Federal Register / Vol. 83, No. 130 / Friday, July 6, 2018 / Proposed Rules 31499 

at the time specified in Maintenance Review 

Board Task 5220/12 (‘‘Servicing of Forward 

RH Emergency Exit Mechanisms’’) of the 

DHC–8–300 Series Maintenance PSM 1–83– 

7, or within 60 days after the effective date 

of this AD, whichever occurs later. 

(h) Inspection and Replacement 

Within 5,000 flight hours or 36 months, 

whichever occurs first, after the effective date 

of this AD: Do a detailed inspection of all ball 

bearings of the forward right-hand type I 

emergency exit for corrosion, seal damage, 

and loss of lubricant; replace bearings as 

applicable; and apply corrosion inhibiting 

compound (CIC); in accordance with the 

Accomplishment Instructions of Bombardier 

Service Bulletin 8–52–65, dated July 26, 

2017. Do all applicable replacements before 

further flight. 

(i) No Alternative Actions or Intervals 

After the maintenance or inspection 

program has been revised as required by 

paragraph (g) of this AD, no alternative 

actions (e.g., inspections) or intervals may be 

used unless the actions and intervals are 

approved as an alternative method of 

compliance (AMOC) in accordance with the 

procedures specified in paragraph (j)(1) of 

this AD. 

(j) Other FAA AD Provisions 

The following provisions also apply to this 

AD: 

(1) Alternative Methods of Compliance 

(AMOCs): The Manager, New York 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 ATTN: Program Manager, 

Continuing Operational Safety, FAA, New 

York ACO Branch, 1600 Stewart Avenue, 

Suite 410, Westbury, NY 11590; telephone 

516–228–7300; fax 516–794–5531. 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, New York ACO Branch, 

FAA; or Transport Canada Civil Aviation 

(TCCA); or Bombardier, Inc.’s TCCA Design 

Approval Organization (DAO). If approved by 

the DAO, the approval must include the 

DAO-authorized signature. 

(k) Related Information 

(1) Refer to Mandatory Continuing 

Airworthiness Information (MCAI) Canadian 

Airworthiness Directive CF–2017–30, dated 

August 30, 2017, for related information. 

This MCAI may be found in the AD docket 

on the internet at http://www.regulations.gov 

by searching for and locating Docket No. 

FAA–2018–0586. 

(2) For more information about this AD, 

contact Neil Doh, Aerospace Engineer, 

Aviation Safety Section, FAA, Boston ACO 

Branch, 1200 District Avenue, Burlington, 

MA 01803; telephone: 781–238–7757; fax: 

781–238–7199; email: neil.doh@faa.gov. 

(3) For information about AMOCs, contact 

Cesar Gomez, Aerospace Engineer, Airframe 

and Mechanical Systems Section, FAA, New 

York ACO Branch, 1600 Stewart Avenue, 

Suite 410, Westbury, NY 11590; telephone: 

516–228–7318; fax: 516–794–5531. 

(4) For service information identified in 

this AD, contact Bombardier, Inc., Q-Series 

Technical Help Desk, 123 Garratt Boulevard, 

Toronto, Ontario M3K 1Y5, Canada; 

telephone 416–375–4000; fax 416–375–4539; 

email thd.qseries@aero.bombardier.com; 

internet http://www.bombardier.com. You 

may view this service information at the 

FAA, Transport Standards Branch, 2200 

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

information on the availability of this 

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

Issued in Des Moines, Washington, on June 

26, 2018. 

Dionne Palermo, 

Acting Director, System Oversight Division, 

Aircraft Certification Service. 

[FR Doc. 2018–14415 Filed 7–5–18; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2018–0583; Product 

Identifier 2018–NM–019–AD] 

RIN 2120–AA64 

Airworthiness Directives; Airbus 

Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Notice of proposed rulemaking 

(NPRM). 

