46670 Federal Register / Vol. 83, No. 179 / Friday, September 14, 2018 / Proposed Rules 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2018–0790; Product 

Identifier 2018–NM–078–AD] 

RIN 2120–AA64 

Airworthiness Directives; Bombardier, 

Inc., Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Notice of proposed rulemaking 

(NPRM). 

SUMMARY: We propose to supersede 

Airworthiness Directive (AD) 2010–14– 

05, which applies to certain 

Bombardier, Inc., Model CL–600–1A11 

(600), CL–600–2A12 (601), and CL–600– 

2B16 (601–3A, 601–3R, and 604 

Variants) airplanes. AD 2010–14–05 

requires inspection for the part numbers 

of the system and brake accumulators, 

and repetitive replacement of affected 

accumulators. Since we issued AD 

2010–14–05, we have determined that 

new or more restrictive airworthiness 

limitations, as well as additional 

actions, are necessary to address the 

unsafe condition. In addition to the 

requirements of AD 2010–14–05, this 

proposed AD would require relocating 

the accumulators and revising the 

maintenance or inspection program to 

incorporate new or more restrictive 

airworthiness limitations. This 

proposed AD would also add optional 

terminating action for certain airplanes. 

We are proposing this AD to address the 

unsafe condition on these products. 

DATES: We must receive comments on 

this proposed AD by October 29, 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 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– 

0790; 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: Neil 

Doh, Aerospace Engineer, Aviation 

Safety Section AIR–7B1, Boston ACO 

Branch, FAA, 1200 District Avenue, 

Burlington, MA 01803; telephone 781– 

238–7757. 

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– 

2018–0790; Product Identifier 2018– 

NM–078–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 

We issued AD 2010–14–05, 

Amendment 39–16350 (75 FR 37994, 

July 1, 2010) (‘‘AD 2010–14–05’’), for 

certain Bombardier Model CL–600– 

1A11 (600), CL–600–2A12 (601), CL– 

600–2B16 (601–3A, 601–3R, and 604 

Variants (including CL–605 Marketing 

Variant)) airplanes. AD 2010–14–05 

requires an inspection to determine the 

part numbers of the system 

accumulators numbers 1, 2, and 3 and 

brake accumulators numbers 2 and 3, 

and repetitive replacement of the 

accumulator. AD 2010–14–05 resulted 

from reports of the on-ground failure of 

the hydraulic accumulator screw cap or 

end cap, resulting in loss of the 

associated hydraulic system and highenergy impact damage to adjacent 

systems and structure. We issued AD 

2010–14–05 to address failure of one of 

the brake accumulator screw caps/end 

caps, resulting in impact damage 

causing loss of both hydraulic systems 

No. 2 and No. 3, with consequent loss 

of both braking and nose wheel steering 

and the potential for a runway 

excursion. 

Actions Since AD 2010–14–05 Was 

Issued 

Since we issued AD 2010–14–05, we 

have determined that new or more 

restrictive airworthiness limitations and 

additional actions are necessary to 

address the unsafe condition. 

Transport Canada Civil Aviation 

(TCCA), which is the aviation authority 

for Canada, has issued Canadian AD 

CF–2009–39R1, issued October 13, 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–600–1A11 (600), CL–600– 

2A12 (601), and CL–600–2B16 (601–3A, 

601–3R, and 604 Variants) airplanes. 

The MCAI states: 

Seven cases of on-ground hydraulic 

accumulator screw cap or end cap failure 

have been experienced on CL–600–2B19 

(CRJ) aircraft, resulting in loss of the 

associated hydraulic system and high-energy 

impact damage to adjacent systems and 

structure. The lowest number of flight cycles 

accumulated at the time of failure, to date, 

has been 6991 flight cycles. 

Although there have been no failures to 

date on any CL–600–1A11, CL–600–2A12 or 

CL–600–2B16 aircraft, the same accumulators 

as those installed on the CL–600–2B19, Part 

Numbers (P/N) 08–60163–002 and 08– 

60164–002 are installed on some of the 

aircraft listed in the Applicability section of 

this directive. 

Notes: 

1. Earlier accumulators, P/Ns 2770571– 

102, 2770571–103, 2770571–104 and 

2770571–105, were installed in production 

on the following aircraft: CL–600–1A11 [all 

Serial Numbers (S/Ns)], CL–600–2A12 (all S/ 

Ns) and CL–600–2B16 (S/Ns 5001 through 

5194 and 5301 through 5524 only). These 

accumulators do not require inspection or 

replacement. However, if any of the 

accumulators with the above P/Ns have been 

replaced in-service by P/Ns 08–60163–002 

and 08–60164–002, these latter accumulators 

require replacement. 

