81788 Federal Register / Vol. 80, No. 251 / Thursday, December 31, 2015 / Proposed Rules 

(h) Repetitive Rototest Inspections 

Within 36 months after the effective date 

of this AD: Remove the fasteners and 

measure the diameter of the fastener holes; 

and, before further flight, do the applicable 

actions required by paragraph (h)(1) or (h)(2) 

of this AD, in accordance with the 

Accomplishment Instructions of Airbus 

Service Bulletin A300–57–0257 (for Model 

A300 B2–1A, B2–1C, B2K–3C, B2–203, B4– 

2C, B4–103, and B4–203 airplanes) or A300– 

57–6115 (for Model A300 B4–601, B4–603, 

B4–620, B4–622, B4–605R, B4–622R, F4– 

605R, F4–622R, and C4–605R Variant F 

airplanes), as applicable. 

(1) If one or more of the hole diameters is 

outside the tolerance of the nominal 

diameter, and outside the tolerance of the 

first and second oversize: Do the applicable 

corrective actions required by paragraph (i) of 

this AD. 

(2) If all of the hole diameters are within 

the tolerance of the nominal diameter or the 

first or second oversize: Do detailed and 

rototest inspections for cracking of the 

fastener holes at the left-hand and right-hand 

sides of the FR40 lower junction, in 

accordance with the Accomplishment 

Instructions of Airbus Service Bulletins 

A300–57–0257 (for Model A300 B2–1A, B2– 

1C, B2K–3C, B2–203, B4–2C, B4–103, and 

B4–203 airplanes) or A300–57–6115 (for 

Model A300 B4–601, B4–603, B4–620, B4– 

622, B4–605R, B4–622R, F4–605R, F4–622R, 

and C4–605R Variant F airplanes), both dated 

April 4, 2014, as applicable. If no cracking is 

found, before further flight, install new 

fasteners of the same diameter in special 

clearance fit for fasteners 1 through 3 of the 

FR40 lower junction, in accordance with the 

Accomplishment Instructions of Airbus 

Service Bulletins A300–57–0257 or A300– 

57–6115, both dated April 4, 2014, as 

applicable. Repeat the rototest inspection 

thereafter at intervals not to exceed 7,000 

flight cycles. Accomplishment of a rototest 

inspection required by this paragraph 

terminates the repetitive HFEC inspections 

required by paragraph (g) of this AD. 

(i) Corrective Actions 

If, during any inspection required by this 

AD, any crack is found, or one or more of the 

hole diameters are outside the tolerance of 

the nominal diameter: Repair before further 

flight 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). 

(j) 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: 

Dan Rodina, Aerospace Engineer, 

International Branch, ANM–116, Transport 

Airplane Directorate, FAA, 1601 Lind 

Avenue SW., Renton, WA 98057–3356; 

telephone 425–227–2125; 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. The AMOC approval letter 

must specifically reference this AD. 

(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): Except 

as required by paragraph (i) of this AD: 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. 

(k) Related Information 

(1) Refer to Mandatory Continuing 

Airworthiness Information (MCAI) European 

Aviation Safety Agency (EASA) 

Airworthiness Directive 2014–0272, dated 

December 12, 2014, 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 it in Docket No. 

FAA–2015–8134. 

(2) For service information identified in 

this AD, contact Airbus SAS, Airworthiness 

Office—EAW, 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 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. 

Issued in Renton, Washington, on 

December 21, 2015. 

Michael Kaszycki, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2015–32848 Filed 12–30–15; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2015–8130; Directorate 

Identifier 2014–NM–175–AD] 

RIN 2120–AA64 

Airworthiness Directives; The Boeing 

Company Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Notice of proposed rulemaking 

(NPRM). 

