Federal Register / Vol. 82, No. 164 / Friday, August 25, 2017 / Rules and Regulations 40479 

(a) Effective Date 

This AD is effective September 29, 2017. 

(b) Affected ADs 

None. 

(c) Applicability 

This AD applies to all The Boeing 

Company Model 737–300, –400, and –500 

series airplanes, certificated in any category. 

(d) Subject 

Air Transport Association (ATA) of 

America Code 57, Wings. 

(e) Unsafe Condition 

This AD was prompted by a manufacturer’s 

review that showed that the fuel tank access 

door at wing buttock line 191.00 did not have 

an engineered ground path with the mating 

wing structure. We are issuing this AD to 

prevent an ungrounded path that could result 

in an increased risk of ignition and 

subsequent fuel tank explosion in the event 

of a lightning strike. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) New Door Assembly, Electrical Bond 

Check, and Related Corrective Actions 

Within 36 months after the effective date 

of this AD: Install a new door assembly, do 

a check of the electrical bond, and do all 

applicable related investigative and 

corrective actions, in accordance with the 

Accomplishment Instructions of Boeing 

Service Bulletin 737–57–1320, dated October 

7, 2016, except as required by paragraph (i) 

of this AD. Do all applicable related 

investigative and corrective actions before 

further flight. 

(h) Revise the Maintenance or Inspection 

Program 

Prior to or concurrently with 

accomplishment of the actions required by 

paragraph (g) of this AD, or within 30 days 

after the effective date of this AD, whichever 

occurs later: Revise the maintenance or 

inspection program, as applicable, to 

incorporate Airworthiness Limitation 28– 

AWL–30, ‘‘Upper Wing Fuel Tank Access 

Panel—Lightning Protection Electrical Design 

Features,’’ as specified in Boeing 737–100/ 

200/200C/300/400/500 Airworthiness 

Limitations (AWLs) and Certification 

Maintenance Requirements (CMRs) D6– 

38278–CMR, dated May 2016. 

(i) Service Information Exception 

Where Boeing Service Bulletin 737–57– 

1320, dated October 7, 2016, specifies to 

contact Boeing for repair instructions, and 

specifies that action as Required for 

Compliance (RC), this AD requires repair 

using a method approved 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–ANM– 

LAACO–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) of 

this AD: For service information that 

contains steps that are labeled as Required 

for Compliance (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 Serj Harutunian, Aerospace Engineer, 

Propulsion Section, FAA, Los Angeles ACO 

Branch, 3960 Paramount Boulevard, 

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

5254; fax: 562–627–5210; email: 

serj.harutunian@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 Service Bulletin 737–57–1320, 

dated October 7, 2016. 

(ii) Boeing 737–100/200/200C/300/400/500 

Airworthiness Limitations (AWLs) and 

Certification Maintenance Requirements 

(CMRs) D6–38278–CMR, dated May 2016. 

(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 90740–5600; 

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 August 

9, 2017. 

Dionne Palermo, 

Acting Director, System Oversight Division, 

Aircraft Certification Service. 

[FR Doc. 2017–17399 Filed 8–24–17; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2017–0516; Product 

Identifier 2016–NM–125–AD; Amendment 

39–19000; AD 2017–17–10] 

RIN 2120–AA64 

Airworthiness Directives; ATR–GIE 

Avions de Transport Re ́gional 

Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Final rule. 

SUMMARY: We are superseding 

Airworthiness Directive (AD) 2015–23– 

12, which applied to all ATR–GIE 

Avions de Transport Re ́gional Model 

ATR42 and ATR72 airplanes. AD 2015– 

23–12 required identifying the serial 

number and part number of the main 

landing gear (MLG) rear hinge pins, and 

replacing pins or the MLG if necessary. 

This AD retains the requirements of AD 

2015–23–12, requires replacing certain 

additional MLG hinge pins, and reduces 

certain compliance times. This AD was 

prompted by a new occurrence of a 

cracked MLG rear hinge pin. We are 

issuing this AD to address the unsafe 

condition on these products. 

DATES: This AD is effective September 

29, 2017. 

The Director of the Federal Register 

approved the incorporation by reference 

of certain publications listed in this AD 

as of September 29, 2017. 


pmangrum on DSK3GDR082PROD with RULES
40480 Federal Register / Vol. 82, No. 164 / Friday, August 25, 2017 / Rules and Regulations 

The Director of the Federal Register 

approved the incorporation by reference 

of certain other publications listed in 

this AD as of December 29, 2015 (80 FR 

73096, November 24, 2015). 

ADDRESSES: For service information 

identified in this final rule, contact 

ATR–GIE Avions de Transport Re ́gional, 

1, Alle ́e Pierre Nadot, 31712 Blagnac 

Cedex, France; telephone +33 (0) 5 62 

21 62 21; fax +33 (0) 5 62 21 67 18; 

email continued.airworthiness@atr.fr; 

Internet http://www.aerochain.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– 

0516. 

