Federal Register / Vol. 83, No. 175 / Monday, September 10, 2018 / Rules and Regulations 45545 

(2) Modification of all affected slat tracks 

on an airplane in accordance with the 

Accomplishment Instructions of Airbus 

Service Bulletin A330–57–3126, including 

Appendixes 02 and 03, dated December 21, 

2017; or Airbus Service Bulletin A340–57– 

4133, including Appendixes 02 and 03, dated 

December 21, 2017; as applicable, terminates 

the repetitive inspections required by 

paragraph (h) of this AD for that airplane, 

provided that, prior to modification, the 

affected slat tracks pass an inspection (crack 

free) in accordance with the instructions of 

Airbus Service Bulletin A330–57–3123, 

Revision 01, including Appendixes 02 and 

03, dated September 27, 2017; or Airbus 

Service Bulletin A340–57–4130, Revision 01, 

including Appendixes 02 and 03, dated 

September 27, 2017; as applicable. 

(l) Parts Installation Limitations 

(1) Except as specified in paragraph (l)(2) 

of this AD: For Group 1 airplanes, after the 

effective date of this AD, an affected slat 

track may be installed, provided the 

installation is accomplished using a method 

approved by the Manager, International 

Section, Transport Standards Branch, FAA; 

or EASA; or Airbus SAS’s EASA DOA. If 

approved by the DOA, the approval must 

include the DOA-authorized signature. 

(2) After modification of a Group 1 airplane 

as specified in paragraph (k)(2) of this AD, no 

person may install an affected slat track on 

that airplane. 

(3) For Group 2 airplanes: As of the 

effective date of this AD, no person may 

install an affected slat track on any Group 2 

airplane. 

(m) Credit for Previous Actions 

This paragraph provides credit for actions 

required by paragraphs (h), (i), and (j) of this 

AD, if those actions were performed before 

the effective date of this AD using Airbus 

Service Bulletin A330–57–3123, dated June 

14, 2016; or Airbus Service Bulletin A340– 

57–4130, dated June 14, 2016, provided that 

within 12 months after the effective date of 

this AD, the additional work identified in 

Airbus Service Bulletin A330–57–3123, 

Revision 01, including Appendixes 02 and 

03, dated September 27, 2017; or Airbus 

Service Bulletin A340–57–4130, Revision 01, 

including Appendixes 02 and 03, dated 

September 27, 2017; as applicable, has been 

completed in accordance with Airbus Service 

Bulletin A330–57–3123, Revision 01, 

including Appendixes 02 and 03, dated 

September 27, 2017; or Airbus Service 

Bulletin A340–57–4130, Revision 01, 

including Appendixes 02 and 03, dated 

September 27, 2017; as applicable. 

(n) 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 Branch, send it 

to the attention of the person identified in 

paragraph (o)(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 EASA; 

or Airbus SAS’s EASA DOA. If approved by 

the DOA, the approval must include the 

DOA-authorized signature. 

(3) Reporting Requirements: A federal 

agency may not conduct or sponsor, and a 

person is not required to respond to, nor 

shall a person be subject to a penalty for 

failure to comply with a collection of 

information subject to the requirements of 

the Paperwork Reduction Act unless that 

collection of information displays a current 

valid OMB Control Number. The OMB 

Control Number for this information 

collection is 2120–0056. Public reporting for 

this collection of information is estimated to 

be approximately 1 work-hour per response, 

including the time for reviewing instructions, 

completing and reviewing the collection of 

information. All responses to this collection 

of information are mandatory. Comments 

concerning the accuracy of this burden and 

suggestions for reducing the burden should 

be directed to the FAA at: 800 Independence 

Ave. SW, Washington, DC 20591, Attn: 

Information Collection Clearance Officer, 

AES–200. 

(4) Required for Compliance (RC): Except 

as required by paragraph (i) of this AD: If any 

service information contains procedures or 

tests that are identified as RC, those 

procedures and tests must be done to comply 

with this AD; any procedures or tests that are 

not identified as RC are recommended. Those 

procedures and tests that are not identified 

as RC may be deviated from using accepted 

methods in accordance with the operator’s 

maintenance or inspection program without 

obtaining approval of an AMOC, provided 

the procedures and tests identified as RC can 

be done and the airplane can be put back in 

an airworthy condition. Any substitutions or 

changes to procedures or tests identified as 

RC require approval of an AMOC. 

