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

18079 

Vol. 82, No. 72 

Monday, April 17, 2017 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2015–7526; Directorate 

Identifier 2014–NM–217–AD; Amendment 

39–18852; AD 2017–08–03] 

RIN 2120–AA64 

Airworthiness Directives; Airbus 

Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Final rule. 

SUMMARY: We are adopting a new 

airworthiness directive (AD) for all 

Airbus Model A318, A319, A320–211, 

–212, –214, –231, –232, and –233 

airplanes, and A321 series airplanes. 

This AD was prompted by the discovery 

of corroded circlips in fuel vent 

protectors (FVP) having a certain part 

number. This AD requires an inspection 

to determine the part number and serial 

number of the FVP, and replacement if 

necessary; and application of sealant on 

certain nuts and bolts of the National 

Advisory Committee for Aeronautics 

(NACA) duct assembly. We are issuing 

this AD to address the unsafe condition 

on these products. 

DATES: This AD is effective May 22, 

2017. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication listed in this AD 

as of May 22, 2017. 

ADDRESSES: For service information 

identified in this final rule, contact 

Airbus, Airworthiness Office—EIAS, 1 

Rond Point Maurice Bellonte, 31707 

Blagnac Cedex, France; telephone +33 5 

61 93 36 96; fax +33 5 61 93 44 51; email 

account.airworth-eas@airbus.com; 

Internet http://www.airbus.com. You 

may view this referenced service 

information at the FAA, Transport 

Airplane Directorate, 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–2015– 

7526. 

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–2015– 

7526; or in person at the Docket 

Management Facility between 9 a.m. 

and 5 p.m., Monday through Friday, 

except Federal holidays. The AD docket 

contains this AD, the regulatory 

evaluation, any comments received, and 

other information. The street address for 

the Docket Office (telephone 800–647– 

5527) is Docket Management Facility, 

U.S. Department of Transportation, 

Docket Operations, M–30, West 

Building Ground Floor, Room W12–140, 

1200 New Jersey Avenue SE., 

Washington, DC 20590. 

FOR FURTHER INFORMATION CONTACT: 

Sanjay Ralhan, Aerospace Engineer, 

International Branch, ANM–116, 

Transport Airplane Directorate, FAA, 

1601 Lind Avenue SW., Renton, WA 

98057–3356; telephone 425–227–1405; 

fax 425–227–1149. 

SUPPLEMENTARY INFORMATION: 

Discussion 

We issued a supplemental notice of 

proposed rulemaking (SNPRM) to 

amend 14 CFR part 39 by adding an AD 

that would apply to all Airbus Model 

A318, A319, A320–211, –212, –214, 

–231, –232, and –233 airplanes, and 

A321 series airplanes. The SNPRM 

published in the Federal Register on 

October 21, 2016 (81 FR 72748) (‘‘the 

SNPRM’’). We preceded the SNPRM 

with a notice of proposed rulemaking 

(NPRM) that published in the Federal 

Register on December 23, 2015 (80 FR 

79742) (‘‘the NPRM’’). The NPRM 

proposed to require an inspection to 

determine the part number and serial 

number of the FVP, and replacement if 

necessary. The NPRM was prompted by 

the discovery of corroded circlips in 

FVPs having a certain part number. The 

SNPRM proposed to require an 

additional action for sealant application 

on some nuts and bolts on the NACA 

duct assembly, and to provide a grace 

period to the compliance time. We are 

issuing this AD to detect and correct 

corroded circlips. Such corrosion could 

lead to failure of the circlips and 

consequent movement of the FVP and 

result in a reduction of the flame 

protector capability of the FVP 

cartridge, which could result in damage 

to the airplane in case of lightning 

impact or fire on the ground. 

