50226 Federal Register / Vol. 86, No. 171 / Wednesday, September 8, 2021 / Rules and Regulations 

§ 39.13 [Amended] 

■ 2. The FAA amends § 39.13 by adding 

the following new airworthiness 

directive: 

2021–16–16 Airbus Helicopters: 

Amendment 39–21679; Docket No. 

FAA–2021–0449; Project Identifier 

2018–SW–001–AD. 

(a) Effective Date 

This airworthiness directive (AD) is 

effective October 13, 2021. 

(b) Affected ADs 

None. 

(c) Applicability 

This AD applies to Airbus Helicopters 

Model AS350B, AS350BA, AS350B1, 

AS350B2, AS350B3, and AS350D 

helicopters; and Model AS355E, AS355F, 

AS355F1, AS355F2, AS355N, and AS355NP 

helicopters, certificated in any category, with 

litter kits installed having any part number 

specified in paragraphs (c)(1) through (3) of 

this AD: 

(1) Part number (P/N) 350–200034 (lefthand litter kit). 

(2) P/N 350–200194 (left-hand litter kit). 

(3) P/N 350–200144 (right-hand litter kit). 

(d) Subject 

Joint Aircraft Service Component (JASC) 

Code: 6700, Rotorcraft Flight Control. 

(e) Unsafe Condition 

This AD was prompted by reports that the 

lanyards (bead chain tethers), which hold the 

quick release pins to the forward bracket 

assembly of certain litter kits, can loop 

around the directional control pedal stubs, 

limiting the movement of the pedals, which 

affect the control of the flight. The FAA is 

issuing this AD to address interference 

between the litter kit lanyards and the flight 

controls. The unsafe condition, if not 

addressed, could result in limited flight 

control movement and difficulty controlling 

the helicopter. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Required Actions 

(1) For litter kits having any part specified 

in paragraphs (c)(1) through (3) of this AD: 

Prior to each flight until the modification 

required by paragraph (g)(2) of this AD is 

accomplished, do a pre-flight check to 

determine if there is interference (e.g. limited 

movement of the pedals due to the lanyards 

that hold the quick release pins to the 

forward bracket assembly being looped 

around the directional control pedal stubs) 

between the lanyards that hold the quick 

release pins to the forward bracket assembly 

and the pedals. If interference is found, 

before further flight, do the modification 

required by paragraph (g)(2) of this AD for 

the affected litter kit. The pre-flight check 

may be performed by the owner/operator 

(pilot) holding at least a private pilot 

certificate and must be entered into the 

aircraft records showing compliance with 

this AD in accordance with § 43.9(a)(1) 

through (4) and § 91.417(a)(2)(v). The record 

must be maintained as required by § 91.417, 

§ 121.380, or § 135.439. 

(2) Within 25 hours time-in-service (TIS) 

after the effective date of this AD, modify the 

attachment location of the lanyard for litter 

kits having any part specified in paragraphs 

(c)(1) through (3) of this AD. Do the 

modification in accordance with paragraph 

3.B.2., ‘‘Procedure,’’ of the Accomplishment 

Instructions of Airbus Helicopters Service 

Bulletin SB–AHCA–128, Revision 0, dated 

March 24, 2017. 

Note 1 to paragraph (g): Litter kits, P/N 

350–200034 and P/N 350–200194, may have 

been installed under supplemental type 

certificate (STC) SR00406NY (for Model 

AS355E, AS355F, AS355F1, AS355F2, 

AS355N, and AS355NP helicopters) or STC 

SR00407NY (for Model AS350B, AS350BA, 

AS350B1, AS350B2, AS350B3, and AS350D 

helicopters). Litter kit P/N 350–200144 may 

have been installed under STC SR00458NY 

(for Model AS350BA, AS350B2, and 

AS350B3 helicopters). 

(h) Parts Installation Limitation 

As of the effective date of this AD, no 

person may install a litter kit having a part 

number identified in paragraphs (c)(1) 

through (3) of this AD, on any helicopter, 

unless the installation is modified as 

required by paragraph (g)(2) of this AD. 

(i) Alternative Methods of Compliance 

(AMOCs) 

(1) The Manager, International Validation 

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 local 

Flight Standards District Office, as 

appropriate. If sending information directly 

to the manager of the International Validation 

Branch, send it to the attention of the person 

identified in paragraph (j)(1) of this AD. 

