Federal Register / Vol. 80, No. 72 / Wednesday, April 15, 2015 / Proposed Rules 20181 

(iii) If the minimum thickness of the wall 

is 0.130 inch or greater and less than 0.140 

inch and the machining defect is not present, 

within 48 months or 3,000 flight cycles after 

the effective date of this AD, whichever 

occurs first, replace the inboard actuator 

attach fitting of the outboard flap, in 

accordance with Part 4 of the 

Accomplishment Instructions of Boeing Alert 

Service Bulletin 747–57A2343, Revision 1, 

dated June 23, 2014. 

(iv) If the minimum thickness of the wall 

is 0.130 inch or greater and less than 0.140 

inch and the machining defect is present, 

before further flight, replace the inboard 

actuator attach fitting of the outboard flap, in 

accordance with Part 4 of the 

Accomplishment Instructions of Boeing Alert 

Service Bulletin 747–57A2343, Revision 1, 

dated June 23, 2014. 

(2) Replace the inboard actuator attach 

fitting of the outboard flap, in accordance 

with Part 4 of the Accomplishment 

Instructions of Boeing Alert Service Bulletin 

747–57A2343, Revision 1, dated June 23, 

2014. 

(k) New Inspection or Replacement for 

Certain Fittings That Were Previously 

Inspected 

For airplanes with any inboard actuator 

attach fitting having P/N 65B08564–7 

installed and the fitting was inspected in 

accordance with Part 3 of the 

Accomplishment Instructions of Boeing Alert 

Service Bulletin 747–57A2343, dated 

September 12, 2013: Within 24 months after 

the effective date of this AD, do the actions 

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

AD. 

(1) Do a detailed inspection of the inner 

conical section for machining defects only, in 

accordance with Part 3 of the 

Accomplishment Instructions of Boeing Alert 

Service Bulletin 747–57A2343, Revision 1, 

dated June 23, 2014. 

(i) If any machining defect is found and the 

minimum thickness of the wall is 0.140 inch 

or greater: Before further flight, do the actions 

specified in paragraph (k)(1)(i)(A) or 

(k)(1)(i)(B) of this AD. 

(A) Overhaul the inboard actuator attach 

fitting of the outboard flap, in accordance 

with Part 5 of the Accomplishment 

Instructions of Boeing Alert Service Bulletin 

747–57A2343, Revision 1, dated June 23, 

2014. 

(B) Replace the inboard actuator attach 

fitting of the outboard flap, in accordance 

with Part 4 of the Accomplishment 

Instructions of Boeing Alert Service Bulletin 

747–57A2343, Revision 1, dated June 23, 

2014. 

(ii) If any machining defect is found and 

the minimum thickness of the wall is 0.130 

inch or greater and less than 0.140 inch: 

Before further flight, replace the inboard 

actuator attach fitting of the outboard flap, in 

accordance with Part 4 of the 

Accomplishment Instructions of Boeing Alert 

Service Bulletin 747–57A2343, Revision 1, 

dated June 23, 2014. 

(iii) If no machining defect is found and 

the minimum thickness of the wall is 0.130 

inch or greater and less than 0.140 inch: 

Within 48 months or 3,000 flight cycles after 

the effective date of this AD, whichever 

occurs first, replace the inboard actuator 

attach fitting of the outboard flap, in 

accordance with Part 4 of the 

Accomplishment Instructions of Boeing Alert 

Service Bulletin 747–57A2343, Revision 1, 

dated June 23, 2014. 

(iv) If a machining defect is or is not found 

and the minimum thickness of the wall is 

less than 0.130 inch: Before further flight, 

replace the inboard actuator attach fitting of 

the outboard flap, in accordance with Part 4 

of the Accomplishment Instructions of 

Boeing Alert Service Bulletin 747–57A2343, 

Revision 1, dated June 23, 2014. 

(2) Replace the inboard actuator attach 

fitting of the outboard flap, in accordance 

with Part 4 of the Accomplishment 

Instructions of Boeing Alert Service Bulletin 

747–57A2343, Revision 1, dated June 23, 

2014. 

