This section of the FEDERAL REGISTER

contains regulatory documents having general

applicability and legal effect, most of which

are keyed to and codified in the Code of

Federal Regulations, which is published under

50 titles pursuant to 44 U.S.C. 1510.

The Code of Federal Regulations is sold by

the Superintendent of Documents.

Rules and Regulations Federal Register

43827 

Vol. 82, No. 181 

Wednesday, September 20, 2017 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 33 

[Docket No. FAA–2017–0586; Special 

Conditions No. 33–019–SC] 

Special Conditions: Safran Aircraft 

Engines, Silvercrest-2 SC–2D; Rated 

Takeoff Thrust at High Ambient 

Temperature 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final special conditions. 

SUMMARY: These special conditions are 

issued for the Safran Aircraft Engines 

(SAE), Silvercrest-2 SC–2D engine 

model. This engine model will have a 

novel or unusual design feature 

associated with an additional takeoff 

rating that maintains takeoff thrust in 

certain high ambient temperature 

conditions for a maximum accumulated 

usage of 20 minutes in any one flight. 

The applicable airworthiness 

regulations do not contain adequate or 

appropriate safety standards for this 

design feature. These special conditions 

contain the additional safety standards 

that the Administrator considers 

necessary to establish a level of safety 

equivalent to that established by the 

existing airworthiness standards. 

DATES: Effective September 20, 2017. 

FOR FURTHER INFORMATION CONTACT: Tara 

Fitzgerald, AIR–6A1, Engine and 

Propeller Standards Branch, Aircraft 

Certification Service, 1200 District 

Avenue, Burlington, Massachusetts 

01803–5213; telephone (781) 238–7130; 

facsimile (781) 238–7199; email 

Tara.Fitzgerald@faa.gov. 

SUPPLEMENTARY INFORMATION: Under 

standard practice, the effective date of 

final special conditions would be 30 

days after the date of publication in the 

Federal Register. However, as the 

certification date for the SAE, 

Silvercrest-2 SC–2D engine model is 

imminent; the FAA finds that good 

cause exists to make these special 

conditions effective upon publication. 

Background 

On April 19, 2011, SNECMA, now 

known as SAE, applied for a type 

certificate for the Silvercrest-2 SC–2D 

engine model. On April 30, 2014, SAE 

requested an extension to their original 

type certificate application, which the 

FAA granted through June 30, 2015. On 

May 26, 2015, SAE requested another 

extension to their type certificate 

application, which the FAA granted 

through September 30, 2018. 

SAE proposed an additional takeoff 

rating that maintains takeoff thrust in 

certain high ambient temperature 

conditions with all engines operating 

(AEO) for the Silvercrest-2 SC–2D 

engine model. Therefore, the 

Silvercrest-2 SC–2D engine model 

would have two different takeoff ratings. 

The first rating corresponds with the 

rated takeoff thrust of the engine. The 

second rating maintains the takeoff 

thrust in certain high ambient 

temperature conditions. This additional 

takeoff rating is named ‘‘Rated Takeoff 

Thrust at High Ambient Temperature’’ 

(Rated TOTHAT). The ‘‘Rated 

TOTHAT’’ is an approved engine thrust 

developed under specified altitudes and 

temperatures within the operating 

limitations established for the engine 

during takeoff operation for a maximum 

usage of 20 minutes in any one flight. 

Type Certification Basis 

Under the provisions of Title 14, Code 

of Federal Regulations (14 CFR) 21.17, 

SAE must show that the Silvercrest-2 

SC–2D engine model meets the 

applicable provisions of 14 CFR part 33, 

amendments 33–1 through 33–34 in 

effect on the date of application. The 

FAA has determined that the applicable 

airworthiness regulations in part 33 do 

not contain adequate or appropriate 

safety standards for the Silvercrest-2 

SC–2D engine model because of their 

novel and unusual design feature 

referred to as ‘‘Rated TOTHAT’’. 

