36672 Federal Register / Vol. 79, No. 125 / Monday, June 30, 2014 / Proposed Rules 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2014–0346; Directorate 

Identifier 2014–NM–010–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 737–100, 

–200, –200C, –300, –400, and –500 

series airplanes. This proposed AD was 

prompted by reports of cracks in 

fuselage frames, and a report of a 

missing strap that was not installed on 

a fuselage frame during production. 

This proposed AD would require an 

inspection to determine if the strap 

adjacent to a certain stringer is installed, 

and repair if missing; repetitive 

inspections of the frame for cracking or 

a severed frame web; and related 

investigative and corrective actions if 

necessary. This proposed AD also 

provides optional actions to terminate 

certain repetitive inspections. We are 

proposing this AD to detect and correct 

missing fuselage frame straps and frame 

cracking that can result in severed 

frames. Continued operation of the 

airplane with multiple adjacent severed 

frames, or the combination of a severed 

frame and fuselage skin chemical mill 

cracks, can result in uncontrolled 

decompression of the airplane. 

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 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. 

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– 

0346; 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: 

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. 

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– 

2014–0346; Directorate Identifier 2014– 

NM–010–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 reports of fuselage 

frame cracking, and a report of a missing 

strap that was not installed on a fuselage 

frame during production. One report 

was a crack in the frame at station 328 

and a crack that severed the frame at 

station 360 on the right side of an 

airplane that had 59,756 total flight 

cycles. The frame web and the failsafe 

chord were completely severed. 

We have received ten reports of cracks 

in the frames at station 328 between 

stringers S–20R and S–21R on Model 

737–200, 737–300, and 737–500 series 

airplanes that had accumulated between 

43,581 and 73,655 total flight cycles. 

These cracks were in the frame web at 

an open tool hole, in the frame web at 

the end fastener in the inner chord, and 

in the frame web notch. The cracks were 

from 0.3 inch to 3.0 inches long. 

We have also received 14 reports of 

cracks in the frames at station 360 

between stringers S–19R and S–21R on 

Model 737–200 and 737–300 series 

airplanes that had accumulated between 

42,183 and 66,588 total flight cycles. 

These cracks were in the frame web at 

an open tool hole, in the frame web at 

an insulation blanket stud hole, in the 

frame web at an end fastener in the 

doubler, and in the inner flange at the 

end fastener in the doubler. The cracks 

were from 2.5 inches long to cracks that 

severed the frame web and fail-safe 

chord. 

We have received a report of three 

cracks in the frame at station 380 

between stringers S–18R and S–20R on 

a Model 737–300 series airplane with 

32,218 total flight cycles. Cracks were in 

the frame inner flange at fasteners 

common to the bulkhead support angle. 

One of the three cracks was also in the 

doubler. 

We have received a report of a strap 

that was not installed on the frame at 

station 312 adjacent to stringer S–22R 

on a Model 737–400 series airplane with 

24,037 total flight cycles. Investigation 

of the drawings determined that this 

was an incorrect frame configuration 

and that the strap should have been 

installed. 

Missing fuselage frame straps and 

frame cracking can result in severed 

frames. Continued operation of the 

airplane with multiple adjacent severed 

frames, or the combination of a severed 

frame and fuselage skin chemical mill 

cracks, can result in uncontrolled 

decompression of the airplane. 

Relevant Service Information 

We reviewed Boeing Alert Service 

Bulletin 737–53A1323, dated December 

6, 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– 

0346. 


emcdonald on DSK67QTVN1PROD with PROPOSALS
Federal Register / Vol. 79, No. 125 / Monday, June 30, 2014 / Proposed Rules 36673 

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 an 

inspection to determine if the strap 

adjacent to a certain stringer is installed, 

and repair if missing; repetitive 

inspections of the frame for cracking or 

a severed frame web; and related 

investigative and corrective actions if 

necessary. This proposed AD also 

provides optional actions to terminate 

the repetitive inspections. 

The phrase ‘‘related investigative 

actions’’ is used in this proposed AD. 

‘‘Related investigative actions’’ are 

follow-on actions that (1) are related to 

the primary actions, and (2) further 

investigate the nature of any condition 

found. Related investigative actions in 

an AD could include, for example, 

inspections. 

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. 

Differences Between This Proposed AD 

and the Service Information 

Boeing Alert Service Bulletin 737– 

53A1323, dated December 6, 2013, 

specifies to contact the manufacturer for 

instructions on how to repair certain 

conditions, but this proposed AD would 

require repairing those conditions in 

one of the following ways: 

• In accordance with a method that 

we approve; or 

• Using data that meet the 

certification basis of the airplane, and 

that have been approved by the Boeing 

Commercial Airplanes Organization 

Designation Authorization (ODA) whom 

we have authorized to make those 

findings. 

Tables 13 through 15 in paragraph 

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

Service Bulletin 737–53A1323, dated 

December 6, 2013, specify postmodification inspections at certain 

locations, which 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 129.109(b)(2)). 

However, this NPRM does not propose 

to require those post-modification 

inspections. This difference has been 

coordinated with Boeing. 

Costs of Compliance 

We estimate that this proposed AD 

affects 417 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 .................... 21 work-hours × $85 per hour = $1,785 per inspection cycle.$0 $1,785 per inspection 

cycle.

$744,345 per inspection 

cycle. 

We have received no definitive data 

that would enable us to provide cost 

estimates for certain on-condition 

actions specified in this proposed AD. 