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– 

0516; 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 (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: 

Shahram Daneshmandi, Aerospace 

Engineer, International Section, 

Transport Standards Branch, FAA, 1601 

Lind Avenue SW., Renton, WA 98057– 

3356; telephone 425–227–1112; fax 

425–227–1149. 

SUPPLEMENTARY INFORMATION: 

Discussion 

We issued a notice of proposed 

rulemaking (NPRM) to amend 14 CFR 

part 39 to supersede AD 2015–23–12, 

Amendment 39–18329 (80 FR 73096, 

November 24, 2015) (‘‘AD 2015–23– 

12’’). AD 2015–23–12 applied to all 

ATR–GIE Avions de Transport Re ́gional 

Model ATR42 and ATR72 airplanes. 

The NPRM published in the Federal 

Register on May 31, 2017 (82 FR 24906). 

The NPRM was prompted by a new 

occurrence of a cracked MLG rear hinge 

pin. The NPRM proposed to continue to 

require identifying the serial number 

and part number of the MLG rear hinge 

pins, and replacing pins or the MLG if 

necessary. The NPRM also proposed to 

require replacing certain additional 

MLG hinge pins, and reducing certain 

compliance times. We are issuing this 

AD to detect and correct cracked rear 

hinge pins, which could lead to MLG 

structural failure, possibly resulting in 

collapse of the MLG and consequent 

injury to the occupants of the airplane. 

The European Aviation Safety Agency 

(EASA), which is the Technical Agent 

for the Member States of the European 

Union, has issued EASA Airworthiness 

Directive 2016–0135, dated July 8, 2016 

(referred to after this as the Mandatory 

Continuing Airworthiness Information, 

or ‘‘the MCAI’’), to correct an unsafe 

condition for all ATR–GIE Avions de 

Transport Re ́gional Model ATR42 and 

ATR72 airplanes. The MCAI states: 

Prompted by cases of rupture of main 

landing gear (MLG) rear hinge pin part 

number (P/N) D61000 encountered in service 

in 1994 and 1996, DGAC [Direction Ge ́ne ́rale 

de l’Aviation Civile] France issued AD 96– 

131–064 (B) for ATR42 aeroplanes and AD 

96–096–029 (B) for ATR72 aeroplanes to 

require inspection and, depending on 

findings, corrective action. Since those 

[French] ADs were issued, new occurrences 

of cracked rear hinge pin P/N [part number] 

D61000 were reported on ATR72 MLG. The 

result of subsequent investigation revealed 

that the affected pins were subjected to a 

non-detected thermal abuse done in 

production during grinding process. Analysis 

also showed that other MLG pin P/N’s could 

be affected by the same production issue. 

This condition, if not detected and 

corrected, could lead to structural failure and 

consequent collapse of the MLG, possibly 

resulting in damage to the aeroplane and 

injury to the occupants. 

To address this potential unsafe condition, 

EASA issued AD 2014–0074 [which 

corresponds to FAA AD 2015–23–12] to 

require inspection and, depending on 

findings, replacement of affected pins. 

After EASA AD 2014–0074 was issued, a 

new occurrence was reported of a cracked 

MLG hinge pin P/N D62055 installed on the 

MLG Side Brace of an ATR42 aeroplane. This 

new occurrence was also identified as related 

to a non-detected thermal abuse done in 

production during grinding process. 

Prompted by this new occurrence, Messier 

Bugatti Dowty (MBD) updated the list of 

MLG hinge pins affected by this unsafe 

condition by adding serial numbers (S/N), 

which were previously not considered by 

EASA AD 2014–0074. In addition, it was 

determined that the compliance time for 

replacement of pins with P/N D62055 must 

be reduced. The six affected MBD Service 

Bulletins (SB) were revised accordingly, and 

six new ones were also published to address 

this issue. 

For the reasons described above, this 

[EASA] AD retains the requirements of EASA 

AD 2014–0074, which is superseded, but 

addresses an expanded MLG hinge pin 

population with appropriate compliance 

time(s). 

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– 

0516. 

Comments 

We gave the public the opportunity to 

participate in developing this AD. We 

received no comments on the NPRM or 

on the determination of the cost to the 

public. 

Conclusion 

We reviewed the available data and 

determined that air safety and the 

public interest require adopting this AD 

as proposed except for 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. 

Related Service Information Under 1 

CFR Part 51 

Messier-Bugatti-Dowty has issued the 

following service information, which 

describes procedures for inspecting and 

replacing the MLG hinge pin. These 

documents are distinct since they apply 

to different airplane models and 

different MLG hinge pin part numbers. 

• Service Bulletin 631–32–213, 

Revision 2, dated March 15, 2016. 