SUMMARY: We propose to adopt a new 

airworthiness directive (AD) for certain 

The Boeing Company Model 777–200 

and –300 series airplanes equipped with 

Pratt and Whitney engines. This 

proposed AD was prompted by reports 

of blocked drain lines at the engine 

forward strut that caused flammable 

fluid to accumulate in a flammable 

leakage zone. This proposed AD would 

require doing the following actions on 

the left strut and right strut: A one-time 

cleaning of certain forward strut drain 

lines; installing new forward strut drain 

lines and insulation blankets; a leak 

check of the forward strut drain lines; 

and repair if any leak is found. This 

proposed AD would also require 

revising the maintenance or inspection 

program, as applicable, to incorporate a 

certain airworthiness limitation. We are 

proposing this AD to prevent blockage 

of forward strut drain lines, which 

could cause flammable fluids to collect 

in the forward strut area and potentially 

cause an uncontrolled fire or cause 

failure of engine attachment structure 

and consequent airplane loss. 

DATES: We must receive comments on 

this proposed AD by February 16, 2016. 

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: Deliver to Mail 

address above between 9 a.m. and 5 

p.m., Monday through Friday, except 

Federal holidays. 

For service information identified in 

this proposed AD, contact Boeing 

Commercial Airplanes, Attention: Data 

& Services Management, P.O. Box 3707, 


tkelley on DSK3SPTVN1PROD with PROPOSALS
Federal Register / Vol. 80, No. 251 / Thursday, December 31, 2015 / Proposed Rules 81789 

MC 2H–65, Seattle, WA 98124–2207; 

telephone 206–544–5000, extension 1; 

fax 206–766–5680; Internet https://

www.myboeingfleet.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– 

8130. 

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– 

8130; 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 proposed AD, the 

regulatory evaluation, any comments 

received, and other information. The 

street address for the Docket Office 

(phone: 800–647–5527) is in the 

ADDRESSES section. Comments will be 

available in the AD docket shortly after 

receipt. 

FOR FURTHER INFORMATION CONTACT: 

Kevin Nguyen, Aerospace Engineer, 

Propulsion Branch, ANM–140S, FAA, 

Seattle Aircraft Certification Office 

(ACO), 1601 Lind Avenue SW., Renton, 

WA 98057–3356; phone: 425–917–6501; 

fax: 425–917–6590; email: 

kevin.nguyen@faa.gov. 

SUPPLEMENTARY INFORMATION: 

Comments Invited 

We invite you to send any written 

relevant data, views, or arguments about 

this proposal. Send your comments to 

an address listed under the ADDRESSES

section. Include ‘‘Docket No. FAA– 

2015–8130; Directorate Identifier 2014– 

NM–175–AD’’ at the beginning of your 

comments. We specifically invite 

comments on the overall regulatory, 

economic, environmental, and energy 

aspects of this proposed AD. We will 

consider all comments received by the 

closing date and may amend this 

proposed AD because of 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 proposed AD. 

Discussion 

We received multiple reports of the 

forward drain lines of the engine struts 

being blocked with coked particles. 

Coked particles form when hydraulic 

fluid is exposed to, and degraded by, the 

high temperatures of the hot core zone 

of the engine and the hot pneumatic 

bleed ducts. In two events, fluids 

backed up into the electrical (left) side 

of the disconnect box assembly of the 

strut system, causing an electrical fault 

that resulted in a false engine indicating 

and crew-alerting system (EICAS) 

message for overheat detection. 

Flammable fluids collecting in the 

electrical side of the disconnect box 

assembly of the strut system can cause 

an electrical fault for electrical 

components, and create a potential 

ignition source for trapped flammable 

fluids that can lead to a fire. 

In three other events, flammable 

fluids backed up and pooled in the fluid 

(right) side of the disconnect box 

assembly of the strut system. Flammable 

fluids collecting in the disconnect box 

assembly of the strut system are a fire 

hazard because that area has no fire 

detection, containment, or extinguishing 

capability, and with an ignition source 

can result in an uncontrolled fire in the 

strut. Also, flammable fluids pooling in 

the disconnect box assembly of the strut 

system can spill over onto the engine 

and initiate an engine fire in the engine 

core cavity compartment. 

