthiness Information and Procedures

j) The disturbing of individual parts of units which are supplied as bench tested units,
except for the replacement or adjustment of items normally replaceable or
adjustable in service.
6.4 Where the maintenance manual for the particular engine provides instruction for the
task, replacement of main casings and/or rotating assemblies comprising the whole
or part of a particular rotating system will be permitted provided that removal from the
engine is achieved solely by disconnecting the flanges of main casings. In accordance
with the above principles, some engines have been assigned the following symbols,
~ or Ž in CAP 562 Leaflet 15-3. Dismantling of these engines is permissible, but is
limited to:
a) ~ – Removal/replacement of main casings, excluding those whose removal
results in concurrent removal of a rotating assembly from the engine. No
dismantling of main rotating assemblies is permitted.
b) Ž – Removal/replacement of main casings including those whose removal results
in concurrent removal of a rotating assembly from the engine, provided this is
accomplished solely by disconnecting at the casing flanges. No dismantling of
main rotating assemblies is permitted.
6.5 In connection with the maintenance of instrument, electrical, automatic pilot and radio
systems installed in rotorcraft (excluding overhaul) the holder of a Type Rated Licence
in Categories 'A' and 'C' Rotorcraft is entitled to issue Certificates of Release to
Service for rotorcraft for which he holds a Type Rating, subject to the limitations
detailed in sub-paragraphs 6.5.1, 6.5.2, 6.5.3 and 6.5.4.
NOTE: Where no limitations are shown, Certificates of Release to Service may be issued
for replacement, modification, repair, mandatory inspection or scheduled
maintenance inspection. In respect of the certification of scheduled maintenance
inspections, reference should also be made to the Maintenance Schedule Approval
Document which may require certification specifically by an engineer licensed in the
appropriate 'X' or ‘R’ Category. However, in the absence of such a requirement, the
holder of a Type Rated Licence in Categories 'A' and 'C' Rotorcraft assumes the
responsibility for establishing compliance with the maintenance schedule
requirements on the systems before issuing the Certificate of Release to Service.
6.5.1 In respect of instrument systems in the rotorcraft if the rotorcraft is specified in sub-
paragraph 7.4 of CAP 562 Leaflet 15-3, Certificates of Release to Service may be
issued relating to replacements only, provided that functioning checks to prove
serviceability do not require the use of test apparatus.
6.5.2 In respect of electrical systems in the rotorcraft, if the rotorcraft is specified in sub-
paragraph 7.4 of CAP 562 Leaflet 15-3, Certificates of Release to Service may be
issued relating to replacements only, provided that functioning checks to prove
serviceability do not require the use of test apparatus.
6.5.3 In respect of automatic pilot/automatic stabiliser systems in rotorcraft, if the rotorcraft
has an automatic pilot/automatic stabiliser system specified in sub-paragraph 13.4 or
13.5 of CAP 562 Leaflet 15-3 installed, Certificates of Release to Service may be
issued relating to replacements only, provided that functioning checks to prove
serviceability do not require the use of test apparatus.
6.5.4 Certificates of Release to Service may not be issued in respect of radio systems,
except that if the rotorcraft has a MTOM not exceeding 2730 kg, certificates may be
issued in respect of the replacement of VHF communication equipment only.

27 March 2008 Part 15 Leaflet 15-2 Page 12

CAP 562 Civil Aircraft Airworthiness Information and Procedures

7 BCAR Section L Aircraft Maintenance Engineer’s Licence – Type Rated in

Category 'X' – Instruments

NOTE: This paragraph must be read in conjunction with paragraph 1 of this Leaflet and
particular attention paid to sub-paragraphs 1.3, 1.4, 1.5 and 1.6 which are concerned
with areas of responsibility.
7.1 The holder of a Section L Category ‘X’ – Instruments Licence may issue Certificates
of Release to Service in respect of maintenance in relation to non-commercial air
transport aircraft instrument systems for which the licence is Type Rated, subject to
the limitations detailed in sub-paragraph 7.3.
7.2 In connection with the certification of maintenance, excluding overhaul, the holder of
a Type Rated Licence in Category ‘X’ – Instruments is responsible for all parts of
instrument systems included in the Type Rating.
7.3 The holder of a Type Rated Licence in Category ‘X’ – Instruments may issue
Certificates of Release to Service in respect of maintenance, excluding overhaul, of
components and parts for which the holder is responsible provided that units which
are supplied as bench tested units may not have their individual parts disturbed,
except for the replacement or adjustment of items normally replaceable or adjustable
in service.

8 BCAR Section L Aircraft Maintenance Engineer’s Licence – Type Rated in

Category 'X' – Electrical

NOTE: This paragraph must be read in conjunction with paragraph 1 of this Leaflet.
8.1 The holder of a Section L Category 'X' – Electrical Licence may issue Certificates of
Release to Service in respect of maintenance in relation to non-commercial air
transport aircraft electrical systems for which the licence is Type Rated, subject to the
limitations detailed in sub-paragraph 8.3.
8.2 In connection with the certification of maintenance, excluding overhaul, the holder of
a Type Rated Licence in Category 'X' – Electrical is responsible for all parts of electrical
systems included in the Type Rating.
8.3 The holder of a Type Rated Licence in Category 'X' – Electrical may issue Certificates
of Release to Service in respect of maintenance, excluding overhaul, of components
and parts for which the holder is responsible provided that units which are supplied
as bench tested units may not have their individual parts disturbed, except for the
replacement or adjustment of items normally replaceable or adjustable in service.

9 BCAR Section L Aircraft Maintenance Engineer’s Licence – Type Rated in

Category 'X' – Automatic Pilots

NOTES: 1) This paragraph must be read in conjunction with paragraph 1 of this Leaflet.
2) For the purpose of certification, automatic stabilisation systems are deemed to
be automatic pilots.
2) Automatic pilots include related systems such as yaw and or roll dampers, mach
trim systems, and automatic throttles.
9.1 The holder of a Section L Category 'X' – Automatic Pilots Licence may issue
Certificates of Release to Service in respect of maintenance in relation to non-
commercial air transport aircraft automatic pilot systems for which the licence is Type
Rated, subject to the limitations detailed in sub-paragraph 9.3.

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CAP 562 Civil Aircraft Airworthiness Information and Procedures

9.2 In connection with the certification of maintenance, excluding overhaul, the holder of
a Type Rated Licence in Category 'X' – Automatic Pilots is responsible for all parts of
the automatic pilot systems included in the Type Rating.
9.3 The holder of a Type Rated Licence in Category 'X' – Automatic Pilots may issue
Certificates of Release to Service in respect of maintenance, excluding overhaul, of
components and parts for which the holder is responsible provided that units which
are supplied as bench tested units may not have their individual parts disturbed,
except for the replacement or adjustment of items normally replaceable or adjustable
in service.

10 BCAR Section L Aircraft Maintenance Engineer’s Licence – Type Rated in

Combined Categories 'X' – Instrument/Automatic Pilots

The Type Rated Licence in Combined Categories 'X' – Instrument/Automatic pilots is

comprised of two 'X' Category ratings and the provisions and limitations contained in
both paragraphs 7 and 9 of this Leaflet apply in relation to the Instrument and
Automatic Pilot systems installed in any aircraft for which the Combined Categories
’X’ Licence is type rated.

11 BCAR Section L Aircraft Maintenance Engineer’s Licence – Type Rated in

Category 'R' – Radio

NOTE: This paragraph must be read in conjunction with paragraph 1 of this Leaflet.
11.1 The holder of a Section L Category 'R' – Radio Licence may issue Certificates of
Release to Service in respect of maintenance in relation to non-commercial air
transport aircraft radio systems for which the licence is Type Rated, subject to the
limitations detailed in sub-paragraph 11.3.
11.2 In connection with the certification of maintenance, excluding overhaul, the holder of
a Type Rated Licence in Category 'R' – Radio is responsible for all parts of the radio
systems included in the Type Rating.
11.3 The holder of a Type Rated Licence in Category 'R' – Radio may issue Certificates of
Release to Service in respect of maintenance, excluding overhaul, of components and
parts for which the holder is responsible provided that units which are supplied as
bench tested units may not have their individual parts disturbed, except for the
replacement or adjustment of items normally replaceable or adjustable in service.
11.4 The holder of a Type Rated Licence in Category 'R' – Radio, endorsed to include the
overhaul of radio apparatus, is responsible for and may issue Certificates of Release
to Service in respect of the maintenance of components and parts of all radio
apparatus undergoing periodic check, repair or overhaul in workshop for which the
Licence is Type Rated, provided that the work done does not involve the making of
radio components or parts.
11.5 The holder of a Type Rated Licence in Category 'R' – Radio endorsed including GPWS
may issue Certificates of Release to Service in respect of maintenance, excluding
overhaul or scheduled maintenance inspection, of Ground Proximity Warning
Systems for aircraft for which the licence is Type Rated in respect of its radio
systems, subject to the limitations of sub-paragraph 11.3.

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CAP 562 Civil Aircraft Airworthiness Information and Procedures

12 Compass Compensation and Adjustment

The Paragraph 15 type rating of CAP 562 Leaflet 15-3 permits the issue of Certificates
of Release to Service by the holder in respect of the compensation and adjustment
of direct and remote reading compasses on any aircraft.

