56158 Federal Register / Vol. 82, No. 227 / Tuesday, November 28, 2017 / Rules and Regulations 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) For Group 1 Airplanes: Inspection and 

Corrective Actions 

For airplanes identified as Group 1 in 

Boeing Alert Service Bulletin 737–57A1329, 

dated January 16, 2017: Within 120 days after 

the effective date of this AD, do an inspection 

for cracking of the upper aft skin of the 

wings, and do all applicable corrective 

actions, using a method approved in 

accordance with the procedures specified in 

paragraph (j) of this AD. 

(h) For Groups 2 and 3 Airplanes: Repetitive 

Inspections and Repair 

For Groups 2 and 3 airplanes identified in 

Boeing Alert Service Bulletin 737–57A1329, 

dated January 16, 2017: At the applicable 

time specified in paragraph 1.E., 

‘‘Compliance,’’ of Boeing Alert Service 

Bulletin 737–57A1329, dated January 16, 

2017, except as required by paragraph (i) of 

this AD, do the applicable inspection for 

cracking of the upper aft skin of the wings 

from wing buttock line (WBL) 159 to WBL 

220, in accordance with the Work 

Instructions of Boeing Alert Service Bulletin 

737–57A1329, dated January 16, 2017. If any 

cracking is found, repair before further flight, 

in accordance with the procedures specified 

in paragraph (j) of this AD. Repeat the 

inspection thereafter at the applicable time 

specified in paragraph 1.E., ‘‘Compliance,’’ of 

Boeing Alert Service Bulletin 737–57A1329, 

dated January 16, 2017. 

(i) Exceptions to the Service Information 

(1) Where Boeing Alert Service Bulletin 

737–57A1329, dated January 16, 2017, 

specifies a compliance time ‘‘after the 

original issue date of this service bulletin,’’ 

paragraph (h) of this AD requires compliance 

within the specified compliance time after 

the effective date of this AD. 

(2) Although Boeing Alert Service Bulletin 

737–57A1329, dated January 16, 2017, 

specifies to contact Boeing for repair 

instructions, and specifies that action as 

‘‘RC’’ (Required for Compliance), this AD 

requires repair in accordance with the 

procedures specified in paragraph (j) of this 

AD. 

(j) Alternative Methods of Compliance 

(AMOCs) 

(1) The Manager, Los Angeles 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 (k) of this 

AD. Information may be emailed to: 9-ANMLAACO-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, Los Angeles 

ACO Branch, 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) Except as required by paragraph (i)(2) 

of this AD: For service information that 

contains steps that are labeled as RC, the 

provisions of paragraphs (j)(4)(i) and (j)(4)(ii) 

of this AD apply. 

(i) The steps labeled as RC, including 

substeps under an RC step and any figures 

identified in an RC step, must be done to 

comply with the AD. If a step or substep is 

labeled ‘‘RC Exempt,’’ then the RC 

requirement is removed from that step or 

substep. An AMOC is required for any 

deviations to RC steps, including substeps 

and identified figures. 

(ii) Steps not labeled 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 RC steps, 

including substeps and identified figures, can 

still be done as specified, and the airplane 

can be put back in an airworthy condition. 

(k) Related Information 

For more information about this AD, 

contact Payman Soltani, Aerospace Engineer, 

Airframe Section, FAA, Los Angeles ACO 

Branch, 3960 Paramount Boulevard, 

Lakewood, CA 90712–4137; phone: 562–627– 

5313; fax: 562–627–5210; email: 

payman.soltani@faa.gov. 

(l) 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– 

57A1329, dated January 16, 2017. 

(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/ibrlocations.html. 

Issued in Renton, Washington, on 

November 15, 2017. 

Chris Spangenberg, 

Acting Director, System Oversight Division, 

Aircraft Certification Service. 

[FR Doc. 2017–25379 Filed 11–27–17; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2017–0478; Product 

Identifier 2016–NM–174–AD; Amendment 

39–19087; AD 2017–22–07] 

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 A319 series airplanes; 

Model A320–211, –212, –214, –231, 

–232, and –233 airplanes; and Model 

A321–111, –112, –131, –211, –212, 

–213, –231, and –232 airplanes. This AD 

was prompted by a report of cracks on 

frame forks and outer skin on the 

forward and aft cargo compartment 

doors. This AD requires repetitive 

inspections of the frame forks, and 

corrective actions if necessary. This AD 

also includes optional modifications 

that constitute terminating action. We 

are issuing this AD to address the unsafe 

condition on these products. 