Hydraulic fluid collecting in the 

disconnect box assembly of the strut 

system can cause contamination and 

hydrogen embrittlement of the titanium 

structure resulting in cracks that can 

compromise the engine firewall by 

allowing a fire in the engine area to 

enter the strut; or by allowing 

flammable fluids to leak down and 

initiate an engine fire in the engine core 

cavity compartment, and also 

compromise the engine fire 

extinguishing system. Hydraulic fluid 

contamination, including contamination 

caused by hydraulic fluid in its liquid, 

vapor, and/or solid (i.e., coked) form, in 

the strut forward dry bay can lead to 

hydrogen embrittlement of the titanium 

fittings of the forward engine mount 

bulkhead and also the consequent 

inability of the fittings to carry engine 

loads, resulting in the loss or separation 

of an engine. Hydrogen embrittlement 

could also cause a through-crack 

formation across the fittings through 

which an engine fire could breach into 

the strut, resulting in an uncontained 

strut fire. We are proposing this AD to 

prevent blockage of forward strut drain 

lines, which could cause flammable 

fluids to collect in the forward strut area 

and potentially cause an uncontrolled 

fire or cause failure of engine 

attachment structure and consequent 

airplane loss. 

Related Service Information Under 1 

CFR Part 51 

We reviewed the following service 

information: 

• Boeing Special Attention Service 

Bulletin 777–71–0055, Revision 1, dated 

April 15, 2015. The service information 

describes procedures for installing new 

forward strut drain lines and insulation 

blankets on the left and right engines. 

• Boeing Special Attention Service 

Bulletin 777–54–0028, Revision 1, dated 

December 10, 2013. This service 

information describes procedures for a 

general visual inspection for hydraulic 

fluid contamination of the interior of the 

strut forward dry bay and corrective 

actions. 

• Airworthiness Limitation 54–AWL– 

01, ‘‘Forward Strut Drain Line’’ as 

specified in Section D.4, Pratt and 

Whitney Forward Strut Drain Line, 

dated March 2014, of the Boeing 777 

Maintenance Planning Data (MPD) 

Document Section 9, Airworthiness 

Limitations (AWLs) and Certification 

Maintenance Requirements (CMRs), 

D622W001–9, dated October 2014. This 

service information describes an 

airworthiness limitation task for the 

functional check of the forward strut 

drain line. 

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 of 

this NPRM. 

FAA’s Determination 

We are proposing this AD because we 

evaluated all the relevant information 

and determined the unsafe condition 

described previously is likely to exist or 

develop in other products of the same 

type design. 

Proposed AD Requirements 

This proposed AD would require 

accomplishing the actions specified in 

the service information described 

previously. For information on the 

procedures and compliance times 

specified in Boeing Special Attention 

Service Bulletin 777–71–0055, Revision 

1, dated April 15, 2015; and Boeing 

Special Attention Service Bulletin 777– 

54–0028, Revision 1, dated December 

10, 2013: See this service information at 

http://www.regulations.gov by searching 

for and locating Docket No. FAA–2015– 

8130. 

The phrase ‘‘corrective actions’’ is 

used in this proposed AD. ‘‘Corrective 

actions’’ are actions that correct or 

address any condition found. Corrective 

actions in an AD could include, for 

example, repairs. 


tkelley on DSK3SPTVN1PROD with PROPOSALS
81790 Federal Register / Vol. 80, No. 251 / Thursday, December 31, 2015 / Proposed Rules 

This proposed AD would require 

revisions to certain operator 

maintenance documents to include a 

new airworthiness limitation containing 

repetitive functional checks of the 

forward engine strut drain line. 

Compliance with these actions is 

required by 14 CFR 91.403(c). For 

airplanes that have been previously 

modified, altered, or repaired in the 

areas addressed by this AD, the operator 

may not be able to accomplish the 

actions described in the revisions. In 

this situation, to comply with 14 CFR 

91.403(c), the operator must request 

approval for an alternative method of 

compliance in accordance with the 

procedures specified in paragraph (k) of 

this AD. The request should include a 

description of changes to the required 

inspections that will ensure the 

continued operational safety of the 

airplane. 