13 Part-66 Category A Aircraft Maintenance Licence

NOTE: A JAR-66 licence is deemed to be compliant with Part-66 and therefore certification
privileges held under JAR-66 may continue to be exercised. Existing JAR-66 licences
held will be automatically converted to a Part-66 licence at the next licensing event.
It is not necessary for JAR-66 licence holders to convert to Part-66.
13.1 A Part-66 Category A Aircraft Maintenance Licence (AML) may be issued to a person
who has demonstrated a competence to complete minor scheduled line maintenance
and simple defect rectification. The licence does not entitle the holder to exercise any
certification privileges in respect of aircraft unless and until the holder is issued with
a corresponding Certification Authorisation. Such authorisations will be issued by a
Part-145 maintenance organisation appropriately approved by the Competent
Authority of a European Union Member State (EU Competent Authority) or EASA.
This means that the Part-66 Aircraft Maintenance Licence issued by the UK CAA can
readily be used as the basis for a certification authorisation throughout European
Union Member States.
NOTES: 1) It should be noted that a Part-66 licence may not provide for full equivalence in
another Member State to certify for work relating to any National legislation
which sits outside of Part-145. Additional language requirements may also apply.
2) The holder of an unrestricted Category B1 licence is also qualified as a Category
A licence holder in the same sub-category, e.g. Aeroplanes Turbine, and may be
issued with Category A certification authorisation.
13.2 These Category A privileges will be limited to the performance and certification of
specific simple maintenance tasks, either individually or in combination, as defined in
Part 145 AMC 145.A.30 (g) and will require a combination of theoretical and practical
training to be undertaken on each aircraft type to qualify for the task authorisation.
Such authorisation, issued by an Approved Part-145 Maintenance Organisation will
specify the limitations of the privileges that may be applicable. Licence holders will
therefore be required to act in accordance with the authorisation procedures of the
company concerned.

14 Part-66 Category B1 Aircraft Maintenance Licence

14.1 A Part-66 Category B1 Aircraft Maintenance Licence (AML) may be issued to a person
who has demonstrated a competence to complete maintenance, including aircraft
structure, powerplant and mechanical and electrical systems. Replacement of avionic
line replaceable units, requiring simple tests to prove their serviceability, shall also be
included in the privileges. The Category B1 licence is primarily intended to be used for
the purposes of qualification of line maintenance staff for authorisation. The licence,
in its own right, does not entitle the holder to exercise any certifying privileges in
respect of aircraft and will be used in conjunction with a Part-145 or Part-M subpart F
certification authorisation.
NOTE: Notwithstanding paragraph 14.1 above, certain limited certification privileges based
on a Type Rated Part-66 Licence may be exercised in accordance with Part
M.A.801(b)2. (See also CAP 562 Leaflet 15-3, paragraph 1.2 Note 2.)

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CAP 562 Civil Aircraft Airworthiness Information and Procedures

14.2 Such authorisations will be issued by a Part-145 or Part-M subpart F maintenance

organisation appropriately approved by the competent Authority of a European Union
member state or EASA. This means that the Part-66 Aircraft Maintenance Licence
issued by the UK CAA can readily be used as the basis for a certification authorisation
throughout the European Union member states. Part 145.A.30 (h) also requires it to
be used as a prerequisite for authorisation of staff acting as inspectors or supervisors
within base maintenance. Licence holders will therefore act in accordance with the
authorisation procedures of the company concerned.
NOTE: It should be noted that a Part-66 licence may not provide for full equivalence in
another EU Member State to certify for work relating to any National legislation
which sits outside of Part-145. Additional language requirements may also apply.
14.3 Category B1 licences apply to aircraft (aeroplanes and helicopters) and are issued in
licence sub-categories which are:
B1.1 Aeroplanes Turbine
B1.2 Aeroplanes Piston
B1.3 Helicopters Turbine
B1.4 Helicopters Piston
NOTE: An unrestricted B1 sub-category entitles the holder to be granted Category A
certification authorisations in the same sub-category, e.g. Aeroplanes Turbine.
14.4 Category B1 certification authorisations allow the holder to issue Certificates of
Release to Service under Part 145 or Part-M subpart F for line maintenance on aircraft
which are endorsed as individual types on the licence and the corresponding
authorisation. Category B1 licences to the full Part-66 standard include scope to allow
the issue of a certification authorisation covering work on a combination of the
following disciplines:
• airframe and their related systems;
• engines and their related systems (including Auxiliary Power Units);
• electrical power generation and distribution systems (power distribution in respect
of airframe and/or engine systems) including lighting systems (this includes all
electrical components in mechanical systems such as sensors, motors and control
units);
• avionic line replaceable units (LRU).
In respect of avionic LRUs, the work is limited to cases where the serviceability of the
system can be established by a simple self test facility (BITE) or by using simple test
equipment and it is expected that, for reference purposes, a list of such components
will be prepared for each aircraft type by the Part-145 or Part-M subpart F approved
organisation. (Defect rectification on avionic systems which requires an element of
decision making in its application other than a simple go/no go decision cannot be
certified).
NOTE: The Category B1 licence holder is not entitled to certify for any overhaul work.
14.5 The certification authorisation can only be issued by a Part-145 or Part-M subpart F
organisation when the licence holder has the appropriate basic sub-category listed
and the aircraft type rating endorsed on the Part-66 Aircraft Maintenance Licence. The
type training for a Category B1 type endorsement, conducted under a Part-147
approval, will represent the appropriate technologies as specified in Part-66. The
certification authorisation will specify the privileges for the individual, giving due
regard to the company scope of approval and any associated procedures agreed with

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CAP 562 Civil Aircraft Airworthiness Information and Procedures

the Competent Authority, and will specify any limitations to the authorisation
accordingly.
NOTES: 1) As of 28 September 2008 a Certificate of Release to Service may be issued for
maintenance on a non-large aircraft, not operating as commercial air transport,
based on a Part-66 licence extended with the appropriate type rating in
accordance with Part-M. This maintenance is limited to items not included in the
list at Part-M Appendix VII.
2) A Part-66 licence issued on the basis of protected rights may contain technical
restrictions equivalent to the limitations of any BCAR Section L licence or
company authorisations previously held. These protected rights under Part-66 are
a continuation of certifying privileges under an existing licence or certifying
authorisation which allows current personnel to continue working and certifying
without the need to re-qualify. Authorisations issued by a Part-145 organisation
should therefore be similarly restricted in scope. It should be noted that
conversion to the full Part-66 licence standard is optional.
14.6 Part-66 Category B1 licences issued by the UK CAA may also allow the certification,
under the provisions of Articles 14 and 16 of the Air Navigation Order 2005 (as
amended), for work outside of a CAA approved maintenance organisation on aircraft
which are not operated for commercial air transport. Such privileges are limited to UK
registered aircraft only. Certifications may only be made for those aircraft types which
are endorsed individually or as Group Type Ratings on the licence. The privileges will
reflect the current limitations for relevant BCAR Section L licence categories
highlighted earlier in the appropriate paragraphs of this Leaflet unless specified
otherwise.

15 Part-66 Category B2 Aircraft Maintenance Licence

15.1 A Part-66 Category B2 Aircraft Maintenance Licence (AML) may be issued to a person
who has demonstrated a competence to complete maintenance on avionic and
electrical systems. The Category B2 licence is primarily intended to be used for the
purposes of qualification of avionic line maintenance staff for authorisation. The
licence, in its own right, does not entitle the holder to exercise any certifying
privileges in respect of aircraft and will be used in conjunction with a Part-145 or Part-
M subpart F certification authorisation.
15.2 Such authorisations will be issued by a Part-145 or Part-M subpart F maintenance
organisation appropriately approved by the competent Authority of a EU Member
State. This means that the Part-66 Aircraft Maintenance Licence issued by the UK
CAA can readily be used as the basis for a certification authorisation throughout the
EU Member States. Part 145.A.30 (h) also requires it to be used as a prerequisite for
authorisation of staff acting as inspectors or supervisors within base maintenance.
Licence holders will therefore act in accordance with the authorisation procedures of
the company concerned.
NOTES: 1) It should be noted that a Part-66 licence may not provide for full equivalence in
another EU Member State to certify for work relating to any National legislation
which sits outside of EASA requirements.
2) A Category B2 licence cannot be used for the purposes of a Category A
certification authorisation unless the Category A licence is also held.
2) As of 28 September 2008 a Certificate of Release to Service may be issued for
maintenance on a non-large aircraft, not operating as commercial air transport,
based on a Part-66 licence extended with the appropriate type rating in
accordance with Part-M. This maintenance is limited to items not included in the
list at Part-M Appendix VII.