DATES: This AD is effective January 2, 

2018. 

The Director of the Federal Register 

approved the incorporation by reference 

of certain publications listed in this AD 

as of January 2, 2018. 

ADDRESSES: For service information 

identified in this final rule, contact 

Airbus, Airworthiness Office—EIAS, 

1 Rond Point Maurice Bellonte, 31707 

Blagnac Cedex, France; telephone: +33 5 

61 93 36 96; fax: +33 5 61 93 44 51; 

email: account.airworth-eas@

airbus.com; Internet: http://

www.airbus.com. You may view this 

referenced service information at the 

FAA, Transport Standards Branch, 1601 

Lind Avenue SW., Renton, WA. For 

information on the availability of this 

material at the FAA, call 425–227–1221. 

It is also available on the Internet at 

http://www.regulations.gov by searching 

for and locating Docket No. FAA–2017– 

0478. 


jstallworth on DSKBBY8HB2PROD with RULES
Federal Register / Vol. 82, No. 227 / Tuesday, November 28, 2017 / Rules and Regulations 56159 

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– 

0478; 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: 

Sanjay Ralhan, Aerospace Engineer, 

International Section, Transport 

Standards Branch, FAA, 1601 Lind 

Avenue SW., Renton, WA 98057–3356; 

telephone: 425–227–1405; fax: 425– 

227–1149. 

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 A319 

series airplanes; Model A320–211, –212, 

–214, –231, –232, and –233 airplanes; 

and Model A321–111, –112, –131, –211, 

–212, –213, –231, and –232 airplanes. 

The NPRM published in the Federal 

Register on May 22, 2017 (82 FR 23160) 

(‘‘the NPRM’’). The NPRM was 

prompted by a report of cracks on frame 

forks and outer skin on the forward and 

aft cargo compartment doors. The 

NPRM proposed to require repetitive 

inspections of the frame forks, and 

corrective actions if necessary. The 

NPRM also included optional 

modifications that constitute 

terminating action. We are issuing this 

AD to detect and correct cracks on the 

frame forks and outer skin on the 

forward and aft cargo compartment 

doors, which could lead to reduced 

structural integrity and failure of the 

cargo compartment door, possible 

decompression of the airplane, and 

injury to occupants. 

The European Aviation Safety Agency 

(EASA), which is the Technical Agent 

for the Member States of the European 

Union, has issued EASA AD 2016–0187, 

dated September 19, 2016 (referred to 

after this as the Mandatory Continuing 

Airworthiness Information, or ‘‘the 

MCAI’’), to correct an unsafe condition 

for certain Airbus Model A319 series 

airplanes; Model A320–211, –212, –214, 

–231, –232, and –233 airplanes; and 

Model A321–111, –112, –131, –211, 

–212, –213, –231, and –232 airplanes. 

The MCAI states: 

During full scale fatigue test, cracks have 

been found on frame forks and outer skin on 

forward and aft cargo doors. 

To improve the fatigue behaviour of the 

frame forks, Airbus introduced modification 

(mod) 22948 in production, and issued 

inspection Service Bulletin (SB) A320–52– 

1032 and modification SB A320–52–1042, 

both recommended. 

Since those actions were taken, further 

improved cargo compartment doors have 

been introduced in production through 

Airbus mod 26213, on aeroplanes having 

[manufacturer serial number] MSN 0759 and 

up. This modification, which is not available 

for in-service retrofit, also includes 

provisions that exclude installation of premod 26213 aft and forward compartment 

cargo doors on an aeroplane. 

In the frame of the Widespread Fatigue 

Damage (WFD) study, it has been determined 

that repetitive inspections are necessary for 

aft and forward cargo compartment doors on 

aeroplanes that do not (or no longer) embody 

mod 22948 (or SB A320–52–1042), and those 

that do not embody mod 26213. Failure to 

detect cracks would reduce the cargo door 

structural integrity. 

