Nachrichten für Luftfahrer 2018 Teil 2 (weicht ggf. von Druckversion ab)
EASA AD No.: 2018-0066
Reason:
Investigation prompted by an EC 225 helicopter accident revealed involvement of a failure of a
second stage planet gear of the Main Gearbox (MGB).
It was determined that one of the two types of planet gear used in the epicyclic module of the MGB
is subject to higher outer race contact pressures and therefore has a greater susceptibility to
spalling and cracking.
As one of a number of measures developed to ensure safe operation of the EC 225 LP/AS 332 L2
fleet, this type of planet gear has been permanently removed from service.
AH is reviewing its entire range of helicopters in regard to this particular issue.
On AS 332 L, L1, C and C1 helicopters there are two types of planet gear part numbers used in the
epicyclic module of the MGB, one of which is subject to higher outer race contact pressures. The
production of this type of planet gear was stopped since 1990; nevertheless, although unlikely, few
of these parts might still be in service or kept in stock.
As a precautionary measure, AH issued the ASB applicable to AS 332 L, L1, C and C1 helicopters
requesting the identification of the installed planet gears and, depending on the finding, their
replacement along with the prohibition to install any MGB equipped with the affected planet gears.
The ASB also provides updated inspection intervals and particle assessment criteria, aligning the
AS 332 L, L1, C and C1 particle inspection to the standards set for EC 225 LP/AS 332 L2 helicopters.
For the reasons described above, this AD requires repetitive inspections of the MGB magnetic plugs,
identification of the affected planet gear assemblies installed in the MGB and, depending on
findings, the precautionary replacement of the affected planet gear assemblies.
Required Action(s) and Compliance Time(s):
Required as indicated, unless accomplished previously:
Inspections / Analyses:
(1) Within 10 flight hours (FH) after the effective date of this AD and, thereafter, at intervals not to
exceed 10 FH, inspect the MGB particle detectors in accordance with the instructions of Section
3 of the ASB.
(2) If, during any inspection as required by paragraph (1) of this AD, particles are detected, before
next flight, analyse the particles in accordance with the instructions of Appendix 4.A. of the
ASB.
Corrective Action(s):
(3) If, during any analysis as required by paragraph (2) of this AD, particles are detected which
exceed the limits specified in Appendix 4.A. of the ASB, before next flight, accomplish the
applicable corrective action(s) in accordance with the instructions of Appendix 4.A. of the ASB.
TE.CAP.00110-006 © European Aviation Safety Agency. All rights reserved. ISO9001 Certified. Page 2 of 3
Proprietary document. Copies are not controlled. Confirm revision status through the EASA-Internet/Intranet.
An agency of the European Union
EASA AD No.: 2018-0066
Replacement:
(4) Within 50 FH after the effective date of this AD, identify the P/N of each second stage planet
gear assembly installed on the MGB and replace each affected MGB with a serviceable MGB in
accordance with the instructions of Section 3.B.4 of the ASB.
Terminating Action:
(5) None.
Parts Installation:
(6) From the effective date of this AD, do not install on any helicopter an affected MGB. It is
allowed to install a serviceable MGB, provided that, following installation, it is inspected as
required by this AD.
Ref. Publications:
AH ASB AS332-05.01.08 original issue dated 20 March 2018.
The use of later approved revisions of the above-mentioned 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. Based on the required actions and the compliance time, EASA have decided to issue a Final AD
with Request for Comments, postponing the public consultation process until after publication.
3. Enquiries regarding this AD should be referred to the EASA Safety Information Section,
Certification Directorate. E-mail: ADs@easa.europa.eu.
4. For any question concerning the technical content of the requirements in this AD, please
contact: Airbus Helicopters (EBSESB) – Aéroport de Marseille Provence, 13725 Marignane
Cedex, France; Telephone +33 (4) 42 85 97 97; Fax +33 (4) 42 85 99 66;
E-mail: Directive.technical-support@airbus.com.
TE.CAP.00110-006 © European Aviation Safety Agency. All rights reserved. ISO9001 Certified. Page 3 of 3
Proprietary document. Copies are not controlled. Confirm revision status through the EASA-Internet/Intranet.
An agency of the European Union
Lufttüchtigkeitsanweisung Luftfahrt-Bundesamt
- Sachgebiet T23 -
D-2018-088 38144 Braunschweig
CAA-NZ AD DCA/750XL/28 vom 23.03.2018 Fax: +49-531-2355-5298
email: ad@LBA.de
PACIFIC AEROSPACE 05.04.2018
Betroffenes Luftfahrtgerät:
Art des Luftfahrtgerätes: Flugzeug
Inhaber der Musterzulassung: Pacific Aerospace Ltd
Hersteller: Pacific Aerospace Ltd (vormals Pacific Aerospace Corporation Ltd)
Muster: 750XL
Baureihen: 750XL
Werknummern: Alle bis einschließlich 215.