(l) Part Installation Limitation 

As of the effective date of this AD, no 

actuator attach fitting having P/N 65B08564– 

7 that meets the requirements of CONDITION 

5 or CONDITION 6 defined in Boeing Alert 

Service Bulletin 747–57A2343, dated 

September 12, 2013, may be installed on any 

airplane unless the inspection specified in 

paragraph (k)(1) of this AD is done and the 

applicable actions in paragraphs (k)(1)(i), 

(k)(1)(ii), (k)(1)(iii), and (k)(1)(iv) are done 

within the applicable times specified in 

paragraphs (k)(1)(i), (k)(1)(ii), (k)(1)(iii), and 

(k)(1)(iv) of this AD. 

(m) Alternative Methods of Compliance 

(AMOCs) 

(1) The Manager, Seattle Aircraft 

Certification Office (ACO), 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 ACO, send it to the 

attention of the person identified in 

paragraph (n)(1) of this AD. Information may 

be emailed to: 9-ANM-Seattle-ACO-AMOCRequests@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 

required by this AD if it is approved by the 

Boeing Commercial Airplanes Organization 

Designation Authorization (ODA) that has 

been authorized by the Manager, Seattle 

ACO, to make those findings. For a repair 

method to be approved, the repair must meet 

the certification basis of the airplane, and the 

approval must specifically refer to this AD. 

(4) If any service information contains 

steps that are identified as RC (Required for 

Compliance), those steps must be done to 

comply with this AD; any steps that are not 

identified as RC are recommended. Those 

steps that are not identified as RC may be 

deviated from using accepted methods in 

accordance with the operator’s maintenance 

or inspection program without obtaining 

approval of an AMOC provided the steps 

identified as RC can be done and the airplane 

can be put back in a serviceable condition. 

Any substitutions or changes to steps 

identified as RC require approval of an 

AMOC. 

(5) AMOCs approved for AD 2013–23–03, 

Amendment 39–17658 (78 FR 68345, 

November 14, 2013) are approved as AMOCs 

for the corresponding provisions of this AD. 

(n) Related Information 

(1) For more information about this AD, 

contact Nathan Weigand, Aerospace 

Engineer, Airframe Branch, ANM–120S, 

FAA, Seattle Aircraft Certification Office, 

1601 Lind Avenue SW., Renton, WA 98057– 

3356; phone: 425–917–6428; fax: 425–917– 

6590; email: nathan.p.weigand@faa.gov. 

(2) For service information identified in 

this AD, contact Boeing Commercial 

Airplanes, Attention: Data & Services 

Management, P. O. Box 3707, MC 2H–65, 

Seattle, WA 98124–2207; telephone 206– 

544–5000, extension 1; fax 206–766–5680; 

Internet https://www.myboeingfleet.com. You 

may view this 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. 

Issued in Renton, Washington, on April 6, 

2015. 

John P. Piccola, Jr., 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2015–08464 Filed 4–14–15; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2015–0827; Directorate 

Identifier 2014–NM–008–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) 2011–07– 

10, for certain Bombardier, Inc. Model 

BD–100–1A10 (Challenger 300) 

airplanes. AD 2011–07–10 currently 

requires revising the Airworthiness 

Limitations section of the Instructions 

for Continued Airworthiness; doing 

detailed visual inspections; removing 

discrepant material; cleaning the 

surfaces of the valves, the plug of the 

sensing port, and the cabin pressuresensing port plug; securing the 

insulation; installing a new safety valve, 

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20182 Federal Register / Vol. 80, No. 72 / Wednesday, April 15, 2015 / Proposed Rules 

and replacing certain cabin pressuresensing port plugs. Since we issued AD 

2011–07–10, we have received reports 

of in-flight loss of cabin pressurization 

that was attributed to partial blockage of 

a safety valve cabin pressure-sensing 

port in conjunction with a failed safety 

valve manometric capsule. This 

proposed AD would retain all 

requirements of AD 2011–07–10. This 

proposed AD would also require a 

detailed visual inspection of both safety 

valves and the surrounding area for 

foreign material, room temperature 

vulcanizing (RTV) silicone, 

contamination, foam on the bulkhead 

structure, tape or insulation, and loose 

material; and corrective actions if 

necessary. We are proposing this AD to 

detect and correct blockage of a safety 

valve cabin pressure-sensing port, 

which could result in loss of cabin 

pressure. 

