2896 Federal Register / Vol. 83, No. 14 / Monday, January 22, 2018 / Rules and Regulations 

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): 

2018–02–11 Airbus: Amendment 39–19164; 

Docket No. FAA–2018–0023; Product 

Identifier 2017–NM–084–AD. 

(a) Effective Date 

This AD becomes effective February 6, 

2018. 

(b) Affected ADs 

None. 

(c) Applicability 

This AD applies to Airbus Model A330– 

301, –321, –322 and A330–342 airplanes, 

certificated in any category, manufacturer 

serial numbers 0012, 0017, 0030, 0037, 0045, 

0050, 0060, 0062, 0064, 0065, 0071, 0082, 

0083, 0098, 0099, 0102, 0106, 0109, 0112, 

0132 and 0177. 

(d) Subject 

Air Transport Association (ATA) of 

America Code 55, Stabilizers. 

(e) Reason 

This AD was prompted by a report of 

cracking in the top skin of the horizontal 

stabilizer (HS) center box (CB) of an airplane 

in pre-modification 41330 configuration. We 

are issuing this AD to detect and correct 

cracking in the HS CB, which could lead to 

reduced structural integrity of the airplane. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Required Action(s) 

Within 30 days after the effective date of 

this AD, request instructions from the 

Manager, International Section, Transport 

Standards Branch, FAA, to address the 

unsafe condition specified in paragraph (e) of 

this AD; and accomplish the actions at the 

times specified in, and in accordance with, 

those instructions. Guidance can be found in 

Mandatory Continuing Airworthiness 

Information (MCAI) European Aviation 

Safety Agency (EASA) AD 2017–0078, dated 

May 3, 2017. 

(h) Alternative Methods of Compliance 

(AMOCs) 

The Manager, International Section, 

Transport Standards 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 International Section, send it to the 

attention of the person identified in 

paragraph (j)(2) of this AD. Information may 

be emailed to: 9-ANM-116-AMOCREQUESTS@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. 

(i) Paperwork Reduction Act Burden 

Statement 

A federal agency may not conduct or 

sponsor, and a person is not required to 

respond to, nor shall a person be subject to 

a 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 OMB Control Number for this 

information collection is 2120–0056. Public 

reporting for this collection of information is 

estimated to be approximately 1 hour per 

response, including the time for reviewing 

instructions, completing and reviewing the 

collection of information. All responses to 

this collection of information are mandatory. 

Comments concerning the accuracy of this 

burden and suggestions for reducing the 

burden should be directed to the FAA at: 800 

Independence Ave. SW, Washington, DC 

20591, Attn: Information Collection 

Clearance Officer, AES–200. 

(j) Related Information 

(1) Refer to MCAI EASA AD 2017–0078, 

dated May 3, 2017, for related information. 

You may examine the MCAI on the internet 

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

for and locating Docket No. FAA–2018–0023. 

(2) For more information about this AD, 

contact Vladimir Ulyanov, Aerospace 

Engineer, International Section, Transport 

Standards Branch, FAA, 1601 Lind Avenue 

SW, Renton, WA 98057–3356; telephone: 

425–227–1138; fax: 425–227–1149. 

(k) Material Incorporated by Reference 

None. 

Issued in Renton, Washington, on January 

10, 2018. 

John P. Piccola, Jr., 

Acting Director, System Oversight Division, 

Aircraft Certification Service. 

[FR Doc. 2018–00949 Filed 1–19–18; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2017–0719; Product 

Identifier 2017–NE–22–AD; Amendment 39– 

19163; AD 2018–02–10] 

RIN 2120–AA64 

Airworthiness Directives; Pratt & 

Whitney Division Turbofan Engines 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule. 

SUMMARY: We are adopting a new 

airworthiness directive (AD) for all Pratt 

& Whitney Division (PW) PW4074, 

PW4074D, PW4077, PW4077D, 

PW4084D, PW4090, and PW4090–3 

turbofan engines. This AD was 

prompted by the discovery of multiple 

cracked outer diffuser cases. This AD 

requires initial and repetitive 

inspections to detect cracks in the outer 

diffuser case and removal from service 

of cases that fail inspection. We are 

issuing this AD to address the unsafe 

condition on these products. 

DATES: This AD is effective February 26, 

2018. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication listed in this AD 

as of February 26, 2018. 