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CAP 562 Civil Aircraft Airworthiness Information and Procedures

15.3 Category B2 certification authorisations allow the holder to issue Certificates of

Release to Service under Part 145.A.50 for the line maintenance on aircraft which are
endorsed as individual types on the licence and the corresponding authorisation.
Category B2 licences to the full Part-66 standard include scope to allow the issue of
a certification authorisation covering work on a combination of the following aircraft
systems:
• instruments;
• automatic pilots (aeroplanes, helicopters and autoland systems);
• radio communication/navigation;
• radio radar;
• electrical power generation and distribution systems (power distribution in respect
of avionic systems) including lighting systems.
Scope is not included for authorisation in respect of work on electrical power
distribution systems or electrical/avionic components in mechanical systems.
NOTE: The Category B2 licence holder is not entitled to certify for any overhaul work.
15.4 The certification authorisation can only be issued by a Part-145 or Part-M subpart F
organisation when the licence holder has the appropriate basic category B2 listed and
the aircraft type rating endorsed on the Part-66 Aircraft Maintenance Licence. The
type training for a Category B2 type endorsement, conducted under a Part-147
approval, will represent the appropriate technologies as specified in Part-66. The
certification authorisation will specify the privileges for the individual, giving due
regard to the company scope of approval and any associated procedures agreed with
the EU Competent Authority, and will specify any limitations to the authorisation
accordingly.
NOTE: A Part-66 licence issued on the basis of protected rights may contain technical
restrictions equivalent to the limitations of any BCAR Section L licence or company
authorisations previously held. These protected rights under Part-66 are a
continuation of certifying privileges under an existing licence or certifying
authorisation which allows current personnel to continue working and certifying
without the need to re-qualify from scratch. Authorisations issued by a Part-145
organisation may therefore be similarly restricted in scope. It should be noted that
conversion to the full Part-66 licence standard is optional at present.
15.5 Part-66 Category B2 licences issued by the UK CAA may also be issued with an
endorsement, within an Annex to the licence, allowing the certification, under the
provisions of Articles 14 and 16 of the Air Navigation Order 2005 (as amended)
(national privileges), for work outside of a CAA approved maintenance organisation on
aircraft which are not operated for commercial air transport. Such privileges are
limited to UK registered aircraft only. Certifications may only be made for those types
which are endorsed individually or as BCAR Section L Group Type Ratings on the
licence. The limitations will reflect the current limitations for relevant BCAR Section L
licence categories highlighted earlier in the appropriate paragraphs to this Leaflet
unless specified otherwise.

16 Part-66 Category C Aircraft Maintenance Licence

16.1 A Part-66 Category C Aircraft Maintenance Licence (AML) may be issued to a person
who has demonstrated a competence to release an aircraft following Base
Maintenance. The privileges apply to the aircraft in its entirety in a Part-145
organisation. The licence, in its own right, does not entitle the holder to exercise any
certifying privileges in respect of aircraft and will be used in conjunction with a Part-
145 certification authorisation.

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CAP 562 Civil Aircraft Airworthiness Information and Procedures

16.2 Such authorisations will be issued by a Part-145 maintenance organisation

appropriately approved by the Competent Authority of an EU Member State. This
means that the Part-66 Aircraft Maintenance Licence issued by the UK CAA can
readily be used as the basis for a certification authorisation throughout the EU
Member States. Licence holders will therefore act in accordance with the
authorisation procedures of the company concerned.
NOTES: 1) It should be noted that a Part-66 licence may not provide for full equivalence in
another EU Member State to certify for work relating to any National legislation
which sits outside of Part-145. Additional language requirements may also apply.
2) Category C licences at present only apply to aircraft greater than 5700 kg
Maximum Take-Off Mass (MTOM).
16.3 Category C certification authorisations allow the holder to issue Certificates of
Release to Service under Part-145.A.50 following the completion of base
maintenance on aircraft which are endorsed on the licence and the corresponding
authorisation as individual types. Such persons are in essence certifying for the
completion of the process associated with base maintenance and are supported by
appropriately qualified and experienced category B1 and B2 staff, who will inspect
and supervise the actual work. The scope of coverage therefore reflects the whole
aircraft and is not limited to certification of solely mechanical or avionic systems.
16.4 It should be noted that a Category C licence holder cannot be authorised to act as
Category B certifying staff, exercising line maintenance certification privileges, nor
conducting base maintenance, in the role of an inspector or supervisor clearing
individual tasks, unless the licence is also endorsed with the appropriate Category B1
and/or B2 licence.
16.5 The certification authorisation can only be issued by a Part-145 organisation when the
licence holder has the basic Category C listed and the aircraft type rating endorsed on
the Part-66 Aircraft Maintenance Licence. The type training for a Category C type
endorsement, conducted under a Part-147 approval, will represent the appropriate
mix of systems knowledge as specified in Part-66. The certification authorisation will
specify the privileges for the individual, giving due regard to the company scope of
approval and any associated procedures agreed with the EU Competent Authority.
NOTE: A person qualified to Category B1 or B2 level with type endorsements will also be
eligible for a Category C type authorisation, providing the basic Category C licence is
held.

17 Part-66 General

Holders of Part-66 AML with type endorsements may be required to undertake

appropriate differences type training where the aircraft type to be authorised
embodies significant variations in the equipment fitted or the aircraft systems
configuration. The responsibility for determining the training to be undertaken will
remain with the Part-145 maintenance organisation.
Commission Regulation 216/2008 Annex II refers to aircraft types which have not
been adopted under Commission Regulation (EC) 2042/2003. Certification on these
aircraft types will continue under National licensing requirements. The UK CAA will
continue to issue National licences, (BCAR Section L), for this purpose for the time
being.
It is anticipated however, that in the future these aircraft types will be endorsed into
an annex to a Part-66 licence, thereby combining the two documents. The
certification basis for the Annex II types will remain as National Requirements.

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CAP 562 Civil Aircraft Airworthiness Information and Procedures

Leaflet 15-3 Aircraft Maintenance Engineers Licences –

Type Ratings

(Previously issued as AN 10)

NOTE: This previously published information has not been amended at this time though it
should be noted that, due to the licensing requirements that will be in force after
September 2008, the UK CAA national licence and all supporting documentation will
undergo significant change at that time. Further information will be available on the
CAA website at www.caa.co.uk/pldwhatsnew from June 2008.
This Leaflet will be updated at the next amendment to include any new information
regarding future changes.

1 Introduction

1.1 When reading this document, the reader must take into account Commission
Regulation (EC) No. 2042/2003. The Commission Regulation is a legal document,
which applies to the UK aviation industry.
1.2 This Leaflet sets out the Type Ratings that may be endorsed upon a BCAR Section L
for Aircraft Maintenance Engineers' Licence or a Part-66 Aircraft Maintenance
Licence issued by the United Kingdom Civil Aviation Authority in respect of the
certification of aircraft registered in the United Kingdom, including also their engines
and systems.
NOTES: 1) A licence can only be used to certify for non-commercial air transport. Aircraft
which are operated for commercial air transport must be maintained by a
Part-145 Approved Organisation and all staff who certify for maintenance within
those organisations must be in possession of a valid certifying authorisation (see
CAP 562 Leaflet 1-1).
2) As of 28 September 2008 Certification of Maintenance on aircraft using a licence
as authority is limited to items which are not listed at Part-M Appendix VII.
1.3 Following the full implementation of JAR-66 on 1 June 2001, type ratings in respect
of types of aircraft of 5700 kg MTOM and above, or the engines or systems fitted to
such aircraft, are not available to holders of Aircraft Maintenance Engineers’ Licences
issued under Issue 14 and subsequent issues of BCAR Section L which came into
effect on 1 June 2001. Part-66 replaced JAR-66 in the UK as of June 2004 for
aeroplanes above 5700 kg and November 2004 for all other aircraft. Holders of
licences granted under earlier issues of Section L, and which already include the
appropriate LWTR, may continue to apply for such type ratings until the privileges are
transferred to a Part-66 licence. Full information may be found in BCAR Section L
Issue 15.

2 General

2.1 The requirements for the grant, extension and renewal of BCAR Section L Aircraft
Maintenance Engineers' Licences are contained in the current Issue of BCAR
Section L. For full understanding of the requirements, Section L must be read in
conjunction with this Leaflet.
NOTE: As of November 2006, new BCAR Section L Licences shall not be issued except
where required to certify (EC) Regulation 216/2008 Annex II aircraft. Current BCAR
Section L Licences may be extended in accordance with current BCAR Section L

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CAP 562 Civil Aircraft Airworthiness Information and Procedures

requirements until 27 September 2008. As of this date a Part-66 licence is required

for certification of all (EC) Regulation 216/2008 Annex I aircraft. This applies to all
categories of aircraft except those listed in (EC) Regulation 216/2008 Annex II.
2.2 The requirements for the grant, variation or renewal of Part-66 Aircraft Maintenance
Licences are contained in Commission Regulation (EC) No. 2042/2003. For full
understanding of the requirements, Part-66 within Commission Regulation (EC) No.
2042/2003 must be read in conjunction with Acceptable Means of Compliance (AMC)
to Part-66 and Guidance Material to Part-66, this Leaflet and, where appropriate, Part-
145. Part-66 Category B1 licences issued by the UK CAA may also allow the
certification, under the provisions of Articles 14 and 16 of the Air Navigation Order
2005 (as amended), for work outside of a CAA approved maintenance organisation on
aircraft which are not operated for commercial air transport. Such privileges are
limited to UK registered aircraft only. Certifications may only be made for those
aircraft types which are endorsed individually or as Group Type Ratings on the licence,
otherwise, a Part-66 licence must be used in conjunction with a Part-145 certification
authorisation (see Part-145 and CAP 562 Leaflet 15-2).
2.3 The requirements of BCAR Section L and Part-66 recognise the standards prescribed
by the International Civil Aviation Organisation (ICAO) for the grant and extension of
licences.