The European Aviation Safety Agency 

(EASA), which is the Technical Agent 

for the Member States of the European 

Union, has issued AD 2016–0114, dated 

June 15, 2016; corrected June 23, 2016 

(referred to after this as the Mandatory 

Continuing Airworthiness Information, 

or ‘‘the MCAI’’), to correct an unsafe 

condition for all Airbus Model A318, 

A319, A320–211, –212, –214, –231, 

–232, and –233 airplanes, and A321 

series airplanes. The MCAI states: 

On each aeroplane wing, a NACA duct 

assembly is installed, including a Fuel Vent 

Protector (FVP) which is used as flame 

arrestor. This FVP is maintained in its NACA 

duct assembly by a circlip (also known as Cclip). Following a wing water pressure test, 

the FVP is removed and dried with heat. 

During an inspection after this test, several 

circlips were reported to be discoloured. 

Investigation revealed that a batch of circlips 

fitted on some FVP Part Number (P/N) 

786073–1–0 have an increased risk of 

corrosion due to a manufacturing quality 

issue. 

This condition, if not detected and 

corrected, could lead to circlip failure and 

consequent FVP movement, reducing the 

flame protector capability of the FVP 

cartridge, possibly resulting in damage to the 

aeroplane in case of lightning impact or fire 

on ground. 

Airbus issued Service Bulletin (SB) A320– 

28–1221, providing instructions for 

identification by serial number (s/n) and 

removal from service of the affected FVP P/ 

N 786073–1–0, and EASA issued AD 2014– 

0234, later revised, to require those actions 

and to implement installation requirements 

for the FVP. 

After that [EASA] AD was issued, one step 

in the FVP re-installation instructions was 

identified as missing. Consequently, Airbus 

revised SB A320–28–1221 to provide 

instructions for sealant installation on some 

nuts and bolts on the NACA duct assembly. 

For the reasons described above, this 

[EASA] AD retains the requirements of EASA 

AD 2014–0234R1, which is superseded, and 

requires additional work for aeroplanes 

already modified in accordance with Airbus 

SB A320–28–1221 original issue or Revision 

01. 

You may examine the MCAI in the AD 

docket on the Internet at http://

www.regulations.gov by searching for 

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18080 Federal Register / Vol. 82, No. 72 / Monday, April 17, 2017 / Rules and Regulations 

and locating Docket No. FAA–2015– 

7526. 

Comments 

We gave the public the opportunity to 

participate in developing this AD. We 

received no comments on the SNPRM or 

on the determination of the cost to the 

public. 

Conclusion 

We reviewed the relevant data and 

determined that air safety and the 

public interest require adopting this AD 

as proposed except for minor editorial 

changes. We have determined that these 

minor changes: 

• Are consistent with the intent that 

was proposed in the SNPRM for 

correcting the unsafe condition; and 

• Do not add any additional burden 

upon the public than was already 

proposed in the SNPRM. 

Related Service Information Under 1 

CFR Part 51 

Airbus has issued Service Bulletin 

A320–28–1221, Revision 02, dated 

January 11, 2016. The service 

information describes procedures for 

inspecting the FVP to determine the part 

number and serial number, replacing 

any affected FVP, and applying sealant 

to the nuts and bolts of the NACA duct 

assembly. 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. 

Costs of Compliance 

We estimate that this AD affects 7 

airplanes of U.S. registry. We also 

estimate that it will take about 19 workhours per product to comply with the 

new basic requirements of this AD. The 

average labor rate is $85 per work-hour. 

Required parts will cost about $25,640 

per product. Based on these figures, we 

estimate the cost of this AD on U.S. 

operators to be $190,785, or $27,255 per 

product. 

Authority for This Rulemaking 

Title 49 of the United States Code 

specifies the FAA’s authority to issue 

rules on aviation safety. Subtitle I, 

section 106, describes the authority of 

the FAA Administrator. ‘‘Subtitle VII: 

Aviation Programs,’’ describes in more 

detail the scope of the Agency’s 

authority. 

We are issuing this rulemaking under 

the authority described in ‘‘Subtitle VII, 

Part A, Subpart III, Section 44701: 

General requirements.’’ Under that 

section, Congress charges the FAA with 

promoting safe flight of civil aircraft in 

air commerce by prescribing regulations 

for practices, methods, and procedures 

the Administrator finds necessary for 

safety in air commerce. This regulation 

is within the scope of that authority 

because it addresses an unsafe condition 

that is likely to exist or develop on 

products identified in this rulemaking 

action. 

