Nachrichten für Luftfahrer 2018 Teil 2 (weicht ggf. von Druckversion ab)
[4910-13-U]
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39 [66 FR 17345 3/30/2001]
[Docket No. 2001-CE-14-AD; Amendment 39-12164; AD 2001-06-17]
RIN 2120-AA64
Airworthiness Directives; Cessna Aircraft Company Models 172R and 172S Airplanes
AGENCY: Federal Aviation Administration, DOT.
ACTION: Final rule ; request for comments.
SUMMARY: This amendment adopts a new airworthiness directive (AD) that applies to certain Cessna
Aircraft Company (Cessna) Models 172R and 172S airplanes. This AD requires a one-time inspection for
proper engine idle speed and fuel control mixture setting and adjustment, as necessary. This AD also requires
incorporating engine operating procedures into the pilots operating handbook (POH) and FAA-approved
airplane flight manual (AFM). This AD is the result of reports of rough engine operation because of an over-
rich fuel mixture (improper fuel flow settings). The actions specified by this AD are intended to detect and
correct such improper fuel flow settings, which could result in rough engine operation or engine stoppage. This
over-rich fuel mixture also contributes to the engine not restarting during flight when using published in-flight
restart procedures.
DATES: This AD becomes effective on April 20, 2001.
The Federal Aviation Administration (FAA) must receive any comments on this rule on or before May 18,
2001.
ADDRESSES: Submit comments in triplicate to FAA, Central Region, Office of the Regional Counsel,
Attention: Rules Docket No. 2001-CE-14-AD, 901 Locust, Room 506, Kansas City, Missouri 64106.
You may examine information related to this AD at FAA, Central Region, Office of the Regional Counsel,
Attention: Rules Docket No. 2001-CE-14-AD, 901 Locust, Room 506, Kansas City, Missouri 64106.
FOR FURTHER INFORMATION CONTACT: Mr. Paul Pendleton, Aerospace Engineer, Wichita Aircraft
Certification Office, FAA, 1801 Airport Road, Mid-Continent Airport, Wichita, Kansas 67209; telephone: (316)
946-4143; facsimile: (316) 946-4407.
SUPPLEMENTARY INFORMATION:
Discussion
What events have caused this AD? The FAA has received several reports of improper engine fuel flow
settings on Cessna Models 172R and 172S airplanes. These improper settings could prevent the engine from
operating at idle speed when the pilot reduces power (i.e., landing approach, power off stalls, etc.). An over-
rich fuel mixture is a reason why the engine may not operate at idle speed. This over-rich fuel mixture also
contributes to the engine not restarting during flight when using published in-flight restart procedures.
The current pilot operating handbook (POH) and FAA-approved airplane flight manual (AFM) procedures
for the Cessna Models 172R and 172S airplanes do not address the pilot bringing the throttle back to the hard
idle stop (throttle full aft). The POH/AFM also does not address emergency engine restart procedures to
enable engine startup if a rich fuel mixture exists.
What are the consequences if the condition is not corrected? This condition, if not corrected, could
result in rough engine operation or engine stoppage. The over-rich fuel mixture also contributes to the engine
not restarting during flight when using published in-flight restart procedures.
FAA's Determination and an Explanation of the Provisions of this AD
What has FAA decided? The FAA has reviewed all available information and determined that:
1
- the unsafe condition referenced in this document exists or could develop on other Cessna Models 172R
and 172S airplanes of the same type design;
- these airplanes should be inspected for proper engine idle speed and fuel control mixture setting, the
engine idle speed or fuel control mixture setting should be adjusted as necessary, and engine operating
procedures should be incorporated into the POH/AFM; and
- AD action should be taken in order to correct this unsafe condition.
Is there service information that applies to this subject? Cessna has issued Service Bulletin SB01-11-02,
dated March 5, 2001. This service bulletin:
- includes procedures for inspecting the engine idle speed; and
- specifies pilot operating procedure changes.
What does this AD require? This AD requires a one-time inspection for proper engine idle speed and fuel
control mixture setting and adjustment, as necessary. This AD also requires incorporating engine operating
procedures into the POH/AFM.
Procedures for accomplishing the inspection are included in the AD. We are not utilizing the procedures
included in Cessna Service Bulletin SB01-11-02, dated March 5, 2001.