DATES: We must receive comments on 

this proposed AD by June 1, 2015. 

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., 400 Coˆte-Vertu Road West, Dorval, 

Que ́bec H4S 1Y9, Canada; telephone 

514–855–5000; fax 514–855–7401; email 

thd.crj@aero.bombardier.com; Internet 

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

view this referenced service information 

at the FAA, Transport Airplane 

Directorate, 1601 Lind Avenue SW., 

Renton, WA. 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 by searching for 

and locating Docket No. FAA–2015– 

0827; 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 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: 

Luke Walker, Aerospace Engineer, 

Airframe and Mechanical Systems 

Branch, ANE–171, FAA, NY Aircraft 

Certification Office (ACO), 1600 Stewart 

Avenue, Suite 410, Westbury, NY 

11590; telephone 516–228–7363; 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–2015–0827; Directorate Identifier 

2014–NM–008–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 

On March 21, 2011, we issued AD 

2011–07–10, Amendment 39–16647 (76 

FR 17758, March 31, 2011). AD 2011– 

07–10 requires actions intended to 

address an unsafe condition on certain 

Bombardier, Inc. Model BD–100–1A10 

(Challenger 300) airplanes. AD 2011– 

07–10 superseded AD 2010–10–18, 

Amendment 39 16297 (75 FR 27406, 

May 17, 2010). 

Since we issued AD 2011–07–10, 

Amendment 39–16647 (76 FR 17758, 

March 31, 2011), we have received 

reports of in-flight loss of cabin 

pressurization that were attributed to 

partial blockage of a safety valve cabin 

pressure-sensing port in conjunction 

with a failed safety valve manometric 

capsule. 

Transport Canada Civil Aviation 

(TCCA), which is the aviation authority 

for Canada, has issued Canadian 

Airworthiness Directive CF–2010–06R1, 

dated August 8, 2013 (referred to after 

this as the Mandatory Continuing 

Airworthiness Information, or ‘‘the 

MCAI’’), to correct an unsafe condition 

for the specified products. The MCAI 

states: 

Investigation of a high altitude loss of 

cabin pressurization on a BD–100–1A10 

aeroplane determined that it was caused by 

a partial blockage of a safety valve cabin 

pressure-sensing port, in conjunction with a 

dormant failure/leakage of the safety valve 

manometric capsule. The blockage, caused by 

accumulation of lint/dust on the grid of the 

port plug, did not allow sufficient airflow 

through the cabin pressure-sensing port to 

compensate for the rate of leakage from the 

manometric capsule, resulting in the opening 

of the safety valve. It was also determined 

that failure of the manometric capsule alone 

would not result in the opening of the safety 

valve. 

The original issue of this [Canadian] AD 

mandated a revision of the maintenance 

schedule, the cleaning of the safety valves, 

the removal of material from the area 

surrounding the safety valves and the 

modification of the safety valves with a 

gridless cabin pressure-sensing port plug. 

Since the original issue of this [Canadian] 

AD, there have been two additional reported 

events of in-flight loss of cabin pressurization 

that were attributed to partial blockage of a 

safety valve cabin pressure-sensing port in 

conjunction with a failed safety valve 

manometric capsule. 

Bombardier Aerospace has determined that 

aeroplanes with a particular interior 

installation require improved instructions to 

clean the safety valves and their surrounding 

area. In addition, Aircraft Maintenance 

Manual tasks have been updated to ensure 

that inspection of the safety valves and their 

surrounding is carried out after any 

maintenance action. 

Revision 1 of this [Canadian] AD is issued 

to mandate inspection and cleaning of the 

safety valves and their surrounding area on 

the affected aeroplanes. 