2. Prior to issuance of [Canadian] AD CF– 

2009–39, the only accumulators ever 

installed in production on CL–600–2B16 


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aircraft, S/Ns 5525 through 5665 and 5701 

through 5908, are P/Ns 08–60163–002 and 

08–60164–002; these accumulators require 

replacement. 

3. After issuance of [Canadian] AD CF– 

2009–39 [which corresponded to FAA AD 

2010–14–05, Amendment 39–16350 (75 FR 

37994, July 1, 2010)], accumulators with P/ 

Ns specified in Note 2, above, began to 

feature various S/N suffixes. Only 

accumulators with S/N suffix ‘‘TNAE’’ do not 

require replacement, but they are subject to 

other mandatory actions detailed in this AD. 

4. Stainless steel accumulators P/Ns 

601R75139–3 (11094–4) and 601R75139–1 

(11093–4) were installed in production on 

CL–600–2B16 aircraft, S/Ns 5909 and 

subsequent. These accumulators do not 

require replacement, but they are subjected to 

other mandatory actions detailed in this AD. 

A detailed analysis of the systems and 

structure in the potential line of trajectory of 

a failed screw cap/end cap for each 

accumulator, P/Ns 08–60163–002 and 08– 

60164–002, has been conducted. On the 

Challengers, it has been identified that the 

worst case scenario would be a failure of 

system No. 1, 2 or 3 accumulator screw caps/ 

end caps (depending on the model), resulting 

in a potential uncontrolled fire in a nondesignated fire zone. 

The original version of this [Canadian] AD 

gave instructions to perform identification 

and records checks, where applicable, and 

replace accumulators, P/Ns 08–60163–002 

and 08–60164–002 within the time 

compliance specified. 

* * * * * 

The unsafe condition is potential 

impact damage that could cause loss of 

both hydraulic systems No. 2 and No. 3, 

and the consequent loss of both braking 

and nose wheel steering, the potential 

for a runway excursion, and damage to 

the airplane. Required actions include 

relocating certain accumulators. 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– 

0790. 

Related Service Information Under 1 

CFR Part 51 

The following Bombardier service 

information describes procedures for 

replacing hydraulic system 

accumulators with new, overhauled, or 

refurbished accumulators. These 

documents are distinct since they apply 

to different airplane models. 

• Service Bulletin 600–742, Revision 4, 

dated June 11, 2015 

• Service Bulletin 601–597, Revision 4, 

dated June 11, 2015 

• Service Bulletin 604–29–008, 

Revision 4, dated June 11, 2015 

• Service Bulletin 605–29–001, 

Revision 4, dated June 10, 2015 

The following Bombardier service 

information describes procedures for 

relocating hydraulic system 

accumulators. These documents are 

distinct since they apply to different 

airplane models in different 

configurations. 

• Service Bulletin 600–0764, dated 

October 8, 2015 

• Service Bulletin 600–0767, dated 

August 25, 2016 

• Service Bulletin 601–0633, dated 

October 8, 2015 

• Service Bulletin 601–0637, dated 

August 25, 2016 

• Service Bulletin 604–29–013, 

Revision 2, dated April 18, 2016 

• Service Bulletin 605–29–006, 

Revision 2, dated April 19, 2016 

The following Bombardier Time 

Limits/Maintenance Checks describe 

certain systems life limits of the safe life 

items. These documents are distinct 

since they apply to different airplane 

models in different configurations. 

• Bombardier Challenger 600 Time 

Limits/Maintenance Checks, PSP 605, 

Revision 39, dated January 8, 2018 

• Bombardier Challenger 601 Time 

Limits/Maintenance Checks, PSP 

601–5, Revision 46, dated January 8, 

2018 

• Bombardier Challenger 601 Time 

Limits/Maintenance Checks, PSP 

601A–5, Revision 42, dated January 8, 

2018 

• Bombardier Challenger 604 CL–604 

Time Limits/Maintenance Checks, 

Revision 30, dated December 4, 2017 

• Bombardier Challenger CL–605 Time 

Limits/Maintenance Checks, Revision 

18, dated December 4, 2017 

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 

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 the same 

type designs. 

This proposed AD would require 

revisions to certain operator 

maintenance documents to include new 

actions (e.g., inspections). Compliance 

with these actions is required by 14 CFR 

91.403(c). For airplanes that have been 

previously modified, altered, or repaired 

in the areas addressed by this proposed 

AD, the operator may not be able to 

accomplish the actions described in the 

revisions. In this situation, to comply 

with 14 CFR 91.403(c), the operator 

must request approval for an alternative 

method of compliance according to 

paragraph (n)(1) of this proposed AD. 

