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authority to approve structural related AMOCs when deviations to the service documents are
required.
The FAA partially agrees with the commenter. For Boeing service bulletins that are not yet
FAA-approved, the ODA authority is not granted at this time. However, for Boeing service bulletins
that are FAA-approved, the FAA has added a provision in paragraph (j)(3) of this AD for delegation
to The Boeing Company ODA for approval of certain AMOCs. This provision allows Boeing to
propose to the FAA the types of AMOCs that may be approved by The Boeing Company ODA.
Request for an Additional Person To Conduct the Inspection
An individual commenter stated that there are only 54 airplanes flying in the United States that
need inspections and believes that someone who is involved in the professional side of the NPRM
should be required to be present while the airplane is being inspected to ensure it is being done
correctly. The commenter believes this will allow the airplane to be inspected the same across the
board rather than each operator inspecting it differently. The commenter also believes that the NPRM
has been needed since the first account of the fan blade failure.
The FAA infers that the commenter is suggesting additional FAA oversight is necessary for the
fan cowl door moisture ingression inspections required by this AD. The FAA has reviewed the
service information for the fan cowl door moisture ingression inspections and has determined that the
FAA's existing oversight activity for operators performing such inspections provide an acceptable
level of safety. The FAA has not changed this final rule in this regard.
Additional Change Made to This AD
In the process of preparing this final rule, the FAA noticed that the unsafe condition statement
could be improved regarding the initial effects of the fan blade failure and the airplane level unsafe
outcomes that could result from each of those initial effects. Therefore, the FAA has updated the
unsafe condition statement in this AD to clarify the specific causes and hazardous effects.
Conclusion
The FAA reviewed the relevant data, considered any comments received, and determined that air
safety requires adopting this AD as proposed. Except for minor editorial changes, and any other
changes described previously, this AD is adopted as proposed in the NPRM. None of the changes
will increase the economic burden on any operator.
Related Service Information Under 1 CFR Part 51
The FAA has reviewed Boeing Alert Requirements Bulletin 777-71A0092 RB, dated January 13,
2022. This service information specifies procedures for inspecting the fan cowl doors for moisture
ingression. The FAA also reviewed Pratt & Whitney Alert Service Bulletin PW4G-112-A72-361,
dated October 15, 2021. This service information specifies procedures for performing thermal
acoustic image and ultrasonic testing inspections of 1st-stage LPC blades. 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 ADDRESSES.
Other Related Service Information
The FAA also reviewed Subtasks 26-21-00-200-018, 26-21-00-200-019, and 26-21-00-840-022,
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and Task 29-11-00-710-806, of Boeing 777-200/300 Aircraft Maintenance Manual, dated September
5, 2021. The service information specifies procedures for performing a functional check of the
engine-driven pump shutoff valve.
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Interim Action
The FAA considers this AD to be an interim action. The manufacturer is currently developing
other actions that will address the unsafe condition identified in this AD. Once these actions are
developed, approved, and available, the FAA might consider additional rulemaking.
Costs of Compliance
The FAA estimates that this AD affects 54 airplanes of U.S. registry. The FAA estimates the
following costs to comply with this AD:
Estimated Costs
Action Labor cost Parts Cost per Cost on U.S.
cost product operators
Installation of T/R debris 115 work-hour × $85 per $4,300 $14,075 $760,050.
shields hour = $9,775
Inspection of fan cowl 64 work-hours × $85 per 0 $5,440 $293,760.
doors hour = $5,440
Functional checks of the 1 work-hour × $85 per 0 $85 per $4,590 per
hydraulic pump shutoff hour = $85 per inspection inspection inspection cycle.
valves cycle cycle
The FAA has received no definitive data on which to base the cost estimates for the on-condition
corrective actions (i.e. repair) specified in this AD.
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.
The FAA is 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) Will not affect intrastate aviation in Alaska, and
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(3) 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.
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List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation safety, Incorporation by reference, Safety.
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:
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AIRWORTHINESS
FAA DIRECTIVE
Aviation Safety
www.faa.gov/aircraft/safety/alerts/
www.gpoaccess.gov/fr/advanced.html
2022-06-10 The Boeing Company: Amendment 39-21976; Docket No. FAA-2021-0962; Project
Identifier AD-2021-00997-T.
(a) Effective Date
This airworthiness directive (AD) is effective April 15, 2022.
(b) Affected ADs
None.
(c) Applicability
This AD applies to The Boeing Company airplanes, certificated in any category, as specified in
paragraphs (c)(1) and (2) of this AD.
(1) Model 777-200 series airplanes equipped with Pratt & Whitney PW4074, PW4074D,
PW4077, PW4077D, PW4084D, PW4090, and PW4090-3 model turbofan engines.