3 Applicability

3.1 Where a type of aircraft (or its engines or systems) is defined by one of the Group
Type Ratings in paragraphs 5 to 9, 12, 13 or 15 of this Leaflet, an engineer may
exercise the certification privileges in respect of that type, subject in particular to the
provisions of CAP 562 Leaflet 15-2 and provided that:
a) he holds a valid UK CAA issued Type Rated Licence, and
b) an aircraft of the type is registered in the United Kingdom and holds a United
Kingdom issued Certificate of Airworthiness.
3.2 Where a type of aircraft (or its engines or systems) is listed individually within
paragraphs 5, 6, 7 and 10 of this Leaflet, the licence holder has certification privileges
in respect of the individual types as listed on the licence, subject in particular to the
provisions of CAP 562 Leaflet 15-2.
3.3 Where a type of aircraft (or its engines or systems) is not defined by a Group Type
Rating or is not listed by name, an application for the Type Rating of a licence in
respect of that type of aircraft, engines or systems, will be considered provided that:
a) an aircraft of the type is registered in the United Kingdom and holds a United
Kingdom issued Certificate of Airworthiness; and
b) the aircraft does not exceed 5700 kg MTOM.
3.4 In respect of aircraft types maintained under Part-145, the CAA will consider
applications for the endorsement of type ratings on a BCAR Section L licence where
the aircraft type rating is required for the issue of a Part-145 certification authorisation
and:
a) the aircraft is a type which is not registered in the United Kingdom and does not
hold a United Kingdom issued Certificate of Airworthiness but is registered in an
EU member state; and
b) the aircraft does not exceed 5700 kg MTOM.

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CAP 562 Civil Aircraft Airworthiness Information and Procedures

4 Categories 'A' 'B' 'C' 'D' Aeroplanes, Engines and Rotorcraft

4.1 Specific Type Ratings

4.1.1 Type Ratings may be granted for specific aircraft and/or engines defined by, or listed
in, paragraphs 5, 6 or 7 of this Leaflet, except as indicated in sub-paragraphs 4.1.2,
4.1.3 and 4.1.4.
4.1.2 A Type Rating in Category 'B' – Aeroplanes, will not be granted in respect of an
unpressurised aeroplane exceeding 5700 kg MTOM, an aeroplane in which the
primary structure is of reinforced plastic/epoxy manufacture, or any pressurised
aeroplane.
4.1.3 A Type Rating in Category 'D' – Engines, will not be granted in respect of a piston
engine with a power rating exceeding 500 kW (670 bhp), or any jet- or propeller-
turbine engine (not available for new licence issue).
4.1.4 A Type Rating in Category 'B' – Rotorcraft, will not be granted in respect of a turbine-
engined rotorcraft exceeding 2730 kg MTOM.
4.2 Group Type Ratings
4.2.1 A Group Type Rating granted in relation to sub-paragraphs of paragraph 5, 6 or 7 of
this Leaflet includes all the aeroplanes, engines, or rotorcraft defined by that sub-
paragraph except as limited by sub-paragraphs 4.2.4 or 4.2.5.
4.2.2 Group Type Ratings for Categories 'A' and 'C' may be granted for a group of
aeroplanes, engines or rotorcraft defined by sub-paragraphs 5.0, 5.1, 5.7, 5.7.1, 5.9.1,
6.0, 6.3, 7.1 or 7.3 only.
4.2.3 Licence holders with Group Type Ratings in Categories 'A', 'B', 'C' or 'D' for sub-
paragraphs 5.2, 5.2.1, 5.3, 5.3.1, 5.4, 5.5, 5.5.1, 6.1, 6.2, 6.3.1 and 6.4 may continue
to exercise the privileges of the licence for the types defined by these groups subject
to any limitations endorsed on the licence.
4.2.4 Group Type Ratings for Category 'B' – Aeroplanes or rotorcraft, may be granted for
sub-paragraphs 5.1, 5.7, 5.7.1, 7.1 and 7.3, excluding any rotorcraft exceeding
2730 kg MTOM.
4.2.5 Group Type Ratings for Category 'D' – Engines may be granted on existing Category
D licences for sub-paragraphs 6.0 and 6.3, and includes rotorcraft and airship engines,
but excludes engines with a power rating exceeding 500 kW (670 bhp).
4.2.6 Sub-paragraphs indicated thus * in this Leaflet are not obtainable as new
endorsements on a licence.

5 Category 'A' and 'B' Aeroplanes

5.0 Composite Materials Aeroplanes Not Exceeding 5700 kg MTOM (not available in
Category B).
5.1 Wooden and Wood and Metal Aeroplanes:
Aeroplanes where the primary structure is manufactured from wood or combinations
of wood and metal.
5.2 *Unpressurised metal aeroplanes not exceeding 2730 kg MTOM.
5.2.1 *Unpressurised metal aeroplanes not exceeding 2730 kg MTOM with fixed landing
gear only.

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CAP 562 Civil Aircraft Airworthiness Information and Procedures

5.3 *Unpressurised metal aeroplanes not exceeding 5700 kg MTOM.

5.3.1 *Unpressurised metal aeroplanes not exceeding 5700 kg MTOM with fixed landing
gear only.
5.4 *Unpressurised metal aeroplanes, but excluding aeroplanes defined in paragraph 14
of this Leaflet.
5.5 *Pressurised metal aeroplanes not exceeding 5700 kg MTOM and all unpressurised
metal aeroplanes, but excluding aeroplanes defined in paragraph 14 of this Leaflet.
5.5.1 *Pressurised and unpressurised metal aeroplanes not exceeding 2730 kg MTOM.
5.6 Reserved.
5.7 Unpressurised metal aeroplanes not exceeding 5700 kg MTOM.
5.7.1 Unpressurised metal aeroplanes not exceeding 2730 kg MTOM.
5.8 Unpressurised metal aeroplanes exceeding 5700 kg MTOM.
5.9 Individual pressurised metal aeroplanes exceeding 2730 kg MTOM, but not
exceeding 5700 kg MTOM.
5.9.1 Pressurised metal aeroplanes not exceeding 2730 kg MTOM.

6 Category 'C' and 'D' – Engines

6.0 Diesel engines in aeroplanes.

6.1 *Unsupercharged reciprocating piston engines, excluding Diesel engines, fitted with
a fixed pitch propeller.
6.2 *Unsupercharged reciprocating piston engines, excluding Diesel engines, fitted with
a fixed or variable pitch propeller.
6.3 Category 'C' Piston engines in Aeroplanes, excluding Diesel engines.
*Category 'D' Piston engines not exceeding 500 kW (670 bhp) in Aeroplanes/
Rotorcraft/ Airships, excluding Diesel engines.
6.3.1 *Piston engines, excluding Diesel engines, in Aeroplanes not exceeding 2730 kg
MTOM.
6.4 Jet-turbine engines in Aeroplanes not exceeding 22·25 kN (5000 lbf) static thrust
including where so endorsed the associated APU installations.
6.5 Individual types of propeller turbine engines in aeroplanes (including, where so
endorsed, the associated APU installations):
Allison 250 Ž
Garret Airesearch TPE 331
Pratt & Whitney Canada PT6 Ž
Turbomeca Astazou
NOTE: For engines annotated ~ or Ž see CAP 562 Leaflet 15-2, sub-paragraph 4.4.
6.6 *Jet turbine engines, in aeroplanes, exceeding 22·25 kN (5000 lbf) static thrust
including where so endorsed the associated APU installation.

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CAP 562 Civil Aircraft Airworthiness Information and Procedures

7 Categories 'A' and 'C' and 'B' – Rotorcraft

7.1 Piston-engined rotorcraft.

7.2 Reserved.
7.3 Turbine-engined rotorcraft not exceeding 2730 kg MTOM.
NOTE: This paragraph includes the Allison 250 and Turbomeca Arriel engines which are
annotated Ž for the purposes of CAP 562 Leaflet 15-2, sub-paragraph 6.4.
7.4 Individual types of turbine-engined rotorcraft exceeding 2730 kg MTOM:
Aerospatiale SA 365 with Turbomeca Arriel Ž
Agusta 109E with P & W Canada 206 series ~
Bell 212 with P & W Canada PT6T Ž
Bell 222 with Lycoming LTS 101 Ž
Bell 412 with Pratt & Whitney PT6
Eurocopter EC135 with Arrius (increased all up weight versions)
Eurocopter EC155 with Arriel
MBB BK 117 with Lycoming LTS 101 Ž
McDonnell Douglas 900 with P & W 206 series (increased all up weight versions)
McDonnell Douglas MD902 with P & W Canada 206 series ~
Sikorsky S76 with Allison 250 Ž
Sikorsky S76 with P & W Canada PT6B Ž
Sikorsky S76 with Turbomeca Arriel Ž
Westland W30 with RR Gem
Westland S55 with BS Gnome ~
NOTE: For an engine annotated ~ or Ž see CAP 562 Leaflet 15-2, sub-paragraph 6.4.

