Nachrichten für Luftfahrer 2012 Teil II (weicht ggf. von Druckversion ab)
EASA AD No : 2012-0011
adhesive could lead to flammable fluids to be inserted and/or retained in the
APU air intake duct.
This condition, if not detected and corrected, could lead to ignition of
flammable vapour or fluid in this area, which cannot be discounted over the
life of the aircraft.
For the reasons described above, this AD requires to perform a one-time
inspection of the APU Air Intake Duct and, depending on findings, the
accomplishment of the associated corrective actions depending on the type of
air intake duct installed.
Note:
AMM task 49-16-00-210-801-A has been updated through a Temporary
Revision, which was released on 01 September 2010 to include instructions
for the application of fire sealant compound for the in-service installation
procedure of the APU air intake duct inspection access cover.
Effective Date: 03 February 2012
Required action(s) Required as indicated, unless accomplished previously:
and Compliance
(1) Within 17 months after the effective date of this AD, inspect the APU air
Time(s):
intake duct and apply, depending on findings, the associated corrective
actions, as applicable (Repair procedure A or B) in accordance with the
instructions of Airbus Service Bulletin (SB) A380-49-8005.
(2) From the effective date of this AD, do not install on an aeroplane an APU
air intake duct as listed in SB A380-49-8005, Figure A-SBAAA – Sheet
01, unless it has been inspected and the associated corrective actions, as
applicable, have been accomplished, in accordance with the instructions
of Airbus SB A380-49-8005.
Ref. Publications: Airbus Service Bulletin A380-49-8005 Original issue dated 10 August 2011.
The use of later approved revisions of this document is acceptable for
compliance with the requirements of this AD.
Remarks : 1. If requested and appropriately substantiated, EASA can approve
Alternative Methods of Compliance for this AD.
2. This AD was posted on 09 December 2011 as PAD 11-133 for
consultation until 06 January 2012. The Comment Response Document
can be found at http://ad.easa.europa.eu.
3. Enquiries regarding this AD should be referred to the Safety Information
Section, Executive Directorate, EASA.
E-mail ADs@easa.europa.eu.
4. For any question concerning the technical content of the requirements in
this AD, please contact:
AIRBUS SAS - EIANA (Airworthiness Office),
Telephone: +33 562110253 ; Fax:+33 562 110 307.
E-mail: account.airworth-A380@airbus.com and/or
Nicolas.Cordeau@airbus.com and/or Sandra.Cuiec@airbus.com.
EASA Form 110 Page 2/2
Lufttüchtigkeitsanweisung Luftfahrt-Bundesamt
T23 LTA-Sachgebiet
38144 Braunschweig
D-2012-066 Fax: +49-531-2355-725
email: ad@lba.de
AGUSTA Datum der Bekanntgabe: 24.01.2012
Betroffenes Luftfahrtgerät:
Art des Luftfahrtgerätes: Drehflügler
Inhaber der Musterzulassung: Agusta S.p.A.
Hersteller: AgustaWestland S.p.A.
Muster: A109
Baureihen: A109A, A109AII und A109C
Werknummern: Alle
Gerätenummer: EASA.R.005
Revisionsstand:
Originalausgabe
Airworthiness Directive der ausländischen Behörde:
EASA AD 2011-0236 (Correction: 23.01.2012) vom 14.12.2011
Betrifft:
(ATA 32) Landing Gear - Main Landing Gear (MLG) Actuator Bracket Attachment Bolts - Replacement / Inspection
Maßnahmen und Fristen:
Detaillierte Informationen über die durchzuführenden Maßnahmen sind der genannten EASA Airworthiness
Directive und der genannten technischen Mitteilung des Herstellers zu entnehmen. Alle erforderlichen Maßnahmen
zur Abstellung des technischen Mangels müssen ordnungsgemäß, vollständig und innerhalb der vorgesehenen
Fristen auf Basis der genannten Bezugsdokumente durchgeführt werden. Alle Abweichungen von den Maßnahmen
und Fristen dieser Lufttüchtigkeitsanweisung bedürfen der vorherigen Zustimmung durch das Luftfahrt-Bundesamt.
Alle anzuwendenden Fristen sind der genannten EASA Airworthiness Directive zu entnehmen. Die Laufzeit aller
anzuwendenden Fristen beginnt mit dem Datum der Inkraftsetzung der genannten EASA Airworthiness Directive.