Therefore, these special conditions are 

prescribed under the provisions of 14 

CFR 11.19 and 14 CFR 21.16, and will 

become part of the type certification 

basis for Silvercrest-2 SC–2D engine 

models in accordance with § 21.17(a)(2). 

If the Administrator finds that the 

applicable airworthiness regulations do 

not contain adequate or appropriate 

safety standards for the SAE, 

Silvercrest-2 SC–2D engine model 

because of a novel or unusual design 

feature, special conditions are 

prescribed under the provisions of 

§ 21.16. 

Special conditions are initially 

applicable to the engine model for 

which they are issued. Should the type 

certificate for that engine model be 

amended later to include any other 

engine model(s) that incorporates the 

same novel or unusual design feature, 

the special conditions would also apply 

to the other engine models under 

§ 21.101. 

In addition to complying with the 

applicable product airworthiness 

regulations and special conditions, the 

Silvercrest-2 SC–2D engine model must 

comply with the fuel venting and 

exhaust emission requirements of 14 

CFR part 34. 

Novel or Unusual Design Features 

The Silvercrest-2 SC–2D engine 

model will incorporate a novel or 

unusual design feature, referred to as 

‘‘Rated TOTHAT’’. This additional 

takeoff rating increases the exhaust gas 

temperature (EGT) limit that maintains 

takeoff thrust in certain high ambient 

temperature conditions for a maximum 

of 20 minutes in any one flight. 

Discussion 

The ‘‘Rated TOTHAT’’ is designed for 

use during takeoff in specified high 

altitudes and high ambient temperature 

conditions. It maintains thrust during 

takeoff for a maximum of 20 minutes in 

any one flight. These special conditions 

contain additional mandatory post-flight 

inspection and maintenance action 

requirements associated with any use of 

the ‘‘Rated TOTHAT’’. These 

requirements add a rating definition in 

paragraph 1.1 below and mandate 

required inspections in the instructions 

for continued airworthiness (ICA); 

instructions for installing and operating 

the engine; engine rating and operating 

limitations; instrument connection; and 

endurance testing. 

The current requirements of the 

endurance test under 14 CFR 33.87 

represent a typical airplane flight profile 

and the severity of the takeoff rating. 

Therefore, the endurance test under 

§ 33.87 covers normal, AEO takeoff 

conditions for which the engine control 

system limits the engine to the takeoff 

thrust rating. It is intended to represent 


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43828 Federal Register / Vol. 82, No. 181 / Wednesday, September 20, 2017 / Rules and Regulations 

the airplane flight profile during takeoff 

under specified ambient temperatures 

for a time until the mandatory 

inspection and maintenance actions can 

be performed. 

These special conditions require 

additional test cycles that include at 

least a 150 hours of engine operation as 

specified in § 33.87(a), to demonstrate 

the engine is capable of performing the 

‘‘Rated TOTHAT’’ rating during AEO 

conditions without disassembly or 

modification. 

The associated engine deterioration, 

after use of the ‘‘Rated TOTHAT’’, is not 

known without the intervening 

mandatory inspections in these special 

conditions. These mandatory 

inspections ensure the engine will 

continue to comply with its certification 

basis, which includes these special 

conditions, after any use of the ‘‘Rated 

TOTHAT’’. The applicant is expected to 

assess the deterioration from use of the 

‘‘Rated TOTHAT’’. The airworthiness 

limitations section (ALS) must prescribe 

the mandatory post-flight inspections 

and maintenance actions associated 

with any use of the ‘‘Rated TOTHAT’’. 

These requirements maintain a level 

of safety equivalent to the level 

intended by the applicable 

airworthiness standards in effect on the 

date of application. 

Discussion of Comments 

Notice of proposed special conditions 

No. 33–17–01–SC for the SAE, 

Silvercrest-2 SC–2D; Rated Takeoff 

Thrust at High Ambient Temperature 

engine model was published in the 

Federal Register on July 03, 2017 (82 FR 

30800). No comments were received, 

and the special conditions are adopted 

as proposed. 

