52832 Federal Register / Vol. 82, No. 219 / Wednesday, November 15, 2017 / Rules and Regulations 

(d) Subject 

Joint Aircraft System Component (JASC) 

Code 7531, Compressor bleed governor. 

(e) Unsafe Condition 

This AD was prompted by an engine fire 

that occurred as a result of malfunctions 

related to the operability bleed valve (OBV). 

We are issuing this AD to prevent failure of 

the OBV. The unsafe condition, if not 

corrected, could result in failure of the OBV, 

engine fire, and damage to the airplane. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Required Actions 

(1) Inspect the bleed air manifold link rod 

assemblies and the OBV supply, return, and 

drain fuel fittings within 500 flight hours 

after the effective date of this AD. 

(2) Use the Accomplishment Instructions, 

paragraph 3.B., in GE Service Bulletin (SB) 

CF34–8C–AL S/B 75–0019 Revision 01, dated 

October 24, 2017, to do the inspection. 

Replace parts that fail this inspection 

according to the following criteria: 

(i) Replace any OBV that fails the 

inspection with a part eligible for installation 

before further flight. 

(ii) Replace any additional hardware that 

fails inspection within 50 flight cycles. The 

engine can be returned to service each day 

for up to the 50 flight cycles if the OBV rosan 

rings and fittings are examined each day for 

fuel leaks and looseness based on the criteria 

in Table 1 of GE SB CF34–8C–AL S/B 75– 

0019 Revision 01, dated October 24, 2017. 

(3) The reporting instructions in 

paragraphs 3.B.(3), 3.B.(5)(e), 3.B.(6)(e), and 

3.B.(8) of GE SB CF34–8C–AL S/B 75–0019 

Revision 01, dated October 24, 2017, are not 

required by this AD. 

(h) Credit for Previous Actions 

You may take credit for the actions that are 

required by paragraph (g) of this AD if you 

performed these actions before the effective 

date of this AD using GE CF34–8C SB 75– 

0019 R00, dated August 4, 2017. 

(i) Alternative Methods of Compliance 

(AMOCs) 

(1) The Manager, ECO 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 (j) of this AD. You 

may email your request to: ANE-AD-AMOC@

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. 

(j) Related Information 

For more information about this AD, 

contact John Frost, Aerospace Engineer, ECO 

Branch, FAA, 1200 District Avenue, 

Burlington, MA 01803; phone: 781–238– 

7754; fax: 781–238–7199; email: john.frost@

faa.gov. 

(k) 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) General Electric Company (GE) Service 

Bulletin CF34–8C–AL S/B 75–0019 Revision 

01, dated October 24, 2017. 

(ii) Reserved. 

(3) For GE service information identified in 

this AD, contact General Electric Company, 

GE-Aviation, Room 285, 1 Neumann Way, 

Cincinnati, OH 45215, phone: 513–552–3272; 

fax: 513–552–3329; email: geae.aoc@ge.com. 

(4) You may view this service information 

at FAA, FAA, Engine & Propeller Standards 

Branch, 1200 District Avenue, Burlington, 

MA. For information on the availability of 

this material at the FAA, call 781–238–7125. 

(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 Burlington, Massachusetts, on 

November 9, 2017. 

Robert J. Ganley, 

Manager, Engine and Propeller Standards 

Branch, Aircraft Certification Service. 

[FR Doc. 2017–24700 Filed 11–14–17; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2017–0710; Product 

Identifier 2017–NM–019–AD; Amendment 

39–19098; AD 2017–23–04] 

RIN 2120–AA64 

Airworthiness Directives; Airbus 

Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Final rule. 

SUMMARY: We are adopting a new 

airworthiness directive (AD) for certain 

Airbus Model A300 B4–600R series 

airplanes; Model A300 B4–603, B4–620, 

and B4–622 airplanes; Model A300 C4– 

605R Variant F airplanes; and Model 

A300 F4–605R airplanes. This AD was 

prompted by a determination that the 

top stringer joints at rib 18 are an area 

of uniform stress distribution, which 

indicates that cracks may develop in 

adjacent stringers at the same time. This 

AD requires an inspection of the upper 

wing skin and top stringer joints, and 

modification of the stringer joint 

couplings if necessary. We are issuing 

this AD to address the unsafe condition 

on these products. 

DATES: This AD is effective December 

20, 2017. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication listed in this AD 

as of December 20, 2017. 

ADDRESSES: For service information 

identified in this final rule, contact 

Airbus SAS, Airworthiness Office— 

EAW, 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. 

It is also available on the Internet at 

http://www.regulations.gov by searching 

for and locating Docket No. FAA–2017– 

0710. 