Regulatory Findings 

We determined that 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 the 

DOT Regulatory Policies and Procedures 

(44 FR 11034, February 26, 1979); 

3. Will not affect intrastate aviation in 

Alaska; and 

4. Will not have a significant 

economic impact, positive or negative, 

on a substantial number of small entities 

under the criteria of the Regulatory 

Flexibility Act. 

List of Subjects in 14 CFR Part 39 

Air transportation, Aircraft, Aviation 

safety, Incorporation by reference, 

Safety. 

Adoption of the Amendment 

Accordingly, under the authority 

delegated to me by the Administrator, 

the FAA amends 14 CFR part 39 as 

follows: 

PART 39—AIRWORTHINESS 

DIRECTIVES 

■ 1. The authority citation for part 39 

continues to read as follows: 

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

§ 39.13 [Amended] 

■ 2. The FAA amends § 39.13 by adding 

the following new airworthiness 

directive (AD): 

2017–08–03 Airbus: Amendment 39–18852; 

Docket No. FAA–2015–7526; Directorate 

Identifier 2014–NM–217–AD. 

(a) Effective Date 

This AD is effective May 22, 2017. 

(b) Affected ADs 

None. 

(c) Applicability 

This AD applies to the airplanes specified 

in paragraphs (c)(1), (c)(2), (c)(3), and (c)(4) 

of this AD, certificated in any category, all 

manufacturer serial numbers. 

(1) Airbus Model A318–111, –112, –121, 

and –122 airplanes. 

(2) Airbus Model A319–111, –112, –113, 

–114, –115, –131, –132, and –133 airplanes. 

(3) Airbus Model A320–211, –212, –214, 

–231, –232, and –233 airplanes. 

(4) Airbus Model A321–111, –112, –131, 

–211, –212, –213, –231, and –232 airplanes. 

(d) Subject 

Air Transport Association (ATA) of 

America Code 28, Fuel. 

(e) Reason 

This AD was prompted by the discovery of 

corroded circlips in fuel vent protectors 

(FVP) having a certain part number. We are 

issuing this AD to detect and correct 

corroded circlips. Such corrosion could lead 

to failure of the circlips and consequent 

movement of the FVP and result in a 

reduction of the flame protector capability of 

the FVP cartridge, which could result in 

damage to the airplane in case of lightning 

impact or fire on the ground. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Inspection of FVP and Corrective Action 

For airplanes having a manufacturer serial 

number specified in figure 1 to paragraphs (g) 

and (i) of this AD: At the time specified in 

paragraph (h) of this AD, do an inspection to 

determine the part number and serial number 

of the FVP. If the FVP has part number (P/ 

N) 786073–1–0 with a serial number that is 

specified in figure 2 to paragraphs (g) and (i) 

of this AD, and the FVP is not marked ‘‘Amdt 

B,’’ replace the FVP with a serviceable part, 

at the time specified in paragraph (h) of this 

AD, in accordance with the Accomplishment 

Instructions of Airbus Service Bulletin A320– 

28–1221, Revision 02, dated January 11, 

2016. A review of airplane maintenance 

records is acceptable in lieu of this 

inspection if the part number and serial 

number of the FVP can be conclusively 

determined from that review. 

FIGURE 1 TO PARAGRAPHS (g) AND (i) OF THIS AD—AFFECTED AIRPLANE MANUFACTURER SERIAL NUMBERS

5438 5461 5485 through 5488 inclusive 5536 

5441 5463 5490 through 5493 inclusive 5539 

5444 5464 5495 through 5505 inclusive 5541 

5445 5469 5507 through 5515 inclusive 5544 

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Federal Register / Vol. 82, No. 72 / Monday, April 17, 2017 / Rules and Regulations 18081 