• Service Bulletin 631–32–214, 

Revision 1, dated March 15, 2016. 

• Service Bulletin 631–32–215, 

Revision 1, dated March 15, 2016. 

• Service Bulletin 631–32–216, 

Revision 3, dated March 15, 2016. 

• Service Bulletin 631–32–219, 

Revision 1, dated March 15, 2016. 

• Service Bulletin 631–32–220, 

Revision 1, dated March 15, 2016. 

• Service Bulletin 631–32–224, dated 

March 15, 2016. 

• Service Bulletin 631–32–231, dated 

March 15, 2016. 

• Service Bulletin 631–32–232, 

Revision 1, dated March 15, 2016. 

• Service Bulletin 631–32–233, dated 

March 15, 2016. 

• Service Bulletin 631–32–234, dated 

March 15, 2016. 

• Service Bulletin 631–32–235, dated 

March 15, 2016. 

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 will affect 

63 airplanes of U.S. registry. 


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Federal Register / Vol. 82, No. 164 / Friday, August 25, 2017 / Rules and Regulations 40481 

The actions required by AD 2015–23– 

12, and retained in this AD take about 

8 work-hours per product, at an average 

labor rate of $85 per work-hour. 

Required parts will cost about $16,000 

per product. Based on these figures, the 

estimated cost of the actions that are 

required by AD 2015–23–12 is $16,680 

per product. 

We also estimate that it will take 

about 8 work-hours per product to 

comply with the basic requirements of 

this AD. The average labor rate is $85 

per work-hour. Required parts will cost 

about $16,000 per product. Based on 

these figures, we estimate the cost of 

this AD on U.S. operators to be 

$1,050,840, or $16,680 per product. 

According to the manufacturer, some 

of the costs of this AD may be covered 

under warranty, thereby reducing the 

cost impact on affected individuals. We 

do not control warranty coverage for 

affected individuals. As a result, we 

have included all costs in our cost 

estimate. 

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 

removing Airworthiness Directive (AD) 

2015–23–12, Amendment 39–18329 (80 

FR 73096, November 24, 2015), and 

adding the following new AD: 

2017–17–10 ATR–GIE Avions de Transport 

Re ́gional: Amendment 39–19000; Docket 

No. FAA–2017–0516; Product Identifier 

2016–NM–125–AD. 

(a) Effective Date 

This AD is effective September 29, 2017. 

(b) Affected ADs 

This AD replaces AD 2015–23–12, 

Amendment 39–18329 (80 FR 73096, 

November 24, 2015) (‘‘AD 2015–23–12’’). 

(c) Applicability 

This AD applies to ATR–GIE Avions de 

Transport Re ́gional Model ATR42–200, –300, 

–320, and –500 airplanes; and ATR72–101, 

–201, –102, –202, –211, –212, and –212A 

airplanes; certificated in any category; all 

certified models; all manufacturer serial 

numbers. 

(d) Subject 

Air Transport Association (ATA) of 

America Code 32, Landing Gear. 

(e) Reason 

This AD was prompted by a new 

occurrence of a cracked main landing gear 

(MLG) rear hinge pin. We are issuing this AD 

to detect and correct cracked rear hinge pins, 

which could lead to MLG structural failure, 

possibly resulting in collapse of the MLG and 

consequent injury to the occupants of the 

airplane. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Retained Hinge Pin Identification and 

Replacement for Model ATR72 Airplanes, 

With Terminating Action 

This paragraph restates the requirements of 

paragraph (g) of AD 2015–23–12, with 

terminating action. For Model ATR72 

airplanes: Within 12 months after December 

29, 2015 (the effective date of AD 2015–23– 

12), inspect for the serial number of the lefthand (LH) and right-hand (RH) MLG rear 

hinge pins having part number (P/N) D61000. 

A review of airplane maintenance records is 

acceptable in lieu of this identification if the 

part number and serial number of the LH and 

RH MLG rear hinge pins can be conclusively 

determined from that review. If a rear hinge 

pin having P/N D61000 has a serial number 

listed in Messier-Bugatti-Dowty Service 

Bulletin 631–32–213, dated December 16, 

2013; or Messier-Bugatti-Dowty Service 

Bulletin 631–32–216, Revision 1, dated 

December 17, 2013; as applicable: Within 12 

months after December 29, 2015, replace the 

pin with a serviceable part as identified in 

paragraph (h) of this AD, in accordance with 

the Accomplishment Instructions of MessierBugatti-Dowty Service Bulletin 631–32–213, 

dated December 16, 2013; or Messier-BugattiDowty Service Bulletin 631–32–216, 

Revision 1, dated December 17, 2013; as 

applicable. Accomplishment of the actions 

required by paragraph (l) of this AD 

terminates the inspection required by this 

paragraph. Accomplishing the actions 

required by paragraph (m) or (o) of this AD 

terminates the actions required by this 

paragraph. 