(o) Related Information 

(1) Refer to Mandatory Continuing 

Airworthiness Information (MCAI) EASA AD 

2017–0060, dated April 7, 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–2018–0454. 

(2) For more information about this AD, 

contact Vladimir Ulyanov, Aerospace 

Engineer, International Section, Transport 

Standards Branch, FAA, 2200 South 216th 

St., Des Moines, WA 98198; phone and fax 

206 231 3229. 

(3) Service information identified in this 

AD that is not incorporated by reference is 

available at the addresses specified in 

paragraphs (p)(3) and (p)(4) of this AD. 

(p) Material Incorporated by Reference 

(1) The Director of the Federal Register 

approved the incorporation by reference 

(IBR) of the service information listed in this 

paragraph under 5 U.S.C. 552(a) and 1 CFR 

part 51. 

(2) You must use this service information 

as applicable to do the actions required by 

this AD, unless this AD specifies otherwise. 

(i) Airbus Service Bulletin A330–57–3123, 

Revision 01, dated September 27, 2017. 

(ii) Airbus Service Bulletin A330–57–3126, 

dated December 21, 2017. 

(iii) Airbus Service Bulletin A340–57– 

4130, Revision 01, dated September 27, 2017. 

(iv) Airbus Service Bulletin A340–57– 

4133, dated December 21, 2017. 

(3) For service information identified in 

this AD, contact Airbus SAS, Airworthiness 

Office—EAL, Rond-Point Emile Dewoitine 

No: 2, 31700Blagnac Cedex, France; phone: 

+33 5 61 93 36 96; fax: +33 5 61 93 45 80; 

email: airworthiness.A330-A340@airbus.com; 

internet http://www.airbus.com. 

(4) You may view this service information 

at the FAA, Transport Standards Branch, 

2200 South 216th St., Des Moines, WA. For 

information on the availability of this 

material at the FAA, call 206–231–3195. 

(5) You may view this service information 

that is incorporated by reference at the 

National Archives and Records 

Administration (NARA). For information on 

the availability of this material at NARA, call 

202–741–6030, or go to: http://

www.archives.gov/federal-register/cfr/ibrlocations.html. 

Issued in Des Moines, Washington, on 

August 22, 2018. 

James Cashdollar, 

Acting Director, System Oversight Division, 

Aircraft Certification Service. 

[FR Doc. 2018–18907 Filed 9–7–18; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2018–0613; Product 

Identifier 2018–SW–041–AD; Amendment 

39–19391; AD 2018–18–12] 

RIN 2120–AA64 

Airworthiness Directives; Airbus 

Helicopters 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule; request for 

comments. 

SUMMARY: We are adopting a new 

airworthiness directive (AD) for Airbus 

Helicopters Model AS350B, AS350B1, 

AS350B2, AS350B3, and AS350BA 

helicopters with a Pall Aerospace 

Corporation inlet barrier filter (IBF) 

element. This AD requires revising the 

Rotorcraft Flight Manual Supplement to 


daltland on DSKBBV9HB2PROD with RULES
45546 Federal Register / Vol. 83, No. 175 / Monday, September 10, 2018 / Rules and Regulations 

1SAIB SW–17–30, dated October 13, 2017, may 

be viewed online at http://rgl/faa/gov. 

prohibit operating a helicopter with an 

IBF element in wet weather and 

replacing the IBF element if wet. This 

AD is prompted by a forced landing 

after an engine flameout. The actions of 

this AD are intended to address an 

unsafe condition on these products. 

DATES: This AD becomes effective 

September 25, 2018. 

We must receive comments on this 

AD by November 9, 2018. 

ADDRESSES: You may send comments by 

any of the following methods: 

• Federal eRulemaking Docket: Go to 

http://www.regulations.gov. Follow the 

online instructions for sending your 

comments electronically. 

• Fax: 202–493–2251. 

• Mail: Send comments to the U.S. 

Department of Transportation, Docket 

Operations, M–30, West Building 

Ground Floor, Room W12–140, 1200 

New Jersey Avenue SE, Washington, DC 

20590–0001. 

• Hand Delivery: Deliver to the 

‘‘Mail’’ address between 9 a.m. and 5 

p.m., Monday through Friday, except 

Federal holidays. 

