44504 Federal Register / Vol. 82, No. 184 / Monday, September 25, 2017 / Rules and Regulations 

condition on these products as a result of 

possible corrosion on the rudder upper hinge 

bracket and internal wing, areas of the 

passenger/crew door hinges and supporting 

structure, the main spar joint, and the engine 

support attachment bolts, which could lead 

to reduced structural integrity with 

consequent loss of control. 

(f) Actions and Compliance 

Comply with paragraphs (f)(1) through (3) 

of this AD within the compliance times 

specified, unless already done: 

(1) Before further flight after October 30, 

2017 (the effective date of this AD), 

incorporate BAE Systems (Operations) 

Limited Jetstream Series 3100 & 3200 

Corrosion Prevention and Control 

Programme, Manual Ref. JS/CPCP/01, 

Revision 8, dated October 15, 2016, into the 

Limitations of your FAA-approved 

maintenance program (instructions for 

continued airworthiness) on the basis of 

which the operator or the owner ensures the 

continuing airworthiness of each operated 

airplane, as applicable to the airplane model. 

(2) Do all tasks in the BAE Systems 

(Operations) Limited Jetstream Series 3100 & 

3200 Corrosion Prevention and Control 

Programme, Manual Ref. JS/CPCP/01, 

Revision 8, dated October 15, 2016, at the 

compliance times specified in the manual, or 

within the next 12 months after October 30, 

2017 (the effective date of this AD), 

whichever occurs later; except for the 

following tasks, which must be done within 

12 months after October 30, 2017 (the 

effective date of this AD): 52–11–002 C1, 

200/EX/01 C2, 500/IN/02 C1, 600/IN/04 C1, 

and 700/IN/04 C1. 

(3) If any discrepancy, particularly 

corrosion, is found during any inspections or 

tasks required by paragraphs (f)(1) or (2) of 

this AD, within the compliance time 

specified, repair or replace, as applicable, all 

damaged structural parts and components 

and do the maintenance procedures for 

corrective action following BAE Systems 

(Operations) Limited Jetstream Series 3100 & 

3200 Corrosion Prevention and Control 

Programme, Manual Ref. JS/CPCP/01, 

Revision 8, dated October 15, 2016. If no 

compliance time is defined, do the applicable 

corrective action before further flight. 

(g) Other FAA AD Provisions 

The following provisions also apply to this 

AD: 

(1) Alternative Methods of Compliance 

(AMOCs): The Manager, Small Airplane 

Standards Branch, FAA, has the authority to 

approve AMOCs for this AD, if requested 

using the procedures found in 14 CFR 39.19. 

Send information to ATTN: Doug Rudolph, 

Aerospace Engineer, FAA, Small Airplane 

Standards Branch, 901 Locust, Room 301, 

Kansas City, Missouri 64106; telephone: 

(816) 329–4059; fax: (816) 329–4090; email: 

doug.rudolph@faa.gov. Before using any 

approved AMOC on any airplane to which 

the AMOC applies, notify your appropriate 

principal inspector (PI) in the FAA Flight 

Standards District Office (FSDO), or lacking 

a PI, your local FSDO. 

(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, Small Airplane Standards 

Branch; or the European Aviation Safety 

Agency (EASA), or BAE Systems 

(Operations) Limited’s EASA DOA. If 

approved by the DOA, the approval must 

include the DOA-authorized signature. 

(3) Reporting Requirements: For any 

reporting requirement in this AD, 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 5 minutes 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. 

(h) Related Information 

Refer to MCAI European Aviation Safety 

Agency 2017–0073, dated April 27, 2017. 

The MCAI can be found in the AD docket on 

the Internet at: https://www.regulations.gov/ 

document?D=FAA-2017-0639-0002. 

(i) 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 the AD specifies otherwise. 

(i) BAE Systems (Operations) Limited 

Jetstream Series 3100 & 3200 Corrosion 

Prevention and Control Programme, Manual 

Ref. JS/CPCP/01, Revision 8, dated October 

15, 2016. 

(ii) Reserved. 

(3) For British Aerospace Jetstream Series 

3100 and 3200 service information related to 

this AD, contact BAE Systems (Operations) 

Limited, Customer Information Department, 

Prestwick International Airport, Ayrshire, 

KA9 2RW, Scotland, United Kingdom; 

telephone: +44 1292 675207; fax: +44 1292 

675704; email: RApublications@

baesystems.com; Internet: http://

www.baesystems.com/Businesses/ 

RegionalAircraft/. 