(h) Retained Definition of Serviceable Hinge 

Pin for Model ATR72 Airplanes for 

Paragraph (g) of This AD, With No Changes 

This paragraph restates the definition in 

paragraph (h) of AD 2015–23–12, with no 

changes. For Model ATR72 airplanes: For 

purposes of paragraph (g) of this AD, a 

serviceable MLG rear hinge pin is a pin that 

is specified in paragraph (h)(1) or (h)(2) of 

this AD. 

(1) A hinge pin that is not identified in 

Messier-Bugatti-Dowty Service Bulletin 631– 

32–213, dated December 16, 2013; or 

Messier-Bugatti-Dowty Service Bulletin 631– 

32–216, Revision 1, dated December 17, 

2013; as applicable. 

(2) A hinge pin that has been inspected and 

reconditioned, in accordance with the 

Accomplishment Instructions of MessierBugatti-Dowty Service Bulletin 631–32–213, 

dated December 16, 2013; or Messier-BugattiDowty Service Bulletin 631–32–216, 

Revision 1, dated December 17, 2013; as 

applicable. 


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40482 Federal Register / Vol. 82, No. 164 / Friday, August 25, 2017 / Rules and Regulations 

(i) Retained MLG Pin Identification and 

Replacement for Model ATR72 Airplanes, 

With Terminating Action 

This paragraph restates the requirements of 

paragraph (i) of AD 2015–23–12, with 

terminating action. For Model ATR72 

airplanes: At the earlier of the times specified 

in paragraphs (i)(1) and (i)(2) of this AD, 

inspect all LH and RH MLG pins for a part 

number and serial number listed in MessierBugatti-Dowty Service Bulletin 631–32–214, 

dated January 13, 2014; or Messier-BugattiDowty Service Bulletin 631–32–219, dated 

March 3, 2014; as applicable. A review of 

airplane maintenance records is acceptable in 

lieu of this inspection if the part number and 

serial number of the LH and RH MLG pin can 

be conclusively determined from that review. 

If any affected MLG pin is found: At the 

earlier of the compliance times specified in 

paragraphs (i)(1) and (i)(2) of this AD, replace 

the MLG with a serviceable MLG as 

identified in paragraph (j) of this AD, using 

a method approved by the Manager, 

International Section, Transport Standards 

Branch, FAA; or the European Aviation 

Safety Agency (EASA); or ATR–GIE Avions 

de Transport Re ́gional’s EASA Design 

Organization Approval (DOA). 

Accomplishment of the actions required by 

paragraph (l) of this AD terminates the 

inspection for the part number and serial 

number of the LH and RH MLG rear hinge 

pins required by this paragraph. 

Accomplishment of the actions required by 

paragraph (m) or (o) of this AD terminates the 

actions required by this paragraph. 

(1) No later than the next MLG overhaul 

scheduled after December 29, 2015 (the 

effective date of AD 2015–23–12). 

(2) Within 20,000 flight cycles or 9 years, 

whichever occurs first, accumulated since 

installation of the MLG on an airplane since 

new or since last overhaul, as applicable. 

(j) Retained Definition of Serviceable MLG 

for Model ATR72 Airplanes for Paragraph 

(i) of This AD, With No Changes 

This paragraph restates the definition in 

paragraph (j) of AD 2015–23–12, with no 

changes. For Model ATR72 airplanes: For 

purposes of paragraph (i) of this AD, a 

serviceable MLG is one that incorporates pins 

specified in paragraph (j)(1) or (j)(2) of this 

AD. 

(1) Pins that are not identified in MessierBugatti-Dowty Service Bulletin 631–32–214, 

dated January 13, 2014; or Messier-BugattiDowty Service Bulletin 631–32–219, dated 

March 3, 2014; as applicable. 

(2) Pins that have been inspected and 

reconditioned in accordance with the 

Accomplishment Instructions of MessierBugatti-Dowty Service Bulletin 631–32–214, 

dated January 13, 2014; or Messier-BugattiDowty Service Bulletin 631–32–219, dated 

March 3, 2014; as applicable. 

(k) Retained MLG Pin Identification and 

Replacement for Model ATR42 Airplanes, 

With Terminating Action 

This paragraph restates the requirements of 

paragraph (k) of AD 2015–23–12, with 

terminating action. Accomplishment of the 

actions required by paragraph (l) of this AD 

terminates the actions required by paragraph 

(k)(1) of this AD. Accomplishment of the 

actions required by paragraph (m) or (o) of 

this AD terminates the actions required by 

paragraph (k)(2) of this AD. 