Examining the AD Docket 

You may examine the AD docket on 

the internet at http://

www.regulations.gov by searching for 

and locating Docket No. FAA–2018– 

0613; or in person at Docket Operations 

between 9 a.m. and 5 p.m., Monday 

through Friday, except Federal holidays. 

The AD docket contains this AD, any 

incorporated-by-reference service 

information, the economic evaluation, 

any comments received, and other 

information. The street address for 

Docket Operations (telephone 800–647– 

5527) is in the ADDRESSES section. 

Comments will be available in the AD 

docket shortly after receipt. 

For service information identified in 

this final rule, contact Pall Aerospace 

Corporation, 10540 Ridge Road, Suite 

300, Newport Richey, Florida 34654; 

telephone 727–514–6491; email cam_

dipronio@pall.com; website 

www.pall.com/aerospace. You may 

review the referenced service 

information at the FAA, Office of the 

Regional Counsel, Southwest Region, 

10101 Hillwood Pkwy., Room 6N–321, 

Fort Worth, TX 76177. 

FOR FURTHER INFORMATION CONTACT: 

Todd Jackson, Aerospace Engineer, 

Atlanta ACO Branch, Compliance and 

Airworthiness Division, FAA, 1701 

Columbia Ave., College Park, GA 30337, 

telephone 404–474–5567, email 

Todd.Jackson@faa.gov. 

SUPPLEMENTARY INFORMATION: 

Comments Invited 

This AD is a final rule that involves 

requirements affecting flight safety, and 

we did not provide you with notice and 

an opportunity to provide your 

comments prior to it becoming effective. 

However, we invite you to participate in 

this rulemaking by submitting written 

comments, data, or views. We also 

invite comments relating to the 

economic, environmental, energy, or 

federalism impacts that resulted from 

adopting this AD. The most helpful 

comments reference a specific portion of 

the AD, explain the reason for any 

recommended change, and include 

supporting data. To ensure the docket 

does not contain duplicate comments, 

commenters should send only one copy 

of written comments, or if comments are 

filed electronically, commenters should 

submit them only one time. We will file 

in the docket all comments that we 

receive, as well as a report summarizing 

each substantive public contact with 

FAA personnel concerning this 

rulemaking during the comment period. 

We will consider all the comments we 

receive and may conduct additional 

rulemaking based on those comments. 

Discussion 

In June 2017, we received a report of 

an incident involving an Airbus 

Helicopters Model AS350B3 helicopter 

fitted with an IBF. The helicopter took 

off in heavy rain and experienced an 

engine flameout as the pilot increased 

power. The helicopter was less than 10 

feet off the ground when the pilot was 

forced to land immediately. An 

inspection showed that violent water 

ingestion damaged six axial compressor 

blades. During our investigation, the 

FAA received additional reports of 

previous incidents of helicopters 

equipped with IBFs or induction filter 

installations experiencing abnormal 

engine operations during heavy 

precipitation. 

The FAA issued Special 

Airworthiness Information Bulletin 

SW–17–30, dated October 13, 2017 1

(SAIB), to warn operators that persistent 

or heavy rains may result in the inlet 

barrier filter media collecting and 

retaining water. The SAIB 

recommended the following to affected 

owners and operators: 

• Use IBF covers when the rotorcraft 

is parked or towed outside, particularly 

when precipitation is reported in the 

area; 

• During the helicopter preflight 

inspection, visually inspect the inlet 

and filter to verify that the inlet and 

filter medium are dry and free of 

accumulated moisture; 

• If the filter medium has moisture 

during the preflight inspection, or if the 

rotorcraft is operating in heavy 

precipitation, open the bypass doors if 

equipped; and 

• When operating in precipitation, 

sudden and rapid power transients 

should be avoided whenever practical. 

Action Since the SAIB Was Issued 

After the SAIB was issued, we 

continued to investigate this issue and 

determined that AD action was 

necessary for certain Pall Corporation 

IBF dry-media filter elements. Filters 

that have a hydrophobic coating resist 

water accumulation, while the drymedia filters that are the subject of this 

AD accumulate water. The risk of 

engine failure caused by the ingestion of 

an excessive amount of water through 

the IBF element results in an unsafe 

condition that requires AD action. 

FAA’s Determination 

We are issuing 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. 

Related Service Information 

We reviewed Pall Corporation Service 

Information Letter CE01301F2SINFOL, 

Revision A, dated July 15, 2015, which 

recommends covering the engine inlet if 

the helicopter is outside while not 

operating. The letter also recommends 

conducting pre-flight inspections to 

ensure the engine inlet is clear of water. 

