37676 Federal Register / Vol. 79, No. 127 / Wednesday, July 2, 2014 / Proposed Rules 

after operation of the high speed 

warning system by application of a load 

of 1.5g (0.5 acceleration increment), or 

such greater load factor that is 

automatically applied by the system 

with the pilot’s pitch control neutral. 

Power may be reduced simultaneously. 

All other means of decelerating the 

airplane, the use of which is authorized 

up to the highest speed reached in the 

maneuver, may be used. The interval 

between successive pilot actions must 

not be less than one second. 

2. The applicant must also 

demonstrate that the speed margin, 

established as above, will not be 

exceeded in inadvertent or gust-induced 

upsets resulting in initiation of the dive 

from non-symmetric attitudes, unless 

the airplane is protected by the flight 

control laws from getting into nonsymmetric upset conditions. The upset 

maneuvers described in Advisory 

Circular 25–7C, Flight Test Guide for 

Certification of Transport Category 

Airplanes, section 8, paragraph 32, subparagraphs c(3)(a) and (b) may be used 

to comply with this requirement. 

3. The probability of any failure of the 

high speed protection system that 

would result in an airspeed exceeding 

those determined by paragraphs 1 and 2 

must be less than 10¥5 per flight hour. 

4. Failures of the system must be 

annunciated to the pilots. Flight manual 

instructions must be provided that 

reduce the maximum operating speeds, 

VMO/MMO. With the system failed, the 

operating speed must be reduced to a 

value that maintains a speed margin 

between VMO/MMO and VD/MD that is 

consistent with showing compliance 

with § 25.335(b) without the benefit of 

the high speed protection system. 

5. Dispatch of the airplane with the 

high speed protection system 

inoperative could be allowed under an 

approved MEL that would require flight 

manual instructions to indicate reduced 

maximum operating speeds, as 

described in paragraph (4). In addition, 

the cockpit display of the reduced 

operating speeds, as well as the 

overspeed warning for exceeding those 

speeds, must be equivalent to that of the 

normal airplane with the high speed 

protection system operative. Also, it 

must be shown that no additional 

hazards are introduced with the high 

speed protection system inoperative. 

Issued in Renton, Washington, on June 17, 

2014. 

Michael Kaszycki, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2014–15539 Filed 7–1–14; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2014–0344; Directorate 

Identifier 2014–NM–034–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) 2013–24– 

13, which applies to certain The Boeing 

Company Model 737–100, –200, –200C, 

–300, –400, –500, –600, –700, –700C, 

–800, and –900 series airplanes. AD 

2013–24–13 currently requires replacing 

the pivot link assembly for certain 

airplanes, replacing the seat track link 

assemblies or modifying the existing 

seat track link assembly for certain 

airplanes, or modifying the existing seat 

track link assembly fastener for certain 

airplanes. AD 2013–24–13 also requires 

inspecting, changing, or repairing the 

seat track link assembly for certain other 

airplanes. Since we issued AD 2013–24– 

13, a paragraph reference was found to 

be mis-identified. This proposed AD 

would correct this paragraph reference. 

We are proposing this AD to prevent 

seat detachment in an emergency 

landing, which could cause injury to 

occupants of the passenger 

compartment and affect emergency 

egress. 

DATES: We must receive comments on 

this proposed AD by August 18, 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– 

0344; 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: 

Sarah Piccola, Aerospace Engineer, 

Cabin Safety and Environmental 

Systems Branch, ANM–150S, FAA, 

Seattle Aircraft Certification Office, 

1601 Lind Avenue SW., Renton, WA 

98057–3356; phone: 425–917–6483; fax: 

425–917–6590; email: sarah.piccola@

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–2014–0344; Directorate Identifier 

2014–NM–034–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 November 19, 2013, we issued AD 

2013–24–13, Amendment 39–17687 (78 

FR 72558, December 3, 2013), for certain 

The Boeing Company Model 737–100, 

–200, –200C, –300, –400, –500, –600, 

–700, –700C, –800, and –900 series 


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Federal Register / Vol. 79, No. 127 / Wednesday, July 2, 2014 / Proposed Rules 37677 

airplanes. AD 2013–24–13 requires 

replacing the pivot link assembly for 

certain airplanes, replacing the seat 

track link assemblies or modifying the 

existing seat track link assembly for 

certain airplanes, or modifying the 

existing seat track link assembly 

fastener for certain airplanes. AD 2013– 

24–13 also requires inspecting, 

changing, or repairing the seat track link 

assembly for certain other airplanes. AD 

2013–24–13 resulted from a report that 

the seat track attachment of body station 

520 flexible joint is structurally 

deficient in resisting a 9g forward 

emergency load condition in certain 

seating configurations. We issued AD 

2013–24–13 to prevent seat detachment 

in an emergency landing, which could 

cause injury to occupants of the 

passenger compartment and affect 

emergency egress. 