SUMMARY: We propose to supersede 

Airworthiness Directive (AD) 2017–16– 

07, which applies to certain Airbus 

Model A330–200, A330–200 Freighter, 

A330–300, A340–500, and A340–600 

series airplanes; and Model A340–313 

airplanes. AD 2017–16–07 requires 

inspection of the fuselage bulk cargo 

door frames at specific locations, and 

corrective action if necessary. Since we 

issued AD 2017–16–07, it was 

determined that only airplanes having 

certain manufacturer serial numbers 

(MSNs) are affected by tartaric sulfuric 

anodizing (TSA)/chromic acid 

anodizing (CAA) surface treatment in 

the door fitting attachment holes, and 

that airplanes having certain MSNs were 

excluded. This proposed AD is intended 

to complete certain mandated programs 

intended to support the airplane 

reaching its limit of validity (LOV) of 

the engineering data that support the 

established structural maintenance 

program. This proposed AD would 

require new inspections of certain 

attachment holes for residual surface 

treatment and cracking, and corrective 

action if necessary; and would provide 

an optional terminating action for the 

inspections. The proposed AD would 

also revise the applicability to add 

certain airplanes and remove others. We 

are proposing this AD to address the 

unsafe condition on these products. 

DATES: We must receive comments on 

this proposed AD by August 20, 2018. 

ADDRESSES: You may send comments, 

using the procedures found in 14 CFR 

11.43 and 11.45, by any of the following 

methods: 

• Federal eRulemaking Portal: Go to 

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

instructions for submitting comments. 

• Fax: 202–493–2251. 

• Mail: U.S. Department of 

Transportation, Docket Operations, M– 

30, West Building Ground Floor, Room 

W12–140, 1200 New Jersey Avenue SE, 

Washington, DC 20590. 

• Hand Delivery: Deliver to Mail 

address above between 9 a.m. and 5 

p.m., Monday through Friday, except 

Federal holidays. 

For service information identified in 

this NPRM, contact Airbus SAS, 

Airworthiness Office—EAL, 2 RondPoint Emile Dewoitine, 31700 Blagnac 

Cedex, France; telephone +33 5 61 93 36 

96; fax +33 5 61 93 45 80; email 

airworthiness.A330-A340@airbus.com; 

internet http://www.airbus.com. You 

may view this referenced service 

information at the FAA, Transport 

Standards Branch, 2200 South 216th St., 

Des Moines, WA. For information on the 

availability of this material at the FAA, 

call 206–231–3195. 

Examining the AD Docket 

You may examine the AD docket on 

the internet at http://

www.regulations.gov by searching for 

and locating Docket No. FAA–2018– 

0583; 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 NPRM, the regulatory 

evaluation, any comments received, and 

other information. The street address for 

the Docket Operations office (telephone 

800–647–5527) is in the ADDRESSES

section. Comments will be available in 

the AD docket shortly after receipt. 

FOR FURTHER INFORMATION CONTACT: 

Vladimir Ulyanov, Aerospace Engineer, 

International Section, Transport 

Standards Branch, FAA, 2200 South 

216th St., Des Moines, WA 98198; 

telephone and fax 206–231–3229. 


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SUPPLEMENTARY INFORMATION: 

Comments Invited 

We invite you to send any written 

relevant data, views, or arguments about 

this proposed AD. Send your comments 

to an address listed under the 

ADDRESSES section. Include ‘‘Docket No. 

FAA–2018–0583; Product Identifier 

2018–NM–019–AD’’ at the beginning of 

your comments. We specifically invite 

comments on the overall regulatory, 

economic, environmental, and energy 

aspects of this proposed AD. We will 

consider all comments received by the 

closing date and may amend this 

proposed AD based on those comments. 

We will post all comments we 

receive, without change, to http://

www.regulations.gov, including any 

personal information you provide. We 

will also post a report summarizing each 

substantive verbal contact we receive 

about this proposed AD. 