Other Relevant Rulemaking 

On September 23, 2014, we issued AD 

2014–20–10, Amendment 39–17983 (79 

FR 60331, October 7, 2014), for certain 

The Boeing Company Model 777–200 

and –300 series airplanes equipped with 

Pratt & Whitney engines. AD 2014–20– 

10 currently requires repetitive general 

visual inspections of the strut forward 

dry bay for the presence of hydraulic 

fluid, and related investigative and 

corrective actions (including checking 

drain lines for blockage due to hydraulic 

fluid coking; cleaning or replacing drain 

lines to allow drainage) if necessary; 

and adds airplanes to the applicability. 

AD 2014–20–10 was prompted by 

reports of hydraulic fluid contamination 

(including contamination caused by 

hydraulic fluid in its liquid, vapor, and/ 

or solid (coked) form) found in the strut 

forward dry bay. 

The actions required by AD 2014–20– 

10, Amendment 39–17983 (79 FR 

60331, October 7, 2014), are intended to 

detect and correct hydraulic fluid 

contamination of the strut forward dry 

bay, which could result in hydrogen 

embrittlement of the titanium forward 

engine mount bulkhead fittings, and 

consequent inability of the fittings to 

carry engine loads and resulting in 

engine separation. Hydrogen 

embrittlement could also cause a 

through-crack formation across the 

fittings through which an engine fire 

could breach into the strut, resulting in 

an uncontained strut fire. 

Accomplishment of the actions 

specified below terminates the 

inspections required by paragraph (g) of 

AD 2014–20–10, Amendment 39–17983 

(79 FR 60331, October 7, 2014), at the 

modified area only; provided the actions 

are accomplished concurrently, or the 

actions specified below for Boeing 

Special Attention Service Bulletin 777– 

54–0028, Revision 1, dated December 

10, 2013, are done after accomplishing 

the actions specified in paragraphs (g)(1) 

through (g)(5) of this proposed AD. 

• The actions specified in paragraphs 

(g)(1) through (g)(4) of this proposed AD 

on the left and right struts, done in 

accordance with the Accomplishment 

Instructions of Boeing Special Attention 

Service Bulletin 777–71–0055, Revision 

1, dated April 15, 2015; and the revision 

done as specified in paragraph (g)(5) of 

this proposed AD. 

• A one-time general visual 

inspection for hydraulic fluid 

contamination of the interior of the strut 

forward dry bay, and all applicable 

related investigative and corrective 

actions, done in accordance with the 

Accomplishment Instructions of Boeing 

Special Attention Service Bulletin 777– 

54–0028, Revision 1, dated December 

10, 2013. 

On August 14, 2015, we issued AD 

2015–17–13, Amendment 39–18246 (80 

FR 52948, September 2, 2015) for 

certain The Boeing Company Model 

777–200 and –300 series airplanes 

equipped with Pratt and Whitney 

engines. AD 2015–17–13 currently 

requires repetitive functional checks for 

blockage of the forward strut drain line, 

and doing corrective actions (including 

cleaning or replacing any blocked drain 

lines) if necessary; and a one-time 

cleaning of certain forward strut drain 

lines. AD 2015–17–13 also includes an 

optional terminating action, which 

specifies accomplishing the actions in 

Boeing Special Attention Service 

Bulletin 777–71–0055, Revision 1, dated 

April 15, 2015 and incorporating 

Airworthiness Limitation 54–AWL–01, 

‘‘Forward Strut Drain Line’’ into the 

maintenance or inspection program, as 

applicable. AD 2015–17–13 was 

prompted by reports of blocked drain 

lines at the engine forward strut that 

caused flammable fluid to accumulate 

in a flammable leakage zone. The 

actions required by AD 2015–17–13 are 

intended to detect and correct blockage 

of forward strut drain lines, which 

could cause flammable fluids to collect 

in the forward strut area and potentially 

cause an uncontrolled fire or cause 

failure of engine attachment structure 

and consequent airplane loss. 