(1) For Model ATR42 airplanes: Within the 

compliance time identified in paragraph 

(k)(1)(i) or (k)(1)(ii) of this AD, whichever 

occurs first, inspect for any LH and RH MLG 

pins having a part number and serial number 

listed in Messier-Bugatti-Dowty Service 

Bulletin 631–32–215, dated January 13, 2014; 

or Messier-Bugatti-Dowty Service Bulletin 

631–32–220, dated March 3, 2014; as 

applicable. A review of airplane maintenance 

records is acceptable in lieu of this 

identification if the part number and serial 

number of the LH and RH MLG pin can be 

conclusively determined from that review. 

(i) No later than the next MLG overhaul 

scheduled after December 29, 2015 (the 

effective date of AD 2015–23–12). 

(ii) Within 20,000 flight cycles or 9 years, 

whichever occurs first, accumulated since 

installation of the MLG on an airplane since 

new or since last overhaul, as applicable. 

(2) If the MLG pin having a part number 

and serial number listed in Messier-BugattiDowty Service Bulletin 631–32–215, dated 

January 13, 2014; or Messier-Bugatti-Dowty 

Service Bulletin 631–32–220, dated March 3, 

2014; as applicable; is found to be installed 

during the identification required by 

paragraph (k)(1) of this AD, within the 

compliance time identified in paragraph 

(k)(1) of this AD, replace the MLG with a 

serviceable MLG, using a method approved 

by the Manager, International Section, 

Transport Standards Branch, FAA; or the 

EASA; or ATR–GIE Avions de Transport 

Re ́gional’s EASA DOA. For the purposes of 

this paragraph, a serviceable MLG is a part 

that has pins identified in paragraph (k)(2)(i) 

or (k)(2)(ii) of this AD. 

(i) Pins that are not listed in MessierBugatti-Dowty Service Bulletin 631–32–215, 

dated January 13, 2014; or Messier-BugattiDowty Service Bulletin 631–32–220, dated 

March 3, 2014; as applicable. 

(ii) Pins that have been inspected and 

reconditioned, in accordance with the 

Accomplishment Instructions of MessierBugatti-Dowty Service Bulletin 631–32–215, 

dated January 13, 2014; or Messier-BugattiDowty Service Bulletin 631–32–220, dated 

March 3, 2014; as applicable. 

(l) New Requirement of This AD: Hinge Pin 

Identification 

Within the applicable compliance time 

specified in, and in accordance with the 

Accomplishment Instructions of, the 

applicable Messier-Bugatti-Dowty Service 

Bulletin specified in figure 1 to paragraphs (l) 

through (p) of this AD, or figure 2 to 

paragraphs (l) through (p) of this AD, as 

applicable to the airplane model and MLG 

hinge part number, identify the serial number 

(S/N) of the LH and RH MLG hinge pins. A 

review of airplane maintenance records is 

acceptable in lieu of this identification if the 

part number and serial number of the LH and 

RH MLG hinge pins can be conclusively 

determined from that review. 

Accomplishment of the actions required by 

this paragraph terminates the inspections 

required by paragraphs (g), (i), and (k)(1) of 

this AD. 

FIGURE 1 TO PARAGRAPHS (l) THROUGH (p) OF THIS AD—MODEL ATR72 AIRPLANES

MLG hinge part Nos. Applicable Messier-Bugatti-Dowty service bulletins Compliance time 

D60955, D60968, D60999, 

D61032, D61061.

Messier-Bugatti-Dowty Service Bulletin 631-32–214, 

Revision 1, dated March 15, 2016, 

Messier-Bugatti-Dowty Service Bulletin 631-32–219, 

Revision 1, dated March 15, 2016, or 

Messier-Bugatti-Dowty Service Bulletin 631-32–233, 

dated March 15, 2016. 

A or B, whichever occurs first: 

A: Not later than the next scheduled MLG overhaul 

after the effective date of this AD. 

B: Within 20,000 flight cycles or 9 years, whichever occurs first, accumulated since first installation of a 

MLG on an airplane since new, or since last overhaul, as applicable. 

D61000 ................................. Messier-Bugatti-Dowty Service Bulletin 631-32–213, 

Revision 2, dated March 15, 2016, 

Within 12 months after the effective date of this AD. 

Messier-Bugatti-Dowty Service Bulletin 631-32–216, 

Revision 3, dated March 15, 2016, or 

Messier-Bugatti-Dowty Service Bulletin 631-32–232, 

Revision 1, dated March 15, 2016. 


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FIGURE 2 TO PARAGRAPHS (l) THROUGH (p) OF THIS AD—MODEL ATR42 AIRPLANES

MLG hinge part Nos. Airplane model(s) Applicable Messier-Bugatti-Dowty service bulletins Compliance time 

D62054, D63823, 

D63825.

All ............................... Messier-Bugatti-Dowty Service Bulletin 

631-32-215, Revision 1, dated March 15, 

2016, 

A or B, whichever occurs first: 

A: Not later than the next scheduled MLG 

overhaul after the effective date of this AD. 