Diese Lufttüchtigkeitsanweisung entspricht hinsichtlich der durchzuführenden Maßnahmen und Fristen der
EASA AD 2011-0236 (Correction: 23.01.2012) vom 14.12.2011.
Zugehörige technische Dokumente:
Hinweis: Die Anwendung von nachfolgenden Ausgaben bzw. Revisionsständen der genannten zugehörigen technischen Dokumente ist zulässig, wenn dies nach
der Airworthiness Directive der ausländischen Behörde ausdrücklich gestattet ist oder wenn diese von der ausländischen Behörde in Bezug auf die referenzierte
Airworthiness Directive genehmigt worden sind.
AgustaWestland Bollettino Tecnico 109-133 vom 04.11.2011
Die sofortige Vollziehung dieses Bescheides wird gemäß § 80 Absatz 2 Satz 1 Nr. 4 der Verwaltungsgerichtsordnung (VwGO) angeordnet.
Begründung
Durch die vorgenannten Mängel ist die Lufttüchtigkeit des Luftfahrtgerätes derart beeinträchtigt, dass es nach Ablauf der genannten Fristen nur in Betrieb genom-
men werden darf, wenn die angeordneten Maßnahmen ordnungsgemäß durchgeführt worden sind. Im Interesse der Sicherheit des Luftverkehrs, das in diesem Fall
das Interesse des Adressaten am Aufschub der angeordneten Maßnahmen überwiegt, ist es erforderlich, die sofortige Vollziehung dieser Lufttüchtigkeitsanweisung
anzuordnen.
Rechtsbehelfsbelehrung:
Gegen diese Verfügung kann innerhalb eines Monats nach Bekanntgabe Widerspruch eingelegt werden. Der Widerspruch ist schriftlich oder zur Niederschrift beim
Luftfahrt-Bundesamt, Hermann-Blenk-Str. 26, 38108 Braunschweig einzulegen. Ein eventueller Widerspruch hat keine aufschiebende Wirkung. Das Verwaltungsge-
richt Braunschweig, Am Wendentor 7, 38100 Braunschweig, kann auf Antrag nach § 80 Abs. 5 VwGO die aufschiebende Wirkung jedoch ganz oder teilweise wie-
derherstellen bzw. anordnen.
D-2012-066 Seite 1 von 1 046/2012
EASA AD No: 2011-0236
EASA AIRWORTHINESS DIRECTIVE
AD No.: 2011-0236
[Correction: 23 January 2012]
Date: 14 December 2011
Note: This Airworthiness Directive (AD) is issued by EASA, acting in accordance with
Regulation (EC) No 216/2008 on behalf of the European Community, its Member States and
of the European third countries that participate in the activities of EASA under Article 66 of
that Regulation.
This AD is issued in accordance with EC 1702/2003, Part 21A.3B. In accordance with EC 2042/2003 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
[EC 2042/2003 Annex I, Part M.A.303] or agreed with the Authority of the State of Registry [EC 216/2008, Article 14(4) exemption].
Type Approval Holder’s Name : Type/Model designation(s) :
Agusta S.p.A A109 helicopters
TCDS Number: EASA.R.005
Foreign AD: Not applicable
Supersedure: None
Landing Gear – Main Landing Gear (MLG) Actuator Bracket
ATA 32
Attachment Bolts – Replacement / Inspection
Manufacturer(s): AgustaWestland S.p.A.
Applicability: A109A, A109AII and A109C helicopters, all serial numbers.
Reason: A case of collapsed right-hand (RH) MLG has recently occurred on an
A109AII helicopter. The results of the technical investigation revealed that the
MLG collapsed due to fatigue fracture of the MLG actuator bracket
attachment bolts, caused by incorrect tightening of the bolts. The same Part
Number (P/N) NAS624H8 and P/N NAS624H10 bolts are also installed on
the MLG of A109A and A109C helicopters.
This condition, if not detected and corrected, could lead to further events of
MLG collapse, which could result in damage to the helicopter and injury to its
occupants.
To address this condition, AgustaWestland issued Bolletino Tecnico (BT)
109-133, which requires replacement of MLG actuator bracket attachment
bolts (with the same bolt P/N), reduces the tolerance of the torque value to be
applied when tightening the bolts and nuts of the MLG actuator bracket,
introduces repetitive inspections of the bolts at reduced intervals (from 600
flight hours) and, depending on findings, replacement of the bolts (with the
same bolt P/N).
For the reasons described above, this AD requires installation of new bolts,
using the correct torque value, repetitive inspections at the new intervals and,
depending on findings, replacement of bolts (with the same bolt P/N).