AD Requirements 

This AD requires, within 30 days, 

revising the rotorcraft flight manual 

supplement by inserting Appendix A of 

this AD into the limitations section. 

Differences Between This AD and the 

Service Information 

The service information allows for 

removing water and reinstalling the IBF 

element if there is standing water on the 

engine inlet. This AD prohibits 

operation unless the IBF element is dry. 

Interim Action 

We consider this AD to be an interim 

action. The design approval holder is 

currently developing a modification that 

will address the unsafe condition 

identified in this AD. Once this 

modification is developed, approved, 

and available, we might consider 

additional rulemaking. 


daltland on DSKBBV9HB2PROD with RULES
Federal Register / Vol. 83, No. 175 / Monday, September 10, 2018 / Rules and Regulations 45547 

Costs of Compliance 

We estimate that this AD will affect 

81 helicopters of U.S. Registry and that 

labor costs average $85 per work-hour. 

Based on these estimates, we expect the 

following costs: 

• Incorporating Appendix A of this 

AD into the rotorcraft flight manual 

requires 1 work-hour and no parts for a 

cost of $85 per helicopter and $6,885 for 

the U.S. fleet. 

• Replacing the inlet barrier filter, if 

required, requires 2 work-hours and 

parts cost $3,995 for a cost of $4,165 per 

filter replacement. 

FAA’s Justification and Determination 

of the Effective Date 

An unsafe condition exists that 

requires the immediate adoption of this 

AD without providing an opportunity 

for public comments prior to adoption. 

The FAA has found that the risk to the 

flying public justifies waiving notice 

and comment prior to adoption of this 

rule because the unsafe condition 

requires corrective action within 30 

days. Therefore, we find good cause that 

notice and opportunity for prior public 

comment are impracticable. In addition, 

for the reason stated above, we find that 

good cause exists for making this 

amendment effective in less than 30 

days. 

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 determined that this AD will not 

have federalism implications under 

Executive Order 13132. This AD will 

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, I certify 

that this AD: 

1. Is not a ‘‘significant regulatory 

action’’ under Executive Order 12866; 

2. Is not a ‘‘significant rule’’ under 

DOT Regulatory Policies and Procedures 

(44 FR 11034, February 26, 1979); 

3. Will not affect intrastate aviation in 

Alaska to the extent that it justifies 

making a regulatory distinction; 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. 

We prepared an economic evaluation 

of the estimated costs to comply with 

this AD and placed it in the AD docket. 

List of Subjects in 14 CFR Part 39 

Air transportation, Aircraft, Aviation 

safety, Incorporation by reference, 

Safety. 

Adoption of the Amendment 

Accordingly, under the authority 

delegated to me by the Administrator, 

the FAA amends 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): 

2018–18–12 Airbus Helicopters: 

Amendment 39–19391; Docket No. 

FAA–2018–0613; Product Identifier 

2018–SW–041–AD. 

(a) Applicability 

This AD applies to Model AS350B, 

AS350B1, AS350B2, AS350B3, and AS350BA 

helicopters, certificated in any category, with 

a Pall Aerospace Inlet Barrier Filter element 

part number CE01301F2 or CE01301F2B 

installed. 

(b) Unsafe Condition 

This AD defines the unsafe condition as 

ingestion of an excessive amount of water by 

the engine. This condition could result in 

engine flame out and failure, leading to loss 

of helicopter control. 

(c) Effective Date 

This AD becomes effective September 25, 

2018. 

(d) Compliance 

You are responsible for performing each 

action required by this AD within the 

specified compliance time unless it has 

already been accomplished prior to that time. 

(e) Required Actions 

Within 30 days, revise the rotorcraft flight 

manual supplement (RFMS) by inserting 

Appendix A of this AD into the limitations 

section of the RFMS. 

(f) Special Flight Permits 

Special flight permits are prohibited. 

(g) Alternative Methods of Compliance 

(AMOCs) 

(1) The Manager, Atlanta ACO Branch, 

FAA, may approve AMOCs for this AD. Send 

your proposal to: Todd Jackson, Aerospace 

Engineer, Atlanta ACO Branch, Compliance 

and Airworthiness Division, FAA, 1701 

Columbia Ave., College Park, GA 30337, 

telephone 404–474–5567, email 

Todd.Jackson@faa.gov. 