Gerätenummer: EASA.IM.A.081, CAA-NZ TCDS A-14
Revisionsstand:
Originalausgabe
Airworthiness Directive der ausländischen Behörde:
CAA-NZ AD DCA/750XL/28 vom 23.03.2018
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 2018-088 geführt.
Betrifft:
(ATA 27) Elevator Bellcrank Pivot - Inspection
Anmerkungen:
Gemäß M.A.303 und M.A.301 5.i) des Anhang I der Verordnung (EU) Nr. 1321/2014 (Teil-M) dürfen Luftfahr-
zeuge nach dem in der Lufttüchtigkeitsanweisung angegebenen Termin nur in Betrieb genommen werden,
wenn die angeordneten Maßnahmen ordnungsgemäß durchgeführt worden sind.
Die Europäische Agentur für Flugsicherheit (EASA) hat die oben referenzierte Lufttüchtigkeitsanweisung
CAA-NZ AD DCA/750XL/28 vom 23.03.2018 herausgegeben oder per Entscheidung Nr. 02/2003 übernom-
men.
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-2018-088 Seite 1 von 1 174/2018
Airworthiness Directive
Pacific Aerospace 750XL Aircraft
Issued by the Civil Aviation Authority of New Zealand in accordance with section 72I(3A) of the Civil Aviation Act. An Airworthiness Directive
(AD) contains regulatory information which is mandatory. An operator of an aircraft must not operate the aircraft unless the operator complies
with every applicable AD issued by the Director in accordance with section 72I(3A) of the Civil Aviation Act. An AD is issued where the
Director believes on reasonable grounds that an unsafe condition exists in an aircraft or aeronautical product.
DCA/750XL/28 Elevator Bellcrank Pivot - Inspection
Applicability: Pacific Aerospace 750XL aircraft, all S/N up to and including 215.
Note: It is possible that the elevator bellcrank pivot joint could be assembled with a bolt P/N AN4-20
that is a little too short, leaving threads inside the working area of the joint.
Requirement: Inspect the elevator bellcrank pivot joint to determine the length of the bolt installed, per the
instructions in Pacific Aerospace Mandatory Service Bulletin (MSB) PACSB/XL/097 issue 1,
dated 12 March 2018, or later approved revision.
If bolt P/N AN4-21 (2.156 inches) is found installed, then no further AD action is required.
If bolt P/N AN4-20 (2.031 inches) is found installed, then accomplish the corrective actions per
MSB PACSB/XL/097, before further flight.
Compliance: At the next scheduled maintenance inspection, or by 22 April 2018, whichever is the later.
Effective Date: 22 March 2018
Background: DCA/750XL/28 with effective date 22 March 2018 mandates the instructions in Pacific
Aerospace Mandatory Service Bulletin (MSB) PACSB/XL/097 issue 1, dated 12 March 2018.
The AD is prompted by the possibility that the elevator bellcrank pivot joint could be
assembled with a bolt P/N AN4-20 that is a little too short leaving threads inside the working
area of the joint. This can be determined by measuring the length of the bolt. If a bolt P/N
AN4-20 (2.031 inches) is found installed, then the bolt must be replaced with a longer bolt P/N
AN4-21 bolt (2.156 inches).
DCA/750XL/28 Page 1 of 1
Lufttüchtigkeitsanweisung Luftfahrt-Bundesamt
- Sachgebiet T23 -
D-2018-089 38144 Braunschweig
FAA AD 2018-06-10 - Amdt. 39-19230 Fax: +49-531-2355-5298
email: ad@LBA.de
HONDA AIRCRAFT 05.04.2018
Betroffenes Luftfahrtgerät:
Art des Luftfahrtgerätes: Flugzeug
Inhaber der Musterzulassung: Honda Aircraft Company LLC
Hersteller: Honda Aircraft Company LLC
Muster: HA-420
Baureihen: HA-420
Werknummern: 42000011 bis 4200089
Betroffen sind alle Flugzeuge, die mit einem "Power Brake Valve" mit den
Hersteller-Teilenummern (P/N) HJ1-13243-101-005 oder HJ1-13243-101-007
ausgerüstet sind.
Gerätenummer: EASA.IM.A.352, FAA TCDS A00018AT
Revisionsstand:
Originalausgabe
Airworthiness Directive der ausländischen Behörde:
FAA AD 2018-06-10 - Amdt. 39-19230
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 2018-089 geführt.
