Federal Register / Vol. 76, No. 202 / Wednesday, October 19, 2011 / Proposed Rules 64847 

(6) Thereafter, within every 350 cyclessince-the-last-engine core vibration survey, 

perform the engine core vibration survey as 

required in paragraphs (k)(1) through (k)(5) of 

this AD. 

(7) If the engine has experienced any 

vibration reported by maintenance or flight 

crew that is suspected to be caused by the 

engine core (N2), perform the engine core 

vibration survey as required in paragraphs 

(k)(1) through (k)(5) of this AD within 10 

cycles after the report. 

(l) Initial and Repetitive FPI of LPT Rotor 

Stage 3 Disks 

(1) At the next shop visit after the effective 

date of this AD: 

(i) Clean the LPT rotor stage 3 disk forward 

spacer arm, including the use of a wetabrasive blast to eliminate residual or 

background fluorescence. 

(ii) Perform an FPI of the LPT rotor stage 

3 disk forward spacer arm for cracks and for 

a band of fluorescence. Include all areas of 

the disk forward spacer arm and the inner 

diameter surface forward cone body (forward 

spacer arm) of the LPT rotor stage 3 disk. 

(iii) Remove the disk from service before 

further flight if a crack or a band of 

fluorescence is present. 

(2) Thereafter, clean and perform an FPI of 

the LPT rotor stage 3 disk forward spacer 

arm, as specified in paragraphs (l)(1)(i) 

through (l)(1)(iii) of this AD, at each engine 

shop visit that occurs after 1,000 cyclessince-the last FPI of the LPT rotor stage 3 

disk forward spacer arm. 

(m) Removal of LPT Rotor Stage 3 Disks 

Remove LPT rotor stage 3 disks listed in 

Table 1 from service as follows: 

(1) For disks that have fewer than 3,200 

flight cycles since new (CSN) on the effective 

date of this AD, remove the disk from service 

before exceeding 6,200 CSN. 

(2) For disks that have 3,200 CSN or more 

on the effective date of this AD, do the 

following: 

(i) If the engine has a shop visit before the 

disk exceeds 6,200 CSN, remove the disk 

from service before exceeding 6,200 CSN. 

(ii) If the engine does not have a shop visit 

before the disk exceeds 6,200 CSN, remove 

the disk from service at the next shop visit 

after 6,200 CSN, not to exceed 3,000 cycles 

from the effective date of this AD. 

(n) Installation Prohibition 

(1) After the effective date of this AD, do 

not install or reinstall in any engine any LPT 

rotor stage 3 disk that exceeds the new life 

limit of 6,200 CSN. 

(2) Remove from service any LPT rotor 

stage 3 disk that is installed or re-installed 

after the effective date of this AD, before the 

disk exceeds the new life limit of 6,200 CSN. 

(o) Definitions 

(1) For the purposes of this AD, an EGT 

above redline is a confirmed overtemperature indication that is not a result of 

EGT system error. 

(2) For the purposes of this AD, a shift in 

the smoothed EGT trending data is a shift in 

a rolling average of EGT readings that can be 

confirmed by a corresponding shift in the 

trending of fuel flow or fan speed/core speed 

(N1/N2) relationship. You can find further 

guidance about evaluating EGT trend data in 

GE Company Service Rep Tip 373 

’’Guidelines For Parameter Trend 

Monitoring.’’ 

(3) For the purposes of this AD, an engine 

shop visit is the induction of an engine into 

the shop after the effective date of this AD, 

where the separation of a major engine flange 

occurs; except the following maintenance 

actions, or any combination, are not 

considered engine shop visits: 

(i) Introduction of an engine into a shop 

solely for removal of the compressor top or 

bottom case for airfoil maintenance or 

variable stator vane bushing replacement. 

(ii) Introduction of an engine into a shop 

solely for removal or replacement of the stage 

1 fan disk. 

(iii) Introduction of an engine into a shop 

solely for replacement of the turbine rear 

frame. 

(iv) Introduction of an engine into a shop 

solely for replacement of the accessory 

gearbox or transfer gearbox, or both. 

(v) Introduction of an engine into a shop 

solely for replacement of the fan forward 

case. 

