Federal Register / Vol. 79, No. 165 / Tuesday, August 26, 2014 / Proposed Rules 50877 

(g) Inspections and Corrective Actions 

Except as specified in paragraph (h) of this 

AD, at the applicable time specified in 

paragraph 1.E., ‘‘Compliance,’’ of Boeing 

Special Attention Service Bulletin 747–57– 

2338, dated January 14, 2014: Do a general 

visual inspection to detect delamination 

damage of the lightning strike applique (LSA) 

on the LE VCK flaps; and do all applicable 

corrective actions before further flight; in 

accordance with the Accomplishment 

Instructions of Boeing Special Attention 

Service Bulletin 747–57–2338, dated January 

14, 2014. Repeat the inspection of the LSA 

on the LE VCK flaps thereafter at the 

applicable intervals specified in paragraph 

1.E., ‘‘Compliance,’’ of Boeing Alert Service 

Bulletin 747–57–2338, dated January 14, 

2014. 

(h) Exception to Service Information 

Where Paragraph 1.E., ‘‘Compliance,’’ of 

Boeing Alert Service Bulletin 747–57–2338, 

dated January 14, 2014, specifies a 

compliance time ‘‘after the Original issue 

date of this service bulletin,’’ this AD 

requires compliance within the specified 

compliance time after the effective date of 

this AD. 

(i) 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 (j)(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) An AMOC that provides an acceptable 

level of safety may be used for any repair 

required by this AD if it is approved by the 

Boeing Commercial Airplanes Organization 

Designation Authorization (ODA) that has 

been authorized by the Manager, Seattle 

ACO, to make those findings. For a repair 

method to be approved, the repair must meet 

the certification basis of the airplane. 

(j) Related Information 

(1) For more information about this AD, 

contact Kenneth Frey, Aerospace Engineer, 

Systems and Equipment Branch, ANM–130S, 

FAA, Seattle Aircraft Certification Office, 

1601 Lind Avenue SW., Renton, WA 98057– 

3356; phone: 425–917–6468; fax: 425–917– 

6190; email: kenneth.frey@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 review 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 August 

15, 2014. 

Jeffrey E. Duven, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 2014–20218 Filed 8–25–14; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2014–0580; Directorate 

Identifier 2014–NM–081–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 supersede 

Airworthiness Directive (AD) 2011–09– 

11, which applies to certain The Boeing 

Company Model 777–200 and –300 

series airplanes. AD 2011–09–11 

currently requires repetitive inspections 

for hydraulic fluid contamination of the 

interior of the strut disconnect 

assembly; repetitive inspections for 

discrepancies of the interior of the strut 

disconnect assembly, if necessary; 

repetitive inspections of the exterior of 

the strut disconnect assembly for cracks, 

if necessary; corrective action if 

necessary; and an optional terminating 

action for the inspections. Since we 

issued AD 2011–09–11, we have 

received reports of side and top cover 

plates installed with missing fastener 

bolts, which results in an unsealed 

opening on the system disconnect 

assembly. This proposed AD would add, 

for certain airplanes, an inspection of 

the side and top cover plates to 

determine if all cover plate attach 

fasteners have been installed, and 

installing any missing fasteners 

including doing an inspection for 

damage, and repair if necessary. We are 

proposing this AD to detect and correct 

hydraulic fluid contamination, which 

can cause cracking of titanium parts in 

the system disconnect assembly; and 

also to detect and correct missing 

fasteners, which results in unsealed 

openings on the system disconnect 

assembly. Both unsafe conditions can 

compromise the engine firewall and 

result in fire hazards for both the engine 

compartment and the strut. 

DATES: We must receive comments on 

this proposed AD by October 10, 2014. 

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, 

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. 

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–2014– 

0580; 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 proposed AD. Send your comments 

to an address listed under the 


tkelley on DSK3SPTVN1PROD with PROPOSALS
50878 Federal Register / Vol. 79, No. 165 / Tuesday, August 26, 2014 / Proposed Rules 

ADDRESSES section. Include ‘‘Docket No. 