(4) You may review copies of the 

referenced service information at the FAA, 

Policy and Innovation Division, 901 Locust, 

Kansas City, Missouri 64106. For information 

on the availability of this material at the 

FAA, call (816) 329–4148. In addition, you 

can access this service information on the 

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

searching for and locating Docket No. FAA– 

2017–0639. 

(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 Kansas City, Missouri, on 

September 14, 2017. 

Pat Mullen, 

Acting Deputy Director, Policy & Innovation 

Division, Aircraft Certification Service. 

[FR Doc. 2017–20047 Filed 9–22–17; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2016–9301; Product 

Identifier 2015–NM–193–AD; Amendment 

39–19056; AD 2017–19–26] 

RIN 2120–AA64 

Airworthiness Directives; The Boeing 

Company Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Final rule. 

SUMMARY: We are superseding 

Airworthiness Directive (AD) 2008–12– 

04, which applied to certain The Boeing 

Company Model 737–600, –700, –700C, 

–800, and –900 series airplanes. AD 

2008–12–04 required various repetitive 

inspections to detect cracks along the 

chem-milled steps of the fuselage skin, 

and to detect missing or loose fasteners 

in the area of a certain preventive 

modification or repairs; replacement of 

the time-limited repair with a 

permanent repair, if applicable; and 

applicable corrective actions which 

would end certain repetitive 

inspections. This AD reduces the postmodification inspection compliance 

times, limits installation of the 

preventive modification to airplanes 

with fewer than 30,000 total flight 

cycles, and adds repetitive inspections 

for modified airplanes. This AD was 

prompted by an evaluation by the 

design approval holder (DAH) that 

indicated that the upper skin panel at 

the chem-milled step above the lap joint 

is subject to widespread fatigue damage 

(WFD) if the modification was installed 

after 30,000 total flight cycles. We are 

issuing this AD to address the unsafe 

condition on these products. 

DATES: This AD is effective October 30, 

2017. 


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Federal Register / Vol. 82, No. 184 / Monday, September 25, 2017 / Rules and Regulations 44505 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication listed in this AD 

as of October 30, 2017. 

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; 

telephone 562–797–1717; Internet 

https://www.myboeingfleet.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. It is also 

available on the internet at http://

www.regulations.gov by searching for 

and locating Docket No. FAA–2016– 

9301. 

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–2016– 

9301; 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 AD, the regulatory 

evaluation, any comments received, and 

other information. The address for the 

Docket Office (phone: 800–647–5527) is 

Docket Management Facility, 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: 

Alan Pohl, Aerospace Engineer, 

Airframe Section, FAA, Seattle ACO 

Branch, 1601 Lind Avenue SW., Renton, 

WA 98057–3356; phone: 425–917–6450; 

fax: 425–917–6590; email: alan.pohl@

faa.gov. 

SUPPLEMENTARY INFORMATION: 

Discussion 

We issued a notice of proposed 

rulemaking (NPRM) to amend 14 CFR 

part 39 to supersede AD 2008–12–04, 

Amendment 39–15547 (73 FR 32991, 

June 11, 2008) (‘‘AD 2008–12–04’’). AD 

2008–12–04 applied to certain The 

Boeing Company Model 737–600, –700, 

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

The NPRM published in the Federal 

Register on November 22, 2016 (81 FR 

83745) (‘‘the NPRM’’). The NPRM was 

prompted by an evaluation by the DAH 

that indicated that the upper skin panel 

at the chem-milled step above the lap 

joint is subject to WFD if the 

modification was installed after 30,000 

total flight cycles. The NPRM proposed 

to continue to require various repetitive 

inspections to detect cracks along the 

chem-milled steps of the fuselage skin, 

and to detect missing or loose fasteners 

in the area of the preventive 

modification or repairs; replacement of 

the time-limited repair with a 

permanent repair, if applicable; and 

applicable corrective actions which 

would end certain repetitive 

inspections. The NPRM also proposed 

to reduce the post-modification 

inspection compliance times, limit 

installation of the preventive 

modification to airplanes with fewer 

than 30,000 total flight cycles, and add 

repetitive inspections for modified 

airplanes. We are issuing this AD to 

detect and correct cracking of the upper 

skin panel at the chem-milled step 

above the lap joint, which could result 

in reduced structural integrity of the 

airplane. 

Comments 

We gave the public the opportunity to 

participate in developing this AD. The 

following presents the comments 

received on the NPRM and the FAA’s 

response to each comment. 

Support for the NPRM 

Boeing and United Airlines supported 

the NPRM. 

Effect of Winglets on Accomplishment 

of the Proposed Actions 

Aviation Partners Boeing stated that 

installation of winglets, as provided in 

Supplemental Type Certificate (STC) 

ST00830SE, does not affect the ability to 

accomplish the actions proposed in the 

NPRM. 