8 Category 'X' Instruments

NOTE: As of 28 September 2006 a BCAR Section L licence cannot be used in support of

certification of aircraft exceeding 5700 kg MTOM.
a) A Rating granted in relation to any of the sub-paragraphs 8.1 to 8.4 inclusive,
includes all of the instruments fitted to those aircraft in which are installed systems
defined by or listed in that sub-paragraph excluding those aircraft listed in
paragraph 10, and as limited by paragraph 3 of this Leaflet.
b) A Rating granted in relation to sub-paragraph 8.8 relates to Instruments – Direct
and remote reading compasses only, but excludes compasses on those aircraft
listed in paragraph 10, and is limited by sub-paragraph 3.3 of this Leaflet.
NOTES: 1) A Type Rated Licence which is valid for paragraphs 8.2, 8.3 or 8.4 also includes
paragraph 8.1.
2) A Type Rated Licence which is rated for Category 'X' – Instruments now includes
the INS, GPWS and compass systems, (excluding compass compensation and
adjustment) whether or not these systems are separately endorsed on the
licence.
3) Where a system is a combined flight director/ automatic pilot the rating does not
include items of equipment associated solely with the automatic pilot.

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CAP 562 Civil Aircraft Airworthiness Information and Procedures

8.1 General aircraft instrument systems but excluding instruments installed on any
aircraft which has installed a Flight Director System.
8.2 Smiths Flight System
Sperry Zero Reader ZL1, ZL2 Flight Director System.
8.3 Flight Director Systems employing air driven gyroscopes (attitude).
8.4 Flight Director Systems employing electrically driven gyroscopes (attitudes) but
excluding those systems defined in sub-paragraph 8.2.
8.5 Reserved.
8.6 Reserved.
8.7 Reserved.
8.8 'X' Instruments (compasses)
Compensation and adjustment of airborne compass and compass systems.

9 Category 'X' – Electrical

A rating granted in relation to any sub-paragraph of paragraph 9 of this Leaflet includes

the generation system and the electrical installation in aircraft as defined by that sub-
paragraph, as limited by paragraph 3 of this Leaflet.
NOTE: A Type Rated Licence which is valid for paragraphs 9.2 or 9.3 also includes paragraph
9.1.
9.1 Aircraft in which the main generation system output is DC (including alternators
having a self-contained rectifier system) and in which secondary alternators having an
individual power rating not exceeding 1·5 kVA may be fitted.
9.2 Aircraft in which the main generation system output is DC and which have installed
'frequency' wild alternators with an individual power rating exceeding 1·5 kVA for
auxiliary services.
9.3 Aircraft in which the main generation system output is 'frequency wild' AC and DC
power is supplied from transformer rectifier units.
9.4 Aircraft in which the main generation system output is 'constant frequency' AC from
alternators driven by constant speed drive units, or variable speed constant frequency
(VSCF) generator/converter systems, and DC power is supplied from transformer
rectifier units.

10 Reserved

11 Reserved

12 Category 'R' – Radio

A rating granted in relation to any sub-paragraph of paragraph 12 of this Leaflet

includes all the types of radio systems listed in that sub-paragraph, as limited by
paragraph 3 of this Leaflet.
NOTE: A Type Rated Licence in Category 'R' – Radio includes Ground Proximity Warning
Systems only when the licence is endorsed to that effect.
12.1 * Airborne Communication Systems.

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CAP 562 Civil Aircraft Airworthiness Information and Procedures

12.2 Airborne Communication Systems, Airborne Navigation Systems.

12.2.1 Airborne Communication Systems and Airborne Navigation Systems installed in
aircraft below 5700 kg MTOM, excluding HF communications systems, Passenger
entertainment systems, Multiplex systems, CVR and Satellite communication
systems.
12.3 Airborne radar systems.
12.3.1 Airborne radar systems installed in aircraft below 5700 kg MTOM, excluding weather
radar and TCAS.

13 Category 'X' – Automatic Pilots

A rating granted in relation to any sub-paragraph of paragraph 13 of this Leaflet

includes all the automatic pilot systems defined by that sub-paragraph when installed
in aircraft not exceeding 5700 kg MTOM and as limited by paragraph 3 of this Leaflet.
NOTES: 1) A Type Rated Licence which is valid for paragraph 13.2 also includes paragraph
13.1.
A Type Rated Licence which is valid for paragraph 13.3 also includes paragraphs
13.1 and 13.2.
A Type Rated Licence which is valid for paragraph 13.5 also includes paragraph
13.4.
2) For the purpose of licensing, automatic stabilisers are deemed to be automatic
pilots.
3) Automatic pilots include related systems such as yaw dampers and/or roll
dampers, mach trim systems and automatic throttle systems.
13.1 Non-Radio-Coupled Automatic Pilots (Aeroplanes)
13.2 Radio-Coupled Automatic Pilots (Aeroplanes) excluding ILS Coupled (LOC and GS)
Automatic Pilots
13.3 ILS Coupled (LOC and GS) Automatic Pilots (Aeroplanes)
13.4 Non-Radio-Coupled Automatic Pilots (Rotorcraft)
13.5 Radio-Coupled Automatic Pilots (Rotorcraft)

14 Reserved

15 Compass compensation and adjustment

Compensation and adjustment of airborne compass and compass systems.

16 Part-66 Category B1, B2 and C Type Ratings

The requirements for the grant, variation or renewal of Aircraft Maintenance Licences
are contained in Commission Regulation (EC) No. 2042/2003. It is possible to obtain
aircraft type ratings in accordance with the provisions of this requirement. This
includes aircraft which are listed above in paragraph 14 of this Leaflet and aircraft
which are registered and operated in another JAA member state but which are
maintained under a Part-145 approval.
The aircraft types are listed in Appendix 1 to Part-66 (AMC) and will be granted only
where Part-147 approved type training has been completed to the appropriate

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CAP 562 Civil Aircraft Airworthiness Information and Procedures

Category B1, B2 or C syllabus and the required practical experience, if appropriate,

can be demonstrated.
Current Section L licence holders will be entitled to protected rights under
Commission Regulation (EC) No. 2042/2003 on existing licence and authorisation
privileges. Section L group type ratings may be transferred directly onto Part-66
licences, except for purposes of reflecting continuing National privileges, identified as
Annex II aircraft of Commission Regulation (EC) No. 216/2008, where, for the time
being, BCAR Section L Licences will be retained for certification purposes.

17 Aircraft Type Lists

Aircraft type list Commission Regulation 2042/2003 Appendix 1 AMC Part-66

Refer to www.srg.caa.co.uk
Aircraft type list Commission Regulation 216/2008 Annex II
Refer to www.srg.caa.co.uk

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CAP 562 Civil Aircraft Airworthiness Information and Procedures

Leaflet 15-4 Personnel Authorisation Systems for

Sailplanes and Balloon Certifying Staff in
Part M Subpart F Organisations

(Previously issued as AN 14 Appendix 3)

1 General

1.1 This Leaflet permits persons to be granted, by the holder of a Part M Subpart F
approval issued by the CAA, Authorisations to issue Certificates of Release to Service
when the CAA has agreed the conditions of such Authorisations. This Leaflet provides
guidance to assist organisations in determining the conditions, which may be agreed
by the CAA.
NOTES: 1) Compliance with this Leaflet does not provide a basis for the grant of personnel
certification privileges outside of a Part-M Subpart F organisation.
2) The introduction of specific requirements for sailplanes and balloons into Part 66
would put in place European legislative provisions that render the Authorisation
concept defined here obsolete. Authorisations systems agreed under this Leaflet
may not therefore be used once any new legislation comes into effect.
Approved organisations wishing to issue certifying staff Authorisations shall develop
suitable procedures to determine the competence of staff to hold such
authorisations, and to manage and control the process within their organisation.
These procedures shall clearly define the limits to which Authorisations can be
granted. The proposed procedure shall be submitted initially through the responsible
CAA Regional Office for approval and when approved shall be contained within an
organisation’s Maintenance Organisation Manual.
1.2 The CAA has chosen not to define, in detail, acceptable boundaries in respect of
defect diagnosis and the types of test equipment that are compatible with the
Authorisation concept. Such definitions would inevitably produce a set of
unnecessarily restrictive requirements.
1.3 The following shall be observed when developing suitable procedures:
1.3.1 Age
An applicant shall be not less than 18 years of age.
1.3.2 Experience
An applicant for an Authorisation shall have had the following minimum experience in
the inspection, servicing and maintenance of sailplanes or balloons, as appropriate:
a) For the issue of Authorisation privileges for a sailplane or balloon in its entirety, at
least:
i) four years of relevant maintenance experience; or
ii) two years if the applicant has satisfactorily completed an approved training
course.
b) For the issue of a restricted Authorisation, a period of time agreed by the CAA that
will enable a level of competency equivalent to that required by a) to be obtained,
provided that this is not less than two years.

