[Federal Register Volume 76, Number 110 (Wednesday, June 8, 2011)]
[Proposed Rules]
[Pages 33173-33176]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2011-14091]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2011-0479; Directorate Identifier 2010-NM-154-AD]
RIN 2120-AA64


Airworthiness Directives; Bombardier Inc. Model DHC-8-102, -103, 
-106, -201, -202, -301, -311, and -315 Airplanes; Equipped With Certain 
Cockpit Door Installations

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:

    During structural testing of the cockpit door, it was observed 
that the door lower hinge block rotated which resulted in 
disengagement of the mating hinge pin and excessive door deflection. 
The lower hinge block rotated because it was attached to its support 
structure with only one attachment bolt, which prevented it from 
reacting to any moment force. This condition, if not corrected could 
result in breakage and uncontrolled release of the cockpit door 
under certain decompression situations.
    After incorporation of Modsum 8Q900267 * * *, an operator 
reported a failure to complete the cockpit door removal function 
test. This condition, if not corrected, could result in the 
inability to remove the cockpit door for emergency egress. * * *

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 July 25, 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

[[Page 33174]]

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 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 [email protected]; 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: Andreas Rambalakos, 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) 228-7345; 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-2011-0479; 
Directorate Identifier 2010-NM-154-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 June 5, 2006, we issued AD 2006-12-16, Amendment 39-14642 (71 FR 
34006, June 13, 2006). That AD required actions intended to address an 
unsafe condition on the products listed above.
    Since we issued AD 2006-12-16, an operator reported a failure to 
complete the cockpit door removal function test. This condition, if not 
corrected, could result in the inability to remove the cockpit door for 
emergency egress. The Transport Canada Civil Aviation (TCCA), which is 
the aviation authority for Canada, has issued Canadian Airworthiness 
Directive CF-2005-34R1, dated August 15, 2007 (referred to after this 
as ``the MCAI''), to correct an unsafe condition for the specified 
products. The MCAI states:

    During structural testing of the cockpit door, it was observed 
that the door lower hinge block rotated which resulted in 
disengagement of the mating hinge pin and excessive door deflection. 
The lower hinge block rotated because it was attached to its support 
structure with only one attachment bolt, which prevented it from 
reacting to any moment force. This condition, if not corrected could 
result in breakage and uncontrolled release of the cockpit door 
under certain decompression situations.
    After incorporation of Modsum 8Q900267 * * *, an operator 
reported a failure to complete the cockpit door removal function 
test. This condition, if not corrected, could result in the 
inability to remove the cockpit door for emergency egress. 
Therefore, * * * this [Canadian] directive is issued to require 
rework of the cockpit door striker plate and replacement of the 
latch block for the affected aircraft serial numbers. * * *

You may obtain further information by examining the MCAI in the AD 
docket.

Relevant Service Information

    Bombardier Inc. has issued Service Bulletins 8-52-58, Revision A, 
dated November 17, 2006; and 8-52-61, dated October 20, 2006. The 
actions described in this service information are intended to correct 
the unsafe condition identified in the MCAI.

Change to Table 3 of the Existing AD

    We have revised Table 3 of the existing AD to remove reference to 
Bombardier Series 100/300 Modification Summary (Modsums) 8Q200015, 
8Q420101, and 8Q420143 in the column labeled ``One approved method for 
doing these actions.'' However, we have approved De Havilland Aircraft 
of Canada, Limited, Modification 8/2337 as an additional source of 
guidance for reworking the cockpit door emergency release. We have 
approved De Havilland Aircraft of Canada, Limited, Modification 8/3339 
as an additional source of guidance for installing a new label 
regarding the alternate release of the door. We have also approved 
Bombardier Series 100/300 Modsum 8Q200015 as an additional source of 
guidance for installing the cockpit door. Operators may contact the 
Manager, New York Aircraft Certification Office, ANE-170, for 
information regarding the use of Bombardier Series 100/300 Modsum 
8Q200015 for installing the cockpit door, as required by paragraph (h) 
of this AD. We have not included Bombardier Series 100/300 Modsums 
8Q420101 and 8Q420143 in this AD because they are optional 
installations of the emergency locator transmitter and blow-out panel 
on the cockpit door and were done during production.