Messier-Bugatti-Dowty Service Bulletin 

631-32-220, Revision 1, dated March 15, 

2016, or 

Messier-Bugatti-Dowty Service Bulletin 

631-32-235, dated March 15, 2016. 

B: Within 20,000 flight cycles or 9 years, 

whichever occurs first, accumulated since 

first installation of a MLG on an airplane 

since new, or since last overhaul, as applicable. 

D56800, D56800–1, 

D56809, D56841, 

D57261, D57401, 

D57407, D58807, 

D62079.

ATR42–300 ................ Messier-Bugatti-Dowty Service Bulletin 

631-32-215, Revision 1, dated March 15, 

2016, 

Messier-Bugatti-Dowty Service Bulletin 

631-32-220, Revision 1, dated March 15, 

2016, or 

Messier-Bugatti-Dowty Service Bulletin 

631-32-235, dated March 15, 2016. 

A or B, whichever occurs first: 

A: Not later than the next scheduled MLG 

overhaul after the effective date of this AD. 

B: Within 20,000 flight cycles or 9 years, 

whichever occurs first, accumulated since 

first installation of a MLG on an airplane 

since new, or since last overhaul, as applicable. 

D62055 ........................ All ............................... Messier-Bugatti-Dowty Service Bulletin 

631-32-224, dated March 15, 2016, 

Within 24 months after the effective date of 

this AD. 

Messier-Bugatti-Dowty Service Bulletin 

631-32-231, dated March 15, 2016, or 

Messier-Bugatti-Dowty Service Bulletin 631– 

32–234, dated March 15, 2016. 

(m) New MLG Hinge Pin Replacement 

If, during the identification required by 

paragraph (l) of this AD, an MLG hinge pin 

with a serial number listed in the applicable 

Messier-Bugatti-Dowty Service Bulletin is 

found to be installed: Within the compliance 

time specified in figure 1 to paragraphs (l) 

through (p) of this AD, or figure 2 to 

paragraphs (l) through (p) of this AD, as 

applicable to airplane model and MLG hinge 

pin part number, replace each affected MLG 

hinge pin with a serviceable MLG hinge pin. 

The replacement must be done in accordance 

with the Accomplishment Instructions of the 

applicable Messier-Bugatti-Dowty Service 

Bulletin specified in figure 1 to paragraphs (l) 

through (p) of this AD, or figure 2 to 

paragraphs (l) through (p) of this AD, as 

applicable to the airplane model and MLG 

hinge part number, except as required by 

paragraph (o) of this AD. Accomplishment of 

the actions required by this paragraph 

terminates the actions required by paragraphs 

(g) and (i) of this AD. Accomplishment of the 

actions required by this paragraph terminates 

the replacement required by paragraph (k)(2) 

of this AD. 

(n) New Definition of Serviceable Hinge Pins 

for Paragraph (m) of This AD 

For the purpose of paragraph (m) of this 

AD, a serviceable MLG hinge pin is a pin that 

is specified in paragraph (n)(1) or (n)(2) of 

this AD. 

(1) A hinge pin that does not belong to the 

identified batch as listed in the applicable 

Messier-Bugatti-Dowty Service Bulletin 

specified in figure 1 to paragraphs (l) through 

(p) of this AD, or figure 2 to paragraphs (l) 

through (p) of this AD, as applicable to the 

airplane model and MLG hinge part number. 

(2) A hinge pin that can be identified, 

through the MLG maintenance records, as 

having been inspected and reconditioned in 

accordance with the Accomplishment 

Instructions of the applicable MessierBugatti-Dowty Service Bulletin specified in 

figure 1 to paragraphs (l) through (p) of this 

AD, or figure 2 to paragraphs (l) through (p) 

of this AD, as applicable to the airplane 

model and MLG hinge part number. 

(o) New MLG Hinge Pin Replacement 

Procedures 

If, during accomplishment of the MLG 

hinge pin replacement required by paragraph 

(m) of this AD, the applicable MessierBugatti-Dowty Service Bulletin specified in 

figure 1 to paragraphs (l) through (p) of this 

AD, or figure 2 to paragraphs (l) through (p) 

of this AD, does not specify the MLG hinge 

pin replacement procedure, do the MLG 

hinge pin replacement using a method 

approved by the Manager, International 

Section, Transport Standards Branch, FAA; 

or the EASA; or ATR—GIE Avions de 

Transport Re ́gional’s EASA DOA. Do the 

MLG hinge pin replacement at the applicable 

compliance time specified in paragraph (m) 

of this AD. Accomplishment of the actions 

required by this paragraph terminates the 

hinge pin replacement required by 

paragraphs (g), (i), and (k)(2) of this AD. 