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CAP 562 Civil Aircraft Airworthiness Information and Procedures

1.3.3 Knowledge
It shall be established by the organisation that applicants have an adequate
knowledge of a relevant sample of the type(s) of sailplanes or balloons gained through
a formalised training course including documented evidence of practical experience.
Formalised training courses may be replaced by demonstration of knowledge, by
documented evidence of experience and by an assessment performed by a Part M
Subpart F organisation in accordance with procedures agreed by the CAA.
This assessment shall include:
a) relevant parts of initial and continuing airworthiness regulations;
b) relevant parts of operational requirements and procedures, if applicable;
c) the organisation’s maintenance organisation manual;
d) knowledge of a relevant sample of the type(s) of sailplanes/balloons/airships
gained through training and/or work experience;
e) maintenance practices and techniques.
Records shall be maintained including:
• results of assessments;
• records of syllabi;
• names and position of assessors.
1.3.4 Continued validity
The organisation shall ensure that all certifying staff are involved in at least six months
of actual relevant sailplane or balloon component maintenance experience in any
consecutive two year period. For the purpose of this supplement ‘involved in actual
relevant sailplane or balloon maintenance’ means that the person has worked in a
sailplane or balloon maintenance environment and has exercised the privileges of the
certification authorisation and/or has actually carried out maintenance on at least
some of the sailplane/balloon type systems specified in the particular certification
authorisation.

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CAP 562 Civil Aircraft Airworthiness Information and Procedures

Leaflet 15-5 Implementation of the Railways and Transport

Safety Act 2003 – Aviation: Alcohol and Drugs

(Previously issued as AN 45)

1 Introduction

1.1 The information contained in this Leaflet has been developed in conjunction with the
Department for Transport, the Home Office and the Police, and is consistent with the
criteria contained in the Police Protocol. It is anticipated that this will facilitate a
consistent approach by relevant parties.
1.2 The aim of this Leaflet is to inform Licensed Aircraft Maintenance Engineers of this
new legislation and how it affects them in the performance of their duties.

2 Legislative Background

2.1 The effect of intoxication, through alcohol or drugs, on aviation personnel has
significant safety implications. The Air Navigation Order (ANO), which is the main
aviation safety regulatory legislation, provides that no member of an aircraft’s crew, a
licensed aircraft maintenance engineer or an air traffic control officer shall be under
the influence of alcohol or drugs to such an extent as to impair his/her capacity to carry
out their duties. The ANO, however, does not set a blood alcohol limit nor does it
require a person who is suspected of an alcohol or drugs offence to be subjected to
a test.
2.2 In 1996, the Government issued a Consultation Paper on alcohol and drug testing for
aircraft crew and other safety critical civil aviation personnel, which proposed the
introduction of a blood/alcohol limit for certain aviation personnel, together with
corresponding Police powers of enforcement. Responses to the consultation were
broadly supportive of the Government's approach. Part 5 of the Railways and
Transport Safety Act 2003 www.legislation.hmso.gov.uk/acts/acts2003/
20030020.htm represents the first suitable legislative opportunity to take forward
these proposals and now brings aviation into line with other transport modes in
seeking to tackle alcohol or drug misuse among key personnel. The Police testing and
enforcement powers broadly mirror those currently applied on our roads and railways
and are based on an officer's reasonable suspicion that an offence either has been,
or is in the process of being, committed.
2.3 The blood/alcohol limit for aviation personnel is lower than that in shipping or on our
roads or railways, but for pilots reflects the Joint Aviation Requirement on
Commercial Air Transportation (JAR-OPS) - adopted by the Joint Aviation Authorities
(JAA) in 1996 - which requires that crew members of commercial aircraft should not
commence a flight duty period with a blood/alcohol level in excess of 20mg of alcohol
per 100ml of blood. The adoption of this limit will go towards the harmonisation of
standards across most of Europe.
2.4 Enforcement of the provisions of the Act is the responsibility of the Police and the
Crown Prosecution Service. There is no provision for random testing.

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CAP 562 Civil Aircraft Airworthiness Information and Procedures

3 Implementation

Part 5 of the Act was brought into force on 30 March 2004.

4 Summary of Part 5 of The Railways and Transport Safety Act 2003 and
Commentary on Enforcement

This Part extends to the flight and cabin crew of an aircraft, air traffic controllers and
licensed aircraft maintenance engineers in the United Kingdom. It also applies to the
crew of an aircraft registered in the United Kingdom wherever it may be in the world.
An Explanatory Note may be found at:
www.legislation.hmso.gov.uk/acts/en/03en20-b.htm.

5 Offences – Being Unfit for Duty (Section 92)

Section 92 makes it an offence to perform an aviation function or an ancillary activity

whilst impaired through alcohol or drugs.

6 Offences – Prescribed Limit (Section 93)

6.1 This Section makes it an offence to perform or prepare to perform certain aviation-
related functions with more than a prescribed level of alcohol in the body.
6.2 The prescribed blood/alcohol alcohol limits are 20 milligrammes of alcohol per 100
millilitres of blood for those activities carried out by aircrew and air traffic controllers,
and 80 milligrams per 100 millilitres for licensed aircraft maintenance engineers. The
different limits reflect the fact that although licensed aircraft maintenance engineers
perform a safety critical role in aviation, they do not necessarily require the same
speed of reaction as aircrew or air traffic controllers may need in an emergency
situation.
The equivalent limits in respect of breath and of urine are also set out in this section.
6.3 Detailed limits are:
a) When:
• acting as a pilot, cabin crew, flight engineer, flight navigator or flight radio-
telephony operator of an aircraft during flight;
• attending the flight deck of an aircraft during flight to give or supervise training,
to administer a test, to observe a period of practice or to monitor or record the
gaining of experience; or
• acting as an air traffic controller in pursuance of a licence granted under or by
virtue of an enactment (other than a licence granted to a student):
the prescribed limit of alcohol is:
i) In the case of breath: 9 microgrammes of alcohol in 100 millilitres.
ii) In the case of blood: 20 milligrammes of alcohol in 100 millilitres.
iii) In the case of urine: 27 milligrammes of alcohol in 100 millilitres.
b) When acting as a licensed aircraft maintenance engineer the prescribed limit of
alcohol in respect of the above is:
i) In the case of breath: 35 microgrammes of alcohol in 100 millilitres.

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CAP 562 Civil Aircraft Airworthiness Information and Procedures

ii) In the case of blood: 80 milligrammes of alcohol in 100 millilitres.

iii) In the case of urine: 107 milligrammes of alcohol in 100 millilitres.

7 Aviation Functions (Section 94)

7.1 This section applies the offences of being either over the limit or unfit, to people
preparing to carry out an aviation function or otherwise holding themselves ready to
carry out one of those functions by virtue of being on duty or standby.
7.2 An activity shall be treated as an ancillary function if it is undertaken by a person
commencing a period of duty in respect of the function, and as a requirement of, for
the purpose of or in connection with the performance of the function during the
period of duty. For example, the pre-flight briefing of the flight and cabin crew and any
post-flight activity such as filing reports is considered to be an ‘ancillary’ function.

8 Testing Under the Act

8.1 Preliminary test (i.e. a breathalyser test)

The Act provides that the power to require a person to co-operate with a preliminary
test shall apply where:
a) a constable in uniform reasonably suspects that the person is over the prescribed
limit,
b) a constable in uniform reasonably suspects that the person has been over the
prescribed limit and still has alcohol or a drug in his body or is still under the
influence of a drug,
c) an aircraft is involved in an accident and a constable reasonably suspects that the
person was undertaking an aviation function, or an activity ancillary to an aviation
function, in relation to the aircraft at the time of the accident, or
d) an aircraft is involved in an accident and a constable reasonably suspects that the
person has undertaken an aviation function, or an activity ancillary to an aviation
function, in relation to the aircraft.
8.2 A person who, without reasonable excuse, fails to provide a specimen when required
to do so in pursuance of this section is guilty of an offence.
8.3 A person commits an offence under the Act if he/she performs an aviation function,
or an activity that is ancillary to an aviation function, at a time when his/her ability to
perform the function is impaired because of alcohol or drugs. This means that a
person can be tested at any time after commencing duty, including standby.
8.4 The Police will determine when to test. As noted above this will in essence be when
there are reasonable grounds for suspicion that someone is over the prescribed limit,
or when an accident has occurred.
8.5 The Police are empowered to breathalyse and to perform subsequent tests (i.e. blood
and urine tests). Police officers have been advised to exercise their powers under the
Act as discreetly as circumstances allow and, if possible, in private, particularly where
passenger aircraft are concerned. Overtly or insensitively exercising these powers in
certain circumstances could have detrimental affect on passenger perception and
confidence, and could have commercial implications and liabilities.
The preliminary drug test is dependent on factors not yet finalised.

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CAP 562 Civil Aircraft Airworthiness Information and Procedures

8.6 Testing following an accident

An accident for these purposes is defined as an unintended event with adverse
physical effect. It is unlikely that every accident involving an aircraft will warrant Police
exercising any or all of their power under this Act.