However, we estimate the following 

costs to do any necessary repairs of the 

station 328 frame and the station 360 

frame. We have no way of determining 

the number of aircraft that might need 

these repairs: 

ON-CONDITION COSTS

Action Labor cost Parts cost Cost per 

product 

Frame 328 repair ............................... 25 work-hours × $85 per hour = $2,125 ...................................................... Negligible ... $2,125 

Frame 360 repair ............................... 5 work-hours × $85 per hour = $425 ........................................................... Negligible ... 425 

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, 


emcdonald on DSK67QTVN1PROD with PROPOSALS
36674 Federal Register / Vol. 79, No. 125 / Monday, June 30, 2014 / Proposed Rules 

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– 

2014–0346; Directorate Identifier 2014– 

NM–010–AD. 

(a) Comments Due Date 

We must receive comments by August 14, 

2014. 

(b) Affected ADs 

None. 

(c) Applicability 

This AD applies to The Boeing Company 

Model 737–100, –200, –200C, –300, –400, 

and –500 series airplanes, certificated in any 

category, as identified in Boeing Alert 

Service Bulletin 737–53A1323, dated 

December 6, 2013. 

(d) Subject 

Air Transport Association (ATA) of 

America Code 53, Fuselage. 

(e) Unsafe Condition 

This AD was prompted by reports of cracks 

in fuselage frames, and a report of a missing 

strap that was not installed on a fuselage 

frame during production. We are issuing this 

AD to detect and correct missing fuselage 

frame straps and frame cracking that can 

result in severed frames. Continued operation 

of the airplane with multiple adjacent 

severed frames, or the combination of a 

severed frame and fuselage skin chemical 

mill cracks, can result in uncontrolled 

decompression of the airplane. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Group 1 Airplane Actions 

For airplanes identified as Group 1 in 

Boeing Alert Service Bulletin 737–53A1323, 

dated December 6, 2013: At the applicable 

time specified in Table 1 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 the repair using a method 

approved in accordance with the procedures 

specified in paragraph (o) of this AD. 

(h) Groups 2 Through 7 Airplanes: 

Inspection for Strap Installation at Station 

312 

For airplanes identified as Groups 2 

through 7 in Boeing Alert Service Bulletin 

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

the applicable time specified in Tables 2 and 

3 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 general 

visual inspection of the frame at station 312 

to determine if the strap adjacent to stringer 

S–22R is installed, in accordance with the 

Accomplishment Instructions of Boeing Alert 

Service Bulletin 737–53A1323, dated 

December 6, 2013. If the strap is not 

installed, before further flight, repair using a 

method approved in accordance with the 

procedures specified in paragraph (o) of this 

AD. 

(i) Groups 2 Through 6 Airplanes With Less 

Than 28,300 Total Flight Cycles: Repetitive 

Inspections, Related Investigative Actions, 

and Corrective Actions at Stations 328, 344, 

and 360 

For airplanes identified as Groups 2 

through 6 in Boeing Alert Service Bulletin 

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

have accumulated less than 28,300 total 

flight cycles as of the effective date of this 

AD: Do the actions required by paragraphs 

(i)(1) and (i)(2) of this AD. 

(1) At the applicable times specified in 

Tables 4, 5, 7, and 8 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 stations 328, 344, 

and 360 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 applicable 

inspections thereafter at the applicable time 

and intervals specified in Paragraph 1.E., 

‘‘Compliance,’’ of Boeing Alert Service 

Bulletin 737–53A1323, dated December 6, 

2013, until the inspection required by 

paragraph (i)(2) of this AD is done. Doing the 

preventative modification of the frame at 

station 360 and the repair of the frame at 

station 328, as applicable, 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 

applicable repetitive inspection requirements 

of paragraph (i)(1) of this AD. 

(2) At the applicable time specified in 

Tables 4, 5, 7, and 8 of paragraph 1.E., 

‘‘Compliance,’’ of Boeing Alert Service 

Bulletin 737–53A1323, dated December 6, 

2013, do the actions specified in paragraph 

(i)(2)(i) or (i)(2)(ii) of this AD. Accomplishing 

the initial inspections required by paragraph 

(i)(2) of this AD terminates the inspections 

required by paragraph (i)(1) of this AD. Doing 

the preventative modification of the frame at 

station 360 and the repair of the frame at 

station 328, as applicable, 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 

applicable repetitive inspection requirements 

of paragraph (i)(2)(i) and (i)(2)(ii) of this AD. 

(i) Do detailed and eddy current 

inspections of the frame at stations 328, 344, 

and 360 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. 

(ii) 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; 

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 applicable 

inspections thereafter at the applicable time 

and intervals specified in Paragraph 1.E., 

‘‘Compliance,’’ of Boeing Alert Service 

Bulletin 737–53A1323, dated December 6, 

2013. 

(j) Groups 2 Through 6 Airplanes With 

28,300 Total Flight Cycles or More: 

Repetitive Inspections, Related Investigative 

Actions, and Corrective Actions at Stations 

328, 344, and 360 

For airplanes identified as Groups 2 

through 6 in Boeing Alert Service Bulletin 

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

have accumulated 28,300 total flight cycles 

or more as of the effective date of this AD: 

At the applicable times specified in Tables 4, 

5, 7, and 8 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 

the inspections specified in paragraphs (j)(1) 

or (j)(2) of this AD; 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 applicable inspections specified 

in paragraphs (j)(1) or (j)(2) of this AD 

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 

preventative modification of the frame at 

station 360 and the repair of the frame at 

station 328, as applicable, 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 

applicable repetitive inspection requirements 

of this paragraph. 

(1) Do detailed and eddy current 

inspections of the frame at stations 328, 344, 

and 360 for cracking or a severed frame web. 


emcdonald on DSK67QTVN1PROD with PROPOSALS
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 


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