This condition, if not detected and 

corrected, could lead to cargo door failure, 

possibly resulting in decompression of the 

aeroplane and injury to occupants. 

To address this unsafe condition, Airbus 

issued SB A320–52–1171 to provide 

inspection instructions. This SB was later 

revised to correct the list of affected cargo 

doors. Airbus also issued SB A320–52–1170, 

introducing a door modification which 

constitutes terminating action for the 

repetitive special detailed inspection (SDI). 

For the reason described above, this 

[EASA] AD requires accomplishment of 

repetitive SDI by rototest of all frame forks 

in beam 4 area to detect cracks, and, 

depending on findings, accomplishment of 

applicable corrective action(s) [repair or 

replacement]. This AD also provides an 

optional [modification that constitutes] 

terminating action for the repetitive SDI 

required by this [EASA] AD. 

One of the optional modifications 

includes related investigative and 

corrective actions. The related 

investigative action is a high frequency 

eddy current (HFEC) rotating probe 

inspection for cracks, and the corrective 

action is a repair. 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–2017–0478. 

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. 

Requests To Refer to Updated Service 

Information 

Delta Air Lines and United Airlines 

requested that we revise the NPRM to 

refer to Airbus Service Bulletin A320– 

52–1171, Revision 02, dated April 10, 

2017. United Airlines mentioned that 

Airbus has made number of updates and 

clarifications in Airbus Service Bulletin 

A320–52–1171, Revision 02, dated April 

10, 2017. Additionally, United Airlines 

pointed out that EASA AD 2016–0187, 

dated September 19, 2016, quoted in the 

‘‘Discussion’’ section of the NPRM, 

allows for use of later approved 

revisions. 

We agree with the commenters for the 

reasons provided. We have revised this 

AD to refer to Airbus Service Bulletin 

A320–52–1171, Revision 02, dated April 

10, 2017. We have also redesignated 

paragraph (m) (of the proposed AD) as 

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

paragraph (m)(2) to provide credit for 

actions done before the effective date of 

this AD, if those actions were done 

using Airbus Service Bulletin A320–52– 

1171, Revision 01, dated September 5, 

2016. 

Request To Clarify That Certain Service 

Information Cancels the Requirements 

of Certain Other Service Information 

United Airlines requested that we 

clarify that Airbus Service Bulletin 

A320–52–1171, Revision 02, dated April 

10, 2017, cancels the requirements of 

Airbus Service Bulletin A320–52–1032. 

The commenter indicated that a 

statement regarding this subject would 

clarify the required actions for 

operators. The commenter also pointed 

out that a statement is listed in Airbus 

Service Bulletin A320–52–1171, 

Revision 02, dated April 10, 2017, that 

specifies the cancellation of the 

requirements of Airbus Service Bulletin 

A320–52–1032. 

We agree to clarify. Airbus Service 

Bulletin A320–52–1171, Revision 02, 

dated April 10, 2017, does include a 

statement indicating that the actions 

specified in Airbus Service Bulletin 

A320–52–1171, Revision 02, dated April 

10, 2017, cancel the actions specified in 

Airbus Service Bulletin A320–52–1032. 

However, the actions specified in 

Airbus Service Bulletin A320–52–1032 

are not required by any AD, and 

therefore, we do not specifically address 

Airbus Service Bulletin A320–52–1032 

in this AD (except for the compliance 

time reference in paragraph (h)(4) of this 

AD). We have not changed this AD in 

this regard. 


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56160 Federal Register / Vol. 82, No. 227 / Tuesday, November 28, 2017 / Rules and Regulations 

Request To Update the NPRM To 

Include Modifications 22948 and 26213 

Delta Air Lines requested that we 

revise paragraphs (c) and (g) of the 

proposed AD to refer to Modifications 

22948 and 26213. Specifically, Delta Air 

Lines requested that we include 

information that elaborates on the 

specific airplanes affected by the NPRM. 