(p) Previous Credit 

(1) A borescope inspection performed 

before the effective date of this AD using AD 

2010–06–15, Amendment 39–16240 (75 FR 

12661, March 17, 2010) or AD 2010–12–10, 

Amendment 39–16331 (75 FR 32649, June 9, 

2010) or AD 2011–02–07, Amendment 39– 

16580 (76 FR 6323, February 4, 2011) within 

the last 75 cycles, satisfies the initial 

borescope inspection requirement in 

paragraph (f)(1) of this AD. 

(2) A UI performed before the effective date 

of this AD using AD 2011–02–07, 

Amendment 39–16580 (76 FR 6323, February 

4, 2011) or GE SB No. CF6–50–SB 72–1312, 

dated August 9, 2010 or GE SB No. CF6–50– 

SB 72–1312 Revision 1, dated October 18, 

2010, satisfies the inspection requirement in 

paragraph (j) of this AD. 

(3) An engine core vibration survey 

performed before the effective date of this AD 

using AD 2011–02–07, Amendment 39– 

16580 (76 FR 6323, February 4, 2011) or GE 

SB No. CF6–50–SB 72–1313, dated August 9, 

2010 or GE SB No. CF6–50–SB 72–1313 

Revision 1, dated October 18, 2010, within 

the last 350 cycles, satisfies the initial survey 

requirement in paragraphs (k)(1) through 

(k)(5) of this AD. 

(4) An FPI of the LPT rotor stage 3 disk 

forward spacer arm performed before the 

effective date of this AD using AD 2011–18– 

01, Amendment 39–16783 (75 FR 3, 52213, 

August 22, 2011), within the last 1,000 flight 

cycles of the LPT rotor stage 3 disk, satisfies 

the initial inspection requirements in 

paragraphs (l)(1)(i) through (l)(1)(iii) of this 

AD. 

(q) Alternative Methods of Compliance 

(AMOCs) 

(1) AMOCs previously approved for AD 

2010–06–15, Amendment 39–16240 (75 FR 

12661, March 17, 2010) are not approved for 

this AD. However, AMOCs previously 

approved for AD 2010–12–10, Amendment 

39–16331 (75 FR 32649, June 9, 2010), AD 

2011–02–07, Amendment 39–16580 (76 FR 

6323, February 4, 2011), or AD 2011–18–01, 

Amendment 39–16783 (76 FR 52213, August 

22, 2011) are approved for this AD. 

(2) The Manager, Engine Certification 

Office, may approve alternative methods of 

compliance for this AD. Use the procedures 

found in 14 CFR 39.19 to make your request. 

(r) Related Information 

(1) For more information about this AD, 

contact Tomasz Rakowski, Aerospace 

Engineer, Engine Certification Office, FAA, 

Engine & Propeller Directorate, 12 New 

England Executive Park, Burlington, MA 

01803; phone: 781–238–7735; fax: 781–238– 

7199; e-mail: tomasz.rakowski@faa.gov. 

(2) For service information identified in 

this AD, contact General Electric Company, 

GE-Aviation, Room 285, 1 Neumann Way, 

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

e-mail: geae.aoc@ge.com. You may review 

copies of the referenced service information 

at the FAA, Engine & Propeller Directorate, 

12 New England Executive Park, Burlington, 

MA. For information on the availability of 

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

Issued in Burlington, Massachusetts, on 

October 13, 2011. 

Peter A. White, 

Manager, Engine & Propeller Directorate, 

Aircraft Certification Service. 

[FR Doc. 2011–27006 Filed 10–18–11; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2011–1090; Directorate 

Identifier 2011–NM–138–AD] 

RIN 2120–AA64 

Airworthiness Directives; Bombardier, 

Inc. Model DHC–8–400 Series 

Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Notice of proposed rulemaking 

(NPRM). 

SUMMARY: We propose to adopt a new 

airworthiness directive (AD) for the 

products listed above. This proposed 

AD results from mandatory continuing 

airworthiness information (MCAI) 

originated by an aviation authority of 

another country to identify and correct 

an unsafe condition on an aviation 

product. The MCAI describes the unsafe 

condition as: 

One case of the inability to open the 

airstair door while on ground was reported 

in service. The airstair door seal did not 

deflate, preventing the airstair door from 

opening. It was found that the existing 

airstair door pneumatic shut-off valve control 

logic prevents the airstair door seal from 


srobinson on DSK4SPTVN1PROD with PROPOSALS
64848 Federal Register / Vol. 76, No. 202 / Wednesday, October 19, 2011 / Proposed Rules 

deflating due to a single Input/Output 

Module failure under certain conditions. The 

inability to open the airstair door could 

impede evacuation in the event of an 

emergency. 