ADDRESSES: For service information 

identified in this final rule, contact Pratt 

& Whitney Division, 400 Main St., East 

Hartford, CT 06118; phone: 800–565– 

0140; fax: 860–565–5442. You may view 

this service information at the FAA, 

Engine and Propeller Standards Branch, 

1200 District Avenue, Burlington, MA. 

For information on the availability of 

this material at the FAA, call 781–238– 

7759. It is also available on the internet 

at http://www.regulations.gov by 

searching for and locating Docket No. 

FAA–2017–0719. 

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– 

0719; or in person at Docket Operations 

between 9 a.m. and 5 p.m., Monday 

through Friday, except Federal holidays. 

The AD docket contains this final rule, 

the regulatory evaluation, any 

comments received, and other 

information. The address for Docket 

Operations (phone: 800–647–5527) is 

Document Operations, U.S. Department 

of Transportation, Docket Operations, 

M–30, West Building Ground Floor, 


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Federal Register / Vol. 83, No. 14 / Monday, January 22, 2018 / Rules and Regulations 2897 

Room W12–140, 1200 New Jersey 

Avenue SE, Washington, DC 20590. 

FOR FURTHER INFORMATION CONTACT: JoAnn Theriault, Aerospace Engineer, 

ECO Branch, FAA, 1200 District 

Avenue, Burlington, MA 01803; phone: 

781–238–7105; fax: 781–238–7199; 

email: jo-ann.theriault@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 PW PW4074, PW4074D, 

PW4077, PW4077D, PW4084D, 

PW4090, and PW4090–3 turbofan 

engines. The NPRM published in the 

Federal Register on August 25, 2017 (82 

FR 40514). The NPRM was prompted by 

the discovery of multiple cracked outer 

diffuser cases. The NPRM proposed to 

require initial and repetitive inspections 

to detect cracks in the outer diffuser 

case and removal from service of cases 

that fail inspection. We are issuing this 

AD to correct the unsafe condition on 

these products. 

Comments 

We gave the public the opportunity to 

participate in developing this final rule. 

The following presents the comments 

received on the NPRM and the FAA’s 

response to each comment. 

Request To Change Compliance 

PW requested that we change the 

effective date of the 1,000 cycle 

drawdown to ‘‘within 1,000 flight cycles 

from March 31, 2017’’, to coincide with 

PW Alert Service Bulletin (ASB) PW4G– 

112–A72–347, rather than ‘‘within 1,000 

flight cycles from the effective date of 

this AD’’. PW stated that making the 

1,000 cycle drawdown effective March 

31, 2017, rather than the effective date 

of this AD, maintains the same level of 

risk. 

We disagree with changing the 

effective date of the 1,000 cycle 

drawdown to ‘‘within 1,000 flight cycles 

from March 31, 2017’’, to coincide with 

PW ASB PW4G–112–A72–347 because 

we cannot force mandatory action based 

on dates in the past. Mandatory action 

must be based on the effective date of 

this AD. In addition, we determined that 

basing the initial inspection and the 

inspection interval on the effective date 

of this AD maintains an acceptable level 

of safety. We did not change this AD. 

Request To Add Credit for Previous 

Actions 

PW and United Airlines (UAL) 

requested that we add Credit for 

Previous Actions to allow operators to 

take credit for inspections performed 

per PW ASB PW4G–112–A72–347, 

dated March 31, 2017 prior to the 

effective date of this AD. 

We disagree. Since use of PW ASB 

PW4G–112–A72–347, dated March 31, 

2017, is required in the compliance 

section of this AD, we do not need to 

reference this SB in the Credit for 

Previous Actions paragraph. Inspections 

performed per PW ASB PW4G–112– 

A72–347 prior to the effective date of 

this AD meet the criteria of ‘‘unless 

already done’’ in the compliance section 

of this AD. 

Request To Change Definitions 

UAL requested that we define ‘‘engine 

disassembly’’ as ‘‘when the M flange is 

split’’. UAL reasoned that this would 

clarify the compliance requirements for 

operators and is consistent with PW 

ASB PW4G–112–A72–347, dated March 

31, 2017. 

We agree. Defining ‘‘engine 

disassembly’’ clarifies compliance 

requirements for operators. We added a 

Definition paragraph to this AD. 