Corrective actions include removing 

foreign material, cleaning surfaces of the 

safety valve and bulkhead, installing a 

new safety valve, removing loose tape, 

and trimming insulation. 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–2015– 

0827. 

Related Service Information Under 1 

CFR Part 51 

Bombardier has issued Service 

Bulletin 100–25–21, Revision 02, dated 

July 25, 2013. The service information 

describes procedures for a detailed 

visual inspection of both safety valves 

and the surrounding area for foreign 

material, RTV silicone, contamination, 

foam on the bulkhead structure, tape or 

insulation, and loose material, and 

applicable corrective actions. The 

actions described in this service 

information are intended to correct the 

unsafe condition identified in the 

MCAI. This service information is 

reasonably available; see ADDRESSES for 

ways to access this service information. 

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Federal Register / Vol. 80, No. 72 / Wednesday, April 15, 2015 / Proposed Rules 20183 

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. 

This AD requires 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 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 AD. The request should 

include a description of changes to the 

required inspections that will ensure the 

continued operational safety of the 

airplane. 

Costs of Compliance 

We estimate that this proposed AD 

affects 67 airplanes of U.S. registry. 

The actions required by AD 2011–07– 

10, Amendment 39–16647 (76 FR 

17758, March 31, 2011), and retained in 

this proposed AD take about 10 workhours per product, at an average labor 

rate of $85 per work-hour. Required 

parts cost $0 per product. Based on 

these figures, the estimated cost of the 

actions that were required by AD 2011– 

07–10 is $850 per product. 

We also estimate that it would take 

about 4 work-hours per product to 

comply with the basic requirements of 

this proposed AD. The average labor 

rate is $85 per work-hour. Based on 

these figures, we estimate the cost of 

this proposed AD on U.S. operators to 

be $22,780, or $340 per product. 

According to the manufacturer, 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 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. 

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 Directives (AD) 

2011–07–10, Amendment 39–16647 (76 

FR 17758, March 31, 2011), and adding 

the following new AD: 

Bombardier, Inc.: Docket No. FAA–2015– 

0827; Directorate Identifier 2014–NM– 

008–AD. 

(a) Comments Due Date 

We must receive comments by June 1, 

2015. 

(b) Affected ADs 

This AD replaces AD 2011–07–10, 

Amendment 39–16647 (76 FR 17758, March 

31, 2011). 

(c) Applicability 

This AD applies to Bombardier, Inc. Model 

BD–100–1A10 (Challenger 300) airplanes, 

certificated in any category, serial numbers 

20001 through 20274. 

(d) Subject 

Air Transport Association (ATA) of 

America Code 25, Equipment/Furnishings. 

(e) Reason 

This AD was prompted by reports of inflight loss of cabin pressurization that were 

attributed to partial blockage of a safety valve 

cabin pressure-sensing port in conjunction 

with a failed safety valve manometric 

capsule. We are issuing this AD to detect and 

correct blockage of a safety valve cabin 

pressure-sensing port, which could result in 

loss of cabin pressure. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Retained Revision 

This paragraph restates the requirements of 

paragraph (g) of AD 2011–07–10, 

Amendment 39–16647 (76 FR 17758, March 

31, 2011), with no changes. For all airplanes: 

Within 30 days after June 1, 2010 (the 

effective date of AD 2010–10–18, 

Amendment 39–16297 (75 FR 27406, May 17, 

2010)), revise the Airworthiness Limitations 

section of the Instructions for Continued 

Airworthiness by incorporating Tasks 21–31– 

09–101 and 21–31–09–102 in the Bombardier 

Temporary Revision (TR) 5–2–53, dated 

October 1, 2009, to Section 5–10–40, 

‘‘Certification Maintenance Requirements,’’ 

in Part 2 of Chapter 5 of Bombardier 

Challenger 300 BD–100 Time Limits/

Maintenance Checks. 