FIGURE 1 TO PARAGRAPHS (g) AND (i) OF THIS AD—AFFECTED AIRPLANE MANUFACTURER SERIAL NUMBERS—Continued 

5447 5473 through 5478 inclusive 5517 5547 

5457 5481 5518 5551 

5459 5482 5520 through 5527 inclusive 5553 

5460 5483 5530 5556 

FIGURE 2 TO PARAGRAPHS (g) AND (i) OF THIS AD—AFFECTED SERIAL NUMBERS FOR PART NUMBER 786073–1–0 

[Manufactured during August 2012] 

Serial No. 786073IN0xxxx (xxxx indicates the last four digits) 

3752 3821 3868 3911 3966 4010 

3753 3826 3871 3914 3967 4011 

3754 3827 3874 3922 3969 4013 

3755 3829 3877 3925 3971 4017 

3756 3830 3878 3927 3972 4019 

3757 3833 3882 3930 3977 4023 

3758 3834 3893 3937 3978 4024 

3759 3836 3897 3938 3980 4025 

3760 3839 3898 3940 3981 4026 

3761 3840 3899 3945 3982 4039 

3787 3848 3900 3946 3983 4048 

3788 3849 3901 3947 3984 4065 

3810 3850 3904 3948 3985 4066 

3812 3851 3905 3951 3986 4068 

3814 3853 3906 3961 3987 4070 

3817 3859 3907 3962 3996 4184 

3819 3860 3908 3964 3997 4187 

3820 3867 3910 3965 4009 None 

(h) Compliance Times for the Requirements 

of Paragraph (g) of This AD 

Do the actions required by paragraph (g) of 

this AD at the earliest of the times specified 

in paragraphs (h)(1), (h)(2), and (h)(3) of this 

AD, or within 30 days after the effective date 

of this AD, whichever occurs later. 

(1) Before the accumulation of 5,000 total 

flight cycles after the date of manufacture of 

the airplane. 

(2) Before the accumulation of 7,500 total 

flight hours after the date of manufacture of 

the airplane. 

(3) Within 30 months after the date of 

manufacture of the airplane. 

(i) Exclusion From Actions Required by 

Paragraph (g) of This AD 

An airplane that does not have a 

manufacturer serial number specified in 

figure 1 to paragraphs (g) and (i) of this AD 

is excluded from the requirements of 

paragraph (g) of this AD, provided that a FVP 

having P/N 786073–1–0 with a serial number 

specified in figure 2 to paragraphs (g) and (i) 

of this AD has not been installed on that 

airplane after July 2012. If a FVP having P/ 

N 786073–1–0 with a serial number specified 

in figure 2 to paragraphs (g) and (i) of this 

AD is installed, or the serial number cannot 

be identified: Within 12 months after the 

effective date of this AD, replace the FVP 

with a serviceable part, in accordance with 

the Accomplishment Instructions of Airbus 

Service Bulletin A320–28–1221, Revision 02, 

dated January 11, 2016. A review of airplane 

maintenance records is acceptable if it can be 

conclusively determined from that review 

that a FVP having a serial number specified 

in figure 2 to paragraphs (g) and (i) of this 

AD has not been installed on that airplane 

after July 2012. 

(j) Parts Installation Limitation 

As of the effective date of this AD, a FVP 

having P/N 786073–1–0 and a serial number 

listed in figure 2 to paragraphs (g) and (i) of 

this AD may be installed on any airplane, 

provided the FVP is marked with ‘‘Amdt B.’’ 

(k) Other FAA AD Provisions 

The following provisions also apply to this 

AD: 

(1) Alternative Methods of Compliance 

(AMOCs): The Manager, International 

Branch, ANM–116, Transport Airplane 

Directorate, 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 International Branch, send it to ATTN: 

Sanjay Ralhan, Aerospace Engineer, 

International Branch, ANM–116, Transport 

Airplane Directorate, FAA, 1601 Lind 

Avenue SW., Renton, WA 98057–3356; 

telephone 425–227–1405; fax 425–227–1149. 

Information may be emailed to: 9-ANM-116- 

AMOC-REQUESTS@faa.gov. 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. 