9 Reasonable Grounds for Suspicion

9.1 Reasonable grounds for suspicion depend upon the circumstances in each case.
There must be an objective basis for that suspicion based on facts, information and/
or intelligence that are relevant to the likelihood of an offence. Reasonable suspicion
cannot be based on generalisations or stereotypical images of certain groups or
categories of people as more likely to be involved in criminal activity.
9.2 Reasonable suspicion can sometimes exist without specific information or
intelligence and on the basis for some level of generalisation stemming from the
behaviour of a person. Reasonable suspicion should normally be linked to accurate
and current intelligence or information. For example, evidence of impairment from
witnesses or from the result of a primary test of an employee by an employer could
be sufficient.

10 Procedure in the Event of a Positive Breathalyser Test

10.1 If, as a result of an initial Police breath test, an officer has reasonable cause to suspect
that a person has more than the prescribed proportion of alcohol in their body, then
they can expect to be arrested and taken to a Police station. There, they will be asked
to provide a further specimen of breath, blood or urine for laboratory analysis. In
practice, this will usually be a specimen of blood, taken by a Police doctor. Failure to
provide a specimen without reasonable cause is an offence. Where a sample of blood
or urine is taken, he/she will be entitled to request a part of the sample for
themselves. He/she will be supplied with a booklet of analysts where they can have
their specimen privately analysed if they wish.
10.2 Once a blood sample has been taken he/she will probably be released from the Police
station on a condition to return at a later date, by which time the Police part of the
sample will have been analysed. If the sample is under the limit he/she will probably
be told not to attend. If, when he/she attends, the results of the analysis of the sample
shows that he/she was over the limit, he/she will be charged with the offence and be
given a date to attend court.
10.3 After giving a specimen, the Police may detain the individual at the Police station until
it appears to the officer that there is no likelihood of them carrying out, or attempting
to carry out, an aviation function of the kind for which they have provided a sample,
whilst still over the prescribed limit or otherwise impaired through alcohol or drugs.

11 Advice to Engineers

This Leaflet should be read in conjunction with CAP 562 Leaflet 15-6, that contains
further information on the Licensed Aircraft Maintenance Engineer’s responsibilities
when medically unfit or under the influence of alcohol or drugs.

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CAP 562 Civil Aircraft Airworthiness Information and Procedures

12 Penalties and Enforcement Powers (Sections 95, 97 and 98)

12.1 Section 95: Penalty

The penalties set out in section 95 are set at the same level as those currently
applying to aircrew and air traffic controllers under Article 148 of the ANO 2005 (as
amended). This section will bring the penalty for licensed maintenance engineers
under the influence of alcohol or drugs into line with them.
12.2 Arrest without a warrant (Section 97)
A constable may arrest a person without a warrant if the constable reasonably
suspects that the person is committing an offence under Section 92 (being unfit for
duty), or has committed an offence under that Section and is still under the influence
of alcohol or drugs.
12.3 Right of entry (Section 98)
12.3.1 A Police constable in uniform may board an aircraft if he/she reasonably suspects that
he/she may wish to exercise a power by virtue of Section 96 (power to administer
tests, etc.) or under Section 97 (arrest without a warrant) in respect of a person who
is or may be on the aircraft.
12.3.2 A Police constable in uniform may enter any place if he/she reasonably suspects that
he/she may wish to exercise a power by virtue of Section 96 (power to administer
tests, etc.) or under Section 97 (arrest without a warrant) in respect of a person who
is or may be in that place.
12.3.3 For the purpose of boarding an aircraft or entering a place under this Section, a Police
constable may use reasonable force or may be accompanied by one or more persons,
e.g. airline personnel, additional Police constables, etc. Officers not used to working
on airports or in aircraft and not trained to consider the relevant aspects of health and
safety may wish to be accompanied by an agent of the airport or the operator as
appropriate.

13 Disclosure of Information

13.1 In exercising their powers under this Act, the Police may acquire information that
gives cause for serious concern that a person performing a safety critical aviation
function is unsuited to hold that position of trust. This acquisition may occur even
before their sample of blood or urine has been analysed or they have been charged,
for example, where such a person has provided a positive preliminary test.
13.2 Such information may be passed to that person’s employer or professional body on
grounds of public safety or for the prevention or detection of crime. This will only be
carried out with the authority of an officer of Assistant Chief of Police rank.
13.2.1 Any disclosure should provide only that information required to determine whether
the offender should continue in their present role pending trial.
13.2.2 If authority to disclose is refused, Police should provide for the analysis of samples to
be fast-tracked by the Forensic Science Service and for the offender to be charged, if
appropriate, at the earliest opportunity.
13.3 In reality it is likely that if an individual is tested positive whilst on a duty, this will have
an immediate impact on their ability to perform their function and will quickly come to
the attention of the employer.

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CAP 562 Civil Aircraft Airworthiness Information and Procedures

14 CAA Protocol in Suspected Alcohol or Drug Misuse

In cases where a licensed engineer may be misusing alcohol or drugs, a decision will
be made whether there is alcohol or drug dependency that could be a risk to flight
safety. If so, the licence may be suspended, or where the licence has been issued by
another state, a recommendation to suspend will be sent to the issuing authority. If
that is so, he/she will then be invited to take part in a treatment and rehabilitation
schedule. If that is successful, the suspension will be lifted. For non-UK licence
holders a recommendation will be sent to the issuing authority that a rehabilitation
schedule was completed.

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CAP 562 Civil Aircraft Airworthiness Information and Procedures

Leaflet 15-6 Licensed Aircraft Maintenance Engineers –

Personal Responsibility When Medically Unfit
or Under the Influence of Drink or Drugs

(Previously issued as AN 47)

1 Introduction

1.1 The International Civil Aviation Organisation (ICAO) has introduced an amendment to
Annex 1 to the convention on international civil aviation which will have the effect of
extending certain standards and recommended practices to all licence holders. The
changes resulting from the amendment are concerned with medical fitness and the
use or abuse of intoxicating liquor, narcotics or drugs.
1.2 To implement these changes the Air Navigation No. 2 Order 1995 (ANO) introduced
two new Articles. Article 13(7) (now Article 18(7) of the Air Navigation Order 2005, as
amended) which prohibits the exercise of the privileges of an aircraft maintenance
engineer’s licence when the holder knows or suspects that their physical or mental
condition renders them unfit to exercise such privileges, and Article 13(8) (now Article
18(8) of the Air Navigation Order 2005, as amended) which prohibits the exercise of
licence privileges when the holder is under the influence of drink and/or drugs to such
an extent as to impair their capacity to exercise such privileges.
1.3 The Commission Regulation (EC) 2042/2003 (The Continuing Airworthiness
Regulation) entered into force on 29 November 2003 and introduced new
requirements applicable to licensed aircraft engineers in the U.K.
Annex III Part 66.B.500 to the Continuing Airworthiness Regulation requires a
competent authority to suspend, limit or revoke an aircraft maintenance licence in all
cases where it has clear evidence that the license holder has carried out maintenance
or issued a certificate of release to service when adversely affected by alcohol or
drugs.

2 General

2.1 An aircraft maintenance engineer’s licence authorises the holder, subject to any
conditions that may be specified on the licence, to issue various certificates relating
to aircraft maintenance. The process of issuing these certificates (Certificates of
Maintenance Review, Certificates of Release to Service and Certificates of Fitness for
Flight under the 'A' Conditions Flight Release Certificate) and similar certificates for
those aircraft detailed within Annex II of Commission Regulation (EC) 216/2008
require clear decisions to be made that directly affect the airworthiness of the aircraft
to which they relate. It follows that the quality of these decisions is directly influenced
by the physical and mental state of the certifier at the time of certification, and
whether or not they are subject to the adverse effects of drink and/or drugs.
2.2 The corporate management of all approved maintenance organisations are required
to review this Leaflet and implement suitable policies and procedures to make all
maintenance staff aware of them. The requirements of Articles 18(7) and 18(8) of the
Air Navigation Order (2005) as amended, in addition to an understanding of the
requirements placed upon the UK CAA within Part 66.B.500, fall on those who certify
the completion of maintenance. The guidance material contained in this Leaflet is

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equally applicable to all non-licensed personnel engaged in aircraft maintenance tasks

and in principle should be adopted throughout the aviation industry as a code of
practice. Organisations shall also take note of items in paragraph 3 which require their
participation in the areas concerned.
2.3 All persons to whom this Leaflet applies should be aware of the guidance material
contained herein. It is the responsibility of the individual concerned to ensure that
they do not report for duty or certify if they are genuinely unfit. Such persons should
also be aware of an organisation’s own internal policies and monitoring procedures to
verify the above.