We agree with the commenter. We 

have redesignated paragraph (c) of the 

proposed AD as (c)(1) and added 

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

installation of STC ST00830SE does not 

affect the ability to accomplish the 

actions required by this AD. Therefore, 

for airplanes on which STC ST00830SE 

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 Revise Certain Compliance 

Time Provisions 

Southwest Airlines (SWA) asked that 

we revise certain compliance language 

in paragraph (p)(4) of the proposed AD, 

which stipulated that post-repair or 

post-mod inspections be done at the 

time specified in the service information 

or at the time specified in the previously 

approved AMOC, ‘‘whichever occurs 

first.’’ SWA stated that previously 

approved AMOCs for post-repair or 

post-modification supplemental 

inspections that comply with certain 

regulations may contain unique damage 

tolerance inspection programs that 

demonstrate a level of safety equivalent 

to that of AD 2008–12–04. SWA added 

that altering those supplemental 

inspections to post-repair or postmodification inspections as specified in 

Boeing Alert Service Bulletin 737– 

53A1232, Revision 3, dated July 27, 

2015, when those are done first, could 

result in incorrect inspection methods 

to geometrical structure that does not 

conform to the repair or modification 

definitions specified in Revisions 1 and 

3 of that service information. 

We partially agree with the 

commenter’s request. We have 

determined that repairs and preventive 

modifications should be handled 

separately. Fleet experience and 

subsequent analysis of Model 737–200, 

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

which have similar chem-milled step 

details, have shown that certain postpreventative modification inspection 

programs may not adequately address 

the unsafe condition. Therefore, 

paragraph (p)(4) of this AD has been 

changed to remove the language 

‘‘preventative modifications’’ and 

remove the reference to the service 

information and ‘‘whichever occurs 

first’’ from the compliance time 

specified. In addition, we have added 

paragraph (p)(5) to this AD to address 

only the preventive modifications 

without change to the service 

information and ‘‘whichever occurs 

first’’ language. 

Request To Retain Certain Exceptions 

Additionally, SWA asked that 

paragraphs (j) and (k) of AD 2008–12– 

04 be included in the proposed AD. 

Paragraph (j) of AD 2008–12–04 

provides an allowance for repairs that 

are FAA-approved and that have a 

minimum of three rows of fasteners 

above and below the chem-milled step. 

SWA stated that paragraph (k) of AD 

2008–12–04 provides a means of 

inspections without an AMOC when an 

external repair is covering the chemmilled step, but that the doubler does 

not span the step by a minimum of three 

rows of fasteners above and below the 

chem-milled step. SWA added that both 

paragraphs (j) and (k) of AD 2008–12– 

04 are missing from the proposed AD 

and should be added, with certain 

clarifications, to paragraph (j) of the 

proposed AD. First, the repair is an 

external doubler repair. Second, in lieu 

of the doing the post-repair 

supplemental inspections in accordance 

with table 2 of paragraph 1.E., 


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‘‘Compliance,’’ of Boeing Alert Service 

Bulletin 737–53A1232, Revision 3, 

dated July 27, 2015, the inspections 

should be done in accordance with 14 

CFR 121.1109(c)(2) or 14 CFR 

129.109(b)(2) supplemental inspection 

requirements, or in accordance with 

FAA-approved damage tolerance 

inspection requirements. 

SWA also stated that if paragraphs (j) 

and (k) of AD 2008–12–04 are not 

restated for compliance with existing 

FAA-approved repairs, operators will be 

required to seek AMOC approvals for 

such existing repairs prior to the 

inspection threshold or repeat interval 

of table 1 of paragraph 1.E., 

‘‘Compliance,’’ of Boeing Alert Service 

Bulletin 737–53A1232, Revision 3, 

dated July 27, 2015. SWA stated that not 

including the exceptions in paragraphs 

(j) and (k) of AD 2008–12–04 could 

potentially lead to disruption of 

operations if it is necessary to request 

AMOC approvals during repair 

discovery, or could burden operators 

with records research to identify these 

repairs for AMOC approvals prior to the 

required compliance times. 

We agree that an allowance can be 

made for repairs that meet the criteria 

specified in paragraph (j) of AD 2008– 

12–04. These repairs address the unsafe 

condition identified in this AD. 

Therefore, we have added paragraph 

(l)(3) to this AD to include the provision 

of paragraph (j) of AD 2008–12–04 for 

repairs that were accomplished before 

the effective date of this AD. 

We disagree that post-repair 

inspections for these repairs should be 

done in accordance with 14 CFR 

121.1109(c)(2) or 14 CFR 129.109(b)(2) 

supplemental inspection requirements. 