(2) Contacting the Manufacturer: For any 

requirement in this AD to obtain corrective 

actions from a manufacturer, the action must 

be accomplished using a method approved 

by the Manager, International Branch, ANM– 

116, Transport Airplane Directorate, FAA; or 

the European Aviation Safety Agency 

(EASA); or Airbus’s EASA Design 

Organization Approval (DOA). If approved by 

the DOA, the approval must include the 

DOA-authorized signature. 

(3) Required for Compliance (RC): If any 

service information contains procedures or 

tests that are identified as RC, those 

procedures and tests must be done to comply 

with this AD; any procedures or tests that are 

not identified as RC are recommended. Those 

procedures and tests that are not identified 

as RC may be deviated from using accepted 

methods in accordance with the operator’s 

maintenance or inspection program without 

obtaining approval of an AMOC, provided 

the procedures and tests identified as RC can 

be done and the airplane can be put back in 

an airworthy condition. Any substitutions or 

changes to procedures or tests identified as 

RC require approval of an AMOC. 

(l) Related Information 

Refer to Mandatory Continuing 

Airworthiness Information (MCAI) EASA 

Airworthiness Directive 2016–0114, dated 

June 15, 2016; corrected June 23, 2016; for 

related information. This MCAI may be 

found in the AD docket on the Internet at 

http://www.regulations.gov by searching for 

and locating Docket No. FAA–2015–7526. 

(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) Airbus Service Bulletin A320–28–1221, 

Revision 02, dated January 11, 2016. 

(ii) Reserved. 

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(3) For service information identified in 

this AD, contact Airbus, Airworthiness 

Office—EIAS, 1 Rond Point Maurice 

Bellonte, 31707 Blagnac Cedex, France; 

telephone +33 5 61 93 36 96; fax +33 5 61 

93 44 51; email account.airworth-eas@

airbus.com; Internet http://www.airbus.com. 

(4) You may view this service information 

at the FAA, Transport Airplane Directorate, 

1601 Lind Avenue SW., Renton, WA. For 

information on the availability of this 

material at the FAA, call 425–227–1221. 

(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, call 

202–741–6030, or go to: http://

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

Issued in Renton, Washington, on March 

31, 2017. 

Michael Kaszycki, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2017–07076 Filed 4–14–17; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2016–9167; Directorate 

Identifier 2016–NE–20–AD; Amendment 39– 

18855; AD 2017–08–06] 

RIN 2120–AA64 

Airworthiness Directives; General 

Electric Company Turbofan Engines 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule. 

SUMMARY: We are adopting a new 

airworthiness directive (AD) for certain 

General Electric Company (GE) GE90 

turbofan engines. This AD was 

prompted by a report of an engine and 

airplane fire. This AD requires replacing 

affected fuel/oil lube/servo coolers 

(‘‘main fuel oil heat exchangers’’) with 

a part eligible for installation. We are 

issuing this AD to correct the unsafe 

condition on these products. 

DATES: This AD is effective May 22, 

2017. 

The Director of the Federal Register 

approved the incorporation by reference 

of certain publications listed in this AD 

as of May 22, 2017. 

ADDRESSES: For service information 

identified in this final rule, contact 

General Electric Company, GE-Aviation, 

Room 285, 1 Neumann Way, Cincinnati, 

OH 45215, phone: 513–552–3272; email: 

aviation.fleetsupport@ge.com. You may 

view this referenced service information 

at the FAA, You may view this service 

information at the FAA, Engine & 

Propeller Directorate, 1200 District 

Avenue, Burlington, MA. For 

information on the availability of this 

material at the FAA, call 781–238–7125. 

It is also available on the internet at 

http://www.regulations.gov by searching 

for and locating Docket No. FAA–2016– 

9167. 

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–2016– 

9167; or in person at the Docket 

Management Facility between 9 a.m. 

and 5 p.m., Monday through Friday, 

except Federal holidays. The AD docket 

contains this AD, the regulatory 

evaluation, any comments received, and 

other information. The address for the 

Docket Office (phone: 800–647–5527) is 

Document Management Facility, U.S. 