The request should include a 

description of changes to the required 

inspections that will ensure the 

continued operational safety of the 

airplane. 

Difference Between Proposed AD and 

MCAI 

Although the MCAI placed no 

restrictions on special flight permits, 

this proposed AD would limit ferry 

flights by requiring an engineering 

recommendation from Bombardier as 

well as approval from the Flight 

Standards District Office. This 

difference has been coordinated with 

TCCA. 

Costs of Compliance 

We estimate that this proposed AD 

affects 130 airplanes of U.S. registry. We 

estimate the following costs to comply 

with this proposed AD: 

ESTIMATED COSTS FOR REQUIRED ACTIONS

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

Retained actions: 20 work-hours × 

$85 per hour = $,1,700.

$7,717 ................................................ $9,417 ................................................ $1,224,210. 

New actions: Up to 170 work-hours × 

$85 per hour = Up to $14,450.

Up to $41,635 .................................... Up to $56,085 .................................... Up to $7,291,050. 


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For the new maintenance/inspection 

program revision, we have determined 

that this action takes an average of 90 

work-hours per operator, although we 

recognize that this number may vary 

from operator to operator. In the past, 

we have estimated that this action takes 

1 work-hour per airplane. Since 

operators incorporate maintenance or 

inspection program changes for their 

affected fleet, we have determined that 

a per-operator estimate is more accurate 

than a per-airplane estimate. Therefore, 

we estimate the total cost per operator 

to be $7,650 (90 work-hours x $85 per 

work-hour). 

According to the manufacturer, some 

or all of the costs of this proposed 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 known 

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 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) 

2010–14–05, Amendment 39–16350 (75 

FR 37994, July 1, 2010), and adding the 

following new AD: 

Bombardier, Inc.: Docket No. FAA–2018– 

0790; Product Identifier 2018–NM–078– 

AD. 

(a) Comments Due Date 

We must receive comments by October 29, 

2018. 

(b) Affected ADs 

This AD replaces AD 2010–14–05, 

Amendment 39–16350 (75 FR 37994, July 1, 

2010) (‘‘AD 2010–14–05’’). 

(c) Applicability 

This AD applies to the Bombardier, Inc., 

airplanes, certificated in any category, 

identified in paragraphs (c)(1) through (c)(5) 

of this AD. 

(1) Model CL–600–1A11 (600) airplanes, 

serial numbers 1004 through 1085 inclusive. 

(2) Model CL–600–2A12 (601) airplanes, 

serial numbers 3001 through 3066 inclusive. 

(3) Model CL–600–2B16 airplanes (601–3A 

Variant), serial numbers 5001 through 5134 

inclusive. 

(4) Model CL–600–2B16 airplanes (601–3R 

Variant), serial numbers 5135 through 5194 

inclusive. 

(5) Model CL–600–2B16 airplanes (604 

Variant), serial numbers 5301 through 5665 

inclusive and 5701 and subsequent. 

Note 1 to paragraph (c) of this AD: Certain 

Model CL–600–2B16 (604 Variant) airplanes 

might be referred to by the marketing 

designation CL–605. 

(d) Subject 

Air Transport Association (ATA) of 

America Code 29, Hydraulic power. 

(e) Reason 

This AD was prompted by reports of onground hydraulic accumulator screw cap or 

end cap failure that resulted in the loss of the 

associated hydraulic system and high-energy 

impact damage to adjacent systems and 

structure. We are issuing this AD to address 

failure of one of the brake accumulator screw 

caps/end caps, which could result in impact 

damage causing loss of both hydraulic 

systems No. 2 and No. 3, and the consequent 

loss of both braking and nose wheel steering, 

the potential for a runway excursion, and 

damage to the airplane. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Retained Part Number Inspection and 

Accumulator Replacement, With Revised 

Formatting, Service Information, and 

Affected Part Numbers 

This paragraph restates the requirements of 

paragraph (g) of AD 2010–14–05, with 

revised formatting, service information, and 

affected part numbers. Do the following 

actions as applicable. 

(1) Within 50 flight hours after August 5, 

2010 (the effective date of AD 2010–14–05), 

inspect to determine the part numbers of the 

system accumulators numbers 1, 2, and 3, 

and brake accumulators numbers 2 and 3 that 

are installed on the airplane. A review of 

airplane maintenance records is acceptable in 

lieu of this inspection if the part number of 

each accumulator can be conclusively 

determined from that review. If all of the 

installed accumulators have part number 

(P/N) 2770571–102, 2770571–103, 2770571– 

104, 2770571–105, 601R75139–3 (11094–4), 

or 601R75139–1 (11093–4), no further action 

is required by paragraph (g) of this AD. 