(2) Model 777-300 series airplanes equipped with Pratt & Whitney PW4090 and PW4098 model
turbofan engines.
(d) Subject
Air Transport Association (ATA) of America Code 71, Powerplant.
(e) Unsafe Condition
This AD was prompted by reports of three incidents involving in-flight fan blade failures on
certain Pratt & Whitney engines. The FAA is issuing this AD to address engine fan blade failure,
which could result in engine in-flight shutdown, and could result in separation of the inlet, the fan
cowl doors, or the thrust reverser (T/R) cowl, or result in uncontrolled engine fire. Separation of the
inlet, the fan cowl doors, or the T/R cowl could result in impact damage to the empennage and loss of
control of the airplane, or to the fuselage or windows with potential injury to passengers; or it could
result in significantly increased aerodynamic drag causing fuel exhaustion or the inability to maintain
altitude above terrain during extended operations (ETOPS) flights, either of which could result in a
forced off-airport landing and injury to passengers. Uncontrolled engine fire could result in loss of
control of the airplane.
(f) Compliance
Comply with this AD within the compliance times specified, unless already done.
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(g) Installation and Inspections
Before further flight after the effective date of this AD, do the actions specified in paragraphs
(g)(1) through (3) of this AD. Repeat the functional check specified in paragraph (g)(3) of this AD
within 10 days prior to each flight.
(1) Install debris shields on the T/R inner wall at the left and right sides of the lower bifurcation,
in accordance with a method approved by the Manager, Seattle ACO Branch, FAA.
(2) Inspect the fan cowl doors for moisture ingression in accordance with paragraphs (g)(2)(i) or
(ii) of this AD, as applicable.
(i) Do the inspection in accordance with a method approved by the Manager, Seattle ACO
Branch, FAA. If any moisture ingression is found, repair before further flight, in accordance with a
method approved by the Manager, Seattle ACO Branch, FAA.
(ii) Do all applicable actions identified in, and in accordance with, the Accomplishment
Instructions of Boeing Alert Requirements Bulletin 777-71A0092 RB, dated January 13, 2022, except
where Boeing Alert Requirements Bulletin 777-71A0092 RB, dated January 13, 2022, specifies to
report inspection findings, this AD does not require any report, and where Boeing Alert
Requirements Bulletin 777-71A0092 RB, dated January 13, 2022, specifies to contact Boeing for a
repair, this AD requires the repair to be accomplished in accordance with a method approved by the
Manager, Seattle ACO Branch, FAA.
(3) Do a functional check of the left and right hydraulic pump shutoff valves to ensure they close
in response to the corresponding engine fire handle input. If any hydraulic pump shutoff valve does
not close, before further flight perform corrective actions until it closes in response to the
corresponding engine fire handle input.
Note (1) to paragraph (g)(3): Guidance for accomplishing the actions required by paragraphs
(g)(3) and (h)(2) of this AD can be found in the “Engine-Driven Pump (EDP) Shutoff Valve Check”
(Subtasks 26-21-00-200-018, 26-21-00-200-019, and 26-21-00-840-022; or Task 29-11-00-710-806)
of Boeing 777-200/300 Aircraft Maintenance Manual.
(h) Special Flight Permit
Special flight permits, as described in 14 CFR 21.197 and 21.199, are permitted provided that the
actions in paragraphs (h)(1) and (2) of this AD have first been accomplished.
(1) A flow path ultrasonic testing (UT) inspection of the 1st-stage low-pressure compressor
(LPC) blades for cracking has been done within the last 275 cycles, as specified in the
Accomplishment Instructions, Part A–Initial Inspection of All LPC Fan Blades Prior to their Return
to Service, paragraph 1.A., of Pratt & Whitney Alert Service Bulletin PW4G-112-A72-361, dated
October 15, 2021, and the 1st-stage LPC blades have been found serviceable. This inspection is not
required for 1st-stage LPC blades with 275 cycles since new or fewer.
(2) A functional check of the left and right hydraulic pump shutoff valves to ensure they close in
response to the corresponding engine fire handle input and all applicable corrective actions (i.e.,
repair) within 10 days prior to flight.
(i) Credit for Previous Actions
This paragraph provides credit for the actions specified in paragraph (h)(1) of this AD, if those
actions were performed before the effective date of this AD using the service information specified in
paragraph (i)(1), (2), or (3) of this AD.
(1) Paragraph 2. of the Accomplishment Instructions of Pratt & Whitney Special Instruction No.
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85F-21, dated May 12, 2021, for a flow path UT inspection.
(2) Paragraph 1.a) of the Accomplishment Instructions of Pratt & Whitney Special Instruction
No. 130F-21, dated July 1, 2021, for a flow path UT inspection.