Why is FAA not requiring the actions specified in the service bulletin? The inspection procedures in
Cessna Service Bulletin SB01-11-02 agree with the service manual procedures. The procedures we are
including in this AD agree with the Cessna factory production procedures. After examining these procedures,
FAA has determined that:
- the procedures in the service bulletin and service manual procedures are too restrictive for a pilot to
accomplish in the field without using specialized equipment (portable electric tachometer);
- the pilot should be able to accomplish the inspection for proper engine idle speed and fuel control
mixture setting; and
- the inspection procedures in this AD allow the pilot to both easily accomplish the inspection and address
the safety intent of this AD.
Will I have the opportunity to comment prior to the issuance of the rule? Because the unsafe condition
described in this could result in rough engine operation or engine stoppage, FAA finds that notice and
opportunity for public prior comment are impracticable. Therefore, good cause exists for making this
amendment effective in less than 30 days.
Comments Invited
How do I comment on this AD? Although this action is in the form of a final rule and was not preceded by
notice and opportunity for public comment, we invite your comments on the rule. You may submit whatever
written data, views, or arguments you choose. You need to include the rule’s docket number and submit your
comments in triplicate to the address specified under the caption “ADDRESSES." We will consider all
comments received on or before the closing date specified above. We may amend this rule in light of
comments received. Factual information that supports your ideas and suggestions is extremely helpful in
evaluating the effectiveness of the AD action and determining whether we need to take additional rulemaking
action.
Are there any specific portions of the AD that FAA wants me to address? The FAA specifically invites
comments on the overall regulatory, economic, environmental, and energy aspects of the rule that might suggest
a need to modify the rule. You may examine all comments we receive before and after the closing date of the
rule in the Rules Docket. We will file a report in the Rules Docket that summarizes each FAA contact with
the public that concerns the substantive parts of this AD.
We are reviewing the writing style we currently use in regulatory documents, in response to the
Presidential memorandum of June 1, 1998. That memorandum requires federal agencies to communicate more
clearly with the public. We are interested in your comments on whether the style of this document is clear, and
any other suggestions you might have to improve the clarity of FAA communications that affect you. You can
get more information about the Presidential memorandum and the plain language initiative at
http://www.plainlanguage.gov.
How can I be sure FAA receives my comment? If you want us to acknowledge the receipt of your
comments, you must include a self-addressed, stamped postcard. On the postcard, write "Comments to Docket
No. 2001-CE-14-AD." We will date stamp and mail the postcard back to you.
2
Regulatory Impact
Does this AD impact various entities? These regulations will not have a substantial direct effect on the
States, on the relationship between the national Government and the States, or on the distribution of power and
responsibilities among the various levels of government. Therefore, FAA has determined that this final rule
does not have federalism implications under Executive Order 13132.
Does this AD involve a significant rule or regulatory action? The FAA has determined that this
regulation is an emergency regulation that must be issued immediately to correct an unsafe condition in aircraft,
and is not a significant regulatory action under Executive Order 12866. It has been determined further that this
action involves an emergency regulation under DOT Regulatory Policies and Procedures (44 FR 11034,
February 26, 1979). If it is determined that this emergency regulation otherwise would be significant under
DOT Regulatory Policies and Procedures, a final regulatory evaluation will be prepared and placed in the Rules
Docket (otherwise, an evaluation is not required). A copy of it, if filed, may be obtained from the Rules
Docket.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation safety, Safety.
Adoption of the Amendment
Accordingly, under the authority delegated to me by the Administrator, the Federal Aviation Administration
amends part 39 of the Federal Aviation Regulations (14 CFR part 39) as follows:
PART 39 - AIRWORTHINESS DIRECTIVES
1. The authority citation for part 39 continues to read as follows:
Authority: 49 U.S.C. 106(g), 40113, 44701.
§ 39.13 [Amended]
2. FAA amends § 39.13 by adding a new airworthiness directive (AD) to read as follows:
3
AIRWORTHINESS DIRECTIVE
Aircraft Certification Service U.S. Department
Washington, DC of Transportation
Federal Aviation
Administration
We post ADs on the internet at "av-info.faa.gov"
The following Airworthiness Directive issued by the Federal Aviation Administration in accordance with the provisions of Title 14 of the Code of Federal Regulations (14 CFR) part 39, applies to an
aircraft model of which our records indicate you may be the registered owner. Airworthiness Directives affect aviation safety and are regulations which require immediate attention. You are cautioned
that no person may operate an aircraft to which an Airworthiness Directive applies, except in accordance with the requirements of the Airworthiness Directive (reference 14 CFR part 39, subpart
39.3).