Delta Air Lines pointed out that EASA 

AD 2016–0187, dated September 19, 

2016, quoted in the ‘‘Discussion’’ 

section of the NPRM, and Airbus 

Service Bulletin A320–52–1042, 

Revision 2, dated January 14, 1997, 

already refer to the modifications. Delta 

Air Lines also mentioned that it has 40 

forward and aft cargo compartment 

doors affected by the NPRM, which are 

pre-Modifications 22948 and 26213 and 

under manufacturer serial number 0758. 

We disagree to refer to Modifications 

22948 and 26213 in paragraphs (c) and 

(g) of this AD; however, we agree that 

clarification is necessary. The 

applicability of this AD refers to the 

affected models having manufacturer 

serial numbers through 0758 inclusive; 

all airplanes having these serial 

numbers are affected by the identified 

unsafe condition. Airbus introduced 

modification 22948 in production, and 

issued Airbus Service Bulletin A320– 

52–1032 for recommended inspections 

and Airbus Service Bulletin A320–52– 

1042 for recommended modification 

22948. Since that service information 

was issued, Airbus has introduced 

further improved forward and aft cargo 

compartment doors (modification 

26213) in production on airplanes 

having manufacturer serial number 0759 

and above; however, this modification is 

unavailable for in-service retrofit. 

Modification 26213 includes provisions 

that prohibit installation of earlier 

configurations of forward or aft cargo 

compartment doors (pre-modification 

26213). Airplanes having manufacturer 

serial numbers 0759 and subsequent 

have modification 26213 installed in 

production. We have not changed this 

AD in this regard. 

Request To Include Instructions for 

Rotable Parts 

Delta Air Lines requested that we 

include instructions for rotable parts in 

paragraph (g) of the proposed AD. The 

commenter mentioned that forward or 

aft cargo compartment doors could be 

migrated from manufacturer serial 

number 0759 and above to airplanes 

that are affected, and asked if those 

airplanes are still affected. The 

commenter also requested that Airbus 

provide a list of manufacturer serial 

numbers that are affected by the 

proposed AD. 

We partially agree with the 

commenter. Airplanes originally 

delivered with the affected doors are 

subject to the requirements of this AD. 

Paragraph (h) of this AD only requires 

actions on affected doors. It is not 

physically possible to install the 

affected doors on serial numbers 0759 

and above; therefore, parts rotability 

does not need to be addressed in this 

AD. 

In addition, paragraph (n) of this AD 

provides a parts installation limitation 

for the forward or aft cargo compartment 

doors for the airplanes identified in 

paragraph (c) of this AD. We have no 

practical method to provide a 

manufacturer serial number list of 

affected airplanes on which a nonaffected door might have been installed 

or to predict an airplane configuration 

in the worldwide fleet. Therefore, we 

have not changed this AD in this regard. 

Request To Clarify Optional 

Terminating Actions 

United Airlines requested that we 

clarify the optional terminating actions 

specified in paragraph (j) of the 

proposed AD. The commenter requested 

we include a statement that specifies 

modification of all affected doors of an 

airplane in accordance with the 

requirements of paragraphs (j)(1), (j)(2), 

or (j)(3) of this AD constitutes 

terminating action. The commenter 

pointed out that EASA AD 2016–0187, 

dated September 19, 2016, quoted in the 

‘‘Discussion’’ section of the NPRM, 

allows for modification of an airplane as 

specified in Airbus Service Bulletin 

A320–52–1042, Revision 2, dated 

January 14, 1997; or Airbus Service 

Bulletin A320–52–1170, dated 

September 5, 2016; and either is 

considered terminating action for the 

repetitive inspections. 

We agree that clarification is 

necessary. We have revised paragraph (j) 

of this AD to include introductory text 

with the statement: ‘‘Modification of all 

affected doors of an airplane in 

accordance with the requirements of 

paragraph (j)(1), (j)(2), or (j)(3) of this AD 

constitutes terminating action . . . .’’ 

Request To Include Compliance Times 

for Optional Terminating Actions 

Mr. Petit requested that we add 

compliance times for the optional 

terminating actions specified in the 

proposed AD. Mr. Petit indicated that 14 

CFR 26.21 might require a mandatory 

terminating action before 56,300 flight 

cycles. Mr. Petit also recommended that 

the optional terminating action not be 

embodied before 21,700 flight cycles. 