Applicability 

As discussed above, these special 

conditions are applicable to the 

Silvercrest-2 SC–2D engine model. 

Should SAE apply at a later date for a 

change to the type certificate to include 

another model on the same type 

certificate incorporating the same novel 

or unusual design feature, these special 

conditions would apply to that model as 

well. 

Conclusion 

This action affects only the ‘‘Rated 

TOTHAT’’ features on Silvercrest-2 SC– 

2D engine models. It is not a rule of 

general applicability and applies only to 

SAE who requested FAA approval of 

this engine feature. 

List of Subjects in 14 CFR Part 33 

Aircraft, Engines, Aviation Safety, 

Reporting and Recordkeeping 

requirements. 

The authority citation for these 

special conditions is as follows: 

Authority: 49 U.S.C. 106(g), 40113, 44701, 

44702, 44704. 

The Special Conditions 

Accordingly, pursuant to the 

authority delegated to me by the 

Administrator, the following special 

conditions are issued as part of the type 

certification basis for SAE, Silvercrest-2 

SC–2D engine model. 

1. Part 1 Definition. 

‘‘Rated Take-off Thrust at High 

Ambient Temperature’’ (Rated 

TOTHAT) means the approved engine 

thrust developed under specified 

altitudes and temperatures within the 

operating limitations established for the 

engine during takeoff operation. Use is 

limited to two periods, no longer than 

10 minutes each under one engine 

inoperative (OEI) conditions or 5 

minutes each under all engines 

operating (AEO) conditions in any one 

flight for a maximum accumulated 

usage of 20 minutes in any one flight. 

Each flight where the ‘‘Rated TOTHAT’’ 

is used must be followed by mandatory 

inspection and maintenance actions. 

2. Part 33 Requirements. 

In addition to the airworthiness 

standards in 14 CFR part 33, effective 

February 1, 1965, which are applicable 

to the engine and the ‘‘Rated TOTHAT’’, 

the following special conditions apply: 

(a) Section 33.4, Instructions for 

Continued Airworthiness. 

(1) The ALS must prescribe the 

mandatory post-flight inspections and 

maintenance actions associated with 

any use of the ‘‘Rated TOTHAT’’. 

(2) The applicant must validate the 

adequacy of the inspections and 

maintenance actions required under 

paragraph 2(a)(1) of these special 

conditions. 

(3) The applicant must establish an 

in-service engine evaluation program to 

ensure the continued adequacy of the 

instructions for mandatory post-flight 

inspections and maintenance actions 

prescribed under paragraph 2(a)(1) of 

these special conditions, and of the data 

for thrust assurance procedures required 

by paragraph 2(b)(2) of these special 

conditions. The program must include 

service engine tests or equivalent 

service engine test experience on 

engines of similar design and 

evaluations of service usage of the 

‘‘Rated TOTHAT’’. 

(b) Section 33.5, Instruction manual 

for installing and operating the engine. 

(1) Installation Instructions: 

(i) The applicant must identify the 

means, or provisions for means, 

provided in compliance with the 

requirements of paragraph 2(e) of these 

special conditions. 

(ii) The applicant must specify that 

the engine thrust control system 

automatically resets the thrust on the 

operating engine to the ‘‘Rated 

TOTHAT’’ level when one engine fails 

during takeoff at specified altitudes and 

temperatures. 

(iii) The applicant must specify that 

the ‘‘Rated TOTHAT’’ is available by 

manual crew selection at specified 

altitudes and temperatures in AEO 

conditions. 

(2) Operating Instructions: The 

applicant must provide data on engine 

performance characteristics and 

variability to enable the airplane 

manufacturer to establish airplane 

thrust assurance procedures. 

(c) Section 33.7, Engine ratings and 

operating limitations. 

(1) ‘‘Rated TOTHAT’’ and the 

associated operating limitations are 

established as follows: 

(i) The thrust is the same as the 

engine takeoff rated thrust with 

extended flat rating corner point. 