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(3) Paragraph 2.a) of the Accomplishment Instructions of Pratt & Whitney Special Instruction
No. 130F-21, Revision A, dated July 28, 2021, for a flow path UT inspection.
(j) Alternative Methods of Compliance (AMOCs)
(1) The Manager, Seattle ACO Branch, FAA, has the authority to approve AMOCs for this AD,
if requested using the procedures found in 14 CFR 39.19. In accordance with 14 CFR 39.19, send
your request to your principal inspector or responsible Flight Standards Office, as appropriate. If
sending information directly to the manager of the certification office, send it to the attention of the
person identified in paragraph (k)(1) of this AD. Information may be emailed to: 9-ANM-Seattle-
ACO-AMOC-Requests@faa.gov.
(2) Before using any approved AMOC, notify your appropriate principal inspector, or lacking a
principal inspector, the manager of the responsible Flight Standards Office.
(3) An AMOC that provides an acceptable level of safety may be used for any repair,
modification, or alteration required by this AD if it is approved by The Boeing Company
Organization Designation Authorization (ODA) that has been authorized by the Manager, Seattle
ACO Branch, FAA, to make those findings. To be approved, the repair method, modification
deviation, or alteration deviation must meet the certification basis of the airplane, and the approval
must specifically refer to this AD.
(k) Related Information
(1) For more information about this AD, contact James Laubaugh, Aerospace Engineer,
Propulsion Section, FAA, Seattle ACO Branch, 2200 South 216th St., Des Moines, WA 98198;
phone and fax: 206-231-3622; email: james.laubaugh@faa.gov.
(2) Service information identified in this AD that is not incorporated by reference is available at
the addresses specified in paragraphs (l)(3) and (4) of this AD.
(l) Material Incorporated by Reference
(1) The Director of the Federal Register approved the incorporation by reference (IBR) of the
service information listed in this paragraph under 5 U.S.C. 552(a) and 1 CFR part 51.
(2) You must use this service information as applicable to do the actions required by this AD,
unless the AD specifies otherwise.
(i) Boeing Alert Requirements Bulletin 777-71A0092 RB, dated January 13, 2022.
(ii) Pratt & Whitney Alert Service Bulletin PW4G-112-A72-361, dated October 15, 2021.
(3) For Boeing service information identified in this AD, contact Boeing Commercial Airplanes,
Attention: Contractual & Data Services (C&DS), 2600 Westminster Blvd., MC 110-SK57, Seal
Beach, CA 90740-5600; telephone 562-797-1717; internet https://www.myboeingfleet.com. For Pratt
& Whitney service information identified in this AD contact Pratt & Whitney Division, 400 Main
Street, East Hartford, CT 06118; phone: 860-565-0140; email: help24@prattwhitney.com; website:
https://connect.prattwhitney.com.
(4) You may view this service information at the FAA, Airworthiness Products Section,
Operational Safety Branch, 2200 South 216th St., Des Moines, WA. For information on the
availability of this material at the FAA, call 206-231-3195.
(5) You may view this service information that is incorporated by reference at the National
Archives and Records Administration (NARA). For information on the availability of this material at
NARA, fr.inspection@nara.gov, or go to: https://www.archives.gov/federal-register/cfr/ibr-
locations.html.
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Issued on March 4, 2022.
Lance T. Gant,
Director, Compliance & Airworthiness Division, Aircraft Certification Service.
[FR Doc. 2022-05309 Filed 3-9-22; 4:15 pm]
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Lufttüchtigkeitsanweisung Luftfahrt-Bundesamt
- Sachgebiet T12 -
D-2022-094 38144 Braunschweig
EASA AD 2022-0053 vom 23.03.2022 Fax: +49-531-2355-5199
email: AD@LBA.de
AIRBUS HELICOPTERS 28.03.2022
Betroffenes Luftfahrtgerät:
Art des Luftfahrtgerätes: Drehflügler
Inhaber der Musterzulassung: AIRBUS HELICOPTERS
Hersteller: Airbus Helicopters (AH), vormals Eurocopter, Eurocopter France, Aerospatiale
Muster: EC 120, EC 130
Baureihen: EC 130 T2, EC 130 B4 und EC 120 B
Werknummern: Alle
Gerätenummer: 3048, 3065, EASA.R.008, EASA.R.508
Revisionsstand:
Originalausgabe
Airworthiness Directive der ausländischen Behörde:
EASA AD 2022-0053 vom 23.03.2022
Genannte Airworthiness Directives unter dieser Rubrik, die nicht durch die EASA herausgegeben worden sind,
wurden durch die EASA über die Entscheidung Nr. 2019/018/ED übernommen und sind somit ebenfalls Airworthin-
ess Directives der EASA.