Information may be emailed to: 9-AVS-AIR730-AMOC@faa.gov. 

(2) Before using any approved AMOC, 

notify your appropriate principal inspector, 

or lacking a principal inspector, the manager 

of the local flight standards district office/ 

certificate holding district office. 

(j) Related Information 

(1) For more information about this AD, 

contact Andrea Jimenez, Aerospace Engineer, 

COS Program Management Section, 

Operational Safety Branch, Compliance & 

Airworthiness Division, FAA, 1600 Stewart 

Ave., Mail Stop: Room 410, Westbury, NY 

11590; telephone (516) 228–7330; email 

andrea.jimenez@faa.gov. 

(2) For information about AMOCs, contact 

the Manager, International Validation 

Branch, FAA, 10101 Hillwood Pkwy., Fort 

Worth, TX 76177; telephone (817) 222–5110; 

email 9-AVS-AIR-730-AMOC@faa.gov. 

(3) The subject of this AD is addressed in 

Transport Canada AD CF–2017–37 dated 

December 19, 2017. You may view the 

Transport Canada AD at https://

www.regulations.gov in Docket No. FAA– 

2021–0449. 

(k) Material Incorporated by Reference 

(1) The Director of the Federal Register 

approved the incorporation by reference 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) Airbus Helicopters Service Bulletin SB– 

AHCA–128, Revision 0, dated March 24, 

2017. 

(ii) [Reserved] 

(3) For service information identified in 

this AD, contact Airbus Helicopters, 2701 

North Forum Drive, Grand Prairie, TX 75052; 

telephone (972) 641–0000 or (800) 232–0323; 

fax (972) 641–3775; or at https://

www.airbus.com/helicopters/services/ 

technical-support.html. 

(4) You may view this service information 

at the FAA, Office of the Regional Counsel, 

Southwest Region, 10101 Hillwood Pkwy., 

Room 6N–321, Fort Worth, TX 76177. For 

information on the availability of this 

material at the FAA, call (817) 222–5110. 

(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, 

email: fr.inspection@nara.gov, or go to: 

https://www.archives.gov/federal-register/cfr/ 

ibr-locations.html. 

Issued on July 30, 2021. 

Lance T. Gant, 

Director, Compliance & Airworthiness 

Division, Aircraft Certification Service. 

[FR Doc. 2021–19252 Filed 9–7–21; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2021–0379; Project 

Identifier MCAI–2021–00068–R; Amendment 

39–21667; AD 2021–16–05] 

RIN 2120–AA64 

Airworthiness Directives; Airbus 

Helicopters 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule. 

SUMMARY: The FAA is superseding 

Airworthiness Directive (AD) 2016–12– 

51, which applied to all Airbus 

Helicopters Model AS332L2 and Model 

EC225LP helicopters. AD 2016–12–51 

prohibited all further flight of Model 

AS332L2 and Model EC225LP 

helicopters. This AD requires replacing 

certain second stage planet gear 

assemblies, removing certain epicyclic 

modules, installing a full flow magnetic 

plug (FFMP), revising the existing 


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Federal Register / Vol. 86, No. 171 / Wednesday, September 8, 2021 / Rules and Regulations 50227 

rotorcraft flight manual (RFM) for your 

helicopter, repetitively inspecting the 

main gearbox (MGB) particle detectors, 

repetitively inspecting the MGB oil filter 

and oil cooler, and corrective action if 

necessary, as specified in a European 

Union Aviation Safety Agency (EASA) 

AD, which is incorporated by reference. 

The actions specified in this AD 

terminate the flight prohibition. The 

FAA is issuing this AD to address the 

unsafe condition on these products. 

DATES: This AD is effective October 13, 

2021. 

The Director of the Federal Register 

approved the incorporation by reference 

of certain publications listed in this AD 

as of October 13, 2021. 