Post-repair inspections for repairs that 

meet the criteria of paragraph (j) of this 

AD are to be accomplished in 

accordance with table 2 of paragraph 

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

Service Bulletin 737–53A1232, Revision 

3, dated July 27, 2015. This is consistent 

with the DAH’s current 

recommendation as well as the 

requirements of paragraph (j) of AD 

2008–12–04. Paragraph (l)(3) of this AD 

reflects these provisions. 

We also disagree with the 

commenter’s request to change the word 

‘‘repair’’ to ‘‘external doubler repair’’ in 

paragraph (l)(3) of this AD because we 

are retaining the provisions of paragraph 

(j) of AD 2008–12–04. 

We also agree to add certain 

provisions of paragraph (k) of AD 2008– 

12–04 to this AD. We have added 

paragraph (l)(4) to this AD to address 

certain repairs as defined in paragraph 

(k) of AD 2008–12–04. However, 

paragraph (l)(4) of this AD does not 

include a reference to Boeing Model 737 

Non-destructive Test (NDT) Manual, 

Part 6, Subject 53–30–20, and instead 

requires that the inspection be done 

using FAA-approved procedures. We 

have also added Note 1 to paragraph 

(l)(4) of this AD to specify that guidance 

on the inspection specified in paragraph 

(l)(4) of this AD can be found in Boeing 

Model 737 NDT Manual, Part 6, Subject 

53–30–20. 

Clarification of Paragraph (i)(1) of This 

AD 

We have revised the language in 

paragraph (i)(1) of this AD to clarify 

which modifications are exempt from 

the actions required by paragraph (i)(1) 

of this AD. 

Conclusion 

We reviewed the relevant data, 

considered the comments received, and 

determined that air safety and the 

public interest require adopting this AD 

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 

correcting 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 AD. 

Related Service Information Under 1 

CFR Part 51 

We reviewed Boeing Alert Service 

Bulletin 737–53A1232, Revision 3, 

dated July 27, 2015. This service 

information describes procedures for an 

external detailed inspection and an 

external nondestructive inspection 

(NDI) for cracks in the fuselage skin at 

chem-milled steps. Corrective actions 

include a permanent or time-limited 

repair, a preventive modification, and 

replacement of loose and missing 

fasteners. Related investigative actions 

include internal and external detailed 

inspections of the repair area. 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. 

Costs of Compliance 

We estimate that this AD affects 376 

airplanes of U.S. registry. 

We estimate the following costs to 

comply with this AD: 

ESTIMATED COSTS

Action Labor cost Parts cost Cost per product Cost on U.S. operators 

Inspections ............ Up to 25 work-hours × $85 per 

hour = $2,125 per inspection 

cycle.

$0 Up to $2,125 per inspection cycle Up to $799,000 per inspection 

cycle. 

We estimate the following costs to do 

any necessary repairs and replacements 

that would be required based on the 

results of the inspections. We have no 

way of determining the number of 

aircraft that might need these 

replacements: 

ON-CONDITION COSTS

Action Labor cost Parts cost Cost per 

product 

Fastener replacement ...................... Up to 1 work-hour × $85 per hour = $85 ................................................... Minimal ......... $85 


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Federal Register / Vol. 82, No. 184 / Monday, September 25, 2017 / Rules and Regulations 44507 

We have received no definitive data 

that would enable us to provide cost 

estimates for the related investigative 

actions, certain repairs, and other 

applicable actions specified in this AD. 

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 AD is issued in accordance with 

authority delegated by the Executive 

Director, Aircraft 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 have 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 above, 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, 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. 

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 

removing Airworthiness Directive (AD) 

2008–12–04, Amendment 39–15547 (73 

FR 32991, June 11, 2008), and adding 

the following new AD: 

2017–19–26 The Boeing Company: 

Amendment 39–19056; Docket No. 

FAA–2016–9301; Product Identifier 

2015–NM–193–AD. 

(a) Effective Date 

This AD is effective October 30, 2017. 

(b) Affected ADs 

This AD replaces AD 2008–12–04, 

Amendment 39–15547 (73 FR 32991, June 

11, 2008) (‘‘AD 2008–12–04’’). 

(c) Applicability 

(1) This AD applies to The Boeing 

Company Model 737–600, –700, –700C, 

–800, and –900 series airplanes, certificated 

in any category, as identified in Boeing Alert 

Service Bulletin 737–53A1232, Revision 3, 

dated July 27, 2015. 

(2) Installation of Supplemental Type 

Certificate (STC) ST00830SE [http://rgl.faa.

gov/Regulatory_and_Guidance_Library/rgstc.

nsf/0/184DE9A71EC3FA5586257EAE00

707DA6?OpenDocument&Highlight=

st00830se] does not affect the ability to 

accomplish the actions required by this AD. 