Request To Change Compliance Time 

UAL requested that we add a third 

option for the initial inspection so that 

it could be performed prior to 

accumulating 13,000 cycles since new, 

or within 1,000 cycles from the effective 

date of this AD, or within 2,000 cycles 

since the last outer diffuser case piecepart fluorescent penetration inspection 

(FPI), whichever occurs later. 

We partially agree. We agree with 

giving operator’s credit for inspections 

done at piece-part exposure because if 

the outer diffuser case was inspected at 

piece-part exposure and passed 

inspection, it meets the initial 

inspection requirement mandated by 

this AD. We added a ‘‘Credit for 

Previous Actions’’ paragraph to this AD. 

Therefore, we disagree with adding the 

third option to the initial inspection 

compliance time specified in paragraph 

(g)(1) of this AD. 

Request To Change Compliance 

UAL requested that we identify the 

outer diffuser case piece-part level FPI 

done in accordance with PW Cleaning, 

Inspection and Repair (CIR) Manual 72– 

41–13, Inspection/Check-02, as an 

acceptable means of compliance for the 

repetitive inspections. UAL reasoned 

that when the outer diffuser case is at 

piece-part level, PW CIR Manual 72–41– 

13, Inspection/Check-02, is performed. 

The piece-part level FPI is equivalent to 

the high sensitivity module level 

inspection provided in PW ASB PW4G– 

112–A72–347, dated March 31, 2017. 

We agree. Inspections performed at 

piece-part exposure maintain an 

acceptable level of safety because the 

piece-part level FPI specified in PW CIR 

Manual Part Number 51A750, section 

72–41–13, Inspection/Check-02 is 

equivalent to the inspection mandated 

by this AD. Since we did not 

incorporate by reference a particular FPI 

process specification, a high sensitivity 

FPI using the methods, techniques, and 

practices equivalent to the current 

manufacturer’s maintenance manual or 

Instructions for Continued 

Airworthiness satisfy both the initial 

and repetitive requirements of this AD. 

We did not change this AD. 

Request To Change Service Information 

PW requested that we change the 

service information reference from PW 

ASB PW4G–112–A72–347, dated March 

31, 2017, to PW ASB PW4G–112–A72– 

347, Revision No. 1, dated October 26, 

2017. PW stated that the SB has been 

revised to provide inspection 

clarifications requested by operators. 

We disagree. We did not include PW 

ASB PW4G–112–A72–347, Revision No. 

1, dated October 26, 2017, since the risk 

analysis was based on the original ASB 

and we did not have the opportunity to 

give the public a chance to comment on 

this revision. We did not change this 

AD. 

Conclusion 

We reviewed the relevant data, 

considered the comments received, and 

determined that air safety and the 

public interest require adopting this 

final rule with the changes described 

previously. We have determined that 

these minor changes: 

• Are consistent with the intent that 

was proposed in the NPRM for 

correcting the unsafe condition; and 

• Do not add any additional burden 

upon the public than was already 

proposed in the NPRM. 

We also determined that these 

changes will not increase the economic 

burden on any operator or increase the 

scope of this final rule. 

Related Service Information Under 1 

CFR Part 51 

We reviewed PW ASB PW4G–112– 

A72–347, dated March 31, 2017. This 

PW ASB provides guidance on 

performing outer diffuser case FPIs. 

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. 

Other Related Service Information 

We reviewed PW4000 Series (112 

Inch) Engine CIR Manual, Part Number 

51A750, Revision Number 74, section 


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72–41–13, Inspection/Check-02, dated 

July 15, 2017. This manual section 

provides guidance on performing a high 

sensitivity FPI of the outer diffuser case 

at piece-part exposure. 

Costs of Compliance 

We estimate that this AD affects 121 

engines installed on airplanes of U.S. 

registry. 

We estimate the following costs to 

comply with this AD: 

ESTIMATED COSTS

Action Labor cost Parts cost Cost per 

product 

Cost on U.S. 

operators 

Tt3 boss inspection ......................................... 3.5 work-hours × $85 per hour = $297.50 ..... $0 $297.50 $35,997.50 

We estimate the following costs to do 

any necessary replacements that would 

be required based on the results of the 

proposed inspection. We estimate six 

cases will need to be replaced in the 

domestic fleet. 

