Federal Register / Vol. 83, No. 153 / Wednesday, August 8, 2018 / Rules and Regulations 38953 

147 to reduce the risk of uncoupling between 

the low-pressure (LP) fuel pump impeller 

and the high-pressure (HP) fuel pump shaft 

of the HP/LP pump and hydro-mechanical 

metering unit (HMU). We are issuing this AD 

to prevent failure of the HMU. The unsafe 

condition, if not corrected, could result in 

failure of the engine, in-flight shutdown, and 

loss of the helicopter. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Required Actions 

(1) Check the transmissible torque between 

the LP fuel pump impeller and the HP fuel 

pump shaft as follows: 

(i) For pre-Modification TU 147 HMUs, 

check the torque before accumulating 500 

engine flight hours (FHs) since March 11, 

2010 or before the next flight after the 

effective date of this AD, whichever occurs 

later. Use Paragraph 2.A. of Turbomeca Alert 

Mandatory Service Bulletin (MSB) A292 73 

2830, Version B, dated July 10, 2009 to do 

the check. 

(ii) For HMUs that incorporated 

Modification TU 147 on or before March 31, 

2010, and those HMUs not listed in Figure 

2 or 3 of Turbomeca Alert MSB A292 73 

2836, Version A, dated August 17, 2010, 

check the torque before the next flight after 

the effective date of this AD. Use Paragraph 

2.A. of Turbomeca Alert MSB A292 73 2836, 

Version A, dated August 17, 2010, to do the 

check. 

(2) If the HMU does not pass the torque 

check, replace the HMU with a postModification TU 178 HMU before the next 

flight after the effective date of this AD. 

(h) Mandatory Terminating Action 

Within 2,200 engine FHs or 72 months 

after the effective date of this AD, whichever 

occurs first, replace any pre-Modification TU 

178 HMU with a post-Modification TU 178 

configuration HMU. 

(i) Installation Prohibition 

After the effective date of this AD, do not 

install a pre-Modification TU 178 HMU on 

engines incorporating a post-Modification TU 

178 HMU. 

(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 certification office, 

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 John Frost, Aerospace Engineer, ECO 

Branch, FAA, 1200 District Avenue, 

Burlington, MA 01803; phone: 781–238– 

7756; fax: 781–238–7199; email: john.frost@

faa.gov. 

(2) Refer to European Aviation Safety 

Agency (EASA) AD 2017–0102, dated June 

13, 2017, for more information. You may 

examine the EASA AD on the internet at 

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

and locating Docket No. FAA–2009–0889. 

(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. 

(3) The following service information was 

approved for IBR on March 11, 2010 (75 FR 

5689, February 4, 2010). 

(i) Turbomeca Alert Mandatory Service 

Bulletin (MSB) No. A292 73 2830, Version B, 

dated July 10, 2009. 

(ii) Reserved. 

(4) The following service information was 

approved for IBR on March 20, 2012 (77 FR 

8092, February 14, 2012). 

(i) Turbomeca Alert MSB No. A292 73 

2836, Version A, dated August 17, 2010. 

(ii) Reserved. 

(5) For Safran Helicopter Engines, S.A, 

service information identified in this AD, 

contact Safran Helicopter Engines, S.A., 

40220 Tarnos, France; phone: (33) 05 59 74 

40 00; fax: (33) 05 59 74 45 15. 

(6) You may view this service information 

at FAA, Engine and Propeller Standards 

Branch, 1200 District Avenue, Burlington, 

MA 01803. For information on the 

availability of this material at the FAA, call 

781–238–7759. 

(7) 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 

July 31, 2018. 

Robert J. Ganley, 

Manager, Engine and Propeller Standards 

Branch, Aircraft Certification Service. 

[FR Doc. 2018–16652 Filed 8–7–18; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2018–0640; Product 

Identifier 2018–NM–075–AD; Amendment 

39–19343; AD 2018–16–03] 

RIN 2120–AA64 

Airworthiness Directives; Airbus SAS 

Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule; request for 

comments. 

SUMMARY: We are adopting a new 

airworthiness directive (AD) for all 

Airbus SAS Model A319–133 airplanes 

and Model A321–232 airplanes. This 

AD requires modification and reidentification, or replacement, of certain 

engine fan cowl doors (FCDs) and 

installation of a placard in the flight 

deck. This AD was prompted by reports 

of in-service engine FCD losses, and the 

development of a new FCD front latch 

and keeper assembly that addresses this 

unsafe condition. We are issuing this 

AD to address the unsafe condition on 

these products. 

