Federal Register / Vol. 83, No. 246 / Wednesday, December 26, 2018 / Proposed Rules 66175 

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– 

2018–1011; Product Identifier 2018– 

NM–131–AD. 

(a) Comments Due Date 

We must receive comments by February 

11, 2019. 

(b) Affected ADs 

None. 

(c) Applicability 

This AD applies to all The Boeing 

Company Model 767–200, –300, –300F, and 

–400ER series airplanes, certificated in any 

category. 

(d) Subject 

Air Transport Association (ATA) of 

America Code 25, Equipment/Furnishings. 

(e) Unsafe Condition 

This AD was prompted by reports of 

uncommanded movements of the Captain’s 

and First Officer’s seats. We are issuing this 

AD to address uncommanded movement of 

the Captain’s and First Officer’s seats. An 

uncommanded seat movement during a 

critical part of a flight, such as take-off or 

landing, could cause a flight control 

obstruction or unintended flight control 

input, which could result in the loss of the 

ability to control the airplane. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Seat Identification and On-Condition 

Actions 

Within 36 months after the effective date 

of this AD, do an inspection to determine the 

part number, and serial number as 

applicable, of the Captain’s and First 

Officer’s seats, and do all applicable oncondition actions, in accordance with the 

Accomplishment Instructions of Boeing 

Special Attention Service Bulletin 767–25– 

0539, Revision 1, dated July 17, 2018. 

(h) Detailed Inspection and Repetitive 

Checks of Horizontal Movement System and 

On-Condition Actions 

Except as specified in paragraph (i) of this 

AD: At the applicable times specified in 

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

Special Attention Service Bulletin 767–25– 

0549, Revision 1, dated August 10, 2018 

(‘‘BSASB 767–25–0549, Revision 1’’), do all 

applicable actions identified as ‘‘RC’’ 

(required for compliance) in, and in 

accordance with, the Accomplishment 

Instructions of BSASB 767–25–0549, 

Revision 1. 

(i) Exceptions to Service Information 

Specifications 

For purposes of determining compliance 

with the requirements of this AD: Where 

BSASB 767–25–0549, Revision 1, uses the 

phrase ‘‘the original issue date of this service 

bulletin,’’ this AD requires using ‘‘the 

effective date of this AD.’’ 

(j) Optional Terminating Action for 

Repetitive Checks 

(1) For Group 1, Configuration 2 and 4 

airplanes identified in BSASB 767–25–0549, 

Revision 1: Installation of a serviceable 

Captain’s seat, as specified in, and in 

accordance with, the Accomplishment 

Instructions of BSASB 767–25–0549, 

Revision 1, terminates the repetitive checks 

of the Captain’s seat as required by paragraph 

(h) of this AD for that airplane only. 

(2) For Group 1, Configuration 3 and 4 

airplanes: Installation of a serviceable First 

Officer’s seat BSASB 767–25–0549, Revision 

1, as specified in, and in accordance with, 

the Accomplishment Instructions of BSASB 

767–25–0549, Revision 1, terminates the 

repetitive checks of the First Officer’s seat as 

required by paragraph (h) of this AD for that 

airplane only. 

(k) Alternative Methods of Compliance 

(AMOCs) 

(1) The Manager, Seattle ACO 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 (l)(1) of 

this AD. Information may be emailed to: 9- 

ANM-Seattle-ACO-AMOC-Requests@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, 

modification, or alteration 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 

Branch, FAA, to make those findings. To be 

approved, the repair method, modification 

deviation, or alteration deviation must meet 

the certification basis of the airplane, and the 

approval must specifically refer to this AD. 

(4) For service information that contains 

steps that are labeled as Required for 

Compliance (RC), the provisions of 

paragraphs (k)(4)(i) and (k)(4)(ii) of this AD 

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. If a step or substep is 

labeled ‘‘RC Exempt,’’ then the RC 

requirement is removed from that step or 

substep. 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 Brandon Lucero, Aerospace Engineer, 

Cabin Safety and Environmental Systems 

Section, FAA, Seattle ACO Branch, 2200 

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

phone and fax: 206–231–3569; email: 

Brandon.Lucero@faa.gov. 