We disagree with the commenter’s 

request to include compliance times for 

the optional terminating action 

specified in this AD. 14 CFR 26.21 

mandates the limit of validity (LOV) and 

does not specify compliance times for 

the optional terminating action 

specified in this AD. This AD mandates 

repetitive inspections of the frame forks 

as specified in the service information 

provided by the design approval holder 

(DAH) to meet the LOV. In addition, we 

do not include compliance times for 

optional actions in ADs because doing 

so would make the actions mandatory. 

We intend for the terminating actions in 

this AD to be optional, which aligns 

with the MCAI. 

Regarding the commenter’s 

recommendation to prohibit 

accomplishing the optional terminating 

action before 21,700 flight cycles, the 

commenter provided no substantiation 

for this prohibition. We have received 

no data indicating that the optional 

terminating action should not be 

accomplished before 21,700 flight 

cycles. Therefore, we have not changed 

this AD in this regard. 

Clarification of Exception 

Paragraph (i)(2) of the proposed AD, 

which refers to Airbus Service Bulletin 

A320–52–1170, dated September 5, 

2016, includes an exception as specified 

in paragraph (k) of the proposed AD. 

However, paragraph (k) of the proposed 

AD does not mention Airbus Service 

Bulletin A320–52–1170, dated 

September 5, 2016. We have added 

Airbus Service Bulletin A320–52–1170, 

dated September 5, 2016, to the 

exception specified in paragraph (k) 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 

Airbus has issued the following 

service information. 


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Federal Register / Vol. 82, No. 227 / Tuesday, November 28, 2017 / Rules and Regulations 56161 

• Airbus Service Bulletin A320–52– 

1171, Revision 02, dated April 10, 2017, 

describes procedures for repetitive 

special detailed inspections of all frame 

forks in the beam 4 area of any affected 

door, and corrective actions. 

• Airbus Service Bulletin A320–52– 

1042, Revision 2, dated January 14, 

1997, describes procedures for 

modification of all affected forward and 

aft cargo compartment doors of an 

airplane. 

• Airbus Service Bulletin A320–52– 

1170, dated September 5, 2016, 

describes modification of all affected 

forward and aft cargo compartment 

doors of an airplane, including related 

investigative and corrective actions. 

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 88 

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 

Special detailed inspection ..... 25 work-hours × $85 per hour = $2,125 ................................ $0 $2,125 $187,000 

OPTIONAL ACTIONS

Action Labor cost Parts cost Cost per 

product 

Modification ............................. 24 work-hours × $85 per hour = $2,040 ........................................................... Up to $240 ..... Up to $2,280. 

We have received no definitive data 

that would enable us to provide cost 

estimates for the on-condition repairs 

and replacements 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 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): 

2017–22–07 Airbus: Amendment 39–19087; 

Docket No. FAA–2017–0478; Product 

Identifier 2016–NM–174–AD. 

(a) Effective Date 

This AD is effective January 2, 2018. 

(b) Affected ADs 

None. 

(c) Applicability 

This AD applies to Airbus Model A319– 

111, –112, –113, –114, –115, –131, –132, and 

–133 airplanes; Model A320–211, –212, –214, 

–231, –232, and –233 airplanes; and Model 

A321–111, –112, –131, –211, –212, –213, 

–231, and –232 airplanes, certificated in any 

category, manufacturer serial numbers 

through 0758 inclusive. 

(d) Subject 

Air Transport Association (ATA) of 

America Code 52, Doors. 

(e) Reason 

This AD was prompted by a report of 

cracks on the frame forks and outer skin on 

the forward and aft cargo compartment doors. 

We are issuing this AD to detect and correct 

cracks on the frame forks and outer skin on 

the forward and aft cargo compartment doors, 

which could lead to reduced structural 

integrity and failure of the cargo 

compartment door, possible decompression 

of the airplane, and injury to occupants. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Definition of Affected Door 

For the purpose of this AD, an ‘‘affected 

door’’ is a forward or aft cargo compartment 


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door, having any part number listed in table 

1 to paragraph (g) of this AD, except a cargo 

compartment door on which Airbus Service 

Bulletin A320–52–1042 or Airbus Service 

Bulletin A320–52–1170 is embodied. 