FAA–2014–0580; Directorate Identifier 

2014–NM–081–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 

On April 12, 2011, we issued AD 

2011–09–11, Amendment 39–16673 (76 

FR 24354, May 2, 2011), for The Boeing 

Company Model 777–200 and –300 

series airplanes equipped with Pratt and 

Whitney engines. AD 2011–09–11 

requires repetitive inspections for 

hydraulic fluid contamination of the 

interior of the strut disconnect 

assembly; repetitive inspections for 

discrepancies of the interior of the strut 

disconnect assembly, if necessary; 

repetitive inspections of the exterior of 

the strut disconnect assembly for cracks, 

if necessary; corrective action if 

necessary; and an optional terminating 

action for the inspections. AD 2011–09– 

11 resulted from reports of system 

disconnect boxes contaminated with 

hydraulic fluid, which led to 

subsequent cracking of titanium parts in 

the system disconnect assembly. We 

issued AD 2011–09–11 to detect and 

correct hydraulic fluid contamination, 

which can cause cracking of titanium 

parts in the system disconnect 

assembly, resulting in compromise of 

the engine firewall. A cracked firewall 

can allow fire in the engine area to enter 

the strut and can lead to an uncontained 

engine strut fire if flammable fluid is 

present. Cracking of the disconnect box 

may also reduce the effectiveness of the 

fire extinguishing system in the engine 

compartment and could contribute to an 

uncontained engine fire. In addition, a 

cracked disconnect box can leak 

flammable fluids into the engine 

compartment, which can initiate an 

engine fire, and lead to one or both fire 

conditions discussed above. 

Actions Since AD 2011–09–11, 

Amendment 39–16673 (76 FR 24354, 

May 2, 2011) Was Issued 

Since we issued AD 2011–09–11, 

Amendment 39–16673 (76 FR 24354, 

May 2, 2011), we have received reports 

of side and top cover plates installed 

with two fastener bolts on airplanes on 

which a replacement of the titanium 

system disconnect assembly was 

accomplished in accordance with AD 

2011–09–11. An operator reported that 

the side and top cover plates were only 

temporarily installed with two fasteners 

for each cover plate; additional bolts 

were not in the kits, and the service 

bulletin did not provide instructions to 

install the remaining bolts. Missing 

fasteners will allow for fastener holes on 

the cover plates to be not closed off, and 

cover plates to be loose and not sealed 

tightly against the disconnect box 

assembly, resulting in compromise of 

the engine firewall. This compromise of 

the engine firewall can lead to a fire 

breach and hazardous effects that have 

the same effects as the disconnect box 

with cracks. In addition, loose cover 

plates on the electrical side of the 

disconnect box, and vibration from the 

airplane and engine can cause damage 

to the electrical connectors and wire 

routing into, through, and out of the 

disconnect box. Damaged electrical 

connectors or wires can cause unwanted 

engine indication and crew alerting 

system (EICAS) messages or nonresponsive action by the crew when 

there are actual EICAS messages. 

Damaged electrical connectors or wires 

can create an ignition source for 

flammable fluids and result in an 

uncontained strut fire or fuel explosion. 

Relevant Service Information 

We reviewed Boeing Service Bulletin 

777–54A0024, Revision 2, dated January 

23, 2014. For information on the 

procedures and compliance times, see 

this service information at http://

www.regulations.gov by searching for 

and locating Docket No. FAA–2014– 

0580. 

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 retain all 

requirements of AD 2011–09–11, 

Amendment 39–16673 (76 FR 24354, 

May 2, 2011). This proposed AD would 

add, for certain airplanes, an inspection 

of the side and top cover plates to 

determine if all cover plate attach 

fasteners have been installed, and 

installing any missing fasteners 

including doing an inspection for 

damage, and repair if necessary. 