(2) For service information identified in 

this AD, 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 

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. 

Issued in Des Moines, Washington, on 

December 13, 2018. 

Michael Kaszycki, 

Acting Director, System Oversight Division, 

Aircraft Certification Service. 

[FR Doc. 2018–27882 Filed 12–21–18; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2018–1058; Product 

Identifier 2018–CE–051–AD] 

RIN 2120–AA64 

Airworthiness Directives; Pilatus 

Aircraft Ltd. Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Notice of proposed rulemaking 

(NPRM). 

SUMMARY: We propose to adopt a new 

airworthiness directive (AD) for Pilatus 

Aircraft Ltd. Model PC–6, PC–6/350, 

PC–6/350–H1, PC–6/350–H2, PC–6/A, 

PC–6/A–H1, PC–6/A–H2, PC–6/B–H2, 

PC–6/B1–H2, PC–6/B2–H2, PC–6/B2– 

H4, PC–6/C–H2, PC–6/C1–H2, PC–6– 

H1, and PC–6–H2 airplanes. This 

proposed AD results from mandatory 

continuing airworthiness information 

(MCAI) originated by an aviation 

authority of another country to identify 


amozie on DSK3GDR082PROD with PROPOSALS1
66176 Federal Register / Vol. 83, No. 246 / Wednesday, December 26, 2018 / Proposed Rules 

and correct an unsafe condition on an 

aviation product. The MCAI describes 

the unsafe condition as sheared or 

missing rivets on the horizontal 

stabilizer hinge bracket assemblies. We 

are issuing this proposed AD to require 

actions to address the unsafe condition 

on these products. 

DATES: We must receive comments on 

this proposed AD by February 11, 2019. 

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. 

• 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 20590, between 9 a.m. 

and 5 p.m., Monday through Friday, 

except Federal holidays. 

For service information identified in 

this proposed AD, contact PILATUS 

Aircraft Ltd., Customer Technical 

Support (MCC), P.O. Box 992, CH–6371 

Stans, Switzerland; phone: +41 (0)41 

619 67 74; fax: +41 (0)41 619 67 73; 

email: techsupport@pilatusaircraft.com; internet: http://

www.pilatus-aircraft.com. You may 

review this referenced service 

information at the FAA, Policy and 

Innovation Division, 901 Locust, Kansas 

City, Missouri 64106. For information 

on the availability of this material at the 

FAA, call (816) 329–4148. 

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– 

1058; 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 proposed 

AD, the regulatory evaluation, any 

comments received, and other 

information. The street address for 

Docket Operations (telephone (800) 

647–5527) is in the ADDRESSES section. 

Comments will be available in the AD 

docket shortly after receipt. 

FOR FURTHER INFORMATION CONTACT: 

Doug Rudolph, Aerospace Engineer, 

FAA, Small Airplane Standards Branch, 

901 Locust, Room 301, Kansas City, 

Missouri 64106; telephone: (816) 329– 

4059; fax: (816) 329–4090; email: 

doug.rudolph@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 

ADDRESSES section. Include ‘‘Docket No. 

FAA–2018–1058; Product Identifier 

2018–CE–051–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://

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 

The European Aviation Safety Agency 

(EASA), which is the Technical Agent 

for the Member States of the European 

Community, has issued AD No. 2018– 

0217, dated October 10, 2018 (referred 

to after this as ‘‘the MCAI’’), to correct 

an unsafe condition for the specified 

products. The MCAI states: 

During a routine inspection, the rivets of 

the hinge bracket assemblies on a Pilatus PC– 

6 were found to be sheared or missing. 

Investigation results identified that this was 

most likely due to application of too much 

force to the ends of the horizontal stabilizer 

during ground handling. 

This condition, if not detected and 

corrected, could lead to failure of the primary 

horizontal stabilizer load path and 

consequent separation of the horizontal 

stabilizer, possibly resulting in loss of control 

of the aeroplane. 

To address this potential unsafe condition, 

Pilatus Aircraft Ltd issued the SB [service 

bulletin] to provide applicable inspection 

instructions. 

