Federal Register / Vol. 79, No. 125 / Monday, June 30, 2014 / Proposed Rules 36675 

(2) Do detailed and eddy current 

inspections of the frame at stations 328, 344, 

and 360 for cracking or a severed frame web; 

and external detailed and eddy current 

inspections of the fuselage skin for cracking. 

(k) Group 7 Airplanes: Repetitive 

Inspections, Related Investigative Actions, 

and Corrective Actions at Station 328 

For airplanes identified as Group 7 in 

Boeing Alert Service Bulletin 737–53A1323, 

dated December 6, 2013: At the applicable 

time specified in Table 6 of Paragraph 1.E., 

‘‘Compliance,’’ of Boeing Alert Service 

Bulletin 737–53A1323, dated December 6, 

2013, except as provided by paragraph (m)(1) 

of this AD, do a detailed inspection of the 

frame at station 328 for cracking or a severed 

frame web; and do all applicable related 

investigative and corrective actions; in 

accordance with the Accomplishment 

Instructions of Boeing Alert Service Bulletin 

737–53A1323, dated December 6, 2013, 

except as specified in paragraph (m)(2) of this 

AD. Do all applicable related investigative 

and corrective actions before further flight. 

Repeat the inspections specified in this 

paragraph thereafter at the applicable time 

and intervals specified in paragraph 1.E., 

‘‘Compliance,’’ of Boeing Alert Service 

Bulletin 737–53A1323, dated December 6, 

2013. Doing the repair of the frame at station 

328, in accordance with the Accomplishment 

Instructions of Boeing Alert Service Bulletin 

737–53A1323, dated December 6, 2013, 

except as specified in paragraph (m)(2) of this 

AD, terminates the repetitive inspection 

requirements of this paragraph. 

(l) Groups 2 Through 5 Airplanes: Repetitive 

Inspections, Related Investigative Actions, 

and Corrective Actions at Station 380 

For airplanes identified as Groups 2 

through 5 in Boeing Alert Service Bulletin 

737–53A1323, dated December 6, 2013: At 

the applicable time specified in Tables 9 and 

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

Boeing Alert Service Bulletin 737–53A1323, 

dated December 6, 2013, except as provided 

by paragraph (m)(1) of this AD, do detailed 

and eddy current inspections of the frame at 

station 380 for cracking or a severed frame 

web; and do all applicable corrective actions; 

in accordance with the Accomplishment 

Instructions of Boeing Alert Service Bulletin 

737–53A1323, dated December 6, 2013, 

except as specified in paragraph (m)(2) of this 

AD. Do all applicable corrective actions 

before further flight. Repeat the inspections 

specified in this paragraph thereafter at the 

applicable time and intervals specified in 

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

Alert Service Bulletin 737–53A1323, dated 

December 6, 2013. 

(m) Exceptions to Service Information 

(1) Where Boeing Alert Service Bulletin 

737–53A1323, dated December 6, 2013, 

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. 

(2) If any cracking is found during any 

inspection required by this AD, and Boeing 

Alert Service Bulletin 737–53A1323, dated 

December 6, 2013, specifies to contact Boeing 

for appropriate action: Before further flight, 

repair the cracking using a method approved 

in accordance with the procedures specified 

in paragraph (o) of this AD. 

(n) Post-Repair Inspections and PostModification Inspections 

The post-repair and post-modification 

inspections specified in Tables 13 through 15 

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

Alert Service Bulletin 737–53A1323, dated 

December 6, 2013, are not required by this 

AD. 

Note 1 to paragraph (n) of this AD: The 

post-repair and post-modification inspections 

specified in Tables 13 through 15 of 

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

Alert Service Bulletin 737–53A1323, dated 

December 6, 2013, may be used in support 

of compliance with section 121.1109(c)(2) or 

129.109(b)(2) of the Federal Aviation 

Regulations (14 CFR 121.1109(c)(2) or 14 CFR 

129.109(b)(2)). The corresponding actions 

specified in the Accomplishment 

Instructions of Boeing Alert Service Bulletin 

737–53A1323, dated December 6, 2013, are 

not required by this AD. 

(o) 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 (p)(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 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. 

(p) Related Information 

(1) For more information about this AD, 

contact Alan Pohl, Aerospace Engineer, 

Airframe Branch, ANM–120S, FAA, Seattle 

Aircraft Certification Office, 1601 Lind 

Avenue SW., Renton, WA 98057–3356; 

phone: 425–917–6450; fax: 425–917–6590; 

email: alan.pohl@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 June 19, 

2014. 