Accomplishment of the actions 

required by paragraph (g) of this 

proposed AD (doing the actions 

specified Boeing Special Attention 

Service Bulletin 777–71–0055, Revision 

1, dated April 15, 2015; and 

incorporating Airworthiness Limitation 

54–AWL–01, ‘‘Forward Strut Drain 

Line’’ as specified in Section D.4, Pratt 

and Whitney Forward Strut Drain Line, 

dated March 2014, of the Boeing 777 

Maintenance Planning Data (MPD) 

Document Section 9, Airworthiness 

Limitations (AWLs) and Certification 

Maintenance Requirements (CMRs), 

D622W001–9, dated October 2014, into 

the maintenance or inspection program, 

as applicable) would terminate the 

actions required by paragraph (g) of AD 

2015–17–13, Amendment 39–18246 (80 

FR 52948, September 2, 2015), at the 

modified area only. 

Explanation of ‘‘RC’’ Steps in Service 

Information 

The FAA worked in conjunction with 

industry, under the Airworthiness 

Directive Implementation Aviation 

Rulemaking Committee (ARC), to 

enhance the AD system. One 

enhancement was a new process for 

annotating which steps in the service 

information are required for compliance 

with an AD. Differentiating these steps 

from other tasks in the service 

information is expected to improve an 

owner’s/operator’s understanding of 

crucial AD requirements and help 

provide consistent judgment in AD 

compliance. The steps identified as 

Required for Compliance (RC) in any 

service information identified 

previously have a direct effect on 

detecting, preventing, resolving, or 

eliminating an identified unsafe 

condition. 

For service information that contains 

steps that are labeled as RC, the 

following provisions apply: (1) The 

steps labeled as RC, including substeps 

under an RC step and any figures 

identified in an RC step, must be done 

to comply with the AD, and an AMOC 

is required for any deviations to RC 

steps, including substeps and identified 

figures; and (2) steps not labeled 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 RC steps, 

including substeps and identified 

figures, can still be done as specified, 

and the airplane can be put back in an 

airworthy condition. 

Costs of Compliance 

We estimate that this proposed AD 

affects 54 airplanes of U.S. registry. 

We estimate the following costs to 

comply with this proposed AD: 


tkelley on DSK3SPTVN1PROD with PROPOSALS
Federal Register / Vol. 80, No. 251 / Thursday, December 31, 2015 / Proposed Rules 81791 

ESTIMATED COSTS

Action Labor cost Parts cost Cost per 

product 

Cost on U.S. 

operators 

Installing new drain lines and insulation blankets, 

doing a leak check, and revising the maintenance or 

inspection program.

16 work-hours × $85 per hour = 

$1,360.

$17,080 $18,440 $995,760 

We have received no definitive data 

that would enable us to provide cost 

estimates for the on-condition actions 

specified in this proposed AD. 

According to the manufacturer, some 

of the costs of this proposed AD may be 

covered under warranty, thereby 

reducing the cost impact on affected 

individuals. We do not control warranty 

coverage for affected individuals. As a 

result, we have included all costs in our 

cost estimate. 

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 proposed AD 

would not have federalism implications 

under Executive Order 13132. This 

proposed AD would 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 this proposed regulation: 

(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. 

The Proposed Amendment 

Accordingly, under the authority 

delegated to me by the Administrator, 

the FAA proposes to amend 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): 

The Boeing Company: Docket No. FAA– 

2015–8130; Directorate Identifier 2014– 

NM–175–AD. 

(a) Comments Due Date 

We must receive comments by February 

16, 2016. 

(b) Affected ADs 

This AD affects the ADs specified in 

paragraphs (b)(1) and (b)(2) of this AD. 

(1) AD 2014–20–10, Amendment 39–17983 

(79 FR 60331, October 7, 2014). 