Discussion 

As described in FAA Advisory 

Circular 120–104 (http://www.faa.gov/ 

documentLibrary/media/Advisory_

Circular/120-104.pdf), several programs 

have been developed to support 

initiatives that will ensure the 

continued airworthiness of aging 

airplane structure. The last element of 

those initiatives is the requirement to 

establish a limit of validity (LOV) of the 

engineering data that support the 

structural maintenance program under 

14 CFR 26.21. This proposed AD is the 

result of an assessment of the previously 

established programs by the design 

approval holder (DAH) during the 

process of establishing the LOV for the 

affected airplanes. The actions specified 

in this proposed AD are necessary to 

complete certain programs to ensure the 

continued airworthiness of aging 

airplane structure and to support an 

airplane reaching its LOV. 

We issued AD 2017–16–07, 

Amendment 39–18984 (82 FR 41874, 

September 5, 2017) (‘‘AD 2017–16–07’’), 

for all Airbus Model A330–200, A330– 

200 Freighter, A330–300, A340–500, 

and A340–600 series airplanes; and 

Model A340–313 airplanes. AD 2017– 

16–07 requires inspection of the 

fuselage bulk cargo door frames at 

specific locations, and corrective action 

if necessary. AD 2017–16–07 resulted 

from the discovery of TSA/CAA surface 

treatment in certain bulk cargo door 

frame holes of airplanes with MSNs 

0400 and higher. We issued AD 2017– 

16–07 to detect and correct fatigue 

cracks in the bulk cargo door frames, 

caused by TSA/CAA surface treatment 

in certain bulk cargo door frame holes. 

Cracks in the bulk cargo door frames can 

cause the in-flight loss of a bulk cargo 

door, damage to the airplane, and 

subsequent reduced control of the 

airplane. 

Actions Since AD 2017–16–07 Was 

Issued 

Since we issued AD 2017–16–07, it 

was determined that only airplanes 

having manufacturer serial numbers 

(MSNs) 0400 through 1779 are affected 

by TSA/CAA surface treatment in the 

door fitting attachment holes due to 

fatigue. However, it was also 

determined that airplanes having MSN 

0001 to MSN 0399 are affected in the 

same attachment holes due to a fatigue 

issue, therefore, the same inspections 

must also be accomplished on these 

airplanes. In addition, based on 

inspection results and calculations, 

Airbus also redefined the inspection 

thresholds and intervals. Airbus 

determined that these actions should 

not be required for Model A340–500 

and –600 airplanes because the unsafe 

condition would only develop beyond 

the design service goal of these 

airplanes. Additionally, Airbus 

developed an optional terminating 

modification. 

The European Aviation Safety Agency 

(EASA), which is the Technical Agent 

for the Member States of the European 

Union, has issued EASA AD 2018–0005, 

dated January 10, 2018 (referred to after 

this as the Mandatory Continuing 

Airworthiness Information, or ‘‘the 

MCAI’’), to correct an unsafe condition 

for certain Airbus Model A330–200, 

A330–200 Freighter, and A330–300 

series airplanes, and Model A340–200 

and A340–300 series airplanes. The 

MCAI states: 

In the frame of the certification of the A330 

Extended Service Goal exercise, it was 

identified that Tartaric Sulfuric Anodising 

(TSA) or Chromic Acid Anodising (CAA) 

surface treatment is present in some frame 

holes, from aeroplane MSN [manufacturer 

serial number] 0400 and later MSN, 

following production process modification. 

On bulk cargo door frames (FR) 67 and FR 

69 right hand (RH) side, the door fitting 

attachment holes have this TSA or CAA 

treatment, which leads to a detrimental effect 

on fatigue behaviour. 

This condition, if not detected and 

corrected, could lead to cracks in the primary 

structure, possibly resulting in in-flight loss 

of a bulk cargo door, consequent 

decompression and potential damage to, and 

reduced control of, the aeroplane. 

To initially address this potential unsafe 

condition, Airbus issued Alert Operators 

Transmission (AOT) A53L012–16 to provide 

instructions to inspect the fuselage bulk 

cargo door frames at specific locations. 