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– 

0710; 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 street address for 

the Docket Office (telephone 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: Dan 

Rodina, Aerospace Engineer, 

International Section, Transport 

Standards Branch, FAA, 1601 Lind 

Avenue SW., Renton, WA 98057–3356; 

telephone 425–227–2125; fax 425–227– 

1149. 

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 Airbus Model A300 B4– 

600R series airplanes; Model A300 B4– 

603, B4–620, and B4–622 airplanes; 


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Federal Register / Vol. 82, No. 219 / Wednesday, November 15, 2017 / Rules and Regulations 52833 

Model A300 C4–605R Variant F 

airplanes; and Model A300 F4–605R 

airplanes. The NPRM published in the 

Federal Register on July 27, 2017 (82 FR 

34885) (‘‘the NPRM’’). The NPRM was 

prompted by a determination that the 

top stringer joints at rib 18 are an area 

of uniform stress distribution, which 

indicates that cracks may develop in 

adjacent stringers at the same time. The 

NPRM proposed to require an 

inspection of the upper wing skin and 

top stringer joints, and modification of 

the stringer joint couplings if necessary. 

We are issuing this AD to detect and 

correct damage (including cracking) at 

the stringer joints, which could reduce 

the structural integrity of the wing. 

The European Aviation Safety Agency 

(EASA), which is the Technical Agent 

for the Member States of the European 

Union, has issued EASA AD 2017–0023, 

dated February 10, 2017 (referred to 

after this as the Mandatory Continuing 

Airworthiness Information, or ‘‘the 

MCAI’’), to correct an unsafe condition 

for certain Airbus Model A300 B4–600R 

series airplanes; Model A300 B4–603, 

B4–620, and B4–622 airplanes; Model 

A300 C4–605R Variant F airplanes; and 

Model A300 F4–605R airplanes. The 

MCAI states: 

In response to the FAA Part 26 rule change 

concerning Widespread Fatigue Damage 

(WFD), all wing structural items of the A300– 

600 design deemed potentially susceptible to 

WFD were assessed. The top stringer joints 

at Rib 18 were highlighted as an area of 

uniform stress distribution, indicating that 

cracks may develop in adjacent stringers at 

the same time which is known as Multi 

Element Damage (MED). Each affected 

stringer joint consists of three main load 

transferring parts: An overlapping flange, two 

straps attached through the stringer web and 

a strap on the top flange. All the components 

of the joint are attached with fasteners. The 

fastener holes were the subject of a MED 

WFD analysis, which showed that cracking 

could occur from a number of the holes in 

the joint on stringers 11, 12, 13, 14, 15, 16, 

17, and 18. 

This condition, if not detected and 

corrected, could reduce the structural 

integrity of the wing. 

Prompted by the conclusion of the WFD 

analysis, Airbus issued Service Bulletin (SB) 

A300–57–6118 to provide modification 

instructions. The modification will both relife via oversizing and inspect via nondestructive test a defined number of stringer 

joint fastener holes at Rib 18. This 

modification will delay the onset of cracking 

at the stringer joint, providing it is completed 

at the specified time and will delay the 

requirement for subsequent inspection. 

For the reasons described above, this 

[EASA] AD requires a detailed visual 

inspection (DVI) [for damage, including 

cracking] of the upper wing skin and the top 

stringer joints at Rib 18, [and corrective 

action if necessary] and modification of the 

stringer joint couplings at Rib 18, on both 

wings [as applicable]. 

The modification includes a related 

investigative action, i.e., a special 

detailed (roto-probe) inspection for 

damage, including cracking, of the 

fastener holes in the upper wing skin, 

and corrective action if necessary. 

Corrective actions include repairing any 

damage. 

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– 

0710. 

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. 

Request To Update the Costs of 

Compliance 

FedEx supported the intent of the 

NPRM, but requested that we update the 

parts cost in the Costs of Compliance 

section of the proposed AD to reflect the 

cost of two parts kits. FedEx noted that 

the proposed AD listed the parts cost for 

only one kit. FedEx pointed out that 

operators may need to modify both 

wings and could therefore need two 

parts kits per airplane. 

We agree with the commenter’s 

request. We have revised the Costs of 

Compliance section of this final rule to 

reflect two parts kits, each costing 

$4,770. 

Request To Fix a Typographical Error 

Airbus requested that we correct a 

reference to ‘‘Airbus Model A300 C4– 

605 Variant F’’ airplanes in paragraph 

(g)(2) of the proposed AD. The correct 

model name is ‘‘A300 C4–605R Variant 

F’’ airplanes. 

