Federal Register / Vol. 82, No. 156 / Tuesday, August 15, 2017 / Proposed Rules 38621 

(c) Applicability 

This AD applies to Airbus Model A320– 

211, –212, –214, and –231 airplanes, 

certificated in any category, manufacturer 

serial numbers up through 0104 inclusive. 

(d) Subject 

Air Transport Association (ATA) of 

America Code 57, Wings. 

(e) Reason 

This proposed AD is intended to complete 

certain mandated programs intended to 

support the airplane reaching its limit of 

validity (LOV) of the engineering data that 

support the established structural 

maintenance program. We are proposing this 

AD to prevent fatigue cracking in the 

pressurized floor fittings at frame 36, which 

could result in the reduced structural 

integrity of the floor fittings and subsequent 

depressurization of the fuselage. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Inspection 

(1) At the latest of the times specified in 

paragraphs (g)(1)(i), (g)(1)(ii), and (g)(1)(iii) of 

this AD: Do a detailed inspection of the 

pressurized floor fittings at FR 36, in 

accordance with the Accomplishment 

Instructions of Airbus Service Bulletin A320– 

57–1028, Revision 02, dated June 3, 2013. 

Repeat the inspection thereafter at intervals 

not to exceed 9,300 flight cycles or 18,600 

flight hours, whichever occurs first. 

(i) Before exceeding 20,900 flight cycles or 

41,800 flight hours, whichever occurs first 

since first flight of the airplane. 

(ii) Within 9,300 flight cycles or 18,600 

flight cycles since the most recent inspection 

accomplished in accordance with the 

Accomplishment Instructions of Airbus 

Service Bulletin A320–57–1028, Revision 02, 

dated June 3, 2013. 

(iii) Within 1,250 flight cycles or 2,500 

flight hours after March 3, 2016 (the effective 

date of AD 2016–02–01), without exceeding 

12,000 flight cycles since the most recent 

inspection accomplished in accordance with 

the Accomplishment Instructions of Airbus 

Service Bulletin A320–57–1028, Revision 02, 

dated June 3, 2013. 

(2) If any crack is found during any 

inspection required by paragraph (g)(1) of 

this AD: Before further flight, repair using a 

method approved by the Manager, 

International Section, Transport Standards 

Branch, FAA; or the European Aviation 

Safety Agency (EASA); or Airbus’s EASA 

Design Organization Approval (DOA). 

(h) Modification 

Before exceeding 48,000 total flight cycles 

or 96,000 total flight hours, whichever occurs 

first since first flight of the airplane: Modify 

(replace aluminum fittings with titanium 

fittings) the pressurized floor fittings at FR 

36, in accordance with the Accomplishment 

Instructions of Airbus Service Bulletin A320– 

57–1029, Revision 02, dated June 16, 1999. 

Accomplishment of this modification is 

terminating action for the repetitive 

inspections required by paragraph (g) of this 

AD for the modified airplane only. 

(i) Credit for Previous Actions 

(1) This paragraph provides credit for the 

inspection required by paragraph (g) of this 

AD, if that inspection was performed before 

the effective date of this AD using Airbus 

Service Bulletin A320–57–1028, dated 

August 12, 1991; or Revision 01, dated June 

3, 2013. 

(2) This paragraph provides credit for the 

modification required by paragraph (h) of 

this AD, if that modification was performed 

before the effective date of this AD using 

Airbus Service Bulletin A320–57–1029, 

dated August 12, 1991; or Revision 01, dated 

November 10, 1992. 

(j) Other FAA AD Provisions 

The following provisions also apply to this 

AD: 

(1) Alternative Methods of Compliance 

(AMOCs): The Manager, International 

Section, Transport Standards Staff, 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 International Section, send it to the 

attention of the person identified in 

paragraph (k)(2) of this AD. Information may 

be emailed to 9-ANM-116-AMOCREQUESTS@faa.gov. 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. 

(2) Contacting the Manufacturer: As of the 

effective date of this AD, for any requirement 

in this AD to obtain corrective actions from 

a manufacturer, the action must be 

accomplished using a method approved by 

the Manager, International Section, Transport 

Standards Branch, FAA; or the EASA; or 

Airbus’s DOA. If approved by the DOA, the 

approval must include the DOA-authorized 

signature. 

(k) Related Information 

(1) Refer to Mandatory Continuing 

Airworthiness Information (MCAI) EASA AD 

2016–0181, dated September 13, 2016, for 

related information. This MCAI may be 

found in the AD docket on the Internet at 

http://www.regulations.gov by searching for 

and locating Docket No. FAA–2017–0716. 

(2) For more information about this AD, 

contact Sanjay Ralhan, Aerospace Engineer, 

International Section, Transport Standards 

Branch, FAA, 1601 Lind Avenue SW., 

Renton, WA 98057–3356; telephone 425– 

227–1405; fax 425–227–1149. 