DATES: This AD becomes effective 

August 23, 2018. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication listed in this AD 

as of August 3, 2017 (82 FR 29371, June 

29, 2017). 

We must receive comments on this 

AD by September 24, 2018. 

ADDRESSES: You may send comments, 

using the procedures found in 14 CFR 

11.43 and 11.45, by any of the following 

methods: 

• Federal eRulemaking Portal: Go to 

http://www.regulations.gov. Follow the 

instructions for submitting comments. 

• Fax: 202–493–2251. 

• Mail: U.S. Department of 

Transportation, Docket Operations, M– 

30, West Building Ground Floor, Room 

W12–140, 1200 New Jersey Avenue SE, 

Washington, DC 20590. 

• Hand Delivery: U.S. Department of 

Transportation, Docket Operations, M– 

30, West Building Ground Floor, Room 

W12–140, 1200 New Jersey Avenue SE, 

Washington, DC, between 9 a.m. and 5 

p.m., Monday through Friday, except 

Federal holidays. 

For service information identified in 

this final rule, contact Airbus SAS, 

Airworthiness Office—EIAS, RondPoint Emile Dewoitine No: 2, 31700 

Blagnac Cedex, France; telephone +33 5 

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


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account.airworth-eas@airbus.com; 

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

may view this referenced service 

information at the FAA, Transport 

Standards Branch, 2200 South 216th St., 

Des Moines, WA. For information on the 

availability of this material at the FAA, 

call 206–231–3195. It is also available 

on the internet at http://

www.regulations.gov by searching for 

and locating Docket No. FAA–2018– 

0640. 

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–2018– 

0640; or in person at the Docket 

Operations office 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 Operations office (telephone 

800–647–5527) is in the ADDRESSES

section. Comments will be available in 

the AD docket shortly after receipt. 

FOR FURTHER INFORMATION CONTACT: 

Sanjay Ralhan, Aerospace Engineer, 

International Section, Transport 

Standards Branch, FAA, 2200 South 

216th St., Des Moines, WA 98198; 

telephone and fax 206–231–3223. 

SUPPLEMENTARY INFORMATION: 

Discussion 

The European Aviation Safety Agency 

(EASA), which is the Technical Agent 

for the Member States of the European 

Union, has issued EASA AD 2016–0053, 

dated March 14, 2016 (referred to after 

this as the Mandatory Continuing 

Airworthiness Information, or ‘‘the 

MCAI’’), to correct an unsafe condition 

for all Airbus Model A319–131, –132, 

and –133 airplanes, Model A320–231, 

–232, and –233 airplanes, and Model 

A321–131, –231, and –232 airplanes. 

The MCAI states: 

Fan Cowl Door (FCD) losses during take-off 

were reported on aeroplanes equipped with 

IAE V2500 engines. Prompted by these 

occurrences, DGAC [Direction Ge ́ne ́rale de 

l’Aviation Civile] France issued AD 2000– 

444–156(B), mandating FCD latch 

improvements. This [DGAC] AD was later 

superseded by [DGAC] AD 2001–381(B) 

[which corresponds to FAA AD 2003–18–06, 

Amendment 39–13297 (68 FR 53501, 

September 11, 2003)], requiring installation 

of additional fan cowl latch improvement by 

installing a hold open device. 

Since that [DGAC] AD was issued, further 

FCD in flight losses were experienced in 

service. Investigations confirmed that in all 

cases, the fan cowls were opened prior to the 

flight and were not correctly re-secured. 

During the pre-flight inspection, it was then 

not detected that the FCD were not properly 

latched. 

This condition, if not corrected, could lead 

to in-flight loss of a FCD, possibly resulting 

in damage to the aeroplane and/or injury to 

persons on the ground. 

Prompted by these recent events, new FCD 

front latch and keeper assembly were 

developed, having a specific key necessary to 

un-latch the FCD. This key cannot be 

removed unless the FCD front latch is safely 

closed. The key, after removal, must be 

stowed in the flight deck at a specific 

location, as instructed in the applicable 

Aircraft Maintenance Manual. Applicable 

Flight Crew Operating Manual has been 

amended accordingly. After modification, the 

FCD is identified with a different Part 

Number (P/N). 

For the reasons described above, this 

[EASA] AD retains the requirements of DGAC 

AD 2001–381(B), which is superseded, and 

requires modification and re-identification of 

FCD. 

You may examine the MCAI on the 

internet at http://www.regulations.gov 

by searching for and locating Docket No. 

FAA–2018–0640. 

