Airworthiness Approval Note

AIRWORTHINESS APPROVAL NOTE NO: 20082
APPLICANT: F R Aviation Ltd
AIRCRAFT TYPE: Falcon 20 Series F
REGISTRATION NO: G-FRAA
CONSTRUCTOR'S NO: 385
Approval of Falcon 20 Series F s/n 385 G-FRAA
for Issue of a UK Certificate of Airworthiness
including the Omnibus Modification FRAH-122
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Introduction
F R Aviation Ltd have made application for the issue of a UK C of A for Falcon 20 Series F Serial
No.385 registered G-FRAA.
This aircraft has been acquired by the applicant from the USA and as such did not have embodied
the modifications required to show compliance with UK Special Conditions.
The aircraft which was first constructed in 1978 was delivered in a "green" condition for interior and
equipment installation at Little Rock Airmotive to the customers specifications and operated in the
USA under Registration Number N118R.
Details of the customer fit modifications are recorded on the FAA Form 337 and STC information
which the applicant has provided in the Omnibus Modification No FRAH-122.
When acquired by F R Aviation the aircraft was taken to Europe Falcon Service at le Bourget
France, which is the Modification Maintenance and Repair organisation operated by the
Manufacturer, Avion Marcel Dassault - Breguet Aviation (AMD-BA), for all Falcon aircraft. At
EFS le Bourget the aircraft completed a modification programme which included the embodiment of
the manufacturers modifications raised for compliance with UK Special Conditions. Some new
modifications offering alternative means of compliance with UK Special Conditions, and other
modifications related to the new role of the aircraft required by the applicant, have also been
embodied, using the agreed arrangements between the French Authority (DGAC) and CAA for
approval of modifications by the authority of the country of manufacture, for aircraft designed and
manufactured in France.
The UK Certification Basis is already defined because Falcon 20 Series E and Series F aircraft have
previously been Type Certificated in the UK(UK Type Certificate No FA12 and AAN No 14178 for
the 20E (June 1975) and AAN No 16535 for the 20F (October 1979) refer).
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2.
Build Standard
The basic build standard of Falcon 20 aircraft as defined in the French Type Certification process
(see Fiche No 103) is acceptable to CAA.
The applicant has made a comparison, using data supplied from AMD-BA sources, of the build
standard differences at original delivery between the subject aircraft s/n 385 and the first UK
Certificated Falcon 20s/n 304. (Note s/n 304 is a Falcon 20E but the major differences between20E
and 20F are known to, and accepted by, the CAA for UK Type Certification). The list of
differences is provided in F R Aviation Ltd Report No FRAA/1/87. The basic build standard as
defined above is considered acceptable to CAA.
The modifications to the basic build standard after the aircraft left the manufacturer have been
provided by the applicant in the form of an Omnibus Modification No FRAH-122, which list the
post manufacturing changes embodied in the USA under the authority of Supplemental Type
Certificates and Forms 337 approved through the FAA certification processes. Apart from two
major items these modifications are all cabin and flight deck interior changes, and specified
customer avionics equipment, some of which have now been replaced by the interior and equipment
modifications embodied for the applicant at EFS le Bourget. The aircraft is fitted with two General
Electric CF 700-2D-2 main engines which have previously been CAA validated, and at the time of
delivery from EFS le Bourget to F R Aviation the aircraft had recorded 3971 flight hours and
2582.landings.
The two major differences which occur on this aircraft are the installation of Aeronca Thrust
Reversers and the installation of a SolarT62-T39 APU neither of which have previously been CAA
approved on Falcon 20 aircraft.
The thrust reverser and APU installations are the subject of detailed assessment by CAA which will
not be completed by end of January 1987. It will be acceptable for a C of A to be issued for the
subject aircraft with the thrust reversers and APU mechanically and electrically deactivated until
these assessments are completed. An addendum to this AAN will be issued when use of these
features is satisfactorily approved.
The build standard of this aircraft at the time of its certification on the UK Register comprises the
above mentioned basic build standard and post manufacture interior and equipment modifications
amended as relevant by the applicants specified interior and equipment changes and embodiment of
the UK Special Conditions compliance modifications defined and approved below.
3.
Compliance with UK Special Conditions
The applicable UK Special Conditions are contained in the document entitled Avions Marcel
Dassault Fan Jet Falcon (Mystere 20) Series E UK Special Conditions Issue 1 dated 16 August
1976. That document, which relates to the Falcon 20 Series E is also applicable to the Falcon
20Series F with minor differences as recorded in AAN No 16535.
The UK Special Conditions document presents a list of AMD-BA modifications additional to the
basic build standard which are required for UK Certification.