(h) Repetitive Special Detailed Inspection of 

Frame Forks 

At the latest of the compliance times listed 

in paragraphs (h)(1) through (h)(4) of this AD: 

Do a special detailed inspection of all frame 

forks in the beam 4 area of any affected door 

as defined in paragraph (g) of this AD, in 

accordance with the Accomplishment 

Instructions of Airbus Service Bulletin A320– 

52–1171, Revision 02, dated April 10, 2017, 

except as specified in paragraphs (k) and (l) 

of this AD. Repeat the inspection thereafter 

at intervals not to exceed 3,000 flight cycles. 

A review of the airplane delivery or 

maintenance records is acceptable to identify 

any affected door installed on the airplane, 

provided that the cargo compartment door 

part number can be conclusively determined 

from that review. 

(1) Before exceeding 37,500 flight cycles 

since first installation of the door on an 

airplane. 

(2) Within 900 flight cycles after the 

effective date of this AD, without exceeding 

41,950 flight cycles since first installation of 

the door on an airplane. 

(3) Within 50 flight cycles after the 

effective date of this AD, for a door having 

reached or exceeded 41,900 flight cycles 

since first installation on an airplane. 

(4) Within 3,000 flight cycles since the last 

inspection of the door as specified in Airbus 

Service Bulletin A320–52–1032. 

(i) Corrective Actions 

If any crack is found during any inspection 

required by paragraph (h) of this AD, before 

further flight, do all applicable corrective 

actions in accordance with the 

Accomplishment Instructions of Airbus 

Service Bulletin A320–52–1171, Revision 02, 

dated April 10, 2017, except as specified in 

paragraphs (k) and (l) of this AD. 

Accomplishment of applicable corrective 

actions does not constitute terminating action 

for the repetitive inspections. 

(j) Optional Terminating Action 

Modification of all affected doors of an 

airplane in accordance with the requirements 

of paragraph (j)(1), (j)(2), or (j)(3) of this AD, 

constitutes terminating action for the 

repetitive inspections specified in paragraph 

(h) of this AD for that airplane. 

(1) Modification of all affected doors of an 

airplane in accordance with the 

Accomplishment Instructions of Airbus 

Service Bulletin A320–52–1042, Revision 2, 

dated January 14, 1997, constitutes 

terminating action for the repetitive 

inspections specified in paragraph (h) of this 

AD for that airplane, provided that, after 

modification, no affected door is re-installed 

on that airplane. 

(2) Modification of all affected doors of an 

airplane including accomplishment of all 

applicable related investigative and 

corrective actions in accordance with the 

Accomplishment Instructions of Airbus 

Service Bulletin A320–52–1170, dated 

September 5, 2016, except as specified in 

paragraph (k) of this AD, constitutes 

terminating action for the repetitive 

inspections specified in paragraph (h) of this 

AD for that airplane, provided that, after 

modification, no affected door is re-installed 

on that airplane. 

(3) Modification of all affected doors on an 

airplane, in case of finding damaged frame 

forks, as specified in an Airbus Repair Design 

Approval Sheet (RDAS), and done in 

accordance with 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); 

constitutes terminating action for the 

repetitive inspection specified in paragraph 

(h) of this AD for that airplane, provided that, 

after modification, no affected door is reinstalled on that airplane. 

(k) Exception to Service Information 

Where Airbus Service Bulletin A320–52– 

1170, dated September 5, 2016; or Airbus 

Service Bulletin A320–52–1171, Revision 02, 

dated April 10, 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 

(o)(2) of this AD. 


jstallworth on DSKBBY8HB2PROD with RULESER28NO17.017</GPH>
Federal Register / Vol. 82, No. 227 / Tuesday, November 28, 2017 / Rules and Regulations 56163 

(l) No Reporting Requirement 

Although Airbus Service Bulletin A320– 

52–1171, Revision 02, dated April 10, 2017, 

specifies to submit certain information to the 

manufacturer, and specifies that action as 

‘‘RC,’’ this AD does not include that 

requirement. 