ADDRESSES: For EASA material 

incorporated by reference (IBR) in this 

AD, contact the EASA, KonradAdenauer-Ufer 3, 50668 Cologne, 

Germany; telephone +49 221 8999 000; 

email ADs@easa.europa.eu; internet 

www.easa.europa.eu. You may find this 

material on the EASA website at https:// 

ad.easa.europa.eu. For Airbus 

Helicopters service information, contact 

Airbus Helicopters, 2701 North Forum 

Drive, Grand Prairie, TX 75052; 

telephone (972) 641–0000 or (800) 232– 

0323; fax (972) 641–3775; or at https:// 

www.airbus.com/helicopters/services/ 

technical-support.html. You may view 

this material at the FAA, Office of the 

Regional Counsel, Southwest Region, 

10101 Hillwood Pkwy., Room 6N–321, 

Fort Worth, TX 76177. For information 

on the availability of this material at the 

FAA, call 817–222–5110. It is also 

available in the AD docket on the 

internet at https://www.regulations.gov 

by searching for and locating Docket No. 

FAA–2021–0379. 

Examining the AD Docket 

You may examine the AD docket on 

the internet at https://

www.regulations.gov by searching for 

and locating Docket No. FAA–2021– 

0379; 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, 

any comments received, and other 

information. The address for Docket 

Operations is U.S. Department of 

Transportation, Docket Operations, M– 

30, West Building Ground Floor, Room 

W12–140, 1200 New Jersey Avenue SE, 

Washington, DC 20590. 

FOR FURTHER INFORMATION CONTACT: 

Mahmood Shah, Aviation Safety 

Engineer, Fort Worth ACO Branch, 

FAA, 10101 Hillwood Pkwy., Fort 

Worth, TX 76177; telephone 817–222– 

5538; email mahmood.g.shah@faa.gov. 

SUPPLEMENTARY INFORMATION: 

Background 

EASA, which is the Technical Agent 

for the Member States of the European 

Union, has issued EASA AD 2017– 

0134R2, dated April 16, 2020 (EASA AD 

2017–0134R2) (also referred to as the 

Mandatory Continuing Airworthiness 

Information, or the MCAI), to correct an 

unsafe condition for all Airbus 

Helicopters Model AS332L2 and 

EC225LP helicopters. 

The FAA issued a notice of proposed 

rulemaking (NPRM) to amend 14 CFR 

part 39 to supersede AD 2016–12–51, 

Amendment 39–18578 (81 FR 43479, 

July 5, 2016) (AD 2016–12–51). AD 

2016–12–51 applied to all Airbus 

Helicopters Model AS332L2 and 

EC225LP helicopters. The NPRM 

published in the Federal Register on 

June 1, 2021 (86 FR 29212). The NPRM 

was prompted by an accident involving 

an Airbus Helicopters Model EC225LP 

helicopter in which the main rotor hub 

detached from the MGB. The Airbus 

Helicopters Model AS332L2 helicopter 

has a similar design to the affected 

Model EC225LP helicopter, therefore, 

this model may be subject to the unsafe 

condition revealed on the Model 

EC225LP helicopter. The NPRM 

proposed to require replacing certain 

second stage planet gear assemblies, 

removing certain epicyclic modules, 

installing an FFMP, revising the existing 

RFM for your helicopter, repetitively 

inspecting the MGB particle detectors, 

repetitively inspecting the MGB oil filter 

and oil cooler, and corrective action if 

necessary, as specified in EASA AD 

2017–0134R2. The NPRM also proposed 

to provide terminating action for certain 

repetitive inspections. 

The FAA is issuing this AD to address 

failure of the main rotor system, which 

would result in loss of control of the 

helicopter. See the MCAI for additional 

background information. 

Discussion of Final Airworthiness 

Directive 

Comments 

The FAA gave the public the 

opportunity to participate in developing 

this final rule. The FAA received no 

comments on the NPRM or on the 

determination of the cost to the public. 

Conclusion 

The FAA reviewed the relevant data 

and determined that air safety and the 

public interest require adopting this 

final rule as proposed, except for minor 

editorial changes. The FAA has 

determined that these minor changes: 

• Are consistent with the intent that 

was proposed in the NPRM for 

addressing the unsafe condition; and 

• Do not add any additional burden 

upon the public than was already 

proposed in the NPRM. 