Consequently, EASA issued AD 2016–0102 

[which corresponds to FAA AD 2017–16–07], 

requiring repetitive non-destructive test 

(rototest and high-frequency eddy-current 

(HFEC)) inspection or visual detailed (DET) 

inspections [to detect cracking] of the 

affected areas, and, depending on findings, 

accomplishment of a repair. 

Since that [EASA] AD was issued, it was 

determined that only aeroplanes from MSN 

0400 to MSN 1779 are affected by CAA or 

TSA surface treatment issue in the door 

fitting attachment holes. However, it was also 

determined that aeroplanes MSN 0001 to 

MSN 0399 are affected in the same 

attachment holes due to a fatigue issue, 

therefore, the same inspections must also be 

accomplished on these aeroplanes. In 

addition, based on inspection results and 

calculation, Airbus redefined inspection 

thresholds and intervals, depending on 

aeroplane type, model and utilisation. Airbus 

published SB A330–53–3278 and SB A340– 

53–4239 providing the inspection 

instructions at the specific locations with 

extended inspection thresholds and intervals. 

Airbus also determined that the actions 

should not be required for A340–500 and 

–600 models, as for these aeroplanes, the 

unsafe condition would only develop beyond 

the Design Service Goal of these aeroplanes. 

Finally, Airbus developed modification 

(mod) 206409 and published associated SB 

A330–53–3275 and SB A340–53–4238, as 

applicable, as optional terminating action. 

For the reasons described above, this 

[EASA] AD retains the requirements of EASA 

AD 2016–0102, which is superseded, 

expands the Applicability and requires 

redefined repetitive inspections of the holes 

at the upper and lower door support fittings 

of FR 67 and FR 69 RH and the holes at door 

latch fitting of FR 69 RH. This [EASA] AD 

also introduces an optional modification, 

which constitutes terminating action for the 

repetitive inspections as required by this 

[EASA] AD. 

The optional modification involves 

related investigative actions of eddy 

current rotating probe testing for cracks 

of the support fittings and the frame 

holes at frame (FR) 67 and FR 69. 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–2018– 

0583. 

Related Service Information Under 1 

CFR Part 51 

Airbus has issued the following 

service information. 

• Service Bulletin A330–53–3275, 

dated August 22, 2017. 

• Service Bulletin A330–53–3278, 

dated August 22, 2017. 

• Service Bulletin A340–53–4238, 

dated September 8, 2017. 

• Service Bulletin A340–53–4239, 

dated September 5, 2017. 

Airbus Service Bulletins A330–53– 

3278 and A340–53–4239 describe 

procedures for rototest, HFEC/ultrasonic 

and detailed inspections for residual 

surface treatment and cracking of the 

upper and lower right-hand fuselage 


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bulk cargo door support fitting 

attachment holes at FR 67 and FR 69 

and the right-hand fuselage bulk cargo 

door latch fitting attachment holes at FR 

69. Airbus Service Bulletins A330–53– 

3275 and A340–53–4238 describe 

procedures for a modification, which 

includes eddy current rotating probe 

testing for cracks of the support fittings 

and the frame holes at FR 67 and FR 69, 

and removal of TSA or CAA in the final 

holes of the bulk door frames FR 67 and 

FR 69. These documents are distinct 

since they apply to different airplane 

models. 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. 

FAA’s Determination and Requirements 

of This Proposed AD 

Although this proposed AD does not 

explicitly restate the actions that are 

part of the requirements of AD 2017– 

16–07, this proposed AD would retain 

those required actions. Those actions 

are referenced in the service information 

identified above. 

This product has been approved by 

the aviation authority of another 

country, and is approved for operation 

in the United States. Pursuant to our 

bilateral agreement with the State of 

Design Authority, we have been notified 

of the unsafe condition described in the 

MCAI and service information 

referenced above. We are proposing this 

AD because we evaluated all pertinent 

information and determined an unsafe 

condition exists and is likely to exist or 

develop on other products of these same 

type designs. 