2001-06-17 CESSNA AIRCRAFT COMPANY: Amendment 39-12164; Docket No. 2001-CE-14-AD.
(a) What airplanes are affected by this AD? This AD applies to Models 172R and 172S, all serial
numbers, that are certificated in any category.
(b) Who must comply with this AD? Anyone who wishes to operate any of the above airplanes must
comply with this AD.
(c) What problem does this AD address? The actions specified by this AD are intended to detect and
correct an over-rich fuel mixture (improper fuel flow settings), which could result in rough engine operation or
engine stoppage. This over-rich fuel mixture also contributes to the engine not restarting during flight when
using published in-flight restart procedures.
(d) What must I do to address this problem? To address this problem, you must accomplish the following
actions:
4
Action Compliance Time Special Instructions
(1) Accomplish one of the following Within the next 10 hours time-in- The owner/operator holding at
inspections for proper engine idle speed service (TIS) after April 20, least a private pilot certificate
and fuel control mixture setting: 2001(the effective date of this as authorized by section 43.7 of
AD), unless already the Federal Aviation
(i) Pilot Procedure: Accomplish the
accomplished. Regulations (14 CFR 43.7) may
inspection with the engine oil
accomplish the inspection
temperature between 120 and 150
specified in paragraph (d)(1)(i)
degrees Fahrenheit (F). Assure that the
of this AD. Make an entry into
engine idle setting is between 575 and
the aircraft records showing
625 revolutions per minute (RPM) and
compliance with this portion of
the mixture setting will produce a
the AD in accordance with
minimum 10 RPM rise and a maximum
section 43.9 of the Federal
50 RPM rise with the throttle at the hard
Aviation Regulations (14 CFR
ground idle stop. Screw the vernier
43.9). You may need to
mixture out slowly counterclockwise to
accomplish seasonal
obtain the RPM rise.
adjustments of the engine idle
(ii) Mechanic Procedure: Accomplish speed setting. These seasonal
the inspection with the engine oil adjustments should not be
temperature between 120 and 150 included in your already
degrees F. Assure that the fuel mixture established 12-month scheduled
setting is between 575 and 625 RPM adjustments.
and the mixture setting will produce a
minimum 10 RPM rise and a maximum
20 RPM rise with the throttle at the hard
ground idle stop. Screw the vernier
mixture out slowly counterclockwise.
The reason the limits are different than
the pilot procedure is that the mechanic
needs to establish a more accurate RPM
indicator than the airplanes engine RPM
gage. You will most likely need to use
an electric tachometer to verify speed
changes.
(2) If, during any inspection required by Accomplish the adjustment (if If you have to adjust the servo
this AD, proper engine idle speed and required) prior to further flight more than twice over a 12-
fuel control mixture setting cannot be after the inspection required by month period, obtain the next
met, accomplish the following: paragraph (d)(1) of this AD. course of action from the FAA
Reinspect within 25 hours TIS at the address referenced in
(i) Adjust the fuel servo. This
after the fuel servo adjustment. paragraph (f) of this AD. We
adjustment or any replacement must be
recommend you use an
accomplished by an appropriately-rated
electronic strobe to verify RPM
mechanic or at an appropriately-rated
settings when making any
repair station; and
adjustment.
(ii) Repeat the inspection specified in
paragraph (d)(1) of this AD.
5
Action Compliance Time Special Instructions
(3) Add the following information to the Within the next 10 hours TIS The owner/operator holding at
end of page 3-20, Section 3 Emergency after April 20, 2001 (the effective least a private pilot certificate
Procedures of the Cessna 172R or 172S date of this AD), unless already as authorized by section 43.7 of
Pilot's Operating Handbook (POH) and accomplished. the Federal Aviation
FAA-approved Airplane Flight Manual Regulations (14 CFR 43.7) may
(AFM): insert the information into the
POH as specified in paragraph
"IDLE POWER ENGINE
(d)(3) of this AD. You may
ROUGHNESS
insert a copy of this AD into
An excessively rich idle fuel flow may the appropriate sections of the
cause low speed engine roughness POH to comply with this
during flight. During most in-flight low action. Make an entry into the
engine speeds (power off stalls, aircraft records showing
approach to landing, etc.), the mixture compliance with portion of the
control is normally in the full-rich AD in accordance with section
position. However, to improve engine 43.9 of the Federal Aviation
roughness (caused by an improperly Regulations (14 CFR 43.9).