This AD has been republished to correct a typographical error in paragraph
EASA Form 110 Page 1/2
EASA AD No: 2011-0236
(3) of the RACT section of the AD, where an incorrect “part” number of
AgustaWestland BT 109-133 was quoted for the replacement of the bolts.
Effective Date: 28 December 2011
Required Action(s) Required as indicated, unless accomplished previously:
and Compliance
(1) Within 100 flight hours (FH) or 5 months, whichever occurs first after the
Time(s):
effective date of this AD, replace the RH and left-hand (LH) MLG
actuator bracket attachment bolts P/N NAS624H8 and P/N NAS624H10
applying the correct torque value, in accordance with the instructions of
part I of the AgustaWestland BT 109-133.
(2) Within 100 FH or 150 FH, as applicable, depending on the inspection
program adopted by the operator, or 12 months, whichever occurs first
after replacement of the MLG actuator bracket attachment bolts as
required by paragraph (1) of this AD, and, thereafter, at intervals not to
exceed 100 FH or 150 FH, as applicable, depending on the inspection
program adopted by the operator, or 12 months, whichever occurs first,
inspect the RH and LH MLG actuator bracket attachment bolts P/N
NAS624H8 and P/N NAS624H10, in accordance with the instructions of
part II of the AgustaWestland BT 109-133.
(3) If, during any inspection as required by paragraph (2) of this AD, a
discrepancy is identified on at least one of the bolts, RH or LH, before
next flight, replace all bolts, RH or LH, as applicable, with serviceable
parts and apply the correct torque value, in accordance with the
instructions of part I of AgustaWestland BT 109-133.
(4) Replacement of bolts, as required by paragraph (3) of this AD, does not
constitute terminating action for the repetitive inspections required by
paragraph (2) of this AD.
Ref. Publications: AgustaWestland Bollettino Tecnico 109-133 dated 04 November 2011.
The use of later approved revisions of this document is acceptable for
compliance with the requirements of this AD.
Remarks : 1. If requested and appropriately substantiated, EASA can approve
Alternative Methods of Compliance for this AD.
2. This AD was posted on 11 November 2011 as PAD 11-120 for
consultation until 09 November 2011. No comments were received
during the consultation period.
3. Enquiries regarding this AD should be referred to the Safety Information
Section, Executive Directorate, EASA. E-mail: ADs@easa.europa.eu .
4. For any question concerning the technical content of the requirements in
this AD, please contact:
AgustaWestland S.p.A. Customer Support
Via del Gregge, 100 - 21015 Lonate Pozzolo (VA) – Italy
Telephone + 39 0331-664396 ; Fax: + 39 0331-664680
E-mail: custserv@agustawestland.com.
EASA Form 110 Page 2/2
Lufttüchtigkeitsanweisung Luftfahrt-Bundesamt
T23 LTA-Sachgebiet
38144 Braunschweig
D-2012-067 Fax: +49-531-2355-725
email: ad@lba.de
GENERAL ELECTRIC Datum der Bekanntgabe: 25.01.2012
Betroffenes Luftfahrtgerät:
Art des Luftfahrtgerätes: Flugmotor
Inhaber der Musterzulassung: General Electric Company
Hersteller: General Electric Company
Muster: CT7-8
Baureihen: CT7-8, CT7-8A, CT7-8A1, CT7-8E, CT7-8F5
Werknummern: Baureihe CT7-8: Alle Werknummern
Baureihe CT7-8A: Werknummern bis einschließlich 947565
Baureihe CT7-8A1: Werknummern bis einschließlich 530017
Baureihe CT7-8E: Werknummern bis einschließlich 953068 und 953070 bis
953072.
Baureihe CT7-8F5: Werknummern bis einschließlich 731005 und 731007,
731008, 817021 und 817022.
Gerätenummer: 7042, EASA.IM.E.010
Revisionsstand:
Originalausgabe
Airworthiness Directive der ausländischen Behörde:
FAA AD 2011-19-03 - Amdt. 39-16808
Betrifft:
(ATA 72) Turboshaft Engine - Axis-A Shaft Assembly Accessory Gearbox Oil Slinger Nut - Installation
Maßnahmen und Fristen:
Detaillierte Informationen über die durchzuführenden Maßnahmen sind der genannten FAA Airworthiness Directive
und der genannten technischen Mitteilung des Herstellers zu entnehmen. Alle erforderlichen Maßnahmen zur
Abstellung des technischen Mangels müssen ordnungsgemäß, vollständig und innerhalb der vorgesehenen Fristen
auf Basis der genannten Bezugsdokumente durchgeführt werden. Alle Abweichungen von den Maßnahmen und
Fristen dieser Lufttüchtigkeitsanweisung bedürfen der vorherigen Zustimmung durch das Luftfahrt-Bundesamt.