Therefore, for airplanes on which STC 

ST00830SE 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. 

(d) Subject 

Air Transport Association (ATA) of 

America Code 53, Fuselage. 

(e) Unsafe Condition 

This AD was prompted by a fatigue test 

that revealed numerous cracks in the upper 

skin panel at the chem-milled step above the 

lap joint, followed by an evaluation by the 

design approval holder (DAH) that indicated 

that location is subject to widespread fatigue 

damage (WFD) on airplanes on which a 

certain modification was installed after 

30,000 total flight cycles. We are issuing this 

AD to detect and correct cracking of the 

upper skin panel at the chem-milled step 

above the lap joint, which could result in 

reduced structural integrity of the airplane. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Inspections at Locations Without the 

Preventive Modification, Time-Limited 

Repair, or Permanent Repair Installed 

At locations where a preventive 

modification, time-limited repair, or 

permanent repair has not been installed as 

specified in Boeing Service Bulletin 737– 

53A1232: At the applicable time specified in 

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

Alert Service Bulletin 737–53A1232, 

Revision 3, dated July 27, 2015, do an 

external detailed inspection and an 

inspection specified in either paragraph (g)(1) 

or (g)(2) of this AD, for any crack in the 

fuselage skin at the chem-milled steps at 

specified locations, in accordance with 

Accomplishment Instructions of Boeing Alert 

Service Bulletin 737–53A1232, Revision 3, 

dated July 27, 2015. Do all applicable related 

investigative and corrective actions before 

further flight in accordance with the 

Accomplishment Instructions of Boeing Alert 

Service Bulletin 737–53A1232, Revision 3, 

dated July 27, 2015, except as required by 

paragraph (l)(1) of this AD, and except as 

provided in paragraphs (l)(3) and (l)(4) of this 

AD. Repeat the inspections thereafter at the 

applicable time specified in paragraph 1.E., 

‘‘Compliance,’’ of Boeing Alert Service 

Bulletin 737–53A1232, Revision 3, dated July 

27, 2015. 

(1) Do an external medium frequency eddy 

current (MFEC), or magneto optic imager 

(MOI), or C-Scan inspection. 

(2) Do an external ultrasonic phased array 

(UTPA) inspection. 

(h) Repetitive Post-Modification Inspections 

and Repair at Any Location With the 

Preventive Modification But No TimeLimited or Permanent Repair 

At any location with a preventive 

modification installed as specified in Boeing 

Service Bulletin 737–53A1232: At the 

applicable time specified in paragraph 1.E., 

‘‘Compliance,’’ of Boeing Alert Service 

Bulletin 737–53A1232, Revision 3, dated July 

27, 2015, except as required by paragraph 

(l)(2) of this AD, do the actions specified in 

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

(1) Do external detailed and external high 

frequency and medium frequency eddy 

current inspections for any crack, in 

accordance with Part 7 of the 

Accomplishment Instructions of Boeing Alert 

Service Bulletin 737–53A1232, Revision 3, 

dated July 27, 2015. If no crack is found 

during the inspection, repeat the inspections 

thereafter at the applicable time specified in 

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

Alert Service Bulletin 737–53A1232, 

Revision 3, dated July 27, 2015. If any crack 

is found during any inspection required by 

this paragraph, repair before further flight, in 

accordance with the Accomplishment 

Instructions of Boeing Alert Service Bulletin 

737–53A1232, Revision 3, dated July 27, 


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44508 Federal Register / Vol. 82, No. 184 / Monday, September 25, 2017 / Rules and Regulations 

2015, except as required by paragraph (l)(1) 

of this AD. 

(2) Do a detailed inspection for any crack 

and any loose or missing fasteners, in 

accordance with Part 7 of the 

Accomplishment Instructions of Boeing Alert 

Service Bulletin 737–53A1232, Revision 3, 

dated July 27, 2015. Repeat the inspections 

thereafter at applicable time specified in 

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

Service Bulletin 737–53A1232, Revision 3, 

dated July 27, 2015. If any crack is found 

during any inspection, or any loose or 

missing fastener is found, before further 

flight, do all applicable corrective actions, in 

accordance with Part V of the 

Accomplishment Instructions of Boeing Alert 

Service Bulletin 737–53A1232, Revision 3, 

dated July 27, 2015, except as specified in 

paragraph (l)(1) of this AD. 