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: 

ESTIMATED COSTS

Action Labor cost Parts cost Cost per 

product 

Cost on U.S. 

operators 

Inspections [retained actions from AD 2011– 

09–11, Amendment 39–16673 (76 FR 

24354, May 2, 2011)].

18 work-hours × $85 per hour = $1,530 ........ $0 $1,530 $82,620 

Inspection of cover plate fasteners [new proposed action].8 work-hours × $85 per hour = $680 ............. 0 680 36,720 

We estimate the following costs to do 

any necessary repairs/replacements that 

would be required based on the results 

of the proposed inspections. We have no 

way of determining the number of 

aircraft that might need these repairs/

replacements: 


tkelley on DSK3SPTVN1PROD with PROPOSALS
Federal Register / Vol. 79, No. 165 / Tuesday, August 26, 2014 / Proposed Rules 50879 

ON-CONDITION COSTS

Action Labor cost Parts cost Cost per 

product 

Replacement [retained actions from AD 2011–09–11, 

Amendment 39–16673 (76 FR 24354, May 2, 

2011)].

35 work-hours × $85 per hour = $2,975 ...................... $420,440 $423,415 

Inspection of electrical components and installation of 

new fasteners [new proposed actions].

14 work-hours × $85 per hour = $1,190 ...................... 458 1,648 

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 proposed 

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 have 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 that the 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 

removing Airworthiness Directive (AD) 

2011–09–11, Amendment 39–16673 (76 

FR 24354, May 2, 2011), and adding the 

following new AD: 

The Boeing Company: Docket No. FAA– 

2014–0580; Directorate Identifier 2014– 

NM–081–AD. 

(a) Comments Due Date 

The FAA must receive comments on this 

AD action by October 10, 2014. 

(b) Affected ADs 

This AD replaces AD 2011–09–11, 

Amendment 39–16673 (76 FR 24354, May 2, 

2011). 

(c) Applicability 

This AD applies to The Boeing Company 

Model 777–200 and –300 series airplanes, 

certificated in any category; equipped with 

Pratt and Whitney engines; as identified in 

Boeing Service Bulletin 777–54A0024, 

Revision 2, dated January 23, 2014. 

(d) Subject 

Air Transport Association (ATA) of 

America Code 54, Nacelles/Pylons. 

(e) Unsafe Condition 

This AD was prompted by reports of 

system disconnect boxes that have been 

contaminated with hydraulic fluid and, in 

one incident, led to subsequent cracking of 

titanium parts in the system disconnect 

assembly. We have received reports of side 

and top cover plates installed with missing 

fastener bolts, which results in an unsealed 

opening on the system disconnect assembly. 

We are issuing this AD to detect and correct 

hydraulic fluid contamination, which can 

cause cracking of titanium parts in the 

system disconnect assembly; and also to 

detect and correct missing fasteners, which 

results in unsealed openings on the system 

disconnect assembly. Both unsafe conditions 

can compromise the engine firewall and 

result in fire hazards for both the engine 

compartment and the strut. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Retained Inspections and Corrective 

Actions With Revised Service Information 

This paragraph restates the requirements of 

paragraph (g) of AD 2011–09–11, 

Amendment 39–16673 (76 FR 24354, May 2, 

2011), with revised service information. 

Within 12 months after June 6, 2011 (the 

effective date of AD 2011–09–11): Do a 

general visual inspection for hydraulic fluid 

contamination of the interior of the strut 

disconnect assembly, in accordance with Part 

1 of the Accomplishment Instructions of 

Boeing Service Bulletin 777–54A0024, 

Revision 1, dated November 4, 2010; or 

Revision 2, dated January 23, 2014. As of the 

effective date of this AD, use only Boeing 

Service Bulletin 777–54A0024, Revision 2, 

dated January 23, 2014, for accomplishing 

the actions in this paragraph. 