Related Service Information Under 1 

CFR Part 51 

EASA AD 2017–0134R2 references 

procedures for replacing certain second 

stage planet gear assemblies with 

serviceable parts; removing certain 

epicyclic modules from service; 

modifying the helicopter by installing 

an FFMP; revising the RFM to prohibit 

MGB particle burning in-flight; 

repetitively inspecting the FFMP and 

MGB particle detectors for metal 

particles, analyzing any metal particles 

that are found, and corrective action; 

and repetitively inspecting the MGB oil 

filter and oil cooler for particles and 

corrective action. The corrective actions 

include replacing an affected MGB with 

a serviceable MGB. EASA AD 2017– 

0134R2 also provides terminating action 

for certain repetitive inspections. 

Airbus Helicopters has issued 

Emergency Alert Service Bulletin 

05A049, Revision 6, dated July 25, 2017, 

for Model EC225 helicopters; and 

Emergency Alert Service Bulletin 

05.01.07, Revision 6, dated July 27, 

2017, for Model AS332 helicopters. The 

service information specifies procedures 

for, among other things, replacing the 

MGB. 

This material 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. 

Differences Between This AD and the 

MCAI 

Although the service information 

referenced in EASA AD 2017–0134R2 

specifies to return affected planetary 

gear assemblies to the manufacturer for 

module overhaul, this AD does not 

include that requirement. 

Although the service information 

referenced in EASA AD 2017–0134R2 

specifies that retrofit of the planet gear 

of the MGB can only be done by Airbus 

Helicopters or Airbus Helicopters 

approved repair centers, this AD does 

not include that requirement. 

EASA AD 2017–0134R2 requires 

operators to ‘‘inform all flight crews’’ of 

revisions to the RFM, and thereafter to 

‘‘operate the helicopter accordingly.’’ 

However, this AD does not specifically 

require those actions. FAA regulations 

mandate compliance with only the 

operating limitations section of the 

flight manual. The flight manual 

changes required by this AD apply to 

the emergency procedures section of the 

existing RFM for your helicopter. 

Furthermore, compliance with such 


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50228 Federal Register / Vol. 86, No. 171 / Wednesday, September 8, 2021 / Rules and Regulations 

requirements in an AD is impracticable 

to demonstrate or track on an ongoing 

basis; therefore, a requirement to 

operate the aircraft in such a manner is 

unenforceable. Nonetheless, the FAA 

recommends that flight crews of the 

helicopters listed in the applicability 

operate in accordance with the revised 

emergency procedures mandated by this 

AD. 

Interim Action 

The FAA considers this AD interim 

action. If final action is later identified, 

the FAA might consider further 

rulemaking then. 

Costs of Compliance 

The FAA estimates that this AD 

affects 28 helicopters of U.S. registry. 

The FAA estimates the following costs 

to comply with this AD: 

ESTIMATED COSTS FOR REQUIRED ACTIONS * 

Action Labor cost Parts 

cost 

Cost per 

product 

Cost on U.S. 

operators 

New actions ............................................ Up to 6 work-hours × $85 per hour = 

$510.

$0 Up to $510 ............. Up to $14,280. 

* Table does not include estimated costs for reporting. 

The FAA estimates that it will take 

about 1 work-hour per product to 

comply with the reporting requirement 

in this AD. The average labor rate is $85 

per hour. Based on these figures, the 

FAA estimates the cost of reporting the 

inspection results on U.S. operators to 

be $2,380, or $85 per product. 

The FAA estimates the following 

costs to do any necessary on-condition 

actions that will be required based on 

the results of any required actions. The 

FAA has no way of determining the 

number of helicopters that might need 

these on-condition actions: 

ESTIMATED COSTS OF ON-CONDITION ACTIONS

Labor cost Parts cost Cost per 

product 

40 work-hours × $85 per hour = $3,400 ................................................................................................................. $295,000 $298,400 

According to the manufacturer, some 

or all of the costs of this AD may be 

covered under warranty, thereby 

reducing the cost impact on affected 

operators. The FAA does not control 

warranty coverage for affected operators. 

As a result, the FAA has included all 

known costs in the cost estimate. 