* * * * * 

The proposed AD would require 

actions that are intended to address the 

unsafe condition described in the MCAI. 

DATES: We must receive comments on 

this proposed AD by December 5, 2011. 

ADDRESSES: You may send comments 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: U.S. Department of 

Transportation, Docket Operations, 

M–30, West Building Ground Floor, 

Room W12–140, 1200 New Jersey 

Avenue, SE., Washington, DC, between 

9 a.m. and 5 p.m., Monday through 

Friday, except Federal holidays. 

For service information identified in 

this proposed 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; e-mail 

thd.qseries@aero.bombardier.com; 

Internet http://www.bombardier.com. 

You may review copies of the 

referenced service information at the 

FAA, Transport Airplane Directorate, 

1601 Lind Avenue, SW., Renton, 

Washington. For information on the 

availability of this material at the FAA, 

call 425–227–1221. 

Examining the AD Docket 

You may examine the AD docket on 

the Internet at http://www.regulations.

gov; or in person at the Docket 

Operations office between 9 a.m. and 5 

p.m., Monday through Friday, except 

Federal holidays. The AD docket 

contains this proposed AD, 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: 

Cesar Gomez, Aerospace Engineer, 

Airframe and Mechanical Systems 

Branch, ANE–171, FAA, New York 

Aircraft Certification Office, 1600 

Stewart Avenue, Suite 410, Westbury, 

New York 11590; telephone (516) 228– 

7318; fax (516) 794–5531. 

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–2011–1090; Directorate Identifier 

2011–NM–138–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 

The Transport Canada Civil Aviation 

(TCCA), which is the aviation authority 

for Canada, has issued Canadian 

Airworthiness Directive CF–2011–15, 

dated June 20, 2011 (referred to after 

this as ‘‘the MCAI’’), to correct an unsafe 

condition for the specified products. 

The MCAI states: 

One case of the inability to open the 

airstair door while on ground was reported 

in service. The airstair door seal did not 

deflate, preventing the airstair door from 

opening. It was found that the existing 

airstair door pneumatic shut-off valve control 

logic prevents the airstair door seal from 

deflating due to a single Input/Output 

Module failure under certain conditions. The 

inability to open the airstair door could 

impede evacuation in the event of an 

emergency. 

This [Canadian] directive mandates the 

wiring changes [ModSum 4–126513, Seal 

System Shut Off Valve Control Logic Change] 

to prevent the above-mentioned failure 

conditions. 

You may obtain further information by 

examining the MCAI in the AD docket. 

Relevant Service Information 

Bombardier, Inc. has issued Service 

Bulletin 84–52–69, Revision C, dated 

June 28, 2011. The actions described in 

this service information are intended to 

correct the unsafe condition identified 

in the MCAI. 

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 design. 

Differences Between This AD and the 

MCAI or Service Information 

We have reviewed the MCAI and 

related service information and, in 

general, agree with their substance. But 

we might have found it necessary to use 

different words from those in the MCAI 

to ensure the AD is clear for U.S. 

operators and is enforceable. In making 

these changes, we do not intend to differ 

substantively from the information 

provided in the MCAI and related 

service information. 

We might also have proposed 

different actions in this AD from those 

in the MCAI in order to follow FAA 

policies. Any such differences are 

highlighted in a NOTE within the 

proposed AD. 

Costs of Compliance 

Based on the service information, we 

estimate that this proposed AD would 

affect about 81 products of U.S. registry. 

We also estimate that it would take 

about 12 work-hours per product to 

comply with the basic requirements of 

this proposed AD. The average labor 

rate is $85 per work-hour. Required 

parts would cost about $0 per product. 

Where the service information lists 

required parts costs that are covered 

under warranty, we have assumed that 

there will be no charge for these parts. 

As we do not control warranty coverage 

for affected parties, some parties may 

incur costs higher than estimated here. 

Based on these figures, we estimate the 

cost of the proposed AD on U.S. 

operators to be $82,620, or $1,020 per 

product. 

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 


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Federal Register / Vol. 76, No. 202 / Wednesday, October 19, 2011 / Proposed Rules 64849 

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. 

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); and 

3. 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. 

We prepared a regulatory evaluation 

of the estimated costs to comply with 

this proposed AD and placed it in the 

AD docket. 