For the reasons described above, this 

[EASA] AD requires a one-time inspection of 

the affected parts and the horizontal 

stabilizer front spar attachment area and, 

depending on findings, accomplishment of 

applicable corrective action(s). This [EASA] 

AD also requires, before installation, 

inspection of, and, depending on findings, 

corrective action(s) on, affected parts held as 

spare. 

The amount of force to the ends of the 

horizontal stabilizer cannot be 

quantified; however, fleet experience 

shows that repetitive pushing or pulling 

on the horizontal stabilizer to move the 

airplane on the ground can overload the 

rivets. Although a root cause could not 

be determined, due to the severity of 

separation of a horizontal stabilizer, 

EASA determined that the corrective 

actions should be required for other 

airplanes of the same type design. 

Pilatus Aircraft Ltd. had previously 

considered the small size of the original 

‘‘DO NOT PUSH’’ markings and the 

significant chance of the markings being 

over-sprayed during a respray. As a 

result, Pilatus Aircraft Ltd. issued a 

service bulletin to specify replacing the 

smaller markings with new, larger 

placards. The FAA proposes to require 

these placards in the NPRM. 

You may examine the MCAI on the 

internet at http://www.regulations.gov 

by searching for and locating Docket No. 

FAA–2018–1058. 

Related Service Information Under 1 

CFR Part 51 

Pilatus Aircraft Ltd. has issued PC–6 

Service Bulletin No. 55–004, dated July 

2, 2018. The service information 

contains procedures for inspecting the 

left-hand and right-hand horizontal 

stabilizer hinge bracket assemblies and, 

if any discrepancies are found, repairing 

or replacing any damaged rivets and 

screws. Pilatus Aircraft Ltd. has also 

issued PC–6 Service Bulletin No. 55– 

002, Revision. No. 1, dated February 18, 

2016. This service information contains 

procedures for inspecting and repairing 

the horizontal stabilizer attachment 

hardware and installing four ‘‘DO NOT 

PUSH’’ placards. 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 the Proposed 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 this State of 

Design Authority, they have notified us 

of the unsafe condition described in the 

MCAI and service information 

referenced above. We are proposing this 

AD because we evaluated all 

information and determined the unsafe 

condition exists and is likely to exist or 

develop on other products of the same 

type design. 

We have reviewed the MCAI and, in 

general, agree with the substance. The 

MCAI AD does not require installing 

‘‘DO NOT PUSH’’ placards. We have 

added that requirement to this proposed 

AD. 

Costs of Compliance 

We estimate that this proposed AD 

would affect 30 products of U.S. 

registry. We also estimate that it would 

take about 9 work-hours per product to 


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Federal Register / Vol. 83, No. 246 / Wednesday, December 26, 2018 / Proposed Rules 66177 

comply with the inspection and placard 

requirements of this proposed AD. The 

average labor rate is $85 per work-hour. 

Required parts would cost about $200 

per product. 

Based on these figures, we estimate 

the cost of the proposed inspection and 

placard requirements on U.S. operators 

to be $28,950, or $965 per product. 

In addition, we estimate the following 

to do any necessary follow-on actions: 

Each rivet replacement would take 2 

work-hours, fastener replacement would 

take 3 work-hours, one hinge bracket 

assembly replacement would take 9 

work-hours, and two hinge bracket 

assembly replacements would take 15 

work-hours. The total estimated cost of 

parts would be $10,000. We have no 

way of determining the number of 

products that may need replacement. 

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 small airplanes, gliders, 

balloons, airships, domestic business jet 

transport airplanes, and associated 

appliances to the Director of the Policy 

and Innovation Division. 

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): 

Pilatus Aircraft Ltd.: Docket No. FAA–2018– 

1058; Product Identifier 2018–CE–051– 

AD. 

(a) Comments Due Date 

We must receive comments by February 

11, 2019. 

(b) Affected ADs 

None. 

(c) Applicability 

This AD applies to Pilatus Aircraft Ltd. 

Model PC–6, PC–6/350, PC–6/350–H1, PC–6/ 

350–H2, PC–6/A, PC–6/A–H1, PC–6/A–H2, 

PC–6/B–H2, PC–6/B1–H2, PC–6/B2–H2, PC– 

6/B2–H4, PC–6/C–H2, PC–6/C1–H2, PC–6– 

H1, PC–6–H2 airplanes, all serial numbers, 

certificated in any category. 