(1) For the new tasks identified in 

Bombardier TR 5–2–53, dated October 1, 

2009: For airplanes identified in the ‘‘Phasein’’ section of Bombardier TR 5–2–53, dated 

October 1, 2009, the initial compliance with 

the new tasks must be carried out in 

accordance with the phase-in schedule 

detailed in Bombardier TR 5–2–53, dated 

October 1, 2009, except where that TR 

specifies a compliance time from the date of 

the TR, this AD requires compliance within 

the specified time after June 1, 2010 (the 

effective date of AD 2010–10–18, 

Amendment 39–16297 (75 FR 27406, May 17, 

2010)). 

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20184 Federal Register / Vol. 80, No. 72 / Wednesday, April 15, 2015 / Proposed Rules 

Thereafter, except as provided by 

paragraph (n)(1) of this AD, no alternative to 

the task intervals may be used. 

(2) When information in Bombardier TR 5– 

2–53, dated October 1, 2009, has been 

included in the general revisions of the 

applicable Airworthiness Limitations section, 

that TR may be removed from that 

Airworthiness Limitations section of the 

Instructions for Continued Airworthiness. 

(h) Retained Inspection, Removal, Cleaning, 

and Installation 

This paragraph restates the requirements of 

paragraph (h) of AD 2011–07–10, 

Amendment 39–16647 (76 FR 17758, March 

31, 2011), with certain clarified compliance 

times. For airplanes having S/Ns 20003 

through 20173 inclusive, 20176, and 20177: 

Within 50 flight hours after June 1, 2010 (the 

effective date of AD 2010–10–18, 

Amendment 39–16297 (75 FR 27406, May 17, 

2010)), do a detailed visual inspection of the 

safety valves and surrounding areas for 

discrepant material (e.g., foreign material 

surrounding the safety valves, room 

temperature vulcanizing (RTV) sealant on 

safety valves, RTV excess on the bulkhead, 

tape near the safety valve opening, and, on 

certain airplanes, insulation near the safety 

valve opening, and foam in the area 

surrounding the safety valves) and a detailed 

visual inspection for contamination (e.g., 

RTV, dust, or lint) in the safety valve 

pressure ports, in accordance with the 

Accomplishment Instructions of Bombardier 

Service Bulletin 100–25–14, dated June 30, 

2008 (for airplanes having S/Ns 20124, 

20125, 20128, 20134, 20139, 20143, 20146, 

20148 through 20173 inclusive, 20176, and 

20177); or Bombardier Service Bulletin 100– 

25–21, dated June 30, 2008 (for airplanes 

having S/Ns 20003 through 20123 inclusive, 

20126, 20127, 20129 to 20133 inclusive, 

20135 to 20138 inclusive, 20140 through 

20142 inclusive, 20144, 20145, and 20147). 

(1) If any discrepant material is found 

during the detailed visual inspection, before 

further flight, remove the discrepant material, 

clean the surfaces of the valves, and secure 

the insulation, as applicable, in accordance 

with the Accomplishment Instructions of 

Bombardier Service Bulletin 100–25–14, 

dated June 30, 2008 (for airplanes having 

S/Ns 20124, 20125, 20128, 20134, 20139, 

20143, 20146, 20148 through 20173 

inclusive, 20176, and 20177); or Bombardier 

Service Bulletin 100–25–21, dated June 30, 

2008 (for airplanes having S/Ns 20003 

through 20123 inclusive, 20126, 20127, 

20129 through 20133 inclusive, 20135 

through 20138 inclusive, 20140 through 

20142 inclusive, 20144, 20145, and 20147). 

(2) If contamination (e.g., RTV, dust, or 

lint) is found on the safety valve pressure 

sensing ports, before further flight, do a 

detailed visual inspection of the outside and 

inside diameters of the pressure sensing port 

conduit for the presence of RTV; and before 

further flight do the actions specified in 

paragraph (h)(2)(i) and (h)(2)(ii) of this AD, 

as applicable; in accordance with the 

Accomplishment Instructions of Bombardier 

Service Bulletin 100–25–14, dated June 30, 

2008 (for airplanes having S/Ns 20124, 

20125, 20128, 20134, 20139, 20143, 20146, 

20148 through 20173 inclusive, 20176, and 

20177); or Bombardier Service Bulletin 100– 

25–21, dated June 30, 2008 (for airplanes 

having S/Ns 20003 through 20123 inclusive, 

20126, 20127, 20129 through 20133 

inclusive, 20135 through 20138 inclusive, 

20140 through 20142 inclusive, 20144, 

20145, and 20147). 