ON-CONDITION COSTS

Action Labor cost Parts cost Cost per 

product 

FPI Inspection of outer diffuser case ........................... 10 work-hours × $85 per hour = $850 ......................... $0 $850 

Replacement of outer diffuser case ............................. $0 .................................................................................. 750,000 750,000 

Authority for This Rulemaking 

Title 49 of the United States Code 

specifies the FAA’s authority to issue 

rules on aviation safety. Subtitle I, 

section 106, describes the authority of 

the FAA Administrator. Subtitle VII: 

Aviation Programs, describes in more 

detail the scope of the Agency’s 

authority. 

We are issuing this rulemaking under 

the authority described in Subtitle VII, 

Part A, Subpart III, Section 44701: 

‘‘General requirements.’’ Under that 

section, Congress charges the FAA with 

promoting safe flight of civil aircraft in 

air commerce by prescribing regulations 

for practices, methods, and procedures 

the Administrator finds necessary for 

safety in air commerce. This regulation 

is within the scope of that authority 

because it addresses an unsafe condition 

that is likely to exist or develop on 

products identified in this rulemaking 

action. 

This AD is issued in accordance with 

authority delegated by the Executive 

Director, Aircraft Certification Service, 

as authorized by FAA Order 8000.51C. 

In accordance with that order, issuance 

of ADs is normally a function of the 

Compliance and Airworthiness 

Division, but during this transition 

period, the Executive Director has 

delegated the authority to issue ADs 

applicable to engines, propellers, and 

associated appliances to the Manager, 

Engine and Propeller Standards Branch, 

Policy and Innovation Division. 

Regulatory Findings 

This AD will not have federalism 

implications under Executive Order 

13132. This AD will not have a 

substantial direct effect on the States, on 

the relationship between the national 

government and the States, or on the 

distribution of power and 

responsibilities among the various 

levels of government. 

For the reasons discussed above, I 

certify that this AD: 

(1) Is not a ‘‘significant regulatory 

action’’ under Executive Order 12866, 

(2) Is not a ‘‘significant rule’’ under 

DOT Regulatory Policies and Procedures 

(44 FR 11034, February 26, 1979), 

(3) Will not affect intrastate aviation 

in Alaska, and 

(4) Will not have a significant 

economic impact, positive or negative, 

on a substantial number of small entities 

under the criteria of the Regulatory 

Flexibility Act. 

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): 

2018–02–10 Pratt & Whitney Division: 

Amendment 39–19163; Docket No. 

FAA–2017–0719; Product Identifier 

2017–NE–22–AD. 

(a) Effective Date 

This AD is effective February 26, 2018. 

(b) Affected ADs 

None. 

(c) Applicability 

This AD applies to all Pratt & Whitney 

Division (PW) PW4074, PW4074D, PW4077, 

PW4077D, PW4084D, PW4090, and PW4090– 

3 turbofan engines with outer diffuser case, 

part number (P/N) 50J775 or P/N 50J930, 

installed. 

(d) Subject 

Joint Aircraft System Component (JASC) 

Code 7240, Turbine Engine Combustion 

Section. 

(e) Unsafe Condition 

This AD was prompted by the discovery of 

multiple cracked outer diffuser cases. We are 

issuing this AD to prevent failure of the outer 

diffuser case. The unsafe condition, if not 

corrected, could result in failure of the outer 

diffuser case, uncontained case release, 

damage to the engine, and damage to the 

airplane. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Required Actions 

(1) Perform an initial high sensitivity 

fluorescent penetrant inspection (FPI) of the 

outer diffuser case T3 thermocouple probe 

boss (Tt3 boss) prior to accumulating 13,000 

cycles since new (CSN), or within 1,000 

flight cycles from the effective date of this 

AD, whichever occurs later. If the case CSN 

is unknown, inspect within 1,000 flight 

cycles from the effective date of this AD. 


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Federal Register / Vol. 83, No. 14 / Monday, January 22, 2018 / Rules and Regulations 2899 

(2) Thereafter, repeat the high sensitivity 

FPI of the outer diffuser case Tt3 boss within 

2,000 flight cycles since the last FPI. 