adjusted fuel servo) during low engine
speeds while in flight, you should rotate
the vernier mixture control (leaning of
fuel mixture). You may also have to
lean the fuel mixture if this low engine
speed results in power loss and you need
to restart the engine during flight. In all
cases, you should land the airplane at the
nearest airport for repairs if low speed
engine roughness requires you to adjust
the fuel mixture control to improve
engine operation."
(4) Insert the following information into Within the next 10 hours TIS The owner/operator holding at
the applicable Cessna Pilot's Operating after April 20, 2001 (the effective least a private pilot certificate
Handbook (POH) and FAA-approved date of this AD), unless already as authorized by section 43.7 of
Airplane Flight Manual (AFM): accomplished. the Federal Aviation
Regulations (14 CFR 43.7) may
"NORMAL PROCEDURES (Before
insert the information into the
Takeoff) item 13. Throttle: 1. Verify
POH as specified in paragraph
smooth engine operation at idle speed of
(d)(4) of this AD. You may
575 to 625 RPM. 2. 1000 RPM or
insert a copy of this AD into
LESS"
the appropriate sections of the
POH to comply with this
action. Make an entry into the
aircraft records showing
compliance with portion of the
AD in accordance with section
43.9 of the Federal Aviation
Regulations (14 CFR 43.9).
6
(e) Can I comply with this AD in any other way? You may use an alternative method of compliance or
adjust the compliance time if:
(1) Your alternative method of compliance provides an equivalent level of safety; and
(2) The Manager, Wichita Aircraft Certification Office (ACO), approves your alternative. Submit
your request through an FAA Principal Maintenance Inspector, who may add comments and then send it to the
Manager, Wichita ACO.
Note: This AD applies to each airplane identified in paragraph (a) of this AD, regardless of whether it has
been modified, altered, or repaired in the area subject to the requirements of this AD. For airplanes that have
been modified, altered, or repaired so that the performance of the requirements of this AD is affected, the
owner/operator must request approval for an alternative method of compliance in accordance with paragraph
(e) of this AD. The request should include an assessment of the effect of the modification, alteration, or repair
on the unsafe condition addressed by this AD; and, if you have not eliminated the unsafe condition, specific
actions you propose to address it.
(f) Where can I get information about any already-approved alternative methods of compliance? Contact
Mr. Paul Pendleton, Aerospace Engineer, Wichita Aircraft Certification Office, FAA, 1801 Airport Road, Mid-
Continent Airport, Wichita, Kansas 67209; telephone: (316) 946-4143; facsimile: (316) 946-4407.
(g) What if I need to fly the airplane to another location to comply with this AD? The FAA can issue a
special flight permit under sections 21.197 and 21.199 of the Federal Aviation Regulations (14 CFR 21.197 and
21.199) to operate your airplane to a location where you can accomplish the requirements of this AD.
(h) When does this amendment become effective? This amendment becomes effective on April 20, 2001.
FOR FURTHER INFORMATION CONTACT: Mr. Paul Pendleton, Aerospace Engineer, Wichita Aircraft
Certification Office, FAA, 1801 Airport Road, Mid-Continent Airport, Wichita, Kansas 67209; telephone: (316)
946-4143; facsimile: (316) 946-4407.
Issued in Kansas City, Missouri, on March 23, 2001.
David R. Showers, Acting Manager, Small Airplane Directorate, Aircraft Certification Service.
7
Lufttüchtigkeitsanweisung Luftfahrt-Bundesamt
- Sachgebiet T23 -
D-2011-077R2 38144 Braunschweig
EASA AD 2012-0053R1 vom 27.11.2018 Fax: +49-531-2355-5298
email: ad@LBA.de
AIRBUS 30.11.2018
Betroffenes Luftfahrtgerät:
Art des Luftfahrtgerätes: Flugzeug
Inhaber der Musterzulassung: AIRBUS S.A.S.