(2) AD 2015–17–13, Amendment 39–18246 

(80 FR 52948, September 2, 2015). 

(c) Applicability 

This AD applies to The Boeing Company 

Model 777–200 and –300 series airplanes, 

certificated in any category, equipped with 

Pratt & Whitney engines, as identified in 

Boeing Special Attention Service Bulletin 

777–71–0055, Revision 1, dated April 15, 

2015. 

(d) Subject 

Air Transport Association (ATA) of 

America Code 71, Powerplant. 

(e) Unsafe Condition 

This AD was prompted by reports of 

blocked drain lines at the engine forward 

strut that caused flammable fluid to 

accumulate in a flammable leakage zone. We 

are issuing this AD to prevent blockage of 

forward strut drain lines, which could cause 

flammable fluids to collect in the forward 

strut area and potentially cause an 

uncontrolled fire or cause failure of engine 

attachment structure and consequent 

airplane loss. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Actions 

Within 4,000 flight cycles or 750 days after 

the effective date of this AD, whichever 

occurs later: Accomplish the actions 

specified in paragraphs (g)(1) through (g)(4) 

of this AD on the left and right struts, in 

accordance with the Accomplishment 

Instructions of Boeing Special Attention 

Service Bulletin 777–71–0055, Revision 1, 

dated April 15, 2015; and accomplish the 

revision specified in paragraph (g)(5) of this 

AD. 

(1) Disconnect and remove the forward 

strut drain lines. 

(2) Clean the left system disconnect, the 

strut forward lower spar, and the forward 

fireseal pan drain lines. 

(3) Install new forward strut drain lines 

and insulation blankets. 

(4) Do a leak check of the forward strut 

drain lines, for any leak, and repair if any 

leak is found. 

(5) Revise the maintenance or inspection 

program, as applicable, to incorporate 

Airworthiness Limitation 54–AWL–01, 

‘‘Forward Strut Drain Line’’ as specified in 

Section D.4, Pratt and Whitney Forward Strut 

Drain Line, dated March 2014, of the Boeing 

777 Maintenance Planning Data (MPD) 

Document Section 9, Airworthiness 

Limitations (AWLs) and Certification 

Maintenance Requirements (CMRs), 

D622W001–9, dated October 2014. The 

initial compliance time for Airworthiness 

Limitation 54–AWL–01 is within 2,000 flight 

cycles or 1,500 days, whichever occurs first, 

after doing the actions specified in 

paragraphs (g)(1) through (g)(4) of this AD. 

(h) No Alternative Actions or Intervals 

After accomplishing the revision required 

by paragraph (g)(5) of this AD, no alternative 

actions (e.g., inspections) or intervals may be 

used unless the actions or intervals are 

approved as an alternative method of 

compliance (AMOC) in accordance with the 

procedures specified in paragraph (k) of this 

AD. 

(i) Terminating Action for Other ADs 

(1) Accomplishing the actions required by 

paragraph (g) of this AD terminates the 

actions required by paragraph (g) of AD 

2015–17–13, Amendment 39–18246 (80 FR 


tkelley on DSK3SPTVN1PROD with PROPOSALS
81792 Federal Register / Vol. 80, No. 251 / Thursday, December 31, 2015 / Proposed Rules 

52948, September 2, 2015, at the modified 

area only. 

(2) Accomplishing the actions specified in 

paragraphs (i)(2)(i) and (i)(2)(ii) of this AD 

terminates the inspections required by 

paragraph (g) of AD 2014–20–10, 

Amendment 39–17983 (79 FR 60331, October 

7, 2014), at the modified area only, provided 

the actions are accomplished concurrently, or 

the actions specified in paragraph (i)(2)(ii) of 

this AD are done after accomplishing the 

actions specified in paragraph (i)(2)(i) of this 

AD. 