Alle anzuwendenden Fristen sind der genannten FAA Airworthiness Directive zu entnehmen. Die Laufzeit aller
anzuwendenden Fristen beginnt mit dem Datum der Inkraftsetzung der genannten FAA Airworthiness Directive.
Diese Lufttüchtigkeitsanweisung entspricht hinsichtlich der durchzuführenden Maßnahmen und Fristen der
FAA AD 2011-19-03 - Amdt. 39-16808.
Zugehörige technische Dokumente:
Hinweis: Die Anwendung von nachfolgenden Ausgaben bzw. Revisionsständen der genannten zugehörigen technischen Dokumente ist zulässig, wenn dies nach
der Airworthiness Directive der ausländischen Behörde ausdrücklich gestattet ist oder wenn diese von der ausländischen Behörde in Bezug auf die referenzierte
Airworthiness Directive genehmigt worden sind.
General Electric Service Bulletin CT7-8 S/B 72-0033 Revision 1 vom 28.04.2011
Die sofortige Vollziehung dieses Bescheides wird gemäß § 80 Absatz 2 Satz 1 Nr. 4 der Verwaltungsgerichtsordnung (VwGO) angeordnet.
Begründung
Durch die vorgenannten Mängel ist die Lufttüchtigkeit des Luftfahrtgerätes derart beeinträchtigt, dass es nach Ablauf der genannten Fristen nur in Betrieb genom-
men werden darf, wenn die angeordneten Maßnahmen ordnungsgemäß durchgeführt worden sind. Im Interesse der Sicherheit des Luftverkehrs, das in diesem Fall
das Interesse des Adressaten am Aufschub der angeordneten Maßnahmen überwiegt, ist es erforderlich, die sofortige Vollziehung dieser Lufttüchtigkeitsanweisung
anzuordnen.
Rechtsbehelfsbelehrung:
Gegen diese Verfügung kann innerhalb eines Monats nach Bekanntgabe Widerspruch eingelegt werden. Der Widerspruch ist schriftlich oder zur Niederschrift beim
Luftfahrt-Bundesamt, Hermann-Blenk-Str. 26, 38108 Braunschweig einzulegen. Ein eventueller Widerspruch hat keine aufschiebende Wirkung. Das Verwaltungsge-
richt Braunschweig, Am Wendentor 7, 38100 Braunschweig, kann auf Antrag nach § 80 Abs. 5 VwGO die aufschiebende Wirkung jedoch ganz oder teilweise wie-
derherstellen bzw. anordnen.
D-2012-067 Seite 1 von 1 040/2012
[Federal Register Volume 76, Number 193 (Wednesday, October 5, 2011)]
[Rules and Regulations]
[Pages 61559-61561]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 2011-25654]
––––––––––––––––––––––––––––––––––
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2011-0392; Directorate Identifier 2011-NE-12-AD; Amendment 39-16808;
AD 2011-19-03]
RIN 2120-AA64
Airworthiness Directives; General Electric Company (GE) CT7-8, CT7-8A, CT7-8A1, CT7-8E,
and CT7-8F5 Turboshaft Engines
AGENCY: Federal Aviation Administration (FAA), DOT.
ACTION: Final rule.
––––––––––––––––––––––––––––––––––
SUMMARY: We are adopting a new airworthiness directive (AD) for the products listed above. This
AD was prompted by four reports of unrecoverable engine stalls, during hover in a left-roll attitude.
This AD requires the installation of an accessory gearbox (AGB) axis-A oil slinger nut to the axis-A
shaft assembly. We are issuing this AD to prevent an unrecoverable engine stall, leading to a
helicopter forced landing or accident.
DATES: This AD is effective November 9, 2011.
The Director of the Federal Register approved the incorporation by reference of a certain
publication listed in the AD as of November 9, 2011.
ADDRESSES: For service information identified in this AD, contact GE-Aviation, M/D Rm. 285,
One Neumann Way, Cincinnati, OH 45215; phone: 513-552-3272; e-mail: geaeaoc@ge.com. You
may review copies of the referenced service information at the FAA, Engine & Propeller Directorate,
12 New England Executive Park, Burlington, MA. For information on the availability of this material
at the FAA, call 781-238-7125.