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 17 products of U.S. registry.
    The actions that are required by AD 2006-12-16 and retained in this 
proposed AD take between 3 and 6 work-hours per product, depending on

[[Page 33175]]

the airplane configuration, at an average labor rate of $85 per work 
hour. Required parts cost about $2,000 per product. Based on these 
figures, the estimated cost of the currently required actions is 
between $2,255 and $2,510 per product.
    We estimate that it would take about 3 work-hours 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 $2,000 
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 $38,335, or $2,255 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 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 39-14642 (71 FR 
34006, June 13, 2006) and adding the following new AD:

Bombardier Inc.: Docket No. FAA-2011-0479; Directorate Identifier 
2010-NM-154-AD.

Comments Due Date

    (a) We must receive comments by July 25, 2011.

Affected ADs

    (b) This AD supersedes AD 2006-12-16, Amendment 39-14642.

Applicability

    (c) This AD applies to Bombardier Model DHC-8-102, -103, -106, -
201, -202, -301, -311, and -315 airplanes, certificated in any 
category; serial numbers (S/Ns) 003 through 557 inclusive; equipped 
with cockpit door installation part numbers (P/Ns) identified in 
Table 1 of this AD.

         Table 1--Cockpit Door Installations Affected by This AD
------------------------------------------------------------------------
                  P/N                             Dash number(s)
------------------------------------------------------------------------
82510074...............................  All
82510294...............................  All
82510310...............................  -001
8Z4597.................................  -001
H85250010..............................  All
82510700...............................  All
82510704...............................  All except -502 and -503
------------------------------------------------------------------------

Subject

    (d) Air Transport Association (ATA) of America Code 52: Doors.

Reason

    (e) The mandatory continuing airworthiness information (MCAI) 
states:
    During structural testing of the cockpit door, it was observed 
that the door lower hinge block rotated which resulted in 
disengagement of the mating hinge pin and excessive door deflection. 
The lower hinge block rotated because it was attached to its support 
structure with only one attachment bolt, which prevented it from 
reacting to any moment force. This condition, if not corrected could 
result in breakage and uncontrolled release of the cockpit door 
under certain decompression situations.
    After incorporation of Modsum 8Q900267 * * * an operator 
reported a failure to complete the cockpit door removal function 
test. This condition, if not corrected, could result in the 
inability to remove the cockpit door for emergency egress. * * *

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 2006-12-16, With New Service 
Information

Modification

    (g) Within 24 months after July 18, 2006 (the effective date of 
AD 2006-12-16), modify the cockpit door from a single-point 
attachment to a two-point attachment in accordance with the 
Accomplishment Instructions of the applicable service bulletin in 
Table 2 of this AD. For airplane serial numbers 452, 464, 490, 506, 
and 508 through 557 inclusive: After the effective date of this AD, 
use Bombardier Service Bulletin 8-52-58, Revision A, dated November 
17, 2006.

   Table 2--Bombardier Service Bulletins for Modification Required by
                        Paragraph (g) of this AD
------------------------------------------------------------------------
 Use this Bombardier Service Bulletin--   For airplane serial numbers--
------------------------------------------------------------------------
8-52-54, Revision A, dated November 5,   003 through 451 inclusive, 453
 2004.                                    through 463 inclusive, 465
                                          through 489 inclusive, 491
                                          through 505 inclusive, and
                                          507.
8-52-58, dated May 12, 2004, or          452, 464, 490, 506, and 508
 Revision A, dated November 17, 2006.     through 557 inclusive.
------------------------------------------------------------------------



[[Page 33176]]

    Note 1:  Bombardier Service Bulletin 8-52-54 refers to 
Bombardier Series 100/300 Modification Summary (Modsum) 8Q100859 as 
an additional source of guidance for installing a hinge pin with a 
two-point attachment. Bombardier Service Bulletin 8-52-58 refers to 
Bombardier Series 100/300 Modsum 8Q900267 as an additional source of 
guidance for reworking and installing the cockpit door, and 
reworking the lower hinge attachment to provide a downward-facing 
pin with a two-point attachment.