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The aircraft manufacturer, AMD-BA raised an omnibus Modification No M1800 (in 1974/75)
which included all the detail modifications raised by AMD-BA and approved by the French
Authorities DGAC on behalf of the CAA, to show compliance with the UK Special Conditions.
The applicant arranged for the subject aircraft to have these modifications embodied in the AMDBA facility Europe Falcon Service at le Bourget France. The list of modifications defined in the UK
Special Conditions and AAN No 16535relating to the Falcon 20F, subject to a number of items
indicated below where alternative means of compliance have been agreed, are presented in F R
Aviation Report No FRAA/1/87. Certification that these modifications have been embodied is given
by Europe Falcon Service in EFS Report No.714/87 which is endorsed by the Bureau Veritas
department of the French Authorities.
CAA accepts the Bureau Veritas certification covering the embodiment of the required UK Special
Condition modifications as listed in EFS Report No 714/87.
The items for which alternative means of compliance have been accepted are as follows.
(1)
Item 6.4. Flight Data Recorder (originally M1793A/B).
The applicant is installing an alternative Flight Data Recorder by EFS Mod 2082/FRAH115 (see below), and M1739 A/B is therefore not directly applicable to this aircraft.
(2)
Item 7.2 Double Generator Failure Warning-Blinking Light (originally M1794).
The applicant is installing an alternative double generator failure warning flashing attention
getter facility by EFS Mod.2089/FRAH-121and M1794 is therefore not directly applicable
to this aircraft.
(3)
Item 8.3. Crew Interphone System (originally M1748)
The applicant is installing an alternative Audio Control System by EFS Mod 2083/FRAH116, (see below) and the original ModificationM1748 relating to the modification threshold
for the voice operated interphone switching system is not directly applicable to this aircraft.
4.
Additional Modifications
(1)
A number of additional avionics modifications have been embodied on this aircraft for the
applicants purposes. These modifications have been certified as embodied by EFS and
Bureau Veritas in EFS Report No 714/87. Where relevant the associated F R Aviation
Modification Number and related CAA Avionics AAN Number are also listed.
(a)
AMD-BA Modification M 2228 - Installation of an Omega antenna in the
horizontal stabiliser (FRAH-114 AAN No.20035).
(b)
EFS 2081 - Installation of TRACOR Omega - VLF (FRAH-114 AAN No 20035).
(c)
EFS 2082 - Installation of Fairchild L800 Flight Data Recorder (FRAH-115 AAN
20036).
(d)
EFS 2083 - Installation of BAKER AM1045 Audio Mixer Boxes (FRAH-116 AAN
20037)
(e)
EFS 2084 - Installation of COSSOR IFF 2720 Transponder (FRAH-117 AAN
20038).
(f)
EFS 2085 - Installation of KING 950 H.F. equipment (FRAH-118 AAN 20039).
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(g)
EFS 2087 - Installation of dual COLLINS ARC 159 VHF equipment (FRAH-119
AAN 20040).
CAA accepts the Bureau Veritas certification covering the embodiment of these
modifications.
Where necessary specific CAA approval of the separate
modifications is given in the AAN's referred to above.
(2)
In addition to the above modifications two other changes which affect the UK Flight
Manual have been requested by the applicant.
(a)
AMD-BA Service Bulletin No 363 allows an increase in zero fuel weight from
8,900 kg to 9980 kg. The substantiation for this change has been received and will
be accepted by CAA subject to receipt by CAA of a document which will
satisfactorily show that Falcon 20E and F aircraft can be cleared by comparison
with the margins of safety achieved for the Falcon 20G aircraft at a higher zero fuel
weight.
(Note: final acceptance of this change will not be given until the proposed
substantiation document is received probably late in 1987 the present Flight Manual
relates to 8900 kg.
(b)
The original bird impact compliance for UK Certification (Item3.1) resulted in a
limitation of 320 kt iAS below 8000 ft. As a result of discussion between CAA and
AMD-BA, CAA have agreed that the Falcon 20 windshield may be cleared on the
basis of JAR25.631. AMD-BA have shown in document DTM 16285 dated9
January 1987 that the JAR requirement can be met at a VMO of350 kt IAS below
8000 ft.
These two changes, which are acceptable to CAA provide for a VMO in the UK
Flight Manual of 350 kt IAS from sea level up to the altitude where the MMO of
0.85 IMN becomes more limiting, and the Flight Manual and Placards relate to this
standard.
5.
Electrical Load Analysis
An Electrical Load Analysis prepared by Europe Falcon Service, dated January 1987 and referring
to S/No.254, taking into account the relevant new modifications to this aircraft has been provided
and is satisfactory.
6.