(2) For operations conducted under a 14 

CFR part 119 operating certificate or under 

14 CFR part 91, subpart K, we suggest that 

you notify your principal inspector, or 

lacking a principal inspector, the manager of 

the local flight standards district office or 

certificate holding district office before 

operating any aircraft complying with this 

AD through an AMOC. 

(h) Additional Information 

Pall Corporation Service Information Letter 

CE01301F2SINFOL, Revision A, dated July 

15, 2015, which is not incorporated by 

reference, contains additional information 

about the subject of this AD. For service 

information identified in this AD, contact 

Pall Aerospace Corporation, 10540 Ridge 

Road, Suite 300, Newport Richey, Florida 

34654; telephone 727–514–6491; email cam_

dipronio@pall.com; website www.pall.com/ 

aerospace. You may review this service 

information at the FAA, Office of the 

Regional Counsel, Southwest Region, 10101 

Hillwood Pkwy., Room 6N–321, Fort Worth, 

TX 76177. 

(i) Subject 

Joint Aircraft Service Component (JASC) 

Code: 7160, Engine Air Intake System. 

Appendix A to AD 2018–18–12 

Rotorcraft Flight Manual Supplement 

(1) Helicopter operation is prohibited if the 

filter is wet or when visible moisture (rain/ 

snow/ice/water) is present in the inlet or on 

the filter (inspect filter by hand for wetness). 

If the filter is wet, it must be dried or 

replaced prior to operation. 

(2) Helicopter flight is prohibited in visible 

moisture. 

(3) If the helicopter inadvertently enters 

precipitation (rain/snow/ice/water), open 

bypass doors (if equipped), avoid sudden and 

rapid power transients, and land as soon as 

practical. 

(4) Inlet covers must be installed when the 

rotorcraft is not in flight to prevent moisture 

from collecting in the inlet or on the filter. 

(5) Inspect inlet and filter for visible 

moisture accumulation prior to flight. If 

moisture is present, helicopter operation is 

prohibited. 


daltland on DSKBBV9HB2PROD with RULES
45548 Federal Register / Vol. 83, No. 175 / Monday, September 10, 2018 / Rules and Regulations 

Issued in Fort Worth, Texas, on August 23, 

2018. 

Scott A. Horn, 

Deputy Director for Regulatory Operations, 

Compliance & Airworthiness Division, 

Aircraft Certification Service. 

[FR Doc. 2018–19431 Filed 9–7–18; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2018–0273; Product 

Identifier 2018–NM–017–AD; Amendment 

39–19382; AD 2018–18–03] 

RIN 2120–AA64 

Airworthiness Directives; the Boeing 

Company Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule. 

SUMMARY: We are adopting a new 

airworthiness directive (AD) for certain 

The Boeing Company Model 737–100, 

–200, –200C, –300, –400, and –500 

series airplanes. This AD was prompted 

by several reports of cracks in a certain 

floor beam lower chord at door stop 

fitting No. 1 of the forward airstair door 

cutout. This AD requires repetitive 

inspections for any cracks and 

applicable on-condition actions. We are 

issuing this AD to address the unsafe 

condition on these products. 

DATES: This AD is effective October 15, 

2018. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication listed in this AD 

as of October 15, 2018. 

ADDRESSES: For service information 

identified in this final rule, contact 

Boeing Commercial Airplanes, 

Attention: Contractual & Data Services 

(C&DS), 2600 Westminster Blvd., MC 

110–SK57, Seal Beach, CA 90740–5600; 

telephone 562–797–1717; internet 

https://www.myboeingfleet.com. You 

may view this service information at the 

FAA, Transport Standards Branch, 2200 

South 216th St., Des Moines, WA. For 

information on the availability of this 

material at the FAA, call 206–231–3195. 

It is also available on the internet at 

http://www.regulations.gov by searching 

for and locating Docket No. FAA–2018– 

0273. 

Examining the AD Docket 

You may examine the AD docket on 

the internet at http://

www.regulations.gov by searching for 

and locating Docket No. FAA–2018– 

0273; or in person at Docket Operations 

between 9 a.m. and 5 p.m., Monday 

through Friday, except Federal holidays. 