Paperwork Reduction Act 

A federal agency may not conduct or 

sponsor, and a person is not required to 

respond to, nor shall a person be subject 

to penalty for failure to comply with a 

collection of information subject to the 

requirements of the Paperwork 

Reduction Act unless that collection of 

information displays a current valid 

OMB control number. The control 

number for the collection of information 

required by this AD is 2120–0056. The 

paperwork cost associated with this AD 

has been detailed in the Costs of 

Compliance section of this document 

and includes time for reviewing 

instructions, as well as completing and 

reviewing the collection of information. 

Therefore, all reporting associated with 

this AD is mandatory. Comments 

concerning the accuracy of this burden 

and suggestions for reducing the burden 

should be directed to Information 

Collection Clearance Officer, Federal 

Aviation Administration, 10101 

Hillwood Pkwy., Fort Worth, TX 76177– 

1524. 

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 

(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. 

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: 

■ a. Removing Airworthiness Directive 

2016–12–51, Amendment 39–18578 (81 

FR 43479, July 5, 2016); and 

■ b. Adding the following new 

airworthiness directive: 


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Federal Register / Vol. 86, No. 171 / Wednesday, September 8, 2021 / Rules and Regulations 50229 

2021–16–05 Airbus Helicopters: 

Amendment 39–21667; Docket No. 

FAA–2021–0379; Project Identifier 

MCAI–2021–00068–R. 

(a) Effective Date 

This airworthiness directive (AD) is 

effective October 13, 2021. 

(b) Affected ADs 

This AD replaces AD 2016–12–51, 

Amendment 39–18578 (81 FR 43479, July 5, 

2016) (AD 2016–12–51). 

(c) Applicability 

This AD applies to all Airbus Helicopters 

Model AS332L2 and EC225LP helicopters, 

certificated in any category. 

(d) Subject 

Joint Aircraft System Component (JASC) 

Code 6320, Main Rotor Gearbox. 

(e) Reason 

This AD was prompted by an accident 

involving a Model EC225LP helicopter in 

which the main rotor hub detached from the 

main gearbox. The FAA is issuing this AD to 

address failure of the main rotor system, 

which would result in loss of control of the 

helicopter. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Requirements 

Except as specified in paragraph (h) of this 

AD: Comply with all required actions and 

compliance times specified in, and in 

accordance with, European Union Aviation 

Safety Agency (EASA) AD 2017–0134R2, 

dated April 16, 2020 (EASA AD 2017– 

0134R2). 

(h) Exceptions to EASA AD 2017–0134R2 

(1) Where EASA AD 2017–0134R2 refers to 

the effective dates specified in paragraphs 

(h)(1)(i) through (v) of this AD, this AD 

requires using the effective date of this AD. 

(i) The effective date of EASA AD 2017– 

0134R2. 

(ii) October 13, 2016 (the effective date of 

EASA AD 2016–0199, dated October 7, 

2016). 

(iii) March 20, 2017 (the effective date of 

EASA AD 2017–0050–E, dated March 17, 

2017). 

(iv) June 30, 2017 (the effective date of 

EASA AD 2017–0111, dated June 23, 2017). 

(v) August 1, 2017 (the effective date of 

EASA AD 2017–0134, dated July 27, 2017). 

(2) The ‘‘Remarks’’ section of EASA AD 

2017–0134R2 does not apply to this AD. 

(3) Where any service information referred 

to in EASA AD 2017–0134R2 specifies to 

discard certain parts after they have been 

removed from the helicopter, this AD 

requires removing those parts from service. 

(4) Where paragraph (2) of EASA AD 2017– 

0134R2 specifies to replace a part before 

exceeding the applicable ‘‘new service life 

limit,’’ this AD requires removing that part 

from service. 

(5) Where any service information referred 

to in EASA AD 2017–0134R2 specifies to 

return certain parts to the manufacturer, 

including for overhaul, after they have been 

removed from the helicopter, this AD does 

not include that requirement. 

(6) Where EASA AD 2017–0134R2 refers to 

flight hours (FH), this AD requires using 

hours time-in-service. 

(7) Where any service information referred 

to in EASA AD 2017–0134R2 specifies to 

perform a metallurgical analysis and contact 

the manufacturer if unsure about the 

characterization of the particles collected, 

this AD does require characterization of the 

particles collected, however this AD does not 

require contacting the manufacturer to 

determine the characterization of the 

particles collected. 