(i) If no RTV is found, clean the plug of the 

sensing port. 

(ii) If any RTV is found, install a new safety 

valve. 

(i) Retained Cleaning for Certain Airplanes 

This paragraph restates the requirements of 

paragraph (i) of AD 2011–07–10, Amendment 

39–16647 (76 FR 17758, March 31, 2011), 

with no changes. For airplanes having S/Ns 

20174, 20175, 20178 through 20189 

inclusive, 20191 through 20228 inclusive, 

20230 through 20232 inclusive, 20235, 

20237, 20238, 20241, 20244, 20247, 20249 

through 20251 inclusive, 20254, 20256 and 

20259: Within 50 flight hours after June 1, 

2010 (the effective date of AD 2010–10–18, 

Amendment 39–16297 (75 FR 27406, May 17, 

2010)), clean the cabin pressure-sensing port 

plug in both safety valves, in accordance 

with Paragraph 2.B., ‘‘Part A—Modification— 

Cleaning,’’ of the Accomplishment 

Instructions of Bombardier Service Bulletin 

A100–21–08, dated June 18, 2009. 

(j) Retained Cleaning for Certain Other 

Airplanes 

This paragraph restates the requirements of 

paragraph (j) of AD 2011–07–10, Amendment 

39–16647 (76 FR 17758, March 31, 2011), 

with no changes. For airplanes having S/Ns 

20003 through 20189 inclusive, 20191 

through 20228 inclusive, 20230 through 

20232 inclusive, 20235, 20237, 20238, 20241, 

20244, 20247, 20249 through 20251 

inclusive, 20254, 20256, and 20259: Within 

50 flight hours after June 1, 2010 (the 

effective date of AD 2010–10–18, 

Amendment 39–16297 (75 FR 27406, May 17, 

2010)), clean the cabin pressure-sensing port 

plug in both safety valves, in accordance 

with Paragraph 2.B., ‘‘Part A—Modification— 

Cleaning,’’ of the Accomplishment 

Instructions of Bombardier Service Bulletin 

A100–21–08, dated June 18, 2009. Repeat the 

cleaning thereafter at intervals not to exceed 

50 flight hours until the actions specified by 

paragraph (k) of this AD are completed. 

(k) Retained Replacement 

This paragraph restates the requirements of 

paragraph (k) of AD 2011–07–10, 

Amendment 39–16647 (76 FR 17758, March 

31, 2011), with no changes. For airplanes 

having S/Ns 20003 through 20189 inclusive, 

20191 through 20228 inclusive, 20230 

through 20232 inclusive, 20235, 20237, 

20238, 20241, 20244, 20247, 20249 through 

20251 inclusive, 20254, 20256, and 20259: 

Within 12 months after May 5, 2011 (the 

effective date of AD 2011–07–10), replace the 

cabin pressure-sensing port plug having part 

number (P/N) 2844–060 in both safety valves 

with a new gridless plug having P/N 2844– 

19 and re-identify the safety valves, in 

accordance with Paragraph 2.C., ‘‘Part B— 

Modification—Replacement,’’ of the 

Accomplishment Instructions of Bombardier 

Service Bulletin A100–21–08, dated June 18, 

2009. Doing the actions in paragraph (k) of 

this AD terminates the repetitive cleanings 

required by paragraph (j) of this AD. 