Die genannte Airworthiness Directive wird im Luftfahrt-Bundesamt unter der Nummer 2022-094 geführt.
Betrifft:
(ATA 32) Landing Gear - Skid-Type Landing Gear - Inspection
Anmerkungen:
Gemäß der EU Verordnung Nr. 1321/2014, Anhang I, Teil M, Unterabschnitt C, M.A.301(f)(1), ML.A.301(d)(1),
M.A.303 und ML.A.303 dürfen Luftfahrzeuge nach dem in der Lufttüchtigkeitsanweisung angegebenen
Termin nur in Betrieb genommen werden, wenn die angeordneten Maßnahmen ordnungsgemäß durchge-
führt worden sind.
Die Europäische Agentur für Flugsicherheit (EASA) hat die oben referenzierte Lufttüchtigkeitsanweisung
EASA AD 2022-0053 vom 23.03.2022 herausgegeben oder per Entscheidung Nr. 2019/018/ED 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.
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EASA AD No.: 2022-0053
Airworthiness Directive
AD No.: 2022-0053
Issued: 23 March 2022
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 or
Annex Vb Part ML.A.301, as applicable, 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 Annex Vb Part ML.A.301, as applicable] 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 HELICOPTERS EC 120 and EC 130 helicopters
Effective Date: 06 April 2022
TCDS Number(s): EASA.R.008 and EASA.R.508
Foreign AD: Not applicable
Supersedure: None
ATA 32 – Landing Gear – Skid-Type Landing Gear – Inspection
Manufacturer(s):
Airbus Helicopters (AH), formerly Eurocopter, Eurocopter France, Aerospatiale
Applicability:
EC 130 T2 and EC 130 B4 helicopters, all serial numbers (s/n); and
EC 120 B helicopters, all s/n.
Definitions:
For the purpose of this AD, the following definitions apply:
Affected part: An EC 130 B4 and EC 130 T2 landing gear assembly having part number (P/N)
350A41-0077-0201, P/N 350A41-0080-1102, P/N 350A41-0080-1103, P/N 350A41-0081-0201,
P/N 350A41-0082-0101 or P/N 350A41-0082-0102, except those having a date of first installation on
a helicopter on 16 February 2022 or later; and
An EC 120 B landing gear assembly having P/N C321A2106102, P/N C321A2501101,
P/N C321A2501102, P/N C321A2601051AA, P/N C321A2601051CA or P/N C321A2601052, except
those having a date of first installation on a helicopter on 16 February 2022 or later.
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EASA AD No.: 2022-0053
If the date of its first installation on a helicopter is unknown, a landing gear assembly must be
considered as an affected part.
Affected part sub-assembly: Front and rear crossbeam, and left-hand (LH) and right-hand (RH) skid
assembly, having a P/N as identified in the ASB, except those having a date of first installation on a
helicopter on 16 February 2022 or later.
Serviceable part: An affected part and an affected part sub-assembly, which have passed (no defect
found) an inspection in accordance with the instructions of the ASB; or an affected part and an
affected part sub-assembly, that, following an inspection in accordance with the instructions of the
ASB, have been repaired in accordance with AH approved repair instructions; or a landing gear
assembly, front and rear crossbeam, and LH and RH skid assembly which is not an affected part.
The ASB: AH Alert Service Bulletin (ASB) EC130-32A013 and AH ASB EC120-32A014, as applicable.
Non-standard helicopter operation: Helicopter operation as defined in AH Master Servicing Manual
chapter 5.6 “Specific and severe atmospheric operating conditions”.
Standard helicopter operation: Any helicopter operation which is not a non-standard operation, as
defined in this AD.
Groups: Group 1 helicopters are those that have an affected part installed. Group 2 helicopters are
those that do not have an affected part installed.
Reason:
An occurrence was reported of corrosion found on an affected part of an EC 130 helicopter.
This condition, if not detected and corrected, could lead to collapse of the landing gear, possibly
resulting in damage to the helicopter and/or injury to occupants.
Due to design similarity, the landing gear assemblies of EC 120 B helicopters could also be affected
by this potential unsafe condition.
To initially address this potential unsafe condition, AH issued ASB EC130-05A035 providing
instructions to inspect a limited batch of helicopters. Following subsequent investigation, AH
determined that additional helicopters must be inspected and issued the ASB, as defined in this AD,
providing inspection instructions.
For the reasons described above, this AD requires a one-time inspection of the external (visual) and
internal (borescope) landing gear tubes for presence of corrosion and/or crack(s), and, depending
on findings, accomplishment of applicable corrective action(s).
This AD is considered an interim action and further AD action may follow.
Required Action(s) and Compliance Time(s):
Required as indicated, unless accomplished previously:
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