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 adding 

the following new AD: 

Bombardier, Inc.: Docket No. FAA–2011– 

1090; Directorate Identifier 2011–NM– 

138–AD. 

Comments Due Date 

(a) We must receive comments by 

December 5, 2011. 

Affected ADs 

(b) None. 

Applicability 

(c) This AD applies to Bombardier, Inc. 

Model DHC–8–400, –401, and –402 

airplanes, certificated in any category, serial 

numbers 4001 through 4361 inclusive. 

Subject 

(d) Air Transport Association (ATA) of 

America Code 52: Doors. 

Reason 

(e) The mandatory continuing 

airworthiness information (MCAI) states: 

One case of the inability to open the 

airstair door while on ground was reported 

in service. The airstair door seal did not 

deflate, preventing the airstair door from 

opening. It was found that the existing 

airstair door pneumatic shut-off valve control 

logic prevents the airstair door seal from 

deflating due to a single Input/Output 

Module failure under certain conditions. The 

inability to open the airstair door could 

impede evacuation in the event of an 

emergency. 

* * * * * 

Compliance 

(f) You are responsible for having the 

actions required by this AD performed within 

the compliance times specified, unless the 

actions have already been done. 

Actions 

(g) Within 6,000 flight hours after the 

effective date of this AD: Incorporate 

ModSum 4–126513, Seal System Shut Off 

Valve Control Logic Change, in accordance 

with the Accomplishment Instructions of 

Bombardier Service Bulletin 84–52–69, 

Revision C, dated June 28, 2011. 

Credit for Actions Accomplished in 

Accordance With Previous Service 

Information 

(h) Actions accomplished before the 

effective date of this AD according to 

Bombardier Service Bulletin 84–52–69, dated 

January 28, 2011; Revision A, dated April 26, 

2011; or Revision B, dated May 9, 2011; are 

considered acceptable for compliance with 

the corresponding actions specified in 

paragraph (g) of this AD. 

FAA AD Differences 

Note 1: This AD differs from the MCAI 

and/or service information as follows: No 

differences. 

Other FAA AD Provisions 

(i) The following provisions also apply to 

this AD: 

(1) Alternative Methods of Compliance 

(AMOCs): The Manager, New York Aircraft 

Certification Office (ACO), ANE–170, 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 ACO, send it to ATTN: 

Program Manager, Continuing Operational 

Safety, FAA, New York ACO, 1600 Stewart 

Avenue, Suite 410, Westbury, New York 

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. The AMOC 

approval letter must specifically reference 

this AD. 

(2) Airworthy Product: For any requirement 

in this AD to obtain corrective actions from 

a manufacturer or other source, use these 

actions if they are FAA-approved. Corrective 

actions are considered FAA-approved if they 

are approved by the State of Design Authority 

(or their delegated agent). You are required 

to assure the product is airworthy before it 

is returned to service. 

Related Information 

(j) Refer to MCAI Canadian Airworthiness 

Directive CF–2011–15, dated June 20, 2011; 

and Bombardier Service Bulletin 84–52–69, 

Revision C, dated June 28, 2011; for related 

information. 

Issued in Renton, Washington, on 

October 6, 2011. 

Ali Bahrami, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 2011–27009 Filed 10–18–11; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2011–1088; Directorate 

Identifier 2011–NM–099–AD] 

RIN 2120–AA64 

Airworthiness Directives; Bombardier, 

Inc. Model DHC–8–400 Series 

Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Notice of proposed rulemaking 

(NPRM). 

SUMMARY: We propose to adopt a new 

airworthiness directive (AD) for the 

products listed above. This proposed 

AD results from mandatory continuing 

airworthiness information (MCAI) 

originated by an aviation authority of 

another country to identify and correct 

an unsafe condition on an aviation 

product. The MCAI describes the unsafe 

condition as: 

Several operators have reported difficulties 

in opening the airstair door. Investigation 

revealed that the airstair door gearbox drain 

paths were blocked by sealant, causing water 

to accumulate and freeze in the gearbox 

assembly. An airstair door that is unable to 

be opened could hinder evacuation in the 

event of an emergency. 

* * * * * 

The proposed AD would require actions 

that are intended to address the unsafe 

condition described in the MCAI. 

DATES: We must receive comments on 

this proposed AD by December 5, 2011. 

ADDRESSES: You may send comments by 

any of the following methods: 


srobinson on DSK4SPTVN1PROD with PROPOSALS