Related Service Information Under 1 

CFR Part 51 

Airbus has issued Service Bulletin 

A320–71–1069, Revision 01, including 

Appendix 01, dated April 28, 2016. This 

service information describes 

procedures for modifying the engine 

FCDs, installing placards, and reidentifying the FCDs with new part 

numbers. 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. 

FAA’s Determination and Requirements 

of This AD 

This product has been approved by 

the aviation authority of another 

country, and is approved for operation 

in the United States. Pursuant to our 

bilateral agreement with the State of 

Design Authority, we have been notified 

of the unsafe condition described in the 

MCAI and service information 

referenced above. We are issuing this 

AD because we evaluated all pertinent 

information and determined the unsafe 

condition exists and is likely to exist or 

develop on other products of these same 

type designs. 

Differences Between This AD and the 

MCAI or Service Information 

The MCAI applies to Airbus SAS 

Model A319–131 and –132 airplanes; 

Model A320–231, –232, and –233 

airplanes; and Model A321–131 and 

–231 airplanes, in addition to Model 

A319–133 airplanes and Model A321– 

232 airplanes. The unsafe condition on 

Model A319–131 and –132 airplanes; 

Model A320–231, –232, and –233 

airplanes; and Model A321–131 and 

–231 airplanes is already addressed in 

AD 2017–13–10, Amendment 39–18940 

(82 FR 29371, June 29, 2017); therefore 

this AD only applies to Model A319– 

133 airplanes and Model A321–232 

airplanes. 

FAA’s Determination of the Effective 

Date 

There are currently no domestic 

operators of this product. Therefore, we 

find that notice and opportunity for 

prior public comment are unnecessary 

and that good cause exists for making 

this amendment effective in less than 30 

days. 

Comments Invited 

This AD is a final rule that involves 

requirements affecting flight safety, and 

we did not precede it by notice and 

opportunity for public comment. We 

invite you to send any written relevant 

data, views, or arguments about this AD. 

Send your comments to an address 

listed under the ADDRESSES section. 

Include ‘‘Docket No. FAA–2018–0640; 

Product Identifier 2018–NM–075–AD’’ 

at the beginning of your comments. We 

specifically invite comments on the 

overall regulatory, economic, 

environmental, and energy aspects of 

this AD. We will consider all comments 

received by the closing date and may 

amend this AD based on those 

comments. 

We will post all comments we 

receive, without change, to http://

www.regulations.gov, including any 

personal information you provide. We 

will also post a report summarizing each 

substantive verbal contact we receive 

about this AD. 

Costs of Compliance 

Currently, there are no affected U.S.- 

registered airplanes. If an affected 

airplane is imported and placed on the 

U.S. Register in the future, we provide 

the following cost estimates to comply 

with this AD: 


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ESTIMATED COSTS FOR REQUIRED ACTIONS

Labor cost Parts cost Cost per 

product 

6 work-hours × $85 per hour = $510 ...................................................................................................................... $4,813 $5,323 

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 transport category 

airplanes to the Director of the System 

Oversight Division. 

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): 

2018–16–03 Airbus SAS: Amendment 39– 

19343; Docket No. FAA–2018–0640; 

Product Identifier 2018–NM–075–AD. 

(a) Effective Date 

This AD becomes effective August 23, 

2018. 

(b) Affected ADs 

None. 

(c) Applicability 

This AD applies to Airbus SAS Model 

A319–133 airplanes and Model A321–232 

airplanes, certificated in any category, all 

manufacturer serial numbers. 

(d) Subject 

Air Transport Association (ATA) of 

America Code 71, Powerplant. 

(e) Reason 

This AD was prompted by reports of inservice engine fan cowl door (FCD) losses, 

and the development of a new FCD front 

latch and keeper assembly that addresses this 

unsafe condition. We are issuing this AD to 

address in-flight loss of an engine FCD and 

possible consequent damage to the airplane. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Modification 

Within 36 months after the effective date 

of this AD, do the actions specified in 

paragraphs (g)(1), (g)(2), and (g)(3) of this AD, 

in accordance with the Accomplishment 

Instructions of Airbus Service Bulletin A320– 

71–1069, Revision 01, including Appendix 

01, dated April 28, 2016. 

(1) Modify the left-hand and right-hand 

engine FCDs on engines 1 and 2. 

(2) Install a placard that specifies the FCD 

keys stowage location in the flight deck on 

the box located at the bottom of panel 120VU 

or at the bottom of the coat stowage, as 

applicable to airplane configuration. 

(3) Re-identify both engine FCDs with the 

new part numbers, as specified in figure 1 to 

paragraphs (g), (j), and (k) of this AD. 