Note 1 to paragraph (c): These airplanes 

may also be identified as Fairchild Republic 

Company airplanes, Fairchild Industries 

airplanes, Fairchild Heli Porter airplanes, or 

Fairchild-Hiller Corporation airplanes. 

(d) Subject 

Air Transport Association of America 

(ATA) Code 55: Stabilizers. 

(e) Reason 

This AD was prompted by mandatory 

continuing airworthiness information (MCAI) 

originated by an aviation authority of another 

country to identify and correct an unsafe 

condition on an aviation product. The MCAI 

describes the unsafe condition as sheared or 

missing rivets on the horizontal stabilizer 

hinge bracket assemblies. We are issuing this 

AD to prevent failure of the primary 

horizontal stabilizer load path, which could 

lead to separation of the horizontal stabilizer 

and result in loss of control of the airplane. 

(f) Actions and Compliance 

Unless already done, do the following 

actions in paragraphs (f)(1) and (2). 

(1) Within the next 100 hours time-inservice after the effective date of this AD or 

within the next 12 months after the effective 

date of this AD, whichever occurs first: 

(i) Inspect the left-hand and the right-hand 

horizontal stabilizer hinge bracket assemblies 

for cracks, loose screws and rivets, sheared 

rivets, missing rivets, and looseness of the 

electrical bonding strap, and inspect the top 

and bottom screws at each hinge bracket. 

Repair or replace any parts with 

discrepancies before further flight. You must 

do the actions required by this paragraph by 

following sections C through G of the 

Accomplishment Instructions—Part 1—On 

Aircraft in Pilatus Aircraft Ltd. PC–6 Service 

Bulletin No. 55–004, dated July 2, 2018. 

(ii) Install four ‘‘DO NOT PUSH’’ placards, 

part number 110.71.06.847 or 110.71.06.848, 

on the horizontal stabilizer by following 

section G of the Accomplishment 

Instructions—Aircraft in Pilatus Aircraft Ltd. 

PC–6 Service Bulletin No. 55–002, Revision. 

No. 1, dated February 18, 2016. 

(2) After the effective date of this AD, do 

not install a horizontal stabilizer on any 

airplane unless it has been inspected as 

specified in paragraph (f)(1)(i) of this AD and 

found to be free of discrepancies or all 

discrepancies have been repaired or replaced. 

(g) Other FAA AD Provisions 

The following provisions also apply to this 

AD: 

(1) Alternative Methods of Compliance 

(AMOCs): The Manager, Small Airplane 

Standards Branch, FAA, has the authority to 

approve AMOCs for this AD, if requested 

using the procedures found in 14 CFR 39.19. 

Send information to ATTN: Doug Rudolph, 

Aerospace Engineer, FAA, Small Airplane 

Standards Branch, 901 Locust, Room 301, 

Kansas City, Missouri 64106; telephone: 

(816) 329–4059; fax: (816) 329–4090; email: 

doug.rudolph@faa.gov. Before using any 

approved AMOC on any airplane to which 

the AMOC applies, notify your appropriate 

principal inspector (PI) in the FAA Flight 

Standards District Office (FSDO), or lacking 

a PI, your local FSDO. 

(2) Contacting the Manufacturer: For any 

requirement in this AD to obtain corrective 

actions from a manufacturer, the action must 

instead be accomplished using a method 

approved by the Manager, Small Airplane 

Standards Branch, FAA, or the European 

Aviation Safety Agency (EASA). 


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66178 Federal Register / Vol. 83, No. 246 / Wednesday, December 26, 2018 / Proposed Rules 

(h) Related Information 

Refer to MCAI European Aviation Safety 

Agency AD No. 2018–0217, dated October 

10, 2018, for related information. You may 

examine the MCAI on the internet at http:// 

www.regulations.gov by searching for and 

locating Docket No. FAA–2018–1058. For 

service information related to this AD, 

contact PILATUS Aircraft Ltd., Customer 

Technical Support (MCC), P.O. Box 992, CH– 

6371 Stans, Switzerland; phone: +41 (0)41 

619 67 74; fax: +41 (0)41 619 67 73; email: 

techsupport@pilatus-aircraft.com; internet: 

http://www.pilatus-aircraft.com. You may 

review this referenced service information at 

the FAA, Policy and Innovation Division, 901 

Locust, Kansas City, Missouri 64106. For 

information on the availability of this 

material at the FAA, call (816) 329–4148. 