Michael Kaszycki, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2014–15251 Filed 6–27–14; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2014–0345; Directorate 

Identifier 2013–NM–230–AD] 

RIN 2120–AA64 

Airworthiness Directives; Beechcraft 

Corporation (Type Certificate 

Previously Held by Hawker Beechcraft 

Corporation; Raytheon Aircraft 

Company; Beech Aircraft Corporation) 

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 

Beechcraft Corporation (Type Certificate 

Previously Held by Hawker Beechcraft 

Corporation; Raytheon Aircraft 

Company; Beech Aircraft Corporation) 

Model 400, 400A, 400T, and MU–300 

airplanes. This proposed AD was 

prompted by a report of a failure of the 

Acme nut threads in a pitch trim 

actuator (PTA). This proposed AD 

would require an inspection to 

determine if PTAs having a certain 

serial number and part number are 

installed, and replacement if they are 

installed. This proposed AD would also 

require repetitive replacements of PTAs 

with new PTAs or certain overhauled 

PTAs. We are proposing this AD to 

prevent failure of the Acme nut threads 

in the PTA, which could lead to loss of 

control of pitch trim and reduced 

controllability of the airplane. 

DATES: We must receive comments on 

this proposed AD by August 29, 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 


emcdonald on DSK67QTVN1PROD with PROPOSALS
36676 Federal Register / Vol. 79, No. 125 / Monday, June 30, 2014 / Proposed Rules 

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 Beechcraft 

Corporation, TMDC, P.O. Box 85, 

Wichita, KS 67201–0085; telephone 

316–676–8238; fax 316–671–2540; email 

tmdc@beechcraft.com; Internet http://

pubs.beechcraft.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– 

0345; 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: Ann 

Johnson, Aerospace Engineer, Systems 

and Propulsion Branch, ACE–116W, 

FAA, Wichita Aircraft Certification 

Office (ACO), 1801 Airport Road, Room 

100, Mid-Continent Airport, Wichita, 

KS 67209; phone: (316) 946–4105; fax: 

(316) 946–4107; email: Ann.Johnson@

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– 

2014–0345; Directorate Identifier 2013– 

NM–230–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 have received a report of a failure 

of the Acme nut threads in a PTA, due 

to accelerated thread wear on the Acme 

nut that mates with the jackscrew. This 

condition, if not corrected, could result 

in failure of the Acme nut threads in the 

PTA, which could lead to loss of control 

of pitch trim and reduced controllability 

of the airplane. 

Relevant Service Information 

We reviewed Hawker Beechcraft 

Mandatory Service Bulletin 27–4100, 

dated March 2012. This service bulletin 

describes procedures for an inspection 

to determine if PTAs having a certain 

serial number and part number are 

installed, and replacing those PTAs 

having specific serial numbers listed in 

the service bulletin. 

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 these same 

type designs. 

Proposed AD Requirements 

This proposed AD would require 

accomplishing the actions specified in 

the service information described 

previously, except as discussed under 

‘‘Differences Between This Proposed AD 

and the Service Information.’’ 

Differences Between This Proposed AD 

and the Service Information 

Although Hawker Beechcraft 

Mandatory Service Bulletin 27–4100, 

dated March 2012, does not require 

repetitive replacements, this proposed 

AD would require repetitive 

replacements of PTAs with new PTAs or 

with overhauled PTAs having an Acme 

nut and jackscrew replaced with a new 

Acme nut and jackscrew every 1,800 

flight hours or at the next PTA overhaul, 

whichever occurs first. 

While the effectivity of Hawker 

Beechcraft Mandatory Service Bulletin 

27–4100, dated March 2012, does not 

include Model MU–300 airplanes, those 

airplanes are included in the 

applicability of this proposed AD since 

the affected PTAs can also be used on 

these airplanes. 

Costs of Compliance 

We estimate that this proposed AD 

affects 735 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 

Identification of serial/part 

numbers (735 airplanes).

1 work-hour × $85 per 

hour = $85.

$0 ...................................... $85 .................................... $62,475. 

Replacement of PTA (26 

airplanes).

10 work-hours × $85 per 

hour = $850 per replacement.

$17,334 per replacement .. $18,184 per replacement .. $472,784 per replacement. 

Repetitive replacement of 

jackscrew and Acme nut 

on PTAs (735 airplanes).

10 work-hours × $85 per 

hour = $850 per replacement.

$17,334 per replacement .. $18,184 per replacement .. $13,365,240 per replacement. 