We agree with the commenter’s 

request. We have corrected the 

typographical error in 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 

Airbus has issued Service Bulletin 

A300–57–6118, Revision 01, dated 

January 31, 2017. This service 

information describes procedures for an 

inspection of the upper wing skin and 

top stringer joints at rib 18, and 

modification of the stringer joint 

couplings. 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 65 

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 

Inspection and modification ................. 37 work-hours × $85 per hour = 

$3,145.

Up to $9,540 ......... Up to $12,685 ....... Up to $824,525. 

We have received no definitive data 

that will allow us to provide cost 

estimates for certain on-condition 

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. 


sradovich on DSK3GMQ082PROD with RULES
52834 Federal Register / Vol. 82, No. 219 / Wednesday, November 15, 2017 / Rules and Regulations 

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 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 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. 

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): 

2017–23–04 Airbus: Amendment 39–19098; 

Docket No. FAA–2017–0710; Product 

Identifier 2017–NM–019–AD. 

(a) Effective Date 

This AD is effective December 20, 2017. 

(b) Affected ADs 

None. 

(c) Applicability 

This AD applies to Airbus Model A300 B4– 

605R, B4–622R, B4–603, C4–605R Variant F, 

B4–620, B4–622, and F4–605R airplanes, 

certificated in any category, all serial 

numbers except Model A300 F4–605R 

airplanes that have embodied Airbus 

modification 12699 in production. 

(d) Subject 

Air Transport Association (ATA) of 

America Code 57, Wings. 

(e) Reason 

This AD was prompted by a determination 

that the top stringer joints at rib 18 are an 

area of uniform stress distribution, which 

indicates that cracks may develop in adjacent 

stringers at the same time. We are issuing this 

AD to detect and correct damage (including 

cracking) at the stringer joints, which could 

reduce the structural integrity of the wing. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Definitions 

For the purposes of this AD, the definitions 

in paragraphs (g)(1) through (g)(5) of this AD 

apply. 

(1) Group 1 airplanes are defined as Airbus 

Model A300 B4–603, B4–605R, B4–620, B4– 

622, and B4–622R airplanes. 

(2) Group 2 airplanes are defined as Airbus 

Model A300 C4–605R Variant F and F4–605R 

(if in pre-modification 12699 configuration) 

airplanes. 

(3) Short range (SR) is defined as airplanes 

with an average flight time of less than 1.5 

flight hours per flight cycle. 

(4) Long range (LR) is defined as airplanes 

with an average flight time equal to or higher 

than 1.5 flight hours per flight cycle. 

(5) For determining the ‘‘short range’’ and 

‘‘long range’’ airplanes, the average flight 

time is the total accumulated flight hours, 

counted from take-off to touch-down, divided 

by the total accumulated flight cycles at the 

effective date of this AD. 

(h) Inspection and Modification 

Not before exceeding the applicable lower 

thresholds as specified in table 1 to 

paragraph (h) of this AD, and within the 

compliance times specified in paragraphs 

(h)(1), (h)(2), (h)(3), and (h)(4) of this AD, as 

applicable: Accomplish a detailed visual 

inspection for damage (including cracking) of 

the upper wing skin and top stringer joints 

at rib 18 on both wings, do all applicable 

corrective actions, and do the applicable 

modification, including related investigative 

and corrective actions, in accordance with 

the Accomplishment Instructions of Airbus 

Service Bulletin A300–57–6118, Revision 01, 

dated January 31, 2017, except as required by 

paragraph (i) of this AD. Do all applicable 

modifications, related investigative actions, 

and corrective actions before further flight. 

(1) For Group 1, LR airplanes: Inspect at 

the time specified in paragraph (h)(1)(i) or 

(h)(1)(ii) of this AD, whichever occurs later. 

(i) Before exceeding 32,500 flight cycles or 

70,300 flight hours, whichever occurs first 

since first flight of the airplane. 

(ii) Within 700 flight cycles, 1,500 flight 

hours, or 12 months, whichever occurs first 

after the effective date of this AD. 

(2) For Group 1, SR airplanes: Inspect at 

the time specified in paragraphs (h)(2)(i) or 

(h)(2)(ii) of this AD, whichever occurs later. 

(i) Before exceeding 35,100 flight cycles or 

52,600 flight hours, whichever occurs first 

since the first flight of the airplane. 

(ii) Within 700 flight cycles or 1,000 flight 

hours, or 12 months, whichever occurs first 

after the effective date of this AD. 

(3) For Group 2, LR airplanes: Inspect 

before exceeding 35,000 flight cycles or 

75,700 flight hours, whichever occurs first 

since the first flight of the airplane. 

(4) For Group 2, SR airplanes: Inspect 

before exceeding 37,800 flight cycles or 

56,700 flight hours, whichever occurs first 

since the first flight of the airplane. 