(3) If an indication is found during the 

inspections required by paragraphs (g)(1) or 

(2) of this AD, re-inspect or remove the outer 

diffuser case from service as follows: 

(i) For engines installed on-wing, reinspect or remove in accordance with the 

Accomplishment Instructions, Part A, 

paragraph 1.G., of PW ASB PW4G–112–A72– 

347, dated March 31, 2017. 

(ii) For assembled engines not installed onwing, re-inspect or remove in accordance 

with the Accomplishment Instructions, Part 

B, paragraph 1.C., of PW ASB PW4G–112– 

A72–347, dated March 31, 2017. 

(iii) For disassembled engines, if any 

cracks are found, remove the outer diffuser 

case from service before further flight. 

(4) Within 30 days of the effective date of 

this AD, update the mandatory inspections of 

the Airworthiness Limitations Section (ALS) 

of your Instructions for Continued 

Airworthiness to include the piece-part 

inspections of the diffuser case as defined in 

Figure 1 to paragraph (g) of this AD. 

(h) Credit for Previous Actions 

You may take credit for the high sensitivity 

FPI of the outer diffuser case Tt3 boss that 

is required by paragraph (g)(1) of this AD if 

you performed a high sensitivity FPI of the 

outer diffuser case at piece-part exposure 

before the effective date of this AD, using 

PW4000 Series (112 Inch) Engine CIR 

Manual, P/N 51A750, section 72–41–13, 

Inspection/Check-02, dated July 15, 2017. 

(i) Definition 

For the purpose of this AD, an engine is 

considered disassembled any time the ‘‘M’’ 

flange is separated. 

(j) Alternative Methods of Compliance 

(AMOCs) 

(1) The Manager, ECO 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 ECO Branch, send it to 

the attention of the person identified in 

paragraph (k)(1) of this AD. You may email 

your request to: ANE-AD-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. 

(k) Related Information 

(1) For more information about this AD, 

contact Jo-Ann Theriault, Aerospace 

Engineer, ECO Branch, FAA, 1200 District 

Avenue, Burlington, MA 01803; phone: 781– 

238–7105; fax: 781–238–7199; email: joann.theriault@faa.gov. 

(2) PW4000 Series (112 Inch) Engine CIR 

Manual, Part Number 51A750, Revision 

Number 74, section 72–41–13, Inspection/ 

Check-02, dated July 15, 2017, which is not 

incorporated by reference in this AD, can be 

obtained from PW, using the contact 

information in paragraph (l)(3) 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) Pratt & Whitney (PW) Alert Service 

Bulletin PW4G–112–A72–347, dated March 

31, 2017. 

(ii) Reserved. 

(3) For PW service information identified 

in this AD, contact Pratt & Whitney Division, 

400 Main St., East Hartford, CT 06118; 

phone: 800–565–0140; fax: 860–565–5442. 

(4) You may view this service information 

at FAA, Engine and Propeller Standards 

Branch, 1200 District Avenue, Burlington, 

MA. For information on the availability of 

this material at the FAA, call 781–238–7759. 

(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 Burlington, Massachusetts, on 

January 12, 2018. 

Robert J. Ganley, 

Manager, Engine and Propeller Standards 

Branch, Aircraft Certification Service. 

[FR Doc. 2018–00999 Filed 1–19–18; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2018–0022; Product 

Identifier 2015–NM–044–AD; Amendment 

39–19162; AD 2018–02–09] 

RIN 2120–AA64 

Airworthiness Directives; Fokker 

Services B.V. Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule; request for 

comments. 

SUMMARY: We are superseding 

Airworthiness Directive (AD) 2008–06– 

20 R1, which applied to all Fokker 

Services B.V. Model F28 Mark 0070 and 

0100 airplanes, and certain Model F28 

Mark 1000, 2000, 3000, and 4000 

airplanes. AD 2008–06–20 R1 required 

revising the Airworthiness Limitations 

Section (ALS) of the Instructions for 

Continued Airworthiness for certain 

airplanes, and the maintenance or 

inspection program, as applicable, for 

certain other airplanes, to incorporate 

new limitations for fuel tank systems. 

AD 2008–06–20 R1 also clarified the 

intended effect on spare and on-airplane 

fuel tank system components, regarding 

the use of maintenance manuals and 

instructions for continued 

airworthiness. This new AD was 

prompted by revised fuel airworthiness 

limitation items (ALI) tasks, and critical 

design configuration control limitations 

(CDCCL) items, and associated 


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