Hersteller: Airbus (vormals Airbus Industrie)
Muster: A330, A340
Baureihen: A330-201, A330-202, A330-203, A330-223, A330-223F, A330-243, A330-243F,
A330-301, A330-302, A330-303, A330-321, A330-322, A330-323, A330-341,
A330-342, A330-343,
A340-211, A340-212, A340-213, A340-311, A340-312, A340-313, A340-541,
A340-542, A340-642 und A340-643
Werknummern: Alle
Ausgenommen sind A330 Flugzeuge, an denen die Airbus Modifikation (Mod)
207165 oder Mod 207649 bei der Flugzeug-Herstellung eingerüstet worden ist
oder die gemäß der in der EASA AD 2012-0053R1 genannten jeweils
anwendbaren "Modification SB" modifiziert worden sind.
Ebenfalls ausgenommen sind A340 Flugzeuge, die gemäß der in der EASA AD
2012-0053R1 genannten jeweils anwendbaren "Modification SB" modifiziert
worden sind.
Gerätenummer: 2849, 2850, EASA.A.004, EASA.A.015
Revisionsstand:
Diese LTA ersetzt D-2011-077R1 vom 03.04.2012
Airworthiness Directive der ausländischen Behörde:
EASA AD 2012-0053R1 vom 27.11.2018
Genannte Airworthiness Directives unter dieser Rubrik, die nicht durch die EASA herausgegeben worden sind,
wurden durch die EASA über die Entscheidung Nr. 02/2003 übernommen und sind somit ebenfalls Airworthiness
Directives der EASA.
Die genannte Airworthiness Directive wird im Luftfahrt-Bundesamt unter der Nummer 2011-077R2 geführt.
Betrifft:
(ATA 32) Landing Gear - Main and Center Landing Gear Bogie Pivot Pins - Inspection / Modification
Anmerkungen:
Gemäß der EU Verordnung Nr. 1321/2014, Anhang I, Teil M, Unterabschnitt C, M.A.301 5.i) und M.A.303 dür-
fen Luftfahrzeuge nach dem in der Lufttüchtigkeitsanweisung angegebenen Termin nur in Betrieb genom-
men werden, wenn die angeordneten Maßnahmen ordnungsgemäß durchgeführt worden sind.
Die Europäische Agentur für Flugsicherheit (EASA) hat die oben referenzierte Lufttüchtigkeitsanweisung
EASA AD 2012-0053R1 vom 27.11.2018 herausgegeben oder per Entscheidung Nr. 02/2003 übernommen.
Gemäß § 14 Abs. 2 der Betriebsordnung für Luftfahrtgerät (LuftBO) sind diese Lufttüchtigkeitsanweisun-
gen direkt in der Bundesrepublik Deutschland gültig und bedürfen keiner Umsetzung durch das Luftfahrt-
Bundesamt.
Mit Hilfe dieser Übersichtsseite veröffentlicht das Luftfahrt-Bundesamt ebenfalls die über § 14 Abs. 2 direkt
gültigen Lufttüchtigkeitsanweisungen der EASA in den Nachrichten für Luftfahrer und im Internet unter
www2.LBA.de/LTAs/. Dieser Service dient reinen Informationszwecken und liegt keinem Verwaltungsver-
fahren zu Grunde. Rechtsmittel sind damit ausgeschlossen.
D-2011-077R2 Seite 1 von 1 554/2018
EASA AD No.: 2012-0053R1
Airworthiness Directive
AD No.: 2012-0053R1
Issued: 27 November 2018
Note: This Airworthiness Directive (AD) is issued by EASA, acting in accordance with Regulation
(EU) 2018/1139 on behalf of the European Union, its Member States and of the European third
countries that participate in the activities of EASA under Article 129 of that Regulation..
This AD is issued in accordance with Regulation (EU) 748/2012, Part 21.A.3B. In accordance with Regulation (EU) 1321/2014 Annex I, Part M.A.301, the
continuing airworthiness of an aircraft shall be ensured by accomplishing any applicable ADs. Consequently, no person may operate an aircraft to which
an AD applies, except in accordance with the requirements of that AD, unless otherwise specified by the Agency [Regulation (EU) 1321/2014 Annex I,
Part M.A.303] or agreed with the Authority of the State of Registry [Regulation (EU) 2018/1139, Article 71 exemption].