(i) Additional Actions for Modified 

Airplanes 

(1) At any location where a preventive 

modification as specified in Boeing Service 

Bulletin 737–53A1232 was installed after the 

accumulation of 30,000 total flight cycles, at 

the applicable time specified in paragraph 

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

Bulletin 737–53A1232, Revision 3, dated July 

27, 2015, except as required by paragraph 

(l)(2) of this AD, do all applicable 

investigative and corrective actions using a 

method approved in accordance with the 

procedures specified in paragraph (p) of this 

AD. For preventive modifications installed 

on airplanes listed in Appendix A of Boeing 

Alert Service Bulletin 737–53A1232, 

Revision 3, dated July 27, 2015, at the 

specified total flight cycles: The actions 

specified in this paragraph are not required. 

(2) For airplanes which have installed STC 

ST01697SE (http://rgl.faa.gov/Regulatory_

and_Guidance_Library/rgstc.nsf/0/0812969a

86af879b8625766400600105/$FILE/ 

ST01697SE.pdf) and the preventive 

modification has been installed after 15,000 

total flight cycles: Before the accumulation of 

25,000 total flight cycles, do all applicable 

investigative and corrective actions using a 

method approved in accordance with the 

procedures specified in paragraph (p) of this 

AD. 

(j) Inspections and Repair at Locations With 

the Permanent Chem-Milled Step Repair 

Installed 

At any location where a permanent repair 

has been installed as specified in Boeing 

Service Bulletin 737–53A1232: At the 

applicable time specified in paragraph 1.E., 

‘‘Compliance,’’ of Boeing Alert Service 

Bulletin 737–53A1232, Revision 3, dated July 

27, 2015, do the inspections specified in 

paragraph (j)(1) or (j)(2) of this AD, in 

accordance with Accomplishment 

Instructions of Boeing Alert Service Bulletin 

737–53A1232, Revision 3, dated July 27, 

2015. Repeat the inspections thereafter at the 

applicable time specified in paragraph 1.E., 

‘‘Compliance,’’ of Boeing Alert Service 

Bulletin 737–53A1232, Revision 3, dated July 

27, 2015. Do all applicable related 

investigative and corrective actions before 

further flight in accordance with Boeing Alert 

Service Bulletin 737–53A1232, Revision 3, 

dated July 27, 2015, except as required by 

paragraph (l)(1) of this AD. 

(1) Do an external low frequency eddy 

current (LFEC) inspection for any crack, and 

doubler external LFEC and external detailed 

inspections for any crack and loose or 

missing fasteners. 

(2) Do an external LFEC inspection for any 

crack, a doubler external LFEC and external 

detailed inspections for any crack and loose 

or missing fasteners, and an internal MFEC 

for any crack. 

(k) Inspection and Replacement at Locations 

With a Chem-Milled Time-Limited Repair 

Installed 

At any location where a chem-milled timelimited repair is installed, do the actions 

specified in paragraphs (k)(1) and (k)(2) of 

this AD, at the applicable time specified in 

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

Bulletin 737–53A1232, Revision 3, dated July 

27, 2015. 

(1) Do internal and external detailed 

inspections of the time-limited repair for any 

crack, or loose or missing fasteners, in 

accordance with Part IV of the 

Accomplishment Instructions of Boeing Alert 

Service Bulletin 737–53A1232, Revision 3, 

dated July 27, 2015. Repeat the inspections 

thereafter at the applicable time specified in 

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

Alert Service Bulletin 737–53A1232, 

Revision 3, dated July 27, 2015. If any crack 

is found during any inspection, or if any 

loose or missing fastener is found, before 

further flight, do all applicable corrective 

actions, in accordance with Part IV of the 

Accomplishment Instructions of Boeing Alert 

Service Bulletin 737–53A1232, Revision 3, 

dated July 27, 2015, except as specified in 

paragraph (l)(1) of this AD. 

(2) Replace the time-limited repair with the 

permanent repair, in accordance with Part IV 

of the Accomplishment Instructions of 

Boeing Alert Service Bulletin 737–53A1232, 

Revision 3, dated July 27, 2015. 

(l) Exceptions to Service Information 

Specifications 

(1) Where Boeing Alert Service Bulletin 

737–53A1232, Revision 3, dated July 27, 

2015, specifies to contact Boeing for repair 

instructions, this AD requires repair before 

further flight using a method approved in 

accordance with the procedures specified in 

paragraph (p) of this AD. 

(2) Where paragraph 1.E., ‘‘Compliance,’’ of 

Boeing Alert Service Bulletin 737–53A1232, 

Revision 3, dated July 27, 2015, specifies a 

compliance time ‘‘after the date of Revision 

2 of this service bulletin,’’ this AD requires 

compliance within the specified compliance 

time after the effective date of this AD. 