Department of Transportation, Docket 

Operations, M–30, West Building 

Ground Floor, Room W12–140, 1200 

New Jersey Avenue SE., Washington, 

DC 20590. 

FOR FURTHER INFORMATION CONTACT: John 

Frost, Aerospace Engineer, Engine 

Certification Office, FAA, 1200 District 

Avenue, Burlington, MA 01803; phone: 

781–238–7756; fax: 781–238–7199; 

email: john.frost@faa.gov. 

SUPPLEMENTARY INFORMATION: 

Discussion 

We issued a notice of proposed 

rulemaking (NPRM) to amend 14 CFR 

part 39 by adding an AD that would 

apply to certain GE GE90 turbofan 

engines. The NPRM published in the 

Federal Register on December 7, 2016 

(81 FR 88145) (‘‘the NPRM’’). The 

NPRM was prompted by a report of an 

engine and airplane fire. The NPRM 

proposed to require replacing affected 

fuel/oil lube/servo coolers (‘‘main fuel 

oil heat exchangers’’) with a part eligible 

for installation. We are issuing this AD 

to prevent failure of a main fuel oil heat 

exchanger, which could result in an 

engine fire. 

Comments 

We gave the public the opportunity to 

participate in developing this AD. The 

following presents the comments 

received on the NPRM and the FAA’s 

response to each comment. 

Request To Revise Applicability 

Reference 

All Nippon Airways, MTU 

Maintenance Hannover GmbH (MTU), 

and Air New Zealand commented that 

this AD should list all vendor part 

numbers referenced in GE Service 

Bulletin (SB) GE90–100 S/B 79–0034, 

Revision 03, dated August 5, 2016. This 

would ensure that the applicability of 

the AD is not misinterpreted. 

We agree. We changed this AD by 

adding a reference in the Applicability 

paragraph to the respective vendor 

number after the part number. 

Request To Clarify Tracking of 

Accomplishment of AD 

MTU commented that clarification of 

the accomplishment of this AD is 

needed because GE SB GE90–100 S/B 

79–0034, Revision 03, dated August 5, 

2016, requires marking repaired parts 

with the suffix ‘‘A’’ at the end of the 

serial number but the proposed AD does 

not. MTU indicated that ‘‘GE fleet 

highlites’’ note that the suffix is not part 

of the actual serial number and must not 

appear on EASA or FAA documents. 

We disagree. Although we are not 

requiring that parts be marked with the 

suffix ‘‘A’’ to reflect compliance with 

this AD, these parts are typically 

marked after repair per the requirements 

of GE SB GE90–100 S/B 79–0034. 

Operators are free, however, to devise 

an alternate tracking system, i.e. through 

part markings and/or records, to show 

that the part has been repaired and is 

eligible for installation. We did not 

change this AD. 

Request To Reference Latest Service 

Bulletin 

MTU requested that we change the 

reference to GE SB GE90–100 S/B 79– 

0034, Revision 03, dated August 5, 

2016, to the ‘‘latest version’’ of this SB. 

We disagree. We cannot require 

compliance to a document that does not 

exist. We note that operators may 

submit a request for an alternate method 

of compliance if this SB is revised after 

the publication of this AD. We did not 

change this AD. 

Request To Revise References to Main 

Heat Exchanger 

GE requested that references in the 

AD to the ‘‘main heat exchanger’’ be 

changed to the ‘‘main fuel oil heat 

exchanger’’ and/or the ‘‘MFOHE.’’ GE 

indicated that ‘‘main fuel oil heat 

exchanger’’ is the term that it uses in 

communications with its operators. 

We agree. We changed references in 

this AD from ‘‘main heat exchanger’’ to 

‘‘main fuel oil heat exchanger.’’ 

Request To Revise Description of 

Incident and Unsafe Condition 

Statement 

GE requested that we revise the 

discussion in the NPRM of the cause of 

the incident and the unsafe condition 

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