Issued in Kansas City, Missouri, on 

December 17, 2018. 

Melvin J. Johnson, 

Aircraft Certification Service, Deputy 

Director, Policy and Innovation Division, 

AIR–601. 

[FR Doc. 2018–27899 Filed 12–21–18; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2018–1012; Product 

Identifier 2018–NM–132–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 all The 

Boeing Company Model 777 airplanes. 

This proposed AD was prompted by 

reports of uncommanded movements of 

the Captain’s and First Officer’s seats. 

This proposed AD would require an 

identification of the part number, and if 

applicable the serial number, of the 

Captain’s and First Officer’s seats, and 

do applicable on-condition actions for 

affected seats. This proposed AD would 

also require a one-time detailed 

inspection and repetitive checks of the 

horizontal movement system of the 

Captain’s and First Officer’s seats and 

applicable on-condition actions. This 

proposed AD would also provide an 

optional terminating action for the 

repetitive checks of the horizontal 

movement system. We are proposing 

this AD to address the unsafe condition 

on these products. 

DATES: We must receive comments on 

this proposed AD by February 11, 2019. 

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 NPRM, 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– 

1012. 

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– 

1012; 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 NPRM, the 

regulatory evaluation, any comments 

received, and other information. The 

street address for Docket Operations 

(phone: 800–647–5527) is in the 

ADDRESSES section. Comments will be 

available in the AD docket shortly after 

receipt. 

FOR FURTHER INFORMATION CONTACT: 

Brandon Lucero, Aerospace Engineer, 

Cabin Safety and Environmental 

Systems Section, FAA, Seattle ACO 

Branch, 2200 South 216th St., Des 

Moines, WA 98198; phone and fax: 206– 

231–3569; email: Brandon.Lucero@

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– 

2018–1012; Product Identifier 2018– 

NM–132–AD’’ at the beginning of your 

comments. We specifically invite 

comments on the overall regulatory, 

economic, environmental, and energy 

aspects of this NPRM. We will consider 

all comments received by the closing 

date and may amend this NPRM 

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 have received reports indicating 

that there have been uncommanded 

movements of the Captain’s and First 

Officer’s seats. A Model 747 operator 

reported that during a takeoff, the First 

Officer’s seat unlocked from its seat 

tracks and moved aft. The First Officer 

was unable to control the airplane and 

the Captain took over the controls to 

avoid a rejected takeoff. The unlocking 

of the seat from the seat tracks was 

caused by actuator damage, which was 

a result of incorrect adjustment of the 

seat’s manual release lever cable, which 

allowed the clutch mechanism to only 

partially engage. Captain’s and First 

Officer’s seats having the same part 

numbers are installed on both Model 

747 and Model 777 airplanes. We are 

considering additional rulemaking to 

address the unsafe condition for Model 

747 airplanes. 

In addition, a Model 777 operator 

reported that the Captain’s seat could 

not be locked in position after an 

adjustment to the horizontal seat 

position in flight. The seat became 

unlocked from the track and moved 

freely forward and aft. Control was 

given to the First Officer for approach 

and landing. The results of an 

inspection revealed that the horizontal 

actuator output shaft had broken. When 

a horizontal actuator output shaft 

breaks, the pilot cannot prevent seat 

movement in a forward and aft direction 

and cannot lock the seat in position. A 

broken horizontal actuator output shaft 

is the result of high loads, that exceed 

the design limits, caused by a stalled 

motor that can occur due to high 

mechanical resistance to motion during 

powered operation of the seat. Foreign 

object debris (FOD) in the seat tracks is 

another condition that can result in a 

stalled motor and cause the horizontal 

actuator output shaft to break. 

An uncommanded seat movement 

during a critical part of a flight, such as 

takeoff or landing, could cause a flight 


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