(ii) The rotational speed limits are the 

same as those associated with the 

engine takeoff rated thrust. 

(iii) The applicant must establish a 

gas temperature steady-state limit and, if 

necessary, a transient gas over 

temperature limit for which the 

duration is no longer than 30 seconds. 

(iv) The use is limited to two periods 

of no longer than 10 minutes each under 

OEI conditions or 5 minutes each under 

AEO conditions in any one flight, for a 

maximum accumulated usage of 20 

minutes in any one flight. Each flight 

where the ‘‘Rated TOTHAT’’ is used 

must be followed by mandatory 

inspections and maintenance actions 

prescribed by paragraph 2(a)(1) of these 

special conditions. 

(2) The applicant must propose 

language to include in the type 

certificate data sheet specified in 14 

CFR 21.41 for the following: 

(i) ‘‘Rated TOTHAT’’ and associated 

limitations. 

(ii) As required by 14 CFR 33.5(b), 

Operating instructions, include a note 

stating that ‘‘Rated Takeoff Thrust at 

High Ambient Temperature (Rated 

TOTHAT) means the approved engine 

thrust developed under specified 

altitudes and temperatures within the 

operating limitations established for the 

engine. Use is limited to two periods, no 

longer than 10 minutes each under OEI 


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Federal Register / Vol. 82, No. 181 / Wednesday, September 20, 2017 / Rules and Regulations 43829 

conditions or 5 minutes each under 

AEO conditions in any one flight, for a 

maximum accumulated usage of 20 

minutes in any one flight. Each flight 

where the ‘‘Rated TOTHAT’’ is used 

must be followed by mandatory 

inspection and maintenance actions.’’ 

(iii) As required by § 33.5(b), 

Operating instructions, include a note 

stating that ‘‘the engine thrust control 

system automatically resets the thrust 

on the operating engine to the ‘‘Rated 

TOTHAT’’ level when one engine fails 

during takeoff at specified altitudes and 

temperatures, and the ‘‘Rated TOTHAT’’ 

is available by manual selection when 

all engines are operational during 

takeoff at specified altitudes and 

temperatures.’’ 

(d) Section 33.28, Engine Control 

Systems. 

The engine must incorporate a means, 

or a provision for a means, for automatic 

availability and automatic control of the 

‘‘Rated TOTHAT’’ under OEI conditions 

and must permit manual activation of 

the ‘‘Rated TOTHAT’’ under AEO 

conditions. 

(e) Section 33.29, Instrument 

connection. 

The engine must: 

(1) Have means, or provisions for 

means, to alert the pilot when the 

‘‘Rated TOTHAT’’ is in use, when the 

event begins and when the time interval 

expires. 

(2) Have means, or provision for 

means, which cannot be reset in flight, 

to: 

(i) Automatically record each use and 

duration of the ‘‘Rated TOTHAT’’, and 

(ii) Alert maintenance personnel that 

the engine has been operated at the 

‘‘Rated TOTHAT’’ and permit retrieval 

of recorded data. 

(3) Have means, or provision for 

means, to enable routine verification of 

the proper operation of the means in 

paragraph 2(e)(1) and (e)(2) of these 

special conditions. 

(f) Section 33.85(b), Calibration tests. 

The applicant must base the 

calibration test on the thrust check at 

the end of the endurance test required 

by § 33.87 of these special conditions. 

(g) Section 33.87, Endurance test. 

(1) In addition to the applicable 

requirements of § 33.87(a): 

(i) The § 33.87 endurance test must be 

modified as follows: 

(A) Modify the 30 minute test cycle at 

the rated takeoff thrust in 

§ 33.87(b)(2)(ii) to run one minute at 

rated takeoff thrust, followed by five 

minutes at the ‘‘Rated TOTHAT’’, 

followed by the rated takeoff thrust for 

the remaining twenty-four minutes. 

(B) The modified 30 minute period 

described above in paragraph 

2(g)(1)(i)(A) must be repeated ten times 

in cycles 16 through 25 of the § 33.87 

endurance test. 

