AIRWORTHINESS APPROVAL NOTE NO 27757 Addendum 1
APPLICANT: Airbus UK
AIRCRAFT TYPE: Concorde Variant 102
REGISTRATION NO: G-BOAF CONSTRUCTOR’S NO: 100-016
OPERATOR: British Airways
INSTALLER: British Airways
DESIGN ORGANISATION: Airbus France
CERTIFICATE CATEGORY: Transport Category (Passenger)
Return to Service flight
1.1 The basic AAN was raised to recommend to issue of a Special Category AAN for the purpose of crew training.
1.2 This AAN has been raised for CAA to formally approve the modification package applied to the Concorde fleet to enable the Certificates of Airworthiness to be reinstated and the aircraft returned to service.
2. Modification Definition
2.1 The following modifications have been applied to the subject aircraft:
Modification 1905 – Installation of Fuel Tank Liner.
This modification introduces Viton impregnated Kevlar liners into certain areas of fuel tanks 1, 4, 5, 6, 7 & 8. The purpose of the liner is to moderate the fuel leak from damage to the lower wing surface by tyre debris, secondary debris or any other debris such as wheel tie bolts.
Modification 1909 – Landing Gear Bay Electrical Harness Armouring.
This modification introduces electrical harness armouring to the cables within the main landing gear bay. The purpose of this modification is to further reduce the risk of damage to electrical cables in the harness by tyre or other debris in order to reduce the possibility of producing spark ignition sources.
Modification 1915 – Brake Fan Inhibit at Take-Off.
This modification introduces a Aircraft Flight Manual change to inhibit the brake fan circuits prior to take-off roll and landing. The purpose of this modification is to prevent the production of spark ignition sources from the 115 Volt brake fan supply cables in the event of damage by tyre or other debris.
Modification 1917 – New Michelin “N.Z.G.” Tyre.
This modification introduces a new radial tyre design which is resistant to FOD and produces tread debris of reduced size and mass compared to the original Concorde tyres. The purpose of this modification is to provide a tyre that, in the event of failure resulting in tread separation, will reduce the size of the potential tyre debris projecting toward the lower wing. This modification also modifies the anti skid control unit.
Modification 1921 – Miscellaneous Changes to theWater Deflector.
This modification deletes the retention cables installed under modification 1869 and modifies the profile of the deflector.
2.2 The following modifications are applicable to G-BOAF only:
Modification 1911 – Data Gathering.
This modification introduces the instrumentation and data gathering package installed on G-BOAF for approximately the first 50 flights.
Modification 1925 – Installation of Provisional Liner Supports.
This modification is raised to cover the additional supports and holes which were installed or drilled on G-BOAF and are not covered by modification 1905.
2.3 The above referenced modifications have been approved by DGAC-F.
2.4 The following Service Bulletins are also approved by DGAC-F and CAA-UK and are subject to Mandatory action under CAA Emergency Airworthiness Directive 001-09-
Modification 1905 Service Bulletin SST 57-078, 57-080 and 57-082 all aircraft except G-BOAF.
Modification 1905 Service Bulletin SST 57-078, 57-079, 57-080 and 57-081 for G-BOAF only.
Modification 1909 Service Bulletin SST 32-107.
Modification 1917 Service Bulletin SST 32-109.
Modification 1921 Service Bulletin SST 32-110.
2.5 Although not part of the return to service package but embodied on the subject aircraft is modification 1919 which introduces improvements to spar 72.
3. Approval Procedures
This modification approval/validation has been carried out in accordance with Concorde Airworthiness Procedures.
4. Basis of Validation/Approval
4.1 CAA Validation/Approval Basis for the Modification
Concorde TSS Standards together with CRI 01.01.
4.2 CAA Design Requirements for Certificate of Airworthiness
Special Condition as defined in CRI 01.01.
4.3 Environmental Requirements
4.4 Design Requirements Associated With Operational Approvals
5. Compliance with the Basis of Certification/Validation/Approval
5.1 Compliance with the Certification/Validation Basis for the Modification
Return to Service Certification Program document reference 543.0507/01 refers.
5.2 Compliance with Design Requirements for Certificate of Airworthiness
Return to Service Certification Program document reference 543.0507/01 refers.
5.3 Compliance with Environmental Requirements
This modification is assessed as having no adverse effect on the aircraft noise, and the status of the aircraft relative to the noise legislation is unaffected. The existing noise certificate, if any, remains valid.
5.4 Compliance with Design Requirements Associated With Operational Approvals
Compliance has been established with the design requirements which are a pre-requisite to approval of the associated operation. This finding of compliance with the design requirements does not signify that any operational approval has been granted.
5.5 Required (Amendments To) Manuals and Other Documents Including Mandatory
5.5.1 Concorde Type 1 Variant 102 Flight Manual reference CSD/FM/2 has been amended by the introduction of the following Temporary Revisions TR 355, 358, 359, 360, 361, 362, 363, 364 and 3126.96.36.199 The MMEL is amended to add the Tyre Deflation Detection System as a NO GO item.
An additional limitation is also introduced such that the system is serviceable up to the commencement of take-off run.
MMEL list item 01-32-02-07 and Dispatch Deviation Procedure item 02-32-02-32.7 refers.
5.5.3 The Crew, Maintenance and Weight and Balance Manuals are also to be amended.
5.5.4 TCDS BA10 is to be raised to issue 4 to amend the Certification Basis to reference the Special Conditions.
6. Conditions Affecting This Approval
6.1 All placards specified by the manufacturer/modification must be installed. Limitations, and conditions defined in the modification/manufacturer’s documentation, and the
Flight Manual Supplement must be observed.
6.2 The compatibility of this modification with other previously approved modifications, installed on the particular aircraft, must be verified by the installer. Where the potential for interactions between modifications exists, the advice of the CAA shall be sought.
6.3 Certain operational approvals require that the aircraft and/or systems comply with specified design requirements. Where this AAN records compliance with those design requirements this shall not be taken as acceptance by the CAA of compliance with the relevant operational requirements, for which further justification may be required.
7. Continued Airworthiness
The influence of the modification on Airworthiness Directive, Service Bulletin eligibility and other data must be considered and the publications monitored accordingly. The maintenance programme for the aircraft should include reference to this material additional to the original design.
This aircraft G-BOAF being the first to embody the modifications to be approved under this AAN, has been surveyed by the CAA.
In the particular areas examined during the survey the modified aircraft was found to conform with the standard recorded by this AAN.
9. Authorisation of Release to Service
In addition to the actions required by the procedures for release to service following maintenance or modification, the following actions must be completed prior to signing the
Certificate of Release to Service:
a. All actions and ground test procedures specified by the modification instructions must be completed satisfactorily.
b. It must be verified that the documents or amendments to documents, and the placards defined under Section 5.5 above are as specified, including any changes specified under Section 8 above.
It is hereby recommended that the design standard of the subject aircraft or any other Concorde
Variant 102 to the same design standard is eligible for certification in the Transport Category
D J Clement
For the Civil Aviation Authority
Date 5 September 2001