(8) Where EASA AD 2017–0134R2 requires 

actions during each ‘‘after last flight’’ of the 

day (ALF) inspection, this AD requires those 

actions before the first flight of each day. 

(9) Where any service information referred 

to in EASA AD 2017–0134R2 specifies to do 

the actions identified in paragraphs (h)(9)(i) 

through (iv) of this AD, this AD does not 

include those requirements. 

(i) Watch a video for removing the grease 

from the full flow magnetic plug (FFMP), 

using a cleaning agent, and collecting 

particles. 

(ii) Return affected planetary gear assembly 

to the manufacturer for module overhaul. 

(iii) Contact the approved repair station/ 

Airbus Helicopters if the reason for a repair 

to an epicyclic module is unknown and 

inform/contact Airbus Helicopters. 

(iv) Contact the approved repair station/ 

Airbus Helicopters depending on who 

performed the last overhaul (RG) to 

determine if a repair has been done on the 

second stage planet gears since new. 

(10) Where any service information 

referred to in EASA AD 2017–0134R2 

specifies that retrofit of the planet gear of the 

main gearbox (MGB) can only be done by 

Airbus Helicopters or Airbus Helicopters 

approved repair centers, this AD does not 

require that the retrofit of the planet gear be 

done only by Airbus Helicopters or Airbus 

Helicopters approved repair centers. For this 

AD the retrofit can also be done by an FAAapproved repair station. 

(11) Where paragraph (5) of EASA AD 

2017–0134R2 specifies accomplishing the 

FFMP additional work within 3 months after 

August 1, 2017, this AD requires 

accomplishing the FFMP additional work 

within 4 months after the effective date of 

this AD. 

(12) Where paragraph (6) of EASA AD 

2017–0134R2 specifies to ‘‘inform all flight 

crews and, thereafter, operate the helicopter 

accordingly,’’ this AD does not require those 

actions. 

(13) Where any service information 

referred to in EASA AD 2017–0134R2 

specifies that if any 16NCD13 particles are 

found you are to take a 1-liter sample of oil 

and send it to the manufacturer, this AD does 

not require those actions. 

(14) Where any service information 

referred to in EASA AD 2017–0134R2 

specifies ‘‘Do not resume flights until 

corrective action(s) are agreed by Airbus 

Helicopters,’’ or to contact Airbus 

Helicopters before resuming flights ‘‘if 

further particles are collected during the 

close monitoring period’’ for this AD, you 

must repair before further flight using a 

method specified in paragraph (h)(14)(i) or 

(ii) of this AD. 

(i) In accordance with FAA approved 

procedures. 

(ii) The procedures specified in Appendix 

4.A., Particle Analysis, of Airbus Helicopters 

Emergency Alert Service Bulletin 05A049, 

Revision 6, dated July 25, 2017; or 

Emergency Alert Service Bulletin 05.01.07, 

Revision 6, dated July 27, 2017, as 

applicable, except as required by paragraphs 

(h)(5), (7), and (13) of this AD. 

(15) Where the service information 

identified in EASA AD 2017–0134R2 

specifies to report inspection results to 

Airbus Helicopters, for this AD, report the 

inspection results at the applicable time 

specified in paragraph (h)(15)(i) or (ii) of this 

AD. 

(i) If the inspection was done on or after 

the effective date of this AD: Submit the 

report within 30 days after the date of the 

inspection. 

(ii) If the inspection was done before the 

effective date of this AD: Submit the report 

within 30 days after the effective date of this 

AD. 

(i) Credit for Previous Actions 

(1) This paragraph provides credit for the 

actions specified in paragraph (4) of EASA 

AD 2017–0134R2, if those actions were 

performed before the effective date of this AD 

using Airbus Helicopters Emergency Alert 

Service Bulletin 63.00.83 or 63A030, both 

Revision 1, both dated October 7, 2016. 

(2) Corrective action(s) for the inspections 

required by paragraphs (8) and (10) of EASA 

AD 2017–0134R2 accomplished on a 

helicopter before the effective date of this 

AD, in accordance with Paragraph 3.B. and 

Appendix 4.A. of the Accomplishment 

Instructions of the applicable Airbus 

Helicopters service information specified in 

paragraphs (i)(2)(i) through (viii) of this AD, 

as applicable, are acceptable to comply with 

the requirements of paragraph (11) of EASA 

AD 2017–0134R2 for that helicopter, but only 

for the corrective actions for the inspections 

required by paragraphs (8) and (10) of EASA 

AD 2017–0134R2. 