TABLE 1 TO PARAGRAPH (h) OF THIS

AD—COMPLIANCE TIME LOWER

THRESHOLDS

Applicable 

airplanes 

Compliance time flight cycles 

(FC) or flight hours (FH), 

whichever occurs first since 

first flight of the airplane 

Group 1, LR Not before exceeding 30,900 FC or 

66,700 FH. 

Group 1, SR Not before exceeding 28,700 FC or 

43,000 FH. 

Group 2, LR Not before exceeding 28,600 FC or 

61,700 FH. 

Group 2, SR Not before exceeding 34,400 FC or 

51,600 FH. 

(i) Service Information Exception 

Where Airbus Service Bulletin A300–57– 

6118, Revision 01, dated January 31, 2017, 

specifies to contact Airbus for appropriate 

action, and specifies that action as ‘‘RC’’ 

(Required for Compliance): Before further 

flight, accomplish corrective actions in 

accordance with the procedures specified in 

paragraph (k)(2) of this AD. 

(j) Credit for Previous Actions 

This paragraph provides credit for actions 

required by paragraph (h) of this AD, if those 

actions were performed before the effective 

date of this AD using Airbus Service Bulletin 

A300–57–6118, dated June 30, 2015. 

(k) Other FAA AD Provisions 

The following provisions also apply to this 

AD: 

(1) Alternative Methods of Compliance 

(AMOCs): The Manager, International 


sradovich on DSK3GMQ082PROD with RULES
Federal Register / Vol. 82, No. 219 / Wednesday, November 15, 2017 / Rules and Regulations 52835 

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 (l)(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 

Airbus’s EASA Design Organization 

Approval (DOA). If approved by the DOA, 

the approval must include the DOAauthorized signature. 

(3) 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. 

(l) Related Information 

(1) Refer to Mandatory Continuing 

Airworthiness Information (MCAI) EASA AD 

2017–0023, dated February 10, 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–2017–0710. 

(2) For more information about this AD, 

contact Dan Rodina, Aerospace Engineer, 

International Section, Transport Standards 

Branch, FAA, 1601 Lind Avenue SW., 

Renton, WA 98057–3356; telephone 425– 

227–2125; fax 425–227–1149. 

(3) Service information identified in this 

AD that is not incorporated by reference is 

available at the addresses specified in 

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

(m) 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 A300–57–6118, 

Revision 01, dated January 31, 2017. 

(ii) Reserved. 

(3) For service information identified in 

this AD, contact Airbus SAS, Airworthiness 

Office—EAW, 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. 

(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/ibrlocations.html. 

Issued in Renton, Washington, on 

November 3, 2017. 

Jeffrey E. Duven, 

Director, System Oversight Division, Aircraft 

Certification Service. 

[FR Doc. 2017–24501 Filed 11–14–17; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2017–0715; Product 

Identifier 2017–NM–073–AD; Amendment 

39–19096; AD 2017–23–02] 

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 737–200, 

–200C, –300, –400, and –500 series 

airplanes. This AD was prompted by an 

evaluation by the design approval 

holder (DAH) indicating that the 

fuselage crown skin panels are subject 

to widespread fatigue damage (WFD). 

This AD requires repetitive inspections, 

replacement, and applicable oncondition actions for certain fuselage 

crown skin panels. We are issuing this 

AD to address the unsafe condition on 

these products. 

DATES: This AD is effective December 

20, 2017. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication listed in this AD 

as of December 20, 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 90740–5600; 

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–2017– 

0715. 

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– 

0715; 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 final rule, 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: 

Jennifer Tsakoumakis, Aerospace 

Engineer, Airframe Section, FAA, Los 

Angeles ACO Branch, 3960 Paramount 

Boulevard, Lakewood, CA 90712–4137; 

phone: 562–627–5264; fax: 562–627– 

5210; email: Jennifer.Tsakoumakis@

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 737–200, –200C, –300, –400, and 

–500 series airplanes. The NPRM 

published in the Federal Register on 

August 10, 2017 (82 FR 37366). The 

NPRM was prompted by an evaluation 

by the DAH indicating that the fuselage 

crown skin panels are subject to WFD. 

The NPRM proposed to require 

repetitive inspections, replacement, and 

applicable on-condition actions for 

certain fuselage crown skin panels. 

We are issuing this AD to detect and 

correct cracking in the fuselage crown 

skin panels. Multiple adjacent cracks in 

the fuselage crown skin could link up 

and lead to decompression or loss of 

structural integrity of the airplane. 


sradovich on DSK3GMQ082PROD with RULES