3 Guidance

3.1 Fitness In most professions there is a duty of care by the individual to assess their
own fitness to carry out professional duties. This has been a legal requirement for
some time for doctors, flight crew members and air traffic controllers. Licensed
aircraft maintenance engineers are also now required by law to take a similar
professional attitude.
Cases of subtle physical or mental illness may not always be apparent to the individual
but as engineers often work as a member of a team any sub-standard performance
or unusual behaviour should be quickly noticed by colleagues or supervisors who
should notify management so that appropriate support and counselling action can be
taken. In particular, a decrease in mental fitness in many cases may be related to
stress from within the working environment or to the personal circumstances of the
individual. Instances of aggressive behaviour, vagueness and slippage of personal
standards (cleanliness, appearance etc.) may be indicative of more serious mental
issues. Such issues may bring into question the ability of the individual to be trusted
or to maintain the necessary levels of concentration to take appropriate decisions on
airworthiness matters.
3.2 Fatigue Tiredness and fatigue can adversely affect performance. Excessive hours
of duty and shift working, particularly with multiple shift periods or additional
overtime, can lead to problems. Whilst the safety management aspects of these
matters are being addressed through the UK Operators Technical Group individuals
should be fully aware of the dangers of impaired performance due to these factors
and of their personal responsibilities.
3.3 Stress Everyone is subject to various stresses in their life and work. Stress can
often be stimulating and beneficial but prolonged exposure to chronic stress (high
levels or differing stress factors) can produce strain and cause performance to suffer
allowing mistakes to occur.
Stress factors can be varied, physical – e.g. heat, cold, humidity, noise, vibration; they
can be due to ill-health or worries about possible ill-health; from problems outside the
workplace – e.g. bereavements, domestic upsets, financial or legal difficulties. A
stress problem can manifest itself by signs of irritability, forgetfulness, sickness
absence, mistakes, or alcohol or drug abuse. Management have a duty to identify
individuals who may be suffering from stress and to minimise workplace stresses.
Individual cases can be helped by sympathetic and skilful counselling which allows a
return to effective work and licensed duties.
3.4 Eyesight A reasonable standard of eyesight is needed for any aircraft engineer to
perform their duties to an acceptable degree. Many maintenance tasks require a
combination of both distance and near vision. In particular, such consideration must
be made where there is a need for the close visual inspection of structures or work

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related to small or miniature components. The use of glasses or contact lenses to

correct any vision problems is perfectly acceptable and indeed they must be worn as
prescribed. Frequent checks should be made to ensure the continued adequacy of
any glasses or contact lenses. In addition, colour discrimination may be necessary for
an individual to drive in areas where aircraft manoeuvre or where colour coding is
used, e.g. in aircraft wiring. Organisations should identify any specific eyesight
requirement and put in place suitable procedures to address these issues.
3.5 Hearing The ability to hear an average conversational voice in a quiet room at a
distance of 2 metres (6 feet) from the examiner is recommended as a routine test.
Failure of this test would require an audiogram to be carried out to provide an
objective assessment. If necessary, a hearing aid may be worn but consideration
should be given to the practicalities of wearing the aid during routine tasks demanded
of the individual.
It is important to remind employers of individuals working in areas of high ambient
noise of the requirement of the Noise at Work Regulations 1989 which require
employers to carry out assessments of noise levels within their premises and take
appropriate action where necessary.
3.6 Drug and Alcohol Abuse Drinking problems or the use of illicit or non-prescribed
drugs are unacceptable where aircraft maintenance safety is concerned and once
identified will lead to suspension of the licence or company authorisation and possibly
further licensing action being considered. The introduction of the Railways and
Transportation Safety Act 2003 set a blood alcohol limit of 80 mg/100 ml for personnel
involved in aircraft maintenance. CAP 562 Leaflet 15-5 describes the implications of
this act and should be referred to for further guidance.
3.7 Medication Any form of medication, whether prescribed by a doctor or purchased
over the counter and particularly if being taken for the first time, may have serious
consequences in the aviation maintenance environment unless three basic questions
can be answered satisfactorily:
a) Must I take medicines at all?
b) Have I given this particular medication a personal trial for at least 24 hours before
going on duty, to ensure that it will not have adverse effects on my ability to work
and make sound decisions?
c) Do I really feel fit for work?
Confirming the absence of adverse effects may need expert advice and General
Practitioners, Company Medical Officers and the Medical Division of the Civil Aviation
Authority are all available to assist in this matter. Common types of medication in use
and their effects are further described in Appendix 1.
3.8 Alcohol Alcohol has similar effects to tranquillisers and sleeping tablets and may
remain circulating in the blood for a considerable time, especially if taken with food.
It should be borne in mind that a person may not be fit to go on duty even eight hours
after drinking large amounts of alcohol. Individuals should therefore anticipate such
effects upon their next duty period. Special note should be taken of the fact that
combinations of alcohol and sleeping tablets, or anti-histamines, can form a highly
dangerous or even lethal combination.
3.9 Anaesthetics It should be remembered that following local, general, dental and
other anaesthetics, a period of time should elapse before returning to duty. This
period will vary depending upon individual circumstances, but may even extend to 24
or 48 hours. Any doubts should be resolved by seeking appropriate medical advice.

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4 Summary

4.1 The effects of illness, injury or medication on work performance are the direct
concern of the individual. Where there is doubt about the ability of an individual to
make sound technical decisions, the implications of Article 18(7) and 18(8) of the Air
Navigation Order (2005) as amended or Part 66.B.500 must be taken into account, i.e.
the individual must not exercise the privileges of their licence or authorisation whilst
unfit. While this Leaflet gives some guidance on the issues to be considered it cannot
be comprehensive. If individual licence holders or their managers have any doubt they
should consult the medical sources mentioned for advice. If there is difficulty in
obtaining this advice, the local CAA regional office or the CAA Personnel Licensing
Department should be contacted in the first instance and they in turn may seek
guidance from the CAA Medical Department. The contact details of the CAA regional
offices are provided in CAP 562 (CAAIP) under General Information.

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Appendix 1

(Previously issued as AN 47, Appendix 1)

1 The following are some of the types of medicine in common use which may impair
work performance. This list is not exhaustive and care should be taken in ensuring the
likely effects of any prescribed drug are adequately known before taking it.
a) Sleeping Tablets – These dull the senses, cause mental confusion and slow
reaction times. The duration of effect is variable from person to person and may
be unduly prolonged. Individuals should have expert medical advice before using
them;
b) Anti-depressants – These can depress the alerting system and have been a
contributory cause of mistakes leading to fatal accidents. A person should stop
work when starting anti-depressants and only return when it is clear that there are
no untoward side-effects. It is recommended that individuals seek medical advice
from their General Practitioner or appropriate medical specialist before returning to
work;
c) Antibiotics – Antibiotics (penicillin and the various mycins and cyclines) and sulpha
drugs may have short term or delayed effects which affect work performance.
Their use indicates that a fairly severe infection may well be present and apart from
the effects of these substances themselves, the side-effects of the infection will
almost always render an individual unfit for work;
d) Anti-histamine – Such drugs are widely used in cold cures and in the treatment of
hay fever, asthma and allergic skin conditions. Many easily obtainable nasal spray
and drop preparations contain anti-histamines. Most of this group of medicines
tend to make the taker feel drowsy. Their effect, combined with that of the
condition, will often prevent the basic three questions (paragraph 3.7 of the
Leaflet) from being answered satisfactorily. Admittedly very mild states of hay
fever etc., may be adequately controlled by small doses of anti-allergic drugs, but
a trial period to establish the absence of side effects is essential before going on
duty. When individuals are affected by allergic conditions which require more than
the absolute minimum of treatment and in all cases of asthma, one of the above
mentioned sources of advice should be consulted;
e) ‘Pep’ pills (e.g. containing Caffeine, Dexedrine, Benzedrine) used to maintain
wakefulness are often habit forming. Susceptibility to each drug varies from one
individual to another, but all of them can create dangerous over-confidence. Over-
dosage may cause headaches, dizziness and mental disturbances. The use of ‘pep’
pills whilst working cannot be permitted. If coffee is insufficient, you are not fit for
work;
f) Drugs for the relief of high blood pressure are proving to be very effective in
controlling this condition. However, antihypertensive agents all have some side
effects and should not be administered before adequate assessment of the need
for treatment. The prescribing practitioner should be able to advise on any side
effects to be considered;
g) Drugs when prescribed for Anti-malaria in normally recommended doses do not
usually have any adverse effects. However, the drug should be taken in good time
so that the question in paragraph 3.7 b) of the Leaflet can be answered;
h) Oral contraceptive tablets in the standard dose do not usually have adverse
effects, although regular supervision is required;

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CAP 562 Civil Aircraft Airworthiness Information and Procedures

i) ‘SUDAFED’ is the trade name of a preparation containing pseudo-ephedrine

hydrochloride. This may be prescribed by GPs for relief of nasal congestion. Side-
effects reported however are anxiety, tremor, rapid pulse and headache. The
preparation does not contain anti-histamines which could sedate and cause
drowsiness but the effects can nevertheless affect skilled performance. Sudafed,
therefore, is not a preparation to be taken when making engineering decisions or
performing licenced duties.
NOTE: Although the above are common groups of drugs, which may have adverse effects
on performance, it should be pointed out that many forms of medication, which
although not usually expected to affect efficiency may do so if the person concerned
is unduly sensitive to a particular drug. Therefore no drugs, medicines, or
combinations, should be taken before or during duty unless the taker is completely
familiar with the effects on him or her of the medication and the drugs or medicines
have specifically been prescribed for the individual alone. Again the sources of
advice mentioned earlier in this Leaflet should be consulted in cases of doubt.

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