(3) For service information identified in 

this AD, contact Airbus, Airworthiness 

Office—EIAS, 1 Rond Point Maurice 

Bellonte, 31707 Blagnac Cedex, France; 

telephone +33 5 61 93 36 96; fax +33 5 61 

93 44 51; email account.airworth-eas@

airbus.com; Internet http://www.airbus.com. 

You may view this referenced service 

information at the FAA, Transport Standards 

Branch, 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 July 28, 

2017. 

John P. Piccola, Jr., 

Acting Director, System Oversight Division, 

Aircraft Certification Service. 

[FR Doc. 2017–16569 Filed 8–14–17; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2017–0777; Product 

Identifier 2017–NM–050–AD] 

RIN 2120–AA64 

Airworthiness Directives; Saab AB, 

Saab Aeronautics (Formerly Known as 

Saab AB, Saab Aerosystems) 

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 

Saab AB, Saab Aeronautics Model 

SAAB 340B airplanes. This proposed 

AD was prompted by reports of natural 

stall events in icing conditions, without 

prior stall warnings. This proposed AD 

would require modifying the stall 

warning system, installing new stall 

warning computers, and activating the 

stall warning system. We are proposing 

this AD to address the unsafe condition 

on these products. 

DATES: We must receive comments on 

this proposed AD by September 29, 

2017. 

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 Saab AB, Saab 

Aeronautics, SE–581 88, Linko ̈ping, 

Sweden; telephone +46 13 18 5591; fax 

+46 13 18 4874; email 

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38622 Federal Register / Vol. 82, No. 156 / Tuesday, August 15, 2017 / Proposed Rules 

saab340techsupport@saabgroup.com; 

Internet http://www.saabgroup.com. 

You may view this service information 

at the FAA, Transport Standards 

Branch, 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–2017– 

0777; 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 NPRM, the regulatory 

evaluation, any comments received, and 

other information. The street address for 

the Docket Operations office (telephone 

800–647–5527) is in the ADDRESSES

section. Comments will be available in 

the AD docket shortly after receipt. 

FOR FURTHER INFORMATION CONTACT: 

Shahram Daneshmandi, Aerospace 

Engineer, International Section, 

Transport Standards Branch, FAA, 1601 

Lind Avenue SW., Renton, WA 98057– 

3356; telephone: 425–227–1112; fax: 

425–227–1149. 

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– 

2017–0777; Product Identifier 2017– 

NM–050–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 based 

on 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 NPRM. 

Discussion 

The European Aviation Safety Agency 

(EASA), which is the Technical Agent 

for the Member States of the European 

Union, has issued EASA Airworthiness 

Directive 2017–0067, dated April 24, 

2017 (referred to after this as the 

Mandatory Continuing Airworthiness 

Information, or ‘‘the MCAI’’), to correct 

an unsafe condition for certain Saab AB, 

Saab Aeronautics Model SAAB 340B 

airplanes. The MCAI states: 

A few natural stall events, specifically 

when operating in icing conditions, have 

been experienced on SAAB 340 series 

aeroplanes, without receiving a prior stall 

warning. 

This condition, if not corrected, could 

result in loss of control of the aeroplane. 

To address this potential unsafe condition, 

SAAB developed a modified stall warning 

system, incorporating improved stall warning 

logic, and issued various Service Bulletins 

(SB) providing instructions to replace the 

Stall Warning Computer (SWC) with a new 

SWC, and instructions to activate the new 

SWC. The new system includes stall warning 

curves optimized for operation in icing 

conditions, which are activated by selection 

of Engine Anti-Ice. 

Consequently, EASA issued AD 2014–0218 

[which corresponds to FAA AD 2016–22–15, 

Amendment 39–18704 (81 FR 76843, 

November 4, 2016)] to require installation 

and activation of the improved SWC. That 

[EASA] AD excluded certain SAAB 340B 

aeroplanes by s/n. 

Since EASA AD 2014–0218 was issued, 

SAAB developed a technical solution 

applicable for some of those previously 

excluded aeroplanes, and issued SB 340–27– 

117 and SB 340–27–118, providing 

instructions to modify and activate the new 

SWC. 

For the reasons described above, this 

[EASA] AD requires installation and 

activation of the improved SWC. 

You may examine the MCAI in the 

AD docket on the Internet at http://

www.regulations.gov by searching for 

and locating Docket No. FAA–2017– 

0777. 

Related Service Information Under 1 

CFR Part 51 

Saab AB, Saab Aeronautics has issued 

Service Bulletin 340–27–117, dated 

January 23, 2017. The service 

information describes procedures for 

modifying the stall warning system. 

Saab AB, Saab Aeronautics has also 

issued Service Bulletin 340–27–118, 

dated January 23, 2017. The service 

information describes procedures for 

installing new stall warning computers 

and activating the modified stall 

warning system. 

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 This 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 the State of 

Design Authority, we have been notified 

of the unsafe condition described in the 

MCAI and service information 

referenced above. We are proposing this 

AD because we evaluated all pertinent 

information and determined an unsafe 

condition exists and is likely to exist or 

develop on other products of the same 

type design. 