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(h) Missing FCD Keys or Placard 

Flights with one or both FCD keys missing 

from the stowage location in the fight deck, 

or with the placard (that specifies the FCD 

keys stowage location) missing or damaged, 

are permitted for a period not to exceed 10 

calendar days from the date of discovery. 

(i) Alternative Location of FCD Keys and 

Placard 

As an option to paragraph (g)(2) of this AD, 

an alternative location for the key stowage in 

the flight deck and installation of a placard 

for identification of that stowage location are 

permitted as specified in the operator’s FAAaccepted maintenance or inspection program, 

provided the keys can be retrieved from that 

flight deck location when needed and the 

placard installation is done within 36 months 

after the effective date of this AD. 

(j) Optional Compliance by Replacement or 

Installation 

(1) Replacing an engine FCD having a part 

number listed as ‘‘Old Part Number’’ in figure 

1 to paragraphs (g), (j), and (k) of this AD 

with an FCD having the corresponding part 

number listed as ‘‘New Part Number’’ in 

figure 1 to paragraphs (g), (j), and (k) of this 

AD is an acceptable method of compliance 

with the requirements of paragraphs (g)(1) 

and (g)(3) of this AD for that engine FCD 

only. 

(2) An airplane on which Airbus 

Modification 157516 has been embodied in 

production is compliant with the 

requirements of paragraphs (g)(1) and (g)(3) 

of this AD, provided no engine FCD having 

a part number identified as ‘‘Old Part 

Number’’ in figure 1 to paragraphs (g), (j), and 

(k) of this AD is installed on that airplane. 

(3) An airplane on which Airbus 

Modification 157718 has been embodied in 

production is compliant with the 

requirements of paragraph (g)(2) of this AD. 

(4) Installation on an engine of a right-hand 

and left-hand engine FCD having a part 

number approved after the effective date of 

this AD is a method of compliance with the 

requirements of paragraphs (g)(1) and (g)(3) 

of this AD for that engine only, provided the 

part number is approved, and the installation 

is accomplished using a method approved by 

the Manager, International Section, Transport 

Standards Branch, 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. 

(k) Parts Installation Limitations 

(1) For an airplane with an engine FCD 

installed having a part number identified as 

‘‘Old Part Number’’ in figure 1 to paragraphs 

(g), (j), and (k) of this AD: After modification 

of that airplane as required by paragraph (g) 

of this AD, do not install an engine FCD, 

having a part number identified as ‘‘Old Part 

Number’’ in figure 1 to paragraphs (g), (j), and 

(k) of this AD. 

(2) For an airplane that does not have an 

engine FCD installed having a part number 

identified as ‘‘Old Part Number’’ in figure 1 

to paragraphs (g), (j), and (k) of this AD: On 

or after the effective date of this AD, do not 

install an engine FCD having a part number 

identified as ‘‘Old Part Number’’ in figure 1 

to paragraphs (g), (j), and (k) of this AD. 

(l) Credit for Previous Actions 

This paragraph provides credit for actions 

required by paragraph (g) of this AD, if those 

actions were performed before the effective 

date of this AD using Airbus Service Bulletin 

A320–71–1069, dated December 18, 2015. 

(m) Other FAA AD Provisions 

The following provisions also apply to this 

AD: 

(1) 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 (n)(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. 

(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 Section, 

Transport Standards Branch, FAA; or EASA; 

or Airbus’s EASA DOA. If approved by the 

DOA, the approval must include the DOAauthorized signature. 

(n) Related Information 

(1) Refer to Mandatory Continuing 

Airworthiness Information (MCAI) EASA AD 

2016–0053, dated March 14, 2016, for related 

information. You may examine the MCAI on 

the internet at http://www.regulations.gov by 

searching for and locating Docket No. FAA– 

2018–0640. 

(2) For more information about this AD, 

contact Sanjay Ralhan, Aerospace Engineer, 

International Section, Transport Standards 


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Branch, FAA, 2200 South 216th St., Des 

Moines, WA 98198; telephone and fax 206– 

231–3223. 

(3) Service information identified in this 

AD that is not incorporated by reference is 

available at the addresses specified in 

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

(o) 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. 

(3) The following service information was 

approved for IBR on August 3, 2017 (82 FR 

29371, June 29, 2017). 

(i) Airbus Service Bulletin A320–71–1069, 

Revision 01, including Appendix 01, dated 

April 28, 2016. 

(ii) Reserved. 