(1) For airplanes on which no hydraulic 

fluid contamination is found (Condition 1): 

Repeat the general visual inspection required 

by paragraph (g) of this AD thereafter at 

intervals not to exceed 6,000 flight cycles or 

750 days, whichever occurs first. 

(2) For airplanes on which hydraulic fluid 

contamination is found (Condition 2): Before 

further flight, do a detailed inspection for 

discrepancies (e.g., hydraulic fluid coking, 

heat discoloration, cracks, and etching or 

pitting) of the interior of the strut disconnect 

assembly, in accordance with Part 2 of the 

Accomplishment Instructions of Boeing 

Service Bulletin 777–54A0024, Revision 1, 

dated November 4, 2010; or Revision 2, dated 

January 23, 2014. As of the effective date of 

this AD, use only Boeing Service Bulletin 

777–54A0024, Revision 2, dated January 23, 

2014, for accomplishing the actions in this 

paragraph. 

(i) For airplanes on which no discrepancy 

is found during the inspection required by 

paragraph (g)(2) of this AD (Condition 2A): 

Repeat the detailed inspection required by 

paragraph (g)(2) of this AD thereafter at 


tkelley on DSK3SPTVN1PROD with PROPOSALS
50880 Federal Register / Vol. 79, No. 165 / Tuesday, August 26, 2014 / Proposed Rules 

intervals not to exceed 6,000 flight cycles or 

750 days, whichever occurs first. 

(ii) For airplanes on which hydraulic fluid 

coking or heat discoloration is found but no 

cracking, etching, or pitting is found during 

the inspection required by paragraph (g)(2) of 

this AD (Condition 2B): Do the actions 

required by paragraph (g)(2)(ii)(A) and 

(g)(2)(ii)(B) of this AD. 

(A) Within 300 flight cycles after doing the 

inspection required by paragraph (g)(2) of 

this AD: Do a detailed inspection of the 

exterior of the strut disconnect assembly for 

cracks, in accordance with Part 3 of the 

Accomplishment Instructions of Boeing 

Service Bulletin 777–54A0024, Revision 1, 

dated November 4, 2010; or Revision 2, dated 

January 23, 2014; and repeat the detailed 

inspection thereafter at intervals not to 

exceed 300 flight cycles. As of the effective 

date of this AD, use only Boeing Service 

Bulletin 777–54A0024, Revision 2, dated 

January 23, 2014, for accomplishing the 

actions in this paragraph. 

(B) Within 6,000 flight cycles or 750 days 

after hydraulic fluid coking and/or heat 

discoloration was found during the 

inspection required by paragraph (g)(2) of 

this AD, whichever occurs first: Replace the 

titanium system disconnect assembly with an 

Inconel system, in accordance with Part 4 of 

the Accomplishment Instructions of Boeing 

Service Bulletin 777–54A0024, Revision 1, 

dated November 4, 2010; or Revision 2, dated 

January 23, 2014. As of the effective date of 

this AD, use only Boeing Service Bulletin 

777–54A0024, Revision 2, dated January 23, 

2014, for accomplishing the actions in this 

paragraph. 

(h) Retained Corrective Action With Revised 

Service Information 

This paragraph restates the requirements of 

paragraph (h) of AD 2011–09–11, 

Amendment 39–16673 (76 FR 24354, May 2, 

2011), with revised service information. For 

airplanes on which any crack, etching, or 

pitting is found during any inspection 

required by paragraph (g)(2) or (g)(2)(ii)(A) of 

this AD (Condition 3): Before further flight, 

replace the titanium system disconnect 

assembly with an Inconel system, in 

accordance with Part 4 of the 

Accomplishment Instructions of Boeing 

Service Bulletin 777–54A0024, Revision 1, 

dated November 4, 2010; or Revision 2, dated 

January 23, 2014. As of the effective date of 

this AD, use only Boeing Service Bulletin 

777–54A0024, Revision 2, dated January 23, 

2014, for accomplishing the actions in this 

paragraph. 