(i) The actions specified in paragraphs 

(g)(1) through (g)(4) of this AD on the left and 

right struts are done in accordance with the 

Accomplishment Instructions of Boeing 

Special Attention Service Bulletin 777–71– 

0055, Revision 1, dated April 15, 2015; and 

the revision specified in paragraph (g)(5) of 

this AD is done. 

(ii) A one-time general visual inspection 

for hydraulic fluid contamination (including 

contamination caused by hydraulic fluid in 

its liquid, vapor, and/or solid (coked) form) 

of the interior of the strut forward dry bay, 

and all applicable related investigative and 

corrective actions (including checking drain 

lines for blockage due to hydraulic fluid 

coking, and cleaning or replacing drain lines 

to allow drainage) are done in accordance 

with the Accomplishment Instructions of 

Boeing Special Attention Service Bulletin 

777–54–0028, Revision 1, dated December 

10, 2013, except where Boeing Special 

Attention Service Bulletin 777–54–0028, 

Revision 1, dated December 10, 2013, 

specifies to contact Boeing for repair, the 

repair must be done using a method 

approved in accordance with the procedures 

specified in paragraph (k) of this AD. 

(j) 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 Boeing Special 

Attention Service Bulletin 777–71–0055, 

dated June 12, 2014, which is not 

incorporated by reference in this AD. 

(k) Alternative Methods of Compliance 

(AMOCs) 

(1) The Manager, Seattle Aircraft 

Certification Office (ACO), 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 ACO, send it to the 

attention of the person identified in 

paragraph (l)(1) of this AD. Information may 

be emailed to: 9-ANM-Seattle-ACO-AMOCRequests@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. 

(3) For service information that contains 

steps that are labeled as Required for 

Compliance (RC), the provisions of 

paragraphs (k)(3)(i) and (k)(3)(ii) apply. 

(i) The steps labeled as RC, including 

substeps under an RC step and any figures 

identified in an RC step, must be done to 

comply with the AD. An AMOC is required 

for any deviations to RC steps, including 

substeps and identified figures. 

(ii) Steps not labeled 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 RC steps, 

including substeps and identified figures, can 

still be done as specified, and the airplane 

can be put back in an airworthy condition. 

(l) Related Information 

(1) For more information about this AD, 

contact Kevin Nguyen, Aerospace Engineer, 

Propulsion Branch, ANM–140S, FAA, Seattle 

Aircraft Certification Office (ACO), 1601 Lind 

Avenue SW., Renton, WA 98057–3356; 

phone: 425–917–6501; fax: 425–917–6590; 

email: kevin.nguyen@faa.gov. 

(2) For service information identified in 

this AD, contact Boeing Commercial 

Airplanes, Attention: Data & Services 

Management, P.O. Box 3707, MC 2H–65, 

Seattle, WA 98124–2207; telephone 206– 

544–5000, extension 1; fax 206–766–5680; 

Internet https://www.myboeingfleet.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. 

Issued in Renton, Washington, on 

December 21, 2015. 

Michael Kaszycki, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2015–32852 Filed 12–30–15; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2015–8132; Directorate 

Identifier 2015–NM–127–AD] 

RIN 2120–AA64 

Airworthiness Directives; Airbus 

Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Notice of proposed rulemaking 

(NPRM). 

SUMMARY: We propose to adopt a new 

airworthiness directive (AD) for certain 

Airbus Model A318, A319, A320, and 

A321 series airplanes. This proposed 

AD was prompted by a report of cracks 

found during maintenance inspections 

on certain lugs of the 10VU rack side 

fittings in the cockpit. This proposed 

AD would require repetitive inspections 

for cracking of the lugs on the 10VU 

rack side fittings, and repair of any 

cracking. We are proposing this AD to 

prevent loss of flight-critical 

information displayed to the flightcrew 

during a critical phase of flight, such as 

an approach or takeoff, which could 

result in loss of airplane control at an 

altitude insufficient for recovery. 

DATES: We must receive comments on 

this proposed AD by February 16, 2016. 

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 proposed 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. 

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. 

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– 

8132; 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 proposed 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 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: 


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