(i) Emergency Alert Service Bulletin 

05.01.07, Revision 2, dated October 7, 2016. 

(ii) Emergency Alert Service Bulletin 

05.01.07, Revision 3, dated February 25, 

2017. 

(iii) Emergency Alert Service Bulletin 

05.01.07, Revision 4, dated March 17, 2017. 

(iv) Emergency Alert Service Bulletin 

05.01.07, Revision 5, dated June 23, 2017. 

(v) Emergency Alert Service Bulletin 

05A049, Revision 2, dated October 7, 2016. 

(vi) Emergency Alert Service Bulletin 

05A049, Revision 3, dated February 25, 2017. 

(vii) Emergency Alert Service Bulletin 

05A049, Revision 4, dated March 17, 2017. 

(viii) Emergency Alert Service Bulletin 

05A049, Revision 5, dated June 23, 2017. 

(j) Special Flight Permit 

Special flight permits, as described in 14 

CFR 21.197 and 21.199, are prohibited. 


jbell on DSKJLSW7X2PROD with RULES
50230 Federal Register / Vol. 86, No. 171 / Wednesday, September 8, 2021 / Rules and Regulations 

(k) Alternative Methods of Compliance 

(AMOCs) 

(1) The Manager, International Validation 

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 local 

Flight Standards District Office, as 

appropriate. If sending information directly 

to the manager of the International Validation 

Branch, send it to the attention of the person 

identified in paragraph (l)(1) of this AD. 

Information may be emailed to: 9-AVS-AIR730-AMOC@faa.gov. 

(2) Before using any approved AMOC, 

notify your appropriate principal inspector, 

or lacking a principal inspector, the manager 

of the local flight standards district office/ 

certificate holding district office. 

(l) Related Information 

(1) For more information about this AD, 

contact Mahmood Shah, Aviation Safety 

Engineer, Fort Worth ACO Branch, FAA, 

10101 Hillwood Pkwy., Fort Worth, TX 

76177; telephone 817–222–5538; email 

mahmood.g.shah@faa.gov. 

(2) Service information identified in this 

AD that is not incorporated by reference is 

available at the addresses specified in 

paragraphs (m)(4) and (5) of this AD. 

(m) 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 this AD specifies otherwise. 

(i) European Union Aviation Safety Agency 

(EASA) AD 2017–0134R2, dated April 16, 

2020. 

(ii) Airbus Helicopters Emergency Alert 

Service Bulletin 05A049, Revision 6, dated 

July 25, 2017. 

(iii) Airbus Helicopters Emergency Alert 

Service Bulletin 05.01.07, Revision 6, dated 

July 27, 2017. 

(3) For EASA AD 2017–0134R2, contact the 

EASA, Konrad-Adenauer-Ufer 3, 50668 

Cologne, Germany; telephone +49 221 8999 

000; email ADs@easa.europa.eu; Internet 

www.easa.europa.eu. You may find this 

EASA AD on the EASA website at https://

ad.easa.europa.eu. 

(4) For Airbus Helicopters service 

information, contact Airbus Helicopters, 

2701 North Forum Drive, Grand Prairie, TX 

75052; telephone (972) 641–0000 or (800) 

232–0323; fax (972) 641–3775; or at https:// 

www.airbus.com/helicopters/services/ 

technical-support.html. 

(5) You may view this service information 

at the FAA, Office of the Regional Counsel, 

Southwest Region, 10101 Hillwood Pkwy., 

Room 6N–321, Fort Worth, TX 76177. For 

information on the availability of this 

material at the FAA, call 817–222–5110. This 

material may be found in the AD docket on 

the internet at https://www.regulations.gov 

by searching for and locating Docket No. 

FAA–2021–0379. 

(6) You may view this material that is 

incorporated by reference at the National 

Archives and Records Administration 

(NARA). For information on the availability 

of this material at NARA, email 

fr.inspection@nara.gov, or go to: https://

www.archives.gov/federal-register/cfr/ibrlocations.html. 

Issued on July 22, 2021. 