Costs of Compliance 

We estimate that this proposed AD 

affects 102 airplanes of U.S. registry. We 

estimate the following costs to comply 

with this proposed AD: 

ESTIMATED COSTS

Action Labor cost Parts cost Cost per 

product 

Cost on U.S. 

operators 

Inspections and modification ........ Up to 40 work-hours × $85 per 

hour = $3,400.

$5,100 Up to $8,500 ............................... Up to $867,000. 

We have received no definitive data 

that would enable us to provide cost 

estimates for the on-condition actions 

specified in this proposed 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 proposed 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 proposed AD 

would not have federalism implications 

under Executive Order 13132. This 

proposed AD would 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 this proposed regulation: 

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. 

The Proposed Amendment 

Accordingly, under the authority 

delegated to me by the Administrator, 

the FAA proposes to amend 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) 

2017–16–07, Amendment 39–18984 (82 

FR 41874, September 5, 2017), and 

adding the following new AD: 

Airbus: Docket No. FAA–2018–0583; Product 

Identifier 2018–NM–019–AD. 

(a) Comments Due Date 

We must receive comments by August 20, 

2018. 

(b) Affected ADs 

This AD replaces AD 2017–16–07, 

Amendment 39–18984 (82 FR 41874, 

September 5, 2017) (‘‘AD 2017–16–07’’). 

(c) Applicability 

This AD applies to the following Airbus 

airplanes, certificated in any category, 

manufacturer serial numbers (MSNs) 0001 to 

1779 inclusive; except airplanes on which 

Airbus Service Bulletin A330–53–3275 or 

Airbus Service Bulletin A340–53–4238 has 

been embodied. 

(1) Airbus Model A330–201, –202, –203, 

–223, and –243 airplanes. 

(2) Airbus Model A330–223F and –243F 

airplanes. 

(3) Airbus Model A330–301, –302, –303, 

–321, –322, –323, –341, –342, and –343 

airplanes. 

(4) Airbus Model A340–211, –212, and 

–213 airplanes. 

(5) Airbus Model A340–311, –312, and 

–313 airplanes. 

(d) Subject 

Air Transport Association (ATA) of 

America Code 53, Fuselage. 

(e) Reason 

This AD is prompted by a determination 

that only airplanes having certain 


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manufacturer serial numbers (MSNs) are 

affected by tartaric sulfuric anodizing (TSA)/ 

chromic acid anodizing (CAA) surface 

treatment in the door fitting attachment 

holes, and that airplanes having certain 

MSNs were excluded from AD 2017–16–07. 

This AD is intended to complete certain 

mandated programs intended to support the 

airplane reaching its limit of validity (LOV) 

of the engineering data that support the 

established structural maintenance program. 

We are issuing this AD to detect and correct 

fatigue cracks in the bulk cargo door frames, 

caused by TSA/CAA surface treatment in 

certain bulk cargo door frame holes. Cracks 

in the bulk cargo door frames can cause the 

in-flight loss of a bulk cargo door, damage to 

the airplane, and subsequent reduced control 

of the airplane. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Repetitive Inspections 

Before exceeding the thresholds specified 

in table 1 to paragraph (g) of this AD, or 

within the applicable time specified in 

paragraph (g)(1) or (g)(2) of this AD, 

whichever is later: Do a rototest, high 

frequency eddy current (HFEC), ultrasonic, or 

detailed inspection, as applicable, for 

residual surface treatment and cracking of the 

upper and lower right-hand fuselage bulk 

cargo door support fitting attachment holes at 

FR 67 and FR 69 and the right-hand fuselage 

bulk cargo door latch fitting attachment holes 

at FR 69, in accordance with the 

Accomplishment Instructions of Airbus 

Service Bulletin A330–53–3278, dated 

August 22, 2017, or Airbus Service Bulletin 

A340–53–4239, dated September 5, 2017; as 

applicable. Thereafter, depending on the 

areas and inspection methods as defined in 

table 2 to paragraph (g) of this AD, repeat the 

inspection at intervals not exceeding those 

specified in table 3 to paragraph (g) of this 

AD. 