(3) For airplanes on which the actions 

specified in paragraph (g) of this AD are 

required: Inspections specified in table 1 of 

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

Alert Service Bulletin 737–53A1232, 

Revision 3, dated July 27, 2015, are not 

required in areas that are spanned by an 

FAA-approved repair that has a minimum of 

3 rows of fasteners above and below the 

chem-milled step, provided that the repair 

was installed before the effective date of this 

AD. Operators must accomplish post-repair 

inspections at the applicable time specified 

in table 2 of paragraph 1.E, ‘‘Compliance,’’ of 

Boeing Alert Service Bulletin 737–53A1232, 

Revision 3, dated July 27, 2015. 

(4) For any airplane that has an external 

doubler covering the chem-milled step, but 

the doubler does not span the step by a 

minimum of 3 rows of fasteners above and 

below the chem-milled step and the doubler 

was installed before the effective date of this 

AD: One method of compliance with the 

inspection requirement of paragraph (g) of 

this AD is to inspect all chem-milled steps 

covered by the repair using non-destructive 

test (NDT) methods approved in accordance 

with the procedures specified in paragraph 

(p) of this AD. These repairs are to be 

considered time-limited and are subject to 

the post-repair supplemental inspections and 

replacement at the times specified in table 3 

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

Alert Service Bulletin 737–53A1232, 

Revision 3, dated July 27, 2015. 

Note 1 to paragraph (l)(4) of this AD: 

Guidance for the procedures for the 

alternative inspection specified in paragraph 

(l)(4) of this AD can be found in the Boeing 

737 NDT Manual, Part 6, Subject 53–30–20. 

(m) Optional Terminating Action 

(1) For airplanes that have accumulated 

30,000 total flight cycles or fewer, or for 

airplanes on which STC ST01697SE was 

installed and that have accumulated 15,000 

total flight cycles or fewer, accomplishment 

of the preventive modification specified in 

Part V of Boeing Alert Service Bulletin 737– 

53A1232, Revision 3, dated July 27, 2015, 

terminates the inspections required by 

paragraph (g) of this AD in the modified areas 

only. 

(2) Installation of a permanent repair as 

specified in Part III of Boeing Alert Service 

Bulletin 737–53A1232, Revision 3, dated July 

27, 2015, or a time-limited repair as specified 

in Part IV of Boeing Alert Service Bulletin 

737–53A1232, Revision 3, dated July 27, 

2015, terminates the inspections required by 

paragraph (g) of this AD in the repaired areas 

only. 

(n) Installation Limitations of Preventive 

Modification 

As of the effective date of this AD, 

installation of the preventive modification 

specified in Boeing Service Bulletin 737– 

53A1232 is prohibited on the airplanes 

identified in paragraphs (n)(1) and (n)(2) of 

this AD. 

(1) Airplanes that have accumulated more 

than 30,000 total flight cycles. 

(2) Airplanes which have installed STC 

ST01697SE and that have accumulated more 

than 15,000 total flight cycles. 

(o) Credit for Previous Actions 

This paragraph provides credit for the 

corresponding actions specified in 

paragraphs (g), (h), (i), (j), (k), and (m) of this 

AD, if those actions were performed before 

the effective date of this AD using the service 

information identified in paragraph (o)(1), 

(o)(2), or (o)(3) of this AD. 

(1) Boeing Special Attention Service 

Bulletin 737–53A1232, dated April 2, 2007. 


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Federal Register / Vol. 82, No. 184 / Monday, September 25, 2017 / Rules and Regulations 44509 

(2) Boeing Special Attention Service 

Bulletin 737–53A1232, Revision 1, dated 

May 18, 2012. 

(3) Boeing Special Attention Service 

Bulletin 737–53A1232, Revision 2, dated July 

26, 2013. 

(p) Alternative Methods of Compliance 

(AMOCs) 

(1) The Manager, Seattle ACO 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 manager of the 

certification office, send it to the attention of 

the person identified in paragraph (q)(1) of 

this AD. Information may be emailed to: 9- 

ANM-Seattle-ACO-AMOC-Requests@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, 

modification, or alteration 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. To be 

approved, the repair method, modification 

deviation, or alteration deviation must meet 

the certification basis of the airplane, and the 

approval must specifically refer to this AD. 

(4) AMOCs approved previously for repairs 

for AD 2008–12–04 are approved as AMOCs 

for the installation of the repair specified in 

this AD, provided all post-repair inspections 

are done at the applicable times specified in 

the AMOC. 