The AD docket contains this final rule, 

the regulatory evaluation, any 

comments received, and other 

information. The address for Docket 

Operations (phone: 800–647–5527) is 

Docket Operations, U.S. Department of 

Transportation, Docket Operations, M– 

30, West Building Ground Floor, Room 

W12–140, 1200 New Jersey Avenue SE, 

Washington, DC 20590. 

FOR FURTHER INFORMATION CONTACT: 

Galib Abumeri, Aerospace Engineer, 

Airframe Section, Los Angeles ACO 

Branch, FAA, 3960 Paramount 

Boulevard, Lakewood, CA 90712–4137; 

phone: 562–627–5324; fax: 562–627– 

5210; email: galib.abumeri@faa.gov. 

SUPPLEMENTARY INFORMATION: 

Discussion 

We issued a notice of proposed 

rulemaking (NPRM) to amend 14 CFR 

part 39 by adding an AD that would 

apply to certain The Boeing Company 

Model 737–100, –200, –200C, –300, 

–400, and –500 series airplanes. The 

NPRM published in the Federal 

Register on April 13, 2018 (83 FR 

16010). The NPRM was prompted by 

several reports of cracks in a certain 

floor beam lower chord at door stop 

fitting No. 1 of the forward airstair door 

cutout. The NPRM proposed to require 

repetitive inspections for any cracks and 

applicable on-condition actions. 

We are issuing this AD to address 

such cracking, which could result in the 

inability of a principal structural 

element to sustain limit loads and 

possible rapid decompression. 

Comments 

We gave the public the opportunity to 

participate in developing this final rule. 

The following presents the comments 

received on the NPRM and the FAA’s 

response to each comment. 

Support for the NPRM 

Boeing stated that it concurs with the 

NPRM. 

Effect of Winglets on Accomplishment 

of the Proposed Actions 

Aviation Partners Boeing stated that 

accomplishing supplemental type 

certificate (STC) ST01219SE does not 

affect the actions specified in the 

NPRM. 

We agree with the commenter’s 

request. We have redesignated 

paragraph (c) of the proposed AD as 

paragraph (c)(1) of this AD and added 

paragraph (c)(2) to this AD to state that 

installation of STC ST01219SE does not 

affect the ability to accomplish the 

actions required by this AD. Therefore, 

for airplanes on which STC ST01219SE 

is installed, a ‘‘change in product’’ 

alternative method of compliance 

(AMOC) approval request is not 

necessary to comply with the 

requirements of 14 CFR 39.17. 

Request To Allow Manual Operation of 

Airstair Door 

Swiftair S.A. requested that a note be 

included in this AD to allow for fully 

manual operation of the forward airstair 

door instead of the electrical operation 

as specified in Appendix A of Boeing 

Alert Requirements Bulletin 737– 

53A1370 RB, dated December 13, 2017. 

Swiftair S.A. observed that two steps in 

Appendix A of Boeing Alert 

Requirements Bulletin 737–53A1370 

RB, dated December 13, 2017, cannot be 

performed on aircraft that have 

incorporated Boeing Service Bulletin 

737–52–1092. Boeing Service Bulletin 

737–52–1092 provides instructions for 

temporary or permanent removal of the 

forward airstair assembly, deactivation 

of the electrical system, and removal of 

the forward airstair door motor, among 

other actions. 

We agree because the forward airstair 

door cannot be operated electrically if 

the electrical system is deactivated and 

the motor is removed. We have changed 

paragraph (h) of this AD to include 

exceptions to certain steps of Appendix 

A of Boeing Alert Requirements Bulletin 

737–53A1370 RB, dated December 13, 

2017, that allow for both manual and 

electrical operation of the airstair door. 

Conclusion 

We reviewed the relevant data, 

considered the comments received, and 

determined that air safety and the 

public interest require adopting this 

final rule with the changes described 

previously and minor editorial changes. 

We have determined that these minor 

changes: 

• Are consistent with the intent that 

was proposed in the NPRM for 

addressing the unsafe condition; and 

• Do not add any additional burden 

upon the public than was already 

proposed in the NPRM. 

We also determined that these 

changes will not increase the economic 

burden on any operator or increase the 

scope of this final rule. 

Related Service Information Under 1 

CFR Part 51 

We reviewed Boeing Alert 

Requirements Bulletin 737–53A1370 

RB, dated December 13, 2017. The 

service information describes 

procedures for repetitive high frequency 


daltland on DSKBBV9HB2PROD with RULES