(p) New Parts Installation Limitation 

As of the effective date of this AD, no 

person may install on any airplane an MLG 

hinge pin having a part number identified in 

figure 1 to paragraphs (l) through (p) of this 

AD, or figure 2 to paragraphs (l) through (p) 

of this AD, and having a serial number 

defined in the applicable Messier-BugattiDowty Service Bulletin specified in figure 1 

to paragraphs (l) through (p) of this AD, or 

figure 2 to paragraphs (l) through (p) of this 

AD, as applicable to the airplane model and 

MLG hinge part number, unless the part can 

be conclusively identified, through the MLG 

maintenance records, as having been 

inspected and reconditioned in accordance 

with the Accomplishment Instructions of the 

applicable Messier-Bugatti-Dowty Service 

Bulletin. 

(q) Credit for Previous Actions 

(1) This paragraph restates the credit 

provided in paragraph (l) of AD 2015–23–12, 

with no changes. This paragraph provides 

credit for the actions required by paragraph 

(g) of this AD, if those actions were 

performed before December 29, 2015 (the 

effective date of AD 2105–23–12), using 

Messier-Bugatti-Dowty Service Bulletin 631– 

32–216, dated October 30, 2013, which is not 

incorporated by reference in this AD. 

(2) This paragraph provides credit for the 

actions required by paragraphs (l) and (m) of 

this AD, if those actions were done before the 

effective date of this AD using the applicable 

service information specified in paragraph 

(q)(2)(i) through (q)(2)(x) of this AD. 

(i) Messier-Bugatti-Dowty Service Bulletin 

631–32–213, December 16, 2013, which was 

incorporated by reference on December 29, 

2015 (80 FR 73096, November 24, 2015). 

(ii) Messier-Bugatti-Dowty Service Bulletin 

631–32–213, Revision 1, dated December 8, 

2014, which is not incorporated by reference 

in this AD. 

(iii) Messier-Bugatti-Dowty Service 

Bulletin 631–32–214, dated January 13, 2014, 

which was incorporated by reference on 

December 29, 2015 (80 FR 73096, November 

24, 2015). 

(iv) Messier-Bugatti-Dowty Service Bulletin 

631–32–215, dated January 13, 2014, which 

was incorporated by reference on December 

29, 2015 (80 FR 73096, November 24, 2015). 

(v) Messier-Bugatti-Dowty Service Bulletin 

631–32–216, dated October 30, 2013, which 

is not incorporated by reference in this AD. 

(vi) Messier-Bugatti-Dowty Service Bulletin 

631–32–216, Revision 1, dated December 17, 

201, which was incorporated by reference on 

December 29, 2015 (80 FR 73096, November 

24, 2015). 

(vii) Messier-Bugatti-Dowty Service 

Bulletin 631–32–216, Revision 2, dated 

December 8, 2014, which is not incorporated 

by reference in this AD. 


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(viii) Messier-Bugatti-Dowty Service 

Bulletin 631–32–219, dated March 3, 2014, 

which was incorporated by reference on 

December 29, 2015 (80 FR 73096, November 

24, 2015). 

(ix) Messier-Bugatti-Dowty Service Bulletin 

631–32–220, dated March 3, 2014, which was 

incorporated by reference on December 29, 

2015 (80 FR 73096, November 24, 2015). 

(x) Messier-Bugatti-Dowty Service Bulletin 

631–32–232, dated December 8, 2014, which 

is not incorporated by reference in this AD. 

(r) 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 manager of the International 

Branch, send it to the attention of the person 

identified in paragraph (s)(2) of this AD. 

Information may be emailed to: 9-ANM-116- 

AMOC-REQUESTS@faa.gov. 

(i) 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. 

(ii) AMOCs approved previously for AD 

2015–23–12 are approved as AMOCs for the 

corresponding provisions of this AD. 

(2) Contacting the Manufacturer: As of the 

effective date of this AD, for any requirement 

in this AD to obtain corrective actions from 

a manufacturer, the action must be 

accomplished using a method approved by 

the Manager, International Section, Transport 

Standards Branch, FAA; or the EASA; or 

ATR—GIE Avions de Transport Re ́gional’s 

EASA DOA. If approved by the DOA, the 

approval must include the DOA-authorized 

signature. 

(s) Related Information 

(1) Refer to Mandatory Continuing 

Airworthiness Information (MCAI) EASA 

Airworthiness Directive 2016–0135, dated 

July 8, 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– 

2017–0516. 

(2) For more information about this AD, 

contact Shahram Daneshmandi, Aerospace 

Engineer, International Section, Transport 

Standards Branch, FAA, 1601 Lind Avenue 

SW., Renton, WA 98057–3356; telephone 

425–227–1112; fax 425–227–1149. 

(3) Service information identified in this 

AD that is not incorporated by reference is 

available at the addresses specified in 

paragraphs (t)(5) and (t)(6) of this AD. 