(l) New Requirement of This AD: Inspection 

and Cleaning 

For airplanes having S/Ns 20003 through 

20123 inclusive, 20126, 20127, 20129 

through 20133 inclusive, 20135 through 

20138 inclusive, 20140 through 20142 

inclusive, 20144, 20145, and 20147: Within 

500 flight hours or 15 months after the 

effective date of this AD, whichever occurs 

first, do a detailed visual inspection of both 

safety valves and the surrounding area for 

foreign material, RTV silicone, 

contamination, foam on the bulkhead 

structure, tape or insulation, and loose 

material, in accordance with the 

Accomplishment Instructions of Bombardier 

Service Bulletin 100–25–21, Revision 02, 

dated July 25, 2013. Do all applicable 

corrective actions before further flight, in 

accordance with the Accomplishment 

Instructions of Bombardier Service Bulletin 

100–25–21, Revision 02, dated July 25, 2013. 

(m) Credit for Previous Actions 

This paragraph provides credit for actions 

required by paragraph (l) of this AD, if those 

actions were performed before the effective 

date of this AD using Bombardier Service 

Bulletin 100–25–21, Revision 01, dated 

February 26, 2013, which is not incorporated 

by reference in this AD. 

(n) Other FAA AD Provisions 

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 New York ACO, send it to 

ATTN: Program Manager, Continuing 

Operational Safety, FAA, New York ACO, 

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. The AMOC approval letter must 

specifically reference 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, New York ACO, ANE–170, 

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. 

(o) Related Information 

(1) Refer to Mandatory Continuing 

Airworthiness Information (MCAI) Canadian 

Airworthiness Directive CF–2010–06R1, 

dated August 8, 2013, for related information. 

mstockstill on DSK4VPTVN1PROD with PROPOSALS

Federal Register / Vol. 80, No. 72 / Wednesday, April 15, 2015 / Proposed Rules 20185 

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–2015–0827. 

(2) For service information identified in 

this AD, contact Bombardier, Inc., 400 CoˆteVertu Road West, Dorval, Que ́bec H4S 1Y9, 

Canada; telephone 514–855–5000; fax 514– 

855–7401; email thd.crj@

aero.bombardier.com; Internet http://

www.bombardier.com. You may view this 

service information at the FAA, Transport 

Airplane Directorate, 1601 Lind Avenue SW., 

Renton, WA. For information on the 

availability of this material at the FAA, call 

425–227–1221. 

Issued in Renton, Washington, on April 6, 

2015. 

John P. Piccola, Jr., 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2015–08463 Filed 4–14–15; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF LABOR 

Occupational Safety and Health 

Administration 

29 CFR 1910, 1926 

[Docket No. OSHA–2014–0018] 

RIN 1218–AC90 

Communication Tower Safety 

AGENCY: Occupational Safety and Health 

Administration (OSHA), Labor. 

ACTION: Request for Information (RFI). 

SUMMARY: OSHA is aware of employee 

safety risks in communication tower 

construction and maintenance activities 

and is requesting information from the 

public on these risks. This RFI requests 

information that will assist the Agency 

in determining what steps, if any, it can 

take to prevent injuries and fatalities 

during tower work. 

DATES: Comments and other information 

must be submitted (postmarked, sent, or 

received) by June 15, 2015. All 

submissions must bear a postmark or 

provide other evidence of the 

submission date. 

ADDRESSES: Submit comments and 

additional materials, identified by 

Docket No. OSHA–2014–0018, using 

any of the following methods: 

Electronically: Submit comments and 

attachments electronically at http://

www.regulations.gov, which is the 

Federal eRulemaking Portal. Follow the 

instructions online for making 

electronic submissions. 

Facsimile: Commenters may fax 

submissions, including attachments, 

that are no longer than 10 pages in 

length to the OSHA Docket Office at 

(202) 693–1648; OSHA does not require 

hard copies of these documents. 

Commenters must submit lengthy 

attachments that supplement these 

documents (e.g., studies, journal 

articles), by the applicable deadline, to 

the OSHA Docket Office, Technical Data 

Center, Room N–2625, U.S. Department 

of Labor, 200 Constitution Avenue NW., 

Washington, DC 20210. These 

attachments must clearly identify the 

commenter’s name, the date of 

submission, the title of this RFI 

(Communication Tower Safety), and the 

docket number (OSHA–2014–0018) so 

the Agency can attach them to the 

appropriate facsimile submission. 