Compliance with Airworthiness Directives, Consigne de Navigabilite, CAA
Airworthiness Notices and Service Bulletins
F R Aviation Report FRAA/1/87 provides a satisfactory statement confirming that compliance has
been shown with all relevant French Consigne de Navigabilite, FAA ADs, CAA Additional
Directives and CAA Airworthiness Notices on this aircraft. The above Report also provides a
statement of the AMD-BA Service Bulletins embodied on this aircraft since manufacture.
7.
Equipment - Air Navigation Order
Satisfied by the provision of equipment and markings and placards which are either approved by or
are acceptable to CAA.
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8.
Physical Inspection
As a used aircraft s/n 385 and its past operating and maintenance history have been inspected and
investigated by CAA and have been found to be generally satisfactory.
A 300 hour and 6 monthly maintenance check to approved schedule MS/FanjetFalcon/3 at an agreed
point of entry has been completed. The Structural Audit programme will come into effect in due
course. The aircraft condition, maintenance status etc., is set out in G-FRAA Final Report
Reference FRAA/1/87 compiled by the applicant. This report is acceptable. In accordance with Para
2 above the Thrust Reversers and the APU have been rendered inoperative pending formal clearance
of the units and systems concerned.
9.
Interior Configuration
The cabin interior arrangements for this aircraft can be changed depending on whether the applicant
wishes to use the long range cabin fuel tank installation.
The basic Transport Passenger Category interior configuration is for two pairs of fore and aft facing
single seats in the forward half of cabin and a sideways facing settee and fore and aft facing single
seats in the aft part of the cabin. The details are shown in Cabin Configuration Drawing Number
734-8121 provided by the applicant.
The seats and seat belts installed in the aircraft are:a)
Five 3240 Custom Products Chairs to TSO C39 with American Safety 449470-1 belts Part
No.501010-DT18B28-2257.
b)
One 3 Place Falcon Jet Corp Side facing Settee to STC SA 2481 SW with American Safety
501401-6 belts Part No 501441-446-2257 as set out in FR Aviation Configuration drawing
734-8121.
When the cabin fuel tanks are installed in place of the settee and two single seats in the aft part of
the cabin the four single seats in the forward part of the cabin remain in place. Details are shown in
the Aerial Work Configuration Drawing Number 111-006 provided by the applicant.(Note AAN No
19940 covers the installation and use of the long range cabin fuel tanks and the alternative Aerial
Work Certification Category).
The cabin materials have been tested to FAR 25.853 and the results of the tests are presented in
Report FRAA/1/87.
10.
Radio and Avionic Installation
The radio and avionic installation in s/n 385 -G-FRAA consists of:King
Collins
Collins
Collins
Collins
Collins
Collins
Cossor
Sperry
Collins
KHF950
VHF20A
AN/ARC159(V)1
VIR30A
DF206
DME40
TDR90ATC
IFF2720
PRIMUS 400
ALT50
(DUP)
(DUP)
(DUP)
(DUP)
(DUP)
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HF/RT Communication
VHF Communication
UHF Communication
ILS, VOR and Marker
ADF
DME
Transponder
IFF/SSR
Weather Radar
Radio Altimeter
Tracor
Baker
11.
TA7900
M1042
Omega/VLF
Intercommunication
Flight Manual
The limitations procedures and performance data applicable to the operation of this aircraft are
contained in the CAA approved Flight Manual document number DTM918 which has had the
following change sheets and supplements added to cover certain of the above listed modifications to
this aircraft, vis Revisions 1 through 4, FR Aviation Change Sheets1/1, 3/2, 7/1 and 8/1 with FR
Aviation supplements 1/1 and 3/2.
In addition, because the drag chute installation has been removed from the aircraft and, until such
time as the thrust reversers are approved and operative, Change Sheets 9 through 15 at Issue 1
relating to icy and low friction runway operations are applicable.
12.
Flight Testing
A CAA series airworthiness flight test has been carried out on this aircraft on 28/1/87 and the results
are presented in CAA Flight Test Report No FTR/6282/S.
13.
Approval
This aircraft and any other Falcon 20 Series F aircraft to the same or an essentially similar basic
build standard and which have been modified in the areas concerned to provide compliance with the
applicable UK Special Conditions by the same means, is eligible for certification in the Transport
Category (Passenger).
This
AAN
should
be
read
in
conjunction
with
the
following
AAN
Numbers20035/20036/20037/20038/20039/20040/20081 dealing with Avionic Installations, all of
which form an integral part of the approval standard and certification data for Falcon 20 Series F s/n
385 G-FRAA.
Falcon 20 Series F Serial No.356 G-FRAB has been assessed in terms of build standard and post
manufacture modifications and can be considered as Series to s/n 385 G-FRAA.
A S McClymont
......................................................
For the Civil Aviation Authority
Date 5th February 1987
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