(5) AMOCs approved previously for 

preventive modifications for AD 2008–12–04 

are approved as AMOCs for the installation 

of the preventive modification specified in 

this AD, provided all post-modification 

inspections are done at the applicable times 

specified in the AMOC, or in tables 1a and 

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

Boeing Alert Service Bulletin 737–53A1232, 

Revision 3, dated July 27, 2015, whichever 

occurs first. The AMOC must include all of 

the inspections specified in Tables 1a and 1b 

of Boeing Alert Service Bulletin 737– 

53A1232, Revision 3, dated July 27, 2015. 

(q) Related Information 

(1) For more information about this AD, 

contact Alan Pohl, Aerospace Engineer, 

Airframe Section, FAA, Seattle ACO Branch, 

1601 Lind Avenue SW., Renton, WA 98057– 

3356; phone: 425–917–6577; fax: 425–917– 

6450; email: alan.pohl@faa.gov. 

(2) Service information identified in this 

AD that is not incorporated by reference is 

available at the addresses specified in 

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

(r) 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 the AD specifies otherwise. 

(i) Boeing Alert Service Bulletin 737– 

53A1232, Revision 3, dated July 27, 2015. 

(ii) Reserved. 

(3) For service information identified in 

this AD, contact Boeing Commercial 

Airplanes, Attention: Contractual & Data 

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

MC 110–SK57, Seal Beach, CA 90740; 

telephone 562–797–1717; Internet https://

www.myboeingfleet.com. 

(4) 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. 

(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/ibr-locations.html. 

Issued in Renton, Washington, on 

September 14, 2017. 

Jeffrey E. Duven, 

Director, System Oversight Division, Aircraft 

Certification Service. 

[FR Doc. 2017–20114 Filed 9–22–17; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2016–9143; Product 

Identifier 2013–SW–037–AD; Amendment 

39–19051; AD 2017–19–21] 

RIN 2120–AA64 

Airworthiness Directives; Airbus 

Helicopters 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule. 

SUMMARY: We are adopting a new 

airworthiness directive (AD) for Airbus 

Helicopters Model EC225LP helicopters. 

This AD requires modifying the 

emergency lubrication system (EMLUB). 

This AD was prompted by two incidents 

of emergency ditching after there was a 

warning of a loss of oil pressure and a 

false EMLUB failure. The actions of this 

AD are intended to address an unsafe 

condition on these products. 

DATES: This AD is effective October 30, 

2017. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain document listed in this AD 

as of October 30, 2017. 

ADDRESSES: For service information 

identified in this final rule, contact 

Airbus Helicopters, 2701 N Forum 

Drive, Grand Prairie, TX 75052; 

telephone (972) 641–0000 or (800) 232– 

0323; fax (972) 641–3775; or at http://

www.airbushelicopters.com/techpub. 

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. 

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–2016– 

9143; or in person at the Docket 

Operations Office between 9 a.m. and 5 

p.m., Monday through Friday, except 

Federal holidays. The AD docket 

contains this AD, the European Aviation 

Safety Agency (EASA) AD, any 

incorporated-by-reference service 

information, the economic evaluation, 

any comments received, and other 

information. The street address for the 

Docket Operations Office (phone: 800– 

647–5527) is U.S. Department of 

Transportation, Docket Operations 

Office, M–30, West Building Ground 

Floor, Room W12–140, 1200 New Jersey 

Avenue SE., Washington, DC 20590. 

FOR FURTHER INFORMATION CONTACT: Rao 

Edupuganti, Aviation Safety Engineer, 

Regulations & Policy Section, Rotorcraft 

Standards Branch, FAA, 10101 

Hillwood Pkwy., Fort Worth, Texas 

76177; telephone (817) 222–5110; email 

rao.edupuganti@faa.gov. 

SUPPLEMENTARY INFORMATION: 

Discussion 

On March 14, 2017, at 82 FR 13565, 

the Federal Register published our 

notice of proposed rulemaking (NPRM), 

which proposed to amend 14 CFR part 

39 by adding an AD that would apply 

to Airbus Helicopters (formerly 

Eurocopter France) Model EC225LP 

helicopters. The NPRM proposed to 

require replacing the EMLUB glycol 

pump, the air and glycol pressure 

switches, and the MGB lubrication card, 

and modifying and re-identifying the 

helicopter wiring harness. The NPRM 

also proposed testing the function of the 

EMLUB and electrical systems and 

revising the Emergency Procedures 

section of the RFM. Lastly, the NPRM 

proposed to prohibit installing certain 

part-numbered EMLUB glycol pumps, 

air-pressure switches, glycol pressure 

switches and electronic boards on any 

helicopter. The proposed requirements 

were intended to prevent a false EMLUB 

warning. This condition when 

associated with a loss of the MGB oil 

pressure could result in an unnecessary 

emergency landing or ditching. 


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