Prior/Concurrent Requirements

    (h) Prior to or concurrently with the modification in paragraph 
(g) of this AD, do the applicable actions specified in Table 3 of 
this AD, according to a method approved by either the Manager, New 
York Aircraft Certification (ACO), FAA; or Transport Canada Civil 
Aviation (TCCA) (or its delegated agent).

 Table 3--Bombardier Service Bulletins for Requirements of Paragraph (h)
                               of This AD
------------------------------------------------------------------------
  For airplanes affected by
Bombardier Service Bulletin--    That have these     Do these actions--
                                serial numbers--
------------------------------------------------------------------------
8-52-54, Revision A, dated    003 through 407       Rework the cockpit
 November 5, 2004.             inclusive, 409        door emergency
                               through 412           release.
                               inclusive, and 414
                               through 433
                               inclusive.
                              ....................  Install a new label
                                                     regarding alternate
                                                     release of the
                                                     door.
8-52-58, dated May 12, 2004.  452, 464, 490, 506,   Install the cockpit
                               and 508 through 557   door.
                               inclusive.
------------------------------------------------------------------------


    Note 2: Bombardier Service Bulletin 8-52-54, Revision A, dated 
November 5, 2004, refers to De Havilland Aircraft of Canada, 
Limited, Modification 8/2337 as an additional source of guidance for 
reworking the cockpit door emergency release; and Modification 8/
3339 as additional source of guidance for installing a new label 
regarding alternate release of the door, on airplanes having serial 
numbers 003 through 407 inclusive, 409 through 412 inclusive, and 
414 through 433 inclusive.


    Note 3:  Bombardier Service Bulletin 8-52-58, dated May 12, 
2004; and Revision A, dated November 17, 2006; refer to Bombardier 
Modsum 8Q200015, as an additional source of guidance for installing 
the cockpit door, on airplanes having serial numbers 452, 464, 490, 
506, and 508 through 557 inclusive.

Actions Done In Accordance With Previous Revision of Service 
Bulletin

    (i) Actions done before July 18, 2006, in accordance with 
Bombardier Service Bulletin 8-52-54, dated May 12, 2004, are 
acceptable for compliance with the corresponding requirements in 
paragraph (g) of this AD.

New Requirements of This AD

    (j) For airplanes having S/N 452, 464, 490, 506, and 508 through 
557 inclusive, and on which the requirements in paragraph (g) of 
this AD have been done as of the effective date of this AD: Within 
12 months after the effective date of this AD rework the cockpit 
door striker plate and replace the latch block, in accordance with 
the Accomplishment Instructions of Bombardier Service Bulletin 8-52-
61, dated October 20, 2006.
    (k) For airplanes having S/Ns 452, 464, 490, 506, and 508 
through 557 inclusive, and on which the requirements in paragraph 
(g) of this AD have not been done as of the effective date of this 
AD: Prior to or concurrently with doing the modification required in 
paragraph (g) of this AD, rework the cockpit door striker plate and 
replace the latch block, in accordance with the Accomplishment 
Instructions of Bombardier Service Bulletin 8-52-61, dated October 
20, 2006.

FAA AD Differences

    Note 4:  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. 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

    (m) Refer to MCAI Canadian Airworthiness Directive CF-2005-34R1, 
dated August 15, 2007; Bombardier Service Bulletin 8-52-54, Revision 
A, dated November 5, 2004; Bombardier Service Bulletin 8-52-58, 
Revision A, dated November 17, 2006; and Bombardier Service Bulletin 
8-52-61, dated October 20, 2006; for related information.

    Issued in Renton, Washington, on May 27, 2011.
Ali Bahrami,
Manager, Transport Airplane Directorate, Aircraft Certification 
Service.

[FR Doc. 2011-14091 Filed 6-7-11; 8:45 am]
BILLING CODE 4910-13-P