According to the manufacturer, the 

costs of this proposed AD associated 

with Hawker Beechcraft Mandatory 

Service Bulletin 27–4100, dated March 

2012, may be covered under warranty, 

thereby reducing the cost impact on 

affected owners/operators. We do not 

control warranty coverage for affected 

individuals. As a result, we have 

included all costs in our cost estimate. 

The costs of the repetitive replacement 

are not covered under warranty. 

However, the PTA manufacturer states 

that it is already replacing the Acme nut 

and jackscrew at every overhaul, so the 

owners/operators should not see a cost 

increase due to this repetitive 

replacement requirement. 


emcdonald on DSK67QTVN1PROD with PROPOSALS
Federal Register / Vol. 79, No. 125 / Monday, June 30, 2014 / Proposed Rules 36677 

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 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): 

Beechcraft Corporation (Type Certificate 

Previously Held by Hawker Beechcraft 

Corporation; Raytheon Aircraft 

Company; Beech Aircraft Corporation): 

Docket No. FAA–2014–0345; Directorate 

Identifier 2013–NM–230–AD. 

(a) Comments Due Date 

We must receive comments by August 29, 

2014. 

(b) Affected ADs 

None. 

(c) Applicability 

This AD applies to the airplanes identified 

in paragraphs (c)(1) and (c)(2) of this AD, 

certificated in any category. 

(1) Beechcraft Corporation (Type 

Certificate Previously Held by Hawker 

Beechcraft Corporation; Raytheon Aircraft 

Company; Beech Aircraft Corporation) 

airplanes identified in paragraphs (c)(1)(i), 

(c)(1)(ii), and (c)(1)(iii) of this AD. 

(i) Model 400 Beechjet airplanes having 

serial numbers RJ–1 through RJ–65, 

inclusive. 

(ii) Model 400A Beechjet airplanes having 

serial numbers RK–1 through RK–604, 

inclusive. 

(iii) Model 400T Beechjet airplanes having 

serial numbers TT–1 through TT–180, 

inclusive, and TX–1 through TX–13, 

inclusive. 

(2) Beechcraft Corporation (Type 

Certificate Previously Held by Hawker 

Beechcraft Corporation; Raytheon Aircraft 

Company; Mitsubishi Heavy Industries, Inc. 

Ltd.) Model MU–300 airplanes, having serial 

numbers A003SA through A093SA, 

inclusive. 

(d) Subject 

Air Transport Association (ATA) of 

America Code 27, Flight Controls. 

(e) Unsafe Condition 

This AD was prompted by a report of a 

failure of the Acme nut threads in a pitch 

trim actuator (PTA). We are issuing this AD 

to prevent failure of the Acme nut threads in 

the PTA, which could lead to loss of control 

of pitch trim and reduced controllability of 

the airplane. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Determination of Serial Number and Part 

Number 

Within 200 flight hours or 6 months after 

the effective date of this AD, whichever 

occurs first, inspect to determine the serial 

number and part number of the PTA, in 

accordance with the Accomplishment 

Instructions of Hawker Beechcraft Mandatory 

Service Bulletin 27–4100, dated March 2012. 

A review of manufacturer delivery and 

operator maintenance records is acceptable, 

in lieu of the inspection, if the serial number 

and part number of the PTA can be 

conclusively determined from that review. 

(h) Replacement 

If any serial number and part number 

found during an inspection required by 

paragraph (g) of this AD is one listed in Table 

1 or Table 2 of Hawker Beechcraft Mandatory 

Service Bulletin 27–4100, dated March 2012: 

Within 200 flight hours or 6 months after the 

effective date of this AD, whichever occurs 

first, replace the PTA with a serviceable PTA 

or an overhauled PTA having an Acme nut 

and jackscrew replaced with a new Acme nut 

and jackscrew, in accordance with the 

Accomplishment Instructions of Hawker 

Beechcraft Mandatory Service Bulletin 27– 

4100, dated March 2012. 

(i) Repetitive Replacements 

Within 1,800 flight hours after the effective 

date of this AD, or at the next PTA overhaul, 

whichever occurs first, replace the PTA with 

a new PTA or an overhauled PTA having the 

Acme nut and jackscrew replaced with a new 

Acme nut and jackscrew, in accordance with 

sections 3.A.(2), (3), and (5) through (10) of 

Hawker Beechcraft Mandatory Service 

Bulletin 27–4100, dated March 2012. Repeat 

the replacement thereafter at intervals not to 

exceed 1,800 flight hours, or at every PTA 

overhaul, whichever occurs first. 

(j) Alternative Methods of Compliance 

(AMOCs) 

(1) The Manager, Wichita 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 (k)(1) of this AD. 