Betrifft:
(ATA 32) Landing Gear - Power Brake Valves - Airplane Flight Manual Temporary Revision / Replacement
Anmerkungen:
Gemäß M.A.303 und M.A.301 5.i) des Anhang I der Verordnung (EU) Nr. 1321/2014 (Teil-M) dürfen Luftfahr-
zeuge nach dem in der Lufttüchtigkeitsanweisung angegebenen Termin nur in Betrieb genommen werden,
wenn die angeordneten Maßnahmen ordnungsgemäß durchgeführt worden sind.
Die Europäische Agentur für Flugsicherheit (EASA) hat die oben referenzierte Lufttüchtigkeitsanweisung
FAA AD 2018-06-10 - Amdt. 39-19230 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-2018-089 Seite 1 von 1 175/2018
[Federal Register Volume 83, Number 61 (Thursday, March 29, 2018)]
[Rules and Regulations]
[Pages 13401-13404]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2018-06091]
––––––––––––––––––––––––––––––––––
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2018-0223; Product Identifier 2018-CE-007-AD; Amendment 39-19230; AD
2018-06-10]
RIN 2120-AA64
Airworthiness Directives; Honda Aircraft Company LLC
AGENCY: Federal Aviation Administration (FAA), DOT.
ACTION: Final rule; request for comments.
––––––––––––––––––––––––––––––––––
SUMMARY: We are adopting a new airworthiness directive (AD) for certain Honda Aircraft
Company LLC Model HA-420 airplanes. This AD requires incorporating a temporary revision into
the airplane flight manual and replacing faulty power brake valves upon condition. This AD was
prompted by reports of unannunciated asymmetric braking during ground operations and landing
deceleration. We are issuing this AD to address the unsafe condition on these products.
DATES: This AD is effective April 13, 2018.
The Director of the Federal Register approved the incorporation by reference of certain
publications listed in this AD as of April 13, 2018.
We must receive comments on this AD by May 14, 2018.
ADDRESSES: You may send comments, using the procedures found in 14 CFR 11.43 and 11.45, by
any of the following methods:
• Federal eRulemaking Portal: Go to http://www.regulations.gov. Follow the instructions for
submitting comments.
• Fax: 202-493-2251.
• Mail: U.S. Department of Transportation, Docket Operations, M-30, West Building Ground
Floor, Room W12-140, 1200 New Jersey Avenue SE, Washington, DC 20590.
• Hand Delivery: U.S. Department of Transportation, Docket Operations, M-30, West Building
Ground Floor, Room W12-140, 1200 New Jersey Avenue SE, Washington, DC 20590,
between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays.
For service information identified in this final rule, contact Honda Aircraft Company LLC, 6430
Ballinger Road, Greensboro, North Carolina 27410; telephone (336) 662-0246; internet:
http://www.hondajet.com. You may view this service information at the FAA, Policy and Innovation
1
Division, 901 Locust, Kansas City, Missouri 64106. For information on the availability of this
material at the FAA, call (816) 329-4148. It is also available on the internet at
http://www.regulations.gov by searching for and locating Docket No. FAA-2018-0223.
Examining the AD Docket
You may examine the AD docket on the internet at http://www.regulations.gov by searching for
and locating Docket No. FAA-2018-0223; or in person at Docket Operations between 9 a.m. and 5
p.m., Monday through Friday, except Federal holidays. The AD docket contains this final rule, the
regulatory evaluation, any comments received, and other information. The street address for the
Docket Operations (phone: 800-647-5107) is listed above. Comments will be available in the AD
docket shortly after receipt.
FOR FURTHER INFORMATION CONTACT: Samuel Kovitch, Aerospace Engineer, Atlanta
ACO Branch, FAA, 1701 Columbia Avenue, College Park, Georgia 30337; phone: (404) 474-5570;
fax: (404) 474-5605; email: samuel.kovitch@faa.gov.
SUPPLEMENTARY INFORMATION:
Discussion
We received reports of unannunciated asymmetric braking during landing deceleration on
several Honda Aircraft Company LLC Model HA-420 airplanes. Investigation revealed that the
power brake valve (PBV) housing design drawing dimension for a bore diameter, which serves as an
O-ring gland outer diameter, is oversized from Society of Automotive Engineers (SAE) specification
guidelines for O-ring gland dimensions. The oversized bore allows back-up ring extrusion damage
during normal operating hydraulic pressure in the valve, O-ring deformation/damage, and internal
leakage of hydraulic pressure within the PBV from the master cylinder brake lines. The damage to
the back-up ring and O-ring worsens during operation and causes the internal leakage rate of the PBV
brake master cylinder lines to increase over time. This condition, if not addressed, could result in
failure of the PBV, which could cause degraded braking performance and reduced directional control
during ground operations and landing deceleration. We are issuing this AD to address the unsafe
condition on these products.