(t) 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. 

(3) The following service information was 

approved for IBR on September 29, 2017. 

(i) Messier-Bugatti-Dowty Service Bulletin 

631–32–213, Revision 2, dated March 15, 

2016. 

(ii) Messier-Bugatti-Dowty Service Bulletin 

631–32–214, Revision 1, dated March 15, 

2016. 

(iii) Messier-Bugatti-Dowty Service 

Bulletin 631–32–215, Revision 1, dated 

March 15, 2016. 

(iv) Messier-Bugatti-Dowty Service Bulletin 

631–32–216, Revision 3, dated March 15, 

2016. 

(v) Messier-Bugatti-Dowty Service Bulletin 

631–32–219, Revision 1, dated March 15, 

2016. 

(vi) Messier-Bugatti-Dowty Service Bulletin 

631–32–220, Revision 1, dated March 15, 

2016. 

(vii) Messier-Bugatti-Dowty Service 

Bulletin 631–32–224, dated March 15, 2016. 

(viii) Messier-Bugatti-Dowty Service 

Bulletin 631–32–231, dated March 15, 2016. 

(ix) Messier-Bugatti-Dowty Service Bulletin 

631–32–232, Revision 1, dated March 15, 

2016. 

(x) Messier-Bugatti-Dowty Service Bulletin 

631–32–233, dated March 15, 2016. 

(xi) Messier-Bugatti-Dowty Service Bulletin 

631–32–234, dated March 15, 2016. 

(xii) Messier-Bugatti-Dowty Service 

Bulletin 631–32–235, dated March 15, 2016. 

(4) The following service information was 

approved for IBR on December 29, 2015 (80 

FR 73096, November 24, 2015). 

(i) Messier-Bugatti-Dowty Service Bulletin 

631–32–213, dated December 16, 2013. 

(ii) Messier-Bugatti-Dowty Service Bulletin 

631–32–214, dated January 13, 2014. 

(iii) Messier-Bugatti-Dowty Service 

Bulletin 631–32–215, dated January 13, 2014. 

(iv) Messier-Bugatti-Dowty Service Bulletin 

631–32–216, Revision 1, dated December 17, 

2013. Pages 4, 5, and 8 of this service bulletin 

are the original issue and are dated October 

30, 2013. 

(v) Messier-Bugatti-Dowty Service Bulletin 

631–32–219, dated March 3, 2014. 

(vi) Messier-Bugatti-Dowty Service Bulletin 

631–32–220, dated March 3, 2014. 

(5) For service information identified in 

this AD, contact ATR–GIE Avions de 

Transport Re ́gional, 1, Alle ́e Pierre Nadot, 

31712 Blagnac Cedex, France; telephone +33 

(0) 5 62 21 62 21; fax +33 (0) 5 62 21 67 18; 

email continued.airworthiness@atr.fr; 

Internet http://www.aerochain.com. 

(6) 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. 

(7) 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 August 

8, 2017. 

Dionne Palermo, 

Acting Director, System Oversight Division, 

Aircraft Certification Service. 

[FR Doc. 2017–17398 Filed 8–24–17; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF HEALTH AND 

HUMAN SERVICES 

Food and Drug Administration 

21 CFR Part 121 

[Docket No. FDA–2013–N–1425] 

Mitigation Strategies To Protect Food 

Against Intentional Adulteration: What 

You Need To Know About the Food 

and Drug Administration Regulation: 

Small Entity Compliance Guide; 

Availability 

AGENCY: Food and Drug Administration, 

HHS. 

ACTION: Notification of availability. 

SUMMARY: The Food and Drug 

Administration (FDA, the Agency, or 

we) is announcing the availability of a 

guidance for industry entitled 

‘‘Mitigation Strategies to Protect Food 

Against Intentional Adulteration: What 

You Need To Know About the FDA 

Regulation: Small Entity Compliance 

Guide.’’ The small entity compliance 

guide (SECG) is intended to help small 

entities comply with the final rule 

entitled ‘‘Mitigation Strategies to Protect 

Food Against Intentional Adulteration.’’ 

DATES: The announcement of the 

guidance is published in the Federal 

Register on August 25, 2017. 

ADDRESSES: You may submit either 

electronic or written comments on 

Agency guidances at any time 

comments as follows: 

Electronic Submissions 

Submit electronic comments in the 

following way: 

• Federal eRulemaking Portal: 

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

instructions for submitting comments. 

Comments submitted electronically, 

including attachments, to https://

www.regulations.gov will be posted to 

the docket unchanged. Because your 

comment will be made public, you are 

solely responsible for ensuring that your 

comment does not include any 

confidential information that you or a 

third party may not wish to be posted, 

such as medical information, your or 

anyone else’s Social Security number, or 

confidential business information, such 

as a manufacturing process. Please note 


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