Actions Since AD 2013–24–13, 

Amendment 39–17687 (78 FR 72558, 

December 3, 2013) Was Issued 

Since we issued AD 2013–24–13, 

Amendment 39–17687 (78 FR 72558, 

December 3, 2013), a paragraph 

reference was found to be mis-identified 

in paragraph (i) of that AD. Paragraph (i) 

of AD 2013–24–13 states that before or 

concurrently with the accomplishment 

of the actions specified in paragraph 

(g)(2) or (g)(3) of this AD, install a new 

seat track link assembly. Where 

paragraph (i) of AD 2013–24–13 referred 

to paragraph (g)(3) of that AD, this AD 

refers to paragraph (g)(4) of this AD. 

We have also revised the terminology 

of the Summary and Discussion sections 

of this AD to clarify the actions required 

by this AD. 

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 2013–24–13, 

Amendment 39–17687 (78 FR 72558, 

December 3, 2013). This proposed AD 

would revise the second sentence of 

paragraph (i) of this proposed AD to 

replace the reference to paragraph (g)(3) 

with reference to paragraph (g)(4) of this 

proposed AD. 

Costs of Compliance 

We estimate that this proposed AD 

affects 1,281 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 U.S. airplanes Cost on U.S. operators 

Replacement or modification [retained actions from AD 2013– 

24–13, Amendment 39–17687 

(78 FR 72558, December 3, 

2013)].

Up to 41 work-hours × $85 per 

hour = $3,485.

Up to $15,478 .. Up to $18,963 .. 1,281 Up to $24,291,603. 

Concurrent installation or modification (Groups 1, 2, 4, and 5 

airplanes) [retained actions 

from AD 2013-24-13, Amendment 39–17687 (78 FR 72558, 

December 3, 2013)] 1.

Up to 60 work-hours × $85 per 

hour = $5,100.

Up to $18,089 .. Up to $23,189 .. 214 Up to $4,962,446. 

1We have received no definitive data that would enable us to provide a cost estimate for the actions required for airplanes in Group 6 identified in Boeing Special Attention Service Bulletin 737–53–1260, Revision 1, dated May 23, 2013. 

This new proposed AD adds no new 

costs to affected operators. 

Authority for This Rulemaking 

Title 49 of the United States Code 

specifies the FAA’s authority to issue 

rules on aviation safety. Subtitle I, 

Section 106, describes the authority of 

the FAA Administrator. Subtitle VII, 

Aviation Programs, describes in more 

detail the scope of the Agency’s 

authority. 

We are issuing this rulemaking under 

the authority described in Subtitle VII, 

Part A, Subpart III, Section 44701, 

‘‘General requirements.’’ Under that 

section, Congress charges the FAA with 

promoting safe flight of civil aircraft in 

air commerce by prescribing regulations 

for practices, methods, and procedures 

the Administrator finds necessary for 

safety in air commerce. This regulation 

is within the scope of that authority 

because it addresses an unsafe condition 

that is likely to exist or develop on 

products identified in this rulemaking 

action. 

Regulatory Findings 

We 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. 


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37678 Federal Register / Vol. 79, No. 127 / Wednesday, July 2, 2014 / Proposed Rules 

§ 39.13 [Amended] 

■ 2. The FAA amends § 39.13 by 

removing Airworthiness Directive (AD) 

2013–24–13, Amendment 39–17687 (78 

FR 72558, December 3, 2013), and 

adding the following new AD: 

The Boeing Company: Docket No. FAA– 

2014–0344; Directorate Identifier 2014– 

NM–034–AD. 

(a) Comments Due Date 

The FAA must receive comments on this 

AD action by August 18, 2014. 

(b) Affected ADs 

This AD supersedes AD 2013–24–13, 

Amendment 39–17687 (78 FR 72558, 

December 3, 2013). 

(c) Applicability 

This AD applies to the airplanes identified 

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

certificated in any category. 

(1) The Boeing Company Model 737–100, 

–200, –200C, –300, –400, and –500 series 

airplanes, as identified in Boeing Special 

Attention Service Bulletin 737–53–1260, 

Revision 1, dated May 23, 2013. 

(2) The Boeing Company Model 737–600, 

–700, –700C, –800, and –900 series airplanes, 

as identified in Boeing Service Bulletin 737– 

53–1244, Revision 5, dated July 27, 2011. 

(d) Subject 

Air Transport Association (ATA) of 

America Code 53, Fuselage. 

(e) Unsafe Condition 

This AD was prompted by a report that a 

Boeing study found that the seat track 

attachment of body station 520 flexible joint 

is structurally deficient in resisting a 9g 

forward emergency load condition in certain 

seating configurations. We are issuing this 

AD to prevent seat detachment in an 

emergency landing, which could cause injury 

to occupants of the passenger compartment 

and affect emergency egress. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Retained Repair or Replacement of Seat 

Track Link Assembly or Seat Track Link 

Assembly Fastener, With No Changes 

This paragraph restates the requirements of 

paragraph (g) of AD 2013–24–13, 

Amendment 39–17687 (78 FR 72558, 

December 3, 2013), with no changes. Within 

60 months after January 7, 2014 (the effective 

date of AD 2013–24–13), do the actions 

specified in paragraph (g)(1), (g)(2), (g)(3), or 

(g)(4) of this AD, as applicable. 