Examining the AD Docket
You may examine the AD docket on the Internet at http://www.regulations.gov; or in person at
the Docket Management Facility between 9 a.m. and 5 p.m., Monday through Friday, except Federal
holidays. The AD docket contains this AD, the regulatory evaluation, any comments received, and
other information. The address for the Docket Office (phone: 800-647-5527) is Document
Management Facility, U.S. Department of Transportation, Docket Operations, M-30, West Building
Ground Floor, Room W12-140, 1200 New Jersey Avenue, SE., Washington, DC 20590.
1
FOR FURTHER INFORMATION CONTACT: Walter Meibaum, Aerospace Engineer, Engine &
Propeller Directorate, FAA, 12 New England Executive Park, Burlington, MA 01803; phone: 781-
238-7119; fax: 781-238-7199; e-mail: walter.meibaum@faa.gov.
SUPPLEMENTARY INFORMATION:
Discussion
We received four reports of GE CT7-8 series turboshaft helicopter engines experiencing
unrecoverable engine stalls, during hover in a left-roll attitude. Investigation revealed that during a
prolonged left roll, excessive return oil from the AGB may return to the A-sump and exceed the
sump's scavenging capability. The sump then floods, leading to over-heated oil, which preheats the
air entering the engine's compressor. This preheated air causes inlet thermal distortion. This
condition, if not corrected, could result in an unrecoverable engine stall, leading to a helicopter forced
landing or accident. We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR part 39 to
include an AD that would apply to the specified products. That NPRM published in the Federal
Register on May 2, 2011 (76 FR 24407). That NPRM proposed to require the installation of an AGB
axis-A oil slinger nut to the axis-A shaft assembly.
Comments
We gave the public the opportunity to participate in developing this AD. We received no
comments on the NPRM published in the Federal Register on May 2, 2011 (76 FR 24407).
Since we issued the NPRM published in the Federal Register on May 2, 2011 (76 FR 24407), GE
issued a revision to the service bulletin we are incorporating by reference in this AD. The revision
includes new information in the procedure required to torque the oil slinger nut. This AD
incorporates by reference, GE Aircraft Engines CT7-8 Turboshaft Engine Service Bulletin No. CT7-8
S/B 72-0033, Revision 1, dated April 28, 2011.
Also since we issued the NPRM published in the Federal Register on May 2, 2011 (76 FR
24407), we discovered that in the applicability paragraph, we inadvertently omitted engine serial
number 953071. We corrected that omission in paragraph (c) (4) by changing ''CT7-8E, engine S/Ns
953068 and below, and S/Ns 953070 and 953072'' to ''CT7-8E, engine S/Ns 953068 and below, and
S/Ns 953070 through 953072''.
Conclusion
We reviewed the relevant data and determined that air safety and the public interest require
adopting the AD as proposed except for minor editorial changes. We have determined that these
minor changes are consistent with the intent that was proposed in the NPRM published in the Federal
Register on May 2, 2011 (76 FR 24407) for correcting the unsafe condition.
Costs of Compliance
We estimate that this AD will affect 80 engines installed on helicopters of U.S. registry. We also
estimate that it will take about one work-hour per engine to perform the actions required by this AD,
and that the average labor rate is $85 per work-hour. Required parts will cost about $700 per engine.
Based on these figures, we estimate the total cost of the AD to U.S. operators to be $62,800.
2
Authority for This Rulemaking
Title 49 of the United States Code specifies the FAA's authority to issue rules on aviation safety.
Subtitle I, section 106, describes the authority of the FAA Administrator. Subtitle VII: Aviation
Programs, describes in more detail the scope of the Agency's authority.
We are issuing this rulemaking under the authority described in Subtitle VII, part A, subpart III,
Section 44701: ''General requirements.'' Under that section, Congress charges the FAA with
promoting safe flight of civil aircraft in air commerce by prescribing regulations for practices,
methods, and procedures the Administrator finds necessary for safety in air commerce. This
regulation is within the scope of that authority because it addresses an unsafe condition that is likely
to exist or develop on products identified in this rulemaking action.
Regulatory Findings
This AD will not have federalism implications under Executive Order 13132. This AD 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.
