
[Federal Register Volume 75, Number 244 (Tuesday, December 21, 2010)]
[Proposed Rules]
[Pages 79984-79988]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 2010-31972]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2010-1200; Directorate Identifier 2010-NM-136-AD]
RIN 2120-AA64


Airworthiness Directives; Bombardier, Inc. Model BD-100-1A10 
(Challenger 300) Airplanes

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Notice of proposed rulemaking (NPRM).

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SUMMARY: We propose to adopt a new airworthiness directive (AD) for the 
products listed above that would supersede an existing AD. 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:

    Investigation of a recent high altitude loss of cabin 
pressurization on a BD-100-1A10 aircraft 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 unsafe condition is possible loss of cabin pressure caused by the 
opening of the safety valve. 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 February 4, 
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 W12-40, 1200 New 
Jersey

[[Page 79985]]

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 C[ocirc]te-Vertu Road West, Dorval, Qu[eacute]bec 
H4S 1Y9, Canada; telephone 514-855-5000; fax 514-855-7401; e-mail 
thd.crj@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 (ACO), 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-2010-1200; 
Directorate Identifier 2010-NM-136-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 May 3, 2010, we issued AD 2010-10-18, Amendment 39-16297 (75 FR 
27406, May 17, 2010). That AD required actions intended to address an 
unsafe condition on the products listed above.
    In Note 2 of AD 2010-10-18, we explained that the AD did not 
mandate replacement of the cabin pressure-sensing port plug in both 
safety valves, with a new gridless plug and that we were considering 
further rulemaking. We now have determined that further rulemaking is 
necessary and this NPRM follows from that determination. The MCAI 
states:

    Investigation of a recent high altitude loss of cabin 
pressurization on a BD-100-1A10 aircraft 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.
    This directive mandates a revision of the maintenance schedule, 
the [repetitive] 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.

The unsafe condition is possible loss of cabin pressure caused by the 
opening of the safety valve. The required actions also include 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 for contamination found 
in the safety valve pressure ports. If contamination is found on the 
safety valve pressure ports, a detailed visual inspection for the 
presence of RTV on the outside and inside diameter of the pressure 
sensing port conduit is required. If discrepant materials are found, 
removing discrepant material, cleaning the surfaces of the valves, and 
securing insulation are required, as applicable. If the presence of RTV 
is detected, cleaning the surfaces of the valves and installing a new 
safety valve are required, as applicable. You may obtain further 
information by examining the MCAI in the AD docket.

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 67 products of U.S. registry.
    The actions that are required by AD 2010-10-18 and retained in this 
proposed AD take about 9 work-hours per product, at an average labor 
rate of $85 per work hour. Required parts cost about $0 per product. 
Based on these figures, the estimated cost of the currently required 
actions is $765 per product.
    We estimate that it would take about 1 work-hour per product to 
comply with the new 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 costs. 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 $5,695, or $85 per product.

[[Page 79986]]

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); 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.


Sec.  39.13  [Amended]

    2. The FAA amends Sec.  39.13 by removing Amendment 39-16297 (75 FR 
27406, May 17, 2010) and adding the following new AD:

Bombardier, Inc.: Docket No. FAA-2010-1200; Directorate Identifier 
2010-NM-136-AD.

Comments Due Date

    (a) We must receive comments by February 4, 2011.

Affected ADs

    (b) This AD supersedes AD 2010-10-18, Amendment 39-16297.

Applicability

    (c) This AD applies to Bombardier, Inc. Model BD-100-1A10 
(Challenger 300) airplanes, having serial numbers (S/Ns) 20001 
through 20274 inclusive, certificated in any category.

    Note 1: This AD requires revisions to certain operator 
maintenance documents to include new inspections. Compliance with 
these inspections is required by 14 CFR 91.403(c). For airplanes 
that have been previously modified, altered, or repaired in the 
areas addressed by these inspections, the operator may not be able 
to accomplish the inspections 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 (l) 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.

Subject

    (d) Air Transport Association (ATA) of America Code 21: Air 
conditioning.

Reason

    (e) The mandatory continuing airworthiness information (MCAI) 
states:

    Investigation of a recent high altitude loss of cabin 
pressurization on a BD-100-1A10 aircraft 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 unsafe condition is possible loss of cabin pressure caused by 
the opening of the safety valve.

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.

Restatement of Requirements of AD 2010-10-18, With No New Service 
Information

Actions

    (g) For all airplanes: Within 30 days after June 1, 2010 (the 
effective date of AD 2010-10-18, Amendment 39-16297) 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 ``Phase-in'' 
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. Thereafter, except as provided by 
paragraph (l)(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) For airplanes having S/Ns 20003 through 20173 inclusive, 
20176, and 20177: Within 50 flight hours after June 1, 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 to 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 to 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 to 20173 inclusive, 20176, and 20177); or 
Bombardier Service

[[Page 79987]]

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 to 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 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 to 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 to 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) 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, 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) 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, 
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.

New Requirements of This AD

    (k) 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 the effective date 
of this AD, 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.

FAA AD Differences

    Note 2: This AD differs from the MCAI and/or service information 
as follows: No differences.

Other FAA AD Provisions

    (l) The following provisions also apply to this AD:
    (1) Alternative Methods of Compliance (AMOCs): The Manager, New 
York Aircraft Certification Office, ANE-170, FAA, has the authority 
to approve AMOCs for this AD, if requested using the procedures 
found in 14 CFR 39.19. Send information 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 on any airplane to 
which the AMOC applies, notify your principal maintenance inspector 
(PMI) or principal avionics inspector (PAI), as appropriate, or 
lacking a principal inspector, your local Flight Standards 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.
    (3) Reporting Requirements: A Federal agency may not conduct or 
sponsor, and a person is not required to respond to, nor shall a 
person be subject to a penalty for failure to comply with a 
collection of information subject to the requirements of the 
Paperwork Reduction Act unless that collection of information 
displays a current valid OMB Control Number. The OMB Control Number 
for this information collection is 2120-0056. Public reporting for 
this collection of information is estimated to be approximately 5 
minutes per response, including the time for reviewing instructions, 
completing and reviewing the collection of information. All 
responses to this collection of information are mandatory. Comments 
concerning the accuracy of this burden and suggestions for reducing 
the burden should be directed to the FAA at: 800 Independence Ave., 
SW., Washington, DC 20591, Attn: Information Collection Clearance 
Officer, AES-200.

Related Information

    (m) Refer to MCAI Canadian Airworthiness Directive CF-2010-06, 
dated February 24, 2010; and the service information specified in 
Table 1 of this AD; as applicable; for related information.

                      Table 1--Service information
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              Document                               Date
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Bombardier Service Bulletin A100-21-  June 18, 2009.
 08.
Bombardier Service Bulletin 100-25-   June 30, 2008.
 14.
Bombardier Service Bulletin 100-25-   June 30, 2008.
 21.
Bombardier Temporary Revision 5-2-    October 1, 2009.
 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.
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    Issued in Renton, Washington, on December 14, 2010.
Ali Bahrami,
Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 2010-31972 Filed 12-20-10; 8:45 am]
BILLING CODE 4910-13-P