(1) For Model 737–600, –700, –700C, –800, 

and –900 series airplanes: Install new, 

improved pivot link assemblies, in 

accordance with the Accomplishment 

Instructions of Boeing Service Bulletin 737– 

53–1244, Revision 5, dated July 27, 2011. 

(2) For airplanes in Groups 1, 2, 3, and 4, 

as identified in Boeing Special Attention 

Service Bulletin 737–53–1260, Revision 1, 

dated May 23, 2013: Replace the seat track 

link assembly, in accordance with the 

Accomplishment Instructions of Boeing 

Special Attention Service Bulletin 737–53– 

1260, Revision 1, dated May 23, 2013. 

(3) For airplanes in Group 6, as identified 

in Boeing Special Attention Service Bulletin 

737–53–1260, Revision 1, dated May 23, 

2013: Inspect, change, or repair the seat track 

link assembly, as applicable, using a method 

approved in accordance with the procedures 

specified in paragraph (k) of this AD. 

(4) For airplanes in Group 5, as identified 

in Boeing Special Attention Service Bulletin 

737–53–1260, Revision 1, dated May 23, 

2013: Modify the existing seat track link 

assembly fastener, in accordance with the 

Accomplishment Instructions of Boeing 

Special Attention Service Bulletin 737–53– 

1260, Revision 1, dated May 23, 2013. 

(h) Retained Optional Modification of Seat 

Track Link Assembly, With No Changes 

This paragraph restates the provisions of 

paragraph (h) of AD 2013–24–13, 

Amendment 39–17687 (78 FR 72558, 

December 3, 2013), with no changes. In lieu 

of the replacement specified in paragraph 

(g)(2) of this AD, doing the optional 

modification of the seat track link assembly, 

in accordance with the Accomplishment 

Instructions of Boeing Special Attention 

Service Bulletin 737–53–1260, Revision 1, 

dated May 23, 2013, is acceptable for 

compliance with the requirements of 

paragraph (g)(2) of this AD, provided the 

modification is done within the compliance 

time specified in the introductory text of 

paragraph (g) of this AD. 

(i) Retained Concurrent Actions, With New 

Concurrent Action for Group 5 Airplanes 

This paragraph restates the requirements of 

paragraph (i) of AD 2013–24–13, Amendment 

39–17687 (78 FR 72558, December 3, 2013), 

with a corrected paragraph reference that 

results in a new concurrent action for Group 

5 airplanes. For airplanes in Groups 1, 2, 4, 

and 5, as identified in Boeing Special 

Attention Service Bulletin 737–53–1260, 

Revision 1, dated May 23, 2013: Before or 

concurrently with the accomplishment of the 

actions specified in paragraph (g)(2) or (g)(4) 

of this AD, install a new seat track link 

assembly or modify the seat track link 

assembly, as applicable, in accordance with 

the Accomplishment Instructions of Boeing 

Service Bulletin 737–53–1120, Revision 1, 

dated May 13, 1993. 

(j) Retained Credit for Previous Actions With 

No Changes 

This paragraph restates the credit specified 

in paragraph (j) of AD 2013–24–13, 

Amendment 39–17687 (78 FR 72558, 

December 3, 2013), with no changes. 

(1) This paragraph provides credit for the 

actions required by paragraph (g)(1) of this 

AD, if those actions were performed before 

January 7, 2014 (the effective date of AD 

2013–24–13, Amendment 39–17687 (78 FR 

72558, December 3, 2013)), using Boeing 

Service Bulletin 737–53–1244, dated April 

17, 2003; Revision 1, dated May 29, 2003; 

Revision 2, dated March 15, 2007; or 

Revision 3, dated December 4, 2008; which 

are not incorporated by reference in this AD. 

(2) This paragraph provides credit for the 

actions required by paragraphs (g)(2) and 

(g)(4) of this AD, if those actions were 

performed before January 7, 2014 (the 

effective date of AD 2013–24–13, 

Amendment 39–17687 (78 FR 72558, 

December 3, 2013)), using Boeing Special 

Attention Service Bulletin 737–53–1260, 

dated May 7, 2007, which is not incorporated 

by reference in this AD. 

(k) Alternative Methods of Compliance 

(AMOCs) 

(1) The Manager, Seattle Aircraft 

Certification Office (ACO), FAA, has the 

authority to approve AMOCs for this AD, if 

requested using the procedures found in 14 

CFR 39.19. In accordance with 14 CFR 39.19, 

send your request to your principal inspector 

or local Flight Standards District Office, as 

appropriate. If sending information directly 

to the manager of the ACO, send it to the 

attention of the person identified in 

paragraph (l) 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 14 

CFR 25.571, Amendment 45, and the 

approval must specifically refer to this AD. 

(l) Related Information 

(1) For more information about this AD, 

contact Sarah Piccola, 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– 

6483; fax: 425–917–6590; email: 

sarah.piccola@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 18, 

2014. 

Michael Kaszycki, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2014–14799 Filed 7–1–14; 8:45 am] 

BILLING CODE 4910–13–P 


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