(2) Except as provided in paragraph (g)(1) 

of this AD: At the applicable time in 

paragraph (g)(2)(i), (g)(2)(ii), or (g)(2)(iii) of 

this AD, replace the accumulator with a new, 

overhauled, or refurbished accumulator with 

the same part number, in accordance with 

the Accomplishment Instructions of the 

applicable service bulletin listed in figure 1 

to paragraphs (g)(2) and (g)(3) of this AD. 

(i) For each accumulator having P/Ns 08– 

60163–002 (601R75138–1), and 08–60164– 

002 (601R75138–3), as applicable, that has 

accumulated more than 3,650 total flight 

cycles as of August 5, 2010 (the effective date 

of AD 2010–14–05): Replace the accumulator 

within 100 flight cycles after August 5, 2010. 

(ii) For each accumulator having P/N 08– 

60163–002 (601R75138–1), and 08–60164– 

002 (601R75138–3), as applicable, that has 

accumulated 3,650 total flight cycles or fewer 


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as of August 5, 2010: Replace the 

accumulator before the accumulation of 

3,750 total flight cycles on the accumulator. 

(iii) For each accumulator having P/N 08– 

60163–002 (601R75138–1), and 08–60164– 

002 (601R75138–3), as applicable, for which 

it is not possible to determine the number of 

flight cycles accumulated: Replace the 

accumulator within 100 flight cycles after 

August 5, 2010. 

(3) Thereafter, before the accumulation of 

3,750 total flight cycles on any accumulator 

having P/Ns 08–60163–002 (601R75138–1), 

and 08–60164–002 (601R75138–3), as 

applicable, replace the accumulator with a 

new, overhauled, or refurbished accumulator 

having the same part number, in accordance 

with the Accomplishment Instructions of the 

applicable service bulletin listed in figure 1 

to paragraphs (g)(2) and (g)(3) of this AD. 

(h) New Provision of This AD: Terminating 

Action for Certain Accumulators 

For each accumulator with one of the 

following part number and serial number 

(S/N) suffixes, the repetitive replacement 

specified in paragraphs (g)(2) and (g)(3) of 

this AD is not required. 

(1) P/N 08–60163–002 with S/N suffix TNAE 

(2) P/N 08–601–002 with S/N suffix TNAE 

(3) P/N 601R75139–3 (11094–4) 

(4) P/N 601R75139–1 (11093–4) 

(i) New Requirement of This AD: Relocation 

of Accumulators 

Within 60 months or 2,400 flight cycles, 

whichever occurs first after the effective date 

of this AD, relocate the hydraulic system 

accumulators as specified in paragraphs (i)(1) 

through (i)(4) of this AD, as applicable. 

Relocation of the hydraulic system 

accumulators as required by this paragraph 

does not terminate any repetitive 

replacement required by paragraph (g)(2) or 

(g)(3) of this AD. 

(1) For Model CL–600–1A11 (600) 

airplanes, S/Ns 1004 through 1085 inclusive: 

Relocate accumulators as specified in 

paragraphs (i)(1)(i) and (i)(1)(ii) of this AD. 

(i) Relocate hydraulic system Nos. 1 and 2 

accumulators, in accordance with the 

Accomplishment Instructions of Bombardier 

Service Bulletin 601–0764, dated October 8, 

2015. 

(ii) Relocate hydraulic system No. 3 

accumulator, in accordance with the 

Accomplishment Instructions of Bombardier 

Service Bulletin 600–0767, dated August 25, 

2016. 

(2) For Model CL–600–2A12 (601) 

airplanes, S/Ns 3001 through 3066 inclusive, 

and Model CL–600–2B16 (601–3A and 601– 

3R Variants) airplanes, S/Ns 5001 through 

5194 inclusive: Relocate accumulators as 

specified in paragraphs (i)(2)(i) and (i)(2)(ii) 

of this AD. 

(i) Relocate hydraulic system Nos. 1 and 2 

accumulators, in accordance with the 

Accomplishment Instructions of Bombardier 

Service Bulletin 601–0633, dated October 8, 

2015. 

(ii) Relocate hydraulic system No. 3 

accumulator, in accordance with the 

Accomplishment Instructions of Bombardier 

Service Bulletin 601–0637, dated August 25, 

2016. 

