[Federal Register Volume 76, Number 62 (Thursday, March 31, 2011)]
[Rules and Regulations]
[Pages 17758-17761]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2011-7296]
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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;
Amendment 39-16647; AD 2011-07-10]
RIN 2120-AA64
Airworthiness Directives; Bombardier, Inc. Model BD-100-1A10
(Challenger 300) Airplanes
AGENCY: Federal Aviation Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule.
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SUMMARY: We are superseding an existing airworthiness directive (AD)
that applies to the products listed above. This AD results from
mandatory continuing airworthiness information
[[Page 17759]]
(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. We are issuing this AD to require
actions to correct the unsafe condition on these products.
DATES: This AD becomes effective May 5, 2011.
The Director of the Federal Register approved the incorporation by
reference of certain publications listed in this AD as of June 1, 2010
(75 FR 27406, May 17, 2010).
ADDRESSES: You may examine the AD docket on the Internet at http://www.regulations.gov or in person at the U.S. Department of
Transportation, Docket Operations, M-30, West Building Ground Floor,
Room W12-140, 1200 New Jersey Avenue, SE., Washington, DC.
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:
Discussion
We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR
part 39 to include an AD that would apply to the specified products.
That NPRM was published in the Federal Register on December 21, 2010
(75 FR 79984), and proposed to supersede AD 2010-10-18, Amendment 39-
16297 (75 FR 27406, May 17, 2010). That NPRM proposed to correct an
unsafe condition for the specified products. 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.
Comments
We gave the public the opportunity to participate in developing
this AD. We received no comments on the NPRM or on the determination of
the cost to the public.
Conclusion
We reviewed the available data and determined that air safety and
the public interest require adopting the AD as proposed.
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 required different actions in this AD from those
in the MCAI in order to follow our FAA policies. Any such differences
are highlighted in a NOTE within the AD.
Costs of Compliance
We estimate that this AD will affect about 67 products of U.S.
registry.
The actions that are required by AD 2010-10-18 and retained in this
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 will take about 1 work-hour per product to
comply with the new basic requirements of this AD. The average labor
rate is $85 per work-hour. Required parts will 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 this AD to the
U.S. operators to be $5,695, or $85 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 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 AD will not have federalism implications
under
[[Page 17760]]
Executive Order 13132. This AD will 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 AD:
(1) Is not a ``significant regulatory action'' under Executive
Order 12866,
(2) Is not a ``significant rule'' under 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.
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 the 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.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation safety, Incorporation by
reference, Safety.
Adoption of the Amendment
Accordingly, under the authority delegated to me by the
Administrator, the FAA amends 14 CFR part 39 as follows:
PART 39--AIRWORTHINESS DIRECTIVES
0
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]
0
2. The FAA amends Sec. 39.13 by removing Amendment 39-16297 (75 FR
27406, May 17, 2010) and adding the following new AD:
2011-07-10 Bombardier, Inc.: Amendment 39-16647. Docket No. FAA-
2010-1200; Directorate Identifier 2010-NM-136-AD.
Effective Date
(a) This airworthiness directive (AD) becomes effective May 5,
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 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
[[Page 17761]]
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.
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 A100-21-08. June 18, 2009.
Bombardier Service Bulletin 100-25-14.. June 30, 2008.
Bombardier Service Bulletin 100-25-21.. June 30, 2008.
Bombardier Temporary Revision 5-2-53, October 1, 2009.
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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Material Incorporated by Reference
(n) You must use the applicable service information contained in
table 2 of this AD to do the actions required by this AD, unless the
AD specifies otherwise.
Table 2--Material Incorporated by Reference
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Document Date
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Bombardier Service Bulletin A100-21-08. June 18, 2009.
Bombardier Service Bulletin 100-25-14.. June 30, 2008.
Bombardier Service Bulletin 100-25-21.. June 30, 2008.
Bombardier Temporary Revision 5-2-53, October 1, 2009.
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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(1) The Director of the Federal Register previously approved
the incorporation by reference of this service information on June
1, 2010 (75 FR 27406, May 17, 2010).
(2) For service information identified in this 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 [email protected]; Internet http://www.bombardier.com.
(3) You may review copies of the 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.
(4) You may also review copies of the service information that
is incorporated by reference at the National Archives and Records
Administration (NARA). For information on the availability of this
material at NARA, call 202-741-6030, or go to: http://www.archives.gov/federal_register/code_of_federal_regulations/ibr_locations.html.
Issued in Renton, Washington, on March 21, 2011.
Kalene C. Yanamura,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 2011-7296 Filed 3-30-11; 8:45 am]
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