(1) For airplanes having MSN 0001 through 

0399 inclusive: Within 200 flight cycles after 

the effective date of this AD. 

(2) For airplanes having MSN 0400 through 

1779 inclusive: Within 800 flight cycles after 

the effective date of this AD. 

BILLING CODE 4910–13–P 


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BILLING CODE 4910–13–C 

(h) Corrective Action 

If any discrepancy is found during any 

inspection required by paragraph (g) of this 

AD, before further flight, repair 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 DOA-authorized signature. 

(i) Non-Terminating Action for Repairs 

Accomplishment of a repair on an airplane, 

as required by paragraph (h) of this AD, does 

not constitute terminating action for the 

inspections required by paragraph (g) of this 

AD for that airplane, unless otherwise 

specified in repair instructions 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. 

(j) Optional Terminating Action 

Accomplishment of the modification, 

including applicable related investigative 

and corrective actions and removal of TSA or 

CAA in the final holes of the bulk door 

frames FR 67 and FR 69, as applicable, 

specified in, and in accordance with Airbus 

Service Bulletin A330–53–3275, dated 

August 22, 2017, or Airbus Service Bulletin 

A340–53–4238, dated September 8, 2017, as 

applicable, constitutes terminating action for 

the inspections required by paragraph (g) of 

this AD for that airplane, unless otherwise 

specified in the repair instructions 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. 


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(k) Credit for Previous Actions 

This paragraph provides credit for the 

actions required by paragraph (g) of this AD 

if those actions were performed before the 

effective date of this AD using Airbus All 

Operators Telex (AOT) A53L012–16, dated 

May 30, 2016, or Revision 1, dated March 9, 

2017. 

(l) Other FAA AD Provisions 

(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 

Section, send it to the attention of the person 

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

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

AMOC-REQUESTS@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: 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 

EASA DOA. If approved by the DOA, the 

approval must include the DOA-authorized 

signature. 

(m) Related Information 

(1) Refer to Mandatory Continuing 

Airworthiness Information (MCAI) EASA AD 

2018–0005, dated January 10, 2018, for 

related information. This MCAI may be 

found in the AD docket on the internet at 

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

and locating Docket No. FAA–2018–0583. 

(2) For more information about this AD, 

contact Vladimir Ulyanov, Aerospace 

Engineer, International Section, Transport 

Standards Branch, FAA, 2200 South 216th 

St., Des Moines, WA 98198; telephone and 

fax 206–231–3229. 

(3) For service information identified in 

this AD, contact Airbus SAS, Airworthiness 

Office—EAL, 2 Rond-Point Emile Dewoitine, 

31700 Blagnac Cedex, France; telephone +33 

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

airworthiness.A330-A340@airbus.com; 

internet http://www.airbus.com. You may 

view this service information at the FAA, 

Transport Standards Branch, 2200 South 

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

on the availability of this material at the 

FAA, call 206–231–3195. 

Issued in Des Moines, Washington, on June 

22, 2018. 

Michael Kaszycki, 

Acting Director, System Oversight Division, 

Aircraft Certification Service. 

[FR Doc. 2018–14407 Filed 7–5–18; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2018–0551; Product 

Identifier 2018–NM–023–AD] 

RIN 2120–AA64 

Airworthiness Directives; Bombardier, 

Inc. 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Notice of proposed rulemaking 

(NPRM). 