(3) For Model CL–600–2B16 (604 Variant) 

airplanes, S/Ns 5301 through 5665 inclusive: 

Relocate hydraulic system No. 3 

accumulator, in accordance with the 

Accomplishment Instructions of Bombardier 

Service Bulletin 604–29–013, Revision 2, 

dated April 18, 2016. 

(4) For Model CL–600–2B16 (605) 

airplanes, S/Ns 5701 and subsequent (i.e., 

Model CL–600–2B16 (604 Variant), referred 

to by the marketing designation CL–605): 

Relocate hydraulic system No. 3 

accumulator, in accordance with the 

Accomplishment Instructions of Bombardier 

Service Bulletin 605–29–006, Revision 2, 

dated April 19, 2016. 

(j) New Requirement of This AD: Revision of 

Maintenance/Inspection Program 

Within 50 flight hours after the effective 

date of this AD, revise the maintenance or 

inspection program, as applicable, to 

incorporate the tasks specified in figure 2 to 

paragraph (j) of this AD. 


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(k) No Alternative Actions or Intervals 

After the maintenance or inspection 

program has been revised as required by 

paragraph (j) of this AD, no alternative 

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

used unless the actions or intervals are 

approved as an alternative method of 

compliance (AMOC) in accordance with the 

procedures specified in paragraph (n)(1) of 

this AD. 

(l) Credit for Previous Actions 

(1) Replacement of an accumulator with a 

new accumulator having the same part 

number is also acceptable for compliance 

with the requirements of paragraphs (g)(2) 

and (g)(3) of this AD, if done before August 

5, 2010 (the effective date of AD 2010–14– 

05), in accordance with the applicable 

service bulletin listed in figure 3 to paragraph 

(l)(1) of this AD. This service information is 

not incorporated by reference in this AD. 


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(2) Replacement of an accumulator with a 

new accumulator having the same part 

number is also acceptable for compliance 

with the requirements of paragraphs (g)(2) 

and (g)(3) of this AD, if done before the 

effective date of this AD in accordance with 

the applicable service bulletin listed in figure 

4 to paragraph (l)(2) of this AD. This service 

information is not incorporated by reference 

in this AD. 


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(3) This paragraph provides credit for 

actions required by paragraph (i)(3) of this 

AD, if those actions were performed before 

the effective date of this AD, in accordance 

with Bombardier Service Bulletin 604–29– 

013, dated April 30, 2015; or Bombardier 

Service Bulletin 604–29–013, Revision 1, 

dated October 19, 2015. This service 

information is not incorporated by reference 

in this AD. 

(4) This paragraph provides credit for 

actions required by paragraph (i)(4) of this 

AD, if those actions were performed before 

the effective date of this AD, in accordance 

with Bombardier Service Bulletin 605–29– 

006, dated April 30, 2015; or Bombardier 

Service Bulletin 605–29–006, Revision 1, 

dated October 19, 2015. This service 

information is not incorporated by reference 

in this AD. 

(m) Special Flight Permit 

Special flight permits may be issued in 

accordance with sections 21.197 and 21.199 

of the Federal Aviation Regulations (14 CFR 

21.197 and 21.199) to operate the airplane to 

a location where the airplane can be 

modified, provided the following conditions 

are met: 

(1) An engineering recommendation must 

be obtained via the Bombardier process 

Service Request for Product Support Action 

(SRPSA) at SRPSA@aerobombardier.com. 

(2) Approval of the special flight permit 

must be obtained from the Flight Standards 

District Office. 

(n) Other FAA AD Provisions 

(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. 

(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) AMOC 15–76R1 and AMOC 15–53, 

approved previously for AD 2010–14–05, are 

approved as AMOCs for the corresponding 

provisions of paragraph (g)(2) of this AD. 

(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’s TCCA Design 

Approval Organization (DAO). If approved by 

the DAO, the approval must include the 

DAO-authorized signature. 

(o) Related Information 

(1) Refer to Mandatory Continuing 

Airworthiness Information (MCAI) Canadian 

AD CF–2009–39R1, dated October 13, 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–2018–0790. 

(2) For more information about this AD, 

contact Neil Doh, Aerospace Engineer, 

Aviation Safety Section AIR–7B1, Boston 

ACO Branch, FAA, 1200 District Avenue, 

Burlington, MA 01803; telephone 781–238– 

7757. 

(3) For service information identified in 

this AD, contact Bombardier, Inc., 400 CoˆteVertu 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. 

Issued in Des Moines, Washington, on 

August 24, 2018. 

James Cashdollar, 

Acting Director, System Oversight Division, 

Aircraft Certification Service. 

[FR Doc. 2018–19759 Filed 9–13–18; 8:45 am] 

BILLING CODE 4910–13–P 


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