Regular mail, express delivery, hand 

(courier) delivery, or messenger service: 

Submit a copy of comments and any 

additional material (e.g., studies, journal 

articles) to the OSHA Docket Office, 

Docket No. OSHA–2014–0018, 

Technical Data Center, Room N–2625, 

U.S. Department of Labor, 200 

Constitution Avenue NW., Washington, 

DC 20210; telephone (202) 693–2350 

(TTY number: (877) 889–5627). Note 

that security procedures may 

significantly delay the Agency’s receipt 

of comments and other written materials 

sent by regular mail. Contact the OSHA 

Docket Office for information about 

security procedures concerning delivery 

of materials by express delivery, hand 

delivery, or messenger service. The 

hours of operation for the OSHA Docket 

Office are 8:15 a.m.—4:45 p.m., E.T. 

Instructions: All submissions must 

include the Agency’s name (OSHA), the 

title of this RFI (Communication Tower 

Safety), and the docket number (OSHA– 

2014–0018). The Agency places all 

submissions, including any personal 

information provided, in the public 

docket without change; this information 

will be available online at http://

www.regulations.gov. Therefore, the 

Agency cautions commenters about 

submitting materials that they do not 

want made available to the public or 

that contain personal information 

(either about themselves or others) such 

as Social Security numbers, birth dates, 

and medical data. 

Docket: To read or download 

submissions or other material in the 

docket, go to: http://

www.regulations.gov, or to the OSHA 

Docket Office at the address above. 

While the electronic docket at http://

www.regulations.gov lists documents in 

the docket, some information (e.g., 

copyrighted material) is not publicly 

available to read or download through 

this Web site. All submissions, 

including copyrighted material, are 

available for inspection at the OSHA 

Docket Office. Contact the OSHA Docket 

Office for assistance in locating docket 

submissions. 

FOR FURTHER INFORMATION CONTACT: 

Information regarding this Request for 

Information is available from the 

following sources: 

Press inquiries: Contact Frank 

Meilinger, Director, OSHA Office of 

Communications, Room N–3647, U.S. 

Department of Labor, 200 Constitution 

Avenue NW., Washington, DC 20210; 

email: meilinger.francis2@dol.gov; 

telephone: (202) 693–1999. 

General and technical information: 

Contact Erin Patterson or Jessica Douma, 

Office of Construction Standards and 

Guidance, OSHA Directorate of 

Construction, Room N–3468, U.S. 

Department of Labor, 200 Constitution 

Avenue NW., Washington, DC 20210; 

emails: Patterson.Erin@dol.gov or 

Douma.Jessica@dol.gov; telephone: 

(202) 693–2020; fax: (202) 693–1689. 

Copies of this Federal Register 

notice: Electronic copies are available at 

http://www.regulations.gov. This 

Federal Register notice, as well as news 

releases and other relevant information, 

also are available at OSHA’s Web page 

at http://www.osha.gov. 

SUPPLEMENTARY INFORMATION: 

Table of Contents 

I. Exhibits Referenced in This RFI 

II. Background 

A. Introduction 

B. Hazards and Incidents 

C. Training and Certification 

D. Applicable OSHA Standards 

E. Consensus Standards and State 

Standards 

III. Request for Data, Information, and 

Comments 

IV. Authority and Signature 

I. Exhibits Referenced in This RFI 

Documents referenced by OSHA in 

this request for information, other than 

OSHA standards and Federal Register 

notices, are in Docket No. OSHA–2014– 

0018 (Communication Tower Safety). 

The docket is available at http://

www.regulations.gov, the Federal 

eRulemaking Portal. For additional 

information on submitting items to, or 

accessing items in, the docket, please 

refer to the Addresses section of this 

RFI. 

II. Background 

A. Introduction 

Communication towers are tall 

structures that carry antennas for 

wireless, cellular, radio, or broadcast 

television communications. There are 

three common types of communication 

towers: free-standing or lattice towers, 

guyed towers, and monopole towers. 

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