SUMMARY: We propose to adopt a new 

airworthiness directive (AD) for certain 

Bombardier, Inc., Model CL–600–2C10 

(Regional Jet Series 700, 701, & 702) 

airplanes; Model CL–600–2D15 

(Regional Jet Series 705) airplanes; 

Model CL–600–2D24 (Regional Jet 

Series 900) airplanes; and Model CL– 

600–2E25 (Regional Jet Series 1000) 

airplanes. This proposed AD was 

prompted by reports of damage to the 

protective coating and corrosion on the 

piston/axle of the main landing gear 

(MLG), caused by friction between the 

inboard axle sleeve and the axle thrust 

face. This proposed AD would require 

revising the maintenance or inspection 

program, as applicable, to incorporate a 

detailed inspection of the MLG piston/ 

axle for damage to the protective coating 

and for corrosion. We are proposing this 

AD to address the unsafe condition on 

these products. 

DATES: We must receive comments on 

this proposed AD by August 20, 2018. 

ADDRESSES: You may send comments, 

using the procedures found in 14 CFR 

11.43 and 11.45, by any of the following 

methods: 

• Federal eRulemaking Portal: Go to 

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

instructions for submitting comments. 

• Fax: 202–493–2251. 

• Mail: U.S. Department of 

Transportation, Docket Operations, 

M–30, West Building Ground Floor, 

Room W12–140, 1200 New Jersey 

Avenue SE, Washington, DC 20590. 

• Hand Delivery: Deliver to Mail 

address above between 9 a.m. and 5 

p.m., Monday through Friday, except 

Federal holidays. 

For service information identified in 

this NPRM, contact Bombardier, Inc., 

400 Coˆte-Vertu Road West, Dorval, 

Que ́bec H4S 1Y9, Canada; Widebody 

Customer Response Center North 

America toll-free telephone 1–866–538– 

1247 or direct-dial telephone 1–514– 

855–2999; fax 514–855–7401; email 

ac.yul@aero.bombardier.com; internet 

http://www.bombardier.com. You may 

view this service information at the 

FAA, Transport Standards Branch, 2200 

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

information on the availability of this 

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

Examining the AD Docket 

You may examine the AD docket on 

the internet at http://

www.regulations.gov by searching for 

and locating Docket No. FAA–2018– 

0551; 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 NPRM, the regulatory 

evaluation, any comments received, and 

other information. The street address for 

the Docket Operations office (telephone 

800–647–5527) is in the ADDRESSES

section. Comments will be available in 

the AD docket shortly after receipt. 

FOR FURTHER INFORMATION CONTACT: 

Darren Gassetto, Aerospace Engineer, 

Airframe and Mechanical Systems 

Section, FAA, New York ACO Branch, 

1600 Stewart Avenue, Suite 410, 

Westbury, NY 11590; telephone 516– 

228–7323; fax 516–794–5531; email 9- 

avs-nyaco-cos@faa.gov. 

SUPPLEMENTARY INFORMATION: 

Comments Invited 

We invite you to send any written 

relevant data, views, or arguments about 

this proposal. Send your comments to 

an address listed under the ADDRESSES

section. Include ‘‘Docket No. FAA– 

2018–0551; Product Identifier 2018– 

NM–023–AD’’ at the beginning of your 

comments. We specifically invite 

comments on the overall regulatory, 

economic, environmental, and energy 

aspects of this NPRM. We will consider 

all comments received by the closing 

date and may amend this NPRM based 

on those comments. 

We will post all comments we 

receive, without change, to http://

www.regulations.gov, including any 

personal information you provide. We 

will also post a report summarizing each 

substantive verbal contact we receive 

about this NPRM. 

Discussion 

Transport Canada Civil Aviation 

(TCCA), which is the aviation authority 

for Canada, has issued Canadian AD 

CF–2017–38, dated December 20, 2017 

(referred to after this as the Mandatory 

Continuing Airworthiness Information, 

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

condition for certain Bombardier, Inc., 

Model CL–600–2C10 (Regional Jet 

Series 700, 701, & 702) airplanes; Model 

CL–600–2D15 (Regional Jet Series 705) 

airplanes; Model CL–600–2D24 


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