(2) Before using any approved AMOC, 

notify your appropriate principal inspector, 

or lacking a principal inspector, the manager 

of the local flight standards district office/

certificate holding district office. 

(k) Related Information 

(1) For more information about this AD, 

contact Ann Johnson, Aerospace Engineer, 

Systems and Propulsion Branch, ACE–116W, 

FAA, Wichita Aircraft Certification Office 

(ACO), 1801 Airport Road, Room 100, MidContinent Airport, Wichita, KS 67209; 

phone: (316) 946–4105; fax: (316) 946–4107; 

email: Ann.Johnson@faa.gov. 

(2) For service information identified in 

this AD, contact Beechcraft Corporation, 

TMDC, P.O. Box 85, Wichita, KS 67201– 

0085; telephone 316–676–8238; fax 316–671– 

2540; email tmdc@beechcraft.com; Internet 

http://pubs.beechcraft.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. 


emcdonald on DSK67QTVN1PROD with PROPOSALS
36678 Federal Register / Vol. 79, No. 125 / Monday, June 30, 2014 / Proposed Rules 

Issued in Renton, Washington, on June 10, 

2014. 

Jeffrey E. Duven, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 2014–15246 Filed 6–27–14; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2014–0426; Directorate 

Identifier 2013–NM–231–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 767 and 

777 airplanes. This proposed AD was 

prompted by reports of uncommanded 

door closure of the large lower lobe 

cargo door. This proposed AD would 

require inspecting for part numbers and 

serial numbers of the rotary actuators of 

the large forward and aft lower lobe 

cargo doors, as applicable, and 

corrective action if necessary. We are 

proposing this AD to detect and correct 

rotary actuators made with a material 

having poor actuator gear wear 

characteristics, which could result in 

failure of the rotary actuators for the 

large forward or aft lower lobe cargo 

door and subsequent uncommanded 

door closure, which could possibly 

result in injury to people on the ground. 

DATES: We must receive comments on 

this proposed AD by August 14, 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 Boeing 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. For 

Eaton service information identified in 

this proposed AD, contact Eaton 

Corporation, Aerospace Operations, 3 

Park Plaza, Suite 1200, Irvine, CA 

92614; telephone 949–253–2100; fax 

949–253–2111; Internet http://

www.eaton.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– 

0426; 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: 

Susan Monroe, Aerospace Engineer, 

Cabin Safety and Environmental 

Systems Branch, ANM–150S, FAA, 

Seattle Aircraft Certification Office, 

1601 Lind Avenue SW., Renton, WA 

98057–3356; phone: 425–917–6457; fax: 

425–917–6590; email: susan.l.monroe@

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– 

2014–0426; Directorate Identifier 2013– 

NM–231–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 reports of uncommanded 

door closure of the large lower lobe 

cargo door. One incident occurred while 

the door was being opened, a second 

one while the door was stationary in the 

open position, and the third incident 

occurred as the door was being closed. 

It was determined that all of the doors’ 

rotary actuators had failed (two 

actuators per door). The three incidents 

occurred on Model 767 airplanes, but 

the same rotary actuator part numbers 

are also used on the large lower lobe 

cargo doors installed on the Model 777 

airplanes. Examination of five of the 

failed rotary actuators found significant 

wear in the gear box and failure of the 

first stage input sun gear set. The sixth 

failed rotary actuator had a failed thirdstage input sun gear from an overload 

condition. All three affected airplanes 

had between 12,500 and 13,500 total 

flight cycles. The failed actuators were 

manufactured with Nitralloy 135M steel 

between August 1994 and December 

2000. Actuators manufactured before or 

after that timeframe were made with 

9310 steel. The rotary actuators made 

from 9310 steel material are considered 

safe. This condition, if not corrected, 

could result in failure of the rotary 

actuators for the large lower lobe cargo 

door, and subsequent uncommanded 

door closures, which could possibly 

result in injury to people on the ground. 

Relevant Service Information 

We reviewed Boeing Service Bulletins 

767–52A0100, Revision 2, dated 

September 26, 2013; and 777–52–0053, 

Revision 1, dated September 26, 2013. 

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– 

0426. 

Boeing Service Bulletins 767– 

52A0100, Revision 2, dated September 

26, 2013; and 777–52–0053, Revision 1, 

dated September 26, 2013; refer to Eaton 

Service Bulletin 692D100–52–4, 

Revision 2, dated August 1, 2013, which 

provides serial number information and 

certain corrective actions (rework of 

certain rotary actuators or 

reidentification of certain other rotary 

actuators). 

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 


emcdonald on DSK67QTVN1PROD with PROPOSALS