Related Service Information Under 1 CFR Part 51
We reviewed Honda Aircraft Company Temporary Revision TR 01.1, dated February 16, 2018,
to the Honda Aircraft Company HA-420 Airplane Flight Manual and Service Bulletin SB-420-32-
001, dated January 8, 2018. Temporary Revision TR 01.1, dated February 16, 2018, to the HA-420
Airplane Flight Manual (AFM) describes procedures for performing pilot checks of the braking
system during ground operations before every flight and before every landing and includes
instructions for corrective actions if any indication of a leaking PBV is found. Service Bulletin SB-
420-32-001, dated January 8, 2018, describes procedures for replacing a defective PBV with an
improved design PBV. This service information is reasonably available because the interested parties
have access to it through their normal course of business or by the means identified in the
ADDRESSES section.
FAA's Determination
We are issuing this AD because we evaluated all the relevant information and determined the
unsafe condition described previously is likely to exist or develop in other products of the same type
design.
2
AD Requirements
This AD requires inserting a temporary revision into the AFM, which may be performed by the
owner/operator (pilot) holding at least a private pilot certificate and must be entered into the airplane
records showing compliance with this AD in accordance with 14 CFR 43.9 (a)(1)-(4) and 14 CFR
91.417(a)(2)(v). The record must be maintained as required by 14 CFR 91.417, 121.380, or 135.439.
This AD also requires replacing the installed PBV, P/N HJ1-13243-101-005 or P/N HJ1-13243-101-
007, with an improved PBV, P/N HJ1-13243-101-009, if a defective PBV is detected during the
required pilot checks as specified in the temporary revision. In addition, this AD provides an optional
terminating action for the temporary revision into the AFM by replacing the installed PBV with the
improved PBV, P/N HJ1-13243-101-009.
Interim Action
We consider this AD interim action. We are currently considering requiring replacement of the
installed PBV, P/N HJ1-13243-101-005 or P/N HJ1-13243-101-007, with an improved part, which
will constitute terminating action for the temporary revision to the AFM. However, the planned
compliance time for the replacement of the PBV would allow enough time to provide notice and
opportunity for prior comment on the merit of the replacement.
FAA's Justification and Determination of the Effective Date
An unsafe condition exists that requires the immediate adoption of this AD without providing an
opportunity for public comments prior to adoption. The FAA has found that the risk to the flying
public justifies waiving notice and comment prior to adoption of this rule because failure of the PBV
could cause degraded braking performance and reduced directional control during ground operations
and landing deceleration. Therefore, we find good cause that notice and opportunity for prior public
comment are impracticable. In addition, for the reason stated above, we find that good cause exists
for making this amendment effective in less than 30 days.
Comments Invited
This AD is a final rule that involves requirements affecting flight safety and was not preceded by
notice and an opportunity for public comment. However, we invite you to send any written data,
views, or arguments about this final rule. Send your comments to an address listed under the
ADDRESSES section. Include the docket number FAA-2018-0223 and Product Identifier 2018-CE-
007-AD at the beginning of your comments. We specifically invite comments on the overall
regulatory, economic, environmental, and energy aspects of this final rule. We will consider all
comments received by the closing date and may amend this final rule because of those comments.
We will post all comments we receive, without change, to http://www.regulations.gov, including
any personal information you provide. We will also post a report summarizing each substantive
verbal contact we receive about this final rule.
Costs of Compliance
We estimate that this AD affects 72 airplanes of U.S. registry.
We estimate the following costs to comply with this AD:
3
Estimated Costs
Action Labor cost Parts cost Cost per Cost on U.S.
product operators
Insert temporary revision into 1 work-hour × $85 Not $85 $6,120
the airplane flight manual per hour = $85 applicable
We estimate the following costs to do any necessary replacements that would be required based
on the results of the pilot check of the braking system during ground operations before every flight
and before every landing. We have no way of determining the number of airplanes that might need
these replacements:
On-Condition Costs
Action Labor cost Parts Cost per
cost product
Replace the power brake 20 work-hours × $85 per hour = $21,878 $23,578
valve $1,700
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.
This AD is issued in accordance with authority delegated by the Executive Director, Aircraft
Certification Service, as authorized by FAA Order 8000.51C. In accordance with that order, issuance
of ADs is normally a function of the Compliance and Airworthiness Division, but during this
transition period, the Executive Director has delegated the authority to issue ADs applicable to small
airplanes, gliders, balloons, airships, domestic business jet transport airplanes, and associated
appliances to the Director of the Policy and Innovation Division.
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.
4
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):
5