Costs of Compliance 

We estimate that this proposed AD 

affects 4 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 

Modification, installation, and activation ......... 78 work-hours × $85 per hour = $6,630 ........ $33,000 $39,630 $158,520 

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 proposed AD is issued in 

accordance with authority delegated by 

the Executive Director, Aircraft 

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Federal Register / Vol. 82, No. 156 / Tuesday, August 15, 2017 / Proposed Rules 38623 

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 transport 

category airplanes to the Director of the 

System Oversight 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): 

Saab AB, Saab Aeronautics (Formerly 

Known as Saab AB, Saab Aerosystems): 

Docket No. FAA–2017–0777; Product 

Identifier 2017–NM–050–AD. 

(a) Comments Due Date 

We must receive comments by September 

29, 2017. 

(b) Affected ADs 

None. 

(c) Applicability 

This AD applies to Saab AB, Saab 

Aeronautics (formerly known as Saab AB, 

Saab Aerosystems) Model SAAB 340B 

airplanes, certificated in any category, serial 

numbers 362, 363, 385, and 405. 

(d) Subject 

Air Transport Association (ATA) of 

America Code 27, Flight Controls. 

(e) Reason 

This AD was prompted by reports of 

natural stall events in icing conditions, 

without prior stall warnings. We are issuing 

this AD to prevent a natural stall event in 

icing conditions without any stall warning, 

which could result in loss of control of the 

airplane. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Modification 

Within 12 months after the effective date 

of this AD, do the actions specified in 

paragraphs (g)(1) and (g)(2) of this AD. 

(1) Install a provision for a modified stall 

warning system, in accordance with the 

Accomplishment Instructions of Saab Service 

Bulletin 340–27–117, dated January 23, 2017. 

(2) Install new stall warning computers and 

activate the modified stall warning system, in 

accordance with the Accomplishment 

Instructions of Saab Service Bulletin 340–27– 

118, dated January 23, 2017. 

(h) Parts Installation Prohibition 

After modification of an airplane as 

required by paragraph (g) of this AD, no 

person may install a stall warning computer 

having part number (P/N) 20AK5 or P/N 

0020AK5 on that airplane. 

(i) Other FAA AD Provisions 

The following provisions also apply to this 

AD: 

(1) Alternative Methods of Compliance 

(AMOCs): The Manager, International 

Section, Transport Standards 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 International Section, send it 

to the attention of the person identified in 

paragraph (j)(2) of this AD. Information may 

be emailed to: 9-ANM-116-AMOCREQUESTS@faa.gov. 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. 

(2) Contacting the Manufacturer: For any 

requirement in this AD to obtain corrective 

actions from a manufacturer, the action must 

be accomplished using a method approved 

by the Manager, International Section, 

Transport Standards Branch, FAA; or the 

European Aviation Safety Agency (EASA); or 

Saab AB, Saab Aeronautics’s EASA Design 

Organization Approval (DOA). If approved by 

the DOA, the approval must include the 

DOA-authorized signature. 

(j) Related Information 

(1) Refer to Mandatory Continuing 

Airworthiness Information (MCAI) EASA 

Airworthiness Directive 2017–0067, dated 

April 24, 2017, for related information. This 

MCAI may be found in the AD docket on the 

Internet at http://www.regulations.gov by 

searching for and locating Docket No. FAA– 

2017–0777. 

(2) For more information about this AD, 

contact Shahram Daneshmandi, Aerospace 

Engineer, International Section, Transport 

Standards Branch, FAA, 1601 Lind Avenue 

SW., Renton, WA 98057–3356; telephone: 

425–227–1112; fax: 425–227–1149. 

(3) For service information identified in 

this AD, contact Saab AB, Saab Aeronautics, 

SE–581 88, Linko ̈ping, Sweden; telephone 

+46 13 18 5591; fax +46 13 18 4874; email 

saab340.techsupport@saabgroup.com; 

Internet http://www.saabgroup.com. You 

may view this service information at the 

FAA, Transport Standards Branch, 1601 Lind 

Avenue SW., Renton, WA. For information 

on the availability of this material at the 

FAA, call 425–227–1221. 

Issued in Renton, Washington, on August 

3, 2017. 

Jeffrey E. Duven, 

Director, System Oversight Division, Aircraft 

Certification Service. 

[FR Doc. 2017–17095 Filed 8–14–17; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2017–0776; Product 

Identifier 2017–NM–062–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 737–200, 

–300, –400, and –500 series airplanes. 

This proposed AD was prompted by 

reports of cracks in the frame web 

adjacent to the air-conditioning support 

brackets. This proposed AD would 

require an inspection for any air 

conditioning bracket assembly or 

intercostal, and depending on the 

results, repetitive inspections for 

cracking of certain locations and 

applicable on-condition actions. We are 

proposing this AD to address the unsafe 

condition on these products. 

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