(m) Credit for Previous Actions 

(1) This paragraph provides credit for the 

actions required by paragraphs (h) and (i) of 

this AD, if those actions were performed 

before the effective date of this AD using 

Airbus Service Bulletin A320–52–1171, 

dated October 29, 2015, provided that it can 

be conclusively determined that any part 

number D52371000018 was also inspected as 

specified in paragraph (h) of this AD. 

(2) This paragraph provides credit for the 

actions required by paragraphs (h) and (i) of 

this AD, if those actions were performed 

before the effective date of this AD using 

Airbus Service Bulletin A320–52–1171, 

Revision 01, dated September 5, 2016. 

(n) Parts Installation Limitation 

As of the effective date of this AD, no 

person may install, on any airplane, an 

affected door specified in paragraph (g) of 

this AD, unless it has been inspected in 

accordance with the requirements of 

paragraph (h) of this AD and all applicable 

corrective actions have been done in 

accordance with paragraph (i) of this AD. 

(o) Other FAA AD Provisions 

The following provisions also apply to this 

AD: 

(1) Alternative Methods of Compliance 

(AMOCs): The Manager, International 

Section, Transport Standards Branch, FAA, 

has the authority to approve AMOCs for this 

AD, if requested using the procedures found 

in 14 CFR 39.19. In accordance with 14 CFR 

39.19, send your request to your principal 

inspector or local Flight Standards District 

Office, as appropriate. If sending information 

directly to the International Section, send it 

to the attention of the person identified in 

paragraph (p)(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’s EASA DOA. If approved by the 

DOA, the approval must include the DOAauthorized signature. 

(3) Required for Compliance (RC): Except 

as specified in paragraphs (k) and (l) 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. 

(p) Related Information 

(1) Refer to Mandatory Continuing 

Airworthiness Information (MCAI) EASA AD 

2016–0187, dated September 19, 2016, for 

related information. This MCAI may be 

found in the AD docket on the Internet at 

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

and locating Docket No. FAA–2017–0478. 

(2) For more information about this AD, 

contact Sanjay Ralhan, Aerospace Engineer, 

International Section, Transport Standards 

Branch, FAA, 1601 Lind Avenue SW., 

Renton, WA 98057–3356; telephone: 425– 

227–1405; fax: 425–227–1149. 

(3) Service information identified in this 

AD that is not incorporated by reference is 

available at the addresses specified in 

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

(q) 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 A320–52–1042, 

Revision 2, dated January 14, 1997 (pages 5, 

9, and 19 through 22 of this document are 

identified as Revision 1, dated November 22, 

1993). 

(ii) Airbus Service Bulletin A320–52–1170, 

dated September 5, 2016, including 

Appendices 01 and 02, dated September 5, 

2016. 

(iii) Airbus Service Bulletin A320–52– 

1171, Revision 02, dated April 10, 2017. 

(3) For service information identified in 

this AD, contact Airbus, Airworthiness 

Office—EIAS, 1 Rond Point Maurice 

Bellonte, 31707 Blagnac Cedex, France; 

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

93 44 51; email: account.airworth-eas@

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

(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 October 

17, 2017. 

Jeffrey E. Duven, 

Director, System Oversight Division, Aircraft 

Certification Service. 

[FR Doc. 2017–23349 Filed 11–27–17; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2017–0933; Product 

Identifier 2017–SW–051–AD; Amendment 

39–19106; AD 2017–24–02] 

RIN 2120–AA64 

Airworthiness Directives; Airbus 

Helicopters Deutschland GmbH 

Helicopters 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Final rule; request for 

comments. 

SUMMARY: We are adopting a new 

airworthiness directive (AD) for Airbus 

Helicopters Deutschland GmbH (Airbus 

Helicopters) Model MBB–BK 117 D–2 

helicopters. This AD requires amending 

the rotorcraft flight manual to establish 

a minimum airspeed limitation for the 

autopilot cruise height mode. This AD 

is prompted by two reports of 

uncommanded helicopter climbs and 

descents. The actions of this AD are 

intended to address an unsafe condition 

on these products. 

DATES: This AD becomes effective 

December 13, 2017. 

The Director of the Federal Register 

approved the incorporation by reference 

of certain documents listed in this AD 

as of December 13, 2017. 

We must receive comments on this 

AD by January 29, 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–2017– 

0933; 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 


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