(2) After completion of the tests 

required by § 33.87(b), as modified in 

paragraph 2(g)(1)(i) above, and without 

intervening disassembly, except as 

needed to replace those parts described 

as consumables in the ICA, the 

applicant must conduct the following 

test sequence for a total time of not less 

than 120 minutes: 

(i) Ten minutes at ‘‘Rated TOTHAT’’. 

(ii) Eighty-eight minutes at rated 

maximum continuous thrust. 

(iii) One minute at 50 percent of rated 

takeoff thrust. 

(iv) Ten minutes at ‘‘Rated TOTHAT’’. 

(v) Ten minutes at rated maximum 

continuous thrust. 

(vi) One minute at flight idle. 

(3) The test sequence of §§ 33.87(b)(1) 

through (b)(6) of these special 

conditions must be run continuously. If 

a stop occurs during these tests, the 

interrupted sequence must be repeated 

unless the applicant shows that the 

severity of the test would not be 

reduced if the current tests were 

continued. 

(4) Where the engine characteristics 

are such that acceleration to the ‘‘Rated 

TOTHAT’’ results in a transient over 

temperature in excess of the steady-state 

temperature limit identified in 

paragraph 2(c)(1)(iii) of these special 

conditions, the transient gas over 

temperature must be applied to each 

acceleration to the ‘‘Rated TOTHAT’’ of 

the test sequence in paragraph 2(g)(2) of 

these special conditions. 

(h) Section 33.93, Teardown 

inspection. 

The applicant must perform the 

teardown inspection required by 

§ 33.93(a), after completing the 

endurance test prescribed by § 33.87 of 

these special conditions. 

(i) Section 33.201, Design and test 

requirements for Early ETOPS 

eligibility. 

In addition to the requirements of 

§ 33.201(c)(1), the simulated ETOPS 

mission cyclic endurance test must 

include two cycles of 10 minute 

duration, each at the ‘‘Rated TOTHAT’’; 

one before the last diversion cycle and 

one at the end of the ETOPS test. 

Issued in Burlington, Massachusetts on 

August 23, 2017. 

Karen M. Grant 

Acting Manager, Engine and Propeller 

Standards Branch, Aircraft Certification 

Service. 

[FR Doc. 2017–19952 Filed 9–19–17; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2017–0334; Product 

Identifier 2017–NM–008–AD; Amendment 

39–19039; AD 2017–19–09] 

RIN 2120–AA64 

Airworthiness Directives; Bombardier, 

Inc., Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Final rule. 

SUMMARY: We are superseding 

Airworthiness Directive (AD) 2014–25– 

01, which applied to certain 

Bombardier, Inc., Model DHC–8–400 

series airplanes. AD 2014–25–01 

required modifying the nose landing 

gear (NLG) trailing arm and installing a 

new pivot pin retention mechanism. 

This AD instead requires modifying the 

NLG shock strut assembly. This AD was 

prompted by reports of discrepancies of 

a certain bolt at the pivot pin link, 

resulting in corrosion of the bolt. We are 

issuing this AD to address the unsafe 

condition on these products. 

DATES: This AD is effective October 24, 

2017. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication listed in this AD 

as of October 24, 2017. 

ADDRESSES: For service information 

identified in this final rule, contact 

Bombardier, Inc., Q-Series Technical 

Help Desk, 123 Garratt Boulevard, 

Toronto, Ontario M3K 1Y5, Canada; 

telephone 416–375–4000; fax 416–375– 

4539; email thd.qseries@

aero.bombardier.com; Internet http://

www.bombardier.com. You may view 

this referenced service information at 

the FAA, Transport Standards Branch, 

1601 Lind Avenue SW., Renton, WA. 

For information on the availability of 

this material at the FAA, call 425–227– 

1221. It is also available on the Internet 

at http://www.regulations.gov by 

searching for and locating Docket No. 

FAA–2017–0334. 

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–2017– 

0334; 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 


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