(4) For service information identified in 

this AD, contact Airbus SAS, Airworthiness 

Office—EIAS, Rond-Point Emile Dewoitine 

No: 2, 31700 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. 

(5) You may view this service information 

at the FAA, Transport Standards Branch, 

2200 South 216th St., Des Moines, WA. For 

information on the availability of this 

material at the FAA, call 206–231–3195. 

(6) 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 Des Moines, Washington, on July 

23, 2018. 

James Cashdollar, 

Acting Director, System Oversight Division, 

Aircraft Certification Service. 

[FR Doc. 2018–16576 Filed 8–7–18; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2018–0276; Product 

Identifier 2017–NM–079–AD; Amendment 

39–19346; AD 2018–16–06] 

RIN 2120–AA64 

Airworthiness Directives; The Boeing 

Company Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule. 

SUMMARY: We are adopting a new 

airworthiness directive (AD) for certain 

The Boeing Company Model 747–100, 

–100B, –100B SUD, –200B, –200C, 

–200F, –300, –400, –400D, 747SP, and 

747SR, and 747–8 series airplanes. This 

AD was prompted by reports indicating 

that additional areas of Boeing Material 

Specification (BMS) 8–39 flexible 

urethane foam were found during an 

inspection required by a related AD. 

This AD requires inspecting for BMS 8– 

39 flexible urethane foam insulation in 

the floor panel assemblies and the 

power drive unit (PDU) cover 

assemblies, doing applicable oncondition actions, modifying certain 

dripshields, and replacing BMS 8–39 

foam strips on certain dripshields with 

BMS 8–371 foam strips. We are issuing 

this AD to address the unsafe condition 

on these products. 

DATES: This AD is effective September 

12, 2018. 

The Director of the Federal Register 

approved the incorporation by reference 

of certain publications listed in this AD 

as of September 12, 2018. 

ADDRESSES: For service information 

identified in this final rule, contact 

Boeing Commercial Airplanes, 

Attention: Contractual & Data Services 

(C&DS), 2600 Westminster Blvd., MC 

110–SK57, Seal Beach, CA 90740–5600; 

telephone 562–797–1717; internet 

https://www.myboeingfleet.com. You 

may view this service information at the 

FAA, Transport Standards Branch, 2200 

South 216th St., Des Moines, WA. For 

information on the availability of this 

material at the FAA, call 206–231–3195. 

It is also available on the internet at 

http://www.regulations.gov by searching 

for and locating Docket No. FAA–2018– 

0276. 

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–2018– 

0276; 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 

Docket Operations, 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: 

Scott Craig, Aerospace Engineer, Cabin 

Safety and Environmental Systems 

Section, FAA, Seattle ACO Branch, 2200 

South 216th St., Des Moines, WA 98198; 

phone and fax: 206–231–3566; email: 

Michael.S.Craig@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 The Boeing Company 

Model 747–100, –100B, –100B SUD, 

–200B, –200C, –200F, –300, –400, 

–400D, 747SP, and 747SR, and 747–8 

series airplanes. The NPRM published 

in the Federal Register on April 17, 

2018 (83 FR 16796). The NPRM was 

prompted by reports indicating that 

additional areas of BMS 8–39 flexible 

urethane foam were found during an 

inspection required by a related AD. 

The NPRM proposed to require 

inspecting for BMS 8–39 flexible 

urethane foam insulation in the floor 

panel assemblies and the PDU cover 

assemblies, doing applicable oncondition actions, modifying certain 

dripshields, and replacing BMS 8–39 

foam strips on certain dripshields with 

BMS 8–371 foam strips. 

We are issuing this AD to address 

BMS 8–39 flexible urethane foam in 

certain areas, which, if exposed to an 

ignition source, could cause an 

uncontrolled fire leading to loss of 

control of the airplane. 

Comments 

We gave the public the opportunity to 

participate in developing this final rule. 

We have considered the comment 

received. Boeing stated that it had no 

objection to the NPRM. 

Conclusion 

We reviewed the relevant data, 

considered the comments received, and 

determined that air safety and the 

public interest require adopting this 

final rule as proposed, except for minor 

editorial changes. We have 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 

We reviewed the following Boeing 

service information. 

• Boeing Special Attention Service 

Bulletin 747–53–2877, dated August 5, 

2014, which describes procedures for 

performing a general visual inspection 

for BMS 8–39 flexible urethane foam 

insulation in the floor panel assemblies 

and the PDU cover assemblies, and 

applicable on-condition actions. 

• Boeing Special Attention Service 

Bulletin 747–25–3646, Revision 1, dated 


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