For the reasons discussed above, I certify that this AD:
(1) Is not a ''significant regulatory action'' under Executive Order 12866,
(2) Is not a ''significant rule'' under DOT Regulatory Policies and Procedures (44 FR 11034,
February 26, 1979),
(3) Will not affect intrastate aviation in Alaska, and
(4) Will not have a significant economic impact, positive or negative, on a substantial number of
small entities under the criteria of the Regulatory Flexibility Act.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation safety, Incorporation by reference, Safety.
Adoption of the Amendment
Accordingly, under the authority delegated to me by the Administrator, the FAA amends 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. The FAA amends § 39.13 by adding the following new airworthiness directive (AD):
3
AIRWORTHINESS DIRECTIVE
FAA
www.faa.gov/aircraft/safety/alerts/
Aviation Safety
www.gpoaccess.gov/fr/advanced.html
2011-19-03 General Electric Company: Amendment 39-16808; Docket No. FAA-2011-0392;
Directorate Identifier 2011-NE-12-AD.
Effective Date
(a) This AD is effective November 9, 2011.
Affected ADs
(b) None.
Applicability
(c) This AD applies to the following General Electric Company (GE) turboshaft engines:
(1) CT7-8, all engine serial numbers (S/Ns).
(2) CT7-8A, engine S/Ns 947565 and below.
(3) CT7-8A1, engine S/Ns 530017 and below.
(4) CT7-8E, engine S/Ns 953068 and below, and S/Ns 953070 through 953072.
(5) CT7-8F5, engine S/Ns 731005 and below, and S/Ns 731007, 731008, 817021, and 817022.
Unsafe Condition
(d) This AD was prompted by four reports of unrecoverable engine stalls, during hover in a left-
roll attitude. We are issuing this AD to prevent an unrecoverable engine stall, leading to a helicopter
forced landing or accident.
Compliance
(e) Comply with this AD at the next engine shop visit, the next 1,500-hour helicopter inspection,
or before operation after next engine installation, whichever occurs first.
Installation of Accessory Gearbox (AGB) Axis-A Oil Slinger Nut
(f) Install the AGB axis-A oil slinger nut to the axis-A shaft assembly. Use Accomplishment
Instructions, paragraphs 3.A. through 3.C. of GE Aircraft Engines CT7-8 Turboshaft Engine Service
Bulletin No. CT7-8 S/B 72-0033, Revision 1, dated April 28, 2011, to do the installation.
Previous Credit
(g) An oil slinger nut installation performed before the effective date of this AD using GE
Aircraft Engines CT7-8 Turboshaft Engine Service Bulletin No. CT7-8 S/B 72-0033, dated February
11, 2011, satisfies the installation requirements of this AD.
4
Alternative Methods of Compliance (AMOCs)
(h) The Manager, Engine Certification Office, FAA, has the authority to approve AMOCs for
this AD, if requested using the procedures found in 14 CFR 39.19.
Related Information
(i) For more information about this AD, contact Walter Meibaum, Aerospace Engineer, Engine
& Propeller Directorate, FAA, 12 New England Executive Park, Burlington, MA 01803; phone: 781-
238-7119; fax: 781-238-7199; e-mail: walter.meibaum@faa.gov.
Material Incorporated by Reference
(j) You must use the following service information to do the actions required by this AD, unless
the AD specifies otherwise. The Director of the Federal Register approved the incorporation by
reference (IBR) under 5 U.S.C. 552(a) and 1 CFR part 51 of the following service information on the
date specified:
(1) GE Aircraft Engines CT7-8 Turboshaft Engine Service Bulletin No. CT7-8 S/B 72-0033,
Revision 1, dated April 28, 2011, approved for IBR November 9, 2011.
(2) For service information identified in this AD, contact GE-Aviation, M/D Rm. 285, One
Neumann Way, Cincinnati, OH 45215; phone: 513-552-3272; e-mail: geaeaoc@ge.com.
(3) You may review copies of the service information at the FAA, Engine & Propeller
Directorate, 12 New England Executive Park, Burlington, MA. For information on the availability of
this material at the FAA, call 781-238-7125.
(4) You may also review copies of the service information that is incorporated by reference at the
National Archives and Records Administration (NARA). For information on the availability of this
material at an NARA facility, call 202-741-6030, or go to http://www.archives.gov/federal_register/
code_of_federal_regulations/ibr_locations.html.
Issued in Burlington, Massachusetts, on September 8, 2011.
Peter A. White,
Manager, Engine & Propeller Directorate,
Aircraft Certification Service.
5