(i) Retained Optional Terminating Action 

With Revised Service Information 

This paragraph restates the requirements of 

paragraph (i) of AD 2011–09–11, Amendment 

39–16673 (76 FR 24354, May 2, 2011), with 

revised service information. Replacing the 

titanium system disconnect assembly with an 

Inconel system disconnect assembly in 

accordance with Part 4 of the 

Accomplishment Instructions of Boeing 

Service Bulletin 777–54A0024, Revision 1, 

dated November 4, 2010; or Revision 2, dated 

January 23, 2014; terminates the actions 

required by paragraphs (g) and (h) of this AD. 

As of the effective date of this AD, use only 

Boeing Service Bulletin 777–54A0024, 

Revision 2, dated January 23, 2014, for 

accomplishing the actions in this paragraph. 

(j) New Inspection and Corrective Action 

For airplanes on which the system 

disconnect assembly has been replaced in 

accordance with Part 4 of the 

Accomplishment Instructions of Boeing 

Service Bulletin 777–54A0024, dated April 1, 

2010; or Revision 1, dated November 4, 2010: 

Within 1,125 days after the effective date of 

this AD, do a detailed inspection of the cover 

plate fasteners to determine if all cover plate 

attach fasteners are installed, in accordance 

with Part 5 of the Accomplishment 

Instructions of Boeing Service Bulletin 777– 

54A0024, Revision 2, dated January 23, 2014. 

If any fastener is missing, before further 

flight, install fasteners (including doing a 

detailed inspection for damage of the 

electrical components and repairing any 

damaged components), in accordance with 

Part 6 of the Accomplishment Instructions of 

Boeing Service Bulletin 777–54A0024, 

Revision 2, dated January 23, 2014. 

(k) Credit for Previous Actions 

This paragraph restates the credit provided 

by paragraph (j) of AD 2011–09–11, 

Amendment 39–16673 (76 FR 24354, May 2, 

2011). This paragraph provides credit for the 

corresponding actions required by 

paragraphs (g), (h), and (i) of this AD, if those 

actions were performed before June 6, 2011 

(the effective date of AD 2011–09–11) using 

Boeing Service Bulletin 777–54A0024, dated 

April 1, 2010, which is not incorporated by 

reference in this AD. 

(l) 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 (m)(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) An AMOC that provides an acceptable 

level of safety may be used for any repair 

required by this AD if it is approved by the 

Boeing Commercial Airplanes Organization 

Designation Authorization (ODA) that has 

been authorized by the Manager, Seattle 

ACO, to make those findings. For a repair 

method to be approved, the repair must meet 

the certification basis of the airplane, and the 

approval must specifically refer to this AD. 

(m) 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 August 

15, 2014. 

Jeffrey E. Duven, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 2014–20221 Filed 8–25–14; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2014–0582; Directorate 

Identifier 2014–NM–065–AD] 

RIN 2120–AA64 

Airworthiness Directives; Bombardier, 

Inc. Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Notice of proposed rulemaking 

(NPRM). 

SUMMARY: We propose to supersede 

Airworthiness Directive (AD) 2014–03– 

05, for certain Bombardier, Inc. Model 

BD–700–1A10 airplanes. AD 2014–03– 

05 currently requires modification of the 

air data probes and sensors. Since we 

issued AD 2014–03–05, we have 

determined that additional airplanes are 

affected by the unsafe condition. This 

proposed AD would add airplanes to the 

applicability. We are proposing this AD 

to detect and correct an unannunciated 

failure of two pitot static probe heaters, 

which could affect controllability of the 

airplane in icing conditions. 

DATES: We must receive comments on 

this proposed AD by October 10, 2014. 

ADDRESSES: You may send comments 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. 


tkelley on DSK3SPTVN1PROD with PROPOSALS