Gaetano A. Sciortino, 

Deputy Director for Strategic Initiatives, 

Compliance & Airworthiness Division, 

Aircraft Certification Service. 

[FR Doc. 2021–19247 Filed 9–7–21; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2021–0198; Project 

Identifier MCAI–2020–00950–E; Amendment 

39–21695; AD 2021–17–12] 

RIN 2120–AA64 

Airworthiness Directives; Rolls-Royce 

Deutschland Ltd & Co KG (Type 

Certificate Previously Held by RollsRoyce plc) Turbofan Engines 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule. 

SUMMARY: The FAA is superseding 

Airworthiness Directive (AD) 2020–13– 

07 for all Rolls-Royce Deutschland Ltd 

& Co KG (RRD) Trent 1000–D2, Trent 

1000–J2, and Trent 1000–K2 model 

turbofan engines with a certain partnumbered fuel pump installed. AD 

2020–13–07 required removal and 

replacement of the fuel pump with a 

part eligible for installation. This AD 

was prompted by the manufacturer’s 

investigation into an unexpected 

reduction in fuel pump performance in 

certain high life fuel pumps and 

subsequent determination that an 

additional part-numbered fuel pump is 

subject to the same unsafe condition. 

This AD requires new and reduced life 

limits for certain part-numbered fuel 

pumps, depending on the engine model 

the fuel pump is installed on. The FAA 

is issuing this AD to address the unsafe 

condition on these products. 

DATES: This AD is effective October 13, 

2021. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication listed in this AD 

as of October 13, 2021. 

ADDRESSES: For service information 

identified in this final rule, contact 

Rolls-Royce plc, P.O. Box 31, Derby, 

DE24 8BJ, United Kingdom; phone: +44 

(0)1332 242424; website: https://

www.rolls-royce.com/contact-us.aspx. 

You may view this service information 

at the FAA, Airworthiness Products 

Section, Operational Safety Branch, 

1200 District Avenue, Burlington, MA 

01803. For information on the 

availability of this material at the FAA, 

call (781) 238–7759. It is also available 

at http://www.regulations.gov by 

searching for and locating Docket No. 

FAA–2021–0198. 

Examining the AD Docket 

You may examine the AD docket at 

https://www.regulations.gov by 

searching for and locating Docket No. 

FAA–2021–0198; 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 

AD, the mandatory continuing 

airworthiness information (MCAI), any 

comments received, and other 

information. The address for Docket 

Operations is U.S. Department of 

Transportation, Docket Operations, M– 

30, West Building Ground Floor, Room 

W12–140, 1200 New Jersey Avenue SE, 

Washington, DC 20590. 

FOR FURTHER INFORMATION CONTACT: 

Kevin M. Clark, Aviation Safety 

Engineer, ECO Branch, FAA, 1200 

District Avenue, Burlington, MA 01803; 

phone: (781) 238–7088; fax: (781) 238– 

7199; email: kevin.m.clark@faa.gov. 

SUPPLEMENTARY INFORMATION: 

Background 

The FAA issued a notice of proposed 

rulemaking (NPRM) to amend 14 CFR 

part 39 to supersede AD 2020–13–07, 

Amendment 39–21152 (85 FR 38312, 

June 26, 2020), (AD 2020–13–07). AD 

2020–13–07 applied to all RRD Trent 

1000–D2, Trent 1000–J2, and Trent 

1000–K2 model turbofan engines with 

fuel pump, part number G5030FPU01, 

installed. The NPRM published in the 

Federal Register on March 30, 2021 (86 

FR 16548). The NPRM was prompted by 

the manufacturer’s investigation into an 

unexpected reduction in fuel pump 

performance in certain high life fuel 

pumps and life-related wear-out of the 

internal components and subsequent 

determination that an additional partnumbered fuel pump is subject to this 

same unsafe condition. In the NPRM, 

the FAA proposed to retain all the 

requirements of AD 2020–13–07. In the 

NPRM, the FAA also proposed to add an 

additional part-numbered fuel pump 

and additional Trent 1000 model 

turbofan engines on which this fuel 

pump is installed to the applicability. In 

the NPRM, the FAA also proposed to 

require new and reduced life limits for 

certain part-numbered fuel pumps, 


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