Design Approval Holder’s Name: Type/Model designation(s):
AIRBUS A330 and A340 aeroplanes
Effective Date: Revision 1: 04 December 2018
Original issue: 13 April 2012
TCDS Numbers: EASA.A.004, EASA.A.015
Foreign AD: Not applicable
Revision: This AD revises EASA AD 2012-0053 dated 30 March 2012. The original issue of
this AD superseded EASA AD 2011-0040 dated 08 March 2011.
ATA 32 – Landing Gear – Main and Center Landing Gear Bogie Pivot Pins –
Inspection / Modification
Manufacturer(s):
Airbus (formerly Airbus Industrie)
Applicability:
Airbus A330-201, A330-202, A330-203, A330-223, A330-223F, A330-243, A330-243F, A330-301,
A330-302, A330-303, A330-321, A330-322, A330-323, A330-341, A330-342 and A330-343
aeroplanes, all manufacturer serial numbers (MSN), except those that have embodied Airbus
modification (mod) 207165 or mod 207649 in production, or have been modified in service through
the applicable modification SB; and
Airbus A340-211, A340-212, A340-213, A340-311, A340-312, A340-313,A340-541, A340-542,
A340-642 and A340-643 aeroplanes, all MSN, except those that have been modified in service
through the applicable modification SB.
TE.CAP.00110-008 © European Aviation Safety Agency. All rights reserved. ISO9001 Certified. Page 1 of 5
Proprietary document. Copies are not controlled. Confirm revision status through the EASA-Internet/Intranet.
An agency of the European Union
EASA AD No.: 2012-0053R1
Definitions:
For the purpose of this AD, the following definitions apply:
The applicable inspection SB: Airbus Service Bulletin (SB) A330-32-3240 Revision 02, or SB
A340-32-4281 Revision 01, or SB A340-32-5096 Revision 01, as applicable.
The applicable modification SB: Airbus SB A330-32-3290, or SB A330-32-3291, or SB A340-32-4315,
or SB A340-32-4316, as applicable.
Reason:
During removals of A330/340 main landing gear (MLG) Bogie Beams and A340-500/600 centre
landing gear (CLG) bogie beams, cracks in the bogie pivot pin were found. Investigations indicated
that these findings were the result of material heating, caused by friction between bogie pivot pin
and bush, leading to chrome detachment and stress corrosion cracking.
This condition, if not detected and corrected, could lead to collapse of the MLG or CLG, possibly
resulting in damage to the aeroplane and/or injury to occupants.
As a precautionary measure, EASA published AD 2011-0040 to require a one-time inspection of the
MLG (all types of A330 and A340 aeroplanes) and CLG (A340-500/600 aeroplanes only) to detect
degradation or cracking of the bogie pivot pin, as applicable to aeroplane model, accomplishment of
applicable corrective action(s) and the reporting of inspections results.
After that AD was issued, several operators reported finding chrome detachment or chrome
dragging on bogie pivot pins. New cases of cracks were also reported. It was confirmed as well that,
due to similar design, the enhanced MLG bogie pivot pin (introduced by Airbus mod 54500) could
also be affected by this condition.
Prompted by these findings, Airbus developed an inspection programme for A340-500 and -600
aeroplanes, and published the applicable inspection SB. Consequently, EASA issued AD 2012-0053,
retaining the requirements of EASA AD 2011-0040, which was superseded, to require repetitive
inspections of the MLG and CLG bogie pivot pins and bushes, and, depending on findings,
accomplishment of applicable corrective action(s).
Since that AD was issued, Airbus developed mod 207165 and mod 207649, introducing a new bogie
pivot pin for certain MLG. Aeroplanes equipped with this new bogie pivot pin, are not subject to the
repetitive inspections of this AD. Airbus published the applicable modification SB, providing
instructions.
For the reason described above, this AD is revised accordingly by reducing the Applicability, and
introduces reference to that modification as optional terminating action. In addition, this revised AD
deletes the reporting requirements. Finally, this AD also contains some editorial changes to meet
the current AD writing standards, without affecting the technical content or requirements.
TE.CAP.00110-008 © European Aviation Safety Agency. All rights reserved. ISO9001 Certified. Page 2 of 5
Proprietary document. Copies are not controlled. Confirm revision status through the EASA-Internet/Intranet.
An agency of the European Union
